U/A Canada PT6A-41
Service difficulty reports · 717
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 = 'PT6A41' 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 = 'PT6A41' 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 AUS20040115Frame · cracked(AUS) FUSELAGE FRAMES (3OFF) LOCATED AT STN 285.188, STN 278.5 AND STN291.875 CRACKED. FRAME PART NUMBERS PN 101-440091-33, PN 101-440090-27 AND PN 101-440092-31. FOUND DURING INSPECTION IAW AD.SDR AUS20040150Fire Detector · faulty(AUS) LT ENGINE FORWARD UPPER FIRE DETECTOR SUSPECT FAULTY.SDR UJJ2004F00000Adapter · crackedWHILE INVESTIGATING CABIN PRESSURE LEAKS, IT WAS FOUND THAT BOTH AFT PRESSURE BULKHEAD RUDDER CARRY THROUGH SEAL ADAPTERS WERE CRACKED IN SEVERAL PLACES. THESE ADAPTERS ARE MADE OF THERMOFORMED (ABS) PLASTIC, RIVETED INTO PLACE USING A METAL DOUBLER, AND HAVESDR CA040224003Rivet · sheared(CAN) BRAKE ASSEMBLY S/N 1544 WAS FOUND WITH THE BRAKE PAD RIVETS SHEARED ALLOWING THE PADS TO BECOME DISLODGED, THIS IS THE SECOND TIME WE HAVE HAD WEAR PADS BEING DISLODGED FROM THE PRESSURE PLATE ASSEMBLY. THIS BRAKE ASSEMBLY WAS IN SERVICE FOR ONE YEAR SISDR CA040212005Channel · cracked(CAN) DURING INSPECTION OF THE DOOR HINGE FOR LOOSE RIVETS, A CRACK WAS DISCOVERED THAT PROPAGATED APPROXIMATELY .7500 THE LENGTH OF THE DOOR CHANNEL. THE DOOR WAS REMOVED AND SENT TO AN APPROVED REPAIR STATION.SDR 2007FA0000421Exhaust Duct · crackedWHILE 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.SDR CA040521007Windshield · failedPILOTS WINDSHIELD INNER PANE SHATTERED WHILE IN FLIGHTSDR AUS20040006Washer · wrong part(AUS) LT AND RT WING LOWER ATTACHMENT BOLT WASHERS INCORRECTLY FITTED. DAMAGE TO BATHTUB FITTING. PERSONNEL/MAINTENANCE ERROR.SDR CA040114004Buss Bar · unserviceable(CAN) PILOTS WERE CARRYING OUT AN ENGINE START ON THE RT ENGINE AND NOTICED THAT THERE WAS NO ITT INDICATION SO THE ENGINE WAS SHUT DOWN. MAINTENANCE TROUBLESHOOTING DETERMINED THE ITT HARNESS WAS SERVICEABLE BUT THAT THE ENGINE INTERNAL BUSSBAR HAD FAILED. TSDR K5LA620JSWindshield · crackedCLIMBING THROUGH 14000 FT IN THE CLOUDS WITH W/S HEAT ON, OAT-5C PILOTS WINDSHIELD OUTER PLY CRACKED ACROSS ENTIRE WINDSHIELD. RETURNED TO AIRPORT AND LANDED. REPLACED WINDSHIELD, NO OTHER DAMAGE NOTED.SDR AUS20031303Frame · cracked(AUS) FUSELAGE FRAMES CRACKED AT FRAME CUTOUTS. FRAME LOCATED AT FS 286.75.SDR AKG2004F00001Windshield · brokenCOPILOTS WINDSHIELD INSIDE GLASS SHATTERED IN FLIGHT AIRCRAFT AND WINDSHIELD.SDR AUS20031320Strap · cracked(AUS) EMERGENCY EXIT DOOR CUTOUT FRAME STRAP AT FS187.375 CRACKED APPROXIMATELY 50 PERCENT THROUGH. CRACK LENGTH APPROXIMATELY 25.4MM(1IN).SDR CA040129007Bracket · cracked(CAN) ELEVATOR FORWARD BALLAST WEIGHT STOP BRACKET AND BOLT FOUND BENT APPROXIMATELY 80 DEGREES FROM ITS ORIGINALLY INSTALLED POSITION. DENTS ON WEIGHT FACE INDICATE STOP BOLT AND BRACKET ASSEMBLY WAS SUBJECTED TO SEVERAL SEVERE CONTROL MOVEMENTS OF THE AIRCRASDR CA031203010Resistor · burned(CAN) ON APPROACH CREW NOTICED SMOKE COMING FROM UNDER THE CAPTAINS INSTRUMENT PANEL. AFTER A UNEVENTFUL LANDING AND INSPECTION OF THE WIRING UNDER THE CAPTAINS INSTRUMENT PANEL WAS CARRIED OUT. FOUND THAT CABIN FLUORESCENT LIGHTING RESISTOR BURNED UP CAUSING SDR CA031128002Chip Detector · broken(CAN) ENG WAS REMOVED AFTER COMPRESSOR SEIZURE AND OIL LOSS DUE TO A BROKEN CHIP DETECTOR. CONFIRMED COMPRESSOR SEIZED. FOUND THAT NR 1 BRG HAD COLLAPSED DUE TO OIL STARVATION. NR 1 BRG FAILURE RESULTED IN HIGH LEVEL OF HEAT GENERATION, LOSS OF COMPRESSOR LOSDR CA031114004Wire Harness · chafed(CAN) A/C DEPARTED, AFTER TAKEOFF, CREW EXPERIENCED A COMMUNICATIONS FAILURE. CREW SQUAKED 7600 & RETURNED FOR LANDING. MAINT TROUBLESHOT COMMUNICATIONS SYS. NR 1 COMM FAILED, REPLACED COMM WITH SERVICEABLE VHF UNIT, COMM NR 1 OPERATING NORMAL. AWAITING STRIPSDR 2004FA0000007Windshield · brokenWHILE AT CRUISE 25,000 FT, WINDSHIELD ON LOW, INNER PANEL OF CO-PILOTS WINDOW SHATTERED. MFG INSPECTED AND DETERMINED FAILURE RESULT ON (CHIP PLY) FAILURE. (NM13PLV200401669)SDR CA031017007Windshield · failed(CAN) CO-PILOTS WINDSHIELD INNER PANE COMPLETELY SHATTERED IN FLIGHT.SDR CA030926002Shaft · cracked(CAN) PILOT REPORTED LACK OF NOSE WHEEL STEERING CONTROL. UPON INSPECTION, THE NOSE WHEEL STEERING SHAFT WAS FOUND CRACKED LONGITUDINALLY BETWEEN BOLT HOLES.SDR AUS20030876Frame · cracked(AUS) FUSELAGE FRAMES PN 1014300263 LT AND PN 10143002611 RT CRACKED. FOUND DURING INSPECTION IAW AD/BEECH200/65 AMDT1.SDR AUS20030870Computer · failed(AUS) FLIGHT DIRECTOR COMPUTER FAILED.SDR K5LA620JSafety Switch · brokenAFTER TAKEOFF, LANDING GEAR FAILED TO RETRACT. GEAR REMAINED DOWN AND LOCKED. AFTER LANDING IT WAS DETERMINED A WIRE ON THE LANDING GEAR EMERGENCY SAFETY SWITCH HAD BEEN BROKEN OFF DURING INSPECTION AND LUBE OF NOSE GEAR CHAIN. JACKING THE AIRCRAFT AND DOINSDR B3OR20033012Flap Track · corrodedDURING A 14 DAY CORROSION INSPECTION THE RIGHT HAND INBORAD FLAP TRACK WAS FOUND TO HAVE DEEP EXIFOLLIATION FLAKING CORROSION ON THE INBOARD SIDE OF THE TRACK.THE FLAKING WAS SEVERE ENOUGH TO CAUSE SEVERAL LAYERS OF FLAKES TO BE PRESENT. THE PART WAS REMOVED ASDR B3OR20033013Flap Track · corrodedDURING A 14 DAY CORROSION INSPECTION THE RIGHT HAND OUTBOARD FLAP TRACK WAS FOUND TO HAVE EXIFOLIATION FLAKING CORROSION ON THE FLAP TRACK. THE FLAKING WAS SEVERE ENOUGH TO CAUSE BUBBLING PAINT AND FLAKING METAL TO BE PRESENT. THE PART WAS REMOVED AND A NEW FLSDR B3OR20033014Flap Track · corrodedDURING A 14 DAY CORROSION INSPECTION THE LEFT OUTBOARD FLAP TACK WAS FOUND TO HAVE EXIFOLIATION FLAKING CORROSION ON THE FLAP TRACK. THE FLAKING WAS SEVERE ENOUGH TO CAUSE SEVERAL LAYERS OF FLAKING METAL TO BE PRESENT. THE PART WAS REMOVED AND A NEW FLAP TRACKSDR CA030826001Door · failed(CAN) DURING DESCENT OUT OF FL270 AND DESCENDING THRU FL240 THE LT WING LOCKER OPENED IN FLIGHT. AIRCRAFT LANDED WITHOUT INCIDENT. WING LOCKER INSPECTED FOR DAMAGE, NO DAMAGED NOTED. TWO LOCKING LATCHES WERE STILL IN THE CLOSED POSITION. AIRCRAFT RETURNED TO BSDR AUS20030732Inverter · burned(AUS) 240 VAC INVERTER BURNED.SDR CA030808002Skin · cracked(CAN) A CRACK IN THE UPPER FUSELAGE SKIN DUE TO VIBRATION PRODUCED BY A GPS/VHF COMBINATION ANTENNA, CRACKS DEVELOPED VERY RAPIDLY IN SKIN & DOUBLER ALONG EDGES OF ANTENNA BASE,SDR CA030721001Drain · leaking(CAN) ABOUT ONE HOUR INTO THE FLT, THE CREW NOTED THAT FUEL WAS LEAKING OUT THE LEFT AFT NACELLE FUEL DRAIN VALVE. ONCE ON THE GROUND INSPECTION OF THE VALVE DETERMINED THAT THE VALVE CENTER BODY HAD SEPERATED FROM THE HOUSING, RESULTING IN THE LEAK. THE BODY SDR CA030825011Diode · failed(CAN) A/C ON APPROACH, TURNED RECOG LIGHT ON, LOST INTERCOM, NR 2 RADIO, COULD NOT EXTEND LAND GEAR. EMER EXTENSION CARRIED OUT. AC LANDED WITHOUT FURTHER INCIDENT. MAINT FOUND NR 2 DUAL FED BUS RT DIODE FAILED AND A LOOSE BUS WIRE NR 2 DUAL FED BUS. DIODE RSDR CA030708001Door · buckled(CAN) ON DESCENT AT 8500 FT, LT WING LOCKER DOOR BUCKLED UP IN MIDDLE APPROX 4-5 INCHES, THEN CAME LOOSE FROM DOOR PIN AND POPPED OPEN & STARTED FLAPPING. AIRCRAFT SPEED WAS REDUCED TO 140 KTS & AIRCRAFT LANDING WAS UNEVENTFUL. DETERMINED THAT WING LOCKER WASSDR 2007FA0000433Exhaust Duct · crackedWHILE PREFORMING SCHEDULED MAINTENANCE,REMOVED EXHAUST STACKS TO FACILTATE INSPECTING THE EXHAUST DUCT.A CRACK WAS FOUND IN THE SKI SLOPE. EXHAUST DUCT SB HAD BEEN COMPLIED WITH 1171 HOURS PRIOR. POWER SECTION WAS REMOVED FOR REPAIR.SDR AUS20030612Frame · cracked(AUS) FUSELAGE FRAME CRACKED AT FLOOR HEIGHT ON RT SIDE. FRAME IS LOCATED AT FS 207.125.SDR CA030612001Switch · inoperative(CAN) ON APPROACH, WHILE DESCENDING THROUGH 8000 FT THE CREW NOTED ILLUMINATION OF THE CABIN DOOR WARNING LIGHT. THE BLEEDS WERE TURNED OFF AND THE CABIN DEPRESSURIZED. JUST PRIOR TO LANDING THE LIGHT EXTINGUISHED. UPON EXITING THE AIRCRAFT, THE CREW VERIFIED SDR 2007FA0000406Exhaust Duct · crackedWHILE 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.SDR AUS20030581Stringer · cracked(AUS) NR 7 STRINGER RT SIDE CRACKED. FOUND DURING INSPECTION IAW AD 200/55 AMDT1.SDR B30R20033010Hinge Fitting · corrodedDURING A 14 DAY CORROSION INSP, MECH NOTED PAINT BLISTERING AROUND RIGHT ELEVATOR HINGE FITTING MOUNTING HARDWARE. REMOVAL OF PAINT BLISTERS FROM HINGE FITTING REVEALED INTERGRANULAR CORROSION. HINGE FITTING WAS REMOVED AND CORRODED AREA WAS CLEANED. AT THIS TSDR B30R20033011Hinge Bracket · damagedDURING A 14 DAY CORROSION INSPECTION, MECHANIC NOTED PAINT BLISTERING ON THE RIGHT INBOARD ELEVATOR HINGE BRACKET. REMOVAL OF THE PAINT BLISTERS FROM HINGE BRACKET REVEALED INTERGRANULAR CORROSION. THE HINGE BRACKET WAS REMOVED AND CORRODED AREA WAS CLEANED. ASDR CA030612003Torque Tube · corroded(CAN) DURING A SCHEDULED FLEET CAMPAIGN INSPECTION OF THE ELEVATOR TORQUE TUBE FOR ANY EVIDENCE OF CORROSION, THERE WAS MINOR CORROSION DETECTED ON THE LT ELEVATOR TORQUE TUBE FLANGE BETWEEN MOUNTING BOLT HOLES. THE TUBE WAS REPLACED. A SPECIAL INSPECTION IN ASDR CA030529002Windshield · fractured(CAN) IN CRUISE AT 24,000 FT ALTITUDE WITH 5.8 PSI PRESSURIZATION AND CLEAR CONDITIONS (OAT -25C) AND THE WINDSHIELD HEAT ON, THE LT WINDSHIELD SUDDENLY CRACKED. THE INNER PLY IN ITS TOTALITY FRACTURED IN MINI PARTICLE 1/4 INCH DIAMETER. NO PRES SURIZATION WASSDR 2007FA0000440Exhaust Duct · crackedWHILE 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.SDR CA030521002Torque Tube · corroded(CAN) DURING A SCHEDULED INSPECTION, CORROSION WAS DETECTED ON THE LT ELEVATOR TORQUE TUBE. THE PAINT WAS LIFTED IN THE AREA ADJACENT TO THE LOWER AFT MOUNTING BOLT. A POWDER COATING AND MINOR FLACKING WAS EVIDENT. CLOSER INSPECTION AND CLEANING DETERMINED THASDR CA030508003Actuator · damaged(CAN) ACTUATOR WAS INSTALLED AFTER HAVING OTHER GEAR PROBLEMS. WHEN GEAR WAS SELECTED UP INFLIGHT THE GEAR MOVED 1/4 OF THE WAY BEFORE THE CLUTCH IN THE GEARBOX BEGAN SLIPPING & CONTINUED TO SLIP UNTIL CIRCUIT BREAKER POPPED. FIRST TIME THIS HAPPENED SUSPECTEDSDR CA030501001Controller · stuck(CAN) FOLLOWING A NORMAL TAKE-OFF, GEAR WAS SELECTED UP AT WHICH TIME THE FLT CREW HEARD A LOUD GRINDING NOISE DURING THE FINAL PHASE OF GEAR UP CYCLE. GEAR WAS RESELECTED DOWN AND THERE WAS NO MOVEMENT OR MOTOR NOISES. FLT CREW COMPLETED A MANUAL GEAR EXTENSISDR CA030501008Motor · failed(CAN) AFTER REPLACING GEAR ACTUATORS, MOTOR CONTROLLER AND GEAR BOX AND COMPLETING 15 GEAR SWINGS. THE AIRCRAFT WENT ON A TRAINING FLIGHT. WHILE TRAINING THE GEAR WAS SELECTED UP. THE GEAR STOPPED MID TRAVEL AND DID NOT RESPOND TO GEAR DOWN SELECTION. A MANUALSDR CA030429001Fire Detector · malfunctioned(CAN) WHILE CLIMBING THROUGH 1500 FT, LT ENGINE FIRE WARNING LIGHT ILLUMINATED INTERMITTENTLY WITH NO APPARENT SIGNS OF FIRE, HEAT OR CHANGE IN ENGINE PARAMETERS. THE AIRCRAFT RETURNED TO BASE FOR LANDING AND THE LIGHT EXTINGUISHED AND STAYED OUT ON FINAL APPRSDR AUS20030822Spar · corroded(AUS) VERTICAL STABILIZER REAR SPAR ANGLES PNO 101-640010-9 AND PN 10164001010 CONTAINED INTERGRANNULAR CORROSION. CORROSION ORIGINATED FROM RIVETS.SDR AUS20030460Bolt · sheared(AUS) NOSE LANDING GEAR UPPER DRAG BRACE BENT AND FORK END OF NOSELANDING GEAR ACTUATOR SPREAD. FURTHER INVESTIGATION ALSO FOUND THE ACTUATOR UPPER SUPPORT BEARINGS ROUGH AND UNSERVICEABLE. SUSPECT CAUSED BY SHEARING OF THE CLEVIS BOLT WHICH ALLOWED THE ACTUASDR CA030508002Wire Harness · burned(CAN) DURING ROUTINE MAINTENANCE, CABIN BEGAN TO FILL WITH SMOKE. A/C POWER WAS DISCONNECTED & A SEARCH WAS CONDUCTED TO LOCATE THE SOURCE. IT WAS FOUND THAT THE PASSENGER COMPARTMENTENTRANCE LIGHTING SYSTEM WAS AT FAULT. WIRE HARNESS W185 HAD CHAFFED ON THE A
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