U/A Canada PT6A-34
Service difficulty reports · 465
Newest first. General aviation reporting is voluntary.
Query with SQL
duckdb -csv -c "SELECT sdr_id, difficulty_date, n_number, aircraft_make, aircraft_model, part_name, part_condition, jasc_code, discrepancy FROM 'https://openairdocs.org/data/latest/faa_service_difficulty_report.parquet' WHERE engine_model_key = 'PT6A34' ORDER BY difficulty_date DESC"
Prints the whole list as CSV. It reads the release’s Parquet files over HTTPS, so there’s nothing to download first. Install DuckDB to run it.
SELECT sdr_id, difficulty_date, n_number, aircraft_make, aircraft_model, part_name, part_condition, jasc_code, discrepancy FROM 'https://openairdocs.org/data/latest/faa_service_difficulty_report.parquet' WHERE engine_model_key = 'PT6A34' ORDER BY difficulty_date DESC
Run it at the DuckDB prompt, or in any tool that reads Parquet over HTTPS. More ways to query the release are on Use the data.
SDR CA110428011Rod · loose(CAN) REMOVED RUDDER ROD ASSY TO REPLACE FOWARD ROD END AND UPON CLOSER INSPECTION FORWARD ATTACH FITTING RIVETS WERE FOUND TO BE LOOSE. REPLACED LOOSE RIVETS.SDR CA110414008Fitting · damaged(CAN) ON AN AMPHIBIOUS FLOAT EQUIPPED ACFT, THE PILOT REPORTED THAT HE HEARD AND FELT A SLIGHT BANG WHICH FELT LIKE THE WATER RUDDERS HAD FALLEN DOWN AS SOON AS HE LEVELED OFF AFTER TAKE-OFF. AFTER THE INITIAL BANG, THE ACFT FELT AND SOUNDED NORMAL. UPON LANDSDR CA110323009Link · worn(CAN) DURING A 200 HR INSPECTION OF THE AMPHIBIAN FLOATS, IT WAS IDENTIFIED THAT THERE WAS CONSIDERABLE SLOP AT THE TOP LT FWD NOSE GEAR POSITION. WHEN THE NOSE GEAR LEG WAS DISASSEMBLED IT WAS FOUND THAT THE NOSE RAM LINK FITTING PN 6A07204-001, FWD HOLES WERSDR CA110324009Torque Shaft · separated(CAN) THE TORQUE SHAFT SEPARATED IN THE LOCATION OF THE UPPER MOUNT BOLT AFTER 65 HRS IN SERVICE. JL PG 004102 & 004129. ANPHIB INSTALLATION ON ACFT.SDR CA110303005Circuit Board · smoke(CAN) DURING A WALK AROUND, THE PILOT TURNED ON THE COCKPIT LIGHTS. SMOKE WAS EMITTED FROM THE PEDESTAL, BATTERY POWER WAS TURNED OFF. MAINTENANCE INVESTIGATED AND FOUND THAT THE SMOKE WAS CAUSED BY A BURNED WHEAT, BULB, PN D158/-100-5T1 ON THE PITCH TRIM LIGSDR CA110228019Oil System · failed(CAN) IFSD, SINGLE ENGINE, DURING A FLIGHT, THE PILOT NOTICED AN OIL PRESSURE DROP AND ELECTED TO SHUT THE ENGINE DOWN BEFORE LANDING IN A FIELD 20 KM NORTH. ASSISTANCE WILL BE OFFERED TO THE LOCAL AUTHORITIES (AAIB). ENGINE MFG WILL INVESTIGATE TO ESTABLISHSDR CA101104010Line · damaged(CAN) ON AN AMPHIBIOUS EQUIPPED AIRCRAFT, THE PILOT REPORTED A PROBLEM WITH THE WHEEL GEAR, THAT IT DID COME DOWN BUT THAT THE PUMP WOULD KEEP RUNNING. UPON INSPECTION BY MAINTENANCE PERSONNEL, A BLISTER WAS NOTED IN THE BLACK PLASTIC COVERING THE HYDRAULIC FSDR EVGR20101005Pump · leaking(EGVR) FUEL PUMP SEAL FAILED, WASHING OUT BLUE DYE FROM THE BEARING. DYE WAS FOUND COMING OUT THE FUEL PUMP /FCU DRAIN LINE.SDR EVGR20101006Fcu · leakingBRG GREASE WAS WASHED OUT DUE TO FUEL PUMP SEAL FAILURE. BLUE DYE WAS FOUND IN THE DRAIN BETWEEN THE FUEL PUMP AND FUEL CONTROL UNIT.SDR 2010FA0001074Pump · leakingFUEL PUMP SEAL LEAKAGE THAT LED TO FCU BEARING GREASE WASHOUT. DISCOVERED BY OBSERVING BLUE DYE COMING FROM WITNESS HOLE IN BOTTOM OF FCU.SDR 2010FA0001079Fcu · leakingFUEL PUMP SEAL LEAKAGE THAT LED TO FCU BRG GREASE WASHOUT. DISCOVERED BY OBSERVING BLUE DYE COMING FROM WITNESS HOLE IN BOTTOM OF FCU.SDR CA100831011Brake Pads · missingDURING DAILY INSP, THE LT BRAKE UNIT WAS NOTICED TO HAVE THE AFT INBD BRAKE PAD MISSING.SDR CA100907008Strut · crackedWING STRUT FITTING, LT, UPPER PN D3081-6L. DURING A SCHEDULED INSP, A SUSPECTED CRACK WAS NOTED ON THE UPPER LINK, INNER FACE, EMANATING FROM BUSHING HOLE. AN EDDY CURRENT INSP WAS PERFORMED ON THE SUSPECTED AREA AND IT WAS CONFIRMED THAT THE AREA WAS CRACKESDR CA100819006Hinge Bracket · crackedDURING INSP, IT WAS NOTICED THAT THERE WERE LOOSE/SMOKING RIVETS ON THE AFT PART OF THE CABIN DOOR AT THE HINGE LOCATION. THE HINGE WAS REMOVED AND THE DOOR WAS FOUND TO BE CRACKED ACROSS THE RIVET HOLES OF THE HINGE SUPPORT. THE CRACK STARTED AT THE AFT ENDSDR CA100806001Engine · hot startEXPERIENCED HOT START IN FACTORY NEW ENGINE WITH LESS THAN 100 HRS TT SINCE NEW. UNABLE TO FLY ACFT BACK TO BASE, DUE TO PERSISTENT HOT START CONDITION. OPENSDR CA100726016Control Cable · loose(CAN) DURING A SPECIAL INSP, THE RT ENGINE IDLE CABLE WAS FOUND TO HAVE EXCESSIVE PLAY IN THE SWAGED END (THE ENGINE END). THE CABLE WAS REPLACED AND ACFT RETURNED TO SERVICE. THIS SPECIAL INSP WAS COMPLETED DUE TO HAVING FOUND A FAILED CABLE ON THE LT ENGINESDR CA100726001Engine · power lossACCIDENT: WHILE CONDUCTING AGRICULTURAL SPRAYING OPERATIONS, THE ACFT EXPERIENCED AN UNCOMMANDED RETURN TO FLIGHT IDLE OF THE ENGINE THAT WAS UNRECOVERABLE RESULTING IN THE ACFT CRASHING INTO A DITCH EMBANKMENT LINED BY TREES THAT SEPARATED 2 FIELDS. MFG WILL SDR CA100903004Engine · failedACCIDENT WHILE CONDUCTING AGRICULTURAL SPRAYING OPERATIONS, THE ACFT EXPERIENCED AN UNCOMMANDED RETURN TO FLIGHT IDLE OF THE ENGINE THAT WAS UNRECOVERABLE RESULTING IN THE ACFT CRASHING INTO A DITCH EMBANKMENT. UPDATE NR 1: INVESTIGATION PERFORMED ON 17 AUG. SDR CA100623004Skin · crackedPILOT REPORTED SLIGHT VIBRATION IN FLAPS. UPON INSP, BEFORE THE NEXT FLIGHT, THE RT AILERON WAS FOUND TO HAVE SIGNIFICANT CRACKING IN MULTIPLE AREAS WITH A PORTION OF THE T/E (APROX 18 INCHES LONG AND 1 INCH FWD) BLOWN OUT. THIS AILERON HAD 118.4 HOURS SINCE SDR 2010FA0000635Strut · leakingAFTER APPROX 65 HOURS SINCE THE NOSE STRUT WAS LAST RESEALED, IT WAS LEAKING BADLY AND NEEDED TO BE RESEALED AGAIN. HYD FLUID WAS COMING FROM THE LOWER GLAND OF THE TRUNNION SUGGESTING THAT THE BOTTOM POLY PACK SEAL WAS LEAKING. AFTER IT WAS DISASSEMBLED, THSDR 2010FA0001075Pump · leakingFUEL PUMP SEAL LEAKAGE THAT LED TO FCU BRG GREASE WASHOUT. DISCOVERED BY OBSERVING BLUE DYE COMING FROM WITNESS HOLE IN BOTTOM OF FCU.SDR CA100617010Cable Assy · separatedAFTER LANDING, THE CREW WAS UNABLE TO SHUTDOWN LT ENGINE USING THE NORMAL PROCEDURES, THE CONDITION LEVER HAD NO EFFECT ON THE ENGINE. THE ENGINE WAS SHUTDOWN USING THE FIREWALL SHUT OFF. WHEN MX INVESTIGATED, IT WAS FOUND THAT THE SWAGED END OF THE LT ENGINESDR CA100622010Engine · power lossPOWER ROLLBACK WITH THE ENGINE POWER AT 90 PERCNET NP AND APPLYING POWER, THE ENGINE ROLLED BACK TO 80 PERCET POWER. THIS IS THE SECOND EVENT ON THIS ENGINE, THE 1ST EVENT WAS REPORTED IN MARCH THIS YEAR. THE POWER SECTION WAS THEN REMOVED AND FORWARDED WHERESDR 2010FA0001076Pump · leakingFUEL PUMP SEAL LEAKAGE THAT LED TO FCU BRG GREASE WASHOUT. DISCOVERED BY OBSERVING BLUE DYE COMING FROM WITNESS HOLE IN BOTTOM OF FCU.SDR 2010FA0001077Seal · leakingFUEL PUMP SEAL LEAKAGE THAT LED TO FCU BEARING GREASE WASHOUT. DISCOVERED BY OBSERVING BLUE DYE COMING FROM WITNESS HOLE IN BOTTOM OF FCU.SDR 2010FA0001078Fcu · leakingFUEL PUMP SEAL LEAKAGE THAT LED TO FCU BRG GREASE WASHOUT. DISCOVERED BY OBSERVING BLUE DYE COMING FROM WITNESS HOLE IN BOTTOM OF FCU.SDR CA100216008Fcu · faulty(CAN) UPON DEPARTURE, THE ENGINE TORQUE INCREASED UNCOMMANDED TO 1500 FT/LB WITH NO RESPONSE TO THROTTLE MOVEMENTS. THE PILOT INITIATED A RETURN TO THE AIRPORT AND THE ENGINE WAS SHUTDOWN DURING FINAL APPROACH. AN UNEVENTFUL DEAD STICK LANDING FOLLOWED. ON TSDR CA091222009Turbine Blades · corroded(CAN) ENGINE WAS RECEIVED FOR INVESTIGATION / REPAIR DUE TO EXCESSIVE SULPHIDATION CORROSION ON CT BLADES. THE CT BLADES ARE OF POST SB 1520R2 CONFIGURATION. THE SB 1520R2 WAS INTRODUCED BY MANUFACTURER TO PROVIDE NEW CT BLADES WITH IMPROVED SULPHIDATION PROSDR CA100105005Mount · cracked(CAN) DURING AN INDEPENDENT CONTROL CHECK OF THE RT ENGINE, IT WAS NOTED THAT THE OIL TO FUEL HEATER SEEMED LOOSE ON ITS MOUNT. FUEL HEATER WAS REMOVED FROM THE ENGINE AND INSPECTED. BOTH MOUNTING FLANGES OF FUEL HEATER WERE CRACKED. IT IS NOT KNOWN HOW THIS SDR CA091223001Skin · cracked(CAN) BOTH WINGS, CORRUGATED INNER SKIN CRACK AT MANY PLACES BETWEEN STATION 47.50 THRU 122.50 AND RIBS DAMAGE AT RIVETS JOINT. MANY RIVETS POPPED AT RIBS AND CORRUGATED INNER SKIN JUNCTION. TCCA COMMENTS: AAIR FROM JUL 15/09 SHOWS THAT AIRCRAFT HAS 29411 HSDR CA091201005Structure · cracked(CAN) PILOT REPORTED VIBRATION IN LT FLAP AFTER SECOND FLIGHT OF THE DAY. UPON INSPECTION BY MAINTENANCE PERSONNEL, CRACKS WERE FOUND ON THE LT FLAP. THE CRACKS WERE LOCATED ON THE TOP OF THE FLAP TOWARDS THE LEADING EDGE ON BOTH THE RT SIDE OF THE FLAP AND SDR CA091222001Bellows · faulty(CAN) THE ENGINE POWER COULD NOT BE REDUCED TO FLIGHT IDLE. THE PROBLEM WAS ISOLATED TO THE FUEL CONTROL UNIT ON WHICH THE ACCELERATION BELLOWS WAS FOUND FAULTY. HARDWARE BE RETURNED FOR INVESTIGATION. MANUFACTURER WILL INVESTIGATE TO ESTABLISH ROOT CAUSE ASDR CA090910002Spar · crackedAPPROX 2 INCH VERTICAL CRACK IN UPPER END OF SPAR WEB AT UPPER HINGE FITTING. UPPER FITTING LOOSE ON RIB - HINGE PIN LOOSE IN FITTING. CRACK IN SPAR NOT READILY VISIBLE UNTIL RUDDER IS REMOVED. PROBABLY A RESULT OF HIGHER AIRSPEEDS WITH TURBINE POWERED OTTER.SDR CA090910003Bolt · crackedIGX POWER VISUAL INSP OF NAS BOLT - CRACKED (APPARANT) UNDER HEAD IN RADIUS. IPC DOES NOT INDICATE A CHAMBERED WASHER TO BE INSTALLED AS IS INDUSTRY PRACTICED WITH NAS BOLTS. NOTE THERE IS NO CHAMBER ON THE FITTINGS PN C3TF6-3. BOTH ATTACH BOLTS TO BE REPLASDR CA090827004Fitting · brokenWHILE DOING A WATER LANDING. PILOT HEARD A LOUD POP ON LANDING. HE TAXIED TO THE DOCK WITH OUT ANY TROUBLES, UPON INVESTIGATION HE FOUND THAT THE FWD DRAG WIRE FITTING PN 9A02066-005 HAD BROKEN AT THE CLEVIS PIN END. ALL OTHER FITTINGS WERE INSPECTED AND DRSDR CA091021002Screw · binding(CAN) THE PILOT REPORTED THAT THE ELEVATOR TRIM WOULD SEEM TO TIGHTEN UP WITH AIR LOAD ON IT. AFTER INSPECTING THE TRIM SYSTEM, IT WAS DETERMINED THAT THE TRIM SCREW JACK AT THE ELEVATOR WAS HARD TO TURN UNDER LOAD. THE PART WAS DISASSEMBLED, CLEANED AND GREASSDR CA090707003Bleed Valve · noisy(CAN) AFTER 382.2 HRS IN ACFT, BLEED VALVE STARTED TO MAKE A HOOTING NOISE AND ALSO PRODUCED VIBRATIONS. ABOVE SYMPTOMS WERE ONLY SEEN ON PWR REDUCTIONS. THERE WAS A SERVICEABLE BLEED VALVE INSTALLED FROM ANOTHER ACFT AND PROBLEM WAS RESOLVED.SDR CA090622008Bleed Valve · inoperative(CAN) AFTER 9.9 HRS IN ACFT, BLEED VALVE STARTED TO MAKE A HOOTING NOISE AND ALSO PRODUCED VIBRATIONS. ABOVE SYMPTOMS WERE ONLY SEEN ON POWER REDUCTIONS. BLEED VALVE WAS REPLACED WITH A SERVICEABLE UNIT WHICH CORRECTED THE DEFECT.SDR CA090622009Bleed Valve · inoperative(CAN) AFTER 3.7 HRS IN ACFT, BLEED VALVE STARTED TO MAKE A HOOTING NOISE AND ALSO PRODUCED VIBRATIONS. ABOVE SYMPTOMS WERE ONLY SEEN ON POWER REDUCTIONS. ORIGINAL BLEED VALVE, WHICH HAD TIME REMAINING ON IT WAS REINSTALLED AND THE PROBLEM WAS RESOVLED.SDR CA090609003Bracket · cracked(CAN) DURING A SCHEDULED INSP CRACKS WERE FOUND ON THE RT OTBD FLAP INBD TRACK (LOWER ATTACHMENT) BRACKETS. FURTHER INSP REVEALED THAT THE LWR 2 RIVETS ON EACH OF THE FWD ATTACHMENT BRACKETS WERE NO LONGER HOLDING, 3 RIVETS WERE SHEARED AND THE SECOND RIVET FRSDR CA090505001Hinge Bracket · loose(CAN) AS PART OF A 500 HR AILERON BEARING INSP, IT WAS NOTICED THAT THE AILERON HINGES WERE LOOSE WHERE THEY ATTACHED TO THE BRACKETS THAT ATTACHED THEM TO THE WING. THE RIVETS HAD LOOSENED UP OVER TIME AND ALLOWED THE HINGE TO MOVE SLIGHTLY IN ATTACH BRACKETSSDR CA090421014Control Column · cracked(CAN) UPON ROUTINE INSP OF THE AD CF-82-34 FOUND CRACKS ON THE LOWER CONTROL COLUMN ADJACENT TO THE WELDS. CONTROL COLUMN WAS REPLACED PN C3CF48 AND ACFT WAS RETURNED TO SERVICE.SDR CA090305013Duct · cracked(CAN) DURING A DAILY INSP AN AME FOUND THE ENGINE OIL TO BE DIRTY AND IT HAD A YELLOWISH COLOR. FURTHER INSP OF THE ENGINE REVEALED A CRACKED INNER EXHAUST OUTLET DUCT. THE ENGINE WAS REPLACED AND THE ACFT RETURNED TO SERVICE.SDR CA090304009Engine · inoperative(CAN) IT WAS REPORTED THAT DURING AN ATTEMPTED EMERGENCY LANDING, ACFT CRASHED IN THE RIVER CLOSE TO THE DESTINATION AIRPORT. THERE ARE 4 CONFIRMED SURVIVORS. WRECKAGE HAS BEEN RECOVERED FROM THE RIVER AND TRANSPORTED TO THE CITY, WHERE PRELIMINARY EXAMINATIONSDR CA090105002Window · failed(CAN) AT 16000 FT LEVEL CRUISE, WINDOW FAILURE OCCURRED, COMPLETE WINDOW FAILED LEAVING ONLY APPROX 2 INCHES OF WINDOW ATTACHED TO AIRFRAME WINDOW SEAL STAYED ATTACHED TO AIRFRAME. CRAZING, PITS AND SCRATCHES REMOVED FROM WINDOW FEB 10, 2000, WINDOW MEASUREDSDR CA081222001Circuit Breaker · unserviceable(CAN) THE FLIGHT CREW REPORTED THE 35 AMP HYDRAULIC PUMP CIRCUIT BREAKER POPPED. THEY ELECTED TO RETURN TO BASE AND USED HYDRAULIC HAND PUMP FOR BRAKE OPS. MX TROUBLESHOT THE SYSTEM, REPLACED 35 AMP CIRCUIT BREAKER, GROUND TESTED THE SYSTEM, AND RETURNED THESDR CA081118003Lock Tab · cracked(CAN) FCU FUEL CONDITION LEVER LOCK SPRING TAB THAT IS USED TO PREVENT THE LEVER MOVING TO FUEL CUT-OFF HAS FAILED.SDR CA081030002Seal · wrong part(CAN) THIS PROBLEM WAS IDENTIFIED WHILE CARRYING OUT ROUTING MX ON AMPHIBIAN FLOAT MAIN WHEELS. THE MFG PARTS BOOK SPECIFIED WHEEL GREASE SEAL THAT WHEN INSTALLED WERE 0.010 TOO SMALL OF A DIAMETER, CAUSING THE SEAL TO FALL OUT OF POSITION. HAVE CONTACTED THSDR CA081125014Pump · damaged(CAN) OVERHAULED FUEL BOOST PUMP MAKING GRINDING NOSE WHEN TURNED ON. PUMP REMOVED AND REPLACED WITH OVERHAULED BOOST PUMP. FAILED PUMP HAD ONLY 6.1 HOURS TIME IN SERVICE SINCE OVERHAUL AND 5 FLIGHT CYCLES. FAILED PUMP RETURNED TO INSTALLER.SDR CA080917002Support · cracked(CAN) WHEEL ASSEMBLIES AND BRAKES REMOVED FOR INSPECTION AND REBUILD. IT WAS DISCOVERED THAT THE AXLE SUPPORT BODIES ON BOTH MAIN GEAR ASSEMBLIES HAD CRACKS AND REQUIRED REPLACEMENT. THIS WAS FOUND ON A 200 HR. INSPECTION.
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