U/A Canada PT6A-114
Service difficulty reports · 165
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 = 'PT6A114' 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 = 'PT6A114' 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 CA100127007Attach Fitting · damaged(CAN) THE HOLE FOR THE WING STRUT ATTACH BOLT APPEARED TO HAVE BEEN IMPROPERLY LINE BORED CAUSING A EGG SHAPED HOLE AT THE FACTORY BOTH FORE & AFT. FITTINGS WERE REPLACED AT THIS TIME.SDR CA100127006Oil Filter · separated(CAN) VISUAL INSP DETECTED SEPARATION OF INTERNAL SCREEN AT SEAM. TECH REP ADVISED UNIT REPLACED WITH NEW.SDR CA091207005Support Bracket · buckled(CAN) UNCOMMANDED RETRACTION OF FLAPS FROM 20 DEG TO 10 DEG ON APPROACH, RESULTING IN A DROP OF 50 FT. FLAP MOTOR CIRCUIT BREAKER POPPED. INSP FOUND THAT THE FLAP TRANSMISSION SUPPORT BRACKET PN 2611144-1 HAD BUCKLED & TWISTED PULLING THE FLAP TRANSMISSION OSDR HSYA2009092209Float Switch · brokenDURING CLIMBOUT, THE CREW ADVISED AT 500 FEET AGL THE FUEL LOW LEVEL RESERVOIR LIGHT ILLUMINATED, THE CLIMB WAS CONTINUED TO 1500 FEET, AN EMERGENCY WAS DECLARED AND THE ACFT RETURNED WITHOUT INCIDENT TO DEPARTURE. MX TROUBLESHOOT THE PROBLEM AND FOUND FAULTSDR BSYA2009029Fuel Control · malfunctionedAIRCRAFT EN ROUTE FROM CPS TO BHM WHEN THE ENGINE WAS FLUCTUATING 100LBS TORQUE IN CLIMB IN TURBULENCE, THEN IN CRUISE IN SMOOTH AIR TORQUE DROPPED 400LBS PILOT THEN ELECTED TO LAND AT MWA. REMOVED AND REPLACED FUEL CONTROL, OPS CHECKS GOOD.SDR 2009FA0000366Turbine · failedON LANDING THE PILOT SAID HE HEARD A POP AND THE ENGINE STARTED TO SPOOL DOWN. HE PULLED OFF THE RUNWAY AND STOPPED BUT THEN SAW SMOKE COMING FROM THE EXHAUST AND THOUGHT IT WAS RESIDUAL FUEL. HE THEN MOTORED THE ENGINE AND THE SMOKE TURNED BLACK. HE CALLED SDR CA090429002Turbine Blades · failed(CAN) EIR PT6A 2009-027 POWER TURBINE BLADE FAILURE.SDR CA090407016Tube · split(CAN) ACFT WAS SITTING AT THE HANGER OVERNIGHT. IN THE MORNING THE PILOTS PREPARED THE ACFT FOR THE MORNING FLIGHT. THEY TAXIED TO THE RUNWAY AND ALIGNED THE ACFT ON RUNWAY 28 FOR DEPARTURE WHEN THE LT MAIN TIRE WENT FLAT. MX WAS CALLED AND THE TIRE REPLACED. SDR 2009FA0000251Blades · crackedDURING HOT SECTION INSP, 2 COMPRESSOR TURBINE BLADES, PN 3045741-01, WERE FOUND TO HAVE CRACKS IN THE T/E OF THE BLADE. THESE CRACKS WERE FOUND ABOUT HALF WAY UP THE T/E. ONE CRACK .3750 INCH IN LENGTH. THE OTHER WAS .1875 INCH IN LENGTH. CRACKS WERE FOUND BYSDR CA090310014Tube · damaged(CAN) ACFT LANDED WITH A FLAT TIRE. THE WHEEL ASSY WAS CHANGE ON THE RUNWAY. WHEN THE TIRE WAS REMOVED IT WAS DISCOVERED THAT THE BALANCE PATCHES (2) WERE LOOSE IN THE TIRE. THE PATCHES LOOKED WORN, INDICATING THAT THEY HAD BEEN LOOSE FOR SOME TIME. SUSPECT THSDR 2009FA0000060Wire · chafedTHE PILOT REPORTED HIS TAIL BEACON INOPERATIVE. MX TECHS TROUBLESHOT THE WIRING AND FOUND THAT THE WIRING BUNDLE THAT CONTAINS THE POWER WIRE FOR THE TAIL BEACON WHERE IT ROUTES OVER THE GLOVE BOX HAD CHAFED ON THE GLOVE BOX. THE CHAFING CAUSED THE WIRE TO BSDR 2009FA0000043Shroud · gougedENG PERFORMANCE RUNS INDICATED ITT WAS EXCEEDING TARGET TEMP +20 DEGREES C. THE ENGINE WAS SPLIT AT THE C-FLANGE AND THE ENG SEPARATED TO INSPECT THE HOT SECTION. IT WAS FOUND THAT THE CT BLADE SEGMENTS HAD SHIFTED AND ALSO THERE WAS SEGMENT TIP CURL AT SEVERSDR 2008FA0000866Mount · crackedTHE CENTER ENGINE MOUNT BRACKET WAS FOUND TO HAVE CRACKS INSIDE THE ASSY AT THE TERMINATION END OF BOTH WELDS. (K)SDR 2008FA0000867Mount · crackedTHE LT ENGINE MOUNT BRACKET WAS FOUND TO HAVE CRACKS INSIDE THE ASSY AT THE TERMINATION END OF BOTH WELDS. (K)SDR MT92008F00008Transistor · burnedTHE PILOT REPORTED SMOKE IN THE COCKPIT TO ATC, DECLARED AN EMERGENCY, AND RETURNED TO DEPARTURE. THE SMOKE THAT WAS SEEN BY THE PILOT APPEARED TO BE COMING FROM UNDER THE GLARE SHIELD ABOVE THE FUEL FLOW AND FUEL QUANTITY INDICATORS. THE PILOT SAID THERE WASDR 2008FA0000657Cowling · crackedTHE SECONDARY EXHAUST COWLING WAS FOUND TO HAVE A 5.5 INCH LONG CRACK NEXT TO THE CENTER EXHAUST HANGER ROD END BRACKET. (K)SDR 2008FA0000622Cowling · crackedTHE SECONDARY EXHAUST COWLING WAS FOUND TO HAVE A 5.5 INCH LONG CRACK NEXT TO THE CENTER EXHAUST HANGER ROD END BRACKET. IT WAS NOTICED THAT ANOTHER CARAVAN IN THE HANGER FOR INSPECTION HAD THE SAME CRACK (LENGTH AND LOCATION) THAT HAD BEEN PREVIOUSLY REPAIREDSDR CA080826007Indicator · defective(CAN) OIL PRESSURE NEEDLE INDICATES HIGH OIL PRESSURE WHEN ENGINE IS OPERATING (100- 105 PSI) READS OFF OF ZERO WHEN ENGINE IS NOT OPERATING (10-15 PSI) 106.5 HRS SINCE OVERHAUL.SDR 2008FA0000602Oil Cooler · crackedUPPER MOUNTING FLANGE HAS A 1.25 INCH CRACK AGAINST OIL COOLER BODY. (K)SDR MT92008F00005Warning Light · illuminatedAFTER ENGINE INSTALLATION FROM OVERHAUL, THE PERFORMANCE RUN PRODUCED THE "AUX FUEL PUMP" AND "FUEL PRESSURE LOW" LIGHTS ON THE ANNUNCIATOR PANEL CYCLING ON AND OFF TOGETHER. THIS HAPPENS WHEN THE FUEL PRESSURE IN THE HOPPER TANK DROPS BELOW 4.75 PSI. (FUEL SDR MT92008F00002Pump · failedDURING AN OPERATIONAL INSPECTION, THE FUEL PUMP WAS REJECTED IAW SB1645. A REPLACEMENT PUMP WAS INSTALLED (TSO 0.0) AND ON THE OPERATIONAL RUN CHECKS THE FUEL PRESSURE LOW LIGHT AND THE FUEL PUMP ON LIGHT ON THE ANNUNCIATOR PANEL STARTED CYCLING WHEN THE TORQSDR 2008FA0000268Drain · pluggedDURING FLT IN MODERATE TURBULENCE THE AP STARTED TO DISCONNECT, TWICE. THIRD ATTEMPT TO ENGAGE THE AP, THE AC MADE AN UNCOMMANDED 1500 FPM DESCENT. ATTEMPT TO CORRECT THE ATTITUDE WITH THE CWS FUNCTION WAS MADE BUT THE AP WOULD NOT DISENGAGE. THE AP DISCONNSDR CA080221010Engine · failed(CAN) DURING CRUISE, A LOUD NOISE WAS HEARD FOLLOWED BY REDUCTION IN ENGINE POWER TO ZERO. THE AC LANDED ON A PUBLIC ROAD. MFG WILL CONTINUE INVESTIGATING THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20080221010)SDR COEA0703940Generator · failedFLIGHT NR 7511,STAND BY POWER LIGHT CAME ON IN FLIGHT, LOSS OF MAIN GENERATOR. PILOT SELECTED STANDBY ALTERNATOR (ON) AND CONTINUED WITHOUT ANY OTHER MALFUNCTIONS FROM THIS SYSTEM, AIRCRAFT LANDED SAFELY. REPLACED STARTER GENERATOR. (K)SDR COEA0701960Control Unit · inoperativeRETURNED TO BLOCKS: FLIGHT NR 8800, ON TAXI TO RUNWAY IN GEG STANDBY ELECTRIC GENERATOR FAULT LIGHT ILLUMINATED. ATTEMPTED RESET WAS UNABLE TO CLEAR THE FAULT, PILOT ELECTED TO RETURN TO RAMP. MAINTENANCE REMOVED AND REPLACED THE ALTERNATOR CONTROL UNIT. (KSDR COEA0701897Button · looseJUST AFTER TAKEOFF, ON FLIGHT NR 7797 THE PILOT RECEIVED A FIRE WARNING. HE DECLARED AND EMERGECY AND RETURNED. AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE DISCOVERED THE FIRE WARNING TEST BUTTON HAD FALLEN OFF CAUSING A FALSE WARNING. MAINTENANCE REINSTSDR CA070515001Relay · inoperative(CAN) A/C ABORTED TAKEOFF AUX PUMP LIGHT ON AT HIGH POWER. RELAY REPLACED, A/C GROUND RUN AT HIGH POWER NO FAULT FOUND (TC NR 20070515001)SDR CA070321006Latch · loose(CAN) LT ENGINE UPPER COWL OPENED IN FLIGHT. AIRCRAFT LANDED WITHOUT INCIDENT. AIRCRAFT WAS FLYING THROUGH TURBULENCE WHEN THE COWL OPENED. DURING THE INSPECTION OF THE COWL, IT WAS FOUND THAT ALL 3 LATCHES WERE LOOSE. THE LATCHES WERE RE-ADJUSTED. (TC NR 20SDR SBAA2124Cooling Fan · burned outUPON ARRIVAL INTO TVC PILOT HAD AN ODOR OF BURNED WIRES. AVIONICS COOLING FAN WAS FOUND TO BE INOP. INSTALLED NEW AVIONICS COOLING FAN. OPS CHECK NORMAL.SDR SBAA1106001Cooling Fan · burned outUPON ARRIVAL, PILOT HAD AN ODOR OF BURNED WIRES. AVIONICS COOLING FAN WAS FOUND TO BE INOP. INSTALLED NEW AVIONICS COOLING FAN. OPS CHECK NORMAL.SDR SBAA200600001Cooling Fan · burned outUPON ARRIVAL, PILOT HAD AN ODOR OF BURNED WIRES IN THE COCKPIT. AVIONICS COOLING FAN CIRCUIT BREAKER WAS PULLED. REPLACED AVIONICS COOLING FAN, OPS CHECK NORMAL.SDR CA060925001Fairing · loose(CAN) DURING LANDING A SLIGHT THUMP AND A VIBRATION WAS FELT. AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE INSPECTED THE AIRCRAFT AND FOUND THE RT MAIN LANDING GEAR FAIRING (GEAR TO FUSELAGE FAIRING) WAS MISSING THE LOWER PORTION. THIS FAIRING IS A ONE PIECE SDR PNSA060804Turbine Blades · failedIN CRUISE AT 9000 FT, PILOT HEARD A LOUD GRINDING NOISE & ENGINE LOST ALL POWER. DECLARED AN EMERGENCY, ATTEMPTED ENGINE RESTART, NO SUCCESS. STARTER WAS ENGAGED NG SHOWED NO ROTATION & INSTRUMENT LIGHTS DIMMED. PROP FEATHERED, NORMAL LANDING. PRELIMARY REPSDR CA060704018Adapter · fractured(CAN) AT TOP OF CLIMB, ENGINE TORQUE WAS SEEN TO FLUCTUATE FOLLOWED BY AN ENGINE LOW OIL PRESSURE WARNING. THE ENGINE WAS SHUT DOWN IN FLIGHT AND A DEAD-STICK LANDING ACCOMPLISHED. SUBSEQUENT INSPECTION REVEALED EXTERNAL OIL LEAKAGE ASSOCIATED WITH A FRACTURSDR CA060223004Jackscrew · failedELEVATOR TRIM SCREW JACK (RT) FAILED ON INSTALLATION.SDR CA060228005Jackscrew · damagedTHE LT ELEVATOR TRIM JACK WAS REMOVED AND DISASSEMBLED FOR INSPECTION AFTER THE RT TRIM JACK FAILED ON INSTALLATION. THE LT TRIM JACK WAS FOUND TO CONTAIN NO GREASE. THE JACK WAS INSPECTED, LUBRICATED IAW AMM 27-30-02, 9A, REASSEMBLED, TESTED AND RETURNED TOSDR CA060227010Compressor · seizedTHE ENGINE ACCESSORY GEARBOX CHIP DETECTOR WARNING ANNUNCIATED IN FLIGHT AND AN UNSCHEDULED LANDING WAS CARRIED OUT. SUBSEQUENT INSPECTION REVEALED SEIZURE OF THE COMPRESSOR SECTION. P&WC WILL INVESTIGATE THE INCIDENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABSDR 2005AP012502Roll Pin · shearedBOTH PRIMARY AND STAND-BY FLAP ACTUATOR WAS IN-OPERATIVE. ACTIVATION OF EITHER SYSTEM WOULD CAUSE THE RESPECTIVE CIRCUIT BREAKER TO OPEN. DISASSEMBLY OF THE ACTUATOR REVEALED A SHEARED ROLL PIN AND ROUGH WORM SHAFT BEARING.SDR 2005AP052501Roll Pin · shearedBOTH PRIMARY AND STAND-BY FLAP ACTUATOR WAS INOPERATIVE. ACTIVATION OF EITHER SYSTEM WOULD CAUSE THE RESPECTIVE CIRCUIT BREAKER TO OPEN. DISASSEMBLY OF THE ACTUATOR REVEALED A SHEARED ROLL PIN AND ROUGH WORM SHAFT BEARING.SDR MPFACTUATOR1Actuator · inoperativeBOTH PRIMARY AND STAND-BY FLAP ACTUATOR WAS INOPERATIVE. ACTIVATION OF EITHER SYSTEM WOULD CAUSE THE RESPECTIVE CIRCUIT BREAKER TO OPEN. DISASSASEMBLY OF THE ACTUATOR REVEALED A SHEARED ROLL PIN AND ROUGH WORM SHAFT BEARING.SDR AWHA120805Spline · corrodedPRECAUTIONARY INSPECTION OF THE FUEL PUMP DRIVE SPLINE IN ACCORDANCE WITH PRATT AND WHITNEY PT6 MAINTENANCE MANUAL, FUEL PUMP COUPLING IN-SITU INSPECTION 73-10-02 PAGE 210, PARAGRAPH 8D, MAINTENANCE FOUND THE FUEL PUMP DRIVE SPLINE SEVERELY CORRODED AND DAMAGSDR 120805BSpline · corrodedPRECAUTIONARY INSPECTION OF THE FUEL PUMP DRIVE SPLINE IN ACCORDANCE WITH PRATT AND WHITNEY PT6 MAINTENANCE MANUAL, FUEL PUMP COUPLING IN-SITU INSPECTION 73-10-02 PAGE 210, PARAGRAPH 8D, MAINTENANCE FOUND THE FUEL PUMP DRIVE SPLINE SEVERELY CORRODED AND DAMAGESDR AWHA5005Spline · corrodedPRECAUTIONARY INSPECTION OF THE FUEL PUMP DRIVE SPLINE IN ACCORDANCE WITH PRATT AND WHITNEY PT6 MAINTENANCE MANUAL, FUEL PUMP COUPLING IN-SITU INSPECTION 73-10-02 PAGE 210, PARAGRAPH 8D, MAINTENANCE FOUND THE FUEL PUMP DRIVE SPLINE SEVERELY CORRODED AND DAMAGESDR 5005120805Spline · corrodedPRECAUTIONARY INSPECTION OF THE FUEL PUMP DRIVE SPLINE IN ACCORDANCE WITH PRATT AND WHITNEY PT6 MAINTENANCE MANUAL, FUEL PUMP COUPLING IN-SITU INSPECTION 73-10-02 PAGE 210, PARAGRAPH 8D, MAINTENANCE FOUND THE FUEL PUMP DRIVE SPLINE SEVERELY CORRODED AND DAMAGSDR 2005F00114Spline · corrodedPRECAUTIONARY INSPECTION OF THE FUEL PUMP DRIVE SPLINE IN ACCORDANCE WITH PRATT AND WHITNEY PT6 MAINTENANCE MANUAL, FUEL PUMP COUPLING IN-SITU INSPECTION 73-10-02 PAGE 210, PARAGRAPH 8D, MAINTENANCE FOUND THE FUEL PUMP DRIVE SPLINE SEVERELY CORRODED AND DAMAGSDR 2005F00115Spline · corrodedPRECAUTIONARY INSPECTION OF THE FUEL PUMP DRIVE SPLINE IN ACCORDANCE WITH PRATT AND WHITNEY PT6 MAINTENANCE MANUAL, FUEL PUMP COUPLING IN-SITU INSPECTION 73-10-02 PAGE 210, PARAGRAPH 8D, MAINTENANCE FOUND THE FUEL PUMP DRIVE SPLINE SEVERELY CORRODED AND DAMAGSDR 2005F00116Spline · corrodedPRECAUTIONARY INSPECTION OF THE FUEL PUMP DRIVE SPLINE IN ACCORDANCE WITH PRATT AND WHITNEY PT6 MAINTENANCE MANUAL, FUEL PUMP COUPLING IN-SITU INSPECTION 73-10-02 PAGE 210, PARAGRAPH 8D, MAINTENANCE FOUND THE FUEL PUMP DRIVE SPLINE SEVERELY CORRODED AND DAMAGSDR 2005F00111Pump · corrodedPRECAUTIONARY INSPECTION OF THE FUEL PUMP DRIVE SPLINE IAW MM, FUEL PUMP COUPLING IN-SITU INSPECTION 73-10-02 PAGE 210, PARAGRAPH 8D, MAINTENANCE FOUND THE FUEL PUMP DRIVE SPLINE SEVERELY CORRODED AND DAMAGED TO THE POINT OF NEAR FAILURE. THE FUEL PUMP ASSEMSDR 2005F00112Pump · corrodedPRECAUTIONARY INSPECTION OF THE FUEL PUMP DRIVE SPLINE IAW MM, FUEL PUMP COUPLING IN-SITU INSPECTION 73-10-02 PAGE 210, PARAGRAPH 8D, MAINTENANCE FOUND THE FUEL PUMP DRIVE SPLINE SEVERELY CORRODED. THE FUEL PUMP ASSEMBLY WAS REPLACED WITH A FRESH OVERHAULED SDR 2005F00113Spline · corrodedPRECAUTIONARY INSPECTION OF THE FUEL PUMP DRIVE SPLINE IAW MM, FUEL PUMP COUPLING IN-SITU INSPECTION 73-10-02 PAGE 210, PARAGRAPH 8D, MAINTENANCE FOUND THE FUEL PUMP DRIVE SPLINE SEVERELY CORRODED. THE FUEL PUMP ASSEMBLY WAS REPLACED WITH A FRESH OVERHAULED
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