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 97ZZZX1174Filter · screen failedTHE INNER CONE SHAPED SCREEN HAD SEPARATED ON OIL FILTER. SEPARATION APPEARED TO BE AT A SEAM ON THE SCREEN.SDR CA970227001Retaining Plate · broken(CAN) OIL LEAK LED TO INFLIGHT SHUTDOWN. POST FLIGHT INSPECTION FOUND THERMOSTATIC OIL BYPASS VALVE RETAINING PLATE BROKEN. THIS ALLOWED OIL PRESSURE TO FORCE OUT THE PLUG WHICH LED TO AN OIL LEAK CAUSING THE INFLIGHT SHUTDOWN.SDR AU970091Handle · broken(AUS) CABIN DOOR HANDLE BROKEN IN AREA AROUND BEARING HOUSING - HANDLE THEN SEPARATED FROM SQUARE SHAFT.SDR CA970523002Valve · failed(CAN) HYDRAULIC PUMP WAS OBSERVED TO BE RUNNING CONTINUOUSLY WHILE TAXIING. HYRAULIC PUMP BREAKER PULLED AND THE AIRCRAFT RETURNED TO THE HANGAR AND PUT ON JACKS. HYDRAULIC RELIEF VALVE WAS FOUND TO GO INTO BYPASS AT LESS THAN 1200 PSI, RATING SHOULD ALLOW FSDR CA970523003Valve · failed(CAN) HYDRAULIC PUMP WAS OBSERVED RUNNING CONTINOUSLY. MAINTENANCE FOUND THE THERMAL PRESSURE RELIEF VALVE TO BE OPENING AT 1200 PSI INSTEAD OF THE RATED 2250 PSI. VALVE CHANGED.SDR CA970206017Gyro · rough & noisy(CAN) CREW REPORTED THE #1 RMI AND THE #2 HSI COMPASS WERE READING UNRELIABLY. INSPECTION FOUND THE 332E-4 GYRO TO BE VERY WARM TO THE TOUCH AND NOISY. SERVICEABLE UNIT WAS INSTALLED.SDR CA970206018Squat Switch · intermittent(CAN) FLIGHT CREW OBSERVED THAT THE ANTI-RETRACTION HOOK ON THE GEAR HANDLE WAS NOT RETRACTING AFTER TAKEOFF. INSPECTION REVEALED THE RIGHT HAND SQUAT SWITCH FUNCTION TO BE INTERMITTENT. REPLACEMENT OF THE SWITCH WAS ACCOMPLISHED.SDR CA970203010Channel · cracked(CAN) WITH CABIN DOOR OPEN, A CRACK WAS FOUND IN THE UPPER FRAME MEMBER. THE CRACK WAS APPROXIMATELY 6 INCHES LONG, ALONG THE DOOR HINGE RIVET LINE, RUNNING FROM THE AFT EDGE FORWARD.SDR CA961231001Switch · failed(CAN) ON APPROACH, GEAR DOWN SELECTED WITH 3 GREENS. WHEN FLAPS SELECTED BEYOND APPROACH SETTING OR WHEN POWER LEVERS WERE REDUCED BELOW 400 POUNDS TORQUE, GEAR WARNING HORN WOULD SOUND AND GEAR IN-TRANSIT LIGHT CAME ON. NOSE GEAR DOWNLOCK MICROSWITCH NOT FUSDR CA961009002Connector · wrong part(CAN) UNAPPROVED BNC CONNECTOR USED TO CONNECT SENSE ANTENNA COAX TO REAR OF ADF TRAY. BNC CONNECTOR ALSO MODIFIED TO ADAPT TO COAX DIAMETER.SDR CA961009003Circuit Breaker · failed(CAN) GEAR FAILED TO EXTEND WHEN SELECTED DOWN. HYDRAULIC MOTOR DID NOT OPERATE. 60 AMP BREAKER WAS CHECKED AS IN. MOTOR THEN STARTED AND GEAR EXTENDED. 60 AMP BREAKER REPLACED.SDR CA960924037Motor · burnt(CAN) ON CLIMB OUT FLAPS SELECTED UP. MOTOR DID NOT SHUT OFF AND BEGAN TO SMOKE UNTIL CB POPPED. THE CAM THAT CONTACTS THE UP LIMIT SWITCH DID NOT MAKE CONTACT BEFORE FLAPS WERE UP TIGHT TO STOP. THE SWITCH P/N BZ7RW82255518T, HAD JUST BEEN REPLACED AND WAS RISDR 96ZZZX5074Engine · failedACFT HAD IN-FLT FAILURE OF RT ENG, AS ACFT REACHED CRUISE ALTITUDE. ENG HAS TTSN 7,559.4, TSHSI 120.9, TSO1605.3. A PRELIM INSP OF ENG FND LARGE OIL STAIN ACROSS TOP OF NACELLE AND OIL DRIPPING FROM COWLING. PROP WOULD NOT ROTATE IN NORMAL DIRECTION OF ROTASDR 96ZZZX4876Engine · failedWHILE IN-FLIGHT, THE RIGHT PROPELLER STOPPED TURNING SUDDENLY. INITIAL INSPECTION REVEALED A FAILURE OF THE COMPRESSOR SECTION OF THE RIGHT ENGINE CAUSING COMPLETE STOPPAGE. ENGINE WAS REMOVED AND SENT TO PRATT AND WHITNEY, CANADA, FOR EVALUATION.SDR CA960925001O-Ring · worn flat(CAN) WITH SYSTEM PRESSURE ON, EMERGENCY UPLOCK ACTUATOR O-RINGS LEAK FLUID INTO THE RIGHT HAND GEAR WELL. WITH NO SYSTEM PRESSURE THERE IS NO LEAK.SDR CA960826031Drain Valve · leaking(CAN) THE PILOT REPORTED A FUEL IMBALANCE. MAINTENANCE FOUND THE FUEL SCREEN BOWL VALVE HAD FAILED.SDR CA960813003Tire · bulged(CAN) DURING DAILY INSPECTION THE SIDEWALL TREAD OF THE MAIN WHEEL WAS FOUND BULGING ON SOME PORTIONS OF THE INBOARD TREAD AREA. THE TREAD WAS SOFT WHEN DEPRESSED.SDR AU961072Actuator · failed(AUS) RT MAIN LANDING GEAR ACTUATOR INTERNAL GEARS STRIPPED - SUSPECT CAUSED BY ADJUSTMENT OF UPLOCK MICROSWITCH ALLOWING OVERTRAVEL OFTHE ACTUATORSDR AU961151Pipe · chafed(AUS) RH MAIN LANDING GEAR TORQUE TUBE PNO 101-810021-3 RUBBING ON INCORRECTLY POSITIONED FUEL LINE BETWEEN THE NACELLE TANK AND THE AUXILIARY TANK WEARING A HOLE IN THE FUEL LINE AND DAMAGING THE TORQUE TUBE - FUEL LEAKING - PERSONNEL/MAINTENANCE ERRORSDR AU961119Terminal · corroded(AUS) BATTERY MONITOR SHUNT TERMINAL CORRODED PREVENTING CORRECT CONTACTSDR CA960801018Gearset · worn splines(CAN) ON FINAL APPROACH THE #2 ENGINE FLAMED OUT AND AUTO FEATHERED. THE LANDING WAS UNEVENTFUL AND MAINTENANCE WAS NOTIFIED. INSPECTION FOUND THE #2 ENGINE DRIVEN HP FUEL PUMP SPLINES WERE WORN OFF AND THE PUMP WAS SEIZED. THE #2 ENGINE HP FUEL PUMP WAS REPLASDR AU961028Housing · cracked(AUS) RH MAIN LANDING GEAR OLEO HOUSING ASSEMBLY CRACKED FROM TOP TO BOTTOM THROUGH THE SHARP RADIUS AT THE BASE OF THE SIDE BRACE ATTACHMENT LUG - LOSS OF OLEO PRESSURESDR CA960801020Valve · failed(CAN) WHEN SELECTING SURFACE DEICER TO EITHER MANUAL OR AUTO IN CRUISE THE WING DEICER BOOTS VISUALLY DO NOT INFLATE AND "MASTER WARNING" CAME ON. ON GROUND FUNCTIONED OK. FURTHER INVESTIGATION FOUND THAT AT CRUISE SPEED THE DEICER DISTRIBUTOR VALVE SOLENOID FSDR AU961032Trim Wheel · mis installed(AUS) TRIM WHEEL INCORRECTLY INSTALLED DURING PREVIOUS MAINTENANCE - INCORRECT ORIENTATION OF TRIM INDICATION IN RELATION TO TRIM TAB - PERSONNEL/MAINTENACE ERRORSDR AU961033Autopilot · faulty(AUS) AUTOPILOT SUSPECT FAULTY - GROUND CHECK COULD FIND NO FAULTS - DEFECT NOT CONFIRMEDSDR AU960995Torque Tube · worn(AUS) MAIN LANDING GEAR RETRACTION MECHANISM TORQUE TUBE HAD A GROOVE WORN AROUND ONE END - SUSPECT CAUSED BY DISPLACED/INCORRECTLYFITTED ADEL CLIPSDR AU960857Fire Detector · faulty(AUS) LH ENGINE FIRE DETECTION SYSTEM FAULTY - INVESTIGATION COULD FIND NO FAULTS WITH THE SYSTEM - A LEAKING GASKET ON THE FLOW PACK MAYHAVE ALLOWED HOT AIR ONTO THE LOWER REAR SENSOR - FOLLOWING REPLACEMENT OF THE FLOW PACK ON THE NEXT FLIGHT THE FIRE WARNISDR AU960851Detector · faulty(AUS) ENGINE FIRE DETECTORS FAULTY - CONTINUING FALSE FIRE WARNING INDICATIONSSDR AU960850Fcu · faulty(AUS) ENGINE LOST POWER DURING TAKEOFF - INVESTIGATION COULD FIND NO FAULTS - SUSPECT FUEL CONTROL PROBLEMSDR AU960782Detection System · faulty(AUS) RH ENGINE FIRE DETECTION SYSTEM FAULTY - SEE MDR 96/0780 AND MDR 96/0781 FOR FURTHER INFORMATIONSDR AU960780Amplifier · faulty(AUS) RH ENGINE FIRE WARNING SYSTEM FIRE CONTROL AMPLIFIER FAULTYSDR AU960781Fire Detector · faulty(AUS) RH ENGINE FORWARD UPPER DETECTOR FAULTYSDR CA960927004O-Ring · undersized(CAN) WHILE CARRYING OUT MAINTENANCE ON AN ENGINE THE INSPECTION OF THE REDUCTION GEARBOX CHIP DETECTOR REQUIRED THE REPLACEMENT OF AN O-RING. IN DRAWING THE O-RING FROM STORES THE AME NOTED THE SIZE OF THE NEW O-RING WAS NOT THE SAME AS THAT OF THE ONE REMOVESDR AU960645Bracket · cracked(AUS) LH ENGINE UPPER OUTBOARD ENGINE MOUNT TO FIREWALL ATTACHMENT BRACKET CRACKED THROUGH VERTICAL FACE FROM TOP WELD LINE EXTENDING DOWN BETWEEN RIVET HOLES - CRACK LENGTH 9MM (0.35IN)SDR CA960524028Fcu · low power(CAN)#2 ENGINE UNABLE TO REACH MAXIMUM CRUISE TORQUE ABOVE 18,000 FEET, ALL ENGINE PARAMETERS NORMAL ON GROUND FCU CHANGED. SAME PROBLEM AGAIN ABOVE 15,000 FEET: NG 3 5 PERCENT LOW, TORQUE 150 LBS LOW ANDTHE TOP ONE INCH OF THROTTLE MOVEMENT HAD NO EFFECT ON SDR CA960619041Indicator · slow reacting(CAN) THE VERTICAL SPEED INDICATOR HAD BEEN INDICATING SLOW, ERRATIC AND SOMETIMES INCORRECTLY. THE UNIT HAS A HISTORY OF ERRATIC BEHAVIOUR EVEN AFTER SUCCESSIVE OVERHAULS.SDR CA960619042Indicator · reads incorrect(CAN) LANDING GEAR HYDRAULIC PRESSURE GAUGE READS INCORRECTLY. THE GAUGE IS RATED FOR 2000 PSI, AND THE SYSTEM OPERATES AT 2000 PSI. SUBMITTER STATES THAT THE RELIEF VALVE FUNCTIONS AT 2200 PSI AND THIS PUTS UNDO STRAIN ON THE GAUGE DURING HOT WEATHER RELATED SDR CA960527001Tire · burst(CAN) ON LANDING, LEFT MAIN TIRE BLEW UP. NO OTHER DAMAGE.SDR HEEA967166Transmitter · defectiveERRATIC FUEL FLOW.SDR AU960629Valve · faulty(AUS) RH BLEED AIR BYPASS VALVE FAULTY - INVESTIGATION FOUND VALVE BUTTERFLY DAMAGED DUE TO A LOOSE SECURING SCREW ALLOWING THE PLATE TO ROTATE OUT OF ALIGNMENT WITH THE VALVE BORESDR AU960627Blower · faulty(AUS) AIRCONDITIONING SYSTEM FORWARD EVAPORATOR VENT BLOWER FAN FAULTY - SUSPECT BURNT OUT CIRCUITSDR AU960884Plate · cracked(AUS) NOSE LANDING GEAR SHOCK ABSORBER REINFORCEMENT PLATE CRACKED IN LOWER WELDED AREA - CRACK LENGTH 28MM (1.1IN)SDR AU960590Chip Detector · contaminated(AUS) LH ENGINE CHIP DETECTOR ILLUMINATED - INSPECTION FOUND A VERY FINE METALLIC HAIR ACROSS THE PROBES - AFTER CLEANING AND REINSTALLING IAW PRATT AND WHITNEY MAINTENANCE MANUAL THE AIRCRAFT WAS OPERATED FOR 15 FLIGHT HOURS AND THE CHIP DETECTORREINSPECTEDSDR AU960585Lever · broken(AUS) LH FUEL CONTROL LEVER FAILED IN AN AREA LEVEL WITH THE PEDESTAL QUADRANT - LEVER EXHIBITED ADVANCED WEAR IN AREA OF FAILURE -FURTHER INVESTIGATION SHOWED SIMILAR WEAR IN THE RH LEVER - SUSPECT LEVER HAD BEEN BENT AND RESTRAIGHTENED AT ONE TIME WHICH CASDR AU960468Fire Detector · faulty(AUS) RH ENGINE FIRE WARNING ILLUMINATED - ON LANDING THERE WAS NO EVIDENCE OF FIRE - FIRE WARNING SENSORS REPLACED BY A NEW TYPE PNO 473275SDR HEEA966968Vane Ring · crackedCRACKED POWER TURBINE 2ND STAGE VANE RING.SDR AU960467Radio System · faulty(AUS) RADIO SYSTEM JAMMED IN TRANSMIT MODE ON THREE OCCASIONS - ON LANDING, AFTER EACH FAILURE THE SYSTEM OPERATED NORMALLYSDR CA960419005Oil System · contaminated(CAN)CHIP DETECTOR WARN DURING TAKEOFF, ABORTED. OIL FILTER CONTAMINATED WITH METAL ENGINE REPLACEDSDR CA960513005Blade · fractured(CAN)ENGINE SHUTDOWN FOLLOWING AN INCREASE IN ITT. AS THE POWER LEVER WAS BEING RETARDED, DRBRIS WAS SEEN TO BE COMING FROM THE EXHAUST. INITIAL REPORT INDICATE THIS TO BE A COMPRESSOR TURBINE BLADE FRACTU RE.SDR CA960404008Tire · bulged(CAN) BULGE ON LEFT INBOARD MAIN WHEEL TIRE TREAD NOTICED WHILE CARRYING OUT A DAILY INSPECTION. INSPECTION OF BULGED AREA SEEMS TO INDICATE A SEPARATION IN THE FIRST TREAD GROOVE AND PART OF THE SIDE WALL. THERE ARE A TOTAL OF FIVE OCCURRENCES OF THIS NATURE
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