U/A Canada PT6A-34

Service difficulty reports · 465

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 = 'PT6A34'
  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 CA080902005Housing · broken(CAN) WHEN LANDING AT THE AIRPORT ON A TRAINING FLIGHT THE NLG PARTIALLY RETRACTED TOWARDS THE REAR OF THE ACFT. THE ACFT PITCHED RT AND FULL LT BRAKE WAS USED TO KEEP THE ACFT ON THE RUNWAY. THE ACFT MOMENTARILY LT THE RT SIDE OF THE RUNWAY AND STRUCK A RUNWAAug 31, 2008 · Emb EMB110P1 · Main Landing Gear Strut/Axle/TruckSDR 2008FA0000410Turbine · damaged06/20/2008 REPORT: ON 5/27/08 AC UNDER LOAD IN TURN EXPERIENCED ENGINE FAILURE RESULTING IN ACCIDENT. LOUD BANG! ENGINE QUIT. CT TURBINE TEETH MISSING, NR 2 BEARING DESTROOYED. 1026.1 HOURS ON PMA BLADES PQ0812NE. (K) (NTSB: DFW08CA155)May 27, 2008 · N3105E · Ayres S2RT34NORMAL · Turbine SectionSDR CA080702009Drive Shaft · distressed(CAN) ACCORDING TO REPORTS, CREW DECLARED AN EMERGENCY DUE TO ENGINE DISTRESS. DURING SUBSEQUENT LANDING, A/C EXITED THE RUNWAY BEFORE HITTING A DITCH. THE LANDING GEAR COLLAPSED AND THE NOSE OF THE A/C WAS SEVERELY DAMAGED. THE RUNWAY EXCURSION WAS CAUSED BY Apr 22, 2008 · Emb EMB110* · Engine Fuel PumpSDR CA080402008Brushes · wornSTARTER WOULD NOT OPERATE TO START ENGINE. (TC NR 20080402008)Mar 14, 2008 · Dhav DHC2MK3 · Starter-GeneratorSDR CA080212001Adapter · cracked(CAN) UPON COMPLIANCE WITH SB 6/540 (WING-FRONT SPAR ADAPTER ASSEMBLY (P/N C6WM1027-1) INSPECTION FOR CRACKS) A CRACK WAS FOUND ON THE LT FRONT SPAR ADAPTER. REPLACED LT FRONT SPAR ADAPTER ASSY PN C6WM1027-1 WITH PN C6WM1027-3 IAW SB NR 61542. (TC NR 200802120Feb 12, 2008 · Dhav DHC6300 · Wing SparSDR CA071115010Rib · cracked(CAN) RIB FLANGE FOUND CRACKED ON IB SIDE WHERE IT IS RIVETED TO THE TOP SKIN CORRUGATIONS. CRACKING FOUND WHEN INSPECTING RIBS 8-22 IAW MFG STRUCTURAL LIFE LIMITS. (TC NR 20071115010)Nov 12, 2007 · Dhav DHC6300 · Fuselage Main, BulkheadSDR CA080213009Worm Drive · stripped(CAN) AFTER LANDING, THE WING FLAPS OF AN AC COULD NOT BE RETRACTED. THE ASYMMETRY WARNING SYSTEM HAD BEEN TRIPPED. THE LT AND RT FLAP ACTUATORS WERE REPLACED WITH OVERHAULED UNITS AND THE AC WAS DISPATCHED. UPON DISASSEMBLY OF THE ACTUATOR AT THE OVERHAUL SHONov 1, 2007 · Emb EMB110P1 · Trailing Edge Flap ActuatorSDR ERH2007F00000Spar · crackedPILOT REPORTED A CRACK FOUND ON THE LT ELEVATOR WHILE PERFORMING A PREFLIGHT INSPECTION. THE ELEVATOR WAS REMOVED FROM THE AIRCRAFT FOR CLOSER INSPECTION. THE CRACK WAS IN THE FORWARD SPAR AND HAD ORIGINATED FROM UNDER THE OB ATTACH FITTING. FATIGUE. RECOMMSep 8, 2007 · N727KT · Dhav DHC3 · Elevator, Spar/RibSDR 2007FA0000917Rod · brokenDURING A 150 HR INSPECTION THE LOWER FUEL CONTROL ROD WAS FOUND BROKEN ON THREADED SHAFT WHERE IT SCREWS INTO COUPLING. IT LOOKS LIKE IT MAY HAVE BEEN BENT AND A MORE DETAILED INSPECTION OF THIS COMPONENT SHOULD OCCUR. (K)Aug 20, 2007 · N621KC · Emb EMB110P1 · Fuel Control/Reciprocating EnginesSDR CA071016016Engine · power loss(CAN) DURING SPRAYING OPERATIONS THE ENGINE EMITTED A LOUD NOISE AND LOST POWER, RESULTING IN A FORCED LANDING.Aug 20, 2007 · Airtrc AT401 · Engine (Turbine/Turboprop)SDR CA070824002Cylinder · corroded(CAN) DURING A WHEELS DOWN LANDING OF AN AMPHIBIOUS EQUIPPED AIRCRAFT, THE LANDING GEAR COLLAPSED. UPON INSPECTION, CORROSION WAS NOTED UNDER THE (ZAP STRAPS), WHICH WERE INSTALLED BY THE MANUFACTURER, ON BOTH LT AND RT NOSE GEAR ACTUATING CYLINDERS. ON THEAug 19, 2007 · Dhav DHC3 · Wheel/Ski/FloatSDR CA070810001Cover · damaged(CAN) THIS TURBO OPERATING AMPH FLOATS WAS ON DESCENT TO LAND AT ITS HOME AIRPORT WHEN THERE WAS NO GEAR DOWN INDICATION ON RT MAIN WHEEL. PILOT ASKED PASSENGER IN THE RT SEAT TO LOOK AT THE TOP OF FLOATS TO CHECK TIE-DOWN ROPES, AND IT WAS NOTICED THAT THE ENAug 9, 2007 · Dhav DHC2MK3 · Emergency Flotation SectionSDR CA071001011Duct · damaged(CAN) WHILE PERFORMING A BOROSCOPE INSPECTION DURING A REGULARLY SCHEDULED FUEL NOZZLE CHANGE, DAMAGE WAS FOUND ON THE LARGE EXIT DUCT (LED). THE LED WAS CHANGED AND UPON CLOSER INSPECTION IT WAS FOUND THAT A LARGE HOLE HAD BEEN BURNED THROUGH ONE LAYER OF THEJul 15, 2007 · Dhav DHC3 · Turbine Engine Combustion SectionSDR CA070524003Strut · cracked(CAN) DURING ANNUAL INSPECTION A (4 TO 5) CRACK WAS FOUND. THE CRACK PROPAGATED COMPLETELY THROUGH THE BOTTOM CENTER OF THE STRUT LEG BETWEEN THE LOWER ATTACH POINTS. THE STRUT LEG WAS REMOVED AND REPLACED. PICTURES ON FILE AT REPAIR STATION. (TC NR 2007052400May 24, 2007 · Dhav DHC3 · Wheel/Ski/FloatSDR CA070426009Rib · cracked(CAN) THIS ELEVATOR LEADING EDGE RIB WAS FOUND CRACKED WHILE CARRYING OUT ANNUAL INSPECTION. IT WAS DETERMINED THAT THE CRACK WAS THE RESULT OF TOO SHARP OF A BEND RADIUS IN THE AREA WHERE THE PART GETS RIVETED TO THE ELEVATOR LEADING EDGE SKIN. THIS DEFECTApr 20, 2007 · Dhav DHC2MKI · Elevator, Spar/RibSDR CA070514035Line · fractured(CAN) A FUEL LEAK WAS DISCOVERED DURING GROUND HANDLING OPERATIONS. SUBSEQUENT INSPECTION REVEALED A FRACTURED FUEL TUBE. (TC NR 20070514035)Mar 26, 2007 · Emb EMB110* · Engine Fuel DistributionSDR CA070514058Compressor · damaged(CAN) DURING CRUISE THE ENGINE EMITTED A LOUD NOISE ACCOMPANIED BY A REDUCTION IN ALL PARAMERTERS TO ZERO. SUBSEQUENT INSPECTION REVEALED COMPRESSOR AND POWER TURBINE DAMAGE. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20Feb 27, 2007 · Emb EMB110* · Turbine Engine Compressor SectionSDR CA070110001Engine · failed(CAN) (IFSD WITH MAJOR INTERNAL DAMAGE). THE ENGINE SUFFERED SEVERE DISTRESS WITH COMPLETE LOSS OF ALL TURBINE BLADES AND ASSOCIATED STATIC COMPONENTS. THE GG CASE AND EXHAUST DUCT WERE SUBJECTED TO SEVERE TORQUE LOADS AND WERE FOUND DISTORTED. ENGINE WAS CONJan 10, 2007 · Engine (Turbine/Turboprop)SDR CA061212001Engine · failed(CAN) SHORTLY AFTER COMPLETING THE DESCENT CHECKS FOR A LANDING (WITH ENGINES OPERATING NORMALLY, ENGINE INSTRUMENTS IN THE GREEN, THE CREW HEARD A LOUD NOISE FOLLOWED BY A SUDDEN LOSS OF POWER ON THE RT ENGINE. IMMEDIATELY FOLLOWING THE SUDDEN LOSS OF POWER TDec 10, 2006 · Emb EMB110P1 · Engine (Turbine/Turboprop)SDR CA061212005Pump · failed(CAN) (5) MINUTES AFTER AN ENGINE FAILURE OF THE RT ENGINE (SDR 20061212001) THE HYDRAULIC LIGHT CAME ON EVEN THOUGH THE LT ENGINE WAS OPERATING NORMALLY. THE CREW ATTEMPTED TO EXTEND THE LANDING GEAR NORMALLY BUT IT WOULD NOT LOCK. THE GEAR WAS THEN SUCCESSFUDec 10, 2006 · Emb EMB110P1 · Hydraulic Pump (Electric/Engine), MainSDR CA070103009Turbine Blades · fractured(CAN) DURING CRUISE ENGINE POWER REDUCED UNCOMMANDED, ACCOMPANIED BY A LOUD NOISE AND FLAMES EXITING THE EXHAUST. SUBSEQUENT INSPECTION REVEALED FRACTURED POWER TURBINE BLADES AND A SEIZED REDUCTION GEARBOX. MFG WILL MONITOR INVESTIGATION OF THE EVENT AND ADDec 10, 2006 · Emb EMB110P1 · Turbine SectionSDR CA061124001Compressor · damaged(CAN) ENGINE TEARDOWN RELATED TO AN IFSD AND A POSSIBLE COMPRESSOR FAILURE. TEARDOWN NOT YET CONCLUSIVE. IT WAS NOT A COMPRESSOR FAILURE BUT APPEARS TO BE FAILURE OF ONE OR MORE CT BLADES AND THEN CAUSED A STRUCTURAL FAILURE OF THE GAS GENERATOR CASE, WHICH TNov 23, 2006 · Turbine Engine Compressor SectionSDR CA061219015Engine · damaged(CAN) ON TAKEOFF, ENGINE OIL PRESSURE WAS SEEN TO FLUCTUATE. THE FIGHT CONTINUED AND ON DESCENT ENGINE OIL PRESSURE FELL TO ZERO RESULTING IN A PROPELLER AUTOFEATHER. THE ENGINE WAS SHUTDOWN IN FLIGHT. GROUND INSPECTION REVEALED INTERNAL ENGINE DAMAGE. MFGNov 1, 2006 · Emb EMB110* · Engine (Turbine/Turboprop)SDR CA061004008Duct · damaged(CAN) DURING A REGULARLY SCHEDULED HOT SECTION INSPECTION A CRACK WAS NOTICED IN THE LARGE EXIT DUCT (LED) BEING REMOVED FROM THE ENGINE. THE CRACK WAS LOCATED ON THE DOME AT THE DOUBLE WALL SEAM. THE LED HAD BEEN RECENTLY OVERHAULED AND HAD A TSO OF 1676.9.Sep 30, 2006 · Dhav DHC3 · Turbine Engine Combustion SectionSDR CA060929005Duct · damaged(CAN) WHILE PERFORMING A BOROSCOPE INSPECTION DURING A REGULARLY SCHEDULED FUEL NOZZLE CHANGE, DAMAGE WAS FOUND ON THE LARGE EXIT DUCT. THE (LED) WAS CHANGED AND UPON CLOSER INSPECTION IT WAS FOUND THAT A LARGE HOLE HAD BEEN BURNED THROUGH ONE LAYER OF THE DUSep 28, 2006 · Fuel Injector NozzleSDR 2007F00024Lift Strut · crackedFOUND RT WING STRUT CRACKED AT LOWER END DURING AICRAFT INSPECTION PROGRAM. 20 DAYS AND 16 HOURS LATER FOUND LT WING STRUT CRACKED AT LOWER END. AIRCRAFT HAS AOG 400 LB UP-GROSS STC SA00438NY INSTALLED.Sep 18, 2006 · N435B · Dhav DHC3 · Fuselage, Wing Attach FittingsSDR CA070103010Engine · flamed out(CAN) THE ENGINE FLAMED OUT IN FLIGHT ACCOMPANIED BY A LOUD NOISE. MFG WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070103010)Sep 11, 2006 · Emb EMB110* · Engine (Turbine/Turboprop)SDR CA060810006Support · cracked(CAN) WHILE DOING AN INSPECTION OF THE LTO ELEVATOR AND ITS ASSOCIATED PARTS A CRACK WAS FOUND IN THE ELEVATOR BALANCE WEIGHT SUPPORT. THE CRACK MEASURED 2.3750 OF AN INCH IN LENGTH AND STARTED APPROXIMATELY 2 INCHES BELOW THE LOWER THROUGH-TUBE FOR THE BALAJul 26, 2006 · Emb EMB110P1 · Elevator, Tab StructureSDR CA060720002Channel · cracked(CAN) WHILE CARRYING OUT MAINTENANCE IN THE RT LANDING GEAR AREA, A CRACK WAS FOUND IN THE IB LOWER NACELLE CHANNEL. THIS NACELLE CHANNEL IS THE ATTACH POINT FOR THE INBOARD GEAR DOOR HINGE. THE CRACK WAS LOCATED IN AFT PORTION OF THE HINGE ATTACH AREA MEASURJul 20, 2006 · Emb EMB110P1 · Nacelle/Pylon, Frame/Spar/RibSDR CA060720001Attach Bracket · cracked(CAN) DURING ROUTINE MAINTENANCE 2 CRACKS WERE DISCOVERED ON THE RT OB ELEVATOR HINGE ATTACH BRACKET. THE CRACKS WERE LOCATED ON THE LOWER FORWARD PORTION OF THE BRACKET IN THE MOST FORWARD PORTION OF A 90 DEGREE BEND AND WERE APPROX .7500 OF AN INCH IN LENGTHJun 21, 2006 · Emb EMB110P1 · Elevator Miscellaneous StructureSDR CA060704007Compressor · damaged(CAN) IN CRUISE, THE ENGINE WAS REPORTED TO EMIT A NOISE FOLLOWED BY A LOSS IN POWER. THE ENGINE WAS SHUT DOWN IN FLIGHT AND THE AIRCRAFT DIVERTED. POST FLIGHT INSPECTION REVEALED COMPRESSOR DAMAGE. P&WC WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE OJun 11, 2006 · Beech C90 · Turbine Engine Compressor SectionSDR CA060607004Blower · burned out(CAN) SHORTLY AFTER START UP, THE GROUND VENTILATION FAN WAS TURNED ON AND SMOKE STARTED TO ENTER THE AIRCRAFT CABIN. MAINTENANCE FOUND THE GROUND VENT BLOWER TO BE AT FAULT. THE GROUND VENT BLOWER WAS REMOVED AND DEFERRED. THE AIRCRAFT WAS THEN RETURNED TO SEJun 6, 2006 · Emb EMB110P1 · Cabin Cooling SystemSDR CA060607002Metering Tube · failed(CAN) FRACTURED AT LOWER THREAD WHERE THE TUBE SCREWS INTO THE PISTON. THIS ALLOWED THE UPPER AND LOWER SECTIONS OF THE SHOCK STRUT TO DISENGAGE CAUSING GEAR COLLAPSE. THE FAILED TUBE IS MADE OF ALUMINUM ALLOY. PART AND PICTURES AVAILABLE UPON REQUEST (TC NR 2Jun 5, 2006 · Dhav DHC6300 · Main Landing Gear Strut/Axle/TruckSDR CA060411001Propeller · malfunctionedON THE TAKEOFF ROLL, THE RT PROPELLER RPM WOULD ONLY GO TO 83% AND NOT BEYOND. THE AIRCRAFT RETURNED TO THE HANGAR WHERE MAINTENANCE FOUND THE RT PROPELLER TO BE AT FAULT. THE PROPELLER WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE. THE PROPELLER HAApr 4, 2006 · Emb EMB110P1 · Propeller GovernorSDR CA060328002Channel · cracked(CAN) DURING COMPLETION OF A 6C INSP, MAINT FOUND A CRACK IN THE FWD LT HORIZONTAL STABILIZER MACHINED CHANNEL. THIS PARTICULAR INSP WAS COMPLETED DUE TO AD 83-03-03R6 REQUESTING AN INITIAL INSP AND MODIFICATION OF ATTACHMENT AREA. INITIAL REQUIREMENTS WERE PRMar 26, 2006 · Emb EMB110P1 · Horizontal Stabilizer Miscellaneous StructureSDR CA060214005Blower · burned(CAN) DURING CRUISE FLIGHT, WITH NO PASSENGERS ON BOARD, THE CREW NOTICED AN ELECTRICAL BURNING SMELL IN THE AIRCRAFT AND SMOKE IN THE CABIN. THE AIRCRAFT WAS DIVERTED TO THE NEAREST SUITABLE AIRPORT AND LANDED. UPON INVESTIGATION MAINTENANCE PERSONNEL DISCOVEFeb 13, 2006 · Emb EMB110P1 · Air Distribution FanSDR HE17107982Cable · bindingCOLLECTIVE BINDING IN FLT FOUND ANTICIPATOR CONTROL CABLE BINDING. REMOVED AND REPLACED CABLE. (K)Feb 3, 2006 · N524MW · Urocop EC120B · Main Rotor ControlSDR CA060129018Turbine Blades · fracturedDURING CRUISE, ENGINE EXPERIENCED AN UNCOMMANDED POWER REDUCTION ACCOMPANIED BY NOISE. ENGINE WAS SHUT DOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED FRACTURED COMPRESSOR TURBINE BLADES.Dec 28, 2005 · Emb EMB110* · Turbine SectionSDR CA051223015Rod End · stiffON POWER REDUCTION FOR DESCENT, THE ENGINE DID NOT RESPOND TO THROTTLE LEVER INPUT. THE ENGINE WAS SHUTDOWN ON FINAL APPROACH AND A DEAD-STICK LANDING ACCOMPLISHED. SUBSEQUENT INSPECTION REVEALED THE FUEL CONTROL INTER-CONNECT ROD END TO BE STIFF AND LIMITEDDec 20, 2005 · Piper PA28140 · Power LeverSDR AU510001504Door · missingRT MAIN LANDING GEAR INBOARD DOOR MISSING. HINGES AND DOOR OPERATING RODS BROKEN.Dec 12, 2005 · Emb EMB110P1 · Landing Gear DoorsSDR AU510001837Steering Sys · unserviceableNOSE WHEEL STEERING SYSTEM FAULTY. STEERING SYSTEM TRAVEL WAS RESTRICTED. LT MAIN LANDING GEAR AND NOSE GEAR RAN OFF RUNWAY AND BECAME BOGGED IN THE SOFT SURFACE AT THE SIDE OF THE RUNWAY.Nov 9, 2005 · Emb EMB110P2 · Landing Gear Steering SystemSDR CA051129010Engine · failedON CLIMB, THE ENGINE WAS REPORTED TO HAVE EMITTED A NOISE ACCOMPANIED BY A LOSS OF POWER. THE AIRCRAFT DIVERTED TO DEPARTURE AND SUBSEQUENTLY CRASHED. MFG WILL INVESTIGATE THE INCIDENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED.Nov 8, 2005 · Emb EMB110* · Engine (Turbine/Turboprop)SDR CA051129016Drive Shaft · fracturedDURING CRUISE, THE ENGINE EXPERIENCED AN UNCOMMANDED POWER REDUCTION AND WAS SHUT DOWN IN FLIGHT. SUBSEQUENT INSPECTION REVEALED A FRACTURED FUEL PUMP DRIVE SHAFT.Nov 5, 2005 · Emb EMB110P1 · Engine Fuel PumpSDR CA051104013Engine · power loss(CAN) THE ENGINE EXPERIENCED AN UNCOMMANDED POWER ROLL-BACK ON TAKE-OFF. THE ENGINE WAS SHUTDOWN IN FLIGHT AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE. SUBSEQUENT INSPECTION REVEALED DAMAGE TO THE COMPRESSOR AND ENGINE INLET AREA. MFG WILL INVESTIGATE TOct 25, 2005 · Emb EMB110* · Engine (Turbine/Turboprop)SDR CA051017005Servo · crackedRIGHT ELEVATOR SERVO TAB FOUND CRACKED DURING ROUTINE INSPECTION.Oct 14, 2005 · Dhav DHC3 · Elevator Tab Control SystemSDR CA051013005Bracket · crackedUPON VISUAL INSPECTION, TOP PLATE OF AFT REVERSING TELEFLEX BRACKET WAS FOUND CRACKED 70 PERCENT THROUGH. TOTAL FAILURE OF THIS BRACKET WOULD ALLOW THE REVERSING TELEFLEX TO MOVE FORE AND AFT CAUSING DIFFICULTIES IN ENGINE CONTROL DURING REVERSE OPERATIONS. Oct 12, 2005 · Dhav DHC6300 · Engine Thrust ReverserSDR CA051026008Beta Ring · failed(CAN) IT WAS FOUND THAT THE CIRCLIP SECURING THE BETA BUSHING HAD PULLED AWAY FROM ITS SLOT. THIS WAS DUE TO IMPROPER ADJUSTMENT OF THE BETA RODS. IT IS RECOMMENDED TO FOLLOW THE INSTRUCTIONS FROM MFG PROPELLER MM P/N 118F PG.7-58 FIG. 7-27, REV.11 OCT 01.Oct 11, 2005 · Dhav DHC2* · Propeller Controlling SystemSDR CA051011006Drive Assy · shearedIN CRUISE FLT AT 7000 FEET, NR 1 ENGINE LOST POWER. FLT CREW SECURED NR 1 ENGINE IAW APPLICABLE FLT MANUAL PROCEDURES AND LANDED A/C AT NEAREST AIRPORT. UPON INVESTIGATION, MX FOUND THAT CAUSE OF ENG FAILURE WAS DUE TO ENG DRIVEN FUEL PUMP. WHEN FUEL PUMP WOct 5, 2005 · Emb EMB110P1 · Engine Fuel PumpSDR CA051104001Spline · damaged(CAN) DURING CRUISE THE ENGINE WAS REPORTED TO HAVE LOST POWER AND THE CREW SHUTDOWN THE ENGINE IN FLIGHT. SUBSEQUENT INSPECTION REVEALED A DAMAGED FUEL PUMP DRIVE SPLINE.Oct 5, 2005 · Emb EMB110P1 · Engine Fuel PumpSDR CA060216008Mount · crackedTOP, ENGINE VIBRATION ISOLATOR MOUNT (RIGHT ENGINE) WAS FOUND CRACKED DURING INSPECTION.Oct 5, 2005 · Dhav DHC6300 · Engine Mount Section
Back to U/A Canada PT6A-34