U/A Canada PT6A-27
Service difficulty reports · 642
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 = 'PT6A27' 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 = 'PT6A27' 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 CA060425019Skin · crackedVISUAL 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 WASSDR CA060920007Generator · shorted(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)SDR CA060425005Engine · power lossDURING 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.SDR CA060330005Mount · mismanufactured(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,SDR 2006FA0000335Sleeve · shiftedOPERATOR 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 HADSDR CA060403012Bleed Valve · faultyDURING 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.SDR 2006FA0000245Engine · making metalLT 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)SDR CA060210001Fitting · cracked(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 WSDR CA060227016Engine · power lossDURING 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.SDR CA060123004Window · missing(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 THESDR CA060228015Mount · damagedDURING 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 RIVSDR CA060227024Mount · detachedUPPER 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 BOROSCSDR 2006FA0000090Plate · crackedDURING 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 CRACKINGSDR CA061201005Rib · cracked(CAN) WHILE PERFORMING AD CF-82-21 R1 USING A BORESCOPE, CRACKS WERE FOUND AT THE ATTACHMENT POINT OF THE TORQUE TUBE TO THE ELEVATOR RIB. SEE PHOTOS AND DAMAGE REPORT. (TC NR 20061201005)SDR CA060127008Bolt · seized(CAN) UPON SCHEDULED REMOVAL OF LOANER ENGINE FOR RETURN TO MFG, 2 OF THE TOP MOUNT BOLTS WERE DISCOVERED TO BE SEIZED IN PLACE. ENGINE WAS RETURNED TO MFG WITH MOUNT IN PLACE FOR THEM TO REMOVE. THIS IS THE SECOND OCCURANCE OF THIS PROBLEM WITHIN OUR COMPANY,SDR AU510002187Retaining Ring · missingENGINE PROPELLER SHAFT ADAPTER PLUG RETAINING RING MISSING. ADAPTER PLUG P/N 3013146 DISLODGED AND LOOSE IN THE PROPELLER SHAFT INTERNAL BORE. RETAINING RING COULD NOT BE FOUND. SUSPECT RETAINING RING HAD NOT BEEN INSTALLED. PERSONNEL/MAINTENANCE ERROR. ASDR CA051124006Adapter · cracked(CAN) DURING MAINTENANCE CHECK, A CRACK WAS FOUND ON THE AFT END FLANGE OF THE ADAPTER. THE ADAPTER WAS REPLACED IAW RD6-57-266 BUT IT WAS FOUND THAT THE LOCK FASTENER COULD NOT BE INSTALLED AT 1 LOCATION DUE TO INTERFERENCE WITH INTERNAL STRUCTURE. OTHER FASTSDR CA051124008Rib · cracked(CAN) DURING MAINTENANCE CHECK THE RIB WAS FOUND TO BE CRACKED IAW ATTACHMENT. RIB WAS REPLACED.SDR TIM2005F00013Engine · failedAIRCRAFT IN FLIGHT AT 13000 FT OIL PRESSURE AND TORQUE STARTS TO FLUCTUATED SLIGHTLY, MOMENTS LATER THE ENGINE FAILED. NO CAUSE FOR FAILURE HAS BEEN FOUND AT THIS TIME. THE ENGINE HAS BEEN TAGGED. THE ENGINE HAS 87.5 HOURS SINCE REPAIRS TO THE ENGINE AT AN SDR TIM2005F00011Ground Wire · corrodedLANDING GEAR FAILED TO EXTEND. INSPECTION FOUND A CORRODED GROUND WIRE. THE FAILURE WAS INTERMITTENT THIS CAUSED CONSIDERABLE TROUBLE IN THE TROUBLESHOOTING AND SEVERAL HOURS OF TIME TO REPAIR THE PROBLEM. (K)SDR AU510001605Fuel Sys · faultyFUEL SYSTEM SUSPECT FAULTY. LIMITED INFORMATION PROVIDED.SDR CA051116007Reservoir · cracked(CAN) FLUID WAS DRIPPING FROM THE HYD AREA.OPON INSPECTION IT WAS NOTICED THAT THE TANK WAS CRACKED ALONG THE FILLER NECK.SDR 2005FA0001571Rib · crackedLT ELEVATOR WAS FOUND CRACKED BEHIND ELEVATOR BALANCE WEIGHT AT THE OB END OF THE ELEVATOR. UPON FURTHER INVESTIGATION IT WAS DISCOVERED THAT THE BALANCE WEIGHT WAS MODIFIED TO INCREASE THE WEIGHT. THE ADDED WEIGHT WAS DETERMINED TO BE INSTALLED BECAUSE THE SDR CA050928002Longeron · cracked(CAN) WHILE CARRYING OUT THE LOWER LONGERON INSPECTION IAW AD CF 81-07R4 AND SB 6/509, THE LT IB LONGERON ON THE RT NACELLE WAS FOUND CRACKED LATERALLY ACROSS THE WEB. THE CRACK WAS JUST AFT OF THE ENGINE MOUNT.SDR CA050831007Turbine Blades · damaged(CAN) DURING CRUISE, THE ENGINE WAS REPORTED TO SURGE AND EMIT LOUD NOISES. THE PILOT SHUT THE ENGINE DOWN IN FLIGHT. A SUBSEQUENT RE-LIGHT ATTEMPT WAS UNSUCCESSFUL AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE. SUBSEQUENT INSPECTION REVEALED POWER TURBINSDR CA050824017Engine · lack of lube(CAN) IN CLIMB, ENGINE TORQUE WAS REPORTED TO FLUCTUATE FOLLOWED BY WHITE SMOKE EMANATING FROM THE EXHAUST. THE ENGINE WAS SHUT DOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED LOW ENGINE OIL QUALITY AND TORSION DAMAGE OF THE EXHAUST CASE. THE ENGINE HAD BEENSDR TIM2005F00009Fire Detector · false indicationTHE RT ENGINE FIRE DETECTION LIGHT CAME ON BRIEFLY ON FINAL APPROACH TO THE AIRPORT. THE RT ENGINE WAS RECENTLY CHANGED AND WAS WASHED TO CHECK FOR POSSIBLE OIL LEAKS. WATER FROM THE WASH CAN ENTER THE ENGINE FIRE DETECTORS AND CAUSE FALSE FIRE WARNINGS. THSDR YDA2005F00001Cover · burnedTHE RT ENGINE WAS REPORTED TO BE THROWING SPARKS OUT THE LOWER PORTION OF THE COWL. UPON INVESTIGATION, THE STARTER GEN WAS FOUND TO HAE BURN SPOTS ON THE BRUSH BAND COVER. THE STARTER GEN WAS REMOVED AND A SERVICEABLE STARTER GEN WAS INSTALLED. UPON FURTHESDR CA050728003Friction Ring · wornDURING INSPECTION, THE FAN WAS FOUND TO HAVE MOVED AFT CONTACTING THE FAN HOUSING. BOTH THE FAN AND HOUSING WERE DAMAGED. THE FRICTION RING AT THE FWD END OF THE SHAFT WAS FOUND COMPLETELY WORN OUT. SUSPECT MIS-ALIGNMENT OF THE GENERATOR INSTALLATION CAUSINSDR CA050801001Duct · leakingWHEN TROUBLESHOOTING A HIGH ENGINE TEMPERATURE PROBLEM, IT WAS DISCOVERED THAT THE BLEED AIR DUCT COMING OFF THAT ENGINE WAS LEAKING THROUGH A CRACK IN THE FLEXIBLE BELLOWS SECTION OF THE DUCT, WHICH IS NOT VISIBLE UNDER THE DUCT'S SHIELD. THE CRACK WAS DETECSDR CA050623003Flex Drive · seized(CAN) A FEW MINUTES AFTER DEPARTURE, THE FLIGHT CREW NOTICED A BURNING ODOR FOLLOWED BY SMOKE EMITTING FROM THE GLARESHIELD. ON INVESTIGATION BY MAINTENANCE, THE FLEX DRIVE BETWEEN THE WIPER MOTOR AND PILOT CONVERTER WAS FOUND TO BE OVERHEATING AND MELTED A POSDR CA050615008Torque Tube · cracked(CAN) UPON REMOVAL OF AIRCRAFT TAILCONE FOR OTHER MAINTENANCE, LT ELEVATOR TORQUE TUBE WAS DISCOVERED CRACKED. CRACK PROPAGATED FROM UNDER ELEVATOR MOUNTING FLANGE FITTING, EMANATING FROM TAPER PIN HOLE. WITH TAPER PINS REMOVED AND FITTING SLID BACK, ONLY THESDR CA050527022Engine · leakingDURING CRUISE, THE ENGINE LOW OIL PRESSURE WARNING ANNUNCIATED AND THE PILOT SHUT THE ENGINE DOWN IN FLIGHT. THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE. SUBSEQUENT INSPECTION REVEALED OIL LEAKAGE FROM THE NR 3 BEARING SEAL AREA.SDR CA050513001Skin · debondedDURING INSTALLATION OF A REPAIR DOUBLER INBOARD OF THE RT NACELLE AS PER RD6-57-618 IT WAS FOUND THAT 3 AREAS OF DISBOND HAD OCCURRED BETWEEN THE UPPER WING SKIN AND THE CORRUGATION . AS PER INSTRUCTIONS IN THE REPAIR DEFINITION THE MANUFACTURE WAS CONTACTED ASDR CA050509005Plate · torn(CAN) UPON ENTERING CRUISE FLIGHT, THE PILOT HEARD A LOUD BANG AND FELT THE AIRCRAFT SHUTTER. HE NOTICED THAT THE RT SKI HARNESS HAD COME UNATTACHED TO THE UPPER WING ATTACH FITTING, LETTING THE RT SKI ROTATE UPWARD AGAINST THE WING STRUT. THE PILOT TOOK MEASSDR VNW2005F00000Universal Joint · failedUPON DEPARTURE, CREW NOTICED LANDING GEAR INTRANSIT LIGHT ILLUMINATED. THE CREW FOLLOWING EMERGENCY PROCEDURES IT WAS NOTICED THAT THE RT MLG DOWN AND LOCKED DID NOT INDICATE. FLIGHT CREW USED EMERGENCY EXTENSION AND STILL HAD NO RT MLG DOWN AND LOCKED INDICSDR TIM2005F00004Fire Detector · contaminatedTHE FIRE DETECTOR WARNING LIGHT ILLUMINATED IN FLIGHT. MOISTURE WAS THE PROBABLE PROBLEM. AFTER TAXI THE LIGHT EXTINGUISHED. NOT OTHER PROBLEM WITH FIRE DETECTION SYSTEM WAS FOUND. (K)SDR CA050408012Washer · missing(CAN) SERVICING THE NOSE OLEO, THE ENGINEER NOTICED THAT THE FORK WAS LOOSE ON THE STRUT. REMOVAL OF THE STRUT REVEALED THAT IT WAS ASSEMBLED INCORRECTLY. THE WASHER P/N 71-309-9 WAS MISSING AND THAT EXTRA PEEL ABLE SHIMS HAD BEEN ADDED. THE SHIMS ARE A SMASDR CA050408003Collar · sheared(CAN) ON AIRCRAFT ARRIVAL AT YZF, THE CREW REPORTED LOSS OF NOSE WHEEL STEERING. INVESTIGATION BY MAINTENANCE STAFF REVEALED THAT THE NWS COLLAR P/N 71-161-11 WAS SHEARED OFF. THE ENTIRE NOSE GEAR ASSEMBLY WAS REPLACED AND THE SURROUNDING AREA WAS INSPECTED SDR CA050329007Drive Assy · malfunctioned(CAN) FRENCH AUTHORITIES HAVE REPORTED AN INFLT SHUTDOWN WITH INDICATIONS OF A FUEL PUMP DRIVE MALFUNCTION.SDR AU510001604Panel · mismarkedNO LABELS ON DUAL RADIOS/INDICATORS AND ADVISORY LABELS AS REQUIRED BY ANO 108.34 SECTION 6.2.SDR CA050224007Hinge Bracket · corroded(CAN) CORROSION FOUND UNDER BLOCK. WHILE INSPECTING CENTER HINGE BRACKET IAW SB 6/512. CORROSION VISIBLE ON SURFACE SURROUNDING BLOCK. BLOCKS REMOVED FOR FURTHER INSPECTION AND EXFOLIATION/CORROSION FOUND UNDER BOTH SIDES.SDR CA060109003Collar · incorrectTHE STEERING COLLAR WAS ASSEMBLED AT THE FACTORY INCORRECTLY. THERE ARE TWO DISCS WHICH ARE ATTACHED TO THE COLLAR. ONE DISC IS BARE METAL AND IS SUPPOSED TO BE AT THE SIDE THAT IS FACING THE STRUT TOUCHING THE FRICTION DISC (WHICH IS GLUED TO THE STRUT ITSELSDR 2005FA0000675Compressor · stalledLT ENGINE PRODUCED A SERIES OF SOUNDS INDICATIVE OF COMPRESSOR STALL WHEN LEVELED AT FL190. TORQUE RAPIDLY DIMINISHED AND TEMPERATURE ROSE. PILOT SHUTDOWN ENGINE AS A PRECAUTION. ENGINE REMOVED AND SENT FOR ANALYSIS. (K)SDR LJJ2005F00000Strap · corrodedCORROSION FOUND AT HOLE B, LWS 90.35, DURING INSPECTION OF LT S AND K SPAR STRAP. DER WAS CONSULTED FOR REPAIR. RECOMMEND CLOSE INSPECTION OF HOLES DURING REPETITIVE INSPECTIONS. ALSO RECOMMEND THE USE OF AN ANTI-CORROSION LUBRICANT DURING BOLT INSTALLATIONSDR LJJ2005F00001Spar · corrodedCORROSION FOUND AT HOLE B, LWS 90.35, DURING INSPECTION OF LT S AND K SPAR STRAP. DER WAS CONSULTED FOR REPAIR. RECOMMEND CLOSE INSPECTION OF HOLES DURING REPETITIVE INSPECTIONS. ALSO RECOMMEND THE USE OF ANTI-CORROSION LUBRICANT DURING BOLT INSTALLATION. (SDR CA041216001Cable · misinstalled(CAN) NOSE WHEEL STEERING CABLE ROUTED INCORRECTLY RESULTING IN ALMOST SAWING THROUGH THE HYDRAULIC HAND PUMP SUCTION LINE P/N C6H1001-294.SDR CA041216003Bolt · sheared(CAN) AT ENGINE REMOVAL 3 OF THE 4 TOP ENGINE MOUNT BOLTS PN CSP282-29 BOLT FAILED. THE HEADS SHEARED OFF AFTER APPROXIMATELY 3/1 - 1.25 TURN(S) OF THE BOLT. (TC NR 20041216003)SDR CA041216004Bolt · sheared(CAN) AT ENGINE REMOVAL, ONE OF THE TOP ENGINE MOUNT BOLTS P/N CSP282-29 BOLT FAILED. THE HEADS SHEARED OFF AFTER APPROXIMATELY A .7500 TURN OF THE BOLT. REVIEWED (TC NR 20041216004)SDR AE1Structure · failedFAILURE OF ELEVATOR ATTACH POINT AND OR HARDWARE. ACTUAL CAUSE IS UNKNOWN BECAUSE THE ELEVATOR HAS NOT BEEN LOCATED FOR RECOVERY.
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