20060512000282006051200028CE 2006 5 12 000 120060331G321351410051 BOLT CESSNA CESSNA421 421A 2076012CE CONT O520 GTSIO520* 17032SO RT MLG DEPARTED P K NONE O OTHER TXTAXI/GRND HDL 1 SO19849JB2000 2000 NA 421A0075 WHILE TAXING TO PARK THE RT MLG LINK ASSEMBLY BOLT CAME OUT CAUSING THE UPPER AND LOWER LINKS TO SEPERATE. THE RT LANDING GEAR TURNED 90 DEGREES BENDING THE GEAR DOOR COVER. 1L72 3O3 O A7CE E7CE 20060608004422006060800442GL 2006 6 8 000000002 120060530G32222032200800 FORK DIAMON DIAMONDA20 DA20C1 2990001GL NOSE WHEEL CRACKED D K NONE O OTHER ININSP/MAINT 1 GL09857PA1544 C0218 DISCOVERED 8 CRACKS, 4 PER SIDE APPROXIMATELY 1 INCH FORWARD OF NOSE GEAR AXLE ADJACENT TO FAIRING ATTACH POINT HOLES. 1L71 3O NTTA4CH 20060613001962006061300196GL 2006 6 13 0079965A 320060404G6114E71693 HUB BEECH 58 58P 1152744CE HARTZLHCJ3Y PHCJ3YF2 GL PROPELLER CORRODED B K NONE O OTHER ININSP/MAINT 1 SW99 PROPELLER HUB HAS INTERNAL AND EXTERNAL CORROSION 1L72 3O A23CE 5 CP36EA 20070613001612007061300161NE 2007 6 13 0089756 320060203G611194LMA4 BLADE CESSNA425 425 2076018CE MCAULY4HFR344HFR34C762 NE PROPELLER CORRODED B EY2RK NONE O OTHER ININSP/MAINT 1 GL03 951649 CORROSION IN BLADE SHANK, NOT REPAIRABLE. 1L72 3T RTA7CE 6 C3PNE 20070613001602007061300160GL 2007 6 13 0093855 320061103G6114D2011 HUB HARTZL BEECH 58 58 1152740CE HARTZLHCC2Y BHCC2YF2 GL PROPELLER CORRODED B EY2RK NONE O OTHER ININSP/MAINT 1 GL03 AN737 HUB CORRODED BEYOND SPEC. 1L72 3O 3A16 5 CP920 20060627003322006062700332CE 2006 6 27 01676201 120060621G3213NAS464414 BOLT CESSNA CESSNA421 421A 2076012CE ZONE 700 FAILED B DYCRE ENGINE SHUTDOWN G MULTIPLE FAILURE TXTAXI/GRND HDL 1 GL07216WA3463 421A0032 LANDING GEAR COLLAPSED DURING ROLLOUT AFTER LANDING. UPON INSPECTION IT WAS NOTED THAT A BOLT CONNECTING THE DOWNLOCK BELLCRANK TO THE UPPER STRUT ASSEMBLY HAD FAILED. THE BOLT HEAD WAS MISSING ALLOWING ALL OF THE FORCE FROM THE BELLCRANK TO BE APPLIED DIRECTLY AND ENTIRELY TO THE FORWARD ATTACH LUG ON THE UPPER STRUT CAUSING THE LUG TO BREAK AND THE GEAR TO COLLAPSE. MAINTENANCE RECOMMENDS TIME CHANGE ON BOLT AND AN NDT INSPECTION OF LUGS AND SURROUNDING AREA AT THE SAME TIME. 1L72 3O A7CE 20060512000382006051200038SO 2006 5 12 0600710 120060331G781089366003 EXHAUST RISER PIPER PA44 PA44180 7104402SO LYC O360 LO360E1A6 41514EA HARTZLHCC3Y HCC3Y* GL RT ENGINE BROKEN B BF8XA UNSCHED LANDING ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CRCRUISE 1 WP07572ER2449 4496148 L74571A AU10894B PILOT'S REPORTED VIBRATION IN RT ENGINE, ALSO STATED SOMETHING SEEMED LOOSE AND RATTLING. LEANED AT DIFFERENT POWER SETTINGS WHILE IN FLIGHT WITH NO CHANGES. RETURNED TO AIRPORT WITHOUT INCIDENT. UNCOWLED RT ENGINE AND FOUND NR 2 CYLINDER EXHAUST RISER BROKEN OFF AT MOUNT FLANGE. REPLACED WITH NEW RISER AND GASKET, OPERATIONAL CHECK GOOD. 1L72 3O3 O A19S0 E286 5 CP25EA 20060913002352006091300235NM 2006 9 13 060602 120060909G531013017R RIB UNIVAR415 415C 0420302NM CENTER SECTION CORRODED D O OTHER O OTHER NRNOT REPORTED 1 SW1599325 1948 THE DEFECT WAS DISCOVERED DURING THE INITIAL COMPLIANCE WITH AD 2002-26-02 ON AN AIRCRAFT THAT HAD BEEN IN STORAGE FOR A NUMBER OF YEARS. AN APPROXIMATE 0.5 INCH BY 0.25 INCH AREA AT THE BOTTOM EDGE OF A LIGHTENING HOLE WAS CORRODED AND FLAKING. A COLLECTION OF NUT SHELLS AND DEBRIS WERE FOUND NEARBY, INDICATING THAT THE CORROSION WAS PROBABLY STARTED DUE TO THE PRESENCE OF ANIMAL WASTE PRODUCTS AND THE BLOCKAGE OF DRAINAGE PATHS. STORAGE IN A RODENT-CONTROLLED AREA, COMBINED WITH PERIODIC USE OF INSPECTION HOLES (WHICH WERE INSTALLED TO COMPLY WITH THE AFOREMENTIONED AD) TO APPLY CLEANING FLUIDS AND CORROSION PREVENTIVE COMPOUND SHOULD HELP PREVENT FUTURE RECURRENCE. 1L71 3O A718 20060718001632006071800163CE 2006 7 18 071106KTR 120060410G3210AN501A105 SCREW BEECH MU300 400A 1155402CE LANDING GEAR SHEARED B NV2RO OTHER O OTHER NRNOT REPORTED 1 CE07 UPON REMOVAL OF THE PLUNGER TUBE ASSEMBLY FROM THE LANDING GEAR CYLINDER, FOUND THE2 AN501A10-5 SCREWS THAT SECURE THE PLUNGER TUBE HEAD TO THE PLUNGER TUBE HAD SHEARED. THE CONDITION RESULTED IN LOOSE PARTS, WHICH CAUSED ONLY MINIMAL INTERNAL STRUT DAMAGE, AND AFFECTED THE SHOCK CHARACTERISTICS OF THE AFFECTED LANDING GEAR STUT. 2H72 4F RTA16SW 20060814001462006081400146CE 2006 8 14 080106 120060801G29101015802181 TUBE BEECH 200 B200 1152922CE HYD SYSTEM DAMAGED B K NONE K FLUID LOSS ININSP/MAINT 1 CE016300F538 BB1865 DURING ROUTINE INSPECTION IT WAS DISCOVERED THAT THE PILOT SIDE RUDDER CABLE HAD BEEN RUBBING ON THE PILOTS SIDE RT BRAKE TUBE ASSY P/N 101-580218-1 NEAR THE FORWARD END OF THE TUBE ASSY CAUSING IT TO BECOME NOTCHED. THE DAMAGE IS TO THE EXTENT THAT REPLACEMENT WAS REQUIRED. THIS DAMAGE WAS FOUND UNDER THE PILOTS SEAT FLOOR INSPECTION PANEL ADJACENT TO THE BUSS FEEDER DIODE ASSY. THE CAUSE APPEARS TO BE IMPROPER TUBE ASSY ROUTING BY NOT ALLOWING FOR PROPER CONTROL CABLE CLEARANCE. RECOMMEND INSPECTION OF THE AFFECTED AREA AND REROUTING AND OR REPLACEMENT OF BRAKE TUBE ASSY. 1L72 4T A24CE 20060825000272006082500027GL 2006 8 25 0823061 320060823G6114D2A34C98NO HUB MCAULY D2A34C98NO MCAULY2A34C D2A34C98 GL PROPELLER CRACKED B O OTHER O OTHER NRNOT REPORTED 1 SO17F-GAP 739321 739321 CRACKED IN BLADE SOCKET. 5 CP3EA 20060614001882006061400188CE 2006 6 14 0MKR20064 120060525G551145A21104641 RIB BEECH BEECH MU300 400A 1155402CE HORIZ STAB CRACKED B OMKRK NONE O OTHER ININSP/MAINT 1 NM03793TA RK224 RK244 LT IB ROLLER SUPPORT RIB FOUND CRACKED. P/N 45A21104-641 WAS REMOVED AND REPLACED WITH NEW. DUE TO THE NUMBER OF THESE WE ARE SEEING, IT IS LIKELY THE ENTIRE 400A FLEET HAS A PROBLEM IN THIS AREA. 2H72 4F RTA16SW 20060123002282006012300228CE 2006 1 23 1054822 120060110G5341 FRAME LEAR 35 35LEAR 5170600CE GARRTTTFE731TFE73122B 01518WP WING ROOT CRACKED B WTXRK NONE O OTHER ININSP/MAINT 1 NM074358N 35065 74505 FOUND CRACKS ON THE FUSELAGE SIDE OF FRAME 20 ON BOTH LT AND RT SIDE. FRAME 20 IS THE WING ATTACH POINT. ON THE LT SIDE THE LENGTH OF THE CRACK WAS 1.25 INCH IN LENGTH AND ON THE RT SIDE, 1.50 INCH. 2L72 4F4 F A10CE E6WE 20060123002292006012300229CE 2006 1 23 10548226 120060110G5341 FRAME LEAR 35 35LEAR 5170600CE GARRTTTFE731TFE73122B 01518WP WING ROOT CRACKED B WTXRK NONE O OTHER ININSP/MAINT 1 NM074358N 35065 74505 FOUND CRACKS ON THE FUSELAGE SIDE OF FRAME 20 ON BOTH LT AND RT SIDE. FRAME 20 IS THE WING ATTACH POINT. ON THE LT SIDE THE LENGTH OF THE CRACK WAS 1.25 INCH IN LENGTH AND ON THE RT SIDE, 1.5 INCH. 2L72 4F4 F A10CE E6WE 20060214002142006021400214SO 2006 2 14 10943282 120060120G5310 FRAME MAULE M5 M5210C 5460134SO CONT IO360 IO360* 17025CE FUSELAGE CRACKED B WTXRK NONE O OTHER ININSP/MAINT 1 NM03314X 6134C FOUND CRACK APPROXIMATELY .3750 INCH IN LENGTH ON RT FRAME 20 WING ATTACH POINT. 1H71 3O3 O 3A23 E1CE 20060323000572006032300057CE 2006 3 23 11143 120060223G5341251120015 FITTING LEAR 35 35A 5170602CE GARRTTTFE731TFE73122B 01518WP FUSELAGE CRACKED C K NONE O OTHER ININSP/MAINT 1 NM0781FR 081 LT AND RT WING ATTACH POINT FITTING AT FRAME 20 IS CRACKED. LT IS CRACKED APPROX. 1.0 INCHES IN LENGTH. RT IS CRACKED APPROX. 1.25 INCHES IN LENGTH. 2L72 4F4 F A10CE E6WE 20060518002532006051800253CE 2006 5 18 11221 120060414G5311 FRAME LEAR 35 35A 5170602CE FUSELAGE CRACKED E WTXRK NONE O OTHER UKUNKNOWN 1 NM0798LC 077 RH FUSELAGE FRAME 20 CRACKED APPROX. 11/8 IN LENGTH AT THE AFT WING ATTACH POINT. 2L72 4F A10CE 20061018000602006101800060CE 2006 10 18 1538T092806 120060928G2120CM321110B335 DUCT CESSNA421 421B 2076014CE RIGHT BLOWN D O OTHER O OTHER CRCRUISE 1 GL111538T1764 176 421B0308 CABIN BEGAN TO CLIMB AT 2000 FPM DURING CRUISE AT 12,500 FT. DESCENT TO 10,500 FT. CABIN WOULD ONLY MAINTAIN 2.5 PSID. CHECKED OUTFLOW AND SAFETY VALVES, MOISTURE DRAINS, LANDING GEAR BOOTS, FAILEADS ALL FOUND OK. PERFORM GROUND CHECK OF SYSTEM FOUND NO AUDIBLE LEAKS ELSEWHERE IN CABIN AND DIFFERENTIAL CHECKED OK. PERFORMED SECOND GROUND CHECK AND PULLED CABIN AIR VALVES ONE AT A TIME ISOLATED PROBLEM TO RIGHT SOURCE. FOUND DUCT PARTIALLY BLOWN OFF OF SONIC VENTURI. REMOVED DUCT AND FOUND .7500 INCH TEAR WHERE IT PASSES THROUGH WING RIB. MFG NO LONGER STOCKS A 33.5 DUCT, ONLY 38 INCH. -38 CUT DOWN IN THE FIELD AND INSTALLED BOTH WINGS. LT DUCTING REPLACED MARCH 2006. RT DUCTING WAS FOUND AIRWORTHY AT T1L72 3O A7CE 20060725001842006072500184CE 2006 7 25 15462006H1 120060710G80106041H190 RELAY BEECH 200 A200 1152921CE NR 2 STARTER BURNED D O OTHER O OTHER NRNOT REPORTED 1 SW991546 BC58 NR 2 START RELAY SHORTED TO GROUND DURING ENGINE START, APPARENTLY DUE TO WATER INCURSION OR CONTACT CORROSION. RELAY BURNED BUT START WAS SECURED BEFORE ADJACENT WIRE BUNDLE WAS DAMAGED. RELAY REPLACED. NEW RELAYS APPEAR TO HAVE ADDITIONAL SEALANT TO PREVENT THIS PROBLEM. MAY BE RELATED TO CORROSIVE ATMOSPHERE AS 2 OTHER IDENTICAL AIRCRAFT HAVE HAD SIMILAR FAILURES CAUSING MORE SEVERE DAMAGE AT THIS SITE. 1L72 4T A24CE 20060512001482006051200148EU 2006 5 12 1MAC06 120060410G2731T700A2740085002 CABLE SOCATATBM TBM700 8682000EU PWA PT6 PT6A64 EA HARTZLHCE4N HCE4N3 NE ELEV TRIM SYS FRAYED B K NONE O OTHER ININSP/MAINT 1 GL11930MA201 100 340 PM0222 HH2276 FRAYED ELEVATOR TRIM CABLE FOUND DURING 100 HR INSPECTION IN AFT FUSELAGE ACCESS PANEL. 1L71 3T4 TRTA60EU E4EA 5 CP10NE 20060518002452006051800245NM 2006 5 18 200600005 120060427G57309006031 PANEL LKHEEDP3A P3A 5260103NM LT WING CRACKED B AUCRK NONE O OTHER ININSP/MAINT 1 WP25925AU16997 151361 NR 2 FUEL CELL LOWER WING SKIN, PLANK NR 2 CRACKED RISER. NO SRM STANDARD REPAIR FOR THIS DAMAGE. REPAIR WILL BE ACCOMPLISHED IAW EO 462557001. 2L74 4T RTA32NM 20060921001242006092100124WP 2006 9 21 200600077 120060919G273078213008 HINGE FRCHLDC82 C82ASTWDAVIS3372004WP PWA R2800 R2800* 52026NE ZONE 300 FRACTURED B KGBRK NONE O OTHER ININSP/MAINT 1 NM049701F 4557814 LT AND RT FURTHEST OB ELEVATOR HINGE BRACKET ON THE STABILIZER WERE BROKEN. IT APPEARS TO BE FROM WIND GUSTS. THE CENTER 3 HINGES WERE UNAFFECTED. 2H73 4R4 RJ AR15 5E8 20060518002542006051800254EU 2006 5 18 20060502D 120060502G5313 LONGERON LET L23 L23 1360308EU REAR COCKPIT CRACKED B PF5RK NONE O OTHER ININSP/MAINT 1 NM03420BA 029007 FIRST LONGERON (N434BA) WAS FOUND CRACKED AT THE ELEVATOR TRIM GUIDE ATTACH POINT, NEAR THE RCP LT RUDDER PEDAL, DURING A SCHEDULED INSPECTION. SUBSEQUENT FINDINGS OCCURRED AS RESULT OF QUALITY DEPARTMENT ISSUING A ONE TIME INSPECTION OF ALL MDS. IT LOOKS AS IF THE OPERATOR, IN THE REAR COCKPIT (RCP), MAY BE STRIKING THE ELEVATOR TRIM GUIDE WITH HIS/HER FOOT WHILE ACTUATING THE RUDDER PEDAL, CAUSING THE SUPPORT STRUCTURE (LONGERON) TO WEAKEN AND FORM CRACKS AT THE ATTACH SCREWS. 1K00 RCG24EU 20060411000352006041100035SO 2006 4 11 2006ADP001 220060224G8530655470A3 CYLINDER CESSNA206 TU206G 2073357CE CONT O520 TSIO520M 17040SO ENGINE CRACKED D K NONE O OTHER ININSP/MAINT 1 WP21 301 U20606365 532260 ALL SIX CYLINDERS HAVE CRACKS IN THE SAME AREA JUST ABOVE THE TOP SPARK PLUG HOLE. 1H71 3O3 O A4CE E8CE 20060815000122006081500012 2006 8 15 2006ADP08001 420060804G2300 ELEC CONNECTOR DIAMONDA40 DA40 2990002GL SHORTED B A UNSCHED LANDING O OTHER CRCRUISE 1 CE0538CF 40567 ADJACENT MIC AND PHONE JACKS SHORTED TOGETHER CAUSING SQUEAL IN AUDIO SYSTEM. 1L71 3O NTA47CE 20060926000312006092600031SO 2006 9 26 2006ADP09001 220060901G7497108326841 WIRE HARNESS CESSNA206 TU206G 2073357CE CONT O520 TSIO520M 17040SO IGNITION SYS CRACKED D K NONE O OTHER ININSP/MAINT 1 NM08PKMAR94 94 U20606231 532296 DURING INSPECTION ON A NEW, LOW TIME ENGINE, THE MT NOTICED A RATHER LARGE CRACK IN THE RT IGNITION HARNESS COVER, WHERE THE HARNESS ATTACHES TO THE MAGNETO. AFTER LOOKING A LITTLE CLOSER, IT IS CLEAR THAT THE CRACK WAS THERE PRIOR TO OVERHAUL AND PAINTING. THIS HARNESS WAS SUPPLIED WITH THE NEW ENGINE NOTED BELOW. 1H71 3O3 O A4CE E8CE 20060411000392006041100039NE 2006 4 11 2006F00011 220060223G8530327628 CYLINDER DOUG DC6 DC6B 3021712WP PWA R2800 CB3 52026NE NR 2 ENGINE CRACKED I E ENGINE SHUTDOWN R PARTIAL RPM/PWR LOSS CRCRUISE 1 AL05444CE 2269 45478 NK510061 NR 2 ENGINE SHUT DOWN DUE ROUGH RUNNING 2L74 4R4 R 6A4 E264 20060804000112006080400011CE 2006 8 4 2006F00024 120060505G5100 CANISTER BEECH 300 300BEECH 1152930CE COWL OPEN E O OTHER O OTHER NRNOT REPORTED 1 SO0352LP FA8 SMOKING ON SHUT DOWN. OPENED RIGHT SIDE COWLING AND FOUND THE END OF THE EPA CAN COMPLETELY OPEN. END PLATE FOUND IN BOTTOM OF COWLING. TT PRESUMED TO BE ORIGINAL. 2L72 4T A24CE 20061012001192006101200119 2006 10 12 2006F00042 120060930G26122158 SMOKE DETECTOR PWA PT6 PT6A42 52043NE FALSE INDICATIOND E ENGINE SHUTDOWN J WARNING INDICATION APAPPROACH 1 GL07200E 6819 PCE93694 LT ENGINE FIRE INDICATION IN DECENT DURING APPROACH PHASE OF FLIGHT. SHUT ENGINE DOWN.INSPECTION OF THE FIRE DETECTION SYSTEM AND DETECTORS PROVED TO HAVE NO ISSUES, COULD NOT DUPLICATE ON GROUND RUN. 4 T E4EA 20061023000762006102300076EU 2006 10 23 2006F00048 120060925G28416653505509 PROBE ISRAEL1124 1124A 4500103EU FUEL SYSTEM MALFUNCTIONED E O OTHER O OTHER LDLANDING 1 SW09211ST8445 303 PRIOR TO REFUELING AIRCRAFT, CREW NOTICED LEFT FUEL QUANTITY GAUGE WAS 1400 LBS HEAVIER THAN RIGHT. SUBMITTED SPECIAL FLIGHT PERMIT AND RETURNED TO BASE. FOUND LEFT MAIN FUEL PROBE BAD. REMOVED AND REPLACED FUEL PROBE, CALIBRATED FUEL QUANTITY SYSTEM. PERFORMED FUNCTIONAL CHECK FLIGHT, NO DEFECTS NOTED. 2M72 4F A2SW 20060105002112006010500211CE 2006 1 5 2006FA0000002 120060104G2497593240101 CIRCUIT BREAKER CESSNA421 421B 2076014CE CONT O520 GTSIO520C 17032SO MASTER CORRODED D H DEACTIVATE SYST/CIRCUITS O OTHER NRNOT REPORTED 1 EA01678DB4950 421B0876 AVIONICS MASTER CIRCUIT BREAKER SWITCH FOUND INTERMITTENT DURING COMPLIANCE WITH AD 2005-20-05, MEB05-1. PN 593-240-101 NOT FOUND IN MFG PARTS MANUAL BUT THIS WAS CLEARLY THE ORIGINAL FACTORY INSTALLED CB. PROBLEM NR1, INTERNAL COMPONENTS OF CB HAD SEVERE CORROSION AND WAS CONTAMINATED WITH DUST, DIRT AND SMALL INSECTS. AIRCRAFT HAS ALWAYS BEEN HANGARED EXCEPT ON TRIPS. PROBLEM NR2 MEB 05-1 AND AD 2005-20-05 DO NOT INCLUDE THIS PART NUMBER. THE AD AND MEB REFERENCE 539-250-101 (50 AMP BREAKER) NOT THE 40 AMP BREAKER FOUND ON ALL 421B AIRCRAFT (IAW THE MFG PARTS MANUAL). 1L72 3O3 O A7CE E7CE 20060106000112006010600011SO 2006 1 6 2006FA0000003 220060104G8550 DIPSTICK CIRRUSSR SR22 2130001GL CONT O550 IO550* SO OIL CAP BROKEN C K NONE O OTHER ININSP/MAINT 1 SO115175L168 1542 DURING PREFLIGHT WHILE CHECKING OIL LEVEL ON DIPSTICK, ENTIRE ROD PORTION OF DIPSTICK CAME APART IN MY HANDS UPON LIFTING IT OUT OF OIL FILLER TUBE. BARELY CAUGHT IT WITH MY HAND BEFORE IT WOULD'VE FALLEN DOWN INSIDE THE ENGINE CRANKCASE WITH POTENTIALLY CATASTROPHIC RESULTS. ROD IS SWAGED IN 2 PLACES ONTO A LOWER CALIBRATED AREA FOR DETERMINING OIL LEVEL AS WELL AS AT TOP WHERE IT AFFIXES TO DIPSTICK COVER. IT HAS COME UNSWAGED IN BOTH UPPER AND LOWER PLACES. IF THIS OCCURRED IN FLIGHT, IT APPEARS A CATASTROPHIC ENGINE FAILURE COULD OCCUR AS METAL ROD PARTS FELL DOWN INTO ENG CRANKCASE/SUMP REGION. BELIEVE THIS DESERVES AN EMERGENCY AD. THIS PLANE IS A 2005 - JUST A FEW MONTHS OLD! 1L71 3O3 ONTA00009CHE3SO 20060110001412006011000141SO 2006 1 10 2006FA0000004 220060104G8550 DIPSTICK CIRRUSSR SR22 2130001GL CONT O550 IO550* SO ENGINE BROKEN C O OTHER O OTHER NRNOT REPORTED 1 SO115175L168 1542 DURING PREFLIGHT WHILE CHECKING OIL LEVEL ON DIPSTICK, THE ENTIRE ROD PORTION OF THE DIPSTICK CAME APART IN MY HANDS UPON LIFTING IT OUT OF THE OIL FILLER TUBE. BARELY CAUGHT IT WITH MY HAND BEFORE IT WOULD'VE FALLEN DOWN INSIDE THE ENGINE CRANK CASE WITH POTENTIALLY CATASTROPHIC RESULTS. ROD IS SWAGED IN 2 PLACES ONTO A LOWER CALIBRATED AREA FOR DETERMINING OIL LEVEL AS WELL AS AT THE TOP WHERE IT AFFIXES TO THE DIPSTICK COVER. IT HAS COME UNSWAGED IN BOTH UPPER AND LOWER PLACES. IF THIS OCCURRED IN FLIGHT, IT APPEARS A CATASTROPHIC ENGINE FAILURE COULD OCCUR AS THE METAL ROD PARTS FELL DOWN INTO THE ENGINE CRANK CASE / SUMP REGION. 1L71 3O3 ONTA00009CHE3SO 20060123002262006012300226CE 2006 1 23 2006FA0000015 120060104G5210 DOOR AYRES S2 S2R 7630202CE PWA R1340 R1340* 52016NE HAMSTD23D 23D40 NE RT CABIN DOOR BULGED D O OTHER B SMOKE/FUMES/ODORS/SPARKS AGAGRICULTURE 1 SW154914X 2105R CARBON MONOXIDE ENTRANCE INTO CABIN AREA. INCREASED AIRSPEED RESULTING FROM THIS COMBINATION CAUSED THE RT CABIN DOOR TO BULGE SLIGHTLY. PILOT CONCERNS ABOUT CARBON MONOXIDE ENTRANCE INTO THE CABIN WERE CONFIRMED WITH THE USE OF CO DETECTORS. RT CABIN DOOR WAS REMOVED AND SENT TO SERVICE CENTER TO BE MODIFIED TO THE 2-LATCH CONFIGURATION FOUND ON TURBINE AIRCRAFT. ADDITIONAL MONITORING FOR CARBON MONOXIDE SHOWED NO FURTHER PROBLEMS. 1L71 3R3 RNCA4SW 5E2 6 CP719 20060120001072006012000107CE 2006 1 20 2006FA0000018 120060111G282012161074 SEAL CESSNA182 182M 2072728CE SELECTOR VALVE DEFORMED D K NONE WK INADEQUATE Q C FLUID LOSS ININSP/MAINT 1 CE07 7069 RESEALED FUEL SELECTOR VALVE PN 0716613-1 AND DURING A LEAK TEST LEAKAGE WAS FOUND FROM ONE OF THE PN 1216107-4 SEALS. INVESTIGATION FOUND THAT THE SEAL FACE WAS DEFORMED AND THAT MOLD LINES FROM THE INJECTION MOLDING PROCESS CAUSED VOIDS IN THE SEALING SURFACE. 1H71 3O NT3A13 20060124001502006012400150GL 2006 1 24 2006FA0000019 120060109G3220 ROLL PIN DIAMONDA20 DA20C1 2990001GL CONT O240 IO240A SO NLG STRUT MISSING D K NONE O OTHER ININSP/MAINT 1 NM03917AF C0172 ROLL PIN LOCKING THE NOSE STRUT ELASTOMERIC SPRING PLATE (PN 20-3220-05-02) TO THE SHOCK ABSORBER ROD (PN 20-3220-05-01) HAD WORKED OUT UNLOCKING THE ASSY. 1L71 3O3 ONTTA4CH E7SO 20060124001982006012400198CE 2006 1 24 2006FA0000021 120060104G3242952891 BRAKE ASSY CESSNA195 195A 2073110CE JACOBSR755 L4* 35003EA WHEEL CORRODED D K NONE O OTHER LDLANDING 1 NM071528D3075 7750 DISASSEMBLED BRAKE AND FOUND THAT THE BRAKE CYLINDER WAS CORRODED FROM WHERE THE O-RING MAKES A SEAL TO THE IB STOP. THE O-RING WAS HARD AND HAD TAKEN A SET. MFG P/N 0341015. 1H71 3R3 R A790 TC121 20060124001182006012400118 2006 1 24 2006FA0000030 120060112G3242244688 KEYWAY BFGOODRICH STATOR/CARRIER CRACKED B K NONE O OTHER ININSP/MAINT 1 SO15 HAVE RECENTLY SEEN (4) BRAKE ASSY'S COME IN WITH THE CARRIER LINING/STATOR COMPLETELY BROKEN WITH MULTIPLE CRACKS AND DISCOLORED FROM WHAT APPEARS TO BE (OVERHEATED). THESE PARTS ARE NOT LIFE LIMITED AND ARE ON CONDITION ONLY. THEY ARE NDI AT THE TIME OF OVERHAUL BUT WITH THE AGING FACTOR AND OVERHEAT CONDITIONS, THESE PARTS WILL CONTINUE TO FAIL AND CRACK. THE TABS ARE COMPLETELY SHEARING OFF AND COULD CAUSE SEVERE BRAKING FAILURE OF THE AIRCRAFT. RE: W122086, W122087, W121926 20060124001202006012400120 2006 1 24 2006FA0000031 120060112G2120 SMOKE COCKPIT DETECTED C O OTHER B SMOKE/FUMES/ODORS/SPARKS NRNOT REPORTED 1 WP15 SMOKE IN COCKPIT FROM AUXILIARY GENERATOR OIL SPILL. 2ND TIME FOR AA MD80 IN LAST 30 DAYS. FLIGHTS: AA1160 12/14/05 SFO TO DFWAA552 1/12/2006 SFO TO ORD. 20060118001862006011800186CE 2006 1 18 2006FA0000032 120060112G2822LW15473 PUMP CESSNA172 172R 2072401CE LYC IO360 IO360L2A EA ENGINE LEAKING D K NONE K FLUID LOSS TXTAXI/GRND HDL 1 SW0979LU 1821 17281163 L3087351A AIRCRAFT WAS PARKED FOR 3 WEEKS. FOUND FUEL/OIL MIX LEAKING FROM MUFFLER EXHAUST PIPE. FUEL LEAKED VIA GRAVITY FROM TANKS THROUGH PUMP, INTO PUMP DRIVE LEVER AREA, THEN, VIA THE ACCESSORY SECTION INTO ENGINE . FOUND ENGINE CRANK CASE FILLED WITH AVGAS. CYLINDERS WERE ALSO FULL OF GAS/OIL MIX AND WERE HYDRAULICALLY LOCKED. FUEL/OIL MIX WAS DRAINING OUT EXHAUST VALVES INTO MUFFLER. NOTE: FUEL DID NOT DRAIN OUT OF DRAIN PORT ON FUEL PUMP. DISASSEMBLED PUMP. DRAIN PORT WAS NOT OBSTRUCTED. 1H71 3O3 ONT3A12 1E10 20060118001872006011800187CE 2006 1 18 2006FA0000033 120060112G2822LW15473 PUMP CESSNA172 172R 2072401CE LYC IO360 IO360L2A EA ENGINE LEAKING D K NONE K FLUID LOSS TXTAXI/GRND HDL 1 SW0979LU 1821 17281163 L3087351A AIRCRAFT WAS PARKED FOR 3 WEEKS. FOUND FUEL/OIL MIX LEAKING FROM MUFFLER EXHAUST PIPE. FUEL LEAKED VIA GRAVITY FROM TANKS THROUGH PUMP, INTO PUMP DRIVE LEVER AREA, THEN, VIA THE ACCESSORY SECTION INTO ENGINE . FOUND ENGINE CRANK CASE FILLED WITH AVGAS. CYLINDERS WERE ALSO FULL OF GAS/OIL MIX AND WERE HYDRAULICALLY LOCKED. FUEL/OIL MIX WAS DRAINING OUT EXHAUST VALVES INTO MUFFLER. NOTE: FUEL DID NOT DRAIN OUT OF DRAIN PORT ON FUEL PUMP. DISASSEMBLED PUMP. DRAIN PORT WAS NOT OBSTRUCTED. 1H71 3O3 ONT3A12 1E10 20060117003412006011700341CE 2006 1 17 2006FA0000034 120060112G7331MS3126F1065 CONNECTOR CESSNA441 441 2076020CE GARRTTTPE331TPE33110 01514WP ZONE 400 MISMARKED B K NONE W INADEQUATE Q C ININSP/MAINT 1 GL07 REPLACEMENT CONNECTOR FOR RT ENGINE FUEL FLOW TRANSDUCER. INSTALLED NEW CONNECTOR AND UPON CHECKOUT FOUND THAT FUEL FLOW INDICATOR NOW OPERATES BACKWARDS. FURTHER INVESTIGATION REVEALS THAT NEWLY INSTALLED CONNECTOR PIN HOLES ARE NOT PROPERLY MARKED. IN FACT THE MARKINGS ON THE FRONT END OF CONNECTOR DO NOT MATCH THE MARKINGS AT THE BACK OF THE CONNECTOR. TROUBLESHOOTING ALSO REVEALED THAT THE MISWIRING OF THE CONNECTOR HAS PERMANENTLY DAMAGED THE FUEL FLOW INDICATOR. PROBLEM WAS RESOLVED BY ORDERING A SECOND NEW CONNECTOR FROM MFG. CHECKED TO MAKE SURE THAT THE PIN LOCATION MARKINGS WERE CORRECT. NEW CONNECTOR INSTALLED WITH NEW FUEL FLOW INDICATOR. 1L72 3T4 TRTA28CE E4WE 20060117003432006011700343CE 2006 1 17 2006FA0000035 120060112G781020M911 MUFFLER ZINAIRCH2000CH2000 9950100CE ENGINE CRACKED D O OTHER B SMOKE/FUMES/ODORS/SPARKS ININSP/MAINT 1 GL159229 80 TAILPIPE CRACKED WHERE WELDED TO CAN, CRACKED .7500 OF WAY AROUND TAILPIPE LETTING EXHUAST INTO CABIN HEAT SHROUD. PART TOTAL TIME IN SERVE OF 80 HRS. FOUND DURING 50 HR OIL CHANGE. 1L71 3O NTTA5CH 20060117003422006011700342CE 2006 1 17 2006FA0000036 120060112G781020M911 MUFFLER ZINAIRCH2000CH2000 9950100CE ENGINE CRACKED D K NONE B SMOKE/FUMES/ODORS/SPARKS ININSP/MAINT 1 GL159229 80 TAILPIPE CRACKED WHERE WELDED TO CAN, CRACKED .7500 OF WAY AROUND TAILPIPE LETTING EXHAUST INTO CABIN HEAT SHROUD. PART TOTAL TIME IN SERVICE OF 80 HRS. FOUND DURING 50 HR OIL CHANGE. 1L71 3O NTTA5CH 20060117003472006011700347CE 2006 1 17 2006FA0000037 120060112G7331MS3126F1065 CONNECTOR CESSNA441 441 2076020CE GARRTTTPE331TPE33110 01514WP FUEL FLOW INDICAMISMARKED B O OTHER W INADEQUATE Q C ININSP/MAINT 1 GL07 PURCHASED A REPLACEMENT CONNECTOR FOR THE RT ENGINE FUEL FLOW TRANSDUCER. INSTALLED NEW CONNECTOR AND UPON CHECKOUT FOUND THAT FUEL FLOW INDICATOR NOW OPERATES BACKWARDS. FURTHER INVESTIGATION REVEALS THAT NEWLY INSTALLED CONNECTOR PIN HOLES ARE NOT PROPERLY MARKED. IN FACT THE MARKINGS ON THE FRONT END OF THE CONNECTOR DO NOT MATCH THE MARKINGS AT THE BACK OF THE CONNECTOR. TROUBLESHOOTING ALSO REVEALED THAT THE MISWIRING OF THE CONNECTOR HAS PERMANENTLY DAMAGED THE FUEL FLOW INDICATOR. PROBLEM WAS RESOLVED BY ORDERING A SECOND NEW CONNECTOR FROM MFG. CHECKED TO MAKE SURE THAT THE PIN LOCATION MARKINGS WERE CORRECT. NEW CONNECTOR INSTALLED WITH NEW FUEL FLOW INDICATOR. 1L72 3T4 TRTA28CE E4WE 20060117003322006011700332CE 2006 1 17 2006FA0000038 120060105G323045A3951141 UPLOCK BEECH MU300 400A 1155402CE PWA JT15 JT15* 52060NE NOSE GEAR UPLOCKINTERMITTENT E A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 GL21674SF2132 RK232 AFTER TAKEOFF LANDING GEAR WAS SELECTED UP AND GEAR CAME UP TOO BUT RED WARNING LIGHT IN GEAR HANDLE STAYED ON AND YOU COULD HEAR THE DOORS WERE STILL OPEN. SELECTED GEAR DOWN AND RETURNED TO BASE. FOUND NOSE GEAR UPLOCK WAS INTERMITTENT. RIGGED UPLOCK AND OPS CHECK. 2H72 4F4 TRTA16SW E1NE 20060117003312006011700331CE 2006 1 17 2006FA0000039 120060105G323045A3951141 UPLOCK BEECH MU300 400A 1155402CE PWA JT15 JT15* 52060NE NOSE GEAR OUT OF RIG E A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 GL21674SF2132 RK232 AFTER TAKEOFF LANDING GEAR WAS SELECTED UP AND GEAR CAME UP TO BUT RED WARNING LIGHT IN GEAR HANDLE STAYED ON AND YOU COULD HEAR THE DOORS WERE STILL OPEN. SELECTED GEAR DOWN AND RETURNED TO BASE. FOUND NOSE GEAR UPLOCK WAS INTERMITTENT. RIGGED UP LOCK AND OPS CHECK GEAR. 2H72 4F4 TRTA16SW E1NE 20060214002472006021400247 2006 2 14 2006FA0000040 420060113G3416 ALTIMETER CESSNA206 T206H 2073303CE LYC O540 TIO540* 41532EA INSTRUMENT PANELERRATIC G K NONE SE AFFECT SYSTEMS VIBRATION/BUFFET CRCRUISE 1 WP231836U65 T20608548 AT TAKEOFF POWER (2500 RPM) AND CRUISE OVER 2390 RPM, THE STANDBY ALTIMETER MAY OSCILLATE 20 FT TO 100 FT (3500 FT CRUISE ALTITUDE).AT CRUISE, THE AUTOPILOT UNCOUPLED ITSELF THREE TIMES.DESCENT AND APPROACH (BELOW 2390 RPM) OSC. WAS 20 TO 40 FEET. BELOW 2300 RPM THE ALT. WAS STEADY.GARMIN 1000 EFIS INSTALLATION HAS THE STNBY ALTIMETER HARD MOUNTED TO A LARGE INSTRUMENT PANEL WITH NO VIBRATION DAMPENING MECHANISM. DURING CRUISE, WHEN THE ALTIMETER WAS OSCILLATING THE GREATEST, APPLYING MODERATE HAND PRESSURE (APPX. 10 LBS.) TO THE INSTRUMENT PANEL LESSENED THE AMOUNT OF OSCILLATION.THE AUTOPILOT CONTROL PANEL (HARD MOUNTED BELOW THE STANDBY ALTIMETER) CONTAINS AN ANEROID SIMILAR TO ONE IN THE STANDBY ALTIMETER. 1H71 3O3 ORTA4CE E14EA 20060117003402006011700340CE 2006 1 17 2006FA0000041 120060112G7331MS3126F1065 CONNECTOR CESSNA441 441 2076020CE GARRTTTPE331TPE33110 01514WP ZONE 400 MISMARKED B O OTHER W INADEQUATE Q C ININSP/MAINT 1 GL07 WE PURCHASED A REPLACEMENT CONNECTOR FOR THE RT ENGINE FUEL FLOW TRANSDUCER. INSTALLED NEW CONNECTOR AND UPON CHECKOUT FOUND THAT FUEL FLOW INDICATOR NOW OPERATES BACKWARDS. FURTHER INVESTIGATION REVEALS THAT NEWLY INSTALLED CONNECTOR PIN HOLES ARE NOT PROPERLY MARKED. IN FACT THE MARKINGS ON THE FRONT END OF THE CONNECTOR DO NOT MATCH THE MARKINGS AT THE BACK OF THE CONNECTOR. TROUBLESHOOTING ALSO REVEALED THAT THE MISWIRING OF THE CONNECTOR HAS PERMANENTLY DAMAGED THE FUEL FLOW INDICATOR. PROBLEM WAS RESOLVED BY ORDERING A SECOND NEW CONNECTOR FROM MFG. CHECKED TO MAKE SURE THAT THE PIN LOCATION MARKINGS WERE CORRECT. NEW CONNECTOR INSTALLED WITH NEW FUEL FLOW INDICATOR. 1L72 3T4 TRTA28CE E4WE 20060214002292006021400229 2006 2 14 2006FA0000042 420060117G23500110040110 AUDIO PANEL DIAMONDA20 DA20C1 2990001GL RADIO PANEL BURNED B K NONE BW SMOKE/FUMES/ODORS/SPARKS INADEQUATE Q C ININSP/MAINT 1 NE03176MA18 C0345 AIRCRAFT HEADSET MICROPHONE JACKS ARE UNIQUILY WIRED FOR SENNHIESER ANR HEADSETS WITH AIRCRAFT SUPPLIED POWER FROM THE MICROPHONE JACK KEY TERMINAL. THIS IS WIRED DIFFERANTLY THAN SHOWN IN MFG GMA-340 INSTALLATION MANUAL. USE OF STANDARD AIRCRAFT HANDHELD MIC IN HEADSET JACKS CAUSED PRINTED CIRCUIT LANDS TO BURN OFF MAIN PRINTED CIRCUIT BOARD OF GMA-340 UNIT RESULTING IN A COMPLETE LOSS OF RADIO COMMUNICATIONS AND INTERCOM OPERATION. JACKS NOT PLACARDED BY MFGR AS (HEADSET MICROPHONE ONLY), OR (NO HAND MIC). ALSO, NO WARNING IN POH. EVEN IF PLACARDS WERE INSTALLED, USING A STANDARD MICROPHONE IN A STANDARD AIRCRAFT JACK, SHOULD NOT CAUSE TOTAL LOSS OF AC COMMUNICATIONS. 1L71 3O NTTA4CH 20060214002302006021400230 2006 2 14 2006FA0000043 420060117G23500110040110 AUDIO PANEL DIAMONDA20 DA20C1 2990001GL RADIO PANEL BURNED B K NONE BW SMOKE/FUMES/ODORS/SPARKS INADEQUATE Q C ININSP/MAINT 1 NE03176MA18 C0345 AC HEADSET MICROPHONE JACKS ARE UNIQUELY WIRED FOR SENNHIESER ANR HEADSETS WITH AIRCRAFT SUPPLIED POWER FROM THE MICROPHONE JACK KEY TERMINAL. THIS IS WIRED DIFFERENTLY THAN SHOWN IN GARMIN'S GMA-340 INSTALLATION MANUAL. USE OF STANDARD AIRCRAFT HANDHELD MIC. IN HEADSET JACKS CAUSED PRINTED CIRCUIT LANDS TO BURN OFF MAIN PRINTED CIRCUIT BOARD OFN GMA-340 UNIT RESULTING IN COMPLETE LOSS OF RADIO COMMUNICATIONS AND INTERCOM OPERATION. JACKS NOT PLACARDED BY MFGR AS (HEADSET MICROPHONE ONLY), OR (NO HAND MIC). ALSO, NO WARNING IN POH. EVEN IF PLACARDS WERE INSTALLED, USING A STANDARD MICROPHONE IN A STANDARD AC JACK, SHOULD NOT CAUSE TOTAL LOSS OF AC COMMUNICATIONS. 1L71 3O NTTA4CH 20060214002452006021400245 2006 2 14 2006FA0000044 420060117G23500110040110 AUDIO PANEL DIAMONDA20 DA20C1 2990001GL RADIO PANEL BURNED B K NONE BW SMOKE/FUMES/ODORS/SPARKS INADEQUATE Q C UKUNKNOWN 1 NE03176MA18 C0345 AIRCRAFT HEADSET MICROPHONE JACKS ARE UNIQUILY WIRED FOR ANR HEADSETS WITH AIRCRAFT SUPPLIED POWER FROM THE MICROPHONE JACK KEY TERMINAL. THIS IS WIRED DIFFERANTLY THAN SHOWN IN MFG GMA-340 INSTALLATION MANUAL. USE OF STANDARD AIRCRAFT HANDHELD MIC IN HEADSET JACKS CAUSED PRINTED CIRCUIT LANDS TO BURN OFF MAIN PRINTED CIRCUIT BOARD OFN GMA-340 UNIT RESULTING IN COMPLETE LOSS OF RADIO COMMUNICATIONS AND INTERCOM OPERATION. JACKS NOT PLACARDED BY MFG AS (HEADSET MICROPHONE ONLY), OR (NO HAND MIC). ALSO, NO WARNING IN POH. EVEN IF PLACARDS WERE INSTALLED, USING A STANDARD MICROPHONE IN A STANDARD AIRCRAFT JACK, SHOULD NOT CAUSE TOTAL LOSS OF AIRCRAFT COMMUNICATIONS. 1L71 3O NTTA4CH 20060126000322006012600032SO 2006 1 26 2006FA0000045 220060118G741410357586 DISTRIBUTOR GEARTELEDYNESYSTS6LSC25 CESSNA172 R172K 2072431CE CONT O360 IO360KB 17025SO MAGNETO FAILED D O OTHER O OTHER NRNOT REPORTED 1 SO114718K175 D04HA269R R1722017 288769 ELEVEN GEAR TEETH FAILED ON NYLON DISTRIBUTOR GEAR. 1H71 3O3 O 3A17 E1CE 20060126000912006012600091SO 2006 1 26 2006FA0000046 120060111G531012034535003 WINDOW FRAME EMB 120 EMB120RT 3260202SO PWA 118 PW118 NE RT COCKPIT CRACKED B OWFRO OTHER O OTHER NRNOT REPORTED 1 CE05200CD26579 120200 COPILOTS SIDE WINDOW LOWER STRUCTURAL BEAM IS CRACKED AT RT WINDSHIELD AFT BEAM. NORMAL OPS. (K) 2L72 4T4 TRTA31SO E20NE 20060124001922006012400192SO 2006 1 24 2006FA0000047 120060111G531012034535001 WINDOW FRAME EMB 120 EMB120RT 3260202SO PWA 118 PW118 NE LT COCKPIT CRACKED B OWFRO OTHER O OTHER NRNOT REPORTED 1 CE05196CA28588 120196 PILOTS SIDE WINDOW LOWER STRUCTURAL BEAM IS CRACKED AT LEFT WINDSHIELD AFT BEAM. NORMAL OPS. (K) 2L72 4T4 TRTA31SO E20NE 20060120001022006012000102SO 2006 1 20 2006FA0000050 220060110G85301864321 CYLINDER BEECH 58 58 1152740CE CONT O520 IO520CB 17032SO ENGINE CRACKED D O OTHER O OTHER ININSP/MAINT 1 SO038195R TH529 299141R ENGINE CYLINDER CRACKED AND BARREL AND HEAD. 1L72 3O3 O 3A16 E5CE 20060126000992006012600099SO 2006 1 26 2006FA0000051 220060110G85301847312 CYLINDER BEECH 58 58 1152740CE CONT O520 IO520CB 17032SO ENGINE CRACKED D O OTHER O OTHER NRNOT REPORTED 1 SO038195R611 TH529 299141R ENGINE CYLINDER CRACKED AT BARREL AND HEAD. (K) 1L72 3O3 O 3A16 E5CE 20060126000962006012600096NE 2006 1 26 2006FA0000053 220060107G8520LW13923 PISTON MAULE M7 M7235 5460170SO LYC O540 IO540W1A5 41532NE ENGINE BROKEN D O OTHER O OTHER NRNOT REPORTED 1 NM019234N1078 4119C L2492048A INSPECTION OF THE OIL FILTER DURING ROUTINE OIL CHANGE FOUND 2 EA (.1250 INCH) DIAMETER PIECES OF ALUMINUM. FURTHER DISASSEMBLY OF THE ENGINE/ CYLINDERS FOUND THE NR 1 CYLINDER PISTON SKIRT WAS MISSING A SECTION (.5 INCH X 1.1250 INCH LONG). PERFORMED A DY PENETRANT INSP TO THE OTHER PISTONS. 3 WERE CRACKED AT THE SAME LOCATION. 1 HAD INDICATION OF POSSIBLE CRACK AND 1 WAS IN SERVICEABLE CONDITION. NO OTHER DAMAGE TO THE PISTON WAS DIAMETER WAS WITHIN SERVICE LIMITS. CYLINDER DIAMETER WAS WITHIN SERVICE LIMITS. (K) 1H71 3O3 ONC3A23 1E4 20060126000862006012600086WP 2006 1 26 2006FA0000055 220060109G726130745732 CARBON SEAL LEAR 45 45LEAR 5170805CE GARRTTTFE731TFE7312 01518WP ENGINE WORN D O OTHER O OTHER NRNOT REPORTED 1 WP07411AJ747 2011 P116515 PERFORMED SOAP SAMPLE DUE TO FILTER BYPASSED. SAMPLE CAME BACK NORMAL. PERFORMED ANOTHER SOAP SAMPLE 50 HOURS LATER AND FILTER FAILED DELTA P-CHECK. RESULTS CAME BACK (INSPECT THIS ENGINE IMMEDIATELY) INSTALLED LOANER ENGINE. ORIGINAL ENGINE HAD NR 1, NR 3, NR 4 AND NR 5 CARBON SEALS REPLACED. RE-INSTALLED ORIGINAL ENGINE AFTER REPAIRE. 25 HOUR SOAP SAMPLE RESULTS ARE NORMAL. PROBABLE CAUSE IS PREMATURE WEAR/FAILURE OF CARBON SEALS. RECOMMEND IMPROVING CARBON SEAL MATERIAL AND QUALITY. (K) 2L72 4F4 FRTT00008WIE6WE 20060126001022006012600102WP 2006 1 26 2006FA0000056 220060109G726130745742 CARBON SEAL LEAR 45 45LEAR 5170805CE GARRTTTFE731TFE7312 01518WP ENGINE WORN D O OTHER O OTHER NRNOT REPORTED 1 WP07411AJ747 2011 P116515 PERFORMED SOAP SAMBLE DUE TO FILTER BYPASSED. SAMPLE CAME BACK NORMAL. PERFORMED ANOTHER SOAP SAMPLE 50 HOURS LATER AND FILTER FAILED DELTA P-CHECK. RESULTS CAME BACK (INSPECT THIS ENGINE IMMEDIATELY). INSTALLED LOANER ENGINE. ORIGINAL ENGINE HAD NR1, NR3, NR4 AND NR5 CARBON SEALS REPLACED. REINSTALLED ORIGINAL ENGINE AFTER REPAIR. 25 HOUR SOAP SAMPLE RESULTS ARE NORMAL. PROBABLE CAUSE IS PREMATURE WEAR/FAILURE OF CARBON SEALS. RECOMMEND IMPROVING CARBON SEAL MATERIAL AND QUALITY. (K) 2L72 4F4 FRTT00008WIE6WE 20060126001032006012600103SO 2006 1 26 2006FA0000057 120060112G57516538834 BALANCE WEIGHT PIPER PA28 PA28150 7102804SO LYC O320 O320* 41508EA LT AILERON BROKEN D V36RO OTHER O OTHER NRNOT REPORTED 1 SO135105W 28122 REMOVED EXISTING BALANCE WEIGHT ASSEMBLY, PN 65388-34 ON THE LT AILERON AND REPLACED WITH A SERVICEABLE BALANCE WEIGHT ASSEMBLY OF THE SAME PN AND WEIGHT. AT ANNUAL INSPECTION, THE WEIGHT WAS FOUND BROKEN OFF AT THE ATTACHMENT TUBE. THE EXISTING RIVET PATTERN WAS REUSED. SINCE THE WEIGHT AND ATTACHMENT POINTS WERE IDENTICAL BETWEEN THE ASSEMBLIES, THERE WAS NO CHANGE TO THE WEIGHT AND BALANCE. THE PILOT DID NOT NOTICE ANY DIFFERENCE IN THE HANDLING OF THE RESPONSE OF THE AC PRIOR TO THE REPAIR. THE BROKEN OFF WEIGHT WAS FOUND IN THE WING BETWEEN THE OUTER RIB AND THE ADJACENT IB RIB. (K) 1L71 3O3 O 2A13 E274 20060126000892006012600089NM 2006 1 26 2006FA0000058 120060102G2910 VENT LINE CHRIS HUSKY A1 221020XNM LYC O360 O360* 41514EA FUEL VENT BLOCKED D O OTHER O OTHER NRNOT REPORTED 1 AL039622V 1154 BOTH LT FUEL VENT LINES BLOCKED BY ICE. ENGINE STOPPED DURING TAXI TO RUNWAY. ALTHOUGH PREFLIGHT LISTS CHECKING FUEL VENT LINES ARE CLEAR, THIS NEEDS TO BE EMPHASIZED MORE. (K) 1H71 3O3 ONCA22NM E286 20060126000872006012600087CE 2006 1 26 2006FA0000060 120060105G5752AA50723 BUSHING BEECH 58 58 1152740CE CONT O550 IO550* SO AILERON TRIM WORN B E81RO OTHER O OTHER NRNOT REPORTED 1 GL03376W 517 TH1970 AILERON TRIM MADE POPPING NOISE AS CONTROL WAS ROTATED. FOUND BUSHING FOR CONTROL SHAFT IN PEDESTAL SEVERELY WORN ALLOWING U-JOINT TO CONTACT STRUCTURE AS CONTROL WAS ROTATED. TRIM CABLE TENSION WAS WITHIN LIMITS, NO REASON FOR ACCELERATED WEAR NOTED. BUSHING IS OILITE TYPE AND NO LUBRICATION IS CALLED FOR. (K) 1L72 3O3 O 3A16 E3SO 20060131002112006013100211 2006 1 31 2006FA0000064 120060112G5100 CASE UNKNOWN LEAKING B JGVRO OTHER O OTHER NRNOT REPORTED 1 GL09 IVSI WAS RECEIVED FOR REPAIR OF A CASE LEAK EXCEEDING MFG TOLERANCES. (RC-60-VIL1) MFG ACCEPTABLE SEALANT FOR DASHPOT CYL ENDS AND FOR FEED-IN-FLANGE MNTG SCREW HEADS IS RED GLYPTAL. 5-MIN EXPOXY WAS APPLIED TO END CAPS AND FITTING FLANGE. 5-MIN EXPOXY HAS BEEN APPLIED OVER SCREW HEADS AND AROUND FITTING FLANGE THAT ATTACHES FEED-IN TUBE FROM DASHPOT ASSY TO REAR OF THE INSTRMT CASE, ALSO PACKED AROUND FEED-IN TUBE ITSELF. THIS METHOD OF SEALING WITH EXPOXY RATHER GYPTAL MAKES IT DIFFICULT TO FURTHER REPAIR THIS IVSI W/O DESTROYING DASHPOT FEED-IN TUBE. NATURE OF EPOXY, IT DOES NOT ALLOW FLEXING AT JOINT, NOT RESPONSIVE TO CHANGE IN TEMP. OVER TIME IT MAY PULL AWAY FROM ONE SURFACE AND ALLOW LEAKAGE. (K) 20060124001762006012400176SO 2006 1 24 2006FA0000065 120060111G531012034535001 WINDOW FRAME EMB 120 EMB120RT 3260202SO PWA 118 PW118 NE WINDSHIELD CRACKED B OWFRO OTHER O OTHER NRNOT REPORTED 1 CE05200CD26579 120200 PILOT`S SIDE WINDOW LOWER STRUCTURAL BEAM IS CRACKED AT LT WINDSHIELD AFT BEAM. NORMAL OPERATIONS. (K) 2L72 4T4 TRTA31SO E20NE 20060131002202006013100220SW 2006 1 31 2006FA0000066 120060111G5320K660000 ANGLE GULSTM690TP 695A 7630519SW GARRTTTPE331TPE331* 01514WP FUSELAGE MISLOCATED D MV5RO OTHER O OTHER NRNOT REPORTED 1 GL117895G 96070 JOGGLE IN PART NEEDS TO BE RELOCATED .2500 INCH FURTHER FROM NEAR END OF ANGLE IN ORDER TO HAVE SUFFICIENT ED TO FASTENER. (K) 1H72 4T3 T 2A4 E2WE 20060131002152006013100215SW 2006 1 31 2006FA0000067 120060111G5320K6600006 ANGLE GULSTM690TP 695A 7630519SW GARRTTTPE331TPE331* 01514WP FUSELAGE MISLOCATED D MV5RO OTHER O OTHER NRNOT REPORTED 1 GL117896G 96070 JOGGLE IN PART NEEDS TO BE RELOCATED .2500 INCH FURTHER FROM NEAR END OF ANGLE IN ORDER TO HAVE SUFFICIENT ED TO FASTENER. (K) 1H72 4T3 T 2A4 E2WE 20060126001062006012600106SW 2006 1 26 2006FA0000068 120060111G5320K6600005 ANGLE GULSTM690TP 695A 7630519SW GARRTTTPE331TPE331* 01514WP FUSELAGE MISLOCATED D MV5RO OTHER O OTHER NRNOT REPORTED 1 GL117896G 96070 JOGGLE IN PRAT NEEDS TO BE RELOCATED .2500 INCH FURTHER FROM NEAR END OF ANGLE IN ORDER TO HAVE SUFFICIENT ED TO FASTENER. (K) 1H72 4T3 T 2A4 E2WE 20060126001072006012600107SW 2006 1 26 2006FA0000069 120060111G5320K6600004 ANGLE GULSTM690TP 695A 7630519SW GARRTTTPE331TPE331* 01514WP FUSELAGE MISLOCATED D MV5RO OTHER O OTHER NRNOT REPORTED 1 GL117896G 96070 JOGGLE IN PART NEEDS TO BE RELOCATED .2500 INCH FURTHER FROM NEAR END OF ANGLE IN ORDER TO HAVE SUFFICIENT ED TO FASTENER. (K) 1H72 4T3 T 2A4 E2WE 20060124001862006012400186NM 2006 1 24 2006FA0000071 120060102G321340005401 CYLINDER PIPER PA60 PA60601P 7106012NM MLG STRUT CRACKED D O OTHER O OTHER NRNOT REPORTED 1 SO1591VK 4148 61P06157963 COLLAR SEPARATING FROM TUBE DUE TO INSUFFICIENT PENETRATION WHEN PART WAS FURNACE BRAZED OR SILVER SOLDERED TOGETHER WORKING COLLAR CAUSED PART TO WORK AND CRACK BOSS. RECOMMEND INSPECTION OF COLLAR AT BOTTOM OF GEAR STRUT FOR ANY MOVEMENT OR WORKING BETWEEN COLLAR AND THE STRUT CYLINDER ASSY DYE CHECK WHERE PART IS MACHINED FOR CLEARANCE ON TORQUE LINKS. (K) 1M72 3O RTA17WE 20060126000822006012600082NE 2006 1 26 2006FA0000076 220060116G72302292260060 TURBINE WHEEL SNIAS 350 AS350B3 8680954EU TMECA ARRIELARRIEL2B NE GAS GENERATOR MIGRATED D O OTHER O OTHER NRNOT REPORTED 1 WP23352SA 01018 3348 22396 DURING A ROUTINE 600 HR BORESCOPE INSP OF THE GAS GENERATOR TURBINE BLADES, 2 BLADES WERE FOUND TO HAVE MOVED AFT IN THEIR (FIR-TREE) TYPE MOUNTS IN THE TURBINE DISK. 1 BLADE WAS FOUND TO HAVE MOVED .1250-.2500 INCH, AND THE OTHER LESS THAN .1250 INCH. THE BLADES HAD TO MOVE PAST A RETAINING CLIP TO ACHIEVE THE AMOUNT OF MOVEMENT OBSERVED. THIS TYPE OF DEFECT IS NOT LISTED AS A POSSIBLE DEFECT IN THE ENGINE MM AND SMALL AMOUNTS OF INSP REGIME. DUE TO THE POTENTIAL EFFECTS OF THE RECOMMEND A BORESCOPE INSP OF THE BLADE ALIGNMENT BEFORE FURTHER FLIGHT AND AT AN INTERVAL OF 300 HOURS ENGINE IS BEING RETURNED TO MFG. (K) 1G71 3U3 U H9EU E00054EN 20060126000782006012600078SO 2006 1 26 2006FA0000077 220060116G8530SA52000 CYLINDER HEAD BEECH 58 58 1152740CE CONT O520 IO520C 17032SO ENGINE SEPARATED B WS9RO OTHER O OTHER NRNOT REPORTED 1 NM077209B992 TH1428 280384R APPEAR THAT THERE WAS A CRACK IN THE CYLINDER HEAD AT THE EXHAUST VALVE SEAT, WHICH PROPOGATED DURING OPERATION UNTIL THE CYLINDER HEAD FAILED AND SEPARATED FROM THE CYLINDER. (K) 1L72 3O3 O 3A16 E5CE 20060126000092006012600009CE 2006 1 26 2006FA0000078 120060103G282325CX1123AC LEVER RAYTHNDH125 HAWKER800 7450004CE GARRTTTFE731TFE731* 01518WP FUEL TRANSFER CORRODED B JGVRO OTHER O OTHER NRNOT REPORTED 1 CE0971MT 8865 258230 FOUND WING FUEL TRANSFER LEVER ASSY CORRODED AT FORKED END. THIS LEVER ASSY IS NOT A DIRECT INSPECTION ITEM NOR IS IT A DIRECT LUBE ITEM. (K) 2L72 4F4 FRTA3EU E6WE 20060130000712006013000071CE 2006 1 30 2006FA0000079 120060105G2823 LEVER RAYTHNDH125 HAWKER800 7450004CE GARRTTTFE731TFE731* 01518WP FUEL TRANSFER CORRODED B JGVRO OTHER O OTHER NRNOT REPORTED 1 CE0975MT 8527 258231 FOUND WING FUEL TRANSFER LEVER ASSY CORRODED AT THE FORK END. THIS LEVER ASSY IS NOT A DIRECT INSPECTION ITEM NOR IS IT A DIRECT LUBE ITEM. (CE09200602408) (K) 2L72 4F4 FRTA3EU E6WE 20060130000722006013000072CE 2006 1 30 2006FA0000080 120060105G282325CX1123AC LEVER RAYTHNDH125 HAWKER800 7450004CE GARRTTTFE731TFE731* 01518WP FUEL TRANSFER CORRODED B JGVRO OTHER O OTHER NRNOT REPORTED 1 CE09954H 5819 258259 FOUND WING FUEL TRANSFER LEVER CORRODED AT BOTH ENDS. THIS LEVER ASSY IS NOT A DIRECT INSPECTION ITEM NOR IS IT A DIRECT LUBE ITEM. (K) 2L72 4F4 FRTA3EU E6WE 20060126000792006012600079CE 2006 1 26 2006FA0000081 120060108G32500543022 ROD CESSNA172 172A 2072404CE CONT O300 O300* 17022SO LT STEERING RUSTED G O OTHER O OTHER NRNOT REPORTED 1 NM139852T 47652 ROD END FAILED. AIRCRAFT TURNED LT AND IMPACTED AN EMBANKMENT. SMALL AMOUNT OF RUST ON ROD END AT THE THREADED AREA. (K) 1H71 3O3 O 3A12 E253 20060130000742006013000074EU 2006 1 30 2006FA0000082 120060109G4940 SWITCH HWKSLYDH125 BH125400A 4230138EU GARRTTTFE731TFE731* 01518WP APU START PANEL PILOT ERROR H O OTHER W INADEQUATE Q C NRNOT REPORTED 1 NM03125CK 25266 PILOT MISTAKENLY TRIPPED THE APU FIRE EXTINGUISHER SWITCH INSTEAD OF THE APU START SWITCH. BOTH SWITCHES ARE OF THE SAME STYLE, ARE LOCATED CLOSE TOGETHER AND BOTH HAVE THE SAME STYLE OF RED GUARDED SWITCHES. (K) 2L72 4J4 F A3EU E6WE 20060131001752006013100175SW 2006 1 31 2006FA0000083 120060102G5751250000225 SKIN GULSTM690TP 690B 7630516SW RT WING AILERON CORRODED B MV5RO OTHER O OTHER NRNOT REPORTED 1 GL11690LL 11544 CORROSION BEYOND 10 PERCENT LIMITS IN LEADING EDGE SKIN UNDER BALANCE WEIGHTS. FOUND DURING SB238. (K) 1H72 3T 2A4 20060130000752006013000075SO 2006 1 30 2006FA0000084 220060110G8530196279 CYLINDER HEAD BEECH 58 58 1152740CE CONT O520 IO520* 17032SO ENGINE CRACKED D O OTHER O OTHER NRNOT REPORTED 1 SO038195R611 TH529 ENGINE CYLINDER CRACKED AT BARREL AND HEAD. (K) 1L72 3O3 O 3A16 E5CE 20060126000472006012600047SO 2006 1 26 2006FA0000086 120060112G3244304K632 TIRE EMB 135 EMB135BJ 3260306SO MLG LEAKING C O OTHER O OTHER NRNOT REPORTED 1 GL25 AFTER INSTALLING NEW TIRE ON WHEEL ASSEMBLY AND INFLATING, THE TIRE WAS DISCOVERED TO BE LEAKING AT ALL SIDEWALL WEEP HOLES. THIS CONDITION CONTINUED EVEN AFTER THE 12 HOUR LEAK CHECK TIME HAD EXPIRED. (K) 2L72 4F RT 20060207002052006020700205EA 2006 2 7 2006FA0000087 220060120G7324 POPPET VALVE LYC 63323440ASY CESSNA172 172S 2072439CE LYC IO360 IO360L2A EA ENGINE STICKING B K NONE O OTHER TXTAXI/GRND HDL 1 CE07575TW33 33 0A10933 172S10078 L3241851E AIRCRAFT WOULD NOT START. ENGINE & FUEL COLD SOAKED (JUST AT BELOW 32 DEG. F). THE FLOW DIVIDER POPPET VALVE WOULD STICK CLOSED AND PREVENT FUEL FLOW. AFTER TROUBLSHOOTING DETERMINED THAT UNIT WOULD STICK IN CLOSED AND OPEN POS. THE CLOSED POS. PREVENTS FUEL FLOW TO NOZZLES. FOUND IF UNIT WAS COOLED ON THE BENCH WITHOUT FUEL IN THE DIVIDER THE POPPET VALVE WOULD STILL STICK. SUSPECT MFG TOLERANCES BAD ON POPPET ASSY. TRIED DUPLICATING ON AN AIRCRAFT 1 1/2 YEARS OLDER. COULD NOT DUPLICATE. HOWEVER, COULD DUPLICATE ON AN AIRCRAFT WHO'S SERIAL NUMBER IS IN CLOSE TO THE SQUAWKED AIRCRAFT. APPEARS TO BE A SPECIFIC LOT NUMBER OF EFFECTED PARTS. HEAT FROM RUNNING ENGINE RUNNING KEEPS VALVE MOVING FREELY. 1H71 3O3 ONT3A12 1E10 20060224001862006022400186CE 2006 2 24 2006FA0000088 120060124G561045AS3101011 WINDOW BEECH MU300 400A 1155402CE PWA JT15 JT15D5 52112NE COCKPIT CRACKED E K NONE O OTHER ININSP/MAINT 1 GL21674SF2141 RK232 DURING INSPECTION, THE PILOTS SIDE WINDOW WAS FOUND TO BE CRACKED THROUGH THE OUTER PANE CONNECTING 5 BOLT HOLES ALONG THE TOP OF WINDOW. 2H72 4F4 FRTA16SW E25EA 20060131001992006013100199CE 2006 1 31 2006FA0000090 120060106G324007515500 PLATE BEECH 90 E90 1152914CE PWA PT6 PT6A27 52043EA BRAKE CYLINDER CRACKED D O OTHER O OTHER NRNOT REPORTED 1 GL09200RE8273 LW164 DURING A PHASE I AND II INSPECTION A CRACK WAS FOUND IN THIS PART ATTACHED TO THE RT GEAR ASSY. THE CRACK IS ON THE TORQUE PLATE UPPER FORWARD BRAKE CYLINDER PIN ATTACH HOLE. A BUSHING INSTALLED IN THIS HOLE HAS NO SIGN OF DAMAGE. PROBABLE CAUSE OF CRACKING WOULD BE STRESS RELATED. (K) 1L72 3T4 T 3A20 E4EA 20060131001642006013100164SW 2006 1 31 2006FA0000092 120060113G7810 RISER GULSTM112 114 7630314SW EXHAUST CRACKED D O OTHER O OTHER NRNOT REPORTED 1 WP284775W207 14105 TURBO SYSTEM INSTALLED IAW STL, BOTH LT AND RT EXHAUST RISERS HAD MANY CRACKS AND DEEMED UNSERVICEABLE. 207.8 HRS SINCE NEW, REPLACED UNITS FAILED IN 140.0 MORE. (K) 1L71 3O A12SO 20060127000692006012700069NM 2006 1 27 2006FA0000093 120060126G3231 SHEAR PIN DORNER DORNERDO32 DO328300 NM PWA 306 PW306B NE BROKEN E A UNSCHED LANDING E VIBRATION/BUFFET TOTAKEOFF 1 GL25328GT 3183 CREW REPORTED DURING GEAR RETRACTION THEY HEARD AND FELT A VIBRATION FROM NOSE GEAR DOOR NOT CLOSING FULLY. DURING INSPECTION THE RIGHT HAND FORWARD GEAR DOOR BREAKING ROD ASSEMBLY WAS FOUND TO HAVE A BROKEN SHEAR PIN. 2H72 4T4 FRTA55NM E35NE 20060131002062006013100206 2006 1 31 2006FA0000094 420060129G2562AK450 TRANSMITTER MOONEYM20 M20J 5870219SW LYC O360 IO360A1A 41514EA ELT DETERIORATED B NT3RK NONE O OTHER ININSP/MAINT 1 WP25201CD 240063 ELT TRANSMITTER WAS REMOVED DURING ANNUAL FOR BATTERY REPLACEMENT AND TESTING. UNIT HAD BATTERIES REPLACED. DURING TESTING THE UNIT MADE A WEAK SIGNAL OUTPUT AND HAS NO RANGE. USED DIFFERENT SET OF BATTERIES FOR RETESTING, SAME RESULTS. HOOKED BACK IN AIRCRAFT TO AIRCRAFT ANTENNA, TEST RESULTS THE SAME. ARMED UNIT AND TESTED THROUGH REMOTE MOUNTED SWITCH WITH SAME UNSATISFACTORY RESULTS. UNIT IS APPROXIMATELY 2 YEARS OLD. TREND OF FAILURES ON THIS MAKE AND MODEL OF ELT. SUSPECT INTERNAL DETERIORATION OF COMPONENT SECURITY. (K) 1L71 3O3 O 2A3 1E10 20060131001732006013100173 2006 1 31 2006FA0000096 420060117G2562 TRANSMITTER MOONEYM20 M20R 5870225SW CONT O550 IO550* SO ELT INTERMITTENT B NT3RK NONE O OTHER ININSP/MAINT 1 WP252164K532 455647 290172 ELT TRANSMITTER WAS REMOVED DURING ANNUAL FOR BATTERY REPLACEMENT AND TESTING. UPON TEST WITH BATTERIES REPLACED. THE UNIT ON/OFF WAS INTERMITTENT AND THE REMOTE OPERATION WAS INTERMITTENT. UNIT IS APPROXIMATELY 7 YEARS OLD. TREND OF FAILURES ON THIS MAKE AND MODEL OF ELT. SUSPECT INTERNAL DETERIORATION OF COMPONENT SECURITY. (K) 1L71 3O3 ORT2A3 E3SO 20060131001762006013100176CE 2006 1 31 2006FA0000098 120060124G3340RN24885023 LENS LEAR 35 36LEAR 5170601CE GARRTTTFE731TFE73122B 01518WP TAIL STROBELIGHTSPLIT B BHKRO OTHER O OTHER NRNOT REPORTED 1 EA2183FN 007 FAA/PMA APPROVED REPLACEMENT SPLITS/CRACKS ON INSTALL. SHAPE IS SLIGHTLY DIFFERENT FROM PN 248850237. (K) 2L72 4F4 F A10CE E6WE 20060131001912006013100191 2006 1 31 2006FA0000099 220060123G7414BL3492901 MAGNETO ENGINE INOPERATIVE B WS9RO OTHER O OTHER NRNOT REPORTED 1 NM07 SHOWER OF SPARKS DOESN`T WORK IAW TEST CELL. (K) 20060131001672006013100167 2006 1 31 2006FA0000100 120060123G7921G05448292 OIL COOLER CRACKED B WS9RO OTHER O OTHER NRNOT REPORTED 1 NM07 CRACKED FOOT ON OIL COOLER. (K) 20060131001922006013100192CE 2006 1 31 2006FA0000101 120060107G3210SM50D7 RELAY BEECH 33 F33A 1151425CE CONT O520 IO520* 17032SO MLG FAILED B VJ3RO OTHER O OTHER NRNOT REPORTED 1 WP075581T CE1350 MECHANIC REMOVED NEW RELAY FROM STOCK AND INSTALLED ON AIRCRAFT AND GEAR FAILED TO EXTEND, AFTER TAPPING ON THE TOP OF RELAY GEAR WENT DOWN. MECHANIC THEN INSTALLS ANOTHER NEW RELAY FROM STOCK AND SYSTEM OPERATED NORMAL. PROBABLE CAUSE AT THIS TIME UNKNOWN. (K) 1L71 3O3 O 3A15 E5CE 20060202001222006020200122SO 2006 2 2 2006FA0000102 120060124G321040288000 TRUNNION PIPER PA31T PA31T 7103124SO PWA PT6 PT6A60A 52043NE RT MLG CRACKED E IPMAO OTHER O OTHER NRNOT REPORTED 1 WP11111KV10500 31T7920035 DURING 100 HOUR INSPECTION FOUND CRACK IN WEB OF AFT MLG TRUNNION ASSY AIRCRAFT. (K) 1L72 3T4 T A8EA E4EA 20060202001082006020200108 2006 2 2 2006FA0000103 420060109G6113C30031 PLATE HARTZLHCB3T HCB3TN3 GL SPINNER FAILED B ME4RO OTHER O OTHER NRNOT REPORTED 1 SO19 BUA26690 SPINNER SUPPORT PLATES RECEIVED BROKEN WITH BOLTS STILL INSTALLED ON HUB, NO OTHER BROKEN PARTS OF THIS SUPPORT PLATE ASSY WERE FOUND ON THIS PROPELLER. (K) 6 CP15EA 20060202001052006020200105SO 2006 2 2 2006FA0000104 120060121G3610J301300AR COUPLING GULSTMG1159 GIV 3980115SO RROYCETAY TAY6118 EU BLEED AIR DUCT FAILED D O OTHER O OTHER NRNOT REPORTED 1 EA25327TL 1339 WITH APU RUNNING AND BLEED AIR SELECTED ON, COUPLING FAILED CAUSING DUCT TO SEPARATE. PROBABLE CAUSE UNKNOWN. SUGGEST MORE AGGRESSIVE LOCKING MECHANISM. (K) 2L72 4F4 FRTA12EA E25NE 20060202001432006020200143EA 2006 2 2 2006FA0000106 220060123G7314 SEAL AMTR SKYSMISMITHMINIPLA05625N3GL LYC O540 TIO540J2BD 41532EA PUMP SHAFT LEAKING D O OTHER O OTHER NRNOT REPORTED 1 GL2511NS 43 HKN023FP 61P0343102 L829261A WITH THE ENGINE OFF AND THE FUEL BOOST PUMP ON , A STEADY STREAM OF FUEL CAME OUT THE ENGINE DRIVEN FUEL PUMP SHAFT SEAL DRAIN HOSE. THE FUEL CONTINUED TO FLOW OUT THE DRAIN HOSE AFTER THE ENGINE WAS STARTED. THIS IS NOT THE FIRST INSTANCE OF LEAKS WITH THIS MODEL PUMP. THIS IS A RELATIVELY NEW DESIGN PUMP. PUMP WAS RETURNED TO THE MFG FOR WARRANTY. (K) 1B71 3O3 ONCEXPA1B71E14EA 20060202001442006020200144EU 2006 2 2 2006FA0000107 120060120G2822568127202 PUMP AIRBUS320 A320* EU FUEL SYS INOPERATIVE B G7EYO OTHER O OTHER NRNOT REPORTED 1 EA35 ONE FUEL PUMP WAS RETURNED FOR INSPECTION/REPAIR DUE TO A FAULT AND ASSOCIATED CB TRIP FOR LT WING TANK PUMP 2. ONE OF TWO NUTS HOLDING THE HOUSING BERING ASSY TO THE STATOR CAP BECAME LOOSE. THE ASSOCIATED SCREW DROPPED INTO THE STATOR WINDING, CAUSING ARCING. THE FLAME TRAP WAS BREACHED. DUE TO THE HOLE LEFT IN THE STATOR HOUSING BY THE MIGRATION OF THE SCREW. THIS LEFT A DIRECT PATH TO THE FUEL. THE MFG HAS ALSO BEEN INFORMED. (K) 2L72 4F RTA46NM 20060202001282006020200128CE 2006 2 2 2006FA0000108 120060116G2823 CONTROL CABLE CESSNA182 182T 2072703CE LYC O540 IO540AB1A5 EA AFT FUEL SELECT CHAFED D O OTHER O OTHER NRNOT REPORTED 1 NE0338US 18281173 L2858348 AT AC STA 22 LWS 3 INCHES, 3.75 INCHES BELOW CABIN FLOOR, ELEVATOR TRIM CONTROL CABLES CHAFING HARD ON BOTTOM SURFACE OF .2500 DIA FUEL TUBE AT LEFT AND AFT OF AIRCRAFT FUEL SELECTOR. IF LEFT CONTROL CABLE WILL CUT THRU FUEL TUBE (CAUSE) NOT SEEN AT FACTORY. REPOSITIONED FUEL TUBE UP AWAY FROM CONTROLS. (NE03200606762) (K) 1H71 3O3 ONT3A13 1E4 20060202001032006020200103CE 2006 2 2 2006FA0000109 120060118G8011642087A64 ADAPTER BEECH 36 A36 1151604CE CONT O550 IO550B SO STARTER ADAPTER WRONG PART B MQ3RO OTHER O OTHER NRNOT REPORTED 1 WP11268EA4 E3473 685983 AIRCRAFT CAME TO OUR SHOP WITH SMOKE AND OIL COMING OUT OF TAIL PIPE. 4 HOURS PRIOR, THE AIRCRAFT ANNUAL INSP WAS COMPLETED AND AT THAT TIME THE STARTER ADAPTOR WAS REPLACED WITH THE WRONG PART. THIS AC HAD BEEN MODIFIED BY STC WITH TORNADO ALLEY TURBO CHARGER SYS. THE STC REQUIRED THAT STARTER ADAPTER ASSEMBLY BE CHANGED TO PN 642087A63 THAT INCLUDES A OIL SCAVENGE PUMP. PN A2087A64 DOES NOT HAVE A SCAVENGE PUMP INSTALLED. THE REPLACEMENT PART WAS ORDERED BY ENGINE SN NOT BY STC MODIFIED PARTS LIST. IT WOULD BE RECOMMENDED THAT WHEN ORDERING PARTS FOR STC MODIFIED AIRCRAFT THAT THE STCC HOLDER BE CONTACTED FOR PARTS. 1L71 3O3 O 3A15 E3SO 20060202001292006020200129 2006 2 2 2006FA0000110 220060123G7414BL6006061 MAGNETO ENGINE INOPERATIVE B WS9RO OTHER O OTHER NRNOT REPORTED 1 NM07 METAL IN MAGNETO. (K) 20060202001062006020200106CE 2006 2 2 2006FA0000111 120060119G3297SM50D7 RELAY BEECH 33 F33A 1151425CE CONT O520 IO520* 17032SO MLG INTERMITTENT B VJ3RO OTHER O OTHER NRNOT REPORTED 1 WP075582X510 CE1353 PILOT REPORTED AFTER PUTTING THE GEAR SELECTOR IN THE DOWN POSITION THE GEAR WOULDN`T EXTEND, AFTER CYCLING GEAR SELECTOR GEAR WENT DOWN, AIRCRAFT RETURNED TO BASE. ON TROUBLESHOOTING THE MECHANIC SELECTED DOWN AND IT FAILED TO EXTEND, AFTER TAPPING ON TOP OF RELAY THE GEAR WENT DOWN. PROBABLE CAUSE AT THIS TIME UNKNOWN. INSTALLED NEW AND IMPROVED RELAY IAW DATE CODE. (K) 1L71 3O3 O 3A15 E5CE 20060203000852006020300085EA 2006 2 3 2006FA0000117 220060120G8520 FLANGE PIPER PA28 PA28161 7102803SO LYC O320 O320D3G 41508EA SNSNCH74DM M74DM EA ENGINE BROKEN B K NONE O OTHER ININSP/MAINT 1 GL21263ND 2842064 L1016739A A58041 BOTH FORWARD BOLT ATTACHMENT FLANGES WERE CRACKED OFF OF STARTER ATTACHMENT FLANGE ASSEMBLY. THIS CAUSED THE STARTER TO DROOP DOWNWARD WITH ONLY THE AFT BOLTS SUPPORTING THE STARTER. AS A RESULT, THE STARTER RING GEAR AND STARTER BENDIX WOULD NOT PROPERLY ENGAGE. THIS RESULTED IN THE TEETH OF THE BENDIX TO BREAK APART. THE STARTER FLANGE WAS CRACKED OFF ON BOTH THE FWD LT SIDE AND FWD RT SIDE AT A 45 DEGREE ANGLE. 1L71 3O3 O 2A13 E274 5 NP88614 20060203000962006020300096EA 2006 2 3 2006FA0000118 220060130G74144302 MAGNETO PIPER PA44 PA44180 7104402SO LYC O360 O360A1H 41514EA INOPERATIVE B O OTHER O OTHER ININSP/MAINT 1 GL21295ND861 4496030 RL74671A ON ENGINE INSPECTION RUN-UP MAGNETO RPM DROP NORMAL. WHEN MECHANIC ATTEMPTED TO CHECK TIMING, FOUND TIMING 20 DEGREES LATE. REMOVED AND DISASSEMBLED MAGNETO. FOUND DISTRIBUTOR CARBON BRUSH MISSING AND ROTOR SHAFT BROKEN AT BASE OF SLOT FOR POINT CAM. ALSO FOUND EXTENSIVE BURNING DAMAGE TO DISTRIBUTOR BLOCK CROSSBEAM AND ARCING DAMAGE TO COIL AND DISTRIBUTOR GEAR SHAFT. 1L72 3O3 O A19S0 E286 20060214001542006021400154CE 2006 2 14 2006FA0000119 120060130G5270631221160 SUPPORT BRACKET CESSNA525 525 2076601CE WILINTFJ44 FJ44 66000GL DOOR CRACKED B K NONE O OTHER ININSP/MAINT 1 GL09345MG1501 5250372 DURING INSPECTION FOUND THE RT ATTENUATOR PIVOT SUPPORT BRACKET CRACKED. THERE IS A SB (SB525-78-03 R1) THAT ADDRESSES THIS PROBLEM HOWEVER IT IS ONLY FOR SN PRIOR TO AND INCLUDING -0135. HAVE BEEN FINDING THIS CONDITION ON ALL 525S EVEN IF THE SB HAS BEEN ACCOMPLISHED. RECOMMEND THAT THE OEM REEVALUATES THIS AREA AND RE-ISSUE A SB TO CORRECT THE CONDITION. 1L72 4F4 FRTA1WI E3GL 20060202001482006020200148CE 2006 2 2 2006FA0000121 120060110G27200025240121 ARM BEECH 36 A36 1151604CE CONT O550 IO550* SO RUDDER PEDAL WORN B E81RO OTHER O OTHER NRNOT REPORTED 1 GL033224G1719 E2924 TROUBLESHOT STIFF RUDDER PEDAL STEERING AND REPLACED PILOTS RT ARM ASSY. PN 002-524012-1 WITH NEW IAW MM. APPEARS ARM ASSY ROLLER BEARING WAS NEVER LUBED DURING BUILD OF AIRCRAFT. THE ROLLER BEARING WEAR CAUSED THE ARM TO SEIZE ON THE RUDDER PEDAL TORQUE TUBE AT RANDOM TRAVEL POSITIONS. (K) 1L71 3O3 O 3A15 E3SO 20060214002352006021400235CE 2006 2 14 2006FA0000123 120060113G2800543003 MOUNT CESSNA206 U206F 2073333CE CONT O550 IO550* SO POWERPLANT CRACKED B HJBRK NONE O OTHER ININSP/MAINT 1 AL058419Q246 U20603279 DURING SCHEDULED INSPECTION FOUND THE FUEL FLOW TRANSDUCER MOUNT CRACKED COMPLETELY ACROSS ON ONE END. (K) 1H71 3O3 O A4CE E3SO 20060214002152006021400215EU 2006 2 14 2006FA0000125 120060111G575125W181001502 AILERON ISRAEL1125 ASTRASPX 4500205EU GARRTTTFE731TFE731* 01518WP UPPER SURFACE DELAMINATED B T77RK NONE F FLT CONT AFFECTED ININSP/MAINT 1 GL03918MJ6061 073 RT AILERON UPPER SKIN FOUND DELAMINATED FROM HONEYCOMB CORE. DELAMINATION COVERS MORE THAN 50 PERCENT OF UPPER SURFACE. AILERON REPLACED WITH SERVICEABLE UNIT. (K) 2L72 4F4 FRTA16NM E6WE 20060214002462006021400246EU 2006 2 14 2006FA0000126 120060126G5753T700A5755001000 FLAP SOCATATBM TBM700 8682000EU PWA PT6 PT6A64 EA IB FLAP END RIB EXCESS PLAY D K NONE F FLT CONT AFFECTED ININSP/MAINT 1 EA05704QD1752 188 FLAP SN SC279 WAS REMOVED FROM SERVICE FOR LOOSE ATTACHMENT INSERTS ON THE IB END RIB. THE FLAP ATTACH CARRIAGE WAS DISCOVERED LOOSE DURING A ROUTINE DAILY PPOST FLIGHT INSPECTION, WHERE PLAY WAS NOTED BETWEEN THE FLAP ATTACH CARRIAGE AND THE IB FLAP END RIB. IT SHOULD BE NOTED THAT ALL OPERATORS SHOULD PERFORM AN INSP IN FLAP ATTACH AREA BEFORE OPERATING AC. (K) 1L71 3T4 TRTA60EU E4EA 20060214002232006021400223EU 2006 2 14 2006FA0000127 120060110G5754F50B134000191B3 PLATE AMD FALC50FALCON900 2700160EU GARRTTTFE731TFE731* 01518WP OB SLATS CRACKED B M2MRK NONE F FLT CONT AFFECTED ININSP/MAINT 1 GL035731 008 SEAL CLAMPING PLATE IS CRACKING AND BREAKING OFF AT THE 6TH AND 7TH SCREWS, (FROM IB TO OB) ON THE INSIDE OF THE OB SLATS. SUBSEQUENT FOD DAMAGE TO THE NUT AND SAFETY WIRE OF THE BLEED AIR TUBE, AND ALSO THE LEADING EDGE OF THE WING BEHIND THE SLAT IS OCCURING DURING SLAT RETRACTION. (K) 2L73 4F4 FRTA46EU E6WE 20060214002242006021400224EU 2006 2 14 2006FA0000128 120060110G5754F50B144000191B3 PLATE AMD FALC50FALCON900 2700160EU GARRTTTFE731TFE731* 01518WP OB SLOTS CRACKED B M2MRK NONE F FLT CONT AFFECTED ININSP/MAINT 1 GL035731 008 SEAL CLAMPING PLATE IS CRACKING AND BREAKING OFF AT THE 6TH AND 7TH SCREWS, (FROM IB TO OB) ON THE INSIDE OF THE OB SLOTS. SUBSEQUENT FOD DAMAGE TO THE NUT AND SAFETY WIRE OF THE BLEED AIR TUBE, AND ALSO THE LEADING EDGE OF THE WING BEHIND THE SLAT IS OCCURRING DURING SLAT RETRACTION. (K) 2L73 4F4 FRTA46EU E6WE 20060214002042006021400204SO 2006 2 14 2006FA0000129 120060125G56001159SCB51021 WINDSHIELD GULSTMG1159 GIV 3980115SO RROYCETAY TAY6118 EU LT CRACKED B BTVRO OTHER O OTHER CRCRUISE 1 GL2349SL 1167 AIRCRAFT WAS FLYING AT 41,000 FT WHEN WINDSHIELD FAILED BY OVERHEATING AND CRACKING. PROBABLE CAUSE, HEATING ELEMENT FAILED THEN WINDSHIELD OUTER PLY FAILED. NO RECOMMENDATION TO PREVENT FAILURE. (K) 2L72 4F4 FRTA12EA E25NE 20060214002132006021400213CE 2006 2 14 2006FA0000132 120060130G56105111604200 WINDSHIELD CESSNA421 421C 2076016CE CONT O520 GTSIO520F 17032SO COCKPIT BLEW OUT B BA EMER. DESCENT UNSCHED LANDING D INFLIGHT SEPARATION CRCRUISE 1 SW01 6622 421C0426 DURING PRESSURIZED FLIGHT, AT 17000 FEET, THE RT SIDE WINDSHIELD CRACKED AND A MAJOR PORTION BLEW OUT. THE GLARESHIELD IS A ONE PIECE ASSY AND STAYED INTACT; THE RT SIDE REMAINED ATTACHED TO THE INSTRUMENT PANEL WHILE THE FASTENERS ON THE RT SIDE FAILED AND ALLOWED THE THAT HALF OF THE GLARESHIELD TO BE PULLED OUTSIDE. 1L72 3O3 O A7CE E7CE 20060214002362006021400236EA 2006 2 14 2006FA0000133 220060120G8510 CRANKCASE LYC 0320D3G PIPER PA28 PA28161 7102803SO LYC O320 O320D3G 41508EA SNSNCH74DM M74DM EA ENGINE BROKEN B K NONE S AFFECT SYSTEMS ININSP/MAINT 1 GL21263ND703 703 L1016739A 2842064 L1016739A A58041 BOTH FORWARD BOLT ATTACHMENT FLANGES WERE CRACKED OFF OF STARTER ATTACHMENT FLANGE ASSEMBLY. THIS CAUSED THE STARTER TO DROOP DOWNWARD WITH ONLY THE AFT BOLTS SUPPORTING THE STARTER. AS A RESULT, THE STARTER RING GEAR AND STARTER BENDIX WOULD NOT PROPERLY ENGAGE. THIS RESULTED IN THE TEETH OF THE BENDIX TO BREAK APART. THE STARTER FLANGE WAS CRACKED OFF ON BOTH THE FWD. LT SIDE AND FWD RT SIDE AT A 45 DEGREE ANGLE. 1L71 3O3 O 2A13 E274 5 NP88614 20060214001582006021400158CE 2006 2 14 2006FA0000134 120060131G7120051313211 ATTACH BRACKET CESSNA175 175 2072502CE CONT IO360 IO360* 17025CE MCAULY2A34C D2A34C* GL ENGINE MOUNT BROKEN G K NONE O OTHER LDLANDING 1 SW156612E 56112 THE AC EXPERIENCED A HARD LANDING. DURING THE LANDING THE 2 TOP ENGINE MOUNT ATTACH BRACKETS FAILED BEHIND THE FIREWALL, ALLOWING THE TOP HALF OF THE FIREWALL TO FAIL, PULLING FORWARD AND DOWN ABOUT 18 INCHES. PN 051313211 ENGINE MOUNT ATTACH BRACKET FITS ONTO THE FRONT OF HAT CHANNELS ITEM 6 AND 7. PN 051213211 WHICH HAS A HOLE IN IT FOR THE ENGINE MOUNT BOLT TO GO THROUGH, HAD FAILED (BROKEN IN 2 PIECES) SOME TIME AGO ON THE PILOTS TOP SIDE WITH RUST ON BOTH BRAKES. THE BRACKET ON THE CO-PILOTS TOP SIDE HAD AN EXISTING CRACK IN THE CENTER THIRD OF IT AT THE BOLT HOLE, RUST WAS ALSO ON THIS CRACK. (K) 1H71 3O3 ONT3A17 E1CE 5 CP3EA 20060217001002006021700100NM 2006 2 17 2006FA0000135 120060130G3210NAS14635 BOLT UNIVAR415 A2ALON 0540102NM CONT C90 C90* 17009SO MLG BROKEN D O OTHER O OTHER NRNOT REPORTED 1 EA135616F1515 A216 BOLT LOCATED TOP OF SPRING OF LANDING GEAR, 3 OF THESE BOLTS HOLD THE SPRING GEAR ON. ALL 3 BOLTS FAILED, RECOMMEND ALL 3 BOLTS IN BOTH MAIN GEAR REPLACED EACH, 1000 HRS TIME IN SERVICE. (EA13200602813) (K) 1L71 3O3 O A787 E252 20060217001012006021700101SO 2006 2 17 2006FA0000136 120060120G36101159SB42000044 LINE GULSTMG1159 GIV 3980115SO RROYCETAY TAY6118 EU PNEUMATIC SYS CHAFED B CW1RO OTHER O OTHER NRNOT REPORTED 1 EA11780E 1165 DURING A ENGINE CHANGE A PYLON INSPECTION WAS BEING PERFORMED. SPIRAL WRAP WAS NOTICED WORN. FURTHER INVESTIGATION REVEALED CHAFF ON HIGH TEMPERATURE BLEED AIR LINE MORE THAN 50 PERCENT THROUGH. (K) 2L72 4F4 FRTA12EA E25NE 20060208001592006020800159CE 2006 2 8 2006FA0000138 120060202G275099100554 MOTOR CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE TE FLAPS FAILED B OJ2RO OTHER O OTHER NRNOT REPORTED 1 CE07550VW 5500307 THE FLAP MOTOR EXPERIENCED AN OUT OF BOX FAILURE IMMEDIATELY AFTER INSTALL. THE MOTOR`S INTERNAL BRAKE MECHANISM MALFUNCTIONED IN A WAY TO NOT ALLOW IT TO RELEASE. THE PART WAS IN NO WAY AIRWORTHY AND MALFUNCTION SHOULD HAVE BEEN NOTICED AT THE REPAIR STATION DURNING THE FUNCTIONAL CHECK WHICH WAS SIGNED OFF BY THEM . 1L72 4F4 F A22CE E1NE 20060214002262006021400226SO 2006 2 14 2006FA0000139 120060119G5740402915 BOLT PIPER PA28 PA28R201 7102816SO LYC O360 IO360A1A 41514EA LT WING WORN B K NONE O OTHER ININSP/MAINT 1 GL21803ND11642 2837003 DURING PHASE INSPECTION LT AFT WING ATTACH BOLT WAS FOUND LOOSE. UPON FURTHER INSP IAW MFG SL 1087 THE HOLE WAS FOUND TO BE ELONGATED AND BOLT SHANK WORN. SL 1087 DOES NOT COVER THIS SN BUT DOES COVER MODEL. 1L71 3O3 O 2A13 1E10 20060411000292006041100029SO 2006 4 11 2006FA0000140 120060119G5740402915 ATTACH FITTING PIPER PA28 PA28R201 7102816SO LT WING DAMAGED B K NONE O OTHER ININSP/MAINT 1 GL21803ND11642 2837003 DURING PHASE INSPECTION LT AFT WING ATTACH BOLT WAS FOUND LOOSE. UPON FURTHER INSP AS PER PIPER SL 1087 THE HOLE WAS FOUND TO BE ELONGATED AND BOLT SHANK WORN. SL 1087 DOES NOT COVER THIS S/N BUT DOES COVER MODEL. 1L71 3O 2A13 20060217000802006021700080SO 2006 2 17 2006FA0000141 220060126G73146467672A1 PUMP BEECH 58 58 1152740CE CONT O550 IO550C SO FUEL SYS MALFUNCTIONED D O OTHER O OTHER NRNOT REPORTED 1 EA053214H1373 TH1731 824463R FUEL PUMP FAILED AFTER LANDING. ENGINE QUIT ON ROLL OUT. PUMP WOULD NOT PRODUCE ENOUGH PRESSURE TO SUSTAIN AN ENGINE RPM ABOVE IDLE. (K) 1L72 3O3 O 3A16 E3SO 20060214002442006021400244CE 2006 2 14 2006FA0000142 120060106G280005160167 VENT LINE CESSNA172 172N 2072434CE LYC O320 O320* 41508EA IB RT/LT RIB CHAFED D K NONE O OTHER NRNOT REPORTED 1 AL0373813 17267693 DEFECT WAS NOTED DURING SEB04-4, WHICH REQUIRED INSP OF FUEL HOSES IN OLDER PRODUCTION AC. IN ORDER TO INSPECT ALL LINES, HEADLINER IS REQUIRED TO BE PULLED. LINES IN QUESTION ARE LOCATED ABOVE DOORS IB OF LT AND RT FUSELAGE RIB. PROBLEM WAS CHAFING OF FUEL VENT LINE AGAINST REAR CABIN VENT HOSE. METAL IN CABIN HOSE RUBBED SURFACE OF FUEL VENT LINE TO PRODUCE 2 WEAR SPOTS, WHICH WHEN GENTLY PROBED WITH A SCRIBE PIERCED TUBING. POTENTIAL FOR THIS PROBLEM TO OCCUR IS ONLY ON AC THAT HAVE DUCTING FOR REAR VENTILATION. WEAR OF LINE COULD CAUSE FUMES TO ENTER CABIN AREA. ACCOMPLISHMENT OF SEB04-4 TO INCLUDE CHECKING FOR POSSIBLE CHAFING OF FUEL VENT LINE AGAINST REAR CABIN VENT HOSE OR OTHER COMPONENTS. (K) 1H71 3O3 ONT3A12 E274 20060214002002006021400200SO 2006 2 14 2006FA0000143 120060206G3220 CABLE AYRES S2RGHT65 AYRES S2 S2RHGT65 0970110SO TAIL WHEEL BINDING C K NONE W INADEQUATE Q C ININSP/MAINT 1 SO19 013DC AIRCRAFT TAIL WHEEL LOCKING / UNLOCKING MECHANISM NOT SATISFACTORY IAW PILOT'S REPORT. ANGLE OF CABLE AT POINT WHERE IT ATTACHES TO THE TAILWHEEL INTRODUCES BINDING. CABLE CLAMP USED DURING MANUFACTURE PINCHES END OF TELEFLEX CABLE AT MOUNTING POINT AND RESTRICTS MOVEMENT OF THE LOCK PIN ASSY. ATTENTION SHOULD BE PAID IN THE ASSEMBLY OF THE CABLE TO THE TAILWHEEL AS WELL AS IN THE DESIGN OF THE ATTACHING BRACKET ANGLES FOR PROPER CABLE RUN W/O BINDING. 1L71 3T NC 20060321000372006032100037SO 2006 3 21 2006FA0000144 120060206G3220 PIN AYRES S2 S2RHGT65 0970110SO TAILWHEEL LOCK MISMANUFACTURED C K NONE W INADEQUATE Q C ININSP/MAINT 1 SO19 013DC AIRCRAFT TAIL WHEEL LOCKING / UNLOCKING MECHANISH NOT SATISFACTORY PER PILOT'S REPORT. FOUND TAIL WHEEL LOCKING PIN OUTSIDE DIAMETER WAS NOT SUFFICIENT TO ALLOW THE LOCK PIN TO SLIDE WITHIN ITS HOUSING. A 1/4 TURN EITHER WAY FREED THE PIN. FURTHER, THE PART OF THE PIN THAT PROTRUDES INTO THE TAIL WHEEL CENTERING CAM WAS NOT SUFFICIENTLY ROUNDED OR TAPERED TO ALLOW A RAPID AND POSITIVE ENGAGEMENT. THE LOCK PIN IS CRITICAL TO THE SAFE LANDING OF THE AIRCRAFT IN GUSTY WIND CONDITIONS. 1L71 3T NC 20060216002352006021600235CE 2006 2 16 2006FA0000145 120060202G2597SPS321135 SWITCH BEECH MU300 400A 1155402CE PWA JT15 JT15D5 52112NE CABIN VIP SEAT OVERTEMP B UO2RO OTHER O OTHER NRNOT REPORTED 1 GL19119QS RK394 CREW SMELLED SMOKE/ODOR IN THE CABIN DURING FLIGHT. FOUND SLIGHT DISCOLORATION OF DUCT DUE TO AN OVERTEMP. NO DELAMINATION NOTED AND NO OTHER SIGN OF WIRING OR COMPONENT DAMAGE. WHILE TROUBLESHOOTING FOUND RELAY INSIDE OF VIP CABIN TEMP SWITCH PANEL THAT WAS DEFECTIVE, NOT ALLOWING COCKPIT CONTROL OF CABIN TEMP IN THE AUTO POSITION. PILOTS HAD TO SWITCH TO MANUAL MODE TO OVERRIDE VIP TEMP SWITCH PANEL. (K) 2H72 4F4 FRTA16SW E25EA 20060217000102006021700010SO 2006 2 17 2006FA0000146 120060119G5512 SKIN PIPER PA30 PA30 7103002SO LYC O320 IO320* 41508EA HORIZONTAL STAB BENT G A5ORO OTHER O OTHER NRNOT REPORTED 1 SO097368Y3234 30419 DURING INSP OF HORIZ STAB, FWD SPAR AND CTR SECTION SKIN WAS FOUND BENT, DISTORTED AT CENTER LIGHTENING HOLE. SKIN AND SPAR BOTH SHOWED SIGNS OF WRINKLING AND DEFORMATION. CLOSE INSP OF PARTS DID NOT SHOW ANY CRACKS. SPAR HAD BEEN REINFORCED WITH SPAR REINFORCEMENT AS REQUIRED BY SEB. STAB WAS REPAIRED USING A NEW FWD SPAR ASSY WITH REINFORCEMENT NEW CTR SECTION SKIN AND COMPLYING WITH SEB. PROBABLE CAUSE IS OVER STRESSING STAB BY FORCING TAIL DOWN TO MOVE AC ON GROUND. RECOMMEND PERSONNEL BE BRIEFED ON PROPER PROCEDURES FOR MOVING AC, MECHANICS CLOSELY INSPECT THIS AREA FOR DAMAGE. ALSO, RECOMMEND THAT SEB INSP OF FWD SPAR LIGHTENING HOLE AND SB INSP OF BOLT HOLES BE COMPLIED WITH AT NEXT ANNUAL INSP. 1L72 3O3 O A1EA 1E12 20060216001972006021600197CE 2006 2 16 2006FA0000156 120060213G5346051313211 ATTACH BRACKET CESSNA CESSNA175 175 2072502CE CONT O300 GO300* 17022SO FUSELAGE CRACKED D K NONE O OTHER ININSP/MAINT 1 CE079456B2417 55256 FOUND THE LT UPPER ENGINE MOUNT ATTACHMENT BRACKET CRACKED THROUGH ON THE IB SIDE. CRACK APPEARS TO HAVE ORIGINATED AT OUTER RADIUS OF WASHER THEN PROGRESSED UP AND DOWN THROUGH BRACKET. THIS INSPECTION WAS PROMPTED AFTER REPORTED FAILURE OF SAME BRACKET, SAME MAKE AND MODEL OF AIRCRAFT, THAT SUFFERED A PARTIAL ENGINE/FIREWALL SEPARATION DURING LANDING. 1H71 3O3 ONT3A17 E298 20060228000652006022800065CE 2006 2 28 2006FA0000157 120060222G5346051313211 BRACKET CESSNA175 175 2072502CE ENGINE MOUNT BENT D K NONE O OTHER ININSP/MAINT 1 CE079456B 55256 A REPLACEMENT 0513132-11 ENGINE MOUNT BRACKET WAS ORDERED TO REPLACE ONE FOUND CRACKED. THE JOGGLED FLANGE WAS INCORRECTLY FORMED. THE FLANGE WAS BENT OUTWARD TO THE POINT THAT IT WOULD NOT FIT IN THE AIRCRAFT. 1H71 3O NT3A17 20060224001802006022400180CE 2006 2 24 2006FA0000159 120060130G2170728802 WATER SEPARATOR CESSNA650 650 2076802CE A/C BAY SEPARATED B O OTHER O OTHER NRNOT REPORTED 1 SW05766MH 6500015 EXPERIENCED AN ABRUPT CABIN PRESS FLUCTUATION DURING FLT. FLT CREW REPORTED, ABLE TO MAINTAIN CABIN ALT WITHIN LIMITS AFTER NOTICED PROBLEM. AFTER THIS A/C LANDED MX PERSONNEL DISCOVERED ONE OF THE ENVIRONMENTAL CONTROL SYS WATER SEPARATOR UNITS HAD SEPARATED DURING FLT. AFFECTED WATER SEPARATOR IS MANUF WITH A CLAMP FLANGE (WHERE THE MAIN V-BAND THAT ALLOWS DISASSEMBLY OF THE UNIT FOR SERVICING IS INSTALLED) THAT IS BONDED TO FWD AND AFT SECTIONS OF UNIT. BONDING MAT`L HAD APPARENTLY LOST ABILITY TO KEEP FLANGE ADHERED TO BODY OF UNIT ALLOWING UNIT TO SEPARATE AND CAUSE LOSS OF PRESS.. 2L72 4F A9NM 20060228000082006022800008NM 2006 2 28 2006FA0000160 120060201G2782 GREASE FITTING ISRAEL ISRAEL1125 1125 NM LE SLAT ACTUATORLEAKING C O OTHER K FLUID LOSS NRNOT REPORTED 1 SW99 1820 080 DURING NORMAL GREASING OPERATION, THE GREASE BALL DID NOT RESET TO THE CLOSED POSITION, ALLOWING GREASE TO FLOW OUT OF THE ACTUATOR. 2L72 4F RTA16NM 20060227002542006022700254EA 2006 2 27 2006FA0000161 220060209G7310 FUEL PIPER PA28 PA28R201 7102816SO LYC O360 IO360C1C6 41514EA FUEL TANK CONTAMINATED B K NONE O OTHER UKUNKNOWN 1 GL21384ND 2844095 L3081251A BROWNISH FUEL WAS DETECTED FROM THE FUEL GASCOLATOR. AFTER TROUBLESHOOTING IT WAS DETERMINED THAT THE BROWNISH FUEL COLOR PRESENT IN THE FUEL SYSTEM. 1L71 3O3 O 2A13 1E10 20060227001472006022700147GL 2006 2 27 2006FA0000162 120060207G3210 PIN DIAMONDA20 DA20C1 2990001GL MLG BACKED OUT D K NONE O OTHER ININSP/MAINT 1 NM03915AF C0149 ROLL PIN LOCKING THE NOSE STRUT ELASTOMERIC SPRING PLATE (PN 20-3220-05-02) TO THE SHOCK ABSORBER ROD (PN 20-3220-05-01) HAD WORKED OUT UNLOCKING THE ASSY. 1L71 3O NTTA4CH 20060228000322006022800032EA 2006 2 28 2006FA0000164 220060207G7421UREM40E SPARK PLUG CESSNA172 172N 2072434CE LYC O360 O360A4M 41514EA ENGINE DEFECTIVE B A5ORO OTHER O OTHER NRNOT REPORTED 1 SO096372D 17272758 DURING THE INSTALLATION AND OPS CHECK OF 2 NEW MAGNETOS, HARNESS AND 8 SPARK PLUGS TO CORRECT A HARD STARTING DISCREPANCY, THE ENGINE HAD A 200 TO 300 RPM MAGNETO DROP O THE LT MAGNETO. TROBLESHOT THE IGNITION SYSTEM USING A COLD CYLINDER TESTER AND DETERMINED THAT 1 OF 8 SPARK PLUGS WAS DEFECTIVE. SEEMS TO BE A TREND OF BAD SPARK PLUGS BEING SHIPPED BY MFG. REMOVED DEFECTIVE SPARK PLUG AND REPLACED WITH A KNOWN GOOD SPARK PLUG AND ENGINE OPS CHECKED GOOD. SPARK PLUGS WERE REPLACED AT TIME OF MAGNETO AND HARNESS CHANGE. ALL OF THIS BECAUSE OF POOR QUALITY CONTROL. (K) 1H71 3O3 ONT3A12 E286 20060228000062006022800006GL 2006 2 28 2006FA0000165 120060214G3220PAF18220P11 BUSHING DIAMONDA40 DA40 2990002GL LYC O360 IO360A1A 41514EA NLG STRUT MISALIGNED B UV6SK NONE O OTHER ININSP/MAINT 1 NM07100UV454 40405 THIS ADDRESSES A CONDITION OF EXCESSIVE (0.085 INCHES) CLEARANCE BETWEEN A BUSHING AT THE BOTTOM OF THE NLG SHOCK STRUT (ITEM NR 290, PN PAF18220P11, FIG .01, CH 32-20-02, IPC) AND THE SHOCK STRUT CENTER ROD (ITEM NR 210, PN D41-3223-20-33B). THIS CLEARANCE ALLOWS THE END FITTING (ITEM NR 310) TO SLOPE APPROX. 10 DEGREES TO ONE SIDE. THIS RESULTS IN THE BOTTOM ELASTOMERIC DONUT TAKING ON A WEDGE SHAPE AND THE SHOCK LOADS BEING TRANSMITTED OFF THE CENTERLINE OF THE NLG SHOCK STRUT. (K) 1L71 3O3 ONTA47CE 1E10 20060228000502006022800050GL 2006 2 28 2006FA0000166 120060214G3220PAF18220P11 BUSHING DIAMONDA40 DA40 2990002GL LYC O360 IO360A1A 41514EA NLG STRUT WORN B UV6SO OTHER O OTHER NRNOT REPORTED 1 NM07834DS1963 40034 REPORT ADDRESSES A CONDITION OF EXCESSIVE (0.085 INCHES) CLEARANCE BETWEEN A BUSHING AT THE BOTTOM OF THE NLG SHOCK STRUT (ITEM NR 290, PN PAF18220P11, FIG 01, CH 32-20-02, IPC) AND THE SHOCK STRUT CENTER ROD (ITEM NR 210, PN D41-3223-20-33B). THIS CLEARANCE ALLOWS THE END FITTING (ITEM NR 310) TO SLOPE APPROX. 10 DEGREES TO ONE SIDE. THIS RESULTS IN THE BOTTOM ELASTOMERIC DONUT TAKING ON A WEDGE SHAPE AND THE SHOCK LOADS BEING TRANSMITTED OFF THE CENTERLINE OF THE NLG SHOCK STUT. (K) 1L71 3O3 ONTA47CE 1E10 20060228000332006022800033EA 2006 2 28 2006FA0000167 220060203G8530751868 CYLINDER HEAD PIPER PA23 PA23250 7102308SO LYC O540 IO540C4B5 41532EA NR 2 CYLINDER SEPARATED E GB7AO OTHER O OTHER NRNOT REPORTED 1 EA1362BA 8566 1752 274859 CYLINDER HEAD SEPARATED FROM CYLINDER FOR REASONS UNKNOWN. (K) 1L72 3O3 O 1A10 1E4 20060228000042006022800004CE 2006 2 28 2006FA0000168 120060216G323326900127 ACTUATOR CESSNA500 500CESSNA 2076602CE PWA JT15 JT15D1 52060NE NLG LEAKING D O OTHER O OTHER NRNOT REPORTED 1 SO11502BE 5000195 HYDRAULIC LEAK AT SWITCH ACTUATOR ENTRY INTO NLG ACTUATOR AT 231 CYCLES INSTALLED AND 4224 CYCLES SOH/NEW. DEPELETED HYDRAULIC SYSTEM ON LANDING. (K) 1L72 4F4 F A22CE E1NE 20060228000222006022800022EU 2006 2 28 2006FA0000169 120060210G8097Z00NN6024017227 ELECTRICAL BOX SOCATATBM TBM700 8682000EU PWA PT6 PT6A64 EA HARTZLHCE4N HCE4N3 NE STARTER OVERHEATED D O OTHER B SMOKE/FUMES/ODORS/SPARKS TXTAXI/GRND HDL 1 EA17704QD 1280 188 PCEPM0073 HH463 DURING THE START SEQUENCE WHEN THE PILOT SELECTED THE START POSITION THE STARTER WOULD NOT RESPOND. THE PILOT COULD HEAR THE SOUND OF RELAY CONTACTS BUT THE STARTER WOULD NOT RESPOND. THE AIRCRAFT WAS EXAMINED BY A LINE TECHNICIAN WHO REPORTED THE ELECTRICAL MASTER SMELLED OVERHEATED AND BURNED. THE UNIT WAS REMOVED, OVERHEATING. REPLACEMENT UNIT OF THE SAME PN WAS INSTALLED AND THE STARTER AND ELECTRICAL SYSTEM FUNCTIONED NORMALLY. (K) 1L71 3T4 TRTA60EU E4EA 5 CP10NE 20060228000052006022800005 2006 2 28 2006FA0000170 120060217G8011MZ4212 STARTER ENGINE SEIZED B WS9RO OTHER O OTHER NRNOT REPORTED 1 NM07 STARTER SEIZED DURING START UP. (K) 20060228000522006022800052 2006 2 28 2006FA0000171 120060217G8011ES6462382 STARTER ENGINE CONTAMINATED B WS9RO OTHER O OTHER NRNOT REPORTED 1 NM07 10 WAX FROM ELECTRICAL WINDING IS SEEPING THROUGH THE PLATE. (K) 20060228000442006022800044 2006 2 28 2006FA0000172 120060210G2420ALX9525B ALTERNATOR ENGINE MISMANUFACTURED B KC2RO OTHER O OTHER NRNOT REPORTED 1 GL03 THIS ALTERNATOR HAS 0-HOURS TIME IN SERVICE SINCE OVERHAUL ON W/O M039030. IN PREPARING THIS UNIT FOR INSTALLATION ON AIRCRAFT, EXCESSIVE SIDE PLAY OF ROTOR SHAFT WAS NOTED. DISASSEMBLY OF THE UNIT REVEALED THAT THE DRIVE-END BEARING BORE WAS .015 INCH OVERSIZE AND THE BEARING WAS VERY LOOSE IN THE BORE. THIS END FRAME SHOULD HAVE BEEN REJECTED DURING THE OVERHAUL PROCESS DUE TO THE EXCESSIVE WEAR OF THE BEARING BORE. RECOMMENDATIONS WOULD INCLUDE CLOSER INSPECTION OF THE BEARING BORE DIMENSIONS DURING THE OVERHAUL PROCESS. THIS UNIT WILL BE RETURNED TO BE INSPECTED AND WARRANTY REPLACED BY OVERHAULER. (K) 20060228000412006022800041CE 2006 2 28 2006FA0000173 120060213G28200020200005A LINE BEECH 58 58 1152740CE CONT O550 IO550C SO MCAULY3AF32C3AF32C512 GL FUEL SYS WORN D O OTHER O OTHER NRNOT REPORTED 1 EA17202P 3255 TH1875 THE CROSS FEED LINE PN 002-92000-51 WAS IMPROPERLY MANUFACTURED WHICH CAUSED THE RT LANDING GEAR DRIVE TUBE TO CONTACT, AND ABRADE THE LINE DURING LANDING GEAR RETRACTION. THE ABRASION HAD PROGRESSED TO THE POINT THAT ONLY 10 PERCENT OF THE WALL THICKNESS REMAINED. THE REPLACEMENT LINE PN HAS BEEN MANUFACTURED TO ALLOW GREATER CLEARANCE WITH THE LANDING GEAR DRIVE TUBE. IT IS RECOMMENDED THAT THE CLEARANCE BETWEEN THE CROSS FEED LINE AND THE DRIVE TUBE BE CHECKED. (K) 1L72 3O3 O 3A16 E3SO 5 CP22EA 20060228000312006022800031 2006 2 28 2006FA0000174 420060216G310070265421901 COMPUTER GULSTMGV GV 3980116SO RROYCEBR700 BR700710A110 NE FAILED B VU2RO OTHER G MULTIPLE FAILURE NRNOT REPORTED 1 GL055PG 340 5046 DURING A RECENT FLIGHT DISPLAY UNITS 1,2, AND 3 BLINKED ON AND OFF. DISPLAY UNITS 1, 2 CYCLED ON AND OFF DISPLAY UNIT 3 WAS RED X`D. DURING THAT TIME AN AMBER (MAU 3A FAIL) MESSAGE DISPLAYED AND A BLUE (DATABASE CONFIG) MESSAGE ALSO DISPLAYED. AFTER 5-8 SECOUNDS, ALL DISPLAY UNITS RETURNED TO NORMAL. AFTER 10 SECONDS THE MESSAGES WENT AWAY. THE FAULT HISTORY WAS DOWNLOADED AND SENT TO MFG. THE NIC/PROC NR5 MODULE WAS REPLACED IAW MFG DIRECTION. CERT CHARLIE (ASC 904) WAS INSTALLED WHICH ADDED THE AUTO REVERSION OF THE DISPLAY UNITS IN CASE OF A FAILURE OPERATOR FEELS THIS IN CONJUNCTION WITH A BAD NIC/PROC NR5 CAUSED THE BLINKING OF THE DISPLAYS. 2L72 4F4 FRTA12EA E00057EN 20060228000092006022800009 2006 2 28 2006FA0000175 120060206G3246 WHEEL MLG FAILED C O OTHER O OTHER NRNOT REPORTED 1 SW99 MAIN WHEEL FAILURE. 20060228000632006022800063SW 2006 2 28 2006FA0000176 120060215G7810PFS16201 EXHAUST PORT MOONEYM20 M20J 5870219SW LYC O360 IO360A1A 41514EA NR 4 BROKEN B ZKGRO OTHER O OTHER NRNOT REPORTED 1 NE05799EC121 240920 INSTALLED POWER FLOW SYSTEMS EXHAUST STC NR SA02871AT AT TACH TIME 4646.93, AT TACH TIME 4768.70 THE NR 4 EXHAUST PORT HAD BROKE FREE OF MUFFLER. (K) 1L71 3O3 O 2A3 1E10 20060228000212006022800021SO 2006 2 28 2006FA0000183 220060203G8520AEC631475 PISTON BEECH 33 E33A 1151424CE CONT O520 IO520BA 17032SO ENGINE DAMAGED B MW2RO OTHER O OTHER NRNOT REPORTED 1 GL171069F CE230 1218098BA ALL 6 PISTON SKIRTS HITTING CASE. ALL PISTON DAMAGE BEYOND REPAIR. (K) 1L71 3O3 O 3A15 E5CE 20060228000772006022800077GL 2006 2 28 2006FA0000185 120060215G270011169002 TORQUE TUBE CIRRUSSR SR22 2130001GL CONT O550 IO550N 17042SO MCAULYD3A34 D3A34C401 GL FLT CONTROLS WORN D K NONE O OTHER ININSP/MAINT 1 EA07150X 315 0813 917119 030521 INSPECTED THE FLIGHT CONTROL SYS IAW SB AND FOUND FREE PLAY AT THE TORQUE TUBE/ END FITTING INTERFACE ON BOTH SIDES. THE RT SIDE WAS MOR PRONOUNCED THAN THE LT. MFG CONSIDERS THIS SB TO BE OPTIONAL, HOWEVER THE CONTINUED USE WITH THIS DEFECT WILL RESULT IN THE BOLT HOLWS IN THE TORQUE TUBES CONTINUING TO ELONGATE AND EXACERBATING THE PROBLEM. AS LONG AS THIS IS CONSIDERED OPTIONAL, CUSTOMERS WON`T PAY FOR REPAIRS UNTIL IT IS DETERMINED TO BE AN AIRWORTHINESS ISSUE. (K) 1L71 3O3 ONTA00009CHE3SO 5 CP47GL 20060228000782006022800078GL 2006 2 28 2006FA0000186 120060215G270011168002 TORQUE TUBE CIRRUSSR SR22 2130001GL CONT O550 IO550N 17042SO MCAULYD3A34 D3A34C401 GL FLT CONTROLS WORN D K NONE O OTHER ININSP/MAINT 1 EA07150X 315 0813 917119 030521 INSPECTED THE FLIGHT CONTROL SYSTEM IAW SB AND FOUND FREE PLAY AT THE TORQUE TUBE/ END FITTING INTERFACE ON BOTH SIDES. THE RIGHT SIDE WAS MORE PORNOUNCED THAN THE LEFT. MFG CONSIDERS THIS SB TO BE OPTIONAL, HOWEVER THE CONTINUED USE WITH THIS DEFECT WILL RESULT IN THE BOLT HOLES IN THE TORQUE TUBES CONTINUING TO ELONGATE AND EXACERGBATING THE PROBLEM. AS LONG AS THIS IS CONSIDERED OPTIONAL, CUSTOMER WON`T PAY FOR REPAIRS UNTIL IT IS DETERMINED TO BE AN AIRWORTHINESS ISSUE. (K) 1L71 3O3 ONTA00009CHE3SO 5 CP47GL 20060228000382006022800038EU 2006 2 28 2006FA0000187 120060221G2741 COVER ISRAEL1124 1124A 4500103EU GARRTTTFE731TFE731* 01518WP ACTUATOR MISSING B GSPRK NONE W INADEQUATE Q C ININSP/MAINT 1 WP05411HB 02834AA 419 WHILE PERFORMING A 200 HOUR INSPECTION ON THIS AIRCRAFT, THE TAIL SECTION FAIRINGS AND PANELS WERE REMOVED. THE PITCH TRIM ACTUATOR WAS FOUND WITH THE DUST SHIELD DOWN AGAINS THE MOTOR HOUSING. IT WAS OBVIOUS THAT THE TIE BOLT HAD BEEN REMOVED, DUST SHIELD LOWERED AND THE TIE BOLT REINSTALLED WITHOUT THE DUST SHIELD IN PLACE. A PREVIOUS FATALITY CRASH HAS OCCURED DUE TO THE SAME INSPECTION BEING PERFORMED AND THE TIE BOLT INCORRECTLY INSTALLED. THIS INSPECTION AND PROCEDURE SHOULD BE REMOVED FROM GUIDE AND BEFORE SOME CAUSES THE SAME PROBLEM AGAIN. THIS INSPECTION SHOULD ONLY BE PERFORMED BY OEM, TOO CRITICAL FOR THE FIELD. (K) 2M72 4F4 F A2SW E6WE 20060228000422006022800042NE 2006 2 28 2006FA0000188 120060216G2820 O-RING SKRSKYS76 S76A 8143006NE ALLSN 250C 250C30S 03013GL FUEL DIST CORRODED B Y3ARK NONE O OTHER ININSP/MAINT 1 SW03376AL 760002 FOUND O-RING AREA PITTED UPON REMOVAL. SEVERAL TUBES IN FUEL SUPPLY SYS ALSO FOUND PITTED IN O-RING AND B-NUT AREA. NO LEAKS FOUND. FOUND DURING ROUTINE MAINTENANCE. (K) 1G72 3U3 U H1NE E1GL 20060228000432006022800043NE 2006 2 28 2006FA0000189 120060216G2820 O-RING SKRSKYS76 S76A 8143006NE ALLSN 250C 250C30S 03013GL FUEL DIST CORRODED B Y3ARK NONE O OTHER ININSP/MAINT 1 SW03376AL 760002 FOUND O-RING AREA PITTED UPON REMOVAL. SEVERAL TUBES IN FUEL SUPLY SYS ALSO FOUND PITTED IN O-RING AND B-NUT AREA. NO LEAKS FOUND. FOUND DURING ROUTINE MAINTENANCE. (K) 1G72 3U3 U H1NE E1GL 20060228000402006022800040NE 2006 2 28 2006FA0000190 120060216G2820 O-RING SKRSKYS76 S76A 8143006NE ALLSN 250C 250C30S 03013GL FUEL DIST CORRODED B Y3ARK NONE O OTHER ININSP/MAINT 1 SW03376AL 760002 FOUND O-RING AREA PITTED UPON REMOVAL. SEVERAL TUBES IN FUEL SUPPLY SYS ALSO FOUND PITTED IN O-RING AND B-NUT AREA. NO LEAKS FOUND. FOUND DURING ROUTINE MAINTENANCE. (K) 1G72 3U3 U H1NE E1GL 20060228000392006022800039NE 2006 2 28 2006FA0000191 120060216G2820 O-RING SKRSKYS76 S76A 8143006NE ALLSN 250C 250C30S 03013GL FUEL SYSTEM CORRODED D Y3ARK NONE O OTHER ININSP/MAINT 1 SW03376AL 760002 FOUND O-RING AREA PITTED UPON REMOVAL. SEVERAL TUBES IN FUEL SUPPLY SYS ALSO FOUND PITTED IN O-RING AND B-NUT AREA. NO LEAKS FOUND. FOUND DURING ROUTINE MAINTENANCE. (K) 1G72 3U3 U H1NE E1GL 20060228000102006022800010CE 2006 2 28 2006FA0000192 120060209G5710S3461111 BOLT CESSNA172 172S 2072439CE LYC IO360 IO360L2A EA MCAULY1A170 1A170E GL WING DAMAGED D O OTHER O OTHER NRNOT REPORTED 1 EA25410BS49 172S9966 23016 3220351E DURING FIRST PHASE INSPECTION (49 HOURS SINCE NEW)FOUND LEFT WING TO UPPER STRUT BOLT HEAD DAMAGED FROM FACTORY, APPARENTLY INSTALLED WITH VISE-GRIP TYPE TOOL. NO TORQUE SEAL FOUND ON NUT. DAMAGE EXTENSIVE ENOUGH THAT TORQUE COULD NOT BE CHECKED WITH SOCKET. PHOTOS AVAILABLE. (S3461-111 REPLACES AN8-25A.) 1H71 3O3 ONT3A12 1E10 5 NP857 20060228000112006022800011CE 2006 2 28 2006FA0000193 120060209G5710S3461111 BOLT CESSNA172 172S 2072439CE LYC IO360 IO360L2A EA MCAULY1A170 1A170E GL ZONE 500 DAMAGED D O OTHER O OTHER NRNOT REPORTED 1 EA25410BS49 172S9966 23016 3220351E DURING FIRST PHASE INSPECTION (49 HOURS SINCE NEW)FOUND LEFT WING TO UPPER STRUT BOLT HEAD DAMAGED FROM FACTORY, APPARENTLY INSTALLED WITH VISE-GRIP TYPE TOOL. NO TORQUE SEAL FOUND ON NUT. DAMAGE EXTENSIVE ENOUGH THAT TORQUE COULD NOT BE CHECKED WITH SOCKET. PHOTOS AVAILABLE. (S3461-111 REPLACES AN8-25A.) 1H71 3O3 ONT3A12 1E10 5 NP857 20060227002992006022700299 2006 2 27 2006FA0000194 420060205G31607018704902 POWER SUPPLY HONEYWELL DU870 DORNERDO32 DO328300 NM PWA 306 PW306B NE DISPLAY UNIT FAILED B A UNSCHED LANDING O OTHER CRCRUISE 1 SO13402FJ9021 00077031 3147 HONEYWELL DU-870 EFIS DISPLAY UNIT FAILURE IN FLIGHT. HONEYWELL PN:7014300-902. 2H72 4T4 FRTA55NM E35NE 20060227002572006022700257 2006 2 27 2006FA0000195 420060205G31607018704902 POWER SUPPLY HONEYWELL DU870 DORNERDO32 DO328300 NM PWA 306 PW306B NE DISPLAY UNIT FAILED B A UNSCHED LANDING O OTHER CRCRUISE 1 SO13402FJ9021 00077031 3147 HONEYWELL DU-870 EFIS DISPLAY UNIT FAILURE IN FLIGHT. HONEYWELL PN:7014300-902. 2H72 4T4 FRTA55NM E35NE 20060227002582006022700258 2006 2 27 2006FA0000196 420060205G31607018704902 POWER SUPPLY HONEYWELL DU870 DORNERDO32 DO328300 NM PWA 306 PW306B NE DISPLAY UNIT FAILED B A UNSCHED LANDING O OTHER CRCRUISE 1 SO13402FJ9021 00077031 3147 HONEYWELL DU-870 EFIS DISPLAY UNIT FAILURE IN FLIGHT. HONEYWELL PN:7014300-902. 2H72 4T4 FRTA55NM E35NE 20060227003002006022700300 2006 2 27 2006FA0000197 420060205G31607018704902 POWER SUPPLY HONEYWELL DU870 DORNERDO32 DO328300 NM PWA 306 PW306B NE DISPLAY UNIT FAILED B A UNSCHED LANDING O OTHER CRCRUISE 1 SO13402FJ9021 00077031 3147 HONEYWELL DU-870 EFIS DISPLAY UNIT FAILURE IN FLIGHT. HONEYWELL PN:7014300-902. 2H72 4T4 FRTA55NM E35NE 20060227003012006022700301GL 2006 2 27 2006FA0000198 120060210G2460 ELECTRICAL BOX CIRRUSSR SR22 2130001GL CONT O550 IO550N 17042SO ELECTRICAL SYS FAULTY G O OTHER S AFFECT SYSTEMS NRNOT REPORTED 1 EA25 OPERATOR REPORTS THREE CASES OF UNCOMMANDED ENGINE STARTER ENGAGEMENT. IN TWO CASES, STARTER ENGAGED WHEN THE BATTERY MASTER WAS TURNED ON. IN THE THIRD CASE, OPERATOR STATES THAT THE SHIP'S BATTERY CAME ON LINE UNCOMMANDED AND THAT STARTER CONCURRENTLY ENGAGED UNCOMMANDED. IN ALL THREE CASES, REPLACEMENT OF THE AIRCRAFT POWER DISTRIBUTION BOX RECTIFIED THE PROBLEM. 1L71 3O3 ONTA00009CHE3SO 20060228000142006022800014 2006 2 28 2006FA0000199 420060205G31607018704902 POWER SUPPLY HONEYWELL DORNERDO32 DO328300 NM PWA 306 PW306B NE DISPLAY FAILED G A UNSCHED LANDING O OTHER CRCRUISE 1 SO13402FJ 00077031 3147 DU-870 DISPLAY UNIT REFERENCE FAILED DURING FLIGHT. THE COMPONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY. 2H72 4T4 FRTA55NM E35NE 20060228000672006022800067SO 2006 2 28 2006FA0000201 120060220G5610 WINDOW PIPER PA24 PA24250 7102404SO COCKPIT INFLT SEPARATIONG BA EMER. DESCENT UNSCHED LANDING D INFLIGHT SEPARATION CRCRUISE 1 NM04456P 243276 PILOTS SIDE WINDOW PARTIALLY POPPED OUT AT 19,000 FEET. PRESSURIZATION ISSUES RESULTED IN EMERGECY DECENT. OPERATOR NOTIFIED KIT MANUFACTURER. 1L71 3O 1A15 20060317000482006031700048CE 2006 3 17 2006FA0000202 120060221G812020591 TURBOCHARGER CESSNA414 414 2075908CE CONT O520 TSIO520NB 17040SO ENGINE DISINTEGRATED B J7BRO OTHER O OTHER ININSP/MAINT 1 SW014243C 4140539 R20836872J TURBOCHARGER CAME APART INTERNALLY RESULTING IN LOSS OF MANIFOLD PRESSURE AND ENGINE METAL CONTAMINATION. ENGINE REMOVED FROM SERVICE. (K) 1L72 3O3 ORTA7CE E8CE 20060317000602006031700060CE 2006 3 17 2006FA0000203 120060131G7120SB997102 TUBE CESSNA172 172S 2072439CE LYC IO360 IO360L2A EA ENGINE MOUNT CHAFED D K NONE O OTHER ININSP/MAINT 1 WP075273U 172S9193 L3050951A DURING 100 HOUR/ANNUAL INSPECTION FOUND THE ENGINE OIL DIPSTICK CHAFING SLIGHTLY ON THE ENGINE MOUNT. INSPECTED FOR DAMAGE, ONLY PROBLEM NOTED WAS PAINT WAS CHAFED. THIS PROBLEM WAS SUPPOSED TO HAVE BEEN TAKEN CARE OF BY THE FACTORY PRIOR TO THIS SN AIRCRAFT. ENGINE OIL FILLER TUBE TO ENGINE MOUNT CLEARANCE, WAS ISSUED TO TAKE CARE OF EARLIER SN AIRCRAFT. THIS AIRCRAFT EVIDENTLY DID NOT GET THE CORRECT HARDWARE AT MANUFACTURER. INSTALLED CORRECT PARTS IAW TE IPC FOR THIS SN AIRCRAFT. (K) 1H71 3O3 ONT3A12 1E10 20060317000582006031700058CE 2006 3 17 2006FA0000204 120060121G57101019800387 COVER BEECH 300 300BEECH 1152930CE PWA PT6 PT6A60A 52043NE WINGS CHAFED B EWGRK NONE O OTHER ININSP/MAINT 1 SO056812W5952 FA38 COVER IS CHAFING LOWER FWD LT AND RT WING ATTACH PORT SPART CAP AND WING SKIN. THE COVER HAS NO ANTI-CHAFE PROTECTION. RECOMMEND RUBBER EDGE SEAL OR FAY SEALED EDGE TO AVOID METAL TO METAL CONTACT WITH SPAR AND WING SKIN. (K) 2L72 4T4 T A24CE E4EA 20060406002122006040600212CE 2006 4 6 2006FA0000205 120060221G30001019800388 COVER BEECH 300 300BEECH 1152930CE PWA PT6 PT6A60A 52043NE WINGS CHAFED B EWGRK NONE O OTHER ININSP/MAINT 1 SO056812W FA38 COVER IS CHAFING LOWER FWD LT AND RT WING ATTACH POINT, SPAR CAP AND WING SKIN. THE COVER HAS NO ANTI-CHAFE PROTECTION. RECOMMEND RUBBER EDGE SEAL OR FAY SEALED EDGE TO AVOID METAL TO METAL CONTACT WITH SPAR AND WING SKIN. (K) 2L72 4T4 T A24CE E4EA 20060406001782006040600178CE 2006 4 6 2006FA0000206 120060221G57201019800387 COVER BEECH 300 300BEECH 1152930CE PWA PT6 PT6A60A 52043NE WINGS CHAFED B EWGRK NONE O OTHER ININSP/MAINT 1 SO0579TE 5991 FA67 COVER IS CHAFING LOWER FWD LT AND RT WING ATTACH POINT, SPAR CAP AND WING SKIN. THE COVER HAS NO ANTI-CHAFE PROTECTION. RECOMMEND RUBBER EDGE SEAL OR FAY SEAL EDGE TO AVOID METAL TO METAL CONTACT WITH SPAR AND WING SKIN. (K) 2L72 4T4 T A24CE E4EA 20060323002052006032300205CE 2006 3 23 2006FA0000207 120060221G30001019800388 COVER BEECH 300 300BEECH 1152930CE PWA PT6 PT6A60A 52043NE WING CHAFED B EWGRK NONE O OTHER ININSP/MAINT 1 SO0579TE 5991 FA67 COVER IS CHAFING LOWER FWD LT AND RT WING ATTACH POINT SPAR CAP AND WING SKIN. THE COVER HAS NO ANTI-CHAFE PROTECTION. RECOMMEND RUBBER EDGE SEAL OR FAY SEAL EDGE TO AVOID METAL TO METAL CONTACT WITH SPAR AND WING SKIN. (K) 2L72 4T4 T A24CE E4EA 20060406001852006040600185CE 2006 4 6 2006FA0000208 120060221G57201019800387 COVER BEECH 300 300BEECH 1152930CE PWA PT6 PT6* 52043EA WINGS CHAFED B EWGRK NONE O OTHER ININSP/MAINT 1 SO05103CW4080 FA64 COVER IS CHAFING LWR FWD LT AND RT WING ATTACH POINT SPAR CAP AND WING SKIN. THE COVER HAS NO ANTI-CHAFE PROTECTION. RECOMMEND RUBBER EDGE SEAL OR FAY SEAL EDGE TO AVOID METAL TO METAL CONTACT WITH SPAR WING SKIN. (K) 2L72 4T3 T A24CE E2NE 20060317000512006031700051CE 2006 3 17 2006FA0000209 120060221G30001019800388 COVER BEECH 300 300BEECH 1152930CE PWA PT6 PT6* 52043EA WINGS CHAFED B EWGRK NONE O OTHER ININSP/MAINT 1 SO05103CW4082 FA64 COVER IS CHAFING LOWER FWD LT AND RT WING ATTACH POINT SPAR CAP AND WING SKIN. THE COVER HAS NO ANTI-CHAFE PROTECTION. RECOMMEND RUBBER EDGE SEAL OR FAY SEAL EDGE TO AVOID METAL TO METAL CONTACT WITH SPAR AND WING SKIN. (K) 2L72 4T3 T A24CE E2NE 20060316001172006031600117SO 2006 3 16 2006FA0000210 120060228G3520P24029 SWITCH GULSTMG1159 GIV 3980115SO RROYCETAY TAY6118 EU FUSELAGE FAILED D O OTHER JN WARNING INDICATION FALSE WARNING TXTAXI/GRND HDL 1 NM09941AM1179 1499 PILOTS RECEIVED PAX OXY OFF MESSAGE BEFORE TAXI OUT, INDICATING LESS THAN 50 PSI IN PASSENGER OXYGEN BOTTLE SYSTEM. VERIFIED PAX BOTTLES WERE TURNED ON AND PRESSURES WERE READING NORMAL AT BOTTLES AND COCKPIT INDICATORS. VERIFIED FLOW FROM THERAPEUTIC OXYGEN PORT AS THIS UTILIZES PASSENGER BOTTLES. TROUBLESHOT INDICATION SYSTEM AND FOUND FAILED SWITCH, IDENTIFIER 95S4. WIRING WAS OK. SWITCH WAS REPLACED WITH NEW UNIT. INDICATION THEN NORMAL. 2L72 4F4 FRTA12EA E25NE 20060404001752006040400175SO 2006 4 4 2006FA0000211 120060211G32101159H5020085 LINE GULSTMGV GULFSTREAMGV3980116SO HYDRAULIC SYS FRAYED C A UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CRCRUISE 1 EA07405LM4569 30 541 DUE TO IMPROPERLY POSITIONED ELBOW DURING AIRCRAFT PRODUCTION ON RT MAIN LANDING GEAR DOOR ACTUATOR, FLEX LINE WAS CONTACTING LINE DURING DOOR RETRACTION. THE FLEX LINE DEVELOPED A HYDRAULIC LEAK WHICH IN TURN DEPLETED THE LT AIRCRAFT HYDRAULIC SYSTEM. 2L72 4F RTA12EA 20060404001802006040400180 2006 4 4 2006FA0000213 420060217G2562 BATTERY ACK RYAN ST3 ST3KR 7830502WP ELT MISINSTALLED D K NONE W INADEQUATE Q C ININSP/MAINT 1 NM01170P 032988 1566 DURING REPLACEMENT OF BATTERIES FROM ELT CASE, MODERATE FORCE WAS NEEDED TO REMOVE THE BOTTOM 4 BATTERIES. THE FIT OF THE NEW BATTERIES INTO THE CASE WAS VERY TIGHT. AFTER CLOSING THE ELT CASE, THE ELT BECAME HOT TO THE TOUCH. SUSPECTING AN ELECTRICAL SHORT CIRCUIT, THE NEW BATTERIES WERE REMOVED. UPON EXAMINING THE NEW BATTERIES JUST REMOVED, IT WAS FOUND THAT THE PROTECTIVE COVERING ON THE TERMINAL END OF THE BATTERIES WAS SCRAPED AWAY. THIS MUST HAVE HAPPENED BY SLIDING THE BATTERIES INTO THE TIGHT CASE. THE RELATIVE BARE SPOTS ON THE BATTERIES WOULD ACCOUNT FOR A SHORT CIRCUITING OF THE BATTERIES THAT CAUSED THE ELT TO OVERHEAT. IT IS BELIEVED THAT THE TECHNIQUE USED TO INSERT THE BATTERIES INTO TH1L71 3R A749 20060323000532006032300053CE 2006 3 23 2006FA0000214 120060308G561099143809 WINDSHIELD CESSNA650 650 2076802CE COCKPIT CRACKED B A UNSCHED LANDING O OTHER CRCRUISE 1 CE09430SA6269 6507041 PILOT'S GLASS WINDSHIELD SHOWED SIGNS OF OVERHEATING AT UPPER CENTER EDGE CAUSING COMPLETE CRACKING OF WINDSHIELD IN A SPIDER WEB FASHION. THE WINDSHIELD REMAINED STRUCTURALLY SOUND AND THE AIRCRAFT WAS ABLE TO LAND WITHOUT INCIDENT. 2L72 4F A9NM 20060321000362006032100036 2006 3 21 2006FA0000215 120060228G2761120611 PISTON BOEING ACTUATOR CRACKED D DM4RK NONE O OTHER ININSP/MAINT 1 SO19 1292 SUBJECT PISTON WAS RECEIVED WITH THE 2 KENY SLOTS CRACKED ON ID RADIUS. CAUSE UNKNOWN. (K) 20060413002642006041300264NM 2006 4 13 2006FA0000216 120060228G2761656952211 HOUSING BOEING737 737* NM SPOILER ACTUATORSPLIT D DM4RK NONE O OTHER ININSP/MAINT 1 SO19 HOUSING RECEIVED SPLIT OPEN IN A RADIAL DIRECTION NEAR LARGE ID, CAUSING TOTAL FAILURE OF ASSY, CAUSE UNKNOWN. (K) 2L72 4F RTA16WE 20060320000302006032000030SO 2006 3 20 2006FA0000217 120060206G56101159SCB310212 WINDSHIELD GULSTMG1159 GIV 3980115SO RROYCETAY TAY6118 EU COPILOT WNDSHLD CRACKED B UO2RO OTHER G MULTIPLE FAILURE CRCRUISE 1 GL19181CW 6058 1001 OUTER PLY OF CO-PILOT WINDSHIELD CRACKED IN FLIGHT. NO LOSS OF PRESSURIZATION OCCURRED. APPEARS HEATING ELEMENT SHORTED. (K) 2L72 4F4 FRTA12EA E25NE 20060405002532006040500253GL 2006 4 5 2006FA0000219 120060210G7800DA403 RISER DIAMONDA40 DA40 2990002GL LYC O360 IO360A1A 41514EA ENGINE CRACKED D K NONE O OTHER ININSP/MAINT 1 GL19164DS 40467 ORDERED A NEW EXHAUST RISER FOR THE NR 2 CYLINDER. INSPECTING THE RISER BEFORE INSTALLATION WE FOUND A CRACK AT THE WELD RADIUS OF THE MOUNT FLANGE AND THE EXHAUST PIPE. THIS MAY HAVE ACCURED FROM EXCESS HEAT DURING MANUFACTUR. THIS THE FIRST CRACK SEEN ON NEW RISERS SEAT TO US, BUT WE HAVE HAD 2 IN SERVICE RISERS CRACKED AT 780.4 HOURS AND 2 IN SERVICE RISERS CRACKED. (K) 1L71 3O3 ONTA47CE 1E10 20060321002372006032100237 2006 3 21 2006FA0000220 420060301G3452SSD12030A ENCODER BEECH 33 35A33 1151404CE CONT O470 IO470* 17026SO COCKPIT OUT OF ADJUST D K NONE O OTHER ININSP/MAINT 1 NM071329Z CD354 CHECKED ENCODER SYSTEM AND COULD NOT VERIFIED REPORT OF ATTITUDE ERROR. REPLACED TRANS CAL BLIND ENCODER AS PRECAUTIONARY MEASURE. RECERTIFY TRANSPONDER AND ENCODER IAW FAR. (K) 1L71 3O3 O 3A15 E1CE 20060322001402006032200140SO 2006 3 22 2006FA0000221 120060216G32308627503 DOWNLOCK PIPER PA44 PA44180 7104402SO LYC O360 O360* 41514EA NOSE GEAR FAILED D K NONE O OTHER LDLANDING 1 NM092163N 447995222 NOSE GEAR COLLAPSE DURING ROLLOUT AFTER BRAKE APPLICATION. PILOT HAD 3 GREEN LIGHTS. HOOK PORTION OF DOWNLOCK PN 86275-03 FOUND CRACKED, BROKEN OFF. FOUND BROKEN NAS 464P4-27 ALSO FOUND FAILED. BOLT FRACTURED MID SHANK. HEAD PORTION OF BOLT NEVER FOUND. REMAINDER OF BOLT WITH NUT AND COTTER PIN INSTALLED FOUND STILL INSTALLED IN DRAGLINK ASSY. UNCLEAR AS TO WHAT FAILED FIRST. DOWNLOCK TT 8258 HRS, BOLT TT UNKNOWN. 1L72 3O3 O A19S0 E286 20060322001452006032200145SO 2006 3 22 2006FA0000222 120060216G3230NAS464P427 BOLT PIPER PA44 PA44180 7104402SO LYC O360 O360* 41514EA NLG FAILED D K NONE O OTHER LDLANDING 1 NM092163N 447995222 NOSE GEAR COLLAPSED DURING ROLL OUT, AFTER BRAKE APPLICATION. PILOT HAD 3 GREEN LIGHTS. HOOK PORTIONOF DOWNLOCK PN 86275-03 FOUND CRACKED, BROKEN OFF. FOUND BROKEN PIECE ON RUNWAY. DRAGLINK BOLT PN NAS 464P4-27 ALSO FOUND FAILED. BOLT FRACTURED MID SHANK. HEAD PORTION OF BOLT NEVER FOUND. REMAINDER OF BOLT WITH NUT AND COTTER PIN INSTALLED FUND STILL INSTALLED IN DRAGLINK ASSY. UNCLEAR AS TO WHAT FAILED FIRST. AD WAS PREVIOUSLY COMPLIED WITH. DOWN LOCK TT 8258 HRS, BOLT TT UNKNOWN. (K) 1L72 3O3 O A19S0 E286 20060320000802006032000080CE 2006 3 20 2006FA0000223 120060106G3411 PITOT SYSTEM LEAR 35 35A 5170602CE UNKNOWN INTERMITTENT D H51RK NONE J WARNING INDICATION DEDESCENT 1 NM03122JW 217 ON 1/4/06 PILOT REPORTED ALTIMETER JUMPS DURING DESCENT, 300 FT, AND WARNING HORN SOUNDS. NO OVERSPEED. ALTIMETER SYSTEM WAS TESTED, IAW SRM AND FOUND TO BE OPERATIONAL. NO TROUBLE NOTED. AIRCRAFT REMAINS RVSM COMPLAINT. (K) 2L72 4F A10CE 20060502000022006050200002 2006 5 2 2006FA0000224 120060228G24222001012 CIRCUIT BOARD MARATHON INVERTER INOPERATIVE B NE2RK NONE O OTHER ININSP/MAINT 1 CE07 1108 RECEIVED STATIC INVERTER FOR OVERHAUL. PRELIMINARY INSPECTION REVEALED THAT THE PRINTED CIRCUIT BOARD (PCB) HAD BEEN MODIFIED WITH IC SOCKETS. THE IC CHIPS WERE INSTALLED IN THE SOCKETS AND SEALED WITH A SILICONE LIKE SUBSTANCE RATHER THAN BEING SOLDERED DIRECTLY INTO THE PCB. JUMPER WIRE INSTALLED ON NON COMPONENT SIDE OF PCB. POOR (COLD) SOLDER JOINTS THROUGHOUT THE PCB NO SEALANT (CONFORMAL COATING) APPLIED TO NON COMPONENT SIDE OF PCCB AFTER REWORK. (K) 20060320000182006032000018EU 2006 3 20 2006FA0000225 120060227G2121125021116 BLOWER MOTOR GROB 120 G120A 1660208EU LYC O540 AEIO540D4D5 EA AC SYSTEM WORN B VJ3RK NONE O OTHER ININSP/MAINT 1 WP07865AF 85005 RL2631948A PILOT REPORTED EXCESSIVE VIBRATION WITH AIR CONDITION ON. WHILE TECH WAS TROUBLESHOOTING SYSTEM FOUND THAT BLOWER MOTOR HAD TOO MUCH END PLAY ON BLOWER FAN SHAFT MAKING IT VIBRATE. NO RECOMMENDATIONS AT THIS TIME. (K) 1L71 3O3 ORTA49CE 1E4 20060320000112006032000011SO 2006 3 20 2006FA0000226 120060128G56101159SCB31029 WINDSHIELD GULSTMG1159 G1159A 3970109SO RROYCESPEY SPEY511* 54523EU PILOT WINDSHIELDBROKEN B VZGRK NONE O OTHER CRCRUISE 1 SW0599PD 5415 314 AT FL 380 PILOTS WINDSHIELD SHATTERED. SHATTERED AT HEATING ELEMENT. (K) 2L72 4F4 F A12EA E2EU 20060502000092006050200009 2006 5 2 2006FA0000227 120060222G2434ALU1003 HOUSING ALTERNATOR WORN B KC2RK NONE O OTHER ININSP/MAINT 1 GL03 F123155 THIS ALTERNATOR HAS 0 HRS TIME IN SERVICE. DURING INSPECTION OF THIS UNIT. IT WAS DISCOVERED THAT THE DRIVE-END BEARING BORE WAS .006, OVERSIZE AND THE BEARING WAS VERY LOOSE IN THE BEARING BORE. THIS END FRAME SHOULD HAVE BEEN REJECTED DURING THE OVERHAUL PROCEDED DUE TO THE EXCESSIVE WEAR OF THE BEARING BORE. THIS SAME DEFECT WAS NOTED ON 2 OF THE LAST 3 UNITS RECEIVED. RECOMMENDATION INCLUDE A CLOSER INSPECTION FOR WEAR OF THE DRIVE END BEARING BORE SINCE THIS IS A FREQUENT PROBLEM WITH THIS MODEL. (K) 20060502000102006050200010 2006 5 2 2006FA0000228 120060302G2434ALU1003 HOUSING ALTERNATOR OUT OF TOLERANCEB KC2RK NONE O OTHER ININSP/MAINT 1 GL03 F123149 THIS ALTERNATOR HAS 0 HOURS. DURING INSPECTIONOF THIS UNIT PRIOR TO INSTALLING ON AIRCRAFT, IT WAS DISCOVERED THAT THE ROTOR HAD EXCESSIVE SIDE PLAY AND WAS ALLOWING THE ROTOR TO RUB AGAINST THE STATOR LAMINATIONS. THE DRIVE END BEARING BORE HAS EXCESSIVE WEAR AND THE BEARING IS LOOSE IN THE BORE. THIS CONDITION WOUD HAE RESULTED IN ALTERNATOR FAILURE AND POSSIBLY RESULTED IN ENGINE FAILURE SINCE THIS UNIT IS GEAR DRIVEN BY THE ENGINE. THIS IS THE 3RD UNIT IN 3 WEEKS FROM THIS SUPPLIER THAT HAD THIS SAME PROBLEM. RETURNED FOR EVALUATION AND WARRANTY REPLACEMENT. (K) 20060321002292006032100229SO 2006 3 21 2006FA0000230 120060223G32216705403 TRUNNION PIPER PA32 PA32R300 7103213SO LYC O540 IO540K1G5 41532EA NOSE GEAR CRACKED D K NONE O OTHER ININSP/MAINT 1 SO33196SQ3921 32R7780259 UPON INSPECTION OF THE NOSE GEAR. A 4.5 INCH CRACK WAS FOUND IN THE TUBULAR AREA OF THE LANDING GEAR TRUNNION CAUSE IS UNKNOWN, BUT SUSPECT HARD LANDING OR NOSE WHEEL TURNED BEYOND LIMITS. (K) 1L71 3O3 O A3SO 1E4 20060321001532006032100153SW 2006 3 21 2006FA0000231 120060227G53022050318211P FITTING BELL 204 UH1H 1181407SW ALLSN 250C 250C20B 03013GL TAILBOOM FRACTURED D K NONE E VIBRATION/BUFFET ININSP/MAINT 1 NM13623PB BBBD1521 6413689 AC LANDED FOR SHUTDOWN AFTER OPERATING FOR APPROX 3 FLIGHT HOURS, AC WAS SHAKING DURING SHUTDOWN. DURING POST FLIGHT INSP IT WAS FOUND THAT UPPER LT MOUNT HARD POINT PN 2050318211P ON TAILBOOM (PN 20503280071), WAS FRACTURED, HAD TORN THRU FWD TAILBOOM BLKHD (PN 205030807123S) ON AIRFRAME WAS ALSO CRACKED IN 2 PLACES RADIATING FROM BOOM MOUNT HOLE TO EDGE OF FITTING. AC RECORDS DO NOT REFLECT ANY INSTANCE OF HARD LANDING, OVER TORQUE, OR OTHER DAMAGE HISTORY. AC HAS APPROX 8400 HOURS TT, RECORDS SHOW THAT TAILBOOM WAS INSTALLED APPROX 5000 HOURS AGO. SUSPECTED, WHEN UPPER FITTING FAILED INSIDE TAILBOOM, BOOM ASSY SAGGED, PLACING EXCESSIVE TWIST ON LWR LT AIRFRAME MOUNT CAUSING IT TO CRACK IN 2 PLACES. (K) 1G71 4U3 U EXPA1G71E4CE 20060321001292006032100129CE 2006 3 21 2006FA0000232 120060223G213010138402831 SWITCH BEECH B300 B300 1159232CE PWA PT6 PT6A6 52043EA CABIN OUT OF TOLERANCEB E81RK NONE O OTHER ININSP/MAINT 1 GL03100BE FL403 DURING INITIAL 12 MONTH TEST OF CABIN ALTITUDE WARNING SYS FOUND BAROMETRIC SWITCH OPERATING OUT OF SPECIFIED MM TOLERANCE. REPLACED SWITCH WITH NEW SUPERSEDING (PN 101-38402845) SWITCH ASSY FROM STOCK, NEW SWITCH ALSO TESTED OUT OF SERVICE LIMITS. REPLACED WITH NEW (PN 101384028-45 SWITCH SUPPLIED BY RAPID, TESTS PASSED SUCCESSFULLY. SUSPECT NEW 101-384028-31 AND 101-384028-45 SWITCH ASSY MAY HAVE FAULT WHICH CAUSES THEM TO PASS INITIAL QA TESTS, BUT FAILED AFTER USE OR IN STORAGE. (K) 2L72 4T3 TRTA24CE E4EA 20060321001162006032100116CE 2006 3 21 2006FA0000233 120060224G352010138402829 SWITCH BEECH B300 B300 1159232CE PWA PT6 PT6A6 52043EA CABIN OUT OF TOLERANCEB E81RK NONE O OTHER ININSP/MAINT 1 GL03100BE468 FL403 DURING INITIAL 12 MONTH TEST OF CABIN OXYGEN SYSTEM FOUND BAROMETRIC SWITCH OPERATING OUT OF SPECIFIED MM TOLERANCE. REPLACED WITH NEW SUPERSEDING PN 10138402843 SWITCH SUPPLIED BY RAPID, TESTS PASSED SUCCESSFULLY. SUSPECT NEW 101384028-29 SEITCH ASSY MAY HAVE FAULT WHICH CAUSES THEM TO PASS INITIAL QA TESTS BUT FAIL AFTER USE OR IN STORAGE. (K) 2L72 4T3 TRTA24CE E4EA 20060321002332006032100233 2006 3 21 2006FA0000234 420060220G22156226717104 SERVO BEECH MU300 400A 1155402CE RUDDER SERVO INTERMITTENT B E81RK NONE F FLT CONT AFFECTED ININSP/MAINT 1 GL03467LX RK447 INVESTIGATED PILOT REPORT OF INTERMITTENT RUDDER BOOST FAILURE ALONG WITH SIMULATANEOUS AUTOPILOT AND YAW DAMPER DISEGAGEMENT. FOUND RUDDER SERVO INTERMITTENTLY FAILING. REPLACED RUDDER SERVO WITH OVERHAULED UNIT, RUDDER BOOST AND AUTOPILOT FUNCTIONAL TESTS SATISFACTORY. (K) 2H72 4F RTA16SW 20060321001192006032100119NE 2006 3 21 2006FA0000235 220060215G7200 ENGINE AMD FALC50FALCON50MYST2730106EU GARRTTTFE731TFE73140 29001NE FUSELAGE UNKNOWN B UO2RE ENGINE SHUTDOWN BJ SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION CRCRUISE 1 GL1923FM 3127 1811 296 115241 OIL TEMP 112, OIL PSI 50, MASTER CAUTION LIGHT CAME ON OIL SMELL IN CABIN. SHUT NR 3 ENGINE DOWN LANDED AT AIRPORT. CAUSE UNKNOWN AT THIS TIME REMOVE ENGINE FOR INSPECTION AND REPAIR, INSTALLED RENTAL. (K) 2L73 4F4 F A46EU E1NM 20060321002342006032100234 2006 3 21 2006FA0000236 420060227G346070000006000 FLIGHT DIR CIRRUSSR SR22 2130001GL CONT O550 IO550* SO COCKPIT INTERMITTENT C K NONE O OTHER ININSP/MAINT 1 GL1356FS 0576 JUST GOT 2003 SR22 BACK FROM GETTING REVISION 6 COMPLETED. PUT ABOUT 10 HOURS ON THE AIRPLANE. TWICE DURING THIS TRIP, THE PFD DISPLAY ROTATED OR ROLLED LIKE THE OLD TELEVISION SETS DID. ONCE FOR ONLY 2 OR 3 SECONDS AND ANOTHER TIME FOR MAYBE 10 TO 20 SECONDS. BOTH OF THESE OCCURRED IN LIGHT TO ODERATE CHOP AND AFTER MORE THAN AN HOUR OF FLIGHT. ONE OF THESE OCCURRENCES WAS IN SOLID INSTRUMENT CONDITIONS AND THE OTHER WHILE ON IFR FLIGHT, WAS IN THE CLEAR. HE IS A PILOT FOR A MAJOR AIRLINE. HIS OPINION WAS THAT THERE COULD BE A WIRE OR CONNECTION LOOSE INSIDE THE BOX. (K) 1L71 3O3 ONTA00009CHE3SO 20060321002282006032100228SW 2006 3 21 2006FA0000237 120060217G2800212040122101 DEBRIS MONITOR BELL 212 212 1181420SW PWA PT6T PT6T3 52045EA SCAVENGE CUP DEBONDED E CUCAK NONE O OTHER ININSP/MAINT 1 WP17911KW1147 30592 AFTER REMOVAL OF DEBRIS MONITOR FOR 50 HR, CLEAN AND INSP, THE SCAVENGE CUP/SCREEN TUBE ASSY (PN A8858 IS UNSCREWED FROM UNIT. THE O-RING FLANGE RING GLUED ONTO SCREEN TUBE SHEARS OFF OF SCREEN GLUE LINE, AND STAYS IN THE MAIN UNIT. FIX MAYBE TO APPLY GLUE TO RUFFED SURFACES (NOT DONE APARENTLY) AN TO INSIDE STEP OF ORING FLANGE RING TO THROUGH TUBE ASSY,OR OTHER METHOD. (K) 1G71 4U4 U H4SW E22EA 20060321002312006032100231EA 2006 3 21 2006FA0000238 120060225G3200 LANDING GEAR BLANCA1413 14132 1201004EA FRNKLN6A41656A4165* 27025EA WINGS FAULTY D K NONE O OTHER LDLANDING 1 WP0774212 1325 THIS LANDING GEAR RETRACTED AT TOUCH-DOWN. AIRCRAFT WAS IN STORAGE FOR A NUMBER OF YEARS. IT WAS PUT BACK IN SERVICE THE SUMMER OF 2005. THE LANDING GEAR WAS OVERHAULED (MECHANICAL) IN JAN 2006. THE GEAR WAS MODIFIED FROM HAND CRANK RETRACT TO ELE/HYD RETRACT, QUITE SOME TIME BACK. FEEL THE ELECTRICAL PART OF THE DESIGN SHOULD BE LOOKED AT. (NO SQUAT SWITCH, ETC) GOOD GROUND SYS IN WOOD AIRCRAFT. (K) 1L71 3O3 O A773 E238 20060322001002006032200100SO 2006 3 22 2006FA0000239 220060315G8550 RELIEF VALVE CIRRUSSR SR22 2130001GL CONT O550 IO550* SO ENGINE OIL SYS RESTRICTED B CTURK NONE O OTHER ININSP/MAINT 1 GL21216N 34 1801 689051 LOSS OF OIL PRESSURE, INSPECTED OIL PRESSURE RELIEF VAVLE AND FOUND TIP OF DRILL BIT LODGED IN RELIEF VALVE. REMOVED TIP OF DRILL BIT AND REASSEMBLED RELIEF VALVE. GROUND RAN, OPS CHECKED GOOD. (K) 1L71 3O3 ONTA00009CHE3SO 20060322001022006032200102 2006 3 22 2006FA0000240 420060208G2565D31591478 SLIDE BOEING737 737300 1384610NM CFMINTCFM56 CFM563C1 13802EU FUSELAGE OUT OF ALIGNMENTB I6XRO OTHER O OTHER ININSP/MAINT 1 GL11389UA 24664 THE ESCAPE SLIDE FOR DOOR R-2 WAS DEPLOYED FOR A SAMPLE INSPECTION. THE SLIDE DID NOT DEPLOY CORRECTLY, THE SLIDE INFLATED TO THE FULL LENGTH, STRAIGHT OUT FROM THE AIRCRAFT, HOWEVER, IT WAS ROTATED 90 DEGREES, AND DID NOT TOUCH THE FLOOR. (K) 2L72 4F4 FRTA16WE E21EU 20060322001032006032200103EA 2006 3 22 2006FA0000241 220060313G7420M2917 HARNESS CESSNA172 172N 2072434CE LYC O320 O320H2AD 41508EA SPARK PLUG CAPS MISMANUFACTURED D O OTHER O OTHER ININSP/MAINT 1 SO065228E 17271783 THE AIRCRAFT HAD MAGNETO LEADS THAT NEEDED TO BE REPLACED. A NEW HARNESS SET WAS RECEIVED AND WAS INSTALLED ON THE ENGINE. THE ENGINE RAN POORLY. FOUND (T-4). ALSO NOTED THAT THE SHIELD ON NR 1 BOTTOM WIRE HAD BEEN CUT DURING MANUFACTURER AND THE SHIELD WAS OPEN. MFG REPLACED THE HARNESS FREE OF CHARGE AND FREIGHT FREE. (K) 1H71 3O3 ONT3A12 E274 20060322001382006032200138CE 2006 3 22 2006FA0000242 120060216G3240 LINE CESSNA525 525A 2076615CE WILINTFJ44 FJ44 66000GL LT MLG BRAKE FAILED C K NONE K FLUID LOSS LDLANDING 1 SO35701TF 525A0112 126045 AIRCRAFT DEPARTED THE RUNWAY DURING LANDING ROLLOUT. FAILURE OF BOTH THE HYDRAULIC AND PNEUMATIC LINES TO THE LT MAIN LANDING GEAR BRAKE CAUSED THE AIRCRAFT TO SPIN INTO A GRASSY AREA ADJACENT TO THE RUNWAY. THE NOSE LANDING GEAR SHEARED OFF AND THE AIRCRAFT CAME TO REST ON THE MAIN LANDING GEAR AND NOSE OF THE AIRCRAFT. THERE IS SUBSTANTIAL DAMAGE TO THE NOSE OF THE AIRCRAFT AND SOME MINOR DAMAGE TO THE WINGS. CAUSE OF THE LINE FAILURE IS UNDER INVESTIGATION. (SO35200603622) 1L71 4F4 FRTA1WI E3GL 20060322001502006032200150SW 2006 3 22 2006FA0000243 120060207G3230 ACTUATOR GULSTM114 114TC 0145002SW LYC O540 TIO540* 41532EA NLG UNKNOWN B CB5YK NONE O OTHER LDLANDING 1 EA35115TB 20031 L1061461A AFTER REFITMENT, NLG FAILED TO EXTEND TO LAND POSITION. AC HAD BEEN UNDERGOING WORK TO SATISFY AD. AFTER WORK, GREEN NOSE WHEEL INDICATOR WOULD NOT ILLUM. FLYBY OF TWR, NLG WAS PARTIALLY EXTENDED TO ANGLE OF 45 DEGREES. RECYCLING STILL FAILED TO EXTEND NLG BEYOND 45 DEGREES. PWROFF LANDING WAS EXECUTED, NLG COLLAPSED, AC CAME TO REST ON 2 PROP BLADES, NOSE WHEEL BAY DOORS. LANDING HAD PUSHED NLG BACK TOWARD RETRACTED POSITION BUT WITH PART OF TIRE PROTRUDING THROUGH PARTIALLY OPEN NOSE BAY DOORS. PIN ATTACHING NOSE GEAR ACTUATOR TO NOSE LEG WAS REMOVED. GEAR FELL UNHINDERED AND UNAIDED TO DOWNLOCKED POSITION. INSP OF NLG, WHEN NG ACTUATOR IS AVAILABLE, (SHAFT BENT 45 DEGREES IN ACCIDENT) . (K) 1L71 3O3 ORTA12SO E14EA 20060322002602006032200260CE 2006 3 22 2006FA0000244 120060210G5753052390138 FLAP CESSNA172 172S 2072439CE LYC IO360 IO360L2A EA MCAULY1A170 1A170E GL WINGS CRACKED B NM2RK NONE F FLT CONT AFFECTED ININSP/MAINT 1 GL193533U1200 172S8890 L2982051A UK23072 AIRCRAFT CAME IN FOR AN ANNUAL INSPECTION, DAMAGE TO THE FLAPS WERE FOUND DURING ROUTINE INSPECTION PROCESS. RT FLAP HAD CRACKS RADIATING OUT FROM RIVETS ON LOWER T/E SKIN, PLUS CRACKS RADIATING OUT FROM L/E SKIN, ON BOTTOM OF FLAP, IB OF MOUNTING BRACKET. DAMAGE DESCRIBED WAS ON RT FLAP. LT FLAP HAD SAME DAMAGE, ONLY LESS SEVERE. THE PROBABLE CAUSE WAS SUSPECTED TO BE CAUSED FROM LOWERING THE FLAPS AT TOO HIGH AN AIRSPEED. FLIGHT DEPARTMENT CHAIRMAN AGREED TO DISCUSS THIS POSSIBLE PROBLEM WITH THE OTHER FLIGHT INSTRUCTORS, SO THEYY CAN DISCUSS THE PROBLEM WITH THEIR STUDENTS. (K) 1H71 3O3 ONT3A12 1E10 5 NP857 20060323000422006032300042EA 2006 3 23 2006FA0000245 220060218G7200 ENGINE DHAV DHC6 DHC6300 2802606EA PWA PT6 PT6A27 52043EA LT WING MAKING METAL C K NONE O OTHER ININSP/MAINT 1 WP1972GC 264 PCE41557 LT ENGINE OIL PRESSURE STARTED FLUCTUATING. PILOT RETURNED TO AIRPORT. MAINTENANCE CHECKED OIL FILTER AND FOUND METAL IN OIL. ENGINE REMOVED AND SENT TO REPAIR FACILITY. (K) 1H72 3T4 TRTA9EA E4EA 20060323001632006032300163EU 2006 3 23 2006FA0000246 120060221G5740T700A5760031020 ATTACH BRACKET SOCATATBM TBM700 8682000EU PWA PT6 PT6A64 EA OB LT WING CRACKED C K NONE O OTHER ININSP/MAINT 1 EA05703QD5659 129 DURING A ROUTINE PHASE INSPECTION, THE LT WING TIP ASSY WAS REMOVED TO FACILITATE FURTHER INSPECTION OF THE AILERON CABLE. AFTER REMOVAL OF THE TIP, THE INSPECTING TECHNICIAN NOTICED A CRACK IN AT THE OB ATTACH POINT. THE BRACKET WAS REMOVED AND INSPECTED WITH A 20X MAGNIFYING GLASS WHICH REVEALED NO LESS THAN 6 CRACKS IN THE BRACKET. IT IS RECOMMENDED THAT ALL LT AND RT ATTACH BRACKETS BE INSPECTED FOR CRACKS WITH THE WING TIPS REMOVED. (K) 1L71 3T4 TRTA60EU E4EA 20060323000502006032300050EU 2006 3 23 2006FA0000247 120060221G5740T700A5760031000 SUPPORT BRACKET SOCATATBM TBM700 8682000EU PWA PT6 PT6A64 EA AILERON CRACKED C K NONE O OTHER ININSP/MAINT 1 EA05701QD5954 126 DURING A 6000 HOUR INSPECTION, THE LT AND RT WING TIP ASSEMBLIES WERE REMOVED TO FACILITATE FURTHER INSPECTION OF THE AILERON SYSTEM. AFTER REMOVAL OF THE TIPS THE INSPECTING TECHNICIAN NOTED CRACKS IN BOTH THE LT AND RT AILERON OB ATTACH POINTS. THE BRACKET WAS REMOVED AND INSPECTED WITH A 10X MAGNIFYING GLASS WHICH CONFIRMED CRACKS IN BOTH THE BRACKETS. IT IS RECOMMENDED THAT ALL LT AND RT ATTACH BRACKETS BE INSPECTED FOR CRACKS WITH THE WING TIPS REMOVED. LT BRACKET (PN T700A5760031000) RT BRACKET (PN T700A5760031001) 1L71 3T4 TRTA60EU E4EA 20060323001642006032300164EU 2006 3 23 2006FA0000248 120060221G5740T700A5760031001 ATTACH BRACKET SOCATATBM TBM700 8682000EU PWA PT6 PT6A64 EA OB WING ASSY CRACKED C K NONE O OTHER ININSP/MAINT 1 EA05701QD 126 DURING A 6000 HOUR INSPECTION, THE LT AND RT WING TIP ASSEMBLIES WERE REMOVED TO FACILITATE FURTHER INSPECTION OF THE AILERON SYSTEM. AFTER REMOVAL OF THE TIPS THE INSPECTING TECHNICIAN NOTED CRACKS IN BOTH THE LT AND RT AILERON OB ATTACH POINTS. THE BRACKET WAS REMOVED AND INSPECTED WITH A 10X MAGNIFYING GLASS WHICH CONFIRMED CRACKS IN BOTH THE BRACKETS. IT IS RECOMMENDED THAT ALL LT AND RT ATTACH BRACKETS BE INSPECTED FOR CRACK WITH THE WING TIPS REMOVED. LT BRACKET (PN T700A5760031000) ( RT BRACKET (PN T700A5760031001) (K) 1L71 3T4 TRTA60EU E4EA 20060406002112006040600211CE 2006 4 6 2006FA0000249 120060215G3510553008 GASKET LEAR 55 55LEAR 5170702CE GARRTTTFE731TFE7313A 01518WP O2 MASK LEAKING B OVVRK NONE O OTHER ININSP/MAINT 1 EA1132KJ 8953 93 PILOT O2 MASK HAD ORIGINAL O/H DATE OF 6/05. MASK WAS PLACED IN SERVICE IN AC 55093. MASK DID NOT TEST PROPERLY AT DELIVERY DATE OF 6/23/05. MASK WAS SENT BACK, FOUND TO HAVE A LEAK. MASK WAS REPAIRED AND SENT BACK TO AC. MASK WAS FOUND TO BE LEAKING AGAIN AFTER 2 WEEKS IN AIRCRAFT. AGAIN, IT WAS REPAIRED. PLACED BACK IN SERVICE, AFTER 2 MONTHS MASK WAS FOUND LEAKING AGAIN. IT WAS SENT BACK FOR ANOTHER REPAIR, DATED 12/5/05. MASK HAS BEEN FOUND TO BE LEAKING FOR FOURTH TIME, SENT BACK FOR FOURTH TIME FOR REPAIR. 4 REPAIRS ON THIS MASK SINCE O/H DATE OF 6/05 IS UNACCEPTABLE. HAVE SERIOUS DOUBTS AS TO CAPABILITIES TO MAKE OVERHAULS AND REPAIRS THAT LAST. PILOT O2 MASK IS VERY CRITICAL COMPONENT. 2L72 4F4 F A10CE E6WE 20060323000432006032300043CE 2006 3 23 2006FA0000250 120060222G5346051313211 BRACKET CESSNA CESSNA175 175 2072502CE CONT O300 GO300* 17022SO ENGINE COMPARTMTCRACKED D K NONE O OTHER ININSP/MAINT 1 CE077362M2268 55662 INSP 0513132-11, MOUNT BRACKET WAS FOUND TO BE CRACKED. CRACK RAN VERT THROUGH BRACKET AROUND OUTER RADIUS OF AN960-616 WASHER ON UPPER ENG MOUNT BOLT. INSP WAS DONE DUE TO 2 OTHER KNOWN REPORTS OF CRACKS IN THIS BRACKET ON SAME MODEL OF AC, ONE RESULTED IN A PARTIAL ENG AND FIREWALL SEPARATION FROM AC ON LANDING. MUST LOOK INSIDE STRINGER BEHIND INSTRUMENT PANEL. RECOMMEND THAT SPECIAL ATTENTION BE PAID TO UPPER ENG MOUNT BRACKETS DURING INSP. 0513132-3 AND -4 STRINGER ASSEMBLIES WERE USED ON 175 SN 55001 THRU 17557119, 172 SN 17247747 THRU 17272884P172 SN P17257120 THRU P17257188 F172 SN F17201235 THRU F17201909 FR172 SN FR172-0001 THRU FR17200655R172 SN R1722000 THRU R1723199. 1H71 3O3 ONT3A17 E298 20060512000442006051200044CE 2006 5 12 2006FA0000251 120060222G3010SMR20142112 BOOT BEECH 90 B90 1152912CE WINGS MISLOCATED B K NONE O OTHER ININSP/MAINT 1 NM03379VM LW27 UPON INSTALLATION OF NEW LT AND RT WING DE-ICE BOOTS WITH NEW PMA P/N SMR2014-21-1, AND -2, IT WAS DISCOVERED THE AIR INLET TUBES ARE INSTALLED IN THE WRONG LOCATION, MAKING IT IMPOSSIBLE TO MATCH THE BOOT CENTERLINE WITH THE LE CENTERLINE. MFG AND OEM DRAWINGS SHOW 1 INCH FROM BOOT CENTERLINE TO INLET TUBE CENTERLINE. SMR BOOTS HAVE 1.5625 INCH. THE ONLY WAY THIS BOOT CAN BE INSTALLED IS TO SHIFT THE ENTIRE BOOT UP ON THE WING AT LEAST .5625 INCH. THIS CAUSES CONCERN FOR CHANGE IN STALLING SPEED AT SLOW FLIGHT WITH THE BOOTS INFLATED. SMR HAS BEEN VERY HELPFUL AND CONCERNED. OEM BOOTS WERE PURCHASED AND INSTALLED. SMR BOOTS WERE RETURNED. 1L72 3T 3A20 20060512000572006051200057CE 2006 5 12 2006FA0000252 120060222G3010SMR20142112 BOOT BEECH 90 B90 1152912CE WINGS MISMANUFACTURED B K NONE O OTHER ININSP/MAINT 1 NM03379VM LW27 ON INSTALLATION OF NEW LT AND RT WING DE-ICE BOOTS, PMA P/N SMR2014-21-1, -2, WAS DISCOVERED AIR INLET TUBES ARE INSTALLED IN WRONG LOCATION, MAKING IT IMPOSSIBLE TO MATCH BOOT CENTERLINE WITH LE CENTERLINE. OEM DRAWINGS SHOW 1 INCH FROM BOOT CENTERLINE TO INLET TUBE CENTERLINE. SMR BOOTS HAVE 1.5625 INCH. ONLY WAY THIS BOOT CAN BE INSTALLED IS TO SHIFT ENTIRE BOOT UP ON WING AT LEAST .5626 INCH. CAUSES CONCERN FOR CHANGE IN STALLING SPEED AT SLOW FLIGHT WITH BOOTS INFLATED. SMR HAS SOLD APPROX 20 UNITS WITH NO COMPLAINTS. SEVERAL MECHANICS (THAT IS JUST REF LINE ON BOOT, GO AHEAD AND GLUE THEM ON). SMR HAS BEEN VERY HELPFUL AND CONCERNED. OEM BOOTS WERE PURCHASED, INSTALLED. SMR BOOTS WERE RETURNED.1L72 3T 3A20 20060323000542006032300054SO 2006 3 23 2006FA0000253 120060217G8000 WIRE PIPER PIPER PA28 PA28161 7102803SO LYC O320 O320D3G 41508EA SNSNCH74D 74DM EA CONTACTOR LOOSE B H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS ININSP/MAINT 1 SO159206H 2841006 L1229139A A53071 MFG HAS RECENTLY ISSUED REPLACEMENT PWR CONTACTORS, IN THIS CASE FOR ENG STARTER, WITH CONTACTORS THAT HAVE PLASTIC INSULATED MOUNTING (FEET). REPLACEMENT CONTACTORS UTILIZE A GROUND WIRE UNDER BOLT HEAD OF ONE OF MOUNT BOLTS FOR CONTACTOR ACTIVATION CIRCUIT GROUND. PLASTIC PORTION OF FEET COMPRESS DURING INSTALLATION, TORQUE PROCESS. CONTACTOR ATTACH POINT LOOSENS CAUSING CIRCUIT WIRE TO GROUND, TO LOOSEN RESULTING IN HIGH RESISTANCE TO GROUND FOR STARTER CONTACTOR ACTIVATION CIRCUIT. RESULT, PLASTIC (FEET) MELT DUE TO HIGH RESISTANCE HEAT, CAUSING MATERIAL ON CABIN SIDE OF FIREWALL TO CAUSE SMOKE IN COCKPIT. BELIEVE THAT THIS COULD CAUSE A FIRE. 1L71 3O3 O 2A13 E274 5 NP88614 20060323002012006032300201CE 2006 3 23 2006FA0000254 120060223G5511 SPAR LEAR 55 55LEAR 5170702CE GARRTTTFE731TFE731* 01518WP STABILIZER CORRODED C K NONE O OTHER ININSP/MAINT 1 SO17355RM 033 INSPECTIONS, HAVE FOUND SERIOUS EXFOLIATION CORROSION IN THE REAR SPAR FLANGES, NEAR THE ELEVATOR HINGE BRACKETS OF AT LEAST 2 AIRCRAFT. CORROSION HAD PROGRESSED TO THE EXTENT REQUIRING REMOVAL/REPLACEMENT OF THE SPAR FLANGES OR REPLACEMENT OF THE STABILIZER. RECOMMEND A MORE DETAILED INSPECTION OF THE SPAR FLANGES AND A CONSIDERABLE SHORTENING OF THE TIME BETWEEN INSPECTION REQUIREMENTS. THE CORROSION HAD PROGRESSED TO THE POINT OF COMPROMISING THE INTERIORITY OF THE SPAR AND ATTACHED ELEVATOR HINGE MOUNTING. 2L72 4F4 F A10CE E6WE 20060323000672006032300067CE 2006 3 23 2006FA0000255 120060223G5511 SPAR LEAR 55 55LEAR 5170702CE GARRTTTFE731TFE731* 01518WP STABILIZER CORRODED C K NONE O OTHER ININSP/MAINT 1 SO17355RM 033 DURING 12,000/12 YR DEMATE INSPECTIONS WE HAVE FOUND SERIOUS EXFOLIATION CORROSION IN THE REAR SPAR FLANGES, NEAR THE ELEVATOR HING BRACKETS OF AT LEAST TWO AIRCRAFT. CORROSION HAD PROGRESSED TO THE EXTENT REQUIRING REMOVAL/REPLACEMENT OF THE SPAR FLANGES OR REPLACEMENT OF THE STABALIZER.I RECOMMEND A MORE DETAILED INSPECTION OF THE SPAR FLANGES AND A CONSIDERABLE SHORTENING OF THE TIME BETWEEN INSPECTION REQUIREMENTS. IN MY OPINION, THE CORROSION HAD PROGRESSED TO THE POINT OF COMPROMISING THE INTERURITY OF THE SPAR AND ATTACHED ELEVATOR HING. MOUNTING. 2L72 4F4 F A10CE E6WE 20060323002022006032300202CE 2006 3 23 2006FA0000256 120060223G5511 SPAR LEAR 55 55LEAR 5170702CE STABILIZER CORRODED C K NONE O OTHER ININSP/MAINT 1 SO17355RM 033 INSPECTIONS HAVE FOUND SERIOUS EXFOLIATION CORROSION IN THE REAR SPAR FLANGES, NEAR THE ELEVATOR HINGE BRACKETS OF AT LEAST 2 AIRCRAFT. CORROSION HAD PROGRESSED TO THE EXTENT REQUIRING REMOVAL/REPLACEMENT OF THE SPAR FLANGES OR REPLACEMENT OF THE STABILIZER. RECOMMEND A MORE DETAILED INSPECTION OF THE SPAR FLANGES AND A CONSIDERABLE SHORTENING OF THE TIME BETWEEN INSPECTION REQUIREMENTS. IN MY OPINION, THE CORROSION HAD PROGRESSED TO THE POINT OF COMPROMISING THE SPAR AND ATTACHED ELEVATOR HINGE MOUNTING. 2L72 4F A10CE 20060323001182006032300118 2006 3 23 2006FA0000257 420060303G2211065001767904 AUTOPILOT SYS CESSNA182 182T 2072703CE INTERMITTENT B FSERO OTHER O OTHER CRCRUISE 1 NE05 INTERMITTENT PITCH TRIM AND ACCELEROMETER FAILURES. POSSIBLY CAUSED BY INADEQUATE CONNECTOR ENGAGEMENT WITH THE MOUNTING RACK CONNECTORS, CAUSED BY IMPROPER POSITIONING OF THE TOP COVER. 1H71 3O NT3A13 20060323001322006032300132CE 2006 3 23 2006FA0000258 120060301G2700 FLT CONTROLS CESSNA172 172M 2072418CE SEIZED C K NONE O OTHER ININSP/MAINT 1 GL001295U 17266989 AIRCRAFT HAD BEEN TREATED WITH ACF-50 OVER THE LIFE OF THE AIRFRAME. SEVERAL PULLEYS IN THE AILERON, ELEVATOR AND FLAP SYSTEMS WERE FOUND SEIZED OR GUMMED UP WITH ACF-50. LAST APPLICATION OF ACF-50; 18MO. 1H71 3O NT3A12 20060405002252006040500225CE 2006 4 5 2006FA0000259 120060307G27102424000258 CASTING LEAR 60 60LEAR 5170707CE PWA 305 PW305 NE LT AILERON BENT B JGVRK NONE F FLT CONT AFFECTED ININSP/MAINT 1 CE09647TS 047 INCOMING INSPECTION FOUND AILERON DRIVE YOKE ATTACH CASTING BENT. UPON FURTHER INSPECTION IT WAS DISCOVERED THE DRIVE YOKE UPPER OR LOWER SHIMS WERE NOT INSTALLED. DRIVE YOKE ATTACH BOLT WAS INSTALLED CAUSING THE CASTING TO BE BENT AND REQUIRES REPLACEMENT BY OEM. THIS COULD HAVE BEEN PREVENTED BY FOLLOWING MAINTENANCE MANUAL INSTALLATION INSTRUCTIONS. (K) 2L72 4F4 FRTA10CE E35NE 20060404002382006040400238CE 2006 4 4 2006FA0000260 120060306G79218406R OIL COOLER CESSNA172 172M 2072418CE LYC O360 O360A1A 41514EA SPLIT C K NONE O OTHER ININSP/MAINT 1 NM015496H 17265466 L2971136A DURING ROUTINE RUN-UP FOLLOWING AN OIL CHANGE, AN IMMEDIATE EXPULSION OF SEVERAL QUARTS OF OIL OCCURRED IN SECONDS. (K) 1H71 3O3 ONT3A12 E286 20060404002372006040400237CE 2006 4 4 2006FA0000262 120060301G2810PMA20331 FUEL CELL BEECH 95 95B55 1152729CE CONT O470 IO470* 17026SO LT, RT WINGS DETERIORATED D K NONE O OTHER ININSP/MAINT 1 SW0556JK 2814 1778 690 TC1938 FOUND FUEL SYTEM CONTAMINATED WITH AN UNKNOWN SUBSTANCE. AFTER HAVING THE ENTIRE SYSTEM DRAINED, FLUSHED AND THE ENGINE FUEL INJECTION SYSTEM OVERHAULED, THE AIRCRAFT WAS REFUELED AND FLOWN. AFTER A SHORT FLIGHT, THE SUMPS WERE CHECKED AGAIN AND THE SUBSTANCE WAS FOUND AGAIN. BOTH FORWARD FUEL CELLS WERE REMOVED FROM THE AIRCRAFT. THE SPONGE-LIKE MATERIAL INSIDE THE WING ROOT HEADER TANK PORTION OF THE FUEL CELL WAS FOUND IN A DETERIORATED CONDITION AND CONTAMINATING THE ENTIRE FUEL SYSTEM. NEW FUEL CELLS WERE ORDERED. (K) 1L72 3O3 ORT3A16 E1CE 20060405001532006040500153CE 2006 4 5 2006FA0000265 120060301G2810PMA20332 BAFFLE BEECH 95 95B55 1152729CE CONT O470 IO470* 17026SO WING FUEL CELLS DETERIORATED D K NONE O OTHER ININSP/MAINT 1 SW0556JK 2814 1778 692 TC1938 FOUND FUEL SYSTEM CONTAMINATED WITH AN UNKNOWN SUBSTANCE. AFTER HAVE THE ENTIRE SYSTEM DRAINED, FLUSHED AND THE ENGINE FUEL INJECTION SYSTEM OVERHAULED, THE AIRCRAFT WAS REFUELED AND FLOWN. AFTER A SHORT FLIGHT, THE SUMPS WERE CHECKED AGAIN AND THE SUBSTANCE WAS FOUND AGAIN. BOTH FORWARD FUEL CELLS WERE REMOVED FROM THE AIRCRAFT. THE SPONGE-LIKE MATERIAL INSIDE THE WING ROOT HEADER TANK PORTION OF THE FUEL CELL WAS FOUND IN A DETERIORATED CONDITION AND CONTAMINATING THE ENTIRE FUEL SYSTEM. NEW FUEL CELLS WERE ORDER. (K) 1L72 3O3 ORT3A16 E1CE 20060405002282006040500228EU 2006 4 5 2006FA0000266 120060217G21204783658519 FLEX DUCT ISRAEL1124 1124 4500102EU GARRTTTFE731TFE731* 01518WP CABIN FLOOR DUCTDETERIORATED C K NONE O OTHER ININSP/MAINT 1 SW19290CA10907 216 DURING C-CHECK, BY ACCESS OF FUSELAGE REPAIR, IT WAS FOUND THAT FLEXIBLE AIR CONDITIONING DUCTS WERE BADLY DETERIORATED. FOAM ON INSIDE OF DUCTS WERE COMING LOOSE AND SOME OF DUCTS WERE COLLAPSED. THESE DUCTS ARE JUST PLAIN OLD. MFG TIME LIMITS DO NOT COVER THESE DUCTS AND DURING 800 HOUR C-CHECK AIRFRAME INSP THERE IS NOT A REQUIREMENT TO INSPECT INSIDE OF DUCTS FOR BLOCKAGE OR COLLAPSED DUCTS. FLEX DUCTS CONNECT BELOW THE BLOW AND RUN UP SIDE OF THE FUSELAGE TO LWR AIR CONDITIONING VENTS. THESE ARE NOT HOT AIR DUCTS, UNDER A UNFORSEEN CIRCUMSTANCE, POSES A POSSIBLE FIRE HAZARD IF DUCT TEMPERATURES GET HOT. CALLED MFG TO GET FLEX DUCTS, PN CROSSED TO A NEW STYLE DUCT (PN BWT103080360A.) (K) 2M72 4F4 F A2SW E6WE 20060405001752006040500175SO 2006 4 5 2006FA0000267 120060228G3260487862 SWITCH PIPER PA31 PA31325 7103105SO LYC O540 TIO540* 41532EA RMLG FAILED B DZZRO OTHER P NO WARNING INDICATION CRCRUISE 1 GL0959815 317612041 AFTER SELECTING (GEAR DOWN), PILOT WAS UNABLE TO GET A GREEN LIGHT FOR RT MLG, IN EITHER NORMAL OR EMERGENCY EXTENSIONS. GROUND OBSERVERS ADVISED RMLG WAS DOWN AND IB GEAR DOORS WERE OPEN. UNEVENTFUL LANDING FOLLOWED. INVESTIGATION REVEALED RMLG DOWNLOCK SWITCH FAILED ELECTRICALLY. SWITCH WAS REPLACED, SEVERAL GEAR CYCLES ON JACKS. AIRCRAFT TEST FLOWN, SATISFACTORY. (K) 1L72 3O3 O A20SO E14EA 20060405001842006040500184NE 2006 4 5 2006FA0000268 220060302G72500292817220 RING SNIAS 350 AS350B3 8680954EU TMECA ARRIELARRIEL2B NE ENGINE CRACKED B HXSRK NONE O OTHER ININSP/MAINT 1 AL05405AE 3286 22103 IN COMPLIANCE WITH AD AND SB, OUR MECHANIC WAS INSPECTING THE ABOVE DESCRIBED ENGINE AND FOUND THE COMPONENT LISTED BELOW TO BE OUT OF SERVICEABLE LIMITS AS INDICATED IN THE 2 DOCUMENTS. REMOVED THE CONTAINMENT RING FROM SERVICE AND INSTALLED A NEW POST MOD TU-22 RING AS ADVISED. (K) 1G71 3U3 U H9EU E00054EN 20060404002402006040400240NM 2006 4 4 2006FA0000269 120060215G2913123412 COVER SMITHSIND BOEING737 737* NM SHUTOFF VALVE CRACKED D IU6RK NONE O OTHER ININSP/MAINT 1 NM01 6313 (REF NR: 204244/PH3) COVERED CRACKED. PROBABLE CAUSE: FATIGUE. REDESIGN COVER. (K) 2L72 4F RTA16WE 20060405002352006040500235NM 2006 4 5 2006FA0000270 120060215G2913123412 COVER SMITHSIND BOEING737 737* NM HYD SYS CRACKED D IU6RK NONE O OTHER ININSP/MAINT 1 NM01 6314 (REF NR: 204200/PH3) COVER CRACKED, PROBABLE CAUSE, FATIGUE. REDESIGN COVER. (K) 2L72 4F RTA16WE 20060404002362006040400236NM 2006 4 4 2006FA0000271 120060213G2900271T00714 HOUSING BOEING BOEING767 767* NM HYDRAULIC SYS CRACKED B IU6RK NONE O OTHER ININSP/MAINT 1 NM01 28833 3087 (203230/FXS) HOUSING CRACK AT THE PRESSURE (INLET) PORT FOR THE CHECK VALVE BORE. PROBABLE CAUSE: FATIGUE. REDESIGN HOUSING. (K) 2L72 4F RTA1NM 20060404002332006040400233NM 2006 4 4 2006FA0000272 120060213G3240511531 HOUSING PNEUDRAULICS BOEING737 737* NM LANDING GEAR CRACKED B IU6RK NONE O OTHER ININSP/MAINT 1 NM01 (204174/PH3) HOUSING CRACKED IN THE BORE OF THE MOUNTING LUG. PROBABLE CAUSE: FATIGUE. REDESIGN HOUSING. (K) 2L72 4F RTA16WE 20060327000022006032700002CE 2006 3 27 2006FA0000273 120060301G7120051313211 MOUNT CESSNA175 175A 2072504CE ENGINE CRACKED D K NONE O OTHER ININSP/MAINT 1 CE076997E1900 56497 DURING VISUAL INSPECTION FOUND THE 0513132-11 UPPER LEFT HAND ENGINE MOUNT BRACKET IN THE 0513132-3 STRINGER ASSEMBLY CRACKED. INSPECTION WAS PERFORMED DUE TO OTHER REPORTED FAILURES OF THIS BRACKET ON THE SAME MODEL OF AIRCRAFT. RECOMMEND INSPECTION OF BRACKETS IN ALL AIRCRAFT WITH THE 0513132-3 ENGINE MOUNT STRINGER ASSEMBLY. 1H71 3O 3A17 20060327000342006032700034NM 2006 3 27 2006FA0000274 120060301G63205100400 HOSE DOUG MD900 MD900 3027375NM PWC PW207 PW207E NE XMSN OIL CRACKED D K NONE KJ FLUID LOSS WARNING INDICATION ININSP/MAINT 1 EA11902PD489 489 9000084 HOSE IS INSTALLED ON MD902 HELICOPTERS. MD P/N IS 900D3409526-105. HOSE IS USED FOR MAIN TRANSMISSION OIL COOLING. FOUND LARGE ACCUMULATION OF OIL ON TRANSMISSION DECK AFTER FLIGHT. HOSE WAS FOUND TO BE CRACKED IN ONE OF THE BELLOWS. (CORE OF HOSE IS STAINLESS STEEL BELLOWS WITH A COVERING OF STAINLESS STEEL BRAID). REPLACED HOSE WITH NEW. 1G72 3U3 UNCH19NM E42NE 20060327000452006032700045CE 2006 3 27 2006FA0000275 120060307G2420991059112 ALTERNATOR CESSNA206 206H 2073301CE LYC O540 IO540AC1A5 EA ENGINE BURNED C HO DEACTIVATE SYST/CIRCUITSOTHER HJSELECT. POWER LOSS-50 PC WARNING INDICATION AFFECT SYSTEMS CRCRUISE 1 CE07 76 76 08255 L3083148E BATTERY TERMINAL LUG BURNT OFF DUE TO SHORT CAUSED BY TERMINAL ON WIRE HARNESS BREAKING OFF. THIS CAUSED THE ALTERNATOR CONTROL UNIT TO FAIL (SMOKE) AND HEAVY ARCING AT TERMINAL LUG. THERE WAS AN INDICATION OF NOT CHARGING ON G-1000 MFD AND PFD SCREENS. THIS ALSO CAUSED FLUCUATION ON THE FUEL FLOW INDICATION. SUSPECT SHORTED CABLE THRU ALTERNATOR ATTACHED TO ENGINE THRU ENGINE AND THEN THRU SENSOR. NOTE: NO CIRCUIT BREAKER POPPED AND NO FUSEABLE LINK BETWEEN BATTERY HARNESS CONNECTED TO THE ALTERNATOR AND ALTERNATOR CONTROL UNIT. SUSPECT WEAK TERMINAL AT ALTERNATOR ALONG WITH POOR INSTALLATION SUPPORT BY CLAMPS OR TIE-WRAPS. CORRECTED AS REQUIRED WITH A MORE HEAVIER DUTY TERMINAL. 1H71 3O3 ORTA4CE 1E4 20060327000462006032700046SO 2006 3 27 2006FA0000276 120060306G3230 SEQUENCE VALVE PIPER PA46 PA46350P 7104602SO NLG DEFECTIVE B O OTHER J WARNING INDICATION APAPPROACH 1 CE0355WH 1912 4636204 LOUD NOISE REPORTED BY PILOT, AND FOUND NOSE GEAR DOOR ACUATOR ROD END BROKEN. LANDING GEAR UNSAFE LIGHT STAYS ON WITH GEAR UP. FOUND NOSE GEAR DOOR SEQUENCE VALVE INOPERTIVE. 1L71 3O RTA25SO 20060327000472006032700047SW 2006 3 27 2006FA0000285 120060302G2730740101000 TORQUE TUBE MOONEYM20 M20J 5870219SW TRIM SYS WORN B CTYRO OTHER O OTHER NRNOT REPORTED 1 GL21913JN7274 241184 EMPENNAGE TRIM CONTROL TORQUE FOUND TO HAVE A DEEP GROOVE FROM WEARING ON CAT TRACK/GROMMET WHERE IT PASSES THROUGH STIFFENERS. THIS TUBE WAS ALSO WELD REPAIRED AT SOME TIME PREVIOUS THEN SWAPPED END FOR END SO TUBE WOULD WEAR ON A NEW SURFACE. IT APPEARS THIS WAS DONE DURING AN AIRCRAFT REPAIR AFTER AN ACCIDENT. NO DOCUMENTATION IN AIRCRAFT RECORDS OF THIS REPAIR. NEW TUBE INSTALLED BY REPAIR STATION. THIS AIRCRAFT HAD BEEN THROUGH NUMEROUS ANNUAL INSPECTIONS AND NOT REPLACED OR DOCUMENTED. 1L71 3O 2A3 20060518002522006051800252GL 2006 5 18 2006FA0000286 120060227G7603 THROTTLE CABLE AMTR SONEX SONEX 056085QGL COCKPIT BINDING G A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CRCRUISE 1 GL03415KP20 514 AIRCRAFT EXPERIENCED A LOSS OF POWER, AND A SUBSEQUENT FORCED LANDING RESULTING IN EXTENSIVE DAMAGE TO THE AIRCRAFT, DUE TO THE THROTTLE BEING STUCK IN THE IDLE POSITION. WHILE REDUCING POWER TO THE ENGINE PILOT EXPERIENCED BINDING IN THE THROTTLE CABLE , FURTHER ATTEMPTS TO FREE THE THROTTLE RESULTED IN THE THROTTLE BEING STUCK IN THE IDLE POSITION. FOLLOW ON INSPECTIONS OF THE CARBURETOR AND ASSOCIATED LINKAGE FOUND EXCESSIVE PLAY IN THE CABLE BETWEEN THE THROTTLE CONTROL AND THE FIREWALL. THE EXCESS SLACK IN CABLE WAS NOT SECURED OR CLAMPED CAUSING THE CABLE ASSEMBLY TO BEND WHILE MOVING THE THROTTLE AND CAUSING BINDING. 1L71 3O NCEXPA1L71 20060330000032006033000003NE 2006 3 30 2006FA0000299 120060316G3020 HINGE CONAERLA4 LA4200 5110310NE LYC O360 IO360A1A 41514EA CARB HEAT BOX WORN B K NONE O OTHER ININSP/MAINT 1 EA232994P2470 59 956 L1997351A DURING ANNUAL INSPECTION FOUND ALTERNATE AIR VALVE HINGE WORN THRU. REMOVED HEAT BOX ASSY AND FOUND BOX CRACKED 50 PERCENT AROUND MOUNTING FLANGE. CRACK COULD NOT BE SEEN WITH BOX ON AIRCRAFT. 1H71 3O3 O 1A13 1E10 20060330000832006033000083NM 2006 3 30 2006FA0000300 120060315G2761BACS12HL4H10P BOLT BOEING737 7372H6 1384604NM SPOILER BROKEN D K NONE O OTHER ININSP/MAINT 1 SO25902WG 22620 DURING A CHECK FOUND LOWER AFT BOLT HEAD BROKEN AT ACTUATOR TO MANIFOLD MOUNT FLANGE. NO OTHER DAMAGE FOUND AND NO LEAK SEEN. 2L72 4F RTA16WE 20060331000702006033100070CE 2006 3 31 2006FA0000301 120060304G55510431148 ATTACH FITTING CESSNA150 152 2071835CE HORIZONTAL STAB CRACKED B O OTHER O OTHER NRNOT REPORTED 1 WP214896813660 15281080 PART ATTACHES VERTICAL STABILIZER SPAR TO HORIZONTAL STABILIZER SPAR ATTACH FITTING P/N 0432004-9. PROBABLE CAUSE IS HIGH ACTT. 1H71 3O NT3A19 20060411000522006041100052SO 2006 4 11 2006FA0000302 220060310G74146310 MAGNETO CESSNA185 185F 2072820CE CONT O550 IO550D 17042SO ENGINE CHAFED C O OTHER E VIBRATION/BUFFET CRCRUISE 1 WP23 126 680081 ROUGH MAG IN FLIGHT. FOUND THAT CAPACITOR LEAD WAS INSTALLED ON POINTS BACKWARDS ALLOWING LEAD TO CONTACT MAIN DRIVE GEAR. GEAR HAD EATEN THROUGH INSULATION AND ALL BUT 2 STRANDS OF THE WIRE. MAG WAS NEARING COMPLETE FAILURE. 1H71 3O3 O 3A24 E3SO 20060411000552006041100055SO 2006 4 11 2006FA0000303 220060310G74146310 MAGNETO CESSNA185 185F 2072820CE CONT O550 IO550D 17042SO ENGINE CHAFED C O OTHER E VIBRATION/BUFFET CRCRUISE 1 WP23PKMCD126 680081 ROUGH MAG IN FLIGHT. FOUND THAT CAPACITOR LEAD WAS INSTALLED ON POINTS BACKWARDS ALLOWING LEAD TO CONTACT MAIN DRIVE GEAR. GEAR HAD EATEN THROUGH INSULATION AND ALL BUT 2 STRANDS OF THE WIRE. MAG WAS NEARING COMPLETE FAILURE. 1H71 3O3 O 3A24 E3SO 20060411000532006041100053SO 2006 4 11 2006FA0000304 220060310G74146310 MAGNETO CESSNA185 185F 2072820CE CONT O550 IO550D 17042SO ENGINE CHAFED C A UNSCHED LANDING E VIBRATION/BUFFET CRCRUISE 1 WP23PKMCD126 680081 ROUGH MAG IN FLIGHT. FOUND THAT CAPACITOR LEAD WAS INSTALLED ON POINTS BACKWARDS ALLOWING LEAD TO CONTACT MAIN DRIVE GEAR. GEAR HAD EATEN THROUGH INSULATION AND ALL BUT 2 STRANDS OF THE WIRE. MAG WAS NEARING COMPLETE FAILURE. 1H71 3O3 O 3A24 E3SO 20060411000542006041100054SO 2006 4 11 2006FA0000305 220060310G74146310 MAGNETO CESSNA185 185F 2072820CE CONT O550 IO550D 17042SO ENGINE CHAFED C O OTHER E VIBRATION/BUFFET CRCRUISE 1 WP23PKMCD126 680081 ROUGH MAG IN FLIGHT. FOUND THAT CAPACITOR LEAD WAS INSTALLED ON POINTS BACKWARDS ALLOWING LEAD TO CONTACT MAIN DRIVE GEAR. GEAR HAD EATEN THROUGH INSULATION AND ALL BUT 2 STRANDS OF THE WIRE. MAG WAS NEARING COMPLETE FAILURE. 1H71 3O3 O 3A24 E3SO 20060411001062006041100106SO 2006 4 11 2006FA0000307 220060208G8500 ENGINE CONT BEECH 58 58 1152740CE CONT O550 IO550C SO HARTZLHCJ3Y PHCJ3YF1 GL RT WING UNKNOWN H K NONE O OTHER ININSP/MAINT 1 SW11106GA 824277R TH437 824277R ED3372 RT ENGINE WAS STARTED AND PILOT NOTICED LOW OIL PRESSURE. INSTALLED ANOTHER GAUGE IN LINE TO VERIFY PROBLEM RAN ENGINE, OIL PRESSURE CERTIFIED LOW. CHANGED OIL AND INSPECTED FILTER. FOUND NO OBVIOUS PROBLEMS, STARTED ENGINE, HAD NO OIL PRESSURE, PULLED RELIEF VALVE. DETERMINED THAT SOMETHING INSIDE THE ENGINE WAS COMING APART. REMOVED ENGINE TO SEND BACK TO ENGINE OVERHAULER. (K) 1L72 3O3 O 3A16 E3SO 5 CP36EA 20060411000342006041100034EA 2006 4 11 2006FA0000309 220060224G732063B23440 FLOW DIVIDER CESSNA172 172S 2072439CE LYC IO360 IO360L2A EA MCAULY1A170 1A170E GL ENGINE CORRODED B O OTHER R PARTIAL RPM/PWR LOSS TXTAXI/GRND HDL 1 CE07696MS91 50 172S10079 L3242151E JHA7660 AIRCRAFT FAILED TO START & RUN. NO FUEL FLOW INDICATED ON G-1000. TROUBLSHOOT FUEL SYS & FOUND FUEL NOT PASSING THROUGH FLOW DIVIDER. SENT UNIT FOR REPAIR. AT THAT TIME AIRCRAFT HAD 41.0 HRS SINCE NEW. SECOND TIME AT 91.0 HRS.SINCE NEW, HAD THE SAME PROBLEM AS INDICATED AS ABOVE. BOTH TIMES FOUND THE VALVE STEM STUCK INSIDE THE BORE. APPEARS TO BE A RUST/BROWN COLORED CONTAMINATION AND SLIGHT SCORING. FLOWED FUEL INTO TEST JAR AND NO PARTICLES WAS NOTED ON AIRCRAFT FUEL SYSTEM. APPEARS TO BE CORROSION INSIDE BORE. B&S AIRCRAFT POLISHED VALVE STEM AND BORE, OPS. CK. OK. 1H71 3O3 ONT3A12 1E10 5 NP857 20060411000362006041100036CE 2006 4 11 2006FA0000311 120060224G2842 FLOAT CESSNA172 172H 2072424CE FUEL INDICATION FAILED D K NONE N FALSE WARNING ININSP/MAINT 1 NM013786R 17255586 LEFT WING FUEL GAGE REGISTERED EMPTY. UPON INSPECTION OF THE FLOAT ASSEMBLY, FOUND FLOAT TO BE ONE THIRD FULL OF FUEL. METAL FLOAT HAS MULTIPLE PIN HOLES. RIGHT SIDE WAS FINE - NO LEAKS. 1H71 3O NT3A12 20060411000372006041100037EA 2006 4 11 2006FA0000312 220060224G7261156F00512D0260 HOSE PIPER PA31T PA31T 7103124SO PWA PT6 PT6A28 EA HARTZLHCB3T HCB3TN3 GL ENGINE OIL DAMAGED B A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 GL11220FS 31T7620052 PCE51064 BU13482 DURING CLIMB, PILOT NOTED RT OIL PRESS FLUTUATING SLIGHTLY & SLOWLY FALLING. ENGINE SHUTDOWN & RETURNED TO BASE. INVESTIGATION REVEALED A LEAKING OIL COOLER HOSE. LEAK POINT COVERED BY FIRESLEEVING. HOSE REMOVED & SLEEVING CUT OPEN REVEALING WIRE BRAID. EXTERNAL EXAMINATION DID NOT INDICATE ANY OBVIOUS VISIBLE DEFECT. FURTHER INVESTIGATION USING A FLEXIBLE LIGHT SOURCE REVEALED A FAILED INNER WALL MID-WAY IN THE HOSE AND ON THE INSIDE RADIUS OF THE HOSE BEND. THE HOSE MANF. DATE 01/04. PROBABLE CAUSE WAS INCORRECT HANDLING OR INSTALLATION OF HOSE AT SOME POINT WHICH RESULTED IN KINKING OF THE HOSE AND EVENTUAL FAILURE OF THE INNER WALL. 1L72 3T4 T A8EA E4EA 6 CP15EA 20060411000382006041100038CE 2006 4 11 2006FA0000313 120060226G5346051313211 BRACKET CESSNA175 175 2072502CE ENGINE MOUNT CRACKED D K NONE O OTHER ININSP/MAINT 1 CE077536M2641 55836 DURING VISUAL INSPECTION OF UPPER ENGINE MOUNT BRACKETS IN THE UPPER ENGINE MOUNT STRINGER ASSEMBLIES, FOUND THE L/H 0513132-11 BRACKET CRACKED. INSPECTION WAS PERFORMED DUE TO RECENT REPORTS OF FINDING BRACKETS CRACKED ON LIKE MODELS OF AIRCRAFT. 1H71 3O NT3A17 20060411000402006041100040CE 2006 4 11 2006FA0000318 120060227G5346051313211 BRACKET CESSNA175 175 2072502CE ENGINE MOUNT CRACKED D K NONE O OTHER ININSP/MAINT 1 CE07141JA4791 55224 FOUND THE LEFT UPPER ENGINE MOUNT BRACKET P/N 0513132-11 CRACKED THROUGH AROUND THE WASHER. BRACKET IS LOCATED AT THE FRONT OF THE 0513132-3 ENGINE MOUNT STRINGER AND IS DIFFICULT TO SEE DURING ROUTINE INSPECTIONS. INSPECTION WAS PERFORMED DUE TO SEVERAL OTHER CASES OF THE BRACKET BEING FOUND CRACKED ON LIKE AIRCRAFT. 1H71 3O NT3A17 20060411000422006041100042CE 2006 4 11 2006FA0000320 120060301G5346051313211 BRACKET CESSNA175 175A 2072504CE ENG MOUNT CRACKED D K NONE O OTHER ININSP/MAINT 1 CE076997E1900 56497 DURING VISUAL INSPECTION FOUND THE 0513132-11 UPPER RIGHT HAND ENGINE MOUNT BRACKET IN THE 0513132-4 STRINGER ASSEMBLY CRACKED. INSPECTION WAS PERFORMED DUE TO OTHER REPORTED FAILURES OF THIS BRACKET ON THE SAME MODEL OF AIRCRAFT. RECOMMEND INSPECTION OF BRACKETS IN ALL AIRCRAFT WITH THE 0513132-4 ENGINE MOUNT STINGER ASSEMBLY. 1H71 3O 3A17 20060411000432006041100043CE 2006 4 11 2006FA0000321 120060301G554105310051 RIB CESSNA172 172 2072402CE RUDDER MISSING D K NONE O OTHER NRNOT REPORTED 1 NM096775A2262 28875 RUDDER WAS REMOVED TO REPLACE CRACKED CORRUGATED SKIN BETWEEN LOWER TWO RIBS. ON SKIN REMOVAL, IT WAS DISCOVERED THAT SLANT RIB 0531005-1, (EXTENSION OF REAR SPAR) WAS MISSING. THERE WERE NO HOLES DRILLED IN BOTTOM RIB P/N 0531001-25 OR RIB P/N 0531001-22 TO WHICH THE SLANT RIB ATTACHES. LOGBOOK INDICATES THAT RUDDER WAS NEVER REPLACED OR REPAIRED, SO THE ASSUMPTION IS THAT THE PART WAS LEFT OUT DURING AIRCRAFT CONSTRUCTION. NEW RIB WAS INSTALLED. 1H71 3O NT3A12 20060413002592006041300259 2006 4 13 2006FA0000325 120060314G251071513 SEAT FRAME BROKEN B K NONE O OTHER TXTAXI/GRND HDL 1 SW15116SG544 50 THE LOWER SEAT FRAME CONSISTS OF A PERIMETER RECTANGULAR TUBE FRAME THAT HAS THE ENDS OF STEEL STRAPS WELDED TO IT TO FORM A LOOSE WEBBING ASSEMBLY WHICH SUPPORTS THE SEAT CUSHION. DURING A PREFLIGHT THE PILOT NOTICED THE SEAT SAGGING AND FOUND THE ENDS OF TWO STRAPS HAD BROKEN WELDS. 20060413002712006041300271 2006 4 13 2006FA0000326 420060407G3421 ART HORIZION RAYTHNDH125 HAWKER800XP 7150012CE COCKPIT MISWIRED D K NONE O OTHER TXTAXI/GRND HDL 1 NE01875LP 258308 PILOT REPORTED STANDBY ARTIFICIAL HORIZON ILS NEEDLES MOVE IN OPPISITE DIRECTION OF #1 AND #2 ILS NEEDLES ON ILS APPROACH. CONFIRMED REPORT. FOUND THAT ARKANSAS AEROSPACE COMPLETION DRAWINGS( WERE NOT CORRECT WHEN COMPARED TO HONEYWELL RNZ-850 INSTALLATION MANUAL. RNZ-850 PIN B78 VOR LFT DEVIATION WAS WIRED TO STANDBY HORIZON (JET ADI-322B) PIN G NAV DEVIATION +RT. RNZ-850 PIN B75 DEV RTN WAS WIRED TO ADI-322B PIN H NAV DEVIATION + LT. SWAPPED WIRES AT ADI-322B AND TESTED. ILS DEVIATION LEFT AND RIGHT NOW MATCHES PRIMARY ILS DISPLAYS. 2L72 4F RTA3EU 20060412000402006041200040SO 2006 4 12 2006FA0000327 220060313G7414 IMPULSE COUPLING BEECH 95 95B55 1152729CE CONT O470 IO470L 17026SO MAGNETO RUSTED B YEBRK NONE O OTHER ININSP/MAINT 1 CE052278S448 TC2110 DURING A ROUTINE INSP, ALL MAGNETOS WERE REMOVED FOR POINTS AND CONDENSER REPLACEMENT. RUST WAS FOUND ON THE FLYWEIGHT/AXLE AREA OF THE IMPULSE COUPLING. A WEAR CHECK WAS MADE AND IT WAS DETERMINED THAT ALL COUPLINGS FAILED IAW MSB. NOTE: THE FLYWEIGHT/ AXLE PIN WEAR IS IN EXCESS OF .014 AND MAY BE DUE TO RUST. THIS AREA OF INSPECTION MAY BE OVERLOOKED DUE TO THE OMISSION OF MANY IMPULSE COUPLINGS INSTALLED ON ENGINE NOT INCLUDED IN AD. (K) 1L72 3O3 ORT3A16 3E1 20060412000782006041200078EA 2006 4 12 2006FA0000328 220060309G7414M3548 SHAFT PIPER PA28 PA28R201 7102816SO LYC O360 IO360C1C6 41514EA MCAULY2D34C B2D34C213 GL MAGNETO SHEARED B UC2RK NONE O OTHER ININSP/MAINT 1 GL195321U 98070601 2844042 L2958751A 002421 ENGINE RUNUP INDICATED A DEAD MAGNETO. REMOVED AND DISASSEMBLED MAGNETO HOUSING. FOUND ROTOR SHAFT SHEARED OFF AT BOTTOM OF CAM SLOT. A FEW CRACKED SHAFTS HAVE BEEN FOUND AT 500 HR INSPECTIONS. RECOMMEND CLOSE INSPECTION OF THIS AREA AT REPAIR AND OVERHAUL. (K) 1L71 3O3 O 2A13 1E10 5 CP7EA 20060413001682006041300168GL 2006 4 13 2006FA0000330 220060410G723059084 STATOR WILINTFJ44 FJ44 66000GL COMPRESSOR DETERIORATED B WI5RK NONE O OTHER ININSP/MAINT 1 GL23 126173 3RD STAGE IP STATOR ABRADABLE WAS EXFOLIATING CAUSING THE 3RD STAGE IP BLADES TO CONTACT THE STATOR ABRADABLE. THIS RESULT IN N1 LOCK-UP. BASED UPON HARDWARE EVALUATION, ROOT CAUSE OF THE ABRADABLE EXFOLIATING WAS DUE TO THE WATER WASH PROCEDURES (COASTAL A/C) NOT BEING FOLLOWED PG THE ENGINE MM. (K) 4 F E3GL 20060412000382006041200038SO 2006 4 12 2006FA0000331 120060306G2140A23D0475 REGULATOR PIPER PA23 PA23250 7102308SO LYC O540 TIO540* 41532EA CABIN HEATER LEAKING B GFVRK NONE O OTHER ININSP/MAINT 1 NM136549A 277954006 AIRCRAFT RECEIVED FROM NEW OWNER WANTING HEATER MADE OPERATIONAL: TOTALLY DEACTIVATED. REPLACED HEATER ASSY DUE TO EXTREME DETORATION. FUEL REGULATOR REPLACED DUE TO LEAKAGE AND FAILURE TO REGULATE FOUND INLET PORT PARTIALLY PLUGGED BY CORROSION BY-PRODUCTS AND REMNANTS OF DAMAGED THREADS. N/E REPAIRABLE. (K) 1L72 3O3 O 1A10 E14EA 20060413002722006041300272CE 2006 4 13 2006FA0000332 120060327G5412569500511 BULKHEAD CESSNA340 340A 2076405CE LT WING CORRODED D K NONE O OTHER ININSP/MAINT 1 GL25340JY3462 340A0979 DURING 500 HR. VISUAL INSPECTION PER AD2000-01-16 PARA (D) FOUND LEFT ENGINE AFT CANTED BULKHEAD #5695005-11 AND SUPPORT DOUBLER #5695005-6 CORRODED AND HEAT DAMAGED COMPLETELY THROUGH STRUCTURE. DAMAGE LOCATED NEAR OUTBOARD SECTION ABOVE EXHAUST ELBOW CUT OUT AREA. 1L72 3O 3A25 20060510002492006051000249CE 2006 5 10 2006FA0000333 120060327G5412569500511 BULKHEAD CESSNA340 340A 2076405CE LT WING CORRODED D K NONE O OTHER ININSP/MAINT 1 GL25340JY3462 340A0979 DURING 500 HR. VISUAL INSPECTION PER AD2000-01-16 PARA (D) FOUND LEFT ENGINE AFT CANTED BULKHEAD NR 5695005-11 AND SUPPORT DOUBLER NR 5695005-6 CORRODED AND HEAT DAMAGED COMPLETELY THROUGH STRUCTURE. DAMAGE LOCATED NEAR OB SECTION ABOVE EXHAUST ELBOW CUT OUT AREA. 1L72 3O 3A25 20060511002502006051100250EA 2006 5 11 2006FA0000335 220060322G72103013132 SLEEVE PWA PT6A27 PWA PT6 PT6A27 52043EA ENGINE SHIFTED B K NONE O OTHER ININSP/MAINT 1 SO03 805 42083100 PCE42083 OPERATOR ATTEMPTED TO ROTATE THE PROPELLER DURING A PREFLIGHT CHECK AND NOTED PROP SHAFT LOOSENESS AND DRAG. THE ENGINE WAS REMOVED FOR REPAIR. EXAMINATION OF THE 2ND STAGE CARRIER IN THE RGB REVEALED THAT THE SLEEVE USED TO REPAIR THE NR 5 BEARING JOURNAL HAD SHIFTED OFF OF THE JOURNAL. THERE WAS NO COLLATERAL DAMAGE DUE TO SLEEVE SHIFT. 4 T E4EA 20060414000942006041400094SO 2006 4 14 2006FA0000337 120060406G2434ALU8539LS ALTERNATOR PIPER PA46 PA46350P 7104602SO ENGINE BURNED D K NONE O OTHER ININSP/MAINT 1 NM09110ST142 4636373 OUTPUT POST WAS LOOSE AND BURNED. TERMINAL ON OUTPUT WIRE GOING TO BOSS BAR WAS BURNED, MELTED, AND SEPARATED FROM ALTERNATOR. (K) 1L71 3O RTA25SO 20060417000452006041700045SO 2006 4 17 2006FA0000338 120060317G5711PA28140 SPAR PIPER PA28 PA28140 7102802SO LYC O320 O320* 41508EA WING CORRODED D K NONE O OTHER ININSP/MAINT 1 CE036399W 2820467 DURING 100 HR INSPECTION ON REAR SPAR CHANNEL, RIVET HEADS WERE POPPED ON BOTH SIDES. A COMPLETE INSPECTION REVEALED SEVERE CORROSION BETWEEN CHANNEL AND STEEL PLATES. ALSO, SEVERE CORROSION EXISTED BETWEEN REAR IB ATTACH FITTINGS TO SPAR. THE ATTACH FITTINGS HID VIEW FROM THE OUTSIDE. WITH NO INSPECTION PANELS IN THAT AREA THE INSPECTION HAS TO BE MADE THROUGH THE IB RIB LOOKING AFT. THE STRUCTURAL INTEGRITY OF THE LT SPAR ATTACH AREA WAS SEVERELY COMPROMISED. (K) 1L71 3O3 O 2A13 E274 20060414000922006041400092SO 2006 4 14 2006FA0000339 120060317G571162054000 SPAR PIPER PA28 PA28140 7102802SO LT WING CORRODED C K NONE O OTHER ININSP/MAINT 1 CE036399W3744 2820467 DURING 100 HR INSPECTION ON REAR SPAR CHANNEL, RIVET HEADS WERE POPPED ON BOTH SIDES. A COMPLETE INSPECTION REVEALED SEVERE CORROSION BETWEEN CHANNEL AND STEEL PLATES. ALSO, SEVERE CORROSION EXISTED BETWEEN REAR IB ATTACH FITTINGS TO SPAR. THE ATTACH FITTINGS HID VIEW FROM THE OUTSIDE. WITH NO INSPECTION PANELS IN THAT AREA THE INSPECTION HAS TO BE MADE THROUGH THE IB RIB LOOKING AFT. THE STRUCTURAL INTEGRITY OF THE LT SPAR ATTACH AREA WAS SEVERELY COMPROMISED. (K) 1L71 3O 2A13 20060419002072006041900207CE 2006 4 19 2006FA0000340 120060210G3397L143J20 WIRE BEECH 36 A36 1151604CE CONT O550 IO550B SO MCAULY3A32C D3A32C* GL RT WING NAV LITECHAFED B O OTHER J WARNING INDICATION CRCRUISE 1 WP23806NH E2702 686012 912713 PILOT REPORTED NAVIGATION LIGHT BREAKER SWITCH (POPPED) IN FLIGHT AND WAS NOT ABLE TO RESET. MAINTENANCE PERSONAL TROUBLESHOT NAVIGATION LIGHT SYSTEM AND FOUND A SHORT IN THE WIRING IN THE RT WING AT APPROXIMATE WING STATION 162.5. A NEW WIRE WAS PULLED THROUGH TO REPLACE THE OLD WIRE. TIME IN SERVICE IS A FACTOR IN THIS OCCURRENCE. ALSO IN SERVICE IS A FACTOR IN THIS OCCURRENCE. ALSO THE WIRE LAYS IN A STRINGER CHANNEL AND HAS NO OTHER MEANS OF SUPPORT OTHER THAN GLUED IN STRIPS AT VARIOUS INTERVALS TO KEEP THE WIRE IN THE CHANNEL. THERE IS NO ACCESS TO THIS WIRE FROM WING STA 122.75 TO 191.00. THERE SHOULD BE A PLASTIC CONDUIT TUBING FOR THIS WIRE TO RUN THROUGH. (K) 1L71 3O3 O 3A15 E3SO 5 CP21EA 20060419002192006041900219NM 2006 4 19 2006FA0000342 120060315G3520417N31002933E CABLE BOEING737 7373G7 1384595NM GE CFM56 CFM563B1 13802NE PX OXY SYS MISROUTED B LH6YK NONE O OTHER ININSP/MAINT 1 EA35370WL 24011 (REF: ATC0662) THE ACTUATING CABLE TO THE CHEMICAL OXYGEN GENERATORS ON PASSENGER SERVICE UNITS WERE FOUND INCORRECTLY ROUTED. IE: IT WAS UNDER THE PIN AND RESTING ON THE PLASTIC MOULDING. DEFECT RAISED AS AN (IORS) INTERNAL OCCURRENCIES REPORT AND UPGRADED TO MALFUNCTION AND DEFECT REPORT DUE TO SYSTEM BEING (EMERGENCY). (K) 2L72 4F4 FRTA16WE E2GL 20060419002062006041900206SO 2006 4 19 2006FA0000343 220060401G7414M3081 POINTS AMTR LANCARLC41550FG 5150001GL CONT O550 TSIO550C SO RT MAGNETO BROKEN D O OTHER L NO TEST TXTAXI/GRND HDL 1 NM0979HR 41017 802655 ON ENGINE GROUND RUN PRIOR TO FLIGHT MAGNETO CHECK FOUND RT MAGNETO HAD FAILED INSPECTION FOUND POINTS BROKEN PICTURE INCLOSED. (K) 1L71 3O3 ORTEXPA1L71E5SO 20060419003212006041900321SO 2006 4 19 2006FA0000344 120060317G27318646002 CABLE PIPER PA44 PA44180 7104402SO LYC O360 O360* 41514EA FUSELAGE JAMMED B RJURK NONE O OTHER ININSP/MAINT 1 WP19259AT3151 4496080 PILOT REPORTED THAT STABILATOR TRIM WAS JAMMING IN THE NOSE-UP POSITION. IT WAS DISCOVERED THAT TRIM CABLE TURNBUCKLE WAS CATCHING ON BULKHEAD JAMMING CABLE. CABLE TENSIONS WERE ADJUSTED TO SPECIFICATIONS AND PROBLEM REPEATED. RECOMMEND SLIGHT RADIUS OF MATERIAL AND REINFORCEMENT OF AFFECTED AREA TO PREVENT RECURRENCE OF PROBLEM. (K) 1L72 3O3 O A19S0 E286 20060419003122006041900312CE 2006 4 19 2006FA0000345 120060215G3230NAS4645A15 BOLT CESSNA177 177RG 2073709CE NLG BACKED OUT D K NONE O OTHER ININSP/MAINT 1 CE0352643 177RG1225 NOSE LANDING GEAR FAILED TO LOCKDOWN. THE NAS404-5A15 BOLT THAT BOTH SECURES AND PROVIDES A PIVOT POINT FOR THE LOCK ASSY TO THE DRAG LINK HAD BACKED OUT OF THE DRAG LINK TOTALLY DISCONNECTING THE LOCK ASSY FROM THE DRAG LINK. THERE WAS EVIDENCE OF RED LOCKTITE IN THE DRAG LINK AS IS REQUIRED BY THE SRM BUT IT BACKED OUT ANY WAY. THIS BOLT IS NOT A DRILLED HEAD BOLT, BUT I RECOMMEND THAT IT BE REPLACED WITH ONE TO AVOID REOCCURRENCE. (K) 1H71 3O A20CE 20060419003272006041900327CE 2006 4 19 2006FA0000346 120060320G37101U478003 PUMP BEECH 33 F33A 1151425CE CONT O520 IO520BB 17032SO ENGINE WORN B VJ3RK NONE O OTHER ININSP/MAINT 1 WP075521A304 CE1338 830070R PILOT REPORTED THAT AT 1700 RPM INSTRUMENT AIR PRESSURE (3.5 HG) UPON TROUBLESHOOTING OF THE INSTRUMENT AIR PRESSURE SYSTEM TECHNICIAN FOUND AIR PUMP WAS NOT PRODUCING ENOUGH PRESSURE. PROBABLE CAUSE IS UNKNOWN AT THIS TIME. NO RECOMMENDATION AT THIS TIME EITHER. (K) 1L71 3O3 O 3A15 E5CE 20060419003202006041900320EA 2006 4 19 2006FA0000347 220060324G7322105267 CARBURETOR CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA ENGINE CONTAMINATED H CE8SK NONE Y ENGINE STOPPAGE TOTAKEOFF 1 SO1525566 15280734 RL2324815 CONTAMINANT FOUND INSIDE OF THE MAIN JET OF THE CARBURETOR. ENGINE QUIT ON TAKE OFF ROLL. (K) 1H71 3O3 ONT3A19 E223 20060502000042006050200004 2006 5 2 2006FA0000348 120060227G8011MHB4016R STARTER ENGINE NOISY B WS9RO OTHER O OTHER TXTAXI/GRND HDL 1 NM07 STARTER WHINING, AND WILL NOT START ENGINE. WILL START WITH HAND PROP, BUT WHINES. (K) 20060419003242006041900324NM 2006 4 19 2006FA0000349 120060328G5711 SPAR CAP UNIVAR415 415C 0420302NM CONT C90 C90* 17009SO RT WING CRACKED B N5DRK NONE O OTHER ININSP/MAINT 1 WP153158H 3783 DURING ACCOMPLISHMENT OF SB NR 32, A 0.625 INCH LONG, SPANWISE CRACK WAS NOTED ON THE RT UPPER SPAR CAP IN THE MAIN SPAR CENTER SECTION APPROX 0.250 INCH IB OF THE CENTER SECTION OB END. PROBABLE CAUSE IS UNKNOWN. (K) 1L71 3O3 O A718 E252 20060419003222006041900322NM 2006 4 19 2006FA0000350 120060321G274007322P11070 BALL END BOEING737 737* NM HORIZ STABILIZERFOD B K NONE O OTHER ININSP/MAINT 1 NM01 0728 THE MAJOR COMPONENTS ARE BEYOND ECONOMICAL REPAIR (SCRAP). THE DAMAGE WAS CAUSED BY A FOREIGH OBJECT, PROBABLY LOOSE BALL. THIS CAN HAPPEN ANYTIME THE BALLNUT ASSY IS REMOVED FROM THE SCREWSHAFT. (K) 2L72 4F RTA16WE 20060502000062006050200006 2006 5 2 2006FA0000351 120060320G8011ES6462751 STARTER ENGINE TIGHT B WS9RK NONE O OTHER ININSP/MAINT 1 NM07 STARTER IS TOO TIGHT AND WOULD NOT TURN. (K) 20060419003282006041900328CE 2006 4 19 2006FA0000352 120060322G5312071220510 BULKHEAD CESSNA182 182A 2072704CE CONT O470 O470L 17026SO AFT FUSELAGE CRACKED D K NONE O OTHER ININSP/MAINT 1 NM072233G 51533 668916L BULKHEAD, PN 071220510, CRACKED AT TIE DOWN HOLE. BULKHEAD, PN 0712206 CRACKED AT BOLT HOLES ATTACHMENT TO ELEVATOR BELLCRANK SUPPORT MOUNT. (K) 1H71 3O3 ONT3A13 E273 20060419003232006041900323CE 2006 4 19 2006FA0000353 120060322G5312071220510 BULKHEAD CESSNA182 182A 2072704CE CONT O470 O470L 17026SO FUSELAGE TAIL CRACKED D K NONE O OTHER ININSP/MAINT 1 NM072233G 51533 668916L BULKHEAD, PN 071220510, CRACKED AT TIE DOWN HOLE. BULKHEAD, PN 0712206, CRACKED AT BOLTHOLES ATTACHMENT TO ELEVATOR BELLCRANK SUPPORT MOUNT. (K) 1H71 3O3 ONT3A13 E273 20060502000052006050200005 2006 5 2 2006FA0000354 120060228G81004066109005 TURBOCHARGER ENGINE WEAK B WS9RK NONE O OTHER ININSP/MAINT 1 NM07 2 TURBO CHARGER WOULD NOT MAKE ENOUGH BOOST. (K) 20060419003252006041900325NE 2006 4 19 2006FA0000355 220060318G73200292858570 HMU UROCOPEC130 EC130B4 8680989EU TMECA ARRIELARRIEL2B NE ENGINE UNKNOWN C A UNSCHED LANDING EJ VIBRATION/BUFFET WARNING INDICATION LDLANDING 1 WP1311QF 3482 PRECAUTIONARY LANDING DUE TO BANG HEARD IN FLIGHT BY PILOT. NORMAL LANDING ACCOMPLISHED W/O ACCIDENT, OR INJURIES. AC LANDED ON PRIVATE PROPERTY. UPON LANDING, GOVERNOR WARNING LIGHT ILLUMINATED. SUBSEQUENT INVESTIGATIVE TROUBLESHOOTING REVEALED VEMD TO DISPLAY A CODE (192) HMU FAULT, INDICATING A FAILURE OF EBCAU STEPPER MOTOR. VISUALLY INSPECTED ENG ASSY AND SURGE BLEED VALVE ASSY. NO DEFECTS NOTED, HMU AND EBCAU UNITS WERE REPLACED WITH SERVICABLE UNITS. GROUND AND FLIGHT TESTS PROVED GOOD WITH NO INDICATED ERROR CODES. AC TEST FLOWN BACK TO MAINTENANCE BASE WITH NO FURTHER PROBLEMS NOTED. DETERMINED THE INITIAL BANG HEAR IN FLIGHT WAS MOST LIKELY A COMPRESSOR STALL DUE TO THE MALFUNCTION HMU. (K) 1G72 3U3 U H9EU E00054EN 20060419003262006041900326CE 2006 4 19 2006FA0000356 120060313G710010191000495 DUCT BEECH 200 B200 1152922CE LT ENGINE CRACKED B EHHRK NONE O OTHER ININSP/MAINT 1 EA17326PG BB1709 LT ENGINE LOWER AFT COWLING, LWR DUCT FOUND CRACKED ABOUT 80 PERCENT ITS ENTIRE WIDTH ALONG FIRST RIVET ROW. REMOVED CRACKED DUCT AND FOUND NOT TO BE ROLLED ENOUGH. THIS PUT STRESS ON RIVET ROW. NEW SPARE PART ORDER FROM MFG WAS ROLLED CORRECTLY AND FIT WITHOUT STRESS. (K) 1L72 4T A24CE 20060418002182006041800218EA 2006 4 18 2006FA0000357 220060313G73202576543 SERVO CESSNA206 206H 2073301CE LYC O540 IO540AC1A5 EA ENGINE FUEL SYS INOPERATIVE B EHHRK NONE Y ENGINE STOPPAGE TXTAXI/GRND HDL 1 EA17236KS 20608236 AIRCRAFT LANDED AND ENGINE QUIT. TO RESTART ENGINE MIXTURE HAD TO PULL MIXTURE BACK TO .5 INCH OF IDLE CUT TO KEEP ENGINE RUNNING. TRIED TO ADJUST IDLE MIXTURE WITHOUT SUCCESS. AT THE ADJUSTMENT LEANEST SETTING THERE WAS STILL A 600 RPM RAISE WHEN MIXTURE PULLED TO IDLE CUT OFF. REMOVED SERVO AND SENT. REINSTALLED ON RETURN WITH SMALL ADJUSTMENTS ENGINE RAN SATISFACTORY. THIS SAME SYMPTOMS SHOW ON ANOTHER AC WITH SAME PN SERVO. THE AIRCRAFT HAD 129 HOURS, THIS SERVO EXCHANGED FOR AN OVERHAULED UNIT. TECH SUPPORT STATED THAT THE DIAPHRAGMS HAVE SHIFTED AND THE METERING SEATS NEEDED POLISHING. (K) 1H71 3O3 ORTA4CE 1E4 20060419002032006041900203NM 2006 4 19 2006FA0000358 120060321G274007322P11070 BALL SCREW BOEING737 737* NM STABILIZER FOD B N9GRK NONE O OTHER ININSP/MAINT 1 NM01 0728 FOREIGH OBJECT DAMAGE DISCOVERED DURING INSPECTION OF BALLSCREW ASSY BY SUBCONTRACTOR. THE MAJOR COMPONENTS ARE BEYOND ECONOMIC REPAIR (SCRAP). THE DAMAGE WAS CAUSED BY A FOREIGN OBJECT, PROBABLY LOOSE BALL. THIS CAN HAPPEN ANYTIME THE BALLNUT ASSY IS REMOVED FROM THE SCREWSHAFT. (K) 2L72 4F RTA16WE 20060502000032006050200003 2006 5 2 2006FA0000359 120060322G8011ES6462751 STARTER ENGINE TIGHT B WS9RK NONE O OTHER NRNOT REPORTED 1 NM07 STARTER TOO TIGHT. (K) 20060419001682006041900168 2006 4 19 2006FA0000360 420060314G6113D78115P SPINNER BEECH 58 58 1152740CE MCAULY3AF32C3AF32C512 GL ENGINE CRACKED C K NONE O OTHER ININSP/MAINT 1 WP01 TH2135 SPINNER HAS CRACKS IN 3 PLACES NEAR SCREW HOLES ADJACENT TO PROPELLER BLADES. (K) 1L72 3O 3A16 5 CP22EA 20060418002192006041800219CE 2006 4 18 2006FA0000361 120060310G2910605700311 FLEX LINE LEAR 60 60LEAR 5170707CE HYD SYS RUPTURED D A UNSCHED LANDING KF FLUID LOSS FLT CONT AFFECTED CRCRUISE 1 SW11898PA 111 DURING FLIGHT, LOST NR 1 HYDRAULIC PRESSURE, DIVERTED INTO AIRPORT AND LANDED WITHOUT INCIDENT. TROUBLESHOOT AND FOUND RUPTURED HYDRAULIC FLEX LINE, PN 605700311 WHICH IS MOUNTED ON THE PRESSURE SIDE OF THE HYDRAULIC EDP. INSTALLED NEW HYDRAULIC FLEX LINE WITH PN 605700311. (K) 2L72 4F RTA10CE 20060419001942006041900194EU 2006 4 19 2006FA0000362 120060314G6220C622A1002104 PLATE UROCOPEC120 EC120B 8680987EU MAIN ROTOR HEAD UNBONDED B KW1RK NONE O OTHER ININSP/MAINT 1 EA07453F 3429 M309 1205 LOWER DROOP RING WEAR PLATE BECAME UNBONDED AND CAME OFF THE MAIN ROTOR HUB. THE ENTIRE PLATE WAS FOUND APPROXIMATELY 20 FT FROM THE AIRCRAFT. IT IS NOT CLEAR WHETHER THE PART FELL OFF DURING ENGINE START UP OR SHUTDOWN. WE BELIEVE THE UNBONDING TO BE THE RESULT OF THE DROOP RING STOPS COMING INTO CONTACT WITH THE WEARPLATE, DURING PERIODS OF TIME WHEN THE AIRCRAFT IS STATIC ON THE RAMP AND SUBJECT TO HIGH WINDS. RECOMMEND SECURING THE MAIN ROTOR BLADES WHEN THE PREVAILING WINDS REACH 15 KNOTS. (K) 1G72 3U NCR0001RD 20060418002212006041800221SO 2006 4 18 2006FA0000363 120060301G270062701100 CABLE PIPER PA28 PA28R201 7102816SO LYC O360 IO360A1A 41514EA FUSELAGE FRAYED B WIWRK NONE O OTHER ININSP/MAINT 1 WP07962WW4810 2844022 WHILE CONDUCTING AN ANNUAL INSPECTION PRIOR TO PLACING THE AIRCRAFT ONLINE AFTER PURCHASING IT FROM A LOCAL OPERATOR, BOTH FORWARD RUDDER CABLES WERE FOUND TO BE BADLY WORN AND FRAYED. RESEARCH OF THE MAINTENANCE RECORDS SHOWED THAT THE PREVIOUS OWNERS HAD FAILED TO COMPLY WITH SB WHICH REQUIRES REPETITIVE INSPECTIONS OF ALL FLIGHT CONTROL CABLES. THIS SB WAS APPLICABLE TO THIS AIRCRAFT. (K) 1L71 3O3 O 2A13 1E10 20060419002042006041900204SO 2006 4 19 2006FA0000364 120060301G272062701124 CABLE PIPER PA28 PA28R201 7102816SO LYC O360 IO360A1A 41514EA FUSELAGE FRAYED B WIWRK NONE O OTHER ININSP/MAINT 1 WP07962WW4810 2844022 WHILE CONDUCTING AN ANNUAL INSPECTION PRIOR TO PLACING THE AIRCRAFT ONLINE AFTER PURCHASING IT FROM A LOCAL OPERATOR THE RT AILERON BALANCE CABLE WAS FOUND TO BE BADLY WORN AND FRAYED WITH ONLY A FEW STRANDS LT INTACT. RESEARCH OF THE MAINTENANCE RECORDS SHOWED THAT THE PREVIOUS OWNERS HAD FAILED TO COMPLY WITH SB WHICH REQUIRES REPETITIVE INSPECTIONS OF ALL FLIGHT CONTROL CABLES. THIS SB WAS APPLICABLE TO THIS AIRCRAFT. (K) 1L71 3O3 O 2A13 1E10 20060419002052006041900205SO 2006 4 19 2006FA0000365 120060301G274062701103 CABLE PIPER PA28 PA28R201 7102816SO LYC O360 IO360A1A 41514EA FUSELAGE FRAYED B WIWRK NONE O OTHER ININSP/MAINT 1 WP07962WW4810 2844022 WHILE CONDUCTING AN ANNUAL INSPECTION PRIOR TO PLACING THE AIRCRAFT ONLINE AFTER PURCHASING IT FROM A LOCAL OPERATOR THE LT STABILATOR CABLE WAS FOUND TO BE BADLY WORN AND FRAYED WITH ONLY A FEW STRANDS LT INTACT. RESEARCH OF THE MAINTENANCE RECORDS SHOWED THAT THE PREVIOUS OWNERS HAD FAILED TO COMPLY WITH SB WHICH REQUIRES REPETITIVE INSPECTIONS OF ALL FLIGHT CONTROL CABLES. THIS SB WAS APPLICABLE TO THIS AIRCRAFT. (K) 1L71 3O3 O 2A13 1E10 20060419002642006041900264SO 2006 4 19 2006FA0000366 120060301G274062701102 CABLE PIPER PA28 PA28R201 7102816SO LYC O360 IO360A1A 41514EA FUSELAGE FRAYED B WIWRK NONE O OTHER ININSP/MAINT 1 WP07962WW4810 2844022 WHILE CONDUCTING AN ANNUAL INSPECTION PRIOR TO PLACING THE AIRCRAFT ONLINE AFTER PURCHASING IT FROM A LOCAL OPERATOR THE RT FWD STABILATOR CABLE WAS FOUND TO BE BADLY WORN AND FRAYED. RESEARCH OF THE MAINTENANCE RECORDS SHOWED THAT THE PREVIOUS OWNERS HAD FAILED TO COMPLY WITH SB WHICH REQUIRES REPETITIVE INSPECTIONS OF ALL FLIGHT CONTROL CABLES. THIS SB WAS APPLICABLE TO THIS AIRCRAFT. (K) 1L71 3O3 O 2A13 1E10 20060419002352006041900235SO 2006 4 19 2006FA0000367 120060301G274062701100 CABLE PIPER PA28 PA28R201 7102816SO LYC O360 IO360A1A 41514EA FUSELAGE FRAYED B WIWRK NONE O OTHER ININSP/MAINT 1 WP07963PA5350 2844023 WHILE CONDUCTING AN ANNUAL INSPECTION PRIOR TO PLACING THE AIRCRAFT ONLINE AFTER PURCHASING IT FROM A LOCAL OPERATOR THE LT FORWARD STABILATOR CABLE WAS FOUND TO BE BADLY WORN AND FRAYED. THE AREA OF FRAYING WAS LOCATED UNDER THE REAR SEATS IN THE INSPECTION AREA AT THE REAR PULLEYS. THIS IS A KNOWN AREA OF WEAR FOR ALL PA 28, 34, AND 44 MODEL AIRCRAFT. RESEARCH OF THE MAINTENANCE RECORDS SHOWED THAT THE PREVIOUS OWNERS HAD FAILED TO COMPLY WITH SB WHICH REQUIRES REPETITIVE INSPECTIONS OF ALL FLIGHT CONTROL CABLES. THIS SB WAS APPLICABLE TO THIS AIRCRAFT. (K) 1L71 3O3 O 2A13 1E10 20060419002882006041900288SO 2006 4 19 2006FA0000368 120060301G272062701100 CONTROL CABLE PIPER PA28 PA28R201 7102816SO LYC O360 IO360A1A 41514EA FUSELAGE FRAYED B WIWRK NONE O OTHER ININSP/MAINT 1 WP07963PA5350 2844023 WHILE CONDUCTING AN ANNUAL INSPECTION PRIOR TO PLACING THE AIRCRAFT ONLINE AFTER PURCHASING IT FROM A LOCAL OPERATOR THE RT FWD RUDDER CABLE WAS FOUND TO BE BADLY WORN AND FRAYED. THE LOCATION OF THE FRAYING WAS JUST UNDER THE CENTER CONSOLE FOR THE STABALATOR TRIM AND JUST AS IT EXITED IN TO THE INSPECTION AREA UNDER THE REAR SEATS AT THE FORWARD PULLEY. THIS IS A KNOWN AREA OF WEAR FOR ALL PA 28, 34, AND 44 MODEL AIRCRAFT. RESEARCH OF THE MAINTENANCE RECORDS SHOWED THAT THE PREVIOUS OWNERS HAD FAILED TO COMPLY WITH SB WHICH REQUIRES REPETITIVE INSPECTIONS OF ALL FLIGHT CONTROL CABLES. THIS SB WAS APPLICABLE TO THIS AIRCRAFT. (K) 1L71 3O3 O 2A13 1E10 20060419002792006041900279SO 2006 4 19 2006FA0000369 120060301G271062701123 CONTROL CABLE PIPER PA28 PA28R201 7102816SO LYC O360 IO360A1A 41514EA WING FRAYED B WIWRK NONE O OTHER ININSP/MAINT 1 WP07963PA5350 2844023 WHILE CONDUCTING AN ANNUAL INSPECTION PRIOR TO PLACING THE AIRCRAFT ONLINE AFTER PURCHASING IT FROM A LOCAL OPERATOR THE LT AILERON BALANCE CABLE WAS FOUND TO BE BADLY WORN AND FRAYED. THE LOCATION OF THE FRAYING WAS AT THE 1ST IB PULLEY IN THE WING ROOT. THIS IS A KNOWN AREA OF WEAR FOR ALL PA 28, 34, AND 44 MODEL AIRCRAFT. RESEARCH OF THE MAINTENANCE RECORDS SHOWED THAT THE PREVIOUS OWNERS HAD FAILED TO COMPLY WITH SB WHICH REQUIRES REPETITIVE INSPECTIONS OF ALL FLIGHT CONTROL CABLES. THIS SB WAS APPLICABLE TO THIS AIRCRAFT. (K) 1L71 3O3 O 2A13 1E10 20060419002912006041900291SO 2006 4 19 2006FA0000370 120060301G271062701124 CONTROL CABLE PIPER PA28 PA28R201 7102816SO LYC O360 IO360A1A 41514EA WING FRAYED B WIWRK NONE O OTHER ININSP/MAINT 1 WP07963PA5350 2844023 WHILE CONDUCTING AN ANNUAL INSPECTION PRIOR TO PLACING THE AIRCRAFT ONLINE AFTER PURCHASING IT FROM A LOCAL OPERATOR THE RT AILERON BALANCE CABLE WAS FOUND TO BE BADLY WORN AND FRAYED WITH ONLY 1 STRAND LEFT HOLDING IT TOGETHER. THE LOCATION OF THE FRAYING WAS AT THE 1ST IB PULLEY IN THE WING ROOT. THIS IS A KNOWN AREA OF WEAR FOR ALL PA 28, 34, AND 44 MODEL AIRCRAFT. RESEARCH OF THE MAINTENANCE RECORDS SHOWED THAT THE PREVIOUS OWNERS HAD FAILED TO COMPLY WITH SB 1048 WHICH REQUIRES REPETITIVE INSPECTIONS OF ALL FLIGHT CONTROL CABLES. THIS SB WAS APPLICABLE TO THIS AIRCRAFT. (K) 1L71 3O3 O 2A13 1E10 20060419002992006041900299SO 2006 4 19 2006FA0000371 120060301G271062701099 CONTROL CABLE PIPER PA28 PA28R201 7102816SO LT WING FRAYED B WIWRK NONE O OTHER ININSP/MAINT 1 WP07962WW4810 2844022 WHILE CONDUCTING AN ANNUAL INSPECTION PRIOR TO PLACING THE AIRCRAFT ON LINE AFTER PURCHASING IT FROM A LOCAL OPERATOR THE LT FORWARD AILERON BALANCE CABLE WAS FOUND TO BE BADLY WORN AND FRAYED. RESEARCH OF THE MAINTENANCE RECORDS SHOWED THAT THE PREVIOUS OWNERS HAD FAILED TO COMPLY WITH SB 1048 WHICH REQUIRES REPETITIVE INSPECTIONS OF ALL FLIGHT CONTROL CABLES. THIS SB WAS APPLICABLE TO THIS AIRCRAFT. (K) 1L71 3O 2A13 20060419002572006041900257SO 2006 4 19 2006FA0000372 120060309G32133948903 AXLE PIPER PA34 PA34220T 7103420SO CONT O300 O300* 17022SO MLG CRACKED D NTBRK NONE O OTHER ININSP/MAINT 1 NM059219X 3448038 CRACKS IN BOTH UPPER BOLT HOLES THAT SECURE AXLE TO STRUT ASSEMBLY ON BOTH LT AND RT MLG. PROBABLE CAUSE MAYBE HARD LANDING OR FATIGUE CRACKS DO TO NORMAL USE. (K) 1L72 3O3 O A7SO E253 20060420001202006042000120CE 2006 4 20 2006FA0000373 120060322G551004320049 BRACKET CESSNA150 152 2071835CE LYC O235 O235* 41505EA HORIZONTAL STAB CRACKED D K NONE O OTHER ININSP/MAINT 1 SW1549053* 15281124 3 CRACKS WHERE FOUND ON THE TOP RT OB BOLT HOLE AND ONE CRACK IN WELD JUST AFT OF SAME BOLT HOLE, (NUT PLATES HAD BEEN PREVIOUSLY REMOVED). UNKNOWN CAUSE, AD SHOULD BE REVISED TO REFER FURTHER INSPECTION OF COMPLETE BRACKET ASSY. (K) 1H71 3O3 ONT3A19 E223 20060420001172006042000117SO 2006 4 20 2006FA0000374 120060403G27301159CS52093409 STOP GULSTMGV GULFSTREAMGV3980116SO RROYCEBR700 BR700710A110 NE LT ELEVATOR BROKEN B CW1RK NONE O OTHER ININSP/MAINT 1 EA11780F 3750 530 DURING SCHEDULED TAIL INSPECTION LT ELEVATOR UP AND DOWN STOP WAS FOUND BROKEN OFF AND LAYING IN ELEVATOR ATTACH/HINGE AREA. (K) 2L72 4F4 FRTA12EA E00057EN 20060420001712006042000171CE 2006 4 20 2006FA0000375 120060403G3397 CONNECTOR BEECH MU300 400A 1155402CE PWA JT15 JT15D5 52112NE WIRE HARNESS WRONG PART B E81RK NONE O OTHER ININSP/MAINT 1 GL03493CW RK93 DURING SCHEDULED INSPECTION FOUND SEVERAL INCORRECT TYPE SPLICE CONNECTORS AND REPAIRS IN CABIN COLD CATHODE LIGHTING WIRING. HAVE FOUND THIS TO BE THE APPARENT CAUSE OF MINOR FIRES AND OVERHEATING ABOVE THE HEADLINER IN SEVERAL AIRCRAFT PREVIOUSLY.. SEVERAL COMMUNIQUÉS HAVE NOTED THIS SUBJECT PREVIOUSLY. SUGGEST A MANDATORY SB OR SAFETY COMMUNIQUÉ BE ISSUED FOR A ONE TIME INSPECTION OF COLD CATHODE WIRING FOR NON-APPROVED CONNECTORS AND WIRING REPAIRS. WARNINGS AND SPECIFIC REPAIR INSTRUCTIONS SHOULD BE ADDED TO THE MM. (K) 2H72 4F4 FRTA16SW E25EA 20060420001722006042000172CE 2006 4 20 2006FA0000376 120060330G561010138402518 WINDSHIELD BEECH B300 B300 1159232CE PWA PT6 PT6* 52043EA COCKPIT CRACKED B E81RK NONE O OTHER CRCRUISE 1 GL0337TD 1236 FL25 FLIGHT CREW REPORTED CO-PILOTS WINDSHIELD RAPIDLY FAILED IN CRUISE FLIGHT, INNER LAYER (SPIDER WEBBED) OVER ENTIRE INTERIOR SURFACE. DELAMINATIONS NOTED SPREADING FROM BOTH IB CORNERS UPON REMOVAL. TECH INSTALLING REPLACEMENT WINDSHIELD NOTED PREVIOUS INSTALLATION MAY HAVE HAD SEALS INSTALLED INCORRECTLY, CAUSING INCREASED STRESS ON WINDSHIELD ASSY. RECOMMEND TECH INSTALLING REPLACEMENT WINDSHIELDS REVIEW CURRENT STRESS FREE INSTALL KIT INSTRUCTIONS AND MM INSTALL PROCEDURES CAREFULLY PRIOR TO INSTALLATION. (K) 2L72 4T3 TRTA24CE E2NE 20060420001742006042000174GL 2006 4 20 2006FA0000377 120060327G5552 ATTACH FITTING AMTR ZENITHZENITHCH701 05611WIGL ROTAX 912 ROTAX912 55555EU ELEVATOR HINGE CRACKED G K NONE O OTHER ININSP/MAINT 1 AL01701BX 71514 DURING CONDITION INSPECTION IT WAS DISCOVERED THAT THE RT ELEVATOR HINGE ATTACH SUPPORT HAD A CRACK IN THE T/E RADIUS THAT WAS STOP DRILLED. A DOUBLER REPAIR WAS INSTALLED. THE ELEVATOR HORN ATTACH ALSO HAD A LOOSE RIVET. THIS WAS REPAIRED BY INSTALLING AN HARDWARE. CLOSE ATTENTION SHOULD BE PAID TO THESE AREA EVEN ON PREFLIGHT AS THIS IS THE THIRD KNOWN INCIDENCE OF THIS KIND IN THE AREA. (K) 1H71 3I3 INTEXPA1H71EXPE3I 20060502000082006050200008 2006 5 2 2006FA0000378 120060329G8011MHB4016 STARTER MALFUNCTIONED B WS9RK NONE O OTHER ININSP/MAINT 1 NM07 BENDIX DRIVE WOULD NOT DISENGAGE. (K) 20060420001602006042000160CE 2006 4 20 2006FA0000379 120060403G240010300B ALTERNATOR CESSNA207 207 2073602CE OVERTORQUED B UT2RK NONE O OTHER ININSP/MAINT 1 SO09 PART RECEIVED O/H FROM STOCK. NO CURRENT OUTPUT WHEN INSTALLED ON AIRCRAFT. BENCH CHECKING RESULTED IN MALFUNCTION OF BRUSH BLOCK HARDWARE DUE TO POSSIBLE OVER TORQUING OF HARDWARE DURING ASSY. COMPONENT WAS OVERHAULED BY CRS NR UT2R226L UNDER W/O NR M940120 DATED AUG 17, 2005, FORM TRACKING NR F082283. (K) 1H71 3O A16CE 20060420001802006042000180WP 2006 4 20 2006FA0000380 220060330G75103751160 FITTING LEAR 35 35A 5170602CE GARRTTTFE731TFE731* 01518WP TAIL MISINSTALLED B BIORO OTHER FI FLT CONT AFFECTED FLT. ATTITUDE INST. APAPPROACH 1 EA23288JP 288 AIRCRAFT EXPERIENCED HORIZONTAL STABILIZER STALL DURING APPROACH, DURING SEVERE ICING. AIRCRAFT RECOVERED FROM STALL AND LANDING NORMAL. INSPECTION OF TAIL DE-ICE SYSTEM FOUND BLEED AIR LEAKING IN AFT PART OF TAIL AT 90 DEGREE ELBOW. DURING REMOVAL OF 90 DEGREE ELBOW IT WAS FOUND THAT THE WIGGINS SEALS WERE INSTALLED INCORRECTLY, UNABLE TO DETERMINE WHEN THIS FITTING WAS INSTALLED. COULD HAVE COME FROM MFG DURING PRODUCTION. HAS NOT BEEN CHANGED BY OWNER IN 11 YEARS. TAIL AND WING HEAT FUNCTIONAL CHECKED NORMAL AT LAST INSPECTION. NO INFO IN MM FOR INSTALLING THIS TYPE. (K) 2L72 4F4 F A10CE E6WE 20060420002262006042000226CE 2006 4 20 2006FA0000381 120060324G3213054119810 STRUT CESSNA172 172N 2072434CE LYC O360 O360* 41514EA MLG BROKEN D K NONE O OTHER ININSP/MAINT 1 NE01739YA 17270902 RL514576T LANDING GEAR BROKE JUST OUTSIDE OF THE GEAR BOLT. THE FACE OF THE CRACKED AREA APPEARS TO HAVE RUST ON IT THAT COULD INDICATE A PREVIOUS CRACK. (NE01200603823) (K) 1H71 3O3 ONT3A12 E286 20060512001262006051200126SO 2006 5 12 2006FA0000382 120060323G3320AL1235T422C27 LAMP GULSTMGV GV 3980116SO RROYCEBR700 BR700710A110 NE GALLEY INOPERATIVE G K NONE O OTHER ININSP/MAINT 1 NM091KE 400 574 DURING ROUTINE LAMP REPLACEMENT, IT WAS DISCOVERED THAT ONE END OF THE REMOVED UNIT WAS DISCOLORED. THE DISCOLORATION WAS THOUGHT TO BE DUE TO OVERHEATING. THE LOCATION OF THE FAILED LAMP WAS IN THE GALLEY OVERHEAD. INSTALLED NEW UNIT OF SAME MFG AND PN. OPERATIONAL CHECK, OK. REPORTING THIS DUE TO CONCERN THAT THE OPERATION OF THIS LIGHT COULD RESULT IN A POSSIBLE FIRE CAUSED BY OVERHEATING OF THESE UNITS. (K) 2L72 4F4 FRTA12EA E00057EN 20060424001842006042400184SO 2006 4 24 2006FA0000383 120060306G2140A23D04 REGULATOR JANITROL PIPER PA23 PA23250 7102308SO LYC O540 TIO540* 41532EA CABIN HEATER LEAKING B GFVRK NONE O OTHER ININSP/MAINT 1 NM136549A 8213015F 277954006 AIRCRAFT RECEIVED FROM NEW OWNER WANTING HEATER MADE OPERATIONAL: TOTALLY DEACTIVATED. REPLACED HEATER ASSY DUE TO EXTREME DETERORATION. FUEL REGULATOR REPLACED DUE TO LEAKAGE AND FAILURE TO REGULATE. FOUND INLET PORT PARTIALLY PLUGGED BY CORROSSION BY-PRODUCTS AND REMNANTS OF DAMAGED THREADS. N/E REPAIRABLE. (K) 1L72 3O3 O 1A10 E14EA 20060424001352006042400135CE 2006 4 24 2006FA0000384 120060327G3230101810151 BOLT BEECH 300 300BEECH 1152930CE RT GEAR DRAG LEGMISDRILLED D K NONE O OTHER ININSP/MAINT 1 SO15810N FL419 THIS IS AN ALEMITE TYPE BOLT. IT WAS FOUND THAT GREASE WAS NOT GETTING TO THE BUSHINGS ON THE FAR END OF THE BOLT. UPON EXAMINATION, IT WAS FOUND THAT THE CENTER GREASE PORT IN THE BOLT WAS NOT DRILLED FAR ENOUGH TO ALLOW GREASE TO GET TO THE FINAL SIDE-DRILLED PORT. THUS THE BUSHING FOR THAT PORT WAS NOT GETTING LUBRICATION. DRAG LINKS WITH THIS PN BOLT SHOULD BE CHECKED FOR PROPER LUBRICATION. (K) 2L72 4T A24CE 20060424001742006042400174SO 2006 4 24 2006FA0000385 220060331G8530 CYLINDER HEAD CESSNA414 414A 2075907CE CONT O520 TSIO520BB 17040SO RT ENG SEPARATED D K NONE E VIBRATION/BUFFET CRCRUISE 1 SO15414AM 414A0850 287566R DURING FLIGHT, VIBRATION WAS NOTED ON RT ENGINE. INSPECTED ENGINE AND FOUND NR 6 CYLINDER SEPARATED WHERE BARREL MEETS HEAD. PROBABLE CAUSE: UNKNOWN. RECOMMENDATIONS: THIS IS AN ECI CYLINDER. REFERENCE NEEDS TO BE MADE TO THEM TO RESOLVE THE PROBLEM. (K) 1L72 3O3 O A7CE E8CE 20060424001452006042400145SO 2006 4 24 2006FA0000386 120060405G2121553002 COOLING FAN PIPER PA23 PA23250 7102308SO LYC O540 IO540* 41532EA INST PANEL BURNED B E ENGINE SHUTDOWN BA SMOKE/FUMES/ODORS/SPARKS FLAME/FIRE TXTAXI/GRND HDL 1 EA2352WW 6112 278154014 AFTER STARTING ENGINES, THE PILOT SMELLED SMOKE AND OBSERVED FLAMES BEHIND CO-PILOTS INSTRUMENT PANEL. ENGINES WERE SHUTDOWN. WHEN MASTER SWITCH WAS TURNED OFF, THE FLAME WENT OUT. INVESTIGATION REVEALED THAT THE AVIONICS COOLING FAN HAD CAUGHT FIRE. (K) 1L72 3O3 O 1A10 1E4 20060424001822006042400182CE 2006 4 24 2006FA0000387 120060328G3040260148830 DEICE SYSTEM CESSNA208 208B 2073701CE WINDSHIELD LEAKING C O OTHER O OTHER NRNOT REPORTED 1 EA21208JH 208B1144 WATER LEAKS AROUND/THROUGH EDGE SEAL OF WINDSHIELD DE-ICE HOT PLATE AND OBSTRUCTS FORWARD VIEW OF PILOT. THIS WATER FREEZES BETWEEN THE HOT PLATE AND THE WINDSHIELD. IN RAIN CONDITIONS WITH TEMPERATURE ABOVE FREEZING WATER ACCUMULATES AND FILLS 4 TO 5 INCHES OF THE LOWER PORTION OF THE HOT PLATE. THIS WATER FLOATS AROUND THE IN THE LAYER BETWEEN THE HOT PLATE AND THE WINDSHIELD MAKING LANDING THE AC VERY DANGEROUS FROM THE PILOTS SEAT. IN TEMPERATURES BELOW FREEZING THIS WATER FREEZES AND COMPLETELY BLOCKS THE PILOTS FORWARD VIEW. THIS IS THE SECOND HOT PLATE TRIED ON THIS NEW AIRCRAFT WITH TWO DIFFERENT EDGE SEAL CONFIGURATIONS. THE WINDSHIELD DEICE HOT PLATE HAS BEEN REMOVED FROM THIS AC FOR SAFETY. 1H71 3T A37CE 20060424001532006042400153SO 2006 4 24 2006FA0000388 120060307G551189T20543 RIB GRUMAN GRUMAVS2 S2F 3951006SO GARRTTTPE331TPE331* 01514WP RT HORIZ STAB CRACKED D K NONE O OTHER ININSP/MAINT 1 WP25448DF N11140 152347 DURING MAINTENANCE ON THE RT SIDE HORIZONTAL STABILIZER, CRACKS WERE ON 2 RIB SECTIONS. CRACKS WERE DETECTED ON RIBS PN 89T920543, STA 138.858 AND PN 89T1029-1, STA 80.608. THESE CRACKS WERE FOUND ON THE UPPER FWD LEADING EDGE TABS WHERE THE RIB ATTACHES TO THE HORIZONTAL STAB SKIN. RIBS WERE REPAIRED IAW THE STRUCTURAL REPAIR MANUAL. (K) 2H72 4O3 TRTEXPA2H72E2WE 20060424001552006042400155CE 2006 4 24 2006FA0000389 120060128G323212810281 ACTUATOR CESSNA CESSNA210 210L 2073448CE CONT O550 IO550* SO MCAULYD3A34 D3A34C402 GL RT MLG DOOR FAILED G O OTHER J WARNING INDICATION LDLANDING 1 EA114FL 5258 15 4486 21061382 289006R 921108 MECHANICAL FAILURE OF THE RT MLG DOOR ACTUATOR, PREVENTED THE EXTENSION OF THIS AC LANDING GEAR EITHER BY NORMAL OF EMERGENCY PROCEDURES. THE FAILURE WAS THE ACTUATOR GLAND AND CIRCLIP COMING APART FROM THE ACTUATOR. THE RT MLG ACTUATOR WAS REMOVED AND RESEALED BY A LOCAL MAINTENANCE FACILITY ON 9/24/2004 AT 343.8 HOURS TACH 14.7 HOURS SINCE RESEAL. INVESTIGATION OF THIS INCIDENT WAS INCONCLUSIVE OF WHAT CAUSED THIS FAILURE. (K) 1H71 3O3 O 3A21 E3SO 5 CP47GL 20060424002272006042400227SO 2006 4 24 2006FA0000390 120060320G256045402 HARNESS PIPER PA28 PA28161 7102803SO SHOULDER HARNESSFAILED D K NONE O OTHER ININSP/MAINT 1 EA172203T50 287916300 HAVE HAD NUMEROUS PROBLEMS WITH PACIFIC SCIENTIFIC INERTIA REELS, PN 1107447-29, MFG PN 564-863 (PS50039-4-49). THESE HARNESSES DO NOT RETURN AND/OR DO NOT FUNCTION UNDER A SUDDEN LOAD. ON OCCASION, HAVE FOUND THEM BAD STRAIGHT OUT OF THE BOX. THEY ARE ALSO VERY SUSCEPTABLE TO WARPAGE/ MALFUNCTION UPON INSTALLATION. (K) 1L71 3O 2A13 20060424002282006042400228SO 2006 4 24 2006FA0000391 120060329G324616403506 BRAKE DISC CLEVELAND PIPER PA31 PA31 7103102SO LYC O540 TIO540A2B 41532EA MCAULY3DF36CB3DF36C526 GL WHEEL CRACKED D K NONE O OTHER ININSP/MAINT 1 CE019007Y 3111 R47161 981497 FOUND CRACK IN BRAKE DISC ON OUTER EDGE. CRACK STARTED ON THE (P) IN PARKER FROM THE STAMPED NAME, MODEL, DATE, AND SN. WHEN STAMPED COULD HAVE CAUSED A STRESS CRACK. THE USE OF AN INK STAMP WOULD NOT CAUSE ANY STRESS ON THE DISC. (K) 1L72 3O3 O A20SO E14EA 5 C 20060424002292006042400229SO 2006 4 24 2006FA0000392 220060410G74146310 MAGNETO CESSNA206 U206F 2073333CE CONT O520 IO520F 17032SO ENGINE CRACKED D K NONE O OTHER ININSP/MAINT 1 NE058411Q348 U20603271 CHECKING ENGINE FOR PERSISTENT OIL LEAK, FOUND IT TO BE COMING FROM AREA OF LT MAG. MAG REMOVED AND WAS FOUND TO HAVE 1.5 INCH SECTION OF MOUNTING FLANGE CRACKED OFF. THIS IS THE SECOND MAG ON THIS ENGINE TO HAVE THIS PROBLEM. PREVIOUS MAG WAS TORQUED TO SPECS AS WAS THIS ONE. (K) 1H71 3O3 O A4CE E5CE 20060502000072006050200007 2006 5 2 2006FA0000393 120060411G2434ALU1003 HOUSING ENGINE WORN B KC2RK NONE O OTHER ININSP/MAINT 1 GL03 THIS ALTERNATOR HAS -0- HOURS TIME-IN-SERVICE. DURING INSPECTION, PRIOR TO SALE, IT WAS DISCOVERED THAT THE ROTOR HAD EXCESSIVE LATERAL MOVEMENT AS A RESULT OF EXCESSIVE WEAR OF THE DRIVE END HOUSING BEARING BORE. THIS CONDITION WOULD HAVE LEAD TO PREMATURE FAILURE OF THE DRIVE GEAR/ALTERNATOR AND COULD HAVE LEAD TO A COMPLETE ENGINE FAILURE. HAVE SEEN THIS SAME PROBLEM IN A VERY LARGE PERCENTAGE OF THESE ALTERNATORS RETURNED TO SERVICE BY OVERHAULER. (K) 20060425001292006042500129SO 2006 4 25 2006FA0000394 120060401G575142972 SPAR PIPER J3 J3C* SO AILERON CORRODED D K NONE O OTHER ININSP/MAINT 1 NE02 AILERON SPARS FOUND EXCESSIVE CORROSION UNDER ALL 3 HINGES. NEEDED TO REPLACE SPAR ON BOTH LT AND RT AILERONS BEFORE RECOVERING AILERONS. (K) 1H71 3O ATC660 20060424002352006042400235CE 2006 4 24 2006FA0000397 120060209G5753052390134 FLAP CESSNA182 T182 2072736CE LYC O540 O540L3C5 41532EA RT WING DAMAGED D AVXRK NONE F FLT CONT AFFECTED CRCRUISE 1 NE015464N 18267735 L2248140A ON DEC 4, 2005, THE RT FLAP JAMMED AT THE IB ATTACH ARMS IN ABOUT THE 20 DEGREE POSITION. FLAP MOTOR CONTINUED TO RUN FOR A SHORT PERIOD OF TIME, CAUSING SEVERE DAMAGE AND DISTORTION TO THE JAMMED FLAP, THE PILOT WAS ABLE TO LAND THE AIRPLANE WITHOUT FURTHER INCIDENT. INSPECTION REVELED THAT THE TIP OF THE RT IB FLAP SUPPORT ARM CAME IN CONTACT WITH A BRACKET ON THE FLAP TRACK RIB ASSY CAUSING THE FLAP TO BIND. REPAIRED BY REPLACING THE RT FLAP INCLUDING ALL THE ROLLERS AND BY REPLACING BOTH BRACKETS ON THE IB FLAP TRACK RIB ASSY. (K) 1L71 3O3 O 3A13 E295 20060427002072006042700207CE 2006 4 27 2006FA0000398 120060327G5346051313211 BRACKET CESSNA CESSNA175 175 2072502CE ENGING MOUNT CRACKED D K NONE O OTHER ININSP/MAINT 1 CE077259M3822 55559 FOUND THE UPPER LEFT ENGINE MOUNT BRACKET, P/N 0513132-11 IN THE 0513132-3 UPPER ENGINE MOUNT STRINGER CRACKED THROUGH THE BRACKET AROUND THE RADIUS OF THE WASHER. INSPECTION WAS ACCOMPLISHED DUE TO NUMEROUS REPORTS OF THE SAME CONDITION FOUND ON LIKE MODELS OF AIRCRAFT. 1H71 3O NT3A17 20060427002282006042700228CE 2006 4 27 2006FA0000399 120060327G7120051313211 BRACKET CESSNA CESSNA175 175 2072502CE ENGINE MOUNT CRACKED D K NONE O OTHER ININSP/MAINT 1 CE077259M3822 55559 FOUND THE UPPER RIGHT ENGINE MOUNT BRACKET, P/N 0513132-11 IN THE 0513132-4 UPPER ENGINE MOUNT STRINGER, CRACKED. INSPECTION WAS ACCOMPLISHED DUE TO NUMEROUS REPORTS OF THE SAME CONDITION FOUND ON LIKE MODELS OF AIRCRAFT. 1H71 3O NT3A17 20060512000472006051200047SO 2006 5 12 2006FA0000400 120060106G2824236405492189 VALVE PIPER PA34 PA34200T 7103406SO FUEL SYS LEAKING D K NONE O OTHER NRNOT REPORTED 1 WP05 FUEL COULD NOT BE SHUT OFF AND FUEL WAS CROSS-FEEDING. SEVERAL CROSSFEED VALVES HAVE BEEN EXAMINED AND FOUND TO HAVE DEFECTIVE SEALS. O-RINGS WERE DISSOLVED AND RESEMBLED A TAR LIKE SUBSTANCE. IF THERE IS AN ENGINE FIRE OR LEAK, FUEL CANNOT BE SHUT OFF WHICH CREATES A SAFETY OF FLIGHT CONDITION THAT MUST BE CORRECTED. 1L72 3O A7SO 20060510002472006051000247CE 2006 5 10 2006FA0000401 120060425G555304311481 FITTING CESSNA CESSNA150 152 2071835CE VERTICLE STAB CRACKED B K NONE O OTHER ININSP/MAINT 1 WP2348968 15281080 PART ATTACHES VERTICLE STABILIZER SPAR TO THE HORIZONTAL STABILIZER SPAR ATTACH FITTING P/N 0432004-9(THIS FITTING HAS BEEN THE SUBJECT OF AD 80-11-04 AND SEB 3-06)PROBABLE CAUSE IS HIGH ACTT. AGING AIRCRAFT REQUIRE DILIGENT INSPECTIONS. (REF FAA HANDBOOK"BEST PRACTICES GUIDE FOR MAINTAINING AGING GENERAL AVIATION AIRCRAFT. 1H71 3O NT3A19 20060510002482006051000248CE 2006 5 10 2006FA0000402 120060425G555304311481 FITTING CESSNA CESSNA150 152 2071835CE VERTICLE STAB CRACKED B N2YRK NONE O OTHER ININSP/MAINT 1 WP2348968 15281080 PART ATTACHES VERTICAL STABILIZER SPAR TO THE HORIZONTAL STABILIZER SPAR ATTACH FITTING P/N 0432004-9(THIS FITTING HAS BEEN THE SUBJECT OF AD 80-11-04 AND SEB 3-06)PROBABLE CAUSE IS HIGH ACTT. AGING AIRCRAFT REQUIRE DILIGENT INSPECTIONS. (REF FAA HANDBOOK"BEST PRACTICES GUIDE FOR MAINTAINING AGING GENERAL AVIATION AIRCRAFT. AIRCRAFT TOTAL TIME IS 12,762.1 1H71 3O NT3A19 20060426001162006042600116NM 2006 4 26 2006FA0000403 120060419G57402000610102501 BRACKET PIPER PA60 PA60600 7106001NM RIGHT WING CRACKED D K NONE O OTHER ININSP/MAINT 1 NE0378LS 2177 600546176 FWD WING ATTACHMENTS, LEFT & RIGHT WINGS, FWD & AFT BRACKETS WERE NEVER RIVETED TO TOP & BOTTOM WING SKINS & INBOARD RIB FLANGES ALLOWING ALL LOADING TO BE TAKEN BY BRACKET FLANGES & INBD WING RIBS. ALL 4 BRACKETS ARE CRACKED. PICTURES AVAILABLE. IT SEEMED MORE THAN COINCIDENTAL TO ME THAT THE FOUR RIVETS NEEDED TO ATTACH THE WING SKIN TO THE RIB AND THE ATTACHMENT BRACKET WERE MISSING ON BOTH WINGS, TOP AND BOTTOM. PERHAPS THERE WAS A MISTAKE ON THE ASSEMBLY DRAWING AT THE TIME OF MANUFACTURE. THE HOLES WERE NEVER EVEN DRILLED FOR THE RIVETS. THE AIRCRAFT WAS MANUF. IN 1978, 4 NEWER MODELS WERE INSPECTED AND FOUND TO BE CORRECTLY ASSEMBLED. PICTURES PROVIDED. 1M72 3O RTA17WE 20060511002972006051100297CE 2006 5 11 2006FA0000404 120060331G325059420011 BELLCRANK CESSNA340 340A 2076405CE NLG STEERING CRACKED D K NONE O OTHER ININSP/MAINT 1 GL25340JY4544 340A0979 DURING ANNUAL INSPECTION FOUND NOSE GEAR STEERING BELLCRANK ASSY #5942001-1 CRACKED LEFT AND RIGHT SIDES AT PIVOT RADIOUS. NEW REPLACEMENT PART WITH SAME PART NUMBER OBTAINED FROM CESSNA AIRCRAFT IS MADE MUCH HEAVIER WITH ADDITIONAL MATERIAL IN CRACK PRONE AREA. PART FAILURE COULD LEAD TO LOSS OF NOSE GEAR STEERING CONTROL. 1L72 3O 3A25 20060511002992006051100299CE 2006 5 11 2006FA0000405 120060331G325059420011 BELLCRANK CESSNA340 340A 2076405CE NLG STEERING CRACKED D K NONE O OTHER ININSP/MAINT 1 GL05340JY4544 340A0979 DURING ANNUAL INSPECTION FOUND NOSE GEAR STEERING BELLCRANK ASSY #5942001-1 CRACKED LEFT AND RIGHT SIDES AT PIVOT RADIOUS. NEW REPLACEMENT PART WITH SAME PART NUMBER OBTAINED FROM CESSNA AIRCRAFT IS MADE MUCH HEAVIER WITH ADDITIONAL MATERIAL IN CRACK PRONE AREA. PART FAILURE COULD LEAD TO LOSS OF NOSE GEAR STEERING CONTROL. 1L72 3O 3A25 20060512000492006051200049 2006 5 12 2006FA0000406 420060314G3452 TRANSPONDER CESSNA680 680CE 2076811CE PWA 306 PW306B NE COCKPIT MALFUNCTIONED C A UNSCHED LANDING O OTHER CLCLIMB 1 SO352428 6800046 DEPARTED AND WAS TOLD BY DEPARTURE CONTROL THEY DID NOT HAVE A TARGET ON US. SWITCHED TO SECOND TRANSPONDER WITH SAME RESULT. BOTH TRANSPONDERS APPERARED TO BE IN NORMAL OPS. LANDED AT AND WENT TO A BLACK AIRCRAFT(COMPLETE SHUTDOWN). RESTARTED AND ALL WAS NORMAL DURING NEXT LEG. DOWNLOADED COMPUTERS ON POST FLIGHT AT HOME BASE AND FOUND NO FAULTS. HAVE FLOWN 49 LEGS SINCE THE OCCURANCE AND HAVE HAD NO FAILURES. 2L72 4F4 FRCT00012WIE35NE 20060518001752006051800175SO 2006 5 18 2006FA0000407 120060414G1410LW18724 HOSE LYC TIO540AH1A PIPER PA32 PA32R301T 7103220SO LYC O540 TIO540S1AD 41532EA ENGINE DETERIORATED B UXCRA UNSCHED LANDING R PARTIAL RPM/PWR LOSS CRCRUISE 1 SW05126LM 3257336 L1146461A PARTIAL POWER LOSS, TWO CYLINDERS DROPPED OUT, CAUSED BY SMALL PARTICLES OF RUBBER HOSE FROM UPPER DECK AIR REFERENCE LINES FLAKING OFF AND OCCLUDING THE FUEL INJECTORS 1L71 3O3 O A3SO E14EA 20060518002432006051800243SO 2006 5 18 2006FA0000408 120060329G323067146004 DRAG LINK PIPER PA44 PA44180 7104402SO NLG FRACTURED B K NONE O OTHER LDLANDING 1 SO15938ER620 27 4496200 DURING LANDING, THE NOSE GEAR RETRACT DRAG BRACE FAILED AT THE PIVOT POINT. THE NOSE GEAR COLLAPSED AND THE AIRCRAFT VEERED OFF OF THE RUNWAY STRIKING A LARGE RUNWAY SIGN WITH THE RT OB WING SECTION. THE CAUSE OF THE FAILURE IS STILL UNDER INVESTIGATION. 1L72 3O A19S0 20060518002442006051800244SO 2006 5 18 2006FA0000409 120060329G323067146004 DRAG LINK PIPER PA44 PA44180 7104402SO ZONE 700 FRACTURED B K NONE O OTHER LDLANDING 1 SO15938ER620 27 4496200 DURING LANDING, THE NOSE GEAR RETRACT DRAG BRACE (PN-67146-004) FAILED AT THE PIVOT POINT. THE NOSE GEAR COLLAPSED AND THE AIRCRAFT VEERED OFF OF THE RUNWAY STRIKING A LARGE RUNWAY SIGN WITH THE RT OB WING SECTION. THE CAUSE OF THE FAILURE IS STILL UNDER INVESTIGATION. 1L72 3O A19S0 20060518002552006051800255CE 2006 5 18 2006FA0000410 120060406G712007516001 MOUNT CESSNA182 182Q 2072732CE CONT O470 O470U 17026SO ENGINE CRACKED D K NONE O OTHER ININSP/MAINT 1 SO057551S2290 18265200 286916R DURING ANNUAL INSPECTION THE LT AFT ENGINE MOUNT P/N 0751600-1 WAS FOUND CRACKED THRU THE ENGINE MOUNT BOLT AREA. 1H71 3O3 ONT3A13 E273 20060518002572006051800257CE 2006 5 18 2006FA0000411 120060406G2760632550033 LUG CESSNA525 525A 2076615CE SPEED BRAKE MISDRILLED B K NONE O OTHER ININSP/MAINT 1 GL0320GP 445 525A0131 AC WAS IN FOR A PHASE 1 AND 2 INSPECTION. A BROKEN BONDING STRAP AT THE UPPER LT SPEEDBRAKE DOOR NECESSITATED REMOVAL OF THE BOLT CONNECTING THE PUSH ROD TO THE UPPER DOOR LUG. DURING BOLT REMOVAL THE HELICOIL INSERT CAME OUT WITH THE BOLT AND WAS DEFORMED. PROPER INSERTION OF A NEW HELICOIL WAS UNSUCCESSFUL AS THE BOLT WOULD NOT THREAD INTO IT. A COUPLE OF ATTEMPTS INSUED AND DETERMINATION WAS MADE THAT THE HOLE WAS NOT PROPERLY DRILLED AND TAPPED TO ACCEPT THE HELICOIL. MAINTENANCE SUPPORT HOTLINE REPRESENTATIVE AGREED WITH THE ASSESSMENT AND PROVIDED TECHNICAL DATA TO REMOVE THE UPPER DOOR LUG, BACK DRILL AND TAP TO THE PROPER SIZE. INSTALLATION OF THE HELICOIL WAS THEN SUCCESSFUL. 1L71 4F RTA1WI 20060522002342006052200234SO 2006 5 22 2006FA0000412 220060424G85206416311052 THRU BOLT CESSNA188 A188B 2073005CE CONT O550 IO550* SO HARTZLHCC3Y HCC3YF1 GL ENGINE BROKEN D K NONE D INFLIGHT SEPARATION AGAGRICULTURE 1 NM094918R200 18802435T 284455R EC1151A THE ENGINE CRANKCASE THRU-BOLT BROKE. THIS THRU-BOLT IS LOCATED UNDER THE TOP OF THE OIL COOLER ADAPTER PLATE THRU TO THE NR 6 CYL TOP FRONT. IT BROKE OFF FLUSH AT THE CYL BASE WHILE IN FLIGHT. THE BOLT END WHICH BROKE OFF WITH THE CYL BASE NUT FLEW OUT THE FRONT OF THE COWL, PUT A GOUGE IN THE FACE OF THE PROP BLADE AND THEN HIT THE TOP OF THE COWL LEAVING A LARGE DENT. WHEN IT BROKE, THE OPPOSITE END OF THE BOLT WAS FORCED BACK AGAINST THE OIL COOLER ADAPTER PLATE AND DEFORMED THE PLATE. THIS THRU-BOLT IS A REPLACEMENT INSTALLED LAST AUGUST 2005 DUE TO THE ORIGINAL THRU-BOLT, 650 HRS SINCE REMAN, ALSO BREAKING AT THE SAME LOCATION. A NEW CYL BASE NUT HAD BEEN USED AND TORQUED TO 800 INCH LBS IAW SB96-7C. 1L71 3O3 O A9CE E3SO 5 CP25EA 20060512001532006051200153SO 2006 5 12 2006FA0000413 120060427G8011MZ6222 DRIVE ASSY PIPER PA23 PA23160 7102304SO LYC O320 O320B1A 41508EA STARTER FAILED D K NONE O OTHER NRNOT REPORTED 1 SW013326P152 231277 STARTER DRIVE FAILED. 1L72 3O3 O 1A10 E274 20060512001542006051200154SO 2006 5 12 2006FA0000414 120060427G8011MZ6222 DRIVE ASSY PIPER PA23 PA23160 7102304SO LYC O320 O320B1A 41508EA STARTER FAILED D K NONE O OTHER NRNOT REPORTED 1 SW013326P152 231277 STARTER DRIVE FAILED 1L72 3O3 O 1A10 E274 20060530001692006053000169SO 2006 5 30 2006FA0000415 120060425G272131731 CABLE MAULE MX7 MX7180 5460185SO RUDDER FRAYED G K NONE O OTHER ININSP/MAINT 1 GL2745829 FOUND RIGHT AND LEFT RUDDER TRIM CABLE BADLY FRAYED AS THE CABLE EXISTED THE RUDDER SKIN. 1H71 3O NC3A23 20060530001702006053000170CE 2006 5 30 2006FA0000416 120060425G555304311481 FITTING CESSNA CESSNA150 152 2071835CE RUDDER CRACKED B K NONE O OTHER ININSP/MAINT 1 WP2348968 15281080 PART ATTACHES VERTICLE STABILIZER SPAR TO THE HORIZONTAL STABILIZER SPAR ATTACH FITTING P/N 0432004-9(THIS FITTING HAS BEEN THE SUBJECT OF AD 80-11-04 AND SEB 3-06)PROBABLE CAUSE IS HIGH ACTT. AGING AIRCRAFT REQUIRE DILIGENT INSPECTIONS. (REF FAA HANDBOOK"BEST PRACTICES GUIDE FOR MAINTAINING AGING GENERAL AVIATION AIRCRAFT. AIRCRAFT TOTAL TIME IS 12,762.1 1H71 3O NT3A19 20060613002112006061300211SO 2006 6 13 2006FA0000417 220060329G8530 PACKING CESSNA402 402C 207590RCE CONT O520 TSIO520VB 17040SO ENGINE OUT OF POSITION E E ENGINE SHUTDOWN K FLUID LOSS CRCRUISE 1 SW99 #1 CYLINDER EXHAUST PUSHROD HOUSING PACKING BLEW OUT. SUSPECT POSSIBLE CRANKCASE PRESSURIZATION. PACKING HAD SMALL CUT MOST LIKELY FROM INSTALLATION HOWEVER THAT SOULD NOT HAVE ALLOWED IT TO BLOW OUT. 1L72 3O3 O A7CE E8CE 20060518002412006051800241SO 2006 5 18 2006FA0000418 120060422G32136703704 STRUT PIPER PA44 PA44180T 7104404SO LT MLG BROKEN C K NONE O OTHER TXTAXI/GRND HDL 1 NM03838PC 448107056 LT GEAR STRUT BROKE AT HOUSING. 1L72 3O A19SO 20060518002422006051800242SO 2006 5 18 2006FA0000419 120060422G32136703704 STRUT PIPER PA44 PA44180T 7104404SO LT MLG BROKEN D K NONE O OTHER TXTAXI/GRND HDL 1 NM03838PC 448107056 LH MLG STRUT BROKE ON TAXI 1L72 3O A19SO 20060510001392006051000139CE 2006 5 10 2006FA0000420 120060414G246050369101163 BUSS BAR BEECH BEECH 200 200BEECH 1152920CE PWA PT6 PT6* 52043EA RT WING CORRODED B E81RK NONE O OTHER ININSP/MAINT 1 GL03968T BB570 DURING SCHEDULED INSPECTION FOUND EXCESSIVE CORROSION ON RT WS 54.80 WEB HOT BATTERY BUS PANEL BUS BAR AND FUSE HOLDERS, REQUIRING COMPONENT REPLACEMENT. AIRCRAFT PREVIOUSLY MODIFIED WITH SEALED LEAD-ACID BATTERY. HAVE NOTED SIMILAR CORROSION ISSUES ON OTHER OLDER AC MODIFIED WITH LEAD-ACID BATTERY INSTALLATIONS. RECOMMEND THAT AREAS ADJACENT TO THE BATTERY BOX SHOULD BE INSPECTED CAREFULLY FOR CORROSION EACH SCHEDULED PHASE INSPECTION, ESPECIALLY THE ELECTRICAL SYSTEM COMPONENTS, FOR AIRCRAFT RETROFITTED WITH LEAD-ACID BATTERIES. (K) 1L72 4T3 T A24CE E2NE 20060511000982006051100098CE 2006 5 11 2006FA0000421 120060410G1430MS27039109 SCREW BEECH BEECH MU300 400A 1155402CE FLOOR PANEL WRONG PART B E81RK NONE O OTHER ININSP/MAINT 1 GL03907JE RK107 DURING INSPECTION IAW MFG SB, FOUND BRAKE HYDRAULIC LINE DAMAGED BY FLOOR PANEL ATTACHING SCREW. REPAIRED TUBING AND MODIFIED FLOOR PANELS IAW SB. HAVE FOUND THIS SAME CONDITION ON OTHER AIRCRAFT. (K) 2H72 4F RTA16SW 20060511002002006051100200CE 2006 5 11 2006FA0000422 120060410G361045A6351771 TUBE BEECH MU300 400A 1155402CE BLEED AIR SYS BROKEN B E81RK NONE O OTHER ININSP/MAINT 1 GL03907JE5113 RK107 DURING RECURRING 400 HR INSPECTION REQUIRED BY AD, FOUND AFT FUSELAGE RT BLEED AIR DUCT ASSY. BELLOWS BRAIDED WIRE MESH BLOWN OUT OF END FITTINGS. SUSPECTED TO BE CAUSED BY BLEED AIR LEAK FROM EITHER CRACKED BELLOWS OR FATIGUE/TUBING MIS-ALIGNMENT STRESS. REPLACED TUBE ASSY WITH SUPERSEDING (PN 45A63517-075) TUBE ASSY. RECOMMEND POSSIBLE AFT FUSELAGE BLEED AIR TUBING OF OLDER PN`S HAVE A 5000 HR LIFE LIMIT. (K) 2H72 4F RTA16SW 20060512001422006051200142CE 2006 5 12 2006FA0000423 120060419G32301698200111 DRAG BRACE BEECH 23 A24R 1151252CE LYC O360 IO360A1A 41514EA NLG BROKEN G K NONE O OTHER LDLANDING 1 GL138015R2111 MC54 THE AIRCRAFT TOUCHED DOWN UNEVENTFUL. DURING ROLLOUT, THE NOSE GEAR COLLAPSED ABOUT 1500 FT AFTER TOUCHDOWN. THE DRAG BRACE FAILED AT THE YOKE WHERE IT ATTACHES TO THE NOSE GEAR. (K) 1L71 3O3 O A1CE 1E10 20060510002262006051000226CE 2006 5 10 2006FA0000425 120060417G8011S539800M30 SPRING CESSNA182 182H 2072718CE CONT O470 O470R 17026SO STARTER BROKEN G K NONE O OTHER TXTAXI/GRND HDL 1 CE018503S S1475691 18256603 1317375R4 STARTER DRIVE WAS OVERHAULED BY A CERTIFIED REPAIR STATION. (PN S539800M30) STARTER ADAPTER SPRINGS WERE INSTALLED IAW STC DURING THE OVERHAUL. THE STARTER WAS INSTALLED ON THIS ENGINE AND WAS OPERATED FOR 4.06 HOURS (5 STARTS) BEFORE IT FAILED. AN INSPECTION OF THE STARTER DRIVE ADAPTER FOUND THE STARTER ADAPTER SPRING WAS BROKEN AND DEFORMED. THE INTERNAL PARTS WERE DISCOLORED, AND THERE WERE METAL SHAVINGS FOUND IN THE OIL. (K) 1H71 3O3 ONT3A13 E273 20060512000622006051200062CE 2006 5 12 2006FA0000426 120060412G2434E3FF10300AA ALTERNATOR CESSNA210 T210M 2073451CE ENGINE FAILED B WS9RK NONE O OTHER ININSP/MAINT 1 NM07 ALTERNATOR FAILED, PLATE SCREWS FELL OUT. (K) 1H71 3O 3A21 20060512001442006051200144WP 2006 5 12 2006FA0000427 120060412G62205143711 HUB HILLERUH12 UH12E 4360122WP LYC O540 VO540C2A 41532EA MAIN ROTOR HUB CRACKED B ECGRK NONE O OTHER ININSP/MAINT 1 EA1346MV 2391 264 5046 L248043 M/R HUB DYE CHECK INSPECTION. HUB WAS FOUND TO BE CRACKED. RETIREMENT LIFE, 2500 HOURS. (K) 1G71 3O3 O 4H11 E304 20060510001342006051000134EU 2006 5 10 2006FA0000428 120060421G3233273T411B1 ACTUATOR ROLSCHLS LS3A 3801214EU GE CF6 CF680 30025NE NLG CRACKED B DM4RK NONE O OTHER NRNOT REPORTED 1 SO19325OP 3350 NLG RETRACT ACTUATOR WAS RECEIVED WITH THE PISTON ROD CRACKED. 3 CRACKS RUN AROUND THE CIRCUMFERENCE OF THE ROD AT THE THREADED END. CRACKS RUN ABOUT 95 PERCENT AROUND ROD BUT DO NOT CONNECT (RUN IN A SPIRAL) CORROSION FOUND ON INTERIOR THREADS. CORROSION APPEARS TO BE IN CRACK. (K) 1K00 4 F G37EU E13NE 20060511002892006051100289CE 2006 5 11 2006FA0000429 120060407G2750S19062 SWITCH CESSNA172 172N 2072434CE FLAPS STUCK B BNZRK NONE O OTHER NRNOT REPORTED 1 GL194668G 17273294 FLAP UP LIMIT SWITCH STUCK IN THE OPEN POSITION. (K) 1H71 3O NT3A12 20060512001522006051200152CE 2006 5 12 2006FA0000430 120060331G712034415377 MOUNT BEECH 35 D35 1151510CE CONT E225 E2258 17015SO ENGINE CRACKED D K NONE O OTHER ININSP/MAINT 1 GL212950B4649 D3591 35004D286 MOUNT WAS CROOKED IN WELD. THINK IT HAPPENED DUE TO TIME ON PORT AND AGE OF AIRCRAFT. CLOSE INSPECTION OF THIS AREA DURING ROUTINE MAINTENANCE (UPPER LT, MOUNT CLUSTER/ WEB .1250 INCH CRACK). (K) 1L71 3O3 O A777 E267 20060508000932006050800093SO 2006 5 8 2006FA0000431 120060418G3260211C24312 PRESSURE SWITCH PIPER PA28 PA28R200 7102811SO LYC O360 IO360C1C 41514EA LANDING GEAR CORRODED G A UNSCHED LANDING O OTHER CLCLIMB 1 SW114967T 28R7235164 RL1770951A LANDING GEAR FAILED TO RETRACT IN FLIGHT. PLACING THE AC ON JACKS, THE LANDING GEAR FAILED TO COMPLETELY RETRACT. BY PLACING A JUMPER WIRE BYPASSING THE HYDRAULIC PRESSURE SWITCH THE LANDING GEAR WORKED NORMALLY. AFTER REMOVING THE PRESSURE SWITCH, CORROSION AND PITTING WAS OBSERVED ON THE CONTACTOR ALLOWING IT TO HEAT, WHICH INCREASED RESISTANCE, IN TURN CAUSING A LOW VOLTAGE CONDITION THAT DID NOT ALLOW THE GEAR MOTOR TO OPERATE AND CAUSED PARTIAL RETRACTION. IT WAS NOTED THAT AS THE PRESSURE SWITCH COOLED, IT AGAIN ACTIVATED THE GEAR MOTOR AND CONTINUED THIS CYCLE UNTIL THE LANDING GEAR WAS IN THE UP POSITION. (K) 1L71 3O3 O 2A13 1E10 20060512001392006051200139SO 2006 5 12 2006FA0000432 120060418G571262021005 RIB PIPER PA28 PA28R201 7102816SO WING STA 49.25 CRACKED D K NONE O OTHER NRNOT REPORTED 1 NM13518MW1301 2844105 RIB CRACKED IN FLANGE WHERE LANDING GEAR SIDE BRACE FITTING BOLTS. THE CRACK HAS BEEN NOTED ON LIKE MODELS (6 WINGS). ALL PREVIOUS NOTATIONS FOUND ON AC IN EXCESS OF 6000 HRS TO BE CAUSED BY AN IMPRESSION LEFT BY THE AN960-4 WASHER USED UNDER THE LOCKNUT. THE WASHER APPEARS TO CUT INTO THE RADIUS AND THE CRACKS ORIGINATE AND FOLLOW THE WASHER OUTLINE UNTIL IT PROGRESSES TO A POINT OF CONTINUING IN BOTH DIRECTIONS VERTICALLY. (K) 1L71 3O 2A13 20060510002012006051000201SO 2006 5 10 2006FA0000433 120060414G571278475005 RIB PIPER PA28 PA28R201 7102816SO RT WING STA49.25CRACKED D K NONE O OTHER ININSP/MAINT 1 NM13518MW1301 2844105 INSPECTED RIB IAW SB 1161 AND FOUND RIB CRACKED. THE SAME RIB HAS BEEN FOUND CRACKED IN THE SAME LOCATION ON SIX OTHER WINGS. ALL OTHER WINGS HAD EXCESS OF 6000 HRS REPAIRED AND APPEARED TO HAVE BEEN INSTALLED CROOKED. THE ASSEMBLY PROCESS HAD THIS PART INSTALLED UNDER AN INITIAL LOAD LEADING TO PART CRACKING PREMATURELY. (K) 1L71 3O 2A13 20060510002022006051000202EA 2006 5 10 2006FA0000434 220060414G8520 CAM PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA ENGINE WORN D K NONE O OTHER ININSP/MAINT 1 NM13336PA1100 4496140 NOTED EXCESS MATERIAL IN REMOVED OIL FILTER, SAMPLE ANALYZED AND DETERMINED CAM/LIFTER WEAR. ENGINE REMOVED FOR REPAIRS. WHILE CASE SPLIT SB 569 COMPLIED WITH REPLACING CRANKSHAFT. (K) 1L72 3O3 O A19S0 E286 20060510002322006051000232EU 2006 5 10 2006FA0000435 120060411G6220109011211101 ROD END AGUSTAA109 A119 0261102EU PWA PT6 PT6* 52043EA MAIN ROTOR SEPARATED D K NONE O OTHER ININSP/MAINT 1 WP07820NA 0109 14011 PU0025 DURING DAILY INSPECTION FOUND RED BLADE MAIN ROTOR DAMPER OB ROD END HAD COME APART. BEARING HAD SEPARATED COMPLETELY FROM ROD END. (K) 1G72 3U3 T H7EU E2NE 20060510002332006051000233EU 2006 5 10 2006FA0000436 120060405G29134005303 PUMP AMD FALC10FALCON10 2730101EU GARRTTTFE731TFE731* 01518WP LT ENGINE FAILED B BONRO OTHER O OTHER TOTAKEOFF 1 GL19700FH 1447 158 NR 1 HYDRAULIC PUMP FAILED ON TAKEOFF ROLL. REMOVED PUMP AND INSPECTED BUT FOUND NO OBVIOUS PHYSICAL DEFECTS. REMOVED HYDRAULIC SYSTEM FILTER AND INSPECTED FOR DEBRIS, NONE NOTED. INSTALLED SERVICEABLE HYDRAULIC PUMP IN NR 1 POSITION, ALL SYSTEMS FUNCTION NORMALLY. (K) 2L72 4F4 F A33EU E6WE 20060510002182006051000218SO 2006 5 10 2006FA0000437 120060413G57126701603 RIB PIPER PA28 PA28R180 7102809SO LYC O360 IO360A1A 41514EA WING CRACKED B RMMRK NONE O OTHER ININSP/MAINT 1 CE017536J2294 28R30910 DURING MODIFICATION OF AFT RIB IAW SB, 2 CRACKS WERE FOUND PROPAGATING FROM THE OB BOLT HOLE FOR THE ATTACHMENT OF (PN 9564307) BRACKET. (K) 1L71 3O3 O 2A13 1E10 20060516001362006051600136 2006 5 16 2006FA0000438 120060417G2560BK05SL PIN SEAT BELT BUCKLEFAILED D K NONE O OTHER ININSP/MAINT 1 SW05 DURING DYNAMIC CERTIFICATION TESTING, 2-PLACE SIDE FACING DIVAN, THE BUCKLE ON THE AFT ANTHROPOMORPHIC TEST DUMMY (ATD) POSITION RESTRAINT SYSTEM DISENGAGED ALLOWING THE ATD TO MOVE UNRESTRAINED. PROBABLE CAUSE APPEARS TO BE FAILURE OF THE BUCKLE`S LOCKING PIN TO FULLY ENGAGE THE STRIKING PLATE (CONNECTOR) ON THE OPPOSITE HALF OF THE LAP BELT. PART MAY HAVE BEEN DEFECTIVE. MFG SHOULD IMPROVE INSPECTION PROCESS TO ENSURE THAT NO DEFECTIVE PARTS LEAVE THEIR FACILITY. (K) 20060512001402006051200140EA 2006 5 12 2006FA0000439 220060128G853073938 INTAKE VALVE PIPER PA32 PA32300 7103212SO LYC O540 IO540* 41532EA CYLINDER NR 3 DISINTEGRATED B XXORK NONE ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS NRNOT REPORTED 1 WP0156709127 327440020 INTAKE VALVE DISINTEGRATED, FALLING INTO CYLINDER HEAD NR 3. VALVE BOUNCED AROUND, BEATING THE TOP OF PISTON AND CYL HEAD CAUSING EXTENSIVE DAMAGE, FINALLY THE VALVE WAS SUCKED INTO THE INTAKE CAUSING A GAPPING HOLE ON THE INTAKE PORT. INTAKE VALVE FAILURE IS BELIEVED TO BE THE ONLY CAUSE OF CATASTROPIC FAILURE. (K) 1L71 3O3 O A3SO 1E4 20060508000522006050800052 2006 5 8 2006FA0000440 420060223G34178220839429 ADC LEAR 60 60LEAR 5170707CE PWA 305 PW305 NE LT AFT AVIONICS DEFECTIVE B BSYRO OTHER S AFFECT SYSTEMS CRCRUISE 1 GL07160AN 126 ALL ADC OUTPUTS ON THE COPILOTS PFD (ALTIMETER, VSI AND AIRSPEED, ECT) FLAGGED IN FLIGHT INTERMITTENTLY AND WOULD RESET ITSELF. CREW REQUESTED TO LEAVE RVSM AIRSPACE. THE ADC WAS FOUND TO BE DEFECTIVE AND WAS REPLACED. THE SYSTEM WAS TESTED AND INSPECTED IAW MM AND FOUND TO COMPLY WITH FAR 91.411 PART 43 AND MFG RVSM ADC INSPECTIONS. THE AIRCRAFT REMAINS RVSM COMPLIANT. (K) 2L72 4F4 FRTA10CE E35NE 20060511002732006051100273SO 2006 5 11 2006FA0000441 220060417G8550CH48110 OIL FILTER CESSNA182 182P 2075816CE CONT O470 O470* 17026SO ENGINE MISMANUFACTURED D K NONE O OTHER ININSP/MAINT 1 SO1358946 18262417 MOUNTING STUD TOO LONG, APPROX .200 LONGER. INSTALLED OIL FILTER AFTER OIL CHANGE, RAN ENGINE TO LEAK CHECK AND LOST ALMOST 2 QTS OF OIL. INVESTIGATION FOUND THAT THE OIL FILTER STUD WAS TOO LONG CAUSING THE FILTER TO TORQUE BEFORE SEAL TOUCHED FLANGE, LEAVING .050 GAP. REPLACED FILTER WITH SAME PN BUT WITH SHORTER STUD AND LEAK CHECKED, OK. (K) 1H71 3O3 ONTTA13 E273 20060512001582006051200158SO 2006 5 12 2006FA0000442 120060323G2910 HYDRAULIC LINE PIPER PA23 PA23250 7102308SO LYC O540 IO540* 41532EA RT CABIN SIDE CHAFED D O OTHER K FLUID LOSS APAPPROACH 1 EA07638688803 277854020 COMPLETE INTERIOR REFURBISHING WAS DONE. 100 HRS AFTER AC WAS RETURNED TO SERV, NOSE AND LT MAIN GEAR WOULD NOT LOCK DOWN, PILOT LANDED WITH ONLY RT GEAR EXTENDED. HYD FLUID WAS DRIPPING FROM BELLY, UPON INVESTIGATION, ALUMINUM HYD LINE WAS CHAFED THROUGH BY AILERON CABLE IN FRONT OF MAIN SPAR, UNDER CABIN ENTRANCE DOOR SILL. SUSPECTED THAT AFTER AC WAS INSP, WHEN DISCREP WERE BEING CLEARED, INTERIOR WORK BEING DONE, PERSONNEL SOMEHOW BENT LINE DOWN TO WHERE IT CONTACTED CABLE. WHEN PANEL IS REMOVED UNDER DOOR, HYD LINES ARE EXPOSED, LITTLE SUPPT IN THIS AREA, LITTLE CLEARANCE BTWN LINES, CABLES. LINES, CABLES ON LT SIDE OF CABIN ARE LESS LIKELY TO BE DISTURBED AS AUTOPILOT ROLL SERVO PROTECTS THEM. (K) 1L72 3O3 O 1A10 1E4 20060512001432006051200143NM 2006 5 12 2006FA0000443 120060419G5400F2MA581200817 COWLING AMD FALC50FALCON2000 2730170NM LT ENGINE SEPARATED B UO2RA UNSCHED LANDING D INFLIGHT SEPARATION CRCRUISE 1 GL19722JB 13 AIRCRAFT WAS RETURNING TO HOME FIELD AFTER MAINTENANCE WHEN CREW HEARD A LOUD NOISE AND ELECTED TO RETURN TO DEPARTURE. AFTER ENGINE SHUTDOWN, IT WAS DETERMINED THAT THE LT ENGINE UPPER AND LOWER COWLING HAD SEPARATED FROM THE AC IN FLIGHT. SB CONCERNING COWLING SEPARATION, HAD BEEN PREVIOUSLY APPLIED. COWL SEPARATION HAS BEEN THE SUBJECT OF PREVIOUS SERVICE ADVISORIES AND SERVICE NEWS FLASHES. (K) 2K72 4F RTA50NM 20060511002852006051100285NM 2006 5 11 2006FA0000444 120060419G5400F2MA581260813 COWLING AMD FALC50FALCON2000 2730170NM LT ENGINE SEPARATED B UO2RA UNSCHED LANDING D INFLIGHT SEPARATION CRCRUISE 1 GL19722JB 13 AC WAS RETURNING TO HOME FIELD AFTER MAINTENANCE WHEN CREW HEARD A LOUD NOISE AND ELECTED TO RETURN TO DEPARTURE. AFTER ENGINE SHUT-DOWN, IT WAS DETERMINED THAT THE LT ENGINE UPPER AND LOWER COWLING HAD SEPARATED FROM THE AC IN FLIGHT. SB CONCERNING COWLING SEPARATION, HAD BEEN PREVIOUSLY APPLIED. COWL SEPARATION HAS BEEN THE SUBJECT OF PREVIOUS SERVICE AD AND SERVICE NEWS FLASHES. (K) 2K72 4F RTA50NM 20060508001652006050800165CE 2006 5 8 2006FA0000445 120060330G5610NH2401691 WINDSHIELD RAYTHNDH125 HAWKER800XP 7150012CE GARRTTTFE731TFE731* 01518WP COCKPIT CRACKED D BA EMER. DESCENT UNSCHED LANDING O OTHER CRCRUISE 1 EA07333PC4619 258277 LEVEL FLIGHT AT 360, PILOTS (B) PANEL OUTER HEATED LAYER CRACKED ALONG LOWER FRONT CORNER THEN CONTINUED UP AND ACROSS TOP OF WINDOW. CREW DECLARED AN EMERGENCY AND DESCENDED TO 8000 FT. OUTER PANEL STAYED WITH AIRCRAFT, NO AD OR SB APPLY TO PANEL AT THIS TIME. WINDOW REPLACED WITH NEW UNIT. PRESSURIZATION AND OPS CHECK GOOD. THIS WINDOW HAD NO VISIBLE OR OPERATIONAL PROBLEMS PRIOR TO FAILURE. (K) 2L72 4F4 FRTA3EU E6WE 20070511001532007051100153SW 2007 5 11 2006FA0000446 120060410G62103G6220A00251 BOLT AGUSTAAB139 AB139 0260110SW PWA PT6 PT6* 52043EA MAIN ROTOR GOUGED B LWXRK NONE O OTHER ININSP/MAINT 1 SW19139HS50 31016 DURING ACCOMPLISHMENT OF THE MAIN ROTOR BLADE REMOVAL, IT WAS DISCOVERED THAT EACH OF THE BLADE BOLTS HAS RADIAL GOUGE MARKS AT THE BLADE TO HUB BUSHING LOCATIONS. THE DAMAGE IS OUTSIDE THE AMM PERMITTED REPAIR LIMITS. (REFERENCE: 39A62221300A286AB) MFG HAS BEEN CONTACTED AND PROVIDED THIS INFORMATION. (NOTE: THERE ARE ALSO TYPOGRAPHICAL ERRORS IN THE AMM MILLIMETER TO INCHES CONVERSIONS IN FIGURE 2 INCH (MAXIMUM DAMAGE AND REPAIR DEPTHS). FIG CALLS OUT (MM/IN) 0.02 / 0.0080, SHOULD BE 0.0008. (K) 2G72 6U3 T R00002RDE2NE 20060509001992006050900199SO 2006 5 9 2006FA0000447 120060226G32131180500 STRUT PIPER PA17 PA17 7101702SO CONT A65 A65* 17003SO LANDING GEAR CORRODED D K NONE O OTHER ININSP/MAINT 1 GL134879H725 17178 CHANGING SHOCK CORDS, DISCOLORATION OF INNER STRUT TUBE (LONGER ONE), REMOVED IT FROM OUTER TUBE (SHORTER ONE) OF INNER STRUT TUBES WAS CORRODED APPROX 50 PERCENT OF CIRCUM. OTHER INNER STRUT HAD MULTIPLE CORROSION HOLES THROUGH METAL. BOTH SHORT TUBES (OUTER) SHOWED ELONGATION AT ENDS INDICATING FLEXING/ BENDING OF ASSY DURING LANDING/TAKEOFF. ONLY NEW BUNGEES KEPT GEAR FROM FINAL FAILURE, RESULTANT GROUND LOOP. BUNGEE CORDS, WHEN INSTALLED, COVER THIS AREA, USUALLY HAVE A CLOTH OR ALUMINUM FAIRING OVER THEM. DETECTION REQUIRES REMOVAL OF FAIRINGS AT A MINIMUM, AND REMOVAL OF BUNGEES TO CLEARLY SEE OUTER TUBES CIRCUM. NECESSARY TO DISASSEMBLE UNIT, VIEW INNER PIECE, OUTER PIECE SEPARATELY. (K) 1H71 3O3 O A805 E205 20060509002372006050900237SO 2006 5 9 2006FA0000448 220060414G73226297032 FCU CESSNA210 210E 2073416CE CONT O520 IO520A 17032SO ENGINE WORN D K NONE O OTHER ININSP/MAINT 1 EA03 2240 1740067F FOUND SHAFT AND LINKAGE EXCESSIVELY WORN. HAD COMPLETE ASSEMBLY OVERHAULED. (K) 1H71 3O3 O 3A21 E5CE 20060510001302006051000130CE 2006 5 10 2006FA0000449 120060501G33206900042000 LIGHT BEECH BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA CABIN BURNED OUT C O OTHER B SMOKE/FUMES/ODORS/SPARKS ININSP/MAINT 1 SO11800HA BB220 FLUORESCENT LIGHT ASSY FAILED AND DISPERSED SMOKE IN CABIN. POWER SUPPLY GOT HOT AND DAMAGED ADJACENT INSULATION. LIGHT ASSY WAS REPLACED WITH FACTORY NEW. 1L72 4T4 T A24CE E4EA 20060510001332006051000133CE 2006 5 10 2006FA0000450 120060501G33206900042000 LIGHT BEECH BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA CABIN BURNED OUT C O OTHER B SMOKE/FUMES/ODORS/SPARKS ININSP/MAINT 1 SO11800HA BB220 FLUORESCENT LIGHT ASSY FAILED AND DISPERSED SMOKE IN CABIN. POWER SUPPLY GOT HOT AND DAMAGED ADJACENT INSULATION. LIGHT ASSY WAS REPLACED WITH FACTORY NEW. 1L72 4T4 T A24CE E4EA 20060509002412006050900241EA 2006 5 9 2006FA0000451 220060505G8530 VALVE LYC 0360J2A LYC O360 O360J2A 41514EA MALFUNCTIONED P JWEGR AUTOROTATION E VIBRATION/BUFFET CRCRUISE 1 SW09 L3963136A L3963136A NEW ENGINE IN NEW HELICOPTER. AFTER FLYING 1.5 HOURS, ENGINE WILL START POPPING AND BACKFIRING, CAUSING AN AUTOROTATION. MFG SAID IT'S A NORMAL MAINTENANCE ITEM TO REMOVE VALES AND REAM VALVE GUIDES. 3 O E286 20060512000502006051200050EA 2006 5 12 2006FA0000452 220060425G7322MA4SPA105135 CARBURETOR PIPER PA28 PA28161 7102803SO LYC O320 O320D3G 41508EA ENGINE UNSERVICEABLE D O OTHER YK ENGINE STOPPAGE FLUID LOSS TXTAXI/GRND HDL 1 EA172203T 800 287916300 REF: NM-02-47 DATED 9/30/02 AND CE-06-33R1, DATED 4/12/06. ENGINE QUITS AT IDLE; IDLE SET AT 600, WILL DROP OFF AND QUIT. FUEL SOMETIMES DRAINS FROM CARB AFTER SHUTDOWN. BOTH SYMPTONS MATCH THOSE IN NM-02-47. (K) 1L71 3O3 O 2A13 E274 20060510002382006051000238SO 2006 5 10 2006FA0000453 220060418G8530AEC65385 CYLINDER BEECH 58 58 1152740CE CONT O550 IO550C SO RT ENGINE CRACKED D K NONE O OTHER ININSP/MAINT 1 SW013149P1301 1301 TH1470 810387R NR 1 CYLINDER CRACKED AT SPARK PLUG HOLE. (RT ENGINE) (K) 1L72 3O3 O 3A16 E3SO 20060510002392006051000239SO 2006 5 10 2006FA0000454 220060418G8530AEC65385 CYLINDER BEECH 58 58 1152740CE CONT O550 IO550* SO LT ENGINE CRACKED D K NONE O OTHER ININSP/MAINT 1 SW013149P1301 1301 TH1470 810386R NR 5 CYLINDER CRACKED AFT OF VALVES. (STILL HAD GOOD COMPRESSION BUT COULD HEAR AIR) (LT ENGINE) (K) 1L72 3O3 O 3A16 E3SO 20060512000512006051200051SO 2006 5 12 2006FA0000455 220060418G8530AEC65385 CYLINDER BEECH 58 58 1152740CE CONT O550 IO550* SO LT ENGINE CRACKED D K NONE O OTHER ININSP/MAINT 1 SW013149P1301 1301 TH1470 810386R NR 2 CYLINDER COMPLETELY CRACKED ALL THE WAY AROUND AFT OF VALVES. (LT ENGINE) (K) 1L72 3O3 O 3A16 E3SO 20060510002412006051000241SO 2006 5 10 2006FA0000456 220060418G8530AEC65385 CYLINDER BEECH 58 58 1152740CE CONT O550 IO550* SO LT ENGINE CRACKED D K NONE O OTHER ININSP/MAINT 1 SW013149P1301 1301 TH1470 810386R NR 6 CYLINDER CRACKED AFT OF VALVES. (STILL HAD GOOD COMPRESSION COULD HEAR AIR.) (LT ENGINE) (K) 1L72 3O3 O 3A16 E3SO 20060512000582006051200058SO 2006 5 12 2006FA0000457 220060418G8530AEC65385 CYLINDER BEECH 58 58 1152740CE CONT O550 IO550* SO LT ENGINE CRACKED D K NONE O OTHER ININSP/MAINT 1 SW013149P1301 1301 TH1470 810386R NR 4 CYLINDER CRACKED AFT OF VALVES. (STILL HAD GOOD COMPRESSION BUT COULD HEAR AIR) (LT ENGINE) (K) 1L72 3O3 O 3A16 E3SO 20060512000592006051200059CE 2006 5 12 2006FA0000458 120060419G27500400107146 CABLE CESSNA150 152 2071835CE LYC O235 O235* 41505EA FLAP CONT SYS BROKEN D O OTHER F FLT CONT AFFECTED APAPPROACH 1 NM095494P12872 15284959 ON FINAL, STUDENT SELECTED 30 DEGREE FLAPS, A LOUD POP WAS HEARD, RT FLAP CAME DOWN TO 30 DEGREES, NO MOVEMENT AT LT FLAP. AIRCRAFT LANDED WITHOUT INCIDENT. INVESTIGATION REVEALED SWAGGED BALL END OF CABLE, PN 0400107-146 BROKE FROM REMAINING CABLE. SUSPECT HIGH TIME AND CYCLES AS CONTRIBUTING FACTORS. (K) 1H71 3O3 ONT3A19 E223 20060512000452006051200045SO 2006 5 12 2006FA0000459 120060419G5341 ATTACH FITTING PIPER PA25 PA25235 7102504SO LYC O540 O540* 41532EA FUSELAGE OUT OF LIMITS D K NONE O OTHER ININSP/MAINT 1 GL216719Z3732 252328 ATTACHMENT CONNECTIONS AT RT AND LT SIDES ARE BELOW MINIMUM SPECIFIED IN AD. INSPECTION METHOD- ULTRASONIC. (K) 1L71 3O3 O 2A10 E295 20060517002362006051700236CE 2006 5 17 2006FA0000460 120060413G2840S38521 GAUGE CESSNA172 172R 2072401CE LYC IO360 IO360L2A EA LT FUEL TANK FLUCTUATES B BNZRK NONE N FALSE WARNING NRNOT REPORTED 1 GL195335G50 17281158 PART HAS A DEAD SPOT IN ITS TRAVEL CAUSING FUEL GAUGE TO FLUCTUATE RAPIDLY BETWEEN FULL AND EMPTY ALSO CAUSES LOW FUEL WARNING LIGHT TO FLASH CONTINUOUSLY. (K) 1H71 3O3 ONT3A12 1E10 20060511001822006051100182CE 2006 5 11 2006FA0000461 120060314G2842S38522 SENSOR CESSNA172 172R 2072401CE LYC IO360 IO360L2A EA RT FUEL TANK FLUCTUATES B BNZRK NONE N FALSE WARNING NRNOT REPORTED 1 GL195335G86 17281158 PART HAS A DEAD SPOT IN ITS TRAVEL (NEAR FULL POSITION AT TOP OF TRAVEL) CAUSING FUEL GAUGE TO FLUCTUATE RAPIDLY BETWEEN FULL AND EMPTY, ALSO CAUSES LOW FUEL WARNING LIGHT TO FLASH CONTINUOUSLY. (K) 1H71 3O3 ONT3A12 1E10 20060511001842006051100184 2006 5 11 2006FA0000462 420060316G611305503214 BULKHEAD CESSNA172 172N 2072434CE LYC O320 O320D2G 41508EA SPINNER CRACKED C K NONE O OTHER ININSP/MAINT 1 NM01734QQ292 17269034 L3871627A DURING ROUTINE PHASE INSPECTION FWD PROP BULKHEAD FOUND TO BE CRACKED NEAR SEVERAL MOUNTING BOLT HOLES. HAVE SEEN THIS SEVERAL TIMES BEFORE. SUSPECT DEFECT IN CURRENT MFG PROCESS. (K) 1H71 3O3 ONT3A12 E274 20060512000752006051200075CE 2006 5 12 2006FA0000463 120060427G3246300257 WHEEL BEECH 90 C90A 1152911CE MLG CRACKED C K NONE O OTHER NRNOT REPORTED 1 NM01164WS199 A5643 LJ1736 CRACKED IB WHEEL HALF CAUSING LOSS OF TIRE AIR PRESSURE. NOTE: THIS WAS A BRAND NEW PART ON A NEW AIRPLANE. NOT AN OVERHAULED PART (SEE 5(I) AND 6(I) 1L72 3T RT3A20 20060512001332006051200133CE 2006 5 12 2006FA0000464 120060509G5741130909B103 BOLT BEECH 36 B36TC 1151609CE WING ATTACH CRACKED B K NONE O OTHER ININSP/MAINT 1 GL117258E142 EA455 MAG PART INSP FOUND FWD WING ATTACH POINTS BOLT P/N 130909B103 AND 131790-3 WITH CRACKS. THE BOLTS WERE INSTALLED NEW IN FWD WING BOLT FITTINGS ON BEECH MODEL 36 SERIES AIRCRAFT S/N EA-455 ON 1/25/2002. THE LH UPPER BOLT (P/N 130909B103) WAS REMOVED FOR IT'S FIRST 5 YEAR NDT INSPECTION AND WAS CRACKED AT THE HEAD RADIUS USING MAG PART NDT PROCESS. PART TOTAL TIME 142 HRS SINCE INSTALLED. NO DAMAGE NOTED ON THE ASSOCIATED WING FITTING THAT WOULD INDICATE A CONTRIBUTING STRESS CONDITION. THE RT LOWER WING BOLT ON THE OPPOSITE SIDE OF THE A/C WAS ALSO CRACKED IN THE SAME LOCATION. THIS BOLT IS A DIFFERENT P/N (131790-3). BEECH TECH SUPPORT WAS GIVEN THE BOLTS & INFO FOR EVALUATION. 1L71 3O 3A15 20060512001342006051200134CE 2006 5 12 2006FA0000465 120060509G57411317903 BOLT BEECH 36 B36TC 1151609CE WING ATTACH CRACKED B K NONE O OTHER ININSP/MAINT 1 GL117258E142 EA455 MAG PART INSP FOUND FWD WING ATTACH POINTS BOLT P/N 130909B103 AND 131790-3 CRACKED. BOLTS INSTALLED NEW IN FWD WING BOLT FITTINGS ON BEECH MODEL 36 SER A/C S/N EA-455 ON 1/25/2002. THE LT UPPER BOLT (P/N 130909B103) REMOVED FOR FIRST 5 YEAR NDT INSPECTION AND WAS CRACKED AT THE HEAD RADIUS. USED MAG PART INSP. TTSN 142 HRS. NO DAMAGE WAS NOTED ON THE ASSOCIATED WING FITTING THAT WOULD INDICATE A CONTRIBUTING STRESS CONDITION. RT LOWER WING BOLT ON THE OPPOSITE SIDE OF THE A/C ALSO CRACKED IN SAME LOCATION. THIS BOLT IS A DIFFERENT P/N (131790-3). BEECH TECH SUPPORT GIVEN BOLTS AND ALL THE INFO PERTINENT TO THESE PARTICULAR BOLTS FOR EVALUATION. OPERATING CONDITIONS OF THE AIRCRAFT ARE UNKNOWN. 1L71 3O 3A15 20060511001872006051100187EA 2006 5 11 2006FA0000466 220060410G8520 CONNECTING ROD GULSTM500 500S 0141107SW LYC O540 IO540E1B5 41532EA RT ENGINE BROKEN B BOERO OTHER Y ENGINE STOPPAGE CRCRUISE 1 GL1990JP 3078 L805848 CUSTOMER WAS ENROUTE TO MAINTENANCE SHOP TO GET ANNUAL INSPECTION, BOTH ENGINES OVERHAULED. RT ENGINE CYLINDER NR 2 CONNECTING ROD BROKE AT THE CRANKSHAFT ATTACHMENT CAUSING MAJOR DAMAGE TO THE CAMSHAFT, AND CRANKCASE BREAKING OPEN IN SEVERAL PLACES AROUND THE FRONT PART OF THE ENGINES. (K) 1H72 3O3 O 6A1 1E4 20060517002372006051700237SO 2006 5 17 2006FA0000467 220060410G8530631397 CYLINDER CESSNA340 340A 2076405CE CONT O520 TSIO520NB 17040SO ENGINE CRACKED C BOERK NONE O OTHER NRNOT REPORTED 1 GL19984MW 340A0070 521294 AT 400 HR TSO FOUND CYLINDER NR 4 CRACKED AT THE HEAD 5 FINS BACK TOWARD THE BARREL FROM THE TOP SPARK PLUG. CRACK GOES FROM THE EXHAUST VALVE SEAT TO THE TOP SPARK PLUG HOLE ON THE INSIDE OF THE CYLINDER. AD 04-08-10 DID NOT APPLY BY CLY. SN 13516-4 AND CODE A STAMPED ON THE BOSS FLANGE. (K) 1L72 3O3 O 3A25 E8CE 20060517002172006051700217 2006 5 17 2006FA0000468 420060419G3425NSD360 HSI CESSNA340 340A 2076405CE CONT O520 TSIO520* 17040SO COCKPIT DEACTIVATED B F3ORO OTHER G MULTIPLE FAILURE NRNOT REPORTED 1 SO03594HS 340A0440 PILOT REPORTED HSI WAS INOPERATIVE AND SUSPECTED A PLUG WAS OFF. VISUAL INSPECTION REVEALED THAT THE PUG TO THE HSI, AND THE VACUUM HOSE HAD BOTH BEEN PULLED OFF BY THE AC CONTROL WHEEL. THE HOSES AND WIRING HARNESS HAD BEEN INCORRECTLY ROUTED AROUND THE CONTROL WHEEL. THE AC HAD VERY LITTLE ROOM BEHIND THE INSTRUMENT PANEL, AND THE CORRECT ROUTING OF HOSES AND HARNESSES IS CRITICAL TO FLIGHT SAFETY. THE CONTROLS WERE FREE AFTER THE HOSE AND HARNESS CAME OFF THE PILOTS HSI. WITH MORE AC BEING UPGRADED WITH NEWER AVIONICS AND INSTRUMENTS, INSPECTIONS OF HARNESSES AND HOSES BEHIND THE INSTRUMENT PANEL IS AN AREA THAT REQUIRES INCREASED VIGILANCE. (K) 1L72 3O3 O 3A25 E8CE 20060512001382006051200138CE 2006 5 12 2006FA0000469 120060426G81004656809004 TURBOCHARGER CESSNA210 P210N 2073454CE CONT O520 TSIO520P 17040SO ENGINE LEAKING B WS9RK NONE K FLUID LOSS ININSP/MAINT 1 NM074773P P21000102 OIL LEAKING OUT FROM JOINT IN CENTER OF TURBO. FIRST RUN ON OVERHAULED UNIT JUST INSTALLED ON AIRCRAFT. (K) 1H71 3O3 O 3A21 E8CE 20060807000962006080700096 2006 8 7 2006FA0000470 120060404G8011X13041 BEARING CONT O520 TSIO520C 17040SO STARTER FAILED B R04RK NONE O OTHER ININSP/MAINT 1 NM04 1 WHILE REMOVING THE STARTER FOR MAINTENANCE, THE STARTER ADAPTER WORM SHAFT ROLLER BEARING RETAINER CAGE HALF WAS FOUND STUCK TO THE STARTER FLANGE. ALL THE ROLLER BEARING BALLS WERE STILL IN THEIR RACES BUT BLUISH IN COLOR. AFTER DISASSEMBLING THE ADAPTER, THE INNER HALF AND SMALLER PIECES OF THE CAGE WERE FOUND IN THE LOWER RECESSES OF THE ADAPTER HOUSING. FORTUNATELY, NONE WAS SUSPECTED TO HAVE ENTERED THE ENGINE SUMP. IT WAS SUSPECTED THAT THE STARTER RELAY REMAINED ENGAGED AND THE STARTER WAS ENERGIZED DURING ONE OR MORE GROUND RUNS. 3 O E8CE 20060613002102006061300210CE 2006 6 13 2006FA0000471 120060412G3246300257 WHEEL HALF BFGOODRICH BEECH 90 C90A 1152911CE LT MLG CRACKED C K NONE O OTHER ININSP/MAINT 1 SW99164WS177 A5665 LJ1736 LEFT MAIN WHEEL (INBOARD HALF) FOUND CRACKED. PROBLEM SHOWED ITSELF DUE TO WHEEL/TIRE ASSY SUFFERING A SLOW LEAK OF AIR PRESSURE. THIS IS NOT THE SAME PROBLEM REPORTED FOR THIS AIRCRAFT ON 4/27/2006. THIS IS A PREVIOUS OCCURRENCE ON THE OTHER SIDE. BOTH MAIN WHEELS HAVE NOW BEEN CHANGED. 1L72 3T RT3A20 20060613002342006061300234CE 2006 6 13 2006FA0000472 120060502G284299144272 FLOAT SWITCH CESSNA560 560XL 2076702CE FUEL SYS INOPERATIVE B K NONE B SMOKE/FUMES/ODORS/SPARKS NRNOT REPORTED 1 GL09635QS2291 5605358 THE RIGHT LOW FUEL LEVEL SYSTEM WAS INOPERATIVE. REMOVED SWITCH AND FOUND SIGNS OF ARCING ON THE TOP SIDE OF THE SWITCH. TROUBLESHOT FURTHER AND FOUND THE PC BOARD WAS DEFECTIVE. IT IS NOT KNOWN IF THE SWITCH DAMAGED THE PC BOARD. THIS IS NOT THE FIRST TIME WE HAVE SEEN A DEFECTIVE FLOAT SWITCH WITH SIGNS OF ARCING, HOWEVER, IT IS THE FIRST TIME THAT A DAMAGED PC BOARD WAS ASSOCIATED WITH IT. IT WAS NOTED THAT WHEN THE FLOAT SWITCH IS IN THE 'HIGH FUEL LEVEL' POSITION THE CONTACT SURFACES ARE ALIGNED. WHEN THE SWITCH IS IN THE 'LOW FUEL LEVEL' THE CONTACTS ARE NEARLY COMPLETELY MISALIGNED. 2L72 4F RTA22CE 20060511003012006051100301CE 2006 5 11 2006FA0000473 120060510G29102607003453 HYDRAULIC LINE LEAR 35 35A 5170602CE REAR EQUIP BAY LEAKING B K NONE K FLUID LOSS ININSP/MAINT 1 SO13222BG 35A448 PRE-FLIGHT FOR SECOND LEG OF FLIGHT CREW REPORTED HYDRAULIC FLUID DRIPPING OUT OF REAR EQUIPMENT BAY. INSPECTION REVEALED THAT THE HYDRAULIC PRESSURE LINE HAD CHAFED THROUGH AND WAS LEAKING FLUID. INSTALLED NEW LINE. COMPLIED WITH PRESSURE CHECK OF SYSTEM WITH NO ADDITIONAL LEAKS NOTED. CHECKED ROUTING OF LINE AND INSTALLED CHAFE MATERIAL WHERE NEEDED. PART HOURS OR CYCLES UNKNOWN. 2L72 4F A10CE 20060518002612006051800261EU 2006 5 18 2006FA0000474 120060510G3246AHA1814 WHEEL HALF BRAERODH125 BAE125800A 1500285EU LANDING GEAR CRACKED B K NONE O OTHER ININSP/MAINT 1 SO132QG NA0467 DURING ROUTINE TIRE CHANGE AND EDDY CURRENT INSPECTION OF DUNLOP MAIN WHEEL HALF AND FLANGE. EDDY CURRENT INSPECTION REVEALED TWO CRACKS WHICH RADIATED OUT FROM WHEEL TIE BOLT HOLE. BOTH CRACKS WERE APPROMIXATELY .050 INCHES IN LENGTH. PART WAS REJECTED AND REPLACED WITH NEW PART. WHEEL PART NO. AHA1814 FLANGE PART NO.AH43949. PART HOURS OR CYCLES UNKNOWN. 2L72 4F RTA3EU 20060518002622006051800262CE 2006 5 18 2006FA0000475 120060510G2730083200054 HINGE BRACKET CESSNA CESSNA421 421B 2076014CE RT ELEVATOR ELONGATED B K NONE E VIBRATION/BUFFET DEDESCENT 1 WP231944G8307 421B0844 CUSTOMER REPORTED VIBRATION AT HIGH SPEEDS. INSPECTED AIRCRAFT AND FOUND CENTER ELEVATOR HINGE IB AND OB BRACKETS ELONGATED ON THE RT ELEVATOR. INSTALLED MFG SERVICE KIT SK421-130B REPLACING ALUMINUM ELEVATOR HINGE BRACKETS WITH STAINLESS STEEL BRACKETS. 1L72 3O A7CE 20060519002422006051900242WP 2006 5 19 2006FA0000476 220060426G72108687813 GEAR MTSBSIMU2 MU2B36A 5780413CE GARRTTTPE331TPE33110T WP LT ENGINE GRBOX CRACKED B IZ2RO OTHER EY VIBRATION/BUFFET ENGINE STOPPAGE CRCRUISE 1 SW15777LP 719SA PILOT REPORTED DURING CRUISE LEVEL FLIGHT FEELING A SUDDEN VIBRATION AND HEARING A SCREAMING NOISE FROM THE LT ENGINE. PILOT THEN NOTICED TORQUE INDICATION ON LT ENGINE INDICATING 120 PERCENT WITH NO YAW INDICATED OR NOTICED BY PILOT. WHILE RETARDING LT POWER LEVER TO REDUCE TORQUE THE LT ENGINE SHUTDOWN UNCOMMANDED. ENGINE NTS SYSTEM FUNCTIONED NORMALLY AND AN UNEVENTFUL SINGLE ENGINE LANDING WAS MADE. UPON ENGINE ASSEMBLY A 2 INCH PIECE OF THE BULL GEAR OUTER RIM WAS LAYING IN THE BOTTOM OF THE ACCESSORY HOUSING. INSPECTION OF THE BULL GEAR REVEALED THE MISSING SECTION AND AN APPROX 4 INCH CRACK IN THE HUB AREA WHICH CAUSED LOSS OF DRIVE TO THE PROPELLER SHAFT. 1H72 3T4 T A10SW E4WE 20060517002082006051700208EA 2006 5 17 2006FA0000478 220060501G7414S6LSC21BL5005162MAGNETO PIPER PA25 PA25235 7102504SO LYC O540 O540B2C5 41532EA ENGINE DISINTEGRATED D K NONE O OTHER ININSP/MAINT 1 SO167339Z 740 253289 L1154840 MAGNETO WAS REMOVED FROM ENGINE FOR ROUTINE MAINTENANCE INSPECTION. THREADS ON MAGNETO SHAFT AND NUT WERE COMPLETELY STRIPPED. SLOT IN SHAFT FOR WOODRUFF KEY WAS WALLOWED OUT. COTTER KEY WHICH RETAINED NUT TO SHAFT WAS STILL IN PLACE. AT TIME OF REMOVAL ENGINE WAS OPERATING NORMALLY. ONLY THE MAG BUSHINGS AND RETAINER WERE HOLDING THE IMPULSE COUPLING IN PLACE. THE DRIVE SHAFT AND OR THE WOODRUFF WERE DEFECTIVE AT THE TIME OF MANUFACTURE. THIS CONDITION IF UNDETECTED WILL LEAD TO COMPLETE ENGINE FAILURE. (K) 1L71 3O3 O 2A10 E295 20060518001322006051800132CE 2006 5 18 2006FA0000479 120060508G240070008840 CIRCUIT BREAKER LEAR 35 35A 5170602CE GARRTTTFE731TFE731* 01518WP COCKPIT TRIPPED C B EMER. DESCENT HG ELECT. POWER LOSS-50 PC MULTIPLE FAILURE CRCRUISE 1 SW11242MT10053 621 (ELECTRICAL ANOMALY), LT AND RT ESSENTIAL (A) CIRCUIT BREAKERS DEPLOYED. ALL EFIS WENT DARK. YAW DAMP AND AUTO PILOT DISENGAGED. LOST ALL NAV AND COMM. RADIOS, LOST ANNUNCIATOR PANEL LIGHTS. MAY HAVE LOST AIRSPEED INDICATORS AND FUEL COMPUTERS. LOST BOTH N 1’S . BOTH ITT’S, DC AND AC ELECTRICAL INDICATORS FUNCTIONED NORMALLY AND INDICATED NORMAL ELECTRICAL SYSTEM CONDITION. GEAR, FLAPS, SPOILERS, TRIMS, TR’S ALL FUNCTIONED NORMALLY. TR ARM AND DEPLOY LIGHTS DID NOT WORK. 2L72 4F4 F A10CE E6WE 20060516001832006051600183 2006 5 16 2006FA0000480 420060503G2215 ROLL SERVO GULSTM112 112A 7630302SW LYC O360 IO360A1A 41514EA AUTO PILOT SYS MISINSTALLED B TP4RK NONE O OTHER ININSP/MAINT 1 SO151346J 346 THE ROLL SERVO WAS INSTALLED AND RIGGED INCORRECTLY, THE SET WAS NOT TIGHT ON THE BRIDLE CABLE PIN AND THE BRIDLE CABLE WAS WRAPPED ON THE CAPSTAN INCORRECTLY. THE INCORRECT INSTALLATION IN CONJUNCTION WITH THE LOOSE SET SCREW ALLOWED THE BRIDLE CABLE LOCATING PIN TO PULL OUT OF THE SERVO CAPSTAN. THE LOCATING PIN LOCKED THE AILERONS AT FULL DEFLECTION AGAINST THE CAPSTAN GUARD. THIS CONDITION OCCURRED ON THE GROUND, IN FLIGHT THIS CONDITION WOULD VERY LIKELY RESULT IN AN ACCIDENT. RECOMMEND ROLL SERVO INSTALLATIONS BE INSPECTED FOR PROPER INSTALLATION AND RIGGING. THE CONDITION HAS BEEN CORRECTED IAW FLIGHT DOCUMENT AK 1056. (K) 1L71 3O3 O A12SO 1E10 20060517002092006051700209SO 2006 5 17 2006FA0000481 220060425G8530646743 PISTON MOONEYM20 M20K 5870220SW CONT O360 TSIO360SB SO ENGINE ERODED D K NONE O OTHER ININSP/MAINT 1 NM0743PG 700 252019 THE OIL CONTROL RING LANDS ON PISTON SEVERLY ERRODED AT PISTON PIN HOLE, BOTH SIDES OF PISTON. THIS IS THE 13 TH PISTON THAT WE HAVE SEEN THIS ON, IN OUR ENGINE SHOP. SC MODIFICATIONS, HAS 12 OF THEM, HAVE SAME PROBLEM. HAVE ONE TO SHOW. (K) 1L71 3O3 O 2A3 E9CE 20060516002102006051600210 2006 5 16 2006FA0000482 420060501G2562EBC502 ELT DIAMONDA20 DA20A1 2990000GL BAGGAGE COMPT MISINSTALLED B UKJRK NONE O OTHER ININSP/MAINT 1 EA2371LV 10070 WHEN REMOVING ELT FROM AIRCRAFT TO REPLACE ELT BATTERY, FOUND THAT SOMEONE HAD PUT THE ELT IN BACKWARDS. THE DIRECTION OF FLIGHT ARROW WAS POINTING AFT. THIS INSTALLATION IS LOCATED IN THE BAGGAGE COMPT AND THE PILOT CAN SLIDE IT OUT OF ITS MOUNT AND REINSTALLED IT BACKWARDS. (K) 1L71 3O NTTA4CH 20070511001552007051100155SW 2007 5 11 2006FA0000483 120060428G62103G62200A251 BOLT AGUSTAAB139 AB139 0260110SW MAIN ROTOR GOUGED B LWXRK NONE O OTHER ININSP/MAINT 1 SW19140HS8 31036 UPON RECEIPT OF THE AIRCRAFT, THE MAIN ROTOR BLADE BOLTS WERE REMOVED FOR INSPECTION. IT WAS DISCOVERED THAT ONE BLADE BOLTS HAS A RADIAL GOUGE MARK AT THE LOWER BLADE TO HUB BUSHING LOCATION. THE DAMAGE IS OUTSIDE THE AMM PERMITTED REPAIR LIMITS. THE AC TT IS APPROXIMATELY 58.4 HOURS. ALL OF THE BLADE BOLTS WERE PREVIOUSLY CHANGED APPROX 8.5 HOURS PRIOR TO COMING TO REPAIR STATION. REF: 39A62221300A286AB, MFG HAS BEEN CONTACTED AND PROVIDED THIS INFORMATION. (K) 2G72 6U R00002RD 20060518001812006051800181CE 2006 5 18 2006FA0000484 120060223G57435041000201 TRUNNION CESSNA402 402B 207590PCE LT WING BROKEN G K NONE O OTHER LDLANDING 1 SO19400AR2300 402B0338 ON FEBRUARY 23RD, 2006, PILOT WAS OPERATING AC, VISUAL FLIGHT RULES PREVAILED. UPON LANDING, THERE WAS A FAILURE OF THE TRUNNION (P/N 5041000-201) ON THE LT MAIN LANDING GEAR STRUT CAUSING THE COLLAPSE OF THE LT MAIN LANDING GEAR. THE AIRCRAFT TURNED 180 DEGREES TO THE LT AND SLID OFF THE LT SIDE OF RUNWAY 27L, CAUSING DAMAGE TO THE LT WING, HORIZONTAL STABILIZER AND LT PROPELLER. 1L72 3O A7CE 20060516002112006051600211CE 2006 5 16 2006FA0000485 120060511G2742071250013 JACKSCREW CESSNA185 A185F 2072821CE TRIM SYS STRIPPED G K NONE O OTHER ININSP/MAINT 1 AL01275328672 18503688 MAINTENANCE PERSONNEL WERE ADVISED BY THE PILOT THE HORIZONTAL STABILIZER TRIM QUIT WORKING. INSPECTION FOUND THE BARREL SIDE OF THE TRIM SCREW JACK HAD STRIPPED OUT. THE SYSTEM INCLUDES 2 TRIM SCREW JACKS THE OTHER TRIM SCREW JACK TOOK ALL OF THE LOAD AND JAMMED UP. INSPECTION OF SECOND TRIM SCREW JACK BARREL FOUND THE UPPER THIRD OF THE THREADS WERE STRIPPED IN THE SECOND TRIM SCREW BARREL. MFG DOES NOT SPECIFY ANY INSPECTION CRITERIA FOR WEAR OF THE JACK SCREW THREADS OR THE BARREL THREADS. RECOMMEND EITHER MANDATORY INSPECTION CRITERIA FOR THE BARRELS AND THREADS OR AN AIRWORTHINESS DIRECTIVE TO PRECLUDE LOSS OF CONTROL OF THE TAIL OF THE AIRCRAFT. (K) 1H71 3O 3A24 20060518002632006051800263CE 2006 5 18 2006FA0000486 120060511G2821331996 GASKET BEECH 58 58 1152740CE WHEEL WELL SWOLLEN D K NONE K FLUID LOSS CRCRUISE 1 WP152335R TH1835 THE FUEL FILTER GASKETS SWELLED CAUSING THE FUEL FILTERS TO LEAK A LARGE AMOUNT OF FUEL OB WHILE IN FLIGHT. THE PILOT WAS UNAWARE OF THE LOSS OF FUEL UNTIL AFTER LANDING. APPARENTLY GASKETS ARE NOT COMPATIBLE WITH CURRENT BLENDS OF 100LL. WAS TOLD BY MFG TECHS THAT LOCAL AVGAS MAY HAVE LARGER AMOUNTS OF BENZENE AND TOULENE AND MAY BE CAUSING THE SWELLING OF THE GASKETS. THIS PROBLEM HAS OCCURRED MULTIPLE TIMES. PROBLEM UNRESOLVED AT THIS TIME. 1L72 3O 3A16 20060518002652006051800265CE 2006 5 18 2006FA0000487 120060511G2821331996 GASKET BEECH 58 58 1152740CE WHEEL WELL SWOLLEN D K NONE K FLUID LOSS CRCRUISE 1 WP152335R TH1835 THE FUEL FILTER GASKETS SWELLED CAUSING THE FUEL FILTERS TO LEAK A LARGE AMOUNT OF FUEL OVERBOARD WHILE IN FLIGHT. THE PILOT WAS UNAWARE OF THE LOSS OF FUEL UNTIL AFTER HE LANDED. APPARENTLY GASKETS ARE NOT COMPATIBLE WITH CURRENT BLENDS OF 100LL. WAS TOLD BY MFG TECHS THAT LOCAL AVGAS MAY HAVE LARGER AMOUNTS OF BENZENE AND TOULENE AND MAY BE CAUSING THE SWELLING OF THE GASKETS. THIS PROBLEM HAS OCCURRED MULTIPLE TIMES. PROBLEM UNRESOLVED AT THIS TIME. 1L72 3O 3A16 20060518002672006051800267CE 2006 5 18 2006FA0000488 120060511G2821331996 GASKET BEECH 58 58 1152740CE WHEEL WELL SWOLLEN D K NONE K FLUID LOSS CRCRUISE 1 WP152335R TH1835 THE FUEL FILTER GASKETS SWELLED CAUSING THE FUEL FILTERS TO LEAK A LARGE AMOUNT OF FUEL OVERBOARD WHILE IN FLIGHT. THE PILOT WAS UNAWARE OF THE LOSS OF FUEL UNTIL AFTER HE LANDED. APPARENTLY GASKETS ARE NOT COMPATIBLE WITH CURRENT BLENDS OF 100LL. WAS TOLD BY RAYTHEON TECHS THAT LOCAL AVGAS MAY HAVE LARGER AMOUNTS OF BENZENE AND TOULENE AND MAY BE CAUSING THE SWELLING OF THE GASKETS. THIS PROBLEM HAS OCCURRED MULTIPLE TIMES. PROBLEM UNRESOLVED AT THIS TIME. 1L72 3O 3A16 20060518002722006051800272SO 2006 5 18 2006FA0000489 220060503G8530AEC631397 CYLINDER BEECH 36 A36 1151604CE CONT O550 IO550B SO MCAULY3A32C D3A32C* GL ENGINE SEPARATED B MW8RK NONE O OTHER NRNOT REPORTED 1 SO018277D E2798 G675825 930397 NR 2 CYLINDER HEAD (SN 2253724) SEPARATION WITH 170.2 TOTAL SINCE NEW. NR 6 CYLINDER HEAD (SN 223899) SEPARATION WITH 171.7 TOTAL SINCE NEW. AD 2004-08-10 N/A TO SN. RECOMMEND ALL SN`S APPLICABLE AND REOCCURING CHECKS FOR ECI CYLINDERS USING M 91-6. (K) 1L71 3O3 O 3A15 E3SO 5 CP21EA 20060517002132006051700213SW 2006 5 17 2006FA0000490 120060302G29135001908 COUPLING BELL 206 206B 1181511SW ALLSN 250C 250C20 03013GL HYD PUMP SEPARATED B YJ2RO OTHER O OTHER NRNOT REPORTED 1 WP0137AJ 00010491 1877 HYDRAULIC PUMP TACH DRIVE COUPLING BRAZED WELDING FAILED CAUSING COUPLING TO SEPARATE FROM DRIVE GEAR SHAFT. MFG SHOULD CHECK THE STRENGTH OF BRAZE AFTER WELDING. WHEN THIS COUPLING FAILS, LOSS OF ROTOR TACH OCCURS. (K) 1G71 3U3 U H2SW E4CE 20060518002792006051800279SW 2006 5 18 2006FA0000491 120060302G29135001908 COUPLING BELL 206 206B 1181511SW ALLSN 250C 250C20B 03013GL HYD PUMP FAILED B XJ2RK NONE O OTHER NRNOT REPORTED 1 WP0159479196 99100424 1194 HYDRAULIC PUMP TACH DRIVE COUPLING BRAZED WELDING FAILED CAUSING COUPLING TO BECOME LOOSE. MFG SHOULD CHECK THE STRENGTH OF BRAZE AFTER WELDING. WHEN THIS COUPLING FAILS, LOST OF ROTOR TACH OCCURS. (K) 1G71 3U3 U H2SW E4CE 20060517002142006051700214SW 2006 5 17 2006FA0000492 120060302G29135001908 COUPLING BELL 206 206B 1181511SW HYD PUMP FAILED B XJ2RK NONE O OTHER ININSP/MAINT 1 WP01158H 00010463 2974 HYDRAULIC PUMP TACH DRIVE COUPLING BRAZE WELDING FAILED, CAUSING COUPLING TO SEPARATE FROM DRIVE GEAR SHAFT. MFG SHOULD CHECK THE STRENGTH OF BRAZE AFTER WELDING. WHEN THIS COUPLING FAILS, LOSS OF ROTOR TACH OCCURS. (K) 1G71 3U H2SW 20060519002502006051900250CE 2006 5 19 2006FA0000493 120060504G574050110231 FITTING CESSNA414 414 2075908CE CONT O520 TSIO520* 17040SO LT WING CRACKED B AIHRK NONE O OTHER ININSP/MAINT 1 GL11352TS3751 4140352 DURING ANNUAL INSP FOUND LT STUB WING AFT SPAR, UPPER FITTING CRACKED AT OB BOLT HOLE. FOUND NO CORROSION OR STRESS IN SURROUNDING AREAS. SUSPECT BOLT WAS OVERTORQUED. (K) 1L72 3O3 ORTA7CE E8CE 20060517002302006051700230CE 2006 5 17 2006FA0000494 120060426G7160 AIR BOX CESSNA172 172P 2072436CE LYC O360 O360A4M 41514EA ENGINE MAINT ERROR B BIIRK NONE R PARTIAL RPM/PWR LOSS CRCRUISE 1 EA21657641443 231 17275868 RL3482936A AC HAD 180 HP ENGINE INSTALLED ON 7/10/96. AC HAS 1443.5 HOURS SINCE INSTALLATION. OPERATOR NOTED 2300 RPM AT CRUISE, FULL THROTTLE. INSPECTED AND FOUND AIRBOX STILL HAD THE HOLE SIZE FOR 160 HP ENGINE. AIRBOX HAD NOT BEEN MODIFIED IAW STC. IT HAD BEEN REPAIRED ON SEVERAL OCCASIONS SINCE ENGINE INSTALLED AND HAD NOT BEEN FOUND. (K) 1H71 3O3 ONT3A12 E286 20060517002312006051700231EA 2006 5 17 2006FA0000495 220060509G8550CH481101 OIL FILTER PIPER PA28 PA28R201 7102816SO LYC O360 IO360C1C 41514EA ENGINE LEAKING B JULRK NONE K FLUID LOSS ININSP/MAINT 1 SW011663H 28R7737007 RL723851A PILOT REPORTED OIL SPOTS ON HANGAR FLOOR. ENGINE WAS WASHED AND GROUND RUN FOR LEAK CHECK. INSPECTED ENGINE AFTER ENGINE RUN AND FOUND OIL ON BOTTOM SIDE OF OIL FILTER. FURTHER INSPECTION OF THE OIL LEAK REVEALED THAT THE OIL WAS LEAKING FROM THE HEX NUT ON THE BACK OF THE FILTER. (K) 1L71 3O3 O 2A13 1E10 20060519002512006051900251EU 2006 5 19 2006FA0000496 120060505G6210355A11002011 BLADE SNIAS 350 AS350B 8680801EU TMECA ARRIELARRIEL1 60030NE MAIN ROTOR CRACKED D K NONE O OTHER ININSP/MAINT 1 SW095806H 1935 CRACK FOUND ON LOWER SURFACE OF MAIN ROTOR BLADE NEAR STATION 1000. EXACT CAUSE OF CRACK WOULD ONLY BE SPECULATIVE. (K) 1G71 3U3 U H9EU E19EU 20060518000692006051800069CE 2006 5 18 2006FA0000497 120060509G5310551124914S THRESHOLD CESSNA500 560CESSNA 2076750CE PWA JT15 JT15D5 52112NE CABIN DOOR FRAMECRACKED B JGVRK NONE O OTHER ININSP/MAINT 1 CE09318QS8377 5600418 CABIN ENTRY THRESHOLD CRACKED AT AFT STEP ATTACH BOLT HOLE. COMBINATION OF BOLT HOLE LOCATED IN RADIUS OF FRAME AND MATERIAL THICKNESS NOT SUFFICIENT TO SUPPORT WEIGHT OF PERSON ENTERING OR EXITING AIRCRAFT. RECOMEND STRENGTHING STRUCTURE, USING THICKER METAL. NOTE: HAVE FOUND THESE CRACKS ON MFG INSPECTION PHASE 5. APPROX 75 PERCENT OF AIRCRAFT INSPECTED ARE FOUND CRACKED. (K) 2L72 4F4 FRTA22CE E25EA 20060518000382006051800038SO 2006 5 18 2006FA0000498 220060511G8530AEC631397 CYLINDER CESSNA414 414 2075908CE CONT O520 TSIO520NB 17040SO ENGINE CRACKED D K NONE E VIBRATION/BUFFET DEDESCENT 1 GL13710US330 4140083 519719 DURING DECENT TO AIRPORT, PILOT REPORTED RT ENGINE STARTED HAVING EXCESSIVE VIBRATION. NO OTHER MAJOR ENGINE INDICATIONS WERE NOTED. AFTER LANDING, A MAGNETO CHECK WAS CONDUCTED AND NO DESCREPANCIES WERE FOUND. UPON REMOVAL OF COWLING, RT ENGINE NR 6 CYLINDER WAS FOUND TO HAVE CRACKED AROUND THE CIRCUMFERENCE OF CYLINDER HEAD AT THE NR 9 AND 10 COOLING FIN, COMPLETELY SEPARATING THE CYLINDER HEAD FROM THE BARREL AT THE VERY TOP OF STEEL CYLINDER BARREL. AFTER RESEARCHING AD, AMENDMENT, THE CYLINDER ASSY WAS FOUND NOT TO APPLY DUE TO S/N OF CYLINDER AND THE PRESENCE OF THE (A) STAMPED ON THE ROCKER BOX FLANGE. (K) 1L72 3O3 ORTA7CE E8CE 20060517002062006051700206SO 2006 5 17 2006FA0000499 220060411G8530641916A1 CYLINDER CESSNA172 172D 2072410CE CONT O300 O300D 17022SO ENGINE CRACKED C K NONE O OTHER ININSP/MAINT 1 NE032566Y 1432 17249866 27538 NR 1 CYLINDER WAS REMOVED DUE TO A CRACK .75 AROUND STEEL BARREL. IT APPEARS THAT AN OIL CONTROL RING BROKE AND EVENTUALLY DESTROYED THE PISTON AND JAMMED BETWEEN THE PISTON AND CYLINDER. TT ON THE ENGINE IS 4156.9 HRS. SMOH IS 1432.9 HRS, THE CYLINDER WAS LAST REMOVED AT 598.4 HOURS FOR HONE AND NEW RINGS. TT ON CYLINDERS, UNKNOWN. AIRCRAFT WAS ANNUALED 1.1 HRS PRIOR. THE OIL ANALYSIS PERFORMED AT ANNUAL WAS NORMAL AND ALL READINGS/RESULT WERE LOWER THAN THAT OF PREVIOUS AVIATION LABORATORY SAMPLES WHICH WERE ALSO NORMAL. ENGINE WILL BE TORN DOWN FOR INTERNAL INSPECTION. (K) 1H71 3O3 ONT3A12 E253 20060519002432006051900243SW 2006 5 19 2006FA0000500 120060428G5711271L SPAR BBAVIA7 7GCBC 1220601SW LYC O320 O320* 41508EA LT WING CRACKED D K NONE O OTHER ININSP/MAINT 1 GL1588237 74474 DURING WING RECOVER, FOUND LT WING FRONT SPAR WITH A CRACK ORIGINATING AT THE BUTT END, FOLLOWING THE WOOD GRAIN OB THROUGH UPPER ATTACH BRACKET HOLES AND EXTENDING APPROXIMATELY 1 INCH PAST IB MOST FUEL TANK SUPPORT BRACKET, UPPER HOLE. NO EVIDENCE OF CRACKS IN BUTT ENG SPAR DOUBLERS. TOTAL LENGTH OF CRACK APPROX 8.3750 INCHES. NO RECOMMENDATION FOR CAUSE OR RECURRENCE. (K) 1H71 3O3 ONCA759 E274 20060518001382006051800138NM 2006 5 18 2006FA0000501 120060516G7921900D3658501103 OIL COOLER DOUG MD900 MD900 3027375NM PWC PW207 PW207E NE ENG OIL SYS LEAKING D K NONE K FLUID LOSS ININSP/MAINT 1 EA11902PD589 9000084 FOUND WETTING OIL MAIN TRANSMISSION/ENGINE OIL COOLER CORE. REMOVED AND SENT OUT FOR EVALUATION. COOLER FOUND TO HAVE INTERNAL CORROSION THAT CAUSED MATERIAL LOSS AND SUBSEQUENT LEAKING. REPLACED COOLER WITH NEW. LEAK CHECK WAS SATISFACTORY. 1G72 3U3 UNCH19NM E42NE 20060518002662006051800266SO 2006 5 18 2006FA0000502 120060503G29101159SCH5019 SHUTOFF VALVE GULSTMGV GULFSTREAMGV3980116SO RROYCEBR700 BR700710A110 NE LT & RT WING MALFUNCTIONED D K NONE O OTHER ININSP/MAINT 1 SW05130GV2943 630 DURING A SCHEDULED INSPECTION, OPERATIONAL CHECK OF THE AILERON HARD OVER PROTECTION TEST. BOTH LT AND RT AILERON HYD SHUT OFF CIRCUIT BREAKERS POPPED. REPLACED RT AILERON , LT HYD SYSTEM SHUTOFF VALVE AND LT AILERON, LT HYD SYS SHUTOFF VALVE. (K) 2L72 4F4 FRTA12EA E00057EN 20060518002302006051800230NM 2006 5 18 2006FA0000503 120060516G632051003400 HOSE DOUG MD900 MD900 3027375NM PWC PW207 PW207E NE MAINTRANSMISSIONCRACKED D K NONE K FLUID LOSS ININSP/MAINT 1 EA11902PD489 9000084 DISCOVERED MAIN TRANSMISSION OIL HOSE FROM OIL COOLER TO MAIN TRANSMISSION LEAKING FROM STEEL BRAIDING. PULLED BACK BRAIDING AND FOUND HOSE TO BE CRACKED. REPLACED LINE WITH NEW. LEAK CHECK OF NEW LINE WAS SATISFACTORY, P/N 900D3409526-105. 1G72 3U3 UNCH19NM E42NE 20060518002562006051800256GL 2006 5 18 2006FA0000504 120060508G552410146008 RIVET CIRRUSSR SR22 2130001GL CONT O550 IO550N 17042SO ELEVATOR LOOSE D K NONE O OTHER ININSP/MAINT 1 WP155226R 1767 BOTH LT AND RT ELEVATOR OB HINGE BRACKETS ARE RIVETED TO THE ELEVATORS WITH FLUSH HEAD BLIND RIVETS AND FLUSH HEAD SOLID DRIVE RIVETS. AT 121 HOURS TT. DURING A 100 HOUR INSPECTION, THE RIVETS ON THE OB HINGE BRACKETS, LT AND RT ELEVATORS, WERE FOUND TO BE SMOKING- STREAKS OF BLACK POWDER TRAILING BEHIND THEM, AND THE PAINT AROUND THE RIVET HEADS BROKEN. RECOMMEND MFG DESIGN FIND A SECURE WAY TO HOLD THE ELEVATOR HINGE BRACKETS TO THE ELEVATORS SUCH AS THROUGH USE OF SOLID-DRIVEN RIVETS INSTEAD OF BLIND RIVETS. (K) 1L71 3O3 ONTA00009CHE3SO 20060518001962006051800196NM 2006 5 18 2006FA0000506 120060516G632051003400 HOSE DOUG MD900 MD900 3027375NM PWC PW207 PW207E NE MAIN TRANSMSN CRACKED D K NONE K FLUID LOSS ININSP/MAINT 1 EA11902PD489 9000084 DISCOVERED MAIN TRANSMISSION OIL HOSE FROM OIL COOLER TO MAIN TRANSMISSION LEAKING FROM STEEL BRAIDING. PULLED BACK BRAIDING AND FOUND HOSE TO BE CRACKED. REPLACED LINE WITH NEW. LEAK CHECK OF NEW LINE WAS SATISFACTORY. P/N 900D3409526-105. 1G72 3U3 UNCH19NM E42NE 20060518000572006051800057NM 2006 5 18 2006FA0000507 120060516G6220900R1103001113 BEAM DOUG MD900 MD900 3027375NM PWC PW207 PW207E NE MR HUB CRACKED D K NONE O OTHER ININSP/MAINT 1 EA11902PD1898 100 9000084 DURING SCHEDULED INSPECTION FOUND FLEXBEAM CRACKED IN LEG OF FLEXBEAM. REJECTED FLEXBEAM IAW INSPECTION CRITERIA IN MAINTENANCE MANUAL. REPLACED WITH NEW FLEXBEAM. 1G72 3U3 UNCH19NM E42NE 20060518002462006051800246NM 2006 5 18 2006FA0000508 120060516G6220900R1103001113 BEAM DOUG MD900 MD900 3027375NM PWC PW207 PW207E NE MR HUB CRACKED D K NONE O OTHER ININSP/MAINT 1 EA11902PD1898 100 9000084 DURING SCHEDULED INSPECTION FOUND FLEXBEAM CRACKED IN LEG OF FLEXBEAM. REJECTED FLEXBEAM IAW INSPECTION CRITERIA IN MM. REPLACED WITH NEW FLEXBEAM. 1G72 3U3 UNCH19NM E42NE 20060530001752006053000175SW 2006 5 30 2006FA0000509 120060513G6720500N72205 CABLE HUGHES500N 500N 3027374SW TAILBOOM SEVERED B K NONE O OTHER ININSP/MAINT 1 WP05520HB LN029 DURING PRACTICE AUTOROTATIONS, PILOT FELT A CHANGE IN THE ANTI-TORQUE PEDALS. AFTER TOUCHDOWN HE ATTEMPTED TO RAISE THE COLLECTIVE AND THE HELICOPTER BEGIN TO SPIN, HE LOWERED THE COLLECTIVE AND SHUTDOWN. NO DAMAGE WAS NOTED. THE ROTATING CONE CONTROL CABLE WAS FOUND TO HAVE A CLEAN BREAK. THE OTHER CABLES WERE INSPECTED AND FOUND TO BE OK. P/N 500N7220-05 WAS INSPECTED AT THE LAST 300HR INSPECTION 232.8 HOURS AGO, AND WAS FOUND TO BE AIRWORTHY. THIS PART DOES NOT HAVE A SERVICE LIFE LIMIT FROM THE MFGR. RECOMMEND A SERVICE LIFE OF 1000 HOURS. 1G71 3U NCH3WE 20060522001722006052200172SO 2006 5 22 2006FA0000510 120060421G3220402940 BOLT PIPER PA44 PA44180 7104402SO NOSE GEAR BROKEN B NI1RK NONE O OTHER LDLANDING 1 CE03554PC 4496073 NOSE GEAR COLLAPSED ON TOUCHDOWN. MAINS TOUCHED FIRST THEN NOSE. 2 COMPONENTS THAT ARE DAMAGED IN NOSE GEAR RETRACT/EXTEND SYS. W/O DISASSEMBLING LINKAGE, VISUAL EVIDENCE, BOLT CONNECTING UPPER DRAG LINK TO LWR DRAG LINK FAILED DUE TO POSSIBLE OVERLOAD CONDITION. (FRACTURED END OF BOLT IS BRIGHT AND SHINNY, INDICATING AN INSTANTANEOUS FAILURE). ONE HALF OF THAT BOLT, WASHER, NUT AND COTTER PIN IS STILL INSERTED IN JOINT. OTHER DAMAGED COMPONENT IS BOLT THAT DOWNLOCK HOOK ENGAGES, BOLT IS BENT IN SUCH A WAY AS TO INDICATE IT WAS DAMAGED AS A RESULT OF NOSE GEAR COLLAPSE. AFTER UPPER AND LWR DRAG LINK ASSEMBLIES HAVE BEEN REMOVED SENT TO MFG FOR FURTHER INSP AND ANALYSIS. 1L72 3O A19S0 20060522001422006052200142CE 2006 5 22 2006FA0000511 120060504G79209696001123 LINE BEECH 58 58 1152740CE CONT O550 IO550C SO ENGINE CHAFED D E ENGINE SHUTDOWN JK WARNING INDICATION FLUID LOSS CRCRUISE 1 EA13251P TH2139 686637 2 LINES CHAFFING TOGETHER. NEED TO SEPARATE THE LINES. LOW OIL PSI IN FLIGHT. PILOT SHUTOFF ENGINE IN FLIGHT AND LANDED THE AIRCRAFT. REMOVED AND REPLACED THE LINE. (K) 1L72 3O3 O 3A16 E3SO 20060522001442006052200144 2006 5 22 2006FA0000512 420060421G342570000006000 FLIGHT DIR CIRRUSSR SR22 2130001GL COCKPIT FAILED D OBKRK NONE O OTHER ININSP/MAINT 1 GL13629LF 0843 PFD WAS JUST UPDATED TO REV 6. 2 DAYS AFTERWARDS, SCREEN WOULD FAIL IN FLIGHT. DISPLAY WOULD FLICKER AND NOT BE USABLE. UNIT WOULD ALSO FAIL TO BOOT UP IN HANGAR. CUSTOMER WAS GIVEN EXCHANGE. (K) 1L71 3O NTA00009CH 20060522001702006052200170 2006 5 22 2006FA0000513 420060404G342570000006000 FLIGHT DIR CIRRUSSR SR22 2130001GL COCKPIT FAILED D OBKRK NONE O OTHER CRCRUISE 1 GL13623KT 0486 THIS PARTICULAR PFD HAD 3 BACK TO BACK FAILURES THAT COULD ONLY BE DETECTED AFTER 1 HOUR + OF FLIGHT. DISPLAY WOULD LIGHTEN UP, TURN GREEN AND FLICKER. WOULD NOT BE USABLE. THIS UNIT WAS UPGRADED TO REV 6 SOFTWARE FOR FLIGHT DIRECTOR. FAILURES HAPPENED AFTER THIS MOD. FAILURES HAPPENED AFTER THIS MOD UNIT WAS SENT TO MFG AFTER FIRST 2 FAILURES, THIRD FAILURE RESULTED IN AN EXCHANGE. (1ST-3-6-06-W/O AVO6-6617) (2ND - 3-29-06, W/O AVO6-6658) (3RD-4-4-06 W/O AVO6-6687) 1L71 3O NTA00009CH 20060522001502006052200150SO 2006 5 22 2006FA0000514 220060420G8530 CYLINDER CESSNA210 T210N 2073456CE CONT O520 IO520L 17032SO ENGINE ERODED D E ENGINE SHUTDOWN E VIBRATION/BUFFET CRCRUISE 1 CE015337Y 517945 21064171 517945 FOUND NR 6 PISTON ERODED FROM POSSIBLE DETONATION BY UNKNOWN CAUSES. FOUND NR5 CYLINDER CONNECTING ROD CAP MISSING AND INTERNAL DAMAGE TO THE CRANKCASE. NO OIL WAS NOTED ON THE DIPSTICK PRESUMED TO BE FORCED OUT OF THE ENGINE DUE TO EXCESSIVE BLOW BY FROM THE ERODED NR 5 CYL. THE ENGINE WAS SHUT DOWN AND LANDED IN A GRASS FIELD WITH NO DAMAGE TO THE AIRCRAFT. (K) 1H71 3O3 O 3A21 E5CE 20060522001732006052200173 2006 5 22 2006FA0000515 420060505G2562 ELT CESSNA210 2105 2073404CE FUSELAGE FAILED D K NONE O OTHER ININSP/MAINT 1 GL098197Z 2050197 ELT FAILED UPON INSPECTION AFTER 12 MONTHS OF SERVICE, DID NOT TRANSMIT THROUGH ANTENNA, LIGHT WENT ON INDICATING FUNCTION. THIS IS THE 3RD FAILURE ON UNITS NEWER THAN ONE YEAR OLD, IN 1.5 YEARS IN OUR SHOP. (K) 1H71 3O 3A21 20060522001542006052200154 2006 5 22 2006FA0000516 420060306G2562AK450 ELT HUGHES269 269A 4470402WP LYC O360 IO360A1A 41514EA FUSELAGE FAILED D K NONE O OTHER ININSP/MAINT 1 GL0962273 291096 ELT FAILED UPON INSPECTION AFTER EIGHT MONTHS OF SERVICE, DID NOT TRANSMIT THOUGH ANTENNA, LIGHT WENT ON INDICATING FUNCTION. THIS IS THE SECOND TIME THIS HAS FAILED THIS YEAR. (K) 1G71 3O3 O 4H12 1E10 20060522001662006052200166 2006 5 22 2006FA0000517 420060306G2562AK450 ELT HUGHES269 269A 4470402WP FUSELAGE FAILED D K NONE O OTHER ININSP/MAINT 1 GL0962273 291096 ELT FAILED UPON INSPECTION AFTER NINE MONTHS OF SERVICE. DID NOT SWEEP. (K) 1G71 3O 4H12 20060522001712006052200171GL 2006 5 22 2006FA0000518 120060505G8011 SOLENOID CIRRUSSR SR22 2130001GL CONT O550 IO550N 17042SO STARTER INTERMITTENT B LC1RK NONE O OTHER ININSP/MAINT 1 EA07343CD399 1343 917602 THE STARTER ON THIS AIRCRAFT FAILED. THIS IS THE THIRD FAILURE OF THIS TYPE STARTER HAS A SOLENOID ATTACHED AND THE PROBLEM NOTED IS THAT THIS SOLENOID BECOMES INTERMITTENT. (K) 1L71 3O3 ONTA00009CHE3SO 20060522001472006052200147CE 2006 5 22 2006FA0000519 120060331G3233508202085 ACTUATOR BEECH 200 200BEECH 1152920CE NOSE GEAR UNSERVICEABLE D O OTHER J WARNING INDICATION LDLANDING 1 GL11641TS BB641 AIRCRAFT NOSE WHEEL FAILED TO EXTEND WHEN GEAR SELECTOR WAS PLACED IN DOWN POSITION. NOSE GEAR WAS OBSERVED BY TOWER PERSONNEL TO BE PARTIALLY EXTENDED BUT NOT LOCKED DOWN. PILOT ATTEMPTED EMERGENCY EXTENSION WITHOUT SUCCESS. AIRCRAFT LANDED ON MAIN GEAR AND SLOWED AS MUCH AS POSSIBLE BEFORE LOWERING NOSE TO GROUND. AIRCRAFT SUSTAINED VERY LITTLE DAMAGE UPON LANDING. ENGINES WERE SHUT DOWN AND PROPELLERS FEATHERED PRIOR TO LOWERING NOSE. DAMAGE WAS CONTAINED TO RAYDOME, PITOT TUBES, NOSE GEAR DOORS AND PROPELLERS. AIRCRAFT WAS FURTHER DAMAGED DURING RECOVERY PHASE WHEN HOISTING STRAP BROKE AND AIRCRAFT FELL BACK TO GROUND APPROX 4 FEET CAUSING STRUCTURE DAMAGE TO AFT FUSELAGE BEHIND PRESSURE BULKHEAD. 1L72 4T A24CE 20060523002312006052300231EA 2006 5 23 2006FA0000521 220060518G8520LW13820 CRANKCASE LYC O360A4M CESSNA172 172N 2072434CE LYC O360 O360A4M 41514EA ENGINE CRACKED D K NONE K FLUID LOSS ININSP/MAINT 1 EA071962F4956 1460 L1726436A 17273052 L1726436A DURING A 100 HR INSPECTION, AN OIL LEAK WAS NOTED AROUND THE L/H FORWARD CRANKCASE AROUND THE UPPER CRANKCASE BOLT (PN 6-34A WITH PN LW-11866 NUT). THE ENGINE WAS CLEANED AND A DYE PENETRANT INSPECTION PERFORMED. A CRACK ROUGHLY 4 INCHES LONG WAS FOUND RUNNING VERTICALLY ON THE CRANKCASE FROM ABOUT 1 INCH BELOW THE CRANKCASE SEAM DOWN TO THE EDGE OF THE BEARING SURFACE OF THE BOLT HOLE, THEN DOWN ANOTHER 3 INCHES. THE ENGINE IS BEING REMOVED FOR REPAIR OF CRANKCASE (IF POSSIBLE) OR REPLACEMENT. 1H71 3O3 ONT3A12 E286 20060522002002006052200200CE 2006 5 22 2006FA0000522 120060522G2424UAM100 CURRENT LIMITER RAYTHN RAYTHNDH125 HAWKER800XP 7150012CE GARRTTTPE331TPE331* 01514WP ELECT PANEL MISDRILLED B K NONE O OTHER NRNOT REPORTED 1 SW11875QS 258375 MOUNTING HOLES IN CURRENT LIMITER DOES NOT MATCH LUGS IN ELECTRICAL PANEL. 2L72 4F3 TRTA3EU E2WE 20060523002322006052300232CE 2006 5 23 2006FA0000523 120060520G5500550 SKIN CESSNA CESSNA500 550 2076604CE EMPENNAGE CORRODED B K NONE O OTHER ININSP/MAINT 1 SW171255K 0505 5500505 AFTER A PHASE 1,2,3,4,49&59 CORROSION AND DELAMINATION WAS FOUND ON TOP AND BOTTOM SKINS LT AND RT SIDES OF THE HORIZONTAL STABILIZER, LT SKIN OF THE VERTICAL STABILIZER. TAIL SKINS 5512010-9 AND 6512010-20 (SKINS UNDER VERT. STAB.) AS WELL AS THE AFT BULKHEAD 6412016-1SP WERE REPLACED. 1L72 4F A22CE 20060523002332006052300233CE 2006 5 23 2006FA0000524 120060521G37101U478003 PUMP CONT BEECH 33 F33A 1151425CE ENGINE BROKEN D O OTHER IG FLT. ATTITUDE INST. MULTIPLE FAILURE CRCRUISE 1 GL1911BX 219 CE388 VACUUM PUMP FAILURE INFLIGHT - FIRST NOTICED ATTITUDE CHANGE (STARTED DECENDING RAPIDLY) (AUTOPILOT ENGAGED) 1L71 3O 3A15 20060523002352006052300235CE 2006 5 23 2006FA0000525 120060520G55205534000204 ELEVATOR CESSNA CESSNA500 550 2076604CE RT ELEVATOR MAINT ERROR B L ABORTED APPROACH O OTHER ININSP/MAINT 1 SW171255K9471 0505 AFTER A REPAIR AT ANOTHER FACILITY THIS ELEVATOR WAS IN A BIND AND NOT ABLE TO STREAMILINE WITH THE STABILIZER (COULD NOT RIG). IT APPEARS THAT THIS CONTROL WAS NOT INSTALLED CORRECTLY IN A JIG FIXTURE. WHILE REPLACING THE UPPER AND LOWER SKINS IT WAS ALSO FOUND THAT THE FWD. SPAR WAS DAMAGED BY ALLOWING DRILL BITS TO GO THROUGH AND IMPACT ON THE SPAR. THIS CAUSED THE FWD. SPAR TO ALSO BE REPLACED. 1L72 4F A22CE 20060523002362006052300236CE 2006 5 23 2006FA0000526 120060520G5751 AILERON CESSNA CESSNA500 550 2076604CE RT AILERON CRACKED B K NONE O OTHER ININSP/MAINT 1 SW1743SA 9863 0086 DURING A PHASE 1,2,3,4 INSPECTION THE RT AILERON WAS FOUND TO BE CRACKED AT THE LEADING EDGE IN THE AREA OF ATTACHMENT POINTS FOR THE WEIGHTS. THE SKIN WAS REMOVED AND REPLACED. HAD SEVERAL CRACKED AILERONS IN OUR OTHER AIRCRAFT BOTH LT AND RT CRACK IN THIS AREA. WE OPERATE A FLEET OF THESE AIRCRAFT AND LOOK AT THIS ON A 300HR. INSPECTION SCH. THE CRACKS GO AROUND THE SCREW HOLES OR RADIATE OUT FROM THEM. 1L72 4F A22CE 20060523002372006052300237CE 2006 5 23 2006FA0000527 120060521G37101U478003 PUMP CONT BEECH 33 F33A 1151425CE CONT O520 IO520B 17032SO ENGINE FAILED D O OTHER IG FLT. ATTITUDE INST. MULTIPLE FAILURE CRCRUISE 1 GL1911BX 219 CE388 VACUUM PUMP FAILURE INFLIGHT, FIRST NOTICED ATTITUDE CHANGE (STARTED DECENDING RAPIDLY) (AUTOPILOT ENGAGED). 1L71 3O3 O 3A15 E5CE 20060530001582006053000158SW 2006 5 30 2006FA0000528 120060518G5302 FITTING BELL BELL 204 UH1H 1181407SW TAIL BOOM CRACKED H K NONE J WARNING INDICATION ININSP/MAINT 1 SO15 4000 TAIL BOOM ATTACH FITTING CRACKED UPPER LEFT [TAIL BOOM SIDE] 1G71 4U EXPA1G71 20060530001592006053000159SW 2006 5 30 2006FA0000529 120060518G5302 FITTING BELL BELL 204 UH1H 1181407SW TAIL BOOM CRACKED H K NONE O OTHER ININSP/MAINT 1 SO15 4000 TAIL BOOM ATTACH FITTING CRACKED UPPER LEFT [TAIL BOOM SIDE] 1G71 4U EXPA1G71 20060530001602006053000160SW 2006 5 30 2006FA0000530 120060518G5302 FITTING BELL BELL 204 UH1H 1181407SW TAIL BOOM CRACKED H K NONE O OTHER ININSP/MAINT 1 SO15 4000 TAIL BOOM ATTACH FITTING CRACKED UPPER LEFT [TAIL BOOM SIDE] 1G71 4U EXPA1G71 20060530001612006053000161CE 2006 5 30 2006FA0000531 120060521G2424UAM100 CURRENT LIMITER RAYTHNDH125 HAWKER800XP 7150012CE ELECT REG SYS FAILED B A UNSCHED LANDING H ELECT. POWER LOSS-50 PC TOTAKEOFF 1 SW11203TM 258653 CURRENT LIMITER BLOWN, CAUSING LOSS OF ELECTRICAL POWER 2L72 4F RTA3EU 20060530001622006053000162SO 2006 5 30 2006FA0000532 120060521G2436UAM100 CURRENT LIMITER PIPER PA18 PA18 7101802SO ELECT REG SYS FAILED B K NONE H ELECT. POWER LOSS-50 PC TOTAKEOFF 1 SW11203T 182317 CURRENT LIMITER BLOWN, CAUSING LOSS OF ELECTRICAL POWER. 1H71 3O 1A2 20060530001642006053000164GL 2006 5 30 2006FA0000533 120060518G7810DC00015B EXHAUST RISER DIAMONDA20 DA20C1 2990001GL CONT O240 IO240B 17063SO ENGINE CRACKED D K NONE O OTHER ININSP/MAINT 1 SW19107TX52 C0310 ON A 100HR INSP NR 2 EX RISER CRACKED AT FLANGE. THIS HAS BEEN FOUND ON A NUMBER OF AIRCRAFT OF THIS TYPE. 1L71 3O3 ONTTA4CH E7SO 20060522002412006052200241GL 2006 5 22 2006FA0000534 120060518G7810DC00015B EXHAUST RISER DIAMONDA20 DA20C1 2990001GL CONT O240 IO240B 17063SO ENGINE CRACKED D K NONE O OTHER ININSP/MAINT 1 SW19107TX52 C0310 ON A 100HR INSP #2 EX RISER CRACKED AT FLANGE. THIS HAS BEEN FOUND ON A NUMBER OF AIRCRAFT OF THIS TYPE. 1L71 3O3 ONTTA4CH E7SO 20060530001652006053000165GL 2006 5 30 2006FA0000535 120060518G7810DC00015B EXHAUST RISER DIAMONDA20 DA20C1 2990001GL CONT O240 IO240B 17063SO ENGINE CRACKED D K NONE O OTHER ININSP/MAINT 1 SW19107TX52 C0310 ON A 100HR INSP NR 2 EX RISER CRACKED AT FLANGE. THIS HAS BEEN FOUND ON A NUMBER OF AIRCRAFT OF THIS TYPE. 1L71 3O3 ONTTA4CH E7SO 20060530001662006053000166GL 2006 5 30 2006FA0000536 120060518G7810DC00015B EXHAUST RISER DIAMONDA20 DA20C1 2990001GL CONT O240 IO240B 17063SO ENGINE CRACKED D K NONE O OTHER ININSP/MAINT 1 SW19107TX52 C0310 ON A 100HR INSP NR 2 EXHAUST RISER CRACKED AT FLANGE. THIS HAS BEEN FOUND ON A NUMBER OF AIRCRAFT OF THIS TYPE. 1L71 3O3 ONTTA4CH E7SO 20060530001732006053000173CE 2006 5 30 2006FA0000537 120060520G5220 CHANNEL CESSNA500 550 2076604CE ESC DOOR FRAME DAMAGED B K NONE O OTHER ININSP/MAINT 1 SW1743SA 0086 THE STRIKER PLATE HAD COME LOSE AT THE TOP LATCH POINT FOR THE ESCAPE HATCH ALLOWING THE LOCK PIN TO ELONGATE OUT THE HOLE. THIS REQUIRED THE REPLACEMENT OF 5511162-12 CHANNEL AND 5511162-48 ZEE CHANNEL. 1L72 4F A22CE 20060524002162006052400216SO 2006 5 24 2006FA0000538 220060510G8520 CAMSHAFT BEECH 58 58 1152740CE CONT O520 IO520CB 17032SO HARTZLHCJ2Y BHCJ2YF2C GL ENGINE WORN D K NONE O OTHER ININSP/MAINT 1 SW13866SH TH1083 298751R DZ699 COMPRESSION CHECKED ENGINE, NR 2 CYLINDER 40/80. REMOVED NR 2 CYL FOR REPAIR. INSP INSIDE OF ENG, FOUND NR 1 CYL EXHAUST LIFTER/CAM LOBE BADLY WORN. UNKNOWN HOW LONG IT HAS BEEN LIKE THIS, KNOW IT WOULD NOT HAVE LASTED TOO MUCH LONGER. REBUILT/ZERO TIMED. AIRPLANE SHOWN TO HAVE FLOWN AS LITTLE AS 5 HRS IN 9 MONTHS. SUSPECT TOO LONG PERIOD BETWEEN ENGINE RUNS, LOSING OIL FILM ON LIFTER/LOBE CONTACT, MAYBE LITTLE CORROSION, CAUSING METAL /METAL WEAR AND (GALLING) BEARING SURFACES. HAVE BEEN PULLING WAY TOO MANY CYLINDERS LATELY DUE TO LONG PERIODS OF STORAGE OF AIRCRAFT THAT WERE NOT PRESERVED FOR STORAGE. (K) 1L72 3O3 O 3A16 E5CE 5 CP37EA 20060524002172006052400217 2006 5 24 2006FA0000539 420060507G83007650004503074 BREATHER TUBE SKRSKYS76 S76B 8143007NE PWA PT6 PT6B36 52043EA ACCY GEARBOX DETERIORATED D O OTHER BJ SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION CRCRUISE 1 GL09176BA 760317 ENROUTE TO A PICK UP A PATIENT. WITHIN 4 MINUTES OF TAKEOFF, MEDICAL CREW REPORTED, SMELLED SMOKE IN CABIN, BECOMING VISIBLE ALSO. PILOT NOTICED IT ABOUT SAME TIME. PILOT RETURNED WITHOUT DELAY, APPROX 30 SECONDS BEFORE TOUCHDOWN, BAGGAGE COMPARTMENT SMOKE DETECTOR WENT OFF. AC LANDED WITHOUT INCIDENT. INVESTIGATION SHOWED NR 2 ENG ACCY GEARBOX VENT TUBE HAD BROKEN FREE OF ENG DECK FITTING. THIS OVERBOARD BREATHER TUBE MADE OF A VINYL MATERIAL, HAD DETERIORATED TO POINT OF BREAKING OFF OF FITTING ON BOTTOM OF ENG DECK. TUBE RUNS THROUGH AFT CORNER OF BAGGAGE COMPT, WHEN TUBE BROKE, FILLED COMPT WITH OIL MIST/VAPOR THAT ILLUMINATED SMOKE DETECTOR. VINYL TUBE WAS REPLACED, AC RETURNED TO SERVICE. (K) 1G72 4U4 U H1NE E4EA 20060612002672006061200267NE 2006 6 12 2006FA0000540 120060508G26127630607902103 FIRE DETECTOR SKRSKYS76 S76B 8143007NE NR 1 ENGINE FALSE ACTIVATIOND O OTHER N FALSE WARNING CRCRUISE 1 GL09176BA 760317 ENROUTE, WHEN NR 1 ENG FIRE WARNING SYS WAS ACTIVATED. PILOT REPORTED WARNING LIGHTS, HORN AND T-HANDLES ILLUMINATED WITH FIRE WARNING INDICATION. WARNING STAYED ON FOR 30 SECONDS, WENT OUT. AFTER SHORT PERIORD OF TIME, WARNING CAME BACK. PILOT DECLARED EMERGENCY WITH GRR CONTROLLERS. WARNING WENT OUT AND CAME BACK ON 2 ADDITIONAL TIMES. ENG PWR WAS REDUCED TO IDLE,THEN WAS SECURED USING FIRE T-HANDLE. WHEN AC WAS IN SIGHT, IT WAS REPORTED, NO VISIBLE SMOKE TRAILING AC. PILOT CONTINUED, MADE EMERGENCY LANDING W/O INCIDENT. ENG WAS OPENED AND INSPECTED FOR ANY VISIBLE SIGNS OF DAMAGE. NO FIRE INDICATIONS. TROUBLESHOOTING RESULTED FROM DEFECTIVE FIRE WARNING SENSOR, REPLACED. AC RETURNED TO SERVICE. 1G72 4U H1NE 20060530001742006053000174SO 2006 5 30 2006FA0000541 120060523G32216705403 TRUNNION PIPER PA44 PA44180 7104402SO NLG CRACKED C K NONE O OTHER ININSP/MAINT 1 NM038184U 448095023 NOSE LANDING GEAR TRUNNION CRACKED AT UPPER ATTACH POINTS AND LOWER DRAG LINK ATTACH POINT. 1L72 3O A19S0 20060530001152006053000115 2006 5 30 2006FA0000542 420060515G2562AK450 ELT CESSNA172 172L 2072432CE LYC O320 O320E2D 41508EA FUSELAGE DEFECTIVE D K NONE L NO TEST ININSP/MAINT 1 SO149894G 17259794 BRAND NEW ELT UNIT AMERIKING AK-450 WAS INSTALLED ON THE AIRCRAFT 8/04. UNIT WORKED AFTER INSTALLATION WITH REMOTE PANEL, G-SWITCH AND TOGGLE SWITCH LOCATED ON THE UNIT AND AT SUBSEQUENT ANNUAL INSPECTION. AIRCRAFT HAS FLOWN APPROXIMATELY 25 HOURS SINCE INSTALLATION. ELT UNIT WAS FOUND DEFECTIVE DURING A ROUTINE INSPECTION ON 5/15/06. THE SIX D BATTERIES WERE FOUND TO BE AT FULL CHARGE, NO SIGNS OF CORROSION. UNIT SENT BACK TO AMERIKING IN CA. FOR WARRANTY REPAIR. 1H71 3O3 ONT3A12 E274 20060614002082006061400208 2006 6 14 2006FA0000543 420060515G2562AK450 ELT CESSNA172 172L 2072432CE LYC O320 O320E2D 41508EA FUSELAGE DEFECTIVE D K NONE O OTHER ININSP/MAINT 1 SO149894G 17259794 BRAND NEW ELT UNIT WAS INSTALLED ON THE AIRCRAFT 8/04. UNIT WORKED AFTER INSTALLATION WITH REMOTE PANEL, G-SWITCH AND TOGGLE SWITCH LOCATED ON THE UNIT AND AT SUBSEQUENT ANNUAL INSPECTION. AIRCRAFT HAS FLOWN APPROXIMATELY 25 HOURS SINCE INSTALLATION. ELT UNIT WAS FOUND DEFECTIVE DURING A ROUTINE INSPECTION ON 5/15/06. THE 6 (D) BATTERIES WERE FOUND TO BE AT FULL CHARGE, NO SIGNS OF CORROSION. UNIT SENT BACK TO MFG FOR WARRANTY REPAIR. 1H71 3O3 ONT3A12 E274 20060614002102006061400210GL 2006 6 14 2006FA0000544 220060526G8510 DRIVE GEAR AMTR AVDFLYAVIDFLYER GL AMTR 430 CUYUNA430 19050GL ENGINE DAMAGED G A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CLCLIMB 1 NM05157VM75 0157 ACCIDENT INVESTIGATION. ON CLIMB-OUT ENGINE RPM INCREASED AND PROPELLER RPM DECREASED. THE GRD-2000 GEAR REDUCTION UNIT WAS DISASSEMBLED AND THE DRIVE GEAR WAS FOUND TO DAMAGED. (TEETH GONE) 1H71 3O3 I EXPA1H71EXPE3I 20060613001982006061300198EU 2006 6 13 2006FA0000545 120060511G2720 RUDDER PEDAL GROB 103TWNG103ATWINII 1660206EU COCKPIT CRACKED D K NONE O OTHER ININSP/MAINT 1 EA014446T 3824 SIGNIFICANT CORROSION NOTED AT HORIZONTAL BASE OF LEFT RUDDER PEDAL. RUDDER PEDAL CRACKED AND STARTED TO DEFORM SLIGHTLY IN THE VICINITY OF THE CRACK. THE RUDDER PEDAL IS PLATED AND THE CORROSION APPEARED TO HAVE STARTED FROM THE INSIDE BUT THE EXACT CAUSE HAS YET TO BE DETERMINED. THESE PEDALS SHOULD BE EXAMINED AT LEAST EVERY YEAR DURING THE ANNUAL INSPECTION WITH A MIRROR AND LIGHT. 1K00 3O 0 G39EU 20060613002292006061300229GL 2006 6 13 2006FA0000546 120060526G2434657046 BRACKET CIRRUSSR SR20 05628AJGL CONT O360 IO360CONT 17025SO ENGINE CRACKED D K NONE O OTHER UKUNKNOWN 1 SO06145CD446 1020 ALTERNATOR BRACKET FOUND CRACKED. NEW PART IS OF A HEAVIER DESIGN BUT RETAINS THE SAME PART NUMBER. 1L71 3O3 ONTA00009CHE1CE 20060609002672006060900267SW 2006 6 9 2006FA0000547 120060602G781040B19822 EXHAUST RISER MOONEYM20 M20M 5870222SW LYC 0540 TIO540AF1B 41532EA ENGINE CRACKED C K NONE O OTHER NRNOT REPORTED 1 NM03223KT631 270067 CUSTOMER SENT IN THE EXHAUST SYSTEM BECAUSE OF CRACKS FOUND IN THE WELDS OF THE RISER LEGS TO THE STACK TUBES OF THE NR 1 AND NR 2 SECTIONS. ADVISED CUSTOMER TO REPLACE COMPONENTS. CUSTOMER BOUGHT NEW PARTS AND BROUGHT THEM IN TO HAVE ATTACHING PIECES INSTALLED TO CHECK ALIGNMENT. THE CUSTOMERS REQUIREMENTS THAT THEY FIT UNIFORMLY. GENERAL COMMENTS REGARDING THESE PARTS: THE WORKMANSHIP OF THE NEW PIECES WAS GENERALLY POOR IN MY OPINION, NOT REPRESENTATIVE OF THE TYPE OR QUALITY THAT SHOULD BE EXPECTED FROM A MAJOR AIRCRAFT ENGINE MANUFACTURER. IF IMPROVEMENTS ARE NOT MADE TO THE COMPONENTS ON THIS ENGINE/AIRCRAFT MODEL, SIGNIFICANT SAFETY PROBLEMS SHOULD BE EXPECTED. 1L71 3O3 ORT2A3 E14EA 20060612002332006061200233 2006 6 12 2006FA0000548 420060517G611305522311 BULKHEAD CESSNA172 172N 2072434CE LYC O320 O320* 41508EA SPINNER CRACKED B WIWRK NONE O OTHER ININSP/MAINT 1 WP07123GJ1100 17270706 DURING AN ANNUAL INSPECTION FO THE PROPELLER IT WAS NOTICED THAT THERE WERE CRACKS AROUND 3 OF THE BOLT HOLWS OD THE FORWARD SPINNER BULKHEAD. THE PROBABLE CAUSE IS THAT THE BULKHEAD IS BEING STRESSED AND BENT AS IT IS BEING TIGHTENED AGAINST THE PROPELLER HUB. IT IS SUGGESTED THAT THE SPINNER BULKHEAD BE MADE OF A THICKER MATERIAL. (K) 1H71 3O3 ONT3A12 E274 20060612002652006061200265CE 2006 6 12 2006FA0000549 120060516G27100510105365 CABLE CESSNA172 172S 2072439CE LYC IO360 IO360L2A EA RT AILERONS FRAYED B WIWRK NONE O OTHER ININSP/MAINT 1 WP07141CW2657 172S9389 DURING A 100 HOURS INSPECTION THE RT AILERON CROSSOVER CABLE WAS FOUND TO BE FRAYED AT THE PHANALIC BLOCK. PROBABLE CAUSE IS FRICTION BETWEEN THE CABLE AND THE WARE BLOCK. TO PREVENT RECURRENCE REMOVE PHANALIC BLOCK AND INCREASE TENSION ON CABLES. (K) 1H71 3O3 ONT3A12 1E10 20060609002492006060900249 2006 6 9 2006FA0000550 420060511G611305522311 BULKHEAD CESSNA172 172S 2072439CE LYC O360 IO360A1A 41514EA MCAULY1A170 1A170E GL SPINNER CRACKED B WIWRK NONE O OTHER ININSP/MAINT 1 WP07533BM 172S8340 DURING 100 HRS INSPECTION, FOUND FORWARD SPINNER BULKHEAD CRACKED IN 2 PLACES AROUND PROPELLER BOLT HOLES. RECOMMENDATION: DIMPLING OF BOLT HOLES. (K) 1H71 3O3 ONT3A12 1E10 5 NP857 20060612001572006061200157 2006 6 12 2006FA0000551 420060517G611305522311 BULKHEAD CESSNA172 172N 2072434CE LYC O320 O320* 41508EA MCAULY1C160 1C160DTM GL SPINNER CRACKED B WIWRK NONE O OTHER ININSP/MAINT 1 WP07123GJ 17270706 DURING AN ANNUAL INSPECTION OF THE PROPELLER IT WAS NOTICED THAT THERE WERE CRACKS AROUND 3 OF THE BOLT HOLES OF THE FORWARD SPINNER BULKHEAD. THE PROBLEM CAUSE IS THAT THE BULKHEAD IS BEING STRESSED AND BENT AS IT IS BEING TIGHTENED AGAINST THE PROPELLER HUB. IT IS SUGGESTED THAT THE SPINNER BULKHEAD BE MADE OF A THICKER MATERIAL. (K) 1H71 3O3 ONT3A12 E274 5 NP910 20060606002422006060600242SW 2006 6 6 2006FA0000552 120060513G6720500N72205 CABLE HUGHES500N 500N 3027374SW ROTAT CONE CNTRLBROKEN B H2BRR AUTOROTATION F FLT CONT AFFECTED DEDESCENT 1 WP05520HB LN029 PILOT WAS PRACTICING AUTOROTATION AND FELT A CHANGE IN THE PEDALS. AFTER TOUCHDOWN, HE ATTEMPTED TO HOVER BY RAISING THE COLLECTIVE, AND THE HELICOPTER BEGAN TO SPIN, HE LOWERED THE COLLECTIVE, AND SHUTDOWN. NO DAMAGE TO THE HELICOPTER WAS NOTED. THE ROTATING CONE CONTROL CABLE WAS FOUND TO HAVE A CLEAN BREAK. THE OTHER CABLES WERE INSPECTED AND FOUND OK. PAN 500N72205 CABLE WAS INSPECTED AT THE LAST 300 HR INSPECTION AND WAS FOUND TO BE AIRWORTHY. THIS PART IS NOT A LIFE LIMITED PART SO NO RECORD OF HRS IN SERVICE IS AVAILABLE. RECOMMEND A SERVICE LIFE FOR THE CABLE: 1000 HRS. (K) 1G71 3U NCH3WE 20060612001182006061200118 2006 6 12 2006FA0000554 120060523G8011ES6462382 STARTER ENGINE INOPERATIVE B WS9RK NONE O OTHER ININSP/MAINT 1 NM07 STARTER IS DIFFICULT TO TURN. (K) 20060612001602006061200160EA 2006 6 12 2006FA0000555 220060519G7320 CLIP PIPER PA34 PA34200 7103405SO LYC O360 IO360A1A 41514EA ENGINE MISSING B DYTRE ENGINE SHUTDOWN O OTHER NRNOT REPORTED 1 SO1515139 347350025 THE RETAINING CLIP FROM THE ROD END EITHER BROKE OR FELL OFF CAUSING THE THROTTLE CABLE TO DETACH FROM THE FUEL INJECTION SERVO. THE ENGINE THEN WENT TO FULL POWER. ENGINE HAD TO BE SHUT DOWN AND FEATHERED IN ORDER TO LAND THE AIRCRAFT. RECOMMEND USING PN 452-606 BEARING INSTEAD WITH APPROPRIATE HARDWARE AND COTTER PIN. (K) 1L72 3O3 O A7SO 1E10 20060606002392006060600239NE 2006 6 6 2006FA0000556 120060512G2100S76A12 A/C PACK SKRSKYS76 S76A 8143006NE AC SYSTEM BURNED G MV1RK NONE B SMOKE/FUMES/ODORS/SPARKS ININSP/MAINT 1 EA1738 2749 760087 AFTER THE DAYS FLIGHT, THE PILOT REPORTED THAT THE AIR CONDITIONING SYSTEM WAS INOPERATIVE. MAINTENANCE WENT TO CHECK THE FREON CHANGE, WHEN THEY OPENED THE BAGGAGE AREA A FAINT SMELL OF BURNT WIRING WAS DETECTED. UPON INSPECTION IT WAS FOUND THAT WIRE A1K925A1130AMP WAS BURNT THRU. THE CURRENT LIMITER AND ITS MOUNT WERE HEAT DAMAGED. THE RELAY K9 FOR THE AIR CONDITIONING SYSTEM ALSO LOOKS LIKE IT WAS EXPOSED TO HEAT. THE DAMAGED PARTS WERE REMOVED, THE SYSTEM DEACTIVATED AND STOWED. REP WAS CALLED AND IS COMING TO SEE WHAT WAS FOUND. NO OTHER SYSTEMS ON BOARD THE AIRCRAFT ARE EFFECTED AND ALL DAMAGE CONFINED TO THE AIR-CONDITIONING SYSTEM. (K) 1G72 3U H1NE 20060612001262006061200126 2006 6 12 2006FA0000557 120060517G8011MZ6222 STARTER ENGINE INOPERATIVE B WS9RK NONE O OTHER ININSP/MAINT 1 NM07 WHINNING STARTER, WOULD NOT ENGAGE. (K) 20060612001582006061200158 2006 6 12 2006FA0000558 220060509G7314 DIAPHRAGM FUEL PUMP WORN B YV4RK NONE O OTHER NRNOT REPORTED 1 SO05 DURING DISASSEMBLY FOR OVERHAUL, OVER THE PAST FEW MONTHS, HAVE NOTED THAT THE STEEL WASHER ON TOP OF THE DIAPHRAGM STEM IS LOOSE ON THE STEM AND IN SOME CASES IS PARTIALLY EATEN THROUGH OR WORN AWAY BY HAMMERING AGAINST UPSET END OF DIAPHRAGM STEM. IF WASHER COMES COMPLETELY OFF, FUEL PUMP WILL BE INOPERABLE. SOME WASHERS HAVE BEEN OBSERVED TO BE WORN 60-80 PERCENT THROUGH THEIR THICKNESS. SB NR 548A IS APPLICABLE TO THIS ISSUE. HOWEVER, MANY OF THE PUMPS WITH WORN/LOOSE WASHERS ARE OUTSIDE DATE CODES COVERED BY SB. THIS HAS BEEN OBSERVED IN MODELS 15472 AND 15473. AT THE SAME TIME, A MODEL 16775 WAS DISCOVERED TO HAVE A WORN/LOOSE WASHER. THIS MODEL NR WAS NOT IN THE SB. (K) 20060609002512006060900251CE 2006 6 9 2006FA0000559 120060430G5346051313211 ATTACH BRACKET CESSNA175 175 2072502CE LYC O360 IO360A1A 41514EA HARTZLHCC2Y HCC2YR1 GL ENG MOUNT CRACKED D K NONE O OTHER ININSP/MAINT 1 AL019366B 55166 ENGINE MOUNT ATTACHMENT BRACKET BROKEN AND WITH CRACKS AT THE 12 AND 6 O`CLOCK POSITION. CRACKS ON IB AND OB SIDES OF THE AN960-616 WASHER. NORMAL FLIGHT CONDITIONS UNDER WHICH IT OCCURRED. POSSIBLE CAUSE AN960-616 WASHER TOO SMALL. LARGER AREA AND THICKER WASHER NEEDED TO SUPPORT THE UPPER LOAD. (K) 1H71 3O3 ONT3A17 1E10 5 CP920 20060612001152006061200115CE 2006 6 12 2006FA0000560 120060430G5346051313211 ATTACH BRACKET CESSNA175 175 2072502CE FRNKLN6AV3506A350C1 27043EA ENG MOUNT BROKEN D K NONE O OTHER NRNOT REPORTED 1 AL01175FW 55020 ENGINE MOUNT ATTACHMENT BRACKET BROKEN AND WITH CRACKS AT THE 12 AND 6 O`CLOCK POSITION. CRACKS ON IB AND OB SIDES OF THE AN960-616 WASHER. NORMAL FLIGHT CONDITIONS UNDER WHICH IT OCCURRED. POSSIBLE CAUSE AN960-616 WASHER TOO SMALL. LARGER AREA AND THICKER WASHER NEEDED TO SUPPORT THE UPPER ENGINE MOUNT LOAD. (K) 1H71 3O3 ONT3A17 E9EA 20060612000592006061200059CE 2006 6 12 2006FA0000561 120060531G5346051313211 ATTACH BRACKET CESSNA175 175 2072502CE CONT IO360 IO360* 17025CE ENG MOUNT CRACKED D K NONE O OTHER NRNOT REPORTED 1 AL016622E 56122 ENGINE MOUNT ATTACHMENT BRACKET WITH CRACKS AT THE 12 AND 6 O`CLOCK POSITION. CRACKS ON IB AND OB SIDES OF THE AN960-616 WASHER. NORMAL FLIGHT CONDITIONS UNDER WHICH IT OCCURRED. POSSIBLE CAUSE AN960-616 WASHER TOO SMALL. LARGER AREA AND THICKER WASHER NEEDED TO SUPPORT THE UPPER ENGINE MOUNT LOAD. (K) 1H71 3O3 ONT3A17 E1CE 20060609002522006060900252CE 2006 6 9 2006FA0000562 120060518G301040653481 BLANKET LEAR 55 55LEAR 5170702CE GARRTTTFE731TFE731* 01518WP STABILIZER DAMAGED B FJKRK NONE P NO WARNING INDICATION CRCRUISE 1 SO17417AM 123 THIS INCIDENT HAPPENED IN FLIGHT. CREW REPORTED THAT THERE WAS NO INDICATION IN COCKPIT, THAT THERE WAS A PROBLEM. CREW DISCOVERED DAMAGE TO RT HORIZONTAL STAB ICE GUARD BLANKET DURING THERE POST FLIGHT INSPECTION. IB SECTION OF THE RT ICE GUARD BLANKET WAS DAMAGED. UPON FURTHER INVESTIGATION BY MECHANICS, WAS NOTED THAT A HOLE HAD BEEN MADE IN THE HORIZONTAL LEADING EDGE BY THE ARCING OF THE HORIZONTAL LEADING EDGE ICE GUARD BLANKET WIRING. THE RT HORIZONTAL STAB LEADING EDGE AND ICE GUARD BLANKET WERE REPLACED. (K) 2L72 4F4 F A10CE E6WE 20060612001642006061200164EA 2006 6 12 2006FA0000563 120060424G2420728318 ADG CNDAIRCL600 CL6001A11 1900302EA LYC ALF502ALF502* 41580EA NOSE BAY DEPLOYED G A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 SO05777GD 1023 AIR DRIVEN GENERATOR (ADG) UNEXPECTED DEPLOYED ON POST TAKEOFF CLIMB OUT. PRECAUTIONARY LANDING ACCOMPLISHED. ADG MECHANICALLY RETRACTED/ SAFED; AIRCRAFT FERRIED TO MAINTENANCE DEPOT. ALL WORK ACCOMPLISHED IAW MM. (K) 2L72 4F4 FRTA21EA E6NE 20060607001352006060700135CE 2006 6 7 2006FA0000564 120060418G2820530010854 LINE CESSNA340 340A 2076405CE CABIN CORRODED D K NONE O OTHER ININSP/MAINT 1 SO09320RM5275 340A0939 DURING AC MAINT, A STRONG FUEL ODOR WAS OBSERVED IN CABIN OF THE AC. THIS AC HAD SAT IDLE ON RAMP FOR AT LEAST 10 MONTHS. EXTERIOR OF AC WAS INSPECTED FOR OBVIOUS FUEL LEAKS WITH NONE BEING DETECTED. BY THIS TIME FUEL SMELL IN CABIN HAD CLEARED UP, AC ENGINES WERE OPERATED. DURING PART OF THIS OPERATION, MECH WAS RUNNING ENGINES WITH FUEL SYS IN CROSSFEED POSITION, AGAIN NOTICED A STRONG FUEL ODOR. AC WAS BROUGHT BACK TO HANGER, FLOOR PANELS WERE TAKEN UP IN AREA OF CROSSFEED LINES WHERE THEY RUN THROUGH CABIN AREA. IT WAS OBSERVED THAT A HEATER DUCT THAT WAS RUNNING PERPENDICULAR TO CROSSFEED LINES AND WAS IN CONTACT WITH LINES HAD CAUSED CORROSION TO FORM AND RESULTED IN PINHOLES IN BOTH LINES. (K) 1L72 3O 3A25 20060607001372006060700137CE 2006 6 7 2006FA0000566 120060524G5610991438011 WINDSHIELD CESSNA560 560XL 2076702CE PWA 545 PW545A NE COCKPIT CRACKED D K NONE O OTHER ININSP/MAINT 1 GL13240B 3548 5605057 PILOTS WINDSHIELD OUTER PANE CRACKED AT 39,000 FT. IT IS BELIEVED THAT A HEATING ELEMENT SHORTED CAUSING THE OUTER PANE TO CRACK. WINDSHIELD REMAINS STRUCTURALLY INTERGRAL WITH THE OUTER PANE CRACKED. MFG ENGINEERING IS EVALUATING THE FAILURE. (K) 2L72 4F4 FRTA22CE E00059EN 20060607001402006060700140EA 2006 6 7 2006FA0000567 220060601G7321 BEARING BEECH 90 C90A 1152911CE PWA PT6 PT6* 52043EA FCU FAILED D K NONE O OTHER ININSP/MAINT 1 SO05530CH2896 LJ1322 THE BEARING IN FUEL CONTROL UNIT FAILED CAUSING THE LT ENGINE TO SURGE AND EXCEED THE N1, ITT AND TORQUE LIMITS. THE ITT EXCEEDED 1000 C AND THE TORQUE EXCEEDED 1500 FT POUNDS FOR 5-10 SECONDS. SHORTLY AFTER TAKEOFF, PILOTS REPORTED PLANE HAD YAWED TO THE RT AND FIRST CORRECTED FOR THE YAW BEFORE NOTICING ITT AND TORQUE ABOVE RED LINE. PILOTS THEN REDUCED POWER AND RETURNED TO AIRPORT. ENGINE WAS REMOVED FOR REPAIR AND ALL ROTATING PARTS WERE FOUND TO BE IN NEED OF REPLACEMENT. IN-SITU TEST HAD BEEN DONE REGULARLY AND NO INDICATION OF BEARING INSPECTION BUT IT IS AT THE END OF THE NOTES UNDER THE FUEL SYSTEM INSPECTION. BEARINGS ARE CALLED OUT FOR INSP/ REPLACEMT AT MID TBO OR 6 YEARS. 1L72 3T3 TRT3A20 E2NE 20060612001992006061200199GL 2006 6 12 2006FA0000568 120060601G2720 SPRING DIAMONDA40 DA40 2990002GL RUDDER LOOSE D K NONE O OTHER ININSP/MAINT 1 EA23422DL 42L002 THIS HAS TO DO WITH RUDDER CENTERING BUNGEES OR SPRINGS THERE IS ONE ON BOTH SIDES OF THE RUDDER. AFTER FLT, MECHANIC NOTICED SOME PARTS SETTING ON RUDDER HORN AS IF THEY HAD BEEN REMOVED AND PUT THERE, AN INSP OF RUDDER, IT WAS DETERMINED THAT THEY FELL OFF JUST AS AC WAS PARKED AS ALL OF PARTS FOR BUNGEE WAS THERE. AFTER CONSULTING MAINT, PARTS ALONG WITH AC PARTS WERE REASSEMBLED USING LOCK TIGHT AS THERE IS NO LOCKING DEVICE. PNS FOUND ON RUDDER ARE: (ROD, D60-2723-00-31) (SPACER, D60-2723-00-32) (SPRING, VD-283A-10) (SPACER, D60-2723-00-33) IF THESE PARTS WOULD HAVE FALLEN OUT IN FLIGHT THIS COULD HAVE LOCKED UP THE RUDDER. SUGGEST THERE SHOULD BE SOME SORT OF LOCKING DEVICE INSTALLED. (K) 1L71 3O NTA47CE 20060613001972006061300197NE 2006 6 13 2006FA0000569 220060606G74146351 SCREW MAULE MT7235MT7235 5470209SO LYC O540 IO540W1A5 41532NE MAGNETO LOOSE D K NONE O OTHER NRNOT REPORTED 1 SW01116CP394 394 18063C CHECKED TIMING BOTH WERE OUT OF TIME. REMOVED BOTH MAGS, THE PIVOT SCREW WAS LOOSE. REPLACED POINTS & CAP, WITH 500 HR INSP. BOTH MAGS WERE INSTALLED NEW IN 04/2002 AT 46.1 TT. 1H71 3O3 ONC3A23 1E4 20060612001162006061200116SO 2006 6 12 2006FA0000571 120060531G740010382585 POINTS PIPER PA34 PA34220T 7103420SO CONT O360 TSIO360KB 17025SO ENGINE FAILED D K NONE O OTHER ININSP/MAINT 1 CE038456H9 348233011 268216R THE POINTS WHICH ONLY HAD A TOTAL OF 9.3 HR, HAD THE PLASTIC PORTION WHICH RIDES THE CAM, MELT ON THE METAL OF THE POINTS WHICH REDUCED THE GAP TO CAUSE MISFIREING. CAPACITOR CHECKED GOOD AND WAS NOT REPLACED ON THE 500 HR INSP. AFTER A NEW POINT SET WERE INSTALLED CHANGED THE CAPACITOR. NOTE: WIRE BROKE ON OLD CAPACITOR. (K) 1L72 3O3 O A7SO E9CE 20060612001142006061200114SW 2006 6 12 2006FA0000572 120060519G3210AN3H11A BOLT GULSTM690TP 695A 7630519SW GARRTTTPE331TPE33110 01514WP NLG STEERING ACTSHEARED B O9IRO OTHER J WARNING INDICATION APAPPROACH 1 NM09333UP3934 96015 DURING LANDING GEAR EXTENSION ON APPROACH, (GEAR IN TRANSIT) LIGHT REMAINED ON, NLG DID NOT INDICATE DOWN AND LOCKED. INITIAL FLY BYS INDICATED NLG TO BE ONLY PARTIALLY EXTENDED. AFTER RECYCLING GEAR SEVERAL TIMES, CLUNK WAS HEARD, NLG EXTENDED. INSP REVEALED 4 (AN3) BOLTS USED TO SECURE HYD STEERING ACTUATOR TO NLG OLEO STRUT, SHEARED RESULTING IN STEERING ACTUATOR HANGING ONLY BY ITS HYD LINES. UNSECURED STEERING ACTUATOR HAD POSSIBLY JAMMED PREVENTING FULL EXTENSION OF NLG. RADOME DAMAGE WAS EVIDENT, NO OTHER DAMAGE HAS BEEN FOUND. 4 BROKEN BOLTS CAN BE DAMAGED BY EXCEEDING NLG TURN LIMITS DURING TOWING. BOLTS WERE WEAKENED BY EXCESSIVE TURNING WHILE TOWING. SOMETIME IN PAST, FAILED DURING FLIGHT. (K)1H72 4T4 T 2A4 E4WE 20060612001222006061200122CE 2006 6 12 2006FA0000573 120060525G5541053100121 RIB CESSNA CESSNA172 172 2072402CE CONT O300 O300A 17022SO RUDDER CRACKED H ET9TO OTHER O OTHER NRNOT REPORTED 1 NM075039A5752 28039 10851D5B RIB, CRACKED AT VERTICAL HINGE LINE JUNCTURE. STRESS FROM COUNTER WEIGHT AND NORMAL WEAR. AGE OF THE PART AND THE WIND. SUBMITTER RECOMMENDS CLOSE INSPECTION AND REPLACEMENT OF PART IF DAMAGED. (K) 1H71 3O3 ONT3A12 E253 20060612001302006061200130GL 2006 6 12 2006FA0000574 120060531G7810 FLANGE DIAMON DIAMONDA40 DA40 2990002GL LYC O360 IO360A1A 41514EA HARTZLHCC2Y HCC2YR1 GL EXHAUST RISER BROKEN D O OTHER O OTHER NRNOT REPORTED 1 NM05431JP82 1PA520014 40431 L31683351A CH338383B FOUND NR 2 CYLINDER EXHAUST RISER FLANGE BROKEN. DISCOVERED WHEN DISASSEMBLY EXHAUST FOR MODIFICATION IAW MSB-4000411. PROBABLE CAUSE OF BREAKING FROM EXCESS VIBRATION. RECOMMEND INSTALLING MSB-40-004/1 MUFFLER BRACE. (K) 1L71 3O3 ONTA47CE 1E10 5 CP920 20060612001742006061200174EU 2006 6 12 2006FA0000575 120060309G7600L810BQ54 SOLENOID SNIAS 350 AS350B3 8680954EU TMECA ARRIELARRIEL2B NE AUTOTHROTTLE INOPERATIVE D O OTHER O OTHER NRNOT REPORTED 1 EA01187AE673 3846 22469 PROLONGED OPERATION IN MANUAL MODE CAN CAUSE SOLENOID OVERHEATING AND PISTON SEIZURE. FAILURE OF THE PISTON MOVEMENT MAY RESULT IN THE PILOT BEING UNABLE TO APPLY ADDITIONAL MANUAL THROTTLE BEYOND THE VOL (GATE). THIS CAN RESULT IN ROTOR RPM DECAY IN CERTAIN CRITICAL SITUATIONS. WHILE PERFORMING MAINTENANCE OF COLLECTIVE TWIST GRIP THROTTLE AUTO/MAN SOLENOID PISTON, SYSTEM WAS ACTIVATED FOR 10 MIN. FOLLOWING A 30 SECOND TIME IN WHICH SOLENOID WAS RELAXED PWR WAS AGAIN APPLIED. PISTON FAIL TO FULLY SEAT IN THE SOLENOID. PART WILL BE REPLACED. CMD AS350-06-15 RESCINDED AND REPLACED BY CMD AS350-06-16. NEW CMD CHANGES RELAXED TIME FROM 30 SEC TO 15 MIN TO ALLOW THE SOLENOID TO COOL BEFORE REACTIVATION. (K)1G71 3U3 U H9EU E00054EN 20060614002292006061400229SO 2006 6 14 2006FA0000576 220060606G8520 NUT CIRRUSSR SR22 2130001GL CONT O550 IO550* SO NR 4 CYLINDER SPLIT D K NONE O OTHER ININSP/MAINT 1 GL15746C 699 0413 686383 THRU STUD NUT SPLIT ON NR 4 CYLINDER TOP THRU STUD. (K) 1L71 3O3 ONTA00009CHE3SO 20060614002192006061400219SW 2006 6 14 2006FA0000577 120060521G28412731 GAUGE BBAVIA7 7CCM 21101MWSW CONT C90 C90* 17009SO COCKPIT STUCK G K NONE O OTHER ININSP/MAINT 1 GL134629E 7CCM196 AIRCRAFT LOST POWER AND LANDED IN A HAYFIELD UP ON ITS NOSE. PILOT STATED HE CHECKED THE FUEL GAUGE PRIOR TO THE FLIGHT AND IT READ (HALF FULL). HE DID NOT VISUALLY CHECK THE QUANTITY. INVESTIGATION REVEALED FUEL TANK TO BE EMPTY AND GAUGE STUCK IN THE (HALF FULL) POSITION. (K) 1H71 3O3 O A759 E252 20060614002272006061400227EA 2006 6 14 2006FA0000579 120060420G5310 DOOR FRAME DHAV DHC3 DHC3 2800202EA FUSELAGE CORRODED D K NONE O OTHER ININSP/MAINT 1 AL05435B 12295 183 FORWARD FUSELAGE STRUTS (DOOR POSTS) CORRODED THROUGH FROM INSIDE OUT. THIS IS THE SAME DESIGN AS THE DOOR POST THAT ARE REQUIRED BY AD TO BE REPLACED EVERY 15 YEARS OR INSPECTED ANNUALLY BY ULTRASOUND. (K) 1H71 3R A815 20060614002232006061400223SO 2006 6 14 2006FA0000580 220060508G8520 CONNECTING ROD BEECH 58 58 1152740CE CONT O550 IO550* SO HARTZLHCJ3Y PHCJ3YF1 GL LT ENGINE UNKNOWN D EA ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 SW11106GA TH437 8244276R ED3372 50 MILES OUT OF HOME BASE, PILOT HEARD A (POP) CAME FROM LEFT ENGINE, THEN NOTICED OIL PRESSURE START THE FALL. FEATHERED PROP AND SECURED ENGINE. MADE A UNEVENTFUL LANDING. INSP FOUND NR 4 CYLINDER ON L/E DDEPARTED FROM ENGINE AND NR 4 ROD BROKEN. SUSPECT EITHER ROD BOLTS FAILED OR IMPROPERLY TORQUED, OR CYLINDER IMPROPERLY TORQUED. ENGINE COMPLETE LOSS. (K) 1L72 3O3 O 3A16 E3SO 5 CP36EA 20060614002132006061400213 2006 6 14 2006FA0000581 420060504G611305503214 BULKHEAD CESSNA172 172M 2072418CE PROP SPINNER CRACKED D K NONE O OTHER ININSP/MAINT 1 NM019379H445 17266128 DURING ROUTINE SCHEDULED PHASE INSPECTION. FOUND FORWARD PROP SPINNER BULKHEAD CRACKED RADIALLY OUTWARD FROM MOUNTING BOLT HOLES NEXT TO BEND RADIUS. PROPELLER MOUNTING BOLT BOLT TORQUE AND INDEXING FOUND CORRECT. SUSPECT EITHER IMPROPER HEAT TREAT DURING MFG, OR POSSIBLY TOO TIGHT OF BEND RADIUS. (K) 1H71 3O NT3A12 20060614002162006061400216SO 2006 6 14 2006FA0000582 120060522G3211401421 BOLT PIPER PA34 PA34200T 7103406SO CONT O360 TSIO360* 17025SO NLG LOOSE D K NONE O OTHER LDLANDING 1 NM137609C 347670097 NOSE GEAR RETRACTED ON LANDING. FOUND BOLT PN 401-421 (AN6-41A) LOOSE WHERE NOSE GEAR MOUNT BOLTS TO BULKHEAD AT STA 49.5. THIS RELEAVED DOWNLOCK LINK OVER CENTER POSITION. BOLTS SHOULD BE CHECKED EACH 500 HRS. (K) 1L72 3O3 O A7SO E9CE 20060621002342006062100234CE 2006 6 21 2006FA0000584 120060602G554396630000335 TRIM TAB BEECH 90 C90 1152913CE PWA PT6 PT6A11 52043NE RUDDER TRIM MISMANUFACTURED D O OTHER O OTHER NRNOT REPORTED 1 CE07690GT164 LJ1728 LJ1727 WHEN INSPECTED IAW SB, THIS AC WAS IDENTIFIED AS MISSING THE DRAIN PROVISIONS. C/A WAS TAKEN IAW SB. DURING OUR RESEARCH INTO THIS MATTER IT WAS IDENTIFIED THAT THE CCORRELATING AD TO THIS ISSUE. THIS IS A NEARLY NEW AC. (K) 1L72 3T3 T 3A20 E4EA 20060621002362006062100236CE 2006 6 21 2006FA0000585 120060518G2434991059111RX ALTERNATOR CESSNA172 172S 2072439CE LYC O360 IO360A1A 41514EA ENGINE SHORTED B NF2RO OTHER O OTHER NRNOT REPORTED 1 GL03140JA 172S8653 ALTERNATOR WENT SEVERE OVER VOLT DUE TO INTERNAL SHORT IN THE FIELD WINDINGS. SHORT FRYED THE ACU AND BOSS 1 DIODE (AVIONICS BUSS) DUE TO BADLY DAMAGED ACU, ACU COULD NOT GET ALTERNATOR OFF LINE. DUE TO BOSS 2 DIODE FAILURE AVIONICS BUSS WAS HOT WITH AVIONICS MASTER OFF OVER VOLT BURNED UP ALL RADIOS. ALL ENGINE GAUGES, FUEL GAUGES ANNUNICATOR PANEL AND FLASHING BEACON. THIS IS THE 5TH ALTERNATOR WITH MAJOR PROBLEMS IN THE PAST 11 MONTHS. (K) 1H71 3O3 ONT3A12 1E10 20060621002622006062100262CE 2006 6 21 2006FA0000586 120060518G2435230790001 STARTER GEN BEECH 100 B100 1152919CE GARRTTTPE331TPE3316 01514WP SEIZED B R4ORO OTHER O OTHER NRNOT REPORTED 1 SO33301TS BE76 P271610 RT ENGINE WOULD NOT START. TROUBLESHOT AND FOUND RT STARTER GENERATOR SEIZED DUE TO BRUSHES WORN BEYOND LIMITS AND PIGTAILS ARCHING TO ARMATURE. (K) 1L72 4T4 T A14CE E4WE 20060621002322006062100232EU 2006 6 21 2006FA0000587 120060202G3213TB2047007 CYLINDER SOCATATB20 TB20TRINIDAD8680695EU LYC O540 IO540* 41532EA LT MLG UNSERVICEABLE D K NONE O OTHER ININSP/MAINT 1 NM092808W800 1083 MLG HYD CYL, PN TB2047007/SN WO300497 WAS REMOVED AND SENT FOR INTERNAL LEAK AND A VERY STIFF SPOT ABOUT CENTER OF TRAVEL. CYL WAS RETURNED, REPAIRED, WARRANTY AS IS. INSTALL CYL ON LT MLG. INTERNAL LEAK NO LONGER EXISTED. UPON TESTING EMERGENCY EXTENSION CYL WOULD NOT ALLOW LT MAIN TO EXTEND, STIFF SPOT CENTER OF TRAVEL, CAUSE: REPAIR STATION STAMPED TAG, DISTORTING CYLINDER? CYLINDER HAS TO BE REPLACED WITH SERVICEABLE UNIT. (K) 1L71 3O3 ORTA51EU 1E4 20060621002382006062100238NM 2006 6 21 2006FA0000588 120060607G2910 CAP BOEING737 737205 1384456NM PWA JT8 JT8D17A 52049NE CHECK VALVE INOPERATIVE C NACRK NONE O OTHER ININSP/MAINT 1 AL03736BP 0448 23465 AFTER COMPLETING 2 FLIGHTS, (A) HYDRAULIC SYSTEM BECAME INOPERATIVE. A LARGE AMOUNT OF FLUID WAS NOTED ON THE GROUND UNDER THE LT WHEEL. UPON FURTHER INVESTIGATION IT WAS NOTED THAT THE RT (A) SYSTEM MODULE CHECK VALVE INSTALLATION CAP HAD SHEARED IN THE MODULE CHECK VALVE INSTALLATION CAP HAD SHEARED IN THE MODULE PACKAGE, ALLOWING A LARGE QUANTITY OF HYDRAULIC FLUID TO BE LOST. DO NOT HAVE A PROBABLE CAUSE OR ANY RECOMMENDATIONS. (K) 2L72 4F4 FRTA16WE E2EA 20060621002502006062100250 2006 6 21 2006FA0000589 420060412G2562 BATTERY CNDAIRCL600 CL6001A11 1900302EA ELT LEAKING C PAIRK NONE K FLUID LOSS ININSP/MAINT 1 EA01673TS WO62231 1073 A STRONG ACIDIC ODOR WAS PRESENT AFTER REMOVING ELT BATTERY FROM ELT INSPECTION FOUND A THICK WHITE LIQUID ON THE NEGATIVE SIDE OF ONE BATTERY CELL. THE EXPIRATION DATE OF THE ELT BATTERY IS APRIL 2010 (4 MORE YEARS). THE ELT BATTERY OUTPUT IS 13.2 VOLTS. (K) 2L72 4F RTA21EA 20060627003112006062700311CE 2006 6 27 2006FA0000590 120060608G2810714145 VENT LINE BBAVIA8 8KCAB 2110612CE LYC O360 AEIO360* EA FUEL CELL CRACKED B K NONE KB FLUID LOSS SMOKE/FUMES/ODORS/SPARKS ININSP/MAINT 1 GL21316CA152 152 10132006 L3247851A CREW REPORTED STRONG SMELL OF FUEL IN CABIN. MX INSPECTED FOUND FUEL LEAKING ONTO CARPET ON THE FWD LT SIDE OF CABIN. TRACED LEAK TO THE VENT LINE HEADER TANK ATTACH FITTING. FITTING FOUND TO BE TIGHT BUT LINE CRACKED AT COMPRESSION SLEEVE CONNECTOR. LINE AND CONNECTOR REPLACED NO LEAKS NOTED. 1H71 3O3 O A21CE 1E10 20060619001892006061900189CE 2006 6 19 2006FA0000591 120060608G2810714145 SLEEVE BBAVIA8 8KCAB 2110612CE LYC O360 AEIO360* EA FUEL LINE BROKEN B O OTHER KB FLUID LOSS SMOKE/FUMES/ODORS/SPARKS NRNOT REPORTED 1 GL21316CA152 152 10132006 L3247851A CREW REPORTED STRONG ODOR OF FUEL IN CABIN.MX INSPECTED FOUND FUEL LEAKING ONTO CARPET ON THE FWD LEFT SIDE OF CABIN. TRACED LEAK TO THE VENT LINE HEADER TANK ATTACH FITTING. FITTING FOUND TO BE TIGHT BUT LINE CRACKED AT COMPRESSION SLEEVE CONNECTOR. LINE AND CONNECTOR REPLACED NO LEAKS NOTED. 1H71 3O3 O A21CE 1E10 20060621002612006062100261 2006 6 21 2006FA0000592 420060605G61130522311 BULKHEAD CESSNA172 172S 2072439CE LYC O360 IO360A1A 41514EA SPINNER CRACKED B WIWRO OTHER O OTHER NRNOT REPORTED 1 WP07787WW100 172S8589 DURING A 100 HOUR INSPECTION FO THE PROPELLER IT WAS NOTICED THAT THE FORWARD SPINNER BULKHEAD HAD CRACKS AROUND ALL 6 BOLT HOLES. THE PROBABLE CAUSE IS DURING THE TORQUING PROCESS THE BULKHEAD IS BEING STRESSED AND BENT AS IT IS PULLED TIGHT TO THE PROP HUB. IT IS SUGGESTED THAT THE SPINNER BULKHEAD BE MADE OF THICKER MATERIAL. (K) 1H71 3O3 ONT3A12 1E10 20060621002092006062100209CE 2006 6 21 2006FA0000593 120060606G324012806160 LINE CESSNA206 T206H 2073303CE LYC O540 TIO540* 41532EA RT MLG BRAKE LEAKING B WIWRO OTHER K FLUID LOSS NRNOT REPORTED 1 WP072147Q117 T20608420 DURING NORMAL OPERATION RT BRAKE STARTED LEAKING. REMOVED WHEEL FAIRING AND FOUND A SCREW FROM THE FAIRING CHAFING INTO THE LOWER BRAKE LINE CAUSING THE LINE TO LEAK AND ALMOST FAIL, THEREFORE IT IS RECOMMENDED THAT PROPER ROUTING IS ASSURED DURING INSPECTIONS AND THIS AREA IS ROUTINELY INSPECTED FOR LEAKS AT EVERY PREFLIGHT. (K) 1H71 3O3 ORTA4CE E14EA 20060621000312006062100031NE 2006 6 21 2006FA0000594 220060427G72500292208230 MANIFOLD SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1 60030NE GAS GEN COKED B GO4DK NONE O OTHER ININSP/MAINT 1 WP13711JH2551 3397 7022 DURING A 500 HR (T-INSPECTION), COULD NOT SPIN COMPRESSOR DISK, DUE TO GAS GENERATOR INJECTION MANIFOLD COKING. MFG TECH REMOVED AND REPLACED INJECTION MANIFOLD ON MODULE NR 3. (K) 1G71 3U3 U H9EU E19EU 20060621002542006062100254SW 2006 6 21 2006FA0000595 120060602G57115271L SPAR BBAVIA7 7ECA 21101NNSW LYC O235 O235C1 41505EA LT WING CRACKED B YEBRK NONE O OTHER ININSP/MAINT 1 CE059562S2573 84 RL338815 REQUIRED INSPECTION OF WOODEN WING SPARS IN ACCORDANCE WITH AD. REVEALED A COMPRESSION CRACK IN THE LT WING FWD SPAR AT THE TOP OB OF WING STRUT ATTACH DOUBLER PLATE. (K) 1H71 3O3 O A759 E223 20060621002452006062100245CE 2006 6 21 2006FA0000596 120060607G32336632201000005 ACTUATOR LEAR 45 45LEAR 5170805CE NLG LEAKING B B08RO OTHER O OTHER NRNOT REPORTED 1 SW05CFBLJ 45270 DURING MAINTENANCE, TECH DISCOVERED LEAKING NLG ACTUATOR. FACILITY GAINED ACCESS, REMOVED AND REINSTALLED THE ACTUATOR WITH A REPAIRED UNIT AND RETURNED THE AC TO SERVIC. DURING ATTEMPT TO BEGAN NORMAL TOWING OPERATIONS TO POSITION THE AIRCRAFT FOR DEPARTURE, NLG BEGAN TO RETRACT. IMMEDIATELY CEASED THE TOWING OPERATION AND WERE ABLE TO PLACE A JACK UNDERNEATH THE AIRCRAFT TO SUPPORT IT AND PREVENT ANY DAMAGE. WITH LANDING GEAR FULLY EXTENDED AN INTEGRAL MECHANISM HOLDS THE ACTUATOR DOWN AND LOCKED UNTIL HYDRAULIC PRESSURE IS APPLIED. SUSPECT FAILURE OF INTEGRAL LOCKING MECHANISM. (K) 2L72 4F RTT00008WI 20060621002572006062100257CE 2006 6 21 2006FA0000597 120060613G7120051313211 GUSSET CESSNA175 175 2072502CE CONT O300 GO300* 17022SO ENGINE MOUNT CRACKED B QI2RO OTHER O OTHER NRNOT REPORTED 1 GL156540E2043 56040 FOUND 2 OF 4 ENGINE MOUNT TO FIREWALL BRACKETS CRACKED, BRACELETS ARE LOCATED IN CABIN, ATTACHING AC SKIN TO FIREWALL. POSSIBLE CAUSE OF CRACKING MAY BE OVERTORQUING OF ENGINE MOUNT TO FIREWALL BOLTS. (K) 1H71 3O3 ONT3A17 E298 20060621002432006062100243CE 2006 6 21 2006FA0000598 120060613G7120051313210 GUSSET CESSNA175 175 2072502CE CONT O300 GO300* 17022SO ENGINE MOUNT CRACKED B QI2RO OTHER O OTHER NRNOT REPORTED 1 GL156540E2043 56040 FOUND 2 OF 4 ENGINE MOUNT TO FIREWALL BRACKETS CRACKED, BRACKETS ARE LOCATED IN CABIN, ATTACHING AC SKIN TO FIREWALL. POSSIBLE CAUSE OF CRACKING MAY BE OVERTORQUING OF ENGINE MOUNT TO FIREWALL BOLTS. (K) 1H71 3O3 ONT3A17 E298 20060621002252006062100225CE 2006 6 21 2006FA0000599 120060613G712005131329 GUSSET CESSNA175 175 2072502CE CONT O300 GO300* 17022SO ENGINE MOUNT CRACKED B QI2RO OTHER O OTHER NRNOT REPORTED 1 GL156540E2043 56040 FOUND 2 OF 4 ENGINE MOUNT TO FIREWALL BRACKETS CRACKED. BRACKETS ARE LOCATED IN CABIN, ATTACHING AC SKIN TO FIREWALL. POSSIBLE CAUSE OF CRACKEING MAY BE OVERTORQUING OF ENGINE MOUNT TO FIREWALL BOLTS. (K) 1H71 3O3 ONT3A17 E298 20060621002482006062100248SO 2006 6 21 2006FA0000600 120060609G551163460000 SPAR PIPER PA28 PA28180 7102808SO LYC O360 O360* 41514EA STABILATOR CORRODED B K NONE O OTHER ININSP/MAINT 1 WP118402W2360 282616 WHILE OPENING SOME SKIN LAPS TO TREAT SURFACE CORROSION THE LT SIDE OF THE MAIN SPAR ABOUT 2.5 FEET FROM TIP WAS FOUND TO HAVE SEVERE INTERGRANULAR CORROSION TO THE POINT WHERE A 4-5 INCH LONGITUDNAL CRACK ABOUT .2500 INCH WIDE WAS FOUND. PART WAS SCRAPPED AND REPLACED WITH NEW ASSY, TREATED AC WITH ACF50. (K) 1L71 3O3 O 2A13 E286 20060621002592006062100259CE 2006 6 21 2006FA0000601 120060601G2450251005 FUSE BEECH MU300 400A 1155402CE EMER BUSS FAILED B E81RO OTHER O OTHER NRNOT REPORTED 1 GL03787TA RK260 FLIGHT CREW REPORTED NO BATTERY VOLTAGE INDICATION ON VOLTMETER WITH ALL DC BUSSES POWERED. TROUBLESHOOTING FOUND AIRCRAFT WOULD NOT GO INTO EMERGENCY POWER OR PERFORMED FEEDER FAULT TEST. FOUND 5A MICROFUSE F105 CONNECTED TO K005 EMERGENCY BUSS POWER RELAY OPEN. REPLACED F105 FUSE, ALL DC POWER FUNCTIONS NORMAL, NO FAULTS NOTED. (K) 2H72 4F RTA16SW 20060621002522006062100252 2006 6 21 2006FA0000602 420060530G22136227410302 CIRCUIT CARD BEECH MU300 400A 1155402CE FCC INTERMITTENT B E81RO OTHER O OTHER NRNOT REPORTED 1 GL03408CW RK108 FLIGHT CREW REPORTED AUTOPILOT PITCH TRIM FAILURE ANNUNCIATION CAME ON DURING CLIMB WITH AUTO PILOT DISCONNECTED. AIRCRAFT REPPORTED TO HAVE PITCH-UP MOVEMENT. FOUND NR 1 FCC-850 CARD INTERMITTENTLY NOT CROSS-TALKING TO NR 2 FCC-850 CARD. REPLACED NR 1 FCC 850 CARD WITH OVERHAULED UNIT. GROUND/FLIGHT CHECKS SATISFACTORY. (K) 2H72 4F RTA16SW 20060621002312006062100231 2006 6 21 2006FA0000603 420060530G22136226717004 SERVO BEECH MU300 400A 1155402CE YAW DAMPER INTERMITTENT B E81RO OTHER J WARNING INDICATION APAPPROACH 1 GL03408CW RK108 FLIGHT CREW REPORTED PILOTS CONTROL WHEEL TRIM INTERRUPT/AUTOPILOT DISENGAGE SWITCH NOT DISCONNECTING YAW DAMPER ON FINAL APPROACH. FOUND CONTROL WHEEL SWITCH OPERATIONS NORMAL. REPLACED SVO-85C YAW DAMPER SERVO WITH OVERHAULED UNIT. ALSO, REPLACED NR 1 FCC-850 CARD WITH OVERHAULED UNIT TO CORRECT ADDITIONAL AUTOPILOT INTERMITTENT PITCH TRIM FAILURE FAULT. GROUND AND FLIGHT TESTS SATISFACTORY. (K) 2H72 4F RTA16SW 20060621002562006062100256SO 2006 6 21 2006FA0000604 120060614G273062701159 CONTROL CABLE PIPER PA32 PA32RT300 7103215SO LYC 0540 IO540K1G5D 41532SO HARTZLHCC3Y HCC3Y* GL ELEVATORS SEPARATED D O OTHER O OTHER NRNOT REPORTED 1 SO11317092741 32R7885121 L1571048A DY4524A CABLE TURNBUCKLE MALE END SEPARATED AT FITTING DURING ROLLOUT AFTER LANDING. FITTING SEEMS TO HAVE CORRODED FROM THE SHANK CORE AND PROGRESSED OUTWARD TO THE SURFACE OVER TIME. (K) 1L71 3O3 O A3SO 1E4 5 CP25EA 20060711001062006071100106 2006 7 11 2006FA0000605 420060621G3460 DISPLAY COCKPIT MALFUNCTIONED C K NONE O OTHER ININSP/MAINT 1 GL07 TO DATE, HAVE EXPERIENCED 12 SEPARATE FAILURES OF THE MULTIFUNCTION DISPLAYS (MFD) WITH 6 OF THE 7 AIRCRAFT. THESE FAILURES HAVE OCCURRED EITHER IN FLIGHT OR ON THE GROUND. THERE IS NO APPARENT PATTERN OR FOREWARNING RELATED TO THESE FAILURES. THESE FAILURES CAUSE AN UNAIRWORTHY CONDITION OF THE AIRCRAFT DUE TO THE LACK OF OIL TEMPERATURE INDICATION. ALSO, ACCORDING TO THE PA 28-161 MFG POH, SECTION 9, SUPPLEMENT 10, SECTION 2, PARAGRAPH B TITLED "MFD LIMITATIONS", ITEM 4, (AIRCRAFT DISPATCH IS PROHIBITED WHEN THE MFD IS INOPERATIVE.) CURRENTLY, MANUFACTURERS ARE INVESTIGATING THIS PROBLEM, BUT NO RESOLUTION HAS BEEN FOUND. 20060627003122006062700312CE 2006 6 27 2006FA0000606 120060622G5730 SKIN CESSNA402 402B 207590PCE LT WING CRACKED D K NONE O OTHER ININSP/MAINT 1 SO156375X5321 402B1338 DURING AN ANNUAL INSPECTION, A CRACK WAS FOUND ON THE LT WING SKIN AT THE OB AILERON ATTACH POINT, WHICH IS ALSO THE MAIN FUEL TANK AFT ATTACH POINT. UPON FURTHER INSPECTION OF AREA, THE RIVETS THAT ATTACH THE AILERON SUPPORT TO THE REAR SPAR WERE FOUND SHEARED, CAUSING THE MAIN FUEL TANK TO HAVE MOVEMENT. IF LEFT UNDETECTED, COULD CAUSE MAIN FUEL TANK STRESS AT THE FORWARD ATTACH POINTS, CRACKED REAR SPAR OR POSSIBLE SEPARATION OF TANK. THIS IS THE SECOND AIRCRAFT THAT THIS PROBLEM WAS FOUND ON. 1L72 3O A7CE 20060627003132006062700313CE 2006 6 27 2006FA0000607 120060622G5730 SKIN CESSNA402 402B 207590PCE LT WING CRACKED D K NONE O OTHER ININSP/MAINT 1 SO156375X5321 402B1338 DURING AN ANNUAL INSPECTION, A CRACK WAS FOUND ON THE LT WING SKIN AT THE OB AILERON ATTACH POINT, WHICH IS ALSO THE MAIN FUEL TANK AFT ATTACH POINT. UPON FURTHER INSPECTION OF AREA, THE RIVETS THAT ATTACH THE AILERON SUPPORT TO THE REAR SPAR WERE FOUND SHEARED, CAUSING THE MAIN FUEL TANK TO HAVE MOVEMENT. IF LEFT UNDETECTED, COULD CAUSE MAIN FUEL TANK STRESS AT THE FORWARD ATTACH POINTS, CRACKED REAR SPAR OR POSSIBLE SEPARATION OF TANK. THIS IS THE SECOND AIRCRAFT THAT THIS PROBLEM WAS FOUND ON. 1L72 3O A7CE 20060627003142006062700314SO 2006 6 27 2006FA0000608 120060612G273062701159 CONTROL CABLE PIPER PA32 PA32RT300 7103215SO LYC 0540 IO540K1G5D 41532SO ELEVATOR SEPARATED D O OTHER D INFLIGHT SEPARATION LDLANDING 1 SO16317092741 32R7885121 L1809048A UP ELEVATOR CABLE SEPARATED IN LANDING FLARE. 1L71 3O3 O A3SO 1E4 20060627003152006062700315SO 2006 6 27 2006FA0000609 120060612G273062701159 CONTROL CABLE PIPER PA32 PA32RT300 7103215SO LYC 0540 IO540K1G5D 41532SO ZONE 300 SEPARATED D O OTHER D INFLIGHT SEPARATION LDLANDING 1 SO16317092741 32R7885121 L1809048A UP ELEVATOR CABLE SEPARATED DURING LANDING FLARE. 1L71 3O3 O A3SO 1E4 20060627003162006062700316SO 2006 6 27 2006FA0000610 120060612G273062701159 CONTROL CABLE PIPER PA32 PA32RT300 7103215SO LYC 0540 IO540K1G5D 41532SO ZONE 300 SEPARATED D O OTHER D INFLIGHT SEPARATION LDLANDING 1 SO16317092741 32R7885121 L1809048A UP ELEVATOR CABLE SEPARATED DURING LANDING FLARE. 1L71 3O3 O A3SO 1E4 20060627003172006062700317SO 2006 6 27 2006FA0000611 120060612G273062701159 CONTROL CABLE PIPER PA32 PA32RT300 7103215SO LYC 0540 IO540K1G5D 41532SO ZONE 300 SEPARATED D O OTHER D INFLIGHT SEPARATION LDLANDING 1 SO16317092741 32R7885121 L1809048A UP ELEVATOR CABLE SEPARATED DURING LANDING FLARE. 1L71 3O3 O A3SO 1E4 20060627003182006062700318CE 2006 6 27 2006FA0000612 120060621G53111054200116 FRAME BEECH 76 76 1153005CE RT WINGFEATHERINCRACKED D K NONE O OTHER ININSP/MAINT 1 SO09141P 2269 ME237 CRACK IN RT FORWARD WING BOLT ATTACH FRAME, P/N: 105-420011-6. 1L72 3O A29CE 20060627003192006062700319CE 2006 6 27 2006FA0000613 120060621G53111054200116 FRAME BEECH 76 76 1153005CE RT WING CRACKED D K NONE O OTHER ININSP/MAINT 1 SO09141P 2269 ME237 CRACK IN RT FWD WING BOLT ATTACH FRAME, P/N: 105-420011-6. 1L72 3O A29CE 20060627003212006062700321CE 2006 6 27 2006FA0000614 120060621G53111054200116 FRAME BEECH 76 76 1153005CE ZONE 100 CRACKED D K NONE O OTHER ININSP/MAINT 1 SO09141P 2269 ME237 CRACK IN RT FWD WING BOLT ATTACH FRAME, P/N: 105-420011-6. 1L72 3O A29CE 20060627003222006062700322CE 2006 6 27 2006FA0000615 120060621G53111054200116 FRAME BEECH 76 76 1153005CE ZONE 100 CRACKED D K NONE O OTHER ININSP/MAINT 1 SO09141P 2269 ME237 CRACK IN RT FWD WING BOLT ATTACH FRAME, P/N: 105-420011-6. 1L72 3O A29CE 20060627003232006062700323CE 2006 6 27 2006FA0000616 120060621G53111054200116 FRAME BEECH 76 76 1153005CE ZONE 100 CRACKED D K NONE O OTHER ININSP/MAINT 1 SO09141P 2269 ME237 CRACK IN RT FWD WING BOLT ATTACH FRAME, P/N: 105-420011-6. 1L72 3O A29CE 20060627003242006062700324CE 2006 6 27 2006FA0000617 120060621G53111054200116 FRAME BEECH 76 76 1153005CE ZONE 100 CRACKED D K NONE O OTHER ININSP/MAINT 1 SO09141P 2269 ME237 CRACK IN RT FWD WING BOLT ATTACH FRAME, P/N: 105-420011-6. 1L72 3O A29CE 20060627003252006062700325 2006 6 27 2006FA0000618 120060623G26127503611 CONTROL PANEL AMD STC STCFALC50 FIRE DETECTION FAILED B A UNSCHED LANDING J WARNING INDICATION NRNOT REPORTED 1 SW11223HD2811 283 FIRE CONTROL PANEL FAILED. 2L72 4F A46EU 20060627003262006062700326EU 2006 6 27 2006FA0000619 120060623G26127503611 CONTROL PANEL AMD FALC50FALCON50MYST2730106EU FIRE DETECTION FAILED B A UNSCHED LANDING O OTHER NRNOT REPORTED 1 SW11223HD2811 283 FIRE CONTROL PANEL FAILED. 2L73 4F A46EU 20060627003272006062700327NM 2006 6 27 2006FA0000620 120060608G62305100400 HOSE DOUG MD900 MD900 3027375NM PWC PW207 PW207E NE XMSN OIL CRACKED D A UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CRCRUISE 1 EA11902PD450 9000084 PILOT NOTICED TRANSMISSION OIL PRESSURE INDICATION DROPPED FROM GREEN TO YELLOW TO RED. MADE UNSCHEDULED LANDING. FOUND FWD LT TRANSMISSION OIL COOLER HOSE LEAKING. HOSE IS A FLEXIBLE STAINLESS STEEL HOSE WITH A STAINLESS STEEL OUTER BRAID. HOSE WAS INSPECTED AFTER REMOVAL AND FOUND TO BE CRACKED. REPLACED HOSE P/N 900D3409526-105. 1G72 3U3 UNCH19NM E42NE 20060627003282006062700328CE 2006 6 27 2006FA0000621 120060622G5730 SKIN CESSNA414 414 2075908CE RT WING CRACKED D K NONE O OTHER ININSP/MAINT 1 SO15414JS6794 4140811 DURING AN ANNUAL INSPECTION, A CRACK WAS FOUND ON THE RT WING SKIN AT THE OB AILERON ATTACH POINT, WHICH IS ALSO THE MAIN FUEL TANK AFT ATTACH POINT. UPON FURTHER INSPECTION OF AREA, THE RIVETS THAT ATTACH THE AILERON SUPPORT TO THE REAR SPAR WERE FOUND SHEARED, CAUSING THE MAIN TANK TO HAVE MOVEMENT. IF LEFT UNDETECTED, COULD CAUSE MAIN FUEL TANK STRESS AT THE FWD ATTACH POINTS, CRACKED REAR SPAR OR POSSIBLE SEPARATION OF THE TANK. 1L72 3O RTA7CE 20060627003292006062700329CE 2006 6 27 2006FA0000622 120060622G5730 SKIN CESSNA414 414 2075908CE ZONE 600 CRACKED D K NONE O OTHER ININSP/MAINT 1 SO15414JS6794 4140811 DURING AN ANNUAL INSPECTION, A CRACK WAS FOUND ON THE RT WING SKIN AT THE OB AILERON ATTACH POINT, WHICH IS ALSO THE MAIN FUEL TANK AFT ATTACH POINT. UPON FURTHER INSPECTION OF AREA, THE RIVETS THAT ATTACH THE AILERON SUPPORT TO THE REAR SPAR WERE FOUND SHEARED, CAUSING THE MAIN TANK TO HAVE MOVEMENT. IF LEFT UNDETECTED, COULD CAUSE MAIN FUEL TANK STRESS AT THE FWD ATTACH POINTS, CRACKED REAR SPAR OR POSSIBLE SEPARATION OF THE TANK. 1L72 3O RTA7CE 20060705000252006070500025CE 2006 7 5 2006FA0000624 120060607G3200174302120 SHIMMY DAMPENER CESSNA CESSNA177 177B 2073708CE MLG LEAKING D K NONE KJ FLUID LOSS WARNING INDICATION ININSP/MAINT 1 WP17345974025 17701892 PART BECAME SUSPECT WHEN DAMPENER FLUID WAS NOTICED DRIPPING OFF END OF SHAFT. DURING THE CLEANING/INSP. COMPRESSED AIR WAS INTRODUCED TO SHAFT'S OPEN END. AIR BUBBLES WERE OBSERVED AT BASE OF PISTON. FOUND CRACK ON DAMPENER SHAFT AT BASE OF PISTON. CRACK IS NOTICEABLE 360 DEGREES AROUND SHAFT EVEN THOUGH SHAFT IS STILL INTACT. LOSS OF FLUID MAY HAVE EXAGGERATED VIBRATIONS CAUSING SHAFT TO FATIGUE OR MFG HEAT TREATING PROCESSES SINCE SHAFT IS NOT BROKEN COMPLETELY THROUGH. INSPECT IMMEDIATELY IF FLUID IS SEEN DRIPPING FROM THE END OF THE SHAFT. OR, REMOVE AND DYE PENETRANT INSPECT SHIMMY DAMPENER SHAFT AT NEXT 25/50 HOUR MAINTENANCE INTERVAL. 1H71 3O A13CE 20060705003042006070500304EA 2006 7 5 2006FA0000625 120060620G2910604752383 TUBE CNDAIRCL600 CL6002B16 1900305EA GE CF34 CF34* NE HYD SYSTEM CHAFED B JAVRK NONE O OTHER ININSP/MAINT 1 NE01881TW4180 5348 PRESSURE LINE FROM NR 1 ENGINE DRIVEN PUMP CHAFED AT AFTMOST CLAMP LOCATION (NEAR NR 1 SYSTEM RESERVOIR) UNTIL THE LINE FAILED UNDER PRESSURE CAUSING A COMPLETE LOSS OF NR 1 HYDRAULIC SYSTEM IN FLIGHT. CLAMP CUSHION FAILED CAUSING METAL TO METAL CONTACT. SUSPECT THAT DEFECT WAS NOT READILY VISIBLE BEFORE FAILURE. (K) 2L72 4F4 FRTA21EA E15NE 20060705000102006070500010CE 2006 7 5 2006FA0000626 120060612G2497K3A2 CABLE CESSNA421 421A 2076012CE LT STARTER SHORTED B AGERK NONE O OTHER ININSP/MAINT 1 WP0599VK 421A0091 DURING STARTING OF LT ENGINE, SMOKE WAS OBSERVED COMING FROM THE LOUVERS ON TOP OF THE LT ENGINE. THE ENGINE WAS SHUTDOWN AND THE SMOKE SUBSIDED. INSP REVEALED THAT THE 2-GAUGE STARTER AND ALTERNATOR POWER CABLES WERE BURNED IN HALF NEAR THE TURBOCHARGER. FOURTEEN OTHER WIRES IN THE SAME BUNDLE WERE ALSO BURNED IN HALF OR SEVERELY HEAT DAMAGED. THE ELECTRICAL FIRE WAS A RESULT OF THE STARTER CABLE SHORTING TO GROUND ON THE TURBO SUPPORT BRACKET (PN 5155101-20). THE ELECTRICAL WIRE BUNDLE HAD BEEN RESTING ON THIS BRACKET FOR SOME TIME UNTIL THE WIRE INSULATION WAS CHAFFED THROUGH. INSP OF THE OTHER ENGINE REVEALED SIMILAR CHAFFING AND POSSIBLILITY OF A SHORT. (K) 1L72 3O A7CE 20060711001052006071100105EA 2006 7 11 2006FA0000627 220060605G850071907 WASHER PIPER PA25 PA25235 7102504SO LYC O540 O540* 41532EA COUNTER WEIGHT CRACKED G O OTHER Y ENGINE STOPPAGE AGAGRICULTURE 1 GL277785Z835 835 253989 L677440 COUNTER WEIGHT RETAINING WASHER P/N 71907 CRACKED AND BROKE. THIS ALLOWED THE COUNTER WEIGHT RETAINING PIN TO FALL OUT. ENGINE SEIZED. 1L71 3O3 O 2A10 E295 20060705002942006070500294 2006 7 5 2006FA0000628 120060613G81204066109026 TURBOCHARGER INOPERATIVE B O OTHER O OTHER NRNOT REPORTED 1 NM07 TURBO WILL NOT PRODUCE BOOST. (K) 20060705003032006070500303 2006 7 5 2006FA0000629 120060615G2420ALY6521 ALTERNATOR INOPERATIVE B O OTHER O OTHER NRNOT REPORTED 1 NM07 ALTERNATOR WOULD NOT ENGAGE. (K) 20060705000082006070500008EA 2006 7 5 2006FA0000630 220060612G7414ES10357174 CONTACT BENDIX PIPER PA25 PA25235 7102504SO LYC O540 O540B2B5 41532EA MAG POINTS BROKEN D A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CRCRUISE 1 GL094811Y44 6010962 254592 L713540 MAG FAILED IN FLIGHT, UPON INSPECTION POINTS WERE FOUND TO BE BROKEN WITH 44 HOURS TT ON THE POINTS. THE SPRING PORTION WAS BROKEN DUE TO A DEFECT IN THE STAMPING WHICH SET UP A STRESS POINT AT THE ATTACH SCREW. RECOMMEND MFG CONTACT ASSY BE INSPECTED FOR PROPER BENDING OF THE PARTS AND REMOVE FROM SERVICE THAT DO NOT HAVE PROPER FORMING OF THE SPRING. (K) 1L71 3O3 O 2A10 E295 20060705000132006070500013CE 2006 7 5 2006FA0000631 120060602G29101240016CR0164 LINE BEECH 99 99A 1154003CE PWA PT6 PT6* 52043EA HYDRAULIC SYS RUPTURED B TIMRA UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CLCLIMB 1 NM07326CA U135 DURING CLIMBOUT THE (GEAR IN TRANSIT) AND (DO NOT REVERSE) ANNUNCICATOR ILLUMINATED AND THEN THE LANDING GEAR CIRCUIT BREAKER POPPED. PILOT CONTINUED, HAND PUMPED THE GEAR TO GET 3 GREEN. LANDED OK. INVESTIGATION DETERMINED THAT HYDRAULIC HOSE ON THE LT UP LINE HAD RUPTURED. (K) 1L72 3T3 T A14CE E2NE 20060705000032006070500003CE 2006 7 5 2006FA0000632 120060620G272000252400023 CONTROL CABLE BEECH 33 F33A 1151425CE CONT O520 IO520* 17032SO RUDDER FRAYED B Y5VRK NONE O OTHER ININSP/MAINT 1 NM058259C CE1763 AT ANNUAL INSP RT AFT RUDDER CABLE WAS FOUND FRAYED ALMOST IN TWO. CABLE WAS FOUND ROUTED OVER THE TOP OF ONE CABLE PULLEY GUARD PIN, AND UNDER ANOTHER AT SAME LOCATION IN AFT TAIL SECTION. CABLE REMOVED APPEARED TO BE THE ORIGINAL CABLE INSTALLED IN AIRCRAFT AT FACTORY. LOGBOOKS DID NOT REVEAL ANY EVIDENCE THAT THE CABLE HAD EVER BEEN REMOVED OR DISCONNECTED THAT MAY HAVE CAUSE THIS. BY THE AMOUNT OF CABLE THAT WAS FRAYED, IT APPEARS TO HAVE BEEN RUBBING ON THE PULLEY GUARD PIN FOR SOME TIME. IT IS SUSPECTED THAT THIS CABLE WAS ROUTED INCORRECTLY AT THE FACTORY. POSSIBLE QUICK FASHION ANNUAL PREVIOUS. RECOMMEND THOROUGH ANNUAL IN ITS ENTIRETY. 1L71 3O3 O 3A15 E5CE 20060705003062006070500306CE 2006 7 5 2006FA0000634 120060519G760045A431755 LINK BEECH MU300 400A 1155402CE PWA JT15 JT15D5 52112NE LT ENGINE WORN D EKGRO OTHER O OTHER NRNOT REPORTED 1 WP07435CW RK35 PCE100250 DURING OPERATIONAL CHECK FLIGHT OF AIRCRAFT, PILOT ADVANCED POWER LEVERS FORWARD AND NOTED LT ENG (N) REACHED MAX OF 117 PERCENT N2, REACHED MAXIMUM OF 100 PERCENT. IT IS DETERMINED THAT PROBABLE CAUSE OF OVERSPEED WAS ACHIEVED BY WORN THROTTLE LEVER LINK NOT PROVIDING ACCURATE RANGE OF MOTION TO CORRECTLY ACTUATE THROTTLE STOP. ENGINE LEVERS WERE ENABLE TO ADVANCE FURTHER THAN NORMAL, CAUSING OVERSPEED CONDITION. IT IS RECOMMENDED THAT LINK AND ASSOCIATED HARDWARE BE REPLACED. (K) 2H72 4F4 FRTA16SW E25EA 20060705002992006070500299EU 2006 7 5 2006FA0000635 220060608G72509514M71PO4 SHAFT BOEING737 737300 1384610NM CFMINTCFM56 CFM563C1 13802EU ENGINE FRACTURED B QEMYK NONE O OTHER ININSP/MAINT 1 EA35B294330987 857655 REF: MRD/001/06 - AC CUFFERED AN ABORTED TAKEOFF. INVESTIGATION REVEALED FAILURE AND LIBERATION OF THE HPT REAR SHAFT WHERE A SECTION OF MATERIAL MEASURING 3.5 INCH CIRCUMFERENCE HAD LIBERATED AROUND THE 3 SEAL TOOTH RACK. SIMILAR FAILURES HAVE BEEN EXPERIENCED ON ENGINE. PARTS ARE RETURNED TO MFG FOR INVESTIGATION. EDDY CURRENT INSPECTION INTO 3Q95. (K) 2L72 4F4 FRTA16WE E21EU 20060705003082006070500308 2006 7 5 2006FA0000636 220060501G7497 WIRE DHAV DHC8 DHC8* NM EXCITER FAILED B K NONE O OTHER ININSP/MAINT 1 NE05 415 895 EXCITER ROTOR LEAD WIRES BREAK AT SOLDER CONNECTION TO DIODE. (K) 2H72 4T RTA13NM 20060705003092006070500309 2006 7 5 2006FA0000637 220060501G7497 WIRE DHAV DHC8 DHC8* NM EXCITER FAILED B K NONE O OTHER ININSP/MAINT 1 NE05 392 EXCITER ROTOR LEAD WIRES BROKEN AT SOLDER CONNECTION TO DIODES. (K) 2H72 4T RTA13NM 20060705002912006070500291EU 2006 7 5 2006FA0000638 120060621G2720NB45D1803 CONTROL ROD BNORM BN2 BN2A 1520204EU RUDDER DAMAGED I A UNSCHED LANDING O OTHER CLCLIMB 1 SO17131JL25031 225 AFTER TAKEOFF THE PILOT NOTICED THAT THE RUDDER HAD TO MUCH PLAY IN FLIGHT. HE LANDED AND TAXIED BACK IN. UPON INSPECTION THE RUDDER CONTROL ROD WAS FOUND TO BE DAMAGED, FROM A WIND STORM THE NIGHT BEFORE. TO PREVENT REOCCURANCE, THE AIRCRAFT RUDDER SHOULD BE LOCKED IN PLACE AFTER EACH FLIGHT. 1H72 3O A17EU 20060705003402006070500340EU 2006 7 5 2006FA0000639 120060525G7603L810BQ54 SOLENOID SNIAS 350 AS350B3 8680954EU TMECA ARRIELARRIEL2B NE THROTTLE SYS MALFUNCTIONED D K NONE O OTHER ININSP/MAINT 1 SW15186AE 3872 22484 WHILE PERFORMING CHECK OF TWIST GRIP SOLENOID, ENGAGED SOLENOID BY PLACING THE AUTO/MAN SWITCH TO MAN MODE FOR A TOTAL OF 10 MINUTES. AFTER 10 MINUTE PERIOD HAD ELAPSED. RETURNED AUTO/MAN SWITCH TO AUTO. AFTER 15 SECONDS, MOVED AUTO/MAN SWITCH BACK TO MAN, PISTON FROM SOLENOID FAILED TO MOVE. PISTON SHOULD HAVE RETRACTED IMMEDIATELY. SOLENOID OVERHEATED AND MALFUNCTIONED. RECOMMENDATION TO PREVENT RECURRENCE: REPLACING CURRENT PN OF SOLENOID WITH ONE THAT CAN EITHER RUN COOLER OR WITHSTAND THE HEAT. (K) 1G71 3U3 U H9EU E00054EN 20060718001612006071800161NM 2006 7 18 2006FA0000640 120060705G510035006931 CARRIER ASSY DOUG MD80 MD83 3023681NM UNKNOWN CRACKED B K NONE O OTHER ININSP/MAINT 1 SW99 CARRIER PN 3500693-1 FOUND CRACKED DURING PENERANT INSPECTION OF PART. PART WAS BEING INSPECTED FOR OVERHAUL REPAIR, CRACK IS BEYOND REPAIR LIMITS. 2L72 4F RT 20060718001682006071800168SO 2006 7 18 2006FA0000641 120060623G8011MZ4204R STARTER PIPER PA23 PA23160 7102304SO LYC O320 O320* 41508EA ENGINE MISOVERHAULED D K NONE W INADEQUATE Q C ININSP/MAINT 1 NM033341P 231294 UPON RECEIPT OF STARTER, INITIAL INSPECTION REVEALED LOOSE HARDWARE ATTACHING FRONT HOUSING TO STATOR HOUSING. DISASSEMBLED UNIT AND FOUND TWO PIECES OF SOLDER IN ARMATURE AREA; ONE APPROX .2500 X .7500 X .0625 INCH, THE SECOND APPROX .2500 INCH X 2 INCHES X .0625 INCH. ALSO FOUND 1 OF 4 BRUSHES NOT SEATED IN BRUSH HOLDER AND NOT IN CONTACT WITH COMMUTATOR. FASTENER HOLES IN STATOR HOUSING WERE STRIPPED AS THOUGH FASTENERS WERE OVER-TORQUED TO SEAT FRONT HOUSING IN STATOR HOUSING. RECOMMEND RE-EVALUATE OVERHAUL PROCEDURES, QUALITY CONTROL, AND POST-OVERHAUL TEST PROCEDURES. RECOMMEND ALL OPERATORS CAREFULLY INSPECT COMPONENTS RECEIVED BEFORE INSTALLING ON AIRCRAFT. 1L72 3O3 O 1A10 E274 20060719000022006071900002EU 2006 7 19 2006FA0000643 120060609G275050B275103B ROD AMD FALC50FALCON50MYST2730106EU GARRTTTFE731TFE731* 01518WP TE FLAPS CHAFED B JGVRK NONE O OTHER ININSP/MAINT 1 CE0985TN 6712 237 WHEN COMPLYING WITH SB, FOUND FLAP ROD LOCATED IN RT MAIN LANDING GEAR COMPARTMENT CHAFFED AT IB END. FLAP ROD STIRRUP INSTALLED INCORRECT CAUSING ROD TO CHAFFE WHEN FLAPS ARE OPERATED. REMOVED STIRRUP REPOSITIONED 180 DEGREES. REINSTALLED AND REPLACED FLAP ROD WITH NEW. (K) 2L73 4F4 F A46EU E6WE 20060719000162006071900016CE 2006 7 19 2006FA0000644 120060628G531110581002367 FRAME BEECH 76 76 1153005CE FUSELAGE CORRODED D K NONE O OTHER ININSP/MAINT 1 SW996720T9119 ME335 A-FRAME TUBE ASSY FAILED AT CORROSION PREVENTION PORT CAUSING LT MAIN GEAR COLLAPSE. (K) 1L72 3O A29CE 20060718001712006071800171CE 2006 7 18 2006FA0000646 120060628G534320410201 SUPPORT CESSNA177 177RG 2073709CE LYC O360 IO360A1B6 41514EA MLG BROKEN C K NONE O OTHER ININSP/MAINT 1 WP09177R 4400 177RG0955 MLG ACTUATOR SUPPORT WEB BROKEN AND CRACKED. (K) 1H71 3O3 O A20CE 1E10 20060719000032006071900003CE 2006 7 19 2006FA0000647 120060628G323320410202 PIN CESSNA177 177RG 2073709CE LYC O360 IO360A1B6 41514EA MLG ACTUATOR BROKEN C K NONE O OTHER ININSP/MAINT 1 WP09177R 4400 177RG0955 ACTUATOR RETAINING PIN, FRACTURED. (K) 1H71 3O3 O A20CE 1E10 20060719000082006071900008CE 2006 7 19 2006FA0000648 120060614G279735823071 CONNECTOR BEECH MU300 400A 1155402CE WIRE HARNESS DAMAGED B E81RK NONE O OTHER ININSP/MAINT 1 GL03907JE RK107 INVESTIGATED REPORT OF FLAP ASYMMETRY ANNUNCIATOR LIGHT FLICKERING IN-FLIGHT. FOUND WIRE C458A22 ROUTED SO THAT EXCESSIVE WIRE TENSION AT P156 PLUG WAS CAUSING INTERMITTENT CONTACT WITH A156 PC BOARD J1 CONNECTOR. REROUTED WIRING AS REQUIRED FOR REVEALING WIRE TENSION AT P156 PLUG. FLAP ASSYMETRY FUNCTIONAL TEST SATISFACTORY. (K) 2H72 4F RTA16SW 20060719000172006071900017CE 2006 7 19 2006FA0000649 120060622G21301013840283 SWITCH BEECH 90 C90 1152913CE PWA PT6 PT6A60A 52043NE CABIN PRESSURE OUT OF LIMITS B E81RK NONE O OTHER ININSP/MAINT 1 GL03261GB4490 LJ1119 DURING SCHEDULED 12 MONTH TEST OF CABIN ALTITUDE WARNING SYSTEM FOUND BAROMETRIC SWITCH OPERATING OUT OF SPECIFIED MM. REPLACED PN 1013384028-3 SWITCH ASSY. CABIN ALTITUDE WARNING TESTS WITHIN SPECIFIED SERVICE LIMITS ON RETEST. SUGGEST A SB BE ISSUED TO REPLACE OLDER PN BAROMETRIC SWITCHES THAT TEND TO FAIL BETWEEN TEST PERIODS WITH MORE RELIABLE SWITCHES. (K) 1L72 3T4 T 3A20 E4EA 20060718001592006071800159 2006 7 18 2006FA0000650 420060620G2312CI108 ANTENNA BEECH MU300 400A 1155402CE PWA JT15 JT15D5 52112NE FUSELAGE DEBONDED B E81RK NONE O OTHER ININSP/MAINT 1 GL03731TA RK273 INVESTIGATED PILOT REPORT OF LOSS OF NR 1 AND NR 2 VHF COMMUNICATION RADIOS WHEN FLYING IN PRECIPITATION. IAW P-STATIC TESTING FOUND POOR NR 1 AND NR 2 VHF ANTENNAS BONDS TO FUSELAGE. CLEANED, REBONDED AND REINSTALLED ANTENNAS. ALSO INSTALLED LT FUEL VENT LINE BONDING JUMPER. P-STATIC TESTS AND OPERATIONAL TESTS SATISFACTORY AFTER REPAIRS. SUGGEST VHF ANTENNAS BE REMOVED AND CLOSELY INSPECTED AT SCHEDULED INTERVALS, SUCH AS AN INITIAL 5000 HR OR 10 YEAR INSPECTION, FOLLOWED BY RECURRING 1200 HR OR 2 YEAR INTERVALS (IN CONUNCTION WITH C-CHECK INSPECTIONS). 2H72 4F4 FRTA16SW E25EA 20060721002982006072100298NE 2006 7 21 2006FA0000651 220060628G72503028601 BLADE PWA JD15 JT15D1A NE ENGINE SEPARATED D K NONE O OTHER ININSP/MAINT 1 SW15 2818 PCE76791 DURING POST LEASE INSPECTION, FOUND 1 HIGH TURBINE BLADE SEPARATED AT MID SPAN. APPARENTLY NO OPERATIONAL PROBLEMS. MFG HAS PRODUCED REPLACEMENT BLADES UNDER SPARE PARTS BULLETIN 75. (K) 4 F E25EA 20060711001122006071100112CE 2006 7 11 2006FA0000652 120060601G2620 GAUGE LEAR 45 45LEAR 5170805CE GARRTTTFE731TFE7315BR WP FIRE BOTTLE BROKEN B KW3RK NONE O OTHER ININSP/MAINT 1 WP07456Q 282 THIS THE THIRD FIRE BOTTLE FOUND, ON 2 DIFFERENT AIRCRAFT WITH THE PRESSURE GAUGE SCALE BROKEN FREE FROM ITS MOUNTED POSITION. THE RESULT WAS A FALSE INDICATION OF AGENT (HALON CBRF3) PRESENT INSIDE THE BOTTLE. THE LOCAL QA MANAGER IS LAUNCHING A FORMAL INVESTIGATION WITH THE MFG QA. FORTUNATELY THIS AC WAS NOT INVOLVED IN AN ACCIDENT OR INCIDENT. GOOD ROOT CAUSE ANALYSIS AND CRITICAL THOUGHT FOUND THIS DEFECT. (K) 2L72 4F4 FRTT00008WIE6WE 20060721001322006072100132 2006 7 21 2006FA0000653 220060626G7414 SLICK B WS9RK NONE O OTHER ININSP/MAINT 1 NM07 05111170 HIGH MAGNETO DROP. (K) 20060719000062006071900006 2006 7 19 2006FA0000654 120060621G81204066109005 TURBOCHARGER ENGINE LEAKING B WS9RK NONE O OTHER ININSP/MAINT 1 NM07 LEAKING BETWEEN HOT AND COLD SECTION. (K) 20060718001652006071800165GL 2006 7 18 2006FA0000655 120060608G3210750B POWERPACK BLANCA1419 1419 1220402GL LYC O435 O435A 41516EA LANDING GEAR STUCK G K NONE O OTHER ININSP/MAINT 1 NM096561N 2014 RELIEF VALVE IN LANDING GEAR POWER PACK WAS STUCK. WOULD NOT ALLOW LANDING GEAR HYDARULIC SYSTEM PRESSURE TO BE RELIEVED TO ALLOW GEAR TO EXTEND. RESULT GEAR UP LANDING. POST INCICENT TESTING VALVE WORKED NORMALLY. (K) 1L71 3O3 O 1A3 E228 20060718001662006071800166NE 2006 7 18 2006FA0000656 220060620G7200TFE73160 ENGINE AMD FALC90FALCON900EX 2730009EU GARRTTTFE731TFE73160 NE NR 1 DAMAGED G A UNSCHED LANDING XJ ENGINE FLAMEOUT WARNING INDICATION DEDESCENT 1 SO19977LP1317 77 P112347 AT FL350, AIRCRAFT EXPERIENCED A LOUD BANG AND FAILURE OF NR 1 ENGINE (ITT WENT TO RED AND N1 APPROXIMATELY 20 PERCENT). ENGINE WAS SHUTDOWN. DURING DESCENT EXPERIENCED VIBRATION IN AIR FRAME AND CONTROL COLUMN. POST FLIGHT INSPECTION REVEALED EXTENSIVE DAMAGE TO THE NR 1 ENGINE REAR TURBINE BLADES AND COOKIE CUTTER. NO EXTERNAL DAMAGE WAS NOTED. ENGINE WAS REPALCED. (K) 2L73 4F4 FRTA46EU E1NM 20060721001562006072100156NM 2006 7 21 2006FA0000657 120060720G575165192613 SUPPORT BOEING727 72725C 138400HNM PWA JT8 JT8D5 52046NE LT AILERON CRACKED B NP1YK NONE O OTHER ININSP/MAINT 1 EA33932UP53694 19856 DURING C-CHECK ROUTINE INSPECTION A 1 INCH CRACK (APPROX) WAS FOUND IN LT OB AILERON LOCKOUT MECHANISM SUPPORT ASSY CASTING IN THE RADIUS AREA OF THE AILERON CRANK PIVOT POINT. SUPPORT ASSY IS BEING REPLACED BY ASSY PN 65-2177613. (K) 2L73 4F4 F A3WE E2EA 20060719000042006071900004SO 2006 7 19 2006FA0000658 220060710G7313652312112E NOZZLE TCRAFTBC BC12D 8850316GL CONT O550 IO550N 17042SO FUEL SYSTEM CRACKED G K NONE O OTHER ININSP/MAINT 1 NE03716B 7919 DURING MAINTENANCE THE MECHANIC WAS REPLACING THE FUEL INJECTION NOZZLES DUE TO THE REQUEST OF THE OWNER. THE OWNER WANTED TO INSTALL A NEW KIT THE POSITION-TUNED FUEL INJECTION NOZZLES IAW THE ID SID05-7. DURING THE INSTALLATION OF THESE NOZZLES 1 CRACKED PRIOR TO REACHING THE TORQUE VALUE AS LISTED IN SID05-7. 1H71 3O3 O A696 E3SO 20060719000202006071900020EA 2006 7 19 2006FA0000660 220060710G7414 BUSHING PIPER PA32 PA32300 7103212SO LYC O540 IO540* 41532EA MAGNETO FAILED D B EMER. DESCENT RJ PARTIAL RPM/PWR LOSS WARNING INDICATION NRNOT REPORTED 1 SW0770746469 469 H279705FR 3240521 MAGNETO'S DISTRIBUTOR GEAR BUSHING FAILED RESULTING IN AN ACCIDENT. MAGNETO LAST OVERHAULED EIGHT YEARS BEFORE. DFW06LA172 1L71 3O3 O A3SO 1E4 20060725001832006072500183 2006 7 25 2006FA0000662 120060629G6510538715 SHAFT TAIL ROTOR CRACKED C K NONE O OTHER ININSP/MAINT 1 WP23 MAGNETIC PARTICLE INSPECTION 7 PCS WITH TRANSVERSE CRACKS INDICATIONS ON O.D. OF THE PART 20060718001702006071800170CE 2006 7 18 2006FA0000665 120060711G3220 LANDING GEAR BEECH 35 35BEECH 1151502CE NOSE COLLAPSED C K NONE O OTHER ININSP/MAINT 1 SW99 D2053 NOSE LANDING GEAR COLLAPSED. 1L71 3O A777 20060725002392006072500239SO 2006 7 25 2006FA0000666 220060623G8550629218 IMPELLER CESSNA206 TU206F 2073353CE CONT O520 TSIO520M 17040SO MCAULYD3A34 D3A34C401 GL OIL SYSTEM MISMANUFACTURED C K NONE W INADEQUATE Q C ININSP/MAINT 1 WP075090138 U20601951 532305 972059 INSTALLED NEW ENGINE FOLLOWED RECOMMENDED PROCEDURES FOR BREAK IN. REMOVED & CUT OPEN OIL FILTER AT 1.4 HRS TTSN, AT 7.9HRS, & AT 24.7HRS. NORMAL PRACTICE WITH A NEW OR OVERHAULED ENGINE. EACH TIME FILTERS WERE NORMAL FOR A NEW ENGINE. ACFT DUE A 100 HR INSPECTION AT 38.9HRS TTSN. DURING INSPECTION, EXCESSIVE METAL APPEARED TO BE BRASS NOTED IN OIL FILTER. TOOK OFF STARTER DRIVE & FOUND NO PROBLEMS. TOOK OFF ROCKER COVERS TO SEE IF A ROCKER ARM BUSHING BAD. DISCOVERED THAT BUSHINGS IN OIL PUMP DRIVEN IMPELLER EXCESSIVELY WORN. IMPELLER WOULD CONTACT AN EDGE WITHIN PUMP. RECEIVED NEW PUMP ASSY. BEFORE INSTALLING PUMP PREFORMED DIMENSIONAL INSPECT OF IMPELLER & SHAFT, WITHIN NEW PARTS LIMITS. FLEW THE ACFT FO1H71 3O3 O A4CE E8CE 5 CP47GL 20060718001732006071800173EA 2006 7 18 2006FA0000667 220060707G731415473 PUMP AMTR VANRV4VANSRV4 GL LYC O360 IO360A1A 41514EA HARTZLHCM2Y HCM2YR GL FUEL SYS FAULTY G A UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CLCLIMB 1 GL11342MG19 1863 L136451A T/O ROLL OK, ENG STARTED LOSING PWR JUST AFTER T/O AT APROX 150 FT, DETECTED A SLIGHT MISS OR LOSS OF PWR, MADE A SHARP LT TURN , ENG CONTINUED TO LOSE PWR, SWITCHED ON BOST PUMP AT THIS TIME, ENG SEEMED TO RESPOND FOR A SECOND, BUT CONTINUED TO LOSE PWR, MADE ANOTHER LT, LANDED, PULLED AC BACK TO HANGER. AC HAS VISION VM1000 INSTRUMENT. CKD LAST FLT READINGS, FUEL PRES LOW 18 PSI, HIGH OF 29 PSI. RESTARTED ENG, IDLE WAS OK, FUEL PRESS WAS JUMPING FROM 20 TO 31 PSI. PWR WAS INCREASED TO FULL PWR, HELD APROX 30 SECONDS, ENG STARTED LOSING PWR, BOOST PUMP ON NO CHANGE. TURNED BOOST PUMP OFF, WATCHED FUEL PRESS, IT WAS JUMPING FROM 19 TO 31 PSI THEN DOWN TO 23. BYPASSED ENG DRIVEN PUMP AND ENG RAN, HELD PWR. 1L71 3O3 O EXPA1L711E10 5 CP43GL 20060718001812006071800181 2006 7 18 2006FA0000668 420060630G6113 SPINNER BEECH 300 300BEECH 1152930CE HARTZLHCB4M HCB4MP3 GL RT PROPELLER BROKEN B K NONE O OTHER ININSP/MAINT 1 NE05603WM FA198 FWA2935 RT PROPELLER WAS OVERHAULED AND INSTALLED IN THE RT POSITION. ENGINE RAN TO LEAK CHECK AND FUNCTIONAL CHECK PROPELLER SYSTEM ON THE RT SIDE AND TO FULL POWER FOR APPROXIMATELY 60 SECONDS. A SLIGHT CHANGE IN THE HARMONICS WAS NOTED BUT NOT A SIGNIFICANT CHANGE. AIRCRAFT RETURNED TO HANGER AFTER THE MAINTENANCE RUN UP AND A LEAK CHECK WAS PERFORMED. IT WAS NOTED THAT ONE BLADE HAD A LARGE AMOUNT OF GREASE ON THE BLADE FACE. THE SPINNER WAS REMOVED AND IT WAS FOUND BY VISUAL INSPECTION THAT A BLADE CLAMP BOLT HAD BROKEN AT THE HEAD. THE HEAD OF THE BOLT WAS RECOVERED LODGED IN THE HUB AND BULKHEAD AREA. THE BOLT P/N ACA-1372. 2L72 4T A24CE 6 CP56GL 20060719000112006071900011CE 2006 7 19 2006FA0000669 120060712G3211NAS15288 CONE BOLT CESSNA188 188B 2073007CE LT MLG FAILED G D RETURN TO BLOCK O OTHER TXTAXI/GRND HDL 1 SW174996R 18802483T LT LANDING GEAR STRUT IB ATTACHMENT BOLT HEAD POPPED OFF DURING TAXI CAUSING PARTIAL GEAR COLLAPSED 1L71 3O A9CE 20060719000182006071900018 2006 7 19 2006FA0000670 420060622G3460 COMPUTER AMD FALC50FALCON2000 2730170NM FLT MANAGEMENT INTERMITTENT B A UNSCHED LANDING GJ MULTIPLE FAILURE WARNING INDICATION CRCRUISE 1 SW11620MS 31 ALL 3 FMS INTERMITTENTLY RESETS IN FLIGHT WITH INFORMATION RETURNING AT RANDOM. 2K72 4F RTA50NM 20060719000192006071900019 2006 7 19 2006FA0000671 220060627G74146364 MAGNETO ENGINE FAILED B S4CRK NONE O OTHER ININSP/MAINT 1 WP25 DEFECTIVE COIL WINDINGS FOUND. SECONDARY READINGS INDICATE DISCONTINUOUS INTERNAL CONDUCTORS. READINGS VARIED FROM NO RESISTANCE (INDICATING AN OPEN CIRCUIT) TO VERY HIGH, OUT OF TOLERANCE OHMS OF RESISTANCE (20 TIMES NORMAL). OHMMETER WAS CALIBRATED RECENTLY, CROSS REFERENCED AGAINST OTHER COILS TO VERIFY TEST EQUIPMENT USED, WAS STILL FUNCTIONING DURING THIS INSP. OPERATOR OF THIS COMPONENT REPORTED NO DETECTABLE OPERATIONAL MALADIES. SECONDARY WINDING FAILURES MAY AFFECT ENG STARTING, PRODUCE MISFIRING, OR NON-OPERATIONAL IGNITION FROM THE AFFECTED MAGNETO. O.E.M. TYPE (TORQUE SEAL) PRODUCT INTACT AT TIME OF INSP, INDICATING NO INTERNAL MAINT OR INSP SINCE MAGNETO WAS MANUFACTURED. 20060719000862006071900086CE 2006 7 19 2006FA0000672 120060104G3260IN4001 DIODE CESSNA210 210M 2073450CE CONT O520 IO520L 17032SO MCAULY3A32C D3A32C88 GL WARNING UNIT INOPERATIVE G O OTHER N FALSE WARNING LDLANDING 1 SO19LVWHD 21061943 270473R 900308 DURING LANDING, FORGOT TO EXTEND THE LANDING GEAR AND GEAR UP LANDING WAS CARRIED OUT. ACCIDENT INVESTIGATION INCLUDED A SATISFACTORY OPS CHECK OF LANDING GEAR RETRACTION/EXTENSION SYSTEM, BUT WARNING HORN FAILED TO OPERATE. AFTER DISASSEMBLING THE WARNING UNIT ASSEMBLY, A BURNED DIODE WAS FOUND OUT. THEN CONSULTED SM AND REALIZED THAT THERE IS NOT A SPECIFIC ITEM TO CHECK THE OPERATION OF THE GEAR WARNING HORN. THIS SITUATION ALSO TAKES PLACE WITH MFG SRM. GEAR INDICATOR LIGHT AND WARNING HORN-CHECK FOR OPERATION (GEAR EXTENDED AND RETRACTED). 1H71 3O3 O 3A21 E5CE 5 CP21EA 20060721001302006072100130WP 2006 7 21 2006FA0000673 220060316G726031080412 BEARING GARRTT SWRNGNSA227 SA227AC 8780603SW GARRTTTPE331TPE33111U 01514WP ENGINE CORRODED B X2ZRK NONE O OTHER ININSP/MAINT 1 GL25438MA P44090C AC721B P44090C DUE TO CHIP LIGHT ILLUMINATION. TEST RUN COMPLETED. TORQUE SYS CALIBRATION AND ALL REQUIRED FUNCTIONAL/LEAK CHECKS CARRIED OUT. NEW TORQUE DATA ISSUED. NTS TRIF CK REQUIRED PRIOR TO RETURN TO SERVICE. PERFORMED SOAP SAMPLE WITHIN 10-25 OPERATING HRS. FAILURE OF ACCY GEAR ASSY BRG WAS ATTRIBUTED TO RUST PITTING ON ROLLING ELEMENT SURFACES. SIMILAR PITTING WAS FOUND ON FWD PROP SHAFT BRG WITH SPALLING. LOOSENING OF ONE PLANETARY PIN CAUSED CHAFFING OF PIN AND SCORING OF CARRIER. ALL REMAINING BRGS IN ENGINE WERE DISASSEMBLED FOR INSP. ALL BRGS WITH RIVETED CAGES WHICH DID NOT ALLOW FOR INSP WERE REPLACED AS A PRECAUTIONARY MEASURE DUE TO SUSPECTED RUST PITTING. 2L72 4T4 TRTA8SW E4WE 20060721003712006072100371CE 2006 7 21 2006FA0000674 120060612G2720031019613 SPRING CESSNA150 152 2071835CE LYC O235 O235* 41505EA RUDDER PEDALS BROKEN B C85RO OTHER F FLT CONT AFFECTED CRCRUISE 1 NE0194467677 15285682 FLIGHT INSTRUCTOR WAS DEMO-ING A STALL TO STUDENT. MANUVER STARTED AT 2700 FT. CONTROLS LOCKED UP- AC WENT NOSE DOWN. FLT INST RECOVERED AT 700 FT. (K) 1H71 3O3 ONT3A19 E223 20060721001312006072100131EA 2006 7 21 2006FA0000675 220060703G8540 BUSHING MOONEYM20 M20J 5870219SW LYC O360 IO360A3B6 41514EA ENGINE SPUN B X18RK NONE O OTHER ININSP/MAINT 1 NE013860H932 241044 L2178051A FOUND DURING ANNUAL INSP, AN ALUMINUM BUSHING THAT IS LOCATED IN ACCESSORY CASE, WHERE MAGNETO DRIVE GEAR IS LOCATED HAD BECOME LOOSE IN CASE AND SPUN. FOUND THIS PROBLEM, WERE NOT ABLE TO INSTALL MAGNETO CORRECTLY, WHEN MAGNETO WAS INSTALLED, IMPULSE COUPLING WOULD SOMETIMES NOT ENGAGE. FOUND AT LAST OVERHAUL, ACCESSORY CASE WAS SENT OUT FOR OVERHAUL TO ECI. TALKING TO TEAR DOWN PERSONNEL, SAID THAT THIS IS AN APPROVED REPAIR TO INSTALL AN ALUMINUM BUSHING IF IT IS DONE CORRECTLY, THERE SHOULD HAVE BEEN A DRILLED HOLE IN THE BUSHING FOR LUBRICATION, BUT NO HOLE. THUS NOT ALLOWING LUBRICATION TO BUSHING AREA, ALLOWING EXCESSIVE WEAR AND PART FAILURE. SUGGEST WELDING AREA AND DRILLING NEW BOSS. (K) 1L71 3O3 O 2A3 1E10 20060721001632006072100163EU 2006 7 21 2006FA0000676 120060706G6123A3496 SPRING STBROSSD3 SD360 8100606EU HARTZLHCB5M HCB5MP3 GL FEATHER SYSTEM BROKEN B ME4RK NONE O OTHER ININSP/MAINT 1 SO19 156193801 EV755 FEATHERING SPRING WAS FOUND TO BE BROKEN WHILE STILL INSTALLED IN SPRING KIT. THE SPRING BROKE IN 3 DIFFERENT PIECES. KIT WAS DISASSEMBLED AND INSPECTED FOR FURTHER DAMAGE. NOTE: PROPELLER WAS REMOVED FROM SERVICE 08-DEC-00. (K) 2H72 4T A41EU 6 CP44GL 20060721001372006072100137GL 2006 7 21 2006FA0000677 120060701G782014836001 MUFFLER CIRRUSSR SR22 2130001GL CONT O550 IO550N 17042SO EXHAUST DETERIORATED C QRQRK NONE O OTHER ININSP/MAINT 1 SW05752C 0421 686750 REPLACED LT MUFFLER ON AIRCRAFT DO TO THE DETERIORATED CONDITION OF THE SPARK ARRESTER INSIDE OF THE MUFFLER. LT SIDE SPARK ARRESTER MELTED AND FOLDED OVER. LT MUFFLER, PN 14836001. THE FIRST DETECT REPORT WAS FILED WHEN AC HAD A TT 682 HRS. BOTH LT AND RT SPARK ARRESTERS HAD FOLDED OVER AGAIN. THATS 413 HRS SINCE LAST TIME. RECOMMEND MANDITORY REPLACEMENT AT A SPECIFIED TIME OR REDESIGN OF ARRESTERS. (K) 1L71 3O3 ONTA00009CHE3SO 20060725002432006072500243SO 2006 7 25 2006FA0000678 120060713G32107521604 FORK PIPER PA42 PA421000 7104225SO GARRTTTPE331TPE331* 01514WP LT MAIN GEAR CRACKED D FO7RK NONE O OTHER ININSP/MAINT 1 SO134WE 1934 425527041 PILOT REPORTED A LEAKING LT MAIN GEAR STRUT, BUT WAS LEAKING FROM JOINT BETWEEN ALUMINUM FORK ASSY AND CHROMED STEEL STRUT TUBE. STRUT DISASSEMBLED AND A RADIAL CRACK WAS FOUND, 2 INCH LOGN AND .5 INCH. BELOW TOP OF ALUMINUM FORK ASSY. A SERIOUS ACCIDENT COULD RESULT IF THE FORK ASSY DETACHED UPON LANDING. NO DAMAGE OR HARD LANDINGS REPORTED. (K) 1L72 4T3 TRTA23SO E2WE 20060721003302006072100330EA 2006 7 21 2006FA0000679 220060626G7260 CHIP DETECTOR BELL 412 412EP 1182205SW PWA PT6 PT6* 52043EA NR 1 ENGINE CONTAMINATED C A UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 SO15413EV 36381 CPPSTH0691 AC EXPERIENCED NR 1 ENG CHIP LIGHT. MASTER CAUTION WAS EXTINGUISHED, LIGHT WENT OUT. ABOUT 2 SECONDS LATER LIGHT CAME BACK ON WITH MASTER CAUTION, WAS AGAIN EXTINGUISHED, WENT OUT THEN CAME BACK ON. PILOT ELECTED RETURN TO BASE. AFTER LIGHT CAME ON AGAIN FOR 4TH OR 5TH TIME IN 2 MINUTES, PILOT DECIDED TO SECURE ENG, FUEL VALVES AND BOOST PUMPS WERE LEFT ON, IN EVENT THAT THEY NEED TO RESTART ENG. ENG HAD JUST COME OUT OF 300 HR INSP, FLIGHT TO BASE, LANDING WAS UNEVENTFUL. MAINT WAS DISPATCHED, INSPECTED CHIP PLUGS, FOUND A SMALL SILVER ON PLUG. SILVER WAS REMOVED, CHIP PLUG WAS REINSTALLED, SAFETY WIRED. AC WAS 20 MINUTE RUN CHECK FOR ANY ADDITIONAL CHIP LIGHTS AND WAS RELEASED BACK INTO SERVICE. (K) 1G72 4U3 T H4SW E2NE 20060721002972006072100297CE 2006 7 21 2006FA0000680 120060622G2510551900922 SEAT FRAME CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE CHAIR CRACKED B K NONE O OTHER ININSP/MAINT 1 CE05982NA 5500345 UPPER CHAIR BASE ASSEMBLY CRACKED AT CHAIR BACK ATTACH POINTS. CHAIR WAS REPAIRED IAW STRUCTURAL SEAT REPAIR. (K) 1L72 4F4 F A22CE E1NE 20060721003242006072100324CE 2006 7 21 2006FA0000681 120060601G521005170392 HANDLE CESSNA206 U206F 2073333CE REAR DOOR DEFECTIVE D K NONE O OTHER ININSP/MAINT 1 AL05736 U20601781 DOOR HANDLE WAS SPINNING INDEPENDENTLY OF THE MECHANISM FOR THE DOOR LATCH. THE PORTION OF THE HANDLE WITH THE SPLINE IS PRESSED INTO THE HANDLE. THE PRESS FIT WAS DEFECTIVE ALLOWING THE HANDLE TO SPIN FREELY. (K) 1H71 3O A4CE 20060724000392006072400039SO 2006 7 24 2006FA0000682 220060717G8520 CRANKCASE CONT CESSNA401 401B 207590ECE CONT O520 TSIO520E 17040SO ENGINE CRACKED E K NONE O OTHER ININSP/MAINT 1 SW177916Q798 798 182575 401B0016 182575 FOUND A CRACK IN BOTH CASE HALF AT THE FOURTH AFT BOLT HOLE FROM FRONT OF CASE AT 12 O'CLOCK POSITION. CRACKS WERE FOUND ON AN INSPECTION OF ENGINE. 1L72 3O3 O A7CE E8CE 20060724000572006072400057SO 2006 7 24 2006FA0000683 220060717G8520 CRANKCASE CONT CESSNA401 401B 207590ECE CONT O520 TSIO520E 17040SO ENGINE CRACKED E K NONE O OTHER ININSP/MAINT 1 SW177916Q798 798 182575 401B0016 182575 FOUND A CRACK IN BOTH CASE HALVES AT THE FOURTH AFT BOLT HOLE FROM FRONT OF CASE AT 12 O'CLOCK POSITION. CRACKS WAS FOUND ON AN INSPECTION OF ENGINE. 1L72 3O3 O A7CE E8CE 20060725001852006072500185CE 2006 7 25 2006FA0000684 120060717G555104320052 FITTING CESSNA150 150M 2071830CE LYC O320 O320E2D 41508EA RT STAB MISINSTALLED D K NONE O OTHER ININSP/MAINT 1 GL077765U5510 15077837 ON PREFLIGHT INSP, APPLIED A +/- 5 LB UP AND DOWN FORCE ON RT STABILIZER TIP, HEARD A GRUNTING SOUND. FURTHER INVESTIGATION REVEALED A SMALL RELATIVE MOTION BETWEEN STABILIZER AFT FITTING, 0432005-2, AND FUSELAGE. REMOVING NUT OPENED A 0.020 INCH AIR GAP BETWEEN FITTING AND FUSELAGE. CLEANING GAP WITH A CLOTH DIDN’T SHOW ANY METAL PARTICLES. THE FIX WAS TO FABRICATE A 0.020 INCH SHIM. THIS FITTING IS A VERY RIGID CHANNEL SUCH THAT IF THERE WAS AN AIR GAP IT MAY NOT CLAMP ON TO THE FUSELAGE FITTING HARD ENOUGH WITH BOLT TORQUE. THIS MAY NOT BE A DEFECTIVE PART, JUST TOLERANCE STACK UP. LEFT SIDE FITTING WAS CHECKED. IT REQUIRED A 0.010 INCH SHIM. THESE 2 AFT MNT POINTS ARE LOAD CYCLED MORE FREQUENTLY. 1H71 3O3 O 3A19 E274 20060725001862006072500186CE 2006 7 25 2006FA0000685 120060717G555104320052 FITTING CESSNA150 150M 2071830CE LYC O320 O320E2D 41508EA RT STAB LOOSE D K NONE O OTHER ININSP/MAINT 1 GL077765U5510 15077837 ON PREFLIGHT INSP, APPLIED A +/- 5 LB UP AND DOWN FORCE ON RT STABILIZER TIP AND HEARD A GRUNTING SOUND. FURTHER INVESTIGATION REVEALED A SMALL RELATIVE MOTION BETWEEN STABILIZER AFT FITTING, 0432005-2, AND FUSELAGE. REMOVING NUT, OPENED A 0.020 INCH AIR GAP BETWEEN THE FITTING AND FUSELAGE. CLEANING GAP WITH A CLOTH DIDN’T SHOW ANY METAL PARTICLES. FIX WAS TO FABRICATE A 0.020 INCH SHIM. FITTING IS A VERY RIGID CHANNEL THAT IF THERE WAS AN AIR GAP IT MAY NOT CLAMP ON TO FUSELAGE FITTING HARD ENOUGH WITH BOLT TORQUE. THIS MAY NOT BE A DEFECTIVE PART, JUST TOLERANCE STACK UP. LT SIDE FITTING WAS CHECKED. IT REQUIRED A 0.010 INCH SHIM.THESE 2 AFT MOUNTING POINTS ARE LOAD CYCLED MORE FREQUENTLY. 1H71 3O3 O 3A19 E274 20060724000862006072400086GL 2006 7 24 2006FA0000686 320060714G6110ACA1373 NUT HARTZLHCB4M HCB4M GL PROPELLER FAILED B JGVRK NONE O OTHER ININSP/MAINT 1 CE09 FWA2178 WHEN TORQUING OUTER CLAMP NUT P/N ACA1373, 1 EACH NEW OUTER CLAMP NUT THREADS FAILED BEFORE REACHING SPECIFIED TORQUE. PROPELLER WAS BEING REASSEMBLED DURING OVERHAUL. ASSEMBLED USING CALIBRATED TOOLS AND NEW HARDWARE. 6 CP56GL 20060725002492006072500249CE 2006 7 25 2006FA0000687 120060714G5347 SEAT TRACK CESSNA180 180A 2072604CE DAMAGED H O OTHER O OTHER NRNOT REPORTED 1 WP23180LG 32693 A BOLT WAS INSTALLED ON THE FORWARD MOST HOLE ON THE SEAT TRACK FOR USE AS A FORWARD STOP. THE SEAT COULD BE POSITIONED OVER THE HOLE AND THE SEAT LOCKING PIN WOULD ENGAGE, BUT NOT FULLY DUE TO THE BOLT PASSING THROUGH THE HOLE. THE MFG DESIGN DOES NOT ALLOW THE PIN TO ENTER THROUGH THE SEAT STOP HOLE. 1H71 3O 5A6 20060725002522006072500252CE 2006 7 25 2006FA0000688 120060714G5347 SEAT CESSNA180 180A 2072604CE MISINSTALLED H O OTHER F FLT CONT AFFECTED TOTAKEOFF 1 WP23180LG 32693 A BOLT WAS INSTALLED ON THE FORWARD MOST HOLE ON THE SEAT TRACK FOR USE AS A FORWARD STOP. THE SEAT COULD BE POSITIONED OVER THE HOLE AND THE SEAT LOCKING PIN WOULD ENGAGE, BUT NOT FULLY DUE TO THE BOLT PASSING THROUGH THE HOLE. THE MFG DESIGN DOES NOT ALLOW THE PIN TO ENTER THROUGH THE SEAT STOP HOLE. 1H71 3O 5A6 20060724000432006072400043SO 2006 7 24 2006FA0000693 120060718G2910 CIRCUIT BREAKER PIPER PA46 PA46500TP 7104622SO COCKPIT OPEN B K NONE O OTHER DEDESCENT 1 EA0753667 4697158 DURING ROUTINE FLIGHT, GEAR WOULD NOT EXTEND UPON SELECTING GEAR LEVER DOWN. FOUND 25 AMP HYDRAULIC PUMP CIRCUIT BREAKER OPEN. RESET BREAKER AND GEAR OPERATED NORMALLY. GEAR OPERATED NORMAL FOR SEVERAL CYCLES AFTERWARD. HYDRAULIC SYSTEM WAS INSPECTED, INCLUDING CHECK FOR EXCESSIVE CURRENT DRAW WITH NO DISCREPANCY NOTED. INITIAL CURRENT DRAW ON PUMP SPIKES ABOVE THE 25 AMP LIMIT OF CB BUT IS WITHIN THE OPERATING LIMITS OF THE CB.THIS IS SECOND TIME THIS PROBLEM HAS BEEN NOTED ON THIS AIRCRAFT. THIS SAME SCENARIO HAS BEEN NOTED ON T2 OTHER AIRCRAFT. RECOMMEND REPLACEMENT OF CB TO HIGHER CURRENT ( 30 AMPS MINIMUM). THIS MAY REQUIRE PARTIAL REWIRING OF SYSTEM DUE TO INCREASED CURRENT. 1L71 3O RTA25SO 20060724000462006072400046SO 2006 7 24 2006FA0000694 120060718G2910 CIRCUIT BREAKER PIPER PA46 PA46500TP 7104622SO COCKPIT OPEN B K NONE O OTHER DEDESCENT 1 EA0753667 4697158 DURING ROUTINE FLIGHT, GEAR WOULD NOT EXTEND UPON SELECTING GEAR LEVER DOWN. FOUND 25 AMP HYDRAULIC PUMP CIRCUIT BREAKER OPEN. RESET BREAKER AND GEAR OPERATED NORMALLY. GEAR OPERATED NORMAL FOR SEVERAL CYCLES AFTERWARD. HYDRAULIC SYSTEM WAS INSPECTED, INCLUDING CHECK FOR EXCESSIVE CURRENT DRAW WITH NO DISCREPANCY NOTED. INITIAL CURRENT DRAW ON PUMP SPIKES ABOVE THE 25 AMP LIMIT OF CB BUT IS WITHIN THE OPERATING LIMITS OF THE CB.THIS IS SECOND TIME THIS PROBLEM HAS BEEN NOTED ON THIS AIRCRAFT. THIS SAME SCENARIO HAS BEEN NOTED ON TWO OTHER AIRCRAFT. RECOMMEND REPLACEMENT OF CB TO HIGHER CURRENT ( 30 AMPS MINIMUM). THIS MAY REQUIRE PARTIAL REWIRING OF SYSTEM DUE TO INCREASED CURRENT. 1L71 3O RTA25SO 20060725001962006072500196CE 2006 7 25 2006FA0000695 120060202G3040 CONNECTOR BEECH 200 200BEECH 1152920CE WINDSHIELD HEAT FAILED B HBKRK NONE O OTHER ININSP/MAINT 1 SW11440WA BB700 WHILE INVESTIGATING PILOTS AND CO-PILOTS WINDSHIELD HEAT BEING INOPERATIVE, CONNECTION AT DC PWR DISTRIBUTION PNL WAS AT FAULT. USING MFG WIRING DIAGRAM, CONNECTIONS AT JUNCT 195 AND PLUG 195 HAD BEEN SUBJECTED TO EXCESS HEATING TO POINT THAT WIRE AND WIRING INSULATION BEING BURNED AS A RESULT CONNECTIONS BEING LOOSE. STRAIN RELIEF FOR PLUG DOES NOT ENSURE A SECURE CONNECTION FOR 8 AWG WIRE TO MAINTAIN A POS CONTACT. END RESULT IS CONNECTIONS WORK LOOSE, BEGIN TO ARC. ARCING GENERATES HEAT. BURNING WIRE, CAUSING SOCKET CONNECTION, PIN TO BECOME BRITTLE AND WEAK. THIS FAILURE OF CONNECTION RENDER WINDSHIELD HEAT SYS INOPERATIVE. HEAT GENERATED FROM CONNECTION FAILURE CREATES A POTENTIAL FIRE HAZARD FOR AC. 1L72 4T A24CE 20060725002442006072500244CE 2006 7 25 2006FA0000696 120060210G2497 WIRE MTSBSIMU300 MU300 5780602CE PWA JT15 JT15D4 52112NE BURNED B BG5YK NONE O OTHER ININSP/MAINT 1 EA33109PW AO46SA PCE70800 SHORT CIRCUIT, WIRES BURNED ON LT CNTRL JUNCT BOX AREA. DURING SCHEDULED B INSP IAW MM, FOUND WIRES BURNED, DAMAGED ON CABLE LOOM CONNECTOR P AND J 230. DUE TO SHORT CIRCUIT ON TRIPLE WIRES, INSULATION OF SHIELD TERM SUSPECT ON CABLES LOOM CONNECTORS. SB MUST BE APPLIED WHICH MODIFIES SHIELDS GROUND TERM RELOCATION. ALL WIRES AT EFFECTED CONNECTORS TO BE IDENTIFIED, CIRCUITS CHECKED IAW AC WIRING DIAGRAM, CHECKED FOR CONTINUITY, INSULATION RESIST CHECKS ON ALL WIRES NOT ONLY TO DETERMINE IF ANY OF SCREENED CABLES ARE BREAKING DOWN BUT ALSO NOT BREAKING DOWN TO ADJACENT CABLES FURTHER DOWN WIRING LOOM IN AREAS THAT CAN NOT BE VISUALLY INSP DAMAGED WIRES REPAIRED, CONNECTORS REPLACED IAW MM. 2H72 4F4 FRTA14SW E1NE 20060725002052006072500205CE 2006 7 25 2006FA0000705 120060720G61009696001123 LINE BEECH 58 58 1152740CE LT PROPELLER CHAFED B K NONE O OTHER ININSP/MAINT 1 WP27870JA1717 TH2036 LT PROPELLER ACCUMULATOR OIL LINE WAS CHAFED BY THE SHROUD FOR THE FUEL PUMP HOSE. 1L72 3O 3A16 20060725002162006072500216CE 2006 7 25 2006FA0000706 120060720G61009696001123 LINE BEECH 58 58 1152740CE LT PROPELLER CHAFED B K NONE O OTHER ININSP/MAINT 1 WP25874JE1519 TH2045 LT PROPELLER ACCUMULATOR OIL LINE WAS CHAFED BY THE SHROUD FOR THE FUEL PUMP HOSE. 1L72 3O 3A16 20060725002182006072500218CE 2006 7 25 2006FA0000707 120060720G61009696001123 LINE BEECH 58 58 1152740CE LT PROPELLER CHAFED B K NONE O OTHER ININSP/MAINT 1 WP25876JK1449 TH2053 LT PROPELLER ACCUMULATOR OIL LINE WAS CHAFED THROUGH BY THE SHROUD FOR THE FUEL PUMP HOSE. OIL LEAK WAS OBSERVED. THE CAUSE WAS DETERMINED AND REMEDIED BEFORE LOSS OF SIGNIFICANT AMOUNT OIL. 1L72 3O 3A16 20060724000852006072400085SO 2006 7 24 2006FA0000710 220060720G8520 CRANKCASE CONT IO550B BEECH 36 A36 1151604CE CONT O550 IO550B SO ENGINE CRACKED D K NONE K FLUID LOSS ININSP/MAINT 1 WP258296R1320 8288849R E2763 828849R ENGINE CASE CRACKED NEAR (7TH) STUD BETWEEN CYLINDERS 2 AND 4. PROBLEM FOUND WHEN INVESTIGATING OIL LEAK. 1L71 3O3 O 3A15 E3SO 20060803000042006080300004EU 2006 8 3 2006FA0000714 120060713G554380483205801 ATTACH FITTING PIAGIOP180 P180 6960204EU PWA PT6 PT6A6 52043EA RUDDER TRIM CRACKED D K NONE O OTHER ININSP/MAINT 1 SO1329JS 923 1046 ON POST MAINTENANCE WALKAROUND INSPECTION, FOUND RUDDER TRIM TAB LOWER CONTROL ROD ATTACH LUG RADIALLY CRACKED. UNKNOWN CAUSE, NO OTHER DAMAGE OR DEFECTS NOTED. (K) 1H72 3O3 TRTA59EU E4EA 20060802001852006080200185CE 2006 8 2 2006FA0000715 120060619G3297TVA209 CAPACITOR BEECH 23 B24R 1151253CE GLARE SHLD FWD EXPLODED B BFYSA UNSCHED LANDING O OTHER TOTAKEOFF 1 NE056978R MC324 OPERATOR HAD DRAWN THE BATTERY CHARGE DOWN CONSIDERABLY TRYING TO START THE AIRCRAFT. PILOT REPORTED HEARING A POP AND REPORTED SMOKE ING CABIN. TAKEOFF WAS ABORTED AND AN EMERGENCY (GEAR UP) LANDING WAS MADE RESULTING IN SUBSTANTIAL DAMAGE TO AC. ON INSPECTION A CAPACITOR WAS FOUND SECURED TO THE REAR OF THE AUDIO CONTROL PANEL, THIS CAPACITOR WAS INSTALLED IN THE KN 4 CB WIRE. CAPACITOR HAD END BLOWN OUT AND ALL ITS CONTENTS SPLATTERED ON WINSHIELD AIR DUCT. LOW BATTERY CHARGE COUPLED WITH THE HIGH IN RUSH CURRENT DEMAND OF THE GEAR MOTOR OVER AND ABOVE THE NORMAL DEMANDS OF THE AVIONICS MOST LIKELY RESULTED IN AN OVER VOLTAGE CONDITION THAT CAUSED THE CAPACITOR TO EXPLODE. (K) 1L71 3O A1CE 20060803000492006080300049SW 2006 8 3 2006FA0000716 120060307G2622344 EXTINGUISHER BELL 206 206B 1181511SW ALLSN 250C 250C30 03013GL COCKPIT EXPLODED D I22FO OTHER O OTHER NRNOT REPORTED 1 SO23615LH 2263 A NEW 1.25 LB EXTINGUISHER MODEL 344, SN W-968052 CLASSIFICATION 2-B; C WAS INSTALLED IN THE AIRCRAFT ON MARCH 6, 2006. IT WAS REMOVED OVERNIGHT AND REINSTALLED AT 8:50 AM ON MARCH 7, 2006. AS THE HELICOPTER WAS STARTING, THE END EXPLODED OUT OF THE EXTINGUISHER, FIRING IT INTO THE CONSOLE. THE TEMPERATURE IN THE COCKPIT WAS APPROXIMATELY 36 DEGREES C AND THE EXTINGUISHER WAS IN THE SHADE. THE PRESSURE GAUGE WAS IN THE GREEN WHEN INSTALLED. (K) 1G71 3U3 U H2SW E1GL 20060803000082006080300008SO 2006 8 3 2006FA0000717 120060311G5712 RIB PIPER PA34 PA34220T 7103420SO CONT O360 TSIO360* 17025SO LEFT & RIGHT CRACKED B Q2ARK NONE O OTHER ININSP/MAINT 1 SW178164D5963 348233086 DURING COMPLIANCE WITH SB, LT AND RT RIBS FOUND CRACKED AS SUSPECTED. INSTALLED REPAIR KITS. LT DRAG BRACE PIVOT, PN 39479002, ALSO FOUND CORRODED AND CRACKED. THIS IS NOT PART OF SB INSPECTION. (K) 1L72 3O3 O A7SO E9CE 20060803001032006080300103 2006 8 3 2006FA0000718 420060713G2562DMELT6 ELT CESSNA210 T210N 2073456CE CABIN INOPERATIVE B GFVRK NONE O OTHER ININSP/MAINT 1 NM13178JD 21063351 FOUND ELT TOTALLY INOPERATIVE DURING ANNUAL INSPECTION, BATTERY VOLTAGE OK. UNABLE TO DETERMINE IF IMPACT SWITCH WAS ALSO INOPERATIVE. (K) 1H71 3O 3A21 20060803000102006080300010SO 2006 8 3 2006FA0000719 220060601G8530 EXHAUST VALVE CESSNA337 337B 2075706CE CONT O360 IO360CONT 17025SO NR 6 CYLINDER STUCK D K NONE O OTHER ININSP/MAINT 1 EA212362S 3370662 ENGINE RUNNING ROUGH. COLD COMPRESSION CHECK SHOWED -0- COMPRESSION ON NR 6 CYLINDER. AIR LEAKING PAST EXHAUST VALVE. DISASSEMBLY REVEALED EXHAUST VALVE STUCK IN OPEN POSITION. EVIDENCE OF PISTON STICKING EXHAUST VALVE. THIS IS THE SECOND OCCURANCE OF THIS CONDITION ON THIS ENGINE. (K) 1H72 3O3 O A6CE E1CE 20060803000452006080300045SO 2006 8 3 2006FA0000720 220060515G8530 EXHAUST VALVE CESSNA337 337B 2075706CE CONT O360 IO360CONT 17025SO NR 4 STUCK D K NONE O OTHER ININSP/MAINT 1 EA212362S275 AC05AC028 3370662 ENGINE RUNNING ROUGH. PERFORMED COLD COMPRESSION CHECK. COMPRESSION WAS ZERO. AIR LOOKING PAST EXHAUST VALVE. REMOVED ROCKER ARM COVER, NOTED EXHAUST VALVE STICKING IN OPEN POSITION. REMOVED CYLINDER. PISTON HAD STRUCK EXHAUST VALVE. REPLACED CYLINDER AND PISTON. PISTON WAS DIFFERENT THAN ORIGINAL PN WAS THE SAME, TOP OF PISTON WAS CONCAVE WHERE AS ORIGINAL PISTON WAS FLAT. (K) 1H72 3O3 O A6CE E1CE 20060802002762006080200276CE 2006 8 2 2006FA0000721 120060619G25205514551169 SEAT CESSNA501 501 2076603CE CABIN CRACKED D K NONE O OTHER ININSP/MAINT 1 CE05501CF 5010128 UPPER CHAIR BASE ASSEMBLY CRACKED AT CHAIR BACK ATTACH POINTS. ALSO, PREVIOUS INAPPROPRIATE REPAIR. CHAIR WAS REPAIRED IAW STC, STRUCTURAL SEAT REPAIR. (K) 1L72 4F A27CE 20060803000502006080300050 2006 8 3 2006FA0000722 220060725G74143975 MAGNETO ENGINE OUT OF TOLERANCEB S4CRK NONE O OTHER ININSP/MAINT 1 WP25 OUT OF TOLERANCE SECONDARY WINDINGS FOUND ON MAGNETO COIL. READINGS INDICATED VERY LOW RESISTANCE, WHICH FLUCTUATED WITH AMBIENT TEMPERATURE CHANGES. NORMAL READINGS FALL CLOSE TO 15,000 OHMS, WHEREAS THIS FAULTY COIL READ BETWEEN 2,000 OHMS, UP TO 5,000 OHMS. 13,000 OHMS IS DESCRIBED AS THE LOWEST READING ALLOWED BY THE MANUFACTURER OF THIS MAGNETO. THIS ISSUE WAS DISCOVERED DURING PREVENTIVE MAINTENANCE, WHICH INCLUDED INSPECTION OF MAGNETO INTERNALS. THE SN DATE CODE SUGGESTS THAT THIS MAGNETO WAS MANUFACTURED IN 1992. 20060803000992006080300099 2006 8 3 2006FA0000723 220060725G74143975 COIL SLICK MAGNETO OUT OF TOLERANCEB S4CRK NONE O OTHER ININSP/MAINT 1 WP25 92120190 OUT OF TOLERANCE SECONDARY WINDINGS FOUND ON MAGNETO COIL. READINGS INDICATED VERY LOW RESISTANCE, WHICH FLUCTUATED WITH AMBIENT TEMPERATURE CHANGES. NORMAL READINGS FALL CLOSE TO 15,000 OHMS, WHEREAS THIS FAULTY COIL READ BETWEEN 2,000 OHMS, UP TO 5,000 OHMS. 13,000 OHMS IS DESCRIBED AS THE LOWEST READING ALLOWED BY THE MANUFACTURER OF THIS MAGNETO. THIS ISSUE WAS DISCOVERED DURING PREVENTIVE MAINTENANCE, WHICH INCLUDED INSPECTION OF MAGNETO INTERNALS. THE SERIAL NUMBER DATE CODE SUGGESTS THAT THIS MAGNETO WAS MANUFACTURED IN 1992. 20060803001012006080300101 2006 8 3 2006FA0000724 220060725G74143975 COIL SLICK MAGNETO OUT OF TOLERANCEB K NONE O OTHER ININSP/MAINT 1 WP25 92120190 OUT OF TOLERANCE SECONDARY WINDINGS FOUND ON MAGNETO COIL. READINGS INDICATED VERY LOW RESISTANCE, WHICH FLUCTUATED WITH AMBIENT TEMPERATURE CHANGES. NORMAL READINGS FALL CLOSE TO 15,000 OHMS, WHEREAS THIS FAULTY COIL READ BETWEEN 2,000 OHMS, UP TO 5,000 OHMS. 13,000 OHMS IS DESCRIBED AS THE LOWEST READING ALLOWED BY THE MANUFACTURER OF THIS MAGNETO. THIS ISSUE WAS DISCOVERED DURING PREVENTIVE MAINTENANCE, WHICH INCLUDED INSPECTION OF MAGNETO INTERNALS. THE SERIAL NUMBER DATE CODE SUGGESTS THAT THIS MAGNETO WAS MANUFACTURED IN 1992. THANK YOU. 20060802000532006080200053CE 2006 8 2 2006FA0000725 120060711G27100510105365 CONTROL CABLE CESSNA172 172S 2072439CE LYC IO360 IO360L2A EA AILERON FRAYED B 7TFRK NONE O OTHER ININSP/MAINT 1 WP072134M2164 172S9552 DURING AN ANNUAL INSPECTION OF THE RT WING, THE AILERON CROSSOVER CABLE WAS FOUND TO BE FRAYED AT THE WEAR BLOCK. PROBABLE CAUSE IS THAT THE WEAR BLOCK IS CAUSING FRICTION AND WEAR ON THE CABLE. A RECOMMENDED SOLUTION IS TO REMOVE THE WEAR BLOCK. (K) 1H71 3O3 ONT3A12 1E10 20060802001812006080200181SO 2006 8 2 2006FA0000726 120060720G3230 DRAG LINK PIPER PA23 PA23160 7102304SO LYC O320 O320* 41508EA RT MLG FAILED G K NONE O OTHER ININSP/MAINT 1 SW054233P 231730 DURING THE INVESTIGATION, IT WAS DISCOVERED THAT THE RT MLG UPPER DRAG LINK ASSY HAD FAILED AT THE ATTACHMENT POINT FOR THE MLG DOWNLOCK LATCH ASSY. A VISUAL INSPECTION OF THE BROKEN DRAG LINK SHOWED THAT THE ASSY HAD A METAL FATIGUE CRACK ALONG THE CIRCUMFERENCE OF THE COMPONENT. THE CRACKED AREAS SHOWED EVIDENCE OF CORROSION THAT APPEARS TO HAVE BEEN THERE FOR A LONG PERIORD OF TIME. (K) 1L72 3O3 O 1A10 E274 20060803000032006080300003CE 2006 8 3 2006FA0000727 120060714G280007600261 GUARD CESSNA182 T182T 2072738CE LYC O540 TIO540* 41532EA FUEL SYSTEM OUT OF RIG C GFVRK NONE O OTHER ININSP/MAINT 1 NM131568W T18208394 PROTECTIVE GUARDS ARE CALLED OUT BY IPL ORIGINALLY, IPL REV 7 DOES, REV 8 DOES NOT. CURRENT REVISION 12, CALLS FOR THE GUARDS TO BE INSTALLED REV 13 IS IN TRANSIT BUT SHOULD INCLUDE THE CALL OUT. THIS AIRCRAFT HAS INDICATIONS THAT ELEVATOR CONTROL LINES HAVE MADE LIGHT CONTACT WITH FUEL LINES. BUT THERE IS NO DAMAGE. PARTS ORDERED. AIRCRAFT TT 159 HOURS (FIRST ANNUAL INSPECTION). (K) 1H71 3O3 ONT3A13 E14EA 20060803000052006080300005NM 2006 8 3 2006FA0000728 120060703G2910AE70577756 HOSE BOEING757 7572Q8 1384972NM HYDRAULIC SYSTEMMISINSTALLED B LH6YK NONE O OTHER ININSP/MAINT 1 EA35719BC 25131 NR 1 ENGINE HYDRAULIC PUMP SUCTION/SUPPLY DISCONNECT. DURING THE REPLACEMENT OF NR 1, ENGINE EDP DUE TO NO OFFLOAD, IT NOTED THAT THE SUPPLY DISCONNECT WAS FITTED WITH THE PUMP UNION AT THE WRONG END OF THE DISCONNECT, AND ON REMOVAL IT WAS NOTED THAT THE INTERVAL S/OFF MECHANISM HAD BEEN REMOVED. THE VALVE, UNION AND SEALS WERE SUBSEQUENTLY REPLACED. (K) 2L72 4F RTA2NM 20060803000072006080300007EA 2006 8 3 2006FA0000729 220060714G8550 ADAPTER ROBSINR22 R22BETA 7640110NM LYC O320 O320B2C 41508EA ENGINE BROKEN D K NONE O OTHER ININSP/MAINT 1 NM08185MH 0976 WHILE CHANGING OIL FILTER DURING ROUTINE 100 HR INSPECTION, OIL FILTER ADAPTER CENTER THREADED SHAFT BROKE OFF LEAVING HALF SHAFT INSIDE ADAPTER AND OTHER HALF THREADED INTO OIL FILTER. THIS OCCURRED WITH MINIMAL ROTATIONAL TORQUE BEING APPLIED. INSPECTION OF SHAFT REVEALED THAT MACHINED CENTER SECTION OF SHAFT AT SHEAR POINT WAS MACHINED TO DEEP LEAVING ONLY A MAXIMUM WALL THICKNESS OF .020, AND PROBABLY MUCH LESS AT SHEAR LINE JUDGING BY KNIFE EDGE CONDITION OF BREAK POINT. RECOMMENDATION: FURTHER INVESTIGATION AT MFG LEVEL POSSIBLE AD GENERATION TO DETERMINE IF OTHER UNITS CURRENTLY IN SERVICE HAVE SAME DEFECT CONDITION. 1G71 3O3 O H10WE E274 20060802002972006080200297CE 2006 8 2 2006FA0000730 120060702G49403046342 IGNITER LEAR 45 45LEAR 5170805CE GARRTTTFE731TFE731* 01518WP APU SEPARATED D O OTHER O OTHER ININSP/MAINT 1 SW99826CA 222 PART OF IGNITER PLUG THAT SURROUNDS ELECTRODE SEPARATES AND SHORTS AGAINST THE ELECTRODE CAUSING THE APU NOT TO START. PART COULD POSSIBLY ENTER THE COMBUSTION AREA OF THE APU. (NOTE: APU HAS ONE IGNITER, HAD 2 RECENT FAILURES). 2L72 4F4 FRTT00008WIE6WE 20060803000932006080300093CE 2006 8 3 2006FA0000731 120060702G49403046342 IGNITER LEAR 45 45LEAR 5170805CE GARRTTTFE731TFE73160 NE APU BROKEN D K NONE O OTHER ININSP/MAINT 1 SW99882CA792 155 PART OF IGNITER PLUG THAT SURROUNDS ELECTRODE SEPARATES AND SHORTS AGAINST THE ELECTRODE CAUSING THE APU NOT TO START. PART COULD POSSIBLY ENTER THE COMBUSTION AREA OF THE APU. (NOTE: APU HAS ONE IGNITER, WE HAVE HAD 2 RECENT FAILURES). (K) 2L72 4F4 FRTT00008WIE1NM 20060808000802006080800080GL 2006 8 8 2006FA0000732 320060714G6110ACA1373 NUT HARTZLHCB4M HCB4M GL CLAMP FAILED B JGVRK NONE O OTHER ININSP/MAINT 1 CE09 FWA2178 WHEN TORQUING OUTER CLAMP NUT PN ACA1373, NEW OUTER CLAMP NUT THREADS FAILED BEFORE REACHING SPECIFIED TORQUE. PROPELLER WAS BEING REASSEMBLED DURING OVERHAUL. ASSEMBLED USING CALIBRATED TOOLS AND NEW HARDWARE. (K) 6 CP56GL 20060803000942006080300094EU 2006 8 3 2006FA0000733 220060607G72409387M34G01 TUBE BOEING737 737300 1384610NM CFMINTCFM56 CFM563B2 13802EU FUEL DRAIN DAMAGED C QEMYK NONE O OTHER ININSP/MAINT 1 EA35GLGTG 41X24410 (REF: MDR NR MDR002/06) STRIP OF CORE ASSEMBLY NOTED FRETTAGE DAMAGE TO 3 LOCATIONS ON THE NR 3 POSITION FUEL NOZZLE DRAIN TUBE. THE DEEPEST WAS TO A DEPTH OF .016 INCH. THE ROUTE CAUSE OF THE FRETTAGE HAD BEEN DETERMINED AS CONTACT WITH RIVETS ON THE DEFLECTOR ASSY. THE MODULE (41X24410) WAS REFURBISHED IAW BA REFURBISH SPECIFICATION AND IAW 72-41-XX AT LAST SHOP VISIT. (K) 2L72 4F4 FRTA16WE E21EU 20060829000842006082900084CE 2006 8 29 2006FA0000734 120060727G3230 LANDING GEAR BEECH 35 A35 1151504CE CONT E185 E185* 17014SO NLG COLLAPSED C K NONE O OTHER NRNOT REPORTED 1 GL05417TZ D2053 NOSE GEAR COLLAPSED. 1L71 3O3 O A777 E246 20060803000512006080300051SO 2006 8 3 2006FA0000735 120060726G2432 CAPACITOR ELDEC GULSTMGV GULFSTREAMGV3980116SO BATTERY CHARGER BURNED C H DEACTIVATE SYST/CIRCUITS A FLAME/FIRE LDLANDING 1 EA07410LM2996 B317 578 AFTER LANDING AIRCRAFT TAXIED TO HANGAR. WHEN AIRCRAFT STOPPED GROUND CREW NOTICED SMOKE COMING FROM TAIL COMPARTMENT. INVESTIGATION FOUND SMOKE AND FLAMES COMING FROM RT BATTERY CHARGER. ELECTRICAL POWER REMOVED FROM AIRCRAFT. FLAMES SELF EXTINGUISHED AND CHARGER WAS THEN REMOVED FROM AIRCRAFT. NO DAMAGE TO SURROUNDING AIRCRAFT STRUCTURE. REPLACEMENT CHARGER INSTALLED OPS CHECK OK. 2L72 4F RTA12EA 20060816003072006081600307GL 2006 8 16 2006FA0000736 220060525G8530 CYLINDER HEAD MTSBSIMU2 MU2B20 5780407SW HIRTH 2706 2706* GL ENGINE STRIPPED G B EMER. DESCENT O OTHER TOTAKEOFF 1 WP09555C 129 A882299 NOTE: THIS AIRCRAFT WAS BUILT UNDER FAA EXPERIMENTAL AMATURE BUILT GUIDANCE. THIS AIRCRAFT IS NOT A LIGHT SPORT AIRCRAFT. IT WAS BUILT FROM A KIT AND CERTIFIED AS AN EXPERIMENTAL AMATURE BUILT AIRCRAFT. LOST ENGINE POWER AFTER TAKE-OFF AND MADE EMERGENCY LANDING WITH EXPERIMENTAL AMATURE BUILT AIRCRAFT: (HORNET)DETAILS: 2 CYLINDER,2 CYCLE ENGINE. 2 SPARK PLUGS IN EACH CYLINDER. AFT SPARK PLUG SEPARATED FROM AFT CYLINDER. THREADS THAT WERE MILLED INTO CYLINDER HEAD FAILED TO HOLD SPARK PLUG CAUSING DEPARTURE OF PLUG, LOSS OF COMPRESSION AND POWER LOSS CAUSING AN EMERGENCY LANDING. REPAIR WAS MADE BY INSTALLING A HELI-COIL INTO CYLINDER HEAD & REINSTALLING A SPARK PLUG. 1H72 3T3 I A2PC EXPE3I 20060814001212006081400121SO 2006 8 14 2006FA0000740 120060804G78103022406 EXHAUST DUCT GRUMAVG21 G21A 3951204SO PWA PT6 PT6A41 52043EA LT ENGINE CRACKED D K NONE O OTHER ININSP/MAINT 1 SO092293216012660 B139 PCE81118 EXHAUST DUCT ASSY CRACKED AND MISSING PARTS. 1H72 3R4 T TC654 E4EA 20060808000732006080800073NM 2006 8 8 2006FA0000741 120060626G2497 WIRE TRW DHAV DHC8 DHC8* NM AC GENERATOR BROKEN B VNNRK NONE O OTHER ININSP/MAINT 1 EA65 799 EXCITER ROTOR LEADWIRE BROKEN AT SOLDER CONNECTION TO DIODE. (K) 2H72 4T RTA13NM 20060808000762006080800076NM 2006 8 8 2006FA0000742 120060706G2497 WIRE TRW DHAV DHC8 DHC8* NM AC GENERATOR BROKEN B VNNRK NONE O OTHER ININSP/MAINT 1 EA65 2415 1163 EXCITER ROTOR LEAD WIRES BROKEN AT DIODE CONNECTION WIRES WERE INCORRECTLY SOLDERED. (K) 2H72 4T RTA13NM 20060808000742006080800074NM 2006 8 8 2006FA0000743 120060706G249731708301 WIRE DHAV DHC8 DHC8* NM AC GENERATOR BROKEN B VNNRK NONE O OTHER ININSP/MAINT 1 EA65 2476 EXCITER ROTOR LEAD WIRES BROKEN AT CONNECTION TO DIODE. (K) 2H72 4T RTA13NM 20060808000842006080800084NM 2006 8 8 2006FA0000744 120060706G2497 WIRE TRW DHAV DHC8 DHC8* NM AC GENERATOR BROKEN B VNNRK NONE O OTHER ININSP/MAINT 1 EA65 654 EXCITER ROTOR LEAD WIRES BROKEN AT CONNECTION TO DIODES, INCORRECTLY SOLDERED TO DIODE. (K) 2H72 4T RTA13NM 20060808000772006080800077NM 2006 8 8 2006FA0000745 120060706G2497 WIRE TRW DHAV DHC8 DHC8* NM AC GENERATOR BROKEN B VNNRK NONE O OTHER ININSP/MAINT 1 EA65 9658 1188 EXCITER ROTOR LEAD WIRES BROKEN AT CONNECTION BETWEEN DIODE AND RESISTOR. (K) 2H72 4T RTA13NM 20060810001182006081000118EA 2006 8 10 2006FA0000747 220060717G7310050011842 FUEL LINE CESSNA172 172K 2072430CE LYC O320 O320* 41508EA ENGINE CHAFED D K NONE O OTHER ININSP/MAINT 1 WP0979130 17257901 DURING AN ANNUAL INSPECTION, BOTH ENGINE FUEL SUPPLY LINES WERE FOUND TO BE CHAFFING THE FWD BULKHEAD OF THE LANDING GEAR BOX STRUCTURE AT BS 56.70. MDG HAS INSTALLED A THIN PLASTIC SLEEVE OVER THE LINES IN THE AREA OF THE CHAFE BUT, AFTER 2564 HOURS, THE SLEEVE IS CHAFFED TOT HE EXTENT THAT THE TUBES WILL NO LONGER BE PROTECTED. FEEL THAT THE TUBE INTEGRITY WOULD BE COMPROMISED IN THE FUTURE. ADDITIONAL CHAFE PROTECTION AND LINE SECURING IS REQUIRED. ILLUSTRATION SHOWS A HEAVIER CHAFE BARRIER INSTALLED ON THE TUBES IN THE AREA NOTED ABOVE. SUGGEST BONDING A LENGTH OF MIL .3750 INCH ID TUBING OVER THE MFG LINE IN THE CHAFE ARREARS. ADDITIONAL ADJUSTMENT OF THE EXISTING LINE CLAMPS MAY ALSO BE REQUIRED. 1H71 3O3 ONT3A12 E274 20060810001162006081000116SO 2006 8 10 2006FA0000748 120060407G27206282905 SHAFT PIPER PA32 PA32300 7103212SO LYC O540 IO540* 41532EA RUDDER MISREPAIRED C NT2RK NONE W INADEQUATE Q C ININSP/MAINT 1 CE07195PJ 327840092 RUDDER TRIM BUNGEE SHAFT ASSY PN 6282905, HAD BEEN IMPROPERLY REPAIRED BY PERSONS UNKNOWN CAUSING BUNGEE TO BOTTOM OUT WHEN RUDDER PEDAL DEFLECTED TO LIMIT WHICH IN TURN CAUSED UNDO PRESSURE ON RUDDER CONTROL ARM, PN 6345703, EVENTUALLY CAUSING ARM TO BREAK. (K) 1L71 3O3 O A3SO 1E4 20060810001172006081000117EA 2006 8 10 2006FA0000749 220060720G8530LW14995 SPRING LYC SOCATATB20 TB21 8680697EU LYC O540 TIO540AB1A 41533EA CYLINDER BROKEN D K NONE O OTHER ININSP/MAINT 1 CE072802W232 1137 L921061A THE PUSH ROD HOUSING TUBE RETAINING SPRINGS WERE BROKEN AT THE BEND JUST OB OF THE MOUNT HOLE. THE UNBROKEN SPRINGS HAD A TOOL LINE AT THE POINT OF THE BEND. THERE WERE 2 BROKEN SPRINGS, LOCATED ON NR 3 AND NR 4 CYLINDERS. ONE SPRING HAD ONE SIDE BROKEN OFF THE OTHER BOTH SIDES WERE BROKEN. BELIEVE THE TOOL MARKS ARE CAUSING THE PROBLEM. ALL 6 SPRINGS WERE REPLACED WITH NEW MFG PARTS AND SOME ALSO CONTAINED THE TOOL MARKS AT THE BEND. (K) 1L71 3O3 ORTA51EU E14EA 20060810001302006081000130CE 2006 8 10 2006FA0000750 120060604G323398820152 HOUSING CESSNA172 172RG 2072438CE LYC O360 O360F1A6 41514EA MCAULY2D34C B2D34C220 GL ACTUATOR CRACKED D K NONE O OTHER ININSP/MAINT 1 WP099394D 172RG1150 L3758836A 796893 RT MAINT GEAR ACTUATOR HOUSING CRACKED THROUGH THE BOLT HOLES OF CASTING , CAUSING RACK TO DISENGAGE FROM PIVOT GEAR. 1H71 3O3 O 3A17 E286 5 CP7EA 20060810001212006081000121EU 2006 8 10 2006FA0000751 120060713G6220350A310033KIT7 SPRING SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1D1 NE VIBRATION ABSORBBROKEN B K NONE O OTHER ININSP/MAINT 1 EA17461SA2130 M2026 3605 PILOT REPORTED EXCESSIVE CABIN VIBRATION AT FULL POWER WHILE ON THE GROUND. VIBRATION SUBSIDED IN A HOUR AND THROUGHOUT THE FLIGHT ENVELOPE. DISASSEMBLY AND INSPECTION REVEALED 1 OF 3 SPRINGS IN VIBRATION ABSORBER OF MAIN ROTOR CRACKED ALL THE WAY THROUGH. COMPLIED WITH 2500 HR INSPECTION OF VIBRATION ABSORBER JAW MFG MAINT WORK CARDS AND SERVICING RECORDS. REPLACED ALL 3 SPRINGS AND PN EN2023R12L. BEARINGS WHICH HAD EXCESSIVE PLAY. REINSTALLED AN AIRCRAFT AND VIBRATION WAS ELIMINATED. (K) 1G71 3U3 U H9EU E19EU 20060810001122006081000112GL 2006 8 10 2006FA0000752 120060720G7120 SAFETY WIRE AMTR LANCARLC41550FG 5150001GL NR 4 ENG MOUNT MISINSTALLED C K NONE W INADEQUATE Q C ININSP/MAINT 1 SW072542T391 41508 ALL 4 ENGINE VIBRATION ISOLATOR MOUNT BOLTS WERE SAFETY WIRED BACKWARDS. NO EVIDENCE OF DAMAGE. (K) 1L71 3O RTEXPA1L71 20060810001232006081000123CE 2006 8 10 2006FA0000753 120060718G5540081301316 TORQUE TUBE CESSNA310 310Q 2074242CE RUDDER DAMAGED D K NONE O OTHER ININSP/MAINT 1 GL03119RS 310Q0906 RT RUDDER TORQUE TUBE RIPPED AT RUDDER CABLE BRACKET. INSPECT THIS AREA NEXT TO WELD. (K) 1L72 3O 3A10 20060810001382006081000138SO 2006 8 10 2006FA0000755 120060731G8011 RING GEAR PIPER PA31 PA31350 7103110SO LYC O540 TIO540N2BD 41532EA STARTER FAILED B EVTRK NONE O OTHER ININSP/MAINT 1 SO333542D291 E052921 317952232 L1000961A TRIED TO START ENGINE WOULD NOT START VISUAL BENDIX TO RING GEAR TEETH IN BOTTOM OF STARTER HOUSING. (K) 1L72 3O3 O A20SO E14EA 20060810001272006081000127SW 2006 8 10 2006FA0000756 120060721G2497112 WIRE BBAVIA7 7ECA 21101NNSW LYC O235 O235* 41505EA FIREWALL SHORTED D O OTHER B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 1 NE018750V1568 110475 WHILE IN FLIGHT, THE PILOT REPORTED HE COULD SMELL SOMETHING BURNING, LANDED AS SOON AS PRACTICAL. INVESTIGATION REVEALED THAT THE WIRE FROM THE ALTERNATOR TO THE AMMETER, PN 112 HAD SHORTED AGAINST THE FIREWALL, WHERE IR GOES THROUGH THE FIRE WALL. WIRES 112, 114, MASTER RELAY, STARTER RELAY, AMMETER, VOLTAGE REGULATOR AND ALTERNATOR WERE ALL REPLACED. (K) 1H71 3O3 O A759 E223 20060810001362006081000136 2006 8 10 2006FA0000757 420060804G2562AK450 ELT CESSNA150 150K 2071822CE CONT O200 O200* 17020SO CABIN INOPERATIVE C BI1RK NONE O OTHER ININSP/MAINT 1 EA055896G 15071396 THIS IS ONE OF THE ELT`S THAT USES DATED FLASHLIGHT BATTERIES. THE BATTERIES ARE STILL IN DATE BUT OFTEN WE FIND THAT THE BATTERIES ARE LEAKING OR DEAD BEFORE THE EXPIRATION DATE. RECOMMEND THAT THE BATTERIES ARE CHANGED AT EACH ANNUAL TO CORRECT THIS PROBLEM. BATTERIES ARE CHEAP ENOUGH. (K) 1H71 3O3 O 3A19 E252 20060814000712006081400071EA 2006 8 14 2006FA0000758 220060725G8530TISN12OCA CYLINDER HEAD PIPER PA25 PA25 7102502SO LYC O360 O360C2A 41514EA RT ENGINE SEPARATED D A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CRCRUISE 1 EA176471Z410 25673 L2925936A THIS WAS A NEW CYLINDER INSTALLED APRIL 05, AT ENGINE OVERHAUL. THE CYLINDER COMPLETELY SEPARATED BETWEEN THE HEAD AND BARREL, IN FLIGHT. THE AIRCRAFT WAS SAFELY LANDED AT HOME AIRPORT. PN STAMPED ON CLY BASE: AEL65102, SN12.0F. (K) 1L71 3O3 O 2A10 E286 20060810001192006081000119EA 2006 8 10 2006FA0000759 220060802G741410357281L CAPACITOR LYC BELL 47 47G4A 1181031SW LYC O540 VO540B1B3 41532EA MAGNETO FAILED D A UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 1 WP171354X 1012162 7537 L174243 LOADED HELICOPTER SAFELY LANDED AFTER MAGNETO FAILURE. WIRE FROM CAPACITOR TO POINTS OPEN WITHIN INSULATION. NO VISIBLE DAMAGE, HOWEVER, MOVEMENT OF WIRE AGAINST CAPACITOR RESTORES CONTACT. YOU CAN FEEL IT. OPEN LOCATED WHERE WIRE ENTERS CAPACITOR. NO RECOMMENDATIONS. (K) 1G71 3O3 O 2H3 E304 20060810001322006081000132GL 2006 8 10 2006FA0000760 320060802G6111 SNAP RING CESSNA210 210M 2073450CE CONT O520 IO520* 17032SO MCAULYD3A34 D3A34C404 GL PROP BLADES FAILED D K NONE O OTHER ININSP/MAINT 1 SO07965B 2976 1066 21061580 295027R 782194 2 SNAP RINGS FAILED ON PROPELLAR BLADES. (K) 1H71 3O3 O 3A21 E5CE 5 CP47GL 20060810001142006081000114CE 2006 8 10 2006FA0000761 120060802G3297110230102 CIRCUIT BREAKER CESSNA177 177RG 2073709CE LYC O360 IO360A1B6 41514EA MCAULY2D34C B2D34C207 GL MLG MALFUNCTIONED C O OTHER O OTHER NRNOT REPORTED 1 EA2321EB 7567 177RG0589 L1265751A 752186 LANDING GEAR CIRCUIT BREAKER MALFUNCTIONED. AIRCRAFT WAS JACKED AND GEAR CYCLED SEVERAL TIMES. COULD NOT GET THE CIRCUIT BREAKER TO MALFUNCTION ON JACKS. RECOMMEND THAT CIRCUIT BREAKER BE REPLACED WITH NEW. (K) 1H71 3O3 O A20CE 1E10 5 CP7EA 20060810001152006081000115EA 2006 8 10 2006FA0000762 220060520G8520MIOP CRANKSHAFT AMTR SISU SISU1A 0780132GL LYC O360 IO360A1A 41514EA ENGINE SEPARATED D K NONE O OTHER ININSP/MAINT 1 GL27818SH 1017S1S L1479051A CRANKSHAFT FLANGE SEPARATED FROM CRANK AT THE LIGHTENING HOLES. AVOID GYROSCOPIC AEROBATICS USING A CRANKSHAFT FLANGE WITH LIGHTENING HOLES. (K) 1K00 3 ORCEXPA1K001E10 20060814000822006081400082 2006 8 14 2006FA0000764 220060701G8530AEL65102 CYLINDER HEAD PIPER PA18 PA18A 7101804SO ENGINE SEPARATED B OF1RO OTHER J WARNING INDICATION CRCRUISE 1 EA173885Z413 187700 DURING NORMAL CRUISE FLIGHT, PILOT EXPERIENCED ENGINE ROUGHNESS AND A LOSS OF ENGINE OIL OUT OF THE SIDE COWLING, CAUSING AN UNEVENTFUL OFF AIRPORT LANDING. ROUGHNESS AND OIL LOSS WERE DUE TO NR 3 CYL HEAD SEPARATING FROM THE CYLINDER BARREL AT THE 3RD COOLING FIN FROM BOTTOM OF THE HEAD. ALTHOUGH THIS CYLINDER ECI PN IS SAME PN LISTED IN AD, THIS WAS TITAN STYLE CYL, NOT CLASSIC CAST AS INDICATED BY NR CAST INTO CYL HEAD. THESE LATER TITAN CYL UNAFFECTED BY AD, MAY BE EXPERIENCING SAME FAILURES THAT THE EARLIER CAST CYL THAT ARE AFFECTED BY AD WERE EXPERIENCING. (K) 1H71 3O 1A2 20060814001252006081400125SO 2006 8 14 2006FA0000765 120060808G321167042013 TRUNNION PIPER PA44 PA44180 7104402SO MLG CRACKED B K NONE O OTHER ININSP/MAINT 1 WP07571ER3394 4496147 DURING MAINTENANCE INSPECTION OF THE GEAR, THE MECHANIC FOUND THE AFT MAIN GEAR TRUNNION CRACKED. DYE PENETRANT CONFIRMED CRACK. CAUSE IS UNDETERMINED BUT THE AIRCRAFT IS USED FOR FLIGHT TRAINING. 1L72 3O A19S0 20060814001342006081400134 2006 8 14 2006FA0000766 420060731G3497311601 WIRE HARNESS CESSNA650 650 2076802CE DAMAGED C O OTHER O OTHER CRCRUISE 1 GL1396MT 6507065 DUAL TRANSPONDER FAILURE IN HEAVY PRECIPITATION. NO FAILURE INDICATION ON SPZ8000 SYSTEM. CENTER REQUESTED RESET OF TRANSPONDER, AND DIRECTED OUT OF RVSM AIRSPACE WHEN UNSUCCESSFUL. HANGAR TESTS OF POWER OUTPUT SHOWED 40WATTS BEFORE CABLES REPLACED, AND 400 WATTS AFTER. 2L72 4F A9NM 20060814001352006081400135 2006 8 14 2006FA0000767 420060731G3497311601 WIRE HARNESS CESSNA650 650 2076802CE DAMAGED C O OTHER O OTHER CRCRUISE 1 GL1396MT 6507065 DUAL TRANSPONDER FAILURE IN HEAVY PRECIPITATION. NO FAILURE INDICATION ON SPZ8000 SYSTEM. CENTER REQUESTED RESET OF TRANSPONDER, AND DIRECTED OUT OF RVSM AIRSPACE WHEN UNSUCCESSFUL. HANGAR TESTS OF POWER OUTPUT SHOWED 40WATTS BEFORE CABLES REPLACED, AND 400 WATTS AFTER. 2L72 4F A9NM 20060821000552006082100055 2006 8 21 2006FA0000768 420060813G3416 ALTIMETER BOEING777 777 UTILUSENM INOPERATIVE C O OTHER O OTHER NRNOT REPORTED 1 SW99 CAPTAIN ALTIMETER INOPERATIVE. 2L72 4F RTT00001SE 20060814001472006081400147EA 2006 8 14 2006FA0000769 220060320G73101560016D0155 HOSE CESSNA182 R182 2072734CE LYC O540 O540J3C5 41532EA FUEL SYSTEM LEAKING D K NONE KK FLUID LOSS FLUID LOSS ININSP/MAINT 1 SW153648C1177 R18200294 L2047940A DURING AN ANNUAL INSPECTION THE HOSE ASSEMBLY FROM THE ELECTRIC PUMP TO THE ENGINE DRIVEN FUEL PUMP WAS FOUND TO BE LEAKING. HOSE WAS INSTALLED 5-12-03 AND REMOVED 3-20-06. 1H71 3O3 ORT3A13 E295 20060814001952006081400195EA 2006 8 14 2006FA0000770 220060320G7310AE3663819B0190 HOSE CESSNA182 R182 2072734CE LYC O540 O540J3C5 41532EA FUEL SYS LEAKING D K NONE KJ FLUID LOSS WARNING INDICATION ININSP/MAINT 1 SW153648C1177 R18200294 L2047940A DURING AN ANNUAL INSPECTION THE HOSE ASSEMBLY FROM THE TEE FITTING AT CARBURETOR TO THE FIREWALL FITTING FOR FUEL PSI WAS FOUND TO BE LEAKING. HOSE WAS INSTALLED 5-12-03. 1H71 3O3 ORT3A13 E295 20060817001722006081700172GL 2006 8 17 2006FA0000772 220060731G7200 COUPLING ALLSN 250C 250C30P 03013GL ENGINE FAILED B A9URO OTHER O OTHER NRNOT REPORTED 1 SW05 CAT90607 NR 2 COUPLING FAILURE, WHICH CAUSED A NI FAILURE, AND INNER SHAFT FAILURE, POWER TURBINE ROTOR DECOUPLING AND GAS PRODUCER OVERTEMP. (K) 3 U E1GL 20060814001932006081400193SO 2006 8 14 2006FA0000773 120060806G3222 SPRING MICCO 145A MAC145A 5660000SO TAILWHEEL ASSY FRACTURED P O OTHER O OTHER LDLANDING 1 SW05121MA700 10 307 TAILWHEEL SPRING FAILED ON LANDING. BROKEN IN MULTIPLE LOCATIONS. ONE BREAK POINT SHOWS EVIDENCE OF CORROSION, THE OTHER DOES NOT. CRYSTALLIZATION PRESENT AT BOTH BREAK POINTS. CRACKS APPEAR TO HAVE BEEN COVERED BY PAINT. 1L71 3O RC 20060815000112006081500011SO 2006 8 15 2006FA0000774 120060806G3220 SPRING MICCO 145A MAC145A 5660000SO TAILWHEEL ASSY FRACTURED P O OTHER O OTHER LDLANDING 1 SW05121MA700 10 307 TAILWHEEL SPRING FAILED ON LANDING. BROKEN IN MULTIPLE LOCATIONS. ONE BREAK POINT SHOWS EVIDENCE OF CORROSION, THE OTHER DOES NOT. CRYSTALLIZATION PRESENT AT BOTH BREAK POINTS. CRACKS APPEAR TO HAVE BEEN COVERED BY PAINT. 1L71 3O RC 20060815000062006081500006SO 2006 8 15 2006FA0000775 120060810G57116707003 SPAR PIPER PA28 PA28R180 7102809SO RT WING CRACKED D K NONE O OTHER ININSP/MAINT 1 SO153894T5260 28R30223 DURING COMPLIANCE, A CRACK WAS FOUND ON THE MAIN SPAR DIRECTLY BEHIND THE SWIVEL BOLT BRACKET AT THE IB MOUNTING NUTPLATE. THE CRACK IS 3 INCHES IN LENGTH AND CURVES UPWARD ON BOTH ENDS. THE CRACK WAS NOT VISIBLE UNTIL THE AREA WAS CLEANED. IT IS RECOMMENDED THAT THIS AREA OF THE SPAR BE CLEANED AND INSPECTED DURING COMPLIANCE OF SB. A CRACK WAS ALSO FOUND ON ANOTHER PA28R-180 NEAR THE SAME LOCATION ON THE SPAR. THIS INFORMATION AND PICTURES WERE SENT TO FOR EVALUATION. 1L71 3O 2A13 20060815000012006081500001 2006 8 15 2006FA0000776 420060804G2300 ELEC CONNECTOR DIAMONDA40 DA40 2990002GL MICROPHONE SHORTED B A UNSCHED LANDING O OTHER CRCRUISE 1 CE0538CF 40567 ADJACENT MIC AND PHONE JACKS SHORTED TOGETHER CAUSING SQUEAL IN AUDIO SYSTEM. 1L71 3O NTA47CE 20060815000092006081500009SO 2006 8 15 2006FA0000778 120060801G2842 TRANSMITTER PIPER PA46 PA46350P 7104602SO LYC O540 TIO540AE2A 41532EA FUEL SYSTEM UNRELIABLE C O OTHER N FALSE WARNING NRNOT REPORTED 1 SW17319RD 4636139 NEW-STYLE FUEL SENDERS UNRELIABLE. HAVE REPLACED 3 TIMES SO FAR. 1L71 3O3 ORTA25SO E14EA 20060815000102006081500010SO 2006 8 15 2006FA0000779 120060801G2842 TRANSMISSION PIPER PA46 PA46350P 7104602SO LYC O540 TIO540AE2A 41532EA ZONE 500 UNRELIABLE C O OTHER N FALSE WARNING NRNOT REPORTED 1 SW17319RD 4636139 NEW-STYLE FUEL SENDERS UNRELIABLE. HAVE REPLACED 3 TIMES SO FAR. 1L71 3O3 ORTA25SO E14EA 20060815000042006081500004CE 2006 8 15 2006FA0000780 120060808G3230NAS464P426 BOLT CESSNA CESSNA340 340A 2076405CE BELL CRANK SHEARED C A UNSCHED LANDING S AFFECT SYSTEMS LDLANDING 1 SW172745F2113 340A0949 FAILURE OF THE PIVOT BOLT ON THE RT MLG DOWNLOCK BELLCRANK (BOOMERANG) APPEARS TO HAVE RESULTED FROM SHEAR FORCES DURING LANDING. FORCES OF THIS NATURE EXCEEDED DESIGN LIMITS OF THIS SEGMENT OF THE LANDING GEAR SYSTEM. THE EXACT CAUSE COULD NOT BE DETERMINED BUT MAY HAVE RESULTED FROM IMPROPER RIGGING TO THE SYSTEM DURING RECENT MAINTENANCE OF THE LANDING GEAR COMPONENTS. 1L72 3O 3A25 20060815000052006081500005CE 2006 8 15 2006FA0000781 120060803G5544905000377 BRACKET BEECH 90 C90 1152913CE RUDDER UNSECURE B K NONE O OTHER ININSP/MAINT 1 GL1136799200 LJ1799 DURING THE INITIAL 200 HOUR PHASE 1 INSPECTION ON THIS AIRCRAFT, THE MOUNT BRACKETS THAT SECURE THE RUDDER SERVO BRIDLE CABLES AND PULLEYS WERE FOUND TO BE UNSECURED AT THE AFT ATTACH POINTS (FS 364.00) BOTH LT AND RDT BRACKETS WERE NOT ATTACHED. THE ASSOCIATED FUSELAGE (2 EACH BOLTS IAW SIDE WAS LOCATED IN THE AFT FUSELAGE COMPARTMENT. REVIEWED OF THE AIRFRAME LOGBOOKS DETERMINE NO DOCUMENTED WORK HAD BEEN PERFORMED IN THE AREA OR ON THE AFFECTED COMPONENTS. RAYTHEON FIELD TECHNICAL SUPPORT IS CONDUCTING AN INVESTIGATION. 1L72 3T 3A20 20060821000662006082100066EA 2006 8 21 2006FA0000782 120060802G2810G201G202 FITTING FOUND FBA FBA2C 3640102EA LYC O540 IO540* 41532EA FUEL SYSTEM UNDERTORQUED H K NONE WK INADEQUATE Q C FLUID LOSS ININSP/MAINT 1 AL03753 532 44 AS REPORTED FROM THE PILOT, THE MAINTENANCE VENDOR FOUND NUMEROUS FUEL FITTINGS WHICH CONNECT THE FUEL LINES TO THE HEADER TANKS TO BE SEEPING FUEL. APPROXIMATE TIME OF SERVICE 532 HOURS. PIPE THREADED FITTINGS HAD NO THREAD LUBE/SEALANT. THE VENDOR NOTED THAT THE FUEL FITTINGS WERE NOT PROPERLY TORQUED. THIS MAY REPRESENT A QUALITY CONTROL ISSUE AT THE FOUND AIRCRAFT PRODUCTION FACILITY. AT PRESENT THE USDOI, AVIATION MANAGEMENT DIRECTORATE, IS INVESTIGATING THIS EVENT WITHIN ITS FLEET. 1H71 3O3 O A7EA 1E4 20060816002652006081600265CE 2006 8 16 2006FA0000783 120060725G251007140593 SEAT CESSNA182 182R 2072731CE COCKPIT BROKEN B BIIRK NONE O OTHER ININSP/MAINT 1 EA219983H4070 18268161 INSPECTED SEATS IAW AD. FOUND PILOTS SEAT BOTTOM ASSY BROKEN AT LT FWD ATTACH POINT AND RT FWD CRACKED. (K) 1L71 3O NT3A13 20060816003022006081600302 2006 8 16 2006FA0000784 420060814G2562300011 ELT CESSNA172 172S 2072439CE CABIN FAILED B K NONE L NO TEST ININSP/MAINT 1 SW055359K1944 1944 9447 ELT REMOTE SWITCH FOUND TO BE INOP. ELT SENT TO SHOP FOR REPAIR, SYSTEM OPS CKD NORMAL AFTER REPAIR. THIS IS THE 4 OCCURRENCE OF THIS ON THIS TYPE AIRCRAFT IN THE LAST 3 MONTHS. ALL REPAIRS ARE THE SAME REPLACE FUSE F1. 1H71 3O NT3A12 20060816002262006081600226CE 2006 8 16 2006FA0000785 120060804G8011 MOTOR CESSNA172 172P 2072436CE LYC O320 O320* 41508EA STARTER SHORTED B K NONE O OTHER ININSP/MAINT 1 EA0399465 17276450 LIGHT WEIGHT STARTER MOTOR FAILED (SHORTED INTERNALLY) AFTER 1.5 YEARS SERVICE. (K) 1H71 3O3 ONT3A12 E274 20060817001702006081700170CE 2006 8 17 2006FA0000786 120060804G801185034007 DRIVE GEAR CESSNA172 172R 2072401CE LYC O360 IO360B1E 41514EA STARTER BROKEN B O OTHER O OTHER NRNOT REPORTED 1 EA03981CP 17280215 BENDIX DRIVE GEAR BROKE INTO PIECES AFTER 1 YEAR OF SERVICE. (K) 1H71 3O3 ONT3A12 1E10 20060816003002006081600300SW 2006 8 16 2006FA0000787 120060811G53112722019045 FRAME SWRNGNSA227 SA227AC 8780603SW FUSLEAGE CRACKED B OWFRK NONE O OTHER ININSP/MAINT 1 CE05ECIXL AC689 DURING REPAIR OF WING SPAR SHEAR WEB IAW AD AND SRM, IT WAS FOUND THAT THE LT AND RT BELT FRAMES WERE CRACKED AT THE STRINGER 11 CUTOUT. THE CRACKED BELT FRAMES WILL BE REPLACED WITH NEW COMPLETION OF THE SPAR REPAIR. AIRCRAFT IS OPERATING ON THE SPANISH REGISTER. (K) 2L72 4T RTA8SW 20060818001602006081800160SW 2006 8 18 2006FA0000788 120060811G57112722019046 FRAME SWRNGNSA227 SA227AC 8780603SW WING CRACKED B OWFRK NONE O OTHER ININSP/MAINT 1 CE05ECIXL22492 AC689 DURING REPAIR OF WING SPAR SHEAR WEB IAW AD AND SRM, IT WAS FOUND THAT THE LT AND RT BELT FRAMES WERE CRACKED AT THE STRINGER 11 CUTOUT. THE CRAKED BELT FRAMES WILL BE REPLACED WITH NEW UPON COMPLETION OF THE SPAR REPAIR. AIRCRAFT IS OPERATING ONT HE SPANISH REGISTER AS ECIXL. (K) 2L72 4T RTA8SW 20060817001732006081700173SO 2006 8 17 2006FA0000789 220060809G8530 CYLINDER BEECH 58 58 1152740CE CONT O520 IO520* 17032SO ENGINE DAMAGED B CTURK NONE O OTHER ININSP/MAINT 1 GL2158LF TH237 243832R ON ANNUAL INSPECTION, WORK WAS BEING PERFORMED TO REPAIR OIL LEAK ON PUSH ROD TUBE SEALS, WHEN PUSHRODS WERE REMOVED, THEY WERE FOUND TO BE BENT AND GREATER THAN 50 PERCENT OF TOTAL TUBE WORN THROUGH. FURTHER INVESTIGATION FOUND THAT SEVERAL TUBES WERE FOUND IN SAME CODITION AND THAT ALL EXHAUST RODS WERE BENT. THERE WERE ALSO SIGNS ON 5 PISTONS OF VALVE CONTACT. FIREWALL FWD RECONDITIONED CYLINDERS AND STATED THAT VALVE GUIDES HAD COAKING ON THEM AND THAT THE PISTON RINGS HAD LOST THEIR TEMPER. OWNER IS SUSPECT OF BAD PARTS FROM MFG. (K) 1L72 3O3 O 3A16 E5CE 20060817001692006081700169SW 2006 8 17 2006FA0000790 120060801G57115262L SPAR BBAVIA7 7HC 21101PNSW LYC O290 O290 41506EA WING CRACKED D O OTHER O OTHER NRNOT REPORTED 1 NE058906R 7HC26 LONGITUDINAL CRACK FROM STRUT BOLT HOLE OB. PROBABLE CAUSE: WING DAMAGE FROM PAST GROUND LOOPING PROPAGATING OVERTIME. TIME OF INCIDENT IN LOGS, 7/17/72. (K) 1H71 3O3 O A759 E229 20060821000652006082100065CE 2006 8 21 2006FA0000791 120060708G272035660033 HINGE BEECH P35 P35 1151530CE CONT O470 IO470* 17026SO RUDDERVATOR CRACKED D K NONE O OTHER ININSP/MAINT 1 WP079520Y D7016 FAIRLEADS IN RUDDERVATOR TRIM TAB CNTRL CABLE SYS ARE CRACKING UPON INSTALLATION, POSSIBLY DURING FLIGHT. BUTTON-HEAD RIVETS ARE INTERFERING WITH INSTALLATION, CAUSING CRACKS TO FORM IN (TANG) OF FAIRLEADS. CABLE TENSION USED IN RUDDERVATOR TRIM TAB CABLES IS A FACTOR IN CRACKING. A LOOSENING OF RUDDERVATOR TRIM TAB CNTRL CABLES IS NECESSARY DURING INSTALL, FOLLOWED BY RIGGING TO VERIFY PROPER CABLE TENSION. A SMALL AMOUNT OF FILING ON BACK OF (TANG) OF FAIRLEAD FOR CLOSE TOLERANCE OF RIVETS THAT HOLD NUTPLATE FOR MOUNTING OF FAIRLEAD. EITHER A NEW MATERIAL NEEDS TO BE EXPLORED FOR MAKING FAIRLEADS MORE DURABLE, OR A MAINT NOTE NEEDS TO BE MADE ON PROPER INSTALLATION OF FAIRLEADS TO PREVENT CRACKING. (K)1L71 3O3 ORT3A15 E1CE 20060816003412006081600341CE 2006 8 16 2006FA0000792 120060728G325024670036 BUNGEE CYLINDER CESSNA172 172RG 2072438CE LYC O360 O360* 41514EA NLG STEERING BROKEN D V36RK NONE O OTHER TXTAXI/GRND HDL 1 SO1320CU 172RG0323 THE NOSE GEAR STEERING BUNGEE PN 2467003-6, BROKE WHILE TAXIING IN AFTER LANDING. THE AIRCRAFT STOPPED WITHOUT INCIDENT. THE BREAK OCCURRED IN THE THEADED AREA OF THE SHAFT THAT CONTAINS THE CHAIN SPROCKET. NOTE THAT THIS SHAFT HAS THREADS ON BOTH ENDS. THE END THAT BROKE HAS THE SMALLER THREADS (.3125 INCHES) NAD IS ON THE OPPOSITE END FROM THE SPROCKET. THIS FAILURE IS SIGNIFICANT BECAUSE WHEN THE BUNGEE BREAKS THE BODY, WILL PIVOT DOWN AROUND THE ATTACHMENT POINT AND FOUL THE ELEVATOR CONTROLS. BUNGEE WAS REPLACED AT TACH 532 AS A RESULT OF THE AD. THE AC HAS 8070 HRS ON IT SO THE REPLACEMENT PART HAS 7538 HOURS ON IT. (K) 1H71 3O3 O 3A17 E286 20060818001542006081800154CE 2006 8 18 2006FA0000793 120060628G5711 SPAR BEECH 18 E18S 1151006CE PWA R985 R985* 52008NE LT WING CORRODED B O31RK NONE O OTHER ININSP/MAINT 1 SW1192WA 6600 BA379 THE DEFECT IS SEVERE CORROSION IN SPAR TUBE LT SIDE UPPER AT WING STA 90. PROBABLE CAUSE IS EXPOSURE TO MOISTURE OVER AN EXTENDED PERIORD OF TIMEM. RECOMMENDATION TO PREVENT RECURRENCE WOULD BE TO SEAL AND FILL WITH LIN SEED OIL. FURTHER RECOMMENDATION WOULD BE TO ADD A SPLICE TO SPARE SECTION TO PROVIDE STRUCTURE INTEGRITY. FURTHER RECOMMENDATION WOULD BE TO VISUAL INSPECT AND DYE PENETRANT INSPECT THIS AREA AT 25 HOUR INTERVALS UP TO 1ST 100 HOURS. IF NO FATIGUE OR CRACKS ARE NOTED THEN EXTEND VISUAL AND PENETRANT INSP TO EVERY 100 HOURS OR EACH YEAR WHICH EVER OCCURS FIRST. SEE ATTACHED XRAY, PENETRANT REPORT AND ADDITIONAL AREAS OF CONCERN FOR NOTED DEFECT. (K) 1L72 3R3 R A765 5E1 20060818001492006081800149EA 2006 8 18 2006FA0000794 120060708G3210A153034 LEG ASSY GRUMANSA16 G64 EA PWA PT6 PT6A20 52043EA HARTZLHCB3T HCB3TN3 GL RT MLG FAILED D NHXGK NONE O OTHER ININSP/MAINT 1 WP259965 1362 21758 BUA20843 THE RT MAIN GEAR LEG (SPRING GEAR STYLE) FAILED AT THE UPPER END, JUST OB OF THE CLAMP BAV. THIS IS AN AREA OF MAJOR FLEX OF THE GEAR LEG AND IT IS THE THICKEST PART OF THE LEG. IN 25 YEARS WORKING ON THIS TYPE OF AIRCRAFT, I HAVE NEVER SEEN A FAILURE OF THE MAIN GEAR LEGS. THIS SET OF GEAR WAS INSTALLED ON THE AIRCRAFT 4/22/02 AND WAS MAGNAFLUXED, SANDBLASTED, AND PAINTED PRIOR TO INSTALLATION. THE GEAR LEGS WERE A USED SET AT THAT TIME AND THE TT ON THE PAIR IS UNKNOWN. THE TIME SINCE MAGNAFLUX AND INSTALLATION (4/22/02) IS 1687.1 HRS. THIS IS NOT A COMMON FAILURE AND I DO NOT BELIEVE THAT THERE IS A NEED FOR AN AD NOTE OR OTHER ACTION. (K) 2H72 4R3 T EXPA2H72E4EA 6 CP15EA 20060817001892006081700189NE 2006 8 17 2006FA0000795 120060524G64106516100001043 SPAR SKRSKYS64 S64E 8142604NE PWA JFTD12JFTD12A4A 52047NE T/R BLADE CRACKED B JYDRK NONE O OTHER ININSP/MAINT 1 NM09229AC39689 64018 (REF NR: MDR06-088) IB SIDE OF SPAR ON TRAILING EDGE HAS A CRACK. THE CRACK IS APPROX .482 INCH LONG AND RUNS FROM TIP END OF BLADE, DOWN INTO THE SCREW HOLE COUNTERSINK. BLADE HAS ACCUMULATED 660.4 HOURS SINCE LAST REPAIR. (K) 2G72 4U4 U H4EA E15EA 20060817001712006081700171CE 2006 8 17 2006FA0000796 120060721G2910S217840105 HYDRAULIC LINE CESSNA172 172RG 2072438CE HYDRAULIC SYS FAILED D O OTHER K FLUID LOSS CRCRUISE 1 CE035114U 172RG0243 NOSE GEAR HYDRAULIC ACTUATOR HOSE BLEW OUT OF CRIMP IN FLIGHT CAUSING LOSS OF ALL HYDRAULIC FLUID AND GEAR WOULD NOT GO UP OR DOWN, EVEN WITH HAND PUMP. THE MFG HOSE WAS NOT THE AEROQUIP TYPE WITH STEEL BRADING OR THE SCREW ON ENDS. RECOMMEND THE AEROQUIP 303 HIGH PRESSURE HOSE COULD NOT FIND A TT ON HOSE OR A DATE CODE. (K) 1H71 3O 3A17 20060817001832006081700183 2006 8 17 2006FA0000798 420060802G6122210638F GOVERNOR PROPELLER FAILED B IG0RO OTHER O OTHER ININSP/MAINT 1 NM03 THE GOVERNOR FAILED AFTER 106 HOURS OF OPERATION. THIS UNIT WILL NOT PERFORM THE OVERSPEED TEST. COMPONENT WAS OVERHAULED ON WO 39044 ON 5/18/06. (K) 20060817001752006081700175 2006 8 17 2006FA0000799 420060804G61228210024H GOVERNOR PROPELLER FAILED B IG0RO OTHER O OTHER ININSP/MAINT 1 NM03 THE GOVERNOR FAILED AFTER 772.1 HOURS OF OPERATION. PROPELLER SYNCHRONIZATION FUNCTION IS INOPERATIVE. COMPONENT WAS OVERHAULED ON WO 39914 ON 07/06/2006. (K) 20060817001802006081700180 2006 8 17 2006FA0000800 420060527G6122210638 GOVERNOR PROPELLER UNKNOWN B IG0RO OTHER O OTHER ININSP/MAINT 1 NM03 DOCUMENTATION RECEIVED WITH COMPONENT AFTER REPAIR DOES NOT SHOW TIME SINCE OVERHAUL. (K) 20060817001852006081700185 2006 8 17 2006FA0000801 420060413G61228210406H GOVERNOR PROPELLER FAILED B IG0RO OTHER O OTHER ININSP/MAINT 1 NM03 BETA VALVE STICKING CAUSING AIRCRAFT TO YAW DURING ENGINE POWER REDUCTION. GOVERNOR FAILED 291 HOURS AFTER INSTALLATION. (K) 20060817001842006081700184 2006 8 17 2006FA0000802 420060207G6122210638F FASTENER PROP GOVERNOR LOOSE B IG0RO OTHER O OTHER ININSP/MAINT 1 NM03 COMPONENT RECEIVED FROM OVERHAUL SHOP WITH HARDWARE LOOSE ON CONNECTOR. (K) 20060817001862006081700186 2006 8 17 2006FA0000803 420060221G61228210406 GOVERNOR PROPELLER FAILED B IG0RO OTHER O OTHER ININSP/MAINT 1 NM03 GOVERNOR WOULD NOT PASS TEST AFTER INSTALLATION. PROPELLER RPM DOES NOT DECREASE TO 1150 RPM WHEN TEST SWITCH ACTIVATED. UNIT WILL ALSO NOT PASS PY SHIFT TEST. (K) 20060817001882006081700188 2006 8 17 2006FA0000804 420060620G61228210406H GOVERNOR PROPELLER FAILED B IG0RO OTHER O OTHER ININSP/MAINT 1 NM03 BETA VALVE STICKING, CAUSING AIRCRAFT TO YAW DURING ENGINE POWER REDUCTION. GOVERNOR FAILED 171 HOURS AFTER INSTALLATION. (K) 20060817001772006081700177 2006 8 17 2006FA0000805 420060629G61228210406H GOVERNOR PROPELLER FAILED B IG0RO OTHER O OTHER ININSP/MAINT 1 NM03 BETA VALVE STICKING CAUSING AIRCRAFT TO YAW DURING ENGINE POWER REDUCTION. GOVERNOR FAILED 302.6 HOURS AFTER INSTALLATION. (K) 20060817001812006081700181 2006 8 17 2006FA0000806 420060502G6122210638F GOVERNOR PROPELLER FAILED B IG0RO OTHER O OTHER ININSP/MAINT 1 NM03 GOVERNOR WOULD NOT ACTIVATE USING TEST SWITCH ON INSTALLATION AFTER OVERHAUL. (K) 20060817001782006081700178 2006 8 17 2006FA0000807 420060207G61228210406 GOVERNOR PROPELLER FAILED B IG0RO OTHER O OTHER ININSP/MAINT 1 NM03 GOVERNOR WOULD NOT PASS TEST AFTER INSTALLATION. PROPELLER RPM DOES NOT DECREASE TO 1150 RPM WHEN TEST SWITCH ACTIVATED. (K) 20060817001742006081700174 2006 8 17 2006FA0000808 420060207G612282100224H GOVERNOR PROPELLER FAILED B IG0RO OTHER O OTHER ININSP/MAINT 1 NM03 BETA VALVE STICKING WHEN ENGINE POWER IS REDUCED CAUSING AIRCRAFT TO YAW. GOVERNOR FAILED 222 HOURS OF OPERATION AFTER OVERHAUL. (K) 20060817001792006081700179 2006 8 17 2006FA0000809 420060519G612282130391 GOVERNOR PROPELLER MISMANUFACTURED B IG0RO OTHER O OTHER ININSP/MAINT 1 NM03 COMPONENT RECEIVED WITH INCORRECT ARM INSTALLED ON BETA VALVE. ATTACHMENT HOLE FOR LINKAGE WAS TOO SMALL. (K) 20060817001762006081700176 2006 8 17 2006FA0000810 420060620G612258210007 GOVERNOR PROPELLER FAILED B IG0RO OTHER O OTHER ININSP/MAINT 1 NM03 PROPELLER GOVERNOR FAILED AFTER 2.5 HOURS OF OPERATION AFTER OVERHAUL. (K) 20060817001822006081700182 2006 8 17 2006FA0000811 420060616G6122210638F GOVERNOR PROPELLER OUT OF ADJUST B IG0RO OTHER O OTHER ININSP/MAINT 1 NM03 DURING TEST AFTER INSTALLATION, PROPELLER DROPS TO 1800 RPM. GOVERNOR SET TO INCORRECT LIMIT. (K) 20060817001872006081700187 2006 8 17 2006FA0000812 420060613G61228210406H GOVERNOR PROPELLER FAILED B IG0RO OTHER O OTHER ININSP/MAINT 1 NM03 BETA VALVE STICKING CAUSING AIRCRAFT TO YAW DURING ENGINE POWER REDUCTION. GOVERNOR FAILED 36 HOURS AFTER INSTALLATION. (K) 20060825000242006082500024CE 2006 8 25 2006FA0000816 120060815G2810 O-RING CESSNA182 182D 2072710CE FUEL CAP SPLIT D O OTHER K FLUID LOSS NRNOT REPORTED 1 SW058916X300 18253316 THE RT FUEL TANK CAP O-RING SPLIT AND FUEL SIPHONED OUT OF THE RT TANK DURING FLIGHT. 1H71 3O NT3A13 20060821000572006082100057SO 2006 8 21 2006FA0000817 220060816G74146310 MAGNETO BEECH 55 E55 1152732CE CONT O520 IO520C 17032SO LT ENGINE SEPARATED B O OTHER RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 1 SO131850F1600 TE1195 LT ENGINE OB MAGNETO IMPULSE COUPLING FROZE UP, CAUSING MAGNETO HOUSING TO COMPLETELY SEPARATE FROM ENGINE. 1L72 3O3 O 3A16 E5CE 20060825000332006082500033SO 2006 8 25 2006FA0000819 220060709G8530656612 EXHAUST VALVE BBAVIA7 7EC 2110120SW CONT C90 C9012F 17009SO NR 4 CYLINDER BROKEN B AWORO OTHER O OTHER NRNOT REPORTED 1 GL154715E1350 7EC59 42615012 WHEN THE NR 4 CYLINDER WAS REMOVED, THE EXHAUST VALVE HEAD WAS FOUND TO BE BROKEN OFF, ABOUT .5 INCH FROM THE FACE OF THE VALVE, CAUSING FAILURE OF THE PISTON AND FAILURE OF THE INTAKE VALVE. THE CIRCUMSTANCES OF THE FAILURE CAUSED A LOSS OF ENGINE POWER AND A FORCED LANDING IN A FIELD. THE PILOT WAS UNHARMED. (K) 1H71 3O3 O A759 E252 20060825000472006082500047CE 2006 8 25 2006FA0000820 120060706G2910511700712 TUBE CESSNA425 425 2076018CE HYD SYSTEM FAILED D O OTHER K FLUID LOSS NRNOT REPORTED 1 WP05 TUBE FAILED ON LOWER ATTACHMENT, ALL FLUID LOST, CAUSE UNKNOWN. (K) 1L72 3T RTA7CE 20060825000212006082500021CE 2006 8 25 2006FA0000821 120060726G5200 HINGE CESSNA421 421C 2076016CE CONT O520 GTSIO520* 17032SO DOOR CORRODED B AW4RO OTHER O OTHER NRNOT REPORTED 1 WP11485DS4783 421C0459 TO FIND USED SERVICEABLE HINGES AND HINGE SUPPORT FITTINGS FROM AC SALVAGE COMPANIES, EVERY HINGE THAT WAS RECEIVED, SAME TYPE OF CORROSION, BEARING AND BUSHINGS WERE RUSTED TO HINGE BOLT. BUSHINGS AND BEARING ARE PRESS FIT INTO HINGE SO AS TO ALLOW HINGE ASSY TO ROTATE ON BOLT. WHEN BOLT FREEZES TO BEARING AND BUSHINGS, BOLT THEN ROTATES IN SOFT ALUMINUM SUPPORT FITTING WHICH ALLOWS HOLES IN FITTING TO ELONGATE. IT WOULD APPEAR THAT THIS IS A CHRONIC PROBLEM. AS NOTED IN ORIGINAL MD PROBLEM SEEMS TO BE RELATED TO FACT THAT SUPPORT FITTINGS CAN RETAIN WATER. THERE IS NO SPECIFIC INSPECTION REQUIREMENT TO CHECK THESE HINGES FOR CORROSION AND SO CONDITION REMAINS UNDETECTED UNTIL BOLTS HAVE TO BE REMOVED. 1L72 3O3 O A7CE E7CE 20060825000422006082500042SO 2006 8 25 2006FA0000822 120060303G32209617800 SPRING PIPER PA34 PA34200 7103405SO LYC O360 IO360A1A 41514EA NLG UNKNOWN D O OTHER O OTHER NRNOT REPORTED 1 GL11210SK 347250307 WHEN COMPARING THE NEW SPRING TO OLD SPRING, USING A FISH SCALE, THE NEW TOOK 12 LBS TO OFFSET THE COILS THE OLD ONLY TOOK 7LBS. THIS IS BELIEVED TO CONTRIBUTE TO NOSE GEAR COLLAPSE. (K) 1L72 3O3 O A7SO 1E10 20060825000432006082500043SO 2006 8 25 2006FA0000823 120060303G3220400890AN2340A BOLT PIPER PA34 PA34200 7103405SO LYC O360 IO360A1A 41514EA NLG DOWNLOCK BENT D O OTHER O OTHER NRNOT REPORTED 1 GL11210SK 347250307 THIS WITH OTHER PROBLEMS LEAD TO SLOP IN THE DOWNLOCK OF THE NOSE GEAR. THIS CONTRIBUTED TO THE COLLAPSE OF THE NOSE GEAR. BOLT REPLACED WITH NEW. (K) 1L72 3O3 O A7SO 1E10 20060825000222006082500022SO 2006 8 25 2006FA0000824 120060303G32309506189 BUSHING PIPER PA34 PA34200 7103405SO NLG DOWLOCK BROKEN D O OTHER O OTHER NRNOT REPORTED 1 GL11210SK 347250307 INSPECTION REVEALED END OF BUSHING HAD BROKE OFF. REPLACE WITH NEW. THIS CONTRIBUTED TO SLOP IN NOSE GEAR DOWNLOCK MECHANISM AND GEAR COLLAPSE. (K) 1L72 3O A7SO 20060831000292006083100029CE 2006 8 31 2006FA0000825 120060804G2730MS21251B6L TURNBUCKLE BEECH B300 B300 1159232CE ELEVATOR MISMANUFACTURED B E81RK NONE W INADEQUATE Q C ININSP/MAINT 1 GL038YN 697 FL417 WHEN THE PART WAS MFG, THE SAFETY SLOT DID NOT LIME UP WITH THE END SLOTS. THIS DID NOT CAUSE A PROBLEM EITHER OPERATIONALLY, OR IN THE PROCESS OF SAFETYING THE TURNBUCKLE. (K) 2L72 4T RTA24CE 20060831000072006083100007CE 2006 8 31 2006FA0000826 120060727G271005010105364 CONTROL CABLE CESSNA172 172S 2072439CE LYC O360 IO360A1A 41514EA LT AILERON FRAYED B 7TFRK NONE O OTHER ININSP/MAINT 1 WP07533BM 172S8340 DURING AN ANNUAL INSPECTION OF THE AIRFRAME IT WAS FOUND THAT THE LT AILERON CROSSOVER CABLE WAS FRAYED AT THE ABBRASSION STRIP. THE PROBABLE CAUSE IS THE CABLE RUBBING AGAINST THE ABBRASION BLOCK. A POSSIBLE SOLUTION IS TO MAKE THE ABBRASION BLOCK OUT OF A SOFTER MATERIAL. (K) 1H71 3O3 ONT3A12 1E10 20060825000542006082500054CE 2006 8 25 2006FA0000827 120060727G271005010105362 CONTROL CABLE CESSNA172 172S 2072439CE LYC O360 IO360A1A 41514EA RT WING UNSERVICEABLE B 7TFRO OTHER O OTHER NRNOT REPORTED 1 WP07533BM5687 172S8340 DURING AN ANNUAL INSPECTION OF THE AIRFRAME IT WAS FUND THAT THE RT AILERON DIRECT CABLE WAS FRAYED AT THE FAIRLEAD ASSEMBLY. THE PROBABLE CAUSE IS THE CABLE RUBBING AGAINST THE FAIRLEAD ASSY. A POSSIBLE SOLUTION IS TO MAKE THE FAIRLEAD ASSY OUT OF A SOFTER MATERIAL. (K) 1H71 3O3 ONT3A12 1E10 20060831000062006083100006CE 2006 8 31 2006FA0000828 120060727G271005010105365 CONTROL CABLE CESSNA172 172S 2072439CE RT AILERON FRAYED B 7TFRK NONE O OTHER ININSP/MAINT 1 WP07533BM5687 172S8340 DURING AN ANNUAL INSPECTION OF THE AIRFRAME IT WAS FOUND THAT THE RT AILERON CROSSOVER CABLE WAS FRAYED AT THE FAIRLEAD ASSY. THE PROBABLE CAUSE IS THE CABLE RUBBING AGAINST THE FAIRLEAD ASSY. A POSSIBLE SOLUTION IS TO MAKE THE FAIRLEAD ASSY OUT OF A SOFTER MATERIAL. (K) 1H71 3O NT3A12 20060825000452006082500045SO 2006 8 25 2006FA0000829 220060809G74146320 POINTS SLICK AMTR LANCARLC41550FG 5150001GL CONT O550 TSIO550C SO MAGNETO BROKEN D O OTHER O OTHER NRNOT REPORTED 1 NE02400UK 653280 41062 802709 MAGNETO FAILURE, ON ECR ON INSP RT MAGNETO POINT HAD BROKEN IN HALF. (K) 1L71 3O3 ORTEXPA1L71E5SO 20060825000552006082500055CE 2006 8 25 2006FA0000830 120060807G3246MS20002C6 WASHER RAYTHN390 390 7150030CE MLG WHEEL MISINSTALLED B E81RO OTHER W INADEQUATE Q C NRNOT REPORTED 1 GL03390JV 0453 RB129 DURING WHEEL DISASSEMBLY FOR TIRE REPLACEMENT FOUND WHEEL TIE BOLT CHAMFERED WASHERS INSTALLED INCORRECTLY, WITH CHAMFERED SIDES TOWARDS WHEEL HALF. NOTED WASHERS TO BE BENT, WHEEL TIE BOLT HEADS UNDERSIDE RADIUSES DAMAGED. SUSPECT TECHNICIAN ASSEMBLING WHEELS AT PREVIOUS TIRE CHANGE AT ANOTHER FACILITY DID NTO FULLY FOLLOW COMPONENT MM AND WAS NOT FAMILIAR WITH INSTALLATION OF MS20002 SERIES CHAMFERED WASHERS. (K) 17 2 3F RTA00010WI 20060831000282006083100028CE 2006 8 31 2006FA0000831 120060807G3246MS20002C6 WASHER RAYTHN390 390 7150030CE WHEEL MISINSTALLED B E81RK NONE O OTHER ININSP/MAINT 1 GL03390JV284 RB129 DURING WHEEL DISASSEMBLY FOR TIRE REPLACEMENT FOUND WHEEL TIE BOLT CHAMFERED WASHERS INSTALLED INCORRECTLY, WITH CHAMFERED SIDES TOWARDS WHEEL HALF. NOTED WASHERS TO BE BENT, WHEEL TIE BOLT HEADS UNDERSIDE RADIUSES DAMAGED. SUSPECT TECHNICIAN ASSEMBLY WHEELS AT PREVIOUS TIRE CHANGE AT ANOTHER FACILITY DID NOT FULLY FOLLOW COMPONENT MM AND WAS NOT FAMILIAR WITH INSTALLATION OF MS20002 SERIES CHAMFERED WASHERS. (K) 17 2 3F RTA00010WI 20060825000252006082500025CE 2006 8 25 2006FA0000832 120060726G32341SX1T SWITCH BEECH MU300 400A 1155402CE MLG SELECTOR DAMAGED B E81RO OTHER O OTHER NRNOT REPORTED 1 GL03334SR3446 RK129 DURING SCHEDULED INSPECTION, FOUND LANDING GEAR WARNING HORN WOULD NOT OPERATE WITH LT POWER LEVER RETARDED. FOUND THROTTLE QUADRANT SWITCHES S25 AND S26 TO HAVE HIGH INTERNAL RESISTANCE. REPLACED SWITCHES AND ADJUSTED AS REQUIRED IAW MM. LANDING GEAR WARNING SYSTEM TESTS NORMAL. TYPICAL FAILURE MODE FOR THIS TYPE SWITCH USED ON THROTTLE LEVERS FOR VARIOUS FUNCTIONS. RECOMMEND A MORE EXTENDED LIFE SWITCH BEING UTILIZED, OR ESTABLISH A SCHEDULED 2600 HR REPLACEMENT SCHEDULE (IN CONJUNCTION WITH REPLACEMENT SCHEDULE (IN CONJUNCTION WITH ADDITIONAL C-INSPECTION/COMPONENT REPLACEMENT ITEMS). (K) 2H72 4F RTA16SW 20060825000402006082500040CE 2006 8 25 2006FA0000833 120060718G32405010614 BRAKE BEECH MU300 400A 1155402CE MLG SEIZED B E81RC ABORTED TAKEOFF J WARNING INDICATION TOTAKEOFF 1 GL03476LX RK376 DURING INITIAL TAKEOFF ROLL, FOLLOWING POSITIVE PARKING BRAKE RELEASE CHECK, LT MAIN WHEEL BRAKE LOCKED-UP. TAKEOFF ABORTED DUE TO SLOW ACCELERATION, POOR DIRECTIONAL CONTROL. UNABLE TO MOVE AIRCRAFT UNTIL RT BRAKE APPLIED AND RELEASED, THEN TAXI-IN NORMAL. REPLACED LT MAIN WHEEL BRAKE. ALSO REPLACED PN 4500A2 PARKING BRAKE VALVE ASSY. AS A PRECAUTION IAW OPERATOR REQUEST. REPLACED LT MAIN WHEEL ASSY. DUE TO FLAT-SPOTTED TIRE. AT THIS TIME SUSPECTED FAULT IS IN LT BRAKE ASSY, BRAKE ASSY. QUARANTINED BY OPERATOR FOR FURTHER EVALUATION. (K) 2H72 4F RTA16SW 20060825000502006082500050NE 2006 8 25 2006FA0000834 220060728G7322D8531 LINK ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE THROTTLE ARM SEPARATED D O OTHER F FLT CONT AFFECTED NRNOT REPORTED 1 NM07494SH486 10878 3043948A ON 7/26/06 PILOT REPORTED THAT WHILE FLYING THROTTLE CONTROL BECOME INEFFECTIVE. AIRCRAFT LANDED SAFELY AT AIRFIELD AND PUSHED TO HANGAR. INSPECTED THROTTLE CONTROL ATTACHMENT AT ENGINE THROTTLE BODY AND FOUND UPPER ROD END OF LINK, PN D8531 SEPARATED. PHOTOGRAPH TAKEN AND SENT OT MFG, IAW INSTRUCTION , LINK PN B5642 ORDERED AND RETURNED THE SEPARATED LINK PN D8531 TO MFG FOR FURTHER INVESTIGATION. (K) 1G71 3O3 O H11NM 1E4 20060825000442006082500044EA 2006 8 25 2006FA0000835 120060811G2500SPH1606B3 INVERTER CNDAIRCL600 CL6002B16 1900305EA GE CF34 CF341A NE STATIC FREQUENCYMISINSTALLED D O OTHER W INADEQUATE Q C NRNOT REPORTED 1 NE05372G 5351 THIS STATIC FREQUENCY INVERTER WAS INSTALLED IN THE STATED AIRCRAFT ON JUNE 2, 2006. AT THE TIME OF INSTALLATION, THE PART HAD BEEN OVERHAULED BY CONSOLIDATED AC SUPPLY CO, INC. UNDER WO NR 7314, DATED MAR 14,2006. THE STATIC FREQUENCY INVERTER FAILED ON AUGUST 8, 2006. 2L72 4F4 FRTA21EA E15NE 20060825000492006082500049EA 2006 8 25 2006FA0000836 120060811G2130 UNKNOWN CNDAIRCL604 CL604 1900301EA GE CF34 CF34* NE CABIN PRESSURE UNKNOWN D O OTHER O OTHER NRNOT REPORTED 1 NE03373G 5556 REASON REMOVED, PRESSURIZATION CLIMBS AFTER T/O UP TO 2000 FPM. THEN CATCHES AND WORKS DURING FLIGHT. PRIOR TO INSTALLATION IN THE AIRCRAFT, THIS COMPONENT WAS INSPECTED, UNDER WO NR U22732, DATED MAR 30, 2006. COMPONENT WAS INSTALLED ON 06/09/2006. (K) 2L72 4F4 FRTA21EA E15NE 20060825000562006082500056CE 2006 8 25 2006FA0000837 120060607G261222412886 FIRE LOOP BEECH 1900 1900C 1154161CE PWA PT6 PT6A65B 52043EA RT NACELLE BROKEN D O OTHER O OTHER NRNOT REPORTED 1 NM07172GA UB11 PS32232 PILOT EXPERIENCED A FIRE WARNING ANNUNCIATION DURING TAKEOFF ROLL. PILOT ABORTED TAKEOFF. MAINTENANCE FOUND THAT ONE FIRELOOP HAD FAILED AND CAUSED THE FALSE FIRE INDICATION. (K) 2L72 4T4 TRTA24CE E4EA 20060825000532006082500053 2006 8 25 2006FA0000839 120060822G32133581525115 BRACE RAYTHN MLG STRUT MISDRILLED C O OTHER W INADEQUATE Q C NRNOT REPORTED 1 CE09 072 THIS IS A NEW PART PURCHASED THRU MFG (RAPID). BRACE ASSEMBLY HAS 4 BOLT HOLES THAT ARE NOT DRILLED TO THE REQUIRED SIZE TO ACCOMMODATE THE BOLT THAT IS TO BE INSTALLED. HOLE I.D. SIZE IS 0.185. BOLT O.D. SIZE IS 0.310. 20060825000282006082500028CE 2006 8 25 2006FA0000840 120060822G52803511513022 ANGLE BEECH 36 A36 1151604CE MLG DOOR CRACKED D K NONE O OTHER ININSP/MAINT 1 GL19 360 E3384 DURING A ROUTINE ANNUAL INSPECTION IT WAS FOUND THAT BOTH THE LT AND RT IB GEAR DOOR AFT HINGE ANGLES (P/N'S 35-115130-22, -24, 35-115070-16 AND -18 WERE CRACKED. IT IS MY OPINION THAT THIS IS DUE TO THE FACT THAT MFG HAS CHANGED THE DESIGN OF THE INBOARD GEAR DOOR FROM A STAMPED ASSY TO A MILLED PART. THIS CONDITION OBVIOUSLY IS PRESENT IN OTHER LIKE MODELS AND BEECH HAS ACKNOWLEDGED THE PROBLEM IN THEIR PARTS BOOK AS THEY GIVE INSTRUCTIONS FOR ORDERING DIFFERENT PART NUMBERS. THE NEW PART NUMBER PARTS ARE MADE FROM .050" ALUMINUM WHILE THE ORIGINAL PARTS WERE MADE FROM .032 INCHES ALUMINUM. THE CRACKS COULD EASILY GO UNDETECTED AND A SB IS NEEDED TO HELP OTHERS FIND AND ELIMINATE THESE CRACKS. 1L71 3O 3A15 20060825000292006082500029CE 2006 8 25 2006FA0000841 120060822G52803511513022 ANGLE BEECH 36 A36 1151604CE MLG DOOR CRACKED D K NONE O OTHER ININSP/MAINT 1 GL19 360 E3384 DURING A ROUTINE ANNUAL INSPECTION IT WAS FOUND THAT BOTH LT AND RT IB GEAR DOOR AFT HINGE ANGLES (P/N'S 35-115130-22, -24, 35-115070-16 AND -18 WERE CRACKED. IT IS MY OPINION THAT THIS IS DUE TO FACT THAT MFG HAS CHANGED DESIGN OF THE IB GEAR DOOR FROM A STAMPED ASSY TO A MILLED PART. THIS CONDITION OBVIOUSLY IS PRESENT IN OTHER LIKE MODELS AND MFG HAS ACKNOWLEDGED THE PROBLEM IN THEIR PARTS BOOK AS THEY GIVE INSTRUCTIONS FOR ORDERING DIFFERENT PN. THE NEW PN PARTS ARE MADE FROM .050 INCH ALUMINUM WHILE ORIGINAL PARTS WERE MADE FROM .032 INCH ALUMINUM. THE CRACKS COULD EASILY GO UNDETECTED AND A SB IS NEEDED TO HELP OTHERS FIND AND ELIMINATE THESE CRACKS. 1L71 3O 3A15 20060825000302006082500030CE 2006 8 25 2006FA0000842 120060822G52803511513022 ANGLE BEECH 36 A36 1151604CE MLG DOOR CRACKED D K NONE O OTHER ININSP/MAINT 1 GL19 360 E3384 DURING A ROUTINE ANNUAL INSPECTION IT WAS FOUND THAT BOTH THE LT AND RT IB GEAR DOOR AFT HINGE ANGLES (P/N'S 35-115130-22, -24, 35-115070-16 AND -18 WERE CRACKED. IT IS MY OPINION THAT THIS IS DUE TO THE FACT THAT MFG HAS CHANGED THE DESIGN OF THE IB GEAR DOOR FROM A STAMPED ASSY TO A MILLED PART. THIS CONDITION OBVIOUSLY IS PRESENT IN OTHER LIKE MODELS AND MFG HAS ACKNOWLEDGED THE PROBLEM IN THEIR PARTS BOOK AS THEY GIVE INSTRUCTIONS FOR ORDERING DIFFERENT PART NUMBERS. THE NEW PN PARTS ARE MADE FROM .050 INCH ALUMINUM WHILE THE ORIGINAL PARTS WERE MADE FROM .032 INCH ALUMINUM. THE CRACKS COULD EASILY GO UNDETECTED AND A SB IS NEEDED TO HELP OTHERS FIND AND ELIMINATE THESE CRACKS. 1L71 3O 3A15 20060825000312006082500031CE 2006 8 25 2006FA0000843 120060822G52803511513022 ANGLE BEECH 36 A36 1151604CE MLG DOOR CRACKED D K NONE O OTHER ININSP/MAINT 1 GL19 360 E3384 DURING A ROUTINE ANNUAL INSPECTION IT WAS FOUND THAT BOTH THE LT AND RT IB GEAR DOOR AFT HINGE ANGLES (P/N'S 35-115130-22, -24, 35-115070-16 AND -18 WERE CRACKED. IT IS MY OPINION THAT THIS IS DUE TO THE FACT THAT MFG HAS CHANGED THE DESIGN OF THE IB GEAR DOOR FROM A STAMPED ASSY TO A MILLED PART. THIS CONDITION OBVIOUSLY IS PRESENT IN OTHER LIKE MODELS AND MFG HAS ACKNOWLEDGED THE PROBLEM IN THEIR PARTS BOOK AS THEY GIVE INSTRUCTIONS FOR ORDERING DIFFERENT PN. THE NEW PN PARTS ARE MADE FROM .050 INCH ALUMINUM WHILE THE ORIGINAL PARTS WERE MADE FROM .032 INCH ALUMINUM. THE CRACKS COULD EASILY GO UNDETECTED AND A SB IS NEEDED TO HELP OTHERS FIND AND ELIMINATE THESE CRACKS. 1L71 3O 3A15 20060825000372006082500037CE 2006 8 25 2006FA0000847 120060822G52803511513022 ANGLE BEECH 36 A36 1151604CE MLG DOOR CRACKED D K NONE O OTHER ININSP/MAINT 1 GL1945MS 360 E3384 DURING A ROUTINE ANNUAL INSPECTION IT WAS FOUND THAT BOTH THE LT AND RT IB GEAR DOOR AFT HINGE ANGLES (P/N'S 35-115130-22, -24, 35-115070-16 AND -18 WERE CRACKED. IT IS MY OPINION THAT THIS IS DUE TO THE FACT THAT MFG HAS CHANGED THE DESIGN OF THE IB GEAR DOOR FROM A STAMPED ASSY TO A MILLED PART. THIS CONDITION OBVIOUSLY IS PRESENT IN OTHER LIKE MODELS AND BEECH HAS ACKNOWLEDGED THE PROBLEM IN THEIR PARTS BOOK AS THEY GIVE INSTRUCTIONS FOR ORDERING DIFFERENT PN. THE NEW PN PARTS ARE MADE FROM .050 INCH ALUMINUM WHILE THE ORIGINAL PARTS WERE MADE FROM .032 INCH ALUMINUM. THE CRACKS COULD EASILY GO UNDETECTED AND A SB IS NEEDED TO HELP OTHERS FIND AND ELIMINATE THESE CRACKS. 1L71 3O 3A15 20060825000382006082500038CE 2006 8 25 2006FA0000848 120060822G52803511513022 ANGLE BEECH 36 A36 1151604CE MLG DOOR CRACKED D K NONE O OTHER ININSP/MAINT 1 GL1945MS 360 E3384 DURING A ROUTINE ANNUAL INSPECTION IT WAS FOUND THAT BOTH THE LT AND RT IB GEAR DOOR AFT HINGE ANGLES (P/N'S 35-115130-22, -24, 35-115070-16 AND -18 WERE CRACKED. IT IS MY OPINION THAT THIS IS DUE TO THE FACT THAT MFG HAS CHANGED THE DESIGN OF THE IB GEAR DOOR FROM A STAMPED ASSY TO A MILLED PART. THIS CONDITION OBVIOUSLY IS PRESENT IN OTHER LIKE MODELS AND MFG HAS ACKNOWLEDGED THE PROBLEM IN THEIR PARTS BOOK AS THEY GIVE INSTRUCTIONS FOR ORDERING DIFFERENT PN. THE NEW PN PARTS ARE MADE FROM .050 INCH ALUMINUM WHILE THE ORIGINAL PARTS WERE MADE FROM .032 INCH ALUMINUM. THE CRACKS COULD EASILY GO UNDETECTED AND A SB IS NEEDED TO HELP OTHERS FIND AND ELIMINATE THESE CRACKS. 1L71 3O 3A15 20060825000392006082500039CE 2006 8 25 2006FA0000849 120060822G52803511513022 ANGLE BEECH 36 A36 1151604CE MLG DOOR CRACKED D K NONE O OTHER ININSP/MAINT 1 GL1945MS 360 E3384 DURING A ROUTINE ANNUAL INSPECTION IT WAS FOUND THAT BOTH THE LT AND RT IB GEAR DOOR AFT HINGE ANGLES (P/N'S 35-115130-22, -24, 35-115070-16 AND -18 WERE CRACKED. IT IS MY OPINION THAT THIS IS DUE TO THE FACT THAT MFG HAS CHANGED THE DESIGN OF THE IB GEAR DOOR FROM A STAMPED ASSY TO A MILLED PART. THIS CONDITION OBVIOUSLY IS PRESENT IN OTHER LIKE MODELS AND MFG HAS ACKNOWLEDGED THE PROBLEM IN THEIR PARTS BOOK AS THEY GIVE INSTRUCTIONS FOR ORDERING DIFFERENT PN. THE NEW PN PARTS ARE MADE FROM .050 INCH ALUMINUM WHILE THE ORIGINAL PARTS WERE MADE FROM .032 INCH ALUMINUM. THE CRACKS COULD EASILY GO UNDETECTED AND A SB IS NEEDED TO HELP OTHERS FIND AND ELIMINATE THESE CRACKS. 1L71 3O 3A15 20060913003982006091300398CE 2006 9 13 2006FA0000851 120060812G323155421029 TORQUE TUBE CESSNA500 560CESSNA 2076750CE NLG DOOR CRACKED D O OTHER O OTHER NRNOT REPORTED 1 SW99 1461 THE NOSE LANDING GEAR DOOR TORQUE TUBE IS CRACKED AT THE WELD THAT ATTACHES THE MOUNTING BRACKET. (K) 2L72 4F RTA22CE 20060915001332006091500133CE 2006 9 15 2006FA0000852 120060712G528055421029 TORQUE TUBE CESSNA500 560CESSNA 2076750CE NOSE GEAR DOORS CRACKED C O OTHER O OTHER NRNOT REPORTED 1 SW99 3016 THE NOSE LANDING GEAR DOOR TORQUE TUBE IS CRACKED AT THE WELD THAT ATTACHES THE MOUNTING BRACKET. (K) 2L72 4F RTA22CE 20060831000022006083100002CE 2006 8 31 2006FA0000853 120060718G323155421029 TORQUE TUBE CESSNA500 560CESSNA 2076750CE NLG DOOR CRACKED D K NONE O OTHER NRNOT REPORTED 1 SW99 4646 THE NOSE LANDING GEAR DOOR TORQUE TUBE IS CRACKED AT THE WELD THAT ATTACHES THE MOUNTING BRACKET. (K) 2L72 4F RTA22CE 20060927000192006092700019CE 2006 9 27 2006FA0000854 120060718G323155421029 TORQUE TUBE CESSNA500 560CESSNA 2076750CE NLG DOORS CRACKED D O OTHER O OTHER NRNOT REPORTED 1 SW99 4182 THE NOSE LANDING GEAR DOOR TORQUE TUBE IS CRACKED AT THE WELD THAT ATTACHES THE MOUNTING BRACKET. (K) 2L72 4F RTA22CE 20060926002512006092600251CE 2006 9 26 2006FA0000855 120060720G323155421029 TORQUE TUBE CESSNA500 560CESSNA 2076750CE NOSE GEAR DOORS DAMAGED D O OTHER O OTHER NRNOT REPORTED 1 SW99 THE NOSE LANDING GEAR DOOR TORQUE TUBE RECEIVED NEW FROM MFG HAS THE ATTACHMENT ARMS MISALIGNED. HOLE FOR THE LINKAGE ATTACHMENT BOLT HAS BEEN DRILLED WITH LESS THAN ALLOWABLE EDGE DISTANCE TO COMPENSATE FOR THE MISALIGNED ARMS. (K) 2L72 4F RTA22CE 20060913003972006091300397CE 2006 9 13 2006FA0000856 120060712G323155421029 TORQUE TUBE CESSNA500 560CESSNA 2076750CE NLG DOOR CRACKED D O OTHER O OTHER NRNOT REPORTED 1 SW99 1615 THE NOSE LANDING GEAR DOOR TORQUE TUBE IS CRACKED AT THE WELD THAT ATTACHES THE MOUNTING BRACKET. (K) 2L72 4F RTA22CE 20060927000202006092700020CE 2006 9 27 2006FA0000857 120060718G3240169580001143 LINE BEECH 23 C24R 1151254CE LYC O360 IO360A1A 41514EA BRAKE SYSTEM CHAFED D O OTHER O OTHER NRNOT REPORTED 1 NE01824BA MC533 AIRCRAFT LEAKING HYDRAULIC FLUID. INSP FOUND RT BRAKE LINE LEAKING APPROX 8 INCHES FWD OF WING SPAR. FOUND ALUMINUM BRAKE LINE CHAFING AGAINST WIRE REINFORCED HEATING DUCT. ALSO, EVIDENCE OF CORROSION FROM CONTACT WITH DISSIMILAR METALS. CUT OFF DAMAGED AREA AND REPLACED WITH NEW MATERIAL AND ON UNION. ADDED NYLON SPIRAL WRAP FOR CHAFE PROTECTION. (K) 1L71 3O3 O A1CE 1E10 20060926002542006092600254GL 2006 9 26 2006FA0000858 120060718G781014836001 MUFFLER CIRRUSSR SR22 2130001GL CONT O550 IO550N 17042SO LT, RT EXHAUST DAMAGED B QRQRO OTHER O OTHER NRNOT REPORTED 1 SW05948AH 0329 LT AND RT MUFFLER FLAME ARRESTERS FOLDED OVER FROM EXHAUST GAS HEAT COMPOUNDED OVER THE 609 HOURS OF THEIR SERVICE LIFE. (K) 1L71 3O3 ONTA00009CHE3SO 20060828000012006082800001CE 2006 8 28 2006FA0000859 120060817G2720 SERVO CESSNA525 525 2076601CE WILINTFJ44 FJ44 66000GL RUDDER TRIM MALFUNCTIONED B O OTHER O OTHER NRNOT REPORTED 1 SW99719D 1494 5250075 TECH WAS IN TAILCONE AREA AND NOTICED METAL SHAVINGS UNDER RUDDER SERVO ASSY. INVESTIGATION REVEALED THAT THE SERVO DRUM CABLE WAS CUTTING THROUGH THE DRUM GROOVES ARE TO SEVERE SIDE LOADING ON THE CABLE. SUSPECT THAT THE SEVERE SIDE LOAD CONDITION RESULTED FROM IMPROPER PLACEMENT OF SERVO CABLE TO MAIN SYSTEM CABLE CLAMP. ROTATION OF THE CLAMP ON THE MAIN RUDDER SYSTEM CABLE INDUCED THE SIDE LOAD. THIS AC WAS NOT IN FOR AN INSPECTION AND THE TECH FOUND THIS CONDITION BY CHANCE. (K) 1L72 4F4 FRTA1WI E3GL 20060926000712006092600071EA 2006 9 26 2006FA0000860 220060623G8520LW12581 CRANKSHAFT PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA LT ENGINE DAMAGED D O OTHER O OTHER NRNOT REPORTED 1 NE024095L 318152178 L816261A PILOT REDUCED POWER FOR LANDING, PUSHED NOSE OF AC OVER TO DESCEND, LF ENGINE RPM INCREASED. PULL NOSE OF AC UP, RPM DECREASED. THEN PILOT REPORTED SLIGHT VIBRATION AND THE BANG. LT ENGINE WAS SHUTDOWN. AIRCRAFT LANDED WITHOUT INCIDENT. INSPECTION OF LT ENGINE WAS PERFORMED AND FOUND THAT THE FRONT 2 CYLINDERS WERE THE ONLY ONES STILL ATTACHED TO THE FRONT THIRD OF THE CRANKSHAFT (THE CRANKSHAFT WAS IN (3) PIECES). (K) 1L72 3O3 O A20SO E14EA 20060831000032006083100003SO 2006 8 31 2006FA0000861 120060729G2910 HYDRAULIC LINE PIPER PA23 PA23250 7102308SO LYC O540 IO540* 41532EA HYDRAULIC SYS CHAFED B K NONE K FLUID LOSS NRNOT REPORTED 1 NE01401PJ 274112 AIRCRAFT SUFFERED HYDRAULIC PRESSURE LOSS, FOUND LT RUDDER CABLE CHAFED THRU PRESSURE LINE BEHIND PILOTS LT SIDE WALL, AREA IS DIFFICULT TO INSPECT DUE TO SIDE WALL/INSULATION. LINE REPLACE, SYSTEM SERVICED OPERATES NORMAL. PLEASE FIND BELOW ADDITIONAL ITEMS DISCUSSED IAW TELECOM DATED 8/15/2006. PROBLEM WITH THE CABLE CHAFING THROUGH THE PRESSURE LINE HAS BEEN IDENTIFIED ONE TIME PREVIOUS TO THIS INCIDENT. BOTH OCCURRENCES HAPPENED BETWEEN 6000-7000 AC HOURS. PROBLEM IN BOTH CASES WAS NOT IDENTIFIED UNTIL HYDRAULIC LEAK WAS DETECTED. MECHANIC REPOSITIONED THE NEW LINE TO ALLEVIATE THE PROBLEM. (K) 1L72 3O3 O 1A10 1E4 20060926000572006092600057SO 2006 9 26 2006FA0000862 120060828G3097 WIRE PIPER PA31T PA31T 7103124SO PWA PT6 PT6A28 EA BROKEN D CH ABORTED TAKEOFF DEACTIVATE SYST/CIRCUITS RN PARTIAL RPM/PWR LOSS FALSE WARNING TOTAKEOFF 1 EA35160TR4327 31T7920036 51943 RTBETA-LIGHT CAME ON DURING TAKE-OFF ROLL. PROPELLER RPM DROPPED HEAVILY. PULLED CIRCUIT BREAKER. RPM RETURNED TO NORMAL. FOUND ALL SINGLE WIRE INSULATIONS IN WIRE BUNDLE TOENGINE/PROP SWITCHES, INCLUDING DE-ICE WIRES AT REDUCTION GEAR BOX HARDENED AND BROKEN, MAKING CONTACT. WIRE BUNDLE RUNS UNDERNEATH EXHAUST FLANGE. NO OTHER DAMAGE DUE TO FAST PULLING CIRCUIT BREAKER, IF THIS HAPPENS DURING FLIGHT, IT COULD LEAD TO A DANGEROUS SITUATION. REPLACED ALL WIRING. 1L72 3T4 T A8EA E4EA 20060922000832006092200083CE 2006 9 22 2006FA0000863 120060718G781015501261 CLAMP CESSNA337 337H 2075732CE CONT O360 IO360GB 17025SO EXHAUST CRACKED D K NONE O OTHER ININSP/MAINT 1 NE011258S39 33701894 WHILE DOING A PRE-TOW WALKAROUND INSPECTION, NOTICED THE FRONT ENGINE EXHAUST TAIL PIPES WERE LOOSE AND SUPPORT CLAMPS PN 15501261 BROKEN ON BOTH LT AND RT SIDES. BOTH CLAMPS HAD BOTH OUTER EARS BROKEN OFF AT WELDMENT. PREVIOUS CLAMPS FAILED AFTER EXHAUST SYSTEM OVERHAUL AFTER 191 HOURS. SUSPECT THAT FAILURES MAY BE DUE TO EXCESS VIBRATION FROM MUFFLE BALL JOINT CLAMPS INSTALLED TOO TIGHTLY. (K) 1H72 3O3 O A6CE E1CE 20060927000052006092700005EA 2006 9 27 2006FA0000864 220060807G7414M3548 ROTOR SLICK PIPER PA28 PA28161 7102803SO LYC O320 O320D3G 41508EA MAGNETO BROKEN D O OTHER O OTHER NRNOT REPORTED 1 NE039286M 02110612 288616044 RL681539A ROTOR SHAFT BROKEN AT CAM SLOT. REMOVED AND INSPECTED MAGNETO DUE TO 5 PERCENT TIMING DISCREPANCY. INSTALLED NEW MAGNETO. (K) 1L71 3O3 O 2A13 E274 20060922000582006092200058SO 2006 9 22 2006FA0000865 120060226G32131180500 STRUT PIPER PA17 PA17 7101702SO CONT A65 A65* 17003SO LANDING GEAR DAMAGED D O OTHER O OTHER NRNOT REPORTED 1 GL134879H725 17178 WHEN CHANGING SHOCK CORDS ON THIS AC, NOTICED A DISCOLORATION OF THE INNER STRUT TUBE (LONGER ONE, SUB PN 1180400) AND REMOVED IT FROM THE OUTER TUBE (SHORTER, SUB PN 1180300) ONE OF THE INNER STRUT TUBES WAS CORRODED APPROX 50 PERCENT OF CIRCUMFERENCE. THE OTHER INNER STRUT HAD MULTIPLE CORROSION HOLES THROUGH ALL THE METAL. BOTH SHORT TUBES (OUTER) SHOWED OVAL ELONGATION AT THE ENDS INDICATING FLEXING/BENDING OF THE ASSY DURING LANDINGS AND TAKEOFF. RELATIVELY NEW (HOURS) BUNGEES KEPT THIS GEAR FROM FINAL FAILURE AND RESULTANT GROUND LOOP. THE BUNGEE CORDS, WHEN INSTALLED, COVER THIS AREA AND ALSO USUALLY HAVE A CLOTH OR ALUMINUM FAIRING OVER THEM. DETECTION OF THIS REQUIRES REMOVAL OF THE FAIRINGS AT A 1H71 3O3 O A805 E205 20060927000112006092700011CE 2006 9 27 2006FA0000866 120060821G324650300001087 WHEEL BEECH 90 C90A 1152911CE MLG CRACKED B O OTHER O OTHER NRNOT REPORTED 1 EA21304TC214 LJ1719 AFTER SEVERAL ATTEMPTS TO FIND SOURCE OF ONGOING TIRE LEAKAGE, WHEEL ASSEMBLY WAS REMOVED FROM AIRCRAFT AND NSPECTED. FOUND 2 CRACKS OPPOSITE OF (1) OTHER ALONG INNER RADIUS OF INNER WHEEL HALF. DURING DISASSEMBLY IT WAS NOTED THAT WHEEL ASSEMBLY TIE BOLT NUTS DID NOT HAVE ANY SELF LOCKING FEATURE. WHEEL WAS ORIGINAL EQUIPMENT WITH ONLY (1) TIRE CHANGE SINCE NEW. (K) 1L72 3T RT3A20 20060831000042006083100004CE 2006 8 31 2006FA0000867 120060818G2400635A050 SUPPORT BRACKET CESSNA525 525 2076601CE WILINTFJ44 FJ44 66000GL ATTENUATOR CRACKED B O OTHER O OTHER NRNOT REPORTED 1 GL17719D 5250075 FOUND THE LT AND RT ATTENUATOR ACTUATOR LOWER SUPPORT BRACKETS TO BE CRACKED. THESE BRACKETS HAVE BEEN REPLACED BY ACCOMPLISHMENT OF SB AT PRIOR DATE. WE HAVE REPEATEDLY FOUND THESE BRACKETS. CRACKED AGAIN AND AGAIN AFTER THEY ARE REPLACED BY THE SB. CUSTOMERS OF HAVEING CHANGE THE BRACKETS OVER AND OVER WHEN THE SB WAS SUPPOSED TO BE ADDRESSING THE PROBLEM WITH NEWER, IMPROVED BRACKETS. RECOMMEND THE OEM STRENGTHEN THE REPLACEMENT BRACKETS. (K) 1L72 4F4 FRTA1WI E3GL 20060927000102006092700010CE 2006 9 27 2006FA0000868 120060720G284062266502 SWITCH CESSNA650 650 2076802CE GARRTTTFE731TFE731* 01518WP FUEL LOW LEVEL MISMANUFACTURED B O OTHER W INADEQUATE Q C NRNOT REPORTED 1 GL17993LC 6500027 AFTER ARRIVAL, FOUND FUEL LEAK NEAR IB END OF RT WING. INVESTIGATION SHOWED THE LOW LEVEL FUEL LIMIT SWITCH WAS NOT ASSEMBLED. THE FLOAT, PN L15F2, WAS NOT ATTACHED TO THE MOUNT ASSY PN 62266503. THIS ALLOWED FUEL TO LEAK FROM THE WING. SWITCH WAS ASSEMBLED, REINSTALLED AND LEAK CHECKED. NO FURTHER LEAKS NOTED. (K) 2L72 4F4 F A9NM E6WE 20060831000012006083100001CE 2006 8 31 2006FA0000869 120060315G550035405130 FITTING BEECH 35 35BEECH 1151502CE CONT E185 E185* 17014SO STABILIZER CRACKED D K NONE O OTHER ININSP/MAINT 1 GL274473V4329 D1291 STABILIZER FITTING REMOVED FROM AC TO BE CHECKED IAW AD76-05-04. DYE PENETRANT INSPECTION REVEALED (2) CRACKS RADIATING FROM THE LOWER BOLT HOLE ATTACHMENT POINTS AS DEPICTED IN DWG. PROBABLE CAUSE COULD BE FROM IMPROPER TORQUE OF ATTACHMENT BOLTS AT PREVIOUS INSPECTION. THIS PART IS TO BE INSPECTED EACH 1,000 HRS TIME IN SERVICE. SUGGEST PROPER TORQUE BE APPLIED DURING INSTALLATION OR UPGRADE OLD FITTING TO THE NEW STYLE FITTING PN 35405130. (K) 1L71 3O3 O A777 E246 20060914001962006091400196GL 2006 9 14 2006FA0000870 220060819G732321722 GOVERNOR HUGHES369 369E 4470707WP ALLSN 250C 250C20B 03013GL ENGINE MALFUNCTIONED D O OTHER O OTHER NRNOT REPORTED 1 CE07564WP 1003 0564E CAE837044 PILOT OBSERVED ENGINE RPM DROOPED TO APPROX 98 PERCENT N2 AND WOULD NOT BEEP UP. THIS CAUSING LOW ROTOR WARNING TO ILLUMINATE, AS WELL AS AUDIO WARNING TO SOUND. PILOT ENTERED AN AUTO ROTATION AND OBSERVED THE ENGINE SURGING AS HE APPROACHED THE GROUND. NORMAL AUTO ROTATION LANDING WAS MADE WITH NO DAMAGE TO AIRCRAFT OR INJURY TO PERSONS. FOR TROUBLESHOOTING PURPOSE MAINTENANCE CONDUCTED AN ENGINE START AND OBSERVED THE ENGINE WOULD NOT BEEP ABOVE 98 PERCENT N2 AND MINOR SURGING OF THE ENGINE. MAINTENANCE REPLACED THE PT GOVERNOR. ENGINE AND AIRCRAFT PERFORMED NORMAL. AIRCRAFT RETURNED TO SERVICE FOLLOWING OPS FLIGHT CHECK. (K) 1G71 3U3 U H3WE E4CE 20060926001682006092600168EA 2006 9 26 2006FA0000871 220060819G732230804 FLOAT PRECISION CESSNA150 152 2071835CE LYC O235 O235N2C 41505EA CARBURETOR LEAKING D O OTHER O OTHER NRNOT REPORTED 1 NM1395429 732 DT21385 15285892 AIRCRAFT NOTED AS HAVING FUEL DRIPPING FROM BOTTOM COWL, FOUND CAR LEAKING FUEL WHILE SITTING STATIC, REMOVED AND CHECKED CARBURETOR. DETERMINED (1) OF THE (2) PONTOONS OF THE PLASTIC FLOAT WAS FULL OF FUEL, CONTACT MADE WITH MFG WHO SUGGESTED THEY WERE AWARE OF THE PROBLEM AND HAVE SUPERSEDED THE FLOAT TO A NEWER VERSION, REPLACED THE FLOAT WITH THE 30-864 AND 29-184 FLOAT VALVE CLIP, OPS CHECKED OK. (K) 1H71 3O3 ONT3A19 E223 20060914000282006091400028EU 2006 9 14 2006FA0000872 120060804G276065WE0103036 PUMP HWKSLYDH1254HS125400F 230145 EU GARRTTTFE731TFE731* 01518WP SPOILERS FAILED A IAVRO OTHER O OTHER NRNOT REPORTED 1 WP254QB 25255 84435 NR 1 HYDRAULIC SYS FAILURE RESULTING IN LOSS OF HYDRAULIC FLUID. IN FLIGHT DIVERT AFTER DEPARTURE, AFTER ALTERNATE LANDING GEAR/ FLAP EXTNESION. LT HYDRAULIC SYSTEM PRESSURE LOW LIGHT ILLUMINATED ON TAKEOFF AFTER 80 KTS, CONTINUED TAKEOFF. AFTER COMPLETING HYDRAULIC FAILURE CHECK LIST, DETERMINED THERE WAS A HYDRAULIC LEAK. DECLARED AN EMERGENCY AND DIVERTED. COMPLETED THE HYDRAULIC LOSS CHECKLIST, WHICH BASICALLY INVOLVED PUMPIN GHE LANDING GEAR DOWN AND FLAPS TO POSITION. LANDED WITHOUT INCIDENT, STOPPED ON THE RUNWAY. REPLACED 2 PASSENGERS, PINNED THE LANDING GEAR AND TOWED THE AC TO THE FBO RAMP. (K) 2L72 3F4 FRTA3EU E6WE 20060927000222006092700022CE 2006 9 27 2006FA0000874 120060130G8011PM1201H STARTER CESSNA172 172M 2072418CE LYC O320 O320* 41508EA ENGINE FAILED D O OTHER O OTHER NRNOT REPORTED 1 NM0170323 17267200 PM1201-H STARTER FAILED TO ENGAGE. INSTALLED DIFFERENT MFG STARTER. (K) 1H71 3O3 ONT3A12 E274 20060927000292006092700029CE 2006 9 27 2006FA0000878 120060207G8011 PINION GEAR CESSNA172 172S 2072439CE LYC IO360 IO360L2A EA STARTER FAILED D O OTHER O OTHER NRNOT REPORTED 1 NM01510LP 172S9510 PINION GEAR WOULD NOT ENGAGE RING GEAR. (K) 1H71 3O3 ONT3A12 1E10 20060927000232006092700023CE 2006 9 27 2006FA0000879 120060630G8011 PINION GEAR CESSNA172 172S 2072439CE LYC IO360 IO360L2A EA STARTER FAILED D O OTHER O OTHER NRNOT REPORTED 1 NM01510LP 172S9510 PINION GEAR NOT ENGAGING RING GEAR COMPLETELY. (K) 1H71 3O3 ONT3A12 1E10 20060922001192006092200119CE 2006 9 22 2006FA0000880 120060830G2821075601011 PLUNGER CESSNA172 172M 2072418CE LYC O320 O320* 41508EA FUEL STRAINER SEPARATED D O OTHER O OTHER NRNOT REPORTED 1 SO095067H4170 17265326 FUEL STRAINER WOULD NOT DRAIN WHEN ACTUATED. INVESTIGATION REVEALED THAT THE RUBBER NIPPLE HAD SEPARATED FROM THE PLUNGER, (P/N 0756010-11). THE FUEL SUMP DRAIN ON THE LT WING ALSO LEAKED AND WAS REPLACED. THE AC HAD RECENTLY BEEN PURCHASED AND IT WAS NOTED THAT AUTO FUEL HAD BEEN USED IN THE PAST. AN STC WAS SECURED AND INSTALL IT ON THE AIRCRAFT. IT IS MY OPINION THAT AN AUTO FUEL WITH ETHANOL ALCOHOL HAD BEEN USED, IN THAT THE PLUNGER NIPPLE WAS (ROCK) HARD AS WAS THE FUEL SUMP DRAIN SEAL. ALL MECHANICS NEED TO MAKE NOTE AS THIS COULD HAVE CAUSED ALL THE FUEL TO LEAK OUT IN FLIGHT AND CAUSED AN OFF FIELD LANDING OR WORSE. IF YOU SMELL AUTO FUEL GO AS DEEP AS NECESSARY TO DETERMINE THE SERVICEABILITY OF THE S1H71 3O3 ONT3A12 E274 20060925001652006092500165 2006 9 25 2006FA0000881 220060830G7261537650 COVER BLANCA17 1730A 1220433GL OIL SUMP CRACKED D K NONE K FLUID LOSS ININSP/MAINT 1 WP15711LA2100 200 30411 5 INCH SPANWISE CRACK, 10 INCHES AFT OF FORWARD EDGE OF OIL SUMP COVER. 1L71 3O A18CE 20060927000252006092700025EA 2006 9 27 2006FA0000884 220060829G732230804 FLOAT LYC MA4SPA105217PIPER PA28 PA28161 7102803SO LYC O320 O320D3G 41508EA SNSNCH74D 74DM EA CARBURETOR BOWL FAILED D O OTHER O OTHER NRNOT REPORTED 1 CE013066H DC43329 287916219 LW1498739A A60546 ON SHUTDOWN, THE RPM INCREASED 400 RPM. ON IDLE, THE ENGINE WOULD IDLE AT 600 RPM, THEN DROP TO 300 RPM THEN DIE. ON OPENING THE CARBURETOR, HALF OF THE WHITE PLASTIC FLOAT WAS 80 PERCENT FULL OF FUEL. IT DID NOT LEAK OUT OVER NIGHT. (K) 1L71 3O3 O 2A13 E274 5 NP88614 20060913003962006091300396SO 2006 9 13 2006FA0000885 120060812G7820 MUFFLER PIPER PA18 PA18150 7101828SO LYC O320 O320* 41508EA EXHAUST SYS CRACKED D K NONE O OTHER ININSP/MAINT 1 AL034418Z81 188753 DURING ANNUAL INSP FOUND CRACK AT END OF ONE SUPPORT BRACE WITH EVIDENCE OF EXHAUST LEAK. ADVISED OWNER, HE SAID HE HAD EXPERIENCED EXHAUST LEAKAGE WITH MILD NOSE AND LEAKAGE. REPAIRED MUFFLER AND RETURNED TO US AND MUFFLER WAS REINSTALLED. (K) 1H71 3O3 O 1A2 E274 20060913002582006091300258 2006 9 13 2006FA0000886 120060830G8011 STARTER ENGINE FAILED B WS9RO OTHER O OTHER NRNOT REPORTED 1 NM07 45 STARTER, WILL NOT SPIN ON LOAD. 20060922000892006092200089EU 2006 9 22 2006FA0000887 120060815G7797 CONNECTOR SNIAS 350 AS350BA 8680817EU TMECA ARRIELARRIEL1B 6OO30NE TORQUE IND CONTAMINATED B HXSRA UNSCHED LANDING N FALSE WARNING CRCRUISE 1 AL0557954 1127 501 DEPARTED BASE, HEADED FOR THE GLACIER, EN ROUTE THE PILOT NOTICED HIS TORQUE READING WAS FLUCTUATING. THE PILOT RETURNED TO BASE AND THE MECHANIC FOUND THAT THE ENGINE DECK PLUG HAD WATER IN IT FROM THE HEAVY RAINS WE HAVE BEEN ENDURING. THE MECHANIC CLEANED OUT THE PLUG AND THE AIRCRAFT WAS RETURNED TO SERVICE AFTER AN OPERATIONS CHECK WAS COMPLETED. (K) 1G71 3U3 UNCH9EU E19EU 20060913003842006091300384EA 2006 9 13 2006FA0000888 120060608G6210234R0001 BLADE BOEING234 234 1385049EA MAIN ROTOR DEBONDED B CHIRO OTHER O OTHER NRNOT REPORTED 1 NM09CFHFB MJ005 ROTOR BLADE HAD A LARGE SKIN DEBOND ON THE LOWER SURFACE FROM THE TRIM TAB OB, BETWEEN STA 227 AND STA 329, APPROXIMATELY 475-500 SQUARE INCHES (ALLOWABLE REPAIR LIMITS ARE 20 INCHES SPAN WISE AND 13 INCHES CHORD WISE. UNBONDED SKIN WAS REMOVED TO EXPOSE HONEYCOMB CORE FOR INSPECTION. HONEYCOMB WAS OIL FREE AND APPEARED TO BE IN GOOD CONDITION. THE ROTOR BLADE WILL UNDERGO FURTHER INVESTIGATION TO DETERMINE THE PROBABLE CAUSE AND REPAIR SCHEME IF POSSIBLE. THE MANUFACTURER HAS BEEN NOTIFIED. (K) 2G72 4U H9EA 20060913003952006091300395GL 2006 9 13 2006FA0000889 120060829G7920 UNION AMTR LANCARLC41550FG 5150001GL CONT O550 TSIO550C SO ENGINE CRACKED D K NONE K FLUID LOSS ININSP/MAINT 1 NM09999GL251 41034 802678 THE AN911-1J UNION THAT SUPPLIES OIL TO THE OIL PRESSURE TRANSDUCER, THE HOBBS PRESSURE SWITCH, AND THE OIL FEED LINE, AT THE BASE OF THE OIL COOLER, ON THE BACK OF THE ENGINE, WAS CRACKED AT THE PIPE THREADS, AND THEN BROKE IN THE PROCESS OF REMOVING THE PART. THE WEIGHT OF THE FITTINGS ATTACHED TO THE UNION HANGING OUT AS FAR AS THEY ARE, AND THE VIBRATION OF THE ENGINE, MAY HAVE CAUSED THE UNION TO CRACK AT THE PIPE THREADS. THE HARDNESS OF THE STAINLESS STEEL PART COULD ALSO HAVE BEEN PART OF THE PROBLEM. THE AC WAS SCHEDULED THAT DAY BUT AN OIL LEAK WAS NOTICED AND INVESTIGATED BEFORE THE FLIGHT, WHICH WOULD HAVE ENDED WITH A CATASTROPHIC FAILURE OF THE ENGINE DUE TO OIL LOSS. THE TEMPORARY RECOMMENDAT1L71 3O3 ORTEXPA1L71E5SO 20060913003642006091300364CE 2006 9 13 2006FA0000890 120060824G2730 CONTROL CABLE BEECH 90 C90A 1152911CE PWA PT6 PT6A21 52043EA ELEVATOR OUT OF ADJUST B E81RK NONE O OTHER ININSP/MAINT 1 GL03405DD LJ1748 DURING 1ST SCHEDULED PHASE 1 AND PHASE 2 INSPECTIONS NOTED ELEVATOR CONTROL SYSTEM CABLE TENSIONS OUT OF MM SERVICE LIMITS. FOUND ELEVATOR NEUTRAL POSITIONS OUT OF LIMITS FOLLOWING CABLE TENSION ADJUSTMENTS (WITH FORWARD AND AFT RIG PINS INSTALLED). FOUND FORWARD BELLCRANK DOWN STOP BOLT CLEARANCE PAST SERVICE LIMIT AND ADJUSTED. FOUND ELEVATOR BOBWEIGHT CLEARANCE GAP EXCESSIVE. REQUIRED ADJUSTING THE FORWARD PUSHROD ASSY AND ADDING WASHERS TO OBTAIN BOBWEIGHT CLEARANCE WITHIN SERVICE LIMITS. AIRCRAFT HAD BEEN SUBJECT TO SPECIAL FLIGHT CONTROL SYSTEM INSPECTION FOLLOWING MANUFACTURE LOGBOOK RECORDS. RECOMMEND FOLLOW-UP INVESTIGATION BY MFG ON OTHER AC. (K) 1L72 3T4 TRT3A20 E4EA 20060927000432006092700043CE 2006 9 27 2006FA0000891 120060824G33508751062 POWER SUPPLY BEECH MU300 400A 1155402CE EMERGENCY LIGHTSINOPERATIVE B E81RO OTHER O OTHER NRNOT REPORTED 1 GL0345RK 3957 RK43 DURING SCHEDULED 12 MONTH/200 HR INSPECTION OF AIRCRAFT SERVICES EMERGENCY LIGHTING SYS INSTALLED UNDER STS ST00344AT FOUND AFT POWER INSTALLED UNDER STC ST00344AT FOUND AFT POWER SUPPLY TO HAVE NO OUTPUT. VERIFIED POWER SUPPLY RECEIVING BATTERY CHARGING VOLTAGE AND BATTERY FULLY CHARGED. REPLACED POWER SUPPLY WITH NEW UNIT, SYSTEM TESTS SATISFACTORY IAW MANUAL INSPECTION GUIDE. (K) 2H72 4F RTA16SW 20060913003622006091300362 2006 9 13 2006FA0000892 420060824G22156225735002 MOUNT BEECH 90 C90A 1152911CE PWA PT6 PT6A21 52043EA RUDDER SERVO DISTORTED B E81RK NONE O OTHER ININSP/MAINT 1 GL03405DD201 LJ1748 DURING FIRST SCHEDULED 1ST AND 2ND PHASE INSPECTIONS NOTED SQUEAKING AND METAL TO METAL CONTACT NOISES WHEN RUDDER MOVED SIDE TO SIDE. FOUND RUDDER SERVO CABLE RUBBING ON SMT-65 SERVO MOUNT CABLE DRUM COVER. REPLACED SMT-65 UNIT AND REINSTALLED, RIGGED SERVO CABLE. RUDDER OPERATIONS NOW NORMAL, AUTOPILOT OPERATIONAL CHECKS OK. SUSPECT SMT -65 SERVO MOUNT EITHER DISTORTED FROM PRIOR HANDLING OR NOT ASSEMBLED CORRECTLY. (K) 1L72 3T4 TRT3A20 E4EA 20060913003632006091300363CE 2006 9 13 2006FA0000893 120060824G2720 FASTENER BEECH 90 C90A 1152911CE PWA PT6 PT6A21 52043EA RUDDER SYS OVERTORQUED B E81RO OTHER O OTHER NRNOT REPORTED 1 GL03405DD LJ1748 FOUND OTHER LT SIDE RUDDER CONTROL ATTACHING HARDWARE TIGHT OR OVERTIGHTENED. EXAMINED LT RUDDER CONTROL SYSTEM HARDWARE FOR SERVICEABILITY AND REINSTALLED AS REQUIRED WITH NORMAL RECOMMENDED TORQUES, ADJUSTED INTERCONNECT ROD AS REQUIRED WITH NORMAL RECOMMENDED TORQUES, ADJUSTED INTERCONNECT ROD AS REQUIRED. REPLACED PILOT`S OB PUSHROD ASSY BEARINGS AND REINSTALLED. NOSEWHEEL STEERING AND RUDDER OPERATIONS FOUND NORMAL AFTER REASSEMBLY. SUSPECT HARDWARE POSSIBLY OVERTIGHTENED DURING INITIAL AC ASSY, AIRCRAFT WAS ALSO SUBJECT TO SPECIAL FLIGHT CONTROL SYSTEM INSPECTION FOLLOWING MFG. RECOMMENDED FURTHER INVESTIGATION BY MFG TO DETERMINE IF A ONE-TIME SB. (K) 1L72 3T4 TRT3A20 E4EA 20060913003612006091300361CE 2006 9 13 2006FA0000894 120060824G2720139909B47 BOLT BEECH 90 C90A 1152911CE PWA PT6 PT6A21 52043EA RUDDER SYS OVERTORQUED B E81RK NONE O OTHER ININSP/MAINT 1 GL03405DD LF1748 DURING 1ST SCHEDULED PHASE 1 AND PHASE 2 INSPECTION INVESTIGATED PILOT COMPLAINT OF STIFF NOSEWHEEL STEERING. VERIFIED COMPLAINT, FOUND NOSEWHEEL STEERING STIFF AND LOUD POPPING NOISES COMING FROM COCKPIT UNDER FLOOR AREA WHEN TAXIED FROM COPILOTS POSITION. ACCESSED COCKPIT AREA RUDDER CONTROL SYSTEM AND FOUND PILOTS SIDE OB RUDDER CONTROL PUSHROD TO HAVE EXCESSIVE PLAY. UPON REMOVING OB PUSHROD ASSY. BEARINGS FELL OUT OF ROD END BEARING ASSY. FURTHER INVESTIGATION SHOWED PN 50-5244553 LT SIDE RUDDER BELLCRANK ASSY OPERATION TIGHT, FOUND PN 139909B47 PIVOT BOLT OVERTIGHTENED. ALSO FOUND LT TO RT RUDDER CONTROLS INTERCONNECT TUBE ATTACHING HARDWARE OVERTIGHTENED. (K) 1L72 3T4 TRT3A20 E4EA 20060914001522006091400152EU 2006 9 14 2006FA0000896 220060824G72501975M84P01 RETAINER BOEING737 737400 138449ANM CFMINTCFM56 CFM563C1 13802EU ENGINE DISLODGED W QEMYO OTHER O OTHER NRNOT REPORTED 1 EA35SPLKC29341 857849 (REF: 2006FA00008996) DURING STRIP OF ENGINE 857819 FOR SCHEDULED LLP REPLACEMENT IT WAS NOTED THAT THE HPT FORWARD BLADE RETAINER HAD LIBERATED 2 SECTIONS OF MATERIAL, ONG 3.5 INCHES X .8750 INCH AND 1) 2 INCH X .8750 INCH. THE LIBERATED MATERIAL HAD CAUSED MINOR LPT AND HPT IMPACT DAMAGE. MFG HAS BEEN ASKED TO INVESTIGATE THIS DEFECT. (K) 2L72 4F4 FRTA16WE E21EU 20060913003942006091300394EA 2006 9 13 2006FA0000897 220060825G8530AEL65102 CYLINDER CESSNA172 172N 2072434CE LYC O360 O360A4M 41514EA ENGINE SEPARATED D E ENGINE SHUTDOWN O OTHER NRNOT REPORTED 1 EA21733EN206 17268239 PILOT EXPERIENCED A NOTICEABLE POP SOUND IN ENGINE COMPARTMENT FOLLOWED BY ROUGHNESS. SOON AFTER THE ENGINE OIL PRESSURE STARTED TO DETERIORATE AND PILOT ELECTED TO SHUTDOWN ENGINE AND STOPPED PROPELLER FROM TURNING BY PUTTING AIRCRAFT IN NOSE HIGH ATTITUDE. HE MANAGE TO GLIDE TO MAJOR AIRPORT AND DEAD STICK LAND SUCCESSFULLY WITHOUT ACCIDENT. INVESTIGATION SHOWED THAT THE NR 1 CYLINDER HEAD SEPARATED FROM BARREL. THIS CYLINDER WAS REPLACED 206 HOURS PRIOR WHEN ENGINE WAS OVERHAULED. THE CYLINDER WAS PURCHASED NEW. NEW CYLINDER WAS INSTALLED AND ENGINE RAN NORMALLY WITH NO ADVERSE PROBLEMS NOTED. THE SEPARATION OF CYLINDER IS THOUGHT TO BE STRESS CRACKING DUE TO THREADS CUT IN CYLINDER HEAD HAVING LITTLE1H71 3O3 ONT3A12 E286 20060913003992006091300399GL 2006 9 13 2006FA0000898 120060818G321321410103 AXLE BOMBDRBD700 BD7001A10 1390006GL LT MLG CORRODED B K NONE O OTHER ININSP/MAINT 1 NE03700ML2175 9043 LT MLG TRAILING ARM AXLE FOUND TO HAVE CORROSION ON TAPERED WASTELAND AREAS AT BOTH WHEEL POSITIONS. (K) 2L72 4F RTT00003NY 20060913003932006091300393SW 2006 9 13 2006FA0000899 120060809G3230ED10055 BOLT GULSTM690TP 690C 7630517SW GARRTTTPE331TPE331* 01514WP NLG SHEARED D K NONE O OTHER ININSP/MAINT 1 NM09777NV4937 11680 DURING ROUTINE INSPECTION FOUND NOSE GEAR LOWER DRAG BRACE BOLT SHEARED AT JUNCTION OF REDUCED DIAMETER BOLT HAD NOT YET CAME OUT OF ITS BORE AND THEREFORE THE GEAR DID NOT COLLAPSE. BUT IT WAS READY TO. (K) 1H72 3T3 T 2A4 E2WE 20060925001602006092500160WP 2006 9 25 2006FA0000900 120060901G6720HS10537 CABLE HILLERUH12 UH12E 4360122WP TAIL ROTOR BROKEN G A UNSCHED LANDING O OTHER AGAGRICULTURE 1 SW118402D250 1093 LT TAIL ROTOR CABLE FAILED. OPERATOR OPERATES IN VERY DUSTY ENVIRONMENT. BUILD UP OF DUST AND OILY SUBSTANCE FROM PRODUCT FOR SPRAYING CAUSE A FINE ABRASIVE SUBSTANCE ON CABLES AT PULLEYS. CABLE NEEDS PROTECTION FROM ENVIRONMENT AND MORE FREQUENT INSPECTION AND/OR REPLACEMENT. 1G71 3O 4H11 20060915000202006091500020CE 2006 9 15 2006FA0000901 120060912G24971N6391 DIODE CESSNA CESSNA172 172S 2072439CE BUSS BAR FAULTY B K NONE W INADEQUATE Q C ININSP/MAINT 1 SO15452ER48 48 172S10255 ON A RECENT LOCAL FLIGHT, ONE OF THESE AIRCRAFT EXPERIENCED THE LOSS OF THE MFD, OR RT DISPLAY AS WELL AS THE COMM 2, NAV 2, AUDIO PANEL AND TRANSPONDER. THE CREW ELECTED TO MAKE A PRECAUTIONARY LANDING AT THE NEAREST AIRPORT. ON INSPECTION, IT WAS DISCOVERED THAT THE POWER TO BUSS 2 WAS NOT PRESENT. THE BUSS 2 CIRCUIT BREAKER WAS REPLACED AND THE SYSTEM FUNCTIONED PROPERLY. SHORTLY AFTER, THE MFD FAILED AGAIN. AFTER CLOSER INSPECTION THE WIRE PROVIDING POWER TO THE MFD BREAKER WAS FOUND LOOSE ON THE TERMINAL. THIS WIRE WAS SECURED AND THE AIRCRAFT INCURRED NO FURTHER PROBLEMS. A FLEET INSPECTION OF THE BUSS WIRING FOR THE ESSENTIAL BUSS, BUSS 1 AND BUSS 2 WAS COMMENCED. ADDITIONAL LOOSE WIRE TERMINALS WERE FOU1H71 3O NT3A12 20060926000502006092600050SO 2006 9 26 2006FA0000902 220060729G8530649543 CYLINDER CESSNA175 175A 2072504CE CONT O300 GO300* 17022SO ENGINE SEPARATED G A UNSCHED LANDING D INFLIGHT SEPARATION CRCRUISE 1 GL116793E3 3 56293 121479C NR (5) CYLINDER SEPARATED FROM THE CRANK-CASE IN FLIGHT RESULTING IN ENGINE FAILURE AND AN UN-PLANNED, SAFE LANDING OF THE AIRCRAFT. 1H71 3O3 O 3A17 E298 20060918000102006091800010CE 2006 9 18 2006FA0000903 120060913G24971N6391 DIODE CESSNA172 172S 2072439CE NR 1 BUSS LOOSE B K NONE O OTHER ININSP/MAINT 1 SO15465ER38 172S10290 THIS OPERATOR HAS A FLEET OF 16 CESSNA 172S NAVIII AIRCRAFT. DUE TO SOME OPERATIONAL DIFFICULTIES WHERE BUSS WIRING DISCREPANCIES WERE FOUND, A FLEET WIDE INSPECTION OF THE BUSS WIRING, TERMINAL CONNECTIONS AND WIRE ROUTING WAS ACCOMPLISHED. THE FOLLOWING WAS FOUND ON THIS AIRCRAFT: REMOVED CIRCUIT BREAKER PANEL AND FOUND LOOSE WIRES COMING FROM DIODES, GOING TO DIFFERENT CIRCUIT BREAKER BUSSES. TIGHTENED LOOSE NUTS AND CHECKED ALL OTHER WIRE CONNECTIONS, NONE NOTED. REMOVED SPARE WIRES LOOPED THRU OPEN BREAKER MOUNTING HOLE AND SECURED TO WIRE BUNDLE. CHECKED J-BOX FOR LOOSE CONNECTIONS, NONE NOTED. REINSTALLED BREAKER PANELS AND SECURED ALL WIRES AND FITTINGS. 1H71 3O NT3A12 20060921002492006092100249EA 2006 9 21 2006FA0000904 220060914G7313LW15472 PUMP PIPER PA28 PA28180 7102808SO LYC O360 O360A3A 41514EA FUEL SYSTEM LEAKING P O OTHER O OTHER NRNOT REPORTED 1 GL037103W2900 28890 L505536 UPON RETURNING FROM A TRAINING FLIGHT, A FAINT SMELL OF GAS WAS NOTED. SINCE THE ELECTRIC PUMP WAS ON, IT WAS TURNED OFF. NO ENGINE PERFORMANCE PROBLEMS WERE NOTED AND LANDING WAS NORMAL. UPON LANDING IT WAS NOTICED THAT FLUID WAS DRAINING FROM THE FUEL PUMP VENT LINE. THIS APPEARED TO BE A MIX OF GAS AND OIL. IT IS ESTIMATED 3-4 QUARTS DRAINED FROM THE VENT BEFORE STOPPING. THE OIL PAN WAS DRAINED AND WAS FOUND TO CONTAIN 8-10 QUARTS OF GAS/OIL MIX. THE OIL FILTER WAS OPENED AND NO METAL WAS FOUND. THE OLD PUMP HAS NOT YET BEEN OPENED AND WAS OPERATING SUFFICIENTLY FOR THE ENGINE TO RUN, BUT IT IS PRESUMED THE PUMP DIAPHRAGM HAD RUPTURED CAUSING FUEL TO LEAK INTO THE ENGINE CRANKCASE. NO EVIDENCE OF THE PUMP1L71 3O3 O 2A13 E286 20060922000422006092200042EA 2006 9 22 2006FA0000905 220060914G7314 DIAPHRAGM AC PIPER PA28 PA28180 7102808SO LYC O360 O360A3A 41514EA FUEL PUMP RUPTURED P O OTHER KB FLUID LOSS SMOKE/FUMES/ODORS/SPARKS NRNOT REPORTED 1 GL037103W 28890 L505536 UPON RETURNING FROM A TRAINING FLIGHT, A FAINT SMELL OF GAS WAS NOTED. SINCE THE ELECTRIC PUMP WAS ON, IT WAS TURNED OFF. NO ENGINE PERFORMANCE PROBLEMS WERE NOTED AND LANDING WAS NORMAL. UPON LANDING IT WAS NOTICED THAT FLUID WAS DRAINING FROM THE FUEL PUMP VENT LINE. THIS APPEARED TO BE A MIX OF GAS AND OIL. IT IS ESTIMATED 3-4 QUARTS DRAINED FROM THE VENT BEFORE STOPPING. THE OIL PAN WAS DRAINED AND WAS FOUND TO CONTAIN 8-10 QUARTS OF GAS/OIL MIX. THE OIL FILTER WAS OPENED AND NO METAL WAS FOUND. THE OLD PUMP HAS NOT YET BEEN OPENED AND WAS OPERATING SUFFICIENTLY FOR THE ENGINE TO RUN, BUT IT IS PRESUMED THE PUMP DIAPHRAGM HAD RUPTURED CAUSING FUEL TO LEAK INTO THE ENGINE CRANKCASE. NO EVIDENCE OF THE PUMP1L71 3O3 O 2A13 E286 20060927000282006092700028SO 2006 9 27 2006FA0000906 220060823G8520TCM536379 BOLT CONT O550 TSIOL550A SO CRANKSHAFT GEAR SHEARED B VA1RO OTHER O OTHER NRNOT REPORTED 1 SW19 58 800554 CRANKSHAFT GEAR BOLTS SHEARED/BROKE CAUSING ENGINE FAILURE. (ENGINE FIALED ON GROUND, DURING STARTING) (K) 3 O E4SO 20060927000302006092700030CE 2006 9 27 2006FA0000907 120060822G323099100023 MOTOR CESSNA310 310Q 2074242CE CONT O470 IO470* 17026SO MLG FAILED B E81RL ABORTED APPROACH J WARNING INDICATION APAPPROACH 1 GL037940Q 310Q0623 LANDING GEAR WOULD NOT EXTEND ELECTRICALLY ON APPROACH. OPERATIONS NORMAL WHEN LANDING GEAR EXTENDED WITH MANUAL EMERGENCY EXTENSION SYS. FOUND LANDING GEAR ACTUATOR MOTOR INOPERATIVE. WOULD MAKE NOISE BUT NOT ROTATE. REPLACED MOTOR WITH OVERHAULED REPLACEMENT UNIT; LANDING GEAR SYS OPERATIONS NORMAL. CLEANED CORROSION FROM BATTERY TERMINALS, SUSPECT VOLTAGE DROP UNDER LANDING GEAR OPERATIONS LOAD MAY HAVE CONTRIBUTED. TRANSIENT AC, RECORDS NOT AVAILABLE TO VERIFY MOTOR TIME IN SERVICE. (K) 1L72 3O3 O 3A10 E1CE 20060926002382006092600238CE 2006 9 26 2006FA0000908 120060817G3230MS250261 SWITCH BEECH 36 B36TC 1151609CE CONT O520 GTSIO520* 17032SO MLG FOULED B E81RO OTHER O OTHER NRNOT REPORTED 1 GL03515EK EA440 LANDING GEAR WOULD NOT EXTEND ELECTRICALLY UPON APPROACH TO RFD. MANUAL EXTENSION OPERATIONS NORMAL. TROUBLESHOT LANDING GEAR ELECTRICAL SYS. FOUND S45 LANDING GEAR ACTUATOR DYNAMIC BRAKE DOWNLIMIT SWITCH OIL SOAKED AND FOULED BY LINT, FUZZ, ETC. CLEANED DOWNLIMIT SWITCH AS REQUIRED AND CYCLED LANDING GEAR ELECTRICALLY; OPERATION NORMAL. SUSPECT OIL AND LINT BLOCKING FULL SWITCH TRAVEL AND/OR CAUSING HIGH RESISTANCE IN S45 SWITCH. DYNAMIC BRAKE LIMIT SWITCHES SHOULD BE INSPECTED CLOSELY AND CLEANED IF REQUIRED EACH 100 HR OR ANNUAL INSPECTION. THIS AREA CAN BE PRONE TO ATTRACTING DIRT AND UPHOLSTERY (FUZZ). (K) 1L71 3O3 O 3A15 E7CE 20060927000262006092700026GL 2006 9 27 2006FA0000909 120060907G7120 BELT AMTR WOODY WOODYPUSHER GL CONT A65 A65* 17003SO REDUCTION BRACK FRACTURED D O OTHER O OTHER NRNOT REPORTED 1 WP1956JH 191 JEH2 ULTRALIGHT FRACTURED ENGINE BELT REDUCTION BRACKET CAUSING IN-FLIGHT SHUTDOWN AND EMERGENCY LANDING. PROBABLE CAUSE: ENGINE BELT REDUCTION BRACKET STRESS/FATIGUE CRACK CAUSING HEAVY ENGINE VIBRATION AND SHUTDOWN. (K) 1H71 3O3 O EXPA1H71E205 20060927000242006092700024CE 2006 9 27 2006FA0000910 120060626G3000991240217 SHUTOFF VALVE CESSNA650 650 2076802CE GARRTTTFE731TFE731* 01518WP ANTI-ICE SYS MISINSTALLED B EBVRO OTHER O OTHER NRNOT REPORTED 1 CE09993LC 6500027 DETERMINED THE PRESSURE REGULATOR SHUTOFF VALVE WAS LEAKING. FOUND THE REGULATOR HAD BEEN INSTALLED WITHOUT GASKETS. THE PARTS MANUAL DOES NOT CLEARLY IDENTIFY THAT GASKETS ARE REQUIRED TO BE INSTALLED WITH THIS SPECIFIC PN OF VALVE. CONTACTED AND CONFIRMED THAT GASKET PN 24096-150C IS REQUIRED TO BE INSTALLED ON THIS VALVE. MAINTENANCE PERSONNEL INSTALLED GASKETS, PERFORMED LEAK CHECK, AND DETERMINED LEAKAGE PROBLEM HAD BEEN CORRECTED BY INSTALLATION OF GASKETS. (K) 2L72 4F4 F A9NM E6WE 20060927000332006092700033EA 2006 9 27 2006FA0000911 220060828G7314RGRG0957OK1 PUMP GROB 120 G120A 1660208EU LYC O540 AEIO540D4D5 EA ENGINE FUEL LEAKING B VJ3RO OTHER O OTHER NRNOT REPORTED 1 WP07862AF788 85002 RL2155648A PILOT REPORTED A STRANGE ODOR AFTER THEY PUT THE GEAR UP, WHILE TROUBLESHOOTING MECHANIC FOUND ENGINE FUEL PUMP LEAKING FROM PRESSURE ADJUSTMENT SCREW. NO PROPABLE CAUSE OR RECOMMENDATIONS AT THIS TIME. (K) 1L71 3O3 ORTA49CE 1E4 20060927000212006092700021CE 2006 9 27 2006FA0000912 120060817G3610AA3216CW SHAFT BEECH 33 F33A 1151425CE CONT O520 IO520BB 17032SO AIR PUMP SHEARED B VJ3RO OTHER O OTHER NRNOT REPORTED 1 WP078240T173 CE1542 830141R PILOT REPORTED INSTRUMENT AIR PRESSURE WENT TO -0- IN FLIGHT, PILOT THEN SELECTED STANDBY PUMP AND RETURNED TO BASE. UP ON TROUBLESHOOTING THE MECHANIC REMOVED THE AIR PUMP AND FOUND THE SHAFT WAS SHEARED. NO PROBABLE CAUSE OR RECOMMENDATIONS AT THIS TIME. (K) 1L71 3O3 O 3A15 E5CE 20060927000322006092700032CE 2006 9 27 2006FA0000913 120060817G3610AA3216CW SHAFT BEECH 33 F33A 1151425CE CONT O520 IO520BB 17032SO AIR PUMP SHEARED B VJ3RO OTHER O OTHER NRNOT REPORTED 1 WP078240T173 CE1542 830141R PILOT REPORTED INSTRUMENT AIR PRESSURE WENT TO -0- IN FLIGHT, PILOT THEN SELECTED STANDBY PUMP AND RETURNED TO BASE. UPON TROUBLESHOOTING, THE MECHANIC REMOVED THE AIR PUMP AND FOUND THE SHAFT WAS SHEARED. NO PROBABLE CAUSE OR RECOMMENDATIONS AT THIS TIME. (K) 1L71 3O3 O 3A15 E5CE 20060927000372006092700037NE 2006 9 27 2006FA0000914 220060821G72613035890 TRANSFER TUBE BEECH 90 F90 1152909CE PWA PT6 PT6A135 52043NE ENGINE OIL CHAFED B BNGRO OTHER KJ FLUID LOSS WARNING INDICATION NRNOT REPORTED 1 GL19234CW LA236 PCE35079 IN FLIGHT NOTICED TORQUE METER WAS UNSTABLE, CHECKED OIL PRESSURE AND SAW IT DROPPING. REDUCED POWER TO IDLE OIL PRESSURE WAS IN YELLOW RANGE. SHUTDOWN ENGINE AND LANDED. REMOVED FRONT COWLING AND FOUND INLET DEICE TUBE HAD RUBBED A HOLE IN THE OIL PRESSURE TRANSFER TUBE RT SIDE ON ENGINE. CHECKED CHIP DETECTOR CHECKED OK. CHECKED OIL FILTER CHECKED OK. REMOVED AND REPLACED TUBE AND RELOCATED DEICE TUBE. SERVICED OIL SYSTEM AND GROUND RUN RECHECKED CHIP DETECTOR AND FILTER CHECKED OK. RECOMMEND THAT BEFORE FRONT TOP COWLING IS INSTALLED THAT DEICE TUBES BE CHECKED FOR CLEARANCE AT OTHER ITEMS IN COWLING. (K) 1L72 4T4 T A31CE E4EA 20060927000152006092700015NM 2006 9 27 2006FA0000915 120060802G3232273T61027 CYLINDER BOEING BOEING767 767* NM ACTUATOR DAMAGED B IU6RO OTHER O OTHER NRNOT REPORTED 1 NM01 33938 SHL1262 (REF NR: 209609/QN1) PIN HOLE THROUGH CYLINDER WALL. PRESSURES CYCLES AND MATERIAL DEFECT. (K) 2L72 4F RTA1NM 20060927000442006092700044NM 2006 9 27 2006FA0000916 120060802G291365447822 HOUSING BOEING737 737* NM HYD PUMP CRACKED B IU6RO OTHER O OTHER NRNOT REPORTED 1 NM01 (REF NR 209606/PH30) CRACK IN HOUSING. CYCLICAL FATIGUE. (K) 2L72 4F RTA16WE 20060926001342006092600134SO 2006 9 26 2006FA0000917 220060906G8520653631 GEAR CESSNA206 U206F 2073333CE CONT O520 IO520F 17032SO MCAULYD3A34 D3A34C401 GL CRANKSHAFT BROKEN D O OTHER O OTHER NRNOT REPORTED 1 NE058411Q167 U20603271 830575R 011026 AC FLEW A SHORT LEG TO AN ISLAND 25 NM OFFSHORE. AFTER START-UP THE PILOT HEARD AN UNUSUAL NOISE THAT SOUNDED LIKE A LOOSE VALVE TRAIN. THE PILOT QUICKLY SHUT THE POWERPLANT DOWN AND DECIDED IT WOULD NOT BE SAFE TO COMPLETE THE TRIP BACK TO MAINLAND. MECHANIC FLEW OUT TO THE ISLAND TO DETERMINE THE SOURCE OF THIS UNUSUAL NOISE. FURTHER INVESTIGATION REVEALED THAT THE SOURCE OF THE NOISE WAS 2 TEETH BROKEN OFF OF THE CRANKSHAFT GEAR. THE IDLER GEAR AND THE STARTER ADAPTER GEAR WERE ALSO DAMAGED AS A RESULT OF THE INTERACTION WITH THE DAMAGED CRANKSHAFT GEAR. THE TEETH THAT WERE BROKEN OFF HAVE NOT BEEN LOCATED. METAL SLIVERS AND PIECES WERE ALSO IDENTIFIED IN THE AREA AND OIL. THIS IS PRELIMINARY INFORMA1H71 3O3 O A4CE E5CE 5 CP47GL 20060921002462006092100246CE 2006 9 21 2006FA0000918 120060913G2497 JUMPER CESSNA172 172S 2072439CE CB PANEL LOOSE B K NONE W INADEQUATE Q C ININSP/MAINT 1 SO15458ER15 172S10258 DURING INSPECTION OF THE BUS WIRING, THE JUMPER WIRE BETWEEN THE ESSENTIAL BUS AND THE BUS 1 CONNECTION WAS FOUND LOOSE. THE REMAINDER OF THE SCREWS OF THOSE CIRCUIT BREAKERS WERE CHECKED FOR SECURITY, AND SEVERAL WERE FOUND SLIGHTLY LOOSE REQUIRING .2500 TURN OR MORE TO SECURE THEM. 1H71 3O NT3A12 20060921002522006092100252CE 2006 9 21 2006FA0000919 120060911G24971N6391 DIODE CESSNA172 172S 2072439CE ELECTRICAL LOOSE B K NONE W INADEQUATE Q C ININSP/MAINT 1 SO15461ER34 172S10281 DURING INSPECTION OF THE BUSS STRIPS, THE 2 DIODES FOR THE ALT AND WARNING CIRCUIT BREAKERS WERE FOUND LOOSE AT THEIR ATTACH POINTS TO THE BUS. THE ATTACHING HARDWARE (NUTS) WERE SEVERAL COMPLETE TURNS FROM BEING SECURE, OR ABOUT THE WIDTH OF THE NUT GAP SHOWING. 1H71 3O NT3A12 20060926000292006092600029 2006 9 26 2006FA0000922 420060915G23301F220100102 AMPLIFIER BOEING737 737* NM GE CFM56 CFM56* 13802NE ENTERTAIN SYS FIRE C H DEACTIVATE SYST/CIRCUITS AB FLAME/FIRE SMOKE/FUMES/ODORS/SPARKS TXTAXI/GRND HDL 1 EA17367G 28579 WHILE MAINTENANCE PERSONNEL WERE PERFORMING A ROUTINE POST FLIGHT INSPECTION, A TECHNICIAN DISCOVERED A PROBLEM. ACFT POWERED BY EXTERNAL POWER, AND CABIN ENTERTAINMENT SYS OPERATING (PLAYING A DVD MOVIE) WITH THE AUDIO SYSTEM VOLUME AT A LOW LEVEL. AFTER A FEW MINUTES OF OPERATION, A TECHNICIAN NOTICED SMOKE AND FUMES COMING FROM TWO OF THE FORWARD CABIN SPEAKERS (LOUNGE AREA). ONE SPEAKER EMITTED A FLAME APPROXIMATELY 2 TO 3 INCHES IN LENGTH. THE TECHNICIAN QUICKLY SHUT DOWN ALL AIRCRAFT ELECTRICAL POWER, AND RETURNED TO THE DAMAGED SPEAKER AREA WITH AN ONBOARD FIRE EXTINGUISHER. THE FLAME HAD SELF EXTINGUISHED, HOWEVER, THE CABIN WAS VERY SMOKEY AT THAT POINT. UPON FURTHER EXAMINATION, (2) SPEAKERS HAD2L72 4F4 FRTA16WE E2GL 20060922000862006092200086WP 2006 9 22 2006FA0000923 220060823G726130745732 CARBON SEAL AMD FALC50FALCON900 2700160EU GARRTTTFE731TFE7315BR WP ENGINE DETERIORATED D O OTHER O OTHER NRNOT REPORTED 1 GL13922JW 038 (NR 4 CARBON SEAL, PN30745732, SN 010515810208), (NR 5 CARBON SEAL, PN 30745742, SN 0119368002352) PILOTS REPORT HIGH OIL PRESSURE. OIL PRESSURE FOLLOWED THROTTLE HIGH GEARBOX PRESSURE CAUSED BY DETERIORATION OF NR 4 AND NR 5 CARBON SEALS. 2L73 4F4 FRTA46EU E6WE 20060926002412006092600241WP 2006 9 26 2006FA0000924 220060823G726130745742 CARBON SEAL AMD FALC50FALCON900 2700160EU GARRTTTFE731TFE7315BR WP NR 5 DETERIORATED D O OTHER O OTHER NRNOT REPORTED 1 GL13922JW 038 (NR 4 CARBON SEAL, PN30745732, SN 010515810208) (NR 5 CARBON SEAL, PN30745742, SN 011936802352) PILOTS REPORT HIGH OIL PRESSURE. OIL PRESSURE FOLLOWED THROTTLE HIGH GEARBOX PRESSURE CAUSED BY DETERIORATION OF NR 4 AND NR 5 CARBON SEALS. (K) 2L73 4F4 FRTA46EU E6WE 20060921001992006092100199CE 2006 9 21 2006FA0000925 120060917G5711082260039 SPAR CAP CESSNA310 310Q 2074242CE CONT O470 IO470* 17026SO WING CORRODED D K NONE O OTHER ININSP/MAINT 1 SO07697045433 310Q0930 DURING THE ANNUAL INSPECTION, FOUND UPPER AND LOWER REAR SPAR DAMAGE ON THIS AIRCRAFT. THIS DAMAGE IS DUE TO CORROSION ON THE UPPER AND LOWER REAR SPAR CAPS. THE UPPER REAR SPAR CAP DAMAGE IS LOCATED ON THE FORWARD SIDE OF THE REAR SPAR CAP EXTENDING IB FROM UNDER RIB PN 0822175-69 AT STATION 57.50. THIS DAMAGE IS APPROX. 3 INCHES HORIZONTALLY, .7500 INCH VERTICALLY AND .2500 IN DEPTH. THE LOWER REAR SPAR CAP DAMAGE IS LOCATED ON THE FORWARD SIDE OF THE REAR SPAR CAP EXTENDING OB FROM UNDER RIB PN 0822175-69 AT STATION 57.50. THIS DAMAGE IS APPROX. 6 INCHES HORIZONTALLY AND THE ENTIRE LOWER SPAR CAP IN THIS AREA IS ESSENTIALLY MISSING. THE LT WING HAS BEEN REMOVED AND SENT FOR REPAIR. 1L72 3O3 O 3A10 E1CE 20060922000472006092200047CE 2006 9 22 2006FA0000926 120060919G7830HS78320009 THRUST REVERSER RAYTHNDH125 HAWKER800XP 7150012CE CORRODED B K NONE O OTHER ININSP/MAINT 1 CE09852QS5855 258452 MAJOR CORROSION ON THE THRUST REVERSER DOOR RAMP SKINS DUE TO THE PAINT MISSING FROM THE RIVET HEADS. BY MAJOR CORROSION, WE ARE BLENDING THE AREAS BELOW LIMITS AND HAVING TO SEND THEM OUT FOR REPAIR. AREAS OF CORROSION ARE NOT ONLY BEING FOUND ON THE RIVET HEADS WE ARE FINDING SURFACE CORROSION ANYWHERE THE PAINT IS MISSING ON THE RAMP SKINS. 2L72 4F RTA3EU 20060922000482006092200048CE 2006 9 22 2006FA0000927 120060919G7830 SKIN RAYTHNDH125 HAWKER800XP 7150012CE THRUST REVERSER CORRODED B K NONE O OTHER ININSP/MAINT 1 CE09852QS5855 TECAV0114 258452 MAJOR CORROSION ON THE THRUST REVERSER DOOR RAMP SKINS DUE TO THE PAINT MISSING FROM THE RIVET HEADS. BY MAJOR CORROSION I MEAN WE ARE BLENDING THE AREAS BELOW LIMITS AND HAVING TO SEND THEM OUT FOR REPAIR. AREAS OF CORROSION ARE NOT ONLY BEING FOUND ON THE RIVET HEADS WE ARE FINDING SURFACE CORROSION ANYWHERE THE PAINT IS MISSING ON THE RAMP SKINS. 2L72 4F RTA3EU 20060925001622006092500162NE 2006 9 25 2006FA0000928 220060919G7200 ENGINE AGUSTAA109 A109E 0260119EU TMECA ARRIUSARRIUS2K1 NE MAKING METAL C O OTHER J WARNING INDICATION NRNOT REPORTED 1 NM0891LF 11509 33022 ENGINE CHIP LIGHT CAME ON APPROACH TO LANDING. REMOVED GAS GENERATOR MAG PLUG FOUND COVERED WITH METAL CHIPS. PROBABLE CAUSE BEARING FAILURE. 1G72 3U3 URTH7EU E34NE 20060926000302006092600030NE 2006 9 26 2006FA0000929 220060919G7200 ENGINE AGUSTAA109 A109E 0260119EU TMECA ARRIUSARRIUS2K1 NE MAKING METAL C O OTHER O OTHER NRNOT REPORTED 1 NM0891LF 11509 33022 ENGINE CHIP LIGHT CAME ON APPROACH TO LANDING. REMOVED GAS GENERATOR MAG PLUG FOUND COVERED WITH METAL CHIPS. PROBABLE CAUSE BEARING FAILURE. 1G72 3U3 URTH7EU E34NE 20060921001872006092100187CE 2006 9 21 2006FA0000930 120060920G551145A21146006 RIB BEECH MU300 400A 1155402CE PWA JT15 JT15D5 52112NE HORIZONTAL STAB CRACKED B K NONE O OTHER ININSP/MAINT 1 SO13939GP RK125 PCEJA0017 THE HORIZONTAL STABILIZER RIB (RT SIDE) LOCATED UNDER THE ROLLER BRACKET HAD A CRACK IN IT. THIS ITEM IS COVERED UNDER COMMUNIQUÉ NR 70. 2H72 4F4 FRTA16SW E25EA 20060921002122006092100212 2006 9 21 2006FA0000931 120060920G551145A211460506 RIB PWA JT15 JT15D5 52112NE HORIZONTAL STAB CRACKED B K NONE O OTHER ININSP/MAINT 1 SO1327XP THE RIBS LOCATED UNDER THE HORIZONTAL STABILIZER BRACKETS WERE CRACKED, BOTH THE LT AND RT SIDES. THIS IS COVERED UNDER COMMUNIQUÉ NUMBER 70. 4 F E25EA 20060921002132006092100213CE 2006 9 21 2006FA0000932 120060920G551145A211460506 RIB BEECH MU300 400A 1155402CE PWA JT15 JT15D5 52112NE HORIZONTAL STAB CRACKED B K NONE O OTHER ININSP/MAINT 1 SO1327XP RK266 THE RIBS LOCATED UNDER THE HORIZONTAL STABILIZER BRACKETS WERE CRACKED, BOTH THE LT AND RT SIDES. THIS IS COVERED UNDER COMMUNIQUE NUMBER 70. 2H72 4F4 FRTA16SW E25EA 20060921002482006092100248EU 2006 9 21 2006FA0000933 120060806G32228904200484 AXLE SOCATAMS894 MS894A 8402842EU FRNKLN6AV3506V350* 27043EA MCAULY2A31C 2A31C21 GL NLG BROKEN G O OTHER O OTHER LDLANDING 1 EA1733BF 11720 INFORMATION OBTAINED FROM OWNER AND OPERATOR ENCOUNTERED AN INCIDENT UPON LANDING. AT TOUCHDOWN PILOT REPORTED THE NOSE LANDING GEAR AXLE BROKE, LIBERATING THE NOSE WHEEL FROM THE AIRCRAFT. THE NOSE WHEEL CONTACTED THE RT MAIN FLAP ASSY (DAMAGE SEVERITY UNKNOWN, REPLACEMENT APPARENTLY REQUIRED) SUBSEQUENTLY THE PROPELLER CONTACTED THE RUNWAY. PILOT REPORTED THE ENGINE DID NOT SUFFER SUDDEN STOPPAGE AND THERE WAS NO REPORTED INJURY OR DAMAGE TO AIRPORT PERSONNEL, EQUIPMENT OR PROPERTY. 1L71 3O3 O 7A14 E9EA 5 CP919 20060921003192006092100319EA 2006 9 21 2006FA0000934 220060920G8500 ENGINE CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA LACK OF LUBE D O OTHER YJ ENGINE STOPPAGE WARNING INDICATION CRCRUISE 1 SO055330B 2252 83838 L1395415 LOSS OF OIL PRESSURE WHICH LED TO ENGINE FAILURE/SEIZE AND FORCED EMERGENCY LANDING ON HIGHWAY. NO VISUAL PROBLEMS ON EXTERNAL AREA OF ENGINE. REMOVED ENGINE AND SENT TO MFG FOR TEARDOWN AND EVALUATION. MFG REPORTED THAT ENGINE SUFFERED OIL STARVATION. NR 1 AND NR 3 ROD JOURNALS WERE SCORED AND HEAT CHECKED BEYOND REPAIR. SIGNATURE'S ESTIMATION OF OIL STARVATION WAS CAUSED BY DETONATION IN NR 1 CYLINDER. THE NR 1 CYLINDER DETONATION, BURNED HOLE IN THE PISTON, CAUSING OIL TO BE BLOWN OUT OF ENGINE VENT TUBE. THE NR 1 CAMSHAFT INTAKE LOBE WAS SEVERELY WORN AND THE EXHAUST LOBE MODERATELY WORN IN WHICH IS BELIEVED TO HAVE CONTRIBUTED TO THE NR 1 CYLINDER DETONATION PROBLEM. 1H71 3O3 ONT3A19 E223 20060926001332006092600133CE 2006 9 26 2006FA0000939 120060913G3710S2501 HOSE CESSNA172 172P 2072436CE CONT O470 IO470* 17026SO VACUUM SYS FAILED D O OTHER O OTHER NRNOT REPORTED 1 GL1398264 17276271 INVESTIGATION INTO FAILED ATTITUDE INDICATOR ON LISTED AIRCRAFT FOUND APPARENT CAUSE OF FAILURE TO BE FROM CONTAMINATION FROM DISINTEGRATING VACUUM HOSE. THE HOSES IN QUESTION ARE MARKED B906 AND B904 HOSE. TO PREVENT RECURRENCE, SB SEB96-10 SHOULD BE ACCOMPLISHED ON AIRCRAFT. ON OTHER AIRCRAFT HOSE SHOULD BE REPLACED WITH APPROVED EQUIVALENT. DUE TO SEVERITY OF POTENTIAL FOR HOSE TO CONTAMINATE, DAMAGE AND RENDER USELESS NEEDED EQUIPMENT IN IFR FLIGHT, SPECIAL CONSIDERATION SHOULD BE TAKEN TO REMOVE THIS PRODUCT FROM AIRCRAFT IT MIGHT HAVE BEEN INSTALLED AS SOON AS POSSIBLE.(K) 1H71 3O3 ONT3A12 E1CE 20060927000042006092700004CE 2006 9 27 2006FA0000940 120060823G2750 FLAP SYSTEM RAYTHN390 390 7150030CE MISRIGGED B MGORO OTHER W INADEQUATE Q C NRNOT REPORTED 1 CE099LV RB132 DURING PHASE INSPECTION FOUND THE LT IB AFT FLAP TRACK ATTACH BOLT CHAFED 3 LAYERS OF CARBON FIBER INTO THE FUSELAGE. FOUND FLAP MISRIGGED AND TOP 3 FLAP TRACK FASTENERS WORKING. RECOMMEND ADDITIONAL ATTENTION TO FLAP RIGGING AND ALL ATTACHING HARDWARE DURING PHASE INSPECTIONS. (K) 17 2 3F RTA00010WI 20060927000082006092700008CE 2006 9 27 2006FA0000941 120060906G575339005214110002 FLAP TRACK RAYTHN390 390 7150030CE RT WING DAMAGED B MGORO OTHER O OTHER NRNOT REPORTED 1 CE09701KB600 RB103 DURING 200/600 HR PHASE INSPECTION FOUND THE RT IB AFT FLAP TRACK UPPER 3 ATTACH FASTENERS PN: MS90354S0609 WORKING. RECOMMEND ADDITIONAL ATTENTION TO FLAP RIGGING AND ALL ATTACHING HARDWARE DURING PHASE INSPECTIONS. (K) 17 2 3F RTA00010WI 20060927000092006092700009CE 2006 9 27 2006FA0000942 120060906G575339005214110002 FLAP TRACK RAYTHN390 390 7150030CE RT WING DAMAGED B MGORO OTHER O OTHER NRNOT REPORTED 1 CE09701KB600 RB103 DURING 200/600 HR PHASE INSPECTION FOUND THE RT IB AFT FLAP TRACK UPPER 3 ATTACH FASTENERS PN: MS90354S0609 WORKING. RECOMMEND ADDITIONAL ATTENTION TO FLAP RIGGING AND ALL ATTACHING HARDWARE DURING PHASE INSPECTION. (K) 17 2 3F RTA00010WI 20060927000072006092700007CE 2006 9 27 2006FA0000944 120060911G81204709440029 RELIEF VALVE CESSNA182 T182T 2072738CE LYC O540 TIO540AK1A EA WASTEGATE FAILED B Z08RO OTHER O OTHER NRNOT REPORTED 1 CE07182GA89 ILN00185 T18208587 L1240661A PILOT REPORTED, ON TAKEOFF ROLL, THE MANIFOLD PRESSURE WENT TO GREATER THAN 40 MP FOR 3 TO 4 SECONDS. THE PILOT WENT BACK TO RUNUP AREA AND CONFIRMED THAT MP COULD GO ABOUT 40 MP, PILOT TAXIED BACK TO RAMP AND GROUNDED AIRCRAFT. TROUBLESHOT TURBO CHARGER SYSTEM FOUND THE TURBO CHARGER WASTEGATE CONTROLLER HAD FAILED. REMOVED WASTEGATE CONTROLLER AND PRESSURE RELIEF VALVE AND SENT FOR CHECKOUT. FOUND THE WASTE CONTROLLER BAD AND THE PRESSURE RELIEF VALVE WAS FACTORY PRESENT TO THE INCORRECT MP PRESSURE WHICH IF SET CORRECTLY COULD HAVE PREVENTED THE ENGINE FROM OVERBOOSTING. THIS AC ENGINE TURBOCHARGING SYS HAD A DUEL SYS FAILURE. SB 369J ADDRESSES WHAT SHOULD BE DONE WHEN ENG IS OVERBOOSTED. MFG RECOMMEN1H71 3O3 ONT3A13 20060927000122006092700012CE 2006 9 27 2006FA0000945 120060707G7120 MOUNT BEECH 76 76 1153005CE LYC O360 O360* 41514EA RT ENGINE BROKEN D O OTHER O OTHER NRNOT REPORTED 1 SW992009X ME66 BOTH LT AND RT ENGINE MOUNT TO FIREWALL ATTACH POINTS BROKE OUT AFT OF THE FIREWALL IN THE UPPER OB POINT. THIS BREAKAGE IS DIFFICULT TO DETECT DUE TO VISIBILITY ACCESS. THESE BRACKETS BROKE BECAUSE OF FLIGHT THROUGH TURBULENCE. (K) 1L72 3O3 O A29CE E286 20060927000022006092700002CE 2006 9 27 2006FA0000946 120060707G712010598000021 ATTACH ANGLE BEECH 76 76 1153005CE LYC O360 O360* 41514EA ENGINE MOUNT BROKEN D O OTHER O OTHER NRNOT REPORTED 1 SW992009X ME66 BOTH LT AND RT ENGINE MOUNTS TO FIREWALL ATTACH POINTS BROKE OUT AFT OF THE FIREWALL IN THE UPPER OB POINT. THIS BREAKAGE IS DIFFICULT TO DETECT DUE TO VISIBILITY ACCESS. THESE BRACKETS BROKE BECAUSE OF FLIGHT THROUGH TURBULENCE. (K) 1L72 3O3 O A29CE E286 20060927000382006092700038GL 2006 9 27 2006FA0000947 220060908G72406870992 COMBUSTION CASE HUGHES369 369D 4470706WP ALLSN 250C 250C20B 03013GL ENGINE CRACKED B EOORO OTHER O OTHER NRNOT REPORTED 1 AL0390431 1100833D CAE830468 PILOT COMPLAINED THAT THE TOT SUDDENLY WENT 40 DEGREES C, HOT. FOUND OUTER COMBUSTION CAN CRACKS. REPLACED UNIT. (K) 1G71 3U3 U H3WE E4CE 20060926000602006092600060GL 2006 9 26 2006FA0000948 220060908G720023057142 CASE HUGHES369 369D 4470706WP ALLSN 250C 250C20B 03013GL ENGINE ERODED B EOORO OTHER O OTHER NRNOT REPORTED 1 AL03CFASX 684 1150D CAE830467 FOUND CASE HALVES SHOT. ENGINE RUNNING 35 DEGREES C, HOT. (K) 1G71 3U3 U H3WE E4CE 20060926000102006092600010EA 2006 9 26 2006FA0000949 120060907G56106003303025 WINDSHIELD CNDAIRCL600 CL6002A12 1900304EA COCKPIT CRACKED B SH5RO OTHER O OTHER NRNOT REPORTED 1 EA63150MH 3021 LT WINDSHIELD (PILOTS) OUTER-PLY CRACKED DURING FLIGHT. NO KNOWN CAUSE AS TO THE EVENTS LEADING TO CRACK. KNOWN TO BE A COMMON FAILURE ON CHALLENGER ACRYLIC WINDSHIELD AND SIDE WINDOWS. WHETHER DUE TO IMPACT OF SOME SORTS OR WINDSHIELD NEAT FAILURE OR DELAMINATION. WINDSHIELD AND AC WAS RTSD AS AIRWORTHY. (K) 2L72 4F RTA21EA 20060926002562006092600256EA 2006 9 26 2006FA0000950 120060907G56106003303025 WINDSHIELD CNDAIRCL600 CL6002B16 1900305EA GE CF34 CF34* NE COCKPIT CRACKED B SH5RO OTHER O OTHER NRNOT REPORTED 1 EA63500PE 5440 LT WINDSHIELD (PILOTS) OUTER-PLY CRACKED DURING FLIGHT. NO KNOWN CAUSE AS TO THE EVENTS OF THE CRACK. KNOWN TO BE A COMMON FAILURE ON CHALLENGER ACRYLIC WINDSHIELD AND SIDE WINDOWS. WHETHER DUE TO IMPACT OF SOME SORTS OR WINDSHIELD HEAT FAILURE OR DELAMINATION. WINDSHIELD WAS REMOVED AND REPLACED WITH A NEW WINDSHIELD AND AC WAS RETURNED AS AIRWORTHY. (K) 2L72 4F4 FRTA21EA E15NE 20060926002482006092600248NE 2006 9 26 2006FA0000951 120060908G32136525108027103 AXLE SKRSKYS64 CH54B 8142610NE PWA JFTD12JFTD12A5A 52047NE MLG CRACKED B JYDRO OTHER O OTHER NRNOT REPORTED 1 NM09158AC 64081 (REF NR: MDR06-091) UPON DISASSEMBLY, AXLE WAS FOUND TO BE CRACKED AND RUNS AROUND THE CIRCUMFERENCE. THE TRACTURE APPEARS TO ROIGINATE IN THE WELD ON THE CENTER OF THE AXLE SHAFT. THE AXLE WAS FRACTURED UNDER THE SOCKET, PN 6425-50202-101, AS EVIDENCED BY A CRACK EXTENDING AROUND THE CIRCUMFERENCE OF THE SOCKET, FROM APPROXIMATELY THE 10:00 TO 2:00 POSITION. NO RECENT EVENTS ARE KNOWN THAT MAY HAVE CONTRIBUTED TO THIS TYPE OF FAILURE. RECOMMENDATIONS TO PREVENT RECURRENCE: A ONE PIECE AXLE IS AVAILABLE FOR USE IN LIEU OF THE 2 PIECE WELDED AXLE. (K) 2G72 4U4 U H6EA E15EA 20060926001322006092600132CE 2006 9 26 2006FA0000952 120060908G3240 LINE BEECH MU300 400A 1155402CE PWA JT15 JT15D5 52112NE BRAKE CHAFED B E81RO OTHER O OTHER NRNOT REPORTED 1 GL03785TA RK239 DURING A SCHEDULED INSPECTION FOUND PN 128580101-1, BRAKE LINE ASSY CHAFE DAMAGED BY EXCESS LENGTH CABIN FLOOR PANEL ATTACH SCREW AS DESCRIBED IN MFG SB 53-3511. REPAIR REQUIRED SPLICING IN OF NEW BRAKE LINE SEGMENT IAW SB 53-3511. HAVE FOUND THIS CONDITION ON NUMEROUS OTHER AC. RECOMMEND THAT SB 53-3511 BE CHANGED TO A MANDATORY SB DUE TO COMMON OCCURRENCE AND POSSIBILITY FOR LOSS OF BRAKING ACTION IF TUBING CHAFED THROUGH. ALSO RECOMMEND AN ALERT INFO BULLENTIN ON THIS SUBJECT.(K) 2H72 4F4 FRTA16SW E25EA 20060927000012006092700001 2006 9 27 2006FA0000954 420060907G34601017241011 CDU AMD FALC50FALCON50MYST2730106EU GARRTTTFE731TFE731* 01518WP COCKPIT BURNED B JGVRO OTHER B SMOKE/FUMES/ODORS/SPARKS NRNOT REPORTED 1 CE0948KR 127 SMOKE EMANATING FROM NR 1 FMS CDU DURING CRUISE FLIGHT. UNIT SMELLED OF SMOKE AND WOULD NOT POWER UP DURING INITIAL BENCH CHECK. FURTHER TEARDOWN PENDING. (K) 2L73 4F4 F A46EU E6WE 20060926001252006092600125SO 2006 9 26 2006FA0000955 220060925G8530AEC631397CN2C CYLINDER BEECH 36 A36 1151604CE CONT O550 IO550B SO EXHAUST PORT CRACKED B O OTHER O OTHER NRNOT REPORTED 1 SO094307S133 E675 281757 NOTED ON 6 ENGINE COMPONENTS, INC. ECI CYLINDERS WITH 133.1 SINCE NEW AND PUT IN SERVICE ON THE SAME ENGINE DECEMBER 2004. NR4 AND NR5 CYLINDERS WERE CRACKED IN THE EXHAUST PORT WITH A HOLE BURNED THROUGH AT THE CRACK AND WAS LEAKING EXHAUST GASSES OVERBOARD. NR 1, NR 2, NR 3 AND NR 6 CYLINDERS WERE CRACKED IN THE SAME LOCATION AS NR 4 AND NR 5. THE CRACKS ARE IB OF THE EXHAUST GUIDE BOSS. THE THICKNESS OF THE MATERIAL IN THAT AREA OF THE EXHAUST PORT APPEARS TO BE TOO THIN AND NOT ABLE TO WITHSTAND THE HEAT AND STRESS PRESENT DURING NORMAL ENGINE OPERATION. 1L71 3O3 O 3A15 E3SO 20060926002472006092600247GL 2006 9 26 2006FA0000957 220060919G72306876873 IMPELLER HUGHES369 369D 4470706WP ALLSN 250C 250C20B 03013GL COMPRESSOR DAMAGED B EOORK NONE O OTHER ININSP/MAINT 1 AL03511SB289 1090592D CAE834272 DURING REPLACEMENT OF THE S16 SHAFT, IT WAS DISCOVERED THAT THE OUTER LAND OF THE SNAP RING GROOVE WAS VERY THIN AND THE INNER EDGE WAS LIFTING AND (2) .3750 INCH LONG PIECES CAME OFF OF THE LAND. WHEN THE SNAP RING WAS REMOVED THE GROVE FOR THE SNAP RING SEEMS TO BE THE NORMAL DIMENSION. (K) 1G71 3U3 U H3WE E4CE 20060927000032006092700003GL 2006 9 27 2006FA0000958 220060919G725023038241 TURBINE WHEEL HUGHES369 369D 4470706WP ALLSN 250C 250C20B 03013GL ENGINE DAMAGED B EOORO OTHER O OTHER NRNOT REPORTED 1 AL03511SB12352208 1090592D CAE834272 FOUND NR 1, AND NR 2 TURBINES RUBING AFTER ENGINE DISASSEMBLY FOR CHIPS. DURING 100 HR CHIPS WERE FOUND ON THE CHIP PLUGS. DISASSEMBLED ENGINE AND DISCOVERED THE N1 AND N2 TURBINES WERE RUBBING, REPLACED UNIT. (K) 1G71 3U3 U H3WE E4CE 20060926002432006092600243GL 2006 9 26 2006FA0000959 220060919G72106894171 GEARBOX HUGHES369 369D 4470706WP ALLSN 250C 250C20B 03013GL ENGINE MAKING METAL B EOORO OTHER O OTHER NRNOT REPORTED 1 AL03511SB126174455 1090592D CAE834272 FOUND PTO , PTO BALL BEARING AND TORQUEMETER SPALLED. FOUND CHIPS ON CHIP PLUGS. DISASSEMBLED GEAR BOX AND FOUND PTO GEAR, TORQUEMETER GEAR AND PTO BALL BEARING SPALLED. REPLACED GEARBOX. (K) 1G71 3U3 U H3WE E4CE 20061018000832006101800083SO 2006 10 18 2006FA0000961 220060919G8520656935 CRANKCASE CONT O520 GTSIO520* 17032SO ENGINE LEAKING B VA1RK NONE K FLUID LOSS ININSP/MAINT 1 SW19 292082 POROSITY IN CRANKCASE NOSE SECTION ON THE RT SIDE BY THE OIL GALLEY PLUG. LEAKS OIL, MFG HAS BEEN NOTIFIED. (K) 3 O E7CE 20061019001632006101900163SO 2006 10 19 2006FA0000962 220060919G8550656935 CRANKCASE CONT O520 GTSIO520* 17032SO ENGINE LEAKING B VA1RK NONE O OTHER ININSP/MAINT 1 SW19 604918 POROSITY IN CRANKCASE NOSE SECTION ON THE RT SIDE BY THE OIL GALLEY PLUG. LEAKS OIL. MFG HAS BEEN NOTIFIED. (K) 3 O E7CE 20061018000462006101800046 2006 10 18 2006FA0000963 120060918G493038828406 FCU HONEYWELL APU FUEL CORRODED B QKPRO OTHER O OTHER NRNOT REPORTED 1 SO05 FUEL PRESSURE IN THE DIFFERENTIAL PRESSURE VALVE IS CAUSING SEVERE PITTING INSIDE THE FCU HOUSING. THIS PITTING INSIDE THE FCU HOUSING. THIS PITTING EVENTUALLY BECOMES A PIN HOLE IN THE HOUSING. THIS PIN HOLE ALLOWS A STREAM OF FUEL TO EXIT THE FCU DURING OPERATION. IF THE PROBLEM IS NOT CORRECTED IT COULD CREATE A POTENTIAL FIRE HAZZARD. (K) 20061011001472006101100147CE 2006 10 11 2006FA0000964 120060919G5340AN743A ATTACH BOLT BEECH 23 C23 1151242CE LYC O360 O360A4K 41514EA SNSNCH76E 76EM8 EA ALTERNATOR WORN D PVQGO OTHER O OTHER NRNOT REPORTED 1 GL159239S M1732 L2046036A 17458K DURING PRE-RUNUP INSPECTION FOR ANNUAL INSPECTION ALTERNATOR BELT NOTED TO BE LOOSE. UPON INSPECTION OF ALTERNATOR FOR BELT TENSION THE FOLLOWING WAS NOTED: THE CASTLE NUT WAS BACKED OUT TO THE POINT OF CHAFING ON THE A+ WIRE, THE WIRE WAS KEEPING THE NUT FROM BACKING ALL OF THE WAY OFF OF THIS ATTACHMENT BOLT. THIS AIRCRAFT AND ENGINE COMBINATION HAD BEEN INSPECTED FOR ANNUAL AIRWORTHINESS BY THE SAME INSPECTION 3 TIMES DURING THE PAST 22.1 HRS. NOTE ENCLOSED PHOTO’S. THIS ENGINE HAS 237 HRS SINCE MAJOR OVERHAUL BY AN APPROVED SHOP AND WOULD ESTIMATE THAT THE NUT HAD NOT BEEN SAFTIED DURING ANY OF THIS TIME AS THE NUT WOULD ACTUALLY SLIDE ACROSS THE THREADS OF THE BOLT. (K) 1L71 3O3 O A1CE E286 5 NP4EA 20061011001832006101100183SO 2006 10 11 2006FA0000965 120060902G3230211C23412 PRESSURE SWITCH PIPER PA32 PA32R301T 7103220SO LYC O540 TIO540AH1A 42003EA MLG PUMP FAILED D O OTHER O OTHER NRNOT REPORTED 1 SO0598LA 3257031 L992361A AT AN ANNUAL INSPECTION IT WAS NOTED THE MAIN GEAR FAILED TO CYCLE COMPLETELY BEFORE PUMP SHUT OFF. PUMP CYCLED ON AND OFF UNTIL MAINS WERE FULLY RETRACTED. PUMP THEN REMAINED OFF. PRESSURE SHUT OFF SWITCH WAS CHECKED WITH A HIGH PRESSURE GAUGE AND IT WAS FOUND TO TRIP AT 1400 LB WELL BELOW THE 1800 LG IT WAS DESIGNED FOR. SWITCH IS ESTIMATED TO HAVE MADE 500 CYCLES BEFORE FAILING. IT IS NOTED THAT THIS IS MY FIRST INSPECTION OF THIS AIRCRAFT SO THE PROBLEM MAY HAVE BEEN OVER LOOKED IN THE PAST. (K) 1L71 3O3 O A3SO E14EA 20061012000732006101200073GL 2006 10 12 2006FA0000966 320060918G6114C6132C67 HUB CESSNA172 T41D CE CONT O360 IO360D 17025SO MCAULY2A34C D2A34C67 GL PROPELLER CRACKED B LT4RO OTHER O OTHER NRNOT REPORTED 1 SO19 686342 PROPELLER RECEIVED FOR REPAIR, RED DYE OIL LEAK. PROPELLER WAS DISASSEMBLED AND BLADE RETENSION THREADS EDDY CURRENT INSPECTED. NR2 BLADE RETENTION THREAD, 4 THREADS IN AT APPROXIMATELY 7 O`CLOCK POSITION FOUND CRACKED. HUB REMOVED FROM SERVICE. (K) 1H71 3O3 O 3A17 E1CE 5 CP3EA 20061012001232006101200123CE 2006 10 12 2006FA0000967 120060922G5610121140019 WINDOW CESSNA206 T206H 2073303CE LYC O540 TIO540* 41532EA REAR WINDOW DAMAGED B H5GRO OTHER O OTHER NRNOT REPORTED 1 EA07217DL674 T20608224 THE FACTORY ORIGINAL REAR WINDOW OF THIS AC BEGAN TO DEVELOP A CONCAVE AREA IN THE CENTER OF THE WINDOW. THIS AREA WOULD BECOME MORE PRONOUNCED IN DIRECT SUNLIGHT. THIS AC IS 6 YEARS OLD AD HAS ACCUMULATED 674.52 HOURS. THE AC WAS HANGER KEPT MOST OF THE TIME. THE WINDOW WAS REPLACED WITH A NEW UNIT MEASURING .250 INCH THICK. AMPLE CLEARANCE WAS MAINTAINED TO PROVIDE ROOM FOR EXPANSION AND CONTRACTION YET STILL MAINTAINING ADEQUATE ENGAGEMENT OF WINDOW INTO WINDOW RETAINER. THE ORIGINAL WINDOW MEASURED .125 INCH THICK. THIS INSTALLATION WAS PERFORMED UNDER THE FIELD APPROVAL PROCESS AND REQUIRED ONLY MINOR BENDING AND REFORMING OF THE RETAINER FLANGE OF THE AIRCRAFT STRUCTURE TO ACCEPT THIS NEW THICKER 1H71 3O3 ORTA4CE E14EA 20061012001212006101200121CE 2006 10 12 2006FA0000968 120060919G243523085001 STARTER GEN BEECH B300 B300 1159232CE PWA PT6 PT6A60A 52043NE HARTZLHCB4M HCB4MP3 GL LEFT WORN B AHTRO OTHER O OTHER NRNOT REPORTED 1 GL11200VC1737 712 FL316 IN FLIGHT THE LT SIDE STARTER/GEN AFT BEARING AT THE COOLING FAN FAILED AND THE GENERATOR FAILED. THE AC RETURNED TO ITS DEPARTURE TERMINAL WITHOUT INCIDENT. THE STARTER/GEN WAS REPLACED AND THE CHARGING AND ELECTRICAL SYSTEM OPS, CHECKED GOOD. NO KNOWN CAUSE, STARTER/GEN WAS WITHIN THE 1000 HRS FOR BEING OVERHAULED. (K) 2L72 4T4 TRTA24CE E4EA 6 CP56GL 20061012001222006101200122SO 2006 10 12 2006FA0000969 120060927G2140A23D04 SHUTOFF VALVE JANITROL PIPER PA31 PA31 7103102SO LYC O540 TIO540* 41532EA HEATER LEAKING D K NONE K FLUID LOSS ININSP/MAINT 1 AL0316SC 750 1997221 31639 DURING ANNUAL INSPECTION FOUND FUEL LEAKING AROUND DIAPHRAGM JOINT. PART MADE BY DURING FIRST QUARTER OF 2001. PN A23D04, 7.5 PSI, 24 VOLT. (K) 1L72 3O3 O A20SO E14EA 20061018001342006101800134SO 2006 10 18 2006FA0000970 120061002G3210AN617 BOLT PIPER PA31 PA31350 7103110SO MLG BROKEN G O OTHER O OTHER APAPPROACH 1 SO054093W24842250 318152176 MFG SL NR 1092, DATED 06/15/2005 DEALS WITH REPLACEMENT OF RETRACTION ARMS, P/N 42042-000 OR 42042-002 AT 6000 HOURS AND TO PERFORM INSPECTION FOR CRACKS USING 10X MAGNIFYING GLASS AND DYE PENETRANT AFTER REACHING 1500 HOURS AND AT EACH 250 HOURS THERE-AFTER UNTIL ACCUMULATION OF 6000 HOURS. THERE IS NO INSPECTION CRITERIA FOR INSPECTION AND REPLACEMENT OF ATTACHING HARDWARE. ATTACHMENT BOLTS HAVE BEEN VISUALLY INSPECTED EACH 250 HOURS WHEN REMOVED TO INSPECT RETRACTION ARMS. HOWEVER, BOLT FAILED AND WAS FOUND BROKEN AND SHEARED OFF WITH ONLY HEAD PORTION STILL IN PLACE. IT APPEARS THAT WITH BOLT SHEARED, THE LANDING GEAR ACTUATOR WAS PLACED IN A BIND WHICH BROKE THE BALL LINK THAT SCREWS IN THE MAIN SHAFT OF T1L72 3O A20SO 20061121001112006112100111SO 2006 11 21 2006FA0000971 220060926G732055P70D5E608 VALVE MOONEYM20 M20K 5870220SW CONT O360 TSIO360GB 17025SO ENGINE FUEL LEAKING D A UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 1 NM09231GR1340 250087 309083 THE FUEL PRIMER DIVERTER VALVE P/N 642199 (P/N 55P70D5E-608) LEAKED FUEL OVER THE TOP OF THE ENGINE IN FLIGHT, IT WAS LEAKING SO MUCH THE ENGINE WOULD NOT KEEP RUNNING WITHOUT THE USE OF THE ELECTRIC BOOST PUMP. INITIALLY OUR MFG VENDOR GAVE ME A REPLACEMENT P/N 633862 AND SAID NO PARTS WERE AVAILABLE. SO I CONTACTED THE MFG ENGINEERING AND SPOKE WITH THEIR REPAIR STATION MANAGER. HE INFORMED ME THAT THEY HAD JUST OVERHAULED A VALVE THAT HAD CAUSED AN ENGINE FIRE, AND THEY OVERHAUL 8-10 A YEAR. HE ALSO SAID THE OVERHAULED VALVES HAVE PMA AND WILL NEVER LEAK AGAIN. I CALLED MFG AND PASSED ON THE PROBLEM TO THEIR TECH REP, HE DID INFORM ME THAT THEY DO IN FACT STOCK THE NEW P/N VALVE. I CANNOT FIND ANY BULLETINS 1L71 3O3 O 2A3 E9CE 20061019002002006101900200SO 2006 10 19 2006FA0000974 120060929G28231138303 SELECTOR VALVE PIPER PA18 PA18125 7101812SO LYC O290 O290* 41506EA FUEL SYSTEM FAILED D A UNSCHED LANDING YJ ENGINE STOPPAGE WARNING INDICATION CRCRUISE 1 AL051896A 45 181728 FUEL SELECTOR/SHUTOFF VALVE HANDLE MOVED BUT VALVE DID NOT SELECT FROM LT FUEL TANK TO RT FUEL TANK. ENGINE RAN OUT OF FUEL FROM THIS AND AIRCRAFT LANDED ON ROAD. AD 60-10-08 WAS COMPLIED WITH 45 HOURS EARLIER. IA MECHANIC SUGGESTS THAT ROUTINE CLEANING OF VALVE AND INSPECTION OF PLASTIC PLUGS AROUND SHAFT MOUNTING HOLES CRACKS OR REPLACEMENT OF PLASTIC PLUGS WITH BRASS PLUGS. TIME IN SERVICE OF SELECTOR VALVE 11383-03 UNKNOWN. 1H71 3O3 O 1A2 E229 20061018000502006101800050EA 2006 10 18 2006FA0000975 220061003G74141052949 DISTRIBUTOR BLK CONT ROBSINR22 R22BETA 7640110NM LYC O320 O320B2C 41508EA MAGNETO FAILED G K NONE O OTHER ININSP/MAINT 1 WP238280J 4772011 0892 L1492539A DURING 500 H0UR INSPECTION AND SERVICE THE DISTRIBUTOR BLOCK BRONZE BUSHING WAS FOUND TO BE BROKEN AND FREE TO MOVE AROUND. 1G71 3O3 O H10WE E274 20061012001202006101200120 2006 10 12 2006FA0000976 220061003G853015070001 EXHAUST HEADER CIRRUSSR SR22 2130001GL ENGINE CRACKED G O OTHER O OTHER NRNOT REPORTED 1 WP23253SR50 2034 NR 5 EXHAUST STACH/HEADER WAS FOUND TO BE CRACKED AT THE CYLINDER FLANGE AT THE WELD. 1L71 3O NTA00009CH 20061018000322006101800032EU 2006 10 18 2006FA0000977 120061003G3260803682 PROXIMITY SENSOR AMD FALC50FALCON50MYST2730106EU MLG FAILED B A UNSCHED LANDING J WARNING INDICATION LDLANDING 1 SW11784B 118 GEAR SELECTED (DOWN), LT GEAR DOOR INDICATION LIGHT REMAIND RED. MANUAL GEAR PROCEDURES USED TO CLOSE DOOR. 2L73 4F A46EU 20061018000412006101800041SO 2006 10 18 2006FA0000979 220060915G853015070001 EXHAUST HEADER CIRRUSSR SR22 2130001GL CONT O550 IO550N 17042SO NR 5 CRACKED D O OTHER O OTHER NRNOT REPORTED 1 GL15253SR50 2034 NR 5 EXHAUST HEADER CRACKED AT CYLINDER FLANGE AT THE WELD. (K) 1L71 3O3 ONTA00009CHE3SO 20061018000422006101800042SO 2006 10 18 2006FA0000980 220060929G7414M3548 ROTOR SLICK PIPER PA18 PA18 7101802SO CONT C90 C90* 17009SO RT MAGNETO INOPERATIVE D A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CLCLIMB 1 AL037472D400 94010288 185807 PILOT NOTICED LACK OF POWER AND ROUGHNESS AFTER TAKEOFF. RETURNED TO FIELD, DISCOVERED INOPERATIVE RT MAGNETO. DISASSEMBLY OF RT MAGNETO REVEALED ROTOR SHAFT HAD SHEARED FLUSH WITH BOTTOM OF CAM CUTOUT. THE REMAINING ROTOR AND DISTRIBUTOR BOTH ROTATED FREELY. NO EVIDENCE OF PROBLEMS WITH EITHER GEAR. PROBABLE CAUSE IS A DEFECT IN MFG (POSSIBLY BAD METAL OR STRESS CRACK FROM MACHINING CAM SLOT. (K) 1H71 3O3 O 1A2 E252 20061018000402006101800040NM 2006 10 18 2006FA0000981 120061006G282007166171 FUEL LINE UNIVAR108 108 9230402NM LT DOOR POST CHAFED D K NONE O OTHER ININSP/MAINT 1 NM04933D 5401 1082933 AILERON CABLE HAD CHAFED 90 PERCENT THRU FUEL LINE. AREA A LITTLE HARD TO SEE. FOUND BY LOOKING FOR NAV LIGHT SQUAWK THAT LED TO THE LT UPPER DOOR POST AREA. SUGGEST THAT ALL SIMILAR STYLE MFG WITH AILERON CABLE THAT RUNS ALONG FUEL LINES TO BE INSPECTED AND INSTALL SOME FORM OF ANTI-CHAFING MATERIAL TO THE AFFECTED AREA. 1H71 3O A767 20061019001752006101900175CE 2006 10 19 2006FA0000983 120061009G7603 CONTROL CABLE CESSNA172 172RG 2072438CE LYC O360 O360F1A6 41514EA CARBUETOR FAILED D K NONE O OTHER TXTAXI/GRND HDL 1 CE079991B84 172RG1110 L297946A UPON SHUTDOWN AFTER FLIGHT, PILOT PULLED ON CARBURETOR MIXTURE CABLE TO IDLE CUT-OFF. THE CABLE CAME OUT IN THE PILOTS HAND. SUSPECT CARBURETOR MIXTURE CABLE BROKE DURING FLIGHT. SUSPECT CABLE HAS A QUALITY ISSUE. NOTE: DID NOT EFFECT OPERATION OF AIRCRAFT DURING FLIGHT. REPLACED CABLE WITH NEW. 1H71 3O3 O 3A17 E286 20061026001722006102600172GL 2006 10 26 2006FA0000984 320060918G6114C6132C67 HUB MCAULY CESSNA172 T41D CE CONT O360 IO360D 17025SO MCAULY2A34C D2A34C67 GL PROPELLER CRACKED B LT4RO OTHER O OTHER NRNOT REPORTED 1 SO19 3250 1101 686342 806058 PROPELLER RECEIVED FOR 60 MONTH OVERHAUL. PROPELLER WAS DISASSEMBLED AND BLADE RETENTION THREADS EDDY CURRENT INSPECTED. NR1 BLADE RETENTION THREAD, 4 THREADS IN AT APPROX 7 TO 8 OCLOCK POSITION FOUND CRACKED. HUB REMOVED FROM SERVICE. (K) 1H71 3O3 O 3A17 E1CE 5 CP3EA 20061025001272006102500127SO 2006 10 25 2006FA0000985 220060922G7310156F0034S0244 LINE CESSNA421 421C 2076016CE CONT O520 GTSIO520N 17032SO ENGINE FUEL RUPTURED B SI6RO OTHER KJ FLUID LOSS WARNING INDICATION NRNOT REPORTED 1 SW17469S 1120 421C1057 808347R FUEL HOSE RUPTURED, SPRAYING FUEL ON THE HOT EXHAUST MANIFOLD TO TURBO CHARGER CAUSING AN ENGINE FIRE ON THE GROUND. (K) 1L72 3O3 O A7CE E7CE 20061025001282006102500128SO 2006 10 25 2006FA0000986 120060825G3210ANG17 BOLT PIPER PA31 PA31350 7103110SO LYC O540 TIO540* 41532EA MLG BROKEN D O OTHER O OTHER NRNOT REPORTED 1 SO054093W24842 318152176 AIRCRAFT HAD GEAR UNSAFE LIGHT AND NO LT DOWN AND LOCKED INDICATION LIGHT, AS WELL. THE GEAR HANDLE WOULD NOT RETURN TO NEUTRAL POSITION. AIRCRAFT LANDED WITHOUT INCIDENT. WE BELIEVE THAT THE UPPER BOLT THAT RETAINS THE MAIN GEAR RETRACTION ARM BROKE DUE TO FATIGUE. THIS ALLOWED THE MAIN GEAR ACTUATOR TO BIND ON THE UPPER SECTION OF THE DRAG LEG AND BROKE THE MAIN GEAR ACTUATOR BALL END OUT OF THE MAIN SHAFT OF THE ACTUATOR. THERE IS SL NR 1092, DATED JUNE 15TH, 2005 THAT REQUIRES THE MAIN GEAR RETRACTION ARMS, PN 42042000 OR 42042002 TO BE INSPECTED USING A 10X MAGNIFYING GLASS AND LIQUID PENETRANT INSPECTION AFTER REACHING 1500 HOURS TIME IN SERVICE AND THERE AFTER AT EACH 250 HOURS UNTIL THAT PART REACH1L72 3O3 O A20SO E14EA 20061016002692006101600269CE 2006 10 16 2006FA0000987 120060922G282025160281 LINE LEAR 35 31 5170530CE GARRTTTFE731TFE731* 01518WP BOOST PUMP CHAFED B UO2RO OTHER K FLUID LOSS NRNOT REPORTED 1 GL195VG 014 BLEED AIR CLAMP POSITIONED OB OF FUEL LINE CHAFED INTO FUEL LINE CAUSING A FUEL LEAK WITH BOOST PUMP PRESSURE. (K) 2L72 4F4 FRTA10CE E6WE 20061016002182006101600218CE 2006 10 16 2006FA0000988 120060907G3240215286 BRAKE ASSY CESSNA501 551 2076605CE PWA JT15 JT15D4 52112NE LT MLG BROKEN D D RETURN TO BLOCK J WARNING INDICATION TXTAXI/GRND HDL 1 GL03502CL 317 5510002 DURING TAXI ON RAMP, LT BRAKE LOCKED UP (AIRCRAFT WAS MOVING AT A VERY LOW RATE OF SPEED). AFTER REMOVAL OF LT WHEEL, FOUND 1 STATOR BROKEN IN HALF, DROPPING DOWN ONTO WHEEL (BRAKE KEY), CAUSING WHEEL TO LOCK UP. NO DAMAGE NOTED TO WHEEL OR ANY OTHER PART OF AIRCRAFT. (K) 1L72 4F4 F A27CE E1NE 20061016002902006101600290CE 2006 10 16 2006FA0000989 120060922G55324555030001803 PANEL LEAR 45 45LEAR 5170805CE GARRTTTFE731TFE731* 01518WP VERTICAL STAB CRACKED D O OTHER O OTHER NRNOT REPORTED 1 NE0310J 063 DURING MAINTENANCE, DISCOVERED PANEL HAD 6 INCHES LONG CRACK RUNNING VERTICAL AT FWD ATTACH HOLES. PANEL WAS REPLACED. (K) 2L72 4F4 FRTT00008WIE6WE 20061018001052006101800105SO 2006 10 18 2006FA0000990 120060914G242060A4111810R BRUSH HOLDER PIPER PA28 PA28161 7102803SO LYC O320 O320* 41508EA ALTERNATOR WORN C O OTHER O OTHER NRNOT REPORTED 1 NE0336116637 287816614 DURING AC OPERATION, ALTERNATION CEASED PUTTING OUT POWER. UPON INSPECTION AFTER REMOVAL, FOUND FIELD BRUSHES PREMATURELY WORN, AND COCKED OVER IN BRUSH HOLDER. (K) 1L71 3O3 O 2A13 E274 20061020000332006102000033SO 2006 10 20 2006FA0000991 120060914G24204111810 ALTERNATOR PIPER PA28 PA28R201 7102816SO ENGINE INOPERATIVE D O OTHER O OTHER NRNOT REPORTED 1 NE032241Q109 28R7737029 ALTERNATOR CEASED OPERATION WITH ONLY 109 HOURS ON IT IN LIKE NEW CONDITION. (K) 1L71 3O 2A13 20061018000302006101800030WP 2006 10 18 2006FA0000992 220060907G7200 ENGINE RAYTHNDH125 HAWKER800XP 7150012CE GARRTTTFE731TFE7315BR WP NR 2 FAILED B AN3RA UNSCHED LANDING XTJENGINE FLAMEOUT ENGINE CASE PENETRATION WARNING INDICATION CRCRUISE 1 SO33800WW 258661 P107869 (REF NR: 2006-1001) 30,000 FT, ENGINE BANG, ENGINE WAS SHUTDOWN AND FLIGHT DIVERTED. NR 2 ENGINE TURBINE WHEEL FAILURE, UNCONTAINED. INITIAL VISUAL INSPECTION POSSIBLE TURBINE WHEEL FAILURE. INVESTIGATION IN PROCESS WITH ASSISTANCE FROM MFG. PORTION OF ENGINE PROTRUDED THE ENGINE THRUST REVERSER SECTION AT THE APPROXIMATE 5 OCLOCK POSITION. ENGINE REMOVED AND RELOCATED TO MFG. (K) 2L72 4F4 FRTA3EU E6WE 20061020000012006102000001EA 2006 10 20 2006FA0000993 220061005G8530LW19001 EXHAUST VALVE CESSNA182 182T 2072703CE LYC O540 IO540AB1A5 EA MCAULY3D36C B3D36C431 GL NR 5 CYLINDER STUCK B JRURK NONE O OTHER ININSP/MAINT 1 GL0717HP 997 18281436 L2971648A 041547 DURING A PHASE 2 INSPECTION, CYLINDER NR 5 WAS FOUND TO HAVE LOW COMPRESSION (10/80) WITH A STRONG LEAK PASSED THE EXHAUST VALVE. SUBSEQUENT INSPECTION FOLLOWING THE INSTRUCTIONS FOUND IN LYCOMING SB 388C REVEALED THAT THE EXHAUST VALVE WAS PARTIALLY STUCK AND WOULD NOT FULLY CLOSE. THE EXHAUST VALVE ALSO COULD NOT BE REMOVED FROM THE CYLINDER ONCE THE CYLINDER WAS REMOVED FROM THE ENGINE. LYCOMING RECOMMENDS THE FOLLOWING INTERVAL FOR INSPECTING NON-HELICOPTER ENGINES, "400 HOUR INTERVALS OR EARLIER IF VALVE STICKING IS SUSPECTED UNTIL EXHAUST VALVE GUIDES ARE REPLACED WITH GUIDES MADE OF IMPROVED MATERIAL (REFER TO LATEST REVISION OF SERVICE INSTRUCTION 1485)". 1H71 3O3 ONT3A13 1E4 5 C 20061020000392006102000039EA 2006 10 20 2006FA0000995 220060609G8520 CRANKCASE MOONEYM20 M20E 5870212SW LYC O360 AEIO360A1A 41514EA ENGINE BROKEN P A UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CLCLIMB 1 WP09671DB 200 670030 WHEN OUR ENGINE NEEDED A MAJOR OVERHAUL THE CRANKCASE WAS SENT TO DIVCO IN TULSA, OKLAHOMA FOR INSPECTION AND FAA AIRWORTHINESS CERTIFICATION. DIVCO DID REPAIRS AND MACHINE WORK AND CERTIFIED THE CRANKCASE AS AIRWORTHY ON FAA FORM 8130 PER 14 CFR § 43.13 (B). THE ENGINE WAS ASSEMBLED AND INSTALLED IN THE AIRPLANE. AT JUST OVER 200 HOURS THE CRANKCASE NEARLY BROKE IN HALF AT DIVCO'S REPAIR. IN A MATTER OF MINUTES THE ENGINE LOST SIX OF THE EIGHT QUARTS OF OIL IT HAD. THE CRANKCASE BREAK AND A SUBSEQUENT ENGINE FAILURE COULD HAVE BEEN CATASTROPHIC! THE TOTAL LOSS OF THE ENGINE, LOSS OF THE AIRPLANE AND LOSS OF LIFE OF THOSE ON BOARD AND ON THE GROUND WERE A VERY REAL POSSIBILITY. FORTUNATELY, HAD JUST DEP1L71 3O3 O 2A3 1E10 20061020000362006102000036SO 2006 10 20 2006FA0000999 120061002G510234285 LINE BALWKSFIRE FIREFLY715 1050518SO FUEL SYS SEPARATED B OG2RO OTHER O OTHER NRNOT REPORTED 1 CE072203B2 F7B2009 HOSE SEPARATED AT THE FUEL LINE END. PILOT WAS INFLATING BALLOON WHEN THIS OCCURRED. NEW HOSES WERE INSTALLED ON 7/27/2006. THE BALLOON HAD BEEN FLOWN TWICE, WITH A TOTAL OF 2.0 HOURS ON NEW HOSES. (K) 1B00 A14SO 20061023001582006102300158 2006 10 23 2006FA0001000 220061009G7314271T00687 PUMP BOEING767 767* NM ENGINE FUEL CRACKED B DM4RO OTHER O OTHER NRNOT REPORTED 1 SO19 PART HAS CRACK IN FILTER BOWL PORT, UNIT LEAKING. (K) 2L72 4F RTA1NM 20061025001252006102500125 2006 10 25 2006FA0001001 420060927G3417FE422 RELAY AMD FALC50FALCON50MYST2730106EU GARRTTTFE731TFE731* 01518WP AIR DATA FAILED B XJRRO OTHER O OTHER NRNOT REPORTED 1 CE09925BC 257 LOSS OF RT AIR DATA ELECTRICAL POWER CAUSES A SNEAK PATH THROUGH THE ARTHUR Q AIR DATA REVERSION RELAYS ON RELAY CARD 417J. THIS SNEAK PATH WILL CAUSE THE LT RADIO TUNING UNIT TO REVERT TO AIR DATA SOURCE NR 2. BECAUSE AIR DATA SOURCE NR 2 IS NOW INACTIVE, NEITHER TRANSPONDER WILL HAVE ALTITUDE ENCODING. ALTITUDE ENCODING SOURCE SELECTION VIA THE MODE SELECTOR SOURCE SELECTION WILL HAVE NO EFFECT, NOR WILL CHANGING SELECTED TRANSPONDER OR AIR DATA REVERSION SWITCH ON EITHER PILOTS SIDE. THIS IS A SINGLE POINT OF FAILURE CAUSING LOSS OF ALL ALTITUDE ENCODING AND WILL ALSO CAUSE TCAS FAILURE. INSTALLATION OF A STEERING DIODE IN THE ARTHUR Q REVERSION RELAY CIRCUIT WILL PREVENT THIS PROBLEM FROM OCCURRING. T2L73 4F4 F A46EU E6WE 20061026001822006102600182CE 2006 10 26 2006FA0001002 120060906G3260SR008 DOWNLOCK SWITCH CESSNA560 560XL 2076702CE PWA 545 PW545A NE RT MLG FAILED C CNQRO OTHER N FALSE WARNING CLCLIMB 1 CE07651QS4482 5605251 DB0515 AFTER TAKEOFF AND GEAR RETRACTION ALL GEAR LIGHTS WENT OUT. APPROX 5-10 INTO FLIGHT, NOTICED RT GREEN GEAR LIGHT WAS ON. NO OTHER ABNORMAL LIGHTS NOTED. 40 MINUTES LATER LIGHT EXTINGUISHED. TROUBLESHOT SYS BY RIGING ALL DOWN LOCK SWITCH WIRING AND SWITCH MOUNTED TO RT GEAR ACTUATOR AND AFTER COLD SOAKING FOUND SWITCH SR008 (DOWNLOCK SWITCH) HAD A 2.209 M OHM READING WHEN OPEN (SHOULD BE NO READING). REPLACED MLG ACTUATOR WITH A RENTAL UNIT AND OPERATIONAL CHECKS WERE GOOD. RESERVICED EMERGENCY PNEUMATIC GEAR EXTENSION. (K) 2L72 4F4 FRTA22CE E00059EN 20061020000402006102000040CE 2006 10 20 2006FA0001003 120060919G243523085001 STARTER GEN BEECH 300 300BEECH 1152930CE PWA PT6 PT6A60A 52043NE HARTZLHCB4M HCB4MP3 GL LT ENGINE WORN B AHTRO OTHER O OTHER NRNOT REPORTED 1 GL11200VC1737 712 FL316 IN FLIGHT THE LT SIDE STARTER/GENERATOR AFT BEARING AT THE COOLING FAN FAILED AND THE GENERATOR FAILED. THE AC RETURNED TO ITS DEPARTURE TERMINAL WITHOUT INCIDENT. THE STARTER/GENERATOR WAS REPLACED AND THE CARGING AND ELECTRICAL SYSTEM OPS CHECKED GOOD. NO KNOWN CAUSE, STARTER/GENERATOR WAS WITHIN THE 1000 HOURS FOR BEING OVERHAULED. (K) 2L72 4T4 T A24CE E4EA 6 CP56GL 20061023001542006102300154WP 2006 10 23 2006FA0001004 220061009G72108964214 RESTRICTOR VALVE MTSBSIMU2 MU2B26 5780408CE GARRTTTPE331TPE3310T WP HARTZLHCB4T HCB4TN5 GL REDUCTION GB FAILED B IZ2RO OTHER O OTHER NRNOT REPORTED 1 SW15392P 392SA P105025C CDA3129M1 FOLLOWING O/H AND INSTALLATION OF ENGINE ON AC AN IN-FLIGHT CHECK OF THE NTS SYSTEM WAS PERFORMED IAW MM INSTRUCTIONS. UPON ACTUATION OF THE STOP SWITCH BY THE PILOT FOR THE LT ENGINE THE AC YAWED NOSE LT APPROXIMATELY 20 TO 25 DEGREES. ALSO, THE ENGINE RPM HESITATED TO DECAY FOR 1 TO 2 SECONDS THEN DECAYED NORMALLY TO 35 PERCENT RPM. TROUBLESHOOTING FOLLOWING FLIGHT SHOWED THAT THE (TRIP) PRESSURE OF THE ENGINE WAS HIGHER THAN NORMAL AND THE DECISION WAS MADE TO REPLACE THE TORQUE SENSOR ASSY PN 31017263. A SECOND IN FLIGHT CHECK OF THE NTS SYSTEM WAS PERFORMED WITH THE SAME UNSATISFACTORY RESULTS. FURTHER TROUBLESHOOTING IAW MM. INSTRUCTION WAS CONDUCTED WITH NO DEFECTS NOTED. ENGINE REDUCTION GEARBOX 1H72 3T4 TRTA10SW E4WE 6 CP40EA 20061020000972006102000097SW 2006 10 20 2006FA0001007 120060908G5340 TEE FITTING MOONEYM20 M20J 5870219SW LYC O360 IO360A1A 41514EA FUSELAGE LOOSE B B2ERO OTHER O OTHER NRNOT REPORTED 1 EA235760Y721 241635 DURING ANNUAL INSPECTION, FOUND PRECISE FLIGHT SVS V, SN 17245 (T-FITTING) LOOSE IN HOUSING. IF FITTING PULLED OUR YOU WOULD HAVE COMPLETE VACUUM SYS FAILURE. (K) 1L71 3O3 O 2A3 1E10 20061023001572006102300157EA 2006 10 23 2006FA0001008 120061002G2740 CONTROL UNIT CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE HORIZONTAL STAB MALFUNCTIONED B O OTHER O OTHER NRNOT REPORTED 1 SW0587353 7353 REPORTED IN-FLIGHT SQUAWK, (STAB TRIM FAIL IN FLIGHT) ON AC. HSTCU WAS REMOVED AND SENT FOR TEST AND REPAIR. DURING BENCH TEST/INSPECTION THE FOLLOWING ITEMS WERE NOTED. UNIT MEMORY INDICATED (CP PITCH TRIM SWITCH JAMMED) (AC SWITCH). DURING AUTO TEST, (HSTCU DOOR SWITCH (PN 134-30901-005) FAILED) WAS INDICATED. DISASSY AND INSPECTION REVEALED SMALL AMOUNT OF CORROSION ON CIF ASSY OF HSTCU. PROBABLE CAUSES/RECOMMENDATIONS: KNOWN PROBLEM-UNRELIABLE TRIM SWITCH HAS A DOCUMENT THAT ADDRESSES THIS ISSUE. HSTCU DOOR SWITCH PROBABLY BENT AFTER INCIDENT DURING TROUBLESHOOTING, IF PRIOR TO FLIGHT FAULT WOULD HAVE BEEN INDICATED IN COCKPIT/CAUTION MECHANICS TO AVOID BENDING SWITCH ARM DURING MAINTENANCE ACTIONS.2L72 4F4 FRTA21EA E15NE 20061020000242006102000024SO 2006 10 20 2006FA0001009 220060923G7322MA35PA CARBURETOR CESSNA150 150C 2071808CE CONT O200 O200* 17020SO ENGINE FAILED D O OTHER O OTHER NRNOT REPORTED 1 WP157870Z 15059970 250066A48 ENGINE STOPPAGE ON FINAL DUE TO CARBURATOR FLOODING, SUSPECT STUCK FLOAT. REMOVED UNIT AND SENT BACK TO MANUFACTURE FOR INSPECTION. THIS CARBURETOR WAS (FACTORY REBUILT) 1 YEAR EARLIER AND HAD LESS THAN 55 HOURS TT. FUEL WAS FOUND SPILLING OUT OF COWLING WHEN EXITING THE AIRCRAFT, SHUT FUEL VALVE OFF. (K) 1H71 3O3 O 3A19 E252 20061020000302006102000030SO 2006 10 20 2006FA0001010 120060913G510089307000 ROD END PIPER PA28 PA28R200 7102811SO LYC O360 IO360C1C 41514EA CONTROL CABLE BROKEN D O OTHER O OTHER NRNOT REPORTED 1 WP0755068 28R7335176 L1061351A ROD END BROKE AT POINT OF ATTACHMENT ON SERVO ARM. APPEARS BOLT MAY HAVE BEEN OVER TORQUED AT SOME POINT WHICH CAUSED A STRESS CRACK AND FAILURE OF BOLT AT POINT OF ATTACHMENT. TORQUE BOLT AT TIME OF INSTALLATION. (K) 1L71 3O3 O 2A13 1E10 20061023001592006102300159SO 2006 10 23 2006FA0001011 220060925G8530AEC631397CN2C CYLINDER BEECH 36 A36 1151604CE CONT O550 IO550B SO ENGINE DAMAGED D O OTHER O OTHER NRNOT REPORTED 1 SO094307S133 E675 281757 THE DEFECTS WERE NOTED ON 6 ENGINE COMPONENTS, CYLINDERS WITH 133.1 SINCE NEW AND PUT IN SERVICE ON THE SAME ENGINE DECEMBER 2004. NR 4 AND NR 5 CYLINDERS WERE CRACKED IN THE EXHAUST PORT WITH A HOLE BURNED THROUGH AT THE CRACK AND WAS LEAKING EXHAUST GASSES OVERBOARD. NR1, NR2, NR3, AND NR6 CYLINDERS WERE CRACKED IN THE SAME LOCATION AS NR4 AND NR5. THE CRACKS ARE IB OF THE EXHAUST PORT APPEARS TO BE TOO THIN AND NOT ABLE TO WITHSTAND THE HEAT AND STRESS PRESENT DURING NORMAL ENGINE OPERATION. (K) 1L71 3O3 O 3A15 E3SO 20061023001602006102300160EA 2006 10 23 2006FA0001012 220061011G8500AEL13884 MAIN BEARING LYC O320 O320B2B 41508EA ENGINE FAILED B O3ORO OTHER O OTHER NRNOT REPORTED 1 AL03 251 RL1362339A THIS ENGINE WAS DISMANTLED DUE TO METAL CONTAMINATION. WE DISCOVERED THAT THE REAR SURFACE OF THE BEARING WAS PEELING AWAY. PROBABLE CAUSES OF THIS BEARING FAILURE ARE UNKNOWN. (K) 3 O E274 20061026001842006102600184EA 2006 10 26 2006FA0001013 220061009G8550 VALVE GUIDE CESSNA182 182T 2072703CE LYC O540 IO540AB1A5 EA ENGINE LEAKING B LC1RO OTHER K FLUID LOSS NRNOT REPORTED 1 EA07168TA 18281068 L2822248A OPERATOR COMPLAINED OF AN OIL LEAK. WHEN COWL WAS REMOVED IT WAS OBVIOUS THAT THE NR3 AND NR4 EXHAUST PUSH RODS AND PUSH ROD HOUSING WERE BENT. SUSPECTED STICKING EXHAUST VALVES. EXHAUST VALVE TO GUIDE CLEARANCE WAS CHECKED ON ALL CYLINDERS IAW SB AND THE PROBLEM CYLINDERS CHECKED OK. CYLINDERS NR2 AND NR5 CHECKED BELOW THE SPECIFIED CLEARANCE. INSPECTED THE LIFTERS ASSOCIATED THE DAMAGED PUSH RODS AND FOUND NO OTHER PROBLEMS. ALL EXHAUST VALVE GUIDES WERE REAMED IAW SI 1425A, AND EXHAUST VALVE STEMS WERE CLEANED PRIOR TO REASSEMBLY. (K) 1H71 3O3 ONT3A13 1E4 20061023001552006102300155SO 2006 10 23 2006FA0001014 120061011G261223454G10 FIRE LOOP CURTISC46 C46RCURTIS 2622710SO PWA R2800 R280097 52026NE HAMSTD34E 34E60 NE NR 2 NACELLE DAMAGED B EVARO OTHER O OTHER NRNOT REPORTED 1 AL017848B 273 FIRE WARNING LIGHT NR 2 ENGINE ZONE 2 AND 3 ILLUMINATED THEN EXTINGUISHED. VISUAL INSPECTION OF ENGINE SHOWS NO SIGN OF FIRE OR DAMAGE, SUSPECT FAULTY LOOP DETECTOR. (K) 2L72 4R4 R 3A2 E231 6 CP881 20061020000252006102000025SO 2006 10 20 2006FA0001015 120061019G5320AN78310D TEE FITTING GULSTMG1159 G1159 3953505SO BULKHEAD CRACKED E K NONE O OTHER ININSP/MAINT 1 SO19750RA* 117 UPON POST FLIGHT INSPECTION THE PILOT NOTICED SMALL AMOUNT OF HYDRAULIC FLUID SEEPING FROM THE BOTTOM OF THE RADOME. MAINTENANCE DETERMINED THAT THE LEAK WAS COMING FROM A BULKHEAD TEE IN THE NOSE LANDING GEAR DUMP VALVE LINE. THE LEAK WAS INITIALLY THOUGHT TO BE CAUSED BY A DEFECTIVE PACKING BETWEEN THE TEE AND A REDUCER INSTALLED IN THE FEMALE PORT OF THE TEE. THE PACKING WAS RENEWED AND THE SYSTEM WAS LAEK CHECKED. THE LEAK PERSISTED,THE TEE FITTING WAS REMOVED AND INSPECTED. A CRACK WAS FOUND ON THE INNER BORE OF THE FEMALE PORT OF THE FITTING AT THE MOLD LINE OF THE FITTING. THE CRACK WAS NOT VISIBLE ON THE EXTERIOR OF THE TEE. THE TEE WAS REPLACED.THE SYSTEM WAS LEAKED CHECKED AND THE AIRCRAFT WAS 2L72 4F RTA12EA 20061020000292006102000029CE 2006 10 20 2006FA0001016 120061019G5710 STRUCTURE CESSNA500 550 2076604CE RT WING CRACKED B K NONE O OTHER ININSP/MAINT 1 SW011254X9937 300 0494 DURING A PHASE NR 5 A CRACH WAS FOUND IN THE LT & RT WHEEL WELL AREA ADJACENT TO THE INSIDE CORNER OF THE OPENING AT THE WHEEL WELL. A REPAIR WAS DONE AS PER SERRIA INDUSTRIES WING SKIN REPAIR ENGINEERING REPORT NR 3521-36 AND A DER 8110-3. THIS REPAIR HAS BEEN DONE ON SEVERAL OF OUR (26) AIRCRAFT AND IS NOT UNCOMMON TO SEE IN THE FIELD. I WOULD LIKE TO SEE CESSNA TO COME OUT WITH A SB KIT FOR THIS FIX FOR US IN THE FIELD RATHER THAN HAVING TO GET DER SUPPORTON OUR OWN. 1L72 4F A22CE 20061129003802006112900380SW 2006 11 29 2006FA0001017 120061020G5302205030889015S SUPPORT BRACKET BELL 204 UH1H 1181407SW TAILBOOM LOOSE C O OTHER O OTHER NRNOT REPORTED 1 SW99 TAIL BOOM ELEVATOR SUPPORT BRACKET LOOSE. (WORKING RIVETS/SITE OF PREVIOUS REPAIR WITH PULL TYPE RIVETS). 1G71 4U EXPA1G71 20061023001532006102300153SO 2006 10 23 2006FA0001018 120061020G28222B663OH PUMP PIPER PA31 PA31325 7103105SO LYC O540 TIO540J2BD 41532EA FUEL BOOST FAILED B K NONE O OTHER ININSP/MAINT 1 CE0122GE 766 317712091 RL1182161A LT FUEL BOOST PUMP FAILED ON RUNUP, DEBRIS CONTAMINATED FUEL SYSTEM, DAMAGED ENGINE DRIVEN FUEL PUMP, FUEL FLOW TRANSDUCER, CONTAMINATION FOUND IN FUEL SERVO FUEL INLET SCREEN. SERVO REMOVED AND SENT TO REPAIR FACILITY FOR INSPECTION AND OR REPAIRS. 1L72 3O3 O A20SO E14EA 20061025001262006102500126GL 2006 10 25 2006FA0001020 120061018G2820 LINE CIRRUSSR SR20 05628AJGL CONT IO360 IO360* 17025CE FUEL SYSTEM CHAFED B O OTHER O OTHER NRNOT REPORTED 1 GL21777ND 1258 FUEL LINE CHAFED, LINE REPLACED. 1L71 3O3 ONTA00009CHE1CE 20061106000552006110600055CE 2006 11 6 2006FA0001021 120061006G3230991242339 VALVE CESSNA525 525 2076601CE WILINTFJ44 FJ44 66000GL MLG MALFUNCTIONED B CNQ3O OTHER O OTHER NRNOT REPORTED 1 GL13122CS 5250469 CREW REPORTED (HYDRAULIC PRESSURE ON) LIGHT STAYED ILLUMINATED AFTER LANDING GEAR RETRACTION. REPLACED LOADING VALVE AND OPERATIONALLY CHECKED HYDRAULIC SYSTEM. AIRCRAFT WAS RETURNED TO SERVICE. (K) 1L72 4F4 FRTA1WI E3GL 20061026001612006102600161CE 2006 10 26 2006FA0001022 120061006G5610NP13972112 WINDSHIELD CESSNA750 750 2076810CE ALLSN AE3007AE3007C GL COCKPIT FAILED B CNQ3O OTHER O OTHER NRNOT REPORTED 1 GL137SB 7500209 RT WINDSHIELD OUTER PANE FAILED IN FLIGHT. THE OUTER PANE IS NON STRUCTURAL AND DID NOT EFFECT THE INTEGRITY OF THE PRESSURE VESSEL. WINDSHIELD WAS SENT TO MFG ENGINEERING FOR FAILURE EVALUATION. (K) 2L72 4J4 FRTT00007WITE6CH 20061026001602006102600160CE 2006 10 26 2006FA0001023 120061006G2910991242339 VALVE CESSNA525 525 2076601CE WILINTFJ44 FJ44 66000GL HYD SYSTEM FAILED B CNQ3O OTHER O OTHER NRNOT REPORTED 1 GL13122CS 5250469 CREW REPORTED ALL HYDRAULIC SYSTEMS INOPERATIVE IN FLIGHT. LANDING GEAR WAS EXTENDED PNEUMATICALLY AND AIRCRAFT LANDED WITHOUT INCIDENT. IT WAS DETERMINED THE HYDRAULIC LOADING VALVE WAS NOT CLOSING ALLOWING HYDRAULIC PRESSURE TO BUILD. THE HYDRAULIC LOADING VALVE WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE. (K) 1L72 4F4 FRTA1WI E3GL 20061026001672006102600167WP 2006 10 26 2006FA0001024 220061002G7250 TURBINE WHEEL RAYTHNDH125 HAWKER800XP 7150012CE GARRTTTFE731TFE7315BR WP NR 2 ENGINE FRACTURED B ROIRO OTHER O OTHER NRNOT REPORTED 1 GL136NR 679 258701 P107953 IN FLIGHT, CREW FELT SLIGHT TO MODERATE VIBRATION FROM NR 2 ENGINE. AFTER LANDING FURTHER INSPECTION FOUND APPROX ONE INCH OF ONE OF THE 3 LPT DISK BLADES MISSING. REASON FOR FAILURE AT THIS TIME UNDER INVESTIGATION BY MFG, SB 72-3689. (K) 2L72 4F4 FRTA3EU E6WE 20061025001292006102500129NE 2006 10 25 2006FA0001025 220061003G723030B47451 COMPRESSOR WHEEL LEAR 60 60LEAR 5170707CE PWA 305 PW305A 52128NE LT ENGINE CRACKED B BTVRO OTHER O OTHER NRNOT REPORTED 1 GL23699DA2054 237 PCECA0319 (REF NR: 6841.5.30) DURING A SCHEDULED INSPECTION, EDDY CURRENT NDT REVEALED A CRACK IN THE LT ENGINE HP COMPRESSOR STAGE 1 ROTOR. (K) 2L72 4F4 FRTA10CE E35NE 20061026001782006102600178SO 2006 10 26 2006FA0001027 220061017G8520 ROD BEECH 58 58 1152740CE CONT O520 IO520C 17032SO ENGINE FAILED D A UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 1 SW11640LS907 TH1107 827255R CYLINDER NR 2 PISTON ROD FAILED WHILE AIRCRAFT WAS IN CRUISE FLIGHT. PROP WAS FEATHERED. AIRCRAFT LANDED WITHOUT INCIDENT. (K) 1L72 3O3 O 3A16 E5CE 20061026001592006102600159CE 2006 10 26 2006FA0001028 120060912G6100A4564 BEARING CESSNA208 208B 2073701CE PWA PT6 PT6* 52043EA MCAULY3AF34C3GFR34C703 GL PROPELLER BROKEN D O OTHER O OTHER NRNOT REPORTED 1 EA27324SJ1898 208B0908 010761 UPON DISASSEMBLY OF THIS PROPELLER IAW WITH MFG TECH REPORT NR940. IT WAS DISCOVERED THAT THE PITCH CHANGE LINK BUSHINGS, P/N A4564, ON BLADES NR 2 AND NR 3 WERE BROKEN AND PARTIALLY MISSING. AT LEAST 50 PERCENT OF THE BUSHINGS WERE NOT IN THE LINK. THE THICKNESS OF BUSHING WOULD ALLOW THE BLADE ANGLES OF TWO OF THE THREE BLADES TO BE MUCH DIFFERENT ANGLE THAN THEY SHOULD BE, LEADING TO EXCESSIVE VIBRATION AND LOSS OF EFFICIENCY. (THIS WAS THE REASON FOR THE HIGHER VIBRATIONS REPORTED BY THE FLIGHT CREWS). SB137AB HAS A MANDATORY SPECIFIED TIME BETWEEN OVERHAULS FOR THIS PROPELLER OF 4000 HOURS OR 72 CALENDAR MONTHS, WHICHEVER COMES FIRST. THIS PROPELLER WAS REMOVED DUE TO A CALENDAR CHANGE, NOT DUE TO HOURS IN1H71 3T3 T A37CE E2NE 5 CP60GL 20061026001632006102600163CE 2006 10 26 2006FA0001029 120061009G5280634100616 STUD CESSNA CESSNA525 525 2076601CE WILINTFJ44 FJ44 66000GL MLG DOOR BROKEN D O OTHER O OTHER NRNOT REPORTED 1 CE01902GW488 5250553 COMPONENT STUD APPEARS TO HAVE BEEN CRACKED FOR SOME TIME, RUST EVIDENT HALF WAY THRU BOLT CROSS SECTION AT THE START OF THE THREADED AREA, NEAR CENTER OF THE STUD. COULD POSSIBLY HAVE BEEN CAUSED BY MFG FLAW, OVER TORQUEING OF SAFETY JAMB NUTS, TO OVER RIGGING OF MLG DOOR (TOO TIGHT), IN THE GEAR UP POSITION. WHEN THIS LINK BREAKS, THE DOOR DROPS FURTHER THAN THE GEAR ALLOWING IT TO COME INTO CONTACT WITH THE GROUND DAMAGING THE GEAR DOOR, WHICH UNDER THE RIGHT CIRCUMSTANCE COULD CAUSE EXTENSIVE DAMAGE TO THE WING. (K) 1L72 4F4 FRTA1WI E3GL 20061026001652006102600165EA 2006 10 26 2006FA0001030 220061019G8530LW19001 EXHAUST VALVE LYC O320 O320E2D 41508EA CYLINDER NR 3 BROKEN D O OTHER O OTHER NRNOT REPORTED 1 SW99 1606 HEAD OF THE NR 3 EXHAUST VALVE BROKE OFF DURING ENGINE OPERATION. THE BROKEN PIECES DAMAGED THE PISTON AND CYLINDER HEAD AS WELL AS THE LOWER SPARK PLUG. SMALL PIECES FOUND IN THE OTHER 3 CYLINDERS AS WELL. (K) 3 O E274 20061031001562006103100156CE 2006 10 31 2006FA0001031 120060803G7430A5109 IGNITION SWITCH CESSNA172 172S 2072439CE INSTRUMENT PANELINTERMITTENT D D RETURN TO BLOCK O OTHER TXTAXI/GRND HDL 1 GL03656SJ1098 172S8656 DURING A GROUND OUT CHECK OF THE IGNITION SWITCH, THE ENGINE CONTINUED TO RUN. REPEATED TESTS DUPLICATED CONDITION 4 OUT OF 10 TIMES. UPON FURTHER INVESTIGATION IT WAS FOUND THAT THE RT MAGNETO CONTINUED TO RUN WHEN THE FAULT OCCURRED. REPLACED THE MAGNETO/STARTER SWITCH. MAGNETO SWITCH, MODEL NR A-510-9. AC PN C292501-0107, CAGE NR 65873. 1H71 3O NT3A12 20061031001642006103100164CE 2006 10 31 2006FA0001032 120061025G3240656120011 TIE ROD CESSNA500 560CESSNA 2076750CE PWA 530 PW535A NE LEFT CHAFED D K NONE O OTHER NRNOT REPORTED 1 WP27221VP2161 5600585 LT BRAKE TIE-ROD CHAFING ON COCKPIT DEFROST DUCT APPROX 6 INCHES ABOVE COCKPIT FLOOR, ROD WORN APPROX .030 INCHES. NO RELOCATION OF COMPONENTS POSSIBLE TO ALLEVIATE CHAFING. REPLACEMENT PART RECEIVED FROM MFG IS DIFFERENT PN AND SMALLER DIAMETER. 2L72 4F4 FRTA22CE E00053EN 20061031001652006103100165CE 2006 10 31 2006FA0001033 120061030G7160NONEREADABLE AIR FILTER CESSNA172 172S 2072439CE LYC IO360 IO360L2A EA ENGINE DETERIORATED B K NONE O OTHER ININSP/MAINT 1 SO152108L66 39 172S9605 METAL PIECES COMING OFF AIRFILTER (AIR FILTER P/N: CPE1173, PREVIOUSLY INSTALLED IAW STC NR SA01669CH. THE METAL PIECES THAT ARE COMING A PART ARE LOCATED ON THE TOP, FRONT AND REAR OF THE FILTER ASSEMBLY. AN FAA-PMA STAMP COVERS THE PN ON THE FILTER. THE ONLY IDENTIFYING FEATURES ON THE FILTER IS A K&N STAMP, AND A MESSAGE TO SERVICE AT 50,000 MILES. 1H71 3O3 ONT3A12 1E10 20061031001692006103100169SO 2006 10 31 2006FA0001034 220061027G8550ES48108 OIL FILTER CESSNA140 140 2071602CE CONT C85 C8512F 17008SO ENGINE CONTAMINATED C A UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 CE07729512 10149 DURING CRUISE FLIGHT, OIL PRESSURE DROPPED TO BELOW MINIMUM REDLINE. PRECAUTIONARY LANDING WAS MADE. ON INSPECTION, DISCOVERED RECENTLY INSTALLED (2 HOURS IN SERVICE) OIL FILTER HAS DESIGN AND/OR MANUFACTURING DEFECT ALLOWING AN INTERNAL SEAL TO BE DAMAGED DURING MFG SUCH THAT RUBBER SEAL MATERIAL IS RELEASED FROM THE FILTER INTO THE ENGINE OIL. LOW OIL PRESSURE CONDITION WAS DUE TO A CHUNK OF THIS MATERIAL FOULING THE SEAT OF THE OIL PRESSURE REGULATING VALVE, KEEPING THE VALVE PARTIALLY OPEN. THE FILTER HAS BEEN DISSECTED AND I HAVE DIGITAL PHOTOS OF THE PARTS IN QUESTION AS WELL AS THE DEBRIS FOUND IN THE OIL SYSTEM. I WILL RETAIN CUSTODY OF THE PARTS, BUT I CAN MAKE THEM AVAILABLE FOR INSPECTION AT THE1H71 3O3 ONCA768 E233 20061031001702006103100170SO 2006 10 31 2006FA0001035 220061027G8550ES48108 OIL FILTER CESSNA140 140 2071602CE CONT C85 C8512F 17008SO ENGINE CONTAMINATED C A UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 CE07729512 10149 DURING CRUISE FLIGHT, OIL PRESSURE DROPPED TO BELOW MINIMUM REDLINE. PRECAUTIONARY LANDING WAS MADE. ON INSPECTION, DISCOVERED RECENTLY INSTALLED (2 HOURS IN SERVICE) OIL FILTER HAS DESIGN AND/OR MANUFACTURING DEFECT ALLOWING AN INTERNAL SEAL TO BE DAMAGED DURING MFG SUCH THAT RUBBER SEAL MATERIAL IS RELEASED FROM THE FILTER INTO THE ENGINE OIL. LOW OIL PRESSURE CONDITION WAS DUE TO A CHUNK OF THIS MATERIAL FOULING THE SEAT OF THE OIL PRESSURE REGULATING VALVE, KEEPING THE VALVE PARTIALLY OPEN. THE FILTER HAS BEEN DISSECTED AND I HAVE DIGITAL PHOTOS OF THE PARTS IN QUESTION AS WELL AS THE DEBRIS FOUND IN THE OIL SYSTEM. I WILL RETAIN CUSTODY OF THE PARTS, BUT I CAN MAKE THEM AVAILABLE FOR INSPECTION AT THE1H71 3O3 ONCA768 E233 20061101000952006110100095SW 2006 11 1 2006FA0001036 120061031G6320206033426001 SUPPORT BELL BELL 206 206L3 1182108SW ALLSN 250C 250C30 03013GL TAILBOOM CRACKED B SL3RK NONE O OTHER ININSP/MAINT 1 NE01812TV3622 50 AO1402 51185 CRACK FOUND AT TAIL ROTOR GEARBOX AFT LT MOUNTING HOLE ON TAILBOOM CASTING. REPLACED GEARBOX SUPPORT CASTING. 1G71 3U3 U H2SW E1GL 20061117001462006111700146EA 2006 11 17 2006FA0001037 220061101G8530LW19001 EXHAUST VALVE CESSNA182 182S 2072701CE LYC O540 IO540AB1A5 EA MCAULY3D36C B3D36C431 GL ENGINE STUCK B JRURK NONE O OTHER ININSP/MAINT 1 GL07311HP673 18280919 RL2144048A 002157 DURING A PHASE 2 INSPECTION, CYLINDER NR 5 WAS FOUND TO HAVE LOW COMPRESSION (5/80) WITH A STRONG LEAK PASSED THE EXHAUST VALVE. SUBSEQUENT INSPECTION FOLLOWING THE INSTRUCTIONS FOUND IN SB 388C REVEALED THE CYLINDER DID NOT MEET THE MEASUREMENT CRITERIA FOR THE EXHAUST VALVE GUIDE. THE MEASUREMENT TAKEN BEFORE REAMING (IAW SB388C) WAS .007 INCH. THE EXHAUST VALVE WAS REMOVED FROM THE CYLINDER (WITH THE CYLINDER INSTALLED) AND EXHAUST VALVE GUIDE WAS REAMED. A COMPRESSION CHECK WAS TAKEN AGAIN ON CYLINDER NR 5 AND COMPRESSION AFTER REAMING WAS 77/80. MEASUREMENT AFTER REAMING WAS .0175 INCH. THE PERMISSIBLE RANGE IS .015 TO .030 INCH. CYLINDER NR 3 ALSO FAILED THE MEASUREMENT CRITERIA OF SB 388C. THIS EXHAUS1H71 3O3 ONT3A13 1E4 5 C 20061107000652006110700065CE 2006 11 7 2006FA0001039 120061011G323399121202 SWITCH CESSNA500 560CESSNA 2076750CE PWA JT15 JT15D5 52112NE NOSE GEAR ACTUATMALFUNCTIONED D O OTHER O OTHER NRNOT REPORTED 1 EA6194TX 3104 5600247 NOSE GEAR ACTUATOR JAMMED IN THE EXTENDED POSITION. WOULD NOT RETRACT. FOUND ACTUATOR FAULTY INTERANA SWITCH. REPLACED NOSE GEAR ACTUATOR. ACTUATOR PARET NR 15232005, SN 842. (K) 2L72 4F4 FRTA22CE E25EA 20061107000662006110700066NE 2006 11 7 2006FA0001040 220061005G7320310033501 SENSOR BEECH MU300 400A 1155402CE PWA JT15 JT15D5 52112NE LT ENGINE N1 DAMAGED B AHTRO OTHER O OTHER NRNOT REPORTED 1 GL11827SB8181 406 RK2 PCE100183 IN NORMAL FLIGHT, THE EFC OFF(ELECTRONIC FUEL CONTROL) ANNUNCIATOR LIGHT ILLUMINATED. THE PILOTS ATTEMPTED TO RESET THE EFC SEVERAL TIMES, FAILING AT EVERY ATTEMPT. TROUBLESHOOTING REVEALED DAMAGE TO THE N1 SENSOR PROBE CAUSED BY THE N1 PICK-UP, AT 24 EQUALLY-SPACED TOOTHED WHEEL INTEGRAL TO THE COMPRESSOR SHAFT. MINUTE DAMAGE WAS INFLICTED ON THE PROBE, CONSISTING OF AN EXTREMELY SHALLOW GROOVE CUT INTO THE END OF THE PROBE. THE TOOTHED WHEEL DID NOT APPEAR DAMAGED. THE PROBE WAS PROBABLY DAMAGED DUE TO THE IMPROPER INSTALLATION. (K) 2H72 4F4 FRTA16SW E25EA 20061107000642006110700064SW 2006 11 7 2006FA0001041 120061006G6200069A5512 DRIVE BELT HUGHES269 269C1 8059504SW LYC O360 HIO360* 41514EA MAIN ROTOR STRETCHED B HA4RO OTHER O OTHER NRNOT REPORTED 1 SO1517535 0225 NEW DRIVE BELTS WERE INSTALLED, STRETCHED FOR 24 HOURS, AND RE-ADJUSTED IAW MM. THE AIRCRAFT WAS RETURNED TO SERVICE AND .5 HOUR INTO THE FIRST FLIGHT THE PILOT NOTICED THE MAIN ROTOR RPM DECAYING AND ENGINE RPM INCREASING. A STEEP DESCENT WITH POWER WAS PERFORMED AND THE AIRCRAFT LANDED SAFELY. A SUBSEQUENT MAINTENANCE INSPECTION REVEALED THAT THE BELTS HAD CONTINUED TO STRETCH AFTER THE AIRCRAFT WAS RETURNED TO SEVERICE CAUSING THE CLUTCH ACTUATOR TENSION TO BECOME EXCESSIVELY LOOSE. THIS ALLOWED THE BELTS TO SLIP ON THE DRIVE PULLEYS AND ALLOWED THE MAIN ROTOR RPM TO DROOP. (K) 1G71 3O3 OO 4H12 1E10 20061107000572006110700057NM 2006 11 7 2006FA0001042 120061015G5330 SKIN BOEING727 727191 1384063NM PWA JT8 JT8D7B 52053NE BS 360 S24-26R CORRODED B KO0RO OTHER O OTHER NRNOT REPORTED 1 GL23502MG 19391 CORROSION ON FUSELAGE SKIN AT BS 360 CIRCUMFERENTIAL SKIN JOINT BETWEEN STR 24R AND STR 26R. (K) 2L73 4F4 F A3WE E2EA 20061107000682006110700068NM 2006 11 7 2006FA0001043 120061015G5330 SKIN BOEING727 727191 1384063NM PWA JT8 JT8D7B 52053NE BS 441 S17R CORRODED B KO0RO OTHER O OTHER NRNOT REPORTED 1 GL23502MG 19391 CORROSION ON FUSELAGE SKIN AT BS 441, STR 17R. (K) 2L73 4F4 F A3WE E2EA 20061107000582006110700058NM 2006 11 7 2006FA0001044 120061015G551165174375 RIB BOEING727 727191 1384063NM PWA JT8 JT8D7B 52053NE HORIZONTAL STAB CRACKED B KO0RO OTHER O OTHER NRNOT REPORTED 1 GL23502MG 19391 LT HORIZONTAL STABILIZER ELEVATOR HINGE SUPPORT RIB CRACKED (2.5 INCHES) ON OB, UPPER, AFT SIDE OF RIB AT ELEV STA 99.79. (K) 2L73 4F4 F A3WE E2EA 20061107000602006110700060NM 2006 11 7 2006FA0001045 120061015G5511651742812 RIB BOEING727 727191 1384063NM PWA JT8 JT8D7B 52053NE HORIZONTAL STAB CRACKED B KO0RO OTHER O OTHER NRNOT REPORTED 1 GL23502MG 19391 RT HORZ STAB ELEVATOR HINGE SUPPORT RIB CRACKED (2.5 INCH) ON UPPER FLANGE AT ELEV STA 17.20. (K) 2L73 4F4 F A3WE E2EA 20061107000612006110700061NM 2006 11 7 2006FA0001046 120061015G5330 SKIN BOEING727 727191 1384063NM PWA JT8 JT8D7B 52053NE BS 480 S7-8L CORRODED B KO0RO OTHER O OTHER NRNOT REPORTED 1 GL23502MG 19391 EXTERNAL FUSELAGE SKIN CORRODED AT STA 480, STR 7L TO STR 8L, CIRCUMFERENTIAL JOINT. (K) 2L73 4F4 F A3WE E2EA 20061107000672006110700067NM 2006 11 7 2006FA0001047 120061015G5330 SKIN BOEING727 727191 1384063NM PWA JT8 JT8D7B 52053NE BS 480 S9-10L CORRODED B KO0RO OTHER O OTHER NRNOT REPORTED 1 GL23502MG 19391 EXTERNAL FUSELAGE SKIN CORRODED AT STA 480, STR 9L TO STR 10L, CIRCUMFERENTIAL JOINT. (K) 2L73 4F4 F A3WE E2EA 20061107000422006110700042SW 2006 11 7 2006FA0001048 120061003G3220540004 LEG ASSY MOONEYM20 M20C 5870208SW LYC O360 O360* 41514EA NLG ASSY DAMAGED D O OTHER O OTHER NRNOT REPORTED 1 CE0178880 2895 NOSE GEAR COLLAPSED UPON LANDING. INITIAL INSPECTION FOUND BOTH TUBES ON THE NOSE GEAR LEG ASSEMBLY BROKEN. RETRACT MECHANISM TUBES BENT. UNABLE TO DETERMINE WHICH COMPONENTS WERE DAMAGED PRIOR TO THE INCIDENT. PILOT REPORTED THAT THE LANDING GEAR WAS HARDER THAN NORMAL TO RETRACT DURING THE LAST TAKEOFF AND EASIER TO EXTEND THAN NORMAL DURING THIS LANDING. (K) 1L71 3O3 O 2A3 E286 20061107000562006110700056GL 2006 11 7 2006FA0001049 120061010G2810C36L CAP DIAMONDA40 DA40 2990002GL FUEL TANK LEAKING D O OTHER O OTHER NRNOT REPORTED 1 NM07416FP40 40FC016 UPON PREFLIGHT OF THE AIRCRAFT, AND AFTER SITTING OUTSIDE OF THE HANGAR DURING A RAINSTORM, 2 TO 3 SUMP GLASSES WERE FILLED WITH WATER FROM EACH WING FUEL TANK SUMP DRAIN. FURTHER INSPECTION OF 9 OTHER AIRCRAFT OF THE SAME MAKE AND MODEL FOUND 2 OTHER AIRCRAFT WITH SIMILAR AMOUNTS OF WATER IN THE SUMP DRAINS. ALL 3 OF THESE AIRCRAFT WERE TIED DOWN OUTSIDE DURING WEATHER ABOVE STATED. INSPECTION OF THE FUEL FILLER FLANGE/CAP ASSEMBLY OF ALL TWELVE AIRCRAFT REVEALED THE SAME LOOSE FUEL CAP CONDITION. ALL AIRCRAFT FUEL CAPS WERE TIGHTEN AS A PRECAUTION. THE O-RING SEALS DID NOT APPEAR TO BE DAMAGED. 1L71 3O NTA47CE 20061107000542006110700054EA 2006 11 7 2006FA0001050 220061025G8597DA424064100 WIRE HARNESS DIAMONDA40 DA40 2990002GL LYC O360 O360A4M 41514EA ALT/CB DAMAGED D O OTHER O OTHER NRNOT REPORTED 1 NM07417FP69 40FC017 TOTAL ELECTRICAL SYSTEM FAILURE IN FLIGHT. INSPECTION REVEALED THAT THE MAIN POWER WIRE’S RING TERMINAL TO THE ALTERNATOR HAD FAILED CAUSING ARCING WHICH SHORTED THE ALTERNATOR OUT AND CAUSED THE MAIN AND ESSENTIAL BUSS CIRCUIT BREAKERS TO POP. POSSIBLE CAUSE IS TOO SHORT OF A WIRE HARNESS WHICH DOES NOT ALLOW FOR ENGINE VIBRATION. REMEDIED WITH NEW ALTERNATOR AND NEW ALTERNATOR CABLE ASSY PROVIDED BY MFG. THE NEW CABLE ASSY IS A COUPLE OF INCHES LONGER TO PREVENT THIS FROM OCCURRING. (K) 1L71 3O3 ONTA47CE E286 20061107000552006110700055GL 2006 11 7 2006FA0001051 120061010G2701D4122131200 CONTROL STICK DIAMONDA40 DA40 2990002GL CONTROL COLUMN DAMAGED D O OTHER O OTHER NRNOT REPORTED 1 NM07418FP34 40FC018 PILOTS CONTROL STICK GRIP BECAME LOOSE AND WOULD, IF PULLED ON, COULD BECOME DETACHED FROM THE CONTROL ASSEMBLY. CHECK BOTH CONTROL GRIPS FOR LOOSE INSTALLATION AND REATTACH WITH APPROVED ADHESIVE. (K) 1L71 3O NTA47CE 20061107000532006110700053GL 2006 11 7 2006FA0001052 120061010G2810C36L CAP DIAMONDA40 DA40 2990002GL WING FUEL TANK LEAKING D O OTHER O OTHER NRNOT REPORTED 1 NM07420FP 40FC020 UPON PREFLIGHT OF THE AIRCRAFT, AND AFTER SITTING OUTSIDE OF THE HANGAR DURING A RAINSTORM, 2 OR 3 SUMP GLASSES WERE FILLED WITH WATER FROM EACH WING FUEL TANK SUMP DRAIN. FURTHER INSPECTION OF 9 OTHER AC OF THE SAME MAKE AND MODEL FOUND 2 OTHER AC WITH SIMILAR AMOUNTS OF WATER IN THE SUMP DRAINS. ALL 3 OF THESE AC WERE TIED DOWN OUTSIDE DURING WEATHER ABOVE STATED. INSPECTION OF THE FUEL FILLER FLANGE/CAP ASSY ON ALL 12 AIRCRAFT REVEALED THE SAME LOOSE FUEL CAP CONDITION. ALL AC FUEL CAPS WERE TIGHTENED AS A PRECAUTION. THE O-RING SEALS DID NOT APPEAR TO BE DAMAGED. (K) 1L71 3O NTA47CE 20061107000622006110700062GL 2006 11 7 2006FA0001053 120061010G2810C36L CAP DIAMONDA40 DA40 2990002GL WING FUEL TANK LEAKING D O OTHER O OTHER NRNOT REPORTED 1 NM07423FP38 40FC023 UPON PREFLIGHT OF THE AIRCRAFT, AND AFTER SITTING OUTSIDE OF THE HANGAR DURING A RAINSTORM, 2 OR 3 SUMP GLASSES WERE FILLED WITH WATER FROM EACH WING FUEL TANK SUMP DRAIN. FURTHER INSPECTION OF 9 OTHER AC OF THE SAME MAKE AND MODEL FOUND 2 OTHER AC WITH SIMILAR AMOUNTS OF WATER IN THE SUMP DRAINS. ALL 3 OF THESE AC WERE TIED DOWN OUTSIDE DURING WEATHER ABOVE STATED. INSPECTION OF THE FUEL FILLER FLANGE/CAP ASSY ON ALL 12 AC REVEALED THE SAME LOOSE FUEL CAP CONDITION. ALL AC FUEL CAPS WERE TIGHTENED AS A PRECAUTION. THE O-RING SEALS DID NOT APPEAR TO BE DAMAGED. (K) 1L71 3O NTA47CE 20061107000632006110700063 2006 11 7 2006FA0001055 220061025G855083278 PRESSURE SWITCH CESSNA172 172R 2072401CE ENGINE OIL LEAKING D O OTHER O OTHER NRNOT REPORTED 1 CE01243522618 17280835 AC WAS MAKING AN APPROACH AND HAD OIL SPLASH ON THE WINDSHIELD. PILOT MADE A FULL STOP AND TAXIED BACK TO RAMP. OIL PRESSURE AND TEMPERATURE STAYED IN THE GREEN. UPON INVESTIGATION, FOUND THE CAUSE OF THE OIL LEAK TO BE THE (SENSOR-OIL PRESSURE (HOBBS-SWITCH) PN 83278 TO BE THE SOURCE OF THE LEAK. THE SENSOR HAD FAILED INTERNALLY AND THE OIL WAS COMING FROM AROUND THE PRONGS INSIDE THE CONNECTOR AREA. PROBABLE CAUSE-BAD DESIGN. PREVENT REOCCURRENCES-UNKNOWN. (K) 1H71 3O NT3A12 20070605002132007060500213CE 2007 6 5 2006FA0001056 120061022G5100 PIN CESSNA182 R182 2072734CE LYC O540 O540* 41532EA ACTUATOR BROKEN B O OTHER O OTHER NRNOT REPORTED 1 CE015274S R18201534 LOCKDOWN PINS BROKE AT GROOVE FOR ROLL PINS. THIS ALLOWED THE PINS TO MOVE OUT OF ACTUATOR BEARING END AND JAM THE ACTUATOR. IN THE UNLOCKED POSITION, SEB95-20 ACTUATOR DOWNLOCK PIN. INSPECTION SAYS TO CHECK FOR LOOSE PINS. THESE PINS WERE NOT LOOSE IN THE END BEARING UNTIL THE PART WAS THOROUGHLY CLEANED. THERE ARE INDICATIONS THAT THE PINS WERE MOVING BUT COULD NOT BE MOVED. THE NEW ASSEMBLIES USE A PIN THROUGH THE PINS INSTEAD OF A GROVE CUT IN THE CIRCUMFERENCE OF THE LOCKDOWN PIN. SUGGEST THAT ANY ACTUATORS THAT ARE STILL OUT THERE BE REMOVED AND CLEANED TO DETERMINE THAT THE PINS ARE BROKEN OR LOOSE. (K) 1H71 3O3 ORT3A13 E295 20061205002962006120500296SO 2006 12 5 2006FA0001057 120061025G78301159SCP40211RW ACTUATOR GULSTMG1159 GIV 3980115SO RROYCETAY TAY6118 EU THRUST REVERSER FAILED D A UNSCHED LANDING J WARNING INDICATION NRNOT REPORTED 1 WP01595PE143 143 1373 16871 APPROXIMATELY 20 MINUTES INTO THE FLIGHT, THE CREW NOTIFIED MAINTENANCE THAT THEY HAD A (T/R REV UNLOCK) LIGHT. THE CREW BROUGHT BACK POWER AND THE LIGHT EXTINGUISHED, CREW THEN SELECTED (EMERGENCY STOW) AND RETURNED TO DEPARTURE WITHOUT INCIDENT. AS THE AIRCRAFT ROLLED UP WITH ENGINES RUNNING, MAINTENANCE NOTED THE LT T/R DROOPED APPROX .1250 INCH, BUT STILL NOT ON THE SECONDARY LOCK (S HOOKS). THIS ACTUATOR HAD BEEN INSTALLED IN FEB 2006. A NEW REPLACEMENT ACTUATOR PN: 1159CP402-11, SN 2268 HAS BEEN INSTALLED WITH NO FAULTS NOTED AND THE AC HAS BEEN RETURNED TO SERVICE. (K) 2L72 4F4 FRTA12EA E25NE 20061117001662006111700166CE 2006 11 17 2006FA0001058 120061018G34110800106379 PITOT LINE CESSNA310 T310Q 2074244CE CONT O520 TSIO520* 17040SO CORRODED D K NONE L NO TEST ININSP/MAINT 1 WP1787JV 310Q0206 DURING A ROUTINE PITOT/STATIC TEST, FOUND THAT THE PITOT SYSTEM WAS LEAKING BEYOND LIMITS. THE LEAKAGE WAS DETERMINED TO BE IN THE TUBING FROM THE PITOT TUBE TO THE FORWARD CABIN BULKHEAD FITTING. UPON REMOVING THE TUBE (PN 0800106-379) SEVERE CORROSION WAS FOUND AT THE AFT END, NEAR THE FITTING. THIS PORTION WAS FOUND HALF BURIED IN THE OUTER INSULATION OF A HEAT DUCT ON THE LT OB SIDE, ALLOWING MOISTURE TO BE TRAPPED. THIS AREA IS DIFFICULT TO INSPECT AND DAMAGE TO THE TUBE COULD GO UNDISCOVERED UNTIL A LEAK TEST IS PERFORMED. IT IS RECOMMENDED THAT OPERATORS OF AC HAVE THIS LINE INSPECTED, AND THAT CHAFE AND CORROSION PROTECTION BE APPLIED TO THE TUBE WHERE IT CONTACTS THE INSULATION OF THE HEAT DUCT. 1L72 3O3 O 3A10 E8CE 20061205003092006120500309EA 2006 12 5 2006FA0001059 220061020G852072877 LIFTER PIPER PA32 PA32300 7103212SO LYC O540 IO540K1A5 41532EA ENGINE BROKEN B JUJRO OTHER O OTHER NRNOT REPORTED 1 SO071102N 1800 3240756 L1236848 LIFTER BROKE. (K) 1L71 3O3 O A3SO 1E4 20061205003102006120500310EA 2006 12 5 2006FA0001060 220061020G852072877 LIFTER CESSNA182 182S 2072701CE LYC O540 IO540AB1A5 EA ENGINE BROKEN B JUJRO OTHER O OTHER NRNOT REPORTED 1 SO079581V1138 18280257 L2639348A LIFTER BROKE. (K) 1H71 3O3 ONT3A13 1E4 20061205003112006120500311EA 2006 12 5 2006FA0001061 220061020G8520AEL72877 LIFTER PIPER PA46 PA46350P 7104602SO LYC O540 TIO540AE2A 41532EA ENGINE BROKEN B JUJRO OTHER O OTHER NRNOT REPORTED 1 SO07146DG1400 4636066 L975261A LIFTER BROKE. (K) 1L71 3O3 ORTA25SO E14EA 20061205003122006120500312EA 2006 12 5 2006FA0001062 220061003G85201382712170 CRANKSHAFT CESSNA172 172R 2072401CE LYC IO360 IO360L2A EA ENGINE CORRODED B YYBRO OTHER O OTHER NRNOT REPORTED 1 GL03987WU2216 17280550 L170551A INSIDE DIAMETER WAS FOUND TO BE PITTED AFTER REMOVAL OF THE COATING CALLED URETHABOND 104. THIS COATING WAS APPLIED BY MFG. THE SURFACE APPEARED TO BE VERY ROUGH, ALMOST THREADED. THE CAUSE FOR THE CORROSION IS UNCERTAIN. A SUGGESTION FOR PREVENTION IS NOT POSSIBLE. MY SPECULATION WOULD BE THAT THE COATING IS NOT ADEQUATELY SEALING THE SURFACE FROM MOISTURE. (K) 1H71 3O3 ONT3A12 1E10 20061205003152006120500315CE 2006 12 5 2006FA0001063 120061011G8011PM2401 STARTER CESSNA172 172S 2072439CE ENGINE FAILED D O OTHER O OTHER TXTAXI/GRND HDL 1 NM01686SP 172S8097 BENDIX GEAR FAILS DURING START OPERATION. INSTALLED ON 3/10/04, REMOVED ON 8/16/04. (K) 1H71 3O NT3A12 20061205003162006120500316EA 2006 12 5 2006FA0001064 220061012G853017F19357 ROCKER ROBSINR22 R22BETA 7640110NM LYC O360 O360J2A 41514EA NR 4 CYLINDER CRACKED D O OTHER O OTHER NRNOT REPORTED 1 WP17776SH 5 3552 NR 4 CYLINDER INTAKE ROCKER ARM CRACKED/SPLIT INTO 2 PIECES. CRACK/ SPLIT RUNS CROSS-WAYS NEAR ROCKER BOSS ON VALVE STEM SIDE OF ROCKER ARM. AGGRESSIVE MACHINING OF ROCKER ARM AND OR ROCKER ARM INCORRECTLY CONTACTING KEEPER SPRING ASSEMBLY. (K) 1G71 3O3 O H10WE E286 20070118000302007011800030 2007 1 18 2006FA0001065 420060918G256446FASA631201 LIFE RAFT CABIN PARTIAL INFLATE D WV1RO OTHER O OTHER NRNOT REPORTED 1 SO35 LIFE RAFT PARTIALLY INADVERTENTLY DEPLOYED IN CUSTOMERS AIRCRAFT CABIN AREA (UNDER SEAT CUSHION) WHICH COULD HAVE POSSIBLY CAUSED SEVERE DAMAGE TO THE AIRCRAFT, INJURY TO PERSONS OR LOSS OF AIRCRAFT CONTROL HAD LIFE RAFT COMPLETELY INFLATED IN-FLIGHT. THE LIFE RAFT WAS REMOVED FROM THE AIRCRAFT CABIN BY THE OPERATOR BEFORE IT HAD COMPLETELY INFLATED MINIMIZING THE POSSIBILITY OF SEVERE DAMAGE. (K) 20061115003102006111500310 2006 11 15 2006FA0001066 420060926G256446FASA2303603 LIFE RAFT CABIN PARTIAL INFLATE C WV1RO OTHER O OTHER NRNOT REPORTED 1 SO35 LIFE RAFT PARTIALLY INADVERTENTLY INFLATED IN CUSTOMERS AIRCRAFT CABIN AREA (UNDER SEAT CUSHION) WHICH COULD HAVE POSSIBLY CAUSED SEVERE DAMAGE TO THE AIRCRAFT, INJURY TO PERSONS OR LOSS OF AIRCRAFT CONTROL HAD LIFE RAFT COMPLETELY INFLATED IN-FLIGHT. THE LIFE RAFT WAS REMOVED FROM THE AIRCRAFT CABIN BY THE OPERATOR BEFORE IT HAD COMPLETELY INFLATED MINIMIZING THE POSSIBILITY OF SEVERE DAMAGE. (K) 20061205003172006120500317EA 2006 12 5 2006FA0001067 220060926G8530SI74673 COMPRESSION RING GULSTMG44 G44 3951502SO LYC O480 GO480B1C 41527EA PISTON IMPROPER D AV2RK NONE O OTHER ININSP/MAINT 1 SW15645DH 1329 L29228 SUPERIOR COMPRESSION RINGS PN 74673 WERE INSTALLED DURING OVERHAUL, AFTER 3.0 HRS OF RUNNING A BORE SCOPE INSPECTION REVEALED SOME STRANGE BLACKENING OF THE CYLINDER WALLS. A CYLINDER WAS REMOVED TO INVESTIGATE AND THE TOP (2) COMPRESSION RINGS ONLY SHOWED CONTACT ON THE BOTTOM HALF INDICATING THAT THE BEVEL ON THE FACE OF THE RING WAS FACING THE WRONG WAY FOR A COMPRESSION RING. AFTER COMPARING THIS SUPERIOR RING TO A MFG RING IT APPEARS THE SUPERIOR RING IS DEFECTIVE, NUMBERED WRONG, BUT DOES NOT MATCH THE SHAPE OF THE RING AND INFORMATION OBTAINED FROM MFG TECH SUPPORT. SUBSEQUENTLY ALL CYLINDER HAVE BEEN REMOVE TO REPLACE THESE RINGS. RECOMMEND THAT ALL RINGS FROM MFG BE RECALLED FROM THE SYSTEM FOR SAF1H72 3I3 OO A734 E275 20061115003062006111500306SO 2006 11 15 2006FA0001068 120061103G792120017A OIL COOLER PIPER PA28 PA28R201 7102816SO LYC O360 IO360C1C6 41514EA LEAKING B A UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CLCLIMB 1 GL21287ND2365 3 2844036 L1731751A PILOT REPORTED FLICKERING OIL PRESSURE ANNUCIATOR DURING TAKE-OFF. LANDED AND FOUND OIL LEAKING FROM OIL COOLER AREA. UPON CLOSER EXAMINATION BY A&P DETERMINED COOLER WAS LEAKING IN BETWEEN THE COOLING FINS. COOLER WAS REPLACED RUN UP AND LEAK CHECKED GOOD. OIL LEVEL NEVER EXCEDED MINIMUM QUANTITY. 1L71 3O3 O 2A13 1E10 20061115003302006111500330EA 2006 11 15 2006FA0001069 220061109G8530LW19001 EXHAUST VALVE CESSNA182 182S 2072701CE LYC O540 IO540AB1A5 EA MCAULY3D36C B3D36C431 GL ENGINE CYLINDER STUCK B JRURK NONE O OTHER ININSP/MAINT 1 GL07715HP501 18280921 RL2126148A 060202 STUCK EXHAUST VALVES ON NR 3 CYLINDER FOUND DURING PHASE 2 INSPECTION. 1H71 3O3 ONT3A13 1E4 5 C 20061205003182006120500318CE 2006 12 5 2006FA0001070 120060223G8011646275 BEARING CESSNA210 T210N 2073456CE CONT O520 TSIO520R 17040SO STARTER MOTOR SEIZED D O OTHER O OTHER NRNOT REPORTED 1 SO156622N 21063125 OVERHAULER W/O NR 84062, O/H DATE 10/06/2006. STARTER BEARING SEIZED AFTER INSTALLATION STARTER MOTOR FAILED. (K) 1H71 3O3 O 3A21 E8CE 20061205003192006120500319CE 2006 12 5 2006FA0001071 120061028G57201011200953 WEB BEECH 200 B200 1152922CE PWA PT6 PT6A42 52043NE LT WING CRACKED B B92RK NONE O OTHER ININSP/MAINT 1 CE07828FM BB1069 DURING PHASE 1 THROUGH 4 INSPECTION, AFTER REMOVING MOVING ALL WING INSPECTION PANELS. 4 (EA) CRACKS NOTICED IN WEB FLANGE COMMON TO AND EMITTING FROM RIVETS ON LT IB WING BOX AREA, BL-65.50, (2EA) CRACKS AT WS 65, (1EA) CRACK AT WS 56. (K) 1L72 4T4 T A24CE E4EA 20061117000492006111700049SO 2006 11 17 2006FA0001072 120060904G27106271605 SHAFT PIPER PA32 PA32300 7103212SO LYC O540 TIO540* 41532EA AILERONS FAILED C O OTHER O OTHER NRNOT REPORTED 1 SW154112R 3240431 THE HOLE IN THE SHAFT WAS MISDRILLED WHERE THE TAPER PIN ATTACHES IT TO THE SPROCKET, WHICH IS PART OF THE AILERON CONTROL SYSTEM. THE MISDRILLED HOLE ALLOWED THE PIN TO BREAK FREE OF THE SHAFT. THIS FAILURE CAUSED THE SEPARATION OF THE RT CONTROL WHEEL FROM THE AIRPLANE FLIGHT CONTROL SYSTEM. THIS PROBLEM WAS FOUND WHILE CONDUCTING OTHER MAINTENANCE ON THE AIRCRAFT. THE PART IS AVAILABLE FOR INSPECTION. PHOTOS OF THE PART ARE AVAILABLE VIA E-MAIL. (K) 1L71 3O3 O A3SO E14EA 20061205003202006120500320CE 2006 12 5 2006FA0001073 120061029G322008424008 BRACKET CESSNA182 182A 2072704CE CONT O470 O470* 17026SO NLG FAILED D O OTHER E VIBRATION/BUFFET LDLANDING 1 WP075166D5400 51266 DURING LANDING ROLL OUT THE NOSE GEAR BEGAN TO SHIMMY UNTIL NOSE GEAR FAILURE. AN INSPECTION SHOWN, A FAILURE OF THE NOSE GEAR SHIMMY DAMPER BRACKET ON HOUSING. PART ORIGINAL TO 1958 INSTALLATION. (K) 1H71 3O3 ONT3A13 E273 20061205002372006120500237SW 2006 12 5 2006FA0001074 120061031G3250350501 SERVO SWRNGNSA226 SA226TC 8780404SW GARRTTTPE331TPE3313U 01514WP HARTZLHCB3T HCB3TN5 GL NLG STEERING MALFUNCTIONED G O OTHER O OTHER NRNOT REPORTED 1 SO17247ML TC247 AIRCRAFT PULLS TO THE RT. OPERATOR REMOVED AND REPLACED NOSE STEERING SERVO, FLUSHED OUT LINES AND REPLACED FILTER. OPS CHECK GOOD IAW MFG MM. (K) 2L72 4T4 TRTA8SW E4WE 6 CP15EA 20061205003212006120500321CE 2006 12 5 2006FA0001075 120061011G8011PM2401H STARTER CESSNA172 172S 2072439CE LYC O360 IO360A1A 41514EA ENGINE FAILED D O OTHER O OTHER TXTAXI/GRND HDL 1 NM01686SP177 172S8097 THE BENDIX GEAR CRACKED/SHATTERED DURING START OPERATION. NO DAMAGE TO RING GEAR. PART INSTALLED ON 6/23/2006. PART REMOVED ON 10/11/2006. THIS IS BECOMING A VERY BIG PROBLEM WITH THESE STARTERS. (K) 1H71 3O3 ONT3A12 1E10 20070131002552007013100255 2007 1 31 2006FA0001076 220061030G8520 CONNECTING ROD AMTR RWEXECROTORWAY162F GL ENGINE FAILED G A UNSCHED LANDING O OTHER CLCLIMB 1 SW11162HM 6135 ENGINE FAILED ON CIRCLING CLIMB FROM AIRPORT. ROD CAME THRU ENGINE BLOCK. (INCIDENT ISW1107003) (K) 1G71 3O EXPA1G71 20061205002592006120500259SO 2006 12 5 2006FA0001077 220060928G8530SA10200A1 CYLINDER CESSNA150 150M 2071830CE CONT O200 O200A 17020SO NR 3 CRACKED D K NONE O OTHER ININSP/MAINT 1 NE05714DG1100 15079092 OIL LEAK LEAD TO FINDING CYLINDER BARREL CRACKED, MID SECTION IN COOLING FINS, .7500 WAY AROUND BARREL. (K) 1H71 3O3 O 3A19 E252 20070118000332007011800033SO 2007 1 18 2006FA0001078 120061031G321365489000 STRUT PIPER PA28 PA28161 7102803SO LYC O320 O320D3G 41508EA SNSNCH74D 74DM EA MLG DEPARTED B O OTHER O OTHER NRNOT REPORTED 1 WP095513V 287716181 L802639A WHILE PRACTICING TAKEOFF AND LANDINGS, THE TOWER INFORMED PILOT THERE WAS A PROBLEM WITH LEFT LANDING GEAR. THE INSTRUCTOR ELECTED TO RETURN TO TAKEOFF AIRPORT. UPON LANDING THE BRAKEHOSE SEPARATED, AND THE WHEEL, BRAKE ASSY, STUB AXEL AND OLEO PISTON DEPARTED WHEN LANDING WAS MADE ON BOTTOM OF LT GEAR CYLINDER. PROBABLE CAUSE IS NUMEROUS HARD LANDINGS WITH STUDENTS FLYING. (K) 1L71 3O3 O 2A13 E274 5 NP88614 20061205003222006120500322GL 2006 12 5 2006FA0001079 120061005G2434653344 ALTERNATOR CIRRUSSR SR20 05628AJGL CONT O360 IO360ES SO HARTZLHCJ2Y BHCJ2YF1 GL ENGINE SEPARATED D O OTHER O OTHER CRCRUISE 1 NM01269CD940 1204 357442 EF282B DURING FLIGHT, PILOT NOTICED A LOUD BANGING NOISE FROM UNDER ENGINE COWLING PILOT PROCEEDED TO LAND. AFTER LANDING, MAINTENANCE DEPARTMENT. REMOVED COWLING TO FIND THIS ALTERNATOR SEPARATION/ FAILURE. NO OTHER COMPONENTS WERE DAMAGED. INSPECTION PRIOR TO THIS FAILURE SHOWED NO DEFECT TO THIS COMPONENT. (K) 1L71 3O3 ONTA00009CHE1CE 5 CP37EA 20061212002882006121200288 2006 12 12 2006FA0001080 120061016G2750790231509 CONTROL VALVE T/E FLAP DEFECTIVE B W6NRK NONE F FLT CONT AFFECTED ININSP/MAINT 1 GL25 PART HAD OVERHAULED TAG INSTALLED SEPT 2004. THE PART WAS INSTALLED ON A COMMANDER AND STILL HAD THE SAME PROBLEM OF DROOPING FLAPS. WE SENT THE UNIT BACK AND THEY SAID IT NEEDED REPAIRED AND ADDITIONAL SERVICED PERFORMED. THE UNIT WAS SENT BACK TO US JULY 2005 AND THE INSTALLED ON ANOTHER AIRCRAFT IN JULY 2006 AND THE SAME PROBLEM OCCURRED WE HAD ON THE PREVIOUS AC. THIS UNIT WAS NOT ON THE AIRCRAFT LONG ENOUGH TO DO ANY KIND OF DAMAGE. WE RAN THE FLAP SYSTEM 1 TIME AND STILL SAME PROBLEM. WE SENT THE PART BACK AGAIN AND THEY SAID IT NEEDED OVERHAULED THIS TIME. WE INSTALLED A NEW FLAP VALVE ON THE AIRCRAFT AND THE PROBLEM IS GONE. (K) 20070108001472007010800147SO 2007 1 8 2006FA0001081 120061101G25108994406 SEAT BACK PIPER PA46 PA46350P 7104602SO LYC O540 TIO540* 41532EA COCKPIT CRACKED D O OTHER O OTHER NRNOT REPORTED 1 CE07812MB 4636111 CREW SEAT BACK FRAME CROSS SUPPORT BREAKS AT WELDED JOINT ON EITHER SIDE AND OR BOTH. (K) 1L71 3O3 ORTA25SO E14EA 20070116000122007011600012EA 2007 1 16 2006FA0001082 220061108G722010991004933 TUBE BEECH 90 C90A 1152911CE PWA PT6 PT6A21 52043EA INLET CRACKED D O OTHER O OTHER NRNOT REPORTED 1 CE01200HV LJ1478 THE TUBES ARE CRACKING ALONG THE WELDS, WHICH CONNECT THEM TO THE INLET LIP ASSEMBLY. REQUIRES REMOVAL OF INLET LIP ASSY AND REPAIR OF THE CRACKED WELDS. (K) 1L72 3T4 TRT3A20 E4EA 20070118000562007011800056NM 2007 1 18 2006FA0001083 120061002G323065446924 HOUSING BOEING737 737* NM MLG VALVE CRACKED C IU6RO OTHER O OTHER NRNOT REPORTED 1 NM01 REF (211263/KS2) HOUSING CRACKED IN VALVE BORE. CYCLIC STRESS. REDESIGN HOUSING. (K) 2L72 4F RTA16WE 20061117001382006111700138NM 2006 11 17 2006FA0001084 120061006G291365447822 HOUSING BOEING BOEING737 737* NM VALVE ERODED D IU6RO OTHER O OTHER NRNOT REPORTED 1 NM01 1795 (REF: 211704/QN1) PIN HOLE ERODED IN NR 2 PORT HEEL. MATERIAL DEFECT/ TIME. (K) 2L72 4F RTA16WE 20070109000062007010900006GL 2007 1 9 2006FA0001085 220061103G726023034787AL BEARING ALLSN HUGHES369 369D 4470706WP ALLSN 250C 250C20B 03013GL GEARBOX SPALLED B EOORO OTHER O OTHER NRNOT REPORTED 1 AL03CGPHC CAG35789 180257D CAE830015 VISIBLE LINE FOUND ON 2.5 BEARING ROLLERS MATCHING SPALLING FOUND ON SAG SHAFT (SDR DATED 3/NOV/2006). GEARBOX INSTALLED 6/SEPT/2006. TIME IN SERVICE FOR GEAR BOX, 105.1 HOURS. 2.5 BEARING INSTALLATION TIMES NUT SHOWN ON ENGINE CARDS. 2.5 BEARING IS A PMA PART ALCOR. (K) 1G71 3U3 U H3WE E4CE 20070108001722007010800172WP 2007 1 8 2006FA0001086 120061004G5300369A75058 SUPPORT HUGHES369 369D 4470706WP ALLSN 250C 250C20B 03013GL ANTITORQUE PEDALCORRODED B EOORO OTHER O OTHER NRNOT REPORTED 1 AL03511SB 1090592D DURING ANNUAL INSPECTION PEDAL SUPPORT WAS FOUND WITH CORROSION ON LOWER BOLT PADS BEYOND REPAIRABLE LIMITS. REPLACED SUPPORT BRACKET WITH SERVICEABLE PART. (K) 1G71 3U3 U H3WE E4CE 20070116000542007011600054GL 2007 1 16 2006FA0001087 220061103G7230E23031922C SHAFT ALLSN HUGHES369 369D 4470706WP ALLSN 250C 250C20B 03013GL COMPRESSOR ASSY SPALLED B EOORO OTHER O OTHER NRNOT REPORTED 1 AL03CGPHC CAC362283 180257D CAE830015 FOUND SPALLING ON BEARING RACE AT 2.5 BEARING CONTACT POINT. FOUND VISIBLE LINE ON 2.5 BEARING ROLLERS MATCCHING SPALL LINE ON SAG SHAFT. COMPRESSOR ASSY INSTALLED ON AC 6/SEPT/2006, TIME IN SERVICE SINCE INSTALLATION OF COMPRESSOR ASSY 105.1 HOURS, 220 CYCLES. INSTALLATION TIMES NOT SHOWN ON ENGINE CARDS FOR SAG SHAFT. SAG SHAFT IS A PMA PART-EXTEX. (K) 1G71 3U3 U H3WE E4CE 20070104000632007010400063SW 2007 1 4 2006FA0001088 120061119G62002040408123 ADAPTER BELL 205 205A1 1181414SW LYC T53 T5313B 41549NE MAIN ROTOR DAMAGED B EOORO OTHER O OTHER NRNOT REPORTED 1 AL03CGREU 30011 DURING INSPECTION AND REGREASE OF THE M/R TRANS DRIVE SHAFT, A CHECK OF THE TORQUE OF THE DRIVE SHAFT ADAPTOR BOLT WAS ACCOMPLISHED AND IT WAS DISCOVERED THAT THERE WAS NO TORQUE, THAT THE BREAKER BAR`S WEIGHT BROKE THE BOLT LOOSE, REMOVED THE ADAPTOR AND FOUND WEAR ON THE ADAPTOR FLANGE AND IT WAS BEYOND LIMITS IAW TECH BULLETIN. REPLACED PART. (K) 1G71 4U4 U H1SW E17EA 20061117001332006111700133CE 2006 11 17 2006FA0001089 120061115G5210MS203922C63 HINGE PIN BEECH 35 V35B 1151548CE CABIN DOOR LOOSE D K NONE W INADEQUATE Q C ININSP/MAINT 1 SO2566WC 2540 D10199 CABIN DOOR TOP HINGE PIN KEEPER COTTER PIN FAILED. THE PIN, A CLEVIS BOLT, WAS INSTALLED FROM THE BOTTOM DUE TO STRUCTURAL DESIGN LIMITATIONS. THE FAILURE OF THE COTTER PIN ALLOWED THE CLEVIS PIN THE PARTIALLY FALL OUT OF PLACE ALLOWING THE DOOR TO MOVE. COMPLETE LOSS OF THE PIN MIGHT HAVE ALLOWED THE DOOR TO SEPARATE FROM THE AIRCRAFT IN FLIGHT. POSSIBLE IMPACT WITH THE RT RUDDERVATOR. CLOSER INSPECTION AT ANNUAL AND INSTALLING THE PIN FROM THE TOP WOULD HELP AVOID THE PROBLEM. 1L71 3O 3A15 20061117001342006111700134EA 2006 11 17 2006FA0001090 220061115G74146393 MAGNETO PIPER PA23 PA23250 7102308SO LYC O540 IO540C4B5 41532EA ENGINE FAILED D O OTHER RJ PARTIAL RPM/PWR LOSS WARNING INDICATION TXTAXI/GRND HDL 1 GL1315FG 630 140 277554112 L1313448A PILOT REPORTED THAT HE STARTED LT ENGINE AND THEN ATTEMPTED TO START RT ENGINE ON THE GROUND. RT ENGINE WOULD NOT FIRE. TROUBLESHOT AND TRACED PROBLEM TO LT MAGNETO OF RT ENGINE. REMOVED LT MAGNETO FROM ENGINE. UPON REMOVAL, LOOSE PARTS COULD BE HEARD INSIDE OF MAGNETO. MAGNETO WAS DISASSEMBLED. THE WEDGES HOLDING THE COIL IN PLACE WERE FOUND TO BE DISLODGED AND THE COIL HAD SHIFTED AND TAB WAS NOT MAKING CONTACT WITH DISTRIBUTOR BRUSH. MAGNETO WAS INSPECTED AND ALL OTHER PARTS WERE FOUND TO BE SERVICEABLE. A NEW COIL AND WEDGES WERE INSTALLED AND THE MAGNETO WAS REINSTALLED ON THE ENGINE AND OPERATED SATISFACTORILY. THIS MAGNETO WAS NEW AT ENGINE INSTALLATION 630 HOURS AGO AND HAD BEEN DISASSEMBLED AN1L72 3O3 O 1A10 1E4 20061117001372006111700137CE 2006 11 17 2006FA0001093 120061115G5210MS203922C63 HINGE PIN BEECH 35 V35B 1151548CE CONT O520 IO520* 17032SO CABIN DOOR LOOSE D K NONE W INADEQUATE Q C ININSP/MAINT 1 SO2566WC 2540 D10199 CABIN DOOR TOP HINGE PIN KEEPER COTTER PIN FAILED. THE PIN, A CLEVIS BOLT, WAS INSTALLED FROM THE BOTTOM DUE TO STRUCTURAL DESIGN LIMITATIONS. THE FAILURE OF THE COTTER PIN ALLOWED THE CLEVIS PIN THE PARTIALLY FALL OUT OF PLACE ALLOWING THE DOOR TO MOVE. COMPLETE LOSS OF THE PIN MIGHT HAVE ALLOWED THE DOOR TO SEPARATE FROM THE AIRCRAFT IN FLIGHT. POSSIBLE IMPACT WITH THE RT RUDDERVATOR. CLOSER INSPECTION AT ANNUAL AND INSTALLING THE PIN FROM THE TOP WOULD HELP AVOID THE PROBLEM. 1L71 3O3 O 3A15 E5CE 20061129003762006112900376EA 2006 11 29 2006FA0001094 220061116G7414M3548 ROTOR SLICK PIPER PA28 PA28161 7102803SO LYC O320 O320D3G 41508EA SNSNCH74D 74DM EA MAGNETO SHEARED D O OTHER O OTHER NRNOT REPORTED 1 SW99 549 04081167 RT MAGNETO ROTOR SHEARED DIRECTLY UNDER THE PLASTIC ROTOR GEAR. 1L71 3O3 O 2A13 E274 5 NP88614 20061204001062006120400106EA 2006 12 4 2006FA0001095 220061116G7314M3548 ROTOR SLICK PIPER PA28 PA28161 7102803SO LYC O320 O320D3G 41508EA SNSNCH74D 74DM EA MAGNETO SHEARED D O OTHER O OTHER NRNOT REPORTED 1 SW99 549 04081167 RT MAGNETO ROTOR SHEARED DIRECTLY UNDER THE PLASTIC ROTOR GEAR. 1L71 3O3 O 2A13 E274 5 NP88614 20061205002512006120500251SO 2006 12 5 2006FA0001096 120061106G7120102460036 MOUNT PIPER PA46 PA46500TP 7104622SO PWA PT6 PT6* 52043EA ENGINE CRACKED D O OTHER O OTHER NRNOT REPORTED 1 NM075215U757 4697068 CUSTOMER REPORTED THAT HYDRAULIC PUMP KENP CYCLING. INSPECTED LANDING GEAR ACTUATORS FOR LEAKS. FOUND NLG ACTUATOR ATTACH CRACKED ON ENGINE MOUNT. INSTALLING NEW ENGINE MOUNT IAW SB 1154A WILL SOLVE MALFUNCTION. (K) 1L71 3O3 TRTA25SO E2NE 20061205002462006120500246CE 2006 12 5 2006FA0001097 120060815G32502609 SPRING BBAVIA11 11AC 0191102CE CONT A65 A65* 17003SO TAIL STEERING DAMAGED G O OTHER O OTHER NRNOT REPORTED 1 GL153799E 11ACS18 TAIL WHEEL SPRING STRETCHED AT HOOK CPVSWG PILOT TO LOOSE RUDDER CONTROL PAD DEPART TAXIWAY. (K) 1H71 3O3 O A761 E205 20061205002492006120500249CE 2006 12 5 2006FA0001098 120061107G2820LW120981116 PRIMER LINE CESSNA172 172N 2072434CE LYC O320 O320* 41508EA NR 3 CYLINDER LEAKING D O OTHER K FLUID LOSS TXTAXI/GRND HDL 1 EA232059E 17271137 NOTED FUEL SPRAYING OUT WHEN TRYING TO PRIME ENGINE FOR START. FOUND LINE CRACKING AT WELDED TIP AREA. ON PRIMER LINE, WHERE IT ATTACHES TO CYLINDER FITTING. THIS IS A BAD TYPE END ON LINE. SUGGEST MORE SECURITY OF PRIMER LINES AT MORE PLACES, TO MINIMIZE VIBRATIONS. (K) 1H71 3O3 ONT3A12 E274 20061205002392006120500239CE 2006 12 5 2006FA0001099 120061107G2497 WIRE CESSNA172 172N 2072434CE LYC O320 O320* 41508EA ALTERNATOR BROKEN D O OTHER O OTHER NRNOT REPORTED 1 EA232059E 17271137 ALTERNATOR FAILED AND MAIN POWER BUS FEED WIRE BROKEN FROM ALTERNATOR. TERMINAL ENDS, PROBABLY DUE TO VERY TIGHT AREA AND VIBRATION. PREVENTION MIGHT BE TO ENLARGE AREA WHERE WIRES PASS THRU BAFFLING TO LIGHTEN VIBRATION AND STRESS ON WIRES BEING BENT TO FIT IN THIS AREA. (K) 1H71 3O3 ONT3A12 E274 20070111001432007011100143CE 2007 1 11 2006FA0001100 120061025G2810128920185609 FUEL TANK BEECH MU300 400A 1155402CE AUX DEBONDED B E81RO OTHER O OTHER NRNOT REPORTED 1 GL0345RK 5423 RK43 INVESTIGATED REPORTS OF IN-FLIGHT POPPING NOISES FROM UNDER FLOOR AREA ADJACENT TO CABIN DOOR. FOUND FORWARD LT AUXILLARY TANK STRUCTURE UNDERSIDE HONEYCOMB PANELS DISBONDED FROM TANK STRUCTURE SHEETMETAL. NO CORROSION NOTED, HONEYCOMB MATERIAL APPEARS TO HAVE SEPARATED FROM SHEETMETAL AT ADHESIVE BOND LINE. SLIGHT DEFORMATION OF CURVED UNDERSIDE OF FUEL TANK STRUCTURE NOTED. INFORMATION FORWARDED TO MFG FOR FOLLOW-UP INVESTIGATION. POSSIBLE CAUSE IS VACUUM IN FUEL TANK DUE TO VENTING PROBLEM CAUSING TANK DEFORMATION AND/OR HONEYCOMB ADHESIVE FAILURE. (K) 2H72 4F RTA16SW 20070112000012007011200001NE 2007 1 12 2006FA0001101 220061108G73210164248850 FUEL CONTROL SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1D1 NE ENGINE MALFUNCTIONED D O OTHER O OTHER NRNOT REPORTED 1 SO15680CH2352 3540 9798 (4TH FLIGHT OF THE NIGHT) AFTER START UP, ALL SYSTEMS NORMAL, UPON LIFT OFF THE TURBINE AND ROTOR RPM SIMULTANEOUSLY DECREASED. PILOT REDUCED PITCH AND LANDED ON PAD WITHOUT INCIDENT RPM RETURNED TO 100 PERCENT. PILOT AND COPILOT CROSS CHECKED INSTRUMENTS AND CONTROLS POSITIONS, FOUND NORMAL. A SECOND ATTEMPT WAS MADE WITH THE SAME RESULTS. BOTH NEEDLES STAYED TOGETHER DURING EACH EVENT. THE TURBINE AND ROTOR SPEED RETURNED TOT HE NORMAL RANGE UPON THE COLLECTIVE BEING RETURNED TO THE LOCKED POSITION. AIRCRAFT WAS REMOVED FROM SERVICE. MAINTENANCE PERFORMED VISUAL INSPECTIONS AND GROUND/FLIGHT OPERATIONAL CHECKS AND FOUND NO DEFECTS COULD NOT DUPLICATE. MFC/GOV RETURNED TO MFG FOR EVALUATION. (K) 1G71 3U3 U H9EU E19EU 20070109000622007010900062NM 2007 1 9 2006FA0001102 120060904G575469738243 BOLT BOEING737 737322 1384676NM CFMINTCFM56 CFM563C1 13802EU SLAT TRACK LOOSE C K NONE O OTHER ININSP/MAINT 1 EA35354UA 24360 (REF NR: ATC0712) DURING AN A-CHECK INSPECTION OF RT WING LEADING EDGES. THE OB TRACK ATTACHMENT BOLT ON THE NR 6 SLAT WAS FOUND TO BE LOOSE AND ALSO THE SPLIT PIN WAS MISSING. A NON ROUTINE CARD, WO 3956/06 HAS BEEN RAISED TO FIT THE SPLIT PIN AND RECTIFY THE DEFECT. A CONFIDENCE CHECK HAS BEEN CARRIED OUT ACROSS ALL THE LEADING EDGE ATTACHMENTS FOR THE FLAP TRACKS. IN ADDITION ALL FLYING CONTROLS AND TRAILING EDGE FLAPS HAVE BEEN INSPECTED FOR CORRECT LOCKING AND FITMENT. NO OTHER LOCKING OR ASSY DEFECTS WERE FOUND. (K) 2L72 4F4 FRTA16WE E21EU 20070108000042007010800004 2007 1 8 2006FA0001104 120061016G324250030967 BRAKE ASSY LANDING GEAR MISREPAIRED C BIERK NONE O OTHER ININSP/MAINT 1 EA21 SPACER TUBES (PN 5012942) WERE MISSING FROM ASSEMBLY. INCORRECT RETURN PINS WERE INSTALLED. SHOULD BE PN 5001421, INSTALLED WERE PN 9535044. SWAGE ADJUSTER ASSEMBLIES WERE INCORRECTLY SET FOR THIS SERIES OF BRAKE. THE SWAGES WERE SET AT A DEPTH OF 0.18 INCH BELOW FLUSH, THEY SHOULD HAVE BEEN SET FLUSH WITH THE TOP OF THE ADJUSTER TUBE. (K) 20070108000072007010800007 2007 1 8 2006FA0001105 120061016G324250030967 BRAKE ASSY LANDING GEAR MISREPAIRED B BIERK NONE O OTHER ININSP/MAINT 1 EA21 SPACER TUBES (PN 5012942) WERE MISSING FROM ASSEMBLY. INCORRECT RETURN PINS WERE INSTALLED. SHOULD BE PN 5001421, INSTALLED WERE PN 9535044. SWAGE ADJUSTER ASSEMLIES WERE INCORRECTLY SET FOR THIS SERIES OF BRAKE. THE SWAGES WERE SET AT A DEPTH OF 0.18 INCH BELOW FLUSH, THEY SHOULD HAVE BEEN SET FLUSH WITH THE TOP OF THE ADJUSTER TUBE. (K) 20070108000022007010800002 2007 1 8 2006FA0001106 120061016G324250030967 BRAKE ASSY LANDING GEAR MISREPAIRED B BIERK NONE O OTHER ININSP/MAINT 1 EA21 SPACER TUBES (PN 5012942) WERE MISSING FROM ASSEMBLY. INCORRECT RETURN PINS WERE INSTALLED. SHOULD BE PN 5001421, INSTALLED WERE PN 9535044. SWAGE ADJUSTER ASSEMBLIES WERE INCORRECTLY SET FOR THIS SERIES OF BRAKE. THE SWAGES WERE SET AT A DEPTH OF 0.18 INCH BELOW FLUSH, THEY SHOULD HAVE BEEN SET FLUSH WITH THE TOP OF THE ADJUSTER TUBE. (K) 20070108000032007010800003 2007 1 8 2006FA0001107 120061016G324250030964 BRAKE ASSY LANDING GEAR MISREPAIRED B BIERK NONE O OTHER ININSP/MAINT 1 EA21 UPON CONDUCTING REPAIR TO REPLACE THE MISSING RETURN SPRING ASSEMBLY. FOUND THAT THE SPACER TUBES (PN 5012941) WERE MISSING FROM THE REMAINING 3 RETURN SPRING ASSEMBLIES. (K) 20070108000012007010800001 2007 1 8 2006FA0001109 120061016G324250030967 BRAKE ASSY LANDING GEAR MISREPAIRED B BIERK NONE O OTHER ININSP/MAINT 1 EA21 SPACER TUBES (PN 5012942) WERE MISSING FROM ASSEMBLY. INCORRECT PRESSURE PLATE INSTALLED ON BRAKE ASSY. SHOULD PN 5006890, INSTALLED WAS PN 5005117. PN 5006890 MEASURES .240 INCH THICK, PN 5005117 MEASURES .210 INCH THICK. INCORRECT WEAR PAD WAS INSTALLED ON PRESSURE PLATE. SHOULD BE PN 5007328, INSTALLED WAS 5005119. YOU CAN TELL THE DIFFERENCE BECAUSE PN 5007328 DOES NOT HAVE A MILLED OUT AREA FOR STRUT CLEARANCE. INCORRECT STATIONARY DISK INSTALLED ON BRAKE ASSY. SHOULD BE PN 5006892, INSTALLED WAS PN 9544028. PN 5006892 MEASURES .240 INCH THICK, PN 9544028 MEASURES .210 INCH THICK. INCORRECT INSULATORS WERE INSTALLED IN PISTONS. SHOULD BE PN 50068951. (K) 20070116000702007011600070WP 2007 1 16 2006FA0001110 220060907G725030607881 BLADE RAYTHNDH125 HAWKER800XP 7150012CE GARRTTTFE731TFE7315BR WP LPT3 DAMAGED B O OTHER O OTHER NRNOT REPORTED 1 WP07800WW 258661 107869 THE INFLIGHT SHUTDOWN OCCURED ON SEPT 7, 2006, AFTER LEVELING OFF AT 30,000 FT THE CREW REPORTED A LOUD BANG FROM THE NR 2 ENGINE. THE CREW SECURED THE ENGINE, DIVERTED AND LANDED WITHOUT INCIDENT. VISUAL INSPECTION OF THE AC REVEALED DISPLACED MATERIAL ON THE AIRCRAFT NACELLE, DUCTING. ENGINE EXHAUST DUCT AND TURBINE SECTION IN THE FORM OF A UNCONTAINED MALFUNCTION. THE ENGINE WAS RETURNED TO MFG FOR DISASSEMBLY AND INSPECTION. DISASSEMBLY FINDINGS REVEALED MATERIAL LOSS ON THE LPT3 WHEEL BLADES IN THE FORM OF MID SPAN BLADE FRACTURES. (K) 2L72 4F4 FRTA3EU E6WE 20070108002832007010800283CE 2007 1 8 2006FA0001111 120061121G7810227450 CLAMP CESSNA421 421C 2076016CE CONT O520 GTSIO520N 17032SO TAIL PIPE CRACKED C O OTHER O OTHER NRNOT REPORTED 1 CE01 1371 1249 PN 2274-50 (ALSO PN NH1000897-50) CLAMP HOLDING TAILPIPE TO THE TURBO CRACKED LENGTHWISE ALONG THE CIRCUMFERENCE OF THE CLAMP. TOTAL LENGTH OF THE CRACK IS 3 INCHES. 1L72 3O3 O A7CE E7CE 20061129001982006112900198SO 2006 11 29 2006FA0001112 120061126G32137873803 AXLE PIPER PA28 PA28161 7102803SO LYC O320 O320D3G 41508EA SNSNCH74D 74DMS EA LANDING GEAR CRACKED D K NONE O OTHER ININSP/MAINT 1 WP092525Y14786 288516075 DURING A SCHEDULED 100 HOURS INSPECTION OF THE LANDING GEAR, THE MECHANIC FOUND A CRACK ON RT MAIN LANDING GEAR UPPER PART. IT IS SUSPECTED THE FATIGUE OR STRESS CORROSION CRACKING COULD BE THE CAUSE. ANOTHER REASON WHY MOST OF RT MAIN LANDING GEAR WERE FOUND CRACKED IS PROBABLY THE DIFFERENCE OF STRUCTURAL STRENGTH BETWEEN RT AND LT WING. RT WING IS SLIGHTLY STRONGER THAN LT WING BECAUSE IT HAS A (WING WALK PANEL) WHICH DOES NOT ALLOW TRANSFER ALL THE LOADS OCCURRING ON LANDINGS TO THE MAJOR MASS (ENGINE), THIS THEORY IS JUST A STRUCTURAL ANALYSIS BASE ON EXPERIENCE BUT IT NEED BE TESTED AND PROVED. 1L71 3O3 O 2A13 E274 5 NP88614 20070116000772007011600077WP 2007 1 16 2006FA0001118 220061116G7200 ENGINE GARRTTATF3 ATF36 29002WP FIRE D O OTHER A FLAME/FIRE NRNOT REPORTED 1 WP07 P21210C ENGINE FIRE DURING MAINTENANCE GROUND RUN ON 10/2/2006, PERFORMED TO DETERMINE THE CAUSE OF FLUCTUATING OIL PRESSURE. PROBABLE CAUSE OF FIRE FOUND TO BE MISSING ROLL PIN FROM ATOMIZER, FUEL, INTEGRAL FLOW DIVIDER. MISSING PIN PERMITTED ATOMIZER SHROUD TO MOVE, DEFLECTING FUEL FLOW AWAY FROM COMBUSTION CHAMBER UPSTREAM IN THE ATOMIZER. HOT GASSES FROM COMBUSTION CHAMBER WERE PERMITTED TO FLOW INTO THE CAVITY BETWEEN ATOMIZER AND ATOMIZER SHROUD CAUSING FUEL TO IGNITE IN THE ATOMIZER. FIRE BURNED THROUGH FUEL ATOMIZER PILOT DIAMETER AND THROUGH THE COMBUSTOR CASE. MISSING ROLL PIN LOCATION IN THE ENGINE ASSY IS FULLY CAPTURED BY FUEL ATOMIZER SLEEVE PN 3002830-1. NO EVIDENCE OF THE MISSING WAS FOUND DURING DI 4 F E7WE 20061204000012006120400001 2006 12 4 2006FA0001119 220061020G74146324 MAGNETO ENGINE FAILED B PX2RO OTHER O OTHER NRNOT REPORTED 1 CE07 MAGNETO IS DEAD. (K) 20061212003152006121200315 2006 12 12 2006FA0001120 120061110G8011PM2401 STARTER ENGINE FAILED B PX2RO OTHER O OTHER NRNOT REPORTED 1 CE07 151 STARTER SPINS, BENDIX DOES NOT ENGAGE RING GEAR. (K) 20061212003182006121200318 2006 12 12 2006FA0001121 120061110G8011ES6462382 STARTER ENGINE MALFUNCTIONED B PX2RO OTHER O OTHER NRNOT REPORTED 1 CE07 STARTER WILL NOT DISENGAGE. (K) 20061212003162006121200316 2006 12 12 2006FA0001122 220061114G8530EC636122ST CYLINDER ENGINE MISMANUFACTURED B PX2RK NONE WK INADEQUATE Q C FLUID LOSS ININSP/MAINT 1 CE07 INSTALLED CYLINDER ASSEMBLE ON NEWLY OVERHAULED ENGINE. DISCOVERED OIL LEAKING AROUND CYLINDER BASE DURING TEST CELL RUN. REMOVED CYLINDER AND DETERMINED THAT THE CYLINDER BASE IS NOT PROPERLY MACHINED. THERE IS NO RADIUS AT THE AREA WHERE THE O-RING SEAL IS TO SEAT. THIS DOES NOT ALLOW THE O-RING TO PROPERLY SEAL AGAINST THE CRANKCASE. USED RADIUS GAUGES AND OTHER CYLINDERS TO COMPARE AND MAKE THE DETERMINATION THAT THERE WAS A PROBLEM WITH THE CYLINDER. (K) 20061212003142006121200314 2006 12 12 2006FA0001123 220061114G8530EC636122ST CYLINDER ENGINE MISMANUFACTURED B PX2RK NONE W INADEQUATE Q C ININSP/MAINT 1 CE07 INSTALLED CYLINDER ASSEMBLY ON NEWLY OVERHAULED ENGINE. DISCOVERED OIL LEAKING AROUND CYLINDER BASE DURING TEST CELL RUN. REMOVED CYLINDER AND DETERMINED THAT THE CYLINDER BASE IS NOT PROPERLY MACHINED. THERE IS NO RADIUS AT THE AREA WHERE THE O-RING SEAL IS TO SEAT. THIS DOES NOT ALLOW THE O-RING TO PROPERLY SEAL AGAINST THE CRANKCASE. USED RADIUS GAUGES AND OTHER CYLINDERS TO COMPARE AND MAKE THE DETERMINATION THAT THERE WAS A PROBLEM WITH THE CYLINDER. (K) 20061212003172006121200317 2006 12 12 2006FA0001124 220061114G8530EC636122ST CYLINDER ENGINE MISMANUFACTURED B PX2RK NONE WK INADEQUATE Q C FLUID LOSS ININSP/MAINT 1 CE07 INSTALLED CYLINDER ASSEMBLY ON NEWLY OVERHAULED ENGINE. DISCOVERED OIL LEAKING AROUND CYLINDER BASE DURING TEST CELL RUN. REMOVED CYLINDER AND DETERMINED THAT THE CYLINDER BASE IS NOT PROPERLY MACHINED. THERE IS NO RADIUS AT THE AREA WHERE THE O-RING SEAL IS TO SEAT. THIS DOES NOT ALLOW THE O-RING TO PROPERLY SEAL AGAINST THE CRANKCASE. USED RADIUS GAUGES AND OTHER CYLINDERS TO COMPARE AND MAKE THE DETERMINATION THAT THERE WAS A PROBLEM WITH THE CYLINDER. (K) 20070108001412007010800141NM 2007 1 8 2006FA0001125 120061101G2100 CONTROL UNIT PIPER PA60 PA60602P 7106015NM AUTOPILOT MALFUNCTIONED C O OTHER O OTHER NRNOT REPORTED 1 EA0364715 608365003 AC WAS ACQUIRED IN AN OVERHAULED CONDITION FROM AUTO PILOTS CENTRAL. THIS UNIT WAS AN EXCHANGE UNIT WITH AN OVERHAUL DATE OF APPROX, JUNE 2004. THE KI-256 WAS INSTALLED AND MARRIED TO THE EXISTING FACTORY INSTALLED AUTOPILOT SYS IAW INSTALLATION/ SYS MM. AC WAS RETURNED TO SERVICE AFTER A SUCCESSFUL FLIGHT CHECK. ALL AUTOPILOT/ FLIGHT DIRECTOR MODES WERE CHECKED. SINCE THEN THIS FD/HORIZON HAS BEEN REMOVED AND RETURNED TO OVERHAULER NO LESS THAT 3 TIMES. HORIZON HAS BEEN RESPONSIBLE FOR AN ABRUPT AND ERRATIC PURPOSE. THIS UNIT HAS ALWAYS FAILED IN AUTOPILOT PITCH MODE. EACH TIME OVERHAULER FINDS A NEW PROBLEM IN PITCH CIRCUITS. THESE PROBLEMS ARE RELATED TO THE AUTOPILOT IN THE PITCH AXIS, BUT EACH TIM1M72 3O RTA17WE 20061129002162006112900216NE 2006 11 29 2006FA0001126 220061128G7314378200 PUMP PWA JT8 JT8D15A 52051NE FUEL SYSTEM DAMAGED C K NONE O OTHER ININSP/MAINT 1 SW99 5360 UNIT RECEIVED ON 13 NOV 2006. UNIT PROCESSED ON A REPAIR WORKSHOP IAW CUSTOMER REQUIREMENTS. PUMP FAILED AS RECEIVED BENCH TEST FOR LOW FUEL FLOWS. PUMP DISASSEMBLED IAW CMM REF 73-11-1 TO INVESTIGATE INCOMING TEST FINDINGS. DISASSEMBLY OF FUEL PUMP REVEALED EXTENSIVE DAMAGE TO IMPELLER ASSY. PN 216916. DAMAGE WAS CAUSED AS A RESULT OF QTY 2 NUTS ENTERING FUEL PUMP FROM AN UNKNOWN EXTERIOR SOURCE. 4 F E2EA 20061129002742006112900274CE 2006 11 29 2006FA0001127 120061127G53446511695204 HINGE CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE UNKNOWN CORRODED B K NONE O OTHER ININSP/MAINT 1 SW191200N 0494 AT INSPECTION THE HINGE WAS FOUND CORRODED AND THE PINS WORN PAST LIMITS. A FACTORY NEW HINGE ASSY WAS ORDERED AND INSTALLED. UPON COMPLETION OF THE WORK THE AIRCRAFT WAS PRESSURIZED AND THE HINGE ASSY WAS FOUND TO BE LEAKING. UPON CLOSER INSPECTION THE SKIN THAT ATTACHES TO THE HINGE WAS NOT SEALED. MFG WAS CONTACTED WITH THE REQUEST TO PAY FOR THE SEALANT AND MAGNESIUM RIVETS. WE WERE INFORMED THAT MFG WILL NOT PAY FOR THESE PARTS UNLESS WE RETURNED THE HINGE ASSY. DUE TO THE AMOUNT OF TIME TO INSTALL AND FIT THIS HINGE WE DECLINED. MFG NEEDS TO INSPECT MORE CLOSELY THERE PARTS OR BE ABLE TO WORK BETTER WITH THEIR CUSTOMERS. 1L72 4F4 F A22CE E1NE 20070118000192007011800019CE 2007 1 18 2006FA0001128 120061108G302010991004933 TUBE BEECH 90 C90 1152913CE DUCT CRACKED D O OTHER O OTHER NRNOT REPORTED 1 CE0139FB LJ1165 THE LIP-ASSY IS CRACKED AROUND THE WELDS FOR THE INLET AND OUTLET TUBES. REQUIRES REMOVAL OF INLET LIP ASSY AND REPAIR OF CRACKED WELDS. (K) 1L72 3T 3A20 20070116000692007011600069EA 2007 1 16 2006FA0001129 220061114G8530MS139973 KEEPER PIPER PA31 PA31350 7103110SO LYC O540 LTIO540J2BD 41533EA EXHAUST VALVE BROKEN C O OTHER O OTHER NRNOT REPORTED 1 GL13599871550 317552081 L170168A FOUND VALVE KEEPER BROKEN ON ROUTINE VALVE INSPECTION IAW SB 388C. (K) 1L72 3O3 O A20SO E14EA 20070118000772007011800077EA 2007 1 18 2006FA0001130 220061114G853072050 KEEPER PIPER PA31 PA31350 7103110SO LYC O540 LTIO540J2BD 41533EA INTAKE VALVE BROKEN C O OTHER O OTHER NRNOT REPORTED 1 GL13599871550 317552081 L170168A FOUND NR 6 CYLINDER VALVE KEEPER BROKEN ON ROUTINE VALVE INSPECTION IAW SB 388C. (K) 1L72 3O3 O A20SO E14EA 20070116000782007011600078CE 2007 1 16 2006FA0001131 120061030G2720002524040 RUDDER PEDAL BEECH 36 A36 1151604CE RUDDER LOOSE B AKGRO OTHER O OTHER NRNOT REPORTED 1 CE05304E 1015 E3433 UPON INVESTIGATING LOOSE RUDDER PEDALS, THE ASSEMBLY WAS DISASSEMBLED AND IT WAS NOTED THAT THE SHAFT HAD BEEN DOUBLE DRILLED WITH THE HOLES OVERLAPING. THE AIRCRAFT WAS CERTIFICATED JANUARY 2002; THE AIRCRAFT NOW HAS 1015.4 HOURS, TIME IN SERVICE. (K) 1L71 3O 3A15 20070104000222007010400022WP 2007 1 4 2006FA0001132 220061026G7200TPE3316 ENGINE BEECH 100 B100 1152919CE GARRTTTPE331TPE3316 01514WP HARTZLHCB4T HCB4TN5 GL RIGHT FAILED D GSTRO OTHER T ENGINE CASE PENETRATION ININSP/MAINT 1 SW1393WT 4839 BE80 P27168 CDA3823 DURING GROUND RUN FRO A POSSIBLE GENERATOR PROBLEM. WITH THE ENGINE AT FLIGHT IDLE AND SPEED LEVERS FORWARDTHE RT ENGINE HAD A UNCONTAINED ENGINE FAILURE. 2 PIECES OF THE ENGINE PENETRATED THE RT FUSELAGE SKIN ADJACENT TO THE CO PILOT POSITION. (K) 1L72 4T4 T A14CE E4WE 6 CP40EA 20070118000752007011800075CE 2007 1 18 2006FA0001133 120061114G3230508100398 DRAG BRACE BEECH 90 C90 1152913CE PWA PT6 PT6* 52043EA MLG MISMANUFACTURED B O OTHER W INADEQUATE Q C NRNOT REPORTED 1 SO14690GT268 LJ1727 UPPER DRAG BRACE PN 50-8100398 RUBBED AGAINST THE LOWER DRAG BRACE PN 508100404 AT THE KNUCKLE. THIS REMOVED ABOUT .0625 OF AN INCH OF METAL ABOUT .0625 OF AN INCH LONG ON THE TOP SIDE OF BOTH ENDS OF THE KNUCKLE. THE CAUSE IS IMPROPER MACHINING OF THE PART AT MANUFACTURE. PARTS AFFECTED MUST BE REPLACED. (K) 1L72 3T3 T 3A20 E2NE 20070116000522007011600052EA 2007 1 16 2006FA0001134 220061120G7322 FLOAT FACET AMRGENAA5 AA5B 3960105SO LYC O360 O360* 41514EA CARBURETOR DAMAGED B H5GRO OTHER O OTHER NRNOT REPORTED 1 EA0745343400 75115812 AA5B1265 ENGINE IDLE AND LOW POWER PERFORMANCE WAS ERRATIC. UPON ENGINE SHUTDOWN FUEL WAS NOTED DRIPPING FROM CARB/INDUCTION AIRBOX. CARB WAS DISASSEMBLED AND INSPECTED. FOUND PLASTIC TO HAVE PARTIALLY BECOME UNBONDED FROM LOWER SECTION ALLOWING FUEL TO BEGIN LEAKING INTO ASSEMBLY. AS THE FLOAT LOST ITS BOUYANCY IT COULD NO LONGER RESTRICT FUEL SOURCE. POOR RUNNING ENGINE AND A FIRE HAZZARD WERE THE RESULTS. RECOMMEND THE MFG PROCESS (BONDING) OF THE FLOAT BE IMPROVED. IN THE MEANTIME, ALL FLOATS MFG IN THE SAME BATCH SHOULD BE REMOVED FROM SERVICE. (K) 1L71 3O3 O A16EA E286 20070125003012007012500301NE 2007 1 25 2006FA0001135 120061006G6320SB21511 BEARING SKRSKYS64 S64E 8142604NE PWA JFTD12JFTD12A4A 52047NE M/R GEARBOX CRACKED C JYDRO OTHER O OTHER NRNOT REPORTED 1 NM09247AC1085 A6011 60452 (REF NR:MDR06-090) MAIN GEARBOX PN 6435-20400065, SN A6-011 WAS REMOVED DUE TO FINDINGS OF FERROUS METAL IN THE OIL SCREEN AND FILTER. UPON DISASSEMBLY AND TEAR DOWN, THE SOURCE OF THE FERROUS METAL WAS DISCOVERED TO BE COMING FROM GHE SECOND STAGE INPUT ALIGNMENT BEARING PN SB 2151-1, SN EAC18170. THE SB2151-1 BEARING CRACKED THROUGH THE ENTIRE INNER RACE AND CAUSED SUBSEQUENT CONTAMINATION OF THE MAIN GEARBOX, AND DAMAGE TO THE SECOND STAGE PINION PN 6435-20457-104, SN 333 ALIGNMENT BEARING JOURNAL. THE CRACKED INNER RACE WAS SENT TO THE MFG. PROBABLE CAUSE: UNKNOWN. (K) 2G72 4U4 U H4EA E15EA 20070118000762007011800076NE 2007 1 18 2006FA0001136 120061006G6520SB21541 BEARING SKRSKYS64 S64F 8142610NE PWA JFTD12JFTD12A4A 52047NE GEARBOX CRACKED B JYDRO OTHER O OTHER NRNOT REPORTED 1 NM09229AC958 EAC19192 64018 (REF NR MDR06-089) THE IGB CHIP DETECTOR INDICATED A CHIP LIGHT. IGB WAS REMOVED AND THE INNER RACE WAS FOUND TO BE CRACKED THROUGH AND SPALLED. PROBABLE CAUSE: UNKNOWN. (K) 2G72 4U4 U H6EA E15EA 20061212003992006121200399NE 2006 12 12 2006FA0001137 220061106G7250597602 TURBINE BLADES SKRSKYS64 S64E 8142604NE PWA JFTD12JFTD12A4A 52047NE NR 2 ENGINE FRACTURED B JYDRO OTHER E VIBRATION/BUFFET NRNOT REPORTED 1 NM09CFCRN2946 64061 (REF NR: MDR06-092) VIBRATION FELT BY CREW, UPON LANDING, MAINTENANCE PERSONNEL FOUND METAL PARTICLES IN NR 2 ENGINE EXHAUST. UPON CLOSER EXAMINATION, A 2ND STAGE TURBINE BLADE WAS FOUND TO BE FRACTURED APPROXIMATELY 1 INCH FROM THE ROOT. THE FRACTURED PIECE BROKE OFF AND CAUSED SOME ADDITIONAL DAMAGE TO THE 2ND STAGE TURBINE BLADES AND EXTENSIVE DAMAGE TO THE FREE TURBINE AS IT DEPARTED. (K) 2G72 4U4 U H4EA E15EA 20061212004002006121200400NM 2006 12 12 2006FA0001138 120061031G275065446321 HOUSING BOEING737 737* NM T/E FLAP CRACKED B IU6RO OTHER O OTHER NRNOT REPORTED 1 NM01 53778 (REF NR: 212286/ FXS) HOUSING CRACKED INSIDE THE (P) PORT. CYCLIC STRESS. (K) 2L72 4F RTA16WE 20061212002682006121200268EU 2006 12 12 2006FA0001139 120061101G2497 WIRE ISRAEL1124 1124A 4500103EU GARRTTTFE731TFE731* 01518WP ENGINE CHAFED B YLMRO OTHER O OTHER NRNOT REPORTED 1 WP23794TK 373 AIRCRAFT ARRIVED WITH INOPERATIVE STRATER-GENERATOR. TROUBLESHOOTING REVEALED INOPERATIVE GENERATOR, FAILED GENERATOR CONTROL UNIT, AND FAILED CONTROL RELAY. FURTHER TROUBLESHOOTING FOUND (A) AND (D) LEADS TO STARTER-GENERATOR AT ENGINE WIRING WAS BRITTLE AND HAD BARE SPOT CHAFFED TO ENGINE INLET MOUNTING STRUT. THIS ISSUE SHOULD BE CONSIDERED FOR ALL GENERAL AVIATION AIRCRAFT, NOT JUST THIS MFG. WE HAVE NOTED CONDITION ON SEVERAL AIRCRAFT. THIS IS THE FIRST INCIDENT, HOWEVER, THAT HAD CHAFFING AND A CIRCUIT SHORT. RECOMMEND INSPECTION AT NEXT ACCESS FOR ALL GENERAL AVIATION TURBOJET AIRCRAFT AS THIS WIRING IS LOCATED IN EXTREME ENVIRONMENTAL CONDITIONS, WITHIN THE ENGINE COWLING. (K) 2M72 4F4 F A2SW E6WE 20070118000942007011800094CE 2007 1 18 2006FA0001140 120061107G261224412886 FIRE LOOP BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE HARTZLHCE4A HCE4A3I NE RT ENGINE MALFUNCTIONED D O OTHER O OTHER NRNOT REPORTED 1 GL13534M UE333 PCEPS0246 HJ1616 ON 10/4/2006, AFTER DEPARTING, APPROXIMATELY 30 MINUTES INTO THE FIRST LEG OF THE DAYS TRIP, THE PILOT REPORTED GETTING A RT ENGINE FIRE INDICATION. FOLLOWING PROCEDURE, THE PILOT PULLED THE T-HANDLE AND BLEW THE FIRE BOTTLE, SHUTTING DOWN THE ENGINE. THE PILOT DIVERTED TO AIRPORT AND LANDED SAFELY. THE PILOT STATED THAT HE HAD NOT NOTICED ANY UNUSUAL READINGS FROM ANY OF THE GAUGES. A MAINTENANCE CREW WAS SENT TO INVESTIGATE AND FOUND THAT THERE WERE APPROXIMATELY 3 QUARTS OF OIL LEFT IN THE ENGINE. IT WAS DECIDED TO PULL THE ENGINE AND SEND IT FOR TESTING. IT WAS ASSUMED THAT AN OIL SEAL HAD MALFUNCTIONED AND THE SUBSEQUENT OIL LOSS CAUSED THE ENGINE TO OVERHEAT AND ACTIVATE THE ENGINE FIRE DETECTION LO2L72 4T4 TRTA24CE E26NE 5 CP10NE 20070118000372007011800037SO 2007 1 18 2006FA0001141 120061120G21403716725 LINE PIPER PA34 PA34200T 7103406SO CONT O520 TSIO520E 17040SO CABIN HEATER LEAKING B O OTHER O OTHER NRNOT REPORTED 1 CE074566Q 347770241 PILOT REPORTED FUEL SMELL IN THE CABIN WHEN CABIN HEATER IS ON. FURTHER INVESTIGATION REVEALED A PIN HOLE CAUSED BY CORROSION IN THE CABIN HEATER FUEL LINE JUST AFT OF THE AFT SPAR CARRY THRU. (K) 1L72 3O3 O A7SO E8CE 20070118000382007011800038CE 2007 1 18 2006FA0001142 120061115G2731NAS302665170 CONTROL CABLE BEECH 90 C90 1152913CE PWA PT6 PT6* 52043EA ELEVATOR TRIM KINKED B E81RO OTHER O OTHER NRNOT REPORTED 1 GL03400BX LJ686 INVESTIGATED ELEVATOR TRIM OPERATIONS COMPLAINT. FOUND FORWARD ELEVATOR TRIM CABLE, PN NAS302-66-5170, LOOSE AND OFF PULLEYS UNDER LT CABIN FLOOR AREA. CABLE ASSY DAMAGED BY KINKING AND FRAYING FROM CONTACT WITH PULLEY SUPPORTS AND ADJACENT STRUCTURE. ALSO FOUND PN 4000524-8508 ELEVATOR TRIM SERVO DAMAGED AND OPERATIONS ERRATIC. MAINTENANCE RECORDS NOT MADE AVAILABLE, UNABLE TO DETERMINE PREVIOUS MAINTENANCE HISTORY FOR ELEVATOR TRIM SYSTEM. HAVE NOTED SIMILAR DAMAGE IN OTHER SERIES AIRCRAFT. USUALLY CAUSED BY CABLE MISROUTING OR LOW CABLE TENSION FOR AN EXTENDED PERIOD OF OPERATIONS. (K) 1L72 3T3 T 3A20 E2NE 20070116000642007011600064CE 2007 1 16 2006FA0001143 120061109G32601CH25 DOWNLOCK SWITCH BEECH 300 300BEECH 1152930CE MLG INOPERATIVE B E81RO OTHER O OTHER NRNOT REPORTED 1 GL038YN FL417 INVESTIGATED RED WARNING LIGHT ILLUMINATED IN LANDING GEAR CONTROL HANDLE WITH LANDING GEAR DOWN AND LOCKED. FOUND NLG DOWNLOCK SWITCH. S508 INOPERATIVE PN 101-3646289, MICROSWITCH-FREEPORT PN 1CH25. REPLACED SWITCH AND ADJUSTED IAW MM. LANDING GEAR POSITION/WARNING SYSTEM FUNCTIONAL TESTS NORMAL. (K) 2L72 4T A24CE 20070116000652007011600065SO 2007 1 16 2006FA0001144 120061110G7820 MUFFLER MAULE M7235 M7235C 5460110SO LYC O540 IO540* 41532EA HARTZLHCC3Y HCC3YR GL ENGINE CRACKED B FTURO OTHER O OTHER NRNOT REPORTED 1 EA6555105165 25104C L3069248A DY6641B AIRCRAFT CAME IN FOR FIRST ANNUAL AFTER CERTIFICATION. UPON VISUAL INSPECTION FOUND A CRACK ADJACENT TO THE WELD ON THE GUSSET/DOUBLER LOCATED ON THE LOWER PORTION OF THE MUFFLER AT THE EXHAUST OUTLET. THE MUFFLER WAS PRESSURIZED AND VERIFIED THAT THE CRACK HAD EXTENDED INTO THE CAN. MOST LIKELY CAUSED BY THE NORMAL FLEX AND ROTATION OF ENGINE OPERTATIONS. COUPLED WITH THE METHOD OF ATTACHMENT OF THE EXHAUST PIPE. (K) 1H71 3O3 ONC3A23 1E4 5 CP25EA 20070109000442007010900044SO 2007 1 9 2006FA0001145 120061101G321330A04000091 DRAG LINK MAULE M7235 M7235C 5460110SO LYC O540 IO540* 41532EA HARTZLHCC3Y HCC3YR GL RT MLG MISINSTALLED B FTURO OTHER W INADEQUATE Q C NRNOT REPORTED 1 EA6555105 25104C L3069248A DY6641B AIRCRAFT CAME IN FOR FIRST ANNUAL AFTER INSTALLATION. ON INSPECTION FOUND MAIN GEAR DRAG LINK HAD NOT BEEN PROPERLY SEALED AT THE LOWER END ALLOWING WATER TO ENTER THE ASSEMBLY. BECAUSE OF THE SEALANT WE ARE UNABLE TO TELL IF THE INSIDE OF THE TUBE HAS SOME SORT OF CORROSION PROTECTION. MAY WANT TO CONSIDER DOING AWAY WITH THE SEALANT AND APPLYING A CORROSION PREVENTATIVE COMPOUND COUPLED WITH RECURRENT INSPECTION AND REAPPLICATION OF CPC. (K) 1H71 3O3 ONC3A23 1E4 5 CP25EA 20070116000752007011600075SO 2007 1 16 2006FA0001146 120061101G28102117X16 FUEL TANK MAULE M7235 M7235C 5460110SO LYC O540 IO540* 41532EA HARTZLHCC3Y HCC3YR GL RT WING LEAKING B FTURK NONE K FLUID LOSS ININSP/MAINT 1 EA65551051655 25104C L3069248A DY6641B AIRCRAFT CAME IN FOR FIRST ANNUAL AFTER CERTIFICATION, THE OWNER OPERATOR REPORTED FUEL STAINING ON THE RT WING, ON INSPECTION THE FUEL TANK WAS FOUND TO BE LEAKING. THE TANK WAS REMOVED AND UPON CLOSER INSPECTION 2 PIN HOLES WERE FOUND IN THE WELD SEAM, ONE BEING A LIGHT SEEP, THE OTHER LARGE ENOUGH TO PRODUCE A VISIBLE STAIN. RECOMMEND THAT ALL FUEL TANKS BE PRESSURIZED AND LEAK CHECKED , AND THAT AN INSPECTOR PLACE THEIR (STAMP) INDICATING COMPLIANCE. (K) 1H71 3O3 ONC3A23 1E4 5 CP25EA 20070118001262007011800126CE 2007 1 18 2006FA0001147 120061112G2797 WIRE LEAR 55 55LEAR 5170702CE GARRTTTFE731TFE7313 01518WP PITCH SERVO SHORTED D O OTHER O OTHER NRNOT REPORTED 1 SO01550AK 045 AIRCRAFT ABORTED TAKEOFF DUE TO BOTH STALL WARNINGS ILLUMINATED ON DEPARTURE ROLL. C/B LEFT AND RIGHT STALL C/B POPPED. AUTOPILOT, FLIGHT DIRECTOR AND PRIMARY YAW DAMPER INOPERATIVE. (K) 2L72 4F4 F A10CE E6WE 20070118001272007011800127CE 2007 1 18 2006FA0001148 120061030G2510551900921 SEAT FRAME CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE COCKPIT CRACKED B O OTHER O OTHER NRNOT REPORTED 1 EA21550RB 5500117 UPPER CHAIR BASE ASSY CRACKED AT CHAIR BACK ATTACH POINTS. STRESS ON CHAIR BACK AND METAL FATIGUE PROBABLE CAUSE. CHAIR WAS REPAIRED IAW STCC ST01042W STRUCTURAL SEAT REPAIR. (K) 1L72 4F4 F A22CE E1NE 20070118001282007011800128SO 2007 1 18 2006FA0001149 120061101G291021A09000204 HOSE MAULE M7235 M7235C 5460110SO LYC O540 IO540* 41532EA HARTZLHCC3Y HCC3YR GL HYD SYSTEM MISMANUFACTURED B FTURO OTHER O OTHER NRNOT REPORTED 1 EA655510586 25104C L3069248A DY6641B AIRCRAFT CAME IN FOR FIRST ANNUAL AFTER CERTIFICATION. ON INSPECTION HYDRAULIC FLUID WAS FOUND TO BE COMING FROM THE FORWARD FUSELAGE DRAIN. UPON REMOVAL OF THE FLOOR THE INSULATION WAS FOUND TO BE SATURATED WITH HYDRAULIC FLUID. THE SYSTEM WAS REFILED AND TROUBLESHOT, THE LEAK WAS TRACKED TO A HOSE. INSPECTION OF THE HOSE REVEALED THAT THE HOSE END WASN`T PROPERLY INSTALLED RESULTING IN THE FLUID LEAK. THIS WAS A RESULT OF IMPROPPER ASSEMBLY OF THE HOSE BY MFG AND SHOULD HAVE BEEN CAUGHT DURING PRESSURE TESTING AFTER INITIAL ASSY. (K) 1H71 3O3 ONC3A23 1E4 5 CP25EA 20061212003202006121200320CE 2006 12 12 2006FA0001150 120061017G3230998100227 LOCK PLATE BEECH BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA MLG MISINSTALLED D PFBVO OTHER W INADEQUATE Q C NRNOT REPORTED 1 EA27528WG BB151 DURING POST ACCIDENT INSPECTION OF RT AND LT MAIN LANDING GEAR DRAG LEGS, LOCK PLATES WERE FOUND MOUNTED WITH THE BEVEL AT THE NOSE OF THE PLATE FACING UP. INSPECTION OF 5 OTHER AC FOUND THE BEVEL FACING DOWN. REVIEW OF CURRENT REPS COMPONENT MM IS INCONCLUSIVE. (K) 1L72 4T4 T A24CE E4EA 20061208001822006120800182CE 2006 12 8 2006FA0001151 120061207G531460410025601 KEEL BEECH 60 B60 1153605CE FUSELAGE CRACKED D K NONE O OTHER ININSP/MAINT 1 GL193876C3004 P513 DURING ANNUAL INSPECTION, STIFFENER PART NUMBER 60-410025-51 LOCATED UNDER THE NOSE BAGGAGE FLOOR ON THE RIGHT SIDE AT STATION 67 BETWEEN THE MAIN AND STANDBY INVERTER WAS FOUND CRACKED AROUND THE HI-LOK FASTENER HOLES. REMOVAL OF THE STIFFENER ALLOWED FURTHER INSPECTION OF THE KEEL PART NUMBER 60-410025-601, WHICH REVEALED CRACKS IN THE WEB WHICH WERE PREVIOUSLY OBSCURED BY THE INSTALLED STIFFENER. THE MIRROR IMAGE STIFFENER PART NUMBER 60-410025-49 ON THE LEFT SIDE OF THE AIRCRAFT REVEALED SIMILAR CRACKS WITH NO DAMAGE TO THE KEEL. 1L72 3O A12CE 20061212002992006121200299WP 2006 12 12 2006FA0001152 220061108G723030721631 DAMPER LEAR 35 35LEAR 5170600CE GARRTTTFE731TFE73122B 01518WP NR 1 ENGINE BROKEN B UO2RO OTHER E VIBRATION/BUFFET NRNOT REPORTED 1 GL19573RL 153 P74494 AIRCRAFT ARRIVED 10/31/2006 TO TROUBLESHOOT A RUMBLE FROM THE NR 1 ENGINE. UPON INVESTIGATION, FOUND 1 FAN BLADE TO HAVE A BROKEN MIDSPAN DAMPER. (K) 2L72 4F4 F A10CE E6WE 20061208001832006120800183CE 2006 12 8 2006FA0001153 120061207G53146041002551 STIFFENER BEECH 60 B60 1153605CE FUSELAGE CRACKED D K NONE O OTHER ININSP/MAINT 1 GL193876C3004 P513 DURING ANNUAL INSPECTION, STIFFENER PART NUMBER 60-410025-51 LOCATED UNDER THE NOSE BAGGAGE FLOOR ON THE RIGHT SIDE AT STATION 67 BETWEEN THE MAIN AND STANDBY INVERTER WAS FOUND CRACKED AROUND THE HI-LOK FASTENER HOLES. REMOVAL OF THE STIFFENER ALLOWED FURTHER INSPECTION OF THE KEEL PART NUMBER 60-410025-601, WHICH REVEALED CRACKS IN THE WEB WHICH WERE PREVIOUSLY OBSCURED BY THE INSTALLED STIFFENER. THE MIRROR IMAGE STIFFENER PART NUMBER 60-410025-49 ON THE LEFT SIDE OF THE AIRCRAFT REVEALED SIMILAR CRACKS WITH NO DAMAGE TO THE KEEL. 1L72 3O A12CE 20061212003132006121200313NE 2006 12 12 2006FA0001154 220061113G7250RB211524G19 DISC RROYCERB211 RB211524G19 NE ENGINE WORN B QEMYO OTHER O OTHER NRNOT REPORTED 1 EA35 573507399 13048 (REF NR: MDR/004/06) STRIP EXAMINATION REVEALED HEAVY RUBS TO THE LP1 TURBINE DISC AND TO THE LP1 AND LP2 TURBINE BLADES. INITIAL EXAMINATION HAS FAILED TO IDENTIFY THE CAUSE OF THE BLADE AND DISC CONTACT ALL SETTINGS APPEARING NORMAL A REVIEW OF SERVICE OPERATION HAS FAILED TO IDENTIFY ANY INCREASE IN VIBRATION IN SERVICE. (K) 4 F E30NE 20061212003042006121200304WP 2006 12 12 2006FA0001155 120061009G5311 FRAME LKHEED1011 10113853 5265020WP RROYCERB211 RB21122* 54555NE FUSELAGE CRACKED B RJAYK NONE O OTHER ININSP/MAINT 1 EA33753DA 193W1189 (REF NR: 06DA063) DURING C-CHECK, MAINTENANCE TASK 53-02-1000 INSP FS 983 FRAME. A CRACK, 3 INCHES) FOUND AT LT, BY A CLOSE VISUAL INSP AND CONFIRMED BY NDT. NRC NR 546 RAISED FOR CORRECTIVE ACTION. (K) 2L73 4F4 F A23WE A12EU 20061212002732006121200273CE 2006 12 12 2006FA0001156 120061117G2750 FITTING BEECH 65 A65 1152803CE T/E FLAP SHEARED B YCYRO OTHER F FLT CONT AFFECTED UKUNKNOWN 1 SO19V2LDO LC291 (REF NR: MOR NR OCC442) OPERATED FLIGHT NR 101, VFR CONDITIONS, FLIGHT AND APPROACH LANDING WAS NORMAL. AFTER LANDING, ROLLOUT FLAPS WERE RETRACTED. WHEN EXITING THE AC IT WAS NOTICED THAT THE INNER FLAP ON THE PORT SIDE WAS STILL DOWN. THE FLAP WAS MANUALLY RESET TO ZERO, AND THE AIRCRAFT WAS FLOWN BACT TO DEPARTURE AIRPORT. A FLAPLESS LANDING WAS CARRIED OUT. MAINTENANCE FOUND THAT THE LT IB FLAP DRIVE ASSY HAD FAILED. THE 2 LUGS THAT TRANSFER CABLE MOVEMENT 90 DEGREES INTO ACTUATOR MOVEMENT HAD SHEARED. THE LT IB FLAP COULD BE DEPLOYED FROM THE (UP) TO THE (DOWN) POSITION, BUT HAD TO BE RESET TO THE (UP) POSITION MANUALLY. THE LT OB, RT IB AND OUB FLAP DRIVE ASSY`S, FLAP GEAR BOX AND DRIVE ASSY, PN1L72 3O 3A20 20061212002952006121200295EU 2006 12 12 2006FA0001157 120060524G2822SC402 PUMP BRAERO1000 BAE1251000 1500287EU PWA 305 PW305 NE FUEL SYSTEM FAILED B UO2RO OTHER O OTHER NRNOT REPORTED 1 GL1946WC 247 259028 THREE FUEL BOOST PUMPS IN OVERHAULED CONDITION, SAME PART NUMBER, ORDERED FROM THE SAME VENDER HAVE FAILED AFTER SHORT TIME ON SAME AIRCRAFT USED ON LT AND RT SIDES. 1) FUEL BOOST PUMP OVERHAULED CONDITION SN 11A557 FAILED 5/24/06 AFTER 247 HOURS. 2) FUEL BOOST PUMP OVERHAULED CONDITION SN 9AU160 FAILED 5/11/06 AFTER 232 HOURS. 3) FUEL BOOST PUMP OVERHAULED CONDITION SN 1AK23 FAILED 11/17/06 AFTER 157 HOURS. (K) 2L72 4F4 FRTA3EU E35NE 20061212002932006121200293EU 2006 12 12 2006FA0001158 120060511G2822SC402 PUMP BRAERO1000 BAE1251000 1500287EU PWA 305 PW305 NE FUEL SYSTEM FAILED B UO2RO OTHER O OTHER NRNOT REPORTED 1 GL1946WC 232 THREE FUEL BOOST PUMPS IN OVERHAULED CONDITION, SAME PN, ORDERED FROM SAME VENDOR HAVE FAILED AFTER SHORT TIME ON SAME AIRCRAFT USED ON LT AND RT SIDES. 1) FUEL BOOST PUMP OVERHAULED CONDITION SN 11A557 FAILED 5/24/06 AFTER 247 HOURS. 2) FUEL BOOST PUMP OVERHAULED CONDITION SN 9AU160 FAILED 5/11/06 AFTER 232 HOURS. 3) FUEL BOOST PUMP OVERHAULED CONDITION SN 1AK23 FAILED 11/17/06 AFTER 157 HOURS. (K) 2L72 4F4 FRTA3EU E35NE 20061212003012006121200301EU 2006 12 12 2006FA0001159 120061117G2822SC402 PUMP BRAERO1000 BAE1251000 1500287EU PWA 305 PW305 NE FUEL SYSTEM FAILED B UO2RO OTHER O OTHER NRNOT REPORTED 1 GL1946WC 259028 THREE FUEL BOOST PUMPS IN OVERHAULED CONDITION, SAME PN, ORDERED FROM THE SAME VENDOR HAVE FAILED AFTER SHORT TIME ON SAME AIRCRAFT USED ON LT AND RT SIDES. 1) FUEL BOOST PUMP OVERHAULED CONDITION SN 11A557 FAILED 5/24/06 AFTER 247 HOURS. 2) FUEL BOOST PUMP OVERHAULED CONDITION SN 9AU160 FAILED 5/11/06 AFTER 232 HOURS. 3) FUEL BOOST PUMP OVERHAULED CONDITION SN 1AK23 FAILED 11/17/06 AFTER 157 HOURS. (K) 2L72 4F4 FRTA3EU E35NE 20061213000612006121300061WP 2006 12 13 2006FA0001160 120061104G6210 HOUSING ROBSIN ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540* 41532EA M/R BLADE LEAKING D O OTHER K FLUID LOSS NRNOT REPORTED 1 NM05424SH1353 1989C 10877 FLUID LEAKING FROM MAIN ROTOR BLADE PITCH BEARING HOUSING. 1G71 3O3 O H11NM 1E4 20070104000742007010400074WP 2007 1 4 2006FA0001161 120061109G6210C1561 BOOT ROBSIN ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540* 41532EA MAIN ROTOR BLADELEAKING D K NONE K FLUID LOSS ININSP/MAINT 1 NM05424SH1353 1989C 10877 FLUID LEAKING FROM MAIN ROTOR BLADE PITCH BEARING HOUSING. 1G71 3O3 O H11NM 1E4 20070109000452007010900045CE 2007 1 9 2006FA0001163 120060823G526012115041 CABLE CESSNA210 T210M 2073451CE CONT O520 TSIO520* 17040SO PAX DOOR STEP BROKEN H O OTHER S AFFECT SYSTEMS LDLANDING 1 WP176169N1000 21062940 THE PILOT EXTENDED THE LANDING GEAR PRIOR TO LANDING, AND THE NOSEGEAR WOULD NOT EXTEND INTO THE DOWN-AND-LOCKED POSITION (THE MAINS LOCKED). DURING LANDING, THE NOSEGEAR COLLAPSED. POST INCIDENT INSPECTION SHOWED THAT THE PASSENGER STEP CABLE BROKE AT THE FORWARD PULLEY AND INTERTWINED WITH THE NOSE GEAR LINKAGE, NOT ALLOWING IT TO LOCK. 1H71 3O3 O 3A21 E8CE 20070104000752007010400075WP 2007 1 4 2006FA0001164 120061204G6210C1561 BOOT ROBSIN ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540* 41532EA MAIN ROTOR BLADELEAKING D K NONE K FLUID LOSS ININSP/MAINT 1 NM05424SH1408 1989C 10877 FLUID LEAKING FROM MAIN ROTOR BLADE PITCH BEARING HOUSING. 1G71 3O3 O H11NM 1E4 20070108001742007010800174WP 2007 1 8 2006FA0001165 120061203G6210C1561 BOOT ROBSIN ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540* 41532EA M/R BLADE LEAKING D O OTHER K FLUID LOSS NRNOT REPORTED 1 NM05424SH1353 1989C 10877 FLUID LEAKING FROM MAIN ROTOR BLADE PITCH BEARING HOUSING. 1G71 3O3 O H11NM 1E4 20070108001762007010800176WP 2007 1 8 2006FA0001166 120061104G6210C1561 BOOT ROBSIN ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540* 41532EA M/R BLADE LEAKING D O OTHER K FLUID LOSS NRNOT REPORTED 1 NM05424SH1353 1989C 10877 FLUID LEAKING FROM MAIN ROTOR BLADE PITCH BEARING HOUSING. 1G71 3O3 O H11NM 1E4 20070108001792007010800179WP 2007 1 8 2006FA0001167 120061204G6210C1561 BOOT ROBSIN ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540* 41532EA M/R BLADE LEAKING D K NONE K FLUID LOSS ININSP/MAINT 1 NM05424SH1408 1905C 10877 FLUID LEAKING FROM MAIN ROTOR BLADE PITCH BEARING HOUSING. 1G71 3O3 O H11NM 1E4 20070108001832007010800183WP 2007 1 8 2006FA0001168 120061204G6210C1561 BOOT ROBSIN ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540* 41532EA M/R BLADE LEAKING D O OTHER K FLUID LOSS NRNOT REPORTED 1 NM05511CC54 3424 10173 FLUID LEAKING FROM MAIN ROTOR BLADE PITCH BEARING HOUSING. 1G71 3O3 O H11NM 1E4 20070108001842007010800184WP 2007 1 8 2006FA0001169 120061204G6210C1561 BOOT ROBSIN ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540* 41532EA M/R BLADE LEAKING D O OTHER K FLUID LOSS NRNOT REPORTED 1 NM05511CC54 3425 10173 FLUID LEAKING FROM MAIN ROTOR BLADE PITCH BEARING HOUSING. 1G71 3O3 O H11NM 1E4 20070108001902007010800190WP 2007 1 8 2006FA0001170 120061117G5340269A5472 BRACKET HUGHES HUGHES269 269C 4470504WP LYC O360 HIO360C1A 41514EA FUSELAGE BROKEN B O OTHER O OTHER NRNOT REPORTED 1 SW17110472701 29 211031 L2209751A ONE OF THE BELT DRIVE CLUTCH ACTUATION SYSTEM CABLE PULLEY BRACKETS (1 OF 2 P/N 269A5472) BROKE CLEAN ACROSS BETWEEN THE PULLEY AND ITS FRAME MOUNT HOLES DURING THE PROCESS OF ENGAGING THE ROTOR SYSTEM. DURING THE SUBSEQUENT ATTEMPTED TAKEOFF THE OPERATOR NOTED THAT ROTOR RPM WOULD BLEED OFF RAPIDLY DUE TO DRIVE BELT SLIPPAGE WHEN THE COLLECTIVE CONTROL WAS RAISED. THE OPERATOR ABORTED THE TAKEOFF ATTEMPT, SHUTDOWN THE AIRCRAFT, AND INVESTIGATED THE PROBLEM THEN NOTIFIED REPAIR PERSONNEL. THE BRACKET AND THE PULLEY (P/N MS20219-4) WERE THE ONLY PARTS DAMAGED IN THIS ASSEMBLY AS A RESULT OF THIS FAILURE. 1G71 3O3 O 4H12 1E10 20070109000302007010900030WP 2007 1 9 2006FA0001171 120061204G6210C1561 BOOT ROBSIN ROBSINR44 R44 7640120WP LYC O540 O540* 41532EA M/R BLADE LEAKING D K NONE K FLUID LOSS ININSP/MAINT 1 NM057133E408 5068A 0573 FLUID LEAKING FROM MAIN ROTOR BLADE PITCH BEARING HOUSING. 1G71 3O3 O H11NM E295 20070109000312007010900031WP 2007 1 9 2006FA0001172 120061204G6210C1561 BOOT ROBSIN ROBSINR44 R44 7640120WP LYC O540 O540* 41532EA M/R BLADE LEAKING D O OTHER K FLUID LOSS NRNOT REPORTED 1 NM057133E408 5073A 0573 FLUID LEAKING FROM MAIN ROTOR BLADE PITCH BEARING HOUSING. 1G71 3O3 O H11NM E295 20070109000522007010900052WP 2007 1 9 2006FA0001173 120061203G6210C1561 BOOT ROBSIN ROBSINR44 R44 7640120WP LYC O540 O540F1A5 41532EA M/R BLADE LEAKING D O OTHER K FLUID LOSS NRNOT REPORTED 1 NM0569KA 191 4272A 1182 FLUID LEAKING FROM MAIN ROTOR BLADE PITCH BEARING HOUSING. 1G71 3O3 O H11NM E295 20070109000532007010900053WP 2007 1 9 2006FA0001174 120061203G6210C1561 BOOT ROBSIN ROBSINR44 R44 7640120WP LYC O540 O540F1A5 41532EA M/R BLADE LEAKING D O OTHER K FLUID LOSS NRNOT REPORTED 1 NM0569KA 191 4268A 1182 FLUID LEAKING FROM MAIN ROTOR BLADE PITCH BEARING HOUSING. 1G71 3O3 O H11NM E295 20070109000542007010900054WP 2007 1 9 2006FA0001175 120061203G6210C1561 BOOT ROBSIN ROBSINR44 R44 7640120WP LYC O540 O540F1A5 41532EA M/R BLADE LEAKING D O OTHER K FLUID LOSS NRNOT REPORTED 1 NM0569KA 191 4268A 1182 FLUID LEAKING FROM MAIN ROTOR BLADE PITCH BEARING HOUSING. 1G71 3O3 O H11NM E295 20070205000532007020500053WP 2007 2 5 2006FA0001176 120061203G6210C1561 BOOT ROBSIN ROBSINR44 R44 7640120WP LYC O540 O540F1A5 41532EA M/R BLADE LEAKING D O OTHER K FLUID LOSS NRNOT REPORTED 1 NM0569KA 191 4268A 1182 FLUID LEAKING FROM MAIN ROTOR BLADE PITCH BEARING HOUSING. 1G71 3O3 O H11NM E295 20070104000622007010400062SO 2007 1 4 2006FA0001177 120061130G5711 STRUT PIPER J3 J3 7100502SO RIGHT WING CORRODED G O OTHER O OTHER TXTAXI/GRND HDL 1 NM05 RT STRUT WAS DAMAGED FROM LOWERING A BI-FOLD HANGER DOOR ON THE WING TIP. THE STRUT WAS MANUALLY SEPARATED WERE EXTENSIVE CORROSION WAS FOUND INSIDE THE WING STRUT. THE PLANE HAS SET IDLE FOR 3 YEARS OUT OF ANNUAL INSPECTION. THE LAST ANNUAL INSPECTION PERFORMED INCLUDED COMPLYING WITH AD 99-01-05 WITH NO DISCREPANCIES NOTED. 1H71 3O ATC660 20070108001422007010800142CE 2007 1 8 2006FA0001178 120061212G8120227450 CLAMP CESSNA421 421 2076010CE CONT O520 GTSIO520N 17032SO TURBOCHARGER CRACKED D O OTHER O OTHER NRNOT REPORTED 1 SW99 1366 DURING PROGRESSIVE INSPECTION FOUND LT ENGINE TURBOCHARGER TO TAILPIPE CLAMP CRACKED ALONG CIRCUMFERENCE, APPROX. 4 INCH CRACK. FOUND SAME PN CLAMP ON THE RT ENGINE OF THIS AIRCRAFT TO BE CRACKED 7 HOURS PREVIOUSLY. 1L72 3O3 ORTA7CE E7CE 20070108001732007010800173EA 2007 1 8 2006FA0001179 220061205G8530 CONNECTING ROD PIPER PA32 PA32RT300 7103215SO LYC O540 IO540K1G5 41532EA ENGINE FAILED C A UNSCHED LANDING Y ENGINE STOPPAGE CLCLIMB 1 GL272148N1965 32R7985069 1892548A INTERNAL ENGINE FAILURE, CYLINDERS 2 AND 4 CONNECTING RODS FAILED. ENGINE WAS ORIGINAL TO THE AIRCRAFT (1979). 1L71 3O3 O A3SO 1E4 20070108003052007010800305NM 2007 1 8 2006FA0001180 120061207G790030C208301 TRANSDUCER AMD FALC50FALCON2000 2730170NM PWA 306 PW306B NE RT ENGINE OIL FALSE INDICATIONC O OTHER N FALSE WARNING NRNOT REPORTED 1 NM07 028 CF0088 RT ENGINE OIL TRANSDUCER FAILURE WHICH GAVE FALSE ENGINE OIL INDICATION WHICH CAUSED BY AIRCRAFT OPERATIONS MANUAL CHECK LIST ENGINE SHUTDOWN AND SINGLE ENGINE LANDING. 2K72 4F4 FRTA50NM E35NE 20070108003142007010800314NM 2007 1 8 2006FA0001181 120061212G80113617712 HOUSING DOUG MD80 MD83 3023681NM STARTER CRACKED B K NONE O OTHER ININSP/MAINT 1 WP05 STARTER HOUSING FOUND CRACKED DURING DYE PENETRANT INSPECTION. 2L72 4F RT 20070108003182007010800318GL 2007 1 8 2006FA0001182 320061213G6114 HUB PIPER PA28 PA28181 7102807SO LYC O360 O360A4M 41514EA MCAULY1A170 1A170* GL PROPELLER CRACKED D K NONE O OTHER ININSP/MAINT 1 EA112112K1839 287990234 L2600423A RK022 DURING ANNUAL INSPECTION FOUND CRACK EXTENDING THROUGH THE HUB AT ONE OF THE MOUNTING BOLT HOLES. CRACK GOES COMPLETLEY THROUGH THE HUB TO THE INNER BORE OF THE HUB. NO HISTORY OF PROP STIKE OR ANY OTHER VISUAL DAMAGE TO THE PROPELLER. THIS PROPELLER INSTALLED WITH STC NR SA779NE. PROPELLER REMOVED FROM AIRCRAFT AND SENT FOR FURTHER STUDY IAW MFG REQUEST. 1L71 3O3 O 2A13 E286 5 NP857 20070108003272007010800327EU 2007 1 8 2006FA0001183 120061208G251076201113 BRACKET EXTRA EA300 EA300 70218DIEU LYC O540 AEIO540* EA SEAT BACKREST CRACKED D K NONE O OTHER ININSP/MAINT 1 SO15497AF1600 44 072 DURING A ROUTINE INSPECTION IT WAS NOTICED THE 76201.113 TOUNGE BRACKETS LT AND RT WHICH ATTACH THE REAR SEAT BACKREST TO THE LOWER SEAT ASSEMBLY WERE CRACKED THRU THE BOLT HOLES ATTACHING TO THE BACKREST. FURTHER CLOSE EXAMINATION (REMOVED UPHOLSTERY)OF THE REMOVED BACKREST ASSEMBLY REVEALED THE SEAT BACK WAS SIGNIFICANTLY CRACKED IN THE AREA OF THE UPPER BACKREST WHERE THE SEAT BACKREST ANGLE CAN BE ADJUSTED. RECOMMEND CLOSER INSPECTION OF THE AFFECTED PARTS BE ADDED TO THE 100HR AND 1000HR INSPECTION CHECKLISTS. 1M71 3O3 ONCA67EU 1E4 20070108003432007010800343NE 2007 1 8 2006FA0001184 220061129G7323 SPRING WOODWARD GE CF6 CF650* 30018NE GOVERNOR BROKEN C O OTHER O OTHER NRNOT REPORTED 1 SW99 WYG13493 COMPRESSOR DISCHARGE PRESSURE RESTORING SPRING P/N 3018-248 HAS FRACTURED CLOSE TO THE SPRING SEAT 9. 4 F E23EA 20070108003462007010800346NE 2007 1 8 2006FA0001185 220061129G7323 SPRING WOODWARD GE CF6 CF650* 30018NE GOVERNOR BROKEN C O OTHER O OTHER NRNOT REPORTED 1 SW99 WYG13493 COMPRESSOR DISCHARGE PRESSURE RESTORING SPRING P/N 3018-248 HAS FRACTURED CLOSE TO THE SPRING SEAT 9. 4 F E23EA 20070109000462007010900046SO 2007 1 9 2006FA0001186 120061213G2150 TURBINE WHEEL GULSTMG1159 GIV 3980115SO ACM SEIZED C H DEACTIVATE SYST/CIRCUITS O OTHER LDLANDING 1 WP23596CW4541 1145 AIR CYCLE MACHINE TURBINE WHEEL HAS SEIZED CAUSING INOPERATIVE AIR CONDITIONING SYSTEM. 2L72 4F RTA12EA 20070109000512007010900051EU 2007 1 9 2006FA0001188 120061202G5530 RIVET SOCATATB9 TB9 8680694EU CONT C125 C125* 17011SO VERTICAL STAB LOOSE H K NONE O OTHER ININSP/MAINT 1 SW09557J 1326 DURING THE PRE-FLIGHT INSPECTION FOR A LOCAL TRAINING FLIGHT, THE BLIND RIVETS LOCATED HALFWAY UP VERTICAL FIN WERE FOUND TO BE MAKING ALUMINUM OXIDE (DIRT TRAILS) ON BOTH SIDES OF THE VERTICAL FIN. THIS CONDITION IS INDICATIVE OF A POTENTIALLY LOOSE RIVET OR CRACKED INNER RIB. MFG SB 10-083 REQUIRES THIS TYPE OF RIVET (CHERRY-MAX) AT THIS LOCATION. SUSPECT OTHER AIRCRAFT HAVE SAME ISSUE. 1L71 3O3 ONTAS1EU E236 20070109000572007010900057GL 2007 1 9 2006FA0001189 120061212G7921P010904 OIL COOLER AMTR AMD ALARUSCH2T 0033001GL LYC O235 O235* 41505EA LEAKING D O OTHER KJ FLUID LOSS WARNING INDICATION TXTAXI/GRND HDL 1 GL13216LF60 201034 OWNER REPORTED THAT AFTER FLYING AIRCRAFT, THERE APPEARED TO BE OIL LEAKING FROM UNDER COWLING. OIL LEVEL WAS CHECKED AND FOUND TO BE DOWN TO ONLY 3 QUARTS LT. AFTER REMOVAL OF COWLING AND INSPECTION, IT WAS FOUND THAT MOST OF THE OIL LEAKAGE APPEARED TO BE AROUND THE OIL COOLER. OIL COOLER LINES WERE DISCONNECTED AND OIL COOLER WAS PRESSURIZED WITH ABOUT 30 PSI OF AIR PRESSURE. A SMALL HOLE WAS FOUND IN THE UPPER RT EDGE OF OIL COOLER AT A WELD SEAM. THIS AIRCRAFT HAS ONLY ABOUT 60 HOURS TOTAL TIME SINCE NEW. AN ANNUAL INSPECTION ABOUT 2 HOURS AGO DID NOT REVEAL ANY OIL LEAKAGE. IT APPEARS THAT THE CAUSE WAS A DEFECTIVE WELD IN THE MANUFACTURING OF THE OIL COOLER. 1L71 3 O EXPA1L71E223 20070109000582007010900058EU 2007 1 9 2006FA0001190 120061202G5751 RIB SPHRTHCIRRUSCIRRUS 38019VCEU AILERON CRACKED H K NONE O OTHER ININSP/MAINT 1 SW095557 8255 37 DURING PRE-FLIGHT INSPECTION FOR TRAINING FLIGHT, IDENTIFIED CRACKS ON OUTER RIB CAPS ON BOTH AILERONS. CRACKS APPEAR TO BE ORIGINATING AT THE ATTACHMENT RIVETS LOCATED AT THE EDGE OF THE AILERONS. 1K00 G19EU 20070109000492007010900049SO 2007 1 9 2006FA0001192 220061213G8530TISN712BCA221 CYLINDER CESSNA340 340A 2076405CE CONT O520 TSIO520NB 17040SO HARTZLHCC3Y PHCC3YF2 GL ENGINE CRACKED C K NONE O OTHER ININSP/MAINT 1 WP254155A652 340A1001 509812 COMPLIANCE WITH ENGINE COMPONENTS, INC. MANDATORY SB06-2 DISCLOSED CRACKED CYLINDER IN RT ENGINE WITH OBVIOUS LEAKAGE. 1L72 3O3 O 3A25 E8CE 5 CP25EA 20070108001922007010800192CE 2007 1 8 2006FA0001193 120061218G214070893 PUMP JANITROL B4500 BEECH 58 58 1152740CE CONT O550 IO550* SO HEATER BURNED OUT B A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CLCLIMB 1 WP25870JA1935 TH2036 SMOKE IN THE COCKPIT, AND ELECTRICAL BURNING SMELL WERE OBSERVED AFTER TAKEOFF, AFTER THE GEAR WAS RETRACTED. THE HEATER HAD BEEN IN OPERATION APPROXIMATELY 30 MINUTES BEFORE TAKEOFF, WITH NO SMOKE OR SMELL OBSERVED. THE HEATER WAS TURNED OFF, AND THE SMOKE DISSIPATED. THE AIRCRAFT RETURNED TO LAND. THE HEATER FUEL PUMP, LOCATED IN THE NOSE GEAR WELL, WAS FOUND TO BE CHARRED. WHEN THE GEAR IS RETRACTED AND THE GEAR DOORS ARE CLOSED, THERE WOULD BE DIFFERENT AIR-FLOW IN THE GEARWELL, POSSIBLY CAUSING A HIGHER PRESSURE IN THE GEARWELL AND FORCING AIR INTO THE CABIN, PAST THE BOOTS FOR THE NOSE GEAR RETRACT ROD AND STEERING LINKAGES. THIS IS AT LEAST THE THIRD OCCURRENCE OF A BURNED PUMP IN A FLEET OF 11 LIKE 1L72 3O3 O 3A16 E3SO 20070118001232007011800123NE 2007 1 18 2006FA0001195 120061128G6220641026000042 DAMPER SKRSKYS64 S64E 8142604NE BROKEN B JYDRO OTHER O OTHER NRNOT REPORTED 1 NM09CGESG 64065 (REF: MDR06-093) DAMPER WAS REMOVED FROM THE AIRCRAFT DUE TO, THE PISTON PN 6410-26005-104, SN 550 FOUND BROKEN AFTER SHUTDOWN OF HELICOPTER. THE PISTON ROD BROKE NEAR THE FORK ASSEMBLY, PN 6410-26211-041 AND APPEARS TO BE BROKEN AT THREADS. DAMPER WAS INSTALLED ON MRH PN 6410-20004-033, SN A2-013. (K) 2G72 4U H4EA 20070116000132007011600013CE 2007 1 16 2006FA0001196 120061129G291090E551701064 LINE CESSNA CESSNA500 500CESSNA 2076602CE PWA JT15 JT15D1 52060NE BRAKE ASSY CORRODED B AKGRO OTHER O OTHER NRNOT REPORTED 1 CE05501LH 5000342 INVESTIGATING SOFT BRAKE CONDITION IT WAS NOTED THAT BRAKE FLUID WAS LEAKING FROM AROUND THE BELLY BEACON AND THE BEACON LENS WAS FULL OF FLUID. REMOVED THE INTERIOR AND THE CENTER AISLE FLOOR PANELS. HYDRAULIC FLUID WAS NOTED DRIPPING FROM RIDGE BRAKE LINE TO THE RT BRAKE. PN 90E5517010-64 AT FS248.1. MFG INSTALLED AIR-CONDITIONING COLD AIR DUCT IS TY-RAPED TO THE BRAKE FLUID LINES. BELLY BEACON IS DIRECTLY BELOW THE CORROSION AND THE BRAKE FLUID LEAKAGE. THE AIRCRAFT IS NOT EQUIPPED WITH BELLY DRAINS. THE CONDENSATION LIES IN THE BELLY OF THE AIRCRAFT AND THE BEACON CREATES HEAT AND THE HUMIDITY CAUSES CORROSION ON COMPONENT PARTS IN THE UNDER FLOOR AREA. MFG PROBABLY SHOULD ENGINEER A DRAINAGE SYSTEM1L72 4F4 F A22CE E1NE 20070116000162007011600016CE 2007 1 16 2006FA0001197 120060918G5343 TRUSS AYRES S2 S2R 7630202CE MLG BROKEN D O OTHER O OTHER NRNOT REPORTED 1 AL0332LF 9000 5089R UPPER TRUSS TO SHOCK STRUT BROKE OFF GEAR LEG, ALLOWING LANDING GEAR TO COLLAPSE. THIS AIRCRAFT HAS BEEN USED FOR FUEL HAULING AND IS LANDING WITH HEAVY LOADS. IT APPEARS A SMALL CRACK IN 1 TRUSS TUBE DEVELOPED AND EVENTUALLY FAILED, CAUSING TOTAL FAILURE OF THE LANDING GEAR LEG. RECOMMEND DYE PENETRANT INSPECTION OF GEAR LEGS ON AIRCRAFT CONSISTANTLY LANDING WITH HEAVY LOADS EVERY 200 TO 300 HOURS. (K) 1L71 3R NCA4SW 20070116000142007011600014NM 2007 1 16 2006FA0001198 120060912G5540173A01038 RUDDER BOEING737 73776N 13844CHNM GE CFM56 CFM56* 13802NE DAMAGED B I6XRO OTHER O OTHER NRNOT REPORTED 1 GL11279AT 32666 RUDDER DAMAGED DUE TO LIGHTENING STRIKE WHILE AIRCRAFT WAS ON GROUND. DETAILED INFORMATION CONCERNING THIS REPAIR CAN BE FOUND ON (NR 10981-3600-0001). (K) 2L72 4F4 FRTA16WE E2GL 20070116000192007011600019EA 2007 1 16 2006FA0001199 220061003G8520STD21C7 SCREW PIPER PA24 PA24250 7102404SO LYC O540 O540A1A 41532EA IDLR GEAR FAILED D O OTHER O OTHER NRNOT REPORTED 1 EA175097P 24107 L11240 A POST ACCIDENT INVESTIGATION IDENTIFIED THAT THE CRANKSHAFT IDLER GEAR WAS MISSING SEVERAL TEETH. FURTHER EXAMINATION REVEALED THAT THE SCREWS HOLDING THE CRANKSHAFT IDLER GEAR SHAFT HAD FAILED. (K) 1L71 3O3 O 1A15 E295 20070109000052007010900005CE 2007 1 9 2006FA0001200 120061205G5330030A326633 ACCESS PANEL MTSBSIMU2 MU2B60 5780460CE GARRTTTPE331TPE331* 01514WP FUSELAGE CORRODED D O OTHER O OTHER NRNOT REPORTED 1 GL25215MH 1544SA DRAIN HOLE IN COVER NOT BEING LOCATED PROPERLY CAUSES WATER TO LAY IN AFT. FLANGE OF NEXT FRAME FWD CAUSING CORROSION. (DRAIN HOLE NEEDS TO BE IN FRAME RADIUS. (PRIMARY STRUCTURE). (K) 1H72 3T3 TRTA10SW E2WE 20070116000742007011600074CE 2007 1 16 2006FA0001201 120060630G8120C2950010101 TURBOCHARGER CESSNA210 T210N 2073456CE CONT O520 TSIO520* 17040SO ENGINE FAILED B H5GRO OTHER O OTHER NRNOT REPORTED 1 EA076363L32 21064703 NEW TURBO ASSY WAS INSTALLED 3/27/2006. (3) MONTHS LATER ON 6/30/06 (32 HOURS TT) THE TURBO SHAFT TIGHTENED UP ENOUGH TO NOT PRODUCE TAKEOFF POWER ON NEXT FLIGHT. OIL PRESSURE AND OIL VOLUME DELIVERED TO TURBO BEARINGS WAS VERIFIED TO BE ADEQUATE. CUSTOMER PROCEDURES FOR COOL DOWN/ SPOOL DOWN OF TURBO AFTER TAXI WERE VERIFIED TO BE CONSISTENT WITH MFG POH RECOMMENDED PROCEDURES. NEW TURBO WAS INSTALLED AND (4) MONTHS (41 HOURS TURBO TT) LATER IT DID THE SAME THING. M OR D REPORT SUBMITTED THIS DATE ALSO. (K) 1H71 3O3 O 3A21 E8CE 20070116000682007011600068CE 2007 1 16 2006FA0001202 120061006G8120C2950010101 TURBOCHARGER CESSNA210 T210N 2073456CE CONT O520 TSIO520* 17040SO FAILED B H5GRO OTHER O OTHER NRNOT REPORTED 1 EA076363L41 21064703 NEW TURBO ASSY WAS INSTALLED 6/30/06. FOUR MONTHS LATER ON 10/6/06 (41 HOURS TT) THE TURBO SHAFT TIGHTENED UP ENOUGH TO NOT PRODUCE TAKEOFF POWER ON NEXT FLIGHT. OIL PRESSURE AND OIL VOLUME DELIVERED TO TURBO BEARINGS WAS VERIFIED TO BE ADEQUATE. CUSTOMER PROCEDURES FOR COOL DOWN/SPOOL DOWN OF TURBO AFTER TAXI WERE VERIFIED TO BE CONSISTENT WITH POH RECOMMENDED PROCEDURES. THIS IS THE (2ND) TURBO IN 7 MONTHS TO DEVELOP THIS PROBLEM. MFG HAS NUMEROUS REPORTS OF THIS SAME PROBLEM. IT WOULD SEEM APPROPRIATE TO RE-EVALUATE THE ENGINEERING AND OR MFG OF THE SHAFT, BEARINGS, CLEARANCES, ETC OF THE TURBO. (K) 1H71 3O3 O 3A21 E8CE 20070118000932007011800093SW 2007 1 18 2006FA0001203 120061007G3213109152 STRUT AIRPTSA A9B 0144206SW LYC O540 TIO540* 41532EA MLG FAILED D O OTHER O OTHER NRNOT REPORTED 1 GL097638V 1366 THIS PART FAILED AT THE WELD THAT ATTACHES PN 12020( UNIVERSAL) TO THE LANDING GEAR SHOCK STRUT. THIS PART IS LOCATED AT THE POINT WHERE THE SHOCK STRUT ATTACHES TO THE LANDING GEAR TO FUSELAGE SUPPORT TUBE AT THE FRONT OF THE RT WING MAIN SPAR. THIS PART FAILED DURING A NORMAL TAKEOFF. THE PART BROKE AT THE WELD BREAKING THE WELD ON ONE SIDE. THE WELD DID NOT APPEAR TO HAVE COMPLETE PENETRATION. INTERNAL CORROSION MAY HAVE BEE A FACTOR. THIS PART APPEARS TO BE THE WEAKEST PART OF THE ENTIRE SHOCK STRUT SYSTEM. I WOULD RECOMMEND THAT THIS PART BE MADE OF THICKER MATERIAL UTILIZING A MORE EXTENSIVE WELD WITH GOOD PENETRATION. (K) 1L71 3O3 O A758 E14EA 20070109000032007010900003CE 2007 1 9 2006FA0001204 120061118G323012838002115 RELEASE CABLE BEECH MU300 400A 1155402CE PWA JT15 JT15D5 52112NE LT MLG FRAYED B E81RO OTHER O OTHER NRNOT REPORTED 1 GL0395GK 7502 RK27 DURING SCHEDULE (A) AND (B) INSPECTION FOUND LT MLG EMERGENCY UPLOCK RELEASE CABLE ASSY. SEVERLY FRAYED AND CABLE FUNCTION COMPROMISED AT UPLOCK ATTACH CLEVIS END. THIS SB 32-3200. SB 32-3200 IS A RECOMMENDED SB ONLY, COMPLIANCE RECOMMENDED WHEN CABLE ASSY REPLACEMENT REQUIRED. NO RECORD OF PREVIOUS COMPLIANCE ON THIS AIRCRAFT. (K) 2H72 4F4 FRTA16SW E25EA 20070122001862007012200186CE 2007 1 22 2006FA0001205 120061120G551145A21104012 RIB BEECH MU300 400A 1155402CE PWA JT15 JT15D5 52112NE HORIZONTAL STAB CRACKED B E81RO OTHER O OTHER NRNOT REPORTED 1 GL03311HS2142 RK296 DURING AN A, B, AND C INSPECTION, FOUND THE HORIZONTAL STABILIZER MOUNTING FACES NOT PARALLEL WITH THE VERTICAL STABILIZER, HORIZONTAL STABILIZER ROLLER CLEARANCE CHECKS IAW MM 27-40-00 OUT OF SERVICE LIMITS. INSPECTED STABILIZER IAW MFG COMMUNIQUÉ NR 70 AND FOUND RT HORIZONTAL STABILIZER RIB, PN 45A21104012, CRACKED. REPLACED RIB AND REINSTALLED STABILIZER, HORIZONTAL STABILIZER ROLLER CLEARANCE CHECKS NOW WITHIN SERVICE LIMITS. IAW COMMUNIQUÉ NR 70, ROLLER GAP DIMENSIONS OUT OF SERVICE LIMITS MAY BE CONTRIBUTING TO PROBLEM. AFFECTED STRUCTURE HAS NOT YET BEEN INCLUDED IN SCHEDULED INSPECTIONS GUIDE. (K) 2H72 4F4 FRTA16SW E25EA 20070116000712007011600071SO 2007 1 16 2006FA0001206 120061206G5711202394 NUT AYRES S2 S2RRESTD 0970101SO PWA R1340 R1340* 52016NE WING SPAR DAMAGED D PWWGO OTHER O OTHER NRNOT REPORTED 1 WP178960Q 2450R WHILE PERFORMING (SPLICE BLOCK) MAINTENANCE A NEW TUBE NUT HAD ITS THREADS PULLED OUT BEFORE REACHING TORQUE. THE FOLLOW ON PART WAS EXAMINED AND WAS FOUND TO BE LOOSE ON THE BOLT, EVEN THE USED TUBE NUT WAS TIGHTER. SUSPECT PANTS HAVE NO PN OR STAMP, ALSO NO INDENTATIONS ON FACE OF THE NUT (NOT VISIBLE WHEN INSTALLED). ALMOST MADE TORQUE. (K) 1L71 3R3 R A4SW 5E2 20070116000472007011600047SO 2007 1 16 2006FA0001207 220061122G8500 CASE BEECH 35 V35 1151538CE CONT O520 IO520BA 17032SO ENGINE DAMAGED G O OTHER O OTHER NRNOT REPORTED 1 SW11205DB D8060 1207758A ENGINE LT CASE, MALT DEVELOPED HOLE APPROX 6 INCHES X 4 INCHES AS ROD-PISTON APPEARS TO BE MISSING FOR NR 4 CYLINDER. ENGINE OPERATED: (104 HOURS - 2004), (14 HOURS - 2005), (12 HOURS - 2006). PROPELLER RECENTLY SHIMMED BLADE NR 3, RED DYE AROUND PROP SEAL. (K) 1L71 3O3 O 3A15 E5CE 20070116000572007011600057EA 2007 1 16 2006FA0001208 220061010G7320 LINE PIPER PA23 PA23250 7102308SO LYC O540 TIO540C1A 41532EA ENG FUEL LEAKING D O OTHER O OTHER NRNOT REPORTED 1 SO016879A 2 277954104 FUEL LEAKING, TURBOCHARGER AIR LINE TO FUEL PUMP. (K) 1L72 3O3 O 1A10 E14EA 20070116000482007011600048EA 2007 1 16 2006FA0001209 220061010G7310RG17980YM LINE PIPER PA23 PA23250 7102308SO LYC O540 TIO540C1A 41532EA TURBOCHARGER LEAKING D O OTHER KJ FLUID LOSS WARNING INDICATION NRNOT REPORTED 1 SO016879A 2 277954104 FUEL LEAKING OUT TURBOCHARGER AIR LINE TO FUEL PUMP. (K) 1L72 3O3 O 1A10 E14EA 20070116000722007011600072EA 2007 1 16 2006FA0001210 220061010G7310RG179803M TURBOCHARGER PIPER PA23 PA23250 7102308SO LYC O540 TIO540C1A 41532EA LT ENGINE LEAKING D O OTHER O OTHER NRNOT REPORTED 1 SO016879A 2 277954104 FUEL LEAKING OUT TURBOCHARGER AIR LINE TO FUEL PUMP. (K) 1L72 3O3 O 1A10 E14EA 20070116000632007011600063EA 2007 1 16 2006FA0001211 220061010G7310RG17980JM LINE PIPER PA23 PA23250 7102308SO LYC O540 TIO540C1A 41532EA FUEL SYSTEM LEAKING D O OTHER KJ FLUID LOSS WARNING INDICATION NRNOT REPORTED 1 SO016879A 2 277954104 FUEL LEAKING OUT TURBOCHARGER AIR LINE TO FUEL PUMP. (K) 1L72 3O3 O 1A10 E14EA 20070116000762007011600076CE 2007 1 16 2006FA0001212 120061122G552050524414 BELLCRANK BEECH 80 65B80 1152812CE LYC O720 IO720A1B 41546EA RT ELEVATOR CRACKED D O OTHER O OTHER NRNOT REPORTED 1 WP1344MA LD412 L15595YA A CRACK WAS FOUND ON THE RT BELLCRANK SUPPORT ASSY. DURING A MANDITORY 5 YEAR INSPECTION IAW MSB 2231 REV 1. (K) 1L72 3O3 O 3A20 1E15 20070104000612007010400061CE 2007 1 4 2006FA0001213 120060407G8011PM2401H STARTER CESSNA172 172S 2072439CE LYC IO360 IO360L2A EA ENGINE FAILED G K NONE O OTHER ININSP/MAINT 1 WP056564723 172S9778 STARTER WOULD NOT STAY ENGAGED. STARTER ONLY HAS 23.4 HR. 1H71 3O3 ONT3A12 1E10 20070108001532007010800153CE 2007 1 8 2006FA0001214 120061221G8011PM2401 STARTER CESSNA172 172S 2072439CE LYC IO360 IO360L2A EA ENGINE STUCK G K NONE O OTHER ININSP/MAINT 1 WP05 172S9778 STARTER STUCK IN ENGAGED MODE 1H71 3O3 ONT3A12 1E10 20070108001542007010800154CE 2007 1 8 2006FA0001215 120060306G8011PM2401 STARTER CESSNA172 172S 2072439CE LYC IO360 IO360L2A EA ENGINE SPINNING G K NONE O OTHER ININSP/MAINT 1 WP05259TA1585 172S9225 STARTER WILL NOT STAY ENGAGED. 1H71 3O3 ONT3A12 1E10 20070108001552007010800155CE 2007 1 8 2006FA0001216 120061221G8011PM2401 STARTER CESSNA172 172S 2072439CE ENGINE MALFUNCTIONED G GBMSO OTHER O OTHER NRNOT REPORTED 1 WP05879LB289 172S9879 STARTER SPINS BUT WILL NOT ENGAGE. 1H71 3O NT3A12 20070108001622007010800162CE 2007 1 8 2006FA0001217 120060810G8011PM2401H STARTER CESSNA172 172S 2072439CE LYC IO360 IO360L2A EA ENGINE SPINNING G GBMSO OTHER O OTHER NRNOT REPORTED 1 WP0565647240 172S9778 STARTER FAIL, WOULD NOT ENGAGED. 1H71 3O3 ONT3A12 1E10 20070108001632007010800163CE 2007 1 8 2006FA0001218 120061207G8011PM2401H STARTER CESSNA172 172S 2072439CE LYC IO360 IO360L2A EA ENGINE SPINNING G GBMSO OTHER O OTHER NRNOT REPORTED 1 WP0565647146 172S9778 STARTER WOULD NOT ENGAGED. 1H71 3O3 ONT3A12 1E10 20070108001772007010800177CE 2007 1 8 2006FA0001219 120061221G8011 STARTER CESSNA172 172S 2072439CE ENGINE MALFUNCTIONED G GBMSO OTHER O OTHER NRNOT REPORTED 1 WP05879LB231 172S9879 STARTER WOULD NOT ENGAGE. 1H71 3O NT3A12 20070108001802007010800180CE 2007 1 8 2006FA0001220 120061020G8011PM2401 STARTER CESSNA172 172S 2072439CE LYC IO360 IO360L2A EA ENGINE SPINNING G GBMSK NONE O OTHER ININSP/MAINT 1 WP05259TA68 172S9225 STARTER SPINS BUT WILL NOT ENGAGE. 1H71 3O3 ONT3A12 1E10 20070108001812007010800181CE 2007 1 8 2006FA0001221 120060909G8011PM2401 STARTER CESSNA172 172S 2072439CE LYC IO360 IO360L2A EA ENGINE SPINNING G K NONE O OTHER ININSP/MAINT 1 WP05259TA142 172S9225 STARTER SPINS BUT WILL NOT ENGAGE. 1H71 3O3 ONT3A12 1E10 20070108001822007010800182CE 2007 1 8 2006FA0001222 120061221G8011PM2401 STARTER CESSNA182 182T 2072703CE LYC O540 IO540* 41532EA ENGINE MALFUNCTIONED G K NONE O OTHER NRNOT REPORTED 1 WP052019V269 18281699 STARTER STUCK IN ENGAGED MODE. 1H71 3O3 ONT3A13 1E4 20070108001852007010800185CE 2007 1 8 2006FA0001223 120061221G8011PM2401 STARTER CESSNA172 172S 2072439CE LYC IO360 IO360L2A EA ENGINE FAILED G K NONE O OTHER ININSP/MAINT 1 WP05259TA126 172S9225 STARTER BENDIX FAILED. 1H71 3O3 ONT3A12 1E10 20070109000412007010900041CE 2007 1 9 2006FA0001225 120061003G8011PM2401H STARTER CESSNA172 172S 2072439CE LYC IO360 IO360L2A EA ENGINE SPINNING G O OTHER O OTHER NRNOT REPORTED 1 WP0565647115 172S9778 STARTER WOULD NOT ENGAGED. 1H71 3O3 ONT3A12 1E10 20070109000592007010900059CE 2007 1 9 2006FA0001226 120060924G8011PM2401 STARTER CESSNA172 172S 2072439CE ENGINE LOCKED G GBMSK NONE O OTHER ININSP/MAINT 1 WP05658311157 172S9796 STARTER STUCK ENGAGED AND LOCKED PROP. 1H71 3O NT3A12 20070109000602007010900060CE 2007 1 9 2006FA0001227 120061212G8011PM2401H STARTER CESSNA172 172S 2072439CE LYC IO360 IO360L2A EA ENGINE SPINNING G O OTHER O OTHER NRNOT REPORTED 1 WP056564711 172S9778 STARTER WOULD NOT ENGAGED. 1H71 3O3 ONT3A12 1E10 20070118000392007011800039GL 2007 1 18 2006FA0001228 320061222G6110D68315A CLAMP HARTZLHCA2 HCA2MVK2 GL PROPELLER BLADE CRACKED C K NONE O OTHER ININSP/MAINT 1 SO19 H632 DURING A ROUTINE PRE-FLIGHT INSPECTION OF PROPELLER ASSY, A CRACK WAS IDENTIFIED ON BLADE CLAMP PN D-6831-5A, REV K, SN 3194A. PROP WAS REMOVED FROM AC FOR FURTHER INSPECTION. INSPECTION CONFIRMED OPERATOR IDENTIFIED DEFECT AND PART FORWARDED FOR FURTHER EVALUATION. THIS PART IS A TERMINATING ACTION FOR AD NOTE 97-18-02. (K) 5 CP24EA 20070118001312007011800131SO 2007 1 18 2006FA0001229 220061122G8550LPMILH50555 LINE BEECH 35 V35 1151538CE CONT O520 IO520BA 17032SO ENGINE OIL BROKEN G O OTHER K FLUID LOSS NRNOT REPORTED 1 SW11205DB D8060 1207758A STARFLEX 193, LOW PRESSURE HOSE, LP MIL-H-50555 WAS USED TO CONNECT OIL COOLER TO FIREWALL FITTING. OIL PRESSURE WILL RUN BETWEEN 50-100 PSI IN LINE. HOSE BROKE AT FITTING AT OIL COOLER OUTLET, ALL OIL WAS PUMPED OUT OF ENGINE CAUSING ROD TO BE RAMMED THROUGH LT CASE HALF. (NORMAL TSO AS1072 HOSE IS INSTALLED IN THIS POSITION. STARFLEX 2650). (K) 1L71 3O3 O 3A15 E5CE 20070116000662007011600066CE 2007 1 16 2006FA0001230 120061214G2497501122804 WIRE LEAR 35 35A 5170602CE MISINSTALLED B JGVRO OTHER O OTHER NRNOT REPORTED 1 CE09421SV 660 CELL DIP SWITCH INSTALLED 180 DEGREES OUT. CELL WIRING MISROUTED AND IMPROPER GAUGE WIRE. MULTIPLE COLD CRACKED SOLDER JOINTS BROKEN AND POORLY REPAIRED TRACES. BATTERY T3 AND P3 ARE BROKEN. UNIT SENT BACK, AS CORE SEEMS TO BE A WORKMANSHIP ISSUE. (K) 2L72 4F A10CE 20070118001332007011800133CE 2007 1 18 2006FA0001231 120061130G3411E420191 STATIC PORT RAYTHNDH125 DH125 4230106CE GARRTTTFE731TFE731* 01518WP FUSELAGE MISINSTALLED B JGVRO OTHER O OTHER NRNOT REPORTED 1 CE07700VT 257158 ROSEMOUNT STATIC PORTS DO NOT FIT CONTOUR OF AIRCRAFT SKIN. PORTS ARE NOT UNIFORM IN THICKNESS. CAN NOT INSTALL NEW PORT AND MATCH STEP HEIGHT TO MEET ORIGINAL RVSM CERTIFICATION. OTHER ISSUES: WHEN PORT IS INSTALLED, PORT CAUSE STRESS. AC SKIN DO TO CONTOUR FIT. INSTALLATION OF PORT ALSO PUTS STRESS ON PLATE TO HEATER BLOCK AND CAUSES CRACKING IN THE MATING SURFACE CAUSING PORT TO HAVE STATIC SYSTEM LEAK. (K) 2L72 4J4 FRTA3EU E6WE 20070111001462007011100146CE 2007 1 11 2006FA0001233 120061209G2497AE776L845 CONNECTOR CESSNA750 750 2076810CE ALLSN AE3007AE3007C GL MAIN BATTERY SHORTED B CNQRO OTHER O OTHER NRNOT REPORTED 1 CE07913QS6798 7500113 BATTERY OVERTEMP INDICATED R-RED CAS MESSAGE IN FLIGHT. FOUND SPLICE AT THE BATTERY TEMP SENSOR CONNECTOR PY044 BROKEN. ALSO CONNECTOR WAS FOUND BADLY CORRODED INSIDE OF CONNECTOR. REPLACED CONNECTOR PY044 AND REPLACED WIRES IAW CE750 WIRING MANUAL 20-10-06. THE INCIDENT WAS AN INDICATION PROBLEM ONLY AND BOTH AIRCRAFT BATTERIES WERE FOUND TO BE NORMAL (AIRWORTHY) WITH NO ACTION REQUIRED. (K) 2L72 4J4 FRTT00007WITE6CH 20070118000722007011800072EA 2007 1 18 2006FA0001234 220061202G8520 PISTON CESSNA150 152 2071835CE LYC O235 O235N2C 41505EA NR 3 CYLINDER STUCK D O OTHER O OTHER NRNOT REPORTED 1 GL11942868774 1762 15285639 L2404715 ENGINE QUIT IN FLIGHT, FOUND NR 3 CYLINDER PISTON NOT MOVING IN CYLINDER WHEN TURNING PROP. (K) 1H71 3O3 ONT3A19 E223 20070109000102007010900010EA 2007 1 9 2006FA0001235 220061227G8530LW19001 VALVE GUIDE CESSNA182 182T 2072703CE LYC O540 IO540AB1A5 EA STUCK D K NONE O OTHER ININSP/MAINT 1 GL0719HP 1300 200 18281266 L2895948B PERFORMED COMPRESSION CHECK ON ENGINE AND HAD 5/80 PSI ON NR 6 CYL, STAKED EXHAUST VALVE AND GOT 78/80. PERFORMED SB 388C AND HAD TO REAM VALVE GUIDES TO GET WITH-IN LIMITS OF SB. IT WAS ONLY 200 HRS SINCE LAST SB COMPLIANCE. 1H71 3O3 ONT3A13 1E4 20060914001682006091400168 2006 9 14 2006FAA0901 420060906G2210841341 AUTOPILOT SYS PIPER PA46 PA46500TP 7104622SO PWA PT6 PT6* 52043EA BURNED OUT B K NONE B SMOKE/FUMES/ODORS/SPARKS NRNOT REPORTED 1 SW4271562 4697081 THE COMPLAINANT NOTED SMOKE IN THE COCKPIT.THE SOURCE OF THE SMOKE WAS THE FAILURE OF A FILTER CAPACITOR, C20 (P/N 1131013-106035,) ON THE POWER SUPPLY BOARD (P/N 71115-05.) IT HAD BURNED OUT CAUSING THE SMOKE. IT IS A FILTER CAPACITOR FOR THE -15V SIDE OF THE DC TO DC CONVERTER. THE PART WAS INSTALLED CORRECTLY (POLARITY), AND NONE OF THE SURROUNDING DEVICES WERE ABNORMAL. IT WAS A PART THAT HAS HISTORICALLY GIVEN US THIS TYPE OF FAILURE, ALTHOUGH WE’VE NEVER HAD ISSUE WITH THE PART LOCATED HERE. IT APPEARS TO BE A ONE TIME DEFECTIVE DEVICE. 1L71 3O3 TRTA25SO E2NE 20070125001392007012500139NE 2007 1 25 2007FA0000000 220061201G7200 ENGINE CNDAIRCL600 CL6002A12 1900304EA GE CF34 CF341A NE RIGHT FAILED Z C ABORTED TAKEOFF RJ PARTIAL RPM/PWR LOSS WARNING INDICATION TOTAKEOFF 1 WP01388DB6080 380 3016 350152 RT ENGINE FAILURE AT T/O. ALL INDICATIONS WERE NORMAL ON ENGINE START AND TAXI. UPON THRUST ADVANCEMENT FOR TAKEOFF, AT APPROXIMATELY 60 PERCENT N1 WE HEARD AND FELT A COMPRESSOR STALL. THE THRUST LEVER WAS IMMEDIATELY RETARDED TO IDLE AND TEMPERATURES WERE NOTED TO BE IN THE RED(APPROX 950 DEGREESC). WE SHUT DOWN THE ENGINE AND OBSERVED THE TEMPERATURES REMAINING IN THE RED FOR APPROXIMATELY 6 TO 8 SECONDS AFTER SHUTDOWN. WE TAXIED BACK TO BOMBARDIER AND REPORTED THIS INCIDENT. SUBSEQUENT EXAMINATION REVEALED DAMAGE IN THE FORWARD AND AFT SECTIONS OF THE ENGINE. ENGINE REMOVED & ROUTED TO FOR REPAIR. 2L72 4F4 FRTA21EA E15NE 20070118000972007011800097EU 2007 1 18 2007FA0000002 120061206G5302 DOUBLER SNIAS 350 AS350B3 8680954EU TMECA ARRIELARRIEL2B NE TAIL ROTOR CRACKED D O OTHER O OTHER NRNOT REPORTED 1 WP01110E 1065 3322 FOUND CRACKS 2 EA ON LT OUTSIDE DOUBLER ASSY. 2 RIVETS WERE POPED OUT. DAMAGE VISIBLE ONLY AFTER REMOVAL OF TAIL ROTOR GEARBOX COWLING. FOUND DURING 100 HR INSP. (K) 1G71 3U3 U H9EU E00054EN 20070116000672007011600067EU 2007 1 16 2007FA0000003 120061110G36001U478003 PUMP GROB 120 G120A 1660208EU LYC O540 AEIO540* EA ENGINE OUT OF LIMITS B VJ3RO OTHER O OTHER NRNOT REPORTED 1 WP07864AF52 85004 PILOT REPORTED SUCTION INDICATOR WAS BELOW LIMITS, AC RETURNE TO BASE. UPON TROUBLESHOOTING, THE MECHANIC REMOVED THE AIR PUMP AND NOTICED THE SHAFT WAS VERY EASY TO ROTATE, HAD NO RESISTANCE TO IT. NO PROBABLE CAUSE OR RECOMMENDATIONS AT THIS TIME. (K) 1L71 3O3 ORTA49CE 1E4 20070118000362007011800036EU 2007 1 18 2007FA0000004 120061026G37101U478 PUMP GROB 120 G120A 1660208EU LYC O540 AEIO540D4D5 EA VACUUM SYS WEAK B VJ3RO OTHER O OTHER NRNOT REPORTED 1 WP07864AF 85004 RL2802548 IN FLIGHT, THE INSTRUMENT VACUUM SYSTEM WOULD NOT PUT OUT PROPER SUCTION AND CAUSED THE ATTITUDE INDICATOR TO TUMBLE. THE AC RETURNED TO MAINTENANCE AND AN INSPECTION OF THE SYSTEM FOUND THAT THE PUMP WAS WEAK. PUMP WAS REMOVED AND A NEW PUMP INSTALLED. OPERATIONAL CHECK OF THE SYSTEM CHECKED NORMAL. (K) 1L71 3O3 ORTA49CE 1E4 20070116000732007011600073EU 2007 1 16 2007FA0000005 120060922G37001U478 PUMP GROB 120 G120A 1660208EU LYC O540 AEIO540* EA VACUUM SYSTEM WORN B VJ3RO OTHER O OTHER NRNOT REPORTED 1 WP07862AF 85002 RL2515648A DURING FLIGHT SUCTION PRESSURE READING DROPPED TO ZERO, DURING FURTHER TROUBLESHOOTING TECHICIAN FOUND THE ENGINE DRIVEN DRY AIR PUMP SHAFT HAD BROKEN. PROBABLE CAUSE COULD BE FROM ENGINE VIBRATION OR POOR PARTS. RECOMMENDATION AT THIS TIME IS FOR THE MFG TO INVESTIGATE WHY PUMP IS FAILING SO EARLY. (K) 1L71 3O3 ORTA49CE 1E4 20070116000112007011600011EU 2007 1 16 2007FA0000006 120060926G37001U478 SHAFT GROB 120 G120A 1660208EU LYC O540 AEIO540* EA AIR PUMP BROKEN B VJ3RO OTHER O OTHER TXTAXI/GRND HDL 1 WP07865AF194 85005 DURING ENGINE START, SUCTION PRESSURE WAS READING ZERO, DURING FURTHER TROUBLESHOOTING, TECH FOUND THE ENGINE DRIVEN DRIVEN DRY AIR PUMP HAD A BROKEN SHAFT. PROBABLE CAUSE COULD BE FROM VIBRATION OR HARD START. NO RECOMMENDATION AT THIS TIME. (K) 1L71 3O3 ORTA49CE 1E4 20070125001102007012500110EU 2007 1 25 2007FA0000007 120061030G37101U478 PUMP GROB 120 G120A 1660208EU LYC O540 AEIO540* EA VACUUM SYS WORN C VJ3RO OTHER O OTHER NRNOT REPORTED 1 WP07865AF109 85005 DURING FLIGHT SUCTION PRESSURE READING DROPPED TO ZERO, DURING FURTHER TROUBLESHOOTING, TECH FOUND THE ENGINE DRIVEN AIR PUMP WAS NOT PRODUCTING ENOUGH SUCTION. PROBABLE CAUSE COULD BE FROM PISTION WEARING INSIDE OF PUMP. RECOMMENDATION AT THIS TIME IS FOR THE MFG TO INVESTIGATE WHY PUMP PISTON IS FAILING. (K) 1L71 3O3 ORTA49CE 1E4 20070109000022007010900002SO 2007 1 9 2007FA0000008 120061214G57116207006 SPAR PIPER PA28 PA28140 7102802SO LYC O320 O320* 41508EA LT MLG LOOSE B A5ORO OTHER O OTHER NRNOT REPORTED 1 SO09157153501 287325144 DURING AN ANNUAL INSPECTION OF THE LT MAIN LANDING GEAR ASSY PN 35644-902, IT WAS FOUND TO BE LOOSE IN THE MAIN WING SPAR. THE LT MAIN LANDING GEAR WAS REMOVED FOR FURTHER INSPECTION OF THE LT MAIN WING SPAR ASSY GEAR ATTACHING BOLT HOSES AND ATTACH POINTS. CLOSE INSPECTION FO THE WING SPAR SHOWED THAT THE LOWER (4) BOLT HOLES HAD BEEN ELONGATED. IT APPEARED THAT ALL BOLTS WERE TIGHT AND THIS CONDITION HAD BEE LOOSE FOR SOME TIME. RECOMMEND CLOSE INSPECTION OF LANDING GEAR ATTACH POINTS DURING ALL INSPECTIONS. (K) 1L71 3O3 O 2A13 E274 20070111001372007011100137GL 2007 1 11 2007FA0000009 120061218G8011642083 DRIVE ASSY CIRRUSSR SR22 2130001GL CONT O550 IO550N 17042SO STARTER CRACKED B LC1RO OTHER O OTHER NRNOT REPORTED 1 EA07249CK 0766 9117066 STARTER DRIVE WAS REMOVED FROM AIRCRAFT DUE TO SLIPPING. INSPECTION AFTER REMOVAL FOUND A CRACK EMANATING FROM THE STUD BOSS LOCATED AT APPROXIMATELY THE 7:00 POSITION. (K) 1L71 3O3 ONTA00009CHE3SO 20070111001382007011100138 2007 1 11 2007FA0000010 420061218G2562 BATTERY CIRRUSSR SR22 2130001GL CONT O550 IO550* SO ELT LEAKING D K NONE K FLUID LOSS ININSP/MAINT 1 WP11910JR 040334 0142 DURING ANNUAL INSPECTION, FOUND BATTERY COMPARTMENT CONTAMINATED BY LEAKAGE FROM D CELLS AND BATTERY TERMINALS CORRODED. BATTERIES FOUND DEAD. BATTERIES WERE INSTALLED MARCH 2004 AND HAVE A EXPIRATION DATE OF MARCH 2008. THE MODEL ELT IS CERTIFIED BY THE MFG TO USE THE BATTERY EXPIRATION DATES FOR SERVICE RATHER THAN A LIMITED CALENDAR TIME SUCH AS THE TYPICAL 24 MONTHS. THIS INSPECTOR HAS RECENTLY FOUND OTHER ELTS OF THE SAME TYPE IN THE SAME CONDITION. RECOMMENDATION THA THE SERVICE LIFE OF THE BATTERIES BE LIMITED TO 24 MONTHS. (K) 1L71 3O3 ONTA00009CHE3SO 20070116000622007011600062WP 2007 1 16 2007FA0000011 220060929G725030606852 RETAINER LEAR 45 45LEAR 5170805CE GARRTTTFE731TFE731* 01518WP LPT 2 CORRODED F O OTHER O OTHER NRNOT REPORTED 1 WP07VH5QR4660 45195 P111119C MATERIAL LOSS ON THE LPT2 NOZZLE RETAINER WITH DISLODGED PINS THAT LIKELY LED TO DOWN STREAM LPT3 BLADE MID SPAN FRACTURES AND DISPLACED MATERIAL IN THE FORM OF IMPACT DAMAGE. THIS ENGINE WAS PRESERVICE BULLETIN 72-5165 AND ADDRESSES THIS ISSUE. (K) 2L72 4F4 FRTT00008WIE6WE 20070118001292007011800129 2007 1 18 2007FA0000012 420061220G256457FASA2321325 LIFE RAFT ISRAELGALAXYGALAXY 4500307EU CABIN MISRIGGED B JG1RO OTHER O OTHER NRNOT REPORTED 1 EA25889G 046 THIS RAFT WAS INSTALLED ON AC BUT MAY BE INSTALLED ON OTHER SIMILAR AC. MOORING THE LINE (FIRING LINE) WAS FOUND RIGGED WRONG. LINE WAS TIED TO LIFE RAFT FIRST AND THEN TO THE PULL CABLE. THE LINE SHOULD BE TIED TO THE PULL CABLE FIRST AND THEN TO THE LIFE RAFT. RIGGED THIS WAY THE LIFE RAFT WOULD NOT DEPLOY BECAUSE THE PULL CABLE WOULD NOT BE ABLE TO BE FIRED. (K) 2L72 4F RTA53NM 20070111001442007011100144 2007 1 11 2007FA0000013 420061220G256457FASA2321315 LIFE RAFT ISRAELGALAXYGALAXY 4500307EU MISRIGGED B JG1RO OTHER O OTHER NRNOT REPORTED 1 EA25889G 046 THIS RAFT WAS INSTALLED ON AC BUT MAY BE INSTALLED ON OTHER SIMILAR AC. MOOORING LINE (FIRING LINE) WAS FOUND RIGGED WRONG. LINE WAS TIED TO THE RAFT FIRST AND THEN TO PULL CABLE. THE LINE SHOULD BE TIED TO THE PULL CABLE FIRST AND THEN TO THE LIFE RAFT. RIGGED THIS WAY THE LIFE RAFT WOULD NOT DEPLOY BECAUSE THE PULL CABLE WOULD NOT BE ABLE TO BE FIRED. (K) 2L72 4F RTA53NM 20070111001452007011100145 2007 1 11 2007FA0000014 420061220G256457FASA2321315 LIFE RAFT ISRAELGALAXYGALAXY 4500307EU MISRIGGED B JG1RO OTHER O OTHER NRNOT REPORTED 1 EA25889G 046 THIS RAFT WAS INSTALLED ON AC BUT MAY BE INSTALLED ON OTHER SIMILAR AC. MOORING LINE (FIRING LINE) WAS FOUND RIGGED WRONG. LINE WAS TIED TO LIFE RAFT FIRST AND THEN TO THE PULL CABLE. THE LINE SHOULD BE TIED TO THE PULL CABLE FIRST AND THEN TO THE LIFE RAFT. RIGGED THIS WAY THE LIFE RAFT WOULD NOT DEPLOY BECAUSE THE PULL CABLE WOULD NOT BE ABLE TO BE FIRED. (K) 2L72 4F RTA53NM 20070116000562007011600056 2007 1 16 2007FA0000015 120061214G35004357B VALVE OXYGEN SYS LEAKING B WP1RO OTHER O OTHER NRNOT REPORTED 1 SW15 OXYGEN VALVE HAD A FUNCTIONAL TEST, ON 06/07/2006. THE WORK WAS ACCOMPLISHED ON WO 06-5301. THIS COMPONENT LEAKED OXYGEN WHEN INSTALLED. (K) 20070118000782007011800078 2007 1 18 2007FA0000016 120061214G35004357B VALVE OXYGEN SYSTEM LEAKING B O OTHER O OTHER NRNOT REPORTED 1 SW15WP1R OXYGEN VALVE HAD A FUNCTIONAL TEST ON 09/25/2006. THE WORK WAS ACCOMPLISHED ON WO 06-5970. THIS COMPONENT LEAKED OXYGEN WHEN INSTALLED. (K) 20070118000922007011800092 2007 1 18 2007FA0000019 120061214G350029909256B VALVE OXYGEN SYSTEM LEAKING B WP1RO OTHER O OTHER NRNOT REPORTED 1 SW15 OXYGEN VALVE HAD A FUNCTIONAL TEST ON 06/07/2006. THE WORK WAS ACCOMPLISHED ON WO 06-5775. THIS COMPONENT LEAKED OXYGEN WHEN INSTALLED. (K) 20070118001252007011800125 2007 1 18 2007FA0000020 120061214G35004357B VALVE OXYGEN SYSTEM LEAKING B WP1RO OTHER O OTHER NRNOT REPORTED 1 SW15 OXYGEN VALVE WAS INSPECTED ON 10/09/2006. THE WORK WAS ACCOMPLISHED ON WO 066023. THIS COMPONENT LEAKED OXYGEN WHEN INSTALLED. (K) 20070116000342007011600034EU 2007 1 16 2007FA0000021 120061127G5100 PIN AIRBUSA340 A340* EU MISMANUFACTURED B VS6YO OTHER O OTHER NRNOT REPORTED 1 EA35 VARIOUS TWO OCCURRENCES OF A RETAINING PIN HOLDING THE UNIVERSAL-JOINT TOGETHER, HAVING INSUFFICIENT PEENING TO RETAIN THE PIN, HAS BEEN IDENTIFIED IN BUILD OF THE UNIT BY THE ACTUATOR/DRIVE SHAFT MFG. THE PIN IS THEREFORE NOT SUFFICIENTLY RETAINED AND MAY WALK OUT OF THE UNIVERSAL JOINT UNDER ACTUATION LOADS. THREE POTENTIALLY HAZARDOUS CONDITIONS HAVE BEEN IDENTIFIED. 1) THERE WILL BE A NR OF METAL PARTS FREE IN THE FUEL TANK- LIGHTNING STRIKE. 2) THE JOINT WILL FAIL AND PREVENT TRANSMISSION OF DRIVE THROUGH THE SHAFT TO THE ACTUATED VALVE. THE ACTUATED VALVE WILL FAIL TO OPERATE, BUT A POSITIVE ACTUATION WILL BE INDICATED TO THE FLIGHT CREW. MONITORING OF THE FUEL CONTENTS WILL BE REQUIRED TO VERIFY THAT THE C2L74 4F RTA197 20070118000952007011800095SW 2007 1 18 2007FA0000024 120061130G5520F3114 BEARING MOONEYM20 M20G 5870316SW LYC O360 O360A1D 41514EA HARTZLHCC2Y HCC2YK1 GL ELEVATOR ROD ENDFROZEN B DPPRO OTHER O OTHER NRNOT REPORTED 1 WP25684MA 680005 RL2292836A ELEVATOR PUSH ROD END BEARING (PHF31-14, FOUND TO BE FROZEN FROM RUST AND GRIME. ROD END BEARING BROKE AT THREADED PORTION DUE TO LACK OF MOVEMENT. AD 73-21-01 ADDRESSES LUBRICATION OF ALL CONTROL AND LANDING GEAR ROD END BEARINGS BUT DOES NOT ADDRESS INSPECTION OF OPERATION AND FREEDOM OF MOVEMENT. SERVICE INSTRUCTION M20-106 GIVES A GOOD INSPECTION OF PRIMARY FLIGHT CONTROL/ JOINTS. THAT SHOULD BE INCORPORATED INTO THE INSPECTION MANUAL AND/OR AD. (K) 1L71 3O3 O 2A3 E286 5 CP920 20070116000532007011600053CE 2007 1 16 2007FA0000025 120060725G251007140593 SEAT BACK CESSNA172 172N 2072434CE LYC O320 O320* 41508EA COCKPIT BROKEN B BIIRO OTHER O OTHER NRNOT REPORTED 1 EA21733BE4070 17268161 INSPECTED SEATS IAW AD 87-20-03R2 FOUND PILOTS SEAT BOTTOM ASSY BROKEN AT LEFT FWD ATTACH POINT AND RT FWD CRACKED. (K) 1H71 3O3 ONT3A12 E274 20070111001392007011100139SO 2007 1 11 2007FA0000026 120061211G8011MZ6222 STARTER PIPER PA28 PA28161 7102803SO LYC O320 O320D3G 41508EA ENGINE BROKEN B BIIRO OTHER O OTHER NRNOT REPORTED 1 EA219089N600 2816003 L1624939A WHEN STARTING AIRCRAFT, MADE LOUD NOISE AT STARTER. INSPECTED AND FOUND BENDIX SHATTERED. (K) 1L71 3O3 O 2A13 E274 20070112000022007011200002EA 2007 1 12 2007FA0000027 220061204G8530 PISTON CESSNA150 152 2071835CE LYC O235 O235N2C 41505EA MCAULY1A103 1A103TCM GL NR 3 CYLINDER INOPERATIVE D O OTHER O OTHER NRNOT REPORTED 1 GL11942861762 15285639 L2404715 VH43067 NR 3 CYLINDER PISTON DOES NOT MOVE IN CYLINDER WHEN YOU TURN PROPELLER. (K) 1H71 3O3 ONT3A19 E223 5 NP50GL 20070111001412007011100141SO 2007 1 11 2007FA0000028 220061229G85506566161 DIPSTICK AMTR LANCARLC41550FG 5150001GL CONT O550 TSIO550C SO ENGINE SEPARATED B O OTHER O OTHER NRNOT REPORTED 1 EA21442TA189 41532 802791 THE OIL GAGE ASSEMBLY (DIPSTICK) SEPARATED AT THE UPPER SWEDGED JOINT. (K) 1L71 3O3 ORTEXPA1L71E5SO 20070111001402007011100140SO 2007 1 11 2007FA0000029 120061219G3210AN411A BOLT PIPER PA28 PA28161 7102803SO LYC O320 O320D3G 41508EA SNSNCH70C 70CM6 EA MLG CORRODED D O OTHER O OTHER NRNOT REPORTED 1 SO158156T8236 288016219 L9820394 A549B2 WHILE WASHING AC, SCRUB BRUSH NOCKED OFF NUT AND ENGAGED PORTION OF ONE OF THE (AN4-11A) BOLTS THAT SECURES THE RT MLG ASSY TO THE RT WING. BOLT WAS CORRODED ALL THE WAY ACROSS ITS CROSS SECTION. SUGGESTIONS: PERIODICALLY CHECK TORQUE ON THESE BOLTS TO ENSURE BOLT NOT CORRODED THROUGH LIKE THIS ONE. REPLACE THES BOLTS PERIODICALLY TO PRECLUDE CORROSION FAILURE. (K) 1L71 3O3 O 2A13 E274 5 NP28NE 20070111001342007011100134CE 2007 1 11 2007FA0000030 120061215G214083D59 VALVE JANITROL BEECH 95 95B55 1152729CE CONT O470 IO470* 17026SO CABIN HEATER FAILED D O OTHER O OTHER NRNOT REPORTED 1 NE033845L TC2378 FOUND THERMOSTAT WORKING, BUT FUEL SOLENOID NOT STOPPING FUEL DELIVERY EVEN WITH POWER TO VALVE DISTUPTED. CABIN HEATER ONLY SHUTDOWN WHEN OVERHEAT SWITCH OPENED. VALVE INFO: MODEL NR 4400B. 1L72 3O3 ORT3A16 E1CE 20070125001992007012500199CE 2007 1 25 2007FA0000033 120061219G8011MZ4220 STARTER BEECH 76 76 1153005CE LYC O360 O360A1G6D EA ENGINE INTERMITTENT B BIIRO OTHER O OTHER NRNOT REPORTED 1 EA216015639 ME147 L56171A REPEATED TRYS, BENDIX FAILED TO ENGAGE. LUBRICATED AND INSPECTED BENDIX, FAILS TO ENGAGE EVERY OTHER TIME. IT STARTS (1) TIME THEN FAILS. (K) 1L72 3O3 O A29CE E286 20070125002002007012500200CE 2007 1 25 2007FA0000034 120061124G80119301001 DRIVE GEAR LAMAR CESSNA172 172S 2072439CE LYC O360 IO360A1A 41514EA STARTER FAILED D O OTHER O OTHER NRNOT REPORTED 1 EA05856SP 85007449 172S8124 STARTER WAS REMOVED AFTER THE DRIVE GEAR BROKE INTO PIECES AND JAMMED STARTER FROM TURNING. COMPLETE STARTER WAS REPLACED WITH REBUILT ASSEMBLY. SUB-PART (BENDIX DRIVE) IS PN 9301001. THIS MECHANIC HAS SEEN THIS FAILURE 4 TO 5 TIMES. BOTH 12 AND 24 VOLT UNITS. (K) 1H71 3O3 ONT3A12 1E10 20070125001962007012500196CE 2007 1 25 2007FA0000035 120061203G3350645402500 RHEOSTAT LEAR 35 36LEAR 5170601CE GARRTTTFE731TFE731* 01518WP COCKPIT SHORTED D ESPRO OTHER B SMOKE/FUMES/ODORS/SPARKS CLCLIMB 1 SO1171PG 013 SOON AFTER TAKEOFF, THE CREW DETECTED A AN ELECTRICAL SMELL. AFTER ATTEMPTING AND FAILING TO ISOLATE SOURCES. THEY ELECTED TO RETURN TO DEPARTURE. AIRPORT, AND LANDED UNEVENTFULLY. THERE WAS NO EMERGENCY DECLARED. MAINTENANCE REPLACED EL RHEOSTAT IAW MM. (K) 2L72 4F4 F A10CE E6WE 20070126000082007012600008NE 2007 1 26 2007FA0000037 220060915G72503360097050 SHAFT CFMINT AIRBUS320 A320211 3930320EU GE CFM56 CFM565A 13802NE LP TURBINE SEIZED D O OTHER O OTHER NRNOT REPORTED 1 SO19SUPBD 55X31147 ENGINE WAS REMOVED FROM AC, ENG POSITION 1 FOR A SUSPECTED LPT SHAFT FAILURE. ENG FAILED ON 9/15/2006 AND WAS REMOVED ON 12/3/2006. ENG WAS INPUT ON 1/2/2007 FOR DISASSEMBLY. ON RECEIPT OF ENG, IT WAS NOT POSSIBLE TO CARRY OUT A BORESCOPE INSP OF CORE AS IT WAS SEIZED AND WAS UNABLE TO ROTATE. ON ROTATION OF FAN LPC SYSTEM IT WAS FOUND THAT LPT SYSTEM WAS NOT ROTATING. DUE TO EXTENT OF DEBRIS FOUND IN LPT FROM FAILED LPT ROTOR BLADES AND VANES, IT WAS ALSO NOT POSSIBLE TO ROTATE IT INDEPENDENTLY. ENG HAD SUFFERED MAJOR FAILURES ON FOLLOWING COMPONENTS: LPT SHAFT, NR 4 BRG, CENTER VENT TUBE, HPT BLADES, LPT STAGE 1 VANES, LLPT ROTOR BLADES AND VANES ALL STAGES. FURTHER DISASSEMBLY OF MODULES WILL EXPOSE 2L72 4F4 FRTA28NM E29NE 20070122000472007012200047 2007 1 22 2007FA0000044 420061109G3417702490031304 ADC LEAR 35 35LEAR 5170600CE GARRTTTFE731TFE73122B 01518WP COCKPIT DEFECTIVE B BSYRO OTHER O OTHER NRNOT REPORTED 1 GL071140A 35045 DURING PREFLIGHT THE PILOTS ALTIMETER WAS FLAGGED. THE ADC WAS FOUND TO BE DEFECTIVE AND REPLACED. THE SYSTEM WAS TESTED AND INSPECTED AND FOUND TO COMPLY WITH FAR 91 AND TO REMAIN RVSM COMPLAINT. THERE HAS BEEN ONE PRIOR FAILURE REPORTED ON THIS SYSTEM REPORTED ON 11-11-2005. (K) 2L72 4F4 F A10CE E6WE 20070122000482007012200048 2007 1 22 2007FA0000045 420061116G34178220839429 ADC LEAR 60 60LEAR 5170707CE PWA 305 PW305 NE LT AFT AVIONICS MALFUNCTIONED B BSYRO OTHER O OTHER NRNOT REPORTED 1 GL07160AN 126 THE FLIGHTCREW REPORTED INTERMITTENT LOSS OF ADC INFORMATION ON THE CAPTAIN`S PFD. THE PRIMARY AIR DATA COMPUTER WAS FOUND TO BE DEFECTIVE AND WAS REPLACED. THE SYSTEM WAS TESTED AND INSPECTED IAW MM AND WAS FOUND TO COMPLY WITH FAR 91.411, PART 43 AND RVSM ADC INSPECTIORS. THE AIRCRAFT REMAINS RVSM COMPLAINT. (K) 2L72 4F4 FRTA10CE E35NE 20070125002402007012500240NM 2007 1 25 2007FA0000053 120061128G32504I29R12 HOUSING SARGENT BOEING737 737* NM STEERING VAVLE CRACKED B IU6RO OTHER O OTHER NRNOT REPORTED 1 NM01 1106 (REF NR: 213227/FXS) BODY CRACKED IN CHECK VALVE PORT. OVERPRESSURE/ CYCLIC STRESS, REDESIGN BODY. (K) 2L72 4F RTA16WE 20070125000352007012500035CE 2007 1 25 2007FA0000055 120061212G29101114174S0102 HYDRAULIC LINE CESSNA182 TR182 2072735CE LYC O540 O540* 41532EA NLG FAILED D O OTHER K FLUID LOSS APAPPROACH 1 SO035091S R18201503 HYDRAULIC HOSE ON RETRACT SIDE OF NOSE GEAR ACTUATOR FAILED AS AIRCRAT WAS ON APPROACH AND GEARDOWN WAS SELECTED. RESULTED IN AIRCRAFT MAKING AN EMERGENCY GEARUP LANDING. AFTER AC WAS RECOVERED, INSPECTION OF HYDRAULIC SYSTEM REVEALED; TEFLON HYDRAULIC HOSE HAD COMPLETELY BLOW-OUT OF SWEDGED FITTING. NO SIGNS OF HOSE LEAKING PRIOR TO INCIDENT. (K) 1H71 3O3 O 3A13 E295 20070125001452007012500145SO 2007 1 25 2007FA0000060 120061228G2913HYC5005 PUMP PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA HYDRAULIC SYS INOPERATIVE D K NONE O OTHER NRNOT REPORTED 1 WP172PW 447995087 L10677T UPON EXAMINATION OF THE AIRCRAFT IN QUESTION ON THE RUNWAY (AIRPORT MANAGER) TO TAKE PHOTOS OF THE INTERIOR OF THE AIRCRAFT SO AS TO RECORD THE POSITIONS OF ENGINE, GEAR AND CIRCUIT BREAKERS. PIC SO THEY COULD BE RECORDED BEFORE BEING REPOSITIONED FOR SAFETY PURPOSES. AFTER THAT WAS DONE, THE EMERGENCY GEAR KNOB AND PULLED THE LANDING GEAR HYDRAULIC CB. THE AC WAS THEN HOISTED UP BY CRANE AND SLING AND THE GEAR CAME DOWN. WHILE THE AC WAS HOISTED, EXAMINED THE LAND GEAR DOWN LOCKS. ALL (3) WERE IN THE (DOWN AND LOCKED) POSITION. THE AC WAS THEN TOWED TO OUR HANGER WITHOUT ANY PROBLEMS. JACKED UP AC AND REPOSITIONED THE CONTROLS FOR A RETRACT TEST OF THE LANDING GEAR. UPON S3WITCHING BATTERY POWER TO (ON)1L72 3O3 O A19S0 E286 20070125001302007012500130 2007 1 25 2007FA0000061 120061228G8011ES6462751 STARTER ENGINE LEAKING B WS9RK NONE O OTHER NRNOT REPORTED 1 NM07 2 STARTER LEAKING OUT OF REAR OF STARTER PLATE. (K) 20070125003412007012500341NE 2007 1 25 2007FA0000062 220061004G725030606852 RETAINER ISRAEL1125 ASTRASPX 4500205EU GARRTTTFE731TFE73140 29001NE TURBINE SEPARATED D O OTHER A FLAME/FIRE TXTAXI/GRND HDL 1 WP071125S2445 134 P113218 ON 10/4/2006, 4TH AIRCRAFT EXPERIENCED A LT ENGINE EXHAUST FIRE AFTER ENGINE START AND PRIOR TO DEPARTURE. ENGINE WAS REMOVED AND RETURNED TO MFG FOR REPAIR. ENGINE WAS DISASSEMBLED IAW LMM 72-03-06, REV 8 FOR ENGINEERING INVESTIGATION. DISASSEMBLY FINDINGS REVEALED PINS SECURING THE DEFLECTOR SHROUD TO THE RETAINER RING OF THE LPT2 STAGE NOZZLE RETAINER BECAME DISLODGED AND EXHIBITED CONTACT FRETTING WITH MATERIAL LOSS ON THE OUTER RETAINER. THE ENGINE FIRE MAY HAVE RESULTED FROM THE LPT2 STAGE RETAINER PINS DISLODGING WHICH MAY HAVE LOCCKED UP THE N1 ROTATING GROUP AND PREVENTED THE N1 GROUP FROM OBTAINING GROUND IDLE WITH EXCESSIVE RAW FUEL. SB INCORPORATED IMPROVED HARDWARE AND PROVIDES INSTRUCTIONS FO2L72 4F4 FRTA16NM E1NM 20070131001152007013100115 2007 1 31 2007FA0000066 420060501G23301302045100 MONITOR CABIN MALFUNCTIONED B BT7YK NONE O OTHER ININSP/MAINT 1 EA35 POTENTIAL FOR SMOKE IN THE CABIN CAUSED BY FAILURE OF ELECTRONIC COMPONENT WITHIN IFE SCREENS. WHILE CARRYING OUT THE REPAIR OF 6.4 LCD IN ARM AND SEAT BACK UNITS, WORKSHOP TECHNICIANS NOTED DAMAGE TO A CAPACITOR (LABELED AS C100) ON THE CIRCUIT CARD ASSY (CCA) WITHIN THE LCD. ALTHOUGH THE UNIT WAS NOT REMOVED FROM AC FOR THIS DEFECT AND THE FAILURE OF THE COMPONENT DOES NOT APPEAR TO HAVE A DETRIMENTAL AFFECT TO THE PERFORMANCE OF THE UNIT, IT IS CONSIDERED THAT THE DAMAGE TO THE CCA IS SEVERE ENOUGH TO POTENTIALLY CAUSE SMOKE IN THE CABIN. AT THE TIME IT WAS CONSIDERED A ONE-OFF INCIDENT AND THE WHOLE CCA WAS CHANGED. THE THE CCA PN AFFECTED 1302160-102 AND 1302160-103. NO DETAILED CIRCUIT DIAGRAMS OF TH 20070131000072007013100007 2007 1 31 2007FA0000067 420060501G23301302046100 MONITOR CABIN MALFUNCTIONED B BT7YO OTHER O OTHER NRNOT REPORTED 1 EA35 POTENTIAL FOR SMOKE IN THE CABIN CAUSED BY FAILURE OF ELECTRONIC COMPONENT WITHIN IFE SCREENS. WHILE CARRYING OUT THE REPAIR OF 6.4 LCD IN ARM AND SEAT BACK UNITS, WORKSHOP TECHNICIANS NOTED DAMAGE TO A CAPACITOR (LABELED AS C100) ON THE CIRCUIT CARD ASSY (CCA) WITHIN THE LCD. ALTHOUGH THE UNIT WAS NOT REMOVED FROM AC FOR THIS DEFECT AND THE FAILURE OF THE COMPONENT DOES NOT APPEAR TO HAVE DETRIMENTAL AFFECT TOT HE PERFORMANCE OF THE UNIT, IT IS CONSIDERED THAT THE DAMAGE TO THE CCA IS CONSIDERED A ONE-OFF INCIDENT AND THE WHOLE CCA WAS CHANGED. THE CCA PN AFFECTED 1302160-102 AND 1302160-103. NO DETAILED CIRCUIT DIAGRAMS OF THE CCA ARE AVAILABLE AS IT IS DEEMED TO BE A NON REPAIRABLE ITEM BY THE OEM. AS A 20070131000812007013100081GL 2007 1 31 2007FA0000068 120060521G3230194652 SPRING BLANCA17 1731A 1220435GL LYC O540 IO540K1E5 41532EA NLG WEAK D O OTHER O OTHER LDLANDING 1 SW15147461944 7532156 L1214948 AFTER AN INFLIGHT LANDING GEAR POWER PACK FAILURE, THE PILOT WAS UNABLE TO PERFORM AN EMERGENCY NOSE GEAR EXTENSION EVEN THOUGH THE MAIN GEAR WAS SAFELY EXTENDED. DURING LANDING ROLLOUT, THE NOSE GEAR FOLDED CAUSING DAMAGE TO THE PROPELLER AND ENGINE. AN UNSAFE NOSE GEAR INDICATION WAS SHOWN IN THE COCKPIT PRIOR TO LANDING. PILOT STATES HE DID NOT DO (SHARP PULLUPS) AS CALLED OUT IN THE FLIGHT MANUAL IN AN ATTEMPT TO DOWNLOCK THE GEAR. A NEW POWER PACK WAS INSTALLED, THE AIRCRAFT WAS PLACED ON JACKS AND NUMEROUS NORMAL AND EMERGENCY EXTENSIONS WERE PERFORMED, ALL WITHOUT INCIDENT, A COMPLETE CHECK WAS MADE OF THE GEAR RIGGING AND WAS FOUND CORRECT IAW MM. THE NOSE GEAR EXTENSION SPRING WAS REMOVED AND THE 1L71 3O3 O A18CE 1E4 20070129003582007012900358EU 2007 1 29 2007FA0000069 120061226G2400ZN7168752608 RELAY SOCATATB20 TB20TRINIDAD8680695EU LYC O540 IO540* 41532EA ELECTRICAL SYS FAILED D VJBSO OTHER O OTHER NRNOT REPORTED 1 EA091913S8 1913 IT SEEMS THAT THE DEMAND OF THIS RELAY IN THE LANDING GEAR SYSTEM IS GREATER THAN THE DESIGNED LOAD USEAGE OF THE CURRENT RELAY. WOULD RECOMEND A HEAVIER DUTY RELAY, WHICH MFG HAS SINCE MADE AVAILABLE. (K) 1L71 3O3 ORTA51EU 1E4 20070220000142007022000014SO 2007 2 20 2007FA0000093 220061225G8520 CRANKSHAFT BLANCA17 1730A 1220433GL CONT O520 IO520K 17032SO ENGINE BROKEN D O OTHER O OTHER APAPPROACH 1 SW1314690 7430637 224035R CRANKSHAFT IS BROKEN IN AREA OF NR6, NR5 ROD JOURNAL. CRANKSHAFT BROKE ON APPROACH TO LANDING AS PROP RPM CONTROL WAS ADVANCED ON SHORT FINAL. ENGINE POWER UNDER VERY LOW POWER. ENGINE HAS NOT BEEN DISASSEMBLED YET. THERE IS ALREADY AN AD NOTE TO TAKE THESE SHAFTS OUT OF SERVICE. IT WAS A NON VAR SHAFT. (K) 1L71 3O3 O A18CE E5CE 20070214000572007021400057 2007 2 14 2007FA0000094 420060929G3417702490031304 ADC LEAR 35 35A 5170602CE GARRTTTFE731TFE731* 01518WP FWD AVIONICS BAYFAILED B BSYRO OTHER O OTHER NRNOT REPORTED 1 GL07813AS 167 WHILE ENROUTE, THE PILOTS ALTIMETER FLAGGED AND OVERSPEED HORN TRIGGERED. THE ADC BEGAN TO WORK AGAIN AT THE END OF THE FLIGHT. THE ADC WAS FOUND TO BE DEFECTIVE AND REPLACED. THE SYSTEM WAS TESTED AND INSPECTED AND FOUND TO COMPLY WITH FAR 91-411, PART 43 AND TO REMAIN RVSM COMPLIANT. THERE HAS BEEN 2 PRIOR REPORTED FAILURES OF ADC`S IN THIS AIRCRAFT DATED MAY 6, 2005 AND NOV 21, 2005. (K) 2L72 4F4 F A10CE E6WE 20070131000642007013100064CE 2007 1 31 2007FA0000097 120061201G5520243400018 ELEVATOR LEAR 35 36LEAR 5170601CE GARRTTTFE731TFE731* 01518WP RIGHT SEPARATED C O OTHER D INFLIGHT SEPARATION NRNOT REPORTED 1 EA2126FN 12042 011 RT ELEVATOR DEPARTED THE AIRCRAFT AS THE AIRCRAFT EXPERIENCED AND APPROXIMATELY 70 DEGREE BANK, 50-60 DEGREE NOSE DOWN TURN. THE PILOT WAS FLYING IN A FORMATION AND WAS BLINDED BY THE SUN AND TURNED AWAY FROM OTHER AIRCRAFT. AS THE ELEVATOR CAME OFF OF THE HORIZONTAL STABILIZER IT TOOK BOTH HINGE BRACKETS AND THE BELLCRANK ASSY WHERE THE PUSHROD TUBE ATTACHES. BOTH THE HORIZONTAL SKIN AT THE OB END AND THE VERTICAL CAP WHERE BELLCRANK ASSY IS LOCATED ARE TORN AND DAMAGED. FURTHER INVESTIGATION IS IN PROGRESS INCLUDING AN ALIGNMENT AND SYMMETRY INSPECTION OF THE AIRCRAFT. STRESS WILL BE EVALUATING THESE NR TO DETERMINE THE CAUSE AND THE VIABILITY OF THE AIRFRAME FOR REPAIR. ATTACHED IS THE IRREGULARITY REPO2L72 4F4 F A10CE E6WE 20070131001052007013100105SO 2007 1 31 2007FA0000098 120061130G27106755000 SUPPORT BRACKET PIPER PA28 PA28R200 7102811SO LYC O360 IO360A1A 41514EA RT AILERON CRACKED D K NONE O OTHER ININSP/MAINT 1 GL034509X9000 28R7635067 CRACKS IN AILERON BELLCRANK LOWER SUPPORTS BOTH LT AND RT. LOOK REAL CLOSE ON INSPECTION BECAUSE NUT AND WASHER COVER AREAS. (K) 1L71 3O3 O 2A13 1E10 20070213001772007021300177 2007 2 13 2007FA0000099 120061109G610016160DTM PROPELLER MCAULY1C160 1C160DTM GL CRACKED B F3PRO OTHER O OTHER NRNOT REPORTED 1 SW15 4818 726964 CRACK DETECTED LENGTHWISE AT 9 INCH STATION. LATEST LOGBOOK ENTRY FOR TSOH, DATED 7-28-2005. (SW15200706340) (K) 5 NP910 20070213001602007021300160CE 2007 2 13 2007FA0000100 120061204G3210ART73 ROD END MTSBSIMU2 MU2B36A 5780413CE GARRTTTPE331TPE331* 01514WP MLG BROKEN B IZ2RO OTHER O OTHER NRNOT REPORTED 1 SW15777LP10166 719SA DURING GEAR EXTENSION FOR LANDING, A LOUD BANG WAS NOTICED BY THE PIVOT AND UNSAFE LIGHT STAYED ON. AIRCRAFT WAS ROUTED TO MAINTENANCE AFTER LANDING. MAINTENANCE FOUND ROD END ART -7E ON SHAFT HAD COME APART ANDALLOWED DOORS TO BECOME DISCONNECTED FROM ACTUATOR. (SW15200706339) (K) 1H72 3T3 T A10SW E2WE 20070213000592007021300059NE 2007 2 13 2007FA0000110 120061125G541026007 STUD SKRSKYS76 S76C 8143008NE TMECA ARRIELARRIEL1 60030NE RT NACELLE DOOR BROKEN D K NONE DC INFLIGHT SEPARATION F.O.D. ININSP/MAINT 1 EA2588CP 310 760500 20542 ON POST-FLIGHT INSPECTION, MAINTENANCE CREW FOUND NR 2 ENGINE COMPRESSOR FOD. WE DISCOVERED A MISSING COWL FASTENER STUD IPC ITEM 16 FIG 53-20-03 PAGE 0. WHEN FASTENER FAILS, THE LOCKING TAIL OF STUD FALLS INSIDE THE ENGINE AIR PLENUM AND THEN INGESTED BY ENGINE. THIS TYPE OF FASTENER SYSTEM IS USED THROUGH OUT S76 ENGINE AIR PLENUM AREA. THIS IS OUR 4TH EVENT OF THIS TYPE OF FAILURE CAUSING ENGINE FOD. SUGGEST A BETTER QUALITY FASTENER THAT REMAINS INTACT UPON FAILURE, TO HELP PREVENT ENGINE FOD. (K) 1G72 3U3 UNCH1NE E19EU 20070213000582007021300058NE 2007 2 13 2007FA0000111 120061215G2497SPC38G CAP SKRSKYS76 S76C 8143008NE TMECA ARRIELARRIEL1 60030NE INVERTER FILTER BURNED D O OTHER O OTHER NRNOT REPORTED 1 EA2588CP 3240 760500 INVERTER WIRING: THE CREW REPORTED THE NR 1 INVERTER CAUTION LIGHT WOULD NOT COME ON WHEN THE INVERTER WAS SELECTED OFF. AFTER VERIFYING THE PROPER VOLTAGE AT THE RDAU THE AIRCRAFT WAS RAN AGAIN AND THE INVERTER CAUTION LIGHT WAS FUNCTIONING NORMAL. UPON AIRCRAFT RETURN FROM A TRIP THE CREW REPORTED THE NR 2 INVERTER WAS FAILED BUT STILL SHOWED VOLTAGE INDICATION ON THE DISPLAY. AFTER TROUBLESHOOTING THE PROBLEM A SEVERELY BURNED AND MELTED WIRE WAS FOUND IN THE AC JUNCTION BOX. UPON REMOVAL OF THE AC JUNCTION BOX THE FOLLOWING WIRES WERE REPLACED. (THIS WAS THE SEVERELY BURNED WIRE). THE OTHER 2 WIRES LISTED WERE REPLACED DUE TO COLLATERAL DAMAGE FROM WIRE NR W1-036-0-22N THE INSULATION ON THESE 2 WIRES1G72 3U3 UNCH1NE E19EU 20070213000902007021300090WP 2007 2 13 2007FA0000116 220060828G725031081251 TURBINE BLADES GARRTTTPE331TPE33111U 01514WP ENGINE SEPARATED B O OTHER AJ FLAME/FIRE WARNING INDICATION NRNOT REPORTED 1 WP07 349 P44616C ENGINE WAS REPORTED TO HAVE FLAMES OUT OF TAILPIPE. TEARDOWN OF ENGINE SHOWS THAT A TURBINE BLADE HAD SEPARATED AT THE FIRTREE. BLADE DEBRIS CAUSED DAMAGE TO TURBINE OIL LINE, RESULTING IN A LEAK. TURBINE DISC WAS REBLADED AT LAST MAINTENANCE EVENT. TURBINE DISC/BLADES WERE PROVIDED TO MFG PROJECT ENGINEERING FOR MATERIAL ANALYSIS. (K) 4 T E4WE 20070213001372007021300137NM 2007 2 13 2007FA0000123 120060918G53206517684 INTERCOSTAL BOEING737 737300 1384610NM GE CFM56 CFM56* 13802NE BS 303 S10L CRACKED B I6XRK NONE O OTHER ININSP/MAINT 1 GL11586US53459 23931 CABIN STA 303.9 JUST ABOVE STRINGER 10L. INTERCOSTAL OUTER CHORD ANGLE, CRACKED. (K) 2L72 4F4 FRTA16WE E2GL 20070213001422007021300142NM 2007 2 13 2007FA0000124 120060926G5330654577266 SKIN BOEING737 737301 1384611NM GE CFM56 CFM56* 13802NE BS 860-885 GOUGED B I6XRK NONE O OTHER ININSP/MAINT 1 GL11586US53459 23931 UPPER FUSELAGE, STA 860 THRU 885, LBL 8 THRU RBL 8, UNDER DORSAL FIN BLADE SEAL, SKIN IS GOUGED. (K) 2L72 4F4 FRTA16WE E2GL 20070213001362007021300136NM 2007 2 13 2007FA0000125 120060926G5311654653146 FRAME BOEING737 737301 1384611NM GE CFM56 CFM56* 13802NE BS500A S8-9R CRACKED B I6XRK NONE O OTHER ININSP/MAINT 1 GL11586US53459 23931 UPPER FUSELAGE, BS 500A, BETWEEN STR 8R AND STR 9R, FRAME IS CRACKED AT PSU MOUNT. (K) 2L72 4F4 FRTA16WE E2GL 20070213001352007021300135NM 2007 2 13 2007FA0000126 120060927G531165465251 FRAME BOEING737 737301 1384611NM GE CFM56 CFM56* 13802NE BS 727 S14L CRACKED B I6XRK NONE O OTHER ININSP/MAINT 1 GL11586US53459 23931 FRAME IS CRACKED AT BODY STAION 727, STRINGER 14L. (K) 2L72 4F4 FRTA16WE E2GL 20070213001402007021300140NM 2007 2 13 2007FA0000127 120060918G53116546533 FRAME BOEING737 737301 1384611NM GE CFM56 CFM56* 13802NE BS 500A S8-9L CRACKED B I6XRK NONE O OTHER ININSP/MAINT 1 GL11586US53459 23931 MID CABIN, STA 500A FRAME, BETWEEN STRINGER 8 AND 9L, CRACKED AT PSU MOUNT RAIL ATTACH POINT. (K) 2L72 4F4 FRTA16WE E2GL 20070215002012007021500201NM 2007 2 15 2007FA0000128 120060927G53306552988 SKIN BOEING737 737301 1384611NM GE CFM56 CFM56* 13802NE BS 727 S14L DENTED B I6XRK NONE O OTHER ININSP/MAINT 1 GL11586US53459 23931 BODY STATION 915 ABOVE STRINGER 25L LAP JOINT FUSELAGE SKIN HAS DENT. (K) 2L72 4F4 FRTA16WE E2GL 20070301002162007030100216NM 2007 3 1 2007FA0000129 120060924G5315BAC1518399 FLOORBEAM BOEING737 737301 1384611NM GE CFM56 CFM56* 13802NE FUSELAGE GOUGED B I6XRK NONE O OTHER ININSP/MAINT 1 GL11586US53459 23931 CABIN FLOORBEAM, STA 827, WL 203.6, RBL 10, LOWER T-CAP, AFT FLANGE, GOUGED. (K) 2L72 4F4 FRTA16WE E2GL 20070213001412007021300141NM 2007 2 13 2007FA0000130 120060918G531169353521 FRAME BOEING737 737300 1384610NM GE CFM56 CFM56* 13802NE BS 400 S8R CRACKED B I6XRK NONE O OTHER ININSP/MAINT 1 GL11586US53459 23931 MID CABIN, STATION 400 FRAME AT STRINGER 8R, CRACKED AT PSU RAIL OUNT ATTACH POINT. (K) 2L72 4F4 FRTA16WE E2GL 20070213001392007021300139NM 2007 2 13 2007FA0000131 120060918G531065807351 CREASE BEAM BOEING737 737300 1384610NM GE CFM56 CFM56* 13802NE BS 947-992 S17R CORRODED B I6XRK NONE O OTHER ININSP/MAINT 1 GL11586US53459 23931 AFT GALLEY DOOR CREASE BEAM INNER CHORD ANGLE, BS 947 TO 992, STRINGER 17R, WL 208, CORROSION OUT OF LIMITS. (K) 2L72 4F4 FRTA16WE E2GL 20070213001612007021300161NM 2007 2 13 2007FA0000132 120060817G5315BAC1518399 FLOORBEAM BOEING737 737301 1384611NM GE CFM56 CFM56* 13802NE BS 312 CORRODED B I6XRK NONE O OTHER ININSP/MAINT 1 GL11586US53459 23931 CABIN BS 312, FROM LBL 55 TO RBL 55 WL 208, FLOORBEAM HAS LIGHT CORROSION. (K) 2L72 4F4 FRTA16WE E2GL 20070220001792007022000179NM 2007 2 20 2007FA0000133 120060924G531165465935 FRAME BOEING737 737301 1384611NM GE CFM56 CFM56* 13802NE FUSELAGE CRACKED B I6XRK NONE O OTHER ININSP/MAINT 1 GL11586US53459 23931 CABIN, BS 787, FRAME AT STR 8R, CRACKED AT STOW BIN ATTACH BRACKET. (K) 2L72 4F4 FRTA16WE E2GL 20070220001802007022000180NM 2007 2 20 2007FA0000134 120060924G53126545409245 PRESSURE PANEL BOEING737 737301 1384611NM GE CFM56 CFM56* 13802NE FUSELAGE CRACKED B I6XRK NONE O OTHER ININSP/MAINT 1 GL11586US53459 23931 MID CABIN BS 663, LBL 31, WHEEL WELL PRESSURE DECK WEB, CRACKED. (K) 2L72 4F4 FRTA16WE E2GL 20070227000802007022700080NM 2007 2 27 2007FA0000135 120060927G531165465251 FRAME BOEING737 737301 1384611NM GE CFM56 CFM56* 13802NE BS 727 S4L CRACKED B I6XRK NONE O OTHER ININSP/MAINT 1 GL11586US53459 23931 FRAME IS CRACKED AT BODY STATION 727, STRINGER 14L. (K) 2L72 4F4 FRTA16WE E2GL 20070301002062007030100206NM 2007 3 1 2007FA0000136 120060924G53206580736689 FITTING BOEING737 737301 1384611NM GE CFM56 CFM56* 13802NE FUSELAGE CORRODED B I6XRK NONE O OTHER ININSP/MAINT 1 GL11586US53459 23931 DOOR 1R, BS 306-312, WL 248-249, LBL 57-63, SERPENTINE PLATE CASTING CORRODED AROUND FASTENER HOLES. (K) 2L72 4F4 FRTA16WE E2GL 20070301002092007030100209NM 2007 3 1 2007FA0000137 120060918G5340693535214 STRINGER CLIP BOEING737 737300 1384610NM GE CFM56 CFM56* 13802NE FUSELAGE CRACKED B I6XRK NONE O OTHER ININSP/MAINT 1 GL11586US 23931 PASSENGER CABIN, STATION 639 AT STRINGER 4L, STRINGER CLIP, CRACKED. (K) 2L72 4F4 FRTA16WE E2GL 20070301002132007030100213NM 2007 3 1 2007FA0000138 120060918G5311 FRAME BOEING737 737300 1384610NM GE CFM56 CFM56* 13802NE FUSELAGE CRACKED B I6XRK NONE O OTHER ININSP/MAINT 1 GL11586US53459 23931 MID CABIN, STATION 480 FRAME, AT STRINGER 8L, CRACKED AT PSU MOUNT RAIL ATTACH POINT. (K) 2L72 4F4 FRTA16WE E2GL 20070301002182007030100218NM 2007 3 1 2007FA0000139 120060918G53116546533 FRAME BOEING737 737300 1384610NM GE CFM56 CFM56* 13802NE FUSELAGE CRACKED B I6XRK NONE O OTHER ININSP/MAINT 1 GL11586US 23931 MID CABIN, STATION 500A FRAME, BETWEEN STRINGER 8 AND 9L, CRACKED AT PSU MOUNT RAIL ATTACH POINT. (K) 2L72 4F4 FRTA16WE E2GL 20070301002172007030100217NM 2007 3 1 2007FA0000140 120060918G521069773671 SUPPORT BOEING737 737300 1384610NM GE CFM56 CFM56* 13802NE R2 DOOR CRACKED B I6XRK NONE O OTHER ININSP/MAINT 1 GL11586US 23931 AT FWD CABIN STA 328+6, DOOR 2R AFT STOP FTG INTERCOSTAL TEE SUPPORT, CRACKED. (K) 2L72 4F4 FRTA16WE E2GL 20070301002032007030100203CE 2007 3 1 2007FA0000142 120061126G5210MJV3 VALVE CESSNA500 550 2076604CE CABIN DOOR OUT OF POSITION E ON0AB EMER. DESCENT O OTHER NRNOT REPORTED 1 GL0550NF 5500636 AT G; 390 15A, -12 DEGREES CABIN DOOR SEAL DEFLATED NECESSATING AN EMERGENCY DESCENT TO 10,000 FT. AFTER 5-8 MINUTES, DOOR SEAL RE-INFLATED OPERATION WAS NORMAL, CONDITION DID NOT REOCCUR. FOUND DOOR SEAL VALVE WARM AIR TUBE BLAOCKED BY TAPE AND OUT OF POSITION. REMOVED TAPE, POSITIONED WARM AIR TUBE PROPERLY. (K) 1L72 4F A22CE 20070226001542007022600154CE 2007 2 26 2007FA0000143 120061126G27200510105207 CONTROL CABLE CESSNA172 172M 2072418CE LYC O320 O320* 41508EA RUDDER BROKEN D O OTHER F FLT CONT AFFECTED APAPPROACH 1 SO191653V4993 17263703 RUDDER CONTROL CABLE BRAKES DURING FLIGHT TRAINING WHILE PERFORMING FORWARD SLIP MANEUVER ON FINAL APPROACH. INITIAL INSPECTION SHOWS CABLE BROKE JUST FORWARD OF TERMINAL END AT THE LOWER BELL CRANK. FURTHER INSPECTION REVEALED THE CAUSE OF FAILURE TO BE CORROSION INSIDE THE STEEL CABLE (PN 0510105207). SINCE THE LOWER RUDDER BELLCRANK AREA IS EXPOSED TO THE ELEMENTS OUTSIDE OF THE AIRCRAFT, RECOMMENDATIONS IS TO REPLACE THE RUDDER CONTROL CABLE WITH STAINLESS STEEL TYPE (PN 0510105305) AVAILABLE FROM THE OEM. (K) 1H71 3O3 ONT3A12 E274 20070309003342007030900334SO 2007 3 9 2007FA0000152 220061020G8530SA52006A1 CYLINDER CESSNA207 207A 2073604CE CONT O520 IO520F 17032SO CRACKED B CY4RK NONE O OTHER ININSP/MAINT 1 AL03 900 PRESSURE TESTED AT 90 PSI WITH SOAPY WATER APPLIED TO EXHAUST SIDEWALL. AIR LEAKAGE NOTED BETWEEN FINS 19/20 & 20/21. (K) 1H71 3O3 O A16CE E5CE 20070309003352007030900335SO 2007 3 9 2007FA0000153 220061020G8530SA52006A1 CYLINDER CESSNA207 207A 2073604CE CONT O520 IO520F 17032SO CRACKED B CY4RK NONE O OTHER ININSP/MAINT 1 AL03 900 PRESSURE TESTED AT 90 PSI WITH SOAPY WATER APPLIED TO EXHAUST SIDE WALL. AIR LEAKAGE NOTED BETWEEN FINS 19/20 AND 20/21. (K) 1H71 3O3 O A16CE E5CE 20070309003362007030900336SO 2007 3 9 2007FA0000154 220061020G8530SA52006A1 CYLINDER CESSNA207 207A 2073604CE CONT O520 IO520F 17032SO CRACKED B CY4RK NONE O OTHER ININSP/MAINT 1 AL03 PRESSURE TESTED AT 90 PSI WITH SOAP WATER APPLIED TO EXHAUST SIDEWALL. AIR LEAKAGE NOTED BETWEEN FINS 19/20 AND 20/21. (K) 1H71 3O3 O A16CE E5CE 20070301002412007030100241CE 2007 3 1 2007FA0000160 120061216G551445A21085003 BRACKET BEECH BEECH MU300 400A 1155402CE PWA JT15 JT15D5 52112NE HORIZ STAB CRACKED B E81RK NONE O OTHER ININSP/MAINT 1 GL0393XP 7251 RK74 DURING INSPECTION OF HORIZONTAL STABILIZER ROLLER BRACKETS AND STRUCTURE IAW COMMUNIQUÉ NR 70, FOUND LT HORIZONTAL STABILIZER FWD ROLLER BRACKET, PN 45A21085-003, AND LT AFT ROLLER BRACKET, PN 45A21086-003, BOTH CRACKED. MFG AC TECH SUPPORT BELIEVES IMPROPER VERTICAL STABILIZER TO ROLLER GAP CLEARANCES MAY BE CONTRIBUTING TO PROBLEM. INSPECTION AREA NOT CURRENTLY NOTED ON MM AND 5-20-02 INSPECTION GUIDES, REQUIRES BORESCOPE TO INSPECT UNDERLYING STRUCTURE. RECOMMEND A 1-TIME SB AND/OR SAIB. SHOULD BE ADDED TO INSPECTION GUIDES. (K) 2H72 4F4 FRTA16SW E25EA 20070301002512007030100251CE 2007 3 1 2007FA0000161 120061213G3310 TRANSISTOR CESSNA525 525 2076601CE WILINTFJ44 FJ44 66000GL COCKPIT SHORTED B E81RO OTHER O OTHER NRNOT REPORTED 1 GL0366AM 2398 5250160 INVESTIGATED COCKPIT OVERHEAD FLOODLIGHTS TRIPPING ASSOCIATED CB WHEN BATTERY POWER APPLIED TO AIRCRAFT. FOUND ATTACHING SCREW FOR QC001 TRANSISTOR SHORTING TO AIRFRAME. ALSO, FOUND RESISTOR NR150 ON THRUST ATTENTUATOR PC BOARD NZ017 BURNED. REPAIRS REQUIRED REPLACING QC001 TRANSISTOR AND BASE, INSULATING QC001 ATTACHING SCREW, REPLACING DIODE DC046, AND REPLACING PC BOARD JC045. RECOMMENDED FURTHER INVESTIGATION TO DETERMINE IF A FLEET PROBLEM REQUIRING MODIFICATIONS TO PREVENT TRANSISTOR ATTACHING SCREW FROM SHORTING TO AIRFRAME. (K) 1L72 4F4 FRTA1WI E3GL 20070309001692007030900169 2007 3 9 2007FA0000197 420060904G2565BACR12BU9B RING AIRCRUISERS BOEING727 72722C 138400FNM EVAC SLIDE ELONGATED D K NONE O OTHER ININSP/MAINT 1 SO01942UP 1128 19101 DURING ROUTINE C-CHECK INSPECTION OF FORWARD DOOR EMERGENCY ESCAPE SLIDE, THE SLIDE BUSTLE LATCH CHAIN WAS FOUND DETACHED FROM THE SPLIT RING. THE SPLIT RING HAD BECOME ELONGATED AND THE RING COILS HAD SEPARATED THUS ALLOWING THE CHAIN TO DETACH. THE SLIDE WOULD NOT HAVE INFLATED IF REQUIRED. THE SPLIT RING HAS BEEN REPLACED. (K) 2L73 4F A3WE 20070402002202007040200220CE 2007 4 2 2007FA0000198 120060726G5210511150480 BOLT CESSNA421 421C 2076016CE CONT O520 GTSIO520* 17032SO PAX DOOR CORRODED B AW4RK NONE O OTHER ININSP/MAINT 1 WP11485DS4783 421C0459 DURING ACCOMPLISHMENT OF ANNUAL INSPECTION, EXCESSIVE PLAY WAS NOTED AT AFT HINGE POINT OF UPPER MAIN CABIN DOOR. INVESTIGATION REVEALED THAT HINGE BOLT WAS BROKEN, HEAD OF BOLT COULD BE TURNED, BUT END WITH NUT WOULD NOT FOLLOW. TRIED TO REMOVE BOLT BUT WAS UNABLE TO REMOVE EITHER PIECE. ATTEMPTED TO REMOVE FORWARD BOLT AS THE WHOLE DOOR ASSY HAD TO BE REMOVED FOR FURTHER INSPECTION, BUT WERE UNABLE TO REMOVE IT EITHER. HAD TO FINALLY REMOVE HINGES FROM DOOR AND REMOVE HINGE SUPPORTS FROM THE FUSELAGE STRUCTURE. FOUND THAT THE BOLTS AND BUSHINGS IN THE HINGES WERE EXCESSIVELY CORRODED WHICH PREVENTED THEM FROM BEING REMOVED. IN ORDER TO DISASSEMBLE THE FWD HINGE, IT WAS NECESSARY TO HACKSAW OFF THE HEAD 1L72 3O3 O A7CE E7CE 20070309000442007030900044EA 2007 3 9 2007FA0000213 220060627G8520LW18372 CRANKCASE LYC O320D3G PIPER PA28 PA28161 7102803SO LYC O320 O320D3G 41508EA ENGINE CRACKED D K NONE K FLUID LOSS ININSP/MAINT 1 EA178391Y4648 280 RL1519539A 288116235 RL1519539A DURING 100 HOUR INSPECTION A CRACK WAS DISCOVERED ON RT CRANKCASE HALF. THE CRACK (APPROXIMATELY 1 INCH) ORIGINATED FROM A LOWER PARTING FACE BOLT HOLE AND SHOWED EVIDENCE OF OIL LEAKAGE ONTO MUFFLER SHROUD (BURNED OIL). SPECIFIC CAUSE OF CRACK UNKNOWN. 1L71 3O3 O 2A13 E274 20070309003372007030900337SO 2007 3 9 2007FA0000216 220060821G8530SA52006A1 CYLINDER CESSNA207 207A 2073604CE CONT O520 IO520F 17032SO CRACKED B CY4RK NONE O OTHER ININSP/MAINT 1 AL03 690 PENETRANT TEST INDICATES CRACKS BETWEEN FINS 20/21 ADJACENT TO THE EXHAUST SEAT AND BETWEEN 19/20 NEARER TO THE UPPER SPARK SPLUG SIDE OF THE EXHAUST CHAMBER. (K) 1H71 3O3 O A16CE E5CE 20070322000742007032200074SW 2007 3 22 2007FA0000239 120061020G33001220 LIGHT AIRTRCAT802 AT802 0390305SW FAILED F O OTHER B SMOKE/FUMES/ODORS/SPARKS AGAGRICULTURE 1 NM09 PULSELIGHT UNIT FAILED. EVALUATION OF FAILED UNIT REVEALED HIGH HEAT GENERATED WITHIN UNIT AND SIGNIFICANT BURNING. 1L71 3T NCA19SW 20070326000992007032600099NM 2007 3 26 2007FA0000248 120061216G2497 WIRE HARNESS DOUG MD80 MD83 3023681NM BS 905 CHAFED G A UNSCHED LANDING A FLAME/FIRE CLCLIMB 1 GL03 MAIN CABIN AT RT STATION 905 WIRING BUNDLE CHAFED THROUGH ON PARTITION CAUSING FIRE AND SMOKE DAMAGE. THE PARTITION AND THE WIRING BUNDLE LOCATIONS WERE INSTALLED AND POSITION AS PART OF AN EXECUTIVE CABIN INTERIOR MODIFICATION. 50 + WIRES, INTERIOR PANELS, INSULATION BLANKETS AND ONE CEILING RAIL WERE DAMAGED. 2L72 4F RT 20070507000082007050700008CE 2007 5 7 2007FA0000347 120061203G32203A07000001 SCREW CESSNA206 U206F 2073333CE CONT O520 IO520* 17032SO NLG DEPARTED D O OTHER O OTHER NRNOT REPORTED 1 EA078JZ U20602326 AIRCRAFT HAD GEAR UP LANDING, FOUND SCREW PN AN503-8-4 HAD FALLEN OUT. SCREW WAS TO BE SAFTIED, NO SAFETY WIRE FOUND. ONCE SCREW FELL OUT THE POWER PISTON HOUSING PN 3A07402-002 WAS ALLOWED TO FLEX DURING SUB CYCLES ALLOWING THE SCREW TO TEAR THE ORING ON THE HOUSING FLANGE AND PUMP ALL THE HYD (5606) FLUID OVERBOARD AND NOT ALLOWING THE MAIN GEAR THE EXTEND. THE SCREW HOLE WHERE THE SCREW FELL OUT ON THE PISTON HOUSING TORE OUT. REPLACED THE PISTON HOUSING PN 3A07000-001, ALL ORINGS AND INSTALLED NEW SCREWS PN AN503-8-4 AND SAFTIED. SWING LDG 6X`S AND RELEASED AIRCRAFT. (K) 1H71 3O3 O A4CE E5CE 20070504001672007050400167CE 2007 5 4 2007FA0000376 120060907G781002R3022406 EXHAUST DUCT BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA RT ENGINE CRACKED D K NONE O OTHER ININSP/MAINT 1 SO09 11322431 PCE85195 WHILE PERFORMING SCHEDULED MAINTENANCE,REMOVED LT ENGINE EXHAUST STACK TO FACILITATE INSPECTING THE EXHAUST DUCT. FOUND CRACK FOLLOWING THE CIRCUMFERENCE OF THE SKI SLOPE. THE EXHAUST DUCT HAD PWA SB 3380 COMPLIED WITH 431 HOURS EARLIER. POWER SECTION WAS REMOVED AND SENT FOR REPAIR. 1L72 4T4 T A24CE E4EA 20070613002222007061300222CE 2007 6 13 2007FA0000407 120060904G781002R3022406 EXHAUST DUCT BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA ENGINE CRACKED D K NONE O OTHER ININSP/MAINT 1 SO09 13769657 WHILE PREFORMING SCHEDULED MAINTENANCE,REMOVED EXHAUST STACKS TO FACILTATE INSPECTING THE EXHAUST DUCT.A CRACK WAS FOUND IN THE SKI SLOPE.POWER SECTION WAS REMOVED FOR REPAIR. 1L72 4T4 T A24CE E4EA 20070613002242007061300224CE 2007 6 13 2007FA0000409 120060812G781002R3022406 EXHAUST DUCT BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA ENGINE CRACKED D K NONE O OTHER ININSP/MAINT 1 SO09 14327979 WHILE PREFORMING SCHEDULED MAINTENANCE,REMOVED EXHAUST STACKS TO FACILTATE INSPECTING THE EXHAUST DUCT.A CRACK WAS FOUND IN THE SKI SLOPE.POWER SECTION WAS REMOVED FOR REPAIR. 1L72 4T4 T A24CE E4EA 20070604000022007060400002WP 2007 6 4 2007FA0000418 120060501G6210C0165 BLADE ROBSINR44 R44RAVENII 7640122WP MAIN ROTOR DEBONDED D EA ENGINE SHUTDOWN UNSCHED LANDING O OTHER CRCRUISE 1 SW99CFICL5 1 IN FLIGHT BREAK UP. HELICOPTER CRASHED KILLED 2 HUMANS. NO REACTION TIME TO LAND SAFELY, PILOT WAS EJECTED OUT OF SEAT BY BLADE, KILLED INSTANTLY. 1G71 3O H11NM 20070613002192007061300219CE 2007 6 13 2007FA0000424 120060820G781002R3022406 EXHAUST DUCT BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA ENGINE CRACKED D K NONE O OTHER ININSP/MAINT 1 SO09 139262030 WHILE PREFORMING SCHEDULED MAINTENANCE,REMOVED EXHAUST STACKS TO FACILTATE INSPECTING THE EXHAUST DUCT.A CRACK WAS FOUND IN THE SKI SLOPE.POWER SECTION WAS REMOVED FOR REPAIR. 1L72 4T4 T A24CE E4EA 20070613002132007061300213CE 2007 6 13 2007FA0000432 120060705G781002R3022406 EXHAUST DUCT BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA ENGINE CRACKED D K NONE O OTHER ININSP/MAINT 1 SO09 11753431 WHILE PREFORMING SCHEDULED MAINTENANCE,REMOVED EXHAUST STACKS TO FACILTATE INSPECTING THE EXHAUST DUCT.A CRACK WAS FOUND IN THE SKI SLOPE.THE EXHAUST DUCT SB 3380 HAD BEEN COMPLIED WITH 515.2 HOURS PRIOR.POWER SECTION WAS REMOVED FOR REPAIR. 1L72 4T4 T A24CE E4EA 20070613002202007061300220CE 2007 6 13 2007FA0000441 120060908G781002R3022406 EXHAUST DUCT BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA ENGINE CRACKED D K NONE O OTHER ININSP/MAINT 1 SO09 16012660 WHILE PREFORMING SCHEDULED MAINTENANCE,REMOVED EXHAUST STACKS TO FACILTATE INSPECTING THE EXHAUST DUCT.A CRACK WAS FOUND IN THE SKI SLOPE.POWER SECTION WAS REMOVED FOR REPAIR. 1L72 4T4 T A24CE E4EA 20070613001692007061300169WP 2007 6 13 2007FA0000449 120060501G6210C0165 BLADES ROBSINR44 R44RAVENII 7640122WP MAIN ROTOR DEBONDED C BE EMER. DESCENT ENGINE SHUTDOWN O OTHER CRCRUISE 1 SW99CFICL5 1 IN FLIGHT BREAK UP. HELICOPTER CRASHED KILLED 2 HUMANS. NO REACTION TIME TO LAND SAFELY, PILOT WAS EJECTED OUT OF SEAT BY BLADE KILLED INSTANTLY. 1G71 3O H11NM 20070605002142007060500214CE 2007 6 5 2007FA0000452 120061212G3600IU478003 PISTON CESSNA172 172M 2072418CE LYC O320 O320* 41508EA AIR PUMP FAILED D O OTHER O OTHER NRNOT REPORTED 1 NE019899Q65 17265843 L42B2427A INSTALLED A PISTON AIR PUMP (PN IU478-003, SER NR T568A) ON AUG 25, 2005. THE PUMP DRIVE COUPLING FAILED BY 12/06 WITH LESS THAN 66 HOURS ON IT. COUPLING FAILED INTERNALLY IN PUMP, WITH PLASTIC/SILICON DEBRIS IN ENG/DRIVE INTERFACE. (K) 1H71 3O3 ONT3A12 E274 20070808000592007080800059CE 2007 8 8 2007FA0000663 120061121G5740187504 CONTROL ARM BEECH 18 RC45J 1151021CE PWA R985 R985* 52008NE ELEVATOR CRACKED D O OTHER O OTHER NRNOT REPORTED 1 SO03145J 9544 51233 DURING COMPLIANCE WITH AD 77-19-07 PARA B, DYE PENETRANT INSPECTION REVEALED 2 POSSIBLE DEFECTS, 0.75 INCH AND 0.5 INCH LONG. BOTH INDICATIONS RADIATING FROM THE TAPERED PIN ON THE STARBOARD SIDE OF THE CONTROL ARM. INDICATIONS CONTINUED TO APPEAR AFTER REPEATED SURFACE POLISHING AND DYE PENTRANT, ALTHOUGH NO DEFINITIVE. OTHER DEFECTS AND/OR INDICATIONS OBSERVED. INDICATIONS MAY NOT ACTUALLY HAVE BEEN A CRACK, THE INTERMITTENT LINES MAY BE OLD SURFACE FLAWS. HOWEVER, IT WAS DECIDED THAT THE BEST COURSE OF ACTION WAS TO REPLACE PART. OLD PART DID HAVE THE SMALLER AN 386-3-18 TAPERED PINS, INSTEAD OF THE LARGER, AN 386-5-18 PINS USED ON THE LATER MFG ELEVATOR CONTROL ARMS, THIS MAY HAVE BEEN A CONTRIBUTING 1L72 3R3 R A765 5E1 20070906000422007090600042SW 2007 9 6 2007FA0000734 120060724G2424800397501 VOLT REGULATOR MOONEYM20 M20R 5870225SW CONT O550 IO550* SO FAILED D O OTHER O OTHER NRNOT REPORTED 1 GL25999JW296 290293 THE INABILITY OF THE VOLTAGE REGULATOR (PN 800397-501, SN 0165) TO CONTROLTHE OUTPUT OF THE ALTERNATOR WHEN THE BATTERY SWITCH WAS TOGGLED BETWEEN THE NR1 AND NR 2 BATTERY, IN FLIGHT. (K) 1L71 3O3 ORT2A3 E3SO 20070917000732007091700073 2007 9 17 2007FA0000756 420061112G256546FASA0303603 LIFE RAFT AMD FALC20FALCON 2720302EU GARRTTTFE731TFE73160 NE PARTIAL INFLATE B QLCRO OTHER O OTHER CRCRUISE 1 GL11191MC 282 THE LIFE RAFT VACUUM BAG INFLATED DUE TO CYLINDER LEAKAGE BETWEEN THE CYLINDER HEAD AND LIFE RAFT CYLINDER. THE AC WAS CRUISING AT 40,000 FT WHEN THE PILOT HEAR A LOUD POP. UPON INVESTIGATION, THE PILOT HAD DISCOVERED THE LIFE RAFT HAD AN UNCOMMANDED INFLATION. THE BANDS AROUND THE LIFE RAFT CONTAINER HELD THE LIFE RAFT TOGETHER AND IT WAS LATER REMOVED FROM UNDER THE COUCH. 2L72 4F4 F A7EU E1NM 20070917000682007091700068 2007 9 17 2007FA0000757 420061016G256546FASA2311323 LIFE RAFT PARTIAL INFLATE B QLCRO OTHER O OTHER NRNOT REPORTED 1 GL11 LIFE RAFT PARTIALLY INADVERTENTLY INFLATED IN CUSTOMERS AC CABIN AREA (UNDER SEAT CUSHION) WHICH COULD HAVE POSSIBLY CAUSED SEVERE DAMAGE TO THE AIRCRAFT, INJURY TO PERSONS OR LOSS OF AIRCRAFT CONTROL HAD LIFE RAFT COMPLETELY INFLATED IN-FLIGHT. THE LIFE RAFT WAS REMOVED FROM THE AIRCRAFT CABIN BY THE OPERATOR BEFORE IT HAD COMPLETELY INFLATED MINIMIZING THE POSSIBILITY OF SEVERE DAMAGE. IT WAS DETERMINED THAT THE INFLATION CYLINDER HEAD WAS LEAKING AT THE POINT WHERE IT ATTACHES TO THE INFLATION CYLINDER. THIS LIFE RAFT WAS NOT COVERED UNDER THE MFG SIL (SIL001STS) DATED 11/21/2005. (K) 20071204001062007120400106CE 2007 12 4 2007FA0000993 120060828G2750SM50D7 RELAY BEECH 200 B200 1152922CE TE FLAP MOTOR INTERMITTENT D O OTHER S AFFECT SYSTEMS DEDESCENT 1 WP19185XP514 BB952 DURING FLIGHT WHEN THE FLAPS SELECTED DOWN & DID NOT RESPOND. AIRCRAFT LANDED IN A FLAPS UP CONDITION & DELIVERED TO MAINTENANCE. INVESTIGATION REVEALED THE FLAP MOTOR POWER RELAY WAS OPERATING INTERMITTENTLY. A NEW FLAP MOTOR RELAY, PROCURED FROM RAPID (RAYTHEON PARTS INVENTORY AND DISTRIBUTION SYSTEM) WAS INSTALLED AND THE MALFUNCTION WAS RESOLVED. THE REMOVED / FAILED RELAY HAD BEEN IN SERVICE 22 MONTHS AND 514.5 FLIGHT HOURS. 1L72 4T A24CE 20060711001072006071100107EA 2006 7 11 2050506 220060621G7414 BUSHING LYC IO360A3B6D MOONEYM20 M20J 5870219SW LYC O360 IO360A3B6 41514EA MAGNETO DRIVE LACK OF LUBE B K NONE O OTHER ININSP/MAINT 1 NE01386OH 568 241044 L2178051A CRANKCASE WAS FIELD REPAIRED BY INSTALLING A BUSHING IN THE MAGNETO DRIVE GEAR BOSS. IT APPEARS THE OIL SUPPLY HOLE WAS NOT DRILLED IN THE BUSHING. THE BUSHING WAS STARVED FOR OIL AND METAL WAS FOUND IN THE OIL AND FILTER, THE BUSHING WAS LOOSE AND DAMAGED FROM OIL STARVATION. 1L71 3O3 O 2A3 1E10 20060512000632006051200063CE 2006 5 12 21200003AD 120060510G2730083200054 HINGE CESSNA421 421B 2076014CE ELEVATOR DAMAGED B O OTHER O OTHER DEDESCENT 1 SW991944G8307 421B0844 CUSTOMER REPORTED VIBRATION AT HIGH SPEEDS. INSPECTED AIRCRAFT AND FOUND CENTER ELEVATOR HINGE INBOARD AND OUTBOARD BRACKETS ELONGATED ON THE RIGHT ELEVATOR. INSTALLED CESSNA SERVICE KIT SK421-130B REPLACING ALUMINUM ELEVATOR HINGE BRACKETS WITH STAINLESS STEEL BRACKETS. 1L72 3O A7CE 20060803000602006080300060GL 2006 8 3 25869 320060725G6110 STRUCTURE MCAULY CESSNA172 172S 2072439CE LYC O360 IO360A1A 41514EA MCAULY1A170 1A170E GL PILOT BORE CRACKED B W59RK NONE O OTHER ININSP/MAINT 1 WP07428DW2099 TI014 172S8708 TI014 PROPELLER PILOT BORE FOUND CRACKED BY PENETRANT INSPECTION BEING PERFORMED DURING OVERHAUL 1H71 3O3 ONT3A12 1E10 5 NP857 20060516000912006051600091CE 2006 5 16 314901 120060511G3246314901 WHEEL CESSNA500 550 2076604CE MLG CRACKED B K NONE O OTHER ININSP/MAINT 1 SW07 FINDING FATIGUE CRACKS FORMING AT THE INTERSECTION OF THREADED HOLE AND DRILLED PASSAGE OF FUSE PLUG HOLE AND VALVE STEM HOLE. 1L72 4F A22CE 20060321002102006032100210CE 2006 3 21 3969 120060224G282000292000051 LINE BEECH 58 58 1152740CE ZONE 600 CHAFED B PAI5K NONE O OTHER ININSP/MAINT 1 SO056458C7236 TH1495 DURING SCHEDULED INSPECTION FOUND FUEL CROSSFEED LINE IN RT WHEEL WELL CHAFED 75 PERCENT THROUGH BY LANDING GEAR RETRACT ROD. 1L72 3O 3A16 20060315001382006031500138SO 2006 3 15 4381 120060207G242051530007B GCU PIPER PA30 PA30 7103002SO LT GEN INOPERATIVE B K NONE W INADEQUATE Q C ININSP/MAINT 1 NE031509 30798 AIRCRAFT CAME IN FOR GENERATOR PARALLELING. LEFT GENERATOR CONTROL UNIT NEEDED REPLACEMENT. INSTALLED OVERHAULED GCU S/N 10853A; GCU FAILED ON INITIAL RESET. INSTALLED SECOND GCU S/N 9183; GCU FAILED ON INITIAL RESET. (BOTH ABOVE GCU'S HAD JUST BEEN OVERHAULED BY PRECISION ELECTRONICS, INC., ATLANTA, GA FOR THE SAME INITIAL FAILURE PROBLEM). INSTALLED A THIRD GCU S/N 9657; WHICH FUNCTIONED CORRECTLY. (ALSO OVERHAULED BY PRECISION ELECTRONICS, INC.) 1L72 3O A1EA 20060315001742006031500174CE 2006 3 15 4381002 120060207G242051530007B GCU BEECH 200 B200 1152922CE LT GEN MALFUNCTIONED B K NONE W INADEQUATE Q C ININSP/MAINT 1 NE031509G BB1308 AIRCRAFT CAME IN FOR GENERATOR PARALLELING. LEFT GENERATOR CONTROL UNIT NEEDED REPLACEMENT. INSTALLED OVERHAULED GCU S/N 10853A; GCU FAILED ON INITIAL RESET. INSTALLED SECOND GCU S/N 9183; GCU FAILED ON INITIAL RESET. BOTH ABOVE GCU'S HAD JUST BEEN OVERHAULED BY PRECISION ELECTRONICS, INC., ATLANTA, GA FOR THE SAME INITIAL FAILURE PROBLEM. INSTALLED A THIRD GCU S/N 9657; WHICH FUNCTIONED CORRECTLY, ALSO OVERHAULED BY PRECISION ELECTRONICS, INC. 1L72 4T A24CE 20060512001282006051200128SO 2006 5 12 4437811 120060418G7160P151936 AIR FILTER PIPER PA32 PA32R301T 7103220SO ENGINE DEBONDED B K NONE O OTHER ININSP/MAINT 1 GL0930538 3257343 PN P560007-3, GASKET HAD SEPERATED FROM FILTER ON ONE SIDE AND WAS PULLED INTO THE AIR STREAM ON THE ENGINE SIDE OF THE FILTER. INSTALLED NEW FILTER. 1L71 3O A3SO 20061025001062006102500106EA 2006 10 25 5292S1006 220061013G8530 EXHAUST VALVE PIPER PA28 PA28140 7102802SO LYC O320 O320* 41508EA ENGINE SEPARATED D A UNSCHED LANDING YJ ENGINE STOPPAGE WARNING INDICATION CRCRUISE 1 CE075292S 2826923 PILOT REPORTED ENGINE VIBRATION FOLLOWED BY PROGRESSING LOSS OF POWER WHICH EVENTUALLY LED TO COMPLETE LOSS OF POWER AND ENGINE FAILURE. PILOT EXECUTED AN UNEVENTFUL EMERGENCY LANDING ON A PAVED STATE HIGHWAY. NO DAMAGE TO AIRCRAFT UPON LANDING. UPON EXAMINATION OF THE ENGINE, FOUND NR 3 CYLINDER EXHAUST VALVE HEAD FAILURE AND FRAGMENTS OF FAILED EXHAUST VALVE HEAD FOUND IN INDUCTION SYSTEM. 1L71 3O3 O 2A13 E274 20060413002602006041300260SO 2006 4 13 5784607 120060215G272063457003 ARM PIPER PA32 PA32300 7103212SO RUDDER CONTR BROKEN C O OTHER O OTHER TXTAXI/GRND HDL 1 GL194209R5100 3240574 ONE OF THE THE CLIPS (PIPER PN 62832-000) IN THE RUDDER TRIP TUBE YIELDED AND SLIPPED OVER THE END OF THE SPRING. THIS CAUSED THE RUDDER TRIM SPRING TO BIND IN ITS TUBE, RESULTING IN THE RUDDER CONTROL ARM (PIPER PN 63457-003) BREAKING WHERE THE TRIM ATTACHES. THIS CAUSED LOSS OF RUDDER TRIM AND NOSE-WHEEL CENTERING. RUDDER CONTROL AND NOSEWHEEL STEERING WERE UNAFFECTED.I HAVE PHOTOS OF THE FAILED PARTS I CAN EMAIL IF SOMEONE LET'S ME KNOW WHERE TO SEND THEM. 1L71 3O A3SO 20060724000302006072400030GL 2006 7 24 60806 320060608G6111FC7663R BLADE HARTZL LYC O540 IO540K1K5 41532NE HARTZLHCC3Y HCC3YR GL PROPELLER CRACKED D K NONE O OTHER ININSP/MAINT 1 SO17 854 854 EL223A 1800 EL223A CRACKED BLADE SHANK. 3 O 1E4 5 CP25EA 20060724000222006072400022GL 2006 7 24 608062 320060608G6111D68315A CLAMP HARTZL GULSTM500 500 0141K02SW LYC O540 O540* 41532EA HARTZLHCA2 HCA2MVK2 GL PROPELLER CRACKED D K NONE O OTHER ININSP/MAINT 1 SO17 1008 HWA49 791 HWA49 BLADE CLAMPS CRACKED. 1H72 3O3 ORT6A1 E295 5 CP24EA 20060724000242006072400024GL 2006 7 24 608063 320060608G6111D68315A CLAMP HARTZL GULSTM500 500 0141K02SW LYC O540 O540* 41532EA HARTZLHCA2 HCA2MVK2 GL PROPELLER CRACKED D K NONE O OTHER ININSP/MAINT 1 SO17 1008 HWA49 791 HWA49 BLADE CLAMP CRACKED. 1H72 3O3 ORT6A1 E295 5 CP24EA 20060518001802006051800180SW 2006 5 18 77669 120060301G6100 HUB HARTZL HCB3Z302 GULSTM680 680F 0141606SW HARTZLHCB3Z HCB3Z302 GL PROPELLER CORRODED B EY2RK NONE O OTHER ININSP/MAINT 1 GL03 CORRODED CLAMP ASSEMBLY, PN 838-17, SN J4324, U4701, U4646. CORRODED BLADES MODEL NR 9349, SN A41967, A41996, A41251. 1H72 3O 2A4 5 CP907 20060512000482006051200048GL 2006 5 12 77670 320060213G6110 CLAMP GULSTM680 680F 0141606SW HARTZLHCB3Z HCB3Z302 GL PROPELLER ASSY CORRODED B EY2RK NONE O OTHER ININSP/MAINT 1 GL03 CORRODED CLAMP ASSEMBLY PN 838-17, SN U5211, U5188, U5109. 1H72 3O 2A4 5 CP907 20060518001792006051800179GL 2006 5 18 78978 320060306G6114D7292C203 HUB CESSNA182 182 2072702CE MCAULY2A34C 2A34C203 GL PROPELLER CORRODED B EY2RK NONE O OTHER ININSP/MAINT 1 GL03 CORRODED HUB. 1H71 3O NT3A13 5 CP3EA 20060512000682006051200068GL 2006 5 12 79965 320060404G6114E71693 HUB BEECH 58 58 1152740CE HARTZLHCJ3Y PHCJ3YF2 GL PROPELLER CORRODED B EY2RK NONE O OTHER ININSP/MAINT 1 GL03 HUB CORRODED BEYOND REPAIR IAW MFG OVERHAUL MANUAL. 1L72 3O 3A16 5 CP36EA 20060224001582006022400158CE 2006 2 24 8862 120060115G324650107201 WHEEL BEECH MU300 400A 1155402CE PWA JT15 JT15D5 52112NE LT MLG MISOVERHAULED B YGJRC ABORTED TAKEOFF W INADEQUATE Q C TOTAKEOFF 1 GL17234DK 24 RK182 LT MAIN TIRE DISINTEGRATED ON T/O ROLL. AFTER REMOVING WHEEL ASSY, DISCOVERED WHEEL HALVES O-RING EXPOSED BY VALUE STEM. UPON INVESTIGATION DISCOVERED WHEEL WAS NOT OVERHAULED IAW A/C BRAKING SYSTEMS COMPONENT MM. INBOARD WHEEL HALF WAS NOT REMARKED IAW TEMPORARY REVISION NO. 32-6 TO COMPONENT MM MAIN WHEEL ASSY 5010720. UPON INVESTIGATION DISCOVERED THAT THE OTHER MAIN WHEEL INBOARD WHEEL WAS NOT REMARKED EITHER. THE SPARE WHEEL WHICH WAS OVERHAULED BY THE SAME REPAIR STATION WAS NOT MARKED EITHER. 2H72 4F4 FRTA16SW E25EA 20060324000042006032400004CE 2006 3 24 8921 120060303G2897281810613 RELAY LEAR 35 31 5170530CE FUEL PANEL SHORTED D O OTHER O OTHER NRNOT REPORTED 1 SW00XAJYC 30 LEFT ENGINE WOULD NOT START. TROUBLESHOT TO SHORTED RELAY ON FUEL RELAY PANEL. 2L72 4F RTA10CE 20060619002382006061900238EU 2006 6 19 AACSDR061006B 120060610G2150 LINE AIRCOM AGUSTAA109 A119 0261102EU AIR CONDITIONER MAINT ERROR B DT1RK NONE W INADEQUATE Q C ININSP/MAINT 1 EA17119RW 14508 AIR CONDITIONING SYSTEM STC NR SR00463DE UTILIZES RIGID FREON LINES RUNNING FORE AND AFT ON THE ENGINE DECK. AT THE FORWARD END, THESE LINES CONNECT TO FLEX LINES. AT THIS CONNECTION THE LINES WERE SWAPPED. THE CONNECTIONS ARE LOCATED RIGHT NEXT TO EACH OTHER AND THE LINES RUN PARALLEL, MAKING THIS A VERY EASY MISTAKE. THESE LINES SHOULD UTILIZE DIFFERENT FITTINGS TO PREVENT THIS FROM HAPPENING. 1G72 3U H7EU 20070511001542007051100154SW 2007 5 11 AACSDR121406 120061214G53023P5340A11951 LONGERON AGUSTAAB139 AB139 0260110SW PWA PT6 PT6* 52043EA TAILBOOM CRACKED B K NONE O OTHER ININSP/MAINT 1 EA17805HD 31051 DURING INSPECTION OF THE TAILBOOM ATTACHMENT POINTS, A CRACK ABOUT 1.5 INCHES LONG WAS DISCOVERED ON THE TOP LT LONGERON AT STA 8700MM. 2G72 6U3 T R00002RDE2NE 20060711001082006071100108 2006 7 11 AACSDR61006 120060610G53021090371231 LONGERON AGUSTA TAILBOOM CRACKED B DT1RO OTHER O OTHER CRCRUISE 1 EA1745HV 1900 A7093 DURING FLIGHT A BANG WAS HEARD, AIRCRAFT SHUDDERED MOMENTARILY, PILOT SUSPECTED BIRD STRIKE. FLIGHT CONTINUED TO LANDING SITE. AIRCRAFT WAS INSPECTED FOR DAMAGE, NO EVIDENCE OF BIRD STRIKE OR ANY DAMAGE WAS NOTED. DURING A SUBSEQUENT AIRFRAME INSPECTION LT UPPER TAILBOOM TO FUSELAGE FITTING WAS FOUND CRACKED. A/C AND COMPONENT TOTAL TIME APPROXIMATELY 1900.0 HRS. 20070511001522007051100152SW 2007 5 11 AACSDR61606 120060616G6510 DRIVE SHAFT AGUSTAAB139 AB139 0260110SW TAIL ROTOR UNBONDED B DT1RK NONE O OTHER ININSP/MAINT 1 EA17XA00113 31047 NEW AIRCRAFT WAS BEING ASSEMBLED AFTER SHIPPING. DURING ASSEMBLY TAIL ROTOR DRIVESHAFT WAS FOUND SCORED AROUND UPPER FLANGE ATTACHMENT AREA. THIS WAS DIRECTLY BELOW THE TAILROTOR GEARBOX, AT THE TOP OF THE VERTICAL FIN. SCORING WAS CAUSED BY A (CLICK-BOND) TYPE FASTENER/STANDOFF USED TO SECURE A WIRE HARNESS. THE FASTENER CAME UNBONDED FROM THE FUSELAGE AND ALLOWED THE WIRE HARNESS TO CONTACT THE DRIVESHAFT. THE CLAMP AND SCREW CAUSED THE SCORING ON THE DRIVESHAFT FLANGE. 2G72 6U R00002RD 20070108001382007010800138 2007 1 8 AFASVRA335 420061201G2562 G SWITCH DORNEMARGLN ELT FAILED D K NONE L NO TEST ININSP/MAINT 1 NM03 9331 4959 ANNUAL INSPECTION TESTING OF ELT IAW AC 43.13-1B, CHAPTER 12, PARA 12-22C. THE G-SWITCH WOULD NOT ACTIVATE. THE NORMAL ON FUNCTIONED SATISFACTORY. WHEN THE ELT WAS AT ROOM TEMPERATURE, G-SWITCH FUNCTIONED PROPERLY BUT WHEN COLD SOAKED IN THE HANGER IT WOULD NOT ACTIVATE. TRIED THE G-SWITCH NUMERIOUS TIMES AND IT WOULD NOT ACTIVATE WHEN COLD. BATTERY EXPIRATION DATE MAR 2007. 20060518002692006051800269 2006 5 18 AMCR200600001 420060405G2562MN1300 BATTERY ACK E01 CIRRUSSR SR22 2130001GL ELT CORRODED B AMCRK NONE O OTHER ININSP/MAINT 1 GL09679DV420 041133 0196 DURING ANNUAL INSP, ELT DID NOT TEST. FOUND 2 D-CELL BATTERIES CORRODED. THESE 2 BATTERIES WERE AT THE BOTTOM OF THE STACK AND THE CORROSION WAS NOT EVIDENT AT FIRST. THERE WERE 2 YEARS REMAINING BEFORE BATTERY REPLACEMENT WAS DUE. THESE ARE THE ORIGINAL BATTERIES SINCE NEW (APRIL 2002). RECOMMEND BATTERIES BE REMOVED COMPLETELY AT EACH ANNUAL AND INSPECTED. 1L71 3O NTA00009CH 20060926001282006092600128 2006 9 26 AMCR200600002 420060925G3414EA517245CES INDICATOR CESSNA208 208B 2073701CE AIRSPEED LEAKING B AMCRO OTHER O OTHER CRCRUISE 1 GL09479DV129 208B1169 PILOT REPORTED AN AIRSPEED SPLIT BETWEEN THE 2 INDICATORS. MAINTENANCE FOUND THE CO-PILOTS INDICATOR LEAKING INTERNALLY. FOUND INDICATOR TO BE AN OLDER, SUPERSEDED TYPE. LATEST UNIT IAW IPC INSTALLED. MFG P/N C661064-0237. 1H71 3T A37CE 20061115001782006111500178EU 2006 11 15 AMCR200600003 120061107G3244237K232 TIRE BRAERODH125 BAE125800A 1500285EU GARRTTTFE731TFE731* 01518WP MLG LEAKING B AMCRK NONE O OTHER ININSP/MAINT 1 GL09527AC NA0405 AFTER MOUNTING A NEW GOODYEAR TIRE ON AN AHA1814 WHEEL, THE TIRE FAILED THE 24 HOUR LEAK CHECK. EXCESSIVE VENTING WAS SEEN FROM MANY VENT HOLES IN THE BEAD AREA. TWO ADDITIONAL 24 HOUR CHECKS WERE PERFORMED AND LEAK RATE WAS ABOUT 19 PERCENT LOSS. AGAIN, EXCESSIVE LEAKING FROM VENT HOLES. TIRE RETURNED FOR WARRANTY. 2L72 4F4 FRTA3EU E6WE 20061115003212006111500321NE 2006 11 15 AMCR200600004 120061113G79216454474 QUILL SKRSKYS76 S76B 8143007NE PWA PT6 PT6* 52043EA BLOWER WORN B AMCRK NONE O OTHER ININSP/MAINT 1 GL09520AC 580 16471 760380 DURING A POSTFLIGHT INSPECTION, MECHANIC WIGGLED THE IMPELLER OF THE LT OIL COOLER BLOWER AND NOTICED EXCESSIVE PLAY AND PROCEEDED TO REMOVE THE BLOWER. INVESTIGATION REVEALED THE SPLINE SHAFT TEETH OF BOTH THE BLOWER'S QUILL SHAFT AND THE ACCESSORY DRIVE TO BE EXCESSIVELY WORN TO THE POINT THAT FAILURE WAS IMMINENT. THE SPLINE TEETH WERE DRY SO IT IS SUSPECTED THAT THE LUBRICATION WAS MISSED AT LAST INTERVAL. BUT THE REPLACEMENT OIL COOLER BLOWER, WITH AN OVERHAUL TAG, WAS FOUND TO HAVE IT'S IMPELLER INSTALLED UPSIDE DOWN. KUDO'S TO THE MECHANIC FOR THOROUGHLY CHECKING BOTH UNITS WITH UNCANNY ATTENTION TO DETAIL. 1G72 4U3 T H1NE E2NE 20060424001522006042400152NM 2006 4 24 AMTA200600279 120060414G2840 FUEL TANK BOEING737 73783N 13844HINM WING READS HIGH A AMTAK NONE O OTHER CRCRUISE 1 GL11319TZ 30643 RT MAIN FUEL TANK READ 400 LBS HIGH. FQIS TEST SHOWS NO FAULT FOR RT MAIN TANK. CHECK GOOD, C/W FIM 28-41-00-810. (K) 2L72 4F RTA16WE 20060428001162006042800116CE 2006 4 28 AOC06001 120060316G323012806005 ACTUATOR CESSNA NA CESSNA210 T210L 2073449CE NLG BROKEN B R29RK NONE O OTHER LDLANDING 1 SW19579776593 21061475 UPON LANDING, THE NOSE LANDING GEAR COLLAPSED, CAUSING MAJOR DAMAGE TO THE PROPELLER AND DAMAGE TO THE NOSE SECTION OF THE AIRCRAFT. INSPECTION AFTER RECOVERY REVEALED THE THE BEARING END (P/N - 1280600-5) HAD BROKEN, ALSO SHEARING THE PINS (P/N - 1280209-1). NO EVIDENCE OF A PRE-EXISTING CRACK NOTED. PARTS SENT TO CESSNA FOR EVALUATION. 1H71 3O 3A21 20060413002572006041300257GL 2006 4 13 ASWFSDO15OKC 120060207G3233 ACTUATOR AMTR GAIR GLASAIRIII 05691HKGL NLG WORN C K NONE K FLUID LOSS LDLANDING 1 SW99373R THE PILOT STATED THAT DURING ROLLOUT AFTER LANDING A HOME BUILT GLASAIR III HE APPLIED THE BRAKES AND THE NOSE GEAR COLLAPSED. THE PILOT SAID THE LANDING GEAR POSITION INDICATOR LIGHTS WERE GREEN PRIOR TO LANDING. THE NOSE GEAR ACTUATOR WAS FOUND TO BE LEAKING FLUID. DURING DISASSEMBLY OF THE ACTUATOR THE PISTON SEAL WAS FOUND TORN. THE AIRCRAFT OWNER SUSPECTS THAT HYDRAULIC FLUID WAS BY PASSING THE PISTON DURING OPERATION BECAUSE OF THE TORN SEAL. THE ACTUATOR DID NOT PRODUCE ENOUGH FORCE TO OVERCOME THE AIR LOAD ON THE NOSE GEAR TO LOCK THE NOSE GEAR DOWN. THIS IS THE SUBJECT OF STODDARD-HAMILTON SERVICE BULLETIN 136. 1L71 3O RTEXPA1L71 20060227000682006022700068NM 2006 2 27 AUCR200600001 120060201G57309006071 PANEL LKHEEDP3A P3A 5260103NM ALLSN T56 T56A10 03004GL LT WING CRACKED B AUCRK NONE O OTHER ININSP/MAINT 1 WP25927AU16619 151369 LT WING, STA. 82, 2.9 IN. FRACTURE IN NR 7 PLANK FORWARD TANG. FRACTURE WAS LOCATED BY ULTRASONIC INSPECTION DURING EVALUATION OF FUEL STAIN AT ANNUAL INSPECTION. THERE EXISTS AN APPROVED REPAIR FOR THIS DAMAGE IN THE SRM. 2L74 4T4 TRTA32NM E282 20060427001282006042700128NM 2006 4 27 AUCR200600002 120060321G57119010622 SPAR CAP LKHEEDP3A P3A 5260103NM WING CORRODED B AUCRK NONE O OTHER ININSP/MAINT 1 WP25922A 12531 151387 UPPER REAR SPAR CAP STRESS CORROSION CRACKED IN AFT RADIUS FORWARD OF NR 4 FLAP HANGER. DAMAGE CENTERED AT WS275. DAMAGE WAS INITIALLY DETECTED VISUALLY DURING SCHEDULED SPECIAL INSPECTION. DAMAGE WAS FURTHER EVALUATED WITH EDDY CURRENT INSPECTION AND WAS FOUND TO EXCEED THE PARAMETERS OF THE SRM. US TECHNICAL ENGINEERING HAS BEEN CONTRACTED TO GENERATE AN APPROVED REPAIR. 2L74 4T RTA32NM 20060512000842006051200084NM 2006 5 12 AUCR200600003 120060427G57309006051 PANEL LKHEEDP3A P3A 5260103NM RT WING CRACKED B AUCRK NONE O OTHER ININSP/MAINT 1 WP25925AU16997 151361 CRACKED RISER, NR 4 FUEL TANK LOWER PLANK NR 4 AT NR 27 RISER WS397R. 2L74 4T RTA32NM 20060515002032006051500203NM 2006 5 15 AUCR200600004 120060427G57309006041 SKIN PANEL LKHEEDP3A P3A 5260103NM LT WING DAMAGED B AUCRK NONE O OTHER ININSP/MAINT 1 WP25925AU16997 151361 BOTTOM LT WING WS68.5, 4 FUEL BOOST PUMP SCREEN ATTACHING HOLES ELONGATED IN NR 17 AND NR 18 RISER. 2L74 4T RTA32NM 20060612000462006061200046NM 2006 6 12 AUCR200600006 120060531G57119010621 SPAR CAP LKHEEDP3A P3A 5260103NM LT WING CRACKED B AUCRK NONE O OTHER ININSP/MAINT 1 WP25900AU15902 151391 DURING SCHEDULED INSPECTION FOUND CORROSION INDUCED CRACK IN UPPER AFT SPAR CAP EXTENDING OUTBOARD FROM PREVIOUS REPAIR IN THE AREA OF FLAP TRACK 5, WS 346. DURING DISASSEMBLY TO EFFECT REPAIR FOUND ADDITIONAL STRESS CORROSION FRACTURE ON UPPER AFT SPAR CAP AT FLAP TRACK 4, WS 275. THE AFFECTED AREAS RECEIVE A DETAILED INSPECTION ANNUALLY. 2L74 4T RTA32NM 20060512000732006051200073GL 2006 5 12 AVI000021 120060419G552011626002 ELEVATOR CIRRUS 10146005 CIRRUSSR SR22 2130001GL CONT O550 IO550* SO ELEVATOR OUT OF TOLERANCED K NONE OOOOTHER OTHER OTHER ININSP/MAINT 1 SO15753CD796 796 0090 DURING SA 06-05 ELEVATOR GAP VISUAL INSPECTION IT WAS NOTED THAT THE GAP BETWEEN ELEVATOR TIP AND HORIZONTAL STABILIZER WAS LESS THEN 0.10 INCH, UPON FURTHER INVESTIGATION IT WAS NOTED THAT PN 11626-002 ELEVATOR HINGE, OB WAS RUBBING ON HORIZONTAL STABILIZER OB HINGE. ELEVATOR WAS RE-SHIMMED BY INSTALLING SHIM PN 11508-005. 1L71 3O3 ONTA00009CHE3SO 20060518002482006051800248CE 2006 5 18 B3OR20060111 120060419G2497 TERMINAL CESSNA500 550 2076604CE WIRING SYS MISINSTALLED B B3ORD RETURN TO BLOCK O OTHER TXTAXI/GRND HDL 1 SW031200N 5500681 WIRE TERMINAL WAS IMPROPERLY CRIMPED ONTO WIRE INSULATION WITH STRIPPED END OF WIRE STRANDS CONTACTING TERMINAL SCREW AT VOLTAGE METER CIRCUIT BREAKER. THIS DISCREPANCY CAUSED AN INTERMITTENT VOLTAGE METER READING FAILURE. 1L72 4F A22CE 20060214002162006021400216EU 2006 2 14 B3OR20060125 120060126G6510350A34021006 DRIVE SHAFT SNIAS 350 AS350B2 8680813EU TAIL ROTOR MISOVERHAULED B K NONE O OTHER ININSP/MAINT 1 SW035204J 3118 DURING ROUTINE TBO REPLACEMENT OF TAIL ROTOR DRIVESHAFT; IT WAS DISCOVERED THAT THE FORWARD END OF THE RECENTLY OVERHAULED REPLACEMENT WAS UNPAINTED CAUSING THE NR 5 BEARING FIT TOLERANCES TO BE TOO LOOSE. MFG TECHNICAL REPRESENTATIVES VERIFIED THAT THE DRIVESHAFT IS SUPPOSED TO BE PAINTED UP TO THE SPLINES. PART WAS RETURNED FOR FURTHER REWORK. 1G71 3U H9EU 20060127000672006012700067EU 2006 1 27 B3OR20060126 120060126G6510350A34021006 DRIVE ASSY SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1D1 NE TAIL ROTOR MISOVERHAULED B B3ORK NONE O OTHER ININSP/MAINT 1 SW035204J 3118 9318 DURING ROUTINE TBO REPLACEMENT, DISCOVERED THE NEWLY OVERHAULED TAIL ROTOR DRIVESHAFT FORWARD END WAS UNPAINTED CAUSING AN UNSERVICEABLY LOOSE FIT OF THE NR 5 BEARING. MANUFACTURER TECHNICAL REPRESENTATIVES VERIFIED THAT THE AREA IN QUESTION IS SUPPOSED TO BE PAINTED UP TO THE SPLINES. PART WAS RETURNED FOR FURTHER REWORK. 1G71 3U3 U H9EU E19EU 20070108001402007010800140CE 2007 1 8 BIOR061211001 120061211G5350101420024438 FAIRING BEECH 200 B200 1152922CE PWA PT6 PT6A42 52043NE CORRODED B BIORK NONE O OTHER ININSP/MAINT 1 EA23200MJ9672 BB1012 DURING A PHASE 4 INSPECTION PAINT BLISTERS WERE NOTED ON THE LT AND RT WING ROOT FAIRING LOWER AFT PANELS P/N 101-420024-43 AND 101-420024-8. UPON FURTHER INSPECTION BOTH PANELS WERE FOUND TO BE CORRODED THRU IN SEVERAL PLACES FROM THE INSIDE OUT. AFTER REMOVING THE PANELS IT WAS DISCOVERED THAT THE ACOUSTIC FOAM HAD BECOME SOAKED WITH WATER OVER TIME. THIS SET UP CORROSION OVER THE ENTIRE AREA OF THE INSIDE OF BOTH PANELS. ALSO WHERE THIS MATERIAL CONTACTED THE FUSELAGE ON THE LT SIDE IT CAUSED CORROSION THRU THE PRESSURE VESSEL. MFG HAS BEEN NOTIFIED AND SUPPLIED WITH PHOTO DOCUMENTATION. 1L72 4T4 T A24CE E4EA 20061204000042006120400004WP 2006 12 4 BS2R2120003 120061117G6310269A5472 PULLEY BRACKET HUGHES HUGHES269 269C 4470504WP LYC O360 HIO360D1A 41514EA BELT DRIVE SYSTEBROKEN B BS2RCE ABORTED TAKEOFF ENGINE SHUTDOWN R PARTIAL RPM/PWR LOSS TOTAKEOFF 1 SW17110472701 29 211031 L2209551A ONE OF THE TWO BELT DRIVE CLUTCH ACTUATOR CABLE PULLEY BRACKETS BROKE CLEAN ACROSS BETWEEN THE FRAME MOUNT HOLE AND THE PULLEY MOUNT HOLE DURING ENGAGEMENT OF THE ROTOR SYSTEM. DURING THE SUBSEQUENT TAKE OFF ATTEMPT THE ROTOR RPM WOULD BLEED OFF RAPIDLY DUE TO DRIVE BELT SLIPPAGE ANY TIME THE M/R COLLECTIVE CONTROL WAS RAISED.THE AICRAFT WAS SHUT DOWN AND THE PROBLEM INVESTIGATED BY THE OPERATOR THEN MAINTENANCE PERSONELL WERE NOTIFIED. 1G71 3O3 O 4H12 1E10 20060614000702006061400070EA 2006 6 14 CA060103001 220060102G7230 ENGINE BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA HARTZLHCD4N3HCD4N3A GL RIGHT FAILED W A UNSCHED LANDING RXJPARTIAL RPM/PWR LOSS ENGINE FLAMEOUT WARNING INDICATION DEDESCENT 1 CA PCE81119 AT APPROXIMATELY 09:30 THIS MORNING, THE RT ENGINE OF KING AIR 200 HAD AN IN-FLIGHT TORQUE ROLL BACK TO APPROX 200 FT LBS, WITH A RISE IN ITT TO APPROX 680 DEG C, WITH A POPPING NOISE AND CORRESPONDING FLAMES FROM THE RT ENGINE EXHAUST. THE CREW INITIATED THE ENGINE SHUTDOWN. 1L72 4T4 T A24CE E4EA 5 CSTC 20060615000272006061500027EU 2006 6 15 CA060104004 120060102G561001379377C405 WINDSCREEN BAG JETSTMJETSTM3212 1500217EU GARRTTTPE331TPE33110UG 01514WP ROTOL R333 R333482F12 GL COCKPIT CRACKED W BA EMER. DESCENT UNSCHED LANDING A FLAME/FIRE CRCRUISE 1 CA AT CRUISE ALT 20,000 FT, NOTICED CRACK AND SUBSEQUENT FLAME WITHIN LAYERS OF LT WINDSHIELD. FLAME SELF EXTINGUISHED WITH DE-SELECTION OF WINDSHIELD HEAT. DURING DESCENT ADDITIONAL CRACKING. DIVERTED TO CYMM. MX DISPATCHED, REPLACED WINDSHIELD. UPON MX REVIEW FOLLOWING WAS DETERMINED; THE PART WAS IN SERVICE ON THIS A/C ON REGISTER SINCE 2003 JANUARY AND PRIOR. NO ABNORMALITIES OBSERVED DURING REMOVAL REGARDING INSTALLATION, EXCEPT FOR PRC APPLIED OVER EXT SCREW HEADS. AIRFRAME VOLTAGE AND CURRENT OUTPUT TO LT WINDOW HEAT SYS FOUND NORMAL. NO EVIDENCE OF MISTORQUE OF SECURING SCREWS OBSERVED. MX PRELIMINARY CONCLUSION, MALFUNCTION LEADING TO A SHORT CIRCUIT OF INTERNAL HEAT FILAMENTS OF WINDSHIELD. 2L72 4T4 TRTBA15CAA E4WE 6 CP61GL 20060615001422006061500142EU 2006 6 15 CA060104005 120060104G2530820317000 OVEN AIRBUSA330 A330* EU RROYCERB211 RB211* 54555NE FWD GALLEY SHORTED W F ACTIVATE FIRE EXT. A OFLAME/FIRE OTHER CRCRUISE 1 CA FWD GALLEY OVEN FIRE EXTINGUISHED WITH 2 FIRE EXT BOTTLES ACTION. FWD GALLEY NR1/NR 2 OVENS REPLACED. FUNCT CHKD SERV NR 1 OFF HK76R5 NR 2 OFF 8203-17-000 S/N 9403-6150. NR 1 ON 8203-17-000, S/N 96-11-7934 NR 2 ON 568K81. 2L72 4F4 FRTA46NM A12EU 20060615001792006061500179EU 2006 6 15 CA060104007 120060104G3260201122006 UPLOCK AIRBUS320 A320211 3930320EU CFMINTCFM56 CFM565A1 NE MLG DAMAGED W O OTHER J WARNING INDICATION CLCLIMB 1 CA AFTER T/O ECAM L/G DOORS NOT CLOSED. CYCLED LDG GEAR. ECAM RE-APPEARED. LT MAIN GEAR DOOR SHOWED PARTIALLY OPEN IN AMBER. GEAR DOORS SHOW CLOSED WHEN GEAR DOWN. LT GEAR DOOR UPLOCK ASSY REPLACED AS PER TASK, 32-31-33-400-002. 2L72 4F4 FRTA28NM E29NE 20060615001812006061500181NE 2006 6 15 CA060104008 220060104G75300CFM565A5 REDUCER AIRBUSA319 A319114 3930350NM GE CFM56 CFM565A 13802NE P3 LINE SHEARED W E ENGINE SHUTDOWN RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CLCLIMB 1 CA IN CLIMB THRU FL185, ENG NR 2 PWR REDUCED TO 74.5 N1/1200 KGH FF. ENG PARAMETERS NORMAL WHEN PWR REDUCED TO LOWER SETTINGS. ENG NR 1 NORMAL THROUGHOUT. FOUND PS3 LINE REDUCER SHEARED AS PER TSM 77-00-00-810-833. REDUCER REPLACED AS PER AIRBUS STANDARD PRACTICES. GROUND RUN CHKD SERV. 2L72 4F4 FRTA28NM E29NE 20060615001822006061500182SW 2006 6 15 CA060104009 120060104G79212660163501 SHAFT BELL BELL 212 212 1181420SW PWA PT6T PT6T3 52045EA BLOWER CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 8292 582 30791 PERFORMED MAGNETIC PARTICLE INSPECTION IAW BHT-ALL-SPM, SHAFT P/N 2660-1635-01 WAS FOUND TO BE CRACKED IN KEY WAY, PART HAS BEEN SUBSEQUENTLY SCRAPED. BELL HELICOPTER HAS BEEN NOTIFIED FOR INTEREST AND INFORMATION ONLY. 1G71 4U4 U H4SW E22EA 20060615001832006061500183 2006 6 15 CA060104010 420060101G233050401100003 VIDEO DISPLAY BOEING737 737* NM CFMINTCFM567CFM567B22 13802NE SEAT 20E ODOR W H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS DEDESCENT 1 CA A/C WAS ON DESCENT WHEN A BURNING SMELL WAS NOTICED COMING FROM SEAT 20E VDU. THE IFE SYSTEM WAS DEACTIVATED. MAINTENANCE REPLACED THE VDU AND THE SYSTEM WAS TESTED SERVICEABLE. THIS COMPONENT WILL BE RETURNED TO THE MANUFACTURER AND A COMPLETE TEAR DOWN REPORT WILL BE REQUESTED. 2L72 4F4 FRTA16WE E00055EN 20060615001842006061500184SW 2006 6 15 CA060104011 120060102G561027194423REV3 WINDSHIELD FRCHLDSA227 SA227DC 3377521SW GARRTTTPE331TPE33112UHR WP MCAULY4HFR344HFR34C652 NE COCKPIT CRACKED W O OTHER O OTHER CRCRUISE 1 CA LT WINDSHIELD CRACKED WHILE AT FL250. CREW CARRIED ON TO BASE AT LOWER ALTITUDE AND SLOWER AIRSPEED. MAINTENANCE IS CHANGING WINDSHIELD. 2L72 4T4 TRTA18SW E4WE 6 C3PNE 20060615001852006061500185 2006 6 15 CA060105001 420060103G233050401100003 VIDEO DISPLAY BOEING737 737* NM CFMINTCFM567CFM567B22 13802NE SEAT 6D SMOKE W H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 1 CA A/C WAS IN CRUISE WHEN SMOKE WAS OBSERVED COMING FROM SEAT 6D VDU. THE IFE SYSTEM WAS DEACTIVATED. MAINTENANCE REPLACED THE VDU AND THE SYSTEM WAS TESTED SERVICEABLE. THIS COMPONENT WILL BE RETURNED TO THE MANUFACTURER AND A COMPLETE TEAR DOWN REPORT WILL BE REQUESTED. 2L72 4F4 FRTA16WE E00055EN 20060615002032006061500203CE 2006 6 15 CA060105004 120060105G3246NIL CONTROL CABLE CESSNA206 206H 2073301CE LYC O540 IO540AC1A5 EA HARTZLHCF3Y HCF3YR1 GL WATER RUDDER FRAYED W K NONE OK OTHER FLUID LOSS ININSP/MAINT 1 CA 1065 WATER RUDDER STEERING CABLES ARE FRAYED WHERE IT ENTERS THE SIDE OF THE FLOAT. THE MAIN CAUSE OF THIS IS A MISALIGNMENT OF THE HOLE ON THE SIDE OF THE FLOAT TO THE ACTUAL POSITIONING OF THE RUN. IN SOME CASES, THE CABLE HAD CUT A 1/4" SLOT ON THE FLOAT SIDE SKIN DUE TO THIS MISALIGNMENT. 1H71 3O3 ORTA4CE 1E4 5 CP31EA 20060724000762006072400076WP 2006 7 24 CA060106001 220060101G7200 ENGINE BOMBDRBD700 BD7001A10 1390006GL HNYWL AS907 AS90711A 33908WP LEFT MALFUNCTIONED W EA ENGINE SHUTDOWN UNSCHED LANDING O OTHER CLCLIMB 1 CA 3030014 (CAN) ON CLIMB OUT CREW REPORTED A LOUD THUMP FOLLOWED BY A DROP IN LT ENGINE OIL PRESSURE AND AN AIRFRAME VIBRATION. CREW SHUT DOWN THE ENGINE DELARED AN EMERENCY AND RETURNED TO AIRPORT. LT ENGINE REMOVED AND LOANER INSTALLED. (TC NR 20060106001) 2L72 4F4 FRTT00003NYE00010LA 20060616000512006061600051CE 2006 6 16 CA060106003 120060105G3297 WIRE BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE UPLOCK SWITCH DAMAGED W O OTHER O OTHER APAPPROACH 1 CA UPON ARRIVAL, THE GEAR WAS SELECTED DOWN BUT NO DOWN AND LOCKED ANNUNCIATORS ILLUMINATED. THE IN TRANSIT LIGHT WAS ALSO NOT ILLUMINATED SO THE PILOT DID A FLY BY OF TOWER TO CONFIRM GEAR POSITION, THEY ALSO HAD EMERGENCY SERVICES ON STANDBY. AN UNEVENTFUL LANDING WAS COMPLETED. AS THE AIRCRAFT WAS BEING SHUTDOWN THE CREW NOTICED THAT THE CB FOR THE ANNUNCIATORS WAS POPPED. RESET THE CB AND ALL THE ANNUNCIATORS ILLUMINATED AS REQUIRED. A SPECIAL FERRY PERMIT WAS ISSUED TO RETURN THE AIRCRAFT TO A MAINTENANCE BASE. MAINTENANCE FOUND A CHAFED WIRE ON THE HARNESS FOR THE RT UPLOCK MICROSWITCH. GEAR SWUNG AND AIRCRAFT RETURNED TO SERVICE. 2L72 4T4 TRTA24CE E26NE 20060616000522006061600052CE 2006 6 16 CA060106004 120060105G561010138402523 WINDSHIELD BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE HARTZLHCE4A HCE4A3I NE COCKPIT CRACKED W A UNSCHED LANDING O OTHER CLCLIMB 1 CA 1234 DEPARTING AIRPORT THE LT HEATED WINDSHIELD CRACKED. TURNED AROUND AND MADE AN UNEVENTFUL LANDING. THE AIRCRAFT WAS SENT TO MAINTENANCE WHO REPLACED THE WINDSHIELD. 2L72 4T4 TRTA24CE E26NE 5 CP10NE 20060616000532006061600053EA 2006 6 16 CA060108001 120060104G5610NP1393216 WINDSHIELD CNDAIRCL600 CL6002C10 1390015EA GE CF34 CF343B1 NE COPILOT'S CRACKED W A UNSCHED LANDING O OTHER CLCLIMB 1 CA 99307H2825 RIGHT WINDSHIELD CRACKED DURING CLIMB. DIVERTED FLIGHT BACK TO DEPARTURE AIRPORT. 2L72 4F4 FRTA21EA E15NE 20060616000542006061600054EA 2006 6 16 CA060108002 120060103G5610NP1393211 WINDSHIELD CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE CRACKED W O OTHER O OTHER APAPPROACH 1 CA DURING APPROACH, THE LEFT WINDSHIELD CRACKED. 2L72 4F4 FRTA21EA E15NE 20060616000562006061600056WP 2006 6 16 CA060109001 120060103G6730D2121 SERVO ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE HYDRAULIC LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA 92 DURING DAILY INSPECTION, NOTICEABLE AMOUNT OF HYDRAULIC FLUID LEAKING FROM SERVO. GROUND RUN DETERMINED PILOT VALVE SOURCE OF LEAK. AFT SERVO REMOVED AND RETURNED TO ROBINSON HELICOPTERS FOR WARRANTY REPAIRS. 1G71 3O3 O H11NM 1E4 20060616000572006061600057NM 2006 6 16 CA060109002 120060106G3297471515 WIRE HARNESS BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA NLG WOW DAMAGED W A UNSCHED LANDING N FALSE WARNING CLCLIMB 1 CA AIR TURN BACK DUE TO NR 2 WOW CAUTION LIGHT. NLG WOW 2 HARNESS REPLACED. AIRCRAFT RETURNED TO SERVICE. 2H72 4T4 TRTA13NM E00062EN 20060616000602006061600060CE 2006 6 16 CA060110001 120060106G33102K40D10 RESISTOR BEECH 90 C90A 1152911CE PWA PT6 PT6A21 52043EA HARTZLHCB3T HCB3TN3 GL PANEL LIGHT OVERHEATED W K NONE M OVER TEMP ININSP/MAINT 1 CA DURING SPECIAL INSPECTION AS PER CAMPAIGN 681-33-21-018, FOUND RESISTOR R145 (ATA 33-21-01 PAGE 4) OVERHEATED. INSULATION ABOVE THE RESISTOR WAS SCORCHED AND BURNED. THE SYSTEM WAS DEACTIVATED AND DEFERRED. 1L72 3T4 TRT3A20 E4EA 6 CP15EA 20060616000622006061600062NM 2006 6 16 CA060110002 120060108G7933MS280344 PROBE DHAV DHC8 DHC8201 2809001NM PWA 120 PW123D 52152NE HAMSTD14SF 14SF23 NE OIL TEMPERATURE MALFUNCTIONED W A UNSCHED LANDING N FALSE WARNING CRCRUISE 1 CA 18748 DURING CRUISE, THE LT OIL TEMPERATURE INDICATION WAS NOTICED TO BE INTERMITTENTLY FLUCTUATING AND UNSERVICEABLE. CREW ELECTED TO RETURN THE AIRCRAFT TO BASE WHERE AN APPROACH AND LANDING WAS CARRIED OUT WITHOUT INCIDENT. ENGINEERING INVESTIGATION REVEALED THAT THE ENGINE'S OIL TEMPERATURE PROBE WAS UNSERVICEABLE. THE PROBE IN QUESTION WAS REPLACED AND FOLLOWING REQUIRED ENGINE RUNS AND CHECKS THE AIRCRAFT WAS RELEASED BACK TO SERVICE WITHOUT FURTHER INCIDENT. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20060616001082006061600108CE 2006 6 16 CA060110003 120060106G33102K40D10 RESISTOR BEECH 90 C90A 1152911CE PWA PT6 PT6A21 52043EA HARTZLHCB3T HCB3TN3 GL PANEL LIGHTS OVERHEATED W K NONE M OVER TEMP ININSP/MAINT 1 CA DURING SPECIAL INSPECTION AS PER CAMPAIGN 681-33-21-018, FOUND RESISTOR R145 (ATA 33-21-01 PAGE 4) OVERHEATED. INSULATION ABOVE THE RESISTOR WAS SCORCHED AND BURNED. THE SYSTEM WAS DEACTIVATED AND DEFERRED. 1L72 3T4 TRT3A20 E4EA 6 CP15EA 20060616001152006061600115EA 2006 6 16 CA060110004 120060106G3244362K821 TIRE CNDAIRCL600 CL600* EA GE CF34 CF34* NE NR 2 SEPARATED W O OTHER DJ INFLIGHT SEPARATION WARNING INDICATION CLCLIMB 1 CA 1160 504 ON TAKEOFF, THE NR 2 MAIN TIRE RECAP DEPARTED THE TIRE CAUSING DAMAGE TO MLG SIDE STAY SPRINGS AND RETAINING PINS, INBD FLAP AND VANE, THE WING LOWER SKIN AFT OF THE LT GEAR BAY, AND THE INBD SPOILER FITTING ASSEMBLY. SIGNS OF FOD NOTED IN THE LT ENGINE BUT DETAILED INSPECTION AND BOROSCOPE SHOWED NO DAMAGE SUSTAINED. MAIN TIRE PRESSURES NOTED AS FOLLOWS NR 1 198 PSI, NR 2 140 PSI, NR 3 198 PSI, NR 4 198 PSI, S/N (D) IS TIRE SERIAL NUMBER NOT ASSEMBLY, RECAPPED AT WILKERSON. 2L72 4F4 FRTA21EA E15NE 20060616001162006061600116NE 2006 6 16 CA060110005 220060104G7230311074102 SHROUD PWA PT6 PT6A114A 52043NE COMPRESSOR DISTORTED W K NONE O OTHER ININSP/MAINT 1 CA 746 PCE19201 DURING A RECTIFICATION INSPECTION OF RENTAL ENGINE, CT SHROUD SEGMENT RETAINING RING OF POST SB 1627 CONFIG FOUND LOOSE AND MINOR SHIFTING OF CT SHROUD SEGMENT WAS NOTED. CT SHROUD SEGMENT-RETAINING RING WAS OF POST SB 1627 CONFIG AND CT SHROUD SEGMENTS (P/N 3053094) WERE PER SB 1628. QTY 6-RUB SPOTS WERE NOTED ON CT SHROUD SEGMENTS WITH MINOR RUB ON CT BLADES. CT SHROUD SEGMENT-RETAINING RING WAS FOUND DISTORTED AND PARTIALLY DISENGAGED FROM RETAINING GROOVE OF CT SHROUD HOUSING. NO OVER HEATING/BURNING OF HOT SECTION PARTS NOTED. INSPECT OF CT SHROUD HOUSING WAS DONE AND ROUNDNESS OF ALL CRITICAL DIAMETERS NOTED WITHIN O/H MANUAL LIMIT. SHIFTING OF CT SHROUD SEGMENTS WAS DUE TO PARTIAL DISENGAGEMENT OF 3 T E4EA 20060627000032006062700003 2006 6 27 CA060110006 120060110G273082700561003 CABLE ELEVATOR DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA DURING CHECK , 2 CHAIN CABLE ASSY`S, P/N 82700561-003, TITLED "ELEV TRIM AND ELEV GUST LOCK CONTROL" INSPECT OF CHAINS, REF AD CF-2005-38, WAS FOUND INCORRECTLY ASSEMBLED AND SUPPLIED BY SPARES. ASSY FOUND INCORRECTLY BUILT WHEN ATTEMPTING TO INSTALL AS PER AMM 27-36-01, PARA B, STEP 3. SPECIFIES THAT CHAIN PLATE IS REQ`D TO BE ON INBD SIDE OF SPROCKET. THIS CAN'T BE ACCOMP WITH NEW CHAIN ASSY IN ITS PRESENT CONFIG (DWG 82700561 SHOWS THE DIMENSIONS AND CORRECT ORIENTATION OF ASSY). TECH HELP DESK E-MAILED, ADVISED OF ISSUE & REQUESTED TO PULL THEIR DRAWINGS TO CONFIRM OUR FINDINGS. REQUESTED INSPECT EXISTING INVENTORY TO CONFIRM IF THEIR SPARES WERE ALSO AFFECTED. REPLACEMENT CHAIN CABLE ASSY`S ORDERED 20060616001172006061600117NM 2006 6 16 CA060110007 120060110G25308201170000 OVEN AIRBUSA319 A319114 3930350NM GE CFM56 CFM565A 13802NE AFT GALLEY SHORTED W O OTHER A FLAME/FIRE CRCRUISE 1 CA OVEN NR 02-02-17535 OVEN NR 3 IN AFT GALLEY EMITTED AN ELECTRIC SHOCK TO F/A UPON TOUCHING IT. MEL ERASED IN CCS AND CB PULLED AND COLLARED BY FLIGHT CREW. REPLACED NR 3 OVEN CONTROLLER FUNCTION CHECK SATISFACTORY. 2L72 4F4 FRTA28NM E29NE 20060616001182006061600118 2006 6 16 CA060111001 120060103G2400 CIRCUIT BREAKER BURNED W O OTHER O OTHER NRNOT REPORTED 1 CA AIRCRAFT HAD NR 1 AC GENERATOR INOPERATIVE (GOES OFFLINE AFTER 20 SECONDS). INITIALLY, THE GENERATOR HAD BEEN REPLACED, HOWEVER, THE DISCREPANCY REMAINED. SUBSEQUENTLY, CIRCUIT BREAKER, P/N 2TC2-5 FOUND WITH HOLE BURNT IN THE SIDE. FOR RECTIFICATION PURPOSES, CONTACTOR RELAY 2421-K1 REPLACED. RING CONNECTORS TO CB3 AND CB5 REPLACED, P/N HC-AJN022 (CONTACTOR RELAY), P/N 2TC2-5 (CB3) & (CB5). 20060616001202006061600120NM 2006 6 16 CA060111002 120060111G534069215313 BRACKET BOEING737 737522 138449FNM CFMINTCFM56 CFM563C1 13802EU FUSELAGE SPLIT W O OTHER O OTHER LDLANDING 1 CA ON LANDING IN YYZ,FORWARD ATTENDANTS SEAT BELT CAME FREE OF THE ATTACH BRACKET. UPON INVESTIGATION IT WAS FOUND THAT A WASHER WAS MISSING FROM THE RETAINING BOLT. THIS MISSING WASHER WAS LEFT OFF THE BOLT AT INSTALLATION BY A PREVIOUS OPERATOR. 2L72 4F4 FRTA16WE E21EU 20060616001222006061600122GL 2006 6 16 CA060112001 220060107G72406870992 COMBUSTION CASE BOLKMS105 BO105S 5626006EU ALLSN 250C 250C20B 03013GL ENGINE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA CREW REPORTED ABNORMALLY HIGH TOT ON NR 1 ENGINE. INVESTIGATION REVEALED A CRACK IN THE RT ARMPIT AREA OF THE OUTER COMBUSTION CASE. THE OUTER COMBUSTION CASE WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. 1G72 3U3 U H3EU E4CE 20060616001232006061600123WP 2006 6 16 CA060112002 120060111G6730D2121 SERVO ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE ROTOR FLT CONTROLEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA 503 HYDRAULIC LEAK FROM SERVO. SERVO REMOVED FOR REPAIR AND REPLACED WITH SERVICEABLE UNIT. 1G71 3O3 O H11NM 1E4 20060616001242006061600124EA 2006 6 16 CA060112003 120060111G2540601R40467239 INSULATION CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE BURNED W K NONE O OTHER ININSP/MAINT 1 CA 15193 BURNT INSULATION BLANKET FOUND IN CARGO UNDERFLOOR AREA ON RT SIDE OF AIRCRAFT AROUND HEATED LAV WATER SERVICE PORT. 2L72 4F4 FRTA21EA E15NE 20060616001252006061600125WP 2006 6 16 CA060112004 120060111G6700C12131 PUSH-PULL ROD ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE MAST WORN W K NONE O OTHER ININSP/MAINT 1 CA 503 WHILE REMOVING A HYDRAULIC SERVO, IT WAS NOTED THAT THE PUSH PULL TUBE FROM THE SERVO TO THE SWASHPLATE WAS WEARING WHERE IT PASSED THROUGH THE MIDDLE RIB OF THE MAST FAIRING. THE CHAFING WAS MINOR, AND HAD ONLY GONE THOUGH THE TOP LAYER OF PAINT, AND STARTED ON THE PRIMER. THE ENGINEERS SUSPECT THAT THE LOWER RIBS OF THE MAST WERE NOT CENTERED PROPERLY DURING MANUFACTUER, AND WERE ALTERING THE POSITION OF THE MIDDLE RIB. 1G71 3O3 O H11NM 1E4 20060616001502006061600150SW 2006 6 16 CA060112005 120060110G52802755001177 DOOR SWRNGNSA226 SA226TC 8780404SW GARRTTTPE331TPE33110UA 01514WP LANDING GEAR JAMMED W O OTHER J WARNING INDICATION DEDESCENT 1 CA DURING APPROACH, CREW ATTEMPTED TO EXTEND L/G AND NOTICED RT MAIN WAS NOT DOWN AND LOCKED. IT WAS DETERMINED LANDING GEAR WAS NOT COMING OUT OF RT W/W. IT TOOK SEVEN ATTEMPTS TO GET LANDING GEAR TO COME DOWN AND LOCK INTO POSITION. INSPECTION REVEALED RT I/B GEAR DOOR HINGES WERE WORN, ALTHOUGH NOT EXCESSIVE, THAT TWO RT MLG DOORS OVERLAPPED DURING RETRACTION AND DID NOT ALLOW GEAR TO COME DOWN OUT OF W/W WHEN IT WAS EXTENDED FOR LANDING. INSPECTION OF DOOR REVEALED SOME DENTS AND TEARING OF SKIN EDGE ON DOOR WHERE L/G GEAR WAS HITTING DOOR DURING ATTEMPTS TO EXTEND LANDING GEAR. LANDING GEAR DOOR WAS REPLACED AND DOOR AND GEAR RIGGING CHECKED. AIRCRAFT HAS SINCE RETURNED TO SERVICE. 2L72 4T4 TRTA8SW E4WE 20060619000692006061900069GL 2006 6 19 CA060112006 220060105G72506886407 TURBINE BLADES ALLSN 250C 250C* GL ENGINE BROKEN W ED ENGINE SHUTDOWN RETURN TO BLOCK CW F.O.D. INADEQUATE Q C TXTAXI/GRND HDL 1 CA 120 CAT32511P TURBINE RECEIVED AT ESSENTIAL TURBINES IN A DISASSEMBLE STATE. LOG CARDS REFLECT THAT THE TURBINE HAD BEEN INVOLVED IN A HARD LANDING. IT HAD BEEN INSPECTED AND SENT TO MAC-V AVIATION WHO RE-ASSEMBLED THE ENGINE. MAC-V STATED VIA A PHONE CALL THAT THE HARDWARE WAS MIXED IN THE COMBUSTION SECTION AND COULD NOT FIND ALL OF THE NUTS, BOLTS ETC. OUR INVESTIGATION LEADS US TO BELIEVE THAT THE HARD LANDING WAS NOT A FACTOR. THE FAILED TURBINE WHEEL WILL BE FORWARDED TO THE SAFETY BOARD TO EVALUATE THE REASON FOR FAILURE, POSSIBLY DUE TO FOD FROM ITEM MISSED DURING RE-ASSEMBLY. 3 U E4CE 20060619000722006061900072CE 2006 6 19 CA060112007 120060101G5340 INTERCOSTAL CESSNA402 402C 207590RCE CONT O520 TSIO520VB 17040SO MCAULY3AF32C3AF32C505 GL RUDDER PEDAL DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA PILOTS OUTBOARD INTERCOSTAL RUDDER PEDAL MOUNT REPAIRED DUE TO SEVERAL SMALL CRACKS. 1L72 3O3 O A7CE E8CE 5 CP22EA 20060619000772006061900077SW 2006 6 19 CA060112009 120060112G77122719158007 INDICATOR FRCHLDSA227 SA227CC 3377522SW GARRTTTPE331TPE33111U 01514WP MCAULY4HFR344HFR34C652 NE TORQUE INOPERATIVE W C ABORTED TAKEOFF N FALSE WARNING TOTAKEOFF 1 CA ON TAKEOFF, THE TORQUE INDICATOR WENT TO ZERO. TAKEOFF ABORTED AND AIRCRAFT RETURNED TO BLOCKS. MAINTENANCE REPLACED INDICATOR AND RELEASED AIRCRAFT AFTER SATISFACTORY GROUND RUN. 2L72 4T4 TRTA18SW E4WE 6 C3PNE 20060619002452006061900245WP 2006 6 19 CA060112010 120060108G801172566 RING GEAR ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE STARTER DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA 201 STARTER RING GEAR REPLACED AFTER 201.1 HOURS. MISSING TEETH. AIRCRAFT TOTAL TIME 441.3. 1G71 3O3 O H11NM 1E4 20060619002462006061900246WP 2006 6 19 CA060112011 120060105G2913D5001 PUMP ROBSINR44 R44 7640120WP LYC O540 O540F1B5 41532EA HYD SYS CONTAMINATED W K NONE O OTHER ININSP/MAINT 1 CA 42 DURING GROUND CHECK, THE PILOT NOTED PROBLEMS WITH FLIGHT CONTROL CHECK WITH HYDRAULICS. MAINTENANCE FOUND FERROUS DEBRIS IN THE FILTER. THE HYDRAULIC PUMP WAS REPLACED, AND SYSTEM FLUSHED. NO FURTHER DEFECTS FOUND. PUMP WAS SENT BACK TO MFG. 1G71 3O3 O H11NM E295 20060619002482006061900248EA 2006 6 19 CA060112013 120060108G5610NP1393219 WINDSHIELD CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE COCKPIT CRACKED W O OTHER O OTHER TXTAXI/GRND HDL 1 CA 9835 LT WINDSHIELD FOUND CRACKED BEFORE FLIGHT. LT WINDSHIELD REPLACED AND TESTED IAW TO AMM PROCEDURE. 2L72 4F4 FRTA21EA E15NE 20060619002492006061900249EU 2006 6 19 CA060116001 120060112G2910HTE400005 VALVE BAG JETSTMJETSTM3212 1500217EU GARRTTTPE331TPE33110UG 01514WP MCAULY4HFR344HFR34C652 NE RT HYD SYSTEM CRACKED W O OTHER KJ FLUID LOSS WARNING INDICATION APAPPROACH 1 CA 2012620126 ON APPROACH, UPON FLAP SELECTION, NO SYSTEM HYD PRESSURE. EMERG GEAR SELECTION USED TO EXTEND L/G, AND TO OBTAIN 10 DEGREES FLAP. A/C LANDED W/O INCIDENT, DUE TO LOSS OF SYS HYD PRESSURE, N/W STEERING INOP AND MAIN BRAKING WAS LIMITED. TOWED TO HANGAR. MX FOUND PN HTE400005 CHECK VALVE CRACKED, WHICH RESULTED IN LOSS OF SYS HYD FLUID. CHECK VALVE WAS REPLACED, SYS WAS REPLENISHED AND BLED, OPS CHECKED SERVICEABLE. COMPANY ISSUED FLEET INSP TO DETERMINE IF A COMMON PROBLEM WITH FACTORY INSTALLATION. FOUND MULTIPLE A/C WITH THESE NRV'S CRACKED IN RADIUS. (FPI, 10X MAG. GLASS REQUIRED TO DETECT.) VALVE'S REPLACED AS REQ`D AND MFG TO BE CONTACTED. DEFECTIVE VALVES TAGGED AND ON FILE FOR FURTHER INSPECT. 2L72 4T4 TRTBA15CAA E4WE 6 C3PNE 20060619002502006061900250GL 2006 6 19 CA060116002 220060116G726023069576 BEARING EMB 145 EMB145 3260210SO ALLSN AE300 AE3007A GL ENGINE FAILED W K NONE O OTHER ININSP/MAINT 1 CA 12348 CAE311908 ENGINE CAE311908 CAME IN THE SHOP FOR METAL DEBRIS IN THE FILTER. DURING ENGINE DISASSEMBLY IT WAS FOUND THAT NR 6 MID SPAN BEARING ASSEMBLY HAD FAILED. MID-SPAN BEARING OUTER RACE WAS STILL IN ITS HOUSING AND ONLY 3 ROLLERS AND A PIECE OF BEARING CAGE WERE FOUND. THE RADIAL DRIVE QUILL SHAFT WAS FOUND BROKEN ABOVE THE SPLINES CONNECTING TO THE RADIAL DRIVE BEVEL GEARSHAFT. SIMILAR OCCURRENCE ON MID SPAN GEAR TRAIN SYSTEM ON OTHER ENGINES HAD CAUSE IN FLIGHT SHUTDOWN. 2L72 4F4 FRTT00011ATTE6CH 20060619002512006061900251EA 2006 6 19 CA060116003 220060106G8530AEL65102 CYLINDER PIPER PA30 PA30 7103002SO LYC O320 IO320B1A 41508EA HARTZLHCE2Y HCE2YL2 GL ENGINE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 2192 IN RESPONSE TO AD 2005-26-10 ISSUED BY THE FAA, INSPECTED AIRCRAFT TO DETERMINE IF ANY OF SUSPECT SN CYLINDERS INSTALLED. FOUND 2 CYLINDERS ON LT ENGINE WERE PART OF THE AD REQUIREMENT FOR REPLACEMENT. ON CLOSER EXAMINATION OF ONE OF THESE CYLINDERS (NR 3), FOUND A CRACK EXTENDING FROM THE SPARK PLUG HOLE AROUND THE EXHAUST PORT AND PARTIALLY AROUND THE BARREL. THERE WAS A SIGNIFICANT LEAK OF COMPRESSION. BOTH CYLINDERS ARE PRESENTLY BEING REPLACED. ALL OTHER CYLINDERS MADE BY ECI AND ON OUR AIRCRAFT WILL BE MONITORED CLOSELY AS REPLACE THEM ALL PER THE AD SCHEDULE. 1L72 3O3 O A1EA 1E12 5 CP9EA 20060619002532006061900253EU 2006 6 19 CA060116004 120060112G5347B530042 SEAT TRACK SAAB SF340 340B 7860101EU BS 297-375 CORRODED W K NONE O OTHER ININSP/MAINT 1 CA DURING THE 4K2Y BRIDGE CHECK VISIT, THE AISLE LT SIDE SEAT TRACK BL 18.3 WAS FOUND TO HAVE AREAS OF CORROSION FORWARD OF FRAME STA 375 BEYOND ALLOWABLE LIMITS IAW SRM. THE AISLE LT SIDE SEAT TRACK BL 18.3 WILL BE REPLACED WITH A NEW SEAT TRACK SECTION P/N B53004-2 AT FRAME STA 297-375 AND REPAIR BEAM P/N B53004-3 IAW THE COMPANY APPROPIATE EO. 2L72 4T RTA52EU 20060619002542006061900254EU 2006 6 19 CA060116005 120060103G2121TVT10728H3 COOLING FAN AMD FALC90FALCON900B 2730171EU SEIZED W H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS TXTAXI/GRND HDL 1 CA 3067 WHILE ON THE GROUND WITH THE APU RUNNING, SMOKE WAS OBSERVED IN THE CABIN. THE CREW IMMEDIATELY SHUT DOWN THE APU. THE TURBO COOLING FAN WAS FOUND SEIZED. 2L73 4F RT 20060619000802006061900080EA 2006 6 19 CA060116006 220060111G852074968 CRANKSHAFT BBAVIA8 8GCBC 1220803SW LYC O360 O360C2E 41514EA MCAULY1A200 1A200* GL ENGINE CORRODED W K NONE O OTHER ININSP/MAINT 1 CA 698 THE CRANKSHAFT A/C WAS INSPECTED DUE TO A FAILURE OF A CRANKSHAFT ON ANOTHER AIRCRAFT IN THE FLEET (INTERNAL CORROSION). UPON REMOVAL OF THE FRONT CRANK PLUG AND CLEANING OF THE CRANKSHAFT, IT DISCOVERED THAT URETHABOND COATING WAS BLISTERING. URETHABOND REMOVED AND CORROSION WAS FOUND WITHIN FIRST INCH OF CRANK. ENGINE WAS A FACTORY EXCHANGE OVERHAUL (21 APR 2002) AND THE CRANK HAD BEEN RE-WORKED. THE CRANKSHAFT WAS AT MAX ID THEREFORE PITTING FROM CORROSION COULD NOT BE COMPLETLY REMOVED. CRANK WAS INSPECTED BY AN APPROVED AMO(NDT) AS PER LYC SB 505B AND NO FAILING INDICATION WERE FOUND. CRANK WAS MARKED PID AND DID NOT REQURIE ANY INTERNAL INSPECTIONS UNTIL 2000-HRS. 1H71 3O3 O A21CE E286 5 NP874 20060619002552006061900255CE 2006 6 19 CA060116007 120060115G53400512128 BRACKET CESSNA CESSNA185 A185F 2072821CE CONT O520 IO520D 17032SO MCAULYD3A34 D3A34C401 GL BS 65.33 BROKEN W L ABORTED APPROACH F FLT CONT AFFECTED APAPPROACH 1 CA 3815 UPON APPROACH TO LAND ON LAKE, FLAPS 10 SELECTED. A/C IMMEDIATELY BEGAN TO ROLL TO LT, RETURNED FLAPS TO ZERO, A/C RETURNED TO LVL FLT. TRIED TO DEPLOY FLAPS AGAIN (SLOWLY) AND OBSERVED RT FLAP DEPLOYED NORMALLY, LT FLAP DID NOT MOVE, A/C THEN RETURNED TO WHERE A FLAPLESS LANDING WAS CARRIED OUT WITH NO FURTHER PROBLEMS. ONCE ON GROUND PILOT SELECTED FLAPS 10 AND NOTED WHILE RT FLAP DEPLOYED IMMEDIATELY, LT FLAP SLOWLY FELL TO POSITION. ONCE IN HANGAR AND OPENED UP FOR INSPECT IT WAS DISCOVERED THAT FLAP PULLEY BRACKET (LT) AT STA 65.33 DETACHED/TORN FROM BULKHEAD ASSY THUS CAUSING PULLEY TO NO LONGER BE ATTACHED TO AIRFRAME CAUSING FLAP TO MALFUNCTION. PILOT CONFIRMED FLAPS FUNCTIONING NORMALLY FOR T/O. 1H71 3O3 O 3A24 E5CE 5 CP47GL 20060619002562006061900256SW 2006 6 19 CA060116008 120060113G5302205032814103 PANEL BELL 412 412EP 1182205SW TAILBOOM MISMANUFACTURED W O OTHER O OTHER NRNOT REPORTED 1 CA MFG WAS ADVISED BY A SUPPLIER THAT PANELS WERE PROCESSED UNDER A DIFFERENT CURE CYCLE THAN THE ONE PRESCRIBED BY THE MFG PROCESS SPECIFICATION. 1G72 4U H4SW 20060619002572006061900257SW 2006 6 19 CA060116009 120060113G5302 PANEL BELL 412 412EP 1182205SW TAILBOOM MISMANUFACTURED W O OTHER O OTHER NRNOT REPORTED 1 CA MFG WAS ADVISED BY A SUPPLIER THAT PANELS WERE PROCESSED UNDER A DIFFERENT CURE CYCLE THAN THE ONE PRESCRIBED BY THE MFG PROCESS SPECIFICATION. 1G72 4U H4SW 20060619002782006061900278NM 2006 6 19 CA060117001 120060117G7931 ENGINE AIRBUSA319 A319114 3930350NM GE CFM56 CFM565A 13802NE NR 1 INOPERATIVE W E ENGINE SHUTDOWN J WARNING INDICATION APAPPROACH 1 CA ECAM MSG ENG 1 LOW OIL PRESS ON APPROACH/AGAIN ON GRD DROPPED TO 13 PSI ENG SHUTDOWN. TSM 79-00-00 PG 1, FOUND OVER 2 GAL OF OIL IN AGB-OIL DRAINED AND CKD SUPPLY FILTER/SCAVENGE FILTER AND MAG PLUGS. ALL OK, CK AGB SCAVENGE LINE, CLEAR, CK OIL TANK STRAINER, CLEAR. GRD RUN AT T/O POWER AND LEAK CK OK. 2L72 4F4 FRTA28NM E29NE 20060621000762006062100076NE 2006 6 21 CA060117002 220060117G7240 DUCT CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE 14TH STG FAILED W E ENGINE SHUTDOWN F FLT CONT AFFECTED DEDESCENT 1 CA L14TH DUCT MSG ON DESCENT. ACTIONED CHECKLIST AND SHUTDOWN ENGINE. CHANGED DETECTOR ELEMENT A59WK. OP TEST CARRIED OUT IAW AMM SERV. 2L72 4F4 FRTA21EA E15NE 20060621000772006062100077CE 2006 6 21 CA060117003 120060113G37107297088 GEAR CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA MCAULY1C160 1C160DTM GL VACUUM PUMP SEIZED W ED ENGINE SHUTDOWN RETURN TO BLOCK O OTHER TXTAXI/GRND HDL 1 CA 858 858 VACUUM PUMP DRIVE SHAFT SEIZED AND SHEARED OFF 2 GEAR TEETH. 1H71 3O3 ONT3A12 E274 5 NP910 20060621000792006062100079CE 2006 6 21 CA060117005 120060114G561010138402522 WINDSHIELD BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA COCKPIT BROKEN W B EMER. DESCENT O OTHER CRCRUISE 1 CA DURING CRUISE AT 19,000 FT ALTITUDE, CABIN DIFF OF 5.8 PSI, THE INNER PANE OF THE CO-PILOT'S WINDSHIELD SHATTERED. THE CREW LANDED THE AIRCRAFT SAFELY AT IT'S DESTINATION. 1L72 4T4 T A24CE E4EA 20060621000812006062100081NM 2006 6 21 CA060118001 120060116G3040KCD4N RELAY DHAV DHC8 DHC8* NM PWA PW120 PW123 NE HAMSTD14SF 14SF23 NE COCKPIT BURNED W O OTHER B SMOKE/FUMES/ODORS/SPARKS TXTAXI/GRND HDL 1 CA WHEN WINDSCREEN HEAT SELECTED TO WARM UP ON THE GROUND, SMOKE AND SPARKS CAME FROM RT FWD CORNER OF OVERHEAD PANEL. WINDSCREEN HEAT RELAY 3041-K6 FOUND BURNED, RELAY BASE ALSO FOUND DAMAGED. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20060621000822006062100082NE 2006 6 21 CA060118002 220060116G7200 ENGINE BELL 212 212 1181420SW PWA PT6T PT6T3B 52045NE NR 1 MALFUNCTIONED W A UNSCHED LANDING YJ ENGINE STOPPAGE WARNING INDICATION DEDESCENT 1 CA (CAN) HELI-SKING: AC DROPPED SKIERS AT TOP, HAD LIFTED OFF MOUNTAIN TO GO TO SKIER PICK UP PAD. AC WAS ON A DESCENDING, SLIDE SLIPPING, PILOT CARRIED OUT A SCAN OF INDICATORS, NOTICE NR AT 99 PERCENT, DESCENDING TO 98 PERCENT, WAS EXPECTING A 101 PERCENT FOR HIM TO BEEP DWN TO 100 PERCENT. ENG OUT LIGHT NR1 ENG CAME ON AS WELL AS OTHER LIGHTS. NG, ITT WERE DECREASING ON NR 1 ENG. CREEPED NR BACK UP TO 100 PERCENT. ALSO CONFIRMED THAT THROTTLE WAS FULL OPEN. LEVEL OUT AC, ISOLATED DEAD PWR SEC AND RETURNED TO HANGAR. NORMAL SHUTDOWN ON NR 2 PWR SEC. MAINT BOTH PWR SEC WERE STARTED UP ON GROUND, BOTH PWR SEC STARTED NML, OPS CHECK APPEARED TO BE NML. AC GROUNDED TO TROUBLESHOOT THE DEFECT. (TC NR 20060118002) 1G71 4U4 U H4SW E22EA 20060621000832006062100083NE 2006 6 21 CA060118003 220060117G74141050765 CLAMP CONT BL6006163 ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE MAGNETO COIL FAILED W K NONE O OTHER ININSP/MAINT 1 CA 190 C019710E ENGINE MAGNETO COIL CLAMP FAILED. 1G71 3O3 O H11NM 1E4 20060621001412006062100141NM 2006 6 21 CA060119003 120060117G323365C3575816 ACTUATOR BOEING727 727231 1384079NM PWA JT8 JT8D15A 52051NE UPLOCK LEAKING W L ABORTED APPROACH J WARNING INDICATION APAPPROACH 1 CA (CAN) ON APPROACH, NLG FAILED TO EXTEND NORMALLY. SUSPECT POSSIBLE FREEZING IN UPLOCK MECHANISM AND/OR BUNGEE LINK. MANUAL EXTENSION USED, NLG EXTENDED AND LOCKED. AIRCRAFT LANDED WITHOUT INCIDENT. UPON INSPECTION BY MAINTENANCE SUSPECTED ACTUATOR BYPASSING INTERNALLY. ACTUATOR REPLACED. (TC NR 20060119003) 2L73 4F4 F A3WE E2EA 20060621001432006062100143NM 2006 6 21 CA060119004 120060117G323369141001 ACTUATOR BOEING727 727231 1384079NM PWA JT8 JT8D15A 52051NE MLG FROZEN W L ABORTED APPROACH J WARNING INDICATION APAPPROACH 1 CA (CAN) ON APPROACH, NLG FAILED TO EXTEND NORMALLY. SUSPECT POSSIBLE FREEZING IN UPLOCK MECHANISM AND/OR BUNGEE LINK. MANUAL EXTENSION USED. NLG EXTENDED AND LOCKED. AIRCRAFT LANDED WITHOUT INCIDENT. UPON INSPECTION BY MAINTENANCE SUSPECTED BUNGEE ACTUATOR FROZEN. BUNGEE LINK REPLACED. (TC NR 20060119004) 2L73 4F4 F A3WE E2EA 20060621001452006062100145NM 2006 6 21 CA060119005 120060119G3297 WIRE HARNESS BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17EU NLG DAMAGED W A UNSCHED LANDING O OTHER CLCLIMB 1 CA (CAN) LANDING GEAR FAILED TO RETRACT: 3X RED AND 3X GREEN ON (UP) SELECTION. ON ARRIVAL THE ENGINEERS HAVE FOUND A FAULT WITH NWCENT UNREASONABLY FAR. OPERATOR IS REPLACING THE WOW 2 HARNESS P/N 47151-5. (TC NR 20060119005) 2H72 4T4 TRTA13NM E00062EN6 CP17BO 20060621001472006062100147EA 2006 6 21 CA060120001 120060118G5610NP1393216 WINDSHIELD CNDAIRCL600 CL6002B19 1900309EA COCKPIT CRACKED W O OTHER O OTHER CRCRUISE 1 CA 27950 (CAN) FO WINDSHIELD OUTER PLY CRACKED IN FLIGHT. REMOVED AND REPLACED WINDSHIELD. WINDSHIELD IS PRE AD 2001-35-R1 (BA SB 601R56-04). (TC NR 20060120001) 2L72 4F RTA21EA 20060621001482006062100148SW 2006 6 21 CA060120002 120060117G6220206011111003 BEARING RACE BELL 206 206L1 1182107SW ALLSN 250C 250C28B 03013GL M/R TRUNNION CORRODED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) ON A SCHEDULED 1200 HR M/R CORROSION INSPECTION THE INNER RACE OF THE M/R TRUNNION BEARING WAS FOUND TO BE SEVERLY CORRODED TO THE POINT THAT THE INNER RACE WAS CRACKED. THIS BEARING RACE IS THERMALLY PRESS FIT AND THE TIGHT TOLLERANCE, SEVERE CORROSION AND FLIGHT LOADS CAUSED THIS RACE TO CRACK (TC NR 20060120002) 1G71 3U3 U H2SW E1GL 20060621001512006062100151NM 2006 6 21 CA060120003 120060119G291069744131 CONNECTOR BOEING BOEING737 7378Q8 13844BXNM SHUTOFF VALVE CRACKED W K NONE K FLUID LOSS ININSP/MAINT 1 CA 1815618156 (CAN) RT ENGINE HYDRAULIC SHUTOFF VALVE FOUND LEAKING. FAULT TRACED TO CRACKED CONNECTOR - IPC REF 29-11-81-01, ITEM 50. CONNECTOR REPLACED. (TC NR 20060120003) 2L72 4F RTA16WE 20060621001532006062100153EA 2006 6 21 CA060122001 120060119G33102LA0069137 LIGHT CNDAIRCL600 CL6002C10 1390015EA COCKPIT CONTAMINATED W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 1 CA (CAN) CO-PILOT'S FLOOD LIGHT BELOW I-STRAP AREA WAS CONTAMINATED BY WATER, WHICH SHORTED THE FLOOD LIGHT AND MELTED. (TC NR 20060122001) 2L72 4F RTA21EA 20060621001542006062100154NM 2006 6 21 CA060123001 120060117G3233AE7128852 FLEX LINE BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R320 CR3204123F1 GL NLG LOCK ACT RUPTURED W K NONE K FLUID LOSS ININSP/MAINT 1 CA 5895 (CAN) CREW FOUND A PUDDLE OF THE HYDRAULIC FLUID ON THE GROUND AROUND OF THE NLG STRUT AFTER THE AIRCRAFT WAS PARKED. NLG WHEEL WELL WAS WET CONDITION. RESULT OF THE INSPECTION, FOUND WIRE BRAID BROKEN AND FLUID LEAKAGE ON THE FLEXIBLE HOSE CONNECTED TO THE NLG LOCK ACTUATOR (UP) SIDE. HYDRAULIC FLUID QTY OF THE NR 2 SYSTEM WAS DOWN TO 35 PERCENT. THE BROKEN HOSE WAS REPLACED. BOTH NOSE WHEEL ASSEMBLIES WERE REPLACED. NR 2 HYD FLUID LEVEL WAS ADJUSTED (REFILL). LEAKAGE AND OPERATION CHECK NR 2 HYD SYSTEM (FLT CONTROL, STEERING) OPERATION CHECK AND AIR BLEED NR 2 HYD SYSTEM WITH GHPU. (TC NR 20060123001) 2H72 4T4 TRTA13NM E00062EN6 CP5NE 20060621001552006062100155WP 2006 6 21 CA060123002 120060118G6730D2121 SERVO ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE FLT CONTROLS LEAKING W K NONE O OTHER ININSP/MAINT 1 CA 621 (CAN) SERVO REMOVED FROM SERVICE BECAUSE OF A HYDRAULIC FLUID LEAK. SERVO WAS INSTALLED AT THE FACTORY. (TC NR 20060123002) 1G71 3O3 O H11NM 1E4 20060621001572006062100157GL 2006 6 21 CA060123003 220060121G72506898663 TURBINE WHEEL BELL 407 407 1182206SW ALLSN 250C 250C47B GL ENGINE DAMAGED W BA EMER. DESCENT UNSCHED LANDING EJ VIBRATION/BUFFET WARNING INDICATION CRCRUISE 1 CA 54 (CAN) PILOT HEARD LOUD SQUEALING NOISE FOLLOWED BY VIBRATION WHILE IN CRUISE FLIGHT WITH PASSENGERS. ELECTED TO LAND IMMEDIATELY. NORMAL LANDING AWAY FROM BASE CARRIED OUT. INSPECTION FOUND DAMAGE TO ENGINE TURBINE SECTION, SUSPECT 3RD STAGE TURBINE WHEEL PROBLEM. ENGINE REMOVED AND REPLACED. TURBINE WILL BE SENT FOR INSPECTION. (TC NR 20060123003) 1G71 3U3 UO H2SW E1GL 20060623000312006062300031EA 2006 6 23 CA060123004 120060120G5630C3FS5152 WINDOW DHAV DHC6 DHC6300 2802606EA PWA PT6 PT6A27 52043EA HARTZLHCB3T HCB3TN3 GL PAX DOOR MISSING W K NONE O OTHER ININSP/MAINT 1 CA (CAN) AFTER A TRAINING FLIGHT, AC CAME BACK TO DEPARTURE, WHERE ON THE VISUAL INSPECTION OF EXTERIOR OF FUSELAGE IT WAS NOTICED THAT RT AFT DOOR WAS MISSING EXTERIOR PART OF WINDOW (PLEXIGLASS) INCLUDING WEATHER STRIP AND THE FILLER STRIP. INTERIOR PART OF THE WINDOW (SCRATCH PANE) REMAINED IN PLACE. SURROUNDING AREA ON DOOR AND ALL AFT STRUCTURES THAT COULD HAVE BEEN IN CONTACT WITH THE WINDOWS TRAJECTORY WAS INSPECTED AND NO DAMMAGE WAS FOUND. AT THE TIME OF THIS REPORT, WINDOW, WEATHER AND FILLER STRIPS WERE ORDERED AND AWAITING PARTS. OPERATOR HAS INITIATED A ONE-TIME FLEET INSPECTION ON COMPANY CAMPAIGN NOTICE 451-56-30-004. (TC NR 20060123004) 1H72 3T4 TRTA9EA E4EA 6 CP15EA 20060623000462006062300046GL 2006 6 23 CA060123005 120060110G2560 INERTIA REEL DIAMONDA20 DA20C1 2990001GL CONT O240 IO240B 17063SO SNSNCHW69EK W69EK63 EA SHOULDER BELT BROKEN W K NONE O OTHER TXTAXI/GRND HDL 1 CA 1725 (CAN) PILOT REPORTED THAT THE REEL MECHANISM IN THE LT SHOULDER HARNESS ASSEMBLY ON THE RT SEAT WAS DEFECTIVE AND WAS NOT ALLOWING THE BELT TO RETRACT. AFTER REMOVAL, THE BELT WAS FINALLY RETRACTED AFTER SHAKING THE LOOSE NYLON PIECES THAT HAD BROKEN, INSIDE THE REEL. IT WAS THEN NOTED THAT THE BELT WOULD GO IN AND OUT AS IT NORMALLY DOES BUT THE INERTIA REEL WAS NO LONGER LOCKING. BELT ASSY. WAS REPLACED WITH NEW UNIT (TC NR 20060123005) 1L71 3O3 ONTTA4CH E7SO 5 NTA4CH 20060623000472006062300047CE 2006 6 23 CA060123006 120060119G2897D3899926FJ4 PIN LEAR 45 45LEAR 5170805CE GARRTTTFE731TFE731* 01518WP CONNECTOR BURNED W K NONE B SMOKE/FUMES/ODORS/SPARKS ININSP/MAINT 1 CA 1996 (CAN) WHILE DE-FUELING AC FOR ROUTINE MAINT, IT WAS DISCOVERED THAT LT WING WOULD NOT DE-FUEL. MAINT FOUND THAT STBY FUEL PUMP WAS NOT WORKING. TROUBLESHOOTING FOUND CONNECTOR PLUG P221 UNDER CENTER PEDESTAL HAD A BURNED PIN AND CONNECTOR. PLUG AND CONNECTION BOTH SHOWED SIGNS OF OVERHEATING RESULTING FROM A SHORT CIRCUIT. C/B PROTECTING THIS SYS NEVER TRIPPED. IT IS A 15 AMP C/B. INVESTIGATION REVEALED EICAS INDICATION FOR STBY PUMP WAS (ON), INDICATING PUMP WAS WORKING WHEN IT WAS NOT. CONNECTOR PLUG WAS REPLACED AND FUNCTION CHECKS CARRIED OUT, RETURNED TO SERVICE. DISCUSSION WITH MFG FSR IS ON GOING TO DETERMINE HOW THIS COULD HAPPEN. (TC NR 20060123006) 2L72 4F4 FRTT00008WIE6WE 20060623000492006062300049CE 2006 6 23 CA060124001 120060121G32331158100283 PINION GEAR BEECH BEECH 99 99 1154002CE PWA PT6 PT6A28 EA HARTZLHCB3T HCB3TN3 GL ACTUATOR BROKEN W K NONE O OTHER ININSP/MAINT 1 CA 937 ALG5856 (CAN) THE GEAR ACTUATOR WAS REMOVED FROM THE AIRCRAFT FOR A RELUBE AND END PLAY CHECK IAW AD72-10-04R2 PART B AND C. WHEN IT WAS CLEANED UP THE MECHANIC NOTICED THAT SEVERAL OF THE TEETH ON THE PINION GEAR WERE BROKEN OFF. THERE WAS NO OBVIOUS REASON FOR FAILURE OF THE TEETH. THIS WAS THE FIRST INSPECITON SINCE THE ACTUATOR WAS INSTALLED AFTER OVERHAUL. THE ACTUATOR ALSO FAILED THE END PLAY CHECK BY .003 THOUSANDS OF AN INCH. (TC NR 20060124001) 1L72 3T4 T A14CE E4EA 6 CP15EA 20060705000212006070500021SW 2006 7 5 CA060124002 120060120G2720315372LR RUDDER PEDAL BBAVIA8 8GCBC 1220803SW LYC O360 O360C2E 41514EA MCAULY1A200 1A200* GL COCKPIT CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 7559 (CAN) DURING THE COMPANY STRUCTURAL INSPECTION AND REPAIR PROGRAM (SIRP), THE AIRCRAFT RUDDER PEDALS WERE SENT FOR NDT INSPECTION WHERE IT WAS DISCOVERED THAT BOTH LT AND RT REAR RUDDER PEDALS WERE CRACKED. THESE PEDALS ARE AN OLDER STYLE PEDAL AND ARE NO LONGER AVAILABLE FROM MFG. (TC NR 20060124002) 1H71 3O3 O A21CE E286 5 NP874 20060623000562006062300056EU 2006 6 23 CA060124003 120060119G6710ASNA00190961 SPHERICAL STOP UROCOPEC120 EC120B 8680987EU TMECA ARRIUSARRIU2F NE COLLECTIVE CORRODED W O OTHER F FLT CONT AFFECTED CRCRUISE 1 CA 3341 (CAN) ON MONDAY 16 JANUARY 2006, PILOT REPORTED COLLECTIVE WAS ROUGH AT HIGH POWER SETTING. HE WAS UNABLE TO REPLICATE. (TC NR 20060124003) 1G72 3U3 UNCR0001RD E34NE 20060623000612006062300061SO 2006 6 23 CA060124004 120060124G27206342008 BELLCRANK PIPER PA28 PA28140 7102802SO LYC O320 O320E3D 41508EA SNSNCH74D 74DM EA RUDDER CABLE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 1725017250 (CAN) CRACKS ON THE LT RUDDER CABLE ATTACHING BELLCRANK FOR MORE INFORMATION INCLUDING PICTURES CONTACT SUBMITTER. (TC NR 20060124004) 1L71 3O3 O 2A13 E274 5 NP88614 20060623000622006062300062NM 2006 6 23 CA060124005 120060118G7160 ARM ROTAX AMBLP A150 A150 3850110NM ROTAX 912 ROTAX912F3 EU AIRBOX CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 1490 (CAN) ENGINE RECIEVED FOR OVERHAUL WITH AIRBOX INSTALLED. THE CARB DRIP TRAYS ARE CONNECTED TO THE AIRBOX BY A SUPPORT ARM WITH TWO SCREWS HOLDING THE TRAYS ONTO THE SUPPORT ARM. THE DRIP TRAY SUPPORT ARM WAS FOUND CRACKED AT THE HOLES FOR THE SCREWS. (TC 20060124005) 1B72 3O3 O0 SOOOO2SEE00051EN 20060623000632006062300063NE 2006 6 23 CA060124006 220060118G73218063489 FUEL CONTROL CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE NR 1 ENGINE UNSERVICEABLE W E ENGINE SHUTDOWN O OTHER TXTAXI/GRND HDL 1 CA 178723225 807342 (CAN) NR 1 ENGINE FAILED TO START WITH IGNITION OPERATING NORMALLY. 5 ATTEMPTS WERE MADE BY THE FLIGHT CREW. GROUND PERSONNEL NOTED EXTREME AMOUNT OF FLAMES COMING FROM THE JETPIPE AND ADVISED FLIGHT CREW. FUEL CONTROL SN WYG85082 REPLACED, ENGINE GROUND RUN, STARTS NORMAL. GROUND CHECKED SERVICEABLE. FDR DOWNLOAD SHOWED 2300 LBS OF FUEL FLOW ON START. NORMAL FUEL FLOW ON START EQUALS APPROX. 400 LBS. AFFECTED MFC IS BEING SENT FOR INVESTIGATION AND CORRECTIVE ACTION AS APPLICABLE. (TC NR 20060124006) 2L72 4F4 FRTA21EA E15NE 20060623000642006062300064NM 2006 6 23 CA060125001 120060119G3297471515 WIRE HARNESS BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17EU NLG INOPERATIVE W A UNSCHED LANDING O OTHER CLCLIMB 1 CA 2764 (CAN) AFTER TAKEOFF AND LANDING GEAR SELECTED UP, ALL GREEN AND RED UNLOCK LIGHTS REMAINED ON. AIRCRAFT RETURNED TO AIRPORT. MAINT: PSEU PRESENT FAULTS NG WOW 2, NWCENT LOGGED. LANDING GEAR RETRACTION TEST CONFIRMED FAULT. HARNESS RESISTANCE CHECK CONFIRMED OPEN CIRCUIT. REPLACED WOW2/NWCENT HARNESS ASSY THEN LDG AND NW STEERING TESTED OK. (TC NR 20060125001) 2H72 4T4 TRTA13NM E00062EN6 CP17BO 20060623000652006062300065CE 2006 6 23 CA060125002 120060120G311007601316 COLLAR CESSNA172 172N 2072434CE LYC O360 O360A4A 41514EA SNSNCH76E 76EM8S5 EA INSTRUMENT PANELCRACKED W K NONE O OTHER ININSP/MAINT 1 CA 1299 (CAN) DURING INSPECTION THE PILOT CONTROL COLUMN WAS NOTICED TO HAVE MORE MOVEMENT OFF-AXIS THAN THE CO-PILOT CONTROL PANEL. THE PILOT'S CONTROL COLUMN SUPPORT & LOCK COLLAR WAS FOUND TO BE CRACKED LONGITUDINALLY AND WAS REPLACED NEW. (TC# 20060125002) 1H71 3O3 ONT3A12 E286 5 NP4EA 20060623000672006062300067CE 2006 6 23 CA060125003 120060119G27102660001114 CONTROL CABLE CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE MCAULY3AF34C3GFR34C703 GL AILERONS DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING NORMAL INSPECTION IT WAS FOUND THAT ONE OF THE AILERON WING LOOP CABLES WAS WEARING INTO THE SIDE OF THE LIGHTNING HOLE OF THE FIRST WING RIB ON THE LT WING. THE CABLE WAS DAMAGED AS WELL. THE AIRCRAFT WAS GROUNDED UNTIL THE CABLE WAS REPLACED, THE DAMAGE TO THE LIGHTNING HOLE WAS DRESSED OUT AND THE RUBBER SEAL/GUIDE JUST IB OF THE WING RIB (ON THE FUSELAGE) WAS REPLACED. THE OTHER CARAVANS IN OUR FLEET WERE INSPECTED IN THAT AREA, NO OTHER DEFECTS WERE FOUND. (TC NR 20060125003) 1H71 3T3 T A37CE E4EA 5 CP60GL 20060626001292006062600129CE 2006 6 26 CA060125004 120060124G535050910276BSC CAM BEECH 1900 1900C 1154161CE PWA PT6 PT6A65B 52043EA HARTZLHCB4M HCB4MP3 GL BROKEN W O OTHER O OTHER APAPPROACH 1 CA 2298022980 HEARD A BANG DURING APPROACH, FOUND RT UPPER FWD COWL INNER PORTION HAD LIFTED FROM NORM POSITION. FOUND CAM BOLT FAILED THAT PROVIDES TENSION TO LWR COWL ASSY. OVER CTR COWL FASTENERS ON THESE A/C (4) INSTILL CONSIDERABLE FORCE AND HAVE A HISTORY ON ALL SIMILAR INSTALLATIONS WITH VARIOUS FAILURE MODES. AS A RESULT, INSTALLED A BACKUP SYS OF PROVIDING HARDPOINTS TO ALLOW .032 LOCKWIRE TO BE INSTALLED BETWEEN TWO COWL HALVES, SHOULD ANY OF CAM POINTS FAIL. LOCKWIRE ON INBD POINTS ALSO FAILED BUT OUTER POINTS HELD THRU CONCLUSION OF FLT. COWL SUSTAINED SOME DAMAGE REQUIRING REPLACEMENT. NOW LOOKING AT DEVELOPING AN STC TO REMOVE ORIG CAM SYS ENTIRELY AND GOING WITH AN OVERLAP ARRANGEMENT AND SEVERAL CAMLOCK2L72 4T4 TRTA24CE E4EA 6 CP56GL 20060623001362006062300136EA 2006 6 23 CA060125005 220060119G741410382585 POINTS BENDIX PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA HARTZLHCC2Y HCC2YR2 GL MAGNETO WORN W K NONE O OTHER ININSP/MAINT 1 CA 160 (CAN) WHEN PERFORMING GROUND RUNUP,CHECKING MAGS ON RT ENG, ENG WOULD QUIT WHEN RUNNING ON LT MAG ONLY. TROUBLESHOOTING REVEAL THAT LT POINTS WERE WORN SO MUCH THAT THEY WERE NOT OPENNING. POINTS WERE REPLACED AND ENGINE RAN NORMAL AGAIN. THIS HAS BEEN RECURRING, INTERMITTENT PROBLEM, WHERE YOU CANNOT COUNT ON HOW LONG THE POINTS WILL LAST. PLASTIC NYLON ARM THAT RIDES ON THE CAM, WEARS PREMATURELY UNTIL ITS WORN SO MUCH THAT THE POINTS NO LONGER OPEN AND THEN IT QUITS FIRING. SAME PROBLEM WITH THE DUAL MAGNETO. ALSO IT IS A DIFFICULT AREA TO GET AT TO SEE THE PONTS, USUALLY IT'S ON A 500 HOUR INSPECTION ITEM. (TC NR 20060125005) 1L72 3O3 O A19S0 E286 5 CP920 20060623001732006062300173EA 2006 6 23 CA060125006 220060113G7322 SHAFT SEAL BEECH 90 C90A 1152911CE PWA PT6 PT6A21 52043EA HARTZLHCB3T HCB3TN3 GL FUEL PUMP LEAKING W K NONE O OTHER ININSP/MAINT 1 CA 4185 A75755 (CAN) WHILE DOING A GROUND RUN TO VERIFY THE COMPASS SYSTEM, TECH NOTICED UNCOMMANDED ACCELERATION AND DECELERATION OF THE RT ENGINE. VISUAL INSPECTION IDENTIFIED BLUE DYE WASHOUT FROM THE FUEL PUMP TO FUEL CONTROL UNIT SEAL AREA AND CONFIRMED A FAULT. THE FUEL CONTROL UNIT AND FUEL PUMP ASSEMBLY WERE REMOVED AND REPLACED WITH SERVICEABLE UNITS. (TC NR 20060125006) 1L72 3T4 TRT3A20 E4EA 6 CP15EA 20060623001762006062300176 2006 6 23 CA060125007 420060125G3100 UNKNOWN EMB ERJ190ERJ190100IGW3260408EU GE CF34 CF34* NE UNKNOWN MULTIPLE FAIL W D RETURN TO BLOCK G MULTIPLE FAILURE TXTAXI/GRND HDL 1 CA (CAN) ON TAXI OUT (TWICE) EICAS MESSAGES A/T FAIL, A/P FAIL, AFCS FAIL, MACH TRIM FAIL, SHAKER, ANTICIPATED, ADS 2 FAIL, TAT NR 2 FAIL,ADS FAIL, WINDSHEAR FAIL, AOA LIMIT FAIL, ADS PROBE NR 1 FAIL, ADS PROBE NR 2 FAIL, ADS PROBE NR 3 FAIL, ADS PROBE NR 4 FAIL, STALL PROTECTION FAIL, YD FAIL, ECT. ACTION: ADS PROBES, ADS SYSTEM, TEST CARRIED OUT IAW AMM 34-13-01-06 SYSTEM CHECKS SERVICEABLE. STILL UNDER INVESTIGATION WITH FLEET MANAGEMENT AND MFG ENGINEERING. (TC NR 20060125007) 2L72 4F4 FRTA57NM E15NE 20060623001772006062300177SO 2006 6 23 CA060125008 120060124G55406342008 BAR PIPER PA28 PA28140 7102802SO LYC O320 O320E3D 41508EA SNSNCH74D 74DM EA RUDDER CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 1724917249 (CAN) PILOTS SIDE LT RUDDER BAR, CRACK FOUND ON COLLER BETWEEN ACCUATING ARM (FOR RUDDER CABLE) AND RUDDER BAR. 2 ADDITIONAL CRACKS WERE FOUND ADJACENT TO THE INITAL CRACK. (TC NR 20060125008) 1L71 3O3 O 2A13 E274 5 NP88614 20060623001782006062300178CE 2006 6 23 CA060126001 120060125G5520115610010325 TORQUE TUBE BEECH 115610010341BEECH 99 99 1154002CE PWA PT6 PT6A28 EA HARTZLHCB3T HCB3TN3 GL ELEVATOR CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 1850 (CAN) DURING THE 100 HR INSPECTION THE TAIL CONE WAS REMOVED TO INSPECT THE TORQUE TUBES IAW INSPECTION PACKAGE. THE LT TORQUE TUBE WAS FOUND CRACKED AROUND HALF THE TUBE BRACE. IT HAD BEEN 100 HRS SINCE THE LAST INSPECTION. THE PN OF THE BRACKET IS 115-610018-1 (TC NR 20060126001) 1L72 3T4 T A14CE E4EA 6 CP15EA 20060724000892006072400089NE 2006 7 24 CA060126002 220060118G7200CT78A ENGINE GE CT7TP CT7TP* 30030NE NR 2 MAKING METAL W E ENGINE SHUTDOWN J WARNING INDICATION CRCRUISE 1 CA 686 NR 2 ENGINE CHIP LIGHT WAS EXPERIENCED ON OB LEG TO THE FPSO. THE AIRCRAFT WAS TURNED AROUND FOR DEPARTURE POINT. THERE WAS A SECOND INDICATION OF OIL BYPASS, HIGHER TGT AND LOWER OIL PRESSURE. ENGINE WAS SHUTDOWN BY THE FLIGHT CREW. THE AIRCRAFT RETURNED TO BASE ON SINGLE ENGINE WITHOUT FURTHER INCIDENT. UPON ARRIVAL BACK TO BASE THE ENGINE WAS INVESTIGATED AND FOUND TO HAVE METAL CONTAMINATION ON THE CHIP PLUG AND SUMP SCREENS. THE ENG WAS REPLACED AND FORWARDED TO THE MFG FOR A FURTHER INVESTIGATION. 4 T E8NE 20060623001802006062300180 2006 6 23 CA060126005 420060123G233050401100003 VIDEO DISPLAY BOEING737 737* NM CFMINTCFM567CFM567B22 13802NE SEAT 11B SMOKE W H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 1 CA (CAN) ON JANUARY 23, 2006 A/C WAS IN CRUISE WHEN SMOKE WAS OBSERVED COMING FROM SEAT 11B VDU. THE IFE SYSTEM WAS DEACTIVATED. MAINTENANCE REPLACED THE VDU AND THE SYSTEM WAS TESTED SERVICEABLE. THIS COMPONENT WILL BE RETURNED TO THE MANUFACTURER AND A COMPLETE TEARDOWN REPORT WILL BE REQUESTED. THIS SDR WILL BE UPDATED ONCE THAT INFORMATION IS AVAILABLE. (TC NR 20060126005) 2L72 4F4 FRTA16WE E00055EN 20060623001812006062300181WP 2006 6 23 CA060126006 120060126G53435484911503 ATTACH FITTING DOUG DOUG DC6 DC6A 3021706WP PWA R1340 CWASP 52016NE HAMSTD43E 43E60 NE MLG CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 42266 (CAN) DURING ANNUAL INSPECTION, AD 89-11-07 WAS BEING ACCOMPLISHED. THE LT IB MLG ATTACH FITTING WAS FOUND TO BE CRACKED BETWEEN THE 4TH AND 5TH FASTENER HOLES ON THE OB VERTICAL LEG. THERE WERE 2 CRACKS NOTED. THE LENGTH OF THE CRACK RUNNING BETWEEN THE 2 FASTENER HOLES IS APPROXIMATELY .7500 INCH. THERE WAS A SECOND CRACK NOTED RUNNING IN AN OUTWARD DIRECTION AND IS APPROXIMATELY .2500 INCH IN LENGTH. THE FITTING IS BEING REPLACED WITH A SERVICEABLE FITTING. (TC NR 20060126006) 2L74 4R3 R 6A3 ATC14 6 CP871 20060623001832006062300183GL 2006 6 23 CA060126007 320060120G6111T10282N BLADE HARTZL HCB3TN5 SWRNGNSA226 SA226TC 8780404SW GARRTTTPE331TPE33110UA 01514WP HARTZLHCB3T HCB3TN5 GL PROPELLER DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA 2390 BVA7387 BVA7387 (CAN) DISCOVERED WARPED TRAILING EDGE OF PROPELLER BY MAINTENANCE. UNIT HAD BEEN OVERHAULED FEB 2003 THEN RETURNED FOR THIN TRAILING EDGE APRIL 2003. REPAIRED BY SAME FACILITY. TRAILING EDGE WAS SIGNIFICANTLY THINNER THAN SIMILAR IN FLEET. REMOVED PROPELLER FROM SERVICE. (TC NR 20060126007) 2L72 4T4 TRTA8SW E4WE 6 CP15EA 20060623001842006062300184CE 2006 6 23 CA060126008 120060124G5540MS289135 BEARING BEECH 1306300001 BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE HARTZLHCE4A HCE4A3I NE RUDDER WORN W K NONE O OTHER ININSP/MAINT 1 CA 207 (CAN) DURING A GENERAL WALKAROUND THE RUDDER WAS MOVED BY HAND. NOTICING THAT THE RUDDER SEEMED TO MOVE UP AND DOWN AND APPEARED TO RUB AGAINST THE TAIL CONE. RUDDER ATTATCHMENT INSPECTED. INVESTIGATION REVEALED THAT ALL THREE BEARINGS HAVING SOME PLAY. THE LOWER BEARING SEEMED TO CAUSE THE RUDDER TO DROP. THIS INTURN WORE THE CLEVIS BRACKETS. REPLACED ALL THREE BEARINGS AND BOTH CLEVIS BRACKETS. RUDDER REINSTALLED AND TRAVEL CHECKED OK. AIRCRAFT RETURNED TO SERVICE. (TC NR 20060126008) 2L72 4T4 TRTA24CE E26NE 5 CP10NE 20060623001872006062300187NM 2006 6 23 CA060127001 120060127G541085410617005 DOOR DHAV DHC8 DHC8301 1386003NM PWA PW120 PW123 NE HAMSTD14SF 14SF23 NE RT NACELLE SEPARATED W O OTHER D INFLIGHT SEPARATION TXTAXI/GRND HDL 1 CA (CAN) ON ARRIVAL TO BASE, THE DOOR FOR THE REFUEL PANEL WAS FOUND TO HAVE SEPARATED FROM THE NACELLE. THE HINGES, HINGE ATTACHMENT BOLTS AND SMALL FRAGMENTS OF THE COMPOSITE PANEL REMAINED ATTACHED. (TC NR 20060127001) 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20060623002032006062300203 2006 6 23 CA060127002 420060123G2562ELT10 ELT BEECH 100 A100 1152915CE PWA PT6 PT6A28 EA HARTZLHCD4N3HCD4N3A GL CABIN INTERMITTENT W K NONE L NO TEST ININSP/MAINT 1 CA 50 (CAN) ELT FAILED THE ACTIVATION TEST DURING THE ROUTINE INSPECTION. THE UNIT HAD THE BATTERY REPLACED AND RECERTIFIED 21 DAYS EARLIER. AVIONICS SHOP FOUND THE PROBLEM TO BE A INTERMITTENT ON/OFF SWITCH. (TC NR 20060127002) 1L72 3T4 T A14CE E4EA 5 CSTC 20060623002042006062300204CE 2006 6 23 CA060127003 120060119G7333903800097 INDICATOR BEECH 90 F90 1152909CE PWA PT6 PT6A135 52043NE HARTZLHCB4T HCB4TN3 GL FUEL FLOW FAILED W O OTHER N FALSE WARNING CRCRUISE 1 CA (CAN) FUEL FLOW INDICATIONS WENT INTERMITTENT THEN FAILED IN FLIGHT. FOUND TRANSMITTER TO HAVE FAILED INTERNALLY. TIME ON UNIT APROX.5000 HRS. (TC NR 20060127003) 1L72 4T4 T A31CE E4EA 6 CP40EA 20060623002052006062300205CE 2006 6 23 CA060127004 120060126G510010038900161 SWITCH BEECH 100 A100 1152915CE PWA PT6 PT6A28 EA HARTZLHCD4N3HCD4N3A GL FUEL DRAIN UNSERVICEABLE W K NONE O OTHER ININSP/MAINT 1 CA (CAN) FLOAT SWITCH FAILED INTERNALLY CAUSING THE EPA CAN TO DRAIN OVERBOARD ON SHUTDOWN. (TC NR 20060127004) 1L72 3T4 T A14CE E4EA 5 CSTC 20060623002062006062300206EU 2006 6 23 CA060127005 220060124G7260DART5342 ENGINE BRAERO748 HS7482A 4231001EU RROYCEDART DART5342 EU ROTOL R4304 R2124304 EU NR 1 FAILED W H DEACTIVATE SYST/CIRCUITS YJ ENGINE STOPPAGE WARNING INDICATION DEDESCENT 1 CA (CAN) ON DESCENT INTO AIRPORT, THE NR 1 ENGINE FAILED. THE AIRCRAFT LANDED WITHOUT FURTHER INCIDENT. (TC NR 20060127005) 2L72 3T4 T A24EU A196 6 CP899 20060711001162006071100116SW 2006 7 11 CA060127006 120060127G321071461 LANDING GEAR BBAVIA8 8GCBC 1220803SW LYC O360 O360C2E 41514EA MCAULY1A200 1A200* GL CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 796 (CAN) 2 SMALL CRACKS UNDER UPPER RADIUS OF LANDING GEAR. 1H71 3O3 O A21CE E286 5 NP874 20060623002082006062300208EU 2006 6 23 CA060127007 120060127G3097330A63622309 WIRE HARNESS SNIAS AS332 AS332L 8680809EU TMECA MAKILAMAKILA1A 60040EU DE ICE SYS WORN W K NONE O OTHER ININSP/MAINT 1 CA 101 (CAN) A/C RETURNED FROM AN OFFSHORE TRIP, THE MAINTENANCE STAFF WERE CARRING OUT A ROUTINE TURN AROUND CHECK AND FOUND THE M/R DEICE HARNESS BROKEN AT THE CONNECTOR PLUG. MAINTENANCE DEPT REPLACED THE HARNESS AND THE A/C RETURNED TO THE FLYING SCHEDULE. (TC NR 20060127007) 2G72 4U4 U H4EU E12NE 20060623002102006062300210NE 2006 6 23 CA060129001 220060125G7261PW535A ENGINE CESSNA500 560CESSNA 2076750CE PWA 530 PW535A NE LOW PRESSURE W EA ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 CA (CAN) DURING CRUISE, THE LOW OIL PRESSURE WARNING ANNUNCIATED. THE ENGINE WAS SHUTDOWN IN FLIGHT AND THE AIRCRAFT DIVERTED FOR AN UNSCHEDULED LANDING. MFG WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060129001) 2L72 4F4 FRTA22CE E00053EN 20060623002122006062300212NE 2006 6 23 CA060129002 220060115G732250099820 PUMP AEROSPATR72 ATR72 EU PWA PW120 PW127 NE FUEL BOOST FAULTY W E ENGINE SHUTDOWN RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 1 CA (CAN) DURING CRUISE, THE ENGINE LOST POWER AND WAS SHUTDOWN INFLIGHT. SUBSEQUENT INVESTIGATION DETERMINED THE HYDROMECHANICAL FUEL CONTROL TO BE FAULTY. FUEL CONTROL AND FUEL PUMP WERE REPLACED. (TC NR 20060129002) 2H72 4T4 TRT E20NE 20060626000652006062600065NE 2006 6 26 CA060129004 220060123G7200PW545A ENGINE CESSNA500 560CESSNA 2076750CE PWA 545 PW545A NE DAMAGED W EA ENGINE SHUTDOWN UNSCHED LANDING KAJFLUID LOSS FLAME/FIRE WARNING INDICATION CLCLIMB 1 CA (CAN) DURING CLIMB, THE CREW OBSERVED ENGINE TEMPERATURE AND FUEL FLOW SPLIT. THE FLIGHT DIVERTED TO POINT OF DEPARTURE AND THE ENGINE WAS SHUT DOWN DURING DESCENT. SUBSEQUENT INSPECTION REVEALED DAMAGE TO THE ENGINE INNER BYPASS DUCTING CONSISTENT WITH AN INTERNAL ENGINE FIRE. MFG WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060129004) 2L72 4F4 FRTA22CE E00059EN 20060626000762006062600076EA 2006 6 26 CA060129005 220060120G7200 ENGINE BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA FIRE W EA ENGINE SHUTDOWN UNSCHED LANDING ARJFLAME/FIRE PARTIAL RPM/PWR LOSS WARNING INDICATION CLCLIMB 1 CA (CAN) THE ENGINE WAS REPORTED TO EMIT A LOUD NOISE ACCOMPANIED BY A LOSS IN POWER AND FLAMES EMINATING FROM THE EXHAUST. THE ENGINE WAS SHUT DOWN IN FLIGHT. MFG WILL MONITOR INVESTIGATION OF THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC NR 20060129005) 1L72 4T4 T A24CE E4EA 20060626000772006062600077NE 2006 6 26 CA060129006 220060118G7200 ENGINE CESSNA500 560CESSNA 2076750CE PWA 530 PW535A NE FLAMED OUT W O OTHER XJ ENGINE FLAMEOUT WARNING INDICATION TXTAXI/GRND HDL 1 CA DC0262 (CAN) THE ENGINE FLAMED OUT DURING GROUND HANDLING OPERATIONS. MFG WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060129006) 2L72 4F4 FRTA22CE E00053EN 20060626000782006062600078 2006 6 26 CA060129007 420060112G61223037685 GOVERNOR PILATSPC12 PC12 7090550EU PWA PT6 PT6A67B 52043NE OVERSPEED FAULTY W A UNSCHED LANDING RF PARTIAL RPM/PWR LOSS FLT CONT AFFECTED CRCRUISE 1 CA 1599 1 (CAN) DURING CRUISE THE PROPELLER SPEED DECREASED. AN UNSCHEDULED LANDING WAS CARRIED OUT WHICH RESULTED IN A PROPELLER STRIKE. SUBSEQUENT INSPECTION REVEALED A FAULTY PROPELLER OVERSPEED GOVERNOR. IAW WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC NR 20060129007) 1L71 3T4 TRTA78EU E26NE 20060626000792006062600079NE 2006 6 26 CA060129008 220060110G7321 FUEL CONTROL BELL 412 412 1182202SW PWA PT6T PT6T3B 52045NE ENGINE FAULTY W A UNSCHED LANDING RXJPARTIAL RPM/PWR LOSS ENGINE FLAMEOUT WARNING INDICATION CRCRUISE 1 CA (CAN) DURING FLIGHT, THE ENGINE LOST POWER FOLLOWED BY (ENGINE OUT) AND (LOW ROTOR SPEED) WARNING ANNUNCIATIONS. A SINGLE-ENGINE UNSCHEDULED LANDING WAS CARRIED OUT. SUBESQUENT INSPECTION REVEALLED A FAULTY AUTOMATIC FUEL CONTROL UNIT. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC NR 20060129008) 1G72 4U4 U H4SW E22EA 20060626000812006062600081NE 2006 6 26 CA060129010 220060111G7200 ENGINE PILATSPC12 PC12 7090550EU PWA PT6 PT6A67B 52043NE MALFUNCTIONED W A UNSCHED LANDING O OTHER NRNOT REPORTED 1 CA PR0565 (CAN) DURING FLIGHT TEST OPERATIONS (PERFORMING ENGINE RELIGHT) ENGINE DID NOT RELIGHT. A DEADSTICK LANDING WAS ACCOMPLISHED. MFG WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060129010) 1L71 3T4 TRTA78EU E26NE 20060626000822006062600082NE 2006 6 26 CA060129011 220060111G7200 ENGINE PROPJT200 200A 0140304NM PWA 306 PW306B NE SHUTDOWN W O OTHER YJ ENGINE STOPPAGE WARNING INDICATION LDLANDING 1 CA CC0045 (CAN) ON ROLL OUT FOLLOWING LANDING, THE PILOT REPORTED AN UNCOMMANDED ENGINE SHUT DOWN. THE ENGINE BLEED VALVES AND BLEED VALVE SOLENOID WERE SUBSEQUENTLY REPLACED. (TC NR 20060129011) 1L71 3O4 F 3A18 E35NE 20060626000832006062600083CE 2006 6 26 CA060129012 120060102G7931PT6A6D ENGINE BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE LOW PRESSURE W C ABORTED TAKEOFF J WARNING INDICATION TOTAKEOFF 1 CA (CAN) DURING TAKE-OFF ROLL, THE ENGINE LOW PRESSURE WARNING ANNUNCIATED AND THE TAKE-OFF WAS ABORTED. MFG WILL MONITOR INVESTIGATION OF THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060129012) 2L72 4T4 TRTA24CE E26NE 20060626000842006062600084EA 2006 6 26 CA060129013 220060102G7230 COMPRESSOR BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA HARTZLHCD4N3HCD4N3A GL ENGINE DAMAGED W EA ENGINE SHUTDOWN UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION DEDESCENT 1 CA 81119 (CAN) DURING DESCENT, THE ENGINE EXPERIENCED AN UNCOMMANDED POWER REDUCTION, ACCOMPANIED BY NOISE AND FLAMES EMANATING FROM THE EXHAUST. THE ENGINE WAS SHUT DOWN IN FLIGHT, AN EMERGENCY DECLARED AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE. SUBSEQUENT INSPECTION REVEALED COMPRESSOR SECTION DAMAGE. MFG WILL MONITOR INVESTIGATION OF THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060129013) 1L72 4T4 T A24CE E4EA 5 CSTC 20060626000862006062600086NM 2006 6 26 CA060129014 120060104G7900 ENGINE PW308C AMD FALC50FALCON2000 2730170NM PWA 306 PW306B NE ODOR W O OTHER BOOSMOKE/FUMES/ODORS/SPARKS OTHER OTHER NRNOT REPORTED 1 CA CF0049 (CAN) THE ENGINE WAS REPORTED TO EXHIBIT OIL SMELL IN CABIN AIR ACCOMPANIED BY HIGH OIL CONSUMPTION. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC NR 20060129014) 2K72 4F4 FRTA50NM E35NE 20060626000882006062600088EU 2006 6 26 CA060129015 120060103G361031B576201 LINE BRAERO1000 BAE1251000 1500287EU PWA 305 PW305B 52128NE PNEUMATIC SYS FRACTURED W EA ENGINE SHUTDOWN UNSCHED LANDING N FALSE WARNING CLCLIMB 1 CA (CAN) FOLLOWING TAKEOFF, THE ENGINE FIRE WARNING ANNUNCIATED AND THE ENGINE WAS REPORTED TO BE (TRAILING SMOKE). THE ENGINE WAS SHUTDOWN IN FLIGHT, AN EMERGENCY DECLARED AND THE FLIGHT DIVERTED TO POINT OF DEPARTURE. SUBSEQUENT INSPECTION REVEALED NO EVIDENSE OF FLUID LOSS OR FIRE. A BLEED VALVE PNEUMATIC TUBE WAS FOUND FRACTURED. (TC NR 20060129015) 2L72 4F4 FRTA3EU E35NE 20060703000502006070300050NE 2006 7 3 CA060129019 220060102G7200 ENGINE LEAR 60 60LEAR 5170707CE PWA 305 PW305A 52128NE MALFUNCTIONED W E ENGINE SHUTDOWN JA WARNING INDICATION FLAME/FIRE TXTAXI/GRND HDL 1 CA DURING START, AN ENGINE FADEC WARNING LIGHT ANNUNCIATED ACCOMPANIED BY FUEL AND FLAME EMANATING FROM THE ENGINE EXHAUST. THE START WAS ABORTED. PWC WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2L72 4F4 FRTA10CE E35NE 20060703000512006070300051NE 2006 7 3 CA060129020 220060110G7321 FUEL CONTROL PILATSPC12 PC12 7090550EU PWA PT6 PT6A67B 52043NE ENGINE FAULTED W D RETURN TO BLOCK RJ PARTIAL RPM/PWR LOSS WARNING INDICATION TXTAXI/GRND HDL 1 CA DURING TAXI, THE ENGINE EXPERIENCED AN UNCOMMANDED POWER REDUCTION. THE ENGINE WAS SHUT DOWN. SUBSEQUENT INSPECTION REVEALED A FAULTY FUEL CONTROL UNIT. P&WC WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED. 1L71 3T4 TRTA78EU E26NE 20060703000522006070300052NE 2006 7 3 CA060129021 220060121G7200 ENGINE AEROSPATR72 ATR72212A 8680902EU PWA PW120 PW127 NE POWER LOSS W E ENGINE SHUTDOWN RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 1 CA AV0032 DURING CRUISE, ENGINE EXPERIENCED AN UNCOMMANED POWER REDUCTION. THE ENGINE WAS SHUT DOWN IN FLIGHT. PWC WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2H72 4T4 TRTA53EU E20NE 20060703000532006070300053WP 2006 7 3 CA060130001 120060116G6321E02400373500S SPRING ROBSIN ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE ROTOR BRAKE BROKEN W K NONE O OTHER ININSP/MAINT 1 CA 92 10913 DURING THE FIRST 100 HR INSPECTION CARRIED OUT ON THE AIRCRAFT, IT WAS NOTICED THAT THE ABOVE SPRING WAS BROKEN. IT APPEARS TO HAVE BROKEN AT THE UPPER ATTACHMENT POINT WHERE IT ATTACHES TO THE LOWER ROTOR BRAKE CALIPER ARM. THE SPRING WAS REPLACED WITH NEW. 1G71 3O3 O H11NM 1E4 20060703000542006070300054CE 2006 7 3 CA060130002 120060125G5610 WINDSCREEN BEECH 90 C90A 1152911CE PWA PT6 PT6A21 52043EA HARTZLHCB3T HCB3TN3 GL COCKPIT FAILED W B EMER. DESCENT O OTHER CRCRUISE 1 CA WHILE IN CRUISE FLIGHT AT FL230, THE LT WINDSHIELD INNER PANE SHATTERED. THE WINDSHIELD ANTI-ICE HAD BEEN SELECTED AT NORMAL SINCE DEPARTURE AND THE OAT WAS –38°C. THE CREW CONTACTED ATC TO DECLARE AN EMERGENCY AND REQUESTED RETURN TO AIRPORT. THE CREW THEN COMPLETED THE CRACKED OR SHATTERED WINDSHIELD CHECKLIST. AS A PRECAUTION, THE OXYGEN MASKS WERE DONNED BY THE CREW MEMBERS AND PASSENGERS. THE CAPTAIN FLEW THE APPROACH AND THE CO-PILOT FLEW THE DESCENT TO VISUAL AND LANDED SAFELY ON RWY 06. 1L72 3T4 TRT3A20 E4EA 6 CP15EA 20060703000552006070300055NE 2006 7 3 CA060130003 220060116G72503053094CL9 SHROUD BEECH 90 F90 1152909CE PWA PT6 PT6A135 52043NE HARTZLHCB4T HCB4TN3 GL HOT SECTION DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA 1245 ROUTINE BOROSCOPE INSPECTION OF HOT SECTION COMPONENTS REVEALED THAT TWO CT SEGMENTS HAD DROPPED OUT OF PLACE AND CONTACTED CT WHEEL. THE SEGMENT RETAINING RING P/N 3020139 WAS FOUND OUT OF PLACE AND THE CT BLADES HAD WORN BEYOND LIMITS DUE TO HEAVY TIP RUB. THE WHEEL WAS REBLADED AND SEGMENTS REPLACED WITH P/N 3035673CL12 AND RETAINING RING P/N 3110741-02, SB1627 AND SB1628 WERE EMBODIED. 1L72 4T4 T A31CE E4EA 6 CP40EA 20060703000562006070300056NE 2006 7 3 CA060130004 220060116G72503053094CL14 SHROUD BEECH 90 F90 1152909CE PWA PT6 PT6A135 52043NE HARTZLHCB4T HCB4TN3 GL HOT SECTION DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA 1666 ROUTINE BOROSCOPE INSPECTION OF HSI COMPONENTS FOUND TWO SEGMENTS HAD DROPPED OUT OF POSITION. POWER SECTION REMOVED AND CT COMPONENTS INSPECTED. CT BLADES FOUND TO HAVE CONTACTED SEGMENT ENDS AND RETAINING RING P/N 3020159 FOUND OUT OF PLACE. SEGMENTS REPLACED WITH NEW P/N 3053094CL16 AND NEW RETAINING RING P/N 3020159 AND ALTERNATE SEGMENTS AND RING NOT AVAILABLE IN THE REQUIRED CLASS. ENGINE REASSEMBLED. SB1627 EMBODIED. 1L72 4T4 T A31CE E4EA 6 CP40EA 20060703000572006070300057CE 2006 7 3 CA060130005 120060124G5344 HINGE BEECH 200 B200 1152922CE PWA PT6 PT642A NE HARTZLHCE4N HCE4N3 NE CABIN DOOR FAILED W O OTHER O OTHER TXTAXI/GRND HDL 1 CA 598 CABIN DOOR SIDE OF HINGE WAS REPLACED ON MARCH 15 2005 AT 5248.4 TTAF AND 4829 CYCLES. DOOR SIDE OF HINGE FAILED JAN 23 2006 AT 5846.8 TTAF AND 5480 CYCLES DOOR AND HINGE AREA WAS INSPECTED AND NO ADDITIONAL DAMAGE WAS NOTED CHERRYMAX RIVETS WHICH WERE INSTALLED WERE FOUND TO BE INCORRECT SIZE. RECTIFICATION WAS TO REPLACE CHERRYMAX RIVETS WITH SOLID RIVETS. 1L72 4T4 T A24CE E4EA 5 CP10NE 20060703000582006070300058EA 2006 7 3 CA060131001 120060124G2497 WIRE HARNESS CNDAIRCL600 CL6002C10 1390015EA DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA 6607 DURING T/S OF INOP LAV LIGHTS, FOUND 6 WIRES BELOW FLOOR, RT SIDE AFT FWD SERVICE DOOR DAMAGED, BURNED. SMALLER HARNESS IS ROUTED UNDER LARGER HARNESS. TWO BUNDLES WERE NOT SECURED AND THIS ALLOWED 2 HARNESSES TO RUB UNTIL CENTER CONDUCTORS EXPOSED AND A POWER AND GROUND MADE CONTACT RESULTING IN BLACK RESIDUE ON THE HARNESSES. WIRING WAS REPLACED AND HARNESS SECURED TO ELIMINATE THE FOULING. FOLLOWING WIRES ARE DAMAGED, OUTER JACKET DAMAGE WIRE NO ATA SYSTEM FBF7941-22 28-40-00, REFUEL/DEFUEL PANEL FBG6885-18 33-21-00, RT CEILING LT DIM/BRT FBG6884-18 33-21-00, RT CEILING LT DIM CONTROL CORE EXPOSED WIRE NO ATA SYSTEM FBF6420-22 33-24-00, FASTENER SEAT BELT SIGN FBH6770-22 33-22-00, PSU TEST FBH6771-22 33-2L72 4F RTA21EA 20060703000592006070300059EU 2006 7 3 CA060131002 120060127G21605829C00 CONTROLLER PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL CABIN TEMP FAILED W O OTHER J WARNING INDICATION TXTAXI/GRND HDL 1 CA 810 PILOT SELECTED ENVIRONMENTAL SYSTEMS TO AUTO PRIOR TO FLIGHT AND RECEIVED A CAUTION LIGHT ON PANEL THAT THE SYSTEM WAS NOT FUNCTIONING. THE SYSTEM WAS CYCLED ON AND OFF THEN AN INCREASE IN POWER WAS APPLIED AND THE CAUTION LIGHT EXTINGUISHED INDICATING NORMAL. FURTHER FLIGHTS THAT DAY WERE UNEVENTFUL. MAINTENANCE TROUBLESHOOTING VIA THE MANUAL SWITCH FROM FULL COLD THEN FULL HOT RESULTED IN A STUCK IN HOT VALVE. THE TEMP VALVE WAS REPLACED AND SYSTEM FUNCTIONED FINE. AIRCRAFT TTSN 4650HRS,CYC 3286, THE ORIGINAL VALVE WAS REPLACED AT 3837 HRS 2662 CYC. THE ONE REPORTED FAILED AT 810 HRS AND 622 CYC. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20060703000962006070300096CE 2006 7 3 CA060131003 120060120G2823S160315865 CABLE CESSNA337 337C 2075712CE CONT O360 IO360C 17025SO FUEL SELECTOR BENT W EA ENGINE SHUTDOWN UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 1 CA AIRCRAFT WAS IN CRUISE FLT WHEN THE PILOT ATTEMPTED TO CHANGE LT FUEL SELECTOR FOR FORWARD ENGINE TO A DIFFERENT TANK. WHEN SELECTED THE KNOB STOPPED AT THE 1/2 WAY POINT CAUSING FUEL FLOW AND ENGINE POWER TO DECREASE. THE PILOT SHUT DOWN THE ENGINE AND CONTINUED TO BASE WITHOUT FURTHER INCIDENT. UPON MAINTENANCE INSPECTION, THE SELECTOR CABLE WAS FOUND KINKED. THE SELECTOR MECHANISM AND SELECTOR KNOB MECHANISM WERE BOTH FOUND TO MOVE FREELY. NO OTHER DISCREPENCIES FOUND. NEW CABLE BEING INSTALLED. 1H72 3O3 O A6CE E1CE 20060705000272006070500027SW 2006 7 5 CA060131004 120060127G6730AN8345D TEE FITTING BELL 206 206B 1181511SW ALLSN 250C 250C20 03013GL SERVO ACTUATOR CRACKED W HA DEACTIVATE SYST/CIRCUITSUNSCHED LANDING F FLT CONT AFFECTED CRCRUISE 1 CA 3153 WHILE IN CRUISE FLIGHT, THE PILOT FELT FEEDBACK SHOCK IN THE CYCLIC CONTROL. THE PILOT ISOLATED HYDRAULICS AND MADE AN UNSCHEDULED LANDING. MAINTENANCE CREW PERFORMED AN INSPECTION OF THE HYDRAULIC FLIGHT CONTROL SYSTEM. A TEE FITTING THE LEFT HAND SERVO ACTUATOR WAS FOUND CRACKED AROUND HALF IT'S DIAMETER RESULTING IN A LEAK. 1G71 3U3 U H2SW E4CE 20060705000302006070500030GL 2006 7 5 CA060131005 220060120G725023001967 TURBINE WHEEL ALLSN 6898735 ALLSN 25OC 250C20R GL ENGINE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 819 CAT25545 TURBINE RECEIVED AT ETI FOR REPAIR. NR 3 TURBINE WHEEL INSPECTED ON TEARDOWN. NR 3 TURBINE WHEEL SENT TO NDT FOR FPI. CRACKS WERE FOUND ON RIM. LOG CARDS SHOW THAT NR 3 TURBINE WHEEL (S/N HX-84-131) HAS TTSN: 819.1 AND TCSN: 770. NR 3 TURBINE WHEEL LIFE IS TT: 4450 ^ TC: 6000. 3 U E4CE 20060705000362006070500036CE 2006 7 5 CA060201001 120060201G571112212352 SPAR CESSNA210 T210N 2073456CE CONT O520 TSIO520R 17040SO MCAULYD3A34 D3A34C402 GL RT WING CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 3861 3861 A 100 HR INSPECTION WAS STARTED A CRACK WAS DISCOVERED AT THE RIGHT FRONT SPAROUT BOARD END WHERE IT ATTACHES TO THE SUB SPAR. THE CRACK IS VERTICAL RUNNING APPROXIMATELY 1 1/2 TO TWO INCHES IN LENGTH. THE CRACK STARTS AT THE TOP AND RUNS DOWN THROUGH A RIVET AND CONTINUES ON. 1H71 3O3 O 3A21 E8CE 5 CP47GL 20060705000372006070500037GL 2006 7 5 CA060201002 320060201G6111 BEARING HARTZL HC83V202C GRUMAVSTC STCSCANTY30 HARTZLHC83V HC83V202 GL PROPELLER CORRODED W K NONE O OTHER ININSP/MAINT 1 CA UPON MPI INSPECTIONS, IT WAS NOTED THAT 2 A14B BEARINGS, 2 C838-6 CLAMPS, 1 C1404 HUB, AND 1 A1496-0 ARM WERE ALL CORRODED BEYOND LIMITS. THROUGH DIMENSIONAL INSPECTIONS THE FOLLOWING PARTS WERE FOUND TO BE WORN BEYOND SERVICEABLE LIMITS, 1 B806 CYLINDER AND ONE A871 MUSHROOM. 1H72 3I A734 5 CP14EA 20060705000382006070500038GL 2006 7 5 CA060201003 320060201G6111 CLAMP HARTZL HC83V202C GRUMAVSTC STCSCANTY30 HARTZLHC83V HC83V202 GL PROPELLER CORRODED W K NONE O OTHER ININSP/MAINT 1 CA D1629 UPON MPI INSPECTION IT WAS NOTED THAT 2 A14B BEARINGS, 3 C838-6 CLAMPS, 1 C1404 HUB, AND 2 A1496-0 ARMS WERE ALL CORRODED BEYOND LIMITS. THROUGH DIMENSIONAL INSPECTIONS THE FOLLOWING PARTS WERE FOUND TO BE WORN BEYOND SERVICEABLE LIMITS,1 B806 CYLINDER AND 1 A871 MUSHROOM. 1H72 3I A734 5 CP14EA 20060705000392006070500039CE 2006 7 5 CA060201004 120060129G53441154400311 HINGE BRACKET BEECH 100 100BEECH 1152916CE PWA PT6 PT6A28 EA FUSELAGE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA A 3/4 INCH CRACK WAS DISCOVERED WHEN MAINTENANCE WENT TO CHANGE A BUSHING. 1L72 3T4 T A14CE E4EA 20060705000402006070500040CE 2006 7 5 CA060202001 120060131G5297 WIRE BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE HARTZLHCE4A HCE4A3I NE CARGO BAY CHAFED W K NONE N FALSE WARNING ININSP/MAINT 1 CA A/C BROUGHT INTO HANGAR AFTER THE DAY OF FLYING. WHILE IN THE HANGAR THE CARGO DOOR WARNING CAME ON. INSPECTED THE DOOR WARNING AND FOUND THE DOOR AJAR SWITCH STICKY AND THE LATCH HANDLE SWITCH CRACKED. SWITCHES REPLACED ALL CHECKED OK. THE REASON FOR THIS SDR IS THAT DURING THE INSPECTION OF THE CARGO DOOR ELECTRICAL SYSTEM FOUND THAT THE LOWER WIRING HAS BEEN CHAFING ON THE DOOR. THIS COULD POSSIBLE CAUSE ERRONEOUS INDICATIONS IN THE FUTURE. SPIRAL WRAP WAS PLACED ON THE WIRING AND WIRING RESECURED TO TYWRAP POINTS. WOULD SUGGEST THAT THIS WIRING BE SPIRAL WRAPPED TO PREVENT THIS FROM CAUSING A FAULT IN THE FUTURE. 2L72 4T4 TRTA24CE E26NE 5 CP10NE 20060705000412006070500041NE 2006 7 5 CA060202002 220060201G7261 OIL SYSTEM AEROSPATR42 ATR42300 8680920EU PWA 120 PW120 NE HAMSTD14SF 14SF5 NE NR 1 ENGINE LEAKING W E ENGINE SHUTDOWN KJ FLUID LOSS WARNING INDICATION CRCRUISE 1 CA AFTER DEPARTING, THE CREW OBSERVED LOSS OF OIL PRESSURE ON NR 1 ENGINE. THE AIRCRAFT RETURNED TO POINT OF DEPARTURE WITHOUT FURTHER INCIDENT. 2H72 4T4 TRTA53EU E20NE 6 CP7NE 20060705000432006070500043NM 2006 7 5 CA060202003 120060129G2910 HYDRAULIC LINE BOEING737 737522 138449FNM CFMINTCFM56 CFM563C1 13802EU THRUST REVERSER CHAFED W K NONE K FLUID LOSS NRNOT REPORTED 1 CA HYDRAULIC LEAK DISCOVERED ON STOW LINE TO LT INBOARD THRUST REVERSER SYNC ACTUATOR ON NR 2 ENGINE, CAUSED FROM RUBBING ON AN ANGLE EDGE SUPPORT. LINE REMOVED AND FITTINGS CAPPED. A FLEET CAMPAIGN IS NOW IN PROGRESS TO CHECK ALL SYNC ACTUATOR LINES FOR DAMAGE. 2L72 4F4 FRTA16WE E21EU 20060705001112006070500111SO 2006 7 5 CA060202004 120060118G71208621202 MOUNT PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA HARTZLHCC2Y HCC2YR2 GL LEFT ENGINE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 8436 WHILE CARRYING OUT SCHEDULED 100 HOUR INSPECTION ON LEFT ENGINE A CRACK ON THE LT ENGINE MOUNT TOP OUTBOARD SECTION WAS NOTED. MOUNT WAS REMOVED, REPAIRED AND REINSTALLED. 1L72 3O3 O A19S0 E286 5 CP920 20060705001132006070500113 2006 7 5 CA060202005 420060201G2330 VIDEO DISPLAY BOEING737 737* NM CFMINTCFM567CFM567B22 13802NE SEAT 3C MALFUNCTIONED W H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 1 CA A/C WAS IN CRUISE WHEN THE VDU AT SEAT 3C WENT BLANK FOLLOWED BY A SLIGHT ELECTRICAL SMELL. THE IFE SYSTEM WAS DEACTIVATED. MAINTENANCE PLACED THE VDU ON MEL. THIS SDR WILL HAVE THE DEFECTIVE COMPONENT PART NUMBER AND SERIAL NUMBER UPDATED WHEN THAT INFORMATION IS AVAILABLE. 2L72 4F4 FRTA16WE E00055EN 20060705001142006070500114SW 2006 7 5 CA060202006 120060201G5320206031106079 ANGLE BELL 206 206B3 1181506SW FUSELAGE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 11601 ANGLE FROM VERTICAL TUNNEL TO BOX BEAM CRACKED. 1G71 3U H2SW 20060705001152006070500115NE 2006 7 5 CA060203001 220060201G73108280127119 FUEL LINE DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE LT ENGINE DAMAGED W K NONE K FLUID LOSS ININSP/MAINT 1 CA IT WAS DISCOVERED DURING OVERNIGHT ROUTINE MAINTENANCE THAT THE FUEL LINE IN THE LT ENGINE COMPARTMENT HAD BEEN IN CONTACT WITH A BRAIDED SHIELDED WIRE HARNESS CAUSING SEVERAL PIN HOLES WITHIN THE FUEL LINE CAUSING AN ATOMIZING EFFECT OF THE FUEL WITHIN THE ENGINE NACELLE. FUEL LINE WAS REPLACED AND WIRE HARNESS RESECURED TO ENSURE TO CONTACT WITH FUEL LINE. AIRCRAFT GROUND RUN AND RELEASED INTO SERVICE. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20060705000832006070500083SO 2006 7 5 CA060203003 120060129G3297 WIRE HARNESS PIPER 4550402 PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA HARTZLHCE3Y HCE3YR2A GL MLG BROKEN W O OTHER P NO WARNING INDICATION APAPPROACH 1 CA (CAN) WHEN LANDING GEAR WAS SELECTED ON APPROACH THE LT GEAR DOWN AND LOCKED LIGHT DID NOT COME ON. CREW CHECKED THE BULB AND NOTIFIED AIR RADIO OF THE SITUATION. A FLY PAST WAS CARRIED OUT AND THE GEAR WAS CONFIRMED TO BE DOWN AND LOCKED. THE AIRCRAFT LANDED AND THE GEAR WAS INSPECTED FOR THE PROBLEM, A BROKEN WIRE WAS IDENTIFIED AND REPAIRED. (TC NR 20060203003) 1L72 3O3 O A20SO E14EA 5 CP33EA 20060608003862006060800386EA 2006 6 8 CA060203004 220060130G8500 ENGINE PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA HARTZLHCE3Y HCE3YR2A GL RIGHT FAILED W A UNSCHED LANDING Y ENGINE STOPPAGE CRCRUISE 1 CA 2272 DURING CRUISE FLIGHT, THE CREW HAD A SUDDEN LOSS OF POWER ON THE RIGHT HAND ENGINE. THE ENGINE WAS FEATHERED AND THE AIRCRAFT WAS DIVERTED TO THE NEAREST AIRPORT. AFTER LANDING THE ENGINE WAS INSPECTED FOR ANY EXTERNAL DAMAGE OR OIL LEAKS NONE WERE FOUND. OIL FILTER WAS REMOVED, METAL WAS FOUND SO FLIGHT WAS TERMINATED AND ENGINE ORDERED. 1L72 3O3 O A20SO E14EA 5 CP33EA 20060608003872006060800387CE 2006 6 8 CA060203005 120060131G5544AD200020 STOP CESSNA150 150F 2071814CE CONT O200 O200A 17020SO MCAULY1A100 1A100MCM GL RUDDER FAILED W O OTHER O OTHER NRNOT REPORTED 1 CA NO JAMMING OR EVIDENCE OF SEE ON EITHER RUDDER STOPS. 1H71 3O3 O 3A19 E252 5 NP918 20060608003882006060800388NM 2006 6 8 CA060203006 120060129G276082740061020 CLUTCH BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA RT SPOILER UNKNOWN W O OTHER F FLT CONT AFFECTED TXTAXI/GRND HDL 1 CA 326 FLIGHT CREW FOUND THEY COULD NOT OPERATE THE CONTROL WHEEL CCW DIRECTION AFTER ENGINE STARTING. THE FLIGHT WAS CANCELLED. MAINTENANCE FOUND THE MICROSWITCH ON THE RT SPOILER CLUTCH ASSY CONTACTING WITH THE BRACKET-UPPER MOUNTING. THE CONTACT WAS CAUSED BY THE IMPROPER INSTALLATION OF THE MICROSWITCH SCREWS. BOMBARDIER AEROSPACE IS INVESTIGATING THIS EVENT. 2H72 4T4 TRTA13NM E00062EN 20060608003892006060800389CE 2006 6 8 CA060203007 120060202G2701126011131 GUARD CESSNA206 T206H 2073303CE AILERON CABLE LOOSE W O OTHER O OTHER NRNOT REPORTED 1 CA 14 WHILE INSTALLING ALTERNATOR/WIRING UPGRADE, IT WAS NOTICED THAT THE STRAP COVER WAS LOOSE ON THE CABLE GUARD ON THE LEFT SIDE AILERON CONTROL QUADRANT. SUBSEQUENT INSPECTION REVEALED THE RIGHT SIDE WAS ALSO LOOSE. TOP AND BOTTOM SCREWS ON THE LEFT AND RIGHT SIDE WERE TOO SHORT DUE TO A WASHER BEING PLACED IN BETWEEN THE STRAP COVER AND THE AILERON CABLE GUARD FROM THE FACTORY. INSUFFICIENT THREAD DEPTH INTO NUTPLATE, IE: 2 THREADS HOLDING ALL 4 FASTENERS = NOT IN SAFETY. A CONDITION REPORT WAS SENT TO THE CESSNA FIELD REP TO INVESTIGATE QUALITY CONTROL ISSUES IN REGARDS TO THE POSSIBILITY OTHER NEW A/C AFFECTED. 1H71 3O RTA4CE 20060608003902006060800390CE 2006 6 8 CA060205001 120060202G249710936102247 WIRE BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE HARTZLHCE4A HCE4A3I NE DC POWER BURNED W D RETURN TO BLOCK O OTHER TXTAXI/GRND HDL 1 CA ON START, THE CREW ATTEMPTED TO START THE RIGHT ENGINE. BUT NO LUCK STARTING THE ENGINE. AIRCRAFT BROUGHT TO HANGAR AND MAINTENANCE DISPATCHED. UPON ARRIVAL, MAINTENANCE ATTEMPTED TO START THIS ENGINE. NO JOY. THE STARTING ONLY HAD APPROX 300 HOURS REMAINING TIL OVERHAUL THEREFORE MAINTENANCE REPLACED THE STARTER THINKING THIS WOULD BE THE FAULT. THE STARTER GENERATOR WAS NOT THE FAULT. INSPECTION REVEALED THAT THE STARTER CABLE FEED THRU WAS BURNT UP ALONG WITH THE DC POWER PANEL. THE STARTER LUG. REPLACED THE FEED THRU CABLE AND THE POWER PANEL AND ENGINE START AND RUNS CARRIED OUT. NOW CHECKING SERVICEABLE. 2L72 4T4 TRTA24CE E26NE 5 CP10NE 20060608003912006060800391NM 2006 6 8 CA060206001 120060129G3297471509 WIRE HARNESS BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA NLG WOW UNKNOWN W A UNSCHED LANDING O OTHER CRCRUISE 1 CA AN AIRCRAFT EXPERIENCED INTERMITTENT WOW CAUTION LIGHT DURING FLIGHT. MAINTENANCE TELL US THAT THERE IS NO CURRENT FAULT TO BE FOUND IN THE PSEU NVM. HOWEVER, THE NLG WOW 1 SENSOR SHOWS A HISTORY OF FAULTS IN RIGGING HISTORY. WOW 1 SENSOR HARNESS IN NLG REPLACED. A/C RTS. 2H72 4T4 TRTA13NM E00062EN 20060608003922006060800392NM 2006 6 8 CA060206004 120060129G3297471515 WIRE HARNESS BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA NLG WOW UNKNOWN W A UNSCHED LANDING N FALSE WARNING CRCRUISE 1 CA AN AIRCRAFT EXPERIENCED AN INTERMITTENT WOW CAUTION LIGHT DURING FLIGHT. MAINTENACE PERSONNEL FOUND THAT THERE IS NO CURRENT FAULT TO BE FOUND IN THE PSEU NVM. HOWEVER, THE LT GEAR WOW 2 SENSOR SHOWS A HISTORY OF FAULTS IN FAULT HISTORY. WOW NR 2 HARNESS IN NLG REPLACED. A/C RTS. 2H72 4T4 TRTA13NM E00062EN 20060608003932006060800393NM 2006 6 8 CA060206007 120060129G3297471515 WIRE HARNESS BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA NLG CENTERING UNKNOWN W A UNSCHED LANDING O OTHER CLCLIMB 1 CA AN AIRCRAFT HAD TO RETURN TO FIELD BECAUSE OF FAILURE OF THE LANDING GEAR TO RETRACT. UPON INVESTIGATION AND INTERROGATION OF THE PSEU THE FAULT CODES WERE UNREASONABLE FAR -00. NLG WOW 2/CENTERING HARNESS REPLACED. A/C RTS. 2H72 4T4 TRTA13NM E00062EN 20060608003942006060800394NM 2006 6 8 CA060206008 120060201G3297471515 WIRE HARNESS BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA NLG UNKNOWN W A UNSCHED LANDING N FALSE WARNING CRCRUISE 1 CA AN AIRCRAFT EXPERIENCED A WOW CAUTION LIGHT DURING FLIGHT. MAINTENANCE FOUND PSEU INDICATED NR 2 WOW UNREASONABLE FAR, WITH TARGET PLACED IN FRONT OF SENSOR, THERE WAS NO CHANGE. THE TECHNICIANS CHANGED THE NLG NR 2 WOW HARNESS PER AMM 32-21-11-400-801, AND PSEU SHOWS NO FAULTS. A/C RTS. 2H72 4T4 TRTA13NM E00062EN 20060608003952006060800395NM 2006 6 8 CA060206009 120060203G3230483023 SEQUENCE VALVE BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA NLG DOOR MALFUNCTIONED W O OTHER O OTHER DEDESCENT 1 CA DURING DESCENT, THE NLG DID NOT EXTEND UNDER NORMAL EXTENSION, ALTERNATE RELEASE USED. MAINTENANCE REPLACED THE NLG DOOR SOLENOID SEQUENCE VALVE, CONDUCTED HYD BLEEDING AND GEAR SWINGS. A/C RTS. 2H72 4T4 TRTA13NM E00062EN 20060705001752006070500175NM 2006 7 5 CA060206010 120060203G3260471515 WIRE HARNESS BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17EU NLG FAILED W A UNSCHED LANDING N FALSE WARNING CLCLIMB 1 CA (CAN) AFTER TAKEOFF THE GEAR FAILED TO RETRACT UPON GEAR UP SELECTION. MAINTENACE FOUND NWCENT OPEN ON THE PSEU. NLG WOW 2/ CENTERING HARNESS REPLACED. A/C RTS. (TC NR 20060206010) 2H72 4T4 TRTA13NM E00062EN6 CP17BO 20060705001772006070500177NM 2006 7 5 CA060206012 120060128G2740106054554 BEARING RACE BOEING737 737275C NM PWA JT8 JT8D9A 52048NE ELEVATOR MAST WORN W A UNSCHED LANDING F FLT CONT AFFECTED CLCLIMB 1 CA (CAN) LOW FREQUENCY OSCILLATION FELT THROUGH AIRFRAME DURING CLIMB BETWEEN 240-270 KTS. NO CHANGE WITH AUTOPILOT ON OR OFF. ( NOTE: THIS WAS NOT VIBRATION ) HORIZ STAB PIVOT BEARINGS ON BOTH THE LT AND RT SIDE WERE REPLACED, BEARING HOUSING WAS REPLACED ON LT SIDE . ELEVATOR INPUT BEARINGS ON ELEVATOR MAST WERE REPLACED BOTH LT AND RT SIDE. FOLLOW UP ACTION THERE HAS BEEN A HARD FAILURE FOUND. COMPONENTS HAVE BEEN REPLACED. THERE IS NO FOLLOW UP REQUIRED. AC REMOVED FROM SERVICE FOR HORIZONTAL PIVOT BEARING REPLACEMENT. 2L72 4F4 F A16WE E2EA 20060705001792006070500179CE 2006 7 5 CA060207001 120060130G322257411501 AXLE CESSNA441 441 2076020CE GARRTTTPE331TPE33110 01514WP HARTZLHCB3T HCB3TN5 GL NLG CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 9824 (CAN) THE FORK, AXLE ASSY WAS SENT TO SHOP FOR BUSHING REPLACEMENT, INPECTION AND PAINTING. THEY FOUND THE AXLE BACK PLATE CRACKED. NEW AXLE FITTED. 1L72 3T4 TRTA28CE E4WE 6 CP15EA 20060705001802006070500180CE 2006 7 5 CA060207002 120060207G2720504200337 SUPPORT BEAM BEECH 100 A100 1152915CE PWA PT6 PT6A28 EA HARTZLHCB4T HCB4TN3 GL RUDDER QUAD CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 2646926469 (CAN) UNDER THE PILOTS FLOOR BOARDS AT FLIGHT STATION 107 THE PILOTS RUDDER QUADRANT SUPPORT BEAM WAS FOUND CRACKED. THESE CRACKS WERE FOUND AT THE TOP BEND RADIUS AND AT SOME HOLES FOR NUT PLATES. WE HAVE FOUND THESE SAME CRACKS ON 3 OTHER OF OUR AIRCRAFT AROUND THE SAME LOCATIONS. THE BEAM WAS REPLACED AND CHECKED SERVICABLE (TC NR 20060207002) 1L72 3T4 T A14CE E4EA 6 CP40EA 20060705001812006070500181NM 2006 7 5 CA060207003 120060207G323146503105 TARGET BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17EU MLG UPLOCK ASSY MISSING W A UNSCHED LANDING O OTHER CLCLIMB 1 CA 345 (CAN) AFTER THE LANDING GEAR SELECTED TO UP DURING CLIMB, THE LT DOOR AMBER INDICATION REMAINED ON AS WELL AS THE LT MLG RED INDICATOR REMAINED ON. CREW RETURNED TO BASE. MAINTENANCE FOUND: LT UP-LOCK SENSOR INDUCTANCE REPORTED TO BE OUT OF LIMITS. THE LOW INDUCTANCE FOR THE UP-LOCK SENSOR HAS BEEN TRACED TO A MISSING TARGET ON THE UP-LOCK. MLG UPLOCK ASSY TO BE REPLACED. (TCNR 20060207003) 2H72 4T4 TRTA13NM E00062EN6 CP17BO 20060705001822006070500182GL 2006 7 5 CA060207004 320060205G61124E256010 BOOT HARTZL CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE HARTZLHCB3T HCB3TN3 GL PROPELLER MISSING W A UNSCHED LANDING E VIBRATION/BUFFET CRCRUISE 1 CA 344 BUA27749 (CAN) WHILE ON A ROUTINE LOCAL TRAINING FLIGHT, THE PILOT EXPERIENCED SEVERE VIBRATION FROM THE ENGINE/PROPELLER. RETURNING TO THE AIRFIELD THE AIRCRAFT WAS LANDED SAFELY. INSPECTION REVEALED THAT ONE PROPELLER BLADE DE-ICER BOOT HAD DETACHED FROM THE BLADE AND WAS MISSING. THE MISSING BOOT HAD BEEN INSTALLED ON SEPT 9/2005 AND HAD ACCRUED 343.7 HRS TSN. (TC NR 20060207004) 1H71 3T3 T A37CE E4EA 6 CP15EA 20060705001832006070500183CE 2006 7 5 CA060207005 120060207G32220641124 AXLE CESSNA305 305A 2074002CE CONT O470 O47011 17026SO MCAULY1A200 1A200* GL MLG CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 4331 4331 (CAN) DURING A STRUCTURAL INSPECTION, A CRACK WAS FOUND IN RADIUS OF PART WHERE THE CYLINDER PORTION MEET THE BLOCK WHERE THE BOLTS ARE. BOTH AXLES (QTY 2) WERE CRACKED. ONE WAS VERY EASY TO SEE. THE OTHER APPEARED UNDER LIQUID PENETRANT. PARTS HAVE BEEN REPLACED BY NEW PARTS. DND HAVE A SPECIAL INSPECTION ON THAT PART FOR THE MFG OPERATED BY THE MILITARY. SOME WERE FOUND WITH CRACKED AXLES 3 YEARS AGO. (TC NR 20060207005) 1H71 3O3 O 5A5 E269 5 NP874 20060705001842006070500184EA 2006 7 5 CA060208001 120060130G76031603730007 THROTTLE CABLE CNDAIRCL600 CL6002B19 1900309EA COCKPIT BROKEN W EA ENGINE SHUTDOWN UNSCHED LANDING F FLT CONT AFFECTED CRCRUISE 1 CA 11003 (CAN) THE LT ENGINE WOULD NOT GO BELOW 82 PERCENT WHEN THE THROTTLE WAS RETARDED TOWARD IDLE. THE LT ENGINE WAS SHUT DOWN IAW QRH INSTRUCTION. TROUBLESHOOTING REVEALED THE CABLE ASSEMBLY FROM THE GEARBOX TO MFC BROKEN. CABLE WAS REPLACED IAW AMM. (TC NR 20060208001) 2L72 4F RTA21EA 20060705002142006070500214EA 2006 7 5 CA060208002 120060119G27306224404101 CONTROL CABLE CNDAIRCL600 CL6002C10 1390015EA ELEVATOR STUCK W O OTHER F FLT CONT AFFECTED APAPPROACH 1 CA 2991 (CAN) DURING APPROACH ELEVATOR CONTROL STUCK MOMENTARILY. APPROX 5 LB CONTROL FORCE BROKE ELEVATOR CONTROL FREE. ELEVATOR CONTROL OPERATED NORMALLY FOR APPROACH AND LANDING. AUTO PILOT PITCH SERVO CONDITION AND CABLE TENSION, PERFORMING A SLIP CLUTCH CHECK OF THE PITCH SERVO MOUNT, PERFORM OPERATIONAL CHECK OF THE AUTOPILOT SYSTEM. ALSO COMPLETED LUBRICATION OF THE ELEVATOR SERVO IAW REQUEST. ALL CHECKS WERE GOOD AND LUBRICATION COMPLETED (TC NR 20060208002) 2L72 4F RTA21EA 20060705002402006070500240SO 2006 7 5 CA060208003 120060207G322167054003 TRUNNION PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA HARTZLHCC2Y HCC2YR2 GL NLG CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 6857 (CAN) PART OF THE INSPECTION PROGRAM INCLUDES LANDING GEAR SERVICING. THE GEAR TRUNNIONS ARE FITTED WITH GREASE HOLES AND/OR FITTINGS TO ALLOW QUICK AND EASY SERVICING DURING SCHEDULED INSPECTIONS. WHILE CARRYING OUT THIS SERVICING ON THE NOSE GEAR TRUNNION GREASE WAS NOTED COMING OUT OF AN ODD LOCATION. PAINT WAS STRIPPED FROM THE LOWER KNUCKLE AND REVEALED CRACKS TOP AND BOTTOM. A SERVICEABLE INSPECTED UNIT WAS INSTALLED AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20060208003) 1L72 3O3 O A19S0 E286 5 CP920 20060705002412006070500241EU 2006 7 5 CA060208004 120060208G276070282721801 MODULE EMB ERJ190ERJ190100IGW3260408EU SPOILERS FAULTY W O OTHER J WARNING INDICATION CRCRUISE 1 CA (CAN) SPOILER FAULT CAUTION AT 33000. THE AIRCRAFT DID YAW AS A SPOILER PANEL EXTENDED AND RETRACTED. QRH PROCEDURES CARRIED OUT. SPOILERS CONFIRMED RETRACTED VISUALLY FROM CABIN. IB MULTIFUNCTION SPOILERS INDICATED A FAULT ON MFD FLIGHT CONTROL PAGE FLT CTRL NO DISPATCH AFTER LANDING. ACTION: FLIGHT CONTROL MODULE REPLACED IAW AMM 27-03-02 (TC NR 20060208004) 2L72 4F RTA57NM 20060705002422006070500242GL 2006 7 5 CA060208006 220060207G723023059598 SCROLL ALLSN HUGHES369 369D 4470706WP ALLSN 250C 250C20B 03013GL ANTI ICE BOSS CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 1480 CAC33937 (CAN) ON INSPECTION THE ENGINEER WAS TAKING APART THE ANTI-ICE BODY 6856984 FOR INSPECTION AND FOUND A CRACK AROUND THE BOSS. (TC NR 20060208006) 1G71 3U3 U H3WE E4CE 20060705002442006070500244WP 2006 7 5 CA060208007 120060207G6730D2121 SERVO ROBSINR44 R44 7640120WP LYC O540 O540F1B5 41532EA ROTOR LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA 455 (CAN) DURING AN INSPECTION HYDRAULIC LEAKS WAS FOUND AROUND THE FWD AND AFT SERVOS.THE RT FWD SERVO S/N 0251 AND THE AFT SERVO S/N 0667 WERE REMOVED AND NEWLY OVERHAULED ARE BEING INSTALLED. (TC NR 20060208007) 1G71 3O3 O H11NM E295 20060705002462006070500246NM 2006 7 5 CA060208009 120060207G2910NAS1611130 O-RING BOEING727 727247 138408FNM PWA JT8 JT8D15 52051NE HYD SYSTEM SWOLLEN W A UNSCHED LANDING K FLUID LOSS CLCLIMB 1 CA 7336 (CAN) SHORTLY AFTER TAKEOFF, CREW NOTICED SYS (A) HYDR INDICATED ZERO QTY. CREW DECLARED AN EMERGENCY, ASKED FOR A RETURN TO AIRPORT. CREW REQUESTED A FUEL DUMP, THIS WAS APPROVED BY ATC. AFTER FUEL DUMPING WAS COMPLETED AC RETURNED AIRPORT FOR ARRIVALS ILS 29. AC LANDED SAFELY AND WAS TOWED TO RAMP. INSP WAS ACCOMPLISHED. CAUSE OF HYDR FAILURE WAS FAILED O-RING EXTRUDING FROM IB FLAP PWR UNIT HYDR MOTOR. MOTOR ASSY AND O-RING REPLACED, (A) SYSTEM FILTERS REMOVED, INSPECTED FOR METAL. FILTERS FOUND CLEAN. OB MOTOR WAS REMOVED, INSPECTED, FOUND SERVICEABLE. IAW MM FILTERS TO BE REINSPECTED AFTER 200 HOURS. AC HYDR SYS SERVICED, AC WAS RETURNED TO SERVICE. (TC NR 20060208009) 2L73 4F4 F A3WE E2EA 20060705002852006070500285EA 2006 7 5 CA060208011 220060202G732125244392 FCU DHAV DHC6 DHC6200 2802620EA PWA PT6 PT6A20 52043EA HARTZLHCB3T HCB3TN3 GL ENGINE FLUCTUATES W A UNSCHED LANDING XMJENGINE FLAMEOUT OVER TEMP WARNING INDICATION DEDESCENT 1 CA 3479 (CAN) WHEN AC WAS ABOUT 10 MIN FROM LANDING, ON DESCENT, ENG POWER LEVERS WERE RETARDED FROM 38 LBS OF TORQUE. THE RT ENGINE TQ AND T5 STARTED FLUCTUATING. RT POWER LEVER WAS BROUGHT BACK FURTHER BUT TQ AND T5 CONTINUED TO RISE. RT POWER LEVER WAS PUT TO IDLE AND PROP LEVER TO FULL FINE IN AN ATTEMPT TO REDUCE TQ AND T5 HOWEVER BOTH PARAMETERS STILL INCREASED FURTHER TO 55 LBS OF TQ AND 900 DEGREES ON T5. ENG WAS SHUT DOWN AND THE AC LANDED WITHOUT INCIDENT. FCU WAS REPLACED, RIGGED AND ENGINE RUN-UPS COMPLETED. AC WAS FLOWN BACK TO BASE. RT POWER SECTION WAS REMOVED AND SENT FOR AN OVER TORQUE INSPECTION, AND THE FCU SENT FOR REPAIR. (TC NR 20060208011) 1H72 3T3 TRTA9EA E4EA 6 CP15EA 20060711001512006071100151EA 2006 7 11 CA060208015 120060130G712073512562 MOUNT DHAV DHC6 DHC6300 2802606EA ENGINE BROKEN W O OTHER F FLT CONT AFFECTED CRCRUISE 1 CA 631 (CAN) THE PILOT REPORTED AFTER LANDING THE LT ENGINE WAS BROKEN. THE MAINTENANCE CREW REPLACED THE BROKEN TOP LT ENGINE MOUNT ALONG WITH THE VIBRATION ISOLATOR AND NEW GASKETS AND ATTACHMENT BOLTS. (TC NR 20060208015) 1H72 3T RTA9EA 20060711001522006071100152CE 2006 7 11 CA060209001 120060131G2910CM3574D460B0 HOSE CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE HYD SYSTEM BURST W O OTHER KJ FLUID LOSS WARNING INDICATION LDLANDING 1 CA 6000 (CAN) LANDING THE CREW DEPLOYED THE THRUST REVERSERS AND GOT 6 LIGHTS FOLLOWED BY (HYD LOW LEVEL) AND (HYD LOW FLOW) LIGHTS. MAINTENANCE FOUND ONE LINE P/N CM3574D460B000S ON THE LT SIDE HAD BURST. REPLACED LINE WITH NEW. INSPECTED BOTH PRESSURE FILTERS AND NO METAL WAS FOUND. THE HYDRAULIC RESERVOIR WAS SERVICED AND THE THRUST REVERSER AND SPEED BRAKES WERE FUNCTION CHECKED. STARTED RT ENGINE TO PERFORM FUNCTION CHECKS. INSPECTED HYDRAULIC FILTERS FOR METAL, NONE FOUND. AIRCRAFT PLACED ON JACKS AND GEAR SWING COMPLETED. AIRCRAFT RETURNED TO SERVICE. (TC NR 20060209001) 1L72 4F4 F A22CE E1NE 20060711001532006071100153WP 2006 7 11 CA060209002 120060207G3222MS288891 PRESSURE VALVE NAMER B25 B25J 6400710WP WRIGHTR2600 R260035 67050EA HAMSTD23E 23E50 NE NLG INOPERATIVE W O OTHER J WARNING INDICATION CLCLIMB 1 CA 4534 (CAN) AC NOSE WHEEL STEERING INDICATOR SHOWED A NON-CENTRED CONDITION OF NOSE WHEEL IMMEDIATELY AFTER TAKE-OFF. AFTER SEVERAL LOW FLYOVERS TO VISUALLY CHECK CONDITION, EMERGENCY WAS DECLARED, AC WAS LANDED. POST LANDING, NOSE OLEO WAS DISCOVERED TO HAVE BECOME FULLY DEFLATED (ALTHOUGH THERE WAS NO OIL LEAKAGE), WHICH PREVENTED OLEO FROM FULLY EXTENDING, THUS NOT ALLOWING INTERNAL CENTERING DEVICE TO CENTER THE WHEEL. SOURCE OF LEAK WAS DETERMINED TO BE A LEAKING HIGH PRESSURE INFLATION VALVE (SCHRADER). WHILE VALVE IS CORRECT ONE, CALLED FOR IN PARTS MANUAL, STANDARD PRACTICE TO INSTALL MECHANICALLY CLOSED VALVES. THIS WAS DONE, OPERATION OF OLEO CENTRING DEVICE WAS CONFIRMED. (TC NR 20060209002) 2M72 4R4 R AL2 PAGE42 6 CP603 20060711001542006071100154 2006 7 11 CA060209003 420060202G6122 GOVERNOR CESSNA172 R172K 2072431CE CONT O360 IO360KB 17025SO MCAULY2A34C 2A34C203 GL PROPELLER DAMAGED W O OTHER E VIBRATION/BUFFET CLCLIMB 1 CA 2295 477 356706 (CAN) ENGINE OVERSPEED ON A TOUCH AND GO LANDING AT AIRPORT, ON TAKEOFF. ENGINE WAS REPORTED ROUGH ON THE RETURN FLIGHT. THE INSTRUCTOR AND THE OWNER ONBOARD DECIDED TO DECLARE AN EMERGENCY AND LAND BACK WHERE THE AIRCRAFT IS BASED AT THIS TIME. MAINTENANCE HAS DISCOVERED THAT THE SPARK PLUGS WHERE FOULED AND IN POOR SHAPE THE PROP GOVENOR WAS REMOVED FOUND BITS OF A RUBBER SEAL OR O-RING MATERIAL. GOVERNOR WAS SENT OUT FOR TESTING AND RECERTIFICATION. THIS WORK WAS ACCOMPLISHED ON FEB 8 2006. (TC NR 20060209003) 1H71 3O3 O 3A17 E1CE 5 CP3EA 20060711001552006071100155SW 2006 7 11 CA060209004 120060206G5524214001920101 HORN BELL 214 214B1 1182105SW LYC T55 T5508D 41555NE ELEVATOR CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 551 (CAN) AFTER LANDING AND SHUTDOWN, DURING REGULAR INSPECTION, A CRACK WAS FOUND IN THE ELEVATOR HORN ASSY. PART WAS REMOVED AND REPLACED BEFORE FURTHER FLIGHT. (UNDER CODES F1 WAS USED HOWEVER FLIGHT CONTROLS WERE NOT AFFECTED, AS PILOT DID NOT NOTICE ANY CHANGE IN FLIGHT CARACTERISTICS. THE ELEVATOR WAS STILL ABLE TO FUNCTION NORMALY WITH THE CRACK. (TC NR B20060209004) 2G71 4U4 U H6SW E4NE 20060711001562006071100156EU 2006 7 11 CA060209005 120060207G243523079009 STARTER GEN BAG JETSTMJETSTM3212 1500217EU GARRTTTPE331TPE33110UG 01514WP MCAULY4HFR344HFR34C652 NE RT FAILED W O OTHER J WARNING INDICATION APAPPROACH 1 CA 1132 (CAN) RT GENERATOR FAILER INDICATION ON APPROACH. CREW LANDED A/C WITH NO MORE PROBLEMS. STARTER/GENERATOR REPLACED. STARTER/GEN 67.9 HOURS REMAINING BEFORE OVERHAUL DUE. BRUSH INSPECTED TO BE 20 PERCENT REMAINING. (TC NR 20060209005) 2L72 4T4 TRTBA15CAA E4WE 6 C3PNE 20060711001572006071100157CE 2006 7 11 CA060209006 120060208G53120411951 BULKHEAD CESSNA150 150 2071802CE CONT O200 O200A 17020SO MCAULY1A100 1A100* GL MLG WW CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING AN ANNUAL INSPECTION, AM AME NOTICED THE MLG STRUT BULKHEAD UNDER THE CABIN FLOOR HAD SMALL CRACKS. UPON FURTHER INSPECTION WITH THE FLOORS REMOVED IT WAS FOUND THE ENTIRE MLG ATTACHMENT BULKHEAD/BOX STRUCTURE WAS NEAR FAILURE. MANY COMPONENTS MAKE UP THE ENTIRE BOX STRUCTURE AND MANY OF THEM WERE CRACKED OR FAILED. ALL THE DAMAGED AND CRACKED COMPONENTS WERE REPLACED WITH NEW PARTS AND REASSEMBLED. THE PN OF THE 2 BULKHEADS ARE 0411951-5 AND -6. (TC NR 20060209006) 1H71 3O3 ONT3A19 E252 5 NP918 20060711001582006071100158EA 2006 7 11 CA060210001 120060209G5740C6WM102727 FITTING DHAV DHC6 DHC6300 2802606EA PWA PT6 PT6A27 52043EA HARTZLHCB3T HCB3TN3 GL RT WING CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 32840 (CAN) UPON INSPECTION OF WING FRONT SPAR ADAPTER FITTINGS IAW REO 6-57-30-013, CRACKS WERE FOUND ON THE LT AND RT WING FRONT SPAR ADAPTER FITTINGS AS FOLLOWS; LT WING, BETWEEN WING STATION 35.15 AND 47.5, ONE CRACK BETWEEN 5TH AND 6TH RIVET. LT WING, BETWEEN WING STATION 47.5 AND 60.0, ONE CRACK BETWEEN THE 7TH AND 8TH RIVET. RT WING BETWEEN WING STATION 35.15 AND 47.5, ONE CRACK BETWEEN 4TH AND 5TH RIVET. AIRCRAFT ADVISED. (TC NR 20060210001) 1H72 3T4 TRTA9EA E4EA 6 CP15EA 20060710001032006071000103NM 2006 7 10 CA060210002 120060209G3297 GROUND WIRE BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA MLG SELECTOR LOOSE W O OTHER O OTHER APAPPROACH 1 CA PILOT REPORTED THAT THE LANDING GEAR DID NOT EXTEND ON SELECTION. AN ALTERNATE GEAR EXTENSION SELECTION WAS CARRIED OUT AND THE AIRCRAFT LANDED WITH OUT INCIDENT. THE PSEU HISTORY AND PRESENT FAULT WERE AS FOLLOWS: "DIN 01A FAULT"(DISCRETE INPUT EXTEND COMMAND) THE PROBLEM WAS TRACED TO A LOOSE GROUND "GS9" CONNECTED TO THE LANDING GEAR CONTROL AND INDICATION PANEL CONNECTOR P55 PIN "P". REF: WDM 32-61-00 SHT 7 OF 12 PAGE 1. 2H72 4T4 TRTA13NM E00062EN 20060711001642006071100164EU 2006 7 11 CA060210003 120060131G3010FAL1007 HOSE AMD FALC10FALCON10 2730101EU GARRTTTFE731TFE7312 01518WP RT SLAT COLLAPSED W O OTHER J WARNING INDICATION APAPPROACH 1 CA 111 111 (CAN) DURING APPROACH THE FLIGHT CREW NOTICED THAT THE RT OB SLAT WAS NOT SHEDDING ICE WITH THE WING ANTI-ICE ACTIVATED. UPON INSPECTION THE RT OB SLAT FLEX HOSE WAS FOUND TO BE SLIGHTLY COLAPSED INTERNALLY. ANTI-ICE SYSTEM WAS ACTIVATED 44 TIMES. (TC NR 20060210003) 2L72 4F4 F A33EU E6WE 20060711001932006071100193EU 2006 7 11 CA060210004 120060126G2822P94B12208 PUMP SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1D1 NE LT FUEL BOOST FAILED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) BOOST PUMP JUST STOPPED WORKING. REMOVED AND INSTALLED OVERHAUL PUMP SAME P/N AND ALL IS OK. (TC NR 20060210004) 1G71 3U3 U H9EU E19EU 20060711001942006071100194WP 2006 7 11 CA060210006 120060202G2822B8187B PUMP ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE FUEL SYS NOISY W K NONE O OTHER ININSP/MAINT 1 CA 882 (CAN) PILOT RECORDED A DEFECT THAT THE PUMP WAS MAKING A GRINDING NOISE. PUMP ASSEMBLY WAS REPLACED. NO FURTHER DEFECTS NOTED. (TC NR 20060210006) 1G71 3O3 O H11NM 1E4 20060808001012006080800101NE 2006 8 8 CA060210007 220060203G7200 ENGINE SKRSKYS92 S92A NE GE CT7TP CT79B 30030NE NR 2 MAKING METAL W O OTHER J WARNING INDICATION CRCRUISE 1 CA 42 (CAN) AFTER TAKE-OFF, ENGINE NR 2 CHIP LIGHT STARTED TO FLICKER. AC WAS TURNED AROUND TOWARDS PLACE OF DEPARTURE. EMERGENCY CHECKLIST WAS FOLLOWED, ENG NR 2 WAS BROUGHT BACK TO IDLE. DURING A LONG FINAL ON DESCENT, ENGINE WAS BROUGHT BACK ON LINE FOR LANDING. AC LANDED WITHOUT FURTHER INCIDENT, RETURNED TO HANGAR FOR INSP. AFTER INVESTIGATION, TECH REPS WERE CONTACTED, RECOMMENDED A GROUND RUN AS OUTLINED IN MM. THIS GROUND RUN WAS CARRIED OUT, THERE WAS NO CHIP LIGHT BUT UPON FURTHER INVESTIGATION SOME METAL CONTAMINATION WAS FOUND ON THE CHIP PLUG, IT WAS UPON THE ADVICE OF THE MANUFACTURER TO REPLACE THE ENGINE. THE ENGINE WAS REPLACED AND THE A/C WAS RETURNED TO SERVICE. 2G72 4U4 T R00024BOE8NE 20060711001952006071100195CE 2006 7 11 CA060210008 120060209G7110 LATCH BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA RT COWL LOOSE W A UNSCHED LANDING D INFLIGHT SEPARATION CRCRUISE 1 CA 9741 (CAN) RT ENGINE COWLING UNLATCHED IN FLIGHT (CALLED IN PRIORITY LANDING). RT ENGINE COWLING INSPECTED, FOUND FORWARD LATCH WAS LOOSE. RT ENGINE COWLING SECURED. RETRAINING CARRIED OUT WITH FLIGHT CREW AND TECHNICIANS ON PROPER COWLING LATCHING PROCEDURES. (TC NR 20060210008) 1L72 4T4 T A24CE E4EA 20060711001962006071100196NM 2006 7 11 CA060210009 120060210G531285310109 ANGLE DHAV DHC8 DHC8102 2809003NM BULKHEAD CORRODED W K NONE O OTHER ININSP/MAINT 1 CA 35538 (CAN) DURING A C-CHECK HEAVY CORROSION WAS FOUND ON THE FRONT PRESSURE BLK STA 120.0 ON THE LOWER AFT CAP ANGLE P/N 85310109 AND ON THE FORWARD CAP ANGLE P/N 85310108. THE DAMAGE WAS SUBMITTED TO MFG WHO ISSUE A SPECIFIC REPAIR TO BE CARRIED OUT. (TC NR 20060210009) 2H72 4T RTA13NM 20060711001972006071100197 2006 7 11 CA060211001 420060210G6113 PLATE DHAV DHC2 DHC2MKI 2801830GL PWA R985 R985AN14B 52008NE HARTZLHCB3R HCB3R304 GL PROPELLER DAMAGED W O OTHER W INADEQUATE Q C TXTAXI/GRND HDL 1 CA 89 (CAN) SHEARED RIVETS ON BACKPLATE FACE. (TC NR 20060211001) 1H71 3R3 RRCA806 5E1 5 CP28EA 20060711001982006071100198EA 2006 7 11 CA060211002 120060207G5610NP1393226 WINDOW CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE COCKPIT CRACKED W O OTHER O OTHER DEDESCENT 1 CA (CAN) THE COPILOT SIDEWINDOW CRACKED IN DESCENT. WINDOW REPLACED, AIRCRAFT RELEASED TO SERVICE. (TC NR 20060211002) 2L72 4F4 FRTA21EA E15NE 20060711002012006071100201NM 2006 7 11 CA060213001 120060212G7921800600M03005 ACTUATOR BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17EU NR 2 NACELLE OVERHEATED W A UNSCHED LANDING M OVER TEMP CRCRUISE 1 CA (CAN) ABOUT TEN MINUTES AFTER TAKEOFF NR 2 ENGINE OIL TEMPERATURE STARTED RISING, CREW WENT THROUGH CHECKLIST CLOSED BYPASS DOORS, TEMPERATURE WAS ABOVE 107 DEGREES FOR ABOUT 20 MINUTES AND ABOVE 115 DEGREES FOR ABOUT 10 MINUTES. TEMPERATURE PEAKED AT 122 DEGREES THEN IT STARTED COOLING AGAIN ON OUR DESCENT BACK TO BASE. BY THE TIME THE CREW LANDED, THE TEMPERATURE WAS NORMAL AT 94 DEGREES. OIL COOLER DOOR ACTUATOR WAS DETERMINED TO BE THE CAUSE. THE OIL COOLER DOOR ACTUATOR REPLACED. (TC NR 20060213001) 2H72 4T4 TRTA13NM E00062EN6 CP17BO 20060719000322006071900032SW 2006 7 19 CA060213002 120060212G2140ES721822 AIR DUCT AIRCOM BELL 206 206B 1181511SW ALLSN 250C 250C20 03013GL CABIN HEATER MELTED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING MAINTENANCE, AN AME NOTICED THAT HE COULD NOT MOVE THE HEATER AIR OUTLET. ON CLOSER INVESTIGATION, HE FOUND THE OUTLET MELTED. NO OTHER DAMAGE WAS NOTED. (TC NR 20060213002) 1G71 3U3 U H2SW E4CE 20060719000332006071900033NM 2006 7 19 CA060213003 120060210G275118157014 TRANSMITTER BOEING727 727247 138408FNM PWA JT8 JT8D15 52051NE IB TE FLAP FAILED W L ABORTED APPROACH FJ FLT CONT AFFECTED WARNING INDICATION APAPPROACH 1 CA 7591 (CAN) AIRCRAFT EXPERIENCED A FLAP ASYMMETRY ON APPROACH. CREW DECLARED AN EMERGENCY AND ELECTRICLY DROVE THRU FLAPS TO LANDING CONFIGURATION. AIRCRAFT LANDED SAFELY AND WAS TAXIED TO THE HANGER. HANGER MAINTENANCE CONFIRMED THE LT IB FLAP TRANSMITTER AS THE CAUSE. LT IB FLAP TRANSMITER REPLACED AND ENTIRE FLAP SYSTEM CHECKED FOR RIGGING IAW THE MM. NO FURTHER FAULTS FOUND. SUBMITTER WILL UP-DATE THIS SDR AS MORE INFORMATION COMES IN FROM FLIGHT CREW. (TC NR 20060213003) 2L73 4F4 F A3WE E2EA 20060719000342006071900034EA 2006 7 19 CA060213004 120060210G2910MM67075294009 LINE CNDAIRCL215 CL2151A10 1900320EA GE CF34 CF348C1 NE NR 2 HYD SYS CRACKED W O OTHER KJ FLUID LOSS WARNING INDICATION CRCRUISE 1 CA (CAN) TOTAL LOSS OF NR 2 HYDRAULIC FLUID, FROM A RUPTURE ON THE PRESSURE MANIFOLD LINE P/N MM670-75294-009. NR 2 HYDRAULIC LINES P/N MM670-75294-009, MM670-75294-005 AND SUPPORT CLAMPS P/N MM670-75800-041, MM670-75800-029 ALL REPLACED. ENGINE DRIVEN PUMP FAILED AND REPLACED. IT IS SUSPECTED THE CAVITATIONS CAUSED BY THE FAILURE OF THE ENGINE DRIVEN PUMP CAUSED EXCESSIVE BUFFETING IN THE HYDRAULIC LINES. THE BUFFETING OF THESE LINES CAUSED DAMAGE TO THE CLAMPS AND RESULTED IN THE HYDRAULIC LINE CHAFING THROUGH UNTIL TOTAL LOSS OF HYDRAULIC FLUID OCCURED. (TC NR 20060213004) 2H72 4R4 FRTA14EA EOOO63EN 20060719000362006071900036NE 2006 7 19 CA060213006 220060209G7510577957 MANIFOLD BOEING727 727227 1384078NM PWA JT8 JT8D9A 52048NE ENGINE CRACKED W EA ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA (CAN) AFTER DEPARTURE, THE NR 2 FIRE WARNING CAME ON THROUGH CLIMB, POWER LEVER REDUCED WITH SUBSEQUENT WARNING EXTINGUISHING AND AIRCRAFT RETURNED. INSPECTION CARRIED OUT AND FOUND THE NR 2, 13TH STAGE FUEL HEAT DUCT RUPTURED AT BOTH ENDS. THE DUCT WAS THEN REPLACED. (TC NR 20060213006) 2L73 4F4 F A3WE E2EA 20060719000372006071900037SW 2006 7 19 CA060213008 120060210G5302206033004051 SKIN BELL BELL 206 206L 1181522SW TAILBOOM CRACKED W K NONE O OTHER ININSP/MAINT 1 CA AORP00728 (CAN) DURING A 100 HOUR INSPECTION THE ENGINEER DISCOVERED 2 CRACKS EMINATING FROM 2 RIVETS ON THE THE TAIL ROTOR GEARBOX ATTACH SUPPORT. THE CRACKS GO OUT TO THE EDGE OF THE SKIN. THE RIVETS WERE ALSO FOUND TO BE SMOKING OR LOOSE. (TC NR 20060213008) 1G71 3U H2SW 20060719000382006071900038CE 2006 7 19 CA060214001 120060213G2133NN5040 TUBE 10357626 CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE OUTFLOW VALVE MELTED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING UNSCHEDULED MAINT FOR AN UNRELATED MAINTENANCE ISSUE, THE POLYFLOW LINE PROVIDING ATMOSPHERIC REFERENCE PRESSURE TO THE RT OUTFLOW VALVE WAS FOUND MELTED AND OPEN TO CABIN PRESSURE. THE POLYFLOW LINE WAS TOO LONG AND WAS POSITIONED IN SUCH A WAY AS TO REST AGAINST THE EMERGENCY PRESSURIZATION LINE P/N: 6515201-3. THE HEAT FROM THE EMERGENCY PRESSURIZATION LINE CAUSED NYLON TUBING TO MELT. NEW TUBING OF THE CORRECT LENGTH WAS INSTALLED AND ROUTED CLEAR OF THE EMERGENCY PRESSURIZATION LINE. AIRCRAFT WAS RETURNED TO SERVICE. AC SERVICES HAS INITIATED CAMPAIGN 851-21-30-031TO INSPECT THE REST OF OUR FLEET FOR CORRECT INSTALLLATION OF THE POLYFLOW LINE. (TC NR 20060214001) 1L72 4F4 F A22CE E1NE 20060719000392006071900039EU 2006 7 19 CA060214002 120060214G783028850009 LOCK AIRBUSA340 A340313 EU CFMINTCFM56 CFM565C4 13802NE THRUST REVERSER MALFUNCTIONED W E ENGINE SHUTDOWN J WARNING INDICATION CLCLIMB 1 CA (CAN) THRUST REVERSER NR 4 UNLOCKED. SHUTDOWN NR4 V/S ON OVERWEIGHT LANDING 500FT/MIN LANDING WT 233000 KG. SEE FMR M1243972. ACTION:411T/S 78-31-00-810-970 CARRIED OUT NO FAULT FOUND. SUSPECT PRIMARY LOCK P/N 2885000-9 LOCATED AT IB UPPER SIDE. 4 LOCK PLUGS ARE LOCATED IN THE OB PARTS BOX. (TC NR 20060214002) 2L74 4F4 FRTA197 E37NE 20060719000402006071900040EU 2006 7 19 CA060214003 120060207G2710LN93614C46R210 CONTROL CABLE CASA C212 C212CC 2410204EU GARRTTTPE331TPE33110R 0517 WP HARTZLHCB4M HCB4M GL AILERONS BROKEN W K NONE O OTHER ININSP/MAINT 1 CA 18632 (CAN) DURING ROUTINE MAINTAENANCE INSPECTION, SEVERAL WIRES FOUND BROKEN ON RT AILERON CONTROL CABLE AS IT PASSES AROUND CABLE PULLEY AT FRAME 4. PULLEY FOUND SEIZED TO BOLT. CABLE, PULLEY AND BOLTS REPLACED. (TC NR 20060214003) 2H72 4T4 T A43EU E4WE 6 CP56GL 20060719000652006071900065NM 2006 7 19 CA060214004 120060214G3244314381 TIRE BOEING737 737522 138449FNM CFMINTCFM56 CFM563C1 13802EU NOSE GEAR ASSY DEFLATED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) WHEN MAINTENANCE ARRIVED AT THE GATE FOR THE DAY'S FIRST DEPARTURE, IT WAS NOTICED THAT THE LT NOSE TIRE WAS FLAT. UPON FURTHER INVESTIGATION IT WAS DISCOVERED THAT THE RT NOSE TIRE WAS ALSO FLAT. BOTH NOSE ASSEMBLIES REPLACED AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20060214004) 2L72 4F4 FRTA16WE E21EU 20060719000662006071900066SO 2006 7 19 CA060214005 120060213G2121C180559A1 BLOWER EMB 110 EMB110P1 3260122SO PWA PT6 PT6A34 52043EA HARTZLHCB3T HCB3TN3 GL CABIN AIR BURNED W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 1 CA 1598 447 (CAN) DURING CRUISE FLIGHT, WITH NO PASSENGERS ON BOARD, THE CREW NOTICED AN ELECTRICAL BURNING SMELL IN THE AIRCRAFT AND SMOKE IN THE CABIN. THE AIRCRAFT WAS DIVERTED TO THE NEAREST SUITABLE AIRPORT AND LANDED. UPON INVESTIGATION MAINTENANCE PERSONNEL DISCOVERED THAT THE SMELL AND SMOKE WAS COMING FROM THE CABIN BLOWER. THE CABIN BLOWER WAS DISABLED AND DEFERRED AND A GROUND RUN WAS COMPLETED WITH NO FURTHER SMOKE OR BURNING SMELL NOTED. THE AIRCRAFT WAS THEN RETURNED TO SERVICE. ONCE THE AIRCRAFT RETURNED TO A MAINTENANCE BASE THE BLOWER WAS REMOVED AND SENT OUT FOR REPAIR AND A COMPONENT STRIP REPORT. (TC NR 20060214005) 1L72 4T4 T A21SO E4EA 6 CP15EA 20060719000672006071900067GL 2006 7 19 CA060214006 220060210G72606820588 WASHER ALLSN AEROSPAS355 AS355* EU ALLSN 250C 250C20R1 03013GL GEARBOX MISSING W O OTHER O OTHER NRNOT REPORTED 1 CA CAG40968 (CAN) AS ENG NR 2 WAS INCREASED, EXCEEDANCE ON INSTR PANEL, M/R READING HIGH ON TRIPLE TACH, NO INDICATION OF N2 SPEED ON TACH INDICATOR. FOUND N2 GOV GEAR FREEWHEELING, DISENGAGED FROM INTERNAL GB N2 DRV SYS. TEARDOWN OF GB REVEALED BRG RETAINING WASHER WAS MISSING, N2 PWR TRAIN IDLER GEAR ASSY. WASHER RETAINS BRG ON IDLER GEAR SUPT SHAFT. KEY WASHER RETAINED BRG ON IDLER SUPT SHAFT, UNTIL BRG INNER RACE WORE EDGE OF KEY WASHER ALLOWING BRG TO SLIDE AXIALLY, DISENGAGE N2 TACH DRV GEARTRAIN. WITH N2 TACH DRV GEARTRAIN DISENGAGED FROM N2 DRV, ENG COULD OVERSPEED. WEAR ON ID OF N2 PWR TRAIN IDLER BRG, PORTION OF KEY WASHER, IDLER GEAR. PREVIOUS CHIP LIGHTS REPORTED ARE RESULT OF WEAR. (TC NR 20060214006) 1G72 3U3 U H11EU E4CE 20060719000682006071900068NM 2006 7 19 CA060214007 120060210G2730BACB10ET06 BEARING BOEING757 757* NM RROYCERB211 RB211535E43754555NE ELEVATOR SEIZED W O OTHER F FLT CONT AFFECTED CLCLIMB 1 CA 52087 (CAN) REPORTED THAT ELEVATOR FELT HEAVY FOR BOTH CAPT AND F/O. AILERON NORMAL. TROUBLESHOOTING SHOWED THAT THE ROLLER BEARING THAT RIDES IN THE ELEVATOR INPUT CAM WAS SEIZED, CAUSING HIGHER THAN NORMAL FORCE REQUIED TO MOVE FLIGHT CONTROL OUT OF (DETENT). BEARING REPLACED AND SYSTEM CHECKED IAW AMM 27-31-17 P216, OPS FOUND NORMAL. AFTER BEARING REPLACEMENT, NO FURTHER DEFECTS NOTED. (TC NR 20060214007) 2L72 4F4 FRTA2NM E12EU 20060719000692006071900069CE 2006 7 19 CA060215001 120060213G3411AERROQUIP206 HOSE LEAR 35 35LEAR 5170600CE GARRTTTFE731TFE73122B 01518WP PITOT SYS CRACKED W K NONE L NO TEST ININSP/MAINT 1 CA 1873 (CAN) DURING A SCHEDULED PITOT/STATIC CHECK, THE AVIONICS TECHNICIAN DISCOVERED A LEAK ON THE LT PITOT CIRCUIT. AFTER FURTHER TROUBLESHOOTING, THE TECHNICIAN DISCOVERED A HOSE THAT WAS CRACKED (MIL-H-5593-4). THE HOSE WAS REPLACED AND THE SYSTEM WAS SERVICEABLE. (TC NR 20060215001) 2L72 4F4 F A10CE E6WE 20060719000702006071900070GL 2006 7 19 CA060215002 220060213G72616870032N FILTER ALLSN 250C 250C20 03013GL OIL SYSTEM DAMAGED W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA (CAN) ENGINE OIL FILTER, VENDOR NR IS 05228-759280-101. THERE WAS A PROBLEM WITH ONE OF THE SEAMS IN ONE OF THE ELEMENTS NOT BEING SEALED. ALL OF THE PTI FILTERS IN STOCK WERE INSPECTED AND FOUND THE SAME DEFECT IN EACH FILTER. THE FILTERS WERE PURCHASED AND THE VENDOR HAS BEEN NOTIFIED OF THIS DEFECT AND ALL THE FILTERS HAVE BEEN PLACED IN QUARANTINE STORES PENDING RETURN TO THE VENDOR. (TC NR 20060215002) 3 U E4CE 20060719000712006071900071EA 2006 7 19 CA060215003 220060210G72603027977 CARRIER ASSY PWA PT6 PT6A6 52043EA RGB DISPLACED W K NONE O OTHER ININSP/MAINT 1 CA 2998 16 (CAN) OPERATOR COMPLAINED OF NOISE FROM THE REDUCTION GEARBOX, EXCESSIVE PROPELLER LOOSENESS AND METAL ON THE RGB CHIP DETECTOR. UPON GEARBOX DISMANTLE AND EXAMINATION OF THE 2ND STAGE CARRIER (PN 3027977), THE SLEEVE USED TO REPAIR THE NR 5 BEARING JOURNAL WAS FOUND TO HAVE SHIFTED OFF OF THE JOURNAL (REFER TO FIGURES 1 AND 2). NO SECONDARY DAMAGE TO THE REDUCTION GEARBOX ASSEMBLY WAS NOTED. THE SLEEVE REPAIR IS PERMITTED ON 2ND STAGE CARRIER PN 3027977 FOR OTHER ENGINE MODELS, AND THIS PART NR IS ELIGIBLE FOR USE ON THE ENGINE, HOWEVER SLEEVE REPAIR IS PROHIBITED IAW MM 3034543 FOR THE ENGINE APPLICATION. (TC NR 20060215003) 3 T E4EA 20060719000722006071900072EA 2006 7 19 CA060216001 120060215G243503600923 BEARING BFGOODRICH DHAV DHC8 DHC8311 1386006EA PWA PW120 PW123 NE HAMSTD14SF 14SF15 NE STARTER GEN FAILED W K NONE O OTHER ININSP/MAINT 1 CA 189971231 Y20071R (CAN) ORIG SNAG (STARTER SWITCH DOES NOT AUTO DELATCH) DRIVE END BEARING FAILURE (03-6009-23) STARTER GENERATOR HAS BEEN MODIFIED TO -008 (S/B -8-24-81) (TC NR 20060216001) 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20060719000732006071900073EU 2006 7 19 CA060216002 120060124G6321AHA1121 CALIPER BOLKMS105 BO105C 5626005EU ALLSN 250C 250C20B 03013GL MAIN ROTOR BRAKEBINDING W K NONE O OTHER ININSP/MAINT 1 CA (CAN) PISTON DOES NOT RETRACT INTO CALIPER HOUSING AFTER BRAKING CAUSING ROTOR BRAKE PAD TO REMAIN IN CONTACT WITH BRAKE DISC. (TC NR 20060216002) 1G72 3U3 U H3EU E4CE 20060616001282006061600128CE 2006 6 16 CA060216003 120060215G5711 FRAME BEECH 90 C90 1152913CE PWA PT6 PT6A28 EA HARTZLHCB3T HCB3TN3 GL WING CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 16976 UPON BEGINNING A PHASE 3 INSPECTION, A TECHNICIAN DISCOVERED A SMALL CRACK ON THE RIGHT FORWARD LOWER SPAR HINGE CAP. THE CRACK WAS OUT FROM THE FOURTH FASTENER FORWARD TOWARD THE HINGE EDGE. A SMALL AREA OF PAINT HAD BEEN FLAKED AWAY IN THIS AREA. MORE PAINT WAS REMOVED IN THIS AREA IN AID TO FURTHER INVESTIGATE THE DISCREPANCY. IT WAS CLEARLY VISIBLE TO SEE WITHOUT ANY NDT INSPECTION METHODS REQUIRED. THE AIRCRAFT WAS REMOVED FROM SERVICE. IT WAS NOTED THE PREVIOUS EDDY CURRENT INSPECTION (AS REQUIRED IAW THE RAYTHEON SIRM) WAS CONDUCTED IN THIS AREA IN JANUARY 2005, 754.8 HOURS AGO. 1L72 3T4 T 3A20 E4EA 6 CP15EA 20060606002252006060600225NM 2006 6 6 CA060216004 120060216G2140RBGB161 BLOCK BOEING737 7378Q8 13844BXNM TERMINAL BLOCK OVERHEATED W H DEACTIVATE SYST/CIRCUITS O OTHER ININSP/MAINT 1 CA 1844518445 REPLACING AFT WATER DRAIN MAST DUE TO INOPERATIVE HEATER. GROUND TERMINAL BLOCK GD11996 WAS FOUND DAMAGED WITH SIGNS OF OVERHEATING. WIRES DISCONNECTED AND CAPPED, AND EFFECTED CIRCUIT BREAKERS PULLED TO ISOLATE TERMINAL BLOCK UNTIL REPLACEMENT PART AVAILABLE. 2L72 4F RTA16WE 20060619001752006061900175NE 2006 6 19 CA060216005 220060215G74219550175400 IGNITER SNIAS 350 AS350BA 8680817EU TMECA ARRIELARRIEL1B 6OO30NE ENGINE BROKEN W K NONE O OTHER ININSP/MAINT 1 CA 547 4374 (CAN) DURING A 100 HR INSPECTION THE IGNITORS WERE REMOVED AND IT WAS FOUND THAT THE CERAMIC SURROUNDING CENTER ELECTRODE WAS LOOSE. BOTH IGNITORS WERE CHAMPIONS. ENGINE VIB CHECK WAS CARRIED OUT AND FOUND WITHIN LIMITS. LT IGNITOR S/N 04020731 AND RT S/N 03124329. (TC NR 20060216005) 1G71 3U3 UNCH9EU E19EU 20060607002482006060700248NM 2006 6 7 CA060216006 120060216G28223823002 PUMP BOEING727 727247 138408FNM PWA JT8 JT8D15 52051NE NR 2 FUEL TANK UNKNOWN W A UNSCHED LANDING GJ MULTIPLE FAILURE WARNING INDICATION CLCLIMB 1 CA ON CLIMB, NR 2 RT AFT FUEL BOOST PUMP CB RELEASED FOLLOWED BY NR 2 LT AFT CB RELEASING APPROX 3 MIN LATER, NR 2 RT FWD CB RELEASED AND NR 2 LT FWD BOOST PUMP LOW PRESS LIGHT ILLUMINATED INTERMITTENTLY. A/C RETURNED TO DEPARTURE. MX INSPECTED ALL EFFECTED PUMPS, CONNECTORS, BREAKERS AND SWITCHES, NO FAULTS FOUND. BREAKERS WERE RESET, PUMPS WERE RUN FOR AN HOUR. DURING THIS TIME PUMPS WERE SELECTED OFF AND ON NUMEROUS TIMES. A/C RETURNED TO SERV & OPERATED WITH NO INCIDENT. MX REINSPECTED ALL OF ABOVE ALONG WITH CHECKING NR 2 TANK FOR FUEL CONTAMINATION. NOTHING FOUND. DUE TO UNUSUAL CIRCUMSTANCES MAINT HAS DECIDED TO REPLACE THREE EFFECTED BOOST PUMPS, BREAKERS AND SWITCHES. 2L73 4F4 F A3WE E2EA 20060608001972006060800197CE 2006 6 8 CA060217001 120060214G315070H10A DIODE BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA COCKPIT FAILED W O OTHER GJ MULTIPLE FAILURE WARNING INDICATION TXTAXI/GRND HDL 1 CA BB24 CREW REPORTS THAT MULTIPLE SYSTEMS AND ANNUNCIATORS UNSERVICEABLE. MAINTENANCE PERSONAL DISPATCHED AND FOUND THAT NR 1 DUAL FED ELECTRICAL BUS HAD FAILED BOTH MAIN FEED DIODES (P/N 70H10A). DIODES REPLACED AND FUNCTION CHECKED SERVICEABLE. COMPANY HAS NOW IMPLEMENTED A MONTHLY REPETITIVE CHECK OF THE BUS SYSTEM DUE TO THE DORMANT FAILURE RISK OF THESE DIODES. 1L72 4T4 T A24CE E4EA 20060608003972006060800397CE 2006 6 8 CA060217002 120060207G323379990022A ACTUATOR BEECH 100 A100 1152915CE PWA PT6 PT6A28 EA NLG DAMAGED W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA NOSE LANDING GEAR WOULD NOT RETRACT AFTER TAKEOFF. MAINTEANCE DID MULTIPLE GEAR SWINGS BUT COULD NOT DUPLICATE THE PROBLEM. THE ACTUATOR WAS REMOVED AND PUT IN A TEST STAND WHERE IT FINALLY FAILED STAYING IN THE LOCKED POSITION. A OVERHAULED ACTUATOR WAS INSTALLED AND THERE HAS BEEN NO MORE PROBLEMS REPORTED. 1L72 3T4 T A14CE E4EA 20060607002512006060700251 2006 6 7 CA060217003 420060213G2562PS400010 ELT ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540* 41532EA CABIN ACTIVATED W K NONE N FALSE WARNING CRCRUISE 1 CA 194 ELT ACTIVATED IN FLIGHT. ELT REPLACED WITH SERVICEABLE UNIT. 1G71 3O3 O H11NM 1E4 20060608001992006060800199CE 2006 6 8 CA060218001 120060214G3230571302 MOTOR BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE HARTZLHCE4A HCE4A3I NE MLG BURNED W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA AFTER TAKEOFF, AIRCRAFTS LANDING GEAR WOULD NOT RETRACT. CREW CONTACTED MX AND CREW AND MX DECIDED TO LEAVE THE LANDING GEAR DOWN AND CONTINUE THE 30 MINUTE FLIGHT TO THE MAIN BASE. ALL INDICATIONS SHOWED THAT THE LANDING GEAR WAS DOWN AND LOCKED. THE AIRCRAFT LANDED AND DEPLANED THE PASSENGERS AND RETURNED TO THE HANGAR. WHEN MAINTENANCE TROUBLESHOT THE LANDING GEAR SYSTEM THE FAULT WAS FOUND WITH THE MOTOR. MOTOR WAS REPLACED AND GEAR SWINGS CARRIED OUT SATISFACTORY. THE PCB WAS ALSO REPLACED DUE TO THE TIME DELAY BUT THIS HAD NOTHING TO DO WITH THIS FAULT. AIRCRAFT THEN RETURNED TO SERVICE. 2L72 4T4 TRTA24CE E26NE 5 CP10NE 20060608002012006060800201CE 2006 6 8 CA060219001 120060117G55201158100714 SEAL BEECH 100 100BEECH 1152916CE PWA PT6 PT6A28 EA TORQUE SHAFT CUT W O OTHER J WARNING INDICATION NRNOT REPORTED 1 CA RUBBER SEAL DETERIORATED ALLOWING METAL SPRING TO CUT A LARGE GROOVE IN THE TORQUE SHAFT. 1L72 3T4 T A14CE E4EA 20060608002832006060800283EU 2006 6 8 CA060220001 120060214G3897E0266QF20EO261 WIRE HARNESS AIRBUS310 A310 EU GE CF6 CF680C2* GL TOILET BURNED W K NONE S AFFECT SYSTEMS ININSP/MAINT 1 CA AIRCRAFT ARRIVED AT STATION WITH A DEFECT LOG REPORT OF THE FORWARD LAVATORY NOT FLUSHING. TROUBLESHOOTING FOUND THAT 4 WIRES BETWEEN THE FLUSH MOTOR AND THE TIMER UNIT WERE BROKEN. IT WAS NOTED THAT MINOR ARCH/BURNING OF THE WIRES HAD OCCURRED. ALL 4 WIRES AND PINS WERE REPLACED AND SYSTEM WAS TESTED SERVICEABLE. 2L72 4F4 FRTA35EU E23EA 20060612003542006061200354NM 2006 6 12 CA060220002 120060216G5330737200C SKIN BOEING737 737242C 1384478NM PWA JT8 JT8D9A 52048NE FUSELAGE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 71011 DURING THE PREFLIGHT INSPECTION 2 CRACKS WERE OBSERVED IN THE FUSELAGE SKIN. BOTH DEFECTS WERE APPROXIMATELY 2 INCHES IN LENGTH. THE LOCATION IS ESTIMATED TO BE BS 750 STR 19/20. THE AIRCRAFT IS CURRENTLY OUT OF SERVICE FOR REPAIR. 2L72 4F4 F A16WE E2EA 20060613000042006061300004 2006 6 13 CA060220003 120060216G4900MDL15R2001 SCREEN BOMBDR APU INLET DAMAGED W O OTHER C F.O.D. NRNOT REPORTED 1 CA A COMPRESSOR INLET SCREEN MODIFICATION, AWI RECEIVED INFORMATION FROM STANDARD AERO LATE ON FEB 16,2006 THAT THREE OR FOUR OF THE SCREENS HAD RUPTURED IN SERVICE AND THERE WAS A POSSIBILITY THAT FOD TO THE ENGINE HAD OCCURRED. THE PARTS WERE SHIPPED TO AWI AND RECEIVED FEB. 17, 2006, THERE ARE SOME SCREENS THAT HAVE BEEN PERFORATED. BUT, THE INLET SCREENS DO NOT APPEAR TO HAVE BEEN IN SERVICE. THE RUBBER AROUND THE INLET SCREENS IS NOT BURNED FROM ENGINE HEAT AND THE SCREENS ARE NOT BLACKENED. AEROSPACE WELDING TAKES THIS MATTER VERY SERIOUSLY AND A MATERIAL REVIEW BOARD MEETING HAS BEEN CALLED FOR MONDAY AFTERNOON FEB 20,2006 TO REVIEW AND RESOLVE THIS MATTER AS SOON AS POSSIBLE. 20060613000052006061300005GL 2006 6 13 CA060220004 120060208G2730C2TP199 HINGE PIN DHAV DHC2 DHC2MKI 2801830GL PWA R985 R985AN14B 52008NE STABILIZER WRONG PART W K NONE O OTHER ININSP/MAINT 1 CA 19966 DURING A ROUTINE 100 HOUR INSPECTION, ALL FOUR ELEVATOR HINGE PINS WERE FOUND TO BE HOMEMADE. AIRCRAFT WAS RECENTLY IMPORTED FROM VENEZULA. 1H71 3R3 RRCA806 5E1 20060619001912006061900191WP 2006 6 19 CA060220005 120060215G6220369H120351G LINK 369D21200503HUGHES369 369D 4470706WP M/R HUB CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 2156 022222520 (CAN) DURING A 100 HOUR INSPECTION THE ENGINEER NOTICED A CRACK ON ONE OF THE EARS OF THE LEAD LAG LINK OF THE MAIN ROTOR HUB ASSEMBLY. CRACK PROPAGATED FROM THE BUSHING OUTWARD. (TC NR 20060220005) 1G71 3U H3WE 20060613000062006061300006GL 2006 6 13 CA060221001 120060208G5711C2W927A SPAR DHAV DHC2L20 DHAV DHC2 DHC2MKI 2801830GL PWA R985 R985AN14B 52008NE LT WING CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 21602 579 DURING MAINTENANCE (WING REMOVAL) FRONT SPAR WEB FOUND CRACKED AT ROOT FITTING. ONCE DOUBLER WAS REMOVED, THE CRACK WAS FOUND TO HAVE BEEN STOP DRILLED. 1H71 3R3 RRCA806 5E1 20060613000082006061300008GL 2006 6 13 CA060221002 120060208G5720C2FS537A CHANNEL DHAV DHC2 DHC2MKI 2801830GL PWA R985 R985AN14B 52008NE WRONG PART W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA 19966 FOUND CHANNEL ASSEMBLY WAS MADE FROM APPROXIMATELY .125 STEEL. CHECKED WITH VIKING AND WAS INFORMED THAT CHANNEL IS .080 ALUMINUM. AIRCRAFT WAS RECENTLY IMPORTED FROM VENEZULA. 1H71 3R3 RRCA806 5E1 20060613000102006061300010NE 2006 6 13 CA060221003 220060220G73208061532 HMU AIRBUSA321 A321211 3930370EU GE CFM56 CFM56* 13802NE NR 2 ENGINE MALFUNCTIONED W A UNSCHED LANDING F FLT CONT AFFECTED CLCLIMB 1 CA AFTER T/O YOW EN ROUTE YVR ENG 2 COMPRESSOR VANE MSG SEVERAL TIMES DURING FLIGHT. CREW ELECTED TO DIVERT TO YUL. ACFT ROUTED TO BASE FOR INVEST. HMU REPLACED AS PER T/S. 2L72 4F4 FRTA28NM E2GL 20060613000112006061300011GL 2006 6 13 CA060221004 120060208G2730C2CF619A ROD DHAV DHC2 DHC2MKI 2801830GL PWA R985 R985AN14B 52008NE ELEVATOR CORRODED W K NONE O OTHER ININSP/MAINT 1 CA 19966 FOUND ELEVATOR ROD ASSEMBLY RUSTY AD HOLES RUSTED THROUGH TUBE AND WHEN ROD END WAS REMOVED SEVERAL TEASPOONS OF RUSTED METAL FLAKES CAME OUT OF THE TUBE, FOUND DURING AN EXTENSIVE 100 HOUR INSPECTION. 1H71 3R3 RRCA806 5E1 20060613000122006061300012SW 2006 6 13 CA060221006 120060211G54102762019111 PANEL SWRNGNSA226 SA226TC 8780404SW GARRTTTPE331TPE33110UA 01514WP RT NACELLE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 24794 WHILE UN-COWLING, RT ENGINE MAINTEANCE FOUND A PIECE OF STAINLESS STEEL IN THE LOWER SECTION OF COWL. INVESTIGATION REVEALED A HOLE IN THE LT SIDE OF ASPIRATOR ASSEMBLY ABOVE THE OIL COOLER. THE ASPIRATOR WAS REPLACED AND AIRCRAFT SINCE RETURNED TO SERVICE. THE MOST PROBABLE CAUSE WOULD BE FATIGUE CRACKING LEADING TO THE PIECE FALLING INTO THE LOWER COWLING. 2L72 4T4 TRTA8SW E4WE 20060619002072006061900207EU 2006 6 19 CA060221007 120060204G6730SC5083 SERVO SNIAS 350 AS350BA 8680817EU TMECA ARRIELARRIEL1B 6OO30NE FLT CONTROLS FAILED W K NONE O OTHER ININSP/MAINT 1 CA 5759 1753 (CAN) ON GROUND RUN: WHEN HYDRAULIC TEST PUSH BUTTON DEPRESSED AND ACCUMULATORS EMPTY, THE CYCLIC WOULD MOVE HARD TO THE LEFT. SWITCHED LT SERVO AND RT SERVO. THIS PROBLEM MOVED WITH SERVO TO THE RT SIDE. INSTALLED A NEW OVERHAUL SERVO ON THE RT SIDE WHICH CLEARED UP OUR PROBLEM. AC HYDRAULIC SYSTEM NOW OPERATES IAW TYPE. (TC NR 20060221007) 1G71 3U3 UNCH9EU E19EU 20060613000402006061300040 2006 6 13 CA060221008 320060209G6111W69EK763 BLADE DIAMONDA20 DA20C1 2990001GL CONT O240 IO240B 17063SO PROPELLER CRACKED W O OTHER O OTHER TXTAXI/GRND HDL 1 CA 1851 AE7827 DURING PRE-FLIGHT INSPECTION, THE PILOT INSTRUCTOR DISCOVERED A POSSIBLE CRACK ON THE PROPELLER. CLOSER INSPECTION REVEALED AN APPROXIMATELY 4" CRACK ON NR 2 BLADE OF PROPELLER. THE CRACK IS DEVELOPED LONGITUDINAL ON BLADE FROM TIP TO HUB. NO IMPACT MARK OR OTHER DAMAGE TO PROPELLER OBSERVED. PROPELLER REMOVED FROM SERVICE. 1L71 3O3 ONTTA4CH E7SO 20060613001622006061300162SW 2006 6 13 CA060221009 120060213G7603C8102419 CONTROL CABLE SWRNGNSA226 SA226TC 8780404SW GARRTTTPE331TPE33110UA 01514WP HARTZLHCB3T HCB3TN5 GL POWER LEVER FAILED W K NONE O OTHER ININSP/MAINT 1 CA CREW ATTEMPTED TO START THE ENGINE ON 4TH LEG OF THE DAY. ENGINE ACCELERATED TO 30 PERCENT AND TEMPERATURE INCREASED. ENGINE WAS SHUT DOWN. MAINTENANCE DISCOVERED THE POWER LEVER CABLE HAD SEVERED IN THE PEDASTAL AND THE ENGINE WAS STUCK IN FULL REVERSE. (REVERSE IS SELECTED ON SHUTDOWN TO PUT THE PROPS ON THE START LOCKS). THE CABLE WAS REPLACED WITH A SERVICEABLE PART AND THE ENGINE PERFORMED NORMALLY. 2L72 4T4 TRTA8SW E4WE 6 CP15EA 20060613001642006061300164GL 2006 6 13 CA060221010 120060216G24102224121400 BRACKET DIAMONDA20 DA20C1 2990001GL CONT O240 IO240B 17063SO ALTERNATOR CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 550 806495 DURING ROUTINE INSPECTION, A SMALL CRACK WAS DISCOVERED ON THE ALTERNATOR BRACKET. FURTHER INSPECTION REVEALED THAT THE TOP NUT TCM P/N 2443 WHICH IS USED TO MOUNT THE BRACKET TO THE ENGINE WAS STRIPPED. THE NUT ATTACHES TO ONE OF THE ENGINE THRU STUDS AT THE FORWARD MAIN BEARING. LUCKILY THE STUD WAS NOT DAMAGED AND A NEW BRACKET AND NUT WERE INSTALLED AND TQ`D. IT WAS ALSO NOTED THAT ALT BRACKET MOUNTING HOLES ARE LARGER THAN THE STUDS AND BOLT USED TO SECURE THE BRACKET TO ENG. THESE WERE TAUGHT AT FIRST TO BE ELONGATED BUT THE NEW BRACKET SUPPLIED BY THE MANUFACTURE REVEALED THEY WERE MANUFACTURED THIS WAY. A REQUEST WAS SENT TO THE MANUFACTURE FOR EXPLANATION. 1L71 3O3 ONTTA4CH E7SO 20060613001662006061300166NM 2006 6 13 CA060221011 120060220G271085711570102 BRACKET DHAV DHC8 DHC8301 1386003NM PWA PW120 PW123 NE HAMSTD14SF 14SF15 NE AILERON CRACKED W O OTHER F FLT CONT AFFECTED CRCRUISE 1 CA 3531435314 DURING CRUISE FLIGHT, CREW REPORTED AILERON CONTROL SEEMED STIFF. AFTER NORMAL LANDING MAINTENANCE INSPECTION FOUND RT AILERON SUPPORT BRACKET FOR AILERON INPUT QUADRANT CRACKED. CAUSING OUTBOARD AILERON QUADRANT TO RUB ON BRACKET. THIS AIRCRAFT IS PRE MOD 8/2160. DEHAVILLAND SB 8-57-27 REFERS TO THIS BRACKET CRACKING. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20060613001672006061300167EA 2006 6 13 CA060221012 220060220G852018810 CAMSHAFT PIPER PA28 PA28140 7102802SO LYC O320 O320E3D 41508EA SNSNCH74D 74DM EA ENGINE SPALLED W K NONE O OTHER ININSP/MAINT 1 CA 2396 SPALLING ON CAM AND LIFTERS. 1L71 3O3 O 2A13 E274 5 NP88614 20060613001682006061300168SW 2006 6 13 CA060222001 120060217G2820206061677001 LINE BELL 206 206B 1181511SW FUEL SYSTEM CRACKED W K NONE O OTHER ININSP/MAINT 1 CA ON REINSTALLATION OF FUEL LINES IN FUEL VALVE COMPARTMENT TUBE ASSY WAS TORQUED AND FERRULE WAS FOUND TO BE CRACKED. TUBE ASSY WAS SUSPECTED TO BE CRACKED ON REMOVAL BUT NO LEAKS DETECTED. LINE REMOVED FROM SERVICE. RECOMMEND BETTER VISUAL INSPECTION OF ALUMINUM LINES AND PROPER TORQUE PROCEDURES. 1G71 3U H2SW 20060614000392006061400039NE 2006 6 14 CA060222002 320060222G611472429 BOLT HAMSTD CNDAIRCL215 CL2151A10 1900320EA PWA R2800 CA3 52026NE HAMSTD43E 43E60 NE PROP BARREL SHEARED W K NONE O OTHER ININSP/MAINT 1 CA 656 ON RE-ASSEMBLY OF A 43E60-583 PROPELLER, THE TORQUE SEQUENCE OF THE BARREL BOLTS WAS BEING ACCOMPLISHED AS PER CANADAIR MAINTENANCE MANUAL SUPPLEMENT 61-10-51. WHEN TORQING ONE OF THE BARREL BOLTS P/N 72429, THE HEAD SHEARED OFF OF THE BOLT SHANK JUST AS MAXIMUM TORQUE WAS BEING REACHED. IT WAS OBSERVED THAT THE WEIGHT INSERT IN THE MIDDLE OF THE BOLT WAS CORRODED AND COULD BE THE CAUSE OF THE HEAD SHEARING. 2H72 4R4 RRTA14EA E231 6 CP871 20060613001902006061300190CE 2006 6 13 CA060223001 120060223G2510051421518 SEAT BACK CESSNA172 172R 2072401CE LYC IO360 IO360L2A EA MCAULY1C235 1C235LFA GL COCKPIT DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA 3880 WHILE PERFORMING NORMAL MAINTENANCE IT WAS NOTED THAT THE PILOTS SEAT BACK WAS TILTED MORE ON THE LEFT THAN THE RIGHT. THE SEAT WAS REMOVED AND THE MATERIAL WAS REMOVED FROM THE SEAT BACK WHICH REVEALED A CRACKED SEAT BACK FRAME AT THE PIONT WERE THE ALUMINUM SEAT MOUNT CASTING ENDS IN THE SQUARE ALUMINUM TUBING WHICH FORMS THE SEAT BACK. 1H71 3O3 ONT3A12 1E10 5 NP12EA 20060613002942006061300294CE 2006 6 13 CA060223002 120060222G3245302039402 TUBE BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA TIRE SPLIT W O OTHER O OTHER TXTAXI/GRND HDL 1 CA A NORMAL LAND UP UNTIL, SENSED WHAT FELT LIKE DRAGGING BRAKE ON RT M/G. ONCE SAFELY STOPPED, AND ENG`S SHUT DOWN, CREW EXITED A/C, DISCOVERED RT O/B WHEEL ASSY FLAT TIRE. RETURNED TO A/C TO FIND TWO OTHER TIRES FLATTENED. THESE WERE BOTH RT AND LT INBDS TIRES. PLANE RETURNED TO BASE. ONCE THE WHEEL ASSEMBLIES WERE TAKEN APART FOR TIRE/TUBE REPLACEMENT, DISCOVERED INNER TUBES HAD SPLIT IN A RADIAL DIRECTION ACROSS TUBE. THE FOLLOWING MORNING, MX FOUND 4TH MAIN WHEEL, THE ONE NOT PREVIOUSLY REPLACED, ALSO LOST IT'S AIR OVERNIGHT. A SIMILAR SPLIT WAS FOUND IN INNER TUBE. ALL 4 WHEELS WERE NEW JUDGING FROM CONDITION. A/C FLEW DURATION OF FLT IN EXTREME COLD CONDITIONS (-40'C) AT FL 230. 1L72 4T4 T A24CE E4EA 20060613002952006061300295CE 2006 6 13 CA060223003 120060220G273126612159 ACTUATOR CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE HARTZLHCB3T HCB3TN3 GL ELEVATOR TRIM FAILED W K NONE O OTHER ININSP/MAINT 1 CA ELEVATOR TRIM SCREW JACK FAILED ON INSTALLATION. 1H71 3T3 T A37CE E4EA 6 CP15EA 20060614000022006061400002CE 2006 6 14 CA060223004 120060220G273026612159 JACKSCREW CESSNA208 208B 2073701CE PWA PT6 PT6A114 52043NE HARTZLHCB3T HCB3TN3 GL ELEVATOR TRIM FAILED W K NONE O OTHER ININSP/MAINT 1 CA ELEVATOR TRIM SCREW JACK (RT) FAILED ON INSTALLATION. 1H71 3T3 T A37CE E4EA 6 CP15EA 20060614000042006061400004CE 2006 6 14 CA060223005 120060223G523026012031 SPRING CESSNA208 208B 2073701CE DOOR LATCH WEAK W A UNSCHED LANDING E VIBRATION/BUFFET CLCLIMB 1 CA 5337 AIRCRAFT DEPARTED AND AFTER TAKEOFF, ATC INFORMED THE PILOT THAT THE AFT POD CARGO DOOR WAS OPEN. THE AIRCRAFT RETURNED AND THE PILOT IN COMMAND INSPECTED THE DOOR, HINGES AND AND THE POD AND FOUND NO DAMAGE. THE AIRCRAFT DEPARTED AND MAINTENANCE INSPECTED THE DOOR AND FOUND THE DOOR SERVICEABLE. FOUND THE AFT LATCH SPRING WEAK AND REPLACED SPRING AS A PRECAUTION. 1H71 3T A37CE 20060614000062006061400006NM 2006 6 14 CA060224001 120060216G573085720062010 SKIN DHAV DHC8 DHC8* NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE RT WING LE DEPARTED W A UNSCHED LANDING D INFLIGHT SEPARATION CLCLIMB 1 CA 28716 DURING TAKEOFF THE AIRCRAFT LOST THE RT INBOARD LEADING ASSY 611AR UPON ROTATION. THE LEADING EDGE SECTION REPORTEDLY BLEW OFF, AND OVER THE TOP OF THE WING AND CAME DOWN WITHIN THE AIRPORT BOUNDARY AREA TOWARDS THE END OF THE RUNWAY. THE AIRCRAFT WAS ABLE TO PERFORM A CIRCUIT AND LANDED SAFELY. ENGINEERING INSPECTED THE AIRCRAFT AND REPORTED THAT THE UPPER LEADING EDGE ATTACHMENT SCREWS WERE STILL IN PLACE AFTER LANDING, BUT ONLY TWO OF THE 26 LOWER ATTACHMENT SCREWS WERE IN PLACE. ONE SCREW WAS LOCATED TOWARDS THE INBOARD SIDE AND ONE AT THE OUTBOARD SIDE. THE OTHER 24 ATTACHMENT SCREWS WERE MISSING.  2H72 4T4 TRTA13NM E20NE 6 CP7NE 20060614000102006061400010SW 2006 6 14 CA060224002 120060217G6700 CYCLIC CONTROL BELL 427 427 1182207SW COCKPIT OBSTRUCTED W O OTHER F FLT CONT AFFECTED LDLANDING 1 CA CYCLIC STICK FWD MOVEMENT RESTRICTED BY T/R PEDAL STOP MECHANISM CABLE. T/R PEDAL STOP MECHANISM CABLE BRACKET 427-001-296-103 FOUND MISLOCATED. 1G71 3U R00001RC 20060614000122006061400012GL 2006 6 14 CA060224003 220060222G732184250077 FUEL CONTROL BELL 206 206L1 1182107SW ALLSN 250C 250C30 03013GL ENGINE FAILED W E ENGINE SHUTDOWN RJ PARTIAL RPM/PWR LOSS WARNING INDICATION LDLANDING 1 CA 597 CAE895012 ON A TWO MINUTE COOL DOWN AFTER ONE HOUR FLIGHT, THE ENGINE STARTED TO SURGE, THE PILOT SHUTDOWN THE ENGINE AND AFTER A MOMENT TRIED A RESTART BUT IT WOULD NOT LIGHT-OFF. THE ENGINEER FOUND NO FUEL WOULD COME OUT OF FCU. FCU WAS REPLACED. 1G71 3U3 U H2SW E1GL 20060614000142006061400014CE 2006 6 14 CA060224004 120060222G561010138402522 WINDSHIELD BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA COCKPIT FAILED W O OTHER O OTHER CRCRUISE 1 CA WHILE IN CRUISE FLT AT FL 270, APPROXIMATELY 250 MILES INTO THE MIDDAY FLT, FLIGHT CREW REPORTED HEARING A MILDLY LOUD BANG WITHIN THE CABIN. THEY THEN NOTICE SMALL SHARDS OF GLASS FALLING ONTO THE LAP OF THE FIRST OFFICER. THE INNER PANE OF THE RIGHT WINDSHIELD HAD SHATTERED. THE CREW INITIATED THE STANDARD PROCEDURE FOR A CRACKED WINDSHIELD IAW THE POH BY REDUCING THEIR CRUISE SPEED, DESCENDED TO 14000 FEET AND REDUCE CABIN DIFFERENTIAL TO 4.0 PSI. THE FIRST OFFICER DONED HIS GOGGLES AND THEY RETURNED SAFELY. THE WINDSHIELD WAS REPLACED AND THE AIRCRAFT WILL BE RETURNED TO SERVICE UPON COMPLETING THE CURE TIME FOR THE SEALANT. NOTE THAT THE OAT AT THE TIME OF THE FLIGHT AT 270 WAS -47'C. 1L72 4T4 T A24CE E4EA 20060619002322006061900232NE 2006 6 19 CA060224005 220060207G7200 ENGINE SNIAS 350 AS350BA 8680817EU TMECA ARRIELARRIEL1B 6OO30NE FAILED W K NONE O OTHER ININSP/MAINT 1 CA 4272 IN(CAN) AIR OPERATOR: MODULE 3: CENTRIFUGAL COMP. INDUCER PN 0292251370 S/N 1260FT LIFE LIMIT 14000CYC ACTUAL 14711CYC. CENTRIFUGAL COMP. IMPELLER PN 2292252980 S/N 1019FB LIFE LIMIT 14000CYC ACTUAL 14711CYC. REF: MM NR 29201931, CHAP 05-10-03 PAGE 9 (OCT 2003). MODULE 4: FREE TURBINE DISK PN 2292802500 S/N ADB4234YC LIFE LIMIT 10000CYC ACTUAL 10727CYC. REF: MM NR 29201931, CHAP 05-10-03 PAGE 10 (DEC 1996). (TC NR 20060224005). 1G71 3U3 UNCH9EU E19EU 20060614000192006061400019EA 2006 6 14 CA060224006 220060215G7414LW15416 ADAPTER HUGHES269 269C1 8059504SW LYC O360 HO360C1A 41514EA RT MAGNETO BROKEN W K NONE O OTHER ININSP/MAINT 1 CA DURING 25 HOUR INSPECTION, OIL WAS DRAINED FROM ENGINE AND FOUND BEARING CAGE BALL RETAINER MADE OF PLASTIC (KIND OF) ON ENGINE OIL SCREEN. REMOVED BOTH MAGNETO DRIVE ADAPTER ASSEMBLY AND FOUND THE PROBLEM ON THE RT ADAPTER (BALL RETAINERS MISSING). REPLACED THE PART P/N LW15416. 1G71 3O3 OO 4H12 E286 20060614000732006061400073 2006 6 14 CA060224007 420060216G2562 SWITCH POINTER ROBSINR22 R22BETA 7640110NM LYC O320 O320B2C 41508EA ELT FAILED W A UNSCHED LANDING O OTHER CLCLIMB 1 CA 408804 WHEN THE PILOT ACTIVATE THE ELT REMOTE SWITCH IN THE CABIN, THE ELT FAIL TO ACTIVATE. REPLACED ELT. 1G71 3O3 O H10WE E274 20060614000752006061400075CE 2006 6 14 CA060224008 120060224G2710MS21251B5S TURNBUCKLE CESSNA CESSNA650 650 2076802CE GARRTTTPE731TFE7313C WP CONTROL CABLES CHAFED W K NONE O OTHER ININSP/MAINT 1 CA 5899 DURING A SCHEDULED PHASE 5 INSPECTION ON CESSNA 650 C-FIMO, THE TECHNICIAN DISCOVERED THAT THE LT AND RT AILERON OUTBOARD AFT CABLE CHAFED THROUGH THE LOKCLAD AND THE TURNBUCKLE WAS DAMAGED. 2L72 4F4 F A9NM E6WE 20060614000762006061400076CE 2006 6 14 CA060224009 120060224G2510051402133 SEAT CESSNA172 172N 2072434CE LYC O320 O320D2J 41508EA MCAULY1C160 1C160DTM GL COCKPIT CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 11104 WHILE DOING 100HR INSPECTION ON AIRCRAFT AME WAS DOING THE SEAT RAIL INSPECTION NOTICED PILOTS SEAT WAS LOOSE WHEN HE MOVED IT BACK. ON FURTHER INSPECTION OF THE SEAT IT WAS DISCOVERED THAT ONE OF THE ATTACHMENT LEGS USED TO ATTACH THE SEAT TO THE PEDESTAL WAS CRACKED AND ONE OF THE LEGS WAS BROKEN. SEAT WAS REMOVED AND NEW PARTS ORDERED. 1H71 3O3 ONT3A12 E274 5 NP910 20060614000772006061400077CE 2006 6 14 CA060224010 120060222G754042302200 SWIVEL LEAR LEAR 45 45LEAR 5170805CE GARRTTTFE731TFE7312 01518WP PYLON DUCT LEAKING W A UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 CA 1467 ENGINE PYLON DUCT OVERHEAT CAS MESSAGE LIGHT ILLUMINATED 25 MINUTES INTO FLIGHT. AIRCRAFT RETURNED TO BASE. ENGINE GROUND RAN AND FOUND THAT LIGHT EXTINGUISHES WITH POWER BELOW 50%. PYLON DUCT REPLACED. 2L72 4F4 FRTT00008WIE6WE 20060614000792006061400079CE 2006 6 14 CA060224011 120060223G335065181097 BATTERY PACK CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE EMERGENCY LIGHT CORRODED W K NONE O OTHER ININSP/MAINT 1 CA DURING A PHASE INSPECTION, EMERGENCY LIGHT OPERATIONAL CHECK, THE LIGHTS FAILED TO TURN ON. FURTHER INVESTIGATION REVEALED THAT THE EMERGENCY LIGHT POWER SUPPLY WAS DAMAGED. ALL BATTERIES CELLS WERE CORRODED AND THE BATTERY BOX MELTED. THE BATTERY PACK 2 AMP FUSE CHECKED SERVICEABLE. BATTERY PACK WAS REPLACED. 1L72 4F4 F A22CE E1NE 20060614000942006061400094NM 2006 6 14 CA060227001 120060226G324021599 BRAKE ASSY DHAV DHC8 DHC8* NM PWA PW120 PW123 NE HAMSTD14SF 14SF23 NE RT MLG LEAKING W O OTHER KA FLUID LOSS FLAME/FIRE LDLANDING 1 CA BRAKES ON RT MLG CAUGHT FIRE DURING LANDING AND CAUSED A 'FLASH FIRE'. FIRE WAS CAUSED BY FLUID LEAKING FROM BRAKE UNIT AND COMING INTO CONTACT WITH HOT BRAKING SURFACE. AN OFF-DUTY PILOT WITNESSED INCIDENT FROM PAX CABIN AND REPORTED FIRE WAS A 'FLASH BALL' THAT EXTINGUISHED ALMOST IMMEDIATELY. A/C’S FWD MOTION AND PROP WASH BLEW SMOKE AND FLAMES AFT. BOTH TIRES BLEW, FIRE DEPART WERE ON SCENE APPROX 3 MINS AFTER INCIDENT AND COOLED GEAR DOWN, INITIALLY WITH A MIST AND THEN WITH A SPRAY AND THEN A FAN WAS USED TO FURTHER REDUCE TEMP. TEMP READING TAKEN APPROX 23 MINS AFTER INCIDENT SHOWED 350 DEGREES F. A TEMP READING TAKEN A FURTHER 10 MINS LATER SHOWED 240 DEGREES F. A VISUAL INSPECTION OF LWR END OF DR2H72 4T4 TRTA13NM E20NE 6 CP7NE 20060614000952006061400095SW 2006 6 14 CA060227002 120060223G5320206032319023 STIFFENER BELL 206 206L 1181522SW ALLSN 25OC 250C20R GL FUSELAGE CRACKED W O OTHER O OTHER NRNOT REPORTED 1 CA AFTER REMOVAL OF AFT FUSELAGE FAIRING FOR REPAIR. VISUAL INSPECTION AND CLEANING OF AFT FUSELAGE A STIFFENER FOUND CRACKED. STIFFENER REPLACED NEW. 1G71 3U3 U H2SW E4CE 20060614000962006061400096NE 2006 6 14 CA060227003 220060221G7200PW121 ENGINE DHAV DHC8 DHC8* NM PWA PW121 PW121 52124NE HAMSTD14SF 14SF7 NE NR 1 FAILED W O OTHER XJ ENGINE FLAMEOUT WARNING INDICATION DEDESCENT 1 CA PCE121280 DURING DESCENT AN OPERATOR EXPERIENCED AN INCIDENT IN SEVERE TURBULENCE WHERE BOTH PROPELLERS/ENGINES WERE OVERSPEED. THE NR 1 ENGINE HAD THE TORQUE SHAFT BREAK AND THE POWER TURBINE BLADES SEPARATE. BOTH PROPELLERS/ENGINES TO BE REPLACED. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20060614000972006061400097NE 2006 6 14 CA060227004 220060122G7200 TURBINE BLADES CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE HARTZLHCB3T HCB3TN3 GL ENGINE DAMAGED W A UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION NRNOT REPORTED 1 CA 19352 THE PILOT REPORTED A LOSS OF ENGINE POWER AND ATTEMPTED A FORCED LANDING. THE AIRCRAFT CRASHED DURING THE ATTEMPT. PRELIMINARY INVESTIGATION HAS REVEALED TURBINE BLADE DISTRESS. P&WC WILL INVESTIGATE THE INCIDENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 1H71 3T3 T A37CE E4EA 6 CP15EA 20060614000982006061400098 2006 6 14 CA060227005 120060224G71206898806 SUPPORT ALLSN 250C 250C28B 03013GL ENGINE CRACKED W O OTHER O OTHER NRNOT REPORTED 1 CA 8132 1314 ON REMOVAL OF TURBINE SECTION FROM ENGINE ASSY ONE OF THE FWD SUPPORT STUTS WAS FOUND TO BE CRACKED. TURBINE ASSY SENT FOR REPAIR. RECOMMEND BETTER VISUAL INSPECTIONS ON SCHEDUELED INSPECTIONS AND POSSIBLY VIBRATION CHECKS. 3 U E1GL 20060614001732006061400173NE 2006 6 14 CA060227006 220060130G732141380102 FUEL CONTROL PIPER PA46 PA46500TP 7104622SO PWA PT6 PT6A42 52043NE ENGINE MALFUNCTIONED W A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CRCRUISE 1 CA THE ENGINE EXPERIENCED AN UNCOMMANDED POWER REDUCTION IN CRUISE AND WOULD NOT RESPOND TO THROTTLE LEVER INPUT. THE PILOT ACTIVATED THE FUEL CONTROL MANUAL OVER-RIDE AND ACCOMPLISHED AN UNSCHEDULED LANDING. GROUND INSPECTION COULD NOT DUPLICATE THE INCIDENT. THE FUEL CONTROL UNIT WAS SUBSEQUENTLY REPLACED. 1L71 3O4 TRTA25SO E4EA 20060614002072006061400207NE 2006 6 14 CA060227007 220060111G7321 FUEL CONTROL PILATSPC12 PC12 7090550EU PWA PT6 PT6A67B 52043NE ENGINE FAILED W O OTHER RJ PARTIAL RPM/PWR LOSS WARNING INDICATION NRNOT REPORTED 1 CA PR0565 DURING AIRCRAFT FLIGHT TESTING, THE ENGINE DID NOT RE-LIGHT FOLLOWING A COMMANDED INFLIGHT SHUT DOWN FOR RE-LIGHT TEST PURPOSES. A DEAD STICK LANDING WAS ACCOMPLISHED. THE FUEL CONTROL UNIT AND FLOW DIVIDER VALVE WERE SUBSEQUENTLY REPLACED. P&WC WILL MONITOR INVESTIGATION OF THE INCIDENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 1L71 3T4 TRTA78EU E26NE 20060614002092006061400209NE 2006 6 14 CA060227008 220060129G7200 ENGINE AEROSPATR72 ATR72 EU PWA PW120 PW127 NE MALFUNCTIONED W EA ENGINE SHUTDOWN UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 1 CA EB0011 IN CRUISE, THE ENGINE EXPERIENCED AN UNCOMMANDED POWER REDUCTION ACCOMPANIED BY AN UNCOMMANDED INCREASE IN PROP SPEED. THE ENGINE WAS SHUT DOWN IN FLIGHT. GROUND INSPECTION WAS UNABLE TO DUPLICATE THE PROBLEM. THE ENGINE FUEL CONTROL UNIT, FUEL PUMP, FADEC, ELECTRICAL HARNESS AND TORQUE SENSOR WERE SUBSEQUENTLY REPLACED. P&WC WILL MONITOR INVESTIGATION OF THE INCIDENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2H72 4T4 TRT E20NE 20060614002112006061400211EU 2006 6 14 CA060227009 120060203G7930 WARNING LIGHT AEROSPATR72 ATR72 EU PWA PW120 PW127 NE ENGINE OIL SYS ILLUMINATED W E ENGINE SHUTDOWN N FALSE WARNING CRCRUISE 1 CA EB0078 DURING CRUISE, THE ENGINE LOW OIL PRESSURE WARNING ANNUNCIATED. THE ENGINE WAS SHUT DOWN IN FLIGHT. SUBSEQUENT GROUND TESTING WAS UNABLE TO DUPLICATE THE EVENT. THE OIL PRESSURE TRANSMITTER AND LOW OIL PRESSURE SWITCH WERE REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. 2H72 4T4 TRT E20NE 20060614002122006061400212NE 2006 6 14 CA060227010 220060204G7230 COMPRESSOR CESSNA208 208 2073702CE PWA PT6 PT6A114 52043NE ENGINE SEIZED W A UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 CA PR0508 THE ENGINE ACCESSORY GEARBOX CHIP DETECTOR WARNING ANNUNCIATED IN FLIGHT AND AN UNSCHEDULED LANDING WAS CARRIED OUT. SUBSEQUENT INSPECTION REVEALED SEIZURE OF THE COMPRESSOR SECTION. P&WC WILL INVESTIGATE THE INCIDENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 1H71 3T3 TNTA37CE E4EA 20060614002142006061400214EU 2006 6 14 CA060227011 120060225G323019071100403 RELEASE ACTUATOR EMB ERJ170ERJ170100LR EU GE CF34 CF348E5A1 30015NE MLG DOWNLOCK MALFUNCTIONED W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA LEFT MAIN GEAR DID NOT RETRACT AFTER TAKEOFF. NO GEAR PIN ON MAIN WERE FOUND ON ARRIVAL, PARK BRAKE REMAINED ON AFTER BRAKE HANDLE RELEASED. LT MLG DOWNLOCK RELEASE ACTUATOR REPLACED IAW AMM 32-31-05-000-801-A AND 32-31-05-400-801-A. GEAR SWING CARRIED OUT AS PER AMM 32-33-00-710-801-A. ALL FUNCTIONS NORMAL. 2L72 4F4 FRTA56NM E00063EN 20060614002152006061400215NE 2006 6 14 CA060227012 220060201G7210 PACKING AEROSPATR42 ATR42320 8680930EU PWA PW121 PW121 52124NE RGB OIL SYS CUT W E ENGINE SHUTDOWN KJ FLUID LOSS WARNING INDICATION NRNOT REPORTED 1 CA THE ENGINE LOW OIL PRESSURE WARNING ANNUNCIATED AND THE ENGINE WAS SHUT DOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED A CUT O-RING PACKING AT THE PROPELLER CONTROL UNIT ADAPTER INTERFACE TRANSFER TUBE. 2H72 4T4 TRTA53EU E20NE 20060614002172006061400217EU 2006 6 14 CA060227013 120060210G7810 EXHAUST DUCT UROCOPEC135 EC135P1 8680990EU PWA PW206 PW206B 0 NE ENGINE FRACTURED W O OTHER O OTHER NRNOT REPORTED 1 CA DURING FLIGHT, A LOUD WHISTLING NOISE WAS REPORTED BY THE CREW. SUBSEQUENT INSPECTION REVEALED THE ENGINE-MOUNTED AIRFRAME EXHAUST DUCT HAD FRACTURED AND LIBERATED WITH RESULTANT DAMAGE TO THE MAIN ROTOR AND VERTICAL FIN. P&WC WILL MONITOR THE INVESTIGATION OF THE INCIDENT AND WILL ADVISE OF ROOT CAUSE ONCE DETERMINED. 1G72 3U3 UO H88EU E42NE 20060614002182006061400218NE 2006 6 14 CA060227014 220060210G7200 ENGINE CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE FLAMED OUT W O OTHER XJ ENGINE FLAMEOUT WARNING INDICATION TXTAXI/GRND HDL 1 CA 71397 THE ENGINE FLAMED OUT DURING TAXI. SUBSEQUENT INVESTIGATION COULD NOT DUPLICATE THE PROBLEM. THE ENGINE FUEL FILTER WAS REPLACED, THE AIRFRAME RIGGING CHECKED AND THE AIRCRAFT RETURNED TO SERVICE. 1L72 4F4 F A22CE E1NE 20060614002202006061400220SO 2006 6 14 CA060227015 120060223G5740 MOUNT PIPER PA12 PA12 7101202SO LYC O320 O320A2B 41508EA MCAULY1A175 1A175GM GL AFT FLAP PULLEY FAILED W O OTHER F FLT CONT AFFECTED CLCLIMB 1 CA FLAP PULLEY MOUNT INSTALLED IN AFT FUSELAGE CABIN AS PER STC SA578AL AT UNKNOWN TIME, FAILED IN FLIGHT. MOUNT WAS WELDED TO FUSELAGE BRACE TUBE 5/8".035 WALL. TUBING FATIGUED AROUND WELD AND PULLEY MOUNT SHIFTED CAUSING MISALIGNMENT OF PULLEY TO CABLE. THIS CAUSED THE PULLEY TO SUBSEQUENTLY FAIL ON CLIMB AND A LOSS OF "DOWN" FLAP CONTROL. THE TUBING AROUND THE WELD APPEARED WORKED DOWN TO .025" BY UNKNOWN PERSON WHO INSTALLED IT. AIRCRAFT LANDED WITHOUT INCIDENT. 1H71 3O3 O A780 E274 5 NP857 20060614002212006061400221EA 2006 6 14 CA060227016 220060206G7200 ENGINE DHAV DHC6 DHC6300 2802606EA PWA PT6 PT6A27 52043EA POWER LOSS W O OTHER RJ PARTIAL RPM/PWR LOSS WARNING INDICATION DEDESCENT 1 CA 50413 DURING DESCENT, THE ENGINE EMITTED A LOUD NOISE ACCOMPANIED BY A LOSS IN POWER. A SINGLE-ENGINE LANDING WAS ACCOMPLISHED. PWC WILL MONITOR INVESTIGATION OF THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE DETERMINED. 1H72 3T4 TRTA9EA E4EA 20060614002222006061400222NE 2006 6 14 CA060227017 220060215G732181850011 FUEL CONTROL CESSNA500 550 2076604CE PWA 530 PW530A NE ENGINE MALFUNCTIONED W E ENGINE SHUTDOWN F FLT CONT AFFECTED DEDESCENT 1 CA DURING DESCENT, THE ENGINE WAS FOUND TO NOT RESPOND TO THROTTLE LEVER INPUT AND WAS SHUT DOWN IN FLIGHT. THE ENGINE FUEL CONTROL UNIT AND FLOW DIVIDER VALVE WERE SUBSEQUENTLY REPLACED. 1L72 4F4 F A22CE E00053EN 20060614002242006061400224EA 2006 6 14 CA060227018 220060213G7261 ENGINE EMB 110 EMB110* SO PWA PT6 PT6A28 EA OIL SYS LEAKING W EA ENGINE SHUTDOWN UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CLCLIMB 1 CA 50036 DURING CLIMB, THE ENGINE EMITTED A NOISE ACCOMPANIED BY AN UNCOMMANDED REDUCTION IN POWER AND INCREASE IN TURBINE TEMPERATURE. THE ENGINE WAS SHUT DOWN IN FLIGHT AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE. GROUND INSPECTION REVEALED AN ENGINE OIL LEAK. THE ENGINE HAD BEEN OVERHAULED 100 HOURS PRIOR TO THE EVENT, WHERE IT WAS CONVERTED UNDER STC TO A PT6A-34 CONFIGURATION. PWC WILL MONITOR INVESTIGATION OF THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 1L72 4T4 TRTA21SO E4EA 20060614002252006061400225NE 2006 6 14 CA060227019 220060219G7200 ENGINE PILATSPC12 PC12 7090550EU PWA PT6 PT6A67B 52043NE MALFUNCTIONED W O OTHER F FLT CONT AFFECTED APAPPROACH 1 CA PR0117 ON APPROACH, THE ENGINE WAS FOUND NOT TO RESPOND THE THROTTLE LEVER INPUT. THE PILOT ENGAGED THE FUEL CONTROL MANUAL OVER-RIDE AND REGAINED AUTHORITY OVER THE ENGINE. P&WC WILL MONITOR THE INVESTIGATION OF THE INCIDENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 1L71 3T4 TRTA78EU E26NE 20060615000032006061500003NE 2006 6 15 CA060227020 220060213G7200 ENGINE CESSNA500 550 2076604CE PWA JT15 JT15* 52060NE POWER LOSS W E ENGINE SHUTDOWN ERJVIBRATION/BUFFET PARTIAL RPM/PWR LOSS WARNING INDICATION DEDESCENT 1 CA ON DESCENT, THE ENGINE WAS REPORTED TO EMIT A GRINDING NOISE ACCOMPANIED BY AN UNCOMMANDED POWER LOSS. THE ENGINE WAS SHUT DOWN IN FLIGHT AND A SINGLE-ENGINE LANDING ACCOMPLISHED AT POINT OF DESTINATION. GROUND INSPECTION REVEALED INTERNAL ENGINE DAMAGE. P&WC WILL MONITOR INVESTIGATION OF THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE DETERMINED. 1L72 4F4 T A22CE E1NE 20060615000042006061500004NE 2006 6 15 CA060227021 220060221G7261 LINE CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE REDUCTION GBOX FRACTURED W A UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION NRNOT REPORTED 1 CA DURING FLIGHT, THE ENGINE LOW OIL PRESSURE WARNING ANNUNCIATED FOLLOWED BY AN UNCOMMANDED ROLL BACK IN ENGINE POWER. THE ENGINE WAS SECURED IN FLIGHT AND A SUCCESSFUL FORCED LANDING ACCOMPLISHED. SUBSEQUENT INSPECTION REVEALED A FRACTURED PRESSURE OIL TRANSFER TUBE ELBOW. P&WC WILL MONITOR INVESTIGATION OF THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE DETERMINED. 1H71 3T3 T A37CE E4EA 20060615000082006061500008NE 2006 6 15 CA060227022 220060220G7200 ENGINE CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE FAILED W O OTHER XJ ENGINE FLAMEOUT WARNING INDICATION CLCLIMB 1 CA THE ENGINE EXPERIENCED AN UNCOMMANDED IN-FLIGHT SHUT DOWN AFTER TAKEOFF. SUBSEQUENT INSPECTION REVEALED DEBRIS IN THE ENGINE EXHAUST. P&WC WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE DETERMINED. 1L72 4F4 F A22CE E1NE 20060615000102006061500010CE 2006 6 15 CA060227023 120060224G3230M710501 MOTOR BEECH 90 F90 1152909CE PWA PT6 PT6A135 52043NE HARTZLHCB4T HCB4TN3 GL NLG UNSERVICEABLE W L ABORTED APPROACH J WARNING INDICATION LDLANDING 1 CA 5160 NOSE GEAR FAILED TO EXTEND CORRECTLY AS INDICATED BY GEAR IN TRANSIT. GEAR EXTENDED MANUALLY AND LANDED WITHOUT INCIDENT. CAUSE UNDER INVESTIGATION AT THIS TIME. 1L72 4T4 T A31CE E4EA 6 CP40EA 20060615000112006061500011CE 2006 6 15 CA060227024 120060116G7120509800891 MOUNT BEECH 100 A100A CE PWA PT6 PT6A27 52043EA HARTZLHCB3T HCB3TN3 GL RT ENGINE DETACHED W K NONE O OTHER ININSP/MAINT 1 CA UPPER INBOARD ENGINE MOUNT FITTING RT NACELLE UNDER SKIN FOUND DETACHED. SUBSEQUENT INSPECTION OF OTHER FITTINGS ON SAME AIRCRAFT (THERE ARE 4) FOUND ALL WITH ATTACHING FASTENER DEFECTS SUCH AS LOOSE OR SHEARED. AREA IS ALMOST UN-INSPECTABLE. SUGGEST BOROSCOPE INSPECTION OR REMOVING A PORTION OF NACELLE SKIN IF ENGINE MOUNT MOVEMENT IS DETECTED IN FITTING AREA. 1L72 3T4 T A14CE E4EA 6 CP15EA 20060615000122006061500012EA 2006 6 15 CA060228001 120060215G56106003303025 WINDSHIELD CNDAIRCL604 CL604 1900301EA GE CF34 CF343B1 NE CRACKED W O OTHER O OTHER CRCRUISE 1 CA WHILE CRUISING THE LT WINDSHIELD OUTER PLY CRACKED. THE AIRCRAFT CONTINUE INTO WHERE A NEW WINDSHIELD WAS INSTALLED. 2L72 4F4 FRTA21EA E15NE 20060615000142006061500014CE 2006 6 15 CA060228002 120060224G30005918411 DIODE LEAR 45 45LEAR 5170805CE GARRTTTFE731TFE7312 01518WP ANTI-ICE SYSTEM FAILED W O OTHER L NO TEST TXTAXI/GRND HDL 1 CA 2577 DURING PREDEPARTURE CHECK, THE LT ANTI-ICE VALVE FAILED TO OPEN. DURING TROUBLESHOOTING OF THE SYSTEM FOUND THE DIODE D25 HAD HIGH RESISTANCE PREVENTING THE ANTI-ICE SHUTOFF VALVE TO GET A GROUND WHEN REQUIRED. NEW DIODE WAS INSTALLED AND SYSTEM FUNCTIONED CHECK NORMAL. 2L72 4F4 FRTT00008WIE6WE 20060615000162006061500016EU 2006 6 15 CA060228003 120060226G27509028A000201 PICKUP AIRBUS310 A310300 3930305EU GE CF6 CF680C2* GL TE FLAPS CONTAMINATED W O OTHER O OTHER LDLANDING 1 CA AIRCRAFT LANDED WITH FULL SLATS AND NO FLAPS. UNABLE TO EXTEND FLAPS ON LANDING. SYSTEM TORQUE LIMITERS AND SCREW JACKS LIMITER INSPECTED AND NO FAULT FOUND. DURING TROUBLESHOOTING, THE LT AND RT POWER PICK UP UNITS WERE FOUND CONTAMINATED WITH SKYDROL AND READOUTS NOT MEETING THE MM LIMITS. BOTH UNITS REPLACED AND SYSTEM TESTED SERVICEABLE. 2L72 4F4 FRTA35EU E23EA 20060615000172006061500017NM 2006 6 15 CA060228004 120060226G3230846802 PSEU BOEING767 767233 1385113NM PWA JT9 JT9D7R4D 52054NE MLG MALFUNCTIONED W O OTHER J WARNING INDICATION APAPPROACH 1 CA SELECTING LANDING GEAR DOWN, STATUS MSG 'LDG GEAR MONITOR' CAME ON AND REMAINED ON, DURING LANDING, TAXI, AND PARKING. PSEU CARD FAILED ILLUM. PSEU REPLACED PER AMM 32-09-04 PB 401. PSEU BITE TEST OKAY. MESSAGES CLEARED. OKAY TO PROCEED. 2L72 4F4 FRTA1NM E3NE 20060615000192006061500019CE 2006 6 15 CA060228005 120060220G273126612159 JACKSCREW CESSNA208 208B 2073701CE PWA PT6 PT6A114 52043NE HARTZLHCB3T HCB3TN3 GL ELEVATOR TRIM DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA THE LT ELEVATOR TRIM JACK WAS REMOVED AND DISASSEMBLED FOR INSPECTION AFTER THE RT TRIM JACK FAILED ON INSTALLATION. THE LT TRIM JACK WAS FOUND TO CONTAIN NO GREASE. THE JACK WAS INSPECTED, LUBRICATED IAW AMM 27-30-02, 9A, REASSEMBLED, TESTED AND RETURNED TO SERVICE. 1H71 3T3 T A37CE E4EA 6 CP15EA 20060615001442006061500144 2006 6 15 CA060228006 420060222G34189754421421 VANE ROSEMOUNT PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL AOA TRANSMITTER INOPERATIVE W K NONE O OTHER ININSP/MAINT 1 CA 1573 0288 DURING A ROUTINE PHASE 5 INSPECTION , THE LT AOA VANE HEATER WAS FOUND TO BE INOPERATIVE. ASSY REPLACED WITH SERVICEABLE UNIT. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20060615001882006061500188EU 2006 6 15 CA060228007 120060119G21609599020135 CONTROL VALVE PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL CABIN TEMP INTERMITTENT W D RETURN TO BLOCK J WARNING INDICATION TXTAXI/GRND HDL 1 CA 1608 0048 TEMPERATURE CONTROL VALVE FOUND TO INTERMITTENTLY STICK AT HOT POSITION CAUSING A DUCT TEMPERATURE WARNING. VALVE REPLACED WITH SERVICEABLE ASSY. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20060615001892006061500189NM 2006 6 15 CA060228008 120060227G291065C265101024 LINE BOEING737 737522 138449FNM CFMINTCFM56 CFM563C 13802EU HYD SYSTEM CHAFED W K NONE K FLUID LOSS ININSP/MAINT 1 CA FLUID LEAK ON RT GEAR "UP" HYDRAULIC RETURN LINE NOTICED DURING OVERNIGHT CHECK. LINE WAS CHAFED THROUGH DUE TO RUBBING ON A BRACKET. LINE REPLACED,GEAR SWING CARRIED OUT AND AIRCRAFT RETURNED TO SERVICE. TT-37255:17 TC-22887. 2L72 4F4 FRTA16WE E21EU 20060615001912006061500191CE 2006 6 15 CA060228009 120060222G27312661259 JACKSCREW CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE ELEVATOR TRIM FAILED W K NONE W OINADEQUATE Q C OTHER ININSP/MAINT 1 CA 8 AS A PRECAUTION FOLLOWING THE FAILURE ON INSTALLATION OF A SIMILAR TRIM JACK ON A DIFFERENT AIRCRAFT, BOTH ELEVATOR TRIM JACKS ON FSKS WERE REMOVED AND DISASSEMBLED TO INSPECT FOR CORRECT LUBRICATION. THE LT TRIM JACK (S/N CA0009) WAS FOUND TO BE CORRECTLY LUBRICATED. THE RT TRIM JACK (S/N CA0008) WAS FOUND TO BE DEVOID OF GREASE. BOTH JACKS WERE CLEANED, INSPECTED, REPACKED WITH GREASE IAW AMM 27-30-02 9A. REASSEMBLED, FUNCTION TESTED, AND RETURNED TO SERVICE. 1H71 3T3 T A37CE E4EA 20060615001952006061500195CE 2006 6 15 CA060228013 120060220G3340TTGCTA201TWB SWITCH CESSNA172 172P 2072436CE LYC O320 O320D2J 41508EA MCAULY1C160 1C160DTM GL EXTERIOR LIGHTS SEIZED W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS APAPPROACH 1 CA UPON APPROACH TO LAND, PILOT TURNED ON LANDING LIGHT AND OBSERVED A SMALL AMOUNT OF SMOKE COMING FROM THE SWITCH AND WAS UNABLE TO TURN THE SWITCH OFF DUE TO IT SEIZING IN THE 'ON' POSITION. TURNED OFF THE AIRCRAFT MASTER SWITCH INSTEAD AND LANDED SAFELY. THE SWITCH WAS REPLACED. THE REMOVED SWITCH LOOKED NORMAL ON THE OUTSIDE BUT THE WHITE PORTION WAS SLIGHTLY BLACKENED. 1H71 3O3 ONT3A12 E274 5 NP910 20060615001972006061500197CE 2006 6 15 CA060228014 120060206G5700 WING CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE MCAULY3AF34C3GFR34C703 GL BOTH MISINSTALLED W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA DURING INSPECTION, FOUND INBD EDGES OF BOTH LT AND RT FLAP ASSEMBLIES WERE TOUCHING FUSELAGE IN FULL UP POSITION. MX DEPART COMPLETED INSPECTIONS OF FOLLOWING AREAS FLAP ATTACHMENT, FLAP RIGGING, FLAP STRUCTURE FOR BENDING OR WARPING, STRUCTURE OF WINGS FOR BENDING OR WARPING. NOTHING WAS FOUND. 13 MONTHS PREVIOUS, WINGS WERE REMOVED TO FACILITATE INSPECTIONS FOR CORROSION AND STRUCTURAL DAMAGE. WHEN WINGS WERE REINSTALLED ATTACHING HARDWARE REPLACED WITH NEW. REAR ATTACH POINTS OF WINGS ARE ADJUSTABLE TO SET WING AT PROPER ANGLE. WINGS WERE ADJUSTED OUT AND A TEST FLT WAS COMPLETED. ALL OTHER CARAVANS IN FLEET WERE INSPECTED, NO FAULTS FOUND. CESSNA WAS ALSO MADE AWARE OF THE SITUATION. 1H71 3T3 T A37CE E4EA 5 CP60GL 20060615001982006061500198CE 2006 6 15 CA060228015 120060119G71209998000060463 MOUNT BEECH 99 99AFACH CE PWA PT6 PT6A27 52043EA HARTZLHCB3T HCB3TN3 GL RT ENGINE DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA 35093 DURING A SCHEDULED DETAILED NR 3 INSPECTION, OBSERVED THE RT ENGINE MOUNT ASSY HAD SEPARATED APPROX 1/4 OF AN INCH FROM RT NACELLE. LIFTING OF ENG WITH CRANE CONFIRMED MOVEMENT. VISUAL INSPECTION REVEALED 2 OF THE 4 UPPER INBD BOTTOM ENGINE MOUNT CASTING RIVITS SHEARED. THIS AREA IS DIFFICULT TO INSPECT. REMOVAL OF THE INBD AND OUTBD NACELLE SKINS IS THE ONLY WAY TO GAIN ACCESS TO THE UPPER CASTINGS FOR INSPECTION WHICH WERE FOUND WITH SIGNS OF RIVET FAILURE. THE RT ENGINE, PROPELLER, COWLINGS, AND FUSELAGE SUFFERED SUDDEN STOPPAGE DAMAGE BY A DEER STRIKE 125 HOURS PRIOR TO THESE OBSERVATIONS WHICH MAY HAVE ATTRIBUTED IN THIS FAILURE. REPAIRS C/O BY R.D.C. 1L72 3T4 T A14CE E4EA 6 CP15EA 20060615002002006061500200NE 2006 6 15 CA060228016 220060222G7200 ENGINE AEROSPATR72 ATR72 EU PWA PW120 PW127 NE FLAMED OUT W A UNSCHED LANDING XJ ENGINE FLAMEOUT WARNING INDICATION DEDESCENT 1 CA 127025 ON DESCENT, THE ENGINE FLAMED OUT AND THE PROPELLER FEATHERED. A RE-LIGHT ATTEMPT WAS UNSUCCESSFUL. P&WC WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2H72 4T4 TRT E20NE 20060615002012006061500201CE 2006 6 15 CA060228017 120060227G7931 OIL SYSTEM PW306C CESSNA680 680CE 2076811CE PWA 306 PW306B NE ENGINE LOW W EA ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA CG0023 FOLLOWING TAKEOFF ENGINE OIL PRESSURE DECREASED AND THE ENGINE WAS SHUT DOWN IN FLIGHT. THE AIRCAFT DIVERTED FOR AN UNSCHEDULED LANDING. P&WC WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED. 2L72 4F4 FRCT00012WIE35NE 20060615002042006061500204NE 2006 6 15 CA060228018 220060206G7314B8187B PUMP ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE FUEL SYSTEM SEIZED W O OTHER J WARNING INDICATION TXTAXI/GRND HDL 1 CA 628 PILOT WAS ATTEMPTING TO START THE AIRCRAFT AND THE AUX PUMP LIGHT ILLUMINATED AND THE CB POPPED. IT WAS RESET AND AGAIN THE CB POPPED. THE PUMP WAS REPLACED AND NO FURTHER DEFECT WAS NOTED. 1G71 3O3 O H11NM 1E4 20060616000382006061600038NE 2006 6 16 CA060228019 220060220G7314B8187B PUMP ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE FUEL FAILED W K NONE O OTHER ININSP/MAINT 1 CA 128 DURING START UP PILOT COULD NOT PRIME THE AIRCRAFT. FURTHER INVESTIGATION FOUND PUMP FAILED. PUMP REPLACED AND NO FURTHER DEFECTS NOTED. 1G71 3O3 O H11NM 1E4 20060616000402006061600040 2006 6 16 CA060228021 420060210G2562PS400010 ELT ROBSINR44 R44 7640120WP LYC O540 O540F1B5 41532EA CABIN MALFUNCTIONED W K NONE O OTHER ININSP/MAINT 1 CA 93 DURING AN ANNUAL ELT RECERTIFICATION A FUNCTION CHECK OF THE G SWITCH WAS CARRIED OUT. IT WAS NOTED TO SET OFF PRIOR TO ITS REQUIRED SETTING (FAULTY G SWITCH). ELT HAS BEEN SENT BACK TO POINTER FOR REPAIR. 1G71 3O3 O H11NM E295 20060616000432006061600043NM 2006 6 16 CA060301002 120060227G324026124121A CARRIER ASSY BOEING767 7673Y0 NM PWA 4060 PW4060 52119NE NR 4 BRAKE BURNED W O OTHER A FLAME/FIRE TXTAXI/GRND HDL 1 CA GND CREW REPORTED BRAKE FIRE ON RT MAIN GEAR AFTER SHUTDOWN. FIRE EXTINGUISHED. FOUND NR 4 BRAKE PISTONS WORN THROUGH STATORS AND INTO THE ROTORS. AXLE INSPECTED AS PER AMM 05-51-15-212-001 AND 05-51-14 PB201. AXLE OK. BRAKE REPLACED AS PER JC 6-232A. WHEEL ASSY. REPLACED AS PER JC 6-232B. FURTHER INFO WILL FOLLOW WITH WHEEL/BRAKE SHOP REPORT. 2L72 4F4 FRTA1NM E24NE 20060616000442006061600044 2006 6 16 CA060301003 420060301G2562PS400010 ELT ROBSINR44 R44 7640120WP LYC O540 O540F1B5 41532EA CABIN WEAK W K NONE O OTHER ININSP/MAINT 1 CA 657 DURING ANNUAL RECERTIFICATION, FOUND G SWITCH WEAK. ELT SENT BACK TO OVERHAUL FACILITY. 1G71 3O3 O H11NM E295 20060616000452006061600045 2006 6 16 CA060301004 420060301G2562PS400010 ELT ROBSINR44 R44 7640120WP LYC O540 O540F1B5 41532EA CABIN WEAK W K NONE O OTHER ININSP/MAINT 1 CA 92 DURING ANNUAL RECERTIFICATION, FOUND G SWITCH WEAK. ELT SENT BACK TO OVERHAUL FACILITY. 1G71 3O3 O H11NM E295 20060616000472006061600047EA 2006 6 16 CA060301005 120060228G541060L12AA COWL LATCH DHAV DHC2 DHC2MK3 2800107EA NACELLE DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA INSPECTION PERSONNEL AT VIKING AIR HAVE DISCOVERED A REOCCURENCE OF SUBSTANDARD COWL LATCHES; THIS ISSUE WAS PREVIOUSLY RAISED, AND ADDRESSED THROUGH 2 SERVICE BULLETINS, TB/7 (FOR THE TURBO BEAVER) AND 6/34 (FOR THE TWIN OTTER). 1H71 3T A806 20060616000482006061600048EA 2006 6 16 CA060301006 120060228G541060L12AA COWL LATCH DHAV DHC6 DHC6 2802606EA NACELLE DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA INSPECTION PERSONNEL AT VIKING AIR HAVE DISCOVERED A REOCCURRENCE OF SUBSTANDARD COWL LATCHES; THIS ISSUE WAS PREVIOUSLY RAISED, AND ADDRESSED THROUGH 2 SERVICE BULLETINS - TB/7 (FOR THE TURBO BEAVER) AND 6/34 (FOR THE TWIN OTTER). 1H72 3T RTA9EA 20060616000492006061600049CE 2006 6 16 CA060301007 120060224G3230K10004 NUT PLATE BEECH 1018200351 BEECH B300 B300 1159232CE PWA PT6 PT6A60A 52043NE HARTZLHCB4M HCB4M GL MLG DAMAGED W L ABORTED APPROACH N FALSE WARNING APAPPROACH 1 CA 1700 PAC16505 AIRCRAFT WAS ON APPROACH. POSITIVE NOSE GEAR DOWN LOCK WAS NOT INDICATING USING THE NORMAL SYSTEM. EMERGENCY GEAR DOWN WAS REQUIRED TO HAVE POSITIVE DOWN AND LOCK INDICATION. NOSE LANDING GEAR INSPECTION WAS CARRIED OUT OF THE GREEN LIGHT INDICATOR SWITCHES ON THE ACTUATOR AND DRAG BRACE. THE SWITCH STOP WAS BACKED OFF INTO THE ANCHOR NUT. STOP WAS RERIGGED AND SECURED. LANDING GEAR SWING CARRIED OUT AS PER B300 MM AND CHECKED SERVICEABLE. 2L72 4T4 TRTA24CE E4EA 6 CP56GL 20060616001092006061600109NM 2006 6 16 CA060302001 120060227G2121 BEARING SUNDSTRANDAI BOEING767 767300 1385204NM GE CF6 CF680C2B7 NE COOLING FAN DAMAGED W H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 1 CA 8132 3490 FORWARD EQUIPMENT COOLING FAN BEARINGS APPEARED TO BE DAMAGED AND THE FAN SHOWS SIGNS OF RUBBING ON THE CASE. 2L72 4F4 FRTA1NM E13NE 20060619000462006061900046EA 2006 6 19 CA060302002 120060223G2810215640011 FUEL CELL CNDAIRCL215 CL2156B11215 EA PWA PW120 PW123 NE HAMSTD14SF 14SF* NE NR 1 LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA 1253 WHILE COMPLETING THE A 500 HR INSPECTION, FUEL WAS FOUND DRIPPING FROM THE RIGHT WING TIP. BY TRANSFERRING FUEL IT WAS DETERMINED THAT THE LEAK WAS IN THE RIGHT FUEL SYSTEM. THE A/C WAS DEFUELED AND THE FUEL CELLS WERE TAKEN OUT AND CHECKED FOR LEAKS. UPON INSPECTION 6 OUT OF THE 8 CELLS WERE FOUND TO BE LEAKING INCLUDING THIS ONE. CELL WAS REMOVED AND REPLACED. 2H72 4T4 TRTA14EA E20NE 6 CP7NE 20060619000472006061900047EA 2006 6 19 CA060302003 120060223G281021564002 FUEL CELL CNDAIRCL215 CL2156B11215 EA PWA PW120 PW123 NE HAMSTD14SF 14SF* NE NR 2 LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA 1253 WHILE COMPLETING THE A 500 HR INSPECTION FUEL WAS FOUND DRIPPING FROM THE RIGHT WING TIP. BY TRANSFERING FUEL IT WAS DETERMINED THAT THE LEAK WAS IN THE RIGHT HAND FUEL SYSTEM. THE A/C WAS DEFUELED AND THE FUEL CELLS WERE TAKEN OUT AND CHECKED FOR LEAKS. UPON INSPECTION 6 OUT OF THE 8 CELLS WERE FOUND TO BE LEAKING INCLUDING THIS ONE. 2H72 4T4 TRTA14EA E20NE 6 CP7NE 20060619000482006061900048EA 2006 6 19 CA060302004 120060223G2810215640024 FUEL CELL CNDAIRCL215 CL2156B11215 EA PWA PW120 PW123 NE HAMSTD14SF 14SF* NE NR 3 LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA 1253 WHILE COMPLETING THE A 500 HR INSPECTION FUEL WAS FOUND DRIPPING FROM THE RIGHT WING TIP. BY TRANSFERING FUEL IT WAS DETERMINED THAT THE LEAK WAS IN THE RIGHT HAND FUEL SYSTEM. THE A/C WAS DEFUELED AND THE FUEL CELLS WERE TAKEN OUT AND CHECKED FOR LEAKS. UPON INSPECTION 6 OUT OF THE 8 CELLS WERE FOUND TO BE LEAKING INCLUDING THIS ONE. CELL WAS REMOVED AND REPLACED. 2H72 4T4 TRTA14EA E20NE 6 CP7NE 20060619000492006061900049EA 2006 6 19 CA060302005 120060223G2810215640026 FUEL CELL CNDAIRCL215 CL2156B11215 EA PWA PW120 PW123 NE HAMSTD14SF 14SF* NE NR 5 LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA 1253 WHILE COMPLETING THE A 500 HR INSPECTION FUEL WAS FOUND DRIPPING FROM THE RIGHT WING TIP. BY TRANSFERRING FUEL IT WAS DETERMINED THAT THE LEAK WAS IN THE RIGHT HAND FUEL SYSTEM. THE A/C WAS DEFUELED AND THE FUEL CELLS WERE TAKEN OUT AND CHECKED FOR LEAKS. UPON INSPECTION 6 OUT OF THE 8 CELLS WERE FOUND TO BE LEAKING INCLUDING THIS ONE. CELL WAS REMOVED AND REPLACED. 2H72 4T4 TRTA14EA E20NE 6 CP7NE 20060619000502006061900050EA 2006 6 19 CA060302006 120060223G281021564002 FUEL CELL CNDAIRCL215 CL2156B11215 EA PWA PW120 PW123 NE HAMSTD14SF 14SF* NE NR 6 LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA 1253 WHILE COMPLETING THE A 500 HR INSPECTION, FUEL WAS FOUND DRIPPING FROM THE RIGHT WING TIP. BY TRANSFERING FUEL IT WAS DETERMINED THAT THE LEAK WAS IN THE RIGHT HAND FUEL SYSTEM. THE A/C WAS DEFUELED AND THE FUEL CELLS WERE TAKEN OUT AND CHECKED FOR LEAKS. UPON INSPECTION 6 OUT OF THE 8 CELLS WERE FOUND TO BE LEAKING INCLUDING THIS ONE. CELL WAS REMOVED AND REPLACED. 2H72 4T4 TRTA14EA E20NE 6 CP7NE 20060619000512006061900051EA 2006 6 19 CA060302007 120060223G2810215640751 FUEL CELL CNDAIRCL215 CL2156B11215 EA PWA PW120 PW123 NE HAMSTD14SF 14SF* NE NR 8 LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA 1253 WHILE COMPLETING THE A 500 HR INSPECTION FUEL WAS FOUND DRIPPING FROM THE RIGHT WING TIP. BY TRANSFERRING FUEL IT WAS DETERMINED THAT THE LEAK WAS IN THE RIGHT HAND FUEL SYSTEM. THE A/C WAS DEFUELED AND THE FUEL CELLS WERE TAKEN OUT AND CHECKED FOR LEAKS. UPON INSPECTION 6 OUT OF THE 8 CELLS WERE FOUND TO BE LEAKING INCLUDING THIS ONE. CELL WAS REMOVED AND REPLACED. 2H72 4T4 TRTA14EA E20NE 6 CP7NE 20060616001462006061600146EA 2006 6 16 CA060302008 120060223G2810CL215640751 FUEL CELL CNDAIRCL215 CL2156B11215 EA PWA PW120 PW123 NE HAMSTD14SF 14SF* NE LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA 1342 WHILE COMPLETING THE A 500 HR INSPECTION FUEL WAS FOUND DRIPPING FROM THE RIGHT WING TIP. BY TRANSFERRING FUEL IT WAS DETERMINED THAT THE LEAK WAS IN THE RIGHT FUEL SYSTEM. THE A/C WAS DEFUELED AND THE FUEL CELLS WERE TAKEN OUT AND CHECKED FOR LEAKS. UPON INSPECTION 6 OUT OF THE 8 CELLS WERE FOUND TO BE LEAKING INCLUDING THIS ONE. CELL WAS REMOVED AND REPLACED. 2H72 4T4 TRTA14EA E20NE 6 CP7NE 20060616001472006061600147WP 2006 6 16 CA060302009 120060220G2913 SEAL ROBSIN ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE HYDRAULIC PUMP LEAKING W K NONE O OTHER ININSP/MAINT 1 CA 1664 0763 INPUT SEALS FOUND TO BE LEAKING DURING INSPECTION. PUMP WAS REPLACED WITH SERVICEABLE UNIT. 1G71 3O3 O H11NM 1E4 20060616001482006061600148WP 2006 6 16 CA060302010 120060220G6730 SEAL ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE SERVO LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA 1664 LOWER PISTON SEAL WAS FOUND LEAKING. SERVO WAS REPLACED WITH A SERVICEABLE UNIT. 1G71 3O3 O H11NM 1E4 20060616001492006061600149WP 2006 6 16 CA060302011 120060220G6730VARIOUS SEAL ROBSIN ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE SERVO LEAKING W K NONE O OTHER ININSP/MAINT 1 CA 1664 1976 UPPER PISTON SEAL LEAKING. NEW SEAL AND O-RING INSTALLED. NO FURTHER DEFECTS FOUND. 1G71 3O3 O H11NM 1E4 20060619002522006061900252GL 2006 6 19 CA060302012 220060118G7297 WIRE HARNESS CVAC 440 440 2422902WP ALLSN 501D 501D13 03004GL LT ENGINE MISINSTALLED W E ENGINE SHUTDOWN O OTHER CRCRUISE 1 CA AIRCRAFT ON A TEST FLIGHT AND DURING AN RPM DECAY TEST, THE LT ENGINE POWER LEVER WAS REDUCED BELOW 1400 HP. THE RPM THEN STARTED TO DECAY BELOW PRESCRIBED LIMITS. DUE TO THIS, THE CREW ELECTED TO SHUT DOWN THE ENGINE. THE PROBLEM ONLY OCCURRED BELOW 1400 HP. THE CREW CARRIED OUT SEVERAL RESTARTS, WHICH DID NOT RESOLVE THE OCCURRENCE AND ELECTED TO LAND WITH THE ENGINE SHUT DOWN. TROUBLE SHOOTING IDENTIFIED AN INCORRECT WIRING CONFIGURATION, WHICH WAS CORRECTED. 2L72 4R4 T 6A6 E282 20060619000812006061900081EA 2006 6 19 CA060302013 120060226G5610NP1393226 WINDOW CNDAIRCL600 CL6002C10 1390015EA GE CF34 CF348C1 NE COCKPIT CRACKED W O OTHER O OTHER APAPPROACH 1 CA 6762 COPILOT SIDE WINDOW BROKEN. SIDE WINDOW CHECKED, FOUND MIDDLE PLY DAMAGED. RT SIDE WINDOW ACC AMM TASK 56-12-01-000-801 CHANGED. 2L72 4F4 FRTA21EA EOOO63EN 20060619000892006061900089EA 2006 6 19 CA060302014 120060228G2133GG670980041 OUTFLOW VALVE CNDAIRCL600 CL6002C10 1390015EA GE CF34 CF348C1 NE CABIN PRESSURE MALFUNCTIONED W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA UNABLE TO PRESSURIZE CABIN IN FLIGHT. AIRCRAFT RETURNEDTO FIELD OF ORIGIN. GROUND VALVE REPLACED. 2L72 4F4 FRTA21EA EOOO63EN 20060619000912006061900091WP 2006 6 19 CA060303001 120060301G2822B8187B PUMP ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE FUEL SYS FAILED W O OTHER O OTHER TXTAXI/GRND HDL 1 CA 541 DURING START UP THE AUX FUEL PUMP C/B POPPED. FUEL PUMP WAS REPLACED AND NO FURTHER DEFECTS WERE NOTED. HAVE AUDITED THE FUEL PUMP ISSUE. HAVE HAD SEVERAL PUMPS IN THE LAST YEAR FAIL. 1G71 3O3 O H11NM 1E4 20060619000932006061900093CE 2006 6 19 CA060303002 120060201G571118144L SPAR BEECH 18 3TM 1151046CE PWA R985 R985AN14B 52008NE HAMSTD22D 22D30 NE WING CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 8290 CENTER SECTION FUSELAGE REAR WING CARRY-THRU SPAR CRACKED 3/4" FROM TOP OF SPAR RUNNING DOWNWARD AT EDGE OF REINFORCEMENT INSIDE FUSELAGE AT REAR LT FLOAT FITTING STATION NR 199.5 BULKHEAD NR 8. 1L72 3R3 R A765 5E1 5 CP736 20060619000962006061900096 2006 6 19 CA060303003 420060221G3497 CONNECTOR COLLINS 6227384001 CNDAIRCL600 CL600* EA GE CF34 CF34* NE ANTENNA CORRODED W K NONE O OTHER ININSP/MAINT 1 CA 1325 1325 1WGNF WHILE TROUBLESHOOTING A DEFERRAL FOR AN ADF SIGNIFICANT CORROSION AND A BROKEN PIN WAS DISCOVERED ON THE BELLY MOUNTED ADF ANTENNA CONNECTOR. THE ASSOCIATED CONNECTOR WAS ALSO CORRODED AND CONTAINED THE BROKEN PIN. IT IS ASSUMED MOISTURE FROM THE AIRCRAFT INTERIOR FOUND ITS WAY INTO THE CONNECTOR AND POOLED CAUSING THE CORROSION. THE ANTENNA SEALS AERODYNAMIC AND PRESSURE WERE IN A SERVICABLE STATE. MAINTENANCE REPLACED THE ADF ANTENNNA, CONNNECTOR PLUG AND PINS AND RETURNED THE AIRCRAFT TO SERVICE. 2L72 4F4 FRTA21EA E15NE 20060619000982006061900098CE 2006 6 19 CA060303005 120060116G2821305262401 FILTER CESSNA500 560CESSNA 2076750CE PWA 530 PW535A NE RT FUEL SYS CONTAMINATED W K NONE O OTHER ININSP/MAINT 1 CA 1148 RT ENGINE FUEL FILTER CONTAMINATED WITH LINT FROM LARGE (12" X 30") TOWEL WHICH WAS FOUND IN THE RT INTEGRAL WING TANK. THE TOWEL WAS "INSTALLED" BY CESSNA AIRCRAFT FACTORY WHEN THE AIRCRAFT WAS BUILT. THE TOWEL WAS OUTBOARD OF THE BOOST AND EJECTOR PUMPS AND DID NOT AFFECT THE OPERATION OF ENGINE OR PUMPS. 2L72 4F4 FRTA22CE E00053EN 20060619000992006061900099CE 2006 6 19 CA060303006 120060116G2710556555038CR CONTROL CABLE CESSNA500 560CESSNA 2076750CE PWA 530 PW535A NE AILERON BROKEN W K NONE O OTHER ININSP/MAINT 1 CA 1148 RT AILERON CONTROL YOKE CROSSOVER CABLE BROKEN STRANDS. THIS WAS FOUND ON PHASE 5 INSPECTION AND IS A COMMON FINDING AT 1200 HOURS OF USE. 2L72 4F4 FRTA22CE E00053EN 20060619001002006061900100CE 2006 6 19 CA060303007 120060116G2710656512037CR CONTROL CABLE CESSNA500 560CESSNA 2076750CE PWA 530 PW535A NE AILERONS BROKEN W K NONE O OTHER ININSP/MAINT 1 CA 1148 LT AILERON CONTROL YOKE CROSSOVER CABLE BROKEN STRANDS. THIS WAS FOUND AT PHASE 5 INSPECTION AND IS A COMMON FINDING AT 1200 HOURS. 2L72 4F4 FRTA22CE E00053EN 20060619001012006061900101CE 2006 6 19 CA060303008 120060116G5220651126619 SEAL CESSNA CESSNA500 560CESSNA 2076750CE PWA 530 PW535A NE ESCAPE HATCH FAILED W K NONE O OTHER ININSP/MAINT 1 CA 1148 ESCAPE HATCH SEAL MIGRATING UNDER CABIN PRESSURE TO THE EXTERIOR OF THE AIRCRAFT. DUE TO POOR BONDING TO THE HATCH STRUCTURE. REPLACED SEAL AND PRESSURIZED AIRCRAFT, SERVICEABLE. 2L72 4F4 FRTA22CE E00053EN 20060619001022006061900102CE 2006 6 19 CA060303009 120060116G32440316138 TIRE CESSNA500 560CESSNA 2076750CE PWA 530 PW535A NE NLG SEPARATED W K NONE O OTHER ININSP/MAINT 1 CA 678 NOSE WHEEL TIRE, TREAD IS STARTING TO SEPARATE FROM TIRE. 2L72 4F4 FRTA22CE E00053EN 20060619002792006061900279SW 2006 6 19 CA060303010 120060303G3240 HOSE AIRTRCAT802 AT802A 0390308SW PWA PT6 PT6A67A 52043NE HARTZLHCB5M HCB5MA3 GL BRAKE CHAFED W K NONE O OTHER ININSP/MAINT 1 CA 303 WHILE PERFORMING A GEAR SWING DURING THE ANNUAL INSPECTION, IT WAS DISCOVERED THAT THE MLG BRAKE HOSES WERE ROUTED SO THAT THEY WERE RUBBING DIRECTLY ON THE TREAD PORTION OF THE TIRES. THE STRAIGHT BULKHEAD FITTINGS P/N AN832-4D (4 OF) WERE REPLACED WITH 45 DEGREE BULKHEAD FITTINGS AND BRAKE HOSES WERE CHECKED FOR CLEARANCE ON A SUBSEQUENT GEAR SWING WITH NO RUBBING NOTED. BRAKE SYSTEM WAS BLED. THE OTHER AIRCRAFT IN THE FLEET WILL BE INSPECTED. 1L71 3T4 TNCA19SW E26NE 6 CP44GL 20060621000682006062100068CE 2006 6 21 CA060303011 120060204G21607547512 BYPASS VALVE HAMSTD 73838426 CESSNA500 560CESSNA 2076750CE PWA 530 PW535A NE ACM FAILED W O OTHER MP OVER TEMP NO WARNING INDICATION CRCRUISE 1 CA 1189 200303012 BYPASS VALVE INTERMITTENTLY STICKING IN OPEN (HOT) POSITION, UNABLE TO CONTROL CABIN AIR TEMPERATURE IN AUTO OR MANUAL SELECTION. REPLACED VALVE, GROUND CHECK OF VALVE OPERATION SATISFACTORY. 2L72 4F4 FRTA22CE E00053EN 20060621000692006062100069CE 2006 6 21 CA060303012 120060210G2916S53FC GAUGE CESSNA 651710021 CESSNA500 560CESSNA 2076750CE PWA 530 PW535A NE RESERVOIR FAILED W O OTHER O OTHER NRNOT REPORTED 1 CA 1204 BRAKE HYDRAULIC RESERVOIR UPPER AND LOWER SIGHT GAGES UNSERVICEABLE, SIGHT GAGE FLOATS ABSORBED SKYDROL BRAKE FLUID AND WOULD NOT FLOAT, MAKING IT IMPOSSIBLE FOR THE (PILOT) TO DETERMINE THE BRAKE FLUID LEVEL. 2L72 4F4 FRTA22CE E00053EN 20060621000702006062100070CE 2006 6 21 CA060303013 120060211G27520523921 ROLLER CESSNA CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA MCAULY1C160 1C160DTM GL TE FLAP MISSING W O OTHER O OTHER NRNOT REPORTED 1 CA 12 HOURS AFTER THE AIRCRAFT CAME BACK FROM A PAINT JOB, A FLIGHT INSTRUCTOR HEARD A BANG AS THEY WERE RETRACTING THE FLAPS AFTER LANDING. AFTER TAXIING BACK TO THE HANGAR, AND UPON SUBSEQUENT INSPECTION, OUR FLIGHT INSTRUCTOR REPORTED THE LT IB AFT FLAP ROLLER MISSING. 1H71 3O3 ONT3A12 E274 5 NP910 20060621000712006062100071CE 2006 6 21 CA060303014 120060131G2720 STOP FITTING CESSNA150 150F 2071814CE CONT O200 O200A 17020SO MCAULY1A100 1A100MCM GL RUDDER FAILED W O OTHER O OTHER NRNOT REPORTED 1 CA SDA AL-2000-04 CF-2000-20R2 SEB 01-1 COMPLETED, NO EVIDENCE OF JAMMING OR RUBBING ON EITHER RUDDER STOPS. 1H71 3O3 O 3A19 E252 5 NP918 20060621000752006062100075EA 2006 6 21 CA060303019 120060303G2810CL21564002 FUEL CELL CNDAIRCL215 CL2156B11215 EA PWA PW120 PW123 NE HAMSTD14SF 14SF* NE RT NR 6 LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA 1342 WHILE UNDERGOING IT'S 12 MTH INSPECTION FUEL WAS FOUND DRIPPING FROM THE RT WING TIP. ALL 8 FUEL CELLS FROM THE RT WING WERE REMOVED FOR LEAK CHECK. 6 OUT OF 8 CELLS WERE FOUND TO BE LEAKING INCLUDING THIS ONE. DEFECTIVE CELLS WILL BE REPLACED. 2H72 4T4 TRTA14EA E20NE 6 CP7NE 20060622000712006062200071EA 2006 6 22 CA060303020 120060303G2810CL215640026 FUEL CELL CNDAIRCL215 CL2156B11215 EA PWA PW120 PW123 NE RT WING LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA 1342 WHILE UNDERGOING IT'S 12 MTH INSPECTION FUEL WAS FOUND DRIPPING FROM THE RIGHT WING TIP. ALL 8 FUEL CELLS FROM THE RIGHT WING WERE REMOVED FOR LEAK CHECK. 6 OUT OF 8 CELLS WERE FOUND TO BE LEAKING INCLUDING THIS ONE. DEFECTIVE CELLS WILL BE REPLACED. 2H72 4T4 TRTA14EA E20NE 20060621001332006062100133EA 2006 6 21 CA060303021 120060303G2810CL215640024 FUEL CELL CNDAIRCL215 CL2156B11215 EA PWA PW120 PW123 NE HAMSTD14SF 14SF* NE RT NR 3 LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA 1342 (CAN) WHILE UNDERGOING 12 MONTH INSPECTION, FUEL WAS FOUND DRIPPING FROM THE RT WING TIP. ALL 8 FUEL CELLS FROM THE RT WING WERE REMOVED FOR LEAK CHECK. 6 OUT OF 8 CELLS WERE FOUND TO BE LEAKING INCLUDING THIS ONE. DEFECTIVE CELLS WILL BE REPLACED. (TC NR 20060303021) 2H72 4T4 TRTA14EA E20NE 6 CP7NE 20060621001342006062100134EA 2006 6 21 CA060303022 120060303G2810CL21564002 FUEL CELL CNDAIRCL215 CL2156B11215 EA PWA PW120 PW123 NE HAMSTD14SF 14SF* NE RT NR 2 LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA 1342 (CAN) WHILE UNDERGOING 12 MONTH INSPECTION, FUEL WAS FOUND DRIPPING FROM THE RT WING TIP. ALL 8 FUEL CELLS FROM THE RT WING WERE REMOVED FOR LEAK CHECK. 6 OUT OF 8 CELLS WERE FOUND TO BE LEAKING INCLUDING THIS ONE. DEFECTIVE CELLS WILL BE REPLACED. (TC NR 20060303022) 2H72 4T4 TRTA14EA E20NE 6 CP7NE 20060621001352006062100135EA 2006 6 21 CA060303023 120060303G2810CL215640011 FUEL CELL CNDAIRCL215 CL2156B11215 EA PWA PW120 PW123 NE HAMSTD14SF 14SF* NE RT NR 1 LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA 1342 (CAN) WHILE UNDERGOING 12 MONTH INSPECTION, FUEL WAS FOUND DRIPPING FROM THE RT WING TIP. ALL 8 FUEL CELLS FROM THE RT WING WERE REMOVED FOR LEAK CHECK. 6 OUT OF 8 CELLS WERE FOUND TO BE LEAKING INCLUDING THIS ONE. DEFECTIVE CELLS WILL BE REPLACED. (TC NR 20060303023) 2H72 4T4 TRTA14EA E20NE 6 CP7NE 20060621001392006062100139WP 2006 6 21 CA060306004 120060228G2740T40032 TRIM SWITCH ROBSINR44 R44 7640120WP LYC O540 O540F1B5 41532EA FAILED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) TRIM SWITCH INTERMITTENT. REPLACED SWITCH. (TC NR 20060306004) 1G71 3O3 O H11NM E295 20060621001402006062100140EU 2006 6 21 CA060306005 120060106G6720350A33105803 CONTROL LEVER SNIAS 350 AS350* EU TMECA ARRIELARRIEL1B 6OO30NE T/R GEARBOX WORN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) CONTROL TUBE WORN IN ATTACH POINT OF CONTROL LEVER. REPLACED LEVER. (TC NRV 20060306005) 1G71 3U3 U H9EU E19EU 20060623000342006062300034EA 2006 6 23 CA060306006 220060306G7250311532101 TURBINE BLADES PWA PT6T PT6T3 52045EA POWER SECTION DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA 148213641 (CAN) POWER SECTION WAS RECEIVED FROM THE OPERATOR FOR REPAIR DUE TO HIGH VIBRATION LEVELS. INSPECTION REVEALED THAT THE COMPRESSOR TURBINE BLADES HAD SUFFERED EXTENSIVE DAMAGE. 12 CT BLADES WERE FOUND DAMAGED TO VARYING DEGREES OF THE BLADE SURFACE MISSING. ANOTHER 12 BLADES EXHIBITED FATIGUE CRACKING EMANATING FROM THE TRAILING EDGE OF THE BLADE. (TC NR 20060306006) 4 U E22EA 20060623001602006062300160EA 2006 6 23 CA060306007 220060110G74144347 MAGNETO HUGHES269 269C1 8059504SW LYC O360 HO360C1A 41514EA ENGINE FAILED W K NONE O OTHER ININSP/MAINT 1 CA 1793 (CAN) AIRCRAFT HARD TO START AND 125 DROOP. REPLACED LT MAGNETO. (TC NR 20060306007) 1G71 3O3 OO 4H12 E286 20060623001632006062300163EA 2006 6 23 CA060306008 220060112G7322252434710 FUEL CONTROL SCWZER269 269D 8059501EA LYC O360 HIO360D1A 41514EA ENGINE MALFUNCTIONED W K NONE O OTHER ININSP/MAINT 1 CA 500 73707 (CAN) CANNOT UNJUST IDLE MIXTURE. REPLACED FUEL CONTROL. (TC NR 20060306008) 1G71 3U3 O0 4H12 1E10 20060623001692006062300169SW 2006 6 23 CA060306013 120060113G801131B21064 STARTER HUGHES269 269C1 8059504SW LYC O360 HO360C1A 41514EA ENGINE FAILED W K NONE O OTHER ININSP/MAINT 1 CA 61 (CAN) STARTER NOT OPERATING. REPLACED STARTER. (TC NR 20060306013) 1G71 3O3 OO 4H12 E286 20060623002252006062300225 2006 6 23 CA060306017 420060303G25654A40302 SLIDE EMB ERJ170ERJ170100LR EU GE CF34 CF348E5A1 30015NE L1 DOOR FAULTY W K NONE O OTHER ININSP/MAINT 1 CA 792 (CAN) IAW FLEET ENGINEEERING REQUEST VERIFY L-1, R-1, L-2 AND R-2 SLIDE FOR ANY EXTRA LACING AROUND THE SLIDE PACK OPENING PIN. CONTACT MOC FOR INSTRUCTIONS AND PHOTOS OF PROPER INSTALLATION . REPORT FINDING FOR EACH DOOR AND CORRECTIVE ACTION IF REQUIRE. L1 DOOR SLIDE ASSEMBLY REPLACED IAW AMM,NEW SLIDE ASSY INSTALLED IAW AMM. (TC NR 20060306017) 2L72 4F4 FRTA56NM E00063EN 20060623002282006062300228CE 2006 6 23 CA060306018 120060303G3710AA216CWOHE PUMP CESSNA206 U206G 2073356CE CONT O520 IO520F 17032SO HARTZLHCC3Y PHCC3YF1 GL AIR PUMP FAILED W A UNSCHED LANDING L NO TEST CRCRUISE 1 CA 144 (CAN) AIR PUMP WAS INSTALLED IN AIRCRAFT AND FAILED AFTER 144 HOURS. (TC NR 20060306018) 1H71 3O3 O A4CE E5CE 5 CP25EA 20060623002292006062300229CE 2006 6 23 CA060306019 120060304G3710AA216CWOHE PUMP CESSNA206 U206G 2073356CE CONT O520 IO520F 17032SO HARTZLHCC3Y PHCC3YF1 GL AIR PUMP FAILED W E ENGINE SHUTDOWN O OTHER TXTAXI/GRND HDL 1 CA 1 (CAN) AIR PUMP WAS INSTALLED IN AIRCRAFT AND FAILED AFTER 0.7 HOURS, FAILED DURING THE RUN UP. (TC NR 20060306019) 1H71 3O3 O A4CE E5CE 5 CP25EA 20060626000562006062600056EU 2006 6 26 CA060306020 120060304G2750MS24178D1 RELAY DORNERDO228 DO228202 2992030EU GARRTTTPE331TPE3315251K NM HARTZLHCB4T HCB4TN5 GL TE FLAPS INOPERATIVE W O OTHER F FLT CONT AFFECTED APAPPROACH 1 CA (CAN) ON APROACH FLAPS WERE SELECTED TO THE NR 2 POSITION AND DID NOT RESPOND . SYSTEM TROUBLESHOOTING FOUND THE RELAY TO BE NOT FUNCTIONING . RELAY WAS REPLACED WITH A SERVICABLE UNIT AND FLAPS TESTED NORMAL (TC NR 20060306020) 2H72 4T4 TRTA16EU E2WE 6 CP40EA 20060703000022006070300002 2006 7 3 CA060307001 420060304G34606224717004 CONTROL PANEL BOEING767 767375 1385217NM GE CF6 CF680C2B6F 30025NE COCKPIT MALFUNCTIONED W A UNSCHED LANDING F FLT CONT AFFECTED CLCLIMB 1 CA ON CLIMB-OUT YVR, NO A/T, NO CMD BARS, NO A/P L AND C. NO L NAV, (ACFT RETURNED TO YVR). REPLACED MCP PER AMM 22-11-02 PB 201. 2L72 4F4 FRTA1NM E13NE 20060626000572006062600057 2006 6 26 CA060307002 420060305G34449733033111 PROXIMITY SWITCH PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL FAULTY W O OTHER N FALSE WARNING CRCRUISE 1 CA 5497 (CAN) DURING CRUISE, THE (AIR/GROUND) LIGHT ON THE CAWS PANEL ILLUMINATED. UPON TOUCHDOWN, THE LIGHT WENT OUT. INVESTIGATION REVEALED A FAULTY LT GROUND PROXIMITY SWITCH. THE SWITCH WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. (TC NR 20060307002) 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20060626000582006062600058 2006 6 26 CA060307003 420060125G221611538011119 ACCUMULATOR BEECH BEECH 100 A100 1152915CE PWA PT6 PT6A28 EA HARTZLHCB3T HCB3TN3 GL HORIZONTAL STAB FAILED W O OTHER F FLT CONT AFFECTED CRCRUISE 1 CA (CAN) THE ABOVE P/N FAILED SENT FOR REPAIR THEN FAILED AGAIN WITH IN 5.3 HRS. SERVICEABLE ACTUATOR INSTALLED WITH NO MORE PROBLEMS. (TC NR 20060307003) 1L72 3T4 T A14CE E4EA 6 CP15EA 20060626000592006062600059NE 2006 6 26 CA060307004 220060303G7210MS949034 BOLT PWA PT6A65AR PWA PT6 PT6A65AR 52043NE GEARBOX FAILED W K NONE O OTHER ININSP/MAINT 1 CA 20 20 PCEPS97533 (CAN) THE POWER SECTION OF ENGINE S/N PCE-PS 97533 WAS REMOVED DUE TO SEIZED CONDITION. THE REASON FOR REMOVAL AS DESCRIBED BY THE OPERATOR WAS FAILURE ON START-UP. THE POWER SECTION ROTATION HUNG ON LIGHT UP, RELEASED AND HUNG UP AGAIN. START ABORTED. POWER SECTION BINDS UP DURING MANUAL ROTATION. (TC NR 20060307004) 4 T E4EA 20060626000602006062600060CE 2006 6 26 CA060307005 120060106G32301280811 MOTOR CESSNA210 210 2073402CE MLG ERRATIC W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA 721 (CAN) GEAR MOTOR CHANGED DUE TO ERATIC GEAR OPERATION. GEAR MOTOR WAS SPRAYING SOLDER. PRESSURE SWITCH ADJUSTED TO SPEC FOR GEAR OPEARTION. (TC NR 20060307005) 1H71 3O RT3A21 20060626000612006062600061GL 2006 6 26 CA060307006 120060303G2720C2CF177A MOUNT DHAV DHC2 DHC2MKI 2801830GL PWA R985 R985AN14B 52008NE HAMSTD2D 2D30 NE RUDDER PEDALS CRACKED W O OTHER F FLT CONT AFFECTED LDLANDING 1 CA (CAN) UPON LANDING, PILOT NOTICED THAT RUDDER PEDALS FELT LOOSE. HAD NO PROBLEM WITH TAXING AND ON THE WATER. AC WAS REMOVED FROM SERVICE, INSP CARRIED OUT. CABLES WERE FOUND TO BE LOOSE. BELLY PNLS WHERE REMOVED, RUDDER BAR ASSY WAS INSPECTED. IT WAS NOTICED THAT RUDDER TUBES ON LT SIDE WERE RUBBING TOGETHER. UPON FURTHER VISUAL INSP IT WAS NOTICED THAT MOUNT ASSY P/N C2CF177A WAS PULLED AWAY FROM ITS SUPPORT TUBE. WELD THAT SECURES IT TO TUBE HAD FAILED WHICH CAUSED STRESS ON OTHER SUPPORT TUBE, CAUSED MOUNT ASSY TO CRACK, COME AWAY FROM TUBE WHICH IN TURN CAUSED SLACK IN CABLES. RUDDER BAR WAS REMOVED FROM AC, PICTURES TAKEN, BAR WAS SENT FOR REPAIRS AS NO SPARE ASSY WAS AVAILABLE. (TC NR 20060307006) 1H71 3R3 RRCA806 5E1 5 CP206 20060626000622006062600062EU 2006 6 26 CA060307007 120060302G750026361090018 BLEED AIR SYS AIRBUSA319 A319112 3930323EU CFMINTCFM565CFM565B6 13802NE NR 2 INOPERATIVE W B EMER. DESCENT J WARNING INDICATION CRCRUISE 1 CA (CAN) DISPATCHED WITH BLEED NR 2 OFF IAW MEL. LT WING LEAK IN CRUISE EMERGENCY DESCENT COMPLETED. REMOVED ACCESS PANELS FOR ZONE 521 BLEED DUCT FROM THE ENG NR 1 PYLON TO THE FUSELAGE. REMOVED ACCESS DOORS TO AIR CONDITIONING UNITS (191+192). REMOVED BELLY FAIRINGS FOR ACCESS TO BLEED DUCT FWD OF THE AIR CONDITIONING UNITS. (TC NR 20060307007) 2L72 4F4 FRTA28NM E37NE 20060626000662006062600066NE 2006 6 26 CA060307008 220060306G7230 VANE AIRBUS320 A320211 3930320EU CFMINTCFM56 CFM565A1 NE 3RD STAGE VSV CHAFED W B EMER. DESCENT O OTHER CRCRUISE 1 CA (CAN) NR 1 ENG STALL, ENG 1 SHUTDOWN AND LANDED. BORESCOPE CARRIED OUT IAW AMM 72-00-00-200-003 AND 72-31-00-290-001 FOUND 3 RD STAGE VSV VANES RUBBING ON IB END MAKEING A GROOVE WITH DISPLACED METAL AT BOTH ENDS OF VANE TRAVEL. (TC NR 20060307008) 2L72 4F4 FRTA28NM E29NE 20060703000062006070300006EA 2006 7 3 CA060307009 220060306G741410357479 SHAFT BENDIX ROBSINR44 R44 7640120WP LYC O540 O540F1B5 41532EA MAGNETO WORN W K NONE O OTHER ININSP/MAINT 1 CA 790 663 L2294432E DURING A 500 HR MAG INSPECTION, FOUND SHAFT FOR THE ROTATING MAGNET WORN BEYOND LIMITS. BELIEVE SOMEONE HAD TRIED TO CHANGE THE COUPLING AND THEN COULD NOT PULL COUPLING OFF THE SHAFT. THE NUT WAS REINSTALLED, TIGHTEN AND NEW COTTER PIN INSTALLED, BUT FAILED TO TORQUE THE NUT. THIS IN TURN DID NOT LOAD THE SPACER PROPERLY WHICH THEN WORN THE SHAFT PREMATURELY. 1G71 3O3 O H11NM E295 20060626000672006062600067EA 2006 6 26 CA060307010 220060306G741410357426 DISTRIBUTOR BLK BENDIX ROBSINR44 R44 7640120WP LYC O540 O540F1B5 41532EA MAGNETO WORN W K NONE O OTHER ININSP/MAINT 1 CA 755 F189908E (CAN) DURING A 500 HR INSPECTION FOUND DISTRIBUTOR BLOCK BUSHING WORN. THIS CAUSED THE GEAR TO WOBBLE. WHEN THE GEAR WOBBLED THE ELECTRODE MADE CONTACT WITH THE BLOCK TERMINALS. THIS CAUSED THE GEAR TO STRIP AND ELECTRODE TO BREAK. BUSHING POSSIBLY DID NOT HAVE ENOUGH LUBRICATION. (TC NR20060307010) 1G71 3O3 O H11NM E295 20060626000682006062600068NE 2006 6 26 CA060307011 220060306G741410357586 DISTRIBUTOR GEARBENDIX ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE MAGNETO STRIPPED W K NONE O OTHER ININSP/MAINT 1 CA 810 L26962SE (CAN) REMOVED DUE TO ROUGH RUNNING ENGINE. ONCE THE MAGNETO WAS INSPECTED FOUND DISTRIBUTOR GEAR TEETH WERE STIPPED. DUE TO POSSIBLE BACKFIRE ON ENGINE. (TC NR 20060307011) 1G71 3O3 O H11NM 1E4 20060626000692006062600069 2006 6 26 CA060309001 420060208G22109960013 SWITCH CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE AUTOPILOT FAILED W O OTHER F FLT CONT AFFECTED CLCLIMB 1 CA (CAN) ON DEPARTURE, THE FLIGHT CREW REPORTED THEY HAD LOST THE AUTOPILOT, MACH TRIM AND THE STAB TRIM. NR 1 STAB TRIM SWITCH WAS NOTICED TO BE STICKY AND HARD TO DISENGAGE. THE CREW WAS ADVISED THAT IT WAS PROBABLY THE NR 1 (CAPT'S) DISENGAGE SW (P/N 996-0013) AT FAULT AND CAUSING BOTH CHANNELS TO DISENGAGE AND THAT THE SWITCH NEEDED TO BE REPLACED. THE CREW CONTINUED ON IN A SLIGHTLY NOSE UP ATTITUDE AND THE AUTOPILOT UNSERVICEABLE. THE AIRCRAFT LANDED WITHOUT FURTHER INCIDENT AND THE SWITCH (P/N 996-0013) HAS BEEN REPLACED (TC NR 20060309001) 2L72 4F4 FRTA21EA E15NE 20060626000702006062600070EA 2006 6 26 CA060309002 220060225G7322 FUEL CONTROL CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA MCAULY1C160 1C160DTM GL UNSERVICEABLE W A UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CLCLIMB 1 CA (CAN) ON TAKEOFF, THE STATIC RPM WAS ABOUT 2200RPM. AFTER TAKE-OFF AT AN ESTIMATED 300-400FT AGL THE ENGINE FAIRLY ABRUPTLY DROPPED IN RPM AND THE AIRCRAFT BEGAN TO DESCEND. THE ENGINE WAS RUNNING ROUGH AND SOUNDED WEAK BUT STILL RUNNING AT 2000 RPM. PILOT THOUGHT (NOT SURE)HE PULLED ON CARB HEAT AND THEN TRIED TO WORK THE THROTTLE A BIT WITH NO SATISFACTORY RESPONSE. BY THE TIME THE AIRCRAFT WAS TAXIED TO THE HANGAR THE THROTTLE RESPONSE HAD RETURNED TO NORMAL. (TC NR 20060309002) 1H71 3O3 ONT3A12 E274 5 NP910 20060626000712006062600071NE 2006 6 26 CA060309003 220060219G7250 TURBINE BLADES BOEING727 727281 138408NNM PWA JT8 JT8D17 52049NE ENGINE FAILED W ED ENGINE SHUTDOWN RETURN TO BLOCK EJ VIBRATION/BUFFET WARNING INDICATION TXTAXI/GRND HDL 1 CA 709421 (CAN) ON START UP THE CREW WAS UNABLE TO SUCCESSFULLY START THE NR 2 ENGINE. LARGE PIECES OF TURBINE BLADES WERE DISCOVERED LAYING IN THE TAILPIPE AREA. THE ENGINE WAS REPLACED AND A/C RETURNED TO SERVICE. (TC NR 20060309003) 2L73 4F4 F A3WE E2EA 20060626000722006062600072NM 2006 6 26 CA060309004 120060308G533065C32362 SKIN BOEING737 737490 1384715NM BS 871-883 CHAFED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) FUSELAGE SKIN CHAFFING BS 871 TO 883 AT STR 1-2 L REPAIRED IAW EA 5330-02065 (TC NR 20060309004). 2L72 4F RTA16WE 20060626000732006062600073CE 2006 6 26 CA060309005 120060307G55201016100197 RIVET BEECH BEECH 200 200BEECH 1152920CE PWA PT6 PT642A NE HARTZLHCE4N HCE4N3 NE TORQUE TUBE LOOSE W K NONE O OTHER ININSP/MAINT 1 CA 3143 (CAN) PHASE INSPECTION REVEALED SLIGHT MOVEMENT BETWEEN THE TORQUE TUBE AND THE ACTUATING ARM. THE ASSEMBLY IS SECURED BY 8 CHERRY LOCK RIVETS THAT WERE BEGINNING TO WORK, ALLOWING SUBTLE PLAY IN THE ASSEMBLED JOINT. TORQUE TUBE ASSEMBLY DETERMINED TO BE NON-REPAIRABLE AND WILL BE REPLACED. (TC NR 20060309005) 1L72 4T4 T A24CE E4EA 5 CP10NE 20060626000742006062600074CE 2006 6 26 CA060309007 120060308G733199103386 TRANSDUCER CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE MCAULY3AF34C3GFR34C703 GL CONNECTOR FLUCTUATES W A UNSCHED LANDING O OTHER CRCRUISE 1 CA 1037610376 (CAN) DURING CRUISE FLIGHT FUEL FLOW INDICATOR STATED FLUCUATING FROM 80 LBS - 350 LBS/HR. A/C RETURNED TO BASE AND UPON INSPECTION BY MAINT. IT WAS DISCOVERED THAT THE CANNON PLUG ATTACHED TO THE FUEL FLOW TRANSDUCER WAS DIRTY. CONNECTION WAS CLEANED, A/C GROUND RUN SERVICEABLE AND RETURNED TO SERVICE. (MFG OF THE FUEL FLOW INDICATION IS: RIGAN DATA SYSTEMS) (TC NR 20060309007) 1H71 3T3 T A37CE E4EA 5 CP60GL 20060626000752006062600075CE 2006 6 26 CA060310001 120060302G28104572 FUEL CAP LEAR 35 35LEAR 5170600CE GARRTTTFE731TFE73122B 01518WP LT LOOSE W JA DUMP FUEL UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CLCLIMB 1 CA 8331 (CAN) DURING TAKEOFF ROLL AND ATC NOTICED FUEL COMING OUT OF THE LT TIP TANK. ATC CONTACTED THE CREW ABOUT THE SITUATION. THE CREW ELECTED TO DUMP FUEL FROM THE RT TIP TANK DUE TO FUEL IMBALANCE AND LAND THE AIRCRAFT WITH NO FURTHER INCIDENT. THE FUEL CAP WAS FOUND BY AIRPORT MAINTENANCE CREW ON THE RUNWAY. MAINTENANCE EXAMINED THE FUEL CAP AND NOTICED THE LOCKING MECHANISM HAD EXCESSIVE PLAY AND THE LOCKING TAB COULD EASILY BE TRIGGERED UNLOCK. TECHNICIAN ALSO VERIFIED THE RT FUEL CAP AND NOTICED IT WAS ALSO DEFECTIVE. BOTH CAPS WERE REPLACED. (TC NR 20060310001) 2L72 4F4 F A10CE E6WE 20060626000902006062600090WP 2006 6 26 CA060310002 120060227G8011BC3151002 STARTER ROBSINR44 R44 7640120WP LYC O540 O540F1B5 41532EA ENGINE WEAK W K NONE O OTHER ININSP/MAINT 1 CA 2887 1028 (CAN) STARTER WOULD NOT TURN OVER ENGINE. TROUBLESHOOTING REVEALED A STARTER PROBLEM. STARTER WAS REPLACED, AND NO FURTHER DEFECTS WERE NOTED. (TC NR 20060310002) 1G71 3O3 O H11NM E295 20060703000072006070300007 2006 7 3 CA060310005 420060308G2562MN1300 BATTERY ACK ELT CORRODED W K NONE O OTHER ININSP/MAINT 1 CA 043775 AT ANNUAL CERTIFICATION OF ELT, THE BATTERIES REMOVED FROM CASE FOR INSPECTION. FOUND ONE BATTERY LEAKING CAUSING CORROSION ON THE BATTERY CONTACT AT BOTTOM OF CASE. BATTERY CASE AND BATTERIES REPLACED ABD UNIT TESTED SATISFACTORY. 20060703000082006070300008NE 2006 7 3 CA060310006 120060310G6321S6125203480 FLANGE SKRSKYS61 S61A 814210CNE ROTOR BRAKE FAILED W K NONE O OTHER ININSP/MAINT 1 CA ATTEMPTED TO REPLACE A PART DAMAGED BEYOND REPAIR. A PART WAS LOCATED AND ACQUIRED TO REPLACE DAMAGED UNIT. PART WAS DELIVERED TO US FOR REVIEW. SUPPLIER SUBMITTED VARIOUS CERTIFICATION DOCUMENTS TO VALIDATE PART. PART JOURNAL IS UNDERSIZE AND IN NEED OF A CHROME REPAIR PER THE MANUAL. THE ONLY DOCUMENT THAT WAS NOT SUPPLIED WAS AN 8130-03 ATTESTING THAT SIKORSKY HAD ACCEPTED THE MANUFACTURED PART AS AIRWORTHY. ATTEMPTED TO CONTACT VENDOR ABOUT NEED OF THIS DOCUMENT, AND IT IS AT THIS TIME THAT IT WAS DISCOVERED THAT PART WAS AN OVERRUN PART. TOLD VENDOR WE COULD NOT USE THE UNIT AND WOULD RETURN IT 2G72 4U H2EA 20060705000322006070500032CE 2006 7 5 CA060310007 120060309G7830LJ78352005 ISOLATION VALVE LEAR 45 45LEAR 5170805CE GARRTTTFE731TFE7312 01518WP THRUST REVERSER FAULTY W C ABORTED TAKEOFF J WARNING INDICATION TOTAKEOFF 1 CA 55 (CAN) ON TAKEOFF THE LT ENGINE INDICATION SHOWS AN AMBER (REV), WHICH MEANS THE LT THRUST REVERSER IS ARMED WHEN THE AIRCRAFT IS AIRBORNE AND/OR THE THRUST REVERSER IS ARMED WITH THE POWER LEVER ABOVE IDLE POSITION. THE CREW RETURNED. THE SYSTEM WAS TROUBLESHOT TO A DEFECTIVE PRESSURE SWITCH ON THE LT THRUST REVERSER ISOLATION VALVE. AN ISOLATION VALVE ON ORDER. (TC NR 20060310007) 2L72 4F4 FRTT00008WIE6WE 20060705000332006070500033CE 2006 7 5 CA060310008 120060308G5270 SWITCH LEAR 45 45LEAR 5170805CE GARRTTTFE731TFE7312 01518WP PAX DOOR MISRIGGED W B EMER. DESCENT N FALSE WARNING CLCLIMB 1 CA (CAN) WHILE CLIMBING THRU FL400 THE CAS MESSAGE (ENTRY DOOR) ILLUMINATED, THERE WAS NO PRESSURIZATION PROBLEM AND NO WHISTLING SOUND. THE AIRCRAFT RETURNED WHERE AN AIRCRAFT MAINTENANCE ENGINEER INSPECTED THE DOOR AND CHECKED THE DOOR WARNING SWITCHES FOR PROPER RIGGING. DOOR SWITCHES WERE S-115, AND S-117 THRU S-121 WERE RE-RIGGED. SYSTEM WAS FUNCTION CHECKED AND THE AIRCRAFT RETURNED HOME. (TC# 20060310008) 2L72 4F4 FRTT00008WIE6WE 20060705000422006070500042CE 2006 7 5 CA060313001 120060310G491070820262 SEAL LEAR 45 45LEAR 5170805CE GARRTTTFE731TFE7312 01518WP APU MISSING W K NONE O OTHER ININSP/MAINT 1 CA 956 (CAN) AFTER EXPERIENCING DC POWER DIFFICULTIES OVER SEVERAL TIMES, FURTHER INSPECTION REVEALED WATER STAINS ON TOP OF THE LT AFT POWER DISTRIBUTION PANEL (PDP). AFTER REMOVING THE PDP COVERS, WHITE POWDER ALUMINUM LIKE CORROSION WAS FOUND INSIDE THE COVERS. INTERNAL PCB HAD 2 LARGE CORROSION SPOTS OVER SEVERAL CONTACTS. FOUND DIRECTLY ON TOP OF THE LT AFT PDP WAS A MATING FLANGE FOR APU COOLING. THIS FLANGE WAS LEAKING WATER FROM RAIN AND FREQUENT AIRCRAFT WASHING. THE SEALING WAS FOUND TOO THIN ALL OVER THE FLANGE AND SEALING WAS COMPLETELY MISSING WHERE THE 4 RETAINING BOLTS WERE DUE TO FLIGHT VIBRATIONS OVER TIME. (TC NR 20060313001) 2L72 4F4 FRTT00008WIE6WE 20060705000442006070500044EA 2006 7 5 CA060313002 120060308G5514C6FSM182031 BUSHING DHAV DHC6 DHC6 2802606EA ADAPTOR MISMANUFACTURED W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA (CAN) THE RAISED BUSHING AREA OF THE ADAPTOR ARE NOT MACHINED AT THE CORRECT ANGLE. BOTH MACHINED SURFACES ARE ANGLED AFT, THIS CAUSES THE HORIZONTAL AND VERTICAL STABILZERS TO SIT OFF SET ON AN ANGLE AND NOT DOWN FLUSH. MARKING ON THE ADAPTOR ALONG WITH THE PN ARE NR 451443, W/O 0928, AUG 11/99 AND FIRST ARTICAL. PLEASE REFER TO S/B 6/454 AND 6/516 FOR MORE DETAILS. (TC NR 20060313002) 1H72 3T RTA9EA 20060705000452006070500045EU 2006 7 5 CA060313003 120060309G641010531980 BLADES BOLKMS105 BO105S 5626006EU ALLSN 250C 250C20B 03013GL TAIL ROTOR INOPERATIVE W A UNSCHED LANDING F FLT CONT AFFECTED CRCRUISE 1 CA (CAN) AFTER FLIGHT, PILOT REPORTED THAT THE T/R PEDALS WERE STIFF. PEDAL TENSION WAS CHECKED WITH THE AIRCRAFT RUNNING AND IN FLIGHT AND MEASURED AT 30 LBS TENSION. THE T/R BLADES WERE REPLACED BY SERVICEABLE UNITS AND PROBLEM DISAPPEARED, TENSION ON PEDALS RETURNED TO NORMAL AT 14 LBS. THE A/C WAS RETURNED TO SERVICE. (TC NR 20060313003) 1G72 3U3 U H3EU E4CE 20060703000092006070300009SW 2006 7 3 CA060313004 120060308G29102781032776 LINE SWRNGNSA227 SA227AC 8780603SW GARRTTTPE331TPE33111U 01514WP MCAULY4HFR344HFR34C652 NE HYD SYSTEM CHAFED W K NONE K FLUID LOSS ININSP/MAINT 1 CA HYD FLUID LEAKING FROM LEFT ENGINE COMPARTMENT. PRESSURE LINE FROM HYD PUMP TO FIREWALL FOUND CHAFED AND LEAKING. LINE WAS CHAFED ON A UNION FITTING ON THE OIL TANK IN A "OUT OF VIEW" AREA. LINE REPLACED, GEAR SWINGS CARRIED OUT, HYD RESEVOIR TOPPED UP AND AIRCRAFT RETURNED TO SERVICE. 2L72 4T4 TRTA8SW E4WE 6 C3PNE 20060703000172006070300017EU 2006 7 3 CA060313005 120060309G243523032027 STARTER GEN SNIAS 350 AS350BA 8680817EU LYC LTS101LTS101600A3 41560NE ENGINE NOISY W E ENGINE SHUTDOWN EH VIBRATION/BUFFET ELECT. POWER LOSS-50 PC NRNOT REPORTED 1 CA VIBRATION ON START TO 60 PERCENT, AND STRANGE NOISE FROM THE ENGINE, FOUND BROKEN STARTER. 1G71 3U3 UNCH9EU E5NE 20060703000262006070300026WP 2006 7 3 CA060313006 120060310G6730D2121 SERVO ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE MAIN ROTOR LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA 132 SERVO FOUND LEAKING FROM TOP AND BOTTOM OF CYLINDER BARREL. SERVO REMOVED AND REPLACED WITH A SERVICEABLE UNIT. THE ATTACHED PHOTOS SHOW THE SERVO AREAS THAT HAVE BEEN LEAKING. THE BULK OF THE OIL HAS BEEN CLEANED OFF THE SERVO, BUT IT CAN STILL BE SEEN WHERE THE LEAKS WERE COMING FROM. 1G71 3O3 O H11NM 1E4 20060703000272006070300027WP 2006 7 3 CA060313007 120060310G6730D2121 SERVO ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE ROTOR LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA 132 SERVO WAS FOUND LEAKING FROM TOP AND BOTTOM OF CYLINDER BARREL. SERVO WAS REMOVED AND REPLACED WITH A SERVICEABLE UNIT. 1G71 3O3 O H11NM 1E4 20060703000282006070300028NE 2006 7 3 CA060313008 120060307G29137665009808102 PUMP SKRSKYS76 S76A 8143006NE ALLSN 250C 250C30S 03013GL HYDRAULIC SYS FAILED W A UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 CA PUMP FAILURE. 1G72 3U3 U H1NE E1GL 20060703000292006070300029NM 2006 7 3 CA060313009 120060312G4920170101106A APU BOEING737 737522 138449FNM CFMINTCFM56 CFM563C1 13802EU APU BAY FAILED W O OTHER O OTHER TXTAXI/GRND HDL 1 CA 28094 AFTER A FLIGHT FROM A HOLIDAY RESORT, THE AIRCRAFT HAD LANDED AT HOME BASE AND WAS TAXIING TO THE GATE. AN APU START WAS ATTEMPTED BUT THE UNIT WOULD NOT START. ON INSPECTION, THE APU APPEARS TO HAVE HAD AN INTERNAL FAILURE. 2L72 4F4 FRTA16WE E21EU 20060703000302006070300030CE 2006 7 3 CA060313010 120060307G2435M230881320 BRUSHES LUCAS CESSNA441 441 2076020CE STARTER GEN BROKEN W K NONE O OTHER ININSP/MAINT 1 CA 90 90 996 SCHEDULED MX CHECK OF BRUSHES, OPERATOR FOUND 1 BRUSH HAMMERPLATE BROKEN OFF DURING INSPECTION OF BRUSHES. RETURNED UNIT TO OVERHAUL AMO FOR REPAIRS. UNIT HAS ONLY 90 HOURS TSO. AMO FOUND ALL BRUSHES CHIPPED AT T/E AND WORN FROM OSCILLATION MOTION IN BRUSH HOLDERS. ANOTHER BRUSH HAD A BROKEN HAMMERPLATE. ARMATURE COMMUTATOR HAS ONE BAR PROTRUDING ABOVE TURNED DIA BY .003" IND RUNOUT. MAX ALLOWED IS .0002". ARMATURE HAD BEEN REWOUND AT OVERHAUL, SO HAS ONLY 90 HOURS ON IT. STEEL HUB OF COMMUTATOR IS DARKENED, CONSISTENT WITH HIGH HEAT. TO REPAIR, ARMATURE WAS REPLACED WITH REWOUND ONE, AND OEM REGULAR BRUSHES INSTALLED. REMOVED ARMATURE AND BRUSHES ARE QUARANTINED. WRITER IS CONCERNED THAT HIGHER INTE1L72 3T RTA28CE 20060703000312006070300031SW 2006 7 3 CA060313011 120060202G6710212001181001 COLLECTIVE STICK BELL 212 212 1181420SW PWA PT6T PT6T3 52045EA COCKPIT BROKEN W K NONE O OTHER ININSP/MAINT 1 CA 3214 THE AME WAS MANIPULATING THE COLLECTIVE STICK TO EXPOSE GREASE FITTINGS ON THE SWASHPLATE DURING A ROUTINE SERVICING OPERATION. WHEN THE COLLECTIVE STICK WAS PULLED UP, STICK ASSY DETAIL P/N 212-001-181-001 BROKE AND SEPARATED AT THE SLOT WHERE THE NR 2 THROTTLE STOP PIN IS LOCATED, BETWEEN THE TWO THROTTLE GRIPS. 1G71 4U4 U H4SW E22EA 20060703000322006070300032EU 2006 7 3 CA060314001 120060309G5230A5247015100200 COVER AIRBUS310 A310300 3930305EU GE CF6 CF680C2* GL CARGO DOOR MISSING W K NONE O OTHER ININSP/MAINT 1 CA THE AIRCRAFT ARRIVED FROM FLIGHT WITH ONE OF THE FORWARD CARGO DOOR ACCESS PANEL LATCH COVER MISSING. DURING INVESTIGATION FOUND THE PANEL ATTACHMENT AREAS HAD ELONGATED, WHICH ALLOWED THE ATTACHMENT SCREWS TO PASS THROUGH THE ACCESS PANEL. NEW PANEL ASSY WAS INSTALLED. 2L72 4F4 FRTA35EU E23EA 20060703000332006070300033 2006 7 3 CA060314002 420060202G2350GMA340 CIRCUIT BOARD GARMIN INTL DIAMONDA20 DA20C1 2990001GL CONT O240 IO240B 17063SO AUDIO PANEL BURNED W K NONE O OTHER ININSP/MAINT 1 CA 1468 96266004 THREE GARMIN AUDIO PANELS GMA 340 HAD TO BE SENT BACK TO GARMIN FOR REPAIRS DUE TO A SHORT CIRCUIT OCCURRING WHEN PLUGGING IN HEADSETS WITH THE MASTER SWITCH ON. FIRST WAS ON JANUARY 17, 2006, LAST TWO OCCURRED ON SAME DAY FEB 2, 2006. OPERATING AIRCRAFT FOR A LITTLE MORE THAN TWO YEARS, SUSPECTED FIRST FAILURE MAY HAVE BEEN AN ISOLATED EVENT DUE TO FACT THAT REPLACEMENT OF UNIT, WITH A LOANER, FROM ATLANTIC AVIONICS, WORKED JUST FINE. DIAMOND ISSUED SB DAC1-23-01 REV 0 TITLED DA20 C1 - GMA 340 ISOLATION DIODES ISSUED 08 DECEMBER 2004. NOT PROVIDED A COPY OF BULLETIN UNTIL AFTER FAILURES. 1L71 3O3 ONTTA4CH E7SO 20060703000342006070300034NM 2006 7 3 CA060314003 120060312G5100 UNKNOWN BOEING737 737* NM PWA JT8 JT8D17A 52049NE MULTIPLE FAIL W A UNSCHED LANDING SBHAFFECT SYSTEMS SMOKE/FUMES/ODORS/SPARKS ELECT. POWER LOSS-50 PC CLCLIMB 1 CA WHILE CLIMBING THROUGH 15000 FT, THE FOLLOWING WAS ENCOUNTERED: CABIN EMERGENCY LIGHTS FLASHING. THRUST REVERSER ISOLATION VALVE OPEN ILLUMINATED. NOSE GEAR UNSAFE INDICATION (GEAR RETRACTED). DFDR ILLUMINATED. CARGO OVERHEAT/DETECTION FAULT. APU FAILED TO START WHEN SELECTED. CAPTAIN HSI COMPUTER FLAG. CSD LOW OIL PRESSURE ILLUMINATED. ON SHORT FINAL, THE MAIN GEAR GREEN LIGHTS TURNED RED. OVERHEAD MASTER CAUTION WOULD NOT EXTINGUISH. AFTER TOUCH DOWN, THE FOLLOWING WAS FURTHER EXPERIENCED, NR 1 ENGINE THRUST REVERSER WOULD NOT OPERATE. MAIN GEAR ILLUMINATED GREEN AND THEN BLACK. VERY FAINT GEAR CONFIGURATION HORN SOUNDED FOR 30 SECONDS. A FAINT ELECTRICAL SMELL WAS OBSERVED. F/O STATED THAT IT WA2L72 4F4 FRTA16WE E2EA 20060703000352006070300035CE 2006 7 3 CA060314004 120060313G329716001260 CIRCUIT BREAKER BEECH 90 F90 1152909CE PWA PT6 PT6A135 52043NE HARTZLHCB4T HCB4TN3 GL MLG BROKEN W O OTHER O OTHER APAPPROACH 1 CA LANDING GEAR FAILED TO EXTEND WHEN SELECTED. POWERPACK C/B OPEN. 1L72 4T4 T A31CE E4EA 6 CP40EA 20060703000362006070300036EU 2006 7 3 CA060315001 120060314G6300332A67145620 BRACKET SNIAS AS332 AS332L 8680809EU TMECA MAKILAMAKILA1A 60040EU M/R DEICE SYSTEMCRACKED W K NONE O OTHER ININSP/MAINT 1 CA 186 DURING A ROUTINE DAILY INSPECTION, TWO MAIN ROTOR DEICE BRACKET WERE FOUND TO HAVE CRACKS IN THE SAME AREA. THESE BRACKETS WERE REPLACED AND THE A/C RETURNED TO SERVICE. 2G72 4U4 U H4EU E12NE 20060703000442006070300044NE 2006 7 3 CA060315002 220060314G72613037223 CARBON SEAL DHAV DHC8 DHC8* NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE NR 2 ENGINE DAMAGED W A UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CRCRUISE 1 CA 291 120986 IN CRUISE, AT FL200, OBSERVED SHORT INTERMITTENT ILLUMINATION OF OIL PRESS WARN LIGHT OF NR 2 ENG. IND OF SLIGHT OIL PRESS FLUCTUATIONS OF CORRESPONDING GAUGE COUPLED WITH HIGHER OPERATING OIL TEMP ON NR 2 ENG. CREW DECIDED TO DIVERT A/C TO BASE WHERE NORM APPROACH AND LANDING. INVESTIGATION REVEALED SLIGHTLY LWR THAN NORM OIL LEVEL NR 2 ENG. OIL LEVEL ADJUSTED TO MM LEVELS AND FOLLOWING SATIS ENG GROUND RUNS A/C RETURNED TO SERVICE. FOLLOWING DAY OF OPERATION, INVESTIGATIONS WERE UNDERTAKEN TO ENSURE OIL CONSUMPTION NOT COMPROMISED AND DURING INVESTIGATIONS IT WAS REVEALED SEALING FACE OF BREATHER SYS CARBON SEAL DAMAGED WHICH COMPROMISED EFFICIENCY ON BREATHER SYSTEMS OP RESULTING IN INCREASED OIL CONSUM2H72 4T4 TRTA13NM E20NE 6 CP7NE 20060705000772006070500077EU 2006 7 5 CA060315003 120060209G5610350A25902500 WINDSHIELD UROCOPEC130 EC130B4 8680989EU TMECA ARRIELARRIEL2B NE COCKPIT CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 926 926 (CAN) DURING INSPECTION BEFORE FLIGHT THE PILOT FOUND A CRACK IN THE CENTER WINDSHIED. CRACK WAS IN THE LOWER RT CORNER AND WAS 4 INCHES LONG. CRACK WAS STOP DRILLED AND TAPED IAW ECC INSTRUCTION NR 8598. CENTER WINDOW WAS REPLACED AT ECC. (TC NR 20060315003) 1G72 3U3 U H9EU E00054EN 20060703000452006070300045EA 2006 7 3 CA060315004 120060309G2434A700AP RELAY DHAV DHC6 DHC6200 2802620EA PWA PT6 PT6A20 52043EA HARTZLHCB3T HCB3TN3 GL REVERSE CURRENT FAILED W O OTHER H ELECT. POWER LOSS-50 PC NRNOT REPORTED 1 CA 603 A/C SHUT DOWN AFTER FLT, CREW REPORTED NR 2 GENERATOR WARNING LIGHT DID NOT ILLUMINATE. A/C WAS RUN FOR TROUBLESHOOTING, DURING WHICH TIME GEN FUNCTIONED INTERMITTENTLY. WHEN ENGINES WERE SHUT DOWN, SMOKE BEGAN TO EMANATE FROM THE ELECTRICAL BAY IN THE CABIN CEILING. ALL ELECT PWR WAS REMOVED FROM AIRCRAFT AND SMOKING STOPPED. INVESTIGATION REVEALED THAT NR 2 REVERSE CURRENT RELAY HAD FAILED INTERNALLY AND WAS HEAVILY HEAT DAMAGED. LARGE ELECTRICAL LEADS ATTACHED TO IT SHOWED SIGNS OF OVERHEATING AS WELL. ALL DAMAGED WIRING WAS REPLACED, AS WELL AS THE RT REVERSE CURRENT RELAY AND THE RT VOLTAGE REGULATOR. AIRCRAFT WAS RETURNED TO SERVICE. 1H72 3T3 TRTA9EA E4EA 6 CP15EA 20060703000462006070300046 2006 7 3 CA060315005 420060312G2330RDAV2133 MONITOR BOEING757 757236 1384971NM RROYCERB211 RB211535E43754555NE COCKPIT ODOR W H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 1 CA 227 ELECTRICAL BURNING SMELL FROM MONITOR. MONITOR SWITCHED 'OFF'. SMELL DISSIPATED. MONITOR ELECTRICALLY DISCONNECTED. 2L72 4F4 FRTA2NM E12EU 20060703000472006070300047CE 2006 7 3 CA060315006 120060314G28231183890051 SHUTOFF VALVE BEECH 1900 1900C 1154161CE PWA PT6 PT6A65B 52043EA HARTZLHCB4M HCB4MP3 GL FUEL SYSTEM UNKNOWN W K NONE J WARNING INDICATION ININSP/MAINT 1 CA DURING PRE FLIGHT INSPECTION, FUEL PRESSURE ANNUNCIATOR EXTINGUISHED WHILE THE FIRE WALL SHUTOFF VALVE T HANDLE WAS PULLED. THIS INDICATED THAT THE VALVE WAS STILL OPEN. DURING THE MX T/S IT WAS FOUND THAT VALVE POSITION INDICATOR ARM WAS CONTACTING THE FUEL FILTER BRACKET AND PREVENTING THE VALVE FROM CLOSING. REWORK OF THE BRACKET GAVE ENOUGH CLEARANCE FOR THE VALVE TO OPERATE NORMALLY. THE RIGHT HAND SIDE WAS CHECKED AND THE VALVE WAS FROM A DIFFERENT MANUFACTURER AND HAD A MUCH SMALLER INDICATOR ARM. THIS WOULD NOT INTERFERE WITH THE BRACKET. THE MANUFACTURES PART NUMBERS ARE: LEFT - ZMV13 (CIRCLE SEAL CONTROLS) RIGHT - AV24B1351BR. 2L72 4T4 TRTA24CE E4EA 6 CP56GL 20060703000482006070300048SW 2006 7 3 CA060315007 120060302G5347204072921009 YOKE BELL 205 205A1 1181414SW LYC T53 T5313B 41549NE CARGO TRACK CRACKED W K NONE O OTHER ININSP/MAINT 1 CA CRACKS ORIGINATING IN ATTACHMENT BOLT HOLES. 1G71 4U4 U H1SW E17EA 20060703000952006070300095CE 2006 7 3 CA060316001 120060309G7160BAS2452502 CLAMP RAYTHNDH125 HAWKER800XP 7150012CE GARRTTTFE731TFE7315BR WP RT INTAKE FAILED W K NONE O OTHER ININSP/MAINT 1 CA 2743 DURING INSPECTION, RT ENGINE COWLING WAS OPENED AND TECHNICIAN FOUND PARTS OF RUBBER HOSE INSIDE COWLING. FURTHER INVESTIGATION LEAD TO OPENING OF THE RT LOWER ACCESS PANEL WHERE THE CLAMP FOR THE RT LOW PRESSURE BLEED AIR TO THE MIXING VALVE DUCT WAS FOUND BROKEN AND PARTS OF THE RUBBER DUCT. CLAMPS WERE FOUND NOT LOCKWIRED. IT IS FELT THAT THE CLAMP FAILED LEADING TO THE FAILURE OF THE DUCT ASSEMBLY. THE CREW HAD NO INDICATION OF DUCT FAILURE. DUCT ASSEMBLY AND BOTH CLAMPS WERE REPLACED AND THE LT LOW PRESSURE DUCT TO MIXING VALVE WAS INSPECTED AND FOUND TO BE LOCKWIRED AND SECURED. 2L72 4F4 FRTA3EU E6WE 20060705000922006070500092CE 2006 7 5 CA060316002 120060227G2421 TERMINAL CESSNA182 R182 2072734CE LYC O540 O540J3C5 41532EA MCAULY3D32C B3D32C407 GL ALTERNATOR BROKEN W K NONE H ELECT. POWER LOSS-50 PC TXTAXI/GRND HDL 1 CA PILOT REPORTED TOTAL LOSS OF ELECTRICAL POWER. FOUND A BROKEN TERMINAL ON ALTERNATOR OUTPUT WIRE. DURING THE GROUND RUN, FOLLOWING REPAIR, ENGINE STARTED NORMALLY FROM THE BATTERY WITHOUT CHARGING FIRST, AND CHARGING SYSTEM FUNCTIONED NORMALLY. 1H71 3O3 ORT3A13 E295 5 CEXPP5C 20060705000952006070500095GL 2006 7 5 CA060316003 220060314G73146896822 PUMP BELL 206 206L3 1182108SW ALLSN 250C 250C30P 03013GL ENGINE LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA 2435 AFTER COMPLETION OF 300 HR ENGINE INSPECTION ENGINE WAS BEING GND RUN AND LEAK CHECKED. FUEL WAS NOTICED IN ENGINE COMPARTMENT AFTER INVESTIGATING DRAIN LINE WAS REMOVED FROM OVERBOARD DRAIN FOR FUEL PUMP AND EXCESSIVE LEAK WAS DETECTED. PUMP REMOVED AND REPLACED WITH SERVICEABLE UNIT. 1G71 3U3 U H2SW E1GL 20060705000982006070500098CE 2006 7 5 CA060316004 120060306G572012212055 FITTING CESSNA207 T207A 2073614CE CONT O520 TSIO520M 17040SO LT WING GOUGED W K NONE O OTHER ININSP/MAINT 1 CA 13764 DURING WING REMOVAL FOR PAINT, LT LOWER WING STRUT FITTING WAS FOUND TO HAVE A GOUGE OF APPROXIMATELY 1/8" FROM STRUT FAIRING SCREW. 1H71 3O3 O A16CE E8CE 20060705001042006070500104NM 2006 7 5 CA060316005 120060302G246050086003 CIRCUIT BREAKER BOEING727 727223 1384074NM PWA JT8 JT8D17 52049NE ELECTRICAL SYS FAILED W A UNSCHED LANDING GJ MULTIPLE FAILURE WARNING INDICATION CLCLIMB 1 CA CREW REPORTED ON DEPARTURE/CLIMB-OUT, ALL FUEL TANK NR 1 AND NR 2 BOOST PUMP CB'S POPPED. EXTENSIVE VISUAL INSPECTION OF PUMPS, WIRING CONNECTORS, ELECTRICAL HARNESSES AND SPLICES CARRIED OUT. THE FOLLOWING COMPONENTS REPLACED: NR 2 GENERATOR HARNESS FROM FIRE WALL DISCONNECT TO GENERATOR REPLACED DUE TO HIGH RESISTANCE. NR 1 GENERATOR CB (GCB) REPLACED DUE TO 47V DROP ACROSS T2-L2. NR 2 GENERATOR CN (GCB) REPLACED, SUSPECT FAULT. NR 1 GENERATOR CONTROL PANEL PRECAUTIONARY REPLACEMENT. ALL CB'S RESET, SYSTEM FUNCTION TESTED SERVICEABLE. NO FURTHER REPORTS. THIS AIRCRAFT WAS IN STORAGE FOR PREVIOUS 18 MONTHS PRIOR TO RE-ENTERING SERVICE. THE DEFECTS APPEAR TO BE RELATED TO THIS STORAGE PERIOD. 2L73 4F4 F A3WE E2EA 20060705001052006070500105NM 2006 7 5 CA060316006 120060221G282291248075 RELAY BOEING727 727223 1384074NM PWA JT8 JT8D17 52049NE FUEL SYSTEM FAILED W A UNSCHED LANDING GJ MULTIPLE FAILURE WARNING INDICATION CLCLIMB 1 CA ALL 4 FUEL BOOST PUMP CIRCUIT BREAKERS POPPED IN FUEL TANK NR 2. RECTIFICATION: 1 RELAY 109 ESS NR 2 BUS REPLACED. MAINTENANCE DETERMINED L1 AND L2 TERMINALS SHORTED TOGETHER CAUSING INTERNAL DAMAGE. LEFT AFT BOOST PUMP RELAY REPLACED. 2L73 4F4 F A3WE E2EA 20060705001062006070500106SW 2006 7 5 CA060316007 120060314G29107U7467 MANIFOLD BELL 206 206B 1181511SW ALLSN 250C 250C20B 03013GL HYDRAULIC SYS MALFUNCTIONED W O OTHER F FLT CONT AFFECTED LDLANDING 1 CA 12155 DURING PILOT TRAINING AIRCRAFT COMPLETED A HYDRAULICS OFF LANDING. HYDRAULIC SWITCH WAS THEN TURNED BACK ON AND THE FORE AND AFT MOVEMENTS CAME BACK HOWEVER THE LATERAL MOVEMENTS DID NOT COME BACK TO NORMAL HYDRAULIC ON. AIRCRAFT WAS THEN SHUT DOWN AND HYDRAULIC SOLENOID/MANIFOLD WAS CHANGED. SUSPECT OBSTRUCTION IN THE LATERAL SECTIONS OF THE MANIFOLD. AIRCRAFT HAS SINCE RETURNED TO SERVICE AFTER ASSEMBLY WAS CHANGED. DELAY IN REPORTING WSDR WAS DUE TO THE SYSTEM NOT GIVING ME FULL ACCESS TILL THE NEXT DAY. 1G71 3U3 U H2SW E4CE 20060705001072006070500107EA 2006 7 5 CA060316008 320060315G6111W69EK763 BLADE DIAMONDA20 DA20C1 2990001GL SNSNCHW69EK W69EK63 EA PROPELLER CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 20 20 CRACK FOUND ON TRAILING EDGE OF PROPELLER TIP. 1L71 3O NTTA4CH 5 NTA4CH 20060705001082006070500108SO 2006 7 5 CA060316009 220060301G8530 EXHAUST VALVE CESSNA150 150H 2071818CE CONT O200 O200A 17020SO MCAULY1A101 1A101DCM GL ENGINE STICKS W A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CLCLIMB 1 CA 1271 1271 EXHAUST VALVE STICKY. 1H71 3O3 O 3A19 E252 5 NP918 20060705001092006070500109SO 2006 7 5 CA060316010 120060316G8011 GEAR PIPER PA28 PA28140 7102802SO LYC O320 O320E3D 41508EA SNSNCH74D 74DM EA STARTER BENDIX CRACKED W O OTHER O OTHER NRNOT REPORTED 1 CA 1027 THE STARTER BENDIX GEAR WAS BROKEN IN 3 THREE PLACES. THE STARTER HOLD DOWN BOLTS WERE EITHER BROKEN OR STRETCHED. SINCE THE STARTER AND ALT HAVE A SUPPORTING BRACE BETWEEN THEM, VERY STRONGLY SUSPECT THAT THE STARTER WAS ENGAGED WHILE THE ENGINE WAS RUNNING. THE STARTER SW WAS CHECKED FOR DEFECTS BUT NONE FOUND. 1L71 3O3 O 2A13 E274 5 NP88614 20060705001102006070500110WP 2006 7 5 CA060316011 120060219G801172566 RING GEAR ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE STARTER CHIPPED W K NONE O OTHER ININSP/MAINT 1 CA 664 TEETH FOUND MISSING DURING INSPECTION. SERVICEABLE SUPPORT ASSEMBLY INSTALLED. SUSPECT PROBLEM WITH THE STARTER/RING GEAR ENGAGEMENT. A CHIPPED TOOTH WAS ALSO FOUND ON THE STARTER. STARTER P/N BC315-100-4 WAS ALSO REPLACED AT THE SAME TIME. 1G71 3O3 O H11NM 1E4 20060705000842006070500084CE 2006 7 5 CA060317001 120060314G323399810057652 ACTUATOR BEECH BEECH 99 99 1154002CE PWA PT6 PT6A20 52043EA HARTZLHCB3T HCB3TN3 GL MLG FAILED W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA 890273 (CAN) ON DEPARTURE, A LOUD BANG WAS HEARD AFTER GEAR WAS SELECTED UP, LANDING GEAR (IN TRANSIT) LIGHT REMAINED ON. GEAR WAS CYCLED, NO FURTHER NOISES WERE HEARD, (IN TRANSIT) LIGHT REMAINED ON. PASSENGER SEATED IN REAR ADVISED PILOT, RT MLG WAS NOT RETRACTING. PILOT SELECTED GEARDOWN AND OBSERVED THAT ALL 3 GREEN, GEAR DOWN AND LOCKED LIGHTS WERE ILLUMINATED. AC WAS FLOWN WITH GEAR DOWN AND LANDED WITHOUT INCIDENT. AC WAS JACKED UP, A GEAR SWING CARRIED OUT, NOTED THAT DRIVE TO RT MLG ACTUATOR WAS ROTATING, ACTUATOR WOULD NOT EXTEND OR RETRACT, REPLACED, AC RETURNED TO SERVICE. WHEN ACTUATOR WAS TESTED DRIVE WAS ROTATED AND THERE WAS SLIGHT RESISTANCE FELT, PINION DID NOT ENGAGE SCREW HSG. 1L72 3T3 T A14CE E4EA 6 CP15EA 20060913002882006091300288CE 2006 9 13 CA060317002 120060310G33972B1PECC532000 CONNECTOR LEAR 35 36A 5170603CE GARRTTTFE731TFE7312 01518WP GLARESHIELD SHORTED W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 1 CA 15303 (CAN) AIRCRAFT DEPARTED APPROXIMATELY 30 MINUTES AFTER DEPARTURE SMOKE WAS NOTED UNDER GLARESHIELD AND EMERGENCY LANDING EXECUTED. MAINTENANCE PERSONNEL FOUND SOURCE OF SMOKE TO BE GLARESHIELD FLOODLIGHT. MAINTENANCE DE-ACTIVATED FLOODLIGHTING BY PULLING/COLLARING CIRCUIT BREAKER AND DEFERRING FLOODLIGHT IAW MEL. AIRCRAFT RETURNED TO HOME. FURTHER TROUBLESHOOTING REVEALED COAX CONNECTOR/COAX WAS SHORTED WHERE IT ATTACHES TO GLARESHIELD FLORESCENT LAMP ASSEMBLY. (TC NR 20060317002) 2L72 4F4 F A10CE E6WE 20060705000932006070500093 2006 7 5 CA060317003 120060317G3210CRS8517319 BUSHING MLG CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) 16 NEW BUSHINGS RECEIVED, P/N CRS85-173-19 ALL FAILED NDT REQUIREMENT PRIOR TO INSTALL DUE TO CRACK IN THE BORE AREA. (TC NR 20060317003) 20060705000942006070500094GL 2006 7 5 CA060317004 120060316G3246C2UT473 TORQUE TUBE DHAV DHC2 DHC2MKI 2801830GL PWA R985 R985AN14B 52008NE HARTZLHCB3R HCB3R304 GL WATER RUDDER FAILED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) WHILE TAXING FLOAT EQUIPED AIRCRAFT, PILOT HAD COMPLETE FAILURE OF WATER RUDDER STEERING SYSTEM. UPON INSPECTION IT WAS FOUND THAT THE TORQUE TUBE HAD CRACKED, SPLITTING INTO TWO PIECES. FURTHER VISUAL INSPECTION FOUND THAT THE TORQUE TUBE WAS SEVERLY CORRODED INSIDE. THIS CORROSION WAS MOST LIKELY CAUSED FROM WATER COLLECTING INSIDE THE TUBE DUE TO LACK OF DRAINAGE BECAUSE OF THE TILLER BAR WHICH IS ATTACHED HORIZONTALLY AT THE BASE OF THE VERTICAL TORQUE TUBE. (TC NR 20060317004) 1H71 3R3 RRCA806 5E1 5 CP28EA 20060626000222006062600022SW 2006 6 26 CA060317007 120060213G5520214001920101 HORN BELL BELL 214 214B1 1182105SW ELEVATOR CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 1468 RE225 CRACK FOUND ON ELEVATOR HORN ASSY ON REGULAR INSPECTION. REMOVED FROM SERVICE AND REPLACED WITH NEW ASSEMBLY. PART HAS A RETIREMENT LIFE OF 2500 HOURS. 2G71 4U H6SW 20060626000232006062600023EA 2006 6 26 CA060317008 220060315G73143034794 PUMP BEECH 90 C90A 1152911CE PWA PT6 PT6A21 52043EA HARTZLHCB3T HCB3TN3 GL FUEL SYS LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA 1037 VISUAL INSPECTION CARRIED OUT IAW SERVICEABILITY CHECK. PRE-DISPATCH CHECK NOTICED FUEL UNDER THE RT ENGINE. INSPECT FUEL FILTER AND DRAINS WITH THE BOOST PUMP ON AND NO LEAKAGE WAS FOUND. REMOVED FUEL PUMP DRAIN HOSE AND A LARGE AMOUNT OF FUEL WAS EXPELLED FROM THE FUEL PUMP DRAIN. THE FUEL PUMP/FUEL CONTROL ASSEMBLY WAS REMOVED FROM SERVICE DUE TO SUSPECTED INTERNAL BEARING WASHOUT DUE TO SEAL FAILURE. 1L72 3T4 TRT3A20 E4EA 6 CP15EA 20060626000242006062600024CE 2006 6 26 CA060317009 120060317G2435 BEARING LEARSIEGLER BEECH 90 C90A 1152911CE PWA PT6 PT6A21 52043EA HARTZLHCB3T HCB3TN3 GL STARTER GEN FAILED W K NONE O OTHER ININSP/MAINT 1 CA 493 16110 VISUAL INSPECTION CARRIED OUT IAW OPERATION FOUR. NOTICED METAL DUST ON BACK OF THE ACCESSORY GEARBOX AND FOUND IT TO BE MAGNETIC. REMOVED STARTER GENERATOR AND FOUND THE QUILL SHAFT BEARING HAD FAILED. UNIT WAS REMOVED FROM SERVICE. 1L72 3T4 TRT3A20 E4EA 6 CP15EA 20060626000252006062600025CE 2006 6 26 CA060317010 120060311G323350820285 ACTUATOR BEECH BEECH 200 B200 1152922CE PWA PT6 PT6A64 EA NLG SEIZED W O OTHER J WARNING INDICATION CLCLIMB 1 CA 1912 NOSE LANDING GEAR ACTUATOR SEIZED AND OVER-LOADED MLG MOTOR BREAKER. 1L72 4T4 T A24CE E4EA 20060626000342006062600034CE 2006 6 26 CA060317011 120060314G2910 HYDRAULIC SYSTEM BEECH 200 200CBEECH 1152926CE PWA PT6 PT6A41 52043EA HARTZLHCD4N3HCD4N3A GL LEAKING W K NONE KS FLUID LOSS AFFECT SYSTEMS ININSP/MAINT 1 CA 14914 ON INVESTIGATING A HYDRAULIC LEAK IN THE NR 1 GEAR WELL AREA, CRACKS WERE NOTED IN THE CHANNELS P/N 101-120025-57 AND P/N 101-120025-55 AS WELL AS THE ANGLE'S P/N 101-120025-67 AND 101-120025-68. THE A/C HAD A HYDRAULIC GEAR INSTALLED IN 1988 (REPLACING THE MECHANICAL GEAR ACTUATORS), AND AT THAT TIME HAD 2403.9 HOURS ON THE AIRFRAME. THE NR 2 GEAR WELL WAS INSPECTED FOR SIMILAR DAMAGE AND NONE WAS NOTED. THE AFFECTED PARTS WERE REPLACED GEAR SWINGS ACCOMPLISHED AND THE A/C RETURNED TO SERVICE. 1L72 4T4 T A24CE E4EA 5 CSTC 20060705000972006070500097EU 2006 7 5 CA060317012 120060311G2797 WIRE PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL TE FLAPS FAILED W O OTHER F FLT CONT AFFECTED LDLANDING 1 CA 11782 (CAN) FLAPS FAILED TO EXTEND ON LANDING. FLAPS WORKED INTERMITTENTLY IN THE HANGER. VARIOUS FAULTS CODES WERE NOTED BUT THEY WERE NOT CONSISTENT AFTER RESETTING THE SYSTEM. UPON FURTHER INVESTIGATION IT WAS NOTED THAT THE WIRES TO THE P029 PLUG TO THE FCWU HAD FAILED INSULATION ABOUT A INCH BACK FROM THE PLUG UNDERNEATH THE FIRST CLAMP. DAMAGED SECTION OF THE WIRING WAS REMOVED AND THE PLUG REPLACED. FLAPS WERE RESET ETC. AND OP'S CHECKED NORMAL. THIS PLUG AND WIRING WERE INSTALLED AS PART OF SB 27008 WHICH WAS INCORPORATED ON THE A/C AT 26 AFTT AND 12 TC. (TC NR 20060317012) 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20060705000992006070500099EA 2006 7 5 CA060318001 120060315G4950WE38007703 APU CNDAIRCL600 CL6002C10 1390015EA ODOR W C ABORTED TAKEOFF B SMOKE/FUMES/ODORS/SPARKS TOTAKEOFF 1 CA 3891 (CAN) CREW REPORTED SMOKE AFT LAV WARNING MSG ABORTED T/O AND EVACUATED PAX THROUGH MAIN DOOR ON RUNWAY. REPORTED SMELL ONLY, NO VISIBLE SMOKE. SOURCE OF SMOKE SMELL BELIEVED TO BE APU BLEEDS. APU WAS REPLACED IAW AMM. (TC NR 20060318001) 2L72 4F RTA21EA 20060705001002006070500100EA 2006 7 5 CA060318002 120060312G3234601R7520617 SELECTOR VALVE CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE NLG FAILED W O OTHER J WARNING INDICATION APAPPROACH 1 CA 2507 (CAN) A GEAR DISAGREE MESSAGE ON EICAS ALONG WITH MASTER WARNING AFTER GEAR DOWN SELECTION. ON INVESTIGATION, IT WAS NOTED NLG DID NOT SHOW DOWN AND LOCKED. DOING A FLY BY, CONTROL TOWER WAS ABLE TO VERIFY THE NLG WAS NOT DOWN. CREW PROCEEDED WITH QRH PROCEDURES AND ACTIVATED MANUAL RELEASE HANDLE WITHOUT OBTAINING THE DESIRED RESULT. THE MLG HANDLE WAS THEN CYCLED AND ONLY THEN DID THE GEAR INDICATE DOWN AND LOCKED. AN EMERGENCY WAS DECLARED. THE AIRCRAFT LANDED WITHOUT FURTHER EVENT. MAINTENANCE REPLACED THE NLG SELECTOR VALVE AND UPLOCK ACTUATOR. ALL SUBSEQUENT CHECKS IAW AMM. AIRCRAFT WAS RELEASED BACK TO SERVICE. NLG UPLOCK ACTUATOR P/N 1660-103, S/N NGL10329/99 TSN 15283.42 (TC NR20060318002) 2L72 4F4 FRTA21EA E15NE 20060705001012006070500101EA 2006 7 5 CA060319001 120060319G5610 WINDSHIELD CNDAIRCL600 CL6002B19 1900309EA COCKPIT FAILED W A UNSCHED LANDING BA SMOKE/FUMES/ODORS/SPARKS FLAME/FIRE CLCLIMB 1 CA (CAN) APROX 19 MIN AFTER TAKEOFF, AIRCRAFT REPORTED SMOKE, SPARKS AND FIRE IN THE COCKPIT, COMING FROM THE PILOTS WINDSHIELD. WINDSHIELD HEAT WAS IMMEDIATELY SWITCHED OFF AND FIRE/SPARKS EXTINGUISHED. AIRCRAFT RETURNED TO BLOCKS. INITIAL VERBAL REPORT FROM MAINTENANCE CONTROL INDICATES THAT THE PILOT WINDSHIELD HEAT TERMINAL BLOCK IS BURNED, THERE IS SOME SOOT ON THE COCKPIT CELING PANEL AND A SMALL PORTION(TC NR 20060319001) 2L72 4F RTA21EA 20060627000022006062700002GL 2006 6 27 CA060320001 320060316G6110311466001 SEAL BEECH 90 C90A 1152911CE PWA PT6 PT6A21 52043EA HARTZLHCB3T HCB3TN3 GL PROPELLER DAMAGED W E ENGINE SHUTDOWN KJ FLUID LOSS WARNING INDICATION CRCRUISE 1 CA 1 PCE25397 IN CRUISE 16,000 FT, NOTICED OIL LEAK ON TOP RT FWD ENG COWL. LEAK PROGRESSIVELY GOT WORSE, PILOTS ELECTED TO RETURN TO BASE. EVEN THOUGH ENG OIL TEMP AND PRESS NORM, PILOTS SHUTDOWN RT ENG. CREW DECLARED EMERG. BECAUSE QTY OF OIL LOST, PROP SHAFT SEAL SHOULD BE LOOKED AT. RT PROP SEAL HAD BEEN REPLACED 2 DAYS EARLIER DUE TO OIL LEAKAGE IN NOSE CASE AREA. MX FOUND FAULTY PROP SEAL WAS WRONG P/N. BY TIME OF DISCOVERY OUR P & W FSR WAS ON SITE, WENT BACK TO OUR STORES AND PULLED THE REMAINING SEAL IN STOCK STAMPED 3114661-01, AND IT TO WAS WRONG PART INSIDE, (3114660-01). WITNESSED BY FSR. SEALS CAME FROM CPWA, PACKAGED ON 02/2000. BECAUSE OF LOSS OF OIL/AIR PRESSURE IN THE RGB, OIL WAS ALLOWED TO MIGRATE 1L72 3T4 TRT3A20 E4EA 6 CP15EA 20060913002892006091300289CE 2006 9 13 CA060320002 120060315G27506627503000019 TRANSDUCER LEAR 45 45LEAR 5170805CE GARRTTTFE731TFE7312 01518WP TE FLAP CONTROL MALFUNCTIONED W O OTHER O OTHER CRCRUISE 1 CA 68 (CAN) ON THE FLIGHT WITH A SCHEDULED REFUELING STOP. WHILE IN CRUISE APPROXIMATIVELY 1.5 HOURS AFTER DEPARTURE, THE AMBER CAS MESSAGE (FLAP FAIL) ILLUMINATED. THE CREW WAS UNABLE TO RESET THE SYSTEM AND MADE A FLAP LESS LANDING, INSTEAD OF WHERE AUTHORIZED SERVICE FACILITY WAS ABLE TO CONNECT THE DIAGNOSTIC COMPUTER TO THE AIRCRAFT. THE FAULT HAD ALREADY RESET ITSELF AND THE GROUND CREW WAS UNABLE TO DUPLICATE THE PROBLEM. THE AIRCRAFT WAS RETURNED TO SERVICE. ON THE FLIGHT THE AMBER CAS MESSAGE (FLAP FAIL) ILLUMINATED AND THE AIRCRAFT MADE A FLAPLESS LANDING. A TEAM OF TECHNICIANS FROM SERVICE CENTER WAS DISPATCHED TO THE AIRCRAFT WHERE TROUBLESHOOTING WAS PERFORMED. THE TECHNICIANS WERE UNABLE TO DUPLICATE TH2L72 4F4 FRTT00008WIE6WE 20060623000172006062300017CE 2006 6 23 CA060320003 120060309G55201156100153 SUPPORT BRACKET BEECH BEECH 100 A100 1152915CE PWA PT6 PT6A28 EA HARTZLHCD4N3HCD4N3A GL CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) CRACK FOUND ON IB SUPPORT BRACKET WHILE CARRYING OUT REPETITVE INSPECTION MSB 2145. TORQUE TUBE REPLACED WITH NEW. (TC NR 20060320003) 1L72 3T4 T A14CE E4EA 5 CSTC 20060623000182006062300018WP 2006 6 23 CA060320004 120060320G1100369A81433 DATA PLATE HUGHES369 369D 4470706WP ALLSN 250C 250C20B 03013GL FUEL TANK LOOSE W K NONE O OTHER ININSP/MAINT 1 CA (CAN) GLUE ON DATA TAG DETERIORATED DUE TO CONTACT WITH FUEL AND WAS LOCATED AT BOTTOM OF FUEL TANK (TC NR 20060320004) 1G71 3U3 U H3WE E4CE 20060705001022006070500102NM 2006 7 5 CA060320005 120060320G3231CL12068161 SOCKET BOMBDRDHC8 DHC8402 1390042NM MLG DOOR BROKEN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING C-CHECK, FUNCTIONAL CHECK ON TASK CARD 3230/15 (OPERATIONAL CHECK OF LANDING GEAR DOOR SEQUENCE CONTROL CIRCUIT) DOES NOT WORK. AFTER INVESTIGATION, RELAY (3260-K9) SOCKET FOUND BROKEN AND PINS OLDER SOCKET UNGLUED. WIRE WERE FOUND HANGING LOOSE WITH A HI RISK OF CONTACT WITH STRUCTURE. POSSIBILITY OF (WOW) CIRCUIT FAILURE AND THE MOST IMPORTANT, IMPOSSIBILITY OF GEARS EXTENSION IN ALTERNATED RELEASE IN CASE OF EMERGENCY EXTENSION. (TC NR 20060320005) 2H72 4T RTA13NM 20060705001032006070500103 2006 7 5 CA060320006 220060310G732121195761011 ECU BOMBDRBD700 BD7001A10 1390006GL ENGINE INOPERATIVE W O OTHER RY PARTIAL RPM/PWR LOSS ENGINE STOPPAGE CLCLIMB 1 CA (CAN) THE PROBLEM OCCURED ON THE 11/03/2006. DUE TO INTERNET CAPACITY TO DISPLAY THE RIGHT DATE, THE DATE OF MARCH 10 WAS WRITTEN IN THE (OCCURENCE DATE) ABOVE DUE TO INTERNET INCAPACITY TO DISPLAY CERTAIN DATE. FLIGHT CREW NOTICED A LT ENGINE ROLL BACK AT CLIMB. PROBLEM OCCURED TWICE BEFORE ENGINE FLAMED OUT. ENGINE AUTO RESTARTED. WAS FINE FOR THE REST OF THE FLIGHT. AMBER FADEC FAIL CAS POSTED. AFTER LANDING LT T/R WOULD NOT STOW. 3-13-06 REPLACED LT ENGINE FADEC ECU A AND RT ENGINE FADEC ECU B REMOVED AS A PRECAUTIONARY MEASURE. GROUND RUNS OPS CHECKS GOOD. 2L72 4F RTT00003NY 20060705001222006070500122EA 2006 7 5 CA060320008 120060315G5610NP1393225 WINDOW CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE COCKPIT CRACKED W A UNSCHED LANDING O OTHER CRCRUISE 1 CA (CAN) EN ROUTE DISCOVERED 2 CRACKS IN LT SIDE WINDOW, DIVERTED. LT SIDE WINDOW REPLACED AND TESTED IAW AMM PROCEDURE. AIRCRAFT RETURNED TO SERVICE. (TC NR 20060320008) 2L72 4F4 FRTA21EA E15NE 20060711001202006071100120EU 2006 7 11 CA060321001 220060316G7310 FUEL FILTER BRAERO748 HS7482A 4231001EU RROYCEDART DART5342 EU ROTOL R4304 R2124304 EU ENGINE FAILED W C ABORTED TAKEOFF J WARNING INDICATION TOTAKEOFF 1 CA (CAN) DEPARTING, THE CREW OBSERVED A FUEL FILTER INDICATION ON NR 2 ENGINE. THE TAKEOFF WAS REJECTED AND THE AIRCRAFT RETURNED TO THE COMPANY RAMP. MAINTENANCE REPLACED THE FILTER AND AFTER SATISFACTORY GROUND RUN THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20060321001) 2L72 3T4 T A24EU A196 6 CP899 20060705002002006070500200NM 2006 7 5 CA060321002 120060317G3240214747 BRAKE BOEING737 737522 138449FNM CFMINTCFM56 CFM563C 13802EU FAILED W O OTHER O OTHER LDLANDING 1 CA (CAN) UPON LANDING ( MONCTON ) WITH THE ANTI-SKID SYSTEM OPERATING UNDER MEL 32-2 (ANTI-SKID SYSTEM INOP), THE AC LANDED ON A BARE RUNWAY AND BLEW 3 MAIN WHEEL TIRES AND BADLY SCUFFED THE FOURTH. ALL FOUR MAIN TIRES REPLACED. AIRCRAFT FERRIED. UPON FURTHER INVESTIGATION,THE NOSE GEAR SAFETY SENSOR AND E11 CIRCUIT CARD WERE REPLACED. FURTHER INVESTIGATION ON-GOING. TIMES: 37418:14 CYCLES: 22960 (TC NR 20060321002) 2L72 4F4 FRTA16WE E21EU 20060705002012006070500201NM 2006 7 5 CA060321003 120060321G52436556235159 DOOR BOEING727 727247 138408FNM HYD BAY MISSING W O OTHER D INFLIGHT SEPARATION CLCLIMB 1 CA 68406 (CAN) AIRCRAFT WAS LEAVING ON-ROUTE. SHORTLY AFTER TAKEOFF AT APPROX. 12000 FT. THE CREW NOTICED A VIBRATION. ALL INDICATIONS WERE NORMAL AND THE AIRCRAFT CONTINUED. AFTER TAXIING TO THE RAMP THE MAINTENANCE PERSON NOTICED THAT THE HYDRAULIC SERVICING BAY DOOR WAS MISSING. AN INVESTIGATION WAS PERFORMED AND IT WAS FOUND THAT THE MAINTENANCE PERSON HAD NOT CLOSED THE DOOR PROPERLY. NOT ALL LATCHES HAD NOT BEEN CLOSED PROPERLY. SERVICEABLE DOOR AND HINGE WAS INSTALLED AND THE AIRCRAFT WAS INSPECTED. THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20060321003) 2L73 4F A3WE 20060705002022006070500202WP 2006 7 5 CA060321004 220060317G7397C8102414 CABLE SWRNGNSA226 SA226TC 8780404SW GARRTTTPE331TPE33110UA 01514WP HARTZLHCE4N HCE4N3 NE BROKEN W E ENGINE SHUTDOWN O OTHER NRNOT REPORTED 1 CA (CAN) FLIGHT CREW REPORTED THAT DURING START THE RPM WAS UNCONTROLLABLE AND INITIATED A MANUAL SHUT DOWN. MAINTENANCE DISCOVERED THE POWER LEVER BROKEN APPROX. 4 INCHES FROM THE END JUST SHORT OF THE QUICK DISCONNECT FITTING. DUE TO THE FACT THAT THE TELE-FLEX CABLE IS LOCATED INSIDE A (SHEATH) THE DEFECT IS NOT DETECTABLE UNTIL THE CABLE BREAKS. IT APPEARS AS THOUGH THE CABLE HAS BEEN CONTACTING THE INNER PORTION OF THE SHEATH FOR SOME TIME AND THE FACT THAT THE PILOTS PULL THE POWER LEVER INTO REVERSE EVERY SHUT DOWN CAUSED SOME WORK HARDENING OF THE MATERIAL WHICH ULTIMATELY CAUSED IT TO FAIL. (TC NR 20060321004) 2L72 4T4 TRTA8SW E4WE 5 CP10NE 20060705002032006070500203EA 2006 7 5 CA060321005 120060321G2810CL21564001 FUEL CELL CNDAIRCL215 CL2156B11215 EA PWA PW120 PW123 NE HAMSTD14SF 14SF15 NE LT WING LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA 1220 (CAN) WHILE UNDERGOING A SCHEDULED INSPECTION FUEL WAS FOUND DRIPPING FROM THE LT WING. ALL 8 FUEL TANKS WERE REMOVED FOR LEAK CHECK. THIS AND SEVERAL OTHER CELLS WERE FOUND LEAKING INCLUDING THIS ONE. DEFECTIVE CELLS WILL BE REPLACED. (TC NR 20060321005) 2H72 4T4 TRTA14EA E20NE 6 CP7NE 20060705001182006070500118EA 2006 7 5 CA060321006 120060321G2820CL215640026 FUEL CELL CNDAIRCL215 CL2156B11215 EA PWA PW120 PW123 NE HAMSTD14SF 14SF* NE NR 2 LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA 1222 WHILE UNDERGOING A SCHEDULED INSPECTION FUEL WAS FOUND DRIPPING FROM THE LEFT WING. ALL 8 FUEL TANKS WERE REMOVED FOR LEAK CHECK. THIS AND SEVERAL OTHER CELLS WERE FOUND LEAKING INCLUDING THIS ONE. DEFECTIVE CELLS WILL BE REPLACED. 2H72 4T4 TRTA14EA E20NE 6 CP7NE 20060705001192006070500119EA 2006 7 5 CA060321007 120060321G2820CL215640022 FUEL CELL CNDAIRCL215 CL2156B11215 EA PWA PW120 PW123 NE HAMSTD14SF 14SF* NE NR 6 LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA 1222 DURING A SCHEDULED INSPECTION IT WAS OBSERVED THAT THE LEFT WING WAS LEAKING FUEL. ALL 8 FUEL CELLS WERE REMOVED FOR LEAK CHECK AND 6 OUT OF 8 WERE FOUND LEAKING INCLUDING THIS ONE. LEAKING CELLS WILL BE REPLACED. 2H72 4T4 TRTA14EA E20NE 6 CP7NE 20060705002042006070500204EA 2006 7 5 CA060321008 120060321G2810CL21564002 FUEL CELL CNDAIRCL215 CL2156B11215 EA PWA PW120 PW123 NE HAMSTD14SF 14SF15 NE LT WING LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA 1222 (CAN) DURING A SCHEDULED INSPECTION IT WAS OBSERVED THAT THE LT WING WAS LEAKING FUEL. ALL 8 FUEL CELLS WERE REMOVED FO LEAK CHECK AND 6 OUT OF 8 WERE FOUND LEAKING INCLUDING THIS ONE. LEAKING CELLS WILL BE REPLACED. (TC NR 20060321008) 2H72 4T4 TRTA14EA E20NE 6 CP7NE 20060705002082006070500208EA 2006 7 5 CA060321009 120060321G2810CL21564075 FUEL CELL CNDAIRCL215 CL2151A10 1900320EA PWA PW120 PW123 NE HAMSTD14SF 14SF15 NE LT WING LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA 1222 (CAN) DURING A SCHEDULED INSPECTION IT WAS OBSERVED THAT THE LEFT HAND WING WAS LEAKING FUEL. ALL 8 FUEL CELLS WERE REMOVED FOR LEAK CHECK AND 6 OUT OF 8 WERE FOUND LEAKING INCLUDING THIS ONE. LEAKING CELLS WILL BE REPLACED. (TC NR 20060321009) 2H72 4R4 TRTA14EA E20NE 6 CP7NE 20060705002202006070500220GL 2006 7 5 CA060321011 120060130G5344C2FS3282A STRUT DHAV DHC2 DHC2MKI 2801830GL PWA R985 R985AN14B 52008NE HARTZLHCB3R HCB3R304 GL DOOR POST FAILED W K NONE O OTHER ININSP/MAINT 1 CA 29083 (CAN) ULTRASONIC INSPECTION REVEALED THAT THE RT DOOR POST STRUT HAD FAILED THE INSPECTION CRITERIA. NEW DOOR POST STRUTS INSTALLED. (TC NR 20060321011) 1H71 3R3 RRCA806 5E1 5 CP28EA 20060705001372006070500137GL 2006 7 5 CA060321012 120060303G5311C2FS3203A TUBE DHAV DHC2 DHC2MKI 2801830GL PWA R985 R985AN14B 52008NE HAMSTD2D 2D30 NE BIRD CAGE UNSERVICEABLE W K NONE O OTHER ININSP/MAINT 1 CA 4497 DIAGONAL BIRD CAGE TUBE FOUND TO BE BELOW LIMITS DURING ULTRASONIC INSPECTION. 1H71 3R3 RRCA806 5E1 5 CP206 20060705001382006070500138EA 2006 7 5 CA060321013 120060203G5342C3FS4727 HINGE BRACKET DHAV DHC3 DHC3 2800202EA PWA R1340 R134059 52016NE HORIZ STAB DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA 23509 BOTH THE FORWARD HORIZONTAL STABILIZER ATTACH HINGE BRACKETS (C3FS472-7 RT AND C3FS473-7 LT) WERE FOUND TO BE BUSHED BEYOND SERVICEABLE LIMITS. VIKING AIR HAD GIVEN A MAXIMUM OD OVERSIZE BUSHING OF .500. DURING INSPECTION THE BUSHINGS WERE MEASURED AT .650 + BOTH BRACKETS WERE REPLACED WITH NEW PARTS. 1H71 3R3 R A815 5E2 20060705001462006070500146EA 2006 7 5 CA060321014 120060201G5700C3FS145 BAR DHAV DHC3 DHC3 2800202EA PWA R1340 R134059 52016NE WING CORRODED W O OTHER O OTHER ININSP/MAINT 1 CA 23509 DURING A VISUAL INSPECTION OF THE OTTER TIE BAR ASSEMBLY A LARGE COLLECTION OF DEAD FLY CARCASSES WERE FOUND CRAMMED INTO THE "U" CHANNEL SECTION OF THE TIE BAR. ON FURTHER INVESTIGATION WITH THE BUG BIOMASS IT BECAME EVIDENT THAT THE BAR HAD STARTED TO EXFOLIATE. THE TIE BAR ASSEMBLY WAS REPLACED. A CONTRIBUTING FACTOR TO THE FAILURE MAY HAVE BEEN THE FACT THAT THE INSPECTION HOLES THAT WERE INCORPORATED TO INSPECT THE TIE BAR HAD NEVER BEEN ADEQUATELY RESEALED AFTER THE LAST INSPECTION. 1H71 3R3 R A815 5E2 20060705001542006070500154EA 2006 7 5 CA060321016 120060103G5312C3FS3413 BULKHEAD DHAV DHC3 DHC3 2800202EA PWA R1340 R134059 52016NE FUSELAGE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 23509 THE FOLLOWING FLOOR SUPPORTING STRUCTURE WAS FOUND TO BE UNSERVICEABLE IN THE CABIN AREA PN NR C3FS34-13 BULKHEAD LOWER STATION 133.33, C3FS13-27 BULKHEAD LOWER STATION 153.77, C3FS51-27 BULKHEAD LOWER STATION 174.2, C3FS58-15 BULKHEAD LOWER STATION 194.00 REPEATED HEAVY LOADS TO THE FLOOR AREA OVER 23'000 HRS HAD DAMAGED OR WEAKENED THE STRUCTURAL INTEGRITY OF THE FLOORBEAM ATTACH POINTS. ALL OF THE TOP BULKHEAD FLANGES WERE DAMAGED AT THE INTERSECTION OF THE FLOORBEAMS REF #C3FS351-2. THIS DEFECT IS ESPECIALLY IMPORTANT SINCE THE REAR CABIN SEAT/SEAT BELT RESTRAINT IS INDIRECTLY ATTACHED TO THE FLOOR BULKHEADS. 1H71 3R3 R A815 5E2 20060705001582006070500158EA 2006 7 5 CA060321017 120060209G2730C3CF1267 HOUSING DHAV DHC3 DHC3 2800202EA PWA R1340 R134059 52016NE HAMSTD23D 23D40 NE ELEV QUADRANT WORN W K NONE O OTHER ININSP/MAINT 1 CA 23509 THE ELEVATOR QUADRANT BEARING HOUSING WAS WORN BEYOND LIMITS AT THE BEARING ATTACH POINTS, REF NRB538. 1H71 3R3 R A815 5E2 6 CP719 20060705001592006070500159EA 2006 7 5 CA060322001 120060209G2720C3CF1277 HOUSING DHAV DHC3 DHC3 2800202EA PWA R1340 R134059 52016NE HAMSTD23D 23D40 NE RUDDER QUADRANT WORN W K NONE O OTHER ININSP/MAINT 1 CA 23509 THE RUDDER QUADRANT BEARING HOUSING WAS WORN BEYOND LIMITS AT THE BEARING ATTACH POINTS/PIVOT POINT. 1H71 3R3 R A815 5E2 6 CP719 20060705001642006070500164EA 2006 7 5 CA060322002 120060209G2750C3CF1073 FITTING DHAV DHC3 DHC3 2800202EA PWA R1340 R134059 52016NE HAMSTD23D 23D40 NE T/E FLAP WORN W K NONE O OTHER ININSP/MAINT 1 CA 23509 BOTH INBOARD FLAP(C3CF104-5) TUBE END ASSEMBLIES (LT AND RT WINGS) C3CF107-3 WERE REPLACED DUE TO WEAR AND LOOSE ATTACH FASTENERS. FAILURE OF THE PLUG END ON THE FLAP CONTROL TUBE COULD LEAD TO AN ASYMMETRIC FLAP CONDITION. 1H71 3R3 R A815 5E2 6 CP719 20060627000832006062700083NE 2006 6 27 CA060322003 220060314G72406003T07G01 COMBUSTION CASE SKRSKYS61 S61L 8142102NE GE CT58 CT581401 30011NE ENGINE CRACKED W O OTHER J WARNING INDICATION CRCRUISE 1 CA 3356 295269 (CAN) THE PILOT NOTICED A GRADUALLY INCREASING ENGINE OIL PRESSURE, AND T5, ALONG WITH DECREASING OIL PRESSURE. AFTER SHUTDOWN, THE ENGINE WAS INSPECTED, AND A CRACK FOUND IN THE LOWER COMBUSTION CASE HALF. THE ENGINE WAS REMOVED FOR CASE REPLACEMENT AND TEST CELL RUN TO DETERMINE IF ALL INDICATIONS WERE A RESULT OF AIR LOSS THROUGH THE CASE CRACK. (TC NR 20060322003) 2G72 4U4 U 1H15 1E3 20060705001702006070500170EU 2006 7 5 CA060322004 120060320G30205302412140 DEICE SYSTEM PILATS 571101207 PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL INLET CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 4720 DURING MAINTENANCE OPERATION NOTICED EXHAUST SOOT TRAIL FROM INNER EDGE OF DEICE LIP ASSY. REMOVAL OF DEICER LIP ASSY FROM COWL REVEALED A CRACK ON INNER PART OF LIP DEICE ON INLET SIDE. DEICE LIP ASSY REPLACED WITH NEW. P/N; OF CRACKED DEICE LIP ASSY IS 530.24.12.140. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20060711001362006071100136CE 2006 7 11 CA060322006 120060316G2910991242322 VALVE CESSNA525 525 2076601CE HYD SYSTEM STUCK W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA 3247 LANDING GEAR DID NOT COME UP ON CLIMB. PILOT FOUND COMPLETE FAILURE OF ALL HYDRAULIC SYSTEM. ON TROUBLESHOOTING, FOUND SOLENOID LANDING VALVE SCREEN STUCK ON VALVE SEAT CAUSING COMPLETE BYPASS OF THE HYDRAULIC FLUID. THIS VALVE WAS PLANNED TO BE REPLACED AT NEXT VISIT IAW SB 525-24-10. 1L72 4F RTA1WI 20060711001592006071100159EA 2006 7 11 CA060322007 120060321G2797MS3476L2241S CONNECTOR DHAV DHC8 DHC8311 1386006EA PWA PW120 PW123 NE HAMSTD14SF 14SF15 NE ELEVATOR HEAT BURNED W O OTHER J WARNING INDICATION CLCLIMB 1 CA 3453834538 (CAN) DURING CLIMB POSITION LT CIRCUIT BREAKER POPPED. MAINTENANCE TROUBLE SHOOTING FOUND REAR PRESSURE BULKHEAD (STA 708.45) PLUG CONNECTOR (9811-J9) TO HAVE SEVERAL BURNED PINS. ELEVATOR HORN HEAT , LOGO LIGHTS AND AFT POSITION LTS ARE ALL CONNECTED THRU THIS CONNECTOR PLUG. ELEVATOR HORN HEAT, POSITION LIGHTS , AND LOGO LIGHTS HAD REPORTED PREVIOUS INTERMITTANT FAULTS. CONNECTOR REPLACED AND TESTED SERVICEABLE. (TC NR 20060322007) 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20060711001602006071100160WP 2006 7 11 CA060322008 120060320G8011BC3151002 STARTER ROBSINR44 R44 7640120WP LYC O540 O540F1B5 41532EA ENGINE MALFUNCTIONED W K NONE O OTHER ININSP/MAINT 1 CA 456 (CAN) AIRCRAFT FAILED TO START. STARTER WAS REMOVED AND A OVERHAULED UNIT WAS INSTALLED AND NO FURTHER DEFECTS WERE NOTED. STARTER JUST COME OUT OF A REPAIR, 20.5 HRS EARLIER FOR INTERMITTENT/ERRATIC OPERATION. (TC NR 20060322008) 1G71 3O3 O H11NM E295 20060626000012006062600001WP 2006 6 26 CA060322009 120060308G6322369D25623 BELT HUGHES369 369D 4470706WP ALLSN 250C 250C20B 03013GL BLOWER FAILED W K NONE O OTHER ININSP/MAINT 1 CA 421 (CAN) DURING A 100 HOUR INSPECTION THE BLOWER BELT WAS NOTED AS HAVING SEVERAL TEETH MISSING. BELT IS IDENTIFED WITH THE PN IN WHITE MARKER. BELT TENSION WAS VERIFIED AFTER INSTALLATION AND NO DEFECTS WERE NOTED DURING THE NEXT 3-100 HOUR INSPECTIONS. NO VIBRATIONS OR NOISE WERE NOTED. (TC NR 20060322009) 1G71 3U3 U H3WE E4CE 20060710001042006071000104NE 2006 7 10 CA060322010 220060315G7321324485318 FUEL CONTROL DHAV DHC8 DHC8301 1386003NM PWA PW120 PW123 NE HAMSTD14SF 14SF15 NE ENGINE LOOSE W O OTHER J WARNING INDICATION CRCRUISE 1 CA 269831106 DURING CRUISE PILOT REPORTED ENGINE PARAMETERS WANDERING. NH +-0.4% NL +- 0.2%, RPM +- 2 . MAINTENANCE INSPECTION FOUND POWER LEVERS ARMS LOOSE (LOW TORQUE/STILL COTTER PINNED ARMS RETIGHTEN AT ALL PIVOT POINTS AND RE-COTTER PINNED. AIRCRAFT RETURNED TO SERVICE FUEL CONTROL UNIT HAD BEEN INSTALLED FOR 1106 HR/1331 CY. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20060711001612006071100161EA 2006 7 11 CA060323001 220060131G74141068291013 HOUSING BENDIX RKWELL700 700 7630520SW LYC O540 TIO540R2AD 41532EA HARTZLHCE3Y HCE3YR2A GL MAGNETO CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 671 B101195 (CAN) DURING SCHEDULED MAINTENANCE, AN OIL LEAK WAS NOTED AT THE RT ENGINE MAGNETO GASKET. THE MAGNETO WAS REMOVED TO REPLACE A DEFECTIVE GASKET. UPON CLOSER INSPECTION A SMALL CRACK WAS FOUND ALONG THE MAGNETO MOUNTING FLANGE. OIL WAS SEEPING THROUGH THE CRACK. THE CRACK WAS HIDDEN BY THE MAGNETO RETAINING CLAMP, NUT AND LOCK WASHER. (TC NR 20060323001) 1L72 3O3 O A12SW E14EA 5 CP33EA 20060710001052006071000105NE 2006 7 10 CA060323002 220060311G85301830 CYLINDER DOUG DC3 DC3CS1C3G 3021458WP PWA R1830 R183092 52020NE HAMSTD23E 23E50 NE NR 13 CRACKED W E ENGINE SHUTDOWN E VIBRATION/BUFFET CLCLIMB 1 CA 422 CP356035 THE EXHAUST EAR OF NR 13 CYLINDER DEVELOPED A CRACK WHICH AFFECTED THE VALVE CLEARANCE OF THE EXHAUST VALVE, RESULTING IN A ROUGH RUNNING ENGINE. CYLINDER ASSEMBLY WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE. 2L72 4R4 R A669 5E4 6 CP603 20060623000022006062300002EU 2006 6 23 CA060323003 120060224G2930MS2771923 SWITCH SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1D1 NE COLLECTIVE MALFUNCTIONED W O OTHER F FLT CONT AFFECTED NRNOT REPORTED 1 CA THE PILOT WAS CARRYING OUT HIS/HER PRE FLIGHT HYDRAULIC TEST "FAILED", HORN WAS UNABLE TO SOUND DUE TO FAULTY SWITCH. 1G71 3U3 U H9EU E19EU 20060626000912006062600091CE 2006 6 26 CA060323004 120060323G7120 MOUNT HELIO H250 H250 4300302CE ENGINE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA FWD FUSELAGE TUBING MOUNTING BOSSES FOR THE ENGINE MOUNT, AND THE L/H MAIN GEAR REAR ATTACH FITTING FOUND CRACKED DURING INSPECTION. THE AREAS CRACKED WERE THE WELD JOINTS OF ALL 4 FWD FITTINGS AND THE INNER WELD JOINT ON THE LANDING GEAR FITTING. ALL WELDS APPEAR TO BE FACTORY WELDS. CAUSE OF FAILURE BELIEVED TO BE THAT WELD JOINTS WERE NOT PROPERLY NORMALIZED FROM FACTORY CAUSING BRITTLE REGIONS WITHIN THE WELDED AREA ITSELF. 1H71 3O 1A8 20060710001062006071000106GL 2006 7 10 CA060324001 220060316G7200 ENGINE CESSNA525 525 2076601CE WILINTFJ44 FJ441A GL FAILED W EA ENGINE SHUTDOWN UNSCHED LANDING KEJFLUID LOSS VIBRATION/BUFFET WARNING INDICATION CLCLIMB 1 CA DURING CLIMB-OUT, ENGINE BEGAN TO VIBRATE AND COMPRESSOR STALL. OIL PRESSURE WENT TO ZERO. PILOT PERFORMED SHUTDOWN AND RETURNED TO AIRPORT. POST FLIGHT INSPECTION OF ENGINE REVEALED METAL ON CHIP COLLECTORS AND THE SPOOLS DID NOT TURN FREELY (BEARING NOISE). THE MANUFACTURER WILL PROVIDE A TEARDOWN REPORT SOON. 1L72 4F4 FRTA1WI E3GL 20060710001072006071000107NM 2006 7 10 CA060324002 120060322G2897W1134360118 WIRE HARNESS BOEING737 737800* NM GE CFM56 CFM56* 13802NE FUEL PUMP DAMAGED W D RETURN TO BLOCK J WARNING INDICATION TXTAXI/GRND HDL 1 CA 3010 A/C HAS NR 2 AFT FUEL PUMP LOW PRESSURE LIGHT ILLUMINATE ON TAXI. A/C RETURNED TO GATE AND IT WAS DISCOVERED THAT ASSOCIATED CIRCUIT BREAKER WAS TRIPPED. FURTHER INVESTIGATION REVEALED WIRE W1134-3601-18 HAD SHORTED TO GROUND. MOC CONSULTED WITH BOEING ENGINEERING AND THE WIRE WAS TEMPORARILY REPAIRED IAW THE BOEING STANDARD WIRING PRACTICES MANUAL WITH A 10 DAY CONSTRAINT. THE WIRE IS TO BE PERMANENTLY REPAIRED THIS WEEKEND. THIS DEFECT HAS ALSO BEEN SUBMITTED TO THE BOEING FSE AS THIS IS AN IN SERVICE ISSUE. 2L72 4F4 FRTA16WE E2GL 20060626000932006062600093NE 2006 6 26 CA060324003 220060324G73100301007710 LINE SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1D1 NE FUEL SYS BROKEN W O OTHER KBJFLUID LOSS SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION TXTAXI/GRND HDL 1 CA A/C WOULD NOT START, FOUND LINE WAS BROKEN. IF THE CONDITIONS WERE RIGHT A FIRE MAY HAVE OCCURRED ON START UP. TURBOMECA HAS REPLACEMENT LINE WITH AN INCREASED DIAMETER AND WALL THICKNESS. THE SB STATES, IN ORDER TO MINIMIZE THE POSSIBILITY OF THE PIPE RUPTURE DUE TO DISTORTION SB 292 73 0339 UPDATE 1. 1G71 3U3 U H9EU E19EU 20060626000942006062600094NE 2006 6 26 CA060324004 220060324G73100301007720 LINE SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1D1 NE INJECTOR BROKEN W O OTHER KBJFLUID LOSS SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION TXTAXI/GRND HDL 1 CA THE PILOT WAS TRYING TO START THE ENGINE, IT WOULD NOT START. UPON INSPECTION OF THE STARTING PROBLEM IT WAS FOUND THE THIS LINE WAS BROKEN. TURBO MECA HAVE A REPLACEMENT LINE WITH AN INCREASED DIAMETER AND WALL THICKNESS. THE SB IS RECOMMENDED/OPTIONAL. SB292 73 0339 UPDATE 1. 1G71 3U3 U H9EU E19EU 20060626000962006062600096EU 2006 6 26 CA060326001 120060325G6720704A34130184 CONTROL CABLE SNIAS 350 AS350BA 8680817EU TMECA ARRIELARRIEL1B 6OO30NE TAIL ROTOR UNSERVICEABLE W O OTHER F FLT CONT AFFECTED APAPPROACH 1 CA PILOT REPORTED T/R PEDALS FELT STICKY. CABLE WAS INVESTIGATED AND FOUND STIFF AND ROUGH. CABLE WAS CHANGED PROBLEM WAS SOLVED. INSIDE CABLE MOISTURE AND CORROSION WERE FOUND. 1G71 3U3 UNCH9EU E19EU 20060710001082006071000108NM 2006 7 10 CA060327002 120060323G2780745583 SHAFT DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE TE FLAPS SEIZED W O OTHER F FLT CONT AFFECTED LDLANDING 1 CA AFTER LANDING, THE PILOT WAS UNABLE TO RETRACT THE FLAPS. UPON INVESTIGATION BY MAINTENANCE, THE FLAP SECONDARY DRIVE CABLE WAS FOUND SIEZED (THE INNER CABLE HAD BROKEN STRANDS WHICH JAMMED THE CABLE). THE SECONDARY DRIVE CABLE WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20060626000972006062600097EU 2006 6 26 CA060327003 120060324G3411 LINE SOCATATBM TBM700 8682000EU PITOT/STATIC SY CONTAMINATED W K NONE O OTHER ININSP/MAINT 1 CA DURING BIANNUAL ALTIMETER SYSTEM TEST AND INSPECTION PILOTS ALTIMETER AND VSI RESPONDED ERRATICALLY TO INCREASING/DECREASING PRESSURE. WATER DROPLETS WERE FOUND IS PILOTS STATIC SYSTEM BETWEEN NR 1 LEFT STATIC VENT AND Y CONNECTION TO RIGHT VENT. 1L71 3T RTA60EU 20060711001652006071100165CE 2006 7 11 CA060327004 120060321G322007436051 TORQUE LINK CESSNA182 182G 2072716CE CONT O470 O470R 17026SO MCAULY2A36C 2A36C29 GL NLG CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 3826 (CAN) NOSE GEAR UPPER TORQUE LINK WAS FOUND CRACKED INSIDE UPPER CORNER ON THE LT SIDE. FORGING NR 0543034-497, 2014 KAE-2A (TC NR20060327004) 1H71 3O3 ONT3A13 E273 5 CP880 20060719000232006071900023CE 2006 7 19 CA060327005 120060324G3244650C063 TIRE CESSNA425 425 2076018CE PWA PT6 PT6A112 52043NE MCAULY4HFR344HFR34C762 NE MLG CUT W O OTHER E VIBRATION/BUFFET LDLANDING 1 CA 103 (CAN) LT MAIN TIRE POSSIBLE SIDEWALL PUNCTURE DURING LANDING ROLLOUT. NO OTHER DISCREPANCIES NOTED OTHER THAN DAMAGED SIDEWALL. NO DAMAGE TO AIRCRAFT OR OTHER COMPONENTS NOTED. (TC NR 20060327005) 1L72 3T3 TRTA7CE E4EA 6 C3PNE 20060719000242006071900024NE 2006 7 19 CA060328001 220060320G73220319878030 FCU UROCOPEC120 EC120B 8680987EU TMECA ARRIUSARRIU2F NE ENGINE LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA 2891 68 34096 (CAN) DURING ROUTINE DAILY INSPECTION AFTER A FLIGHT, FUEL LEAK NOTICED AT THE MAIN FUEL OUTLET FITTING (NIPPLE) ON THE FCU. SUSPECT O-RING P/N 9794099203 DEFECTIVE. (TC NR 20060328001) 1G72 3U3 UNCR0001RD E34NE 20060719000252006071900025SO 2006 7 19 CA060328002 120060326G55141101411073004 CHANNEL EMB 110 EMB110P1 3260122SO PWA PT6 PT6A34 52043EA HARTZLHCB3T HCB3TN3 GL HORIZONTAL STAB CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING COMPLETION OF A 6C INSP, MAINT FOUND A CRACK IN THE FWD LT HORIZONTAL STABILIZER MACHINED CHANNEL. THIS PARTICULAR INSP WAS COMPLETED DUE TO AD 83-03-03R6 REQUESTING AN INITIAL INSP AND MODIFICATION OF ATTACHMENT AREA. INITIAL REQUIREMENTS WERE PREVIOUSLY COMPLETED BY A PREVIOUS OPERATOR. A REPEAT INSP IS NOW CALLED UP DURING 6C INSP AS REQUIRED BY AD. CRACK WAS FOUND IN NEW MODEL OF MACHINED CHANNEL PART NR 110-4A-1411-07-16 THAT WAS PREVIOUSLY REPLACED. A VISUAL INSP OF ALL SURROUNDING AREA WAS COMPLETED AND AN EDDY CURRENT INSPECTION OF REMAINING FITTING WAS COMPLETED AND NO OTHER DISCREPANCY WAS FOUND. CHANNEL WILL BE REPLACED AND AIRCRAFT WILL BE RETURNED TO SERVICE. (TC NR 20060328002) 1L72 4T4 T A21SO E4EA 6 CP15EA 20060719000262006071900026EU 2006 7 19 CA060328004 120060327G3260C245890002 UPLOCK SWITCH AEROSPATR42 ATR42300 8680920EU PWA 120 PW120 NE HAMSTD14SF 14SF5 NE MLG FAILED W A UNSCHED LANDING N FALSE WARNING CLCLIMB 1 CA (CAN) DEPARTING, THE CREW OBSERVED AN UNSAFE(RED) WARNING ON NR 2 MAIN LANDING GEAR AFTER RETRACTION WAS SELECTED. THE CREW RETURNED TO POINT OF DEPARTURE AND AND CARRIED OUT A NORMAL CONFIGURATION LANDING. MAINTENANCE DETERMINED THAT THE UNSAFE CONDITION INDICATION WAS FALSE DUE TO A FAILED UPLOCK BOX. THE NR 2 MAIN GEAR UPLOCK BOX WAS REPLACED, TESTED SERVICEABLE AND AIRCRAFT RETURNED TO SERVICE.(TC NR 20060328004) 2H72 4T4 TRTA53EU E20NE 6 CP7NE 20060719000272006071900027SO 2006 7 19 CA060328005 120060321G7920PH481101 SEAL CHAMPION PIPER PA28 PA28140 7102802SO LYC O320 O320E3D 41508EA SNSNCH74D 74DM EA OIL FILTER COLLAPSED W K NONE O OTHER ININSP/MAINT 1 CA 48 (CAN) INTERNAL SEAL BETWEEN CARTRIDGE AND BASE PLATE COLLAPSED INTO CENTER OF FILTER. (TC NR 20060328005) 1L71 3O3 O 2A13 E274 5 NP88614 20060719000282006071900028EU 2006 7 19 CA060328006 120060323G56101379377C406 WINDOW BAG JETSTMJETSTM3212 1500217EU GARRTTTPE331TPE33111U 01514WP MCAULY4HFR344HFR34C652 NE COCKPIT CRACKED W B EMER. DESCENT O OTHER CRCRUISE 1 CA (CAN) DURING FLIGHT THE COPILOT WINDOW CRACKED, NO SOUND WAS HEARD. THE CAPTAIN IMMEDIATELY INITIATED DESCENT TO A SAFER LEVEL AND CONTINUED TO LAND. THE WINDOW WAS FOUND TO BE CRACKED ON THE EXTERNAL LAYER WITH NO OBVIOUS INITIATING POINT AND REMOVED FROM THE AIRCRAFT. (TC NR 20060328006) 2L72 4T4 TRTBA15CAA E4WE 6 C3PNE 20060719000292006071900029NM 2006 7 19 CA060328007 120060328G3350D71701100 BATTERY PACK BOEING737 737824 13844BZNM EMERGENCY LIGHT FAILED W K NONE L NO TEST ININSP/MAINT 1 CA (CAN) PERFORMING EMERGENCY LIGHT AT L1,R1 AND R2 DOORS LIGHTS FAILED TO ILLUMINATE AT TEST THIS IS PART OF SERVICE CHECK BATTERY PACK REPLACED (TC NR 20060328007) 2L72 4F RTA16WE 20060626001002006062600100NE 2006 6 26 CA060328008 220060327G7314D7431 PUMP ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE FUEL SYS FAILED W C ABORTED TAKEOFF J WARNING INDICATION TOTAKEOFF 1 CA 599 AS PILOT WAS READY FOR TAKEOFF, THE AUX PUMP LIGHT ILLUMINATED AND THE BREAKER POPPED. PILOT LANDED AND NOTIFIED MAINTENANCE. REPLACED THE PUMP ASSY. THE PUMP ASSY ALSO HAS A WELDON PUMP P/N B8187-B S/N 105188. 1G71 3O3 O H11NM 1E4 20060626001022006062600102CE 2006 6 26 CA060329001 120060321G3230 MOTOR BEECH 200 B200 1152922CE PWA PT6 PT642A NE HARTZLHCB3T HCB3TN3 GL MLG FAILED W A UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 CA AFTER TAKEOFF, EN ROUTE TO DESTINATION, GEAR WARNING LIGHT CAME ON. PILOT TRIED EXTENDING THE GEAR AND NO EXTENSION WAS NOTED. AIRCRAFT RETURNED TO BASE AND GEAR WAS EXTENDED USING MANUAL EXTENSION. AIRCRAFT PUT ON LOCKS. GEAR MOTOR CIRCUIT BREAKER WAS FOUND POPPED AND ACCUMULATOR WAS FOUND TO BE LOW IN PRESSURE. CIRCUIT BREAKER WAS RESET AND ACCUMULATOR CHARGED TO PROPER PRESSURE. GEAR SWUNG SEVERAL TIMES WITH NO ABNORMAL RESULTS. AIRCRAFT RETURNED TO SERVICE. 1L72 4T4 T A24CE E4EA 6 CP15EA 20060719000302006071900030NE 2006 7 19 CA060329002 220060327G8530 CYLINDER HEAD DHAV DHC2 DHC2MKI 2801830GL PWA R985 R985AN14B 52008NE HARTZLHCB3R HCB3R304 GL ENGINE CRACKED W A UNSCHED LANDING EBRVIBRATION/BUFFET SMOKE/FUMES/ODORS/SPARKS PARTIAL RPM/PWR LOSS CLCLIMB 1 CA 136 2593 (CAN) PILOT REPORTED JUST AFTER T/O, HEARD A POP AND THE ENGINE LOST A BIT OF POWER WITH SLIGHT VIBRATION. JUST AFTER THIS HE COULD SMELL A BIT OF BURNED OIL SMELL. AIRCRAFT RETURNED TO POINT OF DEPARTURE. INSPECTION INTO PROBLEM FOUND THAT NR 7 CYLINDER HAD SEPARATED BETWEEN HEAD AND BARREL. CYLINDER HAD 136.2 HRS SINCE OVERHAUL. ULTRASONIC INSPECTION OF CYLINDER IAW A/D 78-08-07 WAS CARRIED OUT AT OVERHAUL. CYLINDER ASSEMBLY WAS REPLACED AND AIRCRAFT WAS RETURNED TO SERVICE (TC NR 20060329002) 1H71 3R3 RRCA806 5E1 5 CP28EA 20060719000422006071900042CE 2006 7 19 CA060330001 120060329G323312802091 PIN CESSNA CESSNA172 172RG 2072438CE LYC O360 O360F1A6 41514EA MCAULY2D34C B2D34C220 GL NLG ACTUATOR CRACKED W O OTHER J WARNING INDICATION APAPPROACH 1 CA 8274 2459 (CAN) NO GEAR DOWN INDICATION UNTILL RECYCLED SEVERAL TIMES. INSPECTION REVEALED CRACKED DOWNLOCK PIN (REF SEB 95-20)AND WORN ACTUATOR BEARING END PIN HOLE. (TC NR 20060330001) 1H71 3O3 O 3A17 E286 5 CP7EA 20060626001082006062600108 2006 6 26 CA060330002 120060330G2824AVZ4B11198 VALVE FUEL SYSTEM DAMAGED W O OTHER O OTHER NRNOT REPORTED 1 CA ELECTRIC MOTOR SECTION OF PUMP ASSY WAS FOUND DURING INSPECTION TO MISSING A "C" CLIP AND PLUG. REPLACED WITH SERVICABLE UNIT. 20060720003202006072000320NM 2006 7 20 CA060330003 120060330G6330500N3139 MOUNT DOUG 600N 600N 3027377NM GEARBOX CRACKED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) CRACKS WERE FOUND IN THE MOUNT IS SIMILAR LOCATION ON 2 COMPANY AIRCRAFT. (TC NR 20060330003) 1G71 3U NCH3WE 20060719000542006071900054CE 2006 7 19 CA060330004 120060326G27517013348931 INDICATOR LEAR 45 45LEAR 5170805CE GARRTTTFE731TFE7312 01518WP TE FLAPS FAILED W L ABORTED APPROACH P NO WARNING INDICATION APAPPROACH 1 CA 1333 (CAN) ON APPROACH, CREW NOTICED THAT AFTER FLAP WAS SELECTED LT FLAP INDICATION MOVED NORMALLY WHERE RT FLAP INDICATION REMAINS AT ZERO DEGREES POSITION. CREW DID NOT FEEL ANY FLAP ASSYMETRY. AC DID NOT REGISTER A FLAP ASSYMETRY, DID NOT PROVIDE A FLAP FAIL CAS MESSAGE. CREW NOTED THIS AS AN INDICATION PROBLEM ONLY. MAINT TROUBLESHOT SYS AND CONFIRMED IT TO BE AN INDICATION PROBLEM ONLY, REASON WHY AC DID NOT PROVIDE A FLAP FAIL CAS MESSAGE. FURTHER TROUBLESHOOTING DISCOVER INDICATION PROBLEM TO BE CAUSED BY RT DATA ACQUISITION UNIT, PORTION OF FLAP POSITION ON CHANNEL (B) HAD FAILED AT ZERO DEGREES POSITION. A REPAIRED DAU WAS INSTALLED AND AC WAS RETURNED TO SERVICE. (TC NR 20060330004) 2L72 4F4 FRTT00008WIE6WE 20060719000552006071900055EA 2006 7 19 CA060330005 120060330G7120C6WM151928 MOUNT DHAV DHC6 DHC6300 2802606EA PWA PT6 PT6A27 52043EA HARTZLHCB3T HCB3TN3 GL ENGINE MISMANUFACTURED W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA 18503587 (CAN) ENGINE MOUNT PLATE INCORRECTLY MANUFACTURED. THE HOLE FOR THE ENGINE MOUNT BOLT (MS21250-06042) IS NOT DRILLED AT THE CORRECT ANGLE. THE HOLE FROM THE MOUNT PLATE TO THE FITTING, ENGINE MOUNT P/N C6WM 1517-28 DOES NOT LINE UP. MARKINGS ON THE PLATE ARE, P/N C6WM 1519-28, W/O14947/1 AND AUG 12/04. (TC NR 20060330005) 1H72 3T4 TRTA9EA E4EA 6 CP15EA 20060719000562006071900056EA 2006 7 19 CA060330006 120060330G28102156400 FUEL CELL CNDAIRCL215 CL2156B11215 EA PWA PW120 PW123 NE HAMSTD14SF 14SF* NE RT WING LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA 1318 (CAN) DURING INSPECTION FOR A FUEL LEAK OF THE RT WING. ALL CELLS WERE REMOVED FOR LEAK CHECK. CELLS NR 1,2,4,6 AND 7 WERE FOUND LEAKING. CELLS WILL BE REPLACED. (TC NR 20060330006) 2H72 4T4 TRTA14EA E20NE 6 CP7NE 20060719000572006071900057NM 2006 7 19 CA060330007 120060330G2997SM601BA20A1 CONTACTOR DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE HYD CIRCUIT BRKRSTUCK W A UNSCHED LANDING O OTHER CLCLIMB 1 CA (CAN) AFTER TAKE-OFF THE PILOTS WERE COMPLETING THE AFTER TAKE-OFF CHECKS AND THEY NOTICED THAT THE NR 2 HYDRAULIC STANDBY POWER UNIT WAS INDICATING PRESSURE EVEN WITH THE SPU SELECTED OFF. THE PILOTS ELECTED TO RETURN TO BASE FOR FURTHER INVESTIGATION. THE MAINTENACE STAFF FOUND THAT THE HYDRAULIC REMOTE CIRCUIT BREAKER CONTACTOR WAS STUCK IN THE ON POSITION. CONTACTOR WAS REPLACED AND AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20060330007) 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20060626001092006062600109WP 2006 6 26 CA060331001 120060330G6510C0411 BEARING ROBSIN ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE T/ROTOR DRIVE SPUN W K NONE O OTHER ININSP/MAINT 1 CA 198 0678 DURING INSPECTION IT WAS NOTED THAT THE T/R D/S ASSY BEARING HAD SPUN. THE INNER RACE ROTATED ON SHAFT ROTATED 1/4 TURN AND WITNESSED BY TORQUE SEAL. DRIVESHAFT REPLACED. 1G71 3O3 O H11NM 1E4 20060719000582006071900058NE 2006 7 19 CA060331002 220060329G73130301007720 INJECTOR SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1D1 NE FUEL SYSTEM CRACKED W K NONE J WARNING INDICATION ININSP/MAINT 1 CA 10205 (CAN) UPON LANDING AT A MOUNTAIN TOP (6000 FT) ASL. PILOT UNABLE TO COMPLETE ENGINE START. AFTER ARRIVAL OF AME IS HAS BEEN DISCOVERED THAT RT FUEL INJECTOR PIPE WAS CRACKED AROUND ENTIRE CIRCUMFERENCE AT THE FLARE END. PIPE SUBSEQUENTLY REPLACED WITH SERVICEABLE. A/C RETURNED TO SERVICE. (TC NR 20060331002) 1G71 3U3 U H9EU E19EU 20060626001112006062600111 2006 6 26 CA060331003 420060331G2562 G SWITCH POINTER PS400010 ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE ELT WEAK W K NONE L NO TEST ININSP/MAINT 1 CA 409070 ELT WAS BEING RECERTIFIED AND TESTED IN-HOUSE. THE G SWITCH WAS FOUND WEAK. ELT WAS RETURNED TO POINTER FOR FURTHER REPAIR. 1G71 3O3 O H11NM 1E4 20060719000592006071900059 2006 7 19 CA060331004 220060331G7261CH481101 OIL FILTER ENGINE DAMAGED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) UPON RECEIPT OF NEW OIL FILTER, THREADS WERE FOUND TO BE GALLED. (TC NR 20060331004) 20060626001122006062600112SW 2006 6 26 CA060331005 120060327G3246 SADDLE BELL 205 205A1 1181414SW LYC T53 T5317A 41549NE SKID TUBE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA CRACK WAS FOUND ON SKID TUBE AT FORWARD CROSSTUBE MOUNTING SADDLE. THERE WAS NO REPORT OF A HARD LANDING WITH THIS AIRCRAFT AT THIS TIME. TIMES FOR THESE SKID TUBES WERE NOT AVAILABLE. 1G71 4U4 U H1SW E17EA 20060626001132006062600113CE 2006 6 26 CA060402001 120060327G553211564000098 SKIN BEECH 100 100BEECH 1152916CE PWA PT6 PT6A28 EA VERTICLE STAB TECRACKED W K NONE O OTHER ININSP/MAINT 1 CA TRAILING EDGE SKIN, RT SIDE CRACKED APPROX 1 INCH AT MAIN SPAR STATION. CRACK STARTS AT ONE JO BOLT FASTENER LOCATION AND GOES DOWN TO EDGE OF SKIN. MOST OF THE CRACK WAS HIDDEN BY THE LOWER RIGHT STABILIZER ATTACH/FAIRING ANGLE P/N 97-440025-14. 1L72 3T4 T A14CE E4EA 20060719000602006071900060EA 2006 7 19 CA060403001 120060328G5610NP13932113 WINDSHIELD CNDAIRCL600 CL6002C10 1390015EA GE CF34 CF348C1 NE COCKPIT BROKEN W A UNSCHED LANDING O OTHER CRCRUISE 1 CA (CAN) ENROUTE THE OUTER PLY PILOT WINDSHIELD SHATTERED AND IMPAIRED CAPT'S VIEW . A/C DIVERTED WINDSHIELD REPLACED, AIRCRAFT DECLARED SERVICEABLE. (TC NR 20060403001) 2L72 4F4 FRTA21EA EOOO63EN 20060626001142006062600114SW 2006 6 26 CA060403002 120060330G6210STC WIRE STRIKE BELL 427 427 1182207SW PWC PW207 PW207D NE DAMAGED W O OTHER F FLT CONT AFFECTED TXTAXI/GRND HDL 1 CA 539 DURING COOL DOWN AT IDLE RPM CYCLIC CONTROL STICK WAS MOVED FORWARD AND MAIN ROTOR BLADE (QTY 2) CONTACTED THE UPPER CUTTER OF THE WIRE STIKE PROTECTION SYSTEM. 1G71 3U3 U R00001RCE42NE 20060719000612006071900061EA 2006 7 19 CA060403003 120060219G21331036322 OUTFLOW VALVE CNDAIRCL604 CL604 1900301EA CABIN PRESSURE FAILED W O OTHER G MULTIPLE FAILURE CLCLIMB 1 CA (CAN) ON A FLIGHT DURING CLIMB OUT AT FL 110 AND CLEARED FOR FL150 A (CABIN ALT) EICAS MESSAGE POSTED. THE CREW OBSERVED THAT CABIN ALTITUDE WAS CLIMBING IN AN UNUSUAL HIGH RATE. WHEN CABIN ALTITUDE REACHED 10000 FEET CREW DECIDED TO CONTROL IN MANUAL MODE. NO RESPONSED WAS NOTED. NOW GOR A MASTER WARNING DUE TO CABIN ALTITUDE HIGHER THAN 10000 FEET AND O2 MASKS DROPPED AND CREW PUT THEIR OWN MASKS ON. CREW DECIDED TO LEVEL OFF AT 15000 FEET AND FERRY FLOWN THE AIRCRAFT AT LOW LEVEL. ALSO OUTFLOW VALVE P/N 103664-2 WAS REPLACED AS BOTH VALVES FAILED THE TO PASS THE AMM TESTING. (TC NR 20060403003) 2L72 4F RTA21EA 20060719000622006071900062EA 2006 7 19 CA060403004 120060305G2820601R626765 SHROUD CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE COLLECTOR BOX FAILED W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) DURING A POST HEAVY CHECK INSPECTION IT WAS DISCOVERED THAT A FUEL LEAK COMING OFF THE FUSELAGE DRAINS AT STATION 559.00 AND 574.00. AFTER INVESTIGATION, IT WAS DETERMINED THAT THE FUEL LEAK WAS COMING FROM THE FUEL COLLECTOR BOX SHROUD (P/N 601R62676-5). A BRACKET INSIDE THE COLLECTOR BOX IS BROKEN AND CHAFED ON THE LT ENGINE FEED LINE. THE AIRCRAFT IS CURRENTLY DOWN AND AWAITING PARTS (TC NR 20060403004) 2L72 4F4 FRTA21EA E15NE 20060719000632006071900063NE 2006 7 19 CA060403005 220060302G7200 ENGINE PWA PT6 PT6A67R 52043NE MAKING METAL W E ENGINE SHUTDOWN J WARNING INDICATION CRCRUISE 1 CA 106004 (CAN) IN FLIGHT, THE ENGINE LOW OIL PRESSURE WARNING ANNUNCIATED AND THE ENGINE WAS SHUTDOWN. SUBSEQUENT INSPECTION REVEALED METALIC DEBRIS IN THE ENGINE OIL. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE EXTABLISHED. (TC NR 20060403005) 4 T E26NE 20060719000642006071900064NE 2006 7 19 CA060403006 220060305G7200 ENGINE CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE FLAMED OUT W A UNSCHED LANDING XJ ENGINE FLAMEOUT WARNING INDICATION CRCRUISE 1 CA (CAN) INFLIGHT THE ENGINE EMITTED A LOUD NOISE, INTERTURBINE TEMPERATURE INCREASED AND THE ENGINE FLAMED OUT. A DEAD-STICK LANDING WAS CARRIED OUT RESULTING IN SIGNIFICANT AIRCRAFT DAMAGE. MFG WILL INVESTIGATE AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060403006) 1H71 3T3 T A37CE E4EA 20060613002502006061300250NE 2006 6 13 CA060403007 220060220G7314 PUMP BEECH 200 200BEECH 1152920CE PWA PT6 PT642A NE FUEL SYS UNSERVICEABLE W O OTHER XJ ENGINE FLAMEOUT WARNING INDICATION DEDESCENT 1 CA ON DESCENT, THE ENGINE EXPERIENCED AN UNCOMMANDED SHUTDOWN. THE FUEL CONTROL UNIT AND FUEL PUMP WERE SUBSEQUENTLY REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. 1L72 4T4 T A24CE E4EA 20060606002262006060600226NE 2006 6 6 CA060403008 220060112G7314 SPLINE BEECH 45 T34C 1152015CE PWA PT6 PT6A25 52043NE FUEL PUMP WORN W K NONE R PARTIAL RPM/PWR LOSS NRNOT REPORTED 1 CA THE ENGINE EXPERIENCED AN UNCOMMANDED POWER REDUCTION WHICH RESULTED IN THE AIRCRAFT CRASHING. INVESTIGATION DETERMINED THE FUEL PUMP SPLINE TO BE SUFFICIENTLY WORN TO RESULT IN THE LOSS OF ENGINE FUEL FLOW. 1L71 3T3 T A26CE E4EA 20060607002522006060700252NE 2006 6 7 CA060403009 220060309G7200 ENGINE PWC PT6A114A CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE ENGINE POWER LOSS W O OTHER R PARTIAL RPM/PWR LOSS CLCLIMB 1 CA PC0624 DURING CLIMB, THE ENGINE EXPERIENCED AN UNCOMMANDED LOSS OF POWER. THE AIRCRAFT CRASHED ON ATTEMPTING TO RETURN TO POINT OF DEPARTURE. P&WC WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 1H71 3T3 T A37CE E4EA 20060607002532006060700253GL 2006 6 7 CA060403010 220060326G7230 TUBE RROYCE 6896024CP BELL 206 206L1 1182107SW ALLSN 250C 250C28B 03013GL ENGINE BROKEN W BE EMER. DESCENT ENGINE SHUTDOWN CERF.O.D. VIBRATION/BUFFET PARTIAL RPM/PWR LOSS TOTAKEOFF 1 CA PILOT HEARD A BIG "BANG" FROM ENGINE AND LOST POWER. THE PILOT LANDED IN THE BUSH WITHOUT DAMAGING THE A/C. AFTER THE INSPECTION OF THE COMPRESSOR BY THE MECHANIC, FOUND THE COMPRESSOR IN BAD SHAPE, CONFIRMED FOD WAS IN TO THE COMPRESSOR. MECHANIC CHECKED AND FOUND SOME LITTLE METAL PIECES IN THE INTAKE BEHIND THE INLET SCREEN, FINALLY FOUND THE INJECTOR TUBE BROKEN ON THE WELDING POINT. 1G71 3U3 U H2SW E1GL 20060607002542006060700254NE 2006 6 7 CA060403011 220060305G7200 ENGINE PWC PT6A114A CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE ENGINE POWER LOSS W A UNSCHED LANDING EX VIBRATION/BUFFET ENGINE FLAMEOUT NRNOT REPORTED 1 CA PC0717 THE ENGINE EMITTED A LOUD NOISE FOLLOWED BY AN UNCOMMANDED INFLIGHT SHUTDOWN. THE AIRCRAFT DEPARTED THE RUNWAY ON LANDING RESULTING IN SIGNIFICANT AIRFRAME DAMAGE. P&WC WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE DETERMINED. 1H71 3T3 T A37CE E4EA 20060607002552006060700255EA 2006 6 7 CA060403012 220060310G7532 BLEED VALVE PWC 310082903 DHAV DHC6 DHC6300 2802606EA PWA PT6 PT6A27 52043EA COMPRESSOR FAULTY W E ENGINE SHUTDOWN ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS APAPPROACH 1 CA DURING APPROACH, THE ENGINE EMITTED AN UNUSUAL NOISE FOLLOWED BY AN UNCOMMANDED POWER REDUCTION. THE ENGINE WAS SHUT DOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED A FAULTY COMPRESSOR BLEED VALVE. 1H72 3T4 TRTA9EA E4EA 20060607002562006060700256NE 2006 6 7 CA060403013 220060315G7200 ENGINE PWC PT6A42 BEECH 200 200BEECH 1152920CE PWA PT6 PT642A NE ENGINE POWER LOSS W A UNSCHED LANDING X ENGINE FLAMEOUT CRCRUISE 1 CA 94570 (CAN) DURING CRUISE THE ENGINE EXPERIENCED AN UNCOMMANDED SHUT DOWN. THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE. P&WC WILL MONITOR INVESTIGATION OF THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 1L72 4T4 T A24CE E4EA 20060607002572006060700257GL 2006 6 7 CA060403014 320060316G6110 SEAL BEECH 90 C90A 1152911CE PWA PT6 PT6A21 52043EA HARTZLHCB3T HCB3TN3 GL PROPELLER LEAKING W E ENGINE SHUTDOWN K FLUID LOSS CRCRUISE 1 CA DURING FLIGHT, AN ENGINE OIL LEAK WAS OBSERVED AND THE ENGINE WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED A LEAKING PROPELLER SHAFT SEAL AND A LOOSE BETA VALVE RETAINING NUT. 1L72 3T4 TRT3A20 E4EA 6 CP15EA 20060607002582006060700258NE 2006 6 7 CA060403015 220060316G7320 FUEL SYS PWC PT6A42 BEECH 200 B200 1152922CE PWA PT6 PT642A NE ENGINE FLUCTUATES W E ENGINE SHUTDOWN M OVER TEMP DEDESCENT 1 CA 94383 DURING INITIAL DESCENT, ENGINE FUEL FLOW WAS OBSERVED TO FLUCTUATE. THROTTLE INPUT RESULTED IN EXCESSIVE INTERTURBINE TEMPERATURE INCREASE AND THE ENGINE WAS SHUT DOWN IN FLIGHT. P&WC WILL MONITOR INVESTIGATION OF THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 1L72 4T4 T A24CE E4EA 20060619001792006061900179NE 2006 6 19 CA060403016 220060323G7200 ENGINE GULSTM200 200 4500308NM PWA 306 PW306B NE MAKING METAL W EA ENGINE SHUTDOWN UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CLCLIMB 1 CA CC0095 (CAN) DURING CLIMB, THE ENGINE EMITTED A LOUD NOISE FOLLOWED BY AN UNCOMMANDED POWER REDUCTION. THE ENGINE WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED METAL DEBRIS IN THE ENGINE EXHAUST. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060403016) 2L72 4F4 FRTA53NM E35NE 20060607002592006060700259NE 2006 6 7 CA060403017 220060321G7200 ENGINE PWC PW123D DHAV DHC8 DHC8* NM PWA 120 PW123D 52152NE HAMSTD14SF 14SF23 NE ENGINE POWER LOSS W A UNSCHED LANDING EJXVIBRATION/BUFFET WARNING INDICATION ENGINE FLAMEOUT CRCRUISE 1 CA AT0009 DURING CRUISE, THE ENGINE EMITTED A LOUD NOISE FOLLOWED BY A LOW ENGINE OIL PRESSURE INDICATION AND AN UNCOMMANDED ENGINE SHUT DOWN. SUBSEQUENT INSPECTION REVEALED METAL CONTAMINATION AND A SEIZED COMPRESSOR. P&WC WILL MONITOR INVESTIGATION OF THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20060607002602006060700260EU 2006 6 7 CA060403018 120060329G7931 OIL SYSTEM PWC PW127E AEROSPATR42 ATR42500 8680948EU PWA PW120 PW127 NE ENGINE LOW PRESSURE W E ENGINE SHUTDOWN J WARNING INDICATION CLCLIMB 1 CA 127187 DURING CLIMB, ENGINE OIL PRESSURE WAS OBSERVED TO FLUCTUATE FOLLOWED BY A LOSS OF OIL PRESSURE. THE ENGINE WAS SHUT DOWN IN FLIGHT. P&WC WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE DETERMINED. 2H72 4T4 TRTA53EU E20NE 20060608002222006060800222EA 2006 6 8 CA060403019 220060429G7200 ENGINE BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA FAILED W O OTHER XJ ENGINE FLAMEOUT WARNING INDICATION NRNOT REPORTED 1 CA THE ENGINE WAS REPORTED TO HAVE EXPERIENCED AN INFLIGHT SHUTDOWN. SUBSEQUENT INSPECTION REVEALED METAL DEBRIS ON THE ENGINE CHIP DETECTOR. P&WC WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 1L72 4T4 T A24CE E4EA 20060608002852006060800285EA 2006 6 8 CA060403020 120060402G2910MS21907D6 ELBOW CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE HYD SYSTEM SPLIT W K NONE K FLUID LOSS ININSP/MAINT 1 CA 45 DEGREE UNIVERSAL ELBOW FITTING FOUND SPLIT WITH HYDRAULIC FLUID LEAKAGE ON THE NR 2 HYDRAULIC SYSTEM, IPC 29-11-00, FIG 20, VIEW K, ITEM NR 45. FITTING REPLACED WITH THE SYSTEM CHECKED SERVICEABLE. 2L72 4F4 FRTA21EA E15NE 20060612003432006061200343EA 2006 6 12 CA060403021 120060403G3246AJ78241 TUBE DHAV DHC3 DHC3 2800202EA MLG CRACKED W O OTHER J WARNING INDICATION CLCLIMB 1 CA AFT LT STRUT TUBE CRACKED PN AJ78-24-1. 1H71 3R A815 20060612003452006061200345EA 2006 6 12 CA060403022 120060403G3246J78221 STRUT DHAV DHC3 DHC3 2800202EA MLG CRACKED W A UNSCHED LANDING O OTHER CLCLIMB 1 CA AFT LT STRUT CLEVIS CRACKED. 1H71 3R A815 20060612003462006061200346EA 2006 6 12 CA060403023 120060403G3246AJ78211 CLEVIS DHAV DHC3 DHC3 2800202EA MLG CRACKED W O OTHER O OTHER CLCLIMB 1 CA AFT RT SPREADER CLEVIS CRACKED. 1H71 3R A815 20060612003482006061200348EA 2006 6 12 CA060403024 120060403G3246J781112 PLATE DHAV DHC3 DHC3 2800202EA FLOAT CORRODED W O OTHER O OTHER CLCLIMB 1 CA SEVERE CORROSION ON FWD AND AFT FLOAT BUILD-UP ESPECIALLY LOWER SURFACES OF P/N J78-11, J78-12. 1H71 3R A815 20060612003492006061200349EA 2006 6 12 CA060403025 120060403G3246J7819 CLEVIS DHAV DHC3 DHC3 2800202EA DAMAGED W O OTHER O OTHER CLCLIMB 1 CA J78-19 CLEVIS, RT AND LT FRONT STRUT LOWER. HOLE IN FITTING FILLED WITH ROD, HOLE MOVED AND LIKELY IN A NON-COMPLIANT MANNER DURING MFG. 1H71 3R A815 20060626001152006062600115WP 2006 6 26 CA060403026 120060403G2910D4523 B-NUT ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE HYD SYSTEM LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA 398 HYDRAULIC FLUID LEAKING FROM FITTING. BACKUP NUT ON FITTING FOUND UNDER TORQUED. FACTORY TORQUE SEAL AND PAL NUT WERE FOUND UNDISTURBED. BACKUP NUT RETORQUED AND NO FURTHER DEFECTS FOUND. 1G71 3O3 O H11NM 1E4 20060626001172006062600117NE 2006 6 26 CA060403028 220060401G73147436024 FUEL CONTROL BOEING727 727225 1384077NM PWA JT8 JT8D9A 52048NE NR 2 ENGINE MALFUNCTIONED W E ENGINE SHUTDOWN RXJPARTIAL RPM/PWR LOSS ENGINE FLAMEOUT WARNING INDICATION CRCRUISE 1 CA 666126 AT CRUISE ALTITUDE(FL350), THE NR 2 ENGINE WAS SURGING AND DROPPING POWER. ENGINE ANTI ICE AND FUEL HEAT CHECK C/W, NO CHANGE, ENGINE FAILURE- SHUTDOWN CHECK LIST C/W, NR 2 ENGINE SHUTDOWN INFLIGHT. MAINTENANCE INSPECTED AIRCRAFT IAW PW MM 72-00-00 PAGE 531. ENGINE FUEL PUMP/FCU PACKAGE REPLACED AND AIRCRAFT RETURNED TO SERVICE. 2L73 4F4 F A3WE E2EA 20060612003502006061200350EA 2006 6 12 CA060403029 120060403G5210C3FS24950 DOOR DHAV DHC3 DHC3 2800202EA FUSELAGE CORRODED W O OTHER O OTHER NRNOT REPORTED 1 CA THE LT STRUT, FUSELAGE DOOR WAS CORRODED THROUGH. SURFACE RUST PITTING WAS NOTICED, AND A PUNCH WAS DRIVEN THROUGH THE TUBE WITH MINIMAL EFFORT SEVERAL TIMES. RT STRUT EXHIBITED SEVERE PITTING ALSO, AND WAS ALSO REMOVED FOR REPLACEMENT. LOGBOOKS INDICATED THAT THE STRUTS WERE INSPECTED AUG 20, 2001 IAW S/B 3/29 BY AMO 78-92. 1H71 3R A815 20060612003512006061200351CE 2006 6 12 CA060404001 120060403G3411MILH55934 HOSE LEAR 35 35A 5170602CE GARRTTTFE731TFE73122B 01518WP RT PITOT/STATIC CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 1975 DURING A SCHEDULED INSPECTION, THE AVIONICS TECHNICIAN VISUALLY DISCOVERED SEVERAL HOSES CRACKED IN THE RT PITOT/STATIC CIRCUIT. HOSES WERE FOUND CRACKED AND LEAKING ON THE LT PITOT/STATIC CIRCUIT APPROXIMATELY 1 MONTH AGO. THESE PARTICULAR HOSES WERE INSTALLED FOR RVSM CONVERSION. 2L72 4F4 F A10CE E6WE 20060612003522006061200352EU 2006 6 12 CA060404002 120060329G2800L95F50603 DISK AIRBUSA321 A321211 3930370EU CENTER TANK RUPTURED W A UNSCHED LANDING O OTHER CLCLIMB 1 CA FUEL AUTO TRANSFER FAULT ECAM IN CLIMB. SELECTED MAN AS PER ECAM. REALIZED NR 1 TANK WAS FEEDING BOTH ENG AND UNBALANCE INCREASED. UNABLE TO GET FUEL FROM CENTER OR RIGHT TANK. RETURNED TO YYZ. RECTIFICATION: TSM TASK 28-12-00-810-801 CARRIED OUT. OVERPRESSURE PROTECTOR DISK 96QM RUPTURED. REMOVED TASK 28-12-41-000-003 AND INSTALLED TASK 28-12-41-400-003 MM TASK 28-25-00-869-001 FUEL TRANSFER AND PANEL LEAK CHECK CARRIED OUT SERVICEABLE. 2L72 4F RTA28NM 20060613000452006061300045 2006 6 13 CA060404003 420060329G2330845438421 VIDEO DISPLAY AIRBUSA340 A340313 EU CFMINTCFM56 CFM565C4 13802NE CABIN BURNED W H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 1 CA 4H VIDEO MACHINE GOT REALLY HOT AND SMELLED BURNED AT THE END OF FLIGHT. THICK WHITE SMOKE CAME FROM PTV. FOUND PTV OPERATION SERV. FOUND SEAT PWR SUPPLY U/S AND ODOR OF SMOKE. DEACTIVATED BY PULLING AND COLLERING C/B. 2L74 4F4 FRTA197 E37NE 20060613001702006061300170NM 2006 6 13 CA060404004 120060314G32402445901 DISC BFGOODRICH DHAV DHC8 DHC8202 2809007NM PWA 120 PW123D 52152NE HAMSTD14SF 14SF23 NE RT MLG BRAKE DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA 435 0279 DURING BRAKE ASSY OVERHAUL THE TECHNICIAN DISCOVERED THE ROTATING DISC WAS BADLY DAMAGED. AFTER FURTHER INVESTIGATION, IT WAS FOUND THAT THE KEYWAYS ON THE WHEEL ASSEMBLY WERE MISALIGNED ON THE BRAKE DISC DURING INSTALLATION. THE BRAKE ASSY WAS INSPECTED DURING OVERHAUL WITH NO DAMAGE FOUND ON IT. THE WHEEL ASSY WAS ALSO REPLACED AND SENT FOR NDT ALSO WITH NO DAMAGE FOUND ON IT. THE ONLY ITEM THAT WAS REPLACED ON THE WHEEL ASSY WERE THE KEYWAYS P/N 170-209-2. THE ROTATING DISC P/N 244-590-1 WAS REPLACED AND AIRCRAFT FOUND SERVICEABLE. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20060626001182006062600118SO 2006 6 26 CA060404005 120060403G2497 WIRE PIPER PA31T PA31T 7103124SO PWA PT6 PT6A28 EA HARTZLHCB3T HCB3TN3 GL DC REGULATOR BROKEN W H DEACTIVATE SYST/CIRCUITS J WARNING INDICATION CRCRUISE 1 CA IN CRUISE, PILOT NOTICED THAT THE RIGHT GENERATOR ANNUNCIATOR WAS ON AND THERE WAS NO INDICATION ON THE RIGHT AMMETER. THE GENERATOR WOULD NOT COME ONLINE AND THE GENERATOR WAS SWITCHED OFF. THERE WAS NO FURTHER EVENTS AND THE AIRCRAFT LANDED WITHOUT INCIDENT. AFTER EXTENSIVE TROUBLESHOOTING, A BROKEN WIRE WAS DISCOVERED OFF THE RIGHT OVERLOAD SENSOR. THE WIRE WAS REPAIRED AND SYSTEM TESTED SERVICEABLE. 1L72 3T4 T A8EA E4EA 6 CP15EA 20060613001712006061300171EA 2006 6 13 CA060404006 120060323G5551600230681 BUSHING CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE HORIZONTAL STAB WORN W O OTHER E VIBRATION/BUFFET CLCLIMB 1 CA 2478924789 ON DEPARTURE (200 KTS GEAR UP FLAPS 0), A LOW FREQUENCY VIBRATION WAS FELT THROUGH THE AIRCRAFT, BOTH FLIGHT DECK AND CABIN. VIBRATION WAS NOTICEABLE ENOUGH TO SHAKE SEATS SIDE TO SIDE, ENGINE FAN VIBRATION 0.2 AND 0.5, SMOOTH AIR FLIGHT CONDITIONS. CHECKED COMPLETE AIRCRAFT AND FOUND ALL FOUR HORIZONTAL STABILIZER BUSHINGS (WHICH HOLD STAB ON) SLIGHTLY WORN. BUSHING REPLACED AS PER SB 601R-55-007 PARTS A & B ONLY. OVERSIZE BUSHINGS NOT REQUIRED IAW SB, STANDARD BUSHINGS INSTALLED. AIRCRAFT TEST FLOWN AND COULD NOT REPRODUCE DEFECT. 2L72 4F4 FRTA21EA E15NE 20060626001192006062600119EA 2006 6 26 CA060405002 220060405G7200 ENGINE PWA PT6 PT6A50 52043EA MAKING METAL W K NONE O OTHER ININSP/MAINT 1 CA ENGINE OIL METAL CONTAMINATION WAS REPORTED AND ENGINE SENT TO APPROVED ENGINE FACULITY. 4 T E4EA 20060613001722006061300172WP 2006 6 13 CA060405003 220060316G7261B441172 ADAPTER BEECH 100 B100 1152919CE GARRTTTPE331TPE3316252B 01514WP HARTZLHCB4T HCB4TN5 GL OIL FILTER CRACKED W K NONE K FLUID LOSS ININSP/MAINT 1 CA DURING AN INSPECTION OF THE "OIL FILTER ADAPTER", IT WAS FOUND CRACKED IN TWO PLACES. A SMALL OIL LEAK WAS EVIDENT. THE PART WAS REPLACED. 1L72 4T4 T A14CE E2WE 6 CP40EA 20060613001732006061300173EA 2006 6 13 CA060405004 120060331G2730HST22DU522 FASTENER BOMBDR CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE ELEVATOR SHEARED W K NONE O OTHER ININSP/MAINT 1 CA 22971 RJ7095 HI-LIGHT FASTENERS (P/N HST22DU5-22) THAT ATTACHES LINKS (P/N 601R24056-55) TO FITTINGS (P/N 601R24056-51 ON LT AND FITTINGS P/N 601R24056-49 ON THE RT ELEVATOR), FOUND WITH SHEARED HEADS. 2L72 4F4 FRTA21EA E15NE 20060613001742006061300174EU 2006 6 13 CA060405005 120060213G2822FRH280002 CANISTER AIRBUSA330 A330* EU RROYCERB211 RB211* 54555NE BOOST PUMP BROKEN W O OTHER RJ PARTIAL RPM/PWR LOSS WARNING INDICATION APAPPROACH 1 CA FOB 5100 KG WING CROSSFEED SELECTED ON AS PER ATB 376. FUEL IS 2500KG IN EACH TANK. NO FUEL IN OUTERS AND TRIM. ON SHORT FINAL "L TANK LOW FUEL" ON ECAMLTANK INDICATED 1200 KG AND RIGHT TANK 3500 KG REF SNAG 4205167. FOUND RT WING NR 1 MAIN BOOST PUMP CANNISTER DELIVERY ELBOW BROKEN AT FLANGE CONNECTION TO FUEL FEED MANIFOLD. NEW ELBOW INSTALLED WITH NEW SEALS. OPERATION CHECK OF FEED SYSTEM COMPLETED. CHECKS SERVICEABLE. 2L72 4F4 FRTA46NM A12EU 20060613001752006061300175EU 2006 6 13 CA060405006 120060404G33409728787158 LAMP PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL NAV LIGHTS FAILED W K NONE O OTHER ININSP/MAINT 1 CA 200 25288300 THE A/C WAS MODIFIED PER LSTC 0-LSA06-001/D, INSTALLATION OF LED NAV LAMPS. LAMPS WERE INTSTALLED PER DRAWINGS ECA-12-TM-05-197. SINCE THIS INSTALLATION THREE NAV LAMP FAILURES HAVE OCCURRED, ONE TIME ON THE RIGHT LED AND TWICE ON THE TAIL NAV LED. THE CAUSE IS UNKNOWN AT THIS TIME, HOWEVER PILATUS A/C HAS BEEN NOTIFIED OF THIS PROBLEM. AT THE FIELD LEVEL, MOISTURE IS SUSPECTED TO BE ENTERING THE UNIT'S THROUGH THE GROMMET WHERE THE WIRING GOES INTO THE LIGHT ASSY. NO CONCRETE EVIDENCE AT THIS TIME AND WILL WAIT FOR THE MANUFACTURER TO RESPOND ON A FIX FOR THIS PROBLEM. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20060626001232006062600123NE 2006 6 26 CA060405008 220060119G73143022375 SEAL BEECH 200 B200 1152922CE PWA PT6 PT642A NE HARTZLHCB3T HCB3TN3 GL FCU/FUEL PUMP FAILED W O OTHER J WARNING INDICATION CLCLIMB 1 CA AIRCRAFT DEPARTED AND ON CLIMB THE PILOT REPORTED A LOW OIL PRESSURE INDICATION ON THE LEFT HAND ENGINE. THE AIRCRAFT RETURNED TO BASE. A TECHNICIAN WAS CALLED IN, AND FOUND THAT THE FCU/FUEL PUMP DRIVE SEAL HAD MIGRATED, AND WAS LEAKING. A NEW SEAL P/N:3022375 AND SEAL CARRIER P/N:3004085 WERE INSTALLED. ENGINE GROUND RUNS COMPLETED SATISFACTORY, AIRCRAFT RETURNED TO SERVICE. 1L72 4T4 T A24CE E4EA 6 CP15EA 20060613001762006061300176SO 2006 6 13 CA060405009 220060405G8500 ENGINE CESSNA172 172F 2072414CE CONT O300 O300C 17022SO MCAULY1C172 1C172EM GL MAKING METAL W K NONE J WARNING INDICATION ININSP/MAINT 1 CA 2640 OIL SCREEN BYPASS LIGHT CAME ON INFLIGHT. SCREEN INSPECTION FOUND FERROUS AND NON-FERROUS METAL IN QUANTITY. 1H71 3O3 ONT3A12 E253 5 NP910 20060613001772006061300177EA 2006 6 13 CA060405010 120060403G32400860163002 ACCUMULATOR CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE BRAKE MALFUNCTIONED W D RETURN TO BLOCK K FLUID LOSS TXTAXI/GRND HDL 1 CA 20623 ON TAXI-OUT CREW REPORTED HEARING A LOUD POP AND THE RAMP PERSONNEL NOTIFIED THE CREW OF A HYDRAULIC LEAK FROM THE NOSE AREA AND THE AIRCRAFT RETURNED TO THE GATE.  UPON FURTHER INVESTIGATION MAINTENANCE FOUND THE AFT END CAP ON THE BRAKE SYSTEM HYDRAULIC ACCUMULATOR HAD FAILED.  WHEN THE END CAP FAILED, IT BLEW THROUGH THE PRESSURE BULKHEAD INTO THE AVIONICS BAY CAUSING DAMAGE TO PITOT AND HYD LINES, BRAKING CONTROL RODS, WIRING AND SURROUNDING STRUCTURE. ROUTE CAUSE OF THE FAILURE WILL BE PROVIDED ONE THE STRIP REPORT IS AVAILABLE. 2L72 4F4 FRTA21EA E15NE 20060613001782006061300178EA 2006 6 13 CA060405011 120060331G49901603662 OIL COOLER CNDAIRCL600 CL6002B19 1900309EA APU LEAKING W A UNSCHED LANDING KB FLUID LOSS SMOKE/FUMES/ODORS/SPARKS CLCLIMB 1 CA 2819 1528 SHORTLY AFTER TAKEOFF, THE CREW REPORTED SMOKE IN THE CABIN AND RETURNED TO FIELD. UPON LANDING, THE CREW DISCHARGE THE APU FIRE BOTTLE. AFTER FURTHER TROUBLESHOOTING, THE SITUATION WAS DUPLICATED AND IT WAS REPORTED THAT THE APU OIL COOLER WAS CLOGGED. REMOVED AND REPLACED OIL COOLER OPS CHECK GOOD. 2L72 4F RTA21EA 20060613001912006061300191EA 2006 6 13 CA060405012 120060326G5610NP13992113 WINDSHIELD CNDAIRCL600 CL6002C10 1390015EA COCKPIT CRACKED W A UNSCHED LANDING O OTHER CLCLIMB 1 CA 923 ON CLIMB, THE PILOT WINDSHIELD CRACKED. A/C RETURNED TO BLOCK. THIS WAS A POST SB WINDSIELD. WINDSHIELD WAS REMOVED AND REPLACED IN ACCORDANCE WITH AMM. 2L72 4F RTA21EA 20060613002812006061300281 2006 6 13 CA060406001 420060329G2311 RELAY CESSNA172 172N 2072434CE LYC O320 O320H2AD 41508EA UHF SYS DEFECTIVE W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS APAPPROACH 1 CA RELAY IS USED TO POWER THE RADIO-NAVIGATION SYSTEM. ON A TRAINING FLIGHT INSTRUMENT APPROACH, SMOKE WAS NOTICED UNDER THE INSTRUMENT PANEL. THE APPROACH WAS ABORTED AND THE AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE PERSONNEL CARRIED OUT A DETAILED INSPECTION OF ALL THE RADIOS, INSTRUMENTS AND WIRING AND NOTHING WAS DISCOVERED, HOWEVER, WHEN THE 'AVIONICS MASTER' SWITCH WHICH FEEDS THE RADIOS WAS SELECTED 'ON' THE RADIOS BECAME UNSTABLE. THE AVIONICS MASTER SWITCH WAS SELECTED OFF AND THE AIRCRAFT WAS DISPATCHED TO THE NEAREST AVIONIC FACILITY. 1H71 3O3 ONT3A12 E274 20060626001242006062600124CE 2006 6 26 CA060406002 120060403G5520 TORQUE TUBE BEECH 100 B100 1152919CE GARRTTTPE331TPE3316252B 01514WP HARTZLHCB4T HCB4TN5 GL ELEVATOR CORRODED W K NONE O OTHER ININSP/MAINT 1 CA 12859 DURING AN INSPECTION OF THE ELEVATOR TORQUE TUBE, THE PRIMARY ELEVATOR TORQUE TUBE WAS FOUND CORRODED. THE PART WAS REPLACED. 1L72 4T4 T A14CE E2WE 6 CP40EA 20060626000062006062600006CE 2006 6 26 CA060406003 120060330G30009755501115 DUCT BEECH 100 A100 1152915CE PWA PT6 PT6A28 EA MCAULY4HFR344HFR34C762 NE HEAT DUCT DISCONNECTED W K NONE O OTHER ININSP/MAINT 1 CA DURING A ROUTINE INSPECTION OF THE CABIN HEATING DUCTS THE HOT AIR DUCT ASSEMBLY P/N 97-555011-15 ITEM NR 22 IN PICTURE NR 1 WAS FOUND DISCONNECTED AT THE AFT END. 2 DUCTS FURTHER FWD WERE FOUND CRACKED ALLOWING THEM TO MOVE FWD AND ALLOWING THIS DUCT TO DISCONNECT FROM ITEM NR 23. ONCE THE DUCT HAD DISCONNECTED THE CABIN HEAT WAS FLOWING INTO THE FLOOR AND ONTO THE DE-ICE PRESSURE TUBE P/N 50-970101-143 ITEM 81 IN PICTURE NR 2. THE HEAT ALLOWED A 15 INCH SECTION OF THE DE-ICE TUBE DEFORM AND COLLAPSE RESTRICTING THE AIRFLOW TO THE TAIL PART OF THE DE-ICE SYSTEM. IT IS UNCLEAR WHETHER OR NOT THE TAIL DE-ICE SYSTEM WAS SERVICEABLE. 1L72 3T4 T A14CE E4EA 6 C3PNE 20061211003722006121100372NM 2006 12 11 CA060406006 120060406G5315 FLOORBEAM BOEING737 737290C 138448VNM BS 1016 S17L CRACKED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) BS 1016 AND STR17L WEB TO FLOOR ATTACH ANGLE CRACKED AND REPAIRED IAW EA AND SRM. (TC NR 20060406006) 2L72 4F A16WE 20061211003742006121100374NM 2006 12 11 CA060406007 120060406G5315 FLOORBEAM BOEING737 737290C 138448VNM BS 807 CORRODED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) CORROSION FOUND ON FWD FLANGE OF FLOORBEAM AT BS 807 RBL 56 AND REPAIRED IAW CUSTOMER EA. (TC NR 20060406007) 2L72 4F A16WE 20061211003772006121100377NM 2006 12 11 CA060406008 120060406G5313 STRINGER BOEING737 737290C 138448VNM BS 937 S24L CORRODED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) CORROSION FOUND ON STR 24L AT BS 937 AND REPAIRED IAW CUSTOMER EA (TC NR 20060406008) 2L72 4F A16WE 20060613002822006061300282EA 2006 6 13 CA060406009 120060403G5751C3WA121 ARM DHAV DHC3 DHC3 2800202EA AILERON LOOSE W K NONE O OTHER ININSP/MAINT 1 CA FW198 MASS BALANCE ARM EXHIBITED LOOSENESS, AND WAS MOVING IN EXCESS OF 1/2 INCH AT THE END WHEN MOVED WITH MINIMAL HAND PRESSURE. AILERON DISASSEMBLED, FASTENERS REPLACED AND RETURNED TO SAFE AND FIT CONDITION IAW TYPE DESIGN. 1H71 3R A815 20060613002832006061300283EA 2006 6 13 CA060407001 120060401G5610NP13932112 WINDSHIELD CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE COCKPIT CRACKED W A UNSCHED LANDING O OTHER CLCLIMB 1 CA 3089 RT WINDSHIELD CRACKED AT FL180. FOLLOWED BY "R WSHLD HEAT" MSG. WINDSHIELD REPLACED IAW AMM 56-11-01. WINDHIELD WAS A POST SERVICE BULLETIN. 2L72 4F4 FRTA21EA E15NE 20060613002842006061300284EA 2006 6 13 CA060407002 120060330G2710 CONTROL CABLE CNDAIRCL600 CL6002C10 1390015EA GE CF34 CF348C1 NE AILERONS FROZEN W D RETURN TO BLOCK F FLT CONT AFFECTED TXTAXI/GRND HDL 1 CA 7286 RIGHT AILERON JAMMED IN DOWN POSITION AFTER FLIGHT. DURING LANDING GROUND ROLL AFTER CROSSWIND LANDING, STUCK CONTROL WHEEL TO RIGHT AFTER RT AILERON INPUT. RIGHT AILERON IN DOWN-POSITION. LT AND RT AILERON CABLE CIRCUIT AND PULLEYS CONTAMINATED WITH DEICING FLUID. CLEANING PERFORMED. OPERATIONAL TEST OF AILERON CONTROL SYSTEM ACC AMM 27-11-00-710-801-A01, AMM 27-11-00-710-802-A01 PERFORMED. DOUBLE INSPECTION PERFORMED. 2L72 4F4 FRTA21EA EOOO63EN 20061211003792006121100379EA 2006 12 11 CA060407004 120060403G5753 SKIN DHAV DHC3 DHC3 2800202EA TE FLAPS CORRODED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) SKIN REPAIRS NOT MADE IAW TYPE DESIGN, AND REPLACED. LEADING EDGE CORRODED, REPAIR MADE IN THE PAST USING INCORRECT (BOGUS) STIFFENER MATERIAL, AND UNPRIMED BY INSTALLER LEAVING A CORRODED MESS. RETURNED TO CONFORMANCE WITH TYPE DESIGN. (TC NR 20060407004) 1H71 3R A815 20060613002862006061300286EA 2006 6 13 CA060407005 120060405G5280CC6701057113 HINGE FITTING CNDAIRCL601 CL6012A12 1900303EA GE CF34 CF34* NE MLG DOOR CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 2279 LHS MAIN LANDING GEAR (MLG) P/N CC670-10520-965, S/N 15042 AND RT MLG DOOR P/N CC670-10520-966, S/N (SAME AS RHS) WERE CRACKED AT THE AFT HINGE FITTING P/N CC670-10571-13 (SEE PIX.1) AND AT FORWARD HINGE FITTING P/N CC670-10570-5 (SEE PIX.2). LOOSE FASTERNERS WERE ALSO FOUND ON THE INBOARD AND OUTBOARD SIDE OF THE DOORS. 2L72 4F4 FRTA21AE E15NE 20060613002872006061300287NE 2006 6 13 CA060407006 220060403G7314510767 PUMP AIRTRCAT802 AT802 0390305SW PWA PT6 PT6A67A 52043NE FUEL SYSTEM LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA 506 DURING DE-INHIBITING INSPECTION, A FUEL LEAK WAS DETECTED AT THE REAR OF THE FUEL PUMP ASSEMBLY. 1L71 3T4 TNCA19SW E26NE 20060613002892006061300289CE 2006 6 13 CA060407007 120060331G77149848025 TACHOMETER CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA MCAULY1C160 1C160DTM GL ENGINE FAILED W A UNSCHED LANDING O OTHER CLCLIMB 1 CA 2328 PILOTS FELT ENGINE WAS NOT PRODUCING FULL POWER RETURNED TO BASE. ENGINE INSPECTED BY AN APPROVED AVIATION COMPANY, ALL ENGINE PARAMETERS WERE NORMAL. HOWEVER, THEY DISCOVERED THE TACHOMETER WAS 100 RPM LOW AT FULL POWER. REPLACED TACHOMETER. 1H71 3O3 ONT3A12 E274 5 NP910 20061211003802006121100380GL 2006 12 11 CA060407008 120060331G5414GS29701378 ACCESS PANEL BOMBDRBD700 BD7001A10 1390006GL RROYCEBR700 BR700710A22009500NE FUSELAGE MISSING W O OTHER O OTHER NRNOT REPORTED 1 CA 1509 (CAN) THE AIRPLANE LANDED AT IT`S DESTINATION WHEN CREW EXITED THE PLANE, THEY NOTICED THAT THE AFT RT BELLY ACCESS PANEL WAS MISSING. NOTHING WAS NOTICED BY CREW WHILE IN FLIGHT (VIBRATIONS). (TC NR 20060407008) 2L72 4F4 FRTT00003NYE00061EN 20061213000732006121300073 2006 12 13 CA060410001 420060404G3417ADS86 ADC RAYTHNDH125 HAWKER800XP 7150012CE GARRTTTFE731TFE7315BR WP COCKPIT MALFUNCTIONED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) THE FLIGHT CREW HAD SNAGGED THE NEUTRAL FUEL TANK FULL INDICATION AS NOT SHOWING FULL WHEN THE TANK WAS ACTUALLY FULL. IN CONJUNCTION WITH THIS DEFECT THEY ALSO REPORTED THAT THE L/VMO TEST WAS NOT FUNCTIONING. BOTH THESE DEFECTS WERE ACTIONED AND DURING THE TESTING OF THE L/VMO SYSTEM WE WERE DIRECTED BY THE AMM TO CONDUCT THE ADC SELF TEST IAW MM 34-10-17 ADS-86 TEST. THE TEST PROCEDURE REQUIRES THAT DURING THE TEST THAT THE (MACH TRIM FAIL) LIGHT ILLUMINATES. WHEN THE TEST WAS ATTEMPTED, THIS LIGHT DID NOT ILLUMINATE. BOTH THE AIR CREW MANUAL AND THE MM INDICATED THAT THE LIGHT WILL ILLUMINATE DURING THIS TEST. THE MACH TRIM SYSTEM WAS FULLY TESTED AND WAS FOUND TO BE FUNCTIONING NORMALLY. THE2L72 4F4 FRTA3EU E6WE 20061212000732006121200073EU 2006 12 12 CA060410002 120060402G2750532A000004 LIMITER AIRBUS330 A330243 3930330EU RROYCERB211 RB211* 54555NE TE FLAPS TRIPPED W O OTHER F FLT CONT AFFECTED APAPPROACH 1 CA 1635016350 (CAN) AIRCRAFT ARRIVED WITH THE FLIGHT CONTROL FLAPS FAULT ECAM MESSAGE ON FINAL WHEN SELECTING FLAPS 2IN. UNABLE TO EXTEND FLAPS FROM THE 0 POSITION. DURING TROUBLE SHOOTING, FOUND THE LT FLAP TORQUE LIMITER TRIPPED. TORQUE LIMITER REPLACED AND SYSTEM CHECKED SERVICEABLE. (TC NR 20060410002) 2L72 4F4 FRTA46NM A12EU 20060613002922006061300292EU 2006 6 13 CA060410003 120060321G7110F50B258707 DOOR AMD FALC50FALCON50MYST2730106EU GARRTTTFE731TFE73131C 01518NE S DUCT DAMAGED W C ABORTED TAKEOFF J WARNING INDICATION TOTAKEOFF 1 CA 7300 DURING TAKEOFF, THE NR 2 ENGINE "FAIL" LIGHT ILLUMINATED. THE TAKEOFF WAS REJECTED AND THE AIRCRAFT RETURNED TO THE RAMP. MAINTENANCE WAS CONTACTED AND UPON INVESTIGATION IT WAS DISCOVERED THAT NR 2 ENGINE S DUCT DOOR AFT LATCH HAD NOT BEEN COMPLETELY ENGAGED WITH THE HOOK. BOTH THE FRONT AND REAR LATCHES WERE RE-ENGAGED AND THE DOOR WAS CHECKED FOR PROPER SECURITY. THE CREW RESUMED THE FLIGHT AND A NORMAL TAKEOFF WAS CONDUCTED. 2L73 4F4 F A46EU E6WE 20060614000992006061400099NE 2006 6 14 CA060410004 220060409G731402532330003 PUMP BEECH 200 B200 1152922CE PWA PT6 PT642A NE RT ENGINE UNSERVICEABLE W EA ENGINE SHUTDOWN UNSCHED LANDING R PARTIAL RPM/PWR LOSS CLCLIMB 1 CA 3946 3946 PCE94220 ON TAKEOFF, THE CREWS ROTATED AND HAD RT ENGINE POWER ROLL BACK. CREWS FEATHERED AND SHUT DOWN THE ENGINE AND TURNED AROUND AND LANDED. MAINTENANCE FOUND FUEL LEAKING FROM RT ENGINE DRIVEN HIGH PRESSURE FUEL PUMP P/N 025323-300-03. PUMP ASSY REPLACED AND GROUND RUN, FLIGHT TEST SERVICEABLE. 1L72 4T4 T A24CE E4EA 20061212000742006121200074EU 2006 12 12 CA060410005 120060406G2750 LIMITER AIRBUS330 A330243 3930330EU RROYCERB211 RB211* 54555NE TE FLAPS MALFUNCTIONED W O OTHER F FLT CONT AFFECTED APAPPROACH 1 CA (CAN) AT BEGINNING OF APPROACH, WHEN SELECTING SLATS/FLAPS DOWN, THE FLIGHT CONTROL FLAPS FAULT ECAM CAME ON. UNABLE TO EXTEND FLAPS FROM 0 POSITION. (REPEAT SNAG) DURING INVESTIGATION, FOUND THE LT TORQUE LIMITER AND THE LT ROTARY ACTUATOR TRIPPED. RESET CARRIED OUT. FOUND THE ROTARY ACTUATOR OIL CONTAMINATED WITH WATER. ALL GEARBOXES AND ROTARY ACTUATORS RE-SERVICED WITH NEW OIL AND FLAPS SYSTEM TESTED SERVICEABLE. CAMPAIGN WAS INITIATED TO REPLACE THE OIL IN ALL GEARBOXES AND ROTARY ACTUATORS OF THE A-330 FLEET. (TC NR 20060410005) 2L72 4F4 FRTA46NM A12EU 20060614001012006061400101 2006 6 14 CA060410006 120060406G3213 CYLINDER MESSIER PWA PW120 PW126A NE HAMSTD2D 2D30 NE MLG CORRODED W K NONE O OTHER ININSP/MAINT 1 CA 23394 DRG721589 AT DISASSEMBLY BY FIRST AIR MAINTENANCE SERVICES (EASA APPROVAL NR 145-7030) THE OUTER CYLINDER WAS FOUND TO HAVE SEVERE CORROSION, VIRTUALLY PERFORATED AND ASSESSED AS INELIGIBLE FOR RETURN TO SERVICE. THE RECORDS INDICATE THE LANDING GEAR ASSEMBLY WAS REMOVED FROM AIRCRAFT SE-LGX (WEST AIR SWEEDEN). 4 T E2ONE 5 CP206 20061212000772006121200077SW 2006 12 12 CA060410008 120060402G2700212010123101 ROD END BELL 212 212 1181420SW PWA PT6T PT6T3 52045EA UNKNOWN DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA 22 (CAN) DURING A SCHEDULED INSPECTION OF THE ROD ENDS, IT WAS NOTED THAT THE BEARING WAS SHOWNING EVIDENCE OF MOVEMENT. BEARING WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20060410008) 1G71 4U4 U H4SW E22EA 20060614001032006061400103CE 2006 6 14 CA060410009 120060401G532010541000057 CHANNEL BEECH 76 76 1153005CE LYC O360 O360A1G6D EA NLG ACTUATOR CRACKED W K NONE O OTHER ININSP/MAINT 1 CA DISCOVERED DURING INSPECTION. NLG ACTUATOR ATTACH BRACKET WAS FOUND CRACKED FROM THE EDGE OF THE BRACKET, THROUGH A LIGHTENING HOLE AND OUT THE OTHER SIDE. THE AREA IS DIFFICULT TO INSPECT. THIS IS THE SUPPORT CHANNEL THAT THE UPPER END OF THE NLG ACTUATOR ATTACHES TO. 1L72 3O3 O A29CE E286 20060614001052006061400105 2006 6 14 CA060411001 420060404G6122HCB3TN3C PROPELLER EMB 110 EMB110P1 3260122SO PWA PT6 PT6A34 52043EA HARTZLHCB3T HCB3TN3 GL RIGHT MALFUNCTIONED W C ABORTED TAKEOFF O OTHER TOTAKEOFF 1 CA 352 ON THE TAKEOFF ROLL, THE RT PROPELLER RPM WOULD ONLY GO TO 83% AND NOT BEYOND. THE AIRCRAFT RETURNED TO THE HANGAR WHERE MAINTENANCE FOUND THE RT PROPELLER TO BE AT FAULT. THE PROPELLER WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE. THE PROPELLER HAS BEEN SENT TO A REPAIR FACILITY FOR FURTHER INVESTIGATION. 1L72 4T4 T A21SO E4EA 6 CP15EA 20060614001062006061400106SO 2006 6 14 CA060411002 120060410G3240 BRAKE PIPER PA42 PA42720 7104212SO PWA PT6 PT6A61 52043EA LEFT FAILED W O OTHER O OTHER LDLANDING 1 CA LEFT SIDE BRAKE FAILED ON LANDING CAUSING RIGHT MAIN TIRE TO BLOW OUT. NO DAMAGE TO A/C. 1L72 4T4 T A23SO E4EA 20061019001962006101900196NM 2006 10 19 CA060412001 120060411G561058935733 WINDOW BOEING737 737522 138449FNM CFMINTCFM56 CFM563C1 13802EU COCKPIT FAILED W O OTHER O OTHER CRCRUISE 1 CA (CAN) DURING CRUISE FLIGHT ON ROUTE THE CAPTAINS NR 4 WINDOW INNER LAYER SHATTERED.AIRCRAFT LANDED AND WINDOW CHANGED. TIMES- 34660:35 CYCLES- 21649 (TCNR 20060412001) 2L72 4F4 FRTA16WE E21EU 20061212000792006121200079GL 2006 12 12 CA060412002 220060411G73006793969 LINE LKHEED188 188C 5262604SO ALLSN 501D 501D13 03004GL ENGINE MISSING W E ENGINE SHUTDOWN WY INADEQUATE Q C ENGINE STOPPAGE NRNOT REPORTED 1 CA (CAN) NR 2 ENGINE HAD A HUNG RESTART WHILE ON A TRAINING FLIGHT, THE ENGINE WAS SHUTDOWN, SECURED AND THE (3) ENGINE PROCEDURES WHEN FOLLOWED ON THE FLIGHT AND LANDING TO THE MAINTENANCE BASE. THE PRIMER PRESSURE LINE WAS FOUND TO BE NOT INSTALLED ON THIS ENGINE. THE PRIMER SYSTEM HAD BEEN PUT BACK INTO SERVICE AFTER THE ENGINE HAD BEEN AQUIRED FROM AN OPERATOR THAT HAD TAKEN THEM OUT OF SERVICE IAW SB. (TC NR 20060412002) 2L74 4T4 T 4A22 E282 20061213000882006121300088NM 2006 12 13 CA060412003 120060411G531065225847 BRACKET BOEING727 727227 1384078NM PWA JT8 JT8D9A 52048NE ENGINE CONTROLS CRACKED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) WHILE INVESTIGATING A STIFF THRUST REVERSER SNAG, MAINTENANCE DISCOVERED THE NR 3 ENGINE CONTROL QUADRANT BRACKET CRACKED. BRACKET WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20060412003) 2L73 4F4 F A3WE E2EA 20060614001082006061400108NE 2006 6 14 CA060413001 220060406G7250 TURBINE BOEING767 767300 1385204NM GE CF6 CF680C2B7 NE NR 1 ENGINE FAILED W EA ENGINE SHUTDOWN UNSCHED LANDING EY VIBRATION/BUFFET ENGINE STOPPAGE CLCLIMB 1 CA 704122 EGT EXCEEDANCE OF NR 1 ENG DURING CLIMB FOLLOWED BY VIBRATION AND ROLLBACK. DAMAGE TO LP TURBINE WAS FOUND. 2L72 4F4 FRTA1NM E13NE 20060614001122006061400112SO 2006 6 14 CA060413002 120060406G7603 FRICTION BRAKE LKHEED382 382G 526414USO ALLSN 501D 501D22A 03006GL HAMSTD54H 54H60117 NE THROTTLE DAMAGED W E ENGINE SHUTDOWN F FLT CONT AFFECTED DEDESCENT 1 CA DURING TRANSITION TO DESCENT, NR 3 THROTTLE WOULD NOT RETARD FULLY. THE CREW ELECTED TO CARRY OUT A PRECAUTIONARY SHUTDOWN OF NR 3 ENGINE. A NORMAL LANDING WAS COMPLETED. MAINTENANCE WAS UNABLE TO DETECT A FAULT DURING POST FLIGHT ASSESSMENT. 2H74 4T4 T A1SO E282 6 CP906 20060614001132006061400113EA 2006 6 14 CA060413003 120060327G3320BR9500106 BALLAST CNDAIRCL600 CL600* EA GE CF34 CF34* NE CABIN LIGHTS BURNED W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 1 CA 2191 2191 EN ROUTE A PASSENGER NOTICED AN ELECTRICAL BURNING SMELL. HE ALERTED THE F/A WHO ALERTED THE CAPTAIN. CAPTAIN CONFIRMED THE SMELL. AIRCRAFT THEN DIVERTED. AIRCRAFT LANDED UNEVENTFULLY WITH NO NEED FOR EMERGENCY SERVICES. AIRCRAFT PROCEEDED TO GATE. IN SPITE OF CREW AND SOC ADVISING STOC THAT THIS WAS A POTENTIAL EMERGENCY, DEPLANEMENT OF PASSENGERS WAS DELAYED 45 MINUTES. MAINTENANCE FOUND LIGHT BALLAST AT ROW 23 U/S. BALLAST WAS REMOVED AND NEW BALLAST INSTALLED. AIRCRAFT WAS VENTED FOR AN EXTENDED PERIOD AND RETURNED TO SERVICE. 2L72 4F4 FRTA21EA E15NE 20060614001212006061400121GL 2006 6 14 CA060413005 220060412G732123070613 FUEL CONTROL BELL 206 206L1 1182107SW ALLSN 250C 250C30P 03013GL ENGINE BROKEN W K NONE K FLUID LOSS ININSP/MAINT 1 CA 1373 ONE OF THE FUEL CONTROL BYPASS COVER SCREWS BROKE CAUSING FUEL TO LEAK INTO THE ENGINE BAY. THIS IS TO BE INSPECTED EVERY 100 HOURS IAW ALLISON 250 C30 CEB A-73-3075R1 WHICH IT WAS. 1G71 3U3 U H2SW E1GL 20060614001242006061400124SO 2006 6 14 CA060413006 120060413G81204038180047 SEAL GARRTT PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA HARTZLHCE3Y HCE3YR2A GL TURBOCHARGER FAILED W K NONE K FLUID LOSS ININSP/MAINT 1 CA 1546 YHO36265 PRIOR TO A TRAINING FLIGHT THE PILOT NOTED THE LT ENGINE OIL LEVEL TO BE AT 9 QUARTS. AFTER THE FLIGHT, OIL WAS FOUND ON THE LT GEAR DOOR AND THE ENGINE WAS DOWN TO 6 QUARTS. MAINTENANCE INSPECTED THE ENGINE AND FOUND OIL AT THE LOW POINT OF THE TURBOCHARGER AND BADLY OIL FOULED SPARK PLUGS. THE TURBOCHARGER OIL SEAL HAD FAILED AND WAS ALLOWING OIL INTO THE COMPRESSOR SIDE OF THE TURBO. THE OIL WAS THE BEING INDUCTED INTO THE CYLINDERS WITH A PORTION OF IT BEING BURNED AND A PORTION OF IT BEING EXHAUSTED. 1L72 3O3 O A20SO E14EA 5 CP33EA 20061213000892006121300089NM 2006 12 13 CA060413007 120060413G5313140N01062 STRINGER SPLICE BOEING757 757200 1384950NM BS 1180 CORRODED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) CORRODED EXTERNAL STRAP ON RT SIDE OF FUSELAGE AT BS 1180 ALONG STRINGER 17. (TC NR 20060413007) 2L72 4F RTA2NM 20061213000902006121300090NM 2006 12 13 CA060413008 120060413G5350148N73081 FAIRING BOEING757 757200 1384950NM HORIZONTAL STAB CHAFED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) RT HORZ STAB TO BODY SEAL FAIRING LOWER IB GUIDE CHAFED AT FORWARD END. (TC NR 20060413008) 2L72 4F RTA2NM 20061213000912006121300091NM 2006 12 13 CA060413009 120060413G5753 SPAR BOEING757 757200 1384950NM LT TE FLAP CORRODED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) LT OB MAIN FLAP AFT SPAR UPPER CHORD 44 INCHES OB OF MAIN FLAP IB EDGE. (TC NR 20060413009) 2L72 4F RTA2NM 20061019001972006101900197NM 2006 10 19 CA060413010 120060413G5754114N40827 SKIN BOEING757 757200 1384950NM NR 7 SLAT CORRODED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) EXFOLIATED CORROSION AT 2 ADJACENT LOCATIONS (TC NR 20060413010) 2L72 4F RTA2NM 20060614001752006061400175EA 2006 6 14 CA060414001 320060414G6114 HUB DIAMONDA20 DA20C1 2990001GL CONT O240 IO240B 17063SO SNSNCHW69EK W69EK63 EA PROPELLER CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 1156 AF4209 4 INCHES LONGITUDINAL CRACK FROM TIP TO HUB ON NR 2 BLADE. PROPELLER REMOVED FROM SERVICE. CRACK SIMILAR TO CRACK ON A/C C-GGMV, 1L71 3O3 ONTTA4CH E7SO 5 NTA4CH 20060614002262006061400226EA 2006 6 14 CA060414002 320060414G6111 BLADE DIAMONDA20 DA20C1 2990001GL CONT O240 IO240B 17063SO SNSNCHW69EK W69EK63 EA NR 2 CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 1156 AF4209 4 INCHES CRACK FROM TIP TO HUB ON NR 2 BLADE, SIMILAR TO THAT REPORTED WITH SDR #20060221008. PROPELLER REMOVED FROM SERVICE. 1L71 3O3 ONTTA4CH E7SO 5 NTA4CH 20060614002282006061400228EA 2006 6 14 CA060417001 220060414G8500 ENGINE BELL 47 47G4 1181030SW LYC O540 VO540B1B3 41532EA SHUTDOWN W RA AUTOROTATION UNSCHED LANDING YJ ENGINE STOPPAGE WARNING INDICATION CRCRUISE 1 CA 286 HELICOPTER WAS FLYING ALONG AND ENGINE QUIT, SUCCESSFUL AUTOROTATION WAS ACCOMPLISHED. UPON INVESTIGATION OF ENGINE, IT WAS FOUND THAT NONE OF THE VALVES WERE OPENING OR CLOSING AND THEREFORE SUGGESTS THAT CAM SHAFT IS NOT TURNING OR HAS BROKEN, ENGINE IS BEING SENT FOR TEARDOWN INSPECTION AT THIS TIME. 1G71 3O3 O 2H3 E304 20060614002322006061400232CE 2006 6 14 CA060418003 120060407G3297 WIRE BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE HARTZLHCE4A HCE4A3I NE MLG CHAFED W O OTHER N FALSE WARNING DEDESCENT 1 CA CREW REPORTED LEFT MAIN GEAR NOT INDICATING GREEN BUT WAS DOWN AND LOCKED. MAINTENANCE FOUND WIRE IN WHEEL WELL AREA CHAFFED TO ACTUATOR DOWNLOCK. WIRE REPAIRED AND PROTECTED. 2L72 4T4 TRTA24CE E26NE 5 CP10NE 20060614002422006061400242EU 2006 6 14 CA060418004 220060417G7261301350238 COVER BOEING737 737522 138449FNM CFMINTCFM56 CFM563C1 13802EU OIL INLET SCORED W K NONE K OFLUID LOSS OTHER ININSP/MAINT 1 CA MAINTENANCE WAS CARRYING OUT A 7 DAY CHECK ON AIRCRAFT WHEN NOTICED SIGNS OF OIL LEAKING IN THE AFT SECTION OF THE NR 2 ENGINE. ON INVESTIGATION, THE OIL WAS FOUND TO BE LEAKING PAST THE OIL INLET COVER FOR THE NR 5 BEARING AREA. THE COVER WAS FOUND TO HAVE SCORING ON THE INTERIOR SMALL RADIUS. THE COVER WAS REPLACED WITH A SERVICEABLE UNIT. THIS SAME ITEM WAS REPLACED FOR A SIMILAR PROBLEM IN JULY 2005. 2L72 4F4 FRTA16WE E21EU 20060614002432006061400243EA 2006 6 14 CA060418005 220060414G8520LW13521 MAIN BEARING CESSNA172 172S 2072439CE LYC IO360 IO360L2A EA CONNECTING ROD FAILED W O OTHER O OTHER NRNOT REPORTED 1 CA 2154 2154 CONNECTING ROD BEARINGS ON NR 1 AND NR 4 RODS SIGNIFICANT SURFACE DELAMINATION. BROKEN PIECES 1/2"L BY 1/8"W FOUND IN BETWEEN CONNECTING ROD BEARING AND CRANKSHAFT. 1H71 3O3 ONT3A12 1E10 20060614002442006061400244EU 2006 6 14 CA060418006 120060413G3260V0214 WARNING HORN BRAERO748 HS7482A 4231001EU RROYCEDART DART5342 EU ROTOL R4304 R2124304 EU MLG OVERHEATED W A UNSCHED LANDING N FALSE WARNING CLCLIMB 1 CA ON TAKEOFF, THE FLIGHT FINE PITCH STOP WARNING HORN SOUNDED FOLLOWED BY AN ACRID SMELL. ON APPROACH THE SHOWING GEAR DOWN AND LOCKED THE CREW OBSERVED AN UNDERCARRIAGE FLAG ON THE ASI AND ELECTED TO HAVE VISUAL CONFIRMATION FROM THE GROUND THAT THE GEAR APPEARED SAFE. THE AIRCRAFT LANDED AT POINT OF DEPARTURE WITHOUT FURTHER INCIDENT. MAINTENANCE FOUND THE FFPS HORN SEVERELY OVERHEATED THE HORN WAS REPLACED AND ALL RELATED SYSTEMS WERE CHECKED IN CONJUNCTION WITH NLG SWING. SMOOTH OVERWEIGHT LANDING CARRIED OUT. AIRCRAFT RETURNED TO SERVICE. 2L72 3T4 T A24EU A196 6 CP899 20060614002452006061400245EU 2006 6 14 CA060419001 120060418G3411 PITOT HEAD AEROSPATR42 ATR42300 8680920EU PWA 120 PW120 NE HAMSTD14SF 14SF5 NE OBSTRUCTED W C ABORTED TAKEOFF O OTHER TOTAKEOFF 1 CA DURING TAKEOFF ROLL, THE CREW OBSERVED A 20 KT DIFFERENTIAL BETWEEN ASIS. THE TAKEOFF WAS REJECTED AND THE AIRCRAFT RETURNED TO RAMP. MAINTENANCE CLEARED DEBRIS FROM THE CAPT'S PITOT PROBE AND CONDUCTED A SYSTEM LEAK CHECK. THE AIRCRAFT WAS RETURNED TO SERVICE. 2H72 4T4 TRTA53EU E20NE 6 CP7NE 20060614002462006061400246NM 2006 6 14 CA060419002 120060417G5711PA60601 SPAR PIPER PA60 PA60601 7106010NM LYC O540 IO540K1J5 41532EA HARTZLHCC3Y HCC3YR GL WING CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 4634 CRACK WAS NOTICED DURING AN ANNUAL INSPECTION WITH THE AID OF FLASHLIGHT AND MIRROR. THE DEFECT AREA IS JUST AFT OF THE NR 2 ENGINE FIREWALL THROUGH AN INSPECTION PANEL LOCATED ON THE WING UPPER SURFACE. MORE INFORMATION TO FOLLOW CONFIRMING THE CRACK(S) WITH HFEC NDT INSPECTION. ALSO THE WING STATION NUMBER AND PART NUMBER WILL BE PROVIDED. 1M72 3O3 ORTA17WE 1E4 5 CP25EA 20060615001452006061500145EA 2006 6 15 CA060419003 220060407G732243564 SCREW PRECISION CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA MCAULY1C160 1C160CTM GL IDLE MIXTURE LOOSE W O OTHER Y ENGINE STOPPAGE APAPPROACH 1 CA 731 DC45353 ON FINAL APPROACH TO LAND, THE ENGINE QUIT. AIRCRAFT GLIDED TO A LANDING AND ROLLED CLEAR OF THE ACTIVE RUNWAY. ENGINE WOULD NOT RESTART, PUSHED AIRCRAFT TO PARKING SPOT. WHEN AME EXAMINED THE ENGINE FOUND THE IDLE MIXTURE CONTROL SCREW HAD WORKED LOOSE AND DEPARTED THE AIRCRAFT IN FLIGHT. REPLACED MIXTURE SCREW AND ENGINE RAN FINE. ALL MIXTURE SCREWS WILL BE LOCKWIRED FOR SAFETY FROM NOW ON. 1H71 3O3 ONT3A12 E274 5 NP910 20060615001572006061500157CE 2006 6 15 CA060419004 120060407G3260BZ2RQ181A2 LIMIT SWITCH BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA HARTZLHCB3T HCB3T* GL MLG FAILED W A UNSCHED LANDING N FALSE WARNING CLCLIMB 1 CA 16 A NEW LANDING GEAR GEARBOX WAS INSTALLED IN THE AIRCRAFT. SEVERAL DAYS LATER THE CREW WERE UNABLE TO SELECT THE GEAR UP AFTER TAKEOFF. THE AIRCRAFT RETURNED AND LANDED NORMALLY. THE UP LIMIT SWITCH WAS FOUND TO BE DAMAGED WHERE THE INTERNAL CONTACTS WERE NOT MAKING AND NOT ALLOWING THE GEAR TO BE POWERED FOR A GEAR UP SELECTION. IT IS NOT KNOWN WHEN THE SWITCH WAS DAMAGED AS IT WAS REPLACED AT THE TIME THE GEARBOX WAS REPLACED. THE SWITCH IS IN AN AREA THAT IS DIFFICULT TO REACH THEREFORE MAKING THE RIGGING ALSO DIFFICULT. 1L72 4T4 T A24CE E4EA 6 CP15EA 20060615001582006061500158SO 2006 6 15 CA060419005 220060418G8530 CYLINDER HEAD CESSNA182 182N 2072730CE CONT O470 O470R 17026SO NR 1 LEAKING W K NONE O OTHER ININSP/MAINT 1 CA 588 588 LEAKAGE FOUND BETWEEN BARREL AND HEAD. 1H71 3O3 ONT3A13 E273 20060619002422006061900242EU 2006 6 19 CA060419006 120060418G7120332A32323300 TIE BOLT SNIAS AS332 AS332L 8680809EU TMECA MAKILAMAKILA1A 60040EU ENGINE MOUNT SHEARED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) A/C RETURNED FROM AN OFFSHORE TRIP, MAINTENANCE PERSONNEL WERE CARRYING OUT THE TURN AROUND CHECKS AND FOUND THAT ONE OF THE 3 ENGINE TIE BOLTS WAS ONLY HELD IN PLACE BY THE LOCKING WIRE. ONCE THE LOCK WIRE WAS CUT THE BOLT WAS PULLED OUT AND FOUND TO BE SHEARED IN THE THREADED AREA. A/C WAS INSPECTED WITH NO OTHER PROBLEMS FOUND, TIE BOLT WAS ORDERED. (TC NR 20060419006) 2G72 4U4 U H4EU E12NE 20060626000082006062600008CE 2006 6 26 CA060419007 120060412G5210504300377 BOLT BEECH 504300377 BEECH 200 B200 1152922CE PWA PT6 PT642A NE HARTZLHCD4N3HCD4N3A GL PAX DOOR FAILED W A UNSCHED LANDING O OTHER CLCLIMB 1 CA WHILE CLIMBING THROUGH 10000 FT, A LOUD BANG WAS HEARD FOLLOWED BY A CONSTANT HISSING SOUND. THE FLIGHT RETURNED UNEVENTFULLY AND MAINT FOUND THE UPPER FWD DRAW BOLT ROLLER HAD FAILED CAUSING THAT PORTION OF THE DOOR TO SHIFT SLIGHTLY. BOTH UPPER DRAW BOLT ROLLERS WERE REPLACED AND DOOR INSPECTED FOR FURTHER DAMAGE. NONE WAS FOUND AND GROUND CHECKS WERE C/O SERVICEABLE. 1L72 4T4 T A24CE E4EA 5 CSTC 20060615001622006061500162GL 2006 6 15 CA060420001 120060410G2820374475 CHECK VALVE DHAV DHC2 DHC2MKI 2801830GL PWA R985 R985AN14B 52008NE HAMSTD2D 2D30 NE FUEL SYSTEM CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 5316 ON ROUTINE INSPECTION AFT FUEL CHECK VALVE FOUND CRACKED, P/N 525 GG 1/2D, 3-744-75. MINOR COLOR TO SHOW THAT FUEL LEAKING. NO LEAK INDICATION AT LAST INSPECTION 50.20 HOURS PREVIOUS. 1H71 3R3 RRCA806 5E1 5 CP206 20060615001652006061500165SW 2006 6 15 CA060420002 120060407G5302206032308003 BULKHEAD BELL 206 206L1 1182107SW ALLSN 250C 250C30 03013GL TAILBOOM CRACKED W K NONE O OTHER ININSP/MAINT 1 CA WHILE PERFORMING 100 HR INSPECTION OF THE ATTACHMENT HOLES FOR TAILBOOM FOUND A CRACK ORIGINATING FROM UPPER RIGHT HOLE. CRACK WAS 1 INCH IN LENGTH. BULKHEAD WAS REPLACED. 1G71 3U3 U H2SW E1GL 20061213000922006121300092NM 2006 12 13 CA060421001 120060420G5315 FLOORBEAM BOEING737 737290C 138448VNM BS 947 CORRODED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) FLOORBEAM CAP AT BS 947 LBL 39 CORRODED AND REPAIRED IAW CUSTOMER EA. (TC NR 20060421001) 2L72 4F A16WE 20061213000932006121300093NM 2006 12 13 CA060421002 120060420G5315 FLOORBEAM BOEING737 737290C 138448VNM BS 967 CORRODED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) FLOORBEAM CAP AT BS 967 LBL 18 CORRODED AND REPAIRED IAW CUSTOMER EA. (TC NR 20060421002) 2L72 4F A16WE 20061213000942006121300094NM 2006 12 13 CA060421003 120060420G5713 STRINGER BOEING737 737290C 138448VNM RT WING CRACKED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) RT WING FUEL TANK AT WBL 135.5 STR 2R CRACKED AND REPAIRED IAW EA. (TC NR 20060421003) 2L72 4F A16WE 20061213000952006121300095NM 2006 12 13 CA060421004 120060420G5313 STRINGER BOEING737 737290C 138448VNM BS 947 S18R CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) STR 18R AT BS 947 CRACKED AND REPAIRED IAW CUSTOMER EA. (TC NR 20060421004) 2L72 4F A16WE 20070129003132007012900313NM 2007 1 29 CA060421005 120060420G5330 SKIN BOEING737 737290C 138448VNM FUSELAGE GOUGED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) BS 867 AT STR 19R SKIN GOUGED AND REPAIRED IAW CUSTOMER EA. (TC NR 20060421005) 2L72 4F A16WE 20070129003142007012900314NM 2007 1 29 CA060421006 120060420G5315 FLOORBEAM BOEING737 737290C 138448VNM FUSEAGE CRACKED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) FLOORBEAM AT BS 767 LBL 24.5 CRACKED AND REPAIRED IAW CUSTOMER EA. (TC NR 20060421006) 2L72 4F A16WE 20070129003152007012900315NM 2007 1 29 CA060421007 120060420G5320 STRUCTURE BOEING737 737290C 138448VNM FUSELAGE CORRODED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) STR 26L BS 380 CORRODED AND REPAIRED IAW CUSTOMER EA. (TC NR 20060421007) 2L72 4F A16WE 20070129003162007012900316NM 2007 1 29 CA060421008 120060420G5534 ATTACH ANGLE BOEING737 737290C 138448VNM VERICAL STAB CORRODED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) VERTICAL STAB LT TRAILING EDGE AT RUDDER STATION 174, PANEL ATTACH ANGLE CORRODED AND REPAIRED IAW CUSTOMER EA (TC NR 20060421008) 2L72 4F A16WE 20061213001002006121300100NM 2006 12 13 CA060421009 120060420G5313 STRINGER BOEING737 737290C 138448VNM BS 520 S26L CORRODED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) STR 26L AT BS 520 CORREDED AND REPAIRED IAW CUSTOMER EA. (TC NR 20060421009) 2L72 4F A16WE 20061213001012006121300101NM 2006 12 13 CA060421010 120060420G5313 STRINGER BOEING737 737290C 138448VNM BS 500B S16L CRACKED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) STR 16L AT BS 500B+13 INCHES CRACKED AT FASTNER HOLE AND REPAIRED IAW CUSTOMER EA. (TC NR 20060421010) 2L72 4F A16WE 20061213001022006121300102NM 2006 12 13 CA060421011 120060420G5313 STRINGER BOEING737 737290C 138448VNM BS 500B-520 CORRODED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) STR 26R AT BS 500B TO BS 520 CORRODED AND REPAIRED IAW CUSTOMER EA. (TC NR 20060421011) 2L72 4F A16WE 20061213001032006121300103NM 2006 12 13 CA060421012 120060420G5730 SKIN BOEING737 737290C 138448VNM LWS 76 CHAFED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) LT WING UPPER SKIN, WBL 76.75 FROM AFT EDGE OF SKIN FWD FOR 9.5 INCH SKIN CHAFED AND REPAIRED IAW CUSTOMER EA. (TC NR 20060421012) 2L72 4F A16WE 20060615001672006061500167EA 2006 6 15 CA060421013 120060417G5610NP1393225 WINDOW CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE COCKPIT CRACKED W O OTHER O OTHER CRCRUISE 1 CA THE LEFT COCKPIT WINDOW CRACKED DURING CRUISE AT FL330. WINDOW REPLACED, AIRCRAFT RETURNED TO SERVICE. 2L72 4F4 FRTA21EA E15NE 20060615001682006061500168NE 2006 6 15 CA060421014 220060416G75324157T43P01 BLEED VALVE CNDAIRCL600 CL6002C10 1390015EA GE CF34 CF348C1 NE 4TH STAGE STICKING W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CLCLIMB 1 CA AT V1 ON TAKEOFF, SMOKE AFT LAV WARNING ILLUMINATED. CONTINUED TAKEOFF, DECLARED EMERGENCY AND RETURNED TO ORD. 4TH STAGE SHUTOFF VALVE FOUND DEFECTIVE. VALVE REPLACED AND OPS CHECK GOOD. 2L72 4F4 FRTA21EA EOOO63EN 20060615001702006061500170CE 2006 6 15 CA060421015 120060402G3397 WIRE LEAR 45 45LEAR 5170805CE GARRTTTFE731TFE731* 01518WP PAX LIGHT CHAFED W H DEACTIVATE SYST/CIRCUITS M OVER TEMP CRCRUISE 1 CA DURING CRUISE, PAX ADVISED CREW PAX TABLE LIGHT SWITCH WAS VERY HOT. PILOT PULLED CB, OPENED CABIN SIDE PANEL AND DISCONNECTED SWITCH CONNECTORS. AFTER INVESTIGATION, FOUND LIGHT CONTROL SWITCH P/N: 30600557 (CUSTOMER P/N: SP-45-33) WIRING WAS CHAFING ON CUP HOLDER LOWER BRACKET. ALSO FOUND CUP HOLDER LATCH WAS MELTED, CUP HOLDER DAMPER (ACTUATOR) SEALS WERE MELTED AND WAS LEAKING, CUP HOLDER SPRING BECAME ANNEALED CONDITION. NO MORE SPRING ACTION AND THE SIDEWALL AC PLUG PLASTIC COVER WAS DEFORMED DUE TO HEAT. NOTICE THAT WHEN A SIDEWALL AC PLUG RECEPTACLE WAS INSTALLED, THAT RECEPTACLE WOULD PUSH ON SWITCH WIRING AGAINST CUP HOLDER LOWER BRACKET AND ANY MOVEMENT OF CUP HOLDER WOULD DAMAGE THE WIRING. 2L72 4F4 FRTT00008WIE6WE 20060615001752006061500175CE 2006 6 15 CA060421016 120060413G3411AN62704D0300 HOSE LEAR 35 35LEAR 5170600CE GARRTTTFE731TFE73122B 01518WP PITOT STATIC SYSCRACKED W O OTHER O OTHER APAPPROACH 1 CA CREW REPORTED A +- 400FT SPLIT WITH ALTEMETERS. FOUND PITOT/STATIC HOSE CRACKED. NOTE: OUR LEARJET 35 FLEET OF AIRCRAFT WERE RVSM CONVERTED WITH A LEARJET STC, THESE HOSES ARE PART OF THE CONVERSION AND FOUND THIS PROBLEM WITH OTHER LEARJET 35 RVSM CONVERTED AIRCRAFTS IN OUR FLEET. 2L72 4F4 F A10CE E6WE 20060615001772006061500177SO 2006 6 15 CA060421017 120060413G24104111810 ALTERNATOR PIPER PA28 PA28R201T 7102813SO LYC O360 IO360C1C6 41514EA MCAULY3D36C B3D36C424 GL ENGINE FAILED W O OTHER H ELECT. POWER LOSS-50 PC CRCRUISE 1 CA 220 THE ALTERNATOR HAS BEEN OVERHAULED AND FAILED. 1L71 3O3 O 2A13 1E10 5 CP58GL 20060710000232006071000023NM 2006 7 10 CA060421018 120060421G2720591841 DIODE BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA AILERON/RUDDER UNKNOWN W K NONE O OTHER ININSP/MAINT 1 CA 240 FOUND RUDDER TRIM FAST MOTION RT SIDE WAS U/S. FAULT CONFIRMED FOUND AILERON/RUDDER TRIM DIODE CR2 WIRE A, UN-CLIP. PANEL TESTED IAW CMM 27-15-01-700-801. AFTER FURTHER INVESTIGATION, FOUND CONNECTOR PINS P/N M39029/58-363 INSTALLED WERE WRONG TYPE AND REPLACED WITH PINS P/N M39029/1-101 IN REF TO CMM 27-15-01. CR2 SPLICE, P/N 591842-1, REPLACED AND TESTED SERVICEABLE IAW CMM 27-15-01, AND SYS TESTED IAW AMM 27-13-16-000-801/-400-801. 2H72 4T4 TRTA13NM E00062EN 20060619002432006061900243EA 2006 6 19 CA060421019 220060323G852074968 CRANKSHAFT BBAVIA8 8GCBC 1220803SW LYC O360 O360C2E 41514EA ENGINE CORRODED W K NONE O OTHER ININSP/MAINT 1 CA 847 L2651636A (CAN) FWD INNER DIA CRANKSHAFT CORRODED BEYOND LIMITS IAW AWD 98-02-08. (TC NR 20060421019) 1H71 3O3 O A21CE E286 20060616000862006061600086EA 2006 6 16 CA060421020 220060323G852074968 CRANKSHAFT BBAVIA8 8GCBC 1220803SW LYC O360 O360C2E 41514EA ENGINE CORRODED W K NONE O OTHER ININSP/MAINT 1 CA 1500 L2717736A CORROSION FOUND UNDER PID AT FWD ID. 1H71 3O3 O A21CE E286 20060616000872006061600087EA 2006 6 16 CA060421021 220060323G852074968 CRANKSHAFT BBAVIA8 8GCBC 1220803SW LYC O360 O360C2E 41514EA ENGINE CORRODED W K NONE O OTHER ININSP/MAINT 1 CA 1300 RL2805636A CORROSION FOUND UNDER PID FWD ID. 1H71 3O3 O A21CE E286 20060803002572006080300257NM 2006 8 3 CA060421022 120060413G3244PNDR0231T TIRE BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA MLG DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA 400 53 (CAN) FOUND DURING DAILY CHECK 1 MAIN WHEEL WITH TIRE BEAD WIRE MIGRATION. LOOKS LIKE LOCKING WIRE PROTRUDING FROM TIRE SIDE WALL. WHEEL ASSY HAS BEEN REMOVED. NO TIRE PRESSURE WAS LOST. INVESTIGATION SHOWN THAT THE MIGRATING BEADWIRE HAS DAMAGED THE WHEEL HUB, THE DAMAGED WAS SO DEEP THAT WE HAD TO SCRAP THE AFT WHEEL. DUNLOP IS AWARE OF THIS MIGRATING BEADWIRE ISSUE CONDITION AND HAS SEEN THIS WIRE COME OUT OF THE TIRE IN THE PAST (SIMILAR TO THIS CONDITION AND IT SEEMS TO BE AN INCREASING PROBLEM). 2H72 4T4 TRTA13NM E00062EN 20061213001042006121300104NM 2006 12 13 CA060421023 120060421G5313 STRINGER BOEING737 737290C 138448VNM BS 350-366 CORRODED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) STR 28R, BS 350 TO BS 366 CORRODED AND REPAIRED IAW CUSTOMER EA. (TC NR 20060421023) 2L72 4F A16WE 20061213001052006121300105NM 2006 12 13 CA060421024 120060421G5313 STRINGER BOEING737 737290C 138448VNM BS 925 S25L GOUGED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) AFT CARGO PIT STR 25L AT BS 925 HAS A GOUGE AND REPAIRED IAW CUSTOMER EA (TC NR 20060421024) 2L72 4F A16WE 20061213001062006121300106NM 2006 12 13 CA060421025 120060421G5313 STRINGER BOEING737 737290C 138448VNM BS 947 S26R GOUGED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) STR 26R AT BS 947 GOUGED AND REPAIRED IAW CUSTOMER EA. (TC NR 20060421025) 2L72 4F A16WE 20061213001072006121300107NM 2006 12 13 CA060421026 120060421G5315 FLOORBEAM BOEING737 737290C 138448VNM BS 727B CORRODED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) AFT CARGO PIT FLOORBEAM UPPER CHORD CORRODED AT BS 727B FROM LBL 25-45 AND REPAIRED IAW CUSTOMER EA. (TC NR 20060421026) 2L72 4F A16WE 20061213001082006121300108NM 2006 12 13 CA060421027 120060421G5330 SKIN BOEING737 737290C 138448VNM BS 326 S2R GOUGED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) FUSELAGE SKIN GOUGED AT BS 326, 2 INCHES ABOVE STR 2R AND REPAIRED IAW CUSTOMER EA. (TC NR 20060421027) 2L72 4F A16WE 20061213001092006121300109NM 2006 12 13 CA060421028 120060421G5330 SKIN BOEING737 737290C 138448VNM BS 500 S25-26L DENTED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) SKIN HAS SMALL DENT BETWEEN STR 25L AND STR 26L AT BS500+13 AND REPAIRED IAW CUSTOMER EA. (TC NR 20060421028) 2L72 4F A16WE 20061213001102006121300110NM 2006 12 13 CA060421029 120060421G5322 SHEAR TIE BOEING737 737290C 138448VNM BS 727A S22-23R CRACKED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) SHEAR TIE CRACKED AT BS 727A BETWEEN STR 22R AND 23R AND REPAIRED IAW CUSTOMER EA. (TC NR 20060421029) 2L72 4F A16WE 20061213001152006121300115NM 2006 12 13 CA060421030 120060421G5532 SKIN BOEING737 737290C 138448VNM VERTICAL STAB DENTED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) SKIN HAS A DENT IN VERTICAL STAB RT SIDE 12 INCHES AFT OF UPPER END AND REPAIRED IAW CUSTOMER EA. (TC NR 20060421030) 2L72 4F A16WE 20061213001162006121300116NM 2006 12 13 CA060421031 120060421G5347 SEAT TRACK BOEING737 737290C 138448VNM BS 504-616 CORRODED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) CORROSION ON SEAT TRACK BEAM BS 504-616 LBL 26 REPAIRED IAW CUSTOMER EA. (TC NR 20060421031) 2L72 4F A16WE 20061213001172006121300117NM 2006 12 13 CA060421032 120060421G5315 FLOORBEAM BOEING737 737290C 138448VNM BS 520 CORRODED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) FLOORBEAM AT BS 520 LBL 45 CORRODED AND REPAIRED IAW CUSTOMER EA. (TC NR 20060421032) 2L72 4F A16WE 20061213001182006121300118NM 2006 12 13 CA060421033 120060421G5511 BUSHING BOEING737 737290C 138448VNM HORIZONTAL STAB CORRODED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) RT HORIZONTAL STABILIZER, FRONT AND REAR SPAR BUSHING CORRODED REPAIRED IAW CUSTOMER EA. (TC NR 20060421033) 2L72 4F A16WE 20061213001192006121300119NM 2006 12 13 CA060421034 120060421G5511 BUSHING BOEING737 737290C 138448VNM HORIZONTAL STAB CORRODED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) LT HORIZONTAL STABILIZER FRONT AND REAR SPAR BUSHINGS CORRODED AND REPAIRED IAW CUSTOMER EA (TC NR 20060421034) 2L72 4F A16WE 20061213001202006121300120NM 2006 12 13 CA060421035 120060421G5230 SUPPORT ANGLE BOEING737 737290C 138448VNM CARGO DOOR CRACKED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) MAIN CARGO DOOR NR1 LATCH SUPPORTING ANGLE CRACKED REPAIRED IAW CUSTOMER EA. (TC NR 20060421035) 2L72 4F A16WE 20061213001212006121300121NM 2006 12 13 CA060422000 120060421G5551 ATTACH FITTING BOEING737 737290C 138448VNM HORIZONTAL STAB NICKED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) LT STABILIZER CENTER SECTION AFT UPPER SPAR, UPPER FWD ATTACH LUG FACE NICKED REPAIRED IAW CUSTOMER EA. (TC NR 20060422000) 2L72 4F A16WE 20061213001222006121300122NM 2006 12 13 CA060422001 120060421G5313 STRINGER BOEING737 737290C 138448VNM BS 947 S26R GOUGED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) STR 26R AT BS 947 GOUGED REPAIRED IAW CUSTOMER EA. (TC NR 20060422001) 2L72 4F A16WE 20061213001232006121300123NM 2006 12 13 CA060422002 120060421G5510 HINGE FITTING BOEING737 737290C 138448VNM HORIZONTAL STAB GOUGED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) RT HORIZONTAL STAB NR 1 ELEVATOR HINGE FITTING LOWER PORTION HAS A GOUGE REPAIRED IAW CUSTOMER EA. (TC NR 20060422002) 2L72 4F A16WE 20061213001242006121300124NM 2006 12 13 CA060422003 120060421G5315 FLOORBEAM BOEING737 737290C 138448VNM BS 986 CORRODED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) FLOORBEAM AT BS 986, LBL 18 TO LBL 52 CORRODED REPAIRED IAW CUSTOMER EA. (TC NR 20060422003) 2L72 4F A16WE 20061213001252006121300125NM 2006 12 13 CA060422004 120060421G5230 STRUCTURE BOEING737 737290C 138448VNM CARGO DOOR CRACKED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) MAIN CARGO DOOR BS492 CRACKED 6 INCHES BELOW HINGE AT FRAME LIGHTNING HOLE TO THE IB EDGE REPAIRED IAW CUSTOMER EA. (TC NR 20060422004) 2L72 4F A16WE 20061213001262006121300126NM 2006 12 13 CA060422005 120060421G5230 SKIN BOEING737 737290C 138448VNM CARGO DOOR GOUGED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) MAIN CARGO DOOR SKIN AT NR 6 HINGE ATTACH AREA BS 441.5 GOUGE REPAIRED IAW CUSTOMER EA. (TC NR 20060422005) 2L72 4F A16WE 20061213001272006121300127NM 2006 12 13 CA060422006 120060421G5230 SKIN BOEING737 737290C 138448VNM CARGO DOOR GOUGED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) MAIN CARGO DOOR SKIN AT NR 5 HINGE STA 418 GOUGED REPAIRED IAW CUSTOMER EA. (TC NR 20060422006) 2L72 4F A16WE 20061019001982006101900198NM 2006 10 19 CA060422007 120060421G5230 SKIN BOEING737 737290C 138448VNM CARGO DOOR GOUGED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) MAIN CARGO DOOR SKIN AT NR 4 HINGE ATTACH AREA STN 492 GOUGED REPAIRED IAW CUSTONER EA (TC NR 20060422007) 2L72 4F A16WE 20061019001992006101900199NM 2006 10 19 CA060422008 120060421G5230 SKIN BOEING737 737290C 138448VNM CARGO DOOR GOUGED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) MAIN CARGO DOOR SKIN AT NR 4 HINGE ATTACH AREA STA 406 GOUGED AND REPAIRED IAW CUSTOMER EA (TC NR 20060422008) 2L72 4F A16WE 20060616000882006061600088CE 2006 6 16 CA060422009 120060421G3233130909B40130909 LOCK NUT BEECH BEECH 200 B200 1152922CE PWA PT6 PT6A41 52043EA HARTZLHCB3T HCB3TN3 GL MLG ACTUATOR MISSING W L ABORTED APPROACH O OTHER APAPPROACH 1 CA F99820 DURING L/G EXT IN FLT, LT MAIN AND NOSE GEAR DOWN AND LOCKED IND PRESENT, WITH NO RT IND AND LOUD BANGING SOUND FROM RT SIDE OF A/C. C/O FLY-BY TO VISUALLY VERIFY ALL THREE LANDING GEARS WERE DOWN. A/C LANDED SAFELY, VERIFIED ALL 3 L/G WERE DOWN AND LOCKED BEFORE TAXING A/C OFF RUNWAY. DURING INSPECTION ACT TQ TUBE TO ACT DRIVE BOLT FOUND MISSING. TQ TUBE END AND ACT DRIVE INSPECTED FOR DAMAGE/CRACKS WITH 10X MAGNIFYING GLASS. NO DAMAGE EVIDENT. INNER TQ TUBE SPACER REPLACED DUE TO SOME SCORING OF INNER BORE. A NEW DRIVE BOLT AND LOCK NUT WAS INSTALLED ON LT AND RT ACT. LANDING GEAR SYSTEM INSPECTION/RIGGING C/O: GOOD IAW KA200 MM NR 101-590010-19B9 CHAPTER 32-30-00. FIVE FAULT FREE GEAR SWINGS C/O. 1L72 4T4 T A24CE E4EA 6 CP15EA 20060616000902006061600090EA 2006 6 16 CA060423001 120060330G2710272955 LINK ASSY CNDAIRCL600 CL6002C10 1390015EA AILERONS BROKEN W K NONE O OTHER ININSP/MAINT 1 CA 4886 RT AILERON OUTBOARD PCU OUTPUT LINK ASSEMBLY BROKEN. WHILE PERFORMING 5000 HOURS INSPECTION FOR THE FLUTTER DAMPENER MAINTENANCE FOUND RT AILERON OUTBOARD PCU OUTPUT LINK ASSEMBLY BROKEN. 2L72 4F RTA21EA 20060616000922006061600092 2006 6 16 CA060424001 220060403G7321414T70P02 FUEL CONTROL CNDAIRCL600 CL6002B19 1900309EA ENGINE MALFUNCTIONED W A UNSCHED LANDING FJ FLT CONT AFFECTED WARNING INDICATION CLCLIMB 1 CA 4836 RT ENGINE N1, N2 AND FUEL FLOW FLUCTUATING CLIMBING FROM 10000 FT AND THEN CLIMBING FROM 10000 FT TO FL210 THE RT ENGINE N1, N2 AND FUEL FLOW WERE FLUCTUATING RAPIDLY. THE FLIGHT DIVERTED AND LANDED WITHOUT INCIDENT. THE CREW REPORTED THAT FLUCTUATION CEASED WHEN THE THROTTLES WERE RETARDED FOR LANDING. THE FUEL CONTROL WAS REPLACED IN ACCORDANCE WITH AMM. 2L72 4F RTA21EA 20060616000972006061600097EA 2006 6 16 CA060424002 120060410G3246AN676AC6300 FLY WIRE FOUND FBA FBA2C 3640102EA LYC O540 IO540* 41532EA MLG BROKEN W O OTHER O OTHER APAPPROACH 1 CA 269 THE AIRCRAFT IS EQUIPPED WITH AEROCET 3450 AMPHIBIAN FLOATS. AFTER A TWO-HOUR FLIGHT AND AT 3000 FT ALTITUDE ON APPROACH FOR LANDING, THE PILOT HEARD A LOUD NOISE. NO TURBULENCE WAS NOTED AT THE TIME AND AN UNEVENTFUL LANDING WAS COMPLETED. UPON GROUND INSPECTION THE FORWARD FLY WIRE (ASSEMBLY P/N: U613) WAS OBSERVED TO HAVE BROKEN APPROXIMATELY 3 1/2 INCHES FROM THE LOWER END. FLY WIRE WAS REPLACED, AREA INSPECTION CONDUCTED WITH NO FURTHER DISCREPANCIES AND THE AIRCRAFT WAS RETURNED TO SERVICE. THE PART IN QUESTION HAS BEEN SENT FOR A FAULT ANALYSIS. A CLOSE VISUAL INSPECTION INDICATED A POSSIBLE FLAW IN THE MATERIAL. 1H71 3O3 O A7EA 1E4 20061018000632006101800063EA 2006 10 18 CA060424003 120060424G2620215T950262 FIRE BOTTLE CNDAIRCL215 CL2156B11215 EA PWA PW120 PW123 NE HAMSTD14SF 14SF* NE MALFUNCTIONED W F ACTIVATE FIRE EXT. J WARNING INDICATION TXTAXI/GRND HDL 1 CA 427 (CAN) 1936 :58 CYCLES : 1316 LARGAGES : 8888 ENGLISH: THE INDICATOR FOR NORMAL DISCHARGE OF THE HEATER EXTINGUISHER (YELLOW DISC) DID NOT WORK AND THE BOTTLE DID NOT COMPLETELY EMPTY AFTER DISCHARGE WAS SELECTED. (TC NR 20060424003) 2H72 4T4 TRTA14EA E20NE 6 CP7NE 20060616000992006061600099WP 2006 6 16 CA060424004 120060331G7810 CLAMP ROBSIN ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE EXHAUST SHIELD FAILED W K NONE O OTHER ININSP/MAINT 1 CA 203 10913 DURING PREFLIGHT INSPECTION, TAIL PIPE EXHAUST HEAT SHIELD P/N D317-1 WAS FOUND BENT AFT. FURTHER INVESTIGATION DETERMINED THAT THE FWD CLAMP FOR THE SHIELD HAD FAILED AND CAME OFF IN FLIGHT ALLOWING THE AIRFLOW TO CATCH THE SHIELD AND BENT IT AFT. ROBINSON HELICOPTER HAS UPGRADED THE TWO CLAMPS WHICH SECURE THE SHIELD TO A LARGE CLAMP SIZE. HEAT SHIELD AND CLAMPS REPLACED. 1G71 3O3 O H11NM 1E4 20060616001012006061600101SW 2006 6 16 CA060424005 120060412G531121949 FRAME BBAVIA8 8GCBC 1220803SW LYC O360 O360C1E 41514EA MCAULY1A200 1A200* GL FUSELAGE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 7559 DURING THE COMPANY STRUCTURAL INSPECTION AND REPAIR PROGRAM (SIRP), THE RIGHT SIDE OF THE FUSELAGE FRAME WAS FOUND CRACKED IN THE AREA WHERE THE RIGHT MAIN GEAR LEG RESTS AGAINST THE AIRFRAME. THE CRACK WAS LONGITUDINAL AND WAS ABOUT 1 1/8" LONG. 1H71 3O3 O A21CE E286 5 NP874 20060616001032006061600103SW 2006 6 16 CA060424006 120060424G57535428L SPAR BBAVIA8 8GCBC 1220803SW LYC O360 O360C2E 41514EA MCAULY1A200 1A200* GL LT WING TE FLAP DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA 2 HOLES FOR MOUNTING INBD FLAP HINGE BRACKET LWR ATTACH AND INBD BOLT FOR SHIM PLATE BOTH FOUND CRUDELY DRILLED AND VERY OVAL. 1H71 3O3 O A21CE E286 5 NP874 20060626000092006062600009NM 2006 6 26 CA060424007 120060422G2612 FIRE LOOP GARRTT GTCP85129 BOEING737 737248C 1384415NM PWA JT8 JT8D9A 52048NE APU FAULTY W F ACTIVATE FIRE EXT. N FALSE WARNING TXTAXI/GRND HDL 1 CA AFTER ARRIVAL AT DESTINATION AND DURING TAXI, A FIRE INDICATION WAS OBSERVED WHEN APU WAS STARTED. FIRE DRILL CARRIED OUT, EMERGENCY CREW FOUND NO EVIDENCE OF FIRE AND THE AIRCRAFT WAS TOWED TO GATE FOR PASSENGERS DEPLANE. AIRCRAFT RELEASED ON MEL, APU INOP. 2L72 4F4 FRTA16WE E2EA 20060616001052006061600105NM 2006 6 16 CA060424008 120060421G612187620130101 SHAFT DHAV DHC8 DHC8301 1386003NM PWA PW120 PW123 NE HAMSTD14SF 14SF15 NE PROPELLER BROKEN W O OTHER F FLT CONT AFFECTED NRNOT REPORTED 1 CA FLIGHT CREW REPORTED EXCESS BACKLASH AND PROP SYNC DOES NOT SYNC. PROP WANDERING + - 5 TO 7 RPM. ENGINE SPRING STRUT ASSEMBLY REPLACED. AFTER DISASSEMBLY IN THE O/H SHOP, SHAFT P/N 87620130-101 WAS FOUND BROKEN AT POINT RIVET P/N MS204170AD3. THE SIZE OF THE RIVET HOLE LEAVES MINIMAL MATERIAL AROUND THE SHAFT, WHICH IS PRONE TO BREAKING UNDER VIBRATION. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20060616001072006061600107SW 2006 6 16 CA060424009 120060327G6700 YOKE BELL 206 206L3 1182108SW COCKPIT OBSTRUCTED W K NONE O OTHER ININSP/MAINT 1 CA WITH THE COLLECTIVE IN THE MID TO FULL DOWN POSITION AND THE CYCLIC FULL FORWARD AND LEFT THE RT CONTROL YOKE CONTACTS THE WINDSCREEN DEFROST HEATER PIPE. 1G71 3U H2SW 20060616001292006061600129WP 2006 6 16 CA060425001 120060423G7697VF741H11 RELAY ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE FUEL PUMP STUCK W O OTHER O OTHER TXTAXI/GRND HDL 1 CA 1482 AFTER PRIMING THE ENGINE, IT WAS NOTED THAT THE AUX FUEL PUMP WOULD NOT SHUT OFF. THE TROUBLE WAS TRACED TO THE CONTROL RELAY. THE INTERNAL POINTS IN THE RELAY HAD STUCK TOGETHER AND WERE KEEPING THE CIRCUIT CLOSED. THE RELAY WAS REPLACED, AND NO FURTHER DEFECTS WERE FOUND. 1G71 3O3 O H11NM 1E4 20060616001512006061600151CE 2006 6 16 CA060425002 120060425G571205230821 RIB CESSNA185 A185F 2072821CE CONT O520 IO520D 17032SO MCAULYD3A34 D3A34C403 GL RT WING CRACKED W O OTHER O OTHER NRNOT REPORTED 1 CA 7169 RIGHT WING RIB AT STN 40.125 AFT UPPER FLANGE CRACKED ALONG BEND RADIUS. 1H71 3O3 O 3A24 E5CE 5 CP47GL 20060616001542006061600154NE 2006 6 16 CA060425003 220060402G7200 ENGINE UROCOPEC135 EC135P1 8680990EU PWA PW206 PW206B 0 NE DAMAGED W O OTHER XTJENGINE FLAMEOUT ENGINE CASE PENETRATION WARNING INDICATION NRNOT REPORTED 1 CA BB0084 DURING FLIGHT, THE ENGINE EMITTED TWO LOUD NOISES ACCOMPANIED BY A CHIP DETECTOR WARNING INDICATION. TWO MINUTES LATER THE ENGINE FLAMED OUT ON APPROACH. INSPECTION REVEALED INTERNAL ENGINE DAMAGE, FRACTURE OF AN ENGINE CASE AND RELEASE OF A SEGMENT OF AN ACCESSORY DRIVE GEAR. PWC WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 1G72 3U3 UO H88EU E42NE 20060616001582006061600158NE 2006 6 16 CA060425004 220060405G7261 OIL SYSTEM CESSNA560 560XL 2076702CE PWA 545 PW545A NE ENGINE LEAKING W E ENGINE SHUTDOWN KB FLUID LOSS SMOKE/FUMES/ODORS/SPARKS CRCRUISE 1 CA DB0706 DURING CRUISE, ENGINE OIL PRESSURE WAS SEEN TO FLUCTUATE ACCOMPANIED BY SMOKE AND ODOR IN THE CABIN AIR. ENGINE OIL PRESSURE SUBSEQUENTLY REDUCED TO ZERO AND THE ENGINE WAS SHUT DOWN IN FLIGHT. PWC WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE, ONCE DETERMINED. 2L72 4F4 FRTA22CE E00059EN 20060616001592006061600159EA 2006 6 16 CA060425005 220060404G7200 ENGINE DHAV DHC6 DHC6 2802606EA PWA PT6 PT6A27 52043EA POWER LOSS W E ENGINE SHUTDOWN RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CLCLIMB 1 CA DURING CLIMB, THE ENGINE EXPERIENCED AN UNCOMMANDED POWER REDUCTION. THE ENGINE WAS SUBSEQUENTLY SHUT DOWN IN FLIGHT. P&WC WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 1H72 3T4 TRTA9EA E4EA 20060616001612006061600161NE 2006 6 16 CA060425006 220060405G7260 TOWERSHAFT AEROSPATR42 ATR42* 8680900EU PWA PW121 PW121 52124NE AGB DAMAGED W O OTHER XJ ENGINE FLAMEOUT WARNING INDICATION CRCRUISE 1 CA DURING CRUISE, THE ENGINE EXPERIENCED AN UNCOMMANDED SHUT DOWN. SUBSEQUENT INSPECTION REVEALED A DISTRESSED ACCESSORY DRIVE TOWER SHAFT. 2H72 4T4 TRTA53EU E20NE 20060619000522006061900052EA 2006 6 19 CA060425007 220060402G7200 ENGINE PIPER PA46 PA46350P 7104602SO PWA PT6 PT6* 52043EA MALFUNCTIONED W EA ENGINE SHUTDOWN UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 1 CA RR0052 DURING CRUISE, ENGINE SPEED INCREASED UNCOMMANDED ACCOMPANIED BY A MANUAL OVERRIDE LIGHT INDICATION. THE ENGINE WAS SHUT DOWN IN FLIGHT. FOLLOWING TWO UNSUCCESSFUL ATTEMPTS, THE ENGINE WAS RE-STARTED IN FLIGHT AND THE AIRCRAFT CONTINUED TO DESTINATION. P&WC WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 1L71 3O3 TRTA25SO E2NE 20060619000542006061900054NE 2006 6 19 CA060425008 220060410G7200 ENGINE MRCHTIS205 S20522R 8120412EU PWA JT15 JT15* 52060NE MALFUNCTIONED W E ENGINE SHUTDOWN J WARNING INDICATION TXTAXI/GRND HDL 1 CA 98023 DURING TAXI, THE ENGINE WAS FOUND NOT TO RESPOND TO THROTTLE INPUT AND SUBSEQUENTLY EXPERIENCED AN UNCOMMANDED POWER REDUCTION. THE ENGINE WAS SHUT DOWN. P&WC WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 1L71 3O4 T A9EU E1NE 20060619000592006061900059EA 2006 6 19 CA060425009 220060409G7200 ENGINE BEECH 90 C90A 1152911CE PWA PT6 PT6A21 52043EA MALFUNCTIONED W E ENGINE SHUTDOWN RJ PARTIAL RPM/PWR LOSS WARNING INDICATION APAPPROACH 1 CA PE0126 ON APPROACH, ENGINE TORQUE AND FUEL FLOW WERE SEEN TO FLUCTUATE. THE ENGINE WAS SUBSEQUENTLY SHUT DOWN IN FLIGHT. P&WC WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 1L72 3T4 TRT3A20 E4EA 20060619000622006061900062NE 2006 6 19 CA060425010 220060408G7200 ENGINE BRAERO1000 BAE1251000 1500287EU PWA 305 PW305B 52128NE MALFUNCTIONED W A UNSCHED LANDING RXJPARTIAL RPM/PWR LOSS ENGINE FLAMEOUT WARNING INDICATION CRCRUISE 1 CA 305031 DURING CRUISE, THE ENGINE SURGED FOLLOWED BY AN UNCOMMANDED POWER REDUCTION TO IDLE. THE WAS NO SUBSEQUENT RESPONSE TO THROTTLE INPUT. P&WC WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2L72 4F4 FRTA3EU E35NE 20060619000652006061900065NE 2006 6 19 CA060425011 220060407G7250 TURBINE BLADES BEECH 45 T34C1 1152016CE PWA PT6 PT6A25 52043NE ENGINE DAMAGED W A UNSCHED LANDING BRXSMOKE/FUMES/ODORS/SPARKS PARTIAL RPM/PWR LOSS ENGINE FLAMEOUT NRNOT REPORTED 1 CA 48053 DURING A TRAINING FLIGHT, THE ENGINE WAS REPORTED TO EMIT NOISES AND SMOKE FOLLOWED BY AN UNCOMMANDED POWER REDUCTION AND FLAME OUT. SUBSEQUENT INSPECTION REVEALED FRACTURED POWER TURBINE BLADES. P&WC WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 1L71 3T3 T A26CE E4EA 20060619002582006061900258NE 2006 6 19 CA060425012 220060416G7261 ENGINE AEROSPATR72 ATR72 EU PWA PW120 PW127 NE OIL SYS LEAKING W A UNSCHED LANDING KRJFLUID LOSS PARTIAL RPM/PWR LOSS WARNING INDICATION CLCLIMB 1 CA DURING CLIMB, ENGINE LOW OIL PRESSURE WARNING ACTIVATED. ENGINE SUBSEQUENTLY EMITTED A NOISE AND EXPERIENCED AN UNCOMMANDED POWER REDUCTION. POST-FLIGHT INSPECTION REVEALED NO OIL REMAINING IN THE ENGINE AND SEIZURE OF THE HIGH PRESSURE ROTOR. MFG WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE DETERMINED. 2H72 4T4 TRT E20NE 20060619002602006061900260NM 2006 6 19 CA060425013 120060425G2913623337 PUMP BOEING737 737522 138449FNM CFMINTCFM56 CFM563C1 13802EU HYD SYSTEM FAILED W O OTHER J WARNING INDICATION CRCRUISE 1 CA AFTER TAKEOFF, CREW NOTICED A LOW HYDRAULIC PRESSURE INDICATION WHEN THE LANDING GEAR WAS RETRACTED. LATER IN THE CLIMB THERE WAS AN INDICATION FOR LOSS OF HYDRAULIC PRESSURE FROM THE NR 1 ENGINE DRIVEN PUMP. THE CREW ELECTED TO RETURN TO BASE FOR MAINTENANCE DUE TO THE UNAVAILABILITY OF REPLACEMENT PARTS AT THEIR DESTINATION. THE AIRCRAFT RETURNED AND LANDED WITHOUT INCIDENT. MAINTENANCE REPLACED THE NR 1 ENGINE DRIVEN HYDRAULIC PUMP. AFTER SUCCESSFUL LEAK AND PRESSURE CHECKS, THE AIRCRAFT WAS RETURNED TO SERVICE. 2L72 4F4 FRTA16WE E21EU 20060619001452006061900145NE 2006 6 19 CA060425014 220060416G7200 ENGINE CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE FLAMED OUT W A UNSCHED LANDING XJ ENGINE FLAMEOUT WARNING INDICATION CLCLIMB 1 CA PC0880 DURING CLIMB, THE ENGINE EMITTED A LOUD NOISE AND FLAMED OUT. A DEADSTICK LANDING WAS SUCCESSFULLY ACCOMPLISHED. P&WC WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED. 1H71 3T3 T A37CE E4EA 20060619001462006061900146NE 2006 6 19 CA060425015 220060405G7240 TURBINE BLADES AYRES S2 S2RT34NORMAL0970106SO PWA PT6 PT6A34AG 52053NE ENGINE FRACTURED W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CLCLIMB 1 CA ON TAKEOFF, THE ENGINE WAS SEEN TO EMIT SMOKE AND SPARKS FROM THE EXHAUST. SUBSEQUENT INVESTIGATION REVEALED FRACTURED COMPRESSOR TURBINE BLADES. PWC WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE DETERMINED. 1L71 3T4 T A3SW E4EA 20060619001472006061900147NE 2006 6 19 CA060425016 220060417G7230 COMPRESSOR CESSNA500 560CESSNA 2076750CE PWA JT15 JT15D5 52112NE ENGINE STALLED W A UNSCHED LANDING BRJSMOKE/FUMES/ODORS/SPARKS PARTIAL RPM/PWR LOSS WARNING INDICATION CLCLIMB 1 CA 500037 DURING CLIMB, THE ENGINE EXPERIENCED COMPRESSOR STALLS ACCOMPANIED BY AN UNCOMMANDED POWER ROLL-BACK AND FUMES IN THE CABIN AIR. THE FLIGHT WAS DIVERTED. SUBSEQUENT INSPECTION REVEALED LP COMPRESSOR BOOST ROTOR DAMAGE. P&WC WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE DETERMINED. 2L72 4F4 FRTA22CE E25EA 20060619002692006061900269NE 2006 6 19 CA060425017 220060420G7200 ENGINE AEROSPATR72 ATR72212 8680945EU PWA PW120 PW127 NE MALFUNCTIONED W EC ENGINE SHUTDOWN ABORTED TAKEOFF RJ PARTIAL RPM/PWR LOSS WARNING INDICATION TOTAKEOFF 1 CA ON TAKEOFF AND CLIMB, THE ENGINE WAS REPORTED TO EXHIBIT PARTIAL POWER LOSS AND WAS SHUTDOWN IN FLIGHT. POST-FLIGHT INSPECTION REVEALED NO ANOMALIES. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2H72 4T4 TRTA53EU E20NE 20060619002752006061900275NE 2006 6 19 CA060425018 220060424G7200 ENGINE DHAV DHC8 DHC8* NM PWA PW120 PW123 NE HAMSTD14SF 14SF23 NE NR 1 MALFUNCTIONED W A UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CLCLIMB 1 CA ON TAKEOFF, THE NR 1 ENGINE AUTOFEATHERED AND THE NR 2 ENGINE UP TRIMMED. THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE. MFG WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20060619002762006061900276CE 2006 6 19 CA060425019 120060425G5414999800007 SKIN BEECH 99 99 1154002CE PWA PT6 PT6A27 52043EA HARTZLHCB3T HCB3TN3 GL LT NACELLE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 33536 VISUAL INSPECTION INDICATED A CRACK ON LT ENGINE NACELLE IB SKIN JUST FORWARD OF WING LEADING EDGE. CRACK RAN VERTICALLY JUST AFT OF IB NACELLE INSPECTION PANEL. A RIVET THAT ATTACHES THE NACELLE FILLET STRIP TO THE WING WAS INCLUDED IN THE CRACK. THERE WAS NO REPORT OF A HARD LANDING AND NO ADJACENT STRUCTURE IS DAMAGED. 1L72 3T4 T A14CE E4EA 6 CP15EA 20060619002772006061900277NE 2006 6 19 CA060425020 220060422G7320 HMU CESSNA500 550 2076604CE PWA 530 PW530A NE ENGINE MALFUNCTIONED W A UNSCHED LANDING RFJPARTIAL RPM/PWR LOSS FLT CONT AFFECTED WARNING INDICATION CRCRUISE 1 CA ON TAKEOFF ROLL, ENGINE POWER ROLLED BACK MARGINALLY AND WAS CORRECTED BY A THROTTLE ADJUSTMENT. POWER FLUCTUATIONS WERE REPORTED DURING CLIMB. IN CRUISE, POWER ROLLED BACK UNCOMMANDED AND THE ENGINE WAS FOUND NOT TO RESPOND TO THROTTLE INPUT. THE AIRCRAFT DIVERTED AND ON DESCENT ENGINE THROTTLE AUTHORITY WAS REGAINED. MFG WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 1L72 4F4 F A22CE E00053EN 20060807000522006080700052CE 2006 8 7 CA060426001 120060405G71207120000101 MOUNT SYMPHOSA160 SA160 05619SUCE LYC O320 O320D2A 41508EA ENGINE DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) INSPECTION FOR ISSUANCE OF A C OF A AIRCRAFT TOTAL TIME: 2.8 HRS DURING THE INSPECITON OF THIS AIRCRAFT BY CIVIL AVIATION INSPECTOR, IT WAS NOTED THAT AN ENGINE CONTROL SUPPORT BRACKET WAS CONTACTING THE LOWER TUBE OF THE ENGINE MOUNT. NO DAMAGE TO THE ENGINE MOUNT WAS NOTICED BUT THE PAINT FINISH WAS MARKED BY CHAFFING. ACTION TAKEN; ENGINE MOUNT BRACKET 760-02043-01 WAS SLIGHTLY RELOCATED ON 760-02041-01 CONTROL SUPPORT BRACKET TO ADD CLEARANCE FOR ENGINE VIBRATIONS AND MOVEMENTS. (TC# 20060426001) 1H71 3O3 ONTA46CE E274 20060621000892006062100089GL 2006 6 21 CA060426003 220060424G7200 ENGINE CVAC 340 340CVAC 242270AWP ALLSN 501D 501D22 03005GL HAMSTD54H 54H60 NE FAILED W EA ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 CA 5056 501636 (CAN) DURING CRUISE, THE CREW NOTICED THE TIT SPIKED TO 1100 DEGRESS F. THE HORSEPOWER DECREASED AND THE ZONE 1 FIRE BELL SOUNDED. THE E HANDLE AWAS PULLED AND THE ENGINE WAS SHUT DOWN AND THE PROPELLER FEATHERED. THE AIRCRAFT LANDED. MAINTENANCE CREW INSPECTED THE AIRCRAFT AND NO STRUCTURAL DAMAGE WAS NOTED. THE ENGINE QEC WILL BE REPLACED WITH A SERVICEABLE UNIT. THE ENGINE IS BEING RETURNED AND WILL BE INSPECTED TO DETERMINE THE CAUSE OF THE FAILURE. (TC NR 20060426003) 2L72 4R4 T 6A6 E282 6 CP906 20060621001162006062100116CE 2006 6 21 CA060427000 120060403G712050980002185 MOUNT BEECH 200 200BEECH 1152920CE PWA PT6 PT642A NE HARTZLHCB3T HCB3TN3 GL ENGINE LOOSE W K NONE O OTHER ININSP/MAINT 1 CA (CAN) BOTH LOWER ENGINE MOUNT FITTINGS P/N 50-980002-185 CONTAINING THE ENGINE MOUNT BARREL NUTS WERE FOUND LOOSE BY LIFTING ON THE NON ENGINE MOUNT AND OBSERVING THE LOWER LEGS OF THE MOUNT IN RELATION TO THE FIREWALL. THE OB FITTING HAD MORE MOVEMENT THAN THE IB. AN ENGINE MOUNT WOULD TAKE A HARDER LIFT TO SHOW MOVEMENT. THE FASTENERS ARE VISIBLE THROUGH THE NACELLE SIDE HATCHES. IF LOOSE THEY COULD EXHIBIT HEAVY SMOKING AND A BLACK GREASE LIKE BUILDUP AT EACH FASTENER. (TC NR 20060427000) 1L72 4T4 T A24CE E4EA 6 CP15EA 20060621001172006062100117EA 2006 6 21 CA060427001 220060419G852013S19646 GEAR CESSNA172 172S 2072439CE LYC IO360 IO360L2A EA CRANKSHAFT CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 2154 2154 L2866351A (CAN) CRANKSHAFT GEAR HAD TWO SMALL MPI INDICATIONS ON ONE GEAR TOOTH. THE GEAR ALSO HAD VISUAL DAMAGE TO 3 GEAR TEETH. CRANKSHAFT GEAR WAS REMOVED FROM SERVICE AND REPLACED WITH NEW GEAR. (TC NR 20060427001) 1H71 3O3 ONT3A12 1E10 20060621001182006062100118EA 2006 6 21 CA060427002 220060413G852074502 CONNECTING ROD PIPER PA25 PA25235 7102504SO LYC O540 O540B2B5 41532EA ENGINE GALLED W K NONE O OTHER ININSP/MAINT 1 CA 192 L893440 (CAN) CONNECTING RODS REMOVED FROM ENGINE AT 192.0HRS DUE TO PROP STRIKE. RODS INSPECTED IAW SB439A, AND ALL 6 RODS HAD FRETTING AND GALLING ON THE CONNECTING ROD BEARING BORE SURFACE. THE RODS WERE REPAIRED AND RETURNED TO SERVICE. THE PREVIOUS OVERHAUL RECORDS HAD NOT INDICATED COMPLIANCE WITH SB439A. (TC NR 20060427002) 1L71 3O3 O 2A10 E295 20060621001202006062100120SW 2006 6 21 CA060427003 120060419G291027810061011 LINE SWRNGNSA227 SA227* SW GARRTTTPE331TPE33111U 01514WP MCAULY4HFR344HFR34C652 NE HYDRAULIC SYS LEAKING W K NONE O OTHER ININSP/MAINT 1 CA (CAN) AIRCRAFT WAS SITTING IN THE HANGER WHEN MAINTENANCE NOTICED A PUDDLE OF HYD FLUID ON THE GROUND UNDER THE AIRCRAFT BY THE LT CENTER SECTION, STATION 27.103. THE LINE HAD A HAIRLINE CRACK AT THE FWD BEND INSIDE THE WING CENTER SECTION. THE LINE WAS PART OF THE GEAR UP PRESSURE SYSTEM. THE LINE WAS REPLACED AND GEAR SWINGS CARRIED OUT SERVICIBLE. (TC NR 20060427003) 2L72 4T4 TRTA5SW E4WE 6 C3PNE 20060621001222006062100122NM 2006 6 21 CA060427004 120060425G2130 SHUTOFF VALVE BOEING727 727233 138408ANM PWA JT8 JT8D15 52051NE CABIN PRESSURE MALFUNCTIONED W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA (CAN) CLIMBING THROUGH FL20 THE F/E ADVISED OF PRESSURIZATION PROBLEMS. AFTER REDUCING TO 10,000 FT. CABIN INDICATED 10,000 WITH 3 PSI DIFF.WHEN THRUST REDUCED THE DIFF WAS 0. THE AIRCRAFT RETURNED TO POINT OF DEPARTURE. MAINTENANCE REPLACED THE PRESSURIZATION CONTROL PANEL AND THE PRESSURE CONTROL MODULATING SOV. THE SYSTEM WAS FUNCTION CHECKED AND THE AIRCRAFT RETURNED TO SERVICE. (TC NR 020060427004) 2L73 4F4 FRTA3WE E2EA 20060621001242006062100124 2006 6 21 CA060427005 420060425G3497688160 WIRE PIPER PA42 PA42720 7104212SO PWA PT6 PT6A61 52043EA HARTZLHCB3T HCB3TN3 GL SWITCH CORRODED W HA DEACTIVATE SYST/CIRCUITSUNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CLCLIMB 1 CA 9201 (CAN) DURING CLIMB FLIGHT CREW SMELLED AND VISUALLY CONFIRMED SMOKE IN COCKPIT. THEY SHUTOFF WINDSHIELD HEAT AND PITOT/STALL HEAT AND SMOKE DISSIPATED. FLIGHT RETURNED TO POINT OF DEPARTURE FOR INVESTIGATION. MAINTENANCE FOUND SURFACE CORROSION ON PITOT/STALL HEAT SWITCH WIRING CONNECTORS. CONNECTORS AND SWITCH REPLACED NEW. OPERATIONS CHECK C/O SATISFACTORY AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20060427005) 1L72 4T4 T A23SO E4EA 6 CP15EA 20060621001272006062100127EA 2006 6 21 CA060427007 120060425G2910AN62498 CHECK VALVE CNDAIRCL215 CL2151A10 1900320EA PWA R1340 CWASP 52016NE HAMSTD43E 43E60 NE HYD SYSTEM SEPARATED W A UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CLCLIMB 1 CA 4050 4050 (CAN) AFTER COMPLETING A WATERDROP, BOTH WATERDOORS FAILED TO CLOSE AND LOCK. AC EXPERIENCED A COMPLETE HYDR FAILURE CAUSED BY FAILURE OF ONE-WAY CHECK VALVE IN MAIN PRESSURE LINE AT WING STA 54 ON RT WING LE. THIS CHECK VALVE'S PURPOSE IS TO STOP HYD PRESSURE FLOWING BACK TO ENG DRIVEN PUMP WHEN USING GROUND TEST EQUIPMENT, AUXILARY HYD PUMP. AC PERFORMED EMERGENCY LANDING GEAR EXTENSION, RETURNED TO BASE, LANDED SAFELY. CHECK VALVE HSG IS CONSTRUCTED OF ALUMINUM. AFTER RECEIVING REPORTS OF FAILURE OF THIS CHECK VALVE, MFG PRODUCED SB 215-0466(STAINLESS STEEL CHECK VALVES)TO RECTIFY THIS PROBLEM. OUR ORGANIZATION WILL EMBODY THIS SB. ORDERED THESE CHECK VALVES(2 PER AC) TO BE INSTALLED. (TC NR 20060427007) 2H72 4R3 RRTA14EA ATC14 6 CP871 20060621001282006062100128WP 2006 6 21 CA060428001 220060427G7261P1070 OIL FILTER SWRNGNSA226 SA226TC 8780404SW GARRTTTPE331TPE33110UA 01514WP HARTZLHCE4N HCE4N3 NE ENGINE BROKEN W K NONE O OTHER ININSP/MAINT 1 CA 45 (CAN) DURING A ROUTINE DAILY INSPECTION THE OIL FILTER BYPASS PIN WAS FOUND POPPED INDICATING AN OBSTRUCTED OIL FILTER. UPON INSPECTION OF THE FILTER IT WAS FOUND TO BE BROKEN AT THE OIL INLET MOUNTING FLANGE. PREVIOUS SDR'S HAVE BEEN ISSUED FOR THIS PROBLEM, REFERENCE SDR NR 20031024003, 20031024002, 20031024004. A OIL SAMPLE WAS COMPLETED ON THE ENGINE. THE FILTER WHICH WAS REMOVED WAS A PMA FILTER WITH A PART NUMBER OF P-1070. OEM FILTER NORMALLY USED IS A 3001436-1. (TC NR 20060428001) 2L72 4T4 TRTA8SW E4WE 5 CP10NE 20060621001302006062100130 2006 6 21 CA060428002 420060428G3421175E28CT TRANSFORMER CNDAIRCL601 CL6012A12 1900303EA GE CF34 CF343A 30015NE INDICATOR INOPERATIVE W A UNSCHED LANDING H ELECT. POWER LOSS-50 PC CRCRUISE 1 CA (CAN) LOSS OF NR 1 MASI, NR 1 ALTIMETER, FDR, NR 1 ADI PITCH AND ROLL INFO, COMPASS INFO, NR 1 ESSENTIAL BUS AND LOSS 26 VAC. CAUSE OF FAULT FOUND TO BE BROKEN WIRES AT T2XD POST NR 3. TRANSFORMER LOCATED ON BACK OF C/B PANEL C. (TC NR 20060428002) 2L72 4F4 FRTA21AE E15NE 20060621001312006062100131SO 2006 6 21 CA060428003 120060425G2912460635 FILTER PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA HARTZLHCE3Y HCE3YR2A GL HYD SYSTEM CRACKED W O OTHER KJ FLUID LOSS WARNING INDICATION DEDESCENT 1 CA (CAN) ON LANDING THE AIRCRAFT LOST HYD PRESSURE AND A EMERGENCY EXTENTION WAS SUCCESSFULLY CARRIED OUT. ON INSPECTING THE CAUSE OF THE HYD LEAK THE RT FILTER BOWL WAS FOUND TO BE LEAKING. WHEN REMOVING THE BOWL THE THIRD THREAD DOWN FROM THE TOP OF THE BOWL WAS FOUND CRACKED (ABOUT HALF WAY AROUND THE BOWL) ALLOWING THE FILTER BOWL TO TIP TO A ANGLE ALLOWING THE HYD PRESSURE TO BLOW THE FLUID OUT. A NEW ASSY WAS INSTALLED WITH NO MORE PROBLEMS REPORTED. (TC NR 20060428003) 1L72 3O3 O A20SO E14EA 5 CP33EA 20060623000412006062300041NE 2006 6 23 CA060501001 220060426G7200 ENGINE CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE FAILED W A UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 1 CA 19265 (CAN) DURING CRUISE THE ENGINE EMITTED A LOUD NOISE ACCOMPANIED BY AN UNCOMMANDED POWER LOSS. THE ENGINE WOULD NOT RESPOND TO THROTTLE INPUT. A SUCCESSFUL DEAD-STICK LANDING WAS ACCOMPLISHED. MFG WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060501001) 1H71 3T3 T A37CE E4EA 20060623001532006062300153EA 2006 6 23 CA060501002 220060426G7200 ENGINE BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA FLAMED OUT W C ABORTED TAKEOFF XJ ENGINE FLAMEOUT WARNING INDICATION TOTAKEOFF 1 CA FA0130 (CAN) ON TAKEOFF ROTATION THE ENGINE EMITTED A LOUD NOISE AND FLAMED OUT. TAKEOFF WAS ABORTED. MFG WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060501002) 2H72 4T4 TRTA13NM E00062EN 20060623001542006062300154EA 2006 6 23 CA060501003 220060407G7321324475520 FUEL CONTROL BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA ENGINE FAILED W EA ENGINE SHUTDOWN UNSCHED LANDING R PARTIAL RPM/PWR LOSS CRCRUISE 1 CA 1650 (CAN) DURING CRUISE THE ENGINE EXPERIENCED AN UNCOMMANDED POWER ROLL-BACK. THE ENGINE WAS SHUTDOWN IN FLIGHT. THE FUEL CONTROL UNIT WAS SUBSEQUENTLY REPLACED. (TC NR 20060501003) 1L72 4T4 T A24CE E4EA 20060623001552006062300155SW 2006 6 23 CA060501004 120060428G56103600151 WINDOW GULSTM690TP 690D 3970405SW GARRTTTPE331TPE3315 01514WP ROTOL R306 R306382F7 GL COCKPIT CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) COCKPIT LT OVERHEAD WINDOW SHOWED SIGNS OF PRESSURIZATION LEAK. WINDOW REMOVED TO REPLACE GASKET AND FOUND WINDOW CRACKED. CRACKS ORIGINATING FROM 4 SCREW ATTACHMENT HOLES. NEW WINDOW INSTALLED. (TC NR 20060501004) 1H72 3T4 T 2A4 E4WE 6 CP8EU 20060623001562006062300156SW 2006 6 23 CA060501005 120060428G56103600152 WINDOW GULSTM690TP 690D 3970405SW GARRTTTPE331TPE3315 01514WP ROTOL R306 R306382F7 GL COCKPIT CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) COCKPIT RT OVERHEAD WINDOW REMOVED FOR INSPECTION AFTER FINDING THE LT WINDOW CRACKED. WINDOW FOUND TO HAVE 2 CRACKS ORIGINATING FROM 2 SCREW ATTACHMENT HOLES. WINDOW REPLACED WITH NEW. (TC NR 20060501005) 1H72 3T4 T 2A4 E4WE 6 CP8EU 20060623001582006062300158CE 2006 6 23 CA060501006 120060417G71601019100203 VANE BEECH 200 200BEECH 1152920CE PWA PT6 PT642A NE MCAULY3AF34C3GFR34C703 GL INTAKE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) VANE FOUND SEVERELY CRACKED ON VISUAL INSPECTION. CRACK APPEARS TO HAVE STARTED AT LEADING EDGE OF VANE FROM THE HINGE AREA. HINGE WAS FOUND CRACKED ALSO. DAMAGE POSSIBLY ACCELERATED DUE TO FLUTTER OF THE DAMAGED VANE. (TC NR 20060501006) 1L72 4T4 T A24CE E4EA 5 CP60GL 20060623001592006062300159CE 2006 6 23 CA060502000 120060424G57305012016318 SKIN BEECH 100 100BEECH 1152916CE PWA PT6 PT6A28 EA HARTZLHCD4N3HCD4N3A GL WING CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) SKIN CRACKED AT HILOC FASTENERS ATTACHING SKIN TO AFT FLANGE OF WING ATTACH FITTING. CONDITION EVIDENT ON BOTH LT AND RT SKINS OF WING CENTER SECTION. MFG HAS A FIELD REPAIR TO DEAL WITH THESE CRACKS. CRACKS FOUND VISUALLY WITH WING BOLT COVERS REMOVED. (TC NR 20060502000) 1L72 3T4 T A14CE E4EA 5 CSTC 20060623001902006062300190EU 2006 6 23 CA060502002 120060427G2497 WIRE AIRBUS310 A310304 3930339EU GE CF6 CF680C2A5 NE BURNED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING ROUTINE INSPECTION, FOUND THE ELECTRICAL OUTLET WIRE FIN 8ME CHAFED ON FRAME 17 BETWEEN STR 28 AND 29 RT SIDE. THE GROMMET PROTECTION HAD FALLEN OFF FROM THE FRAME AND WIRE WAS HANGING ON THE FRAME WITH THE RESULT OF ARCING AND FRAME DAMAGE. THE WIRING AND FRAME WAS REPAIRED. A FLEET CAMPAIGN HAS BEEN INITIATED TO INSPECT THIS AREA ON ALL A-310. (TC NR 20060502002) 2L72 4F4 FRTA35EU E13NE 20060626000632006062600063EU 2006 6 26 CA060502003 120060422G3397 WIRE AIRBUS310 A310304 3930339EU GE CF6 CF680C2A5 NE NAV LIGHT BURNED W O OTHER O OTHER TXTAXI/GRND HDL 1 CA (CAN) DURING AIRCRAFT TOWING, THE NAV 2 POSITION LIGHT CB POPPED. UNABLE TO RESET. DURING INVESTIGATION, FOUND THE 4 WIRES FROM THE LIGHT UNIT ASSY (7LA) BURNED ABOUT 8 INCHES LONG. WIRING WAS REPLACED AND LIGHT ASSEMBLY AND RELAY WERE REPLACED AS PRECAUTIONARY MEASURE. SB 30-0627-33-SB01 WILL BE INCORPORATED IN ALL AIRCRAFT TO UPGRADE THE NAVIGATIONAL LIGHT SYSTEM AND PREVENT THIS TYPE OF PROBLEM. (TC NR 20060502003) 2L72 4F4 FRTA35EU E13NE 20060703000032006070300003NE 2006 7 3 CA060502004 220060424G72503020159 SHROUD PWA PT6 PT6A135 52043NE TURBINE DISTORTED W K NONE O OTHER ININSP/MAINT 1 CA PCE35094 DURING HOT SECTION KIT REPAIR OF A PT6A-135 ENG, CT SHROUD SEGMENT-RETAINING RING WAS FOUND LOOSE AND PARTIALLY DISENGAGED FROM CT SHROUD HOUSING RETAINING GROOVE. MINOR SHIFTING OF CT SHROUD SEGMENTS WERE NOTED (SEE PHOTOGRAPH NR 1 AND 2). THE CT SHROUD SEGMENT-RETAINING RING (P/N 3020159) WAS OF PRE SB 1627 CONFIG AND CT SHROUD SEGMENTS (P/N 3053094) WERE OF PRE SB 1628 CONFIGURATION QTY 7-RUB SPOTS WERE NOTED ON THE CT SHROUD SEGMENTS WITH RUB ON CT BLADES. CT SHROUD SEGMENT-RETAINING RING WAS FOUND DISTORTED AND PARTIALLY DISENGAGED FROM THE RETAINING GROOVE OF CT SHROUD HOUSING. NO OVER HEATING/BURNING OF HOT SECTION PARTS NOTED. INSPECTION OF CT SHROUD HOUSING WAS DONE AND ROUNDNESS OF ALL CRITICAL DI 4 T E4EA 20060703000042006070300004 2006 7 3 CA060502005 120060428G3240266278 BRAKE ASSY MLG DAMAGED W O OTHER O OTHER NRNOT REPORTED 1 CA 2855 658 FOLLOWING MX ONE OF OUR AME NOTICED THAT ONE OF OUR SPARE BRAKE ASSY P/N 2-1605-2 S/N 0378 MADE BY GOODRICH SEAM DIFFERENT FROM THE ONE REMOVED FROM THE A/C. THE REMOVED BRAKE SHOWN 2 INNER SUPPORT FLANGE OF .5 INCH AND THE SPARE ONE SHOWN ONE SINGLE FLANGE OF 1.375 INCHES. THE DOUBLE FLANGE IS WELL IDENTIFIED ON THE MANUFACTURER CMM BUT NO SPECIFICATION OF THE SINGLE ONE. THE MANUF REQUIRED THE UNIT FOR INVESTIGATION. ON THE PRELIMINARY STATUS THIS UNIT IS NOT PER MANUF SPEC DRAWING. INVESTIGATION STILL IN PROGRESS. THIS BRAKE ASSY IS SHOWING THE FOLLOWING DATA, P/N 266-278 CHG C, P/N 260-903 CHG B, S/N 0378 DATE OF MAN 08-01, INSP NR 04-90. 20060720003212006072000321EA 2006 7 20 CA060502006 120060430G29136307901 PUMP DHAV DHC4 DHC4A 2800304EA HYDRAULIC SYS FAILED W O OTHER JF WARNING INDICATION FLT CONT AFFECTED CRCRUISE 1 CA AFTER REPLACING A PUMP DUE TO TIME-EX, NEXT 3 PUMPS INSTALLED FAILED. ALL FAILED DUE TO SHAFT SHEARING. FILTERS PULLED AFTER 1ST FAILURE, THERE WAS ONLY TRACE EVIDENCE OF METAL AND NOTHING ELSE. FILTER WAS CLEANED, REINSTALLED IAW MM. AFTER NEXT 2 FAILURES FILTERS PULLED AGAIN WITH NO METAL FINDINGS. FIRST FAILED PUMP, DISASSEMBLED IT TO TRY AND FIND CAUSE FOR FAILURE. DISASSEMBLY FOUND 2 OF PISTONS SEIZED DUE TO OVERHEATING AND SEPARATED FROM SWASH PLATE. 1 PISTON HAD END TORN OFF AND HAD GENERATED A FAIR AMT OF METAL CONTAM INTERNALLY TO PUMP. STILL INVESTIGATING CAUSE OF OVERHEATING THAT FAILED ORIG PUMP. UNABLE TO CHECK OTHER 2, SHIPPED ALREADY. AWAITING THE REPAIR SHOPS REPORT. 2H72 4R 1A19 20060705000312006070500031 2006 7 5 CA060502008 420060427G2562MN1300 BATTERY ACK PIPER PA34 PA34200T 7103406SO CONT O360 TSIO360E 17025SO HARTZLHCC2Y BHCC2YF2 GL ELT LEAKING W O OTHER K FLUID LOSS NRNOT REPORTED 1 CA 5 026049 (CAN) ELT BATTERIES LEAKED. (TC NR 20060502008) 1L72 3O3 O A7SO E9CE 5 CP920 20060703000372006070300037SW 2006 7 3 CA060503001 120060426G2997212075369001 WIRE BELL 212 212 1181420SW PWA PT6T PT6T3 52045EA CLOG INDICATOR BROKEN W O OTHER N FALSE WARNING NRNOT REPORTED 1 CA 181 DURING ROUTINE INSPECTION, THE INDICATOR WAS SHOWING RED INDICATING FILTER BYPASS CONDITION. UPON INVESTIGATION BY AME NONE OF THE FILTERS HAD BYPASSED ON THE INTEGRATED VALVE AND FILTER ASSEMBLY. AT THIS TIME IT WAS DETERMINED THAT THE CLOGGING INDICATOR WAS THE PROBLEM AND THIS WAS REPLACED AND FUNCTION CHECKED OK. 6.1 HOURS LATER THE SAME CONDITION WAS NOTICED ON THE CLOG INDICATOR AND THE WIRES WERE FOUND TO HAVE BROKEN OFF. THE WIRES WERE SOLDERED BACK AND INDICATOR REPLACED AT A LATER DATE. 1G71 4U4 U H4SW E22EA 20060703000382006070300038CE 2006 7 3 CA060503002 120060501G243523078019 STARTER GEN BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE HARTZLHCE4A HCE4A3I NE LT ENGINE SEIZED W E ENGINE SHUTDOWN J WARNING INDICATION CRCRUISE 1 CA 30704 IN CRUISE, LT GEN FAIL LIGHT ILLUM. ATTEMPT TO RESET GEN, IT WOULD NOT COME ON LINE. AFTER GEN FAILURE, LT ENG FIRE WARN IND ALSO CAME ON. LT ENG WAS SHUT DOWN AND ENG FIRE BOTTLE WAS DISCHARGED AS PER RELATED CHECKLIST. LANDED SAFELY. MX INSPECTED A/C, FOUND LT STARTER-GEN FAILED INTERNALLY AND PAINT ON UNIT BLISTERED INDICATING IT HAD DRASTICALLY OVERHEATED. INVESTIGATION REVEALED STARTER-GEN DRIVE SPLINE HAD SHEARED. APPROPRIATE INSPECTIONS CARRIED OUT PER MM. STARTER GEN AND FIRE BOTTLE REPLACED, A/C RETURNED TO SERVICE. FIRE WIRE IS LOCATED IN CLOSE PROX STARTER-GEN. STARTER-GEN INSTALLED PREV DAY IN REPAIRED CONDITION, AT TIME OF FAILURE STARTER-GEN HAD ONLY ACCUMULATED 1.6 HOURS SINCE REPAIR. 2L72 4T4 TRTA24CE E26NE 5 CP10NE 20060703000392006070300039CE 2006 7 3 CA060503003 120060501G243523078019 STARTER GEN BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE HARTZLHCE4A HCE4A3I NE LT ENGINE FAILED W E ENGINE SHUTDOWN J WARNING INDICATION CRCRUISE 1 CA IN CRUISE, LT GEN FAIL LIGHT ILLUM. CREW ATTEMPT RESET, GEN BUT WOULD NOT COME ON LINE. AFTER GEN FAILURE, LT ENG FIRE WARNING INDICATION ALSO CAME ON. LT ENG WAS SHUT DOWN AND ENG FIRE BOTTLE DISCHARGED PER CHECKLIST. A/C LANDED SAFELY. MX INSPECT A/C AND FOUND LT STARTER-GEN FAILED INTERNALLY AND PAINT ON UNIT WAS BLISTERED INDICATING DRASTICALLY OVERHEATED. INVESTIGATION REVEALED, STARTER-GEN DRIVE SPLINE SHEARED. INSPECTIONS PER MM. STARTER GEN AND FIRE BOTTLE REPLACED, A/C RETURNED TO SERVICE. FIRE WIRE IS LOCATED IN CLOSE PROXIMITY TO STARTER-GEN. STARTER-GEN INSTALLED PREVIOUS DAY IN A REPAIRED CONDITION, AT TIME OF FAILURE STARTER-GEN HAD ONLY ACCUMULATED 1.6 HOURS SINCE REPAIR. 2L72 4T4 TRTA24CE E26NE 5 CP10NE 20060626000102006062600010CE 2006 6 26 CA060503004 120060501G2435 SHAFT LEARSIEGLER BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE HARTZLHCE4A HCE4A3I NE STARTER GEN SHEARED W E ENGINE SHUTDOWN J WARNING INDICATION CRCRUISE 1 CA 307 94094 IN CRUISE, LT GEN FAIL LIGHT ILLUMINATED. ATTEMPTED TO RESET GEN BUT IT STILL WOULD NOT COME ON LINE. SHORTLY AFTER GEN FAILURE, LT ENG FIRE WARNING IND ALSO CAME ON. LT ENG WAS SHUTDOWN AND ENG FIRE BOTTLE WAS DISCHARGED. MX INSPECTED A/C. FOUND LT STARTER GEN HAD FAILED INTERNALLY AND PAINT ON UNIT WAS BLISTERED INDICATING IT HAD DRASTICALLY OVERHEATED. ALSO REVEALED STARTER GEN DRIVE SPLINE HAD SHEARED. INSP CARRIED OUT IAW MM. STARTER GEN, FIRE BOTTLE WERE REPLACED, AND A/C RETURNED TO SERV. NOTED FIRE WIRE IS LOCATED IN CLOSE PROX TO STARTER/GEN. STARTER/GEN WAS INSTALLED PREVIOUS DAY IN A REPAIRED CONDITION, AT TIME OF FAILURE STARTER/GEN HAD ONLY ACCUMULATED 1.6 HRS SINCE REPAIR. 2L72 4T4 TRTA24CE E26NE 5 CP10NE 20060703000402006070300040NM 2006 7 3 CA060503007 120060427G5270AE4888100 SWITCH BOEING727 727223 1384074NM PWA JT8 JT8D15A 52051NE CARGO DOOR FAILED W A UNSCHED LANDING N FALSE WARNING CRCRUISE 1 CA AT FL380, MAIN CARGO DOOR LIGHT ILLUMINATED ACCOMPANIED BY "LATCH LOCK PIN NOT ENGAGED" ON DOOR CONTROL PANEL. A/C TURNED BACK AND DURING DESCENT LIGHTS REMAINED ILLUMINATED UNTIL CABIN PRESSURE WAS REDUCED TO MINIMUM AT WHICH POINT BOTH LIGHTS HAVE EXTINGUISHED. UPON ARRIVAL, MAINTENANCE FOUND THAT FORWARD LATCH PIN MICRO-SWITCH TRIGGER PLATE COTTER PIN WAS INFERRING WITH A RIVET TAIL ON THE DOOR SKIN DOUBLER. THIS WAS A POSSIBLE CAUSE FOR DOOR INDICATION. AFTER ACCESS TO THE AREA WAS PROVIDED BY REMOVING THE ACCESS PANEL, TRIGGER PLATE WAS FREED UP BY REPOSITIONING THE COTTER AND OPERATIONALLY CHECKED SERVICEABLE. SWITCH AND PLATE ASSY REPLACED AS A PRECAUTION. 2L73 4F4 F A3WE E2EA 20060703000412006070300041NE 2006 7 3 CA060503008 220060428G7310 B-NUT SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1D1 NE ENGINE FUEL LOOSE W E ENGINE SHUTDOWN B SMOKE/FUMES/ODORS/SPARKS TXTAXI/GRND HDL 1 CA DURING T/S OF START SYS OF SISTER A/C, START INJECTOR ON RT SIDE OF ENG WAS REMOVED FOR COMPARISON INSPECTION. AFTER INSPECTION ORIG INJECTOR WAS INSTALLED. NO CROSS CHECK INSPECTION, NOR GROUND-RUN WERE COMPLETED. NEXT DAY PILOT NOTED A STAGNATED/HUNG START, AND ADVANCED THROTTLE TO EMERG POSITION TO LIGHT OFF ENGINE. ENG WAS THEN SHUT DOWN AND MX WAS CALLED. ENGINEER ON SITE GOT PILOT TO ATTEMPTED ANOTHER START AND VISUALLY NOTICED SPRAYING FUEL IN ENG BAY, START WAS ABORTED. UPON CLOSE INSPECTION, B-NUT ON START INJECTOR LINE WAS FOUND TO HAVE NO TQE AND LOOSE ON TEE FITTING. TIGHTENED LINE TO PROPER TQ AND THE START WAS ATTEMPTED AGAIN. PERFORMED START/GROUND-RUN/LEAK CHECK ALL SYSTEMS FUNCTIONIN1G71 3U3 U H9EU E19EU 20060703000422006070300042CE 2006 7 3 CA060503009 120060402G7800780000 EXTRACTOR BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA EXHAUST GAS CRACKED W K NONE O OTHER ININSP/MAINT 1 CA DURING INSPECTION THE ENGINEER NOTICED A CRACK IN ONE OF THE EXHAUST GAS EXTRACTORS. FURTHER INVESTIGATION ON THE REMAINING EXHAUST GAS EXTRACTORS REVEALED CRACKS AS WELL. THE PARTS WERE REPAIRED AND REINSTALLED. 1L72 4T4 T A24CE E4EA 20060703000432006070300043EA 2006 7 3 CA060503010 120060420G5610601R3303318 WINDSHIELD CNDAIRCL600 CL6002C10 1390015EA GE CF34 CF348C1 NE COCKPIT CRACKED W A UNSCHED LANDING O OTHER DEDESCENT 1 CA RIGHT FORWARD WINDSHIELD CRACKED DURING DESCENT FROM 350 TO 330. REMOVED AND INSTALLED F/O'S WINDSHIELD. RIGHT FORWARD WINDSHIELD CRACKED DURING DESCENT FROM 350 TO 330. REMOVED AND INSTALLED F/O'S WINDSHIELD. 2L72 4F4 FRTA21EA EOOO63EN 20060719000152006071900015 2006 7 19 CA060504001 220060317G7321442324 HMU BOMBDRBD700 BD7001A10 1390006GL LT ENGINE ACTIVATED W C ABORTED TAKEOFF R PARTIAL RPM/PWR LOSS TXTAXI/GRND HDL 1 CA 173 (CAN) CREW TAXIED OUT,TESTED THRUST REVERSER JUST PRIOR TO TAKEOFF. PLACED BOTH PWR LEVERS IN T/O DETENT, STARTED T/O ROLL. FELT AC SWERVE LT OF CTR LINE. CREW NOTICED LT ENG WAS STILL AT IDLE WITH PWR LEVER IN TAKEOFF DETENT. CREW ABORTED TAKEOFF. NO EICAS MESSAGES WERE POSTED DURING THIS EVENT. LT AND RT N1 BUGS BOTH TARGETED T/O PWR ON DISPLAY DURING THIS EVENT. CREW TAXIED OFF RUNWAY. CREW TRIED TO RUN-UP LT ENG ON RAMP, IT WOULD NOT ACCELERATE. NO EICAS MESSAGES POSTED. CHECKED TIME LIMITED DISPATCH, STATUS CLEAR FOR LT ENG. LT ENG EEI DOWNLOAD REVEALED THAT HMU METERING VALVE DID NOT APPEAR TO RESPOND TO THRUST COMMAND. HMU REMOVED AND REPLACED. BOTH ECU'S ALSO REPLACED. (TC NR 20060504001) 2L72 4F RTT00003NY 20060703000972006070300097EA 2006 7 3 CA060504002 120060327G27304006719904 DRIVE ASSY DHAV DHC7 DHC7102 2802708EA PWA PT6 PT6A50 52043EA HAMSTD24PF 24PF305 GL ELEVATOR SERVO FAILED W O OTHER FE FLT CONT AFFECTED VIBRATION/BUFFET CLCLIMB 1 CA CLIMB TO FL 120, AT FL 085 COMMUNICATION ESTABLISHED WITH APPROACH, AND INSTRUCTED TO MAINTAIN FL 080. CAPT TOLD GO TO DESCENT AND MAINTAIN 080, AUTOPILOT WAS ENGAGED, CAPT REALIZED A/C WAS STILL CLIMBING AND THE WHEEL TRIM WAS TRIMMING FULL NOSE-UP, FO PUSHING ON CONTROL COLUMN, CAPT IMMEDIATELY DISENGAGE AUTO-PILOT, RESULT WAS A SUDDEN PITCH ATTITUDE CHANGE, A/C STARTED TO VIBRATE AND A VERY SCARY MOVEMENT OF A/C FOLLOWED. FLT RESUMED NORMALLY AFTERWARD, AND LANDED SAFELY AT AIRPORT. THE FOLLOWING WAS CARRIED OUT TO T/S & RECTIFY SNAG. AUTO-PILOT FUNCTION CHECKED, FOUND TOUCH CONTROL STEERING NOT WORKING. AUTO-PILOT COMPUTER REPLACED, ELEVATOR SERVO REPLACED, AS PER MM 22-10-00. AUTO-PILOT FUNCTION CHECK2H74 4T4 T A20EA E4EA 6 CP1NE 20060703001082006070300108GL 2006 7 3 CA060504003 220060428G726023005747 BEARING CAGE ALLSN 23005655 ALLSN 250C 250C30P 03013GL GEARBOX FAILED W K NONE O OTHER ININSP/MAINT 1 CA 6078 CAG95018 BEARING, REMOVED FROM GEARBOX DURING 3500 HOURS INSPECTION, HAS BEEN PREVIOUSLY ASSEMBLED WITH ONE BALL NOTICEABLY SMALLER THAN THE OTHER BALLS IN THE BEARING ASSEMBLY. REF ROLLS-ROYCE IPC, 14W4, 72-60-00, FIG.2, P.5, ITEM 39. 3 U E1GL 20060703001092006070300109SO 2006 7 3 CA060504004 220060426G7200 ENGINE DIAMONDA20 DA20C1 2990001GL CONT O240 IO240B 17063SO FAILED W A UNSCHED LANDING YJ ENGINE STOPPAGE WARNING INDICATION APAPPROACH 1 CA ENGINE QUIT ON APPROACH, ONCE LANDED THE PILOT RESTARTED THE ENGINE AND TAXIED TO THE PARKING AREA. THE AIRCRAFT WAS INSPECTED AND IT SEEMS TO BE FUEL PRESSURE THAT WAS THE CAUSE OF THE ENGINE FAILURE. RIGGING AND MULTIPLE TESTS WERE CONDUCTED AND THE PROBLEM DID NOT RE-APPEAR. 1L71 3O3 ONTTA4CH E7SO 20080520 2008 5 20 CA060504005 420060421G2562GS21 BATTERY AYRES S2 S2RR1820 0970215SO WRIGHTR1820 R182099 67020EA HAMSTD23E 23E50 NE ELT UNSERVICEABLE W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) FOUND CORROSION AROUND BATTERY. (TC NR 20060504005) 1L71 4R4 R A4SW 5E10 6 CP603 20060703001102006070300110CE 2006 7 3 CA060504006 120060503G552011561010325 TORQUE TUBE BEECH 100 B100 1152919CE GARRTTTPE331TPE3316252B 01514WP HARTZLHCB4T HCB4TN5 GL ELEVATOR WORN W K NONE O OTHER ININSP/MAINT 1 CA 176 WHILE CHECKING THE ELEVATOR SYSTEM FOR FREEDOM OF MOVEMENT, EXCESSIVE PLAY WAS NOTICED IN THE LEFT ELEVATOR. THE PLAY WAS ISOLATED TO THE ELEVATOR TORQUE TUBE FITTING. THE TORQUE TUBE WAS REPLACED WITH A NEW ASSEMBLY. THE TORQUE TUBE WAS INSPECTED AND FOUND TO HAVE OVER-SIZED TAPER PINS INSTALLED FROM THE MANUFACTURE. 1L72 4T4 T A14CE E2WE 6 CP40EA 20060703001112006070300111EA 2006 7 3 CA060504007 120060425G2760600913563 BRACKET CNDAIRCL604 CL604 1900301EA GE CF34 CF34* NE TRANSMITTER FRACTURED W O OTHER O OTHER NRNOT REPORTED 1 CA 3261 PRIOR TO A/C DEPARTURE, AND DURING A GROUND CHECK OF THE FLIGHT SPOILERS, THE LT SPOILER INDICATED IT WAS EXTENDED WHILE SURFACE WAS PHYSICALLY IN STOWED POSITION (AS COMMANDED BY SPOILER LEVER). FLIGHT SPOILER POSITION TRANSMITTER WAS INSPECTED AND FOUND TO BE LOOSE. MAINTENANCE SECURED TRANSMITTER, AND ITEM WAS DEFERRED IN ACCORDANCE WITH MEL. BRACKET WAS REPLACED UPON RETURN IN ACCORDANCE WITH AMM. BRACKET WAS FOUND WITH FRACTURES IN TWO PLACES ON BORE OF PART. 2L72 4F4 FRTA21EA E15NE 20060703001122006070300112SW 2006 7 3 CA060504008 120060503G6410206016201131 BLADE BELL 206 206L1 1182107SW ALLSN 250C 250C28B 03013GL TAIL ROTOR OUT OF TOLERANCEW K NONE O OTHER ININSP/MAINT 1 CA 548 THE BLADE WAS SENT TO ROTOR BLADES INCORPORATED FOR INSPECTION AS REQUIRED BY ASB 206L-04-127 REVISION C PART 3 AND BY AD CF-2004-05R1 PART D. ROTOR BLADES INCORPORATED HAS REPORTED THAT THE BLADE HAS FAILED THE INSPECTION AND IS BELOW TOLERANCE. THE BLADE IS HELD FOR DISPOSAL AT ROTOR BLADES INCORPORATED AT THE REQUEST OF BELL HELICOPTER. ROTOR BLADES INCORPORATED HAS PROBABLY FILED AN SDR IN THE USA. 1G71 3U3 U H2SW E1GL 20060705000012006070500001EA 2006 7 5 CA060504009 220060504G852076097 CAMSHAFT LYC O320E2A PIPER PA28 PA28140 7102802SO LYC O320 O320E2A 41508EA ENGINE DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA 2069 L1929227A CYLINDERS REMOVED FOR ON CONDITION INSPECTION, CAMSHAFT FOUND TO HAVE SEVERE CORROSION AND DAMAGE TO ALL LOBES. ENGINE DISASSEMBLED FOR OVERHAUL, AND THE FOLLOWING WAS FOUND; BOTH INTAKE LOBES ON CAMSHAFT DESTROYED, ALL TAPPET BODIES DAMAGED, OIL PUMP HOUSING P/N 78528 DAMAGED BEYOND REPAIR, AND OIL PUMP IMPELLERS DAMAGED. ALL INTERNAL COMPONENTS OF THE ENGINE HAD MINOR DAMAGE FROM METAL CONTAMINATION IN THE OIL. 1L71 3O3 O 2A13 E274 20060705000042006070500004CE 2006 7 5 CA060505003 120060505G5712 RIB CESSNA185 185F 2072820CE LT WING CRACKED W K NONE O OTHER NRNOT REPORTED 1 CA RIB ASSEMBLY ON WING CRACKED AT ATTACHMENT POINT TO SPAR. SPAR WAS UNDAMAGED BUT TRACK WAS REPLACED. AIRCRAFT HAS 10870.3 HOUR ON IT AT TIME OF REPAIR POSSIBLE TIME FATIGUED PART. 1H71 3O 3A24 20060705000072006070500007SO 2006 7 5 CA060508001 220060504G7310630662 FUEL LINE CONT IO360G CESSNA337 337G 2075730CE CONT O360 IO360G 17025SO MCAULY2AF34CD2AF34C306 GL REAR ENGINE BROKEN W A UNSCHED LANDING JR WARNING INDICATION PARTIAL RPM/PWR LOSS CLCLIMB 1 CA 355960 SHORTLY AFTER TAKEOFF, THE PILOT OF A CESSNA 337 NOTICED THAT FUEL PRESSURE ON THE REAR ENGINE BEGAN TO DROP OFF AND THE ENGINE BEGAN TO RUN ROUGH. TURNED ON THE ELECTRIC BOOST PUMP AND THE ENGINE CONTINUED TO RUN NORMALLY. ELECTED TO RETURN TO THE AIRPORT AND LANDED WITHOUT INCIDENT. AN INSPECTION OF THE REAR ENGINE REVEALED A BROKEN FUEL INJECTOR LINE FOR THE NUMBER SIX CYLINDER. THE LINE HAD SEVERED COMPLETELY OFF FROM THE FUEL MANIFOLD SPIDER. A SERVICEABLE LINE WAS INSTALLED AND LEAK CHECKS CARRIED OUT. THE AIRCRAFT WAS RETURNED TO SERVICE. 1H72 3O3 O A6CE E1CE 5 CP5EA 20060705000112006070500011NM 2006 7 5 CA060508002 120060506G561058935734 WINDOW BOEING737 737522 138449FNM CFMINTCFM56 CFM563C1 13802EU COCKPIT CRACKED W O OTHER O OTHER APAPPROACH 1 CA ON APPROACH FLIGHT, CREW REPORTED THAT THE FIRST OFFICERS NR 4 EYEBROW WINDOW HAD CRACKED. ON ARRIVAL, WINDOW WAS INSPECTED AND REPLACED. 2L72 4F4 FRTA16WE E21EU 20060705000172006070500017NE 2006 7 5 CA060508003 220060508G7321CL12068161 RELAY DHAV DHC8 DHC8106 2809020NM PWA PW121 PW121 52124NE NR 1 ECU DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA DURING A "C" CHECK INSPECTION, DURING THE OPERATIONAL CHECK OF "DUPLICATED ECU POWER SUPPLIES AND INTEGRITY OF DIODES CHECK" (TASK 73-20-02), THE BASE OF THE RELAY 7611-K3 (ENG NR 1 ECU) WAS FOUND UNGLUED. WITH THIS RELAY DISCONNECTED, THE ECU OF THIS ENGINE GOES IN MANUAL MODE DUE TO THE FULL LOSS OF POWER. IN ADDITION, THE FREE RELAY BASE RESULT IN A HI-RISK OF SHORTING WITH THE STRUCTURE. 2H72 4T4 TRTA13NM E20NE 20060705001122006070500112EU 2006 7 5 CA060508004 120060501G2932973811430 PRESSURE SWITCH PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL HYDRAULIC SYS MALFUNCTIONED W A UNSCHED LANDING S AFFECT SYSTEMS CLCLIMB 1 CA 10610 AFTER TAKEOFF AND GEAR UP SELECTION WAS COMPLETED, THE CREW HAD A HYD. LIGHT ON THERE CAWS. RETURNED AND UPON GEAR DOWN SELECTION THE GEAR MOTOR FAILED TO RUN. GEAR DID A FREE FALL AND LOCKED DOWN. ONCE IN HANGAR IT WAS NOTED THAT HYDRAULIC CONTROL CB WAS OUT. CB WAS RESET AND THE DEFECT COULD NOT BE DUPLICATED. PLEASE NOTE THIS AIRCRAFT HAD BEEN EXPERIENCING HYDRAULIC LIGHTS ON LANDING. (THIS NOTIFIED CREW THE PUMP HAD RUN MORE THAN SIX TIMES IN THE PAST HOUR OF FLIGHT) THIS DEFECT COULD NEVER BE DUPLICATED IN THE HANGAR EITHER. MAINTENANCE REPLACED THE HYDRAULIC SYSTEM PRESSURE SWITCH AS A PRECAUTIONARY MEASURE AND NEITHER DEFECT HAS SINCE REOCCURRED. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20060705001162006070500116NE 2006 7 5 CA060508006 220060508G7321CL12068161 RELAY DHAV DHC8 DHC8102 2809003NM PWA PW121 PW121 52124NE NR 2 ECU SEPARATED W K NONE O OTHER ININSP/MAINT 1 CA DURING THE ACCOMPLISHEMENT OF THE TASK 7320/02 (OPERATIONAL CHECK OF DUPLICATED ECU POWER SUPPLIES AND INTEGRITY OF DIODES), THE 7611-K4 (ENG NR 2 ECU) RELAY BASE WAS FOUND UNGLUED. THIS SITUATION REMOVED ALL THE POWER FOR THE ECU AND LIVE THE ENGINE IN MANUEL MODE. IN ADDITION, THE FREE RELAY BASE GIVE THE OPPORTUNITY OF SHORTING TO THE ELECTRICAL PINS WITH THE ADJACENT STRUCTURE. 2H72 4T4 TRTA13NM E20NE 20060626001262006062600126SO 2006 6 26 CA060508007 120060418G271062701123 CONTROL CABLE PIPER PA44 PA44180 7104402SO LYC O360 O360A1H 41514EA HARTZLHCC2Y HCC2YR2 GL AILERON FRAYED W K NONE O OTHER ININSP/MAINT 1 CA DURING EVENT INSPECTION OF DETAILED WING (RT) BROKEN STRANDS WERE OBSERVED ON RT AILERON BALANCE CABLE AS IT PASSED OVER A PULLEY AT WING STATION 22.00. CABLE AND PULLEY WERE REMOVED. CABLE WAS REPLACED NEW, PULLEY WAS CLEANED INSPECTED, LUBRICATED AND RETURNED TO SERVICE. THERE IS VERY LITTLE CONTROL CABLE DEFLECTION OVER THE PULLEY'S IN THIS LOCATION. ROUTINE CLEANING AND LUBRICATION OF PULLEY MAY FORESTALL CONTROL CABLE WEAR IN THIS AREA. 1L72 3O3 O A19S0 E286 5 CP920 20060626001282006062600128SO 2006 6 26 CA060508008 120060418G534386444800 SPAR PIPER PA44 PA44180 7104402SO LYC O360 O360A1H 41514EA HARTZLHCC2Y HCC2YR2 GL NLG CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 3585 DURING COMPLETION OF PIPER SB 1143 A 3/4" CRACK WAS OBSERVED RADIATING OUT FROM THE LOWER AFT BOLT HOLE OF THE NLG DRAG LINK TRUNNION MOUNTING. FURTHER INVESTIGATION REVEALED A 1/2" CRACK RADIATING OUT FROM THE LOWER AFT BOLT HOLE OF THE RT DRAG LINK TRUNNION MOUNTING. AIRCRAFT LT AND RT NOSE SPAR ASSEMBLIES WERE REPLACED NEW. 1L72 3O3 O A19S0 E286 5 CP920 20060626000112006062600011SO 2006 6 26 CA060508009 120060424G534386444800 SPAR PIPER PA44 PA44180 7104402SO LYC O360 O360A1H 41514EA HARTZLHCC2Y HCC2YR2 GL FUSELAGE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 4063 DURING COMPLETION OF SB1143, A 1 INCH CRACK WAS OBSERVED RADIATING OUT FROM THE LOWER AFT BOLT HOLE OF THE LT DRAG LINK TRUNNION MOUNTING. FURTHER INVESTIGATION REVEALED A .5 INCH CRACK RADIATING OUT FROM LOWER AFT BOLT HOLE OF RT DRAG LINK TRUNNION MOUNTING. AIRCRAFT LT AND RT NOSE SPAR ASSEMBLIES WERE REPLACED NEW. 1L72 3O3 O A19S0 E286 5 CP920 20060626000122006062600012SO 2006 6 26 CA060508010 120060418G57127847506 RIB PIPER PA44 PA44180 7104402SO LYC O360 O360A1H 41514EA HARTZLHCC2Y HCC2YR2 GL WS 49.25 CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 3599 DURING COMPLETION OF INSPECTION REQUIRED SB 1161, A 2 INCH LONG CRACK WAS OBSERVED IN THE LT WING RIB AT STN 49.25. THE CRACK WAS LOCATED IN THE BEND RADIUS UNDER THE MAIN LANDING GEAR (MLG) SIDE BRACE ASSEMBLY (PN 95643-08). A NEW RIB WAS INSTALLED. BEFORE RE-INSTALLATION SHARP CORNERS ON THE SIDE BRACE MOUNT WERE POLISHED TO REDUCE THE POSSIBILITY OF CHAFING THE RIB IN THE AFFECTED AREA. 1L72 3O3 O A19S0 E286 5 CP920 20060626000132006062600013SO 2006 6 26 CA060508011 120060418G57127847507 RIB PIPER PA44 PA44180 7104402SO LYC O360 O360A1H 41514EA HARTZLHCC2Y HCC2YR2 GL WS 49.25 CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 3599 DURING COMPLETION OF INSPECTION REQUIRED SB 1161, A 3 IN LONG CRACK WAS OBSERVED IN THE RT WING RIB AT STN 49.25. THE CRACK WAS LOCATED IN THE RIB BEND RADIUS UNDER THE MLG SIDE BRACE MOUNT (PN 95643-09). A NEW RIB WAS INSTALLED. BEFORE RE-INSTALLATION SHARP CORNERS ON SIDE BRACE MOUNT WERE POLISHED TO REDUCE THE POSSIBILITY OF CHAFING WITH THE RIB IN THIS AREA. 1L72 3O3 O A19S0 E286 5 CP920 20060626000142006062600014SO 2006 6 26 CA060508012 120060424G57127847507 RIB PIPER PA44 PA44180 7104402SO LYC O360 O360A1H 41514EA HARTZLHCC2Y HCC2YR2 GL WS 49.25 CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 4099 DURING COMPLETION OF INSPECTION REQUIRED BY PIPER SB 1161, A 2.5 INCH LONG CRACK WAS OBSERVED IN THE RT WING RIB AND 3 INCH LONG IN THE LT WING RIB AT STN 49.25. THE CRACKS WERE LOCATED IN THE BEND RADIUS UNDER THE MLG SIDE BRACE MOUNT (PN 95643-09). NEW RIBS WERE INSTALLED. BEFORE RE-INSTALLATION SHARP CORNERS ON SIDE BRACE MOUNT WERE POLISHED TO REDUCE THE POSSIBILITY OF CHAFING THE RIBS IN THIS AREA. 1L72 3O3 O A19S0 E286 5 CP920 20060705001912006070500191WP 2006 7 5 CA060508013 120060506G6730 SEAL ROBSIN D2121 ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE SERVO LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA 731 4655 (CAN) SERVO FOUND TO HAVE AN EXCESSIVE OIL LEAK FROM THE UPPER SEAL. THE SERVO WAS REPLACED WITH A SERVICEABLE UNIT. THIS SERVO HAD BEEN REMOVED 109.4 HOURS BEFORE FOR A SEAL LEAK. THE SERVO WAS RETURNED AT THAT TIME TO MFG FOR REPAIR. (TC NR 20060508013) 1G71 3O3 O H11NM 1E4 20060705001922006070500192SW 2006 7 5 CA060508014 120060508G3213MS1699799 BOLT AIRTRCAT802 AT802A 0390308SW PWA PT6 PT6A67 52043NE HARTZLHCB5M HCB5MA3 GL MLG LOOSE W K NONE O OTHER ININSP/MAINT 1 CA 189 (CAN) DURING THE ACCOMPLISHMENT OF THE ANNUAL INSPECTION OF THE LANDING GEAR, MAINTENANCE STAFF NOTICED THAT THE LT IB AND RT OB TORQUE PLATES THAT SECURE THE BRAKE CALIPERS WERE LOOSE. THE 6 BOLTS TAHT SECURE THE TORQUE PLATES TO THE MAIN WHEEL AXLE ASSEMBLY WERE LOOSE CAUSING THE PLATES TO SHIFT AS THE WHEELS WERE ROTATED BACK AND FORTH. THE OTHER AIRCRAFT IN THE FLEET WILL BE INSPECTED TO ENSURE ALL THE BOLTS ARE TIGHT. (TC NR 20060508014) 1L71 3T4 TNCA19SW E26NE 6 CP44GL 20060705001932006070500193CE 2006 7 5 CA060509000 120060501G53305012015682 SKIN BEECH 90 C90A 1152911CE PWA PT6 PT6A21 52043EA HARTZLHCB3T HCB3TN3 GL FUSELAGE WORN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) SKIN P/N 50-120156-82 (PRESSURE VESSEL) EXIBITING WEAR MARK ALONG FASTENER ROW ATTACHING FILLET P/N 50-420023-24 TO IT. WEAR MARK NOT READILY VISIBLE WITHOUT PULLING AWAY FILLET FROM SURFACE OF SKIN. WEAR MARK IS CAUSED BY LOOSENING OF FILLET TO SKIN FASTENERS AND SUBSEQUENT CHAFFING. UN-NOTICED, THIS CONDITION COULD LEAD TO PRESSURE VESSEL RUPTURE. (TC NR 20060509000) 1L72 3T4 TRT3A20 E4EA 6 CP15EA 20060705001952006070500195CE 2006 7 5 CA060509001 120060502G5753122101015 FLAP TRACK CESSNA185 A185F 2072821CE CONT O520 IO520D 17032SO MCAULYD3A34 D3A34C403 GL TE FLAPS CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) LT IB FLAP TRACK, FWD ANGLES, AGAINST SPAR FOUND CRACKED AT BEND RADIUS, LOWER END. (TC NR 20060509001) 1H71 3O3 O 3A24 E5CE 5 CP47GL 20060705001982006070500198CE 2006 7 5 CA060509002 120060428G3340S21604 SWITCH CESSNA172 172N 2072434CE LYC O320 O320H2AD 41508EA MCAULY1C160 1C160DTM GL LANDING LIGHT DEFECTIVE W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 1 CA (CAN) PILOT WAS IN CRUISE WITH LANDING LIGHT ON, WHEN SHE SMELLED SMOKE AND NOTICED SMOKE COMING FROM LANDING LIGHT SWITCH. SMOKE STOPPED WHEN SWITCH TURNED OFF AND PILOT SQUAWKED 7700 FOR HELP AND SHE WAS ADVISED TO LAND. AGAIN IT WAS CONFIRMED THAT THE SWITCH WOULD SMOKE WHEN TURNED ON, BUT NOT WHEN OFF. PILOT FLEW AIRCRAFT HOME WITH LANDING LIGHT OFF, WHERE MAINTENANCE CONFIRMED PROBLEM AND REPLACED THE SWITCH. NOTE: THIS IS NOT AN UNCOMMON PROBLEM WITH THESE SWITCHES. (TC NR0 20060509002) 1H71 3O3 ONT3A12 E274 5 NP910 20060705001992006070500199CE 2006 7 5 CA060509003 120060501G2410DOFF10300F ALTERNATOR CESSNA150 150C 2071808CE CONT O200 O200A 17020SO ENGINE DEFECTIVE W K NONE O OTHER ININSP/MAINT 1 CA (CAN) STATOR AND RECTIFIER DEFECTIVE. (TC NR 20060509003) 1H71 3O3 O 3A19 E252 20060705001172006070500117EU 2006 7 5 CA060509004 120060508G2434AN960JD616 WASHER SAAB SF340 340B 7860101EU GE CT7TP CT79B 30030NE ROTOL R390 R3904123F27 NE STARTER GEN MELTED W K NONE O OTHER ININSP/MAINT 1 CA 14635 WHILE CONDUCTING A VISUAL INSPECTION OF THE PORT STARTER GENERATOR GROUND POINT SEALANT REMOVED. IT WAS DISCOVERED THAT THE ALUMINUM WASHERS, P/N AN960JD616, BETWEEN THE GROUND POINT ATTACH BOLT AND THE BRACKET HAD MELTED. THE GROUND POINT BRACKET SHOWED EVIDENCE OF ARCING AND THE GROUND POINT ATTACH BOLT SHOWED EVIDENCE OF CORROSION. INSPECTION OF A SECOND AIRCRAFT C-GMNM S/N 340B-364 REVEALED CORROSION ON THE ALUMINUM WASHERS P/N AN960JD616. AN INSPECTION OF THE BALANCE OF SAAB 340 FLEET IS ON GOING. 2L72 4T4 TRTA52EU E8NE 6 CP31NE 20060705002882006070500288EA 2006 7 5 CA060509006 220060504G8530SL32006WAZOP CYLINDER HEAD CESSNA172 172P 2072436CE LYC O320 O320D2J 41508EA MCAULY1C160 1C160DTM GL ENGINE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 1800 (CAN) ONE CRACK RUNNING BETWEEN UPPER SPARK PLUG HOLE AND EXHAUST VALVE. SECOND CRACK FROM LOWER SPARK PLUG HOLE EXTENDING APPROX 1 INCH INTO CYL HEAD. (TC NR 20060509006) 1H71 3O3 ONT3A12 E274 5 NP910 20060711001212006071100121WP 2006 7 11 CA060509007 120060504G3213369H600131 STRUT HUGHES369 369D 4470706WP ALLSN 250C 250C20B 03013GL MLG CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) WHILE DOING A 100 HOUR INSPECTION OF THE AIRCRAFT THE ENGINEER NOTICED SOME CRACKED PAINT ON THE BOTTOM SIDE OF THE STRUT EMINATING FROM THE LANDING GEAR BRACE BOLT HOLE. HE THEN REMOVED SOME OF THE PAINT AND REVEALED A CRACK 1.5 INCHES LONG GOING OUTWARDS TOWARD THE LANDING GEAR DAMPER ATTACH POINT. (TC NR 20060509007) 1G71 3U3 U H3WE E4CE 20060705002892006070500289EU 2006 7 5 CA060509008 120060505G3320E033601 BALLAST AEROSPATR42 ATR42300 8680920EU PWA 120 PW120 NE HAMSTD14SF 14SF5 NE LIGHT OVERHEATED W O OTHER MB OVER TEMP SMOKE/FUMES/ODORS/SPARKS CRCRUISE 1 CA (CAN) LAMP SOCKET OVERHEATED AT BALLAST 27LG CAUSING SMOKE ODOR IN CABIN. (TC NR 20060509008) 2H72 4T4 TRTA53EU E20NE 6 CP7NE 20060705001322006070500132NE 2006 7 5 CA060509009 220060414G72600235237790 CHIP DETECTOR SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1D1 NE ENGINE SHORTED W O OTHER N FALSE WARNING HOHOVERING 1 CA 1649 IN FLIGHT, THE PILOT NOTICED THE ENGINE CHIP LIGHT ILLUMINATE. LANDED AND THE ENGINEER LOOKED AT THE CHIP DETECTORS AND NO METAL WAS FOUND. THEN RE INSTALLED THE CHIP DETECTORS AND CARRIED OUT A GROUND RUN. AFTER 10 MINUTES OF GROUND RUNNING ANOTHER CHIP LIGHT OCCURRED. AFTER THE ENGINE COOLED OFF THE CHIP LIGHT WOULD GO OUT. THE ELECTRICALLY OPERATED CHIP DETECTOR WAS FOUND TO CAUSE A LIGHT WHEN HOT AND THEM EXTINGUISH WHEN COOLED OFF. 1G71 3U3 U H9EU E19EU 20060705002902006070500290NE 2006 7 5 CA060510001 220060508G7314B8187B PUMP ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE FUEL SYS LOOSE W K NONE O OTHER ININSP/MAINT 1 CA (CAN) PUMP WAS FOUND TO BE NOISY DURING ENGINE PRIMING. WHEN THE PUMP WAS REMOVED THE HOUSING AROUND THE ELECTRIC MOTOR WAS ALSO FOUND TO BE LOOSE. (TC NR 20060510001) 1G71 3O3 O H11NM 1E4 20060705001332006070500133CE 2006 7 5 CA060510002 120060502G554124130015 RIB CESSNA172 172RG 2072438CE LYC O360 O360F1A6 41514EA MCAULY2D34C B2D34C220 GL RUDDER CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 7635 7635 AT A 100 HOUR INSPECTION A CRACK WAS FOUND UNDER THE LEFT INBOARD RUDDER BAR BLOCK, AT THE MOST FORWARD BOLT HOLE. RUDDER BLOCK HAD ABNORMAL MOVEMENT. CRACK COULD ONLY BEEN SEEN AFTER BLOCK WAS REMOVED. 1H71 3O3 O 3A17 E286 5 CP7EA 20060705001342006070500134NE 2006 7 5 CA060510003 220060503G7321430128806 FCU SNIAS 350 AS350BA 8680817EU LYC LTS101LTS101600A3 41560NE ENGINE FAILED W E ENGINE SHUTDOWN AM FLAME/FIRE OVER TEMP TXTAXI/GRND HDL 1 CA 3283 1218 ON SECOND START OF THE DAY, A FLAME WAS SEEN COMING OUT OF EXHAUST AND A RAPID INCREASE IN TURBINE OUTLET TEMPERATURE. AFTER SEVERAL MINUTES, A SECOND ATTEMPT WAS GIVEN WITH SIMILAR RESULTS. 1G71 3U3 UNCH9EU E5NE 20060705001352006070500135EA 2006 7 5 CA060510004 220060510G7250 BLADE PWA PT6 PT6* 52043EA ENGINE FAILED W K NONE O OTHER ININSP/MAINT 1 CA 3721 FAILED ENGINE SENT TO O/H SHOP WHERE ALL CT BLADES WERE FOUND DAMAGED/BROKEN. SIGNIFICANT DOWNSTREAM DAMAGE WAS EVIDENT. CAUSE OF CT BLADE FAILURE NOT DETERMINED BUT LUGS WERE BROKEN OFF THE CT STATOR AS A RESULT OF HEAVY CONTACT BETWEEN CT DISK AND CT STATOR. ENGINE OEM IS CURRENTLY INVESTIGATING RECENT RASH OF CT BLADE FAILURES ON THIS PT6A-114 ENGINE FAMILY. 3 T E2NE 20060705001362006070500136CE 2006 7 5 CA060510007 120060507G5220 SHAFT BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE HARTZLHCE4A HCE4A3I NE EMERGENCY EXIT CORRODED W K NONE O OTHER ININSP/MAINT 1 CA INTERNAL CABIN PORTION OF PHASE 3 INSPECTION FOUND BOTH RT EMERG EXIT DOORS WOULD NOT OPEN FROM INSIDE. BOTH DOORS WERE REMOVED VIA EXT HANDLE AND DISASSEMBLED, UPON INSPECTION, FOUND RT COUPLING P/N 129-514065-2 WAS MATED TO SHAFT P/N 129-514033-2 AT ALL TIMES. HANDLE LINKAGE WAS REMOVED AND DISASSEMBLED. FOUND THERE WAS JUST ENOUGH SURFACE CORROSION ON EXT SURFACE OF THE SHAFT AND INTERNAL SURFACE OF COUPLER TO KEEP EXTERIOR HANDLE ENGAGED AT ALL TIMES WHICH IN TURN USED THE OUTSIDE HANDLE AS A STOP WHEN TRYING TO OPEN THE EXIT FROM INSIDE. COUPLER WAS REMOVED FROM THE SHAFT AND SURFACE CORROSION REMOVED. UNIT WAS REASSEMBLED AND EMERG EXIT HANDLE FUNCTION TESTED SERVICEABLE. 2L72 4T4 TRTA24CE E26NE 5 CP10NE 20060711001372006071100137 2006 7 11 CA060510009 120060508G8011629435 SHAFT CONT CONT O520 IO520MB 17032SO STARTER ADAPTER BROKEN W K NONE O OTHER ININSP/MAINT 1 CA 277948R THREE GEAR TEETH BROKEN OFF AND MISSING. ONE OTHER TOOTH CRACKED. 3 O E5CE 20060626000162006062600016NE 2006 6 26 CA060510010 220060503G7200ARRIEL1D1 ENGINE SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1D1 NE MAKING METAL W E ENGINE SHUTDOWN KBJFLUID LOSS SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION TXTAXI/GRND HDL 1 CA 6081 92 9135 ON ENGINE STARTUP, THE PILOT NOTICED A FLICKERING ENGINE CHIP LIGHT, SECONDS LATER THE CHIP LIGHT CAME ON SOLID. ENGINE WAS SEEN SMOKING AND OIL COMING FROM EXHAUST STACK. ENGINE WAS SHUTDOWN AFTER APP 1 MINUTE OF OPERATION. ENGINE HAS BEEN SENT TO OVERHAUL COMPANY FOR INVESTIGATION AND REPAIR. ENGINE HAD 91.9 HOURS SINCE OVERHAUL. ENGINE IS AT THE OVERHAUL COMPANY AT THE MOMENT AND A DETAILED REPORT WILL BE COMING AT A LATER DATE. 1G71 3U3 U H9EU E19EU 20060711001382006071100138CE 2006 7 11 CA060510011 120060502G32135041000206 TRUNNION CESSNA401 401B 207590ECE CONT O520 TSIO520EB 17040SO MCAULY3AF32C3AF32C* GL RT MLG CRACKED W O OTHER K FLUID LOSS LDLANDING 1 CA 12920 THE RT MAIN LANDING GEAR OLEO WENT FLAT AFTER LANDING. A CRACK WAS NOTICED ON THE UPPER TRUNNION, JUST UNDER THE SIDE BRACE ATTACH FITTING. THE UPPER TRUNNION WAS REPLACED. 1L72 3O3 O A7CE E8CE 5 CP22EA 20060626000172006062600017SO 2006 6 26 CA060510013 120060509G551146530003 RIB PIPER PA31T PA31T 7103124SO PWA PT6 PT6A28 EA HARTZLHCB3T HCB3TN3 GL HORIZONTAL STAB CRACKED W K NONE O OTHER ININSP/MAINT 1 CA DURING A ROUTINE INSPECTION, THE LT OB STABILIZER RIB WAS FOUND CRACKED NEAR THE HINGE ATTACH AREA. THE RIB WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE. 1L72 3T4 T A8EA E4EA 6 CP15EA 20060626000182006062600018WP 2006 6 26 CA060510014 120060503G2400B2804 RELAY ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE GOVERNOR STUCK W K NONE N FALSE WARNING ININSP/MAINT 1 CA 560 THE GOVERNOR (OFF) WARNING LIGHT WAS STAYING ON, REGARDLESS OF THE STATUS OF THE GOVERNOR. BY ALL CHECKS THE GOVERNOR WAS WORKING WHEN TURNED ON, AND TURNING OFF WHEN THE SWITCH WAS TURNED OFF, HOWEVER THE (GOVERNOR OFF) LIGHT STAYED ON AT ALL TIMES. THE CONTROL RELAY FOR THE LIGHT WAS FOUND TO BE STICKING, KEEPING THE LIGHT ON. RELAY WAS REPLACED, AND NO FURTHER DEFECTS WERE FOUND. 1G71 3O3 O H11NM 1E4 20060711001392006071100139CE 2006 7 11 CA060511001 120060511G531012118061 DOOR FRAME CESSNA207 T207A 2073614CE CONT O520 TSIO520M 17040SO FUSELAGE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 13791 .5 INCH CRACK FOUND IN LOWER LT DOOR POST JAMB DURING ROUTINE INSPECTION. 1H71 3O3 O A16CE E8CE 20060711001402006071100140EU 2006 7 11 CA060511002 120060510G3520630130018 MANIFOLD AIRBUSA340 A340313 EU CFMINTCFM56 CFM565C4 13802NE PAX OXYGEN CRACKED W K NONE O OTHER ININSP/MAINT 1 CA AIRCRAFT HAD 22 MANIFOLDS FOUND CRACKED. LOOKED AT ANOTHER AIRCRAFT TO PROVIDE SPARES, BUT FOUND MOST OF ITS MANIFOLDS CRACKED TOO. DRAGER (VENDOR) CONTACTED, AND WILL PROVIDE REPLACEMENTS. MANIFOLD IS MADE OF A VARIETY OF PLASTIC, WHICH IS BRITTLE. 2L74 4F4 FRTA197 E37NE 20060711001412006071100141SW 2006 7 11 CA060511004 120060509G3211AN324A BOLT FRCHLD 2751500001 SWRNGNSA227 SA227AC 8780603SW GARRTTTPE331TPE33111U 01514WP MCAULY4HFR344HFR34C652 NE TRUNNION SHEARED W E ENGINE SHUTDOWN J WARNING INDICATION TXTAXI/GRND HDL 1 CA 946 PILOT REPORTED LOSS OF GREEN LIGHT AND TRANSIT LIGHT ON THE NOSE GEAR DURING TAXI INTO AIRPORT. PILOT SHUTDOWN AC AND EMPTIED AIRCRAFT. MAINTENANCE MOVED AIRCRAFT TO SAFE LOCATION AND WHILE JACKING THE AIRCRAFT NOTICED THAT NOSE WHEEL PIVOTED SIDEWAYS. UPON INVESTIGATION IT WAS NOTED THAT THE UPPER GEAR TRUNNION PIN RETAINING BOLTS WERE SHEARED AND MISSING. THEY WERE STILL IN PLACE YET THE HEADS WERE SHEARED OFF. REMOVED AND INSPECTED THE LOWER PIN RETAINING BOLTS AND FOUND THEM CORRODED AND READY TO SHEAR. ALL UNSERVICEABLE BOLTS REPLACED AND GEAR SWINGS CHECKED SERVICEABLE AND AIRCRAFT RETURNED TO SERVICE. 2L72 4T4 TRTA8SW E4WE 6 C3PNE 20060711001662006071100166CE 2006 7 11 CA060511005 120060414G533011443007529 SKIN BEECH 1900 1900C 1154161CE PWA PT6 PT6A65B 52043EA HARTZLHCB4M HCB4MP3 GL FUSELAGE CORRODED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) HEAVY CORROSION BETWEEN SKIN AND STRINGERS (BONDED) AT STRINGER SPLICES IN BELLY AT CENTERLINE STRINGER AND 2 LT AND RT OF CENTER. (TC NR 20060511005) 2L72 4T4 TRTA24CE E4EA 6 CP56GL 20060711001852006071100185CE 2006 7 11 CA060511006 120060418G57301141200487374 SKIN BEECH 1900 1900C 1154161CE PWA PT6 PT6A65B 52043EA HARTZLHCB4M HCB4MP3 GL WING CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) OB FWD CORNER OF COLLECTOR TANK OPENING. SKINS P/N 114-120048-73 AND 74 FOUND CRACKED. HEAVY SKIN .071 (TC NR 20060511006) 2L72 4T4 TRTA24CE E4EA 6 CP56GL 20060711001862006071100186SW 2006 7 11 CA060511007 120060509G32602751000305 STRIKER FRCHLDSA227 SA227CC 3377522SW GARRTTTPE331TPE33111U 01514WP MCAULY4HFR344HFR34C652 NE LT GEAR LOOSE W K NONE O OTHER ININSP/MAINT 1 CA (CAN) AFTER GEAR SWING TO CHECK FOR HYD LEAK IT WAS NOTED THAT THE LT GEAR DID NOT EXTEND. THE LT OB STRIKER ON THE LT CAM ASSY WAS LOOSE AND NOT CONTACTING ACTUATOR AREA FOR UPLOCK RELEASE. THE BOLT WAS REMOVED FROM STRIKER AND FOUND TO BE STRIPPED AND THE NUT HAD BACKED OFF CAUSING THE STRIKER TO BE VERY SLOOPY AND NOT CONTACTING THE ACTUATOR ARM ON UPLOCK INTERMITTANTLY. NEW BOLT AND NUT INSTALLED AND SWINGS ACCOMPLISHED SERVICIBLE. AIRCRAFT RETURNED TO SERVICE. (TC NR 20060511007) 2L72 4T4 TRTA18SW E4WE 6 C3PNE 20060711001872006071100187CE 2006 7 11 CA060511008 120060426G573011412004854 DOUBLER BEECH 1900 1900C 1154161CE PWA PT6 PT6A65B 52043EA HARTZLHCB4M HCB4MP3 GL WING CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DOUBLER P/N 114-120048-54 FOUND CRACKED AT FWD OB CORNER. CAN NOT SEE CRACK UNLESS COLLECTOR FUEL TANK IS REMOVED. (TC NR 20060511008) 2L72 4T4 TRTA24CE E4EA 6 CP56GL 20060711001882006071100188CE 2006 7 11 CA060511009 120060511G3230 LANDING GEAR BEECH 1900 1900C 1154161CE PWA PT6 PT6A65B 52043EA HARTZLHCB4M HCB4MP3 GL MALFUNCTIONED W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA (CAN) GEAR WAS RETRACTED AND GEAR HORN AND GEAR HANDLE LIGHT STAYED ON. (TC NR 20060511009) 2L72 4T4 TRTA24CE E4EA 6 CP56GL 20060711001892006071100189CE 2006 7 11 CA060512001 120060501G56203541029114 WINDOW BEECH 58 58 1152740CE CONT O550 IO550C SO MCAULY3AF32C3AF32C512 GL EMERGENCY EXIT SEPARATED W A UNSCHED LANDING D INFLIGHT SEPARATION CLCLIMB 1 CA 5338 (CAN) EMERGENCY EXIT WINDOW OPENED ON TAKEOFF. WINDOW WENT FROM VENT POSITION TO EXIT POSITION INTO FREE AIR AND HINGE BROKE OFF AND WINDOW DETACHED FROM AIRCRAFT. IT IS POSSIBLE THAT AT SOME PRIOR FLIGHT THE WINDOW WAS OPENED INCORRECTLY. WE HAVE OPERATED A FLEET OF 7 AIRCRAFT WITH THE SAME TYPE WINDOW WITH NO PRIOR PROBLEMS. (TC NR 20060512001) 1L72 3O3 O 3A16 E3SO 5 CP22EA 20060719000222006071900022GL 2006 7 19 CA060512002 320060510G61124E220010 BOOT HARTZL HCB3TN3B BEECH 99 99 1154002CE PWA PT6 PT6A28 EA HARTZLHCB3T HCB3TN3 GL BLADE DEICE DEPARTED W K NONE O OTHER ININSP/MAINT 1 CA BUA27150 BUA27150 (CAN) DURING MAINT WALK AROUND, COMPLETE PROP BLADE DE-ICE BOOT HAD DEPARTED AC. AIRFRAME, ENG WAS INSPECTED FOR FOD DAMAGE FROM DE-ICE BOOT. DETERMINED THAT BOOT HAD SEPERATED FROM AC DAY BEFORE DURING TAKE-OFF. PILOT FELT VIBRATION FROM LT ENG DURING RUN-UP, DURING TAKE-OFF FLUCTUATION OF TORQUE INDICATION FOR ENG, THEN SETTLED OUT FOR REST OF FLIGHT BECAUSE VIBRATION WENT AWAY. FURTHER INVESTIGATION SHOWS DE-ICE BOOT WAS THROWN ALONG LENGTH OF BLADE THEN DEPARTED AC (RUBBER STREAKS OUT TO BLADE TIP). GLUE ON BLADE LOOKED TO BE IN NORMAL CONDITION, NO DETERIORATION OF GLUE BED. DETERMINED 2 BOOTS ON THAT PROP WERE CHANGED, CANNOT DETERMINE IF IT WAS ONE OF REPLACED BOOTS. 1L72 3T4 T A14CE E4EA 6 CP15EA 20060711001902006071100190EA 2006 7 11 CA060512003 120060509G3246C3US1563 BOLT DHAV DHC3 DHC3 2800202EA GARRTTTPE331TPE33112UHR WP HARTZLHCB4T HCB4TN5 GL RT WHEEL FAILED W K NONE O OTHER ININSP/MAINT 1 CA 106 (CAN) WHILE PERFORMING A 100 HOUR INSPECTION ON THE MLG WHEEL SKIS, MAINTENANCE FOUND THE RT WHEEL SKI ATTACH BOLT P/N:C3US156-3 TO BE BENT AND CRACKED. BOLT ATTACHES THE SKI BRACKET ASSEMBLY LINK P/N: C3US108-34 TO THE MLG STRUT AND AXLE. THE BOLT HAS CRACKED AT THE START OF THE RADIUS WHERE THE DIAMETER OF THE BOLT CHANGES FRON .500 NR DIA TO .750 IN DIA IT APPEARS THAT THE CRACK OCCURED ON THE TOOLING MARK. (TC NR 20060512003) 1H71 3R4 T A815 E4WE 6 CP40EA 20060711001912006071100191GL 2006 7 11 CA060512006 120060508G7160C2E1079 FLAP DHAV DHC2 DHC2MKI 2801830GL PWA R985 R985AN14B 52008NE HAMSTD2D 2D30 NE CARB HEAT CRACKED W O OTHER R PARTIAL RPM/PWR LOSS TOTAKEOFF 1 CA 23102 (CAN) THE CARB HEAT FLAP ASSEMBLY HAD CRACKED UNDER THE DOUBLER PLATE, ALONG THE RIVET ATTCH LINE THAT CONNECTED THE FLAP/DOOR TO THE ACTUATING SHAFT BRACKET. (TC NR 20060512006) 1H71 3R3 RRCA806 5E1 5 CP206 20060711001922006071100192CE 2006 7 11 CA060514001 120060513G322012436351 TORQUE LINK CESSNA 1243800205 CESSNA207 207 2073602CE CONT O550 IO550F 17042SO HARTZLHCJ3Y PHCJ3YF1 GL NLG CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 2019 2019 (CAN) NOSE LANDING GEAR UPPER TORQUE LINK FOUND CRACKED ON BOTH LT AND RT SIDE OF LWR WEB. CRACK WAS DETECTED VISUALLY DURING 50 HR INSP AND LUBRICATION OF NOSE LANDING GEAR. THIS PART WAS INSTALLED NOVEMBER 2001, PREVIOUS PART HAD SAME CRACKS IN SAME LOCATION. (TC NR 20060514001) 1H71 3O3 O A16CE E3SO 5 CP36EA 20060719000432006071900043SO 2006 7 19 CA060514002 220060511G8530TIST712ACA CYLINDER HEAD CESSNA206 U206G 2073356CE CONT O520 IO520F 17032SO HARTZLHCJ3Y PHCJ3YF1 GL ENGINE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 798 798 291018R (CAN) CYLINDERS NR 2 AND NR 4 WHERE FOUND TO BE CRACKED IN THE CYLINDER HEAD DURING A 200 HR INSPECTION. CYLINDER NR 2 HAD 798.1 HOURS SINCE NEW. CYLINDER NR 4 HAD 897.8 HOURS SINCE NEW. TOTAL TIME ON ENGINE IS 1504.2 HOURS SINCE OVERHAUL. ALL CYLINDERS WHERE INSTALLED NEW AT OVRHAUL. CYLINDER NR 4 WAS REPLACED AT 606.4 HRS DUE TO CRACKED CYLINDER HEAD. AT 706.0 HRS CYLINDERS 1,2,3,5,6 WHERE ALL REPLACED DUE CRACKED CYLINDER HEADS DETECTED IN CYLINDER ASSY NR 2,3, AND 6 (TC NR 20060514002) 1H71 3O3 O A4CE E5CE 5 CP36EA 20060719000442006071900044SO 2006 7 19 CA060514003 220060429G8530TIST712ACA CYLINDER HEAD CESSNA206 U206G 2073356CE CONT O520 IO520F 17032SO HARTZLHCJ3Y PHCJ3YF1 GL ENGINE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 884 884 572522 (CAN) DURING 200 HR INSPECTION CYLINDERS 1,2, AND 5 WHERE FOUND TO BE CRACKED IN THE CYLINDER HEAD CRACKS WHERE DETECTED VISUALLY AND WITH THE AID OF CYLINDER LEAKAGE CHECK AND SOAP WATER SOLUTION. (TC 20060514003) 1H71 3O3 O A4CE E5CE 5 CP36EA 20060719000452006071900045SO 2006 7 19 CA060514004 220060412G8530TIST712ACA CYLINDER HEAD CESSNA185 A185E 2072818CE CONT O520 IO520D 17032SO MCAULY2A34C D2A34C58 GL ENGINE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 968 968 282670R (CAN) CYLINDERS 3, 1, AND 3 REPLACED DUE TO CRACKED CYLINDER HEAD. ALL CYLINDERS ON THIS ENGINE WHERE REPLACED AT 347.7 HRS SINCE OVERHAUL IAW E.C.I. SB 04-1. (TC NR 20060514004) 1H71 3O3 O 3A24 E5CE 5 CP3EA 20060719000462006071900046EA 2006 7 19 CA060514005 120060510G5610NP13932112 WINDSHIELD CNDAIRCL600 CL6002C10 1390015EA COCKPIT CRACKED W A UNSCHED LANDING O OTHER CLCLIMB 1 CA 1786 (CAN) RT WINDSHIELD CRACKED ON CLIMBOUT AT 7000 FT, A/C RETURNED TO BASE. WINDSHIEL WAS REPLACED IAW AMM. THIS WAS A POST SB WINDHIELD. (TC NR 20060514005) 2L72 4F RTA21EA 20060719000472006071900047EA 2006 7 19 CA060515001 120060510G71102285008114 PANEL CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE NOSE COWL MISSING W O OTHER O OTHER CRCRUISE 1 CA 22295 (CAN) DURING FLT NR 1 ENG NOSE COWL LWR ACCESS PNL DEPARTED AC (ACCESS PNL). FLIGHT EXPERIENCED A SLIGHT BUFFET DURING FLT. UPON LANDING, FLT CREW DISCOVERED NOSE COWL LWR ACCESS PNL WAS MISSING. DAMAGE TO TRANSLATING COWL, UPPER NOSE COWL ACCESS PNL, CAUSED BY DEPARTING LWR ACCESS PNL. NR OF LWR ACCESS PNL FASTENERS WERE FOUND STILL ATTACHED MAIN ENG COWLING. PORTION OF DEPARTED ACCESS PNL WAS FOUND 1500 FT SHORT OF RUNWAY (REMAINDER OF PNL SEC WAS NOT RECOVERED). NEW LWR COWL ACCESS PNL WAS INSTALLED, DAMAGED TRANSLATING COWLING, UPPER NOSE COWL ACCESS PNL WERE REPLACED. SHORTS SB (INSP OF COWLING ACCESS PNL FASTENERS ISSUED SEPT/05) IS PRESENTLY BEING CARRIED OUT ON FLEET. 2L72 4F4 FRTA21EA E15NE 20060719000482006071900048EA 2006 7 19 CA060515002 120060503G2810600626401 VENT LINE CNDAIRCL600 CL600* EA GE CF34 CF341A NE FUEL CORRODED W K NONE O OTHER ININSP/MAINT 1 CA 14534 (CAN) MASTER REFUEL PANEL CHECK TO CHECK VALVE FOR OP, FUEL CAME OUT OF LT NACA SCOOP APPROX 2 GALLON, THEN STOP. MAINT WAS ADVISE THIS WAS ONLY HAPPEN WHEN AC WAS PARKED OVERNIGHT. FIGURED THERE WAS A BAD O-RING IN VENT SYS. FUEL WAS DRAINED, FUEL PANELS REMOVED. NOTICED ON VENT LINE, FUEL WAS LEAKING THRU IT. FOUND PIPE HAD A HOLE, CORRODED. PIPE HAD A CAP INTALLED TO THIS VENT LINE, AN UNNAPROVED MOD WAS C/O ON VENT SYS. SB CAME OUT YEARS EARLIER TO REMOVE DRAIN LINE THAT WAS CONNECTED TO PIPE TO DRAIN ANY FUEL THAT COLLECTED IN VENT SYS BY USE OF EJECTOR PUMP. THIS UNAPPROVED MOD, WATER COLLECTED AT BOTTOM OF PIPE, CORRODED THRU. SB WAS COMPLIED WITH, SYSTEM CHECK SERVICABLE (TC NR 20060515002) 2L72 4F4 FRTA21EA E15NE 20060719000492006071900049EA 2006 7 19 CA060515003 120060503G2810600626401 VENT LINE CNDAIRCL601 CL6012A12 1900303EA GE CF34 CF341A NE CORRODED W K NONE B SMOKE/FUMES/ODORS/SPARKS ININSP/MAINT 1 CA 14534 (CAN) REFUELLING WAS C/O, MASTER REFUEL PANEL CHECK C/O TO CHECK VALVE FOR OPERATION, WHAT WAS NOTICED, FUEL CAME OUT OUT OF THE LT NACA SCOOP APPROXIMATE 2 GALLON, THEN STOP. MAINT WAS ADVISED,THIS WAS ONLY HAPPENING WHEN A/C WAS PARK OVERNIGHT. SO MAINT CREW FIGURED THAT THERE WAS A BAD O-RING IN VENT SYS. A/C RETURED TO MAINT, FUEL WAS DRAINED AND FUEL PANELS REMOVED, FOUND VENT LINE, FUEL WAS LEAKING THRU IT. PIPE WAS REMOVED, FOUND PIPE HAD A HOLE THRU IT, CORRODED. PIPE HAD AN A CAP INTALLED TO THIS VENT LINE, A UNAPPROVED MOD WAS C/O ON VENT SYS. BY DOING THIS UNAPPROVED MOD WATER COLLECTED AT BOTTOM OF PIPE AND CORRODED THRU. S/B WAS COMPLIED WITH AND SYSTEM CHECK SERVICABLE. (TC NR 20060515003) 2L72 4F4 FRTA21AE E15NE 20060719000502006071900050SW 2006 7 19 CA060515004 120060508G6410212010750105 BLADE BELL 212 212 1181420SW PWA PT6T PT6T3 52045EA TAIL ROTOR CORRODED W K NONE O OTHER ININSP/MAINT 1 CA 582 (CAN) AT REASSEMBLY OF T/R BLADES IT WAS NOTED THAT WHITE POWDER WAS PRESENT IN THE CUFF AREA OF THE BLADES. BLADES QTY 2 WERE SENT TO COMPOSITE TECHNOLOGY FOR EVALUATION. BOTH BLADES WERE SCRAPPED DUE TO DEEP CORROSION INSIDE OF UPPER AND LOWER GRIP PLATES. TOTAL TIME ON THE BLADES 582.4 HOURS SINCE NEW. (TC NR 20060515004) 1G71 4U4 U H4SW E22EA 20060719000512006071900051CE 2006 7 19 CA060515005 120060501G5511107326022 SPAR CESSNA185 A185F 2072821CE CONT O520 IO520D 17032SO MCAULYD3A34 D3A34C403 GL HORIZONTAL STAB CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 1535 (CAN) 1) SPAR (P/N 0732602-2 2) REINFORCEMENT (P/N 0732603-1 3) BRACKETS (P/N 0732101-4 ALL 3 OF ABOVE ITEMS WERE FOUND CRACKED AND REPLACED. (TC NR 20060515005). 1H71 3O3 O 3A24 E5CE 5 CP47GL 20060719000522006071900052NE 2006 7 19 CA060515006 220060514G7321 FCU AMD FALC10FALCON10 2730101EU GARRTTTFE731TFE73121C NE INOPERATIVE W O OTHER F FLT CONT AFFECTED LDLANDING 1 CA (CAN) UPON RIGGING OF FCU, LOW IDLE STOPS ON THE THROTTLE QUADRANT WERE ADJUSTED TO ACHIEVE DESIRED 20 DEGREES ON THE FCU. THIS ADJUSTMENT WOULD NOT PHYSICALLY ALLOW THE QUADRANT TO DEPLOY THE THRUST REVERSERS. ENGINES WERE GROUND RUN AND FOUND TO BE SERVICEABLE, ALTHOUGH THRUST REVERSERS WERE NOT CHECKED DURING GROUND RUN. THE THROTTLE QUADRANT ONLY ALLOWS FOR THE THRUST REVERSERS TO BE DEPLOYED IN ONE POSITION. NOTE THAT THE ENGINE FCU MUST BE RIGGED AT THE IDLE POSITION ON THE QUADRANT TO ALLOW THE THRUST REVERSER TO BE DEPLOYED AND TO SET THE IDLE POSITION. (TC NR 20060515006) 2L72 4F4 F A33EU E6WE 20060719000532006071900053CE 2006 7 19 CA060515007 120060512G2150 BLADE CESSNA500 560CESSNA 2076750CE PWA JT15 JT15D5 52112NE ACM BROKEN W K NONE O OTHER CRCRUISE 1 CA 6800 (CAN) THE PILOTS REPORTED THAT THEY HEARED A HUM COMING FROMTHE A/C SYSTEM. THE ACM WAS INSPECTED AND FOUND ONE COMPRESSOR BLADE BROKEN OFF NEAR THE ROOT AND THE OTHER BLADES HAD LEADING EDGE DAMAGE. (TC NR 20060515007) 2L72 4F4 FRTA22CE E25EA 20060606002282006060600228CE 2006 6 6 CA060516001 120060514G2422100160001 INVERTER 100160001 RAYTHNDH125 HAWKER800XP 7150012CE GARRTTTFE731TFE7315BR WP ELECT SYS FAILED W A UNSCHED LANDING J WARNING INDICATION TOTAKEOFF 1 CA 791 1350 AIRCRAFT DEPARTED AND DURING CLIMB-OUT AN INDICATION OF XS1 BUS FAILURE. THE CREW COMPLETED THE COCKPIT ABNORMAL CHECK LIST FOR THE ITEM AND RETURNED TO DEPARTURE. MAINTENANCE WAS ADVISED AND MET THE AIRCRAFT UPON ITS RETURN. INVESTIGATION FOUND THE ODOR OF BURNT ELECTRICAL UPON OPENING OF THE AFT EQUIPMENT BAY DOOR. FURTHER INVESTIGATION REVEALED THE NR 1 STATIC INVERTER TO BE FAILED. AN HOUR HAD ELAPSED SINCE THE AIRCRAFT WAS SHUT DOWN AND THE INVERTER WAS STILL HOT TO THE TOUCH AND THE ODOR OF BURNT ELECTRICAL WAS MOST EVIDENT. THE INVERTER WAS REPLACED AND THE AC ELECTRICAL SYSTEM WAS FUNCTION TESTED SERVICEABLE. THE AIRCRAFT WAS RETURNED TO SERVICE. 2L72 4F4 FRTA3EU E6WE 20061018000742006101800074EA 2006 10 18 CA060516002 120060516G32601EN243R1 INDICATOR CNDAIRCL215 CL2156B11215 EA PWA PW120 PW123 NE HAMSTD14SF 14SF* NE MLG MALFUNCTIONED W O OTHER N FALSE WARNING APAPPROACH 1 CA (CAN) INDICATOR ON THE LT MAIN LANDING GEAR ALWAYS INDICATES UP AFTER SELECTING DOWN. THE UP LOCK INDICATOR SWITCH HAS BEEN REPLACED. AIRCRAFT RETURNED TO SERVICE. 2H72 4T4 TRTA14EA E20NE 6 CP7NE 20060606002272006060600227CE 2006 6 6 CA060516003 120060515G2752505211984 ACTUATOR BEECH 99 99 1154002CE PWA PT6 PT6A27 52043EA RT OB FLAP CRACKED W K NONE O OTHER ININSP/MAINT 1 CA ROUTINE VISUAL INSPECTION OF THE FLAP ACTUATORS INDICATED THAT THE OUTBOARD ATTACHMENT FLANGE OF THE RT OUTBOARD FLAP ACTUATOR WAS CRACKED. THERE WAS NO EVIDENCE OF THE ACTUATOR BEING DROPPED OR OTHERWISE ABUSED. THE FLANGE WAS BENT SLIGHTLY INBOARD AND THERE WAS EVIDENCE OF THE ACTUATOR CHAFFING ON THE MOUNTING FRAME DURING ITS NORMAL OPERATING CYCLE. 1L72 3T4 T A14CE E4EA 20060606002372006060600237CE 2006 6 6 CA060516004 120060513G551007321014 REINFORCEMENT CESSNA 12320008 CESSNA185 A185F 2072821CE CONT O520 IO520D 17032SO STABILIZER CRACKED W K NONE F FLT CONT AFFECTED NRNOT REPORTED 1 CA EXCESSIVE MOVEMENT FOUND AT AFT LT HINGE ASSY, INSIDE REINFORCEMENT P/N 0732106-1, ALSO FOUND CRACKED. 1H71 3O3 O 3A24 E5CE 20060606002382006060600238SO 2006 6 6 CA060516005 120060503G7931AS349101 GASKET LYC LIO540J2BD PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA ENGINE DAMAGED W K NONE K FLUID LOSS CRCRUISE 1 CA L217368A WHILE FLYING CRUISE FLIGHT NOTICED ENGINE OIL PRESSURE DROPPING. SHUT DOWN RT ENGINE AND RETURNED TO BASE. UPON INVESTIGATION FOUND THAT THE GASKET UNDERNEATH VACUUM PUMP DAMAGED. VACUUM PUMP CHANGED PRIOR TO FLIGHT. OIL LEAK NOT DETECTED ON RUN UP. GASKET P/N AS3491-01 REPLACED. AIRCRAFT GROUND RUN LEAK CHECKED OK. NO FURTHER DAMAGE FOUND. 1L72 3O3 O A20SO E14EA 20060606002402006060600240NM 2006 6 6 CA060516007 120060513G5610141480149 WINDSCREEN PPG 141480149 BOEING767 767* NM GE CF6 CF680C2B6F 30025NE COCKPIT FAILED W K NONE O OTHER CRCRUISE 1 CA 93026H4349 LOCATION APPROX 30 DEGREES WEST AT FL 320 - IAS M .8 AS REPORTED BY THE FLIGHT CREW: WHILE IN CRUISE THE FLIGHT CREW NOTICED A CRACK STARTING IN THE UPPER LEFT CORNER OF THE CAPTAINS FORWARD WINDOW (NR 1) WITH IN A FEW MINUTES THE CRACK HAD SPREAD ALMOST ALL THE WAY TO THE FAR RIGHT. SHORTLY AFTER THAT THE CREW OBSERVED ARCING OF THE WINDOW HEATER ELEMENT AND LEFT THE WINDOW HEAT IN THE OFF POSITION. APPROXIMATELY ONE MINUTE LATER THE ENTIRE VIEWING AREA OF THE WINDOW CRAZED. THE FLIGHT CREW OBSERVED THE CRAZING TO BE THE OUTER PLY AND CONTINUED THE FLIGHT WITHOUT FURTHER INCIDENT. 2L72 4F4 FRTA1NM E13NE 20060607002362006060700236WP 2006 6 7 CA060516008 120060512G2497 WIRE HARNESS GENDYN CV580A CVAC 440 440 2422902WP ALLSN 501D 501D13D 03004GL ELT WIRING CHAFED W K NONE O OTHER ININSP/MAINT 1 CA 374 DURING INSTALLATION OF ELT REMOTE SWITCH WIRING, ROUTING OF THE WIRE BEHIND THE FORWARD RT EQUIPMENT SHELF, SEVERAL WIRES WERE FOUND CHAFING INTO THE WIRE BUNDLE THAT RUNS VERTICALLY BEHIND THE SHELF. THE WIRES WERE CHAFING ON THE BACK EDGE OF THE FLOOR. THE WIRING WAS REPAIRED AND SECURED AND THE FLOOR WAS TRIMMED TO ENSURE ADEQUATE CLEARANCE. ALL OTHER AIRCRAFT IN THE FLEET WERE INSPECTED WITH NO OTHER DAMAGE REPORTED. 2L72 4R4 T 6A6 E282 20060607002372006060700237SO 2006 6 7 CA060516009 120060424G32306750200 PIN PIPER 7872322 PIPER PA44 PA44180 7104402SO LYC O360 O360* 41514EA MLG CORRODED W K NONE O OTHER ININSP/MAINT 1 CA 4099 DURING LT MLG GEAR REMOVAL A SUBSTANTIAL AMOUNT OF WATER WAS OBSERVED INSIDE MLG RETAINER PIN ASSY. FURTHER INVESTIGATION REVEALED DEEP PITTING ON INNER SURFACE OF PIN, LOSS OF APPROX 50 PERCENT OF CHROME PLATING ON EXT OF PIN AND ASSY RETENTION BOLT HAD LOST APPROX 35% OF IT'S SHANK DIAMETER NEAR TO IT'S HEAD. FAILURE OF THIS BOLT WOULD ALLOW RETAINER PIN TO MIGRATE OUT OF POSITION AND RESULT IN MLG COLLAPSE. THIS DAMAGE BEARS RESEMBLENCE TO A SERVICE DIFFICULTY ALERT AL-2004-06 REPORTED IN 2004. RT RETAINER PIN ASSY ALSO SHOWED SEVERE CORROSION. MLG RETAINER PIN ASSEMBLIES WERE REPLACED WITH NEW AND UPON INSTALLATION RETAINER PIN CAVITIES WERE PACKED WITH GREASE TO EXCLUDE WATER FROM THIS AREA. 1L72 3O3 O A19S0 E286 20060607002382006060700238SO 2006 6 7 CA060516010 120060418G32116750200 PIN PIPER 7872322 PIPER PA44 PA44180 7104402SO LT MLG CORRODED W K NONE O OTHER ININSP/MAINT 1 CA 3599 DURING LT MLG REMOVAL SEVERE CORROSION WAS OBSERVED ON THE INNER SURFACE OF THE MLG RETAINER PIN. FURTHER INVESTIGATION REVEALED LOSS OF APPROXIMATELY 50% OF THE OUTER CHROME SURFACE AND THE PIN RETENTION BOLT HAD LOST 20% OF IT'S SHANK DIAMETER NEAR TO THE HEAD. INSPECTION OF THE RT RETAINER PIN ASSEMBLY ON THIS AIRCRAFT ALSO SHOWED SIMILAR DAMAGE. FAILURE OF THIS BOLT WOULD ALLOW MIGRATION OF THE RETAINER PIN AND COLLAPSE OF THE MLG ASSEMBLY. BOTH MLG RETAINER PIN ASSEMBLIES WERE REPLACED WITH NEW AND UPON INSTALLATION THE RETAINER PIN CAVITIES WERE PACKED WITH GREASE TO EXCLUDE WATER FROM THIS AREA. 1L72 3O A19S0 20060607002392006060700239EA 2006 6 7 CA060517002 120060516G612378249047 PCU HAMSTD 78249047 DHAV DHC8 DHC8311 1386006EA PWA PW120 PW123 NE HAMSTD14SF 14SF15 NE NR 1 PROP SYS FAULTY W EA ENGINE SHUTDOWN UNSCHED LANDING FR FLT CONT AFFECTED PARTIAL RPM/PWR LOSS CRCRUISE 1 CA 1753 1753 970834 SHORTLY AFTER TAKEOFF, NR 1 PROP WENT SLOWLY IN AND OUT OF FEATHER (GENTLY) THREE TIMES. PRECAUTIONARY SHUT DOWN OF NR 1 ENGINE CARRIED OUT. AIRCRAFT DIVERTED TO NEAREST AIRPORT. MAINTENANCE INSPECTED AND REPLACED NR 1 PROP CONTROL UNIT, GROUND RUN AND LEAK CHECKED SERVICEABLE. AIRCRAFT RETURNED TO SERVICE. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20060607002452006060700245NE 2006 6 7 CA060517003 120060505G2720S616561500 DAMPER SKRSKY S616561500 SKRSKYS61 S61N 8142104NE GE CT58 CT581402 30011NE YAW CONT SYS LEAKING W H DEACTIVATE SYST/CIRCUITS KF FLUID LOSS FLT CONT AFFECTED APAPPROACH 1 CA 19511256 990281 PILOT FELT A YAW ON APPROACH, AND AFTER CONFIRMING A YAW HARDOVER, SWITCHED OFF AUX HYDRAULICS, AND CONTINUED TO LAND. ON INSPECTION IT WAS FOUND THAT THE PEDAL DAMPER WAS LEAKING EXCESSIVELY DUE TO A BROKEN BOLT AND CAP. 2G72 4U4 U 1H15 1E3 20060607002462006060700246WP 2006 6 7 CA060518001 120060512G801072566 RING GEAR LYC 31M22972 ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540* 41532EA ENGINE DAMAGED W K NONE O OTHER TXTAXI/GRND HDL 1 CA 572 THE PILOT REPORTED DIFFICULTY STARTING THE AIRCRAFT. UPON INSPECTION TEETH WERE NOTED TO BE MISSING OFF THE STARTER RING GEAR. THE ASSEMBLY WAS REPLACED. THE STARTER DID NOT HAVE ANY DEFECTS ON THE DRIVE GEAR, AND WAS NOT REPLACED. ROBINSON KNOWS THERE IS A PROBLEM WITH THE STARTER RING GEARS. THEY HAVE CHANGED THE BRANDS OF STARTERS INSTALLED AT THE FACTORY FROM B&C TO SKYTEC. THIS AIRCRAFT HAS THE B&C STARTER INSTALLED. 1G71 3O3 O H11NM 1E4 20060626000192006062600019WP 2006 6 26 CA060518002 120060502G801172566 GEAR ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE STARTER DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA 634 PILOT REPORTED DIFFICULTY STARTING THE AIRCRAFT. TEETH WERE FOUND TO BE MISSING FROM THE STATER RING GEAR. THE STARTER RING GEAR ASSEMBLY WAS REPLACED. AIRCRAFT TAFT 1187.3. 1G71 3O3 O H11NM 1E4 20060607002472006060700247CE 2006 6 7 CA060518003 120060511G324634A2000204 STRUT 3450A CESSNA185 A185F 2072821CE CONT O520 IO520D 17032SO ATTACH FITTING SHEARED W K NONE O OTHER LDLANDING 1 CA 260 34122 DURING TOUCH DOWN, INSTRUCTOR HEARD THE VOICE ADVISORY SYSTEM WITH THE MESSAGE "CHECK GEAR" AND LOST THE LIGHT ON THE BLOCK INDICATOR P/N 2A11179-001 ON THE RIGHT AND SIDE. DECIDED TO LAND ON LAKE WITH SMALLER WAVE WITH NO PROBLEM. THE INSTRUCTOR FOUND THE FORWARD STRUT RT P/N 34A2000-204 BROKEN AT THE ATTACHMENT FITTING UPPER FORWARD RT P/N 34A2062-014. 1H71 3O3 O 3A24 E5CE 20060626000202006062600020CE 2006 6 26 CA060518004 120060508G561010138402523 WINDSCREEN BEECH 1900 1900C 1154161CE PWA PT6 PT6A65B 52043EA HARTZLHCB4M HCB4MP3 GL COCKPIT FAILED W K NONE O OTHER ININSP/MAINT 1 CA 4401 WINDSCREEN INSIDE PANE SHATTERED IN FLIGHT. 2L72 4T4 TRTA24CE E4EA 6 CP56GL 20060608002872006060800287EA 2006 6 8 CA060519001 120060518G5314NAS110410 BOLT DHAV DHC8 DHC8311 1386006EA PWA PW120 PW123 NE HAMSTD14SF 14SF23 NE KEELBEAM MISSING W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA LT AND RT FWD (STN387) KEEL BEAM (STR 31L/31R) TO FRONT SPAR ATTACH BOLTS MISSING (X2). BOLTS NOT INSTALLED BY MANUFACTURER REF IPC 53-41-00 FIG 10 ITEMS 330, 333 AND 335. A/C TOTAL TIME 14.0 HRS. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20060612003292006061200329SO 2006 6 12 CA060519002 220060518G8530TIST712ACA CYLINDER HEAD CESSNA206 U206G 2073356CE CONT O520 IO520F 17032SO HARTZLHCJ3Y PHCJ3YF1 GL ENGINE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 1390 1390 293447R CYLINDERS 5 - 6 WERE FOUND TO HAVE CRACKED CYLINDER HEADS DURING A CYLINDER LEAKAGE CHECK. A SOAP WATER SOLUTION WAS USED TO AID IN LOCATING THE CRACKS. 1H71 3O3 O A4CE E5CE 5 CP36EA 20060612003312006061200331NM 2006 6 12 CA060519003 120060518G271082740037101 SPRING DHAV DHAV DHC8 DHC8202 2809007NM GUST LOCK BROKEN W K NONE O OTHER ININSP/MAINT 1 CA 1 OF 2 AILERON GUST LOCK SPRINGS FOUND BROKEN WHEN PANELS REMOVED TO PERFORM OTHER MAINTENANCE REF IPC 27-12-00 FIG 20, ITEM 210. AIRCRAFT TOTAL TIME 19575 HOURS, 12119 CYCLES. 2H72 4T RTA13NM 20060612003332006061200333NE 2006 6 12 CA060521001 220060518G73146272017203 SUPPORT BRACKET CNDAIRCL600 CL6002C10 1390015EA GE CF34 CF34* NE BROKEN W E ENGINE SHUTDOWN KJ FLUID LOSS WARNING INDICATION APAPPROACH 1 CA PRIOR TO FLT, PILOTS CALLED TO HAVE RT SERVICED WITH OIL. MECHS NOTICED RT HAD BEEN SERVICED SEVERAL TIMES IN RECENT HISTORY. INVESTIGATION FOUND BROKEN BRACKET THAT HOLDS EDP OUTLET HYD LINE TO AGB. BROKEN BRACKET HAD CHAFED A HOLE IN AGB CASING CAUSING OIL LEAKAGE. ACCORDING TO LOGBOOK IN RDU 3 QTS OIL WAS ADDED TO RT ENG BEFORE FERRY FLT. NO ENG RUNS BEFORE FERRY TO DESTINATION WHERE IT WAS NOTED, HYD LINE WAS NOT SECURED NOR WAS BRACKET REMOVED. OIL LVL PER EICAS WAS 14%. OIL ALL OVER COWLING AND BACK OF ENG. 14% LOW OIL LVL IS CONSISTENT WITH LOW OIL PRESS IN FLT AND QRH PILOT COMMANDED IFSD. MESA HAVE GE A/C SERV ON SITE TO ROB AN AGB FROM A SPARE ENG AND INSTALL THIS A/C 10104 RT. INITIAL "ROOT C2L72 4F4 FRTA21EA E15NE 20060612003342006061200334EA 2006 6 12 CA060523001 120060522G783022850291109 ARM CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE THRUST REVERSER FAILED W K NONE O OTHER ININSP/MAINT 1 CA NA DURING AN "R" CHECK, LINE MAINTENANCE FOUND THE LT THRUST REVERSER BLOCKER DOOR AT THE 5 O'CLOCK POSITION TORN OUT. THE ACTUATING ROD (P/N 228-50291-109) WAS STUCK THROUGH THE DIVERTER FAIRING IPC REF 78-34-01. AREA INSPECTED FOR POSSIBLE DAMAGE TO FAN CASE, NONE FOUND. DIVERTER FAIRING (LOWER PORTION) REPLACED. BLOCKER DOOR AND ACTUATING ROD REPLACED. LEFT THRUST REVERSER CHECKED SERVICEABLE AND AIRCRAFT RETURNED TO SERVICE. 2L72 4F4 FRTA21EA E15NE 20060612003352006061200335NM 2006 6 12 CA060523002 120060519G56105893543129 WINDOW BOEING737 737522 138449FNM CFMINTCFM56 CFM563C1 13802EU COCKPIT CRACKED W B EMER. DESCENT O OTHER CRCRUISE 1 CA CAPTAINS NR 1 WINDOW SPIDER CRACKED AT 34,000 FT, WINDOW CRACKED THROUGH OUT 50% OF THE WINDOW IN THE OUTER PANE ONLY. AIRCRAFT FERRIED TO BASE FOR NR 1 WINDOW CHANGE. 2L72 4F4 FRTA16WE E21EU 20060612003362006061200336EA 2006 6 12 CA060523003 220060418G7314AF15472 PUMP PIPER PA28 PA28151 7102805SO LYC O320 O320E3H 41508EA SNSNCH74D 74DM EA FUEL SYS FAILED W O OTHER YJ ENGINE STOPPAGE WARNING INDICATION CRCRUISE 1 CA THIS MECHANICAL FUEL PUMP HAS BEEN INSTALLED NEW. ENGINE RUN-UP DONE WITHIN PARAMETER WITH FUEL PRESSURE NORMAL AT ALL RPM ON GROUND STATIC RUN-UP. OWNER RUN-UP BEFORE FLIGHT FOUND FUEL PRESSURE NORMAL. INFLIGHT IN CRUISE DURING CIRCUIT AT THE AIRPORT ENGINE QUIT AND RESTART AFTER WITH ELECTRIC PUMP ON. THE FUEL GAUGE PRESSURE SHOWING FULL 10 PSI AND STAY AT 10. ON GROUND FUEL SYSTEM CHECK WITH GROUND EQUIPMENT TESTER SHOWING RIGHT INDICATING ON AIRCRAFT GAUGE. PUMP REPLACED WITH NEW LYCOMING PUMP, RUN-UP DONE AND FLIGHT TEST OK. DEFECTIVE PUMP RETURNED TO ENGINE SHOP. 1L71 3O3 O 2A13 E274 5 NP88614 20060626000352006062600035WP 2006 6 26 CA060523004 120060512G2510C6284 BUCKLE ROBSINR44 R44 7640120WP LYC O540 O540F1B5 41532EA STRAP CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) METAL STRAP BETWEEN MOUNTING POINT AND BUCKLE IS CRACKED IN TWO. TIME ON THIS PART IS UNKNOWN. TAFT 5902 MFG HAS DEVELOPED A NEW SEAT BELT BUCKLE THAT REPLACES THE STAINLESS STEEL STRAP WITH A FABRIC STRAP. (TC NR 20060523004) 1G71 3O3 O H11NM E295 20060612003382006061200338CE 2006 6 12 CA060523005 120060516G5340NAS57712A NUT MTSBSIMU2 MU2B36A 5780413CE GARRTTTPE331TPE3315 01514WP HARTZLHCB4T HCB4TN5 GL WING CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 17439 WHILE CARRYING OUT A WINGS OFF INSPECTION AND COMPLYING WITH SERVICE BULLETIN 103/57-004 WING ATTACHMENT HARDWARE. INSPECTION, THE RT LOWER FORWARD WING ATTACH BOLT BARRELL NUT WAS FOUND CRACKED THROUGH THE ENTIRE THREADED PORTION OF THE NUT. THE NUT WAS REPLACED AND TORQUED IN ACCORDANCE WITH THE S/B RECOMMENDATIONS. 1H72 3T4 T A10SW E4WE 6 CP40EA 20060626000362006062600036WP 2006 6 26 CA060523006 120060522G2497C05914 WIRE ROBSINR44 R44RAVENII 7640122WP LOOSE W K NONE O OTHER ININSP/MAINT 1 CA 17 (CAN) WHILE INSTALLING OPERATIONAL GEAR INTO A NEW AIRCRAFT, THE MAIN LEAD TO THE BUS BAR ON THE CIRCUIT BREAKER PANEL WAS FOUND LOOSE. THE HARDWARE DID HAVE A LOCK WASHER. THIS SAME PROBLEM WAS FOUND ON OTHER AIRCRAFT. (TC NR 20060523006) 1G71 3O H11NM 20060626000372006062600037WP 2006 6 26 CA060523007 120060522G2497C05914 WIRE ROBSINR44 R44RAVENII 7640122WP LOOSE W K NONE O OTHER ININSP/MAINT 1 CA 17 (CAN) WHILE INSTALLING OPERATIONAL GEAR INTO A NEW AIRCRAFT, THE MAIN LEAD TO THE BUS BAR ON THE CIRCUIT BREAKER PANEL WAS FOUND LOOSE. THE HARDWARE DID HAVE A LOCK WASHER. THIS SAME PROBLEM WAS FOUND ON OTHER AIRCRAFT. (TC NR 20060523007) 1G71 3O H11NM 20060626000382006062600038WP 2006 6 26 CA060523008 120060522G2497C05914 WIRE ROBSINR44 R44RAVENII 7640122WP LOOSE W K NONE O OTHER ININSP/MAINT 1 CA 17 (CAN) WHILE INSTALLING OPERATIONAL GEAR INTO A NEW AIRCRAFT, THE MAIN LEAD TO THE BUS BAR ON THE CIRCUIT BREAKER PANEL WAS FOUND LOOSE. THE HARDWARE DID HAVE A LOCK WASHER. THIS SAME PROBLEM WAS FOUND ON OTHER AIRCRAFT. (TC NR 20060523008) 1G71 3O H11NM 20060626000392006062600039WP 2006 6 26 CA060523009 120060522G2497C05914 WIRE ROBSINR44 R44RAVENII 7640122WP LOOSE W K NONE O OTHER ININSP/MAINT 1 CA 17 (CAN) WHILE INSTALLING OPERATIONAL GEAR INTO A NEW AIRCRAFT, THE MAIN LEAD TO THE BUS BAR ON THE CIRCUIT BREAKER PANEL WAS FOUND LOOSE. THE HARDWARE DID HAVE A LOCK WASHER. THIS SAME PROBLEM WAS FOUND ON OTHER AIRCRAFT. (TC NR 20060523009) 1G71 3O H11NM 20060612003402006061200340NM 2006 6 12 CA060523010 120060523G531514A55067 FLOORBEAM BOEING737 737724 13844BYNM BS 986 CORRODED W K NONE O OTHER ININSP/MAINT 1 CA F001924 FOUND FLOORBEAM AT BS 986 CORRODED AT CLIPNUT HOLES BETWEEN RBL 47 AND RBL 18. 2L72 4F RTA16WE 20060612003412006061200341NM 2006 6 12 CA060523011 120060523G5315141A550424 FLOORBEAM BOEING737 737724 13844BYNM BS 328 CORRODED W K NONE O OTHER ININSP/MAINT 1 CA 28786 FOUND FWD CABIN AREA FLOORBEAM AT 328 BRL 41 CORRODED. 2L72 4F RTA16WE 20060612003422006061200342NM 2006 6 12 CA060523012 120060523G33507002246001 LIGHT BOEING737 737724 13844BYNM SEAT ROW 14ABC INOPERATIVE W K NONE O OTHER ININSP/MAINT 1 CA FOUND SEAT ROW 14ABC RED EMERG EXIT LIGHT DOES NOT ILLUMINATE. 2L72 4F RTA16WE 20060613000462006061300046SW 2006 6 13 CA060524001 120060519G6320212030154101 FITTING BELL 205 205A1 1181414SW LYC T53 T5317A 41549NE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA AIRCRAFT WAS ON SEISMIC DRILL MOVE JOB. THE ENGINEER WAS DOING HIS DAILY INSPECTION WHEN NOTICED THAT ONE EAR OF THE LIFT LINK FITTING WAS APPEARED CRACKED. A CLOSER VISUAL LOOK CONFIRMED IT WAS CRACKED. INVESTIGATING IF THE BUSHING WAS WRONG FOR THIS INSTALLATION. THE BELL 205 PARTS MANUAL AND TB 205-91-88 ARE NOT TO CLEAR OF THE DIFFERENT BUSHINGS NEEDED. 1G71 4U4 U H1SW E17EA 20060613001242006061300124GL 2006 6 13 CA060524002 120060512G3246VALTBS12091 WHEEL DHAV DHC2 DHC2MKI 2801830GL PWA R985 R98539A 52008NE HARTZLHCB3R HCB3R304 GL MLG CORRODED W K NONE O OTHER ININSP/MAINT 1 CA 804 THIS PART WAS INSTALLED MAY 31/04 IN ACCORDANCE WITH VIKING AIR GROSS WEIGHT INSTRUCTION. IT WAS NOTICED THAT EARLY CORROSION HAD BEGUN AT THE WHEEL GEAR ATTACHMENT HOLE. THE CORROSION WAS DEEP AND THE PART WAS REPLACED WITH A NEW UNIT. POSSIBLE CAUSE FOR THE PREMATURE CORROSION IS WHEN THE STEEL BUSH WAS INSTALLED, REMOVING THE ANNODIZING FROM THE MACHINED HOLE, THAN ALLOWING DISSIMILAR CORROSION TO HAPPEN. 1H71 3R3 RRCA806 5E1 5 CP28EA 20060626000402006062600040EU 2006 6 26 CA060524003 120060519G6220350A37122823 YOKE SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1D1 NE M/R HEAD & MAST MISSING W K NONE O OTHER ININSP/MAINT 1 CA (CAN) THE ENGINEER WAS LOOKING AT THE AIRCRAFT AND NOTICED THE THE M/R STATIC STOP YOKE BROKEN OFF AND MISSING OUT OF 3. THE OTHER STATIC STOPS WERE INSPECTED AND FOUND ONE CRACKED. THE AC WAS GROUNDED AND APPROPRIATE PARTS WERE ORDERED. (TC NR 20060524003) 1G71 3U3 U H9EU E19EU 20060626000412006062600041SO 2006 6 26 CA060524004 120060521G2822A10014D44 PUMP PIPER PA31 PA31 7103102SO LYC O540 TIO540A2C 41532EA HARTZLHCE3Y HCE3YR2A GL FUEL BOOST FAILED W O OTHER O OTHER NRNOT REPORTED 1 CA 1097 (CAN) PILOT REPORTED RT FUEL BOOST PUMP UNSERVICEABLE. TROUBLESHOOTING FOUND POWER TO THE PUMP. WHEN THE PUMP WAS CHECKED, THERE WAS NO CONTINUITY THROUGH THE PUMP. THE REPLACMENT PUMP WAS CHECKED AND FOUND TO HAVE 13 OHMS. (TC NR 20060524004) 1L72 3O3 O A20SO E14EA 5 CP33EA 20060613001262006061300126SO 2006 6 13 CA060524005 120060514G81204066109020 TURBOCHARGER PIPER PA31 PA31 7103102SO LYC O540 TIO540A2C 41532EA HARTZLHCE3Y HCE3YR2A GL ENGINE LEAKING W K NONE O OTHER ININSP/MAINT 1 CA 872 DURING INSPECTION, OIL WAS FOUND IN BOTH THE COMPRESSOR AND TURBINE SECTIONS OF THE TURBO. THIS INDICATES THAT THE CENTER SECTIONS OIL SEALS WERE FAILING. 1L72 3O3 O A20SO E14EA 5 CP33EA 20060613001282006061300128EA 2006 6 13 CA060524006 220060514G7314200F5002 PUMP PIPER PA31 PA31 7103102SO LYC O540 TIO540A2C 41532EA HARTZLHCE3Y HCE3YR2A GL FUEL SYSTEM LOW PRESSURE W O OTHER O OTHER TXTAXI/GRND HDL 1 CA 980 DURING GROUND RUN, FUEL PRESSURE OUTPUT FROM THE LEFT ENGINE WAS BELOW NORMAL, AND WOULD FLUCTUATE AT LOWER IDLE SPEEDS. THE FUEL SERVO SCREEN WAS CHECKED DURING THE INSPECTION AND BITS OF METAL WERE FOUND. THE PUMP WAS REMOVED AND WHEN THE DRIVE SPLINE WAS ROTATED BY HAND A RESISTANCE TO ROTATION WAS FELT AT A CERTAIN POINT. 1L72 3O3 O A20SO E14EA 5 CP33EA 20060627000852006062700085SW 2006 6 27 CA060524007 120060519G284151509002 CONTROL UNIT BELL 212 212 1181420SW PWA PT6T PT6T3 52045EA FUEL QTY IND MALFUNCTIONED W O OTHER L NO TEST CRCRUISE 1 CA (CAN) TROUBLESHOOTING A FUEL QUANTITY INDICATING A/C SYSTEM DEFECT. WITH BOTH POWER SECTIONS RUNNING THE FUEL QUANTITY INDICATION WOULD CHANGE WITH NO FUEL ADDED. FUEL QUANTITY SELECTOR WOULD BE POSITIONED TO LT TANK AND VERY SLOWLY THE INDICATOR WOULD SHOW THE CORRECT QUANTITY. THEN MOVE THE SELECTOR TO RT TANK AND THE FUEL QUANTITY WOULD REACT VERY SLOWLY THE FUEL INDICATOR WOULD READ THE CORRECT QUANTITY. THEN MOVE THE SELECTOR BACK TO THE LEFT TANK AND THE READING WOULD BE DIFFERENT THAN THE ORIGINAL FUEL INDICATION. WHAT WAS FOUND THE LEFT DC CONTROL UNIT WAS AFFECTING THE A/C FUEL QUANTITY INDICATING SYSTEM. UNIT REPLACED, FUNCTIONAL/ OPERATIONAL TEST, A/C RETURNED TO SERVICE. (TC NR 20060524007) 1G71 4U4 U H4SW E22EA 20060628002192006062800219SW 2006 6 28 CA060524008 120060524G6320214030606005 SPINDLE BELL 214 214B 1182100SW LYC T55 T5508D 41555NE TRANSMISSION BROKEN W A UNSCHED LANDING Z SIGNIFICANT FAILURE REPORT HOHOVERING 1 CA 1928 AME52013 DONT HAVE ANY OTHER INFO AT THIS TIME, AS THIS INCIDENT JUST OCCURRED THIS MORNING. WILL ADD INFORMATION AS IT COMES IN. THIS INCIDENT SEEMS VERY SIMILAR TO ONE 16 OCT 1996 NTSB REPORT NUMBER A96P0231. WITH ONE GOOD DIFFERENCE, NO LOSS IN FLIGHT CONTROL AND SAFE LANDING. PART WAS NOTED AND X-RAYED AT TIME OF OVERHAUL. 2G71 4U4 U H6SW E4NE 20060613001312006061300131NE 2006 6 13 CA060524009 220060520G72509609000408 BEARING SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1D1 NE GAS GEN FLAKING W A UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 CA 1284 10050TEC WHILE IN CRUISE, THE PILOT HAD AN ENGINE CHIP INDICATION AND RETURNED TO BASE. THE AME LOOKED AT THE REAR BEARING CHIP DETECTOR AND FOUND METAL ON THE PLUG. 1G71 3U3 U H9EU E19EU 20060613001332006061300133NM 2006 6 13 CA060525001 120060517G561007802 WINDSHIELD DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE COCKPIT CRACKED W O OTHER O OTHER DEDESCENT 1 CA UPON DESCENT BETWEEN 8000 FT AND 9000 FT, THE CREW NOTICED SPARKS COMING FROM THE LT WINDSHIELD. SIMULTANEOUSLY, THE WINDSHIELD DEVELOPED A CRACK. THE WINDSHIELD HEAT WAS IMMEDIATELY TURNED OFF AND THE AIRCRAFT WAS DEPRESSURIZED. THE AIRCRAFT LANDED SAFELY 10 MINUTES LATER WITH NO FURTHER INCIDENT. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20060613001342006061300134NM 2006 6 13 CA060525002 120060513G7931 O-RING JANITROL DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE OIL COOLER FAILED W A UNSCHED LANDING J OWARNING INDICATION OTHER CLCLIMB 1 CA 560 L86026903 AIRCRAFT DEPARTED NORMALLY AND ON CLIMB-OUT, THE NR 2 OIL PRESSURE ANNUNCIATOR ILLUMINATED BRIEFLY, AIRCRAFT THEN RETURNED TO DEPARTURE AIRPORT. MAINTENANCE INVESTIGATION REVEALED THAT THE NR 2 OIL COOLER WAS LEAKING OIL AND OIL WAS LEAKING FROM THE VERNATHERM VALVE ASSEMBLY. THE OIL COOLER WAS REPLACED AND THE VERNATHERM VALVE ASSEMBLY (45E04-1) WAS TRANSFERRED TO THE NEW OIL COOLER WITH NEW O-RINGS (25C85-128/129/130). GROUND RUNS CARRIED OUT AND NO LEAKS EVIDENT. AIRCRAFT RETURNED TO SERVICE. OIL COOLER REMOVED IS OUT FOR REPAIR AT THIS TIME. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20060613001382006061300138WP 2006 6 13 CA060525003 220060525G7200 ENGINE BAG JETSTMJETSTM3212 1500217EU GARRTTTPE331TPE33110UG 01514WP RIGHT MALFUNCTIONED W O OTHER RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 1 CA IN CRUISE, RT ENGINE TORQUE INCREASED TO 104.5%, WHEN TTL TURNED OFF WENT TO 120%. FUEL FLOW ON RT ENG DROPPED TO 200LBS. 2L72 4T4 TRTBA15CAA E4WE 20060626000422006062600042CE 2006 6 26 CA060525004 120060524G575335165050271 BRACKET BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE HARTZLHCE4A HCE4A3A NE ACTUATOR CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 7347 (CAN) DURING A BASE INSPECTION THE RT OB FLAP ACTUATOR BRACKET WAS FOUND CRACKED. WHEN THE BRACKET WAS REMOVED FROM THE SKIN, IT WAS DISCOVERED THAT THE SKIN WAS ALSO CRACKED. FURTHER INSPECTION REVEALED THAT THE RIB UNBER THE SKIN WAS ALSO DAMAGED. THE FLAP WILL BE REPLACED. (TC NR 20060525004) 2L72 4T4 TRTA24CE E26NE 5 CP10NE 20060613001392006061300139NM 2006 6 13 CA060525005 120060525G5330 SKIN BOEING737 7372Q8C 138448SNM BS 245 GOUGED W K NONE O OTHER ININSP/MAINT 1 CA FOUND SKIN GOUGE AT BS 245 2" INBD OF STR 25L. REPAIRED IAW CUSTOMER EA. 2L72 4F A16WE 20060613001412006061300141NM 2006 6 13 CA060525006 120060525G5330 SKIN BOEING737 7372Q8C 138448SNM BS 1016-1028 DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA EXISTING REPAIR AT BS 1016 AND 1028 FROM STR 15L TO 12L DAMAGED BEYOND LIMITS (DENTED) AND REPAIR IAW CUSTOMER EA. 2L72 4F A16WE 20060613001432006061300143NM 2006 6 13 CA060525007 120060525G5311 FRAME BOEING737 7372Q8C 138448SNM BS 490 S24R CRACKED W K NONE O OTHER ININSP/MAINT 1 CA FWD PIT DOOR WAY AFT FRAME BS 490 STR 24R CRACKED AND REPAIRED IAW CUSTOMER EA. 2L72 4F A16WE 20060613001922006061300192EA 2006 6 13 CA060526001 220060525G72503037347 SHROUD BEECH 1900 1900C 1154161CE PWA PT6 PT6A65B 52043EA HARTZLHCB4M HCB4MP3 GL ENGINE LOOSE W C ABORTED TAKEOFF MJ OVER TEMP WARNING INDICATION TOTAKEOFF 1 CA 90 DURING TAKEOFF ROLL IT WAS NOTED, RT ENG ITT WAS AT RED LINE AND ENG TQ WAS BELOW REQUIRED T/O VALUE. T/O WAS ABORTED AND A/C RETURNED TO RAMP. DURING MX INVESTIGATION, LARGE INCREASES IN ITT READINGS COULD BE SEEN WHEN SELECTING BLEED AIR ON OR ACCELERATING ENG. ENGINE WAS SPLIT AT THE C FLANGE AND THE CT VANE SHROUD SEGMENTS WERE FOUND TO BE LOOSE AND CONTACTING THE CT DISC BLADES. PART OF ONE SEGMENT WAS MISSING AND THERE WAS IMPACT DAMAGE NOTED ON THE PT TURBINE WITH METAL IN THE EXHAUST STACKS. ENGINE IS BEING REPLACED AND SENT FOR INVESTIGATION AND REPAIR TO AN APPROVED ENGINE OVERHAUL FACILITY. THE ENGINE HAS COMPLETED 90 HOURS SINCE THE LAST HOT SECTION REPAIR. 2L72 4T4 TRTA24CE E4EA 6 CP56GL 20060613001932006061300193SO 2006 6 13 CA060526002 120060406G8120LW1277885 BYPASS VALVE GARRTT PIPER PA31 PA31 7103102SO LYC O540 TIO540A2C 41532EA HARTZLHCE3Y HCE3YR2A GL TURBOCHARGER CRACKED W O OTHER RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 1 CA 3118 3118 RIGHT ENGINE NOT DEVELOPING INCHES OF HG. AFTER RUN-UP AND ATTEMPTED TO ADJUST DENSITY CONTROLLER, WASTEGATE (VALVE - EXHAUST BYPASS) WAS CHECKED AND BUTTERFLY VALVE FOUND TO BE ROTATING FREELY ON ITS SHAFT. AFTER REMOVAL OF SAID PART, THE WASTEGATE VALVE WAS INSPECTED AND SHOWED SIGNS OF CORROSION, CRACKING AND CORRODED/SHEARED HOLDING STUD. ENGINE WAS ON CONDITION, NORMAL OPERATION WAS ACHIEVED AFTER REPLACEMENT OF PART. 1L72 3O3 O A20SO E14EA 5 CP33EA 20060626000432006062600043GL 2006 6 26 CA060526003 220060524G75101885M24601 DUCT BOEING767 767375 1385217NM GE CF6 CF680C2* GL 11TH STAGE RUPTURED W E ENGINE SHUTDOWN J WARNING INDICATION CLCLIMB 1 CA 10356497 (CAN) L GEN CONT MSG ILLUMINATED, IN FLIGHT CHECKLIST C/O, L GENERATOR CONTROL REMAINED OFF. ON CLIMB OUT, L OIL PRESS EICAS FLASHED RED NUMBERS DECREASING WENT BLANK - OIL TEMP INCREASING -QRH FOLLOWED ENGINE SHUT DOWN. FOUND CB FOR LEFT ENGINE OIL PRESSURE TRANSMITTER TRIPPED. FOUND BLEED DUCT RUPTURED AT A PREVIOUS REPAIR. THE TRIANGULAR SHAPED HOLE APPROX 2" ALONG EACH SIDE ALLOWED 11TH STAGE AIR FOR THE TURBINE CASE COOLING SYSTEM TO BE DIRECTED ONTO WIRING BUNDLES. WIRES WERE DAMAGED INCLUDING THOSE FOR THE PERMANET MAGNET GENERATOR AND FOR THE IDG. WIRE P/NS DAMAGED: W5302-301B-18 W5302-301R-18 W5302-301Y-18 (TC# 20060526003) 2L72 4F4 FRTA1NM E23EA 20060613001952006061300195SO 2006 6 13 CA060526004 220060519G7414M3050 IMPULSE COUPLINGSLICK CESSNA206 U206B 2073322CE CONT O520 IO520D 17032SO MAGNETO BROKEN W D RETURN TO BLOCK RJ PARTIAL RPM/PWR LOSS WARNING INDICATION TXTAXI/GRND HDL 1 CA 2157 93120288 DURING FLT, PILOT NOTICED A VERY SLIGHT RPM DROP AND SLIGHT ROUGHNESS. UPON LANDING A GROUND RUN WAS PERFORMED AND WHEN THE IGNITION SWITCH WAS SELECTED TO RT MAG, ENGINE DIED OFF BEFORE SELECTING BACK TO LT OR BOTH. WHEN COWLS WERE REMOVED IT WAS EVIDENT THAT RT MAG HAD SEPARATED FROM ATTACH FLANGE AND WAS LAYING JUST FWD OF ITS ATTACHMENT POINT. UPON INSPECTION OF MAG IT APPEARS THAT IMPULSE COUPLING HAD FAILED INTERNALLY AND THROUGH ROTATION AND CENTRIFICAL FORCE HAD WORN AWAY THE CASING OF THE MAG TO THE POINT OF SEPARATION. MAG WAS REPLACED WITH A NEW UNIT, THE ACCY CASE GEARS WERE VISUALLY INSPECTED, AND THE OIL AND FILTER WERE CHANGED AT THAT TIME AND AGAIN 3 HOURS LATER. 1H71 3O3 O A4CE E5CE 20060628002202006062800220 2006 6 28 CA060526005 120060509G63206107435000060 FREEWHEEL UNIT SKRSKY M/R GEARBOX DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA 789 LT P/N 61074-35000-061 S/N C144-00286 RT P/N 61074-35000-060 S/N C144-00279 THESE UNITS WERE CHANGED UPON REQUEST OF THE CUSTOMER AFTER A SUSPECTED FREEWHEEL SLIP. SEE ATTACHED REPORT AND DIGITAL PICTURES FOR DETAILS. UNABLE TO ATTACH FILES, WILL E-MAIL THEM. THESE UNITS HAVE BEEN SENT TO WALDRON AND COMPANY FOR ANALYSIS. 20060614001262006061400126 2006 6 14 CA060529004 420060428G61228210263C FLANGE BAG JETSTMJETSTM3212 1500217EU GARRTTTPE331TPE33110UG 01514WP ROTOL R333 R333482F12 GL PROP GOVERNOR SPLIT W K NONE K FLUID LOSS ININSP/MAINT 1 CA FOUND OIL DRIPPING UNDER RIGHT ENGINE AFTER SHUT DOWN, ENGINE CLEANED AND CASE NEGATIVE PRESSURE CHECKED, FOUND SERVICEABLE. ENGINE GROUND RUN/MAX POWER CARRIED OUT. OIL FOUND TO BE LEAKING FROM THE PROP GOVERNOR. PROP GOVERNOR REPLACED WITH SERVICEABLE UNIT P/N 8210-263C, S/N 1812067. GROUND RUN CARRIED OUT SATISFACTORY. 2L72 4T4 TRTBA15CAA E4WE 6 CP61GL 20060614001992006061400199NE 2006 6 14 CA060529005 220060529G8550493476 O-RING DOUG DC6 DC6B 3021712WP PWA R2800 CB3 52026NE HAMSTD43E 43E60 NE NR 4 ENGINE DISPLACED W O OTHER K FLUID LOSS TXTAXI/GRND HDL 1 CA 1783 NR 4 ENGINE OUTBOARD UPPER OIL TRANSFER TUBE PLUG FOUND LOOSE AND THE O-RING WAS FOUND DISPLACED, CAUSING RAPID OIL DEPLETION COVERING THE COWLS WITH OIL. MAINTENANCE STAFF NOTED THIS DEFECT DURING GROUND OPERATION BETWEEN FLIGHTS. THE PLUG WAS REMOVED AND THE THREADS WERE CHECKED SERVICEABLE. THE O-RING WAS REPLACED. THE PLUG WAS INSTALLED AND TORQUED IAW MAINTENANCE MANUAL. THE ENGINE WAS GROUND RUN, PROP FEATHER OPERATIONAL CHECK COMPLETED. A LEAK CHECK WAS COMPLETED SERVICEABLE. A LEAK CHECK WAS ALSO COMPLETED UPON COMPLETION OF FLIGHT AND AIRCRAFT WAS SERVICEABLE. 2L74 4R4 R 6A4 E264 6 CP871 20060614002002006061400200NE 2006 6 14 CA060529006 220060529G8550493476 O-RING DOUG DC6 DC6B 3021712WP PWA R2800 CB3 52026NE HAMSTD43E 43E60 NE ENGINE DISPLACED W O OTHER K FLUID LOSS TXTAXI/GRND HDL 1 CA 1784 DURING GROUND OPERATION BETWEEN FLIGHTS, MAINTENANCE CREW DISCOVERED OIL ON THE COWL FLAPS. UPON INVESTIGATION IT WAS DISCOVERED THAT THE UPPER OUTBOARD OIL TRANSFER TUBE PLUG WAS LOOSE. THE O-RING HAD BECOME DISPLACED. THE PLUG WAS REMOVED AND THE THREADS WERE INSPECTED AND FOUND SERVICEABLE. THE O-RING WAS REPLACED. THE PLUG WAS RE-INSTALLED AND TORQUED IAW MM. THE ENGINE WAS GROUND RUN, A PROP FEATHER FUNCTION CHECK AND LEAK CHECK WERE ACCOMPLISHED. ENGINE WAS SERVICEABLE. THE AIRCRAFT COMPLETED A FLIGHT AND A LEAK CHECK WAS ACCOMPLISHED WITH NO SIGNS OF FURTHER LEAKAGE NOTED. 2L74 4R4 R 6A4 E264 6 CP871 20060614002022006061400202GL 2006 6 14 CA060529008 120060524G2820C2P1551A VENT DHAV DHC2 DHC2MKI 2801830GL PWA R985 R98539A 52008NE HARTZLHCB3R HCB3R304 GL FUEL SYSTEM WRONG PART W K NONE KB FLUID LOSS SMOKE/FUMES/ODORS/SPARKS ININSP/MAINT 1 CA 10645 THIS FRONT TANK FUEL VENT TUBE FOUND TO HAVE DISCONNECTED FROM THE RUBBER BLADDER. THE HOSE CLAMP WAS TIGHT BUT THE TUBE WAS ABLE TO WORK ITSELF FROM THE BLADDER CAUSING FUEL LEAKAGE AND GASES TO ESCAPE FROM THE BLADDER. IN INVESTIGATING THIS OCCURRENCE IT WAS NOTICED THAT THIS VENT LINE WHICH HAD A DEHAVILLAND P/N DID NOT HAVE A BULK ON THE END, EVEN THOUGH THE DEHAVILLAND DRAWING P/N C2P1551A CLEARLY SHOWS THIS BULBED END. THIS PART WAS REPLACED WITH A NEW DEHAVILLAND UNIT. 1H71 3R3 RRCA806 5E1 5 CP28EA 20060626000452006062600045CE 2006 6 26 CA060529009 120060518G2913HP3001 PUMP BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA HARTZLHCB3T HCB3TN3 GL HYDRAULIC SYS FAILED W O OTHER J WARNING INDICATION NRNOT REPORTED 1 CA (CAN) MAINTENANCE INSPECTED THE AIRCRAFT, FOUND MAIN 60A CB TRIPPED RESET CB AND SYSTEM APPEARED TO FUNCTION NORMAL FURTHER INVESTIGATION FOUND HYDRAULIC PUMP WOULD INTERMITTENTLY (ONLY OCCUR ON FIRST SYSTEM POWER UP) INTERNALLY BYPASS CAUSING LOW PRESSURE OUTPUT AND PUMP RUN-ON UNTIL CB WOULD TRIP INVESTIGATION OF THE SYSTEM FOUND WIRE (SPRING MATERIAL) IN FIRST CHECK VALVE OFF PUMP AND MAIN FILTER HYDRAULIC PUMP REPLACED, SYSTEM FLUSHED AND FUNCTION CHECKED. (TC NR 20060529009) 1L72 4T4 T A24CE E4EA 6 CP15EA 20060627002522006062700252CE 2006 6 27 CA060529010 120060521G3241991230512 SERVO CESSNA500 550 2076604CE PWA 530 PW530A NE BRAKE ANTI-SKID MALFUNCTIONED W O OTHER O OTHER LDLANDING 1 CA 4017 DURING LANDING, ANTI-SKID INOP ANNUNCIATOR ILLUMINATE THEN EXTINGUISH. ROLLOUT WAS UNEVENTFUL AND DUE LONG RUNWAY, NO BRAKE APPLICATION AT ALL BUT AT END OF RUNWAY RT TURN TO TAXIWAY, BRAKES WERE NON-RESPONSIVE BUT PEDALS WERE EXTREMELY HARD. MX FOUND PRESS STILL LOCKED IN SYS FROM A/S SERVO "UPSTREAM" SEVERAL HOURS POST INCIDENT. NO BRAKE PRESS AVAILABLE AT BRAKE UNITS. PWR BRAKE MOTOR NOT CYCLING AS USUAL DUE PRESS LOCK. EVEN WITH ANTI-SKID SWITCHED OFF, BRAKES WOULD NOT RETURN TO MANUAL, MASTER CYLINDER HYD BRAKE SYS AS PER SYS DESIGN. PRESS DID BLEED OFF HOURS LATER AND SYS RETURNED TO NORM OPS W/O EXT ACTIONS. UNKNOWN WHY TEMP ANTI-SKID LITE DURING LANDING WHICH SEEMS TO HAVE CAUSED ENTIRE BRAKE SYSTEM 1L72 4F4 F A22CE E00053EN 20060627002532006062700253EU 2006 6 27 CA060530001 120060527G63204638001001 TRANSMISSION BOLKMS105 BO105S 5626006EU ALLSN 250C 250C20B 03013GL MAIN ROTOR MAKING METAL W A UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 CA DURING CRUISE, MAIN ROTOR TRANSMISSION METAL PARTICLES LIGHT ILLUMINATE IN COCKPIT. LAND IMMEDIATELY IN SMALL CLEARING NEAR A ROAD. IT WAS A SECOND EVENT TO OCCUR WITHIN LAST 10 MINS, BUT FIRST TIME, WARNING LIGHT HAD EXTINGUISHED WHEN PILOT ACTIVATED PULSE CHIP DETECTOR SWITCH. FOUND A HAIR LIKE PIECE OF METAL, VERY SMALL. PROBABLY REMAINS OF A .003'' IN OF WIRE USE TO VERIFY OPERATION OF PULSE SYSTEM DURING PREVIOUS SCHEDULE INSPECTION. THE DETECTOR WAS CLEANED AND REINSTALLED, THE LIGHT REMAIN OFF. A 20 MINUTES GROUND RUN WAS CARRIED OUT. WARNING LIGHT REMAIN OFF. DETECTOR WAS REMOVED, INSPECTED (NO PARTICLE FOUND) AND REINSTALLED. A/C WAS THEN RETURNED TO SERVICE. 1G72 3U3 U H3EU E4CE 20060626000462006062600046SO 2006 6 26 CA060530003 120060520G2912MS2877816 O-RING PIPER PA31 PA31325 7103105SO LYC O540 TIO540F2BD 41532EA HARTZLHCE3Y HCE3YR2A GL HYDRAULIC FILTERFAILED W O OTHER K FLUID LOSS NRNOT REPORTED 1 CA (CAN) O-RING IN HYDRAULIC FILTER BOWL BLEW OUT SIDE BETWEEN THE BOWL SEATS. THERE ARE 2 DIFFERENT TYPES SIZES OF O-RING FOR THIS SET UP AS THERE ARE 2 SLIGHTLY DIFFERENT BOWL TYPES. THE O-RINGS ARE THE SAME COLOR AND VERY CLOSE IN SIZE MAKING IT REAL EASY TO PUT THE LARGER O-RING ON THE SMALLER BOWL. THE SMALLER O-RING WILL WORK ON THE LARGER BOWL BUT NOT VISE VERSA. ONCE INSTALLED IT IS IMPOSSIBLE TO TELL WHICH O-RING IS THERE. (TC NR 20060530003) 1L72 3O3 O A20SO E14EA 5 CP33EA 20060614002032006061400203CE 2006 6 14 CA060530004 120060512G7160055211313 AIR BOX CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA MCAULY1C160 1C160DTM GL ENGINE SEPARATED W A UNSCHED LANDING RE PARTIAL RPM/PWR LOSS VIBRATION/BUFFET DEDESCENT 1 CA STUDENT REMOVED CARB HEAT AFTER EXERCISE AND A/C RPM RESPONDED BY DROPPING, SO CARB HEAT WAS REAPPLIED. ENG CONTINUED TO GET ROUGHER AND POWER WAS ADDED. ENDED UP WITH FULL POWER/CARB HOT AND ENGINE RESPONSE WAS 1900 RPM/75 KTS DESCENDING. ANY CHANGE TO PUT CARB HEAT CAUSED RPM TO DROP SIGNIFICANTLY (BELOW 1500 RPM) LEFT AT POWER FULL/CARB HOT. ALL ENG INSTRUMENTS READING NORM. A/C WAS NOTICEABLY SHAKING DUE TO ROUGH ENG. ENG RESPONSE STAYED THIS WAY UNTIL ON FINAL, WHERE RESPONSE BECAME NORMAL AND LANDING UNEVENTFUL. UPON EXAM FOUND CARB AIR BOX HAD BEEN REPAIRED PREVIOUSLY, THE PATCH REPAIR RIVETS FAILED, CAUSING REPAIR PATCH TO FALL INSIDE AIR BOX AND PARTIALLY BLOCK CARBURETOR INTAKE. APPLICATION OF CAR1H71 3O3 ONT3A12 E274 5 NP910 20060614002042006061400204EA 2006 6 14 CA060530005 220060516G853072242 ROCKER COVER RKWELL700 700 7630520SW LYC O540 TIO540R2AD 41532EA HARTZLHCE3Y HCE3YR2A GL LT ENGINE SEPARATED W A UNSCHED LANDING YB ENGINE STOPPAGE SMOKE/FUMES/ODORS/SPARKS TOTAKEOFF 1 CA 314 DURING TAKEOFF, THE CREW NOTED THE LT ENGINE SURGING AND SMOKE FROM THE EXHAUST. THE AIRCRAFT COMPLETED THE TAKEOFF AND CAME BACK FOR LANDING WITHOUT ANY TROUBLE. CLOSER INVESTIGATION FOUND THE TAB THAT IS ATTACHED TO THE ROCKER COVER HAD COME OFF. THIS TAB HOLDS BOTH INTAKE AND EXHAUST ROCKER SHAFTS IN PLACE. THE EXHAUST ROCKER SHAFT WAS OUT OF PLACE AND THE INTAKE SHAFT HAD COME OUT AND BROKE THE BOSS OFF THE CYLINDER HEAD. THE ROCKER COVERS ARE MANUFACTURED BY MILLENIUM, THE ORIGINAL LYCOMING COVERS HAVE THE TAB BONDED ALONG THE ENTIRE MATING SURFACE. MILLENIUM COVERS HAVE ONLY TWO SMALL SPOT WELDS. ORDERED ALL NEW CYLINDER COVERS TO REPLACE THESE LIFTER COVERS. 1L72 3O3 O A12SW E14EA 5 CP33EA 20060626000472006062600047EA 2006 6 26 CA060530006 220060525G8500 ENGINE CESSNA172 172N 2072434CE LYC O320 O320H2AD 41508EA MCAULY1C160 1C160DTM GL FAILED W A UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CLCLIMB 1 CA RL114176T (CAN) ON TAKE-OFF THE AIRCRAFT WOULD NOT DEVELOP FULL POWER SO THE PILOT ABORTED THE TAKE-OFF. AIRCRAFT WAS BROUGHT INTO THE HANGER AND AME'S REMOVED COWLING AND REMOVED VALVE COVERS. IT WAS NOTED THAT ALL THE CLEARANCES ON THE VALVES WERE TOO LOOSE. AIRCRAFT HAD A NEW ROLLER LIFTERS AND CAM INSTALLED IAW STC SE 03-3 ONLY 24.0 HRS BEFORE BY AN APPROVED ENGINE SHOP. ENGINE SHOP WAS CONTACTED AND THEY CONTACTED OWNER OF STC. OWNER OF THE STC WAS CONTACTED AND THEY REQUESTED THAT THE ENGINE BE SHIPPED TO THEM FOR REPAIR. (TC NR 20060530006) 1H71 3O3 ONT3A12 E274 5 NP910 20060627000872006062700087WP 2006 6 27 CA060530007 220060515G72003582681 CARRIER ASSY SWRNGNSA226 SA226TC 8780404SW GARRTTTPE331TPE33110UA 01514WP HARTZLHCE4N HCE4N3 NE ENGINE MAKING METAL W K NONE O OTHER ININSP/MAINT 1 CA 328141894 P54019 (CAN) OIL SAMPLE RECEIVED FROM WEAR CHECK INDICATING HIGH OIL FILTER WEIGHT W/MAJOR ALUMINUM, MINOR CARBON STEEL IN SAMPLE. ENG REMOVED FOR INSP. DURING TEARDOWN: PLANETARY CARRIER SPLINE LOCKS STRIPPED/DESTROYED. CARRIER WORN DUE TO EXCESS PIN LOADING. ALL CARRIER GEARS EXCESS GEAR WEAR. INSP REVEALED THAT BOLT NR180 IN REDUCTION GEARBOX LOOSENED, CAME IN CONTACT W/ACCESSORY SPUR GEAR CAUSING SPUR GEAR DAMAGE, OIL DETECTOR DAMAGE. MOST COMPONENTS IN REDUCTION GEAR BOX EXIBITED SIGNS OF EXCESS VIBRATION, BOLTS WHICH WERE UNDER TORQUE AS INDICATED BY WEAR PATTERNS ON WASHERS HAD LOOSENED. PROP INSTALLED ON THIS ENG WAS INSPECTED AND FOUND SERVICEABLE. REASON FOR VIBRATION NOT DETERMINED. (TC NR 20060530007)2L72 4T4 TRTA8SW E4WE 5 CP10NE 20060626000482006062600048EA 2006 6 26 CA060530008 220060530G73103027039 LINE BEECH 90 C90A 1152911CE PWA PT6 PT6A21 52043EA HARTZLHCB3T HCB3TN3 GL FUEL CONTROL CRACKED W ED ENGINE SHUTDOWN RETURN TO BLOCK KRJFLUID LOSS PARTIAL RPM/PWR LOSS WARNING INDICATION TXTAXI/GRND HDL 1 CA (CAN) AIRCRAFT HAD TAXIED TO RUN-UP AREA PRIOR TO TAKEOFF. WHILE COMMENCING ENGINE RUN-UP NOTICED THAT THERE WAS NO THROTTLE RESPONSE ON THE RT ENGINE. CREW CONTACTED MAINTENANCE AND REQUESTED A TOW BACK TO THE HANGER. MAINTENANCE FOUND THAT THE FUEL FEED LINE FROM THE FCU TO THE FUEL FLOW DIVIDER WAS CRACKED AND SPRAYING FUEL INSIDE THE ENGINE NACELLE. CRACK WAS AT THE FCU END OF THE FUEL LINE, CRACK RAN PARALLEL WITH THE SWAGGED FERRULE. FUEL LINE REPLACED AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20060530008) 1L72 3T4 TRT3A20 E4EA 6 CP15EA 20060627000882006062700088NM 2006 6 27 CA060530009 120060525G6123JV5 ACTUATOR BOMBDRDHC8 DHC8402 1390042NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE AUTOFEATHER SYS INOPERATIVE W D RETURN TO BLOCK O OTHER TXTAXI/GRND HDL 1 CA (CAN) DURING PRE-FLIGHT CHECKS WHEN PROP AUTOFEATHER, ON EITHER ENG, WAS SET TO TEST AND PWR LEVER ADVANCED, PROP WOULD GO INTO TEST (FEATHER) AND STAY THERE, RELEASING TEST SWITCH, SETTING PWR LEVERS TO IDLE DID NOT UN-FEATHER PROP. AUTOFEATHER SELECT SWITCH HAD TO BE SET TO (OFF) FOR SYS TO RETURN TO NORMAL. AUTOFEATHER WOULD ARM NORMALLY WHEN PWR LEVERS WERE ADVANCED TO TAKEOFF PWR, PROBLEM ONLY OCCURRED WHEN SYS WAS SET TO TEST. SYS WAS DE-ACTIVATED, AC WAS OPERATED UNDER MEL. MAINT FOUND PIECE OF ACTUATOR (JV5) FOR NR 1 PWR CNTRL MICROSWITCH (S13) HAD BROKEN OFF, WAS KEEPING MICOSWITCH (S13) CLOSED ALL THE TIME. MICROSWITCH AND ACTUATOR WERE REPLACED, AUTOFEATHER SYS TESTED NORMAL. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20060614002052006061400205NM 2006 6 14 CA060531001 120060530G561058935734 WINDOW BOEING737 737522 138449FNM CFMINTCFM56 CFM563C1 13802EU COCKPIT FAILED W O OTHER O OTHER APAPPROACH 1 CA ON APPROACH, THE F/O'S NR 4 EYEBROW WINDOW SHATTERED. APPROACH CONTINUED AND AN UNEVENTFUL LANDING FOLLOWED. WINDOW REPLACED. 2L72 4F4 FRTA16WE E21EU 20060614002062006061400206NE 2006 6 14 CA060531003 220060525G8530899353 CYLINDER HEAD DHAV DHC2 DHC2MKI 2801830GL PWA R985 R985AN14B 52008NE NR 2 CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 1345 CYLINDER ASSEMBLY NR 2 HEAD FOUND CRACKED BETWEEN SPARK PLUG HOLES. OH ASSEMBLY INSTALLED. 1H71 3R3 RRCA806 5E1 20060626000492006062600049EA 2006 6 26 CA060531004 220060426G7250 SCOOP BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA NR 5 BEARING DETERIORATED W C ABORTED TAKEOFF XJ ENGINE FLAMEOUT WARNING INDICATION TOTAKEOFF 1 CA (CAN) THE ENGINE FLAMED OUT ON ROTATION RESULTING IN AN ABORTED TAKE-OFF. SUBSEQUENT INVESTIGATION REVEALED DAMAGE TO THE HPT STUB SHAFT AS A RESULT OF NR 5 BEARING OIL SCOOP DETERIORATION. (TC NR 20060531004) 2H72 4T4 TRTA13NM E00062EN 20060626000502006062600050EA 2006 6 26 CA060531005 220060407G7321324475520 FUEL CONTROL BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA ENGINE INOPERATIVE W EA ENGINE SHUTDOWN UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 1 CA (CAN) DURING CRUISE THE ENGINE EXPERIENCED AN UNCOMMANDED POWER REDUCTION. THE ENGINE WAS SHUT DOWN IN FLIGHT AND THE AIRCRAFT DIVERTED. THE FUEL CONTROL WAS SUBSEQUENTLY REPLACED. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC NR 20060531005) 1L72 4T4 T A24CE E4EA 20060627000902006062700090NE 2006 6 27 CA060531007 220060427G7321 SPLINE DHAV DHC8 DHC8202 2809007NM PWA 120 PW123D 52152NE FUEL CONTROL WORN W E ENGINE SHUTDOWN R PARTIAL RPM/PWR LOSS CRCRUISE 1 CA 1828 C3106 (CAN) ENGINE TORQUE WAS REPORTED TO FLUCTUATE IN CRUISE BY AS MUCH AS 50 PERCENT AND THE ENGINE WAS SHUTDOWN IN FLIGHT. SUSEQUENT INVESTIGATION REVEALED WORN MECHANICAL FUEL CONTROL DRIVE SPLINES. (TC NR 20060531007) 2H72 4T4 TRTA13NM E20NE 20060627000912006062700091NE 2006 6 27 CA060531008 220060428G7200 ENGINE AIRTRCAT500 AT502 0390303SW PWA PT6 PT6A15AG 52043NE FAILED W A UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION NRNOT REPORTED 1 CA (CAN) THE ENGINE WAS REPORTED TO HAVE LOST POWER IN FLIGHT LEADING TO A FORCED LANDING AND RESULTANT AIRFRAME DAMAGE. MFG WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060531008) 1L71 3T4 TNCA9SW E4EA 20060626000512006062600051NE 2006 6 26 CA060531009 220060508G7200 ENGINE BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE MALFUNCTIONED W C ABORTED TAKEOFF YJ ENGINE STOPPAGE WARNING INDICATION TOTAKEOFF 1 CA PS0125 (CAN) DURING TAKE-OFF ROLL THE ENGINE WAS REPORTED TO EMIT A LOUD NOISE ACCOMPANIED BY SEIZURE OF THE POWER SECTION. SUBSEQUENT INSPECTION REVEALED DAMAGED POWER TURBINE BLADES. MFG WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060531009) 2L72 4T4 TRTA24CE E26NE 20060626000522006062600052SW 2006 6 26 CA060531010 120060404G6200 ROTOR BELL 212 212 1181420SW PWA PT6T PT6T3B 52045NE MAIN ROTOR MALFUNCTIONED W A UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CLCLIMB 1 CA (CAN) FOLOWING CLIMB THE MAIN ROTOR SPEED DECREASED UNCOMMANDED AND THE LOW ROTOR RPM WARNING ACTIVATED. AN EMERGENCY LANDING WAS CARRIED OUT RESULTING IN AIRFRAME DAMAGE. NR WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR20060531010) 1G71 4U4 U H4SW E22EA 20060626000532006062600053NE 2006 6 26 CA060531011 220060511G7200 ENGINE PILATSPC7 PC7 7090401EU PWA PT6 PT6A25 52043NE POWER LOSS W A UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CLCLIMB 1 CA PF0037 (CAN) THE ENGINE WAS REPORTED TO HAVE LOST POWER FOLLOWING TAKE-OFF, RESULTING IN A FORCED LANDING. 1L71 3T3 TRTA50EU E4EA 20060627000922006062700092EA 2006 6 27 CA060531012 220060527G7200 ENGINE BEECH 99 99 1154002CE PWA PT6 PT6A28 EA HARTZLHCB3T HCB3TN3 GL POWER SECTION MAKING METAL W EA ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 CA 320 PCE40252 (CAN) IN CRUISE, THE CHIP LIGHT ACTIVATED ON THE LT ENGINE. THE ENGINE WAS SHUTDOWN AS A PRECAUTION AND THE AIRCRAFT DIVERTED TO NEAREST FIELD FOR NORMAL LANDING. CFR WAS REQUESTED TO BE ON STANBY. THERE WAS NO OTHER INDICATIONS OF ENGINE PROBLEMS. THE CHIP PLUG WAS REMOVED AND CLEANED. THE OIL SYSTEM WAS FLUSHED AND CHECKED AGAIN FOR CONTAMINATION. AS A PRECAUTION THE AIRCRAFT WAS FLOWN TO AN ENGINE OVERHAUL FACILITY WHERE THE ENGINE WAS REMOVED. DETAILS OF THE OVERHAUL FINDINGS WILL BE FORWARDED WHEN AVAILABLE. (TC NR 20060531012) 1L72 3T4 T A14CE E4EA 6 CP15EA 20060626000542006062600054NE 2006 6 26 CA060531013 220060427G7200 ENGINE BEECH 200 B200 1152922CE PWA PT6 PT642A NE SURGES W A UNSCHED LANDING XJ ENGINE FLAMEOUT WARNING INDICATION CRCRUISE 1 CA 94609 (CAN) DURING CRUISE THE ENGINE WAS REPORTED TO SURGE AND SUBSEQUENTLY FLAME OUT. MFG WILL INVESTIGATE THE EVENT AND WILL ADVISEOF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060531013) 1L72 4T4 T A24CE E4EA 20060627000932006062700093NE 2006 6 27 CA060531014 220060517G7270 PANEL LEAR 60 60LEAR 5170707CE PWA 305 PW305A 52128NE BYPASS DUCT FRACTURED W K NONE O OTHER ININSP/MAINT 1 CA CA0339 (CAN) DURING GROUND INSPECTION METAL DEBRIS WAS FOUND LODGED IN THE ENGINE BYPASS DUCTING. THE ENGINE'S INNER BYPASS DUCT PANELS WERE FOUND FRACTURED. MFG WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060531014) 2L72 4F4 FRTA10CE E35NE 20060627000952006062700095NE 2006 6 27 CA060531015 220060521G7200 ENGINE BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE MAKING METAL W EF ENGINE SHUTDOWN ACTIVATE FIRE EXT. RA PARTIAL RPM/PWR LOSS FLAME/FIRE DEDESCENT 1 CA 114336 (CAN) DURING DESCENT THE ENGINE WAS REPORTED TO LOSE POWER ACCOMPANIED BY A FIRE. THE CREW DEPLOYED FIRE EXTINGUISHERS AND SHUT THE ENGINE DOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED METAL IN THE ENGINE EXHAUST. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2L72 4T4 TRTA24CE E26NE 20060627001492006062700149NE 2006 6 27 CA060531016 220060530G7250 BLADE BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE HARTZLHCE4A HCE4A3I NE ENGINE FAILED W C ABORTED TAKEOFF J WARNING INDICATION TOTAKEOFF 1 CA 5771 (CAN) UPON APPLYING TAKEOFF POWER FOR DEPARTURE, THE PILOT HEARD A LOUD BANG. HE THEN INITIATED A SUCCESSFULL REJECTED TAKEOFF. UPON STOPPING, A PASSENGER CAME FORWARD AND STATED THAT HE THOUGHT SOMETHING FELL OFF THE RT WING. THE RT ENGINE WAS SECURED. THE AIRCRAFT TAXIED BACK TO THE GATE AND PASSENGERS DISEMBARKED. UPON INVESTIGATION BY MAINTENANCE THE RT ENGINE SEEMS TO HAVE SUFFERED A POWER TURBINE BLADE FAILURE. THE DEBRIS FROM THE BLADES IS WHAT THE PASSENGERS WOULD HAVE SEEN. ENGINE WILL BE FORWARDED TO THE MFG FOR INVESTIGATION. SDR WILL BE LEFT OPEN AND UPDATED WITH INVESTIGATION FINDINGS. (TC NR20060531016) 2L72 4T4 TRTA24CE E26NE 5 CP10NE 20060627001502006062700150NE 2006 6 27 CA060531017 220060521G7200 ENGINE AEROSPATR42 ATR42* 8680900EU PWA 120 PW120 NE MALFUNCTIONED W E ENGINE SHUTDOWN RJ PARTIAL RPM/PWR LOSS WARNING INDICATION APAPPROACH 1 CA 120632 (CAN) ON APPROACH, ENGINE TORQUE WAS REPORTED TO FLUCTUATE AND THE ENGINE WAS SUBSEQUENTLY SHUTDOWN IN FLIGHT. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2H72 4T4 TRTA53EU E20NE 20060627001532006062700153NE 2006 6 27 CA060531018 220060522G7532 BLEED VALVE LEAR 60 60LEAR 5170707CE PWA 305 PW305A 52128NE ENGINE FAILED W E ENGINE SHUTDOWN RJ PARTIAL RPM/PWR LOSS WARNING INDICATION APAPPROACH 1 CA (CAN) ON APPROACH, THE ENGINE EXPERIENCED COMPRESSOR STALLS ACCOMPANIED BY A RISE IN INTER-TURBINE TEMPERATURE AND ODORS IN THE CABIN. THE ENGINE WAS SHUTDOWN IN FLIGHT. THE ENGINE BLEED VALVES AND BLEED VALVE SOLENOID WERE SUBSEQUENTLY REPLACED. (TC NR 20060531018) 2L72 4F4 FRTA10CE E35NE 20060627001612006062700161NE 2006 6 27 CA060531019 220060522G7320 EEC LEAR 60 60LEAR 5170707CE PWA 305 PW305A 52128NE ENGINE MALFUNCTIONED W EA ENGINE SHUTDOWN UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CLCLIMB 1 CA (CAN) DURING CLIMB THE ENGINE EEC FAULT LIGHT ACTIVATED FOLLOWED BY A LOUD NOISE AND A LOSS OF POWER. THE ENGINE WAS SHUTDOWN IN FLIGHT AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE. THE EEC WAS SUBSEQUENTLY REPLACED. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060531019) 2L72 4F4 FRTA10CE E35NE 20060627001682006062700168EA 2006 6 27 CA060531020 220060515G7200 ENGINE BEECH 200 200BEECH 1152920CE PWA PT6 PT6A21 52043EA MALFUNCTIONED W EA ENGINE SHUTDOWN UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CLCLIMB 1 CA 24774 (CAN) DURING CLIMB THE ENGINE WAS REPORTED TO EMIT A NOISE AND WAS SHUT DOWN IN FLIGHT. AN EMERGENCY WAS DECLARED AND THE AIRCRAFT DIVERTED. THE AIRFRAME WAS DAMAGED IN THE SUBSEQUENT LANDING (OVERSHOOT). MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060531020) 1L72 4T4 T A24CE E4EA 20060627001702006062700170NE 2006 6 27 CA060531021 220060523G7250 TURBINE BLADES AEROSPATR72 ATR72212 8680945EU PWA PW120 PW127 NE TURBINE SECTION FAILED W EA ENGINE SHUTDOWN UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CLCLIMB 1 CA (CAN) DURING TAKEOFF CLIMB, THE ENGINE EMITTED A LOUD NOISE ACCOMPANIED BY AN UNCOMMANDED POWER REDUCTION AND A FIRE WARNING. THE ENGINE WAS SHUTDOWN IN FLIGHT, AT WHICH POINT THE FIRE WARNING DEACTIVATED. THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE. SUBSEQUENT INSPECTION REVEALED FRACTURED POWER TURBINE BLADES. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060531021) 2H72 4T4 TRTA53EU E20NE 20060627001752006062700175NM 2006 6 27 CA060531022 120060524G793130B296301 SEAL PROPJT200 200A 0140304NM PWA 306 PW306B NE ACCESSORY GBOX DAMAGED W EA ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 CA (CAN) DURING CRUISE, THE ENGINE LOW OIL PRESSSURE WARNING ACTIVATED. THE ENGINE WAS SHUTDOWN IN FLIGHT AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE. SUBSEQUENT INVESTIGATION REVEALED A DAMAGED AND LEAKING ACCESSORY GEARBOX LIP SEAL. (TC NR 20060531022) 1L71 3O4 F 3A18 E35NE 20060627002542006062700254EA 2006 6 27 CA060531023 220060524G7200 ENGINE PWA PT6 PT6A27 52043EA MAKING METAL W EA ENGINE SHUTDOWN UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 1 CA PG0018 DURING CRUISE, ENGINE OIL PRESSURE WAS REPORTED TO DECREASE ACCOMPANIED BY AN UNCOMMANDED REDUCTION IN POWER. THE ENGINE WAS SHUT DOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED METALLIC DEBRIS ON THE ENGINE CHIP DETECTOR AND AN INABILITY TO ROTATE. P&WC WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 4 T E4EA 20060627001842006062700184NE 2006 6 27 CA060531024 220060429G7250 TURBINE BLADES BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE ENGINE DAMAGED W C ABORTED TAKEOFF ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS TOTAKEOFF 1 CA PS0139 (CAN) DURING TAKEOFF ROLL, THE ENGINE WAS REPORTED TO VIBRATE ACCOMPANIED BY AN UNCOMMANDED REDUCTION IN POWER. TAKEOFF WAS ABORTED. SUBSEQUENT INSPECTION REVEALED DAMAGED POWER TURBINE BLADES. MFG WILL MONITOR INVESTIGATION OF THE EVENT AND REPORT ON ROOT CAUSE ONCE DETERMINED. (TC NR 20060531024) 2L72 4T4 TRTA24CE E26NE 20060627001852006062700185SO 2006 6 27 CA060531025 120060531G32214033600 LINK ASSY PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA HARTZLHCE3Y HCE3YR2A GL NLG CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 16119 (CAN) FOUND PART CRACKED ON 1 LUG EXACTLY WHERE NOTED IN PIPER SERVICE LETTER 1088. THIS CRACK WAS VISIBLE WITH THE NAKED EYE, BUT ONLY AFTER THE PAINT WAS REMOVED. (TC NR 20060531025) 1L72 3O3 O A20SO E14EA 5 CP33EA 20060627001862006062700186GL 2006 6 27 CA060601001 220060531G7510 GASKET LKHEED382 382G 526414USO ALLSN 501D 501D22A 03006GL HAMSTD54H 54H60117 NE ENGINE FAILED W EA ENGINE SHUTDOWN UNSCHED LANDING JJ WARNING INDICATION WARNING INDICATION CLCLIMB 1 CA 500934 (CAN) DEPARTING, CREW OBSERVED A NACELLE OVER HEAT INDICATION ON NR 2 ENGINE. THE ENGINE WAS SHUTDOWN AND THE AIRCRAFT RETURNED TO POINT OF DEPARTURE. ON APPROACH THE LT MAIN GEAR FAILED TO INDICATE DOWN AND LOCKED, AFTER VISUAL CONFIRMATION THE AIRCRAFT LANDED WITHOUT FURTHER INCIDENT. MAINTENANCE REPLACED THE GASKET AT THE UPPER MANIFOLD 14TH STAGE BLEED AND THE LT MAIN GEAR DOWNLOCK SWITCH. THE AFFECTED SYSTEMS WERE FUNCTION CHECKED AND THE THE AIRCRAFT RETURNED TO SERVICE. (TC NR 20060601001) 2H74 4T4 T A1SO E282 6 CP906 20060627001872006062700187EA 2006 6 27 CA060601002 220060531G7220 DUCT BEECH 100 A100 1152915CE PWA PT6 PT6A28 EA HARTZLHCD4N3HCD4N3A GL ENGINE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) CRACK DEVELOPED IN THE DOMED PORTION OF THE SMALL EXIT DUCT BESIDE THE WELD. FOUND DURING THE BOROSCOPE INSPECTION. (TC NR 20060601002) 1L72 3T4 T A14CE E4EA 5 CSTC 20060627001882006062700188NE 2006 6 27 CA060601003 220060527G7261 PACKING PROPJT200 200A 0140304NM PWA 306 PW306B NE OIL CAP MISINSTALLED W EA ENGINE SHUTDOWN UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CLCLIMB 1 CA (CAN) THE ENGINE LOW OIL PRESSURE WARNING ACTIVATED IN CRUISE AND THE ENGINE WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED OIL LOSS ASSOCIATED WITH A MISINSTALLED OIL CAP O-RING PACKING. (TC NR 20060601003) 1L71 3O4 F 3A18 E35NE 20060627001892006062700189EU 2006 6 27 CA060601004 120060530G7931 PRESSURE VALVE AEROSPATR72 ATR72212A 8680902EU PWA PW120 PW127 NE OIL SYSTEM INOPERATIVE W EA ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA (CAN) IN TAKE-OFF CLIMB, THE ENGINE LOW OIL PRESSURE WARNING ACTIVATED AND THE ENGINE WAS SHUTDOWN IN FLIGHT. THE AIRCRAFT RETURNED TO POINT OF DEPARTURE. THE ENGINE OIL PRESSURE REGULATING VALVE WAS REPLACED. (TC NR 20060601004) 2H72 4T4 TRTA53EU E20NE 20060627001902006062700190NE 2006 6 27 CA060601005 220060531G7250 TURBINE BLADES BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE HARTZLHCE4A HCE4A3I NE ENGINE FRACTURED W C ABORTED TAKEOFF RJ PARTIAL RPM/PWR LOSS WARNING INDICATION TOTAKEOFF 1 CA PS0117 (CAN) DURING TAKE-OFF ROLL THE ENGINE EMITTED A LOUD NOISE AND TAKE-OFF WAS ABORTED. SUBSEQUENT INSPECTION REVEALED FRACTURED POWER TURBINE BLADES AND RESULTS, EXHAUST STUB DAMAGE. MFG WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060601005) 2L72 4T4 TRTA24CE E26NE 5 CP10NE 20060627001912006062700191SW 2006 6 27 CA060601006 120060327G77142090753261 DETECTOR BELL 212 212 1181420SW PWA PT6T PT6T3 52045EA RPM LIMIT FAILED W K NONE N FALSE WARNING ININSP/MAINT 1 CA 83 (CAN) ENGINE OUT LIGHT STAYS ON AFTER ENGINES STARTED. RPM LIGHT INTERMITTENT WITH RPM IN NORMAL OPERATING RANGE.THE RELIABILITY OF THESE UNITS ARE NOT GOOD.IN OUR FLEET OF 4 BELL 212'S WE GO THROUGH 6 RPM BOXES IN 1 SUMMER (TC NR 20060601006) 1G71 4U4 U H4SW E22EA 20060627001982006062700198SO 2006 6 27 CA060602002 120060526G214030670000 TUBE PIPER PA23 PA23250 7102308SO LYC O540 IO540C4B5 41532EA HARTZLHCE2Y HCE2YK2 GL HEATER EXHAUST SEPARATED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING REMOVAL OF A BIRDS NEST IN THE FRESH AIR INTAKE LOCATED IN THE NOSE OF THE AIRCRAFT THE HEATER EXHAUST TUBE WAS FOUND TO BE UNSERVICEABLE. THE TUBE ITSELF IS A (WOUND) TUBE AND THE WINDINGS NEAR THE ATTACH POINT HAD SEPARATED THAT WOULD ALLOW HOT EXHAUST TO CONTACT THE TUBE SHROUD. (TC NR 20060602002) 1L72 3O3 O 1A10 1E4 5 CP9EA 20060627001992006062700199SO 2006 6 27 CA060602003 220060602G7322991026720 THROTTLE CABLE CESSNA310 310Q 2074242CE CONT O470 IO470VO 17026SO MCAULY3AF32C3AF32C87 GL ENGINE BROKEN W O OTHER O OTHER CRCRUISE 1 CA (CAN) DOING UPPER AIR WORK, IT WAS NOTICED THEIR WAS NO THROTTLE RESPONSE FROM RT ENGINE. THE ENGINE WAS RUNING NORMAL SO THE CREW RETURNED TO AIRPORT AND DID A NORMAL LANDING AND SHUTDOWN OF ENGINE ON TOUCHDOWN. MAINTENANCE FOUND THE THROTTLE CABLE BROKEN AT THE FUEL CONTROL UNIT WHERE THE FLEX CABLE IS CRIMPED INTO THE SOLID ROD. PARTS ON ORDER. (TC NR 20060602003) 1L72 3O3 O 3A10 3E1 5 CP22EA 20060627002192006062700219SW 2006 6 27 CA060602004 120060529G6220204011179003 DRAG BRACE BELL 205 205A1 1181414SW LYC T53 T5317A 41549NE MAIN ROTOR CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 7778 704 (CAN) THE DRAG BRACE WAS IN THE COMPONENT SHOP GETTING ITS 1200 HR INSPECTION/24 MONTH INSPECTION. THE DRAG BRACE ASSEMBLY WAS PREPARED FOR NDT MAGNETIC PARTICLE INSPECTION. THE NDT SHOP FOUND THIS FITTING WAS CRACKED ON THE IB CURVE. (TC NR 20060602004) 1G71 4U4 U H1SW E17EA 20060627002202006062700220EA 2006 6 27 CA060604001 120060522G2460S69381 BUSS BAR CNDAIRCL600 CL6002C10 1390015EA GE CF34 CF348C1 NE DAMAGED W L ABORTED APPROACH J WARNING INDICATION APAPPROACH 1 CA (CAN) C/B 1D6 (DC 1 FEED) POPPED ON SHORT FINAL CAUSING VARIOUS SYSTEMS TO GO INOP. THEY DID A GO AROUND RESETTING THE C/B, IT POPPED AGAIN ON SHORT FINAL. MAINT FOUND THE BUS BAR BETWEEN CBP-D1 AND CBP-1-D7 (IPC 24-08-01, ITEM 275)WAS NOT SECURED DAMAGING THE CIRCUIT BREAKER. MAINT REPLACED THE DAMAGED CIRCUIT BREAKER AND TIGHTENED THE BUS BAR. OPS GOOD. (TC NR 20060604001) 2L72 4F4 FRTA21EA EOOO63EN 20060627002212006062700221EA 2006 6 27 CA060604002 120060525G492038004883 APU CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE INOPERATIVE W F ACTIVATE FIRE EXT. AB FLAME/FIRE SMOKE/FUMES/ODORS/SPARKS TXTAXI/GRND HDL 1 CA (CAN) WHILE TAXING IN PREPARATION FOR TAKEOFF, CREW NOTED SMOKE AROUND AC, TOWER REPORTED SMOKE, FLAMES COMING FROM AFT AREA OF AC UNDER NR 2 ENG. APU WAS SHUTDOWN, CREW THEN ELECTED TO TAXI OFF ACTIVE TAXIWAY TO A NON ACTIVE TAXIWAY. SHORTLY AFTER STOPPING AC, AN APU FIRE MESSAGE WAS POSTED ON EICAS. CREW COMPLETED QRH PROCEDURE FOR APU FIRE. CREW DISCHARGED AT LEAST ONE FIRE BOTTLE, AND FIRE INDICATIONS EXTINGUISHED. CFR RESPONDED AND DISCHARGED HALON INTO APU ENCLOSURE. CREW THEN EVACUATED PASSENGERS THROUGH MAIN CABIN DOOR EXIT USING QRH PROCEDURE. ONE PASSENGER SUSTAINED A CUT FINGER. NO OTHER INJURIES REPORTED. THE APU WAS REPLACED, AC RETURNED TO SERVICE. 2L72 4F4 FRTA21EA E15NE 20060627002222006062700222EA 2006 6 27 CA060605001 120060530G3510S694603 LINE CNDAIRCL600 CL6002C10 1390015EA GE CF34 CF348C1 NE OXYGEN SYS RUPTURED W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA (CAN) PASSING ABOUT 17000 FT ON CLIMBOUT FROM DFW AN QXYGEN LEAK OCURRED FROM OBSERVERS MASK COMPARTMENT AND DEPLETED ALL THE QXYGEN. FOLLOWED OXY LO PRESS PROCEDURE, DECLARED EMERGENCY, DESCENDED AND RETURNED TO DFW. TROUBLESHOT A/C AND FOUND O2 LINE BEHIND OBSERVERS O2 MASK RUPTURED. REPLACED LINE IAW CRJ MM 35-11-03. INSTALLED SERVICEABLE CREW O2 BOTTLE IAW CRJ MM 35-11-03. NO LEAKS NOTED. LINE REF TO AIPC 35-13-01 FIG 01-A01 PAGE 2 ITEM 70. (TC NR 20060605001) 2L72 4F4 FRTA21EA EOOO63EN 20060627002232006062700223EU 2006 6 27 CA060605002 120060523G6300350A35105901 DISK SNIAS 350 AS350BA 8680817EU TMECA ARRIELARRIEL1B 6OO30NE ROTOR FAILED W K NONE O OTHER ININSP/MAINT 1 CA 4734 (CAN) DURING A 500 HOUR INSPECTION, WHILE INSPECTING THE ENGINE TO MGB ASSY IAW MM, WC 63-00-00-601, AME NOTICED BLACK MARKS AROUND 3 OUT OF 6 BOLTS LINKING DISK ASSY TO POWER SHAFT (MARKS LIKE (SMOKING RIVETS). USING A 13MM WRENCH, COULD EASILY ROTATE THOSE 3 BOLTS BY THE HEAD. THE COTTER PINS WERE NORMALLY INSTALLED BUT THE BOLTS HAD LOST THEIR TORQUE. AFTER REMOVAL, BUSINGS OF THE DISK ASSY SHOWED FRETTING MARKS, AND WERE PARTIALLY UNCRIMPED. REPLACED DISK ASSY AND ASSOCIATED HARDWARE PLUS INSPECTIONS ASKED FOR BY WC 63-00-00-601 C/O. (TC NR 20060605002) 1G71 3U3 UNCH9EU E19EU 20060627002552006062700255SO 2006 6 27 CA060605003 220060601G8530SA52000A1 CYLINDER HEAD CESSNA206 U206F 2073333CE CONT O520 IO520F 17032SO ENGINE CRACKED W D RETURN TO BLOCK O OTHER TOTAKEOFF 1 CA 382 AIRCRAFT HAD JUST TAKEN OFF WHEN THE PILOT HEARD A LOUD BANG, HE TURNED AROUND AND LANDED AGAIN. UPON INSPECTION OF THE ENGINE, FOUND THE NR 4 CYLINDER WAS CRACKED AT THE HEAD JUST ABOVE THE THREADS WHERE THE HEAD AND CYLINDER ARE JOINED. CYLINDER WAS REMOVED AND REPLACED. HAD ENCOUNTERED THE SAME PROBLEM WITH NR 6 AND NR 2 ABOUT 160 HOURS EARLIER HAD TROUBLE WITH NEW PILOTS AND THOUGHT THIS WAS CAUSING PROBLEM. OVERHAUL WAS CARRIED OUT AT AERO RECIP, THEY WERE CONTACTED AND WILL BE INSTALLING 6 NEW CYLINDERS. 1H71 3O3 O A4CE E5CE 20060627002242006062700224EA 2006 6 27 CA060605004 120060603G783022850809801 THRUST REVERSER CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE LEFT FAILED W D RETURN TO BLOCK J WARNING INDICATION TXTAXI/GRND HDL 1 CA (CAN) FLIGHT CREW REPORTED THAT THEY RECEIVED A (L REV UNLOCKED) CAUTION MESSAGE ON RUNWAY AND LINED UP FOR TAKEOFF WITH NO REPORTED CHANGE TO THE N1 OR N2 INDICATIONS. MESSAGE THEN FLICKERED ON AND OFF. WHILE TAXIING BACK TO THE GATE THE MESSAGE WENT OUT. AFTER AC SHUTDOWN MESSAGE REAPPEARED. REV LOCKED OUT IAW MEL 78-30-02 AND TASK 78-30-00-040-802. TRACK ASSY NOTED TO BE CRACKED IAW REO 601R-78-30-3253. AC FERRIED, TRACK ASSY REPLACED. AC RELEASED INTO SERVICE. (TC NR 20060605004) 2L72 4F4 FRTA21EA E15NE 20060627002252006062700225SW 2006 6 27 CA060605005 120060601G3246206020110005 SKID BELL 206 206B 1181511SW ALLSN 250C 250C20B 03013GL MLG CORRODED W K NONE O OTHER ININSP/MAINT 1 CA 12163 (CAN) DURING A ROUTINE 300 HR INSP OF THE AC, IT WAS NOTED THAT A SMALL PIECE OF PAINT HAD FALLEN OFF OF THE LOWER AFT END OF THE TAIL SKID ASSY, AT THE LOWER WELD BEAD JOINT. UPON FURTHER INVESTIGATION, IT WAS NOTED THAT A SMALL HOLE (APPROX .1875) WAS PRESENT. WHEN THE WELD AREA WAS INSPECTED ON THE OPPOSITE SIDE, A SMALL AREA OF CORROSION WAS ALSO NOTED, BUBBLING UNDER THE PAINT. THE CORROSION WAS REMOVED WHICH REVEALED ANOTHER SMALL HOLE (APPROX .1875). THIS AREA OF THE TAIL SKID ASSY IS ALSO THE LOWEST POINT, WHERE WATER AND CONDENSATION CAN BE TRAPPED. A NEW TAIL SKID ASSY WAS PURCHASED AND INSTALLED ON THE AIRCRAFT. (TC NR 20060605005) 1G71 3U3 U H2SW E4CE 20060627002262006062700226SW 2006 6 27 CA060605006 120060531G5320206031121023 WEB BELL 206 206B 1181511SW ALLSN 250C 250C20B 03013GL FUSELAGE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 12163 (CAN) DURING A ROUTINE 300 INSP ON THE AIRFRAME, A CRACK WAS NOTED ON UPPER AFT SECTION OF THE SEAT WEB ASSY. THIS AREA IS PRONE TO STRESS AND CRACKS WHEN THE SEAT PANEL (THAT IS ATTACHED TO IT) IS REMOVED, AND NO SUPPORT IS ADDED TO THE TOP OF THIS WEB ASSY. PEOPLE TEND TO LEAN OVER THIS AREA, PUTTING THEIR HANDS ON THE TOP OF THE WEB AND THE WEB ENDS UP SUPPORTED THE PERSONS WEIGHT. THIS IS THE PROBABLE CAUSE OF THE CRACK, WHICH CAN HAPPEN OVER TIME. THE WEB ASSY WAS REPLACED WITH A NEW PIECE, AND THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20060605006) 1G71 3U3 U H2SW E4CE 20060627002272006062700227GL 2006 6 27 CA060605007 220060603G72107636109103104 SHAFT SKRSKYS76 S76A 8143006NE ALLSN 250C 250C30S 03013GL ENGINE BROKEN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) THREADED END BROKEN OFF DURING ASSY. (ENGINE POWER OUTPUT ADAPTOR SHAFT) (TC NR 20060605007) 1G72 3U3 U H1NE E1GL 20060627002282006062700228SW 2006 6 27 CA060605008 120060531G5313206031123059 LONGERON BELL 206 206B 1181511SW ALLSN 250C 250C20B 03013GL FUSELAGE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 12163 (CAN) DURING A ROUTINE 300 HR INSP, A CRACK WAS FOUND ON THE LONGERON ABOVE THE LT REAR PASSENGER DOOR, AT THE FWD ATTACHMENT TO THE ROLLOVER BULKHEAD. THE CRACK ORIGINATED AT THE ATTACHING RIVETS. THE LONGERON WAS REPLACED WITH A NEW PIECE, AND THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20060605008) 1G71 3U3 U H2SW E4CE 20060627002292006062700229EU 2006 6 27 CA060605009 120060603G2497 WIRE AEROSPATR42 ATR42300 8680920EU PWA 120 PW120 NE HAMSTD14SF 14SF5 NE AC GEN CHAFED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) WE HAD BEEN HAVING TROUBLES WITH NR 2 AC GENERATOR FAULTS IN FLIGHT. AFTER READING SDR NR 20050427005, WE CHECKED OUR ATR AND DISCOVERED NR 2 AC GEN WIRING CHAFING AND ARCING ON NR 2 STARTER GENERATOR COOLING DUCT. WIRING REPAIRED AND INSULATED AS REQUIRED. WIRING SECURED TO PREVENT FUTURE CHAFING. (TC NR 20060605009) 2H72 4T4 TRTA53EU E20NE 6 CP7NE 20060627002302006062700230SW 2006 6 27 CA060605010 120060513G6320204040009061 TRANSMISSION BELL 204 204B 1181404SW LYC T53 T5313B 41549NE MAIN ROTOR MAKING METAL W K NONE O OTHER ININSP/MAINT 1 CA (CAN) METAL PARTICLES FOUND IN TRANSMISSION INTERNAL FILTER AFTER ROUTINE INSPECTION. NO CHIP LIGHT INDICATION. OIL DRAINED WITH NEW FILTER INSTALLED, AIRCRAFT RUN FOR ONE HOUR ON GROUND WITH METAL PARTICLES FOUND IN INTERNAL AND INLINE FILTER ASSY. NO CHIP LIGHT INDICATION. TRANSMISSION WAS REMOVED WITH T.S.N. 6631.1 T.S.O. 472.3 (TC NR 20060605010) 1G71 4U4 U H1SW E17EA 20060627002312006062700231NE 2006 6 27 CA060605011 220060529G7323430110116 GOVERNOR SNIAS 350 AS350D 8680803EU LYC LTS101LTS101600A2 41560NE MAIN ROTOR MALFUNCTIONED W K NONE O OTHER ININSP/MAINT 1 CA 2334 (CAN) HELICOPTER STARTED NORMALLY BUT WHEN THE THROTTLE WAS ADVANCED TO THE GATE (100 PERCENT NR), THE MAIN ROTOR STARTED OVERSPEEDING (400 RPM APPROX). THE THROTTLE WAS THEN PULLED BACK AND THE ROTOR SPEED DROPPED. WHEN THE THROTTLE WAS ADVANCED INTO THE GATE AGAIN, THE NR STARTED OSCILLATING BETWEEN 360 AND 400 NR WITH NO INPUT FROM THE THROTTLE OR COLLECTIVE. THE GOVERNOR WAS REPLACED AND THE PROBLEM WENT AWAY. (TC NR 20060605011) 1G71 3U3 U H9EU E5NE 20060627002322006062700232SW 2006 6 27 CA060605012 120060525G6210212015501115 BLADE BELL 212 212 1181420SW PWA PT6T PT6T3 52045EA MAIN ROTOR CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 3417 (CAN) MAIN ROTOR BLADE SMALL DEBOND FOUND ON LOWER SURFACE APPROX 81.5 INCHES FROM BUTT END JUST AFT OF THE STAINLESS STEEL LEADING EDGE STRIP ON DISASSEMBLY. (APRIL 07 2006) BLADE WILL BE INSPECTED WHEN ARRIVING BACK FOR REPAIR EVALUATION. PAINT REMOVED FROM DEBOND AREA WITH A SMALL CRACK FOUND CHORD WISE APPROX .7500 OF AN INCH LONG.(MAY 25 2006) (TC NR 20060605012) 1G71 4U4 U H4SW E22EA 20060627002332006062700233WP 2006 6 27 CA060606001 120060605G6240B3203 WARNING HORN ROBSINR44 R44RAVENII 7640122WP COCKPIT INTERMITTENT W O OTHER O OTHER NRNOT REPORTED 1 CA 17 (CAN) WARNING HORN WOULD NOT BE TRIGGERED BY THE COLLECTIVE MICRO SWITCHES. THE UNIT WOULD ONLY CLICK WHEN ACTIVATED AND TAPPING DIRECTLY ON THE UNIT WOULD THEN TRIGGER THE HORN. WIRING WAS CORRECT, AND NOT PART OF THE SNAG. (TC NR 20060606001) 1G71 3O H11NM 20060627002342006062700234WP 2006 6 27 CA060606002 120060512G6240B3203 WARNING HORN ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE FAILED W O OTHER O OTHER NRNOT REPORTED 1 CA 31 (CAN) LOW ROTOR RPM WARNING HORN NOT SOUNDING. REPLACED WITH A SERVICEABLE UNIT, NO FURTHER FAULTS FOUND. (TC NR 20060606002) 1G71 3O3 O H11NM 1E4 20060627002352006062700235SW 2006 6 27 CA060606004 120060605G324020700600 LINE CLEVELAND 3098C AIRTRCAT500 AT502B 0390307SW PWA PT6 PT6A34AG 52053NE HARTZLHCB3T HCB3TN3 GL BRAKE ASSY CRACKED W K NONE K FLUID LOSS ININSP/MAINT 1 CA 1910 (CAN) PILOT REPORTED RT BRAKE ALWAYS GOES SOFT WHILE TAXING. AFTER INSPECTING ENTIRE BRAKE INSTALLATION FOR LEAKS, FOUND THE FWD AND AFT BRAKE CALIPER INTERCONNECT HOSE, FWD FITTING CRACKED. THIS CRACK WAS ONLY APPARENT WHEN THE BRAKES HEAT UP AND THE CRACK OPENED AS IT EXPANDED, CAUSE FLUID TO LEAK. THE HOSE WAS REPLACED WITH NEW UNIT AND BRAKES BLED WITH NO FURTHER FAULTS. (TC NR 20060606004) 1L71 3T4 TNCA17SW E4EA 6 CP15EA 20060627002362006062700236WP 2006 6 27 CA060606005 120060512G7720624600718 GAUGE ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE CYLINDER HEAD STICKING W O OTHER O OTHER NRNOT REPORTED 1 CA 31 (CAN) CHT WAS REPORTED TO BE STICKING. THE GAUGE WAS FOUND TO BE NOT INSTALLED PROPERLY, CAUSING THE NEEDLE TO RUB ON THE FACE. THE GAUGE WAS REINSTALLED, AND NO FURTHER FAULTS WERE FOUND. (TC NR 20060606005) 1G71 3O3 O H11NM 1E4 20060627002372006062700237NE 2006 6 27 CA060606006 220060605G7310 FILTER AEROSPATR42 ATR42300 8680920EU PWA 120 PW120 NE HAMSTD14SF 14SF5 NE FUEL SYS CLOGGED W A UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 CA (CAN) IN CRUISE FLIGHT CREW NOTICED NR 1 ENGINE FUEL FILTER CLOG LIGHT ON. AIRCRAFT RETURNED TO BASE. MAINTENANCE REMOVED NR 1 ENGINE LP AND HP FUEL FILTERS FOR INSPECTION. LARGE AMOUNTS OF CONTAMINENTS FOUND IN LP. FILTERS WERE REPLACED. GROUND RUN CARRIED OUT. THIS IS THE SECOND OCCURANCE OF FUEL CLOG WARNING. 1ST AFTER 25 HRS FOLLOWING C-CHECK INSP. THE SECOND 1000HRS FOLLOWING C-CHECK. (TC NR 20060606006) 2H72 4T4 TRTA53EU E20NE 6 CP7NE 20060627002382006062700238EA 2006 6 27 CA060606007 120060602G2913848847 PUSH-PULL CABLE BOMBDR 848847 CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE HYDRAULIC PUMP FAILED W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA 5103 5103 MX564379 (CAN) DURING CLIMB CREW RECEIVED NR 3 HYDRAULIC HIGH TEMPERATURE CAUTION LIGHT. CREW ELECTED TO RETURN TO ORIGINATING AIRPORT. MAINTENANCE REPLACED NR 3 B HYDRAULIC PUMP. A/C RETURNED TO SERVICE. (TC NR 20060606007) 2L72 4F4 FRTA21EA E15NE 20060627002392006062700239CE 2006 6 27 CA060606008 120060527G5697MS24166D1 RELAY BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE HARTZLHCE4A HCE4A3A NE LOW HEAT DAMAGED W H DEACTIVATE SYST/CIRCUITS L NO TEST NRNOT REPORTED 1 CA (CAN) WHEN GROUND POWER WAS APPLIED TO THE AIRCRAFT IT WAS NOTICED THAT THE LT HEATED WINDSHIELD WAS WARM AND ANTI-ICE SWITCH WAS OFF. POWER TO WINDSHIELD, LIMITER IN LT NACELLE, WAS PULLED. INSP OF THE LT WINDSHIELD ANTI-ICE HI/LO RELAYS, BEHIND INSTRUMENT PANEL, REVEALED THAT TERMINAL A2 OF LO HEAT RELAY HAD HEAT DAMAGE AND WAS NO LONGER ATTACHED TO RELAY, IT WAS STILL ATTACHED TO WIRE H16A8, WIRE WAS NO LONGER ATTACHED TO RELAY AND ABOUT ONE INCH OF THE INSULATION FROM WIRE END WAS MISSING. RELAY INTERNAL CONTACTS A1 TO A2 SHOW EXCESSIVE PITTING AND ARCING. RELAY MS24166-D1 WAS REPLACED AND WIRE H16A8 WAS ALSO REPLACED. (TC NR 20060606008) 2L72 4T4 TRTA24CE E26NE 5 CP10NE 20060627002402006062700240GL 2006 6 27 CA060606009 220060529G7322412B0220 CONTROL CABLE BELL 206 206B 1181511SW ALLSN 250C 250C20B 03013GL THROTTLE BROKEN W K NONE O OTHER ININSP/MAINT 1 CA 7112 (CAN) CABLE BROKE APPROXIMATELY 9.5 FROM END. (TC NR 20060606009) 1G71 3U3 U H2SW E4CE 20060627002412006062700241CE 2006 6 27 CA060606010 120060603G2910GPP125040 PRESSURE SWITCH CESSNA208 208 2073702CE HYD SYSTEM FAILED W L ABORTED APPROACH O OTHER APAPPROACH 1 CA 38 (CAN) UPON APPROACH FOR LANDING, WHEELGEAR WOULD NOT EXTEND (AMPHIBIAN AIRCRAFT) ABORTED APPROACH , AICRAFT LANDED ON FLOATS AT WATER BASE. AIRCRAFT PLACARDED (FLOATPLANE OPERATION ONLY). (TC# 20060606010) 1H71 3T NTA37CE 20060627002422006062700242EA 2006 6 27 CA060606011 220060605G7261130F0014S0314 LINE BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA OIL LEAKING W C ABORTED TAKEOFF KBJFLUID LOSS SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION TOTAKEOFF 1 CA (CAN) WHILE APPLYING TAKEOFF POWER THE PILOTS NOTICED SMOKE IN THE CABIN AND ABORTED THE TAKEOFF WITHOUT INCIDENT. DURING INVESTIGATION MAINTENANCE DISCOVERVED THAT A RECENTLY REPLACED OIL PRESSURE LINE TO THE TORQUE TRANSMITTER MANIFOLD WAS LEAKING AT THE FLARE FITTING. THE HOSE WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. (TC NR 20060606011) 1L72 4T4 T A24CE E4EA 20060627002432006062700243SW 2006 6 27 CA060606012 120060530G3246 BEARING SWRNGNSA227 SA227AC 8780603SW GARRTTTPE331TPE33111U 01514WP MCAULY4HFR344HFR34C652 NE LT MAIN WHEEL FAILED W O OTHER O OTHER CRCRUISE 1 CA (CAN) MAINT WAS ADVISED BY BASE AT DEPARTURE THAT LT IB MAIN WHEEL ASSY HAD FALLEN OFF AC ON TAKEOFF. AC CONTINUED TO MAINT BASE WHERE IT DID FLY BY TO DETERMINE IF WHEEL WAS MISSING. IT WAS DETERMINED THAT WHEEL ASSY WAS NOT ON THE AC. AC LANDED WITHOUT INCIDENT. LWR GEAR ASSY WAS REMOVED AND REPLACED WITH SERVICEABLE LWR GEAR, WHEEL ASSEMBLIES INCLUDING BRAKES. AC RETURNED TO SERVICE. UPON INVESTIGATION OF LWR GEAR IT WAS DISCOVERED THAT OUTER WHEEL BRG WAS HEAT DISCOLORED, OUTER RACE AND CAGE WERE MISSING. INNER RACE SHOWED NO SIGNS OF HEAT DISCOLORATION, CAGE WAS STILL ON THE INNER RACE ALTHOUGH QUITE DAMAGED. FOR AN UNDETERMINED REASON OUTER RACE FAILED AND CAUSED ALL DAMAGE. (TC NR 20060606012) 2L72 4T4 TRTA8SW E4WE 6 C3PNE 20060627002442006062700244NE 2006 6 27 CA060607001 220060523G7200 ROTOR CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE LT ENGINE N2 SEIZED W A UNSCHED LANDING EYJVIBRATION/BUFFET ENGINE STOPPAGE WARNING INDICATION CLCLIMB 1 CA (CAN) AS THE AIRCRAFT WAS CLIMBING, FLIGHT CREW HEARD A LOUD BANG AND LOST THE LT ENGINE. THEY NOTICED THAT THE ITT WAS AT 998 DEGREES AND AN ENGINE (VIB) ON THE N2 GAUGE. IT WAS FOUND THAT THE LT ENG N2 ROTOR WAS FOUND SEIZED WITH HAVING THE LT ENGINE REPLACED IAW AMM 71-00-00. ALL ENGINE PERFORMANCE, FUNCTION AND OPERATIONAL CHECKS CARRIED OUT. ALL ENGINE POST GRD RUN LEAK CHECKS CARRIED OUT. AS FOR NOW, THE PROBLEM IS STILL YET TO BE DETERMINED AND THIS SDR WILL BE UPDATED AS SOON AS THERE IS MORE INFORMATION AVAILABLE. (TC NR 20060607001) 2L72 4F4 FRTA21EA E15NE 20060627002452006062700245EA 2006 6 27 CA060607002 120060605G321313A04270006 METERING TUBE DHAV DHC6 DHC6300 2802606EA PWA PT6 PT6A34 52043EA HARTZLHCB3T HCB3TN3 GL STRUT FAILED W O OTHER O OTHER LDLANDING 1 CA 753 (CAN) FRACTURED AT LOWER THREAD WHERE THE TUBE SCREWS INTO THE PISTON. THIS ALLOWED THE UPPER AND LOWER SECTIONS OF THE SHOCK STRUT TO DISENGAGE CAUSING GEAR COLLAPSE. THE FAILED TUBE IS MADE OF ALUMINUM ALLOY. PART AND PICTURES AVAILABLE UPON REQUEST (TC NR 20060607002) 1H72 3T4 TRTA9EA E4EA 6 CP15EA 20060627002462006062700246NE 2006 6 27 CA060607003 220060604G7200CF343A1 ENGINE CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE FAILED W A UNSCHED LANDING YJ ENGINE STOPPAGE WARNING INDICATION CLCLIMB 1 CA 2194421944 (CAN) DURING CLIMB AT 2000 FT THE NR1 ENGINE FAILED, N1 DROPPED OFF AND TGT PEGGED. EMERGENCY WAS DECLARED AND AC RETURNED AND LANDED SAFELY. THIS REPORT IS INITIAL ONLY, FURTHER INFORMATION WILL BE FORWARDED ON RECEIPT OF THE TEARDOWN REPORT FROM THE MANUFACTURER. (TC NR 20060607003) 2L72 4F4 FRTA21EA E15NE 20060803002582006080300258SO 2006 8 3 CA060607004 120060606G2150C180559A BLOWER EMB 110 EMB110P1 3260122SO PWA PT6 PT6A34 52043EA VENT BURNED OUT W O OTHER B SMOKE/FUMES/ODORS/SPARKS NRNOT REPORTED 1 CA 662 (CAN) SHORTLY AFTER START UP, THE GROUND VENTILATION FAN WAS TURNED ON AND SMOKE STARTED TO ENTER THE AIRCRAFT CABIN. MAINTENANCE FOUND THE GROUND VENT BLOWER TO BE AT FAULT. THE GROUND VENT BLOWER WAS REMOVED AND DEFERRED. THE AIRCRAFT WAS THEN RETURNED TO SERVICE. THE BLOWER WILL BE SENT OUT FOR A STRIP REPORT. (TC# 20060607004) 1L72 4T4 T A21SO E4EA 20060627002472006062700247EA 2006 6 27 CA060607005 120060520G5610NP13932212 WINDOW CNDAIRCL600 CL6002C10 1390015EA GE CF34 CF348C1 NE COCKPIT CRACKED W O OTHER O OTHER DEDESCENT 1 CA 3580 (CAN) DESCENDING THROUGH 11,000 FEET, F/O SIDE WINDOW CRACKED MX REMOVED AND REPLACED SIDE WINDOW IAW CRJ 700 AMM 56-12-01. W/S HEAT CHECKS GOOD, NO LEAKS NOTED. (TC NR 20060607005) 2L72 4F4 FRTA21EA EOOO63EN 20060627002482006062700248EU 2006 6 27 CA060607006 120060607G7930704A37642043 TRANSMITTER SNIAS 350 AS350BA 8680817EU TMECA ARRIELARRIEL1B 6OO30NE ENGINE OIL IND ERRATIC W K NONE O OTHER ININSP/MAINT 1 CA 300 (CAN) TRANSMITTER PRODUCED ERRATIC AND ABNORMALLY LOW OIL PRESSURE INDICATIONS AT ENGINE IDLE SPEED. (TC NR 20060607006) 1G71 3U3 UNCH9EU E19EU 20060627002562006062700256NM 2006 6 27 CA060608001 120060604G5270 SWITCH BOEING727 727233 138408ANM PWA JT8 JT8D15 52051NE CARGO DOOR MALFUNCTIONED W O OTHER N FALSE WARNING CRCRUISE 1 CA AFTER DEPARTURE ON AN ACCEPTANCE FLIGHT AFTER HEAVY MAINTENANCE, THE CREW OBSERVED A NR 1 CARGO DOOR UNSAFE INDICATION. THE WARNING LIGHT EXTINGUISHED AT 7.2 PSID AFTER REDUCING ALTITUDE TO 11K FT. THE AIRCRAFT RETURNED TO POINT OF DEPARTURE WHERE THE SWITCH WAS ADJUSTED AND THE AIRCRAFT RELEASED FOR RETURN TO SERVICE. 2L73 4F4 FRTA3WE E2EA 20060627002572006062700257EA 2006 6 27 CA060608002 220060607G8530LW12416 CYLINDER CESSNA172 172P 2072436CE LYC O320 O320D2J 41508EA MCAULY1C160 1C160DTM GL NR 2 CRACKED W K NONE K FLUID LOSS ININSP/MAINT 1 CA 3994 831 L1487939A OIL LEAK FOUND COMING FROM ENGINE COWLING. AFTER FURTHER INVESTIGATION A CRACK WAS DISCOVERED IN THE NR 2 CYLINDER BARREL. 1H71 3O3 ONT3A12 E274 5 NP910 20080520 CE 2008 5 20 CA060608003 120060608G2701041321318 SHAFT CESSNA185 A185E 2072818CE CONT O520 IO520D 17032SO MCAULYD3A34 D3A34C401 GL AFT END DAMAGED W O OTHER O OTHER NRNOT REPORTED 1 CA 3561 (CAN) ON INSP, IT WAS FOUND THAT THE RT AND LT CONTROL WHEELS WERE LOOSE ON THE CONTROL SHAFTS. AVION RESEARCH STC 00709LA HAD PREVIOUSLY BEEN INSTALLED TO REPLACE THE CONTROL WHEELS, HOWEVER, THE INSTALLATION INSTRUCTIONS CW-8001 REV1 FEB26/98 DO NOT ADDRESS THE DIFFERENCE IN FASTENER SIZES BETWEEN THE ORIGINAL AND REPLACEMENT CONTROL WHEELS. THE STC HOLDER WAS CONTACTED AND A REVISED INSTRUCTION PAGE WAS SUPPLIED THAT REQUIRED ASSEMBLY OF THE CONTROL WHEELS WITH LOCTITE APPLIED TO THE CONTROL SHAFT. NO REVISION DOCUMENT WAS PROVIDED FOR THE ORIGINAL INSTUCTIONS. 1H71 3O3 O 3A24 E5CE 5 CP47GL 20060627002582006062700258SW 2006 6 27 CA060608004 120060511G5302 BOLT BELL 427 427 1182207SW TAIL BOOM LOOSE W K NONE O OTHER ININSP/MAINT 1 CA 1606 THE VERTICAL FIN WAS FOUND LOOSE DURING A SCHEDULE INSPECTION. ONE ATTACHMENT BOLT WAS SHANKED-OUT. ANOTHER BOLT WAS LOOSE BUT NOT SHANKED. NO OTHER DAMAGE WAS REPORTED. 1G71 3U R00001RC 20060627003342006062700334GL 2006 6 27 CA060608005 220060130G723023064613 IMPELLER ALLSN DOUG 600N 600N 3027377NM ALLSN 250C 250C47M 03013GL COMPRESSOR CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 3469 CAC44183 (CAN) PILOT REPORTED HIGH TURBINE TEMPERATURES IN FLIGHT, RETURNED TO MAINTENANCE FACILITY AND FOUND CRACK IN COMPRESSOR SCROLL AREA UPON VISUAL INSPECTION AFTER LANDING. ENGINE ASSY WAS REMOVED AND COMPRESSOR INLET WAS INSPECTED AND FOUND TO HAVE A DAMAGED IMPELLER BLADE. COMPRESSOR ASSY WAS REMOVED AND SENT FOR FURTHER INSPECTION. IT WAS LATER DETERMINED THE BLADE HAD FAILED FROM A PREVIOUS REPAIR CARRIED OUT TO REMOVE FOD DAMAGE TO THAT BLADE. SPARE ENGINE WAS INSTALLED AND AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20060608005) 1G71 3U3 UNCH3WE E1GL 20060627003352006062700335NM 2006 6 27 CA060608006 120060321G5302600N3500505 TAIL BOOM DOUG 600N 600N 3027377NM ALLSN 250C 250C47M 03013GL SEPARATED W O OTHER D INFLIGHT SEPARATION NRNOT REPORTED 1 CA 3615 (CAN) AIRCRAFT INVOLVED IN EXTERNAL LIFT OPERATIONS. TAIL BOOM ASSY SEPARATED FROM FUSELAGE IN FLIGHT, AIRCRAFT CRASHED ON RT SIDE OF FUSELAGE IN A REMOTE CLEARING. CAUSE OF FAILURE IS UNDER INVESTIGATION. (TC NR 20060608006) 1G71 3U3 UNCH3WE E1GL 20060627002592006062700259WP 2006 6 27 CA060608007 120060527G5302 STRUCTURE ROBSINR44 R44 7640120WP LYC O540 O540F1B5 41532EA TAILBOOM MISMANUFACTURED W K NONE O OTHER ININSP/MAINT 1 CA DURING SCHEDULED MANDATORY REPLACEMENT OF THE HORIZONTAL STABILIZER IT WAS DETERMINED THAT THE NEW PART SUPPLIED BY THE MANUFACTURE WAS INCORECTLY MANUFACTURED. THE MOUNTING HOLES FOR THE ATTACHMENT OF THE VERTICAL STABILIZERS WERE FOUND TO BE INCORRECTLY LOCATED AND THE ASSOCIATED ANCHOR NUTS WERE MISALIGNED FROM THE HOLES. PART WAS RETURNED TO THE MANUFACTURE TO DETERMINE THE CAUSE OF THE DEFECT. 1G71 3O3 O H11NM E295 20060627002492006062700249NM 2006 6 27 CA060608008 120060606G2622898052 EXTINGUISHER BOEING737 737* NM CFMINTCFM567CFM567B22 13802NE COCKPIT LEAKING W O OTHER O OTHER NRNOT REPORTED 1 CA 7450 THE A/C WAS AT CRUISE WHEN A HISSING SOUND WAS HEARD. IT WAS DETERMINED TO BE LEAKAGE FROM THE PORTABLE FIRE EXTINGUISHER IN THE FLIGHT DECK. THE HISS CHANGED TO A LOUD WHISTLE AS IT INCREASED. THE CAPTAIN GRABBED THE TOP OF THE EXTINGUISHER AND TWISTED IT AND THE LEAK STOPPED. THE EXTINGUISHER HAS BEEN RETRIEVED AND IS BEING SENT TO THE VENDOR FOR COMPLETE INVESTIGATION AND ANALYSIS. ONCE THOSE RESULTS HAVE BEEN RECEIVED THEY WILL BE ADDED TO THIS POSTING. 2L72 4F4 FRTA16WE E00055EN 20060627002502006062700250CE 2006 6 27 CA060608009 120060602G561099143809 WINDSHIELD CESSNA750 750 2076810CE COCKPIT FAILED W A UNSCHED LANDING O OTHER CRCRUISE 1 CA 2532 AIRCRAFT IN CRUISE AT 41000 FT, SMALL CRACK STARTED AT BOTTOM OB LOWER CORNER. WITHIN 15 SECONDS THE CRACK EXTENDED ABOUT 3 INCHES THEN WITHIN ABOUT 30 SECONDS THE OUTER PANE SHATTERED. THE AIRCRAFT WAS FLOWN TO A AIRPORT AND LANDED WITHOUT INCIDENT. THE AIRCRAFT WAS FERRIED TO A SERVICE CENTER UNPRESSURIZED AND A NEW WINDSHIELD INSTALLED. 2L72 4J RTT00007WI 20060627002512006062700251CE 2006 6 27 CA060608010 120060531G27205565096 CHANNEL CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE RUDDER PEDAL BROKEN W O OTHER O OTHER LDLANDING 1 CA 367 PILOTS REPORTED THAT WHEN THE RUDDER PEDALS ARE BOTH PUSHED, THE CO-PILOT'S INSTRUMENT LIGHTS DIM. INVESTIGATION REVEALED THAT THE PILOT'S RUDDER SUPPORT BRACKET WAS BROKEN AT THE TOP OF THE ATTACH CHANNEL. THE CO-PILOTS INSTRUMENT LIGHT RHEOSTAT WAS ALSO DAMAGED. THE SUPPORT CHANNEL AND THE RHEOSTAT WERE BOTH CHANGED. 1L72 4F4 F A22CE E1NE 20060627003362006062700336NE 2006 6 27 CA060608011 120060518G6320S613520060103 COVER SKRSKY SKRSKYS61 S61L 8142102NE GE CT58 CT581401 30011NE M/R GEARBOX CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 233 A14964 MAIN GEAR BOX WAS BEING REMOVED FOR INPUT FREEWHEEL REPLACEMENT. A CRACK WAS DETECTED ON THE RT FOOT OF REAR COVER, AS WELL AS A CRACK ON THE RT REAR AIRFRAME FITTING. THE ALIGNMENT FIXTURE WAS USED TO CHECK THE BOX BEAM, AND FOUND TO BE MISALIGNED. THE RT REAR AND LT FRONT FITTINGS WERE REPLACED TO CORRECT ALIGNMENT, AND GEAR BOX WAS REPAIRED AND REINSTALLED. 2G72 4U4 U 1H15 1E3 20060627003382006062700338EU 2006 6 27 CA060609002 120060406G77121004PGSB TRANSMITTER BRAERO748 HS7482A 4231001EU RROYCEDART DART5342 EU ROTOL R4304 R2124304 EU TORQUETRANSMTTERFAILED W C ABORTED TAKEOFF J WARNING INDICATION TOTAKEOFF 1 CA (CAN) TAKEOFF WAS REJECTED WHEN THE RT ENGINE TORQUE GAUGE BEGAN TO INDICATE ERRATICALLY, MEL 77-02 WAS USED FOR RELIEF AND THE AIRCRAFT CONTINUED ITS TRIP. MAINTENANCE DETERMINED THAT THE TORQUE TRANSMITTER HAD FAILED. THE TRANSMITTER WAS REPLACED, TESTED SERVICEBLE , MEL CLEARED AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20060609002) 2L72 3T4 T A24EU A196 6 CP899 20060627003392006062700339NE 2006 6 27 CA060609004 220060607G7510320115 ANTI-ICE VALVE BOEING737 737201 1384454NM PWA JT8 JT8D9A 52048NE INOPERATIVE W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA IN CLIMB, THE PORT ENGINE COWL ANTI-ICE LITE ILLUMINATED BRIGHT. THE AIRCRAFT RETURNED TO BASE. THE PORT ANTI-ICE VALVE WAS REPLACED, CHECKED SERVICEABLE AND AIRCRAFT RETURNED TO SERVICE. 2L72 4F4 F A16WE E2EA 20060627003402006062700340EU 2006 6 27 CA060612001 120060606G3230 WIRE HARNESS AEROSPATR42 ATR42300 8680920EU PWA 120 PW120 NE HAMSTD14SF 14SF5 NE LT MLG INOPERATIVE W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA DURING DEPARTURE, THE LANDING GEAR WOULD NOT RETRACT. THE AIRCRAFT RETURNED TO POINT OF DEPATURE AND LANDED WITHOUT INCIDENT. MAINTENANCE REPLACED THE UPPER WIRING HARNESS ON THE LT MAIN LANDING GEAR AND THE AIRCRAFT WAS RETURNED TO SERVICE. 2H72 4T4 TRTA53EU E20NE 6 CP7NE 20060705000142006070500014SW 2006 7 5 CA060612003 120060605G5410NAS12918 NUT BELL 430 430 1182150SW PYLON CRACKED W K NONE O OTHER ININSP/MAINT 1 CA ONE (1X) NUT FOUND CRACKED. 1G72 3U RTH9SW 20060705000152006070500015SO 2006 7 5 CA060612004 120060609G2910HYC5005 POWERPACK PIPER PA28 PA28R200 7102811SO LYC O360 IO360C1C 41514EA HYD SYS FAILED W A UNSCHED LANDING FJ FLT CONT AFFECTED WARNING INDICATION CRCRUISE 1 CA 902 HYDRAULIC POWER PACK BRUSHES FAILED, PART REPLACED. 1L71 3O3 O 2A13 1E10 20060705000162006070500016EA 2006 7 5 CA060612005 120060612G2932215T752322 PRESSURE SWITCH BOMBDR CNDAIRCL215 CL2156B11215 EA PWA PW120 PW123 NE HAMSTD14SF 14SF* NE ELEVATOR SYS INTERMITTENT W O OTHER F FLT CONT AFFECTED CRCRUISE 1 CA 2856 DURING A FLIGHT, HAD 3 SUCCESS IFS INPUTS FROM THE ELEVATOR SYSTEM THEY WERE IN NORMAL MODE AND SUDDENLY ITS WENT TO MANUAL MODE AND BACK TO NORMAL IN A COUPLES OF A FEW SECONDS WITHOUT ANY ACTION FROM THE CREWS . 2H72 4T4 TRTA14EA E20NE 6 CP7NE 20060705000182006070500018EU 2006 7 5 CA060612006 120060610G5100 UNKNOWN SNIAS 350 AS350D 8680803EU LYC LTS101LTS101600A2 41560NE UNKNOWN W A UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION APAPPROACH 1 CA ON FINAL APPROACH, APPROX 300 FT AGL, PILOT HEARD LOW ROTOR HORN ACTIVATE AND ENG LOOSE PWR. A SUCCESSFUL AUTOROTATION WAS COMPLETED WITH NO FURTHER INCIDENT. AFTER LANDING, ENG WAS STILL RUNNING AND ONCE COLLECTIVE WAS LOWERED, ENG RETURNED TO FULL PWR. PILOT TRIED RAISING COLLECTIVE AND EVERY TIME DID SO, ENG WOULD DECELERATE AND M/R RPM WOULD DECAY UNTIL COLLECTIVE WAS LOWERED AGAIN. A/C WAS SHUT DOWN AND EXAMINED BY ENGINEER. NO DEFECTS FOUND, AIRCRAFT WAS STARTED AND OPERATED NORM. PILOT WAS ABLE TO HOVER A/C W/OUT RE-EXPERIENCING PREVIOUS SYMPTOMS. SYMPTOMS COULD NOT BE DUPLICATED AND CAUSE OF DECEL COULD NOT BE DETERMINED THEREFORE ALL ENG CONTROL COMPONENTS WERE REPLACED BEFORE FURTHER FLT. 1G71 3U3 U H9EU E5NE 20060627002602006062700260EA 2006 6 27 CA060612007 120060610G3210C6U1180 LEG ASSY DHAV DHC6 DHC6300 2802606EA PWA PT6 PT6A27 52043EA MLG DAMAGED W O OTHER O OTHER LDLANDING 1 CA DURING A NORMAL LANDING PROCEDURE, THE LEFT MAIN LANDING GEAR BROKE OFF FOR A REASON UNKNOWN TO US. THE AIRCRAFT CONTINUED TO SKID ON THE STUD OF THE GEAR UNTIL COMING TO A COMPLETE STOP. AT THE END, THE AIRCRAFT TIPPED TO THE LEFT AND DAMAGED THE LEFT WING TIP. THERE WERE NO PERSONAL INJURIES. THE DAILY INSPECTION HAD BEEN PERFORMED AS USUAL AND THE PRE FLIGHT DID NOT SHOW ABNORMALITIES EITHER. THE TOTAL WEIGHT WAS WITHIN LIMITS. 1H72 3T4 TRTA9EA E4EA 20060705000192006070500019CE 2006 7 5 CA060613001 120060608G5340504200337 SUPPORT BEAM BEECH 100 A100 1152915CE PWA PT6 PT6A28 EA HARTZLHCB4T HCB4TN3 GL RUDDER QUAD CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 1849018490 UNDER THE PILOTS FLOORBOARDS AT FLIGHT STATION 107, THE PILOTS RUDDER QUADRANT SUPPORT BEAM WAS FOUND CRACKED. THESE CRACKS WERE FOUND AT 2 OF THE 4 NUT PLATES. FOUND THESE SAME CRACKS ON 3 OTHER OF OUR AIRCRAFT AROUND THE SAME LOCATIONS. THE BEAM WAS REPLACED. 1L72 3T4 T A14CE E4EA 6 CP40EA 20060705000202006070500020EU 2006 7 5 CA060613002 120060613G3110 WARNING LIGHT SNIAS 350 AS350B3 8680954EU TMECA ARRIELARRIEL2B NE WARNING PANEL FALSE INDICATIONW K NONE N FALSE WARNING ININSP/MAINT 1 CA UNIT RECEIVED AS INSPECTED. INSTALLED THE WARNING PANEL IN THE HELICOPTER AND ON GROUND RUN DISCOVERED THAT THE MAIN GEAR BOX RED PRESSURE LIGHT WOULD NOT EXTINGUISH. WARNING PANEL REPLACED AND THE LIGHT GOES OUT. 1G71 3U3 U H9EU E00054EN 20060803002592006080300259GL 2006 8 3 CA060613003 220060611G72616844716 SEAL LKHEED188 188A 5262602WP ALLSN 501D 501D13 03004GL NR 2 ENGINE LEAKING W E ENGINE SHUTDOWN KJ FLUID LOSS WARNING INDICATION CRCRUISE 1 CA (CAN) AFTER A WATER BOMBING RUN CLIMB OUT NR 2 ENGINE WAS SHOWING TWO GALLONS LOW ON OIL. THERE WAS NO OTHER ABNORMAL INDICATIONS, THE CREW DID A PRECAUTIONARY SHUT DOWN. MAINTENANCE FOUND THE SCAVENGE PUMP SEAL TO BE LEAKING OIL BY, THE SEAL WAS REPLACED AND THE ENGINE RUN CHECKED TO BE SERVICABLE. 2L74 4T4 TRT4A22 E282 20060627002762006062700276CE 2006 6 27 CA060613004 120060612G323350380043 BEARING BEECH 100 A100 1152915CE PWA PT6 PT6A28 EA MLG ACTUATOR MISINSTALLED W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA DURING ACT ENDPLAY CHECK AND LUBE OF N/G ACT 50-820208-5, NOTICED THRUST BEARING IMPROPERLY INSTALLED. INSTRUCTIONS IN COMPONENT MM ARE TO INSTALL BEARING WITH P/N AWAY FROM GEAR, THIS BEARING HAD BEARING MANUF P/N AND WORD THRUST ON ONE SIDE AND RAYTHEON P/N ON OTHER, ALLOWING YOU TO FOLLOW INSTRUCTIONS AND HAVING A 50% CHANCE OF GETTING IT RIGHT. THIS BEARING WAS INSTALLED BACKWARDS WITH RAYTHEON P/N AWAY FROM GEARS PUTTING ACTUAL THRUST SIDE TOWARDS GEARS OPPOSITE TO THRUST LOADS. ACT WAS FURTHER INSPECTED AND SMALL AMT OF SPALLING FOUND ON GEARS. ACT IS BEING RETURNED TO OVERHAUL FACILITY WERE BEARING AND GEARS WILL BE REPLACED. THIS ACT WAS REMOVED FOR IT FIRST ENDPLAY CHECK SINCE LAST OVERHAUL WITH A1L72 3T4 T A14CE E4EA 20060627002772006062700277 2006 6 27 CA060614001 120060614G7921JR28548A OIL COOLER RROYCE JR28548A RROYCETAY TAYMK6118 NE FUEL OIL UNSERVICEABLE W K NONE O OTHER ININSP/MAINT 1 CA VARIOUS 5 FUEL COOL OIL COOLERS (FCOC) RE-CALLED FROM SOUTHWEST COOLER SERVICE INC, APPROVED SUPPLIER FOR ROLLS-ROYCE CANADA) DUE TO FAA UNAPPROVED PART NOTIFICATION NR 2005-00187. ROLLS-ROYCE CANADA HAVE RE-ROUTED 5 SUSPECT UNAPPROVED FCOCS TO SERCK AVIATION (OEM APPROVED SUPPLIER) FOR RE-OVERHAUL. SERCK AVIATION HAS REPORTED FCOC WITH MISSING; THERMO ADAPTOR, NUTS AND WASHERS FROM END COVERS AND ALSO ONE FCOC MATRIX (CORE) THAT FAILED PRESSURE TEST DUE TO 11 TUBES JOINT (FERRULE) LEAKS. THE FCOC WERE PREVIOUSLY DECLARED OVERHAULED CONDITION BY SOUTHWEST COOLER SERVICE INC UNDER RRC PURCHASE ORDER. RRC ENGINEERING AND ROLLS-ROYCE OEM ARE EVALUATING IN SERVICE COOLERS OVERHAULED BY SOUTHWEST COOLER INC. 4 F A25NE 20061213001282006121300128SW 2006 12 13 CA060614004 120060224G6320212030154101 FITTING BELL 212 212 1181420SW PWA PT6T PT6T3 52045EA MAIN ROTOR CRACKED W O OTHER O OTHER CRCRUISE 1 CA (CAN) PILOT REPORTED A FORE-AFT KICK IN THE CYCLIC, AT THE SAME TIME THEY HEARD A NOISE. ON ARRIVAL OF THE AC, INSPECTED THE M/R SYSTEM, SWASHPLATE, SCISSORS AND SLEEVE, TRANSMISSION MOUNTS AND NO DAMAGE WAS FOUND. A/C WAS FLOWN AGAIN AND THE PILOT REPORTED AN INTERMITTENT LATERAL VIBRATION. ON FURTHER INSPECTION, FOUND BOTH EARS ON THE LOWER LIFT LINK FITTING WERE CRACKED. A/C WAS DISASSEMBLED TO ALLOW REPLACEMENT OF THE FITTING, A/C REASSEMBLED AND RETURNED TO SERVICE. FAILURE OF THIS FITTING WAS A RESULT OF AN INCORRECT FITTING/ATTACH BOLT CONFIGURATION, THERE ARE 2 LOWER LIFT LINK CONFIGURATIONS POSSIBLE. (TC NR 20060614004) 1G71 4U4 U H4SW E22EA 20060627002782006062700278NE 2006 6 27 CA060614005 220060609G7200 CASE BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE HARTZLHCE4A HCE4A3I NE ENGINE LEAKING W EA ENGINE SHUTDOWN UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CRCRUISE 1 CA 4833 APPROX 20 MIN INTO CRUISE FLIGHT, THE LT LOW OIL PRESSURE LIGHT CAME ON . THE ENGINE WAS SHUT DOWN AS IT REACHED 50 PSI. ELECTED TO RETURN TO PLACE OF DEPARTURE AND A SUCCESSFUL LANDING WAS MADE. UPON STOPPING A LARGE QUANTITY OF OIL WAS FOUND UNDERNEATH LT ENGINE COWL. MAINTENANCE WAS DISPATCHED AND A COMPLETE REPORT WILL FOLLOW WITH FURTHER FINDINGS. 2L72 4T4 TRTA24CE E26NE 5 CP10NE 20061213001292006121300129CE 2006 12 13 CA060615001 120060613G80006041H190 RELAY BEECH 90 C90 1152913CE PWA PT6 PT6A21 52043EA HARTZLHCB3T HCB3TN3 GL STARTER BURNED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) AIRCRAFT WAS ON A OPS 1 INSPECTION BASE . WHILE WORKING ON SNAG 1769A (OIL COMING FROM A/C COMPRESSOR). AFTER REMOVING THE UNSERVICEABLE A/C COMPRESSOR A VISUAL OF THE SURROUNDING AREA REVEALED THAT THE AIR CONDITIONER START RESISTOR PHENOLIC P/N 100-364190-31 WAS BURNED ON BOTH SIDES AND THAT ONE OF THE TERMINALS WAS BROKEN ON THE START RELAY. WE ARE GOING TO REPLACE A/C COMPRESSOR P/N ER206R-25202 , START RELAY P/N 6041H190 , PHENOLIC P/N 100-364190-31 THAT IS MOUNTED ON BOTH SIDES OF THE A/C START RESISTOR AND SERVICE SYSTEM . (TC NR 20060615001) 1L72 3T4 T 3A20 E4EA 6 CP15EA 20060627002802006062700280EU 2006 6 27 CA060615002 120060604G5514F50B381003111 GUIDE AMD FALC50FALCON50MYST2730106EU GARRTTTFE731TFE73131C 01518NE HORIZONTAL STAB BENT W K NONE O OTHER ININSP/MAINT 1 CA 8351 GUIDE PLATE SEPARATED FROM HORIZONTAL STAB FILLET, WAS FOUND LYING BETWEEN VERTICAL STABILIZER AND HORIZONTAL STABILIZER. UNIT HAD BEEN CRUSHED BETWEEN HORIZONTAL STAB AND VERTICAL STAB AS STAB WAS TRIMMED POTENTIAL THAT GUIDE PLATE COULD HAVE MOVED AFT AND JAMMED ELEVATOR LINKAGE. UNIT WAS REMOVED STRAIGHTENED AND REATTACHED TO HORIZONTAL STAB FILLET ASSEMBLY PER MANUFACTURERS INSTRUCTIONS "SRM SI-20-05, S0-10-04, HORIZONTAL STAB WAS TRIMMED THROUGHOUT ITS ENTIRE RANGE AND NO DISCREPANCIES FOUND. 2L73 4F4 F A46EU E6WE 20060627002812006062700281EA 2006 6 27 CA060615003 220060615G7200 ENGINE BEECH 1900 1900C 1154161CE PWA PT6 PT6A65B 52043EA HARTZLHCB4M HCB4MP3 GL LEFT SURGES W A UNSCHED LANDING XMJENGINE FLAMEOUT OVER TEMP WARNING INDICATION CLCLIMB 1 CA 6914 PCE32506 ON CLIMB-OUT, THE AIRCRAFT EXPERIENCED A LEFT ENGINE SURGE WITH HIGH ITT AND LOW OIL PRESSURE INDICATIONS. THE CREW SHUT DOWN THE ENGINE IN FLIGHT AND RETURNED FOR AN UNEVENTFUL LANDING. MAINTENANCE PERSONNEL REPORTED DEBRIS IN THE EXHAUST AND OIL LEAKING FROM THE ENGINE. THERE IS ALSO AN UNUSUAL NOISE WHEN THE PROPELLER IS ROTATED BY HAND. THE ENGINE WILL BE REMOVED TO AN APPROVED OVERHAUL FACILITY FOR INVESTIGATION. 2L72 4T4 TRTA24CE E4EA 6 CP56GL 20061213001302006121300130SO 2006 12 13 CA060615004 120060609G76032489418 THROTTLE CABLE PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA HARTZLHCE3Y HCE3YR2A GL LT ENGINE FAILED W A UNSCHED LANDING F FLT CONT AFFECTED CLCLIMB 1 CA (CAN) AC DEPARTED AND A SHORT TIME LATER THE PILOT REPORTED THE LT ENGINE THROTTLE / MANIFOLD WAS SET AT 38 AND WAS NOT RESPONDING. THE PILOT DIVERTED BACK. ON DECENT THE LT ENGINE MANIFOLD STAYED CONSTANT AT 38, THE EGT BEGAN TO RISE, ALONG WITH THE CYLINDER HEAD, AND OIL TEMPERATURE. THE AIRCRAFT LANDED SAFELY WITH BOTH ENGINES RUNNING. ONCE ON THE GROUND THE LT ENGINE WAS SHUTDOWN, TAXIED TO RAMP ON RT ENGINE. THE LT ENGINE WAS INSPECTED, FOUND TO HAVE LOST ALL ENGINE OIL. THE ENGINE SUSTAINED EXTENSIVE DAMAGE. MAINTENANCE DETERMINED THE LT THROTTLE CABLE IN THE CABIN PEDESTAL HAD FAILED. THE THROTTLE CABLE WIRES HAD SEVERED APPROXIMATELY .3125 FROM THE SWAGED PORTION OF THE ROD END. UNFORTUNATELY ON A RO1L72 3O3 O A20SO E14EA 5 CP33EA 20060803002602006080300260EA 2006 8 3 CA060615005 120060613G3246C3US1563 BOLT DHAV DHC3 DHC3 2800202EA MLG WHEEL FAILED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) WHILE PERFORMING MAIN LANDING GEAR (MLG) WHEEL/SKI REMOVAL AND CHANGE TO WHEELS ONLY, MAINTENANCE FOUND THE RIGHT HAND WHEEL/SKI ATTACH BOLT P/N: C3US156-3 TO BE BROKEN. THE BOLT ATTACHES THE SKI BRACKET ASSEMBLY LINK P/N: C3US108-34 TO THE MLG STRUT AND AXLE. THE BOLT HAS FAILED AT THE START OF THE RADIUS WHERE THE DIAMETER OF THE BOLT CHANGES FROM .500" DIAMETER, TO .750" DIAMETER. IT APPEARS THAT THE BOLT FAILURE OCCURRED ON THE TOOLING MARK. THIS IS OUR SECOND OCCURRENCE WITHIN 59.4 HOURS AND 115 CYCLES. (TC# 20060615005) 1H71 3R A815 20060627002832006062700283 2006 6 27 CA060615006 120060614G2720M4612BFG ROD END WRIGHTR1820 982C9HE2 67020EA HAMSTD43D 43D51 NE BROKEN W D RETURN TO BLOCK F FLT CONT AFFECTED TXTAXI/GRND HDL 1 CA 1243 DURING GROUND OPERATION THE PILOT FELT A "CLUNK" IN THE RUDDER SYSTEM WHILE OPERATING THE SERA SYSTEM. MAINTENANCE CREWS INVESTIGATED AND FOUND THE SERA LOCK ACTUATOR ROD END HAD BROKEN. THE ROD END WAS REPLACED, THE SYSTEM WAS FUNCTION CHECKED SERVICEABLE AND THE AIRCRAFT WAS RETURNED TO SERVICE. 4 R E259 6 CP8879 20061213001312006121300131EU 2006 12 13 CA060616001 120060326G6220704A33633211 SPHERICAL STOP SNIAS 350 AS350BA 8680817EU TMECA ARRIELARRIEL1B 6OO30NE MAIN ROTOR UNSERVICEABLE W O OTHER O OTHER CRCRUISE 1 CA 3065 (CAN) A/C HAD ABNORMAL VIBRATION AND WOULD NOT STAY IN TRACK. SPHERICAL STOPS HAD EXCESSIVE RUBBER LOSS AND SEPARATION. INSTALLED NEW SPHERICAL STOPS AND M/R COULD BE BALANCE AND TRACKED WITH NO ABNORMAL VIBRATION. (TC NR 20060616001) 1G71 3U3 UNCH9EU E19EU 20060627002872006062700287CE 2006 6 27 CA060616003 120060530G3340CM358910 SWITCH CESSNA172 172S 2072439CE LYC IO360 IO360L2A EA LANDING LIGHT HOT W H DEACTIVATE SYST/CIRCUITS M OVER TEMP CRCRUISE 1 CA 2006 WHEN THE PILOT WENT TO TURN OFF LANDING LIGHT SWITCH, FOUND TO BE HOT AND THE LANDING LIGHT WOULD NOT TURN OFF, THE SWITCH FINALLY TURNED OFF. THE SWITCH WAS REPLACED WITH A NEW UNIT. 1H71 3O3 ONT3A12 1E10 20060627002892006062700289 2006 6 27 CA060616004 120060524G324640289 WHEEL MLG MISMANUFACTURED W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA PURCHASED EIGHT CLEVELAND 40-289 WHEEL ASSEMBLIES NEW FROM FACTORY, RETURNED FIVE ASSEMBLIES DUE TO WHEELS INSPECTED BY EDDY CURRENT AND FOUND SEVERAL CASTING FLAWS (VOIDS) IN BEAD AREAS. WHEEL ASSEMBLIES RETURNED TO FACTORY FOR INVESTIGATION BY THEIR QA DEPARTMENT, HAVE NOT RECEIVED ANY RESPONSE FROM PARKER AEROSPACE AS OF JUNE 9/06. TWO WHEEL ASSEMBLIES RETURNED THROUGH KADEX AERO SUPPLY, NO SERIAL NUMBERS LISTED. THREE WHEEL ASSEMBLIES RETURNED THROUGH AVIALL (CALGARY), SERIAL NUMBERS AS FOLLOWS: 4553/4578, 4581/4554, 4575/NSN. 20060705000232006070500023EU 2006 7 5 CA060616005 220060614G7200 ENGINE BRAERO748 HS7482A 4231001EU RROYCEDART DART5342 EU ROTOL R4304 R2124304 EU NR 2 SHUTDOWN W A UNSCHED LANDING YJ ENGINE STOPPAGE WARNING INDICATION CRCRUISE 1 CA 7971 192902 (CAN) IN CRUISE, ENROUTE TO DESTINATION, THE NR 2 ENGINE AUTO FEATHERED AND SHUTDOWN. THE AIRCRAFT DIVERTED AND LANDED WITHOUT FURTHER PROBLEM. THE NR 2 ENGINE WILL BE REPLACED ON SITE. NO CONCLUSION AS TO THE CAUSE HAVE BEEN ARRIVED AT. (TC NR 20060616005) 2L72 3T4 T A24EU A196 6 CP899 20060803002612006080300261WP 2006 8 3 CA060616006 220060615G7297 CONNECTOR BAG JETSTMJETSTM3101 1500215EU GARRTTTPE331TPE33110UG 01514WP ROTOL R333 R333482F12 GL ENGINE DAMAGED W EA ENGINE SHUTDOWN UNSCHED LANDING XJ ENGINE FLAMEOUT WARNING INDICATION CLCLIMB 1 CA 6916 P63111 (CAN) AFTER DEPARTURE CLIMBING THROUGH 7500FT THE RIGHT ENGINE TORQUE STARTED TO FLUCTUATE.CREW PULLED THE QRH AND FOLLOWED THE DRILLS AND WERE GETTING 10-20% FLUCTUATION CAUSING THE A/C TO YAW RADICALLY LEFT AND RIGHT AT ALL POWER SETTINGS WITH TTL ON OR OFF SO A PRECAUTIONARY SHUTDOWN WAS PERFORMED AND RETURNED TO BASE WITHOUT INCIDENT. MTCE ENGINE RUNUPS CONFIRMED THE TQ FLUCTUATIONS AND TROUBLESHOOTING FOUND A LOOSE PIN CONNECTION ON THE RT ENGINE STRAIN GAUGE CONNECTOR. THE CONNECTION WAS REPAIRED AND THE A/C WAS RUN UP AND RETURNED TO SERVICE. 2L72 4T4 TRTA21EU E4WE 6 CP61GL 20060627002902006062700290EA 2006 6 27 CA060616008 120060610G5610NP1393222 WINDOW CNDAIRCL600 CL6002B19 1900309EA COCKPIT CRACKED W A UNSCHED LANDING O OTHER CRCRUISE 1 CA 16406 THE RT SIDE WINDOW CRACKED WHILE IN CRUISE. FLIGHT WAS DIVERTED TO MAINTENANCE BASE. WINDOW REPLACED IN ACCORDANCE WITH AMM. THIS WINDOW IS A PRE-SERVICE BULLETIN. 2L72 4F RTA21EA 20060627002922006062700292EA 2006 6 27 CA060616009 120060611G5610NP139221 WINDOW CNDAIRCL600 CL6002C10 1390015EA CRACKED W O OTHER O OTHER APAPPROACH 1 CA 9276 THE INNER PLY OF THE LT WINDOW CRACKED WHILE ON APPROACH. WINDOW WAS REPLACED IN ACCORDANCE WITH AMM. THE WINDOW IS A PRE-SERVICE BULLETIN. 2L72 4F RTA21EA 20060627002932006062700293WP 2006 6 27 CA060617001 120060609G325010150 STEERING SYS CVAC 440 440 2422902WP ALLSN 501D 501D22 03005GL HAMSTD54H 54H60 NE NLG MALFUNCTIONED W O OTHER S AFFECT SYSTEMS LDLANDING 1 CA 10605 AFTER T/O, DURING L/G RETRACTION, NOSE WHEELS ENTERED W/W IN A RT TURN ATTITUDE, EVIDENT FROM WEAR MARKS ON TIRES AND RUBBER ON INTERIOR WALLS OF W/W. WHEN A/C LANDED, NOSE WHEELS WERE STILL TURNED TO THE RIGHT, UNKNOWN TO AIRCREW. CAPT TRIED TO STRAIGHTEN NOSE WHEELS OUT BUT HAD TO TRY A COUPLE TIMES BECAUSE THERE WAS NO RESPONSE FROM STEERING ACTUATOR. NOSE WHEEL STEERING DID RESPOND TO INPUTS AND AIRCRAFT WAS ABLE TO TAXI. IT APPEARS THAT ACTUATOR HAD AN UNCOMMANDED STEERING INPUT UPON TAKEOFF AND LOCKED IN THAT POSITION UNTIL LANDING. ACTUATOR WAS CHANGED AND AIRCRAFT DEEMED SERVICEABLE. ACTUATOR WAS SENT BACK TO TYPE CERTIFICATE HOLDER OF AIRCRAFT FOR ANALYSIS. 2L72 4R4 T 6A6 E282 6 CP906 20060627002942006062700294WP 2006 6 27 CA060618001 220060616G7250 TURBINE LEAR 45 45LEAR 5170805CE GARRTTTFE731TFE731* 01518WP ENGINE NICKED W K NONE O OTHER ININSP/MAINT 1 CA DURING A WALK AROUND, MAINTENANCE PERSONNEL NOTICED A PAINT CHIPPED INSIDE THE LT THRUST REVERSER. FURTHER INVESTIGATION FOUND OVER A DOZEN NICKS ON THE 3ND STAGE TURBINE. ENGINE WILL BE REMOVED AND SENT TO AN HEAVY MAINTENANCE FACILITY AND A LOANER ENGINE WILL BE INSTALLED. 2L72 4F4 FRTT00008WIE6WE 20060627002962006062700296CE 2006 6 27 CA060618002 120060617G5753 SKIN LEAR 45 45LEAR 5170805CE GARRTTTFE731TFE731* 01518WP RT TE FLAP BIRD STRIKE W O OTHER O OTHER APAPPROACH 1 CA ON APPROACH, ON FLAIR AIRCRAFT HIT A BIRD. ONCE ON THE GROUND THE CREW REPORTED TO MAINTENANCE PERSONAL WHO AFTER INSPECTING THE AIRCRAFT FOUND A DENT ON THE RT FLAP BOTTOM SKIN. DUE TO THE LOCATION OF THE DENT WHICH WAS NOT COVERED UNDER SRM. SUPPORT ENGINEERING WAS CONTACTED AND A ENGINEERING DISPOSITION WAS ISSUED TO RETURN THE AIRCRAFT INTO SERVICE. AN INSPECTION OF THE AREA IS REQUIRED APPROXIMATELY EVERY 50 HOUR UNTIL REPAIR IS COMPLETED OR ANOTHER FLAP IS INSTALLED. 2L72 4F4 FRTT00008WIE6WE 20060627002972006062700297GL 2006 6 27 CA060619001 320060217G6111S90AT4 BLADE MCAULY D2A34C58NO CESSNA185 A185E 2072818CE CONT O520 IO520D 17032SO MCAULY2A34C D2A34C58 GL PROPELLER CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 800 705814 705814 PROPELLER D2A34C58, SERIAL NR 705814, WORK ORDER NR T68807, C-FYJJ. PROPELLER RECEIVED FOR 10 YEAR OVERHAUL. LAST OVERHAUL MARCH 1996, NOW 800.5 HOURS SINCE OVERHAUL. FOUND BLADE S-90AT-4, SERIAL NR C75151YS, CRACKED IN BLADE THREADS, FOUND WITH EDDY CURRENT. 1H71 3O3 O 3A24 E5CE 5 CP3EA 20060803002622006080300262CE 2006 8 3 CA060619002 120060612G27315061001736 TAB BEECH 90 C90A 1152911CE PWA PT6 PT6A21 52043EA ELEVATOR TRIM CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) CRACK DISCOVERED ON LOWER TAB SURFACE SKIN ADJACENT TO TAB HORN ATTACH RIB. SEE PICTURES ATTACHED.TRIM TAB ASSEMBLY P/N 50-610017-36 REPLACED WITH NEW. ELEVATOR AND TAB ASSEMBLY BALANCED (21.33 IN LBS TAIL HEAVY) AND REINSTALLED. INDEPENDENT CHECK ON R/H TAB AND ELEVATOR INSTALLATION CARRIED OUT - TAB TRAVELS 9.5 DEG NOSE DOWN AND 20.5 DEG NOSE UP. (TC# 20060619002) 1L72 3T4 TRT3A20 E4EA 20060627002982006062700298GL 2006 6 27 CA060619003 320060217G6114D4716 HUB MCAULY D2A34C58NO CESSNA185 A185E 2072818CE CONT O520 IO520D 17032SO MCAULY2A34C D2A34C58 GL PROPELLER CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 800 705814 705814 (CAN) PROPELLER D2A34C58-NO, SERIAL NR 705814, WORK ORDER NR T68807, C-FYJJ. PROPELLER RECEIVED FOR 10 YEAR OVERHAUL. LAST OVERHAUL MARCH 1996, NOW 800.5 HOURS SINCE OVERHAUL. FOUND HUB D4716, SERIAL NR 705814, CRACKED IN THREADS THAT THE BLADE RETENTION NUT SCREW INTO, FOUND WITH EDDY CURRENT. 1H71 3O3 O 3A24 E5CE 5 CP3EA 20060803002632006080300263CE 2006 8 3 CA060619004 120060615G71101099100531516 CHANNEL BEECH 90 C90A 1152911CE PWA PT6 PT6A21 52043EA COWL CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) THE P/N 109-910053-15 AND -16 COWL SUPPORT CHANNELS WERE FOUND CRACKED IN THE LOWER FLANGE AREA, AND SUBSEQUENTLY REPAIRED. MANY OF THE REPAIRS HAVE ALSO FAILED. IT APPEARS THAT A SUBSTANTIAL AMOUNT OF COWLING WEIGHT RESTS ON THESE CHANNELS. THE REPEAT DAMAGED SUGGESTS THAT THIS AREA IS UNDER DESIGNED. SEVERAL OTHER OPERATOR C90A AIRCRAFT HAVE SHOWN SIMILAR FAULTS. (TC# 20060619004) 1L72 3T4 TRT3A20 E4EA 20060627002992006062700299EA 2006 6 27 CA060619005 120060606G2910B030212604 B-NUT CNDAIRCL600 CL600* EA GE CF34 CF34* NE HYD SYSTEM LEAKING W O OTHER KJ FLUID LOSS WARNING INDICATION CLCLIMB 1 CA AFTER TAKEOFF, "NR 2 HYD LOW PRESS" CAUTION MESSAGE WAS DISPLAYED. THE AIRCRAFT RETURNED TO THE ORIGINATING AIRPORT AND PERFORMED AN EMERGENCY LANDING. MAINTENANCE FOUND THE FORWARD NR 2 BRAKE ACCUMULATOR CONNECTING HYDRAULIC LINE'S NUT LOOSE (CRJ700/900 IPC 29-17-06, FIG.23-AA1, ITEM NR 90). THE NUT WAS RE-TORQUED AS PER STANDARD PRACTICES AND NR 2 ENGINE DRIVEN PUMP (P/N 66190-3, S/N K0651) WAS REPLACED AS A PRECAUTION. NR 2 HYDRAULIC SYSTEM WAS SERVICED AND AIRCRAFT RETURNED TO SERVICE. NO MAINTENANCE HAS BEEN PREVIOUSLY PERFORMED ON THE HYDRAULIC LINE, NEITHER ON NR 2 BRAKE ACCUMULATOR. AIRFRAME HOURS WERE: 2625:04 AND CYCLES WERE: 1280. 2L72 4F4 FRTA21EA E15NE 20060627003002006062700300GL 2006 6 27 CA060619006 320060606G6114C2343 HUB MCAULY 2A36C29 CESSNA180 180C 2072608CE CONT O470 O470L 17026SO MCAULY2A36C 2A36C29 GL PROPELLER CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 3564 442 591003 MCCAULEY PROPELLER 2A36C29-AG, SERIAL NR 591003, WORK ORDER NR T69972, C-FLVF. PROPELLER RECEIVED FOR 10 YEAR OVERHAUL. LAST OVERHAUL 1996, NOW 442.5 HOURS SINCE OVERHAUL. FOUND HUB C2343, SERIAL NR 591003, CRACKED IN THREADS THAT THE BLADE RETENTION NUT SCREW INTO, FOUND WITH EDDY CURRENT. 1H71 3O3 O 5A6 E273 5 CP880 20060803002642006080300264GL 2006 8 3 CA060619007 120060425G334010128 LIGHT DHAV DHC2 DHC2MKI 2801830GL PWA R985 R985AN14B 52008NE EXTERIOR SHORTED W H DEACTIVATE SYST/CIRCUITS H ELECT. POWER LOSS-50 PC CRCRUISE 1 CA 29 (CAN) PILOT REPORTED STROBE CIRCUIT BREAKER (C/B) POPPED DURING FLIGHT, TROUBLESHOOTING REVEALED INCORRECT C/B INSTALLED (5AMP INSTEAD OF 7.5AMP). NEW C/B INSTALLED AT THAT TIME AND GROUND CHECKED SERVICEABLE. SEVERAL MONTHS LATER PROBLEM RE-OCCURRED DURING FLIGHT BUT GROUND CHECKED OK. WING TIPS REMOVED AND NOTED EVIDENCE OF ARCING FROM TANK INBOARD WALL/RIB AND WING TIP BOSS TERMINAL STRIP STUDS, STATICALLY THERE WAS NO CONTACT, WITH TANKS FULL DURING FLIGHT CONTACT OCCURRED. THE STUDS ON BOSS BAR HAS SUFFICIENT LENGTH TO TRIM 0.25" AND REMAIN IN SAFETY. TIPS RE-INSTALLED WITH PUTTY ON STUDS AND REMOVED TO REVEAL APPROXIMATELY 0.3" CLEARANCE. (TC# 20060619007) 1H71 3R3 RRCA806 5E1 20060803002542006080300254NE 2006 8 3 CA060619008 220060425G8550C2L293A ADAPTER DHAV DHC2 DHC2MKI 2801830GL PWA R985 R985AN14B 52008NE ENGINE OIL CRACKED W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) AIRCRAFT STATICALLY LEAKING ABOVE AVERAGE AMOUNT OF OIL ON HANGAR FLOOR. LOWER BELLY FAIRING/PANEL REMOVED BELOW RUDDER PEDALS, OIL ADAPTER BETWEEN OIL SHUT OFF AND FIREWALL NOTED TO BE SEVERE OF LEAK. ADAPTER REMOVED AND SILVER SOLDER JOINT FOUND CRACKED/LOSS OF ADHESION TO BASE METAL. ADAPTER REPLACED WITH NEW. (TC# 20060619008) 1H71 3R3 RRCA806 5E1 20060627003032006062700303EU 2006 6 27 CA060619009 120060608G7120 MOUNT BRAERO748 HS7482A 4231001EU RROYCEDART DART5342 EU COMPRESSOR CASE LOOSE W K NONE O OTHER ININSP/MAINT 1 CA 459324340 WHILE CARRYING OUT MAINTENANCE ON THE RT ENGINE, MAINTENANCE PERSONNEL FOUND LOOSE HARDWARE WHILE OPENING UP THE LOWER PORTION OF THE ENGINE COWLING. FURTHER INVESTIGATION REVEALED THAT THIS HARDWARE, CONSISTING OF ONE NUT AND ONE BROKEN STUD WITH THE NUT STILL ATTACHED, CAME FROM THE OUTBOARD ENGINE MOUNT FOOT. AT THIS TIME, IT WAS ALSO DISCOVERED THAT THE OTHER RETAINING NUTS ON THIS FOOT WERE ALSO SLIGHTLY LOOSE. THE ENGINE WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. AN IN-FIELD REPAIR WILL BE CARRIED OUT ON THE ENGINE. 2L72 3T4 T A24EU A196 20060803002672006080300267NM 2006 8 3 CA060619010 120060618G2497286A1062002 WIRE HARNESS BOEING737 737 UTILSYSNM CFMINTCFM567CFM567B22 13802NE NR 2 ENGINE DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA 2265 2265 (CAN) ON 18 JUNE 06 DURING TROUBLESHOOTING OF A RECURING NR 2 SOURCE OFF LIGHT ILLUMINATED SNAG, WIRE CHAFFING CAUSING ARCING WAS FOUND BETWEEN FEEDER WIRE HARNESS PART NUMBER 286A1062-002 BOEING IPC 24-11-51-01A ITEM NR 35 AND THE COWLING HINGE PART NUMBER 314-2241-1 BOEING IPC 71-11-02-10 ITEM 76. INVESTIGATION ALSO REVEALED SOME MINOR CHAFFING ON THE WIRE SHIELDING OF THE NUMBER ONE ENGINE HARNESS IN THE SIMILAR AREA. A FLEET CAMPAIGN IS RAISED TO INSPECT THE FLEET AND CONFIRM IF THIS IS AN ISOLATED EVENT. BOEING HAS BEEN INFORMED AND WILL BE KEPT ADVISED OF ALL FINDINGS AS THEY COME TO LIGHT. THIS SDR WILL BE UPDATED WITH ADDITIONAL INFORMATION WHEN AVAILABLE. 2L72 4F4 FRTA16WE E00055EN 20060803002692006080300269CE 2006 8 3 CA060619012 120060530G5311FS227 FRAME BEECH 100 100BEECH 1152916CE PWA PT6 PT6A28 EA FUSELAGE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) FRAME, F.S. 227 LOWER FLANGE CRACKED AT RADIUS. CRACK WAS APPROX 4.5 INCHES LEFT AND RIGHT OF A/C CENTRELINE. (TC# 20060619012) 1L72 3T4 T A14CE E4EA 20061213001322006121300132CE 2006 12 13 CA060619013 120060530G5220115430100605 SKIN BEECH BEECH 100 100BEECH 1152916CE PWA PT6 PT6A28 EA HARTZLHCD4N3HCD4N3A GL EMERGENCY EXIT CORRODED W K NONE O OTHER ININSP/MAINT 1 CA B8 (CAN) INNER SURFACE LOWER CENTER AREA BETWEEN WINDOW AND LOWER FRAME. CORROSION SPOT 1CM WIDE. WHEN BLENDED MATERIAL THICKNESS WAS INSUFFICIENT. (TC NR 20060619013) 1L72 3T4 T A14CE E4EA 5 CSTC 20061213001332006121300133CE 2006 12 13 CA060619014 120060530G57305012006896 SKIN BEECH 100 100BEECH 1152916CE PWA PT6 PT6A28 EA HARTZLHCD4N3HCD4N3A GL CENTER WING CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) SKIN P/N 50-120068-96 CRACKED AT HIGH SHEAR FASTENERS ATTACHING SKIN TO WING ATTACH FITTING. CRACKS (2) ORIGINATE FROM EDGE OF FASTENER COUNTERSINKS AND HEAD TOWARD NEXT FASTENER LOCATION. (TC NR 20060619014) 1L72 3T4 T A14CE E4EA 5 CSTC 20060627003062006062700306EU 2006 6 27 CA060620001 120060614G6123 SOLENOID VALVE PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL FEATHERING STICKING W K NONE O OTHER ININSP/MAINT 1 CA 1981 FEATHERING SOLENIOD VALVE STICKING INTERMITTENTLY IN FEATHER POSITION AND THEREFORE PROP STAYS FEATHERED AFTER ENGINE START. FAULT ONLY OCCURS DURING QUICK TURN AROUNDS ON HOT DAYS. AFTER ENGINE COOLS VALVE OPERATES NORMALY. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20060627003082006062700308EU 2006 6 27 CA060620002 120060615G61231310160 SOLENOID VALVE PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL FEATHERING STICKING W K NONE O OTHER ININSP/MAINT 1 CA (CAN) OVERSPEED GOVERNOR REPLACED WITH AN OVERHAULED UNIT (DUE TO FEATHERING VALVE STICKING INTERMITTANTLY SEE SDR 20060620001) AND DURING FEATHER CHECK THE PROP WOULD NOT COME OUT OF FEATHER. ELECTRICAL SYSTEM CHECKED. NO FAULTS FOUND. ANOTHER SERVICEABLE OVERSPEED GOV. INSTALLED AND OPERATION CHECKED SERVICEABLE. AIRCRAFT RETURNED TO SERVICE. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20060803002712006080300271NM 2006 8 3 CA060620003 120060620G2422100201022 STATIC INVERTER BOEING737 7377CG 13844FANM CFMINTCFM567CFM567B22 13802NE E & E BAY FAILED W H DEACTIVATE SYST/CIRCUITS JB WARNING INDICATION SMOKE/FUMES/ODORS/SPARKS NRNOT REPORTED 1 CA 149 (CAN) ON THE 20 JUNE 06 WHILE CONDUCTING A SCHEDULED PHASE 3 CHECK. MAINTENANCE FOUND ELEC LIGHT ILLUMINATED ON THE OVERHEAD PANEL. DURING THE TROUBLESHOOTING AN ODOR OF SMOKE WAS NOTICED IN THE E & E BAY. A BITE CHECK WAS CARRIED OUT AND FOUND THE STATIC INVERTER PN 1-002-0102-2090 SN CJ003551 AT FAULT. THE UNIT WAS REPLACED IAW AMM 24-34-21 AND TESTED SERVICEABLE. PREVIOUS HISTORY: ON 03 MAY 06 THE UNIT WAS SENT OUT ON REPAIR ORDER 64509 TO GET ALERT SB 737-24-1165 CARRIED OUT. THIS MODIFIES THE UNIT FROM A S282T004-10 TO A 1-002-0102-2090. THIS SERVICE BULLETIN GIVES INSTRUCTIONS TO REPLACE THE STATIC INVERTER WITH A NEW OR CHANGED STATIC INVERTER. BOEING AND FEDERAL AVIATION ADMINISTRATION (FAA) RECEIVED 2L72 4F4 FRTA16WE E00055EN 20060627003092006062700309CE 2006 6 27 CA060620004 120060615G27506901315 CONTROL LEVER LEAR 45 45LEAR 5170805CE GARRTTTFE731TFE7312 01518WP TE FLAPS FAILED W O OTHER F FLT CONT AFFECTED APAPPROACH 1 CA 102 ON APPROACH INTO TUCSON WHEN FLAP WAS SELECTED TO 8 DEGREE "FLAP FAILED " AMBER CAS ILLUMINATED. AIRCRAFT LANDED UNEVENTFULLY AND LEARJET INC, TUCSON REPLACED THE FLAP CONTROL LEVER ASS'Y AND RETURNED THE AIRCRAFT INTO SERVICE. 2L72 4F4 FRTT00008WIE6WE 20060628001982006062800198CE 2006 6 28 CA060620005 120060618G2750 FLAP SYSTEM LEAR 45 45LEAR 5170805CE GARRTTTFE731TFE731* 01518WP TE FLAPS MALFUNCTIONED W O OTHER F FLT CONT AFFECTED DEDESCENT 1 CA DURING DESCENT FROM 41,000 FT, AT -54 DEGREES TO 26,000 FT WITH NO FLAP SELECTION. "FLAP FAILED" AMBER CAS MESSAGE ILLUMINATED. AT 5000 FT, THE CREW WAS ABLE TO RESET THE FLAP SYSTEM AND AN UNEVENTFUL LANDING WAS MADE. TECHNICIAN FROM LEARJET INC WAS DISPATCHED TO INSPECT AND RETURN THE AIRCRAFT TO SERVICE, AFTER WHICH THE AIRCRAFT FOR FURTHER TROUBLESHOOTING. 2L72 4F4 FRTT00008WIE6WE 20060628001992006062800199CE 2006 6 28 CA060620006 120060620G801151577A1 SOLENOID CESSNA207 207A 2073604CE CONT O520 IO520F 17032SO HARTZLHCC3Y HCC3YF1 GL STARTER STUCK W O OTHER H ELECT. POWER LOSS-50 PC APAPPROACH 1 CA 11455 UPON DESCENT TO LAND FROM A .4 HRS FLIGHT, THE ELECTRICAL POWER WENT OUT AND WAS UNABLE TO BE RESET BY CYCLING THE MASTER SWITCH. THE PILOT C/O NORDO PROCEDURES AND LANDED WITHOUT INCIDENT. UPON INVESTIGATION IT WAS FOUND THAT THE START SOLENOID HAD REMAINED CLOSED UPON START UP CAUSING THE MASTER SOLENOID TO OVERHEAT AND FAIL CAUSING ELECTRICAL POWER TO GO OUT. THE START SOLENOID AND MASTER SOLENOID WERE REPLACED NEW. ALL WIRING WAS INSPECTED AND FOUND TO BE GOOD. AS A PRECAUTIONARY MEASURE THE STARTER AND STARTER DRIVE WERE REPLACED. THE A/C WAS GROUND RUN AND SYSTEMS CHECKED SERVICEABLE. 1H71 3O3 O A16CE E5CE 5 CP25EA 20060628002002006062800200NE 2006 6 28 CA060621001 220060615G7200 ENGINE SKRSKYS64 S64E 8142604NE PWA JFTD12JFTD12A4A 52047NE FAILED W E ENGINE SHUTDOWN R PARTIAL RPM/PWR LOSS HOHOVERING 1 CA A/C INVOLVED IN HELI-LOGGING OPS WITH A/C IN HOVER MADE A MODERATE PWR REDUCTION TO REPOSITION GRAPPLE ON A LOG. AS PWR WAS REDUCED A "WHOOSH" SOUND WAS HEARD AND N1 WARNING HORN ACTIVATED FOR NR 2 ENG. FLT CREW IDENTIFIED AND CONFIRMED THAT NR 2 ENG ENCOUNTERING A ROLL-BACK AND PROCEEDED TO SHUT ENG DOWN TO COUNTER RISING ENG T5 TEMP. WITH ENG SECURED AND NR T5 TEMP LIMITS EXCEEDED FLT CREW ELECTED TO RESTART NR 2 ENG SINCE A/C HAD 15 KILOMETER FERRY FLT BACK TO ITS SERV LANDING. ENG WAS SUCCESSFULLY RESTARTED AND A/C RETURNED TO SERV LANDING W/O FURTHER INCIDENT. A COMPLETE INSPECTION OF ENG AND RELATED LINKAGES REVEALED NOTHING ABNORM. ENG FUEL FILTER WAS INSPECTED FOR CONTAM WITH NO FAULT FOUND. AS STA2G72 4U4 U H4EA E15EA 20060803002722006080300272SO 2006 8 3 CA060621002 120060610G32337LM1025013 ACTUATOR GRUMANG73 G73T 3951902SO LYC O320 O320D1D 41508EA MLG WORN W O OTHER O OTHER NRNOT REPORTED 1 CA 12308 (CAN) ON THE LT MAIN LANDING GEAR ACTUATOR, THE DOWN LOCK PISTON PIN CIRLIP HAS A LID OVER ITS GROOVE LEAVING THE ACTUATOR UNLOCKED WHEN THE GEAR IS DOWN. ALSO, BECAUSE THE PISTON PIN HAS EXCEEDED ITS LIMIT, THE SWITCH HAS BEEN DAMAGE LEAVING THE LT INDICATING GREEN LIGHT UNILLUMINATED. THE AIRCRAFT LANDED WITH NO OTHER INCIDENT. AFTER INVESTIGATION: THE SIDE GROVE RETAINING THE CIRCLIP HAS BEEN FOUND WORN, THE ACTUATOR BODY HAS BEEN REPLACED. (TC# 20060621002) 1H72 3R3 O A783 E274 20060628002022006062800202EA 2006 6 28 CA060621003 220060620G8530CL41CCST041CA CYLINDER HEAD CESSNA172 172K 2072430CE LYC O320 O320E2D 41508EA MCAULY1A175 1A175ATM GL ENGINE CRACKED W C ABORTED TAKEOFF ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS TOTAKEOFF 1 CA 1023 L2430227A ENGINE RUNNING ROUGH FOUND NR 1 CYLINDER HEAD CRACKED. 1H71 3O3 ONT3A12 E274 5 NP857 20060804000192006080400019NM 2006 8 4 CA060621004 120060619G27519660022001 TRANSMITTER BOEING727 727227 1384078NM PWA JT8 JT8D9A 52048NE TE FLAPS MALFUNCTIONED W A UNSCHED LANDING N FALSE WARNING CLCLIMB 1 CA (CAN) AFTER DEPARTURE, CREW OBSERVED AN OUTBOARD FLAP ASYMMETRY INDICATION. A/C RETURNED TO BASE WHERE MAINTENANCE DISCOVERED A FAULTY POSITION TRANSMITTER. PART WAS REPLACED AND A/C RETURNED TO SERVICE. 2L73 4F4 F A3WE E2EA 20070516001612007051600161EA 2007 5 16 CA060621005 220060620G732286245023 FLANGE PIPER PA44 PA44180 7104402SO LYC O360 O360A1H 41514EA HARTZLHCC2Y HCC2YR2 GL CARB MOUNT CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 1120 (CAN) DURING ROUTINE INSPECTION OF RT ENGINE A .5 INCH CRACK WAS OBSERVED ALONG A SCRIBE LINE ON THE FORWARD FACE OF THE CARB AIR BOX NEAR TO THE LOWER MOUNTING BOLT HOLE . AFTER REMOVAL, (2) ADDITIONAL CRACKS WERE OBSERVED ALONG A SCRIBE MARK NEAR TO THE UPPER MOUNTING HOLES. THESE CRACKS TRAVERSED NEARLY COMPLETELY ACROSS THE MOUNTING FLANGE FACE. IN ADDITION THE MOUNTING HOLE ALIGNMENT BETWEEN THE MOUNTING FLANGE AND THE INNER DOUBLER WERE OFFSET BY APPROXIMATELY .0312 INCH. THIS MAY HAVE INDUCED STRESS THAT LED TO CRACK FORMATION ALONG THESE SCRIBE MARKS. BEFORE A NEW ASSEMBLY WAS INSTALLED THE MOUNTING HOLES WERE REAMED TO ALIGN THE HOLES IN BOTH PLATES. (TC NR 20060621005) 1L72 3O3 O A19S0 E286 5 CP920 20060628002032006062800203EU 2006 6 28 CA060621006 120060621G73349550179130 PRESSURE SWITCH SNIAS 350 AS350B3 8680954EU TMECA ARRIELARRIEL2B NE FUEL LOW LEAKING W E ENGINE SHUTDOWN K FLUID LOSS TXTAXI/GRND HDL 1 CA DURING A START, PILOT NOTICED A FUEL PRESSURE WARNING LIGHT NOT EXTINGUISHING. CONTINUED WITH THE START THROUGH TO IDLE. THEN SHUT THE AIRCRAFT DOWN AFTER 10 SECONDS AT IDLE. AFTER SHUT DOWN OPENED UP THE ENGINE COWLING AND NOTICED FUEL ON THE ENGINE DECK. FUEL WAS COMING FROM THE WEEP HOLE OF THE PRESSURE SWITCH WITH AIRCRAFT BOOST PUMP ON. 1G71 3U3 U H9EU E00054EN 20060703000052006070300005EA 2006 7 3 CA060622001 220060621G7313LW18853 NOZZLE PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA HARTZLHCE3Y HCE3YR2 GL ENGINE CONTAMINATED W A UNSCHED LANDING BJ SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION CLCLIMB 1 CA 592 L785461A TOWER ADVISED PILOT OF SMOKE FROM LEFT ENGINE ON CLIMB-OUT. MAINTENANCE FOUND CONTAMINATION IN 1 OF THE FUEL INJECTION NOZZLES. SOURCE COULD NOT BE DETERMINED. 1L72 3O3 O A20SO E14EA 5 CP33EA 20060804000212006080400021CE 2006 8 4 CA060622002 120060620G2810CCA1550 DRAIN BEECH 99 99 1154002CE PWA PT6 PT6A28 EA FUEL SYS BROKEN W O OTHER K FLUID LOSS ININSP/MAINT 1 CA (CAN) AFTER FUELING THE AIRCRAFT THE FIRST OFFICER HEARD A SPLASH AND FOUND FUEL LEAKING FROM UNDER THE LEFT WING. THE T PORTION OF THE FUEL DRAIN HAD FALLEN OUT AND THERE WAS NO WAY TO SHUT THE QUICK DRAIN VALVE OFF. THE TOP PART OF THE VALVE AND ORING WERE RECOVERED WHEN THE DRAIN VALVE WAS REPLACED. (TC# 20060622002) 1L72 3T4 T A14CE E4EA 20060804000232006080400023SW 2006 8 4 CA060622003 120060621G5302206031418001 SUPPORT BELL 206 206B 1181511SW TAIL BOOM CORRODED W K NONE O OTHER ININSP/MAINT 1 CA 6856 (CAN) FIN ATTACH POINTS WERE BEING INSPECTED AS PER ASB 206-06-107, CF2006-12. A LARGE CORROSION PIT WAS FOUND ON THE BOTTOM BOLT HOLE. THE SUPPORT INSTALLATION IS TO BE REPLACED AS PER THE ASB WITH A ONE-PIECE CASTING. (TC# 20060622003) 1G71 3U H2SW 20060804000242006080400024WP 2006 8 4 CA060622004 120060622G7720A0582 SWITCH ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE OVERTEMP STUCK W O OTHER N FALSE WARNING CRCRUISE 1 CA 21 (CAN) MAIN ROTOR TRANSMISSION OVER TEMP LIGHT CAME ON. PILOT LANDED AND LET THE AIRCRAFT COOL DOWN. LIGHT STAYED ON. TRANSMISSION WAS INSPECTED FOR SIGNS OF OVER TEMP, AND NO DEFECTS WERE FOUND. OVERTEMP SWITCH WAS FOUND TO BE STUCK IN THE CLOSED POSTION. (TC# 20060622004) 1G71 3O3 O H11NM 1E4 20060804000252006080400025SW 2006 8 4 CA060622005 120060621G2497206075265103 CABLE BELL 205 205A1 1181414SW LYC T53 T5313B 41549NE STARTER GEN MELTED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING TURN AROUND CHECK BY THE AME, THE WIRES TO THE STARTER GENERATOR WERE FOUND TO BE SUBJECTED TO HEAT DAMAGE. THERE WAS NO INDICATION TO THE PILOT OF ANY DEFECT. FURTHER INVESTIGATION FOUND THE STARTER GENERATOR WIRE BUNDLE BELOW THE ENGINE DECK TO BE BURNT. CAUSE OF THE DEFECT IS NOT KNOWN AT THIS TIME. 1G71 4U4 U H1SW E17EA 20060804000262006080400026SO 2006 8 4 CA060623001 120060620G27521216001 DRIVE ASSY PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA FLAP XMSN SHEARED W D RETURN TO BLOCK O OTHER TXTAXI/GRND HDL 1 CA 3105 (CAN) DURING PRE-DEPARTURE CHECK PILOTS NOTED THAT THE RH FLAP WAS NOT RESPONDING TO DOWN SELECTION, LH FLAP MOVEMENT WAS NORMAL. MAINTENANCE CONFIRMED THE SNAG AND T/S REVEALED THE RH FLAP TRANSMISSION WAS NOT DRIVING THE FLAP, FLAP MOTOR AND DRIVE CABLES WERE CHECKED SERVICEABLE. REPLACED RH FLAP TRANSMISSION,FLAPS RIGGED PER PIPER MM AND AIRCRAFT DISPATCHED. 1L72 3O3 O A20SO E14EA 20060804000282006080400028CE 2006 8 4 CA060623002 120060619G55401015000573 FASTENER BEECH BEECH 1900 1900C 1154161CE PWA PT6 PT6A65B 52043EA RUDDER SHAFT LOOSE W K NONE O OTHER ININSP/MAINT 1 CA UB71 (CAN) RUDDER QUADRANT P/N 101-500057-3 FOUND LOOSE ON INSPECTION. THREE MONEL BLIND RIVETS ATTACHING QUADRANT TO SHAFT ASSY. P/N 114-524025-1 WERE FOUND LOOSE AND DETERMINED TO BE THE CAUSE OF THE QUADRANT LOOSNESS. (TC# 20060623002) 2L72 4T4 TRTA24CE E4EA 20060804000292006080400029WP 2006 8 4 CA060623003 120060528G6730D2121 SERVO ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE HYDRAULIC SYS LEAKING W K NONE O OTHER ININSP/MAINT 1 CA 1570 (CAN) UPON INSPECTION THE AFT SERVO WAS FOUND TO BE LEAKING FROM THE PILOT VALVE. SERVO REPLACED WITH A SERVICEABLE UNIT. (TC# 20060623003) 1G71 3O3 O H11NM 1E4 20061213001342006121300134CE 2006 12 13 CA060624001 120060615G2711130909B20 BOLT BEECH BEECH 95 95B55 1152729CE CONT O470 IO470L 17026SO HARTZLHCC3Y HCC3YF2 GL AILERON LOOSE W K NONE O OTHER ININSP/MAINT 1 CA 2554 2554 (CAN) AILERON TRIM BOLT FOUND MIGRATING OUT OF LINKAGE ARM ON LT AILERON TRIM TAB ASSEMBLY. BOLT WAS NOTED TO BE FINGER-TIGHT ONLY AND NOT SET INTO LOCKING DEVICE. NOTE: BOLT WAS FOUND IN THIS CONDITION AFTER FLIGHT CONTROLS WERE INSTALLED AFTER AIRCRAFT WAS PAINTED BY A THIRD PARTY CONTRACTOR. AS BOLT WAS BEING TIGHTENED DURING RECERTIFICATION, RESISTANCE WAS NOTED ENSURING THE LOCKING PROVISIONS WERE SERVICEABLE.COMPANY PROCEDURES ON AIRCRAFT ACCEPTANCE AFTER THIRD PARTY CONTRACT MAINTENANCE TO BE REVISED TO PREVENT RE-OCCURENCE (TC NR 20060624001) 1L72 3O3 ORT3A16 3E1 5 CP25EA 20060804000312006080400031NM 2006 8 4 CA060626001 120060621G571266191042 RIB BOEING727 727225 1384077NM WING CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING SCHEDULED INSPECTON, MAINTENANCE FOUND THE NR 1 LEADING EDGE SLAT ACTUATOR WING RIB ATTACH POINT CRACKED. CRACKED MOUNT SUPPORT REPLACED. 2L73 4F A3WE 20060804000332006080400033NE 2006 8 4 CA060626002 220060620G7414SB9RU3 MAGNETO BEECH 18 D18S 1151004CE PWA R985 R985AN14B 52008NE ENGINE FAILED W A UNSCHED LANDING E VIBRATION/BUFFET CRCRUISE 1 CA 36 (CAN) INTERNAL FAILURE OF MAGNETO - VISUAL DAMAGE TO GEAR. THIS IS THE SECOND MAGNETO TO FAIL ON THIS OVERHAULED ENGINE (PURCHASED FROM TULSA AERO ENGINE). FIRST MAGNETO FAILED AT 30.3 HOURS FROM TSO. SECOND MAGNETO FAILED AT 36.2 HOURS TSO. S/N ON 1ST MAGNETO IS B33715. BOTH MAGNETOS APPEAR TO HAVE THE SAME INTERNAL PRT FAILURE. (TC# 20060626002) 1L72 3R3 R A765 5E1 20060804000382006080400038 2006 8 4 CA060626004 420060622G61224V1827 GOVERNOR CNDAIRCL215 CL2151A10 1900320EA PROPELLER OVERSPEED W E ENGINE SHUTDOWN F FLT CONT AFFECTED CLCLIMB 1 CA 266 (CAN) AFTER WATER SCOOP, THE LEFT PROP WENT TO OVERSPEED, PROP WAS CONTROLABLE WITH THROTTLE AND POWER LEVER AT 2800 RPM. ENGINE WAS SHUT DOWN AND SECURED. THE A/C RETURNED FOR MAINTENANCE. THE PROP GOVERNOR WAS REPLACED AND THE A/C RETURNED TO SERVICE. 2H72 4R RTA14EA 20060804000422006080400042NE 2006 8 4 CA060626005 320060622G6114 SEAL BAG JETSTMJETSTM3212 1500217EU MCAULY4HFR344HFR34C652 NE RT PROP LEAKING W O OTHER KJ FLUID LOSS WARNING INDICATION TXTAXI/GRND HDL 1 CA 5209 1462 881759 (CAN) DURING THE WALK AROUND, THE PILOTS NOTICED OIL DRIPPING DOWN ONE BLADE OF THE RT PROPELLER. MAINTENANCE WAS NOTIFIED AND THE AME WAS DISPATCHED TO ASSESS. IT WAS DETERMINED THAT A BLADE SEAL HAD FAILED. THE PROPELLER WAS REMOVED FROM THE AIRCRAFT AND SENT TO WESTERN PROPELLER IN EDMONTON FOR REPAIRS. A VERBAL REPORT INDICATED THAT THERE WAS NO DAMAGE OR OBVIOUS CAUSE. ALL SEALS WERE REPLACED. THE PROPELLER WAS RE-INSTALLED AND RETURNED TO BASE THE FOLLOWING DAY. 2L72 4T RTBA15CAA 6 C3PNE 20060804000442006080400044EA 2006 8 4 CA060626006 120060622G21301305221 SELECTOR PANEL DHAV DHC8 DHC8311 1386006EA PWA PW120 PW123 NE HAMSTD14SF 14SF15 NE CABIN PRESSURE UNKNOWN W B EMER. DESCENT J WARNING INDICATION CRCRUISE 1 CA 2374223742 (CAN) DURING FLIGHT CABIN PRESSURE WARNING LIGHT ILLUMINATED AT FLT LVL 230, F/A REPORTED MAIN CABIN DOOR SEAL LEAKING. AIRCRAFT COMMENCED RAPID DECENT AT 3000`/MIN . AFTER NORMAL LANDING AT DESTINATION , AIRCRAFT DEPARTED UNDER MEL FOR UNPRESSURIZED FLIGHT. AFTER ARRIVAL AT MAINTENANCE BASE, MAINTENANCE INSPECTED MAIN CABIN DOOR SEAL AND FOUND SERVICEABLE. CABIN PRESSURE SELECTOR PANEL REPLACED, AIRCRAFT GROUND RUN AND ABLE TO OBTAIN AND MAINTAIN MAXIMUM DIFFERENTIAL. AIRCRAFT RETURNED TO SERVICE. AIRCRAFT HAD PREVIOUS HISTORY OF PRESSURIZATION ISSUES IN AUTO MODE, CABIN PRESSURE COMPUTER PREVIOUSLY REPLACED, (TC# 20060626006) 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20060804000482006080400048EA 2006 8 4 CA060627001 220060623G7250310427801 SNAP RING BEECH 90 C90 1152913CE PWA PT6 PT6A21 52043EA ENGINE BEARING MISSING W K NONE O OTHER ININSP/MAINT 1 CA 2998 PCE24983 (CAN) WHILE TURNING PROPELLER DURING MAINTENANCE, A METAL-ON-METAL GRINDING NOISE WAS COMING FROM INSIDE L/H ENGINE EXHAUST DUCT. MAINTENANCE REACHED IN THRU EXHAUST STACK OPENING AND TAPPED EXHAUST DUCT "SKI SLOPE" AREA AND HEARD A RATTLE SOUND. ENGINE SPLIT, PT DISC REMOVED AND FOUND BEARING COVER SNAP RING MISSING. THE ENGINE HAS SB1389 COMPLIED WITH AT LAST ENGINE O/H. THIS SB CUTS SLOTS TO KEEP BEARING COVER FROM ROTATING. THE SLOTS IN THE PT SHAFT HOUSING WERE FOUND WORN, WHICH ALLOWS BEARING COVER TO SHIFT CAUSING WEAR IN SNAP RING WHICH RETAINS COVER. OVER THE PERIOD OF ENGINE OPERATION FROM O/H `TILL NOW WE SUSPECT THIS HAS CAUSED THE FAILURE OF THE SNAP RING. THIS IN TURN ALLOWED THE BEARING COVER TO 1L72 3T4 T 3A20 E4EA 20060804000492006080400049GL 2006 8 4 CA060627002 220060618G726123070328 OIL TANK EMB 145 EMB145ER 3260211SO ALLSN AE300 AE3007A GL ENGINE RUPTURED W EFB ENGINE SHUTDOWN ACTIVATE FIRE EXT. EMER. DESCENT KYAFLUID LOSS ENGINE STOPPAGE FLAME/FIRE CRCRUISE 1 CA 7913 CAE312063 (CAN) A/C N14930/145011, ENGINE NR 2 S/N CAE312063 SUFFERED A COMMANDED IN-FLIGHT SHUTDOWN (CIFSD) DUE TO AN OIL TANK RUPTURE THAT LED TO OIL LEAKAGE AND SUBSEQUENT FIRE. THE ENGINE WAS SHUT DOWN BY THE CREW AFTER LAV SMOKE, ENGINE FIRE, LOW OIL QUANTITY AND HIGH OIL TEMPERATURE INDICATIONS WERE OBSERVED ENROUTE FROM CRP TO IAH. THE AIRCRAFT DIVERTED TO VCT SAFELY W/O INCIDENT WHERE THE ENGINE IS BEING REMOVED. METAL DEBRIS WAS FOUND IN THE EXPOSED OIL TANK THAT APPEARS TO BE FROM INTERNAL WEAR. ENGINE IS PRESENTLY AT ROLLS-ROYCE CANADA UNDER INVESTIGATION. 2L72 4F4 FRTT00011ATTE6CH 20060804000502006080400050SW 2006 8 4 CA060627003 120060625G6220214030606005 SPINDLE BELL 214 214B1 1182105SW LYC T55 T5508D 41555NE M/R GEARBOX BROKEN W B EMER. DESCENT J WARNING INDICATION HOHOVERING 1 CA 694 AME28043 (CAN) TRANSMISSION SPINDLE ASSY P/N 214-040-606-005 S/N A12-01304 BROKE IN HALF DURRING FLIGHT, AND THE PILOT HEARD A LOUD BANG AND BEGAN A EMERGENCY LANDING. APON SUCSESSFULL LANDING THE ENGINEER FOUND THE SPINDLE CRACKED IN HALF. DURRING THE SHORT TIME IN THE AIR FOR LANDING THE MAIN DRIVESHAFT OVERTEMPED, ONE OF THE TAIL ROTOR DRIVESHAFTS SCRAPED HALF THE WAY THROUGH, AND THE FORWARD DRIVESHAFT COUPLING WAS REMOVED FOR INSPECTION. NEW SPINDLES, LEFT AND RIGHT, AND DRIVESHAFTS WERE INSTALLED AND AIRCRAFT WAS RETURNED TO SERVICE. THIS IS THE SECOND SPINDLE FALURE WE HAVE HAD THIS MONTH. THE TWO SPINDLES HAVE BEEN REQUESTED TO BE SENT TO BELL IN TEXAS BY BELL HELICOPTER AND WILL BE SENT OUT THIS WEEK. (TC# 2002G71 4U4 U H6SW E4NE 20060804000512006080400051WP 2006 8 4 CA060627004 220060627G726031035851 BEARING SWRNGNSA226 SA226TC 8780404SW GARRTTTPE331TPE33110UA 01514WP TORQUE SENSOR FAILED W EA ENGINE SHUTDOWN UNSCHED LANDING R PARTIAL RPM/PWR LOSS CLCLIMB 1 CA 964 P54156 (CAN) THE FRONT SCAVENGE PUMP DRIVE GEAR SHAFT SHEARED IN THE SCAVENGE PUMP, DUE TO THE SCAVENGE PUMP BUSHING THAT SEIZED FROM OIL STARVATION AND METAL CONTAMINATION CAUSED BY THE TORQUE SENSOR BEARING. THE OIL PRESSURE PUMP SHAFT AND BUSHING ALSO HAVE WEAR ON THEM DUE TO OIL STARVATION. THE TORQUE SENSOR BEARING PART NUMBER 3103585-1 FAILED JAMMING UP THE GEAR CAUSING THE BEARING OUTER RETAINER TO HAVE EXCESSIVE WEAR ON IT. THE INNER AND OUTER BEARING RACES AND BALLS HAVE WEAR DAMAGE ON THEM ALSO DUE TO THE FAILED BEARING. 2L72 4T4 TRTA8SW E4WE 20081229 CE 2008 12 29 CA060627005 120060624G2701 ROLLER CESSNA172 172S 2072439CE LYC IO360 IO360L2A EA MCAULY1A170 1A170E GL CONTROL YOKE DISLODGED W O OTHER F FLT CONT AFFECTED TXTAXI/GRND HDL 1 CA (CAN) CO-PILOTS CONTROL YOKE GUIDE ROLLER ASSY FELL OUT AND ON INVESTIGATION WAS FOUND THAT WRONG SIZE BOLT WAS INSTALLED. FURTHER INVESTIGATION OF THE REST OF THE FLEET IT WAS FOUND THAT 2 OTHER ACFT HAD THE WRONG BOLT PN AND SIZE INSTALLED. CORRECT BOLT INSTALLED AND ACFT RETURNED TO SERVICE. 1H71 3O3 ONT3A12 1E10 5 NP857 20060804000602006080400060EA 2006 8 4 CA060627006 120060625G52442153300688 DOOR CNDAIRCL215 CL2151A10 1900320EA LT ACCESSORY SEPARATED W O OTHER ED VIBRATION/BUFFET INFLIGHT SEPARATION NRNOT REPORTED 1 CA 4124 (CAN) AIRCRAFT WAS COMPLETING A SCOOPING RUN WHEN THE LT HAND DOOR ASSEMBLY PN 215-33006-882 OPENED AND DEPARTED THE AIRCRAFT. CREW WERE ABLE TO LIFT AIRCRAFT OFF WATER AND RETURNED TO BASE WITHOUT FURTHER INCIDENT. INVESTIGATION TO FOLLOW TO DETERMINE THE CAUSE OF DOOR OPENING. 2H72 4R RTA14EA 20060804000622006080400062EA 2006 8 4 CA060628001 220060411G7414M3008 GEAR SLICK ZLIN 242 Z242L 9970204EU LYC O360 AEIO360A1B6 41514EA DISTRIBUTER UNSERVICEABLE W D RETURN TO BLOCK E VIBRATION/BUFFET TXTAXI/GRND HDL 1 CA 1185 04040517 (CAN) DURING POST REMOVAL TEARDOWN INSPECTION OF MAGNETO ELECTRODE FINGER FOUND BROKEN OFF OF THE DISTRIBUTER GEAR. 1L71 3O3 O0 A76EU 1E10 20060804000632006080400063WP 2006 8 4 CA060628002 120060621G7810D3171 HEAT SHIELD ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE EXHAUST CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 140 (CAN) DURING A ROUTINE 50 HR ENGINE INSPECTION, IT WAS NOTED THAT THE SUBJECT HEAT SHIELD, THAT IS INSTALLED ON THE EXHAUST TAILPIPE, WAS FOUND CRACKED. THE CRACK ORIGINATED IN A DOUBLER AREA WHERE THE FORWARD CLAMP IS ATTACHED. THE CRACK LOOKS AS THOUGH IT STARTED FROM A RIVET WHICH ATTACHES THE DOUBLER AND BRACKET, WHICH PROVIDES A MEANS TO ATTACH THE CLAMP TO THE EXHAUST TAIL PIPE. THE PART IN QUESTION HAS 140.3 HRS TIME SINCE NEW. THE AIRCRAFT IN QUESTION HAS 343.5 HOURS SINCE NEW. THE PART HAS BEEN SUBMITTED TO ROBINSON HELICOPTER FOR WARRANTY. (TC# 20060628002) 1G71 3O3 O H11NM 1E4 20060804000662006080400066WP 2006 8 4 CA060628003 120060621G7810C1695 COLLECTOR RING ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE EXHAUST BENT W K NONE O OTHER ININSP/MAINT 1 CA 344 (CAN) DURING A ROUTINE 50 HOUR ENGINE INSPECTION, IT WAS NOTED THAT THE L/H EXHAUST COLLECTOR WAS BENT AT THE AFT DOWNPIPE CREASE AREA. DURING FURTHER INVESTIGATION, IT WAS NOTED THAT A CRACK HAD FORMED IN THE SUBJECT AREA. DURING REMOVAL OF THE SUBJECT PART, IT WAS ALSO NOTED THAT THE OUTLET FLANGE THAT FITS INTO THE MUFFLER, WAS DEFORMED AND CRACKED AS WELL. THE SUBJECT PART HAS NOT BEEN REMOVED OR ALTERED SINCE NEW. THE PART HAS BEEN RETURNED TO MANUFACTURER FOR WARRANTY. CONSIDERATION IS BEING MADE THAT THE PART MAY HAVE BEEN PUT IN A STRESSFUL CONDITION WHEN INSTALLED AT THE FACTORY. THE AIRCRAFT HAS 343.5 HOURS SINCE NEW. 1G71 3O3 O H11NM 1E4 20060804000672006080400067EU 2006 8 4 CA060628004 120060628G3320BVO320204114 SOCKET AEROSPATR42 ATR42300 8680920EU PWA 120 PW120 NE HAMSTD14SF 14SF5 NE RT WINDOW LIGHT OVERHEATED W O OTHER B SMOKE/FUMES/ODORS/SPARKS NRNOT REPORTED 1 CA (CAN) LAMP SOCKET P/N BVO3202-04-114 OVERHEATED AND SMOKE SMELL NOTED AT R/H CABIN SIDE WINDOW LIGHT. LAMP SOCKET REPLACED. TESTED SERVICEABLE. (TC# 20060628004) 2H72 4T4 TRTA53EU E20NE 6 CP7NE 20060804000702006080400070NE 2006 8 4 CA060628007 220060608G8530282992 COVER BEECH 18 D18S 1151004CE PWA R985 R985AN14B 52008NE PUSHRODS CORRODED W K NONE O OTHER ININSP/MAINT 1 CA 512 210872 (CAN) DURING ENGINE DIS-ASSEMBLY FOR CYLINDER REPAIRS, THE PUSHROD COVERS (TUBES) WERE FOUND TO BE HEAVILY DAMAGED UNDER THE CONTACT AREA OF THE SEAL PACKINGS. THESE PUSHROD COVERS HAD BEEN CHROME PLATED AT THE PREVIOUS OVERHAUL, AND THIS CHROME WAS FOUND TO HAVE BONDED TO THE PACKINGS AND HAD LIFTED AWAY FROM THE PARENT MATERIAL, CAUSING A SERIOUS POTENTIAL LEAK PATH AND/OR BREAKAGE POINT. I AM NOT AWARE OF ANY APPROVED PROCESS TO CHROME THESE TUBES. ALL TUBES WERE REPLACED WITH NEW. (TC# 20060628007) 1L72 3R3 R A765 5E1 20060804000722006080400072EU 2006 8 4 CA060629001 120060626G3260 UPLOCK AEROSPATR42 ATR42300 8680920EU PWA 120 PW120 NE HAMSTD14SF 14SF5 NE MLG FAILED W A UNSCHED LANDING N FALSE WARNING CLCLIMB 1 CA 2781 (CAN) WHEN THE CREW SELECTED GEAR UP ALL POSITIONS FAILED TO SHOW UP AND LOCKED. THE CREW RETURNED TO POINT OF DEPARTURE AND LANDED WITHOUT INCIDENT. MAINTENANCE REPLACED THE RIGHT HAND MAIN LANDING GEAR UPLOCK BOX ASSY. AND THE WEIGHT ON WHEELS UPPER WIRING HARNESS. THE LANDING GEAR WAS FUNCTION CHECKED AND THE AIRCRAFT RETURNED TO SERVICE. (TC# 20060629001) 2H72 4T4 TRTA53EU E20NE 6 CP7NE 20060804000752006080400075EU 2006 8 4 CA060629002 120060619G3297 CONTACT AEROSPATR42 ATR42300 8680920EU PWA 120 PW120 NE HAMSTD14SF 14SF5 NE MLG FOULED W A UNSCHED LANDING N FALSE WARNING CLCLIMB 1 CA 27455 (CAN) DEPARTING THE LANDING GEAR LEVER WOULD SELECT TO THE UP POSITION. THE AIRCRAFT REURNED TO POINT OF DEPARTURE AND LANDED WITHOUT FURTHER INCIDENT. MAINTENANCE DETERMINED THE GROUND CONTACT FOR THE GEAR LEVER LOCKOUT SOLENOID WAS FOULED. THE CONTACT WAS CLEANED AND A FUNCTION CHECKED PERFORMED PRIOR TO THE AIRCRAFT BEING RETURNED TO SERVICE. 2H72 4T4 TRTA53EU E20NE 6 CP7NE 20060804000782006080400078CE 2006 8 4 CA060629003 120060628G361024538400 FLANGE CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE TUBE DEBONDED W K NONE O OTHER ININSP/MAINT 1 CA 7216 (CAN) WELDED TUBE ASSEMBLY REMOVED FROM AIRCRAFT TO GAIN ACCESS FOR INSPECTION. WELDED TUBE ASSEMBLY INSPECTED - FLANGE ATTACHED APPEARED TO BE BONDED TO TUBE. UPON INSTALLATION ON AIRCRAFT - WHEN CLAMP ATTACHING WELDED TUBE ASSEMBLY TO CABIN VENTILATION JUNCTION BOX WAS TORQUED. THE WELDED TUBE ASSY WAS FREE TO PULL OUT OF FLANGE. INSERTED WELDED TUBE ASSY BACK INTO FLANGE AND RELEASE THE CLAMP. FOUND FLANGE HAD A TIGHT METAL TO METAL FIT. ABLE TO PULL OFF FLANGE WITH SOME FORCE. FLANGE IS BONDED TO WELDED TUBE ASSEMBLY WITH ADHESIVE. 1L72 4F4 F A22CE E1NE 20060804000802006080400080CE 2006 8 4 CA060629004 120060629G531012139881 DOOR FRAME CESSNA206 U206G 2073356CE CONT O550 IO550F 17042SO MCAULYD3A34 D3A34C402 GL FUSELAGE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 5952 (CAN) FORWARD DOOR POST BULKHEAD CRACK DETECTED DURING ACCOMPLISHMENT OF SEB 93-5 CESSNA SERVICE KIT SK206-42 LOWER FORWARD DOORPOST BULKHEAD AND WING STRUT FITTING REINFORCEMENT TO BE INSTALLED. (TC# 20060629004) 1H71 3O3 O A4CE E3SO 5 CP47GL 20060804000822006080400082NE 2006 8 4 CA060629005 220060628G8530356996 CYLINDER DOUG DC6 DC6B 3021712WP PWA R2800 CB3 52026NE HAMSTD43E 43E60 NE ENGINE CRACKED W E ENGINE SHUTDOWN J WARNING INDICATION CRCRUISE 1 CA 808 NK510094 (CAN) DURING CRUISE, NR 1 ENGINE BMEP INDICATION WAS FLUCTUATING, AIRCRAFT HAD A SLIGHT YAW. THE RETARDANT LOAD WAS JETTISONED AND THE ENGINE WAS SHUT DOWN AND PROP FEATHERED. THE AIRCRAFT RETURNED TO BASE. UPON INVESTIGATION NR 15 CYLINDER EAR WAS FOUND CRACKED. THE CYLINDER WAS REPLACED, ENGINE WAS GROUND RUN AND LEAK CHECKED AND THE AIRCRAFT WAS RETURNED TO SERVICE. 2L74 4R4 R 6A4 E264 6 CP871 20061018000752006101800075EU 2006 10 18 CA060629006 120060627G6320DHS43911142 RETAINING NUT UROCOP SNIAS 350 AS350BA 8680817EU TMECA ARRIELARRIEL1B 6OO30NE M/R GEARBOX BROKEN W A UNSCHED LANDING E VIBRATION/BUFFET APAPPROACH 1 CA 1392 M149 (CAN) RETAINING NUT FOR THE INPUT FLANGE ON THE TRANSMISSION (MAIN GEARBOX) BROKE IN 2 PIECES CAUSING THE SPLINED ADAPTER TO BACK OFF, WHICH CAUSED THE HYDRAULIC BELT TO RUN ON THE EDGE OF THE PULLEY. (TC NR 20060629006) 1G71 3U3 UNCH9EU E19EU 20060804000842006080400084CE 2006 8 4 CA060629007 120060620G213310138001313 OUTFLOW VALVE BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA CABIN PRESSURE FAILED W K NONE O OTHER ININSP/MAINT 1 CA 16 BB170 (CAN) THE AIRCRAFT EXPERIENCED A LEAK DOWN OF CABIN PRESSURE. THE TROUBLE WAS TRACED TO THE FLOW CONTROL PACK UNITS. BOTH CONTROL UNITS WERE REPLACED WITH OVERHAULED UNITS. THE UNITS THAT WERE INSTALLED NEVER PROVIDED ENOUGH FLOW FOR PRESURIZATION, HEATING AND COOLING. WHEN THE OVERHAULER OF THE UNITS WAS CONTACTED, THEY INFORMED US THAT THEY HAD PROBLEMS WITH THEIR CALIBRATION SYSTEM WHICH MADE THE FLOW PACKS PUT OUT MINIMUM AIR. THEY HAD KNOWN ABOUT THIS PROBLEM FOR TWO MONTHS OR MORE HOWEVER THEY CONTINUED TO PRODUCE AND SELL OVERHAULED UNITS. OUR COMPANY RECEIVED TWO OVERHAULED UNITS TO REPLACE THESE THAT WERE OVERHAULED IMPROPERLY ALSO. THE COMPANY SPECIFIED THAT ANY PACKS OVERHAULED BEFORE MAY 19 W1L72 4T4 T A24CE E4EA 20060804000862006080400086 2006 8 4 CA060629008 420060620G2562 CONTACT ACK CESSNA195 195A 2073110CE JACOBPR755 R755B2 35007SW ELT BATTERY DEFECTIVE W K NONE L NO TEST ININSP/MAINT 1 CA 2385 (CAN) THE GOLD PLATING ON THE BATTERY CONTACT IS FLAKING OFF. THE EXPOSED METAL IS NON-CONDUCTIVE AND THEREFORE THE UNIT NO LONGER FUNCTIONS. (TC# 20060629008) 1H71 3R3 R A790 E237 20061018000762006101800076EU 2006 10 18 CA060630001 120060405G3246350A41101606 SKID SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1D1 NE MLG CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) SKID TUBE FOUND CRACKED AT 2 LOCATIONS FORWARD OF THE FORWARD CROSSTUBE AND BOTH FOUND CORRODED BEYOND REPAIRABLE LIMITS WHILE PERFORMING 5000 HR LANDING GEAR INSPECTION. TUBES P/N 350A41-1016-1063 AND-1163 REPLACED WITH SAME. (TC NR 20060630001) 1G71 3U3 U H9EU E19EU 20060804000872006080400087CE 2006 8 4 CA060630002 120060629G534705112421 STOP CESSNA172 172P 2072436CE LYC O320 O320D2J 41508EA SEAT TRACK CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING A ROUTINE SEAT REMOVAL PROCEDURE IT WAS NOTICED THAT THE SEAT STOP WAS BROKEN APART AROUND THE FASTENING SCREW HOLE. THERE IS NOT MUCH MATERIAL BETWEEN THE SCREW HOLE AND THE EDGE OF THE STOP WHICH COULD HAVE LED TO A FAILURE OF THIS AFT POSITIONED SEAT STOP. (TC# 20060630002) 1H71 3O3 ONT3A12 E274 20060804000902006080400090NM 2006 8 4 CA060630003 120060629G27821U109592 ACTUATOR BOEING727 727225 1384077NM SLAT INOPERATIVE W JA DUMP FUEL UNSCHED LANDING N FALSE WARNING CLCLIMB 1 CA 8225 (CAN) SHORTLY AFTER TAKEOFF, CREW NOTICED THAT THE #8 LEADING EDGE SLAT WAS NOT INDICATING THAT IT WAS RETRACTED. THE CREW REQUESTED FUEL DUMP AND TURN BACK TO DEPARTURE. MAINTENANCE TESTED THE SLAT AND FOUND THE INDICATION SWITCH IN THE ACTUATOR WAS AT FAULT. MAINTENANCE INSTALLED THE INLINE SLAT JUMPER P/N B2T-27-001-01 AND THE SYSTEM TESTED SERVICEABLE. THE AIRCRAFT WAS DISPATCHED WITHOUT FURTHER FAULTS. ACTUATOR TO BE REPLACED ON THE WEEKEND LAYOVER. (TC# 20060630003) 2L73 4F A3WE 20060804000922006080400092CE 2006 8 4 CA060630004 120060630G251005141823 SEAT CESSNA172 172P 2072436CE LYC O320 O320D2J 41508EA COCKPIT CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) INSPECTION OF SEAT FRAME ASS`Y DURING SCHEDULED MAINTENANCE REVEALED A CRACKED SUPPORT LEG. SAFETY OF SEAT ASS`Y MAY BE COMPROMISED DUE TO THE WEAKENED SUPPORT LEG. (TC# 20060630004) 1H71 3O3 ONT3A12 E274 20060804000962006080400096EU 2006 8 4 CA060630006 120060627G6520350A33020005 GEARBOX SNIAS 350 AS350BA 8680817EU TMECA ARRIELARRIEL1B 6OO30NE TAIL ROTOR FAILED W A UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 CA 5846 2489 (CAN) TAIL ROTOR GEARBOX CHIP LIGHT ILLUMINATED IN FLIGHT. AIRCRAFT LANDED AND CHIP DETECTOR EXAMINED, MALL AMOUNT OF FERROUS MATERIAL ON DETECTOR. DETECTOR CLEANED AND SERVICEABILITY CHECK CARRIED OUT. ON RETURN TO LANDING SITE, SMALL AMOUNT OF FINE HAIR LIKE PARTICLES DISCOVERED. TAIL ROTOR GEARBOX REMOVED AND SENT TO OVERHAUL FACILITY FOR TEARDOWN AND REPAIR. SERVICABLE GEARBOX INSTALLED, AIRCARFT RETURNED TO SERVICE. 1G71 3U3 UNCH9EU E19EU 20060804001022006080400102EU 2006 8 4 CA060702001 120060613G324616103000 WHEEL BNORM BN2 BN2A26 1520226EU LYC O540 O540E4C5 41532EA MLG CRACKED W D RETURN TO BLOCK E VIBRATION/BUFFET TXTAXI/GRND HDL 1 CA (CAN) ON TAXI AFTER LDG, A VIBRATION WAS NOTED ORIGINATION ON THE LH LDG GEAR. IT WAS ORIGINALLY THOUGHT TO BE A WHEEL OUT OF BALANCE. ON INSPECTION, A CRACK WAS OBSERVED ON THE INNER WHEEL 1/2 OUTBOARD ASSEMBLY. THE CRACKED RIM WAS REPLACED WITH NEW CLEAVLAND INNER WHEEL 1/2 PN 161-03000. (TC# 20060702001) 1H72 3O3 O A17EU E295 20060804001052006080400105NE 2006 8 4 CA060704001 220060506G7321 FUEL CONTROL AIRTRCAT802 AT802 0390305SW PWA PT6 PT6A67 52043NE ENGINE MALFUNCTIONED W O OTHER F FLT CONT AFFECTED CRCRUISE 1 CA (CAN) DURING FORMATION FLIGHT THE PILOT REDUCED POWER. WHEN POWER WAS RE-APPLIED THE ENGINE WOULD NOT RESPOND INITIALLY TO THROTTLE INPUT. POWER INCREASED AFTER 7 TO 8 SECONDS. THE FUEL CONTROL UNIT WAS SUBSEQUENTLY REPLACED. PWC WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 1L71 3T4 TNCA19SW E26NE 20060804001072006080400107EA 2006 8 4 CA060704002 220060527G7210 GEARBOX BEECH 99 99 1154002CE PWA PT6 PT6A28 EA ENGINE SPALLED W EA ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 CA 40252 (CAN) THE ENGINE CHIP DETECTOR WARNING ANNUNCIATED IN FLIGHT. THE ENGINE WAS SHUT DOWN AND THE AIRCRAFT DIVERTED TO AN ALTERNATE AIRPORT. SUBSEQUENT INSPECTION REVEALED SPALLING OF THE FIRST STAGE REDUCTION GEARBOX GEARING. (TC# 20060704002) 1L72 3T4 T A14CE E4EA 20060804001092006080400109NE 2006 8 4 CA060704003 220060530G7261 ENGINE AEROSPATR72 ATR72212A 8680902EU PWA PW120 PW127 NE LEAKING W EA ENGINE SHUTDOWN UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CLCLIMB 1 CA AK0001 (CAN) DURING CLIMB THE ENGINE WAS REPORTED TO LOSE OIL PRESSURE. THE ENGINE WAS SHUT DOWN IN FLIGHT AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE. P&WC WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC# 20060704003) 2H72 4T4 TRTA53EU E20NE 20060804001102006080400110EA 2006 8 4 CA060704004 220060515G7250 TURBINE BLADES BEECH 90 C90 1152913CE PWA PT6 PT6A21 52043EA TURBINE SECTION FRACTURED W EA ENGINE SHUTDOWN UNSCHED LANDING O OTHER CLCLIMB 1 CA (CAN) DURING CLIMB THE ENGINE EMITTED A LOUD NOISE AND WAS SHUT DOWN IN FLIGHT. THE AIRCRAFT DIVERTED FOR AN UNSCHEDULED LANDING WHICH RESUTED IN AIRFRAME DAMAGE. SUBSEQUENT INSPECTION REVEALED FRACTURED COMPRESSOR TURBINE BLADES. P&WC WILL MONITOR INVESTIGATION OF THE BLADES AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC# 20060704004) 1L72 3T4 T 3A20 E4EA 20060804001562006080400156EA 2006 8 4 CA060704005 220060606G7321 FUEL CONTROL DHAV DHC6 DHC6 2802606EA PWA PT6 PT6A27 52043EA ENGINE MALFUNCTIONED W EA ENGINE SHUTDOWN UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CLCLIMB 1 CA (CAN) THE ENGINE WAS REPORTED TO EXHIBIT TORQUE FLUCTUATIONS IN CLIMB AND WAS SHUT DOWN IN FLIGHT. THE FUEL CONTROL UNIT WAS SUBSEQUENTLY REMOVED FOR INVESTIGATION. P&WC WILL MONITOR INVESTIGATION OF THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC# 20060704005) 1H72 3T4 TRTA9EA E4EA 20060804001572006080400157NE 2006 8 4 CA060704006 220060607G7320 EEC LEAR 60 60LEAR 5170707CE PWA 305 PW305A 52128NE ENGINE FAILED W O OTHER XJ ENGINE FLAMEOUT WARNING INDICATION DEDESCENT 1 CA (CAN) THE ENGINE FLAMED OUT IN DESCENT. THE EVENT WAS LATER DUPLICATED DURING FLIGHT TEST. THE EEC WAS EXCHANGED AND THE PROBLEM COULD NOT BE DUPLICATED. THE AIRCRAFT WAS RETURNED TO SERVICE. P&WC WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC# 20060704006) 2L72 4F4 FRTA10CE E35NE 20060804001582006080400158EA 2006 8 4 CA060704007 220060611G7230 COMPRESSOR BEECH 90 C90 1152913CE PWA PT6 PT6A34 52043EA ENGINE DAMAGED W EA ENGINE SHUTDOWN UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 1 CA RB0182 (CAN) IN CRUISE, THE ENGINE WAS REPORTED TO EMIT A NOISE FOLLOWED BY A LOSS IN POWER. THE ENGINE WAS SHUT DOWN IN FLIGHT AND THE AIRCRAFT DIVERTED. POST FLIGHT INSPECTION REVEALED COMPRESSOR DAMAGE. P&WC WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC# 20060704007) 1L72 3T4 T 3A20 E4EA 20060804001592006080400159NE 2006 8 4 CA060704008 220060609G7261310047001 ELBOW BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE HARTZLHCE4A HCE4A3I NE OIL SYSTEM FRACTURED W EA ENGINE SHUTDOWN UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CRCRUISE 1 CA (CAN) DURING CRUISE THE ENGINE LOW OIL PRESSURE WARNING ANNUNCIATED. THE ENGINE WAS SHUT DOWN IN FLIGHT AND THE AIRCRAFT DIVERTED FOR AN UNSCHEDULED LANDING. SUBSEQUENT INSPECTION REVEALED THE REDUCTION GEARBOX PRESSURE OIL ELBOW IMPROPERLY SECURED AND FRACTURED. P&WC WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC# 20060704008) 2L72 4T4 TRTA24CE E26NE 5 CP10NE 20060804001622006080400162 2006 8 4 CA060704009 420060613G3418 STALL WARNING CNDAIRCL601 CL6013A 8070802EA FALSE ACTIVATIONW A UNSCHED LANDING N FALSE WARNING CLCLIMB 1 CA (CAN) THE FOLLOWING WAS REPORTED BY THE PILOT; "THE STALL WARNING HORN SOUNDED, STICK SHAKER ACTIVATED FOLLOWED BY THE PUSHER AT FL320 DURING CLIMB. R AFCS WAS ENGAGED AND COUPLED TO CO-PILOT¿S FD AT THE TIME. WHEN THE PILOT GRABBED THE YOKE THE SHAKER ACTIVATED ONE MORE TIME. THE AFCS WAS DISENGAGED AND THE NOSE WAS LEVELLED. THE STALL HORN AND STALL LIGHTS REMAINED ON. AN EMERGENCY WAS DECLARED AND THE AIRCRAFT RETURNED TO OWN BASE. LANDING WAS UNEVENTFUL." THE FOLLOWING FLIGHT TO THE SERVICE CENTRE WAS UNEVENTFUL AND THE STALL PROTECTION SYSTEM WAS TROUBLESHOT WITH NO FAULT FOUND. THE FDR DATA WAS ANALYSED AND SHOWED THAT, DURING CLIMB OUT, AT FL327 THE AIRSPEED HAD SLOWED TO 155 KIAS, A SPEED CONSIST2L72 4F RTA21EA 20060804001662006080400166NE 2006 8 4 CA060704010 220060613G7200 ENGINE LEAR 60 60LEAR 5170707CE PWA 305 PW305A 52128NE MALFUNCTIONED W A UNSCHED LANDING BJ SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION CLCLIMB 1 CA 305269 (CAN) IN CLIMB THE CREW REPORTED SMOKE AND OIL SMELL IN THE CABIN ACCOMPANIED BY AN ENGINE CHIP DETECTOR WARNING. THE CREW DECLARED AN EMERGENCY AND THE FLIGHT WAS DIVERTED TO POINT OF ORIGIN. PWC WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC# 20060704010) 2L72 4F4 FRTA10CE E35NE 20060804001732006080400173NE 2006 8 4 CA060704011 220060628G73217045402L2 FUEL CONTROL SKRSKYS64 S64E 8142604NE PWA JFTD12JFTD12A4A 52047NE ENGINE FAILED W EA ENGINE SHUTDOWN UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CLCLIMB 1 CA 4527 313 672488 (CAN) AFTER SETTING A TURN OF LOGS DOWN ON LOG LANDING WITH A LT CROSS WIND, ACFT TURNED FULLY INTO WIND & BEGAN A CLIMB BACK UP HILL TO LOGGING UNIT WITH APPROXIMATELY 60% TORQUE INDICATED. AFTER ABOUT 7-10 SECONDS INTO CLIMB, N1 UNDERSPEED WARNING HORN SOUNDED. FLT CREW REDUCED POWER & OBSERVED N2 NEEDLE FOR NR 2 ENG DECREASING ON TRIPLE TACH. CO-PILOT NOTICED NR 2 ENG N1 SPEED AT 35% & T5 TEMP STABLE AT 465 DEGREES C. CREW ELECTED TO SHUTDOWN NR 2 ENG & MOTOR TO COOL T5. AN ATTEMPT TO RESTART ENG MADE & THEN ABORTED DUE TO ENG NOT ACCELERATING PAST 35% N1. ACFT LANDED WITHOUT FURTHER INCIDENT. A COMPLETE INSPECTION REVEALED NOTHING ABNORMAL. AN ENGINE START ATTEMPTED & ABORTED DUE TO ENG NOT BEING ABLE TO A2G72 4U4 U H4EA E15EA 20060804001762006080400176NE 2006 8 4 CA060704012 220060615G7200 ENGINE BEECH MU300 400A 1155402CE PWA JT15 JT15D5 52112NE FLAMED OUT W A UNSCHED LANDING XJ ENGINE FLAMEOUT WARNING INDICATION CRCRUISE 1 CA 100208100209 (CAN) DURING CRUISE AT FL380 (AND APPROACHING CLOUD TOP) BOTH ENGINES WERE THROTTLED BACK IN POWER BY THE CREW PRIOR TO ENGAGING ANTI-ICE. BOTH ENGINES FLAMED OUT. THE ENGINES WERE SUBSEQUENTLY RE-STARTED IN FLIGHT AND THE AIRCRAFT DIVERTED. POST-EVENT INSPECTION REVEALLED NO ENGINE ANOMOLIES. P&WC WILL INVESTIGATE THE EVENT AND WILL REPORT ON ROOT CAUSE ONCE ESTABLISHED. 2H72 4F4 FRTA16SW E25EA 20060804001782006080400178NE 2006 8 4 CA060704013 220060619G7250 ENGINE AEROSPATR72 ATR72 EU PWA PW120 PW127 NE MALFUNCTIONED W EA ENGINE SHUTDOWN UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 1 CA (CAN) IN CRUISE THE ENGINE WAS REPORTED TO EXHIBIT TORQUE AND POWER TURBINE SPEED FLUCTUATIONS. THE ENGINE WAS SHUT DOWN IN FLIGHT AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE. P&WC WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC# 20060704013) 2H72 4T4 TRT E20NE 20060804001792006080400179NE 2006 8 4 CA060704014 220060618G73218237002 FUEL CONTROL CESSNA560 560XL 2076702CE PWA 545 PW545A NE ENGINE MALFUNCTIONED W E ENGINE SHUTDOWN FJ FLT CONT AFFECTED WARNING INDICATION DEDESCENT 1 CA (CAN) DURING DESCENT, THE ENGINE WOULD NOT RESPOND TO THROTTLE INPUTS FOR POWER REDUCTION. THE ENGINE WAS SHUT DOWN ON FINAL APPROACH. THE FUEL CONTROL UNIT WAS SUBSEQUENTLY REPLACED. (TC# 20060704014) 2L72 4F4 FRTA22CE E00059EN 20060804001812006080400181NM 2006 8 4 CA060704015 120060619G2120 SMOKE DORNERDO32 DO328300 NM PWA 306 PW306B NE CABIN DETECTED W O OTHER B SMOKE/FUMES/ODORS/SPARKS DEDESCENT 1 CA CD0228 (CAN) ON DESCENT THE CREW REPORTED SMOKE IN THE CABIN AIR. AN EMERGENCY WAS DECLARED AND THE AIRCRAFT LANDED AT POINT OF DESTINATION. P&WC WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC# 20060704015) 2H72 4T4 FRTA55NM E35NE 20060804001832006080400183NE 2006 8 4 CA060704016 220060621G73103031829 TUBE PIAGIOP180 P180 6960204EU PWA PT6 PT6A66 52043NE FUEL SYS FRACTURED W O OTHER XJ ENGINE FLAMEOUT WARNING INDICATION CRCRUISE 1 CA (CAN) THE ENGINE FLAMED OUT IN CRUISE. SUBSEQUENT INSPECTION REVEALLED A FRACTURED FUEL SYSTEM P3 AIR TUBE. (TC# 20060704016) 1H72 3O4 TRTA59EU E26NE 20060804001852006080400185NM 2006 8 4 CA060704017 120060625G7931312244801 PRESSURE SWITCH BOMBDRDHC8 DHC8402 1390042NM PWC 150 PW150A EA OIL SYS FAILED W E ENGINE SHUTDOWN N FALSE WARNING CRCRUISE 1 CA (CAN) IN FLIGHT, THE CREW OBSERVED A LOSS OF ENGINE OIL PRESSURE INDICATION AND THE ENGINE WAS SHUTDOWN. THE ENGINE OIL PRESSURE SWITCH WAS SUBSEQUENTLY REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. (TC# 20060704017) 2H72 4T4 TRTA13NM E00062EN 20060804001862006080400186NE 2006 8 4 CA060704018 220060627G72613007389 ADAPTER CESSNA208 208 2073702CE PWA PT6 PT6A114 52043NE OIL SYS FRACTURED W EA ENGINE SHUTDOWN UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CLCLIMB 1 CA (CAN) AT TOP OF CLIMB, ENGINE TORQUE WAS SEEN TO FLUCTUATE FOLLOWED BY AN ENGINE LOW OIL PRESSURE WARNING. THE ENGINE WAS SHUT DOWN IN FLIGHT AND A DEAD-STICK LANDING ACCOMPLISHED. SUBSEQUENT INSPECTION REVEALED EXTERNAL OIL LEAKAGE ASSOCIATED WITH A FRACTURED REDUCTION GEARBOX PRESSURE OIL ADAPTER. P&WC WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC# 20060704018) 1H71 3T3 TNTA37CE E4EA 20060804001882006080400188NE 2006 8 4 CA060704019 220060627G7532 BLEED VALVE PILATSPC12 PC12 7090550EU PWA PT6 PT6A67B 52043NE ENGINE DIRTY W A UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 1 CA (CAN) DURING CRUISE, THE ENGINE EMITTED A LOUD NOISE ACCOMPANIED BY FLAMES FROM THE EXHAUST AND POWER FLUCTUATIONS. THE PILOT REDUCED ENGINE POWER AND ACCOMPLISHED AN UNSCHEDULED LANDING. SUBSEQUENT INSPECTION FOUND THE ENGINE COMPRESSOR BLEED VALVE TO BE STIFF AND FULL OF SAND, THE BOV WAS CLEANED AND THE ENGINE RAN NORMALLY. (TC# 20060704019) 1L71 3T4 TRTA78EU E26NE 20060804001902006080400190EA 2006 8 4 CA060704020 120060703G2910AN62498 CHECK VALVE CNDAIRCL215 CL2151A10 1900320EA HYD SYSTEM CRACKED W O OTHER KJ FLUID LOSS WARNING INDICATION NRNOT REPORTED 1 CA 96 96 (CAN) DURING FIRE FIGHTING OPERATIONS WATERDROP , HYDRAULIC FAILURE OCCURRED. AIRCRAFT LANDED AFTER EMERGENCY LANDING GEAR EXTENSION WITH BOMB DOORS OPEN AND WAS TOWED OFF RUNWAY. THIS IS THE SECOND FAILURE ON THE SAME AIRCRAFT IN THE SAME POSITION WE HAVE HAD THIS SUMMER FROM CHECK VALVE FAILURE. NEW STAINLESS VALVES HAVE BEEN ORDERED TO COMPLY WITH SUGGESTED CANADAIR SERVICE BULLETIN BUT HAVE NOT ARRIVED. WE HAD TO USE THE OLD STYLE ALUMINUM CHECKVALVE WHEN IT WAS REPLACED EARLIER IN THE SPRING. SEE REFERENCE PREVIOUS SDR #20060427007 DATED MAY 12, 2006. (TC# 20060704020) 2H72 4R RTA14EA 20060804001922006080400192EA 2006 8 4 CA060704021 120060702G291082970009325 LINE DHAV DHC8 DHC8311 1386006EA PWA PW120 PW123 NE HAMSTD14SF 14SF15 NE HYD SYSTEM LEAKING W O OTHER KJ FLUID LOSS WARNING INDICATION DEDESCENT 1 CA (CAN) ENROUTE AIRCRAFT REPORTED LOSS OF NR 2 HYDRAULIC SYSTEM QUANTITY. ALTERNATE GEAR EXTENSION SELECTED FOR ARRIVAL , NORMAL LANDING. MAINTENANCE INSPECTION FOUND NR 2 ENGINE DRIVEN HYDRAULIC PUMP PRESSURE LINE LEAKING, LINE REPLACED. HYD PUMP REPLACED DUE TO UNKNOWN TIME OPERATING WITHOUT FLUID. AIRCRAFT RETURNED TO SERVICE. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20060804001962006080400196EA 2006 8 4 CA060705001 120060702G79314120T16P01 TRANSDUCER CNDAIRCL600 CL6002D24 1390016EA GE CF34 CF348E5 30015NE OIL PRESSURE MALFUNCTIONED W E ENGINE SHUTDOWN O OTHER TXTAXI/GRND HDL 1 CA 2 GEE194466 (CAN) DURING RIGHT ENGINE WINDMILL RELIGHT, RIGHT ENGINE OIL PRESSURE AT 0 PSI UNTIL 24% N2. AT 34% N2, RIGHT OIL PRESSURE AT 3 PSI. ENGINE SHUT DOWN AND RTB SINGLE ENGINE. NOTE: DURING CRUISE PRIOR TO ENGINE SHUTDOWN, RIGHT ENGINE OIL PRESSURE WAS CONSTANTLY 10 PSI BELOW LEFT ENGINE OIL PRESSURE. (TC# 20060705001) 2L72 4F4 FRTA21EA E00063EN 20060804001972006080400197NE 2006 8 4 CA060705002 220060705G7230 COMPRESSOR PWA PT6 PT6A135 52043NE ENGINE BIRD INGESTION W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) DAMAGE TO ENGINE COMPRESSOR CAUSED BY BIRDSTRIKE. COMPRESSOR DAMAGE WAS REPAIRED AND ENGINE RETURNED TO SERVICE. (TC# 20060705002) 4 T E4EA 20060804001982006080400198NM 2006 8 4 CA060705004 120060704G612087620130101 SHAFT DHAV DHC8 DHC8301 1386003NM PWA PW120 PW123 NE HAMSTD14SF 14SF23 NE NR 1 PROPELLER BROKEN W E ENGINE SHUTDOWN F FLT CONT AFFECTED DEDESCENT 1 CA 20301 (CAN) LOSS OF PROPELLER CONTROL DUE TO BROKEN ENGINE CONTROL SPRING STRUT; THE FAILURE OCCURRED DURING FLIGHT AND DISABLED CONTROL OF THE NO 1 PROPELLER. THE EMERGENCY FUEL SHUT-OFF HAD TO BE OPERATED TO SHUT THE ENGINE DOWN AFTER LANDING. AT THE TIME OF THE INCIDENT, THE AIRCRAFT HAD ATTAINED 20301:00 HOURS AND 39275 CYCLES. THE OPERATOR IS PRESENTLY CARRYING OUT A CAMPAIGN OF THEIR FLEET IN AN EFFORT TO AVOID ANY RECURRENCE. (TC# 20060705004) 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20060804001992006080400199CE 2006 8 4 CA060705005 120060705G3320S18802 RHEOSTAT CESSNA185 A185E 2072818CE CONT O520 IO520D 17032SO CABIN LIGHTS MALFUNCTIONED W O OTHER O OTHER NRNOT REPORTED 1 CA 3560 (CAN) AIRWORTHINESS DIRECTIVE SEARCH ON TRANSPORT CANADA`S WEB SITE DID NOT SHOW 93-24-15 APPLYING TO THIS AIRCRAFT. IT APPEARS THAT THE MODEL APPLICABILITY SECTION OF THE FAA AIRWORTHINESS DIRECTIVE IS INCORRECT. (TC# 20060705005) 1H71 3O3 O 3A24 E5CE 20060807000022006080700002CE 2006 8 7 CA060705008 120060628G3230M710501 MOTOR BEECH B300 B300 1159232CE PWA PT6 PT6A60A 52043NE HYD SYSTEM MALFUNCTIONED W O OTHER J WARNING INDICATION APAPPROACH 1 CA 388 (CAN) DURING APPROACH LANDING GEAR WOULD NOT EXTEND NORMALLY AND 2 AMP CONTROL CIRCUIT BREAKER HAD OPENED. LANDING GEAR WAS LOWERED USING MANUAL SYSTEM AND UNEVENTFUL LANDING CARRIED OUT. MAINTENANCE FOUND 60 AMP LANDING GEAR CIRCUIT BREAKER OPEN (IN LH WING). REPLACED LANDING GEAR MOTOR (RIGHT POWER PACK) WITH OVERHAULED SPARE. RESET CIRCUIT BREAKERS AND GROUND TESTED LANDING GEAR OPERATIONS. EXPERIENCE HAS SHOWN THAT THESE MOTORS ARE PRONE TO PREMATURE FAILURE OR EXCESSIVE CURRENT DRAW. 2L72 4T4 TRTA24CE E4EA 20060807000032006080700003NM 2006 8 7 CA060706001 120060703G291065C268091131 LINE BOEING737 737522 138449FNM CFMINTCFM56 CFM563C1 13802EU HYDRAULIC SYS CRACKED W O OTHER KJ FLUID LOSS WARNING INDICATION CLCLIMB 1 CA (CAN) #1 ENGINE HYDRAULIC PUMP CONTROL LIGHT ILLUMINATED IN FLIGHT ON CLIMB FROM LA GUARDIA. AIRCRAFT CONTINUED THE FLIGHT. UPON INVESTIGATION IT WAS FOUND THAT A HYDRAULIC LINE FOR THE "A" SYSTEM PRESSURE MODULE WAS CRACKED. LINE REPLACED AND FLUID LEVEL SERVICED. AIRCRAFT RELEASED FOR SERVICE. TIMES: 37201:46 CYCLES: 22712 (TC# 20060706001) 2L72 4F4 FRTA16WE E21EU 20060807000092006080700009SW 2006 8 7 CA060706002 120060704G6210204011250001 BLADE BELL 205 205A1 1181414SW LYC T53 T5313B 41549NE MAIN ROTOR CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 1988 (CAN) CRACK ON BOTH SIDES OF BLADE BOLT BORE. TRAVELLING IN CHORDWISE DIRECTION. THE LEADING EDGE CRACK TRAVELS RIGHT TO THE LEADING EDGE AND THE TRAILING EDGE CRACK IS APPROXIMATLEY 6 INCHES LONG. IT APPEARS ALL DOUBLERS ON THE LOWER PART OF THE BLADE ARE CRACKED. (TC# 20060706002) 1G71 4U4 U H1SW E17EA 20060807000202006080700020NE 2006 8 7 CA060706003 220060704G7532310562601 CONNECTING ROD PWA JT15 JT15D1 52060NE BLEED VALVE WORN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) PRATT & WHITNEY CANADA OVERHAUL MANUAL 3037323 REV.22, SECTION 72-30-07, PARAGRAPH 88-4 MISTAKENLY CALLS FOR NICKEL PLATING IN ACCORDANCE WITH SPOP 62. SPOP 62 IS A FLORESCENT PENETRANT INSPECTION PROCEDURE. IT IS UNDERSTOOD THAT THE MANUAL SHOULD RATHER CALL FOR SPOP 26 WHICH IS A NICKEL PLATING SPEC. (TC# 20060706003) 4 F E1NE 20060807000612006080700061NM 2006 8 7 CA060706004 120060702G24331032573 TRU BOEING727 727243 138408DNM PWA JT8 JT8D9A 52048NE NR 2 SMOKE W O OTHER B SMOKE/FUMES/ODORS/SPARKS TXTAXI/GRND HDL 1 CA (CAN) WHILE AIRCRAFT WAITING ON THE GATE TO BOARD PASSENGERS FOR DEPARTURE, SMOKE WAS OBSERVED IN THE COCKPIT. CAUSE OF SMOKE WAS DETERMINED TO BE THE NR 2 TRANSFORMER RECTIFIER. UNIT REPLACED WITH NO FURTHER DEFECTS. (TC# 20060706004) 2L73 4F4 FRTA3WE E2EA 20060807000642006080700064EU 2006 8 7 CA060706005 120060622G21509599060114 A/C PACK PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL FAILED W HA DEACTIVATE SYST/CIRCUITSUNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CLCLIMB 1 CA 5380 (CAN) PILOT REPORTED THAT ECS WAS SELECTED ON AT PREFLIGHT CHECK. NO PROBLEM NOTICED. SOON AFTER ROUTINE TAKEOFF AN ODOUR WAS PREVALENT IN COCKPIT. ECS SYSTEM WAS DEACTIVATED AND ODOUR DISSIPATED ALMOST IMMEDIATELY. AIRCRAFT RETURNED TO PLACE OF DEPARTURE WITH NO FURTHER FAULTS. PASSENGERS DEBOARDED AND CAPTAIN PERFORMED GROUND RUN TO TEST ECS. ODOUR RETURNED AS SOON AS ECS SELECTED ON. ECS SYSTEM WAS AGAIN DEAVTIVATED AND AIRCRAFT RETURNED TO BASE UNPRESSURIZED AND TROUBLESHOT SYSTEMS INDICATING COLD AIR UNIT WAS AT FAULT. UNIT WAS REPLACED WITH SERVICEABLE PART. GROUND RUN PERFORMED WITH NO FAULT FOUND. AIRCRAFT RETURNED TO SERVICE. (TC# 20060706005) 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20060807000652006080700065EU 2006 8 7 CA060706006 120060706G32309740926112 RELAY PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL HYD POWER FAILED W O OTHER J WARNING INDICATION CLCLIMB 1 CA 1055510555 (CAN) LANDING GEAR WOULD NOT RETRACT FULLY AND HYDRAULIC LIGHT CAME ON AFTER LANDING GEAR WAS SELECTED UP IN CLIMB. CREW CHECK HYDRAULIC CONTROL CB AND IT WAS IN. CREW FOLLOWED CHECK LIST AND SELECTED GEAR DOWN AND HAND PUMPED LANDING GEAR DOWN AND LOCKED. A/C WAS FLOWN TO MAINTENANCE BASE WITH GEAR DOWN AND LANDED WITHOUT INSIDENCE. HYDRAULIC SYSTEM TROUBLESHOOTING CARRIED OUT AND HYDRAULIC POWER CONTROL RELAY K601 FOUND TO BE AT FAULT. RELAY REPLACED AND LANDING GEAR/HYDRAULIC SYSTEMS FUNCTION CHECKED SERVICEABLE (TC# 20060706006) 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20060807000862006080700086WP 2006 8 7 CA060706007 120060705G291089H1014738LGD4 LINE GRUMANTS2 TS2ACALFORST3951102WP WRIGHTR1820 982C9HE2 67020EA HAMSTD43D 43D51 NE AT BEND CHAFED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING ROUTINE MAINTENANCE IT WAS NOTED THAT THE RH MLG DOOR ACTUATOR OPEN LINE WAS FOUND CHAFED BEYOND LIMITS. THE LINE WAS CHAFED BY AN ADJACENT FLEX LINE. THE AFFECTED LINE WAS REPLACED AND A GEAR SWING WAS COMPLETED. THE AIRCRAFT WAS RETURNED TO SERVICE. (TC# 20060706007) 2H72 4R4 R A25WE E259 6 CP8879 20060807000942006080700094EA 2006 8 7 CA060706008 120060620G291366WA300 PUMP CNDAIRCL215 CL2151A10 1900320EA PWA R2800 CA3 52026NE HYD SYSTEM BROKEN W A UNSCHED LANDING K FLUID LOSS APAPPROACH 1 CA 579 (CAN) AIRCRAFT SUFFERED HYDAULIC FAILURE. PERFORMED EMERGENCY GEAR EXTENSION AND LANDED SAFELY. HYDRAULIC LEAK FOUND ON ENGINE DRIVEN HYDRAULIC PUMP. THE END CAP FACEPLATE HAD A BROKEN BOLT AND THE BOLT IT WAS LOCKWIRED TO BESIDE IT HAD BACKED OFF. WITH BOTH BOLTS INEFFECTIVE, THE SEAL BLEW OUT BEHIND THE FACE PLATE AND ALL OF THE HYDRAULIC FLUID WAS PUMPED OVERBOARD. SUSPECTED PREVIOUS OVERTORQUING OF BOLT MAY HAVE CAUSED THE FAILURE (TC# 20060706008) 2H72 4R4 RRTA14EA E231 20060922001062006092200106NM 2006 9 22 CA060707001 120060626G24972431154B10 WIRE DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE TERMINAL END BURNED W O OTHER B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 1 CA (CAN) CREW REPORTED ELECTRICAL ODOR FROM BEHIND F/O`S SEAT DURING FLIGHT. LASTED FOR APPROX 10 MINUTES. MAINTENANCE FOUND OVERHEATED WIRES, CB`S AND BUS BARS ON THE RT SECONDARY DC CB PANEL. SPECIFIC ITEMS REPLACED AS FOLLOWS, (IPC 24-50-00 FIG.10 PAGES 0 TO 6. WIRE P/N 2431-154B10 FROM CB D1-RT FLARE LIGHT SECONDARY BUS REPLACED DUE TO ONE END OF WIRE AT TERMINAL END BADLY BURNED. APPEARS TO HAVE BEEN CAUSED BY ARCING OF THE WIRE. WIRE MAY HAVE LOOSENED OVER TIME DUE TO VIBRATION AS THERE DOES NOT APPEAR TO HAVE BEEN ANY RECENT WORK COMPLETED IN THIS AREA. WIRE P/N 2431-156A10 FROM CB C1-BUFFET POWER TO SECONDARY BUS LINK ON SECONDARY BUS BAR BETWEEN ROWS 4 AND 5 REPLACED DUE TO ONE END OF WIRE AT TERMINAL 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20060811000542006081100054NE 2006 8 11 CA060707002 220060626G73148187B MOTOR ROBSIN ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE FUEL PUMP FAILED W O OTHER J WARNING INDICATION TXTAXI/GRND HDL 1 CA 987 110738 (CAN) PILOT WAS UNABLE TO USE THE ELECTRIC PUMP TO PRIME THE ENGINE. TROUBLESHOOTING REVEALED THE PUMP WAS GETTING POWER. FUEL PUMP ASSEMBLY WAS REPLACED, AND NO FURTHER DEFECTS FOUND. (TC NR 20060707002) 1G71 3O3 O H11NM 1E4 20060811000552006081100055CE 2006 8 11 CA060707005 120060704G553004310093 FITTING CESSNA150 150M 2071830CE CONT O200 O200A 17020SO MCAULY1A102 1A102OCM GL VERTICAL FIN CORRODED W K NONE O OTHER ININSP/MAINT 1 CA 8896 (CAN) DURING 100 HOUR INSPECTION AME FOUND WHAT APPEARED TO BE A CRACK IN THE RADIUS OF THE LT FLANGE OF THE LT FITTING ATTACHING THE VERTICAL FIN TO THE HORIZONTAL STABILIZER. WHEN THE PART WAS REMOVED FROM THE AIRCRAFT THE LT FLANGE WAS FOUND TO BE BENT TOWARDS THE RT FLANGE, AND WHEN MOVED AWAY FROM THE RT SIDE, IT BROKE FROM THE BASE OF THE FITTING REVEALING INTERGRANULAR CORROSION. (TC NR 20060707005) 1H71 3O3 O 3A19 E252 5 NP918 20060811000562006081100056EA 2006 8 11 CA060708001 120060624G2150GG670950099 ACM CNDAIRCL600 CL6002C10 1390015EA RIGHT FAILED W O OTHER B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 1 CA 6557 00660 (CAN) CREW NOTED THAT THEY GOT RT PACK AUTO FAIL CAUTION AND THEN HAD A STRONG ELECTRICAL BURNNG SMELL /SMOKE IN REAR SECTION OF CABIN. THE PACK WAS REMOVE AND REPLACED IAW AMM. PLEASE ADD THE MFG IN THE MANUFACTURER MENU. THANK YOU (TC 20060708001) 2L72 4F RTA21EA 20060814001002006081400100SO 2006 8 14 CA060710002 120060707G3213MS28775335 SEAL PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA HARTZLHCE3Y HCE3YR2A GL MLG CUT W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) ON THE RAMP AFTER REFUELLING, PILOTS NOTED THE LT MLG OLEO WAS LEAKING FLUID AND DEFLATING. MAINTENANCE FOUND THE LT OLEO COMPLETELY DEFLATED AND APPROX. 1 LITRE OF HYDRAULIC FLUID ON THE RAMP UNDER THE LT OLEO. AFTER OLEO REMOVAL, FOUND THE LOWER OLEO BEARING INNER O-RING SEAL SPIRAL CUT APPROX. 1 INCH ALONG THE SEAL. REPLACED SEAL AND OLEO SERVICED BY AMO 128-94. (TC NR 20060710002) 1L72 3O3 O A20SO E14EA 5 CP33EA 20060814001012006081400101SO 2006 8 14 CA060710003 220060707G7322S122210 THROTTLE CONTROL CESSNA206 U206B 2073322CE CONT O520 IO520D 17032SO SEPARATED W K NONE O OTHER ININSP/MAINT 1 CA 370 (CAN) DURING A SCHEDULED 50 HOUR INSPECTION THE THROTTLE CONTROL WAS FOUND TO BE SEPARATED AT THE SWAGE AREA JUST AFTER THE CLAMP AREA ON THE ROD END END ALLOWING THE CONTROL GUIDE TO MOVE ALONG WITH THE CONTROL END POSSIBLY RESULTING IN CONTROL JAMMING. (TC NR 20060710003) 1H71 3O3 O A4CE E5CE 20060809001932006080900193EU 2006 8 9 CA060710005 120060622G6720350A75111720 SHIM SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1D NE TAIL ROTOR MISINSTALLED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING A 100 HR INSPECTION OF AN A-STAR IN THE FIELD, THE ENGINEER PERFORMING THE INSPECTION FOUND THAT THE T/R SERVO FRICTION/GUIDE SHIM (PAD) WAS INSTALLED ON THE FORWARD BOLT AND NOT ON THE AFT ONE. WHEN RT PEDAL IS APPLIED THE SERVO FRICTION/GUIDE SHIM (PAD) SLIDES .7500 PERCENT OF THE WAY OUT OF THE FIXED GUIDE TAILBOOM). THIS CONDITION COULD POTENTIALLY CAUSE THE SERVO TO JAM. THE FRICTION/GUIDE SHIM (PAD) WAS RELOCATED THE THE AFT BOLT IAW THE MM AND THE SERVO WAS CHECKED FOR CORRECT OPERATION. (TC NR 20060710005) 1G71 3U3 U H9EU E19EU 20060809001942006080900194NE 2006 8 9 CA060710006 220060706G73203031829 LINE AIRTRCAT802 AT802 0390305SW PWA PT6 PT6A67A 52043NE HARTZLHCB5M HCB5MA3 GL P3 CRACKED W O OTHER R PARTIAL RPM/PWR LOSS APAPPROACH 1 CA 1748 (CAN) DURING THE APPROACH TO THE AIRPORT, THE ENGINE LOST POWER. THE AIRCRAFT WAS DAMAGED ON LANDING. DURING PRELIMINARY INVESTIGATION, IT IS SUSPECTED THAT THE P3 LINE CRACKED CAUSING THE ENGINE TO GO INTO FLIGHT IDLE. THE ENGINE HAS BEEN REMOVED FROM THE AIRCRAFT AND HAS BEEN SHIPPED FOR FURTHER INVESTIGATION AND EVALUATION. UPON RECEIPT OF FINDINGS, WILL ADVISE. (TC NR 20060710006) 1L71 3T4 TNCA19SW E26NE 6 CP44GL 20060810000042006081000004NE 2006 8 10 CA060711001 220060711G7240 CASE PWA JD15 JT15D1A NE GAS GENERATOR CRACKED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) CRACKED GAS GENERATOR CASE WAS FOUND CRACKED AT THE LONGITUDINAL WELD AND CIRCUMFERENTIAL WELD. SB7240 IS AVAILABLE AND WILL REPLACE THE GAS GENERATOR CASE WITH A CASE WITH NO LONGITUDINAL WELDS. (TC NR 20060711001) 4 F E25EA 20060810000052006081000005CE 2006 8 10 CA060711002 120060710G2497D4FF10316GA WIRE FORD CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA MCAULY1C160 1C160DTM GL VOLT REGULATOR BURNED W H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 1 CA 4088 (CAN) WHILE ON A LOCAL VFR FLIGHT OVER, THE PILOT SMELLED FUMES AND SAW SMOKE COMING FROM BEHIND THE INSTRUMENT PANEL. THE PILOT ALSO NOTICED THAT THE HIGH VOLTAGE WARNING LIGHT WAS ON AND THE AMMETER SHOWING A DISCHARGE. THE PILOT REPORTED THE SITUATION TO THE FSS OPERATOR AND SUBSEQUENTLY TURNED OFF THE MASTER SWITCH, LANDING WITHOUT FURTHER INCIDENT. MAINTENANCE PERSONNEL DISCOVERED A BURNED WIRE FROM THE VOLTAGE REGULATOR TO THE HIGH VOLTAGE LIGHT. PARTS OF THE REGULATOR CIRCUIT BOARD SHOWED HEAT DAMAGE. THE VOLTAGE REGULATOR, HIGH VOLTAGE SENSOR HIGH VOLTAGE LIGHT AND BURNED WIRE WERE REPLACED. AIRCRAFT WAS RETURNED TO SERVICE WITHOUT FURTHER INCIDENT. (TC NR 20060711002) 1H71 3O3 ONT3A12 E274 5 NP910 20060913002912006091300291NM 2006 9 13 CA060711003 120060711G24339498828VS20 TRU DHAV DHC8 DHC8102 2809003NM NR 1 FAILED W H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS ININSP/MAINT 1 CA (CAN) THE EVENT OCCURRED DURING C-CHECK PROCEDURE AT THE EXTERNAL POWER APPLICATION. THE NR 1 TRU START TO PRODUCE HEAVY SMOKE AND SOME COPPER PARTICLES IN FUSION. COPPER PARTICLES PRODUCE SOME BURNING HOLES IN THE EXHAUST COOLING DUCT. THE NORMAL CAUTION LIGHT NEVER COME ON BEFORE THE ELECTRICAL POWER MANUALLY CUT OFF. (TC NR 20060711003) 2H72 4T RTA13NM 20060810000062006081000006EA 2006 8 10 CA060711004 220060710G7414 DISTRIBUTOR GEARCONT ROBSINR44 R44 7640120WP LYC O540 O540F1B5 41532EA MAGNETO DAMAGED W A UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION APAPPROACH 1 CA E01HA039R (CAN) AC WAS ON FINAL APPROACH WHEN PILOT HEARD A CHANGE IN ENGINE NOISE FOLLOWED BY LOW ROTOR HORN. INITIATED AN AUTOROTATION, NOTICED THAT ENGINE, M/R RPM`S RETURNED TO NORMAL. CONTINUED HIS APPROACH AS INITIALLY PLANED, LANDED HELICOPTER WITHOUT FURTHER INCIDENT. ONCE ON GROUND, PILOT DID A MAG CHECK WHEN LT MAGNETO WAS SELECTED, ENGINE QUIT. LT MAGNETO WAS REPLACED, AC RETURNED TO SERVICE. UPON REMOVAL OF MAGNETO, DISTRIBUTOR GEAR IN MAGNETO WAS FOUND TO HAVE SEVERAL TEETH WORN OR BROKEN OFF. HAVE DECIDED TO HAVE MAGNETOS O/H EVERY 500 HRS. O/H WILL INCLUDE REPLACING DISTRIBUTOR GEAR, EVENTHOUGH MANUAL DOES NOT CALL FOR IT. (TC NR 20060711004) 1G71 3O3 O H11NM E295 20060810000072006081000007EA 2006 8 10 CA060711005 220060706G8530SLC36005F CYLINDER HEAD LYC CESSNA172 172P 2072436CE LYC O320 O320D2J 41508EA MCAULY1C160 1C160DTM GL ENGINE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 1850 L1067229A (CAN) THIS THE 3RD CYLINDER IN 100 HOURS IS CRACKED THE SAME AS THE PREVIOUS 2. CRACKED APPROXIMATLY 30 PERCENT AROUND THE CYLINDER HEAD. CRACKED FROM THE OUTER MOST EXHAUST FLANGE STUD ROUGHLY 2 OR 3 INCHES TO THE EXHAUST VALVE SEAT. THEN CRACK CONTINUING FROM 180 DEGREE ACROSS THE EXHAUST VALVE SEAT TO THE SPARK PLUG HOLE (TC NR 20060711005). 1H71 3O3 ONT3A12 E274 5 NP910 20060810000082006081000008EA 2006 8 10 CA060711006 220060706G8530SLC36005F CYLINDER HEAD LYC CESSNA172 172P 2072436CE LYC O320 O320D2J 41508EA MCAULY1C160 1C160DTM GL ENGINE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 1850 L1067239A (CAN) THIS IS CYL NR 4 IN 100HRS. THE PREVIOUS 3 CYLINDERS EXHIBITED THE SAME TYPE AND LOCAL OF CRACKS. THIS CYLINDER HAS A ONE AND A HALF INCH LONG CRACK AT THE OUTER MOST EXHAUST FLANGE STUD MOVING TOWARDS THE EXHAUST VALVE SEAT. ALSO A CRACK BEGINNING AT THE EXHAUST VALVE SEAT AND MOVING TOWARDS THE SPARK PLUG HOLE (TC NR 20060711006) 1H71 3O3 ONT3A12 E274 5 NP910 20060810000092006081000009GL 2006 8 10 CA060711007 320060707G611005503214 BULKHEAD CESSNA CESSNA172 172P 2072436CE LYC O320 O320D2J 41508EA MCAULY1C160 1C160DTM GL SPINNER CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) THIS FORWARD SPINNER BULKHEAD HAS BEEN IN SERVICE WITH THE ORIGINAL (THIN MATERIAL) SPINNER. THE BULKHEAD HAS CRACKS TO 1.25 INCHES ACROSS EACH/ALL 6 PROP BOLK HOLES. (TC NR 20060711007) 1H71 3O3 ONT3A12 E274 5 NP910 20060810000102006081000010 2006 8 10 CA060711008 420060710G611305503214 BULKHEAD CESSNA172 172N 2072434CE LYC O320 O320D2J 41508EA MCAULY1C160 1C160DTM GL SPINNER CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 489 (CAN) THE SPINNER FORWARD BULKHEAD WAS INSTALLED NEW ONE YEAR EARLIER, WITH THE NEW HEAVIER MATERIAL SPINNER IAW SNL03-9 (ALTERNATE PROPELLER SPINNER INSTALATION) THE FWD BULKHEAD HAS CRACKS OF APPROXIMATLY 1.5 INCHES EACH COMING ACROSS EACH PROP BOLT HOLE AT THE TOP OF AND JUST OUTSIDE OF THE BOLT WASHER CONTACT AREA, BUT NOT DIRECTLY INTERFACING WITH THE HOLE ITSELF. (TC NR 20060711008) 1H71 3O3 ONT3A12 E274 5 NP910 20060810000112006081000011EA 2006 8 10 CA060712000 120060501G5610NP13932114 WINDOW CNDAIRCL600 CL6002C10 1390015EA COCKPIT FAILED W O OTHER O OTHER CRCRUISE 1 CA 1436 (CAN) THE RT SIDE WINDOW SHATTERED IN FLIGHT AT FL320, OUTTER SECTION. WINDOW IS POST SB (TC NR 20060712000) 2L72 4F RTA21EA 20060810000122006081000012SW 2006 8 10 CA060712001 120060710G6220407310101101 BEARING BELL BELL 407 407 1182206SW ALLSN 250C 250C47B GL MAIN ROTOR SEPARATED W A UNSCHED LANDING E VIBRATION/BUFFET NRNOT REPORTED 1 CA 5644 A141 (CAN) AIRCRAFT DEVELOPED A VERTICIAL VIBRATION, VISUAL INSPECTION REVEALED A SEPERATED SHEAR BEARING. (TC NR 20060712001) 1G71 3U3 UO H2SW E1GL 20060811000572006081100057SO 2006 8 11 CA060712002 120060704G27201582102 TUBE PIPER PA23 PA23250 7102308SO LYC O540 IO540C4B5 41532EA HARTZLHCE2Y HCE2YR2 GL RUDDER CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 10678 (CAN) DUE TO HIGH WINDS THAT HIT THE RUDDER (WITHOUT CONTROL LOCKS INSTALLED) INSTALLED THE AIRCRAFT FOR DAMAGE. THE RUDDER PEDAL TUBE WAS FOUND CRACKED. THE PART WAS REPLACED. (TC NR 20060712002) 1L72 3O3 O 1A10 1E4 5 CP9EA 20060811000582006081100058EA 2006 8 11 CA060712003 120060702G2497WIRE2XA80ABBLU FEEDER CABLE CNDAIRCL601 CL6013A 8070802EA GE CF34 CF343A 30015NE FS 625.30 ARCED W O OTHER J WARNING INDICATION APAPPROACH 1 CA 6869 (CAN) RT GEN TRIPPED OFFLINE DURING APPROACH. GEN OFF ANNUNCIATOR CAME ON, PWR AUTO TRANSFERED FROM GEN 1. NO LOSS OF PWR ON ANY AC BUSES. AC FERRIED WITH GENERATOR 2 SELECTED OFF. ON 3RD ENGINE RUN, PROBLEM WAS DUPLICATED. PROBLEM WAS ISOLATED TO A WIRING PROBLEM. MAIN GEN FEED WIRES AWG 8 WERE INSPECTED. AT FS 625.30 JUST AFT OF AFT PRESURE BULKHEAD, EVIDENCE OF ARCING FROM FEEDER WIRE TO AC STRUCTURE WAS FOUND. ARCING REMOVED APPROX 0.780 SQUARE INCH OF MATERIAL. PROBLEM APPEARED TO BE INCORRECT INSTALLATION OF FEEDER WIRES DURING ORIGINAL AC BUILD. INADEQUATE CLEARANCE BETWEEN WIRING AND STRUCTURE. OPPOSITE SIDE WAS INSPECTED AND FOUND WIRING HAD A SAFE CLEARANCE TO STRUCTURE. (TC NR 20060712003) 2L72 4F4 FRTA21EA E15NE 20060810000132006081000013EA 2006 8 10 CA060712004 220060706G8530A4871 RETAINER ROBSINR22 R22BETA 7640110NM LYC O320 O320B2C 41508EA NR2 CYL BAFFLE BROKEN W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) NR 2 AND NR 4 CYLINDER LOWER BAFFLE IB RETAINER BROKE CAUSING BAFFLE CONTACTING NR 2 CYLINDER`S OIL RETURN LINE THUS CHAFED OIL LINE AND OIL SEEPAGE EVIDENT DURING DAILY CHECK. NR 2 AND NR 4 CYLINDER BAFFLE RETAINER P/N A4871 (TC NR 20060712004) 1G71 3O3 O H10WE E274 20060814000592006081400059EA 2006 8 14 CA060712005 220060704G72003031300 ENGINE DHAV DHC7 DHC7103 2802710EA PWA PT6 PT6A50 52043EA HAMSTD24PF 24PF305 GL NR 3 FAILED W A UNSCHED LANDING BJ SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION CLCLIMB 1 CA 119364012 86585 (CAN) ABORTED TAKEOFF DUE TO NR 3 ENGINE FAILURE. DURING TAKEOFF ROLL AIRCRAFT REACHED APPROXIMATELY 45 KNOTS WHEN A JOLT WAS FELT. THE PILOT NOTICED ABNORMAL READINGS ON THE NR 3 ENGINE GAUGES & LARGE AMOUNTS OF SMOKE COMING OUT OF THE NR 3 ENGINE. EMERGENCY SHUT DOWN INCLUDING ACTIVATION OF NR 3 FIRE BOTTLE. THE AIRCRAFT CAME TO A SUCCESSFUL HALT ON THE RUNWAY. UPON ARRIVING AT THE SIGHT OF THE INCIDENT & NOTICED OIL HAD BLOWN OUT THROUGH BOTH OF THE OPENINGS FROM THE BLEED AIR VALVES. INSPECTION REVEALED THAT THE COMPRESSOR HAD FAILED AND THROWN ONE BLADE. AS THE BLADE EXITED THE COMPRESSOR INTAKE IT RUPTURED ONE OF THE OIL TRANSFER TUBES ON THE RIGHT HAND SIDE OF THE ENGINE AND LARGE AMOUNT OF OIL CAME THRO2H74 4T4 T A20EA E4EA 6 CP1NE 20060810000142006081000014CE 2006 8 10 CA060712006 120060707G324695442077 WHEEL CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE NLG CORRODED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) AFTER ONLY ONE TIRE CHANGE AND 9 MONTHS IN SERVICE THE NOSE WHEEL WAS REMOVED AND FOUND EXCESSIVE CORROSION THE BOLT HOLES AND SURFACE CORROSION ON THE INNER WHEEL HALVES. (TC NR20060712006) 1L72 4F4 F A22CE E1NE 20081104 SW 2008 11 4 CA060712007 120060710G6320212040054007 CASE BELL 212 212 1181420SW M/R TRANSMISSIONCRACKED W K NONE O OTHER ININSP/MAINT 1 CA 234 (CAN) THE CRACKED SUPPORT CASE AT THE LIFT LINK FITTING. (TC NR 20060712007) 1G71 4U H4SW 20060913002942006091300294CE 2006 9 13 CA060712008 120060706G5310504200337 SUPPORT BEAM BEECH 100 A100 1152915CE PWA PT6 PT6A28 EA FUSELAGE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) UNDER THE PILOTS FLOOR BOARDS AT FLIGHT STATION 107 THE PILOTS RUDDER QUADRANT SUPPORT BEAM WAS FOUND CRACKED. THESE CRACKS WERE FOUND AT (2) OF THE (4) NUT PLATES. WE HAVE FOUND THESE SAME CRACKS ON 4 OTHER OF OUR AIRCRAFT AROUND THE SAME LOCATIONS. THE BEAM WAS REPLACED. (TC NR 20060712008) 1L72 3T4 T A14CE E4EA 20060913002962006091300296WP 2006 9 13 CA060712009 120060711G6310NAS4283A12 BOLT ROBSIN ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE CLUTCH ACTUATOR BENT W O OTHER O OTHER NRNOT REPORTED 1 CA 36 3172 (CAN) A/C TAFT 36.5 HOURS. MAIN BELT TENSION WAS TO BE ADJUSTED, WHEN IT WAS FOUND THAT THE ADJUSTMENT BOLT, ON THE CLUTCH ACTUATOR, COULD NOT BE MOVED. THE BOLT IS USUALLY HELD IN PLACE WITH A BACK UP NUT. THE BACK UP NUT WAS IN PLACE, AND MOVED AS NORMAL. THE HEAD OF THE BOLT, USED TO STOP A MICRO SWITCH, WAS TIGHT UP AGAINST THE FLANGE. VARIOUS ATTEMPTS WERE MADE TO MOVE THE BOLT, UNTIL FINALLY THE ASSEMBLY WAS REMOVED FROM THE AIRCRAFT WHERE IT COULD BE MOVED, STILL WITH SOME DIFFICULTY. THE BOLT WAS REPLACED WITH A SERVICEABLE PART, AND THE CLUTCH ACTUATOR WAS REINSTALLED. NO OTHER DEFECTS WERE NOTED. (TC NR 20060712009) 1G71 3O3 O H11NM 1E4 20060810000152006081000015NE 2006 8 10 CA060713003 220060703G8530327628 CYLINDER CNDAIRCL215 CL2151A10 1900320EA PWA R2800 R2800CA3 52026NE HAMSTD43E 43E60 NE ENGINE CRACKED W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CLCLIMB 1 CA (CAN) ON CLIMB AFTER SCOOP PILOT NOTICED FLICKER IN THE MANIFOLD PRESSURE GAUGE. ANOTHER A/C ADVISED PILOT OF A SMOKE TRAIL. THE LOAD WAS PITCHED AND THE A/C WAS RETURNING WHEN ANOTHER A/C CONFIRMED THE SMOKE BUT NO FIRE. THE A/C RETURNED TO BASE AND A CRACKED CYLINDER WAS FOUND AND CHANGED. THE A/C WAS RETURED TO SERVICE. (TC NR 20060713003) 2H72 4R4 RRTA14EA 5E8 6 CP871 20060811000592006081100059EA 2006 8 11 CA060713004 120060711G281021564075 FUEL CELL CNDAIRCL215 CL2156B11215 EA PWA PW120 PW123 NE HAMSTD14SF 14SF* NE LT WING LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA 1384 (CAN) AC 2032 DEVELOPED A FUEL LEAK IN THE LT WING ON JULY 10/2006. ALL LT FUEL CELLS WERE REMOVED AND TESTED. CELLS NR 8 PT NR 215-64075, NR 6 PT NR 215-64002-2, NR 4 PT NR 215-64002-4, NR 3 PT NR 215-64006-6 WERE FOUND TO BE LEAKING UPON TESTING. LEAKING CELLS WERE REPLACED. (TC NR 20060713004) 2H72 4T4 TRTA14EA E20NE 6 CP7NE 20060810000162006081000016NE 2006 8 10 CA060714001 220060705G7261793651 LINE BOEING727 727223 1384074NM PWA JT8 JT8D15 52051NE ENGINE OIL SYS LOOSE W E ENGINE SHUTDOWN WKJINADEQUATE Q C FLUID LOSS WARNING INDICATION CRCRUISE 1 CA (CAN) CREW OBSERVED LOSS OF OIL QUANTITY NR 1 ENGINE. ENGINE SHUTDOWN PRIOR TO LOW OIL PRESSURE WARNING LIGHT ILLUMINATING. MAINTENANCE DETERMINED UPON THE JUST COMPLETED NR6 OIL BEARING REPLACEMENT THE FORWARD END OF THE PRESSURE TUBE WAS NOT SECURED AND LOCK WIRED CAUSING LEAK. LINE SECURED AND LEAK CHECK CARRIED OUT SERVICEABLE. (TC NR 20060714001) 2L73 4F4 F A3WE E2EA 20060810000172006081000017SW 2006 8 10 CA060714002 120060605G2121EM6081 BLOWER GULSTM690TP 690D 3970405SW GARRTTTPE331TPE3315 01514WP ROTOL R306 R306382F7 GL CABIN BURNED W O OTHER B SMOKE/FUMES/ODORS/SPARKS DEDESCENT 1 CA 2624 (CAN) DURING DESCENT FLIGHT CREW NOTED A STRONG ODOR FROM THE HEATER OUTLETS. CREW SELECTED RECIRCULATION BLOWER SWITCH OFF AND LANDED AIRCRAFT. GROUND OPERATION CHECK OF THE ENVIRO SYSTEM FOUND RT RECIRCULATION BLOWER INOPERATIVE. FURTHER INSPECTION OF THE BLOWER ASSEMBLY FOUND SIGNS OF MOTOR OVERHEATING AND ROUGHNESS. BLOWER ASSEMBLY REPLACED WITH OVERHAULED ITEM. RECIRCULATION BLOWER NOT IN MAINTENANCE LIMITS SCHEDULE. PART IS ON CONDITION. (TC NR 20060714002) 1H72 3T4 T 2A4 E4WE 6 CP8EU 20060810000182006081000018SW 2006 8 10 CA060714003 120060704G30103D249503 TIMER GULSTM690TP 690D 3970405SW GARRTTTPE331TPE3315 01514WP ROTOL R306 R306382F7 GL DEICE SYSTEM FAILED W A UNSCHED LANDING O OTHER CLCLIMB 1 CA (CAN) DURING CLIMB FLIGHT CREW NOTED VISUALLYTHAT WING DE-ICER BOOTS WERE INFLATED AND WOULD NOT DEFLATE. FLIGHT CREW SELECTED BLEED AIR CLOSED RESULTING IN BOOTS DEFLATING AND RETURNED TO DEPARTURE BASE. MAINTENANCE FOUND THE DE-ICE TIMER TO BE CAUSE OF FAULT. TIMER REPLACED WITH OVERHAULED ITEM AND SYSTEM CHECKED OKAY. (TC 20060714003) 1H72 3T4 T 2A4 E4WE 6 CP8EU 20060810000192006081000019 2006 8 10 CA060714007 420060713G6113C35325P SUPPORT HARTZL CESSNA206 U206F 2073333CE CONT O520 IO520F 17032SO SPINNER CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 392 AC6880 (CAN) DURING 100 HR INSP REMOVED SPINNER AND FOUND THE INNER SUPPORT CRACKED. (TC NR 20060714007) 1H71 3O3 O A4CE E5CE 20060913003132006091300313CE 2006 9 13 CA060716001 120060714G571207221991 RIB CESSNA185 185D 2072812CE CONT O470 IO470F 17026SO MCAULY2A34C D2A34C58 GL WING CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 3981 3981 (CAN) WING CENTER RIBS AT STATION 190.0 IN BOTH WINGS WERE FOUND CRACKED AT THE TRAILING EDGE WERE THEY ATTACH TO THE AUX REAR SPAR OF THE WING. STN 190.0 IN THE OB AILERON HINGE ATTACH POINT. IT IS SUSPECTED THAT AT SOME TIME THIS AIRCRAFT WAS SUBJECTED TO WING GUSTS WITHOUT THE CONTROLS LOCKED. SEE ATTACHED PHOTO`S OF THE CRACKED RIBS. (TC NR 20060716001) 1H71 3O3 O 3A24 3E1 5 CP3EA 20060808000882006080800088NE 2006 8 8 CA060717001 220060701G853011876 PUSHROD AYRES S2 S2RHGT65 0970110SO PWA R1340 AWASP 52016NE HAMSTD12D 12D40 NE ENGINE LOOSE W A UNSCHED LANDING RYJPARTIAL RPM/PWR LOSS ENGINE STOPPAGE WARNING INDICATION CLCLIMB 1 CA (CAN) THE BALL END ON THE NR 5 EXHAUST VALVE PUSHROD WAS LOOSE. THIS CAUSED THE PUSHROD TO LENGTHEN REMOVING ANY VALVE CLEARANCE. THIS CAUSED AN OPEN EXHAUST VALVE SITUATION WHICH ALLOWED EXHAUST FLAME TO ENTER THE NR 5 CYLINDER. WHEN THE NR 5 INTAKE VALVE OPENED THIS ALLOWED THE FLAME TO BURN THE AIR/FUEL MIXTURE THROUGHOUT THE ENTIRE BLOWER AND MANIFOLD CAUSING THE ENGINE TO LOSE POWER AND THEN STOP. (TC NR 20060717001) 1L71 3T3 RNC ATC14 5 CP257 20060808000902006080800090CE 2006 8 8 CA060717002 120060710G782005501579 HEATER CESSNA172 172 2072402CE CONT O300 O300A 17022SO MCAULY1A170 1A170DM GL MUFFLER CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 5791 14566D9A (CAN) LT MUFFLER CRACKING, BURNING THROUGH. RT MUFFLER CRACKED. STACK CRACKED. NOTE: CRACKS NOT VISIBLE WITH ATTACHMENTS (SCROUNDS) ON. MUFFLER HEATER - LT P/N 0550157-9, RT P/N 0550157-32 (TC NR 20060717002) 1H71 3O3 ONT3A12 E253 5 NP857 20060809001952006080900195CE 2006 8 9 CA060717003 120060706G7120075100331 MOUNT CESSNA185 A185F 2072821CE CONT O520 IO520D 17032SO MCAULY2A34C D2A34C58 GL ENGINE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 44 (CAN) DURING ROUTINE INSPECTION, IT WAS DISCOVERED THAT THE FWD LT MOUNT PAD WAS CRACKED. THIS ENGINE MOUNT WAS INSTALLED 44.8 HRS AGO. REPLACED ENGINE MOUNT WITH SERVICEABLE P/N 075-1003-31, AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20060717003) 1H71 3O3 O 3A24 E5CE 5 CP3EA 20060926000752006092600075NM 2006 9 26 CA060717004 120060714G3231478441 SPRING BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17EU NLG DOOR BROKEN W O OTHER O OTHER CRCRUISE 1 CA (CAN) OPERATOR FOUND SPRING OF ALTERNATE NLG RELEASE BROKEN AT THE LOWER END. NEW SPRING INSTALLED. FLEET INSPECTION SCHEDULED. (TC NR 20060717004) 2H72 4T4 TRTA13NM E00062EN6 CP17BO 20060811000602006081100060EA 2006 8 11 CA060717005 120060715G5610NP1393229 WINDOW CNDAIRCL600 CL600* EA GE CF34 CF348C1 NE COCKPIT FAILED W A UNSCHED LANDING O OTHER CLCLIMB 1 CA (CAN) CAPTAIN SIDE FLIGHT DECK WINDOW OUTSIDE PANE SHATTERED ON TAKEOFF. A/C RETURNED. 721377 HAVE INSPECTED THE A/C AND FOUND TO BE SAFE FOR FERRY FLIGHT WITH ZERO STOPS IAW THE RESTRICTIONS CONTAINED IN THE ATTACHED FLIGHT PERMIT. CAPT. SIDE WINDOW REPLACED, WINDOW HEAT AND PRESSURIZATION LEAK CHECKS COMPLETED AND CHECKED SERVICEABLE. (TC NR 20060717005) 2L72 4F4 FRTA21EA EOOO63EN 20060926000792006092600079WP 2006 9 26 CA060717006 120060715G6220369A7010 LOCK HUGHES369 369A 4470503WP ALLSN 250C 250C20B 03013GL MAIN ROTOR UNSERVICEABLE W O OTHER F FLT CONT AFFECTED CRCRUISE 1 CA (CAN) PILOT NOTICED FEEDBACK THRU CYCLIC CONTROL FROM MAIN ROTOR HEAD. HELICOPTER WAS LANDED AT MAIN BASE AND SERVICEABLE UNLOCK WAS INSTALLED TSO 00.0 AND TESTED SATISFACTORY. UNSERVICEABLE UNILOCK WILL BE SENT IN FOR OVERHAUL WITH A TEARDOWN REPORT REQUESTED (TC NR 20060717006) 1G71 3U3 U H3WE E4CE 20060926001352006092600135EA 2006 9 26 CA060717007 120060703G3320BAO80061 BALLAST DHAV DHC7 DHC7* EA PWA PT6 PT6A50 52043EA CABINLIGHTS OVERHEATED W O OTHER BM SMOKE/FUMES/ODORS/SPARKS OVER TEMP ININSP/MAINT 1 CA (CAN) VP-FBQ (DASH 7, S/NO 111) FLUORESCENT TUBE LAMP HOLDER OVERHEATING PROBLEM SHORTLY AFTER RE-INSTATING POWER DURING A C CHECK, A STRONG SMELL OF BURNING WAS NOTED IN THE FWD SECTION OF THE AIRCRAFT. THE FAULT WAS TRACED TO A LAMP HOLDER AT THE FRONT OF THE CABIN IN THE OVERHEAD LIGHTING SYSTEM. THE LAMP HOLDER HAD SUFFERED SERIOUS OVERHEATING RESULTING IN THE MELTING OF THE CONTACTS WITH ASSOCIATED HEAT DAMAGE TO THE INSULATED PORTION OF THE HOLDER. THE FLUORESCENT TUBE HAD ALSO SUFFERED DAMAGE TO THE CONTACT PINS. THE FLUORESCENT TUBE HAD NOT BEEN DISTURBED DURING MAINTENANCE THE LIGHTING CIRCUIT BREAKERS HAD NOT TRIPPED. THE BALLAST UNIT PART NR IS BA08006-1. THE AIRCRAFT IS FITTED WITH A MIXTURE OF BA02H74 4T4 TRTA20EA E4EA 20060926001362006092600136WP 2006 9 26 CA060717008 120060709G5630369350542 WINDOW HUGHES369 369D 4470706WP ALLSN 250C 250C20B 03013GL DOOR DETACHED W O OTHER D INFLIGHT SEPARATION CLCLIMB 1 CA (CAN) HELICOPTER WAS CLIMBING OUT AT 70 KTS WHEN THE RT FWD DOOR WINDOW IMPLODED INTO THE CABIN. UPON INVESTIGATION IT WAS FOUND THE WINDOW INSTALLED REQUIRED A RUBBER GASKET TO HOLD IT IN. THINKING IT WAS A MD WINDOW IT WAS INSTALLED WITH THE ORIGINAL FRAME. THE WINDOW THAT USES THE GASKET IS ABOUT .25 SMALLER IN DIAMETER ALLOWING IT TO COME OUT OF THE FRAME INTO THE CABIN. A NEW WINDOW WITH A RUBBER GASKET WAS INSTALLED AND STAYED IN SATISFACTORY. (TC NR 20060717008) 1G71 3U3 U H3WE E4CE 20060926001372006092600137NM 2006 9 26 CA060718001 120060714G29136617303 PUMP BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17EU HYD SYSTEM SPLIT W A UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CRCRUISE 1 CA (CAN) NR1 EDP FAILED DURING FLIGHT CAUSING NR1 HYDRAULIC SYSTEM DEPLETION. EMERGENCY CHECKLIST PERFORMED. UNEVENTFUL LANDING AND A/C STOPPED ON RWY AND LATER TOWED TO PARKING POSITION. PUMP HOUSING FOUND SPLIT. EDP REPLACED. GROUND RUNS AND LEAK CHECK CARRIED SERVICEABLE. A/C HAS BEEN RTS. (TC NR 20060718001) 2H72 4T4 TRTA13NM E00062EN6 CP17BO 20060811000612006081100061NE 2006 8 11 CA060718002 320060714G6110C459 THRUST PLATE HARTZL HCE4N3G BEECH 200 200BEECH 1152920CE PWA PT6 PT642A NE HARTZLHCE4N HCE4N3 NE PROPELLER DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA 435 HH278 HH278 (CAN) UPON DISASSEMBLY OF THE PROPELLER, IT WAS FOUND TO HAVE A BROKEN THRUST PLATE SCREW (PN A3204). THE THRUST PLATE SCREW WAS FOUND JAMMED BETWEEN THE THRUST PLATE AND THE BLADE BUTT. AS A RESULT OF THIS BROKEN SCREW IT ALSO DAMAGED THE BETA PICKUP PLATE (PN C459) AND GOUGED THE BETA ROD (PN C453). THE THRUST PLATE, BETA PICKUP PLATE, BETA ROD, ALL FOUR THRUST PLATE SCREWS, ALL SEALS, LUBRICANTS AND HUB NUTS WERE REPLACED, PROPELLER WAS ASSEMBLED, LOCKED AND THE PROPELLER RETURNED TO CUSTOMER. (TC NR 20060718002) 1L72 4T4 T A24CE E4EA 5 CP10NE 20061213001352006121300135WP 2006 12 13 CA060718003 120060717G6510C0411 BEARING RACE ROBSIN ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE TAIL ROTOR ROUGH W O OTHER O OTHER NRNOT REPORTED 1 CA 36 1326 (CAN) IT WAS NOTICED THAT THE DAMPER BEARING HAD TURNED ON THE TAIL ROTOR DRIVE SHAFT. SLIPPAGE MARKS WERE ABOUT .5 INCH APART. THE BEARING WAS REMOVED SO IT COULD BE INSPECTED, AND POSSIBLY REINSTALLED. THE BEARING WAS FOUND TO BE ROUGH. IT WAS ALSO NOTED THAT THE GREASE IN THE BEARING WAS A DIFFERENT COLOR THAN THE GREASE IN THE SAME BEARING IN OTHER AIRCRAFT, AND PARTS IN STORES. THE BONDED PLATES WERE THE BEARING SITS WERE MEASURED AND FOUND TO HAVE A TOTAL INDICATED RUNOUT OF .0045 INCH. MANUFACTURES LIMIT IS .003 INCH. THE TAIL ROTOR DRIVE SHAFT ASSEMBLY IS TO BE REPLACED WITH A NEW UNIT. (TC NR 20060718003) 1G71 3O3 O H11NM 1E4 20060926001402006092600140EA 2006 9 26 CA060719001 220060714G73228198007 METERING UNIT BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17EU NR 1 ENG FUEL SHEARED W A UNSCHED LANDING Y ENGINE STOPPAGE CRCRUISE 1 CA 6117 (CAN) DURING CRUISE THE PILOT FELT A YAW-MOMENT AT THE SAME TIME THE TRQ NR 1 WENT TO 0 PERCENT, POWERPLANT MESSAGE APPEARED, ENG NR 1 PROP RPM DOWN TO 600 RPM, ENG NO.1 ITT APP. 200 DEGREES C LESS THAN ENG NR 2. PILOT CONTINUED WITH HIS CHECK LIST, MANUAL FEATHERED PROP NR 1 AND MANUAL SHUTDOWN THE ENG NR 1. AIRCRAFT LANDED SAFELY WITH SINGLE ENGINE OPS. CDS FAULT READ OUT PERFORMED AND FOLLOWING CODES ARE STORED: 360, 907, 911, 935. FAULT CODES SUPPLIED SEEM TO INDICATE A FUEL STARVATION FROM THE FMU. FOUND FMU SHAFT SHEARED. FMU TO BE REPLACED. (TC NR 20060719001) 2H72 4T4 TRTA13NM E00062EN6 CP17BO 20060814000602006081400060EU 2006 8 14 CA060719002 120060717G32339693001105 ACTUATOR PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL MLG LEAKING W K NONE O OTHER ININSP/MAINT 1 CA 153 (CAN) ORIGINAL MAIN LANDING GEAR ACTUATOR REPLACED WITH AN OVERHAULED UNIT. (ORIGINAL ACTUATOR HAD AN INTERNAL LEAK) HYDRAULIC SYSTEM FLUSHED BEFORE OVERHAULED ACTUATOR WAS INSTALLED. INTERNAL LEAK DEVELOPED IN TSO 153.3. HYDRAULIC SYSTEM FLUSHED AGAIN AND A REPAIRED ACTUATOR INSTALLED. NO CONTAMINATION NOTED IN FLUID AFTER EACH SYSTEM FLUSH. HYDRAULIC SYSTEM LEAK CHECKED SERVICEABLE (TC NR 20060719002) 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20060814000612006081400061CE 2006 8 14 CA060719003 120060718G27107020362 POTENTIOMETER CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE ELEVATOR SEPARATED W O OTHER O OTHER NRNOT REPORTED 1 CA 7418 (CAN) VISUAL INSPECTION CARRIED OUT ON ELEVATOR FDR SYSTEM DUE TO A FAILURE OF THE FDR CORRELATION FLIGHT TEST. FLIGHT TEST RECORDER SHOWED ELAVATOR SYSTEM NO RESPONSE TO SIGNAL. VISUAL INSPECTION REVEALED FAILED POTENTIOMETER SHAFT. REPLACED WITH NEW PART IAW MM. FLIGHT TEST TO BE CONDUCTED (TC NR 20060719003) 1L72 4F4 F A22CE E1NE 20060926001482006092600148EU 2006 9 26 CA060719005 120060719G3246300720 WHEEL BAG JETSTMJETSTM3212 1500217EU GARRTTTPE331TPE33110UG 01514WP MCAULY4HFR344HFR34C652 NE MLG DAMAGED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) DURING TOWING OF AIRCRAFT THE PIC AND GROUND HANDLERS NOTICED A WOBBLE ON THE RH MLG. MAINTENANCE WAS CONTACTED AND IT WAS DISCOVERED THAT A 10" PIECE OF THE EDGE OF THE INNER WHEEL RIM WAS MISSING. THE TIRE STILL REMAINED INFLATED. THE WHEEL AND TIRE WAS REMOVED AND REPLACED WITH A SERVICEABLE UNIT. THE IMMEDIATE ADJACENT AREA WAS INSPECTED FOR SECONDARY DAMAGE, NONE OBSERVED. (TC# 20060719005) 2L72 4T4 TRTBA15CAA E4WE 6 C3PNE 20060814000622006081400062SO 2006 8 14 CA060720001 120060621G55244A314003 ATTACH BRACKET EMB 110 EMB110P1 3260122SO PWA PT6 PT6A34 52043EA HARTZLHCB3T HCB3TN3 GL ELEVATOR CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING ROUTINE MAINTENANCE 2 CRACKS WERE DISCOVERED ON THE RT OB ELEVATOR HINGE ATTACH BRACKET. THE CRACKS WERE LOCATED ON THE LOWER FORWARD PORTION OF THE BRACKET IN THE MOST FORWARD PORTION OF A 90 DEGREE BEND AND WERE APPROX .7500 OF AN INCH IN LENGTH EACH. THE BRACKET WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20060720001) 1L72 4T4 T A21SO E4EA 6 CP15EA 20060926001492006092600149SO 2006 9 26 CA060720002 120060720G54114A27122201 CHANNEL EMB 110 EMB110P1 3260122SO PWA PT6 PT6A34 52043EA HARTZLHCB3T HCB3TN3 GL RT NACELLE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) WHILE CARRYING OUT MAINTENANCE IN THE RT LANDING GEAR AREA, A CRACK WAS FOUND IN THE IB LOWER NACELLE CHANNEL. THIS NACELLE CHANNEL IS THE ATTACH POINT FOR THE INBOARD GEAR DOOR HINGE. THE CRACK WAS LOCATED IN AFT PORTION OF THE HINGE ATTACH AREA MEASURING APPROXIMATELY 3.5 INCHES IN LENGTH. THE CRACK WAS DIFFICULT TO SPOT DUE TO THE OBSTRUCTION CAUSE BY THE GEAR DOOR HINGE WHEN IT IS INSTALLED. THE NACELLE CHANNEL HAS BEEN REPLACED. (TC NR 20060720002) 1L72 4T4 T A21SO E4EA 6 CP15EA 20060926001522006092600152NM 2006 9 26 CA060723001 120060717G5311654653120 FRAME BOEING737 737400 138449ANM BS 500B S28R-25LCORRODED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) FWD CARGO PIT FRAME TO SKIN AT BS 500B CORRODED BETWEEN STR 28R AND 28L (TC NR 20060723001). 2L72 4F RTA16WE 20060926001532006092600153NM 2006 9 26 CA060723002 120060717G5311654653170 FRAME BOEING737 737400 138449ANM BS 500C S27-28R CORRODED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) FWD CARGO PIT FRAME TO SKIN AT BS500C CORRODED STR 27R TO 28R (TC NR 20060723002). 2L72 4F RTA16WE 20060926001562006092600156NM 2006 9 26 CA060723003 120060717G5311654653170 FRAME BOEING737 737400 138449ANM BS 500C S28R-28LCORRODED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) FWD CARGO PIT FRAME CORRODED AT BS 500C AND STR 28R TO 28L (TC NR 20060723003) 2L72 4F RTA16WE 20060926001572006092600157NM 2006 9 26 CA060723004 120060717G53116546534 FRAME BOEING737 737400 138449ANM BS 520 S27-28R CORRODED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) SKIN TO FRAME ATTACH ANGLE CORRODED NR BS 520, STR 27R TO 28R (TC NR20060723004) 2L72 4F RTA16WE 20060926001602006092600160NM 2006 9 26 CA060724001 120060713G2740MS28775232 O-RING BOEING727 727225 1384077NM PWA JT8 JT8D15 52051NE STABILIZER SWOLLEN W O OTHER F FLT CONT AFFECTED DEDESCENT 1 CA 1540915409 (CAN) ON DESCENT STABILIZER OUT OF TRIM LIGHT ILLUMINATED, STABILIZER WOULD NOT RESPOND TO COMMANDS FROM AUTOPILOT, MAIN ELECTRIC TRIM OR MANUAL TRIM. FLIGHT CREW ACCOMPLISHED THE STABILIZER JAM EMERGENCY CHECK LIST AND LANDED UNEVENTFULLY. UPON INSPECT MAINTENANCE FOUND WATER INGRESSION IN THE GEAR BOX AND BRAKE ASSEMBLY DUE TO DAMAGED O-RINGS. STABILIZER GEAR BOX ASSEMBLY REPLACED IN ACCORDANCE WITH AMM 27-40-41. CONTRIBUTING FACTOR - EXCESSIVE RAIN EXPERIENCED DURING THE GROUND LAYOVER. (TC NR 20060724001) 2L73 4F4 F A3WE E2EA 20060926001622006092600162NM 2006 9 26 CA060724002 120060713G7810C5P156171 FLANGE DHAV DHC5 DHC5A 2803018NM EXHAUST SYS FAILED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) FLANGE HEIGHT IS 0.25 INCH INSTEAD OF 0.36 INCH. THIS COULD LEAD TO JET PIPE FAILURE, WHICH IN TURN, COULD LEAD TO DAMAGE IN THE INTEGRITY OF THE WINGS AND SYSTEMS NEARBY. CUSTOMERS ARE BEING NOTIFIED OF THIS NON-CONFORMANCE. NOTE(08AUG06): ONLY MILITARY CUSTOMERS WERE AFFECTED. CAUSE: FLANGE HEIGHT DIMENSION WAS OVERLOOKED BY OPERATOR AND INSPECTOR. SPECIFIED FLANGE HEIGHT REQUIREMENT WILL BE FORMALLY STRESSED TO APPLICABLE OPERATORS AND INSPECTORS (DUE DATE: AUG/06). (TC NR 20060724002) 2H72 4T RT 20060814000632006081400063NE 2006 8 14 CA060724003 220060715G7240311583501 BURNER CAN PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL ENGINE FAILED W O OTHER O OTHER NRNOT REPORTED 1 CA 4515 4 PR0176 (CAN) BRIGHT FLASHES COMING FROM EXHAUST STACKS, NO CHANGE TO INDICATIONS. 15 FLASHES IN 2 HOUR PERIOD. ENGINE OUTER BURNER CAN FOUND INOPERATIVE, CERAMIC COATING FLAKING OFF AND IGNITING. REPLACED WITH OVERHAULED UNIT. GROUND RUN AND RELEASED SERVICEABLE. P/N - ON/OFF 3115835-01 S/N OFF A0006973, S/N ON 2K962. (TC NR 20060724003) 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20060814000642006081400064EU 2006 8 14 CA060724004 120060717G771232448821 LIMITER PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL ENGINE FAILED W O OTHER RJ PARTIAL RPM/PWR LOSS WARNING INDICATION NRNOT REPORTED 1 CA 4516 11 PR0175 (CAN) PILOT SNAG: ENGINE POWER LOST IN FLIGHT HAD TO USE MANUAL OVERRIDE. RECTIFICATION: REPLACED TORQUE LIMITER P/N 3244882-1, S/N C50254 WITH REMOVED SERVICEABLE UNIT FROM ENGINE S/N PR0116 P/N 3244882-1 S/N C50621. ALL APPLICABLE ENGINE RUNS COMPLETED AND CHECKS SERVICEABLE. (TC NR 20060724004) 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20070516001622007051600162 2007 5 16 CA060724006 420060720G611305503214 BULKHEAD CESSNA172 172P 2072436CE LYC O320 O320D2J 41508EA MCAULY1C160 1C160DTM GL PROP SPINNER CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 250 (CAN) THIS BULKHEAD HAS CRACKS DIRECTLY ABOVE THE BOLT HOLES APPROXIMATELY ONE INCH LONG RADIALY ALONG THE INNER BEND RADIUS ABOVE THE BOLT HOLE BUT NOT INTERSECTING THE BOLT HOLE. (TC NR 20060724006) 1H71 3O3 ONT3A12 E274 5 NP910 20070516001632007051600163 2007 5 16 CA060724007 420060721G611305503214 BULKHEAD CESSNA172 172P 2072436CE LYC O320 O320D2J 41508EA MCAULY1C160 1C160DTM GL SPINNER CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 750 (CAN) THIS BULKHEAD HAS CRACKS DIRECTLY ABOVE THE BOLT HOLES APPROXIMATELY ONE INCH LONG RADIALY ALONG THE INNER BEND RADIUS ABOVE THE BOLT HOLE BUT NOT INTERSECTING THE BOLT HOLE. (TC NR 20060724007) 1H71 3O3 ONT3A12 E274 5 NP910 20060926001632006092600163 2006 9 26 CA060725001 420060722G34449650976003206 SWITCH HONEYWELL AIRBUSA340 A340313 EU GE CFM56 CFM565A 13802NE GPWS BURNED W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 1 CA (CAN) WHILE ENROUTE, ON A POLAR ROUTE IN THE MIDDLE OF HUDSON BAY, THE FLIGHT CREW REPORTED ACRID SMOKE COMING OUT OF OVERHEAD PANEL IN THE AREA OF THE TERRAIN SWITCH AND THE FAILURE OF THE GPWS. THE SMOKE THEN DISSIPATED. THE CREW DECLARED A PAN PAN (URGENCY), AND RETURNED TO YYZ, WHERE THE FLIGHT LANDED 30,000 KG OVERWEIGHT. (TC NR 20060725001) 2L74 4F4 FRTA197 E29NE 20060814000652006081400065NE 2006 8 14 CA060725002 220060721G73217436024 FUEL CONTROL BOEING737 737242C 1384478NM PWA JT8 JT8D9A 52048NE ENGINE MALFUNCTIONED W A UNSCHED LANDING EJ VIBRATION/BUFFET WARNING INDICATION CRCRUISE 1 CA 708828 (CAN) ENROUTE THE CREW ELECTED TO RETURN TO POINT OF DEPARTURE DUE TO A SUSPECTED ENGINE VIBRATION. AFTER ARRIVING, THE MAINTENANCE PERSONNEL INITIALLY REPLACED THE FORWARD ENGINE MOUNT ISOLATORS WITH NO APPARENT REMEDY OF THE PROBLEM. THE FCU WAS REPLACED AND THE ENGINE RUN UP WITH NO FURTHER VIBRATION INDICATION.THE AIRCRAFT WAS RETURNED TO SERVICE WITH NO FURTHER PROBLEMS. (TC NR 20060725002) 2L72 4F4 F A16WE E2EA 20060926001652006092600165CE 2006 9 26 CA060725004 120060720G261224412886 FIRE LOOP BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE HARTZLHCE4A HCE4A3I NE FIRE DETECTION UNKNOWN W E ENGINE SHUTDOWN N FALSE WARNING CRCRUISE 1 CA (CAN) DURING CRUISE FLIGHT THE CREW RECEIVED A RT ENGINE FIRE ANNUCIATION. ALTHOUGH IT WAS DETERMINED THAT NO FIRE WAS PRESENT, PROCEDURES WERE FOLLOWED TO SHUTDOWN AND SECURE THE ENGINE IN FLIGHT AND THE DISCHARGE OF THE FIRE EXTINGUISHING AGENT. MAINTENANCE FOUND THAT EITHER THE FORWARD OR AFT FIRE WIRE LOOP CAUSED THE ANNUNCIATION ALTHOUGH IT COULD NOT BE DETERMINED AS TO WHICH ONE AS THE FAULT MODE WAS NOT HARD AND THE SYSTEM RETURNED TO NORMAL OPS. BOTH LOOPS WERE REPLACED AS A PRECAUTION WITH NO REPEAT OF THE OCCURRENCE. IT IS ALSO POSSIBLE THAT THE FORWARD LOOP MAY HAVE BEEN TOO CLOSE TO THE STACK AND CAUSED THE FALSE WARNING AS WELL. (TC NR 20060725004) 2L72 4T4 TRTA24CE E26NE 5 CP10NE 20070516001642007051600164NE 2007 5 16 CA060725005 220060723G7200 ENGINE SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1D1 NE MAKING METAL W O OTHER J WARNING INDICATION DEDESCENT 1 CA 4111 1120 9359 (CAN) ON APPROACH, THE ENGINE CHIP LIGHT ILLUMINATED. THE PILOT LANDED THE HELICOPTER NORMALLY. THE ENGINE CHIP PLUGS WERE ALL REMOVED AND DEBRIS (METAL) WAS FOUND ON ALL PLUGS. METAL WAS ALSO FOUND ENTRAPPED IN THE OIL FILTER. THIS ENGINE WAS LAST SHOPPED IN MAY 2005 FOR MO2, MO4, MO5 AND FREEWHEEL OVERHAUL. THE TSO OF THE OVERHAULED COMPONENTS IS 295.9 HOURS (TC NR 20060725005) 1G71 3U3 U H9EU E19EU 20060814000982006081400098GL 2006 8 14 CA060725006 220060724G732323076061 GOVERNOR BELL 206 206B 1181511SW ALLSN 250C 250C20 03013GL INOPERATIVE W O OTHER RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 1 CA 372 (CAN) UNIT HAD ABOUT 25.0 HOURS THIS INSTALL. PILOT REPORTED THAT GOVERNOR WOULD BLEED OFF IN FLIGHT BY 4 TO 5 PERCENT THEN COME BACK TO NORMAL AFTER A FEW SECOND 10 TO 15 SECONDS. THEN IT WOULD BE FINE FOR SOME TIME. UPON REPORTING THIS THE AIRCRAFT WAS REMOVED FROM SERVICE AND A NEW GOVERNOR WAS INSTALLED. (TC NR 20060725006) 1G71 3U3 U H2SW E4CE 20060926001692006092600169WP 2006 9 26 CA060725007 120060725G7820C16932 MUFFLER ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE EXHAUST CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 398 (CAN) DURING A ROUTINE 100 HR INSPECTION, IT WAS NOTED THAT THE MUFFLER/TAILPIPE ASSY WAS DISTORTED AND CRACKED AT THE OUTLET PIPE. THE CRACK WAS NOTICED AFTER THE CABIN HEATER JACKET WAS REMOVED. THE CRACK WOULD NOT BE NOTICEABLE WITH THE CABIN HEATER JACKET INSTALLED. THE CABIN CARBON MONOXIDE DETECTOR SYSTEM SHOWED NO INDICATIONS OF EXCESSIVE CARBON MONOXIDE. IT IS NOTED THAT IF THE AIRCRAFT WAS FLYING IN COLD CONDITIONS, WHERE THE CABIN HEAT WOULD BE SELECTED (TC NR 20060725007) 1G71 3O3 O H11NM 1E4 20060926001712006092600171WP 2006 9 26 CA060725009 120060720G2120D0571 AIR BOX ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE OUTER HOUSING CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 398 (CAN) DURING A ROUTINE 100 HR INSPECTION, A CRACK WAS NOTICED IN THE ABOVE PART. THERE IS A CHANCE THAT THE CRACK COULD BE THE RESULT OF CLEARANCE ISSUES WHEN REMOVING AND INSTALLING THE AIRBOX FROM THE AIRFRAME. THE PART WAS REPLACED WITH A NEW PART, AND IT WAS NOTED THAT THE NEW PART IS NOW MADE FROM FIBERGLASS, WHERE THE ORIGINAL PART IS MADE FROM A PLASTIC MATERIAL. THIS COULD ALSO BE ANOTHER REASON FOR THE CRACK, OR AN ATTRIBUTE. THE PART HAS 398.6 HRS SINCE NEW. THE AIRCRAFT WAS MANUFACTURED NEW IN OCTOBER 2005. (TC NR 20060725009) 1G71 3O3 O H11NM 1E4 20060926001722006092600172EA 2006 9 26 CA060725010 220060723G8530416453 PUSHROD GRUMANTS2 TS2ACALFORST3951102WP WRIGHTR1820 982C9HE2 67020EA HAMSTD43D 43D51 NE ENGINE BROKEN W E ENGINE SHUTDOWN RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 1 CA 500 (CAN) PUSHROD BROKE AT TOP BALLEND AT ROCKER ARM ON NR 1 CYLINDER EXHAUST VALVE. PUSH ROD REPLACED AND ENGINE GROUND RUN, CHECKED OK. AIRCRAFT TEST FLOWN AND FOUND SATISFACTORY (TC NR 20060725010). 2H72 4R4 R A25WE E259 6 CP8879 20060814001242006081400124NE 2006 8 14 CA060726001 220060720G7421955075400 IGNITER SNIAS 350 AS350BA 8680817EU TMECA ARRIELARRIEL1B 6OO30NE ENGINE LOOSE W K NONE O OTHER ININSP/MAINT 1 CA 515 4396 (CAN) INSULATION WITHIN IGNITOR FOUND LOSE. IN LIGHT OF PAST INCIDENCE OF ENGINE FOD, IGNITORS WERE CHANGED. IGNITOR P/N 955075400/CH34745 (TC NR 20060726001) 1G71 3U3 UNCH9EU E19EU 20060814001092006081400109NE 2006 8 14 CA060726002 220060711G72502292253850 TURBINE BLADES SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1D1 NE 1ST STAGE FAILED W K NONE O OTHER ININSP/MAINT 1 CA 254 254 (CAN) THE PILOT SHUTDOWN THE AIRCRAFT TO HOOK UP HIS WATER BUCKET, AFTER A SHORT TIME PERIOD OF APPROXIMATE 8 TO 10 MINUTES HE ATTEMPTED TO RESTART THE AIRCRAFT. THE STARTER WOULD NOT TURN THE ENGINE, A BORESCOPE WAS USED TO LOOK INSIDE THE ENGINE AND FOUND THAT THE 1ST STAGE TURBINE BLADE HAD RUBBED. THE M03 WAS THEN REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. (TC NR 20060726002) 1G71 3U3 U H9EU E19EU 20060926001742006092600174EU 2006 9 26 CA060726003 120060725G631035013001 FREEWHEEL UNIT SNIAS 350 AS350* EU ALLSN 250C 250C30 03013GL MAIN ROTOR MAKING METAL W K NONE O OTHER ININSP/MAINT 1 CA 5074 61 (CAN) AFTER INSTALLING A OVERHAULED FREEWHEEL, METAL WAS FOUND FOUR SEPARATE TIME IN 61.1 HOURS, SILVER FLAKES FOUND ON CHIP PLUG. (TC NR 20060726003) 1G71 3U3 U H9EU E1GL 20060926001772006092600177NM 2006 9 26 CA060726004 120060726G271082742409001 CONTROL UNIT BOMBDRDHC8 DHC8402 1390042NM PWC 150 PW150A EA ROTOL R408 CR4086123F17EU AILERONS WORN W O OTHER W INADEQUATE Q C NRNOT REPORTED 1 CA 1350 (CAN) RT AILERON CABLES PN: 82742409-001 ( WS Y14.25-Y232.00) AND CABLE PN: 82742410-001 (WS Y14.25-Y258.00) WERE APPROACHING PERMISSIBLE WEAR LIMITS AT PULLEY CONTACT AREAS. CABLES REPLACED THIS PROBLEM IS ALREADY KNOWN BY MFG REF TO ALL OPERATOR MESSAGE NR AOM 122 AND SB 84-27-26. INSPECTED THE A/C IN APRIL 2004 FOLLOWING RECEPTION OF AOM122 AND AILERON CABLES REPLACED DUE FOUND WORN. WE ALSO REINSPECTED THE A/C IN MAY 2005 FOLLOWING RECEPTION OF THE S/B 84-27-26 AND AILERON CONTROL CABLES REPLACED AGAIN DUE STILL FOUND WORN. IN JULY 2006 DURING A FLAP INSPECTION OUR AME (KNOWING THE AILERON CONTROL CABLE PROBLEMS) WIPE THE AILERON CABLES WITH A RAG TO FOUND THAT SOME WIRES WERE BROKEN. THESE CABLES MU2H72 4T4 TRTA13NM E00062EN6 CP17BO 20060808000912006080800091EA 2006 8 8 CA060726005 220060724G7261ES48110 OIL FILTER PIPER PA31 PA31 7103102SO LYC O540 TIO540A2B 41532EA HARTZLHCE2Y HCE2YR2 GL ENGINE LEAKING W K NONE O OTHER ININSP/MAINT 1 CA RL103161 (CAN) DURING POST RUN UP INSPECTION OF REGULAR INSPECTION APPROXIMATE ONE FLUID OZ OF OIL WAS NOTED LEAKING FROM THE NEWLY INSTALLED OIL FILTER. IT IS SUSPECTED THAT A SIMILAR DEFECT BUT OF LESSER DEGREE MAY NOT BE PICKUP BY POST RUN UP INSPECTION AND MAY CAUSE A FINE OIL MIST ON HOT TURBO CHARGER AND EXHAUST PARTS ON THIS AND SIMILAR ENGINE INSTALLATIONS. (TC NR 20060726005) 1L72 3O3 O A20SO E14EA 5 CP9EA 20060808000922006080800092CE 2006 8 8 CA060726006 120060726G8011EBB124A DRIVE ASSY PRESTOLITE CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA SNSNCH72C 72CK EA STARTER BROKEN W K NONE O OTHER ININSP/MAINT 1 CA 1102 E042509 (CAN) PILOT TRIED TO START ENGINE BUT THE STARTER WOULD NOT ENGAGE. AIRCRAFT BROUGHT INTO HANGER AND STARTER WAS REMOVED FROM ENGINE. IT WAS DISCOVERED THAT THE TEETH ON THE BENDIX DRIVE THAT ENGAGE THE RING GEAR HAD SHEARED OFF. (TC NR 20060726006) 1H71 3O3 ONT3A19 E223 5 NP9045 20060926001792006092600179CE 2006 9 26 CA060726007 120060724G2435230760011 BRUSHES LEARSIEGLER CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE STARTER GEN WORN W O OTHER O OTHER NRNOT REPORTED 1 CA 3 2004 (CAN) DURING BASE INSPECTION, LT ENGINE COWL WAS COVERED WITH BLACK DUST. UPON FURTHER INSPECTION THE STARTER/GEN WAS REMOVED AND THE BRUSHES INSPECTED TO BE WORN OVER HALF LIFE. STARTER/GEN HAD ONLY 2.7 HRS SINCE OVERHAUL. STARTER/GEN SENT FOR WARRANTY AND TEARDOWN REPORT. (TC NR 20060726007) 1L72 4F4 F A22CE E1NE 20060926001812006092600181SW 2006 9 26 CA060727001 120060727G6220204011116001 NUT BELL BELL 205 205A1 1181414SW LYC T53 T5317A 41549NE M/R HUB CRACKED W K NONE O OTHER ININSP/MAINT 1 CA ADA50015 (CAN) THIS IS AN ON CONDITION ITEM. SO HISTORY MAY NOT BE ACCURATE. M/R HUB ASSY HAS 18437.6 TIME SINCE NEW. M/R HEAD ASSY WAS IN FOR O/H AND REQUIRES ACORN NUTS TO BE NDT. THIS ONE WAS FOUND CRACKED. (TC NR 20060727001) 1G71 4U4 U H1SW E17EA 20060926001832006092600183SW 2006 9 26 CA060728001 120060711G2910206076437003 CHECK VALVE BELL 412 412EP 1182205SW PWA PT6T PT6T3 52045EA HYD SYS 2 JAMMED W O OTHER MJ OVER TEMP WARNING INDICATION TXTAXI/GRND HDL 1 CA (CAN) UPON FIRST GROUND RUN OF M412 DURING MANUFACTURING FTP`S (WITHOUT M/R BLADES INSTALLED), A NOISE (BANG) WAS HEARD TWICE AND HYDR PRESSURE RAISED TO +1300 PSI ON THE GAGE. PILOT SHUTDOWN THE HYDR SYSTEM AND ABORTED GROUND RUN FOR INVESTIGATION. FURTHER INVESTIGATION REVEALED THAT A SWIRL OF COPPER METAL (CHIPS) JAMMED THE HYDRAULIC CHECK VALVE IN AN OPEN POSITION WHICH ALLOWED REVERSED FLOW AND AN HYDR LOCK BY PRESSURIZING THE PUMP CASE DRAIN, FOLLOWED BY A TEMPERATURE RISE. HYDRAULIC COMPONENTS REPLACED AND AIRCRAFT RETURNED TO SERVICE. FURTHER LAB TESTING WERE ABLE TO REPRODUCE THE PROBLEM AND TEMPERATURE WAS TWICE THE NORMAL RANGE WITHIN 4 MIN. OF OPERATION. THE SOURCE OF THE DEBRIS WAS NOT FOUND COULD1G72 4U4 U H4SW E22EA 20060926001862006092600186NM 2006 9 26 CA060728002 120060725G5270 SWITCH BOEING727 727225 1384077NM PWA JT8 JT8D15A 52051NE CARGO DOOR OUT OF RIG W JA DUMP FUEL UNSCHED LANDING N FALSE WARNING CLCLIMB 1 CA (CAN) DURING CLIMB THROUGH FL210 AND 6.0 PSID CABIN DIFFERENTIAL THE CARGO DOOR UNSAFE LIGHT INDICATION ILLUMINATED. AIRCRAFT DUMPED FUEL AND RETURNED TO STATION, DURING APPROACH THE CARGO DOOR UNSAFE LIGHT EXTINGUISHED. UPON INSPECTION MAINTENANCE FOUND DOOR CLOSE MICRO SWITCH OUT OF RIG. SWITCH ADJUSTED IAW AEI MM CHAPTER 24 PAGE 26. CONTRIBUTING FACTORS: PRIOR TO DEPARTURE THE AIRCRAFT WAS UNDERGOING THE INCORPERATION OF SB AEI 04-02 REV 1R. CLARIFICATION OF RIGGING PROCEDURES WAS REQUESTED FROM AEI. (TC NR 20060728002) 2L73 4F4 F A3WE E2EA 20060926001872006092600187SW 2006 9 26 CA060728003 120060714G65102040406009 BEARING BELL BELL 205 205A1 1181414SW LYC T53 T5313B 41549NE TAIL ROTOR DRIVEFAILED W C ABORTED TAKEOFF DF INFLIGHT SEPARATION FLT CONT AFFECTED TOTAKEOFF 1 CA A2079238 (CAN) THE TAIL ROTOR DRIVESHAFT HANGER HAD BEEN INSTALLED THE NIGHT BEFORE THE FAILURE. WE SUSPECT AN INNER COUPLING FAILURE. THE SUSPECT COUPLING HAD BEEN RECOATED JUST BEFORE INSTALLATION BY USING AN AMS2451/4 PROCESS. (TC NR 20060728003) 1G71 4U4 U H1SW E17EA 20060808000952006080800095NE 2006 8 8 CA060728004 220060727G7230 FAN BLADE CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE ENGINE DISAPPEARED W EFA ENGINE SHUTDOWN ACTIVATE FIRE EXT. UNSCHED LANDING ERJVIBRATION/BUFFET PARTIAL RPM/PWR LOSS WARNING INDICATION CLCLIMB 1 CA 10896 873549 (CAN) DURING CLIMB OUT AT 18,000FT, THE COCKPIT CREW HEARD A LOUD BANG, FOLLOWED BY HIGH VIBES ON THE NR 1 ENGINE. FIRE WARNING CAME UP, PILOT DISCHARGED THE FIRE BOTTLES AND SHUTDOWN THE ENGINE. EMERGENCY WAS DECLARED AND AIRCRAFT RETURNED TO BARCELONA, WHERE IT PERFORMED AN UNEVENTFULL SINGLE-ENGINE LANDING. INITIAL REPORT SAYS ONE FAN BLADES DISAPPEARED, JET PIPE IS BURNED AND CRACKED. FURTHER INFORMATION WILL BE PROVIDED ONCE THE ENGINE STRIP REPORT IS AVAIALBLE. (TC NR 20060728004) 2L72 4F4 FRTA21EA E15NE 20060926001882006092600188 2006 9 26 CA060728005 420060721G23128992125014 CONTROL PANEL AIRBUS310 A310300 3930305EU GE CF6 CF680C2* GL VHF SMOKE W H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 1 CA 2410124101 4520 (CAN) DURING FLIGHT, LIGHT SMOKE CAME FROM THE NR 1 VHF CONTROL PANEL. THE CIRCUIT BREAKER WAS PULLED AND THE FLIGHT PROCEEDED WITHOUT ANY FURTHER PROBLEM. THE PANEL WAS REPLACED AT THE ARRIVAL STATION AND WAS SYSTEM CHECKED SERVICEABLE. PANEL WAS ROUTED TO THE VENDOR FOR INVESTIGATION. (TC NR 20060728005) 2L72 4F4 FRTA35EU E23EA 20060808000962006080800096NE 2006 8 8 CA060728006 220060722G7261 ENGINE CNDAIRCL601 CL6012A12 1900303EA GE CF34 CF343B1 NE RIGHT OIL CONSUMPTION W E ENGINE SHUTDOWN KJ FLUID LOSS WARNING INDICATION CRCRUISE 1 CA (CAN) AIRCRAFT HAD TO SHUTDOWN THE RT ENGINE DURING FLIGHT, DUE TO LOW OIL PRESSURE. APPROX 3 HOURS INTO THE FLIGHT, THE PILOT REPORTED THE OIL PRESSURE WAS FLUCUTATING BETWEEN 45 AND 65 PSI, THEN DROPPED AGAIN TO 35 AND 55 PSI, AND FINALLY GOT A STEADY LOW OIL PRESSURE LIGHT. THIS IS WHEN THE PILOT SHUTDOWN THE RT ENGINE, AND DIVERTED. AN INSPECTION REVEALED THE RT ENGINE WAS 4 QTS LOW ON OIL. THE PILOTS HAD ALREADY SERVICED THIS ENGINE WITH 2 QTS, PRIOR TO LEAVING. APPEARS THE AIRCRAFT USED 4 QTS OF OIL IN THAT 3 HOUR PERIOD. AN OIL CONSUMPTION CHECK WAS PERFORMED, AND WAS FOUND TO BE WITHIN LIMITS. THE AIRCRAFT IS UNDERGOING FURTHER TROUBLESHOOTING. (TC NR 20060728006) 2L72 4F4 FRTA21AE E15NE 20060808000972006080800097WP 2006 8 8 CA060728007 220060727G7200 ENGINE DHAV DHC3 DHC3 2800202EA GARRTTTPE331TPE33110R 0517 WP HARTZLHCB4T HCB4TN5 GL VIBRATES W E ENGINE SHUTDOWN E VIBRATION/BUFFET DEDESCENT 1 CA (CAN) DURING DESCENT FOR FLOAT LANDING ON WATER, PILOT NOTICED VIBRATION IN ENGINE . ENGINE SHUTDOWN, PROP FEATHERED. AIRCRAFT LANDED WITHOUT INCIDENT. ENGINE REMOVED SENT TO REPAIR FACILITY. (TC NR 20060728007) 1H71 3R4 T A815 E4WE 6 CP40EA 20060808000982006080800098EA 2006 8 8 CA060729001 120060724G5610NP1393226 WINDOW CNDAIRCL600 CL6002C10 1390015EA GE CF34 CF348C1 NE COCKPIT CRACKED W O OTHER O OTHER APAPPROACH 1 CA 8565 (CAN) DESENDING THROUGH 13000 FT - F/O SIDE WINDOW CRACKED. TAXING TO GATE WINDOW (F/O SIDE WINDOW) CRACKED MORE. WINDOW WAS REPLACED IAW AMM. SIDE WINDOW IS PRE SB NP139322-001 (TC NR 20060729001) 2L72 4F4 FRTA21EA EOOO63EN 20060808000992006080800099CE 2006 8 8 CA060731001 120060727G2720656530129 GUARD CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE RUDDER CONTROL DELAMINATED W K NONE O OTHER ININSP/MAINT 1 CA 7217 (CAN) WHEN MOVING THE RUDDER WITH HAND PRESSURE OF APPROXIMATELY 10 DEGREES EITHER SIDE OF CENTER A NOISE ALONG WITH A ROUGH SNAGGING FEEL NOTICED. TRACING THE NOISE DOWN THROUGH THE TAIL INTO THE CABIN BETWEEN FLIGHT STATION 166 TO 180. THE CABLE GUARD PN 6565301-29 FOUND TO BE DISPLACED FORWARD OUT OF REAR CLAMP AND CABLE END CONTACTING THE END OF THE CABLE GUARD. THE CABLE GUARD WAS REMOVED AND INSPECTED, FOUND INNER LAMINATE OF THE PHENOLIC DELAMINATED WITH WHAT LOOKED LIKE A CONTACT POINT FROM CONTACT WITH THE CABLE END OR TURN BARREL NEAR THE FWD END AND THE GUARD WAS DAMAGED ON THE AFT END FROM CONTACT WITH THE CABLE END. (TC NR 20060731001) 1L72 4F4 F A22CE E1NE 20060926001912006092600191EA 2006 9 26 CA060731002 220060713G7210310152501 PLANETARY GEAR BEECH 99 99 1154002CE PWA PT6 PT6A28 EA HARTZLHCB3T HCB3TN3 GL ENGINE MAKING METAL W A UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 CA 184 PCE41483 (CAN) METAL CONTAMINATION WAS FOUND ON THE CHIP DETECTOR. METAL ORIGINATED FROM RGB AND WAS THE RESULT OF SIGNIFICANT MATERIAL LOSS BETWEEN THE 1ST STAGE SUN GEAR AND THE 1ST STAGE PLANETARY GEARS. THIS IS OUR 2ND SUCH CASE WITH TIME CONTINUED GEARS. (TC NR 20060731002) 1L72 3T4 T A14CE E4EA 6 CP15EA 20060808001002006080800100EA 2006 8 8 CA060731003 220060728G852013828 CRANKCASE PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA HARTZLHCE3Y HCE3YR2A GL ENGINE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 517 L57468A (CAN) DURING A ROUTINE INSPECTION AN AME VISUALLY DISCOVERED A CRACK 2-3 INCHES IN LENGTH. THE CRACK IS LOCATED BETWEEN CYLINDERS 3 AND 5 IN THE VICINITY OF THE LOWER RIB. PREVIOUSLY NO DISCREPANCIES HAD BEEN NOTED. THE ENGINE WAS SUBSEQUENTLY REMOVED FOR REPAIR AT AN APPROVED ENGINE OVERHAUL SHOP. THE TTSN FOR THIS CASE COULD NOT BE OBTAINED. THIS CASE WAS INSTALLED 516.8 HRS EARLIER BECAUSE OF ANOTHER INCIDENT OF CRACKED CASE. 1L72 3O3 O A20SO E14EA 5 CP33EA 20060926001952006092600195CE 2006 9 26 CA060731005 120060728G7714991214736 INDICATOR CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE N2 SPEED SHORTED W K NONE N FALSE WARNING ININSP/MAINT 1 CA (CAN) DURING TROUBLESHOOTING OF A POSSIBLE N2 OVERSPEED OF BOTH ENGINES, THE N2 GAGE WAS TESTED BY SIMULATING SPEEDS WITH VOLTAGE AT SEVERAL FREQUENCIES. WHEN VALUES WERE BROUGHT AT LEVELS TO ILLUMINATE THE RED OVERSPEED WARNING LIGHT, IT WAS NOTED THAT THE INDICATION WAS CROSSED MEANING THAT FOR A READING OF 96 PERCNET N2 AND ABOVE ON LT ENGINE THE RT WARNING LIGHT IN THE GAGE ILLUMINATES. THE REVERSE CONDITION HAPPENS WHEN THE RT ENGINE INDICATION IS TESTED (N2 READING), MEANING THAT THE LT INDICATION (RED WARNING LIGHT) ILLUMINATES. THE SUSPECT GAUGE WAS REPLACED AND THE SYSTEM GROUND CHECKED SERVICEABLE. (TC NR 20060731005) 1L72 4F4 F A22CE E1NE 20060814001102006081400110NE 2006 8 14 CA060731006 220060628G73203031829 LINE AIRTRCAT802 AT802 0390305SW PWA PT6 PT6A67A 52043NE HARTZLHCB5M HCB5MA3 GL P3 AIR TUBE FRACTURED W A UNSCHED LANDING XJ ENGINE FLAMEOUT WARNING INDICATION APAPPROACH 1 CA (CAN) THE ENGINE WAS REPORTED TO FLAME OUT DURING APPROACH RESULTING IN THE AIRCRAFT LANDING SHORT OF THE RUNWAY. SUBSEQUENT INSPECTION REVEALED A FRACTURED P3 PNEUMATIC LINE TO THE FUEL CONTROL. MFG WILL MONITOR INVESTIGATION AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060731006) 1L71 3T4 TNCA19SW E26NE 6 CP44GL 20060814001122006081400112EA 2006 8 14 CA060731007 220060629G7261 OIL SYSTEM DHAV DHC6 DHC6300 2802606EA PWA PT6 PT6A27 52043EA ENGINE LEAKING W EA ENGINE SHUTDOWN UNSCHED LANDING KRJFLUID LOSS PARTIAL RPM/PWR LOSS WARNING INDICATION CLCLIMB 1 CA 41601 (CAN) DURING CLIMB, ENGINE OIL PRESSURE WAS REPORTED TO FLUCTUATE FOLLOWED BY A LOSS IN OIL PRESSURE. THE ENGINE WAS SHUTDOWN IN FLIGHT AND THE AIRCRAFT RETURNED TO POINT OF DEPARTURE. SUBSEQUENT INSPECTION REVEALED INTERNAL OIL LEAKAGE. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060731007) 1H72 3T4 TRTA9EA E4EA 20060814001132006081400113NE 2006 8 14 CA060731008 220060705G7321 FUEL CONTROL CESSNA500 550 2076604CE PWA 530 PW530A NE ENGINE UNSERVICEABLE W O OTHER XJ ENGINE FLAMEOUT WARNING INDICATION APAPPROACH 1 CA (CAN) THE ENGINE WAS REPORTED TO FLAME OUT ON APPROACH. THE FUEL CONTROL UNIT WAS SUBSEQUENTLY REPLACED. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060731008) 1L72 4F4 F A22CE E00053EN 20060814001142006081400114NE 2006 8 14 CA060731009 220060704G7250 TURBINE BLADES AYRES S2T STRT34 0970106SO PWA PT6 PT6A34AG 52053NE ENGINE FRACTURED W A UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 1 CA PH0243 (CAN) THE ENGINE WAS REPORTED TO LOSE ALL POWER IN CRUISE. A DEAD-STICK LANDING WAS PERFORMED IN A FIELD RESULTING IN AIRFRAME DAMAGE. SUBSEQUENT INSPECTION REVEALED FRACTURED POWER TURBINE BLADES. MFG WILL INVESTIGATE AND ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC NR 20060731009) 1L71 3T4 T A3SW E4EA 20060814000662006081400066EA 2006 8 14 CA060731010 220060705G7200 ENGINE BELL 412 412 1182202SW PWA PT6T PT6T3 52045EA MAKING METAL W O OTHER XJ ENGINE FLAMEOUT WARNING INDICATION HOHOVERING 1 CA (CAN) THE ENGINE WAS REPORTED TO LOSE POWER IN HOVER ACCOMPANIED BY A CHIP DETECTOR INDICATION. SUBSEQUENT INSPECTION REVEALLED LOSS OF DRIVE TO THE ACCESSORY GEARBOX. MFG WILL MONITOR INVESTIGATION AND ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC NR 20060731010) 1G72 4U4 U H4SW E22EA 20060814000672006081400067EA 2006 8 14 CA060731011 220060704G7200 ENGINE DHAV DHC7 DHC7103 2802710EA PWA PT6 PT6A50 52043EA HAMSTD24PF 24PF305 GL MALFUNCTIONED W C ABORTED TAKEOFF B SMOKE/FUMES/ODORS/SPARKS TOTAKEOFF 1 CA 86312 (CAN) ON TAKEOFF ROLL THE ENGINE EMITTED A LOUD NOISE AND SMOKE WAS SEEN EMERGING FROM THE EXHAUST. TAKEOFF WAS ABORTED AND THE ENGINE SECURED. MFG WILL MONITOR INVESTIGATION OF THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC NR 20060731011) 2H74 4T4 T A20EA E4EA 6 CP1NE 20060809001962006080900196NE 2006 8 9 CA060731012 220060710G7230 DIFFUSER AEROSPATR72 ATR72212A 8680902EU PWA PW120 PW127 NE LOW COMPRESSOR FRACTURED W C ABORTED TAKEOFF J WARNING INDICATION TOTAKEOFF 1 CA (CAN) DURING TAKEOFF ROLL, ENGINE TEMPERATURE WAS SEEN EXCEEDING LIMITS AND THE TAKE-OFF WAS ABORTED. SUBSEQUENT INSPECTION REVEALED A FRACTURED LOW PRESSURE DIFFUSER TUBE. THE TUBE WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. (TC NR 20060731012) 2H72 4T4 TRTA53EU E20NE 20060809001972006080900197EA 2006 8 9 CA060731013 220060712G7230 COMPRESSOR BEECH 1900 1900C 1154161CE PWA PT6 PT6A65B 52043EA ENGINE SEIZED W E ENGINE SHUTDOWN BXJSMOKE/FUMES/ODORS/SPARKS ENGINE FLAMEOUT WARNING INDICATION CRCRUISE 1 CA (CAN) DURING FLIGHT AN OIL SMELL WAS REPORTED IN THE COCKPIT. THE ENGINE SUBSEQUENTLY SURGED ACCOMPANIED BY A LOW OIL PRESSURE WARNING AND WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED OIL LEAKAGE AND A PARTIALLY SEIZED HIGH PRESSURE COMPRESSOR. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060731013) 2L72 4T4 TRTA24CE E4EA 20060809001982006080900198EA 2006 8 9 CA060731014 220060714G7320312241908 METERING UNIT BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA ENGINE MALFUNCTIONED W E ENGINE SHUTDOWN RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 1 CA (CAN) DURING CRUISE, THE AIRCRAFT YAWED ACCOMPANIED BY A LOSS IN ENGINE TORQUE. THE ENGINE WAS SHUTDOWN IN FLIGHT. THE FUEL METERING UNIT WAS SUBSEQUENTLY DETERMINED TO BE UNSERVICEABLE AND WAS REPLACED. (TC NR 20060731014) 2H72 4T4 TRTA13NM E00062EN 20060809001992006080900199EU 2006 8 9 CA060731015 120060716G7712311629401A LIMITER PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL TORQUE MALFUNCTIONED W O OTHER F FLT CONT AFFECTED DEDESCENT 1 CA (CAN) IN DESCENT THE ENGINE WOULD NOT RESPOND TO THROTTLE INPUT. THE MANUAL FUEL CONTROL OVER-RIDE WAS ENGAGED, AN EMERGENCY DECLARED AND THE AIRCRAFT LANDED WITHOUT INCIDENT. THE ENGINE TORQUE LIMITER WAS SUBSEQUENTLY DETERMINED TO BE FAULTY AND WAS REPLACED. (TC NR 20060731015) 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20060810000202006081000020NE 2006 8 10 CA060731016 220060525G7250 TURBINE BLADES CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE ENGINE FRACTURED W A UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 1 CA PC0951 (CAN) DURING CRUISE THE ENGINE EMITTED A NOISE ACCOMPANIED BY AN UNCOMMANDED REDUCTION IN POWER. THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE. SUBSEQUENT INSPECTION REVEALED A FRACTURED POWER TURBINE BLADE. MFG WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060731016) 1H71 3T3 T A37CE E4EA 20060810000212006081000021NE 2006 8 10 CA060731017 220060719G7200 ENGINE BELL 212 212 1181420SW PWA PT6T PT6T3B 52045NE MAKING METAL W EA ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 CA 63196 (CAN) THE ENGINE EMITTED A NOISE IN FLIGHT ACCOMPANIED BY A RISE IN ITT TEMPERATURE. THE ENGINE WAS SHUTDOWN AND AN UNSCHEDULED LANDING CARRIED OUT. SUBSEQUENT INSPECTION REVEALED METAL DEBRIS IN THE EXHAUST. MFG WILL MONITOR THE INVESTIGATION OF THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC NR 20060731017) 1G71 4U4 U H4SW E22EA 20060810000222006081000022NE 2006 8 10 CA060731018 220060711G7200 ENGINE AYRES S2 S2RT34NORMAL0970106SO PWA PT6 PT6A34AG 52053NE VIBRATES W A UNSCHED LANDING ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CRCRUISE 1 CA PH0054 (CAN) DURING FLIGHT THE ENGINE WAS REPORTED TO LOSE POWER ACCOMPANIED BY HEAVY VIBRATIONS. A FORCED LANDING WAS CARRIED OUT RESULTING IN AIRFRAME DAMAGE. MFG WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060731018) 1L71 3T4 T A3SW E4EA 20060810000232006081000023NE 2006 8 10 CA060731019 220060722G7200 ENGINE BELL 212 212 1181420SW PWA PT6T PT6T3B 52045NE FLAMED OUT W A UNSCHED LANDING XJ ENGINE FLAMEOUT WARNING INDICATION CLCLIMB 1 CA (CAN) FOLLOWING TAKE-OFF THE ENGINE EMITTED A NOISE AND FLAMED OUT. SUBSEQUENT GROUND INSPECTION REVEALED EXERNAL OIL LEAKAGE. MFG WILL MONITOR INVESTIGATION OF THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060731019). 1G71 4U4 U H4SW E22EA 20060814000682006081400068NE 2006 8 14 CA060731020 220060722G7320 HMU DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE ENGIEN MALFUNCTIONED W EA ENGINE SHUTDOWN UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CLCLIMB 1 CA 120282 (CAN) DURING TAKE-OFF ROLL THE ENGINE MASTER CAUTION WARNING ANNUNCIATED. IN CLIMB, ENGINE TORQUE REDUCED UNCOMMANDED AND THE ENGINE WAS SHUTDOWN IN FLIGHT. THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE. THE ELECTRONIC AND HYDROMECHANICAL FUEL CONTROLS WERE SUBSEQUENTLY REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060731020) 2H72 4T4 TRTA13NM E20NE 20060810000242006081000024NE 2006 8 10 CA060731021 220060727G7200 ROTOR UROCOPEC135 EC135P1 8680990EU PWA PW206 PW206B 0 NE ENGINE SEIZED W A UNSCHED LANDING EJ VIBRATION/BUFFET WARNING INDICATION CLCLIMB 1 CA BB0122 (CAN) DURING CLIMB THE ENGINE ELECTRONIC CONTROL REVERTED TO MANUAL AND THE PILOT ELECTED TO LAND. ON DESCENT THE AIRCRAFT BEGAN TO VIBRATE AND THE PILOT AUTOROTATED. SUBSEQUENT INSPECTION REVEALED DAMAGE TO ENGINE REAR MOUNT AND ROTOR SEIZURE. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060731021) 1G72 3U3 UO H88EU E42NE 20060810000252006081000025EA 2006 8 10 CA060731022 220060720G7250 TURBINE BLADES BEECH 1900 1900C 1154161CE PWA PT6 PT6A65B 52043EA ENGINE FRACTURED W EA ENGINE SHUTDOWN UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CLCLIMB 1 CA 3200832167 (CAN) FOLLOWING TAKEOFF THE ENGINE EMITTED A NOISE ACCOMPANIED BY AN UNCOMMANDED REDUCTION IN POWER. THE ENGINE WAS SHUT DOWN IN FLIGHT AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE. SUBSEQUENT INSPECTION REVEALED FRACTURED POWER TURBINE BLADES. MFG WILL MONITOR INVESTIGATION OF THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC NR 20060731022) 2L72 4T4 TRTA24CE E4EA 20060810000262006081000026NE 2006 8 10 CA060801001 220060604G7250 TURBINE BLADES BOEING717 717200 1383700NM RROYCEBR700 BR700715A130 NE ENGINE DAMAGED W C ABORTED TAKEOFF MT OVER TEMP ENGINE CASE PENETRATION TOTAKEOFF 1 CA 13266 (CAN) ON INITIAL TAKEOFF ROLL, ENGINE 13266ON A/C 477-1 SURGED AND EXPERIENCED A BRIEF OVER TEMPERATURE. MAX TGT WAS 903 DEG C FOR LESS THAN A FEW SECONDS. METAL IN TAIL PIPE WAS FOUND AS WELL AS A HOLE IN THE HP T CASE. ENGINE IS UNDER INVESTIGATION AT RRC. FURTHER DETAIL WILL BE SUBMITTED WHEN AVAILABLE. (TC NR 20060801001) 2L72 4F4 FTRA6WE E00061EN 20060926001962006092600196EA 2006 9 26 CA060801003 120060713G3320BR90002 BALLAST CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE CABIN LIGHTS ODOR W K NONE B SMOKE/FUMES/ODORS/SPARKS ININSP/MAINT 1 CA (CAN) DURING PASSENGER BOARDING AND UPON ENTRY TO FLIGHT DECK A STRONG ELECTRICAL SMELL WAS APPARENT AND PROGRESSIVELY GOT WORSE. PASSENGERS WERE DE-PLANED. LINE MAINTENANCE CREW FOUND FORWARD BOARDING LIGHT BALLAST P/N BR9000-2 BURNED. THE BURNED BALLAST WAS REPLACED, GROUND CHECKS PERFORMED AND AIRCRAFT RETURNED TO SERVICE. AIRFRAME HOURS WERE 25426:25 AND CYCLES WERE: 20767. (TC NR 20060801003) 2L72 4F4 FRTA21EA E15NE 20061018000772006101800077SW 2006 10 18 CA060801004 120060722G5302206031329103S FITTING BELL 206 206B 1181511SW ALLSN 250C 250C20 03013GL TAIL BOOM CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 16806 (CAN) A CRACK WAS FOUND FROM THE AFT TOP RIVET HOLE. THE CRACK STARTS AT THE TOP OF THE FITTING AND TRAVELS DOWNWARD THROUGH THE RIVET HOLE AND APPROXIMATELY .2500 FURTHER. (TC NR 20060801004) 1G71 3U3 U H2SW E4CE 20060926001982006092600198NM 2006 9 26 CA060801005 120060412G291082950010141 LINE DHAV DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE HYDRAULIC SYS RUPTURED W A UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CLCLIMB 1 CA 36205 (CAN) AFTER TAKEOFF NR 1 RUDDER FULL PRESSURE AND ROLL SPOILER IB HYDRAULIC CAUTION LIGHT ILLUMINATED. CREW DECLARED EMERGENCY RETURNED TO AIRFIELD. MAINTENANCE REMOVED FLAP WELL PANEL 532AB AND FOUND AREA UNDER PANEL WAS CHARRED FROM FIRE. FIRE WAS HOT ENOUGH TO RUPTURE TWO HYDRAULIC LINES, MELTED SPACER BLOCKS AND MELTED PLASTIC ON WIRE BUNDLE. (TC NR 20060801005) 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20060926002002006092600200EU 2006 9 26 CA060801007 120060731G2197 WIRE AIRBUSA340 A340* EU RROYCERB211 RB211* 54555NE CARGO FAN BURNED W K NONE B SMOKE/FUMES/ODORS/SPARKS ININSP/MAINT 1 CA (CAN) (FWD CARGO VENT FAULT) DISPLAYED ON ECAM. TROUBLESHOOTING IDENTIFIED BURNED WIRING UNDER FWD CARGO FLOOR, APPROX 2 IN FROM ELECTRICAL CONNECTOR 285HN-A ON FWD CARGO EXTRACTION FAN. BURNED WIRES WERE LOCATED BETWEEN SUPPORT STANDOFFS WITH NO EVIDENCE OF CHAFFING. WIRING REPAIRED IAW ESPM, REPLACED FWD CARGO EXTRACT FAN. (TC NR 20060801007) 2L74 4F4 FRTA197 A12EU 20060926002022006092600202NM 2006 9 26 CA060801008 120060708G5753734187B TORQUE TUBE DHAV DHC8 DHC8101 2809002NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE TE FLAPS CHAFED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING A LINE MAINTENANCE WALK-AROUND CHECK, AN ENGINEER FOUND THAT THE LT WING FLAP IB (SECTION BETWEEN NACELLE AND FUSELAGE) TORQUE TUBE HAS BEEN CHAFED THROUGH IN ONE SPOT BY ITS RETAINING BRACKET. TORQUE TUBE ASSY PN REPLACED WITH SERVICEABLE ASSY FUNCTIONAL TEST COMPLETED ON FLAP SYSTEM AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20060801008) 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20060926002032006092600203NM 2006 9 26 CA060801009 120060528G2910A44700009 ACTUATOR DHAV DHC8 DHC8101 2809002NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE SERVO LEAKING W E ENGINE SHUTDOWN KJ FLUID LOSS WARNING INDICATION TXTAXI/GRND HDL 1 CA 40236 (CAN) AFTER NR 2 ENGINE START CREW OBSERVED THAT THE NR 2 HYDRAULIC SYSTEM QUANTITY HAD DECREASED TO 1 QUART. ENGINES SHUTDOWN AND PASSENGERS DISEMBARKED FOR DEFECT INVESTIGATION. ENGINEERING DETERMINED SYSTEM FLUID LOSS TO BE FROM THE RT OB SERVO ACTUATOR HOUSING. THE SERVO ACTUATOR WAS REPLACED AND HYDRAULIC SYSTEM REPLENISHED IAW THE AMM. (TC NR 20060801009) 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20060926002042006092600204EU 2006 9 26 CA060802001 120060725G631035013001 FREEWHEEL UNIT SNIAS 350 AS350BA 8680817EU ALLSN 250C 250C30 03013GL MAIN ROTOR MAKING METAL W O OTHER O OTHER NRNOT REPORTED 1 CA 5074 61 (CAN) AFTER INSTALLING A OVERHAULED FREEWHEEL, METAL WAS FOUND (4) SEPARATE TIMES IN 61.1 HOURS, SILVER FLAKES FOUND ON CHIP PLUG. (TC NR 20060802001) 1G71 3U3 UNCH9EU E1GL 20060810000272006081000027NE 2006 8 10 CA060802002 220060711G72502292253850 TURBINE BLADES SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1D1 NE GAS GENERATOR FAILED W K NONE O OTHER ININSP/MAINT 1 CA 254 254 (CAN) THE PILOT SHUTDOWN THE AIRCRAFT TO HOOK UP HIS WATER BUCKET, AFTER A SHORT TIME PERIOD OF APPROXIMATELY 8 TO 10 MINUTES HE ATTEMPT TO RESTART THE AIRCRAFT. THE STARTER WOULD NOT TURN THE ENGINE. A BORESCOPE WAS USED TO LOOK INSIDE THE ENGINE AND FOUND THAT THE 1ST STAGE TURBINE BLADE HAD RUBBED. THE M03 WAS THEN REPLACED AND THE AIRCRAFT RETURN TO SERVICE. (TC NR 20060802002) 1G71 3U3 U H9EU E19EU 20060926002052006092600205NM 2006 9 26 CA060802003 120060722G61207898426009 CONTROL UNIT DHAV DHC8 DHC8101 2809002NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE NR 1 ENGINE MALFUNCTIONED W EA ENGINE SHUTDOWN UNSCHED LANDING F FLT CONT AFFECTED CLCLIMB 1 CA 198 (CAN) DURING THE TAKEOFF ROLL, THE FIRST OFFICER NOTED ILLUMINATION OF THE NR 1 ENGINE MANUAL CAUTION AND THE CAPTAIN ELECTED TO CONTINUE THE TAKE OFF. SHORTLY AFTER GEAR RETRACTION, THE NR 1 PROPELLER FEATHERED. THE ENGINE WAS SECURED AFTER COMPLETION OF PLATEAU HEIGHT DRILLS AND THE AIRCRAFT MANOEUVRED FOR A RETURN TO LAND. NR 1 ELECTRONIC CONTROL UNIT REPLACED. (TC NR 20060802003) 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20060926002062006092600206EA 2006 9 26 CA060802004 120060801G2752 WARNING MESSAGE CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE TE FLAPS ILLUMINATED W O OTHER F FLT CONT AFFECTED APAPPROACH 1 CA (CAN) 0 FLAP LANDING DUE TO FLAP FAIL EICAS MESSAGE. ON APPROACH, CREW SELECTED FLAPS AND NOTICED THEY WERE STUCK AT ZERO. CREW COMPLETED CHECKLIST, THEN CONTACTED DISPATCH/ MTC. AFTER TALKING TO MTC THE FLIGHT LANDED WITH ZERO FLAP. AIRPORT FIRE FIGHTING WAS CONTACTED AS A PRECAUTION. FLIGHT LANDED WITHOUT INCIDENT. MAINT RESET SYSTEM AND CARRIED OUT INSPECTION IAW TIB CRJ-27-04. SYTEM RESET OK. DMI APPILED TO HAVE FAULT CODES READ AND INTERPRETTED. (801574 8/1/2006 21:01) (TC NR 20060802004) 2L72 4F4 FRTA21EA E15NE 20060926002072006092600207NE 2006 9 26 CA060802005 220060427G7320311496001 COUPLING DHAV DHC8 DHC8202 2809007NM PWA 120 PW123D 52152NE HAMSTD14SF 14SF23 NE RT ENGINE WORN W EA ENGINE SHUTDOWN UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 1 CA 182877506 (CAN) DURING CRUISE, NUMBER 2 ENGINE EXPERIENCED EXTREME TORQUE FLUCTUATIONS OF UP TO 50 PRESENT WITH ASSOCIATED FUEL FLOW AND NH RPM INDICATIONS. AS A RESULT OF A SUBSEQUENT TORQUE DROP THE CREW ELECTED TO CARRY OUT A PRECAUTIONARY ENGINE SHUT DOWN IN FLIGHT. THE NO.2 PROPELLER ASSEMBLY WAS REPLACED DUE TO THE OVERTORQUE AND SENT FOR MAJOR INSPECTION. THE MECHANICAL FUEL CONTROL UNIT (MFCU) AND FUEL PUMP WERE REPLACED DURING WHICH IT WAS DISCOVERED THAT THE INTERCONNECTING COUPLING WAS STRIPPED POSSIBLY DUE TO AN INTERNAL FAILURE OF THE MFCU. (TC NR 20060802005) 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20060926002082006092600208NE 2006 9 26 CA060802007 220060419G7320311717503 FUEL CONTROL DHAV DHC8 DHC8202 2809007NM PWA 120 PW123D 52152NE HAMSTD14SF 14SF23 NE NR 1 ENGINE FAILED W A UNSCHED LANDING XJ ENGINE FLAMEOUT WARNING INDICATION APAPPROACH 1 CA 20271 (CAN) DURING APPROACH NR 1 ENGINE TORQUE AND RPM SURGING 10 PERCENT WITH POWER ABOVE 80 PERCENT. ENGINE SHUTDOWN AT 5000 FEET ON DOWNWIND. MAINTENANCE REPLACED NR 1 ENGINE FUEL PUMP AND FUEL CONTROL. OPERATIONAL CHECK GOOD. AIRCRAFT RETURNED TO SERVICE. (TC NR 20060802007) 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20060926002092006092600209NE 2006 9 26 CA060802008 220060726G7497 WIRE CONT ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE MAGNETO CHAFED W O OTHER X ENGINE FLAMEOUT DEDESCENT 1 CA 400 (CAN) WHEN THE COLLECTIVE LEVER WAS LOWERED DURING DESCENT FOR A LANDING AT THE HELICOPTER BASE THE ENGINE TACHOMETER BECAME ERRATIC, THE ENGINE OVERSPED ABOVE 116 PERCENT AND THE THROTTLE GOVERNOR WAS NOT WORKING. THE ROTOR TACH ALSO INDICATED AN OVERSPEED ABOVE 114 PERCENT. INSPECTION OF THE RT MAGNETO FOUND THAT THE INSULATION ON THE WIRE CARRYING THE SPEED SIGNAL FROM THE SECONDARY POINTS TO THE TACHOMETER AND SPEED GOVERNOR HAD BEEN CUT THROUGH AND SHORTED TO GROUND. THE INTERMITTENT LOSS OF SIGNAL RESULTED IN ERRATIC TACH INDICATION AND THE AIRFRAME MANUFACTURER CONFIRMED THAT WITH THAT CONDITION THE GOVERNOR COULD BE EXPECTED TO GO OFF LINE. THE MOST LIKELY CAUSE OF THE DAMAGE WAS PINCHING OF THE WIRE BE1G71 3O3 O H11NM 1E4 20060913000462006091300046NM 2006 9 13 CA060802009 120060405G3240DSC252A40230 HOSE DHAV DHC8 DHC8201 2809001NM PWA 120 PW123D 52152NE HAMSTD14SF 14SF23 NE BRAKES LEAKING W D RETURN TO BLOCK KJ FLUID LOSS WARNING INDICATION TXTAXI/GRND HDL 1 CA (CAN) DURING PRE TAKE-OFF CHECKS FOR THE FIRST FLIGHT OF THE DAY (PARK BRAKE ON), THE FLIGHT CREW NOTICED THAT THE NR 2 HYDRAULIC SYSTEM HAD LOST MOST OF ITS FLUID. AIRCRAFT GROUND RETURN AND DURING THE TAXI BACK TO THE GATE, THE NR 1 HYDRAULIC SYSTEM QUANTITY WAS ALSO OBSERVED TO BE GOING DOWN. MAINTENANCE INSPECTION REVEALED THAT THE LT OB (NR 1) BRAKE HYDRAULIC FLEX HOSE TO BE LEAKING FLUID. A NEW FLEXIBLE BRAKE HOSE ASSEMBLY P/N: DSC252A4-0230 INSTALLED, BOTH HYDRAULIC SYSTEMS SERVICED AND BLEED IAW AMM (TC NR 20060802009). 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20060913000502006091300050WP 2006 9 13 CA060802010 220060801G7261 ENGINE FRCHLDSA227 SA227DC 3377521SW GARRTTTPE331TPE33112UHR WP MCAULY4HFR344HFR34C652 NE LEFT LEAKING W EA ENGINE SHUTDOWN UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CRCRUISE 1 CA 4828 P70275 (CAN) ON CLIMB, THE LT LOW OIL PRESSURE LIGHT ILLUMINATED, ALONG WITH A OIL PRESSURE GAUGE DECREASE. THE LT ENGINE WAS SHUTDOWN IN FLIGHT AND RETURNED TO BASE. ON INSPECTION IT APPEARS THAT THE OIL EXITED OUT THE EXHAUST. ENGINE REMOVED AND SENT FOR REPAIR AND INSPECTION. (TC NR 20060802010) 2L72 4T4 TRTA18SW E4WE 6 C3PNE 20060913000512006091300051EU 2006 9 13 CA060803001 120060614G5210852G10 SEAL SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1D1 NE PAX DOOR PEELING W A UNSCHED LANDING D INFLIGHT SEPARATION HOHOVERING 1 CA (CAN) THE PILOT WAS LONG LINING WITH THE PILOT SIDE DOORS OFF, THE WEATHER STRIPPING PEELED OFF THE DOOR FRAME. THE LAST 3 INCHES CAUGHT ON THE POCKET DOOR STOP. THE PILOT SLOWED DOWN AND LANDED TO REMOVE THE REST OF THE DOOR SEAL. THE DOOR SEAL IS 4 METERS LONG,AND ALTERNATE P/N 704A39821031. (TC NR 20060803001) 1G71 3U3 U H9EU E19EU 20060913000542006091300054NM 2006 9 13 CA060803003 120060803G2611656020916 CONTROLLER BOEING727 727247 138408FNM PWA JT8 JT8D* NE FIRE DETECTION MALFUNCTIONED W F ACTIVATE FIRE EXT. N FALSE WARNING NRNOT REPORTED 1 CA (CAN) JUST AFTER ENGINE, ALL 3 ENGINES WERE STARTED AND THE FLIGHT CREW WERE CARRYING OUT THE AFTER START CHECKLIST, THE NR 2 ENGINE (FIRE WARNING) ILLUMINATED AND THE (FIRE BELL RANG). THE FIRE HAND WAS PULLED AND THE FIRE BOTTLE DISCHARGED LIGHT WENT OUT. MAINTENANCE CONFIRMED THAT THERE WAS NO FIRE AND THAT THE FIRE DETECTION UNIT HAD FAILED. THIS UNIT IS A ON CONDITION SOLID STATE PART. AIRCRAFT IS CURRENTLY ON THE GROUND AWAITING PARTS. (TC NR 20060803003) 2L73 4F4 F A3WE E2EA 20060913000552006091300055SW 2006 9 13 CA060803004 120060728G291070061H000T13 HOSE BELL 206 206L3 1182108SW ALLSN 250C 250C30P 03013GL HYD SYSTEM LEAKING W O OTHER K FLUID LOSS LDLANDING 1 CA (CAN) UPON LANDING AND SHUTDOWN ON LAST UNEVENTFULL FLIGHT OF THE DAY. PILOT REPORTED HYD FLUID ON SIDE OF A/C. A/C GROUNDED UNTIL INSP, UPON INSP. HYD PRESSURE FEED LINE FOUND LEAKING. LINE REPLACED WITH SEVICEABLE UNIT. RECOMMEND OPERATORS AND MAINT FACILITIES INSPECT O/C HYD LINES FREQUENTLY AND REPLACE. (TC NR 20060803004) 1G71 3U3 U H2SW E1GL 20060913000582006091300058NM 2006 9 13 CA060804001 120060503G760387620136055057 CONTROL ROD DHAV DHC8 DHC8301 1386003NM PWA PW120 PW123 NE HAMSTD14SF 14SF15 NE POWER LEVER MISINSTALLED W A UNSCHED LANDING F FLT CONT AFFECTED CLCLIMB 1 CA (CAN) DURING CLIMB NR 2 ENGINE WAS MAKING ONLY 78 PERCENT POWER AND THE ENGINE POWER LEVER WAS JAMMED 1.5 INCH FROM FULL TRAVEL. AIRCRAFT RETURN ON GROUND SAFELY SHORTLY AFTER TAKEOFF. MAINTENANCE FOUND NR 2 CONTROL AND CONDITION LEVER RODS HARDWARE (BOLT AND NUT) INCORRECTLY INSTALLED. PROPER HARDWARE INSTALLATION AND ENGINE RIGGING WERE PERFORMED. AN INTERNAL SAFETY ALERT WAS ISSUED ON JULY 14, 2006 IN RESPECT TO THIS EVENT. AIRFRAME HOURS: 37405:43. CYCLES:48382 (TC IN 20060804001) 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20060913000592006091300059EA 2006 9 13 CA060804002 120060729G3320BR95005 BALLAST CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE CABIN LIGHTS FAULTED W K NONE B SMOKE/FUMES/ODORS/SPARKS ININSP/MAINT 1 CA (CAN) DURING MAINTENANCE AN ELECTRICAL SMELL WAS APPARENT IN THE FRONT HALF OF THE CABIN. EIGHT (8) CABIN LIGHT BALLASTS WERE FOUND AT FAULT. ALL 8 WERE REPLACED AND AIRCRAFT WAS MONITORED FOR TWO HOURS FOR SNAG RE-OCCURENCE WITH NO FAULT FOUND. AIRFRAME HOURS: 3602:31. CYCLES: 2780. (TC NR 20060804002) 2L72 4F4 FRTA21EA E15NE 20060913000612006091300061NM 2006 9 13 CA060804003 120060602G2910AN81510D FITTING DHAV DHC8 DHC8301 1386003NM PWA PW120 PW123 NE HAMSTD14SF 14SF23 NE NR 1 HYD SYS FRACTURED W A UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CRCRUISE 1 CA 310 (CAN) DURING THE FLIGHT, OPERATOR LOST ALL HYDRAULIC QUANTITY AND PRESSURE FROM THE SYSTEM NR 1 AND ALL ASSOCIATED LIGHTS. CREW COMPLETED THE RESPECTIVE CHECKLIST AND LANDED WITH FLAPS 0° AND WITHOUT NORMAL BRAKING, INVESTIGATION REVEALED THAT THE NR 1 PRESSURE MANIFOLD INLET UNION HAD FRACTURED. (TC NR 20060804003) 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20060913000632006091300063 2006 9 13 CA060804004 420060410G3442707700301 INDICATOR DHAV DHC8 DHC8301 1386003NM PWA PW120 PW123 NE HAMSTD14SF 14SF23 NE WEATHER RADAR MALFUNCTIONED W G O2 MASK DEPLOYED B SMOKE/FUMES/ODORS/SPARKS DEDESCENT 1 CA 9667 1105 (CAN) DURING DESCENT, CREW DETECTED A STRONG BURNING SMELL ON THE FLIGHT DECK. FLIGHT CREW DONNED OXYGEN MASKS AND LANDED WITHOUT FURTHER INCIDENT. FLIGHT CREW HAD REPORTED TO ENGINEERING THAT THE WEATHER RADAR WAS INOPERATIVE FROM TOP OF DESCENT. UPON INVESTIGATION BY ENGINEERING THE WEATHER RADAR INDICATOR WAS FOUND TO HAVE A STRONG BURNING SMELL. WEATHER RADAR INDICATOR REPLACED AND FUNCTIONALLY TESTED SERVICEABLE. (TC NR 20060804004) 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20060913000842006091300084NE 2006 9 13 CA060804005 320060329G611173030SOCN8173881SEAL DHAV DHC8 DHC8301 1386003NM PWA PW120 PW123 NE HAMSTD14SF 14SF23 NE PROPELLER BLADE LEAKING W O OTHER K FLUID LOSS CRCRUISE 1 CA 135 200504062525 (CAN) DURING FLIGHT, NR 1 PROP LOST APPROXIMATELY 7 QUARTS OF OIL FROM THE HUB. UPON ARRIVAL AIRCRAFT WAS COVERED IN OIL (LT). THERE WAS NOT AN INFLIGHT SHUTDOWN AND NO EMERGENCY MEASURES WERE REQUIRED OR TAKEN. THE AIRCRAFT RESPONDED NORMALLY. THE PROP SEAL WAS FOUND TORN AND THE GARTER SPRING WAS DISTORTED WHERE THE TWO ENDS OF THE SPRING ARE WELDED. (TC NR 20060804005) 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20060913001052006091300105 2006 9 13 CA060804006 420060728G61225337050 IDLER GEAR WOODWARD PWA PT6 PT6A67B 52043NE PROPELLER GOVER WORN W K NONE O OTHER ININSP/MAINT 1 CA 1584 13313260 (CAN) ENGINE PCE-PR0055 WAS SUBMITTED FOR A SCHEDULED FIRST TIME OVERHAUL (TSN 3621.0 HRS). THE PROPELLER GOVERNOR S/N 13313260 (TSN 1583.6 HOURS) WAS DISMANTLED FOR CLEANING BEFORE OVERHAUL INSPECTION. IT WAS DISCOVERED THAT THE IDLER GEAR BUSHING WAS SEVERELY WORN AWAY RESULTING IN AN ELLIPTICAL ROTATION OF THE GEAR THAT CAUSED THE GEAR POCKET TO WEAR IN AN OVAL MANNER ON THE PRESSURE SIDE. A NORMAL IDLER GEAR BUSHING MEASURES APPROXIMATELY 0.100 IN. THE WORN IDLER GEAR BUSHING MEASURED 0.0175 IN., I.E. IT HAD WORN AWAY 0.0825 IN. IT IS NOT KNOWN WHAT CAUSED THE EXCESSIVE WEAR. THE PERIODIC OIL ANALYSIS PROGRAM (SOAP) DID NOT INDICATE A PROBLEM. AFTER DISCOVERING THIS CONDITION, WE TRIED TO ROTATE THE G 4 T E26NE 20061213001372006121300137EU 2006 12 13 CA060804007 120060803G2913S40 COUPLING SNIAS 350 AS350BA 8680817EU TMECA ARRIELARRIEL1B 6OO30NE HYD PUMP LEAKING W A UNSCHED LANDING F FLT CONT AFFECTED CRCRUISE 1 CA 40652121 (CAN) PILOT FELT STIFFNESS IN FLIGHT CONTROLS AND LANDED. INVESTIGATION REVEALED THAT THE SLEEVE COUPLING INTERNAL SPLINES HAD WORN EXCESSIVELY SO THAT THE FLIGHT CONTROL HYDRAULIC PUMP WAS NO LONGER DRIVEN BY THE DRIVE BELT FROM THE MAIN GREAR BOX. THE FAILED COUPLING SHOWS SIGNS OF MILD CORROSION IN THE INTERNAL SPLINES. THE COUPLING WAS LUBRIATED DURING THE LAST SCHEDULED INSPECTION 30 HOURS PREVIOUSLY. THE SLEEVE COUPLING WAS REPLACED AND THE AIRCARFT WAS RETURNED TO SERVICE. DISCUSSION WITH OTHER OPERATORS INDICATE AN INCREASE IN THE SLEEVE COUPLING FAILURE RATE SINCE THE INTRODUCTION OF THE POLY V DRIVE BELT AS REQUIRED BY AD CF-2004-10 ( SB 63.00.08) ISSUED 4 JUNE 2004. (TC NR 20060804007) 1G71 3U3 UNCH9EU E19EU 20060913001132006091300113EA 2006 9 13 CA060804008 220060801G8530SLC36005F CYLINDER HEAD CESSNA172 172N 2072434CE LYC O320 O320D2J 41508EA MCAULY1C160 1C160DTM GL ENGINE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 1640 (CAN) ALL 4 CYLINDERS HAVE CRACKS THAT BEGIN AT THE INNER MOST EXHAUST FLANGE STUD AND MOVING TO THE EXHAUST VALVE SEAT, THEN 180 DEGREES ACROSS THE EXHAUST VALVE SEAT TO THE UPPER SPARK PLUG HOLE. SN. E36-10511 E36-10244 E36-10426 E36-10496 NOTE: THIS MAKES 10 OF THESE CYLINDERS FROM 3 DIFFERENT AIRCRAFT IN 6 WEEKS TO HAVE THE SAME CRACKS. TIME ON THESE VARY FROM 1600 TO 2100 HOURS. ALL ON AN (ON CONDITION PROGRAM) REQUIRING AN EXTERNAL SOAPY/WATER LEAK CHECK AND BORESCOPE INSPECTION WHICH IS HOW THE DEFECT IS DISCOVERED. A CYLINDER DPI DOES NOT REVEAL AND A PARTIAL ENGINE TEARDOWN ID REQUIRED FOR VISUAL DETECTION. (TC NR 20060804008) 1H71 3O3 ONT3A12 E274 5 NP910 20080131000132008013100013CE 2008 1 31 CA060804009 120060802G533050420066281 DOUBLER BEECH 200 200BEECH 1152920CE PWA PT6 PT642A NE HARTZLHCB3T HCB3TN3 GL FUSELAGE DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA 12559 1129 (CAN) DURING PHASE 2 INSPECTION AND WHILE PERFORMING SPECIAL INSPECTION ON NR 25 (INSPECTION OF UPPER AND LOWER WINDSHIELD CORNERS), DAMAGE TO THE DOUBLER BELOW THE WINDSCREEN WAS FOUND. THE PN OF THE DOUBLER IS 50-420066-281 LOCATED BETWEEN FS 94.00AND FS 100.50. THE DAMAGE WAS CAUSED FROM THE ITT HARNESSES CHAFFING INTO THE DOUBLER. THE DAMAGE IS LOCATED BETWEEN 1.5 TO 5.5 LT OF THE WINDSCREEN CENTER POST, THE DOUBLER THICKNESS IS .100, THE CHAFFING DAMAGE RANGES FROM .010 TO .069 IN DEPTH. THE DAMAGED AREA HAS BEEN MAPPED, AND THE INFORMATION SENT TO MFG REPAIR DESIGN OFFICE FOR ASSESSMENT. A FOLLOW UP REPORT SHALL BE SUBMITTED. (TC NR 20060804009) 1L72 4T4 T A24CE E4EA 6 CP15EA 20060913001152006091300115WP 2006 9 13 CA060804010 120060731G6320369D25146 BEARING HUGHES369 369D 4470706WP ALLSN 250C 250C20B 03013GL M/R TRANSMISSIONCRACKED W A UNSCHED LANDING J WARNING INDICATION NRNOT REPORTED 1 CA 574 1265 (CAN) 369D25146 ROLLER BEARING INNER RACE CRACKED, THIS RACE IS PRESSED ONTO TRANSMISSION T/R O/P PINION WITH AN INTERFERENCE FIT. CRACKED INNER RACE CAUSED THE RACE TO SPALL AND CAUSED A CHIP LIGHT. SEVERE METAL CONTAMINATION WAS FOUND (TC NR 20060804010) 1G71 3U3 U H3WE E4CE 20060913001162006091300116CE 2006 9 13 CA060806001 120060727G3246RA105002 RIVET CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA MCAULY1C160 1C160DTM GL BRAKE LINING SHEARED W O OTHER O OTHER LDLANDING 1 CA (CAN) UPON LANDING THE PILOT EXPERIENCE A SEVERE PROBLEM WITH THE LT MAIN WHEEL BRAKE SYSTEM. DURING THE DISASSEMBLY OF THE LT BRAKE SYSTEM IT WAS DISCOVERED THAT THE BRAKE LINING RIVETS (RA105-002) HAD BOTH SHEARED AND THE LINING WAS NO LONGER ATTACHED TO THE BACKING PLATE. THE RIVETS THAT SHEARED WERE MADE FROM BRASS (RA105-002) UNLIKE THE CLEVELAND RIVETS (105-002 WHICH ARE BRASS PLATED STEEL. THE AIRCRAFT WAS RETURNED TO SERVICE WITH NEW BRAKE LININGS AND NEW CLEVELAND RIVETS. (TC NR 20060806001) 1H71 3O3 ONT3A12 E274 5 NP910 20060913001182006091300118CE 2006 9 13 CA060807001 120060804G324616211800 WHEEL CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE MCAULY3AF34C3GFR34C703 GL MLG CRACKED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) APPROX 1.5 INCH CRACK AROUND CIRCUMFERENCE OF BEARING RACE, INSIDE OF WHEEL HALF, SUSPECT MIS-ALIGNMENT OF WHEEL HALF SPACER DURING BUILD-UP (TC NR 20060807001) 1H71 3T3 T A37CE E4EA 5 CP60GL 20060913001192006091300119EU 2006 9 13 CA060807002 120060806G6420704A33651190 BEARING SNIAS 350 AS350BA 8680817EU TAIL ROTOR NOISY W K NONE O OTHER ININSP/MAINT 1 CA 200 (CAN) FOUND DURING 500 HOUR INSPECTION. ABNORMAL BEARING NOISE, AXIAL WEAR BEYOND LIMITS. (TC NR 20060807002) 1G71 3U NCH9EU 20060913001212006091300121EU 2006 9 13 CA060808001 120060731G29109740926112 RELAY PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL HYD SYSTEM MALFUNCTIONED W O OTHER J WARNING INDICATION LDLANDING 1 CA 3988 3988 (CAN) LANDING GEAR SELECTED DOWN ON FINAL. NO GEEN DOWN LOCK INDICATION FOR THE NOSE GEAR. PILOT DID AN EMERGENCY GEAR EXTENSION AND GOT THE LANDING GEAR DOWN AND LOCKED INDICATION FOR ALL THREE GEAR. THE SYSTEM WAS TROUBLESHOT AND FOUND TO HAVE A MALFUNCTIONING HYD PWR RELAY K601. THE RELAY WAS REPLACED AND A FUNCTIONAL CHECK OF THE LANDING GEAR SYSTEM WAS CARRIED OUT WITH NO FURTHER PROBLEMS. (TC NR 20060808001) 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20060913001222006091300122EA 2006 9 13 CA060808004 220060703G8520LW13521 BEARING ROBSINR44 R44 7640120WP LYC O540 O540F1B5 41532EA CONNECTING ROD BROKEN W O OTHER O OTHER NRNOT REPORTED 1 CA 2183 2183 (CAN) CONNECTING ROD BEARINGS ON NR 1,3, AND 5 RODS HAD SIGNIFICANT SURFACE DELAMINATION. BROKEN PIECES .5 INCH L X .1250 INCH W FOUND IN BETWEEN CONNECTING ROD BEARING AND CRANKSHAFT. (TC INCH 20060808004) 1G71 3O3 O H11NM E295 20060913001232006091300123GL 2006 9 13 CA060808005 220060719G723023056109 SCROLL ALLSN BELL 206 206L1 1182107SW ALLSN 250C 250C28 03013GL COMPRESSOR CRACKED W O OTHER O OTHER CRCRUISE 1 CA 6983 CAC70614 (CAN) HIGH TOT WAS NOTICED IN CRUISE. ON RETURNING A POWER CHECK WAS CARRIED OUT AND LOW POWER WAS DETECTED. A HAIT LINE CRACK WAS IDENTIFIED BY VISUAL INSPECTION IN THE ELBOW AREA OF SCROLL. COMPRESSOR CHANGED. (TC NR 20060808005) 1G71 3U3 U H2SW E1GL 20060913001252006091300125CE 2006 9 13 CA060808006 120060804G534312116011 FITTING CESSNA206 U206B 2073322CE CONT O520 IO520D 17032SO MCAULY3A32C D3A32C90 GL MLG OUTBOARD CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 9713 (CAN) DURING A 100 HOUR INSPECTION LOOSE RIVETS WERE NOTICED AROUND THE LT MAIN GEAR. ONCE THE FLOOR WAS LIFTED TO PERFORM THE REPAIRS, THE LT MAIN GEAR OB FITTING WAS FOUND TO BE CRACKED PROPOGATING FROM THE AFT END OF THE GEAR LEG OPENING TOWARDS THE AFT END OF THE FITTING. (TC NR 20060808006) 1H71 3O3 O A4CE E5CE 5 CP21EA 20060913001262006091300126WP 2006 9 13 CA060808009 120060703G3213369H600151 STRUT HUGHES369 369D 4470706WP ALLSN 250C 250C20B 03013GL MLG CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING THE YEARLY INSPECTION, THE LT AFT LANDING GEAR STRUT WAS INSPECTED AND FOUND TO BE CRACKED, FROM THE LOWER DRAG BRACE ATTACH HOLE. THE CRACK WAS APPROX. 1.250 INCH LONG, AND EXTENDED LENGTHWISE TOWARDS THE BEND IN THE STRUT (TC NR 20060808009) 1G71 3U3 U H3WE E4CE 20060913001322006091300132EA 2006 9 13 CA060808010 120060710G5610601R3303317 WINDSHIELD CNDAIRCL600 CL6002C10 1390015EA GE CF34 CF348C1 NE COCKPIT CRACKED W A UNSCHED LANDING O OTHER CRCRUISE 1 CA 3949 (CAN) (ENROUTE, CREW SENT ACARS MESSAGE TO DISPATCH THAT THEY HAD A BROKEN CAPTAINS WINDSHIELD, AND WERE DIVERTING) MX DISPATCHED WITH WINDSHIELD. WINDSHIELD REPLACED. (TC NR 20060808010) 2L72 4F4 FRTA21EA EOOO63EN 20060913001472006091300147NE 2006 9 13 CA060808011 220060204G7200CF343A1 ENGINE CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE RIGHT MALFUNCTIONED W E ENGINE SHUTDOWN RJ PARTIAL RPM/PWR LOSS WARNING INDICATION DEDESCENT 1 CA (CAN) EXPERIENCED THE RT ENGINE IFSD, JUST AFTER THE LIGHTNING STRIKE TODAY. PIC DID NOT TRY TO RESTART THE ENGINE DURING THE FLIGHT, BUT AFTER THE LANDING WE COULD START THE ENGINE. THERE IS NO VISIBLE DAMAGE ON THE OUTSIDE OF THE ENGINE, WE WILL DO THE BSI. WE WOULD LIKE TO KNOW THE MOST PROBABLE ROOT CAUSE OF THE IFSD. IF YOU HAVE A SIMILAR EXPERIENCE IN OTHER OPERATORS, PLEASE PROVIDE YOUR INFORMATION. THE CIRCUMSTANCES IS AS FOLLOWS, OCCURRED DATE : APRIL 02, 10:37JST ASN: 7052 ESN : 807222 FLT PHASE : DURING THE DESCENDING TO DESTINATION ALT : 13,000 FT IGNITION : CONTINUOUS IGNITION WEATHER CONDITION : IN-CLOUD, LIGHT RAIN) AFTER THE EVENT THE OPERATOR SUPPLIED THE DFDR TO MFG. MFG ANALYSIS CONCLU2L72 4F4 FRTA21EA E15NE 20060913001482006091300148SW 2006 9 13 CA060809001 120060809G29102781006019 LINE SWRNGNSA227 SA227AC 8780603SW GARRTTTPE331TPE33111U 01514WP MCAULY4HFR344HFR34C652 NE HYDRAULIC SYSTEMLEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) FOUND HYD LEAK IN LT WHEEL WELL. GEAR UP LINE FOUND CRACKED. LINE REPLACED, GEAR SWINGS CARRIED OUT. AIRCRAFT RETURNED TO SERVICE (TC NR 20060809001) 2L72 4T4 TRTA8SW E4WE 6 C3PNE 20060913001492006091300149SO 2006 9 13 CA060809002 120060528G7810LW121127 EXHAUST DUCT PIPER PA31 PA31325 7103105SO LYC O540 TIO540F2BD 41532EA HARTZLHCE3Y HCE3YR2A GL ENGINE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 1599 (CAN) EXHAUST TRANSITION BETWEEN TURBO AND EXHAUST STACKS FROM CYLINDERS HAD CRACKED AND STARTED TO BLOW A HOLE BELOW THE EGT PROBE HOLE. THE DEFECT WAS NOTICED BY AN EXHAUST STAIN ON THE INSIDE OF THE COWL ON A MAINTENANCE DAILY INSPECTION. THE AIRCRAFT WAS 39 HOURS OUT OF INSPECTION. (TC NR 20060809002) 1L72 3O3 O A20SO E14EA 5 CP33EA 20061018000782006101800078NM 2006 10 18 CA060810001 120060810G5220MS2764639 ROD END DHAV DHC8 DHC8301 1386003NM PWA PW120 PW123 NE HAMSTD14SF 14SF15 NE EMERGENCY EXIT SEIZED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING A C-CHECK INSPECTION THE TASK WAS CALL UP TO INSPECT THE FWD EMERGENCY EXIT. UPON INSPECTION IT WAS DETERMINED THAT IT WAS EXTREMELY STIFF AND DIFFICULT TO OPERATE. UPON REMOVAL AND TROUBLESHOOTING IT WAS DETERMINED THAT THE CONNECTING ROD END (X10) REF IPC 52-20-00 FIG. 20 ITEM 180 WERE FOUND SEIZED INTERNALLY. THE FAILURE APPEARS TO BE DUE THE PHENOLIC BALL WIPER NOT ALLOWING THE BEARING TO ROLL FREELY. IT WAS ALSO DETERMINED THAT THE LAYSHAFT BEARINGS (X4) EXHIBITED ABNORMAL WEAR AND CORROSION ASSOCIATED WITH HIGH TIME BEARINGS REF IPC 52-20-00 FIG. 20 ITEM 590. 2 OF THE 4 HAVE FAILED DUE TO INTERNAL SEIZING. ALL PART ARE CURRENTLY BEING REPLACED. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20060913001502006091300150CE 2006 9 13 CA060810004 120060731G5712052303018 RIB CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA MCAULY1C160 1C160DTM GL LT WING CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 19931 (CAN) DURING NR 3 INSPECTION CRACK LOCATED IN (D) RIB JUST OB OF WING STRUT. LT WING. (TC NR 20060810004) 1H71 3O3 ONT3A12 E274 5 NP910 20060913001512006091300151CE 2006 9 13 CA060810005 120060806G77121013890053 TRANSMITTER BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA HARTZLHCD4N3HCD4N3A GL TORQUE FAILED W C ABORTED TAKEOFF N FALSE WARNING TOTAKEOFF 1 CA (CAN) ON TAKEOFF RT TORQUE TRANSMITTER WAS READING HIGH AIRCRAFT RETURNED AIRPORT. AIRCRAFT ELECTRICAL POWER TURNED OFF AND TORQUE INDICATOR WENT TO ZERO. A GROUND RUN WAS ACCOMPLISHED AND TORQUE INDICATION WAS NORMAL AT HIGH AND LOW POWER SETTINGS. AIRCRAFT RETURNED TO DESTINATION WITHOUT FURTHER INCIDENT. MAINTENANCE REPLACED RT ENGINE TORQUE TRANSMITTER P/N 101-390005-3 AS A PRECAUTIONARY. (TC NR 20060810005) 1L72 4T4 T A24CE E4EA 5 CSTC 20060913001522006091300152SO 2006 9 13 CA060810006 120060726G552311030120115 SUPPORT EMB 110 EMB110P1 3260122SO PWA PT6 PT6A34 52043EA HARTZLHCB3T HCB3TN3 GL BALANCE WEIGHT CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) WHILE DOING AN INSPECTION OF THE LTO ELEVATOR AND ITS ASSOCIATED PARTS A CRACK WAS FOUND IN THE ELEVATOR BALANCE WEIGHT SUPPORT. THE CRACK MEASURED 2.3750 OF AN INCH IN LENGTH AND STARTED APPROXIMATELY 2 INCHES BELOW THE LOWER THROUGH-TUBE FOR THE BALANCE SUPPORT TO ELEVATOR TORQUE TUBE ATTACH POINTS. THE SUPPORT WAS REPLACED WITH A NEW ONE. (TC NR 20060810006) 1L72 4T4 T A21SO E4EA 6 CP15EA 20060913001532006091300153EU 2006 9 13 CA060810007 120060726G2740HC273H0344 ARM BAC 146 146200A 1500266EU LYC ALF502ALF502R5 41580NE LEVER FAILED W O OTHER O OTHER NRNOT REPORTED 1 CA 3626114 (CAN) RESTRICTED MOVEMENT OF CONTROL COLUMN IN THE AFT DIRECTION. SEE CA1673 14 NR CTS/06/001 ATTACHED (TC NR 20060810007) 2H74 4F4 F A49EU E6NE 20060913001542006091300154SO 2006 9 13 CA060811001 120060807G2400 PANEL PIPER PA31 PA31P 7103120SO LYC O541 TIGO541E1A 41539EA HARTZLHCC3Y HCC3YN GL CIRCUIT BREAKER SMOKE W O OTHER B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 1 CA (CAN) CIRCUIT BREAKER PANEL STARTED TO SMOKE AND SPARK DURING CRUISE AT 14000 FT. ELECTRICAL FIRE CHECKLIST WAS INITIATED AND DESCENDED TO 7500 FT. UPON COMPLETION OF ELECTRICAL FIRE CHECKLIST SMOKE AND SPARK NO LONGER PRESENT. (TC NR 20060811001) 1L72 3O3 O A8EA E19EA 5 CP25EA 20060913001552006091300155WP 2006 9 13 CA060811002 120060810G7921369D25623 BELT HUGHES369 369D 4470706WP ALLSN 250C 250C20B 03013GL BLOWER OIL COOL WORN W O OTHER O OTHER DEDESCENT 1 CA 816 (CAN) ON APPROACH TO LAND THE PILOT HEARD A NOISE TO THE REAR OF THE AIRCRAFT FOLLOWED BY A VIBRATION. UPON INSPECTION THE ENGINEER NOTICED THE OIL COOLER BLOWER BELT TENSION WAS LOOSE AND THE TEETH OF THE BELT WERE WORN. (TC NR 20060811002) 1G71 3U3 U H3WE E4CE 20061018000792006101800079NM 2006 10 18 CA060811003 120060810G3297471515 WIRE HARNESS BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17EU NLG WOW DAMAGED W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA (CAN) LANDING GEAR DID NOT RETRACT AFTER TAKE OFF, RETURN TO FIELD. FOUND FAULTY NLG WOW 2/ CENTERING HARNESS. HARNESS REPLACED. AIRCRAFT RETURNED TO SERVICE. 2H72 4T4 TRTA13NM E00062EN6 CP17BO 20061213001382006121300138SW 2006 12 13 CA060814002 120060717G6220412010190105 SPINDLE BELL BELL 412 412 1182202SW MAIN ROTOR HUB DEBONDED W K NONE O OTHER ININSP/MAINT 1 CA 2396 A2713 (CAN) ON A MAIN ROTOR HUB ASSY 2500 HOUR INSPECTION THE RED BLADE SPINDLE ASSY WAS FOUND WITH DAMPER BEARING DEBONDED. (TC NR 20060814002) 1G72 4U H4SW 20061018000802006101800080GL 2006 10 18 CA060814003 320060729G61106505656 BRUSH BLOCK LKHEED188 188LKHEED* WP ALLSN 501D 501D13 03004GL ALLSN A6441 A6441FN606 GL NR 2 PROPELLER DAMAGED W E ENGINE SHUTDOWN J WARNING INDICATION CLCLIMB 1 CA (CAN) AFTER TAKEOFF CREW NOTICED NR 2 BETA LIGHT ILLUMINATED AND PROP RPM ERRATIC THE CREW ELECTED TO SHUT-DOWN NR 2 ENG. AND RETURN TO BASE FOR MAINTENANCE. BRUSH BLOCK WAS CHANGED ENG. WAS GROUND RUN AND FOUND SERVICABLE. (TC NR 20060814003) 2L74 4T4 T 4A22 E282 6 CP898 20060913001662006091300166SW 2006 9 13 CA060815001 120060807G29102781032167 LINE SWRNGNSA227 SA227AC 8780603SW GARRTTTPE331TPE33111U 01514WP MCAULY4HFR344HFR34C652 NE HYDRAULIC SYS CRACKED W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) HYDRAULIC FLUID NOTICED BY MAINTENANCE ON BELLY AREA OF AIRCRAFT. GEAR UP LINE FOUND CRACKED. LINE REPLACED AND GEAR SWINGS CHECKED SERVICIBLE. (TC NR 20060815001) 2L72 4T4 TRTA8SW E4WE 6 C3PNE 20061018000812006101800081NM 2006 10 18 CA060815002 120060814G522085220270001 MECHANISM DHAV DHC8 DHC8301 1386003NM PWA PW120 PW123 NE HAMSTD14SF 14SF15 NE EMERGENCY EXIT SEIZED W K NONE O OTHER ININSP/MAINT 1 CA 3786337863 (CAN) DURING INTERNALLY GENERATED MAINTENANCE FLEET CAMPAIGN TO CHECK FOR EMERGENCY DOOR OPERATING FORCE. MAINTENANCE UNABLE TO OPEN FORWARD EMERGENCY EXIT DOOR USING INTERNAL OR EXTERNAL HANDLE ( TASK 5220/07). REQUIRED DISASSEMBLY OF DOOR OUTER SHAFT MECHANISM TO ALLOW DOOR TO BE REMOVED. DISASSEMBLY OF OUTER SHAFT HANDLE FOUND BURR OF METAL ON SHAFT. DOOR REPAIRED AND MECHANISM LUBRICATED. AIRCRAFT HAD ACCUMULATED 1023HR/1823CY SINCE LAST SCHEDULED ACCOMPLISHMENT OF TASK 5220/07 IN JAN2006. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20060913001682006091300168SW 2006 9 13 CA060815003 120060815G79312090620031 PRESSURE SWITCH BELL 212 212 1181420SW PWA PT6T PT6T3 52045EA ENGINE OIL LEAKING W O OTHER K FLUID LOSS NRNOT REPORTED 1 CA 296 (CAN) FLUID LEAK AT UNION OF SWITCH BODY. THE BODY NORMALY HAS A RIVET TO KEEP THE UNIT FROM BEING TAKEN APART, BUT THIS RIVET WAS FOUND TO BE MISSING. THE THREADS HAD DAMAGE WHERE THE RIVET HOLE WAS. A HOLE IS PROVIDED IN THE THREADS TO INSTALL A RIVET. THIS DID NOT LINE UP. (TC NR 20060815003) 1G71 4U4 U H4SW E22EA 20060913001722006091300172WP 2006 9 13 CA060815004 120060815G801131B22111 STARTER ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE ENGINE BROKEN W O OTHER O OTHER NRNOT REPORTED 1 CA 25 (CAN) PILOT WENT TO START THE AIRCRAFT. HE COULD HEAR THE MOTOR TURNING, HOWEVER THE ENGINE WAS NOT TURNING OVER. THE AME FOUND THE DRIVE TO BE ENGAGED TO THE RING GEAR. WHEN THE STARTER WAS REMOVED, THE DRIVE COULD BE TURNED FREELY BY HAND. THE DRIVE FAILED INTERNALLY. NO REPORT OF ANY BACKFIRE OR KICKBACK DURING START. THE AME BELIEVES THAT AN INTERRUPTION OF THE POWER TO THE STARTER MAY HAVE CAUSED THE STARTER TO DISENGAGE AND REENGAGE, DAMAGING THE STARTER PINION. HE BELIEVES THE FAULT TO BE IN THE AIRCRAFT WIRING, NOT IN THE STARTER. (TC NR 20060815004) 1G71 3O3 O H11NM 1E4 20070516001652007051600165NE 2007 5 16 CA060816001 220060815G7261 OIL SYSTEM BOEING767 767233 1385113NM PWA JT9 JT9D7R4D 52054NE ENGINE LOW PRESSURE W EA ENGINE SHUTDOWN UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CRCRUISE 1 CA 4595 (CAN) ENGINE INFLIGHT SHUTDOWN DO TO OIL PRESSURE AND QUANTITY LOSS, ENROUTE, DIVERTED, SUSPECT NR 4 BEARING. (TC NR 20060816001) 2L72 4F4 FRTA1NM E3NE 20061018000822006101800082NM 2006 10 18 CA060816002 120060707G528083231044005 GUARD DHAV DHC8 DHC8301 1386003NM PWA PW120 PW123 NE HAMSTD14SF 14SF15 NE RT NACELLE DAMAGED W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA (CAN) DURING CLIMB, AFTER GEAR UP SELECTION AMBER AND RED LIGHTS ILLUMINATED IN GEAR HANDLE, ALONG WITH 3 AMBER LANDING GEAR DOOR LIGHTS. A LOUD GRINDING NOISE WAS HEARD IN THE COCKPIT. AIRCRAFT RETURNED AND LANDED SAFELY TO THE ORIGINATING AIRPORT. MAINTENANCE FOUND RT NACELLE`S WHEEL WELL DEBRIS GUARD DAMAGED AND WAS REPLACED. NO MAINTENANCE WAS PREVIOUSLY PERFORMED IN THAT AREA. MAINTENANCE FEED-BACK REVEALED THAT THE DEBRIS GUARD GETS LOOSE QUITE OFTEN, DUE TO THE FASTENING SYSTEM USED. AIRFRAME HOURS WERE: 36610:07. CYCLES WERE: 40842. (TC NR 20060816002) 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20060913001732006091300173EA 2006 9 13 CA060816003 120060809G492038004883 APU CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE SMOKE W O OTHER KB FLUID LOSS SMOKE/FUMES/ODORS/SPARKS NRNOT REPORTED 1 CA 1592815928 (CAN) AT THE GATE, CREW TURNED ON BOTH AIR CONDITIONING PACKS AND SMOKE/AND OR HAZE ACCOMPANIED BY ODOR BEGAN TO FILL THE COCKPIT AND CABIN. CREW IMMEDIATELY OPENED THE MAIN CABIN DOOR TO VENT THE AREA, AND SMOKE/HAZE BEGAN TO DISSIPATE. MAINTENANCE FOUND A MAJOR OIL LEAK FROM THE COMPRESSOR SECTION OF THE APU. OIL WAS INJESTED IN TO ONE OR BOTH PACKS. NEW APU INSTALLED. BOTH CONDENSOR BAGS REPLACED AND DUCTS CLEANED OF OIL. INFORMATION WILL BE UPDATED WHEN ROOT CAUSE OF LEAK IS AVAILABLE. (TC NR 20060816003) 2L72 4F4 FRTA21EA E15NE 20060913001912006091300191NE 2006 9 13 CA060816004 220060701G7230 COMPRESSOR SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1D1 NE ENGINE MALFUNCTIONED W E ENGINE SHUTDOWN E VIBRATION/BUFFET TXTAXI/GRND HDL 1 CA 3745 1396 (CAN) PILOT STARTED THE AIRCRAFT IN THE FIELD AND NOTICED THE THE START WAS VERY SLOW, HE RETURNED FROM A FLIGHT AND NOTIFIED THE MAINTENANCE STAFF OF THE PROBLEM. THEY HAD THE PILOT START THE AIRCRAFT AND NOTICED THAT THE ENGINE WAS VIBRATING, THEY MADE THE PILOT ABORT THE START. UPON FURTHER INVESTIGATION THEY MOTORED OVER THE ENGINE WITHOUT STARTING IT AND THERE WAS A SCREACHING GRINDING NOISE COMING FROM THE ENGINE. THEY INSPECTED THE STARTER GENERATOR AND CHECKED THE ENGINE AND DRIVE SHAFT FOR CONDITION BUT DIDN`T FIND ANYTHING. THEY HAND ROTATED THE POWER TURBINE BLADES AND THERE WASN`T ANY NOISE. THEY ROTATED THE COMPRESSOR AND DISCOVERED THAT THERE WAS RUBBING NOISE COMING FROM THE M03. THE ENGINE WAS R1G71 3U3 U H9EU E19EU 20070516001662007051600166NM 2007 5 16 CA060816005 120060815G7600 BEARING DHAV DHC8 DHC8301 1386003NM PWA PW120 PW123 NE HAMSTD14SF 14SF15 NE CONDITION CABLE SEIZED W K NONE O OTHER ININSP/MAINT 1 CA 3733137331 (CAN) DURING ROUTINE MAINTENANCE INSPECTION OF MFG TASK 422 (A CHECK 500 HR REPETITIVE TASK) ZONAL INSPECTION OF RT ENGINE COMPARTMENT. FOUND POWER AND CONDITION CABLE PULLEYS (2 EACH SYSTEM, TOTAL 4 PULLEYS) IN THE UPPER AFT NACELLE/FRONT OF WING SPAR, TO ALL HAVE SEIZED BEARINGS (1 PULLEY WITH BRG ASSY FALLING OUT OF PHENOLIC PULLEY). PULLEYS REPLACED AND ENGINE CONTROLS RE-RIGGED. AIRCRAFT HAD ACCUMULATED 492 HOURS SINCE LAST ACCOMPLISHMENT OF TASK 422, AND 2465 HOURS SINCE LAST ACCOMPLISHMENT OF TASK 7610/05 (C-CHECK 5500 HR TASK) VISUAL INSPECTION OF ENGINE POWER AND CONDITION CONTROL CABLES AND PULLEYS. (TC NR 20060816005) 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20061018000842006101800084SO 2006 10 18 CA060816006 120060815G5330 SKIN PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA HARTZLHCE3Y HCE3YR2A GL FUSELAGE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) WHILE DOING A MOD TO THE AIRCRAFT THE ELT ANTENNA HAD TO BE REMOVED. THE AIRCRAFT SKIN WAS FOUND TO BE CRACKED ON 2 SIDES OF THE ANTENNA. THE ANTENNA HAD NOT BEEN MOUNTED PROPERLY. (TC NR 20060816006) 1L72 3O3 O A20SO E14EA 5 CP33EA 20060913001922006091300192GL 2006 9 13 CA060817001 220060710G7320AN4H12A BOLT CVAC STC STC3405800 WP ALLSN 501D 501D13D 03004GL ALLSN A6441 A6441FN606 GL NR 2 FUEL WORN W E ENGINE SHUTDOWN F FLT CONT AFFECTED DEDESCENT 1 CA (CAN) THIS REPORT IS A FOLLOW-UP TO THE ORIGINAL VERBAL REPORT MADE IMMEDIATELY AFTER THE INCIDENT. THE AC LOST CONTROL OF THE NR 2 FUEL COORDINATOR AT THE TOP OF THE DECENT INTO YVR. THE (E) HANDLE WAS PULLED ON THE NR 2 ENGINE 5 MILES BACK FROM THE YVR APPROACH AND THE AIRCRAFT LANDED SAFELY. ON EXAMINATION WE DISCOVERED THAT THE PINCH BOLT THAT HOLDS THE FUEL COORDINATOR ONTO THE NOTCH IN A SPLINED SHAFT HAD WORN TO A POINT THAT THE COORDINATOR ARM CAME ADRIFT FROM THE FUEL COORDINATOR. WE HAVE CARRIED OUT A FLEET WIDE CAMPAIGN DIRECTIVE CHECKING ALL OUR IN-SERVICE CONVAIRS FOR BOLT CONDITION AND THREAD DAMAGE. WE REPLACED 9 OUT OF 14 BOLTS DUE TO SLIGHT WEAR, AS A PRECAUTION. (TC NR 20060817001) 2L72 4T4 TRT6A6 E282 6 CP898 20060913001942006091300194CE 2006 9 13 CA060817002 120060328G2432S35979 SENSOR CESSNA500 560CESSNA 2076750CE PWA 530 PW535A NE BATTERY FAILED W O OTHER N FALSE WARNING CRCRUISE 1 CA 573 (CAN) INTERMITTENT FAILURE OF TEMPERATURE SENSOR CAUSING INDICATED OVERTEMP OF AIRCRAFT MAIN BATTERY FOR SEVERAL SECONDS AT A TIME IN FLIGHT CAUSING MASTER CAUTION WARNING LIGHT ALSO. REPLACED TEMPERATURE SENSOR, SYSTEM CHECKED OK. NOTE THIS IS SECOND SENSOR TO FAIL IN 1284 HOURS. (TC NR 20060817002) 2L72 4F4 FRTA22CE E00053EN 20060913001972006091300197CE 2006 9 13 CA060817003 120060501G783025630005 SEAL PARKERHANFIN CESSNA500 560CESSNA 2076750CE PWA 530 PW535A NE T/R ACTUATOR LEAKING W O OTHER K FLUID LOSS TXTAXI/GRND HDL 1 CA 1385 1559 (CAN) IB THRUST REVRSER ACTUATOR LEAKING HYDRAULIC FLUID, GETTING PROGRESSIVELY WORSE, LEAKING FLUID TRAIL ON TR STANG. IB STANG CANNOT BE REMOVED MAKING DIAGNOSIS OF PROBEM DIFFICULT. REPLACED IB T/R ACTUATOR WITH OVERHAULED UNIT WHICH REQUIRED ENGINE TO BE REMOVED FROM THE AIRCRAFT. (TC NR 20060817003) 2L72 4F4 FRTA22CE E00053EN 20060913001982006091300198NE 2006 9 13 CA060817004 220060518G7532305265501 GASKET CESSNA500 560CESSNA 2076750CE PWA 530 PW535A NE BLEED VALVE BROKEN W O OTHER R PARTIAL RPM/PWR LOSS CRCRUISE 1 CA 1390 (CAN) ENGINE AT TAKEOFF AND CRUISE AT 40,000 FT AND ABOVE REQUIRED N2 TO BE HIGHER BY 1 - 1.5 PERCENT HIGHER THAN NORMAL FOR A SPECIFIC N1. PROBELEM FOUND TO BE A COMPRESSOR BLEED VALVE NOT CLOSING COMPLETELY. PROBLEM CAUSED BY LEAKING (BROKEN) GASKET BETWEEN COMPRESSOR BLEED VALVE AND BLEED VALVE SERVO (TORK MOTOR). (TC NR 20060817004) 2L72 4F4 FRTA22CE E00053EN 20060913002002006091300200CE 2006 9 13 CA060817005 120060619G251001073370 INERTIA REEL PACIFICSCIEN CESSNA500 560CESSNA 2076750CE PWA 530 PW535A NE SEAT BELT BROKEN W O OTHER W INADEQUATE Q C CRCRUISE 1 CA (CAN) COPILOT SHOULDER HARNESS (JAMS) WHEN EXTENDING: FOUND PLASTIC END COVER OF INERTIA REEL BROKEN LOOSE, CAUSING INTERIM REEL TO MALFUNCTION. CAUSED BY COPILOT PUTTING FLIGHT MANUALS ETC BEHIND SEAT AND PUSHING SEAT AFT ON SEAT RAILS WHICH PUSHED SEAT BOTTOM SKIRT INTO INERTIA REEL. - THIS IS TO BE CORRECTED BY EDUCATING THE (PILOTS) TO THE CAUSE OF THE PROBLEM AND THE REPLACEMENT OF THE INERTIA REEL. (TC NR 20060817005) 2L72 4F4 FRTA22CE E00053EN 20060913002402006091300240EA 2006 9 13 CA060817006 220060804G8530ST203 RING PIPER PA23 PA23250 7102308SO LYC O540 TIO540C1A 41532EA HARTZLHCE2Y HCE2YR2 GL CYLINDER DELAMINATED W K NONE O OTHER ININSP/MAINT 1 CA 506 506 104593 (CAN) THE TECHNICIANS OBSERVED AN ABNORMAL LOSS OF COMPRESSION ON SOME CYLINDERS FOLLOWING A ROUTINE INSPECTION. THEY REMOVED THE CYLINDERS AND SENT THEM TO OUR SHOP FOR INVESTIGATION. WE OBSERVED A DELAMINATION OF CHROME PLATING ON THE CYLINDER RINGS. WE REPAIRED THE CYLINDERS BY REPLACING THE DEFECTIVE PARTS WITH A NEW PARTS. THE MANUFACTURER HAS BEEN ADVISED ABOUT THE DEFECTIVE RINGS. (TC NR 20060817006) 1L72 3O3 O 1A10 E14EA 5 CP9EA 20060913002532006091300253EA 2006 9 13 CA060817007 220060817G8520 BEARING PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA HARTZLHCE3Y HCE3YR2A GL CRANKSHAFT DAMAGED W K NONE KB FLUID LOSS SMOKE/FUMES/ODORS/SPARKS ININSP/MAINT 1 CA 2209 L793261A (CAN) PILOTS NOTICED SMOKE COMING FROM THE LT ENGINE AFTER SHUTDOWN. THEY ALSO NOTICED AN OIL LEAK. FURTHER INVESTIGATION REVEALED THAT ONE CRANKSHAFT BEARING HAD BEEN MOVED FROM ITS ORIGINAL PLACE AND WAS NOW LOOSE. THE ENGINE IS BEING REMOVED FOR REPLACEMENT. A TEARDOWN REPORT WILL BE REQUESTED. (TC NR 20060817007) 1L72 3O3 O A20SO E14EA 5 CP33EA 20061018000852006101800085NM 2006 10 18 CA060818001 120060803G29102890410115 LINE DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HYD SYSTEM CRACKED W O OTHER K FLUID LOSS CRCRUISE 1 CA 33559 (CAN) HYD LINE IN UPPER FORWARD AREA OF NR 1 NACELLE CHAFED THROUGH AT ADJACENT ADELE CLAMP, LEAKAGE LOCATED AND LINE ASSY P/N 82970410-115 REPLACED, SYSTEM BLED AND REPRESSURIZED WITH NO FURTHER FAULTS. GOING THROUGH THE LAST 1 MONTH PERIOD THERE HAVE BEEN NO RELATED DEFECTS IN REGARDS TO ATA 29 ON THIS A/C. THIS WAS AN ISOLATED INCIDENT NOT A RECURRING DEFECT. NO SDR IS REQUIRED OR SUBMITTED. LAST SCHEDULED INSP WAS THE DAILY INSP OF AUG 3 /06 AT TTAF 33549.3 HRS CURRENT TTAF ON A/C 33559.7 HRS. NEXT INSP, DAILY INSP DUE AUG 4 2006 L CHECK AUG 8 2006. (TC NR 20060818001) 2H72 4T4 TRTA13NM E20NE 20061018000862006101800086SW 2006 10 18 CA060818002 120060817G5300S3526EC4 WASHER BELL 407 407 1182206SW ECU DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) THE -4 WASHER IS NOT CUT TO FIT THE BOLT AT THE SHANK, CAUSING FRETTING AND CORROSION ON THE SHANK RADIUS UNDER THE BOLT HEAD. (TC NR 20060818002) 1G71 3U O H2SW 20060913002542006091300254SW 2006 9 13 CA060818003 120060803G5302407530014101 SKIN BELL 407 407 1182206SW ALLSN 250C 250C47B GL TAILBOOM CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 1700 (CAN) DURING SCHEDULED 150 HOUR TAILBOOM INSPECTION A CRACK MEASURING .7500 OF AN INCH LONG WAS DISCOVERED ON THE UPPER LT SIDE OF THE TAILBOOM AT STATION 98.89. AIRCRAFT WAS GROUNDED AND A NEW TAILBOOM WAS ORDERED (200 SERIES). (TC NR 20060818003) 1G71 3U3 UO H2SW E1GL 20061018000872006101800087SW 2006 10 18 CA060818004 120060814G6720UK BOLT BELL 204 204B 1181404SW LYC T53 T5311B 41549NE TAIL ROTOR LOOSE W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING A 100 HOUR INSPECTION THE ENGINEER NOTED A LARGE AMOUNT OF PLAY IN THE CLEVIS OF THE TAIL ROTOR FLIGHT CONTROL ROD. INVESTIGATION REVEALED AN UNDERSIZED BOLT , IE SMALLER DIAMETER, WAS INSTALLED. THE CORREECT BOLT, P/N AN175-20 WAS INSTALLED AND A FUNCTION CKECK CARRIED OUT, WITH NO FAULT FOUND. AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20060818004) 1G71 4U4 U H1SW E1EA 20060913002552006091300255GL 2006 9 13 CA060818005 220060816G72306887167 CASE ALLSN BELL 206 206B 1181511SW ALLSN 250C 250C20 03013GL COMPRESSOR ERODED W K NONE O OTHER ININSP/MAINT 1 CA 1677 CAC33790 (CAN) AIRCRAFT WAS IN FOR AN INSPECTION. THE COMPRESSOR CASE HALVES HAD 23 HOURS LT TO A 1750 INSPECTION. MFG REQUESTED THAT WE CARRY OUT THE INSPECTION. IT WAS FOUND THAT THE 2ND AND 3RD STAGE STATOR BLADES WERE SO UNDER CUT FROM EROSION (NEAR THE ROOT OF THE BLADES) THAT A COMPRESSOR BLADE FAILURE WAS GOING TO OCCUR. IN SOME SPOTS THE PLASTIC LINEAR WAS ERODED TO THE BARE METAL. THE AIRCRAFT DOES HAVE A INTAKE PARTICLE SEPARATOR KIT INSTALLED. ANOTHER COMPRESSOR WAS INSTALLED. (TC NR 20060818005) 1G71 3U3 U H2SW E4CE 20061018000882006101800088NE 2006 10 18 CA060818006 120060817G291366WBL200 BOLT NYAIRBRAKE SKRSKYS61 S61L 8142102NE GE CT58 CT581401 30011NE HYD PUMP BROKEN W K NONE O OTHER ININSP/MAINT 1 CA 234 A0259 (CAN) THE HYDRAULIC PUMP WAS BEING REMOVED FOR MAINTENANCE PLANNING, WHEN 2 BOLT HEADS WERE FOUND TO BE SHEARED OFF, AND HELD IN PLACE BY THE LOCK WIRE. PUMP WILL BE SENT TO VENDOR FOR INVESTIGATION. PUMP WAS OPERATING NORMALLY. (TC NR 20060818006) 2G72 4U4 U 1H15 1E3 20060913002562006091300256CE 2006 9 13 CA060821001 120060812G3242075302781 PLATE CESSNA206 U206F 2073333CE CONT O520 IO520F 17032SO HARTZLHCC3Y PHCC3YF1 GL LT BRAKE SYS CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 4000 (CAN) TORQUE PLATE TOP GUIDE FOR BRAKE CALIPER CRACKED AND BROKE OFF LEAVING CALIPER ATTACHED BY BOTTOM GUIDE HOLE ONLY. PART REPLACED WITH NEW. (TC NR 20060821001) 1H71 3O3 O A4CE E5CE 5 CP25EA 20060913002572006091300257CE 2006 9 13 CA060821002 120060815G6123C1650130604 WIRE HARNESS MCAULY 3AF32C88 CESSNA310 310Q 2074242CE CONT O520 TSIO520B 17040SO MCAULY3AF32C3AF32C* GL PROPELLER WRONG PART W O OTHER W INADEQUATE Q C CRCRUISE 1 CA 739222 (CAN) HARNESS TOO SHORT WOULD NOT ALLOW PROPELLER TO FEATHER. PILOT COULD NOT FEATHER LT OR RT PROPELLERS DURING TRAINING FLIGHT. WRONG PROPELLER DEICE WIRING HARNESSES FOUND INSTALLED AND REPLACED WITH CORRECT P/N D5855-1. (TC NR 20060821002) 1L72 3O3 O 3A10 E8CE 5 CP22EA 20060913002592006091300259EA 2006 9 13 CA060821003 120060812G281021564002 FUEL CELL CNDAIRCL215 CL2151A10 1900320EA PWA PW120 PW123 NE HAMSTD14RF 14RF19 NE FUEL SYSTEM LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA 1361 (CAN) UPON INSPECTION IT WAS DETERMINED THAT THE FUEL LEAK WAS COMING FROM THE RT FUEL CELLS. ALL 8 FUEL CELLS WERE REMOVED AND INSPECTED AND FUEL CELLS NRS 3 AND 4 AND 6 AND 8 WERE LEAKING P/N AND S/N AND POSITION OF LEAKING CELLS. 215-64002-4 S/N 74730 NR 3 CELL 215-64002 S/N 74770 NR 4 CELL 215-64002 S/N 74586 NR 6 CELL 215-64075-1 S/N 72476 NR 8 CELL. (TC NR 20060821003) 2H72 4R4 TRTA14EA E20NE 6 CP11NE 20070516001672007051600167EA 2007 5 16 CA060821004 220060808G732132447531917 FCU DHAV DHC7 DHC7102 2802708EA PWA PT6 PT6A50 52043EA HAMSTD24PF 24PF305 GL NR 1 ENGINE FAILED W D RETURN TO BLOCK XJ ENGINE FLAMEOUT WARNING INDICATION TXTAXI/GRND HDL 1 CA (CAN) AFTER INSTALLING THE FRESHLY OVERHAULED ENGINE IN THE NR 1 POSITION, THE ENGINE WAS STARTED TO PERFORM THE BETA RIGGING; THE PROPELLER WAS UNFEATHERED, THE POWER LEVEL MOVED UP TO THE FWD BETA STOP TO RECORD NUMBERS, ALL THE PARAMETERS STABILIZED. THE NUMBERS WERE ABOUT TO BE RECORDED WHEN THE FCU. FAILED, ALL ENGINE PARAMETERS ACCELERATED. THE POWER LEVER WAS PULLED BACK AND THE ENGINE KEPT ACCELERATING. THE T-HANDLE WAS USED TO SHUTDOWN THE ENGINE. NO ENGINE LIMITS WERE EXCEEDED. THE FCU WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. THE FCU WAS FRESHLY OVERHAULED AND IT HAS BEEN RETURNED TO THE OVERHAUL FACILITY FOR REPAIR. (TC NR 20060821004) 2H74 4T4 T A20EA E4EA 6 CP1NE 20061018000892006101800089CE 2006 10 18 CA060821005 120060812G7921723747 BYPASS VALVE RAYTHN BEECH B300 B300 1159232CE PWA PT6 PT6A60A 52043NE HARTZLHCB4M HCB4MP3 GL OIL COOLER FAILED W A UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 CA 1168 1168 6176 (CAN) RT OIL TEMPERATURE REACHED THE REDLINE WHEN CLIMBING THROUGH 25000 FT. POWER REDUCED AND A/C DESENDED TO 20000 FT. OIL TEMP RETURNED TO NORMAL. ENG POWER SETTING RETURNED TO NORMAL, NO FURTHER FAULT. NR 2 ENGINE OIL COOLER THRMOSTATIC BYPASS VALVE REPLACED IAW MM CH 79-00-00 P 9. GROUND/LEAK CHECKS PERFORMED. SYSTEM CHECKS SERVICEABLE. (TC NR 20060821005) 2L72 4T4 TRTA24CE E4EA 6 CP56GL 20060913002602006091300260NE 2006 9 13 CA060821006 220060726G72304029T16P13P15 RETAINER GE GE CF34 CF343B1 NE FAN ROTOR CRACKED W K NONE O OTHER ININSP/MAINT 1 CA VARIOUS 807315C (CAN) DURING ROUTINE SCHEDULED ENGINE MAINTENANCE, AFTER VISUAL, DIMENSIONAL, AND NON-DESTRUCTIVE INSPECTION, A HIGH NR OF FAN BLADE RETAINING PINS WERE REJECTED FOR CRACKING, DETAILS AS FOLLOWS: ESN 807315C QTY 28 OF 28 P/N 4029T16P15 PINS CRACKED. ESN 872933 - QTY 18 OF 28 P/N 4029T16P13 PINS CRACKED. ESN 872934 - QTY 11 OF 28 P/N 4029T16P13 PINS CRACKED. FURTHER INVESTIGATION AND REVIEW INDICATES THAT THE REJECT RATE FOR THESE COMPONENTS MAY BE UNUSUALLY HIGH ON THE SUBJECT ENGINES. DUE TO THE CRITICAL NATURE OF THE COMPONENT, HAVE INITIATED COMPONENT FAILURE INVESTIGATIONS. PRODUCT SUPPORT ENGINEERING HAS REPORTED THIS CONDITION TO THE FAA, REF. FM&D REPORT CF34-3/06-02. (TC NR 20060821006) 4 F E15NE 20060913002612006091300261CE 2006 9 13 CA060822001 120060805G3246 BOLT BFGOODRICH CESSNA650 650 2076802CE GARRTTTPE731TFE7313C WP MLG WHEEL BROKEN W K NONE O OTHER ININSP/MAINT 1 CA 6248 1841 (CAN) ON DAILY INSPECTION, FOUND (1) BOLT BROKEN ON NR 4 MAIN WHEEL ASSY. (TC NR 20060822001) 2L72 4F4 F A9NM E6WE 20061018000902006101800090EU 2006 10 18 CA060822002 120060818G3246C201950001 WHEEL AIRBUS310 A310 EU GE CF6 CF680C2* GL MLG CRACKED W D RETURN TO BLOCK J WARNING INDICATION TXTAXI/GRND HDL 1 CA (CAN) DURING THE AIRCRAFT PUSHBACK, IT WAS NOTED ON THE ECAM THAT NR 8 MAIN WHEEL WAS LOOSING PRESSURE. AFTER RETURNING TO THE GATE, IT WAS CONFIRMED USING A REGULAR TIRE PRESSURE GAUGE THAT THE PRESSURE WAS DROPPING. USING LEAK DETECTOR FLUID, IT WAS DETERMINED TO BE LEAKING FROM A CRACK BETWEEN TWO TIE BOLTS IN THE OUTER HUB SECTION. WHEEL WAS REPLACED AND ROUTED TO THE REPAIR SHOP FOR INVESTIGATION. (TC NR 20060822002) 2L72 4F4 FRTA35EU E23EA 20061018000912006101800091EU 2006 10 18 CA060822003 120060816G2910A29181081000 LINE AIRBUS310 A310 EU GE CF6 CF680C2* GL HYDRAULIC SYS CHAFED W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) DURING ROUTINE MAINTENANCE INSPECTION, FOUND NR 1 ENGINE DRIVEN PUMP OUTLET PRESSURE TUBE OF GREEN HYDRAULIC SYSTEM CHAFED BY THE AILERON TRIM INPUT CABLE AT REAR SPAR OB OF RIB 5A. HYDRAULIC TUBE REPLACED. CAMPAIGN INITIALIZED TO VERIFY THE REST OF THE FLEET AND ALL FINDING WILL BE REPORTED TO MFG FOR EVALUATION. (TC NR 20060822003) 2L72 4F4 FRTA35EU E23EA 20060913002632006091300263NM 2006 9 13 CA060822004 120060727G7160001A716E1000010 INTAKE DORNERDO32 DO328100 2996000NM NR 1 ENGINE DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA 4393 (CAN) OUR AC WAS ABOUT TO DEPART WHEN DEFECT WAS SPOTTED. DURING A NORMAL PRE-FLIGHT PILOT WALK AROUND OUR PILOT NOTICED A GAP/ ABNORMAL SPACE BETWEEN THE LOWER ENGINE INLET AND THE UPPER MATING COWL. WE GROUNDED THE A/C TO AOG STATUS AND SENT AME`S TO RESCUE. AME`S DISCOVERED QTY. 3 MISSING MOUNTING HARDWARE BOLTS, NUTS AND WASHERS, WHICH ARE STILL MIA. ALSO QTY. 1 MOUNTING BOLT WAS FOUND STILL IN PLACE BUT WAS SHEARED OFF COMPLETELY AND THE APPARENT STRESS CAUSED THE ENGINE METAL MATING FLANGE TO BREAK A 1 INCH DIA. APPROX SECTION OFF AT THE FWD. OB AREA. AME REPLACED THE LOWER INLET ASSY. WITH SAME P/N AND S/N AND ADDED THE WIDER WASHERS MINOR REPAIR IAW MM 72-20-00-300-801-A01-001. A (SPR) SERVICE PR2H72 4T RTA45NM 20060913002642006091300264NM 2006 9 13 CA060822005 120060822G2710BACP30F9 PULLEY BOEING737 737522 138449FNM CFMINTCFM56 CFM563C1 13802EU RT AILERON CORRODED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING A PHASE CHECK, A GRINDING NOISE WAS HEARD WHEN THE AILERON WAS MOVED BY HAND TO CHECK FOR FREEDOM OF MOVEMENT. UPON FURTHER INVESTIGATION,THE BOLT HOLDING THE PULLEY IN PLACE WAS REMOVED AND THE BEARING FELL APART. BEARING WAS SEVERELY CORRODED AND BUSHING FOUND TO BE GOUGED. PULLEY AND BUSHING REPLACED. TIMES: 36,972.52 CYCLES: 23,427 (TC NR 20060822005) 2L72 4F4 FRTA16WE E21EU 20061018000922006101800092CE 2006 10 18 CA060822006 120060822G5311504200285758 FRAME BEECH 90 E90 1152914CE PWA PT6 PT6A28 EA HARTZLHCB3T HCB3TN3 GL BS 176 CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 22986 (CAN) LT SIDE OF FUSELAGE, DISCOVERED 4 LOOSE RIVETS AT FS 176.5. MAINTENANCE DEPT REMOVED INTERIOR TO INVESTIGATE DEFECT. IT WAS DISCOVERED THAT FRAME MEMBER P/N 50-420028-57 WAS CRACKED IN SEVEN SPOTS. MAINTENANCE DECIDED TO INVESTIGATE THE RIGHT HAND OF FUSELAGE EVEN THOUGH NO INDICATION FROM OUTSIDE OF AIRCRAFT. ONLY THREE CRACKS WERE DISCOVERED THERE TO FRAME P/N 50-420028-58. TOTAL CYCLES SINCE LAST DETAILED FUSELAGE INSPECTION OF THESE AREAS IN 1859. REPETITIVE EVERY 3000 CYCLES. NO PREVIOUS DAMAGE NOTED. (TC NR 20060822006) 1L72 3T4 T 3A20 E4EA 6 CP15EA 20061018000932006101800093GL 2006 10 18 CA060822008 120060814G2820C2P2009 LINE DHAV DHC2 DHC2MKI 2801830GL PWA R985 R985AN14B 52008NE HARTZLHCB3R HCB3R304 GL FUEL SYSTEM CORRODED W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) ON INSPECTION, NOTICED FUEL PIPE FROM PUMP TO SHUT-OFF VALVE (BEHIND ENGINE) STAINED GREEN, FOUND CLEARANCE BETWEEN PIPE AND RUDDER PEDAL TQ TUBE INSUFICIENT CAUSING FRETTING/DISSIMILAR CORROSION PITTING ON TUBE CAUSING FUEL LEAK (TC NR 20060822008) 1H71 3R3 RRCA806 5E1 5 CP28EA 20061018000942006101800094NM 2006 10 18 CA060823001 120060823G2710BACP30F9 PULLEY BOEING737 737522 138449FNM CFMINTCFM56 CFM563C1 13802EU LT AILERON SEIZED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING A PHASE CHECK THE LT AILERON CABLE PULLEY WAS FOUND TO HAVE A SEIZED BEARING AND A WORN PULLEY. PULLEY AND BEARING REPLACED. A FLEET CAMPAIGN WILL BE INIATED TO CHECK ALL AILERON PULLEYS FOR FREEDOM OF MOVEMENT AND BEARING CHECK. TIMES: 36,972.52 CYCLES: 23,427 (TC NR 20060823001) 2L72 4F4 FRTA16WE E21EU 20061018000952006101800095GL 2006 10 18 CA060823002 320060822G6114 HUB LKHEED188 188LKHEED* WP ALLSN 501D 501D13 03004GL ALLSN A6441 A6441FN606 GL PROPELLER LEAKING W EA ENGINE SHUTDOWN UNSCHED LANDING KRJFLUID LOSS PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 1 CA 659 HC2555 (CAN) RPM DROOPED TO 13,400 RPM. ENGINE SHUTDOWN AND LANDING IAW SOP. PROP OIL LEAKING OUT OF VENT HOLE IN PROPELLER HUB. (TC NR 20060823002) 2L74 4T4 T 4A22 E282 6 CP898 20061213001392006121300139 2006 12 13 CA060824002 120060821G324650140251 RETAINING RING MAIN WHEEL CRACKED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) DURING SHOP VISIT AND UPON DISASSEMBLY FOR TIRE REPLACEMENT, RETAINING RING FOR THE OUTER WHEEL HALF FOUND SPLIT AXIAL APPROXIMATELY 60 PERCENT OF ITS CIRCUMFERENCE. (TC NR 20060824002) 20060913002682006091300268WP 2006 9 13 CA060824003 220060818G73228978017 FUEL CONTROL SWRNGNSA226 SA226TC 8780404SW GARRTTTPE331TPE33110UA 01514WP HARTZLHCB3T HCB3TN5 GL LT ENGINE MALFUNCTIONED W E ENGINE SHUTDOWN XJ ENGINE FLAMEOUT WARNING INDICATION LDLANDING 1 CA 2552 (CAN) UPON LANDING, CREW APPLIED REVERSE THRUST. BELOW 70 KIAS, THE RPM LEVER WAS SELECTED TO (LOW). ON THE TAXIWAY, THE CREW NOTED VERY LOW ENGINE RPM, LOW OIL PRESSURE LIGHT, AND LOW EGT. THEY DETERMINED THE ENGINE HAD FLAMED OUT AND PARTIALLY RESTARTED. A NORMAL SHUTDOWN WAS CARRIED OUT. A SUBSEQUENT MAINTENANCE GROUND RUN WAS ABLE TO DUPLICATE THE FAILURE, WHEN THE SPEED LEVER WAS RAPIDLY MOVED FROM HIGH TO LOW. THE FUEL CONTROL AND FUEL PUMP WERE REPLACED WITH SERVICEABLE UNITS. (TC NR 20060824003) 2L72 4T4 TRTA8SW E4WE 6 CP15EA 20060913002692006091300269SW 2006 9 13 CA060824004 120060822G29102781006495 LINE SWRNGNSA226 SA226TC 8780404SW GARRTTTPE331TPE33110UA 01514WP HARTZLHCB3T HCB3TN5 GL HYDRAULIC SYS LEAKING W O OTHER KJ FLUID LOSS WARNING INDICATION CRCRUISE 1 CA (CAN) AIRCRAFT WAS IN CRUISE, CREW NOTED HYDRAULIC LEAKAGE ON THE COCKPIT FLOOR. CONDUCTED A NORMAL LANDING, NOSE GEAR UP LINE IN COKPIT WAS LEAKING. REPLACED LINE, ON NEXT LEG, A LINE FAILED IN THE LH GEAR WELL, CREW ACTIVATED EMERGENCY EXTENSION AND NORMAL LANDING CARRIED OUT. THE FOLLOWING DAY ANOTHER LINE CRACKED IN THE WHEEL WELL. MAINTENANCE SERVICED THE ACCUMULATOR AFTER THE SECOND OCCURENCE AND NOTED THE PRESSURE WAS LOW. AFTER THE THIRD OCCURENCE, THE ACCUMULATOR WAS REPLACED AS A PRECAUTION. NO OTHER OCCURENCES THAT WEEK. ON THE WEEKEND, MAINTENANCE PLACED THE AIRCRAFT ON JACKS, AND FOUND SMALL PRESSURE FLUCTUATIONS DUE TO A FAILED MAIN GEAR UPLOCK POWER PACK SWITCH. THE SWITCH WAS REPLACED, THE2L72 4T4 TRTA8SW E4WE 6 CP15EA 20061018000962006101800096NM 2006 10 18 CA060825001 120060822G2997W44000118 WIRE BOEING767 767333 1385301NM PWA 4060 PW4060 52119NE HYD PUMP CHAFED W K NONE O OTHER ININSP/MAINT 1 CA 50063 (CAN) LT ELECTRIC HYDRAULIC PUMP PRESSUE SWITCH S27 WIRING FOUND CHAFED 6 INCHES FROM CONNECTOR D56, WIRING TEMPORARILY REPAIRED IAW AMM FAULT WAS INTERMITTENT AND 4 S27 PRESSURE SWITCHS HAD BEEN REPLACED OVER THE LAST FEW MONTHS. (TC NR 20060825001) 2L72 4F4 FRTA1NM E24NE 20060913002702006091300270CE 2006 9 13 CA060825002 120060823G552007321008 HINGE CESSNA185 A185F 2072821CE CONT O520 IO520D 17032SO HARTZLHCC3Y HCC3YF1 GL STABILIZER CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 3522 (CAN) HINGE ASSEMBLY FOR STABILIZER OB BEARING WAS FOUND CRACKED FOR BOTH ELEVATORS. ELEVATORS REMOVED. SEVERAL CRACKS WERE FOUND ON EACH HINGE ASSEMBLY. HINGE ASSEMBLIES REPLACED ON STABILIZER. ALL PARTS INSTALLED USING NEW (AN) HARDWARE. INDEPENDENT CONTROL CHECK CARRIED OUT. (TC NR 20060825002) 1H71 3O3 O 3A24 E5CE 5 CP25EA 20060913002712006091300271CE 2006 9 13 CA060825003 120060513G5511053200198 SPAR CESSNA172 172K 2072430CE LYC O320 O320E2D 41508EA MCAULY1A175 1A175* GL STABILIZER CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 14693 (CAN) P/N 0532001-97 SPAR REINFORCEMENT AND P/N 0532001-98 FRONT SPAR ASSEMBLY WAS REPALCED DUE TO CRACKED CENTER SECTION OF MAIN SPAR. PARTS WERE INSTALLED USING EXISTING RIVET SIZE AND PATTERN ACCORDING TO SPECIFIED APPROVED METHODS IN MFG SRM. (TC NR 20060825003) 1H71 3O3 ONT3A12 E274 5 NP857 20060913002722006091300272CE 2006 9 13 CA060825004 120060820G7830183238001 SOLENOID CESSNA750 750 2076810CE THRUST REVERSER DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) FOUND THAT THE SOLINOID SHAFT HAD BEEN GROUND DOWN TO ACCOMIDATE A CLEVIS PIN THAT WAS NOT LONG ENOUGH. HALF THE MATERIAL ON THE SHAFT HAD BEEN REMOVED. THIS WAS FOUND ON INSPECTION OF THE TR SYSTEM FOR STICKY TR LEVERS. AT THIS TIME WE DO NOT THINKING THAT IT HAD ANY THING TO DO WITH THE ORIGINAL SNAG. (TC NR 20060825004) 2L72 4J RTT00007WI 20060913002742006091300274NE 2006 9 13 CA060828001 220060828G73146052T06P05 PUMP CNDAIRCL601 CL6012A12 1900303EA GE CF34 CF343A 30015NE ENGINE FUEL BROKEN W O OTHER J WARNING INDICATION NRNOT REPORTED 1 CA 5621 2673 (CAN) LT MAIN AND SCAVENGE EJECTOR FAILURE (MOTIVE FLOW FAILURE). FUEL PUMP SHAFT FOUND BROKEN. FUEL PUMP REPLACED AND AIRCRAFT RETURNED TO SERVICE. A/C HOURS; 25194:25 CYCLES; 29896 (TC NR 20060828001) 2L72 4F4 FRTA21AE E15NE 20061018000972006101800097CE 2006 10 18 CA060828002 120060828G323025800 SELECTOR VALVE BEECH 90 B90 1152912CE PWA PT6 PT6A20 52043EA HARTZLHCB3T HCB3TN3 GL MLG FAILED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING THE SCHEDULED TASK TO LEAK CHECK THE LANDING GEAR SYSTEM (LANDING GEAR MM M-8101, ROUTINE MAINTENANCE) IT WAS NOT POSSIBLE TO BUILD PRESSURE IN THE LANDING GEAR HYDRAULIC SYSTEM WITH THE MANUAL PUMP INSTALLED. UPON INVESTIGATION IT WAS FOUND THAT FLUID WAS BEING ROUTED TO THE DOWN PORT AND THE RETURN PORT AT THE SAME TIME. ELECTRICAL POWER WAS ON THE AIRCRAFT AND THE LANDING GEAR SELECTED TO THE DOWN POSITION. THIS VALVE HAD BEEN PREVIOUSLY REMOVED FROM ANOTHER SIMILAR TYPE AIRCRAFT FOR THE SAME PROBLEM AND WAS REPAIRED. REF NR ASR-6188-011605. WHEN CYCLED USING THE AIRFRAME SYSTEM HYDRAULIC PUMP THE LANDING GEAR OPERATED CORRECTLY AND APPEARED TO NOT HAVE AN FAULTS. (TC NR 20060828002) 1L72 3T3 T 3A20 E4EA 6 CP15EA 20061018000982006101800098CE 2006 10 18 CA060828003 120060828G323025800 SELECTOR VALVE BEECH 90 B90 1152912CE PWA PT6 PT6A20 52043EA HARTZLHCB3T HCB3TN3 GL MLG MALFUNCTIONED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) ON SCHEDULED MAINTENANCE 1000 HRS HYD. SYSTEM 3000 PSI LEAK TEST (LANDING GEAR MM M-8101, ROUTINE MAINTENANCE) HYD. SELECTOR FOUND LEAKING TO RETURN ON GEAR DOWN SECTION. WAS UNABLE TO BUILD UP PRESSURE TO OPERATE GEAR WITH MANUAL EXTERNAL PUMP. NEW HYD. SELECTOR INSTALLED AND IT WAS FOUND LEAKING TO RETURN ON GEAR UP SELECTION. WHEN LANDING GEAR CYCLED WITH AIRCRAFT HYD.PUMP SYSTEM OPERATES NORMALLY. SUSPECT NOT TESTING HYD. SELECTOR VALVES BOTH OLD AND NEW VALVES OVERHAULED BY THEM. (TC NR 20060828003) 1L72 3T3 T 3A20 E4EA 6 CP15EA 20061018000992006101800099WP 2006 10 18 CA060828004 120060827G6420 BEARING ROBSIN ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE T/R PITCH LINK WORN W K NONE O OTHER ININSP/MAINT 1 CA 53 (CAN) PITCH LINKS WERE FOUND TO BE CONTACTING THEIR SPACERS, CAUSING THEM TO WEAR INTO THE STAKING AROUND THE BEARING ON THE PITCH LINKS. TAFT 53.1 HOURS. ALL HARDWARE WAS PROPERLY INSTALLED. (TC NR 20060828004) 1G71 3O3 O H11NM 1E4 20061018001002006101800100WP 2006 10 18 CA060828005 120060826G6420 BEARING ROBSIN ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE T/R PITCH LINK WORN W K NONE O OTHER ININSP/MAINT 1 CA 162 (CAN) PITCH LINKS WERE FOUND TO BE CONTACTING THEIR SPACERS, CAUSING THEM TO WEAR INTO THE STAKING AROUND THE BEARING ON THE PITCH LINKS. TAFT 161.6 HOURS. ALL HARDWARE WAS PROPERLY INSTALLED. THIS WAS THE SECOND OCCURENCE OF THIS ON OUR FLEET IN 2 DAYS. THE MFG HAS RECENTLY CHANGED THE PART FROM B345-2 TO B345-4. THE INSTALLATION IS THE SAME. THIS WAS NEVER A PROBLEM WITH THE -2 PART. (TC NR 20060828005) 1G71 3O3 O H11NM 1E4 20061018001012006101800101SW 2006 10 18 CA060829001 120060829G2910AN937D6 FITTING BELL 206 206B 1181511SW ALLSN 250C 250C20B 03013GL HYD SYSTEM CORRODED W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) DURING INSPECTION, A LEAK WAS DISCOVERED IN THE HYDRAULIC SYSTEM PRESSURE SIDE CROSS FITTING (AN 937-D6). DISASSEMBLY REVEALED CORROSION AT MATING SURFACE OF O-RING AND CROSS. PART REPLACED WITH NEW. O-RINGS AND RETAINING RING REPLACED. SYSTEM SERVICED WITH HYDR OIL. (TC NR 20060829001) 1G71 3U3 U H2SW E4CE 20060913002772006091300277EA 2006 9 13 CA060829002 220060828G8550982C9HE2 ENGINE GRUMANTS2 TS2ACALFORST3951102WP WRIGHTR1820 982C9HE2 67020EA HAMSTD43D 43D51 NE NR 2 OVERTEMP W EA ENGINE SHUTDOWN UNSCHED LANDING MJ OVER TEMP WARNING INDICATION CLCLIMB 1 CA 341 (CAN) AIRCRAFT DEPARTED ENROUTE TO A FIRE. PILOT NOTED THE OIL TEMP ON NR 2 ENGINE WAS VERY HIGH. THE ENGINE WAS SHUTDOWN AND THE PROPELLER WAS FEATHERED. THE AIRCRAFT RETURNED AND LANDED. UPON INVESTIGATION BY MAINTENANCE STAFF, THE MAIN OIL SCREEN WAS FOUND TO BE CONTAMINATED WITH BRONZE MATERIAL. IT APPEARS THAT THE MAIN BEARING FAILED. THE ENGINE IS BEING REPLACED WITH A SERVICEABLE UNIT AND THE AIRCRAFT WILL BE RETURNED TO SERVICE. (TC NR 20060829002) 2H72 4R4 R A25WE E259 6 CP8879 20061018001022006101800102EU 2006 10 18 CA060829003 120060825G3244308419030 TIRE AEROSPATR42 ATR42300 8680920EU PWA 120 PW120 NE HAMSTD14SF 14SF5 NE MLG FAILED W C ABORTED TAKEOFF O OTHER TOTAKEOFF 1 CA (CAN) ON DEPARTURE A PIECE OF TIRE WAS FOUND ON THE RUNWAY. THE AIRCRAFT CARRIED OUT A NORMAL LANDING WITHOUT FURTHER INCIDENT. MAINTENANCE REPLACED NR 1 AND 2 MAIN WHEEL ASSYS, AND THE LT MAIN GEAR DOOR DUE TO DAMAGE FROM THE DEPARTED TREAD SEGMENT (APPROX. 12 INCH X 3 INCH) BEFORE RETURNING THE AIRCRAFT TO SERVICE. (TC NR 20060829003) 2H72 4T4 TRTA53EU E20NE 6 CP7NE 20060913002802006091300280NM 2006 9 13 CA060829004 120060805G273069403483 BEARING BOEING737 737217 1384464NM PWA JT8 JT8D17A 52049NE ELEVATOR CONTROLSEIZED W O OTHER F FLT CONT AFFECTED APAPPROACH 1 CA 64027 (CAN) AIRCRAFT ENCOUNTERED INTERMITTENT REPEAT SNAGS FOR STIFF ELEVATOR MOVEMENT. FINAL RECTIFICATION CAME ON AUGUST 5 2006 WHEN THE REFERENCED BEARING AND RETAINER WERE REPLACED. REFERENCED BEARING WAS FOUND SEIZED. CURRENT MAINTENANCE PROGRAM WAS REVIEWED TOWARDS THIS FINDING. INSP TASKS ARE CONDUCTED EVERY C CHECK. HAS MFG HAD OTHER REPORTS OF STIFF ELEVATORS DUE TO THE REFERENCED BEARING. 2) IF SO, DOES MFG HAVE THE TOTAL TIME OF THE AIRCRAFT WITH THOSE REPORTS. (IE TO DETERMINE IF A LIFE LIMIT EXISTS) 3) MAINTENANCE C CHECK TASKS UTILIZE AMM 27-31-0. AMM D6-12010 IS USED FOR THE AIRCRAFT INVOLVED. AMM 27-31-0 PAGE 535 2.B CONTAINS SPRING SCALE LIMITS FOR DIFFERENT ELEVATOR DEFLECTIONS (HYDRAULICS2L72 4F4 F A16WE E2EA 20061018001032006101800103 2006 10 18 CA060829005 420060811G2565GOODRICH SLIDE BOEING767 767* NM GE CF6 CF680C2B6F 30025NE NO TEST W K NONE L NO TEST ININSP/MAINT 1 CA (CAN) DURING SCHEDULED INSPECTION OF OFF-WING SLIDE COMPARTMENT DOOR LATCHES AND DISCONNECT HOUSING IAW SB 767-25A0260, BOTH OFF-WING SLIDES WERE INFLATED WITHOUT THE ASSOCIATED SLIDE COMPARTMENT DOOR BEING COMMANDED OPEN. AS A RESULT THE COMPARTMENT DOORS, LATCHES, SLIDES AND IB FLIGHT CONTROLS WERE DAMAGED BY THE FORCE OF THE CONFINED SLIDES. ZOOM AIRLINES HAS HAD 2 PREVIOUS SIMILAR UNCOMMANDED OFF-WING SLIDE DEPLOYMENTS (JULY 29, 2005 AND SEPTEMBER 2, 2005) DURING ROUTINE MAINTENANCE. IN BOTH PREVIOUS INCIDENTS ZOOM HAS INVESTIGATED AND TAKEN MITIGATING ACTIONS. MFG IS WELL AWARE OF THE SERVICE RELATED PROBLEMS. REF 767-FTD-25-00004, 767-FTD-25-03003, 767-FTD-25-06001. ZOOM`S TCCA PMI HAS ASKED THAT T2L72 4F4 FRTA1NM E13NE 20060913002812006091300281EU 2006 9 13 CA060830001 120060828G27509787320016 WARNING SYSTEM PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL TE FLAPS MALFUNCTIONED W A UNSCHED LANDING F FLT CONT AFFECTED CRCRUISE 1 CA 159 (CAN) 1 HR INTO CRUISE AT FL 220 PILOT EXPERIENCED INSTANTANEOUS AURAL AND VISUAL WARNINGS OF MULTIPLE SYSTEMS FAILURE. CAUTION ADVISORY PANEL DISPLAYED PUSHER INOP, FLAPS INOP, AUTO PILOT FAIL; FLAP POSITION INDICATOR JUMPED FROM 0 DEG TO 40 DEG.ALSO INDICATING RED OVERSPEED, EADI FAILED TO RAW DATA ONLY ,GEAR INDICATOR LIGHTS WENT TO THREE RED/ UNSAFE,GEAR AND FLAP WARNING TONES AUDIBLE. AFTER APPX. 20 MIN. ALL SYSTEMS SUDDENLY REVERTED TO NORMAL EXCEPT FOR THE FLAPS WHICH REQUIRED A FLAP RESET BY MAINTENANCE FLAPS THEN FUNCTION NORMALLY.PILOT COMPLETED FLIGHT AT ZERO FLAP.MAINTENACE TROUBLESHOOTING IDENTIFIED ONE FAULT CODE ON A/C COMPUTER INDICATING A POSSIBLE FLAP CONTROL WARNING UNIT ERROR.THE FCWU WAS R1L71 3T4 TRTA78EU E26NE 5 CP210NE 20060913002822006091300282EA 2006 9 13 CA060830002 120060817G7810 NOZZLE CNDAIRCL215 CL2156B11215 EA PWA PW120 PW123 NE HAMSTD14SF 14SF* NE RT ENG EXHAUST DETACHED W E ENGINE SHUTDOWN D INFLIGHT SEPARATION TXTAXI/GRND HDL 1 CA 4032 (CAN) DURING ENGINE START-UP, AN OVERHEAT CONDITION WAS DETECTED IN THE RT ENGINE EXHAUST AREA. THE ENGINE WAS SHUTDOWN AND CAUSE OF OVERHEAT INVESTIGATED. THE INVESTIGATION REVEALED THAT A SECTION OF PRIMARY EXHAUST NOZZLE WAS COMPLETLY MISSING AND WAS EXPELLED THROUGH THE SECONDARY DUCT. THERE WERE NO OTHER DAMAGES FOUND. AN INVESTIGATION AS TO CAUSE OF THE PROBLEM WILL BE MADE BY MFG. (TC NR 20060830002) 2H72 4T4 TRTA14EA E20NE 6 CP7NE 20061018001332006101800133SO 2006 10 18 CA060830003 120060829G2750486597 DRIVE ASSY PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA HARTZLHCE3Y HCE3YR2A GL RT FLAP SHEARED W O OTHER F FLT CONT AFFECTED APAPPROACH 1 CA (CAN) DURING APPROACH AND FLAP EXTENSION TO 5 DEGREES CREW NOTICED AIRCRAFT ROLL TO THE RT AND OBSERVED THAT THE RT FLAP HAD NOT EXTENDED. THE LANDING WAS UNEVENTFUL. MAINTENANCE INVESTIGATION REVEALED THE RT FLAP DRIVE CABLE SPLINES AT THE MOTOR END WERE WORN AWAY. THE RT FLAP DRIVE CABLE ASSY WAS REPLACED AND OPERATION CHECKED NORMAL. (TC NR 20060830003) 1L72 3O3 O A20SO E14EA 5 CP33EA 20060913002832006091300283NM 2006 9 13 CA060831002 120060827G32208800121 STRUT DHAV DHC8 DHC8101 2809002NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE NLG CRACKED W J DUMP FUEL O OTHER ININSP/MAINT 1 CA 3945615435 (CAN) DURING A SCHEDULED MAINTENANCE CHECK, TASK CARD 3220/01 AND 02 VISUAL INSPECTION AND LUBRICATION OF NLG ASSY, A CRACK WAS DISCOVERED IN THE NLG SHOCK STRUT HOUSING. THE NLG ASSEMBLY WAS IMMEDIATELY REPLACED. TSN=39456.7HRS / CSN=46723CYC TSO=15435.7HRS / CSO=13147CYC TSI=799.0HRS / CSI=590CYC (TC NR 20060831002) 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20061018001382006101800138GL 2006 10 18 CA060831004 220060828G7200 ENGINE BELL 206 206L 1181522SW ALLSN 25OC 250C20R GL POWER LOSS W R AUTOROTATION RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 1 CA (CAN) AIRCRAFT LOST POWER RESULTING IN A HARD LANDING. DATE OF OCCURRENCE, JUNE 26, 2006. ROTORCRAFT LOST ENGINE POWER AT APPROX 400 FEET AND AUTOROTATED. AIRCRAFT IS CONSIDERED A TOTAL WRITE-OFF. TSB CURRENTLY INVESTIGATION ROOT CAUSE OF THIS EVENT. (TC NR 20060831004) 1G71 3U3 U H2SW E4CE 20060913003362006091300336NM 2006 9 13 CA060831006 120060707G6123D59901 HYDRAULIC SYSTEMHARTZL DORNERDO32 DO328100 2996000NM PWA 119 PW119C NE HARTZLHDE6C HDE6C3B NE PROPELLER FAILED W E ENGINE SHUTDOWN O OTHER TXTAXI/GRND HDL 1 CA 4293 HL316 (CAN) AIRCRAFT READIED AND RT ENGINE START PARAMETERS NORMAL. RT CONDITION LEVER ADVANCED TO MIN. RT PROP DOES NOT UNFEATHER. RT CONDITION LEVER RETARDED TO FEATHER. RT CONDITION LEVER ADVANCED TO MIN. RT PROP DOES NOT UNFEATHER. MAINTENANCE CALLED TO SIGHT FOR INVESTIGATION AND TROUBLESHOOTING. PASSENGERS CHARTERED. AIRCRAFT GROUNDED FOR 3 DAYS. RT HYDRAULIC UNIT D-5990-1 SN S296 UNSERVICEABLE. SN S296 TSN 4293.1. RT HYDRAULIC UNIT D-5990-1 REPLACED WITH OVERHAULED UNIT SN S53. HYDRAULIC UNIT SN S53 TSN 12735.5. (TC NR 20060831006) 2H72 4T4 TRTA45NM E20NE 6 CP34NE 20061018001392006101800139NM 2006 10 18 CA060901002 120060831G2920 PRESSURE SWITCH BOEING737 737522 138449FNM CFMINTCFM56 CFM563C1 13802EU FLT CONTROL MODUUNSERVICEABLE W A UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 CA (CAN) APPROXIMATELY ONE FLIGHT HOUR ENROUTE THE (B) SYSTEM FLIGHT CONTROL MODULE LOW PRESSURE LIGHT ILLUMINATED. AIRCRAFT TURNED BACK. (B) SYSTEM FLIGHT CONTROL MODULE REPLACED DUE TO LOW PRESSURE SWITCH UNSERVICEABLE. TIMES- 37968:59 CYCLES: 23555 (TC NR 20060901002) 2L72 4F4 FRTA16WE E21EU 20060913003442006091300344GL 2006 9 13 CA060901003 220060823G732076715 FADEC CESSNA525 525 2076601CE WILINTFJ44 FJ44 66000GL RT ENGINE FAILED W O OTHER J WARNING INDICATION TXTAXI/GRND HDL 1 CA 424 (CAN) THE RT ENGINE FADEC CHANNEL A FAULT LIGHT ILLUMINATED. MAINTENANCE ACCESSED FADEC DATA AND DOWNLOADED FAULT CODES. FAULT CODES FORWARDED TO MFG, DURING TELEPHONE CONVERSATION WITH MFG OF AC AND ENG, IT WAS DETERMINED THAT THE FADEC HAD AN INTERNAL FAULT. AC MFG SENT A FIELD SERVICE TECHNICIAN WHO REPLACED THE FADEC AND AFTER GROUND RUNS THE SYSTEM WAS SERVICEABLE. (TC NR 20060901003) 1L72 4F4 FRTA1WI E3GL 20060913003452006091300345NE 2006 9 13 CA060901004 220060823G8530399359CR CYLINDER HEAD DHAV DHC3 DHC3 2800202EA PWA R1340 R134059 52016NE HAMSTD23D 23D40 NE NR 2 CYLINDER CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 1174 2P103622 (CAN) FOUND CRACK ON NR 2 CYLINDER HEAD AT EXHAUST ROCKER HOUSING WHILE CHECKING OIL LEAK AT OTHER POSITIONS. CRACK WAS NOT DETECTED AT THE LAST 100 HOUR INSPECTION. 33.5 HOURS PAST. (TC NR 20060901004) 1H71 3R3 R A815 5E2 6 CP719 20061018001402006101800140SW 2006 10 18 CA060901005 120060818G6340 BEARING AIRTRCAT802 AT802 0390305SW PWA PT6 PT6A67A 52043NE HARTZLHCB5M HCB5MA3 GL TACH GENERATOR WORN W K NONE O OTHER ININSP/MAINT 1 CA 450 86342 (CAN) A NOISE WAS DETECTED AND THE TACH GENERATOR WAS REMOVED AND FOUND THAT THE LOWER SHAFT BEARING WAS BADLY WORN. (TC NR 20060901005) 1L71 3T4 TNCA19SW E26NE 6 CP44GL 20060913003462006091300346WP 2006 9 13 CA060901006 220060831G73203055383 SWITCH SWRNGNSA226 SA226TC 8780404SW GARRTTTPE331TPE33110UA 01514WP COCKPIT ODOR W C ABORTED TAKEOFF B SMOKE/FUMES/ODORS/SPARKS TOTAKEOFF 1 CA 78 (CAN) CREW NOTED BEFORE TAKEOFF A BURNING SMELL IN THE COCKPIT PRIOR TO TAKEOFF. NO SYSTEM FAULTS WERE NOTED OR BREAKERS POPPED AND THE SMELL WENT AWAY, SO THE FLIGHT CONTINUED IT`S LAST LEG. NO FAULTS NOTED IN FLIGHT. IT WAS LATER DISCOVERED A SPEED SWITCH HAD FAILED. THIS WAS DETERMINED TO BE THE CAUSE OF THE ELECTRICAL SMELL. THIS UNIT HAD 77.5 HOURS TSO HOURS AND IS ONE OF A NUMBER OF FAILED SWITCHES FROM THIS VENDOR. (TC NR 20060901006) 2L72 4T4 TRTA8SW E4WE 20060913003472006091300347SO 2006 9 13 CA060901007 220060822G8530T1ST712ACA CYLINDER CESSNA206 U206G 2073356CE CONT O520 IO520F 17032SO HARTZLHCJ3Y PHCJ3YF1 GL CYL NR 5 SCORED W O OTHER O OTHER NRNOT REPORTED 1 CA 1019 1019 69166EAB (CAN) THE PILOT REPORTED AN IMPORTANT OIL LEAK TO THE AMO. AFTER INVESTIGATION, THE TECHNICIAN DISCOVERED THE SOURCE TO BE FROM NR 5 CYLINDER BARREL O-RING. THE PISTON WAS FOUND DAMAGED, SCORED, PROBABLY CAUSED BY EXCESSIVE HEAT. PARTS REPLACED. (TC NR 20060901007) 1H71 3O3 O A4CE E5CE 5 CP36EA 20060913003482006091300348NM 2006 9 13 CA060901008 120060818G3231 SENSOR BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17EU NLG DOOR SHORTED W A UNSCHED LANDING O OTHER CLCLIMB 1 CA (CAN) DURING CLIMB, THE LANDING GEAR STARTED TO CYCLE BY ITSELF AND SEVERAL GEAR DOOR AND GEAR UNSAFE ADVISORY LIGHTS WERE ILLUMINATED. ACCORDING QRH ALTERNATE GEAR EXTENSION PERFORMED. NORMAL LANDING PERFORMED. A/C HANDED OVER TO MAINTENANCE FOR FURTHER INVESTIGATION. INVESTIGATION FOUND THE NLGDCL SENSOR SHORTED. REPLACED NLG DOOR CLOSED SENSOR (S19) IAW FIM TASK AND PERF RIGGING OF PROXIMITY SENSOR. ALL READINGS WITHIN LIMIT. THE DAMAGE OF THE NLG DOOR CLOSED SENSOR HARNESS WAS CAUSED BY A BOLT WHICH IS INSTALLED IN THE WRONG DIRECTION. BOLT REPLACED AND DIRECTION INVERTED IAW MODSUM ISQ3200003. BOLT INSTALLATION IS CORRECTLY SHOWN IN IPC/AMM. (TC NR 20060901008) 2H72 4T4 TRTA13NM E00062EN6 CP17BO 20061019001112006101900111SW 2006 10 19 CA060901009 120060901G7797MS3451L10SL4P CONNECTOR SWRNGNSA227 SA227AC 8780603SW GARRTTTPE331TPE33111U 01514WP MCAULY4HFR344HFR34C652 NE ENGINE CORRODED W O OTHER N FALSE WARNING LDLANDING 1 CA (CAN) EGT INDICATION WAS ERRATIC ON LANDING. ALL OTHER PARAMETERS WERE NORMAL. THERE WAS HEAVY PRECIPITATION PRIOR TO THE ERATIC INDICATION. THE CONNECTOR PLUG WAS CLEANED AND RETURNED TO SERVICIBLE CONDITION. EGT INDICATION WAS NOT ERATIC AND AIRCRAFT RETURNED TO SERVICE. (TC 20060901009) 2L72 4T4 TRTA8SW E4WE 6 C3PNE 20070129003172007012900317CE 2007 1 29 CA060903001 120060624G2497 WIRE CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA MCAULY1C160 1C160DTM GL ELECTRICAL SYS IMPROPER W D RETURN TO BLOCK MB OVER TEMP SMOKE/FUMES/ODORS/SPARKS TXTAXI/GRND HDL 1 CA (CAN) OVERVOLTAGE LIGHT FOUND WIRED TO SYSTEM WITH UNAPPROVED AUTOMOTIVE WIRING. THIS WIRING DISCONNECTED, AND CAUSED A DEAD SHORT TO THE SYSTEM. (TC NR 20060903001) 1H71 3O3 ONT3A12 E274 5 NP910 20061019001122006101900112NE 2006 10 19 CA060905001 220060905G74141052947 SHAFT CONT ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE MAGNETO WORN W K NONE O OTHER ININSP/MAINT 1 CA 1005 B140011ER (CAN) DURING A 500 HOUR INSPECTION, THE LOWER BEARING INNER RACE WAS FOUND LOOSE ON THE SHAFT. THE BEARING INNER RACE HAD BEEN SPINNING ON THE SHAFT CAUSING SHAFT JOURNAL TO WEAR. (TC NR 20060905001) 1G71 3O3 O H11NM 1E4 20061019001132006101900113SO 2006 10 19 CA060905002 120060830G3210AN626 BOLT PIPER 1003306 PIPER PA18 PA18150 7101828SO LYC O320 O320A2B 41508EA SNSNCH74D 74DM EA MLG SHEARED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING A ROUTINE INSPECTION OF THE AIRCRAFT, IT WAS DISCOVERED THAT THE FORWARD LT LANDING GEAR ATTACH BOLT WAS LOOSENED IN THE FUSELAGE ATTACH FITTING. CLOSER EXAMINATION FOUND THE BOLT TO BE SHEARED ABOUT HALF WAY DOWN THE SHANK OF THE BOLT. ALL FOUR LANDING GEAR ATTACHMENT BOLTS WERE REMOVED AND REPLACED WITH NEW BOLTS. THE OTHER 3 BOLTS SHOWED SIGNS OF WEAR BUT ONLY THE ONE HAD SEPARATED. (TC NR 20060905002) 1H71 3O3 O 1A2 E274 5 NP88614 20060913003492006091300349CE 2006 9 13 CA060905003 120060831G212199101133 FAN BLADE CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE COOLING FAN FAILED W O OTHER O OTHER TXTAXI/GRND HDL 1 CA (CAN) WHEN PILOTS WERE USING FLOOD COOLING ON THE GROUND THEY HEARED A NOISE AND HAD A VIBRATION THEY SHUT THE SYSTEM DOWN . AFTER MAINTENANCE REMOVED THE FLOOD COOLING FAN MOTOR ASSY THEY FOUND A BROKEN FAN BLADE . THEY REPLACED FLOOD COOLING FAN MOTOR ASSY P/N OFF/ON 9910113-3 S/N ON 0019 GROUND CHECKED SERVICEABLE AND RETURNED AIRCRAFT TO SERVICE. (TC NR 20060905003) 1L72 4F4 F A22CE E1NE 20060914000052006091400005EU 2006 9 14 CA060905004 120060902G5554555401203 RIB PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL RUDDER BROKEN W O OTHER F FLT CONT AFFECTED ININSP/MAINT 1 CA (CAN) WHILE DOING A WALK AROUND ON THE AIRCRAFT, THERE WAS LOTS OF PLAY FOUND AT THE UPPER ATTACHMENT BOLT ON THE RUDDER. THE BOLT HAD ELONGATED THE HOLE AND DAMAGED THE NOSE RIB. WHEN TRYING TO TAKE THE BOLT OUT, THE NUT PLATE BROKE AWAY AND A PIECE OF THE NOSE RIB THAT IT WAS RIVETED TO WAS ALREADY CRACKED FROM SO MUCH PLAY IN THE UPPER ATTACHMENT THAT IT WAS WHAT ACTUALLY BROKE AWAY WITH THE NUT PLATE. THE UPPER BEARING WAS ALSO DAMAGED. THE BOLT HEAD HAD TO BE CUT OFF TO GET BOLT OUT. THE RUDDER WAS REMOVED AND ANOTHER INSTALLED TO MAKE THE AIRCRAFT AIRWORTHY AGAIN. THE DAMAGED RUDDER IS NOW AWAITING PARTS TO FACILITATE A REPAIR. (TC NR 20060905004) 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20060914000062006091400006EU 2006 9 14 CA060905005 120060902G53405531012326 BRACKET PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL HYD ACTUATIOR CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) WHILE DOING A WALKAROUND ON THE AIRCRAFT THERE WAS A CRACK FOUND ON THE UPPER ATTACHMENT BRACKET IN THE NOSE GEAR BAY THAT THE NOSE GEAR HYDRAULIC ACTUATOR ATTACHES TO. BRACKET REPLACED AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20060905005) 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20060914000072006091400007NE 2006 9 14 CA060905006 320060819G61127849141 BULKHEAD HAMSTD DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE PROPELLER DAMAGED W O OTHER O OTHER NRNOT REPORTED 1 CA 880512 (CAN) THE FLIGHT CREW SNAGGED THE PORT PROP DEICE AS U/S NO LIGHTS OR INDICATION ON AC LOAD GAUGE. UPON FURTHER INVESTIGATION, MAINTENANCE FOUND THAT ALL 3 OF THE PROP DEICE BRUSH BLOCK SLIP RINGS HAD COME OFF OF THE PROPELLER BULKHEAD AND WERE WRAPPED AROUND THE PROPELLER SHAFT. THE SURROUNDING AREA OF THE ENGINE COMPARTMENT WAS INSPECTED FOR FURTHER DAMAGE, WITH NO OTHER DAMAGE FOUND. THE PROPELLER BULKHEAD AND DEICE BRUSH BLOCK WERE REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. THE BULKHEAD HAS BEEN SENT OUT FOR REPAIR AND A STRIP REPORT. (TC NR 20060905006) 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20060914000082006091400008SW 2006 9 14 CA060905007 120060831G2497 WIRE SWRNGNSA226 SA226TC 8780404SW GARRTTTPE331TPE33110UA 01514WP ROTOL R321 R321482F8 GL BATTERY/CHARGER DAMAGED W O OTHER J WARNING INDICATION CRCRUISE 1 CA (CAN) AIRCRAFT HAD EXPERIENCED PROBLEMS WITH BATTERY DISCONNECTING INTERMITTENTLY. FIRST TIME WAS CIRCUIT BREAKER POPPED. NEXT TIME FOUND CORROSION ON BATTERY RELAY, REPLACED RELAY. THIS IS A COMMON DEFECT WITH THESE TYPE OF RELAYS. THIRD INSTANCE WAS ON NEXT LEG AFTER BATTERY RELAY WAS REPLACED. CREW EXPERIENCED A BATTERY FAULTY ENUNCIATOR AND BOTH DISCONNECT LIGHTS INDICATED. ONCE ON THE GROUND, THEY WERE UNABLE TO GET EITHER BATTERY ON LINE. MAINTENANCE DISCOVERED THE 4 GAUGE FEEDER WIRES FROM THE RAH BATTERY TO THE SERIES-PARALLEL RELAY CHAFED INSIDE THE WING. THE WIRES WERE PROTECTED WITH FIRE SLEEVE AND HAD CHAFED THROUGH. THERE WAS ASSOCIATED DAMAGE TO THE BLEED AIR LINE THAT THE WIRES RUBBED AGA2L72 4T4 TRTA8SW E4WE 6 CP61GL 20060914000092006091400009EA 2006 9 14 CA060905008 220060729G7230 BLADES DHAV DHC6 DHC6 2802606EA PWA PT6 PT6A27 52043EA COMPRESSOR DAMAGED W O OTHER O OTHER NRNOT REPORTED 1 CA 20529 (CAN) PROBLEMS WERE REPORTED WITH THE ENGINE SHORTLY AFTER TAKE-OFF. THE AIRCRAFT SUBSEQUENTLY CRASHED. PRELIMINARY INVESTIGATION EVIDENSED COMPRESSOR BLADE DISTRESS. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC NR 20060905008) 1H72 3T4 TRTA9EA E4EA 20060914000292006091400029NE 2006 9 14 CA060905009 220060727G7261 ENGINE AEROSPATR42 ATR42* 8680900EU PWA PW121 PW121 52124NE LEAKING W A UNSCHED LANDING KB FLUID LOSS SMOKE/FUMES/ODORS/SPARKS CLCLIMB 1 CA 121400 (CAN) DURING CLIMB SMOKE AND ODORS BECAME EVIDENT IN THE CABIN. ENGINE BLEEDS WERE CLOSED AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE. SUBSEQUENT INSPECTION REVEALED OIL LEAKAGE AT THE ENGINE INLET AND EXTERNALS. MFG WILL MONITOR INVESTIGATION OF THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20060905009) 2H72 4T4 TRTA53EU E20NE 20060914000372006091400037NE 2006 9 14 CA060905010 220060731G7250 BEARING GULSTM200 200 4500308NM PWA 306 PW306B NE TURBINE SECTION FRACTURED W EA ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 CA (CAN) DURING CRUISE THE ENGINE EMITTED A LOUD NOISE ACCOMPANIED BY AN INCREEASE IN INTER-TURBINE TEMPERATURE AND VIBRATIONS AND A CHIP DETECTOR INDICATION. THE ENGINE WAS SHUTDOWN IN FLIGHT AND AN UNSCHEDULED LANDING CARRIED OUT. SUBSEQUENT INSPECTION REVEALED DAMAGE TO THE LOW PRESSURE TURBINE NR4 BEARING. (TC NR 20060905010) 2L72 4F4 FRTA53NM E35NE 20061019001142006101900114NE 2006 10 19 CA060905011 220060731G7200 ENGINE AEROSPATR72 ATR72 EU PWA PW121 PW121 52124NE FAILED W A UNSCHED LANDING ERJVIBRATION/BUFFET PARTIAL RPM/PWR LOSS WARNING INDICATION CLCLIMB 1 CA 120363 (CAN) DURING CLIMB THE ENGINE EMITTED A LOUD NOISE. THE ENGINE WAS SHUT DOWN IN FLIGHT AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE. SUBSEQUENT INSPECTION REVEALED METAL DEBRIS IN THE EXHAUST AND SEIZURE OF THE PROPELLER. MFG WILL MONITOR INVESTIGATION OF THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060905011) 2H72 4T4 TRT E20NE 20061019001152006101900115EA 2006 10 19 CA060905012 220060730G7200 ENGINE PWA PT6 PT6A45R 52043EA FLAMED OUT W O OTHER XJ ENGINE FLAMEOUT WARNING INDICATION CRCRUISE 1 CA 84317 (CAN) THE ENGINE FLAMED OUT IN CRUISE. A SUBSEQUENT IN-FLIGHT RELIGHT ATTEMPT WAS UNSUCCESSFUL. INVESTIGATION REVEALED DAMAGE TO THE COMPRESSOR AND POWER TURBINE BLADES. MFG WILL MONITOR INVESTIGATION OF THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC NR 20060905012) 4 T E4EA 20061019001162006101900116NE 2006 10 19 CA060905013 220060729G7321 FUEL CONTROL CESSNA500 550 2076604CE PWA 530 PW530A NE ENGINE FAILED W O OTHER XJ ENGINE FLAMEOUT WARNING INDICATION DEDESCENT 1 CA (CAN) THE ENGINE FLAMED OUT DURING DESCENT. SUBSEQUENT INSPECTION REVEALED METAL PARTICLES IN THE FUEL SYSTEM DOWNSTREAM OF THE FUEL CONTROL UNIT. THE FUEL SYSTEM COMPONENTS WERE REPLACED. MFG WILL MONITOR INVESTIGATION OF THE FCU AND ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC NR 20060905013) 1L72 4F4 F A22CE E00053EN 20061019001172006101900117NE 2006 10 19 CA060905014 220060804G7200 ENGINE PILATSPC12 PC12 7090550EU PWA PT6 PT6A67B 52043NE SMOKE W G O2 MASK DEPLOYED B SMOKE/FUMES/ODORS/SPARKS NRNOT REPORTED 1 CA (CAN) THE ENGINE WAS REPORTED TO HAVE CAUSED SMOKE IN THE CABIN AIR, REQUIRING THE DEPLOYMENT OF OXYGEN MASKS. MFG WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20060905014) 1L71 3T4 TRTA78EU E26NE 20061019001182006101900118EU 2006 10 19 CA060905015 120060618G7500311221801 SWITCH AEROSPATR72 ATR72 EU PWA PW120 PW124B NE P2 AIR FAILED W O OTHER B SMOKE/FUMES/ODORS/SPARKS APAPPROACH 1 CA (CAN) DURING APPROACH, SMOKE WAS REPORTED IN THE CABIN AIR AND ENGINE CABIN BLEED WAS SELECTED OFF. SUBSEQUENT INSPECTION REVEALED DAMAGED P2.5 AIR SWITCHING VALVE COMPONENTS ON BOTH ENGINES (124335 AND 124297). (TC NR 20060905015) 2H72 4T4 TRT E2ONE 20060914000382006091400038EA 2006 9 14 CA060906001 120060811G5610NP139322001 WINDSHIELD CNDAIRCL600 CL6002C10 1390015EA GE CF34 CF348C1 NE COCKPIT FAILED W A UNSCHED LANDING O OTHER DEDESCENT 1 CA (CAN) CREW NOTED DURING DESCENT CAPT LT SIDE WINDOW SHATTERED THE MIDDLE PANE AND NO PRESSURE PROBLEMS. THEY LANDED WITH NO PROBLEMS. (TC NR 20060906001) 2L72 4F4 FRTA21EA EOOO63EN 20060914000392006091400039EA 2006 9 14 CA060906002 120060817G5610NP1393226 WINDOW CNDAIRCL600 CL6002C10 1390015EA GE CF34 CF348C1 NE COCKPIT FAILED W O OTHER O OTHER CRCRUISE 1 CA 9833 (CAN) RT SIDE WINDOW CRACK. RT SIDE WINDOW IAW AMM CHANGED, WINDOW HEAT TEST PERF. OK.PLEASE PERFORM CABIN PRESS TEST. CABIN PRESS TEST PERF. FOUND OK. (TC NR 20060906002) 2L72 4F4 FRTA21EA EOOO63EN 20060914000402006091400040EA 2006 9 14 CA060906003 120060822G5610NP15932211 WINDOW CNDAIRCL600 CL6002C10 1390015EA GE CF34 CF348C1 NE COCKPIT FAILED W D RETURN TO BLOCK O OTHER CRCRUISE 1 CA 3947 (CAN) LT SIDE WINDOW SHATTERED IN FLIGHT AT FL300 CABIN DIFF 8.2, REDUCE PRESS TO 6.2. QRH INITIATED. MAINTENANCE REPLACED THE LT SIDE WINDOW. (TC NR 20060906003) 2L72 4F4 FRTA21EA EOOO63EN 20060914000412006091400041EA 2006 9 14 CA060906004 120060826G5610NP1393225 WINDOW CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF348C1 NE COCKPIT CRACKED W O OTHER O OTHER CRCRUISE 1 CA 10052 (CAN) LT WINDOW CRACKED. LT SIDE WINDOW IAW AMM 56-12-01 REPLACED. (TC NR 20060906004) 2L72 4F4 FRTA21EA EOOO63EN 20060914000422006091400042EA 2006 9 14 CA060906005 120060828G2150GG67065009 ACM CNDAIRCL600 CL6002C10 1390015EA GE CF34 CF348C1 NE LEFT SMOKE W D RETURN TO BLOCK B SMOKE/FUMES/ODORS/SPARKS TXTAXI/GRND HDL 1 CA 9784 (CAN) DISC- BURN/SMOKE ODOR IN COCKPIT, SMOKE ODOR TEMPORARY LT PACK AUTO FAIL ISSUED MEL 2112. C/A - RAI LT ACM IAW CRJ 700 AMM 21-51-08 OPS CK, LEAK CHECK GOOD MEL RESTORED. (TC NR 20060906005) 2L72 4F4 FRTA21EA EOOO63EN 20061019001192006101900119EU 2006 10 19 CA060906006 120060903G3150 WARNING SYSTEM AIRBUS310 A310304 3930339EU GE CF6 CF680C2A5 NE MULTIPLE IND W C ABORTED TAKEOFF GJ MULTIPLE FAILURE WARNING INDICATION TOTAKEOFF 1 CA (CAN) AT 50 KNOTS, FLIGHT CREW REJECTED TAKE OFF DUE TO NAV ADC, GPS DISAGREE WARNING. DURING TAXI TO THE GATE, FAULT CLEARED IT`S SELF. FMS WAS RESET IAW MM, GPS, IRS AND FM POSITIONAL FOUND MATCHING. AUTO FLIGHT SYSTEMS TESTED AND FOUND SERVICEABLE. AIRCRAFT WAS DISPATCHED WITH NO FURTHER PROBLEM. (TC NR 20060906006) 2L72 4F4 FRTA35EU E13NE 20060914000432006091400043GL 2006 9 14 CA060906007 220060905G725023076977 TURBINE BLADES EMB 145 EMB145LR 3260212SO ALLSN AE300 AE3007A GL ENGINE MISINSTALLED W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA A710015 (CAN) ENGINE HAS BEEN ASSEMBLED WITH THE WRONG HP1 TURBINE BLADES PN CONFIGURATION. THE HP1 TURBINE BLADES INSTALLED ARE POST SB 72-260 ENGINES; NEW HIGH PRESSURE TURBINE UPGRADE (BLOCK111) WHEN THE ENGINE IS PRE SB 72-260 CONFIGURATION. THE OEM (INDIANAPOLIS) HAS BEEN NOTIFIED TO DETERMINED IF THE BLADES COULD REMAIN IN THE ENGINE IN SERVICE. (TC NR 20060906007) 2L72 4T4 FRTT00011ATTE6CH 20060914000442006091400044GL 2006 9 14 CA060906008 220060905G725023076977 TURBINE BLADES EMB 145 EMB145 3260210SO ALLSN AE300 AE3007A GL MISINSTALLED W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA A71843 (CAN) ENGINE HAS BEEN ASSEMBLED WITH THE WRONG HP1 TURBINE BLADES PN CONFIGURATION. THE HP1 TURBINE BLADES INSTALLED ARE POST SB 72-260 ENGINES; NEW HIGH PRESSURE TURBINE UPGRADE (BLOCK111) WHEN THE ENGINE IS PRE SB 72-260 CONFIGURATION. THE OEM (INDIANAPOLIS) HAS BEEN NOTIFIED TO DETERMINED IF THE BLADES COULD REMAIN IN THE ENGINE IN SERVICE. (TC NR 20060906008) 2L72 4F4 FRTT00011ATTE6CH 20060914000452006091400045GL 2006 9 14 CA060906009 220060905G725023079436 TURBINE BLADES EMB 135 EMB135ER 3260203SO ALLSN AE300 AE3007A GL ENGINE MISINSTALLED W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA A71332 (CAN) ENGINE HAS BEEN ASSEMBLED WITH THE WRONG HP1 TURBINE BLADES PART NUMBER CONFIGURATION. THE HP1 TURBINE BLADES INSTALLED ARE POST SB 72-260 ENGINES; NEW HIGH PRESSURE TURBINE UPGRADE (BLOCK111) WHEN THE ENGINE IS PRE SB 72-260 CONFIGURATION. THE OEM (INDIANAPOLIS) HAS BEEN NOTIFIED TO DETERMINED IF THE BLADES COULD REMAIN IN THE ENGINE IN SERVICE. (TC NR 20060906009) 2L72 4F4 FRTT00011ATTE6CH 20061019001202006101900120EU 2006 10 19 CA060906011 120060906G5280 SKIN BRAERODH125 HS125700A 4230170EU GARRTTTFE731TFE7313R 01518WP MLG DOOR CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 9668 (CAN) DURING REMOVAL FOR ACCESS, A GENERAL VISUAL INSPECTION OF THE RT MAIN GEAR DOOR REVEALED A LARGE CRACK IN THE INNER SKIN PANEL AS WELL AS SEVERAL PULLED RIVETS ADJACENT TO THE GEAR DOOR JACK ATTACH BRACKET. SB 32-192-2845 (TO PREVENT CRACKING OF THE BRACKET ITSELF) HAD BEEN PREVIOUSLY EMBODIED AT 4608.6 HOURS TSN AND 3015 CYCLES. THE CRACK HAD PROPAGATED TO 6 INCHES IN LENGTH ALONG THE FORWARD IB EDGE OF THE STRENGTHENED (POST MOD) BRACKET IN THE STRUCTURE THE BRACKET IS ATTACHED TO: THE INNER DOOR PAN. A SOFT (TC NR 20060906011) 2L72 4F4 F A3EU E6WE 20061019001222006101900122NE 2006 10 19 CA060906012 220060904G72302292152810 COMPRESSOR SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1D1 NE ENGINE FOD W K NONE O OTHER ININSP/MAINT 1 CA 2236 2236 9922 (CAN) DURING ROUTINE INSPECTION IT WAS NOTED THAT THE AXIAL COMPRESSOR WHEEL HAD SUFFERED FOD, WHICH WAS BEYOND LIMITS. THERE WAS NO EVIDENCE THAT THE INTAKE COWL HAD LOST ANY HARDWARE WHICH MAY HAVE CAUSED THIS. NOR WAS THERE ANY RESIDUAL PARTICLES/OBJECTS FOUND IN THE INTAKE SCOOP. THE AXIAL COMPRESSOR WHEEL WAS CHANGED AND THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20060906012) 1G71 3U3 U H9EU E19EU 20061019001292006101900129NE 2006 10 19 CA060906013 220060907G7200 ENGINE BEECH MU300 400A 1155402CE PWA JT15 JT15D5 52112NE FLAMED OUT W G O2 MASK DEPLOYED XJ ENGINE FLAMEOUT WARNING INDICATION CRCRUISE 1 CA JA0626 (CAN) THE AIRCRAFT ENTERED RAIN AND TURBULENCE AT 40K FEET AND THE ENGINE FLAMED OUT. ENGINE ANTI-ICE AND CONTINUOUS IGNITION HAD NOT BEEN SELECTED. THE ENGINE WAS SUCCESSFULLY RE-STARTED AT 28K FEET. MFG WILL MONITOR THE INVESTIGATION OF THIS EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060906013) 2H72 4F4 FRTA16SW E25EA 20061019001302006101900130SW 2006 10 19 CA060906014 120060906G2897MS3456W14S5S CONNECTOR BELL BELL 412 412EP 1182205SW PWA PT6T PT6T3 52045EA FUEL VALVE SHORTED W E ENGINE SHUTDOWN J WARNING INDICATION TXTAXI/GRND HDL 1 CA T71706 (CAN) FLASHING LIGHT OF ENGINE FUEL VALVE NR 2 ON STARTING PROCEDURE. CONNECTOR 1B14P1 SHORTED TOGETHER BETWEEN PINS A AND B AND WATER CONTAMINATION FOUND INSIDE BACK SHELL. INTERNAL LEAKAGE MEASURED ON THE CONNECTOR BETWEEN PINS A AND B CAUSING ON-OFF SIMULTANEOUS COMMANDS AND DAMAGES TO THE VALVE (205-060-612-003). CONNECTOR AND VALVE REPLACED AND A/C RETURNED TO SERVICE. A/C HOURS 1754:16 A/C CYCLES 1904 (TC NR 20060906014) 1G72 4U4 U H4SW E22EA 20061019001312006101900131NE 2006 10 19 CA060906015 220060815G7200 ENGINE CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE FLAMED OUT W A UNSCHED LANDING XJ ENGINE FLAMEOUT WARNING INDICATION CRCRUISE 1 CA 19374 (CAN) THE ENGINE WAS REPORTED TO EMIT A LOUD BANG IN FLIGHT FOLLOWED BY A FLAMEOUT. A DEAD-STICK LANDING WAS ACCOMPLISHED. SUBSEQUENT INSPECTION REVEALED DEBRIS IN THE ENGINE OIL FILTER AND SEIZURE OF THE COMPRESSOR. MFG WILL INVESTIGATE THE EVENT AND ADVSE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060906015) 1H71 3T3 T A37CE E4EA 20061019001322006101900132EA 2006 10 19 CA060906016 220060818G73143031709 PUMP PWA PT6 PT6A27 52043EA FUEL SYSTEM FAILED W C ABORTED TAKEOFF XJ ENGINE FLAMEOUT WARNING INDICATION TOTAKEOFF 1 CA 5439 (CAN) THE ENGINE FLAMED OUT DURING TAKE-OFF ROLL AND THE TAKE-OFF WAS ABORTED. METAL DEBRIS WAS FOUND IN THE FUEL PUMP OUTLET FILTER. (TC NR 20060906016) 4 T E4EA 20061019001332006101900133CE 2006 10 19 CA060906017 120060818G7712 ENGINE BEECH 200 B200 1152922CE PWA PT6 PT642A NE MALFUNCTIONED W E ENGINE SHUTDOWN RF PARTIAL RPM/PWR LOSS FLT CONT AFFECTED APAPPROACH 1 CA PJ0711 (CAN) ENGINE TORQUE WAS SEEN TO FLUCTUATE ON APPROACH AND THE ENGINE WOULD NOT RESPOND TO THROTTLE INPUT. THE ENGINE WAS SHUTDOWN IN FLIGHT. MFG WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060906017) 1L72 4T4 T A24CE E4EA 20061019001342006101900134NE 2006 10 19 CA060906018 220060717G7250 ENGINE CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE DAMAGED W E ENGINE SHUTDOWN RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CLCLIMB 1 CA PC0472 (CAN) DURING CLIMB THE ENGINE EMITTED A LOUD BANG ACCOMPANIED BY A LOSS IN POWER AND AN AGB CHIP DETECTOR INDICATION. THE ENGINE WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED DEBRIS IN THE ACCESSORY AND REDUCTION GEARBOXES AND POWER TURBINE ROTOR DAMAGE. MFG WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060906018) 1H71 3T3 T A37CE E4EA 20061019001352006101900135NM 2006 10 19 CA060906019 120060703G7931 SEAL DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE ENG OIL PUMP LEAKING W E ENGINE SHUTDOWN KJ FLUID LOSS WARNING INDICATION NRNOT REPORTED 1 CA (CAN) ENGINE OIL PRESSURE WAS REPORTED TO FLUCTUATE IN FLIGHT AND THE ENGINE WAS SHUT DOWN. SUBSEQUENT INSPECTION REVEALED A LEAKING HYDRAULIC PUMP PAD OIL SEAL. (TC NR 20060906019) 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20061023000752006102300075NE 2006 10 23 CA060906020 220060826G7230 FAN BLADE PWA 306 PW306B NE COMPRESSOR DAMAGED W EA ENGINE SHUTDOWN UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CLCLIMB 1 CA CD0046 (CAN) DURING CLIMB THE ENGINE WAS REPORTED TO EMIT A LOUD NOISE ACCOMPANIED BY AN UNCOMMANDED REDUCTION IN POWER. THE ENGINE WAS SHUT DOWN, AN EMERGENCY DECLARED AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE. SUBSEQUENT INSPECTION REVEALED METAL DEBRIS IN THE ENGINE EXHAUST AND A HEAVY FAN BLADE RUB. PWC WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 4 F E35NE 20061019001362006101900136NE 2006 10 19 CA060906021 220060828G7321305964401 FUEL CONTROL BEECH 200 200BEECH 1152920CE PWA PT6 PT642A NE PNEUMATIC CONTAMINATED W E ENGINE SHUTDOWN F FLT CONT AFFECTED CLCLIMB 1 CA (CAN) ENGINE TORQUE WAS SEEN TO FLUCTUATE DURING CLIMB. DURING DESCENT ENGINE TORQUE INCREASE UNCOMMANDED AND THE ENGINE WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INVESTIGATION REVEALED CONTAMINATION OF THE PNEUMATIC SECTION OF THE FUEL CONTROL UNIT. (TC NR 20060906021) 1L72 4T4 T A24CE E4EA 20061019001372006101900137NE 2006 10 19 CA060906022 220060907G7261 SEAL DORNERDO32 DO328100 2996000NM PWA 119 PW119C NE ALTERNATOR DRIVELEAKING W EA ENGINE SHUTDOWN UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CLCLIMB 1 CA (CAN) FOLLOWING TAKEOFF ENGINE OIL PRESSURE WAS SEEN TO FLUCTUATE AND DECAY TO ZERO. THE ENGINE WAS SHUTDOWN IN FLIGHT AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE. SUBSEQUENT INSPECTION REVEALED A LEAKING ALTERNATOR DRIVE SEAL. (TC NR 20060906022) 2H72 4T4 TRTA45NM E20NE 20061019001382006101900138 2006 10 19 CA060906023 120060824G7931 TRANSDUCER PWA PW120 PW127 NE OIL PRESSURE DIRTY W E ENGINE SHUTDOWN N FALSE WARNING DEDESCENT 1 CA (CAN) DURING DESCENT THE ENGINE LOW OIL PRESSURE WARNING ANNUNCIATED. THE ENGINE WAS SHUTDOWN IN FLIGHT. THE ENGINE OIL PRESSURE TRANSDUCER WAS SUBSEQUENTLY REMOVED, CLEANED AND RE-INSTALLED AND THE AIRCRAFT RETURNED TO SERVICE. (TC NR 20060906023) 4 T E20NE 20061019001392006101900139CE 2006 10 19 CA060906024 120060829G27501005240731 MOTOR BEECH 100 A100 1152915CE PWA PT6 PT6A28 EA HARTZLHCD4N3HCD4N3A GL TE FLAP FAILED W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS NRNOT REPORTED 1 CA 3851 (CAN) SHORTLY AFTER TAKEOFF, AT APPROXIMATELY 1000 FEET ALTITUDE A LIGHT SMOKE APPEARED IN THE CABIN ACCOMPANIED WITH A BURNING SMELL. THE AIRCRAFT IMMEDIATELY RETURNED TO THE DEPARTURE AIRPORT. FURTHER INVESTIGATION BY MAINTENANCE REVEALED THAT THE FLAP MOTOR WAS BURNED OUT AND WAS THE CAUSE OF THE SMOKE AND BURNING SMELL. THE FLAP MOTOR AND GEARBOX WERE REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. (TC NR 20060906024) 1L72 3T4 T A14CE E4EA 5 CSTC 20061019001402006101900140EU 2006 10 19 CA060906025 120060802G6123311809101 AUTOFEATHER SYS AEROSPATR72 ATR72 EU PWA PW120 PW127 NE PROPELLER FAULTY W E ENGINE SHUTDOWN F FLT CONT AFFECTED APAPPROACH 1 CA 4265 (CAN) ON APPROACH THE PROPELLER FEATHERED UNCOMMANDED AND THE ENGINE WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INVESTIGATION REVEALED A FAULTY AUTO FEATHER UNIT. (TC NR 20060906025) 2H72 4T4 TRT E20NE 20070504001272007050400127CE 2007 5 4 CA060906026 120060831G5610991438012 WINDSHIELD CESSNA750 750 2076810CE ALLSN AE3007AE3007C GL COCKPIT FAILED W B EMER. DESCENT O OTHER CRCRUISE 1 CA 542 (CAN) IN CRUISE AT 41000 FEET A SOUND LIKE A SHOTGUN WAS HEARD AND THE RT WINDSHIELD OUTER PANE SHATTERED. AFTER AN UNSCHEDULED LANDING AND INSPECTION BY AN AME IT WAS DETERMINED TO BE EITHER A LIGHTNING STRIKE OR A SHORT OF THE HEATING ELEMENT. THE WINDOW WAS THEN REPLACED AND A LIGHTNING STRIKE INSPECTION WAS COMPLIED WITH. THE AIRCRAFT WAS THEN RETURNED TO SERVICE. (TC NR 20060906026) 2L72 4J4 FRTT00007WITE6CH 20061019001412006101900141CE 2006 10 19 CA060907002 120060901G32404500SA1 VALVE BEECH 100 100BEECH 1152916CE PWA PT6 PT6A28 EA HARTZLHCD4N3HCD4N3A GL PARK BRAKE FAILED W O OTHER O OTHER LDLANDING 1 CA 10221 (CAN) RT BRAKE WOULD NOT RELEASE AFTER TOUCHDOWN, AIRCRAFT STOPPED ON RUNWAY, BRAKE PRESSURE HAD TO BE RELEASED BEFORE AIRCRAFT REMOVED FROM RUNWAY. RT BRAKE MASTER CYLINDER REPLACED WITH USED SERVICEABLE UNIT. OPERATION CHECK CARRIED OUT OKAY. DURING TAKEOFF THE CREW FELT A LUNGE FORWARD AFTER ROTATION. THEY FELT THE BRAKE WAS STILL DRAGGING SO THEY DECIDED TO DIVERT FROM AIRPORT . REQUESTED ERS STANDBY, ANTICIPATING POSSIBLE DIRECTIONAL CONTROL PROBLEMS AFTER TOUCHDOWN. AIRCRAFT LANDED WITHOUT INCIDENT. FURTHER INVESTIGATION REVEALED PROBLEMS WITH THE RT PARK BRAKE VALVE P/N 4500SA1. WHEN THE RT BRAKE PEDAL WAS DEPRESSED, THE PARK BRAKE VALVE HELD PRESSURE, AND WOULD NOT RELEASE THE RT BRAKE. THE PARK BRAKE 1L72 3T4 T A14CE E4EA 5 CSTC 20061019001422006101900142EA 2006 10 19 CA060907003 220060905G7421 SPARK PLUG PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA HARTZLHCE3Y HCE3YR2A GL LT ENGINE FOULED W A UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CLCLIMB 1 CA L411961A (CAN) AIRCRAFT (CARGO FLIGHT, NO PASSENGERS, 2 CREW ON BOARD) RETURNED AFTER TAKEOFF WITH REPORT OF LT ENGINE RUNNING VERY ROUGH AND PARTIAL POWER LOSS AS INDICATED BY SLIGHT YAW OF THE AIRCRAFT AND LT ENGINE RPM FLUCTUATION OF APPROX. 200 RPM. MAINTENANCE INVESTIGATION REVEALED NR3 CYLINDER SPARK PLUGS FOULED; REPLACED WITH NEW FINE-WIRE TYPE PLUGS AND GROUND RUN CHECKED SERVICEABLE. SNAG REOCCURRED NEXT FLIGHT AND AIRCRAFT TAKEN OUT OF SERVICE FOR MAINTENANCE. ALL LT ENGINE FUEL INJECTOR NOZZLES CLEANED, ALL FUEL INJECTOR LINES CLEANED AND GROUND RUN CHECKED SERVICEABLE. AIRCRAFT TEST FLIGHT AND SUBSEQUENT FLIGHTS WITH LH ENGINE OPERATION NOW NORMAL. (TC NR 20060907003) 1L72 3O3 O A20SO E14EA 5 CP33EA 20061019001432006101900143SW 2006 10 19 CA060907004 120060629G7170 O-RING BELL 212 212 1181420SW PWA PT6T PT6T3B 52045NE DRAIN VALVE UNSERVICEABLE W E ENGINE SHUTDOWN KJ FLUID LOSS WARNING INDICATION TXTAXI/GRND HDL 1 CA NA (CAN) STARTED NR 2 ENGINE FIRST. SECOND START OF THE DAY. STARTED NR 1 AND BROUGHT IT UP TO IDLE. THE AME CAME RUNNING TO THE COCKPIT AND GAVE THE SIGNAL TO SHUTDOWN THE ENGINE. ENGINE WAS SHUT DOWN AND BOOST PUMP TURNED OFF. HE SAID FUEL WAS STILL LEAKING FROM THE DRAIN AND TO TURN NR 2 BOOST PUMP OFF. NR 2 BOOST PUMP WAS TURNED OFF. SHORTLY THERE AFTER NR 2 ENGINE FLAMED OUT AND QUIT. ALL BOOST PUMPS AND FUEL VALVES CLOSED. ENGINES SECURED AND PASSENGERS EVACUATED. INVESTIGATION REVEALED THAT THE NR 1 FUEL FILTER DRAIN VALVE WAS DEFECTIVE AND ALLOWED THE BOOST PUMP PRESSURED FUEL TO LEAK OUT THROUGH THE DRAIN. NR 2 ENGINE FLAMED OUT BECAUSE WHEN NR 1 BOOST PUMP WAS SHUTOFF THE CROSSFEED VALVE OPEN1G71 4U4 U H4SW E22EA 20061019001442006101900144SW 2006 10 19 CA060907005 120060830G6730205076031003 ACTUATOR BELL 205 205A1 1181414SW LYC T53 T5317A 41549NE TAIL ROTOR SERVOFAILED W A UNSCHED LANDING FJ FLT CONT AFFECTED WARNING INDICATION NRNOT REPORTED 1 CA 180 (CAN) DURING LONG LINE SLINGING OPERATIONS, UPON APPROACHING A DROP ZONE WITH A LOAD. THE COLLECTIVE WAS RAISED TO CUSHION LANDING OF THE LOAD, THEN LOWERED TO TAKE TENSION OFF OF THE LINE. THE HELICOPTER TURNED TO THE LT AND THE RT TAIL ROTOR PEDAL WAS FOUND TO BE STUCK. THE LOAD WAS ALREADY ON THE GROUND AND SUBSEQUENTLY RELEASED. THE COLLECTIVE WAS THEN AGAIN RAISED UNTIL THE AIRCRAFT STOPPED ROTATING AND FWD FLIGHT COULD BE ACHIEVED. THE HELICOPTER MAINTAINED FWD FLIGHT WHILE THE P/C CONTINUED OPERATING THE COLLECTIVE AND TAIL ROTOR CONTROLS. THE LT PEDAL INPUT WAS FINE BUT THE RT PEDAL INPUT WAS AT FIRST JAMMED, THEN BEGAN TO OPERATE WITH RESISTANCE LIKE A HYDRAULIC FAILURE. THE HYDRAULIC ON/OFF SWITCH WAS1G71 4U4 U H1SW E17EA 20061019001452006101900145EU 2006 10 19 CA060907006 120060125G7931 TRANSMITTER SNIAS 350 AS350BA 8680817EU TMECA ARRIELARRIEL1B 6OO30NE ENG OIL PRESSUREMALFUNCTIONED W O OTHER N FALSE WARNING CRCRUISE 1 CA 292 (CAN) PILOT INDICATED THE PRESSURE INDICATOR WAS FLUCTUATING. TROUBLESHOOTING DETERMINED IT WAS PRESSURE TRANSMITTER. (TC NR 20060907006) 1G71 3U3 UNCH9EU E19EU 20061019001472006101900147CE 2006 10 19 CA060907007 120060829G29101013880167 LINE BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE HARTZLHCE4A HCE4A3I NE HYD SYSTEM LEAKING W A UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CLCLIMB 1 CA (CAN) PILOT REPORTED THAT LANDING GEAR DID NOT RETRACT. 2.5 QUARTS OF HYDRAULIC FLUID WERE LOST AND HYDRAULIC PUMP CIRCUIT BREAKER POPPED AND LOW FLUID LEVEL CAUTION LIGHT ILLUMINATED. MANUAL EXTENSION WAS CARRIED OUT AND AIRCRAFT LANDED SAFELY. INVESTIGATION REVEALED RT MAIN LANDING GEAR HYDRAULIC RETRACT LINE WAS LEAKING. THE LINE WAS REPLACED, HYDRAULIC SYSTEM REPLENISHED, GEAR SWINGS CARRIED OUT AND LEAK CHECKED SERVICEABLE. HYDRAULIC LINE P/N 101-388016-7 WAS PRESSURE TESTED ON BENCH AND FOUND TO HAVE A HOLE ONE INCH FROM SWAGED FITTING. THE MFG RECOMMENDED INSPECTION CRITERIA FOR TEFLON COATED HYDRAULIC LINES CALL FOR A VISUAL INSPECTION FOR DETERIORATION AND LEAKS; HOWEVER THE OUTER SHEATHING PREVENTS S2L72 4T4 TRTA24CE E26NE 5 CP10NE 20061019001502006101900150EA 2006 10 19 CA060907008 120060826G5250 LOCK CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE COCKPIT DOOR MALFUNCTIONED W O OTHER O OTHER CRCRUISE 1 CA (CAN) APPROXIMATELY 10 MINUTES PRIOR TO DESCENT, CALLED THE FLT ATTENDANT TO ENTER AND STAY IN THE FLIGHT DECK AS I WENT TO THE LAV. AFTER RETURNING AND ACTIVATING THE DOOR LOCK CODE THE FLIGHT ATTENDANT HAD PROBLEM UNLOCKING THE DOOR. THE FIRST OFFICER NOW HELPED AND ALSO NOT ABLE TO UNLOCK THE DOOR. I ALSO VERIFIED AND DISCUSSED ALL POSSIBLE OPTIONS VIA THE INTERPHONE. IT WAS DECIDED TO PULL THE DOOR PINS TO OPEN THE DOOR. AFTER RETURNING TO OUR POSITIONS, RESECURED THE DOOR IN POSITION WITHOUT PINS AS NOT TO TRAP OURSELVES IN THE FLIGHT DECK IN THE EVENT OF AN EVACUATION. THE FLIGHT ATTENDANT JUMP SEAT WAS PUT INTO PLACE AS TO CREATE A BARRIER. AFTER LANDING MAINTENANCE WAS CALLED WHO RESECURED THE DOOR AND 2L72 4F4 FRTA21EA E15NE 20061019001512006101900151CE 2006 10 19 CA060908001 120060908G301029S7D517515 BOOT CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE HARTZLHCB3T HCB3TN3 GL DEICE SYS DISTORTED W K NONE O OTHER ININSP/MAINT 1 CA 135 (CAN) THE CARGO POD DEICER BOOT EXHIBITS DETERIORATION DUE TO OIL/FUEL CONTAMINATION. SUSPECTED CAUSE IS LEAKING OR OPEN STOP COCKS ON THE ENGINE DRAINS. (TC NR 20060908001) 1H71 3T3 T A37CE E4EA 6 CP15EA 20061019001532006101900153CE 2006 10 19 CA060908002 120060907G3243MS28775011 O-RING BEECH BEECH 100 100BEECH 1152916CE PWA PT6 PT6A28 EA HARTZLHCD4N3HCD4N3A GL CHECK VALVE CUT W O OTHER O OTHER LDLANDING 1 CA 10222 (CAN) REF. SDR NR 20060907002 RT BRAKE LOCKED-UP PREVIOUS SDR SUBMITTED MENTIONED THE PARK BRAKE VALVE AS THE UNSERVICEABLE PART, HOWEVER THE NEXT FLIGHT THE BRAKES ON THE RT SIDE LOCKED-UP AGAIN, BRAKES INSPECTED, PRESSURE RELIEVED AND AIRCRAFT RETURNED TO BASE FOR TROUBLSHOOTING, FOUND CO-PILOT RT BRAKE MASTER CYLINDER TRAPPING PRESSURE IN THE SYSTEM, BRAKE CYLINDER REMOVED AND EXAMINED, FOUND O-RING ON CHECK VALVE CUT, O-RINGS IN MASTER CYLINDER REPLACED WITH NEW, FUNCTION TEST CARRIED-OUT, BRAKES OPERATED NORMALLY (O-RING P/N MS28775-011) (TC NR 20060908002) 1L72 3T4 T A14CE E4EA 5 CSTC 20061019001552006101900155EU 2006 10 19 CA060909001 120060906G5610NAS1581C3T11 SCREW PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL WINDSCREEN LOOSE W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA (CAN) DURING A SCHEDULEDED PRESSURIZATION CHECK LEAKS WHERE NOTED FROM THE WINDSCREEN ATTACHMENT SCREWS. ATTACHMENT SCREWS RE-TORQUED WHICH REVEALED THAT SEVERAL WERE LOOSE. ALTHOUGH THIS IS NOT AN UNHEARD OF SITUATION IT SEEMS TO BE HAPPENING MORE AND MORE. 2 MORE SDRS WILL BE ENTERED FOR SIMILAR ISSUES. NO OTHER PROBLEMS WERE ENCOUNTERED AND THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20060909001) 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20061019001562006101900156EU 2006 10 19 CA060909002 120060908G5610NAS1581C3T11 SCREW PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL WINDSCREEN LOOSE W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA (CAN) DURING A SCHEDULEDED PRESSURIZATION CHECK LEAKS WHERE NOTED FROM THE WINDSCREEN ATTACHMENT SCREWS. ATTACHMENT SCREWS RE-TORQUED WHICH REVEALED THAT SEVERAL WERE LOOSE. ALTHOUGH THIS IS NOT AN UNHEARD OF SITUATION IT SEEMS TO BE HAPPENING MORE AND MORE. 2 MORE SDRS WILL BE ENTERED FOR SIMILAR ISSUES. NO OTHER PROBLEMS WERE ENCOUNTERED AND THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20060909002) 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20061019001592006101900159EU 2006 10 19 CA060909003 120060823G5610NAS1581C3T11 SCREW PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL WINDSCREEN BACKED OUT W K NONE O OTHER ININSP/MAINT 1 CA (CAN) ON A WALKAROUND SEVERAL WINDSCREEN ATTACHMENT SCREWS WERE NOTED AS BEING PARTIALLY BACKED OUT. ALL ATTACHMENT SCREWS RE-TORQUED AND SEVERAL MORE WERE FOUND TO BE LOOSE. SCREWS RETORQUED AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20060909003) 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20061213001402006121300140CE 2006 12 13 CA060911001 120060909G3260 INDICATOR BEECH 1900 1900C 1154161CE PWA PT6 PT6A65B 52043EA HARTZLHCB4M HCB4MP3 GL MLG INOPERATIVE W O OTHER P NO WARNING INDICATION APAPPROACH 1 CA (CAN) DURING FLIGHT TRAINING GEAR WAS EXTENDED. THERE WAS NO RT MAIN GEAR DOWN AND LOCKED LIGHT. AN EMERGENCY GEAR EXTENSION WAS CARRIED OUT. RT MAIN GEAR LIGHT STILL NOT ILLUMINATED. LAMP TEST CARRIED OUT WITH GEAR HANDLE RED INTRANSIT LIGHT ILLUMINATED. PILOTS WERE UNABLE TO REMOVE LIGHT HOLDER TO INSPECT BULBS. EMERGENCY LANDING DECLARED. LANDING GEAR VISUALLY CHECKED DURING A CIRCUIT BY MAINTENANCE PERSONNEL. GEAR APPEARED DOWN AND LOCKED. AIRCRAFT LANDED WITHOUT EVENT. MAINTENANCE PERSONNEL INSTALLED GEAR PINS AND TOWED AIRCRAFT BACK TO HANGER. FAULTY BULB REPLACED AND SEVERAL GEAR SWINGS CARRIED OUT. NO FAULTS FOUND. THIS PROBLEM COULD HAVE BEEN LESS EVENTFUL IF THE PILOTS WERE MORE EASILY ABLE TO REMOVE2L72 4T4 TRTA24CE E4EA 6 CP56GL 20070507001812007050700181WP 2007 5 7 CA060911002 120060724G2810 FUEL FILTER GRUMANTS2 TS2ACALFORST3951102WP PWA PT6 PT6A67A 52043NE HARTZLHCB5M HCB5MA3 GL ENGINE CONTAMINATED W K NONE C F.O.D. ININSP/MAINT 1 CA (CAN) DURING A ROUTINE 100 HOUR INSPECTION, A LARGE AMOUNT OF PARTICLES WERE FOUND IN THE MAIN FUEL FILTERS AND THE FUEL PUMP INLET FILTERS. THE PARTICLES WERE SENT TO A LAB AND IT WAS DETERMINED THAT IT WAS ORGANIC MATERIAL SIMILAR TO THE EXPLOSION SUPPRESSANT FOAM USED IN THE PYLON FUEL TANKS. THE FOAM HAS BEEN REMOVED, SYSTEM FLUSHED AND NEW FOAM INSTALLED. THE REMAINDER OF THE FLEET (9 AIRCRAFT TOTAL) WILL HAVE THE FOAM REPLACED DURING WINTER MAINTENANCE. (TC NR 20060911002) 2H72 4R4 T A25WE E26NE 6 CP44GL 20061019001642006101900164NM 2006 10 19 CA060911006 120060908G3320AL845T279 LAMP AMD FALC50FALCON2000 2730170NM LAVATORY MELTED W K NONE B SMOKE/FUMES/ODORS/SPARKS ININSP/MAINT 1 CA (CAN) WHILE PERFORMING THE POST FLIGHT INSPECTION, A ELECTRICAL BURNING ODOR WAS DETECTED IN THE AFT AREA OF THE CABIN. APON FURTHER INSPECTION ONE OF THE LAVATORY MIRROR VANITY LIGHTS WAS FOUND TO BE INOP. WHEN THE BULB WAS REMOVED TO BE REPLACED IT WAS NOTICED THAT ONE END OF THE LAMP ASSEMBLY HAD STARTED TO MELT. WITH THE DEFECTIVE LAMP ASSEMBLY REMOVED IT WAS ALSO NOTED THAT THE DEFECTIVE PN WAS WRONG. INSTALLED WAS A AL-845-T-279 BUT IAW THE FALCON IPC THE LAMP ASSEMBLY SHOULD HAVE BEEN A AL-845-T-279-F. AFTER THE DEFECTIVE LAMP ASSEMBLY WAS REMOVED THE ELECTRICAL BURNING SMELL IN THE CABIN WAS NOT DETECTED ANYMORE. THE CORRECT LAMP ASSEMBLY WAS ORDERED AND THE AIRCRAFT HAS BEEN RETURNED TO SERVICE. (TC NR2K72 4F RTA50NM 20061019001652006101900165NE 2006 10 19 CA060912001 220060912G7250BRH20351 TURBINE BLADES BOEING717 717200 1383700NM RROYCEBR700 BR700715A130 NE ENGINE FRACTURED W EC ENGINE SHUTDOWN ABORTED TAKEOFF R PARTIAL RPM/PWR LOSS TOTAKEOFF 1 CA 13801 13322 (CAN) IN CLIMB AT 11000 FT PILOT REPORTED LOUD BANG. TGT ROSE TO 1194 DEG. PILOT SHUT DOWN ENGINE. AND TURNED BACK. FOUND HEAVY METAL CONTAMINATION IN THE TAIL PIPE. EMERGENCY LANDING CONDUCTED WITHOUT INCIDENT. ENGINE PRESENTLY AT RRC FOR REPAIR, STRIP OF ENGINE REVEALED HP1 TURBINE BLADES FAILURE BELOW INNER PLATFORM AND SEVERE SECONDARY DAMAGE IN LP TURBINE MODULE. ENGINE IS HIGH TIME TSN;13801 HOURS, CSN; 9396 AND THIS IS FIRST SHOP VISIT. FAILED BLADES HAVE BEEN SHIPPED TO THE OEM (GERMANY) FOR INVESTIGATION. (TC NR 20060912001) 2L72 4F4 FTRA6WE E00061EN 20061019001662006101900166 2006 10 19 CA060913001 420060816G611305522311 BULKHEAD CESSNA CESSNA172 172S 2072439CE LYC IO360 IO360L2A EA MCAULY1A170 1A170E GL SPINNER CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 492 (CAN) DURING CHANGEOVER FROM FLOATS TO WHEELS, AND DURING THE CHANGE FROM SEAPLANE PROP TO WHEELPLANE PROP , CLOSER INSPECTION OF THE FORWARD PROP SPINNER BULKHEAD REVEALED NUMEROUS CRACKS. THESE CRACKS WERE RADIATING FROM THE PROP ATTACHMENT BOLT HOLES, TO THE BEND RADIUS OF THE BULKHEAD (P/N 0552231-1). CRACKS WERE ALSO AROUND THE RADIUS WHERE THE PROP BOLT WASHERS MEET AGAINST THE SPINNER PLATE. AIRCRAFT HAD FLOWN 157.1 HRS ON FLOATS WITH NUMEROUS TAKEOFFS AND LANDINGS DURING FLOAT FLIGHT TRAINING. THIS SPINNER PLATE WAS LAST CHANGED 492.0 HRS AGO AFTER IT HAD AGAIN BEEN CHANGED OVER FROM FLOATS TO WHEELS. AT THAT TIME, THE PLANE HAD LOGGED 222.1 HRS OF FLOAT FLIGHT TRAINING, AND CRACKS WERE ALSO APPARENT AT1H71 3O3 ONT3A12 1E10 5 NP857 20061019001672006101900167CE 2006 10 19 CA060913002 120060816G322005412024 BUSHING CESSNA172 172S 2072439CE LYC IO360 IO360L2A EA MCAULY1A170 1A170E GL NLG SEPARATED W K NONE O OTHER ININSP/MAINT 1 CA 2578 (CAN) THE MAIN GEAR LEG BUSHINGS ARE A STEEL OUTER TUBE, WITH A THICK INNER URETHANE CENTER. DURING PROGRESSIVE CARE OPERATION NR 1, INSPECTION OF THE RT MAIN GEAR LEG REVEALED THAT THE URETHANE INNER BUSHING MATERIAL HAD DEPARTED FROM THE OUTER STEEL BUSHING (P/N 0541202-4). IT HAD MOVED LOOSELY ALONG THE TUBULAR GEAR LEG TOWARDS THE CENTER OF THE AIRCRAFT. THIS ALLOWED THE TUBULAR GEAR LEG TO RATTLE ON THE INSIDE OF THE STEEL OUTER BUSHING. THE STEEL OUTER BUSHING IS HELD IN PLACE WITH 2 (C) CLIPS, HOWEVER THE URETHANE INNER PART OF THE BUSHING LOOKS TO BE ONLY A PRESS FIT. THE AIRCRAFT WAS JACKED UP, THE LEG WAS REMOVED, AND A NEW BUSHING WAS INSTALLED. THE OTHER 3 MODEL AIRCRAFT IN THE FLEET HAVE BEEN INS1H71 3O3 ONT3A12 1E10 5 NP857 20070507000862007050700086SW 2007 5 7 CA060913003 120060912G530280011P12F20 SKIN BELL BELL 206 206B 1181511SW ALLSN 250C 250C20 03013GL TAILBOOM CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 15442 (CAN) WHILE CARRYING OUT ASB 206-06-107, FIN WAS REMOVED AND A FIN ATTACHMENT INSERT P/N 80-011-P12F2-0 WAS FOUND CRACKED. AFTER REMOVAL OF THE CRACKED INSERT, THE IB SKIN BELOW WAS FOUND TO HAVE SEVERAL CRACKS PROPAGATING UNDERNEATH THE DOUBLER. THE IB DOUBLER WAS REMOVED AND A TOTAL OF APPROXIMATELY 6 CRACKS WAS FOUND, ONE OF WHICH WAS 3 INCHES IN LENGTH. THE FIN WAS REPLACED. (TC NR 20060913003) 1G71 3U3 U H2SW E4CE 20061019001682006101900168EA 2006 10 19 CA060913004 120060906G2810215640015 FUEL CELL CNDAIRCL215 CL2156B11215 EA PWA PW120 PW123 NE HAMSTD14SF 14SF* NE WING LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA 1414 (CAN) A/C DEVELOPED A FUEL LEAK. LEAK WAS MEASURED AND FOUND TO BE THE DRIP TYPE AND COMING FROM THE WING TIP AREA.UPON INSPECTION IT WAS DETERMINED THAT THE FUEL LEAK WAS COMING FROM THE RT FUEL CELLS. DUE TO PREVIOUS REPLACEMENT OF CELLS NR 3 THROUGH NR 8 IT WAS DETERMINED TO TEST CELLS NR 1 AND 2. BOTH CELLS WERE FOUND LEAKING AND SUBSEQUENTLY REPLACED. A/C GROUND CHECKED OK. P/N 215-64001-5 SERIAL NR 72672 NR 1 CELL P/N 215-64002-8 SN 72872 NR 2 CELL (TC NR 20060913004) 2H72 4T4 TRTA14EA E20NE 6 CP7NE 20070507000872007050700087SW 2007 5 7 CA060913005 120060911G7921212030041233 SUPPORT BELL 412 412 1182202SW OIL COOLER OBSTRUCTED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) SUPPORT 212-030-041-233 FOULS WITH TRANSMISSON OIL LINE 212-040-229-001. (TC NR 20060913005) 1G72 4U H4SW 20061019001692006101900169EU 2006 10 19 CA060913006 120060913G324640424 WHEEL PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL MLG DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA 6024 (CAN) DURING AN INSPECTION WHEEL ASSY WAS REMOVED, GREASE COVER FOR THE BEARING AND BEARINGS REMOVED FOR INSPECTION/ REPACKING. THE WHEEL WAS THEN CLEANED AND INSPECTED FOR WEAR. AT THAT POINT IT WAS NOTICED THAT THE WHEEL HOUSING HAD SEVERAL DEEP GROOVES WHERE THE GREASE COVER SITS. WE HAVE NOTICED THIS PROBLEM ON OTHER WHEEL ASSY BUT TO A LESSER DEGREE. WE HAVE SENT AN E-MAIL TO MFG AND INFORMED THEM OF THIS PROBLEM. (TC NR 20060913006) 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20061019001702006101900170EU 2006 10 19 CA060914001 120060911G3150 WARNING MESSAGE AEROSPATR42 ATR42300 8680920EU PWA 120 PW120 NE HAMSTD14SF 14SF5 NE MULTIPLE IND W A UNSCHED LANDING GJ MULTIPLE FAILURE WARNING INDICATION CRCRUISE 1 CA (CAN) AFTER DEPARTING THE CREW OBSERVED NR 1 ADC, NR 1 ENGINE ANTI-ICE AND NR 1 PROP DEICE FAULTS. THE AIRCRAFT RETURNED TO POINT OF DEPARTURE WITHOUT INCIDENT. MAINTENANCE TROUBLE SHOOTING WAS UNABLE TO DUPLICATE THE FAULT. AFTER SATISFACTORY OPERATIONAL TESTING OF THE AFFECTED SYSTEMS THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20060914001) 2H72 4T4 TRTA53EU E20NE 6 CP7NE 20070507000902007050700090SW 2007 5 7 CA060914002 120060906G5302 STRUCTURE BELL BELL 407 407 1182206SW TAILBOOM CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 9257 53247 (CAN) APPROX. 8 IN. CRACK FOUND IN TAILBOOM NEAR THE 5TH HANGER BEARING APPROX. 270 HRS REMAINING OUT OF THE 5000 HRS RETIREMENT LIFE. (TC NR 20060914002) 1G71 3U O H2SW 20061019001712006101900171CE 2006 10 19 CA060914003 120060808G2497 CONNECTOR FORD CESSNA172 172R 2072401CE LYC IO360 IO360L2A EA MCAULY1C235 1C235LFA GL ALTERNATOR BROKEN W BA EMER. DESCENT UNSCHED LANDING HP ELECT. POWER LOSS-50 PC NO WARNING INDICATION CRCRUISE 1 CA 4075 R204620 (CAN) ALTERNATOR FAILURE WHILE ON ROUTE TO DESTINATION WAS CAUSED BY AN AMP CONECTOR LOOP END BREAKING OFF AND CAUSING LOSS OF ELECTRICAL POWER AND A SHORT IN THE SYSTEM. (TC NR 20060914003) 1H71 3O3 ONT3A12 1E10 5 NP12EA 20061019001722006101900172CE 2006 10 19 CA060914004 120060914G251007190131 SEAT BACK CESSNA172 172R 2072401CE LYC IO360 IO360L2A EA MCAULY1C235 1C235LFA GL COCKPIT SEAT BROKEN W O OTHER O OTHER NRNOT REPORTED 1 CA 4089 (CAN) CO PILOTS SEAT BACK WAS FOUND BROKEN ABOUT 2 INCHES ABOVE THE WELDED JOINT ON THE LT SIDE OF THE SEAT BACK. BROKEN PART REMOVED NEW SEAT BACK FRAME ON ORDER WITH CESSNA. (TC NR 20060914004) 1H71 3O3 ONT3A12 1E10 5 NP12EA 20070507000912007050700091WP 2007 5 7 CA060915001 120060914G7820C1963 MUFFLER ROBSINR44 R44 7640120WP LYC O540 O540F1B5 41532EA EXHAUST CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 1939 (CAN) WHILE PERFORMING CF90-3R2 ON THE MUFFLER ASSEMBLY THE EXHAUST SHROUD WAS REMOVED AND A (2) INCH CRACK WAS FOUND WHERE THE EXHAUST PIPE JOINS THE MUFFLER. (TC NR 20060915001) 1G71 3O3 O H11NM E295 20061019001732006101900173NE 2006 10 19 CA060915002 220060914G73142043M12P03 SHAFT EMB ERJ190ERJ190100IGW3260408EU GE CF34 CF34* NE FUEL PUMP BROKEN W A UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 CA 159 994203 (CAN) DURING CRUISE AT FL360, THE NR 1 ENGINE FAILED. THE CREW DECLARED AN EMERGENCY AND BEGAN DESCENT. DURING THE DESCENT A RE-START WAS ATTEMPTED BUT WAS UNSUCCESSFUL. THE FLIGHT DIVERTED AND LANDED APPROX 400 KG OVERWEIGHT. (TC NR 20060915002) 2L72 4F4 FRTA57NM E15NE 20061019001742006101900174EA 2006 10 19 CA060918001 120060918G2750 FLAP SYSTEM CNDAIRCL601 CL6012A12 1900303EA GE CF34 CF343A 30015NE TE FLAPS MALFUNCTIONED W C ABORTED TAKEOFF FJ FLT CONT AFFECTED WARNING INDICATION TOTAKEOFF 1 CA (CAN) FLAP FAILED ON TAKEOFF, A/C RETURNED AND LANDED SAFELY AT QB MAIN BASE, BREAKER WAS RESET IAW OPERATING MANUAL, COULDN`T DUPLICATED THE SNAG. A/C DID ONE FLIGHT AND RETURN TO BASE WITHOUT ANY SNAG. 2L72 4F4 FRTA21AE E15NE 20061019001762006101900176 2006 10 19 CA060918002 420060912G3100285T003117 CIRCUIT CARD BOEING767 767375 1385217NM GE CF6 CF680C2* GL COCKPIT MALFUNCTIONED W C ABORTED TAKEOFF N FALSE WARNING TOTAKEOFF 1 CA (CAN) CAPTAIN REJECTED TAKEOFF ROLL AT 155KTS BECAUSE OF A (TAKEOFF CONFIGURATION SAFETY WARNING) MESSAGE, 4 MAIN LANDING GEAR TIRES REPLACED DUE TO HIGH ENERGY BRAKING AND FUSE PLUGS MELTING. NEW LANDING CONFIGURATION CARD INSTALLED AND TESTED. (TC NR 20060918002) 2L72 4F4 FRTA1NM E23EA 20061213001412006121300141GL 2006 12 13 CA060918003 120060829G52102256136100 HOOK DIAMON DIAMONDA20 DA20C1 2990001GL CONT O240 IO240B 17063SO SNSNCHW69EK W69EK63 EA CANOPY CRACKED W A UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 CA 2175 (CAN) PILOT NOTICED CANOPY LIGHT ON IN FLIGHT AND RETURNED FOR LANDING. INSPECTION REVEALED THAT THE CANOPY LATCH PLATE ( P/N 22-5613-61-00) ON THE LT SIDE WAS BROKEN ALLOWING THE CANOPY LIGHT TO BE ILLUMINATED. 2 MICRO SWITCHES ARE USED TO TURN THE WANING LIGHT OFF ONLY WHEN BOTH LATCHES ARE FULLY CLOSED. THE SYSTEM WORKED PROPERLY WHEN ONE LATCH FAILED. SERVICEABLE LATCH INSTALLED AND SYSTEM CHECKED AND ADJUSTED IAW MM (DMM) AS REQUIRED. AIRCRAFT RELEASED. THE SYSTEM IS INSPECTED EVERY 100 HR, WHICH REQUIRES A PULL TEST TO BE CARRIED OUT FOR FRICTION VERIFICATION AND ADJUSTMENT AS REQUIRED. STRESS CAN BE APPLIED TO THE LATCH HOOK IF THE CANOPY IS ACCIDENTALLY CLOSE WITH THE LATCH IN THE CLOSED POSITION OR IF1L71 3O3 ONTTA4CH E7SO 5 NTA4CH 20061019001772006101900177SO 2006 10 19 CA060918004 120060909G7120LW38275 BOLT PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA HARTZLHCC2Y HCC2YR2 GL ENGINE MOUNT BROKEN W K NONE O OTHER ININSP/MAINT 1 CA 1446 (CAN) DURING ROUTING INSPECTION IT WAS NOTED THAT ONE OF THE BOLTS SECURING THE RT BOTTOM ENGINE MOUNT BRACKET ONTO THE CRANKCASE OF THE RT ENGINE WAS BROKEN AND THE OTHER BOLT WAS LOOSE. BROKEN TREADED BOLT PIECE WAS REMOVED FROM CRANKCASE AND A SERVICEABLE BRACKET INSTALLED DUE TO ELONGATED HOLES IN OLD UNIT. TOP RT BRACKET WAS ALSO FOUND LOOSE, BRACKET REMOVED AND VISUALLY INSPECTED, NO DAMAGE FOUND. BRACKET REINSTALLED. ALL 6 ENGINE MOUNTING BRACKET BOLTS REPLACED AND TORQUED. BOLT TORQUE TO BE RECHECKED NEXT INSPECTION. ALTHOUGH THE ENGINE HAD 1445.6 HRS SINCE LAST OVERHAUL IT IS NOT MANDATORY ACCORDING TO MFG SB 240T TO REPLACE THESE BOLTS. (TC NR 20060918004) 1L72 3O3 O A19S0 E286 5 CP920 20061019001782006101900178GL 2006 10 19 CA060918005 120060908G8011656762 GEAR DIAMONDA20 DA20C1 2990001GL CONT O240 IO240B 17063SO SNSNCHW69EK W69EK63 EA STARTER WORN W K NONE O OTHER ININSP/MAINT 1 CA 28 650199 (CAN) DURING THE FIRST 25/100 HR INSPECTION ON THIS AIRCRAFT, INSPECTION OF THE OIL SYSTEM REVEALED CONTAMINATION ON THE DRAIN PLUG MAGNET AND OIL FILTER. SUBSEQUENTLY, THE STARTER WAS REMOVED FOR CLUSTER AND DRIVE GEAR INSPECTION. THE STARTER AND CLUSTER GEARS WERE FOUND DAMAGED IN THE AREA OF INITIAL STARTER ENGAGEMENT. THE DAMAGE EXCEEDED THE NORMAL WEAR DESCRIBED IN SB04-07. BOTH STARTER AND CLUSTER GEARS WERE REPLACED. (TC NR 20060918005) 1L71 3O3 ONTTA4CH E7SO 5 NTA4CH 20061019001792006101900179GL 2006 10 19 CA060918006 120060915G8011656762 GEAR DIAMONDA20 DA20C1 2990001GL CONT O240 IO240B 17063SO SNSNCHW69EK W69EK63 EA STARTER WORN W K NONE O OTHER ININSP/MAINT 1 CA 37 650197 (CAN) DURING TROUBLESHOOTING OF THE FUEL SYSTEM DUE TO ENGINE QUITTING ON ROLL OUT FROM LANDING, THE ENGINE FUEL SYSTEM WAS BEING CHECKED IAW SID97-3C, AT WHICH TIME DURING A GROUND RUN IT WAS NOTICED THAT OIL PRESSURE HAD DROPPED TO ALMOST (0). THE ENGINE WAS SHUTDOWN IMMEDIATELY. FURTHER INSPECTION OF THE LOSS OF OIL PRESSURE REVEALED METAL CONTAMINATION ON THE OIL PRESSURE RELIEF VALVE. FURTHER INSPECTION OF THE OIL SYSTEM REVEALED MORE CONTAMINATION ON THE DRAIN PLUG MAGNET AND OIL FILTER. SUBSEQUENTLY THE STARTER WAS REMOVED FOR CLUSTER AND DRIVE GEAR INSPECTION. THE STARTER AND CLUSTER GEARS WERE FOUND DAMAGED IN THE AREA OF INITIAL STARTER ENGAGEMENT. THE DAMAGE EXCEEDED THE NORMAL WEAR DESCRIBED IN SB01L71 3O3 ONTTA4CH E7SO 5 NTA4CH 20061019001802006101900180SO 2006 10 19 CA060918007 220060915G731464936849A1 PUMP DIAMONDA20 DA20C1 2990001GL CONT O240 IO240B 17063SO FUEL SYS OUT OF ADJUST W D RETURN TO BLOCK YJ ENGINE STOPPAGE WARNING INDICATION TXTAXI/GRND HDL 1 CA 37 650197 (CAN) PILOT REPORTED ENGINE QUIT ON TOUCH DOWN, ABLE TO RESTART. FUEL INJECTION SYSTEM CHECKED IAW SID97-3C AND ADJUSTED. BOTH INLINE FUEL FILTERS INSPECTED FOR CONTAMINANTS, CLEANED AND RE-INSTALLED. SMALL AMOUNT OF CONTAMINANTS FOUND IN INLINE FILTER AFTER THE MECHANICAL FILTER. AIRCRAFT RELEASED CONDITIONAL TO SATISFACTORY TEST FLIGHT. AIRCRAFT TEST FLIGHT CARRIED OUT SATISFACTORY. A SISTER AIRCRAFT HAS REPORTED A SIMILAR DEFECT. AN SDR WILL BE SUBMITTED AFTER TROUBLESHOOTING IS COMPLETED. TROUBLESHOOTING IS BEING CARRIED OUT BY DIAMOND AIRCRAFT. THESE 2 AC EQUIPED WITH NEW ALTITUDE COMPENSATION FUEL PUMPS. (TC NR 20060918007) 1L71 3O3 ONTTA4CH E7SO 20061019001812006101900181EA 2006 10 19 CA060918009 120060916G783022850809119 TRACK CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30068NE THRUST REVERSER CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 24451 (CAN) NR 2 ENGINE LT LOWER THRUST REVERSER TRACK FOUND CRACKED DURING A C-CHECK INSPECTION. PART REPLACED AS A MAIN TRACK ASSEMBLY P/N 228-50809-801. REFERENCE :MFG CSP A-006 IPC CHAP 78-34-11 FIGURE 1 , ITEM 75A AND 95A. (TC NR 20060918009) 2L72 4F4 FRTA21EA E15NE 20061019001822006101900182NM 2006 10 19 CA060918010 120060913G801297907021 START VALVE BOEING727 727225 1384077NM PWA JT8 JT8D9 52048NE ENGINE MALFUNCTIONED W O OTHER N FALSE WARNING NRNOT REPORTED 1 CA (CAN) THE NR 3 ENGINE START VALVE OPEN LIGHT ILLUMINATED DURING CLIMB OUT. A/C RETURNED TO BASE. A/C INSPECTED AND THE START VALVE REPLACED DUE CRACKED. A/C RETURNED TO SERVICE. FAULT REOCCURRED DURING CLIMB. A/C RETURNED TO BASE. THE FUEL HEAT DUCT WAS FOUND CRACKED CAUSING WIRING DAMAGE (HEAT) AND THE START VALVE INDICATION. DETAILED ENGINE INSPECTION CARRIED OUT. THE FUEL HEAT DUCT WAS REPLACED AND AIRCRAFT WIRING REPAIRED AS REQUIRED. A/C RETURNED TO SERVICE. (TC NR 20060918010) 2L73 4F4 F A3WE E2EA 20061019001832006101900183EA 2006 10 19 CA060918011 120060906G3246L312111 BEARING DHAV DHC8 DHC8311 1386006EA PWA PW120 PW123 NE HAMSTD14SF 14SF23 NE MLG WHEEL DAMAGED W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA 8944 (CAN) AT TIRE CHANGE, DURING WHEEL AND BEARING INSPECTION FOUND THE OUTER WHEEL OUTER BEARING CUP, WITH A PLATING SURFACE MISSING (.3750 INCH X .2500 INCH) AND ROLLER BEARING P/N L81214 * 2-629 THAT MATCH THIS CUP WITH LITTLE MARK ON ROLLER. WHEEL AFT VISUALLY INSPECTED AND FOUND OK. (TC NR 20060918011) 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20061019001842006101900184NE 2006 10 19 CA060919001 220060916G7200 SHUTOFF VALVE BOEING727 727233 138408ANM PWA JT8 JT8D15 52051NE NR 3 ENGINE LEAKING W A UNSCHED LANDING N FALSE WARNING CLCLIMB 1 CA (CAN) DEPARTING THE CREW OBSERVED A STRUT OVERHEAT CONDITION ON NR 3 ENGINE. THE AIRCRAFT DIVERTED WHERE MAINTENANCE DETECTED A LEAK AT THE WING ANTI ICE SHUT-OFF VALVE (SOV). GASKETS WERE REPLACED AND NO FURTHER FAULT APPEARED EVIDENT AT GROUND RUN. DURING THE SUBSEQUENT DEPARTURE THE OVER TEMP CONDITION AT APPLICATION OF TAKE-OFF POWER, THE CREW REJECTED THE TAKE-OFF. MAINTENANCE DETECTED A LEAK AT THE PRE-COOLER WHICH WAS CORRECTED AND CARRIED OUT MULTIPLE TAKE-OFF POWER TESTS WITH NO FAULT INDICATION. THE SUCCEEDING DEPARTURE WAS AGAIN REJECTED AT 60KNOTS DUE TO AN OVERTEMP CONDITION ON NR 3 STRUT. MAINTENANCE REPLACED THE FIRE WIRE LOOP AND CORRECTED AN ADDITIONAL LEAK AT THE PRECOOLER BEFORE RETURNING THE2L73 4F4 FRTA3WE E2EA 20061019001852006101900185CE 2006 10 19 CA060919002 120060918G243530728692 SPLINE LEAR 45 45LEAR 5170805CE GARRTTTFE731TFE7312 01518WP STARTER GEN CRACKED W O OTHER O OTHER NRNOT REPORTED 1 CA P116176C (CAN) ENGINE FAILED TO START. AFTER INSPECTION FOUND THAT STARTER/GEN SPLINE INSERT HAD CRACKED CAUSING THE SPLINE TEETH TO BREAK OFF. UNABLE TO DETERMINE IF CRACK HAD OF OCCURRED BEFORE OR AFTER GEAR TEETH HAD BROKEN OFF. REPLACE SPLINE AND AIRCRAFT STARTED NORMALLY. FLEET INSPECTION TO BE C/O. (TC NR 20060919002) 2L72 4F4 FRTT00008WIE6WE 20061019001862006101900186NM 2006 10 19 CA060919003 120060918G3320BV33001215 SOCKET DHAV DHC8 DHC8301 1386003NM PWA PW120 PW123 NE HAMSTD14SF 14SF23 NE CABIN LIGHTS BURNED W F ACTIVATE FIRE EXT. B SMOKE/FUMES/ODORS/SPARKS NRNOT REPORTED 1 CA (CAN) AFTER BOARDING WAS COMPLETED AND DOORS CLOSED, CA1 REPORTED A STRONG SMELL OF SMOKE COMBINED WITH LIGHT SMOKE DEVELOPMENT IN THE CABIN. CONTROLLED DISEMBARKATION WAS ORDERED, MAYDAY CALL PERFORMED AND ON GROUND EMERGENCY ITEMS COMPLETED ON THE FLIGHT DECK. AFTER PAX DISEMBARKATION COCKPIT CREW DISCHARGED ONE FIRE EXTINGUISHER INTO THE AREA OF SMOKE DEVELOPMENT AND THEN DISEMBARKED THE A/C. REASON FOR THE SMOKE DEVELOPMENT WAS A SHORT IN THE OVERHEAD LIGHTING SYSTEM. THE FAULT OCCURED ON THE FIRST LT OVERHEAD LAMP HOLDER. HOLDER FOUND BURNED. (TC NR 20060919003) 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20061019001872006101900187EA 2006 10 19 CA060919004 120060917G551260021134434 VISOR CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE VERTICAL STAB CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 24451 (CAN) BOTH THE LT AND RT LOWER VISOR ASSEMBLIES WERE FOUND DAMAGED FROM CRACKING AT THE AFT TOP END. THIS MAY HAVE BEEN DUE TO FLUTTER AT THE AFT END OF THE FAIRING DURING FLIGHT. SINCE IT IS ATTACHED TO THE MOVABLE HORIZONTAL STABILIZER, THERE IS NO FASTENERS AT THAT AFT END OF THE FAIRING. THERE WERE NO VIBRATIONS OR DEFECTS OF THAT THAT NATURE REPORTED ON THIS AIRCRAFT BEFORE IT CAME IN FOR A HEAVY CHECK DURING WHICH TIME THIS DAMAGED FAIRINGS WERE FOUND. HOWEVER THIS DAMAGE IS OFTEN NOTED ON OTHER AIRCRAFT AS WELL AND MAY OR MAY NOT HAVE CAUSED AIRFRAME VIBRATION OR INTERFERENCE WITH THE MOVING HORIZONTAL STABILIZER. (TC NR 20060919004) 2L72 4F4 FRTA21EA E15NE 20061019001882006101900188EU 2006 10 19 CA060919005 120060910G2760233009 ACTUATOR FOKKERF28 F28MK0100 4990807EU RROYCETAY TAY65015 54557NE SPEED BRAKE MALFUNCTIONED W D RETURN TO BLOCK O OTHER LDLANDING 1 CA (CAN) FLIGHT CREW REPORTED THAT THE SPEED BRAKE WOULD NOT RETRACT UPON SELECTION TO DO SO. FOLLOWING LANDING. BOTH PADDLES CONFIRMED OPEN. AIRCRAFT WAS FERRIED TO BASE, WHERE THE SPEED BRAKE ACTUATOR WAS REPLACED. SYSTEM TESTED SERVICEABLE AFTER REPLACEMENT. SPEED BRAKE ACTUATOR PN 23300-9 SN MC-046 WAS REPLACED MFG SERVICES HAVE REQUESTED THIS ACTUATOR FOR ANALYSIS DUE TO SIMILAR REPORTS FROM OTHER OPERATORS. ITEM OPEN TO MONITOR THE FOLLOW UP VIA THE QUARTERLY RELIABILITY MEETING. (TC NR 20060919005) 2L72 4F4 FRT E25NE 20061019001892006101900189EA 2006 10 19 CA060919006 120060916G5610601R3303311 WINDOW CNDAIRCL600 CL6002C10 1390015EA GE CF34 CF34* NE COCKPIT CRACKED W O OTHER O OTHER CRCRUISE 1 CA 8346 (CAN) LT SIDE-WINDOW REPLACED IAW AMM. AERODYNAMIC SEAL INSTALLED AND SEALING PERFORMED. CABIN PRESSURE TEST AND LEAK CHECK PERF, OK. WINDOW HEATING CHECKED, OK. (TC NR 20060919006) 2L72 4F4 FRTA21EA E15NE 20061019001902006101900190GL 2006 10 19 CA060920001 220060917G7210 GEARBOX LKHEED382 382G 526414USO ALLSN 501D 501D22A 03006GL HAMSTD54H 54H60117 NE NR 2 RGB MAKING METAL W EA ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA (CAN) DEPARTING THE CREW OBSERVED A CHIP LIGHT INDICATION ON NR 2 RGB. THE ENGINE WAS SHUT-DOWN AND THE AIRCRAFT RETURNED TO POINT OF DEPARTURE WITHOUT FURTHER INCIDENT. MAINTENANCE FOUND CONTAMINATION ON THE RGB PLUG BELIEVED TO BE FROM THE STARTER SEAL. THE SEAL WAS REPLACED AND THE AIRCRAFT RUN AT HIGH POWER SETTING FOR 30 MINUTES WITH NO FURTHER INDICATION. (TC NR 20060920001) 2H74 4T4 T A1SO E282 6 CP906 20061019001912006101900191EU 2006 10 19 CA060920002 120060920G2820416113004 LINE SNIAS 350 AS350BA 8680817EU LYC LTS101LTS101600A3 41560NE FCU CRACKED W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) GOVERNOR FAIL TO RESPONSE ON TAKE OFF, VISUAL CHECK OF ENGINE COMPARTMENT FOUND CRACKED LINE ON GOVERNOR TO FCU LINE NP TO PR TO PG LINE . LINE REPLACED WITH NEW A/C BACK TO SERVICE. (TC NR 20060920002) 1G71 3U3 UNCH9EU E5NE 20061019001922006101900192EU 2006 10 19 CA060920003 120060920G2435150SG116Q STARTER GEN SNIAS 350 AS350BA 8680817EU LYC LTS101LTS101600A3 41560NE ENGINE BROKEN W A UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 CA 350 (CAN) GENERATOR LIGHT CAME ON IN FLIGHT, LANDED AND SHOTDOWN, STARTER FOUND BROKEN. STARTER REPLACED AND SENT FOR OVERHAUL. (TC NR 20060920003) 1G71 3U3 UNCH9EU E5NE 20061019001932006101900193 2006 10 19 CA060920004 420060918G3422 AHRS AEROSPATR42 ATR42300 8680920EU PWA 120 PW120 NE HAMSTD14SF 14SF5 NE NR 2 FAILED W A UNSCHED LANDING I FLT. ATTITUDE INST. CLCLIMB 1 CA (CAN) DURING DEPARTURE THE NR 2 AHRS UNIT FAILED. THE AIRCRAFT RETURNED TO POINT OF DEPARTURE. CURRENTLY AWAITING PARTS. (TC NR 20060920004) 2H72 4T4 TRTA53EU E20NE 6 CP7NE 20061019001942006101900194CE 2006 10 19 CA060920005 120060814G213352771338 OUTFLOW VALVE CESSNA500 560CESSNA 2076750CE PWA 530 PW535A NE CABIN PRESSURE FAILED W O OTHER J WARNING INDICATION DEDESCENT 1 CA 1545 (CAN) UNCOMMANDED PRESSURIZATION DURING DESCENT OF CABIN AT APPROX 10,000 FEET WHILE IN AUTO MODE - PREVENTING TO MANUAL MODE WOULD NOT DECREASE RATE OF CABIN DIVE - CREW CONTROLLED CABIN PRESSURIZATION BY CONTROLLING ENGINE BLEED AIR SOURCE VALVES SUPPLYING CABIN AIR. THIS PROBLEM IS CAUSED BY A STICKING OPEN DIVE SOLENOID VALVE IN THE PRIMARY OUTFLOW VALVE ASSEMBLY. MFG HAS INCORPORATED SB 560-21-27 TO INSTALL A PARTICULATE TRAP IN THE PNEUMATIC LINE TO PREVENT THIS PROBLEM. (TC NR 20060920005) 2L72 4F4 FRTA22CE E00053EN 20061019001952006101900195EA 2006 10 19 CA060920006 120060912G5510 BOLT FOUND FBA FBA2C 3640102EA LYC O540 IO540* 41532EA HARTZLHCC3Y HCC3YR GL HORIZONTAL STAB BROKEN W K NONE O OTHER ININSP/MAINT 1 CA 600 (CAN) UPON REMOVAL OF THE LT FINLET THE REAR ATTACH BOLT (P/N AN3-4A) BROKE. WHEN INSTALLING 4 NEW BOLTS IT WAS NOTICED THAT THE WASHER RODE UP ON THE RADIUS OF THE ATTACH BRACKET CAUSING STRESS ON THE BOLT. WHEN HOLE LOCATION WAS CHECKED AGAINST THE RT FINLET THERE WAS .100 OF AN INCH DIFFERENCE. A SMALL FLAT WAS GROUND IN THE WASHER SO IT WOULD NOT RIDE UP IN THE RADIUS WHEN BOLT INSTALLED. (TC NR 20060920006) 1H71 3O3 O A7EA 1E4 5 CP25EA 20061019001212006101900121EA 2006 10 19 CA060920007 120060413G2434 GENERATOR DHAV DHC6 DHC6 2802606EA PWA PT6 PT6A27 52043EA NR 2 SHORTED W A UNSCHED LANDING HJ ELECT. POWER LOSS-50 PC WARNING INDICATION CLCLIMB 1 CA (CAN) IN CLIMB BOTH GENERATORS TRIPPED OFF LINE AND WOULD NOT RESET. TROUBLE SHOOTING REVEALED AN INTERNAL SHORT IN THE NR 2 GENERATOR THAT CAUSED BOTH GENERATORS TO TRIP THROUGH THE BUSTIE. SUBMITTER FILE IS ADR 150. (TC NR 20060920007) 1H72 3T4 TRTA9EA E4EA 20061011001292006101100129SW 2006 10 11 CA060920008 120060918G7714AG44AF TACH GENERATOR SWRNGNSA227 SA227AC 8780603SW GARRTTTPE331TPE33111U 01514WP MCAULY4HFR344HFR34C652 NE RT ENGINE SLIPPED W A UNSCHED LANDING N FALSE WARNING CLCLIMB 1 CA (CAN) AIRCRAFT DEPARTED AIRPORT AND UPON CLIMBOUT THE RT ENGINE RPM INDICATION BEGAN TO FLUCTUATE. ALL OTHER PARAMETERS REMAINED NORMAL. AIRCRAFT RETURNED AND UPON INVESTIGATION FOUND DRIVE SHAFT INTACT YET SLIPPING INTERNALLY. TACH GENERATOR REPLACED, RUNUP COMPLETED AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20060920008) 2L72 4T4 TRTA8SW E4WE 6 C3PNE 20061011001332006101100133EA 2006 10 11 CA060920009 120060906G3213C6UF10151 STRUT DHAV DHC6 DHC6 2802606EA PWA PT6 PT6A27 52043EA FRONT FLOAT BROKEN W C ABORTED TAKEOFF O OTHER TOTAKEOFF 1 CA (CAN) ON TAKEOFF IN ROUGH WATER THE LT FRONT FLOAT STRUT BROKE AT THE UPPER END. STRUT REPLACED. (TC NR 20060920009) 1H72 3T4 TRTA9EA E4EA 20061011001342006101100134EA 2006 10 11 CA060920010 120060906G3213C6UF10151 STRUT DHAV DHC6 DHC6 2802606EA PWA PT6 PT6A27 52043EA FRONT FLOAT BROKEN W A UNSCHED LANDING O OTHER LDLANDING 1 CA (CAN) ON LANDING IN ROUGH WATER THE RT FRONT FLOAT STRUT BROKE AT THE UPPER END. STRUT REPLACED. (TC NR 20060920010) 1H72 3T4 TRTA9EA E4EA 20061011001352006101100135 2006 10 11 CA060920011 420060918G2565 SLIDE AIRBUS320 A320214 3930316EU CFMINTCFM56 CFM565B4P NE L2 DOOR UNWANTED DEPLOY W H DEACTIVATE SYST/CIRCUITS W INADEQUATE Q C TXTAXI/GRND HDL 1 CA (CAN) ACCIDENTLY FLIGHT ATTENDANT DEPLOYED THE SLIDE AT L-2 DOOR. INITIALLY SHE WENT TO DEACTIVATE THE DOOR BUT WAS DISTRACTED THEN USED THE OPEN LEVER INSTEAD OF THE DISARM LEVER CAUSING THE INCIDENT. SLIDE WAS DEPLOYED BUT NOT INFLATED, DUE TO THE ACTUATION CABLE FOUND WRAPPED AROUND THE TOP OF CYLINDER WHICH PREVENT THE INFLATION. (TC NR 20060920011) 2L72 4F4 FRTA28NM E38NE 20061011001362006101100136SO 2006 10 11 CA060920013 220060916G8520649134 CRANKSHAFT CESSNA206 U206G 2073356CE CONT O520 IO520F 17032SO HARTZLHCJ3Y PHCJ3YF1 GL ENGINE BROKEN W C ABORTED TAKEOFF YJ ENGINE STOPPAGE WARNING INDICATION TOTAKEOFF 1 CA 1835 1835 293447R (CAN) AT APPROXIMATLY 300 FEET AGL ON TAKE OFF THE PILOT REDUCED POWER FOR FULL POWER TO CLIMB POWER. A BANG WAS HEARD AND THE ENGINE LOST POWER. THE AIRCRAFT WAS OPERATING ON FLOATS AND WAS LANDED STRAIGHT AHEAD BACK ON TO THE LAKE IT HAD DEPARTED FROM. INVESTIGATION DETERMINED THAT THE CRANKSHAFT HAD BROKEN BETWEEN CYLINDERS 1-2 /3-4. POSSIBLE CAUSE MAY HAD BEEN MAIN CRANKSHAFT BEARING FAILURE. THE AIRCRAFT HAD A 50 HR INSPECTION CARRIED OUT 11.1 HRS PRIOR TO THE ENGINE FAILURE. AT THAT TIME THE OIL AND OIL FILTER WERE CHANGED. THE REMOVED OIL FILTER WAS OPENED AND INSPECTED. AT THE TIME OF THE INSPECTION NO METAL OR OTHER CONTAMINANTS WERE DISCOVERED IN THE OIL FILTER. (TC NR 20060920013) 1H71 3O3 O A4CE E5CE 5 CP36EA 20061011001372006101100137 2006 10 11 CA060921001 420060827G830070BM011030 GEARBOX SNIAS 350 AS350* EU TMECA ARRIELARRIEL1B 6OO30NE ACCESSORY DAMAGED W B EMER. DESCENT KJ FLUID LOSS WARNING INDICATION CRCRUISE 1 CA 5400 1384 (CAN) OIL PRESSURE LINE FITTING AT ACCESSORY GEARBOX (FELL OUT) OF GEARCASE AND SUBSEQUENT COMPLETE LOSS OF OIL IN FLIGHT. THREADS IN GEARCASE STRIPPED 90 PERCENT; NO PREVIOUS INDICATION OF DISCREPANCY, IE: OIL LEAK OR LOOSENESS. (TC NR 20060921001) 1G71 3U3 U H9EU E19EU 20061011001382006101100138NM 2006 10 11 CA060921002 120060823G2910AN81510D UNION DHAV DHC8 DHC8301 1386003NM PWA PW120 PW123 NE HAMSTD14SF 14SF23 NE NR 2 HYD SYST SHEARED W O OTHER KJ FLUID LOSS WARNING INDICATION APAPPROACH 1 CA 1300 (CAN) CREW REPORTED NR 2 ENG HYD PUMP CAUTION ILLUMINATED, PRESS AND QTY DEPLETED. FOLLOWING GEAR EXTENSION ON APPROACH. NO EMERGENCY DECLARED. MAINTENANCE FOUND THE HYD FITTING FROM THE EDP TO THE PRESS MANIFOLD SHEARED. SYD 8-29-002, REPLACEMENT OF ALUMINIUM UNION WITH STEEL UNION COMPLETED. (TC NR 20060921002) 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20061213001422006121300142SW 2006 12 13 CA060921003 120060916G6220222011114103 PENDULUM BELL 222 222 1182122SW MAIN ROTOR SEPARATED W A UNSCHED LANDING E VIBRATION/BUFFET CRCRUISE 1 CA 2006 (CAN) A/C WAS IN CRUISE FLIGHT AT 700 FT, AGL WHEN A SUDDEN VIBRATION BEGAN.  THE CREW MADE AN IMMEDIATE LANDING IN A FIELD AND SHUTDOWN.  INSPECTION FOUND THAT ONE M/R PENDULUM WEIGHT HAD SEPARATED AND STRUCK A M/R BLADE. THE DAMAGED AREA IS 3 INCHES LONG BY .1250-.2500 INCH WIDE AND A MAX DEPTH OF 0.0025 INCH. THE DAMAGE BLADE 222-015-500-105 S/N AMR06030 TT4840.7 (TC NR 20060921003) 1G72 3U H9SW 20061011001392006101100139NE 2006 10 11 CA060921004 220060911G72503044700 ENGINE BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE HARTZLHCE4A HCE4A3I NE LEAKING W EA ENGINE SHUTDOWN UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CRCRUISE 1 CA 148106715 PS0145 (CAN) THE CREW REPORTED A LOW OIL PRESSURE INDICATION WHILE TAXING, SOME OIL WAS NOTED ON THE FUSELAGE SO AN AME WAS DISPATCHED. THEY COULD FIND NO AREA OF LEAKAGE DURING INSPECTION AND THE AIRCRAFT WAS REPLENISHED AND NUMEROUS GROUND RUNS DID NOT REVEAL ANYTHING FURTHER. THE AIRCRAFT WAS RETURNING TO A MAINTENANCE BASE WHEN THE AME NOTICED OIL COMING FROM THE BREATHER AREA OF THE ENGINE. THE CREW SHUT THE ENGINE DOWN AND RETURNED TO PLACE OF DEPARTURE WHERE THEY HAD AN UNEVENTFULL LANDING. FURTHER INSPECTION HEARD GRINDING NOISES COMING FROM THE POWER SECTION AREA WHICH INDICATES BEARING DAMAGE IN THAT AREA. THE ENGINE WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. THE ENGINE HAS BEEN RETURNED TO THE MAIN 2L72 4T4 TRTA24CE E26NE 5 CP10NE 20061213001432006121300143CE 2006 12 13 CA060921005 120060919G2697 WIRE BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA HARTZLHCB3T HCB3TN3 GL NACELLE CONTAMINATED W A UNSCHED LANDING N FALSE WARNING CRCRUISE 1 CA 14827 (CAN) CREW HAD A FIRE WARNING LIGHT COME ON IN FLIGHT, CREW FOLLOWED PROCEDURES AND TURNED THE AIRCRAFT 90 DEGREES TO RULE OUT LIGHT POSSIBLY TRIPPING DETECTORS AND LIGHT REMAINED ON. NO SIGN OF FIRE WAS NOTED VISUALLY ON WING NOR ON THE GLANCE OF INSTRUMENTATION. CREW THEN CARRIED ON AND THE LIGHT WHEN OFF PRIOR TO APPROACH. MAINTENANCE NOTIFIED AND INSPECTED, FUNCTION CHECKED SYSTEM. SYSTEM FUNCTIONED NORMALLY. WIRING IN NACELLE FOUND WET DUE TO THE WEATHER CONDITION ENROUTE WHICH WE HAVE DETERMINED A CAUSE FOR AN INTERMITTENT WARNING IN THE PAST. MAINTENANCE SEALED WIRING AS REQUIRED TO REDUCE THE CHANCE OF THIS HAPPENING WHILE FLYING IN PRECIP. (TC NR 20060921005) 1L72 4T4 T A24CE E4EA 6 CP15EA 20061011001402006101100140CE 2006 10 11 CA060921006 120060905G7500 LINE CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE MCAULY3AF34C3GFR34C703 GL BLEED AIR CHAFED W O OTHER B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 1 CA (CAN) APPROXIMATELY 10 MIN. INTO THE FLIGHT AT 5500 FT ALTITUDE AND IN CRUISE, THE PILOT NOTICED LIGHT SMOKE COMING FROM THE GENERAL LOCATION OF THE CIRCUIT BREAKER PANEL, AND A DISCOLORING OF THE LT CREW DOOR FWD POST PANEL, LOCATED JUST ABOVE THE CB PANEL. THE PILOT FOLLOWED PROCEDURES FOR CABIN FIRE AND ELECTRICAL FIRE, AND RETURNED SAFELY TO THE AIRPORT OF DEPARTURE. AME`S WERE DISPATCHED TO THE A/C AND UPON INSPECTION FOUND THE CAUSE TO BE THAT THE LT CREW DOOR FWD POST TRIM PANEL WAS TOO CLOSE TO THE BLEED AIR LINE THAT RUNS UP THE DOOR POST FROM THE FIREWALL TO THE WING FOR DE-ICE PURPOSES. THE METAL FLANGE THAT HELD THE PANEL IN PLACE HAD BEEN BENT, POSSIBLY FROM PILOTS REACHING UP AND GRIPPING THE DOOR1H71 3T3 T A37CE E4EA 5 CP60GL 20061213001442006121300144CE 2006 12 13 CA060922001 120060922G324621401400 BEARING CLEVELAND BEECH 90 C90A 1152911CE PWA PT6 PT6A21 52043EA HARTZLHCB3T HCB3TN3 GL RT MAIN GEAR DESTROYED W O OTHER O OTHER TXTAXI/GRND HDL 1 CA 267 DOT6849 (CAN) MAINTENANCE NOTICED FLUID LEAKING FROM THE RT MLG BRAKE ASSY. INVESTIGATION REVEALED THAT THE BRAKE ASSY. PISTON RETENTION BOLT WAS THE SOURCE OF THE LEAK. A MORE DETAILED INSPECTION DISCOVERED THAT THE RT MAIN WHEEL INNER WHEEL HALF CONE AND BEARING HAD BEEN DESTROYED. WHEEL REMOVAL SHOWED THAT THE WHEEL ASSY, AXLE, FORWARD AND AFT BRAKE CALIPERS AND LOWER TORQUE LINK HAD BEEN DAMAGED. THE WHEEL DID NOT DEPART THE AIRCRAFT AS THE OUTER WHEEL HALF BEARING ASSY. REMAINED IN TACT AND RETAINED THE WHEEL. ON THE DAY OF DISCOVERY THE AIRCRAFT HAD RECEIVED A PRE-DISPATCH INSPECTION AND FLEW FOR A TOTAL OF 1.8 HOURS AIRTIME AND COMPLETED 5 LANDINGS. THERE WERE NO DEFECTS RECORDED IN THE JOURNEY LOG BOOK POST FLI1L72 3T4 TRT3A20 E4EA 6 CP15EA 20061213001452006121300145EU 2006 12 13 CA060922002 120060921G6220350A37116200 STOP SNIAS SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1D1 NE MAST YOKE FAILED W K NONE O OTHER ININSP/MAINT 1 CA 5739 M4979 (CAN) DAILY INSPECTION REVEALED YOKE ASSEMBLY STOP WAS BROKEN BELOW THE ATTACHMENT POINT. THE CABLE CLIP LOWER EDGE WOULD FOLLOW THE CRACK LINE. THE CABLE CLIP WOULD NOT CONTAIN THE BROKEN COMPONENT AND COULD CREATE FURTHER PROBLEMS IF UNIT BECOMES DISLODGED FROM THE RING. THE GRANULAR COMPOSITION OF THE BREAK MAY INDICATE A METALLURGICAL PROBLEM. THIS PART WAS NOT TESTED BUT IS BEING RETAINED IF MORE INVESTIGATION IS REQUIRED. (TC NR 20060922002) 1G71 3U3 U H9EU E19EU 20061011001412006101100141CE 2006 10 11 CA060925001 120060925G3201264101828 FAIRING CESSNA208 208B 2073701CE PWA PT6 PT6A114 52043NE MCAULY3AF34C3GFR34C703 GL RT MAIN GEAR LOOSE W O OTHER D INFLIGHT SEPARATION LDLANDING 1 CA 5509 5509 (CAN) DURING LANDING A SLIGHT THUMP AND A VIBRATION WAS FELT. AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE INSPECTED THE AIRCRAFT AND FOUND THE RT MAIN LANDING GEAR FAIRING (GEAR TO FUSELAGE FAIRING) WAS MISSING THE LOWER PORTION. THIS FAIRING IS A ONE PIECE FAIRING.THE LOWER PORTION OF THE FAIRING HAD BROKEN FREE. FURTHER INSPECTION FOUND MINOR DAMAGE TO THE RT HORIZONTAL STAB. LEADING EDGE. REPAIRS ARE CURRENLY BEEN CARRIED AND A NEW FAIRING ORDERED TO BE REPLACED. (TC NR 20060925001) 1H71 3T3 T A37CE E4EA 5 CP60GL 20061011001422006101100142NE 2006 10 11 CA060925002 220060819G7322AKM621RA CARBURETOR DHAV DHC3 DHC3 2800202EA WSK ASZ62 ASZ62IRM18 NE ENGINE LEAKING W A UNSCHED LANDING RE PARTIAL RPM/PWR LOSS VIBRATION/BUFFET CRCRUISE 1 CA 311 (CAN) ACCORDING TO THE PILOT WHILE IN FLT THE ENGINE STARTED TO RUN ROUGH AND SPUTTERED A FEW TIMES, THE PILOT CHECKED LT AND RT MAGNETOS, CARB HEAT, BOOST PUMP, GAUGES-OIL TEMPERATURE AND PRESSURE, FUEL PRESSURE AND CYLINDER HEAD TEMPERATURE. ALL GAUGES WERE INDICATING NORMAL RANGES. SWITCHED FUEL TANKS AND THE PROBLEM THEN WENT AWAY. A FEW MINUTES LATER THE PROBLEM OCCURRED AGAIN. THE PILOT THEN NOTIFIED A COMPANY AIRCRAFT AND PROCEEDED WITH UNSCHEDULED LANDING FOR PURPOSE OF INVESTIGATING PROBLEM. THE ENGINE PROBLEM WAS NOT EVIDENT ON THE APPROACH AND LANDING. ONCE ON THE WATER THE PILOT THEN WENT TO SHORE AND DRAINED THE FUEL SUMPS AND CHECKED THE CARB HEAT FUNCTION. THE PILOT THEN DID MULTIPLE RUN UPS AT D1H71 3R3 R A815 E10NE 20061213001462006121300146SO 2006 12 13 CA060925003 120060830G27976345703 CONNECTOR PIPER PIPER PA28 PA28180 7102808SO LYC O360 O360A4A 41514EA SNSNCH76E 76EM8S5 EA RUDER TRIM ARM BROKEN W O OTHER F FLT CONT AFFECTED CLCLIMB 1 CA 3676 (CAN) WHEN MANUAL RUDDER TRIM WAS APPLIED THE RUDDER FAILED TO RESPOND. SUBSEQUENT INSPECTION FOUND THAT THE ARM THAT CONNECTS THE TRIM ACTUATOR TO THE RUDDER CONTROL ASSEMBLY HAD BROKEN OFF THE ASSEMBLY AT THE EDGE OF THE WELD. THE COMPLETE RUDDER TRIM ARM ASSEMBLY WAS REMOVED AND REPLACED WITH A NEW UNIT. METAL FATIGUE IS SUSPECTED. (TC NR 20060925003) 1L71 3O3 O 2A13 E286 5 NP4EA 20061011001552006101100155NE 2006 10 11 CA060925004 220060912G852027056CAI PISTON DHAV DHC2 DHC2MKI 2801830GL PWA R985 R985* 52008NE HAMSTD2D 2D30 NE ENGINE CRACKED W O OTHER O OTHER NRNOT REPORTED 1 CA 946 (CAN) DURING REGULAR INSPECTION LOW COMPRESSION WAS NOTED ON NR 1 CYL. CYLINDER WAS REMOVED AND PISTON WAS CRACKED. CYLINDER ASSY WAS REPLACED. AIRCRAFT GROUND RUN WAS CARRIED OUT SATISFACTORY. (TC NR 20060925004) 1H71 3R3 RRCA806 5E1 5 CP206 20061213001122006121300112EA 2006 12 13 CA060925005 120060922G7931 SCREEN CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE OIL SCAVENGE FAILED W A UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 CA (CAN) ABOUT 50 NM EAST AND AT FL330 THE CREW REPORTED LT ENG OIL PRESSURE WARNING LIGHT WITH FLUCTUATING LOW OIL PRESSURE READINGS (20-46PSI) AT IDLE POWER LT OIL TEMP WAS INCREASING. THE CREW ELECTED TO SHUT DOWN THE LT ENGINE. LINE MAINTENANCE REMOVED LT ENGINE OIL PUMP AND INSPECTED ALL SCAVENGE SCREENS IAW SB 79-001200 OIL. FOUND SCAVENGE SCREEN PLUGGED WITH COKED OIL. REPLACED OIL PUMP AND PUMP SCREENS IAW AMM 79-21-01 ENGINE RUNS CARRIED OUT AND THE AIRCRAFT WAS RELEASED INTO SERVICE. THE OIL FILTER AND SAMPLE HAVE BEEN SENT FOR ANALYSIS. (TC NR 20060925005) 2L72 4F4 FRTA21EA E15NE 20061208000062006120800006SW 2006 12 8 CA060925007 120060923G2435 SHAFT BELL 206 206B 1181511SW ALLSN 250C 250C20B 03013GL STARTER GEN SHEARED W O OTHER O OTHER TXTAXI/GRND HDL 1 CA 461 (CAN) PILOT REPORTED THAT THE STARTER WOULD NOT TURN THE ENGINE, IT WOULD JUST SPIN. MAINTENANCE FOUND THAT THE SHAFT ON THE STARTER HAD BEEN SHEARED. STARTER HAD BEEN REPLACED AND AIRCRAFT RETURN TO SERVICE. (TC NR 20060925007) 1G71 3U3 U H2SW E4CE 20061011001602006101100160CE 2006 10 11 CA060925008 120060919G321345325400018 STRUT LEAR 45 45LEAR 5170805CE GARRTTTFE731TFE7312 01518WP NLG UNDERSERVICED W A UNSCHED LANDING WJ INADEQUATE Q C WARNING INDICATION CLCLIMB 1 CA 2707 (CAN) AFTER TAKEOFF LANDING GEAR WAS SELECTED UP AND ALL LANDING GEAR NOT-UP AND LOCKED LIGHTS DID NOT EXTINGUISH. AIRCRAFT DIVERTED AND AFTER LANDING IT WAS DISCOVERED THE NOSE STRUT WAS COMPLETELY COLLAPSED. THE NOSE STRUT WAS RE-SERVICED WITH NITROGEN AND GEAR SWINGS ACCOMPLISHED WITH NO PROBLEMS. ON RETURN TO OUR BASE, THE NOSE STRUT WAS MODIFIED TO NEW PN 4532230001-804 (MODIFICATION OF UPPER STRUT SEAL ASSY. INSTALLATION) (TC NR 20060925008) 2L72 4F4 FRTT00008WIE6WE 20061011001612006101100161NM 2006 10 11 CA060925009 120060923G3297D4668 CONNECTOR BOEING727 727223 1384074NM PWA JT8 JT8D15 52051NE ANTI-SKID SYS FAULTED W O OTHER O OTHER LDLANDING 1 CA (CAN) ON LANDING, THE NR 1 AND NR 4 TIRES SKIDDED UNTIL THEY BLEW OUT. THE A/C HAD TO BE TOWED FROM THE RUNWAY. AVIONICS PERSONELL DISCOVERED AN INTERMITTENT FAULT IN AN ANTI-SKID CONNECTOR (D4668) ABOVE THE RT GEAR LEG. ALL 4 TIRES AND THE CONNECTOR WERE REPLACED AND THE A/C RETURNED TO SERVICE. (TC NR 20060925009) 2L73 4F4 F A3WE E2EA 20061208000072006120800007CE 2006 12 8 CA060926003 120060921G561010138402524 WINDSHIELD BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA HARTZLHCB3T HCB3TN3 GL COCKPIT CRACKED W O OTHER O OTHER CRCRUISE 1 CA 1354 (CAN) IN HOLDING PATTERN AT 9,000 FT/-2C/WINDSHIELD HEAT ON LOW; OUTER PANE OF WINDSHIELD CRACKED FOR NO APPARENT REASON. FLIGHT CONTINUED AND LANDED WITHOUT INCIDENT. NO EVIDENCE OF BIRD STRIKE OR FOREIGN OBJECT DAMAGE NOTED. (TC NR 20060926003) 1L72 4T4 T A24CE E4EA 6 CP15EA 20070507000932007050700093CE 2007 5 7 CA060926004 120060923G273111452403725 CONTROL CABLE BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE HARTZLHCE4A HCE4A3I NE ELEVATOR TRIM BROKEN W O OTHER O OTHER APAPPROACH 1 CA 22576 (CAN) CREW REPORTED DIFFICULTY WITH CHANGING THE ELEVATOR TRIM ON APPROACH. MAINTENANCE FOUND THAT THE ELEVATOR TRIM CABLE HAS BROKEN AT THE TRIM SERVO/CAPSTAN LOCATION. THIS SERVO/CAPSTAN COMPONENT IS ONLY INSTALLED ON AUTOPILOT EQUIPPED 1900D`S OF WHICH THERE ONLY VERY FEW. THE CAPSTAN REQUIRES ROUTING OF THE .0625 CABLE. (TC NR 20060926004) 2L72 4T4 TRTA24CE E26NE 5 CP10NE 20061011001622006101100162GL 2006 10 11 CA060926005 320060913G6111M10876ANS BLADE HARTZL STBROSSD3 SD360 8100606EU PWA PT6 PT6A65AR 52043NE HARTZLHCB5M HCB5MP3 GL PROPELLER CORRODED W K NONE O OTHER ININSP/MAINT 1 CA 3341 EVA2469 EVA2469 (CAN) UPON VISUAL INSPECTION , CORROSION WAS FOUND ON THE BLADE SHANK. AFTER REWORK TO MINIMUM DIMENSION DAMAGE STILL REMAINS. BLADE WIDTH AND THICKNESS IS WELL ABOVE MINIMUM DIMENSION. ALL 5 BLADES ARE U/S. (TC NR 20060926005) 2H72 4T4 T A41EU E4EA 6 CP44GL 20061011001632006101100163GL 2006 10 11 CA060927001 220060919G723023053990 SCROLL RROYCE BELL 206 206L1 1182107SW ALLSN 250C 250C30P 03013GL COMPRESSOR CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 6362 5265 CAC90168 (CAN) DURING SCHEDULED 100/300 HR INSPECTION COMPRESSOR SCROLL FOUND CRACKED ON VISUAL INSPECTION. A/C GROUNDED AND COMPRESSOR REPLACED. RECOMMEND BETTER DAILY INSPECTIONS BEFORE FIRST FLIGHT. (TC NR 20060927001) 1G71 3U3 U H2SW E1GL 20061208000202006120800020SW 2006 12 8 CA060927003 120060927G5730 SKIN SWRNGNSA227 SA227AC 8780603SW GARRTTTPE331TPE33111U 01514WP MCAULY4HFR344HFR34C652 NE WINS CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 28657 (CAN) PERIMETER WAS INFORMED FROM ANOTHER OPERATOR OF THE SAME AIRCRAFT OF POTENTIAL WING SKIN CRACKS EMINATING FROM THE LT AND RT BATTERY VENT SCOOPS INSTALLED IN THE LOWER WING SKIN BETWEEN THE NACELLE AND FUSELAGE. INITIAL VISUAL INSPECTION REVEALED NO CRACKS BUT WITH THE USE OF EDDY CURRENT THE CRACKS WERE DISCOVERED AND FOUND PROGRESSING FROM 3 OF THE 4 CORNERS OF THE BATTERY VENT SCOOP AT THE WING SKIN. THE 4 AC OF THIS TYPE INSPECTED, 3 HAD CRACKS FOUND ON THE LOWER WING BATTERY VENT SCOOPS. THEY WERE INSPECTED AND ALL FOUND WITH EDDY CURRENT INSPECTION METHOD. REPAIR DESIGN CERTIFICATE RDC C-RA06-235/D HAS BEEN APPROVED FOR THE REPAIR OF THIS DEFECT. (TC NR 20060927003) 2L72 4T4 TRTA8SW E4WE 6 C3PNE 20061011001642006101100164NM 2006 10 11 CA060928001 120060928G7312S2L354 O-RING DHAV DHC8 DHC8301 1386003NM FUEL HEATER DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING THE ACCOMPLISHMENT OF THE TASK 2150/05 (HEAT EXCHANGER CORE CLEANNING) WE FOUND A NEW O-RING DAMAGED IN THE ORIGINAL PACKAGE. THE O-RING COME FROM NATIONNAL O-RING MFGR. COMPD. NR V-14 MFG BATCH NR: 58978 CURE DATE: 4088 EXP. DATE: OCT 01,2009 THE O-RING WAS DAMAGE ALL AROUND. A OTHER O-RING WITH THE SAME BATCH AND PN USE ON THE SAME JOB WAS FOUND OK FOR THE INSTALLATION. (TC NR 20060928001) 2H72 4T RTA13NM 20061011001652006101100165NE 2006 10 11 CA060928002 220060916G7200 ENGINE AIRBUS320 A320211 3930320EU GE CFM56 CFM565A 13802NE NR 2 VIBRATION W C ABORTED TAKEOFF E VIBRATION/BUFFET TOTAKEOFF 1 CA 731250 (CAN) T/O REJECTED AT APPROX 110 KTS DUE SERIOUS VIBRATIONS (SUSPECT RT MAIN GEAR). AUTO BRAKE USED MAX BRAKE TEMP IND 480 DEG FOR NR 2, OTHERS WERE 450-480. ON STARTING NR 2 ENGINE, FELT HIGH VIBRATION AND HIGH EGT, ABORTED ENGINE START. WHEN TURNING NR 2 FAN BY HAND, COULD HEAR N2 TURNING AS WELL. FOUND RT GEAR FIXED DOOR ASSY WITH 2 ATTACH STUDS SHEARED. SB A320-52-1100 ALREADY AVAILABLE TO INSTALL IMPROVED ATTACH STUDS. 2L72 4F4 FRTA28NM E29NE 20070507000942007050700094SW 2007 5 7 CA060928003 120060909G5521222182 STRINGER BBAVIA7 7ECA 21101NNSW LYC O235 O235K2C 41505EA SNSNCH72C 72CK EA FUSELAGE FAILED W A UNSCHED LANDING O OTHER CRCRUISE 1 CA 3626 (CAN) AFTER RECOVERING FROM AN AEROBATIC MANEUVER, THE PILOT FOUND THAT FULL DOWN ELEVATOR TRAVEL COULD NOT BE OBTAINED. A UNEVENTFUL RETURN TO THE AIRPORT AND LANDING WAS CARRIED OUT. ONCE THE ELEVATOR BELLCRANK COVER WAS REMOVED, THE LT GUSSET FROM THE AFT STRINGER SUPPORT FELL OUT AND FULL ELEVATOR TRAVEL WAS OBTAINED. EXAMINATION OF THE GUSSET, SUPPORT AND RIVETS INDICATED THAT VIBRATION OF THE FABRIC IN FLIGHT HAD LOOSENED THE SOFT ALUMINUM POP RIVETS THAT THE MFG HAD USED IN ATTACHING THE GUSSET HAD WORKED LOOSE AND EVENTUALLY BROKEN, ALLOWING THE GUSSET TO FALL INTO THE BELLY AND WORK ITS WAY BACK INTO THE TAIL WHERE IT BECAME LODGED IN THE NARROW CLEARANCES AROUND THE ELEVATOR BELLCRANK. THE SUBMITTER1H71 3O3 O A759 E223 5 NP9045 20061208000212006120800021CE 2006 12 8 CA060928004 120060817G32101158100325 TORQUE KNEE BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA HARTZLHCD4N3HCD4N3A GL MLG CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING A ROUTINE INSPECTION THE LT UPPER TORQUE KNEE WAS FOUND CRACKED. THE TORQUE KNEE WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. SEE ATTACHED PICTURES. (TC NR 20060928004) 1L72 4T4 T A24CE E4EA 5 CSTC 20061211001542006121100154GL 2006 12 11 CA060928005 320060925G6111R1015255 BLADE DHAV DHC2 DHC2MKI 2801830GL PWA R985 R985AN14B 52008NE HARTZLHCB3R HCB3R302 GL PROPELLER DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA 2015 AH4 (CAN) PROPELLER RECEIVED FOR O/H. UPON DISMANTLING DISCOLORATION ON THE BLADE SHANKS WAS NOTED. SHANKS WERE LIGHTLY MEDIA BLASTED AND THE DAMAGE IS MORE SEVERE THAN AT FIRST INSPECTION. BLADE SHANK RADIUS IS AT 4.194 INCHES MINIMUM FOR REPAIR IS 4.187 INCHES. THESE 3 BLADES ARE UNSERVICEABLE DUE TO THIS CORROSION. (TC NR 20060928005) 1H71 3R3 RRCA806 5E1 5 CP28EA 20061208000222006120800022GL 2006 12 8 CA060928006 320060915G6114C3054 FERRULE MCAULY CESSNA185 185 2072802CE CONT O470 IO470F 17026SO MCAULY2A34C D2A34C58 GL PROPELLER CORRODED W K NONE O OTHER ININSP/MAINT 1 CA 69 778082 (CAN) PROP RECEIVED FOR 10 YR. O/H. UPON DISMANTLING DISCOVERED CORROSION DAMAGE TO FERRULE. PART IS U/S (TC NR 20060928006) 1H71 3O3 ONC3A24 3E1 5 CP3EA 20061011001662006101100166EA 2006 10 11 CA060929001 120060918G5751DSC5108 BEARING DHAV DHC8 DHC8311 1386006EA PWA PW120 PW123 NE HAMSTD14SF 14SF15 NE LT AILERON WORN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) THE DEFECT WAS FOUND DURING A REPAIR OF WING TIP LIGHTNING STRIKE ON SEPTEMBER 18, 2006 AT A/C TCSN 35,548 CYCLES. AT THE OUTER AILERON THE HINGE FITTING ASSY SHOWED A PREMATURE BEARING WEAR. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20061011001672006101100167NM 2006 10 11 CA060929002 120060926G278110608197 INDICATOR BOEING727 727233 138408ANM PWA JT8 JT8D15 52051NE KRUEGER FLAPS FAILED W A UNSCHED LANDING N FALSE WARNING CLCLIMB 1 CA (CAN) DEPARTING THE CREW OBSERVED A L/E FLAP UNRETRACTED INDICATION AT THE NR 1 POSITION.THE AIRCRAFT RETURNED TO POINT WITHOUT FURTHER INCIDENT. MAINTENANCE FOUND THE POSITION INDICATION SWITCH HAD FAIL AT THE NR 1 KRUEGER FLAP LOCATION. THE SWITCH WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. (TC NR 20060929002) 2L73 4F4 FRTA3WE E2EA 20070104000012007010400001 2007 1 4 CA060929003 420060920G6122941521 SCREW AMBLP A150 A150 3850110NM ROTAX 914 ROTAX914 EU GEARBOX BROKEN W O OTHER F FLT CONT AFFECTED NRNOT REPORTED 1 CA 2077 577 (CAN) PROP WOULD NOT CHANGE PITCH DURING RUN-UP. GEARBOX WAS REMOVED AND THE SCREW HOLDING THE GOVENOR DRIVE COUPLING TO THE DRIVE GEAR WAS FOUND BROKEN. THE SCREW APPEARED TO HAVE FAILED FROM TORQUE OVERLOAD. THE SCREW, DRIVE COUPLING AND GEAR WERE REPLACED AND ENGINE RETURNED TO SERVICE. NO FOD NOTED. THE ENGINE HAS 577 HRS SINCE OVERHAUL. (TC NR 20060929003) 1B72 3O3 O0 SOOOO2SEEXPE3I 20061208000292006120800029EU 2006 12 8 CA060929004 120060928G324650104882A WHEEL SAAB SF340 340B 7860101EU GE CT7TP CT79B 30030NE ROTOL R390 R3904123F27 NE MLG MISSING W O OTHER D INFLIGHT SEPARATION TXTAXI/GRND HDL 1 CA (CAN) AFTER ARRIVAL, THE CAPTAIN WAS NOTIFIED THAT THE AIRCRAFT NR 3 MAINWHEEL WAS MISSING. MAINTENANCE INSPECTION REVEALED THAT ALTHOUGH THE WHEEL NUT AND LOCKING BOLT WERE IN PLACE THE WHEEL ITSELF WAS MISSING. (TC NR 20060929004) 2L72 4T4 TRTA52EU E8NE 6 CP31NE 20061208000302006120800030EA 2006 12 8 CA060929005 220060928G7313310926302 DUCT PWA PT6 PT6A34 52043EA ENGINE DAMAGED W O OTHER O OTHER NRNOT REPORTED 1 CA 3035 RB0207 (CAN) WHILE PERFORMING A BOROSCOPE INSPECTION DURING A REGULARLY SCHEDULED FUEL NOZZLE CHANGE, DAMAGE WAS FOUND ON THE LARGE EXIT DUCT. THE (LED) WAS CHANGED AND UPON CLOSER INSPECTION IT WAS FOUND THAT A LARGE HOLE HAD BEEN BURNED THROUGH ONE LAYER OF THE DUCT AND CRACKS HAD FORMED IN THE SECOND LAYER. THE ENGINE HAD OF 3034.6 TSN HOURS AND 6819 CYCLES. THIS WAS THE THIRD (LED) THAT THIS OPERATOR HAS HAD PROBLEMS WITH. IT IS SUSPECTED THAT EITHER A BAD FUEL NOZZLE (NOZZLES HAVE BEEN SENT OUT FOR TESTING) OR MATERIAL DEFECT CAUSED THE FAILURE. (TC NR 20060929005) 4 T E4EA 20061208000312006120800031NE 2006 12 8 CA061002001 220061002G7200AS21040 BOLT GULSTMG1159 GIV 3980115SO RROYCETAY TAYMK6118 NE ENGINE WRONG PART W K NONE O OTHER ININSP/MAINT 1 CA 7000 16230 (CAN) NON APPROVED AS21040 BOLT WAS FOUND. BOLT HEAD WAS MACHINED TO ADD PN AS21040. BOLT END ALSO MACHINED WITH A CENTER HOLE, THREAD LENGTH SHORTER AND DIAMETER OF BOLT IS UNDERSIZE. BOLT LOCATIONS ON ENGINE; CLIPPING POINT FOR P3 AIR TUBE TO FFR UNION P3 LIMITER, IP BLEED VALVE CLAMPING SEAL/RETAINING SEAL AND LP FUEL FILTER MOUNTING BOLT. (TC NR 20061002001) 2L72 4F4 FRTA12EA A25NE 20061208000502006120800050NE 2006 12 8 CA061002002 220060909G72003066T90G02 ENGINE SKRSKYS92 S92A NE GE CT7TP CT79B 30030NE NR 1 FAILED W A UNSCHED LANDING XJ ENGINE FLAMEOUT WARNING INDICATION APAPPROACH 1 CA (CAN) THE FOLLOWING REPORT REFERS TO FLT OCCURRENCE REPORT NR 06-00894. THE AIRCRAFT WAS OPERATING FOR CUSTOMER ON AN OFFSHORE FLIGHT. AT APPROX 09.58 WHILE ON SHORT FINAL APPROACH (IN VMC), 2 POPS WERE HEARD BY THE CREW. A MISSED APPROACH WAS INITIATED, AND DURING THE CLIMB OUT IT WAS APPARENT THE NR 1 ENGINE HAD HIGH TGT AND LOWER TORQUE THAN THE NR 2 ENGINE. DURING THE CLIMB SEVERAL MORE POPS WERE HEARD. AFTER REACHING A SAFE HEIGHT, THE EMERGENCY CHECKLIST WAS FOLLOWED FOR (COMPRESSOR STALLING) ON THE NR 1 ENGINE. IAW THE CHECKLIST, THE NR 1 ENGINE WAS BROUGHT BACK TO IDLE, AND THE COMPRESSOR STALLING CEASED. THE CREW THEN ELECTED TO RETURN TO DEPARTURE, WITH NR 1 ENGINE AT IDLE, IAW THE EMERGENCY CHECKLIS2G72 4U4 T R00024BOE8NE 20061208000512006120800051 2006 12 8 CA061002003 420060824G3442 DIODE HONEYWELL DHAV DHC8 DHC8301 1386003NM PWA PW120 PW123 NE HAMSTD14SF 14SF15 NE WX RADAR SYSTEM BURNED W G O2 MASK DEPLOYED B SMOKE/FUMES/ODORS/SPARKS DEDESCENT 1 CA 2678926789 1643 (CAN) ON DECENT THROUGH 10,000 FEET, F/O NOTICED A HAZY SMOKE IN THE COCKPIT. BOTH THE CAPTAIN AND THE F/O BEGAN TO FEEL A BURNING SENSATION IN THEIR THROATS. THEY DONNED THEIR OXYGEN MASKS AND REQUESTED A VISUAL DIRECT APPROACH. THERE WAS A DEFINITE ELECTRICAL SMELL IN THE COCKPIT. THE CABIN HAD A SLIGHT ODOR BUT NOT RECOGNIZABLE. PASSENGERS WERE UNAWARE OF THE SITUATION, NO PASSENGER REACTION. CREW DID NOT DECLARE AN EMERGENCY AND LANDED SAFELY WITHOUT FURTHER INCIDENT. MAINTENANCE DISCOVERED WEATHER RADAR INDICATOR TO BE AT FAULT. WEATHER RADAR INDICATOR AND TRANSMITTER/RECEIVER REPLACED AND TESTED SERVICEABLE. AIRCRAFT SUCCESSFULLY TEST FLOWN PRIOR TO RETURN TO SERVICE. INDICATOR HAD 865:02 HOURS AND 830 L2H72 4T4 TRTA13NM E20NE 6 CP7NE 20061208000522006120800052WP 2006 12 8 CA061002004 120060805G5411C04618 FRAME ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE NACELLE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 350 350 (CAN) AFT TAB WAS FOUND TO BE CRACKED UPON ROUTINE SCHEDULED INSPECTION. NEW FRAME ORDERED AND HELICOPTER WAS NOTIFIED OF THE PROBLEM. THEY HAVE SINCE RELEASED A NEW BULLETIN ADDING A CLAMP TO THE FRAME. THIS AIRCRAFT IS REGISTERED WITH MFG FOR WHEN THE CORRECTIVE PARTS BECOME AVAILABLE. (TC NR 20061002004) 1G71 3O3 O H11NM 1E4 20061208000532006120800053SW 2006 12 8 CA061002005 120060831G2711 CABLE BBAVIA7 7GCBC 1220601SW LYC O320 O320A2B 41508EA MCAULY1A175 1A175GMA GL AILERON TAB DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA 48 (CAN) IAW AD 2005-24-10 AND MFG SERVICE LETTER NR 427, THE FLIGHT CONTROL CABLE INCLUDED IN THE WING RETROFIT KIT WAS INSPECTED FOR PROPER SWAGING. AILERON CABLES REQUIRED PROPER SWAGING. (TC NR 20061002005) 1H71 3O3 ONCA759 E274 5 NP857 20061208000542006120800054SO 2006 12 8 CA061002006 120060928G3230 LANDING GEAR PIPER PA31 PA31P 7103120SO LYC O541 TIGO541E1A 41539EA HARTZLHCC3Y HCC3YN GL RIGHT FAILED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) DEFECT: UNABLE TO PUT DOWN GEAR AND GET 3 GREEN LIGHTS. UPON 4TH TRY WHILE IN A HARD RT TURN, FINALLY GOT RT MAIN GEAR DOWN AND LOCKED. AIRCRAFT RETURNED TO BASE WITH LANDING GEAR IN DOWN/LOCKED POSITION UNDER FERRY FLIGHT PERMIT. RECTIFICATION: LANDING GEAR INSPECTED, SYSTEM FLUSHED AND BLED IAW MFG MM. LANDING SWUNG 50 FAULT FREE TIMES. UNABLE TO DUPLICATE FAULT. AIRCRAFT RETURNED TO SERVICE. (TC NR 20061002006) 1L72 3O3 O A8EA E19EA 5 CP25EA 20061208000552006120800055EA 2006 12 8 CA061002007 220060928G732125245019 FUEL CONTROL PIPER PA31 PA31P 7103120SO LYC O541 TIGO541E1A 41539EA HARTZLHCC3Y HCC3YN GL ENGINE FAILED W O OTHER RJ PARTIAL RPM/PWR LOSS WARNING INDICATION NRNOT REPORTED 1 CA (CAN) UNCONTROLLABLE POWER FLUCTUATIONS AT HIGH POWER SETTINGS ON LT ENGINE. FOUND FUEL CONTROL UNIT P/N 2524501-9 S/N 70084801 TO BE UNSERVICEABLE. REPLACED WITH REBUILT UNIT P/N 2524501-9 S/N 70157810. SYSTEM GROUND RUN SERVICEABLE. (TC NR 20061002007) 1L72 3O3 O A8EA E19EA 5 CP25EA 20061208000662006120800066WP 2006 12 8 CA061002009 120060926G67971520 WIRE ROBSIN C0581 ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE CYCLIC GRIP CHAFED W K NONE O OTHER ININSP/MAINT 1 CA 2196 (CAN) GRIP ASSEMBLY OPENED TO INSTALL CARGO HOOK SWITCH AND FOUND STARTER BUTTON WIRE CHAFED UP AGAINST A GRIP MOUNTING SCREW. THE INSULATION WAS SPLIT OPEN 0.25 INCH AND 2 WIRE STRANDS REMAINED UNBROKEN. (TC NR 20061002009) 1G71 3O3 O H11NM 1E4 20061208000672006120800067EU 2006 12 8 CA061002010 120060928G2497E0052R22B55SNE CONNECTOR AEROSPATR42 ATR42300 8680920EU PWA 120 PW120 NE HAMSTD14SF 14SF5 NE ELECTRICAL PWR BURNED W O OTHER B SMOKE/FUMES/ODORS/SPARKS LDLANDING 1 CA (CAN) CONNECTOR WAS SHORTING ACROSS INSULATING MATERIAL. PROBLEM WAS BETWEEN ADJACENT PIN CONTACTS. MATING CONNECTOR 704VC WAS UNHARMED. BURNED CONTACTS HAD LOTS OF BLACK CARBON ON THEM. (TC NR 20061002010) 2H72 4T4 TRTA53EU E20NE 6 CP7NE 20061208000692006120800069GL 2006 12 8 CA061002011 320060929G61975038912131 CONNECTOR BEECH 1900 1900C 1154161CE PWA PT6 PT6A65B 52043EA HARTZLHCB4M HCB4MP3 GL NR 2 PROPELLER DAMAGED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) FAULT - LT SIDE AUTOFEATHER LIGHT DOES NOT ARM. NR 2 HIGH PRESS FEATHER SWITCH CONNECTOR, CONNECTOR PIN LETTER B REPLACED. SWITCH CONNECTORS CLEANED. PROBLEM SEEMED TO BE CAUSED BY CONTAMINATION. (TC NR 20061002011) 2L72 4T4 TRTA24CE E4EA 6 CP56GL 20061208000702006120800070EU 2006 12 8 CA061003001 120060924G3240AC13794 PRESSURE VALVE BRAERO748 HS7482A 4231001EU RROYCEDART DART5342 EU ROTOL R4304 R2124304 EU BRAKE MALFUNCTIONED W D RETURN TO BLOCK J WARNING INDICATION TXTAXI/GRND HDL 1 CA 11340 (CAN) DURING TAXI TO POSITION THE THE MAIN HYDRAULIC SYSTEM WAS CYCLING EVERY 30 SECONDS. THE CREW RETURNED TO COMPANY RAMP. THE IB BRAKE PRESSURE REDUCING VALVE WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20061003001) 2L72 3T4 T A24EU A196 6 CP899 20061208000712006120800071EU 2006 12 8 CA061003003 120060928G3060 BRUSH BLOCK AEROSPATR42 ATR42300 8680920EU PWA 120 PW120 NE HAMSTD14SF 14SF5 NE PROPELLER UNKNOWN W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA (CAN) DURING CLIMB AFTER DEPARTURE THE CREW OBSERVED AN ANTI-ICE FAULT ON NR 1 POSITION. THE AIRCRAFT RETURNED TO POINT OF DEPARTURE. MAINTENANCE REPLACED THE BRUSHES ON NR 1 BRUSH BLOCK AND THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20061003003) 2H72 4T4 TRTA53EU E20NE 6 CP7NE 20061208000722006120800072CE 2006 12 8 CA061003004 120060926G5740114430002179 ANGLE BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE HARTZLHCE4A HCE4A3I NE BS 288 CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 9184 (CAN) WHILE COMPLETING A PRESSURIZATION CHECK OF THE CABIN, AIR WAS FOUND TO BE LEAKING OUT AROUND SPAR/ FUSE JOINT AREA. CRACKS WERE FOUND ON THE LT AND RT WING-FUSELAGE CLOSING ANGLES AT FS 288 IN THE SAME SPOTS MEASURING 1.7500 INCHES EACH. LT ANGLE IS P/N 114-430002-179 AND THE RT IS114-430002-180. CRACKS REPAIRED IAW SRM 53-90-23. (TC NR 20061003004) 2L72 4T4 TRTA24CE E26NE 5 CP10NE 20061208000732006120800073GL 2006 12 8 CA061003005 120061001G2910 HYDRAULIC SYSTEM BOMBDRBD100 BD1001A10 1390044GL NR 2 LEAKING W E ENGINE SHUTDOWN KJ FLUID LOSS WARNING INDICATION TXTAXI/GRND HDL 1 CA (CAN) WHILE VERIFYING A NOSE WHEEL STEERING SNAG DURING TAXI TEST, A LOSS OF HYDRAULIC FLUID FROM NR 2 SYSTEM OCCURED. LT AND RT ENGINES WERE SHUTDOWN AND AREA WAS INSPECTED. HYDRAULIC FLUID WAS FOUND TO HAVE SPRAYED IN AFT FUSELAGE AND ON THE RT SIDE. (TC NR 20061003005) 2L72 4F RTT00005NY 20061208000742006120800074SO 2006 12 8 CA061004001 220060924G731464936849A1 PUMP DIAMONDA20 DA20C1 2990001GL CONT O240 IO240B 17063SO SNSNCHW69EK W69EK63 EA ENGINE OUT OF ADJUST W O OTHER Y ENGINE STOPPAGE DEDESCENT 1 CA 88 650201 (CAN) AIRCRAFT ENGINE FAILED IMMEDIATELY AFTER SPIN RECOVERY. INSTRUCTOR CONFIRMED FUEL PUMP ON AND MIXTURE FULL RICH. INSTRUCTOR ESTABLISHED BEST GLIDE ATTITUDE AND RESTARTED ENGINE IAW AFM (ENGAGING STARTER). UPON LANDING AND TAXI, INSTRUCTOR KEPT POWER ABOVE 1000 RPM, SO THERE IS NO FURTHER INFO ON LOW POWER BEHAVIOR DURING THIS FLIGHT. IMMEDIATELY PUT TEST GAUGES ON, AND RAN UP AIRCRAFT. UNMETERED PRESSURE WAS APPROXIMATELY 1.6 PSI LOW AND METERED PRESSURE WAS APPROX 2 PSI LOW. IDLE MIXTURE RISE OF 10 TO 20 RPM. IT IS WORTH NOTING THAT I FELT THE ENGINE DID NOT (SOUND) AS IF IT WAS FUNCTIONING PROPERLY. WE HAVE CURRENTLY REMOVED ALL FUEL SCREENS, INSPECTED AND CLEANED. MODERATE CONTAMINATION FOUND 1L71 3O3 ONTTA4CH E7SO 5 NTA4CH 20061208000762006120800076NM 2006 12 8 CA061004003 120061002G323365446604 ACTUATOR BOEING737 737242C 1384478NM PWA JT8 JT8D9A 52048NE NLG BYPASSING W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA (CAN) ON CLIMB OUT THE NOSE LANDING GEAR FAILED TO RETRACT. THE AIRCRAFT RETURNED TO POINT OF DEPARTURE AND LANDED WITHOUT INCIDENT. MAINTENANCE DETERMINED THAT THE NOSE LANDING GEAR GRAVEL DEFLECTOR ACTUATOR HAD FAILED. THE ACTUATOR WAS REPLACED AND THE AIRCEAFT WAS RETURNED TO SERVICE. (TC NR 20061004003) 2L72 4F4 F A16WE E2EA 20061208000782006120800078EA 2006 12 8 CA061004004 120061002G272282960010147 TUBE DHAV DHC8 DHC8311 1386006EA PWA PW120 PW123 NE HAMSTD14SF 14SF15 NE RUDDER ACTUATOR CRACKED W K NONE KJ FLUID LOSS WARNING INDICATION ININSP/MAINT 1 CA (CAN) CREW NOTICED FLUID STAINS AND ACCUMULATION ON RT SIDE OF RUDDER AND TAIL CONE. MAINTENANCE FOUND CRACK AT FIRST ELBOW FROM TOP FITTING OF NO. 1 HYDRAULIC SYSTEM PRESSURE LINE TO THE RUDDER ACTUATOR. LINE REPLACED AND SYSTEM LEAK CHECKED SERVICEABLE. IPC REF CH 27-21-00 FIG. 20 ITEM 120. AFTT 34,145:10 HOURS, AFTC 38202. (TC NR 20061004004) 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20061208000792006120800079EU 2006 12 8 CA061004005 120060926G3250114068003 ACTUATOR PIAGIOP180 P180 6960204EU PWA PT6 PT6A66 52043NE HARTZLHCE5N HCE5N3 GL NLG STEERING FAILED W D RETURN TO BLOCK J WARNING INDICATION TXTAXI/GRND HDL 1 CA 136 136 (CAN) PILOTS REPORTED NOSE GEAR STEERING FAILURE. NOSE GEAR ACTUATOR REPLACED. SYSTEM TESTED AND AIRCRAFT RETURNED TO SERVICE (TC NR 20061004005) 1H72 3O4 TRTA59EU E26NE 5 CPZONE 20061208000822006120800082EA 2006 12 8 CA061004006 220061001G8520 BEARING PIPER PA31 PA31350 7103110SO LYC O540 LTIO540J2BD 41533EA CRANKSHAFT BROKEN W A UNSCHED LANDING Y ENGINE STOPPAGE CRCRUISE 1 CA 8542 1341 L251768A (CAN) THE AIRCRAFT DEPARTED THE RUNWAY FOR A 1 HOUR TRIP. APPROXIMATELY 17 MINUTES INTO THE CRUISE PORTION OF FLIGHT THE PILOT NOTICED A LOSS IN OIL PRESSURE FOLLOWED BY NOISE FROM THE RT ENGINE. THE PILOT IMMEDIATELY FEATHERED THE PROP AND SHUTDOWN THE ENGINE. THE WEATHER WAS OK AND ELECTED TO RETURN TO THE DEPARTURE RUN-WAY AND LANDED WITHOUT INCIDENT. AN INVESTIGATION REVEALED THAT THE CRANKSHAFT BROKE AT THE NR 2 BEARING JOURNAL. (TC NR 20061004006) 1L72 3O3 O A20SO E14EA 20061208000832006120800083SW 2006 12 8 CA061004007 120061002G5302206020113 INSERT BELL 206 206B 1181511SW ALLSN 250C 250C20B 03013GL VERTICAL STAB CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 13000 (CAN) IN COMPLIANCE WITH CF-2006-12 THE VERTICAL FIN WAS INSPECTED WITH 10X MAGNAFLYING GLASS AND THEN WAS LPI INSPECTED AND A CRACK WAS FOUND ON ONE OF THE INSERTS. THE FIN WAS SENT OUT FOR REPAIR. (TC NR 20061004007) 1G71 3U3 U H2SW E4CE 20061208000842006120800084EA 2006 12 8 CA061004008 220060930G7240310926302 DUCT DHAV DHC3 DHC3 2800202EA PWA PT6 PT6A34 52043EA ENGINE DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA 1677 (CAN) DURING A REGULARLY SCHEDULED HOT SECTION INSPECTION A CRACK WAS NOTICED IN THE LARGE EXIT DUCT (LED) BEING REMOVED FROM THE ENGINE. THE CRACK WAS LOCATED ON THE DOME AT THE DOUBLE WALL SEAM. THE LED HAD BEEN RECENTLY OVERHAULED AND HAD A TSO OF 1676.9. THIS WAS THE 4TH LED DUCT THAT THIS OPERATOR HAS HAD A PROBLEMS WITH. (TC NR 20061004008) 1H71 3R4 T A815 E4EA 20061208000862006120800086EA 2006 12 8 CA061004009 120061004G3200 WASHER DHAV DHC6 DHC6 2802606EA MLG MISMANUFACTURED W O OTHER W INADEQUATE Q C NRNOT REPORTED 1 CA (CAN) WE HAVE FOUND 2 BATCHES OF C6U1156-27 MAIN LANDING GEAR WASHERS MADE FROM ALUMINUM LAMINATED SHIM MATERIAL, BUT SHOULD HAVE BEEN MADE FROM STAINLESS STEEL SHIM MATERIAL. DUE TO THE APPLICATION OF THE WASHER, THERE IS NO STRENGTH REQUIREMENT, HOWEVER, THERE IS A POTENTIAL FOR GALVANIC CORROSION. THE AFFECTED BATCHES OF WASHERS ARE WO-25363/1 AND PO43141/69. (TC NR 20061004009) 1H72 3T RTA9EA 20061208000882006120800088 2006 12 8 CA061005001 120061005G3000 LINE PWA JT15 JT15D4 52112NE ANTI ICE SYS DAMAGED W O OTHER K FLUID LOSS NRNOT REPORTED 1 CA 7161 858 (CAN) SEE REPORT ATTACHED GAS GENERATOR DISPLAYED VISIBLE SIGNS OF COKED OIL ON THE EXTERNAL CASING. ENGINE OIL LEAK WAS CAUSED BY ANTI-ICING STEEL TUBE DEBONDING FROM THE INTERMEDIATE CASE CASTING AT THE STEEL TAB USED TO LOCATE THE TUBE DURING THE CASTING PROCESS. THE TAB PROTRUDES INTO THE OIL TANK AND IF DEBONDED CAN CAUSE OIL LEAKAGE. ENGINEERING REPORT ATTACHED TO THIS SDR. (TC NR 20061005001) 4 F E1NE 20061208000912006120800091CE 2006 12 8 CA061005002 120061005G57400513006142 RIVET CESSNA185 A185E 2072818CE CONT O520 IO520D 17032SO MCAULY2A34C D2A34C58 GL FITTING LOOSE W K NONE O OTHER ININSP/MAINT 1 CA 7171 (CAN) THE AIRCRAFT WAS DISASSEMBLED. IT WAS NOTED THAT THERE WERE SEVERAL LOOSE AND SMOKING FASTENERS THROUGH RT AFT WING FITTING BRACKET IN FUSELAGE. REFERENCED MFG PART MANUAL P527-12 FIGURE 30 INDEX NR 99. (TC NR 20061005002) 1H71 3O3 O 3A24 E5CE 5 CP3EA 20061208000932006120800093NE 2006 12 8 CA061005003 220061005G8530 INTAKE DUCT DHAV DHC2 DHC2MKI 2801830GL PWA R985 R985AN14B 52008NE HAMSTD2D 2D30 NE ENGINE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) 5 OF THE 9 INTAKE TUBES WERE FOUND CRACKED AT THE CYLINDER FLANGE. (TC NR 20061005003) 1H71 3R3 RRCA806 5E1 5 CP206 20061208000952006120800095NE 2006 12 8 CA061005005 220060925G73001851M43P08 ECU AIRBUSA340 A340313 EU CFMINTCFM56 CFM565C4 13802NE NR 2 ENGINE FAILED W EF ENGINE SHUTDOWN ACTIVATE FIRE EXT. J WARNING INDICATION CRCRUISE 1 CA 33115 741568 (CAN) DEPARTURE AND ENROUTE TO DESTINATION, NR 2 ENGINE PARAMETERS ERRATIC, THEN INDICATE THAT NR 2 EGT OVER LIMITS, THEN VIBRATION. ENGINE SHUTDOWN AND BOTTLE DISCHARGED. REPLACED ECU IAW MM, RT VSV ACTUATOR REPLACED. FADEC MOTORING CHK ACCOMPLISHED IAW MM, MIN IDLE LEAK CHK ACCOMPLISHED IAW MM, PWR ASSURANCE CHK ACCOMPLISHED IAW MM, VIBE SURVEY CHK ACCOMPLISHED IAW MM, CHK ACCOMPLISHED IAW MM. ALL CHECKS OK, ENGINE OPS WITHIN NORMAL PARAMETERS. (TC NR 20061005005) 2L74 4F4 FRTA197 E37NE 20061208000972006120800097NM 2006 12 8 CA061005006 120061004G243523088002A STARTER GEN DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE NR 2 FAILED W K NONE O OTHER ININSP/MAINT 1 CA 413 (CAN) THE FLIGHT CREW SNAGGED THAT THE NR 2 GENERATOR FAILED. UPON FURTHER INVESTIGATION MAINTENANCE DISCOVERED THAT STARTER-GENERATOR HAD FAILED INTERNALLY. WHEN THE STARTER-GENERATOR IS COOLING DUCT AND WINDOW STRAP WERE REMOVED LOSE PIECES OF BRUSH MATERIAL FELL OUT OF THE STARTER-GENERATOR. ONE OF THE COMMUTATOR SEGMENTS WAS ALSO PARTIALLY MISSING AND MANY BRUSHES WERE CRACKED OR BROKEN. ONE OF THE DC CURRENT LIMITERS IN THE DC CONTACTOR BOX WAS ALSO FOUND TO BE OPEN. THE STARTER-GENERATOR, GENERATOR CONTROL UNIT, AND THE ASSOCIATED CURRENT LIMITER WERE REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20061005006) 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20061208001012006120800101EA 2006 12 8 CA061005007 120061004G3244900012001 TIRE CNDAIRCL600 CL600* EA GE CF34 CF348C1 NE MLG FAILED W C ABORTED TAKEOFF E VIBRATION/BUFFET TOTAKEOFF 1 CA 455 (CAN) THE CREW REPORTED THAT DURING THE TAKEOFF ROLL THE FLIGHT ATTENDANT REPORT A LOUD BANG. AFTER CONFERENCING WITH MAINTENANCE CONTROL, THE AIRCRAFT WAS ASKED TO CONTINUE TO DESTINATION. UPON ARRIVAL, IT WAS DETERMINED THAT THE NR 4 MAIN WHEEL WAS RAGGED AND APPEARED DEFLATED. THIS IS THE SECOND (WILKERSON RETREAD) FOR THE CRJ 700/900 AS DOCUMENTED IN SDR 20060110004. (TC NR 20061005007) 2L72 4F4 FRTA21EA EOOO63EN 20061208001072006120800107EU 2006 12 8 CA061005009 120061004G5280 BOLT EMB ERJ190ERJ190100IGW3260408EU LT MLG DOOR SHEARED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) LT MLG STAY AND DOOR BRACKET BOLTS SHEARED. OLD BOLTS HAVE P/N 2821-8041, AND THE NEW BOLTS HAVE P/N NAS6605D28 (BETTER QUALITY). THEY ARE BEING INSTALLED THROUGH SB 190-32-0010. (TC NR 20061005009) 2L72 4F RTA57NM 20061208001102006120800110EA 2006 12 8 CA061005010 220060909G7321 SHAFT BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17EU NR 2 FMU SHEARED W BA EMER. DESCENT UNSCHED LANDING XJ ENGINE FLAMEOUT WARNING INDICATION DEDESCENT 1 CA 5602 F48358 (CAN) DURING DESCENT INTO BASE, NR 2 ENGINE SUDDENLY SHUTDOWN. CREW GOT THE INDICATION BY A YAW AND DISCOVERED AFTERWARDS THE PROP TQ WAS ZERO. EMERGENCY DECLARED. POWERPLANT MESSAGE ON ED QRH ACTIONS WERE CARRIED OUT. PAX BRIEFED ON DESCENT AND IN TERMINAL AFTERWARDS. UNEVENTFUL APPROACH/LANDING AND TAXI. MAINT REPORT: FAULT CODES: 360/907/935/970. FMU REMOVED AND FOUND SHAFT SHEARED. FMU REPLACED EGR CARRIED OUT NORMAL. (TC NR 20061005010) 2H72 4T4 TRTA13NM E00062EN6 CP17BO 20061208001112006120800111 2006 12 8 CA061005011 420060914G6122 GOVERNOR CESSNA206 U206G 2073356CE CONT O520 IO520F 17032SO HARTZLHCJ3Y PHCJ3YF1 GL PROPELLER SEIZED W A UNSCHED LANDING YJ ENGINE STOPPAGE WARNING INDICATION CRCRUISE 1 CA 051411 (CAN) THE A/C WAS IN NORMAL FLIGHT AND NOTED AN OVERSPEED CONDITION FROM CRUISE RPM TO FULL POWER. CYCLING THE PROP PITCH CONTROL DID NOTHING; THE PILOT EXECUTED A FORCED LANDING. AME REMOVED THE PROP GOVERNOR AND NOTICED IT WAS SEIZED AND CONTAMINATED. REMOVED THE OIL FILTER AND NOTICED IT WAS CONTAMINATED WITH METAL PARTICLES. DRAINED THE OIL PAN WITH FRESH VARSOL AND FLUSHED THE PAN TO CLEAN ANY CONTAMINATES. INSTALLED FRESH NEW OIL AND INSTALLED NEW GOVERNOR. GROUND RUN UP WAS SATISFACTORY FOR FERRY FLIGHT TO REQUIRED BASE. PROP AND ENGINE REMOVED DUE TO OVERSPEED AND SENT TO REPAIR STATION FOR INSPECTION. (TC NR 20061005011) 1H71 3O3 O A4CE E5CE 5 CP36EA 20080220000032008022000003EU 2008 2 20 CA061005012 120061005G6200355A27008200 LEVER SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1D1 60053NE LOAD COMPENSATORDAMAGED W K NONE O OTHER ININSP/MAINT 1 CA 2315 (CAN) LOAD COMPENSATOR ARM WAS FOUND TO HAVE ELONGATED ATTACHMENT HOLES. NEW LEVER INSTALLED. THE OLD LEVER HAS BEEN SENT TO MFG FOR EVALUATION AS TO WHAT MAY BE THE CAUSE OF THIS. SUSPECT EXCESSIVE FORCE APPLIED BY THE ACCUMULATOR. (TC NR 20061005012) 1G71 3U3 U H9EU E19EU 20061211001562006121100156SW 2006 12 11 CA061006002 120061001G32502719087007 ACTUATOR SWRNGNSA226 SA226AT 8780405SW GARRTTTPE331TPE33110UA 01514WP HARTZLHCB3T HCB3TN5 GL NOSE STEERING MALFUNCTIONED W E ENGINE SHUTDOWN J WARNING INDICATION TXTAXI/GRND HDL 1 CA (CAN) MAINTENANCE WAS COMPLETING AN ENGINE CHANGE. AN AME TAXI`D THE AIRCRAFT FROM THE HANGER TO THE DESIGNATED RUNUP AREA. ON THE TAXI WAY, THE AIRCRAFT ABRUPTLY VEERED TO THE RT, AND THE RT PROPELLER STRUCK A TAXIWAY MARKER. THE ENGINE WAS SHUTDOWN AND DAMAGE WAS EVIDENT TO THE PROPELLER. THE ENGINE AND PROPELLER WERE REPLACED. THE NWS SYSTEM WAS TROUBLESHOT, NO ELECTRICAL CONTROL FAULTS WERE EVIDENT. THE NWS DID FAIL ON A SUBSEQUENT GROUND RUN WITH ANOTHER AME. ALL NWS COMPONENTS AT THE NOSE GEAR WERE REPLACED WITH SERVICEABLE PARTS - ACTUATOR, MANIFOLD, PRESSURE SWITCH, SERVO VALVE. NO FAULTS WERE NOTED ON TAXI TESTS OR TEST FLIGHTS. (TC NR 20061006002) 2L72 4T4 TRTA5SW E4WE 6 CP15EA 20061211001582006121100158EA 2006 12 11 CA061006003 220060901G7321 DRIVE SHAFT HAMSTD BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA FMU FRACTURED W O OTHER XJ ENGINE FLAMEOUT WARNING INDICATION DEDESCENT 1 CA F48358 (CAN) ON DESCENT, THE ENGINE FLAMED OUT. GROUND INSPECTION REVEALED A FRACTURED FUEL METERING UNIT DRIVE SHAFT. (TC NR 20061006003) 2H72 4T4 TRTA13NM E00062EN 20061211001592006121100159NE 2006 12 11 CA061006004 220060904G7230 ENGINE BELL 212 212 1181420SW PWA PT6T PT6T3B 52045NE FIRE W F ACTIVATE FIRE EXT. AJ FLAME/FIRE WARNING INDICATION NRNOT REPORTED 1 CA 61956 (CAN) DURING FLIGHT THE FIRE WARNING ACTIVATED. THE FIRE BOTTLES WERE DISCHARGED AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE. SUBSEQUENT INSPECTION REVEALED A PUNCTURED GAS GENERATOR CASE AND FIRE DAMAGE TO THE ENGINE. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 1G71 4U4 U H4SW E22EA 20061211001612006121100161EA 2006 12 11 CA061006005 220060831G7314 COUPLING PILATSPC12 PC1245 7090551EU PWA PT6 PT6A6 52043EA PUMP FRACTURED W O OTHER J WARNING INDICATION TXTAXI/GRND HDL 1 CA 2254 (CAN) THE ENGINE EXPERIENCED AN UNCOMMANDED ACCELERATION IN FLIGHT. THE ENGINE WAS SHUTDOWN AND SUCCESSFULLY RE-LIT AND THE UNCOMMANDED ACCELERATION REPEATED. THE ENGINE WAS AGAIN SHUTDOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED A FRACTURED FUEL CONTROL / FUEL PUMP COUPLING. (TC NR 20061006005) 1L71 3T3 TRTA78EU E4EA 20061211001632006121100163EA 2006 12 11 CA061006006 220060719G7321 DRIVE SHAFT BEECH 90 C90 1152913CE PWA PT6 PT6A21 52043EA FUEL CONTROL FRACTURED W O OTHER XJ ENGINE FLAMEOUT WARNING INDICATION NRNOT REPORTED 1 CA 2254 A75829 (CAN) THE FUEL CONTROL DRIVE SHAFT WAS FOUND FRACTURED. THE FUEL CONTROL MID LIFE INSPECTION WAS DETERMINED NOT TO HAVE BEEN PERFORMED. (TC NR 20061006006) 1L72 3T4 T 3A20 E4EA 20061211001642006121100164NE 2006 12 11 CA061006007 220060824G7261 PRECOOLER AEROSPATR72 ATR72 EU PWA PW120 PW124B NE ENGINE UNKNOWN W E ENGINE SHUTDOWN J WARNING INDICATION TXTAXI/GRND HDL 1 CA 124481 (CAN) THE ENGINE LOW OIL PRESSURE WARNING ACTIVATED DURING A FLIGHT TEST. THE ENGINE WAS SHUTDOWN IN FLIGHT. THE FUEL-COOLED-OIL-COOLER AND FUEL HEATER WERE SUBSEQUENTLY REPLACED. MFG WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061006007) 2H72 4T4 TRT E2ONE 20061211001652006121100165NE 2006 12 11 CA061006008 220060811G7200 ENGINE BELL 212 212 1181420SW PWA PT6T PT6T3B 52045NE NR 2 UNKNOWN W O OTHER RJ PARTIAL RPM/PWR LOSS WARNING INDICATION HOHOVERING 1 CA 62572 (CAN) ON TRANSITION FROM HOVER, NR 2 POWER SECTION TORQUE DECREASED UNCOMMANDED. AN EMERGENCY LANDING FOLLOWED RESULTING IN AIRFRAME DAMAGE. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061006008) 1G71 4U4 U H4SW E22EA 20061211001672006121100167NE 2006 12 11 CA061006009 220060908G7200 ENGINE LEAR 60 60LEAR 5170707CE PWA 305 PW305A 52128NE FLAMED OUT W O OTHER XJ ENGINE FLAMEOUT WARNING INDICATION DEDESCENT 1 CA CA0090 (CAN) THE ENGINE FLAMED OUT ON DESCENT. AN INFLIGHT RELIGHT WAS SUCCESSFULLY ACCOMPLISHED. MFG WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061006009) 2L72 4F4 FRTA10CE E35NE 20061211001682006121100168NE 2006 12 11 CA061006010 220060913G7310 MANIFOLD CESSNA500 560CESSNA 2076750CE PWA 530 PW535A NE FUEL SYSTEM LEAKING W FE ACTIVATE FIRE EXT. ENGINE SHUTDOWN KA FLUID LOSS FLAME/FIRE DEDESCENT 1 CA (CAN) A LOUD NOISE AND A FLASH FROM THE ENGINE WERE REPORTED ON DESCENT ACCOMPANIED BY A FIRE DETECTOR WARNING. THE ENGINE WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED SEPARATION OF THE NACELLE COWLS WITH RESULTANT AIRFRAME IMPACT DAMAGE. THE ENGINE FUEL MANIFOLD AND EXTERNALS WERE FOUND TO BE FIRE DAMAGED. MFG WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061006010) 2L72 4F4 FRTA22CE E00053EN 20061211002052006121100205NE 2006 12 11 CA061006012 220060918G7261 ENGINE BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE LEAKING W E ENGINE SHUTDOWN KJ FLUID LOSS WARNING INDICATION CLCLIMB 1 CA 114348 (CAN) DURING TAKE-OFF CLIMB, THE ENGINE LOW OIL PRESSURE WARNING ACTIVATED AND OIL PRESSURE DECREASED TO ZERO. THE ENGINE WAS SHUTDOWN IN FLIGHT AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE. INSPECTION REVEALED OIL IN THE ENGINE EXHAUST DUCT. MFG WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061006012) 2L72 4T4 TRTA24CE E26NE 20061211002062006121100206NE 2006 12 11 CA061006013 220060815G7230 COMPRESSOR CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE ENGINE SEIZED W O OTHER XJ ENGINE FLAMEOUT WARNING INDICATION CRCRUISE 1 CA 19374 (CAN) THE ENGINE WAS REPORTED TO EMIT A LOUD NOISE AND SUBSEQUENTLY FLAMED OUT IN FLIGHT. POST-FLIGHT INSPECTION REVEALED METAL DEBRIS IN THE OIL, RUBBING NOISES FROM THE POWER SECTION AND A SEIZED COMPRESSOR. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061006013) 1H71 3T3 T A37CE E4EA 20070108001442007010800144NE 2007 1 8 CA061006014 220060919G7200 BLADE AMTR ALPHA ALPHA 05613GUGL PWA 306 PW306B NE ENGINE DAMAGED W O OTHER XJ ENGINE FLAMEOUT WARNING INDICATION CLCLIMB 1 CA CD0130 (CAN) ON CLIMB, THE ENGINE EMITTED A LOUD NOISE AND FLAMED OUT. SUBSEQUENT INSPECTION REVEALED HPT1 BLADE DAMAGE. P&WC WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061006014) 1D71 3I4 FRTEXPA1D71E35NE 20061211002072006121100207NE 2006 12 11 CA061006015 220060920G7261 ENGINE CESSNA560 560XL 2076702CE PWA 545 PW545A NE LEAKING W E ENGINE SHUTDOWN KJ FLUID LOSS WARNING INDICATION CRCRUISE 1 CA DB0238 (CAN) IN CRUISE, ENGINE OIL PRESSURE WAS SEEN TO DECREASE AND THE LOW OIL PRESSURE WARNING ACTIVATED. THE ENGINE WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED EXTERNAL OIL LEAKAGE. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061006015) 2L72 4F4 FRTA22CE E00059EN 20061211002082006121100208EA 2006 12 11 CA061006016 220060615G7210 PLANETARY GEAR BEECH 1900 1900C 1154161CE PWA PT6 PT6A65B 52043EA HARTZLHCB4M HCB4MP3 GL RGB WORN W E ENGINE SHUTDOWN RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CLCLIMB 1 CA (CAN) DURING CLIMB, ENGINE POWER FLUCTUATED ACCOMPANIED BY AN INCREASE IN ITT TEMPERATURE AND LOW OIL PRESSURE. THE ENGINE WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INVESTIGATION REVEALED FIRST STAGE PLANETARY GEAR DISTRESS. (TC NR 20061006016) 2L72 4T4 TRTA24CE E4EA 6 CP56GL 20061211002092006121100209NE 2006 12 11 CA061006017 220060909G7261 ENGINE BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE HARTZLHCE4A HCE4A3I NE LEAKING W E ENGINE SHUTDOWN KJ FLUID LOSS WARNING INDICATION CRCRUISE 1 CA PS0145 (CAN) IN FLIGHT THE ENGINE LOST OIL PRESSURE. THE ENGINE WAS SHUTDOWN IN FLIGHT AND THE AIRCRAFT DIVERTED TO POINT-OF-DEPARTURE. POST-FLIGHT INSPECTION REVEALED A LOW ENGINE OIL LEVEL AND NOISES FROM THE ENGINE POWER SECTION ON ROTATION. MFG WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061006017) 2L72 4T4 TRTA24CE E26NE 5 CP10NE 20061211002102006121100210NE 2006 12 11 CA061006018 220060927G7200 ENGINE CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE FIRE W D RETURN TO BLOCK AJ FLAME/FIRE WARNING INDICATION TXTAXI/GRND HDL 1 CA (CAN) ON TAXI FOLLOWING LANDING, FLAMES WERE SEEN COMING FROM THE ENGINE EXHAUST. MFG WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061006018) 1H71 3T3 T A37CE E4EA 20061211002112006121100211NE 2006 12 11 CA061006019 220060927G7321 BEARING CAGE CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE FUEL CONTROL FRACTURED W O OTHER RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 1 CA C65140 (CAN) ENGINE TORQUE WAS SEEN TO FLUCTUATE IN CRUISE, REDUCING TO ZERO UNCOMMANDED DURING DESCENT. POWER WAS RECOVERED USING THE FUEL CONTROL MANUAL OVER-RIDE SYSTEM. ON A SUBSEQUENT START THE ENGINE ACCELERATED UNCOMMANDED. SUBSEQUENT INSPECTION REVEALED A PRE-SB1561 FCU BEARING CAGE FRACTURE. (TC NR 20061006019) 1H71 3T3 T A37CE E4EA 20061211002122006121100212EA 2006 12 11 CA061006020 220060925G7200 ENGINE SOCATATBM TBM700 8682000EU PWA PT6 PT6A64 EA SEIZED W E ENGINE SHUTDOWN J WARNING INDICATION CRCRUISE 1 CA 111106 (CAN) ENGINE OIL TEMPERATURE WAS SEEN TO INCREASE IN FLIGHT ACCOMPANIED BY A LOSS OF OIL PRESSURE. THE ENGINE WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED OIL IN THE ENGINE DRAINS AND SEIZURE OF THE POWER SECTION. MFG WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061006020) 1L71 3T4 TRTA60EU E4EA 20061211002132006121100213SW 2006 12 11 CA061006021 120061004G6320 SHAFT BELL 206040004101BELL 206 206L 1181522SW TRANSMISSION FAILED W K NONE O OTHER ININSP/MAINT 1 CA 4049 4049 BMC00615 (CAN) EXCESSIVE CORROSION ON SHAFT. (TC NR 20061006021) 1G71 3U H2SW 20061211002142006121100214CE 2006 12 11 CA061010001 120061003G57120513006142 BULKHEAD CESSNA185 A185F 2072821CE CONT O520 IO520D 17032SO HARTZLHCC3Y HCC3YF1 GL DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA 3535 (CAN) AT INSPECTION, SMOKING FASTENERS AT THE LT WING AFT FITTING WERE FOUND. FASTENERS WERE REPLACED AS REQUIRED. (TC NR 20061010001) 1H71 3O3 O 3A24 E5CE 5 CP25EA 20061211002152006121100215EU 2006 12 11 CA061010002 120061010G32505325012044 BEARING PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL MLG FORK TWISTED W O OTHER E VIBRATION/BUFFET LDLANDING 1 CA (CAN) AFTER LANDING, CREW REPORTED TO MAINTENANCE THAT THEY HAD A HARD SHIMMY IN THE RUDDER PEDALS. UPON INSPECTION WE FOUND THE NOSE STEERING BRACKETS BENT AND THE SPRING STRUT UNABLE TO MOVE. THE STEERING STRUT CONNECTED TO THE STEERING HAD FAILED CAUSING THE FORK BEARING TO TWIST. THE BENT BRACKET WAS REPLACED AND THE SPRING STRUT WAS SERVICED. THE SYSTEM WAS FUNCTION CHECKED AND THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20061010002) 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20061211002162006121100216CE 2006 12 11 CA061010003 120061010G304026106731 LINE CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE MCAULY3AF34C3GFR34C703 GL DE ICE CHAFED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) WIRE BUNDLE SECURED INCORRECTLY LEADING TO CHAFING ON/THRU PNEUMATIC DEICE AIR SUPPLY LINES. DURING THE INITIAL COMPLETION OF THE DEICE SYSTEM TEST AND SERVICE IT WAS FOUND THAT THE WIRING BUNDLE FOR THE DEICE SOLENOIDS AND PRESSURE SWITCHES HAD BEEN SECURED IN A POSITION WHICH ALLOWED THEM TO CONTACT SUPPLY LINE P/N 261067-31, WEARING A HOLE IN THE LINE AND DAMAGING SEVERAL WIRES. DEICE PIPES P/N 2601067-31 AND -32 WERE REPLACED. WIRING WAS REPAIRED, REROUTED AND PROTECTED TO PREVENT FURTHER CONTACT WITH DEICE PIPES. THE AIRCRAFT WAS RETURNED TO SERVICE. OTHER AIRCRAFT IN THE FLEET WERE INSPECTED WITH NO FAULTS FOUND. (TC NR 20061010003) 1H71 3T3 T A37CE E4EA 5 CP60GL 20061211002172006121100217NM 2006 12 11 CA061010004 120060927G5512184T10071 SKIN BOEING BOEING767 767233 1385113NM PWA JT9 JT9D7R4D 52054NE HORIZONTAL STAB DELAMINATED W K NONE O OTHER ININSP/MAINT 1 CA 73006 (CAN) LT HORIZONTAL STAB LEADING EDGE PANEL 332CL INNER SKIN COMPLETELY DELAMINATED. DELAMINATED SKIN WEARING INTO VERTICAL STIFFENERS LOCATED ALONG FRONT SPAR. (TC NR 20061010004) 2L72 4F4 FRTA1NM E3NE 20061211002182006121100218EA 2006 12 11 CA061010005 120061009G2750 FLAP SYSTEM CNDAIRCL601 CL6012A12 1900303EA GE CF34 CF343A 30015NE TE FLAPS MALFUNCTIONED W A UNSCHED LANDING F FLT CONT AFFECTED CLCLIMB 1 CA (CAN) FLAP FAIL BETWEEN 20 DEGREES TO 0 DEGREE DURING RETRACTION OF THE FLAPS AT TAKEOFF , FLAPS RESET ON GROUND IAW OPERATING MANUAL NR 1 ABNORMAL PROCEDURE SECTION 10 P3-4. A/C RETURN TO SERVICE. NO SNAG. FLAP FAIL BETWEEN 20 DEGREES TO 0 DEGREE DURING RETRACTION OF THE FLAPS AT TAKEOFF, FLAPS RESET ON GROUND IAW OPERATING MANUAL NR 1 ABNORMAL PROCEDURE SECTION 10 P3-4. A/C RETURN TO SERVICE. NO SNAG. (TC NR 20061010005) 2L72 4F4 FRTA21AE E15NE 20061211002192006121100219NE 2006 12 11 CA061010006 220060913G7310305262701 MANIFOLD CESSNA500 560CESSNA 2076750CE PWA 530 PW535A NE FUEL SYSTEM FAILED W E ENGINE SHUTDOWN KJ FLUID LOSS WARNING INDICATION DEDESCENT 1 CA 2117 DC0045 (CAN) THE PILOTS HEARD A LOUD NOISE FOLLOWED BY A MOMENTARY FIRE WARNING LIGHT. THE PILOTS SHUT THE ENGINE DOWN AND RETURNED TO BASE. AFTER LANDING THE COWLING FOR THE RT ENGINE WAS FOUND TO BE MISSING THE ENGINE DAMAGED BY FIRE AND THE TAIL DAMAGED. (TC NR 20061010006) 2L72 4F4 FRTA22CE E00053EN 20061211002202006121100220GL 2006 12 11 CA061010007 120061010G5511C2TP1A SPAR DHAV DHAV DHC2 DHC2MKI 2801830GL PWA R985 R985AN14B 52008NE HAMSTD2D 2D30 NE HORIZONTAL STAB CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 3180 SA387 (CAN) DURING THE CF-91-42 INSPECTION THE FORWARD SPAR WAS FOUND CRACKED AT THE TOP OF THE TOP ATTACH HOLE FOR THE FORWARD ATTACH BRACKETS PN C2TP159/160. (TC NR 20061010007) 1H71 3R3 RRCA806 5E1 5 CP206 20061211002212006121100221WP 2006 12 11 CA061011001 220060829G720031030351 BEARING MTSBSIMU2 MU2B60 5780460CE GARRTTTPE331TPE33110 01514WP HARTZLHCB4T HCB4TN5 GL ENGINE FAILED W EA ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 CA 5858 P38328C (CAN) AN IN-FLIGHT SHUTDOWN WAS CARRIED OUT WHEN THE ENGINE STARTED TO SURGE AND THE NEGATIVE TORQUE SYSTEM (NTS) PULSE. UPON DISASSEMBLY AT AN ENGINE REPAIR FACILITY, IT WAS NOTED THAT THE CAUSE WAS PREMATURE WEAR AND SUBSEQUENT FAILURE OF THE DUAL P/N: 3103035-1 BEARINGS. FAILURE OF THIS BEARING SET CAUSED LOSS OF ENGAGEMENT BETWEEN THE SPUR GEAR P/N: 896804-2 AND THE MATING GEAR IN THE TORQUE SENSOR. THE INTEGRITY OF THE FCU DRIVE TRAIN WAS LOST AND THE ENGINE FAILED WHEN THE FUEL CONTROL STOPPED BEING DRIVEN. THE ENGINE IS BEING OVERHAULED AT THIS TIME. IT IS TO BE NOTED THAT AN OIL SAMPLE WAS TAKEN 9.7 HOURS PRIOR TO THE FAILURE. THE SAMPLE CAME BACK (INSPECT THIS ENGINE IMMEDIATELY) ONE WEEK AFTER THE EN1H72 3T4 TRTA10SW E4WE 6 CP40EA 20061211002222006121100222SO 2006 12 11 CA061011002 120060830G55436345703 CONNECTOR PIPER PIPER PA28 PA28180 7102808SO LYC O360 O360A4A 41514EA SNSNCH76E 76EM8S5 EA RUDDER TRIM ARM BROKEN W D RETURN TO BLOCK F FLT CONT AFFECTED CLCLIMB 1 CA 3675 (CAN) WHEN MANUAL RUDDER TRIM WAS APPLIED IN CLIMB THERE WAS NO RESPONSE. SUBSEQUENT INSPECTION FOUND THAT THE ARM THAT CONNECTS THE TRIM ACTUATOR TO THE RUDDER CONTROL ASSEMBLY HAD BROKEN OFF THE ASSEMBLY AT THE EDGE OF THE WELD. THE COMPLETE RUDDER TRIM ARM ASSEMBLY WAS REMOVED AND REPLACED WITH A NEW UNIT SUPPLIED FROM MFG. METAL FATIGUE IS SUSPECTED. (TC NR 20061011002) 1L71 3O3 O 2A13 E286 5 NP4EA 20061211002232006121100223EA 2006 12 11 CA061011003 220060927G72004708849004 CONTROLLER PIPER PA31 PA31 7103102SO LYC O540 TIO540A2C 41532EA HARTZLHCE3Y HCE3YR2A GL LT ENGINE DEFECTIVE W EA ENGINE SHUTDOWN UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CRCRUISE 1 CA 686 (CAN) DURING A FLIGHT, THERE WAS A LOSS OF LT ENGINE OIL PRESSURE. THE AFFECTED ENGINE WAS SHUTDOWN AND AN UNSCHEDULED LANDING ACCOMPLISHED. AFTER INVESTIGATION, THE DENSITY CONTROLLER WAS FOUND DEFECTIVE. THE SEAL WAS RUPTURED ON THE (INTAKE) SIDE AND OIL WAS LEAKING INTO THE ENGINE AIR INTAKE. (TC NR 20061011003) 1L72 3O3 O A20SO E14EA 5 CP33EA 20061211002242006121100224EU 2006 12 11 CA061011004 120061001G253072067002M OVEN AIRBUS330 A330243 3930330EU RROYCERB211 RB211* 54555NE GALLEY SMOKE W H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 1 CA (CAN) BURNING SMELL WAS NOTICED IN THE FWD GALLEY BY THE FLIGHT ATTENDANT WITH AN ASSOCIATE ECAM SMOKE WARNING OF THE FWD LAVATORY. F/A NOTICED SMELL COMING FROM NR 3 OVEN TIMER. OVEN WAS SWITCHED OFF FOR THE REMAINING OF THE FLIGHT WITH NO FURTHER PROBLEM. AIRCRAFT WAS INSPECTED AT THE ARRIVAL STATION AND THE OVEN WAS DEACTIVATED. OVEN WAS REPLACED ON ARRIVAL AT MAIN BASE. DURING SHOP INSPECTION THE OVEN OPERATION WAS NORMAL BUT A SMALL PIECE OF MELTED PLASTIC WAS FOUND AT THE FWD BOTTOM CORNER OF THE OVEN. OVEN WAS TESTED AND RETURNED TO SERVICE. (TC NR 20061011004) 2L72 4F4 FRTA46NM A12EU 20061211002252006121100225EU 2006 12 11 CA061011005 120060929G5300A5247017100200 ACCESS PANEL AIRBUS310 A310300 3930305EU GE CF6 CF680C2* GL FUSELAGE MISSING W O OTHER O OTHER TXTAXI/GRND HDL 1 CA (CAN) UPON AIRCRAFT ARRIVAL, DURING WALK AROUND INSPECTION, FOUND THE FWD CARGO DOOR LOWER FWD ACCESS PANEL, FIN811AR, MISSING. MOUNTING HARDWARE, FASTENERS AND LANYARDS WERE STILL ATTACHED TO THE CARGO DOOR. DOOR WAS INSPECTED AND NO FURTHER DAMAGE WAS NOTICED. AIRCRAFT WAS DISPATCH UNDER CDL. NEW PANEL INSTALLED OCT5/06. (TC NR 20061011005) 2L72 4F4 FRTA35EU E23EA 20061211002512006121100251NM 2006 12 11 CA061011007 120060721G29136617303 PUMP BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17EU NR 2 HYD SYSTEM CRACKED W A UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CRCRUISE 1 CA 1576 K0294 (CAN) DURING CRUISE AT 18000 FT, (NR 2 HYD ISO VLV, NR2 ENG HYD PUMP) AND (ROLL SPLR OB HYD) CAUTION LIGHT WERE ILLUMINATED, AND THEN, NR 2 HYD PRESS DROPPED TO 0 PSI AND QUANTITY ALSO DROPPED TO 0. EMERGENCY LANDING CONDUCTED WITH ALTERNATE LDG EXTENSION. THE AIRCRAFT WAS TOWED TO PARKING SPOT. THE GROUND INSPECTION REVEALED THAT NR 2 EDP WAS CRACKED AND HAD A (1.5 X 1.0 CM) HOLE. METAL DEBRIS WAS FOUND IN ALL FILTERS (PRESS, RETURN AND CASE DRAIN), AND DPI FOR NR 2 CASE DRAIN FILTER WAS POPPED OUT. EDP REPLACED, HYDRAULIC SYSTEM FLUSHED. (TC NR 20061011007) 2H72 4T4 TRTA13NM E00062EN6 CP17BO 20061211002542006121100254NM 2006 12 11 CA061011008 120061004G2611473925 CONTROL UNIT BOEING737 7372L9 1384497NM PWA JT8 JT8D17 52049NE SMOKE DETECTION MALFUNCTIONED W D RETURN TO BLOCK N FALSE WARNING TXTAXI/GRND HDL 1 CA (CAN) ON TAXI FOR DEPARTURE THE CREW OBSERVED A NR 2 CARGO PIT CAUTION INDICATION. THE AIRCRAFT RETURNED TO COMPANY RAMP WHERE MAINTENANACE DETERMINED THE SMOKE DETECTOR SYSTEM CONTROL ELECTRONICS UNIT IN THE NR 2 PIT WAS AT FAULT. THE UNIT WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20061011008) 2L72 4F4 FRTA16WE E2EA 20061211002562006121100256NM 2006 12 11 CA061011009 120061004G324665446604 ACTUATOR BOEING737 737242C 1384478NM PWA JT8 JT8D9A 52048NE MLG BYPASSING W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA (CAN) DURING DEPARTURE THE NOSE LANDING GEAR FAILED TO RETRACT. THE AIRCRAFT RETURNED TO POINT OF DEPARTURE WITHOUT FURTHER INCIDENT. MAINTENANCE FOUND THE NOSE LANDING GEAR GRAVEL DEFLECTOR ACTUATOR WAS BYPASSING. THE UNIT WAS REPLACED AND THE AIRCRAFT REURNED TO SERVICE. THE ACTUATOR REMOVED HAD BEEN REPLACED THE PREVIOUS DAY AND THE VENDOR HAS BEEN CONTACTED TO PROVIDE AN IMMEDIATE TEARDOWN REPORT. (TC NR 20061011009) 2L72 4F4 F A16WE E2EA 20061211002582006121100258SW 2006 12 11 CA061011010 120061004G6310CL422501 CLUTCH BELL 206 206B 1181511SW ALLSN 250C 250C20B 03013GL FREEWHEEL UNIT CRACKED W E ENGINE SHUTDOWN O OTHER TXTAXI/GRND HDL 1 CA 1927 (CAN) 2 SPRAG RETAINER WERE CRACKED, THEREFORE ALLOWING MISALIGNMENT AND CAUSING A NOISE. (TC NR 20061011010) 1G71 3U3 U H2SW E4CE 20061211002622006121100262GL 2006 12 11 CA061011011 320061004G6110M5150021 FITTING HARTZL CESSNA206 U206G 2073356CE CONT O520 IO520F 17032SO HARTZLHCJ3Y PHCJ3YF1 GL PROPELLER OPEN W A UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CLCLIMB 1 CA 1483 FP1078A FP1078A (CAN) PILOT EXPERIENCED EXCESSIVE GREASE LEAKAGE ON WINDSCREEN DURING TAKEOFF AND CLIMB, RETURNED TO MAINTENANCE BASE IMMEDIATELY. ON INSPECTION ONE GREASE FITTING WAS FOUND DEFECTIVE. GREASE FITTING WAS REPLACED. PROP RE-GREASED IAW PROP OWNERS MANUAL, PN115N, CHAP6-6. A/C GROUND RUN + PROP LEAK CHECKED. NO FAULTS FOUND. A/C TEST FLOWN TO ENSURE NO LEAKAGE AT HIGH POWER SETTINGS AND FOR PROPER PROPELLER FUNCTION. CHECKED SERVICEABLE - 100HR PROPELLER INSPECTION AND LUBRICATION WAS C/O PRIOR TO FLIGHT ON OCT.3/06 (TC NR 20061011011) 1H71 3O3 O A4CE E5CE 5 CP36EA 20061211002642006121100264SW 2006 12 11 CA061011012 120061010G6730C4264278 GLAND NUT TACTAIR BELL 206 206L4 1182110SW ALLSN 250C 250C30P 03013GL SERVO ACTUATOR CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 3581 RH4576A (CAN) DURING THE FIRST OVERHAUL OF THREE SERVO ACTUATORS 2 WERE FOUND TO HAVE CRACKS ON THE GLAND THAT RETAINS THE PISTON SEAL. BOTH SERVO ACTUATOR GLAND ASSEMBLIES WERE CRACKED IN THE SAME AREA. (TC NR 20061011012) 1G71 3U3 UNCH2SW E1GL 20061211002662006121100266NE 2006 12 11 CA061011013 220061007G7250597602A TURBINE BLADES SKRSKYS64 S64E 8142604NE PWA JFTD12JFTD12A4A 52047NE ENGINE BROKEN W A UNSCHED LANDING EJ VIBRATION/BUFFET WARNING INDICATION DEDESCENT 1 CA 2947 672488 (CAN) THE AIRCRAFT WAS INVOLVED IN AERIAL LOGGING OPERATIONS, ON A SHORT FINAL APPROACH TO THE LOG LANDING THE AIRCRAFT DEVELOPED A VERY NOTICEABLE HIGH FREQUENCY VIBRATION THAT WAS FELT BY THE FLIGHT CREW THROUGHOUT THE AIRCRAFT INCLUDING THE FLIGHT CONTROLS. THE VIBRATION WAS ALSO ACCOMPANIED BY A VERY LOUD GROWLING NOISE. A SCAN OF THE AIRCRAFT INSTRUMENTS REVEALED NOTHING ABNORMAL. THE PILOT ELECTED TO CONTINUE THE APPROACH TO DROP OFF THE LOAD AT THE LOG LANDING AND THEN MADE A PRECAUTIONARY LANDING AT A NEAR BY LOCATION ON THE BEACH OF THE LAKE. AFTER SHUTDOWN, AN EXTENSIVE INSPECTION OF THE ENTIRE AIRCRAFT CARRIED OUT BY MAINTENANCE PERSONNEL REVEALED A LARGE AMOUNT OF METAL PARTICLES FUSED TO THE INSIDE2G72 4U4 U H4EA E15EA 20061211002682006121100268NE 2006 12 11 CA061011014 220061005G73221D1 FUEL CONTROL SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1D1 NE LEAKING W O OTHER B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 1 CA (CAN) FUEL SMELL WAS REPORTED IN THE CABIN WHEN THE HEATER WAS TURNED ON. FCU WAS REMOVED AND FUEL WAS FOUND IN THE P2 AIR CHAMBER WHEN THE FCU WAS INVERTED. FCU WAS REMOVED AND RETURNED TO MFG FOR REPAIRS. FCU RAN 712.6 HRS SINCE LAST REPAIR. FCU P/N 2915145338508 S/N A969B (TC NR 20061011014) 1G71 3U3 U H9EU E19EU 20061211002692006121100269EU 2006 12 11 CA061012001 120061012G2740200031800 CLUTCH PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL PITCH SERVO CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING A ROUTINE PHASE INSPECTION, THE AREA AROUND THE PITCH SERVO IS INSPECTED. DURING THIS, THE FRICTION PLATE WAS DISCOVERED TO BE CRACKED IN HALF. THE PITCH SERVO CLUTCH WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20061012001) 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20061211002702006121100270 2006 12 11 CA061012002 420060526G3160C19190AB04 DISPLAY BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17EU COCKPIT SHORTED W O OTHER B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 1 CA 1670 (CAN) DURING FLIGHT, THE FLIGHT CREW REPORTED THAT THE COPILOT`S PFD WENT BLANK, THEN CAME BACK ON IN POST MODE (GREEN T) THEN WENT BLANK AGAIN PERMANENTLY, FOLLOWED BY A BURNING ODOR (NO VISIBLE SMOKE OR FLAMES). THE ODOR WAS CARRIED BY THE RECIRC FAN THROUGHOUT THE CABIN AND DETECTED BY THE FLIGHT ATTENDANTS. MECHANICS FOUND EVIDENCE OF SOOT AROUND THE COOLING HOLES OF THE REMOVED PFD. (TC NR 20061012002) 2H72 4T4 TRTA13NM E00062EN6 CP17BO 20061211002712006121100271EA 2006 12 11 CA061012003 120061011G27306229815704 CIRCUIT CARD CNDAIRCL600 CL6002B19 1900309EA ELEVATOR CONTROLFAILED W O OTHER O OTHER CLCLIMB 1 CA (CAN) DURING CLIMB OUT, ENROUTE, CREW EXPERIENCED PITCH TRIM, MACH TRIM AND STAB TRIM CAUTION INDICATIONS. CREW THOUGHT THEY EXPERIENCED FLIGHT CONTROL ISSUES. AFTER SOURCING THE QUICK REFERENCE HANDBOOK, CREW ELECTED TO DIVERT, BEING THE CLOSEST SUITABLE AIRPORT. CREW DID CONTACT MAINTENANCE TO RESET SOME CIRCUIT BREAKERS AND ALSO DID HOLD WEST OF YFC FOR FUEL BURN OFF. CREW DID DECLARE AN EMERGENCY AND DID HAVE EMERGENCY VEHICLES STANDING BY. PASSENGER ANNOUNCEMENT WAS MADE TO THE EFFECT THAT AIRCRAFT WAS HAVING A FLIGHT CONTROL PROBLEM HOWEVER EVERYTHING WAS UNDER CONTROL. PASSENGERS WERE ADVISED TO BRACE FOR LANDING. PASSENGER REACTION WAS NIL. FLIGHT LANDED SAFELY AND PASSENGERS DEPLANED. (TC NR 2006101202L72 4F RTA21EA 20061211002722006121100272NE 2006 12 11 CA061012004 220061012G75103039936 GASKET PWC BEECH 200 200BEECH 1152920CE PWA PT6 PT642A NE HARTZLHCE4N HCE4N3 NE ENGINE CRACKED W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA (CAN) GASKET PN 3007342 AND SUBSEQUENT SUPERCEDURE TO 3039936 ARE THE ONLY GASKETS SPECIFIED FOR USE ON THE CABIN BLEED AIR PORT. THE 3039936 GASKETS ARE MADE OF A FIBER OR OTHER MATERIAL NOT WELL SUITED TO THIS HOT AND HIGH PRESSURE AREA. OTHER ENGINES LIST A METAL GASKET OPTION PN 3029677 AS APPROVED FOR INSTALLATION AT THIS PORT. MFG HAS BEEN NOTIFIED OF THIS ISSUE IN THE -42 IPC. (TC NR 20061012004) 1L72 4T4 T A24CE E4EA 5 CP10NE 20061211002742006121100274NM 2006 12 11 CA061012005 120061008G3260858601 PSEU DHAV DHC8 DHC8301 1386003NM PWA PW120 PW123 NE HAMSTD14SF 14SF15 NE PRXY SENSOR WARNING LIGHT W A UNSCHED LANDING N FALSE WARNING CLCLIMB 1 CA 301899400 (CAN) AFTER TAKEOFF GEAR SELECTED UP , VISUALLY CONFIRMED GEAR WAS UP , INDICATION STILL SHOWED GEAR DOWN AND LOCKED (3 GREEN LIGHTS) , NORMAL GEAR EXTENSION AND AIRCRAFT RETURNED TO DEPARTURE AIRPORT FOR NORMAL LANDING. MAINTENANCE INSPECTION FOUND PSEU INTERNAL HISTORY SHOWING CARD FAULT . PSEU REPLACED. AIRCRAFT RETURNED TO SERVICE. (TC NR 20061012005) 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20061211002752006121100275EU 2006 12 11 CA061013001 120061010G7500690200 DUCT SEAL AEROSPATR42 ATR42300 8680920EU PWA 120 PW120 NE HAMSTD14SF 14SF5 NE BLEED AIR SYS LEAKING W A UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 CA (CAN) ENROUTE THE CREW OBSERVED A BLEED AIR LEAK WARNING. THE AIRCRAFT RETURNED TO POINT OF DEPARTURE AND LANDED WITH NO FURTHER PROBLEM. MAINTENANCE DETERMINED THAT A BLEED AIR SYSTEM DUCT SEAL HAD FAILED. THE AIRCRAFT IS AWAITING PARTS. (TC NR 20061013001) 2H72 4T4 TRTA53EU E20NE 6 CP7NE 20061211002782006121100278EA 2006 12 11 CA061013003 120061011G5730 SKIN DHAV DHC6 DHC6 2802606EA PWA PT6 PT6A27 52043EA LT WING DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) A MAINTENANCE FACILITY RECEIVED THESE RE-LIFED WINGS FROM RW MARTIN. INCOMING INSPECTION REVEALED A LT/RT BUCKLED TOP SKIN AND DAMAGED SHROUD SKINS. THE DAMAGE DOES NOT APPEAR TO BE SHIPPING RELATED. RW MARTIN WERE NOT ABLE TO SEND AN NDT REPORT FOR DELAMINATION OF BONDED UPPER SKINS THEREFORE THE MAINTENANCE FACILITY PROVIDED AN INDEPENDENT NDT SPECIALIST TO INSPECT THE WINGS. THE PICTURES REVEAL WHERE THE SKINS WERE FOUND DELAMINATED (COLORED SPOTS). THE DELAMINATION IS MAINLY ON THE OB SKIN, WITH THE EXCEPTION OF 2 LOCATIONS: RT WING IB OF RIB WS 297.50 AND LT WING IB OF RIB WS 272. (TC NR 20061013003) 1H72 3T4 TRTA9EA E4EA 20061211002792006121100279EA 2006 12 11 CA061013004 120061011G5730 SKIN DHAV DHC6 DHC6 2802606EA PWA PT6 PT6A27 52043EA RT WING DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) A MAINTENANCE FACILITY RECEIVED THESE RE-LIFED WINGS FROM RW MARTIN. INCOMING INSPECTION REVEALED A LT/RT BUCKLED TOP SKIN AND DAMAGED SHROUD SKINS. THE DAMAGE DOES NOT APPEAR TO BE SHIPPING RELATED. RW MARTIN WERE NOT ABLE TO SEND AN NDT REPORT FOR DELAMINATION OF BONDED UPPER SKINS THEREFORE THE MAINTENANCE FACILITY PROVIDED AN INDEPENDENT NDT SPECIALIST TO INSPECT THE WINGS. THE PICTURES REVEAL WHERE THE SKINS WERE FOUND DELAMINATED (COLORED SPOTS). THE DELAMINATION IS MAINLY ON THE OB SKIN, WITH THE EXCEPTION OF 2 LOCATIONS: RT WING IB OF RIB WS 297.50 AND LT WING IB OF RIB WS 272. (TC NR 20061013004) 1H72 3T4 TRTA9EA E4EA 20061211002802006121100280NE 2006 12 11 CA061013005 220061008G7310J1175D0244AA FUEL LINE CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE NR 1 ENGINE LEAKING W D RETURN TO BLOCK KJ FLUID LOSS WARNING INDICATION TXTAXI/GRND HDL 1 CA 1043910439 (CAN) RAMP CREW SERVICING AIRCRAFT REPORTED FUEL LEAKING FROM NR 1 ENGINE ON TAXI OUT. SHUTDOWN NR 1 ENGINE. FUEL DRIPPING FROM LOWER COWL. MAINTENANCE INSPECTION FOUND VARIABLE GUIDE VANE FUEL LINE LEAKING. LINE P/N J1175D0244AA REPLACED. LEAK CHECKED AND AIRCRAFT RETURNED TO SERVICE. NOTE: THIS PART IS NOT TRACKED AS A ROTABLE COMPONENT , TIMES PROVIDED ARE THE ENGINE INSTALLED TIMES . NR 1 ENGINE S/N 873093 , NR 1 ENGINE P/N 6089T11G01 (TC NR 20061013005) 2L72 4F4 FRTA21EA E15NE 20061211003042006121100304EA 2006 12 11 CA061013006 120061011G2750855D100 BPSU CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE INTERNAL MALFUNCTIONED W A UNSCHED LANDING F FLT CONT AFFECTED APAPPROACH 1 CA 4796 4796 (CAN) ON SELECTING FLAPS FOR APPROACH (FLAP FAIL) MESSAGE DISPLAYED. DUE TO WEATHER CONDITION AIRCRAFT PROCEEDED WITH MISSED APPROACH. UNABLE TO RETRACT FLAPS. AIRCRAFT DIVERTED TO NEAREST ALTERNATE AIRPORT WITH IMPROVED WEATHER , WITH FLAPS REMAINING EXTENDED AT 30 DEG. IN-FLIGHT RESET PROCEDURE FOR FLAPS UNSUCCESSFUL. AFTER ARRIVAL AT ALTERNATE AIRPORT FLAP RESET PROCEDURE CARRIED OUT , FLAPS RETRACTED TO 8 DEG AND AIRCRAFT FERRIED TO MAINTENANCE BASE. MAINTENANCE REPLACED LT BRAKE AND POSITION SENSING UNIT. RIGGING AND FUNCTION CHECKS COMPLETED. AIRCRAFT RETURNED TO SERVICE. (TC NR 20061013006) 2L72 4F4 FRTA21EA E15NE 20061211003072006121100307NM 2006 12 11 CA061014001 120061011G215039854021 VALVE BOEING727 727243 138408DNM PWA JT8 JT8D9A 52048NE A/C PACK FAILED W A UNSCHED LANDING O OTHER CLCLIMB 1 CA (CAN) AFTER DEPARTURE, CREW DISCOVERED THAT THE A/C WOULD NOT PRESSURIZE. A/C RETURNED TO BASE WHERE A PACK VALVE WAS FOUND FAILED IN THE CLOSED POSITION. VALVE WAS REPLACED AND A/C RETURNED TO SERVICE. (TC NR 20061014001) 2L73 4F4 FRTA3WE E2EA 20061211003082006121100308NM 2006 12 11 CA061016001 120060821G2497 WIRE DHAV DHC8 DHC8301 1386003NM PWA PW120 PW123 NE HAMSTD14SF 14SF23 NE AC POWER BURNED W K NONE B SMOKE/FUMES/ODORS/SPARKS ININSP/MAINT 1 CA 7115 (CAN) AN OPERATOR EXPERIENCED AN EXTERNAL AC POWER PROBLEM THAT WAS TRACED TO SEVERAL BURNED WIRES AND A BLOWN (F4) FUSE. IT IS DETERMINED THAT THE MOST PROBABLE CAUSE FOR THIS EVENT WAS THE (12 GAUGE) FEEDER CABLES CHAFING TOGETHER ON THE ADJACENT STRUCTURE. (TC NR 20061016001) 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20061205003052006120500305GL 2006 12 5 CA061016002 120061014G321358S9241 STRUT DHAV DHC2 DHC2MKI 2801830GL PWA R985 R985AN14B 52008NE FLOATS CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING 100 HOUR INSPECTION, THE L/H MIDDLE FLOAT STRUT WAS FOUND TO HAVE A 4" STRESS CRACK EXTENDING DOWN THE LEADING EDGE FROM THE TOP OF THE STRUT. THE AIRCRAFT IS OPERATED EXCLUSIVELY ON FLOATS IN A CORROSIVE ENVIRONMENT IN GENERALLY ADVERSE LANDING CONDITIONS. TSN UNKNOWN. (TC# 20061016002) 1H71 3R3 RRCA806 5E1 20061211003102006121100310NE 2006 12 11 CA061016003 220061006G7200M8505237 CLAMP SAAB SF340 SF340A 7850100EU GE CT7TP CT75A2 30030NE ROTOL R389 R3894123F25 NE ENGINE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) ENGINE CONTROL CLAMP FOUND CRACKED ON ENGINE INSPECTION. REFERENCE AIRCRAFT IPC 71-00-02 FIG 15, ITEM NR 6 THE PART WAS NOT IDENTIFIED BY A SPECIFIC PN MARKED ON THE CLAMP. SUSPECT POSSIBLE UNAPPROVED PART PREVIOUSLY INSTALLED. (TC NR 20061016003) 2L72 4T4 TRTA52EU E8NE6 6 CP30NE 20061205003032006120500303GL 2006 12 5 CA061016004 120061014G321358S9242 STRUT DHAV DHC2 DHC2MKI 2801830GL PWA R985 R985AN14B 52008NE FLOAT CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING 100 HOUR INSPECTION THE RT REAR FLOAT STRUT WAS FOUND TO HAVE A 6` STRESS CRACK ORIGINATING AT THE TOP FORWARD SIDE OF THE STRUT. TIME IN SERVICE IS UNKNOWN. TAT 22,057 HOURS. THE AIRCRAFT IS OPERATED EXCLUSIVELY ON FLOATS IN A CORROSIVE ENVIRONMENT AND GENERALLY ADVERSE LANDING CONDITIONS. (TC# 20061016004) 1H71 3R3 RRCA806 5E1 20061211003122006121100312 2006 12 11 CA061016005 420061012G342179266941 GYRO LKHEED382 382G 526414USO ALLSN 501D 501D22A 03006GL HAMSTD54H 54H60117 NE COCKPIT MALFUNCTIONED W A UNSCHED LANDING O OTHER DEDESCENT 1 CA (CAN) DURING DESCENT THE CREW OBSERVED A GYRO FLAG AND THE A/P DISENGAGED. THE COMPASS BEGAN TO OSCILLATE WITH A COMPARATOR FAIL LIGHT INDICATION. THE AIRCRAFT RETURNED TO POINT OF DEPARTURE AND LANDED WITHOUT INCIDENT. MAINTENANCE REPLACED THE NR 1 VG AND THE AIRCRAFT WAS RETURNED TO SERVICE AFTER SATISFACTORY GROUND TEST. (TC NR 20061016005) 2H74 4T4 T A1SO E282 6 CP906 20061211003132006121100313NE 2006 12 11 CA061016006 220061011G7230 CASE DHAV DHC8 DHC8103 1386005NM PWA PW121 PW121 52124NE HAMSTD14SF 14SF7 NE GAS GENERATOR CRACKED W A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CLCLIMB 1 CA 2318714478 120775 (CAN) SHORTLY AFTER TAKE-OFF AT 500FT AGL THE CREW REDUCED POWER TO CLIMB POWER AND REALIZED THAT THE LT ENGINE ITT ROSE RAPIDLY TO APPROXIMATELY 850-900 DEGREES CELSIUS. THE OVER-TEMPERATURE LIGHT ILLUMINATED AND THE ENGINE OIL TEMPERATURE WAS ALSO RISING. THE ENGINE POWER WAS REDUCED TO STAY WITHIN LIMITS AND THE AIRCRAFT TURNED BACK TO LAND SAFELY WITHOUT INCIDENT. MAINTENANCE FOUND THAT THE ENGINE HAD DEVELOPED 2 SUBSTANTIAL CRACKS ON THE GAS-GENERATOR CASE. THE CRACKS MEASURED APPROXIMATELY 3.5 INCHES IN LENGTH EACH AND WERE LOCATED AT APPROXIMATELY THE 11:30 AND 10 O’CLOCK POSITIONS. IT SHOULD ALSO BE NOTED THAT THIS PORTION OF THE GAS GENERATOR CASE IS NORMALLY COVERED WITH AN INSULATION BLANKET. THE E2H72 4T4 TRTA13NM E20NE 6 CP7NE 20061205003042006120500304CE 2006 12 5 CA061016007 120061014G553404310093 ATTACH BRACKET CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA VERTICAL STAB CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 21277 (CAN) ONE OF THE TWO VERTICAL TAIL ATTACH BRACKETS WAS DISCOVERED CRACKED APPROXIMATELY 90% OF IT’S LENGTH DURING A SCHEDULED INSPECTION. THE CRACK LOCATION IS IN THE RADIUS WHERE THE VERTICAL LEG INTERSECTS THE HORIZONTAL LEG. THERE IS A SERVICE LETTER WHICH DEALS WITH THIS, HOWEVER IT DOESN’T APPLY TO THIS SERIAL NUMBER AIRCRAFT. WE ARE REPLACING THE TWO ON THIS AIRCRAFT AS WELL AS ON THE OTHER C152 IN THE FLEET. (TC# 20061016007) 1H71 3O3 ONT3A19 E223 20070129003252007012900325EU 2007 1 29 CA061017004 120061016G29109740926112 RELAY PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL HYDRAULIC SYS BURNED W K NONE J WARNING INDICATION LDLANDING 1 CA 5042 (CAN) FOLLOWING LANDING OF AIRCRAFT AMBER (HYD). ANNUNCIATOR ILLUMINATED. INSPECTION OF HYDRAULIC MOTOR POWER RELAY MAIN CONTACTS INDICATED THE CONTACTS WERE SEVERLY BURNED. NEW RELAY INSTALLED ,FUNCTION TEST OF LANDING GEAR SYSTEM PERFORMED SATISFACTORY. (TC NR 20061017004) 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20061205002932006120500293SO 2006 12 5 CA061017005 120061016G3260 DOWNLOCK SWITCH LKHEED382 382G 526414USO ALLSN 501D 501D22A 03006GL HAMSTD54H 54H60117 NE MLG OUT OF ADJUST W A UNSCHED LANDING N FALSE WARNING CLCLIMB 1 CA (CAN) DURING DEPARTURE THE NOSE LANDING GEAR FAILED TO RETRACT ON TAKE-OFF. THE AIRCRAFT RETURNED TO POINT OF DEPARTURE WITHOUT FURTHER PROBLEM. MAINTENANCE ADJUSTED THE DOWNLOCK SWITCH AND CARRIED OUT A GEAR SWING BEFORE THE AIRCRAFT WAS RETURNED TO SERVICE. (TC# 20061017005) 2H74 4T4 T A1SO E282 6 CP906 20061205003062006120500306 2006 12 5 CA061017006 420061013G83006014T81G26 GEARBOX CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE LT ENGINE FAILED W A UNSCHED LANDING Y ENGINE STOPPAGE DEDESCENT 1 CA (CAN) LEFT ENGINE IN-FLIGHT SHUTDOWN DUE TO ACCESORIES GEARBOX (AGB)FAILURE. AGB BORESCOPE INSPECTION REVEALED A BROKEN GEAR. AIRFRAME HOURS=25499:54. CYCLES=21133. (TC# 20061017006) 2L72 4F4 FRTA21EA E15NE 20070129003262007012900326 2007 1 29 CA061017007 420061017G611304500391791 BULKHEAD CESSNA150 150H 2071818CE CONT O200 O200A 17020SO MCAULY1A101 1A101DCM GL PROPELLER CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 3509 (CAN) ON PILOT WALK AROUND THE SPINNER ASSY WAS NOTED TO BE LOOSE. UPON INSPECTION IT WAS OBSERVED THAT THE FWD SPINNER BULKHEAD WAS CRACKED. THIS WAS MOST LIKELY CAUSED BY PILOTS PUSHING ON THE SPINNER WHEN GROUND HANDLING THE AIRCRAFT. (TC NR 20061017007) 1H71 3O3 O 3A19 E252 5 NP918 20061205003072006120500307CE 2006 12 5 CA061018001 120061013G78001754001 EXHAUST RISER CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA MCAULY1C160 1C160DTM GL NR 3 CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 150 (CAN) THE (EXHAUST) FLANGE WAS CRACKED THROUGH AND INTO THE UPPER END OF THE (EXHAUST) PIPE ITSELF, WITH THE CRACK TRAVELLING ALMOST HALFWAY AROUND THE PIPE. SUBMITTER REGULARLY FINDS THESE RISERS CRACKED AND SUSPECTS THAT A SHARP/ROUGH EDGE ON THE FLANGE CONTRIBUTES TO ITS FAILURE. THOROUGH INSPECTION OF THIS TYPE OF EXHAUST SYSTEM AT EVERY 50-HOUR INTERVAL IS RECOMMENDED BY THE SUBMITTER. EXHAUST STAINING AROUND THE TOP OF THE PIPE IS USUALLY APPARENT. PRESSURE-TESTING OF THE WHOLE SYSTEM WHILE CARRYING OUT A.D. CF90-03R2 WILL ALSO FIND THESE DEFECTS. (TC# 20061018001) 1H71 3O3 ONT3A12 E274 5 NP910 20061205003022006120500302SW 2006 12 5 CA061018002 120061014G6210407015001117 BLADE BELL 407 407 1182206SW ALLSN 250C 250C47B GL MAIN ROTOR DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA 3940 (CAN) UPON POST FLIGHT INSPECTION, A TEAR AND PROTRUTION OF THE LOWER SKIN, JUST AFT OF THE LEADING EDGE OUTBOARD ERROSION STRIP WAS DISCOVERED APPROXIMATELY 4 INCHES INBOARD FROM THE TIP OF THE BLADE AT STATION 206. (TC# 20061018002) 1G71 3U3 UO H2SW E1GL 20061211003142006121100314NE 2006 12 11 CA061018003 120061010G6220641026005104 ROD SKRSKY SKRSKYS64 S64E 8142604NE PWA JFTD12JFTD12A4A 52047NE DAMPER PISTON BROKEN W O OTHER O OTHER NRNOT REPORTED 1 CA 3464 827 106 (CAN) THE AIRCRAFT WAS INVOLVED IN AERIAL LOGGING OPERATIONS AND HAD JUST SHUT DOWN FOR IT’S MIDDAY MAINTENANCE. THIS MAINTENANCE INVOLVES A FLUID LEVELS CHECK, SERVICING AND INSPECTION OF CRITICAL AREAS ON THE AIRCRAFT. ON THIS PARTICULAR DAY THE MAIN ROTOR DAMPERS WERE BEING CHECKED FOR PROPER OPERATION AND ASSOCIATED LINKAGE WEAR. THIS IS ACCOMPLISHED BY SWEEPING THE CORRESPONDING MAIN ROTOR BLADE BACK AND FORTH AT THE TIP END TO EXTEND AND RETRACT THE DAMPER PISTON AND ROD. WHEN THE AME CAME TO CHECK THE SUBJECT DAMPER HE DISCOVERED THE BLADE MOVED BACK AND FORTH FREELY WITH NO RESISTANCE FROM THE DAMPER. A CLOSER INSPECTION OF THE DAMPER BY A SECOND AME WHILE THE BLADE WAS BEING MOVED REVEALED THE DAMPER P2G72 4U4 U H4EA E15EA 20061211003162006121100316EA 2006 12 11 CA061018004 220061007G8530RBLW12967EC CYLINDER HEAD RKWELL700 700 7630520SW LYC O540 TIO540R2AD 41532EA HARTZLHCE3Y HCE3YR2A GL ENGINE BROKEN W EA ENGINE SHUTDOWN UNSCHED LANDING RK PARTIAL RPM/PWR LOSS FLUID LOSS CLCLIMB 1 CA 428 RL352361A (CAN) AFTER CLIMB OUT THE LT ENGINE LOST POWER AND A LOUD BANG WAS HEARD. THE ENGINE (PROPELLER) WAS FEATHERED AND THE AIRCRAFT RETURNED TO THE AIRPORT WITHOUT INCIDENT. UPON INSPECTION IT WAS FOUND THAT THE NR 2 CYLINDER ASSEMBLY WAS CRACKED/BROKEN BETWEEN THE HEAD AND BARREL. THIS ALLOWED THE HEAD TO MISALIGN AND ALLOWED THE PUSH ROD TUBES TO LEAK OIL ONTO THE TOP COWL. THE CYLINDER WAS REMOVED AND AN OVERHAUL ASSEMBLY INSTALLED. THE ADJACENT CYLINDER WAS INSPECTED AND FOUND SERVICEABLE, OIL AND SCREWS WERE INSPECTED SERVICEABLE. THE ENGINE WAS GROUND RUN AND CHECKED SERVICEABLE. (TC NR 20061018004) 1L72 3O3 O A12SW E14EA 5 CP33EA 20061211003182006121100318NM 2006 12 11 CA061018005 120060919G3213MS2877A344 SEAL BOEING737 737* NM PWA JT8 JT8D17 52049NE STRUT TORN W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA 1732 (CAN) ON CLIMB OUT, NOSE GEAR RED WARNING LIGHT STAYED ON; GEAR CYCLED TWICE, NIL CURE. AIRCRAFT PROCEEDED TO AIRPORT, LANDING WAS NORMAL. ON GROUND, NOSE GEAR SERVICED, SUBSEQUENT TAKEOFF NORMAL. ON RETURN TO BASE, ONE SEAL FOUND TORN, ALL SEALS REPLACED, FULL NOSE GEAR SERVICING CARRIED OUT. (TC NR 20061018005) 2L72 4F4 FRTA16WE E2EA 20061211003192006121100319 2006 12 11 CA061018006 120061006G5711 SPAR ARONCA7A LSA7AC CONT A65 A658 17003SO SNSNCH72C 72CK EA LT WING CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 2452 (CAN) CRACKING AT REINFORCING PLATES. PREVIOUS DAMAGE AT TIP. HAD PREVIOUS REPAIR. REPLACED BOTH FRONT AND REAR SPARS. (TC NR 20061018006) 1H71 3O3 O A759 E205 5 NP9045 20070108001872007010800187SO 2007 1 8 CA061018007 220061011G8520 PISTON AMTR CUBY CUBYACROTNER05624DPGL CONT O200 O200* 17020SO NR1 CYLINDER CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 1100 (CAN) ENGINE WAS TORN DOWN FOR INSPECTION DUE TO SMALL AMOUNT NON FERROS METAL IN FILTER. ENGINE TIME 2,707 HOUR. FRONT BEARING SLIGHT WEAR AND FLAKING (NORMAL FOR HIGH TIME ENGINE). NR 1 PISTON SKIRT CRACKED AT 1,100 HOURS. NOTE: THIS IS THE 4TH PISTON THAT I HAVE SEEN. RANGING FROM 1,100 HOURS TO 2,100 HOURS. ACTION ON ENGINE - PISTON REPLACED NEW MAIN BEARINGS INSTALLED. (TC NR 20061018007) 1H71 3O3 ONCEXPA1H71E252 20070613001222007061300122 2007 6 13 CA061018008 420061011G6113SB10401 SPINNER FRCHLDSA227 SA227CC 3377522SW GARRTTTPE331TPE33111U 01514WP MCAULY4HFR344HFR34C652 NE LT PROPELLER DENTED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) GOOSE HIT THE OB SIDE OF THE LT PROP SPINNER. DAMAGE WAS MINIMAL TO THE SPINNER WHERE THE BLADE CUT OUT IS. THERE WAS ALSO MINIMAL DAMAGE TO THE CHIN COWL PN 27-63026-053. DAMAGE ON BOTH UNITS WERE COVERED BY THE SRM LIMITS OF .3750 DEGREES 4. (TC NR 20061018008) 2L72 4T4 TRTA18SW E4WE 6 C3PNE 20070507000952007050700095SW 2007 5 7 CA061018009 120061005G29102781032005 LINE FRCHLDSA227 SA227CC 3377522SW GARRTTTPE331TPE33111U 01514WP MCAULY4HFR344HFR34C652 NE HYD SYSTEM CRACKED W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) HYD FLUID WAS DISCOVERED FROM GEAR UP LINE WHEN SYSTEM PRESSURE WAS APPLIED. LINE WOULD ONLY LEAK AFTER 1200 PSI WAS APPLIED, SYSTEM PRESSURE WAS 2000 PSI. PIN HOLE WAS IN RADIUS OF LINE. (TC NR 20061018009) 2L72 4T4 TRTA18SW E4WE 6 C3PNE 20070507000962007050700096SW 2007 5 7 CA061018010 120060920G2913PV304426 PUMP FRCHLDSA227 SA227CC 3377522SW GARRTTTPE331TPE33111U 01514WP MCAULY4HFR344HFR34C652 NE HYD SYSTEM CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) UPON ROUTINE SPLINE REPLACEMENT IT WAS NOTICED THAT A CASTING DEFECT HAD BEEN FOUND AT THE BASE OF THE PUMP BELOW A FITTING. THE NATURE OF THE CASTING DEFECT IS WHAT IS TERMED AS A COLD SHUNT. A FLOURSECENT PENETRANT INSPECTION WAS CARRIED OUT AND THE COLD SHUNT WAS NOT FUSED CREATING A FATIQUE CRACK SINCE THE PUMP HAD BEEN IN SERVICE FOR SOME TIME. PUMP WAS REJECTED. (TC NR 20061018010) 2L72 4T4 TRTA18SW E4WE 6 C3PNE 20070808001172007080800117SW 2007 8 8 CA061018011 120061018G76033219012123 CABLE SWRNGNSA227 SA227AC 8780603SW GARRTTTPE331TPE33111U 01514WP MCAULY4HFR344HFR34C652 NE POWER LEVER BROKEN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) RT POWER LEVER CABLE WAS DISCOVERED BROKEN 1 FOOT FROM POWER LEVER ATTACH POINT (TC NR 20061018011). 2L72 4T4 TRTA8SW E4WE 6 C3PNE 20070808001182007080800118SW 2007 8 8 CA061018012 120061015G561092063H0421 WINDSHIELD SWRNGNSA227 SA227AC 8780603SW GARRTTTPE331TPE33111U 01514WP MCAULY4HFR344HFR34C652 NE COCKPIT FAILED W O OTHER O OTHER CRCRUISE 1 CA (CAN) AIRCRAFT WAS IN CRUISE FLIGHT WHEN THE RT WINDSHIELD SHATTERED, OUTER PANE. THE ELT WENT OFF AND HAD TO BE RESET AT THE SAME TIME. REPORTS OF ARCING ON INSIDE OF WINDSHIELD FROM (P) STATIC BEFORE OUTER PANE CRACKED. (TC NR 20061018012) 2L72 4T4 TRTA8SW E4WE 6 C3PNE 20061205002602006120500260NM 2006 12 5 CA061018013 120061018G5315147A550412 FLOORBEAM BOEING737 737790 13844CNNM BS 947 CORRODED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) FLOORBEAM CORRODED AT BS 947. 2L72 4F RTA16WE 20061211003202006121100320 2006 12 11 CA061018014 420060915G6122 GOVERNOR CESSNA206 U206G 2073356CE CONT O520 IO520F 17032SO MCAULYD3A34 D3A34C404 GL ENGINE MALFUNCTIONED W A UNSCHED LANDING XJ ENGINE FLAMEOUT WARNING INDICATION CRCRUISE 1 CA 1686209F (CAN) PROPELLER GOVERNOR FAILED IN FLIGHT CAUSING SEVERE OVERSPEED OF ENGINE. UPON LANDING, THE ENGINE OIL SCREEN WAS FOUND TO BE METAL CONTAMINATED. PROPELLER GOVERNOR WAS REMOVED AND METAL WAS DISCOVERED AT GOVERNOR PAD. NO SCREEN WAS PRESENT BETWEEN GOVERNOR AND ENGINE. ENGINE DISMANTLED AND OIL TRANSFER COLLAR FOUND SEVERELY WORN, THE OIL PUMP WAS DAMAGED BEYOND REPAIR, THE CRANKSHAFT WAS WORN IN THE TRANSFER COLLAR AREA AND THE CRANKCASE WAS BADLY FRETTED. ONE CAMSHAFT LOBE AND ONE LIFTER FACE WERE ALSO SEVERELY WORN. INSPECTION WAS LIMITED TO VISUAL AND MEASURING. NO NON-DESTRUCTIVE TESTING WAS CARRIED OUT. (TC NR 20061018014) 1H71 3O3 O A4CE E5CE 5 CP47GL 20061205003132006120500313CE 2006 12 5 CA061019002 120061013G53111014300263 FRAME BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA BS 207 CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 16144 (CAN) SPECIAL INSPECTION 50 WAS COMPLETED AS PER RAYTHEON MM 5-20-05, WHICH INVOLVES THE FOLLOWING: FRAME WEB FS 179 THROUGH FS 271 INSPECT THE FRAME WEBS FOR CRACKS FROM THE LIGHTNING HOLES AND STRINGER CUTOUTS. THE FRAMES SHOULD BE INSPECTED FROM THE LOWER CENTERLINE TO STRINGER 4. EXAMINE THE CROSSTIES CLOSELY AT STRINGER 7 POSITION. THE INSPECTION INTERVAL IS INITIALLY 10,000 CYCLES AND AT 1000 CYCLES THERE AFTER. DURING THIS INSPECTION THE RT FUSELAGE FRAME 207.0 (P/N:101-430026-3) WAS FOUND CRACKED IN TWO LOCATIONS. THE FIRST CRACK WAS LOCATED AT THE UPPER EDGE OF THE FRAME LIGHTNING HOLE MIDPOINT OF RT STRINGER 9 AND RT STRINGER 10 (WL 103.0). THE CRACK MEASURED .900 IN LENGTH. THE SECOND CRACK WAS 1L72 4T4 T A24CE E4EA 20070129003272007012900327CE 2007 1 29 CA061019003 120061018G3220AN517A BOLT CESSNA310 310R 2074245CE CONT O520 IO520M 17032SO MCAULY3AF32C3AF32C* GL NLG SHEARED W O OTHER O OTHER LDLANDING 1 CA (CAN) ON LANDING THE MAIN GEAR CAME DOWN AND LOCKED BUT THE NOSE GEAR STAYED UNLOCKED. THE AN5-17A BOLT CONNECTING THE DRAG LINK ASSY TO THE DRAG BRACE TRUSS ASSY. HAD FAILED CAUSING THE NOSE GEAR STRUT ASSY TO JAM AGAINST THE TRUSS ASSY HOLDING THE GEAR FROM COLLAPSING ON LANDING. (TC NR 20061019003) 1L72 3O3 O 3A10 E5CE 5 CP22EA 20061211003212006121100321SW 2006 12 11 CA061019004 120061003G2844 INDICATOR BELL 206 206L 1181522SW ALLSN 25OC 250C20R GL FUEL PRESSURE MALFUNCTIONED W K NONE O OTHER ININSP/MAINT 1 CA 210D (CAN) FUEL PRESSURE OVER-READING. PEGS AT 30 PSI WITH BOTH PUMPS AND GENERATOR ON. REMOVED FOR REPAIR AT INSTRUMENT SHOP. (TC NR 20061019004) 1G71 3U3 U H2SW E4CE 20061211003232006121100323SW 2006 12 11 CA061019005 120061003G77122060751853 INDICATOR BELL 206 206L 1181522SW ALLSN 25OC 250C20R GL TORQUE LEAKING W K NONE O OTHER ININSP/MAINT 1 CA (CAN) OIL IN GAUGE GLASS. REMOVED FOR REPAIR AT INSTRUMENT SHOP. (TC NR 20061019005) 1G71 3U3 U H2SW E4CE 20061205002682006120500268EA 2006 12 5 CA061019007 120061018G61238190026 PRESSURE SWITCH DHAV DHC6 DHC6300 2802606EA PWA PT6 PT6A27 52043EA HARTZLHCB3T HCB3TN3 GL AUTOFEATHER SYS FAILED W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA 1439 (CAN) AFTER TAKE OFF WHILE REDUCING POWER FROM TAKE OFF POWER TO CLIMB, THE L/H PROP AUTOFEATHERED. AUTO FEATHER CIRCUIT BREAKER PULLED AND PROP RETURNED TO NORMAL. MAINTENANCE CONFIRMED SNAG AND REPLACED THE AUTOFEATHER PRESSURE SWITCH, CARRIED OUT GROUND RUNS AND RETURNED THE AIRCRFAT TO SERVICE. (TC# 20061019007) 1H72 3T4 TRTA9EA E4EA 6 CP15EA 20061205002762006120500276NM 2006 12 5 CA061019008 120061017G522085220281007 SEAL DHAV DHC8 DHC8301 1386003NM PWA PW120 PW123 NE HAMSTD14SF 14SF15 NE EMERGENCY EXIT LEAKING W O OTHER O OTHER CRCRUISE 1 CA 4982 4982 (CAN) DURING CRUISE, FLIGHT CREW REPORTED R SIDE EMERG EXIT DOOR SEAL FAILED (LEAKING) RESULTING IN PRESSURIZATION LOSS . AIRCRAFT REQUESTED AND WAS CLEARED TO A LOWER ALTITUDE. AFTER NORMAL LANDING, MAINTENANCE INSPECTED AND REPLACED EMERGENCY EXIT DOOR SEAL. (TC# 20061019008) 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20061205002732006120500273SO 2006 12 5 CA061019009 220061018G74141051324 SPRING CESSNA210 T210L 2073449CE CONT O520 TSIO520H 17040SO MCAULYD3A34 D3A34C402 GL MAGNETO BROKEN W O OTHER R PARTIAL RPM/PWR LOSS NRNOT REPORTED 1 CA 217469R (CAN) NOTE THE SERIAL NUMBER ON THE ENGINE ON THIS FORM IS INCORRECT IT IS 217469-R. THE IMPULSE COUPLING SPRING WAS FOUND BROKEN. CUSTOMER HAD COMPLAINED OF ROUGH RUNNING CHECK MAG DROP, REMOVED MAGS AND INSPECTED. THE SPRINGS WERE BROKEN IN BOTH MAGNETOS, 1H71 3O3 O 3A21 E8CE 5 CP47GL 20061211003242006121100324EA 2006 12 11 CA061019011 120060806G2897CC670582071 CONDUIT CNDAIRCL600 CL600* EA GE CF34 CF348C1 NE WIRING COVER INTERFERENCE W K NONE O OTHER ININSP/MAINT 1 CA 2551 2551 (CAN) DURING GROUND INSPECTION NOTICED FUEL LEAK NEAR FRONT SPAR AREA IN BELLY PANEL. INSPECTION FOUND ELECTRICAL CONDUIT FOR LT FUEL BOOST PUMP, WIRE COVERING INTERFERING WITH FLARE AT BULKHEAD FITTING. THIS ALLOWED FUEL TO PASS INTO THE CONDUIT AND OUT OF BELLY. WIRING COVERING TRIMMED BACK AND CONDUIT RESECURED. (TC NR 20061019011) 2L72 4F4 FRTA21EA EOOO63EN 20061211003252006121100325EA 2006 12 11 CA061019012 220060821G732230804 FLOAT PREAIR LYC O320 O320* 41508EA CARBURETOR UNSERVICEABLE W O OTHER O OTHER NRNOT REPORTED 1 CA 3 A1211973 (CAN) THE CARBURETOR WAS DISASSEMBLED INSPECTED AND THE FLOAT ASSY HAD GAS IN .5 OF THE FLOAT. FLOAT HAD NO APPARENT HOLES OR CRACKS AS FLUID WAS INSIDE AND WOULD NOT DRAIN OUT. (TC NR 20061019012) 3 O E274 20070129003282007012900328EU 2007 1 29 CA061020001 120061018G2750527521213 FLAP PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL WING OBSTRUCTED W O OTHER F FLT CONT AFFECTED NRNOT REPORTED 1 CA (CAN) ICE BUILD UP INTO THE IB FLAP COVER CAUSED THE FLAPS TO NOT GO FULL UP. IT TRIPPED THE FLAP CIRCUIT BREAKER. THE ICE CAUSED THE ROD TO BEND FROM THE STRESS OF TRYING TO MOVE THE FLAP UP. IT WAS NOTICE BY SEEING A 50 AMP DRAW FROM THE FLAP MOTOR. ROD REPLACED, ICE MELTED AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20061020001) 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20061205003012006120500301EU 2006 12 5 CA061020004 120061014G73341379287L405 LINE BAG JETSTMJETSTM3212 1500217EU GARRTTTPE331TPE33110UG 01514WP LT NACELLE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) P3 LINE FLANGE FOUND WITH SMALL CRACK DURING ROUTINE ENGINE CHANGE. LINE REPLACED WITH NEW UNIT. (TC# 20061020004) 2L72 4T4 TRTBA15CAA E4WE 20061211003272006121100327NM 2006 12 11 CA061020005 120060815G3230483023 SEQUENCE VALVE BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17EU NLG DOOR FAILED W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA (CAN) AFTER GEAR WAS SELECTED UP IN CLIMB OUT, NOSE GEAR DOOR CAUTION WAS ON TOGETHER WITH NOISE OF SPINNING WHEEL. QRH LANDING GEAR DOOR MALFUNCTION PERFORMED. AFTER GEAR WAS SELECTED DOWN DOOR CAUTION DISAPPEARED BUT WE NOW HAD AN INDICATION OF UNSAFE NOSE GEAR ( RED ). QRH ALTERNATE LANDING GEAR EXTENSION PERFORMED AND GREEN LIGHT FOR NOSE GEAR RECEIVED. NORMAL LANDING PERFORMED AND TAXIED TO PARKING. PASSENGERS AND CREW WAS BRIEFED SEVERAL TIMES DURING THE FLIGHT. NLG SOLENOID SEQUENCE VALVE REPLACED IAW 32-31-71-400-801 (TC NR 20061020005) 2H72 4T4 TRTA13NM E00062EN6 CP17BO 20061211003292006121100329NM 2006 12 11 CA061020006 120060824G3220471515 SENSOR BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17EU NLG FAILED W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA (CAN) AFTER TAKEOFF, LANDING GEAR DID NOT RETRACT. INDICATION SHOWED 3 GREENS AND 3 REDS. AFTER EMERGENCY CHECKLIST WAS COMPLETED THE DECISION FOR RE-LANDING WAS MADE. CABIN PAX AND STATION WERE INFORMED AND SUCCESSFUL RELANDING PERFORMED. FOUND NOSE WHEEL CENTER SENSOR FAULT AND SENSOR REPLACED. (TC NR 20061020006) 2H72 4T4 TRTA13NM E00062EN6 CP17BO 20061205002812006120500281EA 2006 12 5 CA061020007 120061017G5700 UNKNOWN DHAV DHC6 DHC6300 2802606EA UNKNOWN W A UNSCHED LANDING E VIBRATION/BUFFET CRCRUISE 1 CA (CAN) TYPE CERTIFICATE HOLDER (TCH) RECEIVED CALL INDICATING THIS AIRCRAFT WAS IN LEVEL FLIGHT WITH AN INDICATED AIRSPEED OF 120 KNOTS. THE PILOT FELT A VIBRATION IN THE AIRFRAME, LOOKED OUT THE LT WINDOW AND SAW THAT THE LT WING WAS FLUTTERING UP AND DOWN. THE PILOT REDUCED POWER AND IMMEDIATELY RETURNED TO BASE. (TC# 20061020007) 1H72 3T RTA9EA 20061205002952006120500295EA 2006 12 5 CA061022009 120061015G5610NP13932211 WINDOW CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE COCKPIT CRACKED W A UNSCHED LANDING O OTHER CRCRUISE 1 CA (CAN) LEFT SIDE WINDOW CRACKED (NOT SHATTERED) AT FL 350 (TC# 20061022009) 2L72 4F4 FRTA21EA E15NE 20061205002572006120500257NE 2006 12 5 CA061023002 120061019G52109220902411043 HINGE FITTING SKRSKYS92 S92A NE PAX DOOR CRACKED W O OTHER O OTHER NRNOT REPORTED 1 CA 103 (CAN) THE FOLLOWING INFORMATION REFERS TO CHC HELICOPTERS INTERNATIONAL GROUND OCCURRENCE REPORT ,WHICH WAS SUBMITTED BY OUR BASE IN MALAYSIA: "ON CARRYING OUT 50 HOUR INSPECTION ON PASSENGER DOOR AND HINGES, FOUND FORWARD UPPER HINGE CRACKED. CRACK WAS RUNNING FROM UPPER AFT BOLT HOLE AND DOWN ALONG HINGE FITTING". PLEASE NOTE THAT THIS PARTICULAR HINGE FITTING HAS ONLY BEEN INSTALLED SINCE AUGUST 2006. . THE PREVIOUSLY INSTALLED HINGE FITTING WAS FOUND CRACKED ON 22 AUGUST 2006 AND HAD FLOWN A TOTAL OF 168.6 HOURS (AIRCRAFT WAS UNDERGOING 50 HOURS INSPECTION. DID NOT RESULT IN ANY OTHER FAILURE. INSPECTION/MAINTENANCE WAS CONTINUED AND REPORT SUBMITTED. (TC# 20061023002) 2G72 4U R00024BO 20061205002942006120500294EA 2006 12 5 CA061023004 120061016G3097302114BB1 WIRE DHAV DHC8 DHC8311 1386006EA PWA PW120 PW123 NE HAMSTD14SF 14SF15 NE ELECTRICAL BURNED W O OTHER J WARNING INDICATION CRCRUISE 1 CA 3371933719 (CAN) DURING CRUISE , FLIGHT CREW NOTICED NR 2 ENGINE LIP HEATER INDICATION SHOWING FAILURE OF LIP HEATER, DUE TO ICING CONDITIONS AT DESTINATION AIRPORT CREW ELECTED TO RETURN TO ORIGINATING AIRPORT. NORMAL LANDING. DURING MAINTENANCE INVESTIGATION FOUND NO POWER TO LIP HEATER. PROBLEM TRACED TO BURNED WIRE 30-21-14BB-18 IN WIRING BUNDLE BEHIND LAVATORY WALL ( AFT OF CO-PILOT SEAT). WIRING BUNDLE HAD CHAFED ON LAVATORY WALL CAUSING INSULATION TO BE WORN. WIRE ( AND 3 OTHER WIRES IN SAME BUNDLE) REPAIRED. AIRCRAFT RETURNED TO SERVICE. (TC# 20061023004) 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20061211003302006121100330SO 2006 12 11 CA061023005 220061012G8520643202 CASE CESSNA401 401 207590CCE CONT O520 TSIO520E 17040SO MCAULY3AF32C3AF32C* GL ENGINE CRACKED W K NONE K FLUID LOSS ININSP/MAINT 1 CA 1324 521407 (CAN) THE ENGINE HAD A SMALL OIL LEAK. AFTER REMOVING THE DIP STICK ASSEMBLY, A CRACK WAS FOUND BETWEEN NR 2 AND NR 4 CYLINDERS. THE ENGINE WAS REMOVED FOR OVERHAUL. (TC NR 20061023005) 1L72 3O3 O A7CE E8CE 5 CP22EA 20061205002482006120500248EA 2006 12 5 CA061024001 120061023G5610601R3303314 WINDSHIELD CNDAIRCL600 CL6002C10 1390015EA FAILED W O OTHER O OTHER CRCRUISE 1 CA (CAN) F/O WINSHIELD BROKE WHILE AT CRUISE ALTITUDE, DIVERTED C/A -RAR F/O WINDSHIELD IAW AMM (CRJ 700) 56-11-01 REF LGPG2160865 ITEMS 1 AND 2 FOR FUNCTIONAL CHECK AND OPERATIONAL CHECK. OPS CHECKS AND FUNCTIONAL CHECKS OK. (TC# 20061024001) 2L72 4F RTA21EA 20061205002562006120500256EA 2006 12 5 CA061024002 220061020G8500TIGO541E1A ENGINE PIPER PA31 PA31P 7103120SO LYC O541 TIGO541E1A 41539EA RIGHT MALFUNCTIONED W E ENGINE SHUTDOWN MJ OVER TEMP WARNING INDICATION CLCLIMB 1 CA RL27662 (CAN) AFTER TAKEOFF, RT ENGINE STARTED MAKING POWER FLUCTUATIONS WITH A RAPID EGT RISE. RT ENGINE WAS SHUT DOWN IN DESCENT AND AIRCRAFT RETURNED SAFELY. A MAINTENANCE INVESTIGATION IS UNDER WAY TO DETERMINE THE CAUSE. REPORT TO FOLLOW WHEN CAUSE IS IDENTIFIED. (TC# 20061024002) 1L72 3O3 O A8EA E19EA 20061205002452006120500245EU 2006 12 5 CA061024003 120061024G2120 UNKNOWN BAG JETSTMJETSTM3212 1500217EU GARRTTTPE331TPE33110UG 01514WP ROTOL R333 R333482F12 GL COCKPIT ODOR W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 1 CA (CAN) DURING CRUISE FLIGHT CREW COULD DETECT FUMES OF AN ELECTRICAL NATURE. AIRCRAFT RETURNED TO DEPARTURE POINT WITHOUT INCIDENT. A MAINTENANCE INVESTIGATION IS UNDER WAY TO DETERMINE THE CAUSE OF THE FUMES/ODOUR. A REPORT WILL FOLLOW WHEN CAUSE IS IDENTIFIED. (TC# 20061024003) 2L72 4T4 TRTBA15CAA E4WE 6 CP61GL 20061205002472006120500247EA 2006 12 5 CA061025002 120061024G352013740003 SWITCH CNDAIRCL604 CL604 1900301EA GE CF34 CF343B1 NE OXYGEN CONTROL INOPERATIVE W O OTHER G MULTIPLE FAILURE NRNOT REPORTED 1 CA 1656 (CAN) WHILE CARRYING OUT A 12 MONTH CABIN OXYGEN FUNCTIONAL TEST, FOUND THE OXYGEN CONTROL PANEL SEMI-FUNCTIONAL. THE ROTARY KNOB WOULD NOT GO TO THE "CLOSED" POSITION WITHOUT EXCESSIVE FORCE. ROTATING TO THE "OVERRIDE" POSITION FUNCTIONED PROPERLY BUT OXYGEN FLOW TO THE CABIN MASKS SEEMED RESTRICTED. SELECTING THE "THERAPEUTIC" SWITCH "ON" WAS EXTREMELY STIFF AND WOULD NOT TURN OFF WHEN SELECTED. FOUND PANEL TO BE CONTAMINATED. MOST LIKELY COFFEE AND/OR SOFT DRINK RESIDUE. NEW PANEL INSTALLED, FLOW TO CABIN OXYGEN MASKS SEEMED TO INCREASE TO DOUBLE THE FLOW RATE OF THE ORIGINAL. THERAPEUTIC SWITCH OPERATED AS NORMAL.412 SQUADRON OPS WILL BE CONTACTED TO APPRISE PILOTS OF THE FINDINGS. (TC# 20061025002) 2L72 4F4 FRTA21EA E15NE 20061205002552006120500255NM 2006 12 5 CA061025003 120061020G271082700567001 CABLE DHAV DHC8 DHC8301 1386003NM PWA PW120 PW123 NE HAMSTD14SF 14SF23 NE RT AILERON BROKEN W O OTHER O OTHER NRNOT REPORTED 1 CA 16203 (CAN) FINDINGS DURING C-CHECK INSPECTION IN AREA WING STA 171, AFT SPAR, LT AND RT REVEALED HEAVILY CHAFED AILERON CABLES IN PULLEY AREA AT WING BS 171. ON RT SIDE THE CABLE WAS SEVERELY DAMAGED AND ONLY A PART OF ONE STRAND WAS LEFT INTACT. THE CABLE IS OF TYPE 19X7 (7 STRANDS AND WITH 19 WIRES). LAST INSPECTION PERFORMED IN 2001 (TASK 2C INTERVAL) - NO FINDINGS. ON LT SIDE APPROX 40% OF THE STRANDS/WIRES WAS BROKEN. THE PULLEYS ARE MADE OF STEEL WITH A ROLLER BEARING AND UNDERNEATH THE PULLEYS IS A CABLE GUARD. CABLE TENSION APPROX 52 LBS (AMM) INSPECTION OF A NUMBER OF PULLEYS, AILERON AND SPOILER, REVEALED HEAVY WEAR/INDENTATION AT ONE SPOT AS IF THE PULLEY HAD BEEN. (TC# 20061025003) 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20061205002532006120500253GL 2006 12 5 CA061025004 320061022G6110 STUD MCAULY CESSNA185 185F 2072820CE CONT O520 IO520D 17032SO MCAULYD3A34 D3A34C403 GL PROPELLER UNSERVICEABLE W O OTHER O OTHER NRNOT REPORTED 1 CA 306 7710359 (CAN) WHILE INSTALLING THE MCCAULEY MODEL D3A34C403-B PROPELLER ONTO A CESSNA 185, THE ENGINEER WAS TIGHTENING THE FIBER LOCK NUTS ONTO THE PROPELLER MOUNTING STUDS, WHEN ONE OF THE NUTS KEPT ON TURNING AND DID NOT SEEM TO BE GETTING ANY TIGHTER. HE TRIED ANOTHER NEW LOCK NUT BUT THE SAME THING HAPPENED AND THEN NOTICED THAT THE MOUNTING STUD WAS BEING PULLED OUT FROM THE PROP HUB. THE LOCK NUT HAD NOT BEEN TIGHTENED UP TO THE RECOMMENDED TORQUE VALUE FOR MOUNTING THE PROP BEFORE THIS STARTED TO HAPPEN. THE PROPELLER BEING INSTALLED HAD ONLY 305.7 TSO. IT WAS SENT BACK TO THE SHOP THAT OVERHAULED IT. (TC# 20061025004) 1H71 3O3 O 3A24 E5CE 5 CP47GL 20061211003332006121100333SW 2006 12 11 CA061025005 120060907G28221C27 CARTRIDGE BELL 206 206B 1181511SW ALLSN 250C 250C20 03013GL BOOST PUMP INTERMITTENT W O OTHER J WARNING INDICATION CLCLIMB 1 CA (CAN) ABOVE 7000 FEET BOOST PUMP LIGHT WOULD COME ON. BELOW 7000 FEET WARNING LIGHT WOULS EXTINGUISH. BOOST PUMP CARTRIDGE P/N 1C27 REPLACED. (TC NR 20061025005) 1G71 3U3 U H2SW E4CE 20061211003352006121100335CE 2006 12 11 CA061025006 120060502G5711 SPAR BEECH 95 E95 1153410CE LYC O360 IO360B1B 41514EA HARTZLHCC2Y HCC2YK2 GL LT WING CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 7004 (CAN) DUING INSPECTION IAW FAA AD 90-08-14 AND SB53-2269 REV 2 SHORT CRACKS WERE VISUALLY FOUND EMINATING FROM 2 HUCK BOLT LOCATIONS ON THE LT FORWARD WING SPAR CARRY THROUGH WEB FACE. CRACKS WERE CONFIRMED BY LPI. REPAIRED IAW MFG FAA APPROVED DRAWING 58-40009 AND 58-4008 REV C FORWARD LT FACE ONLY. (TC NR 20061025006) 1L72 3O3 O 3A16 1E10 5 CP920 20070129003292007012900329CE 2007 1 29 CA061025007 120060930G6123 CONTROL CABLE BEECH 95 E95 1153410CE LYC O360 IO360B1B 41514EA HARTZLHCC2Y HCC2YK2 GL RT PROP DEFECTIVE W O OTHER F FLT CONT AFFECTED CRCRUISE 1 CA (CAN) AFTER A ROUTINE TRAINING FLIGHT THE PILOT REPORTED THAT THE RT PROP CONTROL WAS VERY STIFF AND SPRINGY AND THE PROP WAS SLOW TO FEATHER. THE CONTROL WAS DISCONNECTED FROM THE GOVERNOR AND THE DEFECT WAS CONFIRMED TO BE THE CONTROL CABLE. THE TTSN FOR THE ENGINE CONTROL CABLES WERE UNKNOWN. ALL LT AND RT ENGINE CONTROL CABLES WERE REPLACED WITH NEW CONTROLS. (TC NR 20061025007) 1L72 3O3 O 3A16 1E10 5 CP920 20061205002412006120500241NM 2006 12 5 CA061026001 120061025G49104503067A APU BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA MALFUNCTIONED W O OTHER B SMOKE/FUMES/ODORS/SPARKS ININSP/MAINT 1 CA (CAN) APU ENCLOSURE SUFFERED STRUCTURAL DAMAGE AFTER FUEL VAPOR IGNITED. CREW HAD TRIED TO START APU AFTER LANDING MINIMUM TWICE, UNABLE TO START. NOT POSSIBLE TO GET FAULT CODES SO MECHANIC CALLED. MECH STARTED APU AND THEN IT AUTO SHUTDOWN. MECH STARTED APU AGAIN AND SAME RESULT. MECH OBSERVED FUEL VAPOR FROM EXHAUST BUT NOT FROM FUEL DRAIN. MECH PULLED CIRCUIT BREAKER FOR FUEL SOLENOID IN ORDER TO PERFORM DRY CRANK TO VENT APU. WHEN PUSHING POWER SWITCH THERE WAS AN EXPLOSION IN THE APU BAY. DAMAGE TO THE APU ENCLOSURE AND DOORS OCCURRED. TAIL CONE TO BE REPLACED. (TC# 20061026001) 2H72 4T4 TRTA13NM E00062EN 20061205002312006120500231NM 2006 12 5 CA061026002 120061026G2710FL4C62 BEARING DHAV DHC8 DHC8102 2809003NM AILERON CONTROL JAMMED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING THE C CHECK INSPECTION, NR 5 BEARING ON 8 IN A WING AILERONS SYSTEME CABLE FAIRLEADS WAS FOUND JAMMED AND FLAT SPOTTED. ALL CABLES PASSING THRU THE FAIRLEAD HAVE TO BE REPLACE DUE TO THE CHAFFING IN THE BEARING, THE WORSE ONE WAS THE CABLE P/N:82700519-001. THE PART NUMBER IN THE IPC WAS FL4C6-2 BUT THE NUMBER ON THE BEARING WAS P15SP1 WITH THE WORD SARMA STAMP ON IT. (TC# 20061026002) 2H72 4T RTA13NM 20061205002402006120500240CE 2006 12 5 CA061026003 120061025G324650060285 WHEEL BEECH 1900 1900C 1154161CE PWA PT6 PT6A65B 52043EA MLG DEPARTED W K NONE D INFLIGHT SEPARATION ININSP/MAINT 1 CA (CAN) PILOTS DISCOVERED NR 4 WHEEL ASSY MISSING AFTER ARRIVING AT DESTINATION. PASSENGER SAID A BANG WAS HEARD DURING TAKE-OFF. MAINTENANCE PERSONNEL DISPATCHED TO INSPECT AIRCRAFT, AND IF INSPECTED SERVICEABLE INSTALL NEW WHEEL ASSY AND RETURN TO BASE. AIRCRAFT INSPECTED SERVICEABLE, M/W INSTALLED AND AIRCRAFT FLOWN TO BASE. O/B BEARING APPEARS TO HAVE FAILED. (TC# 20061026003) 2L72 4T4 TRTA24CE E4EA 20061205002352006120500235EU 2006 12 5 CA061026004 120061026G3411 INDICATOR GIPPLDGA8 GA8 3900102EU LYC O540 IO540K1A5 41532EA PITOT HEAT BURNED W O OTHER BH SMOKE/FUMES/ODORS/SPARKS ELECT. POWER LOSS-50 PC NRNOT REPORTED 1 CA 1100 (CAN) PILOT REPORTED MALFUNCTION OF PITOT HEAT BREAKER SWITCH, UPON INSPECTION, CIRCUIT BOARD ATTACHED TO BACK OF SWITCH WAS FOUND BADLY BURNT AND END OF WIRE CONNECTION FROM THE PITOT TO THE POWER SWITCH WAS FOUND OVERHEATED. MAIN PITOT WAS REPAIRED. THE CIRCUIT BOARD CLAMPED BETWEEN THE BREAKER SWITCH AND THE PITOT HEAT WIRE WAS U/S DUE TO OVERHEAT. THIS INSTALLATION APPEARS TO BE FROM FACTORY. 2 POSSIBLE CAUSES OF THIS FAILURE: 1) FIBERGLASS CIRCUIT BOARD COULD NOT STAND UP TO PRESSURE OF ATTACHMENT SCREW. DUE TO POOR CONNECTION , THE CONNECTION WOULD HAVE HEATED UP AND UPON GETTING HOT ENOUGH, RESIN IN FIBERGLASS BOARD WOULD HAVE DISINTIGRATED CAUSING PITOT HEAT FAILURE. 2) PRINTED CIRCUIT BOARD HAS WI1H71 3O3 ONT 1E4 20061205002922006120500292WP 2006 12 5 CA061026005 120061016G7600 SUPPORT GRUMANTS2 TS2ACALFORST3951102WP ENG CONTROLS UNSERVICEABLE W O OTHER O OTHER NRNOT REPORTED 1 CA NA (CAN) IN SOME CASES, THE WELD BRAZING THAT CONNECTS THE TELEFLEX CONTROL SUPPORT BEARINGS TO THE ENGINE CONTROL QUADRANT ASSEMBLY HAVE BEEN FOUND TO BE CRACKED OR HAVE INSUFFICIENT BONDING TO THE BEARING SUPPORT PLATE. THIS PROBLEM, IN ADDITION TO INTERNAL WEAR IN THE BEARINGS, CAN CAUSE ADDITIONAL STRESS TO THE REMAINING BRAZED WELD. IN EXTREME CASES THE BEARING CAN SEPARATE FROM THE BEARING SUPPORT PLATE AND CAUSE UNEXPECTED POWERPLANT SETTINGS. ORIGINALLY DISCOVERED IN AUGUST 2002 - CASCADE AEROSPACE ISSUED A SERVICE BULLETIN (SB 3127-001) TO INSPECT THE ENTIRE FLEET WITHIN SEVEN DAYS OR 60 FLIGHT HOURS (WHICHEVER CAME FIRST). RECURRING NDT INSPECTIONS WERE SCHEDULED EVERY 400 HOURS TAT OR DURING AN ANNUAL 2H72 4R A25WE 20070129001292007012900129CE 2007 1 29 CA061027001 120061023G27200510105338 CONTROL CABLE CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA MCAULY1C160 1C160DTM GL RUDDER SYSTEM MISROUTED W K NONE WF INADEQUATE Q C FLT CONT AFFECTED ININSP/MAINT 1 CA 6326 6326 (CAN) WHILE CARRYING OUT A 100 HOUR INSPECTION IT WAS DISCOVERED THAT WHEN TENSION WAS PLACED ON THE RT RUDDER PEDAL, IT WAS RUBBING AGAINST THE RT AILERON DIRECT CABLE PULLEY CLEVIS PULLEY GUARD IN THE FORWARD TUNNEL SECTION OF THE FUSELAGE. THE RUBBING WAS SUFFICIENT ENOUGH TO CAUSE 6 WIRES TO BREAK. THE CABLE WAS IMPROPERLY ROUTED OVER THE AILERON DIRECT PULLEY CLEVIS PIN CABLE GUARD AND SHOULD HAVE PASSED UNDERNEATH. THE CABLE WAS FRAYED APPROXIMATELY 7 INCH AFT OF THE ATTACHMENT TO THE AFT RUDDER BAR. THE FRAYED WIRE CAN ONLY BE SEEN BY REMOVAL OF THE PLASTIC CENTER CONSOLE AND VIEWED THROUGH THE TUNNEL SECTION WITH AN INSPECTION MIRROR AND TENSION APPLIED TO THE RT RUDDER. NO RECORD OF THE CABLE EVER BEI1H71 3O3 ONT3A12 E274 5 NP910 20061205002502006120500250SW 2006 12 5 CA061027002 120061023G553141000823 SPAR AEROCD GULSTM690TP 690A 0141722SW GARRTTTPE331TPE3315 01514WP VERTICAL STAB CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 8830 (CAN) DURING ANNUAL X-RAY INSPECTION OF THE VERTICAL STABILIZER, A CRACK WAS DETECTED ON THE LEFT HAND SIDE OF THE VERTICAL STABILIZER CENTRE SPAR AT THE 4TH FASTENER ABOVE THE DOUBLER. THE CRACK APPEARS TO RUN INTO THE RADIUS OF THE CENTRE SPAR. THE AIRCRAFT WILL BE REPAIRED PRIOR TO BEING RELEASED BACK INTO SERVICE. (TC# 20061027002) 1H72 3T4 T 2A4 E4WE 20061205003002006120500300SW 2006 12 5 CA061027003 120061014G771231017263 TORQUE SENSOR SWRNGNSA226 SA226TC 8780404SW RT ENGINE DAMAGED W E ENGINE SHUTDOWN N FALSE WARNING TXTAXI/GRND HDL 1 CA 4015 (CAN) UPON TAXI INTO AIRPORT, THE RT ENGINE SHUT DOWN DUE TO THE CENTER GEAR ON THE TORQUE SENSOR SHAFT & WHERE NUT HOLDS THE GEAR ON BROKE OFF. AT THIS TIME THE A/C WAS AT THE TERMINAL AND NO PROBLEMS AROSE DUE TO THIS INCIDENT. SUSPECT THE NUT ON THE SHAFT WAS OVERTORQUED AT OVERHAUL BY A APPROVED OUTSIDE FACILITY. THE R/H ENGINE WAS REPLACED AND THE ENGINE P-54108 WAS FORWARDED TO THE ENGINE SHOP FOR REPAIR. (TC# 20061027003) 2L72 4T RTA8SW 20061205002542006120500254NE 2006 12 5 CA061027004 220061021G73221897001161 SHAFT BEECH BEECH 18 D18S 1151004CE PWA R985 R985AN14B 52008NE AIR VALVE WORN W D RETURN TO BLOCK F FLT CONT AFFECTED TXTAXI/GRND HDL 1 CA 5598 (CAN) PRIOR TO STARTUP, PILOTS` FOUND THE LH MANIFOLD HEAT CONTROL JAMMED. FURTHER INVESTIGATION DISCOVERED ONE OF THE SCREWS SECURING THE AIR VALVE PLATE TO THE AIR VALVE SHAFT HAD DEPARTED, AND THE OTHER SCREWS WERE VERY LOOSE. WRONG TYPE OF NUT WAS USED ON THE SCREWS, CONTRIBUTING TO THE LOOSE HARDWARE. PARTS MANUAL REQUIRES AN365-832 TYPE NUTS, WHILE PRESSED STEEL TYPE OF NUT WAS FOUND INSTALLED IN BOTH AIRBOXES. VALVE WAS REPAIRED AND AIRCRAFT RETURNED TO SERVICE. THIS HAD THE POTENTIAL TO BE AN ENGINE FAILURE. (TC# 20061027004) 1L72 3R3 R A765 5E1 20061205002872006120500287NM 2006 12 5 CA061029001 120061017G5753654952921 BELLCRANK BOEING737 737201 1384454NM PWA JT8 JT8D9A 52048NE NR 2 FLAP TRACK BROKEN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) NR 2 AFT FLAP BELLCRANK WAS FOUND BROKEN WHILE ACCOMPLISHING DAILY CHECK. INVESTIGATION FOUND EXCESSIVE WEAR ON THE NR 2 AFT FLAP BELLCRANK CAM TRACK WHICH RESULTED IN THE BELLCRANK POPPING OUT OF THE CAM TRACK. UPON REPLACEMENT OF THE CAM TRACK, IT WAS DETERMINED THE CAM TRACK WAS NOT INSTALLED IAW BOEING MAINTENANCE MANUAL. THE MM REQUIRES INSTALLATION OF A TAPER SHIM TO PROPER ALIGN TRACK SO THAT THE BELLCRANK CAM ROLLER WILL RIDE PROPERLY IN THE CAM TRACK. WE BELIEVE THE BELLCRANK BROKE AFTER IT POPPED OUT OF THE CAM TRACK AND JAMMED WHEN THE FLIGHT CREW MOVED THE FLAPS. A FLEET CAMPAIGN FOUND 2 OTHER CAM TRACKS WITH SIMULAR WEAR AND WERE ALSO MISSING REQUIRED TAPER SHIM. THE CAM TRACKS WERE REPLACED2L72 4F4 F A16WE E2EA 20061205002082006120500208EU 2006 12 5 CA061030001 120061028G2910316Q2277 LINE BRAERO748 HS7482A 4231001EU RROYCEDART DART5342 EU HYDRAULIC RETURNFRACTURED W A UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CRCRUISE 1 CA (CAN) WHILE EN-ROUTE THE HYDRAULIC FLOW LIGHTS ILLUMINATED AND THE HYDRAULIC PRESSURE DROPPED TO 1900PSI. THE AIRCRAFT DIVERTED, WHERE AN UNEVENTFUL LANDING WAS MADE. MAINTENANCE INVESTIGATION REVEALED THAT THE HYDRAULIC RETURN LINE BETWEEN THE HYDRAULIC CUT OUT VALVE AND THE HYDRAULIC RESERVOIR HAD FRACTURED AT THE RESERVOIR CONNECTION. THE LINE WAS REPLACED AND THE SYSTEM TESTED SERVICEABLE. AN OPTIONAL MOD (S/B 29/44, MOD 7297) RAISED BY BAE IN 1986 REPLACED THIS RIGID LINE WITH A FLEXIBLE LINE TO PRECLUDE THIS TYPE OF FAILURE. THE LINE IN QUESTION WAS A PRE-MOD ITEM. (TC# 20061030001) 2L72 3T4 T A24EU A196 20061211003372006121100337WP 2006 12 11 CA061030002 120061010G6510C0411 BEARING ROBSINR44 R44 7640120WP LYC O540 O540F1B5 41532EA DAMPER DAMAGED W O OTHER O OTHER NRNOT REPORTED 1 CA 197 (CAN) ABNORMAL SOUND HEARD ON SHUTDOWN. ON FURTHER INSPECTION THE INNER RACE OF THE DAMPER BEARING ON THE TAIL ROTOR DRIVESHAFT HAD BEEN FOUND TO HAVE SPUN. THE INNER RACE OF THE BEARING IS NOT ALLOWED ANY MOVEMENT RELATIVE TO THE DRIVE SHAFT. THE TAIL ROTOR DRIVE SHAFT ASSEMBLY WAS REPLACED WITH A SERVICEABLE UNIT. (TC NR 20061030002) 1G71 3O3 O H11NM E295 20061211003392006121100339CE 2006 12 11 CA061030003 120060627G8011631847 GEAR CONT CESSNA421 421 2076010CE CONT O520 GTSIO520H 17032SO STARTER SHAFT BROKEN W A UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION NRNOT REPORTED 1 CA 5 (CAN) (1)GEAR TOOTH BROKE OFF THE STARTER SHAFT GEAR IN A NEW STARTER ADAPTER ASSEMBLY CAUSING FOREIGN MATERIAL TO ENTER THE ENGINE LEADING TO FURTHER DAMAGE INSIDE THE CRANKCASE. FINAL RESULT WAS LOSS OF POWER TO THE RT ENGINE AND UNSCHEDULED LANDING. (TC NR 20061030003) 1L72 3O3 ORTA7CE E7CE 20061211003402006121100340 2006 12 11 CA061030004 420061006G3422568195301 SPRING JET VERTICAL GYRO FAILED W O OTHER O OTHER NRNOT REPORTED 1 CA 4681 1367M (CAN) AT PREVIOUS REPAIR UNIT WAS ASSEMBLED WITH A SHOP FABRICATED PRELOAD SPRING OF LARGED DIAMETER AND HIGHER PRESSURE RATE PRELOAD SPRING SHOULD HAVE BEEN REMOVED WHEN MOD 5 INCORPORATED (TC NR 20061030004) 20070126003032007012600303CE 2007 1 26 CA061030005 120061023G325005430223 ARM CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA MCAULY1A103 1A103TCM GL NLG STEERING BENT W K NONE O OTHER ININSP/MAINT 1 CA 9448 (CAN) DURING INSPECTION OF STERRING SYSTEM LT STEERING ARM TUBE FOUND BENT ON THE TUBE ASSY. NEW PART ORDERED AND INSTALLED. (TC NR 20061030005) 1H71 3O3 ONT3A19 E223 5 NP50GL 20061205002102006120500210SO 2006 12 5 CA061030006 120061027G7120 MOUNT PIPER PA31T PA31T 7103124SO PWA PT6 PT6A28 EA ENGINE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 8215 3512 (CAN) THE TOP ENGINE MOUNT PAD, LOCATED ON THE GAS GENERATOR CASE, HAD A CRACK ON THE WELD LINE APPROX. 1.75 INCHES LONG. (TC# 20061030006) 1L72 3T4 T A8EA E4EA 20061211003412006121100341EU 2006 12 11 CA061030007 120060518G6220350A37116220 RETAINER SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1D1 NE DROOP STOP CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) ON THE DAILY CHECK BY THE ENGINEER THE MAIN ROTOR BLADE DROOP STOP RING RETAINER WAS FOUND CRACKED BELOW THE RETAINER CLAMP. NO FURTHER DAMAGE. (TC NR 20061030007) 1G71 3U3 U H9EU E19EU 20061205002032006120500203NM 2006 12 5 CA061031001 120061030G324082920010147 TUBE DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE MLG LEAKING W A UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CLCLIMB 1 CA (CAN) DURING CLIMB OUT CREW REPORTED LOSS OF HYDRAULIC FLUID (DOWN 1/2 QUART). FLIGHT RETURNED TO DEPARTING AIRPORT. ALL SYSTEMS WERE OPERATING NORMALLY UNTILL LANDING ROLLOUT, AT WHICH TIME CREW REPORTED NIL BRAKES. AIRCRAFT STOPPED WITH EMERGENCY BRAKE AND WAS TOWED TO RAMP AREA WITHOUT FURTHER INCIDENT. ERS WAS REQUESTED FOR ARRIVAL BUT AN EMERGENCY WAS NOT DECLARED. NO ADVERSE PASSENGER REACTION WAS NOTED. MAINTENANCE TROUBLESHOOTING FOUND THE NR 1 SYSTEM PRESSURE LINE (IPC REF. 32-42-00 FIG. 5 ITEM - 160) TO THE LT BRAKE CONTROL VALVE TO HAVE A PIN HOLE AT THE LOWER FORWARD ELBOW. REPLACED WITH A TEMPORARY FLEX LINE. SYSTEM LEAK AND FUNCTION CHECKED SERVICEABLE. AIRCRAFT AFTT-41155:50 HOURS, CYCLES-41543. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20061205002092006120500209GL 2006 12 5 CA061031002 320061027G611405503214 BULKHEAD CESSNA172 172N 2072434CE LYC O320 O320D2J 41508EA MCAULY1C160 1C160DTM GL SPINNER CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 77 (CAN) BULKHEAD WAS INSTALLED IAW CESSNA SK172-156A INSTRUCTIONS. BULKHEAD HAS CRACKS CURVING AROUND BOLT HOLES ABOUT HALF INCH AWAY FROM THE HOLE EDGE AT THE INNER BEND RADIUS. NOTE: THIS IS THE FOURTH OR FIFTH IDENTICALLY CRACKED BULK HEAD FOUND ON AS MANY OTHER 172 A/C IN THE PAST THREE OR SO MONTHS AT OUR FACILITY. CESSNA IS GIVING US WARRANTY FOR THE PARTS BUT NO CORRECTIVE ACTION HAS COME FORWARD AS YET. (TC# 20061031002) 1H71 3O3 ONT3A12 E274 5 NP910 20061211003422006121100342SW 2006 12 11 CA061031003 120060920G6730206076031021 SERVO BELL 206 206B 1181511SW ALLSN 250C 250C20 03013GL ROTOR SERVO LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA 115401112 (CAN) EXCESSIVE FLUID LEAKAGE. LEAKING BEYOND LIMITS (TC NR 20061031003) 1G71 3U3 U H2SW E4CE 20061205002902006120500290SO 2006 12 5 CA061031004 120061017G5344 HINGE PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA PAX DOOR CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) CABIN LOWER ENTRANCE DOOR FORWARD HINGE LOOSE, DOOR MOVES UP AND DOWN WHEN PASSENGERS STEP ON THE LOWER DOOR STEP. FOUND THE FORWARD DOOR HINGE ATTACHMENT FRAME CRACKED AT THE ATTACHMENTS FOR THE HINGE, ALLOWING THE DOOR SILL AND CABIN FLOOR AT THE ENTRANCE TO MOVE UP AND DOWN WHEN A LOAD WAS APPLIED TO THE DOOR. FRAME REPLACED WITH NEW PART AND DOOR REINSTALLED. (TC# 20061031004) 1L72 3O3 O A20SO E14EA 20061205002442006120500244EU 2006 12 5 CA061101001 120061024G2810A2824004900200 VALVE AIRBUS310 A310 EU GE CF6 CF680C GL FUEL SYSTEM BROKEN W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) WHILE PERFORMING A GENERAL VISUAL INSPECTION INSIDE THE RIGHT HAND/OUTER FUEL TANK, THE OUTBOARD FUEL PUMP SEQUENCE VALVE WAS FOUND BROKEN. DEBRIS OF THE SEQUENCE VALVE WHERE FOUND NEARS THE RESPECTIVE FUEL PUMP CANISTER. AREA WAS CLEAN OUT. SEQUENCE VALVE ASSEMBLY REPLACED. 2L72 4F4 FRTA35EU E23EA 20061205001992006120500199EA 2006 12 5 CA061101002 120061030G5730601R1090719 CLAMP CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE ACCESS DOOR BURNED W K NONE O OTHER ININSP/MAINT 1 CA 25347 (CAN) ELECTRICAL ARC BURN MARKS FOUND ON THE REAR FACE OF NUTPLATES (QTY 17) FOR THE WING FUEL TANK ACCESS DOORS. AS PER THE TECHNICAL RECORDS THERE WERE TWO REPORTED LIGHTNING STRIKES ON THIS AIRCRAFT SINCE NOVEMBER 09/2005. THE BURN MARKS ARE A LIKELY INDICATION OF LIGHTNING STRIKE ENERGY PATH. SOME OF THE ACCESS CUT-OUT ON THE UNDERWING WERE FOUND PAINTED OVER. THESE PAINT WERE REMOVED, AREA RETREATED AND NEW PANELS WERE INSTALLED. (TC# 20061101002) 2L72 4F4 FRTA21EA E15NE 20061205002022006120500202NE 2006 12 5 CA061101003 220061030G8530205364205523 STUD CNDAIRCL215 CL2151A10 1900320EA PWA R2800 CA3 52026NE CYLINDER HOLD DOSHEARED W K NONE O OTHER ININSP/MAINT 1 CA 1124 P36383 (CAN) DURING ANNUAL INSPECTION OF THE RT ENGINE 5 OF THE 15 CYLINDER HOLD DOWN STUDS ON CYLINDER NO. 2 WERE FOUND SHEARED. 3 HOLD DOWN NUTS WERE LOOSE, ALL PAL NUTS WERE INSTALLED AND TIGHT. THE PART NUMBERS FOR THE SHEARED STUDS ARE AS FOLLOWS: 205364 (QTY 2), 205523 (QTY 2)AND 204850 (QTY 1). ADDITIONAL INSPECTIONS OF THE ENGINE WILL BE ACCOMPLISHED. ANY FURTHER FINDINGS/RESULTS WILL BE REPORTED. 2H72 4R4 RRTA14EA E231 20061205002052006120500205NE 2006 12 5 CA061101005 120061029G32465004410 WHEEL SKRSKYS76 S76A 8143006NE MLG CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) WHEEL CRACKED AND AUDIBLE AIR ESCAPING FOUND ON DAILY INSPECTION (TC# 20061101005) 1G72 3U H1NE 20061205002062006120500206EA 2006 12 5 CA061102001 120061029G5610NP1393215 WINDSHIELD CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE COCKPIT CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) LT WINDSHIELD REMOVED AND REPLACED ACC AMM TASK 56-11-01-000-801. (TC# 20061102001) 2L72 4F4 FRTA21EA E15NE 20061205002362006120500236EA 2006 12 5 CA061102002 120061026G5610601R3303314 WINDSHIELD CNDAIRCL600 CL6002C10 1390015EA GE CF34 CF348C1 NE COCKPIT CRACKED W O OTHER O OTHER APAPPROACH 1 CA (CAN) WINDSHIELD CHANGED AND TESTED IAW AMM TASK 56-11-01-401-801-A01. 2L72 4F4 FRTA21EA EOOO63EN 20061205002382006120500238EA 2006 12 5 CA061102003 120061026G5610NP13932113 WINDSHIELD CNDAIRCL600 CL6002C10 1390015EA GE CF34 CF348C1 NE COCKPIT FAILED W A UNSCHED LANDING O OTHER CRCRUISE 1 CA (CAN) CAPTAIN WINDSHIELD SHATTERED AT FL320 ENROUTE TO ORD. DIVERTED TO BIS. (TC# 20061102003) 2L72 4F4 FRTA21EA EOOO63EN 20070126003062007012600306CE 2007 1 26 CA061102004 120061102G27202613017202 RUDDER CESSNA208 208B 2073701CE STIFF W D RETURN TO BLOCK F FLT CONT AFFECTED TXTAXI/GRND HDL 1 CA 4088 4088 (CAN) AIRCRAFT WAS BEING TAXIED TO THE RAMP FROM THE HANGER. THE PILOT NOTICED THAT THE RUDDER CONTROLS FELT STIFF. THE PILOT DECIDED TO RETURN TO THE HANGER AND ADVISE MAINTENANCE. THE AIRCRAFT IS BEING EXAMINED AT THIS TIME AND WILL UP-DATE THIS SDR WHEN A CAUSE OF THIS FAULT IS FOUND. (TC NR 20061102004) 1H71 3T A37CE 20061205001742006120500174 2006 12 5 CA061102005 120061102G5412K6600013 FIREWALL GARRTTTPE331TPE3315251K NM NACELLE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) CRACKS FOUND IN FIREWALL ASSEMBLY WHILE DOING SB 217. (TC# 20061102005) 4 T E2WE 20061211003452006121100345NM 2006 12 11 CA061102006 120061004G3230 HOUSING TACTAIR DHAV DHC8 DHC8301 1386003NM PWA PW120 PW123 NE HAMSTD14SF 14SF23 NE SEQUENCE VALVE FAILED W A UNSCHED LANDING K FLUID LOSS APAPPROACH 1 CA 13093 1769 (CAN) DURING APPROACH WHEN CREW SELECTED GEAR DOWN, NR 2 HYD ENG PUMP CAUTION LIGHT ILLUMINATED DURING EXTENSION CYCLE. NOSE GEAR DOORS AND RT MAIN GEAR DOORS REMAINED OPEN, LT MAIN GEAR DOOR CLOSED. QRH ITEMS FOR NR 2 HYDRAULIC SYSTEM AND GEAR DOORS OPEN WERE COMPLETED. INVESTIGATION BY ENGINEERING DETERMINED THAT THE LEAK WAS ORIGINATING FROM THE RT MLG DOOR SOLENOID SEQUENCE VALVE. (3) OF THE FOUR BOLTS SECURING THE SOLENOID TO THE VALVE BODY HAD SHEARED RESULTING IN THE PARTIAL SEPARATION OF THE SOLENOID FROM VALVE BODY. THIS CAUSED A LOSS OF NR 2 HYDRAULIC SYSTEM QUANTITY AND PRESSURE. NO SECONDARY DAMAGE WAS CAUSED AS A RESULT OF THE FAILURE. THE SOLENOID SEQUENCE VALVE ASSEMBLY WAS REPLACED IAW THE AIRC2H72 4T4 TRTA13NM E20NE 6 CP7NE 20061211003472006121100347EA 2006 12 11 CA061102007 120060926G5751 HINGE BOMBDR CNDAIRCL215 CL2156B11215 EA PWA PW120 PW123 NE HAMSTD14SF 14SF* NE AILERON DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA 2936 (CAN) DURING AN ANNUEL INSPECTION WE FOUND BOTH AILERONS WITH SEVERE DAMAGE AT CENTER HINGE (TC NR 20061102007) 2H72 4T4 TRTA14EA E20NE 6 CP7NE 20061205001762006120500176NM 2006 12 5 CA061103002 120061101G574072760059101 ADAPTER DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE ACTUATOR CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 48562 1341 (CAN) A CRACK WAS DISCOVERED (C-CHECK INSPECTION) ON THE RUDDER ACTUATOR MOUNTING ADAPTOR (UPPER) TO VERTICAL STAB SPAR. THE CRACK IS APPROXIMATELY 2.5 INCHES AROUND THE CIRCUMFERENCE OF THE ADAPTOR TUBE. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20061211003492006121100349NE 2006 12 11 CA061103003 220060927G7200 ENGINE CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE OVERHEATED W O OTHER MJ OVER TEMP WARNING INDICATION TXTAXI/GRND HDL 1 CA PC1299 (CAN) DURING TAXI FOLLOWING LANDING THE ENGINE EXPERIENCED AN ITT OVER-TEMPERATURE. SUBSEQUENT INSPECTION REVEALED DEBRIS IN THE EXHAUST AND HEAT DISCOLORATION OF THE AIRCRAFT COWLING IN THE EXHAUST REGION. MFG WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061103003) 1H71 3T3 T A37CE E4EA 20061211003512006121100351EA 2006 12 11 CA061103004 220060925G7261 OIL SYSTEM SOCATATBM TBM700 8682000EU PWA PT6 PT6A64 EA ENGINE OVERTEMP W E ENGINE SHUTDOWN MJ OVER TEMP WARNING INDICATION NRNOT REPORTED 1 CA (CAN) IN FLIGHT ENGINE OIL TEMPERATURE WAS SEEN TO INCREASE ACCOMPANIED BY A DROP IN OIL PRESSURE. THE ENGINE WAS SHUTDOWN IN FLIGHT. POST FLIGHT INSPECTION REVEALED DEBRIS IN THE ENGINE OIL SYSTEM AND EVIDENSE OF OIL LEAKAGE FROM THE ENGINE DRAIN. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061103004) 1L71 3T4 TRTA60EU E4EA 20061211003522006121100352NE 2006 12 11 CA061103005 220060927G7210 SHAFT BOMBDRDHC8 DHC8400 NM PWA PW120 PW123 NE RGB DAMAGED W O OTHER XJ ENGINE FLAMEOUT WARNING INDICATION CRCRUISE 1 CA (CAN) THE ENGINE FLAMED-OUT IN CRUISE AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE. SUBSEQUENT INSPECTION REVEALED METAL DEBRIS ON THE ENGINE CHIP DETECTOR AND DAMAGE TO THE TOWERSHAFT. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061103005) 2H72 4T4 TRTA13NM E20NE 20061211003532006121100353NE 2006 12 11 CA061103006 220060810G7261 TUBE AEROSPATR42 ATR42* 8680900EU PWA PW121 PW121 52124NE OIL TRANFER CRACKED W E ENGINE SHUTDOWN KJ FLUID LOSS WARNING INDICATION TOTAKEOFF 1 CA 121355 (CAN) FOLLOWING TAKEOFF ENGINE SPEEDS REDUCED UNCOMMANDED AND AN ENGINE FIRE WARNING ACTIVATED. THE ENGINE WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INSPECTION FOUND THE PROPELLER DIFFICULT TO ROTATE, EVIDENCE OF OVER-HEATING ON THE GAS GENERATOR CASE, AND A FRACTURED OIL TRANSFER TUBE. MFG WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061103006) 2H72 4T4 TRTA53EU E20NE 20061211003542006121100354NE 2006 12 11 CA061103007 220060923G7250 TURBINE BLADES CESSNA425 425 2076018CE PWA PT6 PT6A112 52043NE ENGINE FRACTURED W O OTHER O OTHER NRNOT REPORTED 1 CA 12439 (CAN) IN FLIGHT THE ENGINE EMITTED A LOUD NOISE FOLLOWED BY FLAMES FROM THE EXHAUST AND VIBRATION. THE ENGINE WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED FRACTURED COMPRESSOR TURBINE BLADES. MFG WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061103007) 1L72 3T3 TRTA7CE E4EA 20061211003562006121100356NE 2006 12 11 CA061103008 220060902G7321324485718 FUEL CONTROL DHAV DHC8 DHC8301 1386003NM PWA PW120 PW123 NE ENGINE FAULTY W O OTHER XJ ENGINE FLAMEOUT WARNING INDICATION CLCLIMB 1 CA 3144 (CAN) THE ENGINE FLAMEOUT IN CLIMB AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE. THE HYDROMECHANICAL FUEL CONTROL UNIT WAS SUBSEQUENTLY REPLACED. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061103008) 2H72 4T4 TRTA13NM E20NE 20061211003572006121100357NE 2006 12 11 CA061103009 220061005G7200 ENGINE AEROSPATR42 ATR42* 8680900EU PWA 120 PW120 NE FAILED W E ENGINE SHUTDOWN RJ PARTIAL RPM/PWR LOSS WARNING INDICATION TOTAKEOFF 1 CA 120100 (CAN) ON TAKEOFF ENGINE POWER REDUCED UNCOMMANDED FOLLOWED BY SMOKE IN THE CABIN AIR. THE ENGINE WAS SHUTDOWN IN FLIGHT AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE. SUBSEQUENT INSPECTION FOUND THE PROPELLER SEIZED AND METAL DEBRIS IN THE ENGINE CASES. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061103009) 2H72 4T4 TRTA53EU E20NE 20061211003582006121100358NE 2006 12 11 CA061103010 220061007G7321 FUEL CONTROL CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE ENGINE FAULTY W EA ENGINE SHUTDOWN UNSCHED LANDING F FLT CONT AFFECTED CLCLIMB 1 CA (CAN) ON TAKEOFF ENGINE POWER INCREASED UNCOMMANDED AND THE ENGINE WOULD NOT RESPOND TO THROTTLE INPUT. THE ENGINE WAS SHUTDOWN IN FLIGHT AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC NR 20061103010) 1H71 3T3 T A37CE E4EA 20061205001722006120500172EA 2006 12 5 CA061103011 120061102G2750 CONTROL UNIT CNDAIRCL600 CL600* EA GE CF34 CF343A 30015NE TE FLAPS FAILED W A UNSCHED LANDING F FLT CONT AFFECTED CLCLIMB 1 CA (CAN) DURING TAKE OFF FLAP FAIL DURING FLAP RETRACTION, A/C RETURN TO TERMINAL .BREAKER RESET AS PER OPERATING MANUAL NR 1 ABNORMAL PROCEDURE SECTION 10 P 3-4. A/C RETURN TO SERVICE ,NO FURTHER SNAG.TWO MORE TAKE -OFF WERE CARRIED OUT FOLLOWING THAT INCIDENT, NO SNAG. 2L72 4F4 FRTA21EA E15NE 20061211003602006121100360NE 2006 12 11 CA061103012 220061012G73201240KDC0400 EEC LEAR 60 60LEAR 5170707CE PWA 305 PW305A 52128NE FAILED W O OTHER XJ ENGINE FLAMEOUT WARNING INDICATION DEDESCENT 1 CA (CAN) THE ENGINE FLAMED OUT ON DESCENT. THE PROBLEM COULD NOT BE DUPLICATED ON THE GROUND AND THE EEC WAS SUBSEQUENTLY REPLACED. MFG WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061103012) 2L72 4F4 FRTA10CE E35NE 20061211003622006121100362NE 2006 12 11 CA061103013 220061005G7250 TURBINE BLADES BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE ENGINE DAMAGED W C ABORTED TAKEOFF RJ PARTIAL RPM/PWR LOSS WARNING INDICATION TOTAKEOFF 1 CA PS0469 (CAN) ON TAKEOFF ROLL THE ENGINE EMITTED A LOUD NOISE ACCOMPANIED BY A LOSS IN POWER. TAKEOFF WAS ABORTED. SUBSEQUENT INSPECTION REVEALED DAMAGED POWER TURBINE BLADES. MFG WILL MONITOR INVESTIGATION OF THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061103013) 2L72 4T4 TRTA24CE E26NE 20070126003072007012600307SW 2007 1 26 CA061103014 120061030G29102781006025 HYDRAULIC LINE SWRNGNSA227 SA227AC 8780603SW GARRTTTPE331TPE33111U 01514WP MCAULY4HFR344HFR34C652 NE LT MLG WW CRACKED W O OTHER K FLUID LOSS ININSP/MAINT 1 CA (CAN) HYD FLUID LEAKING FROM LT WHEEL WELL. WHEN LT GEAR DOORS WERE OPENED TO INSPECT, ENTIRE GEAR BAY WAS COVERED WITH FLUID. AFTER CLEANING, REPLACING LINE AND PUTTING AIRCRAFT ON JACKS TO CHECK FOR FURTHER LEAKS ALL CHECKED WITHIN MANUFACTURERS LIMITATIONS. AIRCRAFT RETURNED OT SERVICE. (TC NR 20061103014) 2L72 4T4 TRTA8SW E4WE 6 C3PNE 20061205002992006120500299NE 2006 12 5 CA061103015 220061014G7250 TURBINE BLADES CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE ENGINE FRACTURED W EA ENGINE SHUTDOWN UNSCHED LANDING E VIBRATION/BUFFET CRCRUISE 1 CA (CAN) IN CRUISE THE ENGINE EXPERIENCED VIBRATIONS FOLLOWED BY A LOUD NOISE AND WAS SHUT DOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED FRACTURED TURBINE BLADES. P&WC WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC# 20061103015) 1L72 4F4 F A22CE E1NE 20061205002142006120500214NE 2006 12 5 CA061103016 220061027G7200 ENGINE CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE FLAMED OUT W O OTHER XJ ENGINE FLAMEOUT WARNING INDICATION NRNOT REPORTED 1 CA 71397 (CAN) THE ENGINE FLAMED OUT IN FLIGHT FOLLOWING A COMMANDED REDUCTION IN POWER TO IDLE. PWC WILL MONITOR INVESTIGATION OF THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC# 20061103016) 1L72 4F4 F A22CE E1NE 20061205001962006120500196GL 2006 12 5 CA061103017 220061030G724023064570B COMBUSTION LINER BELL 407 407 1182206SW ALLSN 250C 250C47B GL ENGINE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA CAE847206 (CAN) COMBUSTION LINER FOUND CRACKED ON REMOVAL DURING TURBINE SECTION REPLACEMENT TO COMPLY WITH ROLLS ROYCE CEB A-72-6060. THIS PART IS FOUND TO BE CRACKED ANY TIME IT IS REMOVED AFTER ANY LENGTH OF TIME IN SERVICE. MANUFACTURERS MAINTENANCE MANUAL ALLOWS NO CRACKS IN THIS AREA. 1G71 3U3 UO H2SW E1GL 20061205001982006120500198GL 2006 12 5 CA061103018 220061030G724023030911K COMBUSTION CASE BELL 407 407 1182206SW ALLSN 250C 250C47B GL ENGINE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA CAE847206 (CAN) CRACK ALONG LEFT SIDE "ARMPIT" WELD LINE FOUND DURING UNSCHEDULED TURBINE REMOVAL FOR CEB A-72-6060. NO CRACKS ALLOWED IN THIS AREA. 1G71 3U3 UO H2SW E1GL 20061205001772006120500177EU 2006 12 5 CA061104001 120061101G5510258TF4331 PLATE BRAERODH125 BAE125800A 1500285EU HORIZONTAL STAB CORRODED W K NONE O OTHER ININSP/MAINT 1 CA 6160 (CAN) UPON VISUAL INSPECTION AND CLEANING OF ATTACHMENT LUG AREA OF VERTICAL FIN TO HORIZONTAL STABILIZER, MECHANIC NOTICED MATERIAL FLAKING OFF OF ONE BOLT HOLE. FURTHER INSPECTION REVEALED EXFOLIATION CORROSION. SINCE THIS TYPE OF CORROSION IS DIFFICULT TO DETECT VISUALLY IT WAS ONLY WHEN THE MECHANIC WAS CLEANING THE AREA THAT HE NOTICED THE DAMAGE. UPON CONSULTATION WITH THE MANUFACTURER (RAYTHEON) THE CORROSION WAS REMOVED TO DETERMINE THE EXTENT OF PENETRATION AND COVERAGE (PHOTO ILLUSTRATION) WHICH WAS DETERMINED TO BE OUT-OF-TOLERANCE AND REQUIRED REPLACEMENT OF THE REINFORCEMENT PLATE. THIS DEFECT WAS THE FIRST TIME THE MANUFACTURER HAD COME ACROSS. ESPECIALLY SIGNIFICANT WAS THE FACT THAT IT WAS EXFOL2L72 4F RTA3EU 20061211003632006121100363NE 2006 12 11 CA061106001 220060821G7210311196801 SHAFT EMB 120 EMB120 3260201SO PWA PW118 PW118B NE FRACTURED W O OTHER XJ ENGINE FLAMEOUT WARNING INDICATION NRNOT REPORTED 1 CA 26695 (CAN) THE ENGINE SUFFERED AN IN FLIGHT SHUTDOWN AS A RESULT OF A FRACTURED TOWER SHAFT. (TC NR 20061106001) 2L72 4T4 TRTA31SO E20NE 20061205002582006120500258NE 2006 12 5 CA061106002 220061019G7261 ENGINE DHAV DHC8 DHC8201 2809001NM PWA 120 PW123D 52152NE LEAKING W O OTHER KB FLUID LOSS SMOKE/FUMES/ODORS/SPARKS NRNOT REPORTED 1 CA 123308 (CAN) THE AIRCRAFT LAVATORY SMOKE DETECTOR ACTIVATED SHORTLY AFTER TAKE OFF AND OIL SMELL BECAME EVIDENT IN THE CABIN. A SMALL EXTERNAL ENGINE OIL LEAK WAS SUBSEQUENTLY FOUND. &WC WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC# 20061106002) 2H72 4T4 TRTA13NM E20NE 20061205002972006120500297NE 2006 12 5 CA061106003 220061015G7200 ENGINE AEROSPATR42 ATR42300 8680920EU PWA 120 PW120 NE SHUTDOWN W O OTHER RJ PARTIAL RPM/PWR LOSS WARNING INDICATION NRNOT REPORTED 1 CA (CAN) THE ENGINE WAS REPORTED TO HAVE EXPERIENCED THREE INCIDNETS OF TORQUE FLUCTUATION RESULTING IN EITHER PROPELLER FEATHERING OR IN-FLIGHT SHUT-DOWN BETWEEN OCTOBER 15TH AND 17TH. THE ENGINE FUEL SYSTEM COMPONENTS WERE SUBSEQUENTLY REMOVED FOR INVESTIGATION. P&WC WILL MONITOR THE INVESTIGATION AND ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC# 20061106003) 2H72 4T4 TRTA53EU E20NE 20061205002422006120500242NE 2006 12 5 CA061106004 220061025G73218236602 HYDROMECH UNIT CESSNA500 560CESSNA 2076750CE PWA 530 PW535A NE ENGINE MALFUNCTIONED W O OTHER XJ ENGINE FLAMEOUT WARNING INDICATION CRCRUISE 1 CA (CAN) THE ENGINE FLAMED-OUT IN CRUISE AND THE AIRCRAFT DIVERTED FOR A SINGLE ENGINE LANDING. THE HYDROMECHANIAL FUEL CONTROL UNIT WAS SUBSEQUENTLY REPLACED. P&WC WILL MONITOR INVESTIGATION OF THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC# 20061106004) 2L72 4F4 FRTA22CE E00053EN 20061205002982006120500298EA 2006 12 5 CA061106005 220061015G7200 ENGINE BELL 212 212 1181420SW PWA PT6T PT6T3 52045EA MALFUNCTIONED W E ENGINE SHUTDOWN BJ SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION NRNOT REPORTED 1 CA 60244 (CAN) DURING GROUND RUNS FOLLOWING EXTENSIVE MAINTENANCE THE POWER SECTION ACCELERATED UNCOMMANDED. POWER WAS REDUCED TO IDE AND THE ENGINE LOW OIL PRESSURE WARNING ACTIVATED. ON SHUT DOWN SMOKE WAS SEEN EMINATING FROM THE EXHAUST. SUBSEQUENT INSPECTION REVEALED FRACTURED POWER TURBINE BLADES AND RESULTANT ENGINE DAMAGE. PWC WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC# 20061106005) 1G71 4U4 U H4SW E22EA 20061205001802006120500180NE 2006 12 5 CA061106006 220061101G7200 ENGINE AEROSPATR42 ATR42300 8680920EU PWA 120 PW120 NE FAILED W O OTHER J WARNING INDICATION CRCRUISE 1 CA 120983 (CAN) IN CRUISE THE ENGINE EMITTED A LOUD NOISE AND ENGINE ITT TEMPERATURE WAS SEEN TO INCREASE. POST-FLIGHT INSPECTION FOUND THE PROPELLER COULD NOT BE ROTATED. P&WC WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 2H72 4T4 TRTA53EU E20NE 20061205002432006120500243NE 2006 12 5 CA061106007 220061024G73203035381 TUBE DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE FUEL SYSTEM FRACTURED W E ENGINE SHUTDOWN RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 1 CA (CAN) ENGINE POWER REDUCED TO IDLE UNCOMMANDED IN CRUISE. AN EMERGENCY WAS DECLARED AND THE ENGINE WAS SHUT DOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED A FRACTURED FUEL CONTROL P3 AIR SUPPLY TUBE. THE FRACTURE HAD OCCURRED IN THE WELD AREA AT THE TUBE "B" NUT. (TC# 20061106007) 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20061205000962006120500096EA 2006 12 5 CA061106008 120061103G2497M2750010JB3U00 WIRE HARNESS CNDAIRCL600 CL600* EA ADG SHORTED W O OTHER O OTHER NRNOT REPORTED 1 CA 7305 (CAN) ADG DROPPED IN FLIGHT FOR TEST, NO POWER, LANDED NORMALLY. FOUND WIRING HARNESS AND WIRES BURNED & SHORTED AT CONNECTOR P1XC ON ADG. BOMBARDIER PSP603A WIRING MANUAL 24-25-01 FIG. 1 SHEET1. WIRING HARNESS AND CONNECTOR REPLACED. 2L72 4F RTA21EA 20061205000972006120500097EU 2006 12 5 CA061106009 120061103G2910137311D1431 LINE BAG JETSTMJETSTM3212 1500217EU HYD SYSTEM CHAFED W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) L/H HYDRAULIC BRAKE LINE FOUND LEAKING FLUID. LEAK FOUND AT MYCARTA CLAMPING BLOCK. NEW LINE INSTALLED. (TC# 20061106009) 2L72 4T RTBA15CAA 20070126003092007012600309EU 2007 1 26 CA061106011 120061102G3010FAL1007 HOSE AMD FALC10FALCON10 2730101EU GARRTTTFE731TFE7312 01518WP LT SLAT COLLAPSED W O OTHER O OTHER TXTAXI/GRND HDL 1 CA 306 (CAN) AFTER LANDING THE PILOTS NOTICED THAT THE LT IB SLAT HAD A SMALL TRACE OF ICE FORMED. AFTER INSPECTION IT WAS FOUND THAT THE LT IB SLAT ANTI-ICE HOSE INNER WALL HAD COLLAPSED. THE HOSE WAS REPLACED AND ALL OTHER SLAT ANTI-ICE HOSES WERE INSPECTED AND FOUND SERVICEABLE. (TC NR 20061106011) 2L72 4F4 F A33EU E6WE 20061205003142006120500314GL 2006 12 5 CA061106012 320061013G6111163356 SEAL MCAULYD3A36 D3A36C410 GL BLADE ROOTS INCORRECT W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA 63 (CAN) PROPELLER WAS FACTORY ASSEMBLE WITH INCORRECT BLADE SEALS ON ALL 3 BLADES. P/N 1633-56 SHOULD HAVE BEEN INSTALL BUT SEALS FOR A NON-OIL FILLED HUB WERE FOUND INSTALLED INSTEAD. THIS WAS A WARRANTY REPAIR. 5 CP47GL 20061205002122006120500212SW 2006 12 5 CA061106014 120061027G3230 LANDING GEAR BELL 430 430 1182150SW MALFUNCTIONED W O OTHER O OTHER LDLANDING 1 CA (CAN) ON APPROACH TO HELIPAD, LANDING GEAR DID NOT BE DEPLOYED. PILOT NOTICE AT THE LAST MOMENT AND ALMOST LANDED ON BELLY. ADD NO GREEN LIGHT NOR AUDIO WARNING. USE THE EMERGENCY GEAR RELEASE. LANDING UNEVENTFUL AFTERWARD. (TC# 20061106014) 1G72 3U RTH9SW 20061205002522006120500252EA 2006 12 5 CA061106015 220061022G72303023779 DIFFUSER DHAV DHC7 DHC7102 2802708EA PWA PT6 PT6A50 52043EA HAMSTD24PF 24PF305 GL ENGINE LOOSE W A UNSCHED LANDING XJ ENGINE FLAMEOUT WARNING INDICATION CRCRUISE 1 CA 86199 (CAN) SHORTLY AFTER LEVELLING OFF AT 17000 FEET, THE NR 2 ENGINE BEGAN TO SURGE AFFECTING ALL ENGINE PARAMETERS. THE POWER WAS REDUCED TO ALLEVIATE THE RESULTING OVER TEMPERATURE CONDITION. AT POWER SETTING ABOVE 70% NG THE ITT WOULD FLUCTUATE WILDLY TO OVER 900 DEGREES. THE ENGINE WAS SHUTDOWN AND THE AIRCRAFT LANDED WITHOUT FURTHER INCIDENT. AFTER TROUBLESHOOTING, THE ENGINE WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. THE ENGINE WAS SPLIT AND THE DIFFUSER TUBE AT 6 O-CLOCK WAS FOUND LOOSE. THIS LOOSE DIFFUSER TUBE DISRUPTED THE AIRFLOW TO THE BLEED VALVE SENSE LINE, CAUSING THE BLEED VALVES TO MALFUNCTION AND THE ENGINE TO SURGE. THE ENGINE WAS SENT FOR REPAIR. 2H74 4T4 T A20EA E4EA 6 CP1NE 20061205000852006120500085CE 2006 12 5 CA061106016 120061104G27501015210579 SWITCH BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE HARTZLHCE4A HCE4A3I NE TE FLAPS FAILED W A UNSCHED LANDING F FLT CONT AFFECTED DEDESCENT 1 CA 15902 (CAN) AFTER TWO MISSED APPROACHES, THE FLAPS WOULD NOT RETRACT FROM 17 DEGREES. AIRCRAFT DIVERTED, ON THE GROUND THE FLAP ASYMETRICAL OVERRIDE SWITCH WAS USED AND FLAPS RETRACTED. THE FLAPS WHERE THEN DEFERRED UNTIL MAINTENANCE INPECTED SYSTEM AND FOUND FAULTY ASYMETRICAL SWITCH. SWITCH WAS REPLACED. 2L72 4T4 TRTA24CE E26NE 5 CP10NE 20061205000862006120500086CE 2006 12 5 CA061106017 120061104G79311013890235 TRANSDUCER BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE OIL PRESSURE MALFUNCTIONED W A UNSCHED LANDING N FALSE WARNING CLCLIMB 1 CA 9301 (CAN) ON CLIMB NR 2 ENGINE DISPLAYED OIL PRESSURE FLUCTUATIONS FROM 120 TO 60 PSI. NO LOW OIL PRESSURE LIGHTS ILLUMINATED AND NO TORQUE FLUCUATIONS. THEY ELECTED TO RETURN TO AIRPORT. MAINTENANCE REPLACED THE R/H OIL PRESSURE TRANSDUCER AND AIRCRAFT WAS TESTED AND RETURNED TO SERVICE. 2L72 4T4 TRTA24CE E26NE 20061205000872006120500087EA 2006 12 5 CA061106018 220061103G72303035279 LINE DHAV DHC7 DHC7103 2802710EA PWA PT6 PT6A50 52043EA HAMSTD24PF 24PF305 GL P3 SENSE BROKEN W E ENGINE SHUTDOWN RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 1 CA PCE86509 (CAN) WHILE IN CRUISE THE NR 3 ENGINE ROLLED BACK TO 60% NG.. A PRECAUTIONARY SHUT DOWN OF THE ENGINE WAS COMPLETED AND THE AIRCRAFT RETURNED TO BASE. ON INSPECTION OF THE ENGINE IT WAS FOUND THAT THE P3 SENSE LINE, FROM THE GAS GENERATOR CASE TO THE P3 FILTER, WAS BROKEN, CAUSING THE ENGINE TO ROLL BACK TO IDLE. THE SENSE LINE WAS POST P&WC S/B-4112. THIS S/B INTRODUCED A BRACKET TO HELP SUPPORT THE LINE AT THE GAS GENERATOR ATTACHMENT END. THE LINE WAS REPLACED WITH A SERVICEABLE PART, AN ENGINE RUN-UP WAS COMPLETED AND FOUND TO BE SERVICEABLE. 2H74 4T4 T A20EA E4EA 6 CP1NE 20061205001732006120500173EA 2006 12 5 CA061107001 120061102G2722AL00102 ACTUATOR CNDAIRCL600 CL6002C10 1390015EA RUDDER TRIM MALFUNCTIONED W O OTHER F FLT CONT AFFECTED APAPPROACH 1 CA 6372 (CAN) DISC-RUDDER TRIM MOVING ON ITS OWN WITHOUT INPUT FROM COCKPIT CONTROLS. PULLED C/B 2F2 IAW AOM VOL 1. INDICATOR STILL SHOWS UNCOMMANDED MOVEMENT AND PLANE STILL FLIES SIDEWAYS, FDR DOWLNLOAD WAS REQUESTED TO CONFIRM THE TRIM MOUVEMENT. MAINTENANCE WAS UNABLE TO DUPLICATE. THE RUDDER TRIM ACTUATOR WAS REPLACED IAW CRJ700 AMM 27-22-01 AND PERFORMED FUNCTIONAL TEST OF THE RUDDER TRIM SYSTEM. FOUND SYSTEM WORKING PROPERLY AT THIS TIME IAW CRJ700 AMM 27-22-00. 2L72 4F RTA21EA 20061205001572006120500157EA 2006 12 5 CA061107002 120061103G7120ASB1810617 BOLT CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE ENGINE MOUNT UNSECURE W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA (CAN) AFT ENGINE MOUNT THRUST FITTING ATTACHMENT BOLTS ARE NOT SECURED (TORQUE IS UNKNOWN AND LOCKWIRE IS NOT INSTALLED) AT RH ENGINE. TO COMPLETE THE PROCEDURE IAW AMM 71-22-01 ENGINE TO BE REMOVED. (TC# 20061107002) 2L72 4F4 FRTA21EA E15NE 20061205001702006120500170NM 2006 12 5 CA061107003 120061102G29136617303 PUMP BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA HYD SYSTEM FAILED W A UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION DEDESCENT 1 CA 1262 (CAN) DURING DECENT TO THE AIRPORT PILOTS OBSERVED LOSS OF NR 2 HYD PRESSURE AND NR 2 EDP CAUTION LIGHT. THE PTU WAS SELECTED ON AND THE NR 2 HYD PRESSURE RECOVERED AND FLUID QUANTITY HAD DROPPED TO 40%. CREW ELECTED TO RETURN TO BASE. NON-EMERGENCY LANDING AND AIRCRAFT TAXIED TO RAMP UNDER ITS OWN CONTROL. NR 2 EDP HAD INTERNAL ROTATING GROUP FAILURE, EDP REPLACED. 2H72 4T4 TRTA13NM E00062EN 20061205001712006120500171SW 2006 12 5 CA061107004 120061102G5210AR835OXT4619 HANDLE BELL 412 412EP 1182205SW PAX DOOR MISSING W K NONE O OTHER ININSP/MAINT 1 CA 2 (CAN) UPON TEST FLIGHT RETURN TO BASE, IT WAS NOTICED THAT THE CO-PILOT OUTSIDE DOOR HANDLE WAS MISSING, SUSPECT IT WAS LOST IN FLIGHT. (TC# 20061107004) 1G72 4U H4SW 20061205000832006120500083NM 2006 12 5 CA061107005 120061105G5610NP15790112 WINDSHIELD DHAV DHC8 DHC8301 1386003NM COCKPIT CRACKED W A UNSCHED LANDING O OTHER CLCLIMB 1 CA 20816 (CAN) DURING CLIMB OUT, ALTITUDE APPROX. FL70, THE CO-PILOT NOTICED A SMALL CRACK IN THE MIDDLE OF HIS WINDSHIELD, WHICH WAS GETTING RAPIDLY BIGGER. EMERGENCY CHECKLIST FOR CRACKED WINDSHIELD WAS PERFORMED. RELANDING WAS UNEVENTFUL. A/C HANDED OVER TO MAINTENANCE. CO-PILOT`S WINDSHIELD REPLACED. 2H72 4T RTA13NM 20070126003142007012600314NM 2007 1 26 CA061107008 120061101G33103280080 TRIM PANEL DORNERDO32 DO328100 2996000NM PWA 119 PW119C NE HARTZLHDE6C HDE6C3B NE COCKPIT SHORTED W K NONE B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 1 CA 6671 (CAN) ENROUTE THE PILOT REPORTED A STRONG SMELL AND A FLASH OF LIGHT FROM CENTER CONSOLE AREA. THEY TURNED THE INTERIOR DOME LIGHT ON A CONFIRMED THAT A PLASTIC LIGHTING PANEL WAS MELTING ON THE RUDDER LIMITER AND STANDBY ELEVATOR BUTTONS. HE POKED THE SPOT WITH A PEN WHICH RESULTED IN FURTHER ARCING AND SMOKE. HE REQUESTED A LOWER ALTITUDE AND LANDED. MAINTENANCE WAS CONTACTED AND DISPATCHED TO THE AIRCRAFT. MAINTENANCE FOUND THE LIGHTING PANEL FOR THE TRIM HAD SHORTED. IT WAS DISABLED AND THE INTERIOR LIGHTING TESTED WITH NO FURTHER PROBLEMS. THE ITEM WAS DEFERRED AND THE AIRCRAFT RETURNED TO SERVICE. THE PILOT REPORTED THAT THE CB DID NOT POP AND THAT HE HAD A HARD TIME IN LOCATING THE CORRECT CB TO ISOLATE2H72 4T4 TRTA45NM E20NE 6 CP34NE 20061205000772006120500077EA 2006 12 5 CA061107009 220061106G7414 DISTRIBUTOR GEARCONT ROBSINR44 R44 7640120WP LYC O540 O540F1B5 41532EA MAGNETO FAILED W O OTHER R PARTIAL RPM/PWR LOSS CRCRUISE 1 CA 249 E01HA137R (CAN) DURING CRUISE FLIGHT, THE PILOT NOTICED A CHANGE IN ENGINE NOISE AND A SLIGHT YAW FOLLOWED BY THE LOW ROTOR HORN. PILOT DECREASED POWER WHICH RESULTED IN THE ROTOR RPM RECOVERING TO A NORMAL SETTING. THE PILOT FINISHED THE SHORT FLIGHT AT A LOWER POWER SETTING AND LANDED THE AIRCRAFT WITHOUT FURTHER INCIDENT. AFTER LANDING, A MAGNETO CHECK WAS CONDUCTED WHICH RESULTED IN THE ENGINE QUITING WHEN THE R/H MAG WAS SELECTED. WHEN THE MAGNETO WAS REMOVED, A FEW TEETH WERE FOUND BROKEN OFF THE DISTRIBUTOR GEAR. 1G71 3O3 O H11NM E295 20061205001602006120500160EA 2006 12 5 CA061107011 120061103G213092E204 CHECK VALVE CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE PRESS BULKHEAD FAILED W O OTHER O OTHER DEDESCENT 1 CA (CAN) THE CREW REPORTED THAT ON DESCENT THEY HAD PRESSURIZATION PROBLEMS. DURING THE DESCENT THEY GOT AUTO PRESS1 AND AUTO PRESS 2 FAIL AND MASKS DEPLOYED AND WERE USED. ALSO LT PACK HAD A BLOWN DUCT. LH PACK AIR CONDITIONING DUCT P/N601R895211-113 REPLACED BOTH 4.5 BUKHEAD CHECK VALVES REPLACED. NR 1 FOUND WITH NO SPRING LEFT. SB A601R-21-054 PG. 2 OF 18 EVIDENCE SECTION STATES: "AN AIRCRAFT WAS DEPRESSURIZED WHEN A FLAPPER ON THE BULKHEAD CHECK VALVE DETACHED AND AN AIR DUCT UPSTREAM OF THE BULKHEAD CHECK VALVE IS DISCONNECTED". BOTH CONSITIONS WERE PRESENT. O2 GENERATORS WERE REPLACED, SB APPLIED AND TEST FLIGHT WAS CARRIED OUT. AIRCRAFT RETURNED TO SERVICE. 2L72 4F4 FRTA21EA E15NE 20061205000742006120500074EU 2006 12 5 CA061108001 120061107G5340350A35101700 MOUNT SNIAS 350 AS350BA 8680817EU TMECA ARRIELARRIEL1B 6OO30NE HYDRAULIC PUMP DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING A 100 HOUR INSPECTION IT WAS DISCOVERED THAT TWO OF THE FOUR RIVETS USED TO ATTACH THE BEARING SUPPORT TO THE PUMP MOUNT WERE BROKEN. THE BEARING SUPPORT AND ATTACHING RIVETS ARE NOT LISTED IN THE AS350 ILLUSTRATED PARTS CATALOG, AS THEY ARE PART OF THE PUMP MOUNT. THE PUMP MOUNT WILL BE REPLACED AND THE AIRCARFT RETURNED TO SERVICE. (TC# 20061108001) 1G71 3U3 UNCH9EU E19EU 20061211003672006121100367SW 2006 12 11 CA061108002 120060929G71202060621021 MOUNT BELL 206 206B 1181511SW ALLSN 250C 250C20 03013GL LT ENGINE BROKEN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING DAILY INSPECTION PILOT NOTICED UNUSUAL PIECE OF METAL IN THE ENGINE BAY. INVESTIGATION REVEALED BROKEN LOWER LT ENGINE MOUNT. (TC NR 20061108002) 1G71 3U3 U H2SW E4CE 20070126003152007012600315CE 2007 1 26 CA061108003 120060919G53205042002815 FLOOR SUPPORT BEECH 90 C90A 1152911CE PWA PT6 PT6A21 52043EA HARTZLHCB3T HCB3TN3 GL FUSELAGE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) FLOOR SUPPORT ANGLE P/N UNKNOWN FOUND CRACKED. ANGLE IS PART OF BULKHEAD ASSY. P/N 50420028-15. ANGLE IS LOCATED UNDER CENTRE FLOOR PANEL. (TC NR 20061108003) 1L72 3T4 TRT3A20 E4EA 6 CP15EA 20070808001192007080800119CE 2007 8 8 CA061108004 120060828G552017121532 HINGE BRACKET CESSNA177 177B 2073708CE LYC O360 O360A1F6 41514EA MCAULY2D34C B2D34C211 GL RT STAB CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) RT STABILIZER HINGE BRACKET FOUND CRACKED AT FASTENER LOCATION. (TC NR 20061108004) 1H71 3O3 O A13CE E286 5 CP7EA 20061211003712006121100371EU 2006 12 11 CA061108005 120060912G5753137203B5761 BRACKET BAG JETSTMJETSTM3212 1500217EU GARRTTTPE331TPE33110UG 01514WP ROTOL R333 R333482F12 GL TE FLAP CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) FLAP SLAT BRACKETS CRACKED AT RADIUS. (TC NR 20061108005) 2L72 4T4 TRTBA15CAA E4WE 6 CP61GL 20070126003182007012600318 2007 1 26 CA061108006 420061105G3497KG102A CONNECTOR BEECH 76 76 1153005CE LYC O360 O360A1G6D EA HARTZLHCM2Y HCM2YR GL REMOTE GYRO CONTAMINATED W A UNSCHED LANDING O OTHER CRCRUISE 1 CA (CAN) DURING TRAINING IN IMC CONDITIONS, ATC REPORTED TO STUDENT THAT HE WAS WAY OFF TRACK, PILOT CONFIRMED THAT HSI SYSTEM HAD FAILED. AIRCRAFT RETURNED TO BASE WITH HELP FROM ATC WITH NO OTHER INCIDENCE. MAINTENANCE DUPLICATED DEFECT, HSI SYSTEM INSPECTED AND FOUND WATER ON CONNECTOR TO REMOTE GYRO. CONNECTOR DRIED AND CLEANED, OPS CHECKED SYSTEM OK. GYRO IS LOCATED IN NOSE COMPARTMENT. CLOSE OUT PANEL CAN LET IN SMALL AMOUNTS OF WATER IF PANEL IS NOT FIT PROPERLY BEFORE TIGHTENING THE SCREWS. THERE IS NO SEAL ON THIS PANEL. PANEL FIT AND INSTALLED CORRECTLY. (TC NR 20061108006) 1L72 3O3 O A29CE E286 5 CP43GL 20061205001942006120500194EU 2006 12 5 CA061108008 120061030G3230 DIODE BAG JETSTMJETSTM3212 1500217EU MLG CONTROL MELTED W O OTHER FJ FLT CONT AFFECTED WARNING INDICATION APAPPROACH 1 CA (CAN) DEFECT LANDING GEAR FAILED TO EXTEND. CIRCUIT BREAKER RESET AS PER QRH. GEAR LOWERED NORMALLY. RECTIFICATION LANDING GEAR WARNING SYSTEM TROUBLESHOT. FOUND DIODE 1GA28(P/N IN4007) TO BE MELTED. ALSO FOUND CAPACITOR 1GA26(P/N 114-19152) TO BE UNSERVICEABLE. NEW CAPACITOR AND DIODE INSTALLED. GROUND TEST CARRIED OUT AND FOUND SERVICEABLE. REF. W/O 1612 AND LOG PAGE 5037. DATE CLEARED OCTOBER 31, 2006. (TC# 20061108008) 2L72 4T RTBA15CAA 20070808001202007080800120CE 2007 8 8 CA061109001 120061108G5520656530128 TUBE CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE ELEVATOR CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING COMPLIENCE WITH CAMPAIGN NOTICE 851-27-20-035 (RUDDER AND ELEVATOR CABLE GUARDS) BOTH ELEVATOR CABLE GUARDS WERE FOUND TO BE UNSERVICEABLE. ALL (4) CLAMPS WERE DISTORTED AND CAUSED DISTORSION TO THE TUBES WHEN CLAMPED CAUSING CRACKS IN THE TUBES. BOTH ELEVATOR CABLE GUARD TUBES P/N 6565301-28 AND (4) CLAMPS P/N MS21919WD10 WERE REPLACE WITH NEW PARTS. THE RUDDER CABLE GUARDS WERE INSPECTED AND FOUND SERVICEABLE. (TC NR 20061109001) 1L72 4F4 F A22CE E1NE 20070808001212007080800121CE 2007 8 8 CA061109004 120060922G552012430192 BRACKET CESSNA210 T210L 2073449CE CONT O520 TSIO520H 17040SO MCAULY3A32C D3A32C88 GL RT ELEVATOR LOOSE W K NONE O OTHER ININSP/MAINT 1 CA (CAN) BRACKET P/N 1243019-2 FOUND LOOSE AGAINST TORQUE TUBE P/N 1234650-2. LOOSE FASTENERS REMOVED AND REPLACED. (TC NR 20061109004) 1H71 3O3 O 3A21 E8CE 5 CP21EA 20061213000742006121300074EU 2006 12 13 CA061109005 120060904G5753137204B5167 BRACKET BAG JETSTMJETSTM3212 1500217EU GARRTTTPE331TPE33110UG 01514WP ROTOL R333 R333482F12 GL TE FLAP CRACKED W K NONE O OTHER ININSP/MAINT 1 CA SDJ13614 (CAN) IB FLAP P/N 13760B463, SLAT BRACKETS P/N 137204B51 AND 137205B67 FOUND CRACKED AT BEND RADIUS. REMOVED AND REPLACED WITH NEW. (TC NR 20061109005) 2L72 4T4 TRTBA15CAA E4WE 6 CP61GL 20080220000042008022000004SW 2008 2 20 CA061109006 120061109G5330 SKIN BELL 206 206L4 1182110SW ALLSN 25OC 250C20R GL FUSELAGE CRACKED W OK OTHER NONE O OTHER ININSP/MAINT 1 CA 4113 (CAN) CRACK FOUND IN SKIN UNDER FWD BEARING OIL COOLER SUPPORT RT STA 192.00 BUTT 4.0. REPAIR WAS MADE IAW BHT-206-SRM-4-2 (TC NR 20061109006) 1G71 3U3 UNCH2SW E4CE 20061205001692006120500169NM 2006 12 5 CA061109007 120061102G3230104071 JOURNAL MESSIER DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE MLG STAB WORN W K NONE O OTHER ININSP/MAINT 1 CA 4153021725 DCL2048797 (CAN) AIRCRAFT WAS POSITIONED ON GATE FOR NEXT FLIGHT. IT WAS THEN FOUND THAT RT MAIN LANDING GEAR PIN COULD NOT BE REMOVED. TROUBLESHOOTING BY MAINTENANCE FOUND ON THE FOLLOWING ON THE RT MAIN LANDING GEAR STABILIZER STAY ASSEMBLY. THE AFT LINED JOURNAL BUSHING (ITEM 305) FOUND TO HAVE EXCESSIVE WEAR (1/16TH 3/32ND) CAUSING THE DOWN LOCK PIVOT POINT LOCK LINK ASSEMBLY (ITEM 280) TO OVERCENTER TOO FAR. THE STAY ASSEMBLY WAS REPLACED PER DHC 8 AMM 32-10-26, OPERATION AND LEAK CHECKS CARRIED OUT WITH NO FAULTS, AND THE AIRCRAFT RETURNED TO SERVICE. REFERENCE MESSIER-DOWTY COMPONENT MAINTENANCE MANUAL 32-10-04 FIG 1, PAGES 1010-1016. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20061205000732006120500073EA 2006 12 5 CA061109008 220061107G8520LW18729 PISTON CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA ENGINE CRACKED W A UNSCHED LANDING MBJOVER TEMP SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION CRCRUISE 1 CA 1005 (CAN) HIGH OIL TEMPERATURE AND BURNING ODOR IN CABIN PROMPTED RETURN TO AIRPORT. COMPRESSION CHECK REVEALED LOW COMPRESSION NR 3 CYLINDER, REMOVAL REVEALED A PORTION OF THE SECOND RING LAND APPROX. 1.5 INCHES LONG BROKEN OFF THE PISTON AT THE 10 O`CLOCK POSITION VEIWED FROM TOP. 1H71 3O3 ONT3A19 E223 20061212000822006121200082NM 2006 12 12 CA061110002 120060911G2530DL561064 MOTOR BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17EU NR 3 OVEN BURNED W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 1 CA 9283 990412511 (CAN) A OPERATOR MADE A UNSCHEDULED LANDING DUE TO HEAVY SMELL COMING FROM AFT GALLEY. INVESTIGATION SHOWED THAT THE BLOWER MOTOR OF ONE GALLEY OVEN SHOWS BURN DAMAGE. OVEN REMOVED AND SENT FOR REPAIR. (TC NR 20061110002) 2H72 4T4 TRTA13NM E00062EN6 CP17BO 20080220000052008022000005SO 2008 2 20 CA061110003 120061109G30007961502 SHROUD PIPER 7961502 PIPER PA28 PA28140 7102802SO LYC O320 O320E3D 41508EA SNSNCH74D 74DM EA CABIN OVERHEATED W K NONE M OVER TEMP ININSP/MAINT 1 CA 1356413564 (CAN) PART FOUND DEFORMED ABD DISCOLORED AND HEAT BLISTERS. (TC NR 20061110003) 1L71 3O3 O 2A13 E274 5 NP88614 20061205001672006120500167EU 2006 12 5 CA061110005 120061102G261237200000 FIRE DETECTOR AIRBUSA319 A319112 3930323EU CFMINTCFM565CFM565B6 13802NE APU BAY FAILED W O OTHER N FALSE WARNING NRNOT REPORTED 1 CA (CAN) APU EMERG SHUTDOWN ECAM FOLLOWED BY FIRE WARN AND MASTER CAUTION, APU SHUTDOWN VIA MASTER SWITCH, ECAM APU EMERG SHUTDOWN MSG CONTINUED WITH FIRE WARN LIGHT. APU FIRE EXT BUTTON PUSHED, INDICATIONS REMAINED, FIRE BOTTLE DISCHARGED AS PRECAUTION. NO VISIBLE SIGNS OF FIRE OR SMOKE NOTICED. FIRE WARN INDICATION REMAINED, AIRPORT FIRE DEPT CALLED AS PRECAUTION. PLEASE NOTE THAT MANUFACTURER IS L HOTELLIER, LOUIS AND DOES NOT EXIST ON DROP-DOWN LIST. (TC# 20061110005) 2L72 4F4 FRTA28NM E37NE 20080220000062008022000006WP 2008 2 20 CA061110006 120061109G5410C04623 FRAME ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE NACELLE BROKEN W K NONE O OTHER ININSP/MAINT 1 CA 333 (CAN) DURING INSPECTION FOR SB NR 59, C046-23 FOUND BROKEN AT THE EAR AS DESCRIBED IN THE SB PART, ON ORDER FOR REPLACEMENT AND A KIT KI-185 TO PREVENT VIBRATION OF THE TUBE WILL BE INSTALLED. FRAME WILL BE SENT TO MFG FOR EVALUATION IAW THEIR REQUEST. (TC NR 20061110006) 1G71 3O3 O H11NM 1E4 20061205002242006120500224WP 2006 12 5 CA061110007 220061026G7250TFE73120BR ENGINE LEAR 45 45LEAR 5170805CE GARRTTTFE731TFE7312 01518WP FAILED W K NONE O OTHER ININSP/MAINT 1 CA P116549C (CAN) DURING POST/PREFLIGHT INSPECTION MAINTENANCE PERSONNEL NOTICED NICKS ON 2 OF THE THE THIRD STAGE TURBINE BLADES. ENGINE HAS BEEN REMOVED AND SENT TO AN HEAVY MAINTENANCE FACILITY FOR INVESTIGATION AND REPAIR. A RENTAL ENGINE HAS BEEN INSTALLED AND THE AIRCRAFT RETURNED TO SERVICE (TC# 20061110007) 2L72 4F4 FRTT00008WIE6WE 20070126003232007012600323NE 2007 1 26 CA061113001 220061105G7200PT6AD ENGINE BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE HARTZLHCE4A HCE4A3I NE MALFUNCTIONED W EA ENGINE SHUTDOWN UNSCHED LANDING O OTHER CLCLIMB 1 CA (CAN) .5 HRS AFTER A SCHEDULED REPLACEMENT OF THE NR 3 AND NR 4 BEARING ASSY AND THE NR 1 AND NR 2 POWER TURBINE DISC`S DUE TO CYCLE LIFE LIMIT BEING REACHED, THE ENGINE LOST OIL PRESSURE AND WAS SHUTDOWN AND AIRCRAFT RETURNED TO DEPARTURE FIELD WITHOUT FURTHER INCIDENT. AWAITING TEAR DOWN REPORT FOR ADDITIONAL DETAILS. (TC NR 20061113001) 2L72 4T4 TRTA24CE E26NE 5 CP10NE 20061205000642006120500064EU 2006 12 5 CA061114001 320061113G6197697070212 BUSS BAR BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R4304 R4304* EU PROPELLER ASSY CHAFED W E ENGINE SHUTDOWN FJ FLT CONT AFFECTED WARNING INDICATION CRCRUISE 1 CA (CAN) NO.1 ENGINE SHUTDOWN MANUALLY IN FLT DUE PEC FAIL CAUTION AND PROP SPEED AT 1060 RPM. FAULT CODES LH CH A/B 160 AND 162. MAINT DISPATCHED TO T/S. FOUND BUSBAR FOR PROPELLER DEICE CHAFING ON MPU BRACKET, CAUSING MPU TO PICKUP SENS FROM BUSBAR. MPU ADJUSTED AND NEW BUSBAR INSTALLED. ENGINE GROUND RUNS C/O NORMAL. (TC# 20061114001) 2H72 4T4 TRTA13NM E00062EN6 CP890 20061205000722006120500072EU 2006 12 5 CA061114003 120061107G783032143304 SHUTOFF VALVE AIRBUS310 A310304 3930339EU GE CF6 CF680C2* GL THRUST REVERSER LEAKING W C ABORTED TAKEOFF J WARNING INDICATION TOTAKEOFF 1 CA AEX10603 (CAN) DURING TAKE OFF AT APPROXIMATELY 100 KNOTS NR 1 ENGINE THRUST REVERSER UNLOCKED LIGHT ILLUMINATED ACCOMPANIED WITH EAM MESSAGE NR 1 ENG REV UNLOCK¿. THE FLIGHT CREW REJECTED THE TAKE OFF ROLL, CYCLED THE REVERSER WITH NO FAULTS. CREW THEN ELECTED TO RETURN TO GATE. TO AVOID FURTHER DELAY, THE REVERSER WAS DEACTIVATED AND THE FLIGHT WAS DISPATCHED UNDER MEL. DURING TROUBLE SHOOTING FOUND THE PRESSURE REGULATING AND SHUT OFF VALVE BYPASSING. PRESSURE REGULATING/SHUT OFF VALVE REPLACED AND SYSTEM TESTED SERVICEABLE. 2L72 4F4 FRTA35EU E23EA 20070126003302007012600330CE 2007 1 26 CA061114005 120061110G2730656530128 GUARD CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE ELEVATOR CRACKED W O OTHER O OTHER ININSP/MAINT 1 CA (CAN) WHILE COMPLYING WITH COMPANY CAMPAIGN NOTICE CN 851-27-20-035, BOTH ELEVATOR CABLE GAURDS WERE FOUND CRACKED ADJASENT TO THE CLAMPS. THE TUBES WERE FOUND WITH .5 INCH LONGITUDINAL CRACKS. ADDITIONALLY ONE OF THE ATTACH CLAMPS WAS FOUND TO HAVE THE WRONG PN MS 21919WH10 INSTEAD OF MS 21919WDG10. MAINTENANCE ENTRIES WERE MADE WITH RESPECT TO THE WORK ACCOMPLISHED IN THE CONDITION AND CORRECTION SHEET ASD MP-01-860-10-30-01. (TC NR 20061114005) 1L72 4F4 F A22CE E1NE 20061205000662006120500066EU 2006 12 5 CA061114006 120061112G2150 A/C PACK AIRBUS310 A310304 3930339EU GE CF6 CF680C2* GL NR 2 ODOR W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CLCLIMB 1 CA (CAN) IN CLIMB OUT ECAM WARNING MIN EQUIPMENT BAY SMOKE CAME ON WITH BURNING ODOR AND A SMALL AMOUNT OF SMOKE IN THE FLIGHT DECK AND FWD CABIN. AIRCRAFT RETURNED TO THE STATION. MAINTENANCE INSPECTED THE MIN EQUIPMENT COMPARTMENT (NO FINDING). DURING ECS COMPARTMENT INSPECTION FOUND A BOOT LEAKING ON NR 2 PACK HEAT EXCHANGER WITH A BURNING ODOR COMING OUT OF THE PACK. NR 2 ENGINE BLEED AND NR 2 PACK DEACTIVATED AND RELEASE UNDER MEL. GROUND RUN PERFORMED WITH NR 1 SYSTEM AND NO FURTHER WARNING AND BURNING ODOR. DURING INVESTIGATION THE BROKEN BOOT COUPLING WAS REPLACED ON NR 2 PACK. THE AIR-COOLING SYSTEM WAS CLEANED AS PER M/M AND NR 2 COALESCOR BAG WAS REPLACED. SYSTEM WAS GROUND CHECKED SERVICEABLE. 2L72 4F4 FRTA35EU E23EA 20070126003352007012600335SO 2007 1 26 CA061114007 120061110G7603454253 THROTTLE CABLE PIPER PA31 PA31325 7103105SO LYC O540 TIO540F2BD 41532EA HARTZLHCE3Y HCE3YR2A GL COCKPIT FAILED W O OTHER O OTHER TXTAXI/GRND HDL 1 CA (CAN) RT ENGINE THROTTLE CABLE FAILURE: DURING A ROUTINE FLIGHT, THE PILOT, ENROUTE , NOTED THAT THE RT ENGINE THROTTLE CONTROL WAS STIFF ON APPROACH. THE AIRCRAFT EXPERIENCED A NORMAL LANDING, ONCE ON THE GROUND THE PILOT REPORTED THAT THE RT ENGINE WAS RUNNING AT IDLE AND WOULD NOT RESPOND TO THROTTLE MOVEMENTS. THE AIRCRAFT WAS TAXIED TO THE RAMP AND SHUTDOWN. THE RT ENGINE WAS INSPECTED, AND MAINTENANCE DETERMINED THE RT THROTTLE CABLE IN THE CABIN PEDESTAL HAD FAILED. THE THROTTLE CABLE WIRES HAD SEVERED APPROXIMATELY .2500 FROM THE SWAGED PORTION OF THE ROD END. UNFORTUNATELY ON A ROUTINE INSPECTION THIS PORTION OF THE CABLE IS COVER BY THE CABLE SLEEVE AND CANNOT BE INSPECTED. THE RT ENGINE THROTTLE1L72 3O3 O A20SO E14EA 5 CP33EA 20061205001852006120500185NM 2006 12 5 CA061114008 120061101G561058935734 WINDOW BOEING737 7377CG 13844FANM CFMINTCFM567CFM567B22 13802NE COCKPIT FAILED W O OTHER O OTHER CRCRUISE 1 CA 10744 (CAN) ON NOV. 1, 2006 A/C 216 EXPERIENCED A CRACKED NR 4 RT EYEBROW WINDOW. THE A/C CONTINUED TO ITS DESTINATION WITHOUT ANY FURTHER EVENTS. THE NR 4 WINDOW WAS REPLACED.BOEING IS AWARE OF THIS IN SERVICE ISSUE AND HAS INITIATED SERVICE RELATED PROBLEM (SRP) 56-0018. BOEING HAS ALSO ISSUED SERVICE BULLETIN 737-56-1017 TO PROVIDE 737NG OPERATORS WITH AN OPTION TO REPLACE THE NR 4 AND 5 WINDOWS WITH STRUCTURAL PLUGS. WESTJET IS PLANNING ON INCORPORATING THIS SERVICE BULLETIN. 2L72 4F4 FRTA16WE E00055EN 20061205002192006120500219NM 2006 12 5 CA061114009 120061027G561058935733 WINDOW BOEING737 7377CG 13844FANM CFMINTCFM567CFM567B22 13802NE COCKPIT CRACKED W O OTHER O OTHER CRCRUISE 1 CA 14236 (CAN) ON OCT. 27, 2006 A/C 201 EXPERIENCED A CRACKED NR 4 LT EYEBROW WINDOW. THE A/C CONTINUED TO ITS DESTINATION WITHOUT ANY FURTHER EVENTS. THE NR 4 WINDOW WAS REPLACED. BOEING IS AWARE OF THIS IN SERVICE ISSUE AND HAS INITIATED SERVICE RELATED PROBLEM (SRP) 56-0018. BOEING HAS ALSO ISSUED SERVICE BULLETIN 737-56-1017 TO PROVIDE 737NG OPERATORS WITH AN OPTION TO REPLACE THENR 4 AND 5 WINDOWS WITH STRUCTURAL PLUGS. WESTJET IS PLANNING ON INCORPORATING THIS SERVICE BULLETIN. (TC# 20061114009) 2L72 4F4 FRTA16WE E00055EN 20061205001912006120500191NM 2006 12 5 CA061114010 120061031G561058935733 WINDOW BOEING737 7377CG 13844FANM CFMINTCFM567CFM567B22 13802NE COCKPIT FAILED W O OTHER O OTHER CRCRUISE 1 CA 14250 (CAN) ON OCT. 31, 2006 A/C 202 EXPERIENCED A CRACKED NR 4 LT EYEBROW WINDOW. THE A/C CONTINUED TO ITS DESTINATION WITHOUT ANY FURTHER EVENTS. THE NR 4 WINDOW WAS REPLACED. BOEING IS AWARE OF THIS IN SERVICE ISSUE AND HAS INITIATED SERVICE RELATED PROBLEM (SRP) 56-0018. BOEING HAS ALSO ISSUED SERVICE BULLETIN 737-56-1017 TO PROVIDE 737NG OPERATORS WITH AN OPTION TO REPLACE THE NR 4 AND 5 WINDOWS WITH STRUCTURAL PLUGS. WESTJET IS PLANNING ON INCORPORATING THIS SERVICE BULLETIN. 2L72 4F4 FRTA16WE E00055EN 20061205000812006120500081NM 2006 12 5 CA061114011 120061106G561058935841 WINDOW BOEING737 73776N 13844CHNM CFMINTCFM567CFM567B22 13802NE COCKPIT CRACKED W O OTHER O OTHER CRCRUISE 1 CA 13936 (CAN) ON NOV. 6, 2006 A/C 011 EXPERIENCED A CRACKED NR 5 LT EYEBROW WINDOW. THE A/C CONTINUED TO ITS DESTINATION WITHOUT ANY FURTHER EVENTS. THE NR 5 WINDOW WAS REPLACED.BOEING IS AWARE OF THIS IN SERVICE ISSUE AND HAS INITIATED SERVICE RELATED PROBLEM (SRP) 56-0018. BOEING HAS ALSO ISSUED SERVICE BULLETIN 737-56-1017 TO PROVIDE 737NG OPERATORS WITH AN OPTION TO REPLACE THE NR 4 AND 5 WINDOWS WITH STRUCTURAL PLUGS. WESTJET IS PLANNING ON INCORPORATING THIS SERVICE BULLETIN. 2L72 4F4 FRTA16WE E00055EN 20070126003412007012600341EA 2007 1 26 CA061114012 120061114G26122155101681 BRACKET CNDAIRCL215 CL2151A10 1900320EA PWA R1340 CWASP 52016NE HAMSTD43E 43E60 NE FIRE WARNING CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING INSPECTION OF PN 215-51016-816 RELAY BRACKET ASSY, (IPC 26-10-00 FIG 2 PAGE 4) 3 OF THE RELAY BASES (ITEM 35) WERE FOUND CRACKED. THE MOUNTING HARDWARE (ITEM 36) WAS INCORRECT FROM NEW, ACCORDING TO THE DIAGRAM AND INCOMPATIBLE WITH THE RELAYS, 4 OF ON THIS ASSY. 2 OTHER AIRCRAFT WERE INSPECTED AND ONE RELAY BASE WAS FOUND CRACKED ON EACH OF THEM. THESE RELAYS ARE PART OF THE FIRE WARNING, LANDING GEAR INDICATION AND WATER DOOR SYSTEM. THE RELAY BASES WILL BE REPLACED WITH SERVICEABLE UNITS. WE WOULD LIKE TO SUGGEST OTHER OPERATORS INSPECT THESE RELAY BASES FOR CRACKS. (TC NR 20061114012) 2H72 4R3 RRTA14EA ATC14 6 CP871 20070125001182007012500118SO 2007 1 25 CA061115001 220061115G8500 UNKNOWN DIAMONDA20 DA20C1 2990001GL CONT O240 IO240B 17063SO SNSNCHW69EK W69EK63 EA ENGINE UNKNOWN W D RETURN TO BLOCK R PARTIAL RPM/PWR LOSS TXTAXI/GRND HDL 1 CA 138 (CAN) REPORTED DEFECT, ON APPLICATION OF FULL POWER, ENGINE WOULD ALMOST CUT-OUT, THEN CATCH AND ACHIEVE FULL POWER. THE AIRCRAFT HAD PREVIOUSLY BEEN SNAGGED FOR QUITING SHORTLY AFTER LANDING, ON OCT. 17TH, AT WHICH TIME THE FUEL SYSTEM HAD BEEN INSPECTED, AND ADJUSTED IAW SID 97-3C AND RELEASED. THEREFORE MFG WAS CONTACTED AND ELECTED TO SEND A TECH REP TO OUR FACILITIES AND REPLACED MECHANICAL FUEL PUMP, THROTTLE BODY, FUEL MANIFOLD, WITH NEW UNITS. COMPLETE FUEL SYSTEM WAS FLUSHED AND FUEL INJECTOR NOZZLES CLEANED. FUEL SYSTEM SET UP IAW SID97-3C AND AIRCRAFT RELEASED. (TC NR 20061115001) 1L71 3O3 ONTTA4CH E7SO 5 NTA4CH 20061213000752006121300075 2006 12 13 CA061115002 120060616G61208210263 CSD GARRTTTFE731TFE731* 01518WP PROPELLER MAKING METAL W O OTHER J WARNING INDICATION TXTAXI/GRND HDL 1 CA (CAN) S/N 2479220 UNIT OVERHAULED AT MFG. UNIT WAS INSTALLED ON ENGINE IN A TEST CELL AND WAS RETURNED WITH TSO: 0.0 AND REPORTED SNAG OF RESET PRESSURE TOO LOW, PART REJECTED. AFTER DISASSEMBLY AT OUR FACILITY IT WAS NOTICED THAT THE INTERNAL SHAFT ASSEMBLY WAS SCORING THE HOUSING, MAKING METAL AND PROGRESSING TOWARD SEIZURE AND POSSIBLE SHAFT SHEARING. ALTHOUGH THE CAUSE HAS NOT BEEN DETERMINED, OIL STARVATION IS SUSPECTED. UNIT HAS BEEN SENT TO (OEM) FOR A LABORATORY INVESTIGATION TO DETERMINE THE FAILURE ROOT CAUSE. RESULTS OF THE INVESTIGATION WILL FOLLOW. (TC NR 20061115002) 4 F E6WE 20061205000672006120500067EU 2006 12 5 CA061115004 120061112G3230005LG005B CONTROL UNIT AIRBUS330 A330243 3930330EU MLG MALFUNCTIONED W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA 16519 (CAN) DURING CLIMB, CREW RETRACTED THE LANDING GEAR AND THE LEFT HAND GEAR UNLOCK LIGHT REMAINED ILLUMINATED ALONG WITH ASSOCIATED ECAM NR 1 SYSTEM LT GEAR TRIANGLE AND INTERMITTENT NOSE GEAR UNLOCK LIGHT. THE FLIGHT CREW ELECTED TO DIVERT INTO A MAIN MAINTENANCE BASE FOR RECTIFICATION OF THE FAULT. RECTIFICATION; NR 1 LGCIU REPLACED. 2L72 4F RTA46NM 20061205000792006120500079WP 2006 12 5 CA061115005 220061106G7314307085063 PUMP LEAR 35 35LEAR 5170600CE GARRTTTFE731TFE731* 01518WP LT ENGINE FUEL FAILED W C ABORTED TAKEOFF XJ ENGINE FLAMEOUT WARNING INDICATION TOTAKEOFF 1 CA 9218 (CAN) AIRCRAFT WAS CLEARED FOR T/O. POWER WAS ADVANCED TO 93.5% N1 ON BOTH ENGINES. APPROXIMATELY 1 SECOND LATER LT ENGINE FAILED. T/O WAS REJECTED. AME TROUBLESOT THE SNAG AND DISCOVERED THAT THE LT ENGINE FUEL PUMP PRESSURE WAS NOT WITHIN ACCEPTABLE LIMITS. FUEL PUMP AND FUEL CONTROL UNIT REPLACED. 2L72 4F4 F A10CE E6WE 20070125001192007012500119SO 2007 1 25 CA061115006 120061114G55114653003 RIB PIPER PA31T PA31T 7103124SO PWA PT6 PT6A28 EA HARTZLHCB3T HCB3TN3 GL HORIZONTAL STAB CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 407 (CAN) DURING AN EVENT NR 1 INSPECTION THE LT HORIZONTAL STABILIZER OB RIB WAS FOUND CRACKED WHERE THE ELEVATOR OB HINGE ATTACH POINT IS. THE RIB WAS REPLACED. (TC NR 20061115006) 1L72 3T4 T A8EA E4EA 6 CP15EA 20070125001212007012500121SW 2007 1 25 CA061115007 120061101G5330 SKIN BELL 206 206B 1181511SW ALLSN 250C 250C20B 03013GL FUSELAGE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 14725 (CAN) DURING SCHEDULED MAINTENANCE, IN COMPLIANCE WITH CF-91-35 (CABIN ROOF BOXBEAM INSPECTION), A CRACK WAS DISCOVERED IN THE BOXBEAM LOWER SKIN ORIGINATING FROM AN INSPECTION PANEL CUT-OUT RIVET HOLE. THIS SKIN WAS CRACKED ACROSS THE RIVET HOLE ABOUT 1.25 INCHES IN EACH DIRECTION. (TC NR 20061115007) 1G71 3U3 U H2SW E4CE 20061205000712006120500071EA 2006 12 5 CA061116001 120061109G5610NP1393226 WINDOW CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE COCKPIT CRACKED W A UNSCHED LANDING O OTHER CRCRUISE 1 CA 11003 (CAN) AIRPLANE DIVERTED FOUND: RT SIDE-WINDOW CRACKED. RT SIDE WINDOW REMOVED ACC.AMM. RT SIDEWINDOW INSTALLED ACC AMM 56-12-01-400-801. CABIN PRESS TEST PERF,. OK 2L72 4F4 FRTA21EA E15NE 20061205000782006120500078EA 2006 12 5 CA061116002 120061106G5610NP139321002 WINDSHIELD CNDAIRCL600 CL6002C10 1390015EA GE CF34 CF348C1 NE COCKPIT CRACKED W A UNSCHED LANDING O OTHER CRCRUISE 1 CA (CAN) NOTIFED BY SOC (OPERATIONS) THAT AIRCRAFT WAS DIVERTING TO IND DUE TO CAPT FWD WINDSHIELD CRACKED AT 39,000 FEET ON OUTER PLY.  C/A - RAR CAPT W/S IAW CRJ 700 AMM 56-11-01 OPS CHECK LEAK CHECK GOOD. 2L72 4F4 FRTA21EA EOOO63EN 20061205000572006120500057EA 2006 12 5 CA061116003 120061116G5712600911545 BULKHEAD CNDAIRCL600 CL600* EA GE CF34 CF343A 30015NE BS 559 CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) BULKHEAD STRUCTURE AT STATION 559.00 CRACKED ON TWO AILERON MIXER (P/N 600-91154-5) ATTACHMENTS BOLTS. A/C HOURS:25688 A/C CYCLES:30488 2L72 4F4 FRTA21EA E15NE 20061205000692006120500069EU 2006 12 5 CA061116004 120061110G2497 CABLE AEROSPATR42 ATR42300 8680920EU PWA 120 PW120 NE HAMSTD14SF 14SF5 NE DC GENERATOR ARCED W O OTHER B SMOKE/FUMES/ODORS/SPARKS TXTAXI/GRND HDL 1 CA (CAN) ON START UP THE NR 2 STARTER GENERATOR `PLUS` CABLE ARCED THROUGH A FEW INCHES FROM THE CONNECTION AT THE STARTER.THE CABLE WAS COMPLETELY SEVERED AND THE ADJACENT CONDUCTORS WERE DAMAGED. THE NR 2 GENERATOR, AFFECTED CONDUCTORS AND THE INVERTER WERE REPLACED AND THE AIRCRAFT RETURNED TO BASE WHERE ADDITION ASSESSMENT IS ON GOING. 2H72 4T4 TRTA53EU E20NE 6 CP7NE 20061205000622006120500062NM 2006 12 5 CA061116005 120061113G75408209074 SWITCH BOMBDRDHC8 DHC8402 1390042NM RT NACELLE FAILED W D RETURN TO BLOCK J WARNING INDICATION TXTAXI/GRND HDL 1 CA 135 135 (CAN) BLEED HOT CAUTION NR 2 CAME ON. CDS INTEREGATION FAULT CODE 1701. RIGHT BLEED OVERTEMPERATURE SWITCH FLAGGED. REPLACE SWITCH. SERIAL NUMBER 0781. 2H72 4T RTA13NM 20070125001242007012500124CE 2007 1 25 CA061116006 120061116G53301014302051 SKIN BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA HARTZLHCB3T HCB3TN3 GL BS 251 CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) CABIN BOTTOM SKIN FOUND CRACKED ADJACENT TO ROTATING BEACON DOME MOUNTING. REPAIR DRAWING REQUESTED. (TC NR 20061116006) 1L72 4T4 T A24CE E4EA 6 CP15EA 20070125001272007012500127SW 2007 1 25 CA061117001 120061103G73342060615357 TRANSDUCER BELL 206 206L 1181522SW ALLSN 250C 250C20R2 GL FUEL PRESSURE READS LOW W K NONE N FALSE WARNING ININSP/MAINT 1 CA (CAN) UNDER READING FUEL PRESSURE. REMOVED AND INSTALLED REPLACEMENT PRESSURE TRANSDUCER PN BSE 206-30G SN2617-1-251 (TC NR 20061117001) 1G71 3U3 U H2SW E4CE 20080306002732008030600273SO 2008 3 6 CA061117002 220060921G85604707829003R CONTROLLER CESSNA206 TU206A 2073318CE CONT O520 TSIO520C 17040SO HARTZLHCC3Y PHCC3YF1 GL OIL PRESSURE FAILED W C ABORTED TAKEOFF R PARTIAL RPM/PWR LOSS TOTAKEOFF 1 CA 1350 (CAN) ERRATIC MANIFOLD PRESSURE DUE TO CONTROLLER FAILURE TO REGULATE OIL PRESSURE FROM WASTEGATE (TC NR 20061117002) 1H71 3O3 O A4CE E8CE 5 CP25EA 20070808001222007080800122CE 2007 8 8 CA061117003 120061116G57538005T20062 DOUBLER CESSNA340 340A 2076405CE CONT O520 TSIO520NB 17040SO MCAULY3AF34C3AF34C* GL TE FLAP MISINSTALLED W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA 1324 (CAN) DURING A ROUTINE INSPECTION, DISCOVERED LT AND RT WING RIBS AT STA 117.48 TO BE CONFLICTING WITH THE RIB AT SIMILAR LOCATION WHEN FLAPS ARE RETRACTED. AFTER INSPECTION, FOUND THAT THE SPOILER DOUBLER INSTALLED IN 1995 WAS THE WRONG DIMENSION ALLOWING WING RIB TO BE POSITIONED INCORRECTLY. ON FURTHER INVESTIGATION FOUND THE TEMPLATE NR 8005T AND THE INSTALLATION INSTRUCTIONS NR SP8000 SUPPLIED WITH THE STC SA4948NM TO BE CONTRADICTING EACH OTHER IN RESPECT TO THE NEW LOCATION OF THE WING RIB. IF ONE OF THE FLAPS BECAME INOPERATIVE DUE TO THE FACT THAT THE RIBS HOOKED ON EACH OTHER. (TC NR 20061117003) 1L72 3O3 O 3A25 E8CE 5 CP22EA 20061205000842006120500084EA 2006 12 5 CA061117004 220061104G8530SL36006WA1 CYLINDER HEAD BEECH 95 95 1153402CE LYC O360 IO360B1B 41514EA ENGINE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 1989 (CAN) DURING A ROUTINE 100 HOUR INSPECTION A CRACK WAS FOUND ON THE RH ENGINE #4 CYLINDER STARTING AT THE TOP SPARK PLUG HOLE AND CONTINUING DOWN TO THE EXHAUST PORT. THE CYLINDER WAS REMOVED AND REPLACED. (TC# 20061117004) 1L72 3O3 O 3A16 1E10 20061205000822006120500082NM 2006 12 5 CA061117005 120061106G322069601002 SUPPORT BOEING737 737200 1384453NM PWA JT8 JT8D17 52049NE MLG CRACKED W O OTHER O OTHER TXTAXI/GRND HDL 1 CA (CAN) ON WALK AROUND AFTER LANDING FOUND CENTER SUPPORT ASSY OF GRAVEL DEFLECTOR CRACKED. CENTER SUPPORT ASSY CRACK REPAIRED. ASSEMBLY SUPPORT FITTING P/N69-60100-2 REPLACED AIRCRAFT RETURNED TO SERVICE. 2L72 4F4 F A16WE E2EA 20061205000632006120500063EA 2006 12 5 CA061117006 120061113G499038004882 APU CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE OVERSERVICED W O OTHER BJ SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION DEDESCENT 1 CA 1787717877 (CAN) APPROXIMATELY 10 MINUTES FROM DESTINATION, AIRCRAFT DECLARED AN EMERGENCY DUE TO SMOKE IN THE LAVATORY. AIRCRAFT WAS DESCENDING THROUGH 5,000 FT WHEN THE BLEEDS WERE SWITCHED FROM ENGINES TO APU. WITHIN A SHORT PERIOD OF TIME A BURNT OIL SMELL WAS OBSERVED IN THE CABIN, AND THE LAV SMOKE DETECTOR WAS GOING OFF. THE CREW ALSO RECEIVED A "TOILET SMOKE" CAUTION MESSAGE. CREW REQUESTED EMERGENCY SERVICES BE ALERTED FOR ARRIVAL. SHORTLY THEREAFTER THE SMOKE INDICATION WENT OUT. FLIGHT LANDED SAFELY. MAINTENANCE INVESTIGATED AND FOUND THE APU OVER SERVICED. EXCESS OIL WAS DRAINED TO AN ACCEPTABLE LEVEL, AND LT & RT COALESCER BAGS P/N 753689-3 REPLACED IN ACCORDANCE WITH THE AMM 21-51. AIRCRAFT WAS THEN RUN ON A2L72 4F4 FRTA21EA E15NE 20070808001232007080800123EU 2007 8 8 CA061117007 120061102G8011A2042C PDU SAAB SF340 SF340A 7850100EU GE CT7TP CT75A2 30030NE ROTOL R389 R3894123F25 NE LT START RELAY FAILED W K NONE O OTHER ININSP/MAINT 1 CA 340A019 (CAN) WHEN GROUND POWER WAS ATTACHED TO THE AIRCRAFT THE LT ENGINE BEGAN AN UNCOMMANDED START SEQUENCE. THE FAULT WAS TRACED TO THE LT STARTER RELAY CONTACTS LOCATED IN THE LT POWER DISTRIBUTION UNIT (PDU). THE PDU WAS REPLACED AND THE AIRCRAFT OPERATED NORMALLY. (TC NR 20061117007) 2L72 4T4 TRTA52EU E8NE6 6 CP30NE 20061205000552006120500055NE 2006 12 5 CA061118001 220061117G7230 ENGINE CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE NR 1 BIRD INGESTION W A UNSCHED LANDING CEJF.O.D. VIBRATION/BUFFET WARNING INDICATION CLCLIMB 1 CA (CAN) AFTER GEAR-UP SELECTION THE AIRCRAFT ENCOUNTERED A VIBRATION, FELT THROUGHOUT ENTIRE PLANE,THAT WOULD INCRESE/DECREASE WITH THROTTLE MOVEMENT. AIRCRAFT RETURNED TO THE ORIGINATING DEPARTURE STATION AND LANDED SAFELY. MAINTENANCE FOUND NR 1 ENGINE FAN BLADES DAMAGED & BIRD REMAINS ON OIL COOLER, DUE TO A LARGE BIRD INGESTION. 2L72 4F4 FRTA21EA E15NE 20070125001292007012500129SW 2007 1 25 CA061120001 120061104G7333205061635005 SWITCH BELL 206 206L 1181522SW ALLSN 250C 250C20R2 GL FUEL FLOW LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) REMOVED LT FUEL FLOW SWITCH DUE TO LEAKING. INSTALLED FUEL FLOW SWITCH PN 205-061-635-005 SN 9607 (TC NR 20061120001). 1G71 3U3 U H2SW E4CE 20070125001312007012500131SO 2007 1 25 CA061120002 220060930G73235038901029 GOVERNOR BEECH 58 58 1152740CE CONT O550 IO550C SO ENGINE SEPARATED W A UNSCHED LANDING F FLT CONT AFFECTED LDLANDING 1 CA 1121 (CAN) SNAS: ENGINE GOVERNOR CONTROL NO RESPONSE. FOUND LT GOVERNOR CABLE END, SEPARATE FROM CRIMPED END FILET ATTACHED TO ROD END. (TC NR 20061120002) 1L72 3O3 O 3A16 E3SO 20070125001322007012500132SO 2007 1 25 CA061120003 120061115G270062701153 CONTROL CABLE PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA HARTZLHCC2Y HCC2YR2 GL STABILATOR SEVERED W A UNSCHED LANDING F FLT CONT AFFECTED CRCRUISE 1 CA (CAN) PILOT REPORTED LOSS OF EFFECTIVE ELEVATOR CONTROL DURING ROUTINE TRAINING FLIGHT. AIRCRAFT RETURNED TO BASE WITH STABILATOR CONTROL MANAGED MAINLY BY STABILATOR TRIM SYSTEM. AIRCRAFT LANDED SAFELY. INITIAL INSPECTION OF STABILATOR SYSTEM CONFIRMED LIMITED RESPONSE TO CONTROL YOKE MOVEMENT. FURTHER INSPECTION OF CABLES REVEALED THAT THE SWAGED END OF THE AFT LOWER CABLE WAS BROKEN AND SYSTEM WAS HELD TOGETHER BY TURNBUCKLE SAFETY LOCK WIRE. AFFECTED CABLE HAS BEEN REMOVED FOR FURTHER INSPECTION AND REPLACEMENT. CABLE DEFECT LOCATED BETWEEN FUSELAGE STA: 156.00 AND 191.00. PART TOTAL TIME IS UNKNOWN. AIRCRAFT TOTAL TIME IS 6593.3 HRS. (TC NR 20061120003) 1L72 3O3 O A19S0 E286 5 CP920 20061205000372006120500037NE 2006 12 5 CA061120005 220061119G72304114T15P02 FAN BLADE CNDAIRCL600 CL600* EA GE CF34 CF348E5 30015NE ENGINE BENT W O OTHER C F.O.D. APAPPROACH 1 CA 4477 182 194301 (CAN) ON APPROACH CREW SAW LARGE WHITE BIRD , FELT AND HEARD THUMP ON LEFT SIDE OF AIRCRAFT. MAINTENANCE INSPECTION FOUND #1 ENGINE INLET BYPASS FAN BLADES POSITIONS 1 THRU 5 DAMAGED AND BENT. BORESCOPE OF ENGINE COMPRESSOR FOUND NO OTHER DAMAGE. AIRCRAFT WILL BE RETURNED TO SERVICE AFTER BLADE REPLACEMENT AND SATISFACTORY GROUND RUNS. (TC# 20061120005) 2L72 4F4 FRTA21EA E00063EN 20080124003212008012400321SW 2008 1 24 CA061120006 120061120G272041621L RUDDER PEDAL BBAVIA7 7GCBC 1220601SW LYC O320 O320A2D 41508EA SNSNCH74D 74DM EA COCKPIT CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 1739 (CAN) DURING REPLACEMENT OF THE FUEL SHUTOFF VALVE THE LT FRONT RUDDER/BRAKE PEDAL WAS FOUND CRACKED BETWEEN THE BRAKE PEDAL UPRIGHT AND THE OB PEDAL HINGE. THE DEFECT APPEARS TO BE CAUSED BY BRAKING FORCES APPLIED BY THE FLIGHT INSTRUCTOR IN THE REAR SEAT, THE LINK ROD AND BELLCRANK ON THE FRONT PEDAL TWIST THE PEDAL TO ACTUATE THE MASTER CYLINDERS, LOCATED FORWARD OF THE FRONT PEDALS. THE TWISTING BENDS AND CRACKS THE PEDAL. THIS IS THE OLD-STYLE PEDAL. THE NEWER STYLE IS PLATE-SHAPED RATHER THAN TEE-SHAPED AND SHOULD BE MORE RESISTANT TO THE TWISTING FORCES. (TC NR 20061120006) 1H71 3O3 ONCA759 E274 5 NP88614 20070125001332007012500133EU 2007 1 25 CA061120007 120061117G6310350A35105901 COUPLING SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1D1 NE M/R DRIVESHAFT CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING 1000 HR INSPECTION DISC COUPLING FOUND CRACKED. 1G71 3U3 U H9EU E19EU 20061205000562006120500056NE 2006 12 5 CA061120008 320061117G611178229911 SPACER HAMSTD AEROSPATR42 ATR42300 8680920EU PWA 120 PW120 NE HAMSTD14SF 14SF5 NE PROPELLER TORN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) PROPELLER BLADE INSPECTED AND FOUND TIGHT IN HUB. INVESTIGATION REVEALED PROP BLADE SPACER HAD FAILED. PROP BLADE REMOVED AND NEW SPACER INSTALLED. PROP BLADE REINSTALLED AND GROUND RUN CHECKED SERVICEABLE. 2H72 4T4 TRTA53EU E20NE 6 CP7NE 20061205000392006120500039NE 2006 12 5 CA061120009 220061118G7230652244143 DUCT BOEING727 727223 1384074NM PWA JT8 JT8D9 52048NE 13TH STAGE SADDLRUPTURED W E ENGINE SHUTDOWN RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CLCLIMB 1 CA (CAN) ENROUTE TO DESTINATION, #2 ENGINE FIRE WARNING. CHECKLIST ACCOMPLISHED, ENGINE SHUTDOWN. 13TH STAGE SADDLE DUCT FOUND RUPTURED, REPLACED AND AIRCRAFT RETURNED TO SERVICE. (TC# 20061120009) 2L73 4F4 F A3WE E2EA 20061205000352006120500035NE 2006 12 5 CA061121001 220061119G7200 ENGINE AIRBUS310 A310304 3930339EU GE CF6 CF680C2A5 NE NR 2 FAILED W A UNSCHED LANDING BJ SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION CLCLIMB 1 CA 259454946 690285 (CAN) AFTER TAKE OFF AND DURING LEVEL AT 40,000 FT CREW GOT ECAM MESSAGE MIN EQUIPMENT SMOKE WITH OVERHEAD WITH OVERHEAD LIGHT ON AND ODOR IN THE CABIN AND COCKPIT. CREW DECIDED TO RETURN BACK TO THE AIRPORT. QRH PROCEDURES WERE FOLLOWED. BOROSCOPE CARRIED OUT ON BOTH ENGINES. FOUND EVIDENCE OF OIL IN NR 2 ENGINE COMPRESSOR. NR 2 ENGINE REPLACED. 2L72 4F4 FRTA35EU E13NE 20070125001352007012500135SW 2007 1 25 CA061121002 120060826G6320206040156101 MAGNETIC SEAL BELL 206 206B 1181511SW ALLSN 250C 250C20 03013GL M/R GEARBOX LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) MAIN ROTOR GEARBOX MAGNETIC SEAL HAS EXCESSIVE LEAKAGE FROM MAIN INPUT SEAL. (TC NR 20061121002) 1G71 3U3 U H2SW E4CE 20061205000322006120500032NM 2006 12 5 CA061121003 120061120G572082920010255 LINE DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE WING SPLIT W K NONE O OTHER ININSP/MAINT 1 CA (CAN) WHILE CARRYING OUT ZONAL INSPECTION 263 AND 264, BOTH WING ROOT DRAIN LINES WERE FOUND BLOCKED AT THE BELLY DRAINS. THE ACCUMULATED WATER IN THE DRAIN LINE IN TURN FROZE AND SPLIT THE DRAIN LINE CAUSING PRESSURIZATION LEAK AND WATER AND SKYDROL TO LEAK IN THE BELLY. (TC# 20061121003) 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20061205000312006120500031SW 2006 12 5 CA061122001 120061120G81204709549001 WASTEGATE VALVE RKWELL700 700 7630520SW LYC O540 TIO540R2AD 41532EA FAILED W D RETURN TO BLOCK RJ PARTIAL RPM/PWR LOSS WARNING INDICATION TXTAXI/GRND HDL 1 CA 2124 (CAN) WHEN THE PILOTS APPLIED MAX POWER FOR TAKE-OFF THE LH ENGINE WOULD ONLY PRODUCE 30 INCHES M.P. THE TAKE-OFF WAS STOPPED AND THE AIRCRAFT RETURNED TO CHALKS. AFTER FOUND NO FAULTS. THE TURBO WHEEL WAS ABLE TO TURN FREELY. THE WASTE GATE WAS CHANGED OUT. REMOVED S/N WC-60101 AND INSTALLED S/N ML0144. THE AIRCRAFT WAS GROUND RUN AND THE MANIFOLD PRESSURE WAS AT MAX 44 INCHES AS REQUIRED. SYSTEMS CHECKED SERVICEABLE. (TC# 20061122001) 1L72 3O3 O A12SW E14EA 20070125001362007012500136SW 2007 1 25 CA061122002 120061103G243503600923 BEARING BELL 206 206B 1181511SW ALLSN 250C 250C20 03013GL STARTER GEN FAILED W O OTHER O OTHER NRNOT REPORTED 1 CA 167 167 13955 (CAN) CUSTOMER REPORTED BEARING FAILURE ON MAIN SHAFT OF STARTER/GENERATOR. BEARING CAGE CAME APART. UPON INSPECTION. IT WAS FOUND THE BEARING CAGE WAS NON-EXISTANT. WE CONTACTED OUR SUPPLIER. (TC NR 20061122002) 1G71 3U3 U H2SW E4CE 20070125001422007012500142SO 2007 1 25 CA061122003 120061121G30972937102 TERMINAL PIPER PA31T PA31T 7103124SO PWA PT6 PT6A28 EA HARTZLHCB3T HCB3TN3 GL DE ICE SYSTEM BURNED W O OTHER L NO TEST CRCRUISE 1 CA (CAN) PILOT REPORTED PROP AND ENGINE INLET BOOTS DE-ICE SYSTEM U/S ON LT ENGINE. SYSTEM HAS BEEN INSPECTED. FOUND NO POWER FROM CB TO MAIN POWER RELAY. PLATE ASSEMBLY CIRCUIT PROTECTOR FORWARD MOUNTING LT REMOVED AND DISCOVERED THAT WIRE FROM CB BURNED OUT AT TERMINAL CONNECTION DUE OVERHEAT OF TERMINAL. OVERHEATING OF TERMINAL APPEARED TO BE DUE CORROSION OF TERMINAL AND LOST OF CONDUCTIVITY THAT INCREASE THE RESISTANCE AND GENERATE ADDITIONAL HEAT. (TC NR 20061122003) 1L72 3T4 T A8EA E4EA 6 CP15EA 20061205000282006120500028NE 2006 12 5 CA061122004 220061122G7250 GAS GENERATOR PWA 120 PW123D 52152NE ENGINE CRACKED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) SEE REPORT ATTACHED REGARDING SMOKE IN THE EXHAUST DURING ENGINE SHUTDOWN. ENGINE S/N AG0060 DISASSEMBLY OF ENGINE REVEALED LARGE AMOUNT OF COKED OIL IN THE TURBINE SUPPORT CASE (NR 5 BEARING VENT TUBE AREA), WHICH IS TYPICALLY INDICATIVE OF CRACKS IN THE NR 5 BEARING SUPPORT AREA OF THE GAS GENERATOR CASE. OIL FROM THESE CRACKS CONTAMINATED THE P3 AIR SYSTEM. (TC# 20061122004) 4 T E20NE 20070125001442007012500144SO 2007 1 25 CA061122006 120061106G321167042013 TRUNNION PIPER PA44 PA44180 7104402SO LYC O360 LO360E1A6 41514EA HARTZLHCC2Y HCC2YR2 GL MLG CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 8804 (CAN) AT INSPECTION NOTICED CRACK RIGHT THROUGH TRUNNION ASSY 67042-013. 1L72 3O3 O A19S0 E286 5 CP920 20061205000682006120500068 2006 12 5 CA061122007 420061111G34215040002902 INDICATOR BRAERO748 HS7482A 4231001EU RROYCEDART DART5342 EU COCKPIT FAILED W A UNSCHED LANDING O OTHER CLCLIMB 1 CA (CAN) DEPARTING THE CAPT`S HORIZON FAILED DURING TAKE-OFF. THE AIRCRAFT RETURNED TO POINT OF DEPARTURE WITHOUT INCIDENT. MAINTENANCE REPLACED THE GYRO AND THE AIRCRAFT WAS RETURNED TO SERVICE. (TC# 20061122007) 2L72 3T4 T A24EU A196 20061205000302006120500030EA 2006 12 5 CA061122008 120061121G2750NA FLAP SYSTEM CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE TE FLAPS JAMMED W O OTHER FJ FLT CONT AFFECTED WARNING INDICATION CLCLIMB 1 CA 1072710727 (CAN) DURING MISSED APPROACH WHEN FLAP RETRACTION SELECTED, FLAPS REMAINED AT FULL 45DEG EXTENSION. CREW RECEIVED FLAP FAIL MESSAGE. DUE TO WEATHER CONDITIONS AIRCRAFT DIVERTED TO ALTERNATE AIRPORT WITH FLAPS REMAINING EXTENDED AT 45DEG. IN-FLIGHT FLAP RE-SET PROCEDURE CARRIED OUT WITH NO SATISFACTORY RESULT. AIRCRAFT LANDED NORMALLY AT ALTERNATE AIRPORT. AFTER ARRIVAL ON GROUND AIRCRAFT ELECTRICAL POWERED DOWN AND THEN RE-POWERED. FLAP SYSTEM FUNCTIONED NORMALLY. AIRCRAFT POSITIONED TO MAINTENANCE BASE FOR FURTHER INVESTIGATION. (TC# 20061122008) 2L72 4F4 FRTA21EA E15NE 20070808001242007080800124EA 2007 8 8 CA061123001 120061123G249721551226808 WIRE CNDAIRCL215 CL2151A10 1900320EA PWA R2800 CA3 52026NE HAMSTD43E 43E60 NE DC POWER SYS CHAFED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DC OVERHEAD PANEL WIRES CHAFING ON AIRCRAFT STRUCTURE. (TC NR 20061123001) 2H72 4R4 RRTA14EA E231 6 CP871 20061205000232006120500023NE 2006 12 5 CA061123002 220061123G7200PW121 ENGINE PWA PW121 PW121 52124NE MAKING METAL W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) METAL CONTAMINATION OF TURBOMACHINE OIL SYSTEMS DETECTED VIA TREND MONITORING ANALYSIS. 4 T E20NE 20061205000242006120500024EA 2006 12 5 CA061123003 220061123G7230 IMPELLER PWA PT6 PT6A50 52043EA ENGINE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) "IMPACT DAMAGE AND A CRACKED IMPELLER". A CRACK IN THE OUTER IMPELLER WAS FOUND. (TC# 20061123003) 4 T E4EA 20080306002782008030600278EA 2008 3 6 CA061123005 220061121G7322055211313 FLAPPER VALVE CESSNA CESSNA172 172N 2072434CE LYC O320 O320H2AD 41508EA MCAULY1C160 1C160DTM GL CARB HEAT BOX WORN W K NONE O OTHER ININSP/MAINT 1 CA 705 705 (CAN) DURING PROGRESSIVE CARE OPERATION NR 2, INSP OF THE CARBURETOR HEAT BOX (P/N 05521644) REVEALED THAT THE 2 ALUMINUM RIVETS THAT HOLD THE FLAPPER DOOR TO THE ACTUATOR SHAFT WERE VERY CLOSE TO SHEARING OFF. IF THE ALUMINUM RIVETS DID SHEAR, AND THE AC WAS FLYING IN CARBURETOR ICING CONDITIONS, ENGINE FAILURE COULD OCCUR. THERE IS ALSO THE CONCERN OF PIECES OF RIVETS BEING INGESTED INTO THE ENGINE. THE CARB AIR BOX WAS PURCHASED NEW FROM MFG, INSTALLED 16 MONTHS AGO AND IN SERVICE ON THIS ENGINE FOR 704.7 HRS. NOT SO LONG AGO, MFG USED STEEL RIVETS INSTEAD OF ALUMINUM. THIS DID NOT SEEM TO BE A PROBLEM IN THE PAST WITH STEEL RIVETS. (TC NR 20061123005) 1H71 3O3 ONT3A12 E274 5 NP910 20070820000282007082000028CE 2007 8 20 CA061123006 120061120G5420085150047 CAP CESSNA414 414 2075908CE CONT O520 TSIO520N 17040SO MCAULY3AF32C3AF32C505 GL LT NACELLE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) CRACK NOTED AT LT NACELLE CANTED BULKHEAD CAP. CAP REPAIRED. (TC NR 20061123006) 1L72 3O3 ORTA7CE E8CE 5 CP22EA 20061205000272006120500027EA 2006 12 5 CA061123008 120061122G5610NP13932112 WINDSHIELD CNDAIRCL600 CL6002C10 1390015EA COCKPIT CRACKED W O OTHER O OTHER CRCRUISE 1 CA 7288 (CAN) RH WINDSHIELD CRACK WHILE IN CRUISE. (TC# 20061123008) 2L72 4F RTA21EA 20061205000252006120500025EA 2006 12 5 CA061124001 220061123G7230 COMPRESSOR PWA PT6 PT6A34 52043EA ENGINE DAMAGED W O OTHER O OTHER CRCRUISE 1 CA (CAN) ENGINE TEARDOWN RELATED TO AN IFSD AND A POSSIBLE COMPRESSOR FAILURE. TEARDOWN NOT YET CONCLUSIVE. IT WAS NOT A COMPRESSOR FAILURE BUT APPEARS TO BE FAILURE OF ONE OR MORE CT BLADES AND THEN CAUSED A STRUCTURAL FAILURE OF THE GAS GENERATOR CASE, WHICH THEN RESULTED IN COMPRESSOR DAMAGE. COMPRESSOR ROTOR WAS LOCKED UP BUT THE PT ROTOR WAS FREE TO ROTOATE. IT APPEARS TO BE UNECONOMICAL TO REPAIR THIS ENGINE. (TC# 20061124001) 4 T E4EA 20061205000262006120500026EU 2006 12 5 CA061124002 320061123G6197697070212 BUSS BAR R408 BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R4304 R4304* EU NR 1 PROP SHORTED W E ENGINE SHUTDOWN F FLT CONT AFFECTED CRCRUISE 1 CA 10 NA (CAN) NO.1 ENGINE SHUTDOWN DURING FLIGHT DUE PEC FAIL CAUTION LIGHT AND PROP SPEED AT 1060 RPM. FAULT CODES LH CH A/B 160 AND 162. MAYDAY CALLED AND A NORMAL LANDING PERFORMED. PAX DEBRIEFED DURING TAXING AND AFTER PARKING. MAINTENANCE DISPATCHED TO TROUBLE SHOOT. NOTE PROP ASSY ONLY INSTALLED LAST WEEK. TECHNICIAN FOUND PROP HEATER BUSBAR ASSEMBLY CHAFED BY NO.1 PROP MPU BRACKET. BUSBAR REPLACED AND BUSBAR/PICK-UP CLEARANCE CHECKED OK. ENGINE RUN, PROP RPM AND PROP DE-ICE CHECKED OK. (TC# 20061124002) 2H72 4T4 TRTA13NM E00062EN6 CP890 20070820000292007082000029EA 2007 8 20 CA061124003 120061123G2750 FLAP SYSTEM CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE TE FLAPS MALFUNCTIONED W O OTHER F FLT CONT AFFECTED APAPPROACH 1 CA 1115111151 (CAN) DURING APPROACH UPON INITIAL FLAP DOWN SELECTION, FLAP FAILED TO MOVE AND CREW RECEIVED (FLAP FAIL) MESSAGE ON EIACS. APPROACH CONTINUED AND NORMAL FLAPLESS LANDING CARRIED OUT. MAINTENANCE INSPECTION CARRIED OUT, NO EVIDENCE OF TWISTING, SKEWING OR DEFORMATIONS NOTED. FECU (FLAP ELECTRONIC CONTROL UNIT) CIRCUIT BREAKERS CYCLED IAW RE-SET PROCEDURE AND FLAPS FUNCTION CHECKED NORMAL OPERATIONS. (TC NR 20061124003) 2L72 4F4 FRTA21EA E15NE 20070820000302007082000030SW 2007 8 20 CA061124005 120061121G57532736041001 CHANNEL SWRNGNSA226 SA226TC 8780404SW GARRTTTPE331TPE33110UA 01514WP TE FLAP CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 19186 (CAN) DURING OVERHAUL OF THE RT FLAP ASSY, THE CENTER HINGE CHANNEL WAS REMOVED FOR REPLACEMENT AND WAS FOUND CRACKED BETWEEN (2) RIVET HOLES. THE CHANNEL HAS BEEN REPLACED. (TC NR 20061124005) 2L72 4T4 TRTA8SW E4WE 20061205000202006120500020CE 2006 12 5 CA061124006 120061124G3060 BOOT MCAULY B3D36C432 CESSNA206 T206H 2073303CE LYC O540 TIO540AJ1A EA MCAULY3D36C B3D36C432 GL PROPELLER DE-ICEFAILED W K NONE J WARNING INDICATION ININSP/MAINT 1 CA 294 030476 (CAN) DURING PHASE NR 2 INSPECTION IT WAS NOTED ON PRE-INSPECTION RUNUP THAT THE PROP DE-ICE WAS INOPERATIVE. INVESTIGATION REVEALED THAT 2 OF THE 3 DE-ICE BOOT LEADS WERE DEFECTIVE. NEW PARTS ORDERED. 1H71 3O3 ORTA4CE E14EA 5 CP58GL 20070131001022007013100102SW 2007 1 31 CA061124007 120061124G5531410009505 SPAR CAP GULSTM690TP 690 0141720SW GARRTTTPE331TPE3315251K NM HARTZLHCB3T HCB3TN5 GL VERTICAL STAB CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) CRACK FOUND IN LT HAND SPAR CAP 1.5 IN. FROM BOTTOM. (TC NR 20061124007) 1H72 3T4 T 2A4 E2WE 6 CP15EA 20070820000312007082000031CE 2007 8 20 CA061124008 120061124G32100541121497 SUPPORT CESSNA172 172K 2072430CE LYC O320 O320E2D 41508EA MCAULY1A175 1A175ATM GL MLG CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 18284 (CAN) AIRCRAFT BEING SERVICED FOR MFG CARE NR 4 (200-HOUR) INSPECTION AND CHANGED OVER TO SKIS. LT OB SUPPORT FOR LANDING GEAR WAS FOUND TO HAVE SEVERAL CRACKS. PART WAS REPLACED WITH NEW. AIRCRAFT IS OPERATED AS FLOATPLANE AND SKIPLANE FOR FLIGHT TRAINING. (TC NR 20061124008) 1H71 3O3 ONT3A12 E274 5 NP857 20061205000292006120500029NM 2006 12 5 CA061124009 120061121G561058935734 WINDOW BOEING737 737* NM CFMINTCFM567CFM567B22 13802NE COCKPIT DELAMINATED W K NONE O OTHER ININSP/MAINT 1 CA 13516 (CAN) ON NOV. 22, 2006 A/C 208 DURING INSPECTION OF THE NR 5 RT EYEBROW WINDOW IT WAS NOTED THAT THE NR 4 RT EYEBROW WINDOW WAS DELAMINATED BEYOND LIMITS. THE AIRCRAFT WAS REMOVED FROM SERVICE AND THE NR 4 RT EYEBROW WINDOW WAS REPLACED. BOEING IS AWARE OF THIS IN SERVICE ISSUE AND HAS INITIATED SERVICE RELATED PROBLEM (SRP) 56-0018. BOEING HAS ALSO ISSUED SERVICE BULLETIN 737-56-1017 TO PROVIDE 737NG OPERATORS WITH AN OPTION TO REPLACE THE NR 4 AND 5 WINDOWS WITH STRUCTURAL PLUGS. WESTJET IS PLANNING ON INCORPORATING THIS SERVICE BULLETIN. 2L72 4F4 FRTA16WE E00055EN 20070125001472007012500147SW 2007 1 25 CA061124010 120061120G6320204040353023 CASE BELL BELL 205 205A1 1181414SW TRANSMISSION CRACKED W K NONE K FLUID LOSS ININSP/MAINT 1 CA 109661520 ABT364 (CAN) CRACKING AT INPUT QUILL BOSS OF MAIN ROTOR TRANSMISSION. (TC NR 20061124010) 1G71 4U H1SW 20070125001482007012500148SW 2007 1 25 CA061124011 120061114G781023008052 COLLECTOR BELL 206 206L1 1182107SW ALLSN 250C 250C28B 03013GL ENGINE EXHAUST CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 1278 CAT28028 (CAN) DURING ENGINE MAINTENANCE, THE HORIZONTAL FIRESHIELD WAS REMOVED AND (2) CRACKS WERE NOTED AT THE 5 O`CLOCK AND 7 O`CLOCK POSTION IN THE EXHAUST COLLECTOR. TURBINE REMOVED REPAIRED RE-INSTALLED. (TC NR 20061124011) 1G71 3U3 U H2SW E1GL 20070125001502007012500150CE 2007 1 25 CA061127001 120061123G3230MC815AS1 CONTROLLER BEECH 100 A100 1152915CE PWA PT6 PT6A28 EA MCAULY4HFR344HFR34C762 NE MLG UNSERVICEABLE W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA (CAN) FLIGHT CREW REPORTED LANDING GEAR WOULD NOT RETRACT AFTER TAKE-OFF. AFTER TROUBLESHOOTING THE MOTOR CONTROLLER WAS FOUND UNSERVICEABLE. MOTOR CONTROLLER WAS REPLACED, GEAR SWINGS COMPLETED AND THE AIRCRAFT RETURNED TO SERVICE. THIS UNIT HAD 928 LANDINGS SINCE OVERHAUL; INSPECTION REQUIREMENTS ARE 8000 LANDING OVERHAUL AND 1000 LANDING POINT CHECK. 1L72 3T4 T A14CE E4EA 6 C3PNE 20070125001522007012500152CE 2007 1 25 CA061127002 120061126G3260 UNKNOWN BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE HARTZLHCE4A HCE4A3I NE MLG UNKNOWN W A UNSCHED LANDING N FALSE WARNING CLCLIMB 1 CA (CAN) AIRCRAFT DEPARTED, DURING CLIMB THE LANDING GEAR RED UNSAFE LIGHT ILLUMINATED. GEAR WAS CYCLED AND LIGHT WOULD NOT EXTINGUISH. GEAR WAS SELECTED DOWN AND (3) GREEN ILLUMINATED WITH NO RED HANDLE. CREW ELECTED TO RETURN TO MAINTENANCE. MAINTENANCE INSPECTED AND SWUNG GEAR WITHOUT FAULT. AIRCRAFT OPERATING WITHOUT FURTHER INSTANCE. WEATHER EXTREMELY COLD ON DAY OF OCCURRENCE. (TC NR 20061127002) 2L72 4T4 TRTA24CE E26NE 5 CP10NE 20061205000212006120500021EA 2006 12 5 CA061127003 120061123G5712600102211 RIB CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE LT WING CHAFED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) IN LEFT HAND WING TANK INBOARD BAY, STEAL BRAIDED FUEL LINE PART NUMBER 00624-AE7013343N0220 WAS FOUND CHAFING ON THE WING RIB STIFFENER PART NUMBER 600-10221-1. CHAFING OCCURRED APPROXIMATELY 9 1/2 INCHES FROM BOTTOM OF TANK. DAMAGE EXTENDS OVER AN AREA OF APPROXIMATELY 3/4 OF AN INCH WITH THE MAIN DAMAGE COVERING APPROXIMATELY 5/8 OF AN INCH INSIDE THE 3/4 INCH AREA. SEE ATTACHED PHOTOS. DAMAGE IS TAPERED FROM 0 INCHES TO APPROXIMATELY 0.120 INCHES AREA HAS NOT YET BEEN DRESSED SO FINAL DEPTH MEASUREMENTS ARE NOT AVAILABLE. (TC# 20061127003) 2L72 4F4 FRTA21EA E15NE 20080201000982008020100098SW 2008 2 1 CA061128001 120061124G2810206063688001 LINE BELL 206 206L 1181522SW ALLSN 25OC 250C20R GL FUEL SYSTEM LEAKING W O OTHER KB FLUID LOSS SMOKE/FUMES/ODORS/SPARKS NRNOT REPORTED 1 CA (CAN) DURING A SCHEDULED FLIGHT, FUEL FUMES WERE DETECTED IN REAR CABIN AREA. A/C RETURNED TO BASE WITH NO PROBLEMS NOTED. A/C INSPECTED AND FWD FUEL TANK VENT LINE FOUND WEEPING WHEN REAR TANK WAS FILLED TO CAPACITY. LINE REMOVED AND REPLACED. LINE INPECTED AND FOUND TO BE ORIGINAL FROM DATE OF A/C MFG 1975. RECOMMEND REPLACEMENT DATE OF FLEX HOSE BE ADDED TO MM. (TC NR 20061128001) 1G71 3U3 U H2SW E4CE 20061205000222006120500022 2006 12 5 CA061128002 420061123G3421ASN43 INDICATOR BRAERO748 HS7482A 4231001EU RROYCEDART DART5342 EU NR 1 HORIZON FAILED W A UNSCHED LANDING O OTHER CLCLIMB 1 CA 1459 (CAN) DURING DEPARTURE THE CAPTAINS HORIZON FAILED ON CLIMB OUT. THE AIRCRAFT RETURNED TO POINT OF DEPARTURE WITHOUT FURTHER PROBLEM. MAINTENANACE REPLACED THE NO1. GYRO AND THE AIRCARFT WAS RETURNED TO SERVICE. (TC# 20061128002) 2L72 3T4 T A24EU A196 20070125001532007012500153CE 2007 1 25 CA061128003 120061116G571220062 RIB CESSNA340 340A 2076405CE CONT O520 TSIO520NB 17040SO MCAULY3AF34C3AF34C* GL RT WING WRONG PART W O OTHER W INADEQUATE Q C NRNOT REPORTED 1 CA 1324 (CAN) DURING A ROUTINE INSPECTION DISCOVERED LT AND RT WING RIBS AT STATION 117.48 TO BE CONFLICTING WITH THE FLAP RIB AT SIMILAR LOCATION WHEN FLAPS ARE RETRACTED. AFTER INSPECTION FOUND THAT THE SPOILER DOUBLER INSTALLED IN 1995 WAS THE WRONG DIMENSION ALLOWING WING RIB TO BE POSITIONED INCORRECTLY. UPON FARTHER INVESTIGATION FOUND THE TEMPLATE NR 8005T AND THE INSTALLATION INSTRUCTIONS NR SP8000 SUPPLIED WITH THE STC SA4948NM TO BE CONTRADICTING EACH OTHER IN RESPECT TO THE NEW LOCATION OF THE WING RIB. THIS COULD BE VERY SERIOUS, IF ONE OF THE FLAPS BECAME INOPERATIVE DUE TO THE FACT THAT THE RIBS HOOKED ON EACH OTHER. (TC NR 20061128003) 1L72 3O3 O 3A25 E8CE 5 CP22EA 20080219001022008021900102SW 2008 2 19 CA061128004 120061117G5320206031202015 SUPPORT BELL 206031200 BELL 206 206B 1181511SW ALLSN 250C 250C20 03013GL FUSELAGE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 14060 (CAN) STRAP PN 206-031-200-076 WAS FOUND CRACKED AT INSPECTION. WHEN IT WAS REMOVED, SUPPORT PN 206-031-202-015 WAS ALSO FOUND CRACKED. BOTH WERE REPLACED IAW MFG INSTRUCTIONS. (TC NR 20061128004) 1G71 3U3 U H2SW E4CE 20061205000592006120500059EA 2006 12 5 CA061128005 220061115G7230 COMPRESSOR DHAV DHC6 DHC6100 2802610EA PWA PT6 PT6A20 52043EA NR 2 ENGINE DAMAGED W C ABORTED TAKEOFF YJ ENGINE STOPPAGE WARNING INDICATION TOTAKEOFF 1 CA 120997187 (CAN) ON POWER APPLICATION FOR TAKEOFF, THE #2 ENGINE ACCELERATED NORMALLY TO TAKEOFF POWER. AS THE AIRCRAFT BEGAN TO CLIMB ONTO THE STEP, THE F/O OBSERVED A FLASH OF LIGHT AND HEARD A BANG FROM THE ENGINE. THE TAKEOFF WAS REFECTED AND THE AIRCRAFT RETURNED TO THE DOCK. THE ENGINE WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE. INVESTIGATION REVEALED THAT THE COMPRESSOR SECTION OF THE ENGINE HAD FAILED. RESULTS OF THE TEARDOWN WILL BE FORTHCOMING. THIS ENGINE HAS BEEN OPERATING "ON CONDITION" SINCE PURCHASE IN 2002. (TC# 20061128005) 1H72 3T3 TRTA9EA E4EA 20080219001142008021900114CE 2008 2 19 CA061128008 120061120G243240576 BATTERY BEECH 200 B200 1152922CE PWA PT6 PT642A NE HARTZLHCB3T HCB3TN3 GL MAIN THERMAL RUNAWAY W H DEACTIVATE SYST/CIRCUITS MB OVER TEMP SMOKE/FUMES/ODORS/SPARKS ININSP/MAINT 1 CA 3112 55 (CAN) WHILE CONNECTED TO A GPU, DURING ROUTINE MAINTENANCE, THE TECHNICIANS NOTED SMOKE IN THE AREA OF THE BATTERY BOX COMPARTMENT. THE GPU WAS IMMEDIATELY DISCONNECTED, BATTERY POWER TURNED OFF AND THE BATTERY DISCONNECTED FROM THE AIRCRAFT BY REMOVAL OF THE ALCON CONNECTOR AT THE BATTERY. THE BATTERY HAD OVERHEATED AND WENT INTO A THERMAL RUNAWAY CONDITION. THE BATTERY WAS REPLACED AS WELL AND THE BATTERY CHARGE MONITORING PRINTED CIRCUIT CARD. (TC NR 20061128008) 1L72 4T4 T A24CE E4EA 6 CP15EA 20080219001202008021900120EA 2008 2 19 CA061129003 120061124G2710N025 MASTER LINK FOUND FBA FBA2C 3640102EA AILERON CONTROL DEFECTIVE W A UNSCHED LANDING F FLT CONT AFFECTED CRCRUISE 1 CA 31 (CAN) DURING FIGHT ID 2C3-30 THE MASTER LINK (N025) FELL OFF THE COPILOT’S AILERON CHAIN CAUSING A LOSS OF AILERON CONTROL FROM THE COPILOT’S SIDE. THE FLIGHT TEST ENGINEER WAS ABLE TO COLLECT ALL THE PIECES FROM THE MASTER LINK DURING THE FLIGHT HOLD AND THE CHAIN FROM JAMMING THE AILERON CONTROL FOR THE REST OF THE FLIGHT. THE PILOT WAS ABLE TO FLY AND LAND THE AC SAFELY WITHOUT USING THE AILERONS. THE AC IS AN EXPERIMENTAL AC IN A FLIGHT TEST PROGRAM, THIS MODEL USES THE SAME AILERON CONTROL SYS AS THE 2C1 AND 2C2 MODELS. BEING THE MFG WE HAVE INITIATED A MATERIAL REVIEW AND WILL BE ISSUING A SB. (TC NR 20061129003) 1H71 3O A7EA 20061205000042006120500004 2006 12 5 CA061129004 420061129G2210 CLAMP DHAV DHC6 DHC6300 2802606EA PWA PT6 PT6A27 52043EA BRIDLE CABLE DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) THIS DEFECT WAS ORIGINALLY IDENTIFIED IN THE SUBJECT AIRCRAFT FLIGHT LOG DATED OCTOBER 26, 2006.SUBSEQUENT INVESTIGATION BY OUR QUALITY ASSURANCE DEPARTMENT GENERATED THE REQUEST THAT A SDR BE FILED. THE AIRCRAFT ARRIVED IN OTTAWA FOR A SCHEDULED INSPECTION WITH A REPORTED AUTO-PILOT SNAG. " AUTO-PILOT U/S - SOMETIMES WON`T ENGAGE, WHEN IT DOES - IT YAWS & BANKS". ON SUBSEQUENT GROUND TESTING THE "BRIDAL CABLES" TO THE RUDDER SERVO-MOTOR WERE FOUND TO BE COMPLETELY WITHOUT TENSION. THE INSTALLATION WAS INSPECTED AND IT WAS DETERMINED THAT EVEN THOUGH THE BRIDLE CABLE TO RUDDER CABLE CLAMPS WERE INSTALLED AND TORQUED CORRECTLY THE WITNESS MARKS WERE NOT VISIBLE. IT IS BELIEVED THAT THE CLAMP SLIPPED ON THE1H72 3T4 TRTA9EA E4EA 20070125001542007012500154CE 2007 1 25 CA061129005 120061129G2820050011849 LINE CESSNA172 172S 2072439CE LYC IO360 IO360L2A EA MCAULY1A170 1A170* GL FUEL RETURN WORN W K NONE K FLUID LOSS ININSP/MAINT 1 CA 2810 (CAN) A FUEL LEAK WAS NOTED ON THE AIRCRAFT. UPON INSPECTION THE FUEL LINE BETWEEN THE FCU AND FUEL RESERVOIR WAS FOUND WORN. THE NOSE WHEEL STEERING ROD HAD BEEN RUBBING INTO THE LINE, AND WORN A GROOVE DEEP ENOUGH TO ALLOW FUEL TO LEAK. THE FUEL LINE IS ALUMINIUM, AND THE STEERING ROD IS STEEL. NO DAMAGE WAS NOTED ON THE STEERING ROD. (2) OF THESE TYPE OF AIRCRAFT ARE OPERATED, AND THE SECOND WILL BE INSPECTED FOR THE SAME TYPE OF PROBLEM. (TC NR 20061129005) 1H71 3O3 ONT3A12 1E10 5 NP857 20061205000052006120500005EA 2006 12 5 CA061129006 120061129G3220AW24VDU BEARING CNDAIRCL215 CL2151A10 1900320EA LT MLG CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) LT FOLDING STRUT LOWER BEARING CRACKED AT 4 PLACES. 2H72 4R RTA14EA 20061205000192006120500019NM 2006 12 5 CA061130001 120061124G27403994001013 ACTUATOR BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA PITCH TRIM FAILED W A UNSCHED LANDING F FLT CONT AFFECTED CLCLIMB 1 CA (CAN) PITCH TRIM CAUTION LIGHT AND AUTO TRIM FAIL MESSAGE APPEARED DURING CLIMB. AIRCRAFT RETURNED TO BASE. WIRING CHECKS CARRIED OUT BETWEEN THE FCECU AND PITCH TRIM ACTUATOR. (FCECU CODES 67, 63, E7 AND E3) ACTUATOR REPLACED. (TC# 20061130001) 2H72 4T4 TRTA13NM E00062EN 20061205000702006120500070CE 2006 12 5 CA061130002 120061109G5740122005311 ATTACH BRACKET CESSNA206 U206F 2073333CE CONT O520 IO520F 17032SO AILERON CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 8544 (CAN) AILERON ATTACH BRACKET CRACKED ON RADIUS LWR LT INBD FWD. PART REMOVED AND REPLACED WITH NEW P/N 1220053-17, ALL OTHER BRACKETS CHECKED NO CRACKS FOUND. 1H71 3O3 O A4CE E5CE 20061212000972006121200097EU 2006 12 12 CA061130003 120061001G261351533172 ELEMENT SAAB SF340 SF340A 7850100EU GE CT7TP CT75A2 30030NE ROTOL R389 R3894123F26 NE OVERTEMP CHAFED W E ENGINE SHUTDOWN N FALSE WARNING CLCLIMB 1 CA 45559 (CAN) AIRCRAFT RETURNED TO BASE SHORTLY AFTER DEPARTURE DUE TO A NR 2 BLEED AIR LEAK LIGHT ILLUMINATION DURING CLIMB OUT. THE BLEED AIR WAS SELECTED OFF BUT THE LIGHT REMAINED ILLUMINATED. IAW THE REQUIRED PROCEDURES THE ENGINE WAS SHUTDOWN AND THE AIRCRAFT LANDED UNEVENTFUL. INSPECTION OF THE AIRCRAFT BY MAINTENANCE DETERMINED THAT THE WARNING LIGHT WAS A FALSE INDICATION CAUSED BY A CHAFED BLEED AIR SENSE LINE IN THE AFT RT WING TRAILING EDGE. THE AFFECTED SENSE LINE WAS REPLACED. AN ADDITIONAL INSPECTION OF THIS AREA HAS BEEN ISSUED FOR COMPLETION ON THE ADJACENT SIDE OF THIS AIRCRAFT AS WELL AS A PLANNING CARD TO INSPECT THE SECOND AIRCRAFT IN THE FLEET. (TC NR 20061130003) 2L72 4T4 TRTA52EU E8NE6 6 CP30NE 20070125001552007012500155EA 2007 1 25 CA061130004 120061128G3234 RELEASE CABLE CNDAIRCL600 CL6002B19 1900309EA MLG LEVER DISLODGED W K NONE L NO TEST ININSP/MAINT 1 CA (CAN) DURING OF OPERATIONAL TEST OF THE LANDING GEAR MANUAL RELEASE SYSTEM THE NLG HAS NOT BEEN EXTENDED.AFTER INVESTIGATION FOUND THAT NLG RELEASE CABLE IS OUT OF PULLEY INSTALLED INSIDE OF THE LEVER P/N 600-85015-29. SEVERAL DAYS LATER INSPECTING ANOTHER AIRCRAFT. A SIMILAR SNAG HAS BEEN DETECTED. BOTH CABLES WERE REINSTALLED AND ADJUSTED IAW AMM,OPERATIONAL TEST CARRIED OUT AND FOUND SERVICEABLE. SEE ATTACHMENTS: LEVER AFFECTED IS ITEM NR 225 AND PULLEY IS ITEM NR 155. 2L72 4F RTA21EA 20070126003462007012600346NM 2007 1 26 CA061130005 120061126G4920APS2000 APU BOEING737 737522 138449FNM CFMINTCFM56 CFM563C 13802EU APU BAY DAMAGED W K NONE J WARNING INDICATION TXTAXI/GRND HDL 1 CA 1947782 (CAN) MFG WAS GETTING READY TO DEPART. ON ATTEMPTING TO START THE APU, THE FAULT LIGHT CAME ON AND THE APU FAILED TO START. THE ITEM WAS DEFERRED TO (MEL) MINIMUM EQUIPMENT LIST AND THE FLIGHT CONTINUED TO ITS DESTINATION. ON INVESTIGATION THERE WAS CONSIDERABLE DAMAGE TO THE GEARBOX AND STARTER SHAFT. THIS UNIT WAS REMOVED FOR A SIMILAR PROBLEM 82 HOURS PREVIOUSLY AND HAD BEEN OVERHAULED. ONCE A TEARDOWN REPORT IS RECEIVED, A FOLLOW UP WILL BE SUBMITTED. (TC NR 20061130005) 2L72 4F4 FRTA16WE E21EU 20061205000162006120500016EA 2006 12 5 CA061130006 120061128G29136619003 PUMP CNDAIRCL600 CL600* EA HYDRAULIC SYS LEAKING W A UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 CA 3569 (CAN) DURING CRUISE, THE NR 1 HYDRAULIC SYSTEM WAS DEPLETING AND WAS DOWN TO 20% OF CAPACITY. NO ASSOCIATED EICAS MESSAGE. AIRCRAFT WAS DIVERTED TO MAINTENANCE BASE.LEAK WAS FOUND AT NR 1 HYDRAULIC PUMP. PUMP WAS REPLACED. AIRCRAFT GROUND RUNS CARRIED OUT, SYSTEM REPLENISHED AND AIRCRAFT RETURNED TO SERVICE. 2L72 4F RTA21EA 20061205000022006120500002EA 2006 12 5 CA061201001 120061201G271021592315122 CONTROL CABLE CNDAIRCL215 CL2151A10 1900320EA AILERONS WORN W K NONE O OTHER ININSP/MAINT 1 CA 151 (CAN) LT AILERON CONTROL CABLE WORNED IN FAIRLEAD, ACCESS PANEL 740-2 (RT SIDE). CABLE NEEDS REPLACEMENT. THIS CABLE HAS BEEN REPLACED ON 2005-11-22 AND CUMULATED 151 HOURS FLYING TIME. 2H72 4R RTA14EA 20080219001222008021900122EA 2008 2 19 CA061201002 120061129G554133700K5 SPAR SCWZER 33700K3 SCWZERSG2 SGS233A 8051606EA RUDDER CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 3891 (CAN) DURING THE COMPANY 12 YEAR STRUCTURAL INSPECTION AND REPAIR PROGRAM (SIRP), A CRACK WAS FOUND IN ON RUDDER SPAR ON THE OUTER LT EDGE OF THE UPPER HINGE ATTACH POINT. LPI INSPECTION WAS USED TO VERIFY THE CRACK (TC NR 20061201002) 1K00 G2EA 20080219001252008021900125EA 2008 2 19 CA061201003 120061129G554133700K5 SPAR SCWZER 33700K3 SCWZERSG2 SGS233A 8051606EA RUDDER CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 4138 (CAN) DURING THE COMPANY 12 YEAR STRUCTURAL INSPECTION AND REPAIR PROGRAM (SIRP), A CRACK WAS FOUND ON THE RUDDER SPAR ON THE OUTER LT EDGE OF THE UPPER HINGE ATTACH POINT. (TC NR 20061201003) 1K00 G2EA 20080219001282008021900128SW 2008 2 19 CA061201004 120061124G2810714931L TANK BBAVIA8 8GCBC 1220803SW LYC O360 O360C2E 41514EA MCAULY1A200 1A200* GL WING CRACKED W K NONE K FLUID LOSS ININSP/MAINT 1 CA 2504 (CAN) AIRCRAFT HAD RETURNED TO MAINTENANCE FACILITY FOR WINTER STORAGE. FUEL STAINS WERE NOTICED ON THE BOTTOM OF THE WING NEAR THE TRAILING EDGE. LT IB TANK WAS REMOVED AND A 1.5 INCH CRACKED WAS FOUND ON THE RADIUS OF THE LATERAL RE-ENFORCEMENT INDENT OF TANK. (TC NR20061201004) 1H71 3O3 O A21CE E286 5 NP874 20070126003492007012600349EA 2007 1 26 CA061201006 120061104G2750 FLAP SYSTEM CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE WING MALFUNCTIONED W K NONE F FLT CONT AFFECTED APAPPROACH 1 CA 4750 4750 (CAN) DURING APPROACH WHEN FLAPS SELECTED TO 45 DEG , FLAPS REMAINED AT 30DEG AND (FLAP FAIL) MESSAGE ON EICAS, CONTINUED APPROACH AND NORMAL LANDING WITH FLAPS AT 30 DEG EXTENSION. MAINTENANCE CLEANED AND LUBRICATED FLAP DRIVE SHAFTS, FLAP ACTUATORS GREASED/PURGED. NO WATER INDICATIONS NOTED. FLAPS CYCLED NUMEROUS TIMES, NORMAL OPERATION AIRCRAFT RETURNED TO SERVICE. (TC NR 20061201006) 2L72 4F4 FRTA21EA E15NE 20070126003542007012600354EA 2007 1 26 CA061201007 120061101G2750 FLAP SYSTEM CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE WING MALFUNCTIONED W K NONE F FLT CONT AFFECTED APAPPROACH 1 CA 4760 4760 (CAN) DURING APPROACH FLAPS 20DEG SELECTED AND FLAPS AT 20DEG, WHEN 30DEG SELECTED FLAPS REMAINED AT 20DEG. NORMAL LANDING WITH FLAPS AT 20DEG. MAINTENANCE UNABLE TO DUPLICATE FAULT ON GROUND. AIRCRAFT FERRIED TO MAINTENANCE BASE. MAINTENANCE CARRIED OUT TORQUE CHECK OF FLAP DRIVE, NO FAULTS FOUND. OPERATIONAL TEST OF FLAPS CARRIED OUT WITH NO FAULTS FOUND. (TC NR 20061201007) 2L72 4F4 FRTA21EA E15NE 20061205000182006120500018NM 2006 12 5 CA061204001 120061128G5610NP15790213 WINDOW DHAV DHC8 DHC8* NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE COCKPIT FAILED W O OTHER O OTHER CRCRUISE 1 CA 32287 (CAN) DURING CRUISE, THE PILOT`S SIDE WINDOW OUTER PANE SHATTERED. AN UNEVENTFUL LANDING WAS CONDUCTED. ENGINEERING INSPECTED THE AIRCRAFT AFTER LANDING AND FOUND THE SIDE WINDOW OUTER PANE HAD SHATTERED. THE SIDE WINDOW ASSEMBLY WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. (TC# 20061204001) 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20061205000032006120500003EA 2006 12 5 CA061204002 120061130G3320336710 BALLAST DHAV DHC3 DHC3 2800202EA CABIN LIGHTS FAILED W K NONE H ELECT. POWER LOSS-50 PC ININSP/MAINT 1 CA 91 (CAN) ON POWER UP OF AIRCRAFT, CABIN LIGHT BALLASTS FAIL. THIS AIRCRAFT HAS HAD 10 BALLAST UNITS 3367-10 REPLACED. (TC# 20061204002) 1H71 3R A815 20070126003572007012600357WP 2007 1 26 CA061204003 220061204G7200TPE33112UHR ENGINE FRCHLDSA227 SA227DC 3377521SW GARRTTTPE331TPE33112UHR WP MCAULY4HFR344HFR34C652 NE MAKING METAL W K NONE J WARNING INDICATION ININSP/MAINT 1 CA (CAN) DURING ENGINE MAINTENANCE, IT WAS NOTICED THAT THE ENGINE OIL FILTER BYPASS PIN HAD POPPED. THE OIL FILTER WAS REMOVED AND INSPECTED. METAL CONTAMINATION WAS FOUND AND A SOAP SAMPLE WAS TAKEN. (TC NR 20061204003) 2L72 4T4 TRTA18SW E4WE 6 C3PNE 20070126003602007012600360EU 2007 1 26 CA061204004 120061128G21619599020135 CONTROL VALVE PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL CABIN TEMP MALFUNCTIONED W A UNSCHED LANDING O OTHER CLCLIMB 1 CA 1309413094 (CAN) AIRCRAFT WAS ON CLIMBOUT GOING THROUGH 6000 FEET WHEN ECS LIGHT CAME ON AND CABIN STARTED TO DE-PRESSURIZE. AIRCRAFT RETURNED TO RANKIN INLET WHERE MAINTENANCE DISCOVERED THAT TCA VALVE WAS STUCK IN THE FULL OPEN POSITION AND EXCESS HEAT TRIPPED THE SYSTEM OFF. TCA VALVE WAS REPLACED AND ECS SYSTEM CHECKED OK. (TC NR 20061204004) 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20070126003642007012600364EA 2007 1 26 CA061204005 120061201G3244362K821 TIRE CNDAIRCL600 CL600* EA NR 3 SEPARATED W O OTHER O OTHER LDLANDING 1 CA (CAN) NR 3 TIRE HAS THROWN A TREAD. CREW INSPECTED FLAP/ GEAR FOR DAMAGE, NO DAMAGE FOUND JUST RUBBER TRANSFER. SUSPECT IT HAPPENED ON ARRIVAL LAST NIGHT. BUT NOT DISCOVERED UNTIL IN THE AM. (TC NR 20061204005) 2L72 4F RTA21EA 20070126003702007012600370NE 2007 1 26 CA061204006 220061204G7230 BLADES PWA PT6 PT6A114A 52043NE ENGINE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 8000 4100 (CAN) SEE REPORT ATTACHED CRACK INDICATIONS WERE FOUND ON THE CT BLADES AT OVERHAUL. CRACKS WERE FATIGUE RELATED ON ALL THE CT BLADES. HOWEVER, THE ATTACHED REPORT STATES THAT THE CT BLADES DID NOT FAIL IN CREEP AS DETAILED IN MFG SILS, DUE TO OVERTEMP OR EXCEEDING ENGINE LIMITATIONS. FAILURE APPEARS TO BE DUE TO FLAP MODE VIBRATIONS. PLEASE REFER TO ATTACHED ENGINEERING REPORT FOR DETAILS. (TC NR 20061204006) 3 T E4EA 20070129001422007012900142NM 2007 1 29 CA061204007 120061201G2910MS219134 O-RING PARKERHANFIN9451693 DHAV DHC8 DHC8* NM HYDRAULIC SYS FAILED W O OTHER KJ FLUID LOSS WARNING INDICATION APAPPROACH 1 CA 16 16 0841 (CAN) WHILE ON APPROACH AT 10,000 FEET CREW NOTICED NR 2 HYD QTY WAS LOW. SHORTLY AFTER THAT THE NR 2 HYD ISO VLV CAUTION LIGHT CAME ON. ALTERNATE LANDING GEAR EXTENSION CARRIED OUT. FOUND THE O-RING FOR THE NR 4 PLUG-BLANKING ON THE NR 2 HYDRAULIC SYSTEM MANIFOLD-FILTER HAD FAILED. (TC NR 20061204007) 2H72 4T RTA13NM 20070129001452007012900145NM 2007 1 29 CA061204008 120061130G291082950010273 HYDRAULIC LINE DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE HYDRAULIC SYS DAMAGED W O OTHER J WARNING INDICATION CRCRUISE 1 CA 41474 (CAN) SMALL PIN HOLE IN BEND RADIUS OF NR DIAMETER 4 TUBE ASSY, NR 1 GROUNDING ITEM IS THE HYDRUALIC LINES ON THE DASH 8`S. (TC NR 20061204008) 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20070126003742007012600374NM 2007 1 26 CA061205001 120061204G321310300555 YOKE DHAV DHC8 DHC8301 1386003NM PWA PW120 PW123 NE HAMSTD14SF 14SF23 NE RT MLG CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING SCHEDULED A CHECK, RT MLG YOKE WAS FOUND TO HAVE A CRACKED FITTING AT THE AUX ACTUATOR ATTACH POINT. (TC NR 20061205001) 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20070129001482007012900148EA 2007 1 29 CA061205002 120061204G2750 FLAP CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE WING MALFUNCTIONED W O OTHER F FLT CONT AFFECTED APAPPROACH 1 CA (CAN) AT APROX 2500-3000 FT ON FINAL APPROACH THE CREW RECEIVED A FLAP FAIL MESSAGE. THE QRH WAS FOLLOWED AND THE FLAPS WERE INDICATING AT 30 DEGREES. THE CREW LANDED WITHOUT INCIDENT AND PERFORMED A CIRUIT BREAKER REST AND THE FLAPS RETURNED TO ZERO. FLT TO WHERE THE FLAPS OPERATED NORMALLY. (TC NR 20061205002) 2L72 4F4 FRTA21EA E15NE 20070129001532007012900153EA 2007 1 29 CA061205003 120061201G2750 BPSU CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE T/E FLAP OUT OF RIG W O OTHER O OTHER APAPPROACH 1 CA (CAN) ON APPROACH THE CREW REPORTED THAT THE FLAPS WERE FAILED AT 4 DEGREES. THE AIRCRAFT WAS FERRIED WITH THE FLAPS AT 4 DEGREES. LINE MAINTENANCE COMPLETED TASK 27-51-10-830-801( RIGGING OF THE BPSU`S). BOTH WERE FOUND OUT OF RIG ALSO THE NR 7 DFECU POTENTIOMETER OUT OF RIG. ALSO THE FOLLOWING TASKS WERE COMPLETED 000-27-160-001, 000-27-160-103, 000-27-580-103, 000-27-590-001, 000-27-59-104, 000-27-680-001, 000-27-680-103,000-27-690-001 & 000-27-690-104. LT FLEX DRIVE CORE NR 1 FOUND DAMAGED AND WAS REPLACED. ALL RT AND LT FLAP ACTUATORS WERE REMOVED AND COLD SOAKED/TORQUE CHECK IAW 27-53-00-750-8011 AND SL RJ-SL-27-036. ALL ACTUATORS FOUND SERVICEABLE AND RE-INSTALLED IAW AMM 27-53-01 & 27-53-05, FUNCTION CH2L72 4F4 FRTA21EA E15NE 20070125001582007012500158EA 2007 1 25 CA061205004 120061204G2750 FLAP SYSTEM CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE TE FLAPS MALFUNCTIONED W O OTHER J WARNING INDICATION APAPPROACH 1 CA (CAN) THE CREW REPORTED THAT ON APPROACH THEY RECEIVED THE (FLAP FAIL) CAUTION MESSAGE. ON APPROACH INTO. CIRCUIT BREAKER RESET OF 1F4 AND 2F4 THE FLAPS RETURNED TO NORMAL FOR FLIGHT CONDITION. UPON ARRIVAL THE FLAPS WERE AT 0 DEGREES AND INSPECTED FOR BINDING OR TWISTING WITH NO FAULT FOUND. CYCLED TO 45 DEGREES WITH NFF. FECU LOG FAULT CODE FOR LEG ARE 5 1B, 5 2B, 171A, 172B, 25BC, 33 PC, FLAPS SYSTEM TESTED SERVICEABLE WITH OAT -7 DEGREES. AIRCRAFT RELEASED INTO SERVICE. (TC NR 20061205004) 2L72 4F4 FRTA21EA E15NE 20070129001542007012900154NM 2007 1 29 CA061205005 120061130G3246314802OPT4 BEARING DHAV DHC8 DHC8* NM PWA PW120 PW123 NE HAMSTD14SF 14SF23 NE MLG FAILED W O OTHER K FLUID LOSS TXTAXI/GRND HDL 1 CA 7209 (CAN) WHEN THE AC ARRIVED TO THE PARKING POSITION, A BIG HYDRAULIC LEAKAGE WAS NOTED ON THE RUNWAY. AT THE SAME TIME, MLG WHEEL NR 3 WAS FOUND TO BE DISPLACED FROM ITS NORMAL POSITION. THE WHEEL OUTER BEARING WAS FOUND DAMAGED. RT MLG SHOCK STRUT AND WHEEL ASSY REPLACED. (TC NR 20061205005) 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20070129001582007012900158GL 2007 1 29 CA061205006 320061114G6110 SHIM HAMSTD 24PF309 DHAV DHC7 DHC7* EA PWA PT6 PT6A50 52043EA HAMSTD24PF 24PF305 GL PROP BLADE BROKEN W O OTHER WK INADEQUATE Q C FLUID LOSS ININSP/MAINT 1 CA 4025 43 (CAN) AFTER LANDING, A POST-FLIGHT INSPECTION REVEALED AN OIL LEAK IN THE NR1 PROP. FURTHER INVESTIGATION SHOWED THAT THE BLADE SHIMS HAD BEEN INSTALLED ON THE WRONG SIDE OF THE BLADE RETAINING RING. THE SHIMS HAD BROKEN AND DAMAGED THE OIL SEALS. THE OTHER 3 PROPS WERE CHECKED AND THE SAME PROBLEM WAS FOUND ALONG WITH MORE DAMAGED SEALS. (TC NR 20061205006) 2H74 4T4 TRTA20EA E4EA 6 CP1NE 20070125001622007012500162EA 2007 1 25 CA061205007 120061201G2750 FLAP SYSTEM CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE TE FLAPS MALFUNCTIONED W O OTHER F FLT CONT AFFECTED APAPPROACH 1 CA 4762 4762 (CAN) DURING APPROACH WHEN FLAPS SELECTED, FLAPS REMAINED RETRACTED (0 DEG). AIRCRAFT DID FLAPLESS LANDING. ON GROUND FLAP CIRCUIT BREAKER RE-SET CARRIED OUT, FLAPS FUNCTIONED NORMALLY. AIRCRAFT DEPARTED FOR MAINTENANCE BASE FOR ADDITIONAL INSPECTIONS (TC NR 20061205007) 2L72 4F4 FRTA21EA E15NE 20070125001632007012500163CE 2007 1 25 CA061205008 120061205G3233AN6289D6 NUT LEAR 35 35LEAR 5170600CE GARRTTTFE731TFE7312 01518WP LT MLG ACTUATOR CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 14603 2324 (CAN) NUT ON HYDRAULIC LINE LEADING TO LT MAIN LANDING ACTUATOR FOUND CRACKED DURING DAILY INSPECTION. THE NUT WAS REPLACED, GEAR SWINGS CARRIED OUT, AIRPLANE IS NOW SERVICEABLE. (TC NR 20061205008) 2L72 4F4 F A10CE E6WE 20070125001642007012500164EA 2007 1 25 CA061206001 120061011G2750 FLAP SYSTEM CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE TE FLAPS MALFUNCTIONED W O OTHER F FLT CONT AFFECTED APAPPROACH 1 CA 2577725777 (CAN) ON APPROACH FLAPS SELECTED TO 8 DEG, FLAP DID NOT TRAVEL AND (FLAP FAIL) MESSAGE DISPLAYED. NORMAL FLAP ZERO LANDING . AFTER LANDING , FLAP CIRCUIT BREAKER RESET PROCEDURE CARRIED OUT . FLAPS INSPECTED AND NO FAULTS FOUND. FLAPS CYCLED WITH NO FAULTS FOUND. (TC NR 20061206001) 2L72 4F4 FRTA21EA E15NE 20070125001662007012500166EA 2007 1 25 CA061206002 120061202G5520NAS620413D BOLT CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE LT ELEVATOR MISINSTALLED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) LT ELEVATOR, FOUND NUT/BOLT COMBINATION INCORRECTLY INSTALLED ON LT NR 1 PCU JAM TOLERANT MECHANISM. AIRFRAME HOURS: 25355:05. CYCLES: 20701. (TC NR 20061206002) 2L72 4F4 FRTA21EA E15NE 20070125001682007012500168NE 2007 1 25 CA061206003 220061202G7230 BLADES CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE LT ENGINE DAMAGED W O OTHER E VIBRATION/BUFFET NRNOT REPORTED 1 CA (CAN) UNUSUAL NOISE AND VIBRATION FROM LT ENGINE. FOUND FAN BLADES NRS: 8,9,10,11,22,23,24 AND 25 BENT AND DAMAGED. AIRFRAME HOURS=5306:19. CYCLES=3929. (TC NR 20061206003) 2L72 4F4 FRTA21EA E15NE 20070125001692007012500169EA 2007 1 25 CA061206004 120061206G2750 FLAP SYSTEM CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE TE FLAPS MALFUNCTIONED W D RETURN TO BLOCK J WARNING INDICATION TXTAXI/GRND HDL 1 CA 1118711187 (CAN) (FIRST FLIGHT OF DAY, AIRCRAFT HAD BEEN OUTSIDE ON GATE OVERNIGHT, OAT AT -20DEG OR LOWER) DURING TAXI FROM GATE UPON SELECTING FLAP TO 8DEG POSITION, (FLAPS FAIL) MESSAGE AND FLAPS FAILED TO EXTEND. AIRCRAFT RETURNED TO GATE. FLAP CIRCUIT BREAKER RE-SET PROCEDURE CARRIED OUT UNSUCCESSFUL. AIRCRAFT COMPLETELY POWERED DOWN. UPON POWER UP, FLAPS FUNCTIONED NORMAL. FLAP VISUAL INSPECTED AND FUNCTIONED SEVERAL TIMES. AIRCRAFT DEPARTED AS SCHEDULED FLIGHT. UPON FLAP SELECTION AT DESTINATION AIRPORT, FLAPS FAILED TO EXTEND, FLAP (O) LANDING CARRIED OUT. AIRCRAFT TO BE FERRIED TO MAIN MAINTENANCE BASE FOR INSPECTION. (TC NR 20061206004) 2L72 4F4 FRTA21EA E15NE 20070125001712007012500171CE 2007 1 25 CA061206005 120061124G2810244224152 HOSE LEAR 45 45LEAR 5170805CE GARRTTTFE731TFE7312 01518WP FUEL SYSTEM LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA 1266 (CAN) AFTER AIRCRAFT WAS PARKED OVERNIGHT WITH FULL FUEL, A MINOR FUEL SEEP WAS DISCOVERED COMING FROM RT FUSELAGE FUEL TANK TO WING FLEX HOSE ASSY. DURING REPLACEMENT OF RT HOSE WITH FULL LT WING FUEL IT WAS DISCOVERED THE LT FUSELAGE TO WING FUEL FLEX HOSE ALSO HAD A MINOR SEEP. THIS IS ONLY NOTICEABLE WHEN THE AIRCRAFT IS SITTING FOR A FEW HOURS WITH FULL FUEL IN THE WINGS. ON INVESTIGATION OF OUR OTHER AIRCRAFT IT WAS DISCOVERED THE RT FLEX HOSE HAD THE SAME PROBLEM. THESE ARE P/N 244224151 AND 244224152 FLEX HOSE ASSEMBLIES. (TC NR 20061206005) 2L72 4F4 FRTT00008WIE6WE 20070125001732007012500173CE 2007 1 25 CA061207001 120061206G2897 WIRE CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE FUEL CELL DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA 5877 (CAN) THE FUEL TANKS SHOW EVIDENCE OF LOCALIZED DISCOLORATION AND VARIOUS NICKS ON OUTER JACKETS OF FUEL QUANTITY PROBE WIRING. THERE IS ALSO DISCOLORATION ON THE TERMINALS OF THE VARIOUS FUEL PROBES. THIS DAMAGE IS PROBABLY CAUSED BY IMPROPER USE OF THE TYRAP TOOL MOST LIKELY AT THE FACTORY LEVEL. THIS IS THE SECOND TIME THIS TYPE OF DAMAGE HAS BEEN FOUND ON A COMPANY AIRCRAFT. (TC NR 20061207001) 1L72 4F4 F A22CE E1NE 20070125002612007012500261EU 2007 1 25 CA061207002 120061207G5310F10A212107 WINDOW FRAME AMD FALC10FALCON10 2730101EU WINDOW CORRODED W K NONE O OTHER ININSP/MAINT 1 CA 6674 (CAN) REMOVED FRONT WINDSHIELDS TO COMPLY WITH COCKPIT WINDOW FRAME INSPECTION REQUIREMENT OF THE C2 INSPECTION. FOLLOWING REMOVAL OF PILOT’S WINDSHIELD, SEVERE EXFOLIATION CORROSION WAS FOUND ON LOWER FRAME APPROX. 16 INCHES FROM OUTER RAIL OVER AN 8 INCH WIDTH ON THE FRAME. (TC NR 20061207002) 2L72 4F A33EU 20070129001662007012900166EU 2007 1 29 CA061207003 120061203G523017040238003 PLATE 17040236407 EMB ERJ170ERJ170100 EU GE CF34 CF348E5A1 30015NE CARGO DOOR BENT W O OTHER WP INADEQUATE Q C NO WARNING INDICATION TXTAXI/GRND HDL 1 CA 2611 (CAN) ACFT WAS TAXIING TO DE-ICING BAY, WHERE THE DEICING PERSONNEL NOTICED THAT THE C1 CARGO DOOR WAS AJAR BY 2 INCHES. MAINTENANCE WAS CALLED IN, AND THEY NOTICED THAT BOTH HANDLES WERE STOWED. THE DOOR WAS OPENED TO CHECK FOR OBSTRUCTIONS, AND FOUND THE COVER PLATE TO BE BENT. NO OTHER DAMAGE WAS NOTED, AND THE DOOR WAS CLOSED NORMALLY. THE GREEN INDICATION ON THE DOOR WINDOW WAS APPARENT. THIS INFO WAS THEN PASSED ON TO THE F/O. ALSO, THE COCKPIT INDICATION DID NOT SHOW DOOR TO BE OPENED. CREW DID NOT REALIZE DOOR WAS OPENED. IT IS SUSPECTED THAT THE MIDWAY LATCH WAS ROTATED BY A BENT PLATE, WHICH THEN ALLOWED THE HANDLES TO BE STOWED WITHOUT THE LATCH CAMS ENGAGED AROUND THE LATCH PINS. (TC NR2006122L72 4F4 FRTA56NM E00063EN 20070129001682007012900168SW 2007 1 29 CA061207004 120061207G79218543909 OIL COOLER BELL 206 206L1 1182107SW ALLSN 250C 250C28B 03013GL ENGINE LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) ON AIRCRAFT RETURNING TO BASE IT WAS NOTED THAT THERE WAS OIL ON THE TAILBOOM. ON INVESTIGATION THE SOURCE OF THE OIL WAS FOUND TO BE THE OIL COOLER. COOLER CHANGED. (TC NR 20061207004) 1G71 3U3 U H2SW E1GL 20070129001792007012900179SO 2007 1 29 CA061207005 120061206G8011 DRIVE GEAR MHB4014R PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA HARTZLHCE3Y HCE3YR2A GL STARTER DESTROYED W O OTHER O OTHER TXTAXI/GRND HDL 1 CA 1926 C120571 (CAN) WHILE AIRCRAFT WAS AWAY FROM BASE ON A SCHEDULED RUN THE CREW WAS ATTEMPTING TO STAR THE NR 2 ENGINE. THEY NOTED NO ENGAGEMENT OF THE STARTER (ENGINE DID NOT TURN OVER). A MAINTENANCE CREW WAS DISPATCHED TO REPAIR THE AIRCRAFT, WHEN THE COWLINGS WERE REMOVED SEVERAL PIECES OF METAL WERE OBSERVED. UPON REMOVAL OF THE STARTER IT WAS DISCOVERED THAT THE ENGAGEMENT GEAR ON THE BENDIX DRIVE HAD DISINTIGRATED, DAMAGING THE DRIVE HOUSING AS THE PIECES DEPARTED. THE STARTER WAS LESS THAN 80 HRS FROM OVERHAUL. AFTER DISCUSSION WITH THE CREW, THEY STATED THEY DID NOT DOUBLE TAP THE START SWITCH. AN INVESTIGATION IS STILL IN PROGRESS. (TC NR 20061207005) 1L72 3O3 O A20SO E14EA 5 CP33EA 20070129001812007012900181EA 2007 1 29 CA061208001 120061206G275220222788 ACTUATOR CNDAIRCL601 CL6013A 8070802EA GE CF34 CF343A 30015NE T/E FLAP CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 4684 (CAN) DURING SCHEDULE LUBRICATION OF THE FLAP ACTUATORS, THE TECHNICIAN NOTICED GREASE WAS OOZING OUT OF A CRACKED WELD ON THE HOUSING OF THE LT OB FLAP ACTUATOR JACK SCREW. (TC NR 20061208001) 2L72 4F4 FRTA21EA E15NE 20070202001222007020200122SW 2007 2 2 CA061208003 120061205G634022A656 TACH GENERATOR BELL 206 206L4 1182110SW ALLSN 250C 250C30P 03013GL WORN W H DEACTIVATE SYST/CIRCUITS O OTHER CRCRUISE 1 CA (CAN) GREASE FOUND WASHED OUT CAUSING PREMATURE WEAR OF DRIVE SPLINES LEADING TO HYDRAULIC SYSTEM FAILURE. 298.7 HRS SINCE PREVIOUS LUBRICATION. (TC NR 20061208003) 1G71 3U3 UNCH2SW E1GL 20080219001392008021900139SW 2008 2 19 CA061208004 120061205G2913206076030111 PUMP BELL 206 206L4 1182110SW ALLSN 250C 250C30P 03013GL HYDRAULIC SYSTEMLACK OF LUBE W H DEACTIVATE SYST/CIRCUITS F FLT CONT AFFECTED CRCRUISE 1 CA (CAN) GREASE FOUND WASHED OUT CAUSING PREMATURE WEAR OF DRIVE SPLINES LEADING TO HYDRAULIC SYSTEM FAILURE. 198.3 HRS SINCE PREVIOUS LUBRICATION. (TC NR 20061208004) 1G71 3U3 UNCH2SW E1GL 20070129001822007012900182NE 2007 1 29 CA061208005 220061203G72309324M70G06 COMPRESSOR AIRBUSA340 A340313 EU CFMINTCFM56 CFM565C4 13802NE ENGINE STALLED W E ENGINE SHUTDOWN ME OVER TEMP VIBRATION/BUFFET CRCRUISE 1 CA 299614857 (CAN) IN CRUISE, 2 HOURS FROM DESTINATION THE ENGINE STALLED AND EGT WAS RISING. WHEN EGT REACHED 1010 DEG. C, THE ENGINE WAS SHUTDOWN. THE OIL PRESSURE WENT TO ZERO AND BOTH N1 AND N2 ROTORS WERE ROTATING. DFDR DATA SHOWS: N2 VIBRATION WAS HIGH (3.5 TO 5.5 UNITS) AFTER THE STALL, RAPIDLY REDUCED TO 2.O UNITS AND THEN SLOWLY REDUCED TO ZERO BEFORE ENGINE SHUTDOWN. N1 VIBRATION WAS LOW AFTER THE STALL (0.5-2 UNITS) AND RAPIDLY INCREASED AFTER STALL TO 5-5.5 UNITS AND STAYED THERE. N1, N2, FUEL FLOW HAD A RAPID DECREASE AFTER THE STALL AND RECOVERED SLIGHTLY, THEN SLOWLY DECREASED WITH EGT RISING. AFTER AIRCRAFT LANDED, BASE MAINTENANCE CARRIED OUT A VISUAL INSPECTION WITH THE FOLLOWING FINDINGS: NO DAMAGE O2L74 4F4 FRTA197 E37NE 20070129001832007012900183EA 2007 1 29 CA061211001 120061203G5610NP13932100 WINDSHIELD CNDAIRCL600 CL6002C10 1390015EA COCKPIT CRACKED W O OTHER O OTHER TXTAXI/GRND HDL 1 CA (CAN) RT SIDE WINDSHIELD SHATTERED (TC NR 20061211001) 2L72 4F RTA21EA 20070129001842007012900184EA 2007 1 29 CA061211002 120061203G5610601R3303311 WINDOW CNDAIRCL600 CL6002B19 1900309EA COCKPIT CRACKED W K NONE O OTHER TXTAXI/GRND HDL 1 CA (CAN) LT SIDE WINDOW SHATTERED. (TC NR 20061211002) 2L72 4F RTA21EA 20070129001852007012900185 2007 1 29 CA061211003 420061210G34177000700940 ADC DHAV DHC8 DHC8* NM PWA PW120 PW123 NE HAMSTD14SF 14SF23 NE NR 2 MALFUNCTIONED W A UNSCHED LANDING G MULTIPLE FAILURE CRCRUISE 1 CA (CAN) DURING CRUISE, THE F/O ALTIMETER OFF FLAG CAME INTO VIEW ON NUMEROUS OCCASSIONS. THE EGPWS FAULT LIGHT ALSO ILLUMINATED. PILOT ELECTED TO PERFORM AN AIR TURN BACK. NR 2 DIGITAL AIR DATA COMPUTER REPLACED. (TC NR 20061211003) 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20070129001862007012900186EA 2007 1 29 CA061211004 120061207G7120601370541 PLUG CNDAIR ASB1810617 CNDAIRCL600 CL6002B19 1900309EA LT ENGINE MISSING W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA (CAN) DURING OF C-CHECK INSPECTION FOUND THAT PLUG ASSY P/N 60137054-1 IS NOT INSTALLED AT THE AFT ENGINE TRUST FITTING P/N ASB18106-17 OF LT ENGINE. TO INSTALL THE PLUG ENGINE NEED TO BE REMOVED. (TC NR 20061211004) 2L72 4F RTA21EA 20070125001862007012500186NE 2007 1 25 CA061211005 320061207G611114SF23 BEARING RACE DHAV DHC8 DHC8301 1386003NM PWA PW120 PW123 NE HAMSTD14SF 14SF23 NE NR 1 PROP FRACTURED W EA ENGINE SHUTDOWN UNSCHED LANDING E VIBRATION/BUFFET CRCRUISE 1 CA 24284 (CAN) LIGHT TO MODERATE PROP VIBRATION IN CRUISE, AS POWER WAS REDUCED FOR DESCENT VIBRATION BECAME EXCESSIVE. AS A RESULT THE NR 1 PROP (CONDITION LEVER) WAS SELECTED TO START FEATHER (VIBRATION STOP) AND THEN NR 1 ENGINE WAS SHUTDOWN. ALL ENGINE PARAMETERS WERE NORMAL PRIOR TO SHUTDOWN. FOLLOWING THE IFSD AS DESCRIBED ABOVE, MAINTENANCE PERFORMED A LOW POWER RUN TO VERIFY THE VIBRATION AS REPORTED. THE VIB WAS CONFIRMED AND THE ENGINE SHUTDOWN. OIL WAS THEN NOTED DRIPPING FROM THE VICINITY OF THE NR 1 PROP. INITIAL INVESTIGATION HAS REVEALED THAT THE NR 1 PROP, NR 4 BLADE BEARING RACE HAS FRAGMENTED INTO SEVERAL PARTS. (TC NR 20061211005) 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20070125002092007012500209EA 2007 1 25 CA061211006 120061203G493038301552 LINE HONEYWELL CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE FUEL MANIFOLD BROKEN W O OTHER KB FLUID LOSS SMOKE/FUMES/ODORS/SPARKS APAPPROACH 1 CA 1526815268 P365C (CAN) RT AIR CONDITIONING PACK WAS DEFERRED AND CREW HAD TO SHUTDOWN APU ON APPROACH BECAUSE OF OIL/FUEL ODOR IN THE CABIN. CREW REPORTED A PRESSURE BUMP WHEN APU WAS SHUTDOWN. APU WAS SUSPECTED TO BE OVER SERVICED, BUT EVEN AFTER DRAINING A LITRE OF OIL APU WOULD NOT RE-START. FURTHER TROUBLESHOOTING FOUND THE PRIMARY FUEL MANIFOLD LINE BROKEN. ONCE REPLACED APU OPERATED SERVICEABLE. (TC NR 20061211006) 2L72 4F4 FRTA21EA E15NE 20070125002122007012500212 2007 1 25 CA061211007 420061209G22117003974730 COMPUTER HONEYWELL DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE FLIGHT GUIDANCE FAULTED W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA 3871815860 90012118 (CAN) LEVELING OFF AT 4000 FT, AFCS FAILED, ID802 SHOWED LINES, YD AND FLIGHT DIRECTOR FAILED, CAPT AND F/O ADI`S FLAGGED OFF. AIRCRAFT RETURNED TO ORIGINATING AIRPORT FOR NORMAL LANDING. MAINTENANCE INSPECTION OF FLIGHT FAULT SUMMARY SHOWED FAILURE OF RIGHT FLIGHT GUIDANCE COMPUTER. COMPUTER REPLACED AND FUNCTION CHECKED. AIRCRAFT RETURNED TO SERVICE. (TC NR 20061211007) 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20070125002142007012500214SW 2007 1 25 CA061211008 120061208G293227191543 TRANSDUCER SWRNGNSA227 SA227AC 8780603SW GARRTTTPE331TPE33111U 01514WP MCAULY4HFR344HFR34C652 NE HYD PRESS TRANS SPLIT W O OTHER J WARNING INDICATION LDLANDING 1 CA (CAN) AIRCRAFT LOST HYD PRESSURE ON LANDING. THERE WAS NO INDICATION OF PRESSURE ON GAUGE AND ON THE ANUNCIATOR PANEL. HYDRAULIC PRESSURE TRANSDUCER FOUND SPLIT AROUND HYDRAULIC FITTING END. TRANSDUCER AND SHUTTLE VALVE WERE REPLACED AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20061211008) 2L72 4T4 TRTA8SW E4WE 6 C3PNE 20070125002152007012500215NM 2007 1 25 CA061211009 120061209G5610141A481014 WINDOW BOEING737 73776N 13844CHNM CFMINTCFM567CFM567B22 13802NE COCKPIT CRACKED W O OTHER O OTHER CRCRUISE 1 CA 19028 (CAN) WINDOW FLT COMPARTMENT DELAMINATED, CRACKED NR 2 LT DESCENDED TO FL210 + INC CABIN ALT TO 9000 FT, WHICH GAVE US A CABIN DIFF OF 3.6 PSI. CAPT`S NR 2 SLIDING WINDOW REPLACED IAW AMM 56-12-11, GND CHECKED SERVICABLE. COCKPIT WINDOW FAILURES ARE PART OF A SAFETY RELATED SERVICE PROBLEM SRP 56-0018 WITH MFG. ICA ISSUANCE IS AWAITED FOR PERMANENT RECOMMENDED ACTION. (TC NR 20061211009) 2L72 4F4 FRTA16WE E00055EN 20070125002182007012500218EA 2007 1 25 CA061212001 220061210G7200 ENGINE EMB 110 EMB110P1 3260122SO PWA PT6 PT6A34 52043EA HARTZLHCB3T HCB3TN3 GL RIGHT FAILED W FA ACTIVATE FIRE EXT. UNSCHED LANDING XA ENGINE FLAMEOUT FLAME/FIRE DEDESCENT 1 CA 20124214 42129 (CAN) SHORTLY AFTER COMPLETING THE DESCENT CHECKS FOR A LANDING (WITH ENGINES OPERATING NORMALLY, ENGINE INSTRUMENTS IN THE GREEN, THE CREW HEARD A LOUD NOISE FOLLOWED BY A SUDDEN LOSS OF POWER ON THE RT ENGINE. IMMEDIATELY FOLLOWING THE SUDDEN LOSS OF POWER THE RT ENGINE CAUGHT ON FIRE. THE PROCEDURES FOR AN IN-FLIGHT ENGINE FIRE WERE CARRIED OUT AND THE FIRE WAS EXTINGUISHED. AFTER INITIAL INSPECTION THE CAUSE OF THE ENGINE FAILURE WAS DUE TO AN INTERNAL FAILURE OF THE ENGINE. ITEMS NOTICED DURING INITIAL INSPECTION ARE AS FOLLOWS: POWER SECTION SEIZED, OIL VISIBLE IN BOTH EXHAUST STACKS, NO EXTERNAL INDICATION OF FIRE DAMAGE TO ENGINE VISIBLE (FIRE WAS LIMITED TO EXHAUST STACKS DUE TO OIL LOSS FROM INTERNAL 1L72 4T4 T A21SO E4EA 6 CP15EA 20070125002192007012500219SO 2007 1 25 CA061212002 120061112G6100 PROPELLER LKHEED382 382G 526414USO ALLSN 501D 501D22A 03006GL HAMSTD54H 54H60117 NE NR 4 DAMAGED W E ENGINE SHUTDOWN KJ FLUID LOSS WARNING INDICATION CRCRUISE 1 CA (CAN) IN CRUISE AT FL240 AFTER DEPARTURE THE CREW OBSERVED LOW OIL QTY ON NR 2 ENGINE. THE ENGINE WAS SHUTDOWN AND THE AIRCRAFT CONTINUED TO DESTINATION. SHORTLY AFTER RE-ESTABLISHING CRUISE AT FL220 THE CREW OBSERVED LOW OIL QTY ON NR 4 PROPELLER. THE PROP WAS SELECTED TO MECHANICAL GOVERNING AND THE AIRCRAFT CONTINUED TO DESTINATION. THE NR 4 ENGINE WAS SHUTDOWN ON DESCENT TO PRECLUDE PROP OVERSPEED. THE AIRCRAFT ARRIVED WITHOUT FURTHER PROBLEMS. MAINTENANCE REPLACED THE NR 2 ENGINE SCAVENGE FILTER AND THE NR 4 PROPELLER ASSY. AIRCRAFT SATISFACTORILY GROUND RUN AND RETURNED TO SERVICE. 2H74 4T4 T A1SO E282 6 CP906 20070125002202007012500220NM 2007 1 25 CA061212003 120061211G75008209074 SWITCH BOMBDRDHC8 DHC8402 1390042NM RT NACELLE FAILED W O OTHER J WARNING INDICATION APAPPROACH 1 CA 40 (CAN) NR 2 BLEED HOT CAUTION LIGHT COME ON 4 MILES OUT. CDS INTEROGATION FAULT CODES 7005, 7001 AND 1701. (TC NR 20061212003) 2H72 4T RTA13NM 20070125002212007012500221EA 2007 1 25 CA061212004 120061202G5610NP13932111 WINDSHIELD CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE COCKPIT CRACKED W O OTHER O OTHER CRCRUISE 1 CA 3695 3695 (CAN) DURING CRUISE CAPTAIN’S FRONT WINDSHIELD SHATTERED. (NO PRESSURIZATION LOSS). CREW DECLARED EMERGENCY AND DESCENDED TO 10000 FT AND DIVERTED TO NEAR BY ALTERNATE AIRPORT. MAINTENANCE REPLACED WINDSHIELD AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20061212004) 2L72 4F4 FRTA21EA E15NE 20070125002232007012500223SO 2007 1 25 CA061212005 120061210G291365WE002241 PUMP EMB 110 EMB110P1 3260122SO PWA PT6 PT6A34 52043EA HARTZLHCB3T HCB3TN3 GL HYDRAULIC FAILED W O OTHER J WARNING INDICATION APAPPROACH 1 CA (CAN) (5) MINUTES AFTER AN ENGINE FAILURE OF THE RT ENGINE (SDR 20061212001) THE HYDRAULIC LIGHT CAME ON EVEN THOUGH THE LT ENGINE WAS OPERATING NORMALLY. THE CREW ATTEMPTED TO EXTEND THE LANDING GEAR NORMALLY BUT IT WOULD NOT LOCK. THE GEAR WAS THEN SUCCESSFULLY HAND PUMPED DOWN. A FAILURE OF THE LT ENGINE DRIVEN HYDRAULIC PUMP IS SUSPECTED TO BE THE CAUSE OF NOT BEING ABLE TO EXTEND THE LANDING GEAR NORMALLY. THE HYDRAULIC PUMP WILL BE REMOVED AND SENT OUT FOR A TEARDOWN. (TC NR 20061212005) 1L72 4T4 T A21SO E4EA 6 CP15EA 20070125002632007012500263NM 2007 1 25 CA061212006 120061212G323054C546349 SEQUENCE VALVE DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE MLG RUPTURED W O OTHER KJ FLUID LOSS WARNING INDICATION CLCLIMB 1 CA (CAN) UPON RETRACTION OF THE LANDING GEAR THE CREW HEARD A STRANGE NOISE FOLLOWED BY HYDRAULIC FLUID QUANTITY LOSS IN THE NR 2 SYSTEM. THE CREW CARRIED OUT THE APPLICABLE PROCEDURES TO EXTEND THE LANDING GEAR BUT WERE NOT ABLE TO GET THE NOSE LANDING GEAR TO EXTEND. THE CREW FLEW THE AIRCRAFT FOR SEVERAL HOURS TO BURN OFF FUEL AND TRY TO GET THE NOSE GEAR TO EXTEND BUT WERE UNSUCCESSFUL AND COMPLETED A NOSE GEAR RETRACTED LANDING ON A SNOW PACKED RUNWAY. THE AIRCRAFT WAS SUBSEQUENTLY DAMAGED IN THE NOSE LANDING GEAR DOOR AND RADOME AREAS. UPON INITIAL INVESTIGATION BY MAINTENANCE IT WAS FOUND THAT THE LT MLG DOOR SEQUENCING SOLENOID VALVE WAS RUPTURED CAUSING THE LOSS OF THE NR 2 HYDRAULIC SYSTEM FLUID. IT IS 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20070125002252007012500225WP 2007 1 25 CA061212007 220061030G7250310210610 TURBINE WHEEL GARRTTTPE331TPE33110U 01514WP NR 2 DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA 1122 (CAN) FOUND UPON DOING A HSI INSPECTION THAT THE NR 2 ROTOR THE RIVETS WERE FOUND LOOSE TO THE POINT THAT THEY WERE GOING TO START COMING OUT. THIS WHEEL IN QUESTION ONLY HAD 1409 CYCLES TOTAL ON IT. (TC NR 20061212007) 4 T E4WE 20070125002282007012500228WP 2007 1 25 CA061212008 220061212G7250310210610 TURBINE WHEEL 310210610 GARRTTTPE331TPE33110UA 01514WP ENGINE DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA 3598 (CAN) FOUND UPON INSPECTION AT THE HSI INSPECTION THAT THE RIVETS WERE LOOSE AND DEFORMED TO THE POINT THAT THE RIVETS WERE GOING TO COME OUT AND POSSIBLY WOULD CAUSE MORE DAMAGE INSIDE THE ENGINE. (TC NR 20061212008) 4 T E4WE 20070125002302007012500230EA 2007 1 25 CA061212009 120061121G2750 FLAP SYSTEM CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE TE FLAPS MALFUNCTIONED W O OTHER F FLT CONT AFFECTED APAPPROACH 1 CA 1159311593 (CAN) ON APPROACH WHEN FLAPS SELECTED, (FLAP FAIL) MESSAGE AND FLAPS REMAINED AT ZERO DEG., FLAPLESS LANDING. ON GROUND FLAP CIRCUIT BREAKERS RESET PROCEDURE CARRIED OUT, FLAPS FUNCTION CHECKED NORMAL. (TC NR 20061212009) 2L72 4F4 FRTA21EA E15NE 20070125002312007012500231EU 2007 1 25 CA061213001 120061210G521019017111401 DOOR EMB ERJ190ERJ190100IGW3260408EU GE CF34 CF34* NE COCKPIT DISLODGED W O OTHER O OTHER CRCRUISE 1 CA 250 (CAN) FLIGHT DECK DOOR CAME FREE ON FRAME WHEN OPENED FROM CABIN SIDE IN FLIGHT. BOTTOM LOCATING PIN FOUND BENT AND TEMPORARILY FIXED. TOP PIN DOES NOT REMAIN IN FRAME BRACKET. DOOR SERVICEABLE FOR REMAINDER OF FLIGHT ONLY. (TC NR 20061213001) 2L72 4F4 FRTA57NM E15NE 20070125002332007012500233EA 2007 1 25 CA061213002 120061208G262013739002 SWITCH CNDAIRCL600 CL6002B19 1900309EA EXTINGUISHER JAMMED W K NONE L NO TEST ININSP/MAINT 1 CA (CAN) BOTH CARGO FIRE X-BOTTLES DISCHARGED WHEN , NORMAL CARGO SMOKE PUSH) SWITCH-LIGHT ACTUATED TO ARM THE DISCHARGE SQUIBS. AFTER INVESTIGATION FOUND THAT BOTTLE ARMED (PUSH TO DISCHARGE) SWITCH-LIGHT JAMMED IN THE (PUSH) POSITION. (TC NR 20061213002) 2L72 4F RTA21EA 20070129001872007012900187EA 2007 1 29 CA061213003 120061208G261213739002 LIGHT BOMBDR 601R5107083 CNDAIRCL600 CL6002B19 1900309EA FIRE WARNING INTERMITTENT W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) DUE TO INCIDENT, CARGO FIREX PANEL TESTED AND FOUND THAT (NORMAL BOTTLE ARMED PUSH TO DISCH) SWITCH-LIGHT IS INTERMITTENT OR JAMMED IN THE CLOSE POSITION. (TC NR 20061213003) 2L72 4F RTA21EA 20070129001882007012900188EA 2007 1 29 CA061213004 120061208G261213739002 LIGHT CNDAIR 601R5107083 CNDAIRCL600 CL6002B19 1900309EA FIRE WARNING INTERMITTENT W O OTHER O OTHER ININSP/MAINT 1 CA (CAN) DUE TO INCIDENT ON AC N639BR, CARGO FIREX PANEL TESTED AND FOUND THAT (NORMAL BOTTLE ARMED PUSH TO DISCH) SWITCH-LIGHT IS INTERMITTENT OR JAMMED IN CLOSE POSITION. (TC NR 20061213004) 2L72 4F RTA21EA 20070129001892007012900189NM 2007 1 29 CA061213005 120061210G792128E997 OIL COOLER DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE ENGINE CRACKED W O OTHER KJ FLUID LOSS WARNING INDICATION CRCRUISE 1 CA 301 (CAN) OIL COOLER SEAM WELD CRACKED DURING FLIGHT ALLOWING LEAKAGE AND LOW ENGINE OIL PX. (TC NR 20061213005) 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20070125002352007012500235EA 2007 1 25 CA061214001 120061213G2750 FLAP SYSTEM CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE TE FLAPS MALFUNCTIONED W O OTHER O OTHER APAPPROACH 1 CA (CAN) ON APPROACH THE CREW SELECTED FLAP 40 AND THE FLAPS FAILED AT 20 DEGREES. THE AIRCRAFT LANDED WITHOUT INCIDENT AND WAS LATER FERRIED WHERE IT IS CURRENTLY UNDERGOING INSPECTION. (TC NR 20061214001) 2L72 4F4 FRTA21EA E15NE 20070125002372007012500237SO 2007 1 25 CA061214002 220061207G7314 SEAL DIAMONDA20 DA20C1 2990001GL CONT O240 IO240B 17063SO SNSNCHW69EK W69EK63 EA FUEL PUMP LEAKING W O OTHER R PARTIAL RPM/PWR LOSS NRNOT REPORTED 1 CA 1337 (CAN) AIRCRAFT BROUGHT IN FOR 50 HR.MAINTENANCE CHECK FOUND FUEL ON BOTTOM OF COWL AND IT WAS TRACED BACK TO THE ENGINE DRIVEN FUEL PUMP. THE SEALS IN THE FUEL PUMP HAD STARTED TO FAIL OR HAD FAILED AROUND THE MIXTURE CONTROL LEVER ASSY. THE TOP COVER ALSO WAS LEAKING FUEL. FUEL PUMP WAS REMOVED AND SENT FOR REPAIRS. UNIT REPAIRED AND RELEASED ON 24-0078 NR A47159 (TC NR 20061214002). 1L71 3O3 ONTTA4CH E7SO 5 NTA4CH 20070125002392007012500239EU 2007 1 25 CA061214003 120061129G3010 BOOT PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL DEICE SYSTEM SPLIT W K NONE O OTHER ININSP/MAINT 1 CA 6085 6085 (CAN) AIRCRAFT RETURNED FROM FLIGHT TO ARCTIC. ALL DE-ICE BOOTS ON AIRCRAFT WERE FOUND SPLIT ALONG CHORD AND HAD TO BE REPLACED. THE PRESSURE REGULATOR WAS TESTED AND FOUND TO BE FUNCTIONING NORMAL. WE WERE UNABLE TO DETERMINE THE CAUSE OF THE FAILURE. THE PILOT REPORTED IT WAS COLD AT ALTITUDE AND NOT SURE IF THE BOOTS WERE ACTIVATED. (TC NR 20061214003) 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20070129001902007012900190NE 2007 1 29 CA061214004 220061214G72305009T34P01 BLADE GE 5012T75624 GE CT58 CT581402 30011NE COMPRESSOR MISSING W O OTHER R PARTIAL RPM/PWR LOSS ININSP/MAINT 1 CA 893 HAAH2079 (CAN) RECEIVED THIS ENGINE WITH A DEFECT OF LOW POWER. IT WAS RUN ON THE TEST STAND TO CONFIRM THE POWER OUTPUT WHICH WAS 1440 SHP. WHEN THE ENGINE WAS DISASSEMBLED THEY FOUND THAT A BLADE WAS MISSING FROM THE COMPRESSOR 4TH STAGE. THERE WAS NO DAMAGE TO THE FIRST 3 SECTIONS BUT IT RESULTED IN DAMAGING THE DOWNSTREAM BLADES AND VANES. THE 4TH STAGE BLADES ARE CURRENTLY AT INVESTIGATIION. THIS ENGINE IS OWNED BY OPERATOR AND A COPY OF THIS SDR WILL BE SUBMITTED. THERE IS MORE INFORMATION TO FOLLOW. THE OWNER OF THE ENGINE IS HELI-ONE AND IT WAS BEING OPERATED ON A POWER BY THE HOUR PROGRAM. (TC NR 20061214004) 4 U 1E3 20070125002412007012500241GL 2007 1 25 CA061215001 220061202G7261 FILTER LKHEED382 382G 526414USO ALLSN 501D 501D22A 03006GL HAMSTD54H 54H60117 NE SCAV PUMP UNKNOWN W EA ENGINE SHUTDOWN UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CLCLIMB 1 CA (CAN) ON DEPARTURE, THE CREW OBSERVED NR 2 ENGINE OIL LEVEL DROPPING TO 2.75 GAL. WITH A LOW OIL LIGHT ILLUMINATED. THE AIRCRAFT RETURNED TO POINT OF DEPARTURE. MAINTENANCE REPLACED THE NR 2 SCAVENGE OIL FILTER AND REPLENISHED THE OIL QUANTITY TO 10 GAL. THE AIRCRAFT WAS FOUND SATISFACTORY AND RETURNED TO SERVICE. (TC NR 20061215001) 2H74 4T4 T A1SO E282 6 CP906 20070125002422007012500242CE 2007 1 25 CA061215002 120061212G5520115520219 HINGE BEECH BEECH 100 100BEECH 1152916CE GARRTTTPE331TPE3316252B 01514WP HARTZLHCB4T HCB4TN5 GL ELEVATOR DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA 9051 BE114A (CAN) DURING PHASE NR 2 INSPECTION, IT WAS NOTICED THAT THE LT ELEVATOR WAS LOOSE AT THE OB HINGE. AREA INSPECTED AND FOUND THAT THE 4 BOLTS THAT ATTACH THE HINGE TO THE HORIZONTAL STAB WERE LOOSE. THE HINGE WAS REMOVED AND FOUND THAT THE HOLES WERE ELONGATED. THE HINGE AND ATTACHING STRUCTURE WERE REPLACED. 1L72 3T4 T A14CE E2WE 6 CP40EA 20070125002432007012500243 2007 1 25 CA061216001 420061214G3100A6611 IGNITION SWITCH ROBSINR44 R44RAVENII 7640122WP LYC O540 IO540AE1A5 41530NE INSTRUMENT PANELOBSTRUCTED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) REPLACED IGNITION SWITCH DURING 2200 HR O/H AND REINSTALLED IN INSTRUMENT PANEL. THE SEATING OF THE SWITCH STOPPED THE CONSOLE FROM OPENING AGAIN. THE SWITCH WAS REMOVED AND RESEATED TO ALLOW TRAVEL PAST THE INSTRUMENT CONSOLE. WE COULD NOT ALIGN THE SWITCH TO PREVENT THE TERMINAL (RT MAG CONNECTION) FROM CONTACTING THE SIDE WALL OF THE LOWER CONSOLE. THE TERMINAL ONLY MAKES CONTACT DURING THE TRANSITION FROM OPEN TO CLOSE AND VICE-VERSA. ONCE THE CONSOLE IS CLOSED THERE IS NO CONTACT OF THE TERMINAL, SIDEWALL OR LIP. WE ARE TALKING WITH MFG TO SEE IF THERE MAYBE A FIX. COULD BE IGNITION SWITCH MAYBE HAVE TO BE DESIGNED A LITTLE SMALLER OR MORE ROOM ON PANEL. (TC NR 20061216001) 1G71 3O3 O H11NM 1E4 20070125002442007012500244CE 2007 1 25 CA061216002 120061215G32421013810127 VALVE BEECH 300 300BEECH 1152930CE PWA PT6 PT6A60A 52043NE HARTZLHCB4M HCB4MP3 GL LANDING GEAR FALSE INDICATIONW K NONE N FALSE WARNING ININSP/MAINT 1 CA 28 (CAN) NEW VALVE WAS INSTALLED. LANDING GEAR VALVE FAILS TO INDICATE THAT IT IS OPEN WHEN SELECTED. VALVE WORKS CORRECTLY, BUT FAILS TO INDICATE TO CREW THAT IT IS WORKING. SEEMS TO BE JUST AN ISSUE WITH THE INDICATION SIDE OF THE VALVE AND NOT THE ACTUAL MECHANICS. (TC NR 20061216002) 2L72 4T4 T A24CE E4EA 6 CP56GL 20070125002452007012500245NM 2007 1 25 CA061216003 120061212G2910BACH8C08NN0290 LINE BOEING727 727243 138408DNM HYD SYSTEM LEAKING W A UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CLCLIMB 1 CA (CAN) AFTER T/O DURING CLIMB (B) PUMP LOW PX LITE ILLUMINATED WITH FLUID QTY DROP. RETURNED TO DEPARTURE, HYD LINE REPLACED IN B COMPT. (TC NR 20061216003) 2L73 4F RTA3WE 20070125002462007012500246SO 2007 1 25 CA061217001 120061216G32104025700 TORQUE LINK PIPER PA31 PA31 7103102SO LYC O540 TIO540A1B 41532EA HARTZLHCE2Y HCE2YR2 GL RT MLG STRUT BROKEN W O OTHER O OTHER LDLANDING 1 CA (CAN) THE PILOT REPORTED NOTICING A VIBRATION DURING TAXI BUT ATTRIBUTED IT TO RUNWAY CONDITION. IN FLIGHT HE WAS UNABLE TO RETRACT THE LANDING GEAR. UPON LANDING HE WAS UNABLE TO EXECUTE TURNS. AFTER DEPLANING HE FOUND THE FORWARD LUG ON THE UPPER TORQUE LINK OF THE RT MLG BROKEN. THE TORQUE LINK ASSEMBLY WAS HELD IN PLACE ONLY BY THE BOTTOM TORQUE LINK ATTACH BOLT. THE BOLT THAT ATTACHES THE UPPER TORQUE LINK WAS MISSING ALONG WITH THE BROKEN LUG. A CAUSE COULD NOT BEEN DETERMINED. THE AIRCRAFT WAS TOWED TO THE HANGER. (TC NR 20061217001) 1L72 3O3 O A20SO E14EA 5 CP9EA 20070125002472007012500247EA 2007 1 25 CA061218001 120061216G2750855D1009 BPSU CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE TE FLAPS FAILED W A UNSCHED LANDING O OTHER CLCLIMB 1 CA (CAN) THE CREW REPORTED THAT CLIMBING THROUGH FL220 (FLAP FAILED) MESSAGE CAME ON. THE CREW ELECTED TO CONTINUE AND THE FLIGHT LANDED WITHOUT FURTHER INCIDENT. LINE MAINTENANCE FOUND THE FOLLOWING FAULT CODES 1-12-2B RH BPSU. FECU TEST CARRIED OUT NFF. WIRING BETWEEN FECU AND BPSU COMPLETED. BPSU REMOVED, NEW ONE INSTALLED AND RIGGED IAW AMM 27-51-10 FLAPS FUNCTION CHECKED SEVERAL TIMES AIRCRAFT RELEASED FOR SATISFACTORY TEST FLIGHT THEN RELEASED INTO SERVICE. 2L72 4F4 FRTA21EA E15NE 20070125002482007012500248EA 2007 1 25 CA061218002 220061126G7414K3823 BRUSH BLOCK SLICK FOUND FBA FBA2C 3640102EA LYC O540 IO540* 41532EA HARTZLHCC3Y HCC3YR GL MAGNETO WORN W K NONE O OTHER ININSP/MAINT 1 CA 587 05061176 (CAN) THE DISTRIBUTOR GEAR BRUSH WAS EXCESSIVELY WORN FOR HAVING 587.2 HOURS ON IT IN A COMPONENT DESIGNED WITH A 2000 HOUR TBD. BRUSH BUSHING AND MOUNT OF POOR QUALITY WHICH IF LEFT UNDETECTED WOULD RESULT IN FAILURE IN 2 OR 300 MORE HOURS IF BEARING AND BUSHING AND BRUSH. (TC NR 20061218002) 1H71 3O3 O A7EA 1E4 5 CP25EA 20070125002492007012500249SO 2007 1 25 CA061218003 220061106G7414K3823 DISTRIBUTOR GEARSLICK CESSNA206 U206F 2073333CE CONT O520 IO520F 17032SO HARTZLHCC3Y PHCC3YF1 GL MAGNETO BURNED W C ABORTED TAKEOFF RJ PARTIAL RPM/PWR LOSS WARNING INDICATION TOTAKEOFF 1 CA 727 05012258 (CAN) DURING RUNUP AND PRE-TAKE OFF THE PILOT OBSERVED LARGE MAG DROPS AND POWER FLUCTUATIONS. THE AIRCRAFT WAS BROUGHT INTO THE SHOP. THE MAGNETOS WERE REMOVED AND INSPECTED. UPON INSPECTION, IT WAS DISCOVERED BOTH DISTRIBUTOR BLOCK AND GEAR HOUSINGS WERE BURNED THRU AT THE BRUSH HOLDER. ONE BRUSH WAS MISSING. THE COIL WAS ARCING THRU TO THE MAGNET. INVESTIGATION DETERMINED THE BUSHINGS AND DISTRIBUTOR GEAR BRUSH HAS WORN ABNORMALLY. THE BUSHINGS GOT VERY LOOSE CAUSING THE SECONDARY BRUSH TO WEAR AND ARC. THE DISTRIBUTOR GEAR AND HOUSING ARE PLASTIC. THE PLASTIC MELTED AND BOTH MAGS WERE ABOUT TO TOTALLY FAIL, DO NOT KNOW HOW IT KEPT RUNNING. 1H71 3O3 O A4CE E5CE 5 CP25EA 20070125002532007012500253EU 2007 1 25 CA061218004 120061120G79300292005340 ENGINE SNIAS 350 AS350B3 8680954EU TMECA ARRIELARRIEL2B NE MAKING METAL W A UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 CA 779 22364 (CAN) AIRCRAFT HAD AN INFLIGHT ENGINE CHIP LIGHT. PILOT LANDED AS SOON AS POSSIBLE. AIRCRAFT WAS LANDED UNDER ITS OWN POWER (NORMAL LANDING). PILOT THEN SHUT THE AIRCRAFT DOWN TO CHECK ALL ENGINE CHIP DETECTORS. HE FOUND METAL ON THE ELECTRIC CHIP PLUG, ENGINE OIL TANK CHIP PLUG AND THE ENGINE MOI CHIP PLUG. ENGINE WAS REMOVED AND SENT TO MFG. ANOTHER ENGINE WAS INSTALLED. (TC NR 20061218004) 1G71 3U3 U H9EU E00054EN 20070125002552007012500255CE 2007 1 25 CA061218005 120060724G3110903640143 CIRCUIT BOARD BEECH 100 A100 1152915CE PWA PT6 PT6A28 EA HARTZLHCB4T HCB4TN3 GL ANNUNCIATOR PANEMALFUNCTIONED W K NONE N FALSE WARNING ININSP/MAINT 1 CA (CAN) ANNUNCIATOR PANEL SHOWED A FALSE WARNING INDICATION FOR MASTER CAUTION LIGHT. SYSTEM TROUBLESHOOTING CARRIED OUT AND FOUND FAULT WARNING CIRCUIT BOARD UNSERVICEABLE AND FAULT WARNING CIRCUIT BOARD REPLACED. 1L72 3T4 T A14CE E4EA 6 CP40EA 20070125002652007012500265GL 2007 1 25 CA061218006 220061205G7310 DRAIN MAST LKHEED382 382G 526414USO ALLSN 501D 501D22A 03006GL HAMSTD54H 54H60117 NE NR 2 ENGINE LEAKING W E ENGINE SHUTDOWN KJ FLUID LOSS WARNING INDICATION CLCLIMB 1 CA (CAN) ENROUTE AFTER MISSED APPROACH AT SNAP LAKE THE CREW OBSERVED A FUEL LEAK AT THE DRAIN MAST ON NR 2 ENGINE. THE ENGINE WAS SHUTDOWN AND THE AIRCRAFT CONTINUED TO DESTINATION WITHOUT FURTHER PROBLEM. MAINTENANCE DETERMINED THE LEAK SOURCE TO BE FROM THE MANIFOLD DRAIN COLLECTOR. THE MANIFOLD WAS CAPPED AND THE AIRCRAFT COMPLETED A SATIFACTORY GROUND RUN BEFORE RETURN TO SERVICE. (TC NR 20061218006) 2H74 4T4 T A1SO E282 6 CP906 20070507001112007050700111NE 2007 5 7 CA061218007 120061202G7931 OIL SYSTEM SKRSKYS64 S64E 8142604NE PWA JFTD12JFTD12A4A 52047NE ENGINE MALFUNCTIONED W EA ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION DEDESCENT 1 CA 638214 (CAN) THE AIRCRAFT WAS INVOLVED IN HELICOPTER LOGGING OPERATIONS. AS THE AIRCRAFT WAS APPROACHING THE LOG LANDING WITH A LOAD, THE FLIGHT CREW WERE ALERTED BY A LOW OIL PRESSURE WARNING LIGHT FOR THE NR (2) ENGINE. A SCAN OF THE CORRESPONDING OIL PRESSURE INDICATOR CONFIRMED THE ENGINE OIL PRESSURE HAD DROPPED TO 20 PSI. AS THE PILOT RELEASED THE LOAD OF LOGS ON THE LOG LANDING THE OIL PRESSURE RETURNED TO NORMAL. THE FLIGHT CREW ELECTED TO RETURN TO THE SERVICE LANDING TO HAVE THE MAINT PERSONNEL INVESTIGATE THE PROBLEM. ENROUTE THE LOW OIL PRESSURE LIGHT ILLUMINATED AGAIN WITH THE CORRESPONDING OIL PRESSURE INDICATION DROPPING TO 20 PSI. AT THIS TIME THE FLIGHT CREW ELECTED TO SHUTDOWN THE NR (2) ENGINE AS A2G72 4U4 U H4EA E15EA 20070125002662007012500266EA 2007 1 25 CA061218008 220061216G853005K21108 SLEEVE PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA HARTZLHCE3Y HCE3YR2A GL CYLINDER DAMAGED W K NONE K FLUID LOSS ININSP/MAINT 1 CA 930 RL90768A (CAN) DURING INSPECTION OIL WAS NOTED ON THE BOTTOM COWL OF ENGINE. UPON CLOSER INSPECTION, NR 4 CYLINDER WAS FOUND TO BE WET AT THE CYLINDER TO HEAD FLANGE. AFTER CLEANING, OIL WAS SEEN TO BE SEEPING FROM FLANGE AREA. THERE WAS NO VISIBLE CRACK SO DYE PENETRANT WAS CARRIED OUT, AT THIS TIME A PINHOLE WAS REVEALED. COMPRESSION WAS GOOD DURING THE INSPECTION, THE JUG WAS CHANGED OUT FOR A NEW ONE. (TC NR 20061218008) 1L72 3O3 O A20SO E14EA 5 CP33EA 20070507001122007050700112CE 2007 5 7 CA061218009 120061215G55201156100103 TORQUE TUBE BEECH 100 B100 1152919CE GARRTTTPE331TPE3316252B 01514WP HARTZLHCB4T HCB4TN5 GL ELEVATOR CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 958 (CAN) DURING COMPLIANCE WITH SB 2145, CHANGED OUT THE DUE TORQUE TUBES AND REPLACE THEM WITH INSPECTED ONES. WHEN THE LT WAS REMOVED A CRACK WAS NOTED GOING FROM THE TAPER PIN HOLE TO THE EDGE OF THE TORQUE TUBE MOUNT BRACKET. IT APPEARS THAT THE PIN WAS OVER-TORQUED DURING ASSEMBLY LEADING TO THE CRACK. (TC NR 20061218009) 1L72 4T4 T A14CE E2WE 6 CP40EA 20070507001922007050700192NE 2007 5 7 CA061218010 120061121G5302NAS146A37 BOLT SKRSKYS64 S64E 8142604NE PWA JFTD12JFTD12A4A 52047NE TAIL BOOM DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) THE AIRCRAFT WAS INVOLVED IN HELICOPTER LOGGING OPERATIONS. THE YARDING PROFILE WAS A DOWN HILL FLIGHT FROM THE HARVEST CUT BLOCK TO A ROAD SIDE LOG LANDING. AFTER ENCOUNTERING DOWN FLOWING WIND CONDITIONS THROUGH OUT THE FIRST LOGGING CYCLE OF THE DAY THE FLIGHT CREW ELECTED TO SHUTDOWN AND WAIT FOR MORE FAVORABLE WIND CONDITIONS. DURING A ROUTINE POST FLIGHT INSPECTION OF THE AIRCRAFT, THE MAINTENANCE PERSONNEL WERE CHECKING THE HORIZONTAL STABILIZER FOR GENERAL CONDITION AND SECURITY WHEN THEY DISCOVERED IT TO BE LOOSE. FURTHER INSPECTION OF THE STABILIZER TO PYLON FORWARD ATTACHMENT FITTINGS REVEALED THE BOLT THAT ATTACHES THE (2) FITTINGS WAS MISSING. A VISUAL INSPECTION OF THE ENTIRE AIRCRAFT UNCO2G72 4U4 U H4EA E15EA 20070507001132007050700113CE 2007 5 7 CA061218011 120061215G55201156100103 TORQUE TUBE BEECH 100 B100 1152919CE GARRTTTPE331TPE3316252B 01514WP HARTZLHCB4T HCB4TN5 GL ELEVATOR CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 988 (CAN) DURING COMPLIANCE WITH SB 2145 (REMOVED THE DUE TUBES TO SEND OUT FOR NDT AND REPLACE WITH INSPECTED SERVICEABLE ONES), A CRACK WAS DISCOVERED RADIATING FROM ONE OF THE TAPER PIN HOLES TO THE EDGE OF THE ATTACH BOSS ON THE LT TUBE. IT APPEARS THAT THE TAPER PIN WAS OVERTORQUED DURING ASSEMBLY CAUSING THE CRACK. THE TUBE HAS BEEN SCRAPPED. (TC NR 20061218011) 1L72 4T4 T A14CE E2WE 6 CP40EA 20070125002932007012500293NE 2007 1 25 CA061218012 220061215G7261 OIL SYSTEM PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL ENGINE CONTAMINATED W A UNSCHED LANDING CJ F.O.D. WARNING INDICATION NRNOT REPORTED 1 CA 8331 215 (CAN) NON ALLOWABLE DEBRIS FOUND IN OIL SYSTEM, CONFIRMED BY OIL ANALYSIS REPORT. ENGINE SENT BACK TO MANUFACTURER FOR INVESTIGATION. ENGINE EXCHANGED, WILL NOT BE SENT BACK TO THE OPERATOR. ENGINE TSO 214.7 TSN 8330.9 (TC NR 20061218012) 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20070125002942007012500294NM 2007 1 25 CA061218013 120061129G3260H1010153 SWITCH BOEING727 727223 1384074NM PWA JT8 JT8D15A 52051NE MLG MALFUNCTIONED W O OTHER N FALSE WARNING APAPPROACH 1 CA (CAN) NOSE GEAR GREEN LIGHT DID NOT ILLUMINATE WITH LANDING GEAR SELECTED DOWN. VISUALLY INSPECTED TO ENSURE NOSE GEAR WAS DOWN AND LOCKED THROUGH VIEWPORT AND CONFORMED NOSE GEAR WAS DOWN AND LOCKED. AS A PRECAUTIONARY ACTION NOSE GEAR LOCK SWITCH REMOVED AND REPLACED ALONG WITH CONNECTOR D298 IAW MM 32-61-71. FUNCTION CHECKED SERVICEABLE. NO FURTHER OCCURRENCE REPORTED. (TC NR 20061218013) 2L73 4F4 F A3WE E2EA 20070125002952007012500295GL 2007 1 25 CA061218014 320061218G6111A163395 SEAL CESSNA206 TU206G 2073357CE CONT O520 TSIO520M 17040SO MCAULYD3A34 D3A34C402 GL PROPELLER LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA 226 810380 810380 (CAN) BLADE GREASE SEAL FAILED. GREASE LEAVING HUB. PROP REMOVED AND SENT TO REPAIR FACILITY WHERE NEW SEALS WERE INSTALLED. PROP REINSTALLED AND A/C SERVICEABLE (TC NR 20061218014). 1H71 3O3 O A4CE E8CE 5 CP47GL 20070125002962007012500296EA 2007 1 25 CA061218015 120061218G2913 PUMP CNDAIRCL601 CL6013A 8070802EA GE CF34 CF343A 30015NE HYDRAULIC SYS DAMAGED W O OTHER KJ FLUID LOSS WARNING INDICATION CRCRUISE 1 CA 1371 2353858 (CAN) LOST OF NR 3 SYSTEM HYDRAULIC FLUID IN FLIGHT. THE NR 3B PUMP HAS FAILED ON FLANGE GASKET. THE PUMP HAS BEEN REPLACED AND A\C RETURNED TO SERVICE. A/C HOURS: 6816:27 A/C CYCLES ; 7302 (TC NR 20061218015) 2L72 4F4 FRTA21EA E15NE 20070507001142007050700114SW 2007 5 7 CA061218016 120061108G291070060T000X186 HOSE BELL 427 427 1182207SW HYD SYSTEM CHAFED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) HOSE ASSEMBLY 70-060T000X186 (18.750 INCHES LONG) RUBS AGAINST SUPPORT 427-001-005 WHEN THE COLLECTIVE STICK IS DOWN AND THE CYCLIC STICK IS CENTER AND FULL FORWARD. (TC NR 20061218016) 1G71 3U R00001RC 20070125002972007012500297EA 2007 1 25 CA061218017 120061117G76032100140003 GEARBOX CNDAIRCL600 CL6002B16 1900305EA GE CF34 CF343A1 30015NE THROTTLE STIFF W O OTHER F FLT CONT AFFECTED LDLANDING 1 CA 4134 (CAN) PILOT REPORTED LT POWER LEVER STIFF TO MOVE AS COMPARED TO RT. TROUBLESHOOTING REVEALED THAT INPUT SHAFT ON GEARBOX ATTACHED, (COULD BARELY BE RETACTED BY HAND). SB601-0583 (TC NR 20061218017) 2L72 4F4 FRTA21EA E15NE 20070125002982007012500298NM 2007 1 25 CA061218018 120061218G271082740191053 ROD DHAV DHC8 DHC8102 2809003NM AILERON MISINSTALLED W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA (CAN) DURING C-CHECK, A INSPECTOR FOUND THE AILERON INPUT ROD NOT PROPERLY INSTALLED ON BOTH SIDE LT AND RT AILERON. THE ROD END WAS FABRICATED WITH A CUT OUT FOR AVOID THE CONTACT BETWEEN THE ROD END AND THE QUADRANT SHAFT. ON THE SAME A/C, WE FOUND THE BOTH ROD DIRECTLY IN CONTACT WITH THE SHAFT IN FULL TRAVEL POSITION. ATTACH 2 VERY CLEAR PICTURES WITH THIS FDR. (TC NR 20061218018) 2H72 4T RTA13NM 20070125002992007012500299 2007 1 25 CA061218019 420061218G611305503214 BULKHEAD CESSNA172 172N 2072434CE LYC O320 O320D2J 41508EA MCAULY1C160 1C160DTM GL SPINNER CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 50 (CAN) THIS AIRCRAFT HAS HAD ALL THE AFT BULKHEAD AND HEAVIER SPINNER UPGRADES AND HAS HAD IT ALL ASSEMBLED IAW THE LATEST SB. THE (FORWARD SPINNER BULKHEAD) IS CRACKED AGAIN WITH LESS THEN 50 HOURS TSN, CRACKS RADIATING .2500 TO 1 INCH FROM 3 OF THE 6 HOLES. YOU HAVE TO LOOK VERY CARFULLY AS THE CRACKS RADIATING FROM THE PROP BOLT HOLES ARE VERY FINE AND HIDE UNDER THE FACTORY PRIMER. (TC NR 20061218019) 1H71 3O3 ONT3A12 E274 5 NP910 20070125003002007012500300EA 2007 1 25 CA061218020 120061124G61238190026 PRESSURE SWITCH DHAV DHC6 DHC6300 2802606EA PWA PT6 PT6A27 52043EA HARTZLHCB3T HCB3TN3 GL AUTOFEATHER FAILED W K NONE L NO TEST ININSP/MAINT 1 CA (CAN) ON INVESTIGATION OF THE REPORTED AUTOFEATHER DEFECT, THE LT ENGINE PRESSURE SWITCH, PN 8190026, WAS FOUND TO BE DEFECTIVE. REPLACEMENT OF THE COMPONENT CURED THE PROBLEM WHICH IS CONSIDERED TO BE AN ISOLATED RANDOM FAILURE. (TC NR 20061218020) 1H72 3T4 TRTA9EA E4EA 6 CP15EA 20070125003212007012500321NM 2007 1 25 CA061219001 120061126G7500655881313 DUCT BOEING727 727225 1384077NM PWA JT8 JT8D15A 52051NE BLEED AIR SUPPLYDISCONNECTED W O OTHER J WARNING INDICATION CRCRUISE 1 CA (CAN) LOWER AFT BODY HEAT WARNING LIGHT ILLUMINATED IN FLIGHT. FLIGHT CREW FOLLOWED EMERGENCY CHECKLIST AND LIGHT EXTINGUISHED WHEN NR 3 BLEED AND THRUST LEVER CLOSED. UPON INVESTIGATION MAINTENANCE DISCOVERED SUPPLY DUCT FORWARD OF STA 1183 DISCONNECTED AND DUCT DAMAGED. DUCT AND CLAMPS REPLACED, ENGINE RUNS AND LEAK CHECKS CARRIED OUT. NO FURTHER PROBLEMS NOTED. (TC NR 20061219001) 2L73 4F4 F A3WE E2EA 20070125003222007012500322NM 2007 1 25 CA061219002 120061116G561058935733 WINDOW BOEING727 727223 1384074NM PWA JT8 JT8D15A 52051NE COCKPIT CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING SERVICING THE L4 WINDOW WAS FOUND CRACKED. WINDOW REPLACED IAW MM 56-11-31, FUNCTION CHECKED SERVICEABLE WITH NO FURTHER FAULTS REPORTED. (TC NR 20061219002) 2L73 4F4 F A3WE E2EA 20070125003242007012500324NM 2007 1 25 CA061219003 120061122G3242 DISC BOEING727 727223 1384074NM PWA JT8 JT8D15 52051NE BRAKE ASSY DETACHED W O OTHER O OTHER TXTAXI/GRND HDL 1 CA A0726 (CAN) WHILE TOWING AIRCRAFT TO LINE IT WAS REPORTED THAT NR 1 BRAKE WAS TRYING TO LOCK UP. UPON REMOVAL OF BRAKE ASSEMBLY THE DISC RING WAS FOUND DETACHED FROM THE ASSEMBLY. A RIVET WAS FOUND SHEARED AND THE DISC RING CAME APART. FURTHER TO FOLLOW AFTER STRIP REPORT IS RECEIVED FROM OVERHAUL FACILITY. (TC NR 20061219003) 2L73 4F4 F A3WE E2EA 20070507001152007050700115GL 2007 5 7 CA061219004 220061121G732323036657 GOVERNOR BELL 206 206L 1181522SW ALLSN 25OC 250C20R GL ENGINE ERRATIC W K NONE O OTHER ININSP/MAINT 1 CA 1889 (CAN) HIGH TIME GOVERNOR TSO 1889.2, REMOVED FOR O/H DUE TO ERRATIC RPM REPLACED WITH NEW GOVERNOR PN 23076061 SN HR47346 TSN 0:0 (TC NR 20061219004) 1G71 3U3 U H2SW E4CE 20070507001162007050700116GL 2007 5 7 CA061219005 220061121G7323718513 ACTUATOR BELL 206 206L 1181522SW ALLSN 25OC 250C20R GL ENGINE FAILED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) REMOVED LINEAR ACTUATOR PN 7185-13 SN 0296A DUE TO INTERNAL LOCKING CLIP FALLING OFF. INSTALLED SERVICEABLE USED LINEAR ACTUATOR PN 206-062-721-003 SN 11842. (TC NR 20061219005) 1G71 3U3 U H2SW E4CE 20070507001172007050700117SO 2007 5 7 CA061219006 120060123G2497KA39 CONVERTER PIPER PA31 PA31350 7103110SO NR 1 NAV COMM MALFUNCTIONED W O OTHER O OTHER CRCRUISE 1 CA (CAN) VOLTAGE CONVERTER SUPPLYING POWER TO NR 1 NAV COM FAILED CAUSING LOSS OF POWER TO RADIO (TC NR 20061219006) 1L72 3O A20SO 20070507001182007050700118CE 2007 5 7 CA061219007 120061106G24971385 RELAY BEECH 100 A100 1152915CE PWA PT6 PT6A28 EA HARTZLHCB4T HCB4TN3 GL OVERVOLTAGE FAILED W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA (CAN) AFTER TAKEOFF ON CLIMB-OUT THE RT GENERATOR CHARGING SYSTEM FAILED. THE AIRCRAFT RETURNED TO BASE. SYSTEM TROUBLESHOOTING CARRIED OUT AND FOUND THE OVER VOLTAGE RELAY HAD FAILED. (TC NR 20061219007) 1L72 3T4 T A14CE E4EA 6 CP40EA 20070125003262007012500326CE 2007 1 25 CA061219009 120060913G8010S1991A1 RELAY CESSNA150 150M 2071830CE CONT O200 O200A 17020SO MCAULY1A102 1A102OCM GL STARTER STUCK W K NONE O OTHER ININSP/MAINT 1 CA (CAN) POWER ON STARTER WITH WHEN MASTER SWITCH ON. FOUND MASTER RELAY STUCK IN POSITION. NEW RELAY S-1991-A1 INSTALLED. 1H71 3O3 O 3A19 E252 5 NP918 20070125003272007012500327SW 2007 1 25 CA061219010 120061215G80113108281 INSERT SWRNGNSA227 SA227AC 8780603SW GARRTTTPE331TPE33111U 01514WP MCAULY4HFR344HFR34C652 NE STARTER WORN W K NONE J WARNING INDICATION ININSP/MAINT 1 CA (CAN) UPON START PROP STARTED TO ROTATE AND THEN STOPPED. STARTER CONTINUED TO TURN. TORLON INSERT WAS WORN ENOUGH THAT THE STARTER TURNED INSIDE THE TORLON INSERT. INSERT WAS REPLACED AND AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20061219010) 2L72 4T4 TRTA8SW E4WE 6 C3PNE 20070125003282007012500328NE 2007 1 25 CA061219011 220061107G7530 LINE AEROSPATR42 ATR42* 8680900EU PWA 120 PW120 NE P3 FRACTURED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) DURING A MAINTENANCE TEST FLIGHT A LOUD NOISE WAS HEARD ACCOMPANIED BY AN ENGINE FIRE WARNING. THE ENGINE WAS SHUTDOWN IN FLIGHT AND FIRE BOTTLES DISCHARGED. SUBSEQUENT INSPECTION REVEALED A FRACTURED ENGINE P3 BLEED AIR TUBE. (TC NR 20061219011) 2H72 4T4 TRTA53EU E20NE 20070125003292007012500329NE 2007 1 25 CA061219012 220061022G7200 ENGINE CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE UNKNOWN W O OTHER K FLUID LOSS NRNOT REPORTED 1 CA (CAN) IN FLIGHT A LOUD NOISE WAS HEARD AND THE WINDSHIELD BECAME COVERED IN OIL. A FORCED LANDING FOLLOWED RESULTING IN AIRFRAME DAMAGE. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED. 1H71 3T3 T A37CE E4EA 20070125003302007012500330EA 2007 1 25 CA061219013 220061103G75303035279 TUBE DHAV DHC7 DHC7103 2802710EA PWA PT6 PT6A50 52043EA HAMSTD24PF 24PF305 GL FCU FRACTURED W E ENGINE SHUTDOWN R PARTIAL RPM/PWR LOSS CLCLIMB 1 CA (CAN) ENGINE POWER ROLLED BACK UNCOMMANDED DURING CLIMB. THE ENGINE WAS SHUTDOWN IN FLIGHT AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE. SUBSEQUENT INSPECTION REVEALED A FRACTURED P3 PRESSURE LINE TO THE FUEL CONTROL UNIT. (TC NR 20061219013) 2H74 4T4 T A20EA E4EA 6 CP1NE 20070125003312007012500331 2007 1 25 CA061219014 320061109G6110 SEAL BAG ATP ATP EU PWA PW120 PW126A NE PROPELLER SHAFT LEAKING W E ENGINE SHUTDOWN KJ FLUID LOSS WARNING INDICATION CRCRUISE 1 CA (CAN) DURING CRUISE, THE ENGINE OIL PRESSURE BEGAN TO FLUCTUATE IN THE RED BAND. THE ENGINE WAS SHUTDOWN IN FLIGHT AND THE AIRCRAFT RETURNED TO POINT OF DEPARTURE. SUBSEQUENT INSPECTION REVEALED A LEAK AT THE PROP SHAFT OIL SEAL. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061219014) 2L72 4T4 TRTA27NM E2ONE 20070125003362007012500336EA 2007 1 25 CA061219015 220061101G7200 ENGINE EMB 110 EMB110* SO PWA PT6 PT6A34 52043EA DAMAGED W E ENGINE SHUTDOWN RJ PARTIAL RPM/PWR LOSS WARNING INDICATION DEDESCENT 1 CA (CAN) ON TAKEOFF, ENGINE OIL PRESSURE WAS SEEN TO FLUCTUATE. THE FIGHT CONTINUED AND ON DESCENT ENGINE OIL PRESSURE FELL TO ZERO RESULTING IN A PROPELLER AUTOFEATHER. THE ENGINE WAS SHUTDOWN IN FLIGHT. GROUND INSPECTION REVEALED INTERNAL ENGINE DAMAGE. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 1L72 4T4 TRTA21SO E4EA 20070125003382007012500338CE 2007 1 25 CA061219016 120061116G7312311705601 HEATER BEECH MU300 400BEECH CE PWA JT15 JT15D5 52112NE FUEL LEAKING W E ENGINE SHUTDOWN KRJFLUID LOSS PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 1 CA (CAN) DURING FLIGHT ENGINE FUEL PRESSURE BEGAN TO FLUCTUATE FOLLOWED BY AN UNCOMMANDED POWER REDUCTION. THE ENGINE WAS SHUTDOWN IN FLIGHT AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC NR 20061219016) 2H72 4F4 FRTA16SW E25EA 20070125003402007012500340NE 2007 1 25 CA061219017 220061115G7310 MANIFOLD CESSNA560 560XL 2076702CE PWA 545 PW545A NE FUEL SYSTEM LEAKING W EA ENGINE SHUTDOWN UNSCHED LANDING AKJFLAME/FIRE FLUID LOSS WARNING INDICATION DEDESCENT 1 CA (CAN) ON DESCENT THE ENGINE FIRE WARNING ACTIVATED AND THE ENGINE WAS SHUTDOWN IN FLIGHT. POST FLIGHT INSPECTION REVEALED LEAKAGE FROM THE ENGINE FUEL MANIFOLD AND EVIDENCE OF BURNING OF THE ENGINE INNER BYPASS DUCTING. (TC NR 20061219017) 2L72 4F4 FRTA22CE E00059EN 20070125003442007012500344EA 2007 1 25 CA061219020 220061115G7200 ENGINE DHAV DHC6 DHC6200 2802620EA PWA PT6 PT6A27 52043EA FAILED W D RETURN TO BLOCK RJ PARTIAL RPM/PWR LOSS WARNING INDICATION TXTAXI/GRND HDL 1 CA 24085 (CAN) DURING TAXI, THE ENGINE EMITTED A NOISE AND LOST POWER. SUBSEQUENT INSPECTION REVEALED INTERNAL ENGINE DAMAGE. MFG WILL INVESTIGATE AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. 1H72 3T4 TRTA9EA E4EA 20070125003662007012500366NE 2007 1 25 CA061219021 220061120G7261JT5D5 ENGINE BEECH MU300 400BEECH CE PWA JT15 JT15D5 52112NE MALFUNCTIONED W E ENGINE SHUTDOWN J WARNING INDICATION DEDESCENT 1 CA 100119 100119 (CAN) THE ENGINE OIL FILTER BYPASS INDICATOR ACTIVATED IN DESCENT AND THE ENGINE WAS SHUTDOWN IN FLIGHT. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED. 2H72 4F4 FRTA16SW E25EA 20070125003672007012500367EA 2007 1 25 CA061219022 220060925G7261PT6A64 ENGINE SOCATATBM TBM700 8682000EU PWA PT6 PT6A64 EA LEAKING W E ENGINE SHUTDOWN KJ FLUID LOSS WARNING INDICATION CRCRUISE 1 CA 111106 (CAN) IN FLIGHT THE ENGINE OIL TEMPERATURE INCREASED ACCOMPANIED BY A LOSS OF OIL PRESSURE. THE ENGINE WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED METAL CONTAMINATION OF THE OIL SYSTEM, INTERNAL OIL LEAKAGE AND SEIZURE OF THE REDUCTION GEAR BOX. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED. 1L71 3T4 TRTA60EU E4EA 20070125003682007012500368EU 2007 1 25 CA061219023 120061123G7712 ENGINE FOKKERF27 F27MK50 EU PWA PWA120PW125B NE MALFUNCTIONED W E ENGINE SHUTDOWN RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 1 CA (CAN) IN CRUISE THE ENGINE EXPERIENCED TORQUE FLUCTUATIONS ACCOMPANIED BY INCREASED ITT TEMPERATURES. THE ENGINE WAS SHUTDOWN IN FLIGHT AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE. MFG WILL MONITOR INVESTIGATION OF THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061219023) 2H72 4T4 TRTA817 E20NE 20070125003692007012500369NE 2007 1 25 CA061219024 220061126G7250 TURBINE BLADES AEROSPATR42 ATR42500 8680948EU PWA PW120 PW127 NE ENGINE DAMAGED W EC ENGINE SHUTDOWN ABORTED TAKEOFF J WARNING INDICATION TOTAKEOFF 1 CA (CAN) ON TAKE-OFF, THE ENGINE FIRE WARNING ACTIVATED AND THE CREW SHUT THE ENGINE DOWN IN FLIGHT AND DISCHARGED THE FIRE BOTTLES. THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE. SUBSEQUENT INSPECTION REVEALED DAMAGED POWER TURBINE BLADES AND METAL IN THE ENGINE OIL. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC NR 20061219024) 2H72 4T4 TRTA53EU E20NE 20070125003702007012500370SW 2007 1 25 CA061219025 120061120G56102719442003 WINDSHIELD SWRNGNSA226 SA226TC 8780404SW GARRTTTPE331TPE33110UA 01514WP COCKPIT FAILED W A UNSCHED LANDING O OTHER CRCRUISE 1 CA 3868 (CAN) DURING FLIGHT THE LT COCKPIT HEATED WINDSHEILD SHATTERED BUT REMAINED INTACT. THE AIRCRAFT IMMEDIATLY RETURNED TO THE AIRPORT AND THE WINDOW WAS REPLACED BY MAINTENANCE. NO CAUSE COULD BE DETERMINED AS TO WHY THIS WINDOW SHATTERED. (TC NR 20061219025) 2L72 4T4 TRTA8SW E4WE 20070125003712007012500371EA 2007 1 25 CA061219026 220061128G7250 TURBINE BLADES BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA ENGINE FAILED W O OTHER XJ ENGINE FLAMEOUT WARNING INDICATION CRCRUISE 1 CA (CAN) IN CRUISE THE ENGINE EMITTED A LOUD NOISE AND FLAMED OUT. SUBSEQUENT INSPECTION REVEALED FRACTURED TURBINE BLADES AND VANES AND A PUNCTURED GAS GENERATOR CASE. LIGHT IMPACT DAMAGE WAS FOUND ON THE AIRCRAFT WING LEADING EDGE AND FUSELAGE WINDOWS. MFG WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061219026) 1L72 4T4 T A24CE E4EA 20070125003722007012500372SW 2007 1 25 CA061219027 120061215G56102719442004 WINDSHIELD SWRNGNSA226 SA226TC 8780404SW GARRTTTPE331TPE33110UA 01514WP COCKPIT FAILED W A UNSCHED LANDING O OTHER CRCRUISE 1 CA 1299 (CAN) DURING FLIGHT THE RT COCKPIT HEATED WINDSHEILD SHATTERED BUT REMAINED INTACT. THE FLIGHT CREW DECALRED AN EMERGENCY AND RETURNED TO THE AIRPORT UNEVENTFULLY. THE WINDOW WAS REPLACED BY MAINTENANCE. THE CREW EXPLAINED THAT PRIOR TO THE WINDOW SHATTERING A ELECTRICAL DISCHARGE WAS WITNESSED GOING ACROSS THE WINDSHIELD. OTHER THAN THE STATIC DISCHARGE, NO CAUSE FOR THE WINDOW TO SHATTER HAS BEEN DETERMINED. (TC NR 20061219027) 2L72 4T4 TRTA8SW E4WE 20070125003732007012500373NM 2007 1 25 CA061219028 120061213G52306557204520 ROD BOEING727 727227 1384078NM PWA JT8 JT8D9A 52048NE CARGO DOOR BENT W EA ENGINE SHUTDOWN UNSCHED LANDING O OTHER CLCLIMB 1 CA (CAN) ON ROTATION, NR 2 CARGO DOOR LIGHT ILLUMINATED. NR 3 ENGINE SURGED AND A SHUTDOWN PROCEDURE WAS CARRIED OUT. THE A/C LANDED SAFELY, WHERE A LEVEL 1 BORESCOPE INSPECTION WAS CARRIED OUT, WITH NO FOD DAMAGE FOUND. UPON INSPECTION, THE CARGO DOOR WAS FOUND TO BE OPEN BUT IN THE LATCHED POSITION. THE CARGO DOOR WOULD NOT CLOSE. FURTHER INSPECTION FOUND 4 BENT DOOR HINGE ROD ARMS. THE NR 2 CARGO DOOR, HINGE ARMS AND POSITIONING SWITCH WERE REPLACED. THE ASSEMBLY FUNCTIONED PROPERLY AND THE A/C WAS RETURNED TO SERVICE. (TC NR 20061219028) 2L73 4F4 F A3WE E2EA 20070129003452007012900345EU 2007 1 29 CA061219029 220061210G7310 FUEL BRAERO748 HS7482A 4231001EU RROYCEDART DART5342 EU ROTOL R4304 R2124304 EU FUEL SYSTEM CONTAMINATED W A UNSCHED LANDING XJ ENGINE FLAMEOUT WARNING INDICATION CRCRUISE 1 CA (CAN) PILOT OBSERVED ENGINE NR 1 FUEL FILTER DE-ICING WARNING LIGHT ILLUMINATED IN CRUISE FLIGHT. SHORTLY AFTER APPLYING FUEL HEAT, ENGINE NR 1 QUIT. PILOT FEATHERED PROPELLER AND LANDED UNEVENTFUL. MAINT REMOVED ENGINE NR 1 LOW PRESSURE FUEL FILTER AND FOUND A LACK OF FUEL. MAINT THEN DRAINED CONTENTS OF NR 1 FUEL COLLECTOR TANK INTO A BUCKET AND OBSERVED .5 LITER OF WATER PRESENT IN FUEL. MAINT FILLED AND DRAINED TANK 3 MORE TIMES TO ENSURE ALL WATER CONTAMINATION HAD BEEN REMOVED. NR 1 ENGINE FUEL SYS WAS RESTORED IAW MM. ENGINE WAS RUN AND TESTED SERVICEABLE. MAINT CHECKED FOR WATER CONTAMINATION IN THE LT WING SUMP, RT WING SUMP AND NR 2 FUEL COLLECTOR TANK AND FOUND NO EVIDENCE OF WATER. OPERATOR CHECKED2L72 3T4 T A24EU A196 6 CP899 20070125003742007012500374SW 2007 1 25 CA061220001 120061220G275021903 CABLE BBAVIA8 8GCBC 1220803SW FLAP HANDLE ASSYFRAYED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) CABLE FOUND FRAYED AT FWD END WHERE CABLE BENDS HARD OFF OF HANDLE TRACK TO FWD CABLE ATTACH POINT. (TC NR 20061220001) 1H71 3O A21CE 20070125003752007012500375NM 2007 1 25 CA061220002 120061127G793130C2083 TRANSDUCER AMD FALC50FALCON2000 2730170NM OIL PRESS TRANSDUNSERVICEABLE W E ENGINE SHUTDOWN N FALSE WARNING NRNOT REPORTED 1 CA (CAN) ENGINE OIL PRESSURE INDICATION FLUCTUATED IN FLIGHT AND FELL BELOW 35 PSI. AS A PRECAUTION, THE ENGINE WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INVESTIGATION REVEALED A FAULTY MAIN OIL PRESSURE TRANSDUCER. (TC NR 20061220002) 2K72 4F RTA50NM 20070125003802007012500380EA 2007 1 25 CA061220003 220061022G7230 TURBINE BLADES DHAV DHC6 DHC6300 2802606EA PWA PT6 PT6A27 52043EA ENGINE DAMAGED W E ENGINE SHUTDOWN RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 1 CA 41691 (CAN) DURING CRUISE THE ENGINE EMITTED A LOUD NOISE ACCOMPANIED BY A DECAY ON ENGINE PARAMETERS. THE ENGINE WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED DAMAGE TO COMPRESSOR AND POWER TURBINE BLADES. MFG WILL MONITOR INVESTIGATION OF THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED. 1H72 3T4 TRTA9EA E4EA 20070125003822007012500382EA 2007 1 25 CA061220004 220061128G7200 ENGINE BEECH 1900 1900C 1154161CE PWA PT6 PT6A65B 52043EA MALFUNCTIONED W CE ABORTED TAKEOFF ENGINE SHUTDOWN E VIBRATION/BUFFET TOTAKEOFF 1 CA 32399 (CAN) THE ENGINE EMITTED A LOUD NOISE ON TAKE-OFF ROLL. TAKE-OFF WAS ABORTED AND THE ENGINE SHUTDOWN. MFG WILL MONITOR INVESTIGATION OF THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061220004) 2L72 4T4 TRTA24CE E4EA 20070125003832007012500383NE 2007 1 25 CA061220005 220061010G7210 BOLT BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE 1ST STAGE CARRIESHEARED W E ENGINE SHUTDOWN J WARNING INDICATION CRCRUISE 1 CA (CAN) IN CRUISE FLIGHT, ENGINE OIL PRESSURE WAS SEEN TO FLUCTUATE AND THEN DECAY TO ZERO. THE ENGINE WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INVESTIGATION REVEALED A SHEARED 1ST STAGE REDUCTION GEAR BOX CARRIER BOLT. (TC NR 20061220005) 2L72 4T4 TRTA24CE E26NE 20070125003842007012500384CE 2007 1 25 CA061220006 120061214G284066082813 INDICATOR CESSNA560 560XL 2076702CE PWA 545 PW545A NE FUEL SYSS CHAFED W O OTHER WJ INADEQUATE Q C WARNING INDICATION DEDESCENT 1 CA 4429 4429 (CAN) LT FUEL QUANTITY CAUTION LIGHT ILLUMINATES DURING DESCENT. FAULT CODE INDICATES PROBES NR 3 DEFECTIVE. PROBE NR 3 REPLACED AND FURTHER INVESTIGATION REVEALED THAT THE WIRING IN LT TANK FOUND CHAFING AT (2) PLACES (WS 116.0) ON TOP OF FUEL PILOT VALVE LINE DUE HARNESS ASSEMBLY WAS NOT SUPPORTED PROPERLY DURING THE PRODUCTION ASSEMBLY PROCESS. NO CHAFING WAS FOUND IN RT FUEL TANK, BUT SIMILAR DEFECTIVE ATTACHMENT WAS FOUND. A SERVICE CONDITION REPORT (SCR NR 268343) WAS DONE TO AIRCRAFT. (TC NR 20061220006) 2L72 4F4 FRTA22CE E00059EN 20070125003852007012500385 2007 1 25 CA061220007 120061218G3246 BEARING CFMINTCFM567CFM567B22 13802NE MLG WHEEL FAILED W O OTHER O OTHER TXTAXI/GRND HDL 1 CA * (CAN) ON DECEMBER 18, THE CREW REPORTED THAT SOME SLIGHT DRAG WAS FELT IN BRAKING UPON ARRIVAL. INVESTIGATION REVEALED WHAT APPEARS TO BE A NR 4 WHEEL, IB BEARING FAILURE. AN INVESTIGATION INTO THE ROOT CAUSE OF THE FAILURE HAS BEEN INITIATED AND THIS ITEM WILL BE UPDATED ONCE THOSE RESULTS ARE AVAILABLE (TC NR 20061220007) 4 F E00055EN 20070125003862007012500386NM 2007 1 25 CA061220008 120061216G2913623303 PUMP BOEING757 757236 1384971NM RROYCERB211 RB211535E43754555NE HYD SYSTEM FAILED W O OTHER KJ FLUID LOSS WARNING INDICATION NRNOT REPORTED 1 CA MX607076 (CAN) LT ACMP LEAKING FLUID CAUSING LOSS OF HYDRAULIC QUANTITY AND SYSTEM PRESSURE. AIRCRAFT LANDED AND WAS TOWED OFF THE RUNWAY DUE TO NO NOSE WHEEL STEERING. (TC NR 20061220008) 2L72 4F4 FRTA2NM E12EU 20070125003872007012500387WP 2007 1 25 CA061220009 220061219G75302762026311 LINE FRCHLDSA227 SA227DC 3377521SW GARRTTTPE331TPE33112UHR WP MCAULY4HFR344HFR34C652 NE BLEED AIR CRACKED W EA ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA (CAN) DURING CLIMB, THE ENGINE FIRE WARNING LIGHT ILLUMINATED. THE ENGINE WAS SHUTDOWN. THE FIRE LIGHT EXTINGUISHED, WHEN THE STOP FEATHER LEVERS WERE PULLED BACK. THE CREW BLEW A FIRE BOTTLE, DECLARED AN EMERGENCY AND LANDED. A DAMAGED FIRE DETECTOR (1000 DEG F) P/N 17343-61-600 WAS FOUND AND A CRACKED BLEED AIR LINE P/N 27-62026-311 (TC NR 20061220009) 2L72 4T4 TRTA18SW E4WE 6 C3PNE 20070125003882007012500388NM 2007 1 25 CA061221001 120061216G29136617303 PUMP BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17EU HYD SYSTEM FAILED W O OTHER J WARNING INDICATION DEDESCENT 1 CA 1754 (CAN) DURING DESCENT NR 1 ENG HYD PUMP CAUTION LIGHT ILLUMINATED. CONTINUED TO DESTINATION AIRPORT FOR LANDING WITH OUT INCIDENT. MAINTENANCE CONFIRMED NR 1 ENG DRIVEN PUMP INTERNAL FAILURE. CASE DRAIN AND PRESSURE FILTERS CONTAMINATED WITH METAL. (TC NR 20061221001) 2H72 4T4 TRTA13NM E00062EN6 CP17BO 20070125003892007012500389CE 2007 1 25 CA061221002 120061218G52105043003211 LATCH BEECH 100 A100 1152915CE PWA PT6 PT6A28 EA MCAULY4HFR344HFR34C762 NE PAX DOOR BROKEN W O OTHER O OTHER CRCRUISE 1 CA (CAN) DURING FLIGHT THE CREW NOTICED AIR LEAKING OUT THE PASSENGER DOOR AND THE AIRCRAFT BEGAN TO DEPRESSURIZE. THE CREW DESCENDED TO 9000 FT FOR THE REMAINDER OF THE FLIGHT AND LANDED WITHOUT FURTHER INCIDENT. UPON LANDING THEY NOTICED THE LT UPPER DOOR HOOK WAS UNSERVICEABLE. FURTHER INSPECTION BY MAINTENANCE REVEALED THAT THE AFT CABIN DOOR HOOK LATCH BRACKET ATTACHMENT PIN P/N MS20392-2C35 HAD FAILED. THIS FAILURE RENDERED THE DOOR HOOK UNSERVICEABLE. THE DAMAGED WAS NOT LIMITED TO THE CLEVIS PIN IT WAS ALSO FOUND THAT THE MOUNTING BRACKET WAS BENT AND THE BUSHING WAS LOOSE. THE FRAME, THE BUSHING AND THE PIN WERE REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. (TC NR 20061221002) 1L72 3T4 T A14CE E4EA 6 C3PNE 20070507001212007050700121CE 2007 5 7 CA061221003 120061218G32301153800025 MOTOR BEECH 200 B200C 1152924CE PWA PT6 PT642A NE HARTZLHCD4N3HCD4N3A GL LANDING GEAR FAILED W O OTHER J WARNING INDICATION APAPPROACH 1 CA (CAN) DURING FLIGHT THE LANDING GEAR WOULD NOT EXTEND AND AN EMERGENCY WAS DECLARED. A MANUAL GEAR EXTENSION WAS COMPLETED THE (3) GREEN LIGHTS ILLUMINATED AND THE AIRCRAFT LANDED WITHOUT FURTHER INCIDENT. MAINTENANCE INVESTIGATED AND FOUND THAT THE LANDING GEAR MOTOR HAD FAILED. THE MOTOR WAS REPLACED, GEAR SWINGS COMPLETED AND THE AIRCRAFT RETURNED TO SERVICE. THIS MOTOR HAS A 2500 LANDING OVERHAUL INTERVAL AND ONLY HAD 390 LSO. (TC NR 20061221003) 1L72 4T4 T A24CE E4EA 5 CSTC 20070507001632007050700163 2007 5 7 CA061221004 420061218G2210 AUTOPILOT SYS BELL 412 412EP 1182205SW MALFUNCTIONED W H DEACTIVATE SYST/CIRCUITS F FLT CONT AFFECTED APAPPROACH 1 CA (CAN) DURING AN APPROACH TO RUNWAY 24 RIGHT AT THE MFG PLANT, BOTH AUTO-PILOTS WENT OFF LINE. THE MASTER CAUTION LIGHTS WERE OFF ON THE AUTO-PILOTS. A/C WAS ABLE TO LAND. (TC NR 20061221004) 1G72 4U H4SW 20070125003902007012500390EA 2007 1 25 CA061221005 120061221G2820AE7010000N130 HOSE CNDAIRCL604 CL604 1900301EA GE CF34 CF343B1 NE FUEL SYS RUPTURED W O OTHER KJ FLUID LOSS WARNING INDICATION TXTAXI/GRND HDL 1 CA 15 (CAN) UPON SHUTDOWN ON THE RAMP, CREW NOTICED A STRONG SMELL OF FUEL WHEN MAIN CABIN DOOR WAS OPENED. LT MAIN GEAR WAS SITTING IN A PUDDLE OF FUEL. FOUND ENGINE FUEL FEED AUX TANK LINE RUPTURED. (IPC 28-21-16 NR 285) (TC NR 20061221005) 2L72 4F4 FRTA21EA E15NE 20070125003912007012500391EA 2007 1 25 CA061221006 120061218G2700C6R1806135 CABLE ASSY DHAV DHC6 DHC6 2802606EA PWA PT6 PT6A27 52043EA HARTZLHCB3T HCB3TN3 GL FLT CONTROLS INCORRECT W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA (CAN) WHEN AN OPERATOR TRIED TO INSTALL ONE OF THESE CABLE ASSEMBLIES HE FOUND THAT THE END THAT ENGAGES THE SERVO CAPSTAN WOULD NOT FIT PROPERLY SO THAT THE LOCK SCREW COULD BE INSTALLED. UPON INVESTIGATION IT WAS FOUND THAT THE ORIGINAL DRAWING FOR THE CABLE ASSEMBLY PICTORIALLY SHOWED THIS CABLE END SWAGED ON INCORRECTLY. THE DRAWING HAS BEEN CORRECTED AND A SERVICE LETTER WILL BE ISSUED TO CHECK FOR ANY INCORRECTLY INSTALLED CABLE ASSEMBLIES OR SPARES ON HAND THAT MAY BE AFFECTED. (TC NR 20061221006) 1H72 3T4 TRTA9EA E4EA 6 CP15EA 20070125003922007012500392NE 2007 1 25 CA061222002 220061217G7310AE7010000N0130 HOSE CNDAIRCL604 CL604 1900301EA GE CF34 CF348E5A1 30015NE FUEL SYSTEM TORN W O OTHER KJ FLUID LOSS WARNING INDICATION NRNOT REPORTED 1 CA (CAN) FUEL LEAK WAS FOUND FROM HOSE ASSY P/N AE7010000N0130 AFTER THE SECOND ENGINE RUN. NOTE: PRIOR RUN, LINE WAS REPLACED IAW (DISCLOSURE LETTER), BATCH RECALL DUE TO DEFECTIVE HOSE (BATCH NR 8740850) (TC NR 20061222002) 2L72 4F4 FRTA21EA E00063EN 20070125003932007012500393EU 2007 1 25 CA061222003 120061214G28000725145 ELEMENT 0725185 AIRBUS320 A320232 3930326EU IAE V2527 V2527A5 NE REFUEL COUPLING LEAKING W O OTHER K FLUID LOSS NRNOT REPORTED 1 CA (CAN) WHILE REFUELING, IT WAS NOTICED THAT FUEL WAS LEAKING FROM THE ELEMENT ASSY. INITIALLY IT WAS THOUGHT THAT THE COUPLING HAD BEEN DAMAGED BUT ON INSPECTING THE PART IT WAS DETERMINED THAT THE 8 SECURING SCREWS HAD ROTATED APPROX A HALF TURN LOOSE. (TC NR 20061222003) 2L72 4F4 FRTA28NM E40NE 20070507001962007050700196SW 2007 5 7 CA061222004 120061204G6220204011116001 NUT BELL 205 205B SW LYC T53 T5317A 41549NE MAIN ROTOR HEAD CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 14698 A49 (CAN) THE ACORN NUTS WERE SENT OUT FOR NDT IAW THE REQUIREMENT OF THE OVERHAUL OF THE M/R HEAD ASSY. THE NDT SHOP FOUND A CRACK DEVELOPING NEAR THE BASE IN THE TRANSITION AREA OR CURL OF THE DOME AND THE GEAR PART OF THE ACORN NUTS. THE ESTIMATED TIME ON THE ACORN NUTS IS 14698 HOURS IAW M/R HEAD ASSY. (TC NR 20061222004) 1G71 4U4 U H1SW E17EA 20070125003942007012500394GL 2007 1 25 CA061222005 220061208G7261 OIL SYSTEM LKHEED382 382G 526414USO ALLSN 501D 501D22A 03006GL HAMSTD54H 54H60117 NE NR 2 ENGINE LEAKING W EA ENGINE SHUTDOWN UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CRCRUISE 1 CA (CAN) ENROUTE THE CREW OBSERVED LOW OIL QUANTITY ON THE NR 2 ENGINE. FLUID WAS OBSERVED DEPARTING THE DRAIN MAST. THE ENGINE WAS SHUTDOWN AND THE AIRCRAFT RETURNED TO POINT OF DEPARTURE WITHOUT FURTHER PROBLEM. MAINTENANCE FOUND AN AIR LEAK OCCURING AT THE OIL QUANTITY TRANSMITER ACCESS PANEL ON THE OIL TANK. FOAMING RESULTED DUE TO LOSS OF PNEUMATIC HEAD PRESSURE CAUSING THE SYSTEM TO VENT. THE ACCESS PANEL BOLTS WERE RETORQUED ENGINE OIL REPLENISHED. THE AIRCRAFT WAS GROUND RU AND RETURNED TO SERVICE. 2H74 4T4 T A1SO E282 6 CP906 20070125003952007012500395EU 2007 1 25 CA061222006 120061209G7712567775080 INDICATOR AEROSPATR42 ATR42300 8680920EU PWA 120 PW120 NE HAMSTD14SF 14SF5 NE TORQUE MALFUNCTIONED W A UNSCHED LANDING N FALSE WARNING CRCRUISE 1 CA (CAN) ENROUTE THE CREW OBSERVED DRAMATIC FLUCTUATION IN THE NR 2 ENGINE TORQUE INDICATOR. THE AIRCRAFT RETURNED TO POINT OF DEPARTURE WITHOUT INCIDENT. AFTER TROUBLE SHOOTING MAINTENANCE REPLACED THE NR 1 TORQUE INDICATOR AND THE SYSTEM WAS CHECKED SERVICEABLE. (TC NR 20061222006) 2H72 4T4 TRTA53EU E20NE 6 CP7NE 20070125003962007012500396CE 2007 1 25 CA061222007 120061220G24353022376 SEAL BEECH 200 B200 1152922CE PWA PT6 PT642A NE HARTZLHCE4N HCE4N3 NE ENGINE LEAKING W O OTHER KJ FLUID LOSS WARNING INDICATION CRCRUISE 1 CA (CAN) PILOT NOTICED OIL PRESSURE FLUCTUATIONS IN CRUISE FLIGHT. ENGINE LIMITS NOT EXCEEDED AND THE AIRCRAFT LANDED AT DESTINATION. ENGINE OIL WAS LOST THROUGH A LEAKING STARTER GENERATOR DRIVE GARLOC SEAL. SEAL REPLACED WITH NEW PN 3059046-01 IAW MFG CATEGORY 8 (OPTIONAL) SB 3420. GROUND RUNS C/O SATISFACTORY AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20061222007) 1L72 4T4 T A24CE E4EA 5 CP10NE 20070125003972007012500397EA 2007 1 25 CA061225001 120061223G77972572152545A CONNECTOR CNDAIRCL600 CL600* EA GE CF34 CF34* NE RT ENGINE SHORT W O OTHER EN VIBRATION/BUFFET FALSE WARNING APAPPROACH 1 CA (CAN) FLIGHT CREW REPORTED ENGINE VIBRATION. MAINTENANCE INSPECTION REVEALED A TAR LIKE SUBSTANCE ON ENGINE FAN BLADES. SUBSTANCE ALSO FOUND ON UNDERSIDE OF FLAPS BEHIND MAIN WHEELS. SUBSTANCE WAS CLEANED OFF AND FAN LUBE AND RUNS WERE CARRIED OUT, NO FIX VIBES STILL FLUCTUATING BETWEEN .2 AND 5.7 AT IDLE. N1 SENSORS SWAPPED STILL NO FIX. AFTER FURTHER INSPECTION ENGINE CONNECTOR J554 FOR THE RT ENGINE LOCATED BEHIND THE AFT CARGO BULKHEAD WAS FOUND TO HAVE AN INTERNAL SHORT. CONNECTOR REPLACED AND AIRCRAFT FOUND SERVICEABLE. (TC NR 20061225001) 2L72 4F4 FRTA21EA E15NE 20070125003982007012500398 2007 1 25 CA061227001 420061219G349734440058 WIRE AIRBUS310 A310300 3930305EU GE CF6 CF680C2* GL AIR COLLISION BURNED W O OTHER J WARNING INDICATION CRCRUISE 1 CA (CAN) ON ARRIVAL, FLIGHT CREW REPORTED TCAS AND RA FAILURE FLAGS ON BOTH IVSI’S DURING FLIGHT. WHILE TROUBLESHOOTING TCAS FAILURE, SEVERAL BURNED WIRES WERE DISCOVERED IN A BUNDLE LOCATED BEHIND THE ATC1 AND TCA RACK (500VU). THE WIRE SUSPECTED OF CAUSING THE DAMAGE IS THE TCAS POWER SUPPLY WIRE 3444-0058 BETWEEN CONNECTOR 221VC AND TERMINAL BOARD 1487VT MODULE AND PIN A. (REF A-310 AWM 34-44-01 PG 003 SHEET 1). ALL DAMAGED WIRES WERE REPLACED, CONNECTORS VERIFIED AND AS PRECAUTION AND MFG RECOMMENDATION THE TCAS PROCESSOR AND TCAS POWER SUPPLY CIRCUIT BREAKER WERE REPLACED. (TC NR 20061227001) 2L72 4F4 FRTA35EU E23EA 20070507001972007050700197CE 2007 5 7 CA061227002 120061226G79311013890235 TRANSMITTER BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE HARTZLHCE4A HCE4A3I NE OIL PRESSURE MALFUNCTIONED W A UNSCHED LANDING N FALSE WARNING CRCRUISE 1 CA (CAN) ENROUTE FROM RT OIL PRESSURE INDICATED 50 PSI. THERE WAS NO CORRESPONDING R LOW ANNUNCIATOR, DECLARED AN EMERGENCY AND PERFORMED A PRECAUTIONARY SHUTDOWN OF THE RT ENGINE. RETURNED WITHOUT INCIDENT. MAINTENANCE TROUBLESHOT INDICATION TO A FAULTY OIL PRESSURE TRANSDUCER. NEW TRANSDUCER INSTALLED, A/C GROUND RUN WITH NO FURTHER INDICATION PROBLEMS (TC NR 20061227002) 2L72 4T4 TRTA24CE E26NE 5 CP10NE 20070125003992007012500399EA 2007 1 25 CA061227003 220061222G8500 ENGINE CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA MCAULY1C160 1C160DTM GL MAKING METAL W K NONE O OTHER ININSP/MAINT 1 CA 2510 (CAN) DURING SCHEDULED MAINTENANCE, AT A 200HR. INSPECTION, METAL FOUND IN OIL. METAL TURNED OUT TO BE FROM NR 3 CYLINDER CONNECTING ROD, LOWER BEARING. (TC NR 20061227003) 1H71 3O3 ONT3A12 E274 5 NP910 20070125004002007012500400EA 2007 1 25 CA061227004 220061221G8500 ENGINE CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA MCAULY1A175 1A175ATM GL MAKING METAL W K NONE O OTHER ININSP/MAINT 1 CA 1452 (CAN) DURING 50 HR. OIL CHANGE, HEAVY BRASS-LIKE MATERIAL WAS NOTED IN THE OIL FILTER. CYLINDER WAS REMOVED TO INSPECT ENGINE CORE. CRANKSHAFT CENTER JOURNAL BEARING WAS FOUND TO BE DISINTEGRATING. ENGINE REMOVED FROM SERVICE. (TC NR 20061227004) 1H71 3O3 ONT3A12 E274 5 NP857 20070125004012007012500401EA 2007 1 25 CA061227005 220061218G8520 CRANKSHAFT PIPER PA34 PA34200 7103405SO LYC O360 IO360C1E6 41514EA HARTZLHCC2Y HCC2YK2 GL ENGINE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 1976 (CAN) LT ENGINE DEVELOPED AN OIL LEAK FROM CRANKSHAFT SEAL. DURING SEAL REPLACEMENT, IT WAS NOTICED THAT THE CRANKSHAFT FLANGE WHERE PROPELLER BOLTS ON, WAS CRACKED FROM ONE LIGHTNING HOLE TO THE OTHER. IT LOOKED AS IF THERE WAS AN INDENTATION ON THE BACK SIDE OF THE LIGHTNING HOLE. THIS IS THE POINT FROM WHICH THE CRACK APPEARED TO HAVE STARTED. THE MARK/INDENTATION APPEARS TO BE FROM A ROUND BAR BEING USED TO TURN THE CRANKSHAFT WHEN THE PROPELLER IS NOT INSTALLED. ENGINE IS BEING REMOVED FOR REPLACEMENT. (TC NR 20061227005) 1L72 3O3 O A7SO 1E10 5 CP920 20070129003482007012900348EA 2007 1 29 CA061227006 120061227G56106003303026 WINDSHIELD CNDAIRCL601 CL6013A 8070802EA GE CF34 CF343A 30015NE COCKPIT BROKEN W O OTHER O OTHER APAPPROACH 1 CA 2774 (CAN) RT WINDSHIELD FACE PLY BROKEN IN FLIGHT. APPROX. 7000 INCH ON APPROACH. FOD INSPECTION CARRIED OUT ON ENGINE INTAKE AND WINDSHIELD REPLACED. A/C HOURS; 6836 A/C CYCLES; 7326 (TC NR 20061227006) 2L72 4F4 FRTA21EA E15NE 20070507001992007050700199EU 2007 5 7 CA061228001 120061221G673010546662 HOUSING BOLKMS117 BK117A1 5626010EU ACTUATOR CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 2550 (CAN) DURING A ROUTINE DISASSEMBLY TO CORRECT SEAL LEAKAGE A CRACK WAS FOUND AT THE LEE PLUG ON THE FRONT OF THE ACTUATOR. THE CRACK EXTENDS UP TOWARDS THE SERVO VALVE (TC NR 20061228001) 1G72 3U H13EU 20070129003302007012900330GL 2007 1 29 CA061228002 220061215G7261 GASKET LKHEED382 382G 526414USO ALLSN 501D 501D22A 03006GL HAMSTD54H 54H60117 NE NR 1 ENGINE FAILED W EA ENGINE SHUTDOWN UNSCHED LANDING K FLUID LOSS CRCRUISE 1 CA 550302 (CAN) AFTER DEPARTING AND CLIMBING THROUGH 10K FEET THE CREW OBSERVED A LOW OIL QUANTITY CONDITION ON NR 1 ENGINE. VISUAL CONFIRMATION OF OIL LOSS ACCOMPLISHED AND NR 1 ENGINE SHUTDOWN. THE AIRCRAFT RETURNED WITHOUT INCIDENT TO POINT OF DEPARTURE. MAINTENANCE REPLACED THE NR 1 ENGINE SCAVENGE PUMP AND FILTER. ALSO REPLACED THE GASKET ON THE OIL TANK ACCESS PANEL FOR THE QUANTITY TRANSMITTER. THE AIRCRAFT WAS GROUND RUN AND RETURNED TO SERVICE. (TC NR 20061228002) 2H74 4T4 T A1SO E282 6 CP906 20070507002002007050700200CE 2007 5 7 CA061229001 120061227G32301153800025 MOTOR BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA HARTZLHCB3T HCB3TN3 GL MLG UNSERVICEABLE W O OTHER O OTHER DEDESCENT 1 CA 4 (CAN) WHEN LANDING GEAR ONLY EXTENDED HALFWAY. EMERGENCY EXTENSION USED TO EXTEND TO LANDING CONFIGURATION. MOTOR WAS INSTALLED AS AN OVERHAULED UNIT 4.4 HRS PRIOR TO FAILURE. C/B WAS FOUND TRIPPED UNDER CABIN FLOOR. BREAKER RESET AND GEAR CYCLED. MOTOR WAS LABORING TO OPERATE. NEW MOTOR INSTALLED AND GEAR CYCLES CARRIED OUT WITH NO FAULTS FOUND. (TC NR 20061229001) 1L72 4T4 T A24CE E4EA 6 CP15EA 20070129003312007012900331EA 2007 1 29 CA061229002 120061227G3320BC10065003 RECEPTACLE CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE CABIN DAMAGED W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CLCLIMB 1 CA (CAN) DURING CLIMB, PASSENGER ALERTED FA TO SMOKE SMELL IN REAR OF CABIN. SMOKE WAS THEN VISIBLY OBSERVED BY PASSENGERS AND FA. FLIGHT RETURNED TO DEPARTURE AIRPORT AND ERS WAS REQUESTED. AIRCRAFT WAS APPROX 2000 LBS OVERWEIGHT BUT LANDED AND TAXIED TO THE GATE WITHOUT FURTHER INCIDENT. TROUBLESHOOTING BY MAINTENANCE DETERMINED THAT THE SIDEWALL LIGHTING ASSEMBLY AT SEAT 6F TO BE AT FAULT. RECEPTACLE FOR LIGHT APPEARED PITTED AND MAY HAVE CAUSED LIGHT ASSEMBLY TO SHORT OUT. LIGHT ASSEMBLY WAS REPLACED WITH NO FURTHER EVIDENCE OF SMOKE OR ELECTRICAL SMELL. IAW AMM 05-51-01 PAGE 601 AND FIG 601 NO FURTHER OVER WEIGHT INSPECTIONS REQUIRED. AFTT 26345, TOTAL CYCLES 21861. (TC NR 20061229002) 2L72 4F4 FRTA21EA E15NE 20070129003322007012900332NM 2007 1 29 CA070102002 120061225G5610NP15790112 WINDSHIELD DHAV DHC8 DHC8* NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE COCKPIT CRACKED W A UNSCHED LANDING O OTHER CRCRUISE 1 CA (CAN) F/O WINDSHIELD SHATTER IN FLIGHT AT FL20. NO EVIDENCE OF ANY IMPACT. AIRCRAFT RETURNED TO BASE AND LANDED WITHOUT ANY FURTHER INCIDENT. WINDSHIELD ASSEMBLY WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20070102002) 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20070129003332007012900333NE 2007 1 29 CA070102003 220061223G8500R20007M2 ENGINE DOUG DC4 C54EDC 3021528WP PWA R2000 R20007M2 52023NE HAMSTD23E 23E50 NE MAKING METAL W E ENGINE SHUTDOWN EK VIBRATION/BUFFET FLUID LOSS NRNOT REPORTED 1 CA (CAN) ENGINE BEGAN TO RUN ROUGH, DECREASE IN OIL PRESSURE, ENGINE WAS SHUTDOWN AND FEATHERED. OIL SCREEN PULLED, MODERATE AMOUNT OF ALUMINUM FILINGS, ENGINE REMOVED AND SENT FOR OVERHAUL. NOTE: SUSPECT LINK PIN (TC NR 20070102003) 2L74 4R4 R A762 5E5 6 CP603 20070129003362007012900336EA 2007 1 29 CA070102004 120061219G2752 ACTUATOR CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE T/E FLAP EXCESS PLAY W O OTHER FJ FLT CONT AFFECTED WARNING INDICATION APAPPROACH 1 CA (CAN) ON APPROACH (FLAPS FAIL) CAUTION MESSAGE APPEARED WHEN THE CREW SELECTED FLAPS FROM 30 - 45 DEG. ON LANDING. MAINTENANCE INSPECTED THE A/C FLAP SYSTEM AND FOUND RT AND LT IB FLAP (O/B ACTUATORS HAD EXCESSIVE SIDE PLAY OVER 0.015) IAW AMM 27-53-01-400-801, ALSO RT NR3 AND NR5 FLEX DRIVES FOUND DEFECTIVE. ALL COMPONENTS WERE REPLACED AND THE A/C WAS RETURNED TO SERVICE UPON A SATISFACTORY TEST FLIGHT . FLAPS FAILED ON FINAL APPROACH AT 30 DEG. FURTHER INSP. WAS CARRIED OUT ON THE FLAP SYSTEM AND THE IB NR1 FLAP ACTUATORS WERE REPLACED DUE TO EXCESSIVE FORE AND AFT PLAY AND THE FLAP DRIVE UNIT WAS REPLACED. THE FLAP SYSTEM WAS RIGGED IAW AMM 27-53-00 AND GROUND/FUNCTION CHECKED SERVICEABLE. THE A/C WAS2L72 4F4 FRTA21EA E15NE 20070129003402007012900340EU 2007 1 29 CA070103002 120061229G561066642023 WINDSHIELD AIRBUS320 A320214 3930316EU CFMINTCFM56 CFM565B4P NE COCKPIT CRACKED W O OTHER M OVER TEMP NRNOT REPORTED 1 CA (CAN) WINDOW HEAT CONTROLLER MALFUNCTIONED CAUSING CAPT WINDSHIELD OUTER PLY TO CRACK. (TC NR 20070103002) 2L72 4F4 FRTA28NM E38NE 20070129003412007012900341NE 2007 1 29 CA070103003 220061201G7200PT6A42 ENGINE PIPER PA46 PA46500TP 7104622SO PWA PT6 PT6A42 52043NE MALFUNCTIONED W O OTHER R PARTIAL RPM/PWR LOSS CLCLIMB 1 CA (CAN) THE ENGINE WAS REPORTED TO LOSE POWER SHORTLY AFTER TAKEOFF, RESULTING IN A FORCED LANDING AND DAMAGE TO THE AIRCRAFT. MFG WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070103003) 1L71 3O4 TRTA25SO E4EA 20070129003422007012900342NM 2007 1 29 CA070103004 120061226G27303906001007 PCU BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA ROTOL R408 CR4086123F17EU RT ELEVATOR DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA 299 (CAN) MAINTENANCE NOTICE RT ELEVATOR DROOP WHEN PARKED. FURTHER INVESTIGATION FOUND BROKEN NR 3 RT PCU. ELEVATOR PCU FAILURE CAUSED DAMAGE TO THE HORIZONTAL STABILIZE STRUCTURE. (TC NR 20070103004) 2H72 4T4 TRTA13NM E00062EN6 CP17BO 20070129003432007012900343 2007 1 29 CA070103005 220061203G7321 SEAL AMD FALC50FALCON2000 2730170NM PW308C FUEL CONTROL LEAKING W E ENGINE SHUTDOWN KJ FLUID LOSS WARNING INDICATION CRCRUISE 1 CA (CAN) ENGINE OIL PRESSURE WAS REPORTED TO FLUCTUATE AND GRADUALLY DECREASE IN CRUISE. THE ENGINE WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED A LEAKING FUEL CONTROL DRIVE SEAL. (TC NR 20070103005) 2K72 4F RTA50NM 20070129003442007012900344NE 2007 1 29 CA070103006 220061207G726130B336201 CARBON SEAL DORNERDO32 DO328300 NM PWA 306 PW306B NE ENGINE LEAKING W E ENGINE SHUTDOWN KJ FLUID LOSS WARNING INDICATION DEDESCENT 1 CA (CAN) DURING DESCENT THE ENGINE LOW OIL PRESSURE WARNING ACTIVATED AND THE ENGINE WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED A LEAKING CARBON SEAL AT THE FUEL CONTROL DRIVE PAD. (TC NR 20070103006) 2H72 4T4 FRTA55NM E35NE 20070129001912007012900191NE 2007 1 29 CA070103007 220061211G7261 PUMP GULSTM200 200 4500308NM PWC PW306 PW306A 52165NE ENGINE MALFUNCTIONED W EA ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 CA (CAN) ENGINE OIL PRESSURE WAS REPORTED TO GRADUALLY DECREASE AND THE ENGINE WAS SHUTDOWN IN FLIGHT. THE AIRCRAFT DIVERTED FOR AN UNSCHEDULED LANDING. THE ENGINE OIL PRESSURE PUMP WAS SUBSEQUENTLY REPLACED. (TC NR 20070103007) 2L72 4F4 FRTA53NM E35NE 20070129001922007012900192NE 2007 1 29 CA070103008 220061209G7200PW305A ENGINE LEAR 60 60LEAR 5170707CE PWA 305 PW305A 52128NE FIRE W E ENGINE SHUTDOWN A FLAME/FIRE TXTAXI/GRND HDL 1 CA (CAN) ON START, FLAMES WERE SEEN EXITING THE ENGINE EXHAUST. THE START WAS ABORTED. MFG WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070103008) 2L72 4F4 FRTA10CE E35NE 20070129001932007012900193EA 2007 1 29 CA070103009 220061210G7250 TURBINE BLADES EMB 110 EMB110P1 3260122SO PWA PT6 PT6A34 52043EA HARTZLHCB3T HCB3TN3 GL ENGINE FRACTURED W E ENGINE SHUTDOWN ZRASIGNIFICANT FAILURE REPORTPARTIAL RPM/PWR LOSS FLAME/FIRE CRCRUISE 1 CA 42192 (CAN) DURING CRUISE ENGINE POWER REDUCED UNCOMMANDED, ACCOMPANIED BY A LOUD NOISE AND FLAMES EXITING THE EXHAUST. SUBSEQUENT INSPECTION REVEALED FRACTURED POWER TURBINE BLADES AND A SEIZED REDUCTION GEARBOX. MFG WILL MONITOR INVESTIGATION OF THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070103009) 1L72 4T4 T A21SO E4EA 6 CP15EA 20070129001942007012900194EA 2007 1 29 CA070103010 220060911G7200PT6A34 ENGINE EMB 110 EMB110* SO PWA PT6 PT6A34 52043EA FLAMED OUT W O OTHER X ENGINE FLAMEOUT NRNOT REPORTED 1 CA (CAN) THE ENGINE FLAMED OUT IN FLIGHT ACCOMPANIED BY A LOUD NOISE. MFG WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070103010) 1L72 4T4 TRTA21SO E4EA 20070129001962007012900196EA 2007 1 29 CA070104001 120061224G5610NP13932200 WINDOW CNDAIRCL600 CL6002B19 1900309EA COCKPIT UNKNOWN W K NONE O OTHER CRCRUISE 1 CA 11983 (CAN) MAINTENANCE REPLACED SIDE WINDOW. (TC NR 20070104001) 2L72 4F RTA21EA 20070129001972007012900197NE 2007 1 29 CA070104002 220061224G73216078T39P03 FCU CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE LT ENGINE MALFUNCTIONED W A UNSCHED LANDING F FLT CONT AFFECTED APAPPROACH 1 CA 10542 (CAN) (DIVERTED, WITH ENGINE PROBLEMS, CREW CALLED WHEN ON GROUND. ON APPROACH, THE LT ENGINE WOULD NOT IDLE BACK BELOW 79 PERCENT N1. IT WOULD RESPOND TO INPUTS ABOVE 79 PERCENT. CREW ELECTED TO SHUTDOWN THE ENGINE, AND DIVERT.) MX WAS UNABLE TO DUPLICATE THIS PROBLEM, WHILE INITIATING START, N1 RAN AWAY SHORTLY AFTER LIGHT OFF. MX REPLACED FCU. (TC NR 20070104002) 2L72 4F4 FRTA21EA E15NE 20070129001982007012900198EA 2007 1 29 CA070105001 120061230G5350 RADOME CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE FUSELAGE BIRD STRIKE W A UNSCHED LANDING O OTHER CLCLIMB 1 CA (CAN) AFTER DEPARTURE CREW WITNESSED A BIRD STRIKE ON THE NOSE OF THE AIRCRAFT. CREW ELECTED TO RETURN TO DEPARTURE AIRPORT AND LAND OVERWEIGHT (ESTIMATED AT 49200 LBS). AIR TRAFFIC CONTROL WAS NOTIFIED BUT EMERGENCY EQUIPMENT WAS NOT REQUIRED. MAINTENANCE INSPECTION DISCOVERED A DEAD SEAGULL WHICH HAD PENETRATED THE RADOME DAMAGING THE WEATHER RADAR ANTENNA AND THE NOSE BULKHEAD. FDR REMOVED FOR READING. FURTHER OVERWEIGHT LANDING INSPECTION NOT REQUIRED IAW FDR READOUT AND AMM 05-51-01 PAGE 609, SUBTASK 05-51-01-970-004 FOR IMPACT SPEED OF 120 FT/MIN. THE FOLLOWING PART REPLACEMENTS WERE COMPLETED: FDR P/N S800-20000-00. ULB DK120. RADOME P/N 4926-201. WEATHER RADAR ANTENNA P/N 622-9302-003. DAMAGE TO BULKHE2L72 4F4 FRTA21EA E15NE 20070129001992007012900199EA 2007 1 29 CA070105002 220061216G7250 TURBINE BLADES DHAV DHC6 DHC6300 2802606EA PWA PT6 PT6A27 52043EA HARTZLHCB3T HCB3TN3 GL ENGINE FRACTURED W O OTHER JY WARNING INDICATION ENGINE STOPPAGE CRCRUISE 1 CA (CAN) ENGINE OIL PRESSURE WERE REPORTED TO FLUCTUATE IN CRUISE FOLLWED BY A LOUD NOISE AND AN UNCOMMANDED ENGINE SHUTDOWN. SUBSEQUENT INSPECTION REVEALED METAL DEBRIS IN THE ENGINE OIL AND FRACTURED POWER TURBINE BLADES. MFG WILL MONITOR INVESTIGATION OF THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070105002) 1H72 3T4 TRTA9EA E4EA 6 CP15EA 20070129002002007012900200NE 2007 1 29 CA070105003 220061214G7250 TURBINE BLADES PWC PT6A114A CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE ENGINE FRACTURED W O OTHER Y ENGINE STOPPAGE CRCRUISE 1 CA 19232 19232 (CAN) THE ENGINE SUFFERED AN INFLIGHT SHUTDOWN IN CRUISE. SUBSEQUENT INSPECTION REVEALED THE AIRFRAME INLET AIR BOX PARTIALLY OPEN WITH A FASTENING PIN MISSING. THE ENGINE COMPRESSOR WAS FOUND STIFF TO ROTATE WITH DAMAGE EVIDENT TO THE SECOND STAGE STATOR AND THE POWER TURBINE BLADES WERE FOUND FRACTURED. MFG WILL MONITOR INVESTIGATION OF THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070105003) 1H71 3T3 T A37CE E4EA 20070129002032007012900203EA 2007 1 29 CA070106001 120061227G3320BC10065005 RECEPTACLE CNDAIRCL600 CL6002B19 1900309EA CABIN FAULTY W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CLCLIMB 1 CA (CAN) DURING CLIMBOUT PASSENGER ALERTED FA TO SMOKE SMELL IN REAR OF CABIN , SMOKE WAS THEN VISIBLY OBSERVED BY PASSENGERS AND FA. FLIGHT RETURNED TO DEPARTURE AIRPORT AND ERS WAS REQUESTED. AIRCRAFT WAS APPROX. 2000 LBS OVERWEIGHT BUT LANDED AND TAXIED TO THE GATE WITHOUT FURTHER INCIDENT. MAINTENANCE DETERMINED THAT THE SIDEWALL LIGHTING ASSEMBLY AT SEAT 6F TO BE AT FAULT. RECEPTACLE FOR LIGHT APPEARED PITTED AND MAY HAVE CAUSED LIGHT ASSEMBLY TO SHORT OUT. LIGHT ASSEMBLY WAS REPLACED IAW AMM 05-51-01 PAGE 601 (TC NR 20070106001) 2L72 4F RTA21EA 20070508001932007050800193EU 2007 5 8 CA070108004 120061221G6320350A32315520 CASE HALF SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1D1 NE GEAR BOX WORN W K NONE O OTHER ININSP/MAINT 1 CA 3727 (CAN) HALF SHELLS WERE WORN OUT DUE TO MOVEMENT OF THE SUN GEAR, WEARING S STEP INTO THE SHELLS. THERE IS NO PUBLISHED LIMITS ON THE SHELLS AND WE HAVE ASKED ECL FOR THIS INFORMATION. THERE IS NORMAL WEAR IN THIS AREA, THIS WAS A BIT EXCESSIVE WITH SLIVERS OF METAL COMING OFF THE PARTS. THIS WOULD HAVE LEAD TO A CHIP LIGHT EVENTUALLY. (TC NR 20070108004) 1G71 3U3 U H9EU E19EU 20070129002112007012900211EA 2007 1 29 CA070108005 120061228G4930388273010 FCU CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE APU LEAKING W O OTHER K FLUID LOSS TXTAXI/GRND HDL 1 CA 396 396 (CAN) DEC 28/06, AERO CALLOUT 061228/01, ON PUSHBACK, A RAMP AGENT NOTICED A PUDDLE OF FUEL ON THE GROUND AT THE BACK OF THE AIRCRAFT. APPARENTLY, FUEL WAS LEAKING FROM THE APU. THE CAPTAIN CHECKED THE LEAK AS F/O CALLED APRON. THE FIRE TRUCKS WERE CALLED AS WELL AS CONSOLIDATED FUELERS TO CLEAN UP THE AREA. THE PASSENGERS WERE DEPLANED AS A PRECAUTION. MAINTENANCE CONFIRMED THAT THE LEAK WAS FROM THE APU FCU DRAIN LINE, THEY THEN DEFERRED THE APU AND THE A/C DEPARTED WITHOUT INCIDENT. THE FCU WAS REPLACED AND LEAK CHECKS WERE CARRIED OUT. TEARDOWN REPORT TO FOLLOW. (TC NR 20070108005) 2L72 4F4 FRTA21EA E15NE 20070129002122007012900212NM 2007 1 29 CA070108006 120061227G322288295 NUT MESSIER 8800121 DHAV DHC8 DHC8106 2809020NM PWA PW121 PW121 52124NE HAMSTD14SF 14SF7 NE NLG BROKEN W K NONE O OTHER TOTAKEOFF 1 CA DCL051085 (CAN) SUSPECT CAP NUT SHEARED UPON TAKEOFF DUE TO THE UNEVEN RUNWAY. REF ATTACHED PILOTS REPORTS AND PHOTO`S OF DAMAGED CAP NUT. (TC NR 20070108006) 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20070508001942007050800194EU 2007 5 8 CA070108007 120061219G2910MS2771923 SWITCH SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1D1 NE COLLECTIVE INTERMITTENT W K NONE O OTHER ININSP/MAINT 1 CA (CAN) PROBLEM REPORTED BY PILOT IN DECEMBER ABOUT INTERMITTENT SWITCH. THIS HAPPENED ONCE IN THE FIELD. THE A/C WAS BROUGHT IN FOR AN INSPECTION AT THE END OF DECEMBER/06 AND THE SWITCH WAS REPLACED. BAD SWITCHES, SHOULD BE REPLACED WITH SOMETHING BETTER. (TC NR 20070108007) 1G71 3U3 U H9EU E19EU 20070129002142007012900214EA 2007 1 29 CA070109001 120061207G2820600624623 TUBE CNDAIRCL604 CL604 1900301EA GE CF34 CF343B1 NE FUEL SYSTEM BLOCKED W O OTHER K FLUID LOSS TXTAXI/GRND HDL 1 CA 65 (CAN) AUTO SHUTOFF DID NOT OCCUR DURING PRESSURE REFUELING OPERATIONS RESULTING IN FUEL SPILL ON RAMP. OPERATOR REPORTED SIMILAR PROBLEMS SINCE TAKING DELIVERY OF NEW AIRCRAFT. IT WAS FOUND THAT A NUMBER OF LT AND RT WING TRANSFER AND BALANCING PIPES (TUBES) HAD BEEN PARTIALLY OBSTRUCTED AT THE CONNECTING JOINTS BY SEALANT. AIRCRAFT OEM FIELD SERVICE REPRESENTATIVES WERE ON SITE FOR RECTIFICATIONS. (TC NR 20070109001) 2L72 4F4 FRTA21EA E15NE 20070129002202007012900220EA 2007 1 29 CA070109003 120061227G5220H341935 HOUSING CNDAIRCL600 CL6002B19 1900309EA ESCAPE HATCH CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 867 (CAN) ESCAPE HATCH OUTER HANDLE HOUSING WAS FOUND CRACK DURING AN AFTER STORAGE RETURNED TO SERVICE. INVESTIGATION IS IN PROGRESS. (TC NR 20070109003) 2L72 4F RTA21EA 20070129002212007012900221EU 2007 1 29 CA070109005 120061108G28101608565 VALVE FOKKERF28 F28MK0100 4990807EU RROYCETAY TAY65015 54557NE FUEL SYSTEM MALFUNCTIONED W D RETURN TO BLOCK K FLUID LOSS TXTAXI/GRND HDL 1 CA (CAN) DATE OF DELAY NOV 8, 2006 CADORS NR: 2006C2915. THE FLIGHT CREW WAS NOTIFIED THAT DURING TAXI FOR DEPARTURE FUEL WAS LEAKING FROM LT WING. AIRCRAFT TAXIED OFF RUNWAY BY WHICH TIME THE LEAK HAD STOPPED. FLIGHT CREW IN CONTACT WITH MAINTENANCE CONTROL AGREED THAT THE LEAK WAS FROM THE WING TANK VENTING SYSTEM. AFTER THE SPILL WAS CLEANED, AC DEPARTED. FOLLOW UP ACTION, THIRD OCCURRENCE OF FUEL LEAK FROM THE VENT SYSTEM ON THIS AIRCRAFT. THE FIRST EVENT WHICH OCCURRED OCT 28 WAS RECTIFIED WITH REPLACEMENT OF THE SUCTION RELIEF VALVE. SNAG RETURNED NOV 3 AT WHICH TIME MAINTENANCE REFUEL AND DE-FUEL THE AIRCRAFT SEVERAL TIMES AND COULD NOT FAULT THE SYSTEM. IN FOLLOW UP TO THIS LATEST SNAG, WE HAVE AN EN2L72 4F4 FRT E25NE 20070129002232007012900223SO 2007 1 29 CA070109007 220061206G8530AEC648009PL PISTON RING CONT O470 O470* 17026SO ENGINE SEPARATED W O OTHER O OTHER NRNOT REPORTED 1 CA 45 (CAN) MATERIAL FROM THE FACE OF THE TOP COMPRESSION RING HAD FLAKED AWAY ON CYLINDER NR 2 (TC NR 20070109007). 3 O E273 20070129002252007012900225NM 2007 1 29 CA070110002 120061217G5610 WINDOW BOEING737 737210C 1384459NM PWA JT8 JT8D9A 52048NE COCKPIT CRACKED W A UNSCHED LANDING O OTHER CLCLIMB 1 CA (CAN) DURING DEPARTURE THE RT NR 3 FLT DECK WINDOW SHATTERED. THE AIRCRAFT RETURNED TO POINT OF DEPARTURE WITHOUT FURTHER PROBLEM. THE AIRCRAFT MOVED TO MAINTENANCE BASE UNDER MEL AUTHORITY WHERE A REPLACEMENT WINDOW WAS INSTALLED. (TC NR 20070110002) 2L72 4F4 F A16WE E2EA 20070129002262007012900226CE 2007 1 29 CA070110003 120061220G322205430358 TORQUE LINK CESSNA172 172D 2072410CE LYC O360 O360A1A 41514EA HARTZLHCC2Y HCC2YK1 GL NLG CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 3691 (CAN) PRIOR TO INSTALLATION ON AIRCRAFT, NOSE GEAR SHOCK STRUT ASSEMBLY WAS THOROUGHLY INSPECTED. SEVERAL CRACKS WERE FOUND ON UPPER TORQUE LINK. NEW MFG PART WAS INSTALLED. (TC NR 20070110003) 1H71 3O3 ONT3A12 E286 5 CP920 20070129002272007012900227 2007 1 29 CA070110005 420061009G2340 WARNING SYSTEM 6225342001 FOKKERF28 F28MK0100 4990807EU RROYCETAY TAY65015 54557NE COCKPIT MALFUNCTIONED W O OTHER P NO WARNING INDICATION LDLANDING 1 CA 3054 (CAN) THE REFERENCED AIRCRAFT AN EVENT INVOLVING THE AUTOMATIC SILENCING OF CABIN CHIMES. NORMALLY THE FLIGHT CREW WILL ADVISE THE FLIGHT ATTENDANTS TO TAKE THEIR POSITIONS FOR LANDING WITH 3 CHIMES SELECTED MANUALLY IN THE COCKPIT. IT APPEARS HOWEVER IN LANDING CONFIGURATION THAT THE CHIMES ARE SILENCED AND STORED UNTIL THE NR 1 ENGINE IS SHUT DOWN. THE CHIMES ARE INHIBITED AT CERTAIN FLIGHT PHASES. AS INDICATED MAINTENANCE WAS ABLE TO DUPLICATE THE FAULT. BY PUTTING THE AIRCRAFT INTO FLIGHT MODE. ONCE THE AIRCRAFT WAS PUT BACK INTO GROUND MODE (ENGINES NOT RUNNING) THE STORED CHIMES SOUNDED. WE HAVE POSED THIS ISSUE TO MFG. WE HAVE REVIEWED THE SB’S SL’ AND SED’S BUT FOUND NO INFORMATION PERTAINING2L72 4F4 FRT E25NE 20070129002282007012900228SO 2007 1 29 CA070111001 120061224G3260 SWITCH LKHEED382 382G 526414USO ALLSN 501D 501D22A 03006GL HAMSTD54H 54H60117 NE RT MLG MALFUNCTIONED W O OTHER N FALSE WARNING CLCLIMB 1 CA (CAN) DURING DEPARTURE THE RT MLG CONTINUED TO INDICATE DOWN AND LOCKED AFTER THE GEAR WAS SELECTED UP. THE AIRCRAFT CONTINUED TO DESTINATION, ENROUTE THE GEAR WAS CONFIRMED UP. THE GEAR WAS VISUALLY CONFIRMED AND THE AIRCRAFT LANDED WITHOUT FURTHER PROBLEM. MAINTENANCE REPLACED THE RT MLG FORWARD MICROSWITCH AFTER A SATISFACTORY GEAR SWING THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20070111001) 2H74 4T4 T A1SO E282 6 CP906 20070129002372007012900237 2007 1 29 CA070111014 420061230G34257004544713 SYMBOL GENERATOR AEROSPATR42 ATR42300 8680920EU PWA 120 PW120 NE HAMSTD14SF 14SF5 NE NR 1 FAILED W A UNSCHED LANDING I FLT. ATTITUDE INST. CRCRUISE 1 CA (CAN) THE CAPTAINS EFIS SCREEN CIRCUIT BREAKER TRIPPED. THE BREAKER WAS RESET AND TRIPPED AGAIN AND THE AIRCRAFT RETURNED TO POINT OF DEPARTURE. MAINTENANCE REPLACED THE NR 1 SYMBOL GENERATOR UNIT (SGU)THE AIRCRAFT WAS RETURNED TO SERVICE AFTER SATISFACTORY FUNCTION CHECK COMPLETED. (TC NR 20070111014) 2H72 4T4 TRTA53EU E20NE 6 CP7NE 20070131001082007013100108NE 2007 1 31 CA070111016 220061219G7230FW34114 FAN BLADE BOMBDRBD700 BD7001A10 1390006GL RROYCEBR700 BR700710A22009500NE LT ENGINE SEPARATED W O OTHER Y ENGINE STOPPAGE CLCLIMB 1 CA 650 (CAN) DURING CLIMB AT APPROXIMATELY 35,000 FEET, THE CREW HEARD A LOUD BANG AND THE LT ENGINE SHUTDOWN. THE CREW DECLARED AN EMERGENCY AND LANDED UNEVENTFULLY. AN INSPECTION OF LT ENGINE REVEALED ONE FAN BLADE HAD FRACTURED JUST ABOVE THE ROOT. THE BLADE ROOT WAS STILL ATTACHED AND THE FRACTURED PORTION WAS RECOVERED. DAMAGE WAS ALSO FOUND ON THE INSIDE OF THE INLET, TO SOME OF THE OTHER FAN BLADES AND TO THE GUIDE VANES. THE FAILURE WAS COMPLETELY CONTAINED AND NO DAMAGE WAS FOUND ON THE EXTERIOR OF THE NACELLE OR AIRCRAFT STRUCTURE. (TC NR 20070111016) 2L72 4F4 FRTT00003NYE00061EN 20070509000652007050900065EU 2007 5 9 CA070112001 120061209G55409408328506 BEARING PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL RUDDER WORN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING INSPECTION OF TAIL TOP ATTACH BOLT FOUND TO HAVE EXCESSIVE WEAR. RUDDER REMOVED FOR REPAIR. DURING REPAIR ANCHOR NUT WAS DAMAGED. NEW OVERSIZED BUSHING INSTALLED, WITH NEW BOLT, BEARING AND ANCHOR NUT. MFG WAS NOTIFIED OF THIS DEFECT. (TC NR 20070112001) 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20070509000742007050900074NE 2007 5 9 CA070115006 120061214G632092351510042 GEARBOX SKRSKYS92 S92A NE MAIN ROTOR MALFUNCTIONED W C ABORTED TAKEOFF J WARNING INDICATION LDLANDING 1 CA 2076 2076 (CAN) MAIN GEARBOX HAD SEVERAL OCCURENCES OF OIL PRESSURE DROPPING TO THE PRECAUTIONARY RANGE IN OPERATION. (TC NR 20070115006) 2G72 4U R00024BO 20070129002672007012900267NE 2007 1 29 CA070115008 220061009G7250ARRIEL2B ENGINE SNIAS 350 AS350B3 8680954EU TMECA ARRIELARRIEL2B NE FAILED W O OTHER O OTHER CRCRUISE 1 CA 709 (CAN) AIRCRAFT FAILED POWER CHECK: ON INSPECTION ON WHY WE DID A BORESCOPE INSPECTION ON THE ENGINE AND FOUND THAT WE HAD A POSSIBLE TURBINE RUB. AS THIS ENGINE IS A RENTAL FROM MFG, WE CHANGED OUT THE MODULE 2 AND 3 AND SENT IT BACK TO THEM. THE NEW M02 AND M03 MODULES FIXED OUR FAILED POWER CHECK. WE DO NOT KNOW FOR SURE WHAT CAUSED OUR PROBLEM. (TC NR 20070115008) 1G71 3U3 U H9EU E00054EN 20070129002722007012900272NE 2007 1 29 CA070115009 220061217G7310AE7010000N0130 FUEL LINE CNDAIRCL604 CL604 1900301EA GE CF34 CF348E5A1 30015NE ENGINE TORN W O OTHER K FLUID LOSS NRNOT REPORTED 1 CA (CAN) FUEL LEAK WAS FOUND FROM HOSE ASSEMBLY P/N AE7010000N0130 ON THE SECOND ENGINE RUN AFTER THAT HOSE WAS REPLACED. NOTE: THIS LINE WAS REPLACED AS REQUESTED BY MFG (DISCLOSURE LETTER), BATCH RECALL DUE TO DEFECTIVE HOSE (BATCH NR 840850). (TC NR 20070115009) 2L72 4F4 FRTA21EA E00063EN 20070129002962007012900296EA 2007 1 29 CA070115010 220061216G72503013102 TURBINE PWC PT6A27 DHAV DHC6 DHC6300 2802606EA PWA PT6 PT6A27 52043EA HARTZLHCB3T HCB3TN3 GL ENGINE DISINTEGRATED W A UNSCHED LANDING YJ ENGINE STOPPAGE WARNING INDICATION CRCRUISE 1 CA 2741 PCE41266 (CAN) DURING CRUISE FLIGHT, THE CREW NOTICED OIL PRESSURE ON THE NR 2 ENGINE FLUCTUATING BETWEEN 60-70 PSI, WITHIN SECONDS THE TQ PRESSURE STARTED TO FLUCTUATE. THE ENGINE MADE 3 BIG BANGS AND SHUTDOWN. THE CREW LANDED THE AIRCRAFT AT THE NEAREST AIRPORT WITHOUT INCIDENT. MAINTENANCE FOUND METAL IN THE OIL FILTER AND IN THE RGB. MOST OF THE PT BLADES EXITED THE EXHAUST. ENGINE SENT TO OVERHAUL SHOP FOR INVESTIGATION. (TC NR 20070115010) 1H72 3T4 TRTA9EA E4EA 6 CP15EA 20070129003012007012900301WP 2007 1 29 CA070115011 220061126G72603586763 PLANETARY GEAR GARRTTTPE331TPE33110UG 01514WP ENGINE DAMAGED W O OTHER O OTHER ININSP/MAINT 1 CA 206 (CAN) UPON DOING A OIL SAMPLE, METAL WAS NOTED IN THE OIL FILTER. THE ENGINE P-63235C WAS REMOVED. ENGINE WAS FORWARDED TO THE ENGINE SHOP FOR INSPECTION OF THE METAL AND FOUND THAT 1 PLANETARY GEAR WITH THE INNER RACE PEELING METAL AND 3 PLANETARY GEARS WITH PITTING ON THE GEAR TEETH. ALL 4 PLANETARY GEARS HAVE 205.9 HRS SINCE O/H. (TC NR 20070115011) 4 T E4WE 20070820000352007082000035SW 2007 8 20 CA070115012 120061214G5312320035501 ANGLE GULSTM690TP 690D 3970405SW GARRTTTPE331TPE3315 01514WP ROTOL R306 R306382F7 GL BULKHEAD CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 16737 (CAN) FLIGHT CREW REPORTED LOWER THAN NORMAL CABIN DIFFERENTIAL PRESSURE. A GROUND PRESSURIZATION CHECK WAS CARRIED OUT AND FOUND LEAK IN AREA OF AFT PRESSURE BULKHEAD LOWER SECTION. FURTHER INSPECTION REVEALED A CRACK IN THE BEND RADIUS OF ANGLE P/N 320035-501. P/N M690003-4 FIGURE 2-56D ITEM II. NEW ANGLE INSTALLED AND SEALED. GROUND PRESSURIZATION CHECK CARRIED OUT OKAY. (TC NR 20070115012) 1H72 3T4 T 2A4 E4WE 6 CP8EU 20070820000362007082000036SW 2007 8 20 CA070115013 120061219G57201101918 FILLET GULSTM690TP 690D 3970405SW GARRTTTPE331TPE3315 01514WP ROTOL R306 R306382F7 GL RT WING CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 16738 (CAN) DURING INSPECTION OF THE AIRCRAFT A CRACK WAS SUSPECTED IN THE RT UPPER FILLET WING TO FUSELAGE. NON DESTRUCTIVE TESTING CONFIRMED (2) CRACKS, 25 MM AND 18 MM LENGTH. LT UPPER FILLET INSPECTED BY NDT AND NO CRACKS FOUND. AN APPROVED REPAIR CARRIED OUT. (TC NR 20070115013) 1H72 3T4 T 2A4 E4WE 6 CP8EU 20070129003062007012900306 2007 1 29 CA070117001 420061216G22154015373823 SERVO BOMBDRBD700 BD7001A10 1390006GL RROYCEBR700 BR700710A22009500NE AUTOPILOT SYS MALFUNCTIONED W A UNSCHED LANDING F FLT CONT AFFECTED CRCRUISE 1 CA (CAN) THE OPERATOR REPORTED AILERON CONTROL DIFFICULTIES AT FL470 WHILE ENROUTE. THE AIRCRAFT DEPARTED IN HEAVY RAIN. THE PILOT-IN-COMMAND (PIC) DISCONNECTED THE AUTOPILOT AFTER AN AP TRIM IS LWD CAS MESSAGE WAS ANNUNCIATED AND NOTED THAT THE AILERON CONTROL WHEELS WOULD NOT ROTATE WHEN ATTEMPTED BY HAND. THE CREW OVERPOWERED THE CONDITION AND THEN ELECTED TO DESCEND TO A LOWER ALTITUDE. THE PIC STATED THAT AT APPROXIMATELY FL440 THE CONTROL WHEEL LOCKED UP AGAIN AND THE CONDITION WAS OVERPOWERED BY THE CREW. THE FORCE APPLIED TO OVERPOWER THE CONTROL WHEEL FOR BOTH OCCURRENCES WAS APPROXIMATELY 20 LBS. THE PIC ALSO STATED THAT THE AILERON CONTROL SYSTEM WAS BACK TO NORMAL FOR THE DURATION OF THE FLIGHT 2L72 4F4 FRTT00003NYE00061EN 20070509001912007050900191 2007 5 9 CA070118007 420061207G34170102AH2AF PROBE BOMBDRBD700 BD7001A10 1390006GL RROYCEBR700 BR700710A22009500NE TAT MALFUNCTIONED W O OTHER F FLT CONT AFFECTED CRCRUISE 1 CA 372 (CAN) DURING CRUISE AT 43,000 FEET, CREW HAD EICAS MESSAGE AIR DATA COMPUTER (ADC) 3 MISCOMPARE ANNUNCIATED FOR 2 MINUTES FOLLOWED MOMENTARILY BY ADC 1 MISCOMPARE AND THEN ADC 2 MISCOMPARE MESSAGES. AFTER THE MESSAGES WENT OUT, COCKPIT INDICATIONS STARTED TO SHOW DECREASING AIR SPEED AND ENGINE PRESSURE RATIO (EPR) WHICH COULD NOT BE MAINTAINED WITH THE THROTTLE LEVERS AT THE MAXIMUM SETTING. A STALL WARNING ANNUNCIATION WAS POSTED ON THE PRIMARY FLIGHT DISPLAYS WITH STICK SHAKER ACTIVATED AND THE CREW BEGAN A DESCENT TO 39,000 FT. AT THAT ALTITUDE, THE ENGINE POWER INDICATIONS RETURNED TO NORMAL ACCOMPANIED WITH HIGHER THAN NORMAL ENGINE VIBRATION (WITHIN ALLOWABLE LIMITS) WHICH REMAINED UNTIL THE A/C DESCE2L72 4F4 FRTT00003NYE00061EN 20070511000102007051100010GL 2007 5 11 CA070119002 220061019G732323076061 GOVERNOR BELL 206 206B 1181511SW ALLSN 250C 250C20B 03013GL POWER TURBINE FAILED W O OTHER O OTHER DEDESCENT 1 CA 17 (CAN) THE GOVERNOR WAS INSTALLED WITH ZERO TSN. GROUND RUNS AND RIGGING WERE CARRIED OUT IAW THE MM WITH NO DIFFICULTIES. THE AIRCRAFT WAS FLOWN AND IT WAS NOTICED BY THE PILOT THAT HE WAS ALWAYS CHASING THE N2 TO KEEP IT WITHIN LIMITS (ERRATIC N2 OPS). THE ERRATIC OPS DID NOT IMPROVE AND SEEMED TO WORSEN. THE AIRCRAFT WAS THEN GROUNDED. THE PT GOVERNOR WAS RETURNED FOR WARRANTY. (TC NR 20070119002) 1G71 3U3 U H2SW E4CE 20070511000122007051100012SW 2007 5 11 CA070119006 120061013G2435 SPRING LUCAS BELL 206 206L3 1182108SW ALLSN 250C 250C30P 03013GL STARTER-GEN BROKEN W E ENGINE SHUTDOWN BH SMOKE/FUMES/ODORS/SPARKS ELECT. POWER LOSS-50 PC TXTAXI/GRND HDL 1 CA 1289 (CAN) THE STARTER GENERATOR WAS THEN INSTALLED. UPON FIRST GROUND RUN OF THE AIRCRAFT, SPARKS WERE NOTICED TO BE COMING FROM THE BRUSH AREA. THE AIRCRAFT WAS SHUTDOWN, THE STARTER GENERATOR WAS REMOVED. UPON REMOVAL WE HEARD SOMETHING LOOSE/RATTLING AROUND. WE REMOVED THE BRUSH COVER AND FOUND THAT ONE OF THE SPRINGS WHICH HOLD DOWN THE BRUSHES WAS BROKEN OFF AND RATTLING AROUND CAUSING ARCING. THIS STARTER-GENERATOR WAS RETURNED TO FOR FULL WARRANTY AND A NEW UNIT WAS SENT TO US. (TC NR 20070119006) 1G71 3U3 U H2SW E1GL 20070511000142007051100014GL 2007 5 11 CA070119008 220061016G732123070606 FCU BELL 206 206B 1181511SW ALLSN 250C 250C20B 03013GL ENGINE FAILED W E ENGINE SHUTDOWN F FLT CONT AFFECTED TXTAXI/GRND HDL 1 CA 460 (CAN) THE AIRCRAFT WAS STARTED AND WARMED UP. THE PILOT THEN BEGAN TO SPOOL THE AIRCRAFT UP FROM GROUND IDLE TO FLIGHT IDLE, HOWEVER NOTHING HAPPENED. THIS WAS TRIED A FEW TIMES BUT STILL NO RESPONSE. OTHER TROUBLESHOOTING WAS PERFORMED WITH NO FINDINGS. THE FUEL CONTROL UNIT (FCU) IN QUESTION WAS REMOVED AND AN OVERHAULED UNIT WAS INSTALLED. THE DEFECT WAS RECTIFIED. (TC NR 20070119008) 1G71 3U3 U H2SW E4CE 20070511000542007051100054NE 2007 5 11 CA070123011 220060112G7261PT6A67D ENGINE BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE NR 1 OIL CONSUMPTION W A UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 CA 1048810488 PCEPSO290 (CAN) CREW NOTED THEIR NR 1 OIL PRESSURE, FLUCTUATING AROUND 75 PSI. THEY RETURNED TO THE GATE AND REPORTED TO MAINTENANCE. INSPECTION OF THE CHIP DETECTOR AND OIL FILTER REVEALED NO FAULTS. THE ENGINE WAS FILLED WITH OIL AND GROUND RUN WITH NO CONSUMPTION OF OIL NOTED. THE OIL BREATHER LINE WAS BAGGED AND THE A/C RAN FOR 30 MINUTES ON THE GROUND UNDER TARGET TORQUE LOADS AND VERY LITTLE CONSUMPTION WAS NOTED. THE A/C WAS SENT ON AN HOUR LONG TEST FLIGHT WHEN IT RETURNED IT WAS APPROX .5 LITER LOWER ON THE OIL LEVEL. SINCE THE OIL LEVEL WAS STILL AT .75 OF A LITER LOW, MAINTENANCE LATER DETERMINED THE ENGINE HAD RETURNED TO ITS NORMAL OIL LEVEL. THE A/C WAS FLOWN ON A COUPLE MORE SHORT HOP ROUTS WITH NO OIL U2L72 4T4 TRTA24CE E26NE 20070511000722007051100072EA 2007 5 11 CA070126003 220060705G7414BL3493704 MAGNETO BNORM BN2 BN2A 1520204EU LYC O540 O540E4C5 41532EA HARTZLHCC2Y HCC2YK2 GL ENGINE LOOSE W O OTHER E VIBRATION/BUFFET TXTAXI/GRND HDL 1 CA 1403 (CAN) ROUGH RUNNING ON RUNUP. FOUND ATTACHMENT FLANGE ON MAGNETO LOOSE. (TC NR 20070126003) 1H72 3O3 O A17EU E295 5 CP920 20070511000732007051100073EU 2007 5 11 CA070126004 120060831G79218406E OIL COOLER BNORM BN2 BN2A 1520204EU LYC O540 O540E4C5 41532EA HARTZLHCC2Y HCC2YK2 GL CRACKED W EA ENGINE SHUTDOWN UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CRCRUISE 1 CA 1400 (CAN) OIL LEAK AROUND CASTING PORT ON THE OIL COOLER ASSEMBLY. (TC NR 20070126004) 1H72 3O3 O A17EU E295 5 CP920 20070511001892007051100189 2007 5 11 CA070129006 420061221G3497 CONNECTOR BEECH 76 76 1153005CE LYC O360 O360A1G6D EA HARTZLHCM2Y HCM2YR GL ADF DISCONNECTED W O OTHER O OTHER CRCRUISE 1 CA (CAN) ADF INTERMITTENT NDB AND HEADING. AFTER SWAPPING RECEIVERS, ANTENNA, REPLACING ANTENNA TRAY AND CONNECTOR, REPLACING PINS IN RECEIVER TRAY, FOUND CO-AX CONNECTOR INNNER CORE TOUCHING SHIELDING AT RECEIVER TRAY. SNAG ONLY APPREARED WHEN WIRING HARNESS WAS PULLED ON. SOLDERED PORTION OF CONNECTOR HAD WEAKENED OVER TIME AND COULD NO LONGER SUPPORT THE CO-AX WHICH LED TO THE SHORTING. (TC NR 20070129006) 1L72 3O3 O A29CE E286 5 CP43GL 20070808001342007080800134CE 2007 8 8 CA070131006 120060929G5730 SKIN CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA SNSNCH72C 72CK EA WING CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) 2 CRACKS WERE DETECTED ON THE WING SKIN JUST UNDER THE LEADING EDGE ON BOTH WINGS. THE WING ATTACHMENT FITTINGS OF THE AIRCRAFT WERE INSPECTED AND NO FURTHER CRACKS WERE DISCOVERED. THE WINGS WERE REMOVED TO CONDUCT A MORE DETAILED EXAMINATION AND THE AMO IS IN CONTACT WITH MFGV FOR REPAIR INSTRUCTIONS. (TC NR 20070131006) 1H71 3O3 ONT3A19 E223 5 NP9045 20070514000012007051400001NM 2007 5 14 CA070201002 120061218G2821218371 FUEL FILTER BOEING767 767300 1385204NM PWA R985 R985AN14B 52008NE DIRTY W JA DUMP FUEL UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA (CAN) ON CLIMB (L ENG FUEL FILT) EICAS MSG. RETURNED TO DEPARTURE. FUEL FILTER INSPECTED AND FOUND DIRTY. (NO DEBRIS) TECH NOTED NOT TO THE EXTENT THAT WOULD CAUSE THE EICAS INDICATION. FILTER REINSTALLED. LT ENG DIFFERENTIAL PRESS SW CONX FND CORRODED. CONX CLEANED NR DIFF PRESS SW REPLACED. CKD SERV ON GRND RUN. REPEAT SNAG ON NEXT T/O. FILTER REPLACED AND CKD SERV ON HIGH PWR GROUND RUN. (TC NR 20070201002) 2L72 4F3 RRTA1NM 5E1 20070514001242007051400124SO 2007 5 14 CA070207004 220060303G8530 VALVE CESSNA150 150H 2071818CE CONT O200 O200A 17020SO MCAULY1A101 1A101DCM GL CYLINDER STUCK W O OTHER R PARTIAL RPM/PWR LOSS NRNOT REPORTED 1 CA 1291 253128 (CAN) STUCK VALVE - ENGINE WAS ROUGH RUNNING. FOUND TO BE A STUCK VALVE. (TC NR 20070207004) 1H71 3O3 O 3A19 E252 5 NP918 20070514001262007051400126SO 2007 5 14 CA070207005 220060120G7322 PUMP CESSNA150 150M 2071830CE CONT O200 O200A 17020SO MCAULY1A102 1A102OCM GL ACCELERATOR FAILED W O OTHER Y ENGINE STOPPAGE NRNOT REPORTED 1 CA 5800 (CAN) ON ADDING FULL POWER THE ENGINE STALLED AND STOPPED RUNNING. - FOUND TO BE THE ACCELERATOR PUMP WAS NOT WORKING PROPERLY. (TC NR 20070207005) 1H71 3O3 O 3A19 E252 5 NP918 20070514001282007051400128SO 2007 5 14 CA070207006 120060120G5343 TRUNNION PIPER PA34 PA34220T 7103420SO CONT O360 TSIO360KB 17025SO MCAULY3AF32C3AF32C509 GL NLG FAILED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) NOSE GEAR TRUNNION DAMAGED AND REPAIRED. (TC NR 20070207006) 1L72 3O3 O A7SO E9CE 5 CP22EA 20070514001702007051400170EA 2007 5 14 CA070209006 220061220G7250 TURBINE BLADES DHAV DHC6 DHC6300 2802606EA PWA PT6 PT6A27 52043EA POWER SECTION FRACTURED W O OTHER X ENGINE FLAMEOUT CLCLIMB 1 CA (CAN) DURING CLIMB THE ENGINE EMITTED A LOUD NOISE AND SHUTDOWN UNCOMMANDED. THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE. SUBSEQUENT INSPECTION REVEALED FRACTURED POWER TURBINE BLADES. MFG WILL MONITOR INVESTIGATION OF THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070209006) 1H72 3T4 TRTA9EA E4EA 20070514001712007051400171NE 2007 5 14 CA070209007 220060918G7250 TURBINE BLADES AEROSPATR42 ATR42320 8680930EU PWA 120 PW120 NE ENGINE FRACTURED W E ENGINE SHUTDOWN RJ PARTIAL RPM/PWR LOSS WARNING INDICATION APAPPROACH 1 CA (CAN) ON APPROACH THE ENGINE FIRE WARNING ACTIVATED, ACCOMPANIED BY AN UNCOMMANDED POWER REDUCTION. THE CREW DISCHARGED FIRE BOTTLES AND SHUT THE ENGINE DOWN IN FLIGHT. SUBSEQUENT INVESTIGATION AT MFG REVEALED LPT BLADE FRACTURE IN CREEP. (TC NR 20070209007) 2H72 4T4 TRTA53EU E20NE 20070515001972007051500197NE 2007 5 15 CA070209018 220061230G7310 PACKING DHAV DHC8 DHC8301 1386003NM PWA PW120 PW123 NE FUEL MANIFOLD LEAKING W E ENGINE SHUTDOWN KRJFLUID LOSS PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 1 CA (CAN) THE ENGINE LOST POWER IN CRUISE AND WAS SHUT DOWN IN FLIGHT. SUBSEQUENT INSPECTION FOUND A LEAK AT THE FUEL MANIFOLD TRANSFER TUBES. ALL TRANSFER TUBE O-RING PACKINGS WERE REPLACED. ON JAN 4TH FUEL LEAKAGE FROM THE SAME TRANSFER TUBES WAS OBSERVED DURING GROUND OPERATIONS. MFG IS INVESTIGATION PACKING INSTALLATION PROCEDURES AND PROCUREMENT SOURCE AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070209018) 2H72 4T4 TRTA13NM E20NE 20070516001722007051600172SW 2007 5 16 CA070216007 120060919G6330206031554003 SPINDLE BELL 206 206B 1181511SW RT GEARBOX FAILED W O OTHER O OTHER CRCRUISE 1 CA 1667 (CAN) THE RT TRANSMISSION PYLON SUPPORT SPINDLE FAILED IN-FLIGHT AND AIRCRAFT SUBSEQUENTLY HAD AN UNCONTROLLED COLLISION IN THE WATER. REFERENCE: TRANSPORT SAFETY BOARD OCCURENCE BULLETIN NR A06P0190 (TC NR 20070216007) 1G71 3U H2SW 20070517001302007051700130EU 2007 5 17 CA070221008 120060904G2913350A35109222 PULLEY SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1D1 NE HYDRAULIC LOOSE W O OTHER O OTHER NRNOT REPORTED 1 CA 343 (CAN) HYDRAULIC PULLEY BEARING CONTACT SURFACE WORN CAUSING PULLEY WOBBLE AND LOSS OF BELT TENSION. (CLICKING) NOISE DURING START UP AND SHUT DOWN, PULLEY AND BEARING REPLACED NEW. (TC NR 20070221008) 1G71 3U3 U H9EU E19EU 20070530000222007053000022GL 2007 5 30 CA070226003 320061212G6110HCA3V203 PROPELLER STOLAMRC3 RC3 3080203NM LYC O480 GO480G1A6 41527EA HARTZLHCA3V HCA3V203 GL CORRODED W K NONE O OTHER ININSP/MAINT 1 CA 304 FC33 (CAN) PROP COME IN FOR 10 YEAR OVERHAUL. PIS, CLEAN, NDT, VISUAL INSPECTION, LUB UNSERVICEABLE DUE TO RUST. LINK ARMS P/N 861-3C WORN UNSERVICEABLE, P/N A971 BEARING CORRODED UNSERVICEABLE P/N VL9333C-5 BLADE BORES CORRODED HAD TO BE REAMED AND RE-SHOT PEENED. THIS PROP NORMALLY WOULD COST APPROXIMATELY NR 4,500 TO OVERHAUL WITH REPLACED PARTS AND REWORKED BLADE BORES. THIS OVERHAUL HAS BECOME NR 14,000. (TC NR 20070226003) 1H71 3O3 ORCA769 E275 5 CP6EA 20070530000232007053000023SO 2007 5 30 CA070226004 120061220G32104025700 TORQUE LINK PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA HARTZLHCE3Y HCE3YR2A GL LT MLG CRACKED W D RETURN TO BLOCK O OTHER TXTAXI/GRND HDL 1 CA 11942 (CAN) PILOT NOTICED A VIBRATION ON LT WHEEL. AIRCRAFT RETURNED TO RAMP. LT MAIN LANDING GEAR UPPER TORQUE LINK WAS FOUND CRACKED/BROKEN AT ATTACH LUG. THE TORQUE LINK WAS REPLACED. (TC NR 20070226004) 1L72 3O3 O A20SO E14EA 5 CP33EA 20070530000262007053000026SW 2007 5 30 CA070226007 120061103G3246D2571 SADDLE BELL 212 212 1181420SW PWA PT6T PT6T3B 52045NE SKID TUBE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) LT SKID SADDLE WAS FOUND CRACKED. (TC NR 20070226007) 1G71 4U4 U H4SW E22EA 20070530000342007053000034GL 2007 5 30 CA070227007 220060915G7323 CONTROL LEVER BELL 206 206B 1181511SW ALLSN 250C 250C20B 03013GL GOVERNOR STIFF W K NONE O OTHER ININSP/MAINT 1 CA 271 (CAN) THE CONTROL LEVER SHAFT ON THE GOVERNOR WAS FOUND HARD TO MOVE. SO STIFF THAT THE LINEAR ACTUATOR HAD TO WORK HARD TO MAKE IT TO MOVE. (TC NR 20070227007) 1G71 3U3 U H2SW E4CE 20070530000362007053000036GL 2007 5 30 CA070227009 220060616G7323 CONTROL LEVER BELL 206 206B 1181511SW ALLSN 250C 250C20B 03013GL GOVERNOR STIFF W K NONE O OTHER ININSP/MAINT 1 CA 734 (CAN) LEVER CONTROL LEVER HARD TO MOVE ON A FUNCTIONAL CHECK. (TC NR 20070227009) 1G71 3U3 U H2SW E4CE 20070530000372007053000037GL 2007 5 30 CA070227011 220061023G732323065123 CONTROL LEVER BELL 206 206B 1181511SW ALLSN 250C 250C20B 03013GL GOVERNOR STIFF W K NONE O OTHER ININSP/MAINT 1 CA 152 (CAN) ON A FUCTIONAL CHECK OF THE GOVERNOR CONTROL THERE APPEARED THAT THE CONTROL LEVER ON THE GOVERNOR WAS HARD TO MOVE. THIS WAS CONFIRMED AND THE GOVERNOR WAS REMOVED FOR REPAIR. (TC NR 20070227011) 1G71 3U3 U H2SW E4CE 20070530000422007053000042SW 2007 5 30 CA070228004 120061016G5302212030132037 SPLICE BELL BELL 212 212 1181420SW PWA PT6T PT6T3 52045EA TAILBOOM CORRODED W K NONE O OTHER ININSP/MAINT 1 CA 10085 ADW03247 (CAN) SPLICE CORRODED,TAIL BOOM REPLACED, A/C RETURNED TO SERVICE. (TC NR 20070228004) 1G71 4U4 U H4SW E22EA 20070530000432007053000043SW 2007 5 30 CA070228005 120060925G7921R34665 BLADE BELL BELL 205 205A1 1181414SW LYC T53 T5313B 41549NE BLOWER MISSING W K NONE O OTHER ININSP/MAINT 1 CA 434 10880704 (CAN) VIBRATION ON OIL COOLER BLOWER, FURTHER INVESTIGATION REVEALED ONE BLADE MISSING. SERVICEABLE OIL COOLER BLOWER INSTALLED, A/C RETURNED TO SERVICE. (TC NR 20070228005) 1G71 4U4 U H1SW E17EA 20070524002092007052400209 2007 5 24 CA070302003 420061212G23703LO4534 SWITCH DHAV DHC6 DHC6300 2802606EA PWA PT6 PT6A27 52043EA HARTZLHCB3T HCB3TN3 GL VOICE RECORDER TRIPPED W K NONE L NO TEST ININSP/MAINT 1 CA (CAN) FOLLOWING REMOVAL OF THE CVR FOR TESTING IT WAS DETERMINED THAT THE INERTIA SWITCH HAD BEEN PREVIOUSLY TRIPPED CAUSING THE REQUIRED DATA NOT TO BE RECORDED. A RESET OF THE SWITCH HAD THE SAME RESULTS WITH PREMATURE ACTIVATION CAUSING THE RECORDING TO STOP. THE SWITCH WAS REPLACED WITH A NEW ASSEMBLY. (TC NR 20070302003) 1H72 3T4 TRTA9EA E4EA 6 CP15EA 20070613001352007061300135EU 2007 6 13 CA070315006 220061018G7322963178 BOWL ROTAX 914 ROTAX914 EU CARBURETOR DISTORTED W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA 330 (CAN) CARB FLOAT BOWL NUT WAS OVERTORQUED DURING A PREV MAINTENANCE EVENT. THIS DISTORTED THE FLOAT BOWL AND CAUSED THE FLOAT PINS TO BEND OUTWARDS. THIS CAUSED THE FLOATS TO CONTACT THE SIDE OF THE BOWL DURING OPERATION. OPERATOR NOTED INTERMITTENT ROUGH RUNNING THAT WAS ELIMINATED AFTER FLOAT BOWL WAS REPLACED. MM CONTAINS A CONVERSION ERROR THAT INCORRECTLY LISTS THE TORQUE FOR THIS NUT IN FOOT POUND INSTEAD OF INCH POUNDS. THE METRIC TORQUE LISTED IS CORRECT. THIS MM IS CURRENTY BEING REVISED. (TC NR 20070315006) 3 O EXPE3I 20070604000352007060400035GL 2007 6 4 CA070322002 120061115G8011656762 GEAR DIAMONDA20 DA20C1 2990001GL CONT O240 IO240B 17063SO SNSNCHW69EK W69EK63 EA STARTER WORN W K NONE O OTHER ININSP/MAINT 1 CA 206 650200 (CAN) THE FACT THAT IT IS POSSIBLE TO ACCIDENTALLY ENGAGE THE STARTER DRIVE WHILE THE ENGINE IS RUNNING AND THAT THE STARTER GEAR ENGAGES INTO THE ACCESSORY CASE OF THE ENGINE WHICH WOULD RESULT IN SIMILAR DAMAGE, IT WAS SUSPECTED AT THE TIME THAT THE DAMAGE FOUND WAS A RESULT OF SUCH ENGAGEMENT. THEREFORE AT THE TIME A SDR DID NOT SEEM REQUIRED. METAL WAS FOUND IN THE OIL FILTER ON INSPECTION, STARTER WAS REMOVED AND BOTH STARTER GEAR AND CLUSTER GEAR WERE FOUND DAMAGED BEYOND MFG LIMITS DESCRIBED IN SB04-7. FURTHER INSPECTION AT A LATER DATE INDICATED THAT THESE WERE MOST LIKELY NOT DUE TO ACCIDENTAL ENGAGEMENT AS THE DAMAGED AREA ON THE CLUSTER GEAR WAS CONCENTRATED 180 DEGREES APART WHICH WOULD BE CONSIS1L71 3O3 ONTTA4CH E7SO 5 NTA4CH 20070604000362007060400036GL 2007 6 4 CA070322003 120061129G55402055450001 BUSHING DIAMON DIAMONDA20 DA20C1 2990001GL CONT O240 IO240B 17063SO SNSNCHW69EK W69EK63 EA RUDDER MISSING W K NONE O OTHER ININSP/MAINT 1 CA 102 (CAN) DURING INSPECTION IT WAS NOTED THAT THE TOP RUDDER ATTACHMENT PIN BUSHING WAS MISSING. FURTHER INSPECTION REVEALED THE BUSHING HAD FALLEN OUT AND WAS SITTING IN A VOID AREA BELOW THE ASSEMBLY. THE BUSHING WAS RE-INSTALLED IAW MFG INSTRUCTION. THE RUDDER HAD NEVER BEEN REMOVED SINCE MANUFACTURE. (TC NR 20070322003) 1L71 3O3 ONTTA4CH E7SO 5 NTA4CH 20070604000512007060400051CE 2007 6 4 CA070327004 120060812G2434DOFF300JR ALTERNATOR CESSNA206 U206G 2073356CE CONT O520 IO520F 17032SO MCAULYD3A34 D3A34C404 GL ENGINE FAILED W B EMER. DESCENT HB ELECT. POWER LOSS-50 PC SMOKE/FUMES/ODORS/SPARKS CRCRUISE 1 CA 300 (CAN) BURNING ELECTRICAL SMELL IN COCKPIT, LOSS OF CHARGING SYSTEM. (TC NR20070327004) 1H71 3O3 O A4CE E5CE 5 CP47GL 20070604000532007060400053NE 2007 6 4 CA070327007 220060610G8500R985 ENGINE DHAV DHC2 DHC2MKI 2801830GL PWA R985 R985AN14B 52008NE HAMSTD2D 2D30 NE MALFUNCTIONED W C ABORTED TAKEOFF R PARTIAL RPM/PWR LOSS TOTAKEOFF 1 CA (CAN) ENGINE NOT PRODUCING FULL TAKEOFF MANIFOLD PRESSURE. (TC NR 20070327007) 1H71 3R3 RRCA806 5E1 5 CP206 20070503000252007050300025CE 2007 5 3 CA070402005 120060102G32469543991 WHEEL LEAR 35 35A 5170602CE GARRTTTFE731TFE73122B 01518WP NR 3 WRONG PART W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA 147 (CAN) DURING ROUTINE PRE-FLIGHT INSPECTION, NR 3 MAIN WHEEL ASSY FOUND TO BE ASSEMBLED INCORRECTLY. WHEEL HALF`S WERE MISALIGNED BY ONE BOLT HOLE. AMM 32-A2-00 PG.210. FORGED NRS AND LOT NRS WERE NOT ALIGNED. MAIN WHEEL ASSEMBLY REMOVED FROM AIRCRAFT, REPAIRED AND RE-ASSEMBLED IAW AMM 32-42-00 AND CMM AP-480 32-40-35. (TC NR 20070402005) 2L72 4F4 F A10CE E6WE 20070503000282007050300028GL 2007 5 3 CA070402007 120060710G3246C2UF2291 MECHANISM EDOFLOATS DHAV DHC2 DHC2MKI 2801830GL PWA R985 R985AN14B 52008NE HARTZLHCB3R HCB3R304 GL FLOAT WIRE PULL WRONG PART W K NONE O OTHER ININSP/MAINT 1 CA 489 (CAN) FORWARD RT WIRE PULL BROKE, NEW WIRE PULL P/N C2UF2291 FOUND TO BE TOO SHORT. INVESTIGATION REVEALED WRONG TIE RODS AND WIRE PULLS INSTALLED IAW APPROVED DRAWINGS ACCEPTED REPLACEMENT PARTS INSTALLED IAW APPROVED DRAWINGS. (TC NR 20070402007) 1H71 3R3 RRCA806 5E1 5 CP28EA 20070504001052007050400105NM 2007 5 4 CA070404005 120060426G5697 TERMINAL BLOCK BOEING BOEING757 75728A 1384976NM RROYCERB211 RB211535E4 54555NE WINDOW OVERHEATED W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 1 CA 0525141740 (CAN) UNKNOWN ODOR IN CONTROL CABIN THOUGHT TO BE FROM LAVATORY. ISOLATED TO FLIGHT DECK. ON DESCENT INTO AIRPORT, ODOR DISSIPATED AND FAULT COULD NOT BE FOUND. AIRCRAFT CONTINUED WITH NO FUMES BUT SLIGHT ODOR WAS PRESENT AT END OF FLIGHT. TERMINAL BLOCK ON SLIDING WINDOW WAS FOUND OVERHEATED. WINDOW WAS REPLACED. (TC NR 20070404005) 2L72 4F4 FRTA2NM E12EU 20070808001602007080800160CE 2007 8 8 CA070502013 120060603G2720051010551 CONTROL CABLE CESSNA185 185A 2072804CE CONT O520 IO520D 17032SO MCAULY2A34C D2A34C58 GL RUDDER CONTROL BROKEN W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) THE BOLT THAT ATTACHES THE LT FORWARD RUDDER CABLE TO THE RUDDER PEDAL SETUP WAS ORIGINALLY TOO TIGHTLY DONE UP. THE CABLE ATTACHMENT FORK WAS NOT ABLE TO MOVE FREELY ON END, IN THE FORK, AND BREAK UNDER LOAD. (TC NR 20070502013) 1H71 3O3 O 3A24 E5CE 5 CP3EA 20070809000372007080900037CE 2007 8 9 CA070517003 120061214G27010411257 CONTROL WHEEL CESSNA172 172P 2072436CE LYC O320 O320D2J 41508EA COCKPIT FAILED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) EXCESSIVE PLAY IN (U) JOINT ON LT CONTROL WHEEL. (TC NR 20070517003) 1H71 3O3 ONT3A12 E274 20080319001382008031900138CE 2008 3 19 CA070517004 120060918G3710211CW PUMP CESSNA172 172P 2072436CE LYC O320 O320D2J 41508EA VACUUM SYS FAILED W E ENGINE SHUTDOWN O OTHER TXTAXI/GRND HDL 1 CA 629 (CAN) LOSS OF VACUUM DURING START-UP. (TC NR 20070517004) 1H71 3O3 ONT3A12 E274 20070618001602007061800160EA 2007 6 18 CA070517005 220061203G7414 COIL CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA MAGNETO BURNED W K NONE O OTHER ININSP/MAINT 1 CA 1785 (CAN) RT MAGNETO DEAD ON RUN-UP. (TC NR 20070517005) 1H71 3O3 ONT3A12 E274 20070618001612007061800161EA 2007 6 18 CA070517006 220061125G8500 ENGINE CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA SMOKE W FE ACTIVATE FIRE EXT. ENGINE SHUTDOWN B SMOKE/FUMES/ODORS/SPARKS NRNOT REPORTED 1 CA 17262921 (CAN) SMOKE SEEN COMING FROM COWLS INDUCTION FIRE SUSPECTED, SHUTDOWN AND PILOT DISCHARGED FIRE EXTINGUISHER INTO COWLING. (TC NR 20070517006) 1H71 3O3 ONT3A12 E274 20070820001112007082000111SO 2007 8 20 CA070716004 220060511G8530AEC631397 CYLINDER CESSNA185 A185E 2072818CE CONT O520 IO520D 17032SO HARTZLHCC3Y HCC3YF1 GL NR 4 CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) NR 4 CYLINDER FOUND CRACKED DURING INSPECTION (TC IN20070716004) 1H71 3O3 O 3A24 E5CE 5 CP25EA 20070820001382007082000138EA 2007 8 20 CA070720009 120060727G56106003303025 WINDSHIELD CNDAIRCL601 CL6012A12 1900303EA GE CF34 CF348E5A1 30015NE COCKPIT CRACKED W O OTHER O OTHER CRCRUISE 1 CA 1233 (CAN) LT WINDSHIELD OUTER PANE CRACKED IN FLIGHT WITH NO LOSS OF PRESSURIZATION. FLIGHT CONTINUED NORMALLY. NEW WINDSHIELD INSTALLED AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20070720009) 2L72 4F4 FRTA21AE E00063EN 20081104 CE 2008 11 4 CA070726005 120061230G8011EBB75A GEAR MZ4206 CESSNA172 172K 2072430CE LYC O320 O320E2D 41508EA MCAULY1C160 1C160DTM GL STARTER FAILED W O OTHER O OTHER NRNOT REPORTED 1 CA 241 (CAN) ENGINE WOULD NOT START, STARTER REMOVED, BENDIX FOUND SHATTERED. (TC NR 20070726005) 1H71 3O3 ONT3A12 E274 5 NP910 20070820001622007082000162GL 2007 8 20 CA070731003 120060929G5540C2CF17778 TORQUE TUBE DHAV DHC2 DHC2MKI 2801830GL PWA R985 R985AN14B 52008NE HAMSTD2D 2D30 NE RUDDER CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) CRACK ON RUDDER TORQUE TUBE RT SIDE OB. (TC NR 20070731003) 1H71 3R3 RRCA806 5E1 5 CP206 20070820001632007082000163CE 2007 8 20 CA070731004 120061023G272007123094 BELLCRANK CESSNA185 A185E 2072818CE CONT O520 IO520D 17032SO MCAULY2A34C D2A34C58 GL RUDDER CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) BELLCRANK HAS CRACKS ADJACENT TO AN3 BOLT HOLES. (TC NR 20070731004) 1H71 3O3 O 3A24 E5CE 5 CP3EA 20080131000502008013100050 2008 1 31 CA071018002 420061113G2562AK450 ELT ROBSINR22 R22BETA 7640110NM LYC O360 O360J2A 41514EA CABIN FAILED W K NONE L NO TEST ININSP/MAINT 1 CA (CAN) SENT 2 ELTS TO INLAND COMMUNICATIONS FOR SERVICING, BOTH ELTS HAD FAULTY G-SWITCHES AND COULD NOT BE REPAIRED. SENT CORE IN FOR NEW AK-450 S/N 485068 THAT WAS INSTALLED ON NOV 13/06, WENT OFF ON LANDING AND AGAIN IN FLIGHT. REMOVED ELT ON HOV 14/06. INSTALLED NEW AK-450-1 ELT S/N 485603 JAN 11/07, FAILED ON MAR 4/07 AND REMOVED. INSTALLED ANOTHER NEW AK-450-1 ELT S/N 484979 ON MAY 30/07 AND IS STILL SERVICE. (TC NR 20071018002) 1G71 3O3 O H10WE E286 20080225000842008022500084NE 2008 2 25 CA071207001 320061005G61116903A10 BLADE HAMSTD CNDAIRCL215 CL2151A10 1900320EA PWA R1340 CWASP 52016NE HAMSTD43E 43E60 NE PROPELLER UNSERVICEABLE W K NONE O OTHER ININSP/MAINT 1 CA 405 N196694 (CAN) DURING INSPECTION IAW AD 81-13-06R2 AND S/B 664, A CRACK WAS FOUND EMINATING FROM THE BLADE BUSHING SCREW HOLE. CRACK WAS FOUND TO BE TOO LARGE TO BE REMOVED. BLADE WAS RENDERED UNSERVICEABLE. BLADE S/N 852006. (TC NR 20071207001) 2H72 4R3 RRTA14EA ATC14 6 CP871 20080225000882008022500088SW 2008 2 25 CA071210002 120061227G6330204031927005 MOUNT BELL 205 205A1 1181414SW LYC T53 T5317BLYC 41616NE TRANSMISSION SHEARED W O OTHER O OTHER NRNOT REPORTED 1 CA 775 A124043 (CAN) DURING ROUTINE POST FLIGHT DAILY INSP, (3) OF THE (4) AN4H6A BOLTS THAT ATTACH THE TRANSMISSION AFT (5TH) MOUNT TO THE AIRFRAME FITTING ASSY WERE FOUND SHEARED OFF. FLIGHT OPERATION WERE NOT AFFECTED AND CONSIDERED TO BE NORMAL AT THE TIME. THE MOUNT AND FITTING WERE REMOVED, INSPECTED AND THE AIRCRAFT RETURNED TO SERVICE. (TC NR 20071210002) 1G71 4U4 U H1SW E17EA 20080225001002008022500100NE 2008 2 25 CA071212001 220061227G7200 ENGINE AMD FALC50FALCON50MYST2730106EU GARRTTTFE731TFE73140 29001NE NR 2 MAKING METAL W E ENGINE SHUTDOWN KMJFLUID LOSS OVER TEMP WARNING INDICATION NRNOT REPORTED 1 CA P115243 (CAN) ON DESERT TO BASE CREW NOTICED NR 2 ENGINE OIL PRESSURE AND TEMPERATURE CLIMBING, POWER REDUCED TO IDLE. OIL PRESSURE DROPPED TO BELOW MINIMUMS (IN YELLOW ARC). CREW PERFORMED PRECAUTIONARY SHUTDOWN AND LANDED NORMALLY. SUBSEQUENT INVESTIGATION REVEALED OIL HAD VENTED OUT THROUGH BREATHER. CHIP DETECTOR AND GEARBOXES CONTAMINATED WITH METAL PARTICLES. ENGINE RETURNED FOR REPAIR AND INVESTIGATION OF CAUSE. (TC NR 20071212001) 2L73 4F4 F A46EU E1NM 20080225001162008022500116EU 2008 2 25 CA071212015 120061123G28222260961 PUMP BAG JETSTMJETSTM3212 1500217EU GARRTTTPE331TPE33112UHR WP ROTOL R333 R333482F12 GL FUEL BOOST FAILED W O OTHER J WARNING INDICATION CRCRUISE 1 CA (CAN) RT FUEL BOOST PUMP FAILED. (TC NR 20071212015) 2L72 4T4 TRTBA15CAA E4WE 6 CP61GL 20080220000452008022000045NM 2008 2 20 CA080123009 120061218G291082590010239 LINE DHAV DHC8 DHC8103 1386005NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE HYDRAULIC SYS LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA 43213 (CAN) LEAK FROM PIN HOLE IN HYD LINE RT WING, ON GROUND PRIOR TO TAXI TO GATE A/C GROUNDED. HYD LINE ASSY FOR RT WING SPOILERS REPLACED WITH NO FURTHER INCIDENT OR LEAKAGE. (TC NR 20080123009) 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20081107 SO 2008 11 7 CA080717004 120060517G2435 FRICTION DISC PIPER PA31 PA31 7103102SO LYC O540 TIO540A2C 41532EA STARTER GEN WORN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) GENERATOR FRICTION DISC WAS WORN OUT AND WAS ALLOWING THE STARTER GENERATOR SHAFT TO WHIP ABOUT 6000 RPM (OPERATING RANGE) 1L72 3O3 O A20SO E14EA 20081107 EA 2008 11 7 CA080915001 120060802G2820G201G202 FITTING FOUND FBA FBA2C1 3640103EA LYC O540 IO540AE1A5 41530NE FUEL SYSTEM UNDERTORQUED W K NONE O OTHER ININSP/MAINT 1 CA 532 (CAN) FOUND NUMEROUS FUEL FITTINGS WHICH CONNECT THE FUEL LINES TO THE HEADER TANKS TO BE SEEPING FUEL. APPROXIMATE TIME OF SERVICE 532 HRS. PIPE THREAD FITTINGS HAD NO THREAD LUBE/SEALANT. THE VENDOR NOTED THAT THE FUEL FITTINGS WERE NOT PROPERLY TORQUED. THIS MAY REPRESENT A QUALITY CONTROL ISSUE AT THE FOUND ACFT PRODUCTION FACILITY. AT PRESENT THE USDOI, AVIATION MANAGEMENT DIRECTORATE, IS INVESTIGATING THIS EVENT WITHIN ITS FLEET." 1H71 3O3 ONCA7EA 1E4 20060705000122006070500012NE 2006 7 5 CHI2852 220060419G72502002T29P01 LOCK NUT GE BOEING107 1072 9420604EA GE CT58 CT581401 30011NE PWR TURBINE FAILED B CHIRK NONE O OTHER ININSP/MAINT 1 NM096672D 52 2 280102L UPON RECEIPT OF ENGINE FOR MAINTENANCE, IT WAS DISCOVERED THAT THE POWER TURBINE LOCKNUT HAD LOST TORQUE AND BACKED OFF OF THE POWER TURBINE TIE BOLT. THE PROBABLE CAUSE WAS LOSS OF TORQUE. A SPECIAL INSPECTION WAS INITIATED TO INCLUDE INSPECTING RUN-ON TORQUE. A SPECIAL INSPECTION WAS INITIATED TO INCLUDE INSPECTING RUN-ON TORQUE AND PERFORMING AN NDT INSP OF ALL LOCKNUTS IN INVENTORY AND THOSE UNDERGOING MAINT. ALL LOCKNUTS CURRENTLY INSTALLED ON AC WILL BE REPLACED AND THOSE LOCKNUTS WILL BE RETURNED TO REPAIR STA FOR INSP. MFG WILL BE NOTIFIED OF INCIDENT IMMEDIATELAY. (K) 2G72 4U4 U 1H16 1E3 20060705000092006070500009EA 2006 7 5 CHI44188 120060518G6300107D25535 COVER BOEING107 1072 9420604EA MIXER BOX CRACKED B CHIRK NONE O OTHER ININSP/MAINT 1 NM09194CH858 404 CRACK DISCOVERED IN THE MIX BOX COVER, PN 107D25535. THE CRACK RUNS FROM JUST UNDER THE WEB ON THE TOP OF THE MIX BOX LT SIDE, INTO THE O-RING GROOVE IN THE FRONT OF THE COVER. CRACK IS APPROX 6 INCHES OVERALL IN LENGTH. DAMAGED AREA OF THE COVER HAS BEEN SENT TO LABORATORY FOR ANALYSIS. (K) 2G72 4U 1H16 20060706001032006070600103EA 2006 7 6 CHIR823CA 120060608G6410114R170244 BLADE BOEING234 234 1385049EA TAIL ROTOR DEBONDED C CHIRK NONE O OTHER ININSP/MAINT 1 NM09CFHFB21142 MJ005 ROTOR BLADE HAD A LARGE SKIN DEBOND ON THE LOWER SURFACE FROM THE TRIM TAB OB, BETWEEN STA 227 AND STA 329 APPROXIMATELY 475-500 SQ INCHES (ALLOWABLE REPAIR LIMITS ARE 20 INCHES SPAN WISE AND 13 INCHES CHORD WISE. UNBONDED SKIN WAS REMOVED TO EXPOSE HONEYCOMB CORE FOR INSPECTION. HONEYCOMB WAS OIL FREE AND APPEARED TO BE IN GOOD CONDITION. THE ROTOR BLADE WILL UNDERGO FURTHER INVESTIGATION TO DETERMINE THE PROBABLE CAUSE AND REPAIR SCHEME, IF POSSIBLE. MFG HAS BEEN NOTIFIED. (K) 2G72 4U H9EA 20060321000582006032100058 2006 3 21 CMRR200602002 420060227G31607018704902 POWER SUPPLY HONEYWELL DU870 DORNERDO32 DO328300 NM PWA 306 PW306B NE EFIS OVERTEMP B CMRRK NONE MH OVER TEMP ELECT. POWER LOSS-50 PC ININSP/MAINT 1 SO13406FJ9042 00046519 3156 THE HONEYWELL DU-870 DISPLAY UNIT REFERENCED HEREIN FAILED JUST PRIOR TO TAKEOFF. THE SUSPECTED SPECIFIC COMPONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY P/N:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT. FURTHER INSPECTION WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF DU FAILURE. 2H72 4T4 FRTA55NM E35NE 20060316000402006031600040 2006 3 16 CMRR200602003 420060222G31607018704902 POWER SUPPLY HONEYWELL DU870 DORNERDO32 DO328300 NM PWA 306 PW306B NE COCKPIT OVERTEMP B CMRRK NONE HM ELECT. POWER LOSS-50 PC OVER TEMP ININSP/MAINT 1 SO13406FJ9042 99095560 3156 +THE NR 1 PFD DU-870 DISPLAY UNIT REFERENCED HERE IN FAILED DURING GROUND OPERATIONS. THE SUSPECTED SPECIFIC COMPONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY PN 7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT. FURTHER INSPECTION WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF DU FAILURE. 2H72 4T4 FRTA55NM E35NE 20060322000492006032200049 2006 3 22 CMRR200603004 420060314G31607018704902 POWER SUPPLY HONEYWELL DU870 DORNERDO32 DO328300 NM PWA 306 PW306B NE EFIS OVERTEMP B CMRRK NONE MH OVER TEMP ELECT. POWER LOSS-50 PC ININSP/MAINT 1 SO13423FJ7360 00107696 3181 THE NR 1 PFD HONEYWELL DU-870 DISPLAY UNIT REFERENCED HEREIN FAILED DURING GROUND OPERATIONS. THE SUSPECTED SPECIFIC COMPONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY P/N:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT. FURTHER INSPECTION WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF DU FAILURE. 2H72 4T4 FRTA55NM E35NE 20060321000672006032100067 2006 3 21 CMRR200603005 420060314G31607018704902 POWER SUPPLY HONEYWELL DU870 DORNERDO32 DO328300 NM PWA 306 PW306B NE EFIS OVERTEMP B CMRRK NONE MH OVER TEMP ELECT. POWER LOSS-50 PC ININSP/MAINT 1 SO13423FJ7360 00107818 3181 THE NR 2 MFD HONEYWELL DU-870 DISPLAY UNIT REFERENCED HEREIN FAILED DURING GROUND OPERATIONS PRIOR TO FERRY. THE SUSPECTED SPECIFIC COMPONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY P/N:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT. FURTHER INSPECTION WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF DU FAILURE. 2H72 4T4 FRTA55NM E35NE 20060321000492006032100049 2006 3 21 CMRR200603006 420060314G31607018704902 POWER SUPPLY HONEYWELL DU870 DORNERDO32 DO328300 NM PWA 306 PW306B NE EFIS OVERTEMP B CMRRK NONE MH OVER TEMP ELECT. POWER LOSS-50 PC ININSP/MAINT 1 SO13423FJ7360 00107817 3181 THE NR 1 MFD HONEYWELL DU-870 DISPLAY UNIT REFERENCED HEREIN FAILED DURING GROUND OPERATIONS PRIOR TO FERRY. THE SUSPECTED SPECIFIC COMPONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY P/N:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT. FURTHER INSPECTION WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF DU FAILURE. 2H72 4T4 FRTA55NM E35NE 20060321001202006032100120 2006 3 21 CMRR200603007 420060314G31607018704902 POWER SUPPLY HONEYWELL DU870 DORNERDO32 DO328300 NM PWA 306 PW306B NE EFIS OVERTEMP B CMRRK NONE MH OVER TEMP ELECT. POWER LOSS-50 PC ININSP/MAINT 1 SO13423FJ7360 00107359 3181 THE NR 2 PFD HONEYWELL DU-870 DISPLAY UNIT REFERENCED HEREIN FAILED DURING GROUND OPERATIONS PRIOR TO FERRY. THE SUSPECTED SPECIFIC COMPONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY P/N:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT. FURTHER INSPECTION WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF DU FAILURE. 2H72 4T4 FRTA55NM E35NE 20060321001812006032100181 2006 3 21 CMRR200603008 420060314G31607018704902 POWER SUPPLY HONEYWELL DU870 DORNERDO32 DO328300 NM PWA 306 PW306B NE EFIS OVERTEMP B CMRRK NONE MH OVER TEMP ELECT. POWER LOSS-50 PC ININSP/MAINT 1 SO13423FJ7360 00036246 3181 THE EICAS HONEYWELL DU-870 DISPLAY UNIT REFERENCED HEREIN FAILED DURING GROUND OPERATIONS PRIOR TO FERRY. THE SUSPECTED SPECIFIC COMPONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY P/N:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT. FURTHER INSPECTION WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF DU FAILURE. 2H72 4T4 FRTA55NM E35NE 20060427001332006042700133 2006 4 27 CMRR200603009 420060324G31607018704902 POWER SUPPLY HONEYWELL DU870 DORNERDO32 DO328300 NM PWA 306 PW306B NE DISPLAY UNIT FAILED B CMRRK NONE O OTHER TXTAXI/GRND HDL 1 SO13423FJ7360 0201A741 3181 THE EICAS HONEYWELL DU-870 DISPLAY UNIT REFERENCED HEREIN FAILED DURING TAXI PRIOR TO FERRY. THE SUSPECTED SPECIFIC COMPONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY UNIT PN:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT. THIS PARTICULAR DU POSITION WAS PREVIOUSLY REPLACED AS WELL ON 3-14-06 BUT THE CUSTOMER DID NOT WANT AN UPGRADED MOD K UNIT INSTALLED. FURTHER INSPECTIONS WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF DU FAILURE. 2H72 4T4 FRTA55NM E35NE 20060510002242006051000224 2006 5 10 CMRR200604010 420060426G31607018704902 POWER SUPPLY HONEYWELL DU870 DORNERDO32 DO328300 NM PWA 306 PW306B NE DISPLAY UNIT FAILED B CMRRK NONE O OTHER TXTAXI/GRND HDL 1 SO13407FJ8913 00046519 3157 THE NR 1 PFD DISPLAY UNIT REFERENCED HERE IN FAILED DURING TAXI OPERATIONS PRIOR TO FLIGHT. THE SUSPECTED SPECIFIC COMPONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY UNIT PN:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT. FURTHER INSPECTIONS WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF DU FAILURE. 2H72 4T4 FRTA55NM E35NE 20060510002252006051000225 2006 5 10 CMRR200604011 420060426G31607018704902 POWER SUPPLY HONEYWELL DU870 DORNERDO32 DO328300 NM PWA 306 PW306B NE DISPLAY UNIT FAILED B CMRRK NONE O OTHER TXTAXI/GRND HDL 1 SO13407FJ8913 00036262 3157 THE NR 1 MFD DISPLAY UNIT REFERENCED HERE IN FAILED DURING TAXI OPERATIONS PRIOR TO FLIGHT. THE SUSPECTED SPECIFIC COMPONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY UNIT PN:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT. FURTHER INSPECTIONS WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF DU FAILURE. 2H72 4T4 FRTA55NM E35NE 20060619001772006061900177 2006 6 19 CMRR200606012 420060526G31607018704902 POWER SUPPLY HONEYWELL DU870 DORNERDO32 DO328300 NM PWA 306 PW306B NE EFIS FAILED B CMRRK NONE MH OVER TEMP ELECT. POWER LOSS-50 PC ININSP/MAINT 1 SO13403FJ9553 00036143 3149 THE NR 1 MFD DISPLAY UNIT REFERENCED HEREIN FAILED DURING GROUND OPERATIONS PRIOR TO FLIGHT. THE SUSPECTED SPECIFIC COMPONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY UNIT PN: 7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT. FURTHER INSPECTION WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF DU FAILURE. 2H72 4T4 FRTA55NM E35NE 20060620000192006062000019 2006 6 20 CMRR200606013 420060526G31607018704902 POWER SUPPLY HONEYWELL DU870 DORNERDO32 DO328300 NM PWA 306 PW306B NE DISPLAY FAILED B CMRRK NONE O OTHER ININSP/MAINT 1 SO13403FJ9553 00087125 3149 THE NR 1 PFD HONEYWELL DISPLAY UNIT REFERENCED HEREIN FAILED DURING GROUND OPERATIONS PRIOR TO FLIGHT. THE SUSPECTED SPECIFIC COMPONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY UNIT PN:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT. FURTHER INSPECTION WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF DU FAILURE. 2H72 4T4 FRTA55NM E35NE 20061031001282006103100128 2006 10 31 CMRR200610014 420061027G31607018704902 POWER SUPPLY HONEYWELL DU870 DORNERDO32 DO328300 NM PWA 306 PW306B NE EFIS FAILED B CMRRK NONE H ELECT. POWER LOSS-50 PC ININSP/MAINT 1 SO13428FJ6881 01028536 3193 THE NR 1 PFD DISPLAY UNIT REFERENCED HEREIN FAILED DURING GROUND OPERATIONS. THE SUSPECTED SPECIFIC COMPONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY UNIT P/N:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT. FURTHER INSPECTION WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF THE DU FAILURE. 2H72 4T4 FRTA55NM E35NE 20061031001292006103100129 2006 10 31 CMRR200610015 420061027G31607018704902 POWER SUPPLY HONEYWELL DU870 DORNERDO32 DO328300 NM PWA 306 PW306B NE EFIS FAILED B CMRRK NONE H ELECT. POWER LOSS-50 PC ININSP/MAINT 1 SO13428FJ6881 01059291 3193 THE NR 2 MFD DISPLAY UNIT REFERENCED HEREIN FAILED DURING GROUND OPERATIONS. THE SUSPECTED SPECIFIC COMPONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY UNIT P/N:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT. FURTHER INSPECTION WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF THE DU FAILURE. 2H72 4T4 FRTA55NM E35NE 20061031001302006103100130 2006 10 31 CMRR200610016 420061027G31607018704902 POWER SUPPLY HONEYWELL DU870 DORNERDO32 DO328300 NM PWA 306 PW306B NE EFIS FAILED B CMRRK NONE H ELECT. POWER LOSS-50 PC ININSP/MAINT 1 SO13428FJ6881 01018337 3193 THE EICAS DISPLAY UNIT REFERENCED HEREIN FAILED DURING GROUND OPERATIONS. THE SUSPECTED SPECIFIC COMPONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY UNIT P/N:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT. FURTHER INSPECTION WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF THE DU FAILURE. 2H72 4T4 FRTA55NM E35NE 20061031001312006103100131 2006 10 31 CMRR200610017 420061027G31607018704902 POWER SUPPLY HONEYWELL DU870 DORNERDO32 DO328300 NM PWA 306 PW306B NE EFIS FAILED B CMRRK NONE H ELECT. POWER LOSS-50 PC ININSP/MAINT 1 SO13428FJ6881 00097242 3193 THE NR 4 MFD DISPLAY UNIT REFERENCED HEREIN FAILED DURING GROUND OPERATIONS. THE SUSPECTED SPECIFIC COMPONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY UNIT P/N:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT. FURTHER INSPECTION WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF THE DU FAILURE. 2H72 4T4 FRTA55NM E35NE 20061031001322006103100132 2006 10 31 CMRR200610018 420061027G31607018704902 POWER SUPPLY HONEYWELL DU870 DORNERDO32 DO328300 NM PWA 306 PW306B NE EFIS FAILED B CMRRK NONE H ELECT. POWER LOSS-50 PC ININSP/MAINT 1 SO13428FJ6881 00097260 3193 THE NR 5 PFD DISPLAY UNIT REFRENCED HEREIN FAILED DURING GROUND OPERATIONS. THE SUSPECTED SPECIFIC COMPONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY UNIT P/N:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT. FURTHER INSPECTION WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF THE DU FAILURE. 2H72 4T4 FRTA55NM E35NE 20061031001332006103100133 2006 10 31 CMRR200610019 420061019G31607018704902 POWER SUPPLY HONEYWELL DU870 DORNERDO32 DO328300 NM PWA 306 PW306B NE EFIS FAILED B CMRRK NONE H ELECT. POWER LOSS-50 PC ININSP/MAINT 1 SO13405FJ9298 00036374 3155 THE EICAS DISPLAY UNIT REFERENCED HEREIN FAILED DURING GROUND OPERATIONS. THE SUSPECTED SPECIFIC COMPONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY UNIT P/N:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT. FURTHER INSPECTION WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF THE DU FAILURE. 2H72 4T4 FRTA55NM E35NE 20061031001342006103100134 2006 10 31 CMRR200610020 420061023G31607018704902 POWER SUPPLY HONEYWELL DU870 DORNERDO32 DO328300 NM PWA 306 PW306B NE EFIS FAILED B CMRRK NONE H ELECT. POWER LOSS-50 PC ININSP/MAINT 1 SO13420FJ8290 00046474 3178 THE NR 5 PFD DISPLAY UNIT REFERENCED HEREIN FAILED DURING GROUND OPERATIONS. THE SUSPECTED SPECIFIC COMPONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY UNIT P/N:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT. FURTHER INSPECTION WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF THE DU FAILURE. 2H72 4T4 FRTA55NM E35NE 20061031001352006103100135 2006 10 31 CMRR200610021 420061023G31607018704902 POWER SUPPLY HONEYWELL DU870 DORNERDO32 DO328300 NM PWA 306 PW306B NE EFIS FAILED B CMRRK NONE H ELECT. POWER LOSS-50 PC ININSP/MAINT 1 SO13420FJ8290 00107614 3178 THE NR 1 PFD DISPLAY UNIT REFERENCED HEREIN FAILED DURING GROUND OPERATIONS. THE SUSPECTED SPECIFIC COMPONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY UNIT P/N:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT. FURTHER INSPECTION WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF THE DU FAILURE. 2H72 4T4 FRTA55NM E35NE 20061031001362006103100136 2006 10 31 CMRR200610022 420061019G31607018704902 POWER SUPPLY HONEYWELL DU870 DORNERDO32 DO328300 NM PWA 306 PW306B NE EFIS FAILED B CMRRK NONE H ELECT. POWER LOSS-50 PC ININSP/MAINT 1 SO13405FJ9298 00067009 3155 THE NR 2 MFD DISPLAY UNIT REFERENCED HEREIN FAILED DURING GROUND OPERATIONS. THE SUSPECTED SPECIFIC COMPONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY UNIT P/N:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT. FURTHER INSPECTION WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF THE DU FAILURE. 2H72 4T4 FRTA55NM E35NE 20061031001372006103100137 2006 10 31 CMRR200610023 420061023G31607018704902 POWER SUPPLY HONEYWELL DU870 DORNERDO32 DO328300 NM PWA 306 PW306B NE EFIS FAILED B CMRRK NONE H ELECT. POWER LOSS-50 PC ININSP/MAINT 1 SO13420FJ8290 02014704 3178 THE NR 4 MFD DISPLAY UNIT REFERENCED HEREIN FAILED DURING GROUND OPERATIONS. THE SUSPECTED SPECIFIC COMPONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY UNIT P/N:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT. FURTHER INSPECTION WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF THE DU FAILURE. 2H72 4T4 FRTA55NM E35NE 20061101001122006110100112 2006 11 1 CMRR200611024 420061017G31607018704902 POWER SUPPLY HONEYWELL DU870 DORNERDO32 DO328300 NM PWA 306 PW306B NE EFIS FAILED B CMRRK NONE H ELECT. POWER LOSS-50 PC ININSP/MAINT 1 SO13365SK8912 00066818 3165 THE NR 1 PFD DISPLAY UNIT REFERENCED HEREIN FAILED DURING GROUND OPERATIONS. THE SUSPECTED SPECIFIC COMPONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY UNIT P/N:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT. FURTHER INSPECTION WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF THE DU FAILURE. 2H72 4T4 FRTA55NM E35NE 20061101001112006110100111 2006 11 1 CMRR200611025 420061017G31607018704902 POWER SUPPLY HONEYWELL DU870 DORNERDO32 DO328300 NM PWA 306 PW306B NE EFIS FAILED B CMRRK NONE H ELECT. POWER LOSS-50 PC ININSP/MAINT 1 SO13365SK8912 00066839 3165 THE EICAS DISPLAY UNIT REFERENCED HEREIN FAILED DURING GROUND OPERATIONS. THE SUSPECTED SPECIFIC COMPONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY UNIT P/N:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT. FURTHER INSPECTION WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF THE DU FAILURE. 2H72 4T4 FRTA55NM E35NE 20061101001152006110100115 2006 11 1 CMRR200611026 420061017G31607018704902 POWER SUPPLY HONEYWELL DU870 DORNERDO32 DO328300 NM PWA 306 PW306B NE EFIS FAILED B CMRRK NONE H ELECT. POWER LOSS-50 PC ININSP/MAINT 1 SO13365SK8912 00066873 3165 THE NR 2 MFD DISPLAY UNIT REFERENCED HEREIN FAILED DURING GROUND OPERATIONS. THE SUSPECTED SPECIFIC COMPONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY UNIT P/N 7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT. FURTHER INSPECTION WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF THE DU FAILURE. 2H72 4T4 FRTA55NM E35NE 20061101001142006110100114 2006 11 1 CMRR200611027 420061017G31607018704902 POWER SUPPLY HONEYWELL DU870 DORNERDO32 DO328300 NM PWA 306 PW306B NE EFIS FAILED B CMRRK NONE H ELECT. POWER LOSS-50 PC ININSP/MAINT 1 SO13365SK8912 00128053 3165 THE NR 5 PFD DISPLAY UNIT REFERENCED HEREIN FAILED DURING GROUND OPERATIONS. THE SUSPECTED SPECIFIC COMPONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY UNIT P/N 7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT. FURTHER INSPECTION WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF THE DU FAILURE. 2H72 4T4 FRTA55NM E35NE 20061101001132006110100113 2006 11 1 CMRR200611028 420061017G31607018704902 POWER SUPPLY HONEYWELL DU870 DORNERDO32 DO328300 NM PWA 306 PW306B NE EFIS FAILED B CMRRK NONE H ELECT. POWER LOSS-50 PC ININSP/MAINT 1 SO13365SK8912 00066838 3165 THE NR 4 MFD DISPLAY UNIT REFERENCED HEREIN FAILED DURING GROUND OPERATIONS. THE SUSPECTED SPECIFIC COMPONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY UNIT P/N 7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT. FURTHER INSPECTION WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF THE DU FAILURE. 2H72 4T4 FRTA55NM E35NE 20070104000232007010400023NM 2007 1 4 COOSDR060032 120060824G5712 RIB BOEING737 737301 1384611NM GE CFM56 CFM56* 13802NE RT WING CRACKED B EE4YK NONE O OTHER ININSP/MAINT 1 SO23563AU 23551 RT WING AT WBL 114 RIB UPPER CHORD CRACKED NEAR STR-2. (K) 2L72 4F4 FRTA16WE E2GL 20070104000242007010400024NM 2007 1 4 COOSDR060034 120060825G3320S283U00816 BALLAST BOEING737 7377Q8 1384418NM CFMINTCFM56 CFM563B2 13802EU CABIN OVERHEATED B EE4YO OTHER B SMOKE/FUMES/ODORS/SPARKS NRNOT REPORTED 1 SO23161LF 28224 PAX CABIN LIGHT BALLAST OVERHEATED BURNING INSULATION BLANKET AT BS 328, STR 1. (K) 2L72 4F4 FRTA16WE E21EU 20070125000202007012500020CE 2007 1 25 CWQD200701 120061225G2910AE1011888G0106 HOSE CESSNA750 750 2076810CE ALLSN AE3007AE3007C GL HYD SYSTEM LEAKING E DXTAO OTHER KJ FLUID LOSS WARNING INDICATION APAPPROACH 1 GL05990QS4918 7500190 DURING FINAL APPROACH THE GEAR WAS SELECTED DOWN AND THE (A) HYDRAULIC QTY FELL TO 6 PERCENT WITH (HYD VOL LOW) CAS MESSAGE. JACKED AIRCRAFT, REMOVED PANEL 184DB AND FOUND THE RT GEAR MLG ACTUATOR RETRACT HOSE ASSY HAD A HOLE IN IT. 2L72 4J4 FRTT00007WITE6CH 20060405000022006040500002CE 2006 4 5 CWQR2006001 120060302G2710666000216 TURNBUCKLE CESSNA560 560XL 2076702CE CONTROL CABLE MISMANUFACTURED B DXTAK NONE W INADEQUATE Q C ININSP/MAINT 1 GL05631QS 5605131 DURING A CABLE CHANGE ON THE AILERON SYSTEM, THE PROPER CABLE TENSION COULD NOT BE BROUGHT UP. UPON INSPECTION FOUND NEW CABLE ASSEMBLY TERMINAL END WAS NOT PROPERLY MACHINED. BECAUSE THE NECK (AREA BETWEEN THREADS AND TOOL HOLE) WAS NOT REDUCED THE TURNBARREL BOTTOMS ON THREADS AND CAN NOT BE ADJUSTED TO TENSION REQUIRED. 2L72 4F RTA22CE 20060405000362006040500036CE 2006 4 5 CWQR2006002 120060302G5100991406742 OXYGEN BOTTLE CESSNA750 750 2076810CE UNSERVICEABLE B DXTAO OTHER O OTHER NRNOT REPORTED 1 GL05942QS 7500024 RECEIVED OXYGEN CYLINDER AND REGULATOR FROM CESSNA WITH A CYLINDER BEYOND ITS SERVICE LIFE. BOTTLE HAS 15 YEAR SERVICE LIFE PER CE750 M/M CHAP 5. BOTTLE MFD DATE 9/87. RED TAGGED BOTTLE AND RETURNED TO CESSNA PARTS. 2L72 4J RTT00007WI 20060501002392006050100239CE 2006 5 1 CWQR2006003 120060308G341168C48 DRAIN VALVE CESSNA560 560XL 2076702CE PITOT STATIC SYSLOOSE B DXTAK NONE O OTHER ININSP/MAINT 1 GL05633QS 5605526 FOUND THE STATIC SYSTEM DRAIN VALVE POPPET RETAING RING COMING LOOSE FROM VALVE BASE. 2L72 4F RTA22CE 20060411000482006041100048CE 2006 4 11 CWQR2006004 120060308G341168C48 DRAIN VALVE CESSNA560 560XL 2076702CE STATIC SYSTEM LOOSE B DXTAK NONE O OTHER ININSP/MAINT 1 GL05648QS 5605574 FOUND THE STATIC SYSTEM DRAIN VALVE POPPET RETAING RING COMING LOOSE FROM VALVE BASE. 2L72 4F RTA22CE 20060324000342006032400034CE 2006 3 24 CWQR2006005 120060308G341168C48 DRAIN VALVE CESSNA560 560XL 2076702CE STATIC SYS LOOSE B DXTAK NONE O OTHER ININSP/MAINT 1 GL05609QS 5605522 FOUND THE STATIC SYSTEM DRAIN VALVE POPPET RETAINING RING COMING LOOSE FROM VALVE BASE. 2L72 4F RTA22CE 20060411000492006041100049CE 2006 4 11 CWQR2006006 120060308G341168C48 DRAIN VALVE CESSNA560 560XL 2076702CE LOOSE B DXTAK NONE O OTHER ININSP/MAINT 1 GL05650QS 5605150 FOUND THE STATIC SYSTEM DRAIN VALVE POPPET RETAING RING COMING LOOSE FROM VALVE BASE. 2L72 4F RTA22CE 20060411000502006041100050CE 2006 4 11 CWQR2006007 120060308G341168C48 DRAIN VALVE CESSNA560 560XL 2076702CE LOOSE B DXTAK NONE O OTHER ININSP/MAINT 1 GL05664QS 5605264 FOUND THE STATIC SYSTEM DRAIN VALVE POPPET RETAING RING COMING LOOSE FROM VALVE BASE. 2L72 4F RTA22CE 20060331001162006033100116CE 2006 3 31 CWQR2006008 120060308G3411 RETAINER CESSNA560 560XL 2076702CE DRAIN VALVE LOOSE B DXTAK NONE O OTHER ININSP/MAINT 1 GL05651QS 5605251 FOUND THE STATIC SYSTEM DRAIN VALVE POPPET RETAINING RING COMING LOOSE FROM VALVE BASE. 2L72 4F RTA22CE 20060501002462006050100246CE 2006 5 1 CWQR2006009 120060417G2701666000269 CABLE ASSY CESSNA560 560XL 2076702CE FUSELAGE DAMAGED B DXTAK NONE O OTHER ININSP/MAINT 1 GL05 DURING A SCHEDULED MAINTENANCE VISIT BEFORE REPLACING A CABLE ASSEMBLY ON A THE CABLE TERMINAL END WAS FOUND TO HAVE BEEN DRILLED TO A DEPTH OF .3750-.5 INCH AT AN ANGLE AND DAMAGED THE THREADS. THIS CABLE ASSEMBLY WAS ORDERED FROM AND DOCUMENTED AS NEW. 2L72 4F RTA22CE 20060501002472006050100247CE 2006 5 1 CWQR2006010 120060427G325055423043 FORK CESSNA560 560XL 2076702CE NOSE STEERING GOUGED B DXTAK NONE O OTHER ININSP/MAINT 1 GL05638QS2260 5605363 DURING AN INSPECTION FOUND THE NOSE GEAR STEERING LOWER FORK ASSY (5542304-3) GOUGED. FURTHER INVESTIGATION FOUND THE FORK ASSY IS GOUGED ONLY DURING A MAINTENANCE GEAR RETRACTION TEST, WHEN THE RUDDER PEDALS ARE DEFLECTED FULL RT AND LT. REMOVED FORK ASSY, MEASURED GOUGE WAS BEYOND LIMITS. REPLACED FORK AND PREFORMED GEAR RETRACTION TEST, THE NEW FORK ASSY WAS MEASURED AND PREFORMED NDT, WAS WITHIN LIMITS IAW MM. SUBMITTED SERVICE CONDITION REPORT MFG UNDER NR 234220 DATED 04/27/2006. 2L72 4F RTA22CE 20060629001092006062900109CE 2006 6 29 CWQR2006011 120060626G2731666000134 CONTROL CABLE CESSNA560 560XL 2076702CE ELEVATOR TRIM FRAYED B DXTAK NONE O OTHER ININSP/MAINT 1 GL05692QS 5605092 DURING A PHASE 1-4 INSPECTION THE ELEVATOR TRIM CABLE ASSEMBLY WAS FOUND TO BE FRAYED WHERE IT PASSES THROUGH THE HORIZONTAL STABILIZER. THE CABLE APPEARS TO HAVE BEEN INSTALLED PROPERLY AND IT DOES NOT LOOK AS IF IT WAS DAMAGED DURING INSTALLATION. AN SCR HAS BEEN SUBMITTED TO CESSNA CITATION UNDER 242171. 2L72 4F RTA22CE 20060629001102006062900110CE 2006 6 29 CWQR2006012 120060626G2731666000134 CONTROL CABLE CESSNA560 560XL 2076702CE ELEVATOR TRIM FRAYED B DXTAK NONE O OTHER ININSP/MAINT 1 GL05684QS 5605084 DURING A PHASE 1-4 INSPECTION THE ELEVATOR TRIM CABLE ASSEMBLY WAS FOUND TO BE FRAYED WHERE IT PASSES THROUGH THE HORIZONTAL STABLIZER. THE CABLE APPEARS TO HAVE BEEN INSTALLED PROPERLY AND IT DOES NOT LOOK AS IF IT WAS DAMAGED DURING INSTALLATION. AN SCR HAS BEEN SUBMITTED TO CESSNA CITATION UNDER 242172. 2L72 4F RTA22CE 20060714000582006071400058CE 2006 7 14 CWQR2006013 120060628G2731666000134 CONTROL CABLE CESSNA560 560XL 2076702CE ELEVATOR FRAYED B DXTAK NONE O OTHER ININSP/MAINT 1 GL05671QS 5605071 DURING A PHASE 1-4 INSPECTION THE ELEVATOR TRIM CABLE ASSEMBLY WAS FOUND TO BE FRAYED WHERE IT PASSES THROUGH THE HORIZONTAL STABILIZER. THE CABLE APPEARS TO HAVE BEEN INSTALLED PROPERLY AND DOES NOT LOOK AS IF IT WAS DAMAGED DURING INSTALLATION. AN SCR HAS BEEN SUBMITTED TO CESSNA CITATION UNDER # 242686 2L72 4F RTA22CE 20060719000012006071900001CE 2006 7 19 CWQR2006014 120060712G2731666000134 CABLE ASSY CESSNA560 560XL 2076702CE ELEVATOR TRIM FRAYED B DXTAK NONE O OTHER ININSP/MAINT 1 GL05637QS 5605137 REQUESTED CABLE INSPECTION OF AFT ELEVATOR TRIM CABLE, BECAUSE AC IN THE FLEET OF THIS SN BLOCK AND TIME SHOWED SIGNS OF FRAYING. DURING INSPECTION FOUND THE CABLE FRAYED AS IT TRANSVERSED THE PULLEY. REMOVED CABLE AND CHAIN ASSEMBLY AND PREFORMED LOOP CHECK, THIS SHOWED MORE STRANDS BROKEN THEN WHEN VISUALLY INSPECTED ON AIRCRAFT. PRIOR TO REMOVAL THE CABLE TENSION WAS CHECKED AND FOUND TO BE WITHIN LIMITS, CABLE AND PULLEYS HAD GOOD ALIGNMENT AND NO ABNORMAL WEAR ON THE PULLEYS. AN SCR HAS BEEN SUBMITTED TO MFG UNDER NR 244358 2L72 4F RTA22CE 20060725002372006072500237CE 2006 7 25 CWQR2006015 120060717G2731666000134 CABLE CESSNA560 560XL 2076702CE ELEVATOR TRIM FRAYED B DXTAK NONE P NO WARNING INDICATION ININSP/MAINT 1 GL05690QS 5605090 DURING A SCHEDULED INSP ON THIS AIRCRAFT THE OPERATOR REQUESTED THAT WE INSPECT THE AFT CABLES ON THE ELEVATOR TRIM SYSTEM. PRIOR TO REMOVAL WE CHECKED THE CABLE TENSION, FOUND IT TO BE 30 LBS CABLE TENSION SHOULD BE 45 +/-5 LBS AT 75 DEGREES. INSP AFTER THE CABLE WAS REMOVED REVEALED 1 COMPLETE STRAND BROKE AND SEVERAL WIRES. THE DAMAGED AREA WAS LOCATED DIRECTLY OVER THE PULLEY WHEN THE TAB IS IN THE 2-3 DEGREE DOWN POSITION. THIS IS THE FIFTH ELEVATOR TRIM CABLE THIS REPAIR STATION HAS FOUND DAMAGED ON THIS MODEL AIRCRAFT WITH TOTAL TIME OF 5000 +/-500 HOURS. AN SCR HAS BEEN SUBMITTED TO MFR UNDER NR 244926 2L72 4F RTA22CE 20060816003092006081600309CE 2006 8 16 CWQR2006016 120060728G2731666015021 CONTROL CABLE CESSNA560 560XL 2076702CE ELEVATORS FRAYED B DXTAK NONE O OTHER ININSP/MAINT 1 GL05694QS 5605194 DURING PHASE 1-4 INSPECTION, IAW OPERATOR REQUEST WE INSPECTED THE AFT ELEVATOR TRIM CABLES. UPON INSPECTION WE FOUND A SINGLE BROKEN WIRE. REMOVED CABLE AND PREFORMED LOOP TEST AND FOUND SEVERAL MORE BROKEN WIRES. PRIOR TO DISASSEMBLY THE CABLE TENSION, WAS WITHIN MM LIMITS. INSPECTED CABLE ROUTING AND PULLEYS, ALL CHECKED GOOD. AN SCR HAS BEEN SUBMITTED UNDER NR 246824. 2L72 4F RTA22CE 20060814001442006081400144CE 2006 8 14 CWQR200617 120060731G2731666015011 CONTROL CABLE CESSNA560 560XL 2076702CE ELEVATOR TRIM FRAYED B DXTAK NONE O OTHER ININSP/MAINT 1 GL05687QS 5605187 DURING PHASE B INSPECTION, IAW OPERATOR REQUEST, INSPECTED THE AFT ELEVATOR TRIM CABLES. UPON INSPECTION WE FOUND 3 BROKEN WIRES. REMOVED CABLE AND PREFORMED LOOP TEST AND FOUND SEVERAL BROKEN WIRES IN EACH STRAND. THE BROKEN WIRES WERE FOUND IN THE AREA AS IT CROSSES THE PULLEY, WITH TAB NEUTRAL TO 1-2 DEGREES DOWN. PRIOR TO DISASSEMBLY THE CABLE TENSION WAS CHECKED, WAS WITHIN MM LIMITS. INSPECTED CABLE ROUTING AND PULLEYS, ALL CHECKED GOOD. AN SDR HAS BEEN SUBMITTED TO MFG UNDER NR 246824. 2L72 4F RTA22CE 20060825000412006082500041CE 2006 8 25 CWQR200618 120060807G2731666000133 CABLE ASSY CESSNA560 560XL 2076702CE ELEVATOR TRIM FRAYED B DXTAK NONE O OTHER ININSP/MAINT 1 GL05659QS 5605359 DURING A PHASE B INSPECTION, OPERATOR REQUESTED WE INSPECT THE AFT ELEVATOR TRIM CABLES. UPON INSPECTION WE FOUND BROKEN WIRES, TOOK CABLE TENSIONS, FOUND TO BE WITHIN LIMITS AND CABLE WAS CENTERED IN PULLEY. THE CABLE WAS REMOVED AND LOOP TEST SHOWED MORE BROKEN WIRES. THE WEAR ON THE CABLE APPEARS TO BE IN THE SAME LOCATION THAT WE FOUND ON THE PREVIOUS SIRS SUBMITTED. THAT BEING 0 TO 2 DEGREES TAB DOWN AND FRAYED AREA CENTERED ON PULLEY. AN SCAR HAS BEEN SUBMITTED TO MFG UNDER NR 248175. 2L72 4F RTA22CE 20060825000512006082500051CE 2006 8 25 CWQR200619 120060809G2731666000133 CABLE ASSY CESSNA560 560XL 2076702CE ELEVATOR TRIM FRAYED B DXTAK NONE O OTHER ININSP/MAINT 1 GL05605QS 5605321 DURING A PHASE B INSPECTION, OPERATOR REQUESTED WE INSPECT THE AFT ELEVATOR TRIM CABLES. UPON INSPECTION WE FOUND BROKEN WIRES, TOOK CABLE TENSIONS, FOUND TO BE WITHIN LIMITS AND CABLE WAS CENTERED IN PULLEY. THE CABLE WAS REMOVED AND LOOP TEST SHOWED MORE BROKEN WIRES. THE WEAR ON THE CABLE APPEARS TO BE IN THE SAME LOCATION THAT WE FOUND ON THE PREVIOUS SDRS SUBMITTED. THAT BEING 0 TO 2 DEGREES TAB DOWN AND FRAYED AREA CENTERED ON PULLEY. AN SCR HAS BEEN SUBMITTED TO UNDER NR 248556. 2L72 4F RTA22CE 20060825000342006082500034CE 2006 8 25 CWQR200620 120060814G2731666000133 CONTROL CABLE CESSNA560 560XL 2076702CE ELEVATOR TRIM FRAYED B DXTAK NONE O OTHER ININSP/MAINT 1 GL05610QS 5605210 DURING A PHASE B-INSPECTION, OPERATOR REQUESTED WE INSPECT THE AFT ELEVATOR TRIM CABLES. UPON INSPECTION WE FOUND BROKEN WIRES, TOOK CABLE TENSIONS, FOUND TO BE WITHIN LIMITS AND CABLE WAS CENTERED IN PULLEY.THE CABLE WAS REMOVED AND LOOP TEST SHOWED MORE BROKEN WIRES. THE WEAR ON THE CABLE APPEARS TO BE IN THE SAME LOCATION THAT WE FOUND ON THE PREVIOUS SDRS SUBMITTED. THAT BEING 0 TO 2 DEGREES TAB DOWN AND FRAYED AREA CENTERED ON PULLEY. AN SCR HAS BEEN SUBMITTED TO UNDER NR 249122. 2L72 4F RTA22CE 20060825000352006082500035CE 2006 8 25 CWQR200621 120060821G2731666000133 CONTROL CABLE CESSNA560 560XL 2076702CE ELEVATOR TRIM FRAYED B DXTAK NONE O OTHER ININSP/MAINT 1 GL05640QS 5605240 DURING A PHASE B-INSPECTION, OPERATOR REQUESTED WE INSPECT THE AFT ELEVATOR TRIM CABLES. UPON INSPECTION WE FOUND BROKEN WIRES, TOOK CABLE TENSIONS, FOUND TO BE WITHIN LIMITS AND CABLE WAS CENTERED IN PULLEY. THE CABLE WAS REMOVED AND LOOP TEST SHOWED MORE BROKEN WIRES. THE WEAR ON THE CABLE APPEARS TO BE IN THE SAME LOCATION THAT WE FOUND ON THE PREVIOUS SDRS SUBMITTED. THAT BEING 0 TO 2 DEGREES TAB DOWN AND FRAYED AREA CENTERED ON PULLEY. AN SCR HAS BEEN SUBMITTED TO MFG UNDER NR 250170. 2L72 4F RTA22CE 20060825000162006082500016CE 2006 8 25 CWQR200622 120060821G2731666000134 CONTROL CABLE CESSNA560 560XL 2076702CE ELEVATOR TRIM FRAYED B DXTAK NONE O OTHER ININSP/MAINT 1 GL05621QS 5605280 DURING A PHASE B-INSPECTION, OPERATOR REQUESTED, INSPECT THE AFT ELEVATOR TRIM CABLES. UPON INSPECTION FOUND BROKEN WIRES, TOOK CABLE TENSIONS, FOUND TO BE WITHIN LIMITS AND CABLE WAS CENTERED IN PULLEY. THE CABLE WAS REMOVED AND LOOP TEST SHOWED MORE BROKEN WIRES. THE WEAR ON THE CABLE APPEARS TO BE IN THE SAME LOCATION THAT WE FOUND ON THE PREVIOUS SDRS SUBMITTED. THAT BEING 0 TO 2 DEGREES TAB DOWN AND FRAYED AREA CENTERED ON PULLEY. AN SCR HAS BEEN SUBMITTED TO MFG UNDER NR 250168. 2L72 4F RTA22CE 20060825000322006082500032CE 2006 8 25 CWQR200623 120060821G2720666000228 CONTROL CABLE CESSNA560 560XL 2076702CE RUDDER FRAYED B DXTAK NONE P NO WARNING INDICATION ININSP/MAINT 1 GL05 THE CABLE ASSEMBLY WAS RECEIVED FROM MFG, WITH AN 8130 SHOWING IT TO BE NEW. THE CABLE HAS SEVERAL BROKEN WIRES THAT APPEARS TO BE A MANUFACTURING DEFECT. THIS REPORT AND PICTURES WILL BE FORWARDED TO THE OPERATOR AND MFG. AN SCR HAS BEEN SUBMITTED TO MFG UNDER NR 250181. 2L72 4F RTA22CE 20060913001452006091300145CE 2006 9 13 CWQR200624 120060821G2740666000134 CONTROL CABLE CESSNA560 560XL 2076702CE ELEVATOR TRIM BROKEN B DXTAK NONE O OTHER ININSP/MAINT 1 GL05668QS 5605268 DURING A PHASE 1-4 INSPECTION, OPERATOR REQUESTED WE INSPECT THE AFT ELEVATOR TRIM CABLES. UPON INSPECTION WE FOUND BROKEN WIRES. TOOK CABLE TENSIONS, FOUND TO BE WITHIN LIMITS AND CABLE WAS CENTERED ON THE PULLEYS. THE CABLE WAS REMOVED AND LOOP TEST SHOWED MORE BROKEN WIRES. AN SCR HAS BEEN SUBMITTED TO MFG UNDER NR 250293. 2L72 4F RTA22CE 20060922001052006092200105CE 2006 9 22 CWQR200625 120060829G2720666000134 CONTROL CABLE CESSNA560 560XL 2076702CE TRIM BROKEN B DXTAK NONE O OTHER ININSP/MAINT 1 GL05646QS 5605246 DURING A ROUTINE MAINTENANCE VISIT, OPERATOR REQUESTED WE INSPECT THE AFT ELEVATOR TRIM CABLES. UPON INSPECTION WE FOUND ABOUT .333 OF THE CABLE STRANDS BROKEN. TOOK CABLE TENSIONS, FOUND TO BE WITHIN LIMITS AND CABLE WAS CENTERED ON THE PULLEYS. THE CABLE APPEARS TO HAVE THE MOST DAMAGE CENTERED ON THE PULLEY WITH THE ELEVATOR TRIM TAB IN THE NEUTRAL TO 1-2 DEGREE DOWN POSITION. AN SCR HAS BEEN SUBMITTED TO MFG UNDER NR 251700. 2L72 4F RTA22CE 20060518002322006051800232EU 2006 5 18 D20060502 120060502G5313 LONGERON LET L23 L23 1360308EU REAR COCKPIT CRACKED B PF5RK NONE O OTHER ININSP/MAINT 1 NM03420BA 029007 FIRST LONGERON (N434BA) WAS FOUND CRACKED AT THE ELEVATOR TRIM GUIDE ATTACH POINT, NEAR THE RCP LH RUDDER PEDAL, DURING A SCHEDULED INSPECTION. SUBSEQUENT FINDINGS OCCURRED AS RESULT OF QUALITY DEPARTMENT ISSUING A ONE TIME INSPECTION OF ALL MDS. IT LOOKS AS IF THE OPERATOR, IN THE REAR COCKPIT (RCP), MAY BE STRIKING THE ELEVATOR TRIM GUIDE WITH HIS/HER FOOT WHILE ACTUATING THE RUDDER PEDAL - CAUSING THE SUPPORT STRUCTURE (LONGERON) TO WEAKEN AND FORM CRACKS AT THE ATTACH SCREWS. 1K00 RCG24EU 20070108002752007010800275WP 2007 1 8 DJSA20061202 220061202G7200TFE7315BR2C ENGINE AMD FALC20FALCON20C5 2730107EU GARRTTTFE731TFE7315BR WP FAILED E DJSRA UNSCHED LANDING YJ ENGINE STOPPAGE WARNING INDICATION CLCLIMB 1 GL23531FL5815 961 113 P95155C UNCONTAINED ENGINE FAILURE DURING CLIMB AT 600 FEET AGL. AIRCRAFT RETURNED, MAKING AN UNEVENTFUL LANDING. ENGINE HAS BEEN RETURNED TO MANUFACTURER FOR TEARDOWN AND EVALUATION TO DETERMINE CAUSE OF FAILURE. 2L72 4F4 FRTA7EU E6WE 20060518002292006051800229EU 2006 5 18 DOSS002 120060502G5313 LONGERON LET L23 L23 1360308EU REAR COCKPIT CRACKED B PF5RK NONE O OTHER ININSP/MAINT 1 NM03420BA 029007 FIRST LONGERON (N434BA) WAS FOUND CRACKED AT THE ELEVATOR TRIM GUIDE ATTACH POINT, NEAR THE RCP LH RUDDER PEDAL, DURING A SCHEDULED INSPECTION. SUBSEQUENT FINDINGS OCCURRED AS RESULT OF QUALITY DEPARTMENT ISSUING A ONE TIME INSPECTION OF ALL MDS. IT LOOKS AS IF THE OPERATOR, IN THE REAR COCKPIT (RCP), MAY BE STRIKING THE ELEVATOR TRIM GUIDE WITH HIS/HER FOOT WHILE ACTUATING THE RUDDER PEDAL - CAUSING THE SUPPORT STRUCTURE (LONGERON) TO WEAKEN AND FORM CRACKS AT THE ATTACH SCREWS. 1K00 RCG24EU 20060518001972006051800197EU 2006 5 18 DOSS01 120060502G5313 LONGERON LET L23 L23 1360308EU ZONE 200 CRACKED B PF5RK NONE O OTHER ININSP/MAINT 1 NM03434BA1330 029011 LONGERON WAS FOUND CRACKED AT THE ELEVATOR TRIM GUIDE ATTACH POINT, NEAR THE RCP LT RUDDER PEDAL, DURING A SCHEDULED INSPECTION. IT LOOKS AS IF THE OPERATOR, IN THE REAR COCKPIT (RCP), MAY BE STRIKING THE ELEVATOR TRIM GUIDE WITH HIS/HER FOOT WHILE ACTUATING THE RUDDER PEDAL, CAUSING THE SUPPORT STRUCTURE (LONGERON) TO WEAKEN AND FORM CRACKS AT THE ATTACH SCREWS. THIS WAS ENCOUNTERED ON TWELVE OUT OF SEVENTEEN AIRCRAFT (L13AC AND L23). 1K00 RCG24EU 20060518002282006051800228EU 2006 5 18 DOSS02 120060502G5313 LONGERON LET L23 L23 1360308EU REAR COCKPIT CRACKED B PF5RK NONE O OTHER ININSP/MAINT 1 NM03420BA 029007 FIRST LONGERON (N434BA) WAS FOUND CRACKED AT THE ELEVATOR TRIM GUIDE ATTACH POINT, NEAR THE RCP LT RUDDER PEDAL, DURING A SCHEDULED INSPECTION. SUBSEQUENT FINDINGS OCCURRED AS RESULT OF QUALITY DEPARTMENT ISSUING A ONE TIME INSPECTION OF ALL MDS. IT LOOKS AS IF THE OPERATOR, IN THE REAR COCKPIT (RCP), MAY BE STRIKING THE ELEVATOR TRIM GUIDE WITH HIS/HER FOOT WHILE ACTUATING THE RUDDER PEDAL, CAUSING THE SUPPORT STRUCTURE (LONGERON) TO WEAKEN AND FORM CRACKS AT THE ATTACH SCREWS. 1K00 RCG24EU 20060522002112006052200211EU 2006 5 22 DOSS03 120060502G5313 LONGERON LET L23 L23 1360308EU REAR COCKPIT CRACKED B PF5RK NONE O OTHER ININSP/MAINT 1 NM03426BA1115 92 029008 FIRST LONGERON (N434BA) WAS FOUND CRACKED AT THE ELEVATOR TRIM GUIDE ATTACH POINT, NEAR THE RCP LH RUDDER PEDAL, DURING A SCHEDULED INSPECTION. SUBSEQUENT FINDINGS OCCURRED AS RESULT OF QUALITY DEPARTMENT ISSUING A ONE TIME INSPECTION OF ALL MDS. IT LOOKS AS IF THE OPERATOR, IN THE REAR COCKPIT (RCP), MAY BE STRIKING THE ELEVATOR TRIM GUIDE WITH HIS/HER FOOT WHILE ACTUATING THE RUDDER PEDAL, CAUSING THE SUPPORT STRUCTURE (LONGERON) TO WEAKEN AND FORM CRACKS AT THE ATTACH SCREWS. 1K00 RCG24EU 20060518002332006051800233EU 2006 5 18 DOSS04 120060502G5313 LONGERON LET L23 L23 1360308EU REAR COCKPIT CRACKED B PF5RK NONE O OTHER ININSP/MAINT 1 NM03427BA873 14 029009 FIRST LONGERON (N434BA) WAS FOUND CRACKED AT THE ELEVATOR TRIM GUIDE ATTACH POINT, NEAR THE RCP LT RUDDER PEDAL, DURING A SCHEDULED INSPECTION. SUBSEQUENT FINDINGS OCCURRED AS RESULT OF QUALITY DEPARTMENT ISSUING A ONE TIME INSPECTION OF ALL MDS. IT LOOKS AS IF THE OPERATOR, IN THE REAR COCKPIT (RCP), MAY BE STRIKING THE ELEVATOR TRIM GUIDE WITH HIS/HER FOOT WHILE ACTUATING THE RUDDER PEDAL - CAUSING THE SUPPORT STRUCTURE (LONGERON) TO WEAKEN AND FORM CRACKS AT THE ATTACH SCREWS. 1K00 RCG24EU 20060530001682006053000168EU 2006 5 30 DOSS05 120060502G5313 LONGERON LET L23 L23 1360308EU REAR COCKPIT CRACKED B PF5RK NONE O OTHER ININSP/MAINT 1 NM03428BA1123 5 029010 FIRST LONGERON (N434BA) WAS FOUND CRACKED AT THE ELEVATOR TRIM GUIDE ATTACH POINT, NEAR THE REAR COCKPIT (RCP) LT RUDDER PEDAL DURING A SCHEDULED INSPECTION. SUBSEQUENT FINDINGS OCCURRED AS RESULT OF QUALITY DEPARTMENT ISSUING A ONE TIME INSPECTION OF ALL MODELS. IT LOOKS AS IF THE OPERATOR, IN THE REAR COCKPIT (RCP), MAY BE STRIKING THE ELEVATOR TRIM GUIDE WITH HIS/HER FOOT WHILE ACTUATING THE RUDDER PEDAL - CAUSING THE SUPPORT STRUCTURE (LONGERON) TO WEAKEN AND FORM CRACKS AT THE ATTACH SCREWS. 1K00 RCG24EU 20060518002342006051800234EU 2006 5 18 DOSS06 120060502G5313 LONGERON LET L23 L23 1360308EU REAR COCKPIT CRACKED B PF5RK NONE O OTHER ININSP/MAINT 1 NM03430BA1461 029012 FIRST LONGERON (N434BA) WAS FOUND CRACKED AT THE ELEVATOR TRIM GUIDE ATTACH POINT, NEAR THE RCP LT RUDDER PEDAL, DURING A SCHEDULED INSPECTION. SUBSEQUENT FINDINGS OCCURRED AS RESULT OF QUALITY DEPARTMENT ISSUING A ONE TIME INSPECTION OF ALL MDS. IT LOOKS AS IF THE OPERATOR, IN THE REAR COCKPIT (RCP), MAY BE STRIKING THE ELEVATOR TRIM GUIDE WITH HIS/HER FOOT WHILE ACTUATING THE RUDDER PEDAL - CAUSING THE SUPPORT STRUCTURE (LONGERON) TO WEAKEN AND FORM CRACKS AT THE ATTACH SCREWS. 1K00 RCG24EU 20060518002352006051800235EU 2006 5 18 DOSS07 120060502G5313 LONGERON LET L23 L23 1360308EU REAR COCKPIT CRACKED B PF5RK NONE O OTHER ININSP/MAINT 1 NM03431BA1120 68 029013 FIRST LONGERON (N434BA) WAS FOUND CRACKED AT THE ELEVATOR TRIM GUIDE ATTACH POINT, NEAR THE RCP LT RUDDER PEDAL, DURING A SCHEDULED INSPECTION. SUBSEQUENT FINDINGS OCCURRED AS RESULT OF QUALITY DEPARTMENT ISSUING A ONE TIME INSPECTION OF ALL MDS. IT LOOKS AS IF THE OPERATOR, IN THE REAR COCKPIT (RCP), MAY BE STRIKING THE ELEVATOR TRIM GUIDE WITH HIS/HER FOOT WHILE ACTUATING THE RUDDER PEDAL - CAUSING THE SUPPORT STRUCTURE (LONGERON) TO WEAKEN AND FORM CRACKS AT THE ATTACH SCREWS. 1K00 RCG24EU 20060518002362006051800236EU 2006 5 18 DOSS08 120060502G5313 LONGERON LET L23 L23 1360308EU REAR COCKPIT CRACKED B PF5RK NONE O OTHER ININSP/MAINT 1 NM03433BA978 029014 FIRST LONGERON (N434BA) WAS FOUND CRACKED AT THE ELEVATOR TRIM GUIDE ATTACH POINT, NEAR THE RCP LH RUDDER PEDAL, DURING A SCHEDULED INSPECTION. SUBSEQUENT FINDINGS OCCURRED AS RESULT OF QUALITY DEPARTMENT ISSUING A ONE TIME INSPECTION OF ALL MDS. IT LOOKS AS IF THE OPERATOR, IN THE REAR COCKPIT (RCP), MAY BE STRIKING THE ELEVATOR TRIM GUIDE WITH HIS/HER FOOT WHILE ACTUATING THE RUDDER PEDAL - CAUSING THE SUPPORT STRUCTURE (LONGERON) TO WEAKEN AND FORM CRACKS AT THE ATTACH SCREWS. 1K00 RCG24EU 20060518002372006051800237EU 2006 5 18 DOSS10 120060502G5313 LONGERON LET L23 L23 1360308EU REAR COCKPIT CRACKED B PF5RK NONE O OTHER ININSP/MAINT 1 NM03438BA524 41 029016 FIRST LONGERON (N434BA) WAS FOUND CRACKED AT THE ELEVATOR TRIM GUIDE ATTACH POINT, NEAR THE RCP LT RUDDER PEDAL, DURING A SCHEDULED INSPECTION. SUBSEQUENT FINDINGS OCCURRED AS RESULT OF QUALITY DEPARTMENT ISSUING A ONE TIME INSPECTION OF ALL MDS. IT LOOKS AS IF THE OPERATOR, IN THE REAR COCKPIT (RCP), MAY BE STRIKING THE ELEVATOR TRIM GUIDE WITH HIS/HER FOOT WHILE ACTUATING THE RUDDER PEDAL - CAUSING THE SUPPORT STRUCTURE (LONGERON) TO WEAKEN AND FORM CRACKS AT THE ATTACH SCREWS. 1K00 RCG24EU 20060518002312006051800231EU 2006 5 18 DOSS102 120060502G5313 LONGERON LET L23 L23 1360308EU REAR COCKPIT CRACKED B PF5RK NONE O OTHER ININSP/MAINT 1 NM03420BA 029007 FIRST LONGERON (N434BA) WAS FOUND CRACKED AT THE ELEVATOR TRIM GUIDE ATTACH POINT, NEAR THE RCP LT RUDDER PEDAL, DURING A SCHEDULED INSPECTION. SUBSEQUENT FINDINGS OCCURRED AS RESULT OF QUALITY DEPARTMENT ISSUING A ONE TIME INSPECTION OF ALL MDS. IT LOOKS AS IF THE OPERATOR, IN THE REAR COCKPIT (RCP), MAY BE STRIKING THE ELEVATOR TRIM GUIDE WITH HIS/HER FOOT WHILE ACTUATING THE RUDDER PEDAL - CAUSING THE SUPPORT STRUCTURE (LONGERON) TO WEAKEN AND FORM CRACKS AT THE ATTACH SCREWS. 1K00 RCG24EU 20060518002382006051800238EU 2006 5 18 DOSS11 120060502G5313 LONGERON LET L23 L23 1360308EU REAR COCKPIT CRACKED B PF5RK NONE O OTHER ININSP/MAINT 1 NM03419BA1320 71 029006 FIRST LONGERON (N434BA) WAS FOUND CRACKED AT THE ELEVATOR TRIM GUIDE ATTACH POINT, NEAR THE RCP LT RUDDER PEDAL, DURING A SCHEDULED INSPECTION. SUBSEQUENT FINDINGS OCCURRED AS RESULT OF QUALITY DEPARTMENT ISSUING A ONE TIME INSPECTION OF ALL MDS. IT LOOKS AS IF THE OPERATOR, IN THE REAR COCKPIT (RCP), MAY BE STRIKING THE ELEVATOR TRIM GUIDE WITH HIS/HER FOOT WHILE ACTUATING THE RUDDER PEDAL - CAUSING THE SUPPORT STRUCTURE (LONGERON) TO WEAKEN AND FORM CRACKS AT THE ATTACH SCREWS. 1K00 RCG24EU 20060530001632006053000163EU 2006 5 30 DOSS12 120060502G5313 LONGERON LET L13 L13ACBLANIK 1360312EU REAR COCKPIT CRACKED B PF5RK NONE O OTHER ININSP/MAINT 1 NM03422BA1109 54 028903 FIRST LONGERON (N434BA) WAS FOUND CRACKED AT THE ELEVATOR TRIM GUIDE ATTACH POINT, NEAR THE REAR COCKPIT (RCP) LT RUDDER PEDAL, DURING A SCHEDULED INSPECTION. SUBSEQUENT FINDINGS OCCURRED AS RESULT OF QUALITY DEPARTMENT ISSUING A ONE TIME INSPECTION OF ALL MDS. IT LOOKS AS IF THE OPERATOR, IN THE REAR COCKPIT, MAY BE STRIKING THE ELEVATOR TRIM GUIDE WITH HIS/HER FOOT WHILE ACTUATING THE RUDDER PEDAL - CAUSING THE SUPPORT STRUCTURE (LONGERON) TO WEAKEN AND FORM CRACKS AT THE ATTACH SCREWS. 1K00 G24EU 20060518002582006051800258EU 2006 5 18 DOSS13 120060502G5313 LONGERON LET L23 L23 1360308EU REAR COCKPIT CRACKED B PF5RK NONE O OTHER ININSP/MAINT 1 NM03410BA1109 54 029005 FIRST LONGERON (N434BA) WAS FOUND CRACKED AT THE ELEVATOR TRIM GUIDE ATTACH POINT, NEAR THE RCP LT RUDDER PEDAL, DURING A SCHEDULED INSPECTION. SUBSEQUENT FINDINGS OCCURRED AS RESULT OF QUALITY DEPARTMENT ISSUING A ONE TIME INSPECTION OF ALL MDS. IT LOOKS AS IF THE OPERATOR, IN THE REAR COCKPIT (RCP), MAY BE STRIKING THE ELEVATOR TRIM GUIDE WITH HIS/HER FOOT WHILE ACTUATING THE RUDDER PEDAL, CAUSING THE SUPPORT STRUCTURE (LONGERON) TO WEAKEN AND FORM CRACKS AT THE ATTACH SCREWS. 1K00 RCG24EU 20061013000402006101300040WP 2006 10 13 DSC4L6255 220061003G721018118 BEARING GARRTTTPE331TPE33111U 01514WP GEARBOX FAILED B DSC4K NONE J WARNING INDICATION ININSP/MAINT 1 SO15 6475 P44628C ENGINE RECEIVED FOR REPORTED METAL IN OIL. UPON DISASSEMBLY, FOUND BEARING PN: 18118 (FAA-PMA REPLACEMENT PN: 3103585-1) INSTALLED IN ACCESSORY GEAR ASSY PN: 3103598-1 HAD FAILED, CAUSING MULTIPLE ACCESSORY GEAR DAMAGE AND METAL CONTAMINATION IN GEARBOX / OIL SYSTEM. 4 T E4WE 20060411000272006041100027NM 2006 4 11 DU4R2006342 120060313G5330 SKIN BOEING727 727223 1384074NM BS 1074 S18-19L DENTED B DU4RK NONE O OTHER ININSP/MAINT 1 SO15289MT 22467 FUSELAGE SKIN DENTED AT BS 1074 BETWEEN S-18L - 19L. CUT OUT DENTED AREA IAW B727 SRM 53-30-2 FIG. 1 HFEC AROUND CUT OUT PER D6-48875, PT 6, 51-10-00 FIG. 23. NO RELEVANT INDICATION NOTED. FABRICATED AND INSTALLED REPAIR DOUBLER 12" X 11.7" X 7.55" FROM 2024-T3 .063 IAW B727 SRM 51-30-3 FIG. 1, 51-10-2, 51-30-2, 53-30-3 CLASS "A" REPAIR. 2L73 4F A3WE 20060411000282006041100028NM 2006 4 11 DU4R2006343 120060313G5330 SKIN BOEING727 727223 1384074NM BS 1079 DENTED B DU4RK NONE O OTHER ININSP/MAINT 1 SO15289MT 22467 FUSELAGE SKIN DENTED AT BS 1079 BETWEEN S-13-14L. CUT OUT DENTED AREA IAW B727 SRM 53-30-3 FIG. 13A. FABRICATED AND INSTALLED REPAIR DOUBLER 5.80 DIAMETER FROM 2024-T3 .090 IAW B727 SRM 51-10-2 PG. 7, AMM 51-20-23 PG. 704. CLASS "A" REPAIR. 2L73 4F A3WE 20060411000242006041100024NM 2006 4 11 DU4R2006344 120060320G5330 SKIN BOEING727 727223 1384074NM BS 1145 DENTED B DU4RK NONE O OTHER ININSP/MAINT 1 SO15289MT 22467 FUSELAGE SKIN DENTED AT BS 1145 BETWEEN S18-19L. FABRICATED AND INSTALLED REPAIR DOUBLER 10-3/4" X 9" FROM 2024-T3 .063 IAW B727 SRM 53-30-3 AND 51-30-2. CLASS "A" REPAIR. 2L73 4F A3WE 20060411000262006041100026NM 2006 4 11 DU4R2006345 120060322G531565255896 FLOORBEAM BOEING727 727223 1384074NM BS 760 RBL 1 CRACKED B DU4RK NONE O OTHER ININSP/MAINT 1 SO15289MT 22467 CRACK IN CABIN FLOOR SUPPORT BS 760 RBL 1. REMOVED AND REPLACED FLOOR SUPPORT WITH IAW B727 SRM 51-30-2 AND 51-30-5. 2L73 4F A3WE 20060411000232006041100023NM 2006 4 11 DU4R2006346 120060326G5310 STRUCTURE BOEING727 727223 1384074NM BS 1166 CORRODED B DU4RK NONE O OTHER ININSP/MAINT 1 SO15289MT 22467 RT AFT LAV SUB FLOOR HAS CORROSION IN SEVERAL PLACES AT BS 1166. CUT OUT CORROSION. FABRICATED AND INSTALLED WEB REPAIR 15-3/4" X 4-3/4" FROM 2024-T3 .071 IAW B727 SRM 51-40-2, 51-30-2, 51-10-2 AND AMM 51-20-23. 2L73 4F A3WE 20060411000252006041100025NM 2006 4 11 DU4R2006347 120060326G5347656426110 SEAT TRACK BOEING727 727223 1384074NM BS1120-1133 CORRODED B DU4RK NONE O OTHER ININSP/MAINT 1 SO15289MT 22467 CORROSION ON LT O/B SEAT TRACK BS 1100-1133. REMOVED CORRODED SEAT TRACK FROM BS 1070 TO BS 1137 AND REPLACED IAW B727 SRM 51-30-2, 51-10-2 AND AMM 51-20-23. 2L73 4F A3WE 20060411000222006041100022NM 2006 4 11 DU4R2006355 120060331G5330 SKIN BOEING727 727223 1384074NM BS 1137 S20L DENTED B DU4RK NONE O OTHER ININSP/MAINT 1 SO15289MT 22467 FUSELAGE SKIN BELOW NR 1 ENGINE DENTED AT LAP SEAM BS 1137 S-20L. CUT OUT DENTED AREA. FABRICATED AND INSTALLED EXTERNAL REPAIR 7.75" X 9.25" X5.75" X 2.5" FROM 20240-T3 .063 AND LAP SPLICE REPAIR 10" X 4.25" X 4.5" X 2.75" X 4.5" FROM 2024-T3 .050 IAW B727 SRM 53-30-3 FIG. 5, 51-10-3. 2L73 4F A3WE 20060518001782006051800178NM 2006 5 18 DU4R2006358 120060412G5752 TAB BOEING727 727223 1384074NM RT AILERON DELAMINATED B DU4RK NONE O OTHER ININSP/MAINT 1 SO15289MT 22467 S/O 304001; NR 21453 - RT IB AILERON TAB DELAMINATED AT LOWER SURFACE OUTER L/E AREA. CUT OUT DISBONDED SKIN. FABRICATED AND BONDED DOUBLER 10.5 X 3.7500 INCH X 9 X 3.5 X 2.2500 INCH AND FILLER 8 INCH X 1.7500 INCH X 7.2500 INCH X 1 INCH X 1 INCH FROM 2024-T3, .012 IAW SRM 51-40-20 PG. 14, 15, 42 - 47 AND 62, 51-60-3 AND 51-80-3. 2L73 4F A3WE 20060512001592006051200159NM 2006 5 12 DU4R2006359 120060412G5753 FLAP BOEING727 727223 1384074NM LT WING DELAMINATED B DU4RK NONE O OTHER ININSP/MAINT 1 SO15289MT 22467 S/O 304001 N/R 21634 - LT IB FORE FLAP UPPER SIDE HAS DISBOND AFT OF CENTER ACCESS PANEL. CUT OUT DISBONDED UPPER SKIN AND HONEYCOMB. FABRICATED AND BONDED DOUBLERS 13-5/8" X 11" AND 12-1/2" X 11-1/4" AND 9-1/4" X 8? X 5" X 5" X 5" FROM 2024-T3 .016 AND AND 2 EA. HONEYCOMB REPAIRS 9-1/4" X 5" X 5" X 5" X 8" FROM BMS4-4 IAW B727 SRM 57-50-2 PG. 5, 51-40-20 PG. 15, 22, 23, 44 - 47, 53-57, 59, 62 AND 51-40-23 PG. 1-8. 2L73 4F A3WE 20060518002602006051800260NM 2006 5 18 DU4R200636 120060412G5320 FLOOR SUPPORT BOEING727 727223 1384074NM FUSELAGE CORRODED B DU4RK NONE O OTHER ININSP/MAINT 1 SO15289MT 22467 S/O 304001) N/R 21660, CORROSION ON FLOOR SUPPORT THAT ATTACHES TO CUSP WEB AT BS 1070 - 1030 LT. MECHANICALLY REMOVED CORROSION FOUND OUT OF LIMITS. CUT AND TRIMMED CORRODED SECTION. FABRICATED AND INSTALLED FLOOR SUPPORT ANGLES 88.0 INCHES X 4.50 FROM 7075-T6 .080 AND 10.0INCHES X 1.80 INCHES X 1.50 INCHES 7075-T6 .090 IAW SRM 51-30-2. 2L73 4F A3WE 20060518002262006051800226NM 2006 5 18 DU4R2006360 120060412G5753 FLAP BOEING727 727223 1384074NM LT WING CHAFED B DU4RK NONE O OTHER ININSP/MAINT 1 SO15289MT 22467 S/O 304001) N/R 21637 - LT IB FORE FLAP UNDER SIDE LEADING EDGE 8 INCHES FROM OB END HAS CHAFED AREA. BLENDED CHAFED AREA, FOUND OUT OF LIMITS, FABRICATED AND INSTALLED DOUBLER 3.750 INCHES X 6.0 INCHES FROM 2024-T3 .063 IAW SRM 57-50-04 PG. 2-3. 2L73 4F A3WE 20060518002272006051800227NM 2006 5 18 DU4R2006361 120060412G5753 FLAP BOEING727 727223 1384074NM LT WING DEBONDED B DU4RK NONE O OTHER ININSP/MAINT 1 SO15289MT 22467 S/O 304001) N/R 21640 - LT IB FT FLAP IB END HAS AREA OF DEBOND. REPAIRED BY CLEANING, PREPPED AND REPAIRED IAW SRM 51-40-21 FIG. 1. 2L73 4F A3WE 20060518002252006051800225NM 2006 5 18 DU4R2006362 120060412G5347BAC1518338 FLOORBEAM BOEING727 727223 1384074NM FUSELAGE CORRODED B DU4RK NONE O OTHER ININSP/MAINT 1 SO15289MT 22467 S/O 304001) N/R 21652 - CORROSION ON BS 1070 LBL 10 FLOOR BEAM. CUT OUT CORRODED AREA. FABRICATED AND INSTALLED FLOORBEAM REPAIR 22.20 INCHES FROM BAC1505-100617 7075-T73 AND 22.20 INCHES FROM BAC1490-2831 7075-T6 IAW SRM 53-10-8 FIG. 8, AND 51-10-1. 2L73 4F A3WE 20060518002242006051800224NM 2006 5 18 DU4R2006363 120060412G5347BAC1518338 SEAT TRACK BOEING727 727223 1384074NM FUSELAGE CORRODED B DU4RK NONE O OTHER ININSP/MAINT 1 SO15289MT 22467 S/O 304001, N/R 21653 - CORROSION ON IB SIDE OF SEAT TRACK ALONG RADIUS AT BS 1090 - 1030 LBL 40. CUT OUT CORRODED AREA OF SEAT TRACK. FABRICATED AND INSTALLED SEAT TRACK REPAIR 18 INCHES X 3.5 FROM BAC1520-792 IAW SRM 51-30-2, 51-20-2 AND 51-10-1. 2L73 4F A3WE 20060518002492006051800249NM 2006 5 18 DU4R2006364 120060412G5347656426110 SEAT TRACK BOEING727 727223 1384074NM FUSELAGE CORRODED B DU4RK NONE O OTHER ININSP/MAINT 1 SO15289MT 22467 S/O 304001) N/R 21656, CORROSION ON LT OB SEAT TRACK AT BS 1080. MECHANICALLY REMOVED CORROSION FOUND OUT OF LIMITS. REMOVED AND REPAIRED SEAT TRACK WITH P/N 65-64261-10 IAW SRM 51-30-2. 2L73 4F A3WE 20060518002592006051800259NM 2006 5 18 DU4R2006365 120060412G5320 FLOOR SUPPORT BOEING727 727223 1384074NM FUSELAGE CORRODED B DU4RK NONE O OTHER ININSP/MAINT 1 SO15289MT 22467 S/O 304001) N/R 21660, CORROSION ON FLOOR SUPPORT THAT ATTACHES TO CUSP WEB AT BS 1070 - 1030 LT. MECHANICALLY REMOVED CORROSION FOUND OUT OF LIMITS. CUT AND TRIMMED CORRODED SECTION. FABRICATED AND INSTALLED FLOOR SUPPORT ANGLES 88.0 INCH X 4.50 FROM 7075-T6 .080 AND 10.0 INCHES X 1.80 INCHES X 1.50 INCHES 7075-T6 .090 IAW SRM 51-30-2. 2L73 4F A3WE 20060518002502006051800250NM 2006 5 18 DU4R2006366 120060412G5330 SKIN BOEING727 727223 1384074NM FUSELAGE GOUGED B DU4RK NONE O OTHER ININSP/MAINT 1 SO15289MT 22467 S/O 304001) N/R 21743, 2 GOUGES IN SKIN ON LT SIDE OF FS 460 AND 4 INCHES BELOW S-14 BELOW NR 5 WINDOW. FABRICATED AND INSTALLED 2 EA. DOUBLERS 4.5 INCH AND 4.3 DIAMETER FROM 2024-T3 .071 AND 1 EA, .7500 INCH DIAMETER FROM 2024-T3 .050 IAW SRM 53-30-3 FIG. 13, MM 25-21-01. 2L73 4F A3WE 20060518002702006051800270NM 2006 5 18 DU4R2006367 120060412G5754 SKIN BOEING727 727223 1384074NM RT WING SLAT DENTED B DU4RK NONE O OTHER ININSP/MAINT 1 SO15289MT 22467 S/O 304001, N/R 23584 - RT WING NR 5 SLAT TOPSIDE L/E DENTED. CUT OUT DENT THAT WAS OUT OF LIMITS. FABRICATED AND INSTALLED REPAIR SKIN DOUBLER 5.5 INCH X 5.5 INCH FROM 2024-T3 .016 AND 2 EA. SKIN REPAIR DOUBLERS 4.1 INCH X 4.1 INCH AND 1.6 INCH X 1.6 INCH 2024-T3 .040 IAW SRM 55-50-3 FIG. 1, AND 51-30-2. 2L73 4F A3WE 20060518002642006051800264NM 2006 5 18 DU4R2006368 120060412G5751 AILERON BOEING727 727223 1384074NM RT WING DENTED B DU4RK NONE O OTHER ININSP/MAINT 1 SO15289MT 22467 S/O 304001) N/R 24581, RT WING IB AILERON NUMEROUS DENTS. REMOVED DENTED SKIN. FABRICATED AND INSTALLED REPAIR SKIN DOUBLER 5.5 INCH X 5.5 INCH FROM 2024-T3 .016 AND 2 EA. SKIN REPAIR DOUBLER 24 INCH X 54 INCH FROM 2024-T3 .040 IAW SRM 51-10-2 AND 51-30-2. 2L73 4F A3WE 20060518002512006051800251NM 2006 5 18 DU4R2006369 120060412G32306523369 FRAME BOEING727 727223 1384074NM FUSELAGE CORRODED B DU4RK NONE O OTHER ININSP/MAINT 1 SO15289MT 22467 S/O 304001) N/R 24783 CORROSION FOUND INSIDE THE HOLE OF UPLOCK HOOK INSTALL FITTING BOTH FWD AND AFT SIDE. REMOVED 2 EA BUSHINGS (REPAIR SLEEVES) IAW SOPM 32-32-51. REWORKED FRAME HOLE 9 IAW OHM 32-37-02 AND SRM 51-10-1. FABRICATED AND INSTALLED 2 EA. REPAIR SLEEVES IAW OHM 32-37-02 FIG. 404, 405 AND SOPM 20-50-3. REINSTALLED UPLOCK FRAME AND UPLOCK ASSY IAW MM 32-32-51. 2L73 4F A3WE 20060512000462006051200046NM 2006 5 12 DU4R2006370 120060414G5753 SKIN BOEING727 727223 1384074NM RT WING,FOREFLAPDELAMINATED B K NONE O OTHER ININSP/MAINT 1 SO15289MT 22467 NR 24718 DENTED AND DISBONDED RT IB FORE FLAP UPPER SKIN 19 INCHES FROM IB EDGE. REPAIRED DENTED AND DISBONDED RT IB FORE FLAP UPPER SKIN 19 INCHES FROM IB EDGE BY CUTTING OUT DELAMINATED AREA, APPROX 5 INCHES IN DIAMETER. FABRICATED AND INSTALLED DOUBLER AND FILLER 8 INCHES DIAMETER AND 5 INCHES FROM 2024-T3 .016 IAW SRM 51-40-20 PARA. 7, 8, 10, 14, 15, 18, 20, 21, 22. 2L73 4F A3WE 20060518001612006051800161NM 2006 5 18 DU4R2006371 120060414G5753 SKIN BOEING727 727223 1384074NM PWA JT8 JT8D NE LT FLAP DELAMINATED B DU4RK NONE O OTHER ININSP/MAINT 1 SO15289MT 22467 N/R 24751) FOUND SMALL AREA OF DELAMINATION OF UPPER IB SKIN LT IB FORE FLAP. CUT OUT DELAMINATED (DISBONDED) AREA ON UPPER SKIN LT IB FORE FLAP. FABRICATED AND BONDED DOUBLER 6.5 X 5.6250 INCH AND FILLER 3.3750 INCH X 1.2500 INCH FROM 2024-T3 .016 IAW SRM 57-50-2 PG. 5, 51-40-20 PG. 11-16, 42-47, 57-59, AND 62. 2L73 4F4 F A3WE E2EA 20060518001732006051800173NM 2006 5 18 DU4R2006372 120060414G5512 SKIN BOEING727 727223 1384074NM PWA JT8 JT8D* NE RT STABILIZER TORN B DU4RK NONE O OTHER ININSP/MAINT 1 SO15289MT 22467 NR 24794 FOUND RT HORIZ STAB. T/E UPPER SKIN TORN BOTH IB AND OB SIDE OF NR3 BALANCE BAY STAB. STA. 157 AND 195 AFT OF AFT SPAR. CUT OUT TORN SKIN OF RT HORIZ. STAB. T/E BOTH IB AND OB END OF NR3 BALANCE BAY. FABRICATED AND INSTALLED DOUBLERS 10.8 X 5.3 INCHES, 4.7 X 4.6 INCHES AND 3.8 X .7 INCHES FROM 2024-T3 .032 IAW SRM 51-40-20 FIG. 1. 2L73 4F4 F A3WE E2EA 20060510002512006051000251NE 2006 5 10 DU4R2006373 220060416G7230 DISC BOEING727 727223 1384074NM PWA JT8 JT8D NE ENGINE UNSERVICEABLE B DU4RK NONE O OTHER ININSP/MAINT 1 SO16289MT 22467 702863 S/O 304001 NR 24710 C-1 DISK REQUIRES REPLACEMENT. PERFORMED VIBRATION CHECK ON NR 1 ENGINE AFTER C-1 DISK REPLACEMENT IAW P/W MM 72-00-00, PG. 571 TEST I AND MM 71-00-00 PG. 500. FOUND ALL VALVES WITHIN LIMITS. 2L73 4F4 F A3WE E2EA 20060926000632006092600063EA 2006 9 26 DYCR0596101 220060831G732225765362 FUEL CONTROL CESSNA172 172R 2072401CE LYC IO360 IO360L2A EA ENGINE MISOVERHAULED B DYCRO OTHER Y ENGINE STOPPAGE APAPPROACH 1 GL07173QS4017 31 17280460 L2749851A A STUDENT PILOT WITH AN INSTRUCTOR ON BOARD WERE PRACTICING STALLS WHEN THE ENGINE CUT OFF, THEY WERE ABLE TO RESTART THE ENGINE WITHOUT FURTHER INCIDENT. DURING THE SAME FLIGHT, WHILE ON APPROACH FOR LANDING THE ENGINE CUT OFF AGAIN. THE STUDENT AND THE INSTRUCTOR WERE ABLE TO LAND THE AIRCRAFT ON THE RUNWAY WITHOUT INCIDENT. IN BOTH CASES THE PROPELLER WAS WINDMILLING. THE AIRCRAFT WAS TOWED TO MAINTENANCE FROM THE RUNWAY. MAINTENANCE CHECKED FUEL SYSTEM FOR FOD, LEAKS, CHECKED RIGGING AND COMPLIED WITH AD 2001-06-17. MAINTENANCE WAS UNABLE TO DUPLICATE PROBLEM ON THE GROUND. FUEL SERVO WAS STILL SUSPECT AFTER READING OTHER SDR'S ON LIKE MODEL AIRCRAFT WITH SIMILAR PROBLEMS SO SERVO WAS REMOVED AND SENT TO A 1H71 3O3 ONT3A12 1E10 20061031001662006103100166SO 2006 10 31 EDRCCUI 220061021G8550629448 GEAR SHAFT CONT CESSNA206 U206G 2073356CE CONT O550 IO550F 17042SO HARTZLHCJ3Y PHCJ3YF1 GL ENGINE SHEARED D E ENGINE SHUTDOWN O OTHER TXTAXI/GRND HDL 1 NM089QCUI404 U20606373 679590 DURING PREFLIGHT, ENGINE RUNUP PILOT WAS UNABLE TO CYCLE PROP AND THEN NOTICED ZERO OIL PRESSURE ON THE OIL PRESSURE GAUGE, ENGINE SHUTDOWN. INSPECTION REVEALED THE GEAR SHAFT ASSY IN THE OIL PUMP HOUSING WAS SHEARD. MFG HAS ASKED US TO SEND THE ENGINE BACK TO THE FACTORY FOR EXAMINATION. WE HAVE PHOTOS OF THE FAILED PART IF YOU TELL US HOW TO SEND THEM TO YOU. 1H71 3O3 O A4CE E3SO 5 CP36EA 20061115002982006111500298CE 2006 11 15 EVGR1113735 120061109G5310 DOOR FRAME BEECH 90 65A901 1152901CE PWA PT6 PT6A20 52043EA BS 255 CORRODED B EVGRK NONE O OTHER ININSP/MAINT 1 SO3365JA 13353173 LM34 CORROSION WAS FOUND AT THE AFT DOOR FRAME AT FUSELAGE STATION 255.5 JUST BELOW AND OUT BOARD OF THE DOOR SNUBBER MOUNT. DAMAGE WAS REPAIRED IAW SIRM PN 9839006C, DATED MARCH 2003, ATA 20-10-03 FIGURE 202, PAGES 204 AND 205 AND ATA 20-10-34, FIGURE 201, PAGES 201 AND 202. 1L72 3T3 T 3A20 E4EA 20060922000712006092200071EA 2006 9 22 EVGR20060915 220060913G7414103571651 COIL ROBSINR44 R44 7640120WP LYC O540 O540F1B5 41532EA MAGNETO WORN B EVGRK NONE O OTHER ININSP/MAINT 1 SO33628PM498 E04JA347 1493 L2642740A DURING THE FIRST 500 HOUR MAGNETO INSPECTION, THE TAB ON THE COIL WAS MISALIGNED AND EXHIBITED EXCESSIVE WEAR. 1G71 3O3 O H11NM E295 20060512000312006051200031GL 2006 5 12 EY2R0079965 320060421G6114E71693 HUB BEECH 58 58P 1152744CE HARTZLHCJ3Y PHCJ3YF2 GL PROPELLER CORRODED B EY2RK NONE O OTHER ININSP/MAINT 1 GL03 CORROSION ON PROPELLER HUB. 1L72 3O A23CE 5 CP36EA 20060718001772006071800177CE 2006 7 18 FAA0607001 120060627G531212534095 FIREWALL CESSNA210 210K 2073446CE CONT O550 IO550* SO MCAULYD3A34 D3A34C402 GL ZONE 100 CRACKED B K NONE P NO WARNING INDICATION ININSP/MAINT 1 SW178142G6980 21059442 289152R 931755 WHILE UNDERGOING AN ANNUAL INSPECTION THE ENGINE FIREWALL WAS FOUND TO BE CRACKED WHERE THE EXHAUST HANGER BRACKETS ATTACH ON THE LT SIDE. ADDITIONAL CRACKING WAS ALSO FOUND ON THE INNER BULKHEAD. 1H71 3O3 O 3A21 E3SO 5 CP47GL 20060718001782006071800178CE 2006 7 18 FAA0607002 120060627G531212534095 FIREWALL CESSNA210 210K 2073446CE CONT O550 IO550* SO MCAULYD3A34 D3A34C402 GL ZONE 100 CRACKED B K NONE O OTHER ININSP/MAINT 1 SW178142G6980 21059442 289152R 931755 WHILE UNDERGOING AN ANNUAL INSPECTION THE ENGINE FIREWALL WAS FOUND TO BE CRACKED WHERE THE EXHAUST HANGER BRACKETS ATTACH ON THE LT SIDE. ADDITIONAL CRACKING WAS ALSO FOUND ON THE INNER BULKHEAD. 1H71 3O3 O 3A21 E3SO 5 CP47GL 20070108003082007010800308CE 2007 1 8 FAA061214001 120061214G3230963800225 MOTOR BEECH 95 D95A 1153408CE LYC O360 IO360A1A 41514EA LAND GEAR SHORTED B A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CE038950U4094 164 TD641 LANDING GEAR MOTOR CIRCUIT BREAKER BLEW WHEN GEAR WAS RETRACTED ON TAKEOFF. AT THE SAME TIME THE ALTERNATORS DROPPED OFFLINE. PILOT SWITCHED TO THE OTHER VOLTAGE REGULATOR AND THE ALTERNATORS CAME BACK ONLINE. AIRCRAFT WAS FLOWN FOR AN HOUR OR MORE TO BURN OFF FUEL. PRIOR TO LANDING. AN EMERGENCY WAS DECLARED. PILOT WAS ABLE TO CRANK THE GEAR DOWN AND LAND WITHOUT INCIDENT. DISCOVERED THAT THE FIELD IN THE EXTEND SIDE OF THE LANDING GEAR MOTOR WAS SHORTED. REPLACED MOTOR WITH OVERHAULED EXCHANGE PART. FUNCTIONALLY CHECKED OK. 1L72 3O3 O 3A16 1E10 20061012000062006101200006CE 2006 10 12 FAA1012001 120061007G2800 FUEL CESSNA182 T182T 2072738CE UNKNOWN LEAKING P A UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CLCLIMB 1 SW996004S T18208508 AFTER AN APPROXIMATELY 30 MILE UNEVENTFUL FLIGHT WITH A LANDING AND TAXIBACK FOR DEPARTURE AT HVN THE AIRCRAFT WAS CLEARED FOR TAKEOFF BY THE TOWER. THERE WAS A FEW MINUTES OF HOLDING PRIOR TO BEING RELEASED. ON TAKEOFF FROM HVN RWY 2, THE AIRCRAFT FUNCTIONED NORMALLY UNTIL THE FIRST POWER REDUCTION AT 700 FEET AGL. THE THROTTLE, PROP AND MIXTURE CONTROLS WERE FULL FORWARD. THE PRIVATE PILOT ON BOARD PULLED THE THROTTLE BACK TO REDUCE THE TAKEOFF MANIFOLD PRESSURE FROM 32 TO 25 INCHES. DURING THIS REDUCTION, THE ENGINE LOST POWER, SURGED BRIEFLY AND LOST POWER AGAIN. THE THROTTLE APPEARED TO HAVE BEEN RETARDED SLOWLY AND CORRECTLY FOR THE EXPECTED POWER REDUCTION. THE THROTTLE WAS ADVANCED AND NO POWER B1H71 3O NT3A13 20061012000762006101200076 2006 10 12 FAA1012002 420060926G6113 BALANCE WEIGHT CESSNA177 177RG 2073709CE LYC O360 AEIO360A1B6 41514EA MCAULY2D34C B2D34C208 GL SPINNER TORN C A UNSCHED LANDING E VIBRATION/BUFFET CRCRUISE 1 WP27177SD10 10 177RG0997 PROPELLER WAS BALANCED IN PLACE. 10 FLIGHT HOURS LATER, IN CRUISE OVER WYOMING EN ROUTE TO OSHKOSH, SIGNIFICANT VIBRATION OCCURRED, CAUSING DIVERSION TO THE NEAREST AIRPORT. UPON LANDING, BYSTANDERS RAN TOWARD THE AIRPLANE TO EFFECT RESCUE, ASSUMING THE AIRPLANE TO BE ON FIRE FROM THE LARGE CLOUDS OF SMOKE. BALANCE WEIGHTS HAD BEEN ATTACHED BY SCREW RADIALLY INSIDE THE SPINNER BACKING PLATE. THE WEIGHTS (THREE WASHERS ON ONE SCREW) HAD PULLED THROUGH THE ALUMINUM OF THE BACKING PLATE, AND THE RESULTANT PROJECTION DAMAGED THE COWL MOUNT SYSTEM AND COWLING, AS WELL AS THE BACKING PLATE, AND SEPARATION OF THE BALANCE WEIGHTS. THE IMBALANCE CREATED BY THIS TEARING OF THE BACKING PLATE CAUSED SEVERE VIBRATION, 1H71 3O3 O A20CE 1E10 5 CP7EA 20061020000982006102000098SW 2006 10 20 FAA1020001 120060921G28233610021 SELECTOR VALVE MOONEYM20 M20R 5870225SW CONT O550 IO550G 17042SO HARTZLHCJ3Y PHCJ3YF1 GL COCKPIT STUCK D O OTHER O OTHER NRNOT REPORTED 1 EA07533LJ71 290443 688726 FP4606B FUEL SELECTOR VALVE STUCK IN (OFF) POSITION WHILE AIRCRAFT WAS SITTING ON THE RAMP. ONCE STUCK IN THE OFF POSITION, IT BECAME IMPOSSIBLE TO TURN USING HAND FORCE. (K) 1L71 3O3 ORT2A3 E3SO 5 CP36EA 20061025000872006102500087EA 2006 10 25 FAA1023001 220061013G8520 EXHAUST VALVE PIPER PA28 PA28140 7102802SO LYC O320 O320* 41508EA ENGINE SEPARATED D A UNSCHED LANDING Y ENGINE STOPPAGE CRCRUISE 1 CE075292S 2826923 PILOT REPORTED ENGINE VIBRATION FOLLOWED BY PROGRESSING LOSS OF POWER WHICH EVENTUALLY LED TO COMPLETE LOSS OF POWER AND ENGINE FAILURE. PILOT EXECUTED AN UNEVENTFUL EMERGENCY LANDING ON A PAVED STATE HIGHWAY. NO DAMAGE TO AIRCRAFT UPON LANDING. RESULTS OF ENGINE EXAMINATION AND PARTICULAR PART FAILURE INFORMATION TO FOLLOW: 1L71 3O3 O 2A13 E274 20061031001442006103100144NM 2006 10 31 FAA1031001 120061027G5522 SKIN ISRAEL1125 1125 NM ALIDSGTFE731TFE7313AR WP ELEVATOR DELAMINATED B G7QRK NONE O OTHER ININSP/MAINT 1 WP0771FS 4861 071 DEBOND AREA APPROX. 7 IN X 7 IN ON THE RT OB ELEVATOR LOWER COMPOSITE SKIN. ELEVATOR WAS SENT TO MFG FOR EVALUATION AND WAS DEEMED (BEYOND ECONOMICAL REPAIR). A LOANER UNIT WAS INSTALLED WHILE NEW/EXCHANGE UNIT PREPARED. REPLACEMENT ELEVATOR INSTALLED ON THIS DATE. 2L72 4F4 FRTA16NM E6WE 20060821000822006082100082 2006 8 21 FAA200608001 120060609G32440398561 TIRE MLG SEPARATED B C ABORTED TAKEOFF S AFFECT SYSTEMS TOTAKEOFF 1 SO250874 LOUD BANG REPORTED BY PILOTS RESULTING IN REJECTED TAKE-OFF. MAINT FOUND DAMAGE TO ENGINE FROM TIRE. SHOP INVESTIGATION REVEALED, TIRE TREAD SEPARATED FROM CARCASS. NO LEAKAGE FROM WHEEL. PASSED AIR RETENTION AFTER 167 HOURS WITH ACCEPTABLE AIR LOSS FROM WHEEL SERIAL NUMBER 01466. CAUSE IS UNDETERMINED TO WHY TREAD SEPARATED, TIRE TO BE SENT TO MICHELIN FOR TIRE INVESTIGATION. 20061207002452006120700245SO 2006 12 7 FAA200612001 220061206G8530 CYLINDER CESSNA421 421C 2076016CE CONT O520 GTSIO520L 17032SO SEPARATED B C ABORTED TAKEOFF RJ PARTIAL RPM/PWR LOSS WARNING INDICATION TOTAKEOFF 1 WP2393PJ 554 421C0824 245999R DURING TAKEOFF ROLL PILOT REPORTED A LOUD POP FROM THE LEFT ENGINE AND THE AIRCRAFT YAWED TO THE LEFT. THE TAKEOFF WAS ABORTED. VISUAL INSPECTION REVEALED THE NUMBER SIX CYLINDER HEAD HAD SEPARATED FROM THE BARREL. THE ENGINE HAD 554 HOURS SINCE OVERHAUL. THIS ENGINE WAS INSTALLED ON A CESSNA 421C. 1L72 3O3 O A7CE E7CE 20061012000132006101200013 2006 10 12 FAA63837 420061003G6113D78115P SPINNER HARTZLHCJ3Y PHCJ3YF2 GL PROPELLER CRACKED B O OTHER O OTHER NRNOT REPORTED 1 GL2558HW 102 ED4696B RT PROPELLER SPINNER CRACKED. CRACKS ORIGINATE FROM 1ST SCREW HOLE ADJACENT TO BLADE OPENING. THIS IS THE 2RD OCCURANCE OF THIS DEFECT. PROBABLE CAUSE UNKNOWN. 5 CP36EA 20060926000442006092600044GL 2006 9 26 FASD0601 120060904G5210 ROLLER BOMBDRBD700 BD7001A10 1390006GL PAX DOOR OUT OF ADJUST B A UNSCHED LANDING O OTHER CLCLIMB 1 GL15889CP 9104 AFTER TAKE-OFF AIRCRAFT CABIN WOULD NOT PRESSURIZE. AIRCRAFT RETURNED TO AIRPORT WITHOUT INCIDENT. INVESTIGATION BY GROUND CREW FOUND REAR BAGGAGE DOOR MISALIGNED AND AFT ROLLER OUT OF GUIDE TRACK AND REAR LOCKING PIN NOT FULLY ENGAGED, ALL INDICATIONS IN THE COCKPIT WERE NORMAL AS SENSORS ARE FITTED TO FRONT PIN AND DOOR LOCKING MECHANISM ONLY. DOOR WAS RE-FITTED INTO THE TRACK CORRECTLY, DOOR SECURED CLOSED NORMALY, AIRCRAFT DEPARTED AND FLIGHT CONTINUED WITHOUT INCIDENT. 2L72 4F RTT00003NY 20070108001712007010800171NE 2007 1 8 FCPR20060026 220061213G720065526022 RING CESSNA500 560CESSNA 2076750CE PWA 530 PW535A NE RT ENGINE CRACKED B FCPRK NONE O OTHER ININSP/MAINT 1 NM09591DK940 300 5600591 RT ENGINE INLET SUPPORT RING CRACKED. 2L72 4F4 FRTA22CE E00053EN 20070108002172007010800217CE 2007 1 8 FCPR20060027 120061215G3830105881 HEATER CESSNA525 525A 2076615CE WILINTFJ44 FJ44 66000GL ZONE 100 BURNED B FCPRO OTHER A FLAME/FIRE TXTAXI/GRND HDL 1 NM09523BT1247 300 525A0124 AFT TOILET RELIEF TUBE HEATER ELEMENT FAILED WITH EXTERNAL POWER APPLIED BURSTING INTO FLAMES. IPC REFERENCE 38-30-00 FIG 3 ITEM 16. 1L71 4F4 FRTA1WI E3GL 20060829001332006082900133CE 2006 8 29 FCPR20060030 120060822G79311013890237 TRANSMITTER BEECH 300 300BEECH 1152930CE LT ENGINE FAILED B FCPRE ENGINE SHUTDOWN N FALSE WARNING CRCRUISE 1 NM09528AM4273 FA59 LT ENGINE OIL PRESSURE TRANSMITTER FAILED, GIVING A LOW OIL PRESSURE INDICATION. 2L72 4T A24CE 20060510002372006051000237 2006 5 10 FCPR20060050 420060509G22114008519 COMPUTER CESSNA500 S550 2076607CE COCKPIT FAILED B FCPRO OTHER S AFFECT SYSTEMS NRNOT REPORTED 1 NM09543SC6347 S5500144 AUTOPILOT COMPUTER FAILED CAUSING PILOTS ALTIMETER/AIRDATA COMPUTER TO FAIL. 1L72 4F RTA22CE 20060511002902006051100290CE 2006 5 11 HAG06002 120060406G531325FN86 LONGERON RAYTHNDH125 DH125 4230106CE FUSELAGE CRACKED B J7EAK NONE O OTHER ININSP/MAINT 1 NM03125CK10555 25266 CRACK IN KEEL LONGERON BETWEEN FRAMES 4 AND 5, APROXIMATE STATION 175.00.CRACK IS ONLY IN LONGERON, NOT IN MAIN BEAM. CRACK LOCATED IN LOWER AFT HOLE FOR NOSE GEAR ATTACH BRACKET. DISCOVERED DURING REQUIRED CHECK OF ATTACH BOLT TORQUE, ALL BOLTS FOUND LOOSE. BRACKET REMOVED FOR HIDDEN DAMAGE INSPECTION. 2L72 4J RTA3EU 20061117001392006111700139NE 2006 11 17 HL01102006001 120061031G6320SB24102 BEARING SKRSKY SKRSKYS64 CH54A 8142501NE M/R GEARBOX FAILED C O OTHER O OTHER NRNOT REPORTED 1 WP23 357 77 6818447 MAIN GEAR BOX BEGAN MAKING METAL, THIS WAS NONFERROUS METAL, UPON REMOVAL AND DISASSEMBLY IT WAS DISCOVERED THAT THE 1ST STAGE PLANETARY BEARING, P/NSB2410-2 HAD FAILED, BEARING WAS REPLACED AND RETURNED TO SERVICE. FOR FURTHER INFO SEE HEAVY LIFT WORK ORDER NR. 2G72 4U H16NM 20070108001462007010800146 2007 1 8 HN8R200600001 420061207G2200065001782400 SERVO GIPPLDGA8 GA8 3900102EU LYC O540 IO540K1A5 41532EA AUTOPILOT DEFECTIVE B HN8RC ABORTED TAKEOFF O OTHER TOTAKEOFF 1 CE05576GA1 1 05076 NOSE DOWN AUTO TRIM INOP WAS REPORTED BY PILOT. TROUBLESHOOTING REVEALED THE AUTOPILOT COMPUTER WAS NOT RECEIVING INPUT CALLING FOR NOSE DOWN TRIM FROM THIS PITCH SERVO. 1H71 3O3 ONT 1E4 20070108002212007010800221EA 2007 1 8 HN8R200700001 220061223G8550 SCREEN GIPPLDGA8 GA8 3900102EU LYC O540 IO540K1A5 41532EA ENGINE OIL SUMP CONTAMINATED B HN8RK NONE J WARNING INDICATION ININSP/MAINT 1 CE05576GA219 GA805076 L3033548A FOUND 2 PIECES OF METAL IN THE OIL SUMP SUCTION SCREEN DURING ANNUAL INSPECTION. ONE PIECE LOOKS LIKE A DRILLED OUT HELI COIL .5 INCH LONG X .25 WIDE AND THE OTHER LOOKS LIKE A PIECE OF CASTING .2 LONG X .125 WIDE. THE ENGINE WILL BE REMOVED AND SENT OUT FOR TEARDOWN AND INSPECTION. 1H71 3O3 ONT 1E4 20061115002122006111500212CE 2006 11 15 IALFAASDR1 120061103G2430 WIRE HARNESS BEECH 58 58 1152740CE CONT O520 IO520* 17032SO AIR DRIVEN GEN BROKEN H K NONE G MULTIPLE FAILURE ININSP/MAINT 1 SO05302P TH952 AIR DRIVEN GENERATOR TEST IN FLIGHT, FOUND NO OUTPUT. FOUND WIRING HARNESS FROM ADG TO ADG BUSS BURNED-BROKEN AT CONNECTOR BACKSHELL. CONNECTOR AND WIRING REPLACED ADG INSPECTED AND TESTED SERVICEABLE. 1L72 3O3 O 3A16 E5CE 20060512000792006051200079CE 2006 5 12 IGL032006007 120060329G3222084200077 STRUT CESSNA CESSNA310 310K 2074228CE CONT O470 IO470* 17026SO NLG FAILED G A UNSCHED LANDING K FLUID LOSS LDLANDING 1 GL037035L 310K0135 NOSE GEAR STRUT ASSEMBLY COLLAPSED DURING EITHER TAXI OR TAKEOFF. WHEN GEAR WAS RETRACTED THE NOSE FENDER CAUGHT ON THE GEAR DOOR BRACKETS. MOTOR CONTINUED UNTIL IDLER BELLCRANK BROKE. AIRCRAFT MADE AN EMERGENCY LANDING WITH THE NOSE GEAR COLLAPSED. PILOT REPORTED NO ABNORMAL OBSERVATIONS OF THE NOSE GEAR DURING PREFLIGHT INSPECTION. IT IS NOT UNCOMMON FOR THE STRUT TO BLOW THE SEALS AND LOOSE ALL OF ITS FLUID AND NITROGEN DURING COLD WEATHER. LOW UTILIZATION MIGHT HAVE BEEN A CONTRIBUTING FACTOR AS WELL. 1L72 3O3 O 3A10 E1CE 20060411000312006041100031CE 2006 4 11 ISW1520050019 120060223G8000643359K46 ADAPTER CESSNA421 421C 2076016CE CONT O520 GTSIO520N 17032SO STARTER FAILED G O OTHER Y ENGINE STOPPAGE CRCRUISE 1 SW15421LH714 421C1207 808393 THE ENGINE QUIT RUNNING AND SEIZED DURING FLIGHT. THE STARTER ADAPTER FAILED AND CAUSED THE ENGINE TO SEIZE. MAINTENANCE RECORDS SHOW THAT THE STARTER WAS REPLACED TWO TIMES BECAUSE OF HARD STARTING. ONCE AT 99 HOURS AND AGAIN AT 90 HOURS PRIOR TO ENGINE FAILURE 1L72 3O3 O A7CE E7CE 20070109000012007010900001CE 2007 1 9 JEMA11302006A 120061130G5610991438010 WINDSHIELD CESSNA500 560CESSNA 2076750CE PWA 545 PW545A NE COCKPIT CRACKED G JEMAA UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 CE01108EK2662 5605032 AIRCRAFT HAD DEPARTED, HAD LEVELED OFF AT 37,000 FEET, ENROUTE. CREW NOTICED A RT WINDSHIELD FAULT WARNING LIGHT. IAW AFM PROCEDURES RT WINDSHIELD HEAT WAS TURNED OFF. APPROX 3-4 MINUTES LATER CO-PILOT SAW FLASH AND RT WINDSHIELD SPIDER WED CRACKED. FLIGHT CREW MADE A PRECAUTIONARY LANDING AT AIRPORT, WITH NO FURTHER INCIDENTS. 2L72 4F4 FRTA22CE E00059EN 20060718001642006071800164CE 2006 7 18 LJCR2453796 120060301G302045A403041 DUCT BEECH MU300 400A 1155402CE OUT OF LIMITS B LJCRK NONE O OTHER ININSP/MAINT 1 SW09999JF RK98 DURING SCHEDULED MAINTENANCE, FOUND BRAIDING AROUND FLEXIBLE BELLOWS DISBONDED FROM ENTIRE CIRCUMFERENCE. NEW REPLACEMENT DUCT ASSEMBLIES NOT AVAILABLE FROM MANUFACTURER. REPLACED WITH SERVICEABLE UNIT. INSPECTED REPLACEMENT UNIT PER AD 2001-03-06 EFF. 3-21-2001 2H72 4F RTA16SW 20061117001592006111700159GL 2006 11 17 LX5R200600002 320061115G6197K31C22 WIRE HARNESS BEECH BEECH B300 B300 1159232CE PWA PT6 PT6A60A 52043NE HARTZLHCB4M HCB4MP3 GL AUTOFEATHER SYS SHORTED C LX5RC ABORTED TAKEOFF J WARNING INDICATION TOTAKEOFF 1 GL19961LL3310 FL264 UPON TAKEOFF ROLL THE CREW GOT THE AUTOFEATHER OFF LIGHT AND THE MASTER CAUTION LIGHT. THE CREW THEN OPTED TO ABORT TAKEOFF ROLL AND RETURN TO RAMP WITHOUT INCIDENT. UPON RETURNING TO RAMP THE CREW NOTICED THAT THE AUTOFEATHER CIRCUIT BREAKER HAD POPPED, IT WAS RESET BUT WOULD POP AGAIN UPON PUSHING THE LT POWER LEVER FORWARD. THE PLANE WAS BROUGHT INTO MAINTENANCE AND THE MECHANIC FOUND THAT THERE WAS A CHAFED WIRE BEHIND THE INSTRUMENT PANEL FOR THE AUTOFEATHER SWITCH. THIS WIRE WAS REPAIRED AND THE AIRCRAFT WAS OPS CHECKED AND RETURNED TO SERVICE. 2L72 4T4 TRTA24CE E4EA 6 CP56GL 20061212003982006121200398 2006 12 12 LX5R200600003 320061115G6197K31C22 WIRE HARNESS BEECH B300 B300 1159232CE PWA PT6 PT6A60A 52043NE COCKPIT SHORTED B LX5RC ABORTED TAKEOFF J WARNING INDICATION TOTAKEOFF 1 GL19961LL3310 FL264 UPON TAKEOFF ROLL, THE CREW GOT THE AUTO FEATHER OFF LIGHT AND THE MASTER CAUTION LIGHT. THE CREW THEN OPTED TO ABORT TAKEOFF ROLL AND RETURN TO RAMP WITHOUT INCIDENT. UPON RETURNING TO RAMP, THE CREW NOTICED THAT THE AUTO FEATHER CRICUIT BREAKER HAD POPPED, IT WAS RESET BUT WOULD POP AGAIN UPON PUSHING THE LT POWER LEVER FWD. THE PLANE WAS BROUGHT INTO MAINTENANCE AND THE MECHANIC FOUND THAT THERE WAS A CHAFED WIRE BEHIND THE INSTRUMENT PANEL FOR THE AUTOFEATHER SWITCH. THIS WIRE WAS REPAIRED AND THE AIRCRAFT WAS OPS CHECKED AND RETURNED TO SERVICE. (K) 2L72 4T4 TRTA24CE E4EA 20060518001722006051800172SO 2006 5 18 MPVMANIFOLD 220060328G732463432612A2 FUEL DIVIDER CESSNA206 TU206G 2073357CE CONT O520 TSIO520M 17040SO ENGINE LEAKING D K NONE K FLUID LOSS ININSP/MAINT 1 WP21PKMPV98 U20605864 532289 FUEL MANIFOLD VALVE IS LEAKING FROM THE VENT PORT. 1H71 3O3 O A4CE E8CE 20060530001562006053000156CE 2006 5 30 N6265B 120060524G5312125340956 BULKHEAD CESSNA CESSNA210 210M 2073450CE FIREWALL CRACKED B K NONE O OTHER ININSP/MAINT 1 SW176265B4908 21062727 WHILE UNDERGOING AN ANNUAL INSPECTION, FOUND THE FIREWALL TO BE CRACKED ON THE LT & RT SIDE WHERE THE P/N 1250255-7 EXHAUST HANGAR BRACKETS ATTACH. THE CRACKS WERE EXTENDING OUT FROM UNDER THE HANGAR BRACKETS AND EXTENDED IN MULTIPLE DIRECTIONS. ADDITIONAL INSPECTION REVEALED THE LT BULKHEAD P/N 1253409-5 AND RT BULKHEAD P/N 1253409-6 BEHIND THE FIREWALL TO BE CRACKED IN MULTIPLE DIRECTIONS ALSO. THE BULKHEAD SECTIONS WERE REPLACED AND THE FIREWALL CRACKS WERE REPAIRED. 1H71 3O 3A21 20060718001762006071800176CE 2006 7 18 N8142G 120060627G531212534095 FIREWALL CESSNA210 210K 2073446CE CONT O550 IO550* SO MCAULYD3A34 D3A34C402 GL FUSLEAGE CRACKED D K NONE O OTHER ININSP/MAINT 1 SW178142G6980 21059442 289152R 931755 WHILE UNDERGOING AN ANNUAL INSPECTION THE ENGINE FIREWALL WAS FOUND TO BE CRACKED WHERE THE EXHAUST HANGER BRACKETS ATTACH ON THE LT SIDE. ADDITIONAL CRACKING WAS ALSO FOUND ON THE INNER BULKHEAD. 1H71 3O3 O 3A21 E3SO 5 CP47GL 20060914001622006091400162CE 2006 9 14 NA 120060822G52803511513022 ANGLE BEECH 36 A36 1151604CE MLG DOOR CRACKED C K NONE O OTHER ININSP/MAINT 1 GL19 360 E3384 DURING A ROUTINE ANNUAL INSPECTION IT WAS FOUND THAT BOTH THE LT AND RT IB GEAR DOOR AFT HINGE ANGLES (P/N'S 35-115130-22, -24, 35-115070-16 AND -18 WERE CRACKED. IT IS MY OPINION THAT THIS IS DUE TO THE FACT THAT MFG HAS CHANGED THE DESIGN OF THE IB GEAR DOOR FROM A STAMPED ASSY TO A MILLED PART. THIS CONDITION OBVIOUSLY IS PRESENT IN OTHER LIKE MODELS AND MFG HAS ACKNOWLEDGED THE PROBLEM IN THEIR PARTS BOOK AS THEY GIVE INSTRUCTIONS FOR ORDERING DIFFERENT PN. THE NEW PN PARTS ARE MADE FROM .050 INCH ALUMINUM WHILE THE ORIGINAL PARTS WERE MADE FROM .032 INCH ALUMINUM. THE CRACKS COULD EASILY GO UNDETECTED AND A SB IS NEEDED TO HELP OTHERS FIND AND ELIMINATE THESE CRACKS. 1L71 3O 3A15 20060518001352006051800135CE 2006 5 18 OMKR200600002 120060509G551145A21104642 RIB BEECH MU300 400A 1155402CE ZONE 300 CRACKED B OMKRK NONE O OTHER ININSP/MAINT 1 NM03899TA4933 RK292 CRACKED ROLLER RIB ASSEMBLY. 2H72 4F RTA16SW 20060516000902006051600090CE 2006 5 16 OMKR200600003 120060510G551445A21104641 RIB BEECH MU300 400A 1155402CE HORIZ STAB CRACKED B OMKRK NONE O OTHER ININSP/MAINT 1 NM03686TA 686TA CRACKED ROLLER RIB SUPPORT. 2H72 4F RTA16SW 20060718000972006071800097CE 2006 7 18 OMKR20064 120060712G57405012007378 FITTING BEECH 90 65A90 1152908CE WING SPAR CRACKED B OMKRK NONE O OTHER ININSP/MAINT 1 NM0366GS 11099 LJ237 DURING ACCOMPLISHMENT OF AD 89-25-10, BOTH THE FOREWARD, LOWER, INBOARD, BATHTUB FITTINGS WERE FOUND WITH TWO EACH 1/4" CRACKS. THE FEATHERED EDGE CRACKS EXTENDED INTO THE BOLT HOLE RADIUS, AND THE SLOT CRACKS EXTENDED UPWARD. BOTH FITTINGS WERE CRACKED VIRTUALLY THE SAME. PARTS WERE REPLACED WITH NEW. 1L72 3T 3A20 20060510002422006051000242CE 2006 5 10 PAI5200604049 120060417G32427540 PLATE CLEVELAND BEECH 95 95B55 1152729CE RT BRAKE CRACKED B PAI5K NONE O OTHER ININSP/MAINT 1 SO056747V3103 TC2316 DURING ANNUAL INSPECTION FOUND RT BRAKE TORQUE PLATE CRACKED .7500 OF THE LENGTH OF THE CALIPER PIN BORE. 1L72 3O RT3A16 20060721001402006072100140EU 2006 7 21 PAI5200641881 120060628G554080363216801 STOP PIAGIOP180 P180 6960204EU RUDDER BROKEN B PAI5K NONE O OTHER ININSP/MAINT 1 SO05153SL2966 1054 DURING D CHECK (3000 HOUR INSPECTION) FOUND RUDDER STOP LOCATED AT BOTTOM OF RUDDER BROKEN IN TWO. BREAK OCCURRED AT SCREW HOLES USED TO ATTACH WEAR STRIP TO RUDDER STOP. SMALL AREA OF METAL EXISTS AROUND THE SCREW HOLES, SUGGEST REDESIGN OF THIS PART. 1H72 3O RTA59EU 20060926000272006092600027NE 2006 9 26 PAI5200642401 220060825G72613040124 LINE PIAGIOP180 P180 6960204EU PWA PT6 PT6A66 52043NE OIL COOLER CHAFED B PAI5K NONE K FLUID LOSS ININSP/MAINT 1 SO05153SL2989 1054 PCERK0064 DURING 3000 HOUR D-CHECK FOUND OIL SCAVENGE LINE PN 3040124 AT SCAVENGE PUMP CHAFED APPROX 50 PERCENT THROUGH BY CONTACT WITH CRIMP TYPE CLAMP THAT SECURES HEAT SLEEVE ON OIL COOLER FLEX LINE. SAME CONDITION FOUND ON BOTH LT AND RT ENGINES. INSTALLED NEW SCAVENGE LINE BOTH ENGINES. 1H72 3O4 TRTA59EU E26NE 20060913001032006091300103EU 2006 9 13 PAI5200642731 120060901G301080232118401 DUCT PIAGIO PIAGIOP180 P180 6960204EU WING CRACKED B PAI5K NONE O OTHER ININSP/MAINT 1 SO05107SL2993 1073 DURING 3000 HOUR D-CHECK FOUND ALL 4 WING LEADING EDGE PANELS WITH CRACKED HEATING DUCTS. WING LEADING EDGE ASSY P/N'S 80-232116-401, 80-232116-402, 232117-401, 232117-402. 1H72 3O RTA59EU 20060627003312006062700331EU 2006 6 27 PAI52006S4188 120060622G301080237666403A TUBE PIAGIOP180 P180 6960204EU ANTI ICE SYS CHAFED B PAI5K NONE O OTHER ININSP/MAINT 1 SO05153SL2966 2966 1054 DURING D-CHECK (3000 HOUR INSPECTION) FOUND WING LEADING EDGE ANTI-ICE PLUMBING CHAFFED 50 PERCENT OF WALL THICKNESS BY LEADING EDGE TEMP SENSOR BRACKET. 1H72 3O RTA59EU 20060802003062006080200306SO 2006 8 2 PAI52006S4248 120060726G2823 CONTROL CABLE PIPER PA23 PA23250 7102308SO FUEL SELECTOR BROKEN B PAI5A UNSCHED LANDING X ENGINE FLAMEOUT CRCRUISE 1 SO0518MW 27369 PILOT REPORTED LT ENGINE QUIT IN FLIGHT. FOUND LT OB FUEL TANK EMPTY, LT IB FUEL TANK HAD FUEL. FOUND FUEL SELECTOR CONTROL CABLE BROKEN AT SELECTOR VALVE IN LT NACELLE. WHEN SELECTED TO LT IB TANK THE ENGINE RAN NORMALLY. 1L72 3O 1A10 20061031001632006103100163CE 2006 10 31 PAI52006S4330 120061025G3246300257 WHEEL BEECH 90 C90A 1152911CE MLG CRACKED B PAI5K NONE O OTHER ININSP/MAINT 1 SO05511KV3500 LJ1422 PILOT NOTED RT MAIN TIRE LOW PRESSURE ON PREFLIGHT. MAINTENANCE FOUND, UPON DISASSEMBLY OF WHEEL, THAT THE INNER WHEEL HALF WAS CRACKED IN THE O-RING GROOVE ADJACENT TO THE WHEEL TIE BOLT HOLES. 1L72 3T RT3A20 20060518001862006051800186EU 2006 5 18 PAZR200620412 120060428G3211MY201121605 PLUG AMD AMD FALC20FALCON20F5 2730105EU ZONE 700 CORRODED B PAZRK NONE O OTHER ININSP/MAINT 1 CE03620A 412 DURING THE COURSE OF REPLACING THE LT MLG ASSEMBLY, THE TECHNICIAN, UPON VISUAL INSPECTION AFTER REMOVAL OF MLG ASSY, FOUND SIGNS OF CORROSION ON THE PLUG, P/N MY20112-1605. UPON FURTHER DISASSEMBLY, IT WAS NOTED THAT THE CORROSION HAD GONE THROUGH THE PLUG. THE SEALANT ON ONE SIDE OF THE PLUG WAS PREVENTING FUEL LEAKAGE. PART WAS ORDERED FROM MFG AND REPLACED WITH A NEW PLUG, P/N MY20112-1605-1. IT APPEARS THAT THE NEW PLUG HAS A DIFFERENT DESIGN AND PAINT PROTECTION SYSTEM; THUS AIDING IN THE PREVENTION OF FUTURE CORROSION. THE AIRCRAFT WAS MFG. IN 1979. 2L72 4F RTA7EU 20060630000212006063000021NM 2006 6 30 PIDR2006001 120060608G5551 ATTACH FITTING BOEING737 73735B 13844BMNM HORIZ STAB DAMAGED B K NONE O OTHER ININSP/MAINT 1 SO05223DZ 23972 DURING AN A-CHECK/BRIDGING CHECK FOR RETURN TO SERVICE FROM STORAGE, MAINTENANCE DISCOVERED A TIME LIMITED BLENDOUT REPAIR TO THE AFT FACE OF THE LEFT HORIZONTAL STABILIZER LOWER FORWARD ATTACH LUG. REWORKED AFT FACE OF LOWER FORWARD ATTACH LUG PER DELTA ENGINEERING REPAIR/AUTHORIZATION 089066-14 REVISION D DATED 5/10/06 WITH FAA 8100-9 APPROVAL DATED 5/30/2006. 2L72 4F RTA16WE 20060711000652006071100065NM 2006 7 11 PIDR2006002 120060608G5753 SKIN BOEING737 73735B 13844BMNM TR FLAPS CHAFED B K NONE O OTHER ININSP/MAINT 1 SO05223DZ 23972 INSPECTION NOTED A CHAFED AREA ON AN EXISTING SRM ALUMINUM REPAIR DOUBLER ON THE RIGHT WING OUTBOARD FLAP MID-FLAP LEADING EDGE 20 INCHES FROM THE INBOARD END. REPAIRED DAMAGED AREA IN ACCORDANCE WITH PACE AIRLINES REPAIR PROCEDURE REPORT EA 57-145 DATED 05/25/06 WITH FAA DER APPROVAL FORM 8110-3 DATED MAY 30, 2006. 2L72 4F RTA16WE 20060705000242006070500024NM 2006 7 5 PIDR2006003 120060608G5330 SKIN BOEING737 73735B 13844BMNM FUSELAGE DAMAGED B K NONE O OTHER ININSP/MAINT 1 SO05223DZ 23972 AN EXISTING REPAIR TO THE FUSELAGE SKIN BETWEEN THE L1 DOOR HINGES JUST FORWARD OF THE DOOR REQUIRES REWORK TO REMOVE THE DAMAGE. REWORKED DAMAGED AREA IAW EA NR 53-146 DATED 05/26/06 WITH FAA DER APPROVED 8110-3 DATED MAY 27, 2006.. 2L72 4F RTA16WE 20060711000642006071100064NM 2006 7 11 PIDR2006004 120060608G5754 SKIN BOEING737 73735B 13844BMNM NR 5 SLAT CRACKED B K NONE O OTHER ININSP/MAINT 1 SO05223DZ 23972 INSPECTION NOTED A GOUGE ON THE NR 5 SLAT UPPER LEADING EDGE SURFACE 28 INCHES FROM THE INBOARD END (SS169.0). REPAIRED DAMAGED AREA IN ACCORDANCE WITH PACE AIRLINES REPAIR PROCEDURE REPORT EA 57-140 DATED 05/20/06 WITH FAA DER APPROVED 8110-3 DATED MAY 20, 2006. 2L72 4F RTA16WE 20060711000632006071100063NM 2006 7 11 PIDR2006005 120060608G5754 SKIN BOEING737 73735B 13844BMNM NR 5 SLAT CRACKED B K NONE O OTHER ININSP/MAINT 1 SO05223DZ 23972 INSPECTION NOTED CRACKS AT SEVERAL FASTENER LOCATIONS IN THE NR 5 SLAT LOWER TRAILING EDGE SKIN PANEL UNDER THE SLAT ACTUATOR. REPAIRED DAMAGED AREA IN ACCORDANCE WITH SRM 57-43-01. 2L72 4F RTA16WE 20060711000622006071100062NM 2006 7 11 PIDR2006006 120060608G5754 SKIN BOEING737 73735B 13844BMNM NR 3 SLAT CRACKED B K NONE O OTHER ININSP/MAINT 1 SO05223DZ 23972 INSPECTION NOTED SEVERAL CRACKS IN THE NR 3 SLAT LOWER TRAILING EDGE SKIN BELOW THE SLAT ACTUATOR. REPAIRED DAMAGED AREA PER SRM 57-43-01. 2L72 4F RTA16WE 20060627003332006062700333NM 2006 6 27 PIDR2006007 120060619G5330 SKIN BOEING737 7373L9 1384470NM BS 887-907 DENTED B K NONE O OTHER ININSP/MAINT 1 SO05231DN 23717 DURING A-CHECK/BRIDGING CHECK FOR RETURN TO SERVICE FROM STORAGE, INSPECTION NOTED DENTS BEYOND ALLOWABLE LIMITS IN FUSELAGE SKIN FROM BS887 TO BS907 BETWEEN STR20RT AND STR22RT. REPAIRED IAW SRM 53-00-01. 2L72 4F RTA16WE 20060630000192006063000019NM 2006 6 30 PIDR2006008 120060613G5330 SKIN BOEING737 7373L9 1384470NM FUSELAGE DENTED B K NONE O OTHER ININSP/MAINT 1 SO05231DN 23717 DURING A-CHECK/BRIDGING CHECK FOR RETURN TO SERVICE FROM STORAGE, INSPECTION NOTED A DENT IN THE FUSELAGE SKIN BEYOND ALLOWABLE LIMITS AT BS 887 STR 22 LT. REPAIRED PER SRM 53-00-01. 2L72 4F RTA16WE 20060630000202006063000020NM 2006 6 30 PIDR2006009 120060606G5512 SKIN BOEING737 7373L9 1384470NM HORIZ STAB DAMAGED B K NONE O OTHER ININSP/MAINT 1 SO05231DN 23717 DURING A-CHECK/BRIDGING CHECK FOR RETURN TO SERVICE FROM STORAGE, DAMAGE NOTED ON THE RIGHT HORIZONTAL STABILIZER APPROXIMATELY 8 FEET FROM THE INBOARD END. REPAIRED PER SRM 55-10-01. 2L72 4F RTA16WE 20060724000182006072400018NM 2006 7 24 PIDR2006010 120060717G5300 REPAIR BOEING737 737330 13844BJNM FUSELAGE IMPROPER B K NONE O OTHER ININSP/MAINT 1 SO05241DL 23833 EXISTING REPAIR AT BS887 AND STR25RT NOT IN COMPLIANCE WITH THE SRM. REPLACED EXISTING REPAIR IAW SRM 53-00-01 REPAIR 31. 2L72 4F RTA16WE 20060831000922006083100092NM 2006 8 31 PIDR2006011 120060824G5754 SKIN BOEING737 737330 13844BJNM L/E SLAT CRACKED B K NONE O OTHER ININSP/MAINT 1 SO05242DL 23834 NUMBER THREE SLAT LOWER SKIN IS CRACKED AT THE ACTUATOR. REPAIRED PER SRM 57-43-01. 2L72 4F RTA16WE 20060831000902006083100090NM 2006 8 31 PIDR2006012 120060826G5330 SKIN BOEING737 737330 13844BJNM FUSELAGE DENTED B K NONE O OTHER ININSP/MAINT 1 SO05242DL 23834 FUSELAGE SKIN DENTED FROM BS 867 TO BS 947 BETWEEN STR 21 RT AND 22 RT. REPAIRED PER EA 53-220. 2L72 4F RTA16WE 20060831000892006083100089NM 2006 8 31 PIDR2006013 120060826G5313 STRINGER BOEING737 737330 13844BJNM FUSELAGE DAMAGED B K NONE O OTHER ININSP/MAINT 1 SO05242DL 23834 STRINGER 19 LT AT BS 967 HAS TWO REPAIRS NOT PER THE SRM. REPLACED SECTION OF STRINGER PER SRM 53-00-03 FIG 201, REPAIR 1 AND 51-40-2. 2L72 4F RTA16WE 20060831000912006083100091NM 2006 8 31 PIDR2006014 120060824G5320 STRUCTURE BOEING737 737330 13844BJNM FUSELAGE DAMAGED B K NONE O OTHER ININSP/MAINT 1 SO05242DL 23834 DOUBLER UNDER THE L-2 DOOR AT BS 975 HAS NO DOCUMENTATION. REPLACED EXISTING DOUBLER PER EA 53-221. 2L72 4F RTA16WE 20060913002392006091300239NM 2006 9 13 PIDR2006015 120060823G5711 SPAR BOEING737 737330 13844BJNM WING DAMAGED B PIDRK NONE O OTHER ININSP/MAINT 1 SO05242DL 23834 DURING REPLACEMENT OF THE AFT OB SUPPORT FITTING FOR THE MAIN LANDING GEAR BEAM IAW SB 737-1216R2 PART III, NOTED SEVERAL ATTACHMENT HOLES IN SPAR CHORD AND WEB TO BE OUT OF ROUND. REPAIRED DAMAGE IAW MFG MESSAGE NR 1-21375291-12 DATED 26 JULY 2006 AND FAA FORM 8100-9 DATED 7 AUG 2006 AS AN AMOC TO AD 2005-18-08. 2L72 4F RTA16WE 20060913002382006091300238NM 2006 9 13 PIDR2006016 120060823G574365C365451 FITTING BOEING737 737330 13844BJNM MLG ELONGATED B PIDRK NONE O OTHER ININSP/MAINT 1 SO05242DL 23834 DURING REPLACEMENT OF THE AFT OB SUPPORT FITTING FOR THE MAIN LANDING GEAR BEAM IAW SB 737-1216R2, PART III, NOTED SEVERAL ATTACHMENT HOLES IN THE REPLACEMENT FITTING OUT OF ROUND. REPAIRED DAMAGE AREA IN FITTING IAW MESSAGE NUMBER 1-213752921-12 DATED 26 JUL 2006 AND FAA FORM 8100-9 DATED 7 AUG 2006 WHICH IS AN AMOC TO AD 2005-18-08. 2L72 4F RTA16WE 20060913002662006091300266NM 2006 9 13 PIDR2006017 120060801G5711654532421 SPAR BOEING737 737330 13844BJNM BS 224 DAMAGED B PIDRK NONE O OTHER ININSP/MAINT 1 SO05241DL 23833 FASTENER HOLE IN THE LT UPPER REAR SPAR CHORD AT STA 224.14 (AT THE LANDING GEAR BEAM OB ATTACH FITTING) CRACKED .024 INCHES BEYOND ALLOWABLE LIMITS. REPLACED THE REAR SPAR CHORD SEGMENT FROM THE SIDE OF THE FUSELAGE BODY TO REAR SPAR STA 285. NOTE: PLEASE REMOVE PIDR AS THE OPERATOR DESIGNATOR IN ORDER TO IDENTIFY THE OPERATOR AS A GENERAL AVIATION OPERATOR. 2L72 4F RTA16WE 20060918000092006091800009NM 2006 9 18 PIDR2006018 120060814G5711 SPAR BOEING737 737330 13844BJNM BS 224 CRACKED B K NONE O OTHER ININSP/MAINT 1 SO05241DL 23833 TWO FASTENER HOLES IN THE RIGHT REAR SPAR AT STA 224.14 (AT THE LANDING GEAR BEAM O/B ATTACH FITTING) CRACKED. REAMED ONE HOLE PER BOEING SB 737-1216R2 AND REAMED SECOND HOLE AND INSTALLED A FREEZE PLUG PER BOEING MESSAGE 1-210954789-9 WITH FAA APPROVED 8100-9 DATED 24 AUG 2006. 2L72 4F RTA16WE 20061018000292006101800029NM 2006 10 18 PIDR2006019 120060928G5315 FLOORBEAM BOEING737 7373B7 1384580NM GE CFM56 CFM56* 13802NE BS 727D CORRODED B K NONE O OTHER ININSP/MAINT 1 SO05385US 22958 UNDERSIDE OF BS 727D+5 FLOORBEAM IN AFT CARGO BIN IS CORRODED FROM LBL17 TO RBL8. REPAIRED AREA IAW SRM 53-00-53 FIG. 201. 2L72 4F4 FRTA16WE E2GL 20061018000282006101800028NM 2006 10 18 PIDR2006020 120060928G5330 SKIN BOEING737 7373B7 1384580NM GE CFM56 CFM56* 13802NE BS 400 S23R DENTED B K NONE O OTHER ININSP/MAINT 1 SO05385US 22958 EXISTING DOUBLER ON FUSELAGE AT BS 400 AND S23RT HAS A DENT. REMOVED EXISTING DOUBLER AND INSTALLED NEW IAW SRM 53-00-01 FIG. 201. 2L72 4F4 FRTA16WE E2GL 20061018000272006101800027NM 2006 10 18 PIDR2006021 120060928G5330 SKIN BOEING737 7373B7 1384580NM GE CFM56 CFM56* 13802NE FUSELAGE WORN B K NONE O OTHER ININSP/MAINT 1 SO05385US 22958 FUSELAGE SKIN WORN UNDER DORSAL FIN. REPAIRED AREA IAW SB 737-55-1057. 2L72 4F4 FRTA16WE E2GL 20061018000262006101800026NM 2006 10 18 PIDR2006022 120060928G5315 FLOORBEAM BOEING737 7373B7 1384580NM GE CFM56 CFM56* 13802NE BS 312 CORRODED B K NONE O OTHER ININSP/MAINT 1 SO05385US 22958 FLOORBEAM AT BS 312 CORRODED AT NUTPLATE HOLES FROM RBL8 TO RBL32. REPLACED FLOORBEAM T-CAP IAW SRM 53-10-51. 2L72 4F4 FRTA16WE E2GL 20061019002312006101900231NM 2006 10 19 PIDR2006023 120060105G5315 FLOORBEAM BOEING737 7373B7 1384580NM BS 986 CORRODED B K NONE O OTHER ININSP/MAINT 1 SO05385US 22958 BS 986.5 FLOORBEAM CORRODED AT A PREVIOUS REPAIR FROM RBL14 TO RBL18. REPLACED UPPER T CAP OF FLOORBEAM IAW EA NR 53-264. 2L72 4F RTA16WE 20061013000022006101300002NM 2006 10 13 PIDR2006024 120061010G5315 FLOORBEAM BOEING737 7373B7 1384580NM BS 520 DAMAGED B K NONE O OTHER ININSP/MAINT 1 SO05385US 22958 VERTICAL WEB OF BS 520 FLOORBEAM DAMAGED AT RBL 36. REPAIRED DAMAGED AREA IAW EA 53-273. 2L72 4F RTA16WE 20061013000032006101300003NM 2006 10 13 PIDR2006025 120061011G5330 SKIN BOEING737 7373B7 1384580NM BS 360-540 DAMAGED B K NONE O OTHER ININSP/MAINT 1 SO05385US 22958 STR 14 LT SKIN LAP HAS SCRIBE LINE DAMAGE IN SEVERAL PLACES FROM BS 360 TO BS 540. REPAIRED DAMAGED AREA IAW SB 737-53A1177. 2L72 4F RTA16WE 20061020000502006102000050NM 2006 10 20 PIDR2006026 120061014G5311 FRAME BOEING737 7373B7 1384580NM BS 767 S13L CRACKED B PIDRK NONE O OTHER ININSP/MAINT 1 SO05385US 22958 CRACK IN BS 767 FRAME AT STR 13 RT. REPAIRED PER SRM 53-00-07 FIG 201. NOTE: PLEASE REMOVE PIDR AS THE OPERATOR DESIGNATOR IN ORDER TO IDENTIFY THE OPERATOR AS A GENERAL AVIATION OPERATOR. 2L72 4F RTA16WE 20061020001262006102000126NM 2006 10 20 PIDR2006027 120061016G5311 FRAME BOEING737 7373B7 1384580NM BS 867 S13R CRACKED B PIDRK NONE O OTHER ININSP/MAINT 1 SO05385US 22958 FOUND CRACK IN BS 867 FRAME AT STR 13RT. REPAIRED FRAME PER SRM 53-00-07 FIG 201. PLEASE REMOVE PIDR AS THE OPERATOR DESIGNATOR IN ORDER TO IDENTIFY THE OPERATOR AS A GENERAL AVIATION OPERATOR. 2L72 4F RTA16WE 20061020001272006102000127NM 2006 10 20 PIDR2006028 120061016G5314 KEELBEAM BOEING737 7373B7 1384580NM BS 500D-540 CORRODED B PIDRK NONE O OTHER ININSP/MAINT 1 SO05385US 22958 CORROSION ON RIGHT KEEL BEAM (STR28RT) FROM BS 500D TO BS 540. REPAIRED AREA BY SPLICING IN A REPLACEMENT SECTION OF KEEL BEAM PER EA 53-268. PLEASE REMOVE PIDR AS THE OPERATOR DESIGNATOR IN ORDER TO IDENTIFY THE OPERATOR AS A GENERAL AVIATION OPERATOR. 2L72 4F RTA16WE 20061020001252006102000125NM 2006 10 20 PIDR2006029 120061016G5330 LAP JOINT BOEING737 7373B7 1384580NM BS 360-540 CRACKED B PIDRK NONE O OTHER ININSP/MAINT 1 SO05385US 22958 CRACK IN LOWER FASTENER ROW OF STR 10LT SKIN LAP AT BS 500D+10 AND VARIOUS LOCATIONS OF SCRIBE LINES AT STR 10LT LAP AREA WERE REPAIRED BY REPLACING THE SKIN LAP PER SB 737-53A1177. PLEASE REMOVE PIDR AS THE OPERATOR DESIGNATOR IN ORDER TO IDENTIFY THE OPERATOR AS A GENERAL AVIATION OPERATOR. 2L72 4F RTA16WE 20061020001512006102000151NM 2006 10 20 PIDR2006030 120061011G5330 LAP JOINT BOEING737 7373B7 1384580NM BS 360-540 DAMAGED B PIDRK NONE O OTHER ININSP/MAINT 1 SO05385US 22958 SEVERAL AREAS OF SCRIBE LINE DAMAGE AT STR 14LT FROM BS 360 TO BS 540. REPAIRED AREA BY REPLACING THE SKIN LAP PER SB 737-53A1177. PLEASE REMOVE PIDR AS THE OPERATOR DESIGNATOR IN ORDER TO IDENTIFY THE OPERATOR AS A GENERAL AVIATION OPERATOR. 2L72 4F RTA16WE 20061026001122006102600112NM 2006 10 26 PIDR2006031 120061016G5330 SKIN BOEING737 7373B7 1384580NM BS 350-360 S25L CORRODED B K NONE O OTHER ININSP/MAINT 1 SO05385US 22958 CORROSION IN FUSELAGE SKIN AT BS 360 AND STR 25 LT. CORROSION ON STR 25 LT BEYOND ALLOWABLE LIMITS. SPLICED A NEW PIECE OF STRINGER SECTION AND REMOVED LIGHT SURFACE CORROSION ON FUSELAGE SKIN PER EA 53-270. 2L72 4F RTA16WE 20061031001522006103100152NM 2006 10 31 PIDR2006032 120061022G5330 SKIN BOEING737 7373B7 1384580NM BS 727A CORRODED B K NONE O OTHER ININSP/MAINT 1 SO05385US 22958 CORROSION IN FUSELAGE SKIN IN AREA OF LT KEELBEAM (STR 28LT) AND RT KEELBEAM (STR 28RT)AT BS727A-4. CUT OUT FUSELAGE SKIN FOR ACCESS TO LT AND RT KEELBEAMS. REMOVED CORROSION FROM LT AND RT KEELBEAM AREAS WITHIN LIMITS OF SRM 53-60-12 FIG. 101. REPLACED CORRODED SECTION OF FUSELAGE SKIN IAW EA NR 53-275. 2L72 4F RTA16WE 20061031001542006103100154NM 2006 10 31 PIDR2006033 120061016G5311 FRAME BOEING737 737301 1384611NM GE CFM56 CFM56* 13802NE BS 616 CRACKED B K NONE O OTHER ININSP/MAINT 1 SO05573US 23560 CRACK IN BS 616 FRAME RT SIDE BELOW FLOOR. REPAIRED DAMAGED AREA IAW SB 737-53-1182. 2L72 4F4 FRTA16WE E2GL 20061031001532006103100153NM 2006 10 31 PIDR2006034 120061013G5313 STRINGER BOEING737 737301 1384611NM GE CFM56 CFM56* 13802NE BS 312-328 CORRODED B K NONE O OTHER ININSP/MAINT 1 SO05573US 23560 STRINGER 28RT CORRODED BETWEEN BS 312 AND BS 328. REPLACED STRINGER SECTION IAW SRM 51-40-02. 2L72 4F4 FRTA16WE E2GL 20061031001552006103100155NM 2006 10 31 PIDR2006035 120061019G5230 BEAM BOEING737 737301 1384611NM GE CFM56 CFM56* 13802NE CARGO DOOR CRACKED B K NONE O OTHER ININSP/MAINT 1 SO05573US 23560 LOWER LT AND RT INTERNAL BEAMS CRACKED. REPAIRED BEAMS SB 737-52A1079. 2L72 4F4 FRTA16WE E2GL 20061031001712006103100171NM 2006 10 31 PIDR2006036 120061026G5330 SKIN BOEING737 7373B7 1384580NM BS 328-332 CRACKED B K NONE O OTHER ININSP/MAINT 1 SO05385US 22958 CRACK IN FUSELAGE SKIN AT AFT LOWER CORNER OF FORWARD SERVICE DOOR (R1). NDT CONFIRMED ADDITIONAL CRACK IN BONDED DOUBLER. REPAIRED AREA IAW SRM 53-00-01 FIG. 201 REPAIR 32 AND EA NR 53-265. 2L72 4F RTA16WE 20061031001402006103100140NM 2006 10 31 PIDR2006037 120061023G5311 FRAME BOEING737 7373B7 1384580NM BS 663 S2-3R CRACKED B K NONE O OTHER ININSP/MAINT 1 SO05385US 22958 CRACKS IN BS663.75 FRAME AT STR 2RT AND STR 3RT. REPAIRED FRAME IAW SRM 53-00-07. 2L72 4F RTA16WE 20061106000812006110600081NM 2006 11 6 PIDR2006038 120061027G5743 FITTING BOEING737 737301 1384611NM GE CFM56 CFM56* 13802NE LT MLG CRACKED B K NONE O OTHER ININSP/MAINT 1 SO05573US 23560 LT MLG FITTINGS CRACKED AT THE NR 2 HOLE. REPLACED FITTING IAW SB 737-57-1216. 2L72 4F4 FRTA16WE E2GL 20061106000822006110600082NM 2006 11 6 PIDR2006039 120061101G5753 SKIN BOEING737 737301 1384611NM GE CFM56 CFM56* 13802NE LT FORE FLAP DELAMINATED B PIDRK NONE O OTHER ININSP/MAINT 1 SO05573US 23560 DELAMINATION AT THE IB END OF THE LT OB FORE FLAP. REPAIRED DAMAGED AREA IAW SRM 51-70-10. 2L72 4F4 FRTA16WE E2GL 20061106000802006110600080NM 2006 11 6 PIDR2006040 120061031G5752 TAB BOEING737 7373B7 1384580NM GE CFM56 CFM56* 13802NE RT AILERON SEPARATED B PIDRK NONE O OTHER ININSP/MAINT 1 SO05385US 22958 TRAILING EDGE OF THE RT AILERON TAB IS SEPARATED. REPAIRED MINOR DAMAGE PER SRM 51-70-16. BALANCED TAB, NO WEIGHT CHANGE. 2L72 4F4 FRTA16WE E2GL 20061115003172006111500317NM 2006 11 15 PIDR2006041 120061107G5311 FRAME BOEING737 737301 1384611NM GE CFM56 CFM56* 13802NE BS 440 CRACKED B PIDRK NONE O OTHER ININSP/MAINT 1 SO05573US 23560 FORWARD FRAME OF THE FORWARD CARGO DOOR CUTOUT (BS 440 FRAME) CRACKED AT LOWER FORWARD STOP FITTING. REPAIRED CRACK PER INSTRUCTIONS FROM MFG WITH FAA APPROVED 8100-9 DATED NOV.6, 2006. 2L72 4F4 FRTA16WE E2GL 20061115003192006111500319NM 2006 11 15 PIDR2006042 120061031G5330 BEAR STRAP BOEING737 737301 1384611NM GE CFM56 CFM56* 13802NE FUSELAGE CRACKED B PIDRK NONE O OTHER ININSP/MAINT 1 SO05573US 23560 CRACK INDICATION IN FASTENER HOLE JUST FORWARD AND BELOW THE L1 DOOR UPPER HINGE CUTOUT IN THE BEAR STRAP (SECOND LAYER) CONFIRMED BY HFEC. REPAIRED IAW MFG INSTRUCTIONS WITH FAA APPROVED 8100-9 DATED NOV 3, 2006. 2L72 4F4 FRTA16WE E2GL 20061115002272006111500227NM 2006 11 15 PIDR2006043 120061026G534265538344 FITTING BOEING737 7373B7 1384580NM DRAG ANGLE CORRODED B K NONE O OTHER ININSP/MAINT 1 SO05385US 22958 CORROSION ON THE FORWARD FACE AND INSIDE DIAMETER OF THE RT FORWARD DRAG ANGLE FITTING AT THE VERTICAL STABILIZER AFT RT ATTACH FITTING. REPLACED FITTING IAW SRM 51-40-02, 51-40-03, AND DRAWING NR 65-53744. 2L72 4F RTA16WE 20061115002302006111500230NM 2006 11 15 PIDR2006044 120061103G5330 SKIN BOEING737 7373B7 1384580NM FUSELAGE DAMAGED B K NONE O OTHER ININSP/MAINT 1 SO05385US 22958 FASTENER HOLES JUST FORWARD AND ABOVE THE RIGHT FWD DOOR UPPER HINGE CUTOUT AND JUST FORWARD OF THE LOWER HINGE CUTOUT ARE CRACKED. REPAIRED SKIN AND BEAR STRAP IAW MESSAGES 1-232472835 WITH FAA DER APPROVED 8100-9 DATED NOV. 3, 2006. 2L72 4F RTA16WE 20061115002282006111500228NM 2006 11 15 PIDR2006045 120061103G5310 STRUCTURE BOEING737 7373B7 1384580NM FUSELAGE CRACKED B PIDRK NONE O OTHER ININSP/MAINT 1 SO05385US 22958 FASTENER HOLES CRACKED AT THE UPPER HINGE CUTOUT AND LOWER HINGE CUTOUT OF THE LT FORWARD ENTRY DOOR. REPAIRED AREA IAW MESSAGE 1-232472835 WITH FAA DER APPROVED 8100-9 DATED NOV.3, 2006. 2L72 4F RTA16WE 20061205000072006120500007NM 2006 12 5 PIDR2006046 120061115G5754 SLAT BOEING737 7373B7 1384580NM LT WING DAMAGED B K NONE O OTHER ININSP/MAINT 1 SO05385US 22958 LT WING LEADING EDGE AT THE OB END OF THE NR3 SLAT DAMAGED. REPAIRED DAMAGE PER SRM 51-70-11, 51-70-14, AND 51-70-16. 2L72 4F RTA16WE 20061117001712006111700171NM 2006 11 17 PIDR2006047 120061115G5520 HINGE BOEING737 7373B7 1384580NM RT ELEVATOR DAMAGED B K NONE O OTHER ININSP/MAINT 1 SO05385US 22958 RT ELEVATOR LOWER SIDE AT NR 5 HINGE HAS DAMAGE. REPAIRED IAW SRM 51-70-17 AND MFG MESSAGE NR 1-247071893 WITH FAA DOA APPROVAL FORM 8100-9. 2L72 4F RTA16WE 20060724000312006072400031GL 2006 7 24 PNC2006001 120060718G3244269K431 TIRE BOMBDRBD700 BD7001A10 1390006GL LANDING GEAR BULGED D K NONE O OTHER LDLANDING 1 EA03387PC78 20087 SIDE WALL BULGED 4 INCHES BY 4 INCHES BY APPROX 3 INCHES HIGH. ISSUE ADDRESSED BY ADVISORY WIRE AW300-32-0040. 2L72 4F RTT00003NY 20060816003052006081600305GL 2006 8 16 PNC2006004 120060814G3244269K431 TIRE BOMBDRBD100 BD1001A10 1390044GL ZONE 700 BULGED C K NONE O OTHER ININSP/MAINT 1 EA03387PC91 20087 BULGE IN TIRE ON SIDEWALL THAT EXTENDS ONTO THE TREAD. 2L72 4F RTT00005NY 20060724000842006072400084GL 2006 7 24 PNC20062 120060721G3244269K431 TIRE BOMBDRBD100 BD1001A10 1390044GL LANDING GEAR BULGED C K NONE O OTHER ININSP/MAINT 1 EA03353PC137 20053 BULGE ON SIDEWALL OF TIRE THAT EXTENDS INTO THE TREAD. BULGE SIZE 2.5 INCHES X 2.5 INCHES X .7INCH HIGH. 2L72 4F RTT00005NY 20060724000792006072400079GL 2006 7 24 PNC20063 120060721G3244269K431 TIRE BOMBDRBD100 BD1001A10 1390044GL LANDING GEAR SEPARATED C K NONE O OTHER ININSP/MAINT 1 EA03353PC94 20053 TIRE SIDEWALL SEPERTED AT SEVERAL LOCATIONS ABOUT ONE INCH ABOVE BEAD SEAT,NEAR MOLDING MARK. ABOUT A ONE INCH LONG VOID. 2L72 4F RTT00005NY 20060816003062006081600306GL 2006 8 16 PNC20064 120060814G3244269K431 TIRE BOMBDRBD100 BD1001A10 1390044GL BULGED C K NONE O OTHER ININSP/MAINT 1 EA03387PC91 20087 BULGE IN TIRE ON SIDEWALL THAT EXTENDS ONTO THE TREAD. 2L72 4F RTT00005NY 20060724000342006072400034CE 2006 7 24 PT196042 120060615G61239638003013 JAM-NUT BEECH 58 58 1152740CE CONT O550 IO550C SO PROP GOVERNOR LOOSE D K NONE O OTHER ININSP/MAINT 1 GL03376W 550 TH1970 684427 RT PROPELLER RPM DECREASES TOWARD FEATHER BEFORE PROP CONTROL IS BROUGHT BACK INTO FEATHER DETENT. FOUND JAM NUT ON FEATHER SPEED ADJUSTMENT SCREW HAD WORKED LOOSE AND THE ADJUSTMENT SCREW WAS BACKING OUT. THE DESIGN OF THESE NUTS HAS BEEN CHANGED IN THE LAST FEW YEARS, THE EARLY TYPE DID NOT SEEM TO LOOSEN. IF THE ADJUSTMENT SCREW HAD CONTINUED TO BACK OUT, THE ENGINE COULD HAVE EXPERIENCED AN UNCOMMANDED FEATHER WITH LITTLE OR NO WARNING. SUGGEST CHECKING TORQUE OF JAM NUT AT EACH INSPECTION AND APPLICATION OF TORQUE PUTTY UNTIL BETTER RETENTION SYSTEM IS DEVELOPED. (K) 1L72 3O3 O 3A16 E3SO 20061219001552006121900155 2006 12 19 QKPR06001 120060912G493038828406 FCU HONEYWELL GTCP36150RR ENGINE LEAKING B QKPRK NONE K FLUID LOSS ININSP/MAINT 1 SO05 FUEL PRESSURE IN THE DIFFERENTIAL PRESSURE VALVE IS CAUSING SEVERE PITTING INSIDE THE FCU HOUSING. THIS PITTING EVENTUALLY BECOMES A PIN HOLE IN THE HOUSING. THIS PIN HOLE ALLOWS A STREAM OF FUEL, AT IDLE AND WHEN PRESSURE IS APPLIED, TO EXIT THE FCU. POTENTIALLY, IF THIS PROBLEM IS NOT CORRECTED IT COULD CREATE A FIRE HAZZARD. 20061219001082006121900108 2006 12 19 QKPR06002 120060912G493038828406 FCU HONEYWELL GTCP36150RR ENGINE LEAKING B QKPRK NONE K FLUID LOSS ININSP/MAINT 1 SO05 FUEL PRESSURE IN THE DIFFERENTIAL PRESSURE VALVE IS CAUSING SEVERE PITTING INSIDE THE FCU HOUSING. THIS PITTING EVENTUALLY BECOMES A PIN HOLE IN THE HOUSING. THIS PIN HOLE ALLOWS A STREAM OF FUEL, AT IDLE AND WHEN PRESSURE IS APPLIED, TO EXIT THE FCU. POTENTIALLY, IF THIS PROBLEM IS NOT CORRECTED IT COULD CREATE A FIRE HAZZARD. 20061219001562006121900156 2006 12 19 QKPR06003 120060629G493038828406 FCU HONEYWELL GTCP36150RR ENGINE LEAKING B QKPRK NONE O OTHER ININSP/MAINT 1 SO05 P254 FUEL PRESSURE IN THE DIFFERENTIAL PRESSURE VALVE IS CAUSING SEVERE PITTING INSIDE THE FCU HOUSING. THIS PITTING EVENTUALLY BECOMES A PIN HOLE IN THE HOUSING. THIS PIN HOLE ALLOWS A STREAM OF FUEL, AT IDLE AND WHEN PRESSURE IS APPLIED, TO EXIT THE FCU. POTENTIALLY, IF THIS PROBLEM IS NOT CORRECTED, IT COULD CREATE A FIRE HAZZARD. ORIGINAL DIFFICULTY DATE 6/29/01. 20070108002822007010800282GL 2007 1 8 QKPR06007 120060815G493038828406 FUEL CONTROL HONEYWELL GTCT36150RR DOUG A4D A4D GL APU LEAKING B QKPRO OTHER O OTHER NRNOT REPORTED 1 SO05 FUEL PRESSURE IN THE DIFFERENTIAL PRESSURE VALVE IS CAUSING SEVERE PITTING INSIDE THE FCU HOUSING. THIS PITTING EVENTUALLY BECOMES A PIN HOLE IN THE HOUSING. THIS PIN HOLE ALLOWS A STREAM OF FUEL, AT IDLE AND WHEN PRESSURE IS APPLIED, TO EXIT THE FCU. POTENTIALLY, IF THIS PROBLEM IS NOT CORRECTED IT COULD CREATE A FIRE HAZARD. * REMOVE AIRCRAFT INFORMATION. REPORT ORIGINALLY SUBMITTED ON 8/15/01 UNDER R/S NR PIDR318B. 2L71 4R RTA1GL 20070108002882007010800288GL 2007 1 8 QKPR06009 120060918G493038828406 FUEL CONTROL HONEYWELL GTCT36150RR DOUG A4D A4D GL APU LEAKING B QKPRO OTHER O OTHER NRNOT REPORTED 1 SO05 FUEL PRESSURE IN THE DIFFERENTIAL PRESSURE VALVE IS CAUSING SEVERE PITTING INSIDE THE FCU HOUSING. THIS PITTING EVENTUALLY BECOMES A PIN HOLE IN THE HOUSING. THIS PIN HOLE ALLOWS A STREAM OF FUEL, AT IDLE AND WHEN PRESSURE IS APPLIED, TO EXIT THE FCU. POTENTIALLY, IF THIS PROBLEM IS NOT CORRECTED IT COULD CREATE A FIRE HAZARD. * REMOVE AIRCRAFT INFORMATION. 2L71 4R RTA1GL 20060224001982006022400198NE 2006 2 24 R018276 320060120G6114C459 PLATE HARTZL HARTZLHCE4N HCE4N3 NE PROPELLER HUB GOUGED B K NONE O OTHER NRNOT REPORTED 1 GL05SJ3R HH2369 HH2369 C-459 PRELOAD PLATE. THREE PRELOAD PLATES FOUND TO BE DAMAGED BEYOND REPAIRABLE LIMITS. GOUGE IS LOCATED OPPOSITE OF THE WINDOW AND IS APPROXIMATELY 0.030 WIDE BY 1 INCH LONG BY 0.020 DEEP. 5 CP10NE 20060224001952006022400195NE 2006 2 24 R018683 320060120G6114 PLATE HARTZL HARTZLHCE4N HCE4N3 NE PROPELLER HUB GOUGED B K NONE O OTHER NRNOT REPORTED 1 GL05SJ3R HH2422 HH2422 C-459 PRELOAD PLATE. GOUGE IS APPROXIMATELY 1.120 INCH LONG BY 0.050 INCH WIDE. 5 CP10NE 20060201001262006020100126GL 2006 2 1 R018909 320060128G6110 O-RING HARTZL HCC2YR4CF HARTZLHCC2Y HCC2YR4 GL PROPELLER BLADESWRONG PART B O OTHER O OTHER NRNOT REPORTED 1 GL05SJ3R DN5325B DN5325B PROP LEAKING GREASE FROM BLADES. INSPECTION REVEALED INCORRECT BLADE SEALS INSTALLED. SRM 113B REQUIRES ITEM 540, B-3883-4339 QUAD RING WITH NO ALTERNATE. SEALS REMOVED FROM PROPELLER ARE O-RINGS. 5 CP920 20060322001922006032200192GL 2006 3 22 R019142 320060222G6110D32517 HUB HARTZL CESSNA340 340CESSNA 2076404CE CONT O520 TSIO520NB 17040SO HARTZLHCC3Y PHCC3YF2 GL PROPELLER ASSY CRACKED B SJ3RK NONE K FLUID LOSS ININSP/MAINT 1 GL05SJ3R EB2069 EB2069 CUSTOMER WAS INVESTIGATING AN ABNORMAL GREASE LEAK ON THE RIGHT HAND PROPELLER. REMOVED THE SPINNER, DISCOVERED THAT THE ENGINE-SIDE HUB HALF WAS VISIBLY CRACKED. CRACKS ARE LOCATED ON THE PROPELLER MOUNTING FLANGE HUB HALF, LEAD EDGE SIDE OF BLADE SOCKETS NUMBER 1 AND 2. CRACKS RUN FROM HUB PARTING SURFACE TO MOUNTING FLANGE. 1L72 3O3 O 3A25 E8CE 5 CP25EA 20060321000482006032100048GL 2006 3 21 R019184 320060306G6110B4776 BUSHING HARTZL HCC3YR1A PITTS S2B S2B 2210006SO LYC O540 AEIO540D4A5 41532EA HARTZLHCC3Y HCC3YR GL PROPELLER ASSY LOOSE B SJ3RO OTHER KJ FLUID LOSS WARNING INDICATION NRNOT REPORTED 1 GL05SJ3R EL270B EL270B CUSTOMER REMOVED PROP DUE TO OIL LEAKING FROM BLADE. DISASSEMBLY OF THE PROPELLER REVEALED A LOOSE PITCH CHANGE ROD BORE BUSHING CAUSING THE OIL LEAK. THE PC ROD BUSHING WAS FOUND WEDGED BETWEEN THE FORK AND HUB. CENTRAL WEB AREA OF HUB WAS FULL OF OIL. THE PC ROD BORE BUSHING HAD BEEN INSTALLED AT OVERHAUL IN ACCORDANCE WITH HARTZELL MANUAL 202A VOLUME 3 REVISION 28. 1Q71 3O3 ONCA8SO 1E4 5 CP25EA 20060321001182006032100118NE 2006 3 21 R019280 320060303G6110D7745 BEARING RACE HARTZL HCE4A3I BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE HARTZLHCE4A HCE4A3I NE PROPELLER BROKEN B SJ3RO OTHER E VIBRATION/BUFFET NRNOT REPORTED 1 GL05SJ3R 2134 KX201 KX201 CUSTOMER REMOVED PROPELLER DUE TO LOOSE BLADE IAW HARTZELL SERVICE BULLETIN HC-SB-61-283. ONE D-7745 BLADE SIDE BEARING INSTALLED ON BLADE SERIAL NUMBER 2828 WAS FOUND CRACKED CIRCUMFERENTIALLY. 2L72 4T4 TRTA24CE E26NE 5 CP10NE 20060530001672006053000167SO 2006 5 30 R019692 120060519G6120C6512 ROD HARTZL PHCG3YF1E PIPER PA46 PA46310P 7104605SO CONT O520 TSIO520BE 17040SO HARTZLHCC2Y BHCC2Y* GL ENGINE WORN B SJ3RK NONE O OTHER ININSP/MAINT 1 GL05SJ3R 1338 HP900B HP900B THE AREA OF THE PITCH CHANGE ROD THAT IS GUIDED THROUGH THE ENGINE SIDE HUB HALF BORE HAS WORN THROUGH THE CHROME PLATING BEFORE FIRST OVERHAUL. 1L71 3O3 ORTA25SO E8CE 5 CP920 20060914000722006091400072NE 2006 9 14 R020646 320060824G61101006411 PLATE HCE4A3J BEECH 1900 1900D 1154162CE PWA PT6 PT6* 52043EA HARTZLHCE4A HCE4A3A NE PROPELLER MISMARKED B SJ3RK NONE O OTHER ININSP/MAINT 1 GL05 522 HJ1190 UE370 HJ1190 PRELOAD PLATES ARE MARKED WITH PN 100641 BUT CONFIGURED AS PN 100641-1. LOGBOOK INDICATES PROP WAS REMOVED ON 5/17/05 FROM AIRCRAFT D2-EVN, S/N UE-370 RT POSITION DUE TO DEEP GOUGE OVER ACCEPTABLE LIMITS. PROP WAS OVERHAULED ON 7/14/05 WITH 824.0 TSN. PRELOADS MAY HAVE BEEN INSTALLED AT THIS TIME IAW S/B HC-SB-61-278. I DO NOT KNOW IF THE BEARINGS WERE REMOVED TO MAKE P/N 100641-1 OR THE PART WAS INCORRECTLY MARKED AT HPI. 2L72 4T3 TRTA24CE E2NE 5 CP10NE 20070104000712007010400071CE 2007 1 4 RDA113006 120061130G2437VA100 AMMETER CESSNA175 175 2072502CE FAILED G O OTHER O OTHER NRNOT REPORTED 1 GL239456B18 55256 AEROSPACE LOGIC VA-100 DIGITAL VOLT/AMMETER AMP FUNCTION FAILED. AMP READING VARIES FROM -12 TO -18.5 AMPS, THIS INDICATION IS PRESENT WITH NO LOAD ON SYSTEM OR WITH ENGINE OPERATING AND GENERATOR OPERATING NORMALLY. VOLT FUNCTION OPERATES NORMALLY AND VOLTAGE READING IS NORMAL. CONSULTED WITH MANUFACTURER AND TROUBLESHOT IAW THEIR PROCEDURE TO VERIFY THAT GAUGE HAS MALFUNCTIONED. A REVIEW OF THE MANUFACTURER'S ON-LINE FORUM HAS REPORTS OF SIMILAR FAILURES OF THE VA-100. 1H71 3O NT3A17 20060228000202006022800020WP 2006 2 28 ROBSUL0106 120060203G5302C0231 STRUCTURE ROBSINR44 R44RAVENII 7640122WP TAILBOOM DENTED Z K NONE O OTHER ININSP/MAINT 1 SW99105GK185 10527 DURING 100 HOUR/ANNUAL INSPECTION A DENT WAS FOUND ON THE TAILBOOM CAUSED BY M/R BLADE CONTACT WITH BOOM. DUE TO SUSPECTED STATIC CONTACT DURING HIGH WIND CAUSING ROTOR SYSTEM TO TEETER RAPIDLY AND CONTACT BOOM. ADDITIONAL DAMAGE FOUND WITH BENDING OF PITCH LINK ROD ENDS AND CONTACT WITH HUB OF THE RUBBER BOOTS OF THE SPINDLE PITCH HORNS. THIUS DAMAGE CONSISTENT WITH BLADE RISING DUE TO HIGH WIND. 1G71 3O H11NM 20060511002542006051100254SO 2006 5 11 RX8R2006001 120060410G32305777402 HYDRAULIC LINE PIPER PA42 PA42720 7104212SO PWA PT6 PT6A61 52043EA HARTZLHCB3T HCB3TN3 GL LG RETRACT SYS DAMAGED B RX8RA UNSCHED LANDING K FLUID LOSS CLCLIMB 1 SO159085U5679 425501034 PCE99076 BUA26367 AFTER TAKEOFF THE LANDING GEAR HANDLE WAS MOVED TO THE UP POSITION THE LANDING GEAR CAME UP BUT THE GEAR DOORS DID NOT CLOSE. THE LANDING GEAR HANDLE WAS PUT IN THE DOWN POSITION BUT THE LANDING GEAR DID NOT LOCK DOWN. THE EMERGENCY HAND PUMP WAS USED TO MAKE THE LANDING GEAR LOCK IN THE DOWN POSITION. THE AIRCRAFT WAS LANDED WITHOUT INCIDENT. DISCOVERED HYDRAULIC LINE FROM HYDRAULIC FILTER WAS RUBBING ON NUT PLATE AND HAD WORN A HOLE IN IT. RIGHT WING TO NACELLE AREA WAS INSPECTED AND THE SAME HYDRAULIC LINE WAS FOUND RUBBING IN THE SAME AREA BUT HAD NOT WORN THROUGH. RECOMMEND INSPECTING THIS AREA ON ALL PA42-720 AIRCRAFT. AREA LOCATED BEHIND SMALL (FOUR INCH) PANEL JUST INBOARD OF THE ENGINE NACELLE ON LE. 1L72 4T4 T A23SO E4EA 6 CP15EA 20060620000122006062000012EU 2006 6 20 RX8R2006002 120060607G7603L810BQ54 SOLENOID SNIAS 350 AS350B3 8680954EU TMECA ARRIELARRIEL2B NE THROTTLE SYS DEFECTIVE B RX8RK NONE O OTHER ININSP/MAINT 1 SO15578AE 3716 22381 TWIST GRIP SOLENOID DOES NOT STAY IN THE MANUAL MODE POSITION (RETRACTED) WHEN MANUAL MODE IS SELECTED. AFTER APPROXIMATELY 5 MINUTES SOLENOID WILL GRADUALLY EXTEND, LOCKING THE TWIST GRIP IN THE AUTO POSITION AS THE SOLENOID HEATS UP FROM USE. THIS COULD CREATE A BIG PROBLEM IN AN EMERGENCY SITUATION WHERE THE PILOT SELECTS MANUAL MODE FOR CONTROL OF TWIST GRIP FOR POWER AND WOULD NOT HAVE IT (AFTER APPROX 5 MINUTES) DUE TO SOLENOID LOCKING THE TWIST GRIP. NOTE: THIS PART WAS JUST INSTALLED, NEW. 1G71 3U3 U H9EU E00054EN 20060814001452006081400145SO 2006 8 14 RX8R2006003 120060807G52804579411AND12 STRUCTURE PIPER PA42 PA42720 7104212SO PWA PT6 PT6A61 52043EA HARTZLHCB3T HCB3TN3 GL NLG DOOR CRACKED B RX8RK NONE O OTHER ININSP/MAINT 1 SO159085U5726 425501034 PCE99076 BUA26367 FOUND CRACK IN LT NOSE LANDING GEAR DOOR ON RADIUS OF FRONT STIFFENER SECTION. ALSO FOUND CRACK IN RT NOSE LANDING GEAR DOOR AT FORWARD HINGE ATTACH POINT. HAVE PREVIOUSLY FOUND CRACKS IN THE NOSE LANDING GEAR DOORS ON 4 OTHER PA-42'S. THE CRACKS ARE USUALLY IN THE DOOR HINGE ATTACH AREA. WE BELIEVE THE CRACKS ARE BEING CAUSED BY IN FLIGHT TURBULENCE, CAUSING THE DOORS TO VIBRATE IN FLIGHT. 1L72 4T4 T A23SO E4EA 6 CP15EA 20060201000752006020100075NE 2006 2 1 SJ3R018954 320060128G6114D7745 BEARING HARTZL HCE4A3I HARTZLHCE4A HCE4A3I NE PROPELLER HUB BROKEN B SJ3RK NONE O OTHER ININSP/MAINT 1 GL05 HJ1533 HJ1533 OPERATOR FAILED PROPELLER FOR BLADE END PLAY IAW SB HC-SB-61-283 AND SERVICE LETTER HC-SL-61-215. AFTER DISASSEMBLY, INSPECTION REVEALED ONE BROKEN D-7745 BLADE THRUST BEARING INSTALLED ON BLADE S/N 288MA LOCATED IN HUB SOCKET NR 3. 5 CP10NE 20060825000482006082500048GL 2006 8 25 SJ3R020511 320060809G6114D32511R HUB HARTZL INLANDS300 S300 4551002CE LYC O540 AEIO540* EA HARTZLHCC3Y HCC3YR GL PROPELLER DAMAGED B SJ3RK NONE O OTHER ININSP/MAINT 1 GL05 790 HTA1 HTA1 PROPELLER MOUNTING FLANGE HAS EXCESSIVE FRETTING DAMAGE. HUB IS SCRAP. 1H71 3R3 O ATC259 1E4 5 CP25EA 20070125000912007012500091NE 2007 1 25 SJ3R021444 320061118G6110D7745 BEARING HARTZL HCE4A3J BEECH 1900 1900D 1154162CE PWA PT6 PT6* 52043EA HARTZLHCE4A HCE4A3A NE PROPELLER BLADE BROKEN B SJ3RK NONE O OTHER ININSP/MAINT 1 GL05 HJ1797 HJ1797 BLADE POSITION 4, S/N 1091 THRUST BEARING BROKEN. DAMAGE TO PROPELLER HUB BLADE SOCKET NR 4 IS BEYOND REPAIRABLE LIMITS. MFG SB 287 HAS NOT BEEN PERFORMED ON THIS PROPELLER. 2L72 4T3 TRTA24CE E2NE 5 CP10NE 20060512000702006051200070NM 2006 5 12 SROM200600001 120060329G5313652072623 LONGERON BOEING737 737205 1384456NM FUSELAGE CRACKED C SROMK NONE O OTHER ININSP/MAINT 1 AL03733PA364551951 23466 DURING HEAVY MAINTENANCE INSPECTION FOUND CRACKS IN UPPER FLANGE RADIUS OF LONGERON/WEB P/N 65-20726-23 AT STA 455 AND 470, STR 26R. REMOVED WEB BETWEEN STA 440 - 493, FABRICATED REPLACEMENT WEB WITH 7075-T6 .063, IN LIEU OF ORIGINAL .056, AND INSTALLED IAW SRM AND MFG DRAWING NO 65-20726 AS SPECIFIED IN 8110-3 APPROVED DRAWING 5330-236-ERA, REV ORIGINAL, DATED 03-23-2006 AND MATERIAL SUBSTITUTION REPORT NO 5330236-ER, REV. ORIGINAL, DATED 03-23-2006. 2L72 4F RTA16WE 20060512000712006051200071NM 2006 5 12 SROM200600002 120060330G783065MK784132 THRUST REVERSER BOEING737 737205 1384456NM ENGINE CRACKED C SROMK NONE O OTHER ININSP/MAINT 1 AL03733PA 23466 DURING MAINTENANCE INSPECTION FOUND CRACK IN NR 2 LOWER THRUST REVERSER DOOR P/N 65MK78413-2 ALONG IB BUMPER. REMOVED BUMPER, STOP DRILLED CRACK, FABRICATE/INSTALL DOUBLER AND TRIPLER. FABRICATE AND INSTALL NEW CAP TO COMPENSATE FOR DOUBLER AND TRIPLER. ALL WORK ACCOMPLISHED IAW 8110-3 APPROVED DRAWING NR 7830233-1, REV ORIGINAL, DATED 03-20-2006 AND MATERIAL SUBSTITUTION REPORT NR 7830233-ER, REV ORIGINAL, DATED 03-20-2006. 2L72 4F RTA16WE 20060512000722006051200072NM 2006 5 12 SROM200600003 120060316G5753657194041 FLAP BOEING737 737205 1384456NM PWA JT8 JT8D17 52049NE LT WING DENTED C SROMK NONE O OTHER ININSP/MAINT 1 AL03733PA 1951 23466 DURING HEAVY MAINTENANCE VISIT FOUND DENT ON UPPER SURFACE OF LT IB MIDFLAP. REPAIRED FLAP BY INSTALLING INTERNAL DOUBLER AND FLUSH PART IN IAW SRM 57-50-4, FIG. 4 PG. 8 AND 9. 2L72 4F4 FRTA16WE E2EA 20060511002042006051100204NM 2006 5 11 SROM200600004 120060403G5730 SKIN BOEING737 737205 1384456NM ZONE 600 CRACKED C SROMK NONE O OTHER ININSP/MAINT 1 AL03736BP 882 23465 RT WING LEADING EDGE CRACKED AT NR 5 SLAT UPSTOP CUTOUT JUST OB OF THE ACTUATOR. REPAIRED BY INSTALLING INTERNAL STAINLESS DOUBLER IAW DER APPROVED 8110, REPORT NR SCS-5740-001SR. 2L72 4F RTA16WE 20060530001552006053000155NM 2006 5 30 SROM200600005 120060503G5313 STRINGER BOEING737 737201 1384454NM FUSELAGE CORRODED C SROMK NONE O OTHER ININSP/MAINT 1 AL03245US 1210 22751 DURING HEAVY MAINTENANCE INSPECTION FOUND CORROSION AT STR 28 LT, STA 1000 TO 1006. CORROSION FOUND TO BE BEYOND LIMITS. STRINGER REPLACED I.A.W. B737 SRM 53-10-2 AND 51-10-1 PG. 9 PARA 7. STRINGER REPLACED STA 986 - 1016 PLUS/MINUS 28". ORIGINAL SPLICE REUSED. SPLICE PIECE CLEANED AND PAINTED. LEVEL 1 CPCP ISOLATED TO LAV LEAK AND NOT EXPERIENCED ACROSS THE FLEET. 2L72 4F A16WE 20060530001512006053000151NM 2006 5 30 SROM200600006 120060510G5330 SKIN BOEING737 737201 1384454NM FUSELAGE CRACKED C SROMK NONE O OTHER ININSP/MAINT 1 AL03245US 1210 22751 DURING HEAVY MAINTENANCE INSPECTION FOUND SKIN CRACK UNDER RT WING TO BODY FAIRING AT STA 727B, STR 19R. REMOVED EXSISTING ADJACENT PATCH AT STA 727A, STR 18R. INSTALLED PATCH, INCORPORATING OLD REPAIR AND NEW DAMAGE IAW B737 SRM FIG. 48, 55-30-3 AND BOEING ENGINEERING 1-185385517-1. 2L72 4F A16WE 20060530001532006053000153NM 2006 5 30 SROM200600008 120060516G321065461406SPL BOLT BOEING B737200 BOEING737 737201 1384454NM LT MLG CRACKED C SROMK NONE O OTHER ININSP/MAINT 1 AL03245US295719248 XC89752 22751 DURING INSPECTION REQUIREMENTS OF AD2005-20-39, SB737-32A1367 FOUND LT MLG TEE BOLT, P/N 65-46140-6SPL, S/N XZ865 CRACKED AT RADIUS OF LARGEST BEARING SURFACE CIRCUMFERENCE. UNIT HAD TOTAL HOURS OF 29571, TOTAL CYCLES 22830. LAST OVERHAULED 1998 WITH ACCUMULATION OF 9248 HOURS AND 5265 CYCLES SINCE OVERHAUL. CRACK WAS AROUND 80% OF CIRCUMFERENCE. REPLACED WITH SERVICABLE UNIT. 2L72 4F A16WE 20060530001542006053000154NM 2006 5 30 SROM200600009 120060517G5330 SKIN BOEING737 737201 1384454NM FUSELAGE DENTED C SROMK NONE O OTHER ININSP/MAINT 1 AL03245US535811210 22751 DURING HEAVY CHECK INSPECTION DISCOVERED 9 CREASE/DENTS ON EXTERIOR SKIN AT STA 305 - 372, STR 23R - STR 24R. REPAIRED EXTERIOR SKIN IAW B 737 SRM FIGURE 48, DETAIL XXIX AND XIX. 2L72 4F A16WE 20060613003802006061300380NE 2006 6 13 SROM200600010 220060523G7250648031 CASE BOEING737 737201 1384454NM PWA JT8 JT8D15 52051NE NR 2 ENGINE CRACKED I SROMK NONE O OTHER ININSP/MAINT 1 AL03245US 1210 22751 696531 DURING HEAVY MAINTENANCE INSPECTION FOUND CRACKED OUT SECTION IN REAR EXHAUST CASE OF NR 2 ENGINE. REPLACED WITH OVERHAULED UNIT. 2L72 4F4 F A16WE E2EA 20060530000842006053000084NM 2006 5 30 SROM200600011 120060510G575365682979 CARRIAGE BOEING737 737201 1384454NM ZONE 500 CORRODED C SROMK NONE O OTHER ININSP/MAINT 1 AL03245US 15552 22751 DURING HEAVY MAINTENANCE CHECK WHILE PERFORMING A 10 YEAR CPCP INSPECTION REQUIREMENTS OF THE TRAILING EDGE FLAP CARRIAGES FOUND LEVEL 2 CORROSION ON NR 3 CARRIAGE OB CARRIAGE HALF. REPLACED WITH NEW HALF V/S REPAIR FOR COMPANY CONVENIENCE. 2L72 4F A16WE 20060530001192006053000119NM 2006 5 30 SROM200600012 120060510G5753656829710 CARRIAGE BOEING737 737201 1384454NM WING CORRODED C SROMK NONE O OTHER ININSP/MAINT 1 AL03245US 15552 22751 DURING HEAVY MAINTENANCE CHECK WHILE PERFORMING CPCP 10 YEAR REQUIREMENTS TO THE TRAILING EDGE FLAP CARRIAGES FOUND THE NR 3 TRAILING EDGE FLAP CARRIAGE IB CARRIAGE HALF TO HAVE LEVEL 2 CORROSION. REMOVED AND REPLACED WITH NEW UNIT V/S REPAIR FOR COMPANY CONVENIENCE. 2L72 4F A16WE 20060530001212006053000121NM 2006 5 30 SROM200600013 120060524G5753655224618 CARRIAGE BOEING737 737201 1384454NM TE FLAP CORRODED C SROMK NONE O OTHER ININSP/MAINT 1 AL03245US 15552 22751 DURING HEAVY MAINTENANCE CHECK WHILE PERFORMING 10 YEAR CPCP REQUIREMENTS TO TRAILING EDGE FLAP CARRIAGES FOUND NR 5 CARRIAGE, INBD CARRIAGE HALF CORRODED. LEVEL 2. REMOVED AND REPLACED WITH SERVICEABLE UNIT V/S REPAIR FOR CUSTOMER CONVENIENCE. 2L72 4F A16WE 20060530001182006053000118NM 2006 5 30 SROM200600014 120060524G575365522469 CARRIAGE BOEING737 737201 1384454NM WING CORRODED C SROMK NONE O OTHER ININSP/MAINT 1 AL03245US 15552 22751 DURING HEAVY MAINTENANCE INSPECTION WHILE PERFORMING 10 YEAR CPCP INSPECTION REQUIREMENTS TO THE TRAILING EDGE FLAP CARRIAGES FOUND THE NR 5 CARRIAGE OTBD CARRIAGE HALF TO BE CORRODED. LEVEL 2. REPLACED WITH SERVICABLE UNIT V/S REPAIR FOR CUSTOMER CONVENIENCE. 2L72 4F A16WE 20060530001222006053000122NM 2006 5 30 SROM200600015 120060524G575365522111 TORQUE TUBE BOEING737 737201 1384454NM ZONE 600 CORRODED C SROMK NONE O OTHER ININSP/MAINT 1 AL03245US 15552 22751 DURING HEAVY MAINTENANCE CHECK WHILE PERFORMING 10 YEAR CPCP REQUIREMENTS TO THE TRAILING EDGE FLAP CARRIAGES FOUND NR 5 FLAP CARRIAGE OUTER TORQUE TUBE TO BE CORRODED. LEVEL 2. REPLACED WITH SERVICABLE UNIT V/S REPAIR FOR CUSTOMER CONVENIENCE. 2L72 4F A16WE 20060530001202006053000120NM 2006 5 30 SROM200600016 120060524G575365372061 TORQUE TUBE BOEING737 737201 1384454NM WING FLAP CORRODED C SROMK NONE O OTHER ININSP/MAINT 1 AL03245US 15552 22751 DURING HEAVY MAINTENANCE CHECK WHILE PERFORMING 10 YEAR CPCP INSPECTION REQUIREMENTS TO THE TRAILING EDGE FLAP CARRIAGES FOUND THE NR 5 CARRIAGE INNER TORQUE TUBE TO BE CORRODED. LEVEL 2. REPLACED WITH SERVICEABLE UNIT V/S REPAIR FOR CUSTOMER CONVENIENCE. 2L72 4F A16WE 20061115002462006111500246NM 2006 11 15 SROM200600017 120061109G32606552811109 ACCESSORY UNIT BOEING737 737205 1384456NM PWA JT8 JT8D17A 52049NE RT MLG FAULTY C SROMA UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 AL03736BP 23465 DURING DEPARTURE, UPON LANDING GEAR RETRACTION RT MLG INDICATION REMAINED RED. MOVED LANDING GEAR HANDLE TO OFF AND THEN BACK TO UP, RED INDICATOR LIGHT REMAINED ON. SELECTED GEAR DOWN AND GOT 3 GREEN AND NO RED. RETURNED TO ANC WITH NORMAL LANDING. WITH AIRCRAFT ON JACKS FOUND LANDING GEAR ACCESSORY UNIT TO BE FAULTY. REPLACED LANDING GEAR ACCESSORY UNIT AND ALL OPERATIONS CHECK NORMAL. AIRCRAFT RELEASED WITH NORMAL OPERATIONS ON SUBSEQUENT FLIGHTS. 2L72 4F4 FRTA16WE E2EA 20061213000052006121300005NM 2006 12 13 SROM200600018 120061130G5330 SKIN BOEING737 737201 1384454NM FUSELAGE MISREPAIRED C SROMK NONE W INADEQUATE Q C ININSP/MAINT 1 AL03245US 22751 DURING OWNER REQUEST FOR REPLACEMENT OF FUSELAGE SKIN BS 907 - 1016, STR 20L - 25L (P/N 65C80736-834) TO ELIMINATE PREVIOUS PERMANENT AND TEMPORARY SKIN REPAIRS, DISCOVERED NON-STANDARD REPAIR AT BS992.80, STR 20L IDENTIFIED AS A CUTOUT IN THE ADJACENT UPPER SKIN. INSTALLED NEW REPAIR PER BOEING REPAIR INSTRUCTION 1-248459651-6, REFERENCE BOEING ISSUED FAA FORM 8100-9, DATED 30 NOV 2006. 2L72 4F A16WE 20061213000402006121300040NM 2006 12 13 SROM200600019 120061203G5330 SKIN BOEING737 737205 1384456NM BS 895 GOUGED C SROMK NONE O OTHER ININSP/MAINT 1 AL03733PA 23466 ON POST FLIGHT INSPECTION FOUND THREE INCH SKIN GOUGE AT FUSELAGE BS 895 BETWEEN STRS 22R AND 23R. REPAIRED WITH SKIN DOUBLER PER BOEING 737 SRM 53-30-3 AND 51-20-1. 2L72 4F RTA16WE 20061213000072006121300007NM 2006 12 13 SROM200600020 120061130G5521657378443 SPAR BOEING737 737205 1384456NM ELEVATOR CRACKED C SROMK NONE O OTHER ININSP/MAINT 1 AL03736BP 4604 23465 DURING INSPECTION FOUND LT ELEVATOR TAB OUTBOARD HINGE FITTING TO HAVE CONSIDERABLE FLEX. UPON FURTHER EXAMINATION FOUND ELEVATOR REAR SPAR CRACKED IN THE AREA WHERE TAB HINGE FITTING ATTACHES. AD 2006-14-07/SB 737-55A1078 HAD NOT BEEN ACCOMPLISHED PRIOR TO THIS FINDING. REPLACED ELEVATOR AND TAB WITH NEW. 2L72 4F RTA16WE 20070108001892007010800189NM 2007 1 8 SROM200600021 120061221G3220 LANDING GEAR BOEING737 737205 1384456NM PWA JT8 JT8D17A 52049NE NLG CONTAMINATED C SROMA UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 AL03733PA 23466 UPON DEPARTURE DURING HEAVY SNOW CONDITIONS WITH GRAVEL SKI EQUIPPED AIRCRAFT THE NOSE GEAR UNLOCK LIGHT REMAINED ON AFTER LANDING GEAR RETRACTION. LANDING GEAR EXTENDED AND AIRCRAFT RETURNED TO DEPARTURE AIRPORT WITH NORMAL LANDING. UPON INSPECTION FOUND GRAVEL DEFLECTOR TO BE CONTAMINATED WITH SNOW AND ICE. REMOVED SNOW AND ICE, JACKED AIRCRAFT AND SWUNG GEAR WITH NO DEFECTS NOTED. VERY HEAVY SNOW CONDITIONS ALLOWED FOR SNOW BUILD UP ON DEFLECTOR DURING TAXI OUT. DEFLECTOR WAS DEICED PRIOR TO TAXI. 2L72 4F4 FRTA16WE E2EA 20070104000732007010400073NM 2007 1 4 SROM200600022 120061227G5753 CARRIAGE BOEING737 737201 1384454NM PWA JT8 JT8D15 52051NE SPINDLE CRACKED C SROMK NONE O OTHER ININSP/MAINT 1 AL03245US 64 22751 DURING ROUTINE ACCOMPLISHMENT OF ULTRASOUND INSPECTION OF THE SPINDLES ON THE OB FLAPS IAW AD 2003-24-08 FOUND THE RT IB SPINDLE TO SHOW A CRACK INDICATION. LAST ULTRASONIC INSPECTION PERFORMED 46 CYCLES AGO. REPLACED SPINDLE AND CARRIAGE ASSEMBLY WITH NEW P/N 65C80736-712. 2L72 4F4 F A16WE E2EA 20060530001522006053000152NM 2006 5 30 SRON200600007 120060516G5330 SKIN BOEING737 737201 1384454NM FUSELAGE MISDRILLED C SROMK NONE O OTHER ININSP/MAINT 1 AL03245US 1210 22751 DURING HEAVY MAINTENANCE INSPECTION FOUND SNOWMAN SHAPED HOLE WITH A SOLID AND CHERRY MAX IN IT AT STA 727A, STR 26L. REPAIR PATCH AND DOUBLER INSTALLED PER BOEING ENGINEERING 1-185416133. FAA FORM 8109-9.0 2L72 4F A16WE 20060530001712006053000171EU 2006 5 30 THMN4113SQ116 120060508G5414MY2055270 COWLING AMD FALCONFALCON20 2730103EU ENGINE CRACKED B T0DRK NONE O OTHER ININSP/MAINT 1 CE03453SB 308 RT INBOARD ENGINE COWL HAS SMALL CRACK IN SKIN AT TOP/FWD CORNER. MADE AIRWORTHY REPAIR IAW DASSAULT FALCON 20 SRM 51-10-21. 2L72 4F RTA7EU 20060613003772006061300377EU 2006 6 13 THMN4113SQ118 120060508G5414MY20552302 COWLING AMD FALCONFALCON20 2730103EU RT ENGINE CRACKED B T0DRK NONE O OTHER ININSP/MAINT 1 CE03453SB 308 RT UPPER ENGINE COWL SKIN CRACKED AT FWD SEAL BRACKET. MADE AIRWORTHY REPAIR IAW SRM 54-20-43. 2L72 4F RTA7EU 20060518002402006051800240EU 2006 5 18 THMN4113SQ120 120060508G5420MY20552302 COWLING AMD FALCONFALCON20 2730103EU ENGINE CRACKED B T0DRK NONE O OTHER ININSP/MAINT 1 CE03453SB 308 RT UPPER ENGINE COWL AFT IB BRACKET CRACKED AT CORNER. MADE AIRWORTHY REPAIR IAW SRM 54-20-43 AND SRM 51-10-22. 2L72 4F RTA7EU 20060530001722006053000172EU 2006 5 30 THMN4113SQ121 120060508G5420MY20552302 COWLING AMD FALCONFALCON20 2730103EU ENGINE CRACKED B T0DRK NONE O OTHER ININSP/MAINT 1 CE03453SB 308 R/H UPPER ENGINE COWL CRACKED IN BRACKET UNDER SEAL IN CENTER SECTION. MADE AIRWORTHY REPAIR IAW FALCON 20 SRM 54-20-43. 2L72 4F RTA7EU 20060530001232006053000123CE 2006 5 30 THMN4129SQ111 120060522G5753 RIVET CESSNA500 500CESSNA 2076602CE RT IB FLAP LOOSE B T0DRK NONE O OTHER ININSP/MAINT 1 CE0327SF 64 RT INBOARD FLAP LOWER L/E HAS 7 LOOSE RIVETS. REMOVED AND REPLACED RIVITS IAW SRM 51-30-1. 1L72 4F A22CE 20060530001572006053000157CE 2006 5 30 THMN4129SQ112 120060522G5730552280051 SKIN PANEL CESSNA500 500CESSNA 2076602CE LT WING CRACKED B T0DRK NONE O OTHER ININSP/MAINT 1 CE0327SF 64 LT WING PANEL PN 5522800-51 CRACKED. REPLACED PANEL IAW MM 57-30-00 1L72 4F A22CE 20060718001822006071800182SO 2006 7 18 THMN4165SQ117 120060630G5753 SKIN PIPER PA30 PA39 7103902SO TE FLAP CRACKED B T0DRK NONE O OTHER ININSP/MAINT 1 CE03320GC 3960 FLAP LT IB LWR SKIN CRACKED. MADE AIRWORTHY REPAIR IAW PA-39 SERVICE MANUAL, CHAPTER 4 PG 1F6 AND AC 43.13-1B SECTION 4 PARAGRAPH 4-57 FIGURE 4-6 AND SECTION 4 PARAGRAPH 4-58 FIGURE 4-16. 1L72 3O A1EA 20060718001832006071800183SO 2006 7 18 THMN4165SQ118 120060630G5730 SKIN PIPER PA30 PA39 7103902SO RT WING CRACKED B T0DRK NONE O OTHER ININSP/MAINT 1 CE03320GC 3960 CRACK IN RT WING OB SKIN NEAR SPAR. MADE AIRWORTHY REPAIR IAW PA-39 SERVICE MANUAL CHAPTER 4 PG 1F6 AND AC43.13-1B SECTION 4 PARAGRAPH 4-57 FIGURE 4-6 AND SECTION 4 PARAGRAPH 4-58 FIGURE 4-16 1L72 3O A1EA 20060718001842006071800184SO 2006 7 18 THMN4165SQ123 120060630G5414 SKIN PIPER PA30 PA39 7103902SO LT NACELLE CRACKED B T0DRK NONE O OTHER ININSP/MAINT 1 CE03320GC 3960 LT ENGINE COWL CRACKED AT FWD FASTENER. MADE AIRWORTHY REPAIR IAW PA-39 SRM CHAPTER 4 PG 1F6 AND AC43.13-1B SECTION 4 PARAGRAPH 4-57 FIGURE 4-6 AND SECTION 4 PARAGRAPH 4-58 FIGURE 4-16. 1L72 3O A1EA 20060815000072006081500007NM 2006 8 15 TL9R200600001 120060809G324626123111 WHEEL BOEING737 737* NM MLG FRACTURED B TL9RO OTHER B SMOKE/FUMES/ODORS/SPARKS NRNOT REPORTED 1 GL13 OPERATOR STATES THAT SMOKE WAS REPORTED COMING FROM A WHEEL/BRAKE ASSEMBLY. TECHNICIANS DISCOVERED THAT THE HUB ON THE IB WHEEL HAD A COMPLETE CIRCUMFERENTIAL FRACTURE. THE COMPLETE WHEEL ASSEMBLY IS BEING SENT TO MFG FOR EVALUATION. 2L72 4F RTA16WE 20060815000082006081500008NM 2006 8 15 TL9R200600002 120060809G324626123111 WHEEL BOEING737 737* NM ZONE 700 FRACTURED B TL9RO OTHER B SMOKE/FUMES/ODORS/SPARKS NRNOT REPORTED 1 GL13 OPERATOR STATES THAT SMOKE WAS REPORTED COMING FROM A WHEEL/BRAKE ASSEMBLY. TECHNICIANS DISCOVERED THAT THE HUB ON THE IB WHEEL HAD A COMPLETE CRCUMFERENTIAL FRACTURE. THE COMPLETE WHEEL ASSEMBLY IS BEING SENT TO HONEYWELL IN SOUTH BEND, INDIANA FOR EVALUATION. 2L72 4F RTA16WE 20061117001722006111700172EU 2006 11 17 TL9R200600003 120061116G3242C200601004 BRAKE AIRBUS330 A300* EU MLG DEBONDED B TL9RK NONE O OTHER ININSP/MAINT 1 GL13 OPERATOR/CUSTOMER REPORTED THIS BRAKE AS (BRAKE STUCK). SUBSEQUENT INSPECTION OF THE BRAKE AT THIS REPAIR STATION DOCUMENTED THAT THE TEMPERATURE SENSOR WAS BENT, AND PARTS OF THE HEAT STACK HAD DELINED. 2L72 4F RTA26NM 20060323001562006032300156CE 2006 3 23 UVVR200600001 120060221G5711NAS12913 NUT RKWELLNA265 NA26560 7630106CE PWA JT12 JT12A8 52042NE WINGS CRACKED B K NONE O OTHER ININSP/MAINT 1 CE0371CC 30671 WHILE PERFORMING MAINTENANCE ON AIRCRAFT, IT WAS DISCOVERED THAT APPROXIMATELY 10 NUTS ON EACH WING THAT SECURES UPPER WING PLANK TO REAR SPAR UPPER FLANGE, FROM REAR SPAR STATION 161.1 TO 281.8 WERE CRACKED, WITH SOME MISSING PARTS OF THE NUT. AS A PRECAUTION, A TOTAL OF 96 SCREWS AND NUTS AT THESE LOCATIONS WERE REPLACED WITH NEW HARDWARE. 2L72 4J4 JRTA2WE 1E9 20060323000562006032300056CE 2006 3 23 UVVR200600002 120060223G5744258WF71A FITTING RAYTHNDH125 HAWKER800XP 7150012CE LT WING CORRODED B K NONE O OTHER ININSP/MAINT 1 CE03877DM3668 258279 WHILE CHANGING A BONDING BRAID ON THE LT OB FLAP ATTACH FITTING, THE INNER SURFACE OF THE LOWER ATTACH POINT FLANGE WAS FOUND CORRODED. APPROXIMATELY .050 INCH DEEP AROUND THE BOLT HOLE. THE PART WAS REPLACED WITH A NEW FITTING. 2L72 4F RTA3EU 20061018000452006101800045GL 2006 10 18 WI5R1005001 220061005G725073792 TURBINE BLADES CESSNA525 525 2076601CE WILINTFJ44 FJ441A GL ENGINE FRACTURED G WI5RK NONE O OTHER ININSP/MAINT 1 GL23103CS588 588 5250438 1903 DURING A PRE-BUY A/C INSPECTION, ENGINE SN 1903 WAS FOUND TO EXHIBIT A FRACTURED TRAILING EDGE OF HP TURBINE BLADE. 1L72 4F4 FRTA1WI E3GL 20061031001682006103100168 2006 10 31 WL7R200600001 420061005G25641218FAUL03011 LIFE RAFT UNSERVICEABLE B WL7RK NONE W INADEQUATE Q C ININSP/MAINT 1 SO35 LIFE RAFT HAD A PARACHUTE CORD TIED AROUND THE INFLATABLE PORTION OF THE LIFE RAFT, WHICH WOULD HAVE CAUSED THE LIFE RAFT TO STRANGLE AND THE LIFE RAFT WOULD HAVE FAILED TO DEPLOY. 20061031001492006103100149 2006 10 31 WL7R200600002 420061005G25641218FAUL03011 LIFE RAFT UNSERVICEABLE B WL7RK NONE W INADEQUATE Q C ININSP/MAINT 1 SO35 LIFE RAFT HAD A PARACHUTE CORD TIED AROUND THE INFLATABLE PORTION OF THE LIFE RAFT, WHICH WOULD HAVE CAUSED THE LIFE RAFT TO STRANGLE AND THE LIFE RAFT WOULD HAVE FAILED TO DEPLOY. PICTURE AVAILABLE. 20061115002532006111500253WP 2006 11 15 WP07110306 220061103G72003103336 BEARING GARRTTTPE331TPE3312U 01514WP ENGINE FAILED B ZN3RE ENGINE SHUTDOWN XJ ENGINE FLAMEOUT WARNING INDICATION CRCRUISE 1 WP07 1566 P70176C ENGINE WAS SENT TO MFG FOR A FLAME OUT INVESTIGATION. AT RECEIPT 2 KEY OBSERVATIONS WERE MADE. FIRST THE FILTER BYPASS INDICATOR WAS EXTENDED AND SECOND THE ROTATING GROUP WOULD NOT ROTATE. ONCE THE NOSE CONE AND DIAPHRAGM WERE REMOVED METAL WAS SEEN SHED THROUGHOUT GEARBOX. THE BINDING WAS FOUND TO BE DUE TO DAMAGE BETWEEN THE BULL GEAR AND HIGH SPEED PINION MATING TEETH. UPON FURTHER DISASSEMBLY, COMPRESSOR BEARING WAS DESTROYED. MFG BELIEVES THE COMPRESSOR BEARING AND NUT LOST THEIR FUNCTIONALITY, CAUSING THE ROTATING GROUP TO SHIFT FORWARD AND CAUSE RUBS. OVERALL THE SECONDARY DAMAGE DUE TO THIS EVENT WAS MINOR. 3 T E3WE 20061020000422006102000042 2006 10 20 WSAOCT182006 420061018G3100704A46814049 LIGHT SNIAS 350 AS350B3 8680954EU INSTRUMENT PANELCORRODED B K NONE O OTHER ININSP/MAINT 1 SW17578AE702 3716 A TECHNICIAN REMOVED THE INSTRUMENT PANEL GRADUATOR, LIGHT (LIGHTING DIMMER) FOR ACCESS PURPOSES. IT WAS FOUND UPON REMOVAL THAT THE 24 PIN ELECTRICAL CONNECTOR ON THIS DIMMER HAD MODERATE CORROSION ON OVER HALF OF THE CONNECTOR PINS WITH SIGNS OF CORROSION ON THE PC BOARD. THE SOURCE OF THE CORROSION IS BELIEVED TO BE WATER INGRESS FROM THE FRESH AIR DUCT LOCATED ABOVE THIS PART. 1G71 3U H9EU 20060227001452006022700145CE 2006 2 27 WTXR10549 120060208G5340 ATTACH BRACKET LEAR 35 35A 5170602CE FUSELAGE CRACKED C WTXRK NONE O OTHER ININSP/MAINT 1 SW99 113 FOUND CRACK AT LT AND RT FUSELAGE FRAME 20 AT THE WING ATTACH POINT. LT CRACK IS APPROX 1.0 INCHES IN LENGTH, RT CRACK IS APPROX .75 INCHES IN LENGTH. 2L72 4F A10CE 20060522002052006052200205SW 2006 5 22 YTRR109168 120060504G6520206033426001A GEARBOX BELL 206 206L4 1182110SW TAIL ROTOR CRACKED B YTRRK NONE O OTHER ININSP/MAINT 1 SW03410RL1387 52310 52310 DURING ROUTINE 100-HOUR AIRFRAME INSPECTION, FOUND TAIL ROTOR GEARBOX CASTING CRACKED. 1G71 3U NCH2SW 20060330001002006033000100EA 2006 3 30 ZB0R200600001 220060309G8530 CYLINDER PIPER PA28 PA28R200 7102811SO LYC O360 O360C1C 41514EA ENGINE SEPARATED B ZB0RE ENGINE SHUTDOWN E VIBRATION/BUFFET TXTAXI/GRND HDL 1 SO0515143 28R7335027 L958451A ON RUN-UP, PILOT AND INSTRUCTOR FELT ENGINE VIBRATION. MAG DROPS WERE GOOD. AIRPLANE WAS TAXIED TO MAINTENANCE. MECHANIC FOUND NR 3 CYLINDER WITH 4 BROKEN MOUNT STUDS AND OIL COMING FROM EXHAUST. CYLINDER REMOVED AND REPAIRED BY ENGINE SHOP. ENGINE INSPECTION REVEALED NO FURTHER DAMAGE. SUSPECT DETONATION AS CAUSE. 1L71 3O3 O 2A13 E286 20060807002412006080700241SO 2006 8 7 ZB0R20060001 120060725G324216402000 BRAKE DISC PIPER PA28 PA28236 7102815SO RT MLG BROKEN B ZB0RO OTHER O OTHER TXTAXI/GRND HDL 1 SO05270SW 25 287911118 ON LANDING ROLLOUT, PILOT LOST RIGHT BRAKING. MAINT DISCOVERED RIGHT BRAKE DISK BROKEN AT WELD COMPLETELY AROUND CIRCUMFERENCE. SUSPECT CORROSION ATTRIBUTED TO WELD FAILURE. PART REPLACED BY MAINT. 1L71 3O 2A13 20061020000962006102000096CE 2006 10 20 ZB0R20060002 120061016G32420500118127 LINE CESSNA172 172S 2072439CE BRAKE SYSTEM CORRODED B ZB0SO OTHER S AFFECT SYSTEMS NRNOT REPORTED 1 SO053513K1147 15 172S8917 DURING PREFLIGHT, PILOT NOTICED HYD FLUID COMING FROM RT BRAKE AREA. REPORTED TO MAINTENANCE. FOUND RT BRAKE LINE LEAKING. REMOVED LINE AND DISCOVERED PINHOLE CORROSION UNDER CHAFE PROTECTOR AT LOWER BEND OF LINE. SUSPECT WATER ENTERED CHAFE PROTECTOR AND CAUSED CORROSION. THE CHAFE PROTECTOR SHOULD BE SEALED AT EACH END TO PREVENT MOISTURE FROM ENTERING. REPLACED PART - OPS CK OK. 1H71 3O NT3A12 20061204001092006120400109SO 2006 12 4 ZB0R20060003 120061120G272067174000 BAR PIPER PA28 PA28R200 7102811SO RUDDER PEDALS CRACKED B ZB0RK NONE O OTHER ININSP/MAINT 1 SO05151434068 48 28R7335027 DURING PROGRESSIVE INSPECTION, FOUND PILOT LT RUDDER BAR CROSS-OVER JOINT CRACKED AT WELD. 1L71 3O 2A13 20060203000822006020300082WP 2006 2 3 ZN3R556712 220060103G723030745557 STATOR CESSNA650 650 2076802CE GARRTTTPE731TFE7313C WP SEPARATED B K NONE O OTHER ININSP/MAINT 1 WP07650TA2556 6500088 P87152C ENGINE 4TH LPC STATOR HAD INNER RING FRACTURE, LEADING TO A SINGLE VANE SEPARATING FROM THE STATOR ASSEMBLY. THE VANE CAUSED DAMAGE TO THE HPC AREA OF THE ENGINE. AIRCRAFT DID NOT EXPERIENCE ANY PROBLEMS WITH ENGINE DURING FLIGHT, AND PERFORMED SCHEDULED LANDING WITHOUT INCIDENT. 2L72 4F4 F A9NM E6WE