U/A Canada PT6A-20

Service difficulty reports · 197

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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 = 'PT6A20'
  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.

SDR CA050912004Mount · broken(CAN) AFTER TAKEOFF, PILOT ENCOUNTERED PWR LEVER MISMATCH AS REDUCED TO CLIMB POWER. REPORTED PROBLEM AND LANDED UNEVENTFULLY. INVESTIGATION REVEALED THAT TOP ENGINE MOUNT ON NR 1 ENG HAD BROKEN AT A POINT BETWEEN FLANGE AND BASE. THIS CAUSED ENG TO SAG ENOSep 9, 2005 · Dhav DHC6100 · Engine Mount SectionSDR CA050824008Blades · damaged(CAN) DURING CLIMB, THE ENGINE EXHIBITED A SQUEALING NOISE ACCOMPANIED BY AN UNCOMMANDED POWER REDUCTION. THE ENGINE WAS SHUTDOWN IN FLIGHT AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE. SUBSEQUENT INSPECTION REVEALED COMPRESSOR AND POWER TURBINE BLADE DAMAug 6, 2005 · Pilats PC6 · Turbine Engine Compressor SectionSDR CA050728008Switch · failedDURING CLIMB-OUT, THE FLT CREW EXPERIENCED NR 2 ENGINE AND PROP SURGING. ENG POWER WAS REDUCED, AND PROPS ADJUSTED TO MIN GOVERNING. IN THIS CONFIGURATION THE SURGING WAS NOT PRESENT. FLIGHT CREW DIVERTED TO A MAINTENANCE BASE AND LANDED UNEVENTFULLY WITHOUJul 22, 2005 · Dhav DHC6100 · Propeller Controlling SystemSDR CA050714003Cover · chafedON ENGINE SHUTDOWN, THE CAPTAIN HEARD A RUBBING SOUND EMANATING FROM THE NR 1 ENGINE. TURNING THE PROPELLER BY HAND REPRODUCED THE RUBBING SOUND. THE POWER SECTION WAS REMOVED FOR INVESTIGATION. REMOVAL OF THE PT WHEEL REVEALED THAT THE NR 3 BEARING COVER IJul 9, 2005 · Dhav DHC6100 · Turbine SectionSDR CA050711007Strut · damaged(CAN) DURING WALKAROUND, THE FLIGHT CREW OBSERVED A RIVET HEAD MISSING FROM THE OUTSIDE OF THE LOWER LUG OF THE LT FORWARD FLOAT STRUT. THE AIRCRAFT WAS FERRIED TO MAINTENANCE WHERE THE STRUT WAS REMOVED AND INSPECTED. THE RIVET STEM SHOWED SIGNS OF INTERNALJul 8, 2005 · Dhav DHC6200 · Main Landing Gear Strut/Axle/TruckSDR CA050708004Pump · failedDURING EMMA CHECK, THE NR 1 FUEL SYSTEM STRAINER WAS FOUND TO BE HEAVILY CONTAMINATED WITH A FINE, GRITTY SUBSTANCE THAT STAYED SUSPENDED IN THE FUEL. FUEL TANKS AND DRAINS WERE FOUND TO BE CLEAR. FURTHER INVESTIGATION REVEALED THAT THE OUT PUT FROM THE NR 1Jul 2, 2005 · Dhav DHC6100 · Fuel Boost PumpSDR CA050524003Connecting Rod · bindingDURING OVERHAUL AND FUNCTION TESTING, THE INTAKE DEFLECTOR ACTUATOR WAS FOUND TO BE BINDING DURING OPERATION. THE CONNECTING ROD HAD BEEN ASSEMBLED AND RIGGED IAW THE CMM CH 71-60-01, FIGURE 1, PAGE 5, WITH THE ROD ENDS AT 90 DEGREES TO EACH OTHER. IT WAS FOMay 24, 2005 · Dhav DHC6100 · Air Intake Anti/De-Ice SystemSDR CA050419003Drive Assy · inoperative(CAN) DURING TAKEOFF ROLL THE ENGINE EXPERIENCED AN UNCOMMANDED SHUTDOWN. TROUBLESHOOTING REVEALED A WORN FUEL PUMP DRIVE. THE FUEL PUMP WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.Mar 29, 2005 · Beech B90 · Engine Fuel PumpSDR CA050323010Bracket · corroded(CAN) DURING THE FIVE YEAR CORROSION CHECK, BOTH RUDDER TORQUE TUBE ATTACH BRACKETS WERE FOUND TO BE HEAVILY RUSTED FROM THE INSIDE. THERE WAS NO EVIDENCE OF CORROSION PROOFING HAVING BEEN INSTALLED ON THE INSIDE OF THE BRACKETS. AIRCRAFT IS OPERATED IN A CORMar 21, 2005 · Dhav DHC6100 · Rudder StructureSDR CA050309013Csu · failed(CAN) ON RUNUP AFTER INSTALLATION, IT WAS FOUND THAT THE OVERHAULED PROPELLER CONTROL UNIT WOULD NOT FUNCTION PROPERLY. THE PROPELLER REMAINED IN THE BETA MODE AND THERE WAS NO CONTROL OTHER THAN FEATHER/UNFEATHER. ANY ADDITION OF POWER RESULTED IN THE PROPEMar 6, 2005 · Dhav DHC6200 · Propeller Controlling SystemSDR ACS2005F00000Stiffener · crackedDURING INSPECTION, IT HAS BEEN FOUND THAT 4 OF 4 AIRCRAFT HAVE HAD A CRACK ORIGINATING FROM THE TOP RIVET OF THE AFT STIFFENER, RT SIDE OF NOSE WHEEL WELL. THE CRACK HAS BEEN IN THE SKIN SPREADING IN BOTH FORWARD AND AFT. (K)Mar 2, 2005 · N7165Y · Beech 65A901 · Fuselage Miscellaneous StructureSDR CA050207001Tube · corroded(CAN) INVESTIGATION OF A (FUEL SMELL IN THE CABIN) AND A MINOR EXTERNAL FUEL LEAK REVEALED THAT WELDED FUEL TUBE ASSY BETWEEN FUEL TANK AND FLEX HOSE TO THE WING STRUT WAS LEAKING. REMOVAL OF ADEL CLAMP REVEALED CORROSION PITS UNDERNEATH WITH ASSOCIATED FUEL Feb 5, 2005 · Dhav DHC6100 · Aircraft Fuel Distribution SystemSDR CA050128007Hinge Bracket · damaged(CAN) LOOSE RIVETS ATTACHING CENTER FLAP HINGE BRACKET TO IB AND OB PORTIONS OF FORE FLAP ASSY. HIDDEN PROBLEM DOES NOT REALLY SHOW UP UNTILL YOU TAKE THE FLAP OFF. FORE FLAP DISASSEMBLED AND RIVETS REPLACED WITH NEW.Nov 20, 2004 · Dhav DHC6200 · Trailing Edge FlapsSDR CA041115004Generator · intermittent(CAN) ON CLIMB OUT THE PILOT OBSERVED THAT ONLY ONE GENERATOR WAS ACCEPTING LOAD. DECIDED TO RETURN TO DEPARTURE AERODROME WITHOUT CARRYING OUT ANY CONFIRMATION CHECKS. A SUBSEQUENT MAINTENANCE INSPECTION DETERMINED THAT AT LIGHT ELECTRICAL LOADS BOTH GENERANov 11, 2004 · Beech 99 · DC Generator-AlternatorSDR CA041104009Switch · failed(CAN) WHILE TROUBLESHOOTING A RECURRENT DC GENERATION SNAG, THE GENERATOR BUSS-TIE SWITCH WAS FOUND TO BE FAILING INTERMITTENTLY. THE SWITCH WAS REPLACED AND THE SNAG CLEARED. THIS SWITCH IS NOT A TRACKABLE ITEM AND THERE ARE NO EXISTING RECORDS OF IT EVER HAOct 26, 2004 · Dhav DHC6100 · DC Generating SystemSDR CA040928014Engine · failed(CAN) ON DESCENT TO LAND, THE PILOT HEARD A LOUD BANG AND LOSS OF TQ IN THE LT ENGINE. ALL OTHER INDICATIONS WERE NORMAL. THEY SECURED THE LEFT ENGINE AND MADE A NORMAL LANDING.Sep 27, 2004 · Dhav DHC6200 · Engine (Turbine/Turboprop)SDR CA040927007Door · inoperative(CAN) ON APPROACH, AT 20 MILES OUT AND 2500 FT ASL THE CABIN DOOR OPENED. FLIGHT SERVICES WAS INFORMED AND THE AIRCRAFT LANDED UNEVENTFULLY. THE COPILOT CLOSED THE DOOR AFTER LANDING. THE DOOR AND SURROUND WERE INSPECTED NO DAMAGE FOUND.Sep 24, 2004 · Beech 99 · Passenger/Crew DoorsSDR CA040825012Engine · shutdown(CAN) THE AIRCRAFT WAS ON THE TAKE OFF ROLE IN LUTSLE KE (SNOWDRIFT) TO FLY TO EKATI (YOA). AT 80 KNOTS A LARGE DROP IN POWER WAS FELT ON THE LEFT SIDE WITH A YAW TOTHE LEFT. THE TAKE OFF WAS REJECTED ANDTHE AIRCRAFT BROUGHT TO A STOP SAFELY ON THE RUNWAY. TAug 25, 2004 · Beech 65A90 · Engine (Turbine/Turboprop)SDR CA040804011Fuel Control · failed(CAN) WHEN THE FLIGHT CREW REDUCED POWER ON FINAL APPROACH, NR 1 ENGINE FAILED TO RESPOND TO POWER LEVEL INPUT, AND REMAINED AT 15 LBS TORQUE. THE TORQUE THEN SLOWLY DROPPED TO IDLE WITHOUT ANY POWER LEVER INPUT AND A LANDING WAS COMPLETED WITHOUTFURTHER INCIAug 3, 2004 · Dhav DHC6200 · Fuel Control/Turbine EnginesSDR MWR2004F00000Inverter · failedAIRCRAFT WAS RESENT TO MAINTENANCE FOR REPORTED SMOKE IN COCKPIT. PILOT REPORTED LOSS OF NR 1 INVERTER CIRCUIT BREAKER POPPED. TROBLESHOT PROBLEM TO PRIMARY INVERTER UNIT PC-17.Jul 22, 2004 · N70264 · Beech 65A901 · AC InverterSDR CA040513008Spring · damaged(CAN) ON TAKE OFF ROLL, PWR SET TO 1290 FT LBS. AFTER ROTATION NOTICED TORQUE INCREASING ON RT ENG. FO ATTEMPTED TO REDUCE PWR BUT PWR LEVER WOULD NOT MOVE. TORQUE INCREASED TO APPROX 1500 FT LBS FOR ABOUT 90 SECONDS. AFTER REACHING SAFE ALTITUDE RT ENG SHMay 12, 2004 · Beech 99 · Power LeverSDR 040604Bolt · damagedTHE ENGINE WAS SPLIT AT THE (C) FLANGE. AFTER REMOVAL OF THE C.T. DISC, IT WAS NOTED THAT 2 BOLTS HOLDING THE INNER EXIT DUCT TO THE ENGINE HAD SHEARED OFF AND WERE LODGED IN THE AREA, WITH THE REMAINDER OF THE BOLT SHANKS LEFT IN THE BOLT HOLES. DAMAGE WAS Apr 6, 2004 · N30HF · Beech C90 · FastenersSDR 033104Bolt · backed outPILOT REPORTS (GRINDING) SOUND WHEN PROPELLER IS SPUN BY HAND. THE ENGINE WAS SPLIT AT THE (C) FLANGE WHERE DEBRIS WAS NOTED AT THE 6 O'CLOCK AREA BETWEEN THE COMPRESSOR TURBINE BLADES AND SHROUD SEGMENTS. AFTER REMOVAL OF THE CT DISK, IT WAS NOTED THAT FOUR BMar 24, 2004 · N30HF · Beech C90 · Turbine Engine Compressor SectionSDR AHT2004F00000Clevis Pin · brokenPILOT REPORTED A LOUD NOISE FROM THE CABIN DOOR FOLLOWED BY RAPID DEPRESSURIZATION. INSPECTION OF THE CABIN DOOR REVEALED A BROKEN CLEVIS PIN IN THE LINKAGE GOING TO THE FUEL UPPER LATCH HOOK. THE LATCH HOOK AND LINKAGE IN THIS AREA ARE ON A REPLACEMENT SCHEFeb 27, 2004 · N976JT · Beech C90 · Passenger/Crew DoorsSDR CA031119002Governor · failed(CAN) NR 1 ENGINE POWER SURGING PRIOR TO LANDING, AFTER LANDING ENGINE FLAME OUT OCCURED.Nov 13, 2003 · Dhav DHC6100 · Turbine GovernorSDR FF22003F00000Engine · making metalDURING A PREFLIGHT INSPECTION, THE LT PROPELLER WAS FOUND TO BE SEIZED. THIS LED TO AN INSPECTION OF THE CHIP DETECTOR WHICH REVEALED METAL CHIPS. THE RT ENGINE CHIP DETECTOR WAS THEN INSPECTED. METAL CHIPS WERE ALSO PRESENT. BOTH ENGINES WERE REMOVED AND Nov 1, 2003 · N65KA · Beech C90 · Engine (Turbine/Turboprop)SDR CA030925006Switch · shorted(CAN) WHILE TAXIING FROM DOCK, NR 1 ENGINE DID NOT RESPOND TO (REVERSE) COMMAND BUT POWERED UP TO FORWARD MODE. FOUND WIRING WRAP INTERFERED WITH PROP RESET SWITCH IN OVERHEAD POWER LEVER QUADRANT. MODIFICATION WAS COMPLETED IAW DHC-6-100, MOD6/1912 (INSTALLATSep 1, 2003 · Dhav DHC6100 · Propeller/Propulsor System WiringSDR CA030731018Wire · chafed(CAN) SHORTLY AFTER TAKE OFF FROM FORT SMITH THE OIL PRESSURE INDICATION ON THE LT ENGINE DROPPED TO ZERO AND THE OIL PRESSURE LIGHT CAME ON. A PRECAUTIONARY SHUTDOWN WAS CARRIED OUT AND THE A/C RETURNED TO FORT SMITH. ON INVESTIGATION IT WAS DISCOVERED THAT Jul 30, 2003 · Beech 99 · Nacelle/Pylon System WiringSDR CA030723005Switch · misinstalled(CAN) NR 1 ENGINE, BETA BACK-UP SYSTEM, STEADY BLUE LIGHT ILLUMINATED IN CRUISE. FAULT FOUND TO BE KLIXON SPRING PN KX5, DRILLED MOUNTING HOLES NOT LINING UP WITH SWITCH KX511.Jul 19, 2003 · Dhav DHC6200 · Propeller Feathering/ReversingSDR AUS20030500Control Cable · frayed(AUS) AILERON CABLES PNO C6CW1031-1 (2OFF) AND PNO C6CW1032-1 CONTAINED BROKEN STRANDS IN AREA OF WING ROOT FAIRLEADS.Apr 24, 2003 · Dhav DHC6200 · Aileron Control SystemSDR CA030424007Nozzle · leaking(CAN) HEATER UNSERVICEABLE, LEAK FOUND ON HEAD ASSY. PARTS INSTALLED, NOZZEL, GASKETS, ELEC GROUND, ELEC WASHERS, GASKET HEAD, IGN, IGN UNIT, VALVE, BRUSH KIT, FILTER, VENT BLOWER MOTOR O/H. HEATER, SMOKY BLACK, PARTS INSTALLED, REG VALVE, VALVE, IGN, EXHAUST Mar 28, 2003 · Beech B90 · Heating SystemSDR CA030127005Switch · broken(CAN) ON APPROACH , THE LANDING GEAR WAS SELECTED DOWN, BUT THE GEAR DID NOT EXTEND. FIVE ATTEMPTS WERE MADE TO EXTEND THE GEAR NORMALLY AND NO JOY. THE GEAR WAS EXTENDED USING THE EMERGENCY EXTENSION SYSTEM. THE PILOT NOTED THAT IT WAS DIFFICULT TO EXTEND. TJan 25, 2003 · Beech 65A90 · Landing Gear Position and WarningSDR CA021120007Gear · worn(CAN) FUEL PUMP WAS REMOVED FROM ENGINE DURING ENGINE CONVERSION FROM PT6A-20 TO PT6A-27. THE PUMP WAS SENT TO PWC FOR BENCH TEST AND INHIBITING. CONTRACTOR ASSERTS THAT THE PUMP WAS TESTED AND THAT THE SEALS WERE LEAKING. DISMANTLED THE PUMP AND FOUND THAT THNov 20, 2002 · Dhav DHC6200 · Engine Fuel PumpSDR CA021113005Case · cracked(CAN) CRACK FOUND IN CASE 6 O`CLOCK POSITION BY FUEL DUMP VALVE.Nov 6, 2002 · Dhav DHC6100 · Engine (Turbine/Turboprop)SDR CA021016027Switch · failed(CAN) AIRCRAFT WAS TAXIING AWAY FROM DOCK WHEN FLIGHT CREW DEMANDED REVERSE POWER FROM NR 2 ENGINE. IT FAILED TO RESPOND AND AIRCRAFT HIT THE DOCK WITH FRONT OF RT FLOAT. FAILURE OF PROP TO RESPOND TO POWER LEVER INPUT IS ATTRIBUTED TO THE PROP OVERSPEED TESOct 13, 2002 · Dhav DHC6100 · Propeller Controlling SystemSDR CA021016025Case · cracked(CAN) DURING INSPECTION, CRACK FOUND ALONG WELDED SEAM.Oct 7, 2002 · Dhav DHC6 · Engine (Turbine/Turboprop)SDR CA021001009Terminal · loose(CAN) ON DESCENT INTO FORT SMITH FROM FORT CHIPEWYAN, THE CREW NOTICED AN ELECTRICAL SMELL, FOLLOWED SHORTLY BY SMOKE.ALL ELECTRICAL POWER WAS TURNED OFF.ALL NON ESSENTIAL FUNCTIONS WERE TURNED OFF THEN POWER WAS TURNED BACK ON. THE SMELL REAPPEARED.POWER WASSep 30, 2002 · Beech 99 · Electrical Power System WiringSDR CA021011002Engine · overtorqued(CAN) AIRCRAFT HIT LARGE WAVE SWELL AND CREW INADVERTENTLY ALLOWED POWER LEVER TO ADVANCE FORWARD TO OVER TORQUE ENGINE. POWER SECTION WAS REPLACED.Sep 26, 2002 · Dhav DHC6200 · Engine (Turbine/Turboprop)SDR CA020913012Longeron · cracked(CAN) NR 2 ENGINE NACELLE LONGERON CRACKED ON INBOARD SIDE.Sep 5, 2002 · Dhav DHC6 · Nacelle/Pylon, Longeron/StringerSDR CA020627010Longeron · cracked(CAN) CRACK FOUND IN LONGERON IN NACELLE AS PER CF-81-07R4 (DHC SB6/509)Jun 22, 2002 · Dhav DHC6100 · Nacelle/Pylon, Frame/Spar/RibSDR CA020617004Cover · failed(CAN) THE PLASTIC COVER UNDER THE PILOT SEAT THAT PROTECTS THE AILERON PULLEY AND CABLE WAS DAMAGED. THE AIRCRAFT HIT SOME TURBULENCE AND A SMALL ROCK CAME OFF THE FLOOR AND DOWN INTO THE PULLEY BETWEEN THE CABLE AND PULLEY JAMMING THE CONTROL. AIRCRAFT MADE AMay 27, 2002 · Dhav DHC6200 · Fuselage Miscellaneous StructureSDR CA020627011Sleeve · loose(CAN) DURING INSPECTION SLEEVE FOUND LOOSE.May 27, 2002 · Dhav DHC6100 · Elevator StructureSDR AUS20021467Arm · corroded(AUS) LH OUTBOARD AILERON HINGE ARM CONTAINED EXFOLIATION CORROSION AROUND BOLT HOLE.May 24, 2002 · Dhav DHC6100 · AileronsSDR CA020507013Bolt · sheared(CAN) DURING ENGINE REMOVAL OF A PT6A-20 FROM A DHC-6-200, TWO OF THE TWELVE (12) LEFT HAND ENGINE MOUNT BOLT SHEARED OFF. 1 BOLT TOP MOUNT, 1 BOLT R/H SIDE MOUNT. BOTH BOLTS FOUND BROKEN OFF AT AREA WHERE SHANK AREA IS REDUCED . BOTH BOLTS TURNED APPROX 1/4 OApr 24, 2002 · Dhav DHC6200 · Engine Mount SectionSDR AUS20020474Engine · making metal(AUS) ENGINE SURGING. INVESTIGATION FOUND METAL CONTAMINATION OF THE ENGINE.Feb 11, 2002 · Piper PA36285 · Engine (Turbine/Turboprop)SDR CA020124002Wire · shorted(CAN) WIRE INSULATION WAS FOUND BURNED AND APPEARED TO HAVE SHORTED OUT ON OVERHEAD SWITCH PANEL IN FLIGHT COMPARTMENT, WHICH CAUSED ELECTRICAL BURNING ODOR IN THE FLIGHT DECK.Jan 23, 2002 · Dhav DHC6100 · Windshield/Door Rain/Ice RemovalSDR CA020121011Compressor · failed(CAN) ENGINE SENT FOR INVESTIGATION & REPAIR AFTER IT FOUND THAT ENGINE MAKING RUBBING NOISE COMING FROM COMPRESSOR SECTION WHILE SCHEDULE HSI BEING PERFORMED. THE COMPRESSOR HAD SUFFERED EXTENSIVE DAMAGE. DAMAGE STARTED WITH RUBBING AT 1ST STAGE COMPRESSOR Jan 7, 2002 · Turbine Engine Compressor SectionSDR AUS20020012Bolt · cracked(AUS) TAILPLANE LIFT STRUT CLEVIS BOLT CRACKED IN AREA OF FIRST THREAD ON THE HEAD END OF THE BOLT.Jan 2, 2002 · Piper PA36285 · Horizontal Stabilizer StructureSDR AUS20011405Blade · failed(AUS) LT ENGINE INTERNAL FAILURE. INITIAL REPORTS INDICATE POWER TURBINE BLADE FAILURE.Nov 26, 2001 · Dhav DHC6200 · Turbine SectionSDR CA011210009Drain Valve · broken(CAN) DURING THE LATTER PART OF A FLIGHT THE RT NACELLE WAS SHOWING A DECLINE IN DUEL CAPACITY ABOVE NORMAL. WHEN REACHING THE DESTINATION IT WAS DISCOVERED THAT FUEL WAS ESCAPING FROM THE RT FUEL MANIFOLD DRAIN. UPON FURTHER INVESTIGATION IT WAS FOUND THAT THOct 29, 2001 · Beech 99 · Engine Drains
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