Pratt & Whitney Canada PT6A-64
Service difficulty reports · 59
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 = 'PT6A64' 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 = 'PT6A64' 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 2016FA0000608Fuel Control · malfunctionedENGINE HANGS DURING START BELOW 40%. SEND FOR RE-CALIBRATION.SDR 2016FA0000609Fuel Control · malfunctionedAFTER RECEIPT OF FCU AFTER RE-CALIBRATION ENGINE WILL START NORMALLY BUT WILL NOT MAKE MAX REVERSE CHECK. SEND OUT FOR RE-CAL.SDR 2016FA0000610Fuel Control · malfunctionedMAX REVERSE FAILED CHECK. RE-CALIBRATE FCU.SDR 2016FA0000611Fuel Control · malfunctionedENGINE SURGES IN MAX REVERSE. FCU TO RECALIBRATE.SDR 2016FA0000625Fuel Control · malfunctionedITT LIGHT WHEN GOING INTO MAX REVERSE. RECALIBRATE FCU.SDR 2016FA0000623Fuel Control · abnormalMAX ITT LIGHT WHEN GOING INTO MAX REVERSE. RE-CALIBRATE FCU.SDR 2016FA0000622Fuel Control · malfunctionedENGINE STARTING WARM. RE-CALIBRATE FCU.SDR 2016FA0000621Fuel Control · malfunctionedENGINE STATING WARM. RE-CALIBRATE FCU.SDR 2016FA0000620Fuel Control · malfunctionedENGINE STARTS WARM. RE-CALIBRATE FCU.SDR 2016FA0000624Fuel Control · malfunctionedENGINE STARTING WARM AND SLOW STARTS. RE-CALIBRATE FCU.SDR CA160120012Governor · faulted(CAN) DURING CRUISE, WITH THE POWER SETTING ABOVE 80 PERCENT, THE PILOT REPORTED 5 PERCENT TO 15 PERCENT TORQUE FLUCTUATIONS, WITH ASSOCIATED TEMP VARIATIONS, UNSPECIFIED VALUE. HE ELECTED TO DIVERT. TROUBLESHOOTING IDENTIFIED A POSSIBLE FAULTY PROPELLER GOVSDR 2016FA0000617Fcu · malfunctionedHIGH TEMPS DURING START. RE-CLAIBRATE FCU.SDR 2016FA0000615Fuel Control · malfunctionedMAX ITT LIGHT COMES ON WHEN PULLING INTO MAX REVERSE. RE-CALIBRATE FCU.SDR 2016FA0000616Fcu · malfunctionedENGINE START TEMPS EXCESSIVE. RECALIBRATE FCU.SDR 2016FA0000614Fuel Control · malfunctionedFAILED MAX REVERSE CHECK. RE-CALIBRATED FCU.SDR 2016FA0000595Fuel Control · out of limitsMANUAL OVER RIDE LOWER THAN 40 PERCENT AND FUEL FLOW LOWER THAN 60 PERCENT. FUEL CONTROL UNIT CONTACTING STOPS.SDR 2016FA0000597Fuel Control · abnormalENGINE IS SLOW TO START AND NOT MAKING MAX REVERSE. CALIBRATED FUEL CONTROL UNIT.SDR CA141024008Oil System · low pressure(CAN) WHILE ENROUTE, HAD AN INDICATION OF LOW OIL PRESSURE. THE PILOT WAS UNABLE TO LAND. WHILE MANEUVERING FOR A FORCED LANDING ON A FOOTBALL FIELD THE AIRPLANE COLLIDED WITH TREES THAT SEPARATED THE RT WING. THE AIRPLANE CAME TO REST UPRIGHT ON THE FOSDR 2016FA0000596Fuel Control · abnormalENGINE IS SLOW TO START. FUEL CONTROL UNIT HAD TO BE RE-CALIBRATED.SDR 2014FA0000294Structure · contaminatedHORIZONTAL STABILIZER STRUCTURE COMPROMISED BY APPARENT WATER DAMAGE CREATING CRACKS AND CORROSION. DEFECTS WITHIN THE PRIMARY STRUCTURE OF THE HORIZONTAL STABILIZER. HONEYCOMB CORE CONTAMINATED WITH WATER INTRUSION.SDR CA131007007Fuel Control · malfunctioned(CAN) DURING FLIGHT, THE ENGINE TQ STAYED AT 72.7 PERCENT AND THE ENGINE ITT WAS 752. IT REMAINED BELOW 72.7 PERCENT EVEN WHEN THE MANUAL OVERRIDE USED TO 100 PERCENT TORQUE. THE FCU WAS REMOVED FOR INVESTIGATION.SDR RL8R2013FA0000541Roll Pin · looseDURING A ROUTINE ANNUAL INSPECTION, THE LT AND RT AILERON MOUNTING PIVOT POINT ROLL PINS WERE FOUND TO BE LOOSE AND WORKING.SDR RL8R2013FA0000542Roll Pin · looseDURING A ROUTINE ANNUAL INSPECTION, THE LT & RT INBD AILERON MOUNTING PIVOT POINTS ROLL PINS WERE FOUND TO BE LOOSE AND WORKING.SDR RL8R2013FA0000543Roll Pin · looseDURING A ROUTINE ANNUAL INSPECTION, THE LT & RT INBD AILERON MOUNTING PIVOT POINT ROLL PINS WERE FOUND TO BE LOOSE AND WORKING.SDR RL8R2013FA0000544Roll Pin · looseDURING A ROUTINE ANNUAL INSPECTION, THE LT INBD AILERON MOUNTING PIVOT POINT ROLL PIN WAS FOUND TO BE LOOSE AND WORKING.SDR CA130610001Engine · malfunctioned(CAN) EIR PT6A 2013-039, ENGINE WAS SENT FOR INVESTIGATION AFTER THE CUSTOMER REPORTED A LOSS OF OIL PRESSURE FOLLOWED BY AN IN-FLIGHT SHUTDOWN. ACCORDING TO INFORMATION RECEIVED FROM THE CUSTOMER, SOON AFTER TAKEOFF, A SLIGHT VIBRATION WAS FELT FROM THE ENGISDR CA130603004Engine · making metal(CAN) THE PILOT REPORTED THAT 5 MINUTES AFTER TAKEOFF DURING CLIMB HE FELT A SLIGHT VIBRATION AND THE OIL PRESSURE WENT MOMENTARILY IN TO THE YELLOW RANGE. THE PILOT MADE RIGHT TURN TO RETURN TO HOME BASE WITH THE LOP WARNING LLUMINATED AND A GROWL NOISE BEINGSDR CA130502001Engine · power loss(CAN) SHORTLY AFTER T/O, A LOSS OF ENGINE POWER OCCURRED AND THE A/C MADE A FORCED WHEELS UP LANDING IN AN OPEN FIELD. NO ONE ON BOARD WAS SERIOUSLY INJURED. THE A/C SUFFERED DAMAGE TO THE PROPELLER AND LOWER FUSELAGE. OFFER OF ASSISTANCE WILL BE MADE TO THE DSDR CA130401008Oil System · overheated(CAN) DURING CRUISE FLIGHT AT FL260, THE OIL TEMPERATURE WAS OBSERVED TO EXCEED THE RED LINE. THE PILOT PERFORMED AN EMERGENCY DESCENT TO FL20 AND DECLARED AN EMERGENCY. THE ENGINE WAS REDUCED TO IDLE POWER DURING DESCENT AND THE ACFT WAS LANDED UNEVENTFULLYSDR 2013FA0000281Insert · looseINBD FLAP CARRIAGE INSERTS HAVE LOOSENED UP UNDER NORMAL USE. COULD POSSIBLY LEAD TO FLAP CARRIAGE ATTACHMENT FAILURE DURING FLAP DEPLOYMENT WITH SUBSEQUENT LOSS OF FLAP OR WORSE. REQUIRES REPAIR TO FLAP END AND INSTALLATION OF NEW FLAP CARRIAGE INSERTS. THSDR 2013FA0000282Insert · looseINBD FLAP CARRIAGE INSERTS HAVE LOOSENED UP UNDER NORMAL USE. COULD POSSIBLY LEAD TO FAP CARRIAGE ATTACHMENT FAILURE DURING FLAP DEPLOYMENT WITH SUBSEQUENT LOSS OF FLAP OR WORSE. REQUIRES REPAIR TO FLAP END AND INSTALLATION OF NEW FLAP CARRIAGE INSERTS. THISDR 2013FA0000283Insert · looseINBOARD FLAP CARRIAGE INSERTS HAVE LOOSENED UP UNDER NORMAL USE. COULD POSSIBLY LEAD TO FAP CARRIAGE ATTACHMENT FAILURE DURING FLAP DEPLOYMENT WITH SUBSEQUENT LOSS OF FLAP OR WORSE. REQUIRES REPAIR TO FLAP END AND INSTALLATION OF NEW FLAP CARRIAGE INSERTS. SDR 2014FA0000149Insert · looseINBD FLAP CARRIAGE INSERTS HAVE LOOSENED UP UNDER NORMAL USE. COULD POSSIBLY LEAD TO FLAP CARRIAGE ATTACHMENT FAILURE DURING FLAP DEPLOYMENT WITH SUBSEQUENT LOSS OF FLAP OR WORSE. REQUIRES REPAIR TO FLAP END AND INSTALLATION OF NEW FLAP CARRIAGE INSERTS. THSDR RL8R2014030700150Carriage · damagedINBD FLAP CARRIAGE INSERTS HAVE LOOSENED UP UNDER NORMAL USE. COULD POSSIBLY LEAD TO FLAP CARRIAGE ATTACHMENT FAILURE DURING FLAP DEPLOYMENT WITH SUBSEQUENT LOSS OF FLAP OR WORSE. REQUIRES REPAIR TO FLAP END AND INSTALLATION OF NEW FLAP CARRIAGE INSERTS. THSDR CA130116005Fuel Nozzle · malfunctioned(CAN) FOLLOWING AN ENGINE CHANGE, THE CREW PERFORMED A FLIGHT TO PERFORM CUTOFF AND RELIGHT TEST. THE ENGINE DID NOT RELIGHT AFTER 2 ATTEMPTS. A SINGLE ENGINE UNEVENTFUL LANDING WAS PERFORMED. THE ENGINE DID NOT RELIGHT DURING THE ON GROUND INVESTIGATION. TSDR CA120821002Engine · power loss(CAN) DURING CLIMB AT 1900 FT, THE PILOT HEARD ABNORMAL NOISES FROM THE ENGINE FOLLOWED BY EXHAUST SMOKE AND POWER LOSS. THE PILOT SECURED THE ENGINE INTO FEATHER MODE. THE ACFT LANDED SAFELY. PRELIMINARY INSPECTION REVEALED SEIZED PROPELLER SHAFT.SDR CA120723001Oil System · malfunctioned(CAN) THE PILOT REPORTED THAT THE OIL PRESSURE HAS DECREASED STEADILY FOR THE PAST 4 FLIGHTS, ENDING VERY CLOSE TO THE YELLOW BAND IN CRUISE ON THE LAST FLIGHT. THE TORQUE ALSO WENT DOWN ON THE LAST FLIGHT, THE PILOT COULD ACTUALLY FEEL IT. AFTER LANDING, THSDR 2012FA0000081Fuel Control · failedDURING RUNUP, PROP FEATHER CHECK CONDUCTED NORMALLY. WHEN ADVANCING POWER LEVER TO DO A PROP OVERSPEED TEST, COULD NOT REACH 1900 RPM WITH POWER LEVER FORWARD. HIGHEST RPM ACHIEVED WAS 1700. SHUTDOWN AND RESTART. DURING THE START, AT LOW IDLE, FLAMES SHOTSDR CA120129001Fuel Control · failed(CAN) WHILE PREPARING FOR THE SCHEDULED NIGHT FLIGHTS, AFTER NORMAL ENGINE START, WHILE RUNNING UP TO PERFORM THE FEATHERING CHECK, THE ENGINE COULD ONLY ACHIEVE 1700 RPM ON THE PROPELLER WHERE 1900 RPM SHOULD HAVE BEEN AVAILABLE WITH THROTTLE FULL FORWARD. FLSDR 2011FA0000329Gasket · separatedPROPELLER OVERSPEED GOVERNOR TO ENGINE PAD GASKET FAILED CAUSING LOSS OF OIL.SDR CA110516016Gasket · leaking(CAN) OIL LEAK 5 MILES OUT, THE ENGINE HAD A MAJOR OIL LOSS. THE PILOT ELECTED TO RETURN TO THE DEPARTURE AIRPORT WITHOUT SHUTTING THE ENGINE DOWN. AN UNEVENTFUL LANDING WAS MADE. GROUND INSP FOUND NO OIL LEFT IN THE ENGINE. THE PROBLEM WAS TRACED BACK TO A LSDR 2010FA0000931Control Cable · brokenPERFORMED NORMAL START, NOTED LOW IDLE LOW, MOVED CONDITION LEVER TO HIGH IDLE WITH NO RESPONSE FROM ENGINE, TRIED SEVERAL TIMES & HAD NO RESPONSE. PERFORMED ENGINE SHUTDOWN. MOVED CONDITION LEVER IN COCKPIT WHILE 2ND PERSON WATCHED MOVEMENT ON FCU. MOVEMENTSDR CA100608001Electrical Sys · unknownACCIDENT DURING CRUISE AT FL130, THE ACFT RUDDER STOPPED RESPONDING, GETTING STUCK FULL LT. PILOT MANAGED TO MAINTAIN CONTROL BUT HE THEN SAW THAT BOTH GPS`S WENT OUT FOLLOWED BY LOW FUEL PRESSURE WARNING AND ENGINE SPOOL DOWN. FEATHERED THE PROPELLER AND ASKSDR GLBA200911301Linkage · out of adjustRT AUTO FEATHER ENGAGED ON APPROACH TO LANDING AT 780 FT AGL AS PWR WAS INCREASED FROM IDLE THROUGH 600LBS OF TORQUE. WHEN THE AUTO FEATHER ENGAGED IT WENT IN AND OUT OF FEATHER SEVERAL TIMES BEFORE MORE PWR WAS APPLIED AND THE AUTO FEATHERING CYCLE STOPPED OSDR 2009FA0000623Shaft · fracturedDURING START ATTEMPT, THE POWER SECTION DID NOT ROTATE WHEN THE NG REACHED 13 PERCENT. START WAS ABORTED AND PROPELLER TURNED BY HAND. A NOISE WAS HEARD FROM THE EXHAUST STACK AND DRAGGING/BINDING WAS FELT. POWER SECTION WAS REMOVED AND SENT FOR TROUBLESHOSDR 2007FA0000328Fitting · crackedDURING A 6000HR/10 YEAR CORROSION INSPECTION AD2007-06-11 WAS BEING COMPLIED IAW AD AND MANDATORY SB70-=104, AMENDMENT 2. AFTER COMPLETING THE PENETRANT INSPECTION NO CRACKS WERE DETECTED IN THE SPECIFIED AREAS HOWEVER THE FITTINGS LISTED IN BLOCK 5 WERE REMOSDR 2007FA0000329Fitting · corrodedDURING A 6000HR/10 YEAR CORROSION INSPECTION AD2007-06-11 WAS BEING COMPLIED IAW AD AND MANDATORY SB70-104, AMENDMENT 2. AFTER COMPLETING THE PENETRANT INSPECTION, NO CRACKS WERE DETECTED IN THE SPECIFIED AREAS HOWEVER THE FITTINGS LISTED IN BLOCK 5 WERE REMOSDR CA061006020Engine · seized(CAN) ENGINE OIL TEMPERATURE WAS SEEN TO INCREASE IN FLIGHT ACCOMPANIED BY A LOSS OF OIL PRESSURE. THE ENGINE WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED OIL IN THE ENGINE DRAINS AND SEIZURE OF THE POWER SECTION. MFG WILL INVESTIGATE THE EVENT ANSDR CA061103004Oil System · overtemp(CAN) IN FLIGHT ENGINE OIL TEMPERATURE WAS SEEN TO INCREASE ACCOMPANIED BY A DROP IN OIL PRESSURE. THE ENGINE WAS SHUTDOWN IN FLIGHT. POST FLIGHT INSPECTION REVEALED DEBRIS IN THE ENGINE OIL SYSTEM AND EVIDENSE OF OIL LEAKAGE FROM THE ENGINE DRAIN. MFG WILLSDR CA061219022Engine · leaking(CAN) IN FLIGHT THE ENGINE OIL TEMPERATURE INCREASED ACCOMPANIED BY A LOSS OF OIL PRESSURE. THE ENGINE WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED METAL CONTAMINATION OF THE OIL SYSTEM, INTERNAL OIL LEAKAGE AND SEIZURE OF THE REDUCTION GEAR BOX.
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