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 CA070413004Control Box · failed(CAN) THE AIRCRAFT WAS BEING USED FOR CREW TRAINING WHEN, ON TAKEOFF, THE RT PROPELLER RPM DROPPED TO 30 PERCENT. THE PILOTS ABORTED THE TAKEOFF AND RETURNED TO THE RAMP. THE PILOTS NOTED THAT NP WAS STILL AT 30 PERCENT WITH THE POWER LEVER AT IDLE. THE PROPELSDR CA070405005Flapper Valve · obstructed(CAN) THE RAM AIR FLAPPER VALVE, P/N C6VF1153-1, BECAME JAMMED IN IT`S DUCT. ATTEMPTS BY THE PILOT TO RECTIFY THE PROBLEM BY MOVING THE CONTROL LEVER BACK AND FORTH RESULTED IN THE CONTROL CABLE, P/N 130-032A22.75B29.0, BECOMING KINKED AND UNSERVICEABLE. DIS-SDR CA070405006Collar · cracked(CAN) STEERING COLLAR CRACKED AT RADIUSED AREA OF ATTACH STUD TO STEERING ACTUATOR. FOUND AT ROUTINE MAINTENANCE INSPECTION (TC NR 20070405006)SDR CA070405008Torque Link · cracked(CAN) LOWER TORQUE LINK CRACKED AT ATTACHMENT LUG TO UPPER TORQUE LINK. CRACK FOUND ON ROUTINE MAINTENANCE INSPECTION (TC NR 20070405008)SDR CA070329007Governor · unserviceable(CAN) A GROUND INCIDENT OCCURRED WHERE ONE AC TAXIED INTO ANOTHER. BOTH AIRCRAFT WERE ON STRAIGHT SKIS. AFTER START-UP THE AC MOVED FORWARD FROM ITS PARKING SPOT, THEN WHEN THE PILOT MOVED THE POWER LEVER INTO REVERSE THE NR 2 PROP WENT INTO REVERSE MOMENTARSDR S9BA00107Fuel Line · crackedPERFORMED PRECAUTIONARY SHUTDOWN DUE TO A MAJOR FUEL LEAK SIGHTED COMING FROM THE LT ENGINE. REPLACED FUEL LINE FROM FCU TO TOP OF START CONTROL.SDR S9BA00207Compressor Wheel · damagedLT ENGINE VIBRATION OCCURRED WHEN MOTORED AFTER FUEL LINE REPLACEMENT. REMOVED AND HAD C/T DISK ASSEMBLY OVERHAULED INSTALLED SAME ASSEMBLY. (SULFIDATION)SDR CA070307002Buckle · damaged(CAN) WHEN COMPLYING WITH COMPANY CAMPAIGN NOTICE 010-25-10-011 AN INSPECTION FOR INTERFERENCE BETWEEN THE YOKE AND SEATBELT BUCKLE WAS CARRIED OUT IAW NM-06-29.THE RESTRAINT RELEASE MECHANISM ON PILOT AND COPILOTS SEAT BELTS CAN BE OPERATED UNINTENTIONALLY BYSDR CA070307003Skin Panel · debonded(CAN) DEBONDING OF UPPER WING SKIN, OB OF NACELLE. DEBONDING DETECTED DURING ULTRA SONIC INSPECTION IAW SB 6/543. REPAIR CARRIED OUT IAW REO6-57-30-V013 REV A. (TC NR 20070307003)SDR CA070307004Skin Panel · debonded(CAN) DEBONDING OF UPPER WING SKIN, IB OF NACELLE. DEBONDING DETECTED DURING ULTRA SONIC INSPECTION IAW SB 6/543. REPAIR CARRIED OUT IAW REO6-57-30-V012 REV A. (TC NR 20070307004)SDR CA070307006Skin · corroded(CAN) SEVERAL CORRODED RIVET HEADS FOUND ON THE LOWER SURFACE OF WING. THE AREA OF CONCENTRATION IS THE GAS PATHS FROM THE EXHAUST STACKS. REPAIRS CARRIED OUT IAW REO6-57-30-V017 (YW 85-91.25) AND REO6-57-30-V018 (YW 127-146). (TC NR 20070307006)SDR CA070307007Skin · corroded(CAN) SEVERAL CORRODED RIVET HEADS FOUND ON THE LOWER SURFACE OF WING. THE AREA OF CONCENTRATION IS THE GAS PATHS FROM THE EXHAUST STACKS. REPAIRS CARRIED OUT IAW REO6-57-30-V019 (YW 85-91.25) AND REO6-57-30-V020 (YW 122-135). (TC NR 20070307007)SDR CA070307008Skin Panel · corroded(CAN) SEVERAL CORRODED RIVET HEADS FOUND ON THE LOWER SURFACE OF WING. THE AREA OF CONCENTRATION IS THE GAS PATHS FROM THE EXHAUST STACKS. REPAIRS TO CORRODED RIVETS WAS INITIATED AND REVEALED CORROSION UNDER THE RIVET HEADS EXISTED TO A DEPTH OF 0.011. REPAIRSDR CA070223004Skin · corroded(CAN) AIRCRAFT IS IN THE PROCESS OF GOING THROUGH ITS (5) YEAR CORROSION INSPECTION. DURING INSPECTION, SEVERAL AREAS OF CORROSION WERE NOTED IN AREAS WHERE CORROSION IS USUALLY NOT FOUND. THE HORIZONTAL STAB LOWER SKIN (CENTER) WAS CORRODED AROUND SOME ANCHORSDR CA070219008Bracket · loose(CAN) WHILE FLIGHT CREW WHERE CONDUCTING A GROUND RUN, MAINTENANCE ON THE GROUND NOTED THE RT ELEVATOR WAS MOVING UP AND DOWN EXCESSIVELY. UPON INVESTIGATION, MAINTENANCE FOUND BRACKET P/N C6TPM1022-28 WITH RIVETS WORKING AND SEVERAL WHERE ACTUALLY MISSING. THSDR CA070130001Line · leaking(CAN) FLIGHT CREWS REPORTED THAT FUEL FLOW FLUCTUATES WHEN BOOST PUMPS ARE SELECTED OFF. SEVERAL VACUUM LEAKS WHERE FOUND IN THE FUEL LINES IN THE NACELLE AREA. SYSTEM SEALED AS REQUIRED, ENGINE GROUND RUNS CARRIED OUT AND NO FLUCTUATIONS NOTED AT TAKEOFF POWESDR CA070131001Connector · separated(CAN) AIRCREW REPORTED THAT THE NR 1 FUEL FLOW WAS FLUCTUATING WITH NO OTHER ENGINE PARAMETERS BEING AFFECTED. MAINTENANCE TROUBLESHOT THE SYSTEM, SWAPPED GAUGES FROM SIDE TO SIDE, PERFORMED ENGINE RUNS AND COULD NOT FAULT THE SYSTEM. AIRCRAFT WAS RELEASED FOSDR CA070212007Torque Tube · cracked(CAN) THE TAIL CONE WAS REMOVED FOR OTHER SCHEDULED MAINTENANCE. IT WAS NOTICED THAT THE ELEVATOR BELLCRANK TORQUE TUBE WAS CRACKED. THE CRACK STARTED AT THE HORN ATTACH TAPER PIN AND SPIRALED AROUND THE TORQUE TUBE APPROX 270 DEGREES. THE ASSEMBLY WAS REPLACSDR CA070117005Cable · damaged(CAN) NEW CABLE, THE BALL END OF THE TRIM CABLE IS OUT OF ROUND AND WILL NOT FIT INTO THE TRIM JACK ASSEMBLY. WHERE THE CABLE MEETS THE BALL END IT HAS BEEN BRAZED AND THE CABLE HAS NOW FRAYED AFTER ATTEMPTING TO INSTALL IT INTO HTE TRIM JACK ASSEMBLY. (TC NR SDR CA070129004Buckle · damaged(CAN) SPECIAL INSPECTION OF CREW SEAT BELT ROTORY LATCH SYSTEM PERFORMED. BOTH LT AND RT CREW SEATBELT BUCKLE ASSEMBLIES WERE CAPABLE OF BEING UNLATCHED WHEN CONTACTED BY THE CONTROL YOKE WHEN ROTATED LT OR RT WITH THE YOKE FULL AFT AND THE SEAT IN THE MOST FOSDR CA070115016Control Cable · broken(CAN) TRIM CABLE WAS FOUND BROKEN AND WAS REPLACED. THE BROKEN CABLE IS BEING ANALYZED AT THEIR LOCAL AIRWORTHINESS AUTHORITY AND WE AWAIT THE RESULTS. (TC NR 20070115016)SDR CA070103011Turbine Blades · fractured(CAN) ENGINE OIL PRESSURE AND TORQUE WERE SEEN TO FLUCTUATE IN FLIGHT FOLLOWED BY A LOUD NOISE AND AN ENGINE FLAMEOUT. SUBSEQUENT INSPECTION REVEALED METAL IN THE ENGINE OIL AND FRACTURED POWER TURBINE BLADES. MFG WILL MONITOR THE INVESTIGATION OF THE EVENT SDR CA070209006Turbine Blades · fractured(CAN) DURING CLIMB THE ENGINE EMITTED A LOUD NOISE AND SHUTDOWN UNCOMMANDED. THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE. SUBSEQUENT INSPECTION REVEALED FRACTURED POWER TURBINE BLADES. MFG WILL MONITOR INVESTIGATION OF THE INCIDENT AND ADVISE OF ROOT CAUSE SDR CA061221006Cable Assy · incorrect(CAN) WHEN AN OPERATOR TRIED TO INSTALL ONE OF THESE CABLE ASSEMBLIES HE FOUND THAT THE END THAT ENGAGES THE SERVO CAPSTAN WOULD NOT FIT PROPERLY SO THAT THE LOCK SCREW COULD BE INSTALLED. UPON INVESTIGATION IT WAS FOUND THAT THE ORIGINAL DRAWING FOR THE CABLESDR CA070105002Turbine Blades · fractured(CAN) ENGINE OIL PRESSURE WERE REPORTED TO FLUCTUATE IN CRUISE FOLLWED BY A LOUD NOISE AND AN UNCOMMANDED ENGINE SHUTDOWN. SUBSEQUENT INSPECTION REVEALED METAL DEBRIS IN THE ENGINE OIL AND FRACTURED POWER TURBINE BLADES. MFG WILL MONITOR INVESTIGATION OF THESDR CA070115010Turbine · disintegrated(CAN) DURING CRUISE FLIGHT, THE CREW NOTICED OIL PRESSURE ON THE NR 2 ENGINE FLUCTUATING BETWEEN 60-70 PSI, WITHIN SECONDS THE TQ PRESSURE STARTED TO FLUCTUATE. THE ENGINE MADE 3 BIG BANGS AND SHUTDOWN. THE CREW LANDED THE AIRCRAFT AT THE NEAREST AIRPORT WITHOSDR CA070302003Switch · tripped(CAN) FOLLOWING REMOVAL OF THE CVR FOR TESTING IT WAS DETERMINED THAT THE INERTIA SWITCH HAD BEEN PREVIOUSLY TRIPPED CAUSING THE REQUIRED DATA NOT TO BE RECORDED. A RESET OF THE SWITCH HAD THE SAME RESULTS WITH PREMATURE ACTIVATION CAUSING THE RECORDING TO STOSDR CA061129004Clamp · damaged(CAN) THIS DEFECT WAS ORIGINALLY IDENTIFIED IN THE SUBJECT AIRCRAFT FLIGHT LOG DATED OCTOBER 26, 2006.SUBSEQUENT INVESTIGATION BY OUR QUALITY ASSURANCE DEPARTMENT GENERATED THE REQUEST THAT A SDR BE FILED. THE AIRCRAFT ARRIVED IN OTTAWA FOR A SCHEDULED INSPECTSDR CA061218020Pressure Switch · failed(CAN) ON INVESTIGATION OF THE REPORTED AUTOFEATHER DEFECT, THE LT ENGINE PRESSURE SWITCH, PN 8190026, WAS FOUND TO BE DEFECTIVE. REPLACEMENT OF THE COMPONENT CURED THE PROBLEM WHICH IS CONSIDERED TO BE AN ISOLATED RANDOM FAILURE. (TC NR 20061218020)SDR CA061219020Engine · failed(CAN) DURING TAXI, THE ENGINE EMITTED A NOISE AND LOST POWER. SUBSEQUENT INSPECTION REVEALED INTERNAL ENGINE DAMAGE. MFG WILL INVESTIGATE AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.SDR S9BA00806Hinge · corrodedDURING INSPECTION, FOUND LT IB FORE FLAP OB HINGE (PN C6WF1101045) CORRODED.SDR S9BA00906Hinge · corrodedDURING INSPECTION, FOUND LT IB FORE FLAP IB HINGE (PN 6WFM1109-33) WITH ATTACHED RIB CORRODED.SDR CA061220003Turbine Blades · damaged(CAN) DURING CRUISE THE ENGINE EMITTED A LOUD NOISE ACCOMPANIED BY A DECAY ON ENGINE PARAMETERS. THE ENGINE WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED DAMAGE TO COMPRESSOR AND POWER TURBINE BLADES. MFG WILL MONITOR INVESTIGATION OF THE EVENT ANDSDR CA061019007Pressure Switch · failed(CAN) AFTER TAKE OFF WHILE REDUCING POWER FROM TAKE OFF POWER TO CLIMB, THE L/H PROP AUTOFEATHERED. AUTO FEATHER CIRCUIT BREAKER PULLED AND PROP RETURNED TO NORMAL. MAINTENANCE CONFIRMED SNAG AND REPLACED THE AUTOFEATHER PRESSURE SWITCH, CARRIED OUT GROUND RUNSDR S9BA01006Bushing · wornAT 123 KNOTS FELT OSCILLATION, OBSERVED LT WING BOUNCING UP AND DOWN. FOUND LT (V) STRUT BUSHING WORN. SEE WORK PACKAGE 10/17/06 TO 11/07/06. RELEASED AIRCRAFT FOR FUNCTIONAL CHECK FLIGHT. FUNCTIONAL CHECK FLIGHT WAS SATISFACTORY.SDR 9SBA00706Frame · corrodedCORROSION FOUND ON LT NACELLE HOOP FRAME (ANGLE FIREWALL) REMOVED AND REPLACE HOOP FRAME IAW AC 43.13-1B PARA 4.23 AND 4-6.SDR CA061013003Skin · damaged(CAN) A MAINTENANCE FACILITY RECEIVED THESE RE-LIFED WINGS FROM RW MARTIN. INCOMING INSPECTION REVEALED A LT/RT BUCKLED TOP SKIN AND DAMAGED SHROUD SKINS. THE DAMAGE DOES NOT APPEAR TO BE SHIPPING RELATED. RW MARTIN WERE NOT ABLE TO SEND AN NDT REPORT FOR DELSDR CA061013004Skin · damaged(CAN) A MAINTENANCE FACILITY RECEIVED THESE RE-LIFED WINGS FROM RW MARTIN. INCOMING INSPECTION REVEALED A LT/RT BUCKLED TOP SKIN AND DAMAGED SHROUD SKINS. THE DAMAGE DOES NOT APPEAR TO BE SHIPPING RELATED. RW MARTIN WERE NOT ABLE TO SEND AN NDT REPORT FOR DELASDR CA060920009Strut · broken(CAN) ON TAKEOFF IN ROUGH WATER THE LT FRONT FLOAT STRUT BROKE AT THE UPPER END. STRUT REPLACED. (TC NR 20060920009)SDR CA060920010Strut · broken(CAN) ON LANDING IN ROUGH WATER THE RT FRONT FLOAT STRUT BROKE AT THE UPPER END. STRUT REPLACED. (TC NR 20060920010)SDR OEZ2006F00000Oil Cap · leakingENROUTE, RT ENGINE OIL PRESSURE WAS DROPPING TO 45 PSI. AIR CREW IMMEDIATELY BEGAN TROUBLESHOOTING WITH THE CHECKLISTS. THE OIL PRESSURE LIGHT BEGAN TO FLICKER, AIRCREW SHUTDOWN THE RT ENGINE, DECLARED AND EMERGENCY WITH APPROACH AND LANDED NORMALLY SINGLE ESDR S9B2006F00004Ring · crackedREF NR (S9BA-002) DURING HSI FOUND CRACK ON THE PT VANE RING. LOOKING FROM AFT TO FWD AT 3 OCLOCK POSITION CRACK EXTENDS ACROSS INNER HOUSING THROUGH THE FILLET RADIUS AND AIRFOIL. REMOVED AND REPLACED PT VANE RING. (K)SDR CA060906016Pump · failed(CAN) THE ENGINE FLAMED OUT DURING TAKE-OFF ROLL AND THE TAKE-OFF WAS ABORTED. METAL DEBRIS WAS FOUND IN THE FUEL PUMP OUTLET FILTER. (TC NR 20060906016)SDR OEZ2006F00001Relay · shortedODOR OF BURNING WIRE AFTER LANDING FOLLOWED BY ELECTRICAL FAILURE NR 1 FOUND LT REVERSE CURRENT RELAY SHORTED OUT NR 2 FOUND REVERSE CURRENT RELAY CIRCUIT BREAKER AND BUS TIE RELAY SHORTED OUT BY THE RCR FAILURE. THE REVERSE CURRENT RELAY IS CURRENTLY IN OUR SDR CA060905008Blades · damaged(CAN) PROBLEMS WERE REPORTED WITH THE ENGINE SHORTLY AFTER TAKE-OFF. THE AIRCRAFT SUBSEQUENTLY CRASHED. PRELIMINARY INVESTIGATION EVIDENSED COMPRESSOR BLADE DISTRESS. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC NR 2006090500SDR CA060731007Oil System · leaking(CAN) DURING CLIMB, ENGINE OIL PRESSURE WAS REPORTED TO FLUCTUATE FOLLOWED BY A LOSS IN OIL PRESSURE. THE ENGINE WAS SHUTDOWN IN FLIGHT AND THE AIRCRAFT RETURNED TO POINT OF DEPARTURE. SUBSEQUENT INSPECTION REVEALED INTERNAL OIL LEAKAGE. MFG WILL INVESTIGATESDR CA060612007Leg Assy · damagedDURING A NORMAL LANDING PROCEDURE, THE LEFT MAIN LANDING GEAR BROKE OFF FOR A REASON UNKNOWN TO US. THE AIRCRAFT CONTINUED TO SKID ON THE STUD OF THE GEAR UNTIL COMING TO A COMPLETE STOP. AT THE END, THE AIRCRAFT TIPPED TO THE LEFT AND DAMAGED THE LEFT WING SDR CA060704005Fuel Control · malfunctioned(CAN) THE ENGINE WAS REPORTED TO EXHIBIT TORQUE FLUCTUATIONS IN CLIMB AND WAS SHUT DOWN IN FLIGHT. THE FUEL CONTROL UNIT WAS SUBSEQUENTLY REMOVED FOR INVESTIGATION. P&WC WILL MONITOR INVESTIGATION OF THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (SDR CA060531023Engine · making metalDURING CRUISE, ENGINE OIL PRESSURE WAS REPORTED TO DECREASE ACCOMPANIED BY AN UNCOMMANDED REDUCTION IN POWER. THE ENGINE WAS SHUT DOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED METALLIC DEBRIS ON THE ENGINE CHIP DETECTOR AND AN INABILITY TO ROTATE. P&WC WILSDR CA060516003Actuator · crackedROUTINE VISUAL INSPECTION OF THE FLAP ACTUATORS INDICATED THAT THE OUTBOARD ATTACHMENT FLANGE OF THE RT OUTBOARD FLAP ACTUATOR WAS CRACKED. THERE WAS NO EVIDENCE OF THE ACTUATOR BEING DROPPED OR OTHERWISE ABUSED. THE FLANGE WAS BENT SLIGHTLY INBOARD AND THER
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