U/A Canada PT6A-50
Service difficulty reports · 225
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 = 'PT6A50' 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 = 'PT6A50' 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 QMLA2026101320078Synchrophaser · out of adjustLEFT PROP LEVER ACTING LIKE IT WAS HOOKED UP BACKWARDS. PUSHING THE LEVER FORWARD INCREASED RPM, AND VICE VERSA. ADJUSTED LT ENGINE PROPELLER SYNCHROPHASER MAGNETIC PICKUPS IAW KING AIR B200GT AMM 61-23-01. PERFORMED REQUIRED FUNCTIONAL GROUND CHECKS. NO FAULTSDR 2026FA0000537Autothrottle Sys · abnormalPILOTS HAVE REPORTED MULTIPLE INSTANCES OF AUTOTHROTTLE INDUCED WARNING/RED TORQUE INDICATIONS OCCURRING DURING TAKEOFF, GO-AROUND, AND CLIMB PHASES OF FLIGHT ON SIX DIFFERENT AIRCRAFT (S/N BY-472 AND UP). THREE INSTANCES WERE SEVERE ENOUGH TO ACTIVATE THE MASSDR 2025F00230Brake · no discrepancyWHILE TAXIING OUT FOR AN AIR AMBULANCE FLIGHT, THE MED TEAM THOUGHT THEY OBSERVED SMOKE FROM THE LEFT MLG AREA. THE FLIGHT CREW RETURNED TO THE BLOCKS AND HAD MAINTENANCE INSPECT THE LEFT MAIN LANDING GEAR, WHEELS AND BRAKES. NO DEFECTS WERE FOUND. THE CREW ANSDR 2023F00320Hydraulic Line · rupturedWHILE ON APPROACH INTO BFI FROM BIL, THE LANDING GEAR EXTENDED UN-COMMANDED, THE LANDING GEAR HANDLE LIGHT (IN-TRANSIT LIGHT) ILLUMINATED, THE "HYD LOW" ANNUNCIATOR LIGHT ILLUMINATED AND THE LANDING GEAR CIRCUIT BREAKER POPPED. THE THREE GREEN "GEAR DOWN AND LSDR CA190621012Buss · damaged(CAN) DURING CRUISE , LEFT AC BUS CAUTION LIGHT ILLUMINATED. CAPTAIN ELECTED TO RETURN TO DESTINATION FOR TROUBLESHOOTING. MAINTENANCE FOUND THE LEFT AC BUS CONTACTOR WAS STICKING INTERMITTENTLY . THE CONTACTOR WAS REPLACED AND AIRCRAFT RELEASED BACK TO SERVICSDR CA190516015Planetary Gear · failed(CAN) ENGINE SENT TO STANDARDAERO AFTER THE OPERATOR REPORTED AN IN-FLIGHT SHUT DOWN WITH METAL IN OIL. THIS REPORT IS ISSUED TO DISCUSS THE INVESTIGATION AND TEARDOWN FINDINGS. IN ADDITION THE CUSTOMER ELECTED TO OVERHAUL THE ENGINE DURING THIS SHOP VISIT. SSDR CA190211014Circuit Board · damaged(CAN) L/R BLEED AIR FAIL LIGHTS ON AFTER START. WHEN SWITCH`S (BLEED AIR) WERE CYCLED ON/OFF, L/H AND R/H BLEED AIR CONTROL AND RUDDER BOOST CIRCUIT BREAKERS TRIPPED. NOTE ON DEFECT: ELECTRICAL BURNING SMELL IN CABIN AFTER CIRCUIT BREAKERS POPPED. A118 RELAY PSDR CA180808026Compressor · leaking(CAN) AIR CONDITIONING COMPRESSOR WEEPING OIL FROM AFT SEAL. ADDITIONAL AIRCRAFT IN THE COMPANY FLEET HAVE ENCOUNTERED THIS SAME PART NUMBER OF COMPRESSOR TO HAVE FAILED. THE SYSTEM WAS DEFERRED IN ACCORDANCE WITH COMPANY PROCEDURES FOR PARTS ON ORDER. (TC# SDR CA180808021Display · inoperative(CAN) ROCKWELL COLLINS PROLINE FUSION EQUIPPED AIRCRAFT, ADAPTIVE FLIGHT DISPLAY AFD-3700. DEFECT REPORTED AS CHECK MAINTENANCE CAS MESSAGE GNSS-1 FAILURE FLAG CAME ON. TROUBLESHOOTING INCLUDED REMOVAL AND REPLACEMENT OF AFD WITH ORIGINAL UNIT (NOT EXCHANGEDSDR CA180808022Display · inoperative(CAN) ADAPTIVE FLIGHT DISPLAY AFD-3700. DEFECT REPORTED AS CHECK MAINTENANCE CAS MESSAGE AND FMS 2 FAILURE FLAG CAME ON. TROUBLESHOOTING FAULT CODES 000-0632:AC1, 000-0468:AC1, 000-0336AC1, 000-373:AC1, 000-0590:AC1, 000-2027:AC1, 000-1059:AC1, 000-1060:AC1,SDR CA160203019Heater · burned(CAN) MAINTENANCE DISCOVERED A BURN HOLE THROUGH THE PROPELLER BLADE DE-ICE ELEMENT ON THE NR 4 PROPELLER, NR 3 BLADE. MAINTENANCE REPLACED THE PROPELLER BLADE AND CHECKED THE SYSTEM SERVICEABLE.SDR CA160108007Line · ruptured(CAN) ON APPROACH, WHEN FLAP 25 WAS SELECTED, HAD A MASTER CAUTION AND NOTICED, HYDRAULIC PUMPS NR 1 AND NR 2 HAD FAILED AND HYDRAULIC SYS PRESSURE ON NR 1 WAS LOST. A GO-AROUND WAS THEN CONDUCTED AND RETURNED TO DEPARTURE. LANDED AND TAXIED IN WITHOUT INCIDSDR CA151009001Indicator · malfunctioned(CAN) DURING CRUISE THE DECIMAL PART OF T5 GAUGE OF ENGINE 2 STOPPED GIVING INFORMATION. AFTER RECYCLING THE BREAKER THE CREW NOTICED THAT EVEN WITH BREAKER PULLED THE GAUGE WAS STILL POWERED. SHORTLY AFTER STARTING DESCENT, THE T5 GAUGE OF ENGINE 2 STOPPED GSDR CA150714007Sleeve · inoperative(CAN) ENGINE WAS SENT FOR INVESTIGATION AND REPAIR AFTER THE OPERATOR REPORTED THAT THE REVERSE ARM AND THE BETA SLEEVE WILL NOT MOVE. DUE TO THE LOW TIME REMAINING UNTIL O/H, THE OPERATOR ELECTED TO O/H THE ENGINE. THIS REPORT IS ISSUED TO DISCUSS THE INVESTSDR CA150701009Garlock Seal · damaged(CAN) EN-ROUTE AT 15,000 FEET WHEN THE CREW RECEIVED A LOW OIL PRESS INDICATION FOR ONE OF THE LT ENGS. PT6A, & SHUT THE ENG DOWN AS A PRECAUTION. THE ACFT DIVERTED FOR A SAFE LANDING. IT WAS REPORTED THAT MX IDENTIFIED THE GARLOCK OIL SEAL ON THE HYD PUMP WSDR CA150515011Pump · failed(CAN) THE AIRCRAFT WAS ON A CREW CHANGE FLIGHT FOR A CUSTOMER, UPON START UP FOR DEPARTURE, THE FLIGHT CREW SAW THE HYDRAULIC QUANTITY FALL TO 0. THEY DISEMBARKED THEIR PASSENGERS AND CALLED MAINTENANCE. MAINTENANCE ARRIVED AND FOUND THAT THE NR 3 PUMP, SN 16SDR CA150422004Connector · broken(CAN) ON ARRIVAL AT DESTINATION ON FINAL APPROACH, CREW WERE UNABLE TO LOWER THE GEAR USING NORMAL PROCEDURE. ACFT DID NOT LAND BUT RETURNED & WENT INTO HOLD POSITION & CARRIED OUT A SUCCESSFUL EMER GEAR LOWERING PROCEDURE. ACFT THEN LANDED UNEVENTFULLY. FASDR CA150318015Spoiler · separated(CAN) DURING TOWING OPS MAINTENANCE DISCOVERED THE RT ROLL SPOILER ASSY SEPARATED FROM THE ACFT. THE ROLL SPOILER IS BELIEVED TO HAVE SEPARATED DURING THE PREVIOUS FLIGHT. FLIGHT CREW REPORTED NO CHANGE TO THE FLIGHT CONTROL CHARACTERISTICS AND NO INDICATIONSDR CA141209005Fuel Control · failed(CAN) WHILE IN THE DESCENT, THE POWER LEVER WAS REDUCED AND THE NUMBER 1 ENGINE TORQUE REMAINED AT CRUISE POWER SETTING OF 3800 FT-LBS. THE CREW VERIFIED THAT THE ENGINE AND GAUGES WERE RESPONSIVE ABOVE 3800 FT-LBS TORQUE BUT WOULD NOT REDUCE. A DIVERSION WAS SDR CA150113007Fcu · faulted(CAN) WHEN THE CREW REDUCED ENGINE POWER FOR THE DESCENT, THE LT ENGINE REMAINED AT CRUISE POWER OF 3800 FT-LBS. THE CREW VERIFIED THE ENGINE WAS RESPONSIVE ABOVE 3800 FT-LBS BUT WOULD NOT REDUCE BELOW, THEN THE PILOT REQUESTED TO RETURN TO THE AIRPORT. WHENSDR CA141126003Strap · corroded(CAN) FOLLOWING REMOVAL OF THE FOUR (4) ENGINE NACELLE INLET DEICE BOOTS, MISSING AND CORRODED RIVET HEADS WERE DISCOVERED ON THE FIBERGLASS INLET LIPS. FURTHER CORROSION WAS FOUND ON THE FOUR (4) ENGINE NACELLE STRAPS BENEATH THE FIBERGLASS INLET LIPS. MAISDR CA141024001Engine · power loss(CAN) DURING TAKEOFF CLIMB, AT AROUND 9000 FT, ENGINE ROLLED BACK AND ALL PARAMETERS WENT DOWN. CREW ELECTED TO SHUTDOWN THE AFFECTED ENGINE AND PERFORMED AN UNEVENTFUL LANDING WITH THE REMAINING ENGINES.SDR CA140906001Seal · cracked(CAN) AFTER ABNORMAL OIL CONSUMPTION REPORTED TO MAINTENANCE ON THE NR 2 ENGINE, THE REPLACEMENT OF THE HYDRAULIC PUMP GARLOC SEAL, REPLACEMENT OF THE OIL TO FUEL HEATER, REPLACEMENT OF THE OIL FILTER HOUSING/RELIEF VALVE, WAS CONDUCTED OVER A SERIES OF FLIGHTSDR CA140713001Vortex Gen · missing(CAN) ON A PRE-FLIGHT 4 VORTEX GENERATORS WERE FOUND MISSING ON THE WING TOP. THE CREW REVIEWED THE CDL AND THE AIRCRAFT COULD OPERATE WITH NO PERFORMANCE PENALTY. MAINTENANCE WAS MADE AWARE AND GENERATED A WORK CARD FOR WHEN IT RETURNS TO REPLACE THE UNITS MISDR CA140701014Engine · malfunctioned(CAN) WHEN APPROACHING AIRPORT, THE PILOT HEARD A LOUD BANG ON LT ENGINE, ASSOCIATED WITH ACFT TENDENCY TO THE LT. LEFT ENGINE LOST POWER AND ITT INCREASED. THE PILOT ELECTED TO SHUTDOWN ENGINE AND PERFORM A SINGLE ENGINE LANDING. TROUBLESHOOTING ONGOING.SDR CA140529007Garlock Seal · failed(CAN) SHORTLY AFTER LEVELING OFF AT FL170 NR 1 ENGINE OIL PRESSURE WAS OBSERVED FLUCTUATING, CAUTION LIGHT ILLUMINATED AND THE ENGINE WAS SHUTDOWN. ENGINE HYDRAULIC PUMP GARLOC SEAL REPLACED AND ACFT WAS RETURNED TO SERVICE.SDR CA140402004Arm · cracked(CAN) WHEN DISASSEMBLING THE RT ENGINE POWER LEVER ASSY FOR FRICTION BRAKE REPAIR A CRACK WAS OBSERVED IN THE ARM ASSEMBLY BUSHING, AROUND WHICH THE POWER LEVER AND THE FRICTION BRAKE PIVOT.SDR CA131218027Switch · failed(CAN) THERE HAVE BEEN 4 OCCURRENCES, THE 4TH WAS A TEST FLIGHT, WHERE THE ACFT TOOK OFF AND THE LANDING GEAR WOULD NOT RETRACT. THE WEIGHT ON WHEELS SWITCHES WERE CLEANED, THE CABIN SAFETY VALVES WOULD NOT CLOSE DUE TO A FAULT IN THE WEIGHT ON WHEELS SYSTEM, SDR CA131217009Windscreen · arced(CAN) THE LT WINDSCREEN BEGAN ARCHING JUST AFTER TAKEOFF, THE WINDSHIELD HEAT WAS TURNED OFF AND THE ACFT RETURNED TO BASE, DURING THE RETURN TO DEPARTURE THE WINDSCREENS ICED UP REDUCING THE FLIGHT CREWS VISIBILITY. CADORS, 2013C5268 REFERENCES THIS INCIDENTSDR CA131218012Gcu · failed(CAN) RETURNED DUE TO AN ELECTRICAL PROBLEM (RT DC BUSS FAULT). ENGINE 1 THRU 4 GROUND RUN. DC SYSTEM BROUGHT ONLINE. NR 4 DC GEN OPENS DC BUS TIE AND AFTER A SHORT DELAY THERE WAS A RIGHT DC BUS FAULT. REPLACED NR 4 DC GCU. SYSTEM FUNCTION CHECKED, NO FAUSDR CA131030005Actuator · failed(CAN) AFTER O/H, MLG ACTUATOR WAS INSTALLED AND WHEN JACKED, FUNCTIONED ON RETRACTION, BUT FAILED ON EXTENSION DURING GEAR SWING.SDR CA130918010Engine · surges(CAN) ON CLIMB THROUGH 15 000 FT NR 4 ENGINE BEGAN TO SURGE WITH ASSOCIATED FLUCTUATIONS IN TORQUE, ITT AND FUEL FLOW. WHEN THE FLIGHT CREW CLOSED THE NR 4 AIRFRAME BLEED VALVE AND REDUCED POWER THE ENGINE STABILIZED. NO FURTHER ISSUES WERE NOTED FOR THE RESSDR CA130918008Acm · failed(CAN) SHORTLY AFTER TAKEOFF, F/A CALLED COCKPIT, STATING THERE WAS SMOKE IN THE CABIN. CREW RETURNED TO AIRPORT AND ON FINAL APPROACH, SMOKE CLEARED. FLIGHT CREW REPORTED THERE WAS A SMELL LIKE ENGINE OIL. MAINTENANCE CARRIED OUT TROUBLESHOOTING AND FOUND OISDR CA130625001Engine · unknown(CAN) ENGINE WAS SENT FOR INVESTIGATION AND REPAIR AFTER THE OPERATOR REPORTED POOR PERFORMANCE. THE OPERATOR REPORTED THAT THE ENGINE STARTED HOTTER THAN NORMAL AND WAS SURGING.SDR CA130620011Oil System · leaking(CAN) ON START OF NR 4 ENGINE AT CDK2, ENGINE OIL WAS OBSERVED EXITING FROM THE ENGINE BREATHER OVERBOARD VENT, COMPRESSOR DRAIN AND GAS GENERATOR DRAIN. THE START WAS ABORTED AND MAINTENANCE WAS CONTACTED. ON INSPECTION THE ENGINE WAS DETERMINED TO BE UNSERSDR CA130607015Actuator · failed(CAN) ON APPROACH THE T/E FLAPS WOULD NOT EXTEND WHEN SELECTED. ON INSPECTION MAINTENANCE PERSONNEL FOUND THE FLAP BALLSCREW ACTUATOR RT MID POSITION DIFFICULT TO ROTATE, ADEQUATE LUBRICATION WAS PRESENT. THE ADDED TORQUE REQUIRED TO ROTATE THE SCREWJACK CAUSDR CA130531014Starter Gen · malfunctioned(CAN) WHEN REMOVING THE STARTER/GENERATOR DURING A SCHEDULED ENGINE CHANGE THE GENERATOR DRIVESHAFT STAYED IN THE ACCESSORY GEARBOX. ON INSPECTION IT WAS NOTED THE RETAINING NUT FOR THE DRIVESHAFT HAD BACKED OFF AND PASSED THROUGH THE COOLING FAN WHILE THE STASDR CA130430009Engine · power loss(CAN) THE FLIGHT CREW REPORTED NG DROP DURING CRUISE WITH THE PROP RPM AT 1700 AND PULLING BACK ON THE POWER LEVERS TO APPROXIMATELY 1100 ON BOTH ENGINES. THE RIGHT ENGINE DROPPED TO 300 LBS OF TORQUE AND THE FUEL FLOWS DID FOLLOW. THE AIRCRAFT DID YAW AND THESDR CA130128019Blade · cracked(CAN) BLADE SHANK WAS REWORKED FOR CORROSION TO MAXIMUM LIMITS IN ZONE 1, QUADRANT 2. LPI INSPECTION SUBSEQUENTLY REVEALED WHAT LOOKS TO BE A CRACK.SDR CA130124025Garlock Seal · leaking(CAN) NR 2 ENGINE SHUTDOWN ON FINAL APPROACH DUE TO LOSS OF ENGINE OIL PRESSURE. FAULTY HYDRAULIC PUMP GARLOC SEAL REPLACED, CHECKED SERVICEABLE.SDR CA130125004Wire · damaged(CAN) BOTH NR 4 ENGINE FIRE DETECTION ELEMENTS FOUND TO HAVE CHAFE DAMAGE FROM CONTACT WITH AIRFRAME STRUCTURE CAUSING ACTIVATION OF THE FIRE WARNING. BOTH DETECTION ELEMENTS REPLACED, CHECKED SERVICEABLE.SDR CA121210009Oil System · low pressure(CAN) ACFT DEPARTED FOR A MAINTENANCE TEST FLIGHT. PART WAY THROUGH THE CVR TEST, THE PILOTS RECEIVED THE MASTER CAUTION, NR 2 LOW OIL PRESSURE CAUTION LIGHT. THE GAUGE CONFIRMED LOW OIL PRESSURE SO THEY SHUTDOWN NR 2 ENGINE AND RETURNED TO DEPARTURE AIRPORTSDR CA121228002Oil System · low pressure(CAN) NR 2 ENGINE WAS SHUTDOWN FOR PRECAUTIONARY MEASURES. THE PILOT REPORTED THAT THE ENGINE OIL PRESSURE WAS DROPPING OFF AND THE LOW OIL PRESSURE LIGHT WAS FLICKERING. UPON A MAINTENANCE INSPECTION, MAINTENANCE WAS UNABLE TO START THE EFFECTED ENGINE FOR SDR CA121005005Engine · power loss(CAN) DURING CRUISE, THE NR 4 ENGINE T5 ROSE ABOVE 800 DEGREES C ILLUMINATING THE ASSOCIATED WARNING LIGHT WITH A CORRESPONDING YAW TO THE RT AND THE TORQUE DROPPED TO A MINIMUM POWER LEVEL, NG DROPPED TO APPROXIMATELY 60 PERCENT AND AN ODOR WAS DETECTED IN THSDR CA120920006Strut · broken(CAN) DURING POST FLIGHT INSPECTION, THE RT MLG UPPER LOCK STRUT WAS FOUND TO BE BROKEN AT THE UPPER, LOCK STRUT ACTUATOR, ATTACH POINT. THE LIFE LIMIT FOR THIS PART IS 60,000 LANDINGS AND IT HAD 15,949 LANDINGS REMAINING. THERE HAVE BEEN 3 SB ISSUED, 7-32-21SDR CA120905011Contactor · failed(CAN) WHEN THE FLIGHT CREW SELECTED PROP DE-ICE IT FAULTED. UPON INSPECTION THE AC CONTACTOR FOR THE NR 2 PROP, IN THE NR 2 WHEEL WELL ELECTRICAL BOX, HAD FAILED. THE CONTACTOR AND SEVERAL TERMINALS WERE REPLACED AND THE SYS FUNCTION CHECKED WITH NO DEFECTS SDR CA120605006Turbine Blades · fractured(CAN) SHORTLY AFTER LEVELING OFF AT CRUISE ALTITUDE, THE FLIGHT CREW OBSERVED A DECREASE IN TORQUE FROM THE NR 2 ENGINE. THE ENGINE WAS SHUTDOWN AND THE FLIGHT RETURNED TO THE DEPARTURE POINT WHERE AN UNEVENTFUL LANDING WAS ACCOMPLISHED. POST FLIGHT INSPECTIOSDR CA120528009Blade · separated(CAN) APPROXIMATELY 40 NM NORTH OF AIRPORT, SHORTLY AFTER LEVELING OFF AT CRUISE ALTITUDE, THE FLIGHT CREW OBSERVED A DECREASE IN TORQUE FROM THE NR 2 ENGINE. THE NR 2 ENGINE WAS SHUTDOWN AND THE CREW RETURNED TO DEPARTURE. VISUAL INSPECTION OF THE 1ST STAGESDR CA120522005Wire · chafed(CAN) WHILE PERFORMING A ROUTINE TASK FOR EWIS INSPECTIONS IT WAS NOTICED THAT THERE WERE NUMEROUS WIRE CHAFING INSIDE THE LT AND RT AC CONTACTOR BOXES. THE CHAFING WAS CAUSED BY INSUFFICIENT WIRE PROTECTION AND POOR ROUTING OF BUNDLES THROUGHOUT THE CONTACTOSDR CA120502013Housing · cracked(CAN) DURING THE ROUTINE SSI INSPECTION OF THE APU MOUNT AND STRUCTURE, IT WAS NOTICED THAT THE APU, PN 160371-201, SN 897402, HAD A SIGNIFICANT JAGGED CRACK ON THE FWD FACE OF THE COMBUSTION HOUSING, PN 160184-100, AFT OF THE V-BAND CLAMP WHICH SECURES THE CO
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