U/A Canada PT6A-135

Service difficulty reports · 128

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 = 'PT6A135'
  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 CA000530075Bolt · broken(CAN) DURING TAKEOFF RUN, A SOUND WAS HEARD OUTSIDE THE AIRCRAFT. THE PASSENGER IN RIGHT SEAT NOTED RIGHT SKI WAS TIPPED FORWARD AMD HANGING BY CHECK CABLE. LANDING WAS CARRIED OUT AND RESULTED IN SKI DIGGING IN FRONT AND CUTTING THE REAR GEAR ATTACHMENT STRMay 11, 2000 · Dhav DHC3 · Wheel/Ski/FloatSDR CA000301022Inverter · failed(CAN) A PORTABLE INVERTER WAS USING THE AIRCRAFT''S 28 VOLT SUPPLY TO POWER A LIFEPACK DEFLIBRILLATOR/MONITOR 120 V AT 3.5 AMPS. DURING CLIMB, THE PARAMEDIC ADVISED THE FLIGHT CREW OF SMOKE IN THE CABIN. THE PARAMEDIC DETERMINED THAT THE CAUSE OF SMOKE WAS TJan 22, 2000 · Piper PA31T2 · AC InverterSDR CA991230027Wheel · cracked(CAN) DURING TIRE & TUBE REPLACEMENT, THE WHEEL ASSEMBLY WAS INSPECTED AND ONE WHEEL HALF WAS FOUND CRACKED.Dec 8, 1999 · Piper PA31T2 · Wheel/Ski/FloatSDR CA991230002Valve · contaminated(CAN) ON THE TAKE-OFF ROLL THE LT ENGINES PROP WOULDN''T EXCEED 1300 RPM. THE PROBLEM WAS FOUND TO BE A DIRTY HYDRAULIC TOPPING GOVERNOR VALVE. THE UNIT WAS CLEANED AND RETURNED TO SERVICE.Dec 2, 1999 · Piper PA31T2 · Propeller GovernorSDR CA991209071Rod · worn(CAN) DURING INSPECTION, IT WAS FOUND THAT THE PUSH PULL ROD FOR THE ELEVATOR TRIM TAB WAS SEVERELY WORN. THE WEAR SPOT OCCURRED WHERE THE PUSH PULL ROD RUNS THROUGH THE BULKHEAD AND CONTACTS THE ROLLERS WHICH IT RIDES ON. THE ROD WAS REMOVED AND INSPECTED-THNov 18, 1999 · Dhav DHC3 · Elevator Tab Control SystemSDR CA991103044Rod · worn(CAN) DURING INSPECTION, THE PUSH/PULL ROD FOR THE ELEVATOR TRIM TAB WAS SEVERELY WORN. THE WEAR SPOT OCCURRED WHERE THE ROD RUNS THROUGH THE BULKHEAD AND CONTACTS THE TWO ROLLERS WHICH IT RIDES ON. RODS REPLACED. ROLLERS HAD WORN THROUGH THE ROD.Oct 27, 1999 · Dhav DHC3 · Elevator Tab Control SystemSDR CA991103050Door Frame · broken(CAN) DOOR FRAME (BULKHEAD) BROKE AT SNUBBER UPPER ATTACHMENT POINT.Oct 13, 1999 · Piper PA31T2 · Fuselage Main, StructureSDR CA991007080Bearing · worn(CAN) DURING INSPECTION, RUDDER PEDALS FOUND TO HAVE PLAY UP AND DOWN. LEFT SUPPORT BRACKET, BEARING AND BOLT WERE FOUND TO HAVE SIGNIFICANT AMOUNT OF WEAR. ALL PARTS REPLACED.Sep 24, 1999 · Dhav DHC3 · Rudder Control SystemSDR CA991007081Detent · worn(CAN) FLAP SELECTOR DETENT HOLES FOUND WORN WHERE THERE IS NO POSITIVE DETENT FOR HANDLE POSITION. NEW SELECTOR INSTALLED.Sep 24, 1999 · Dhav DHC3 · Trailing Edge Flap Control SystemSDR CA991007082Servo Tab · cracked(CAN) DURING INSPECTION, ELEVATOR SERVO TAB WAS FOUND CRACKED. TAB REPLACED.Sep 24, 1999 · Dhav DHC3 · Elevator, Tab StructureSDR CA990219012O-Ring · failed(CAN) LEFT INBOARD GEAR DOOR ACTUATOR BOTTOM GT RING. THE O-RING AND BACK-UP FAILED. THIS CAUSED THE ALL HYDRAULIC FLUID LOSS. EMERGENCY GEAR EXTENSION USED. CAUSE OF O-RING FAILURE WAS A PAINT CHIP ON INSIDE OF THE O-RING AND BACK-UP RING.Feb 7, 1999 · Piper PA31T2 · Landing Gear Door ActuatorSDR CA990311064Fitting · cracked(CAN) CRACKS FOUND IN LANDING GEAR FITTING ON INNER SURFACE EDGE OF FITTING. PARTS REPLACED.Jan 12, 1999 · Dhav DHC3 · Main Landing Gear Attach SectionSDR CA980922011Tube · worn(CAN) AIRCRAFT ELEVATOR PULL-UP CABLE DAMPENER TUBE WAS FOUND DAMAGED IN THE MID-SECTION. SPRING RETAINING WASHER RUBBED THROUGH THE TUBE, HALF ITS CIRCUMFERENCE.Sep 10, 1998 · Piper PA31T2 · Elevator Control SystemSDR 98ZZZX3331Blade · failedENGINE RECEIVED FOR SUSPECTED COMPRESSOR TURBINE BLADE FAILURE. UPON INSPECTION, ONE OR MORE CT BLADES WERE FOUND TO HAVE FAILED. ENGINE TOTAL TIME 4,827.5 HOURS. TIME SINCE OVERHAUL 689 HOURS.Aug 26, 1998 · N444MF · Beech F90 · Turbine Engine Compressor SectionSDR CA980506003Spar · cracked(CAN) LEFT ELEVATOR SPAR CRACKED IN 2 PLACES AT OUTBOARD HINGE ATTACH POINT UNDER HINGE. REPAIRED.Apr 30, 1998 · Piper PA31T2 · Elevator, Spar/RibSDR CA980602076Skin · cracked(CAN) TWO CRACKS NOTED ON THE HORIZONTAL STABILIZER LOWER SKIN AT THE OUTBOARD HINGE. THE HINGE BRACKET WAS FOUND LOOSE. TWO RIVETS THAT SECURE THE HINGE TO THE REAR SPAR WERE LOOSE AND HOLES IN THE SPAR ELONGATED. THE HORIZONTAL STABILIZER END RIB WAS ALSO CApr 13, 1998 · Dhav DHC3 · Horizontal Stabilizer, Plate/SkinSDR CA970807045Regulator · malfunctioned(CAN) CREW REPORTED ELECTRICAL BUS SEPARATION FOLLOWED BY AVIONICS CIRCUIT BREAKERS TRIPPING. LEFT GENERATOR DEEMED TO BE THE CAUSE AND WAS ISOLATED. MAINTENANCE FOUND THAT THE LEFT HAND GENERATOR CONTROL UNIT FAILED.Mar 12, 1998 · Beech F90 · DC RegulatorSDR 97ZZZX4850Pump · failedLEFT ENGINE HIGH PRESSURE FUEL PUMP FAILED. DISASSEMBLY REVEALED DRIVE COUPLER SPLINES WORN OUT ON PUMP. OIL MISTING HOLE PLUGGED, SPLINES RUNNING DRY. THIS CONDITION CAN BE REVEALED BY PUSHING A PIPE CLEANER INTO PUMP DRAIN CAVITY. RUST DEPOSITS INDICATE Nov 3, 1997 · N701NC · Beech F90 · Engine Fuel PumpSDR CA971125005Servo Tab · broken(CAN) IN CRUISE WHEN PILOT NOTED VIBRATION WITH CONTROL STICK. VIBRATION BECAME MORE VIOLENT AND HE SLOWED AIRCRAFT. VIBRATION DID NOT GO AWAY, BUT WAS LESS VIOLENT. AIRCRAFT LANDED OK. IT APPEARS THAT THE ARM THAT CONNECTS TO CONTROL ROD BECAME DETACHED FROM Oct 13, 1997 · Dhav DHC3 · Elevator Tab Control SystemSDR CA970731021Itt Harness · separated(CAN) DURING NORMAL OPERATIONS THE CREW NOTICED THE NR2 ENGINE ITT DROPPED TO ZERO. THE ITT HARNESS WAS REPLACED AND THE ENGINE TESTED SERVICEABLE. INSPECTION OF THE HARNESS FOUND THE CHROMEL CONNECTION ON THE CRIMPED END WAS SEPARATED AND THE GLASS CERAMIC MJul 22, 1997 · Beech F90 · Engine EGT/TIT Indicating SystemSDR CA970610011Ct Blades · fractured(CAN) DURING DESCENT THERE WAS A LOUD BANG. THE PILOT SECURED THE ENGINE. POST FLIGHT INSPECTION AT THE "C" FLANGE REVEALED SEVERAL CT BLADES FRACTURED. THE ENGINE IS BEING RETURNED TO THE MANUFACTURER.May 27, 1997 · Turbine SectionSDR CA970624029Turbine Blade · broken(CAN) INFLIGHT ENGINE FAILURE, EMERGENCY LANDING ON SMALL LAKE. POST FLIGHT INSPECTION FOUND COMPRESSOR TURBINE WHEEL BLADE FRACTURED, DAMAGING ADJACENT BLADES. THE FAILED BLADE WAS VERIFIED AND IT SHOWED TO HAVE AN OIL CRACK OF ABOUT 3/16", PROGRESSING FROM TMay 27, 1997 · Dhav DHC3 · Turbine SectionSDR CA970421072Servo Tab · broken(CAN) ABOUT 10 MINUTES AFTER TAKEOFF THE PILOT NOTICED BUFFETING OF THE ELEVATORS. THIS WAS FOLLOWED BY SEVERE NOSE DOWN AND NOSE UP FORCE COMING FROM THE ELEVATOR CONTROL. POWER REDUCED AND CONTROLS RETURNED TO NORMAL. AIRCRAFT LANDED OK. RIGHT ELEVATOR SERVOMar 9, 1997 · Dhav DHC3 · Elevator Tab Control SystemSDR CA970115001Drag Leg · cracked(CAN) AIRCRAFT LANDED ON ICY RUNWAY WITH FROZEN BRAKES AND CAME TO A JARRING STOP WHEN CLEAR RUNWAY WAS ENCOUNTERED. INSPECTION FOUND THE RADII OF THE LEFT HAND DRAG LEG CRACKED.Dec 30, 1996 · Beech F90 · Main Landing Gear Attach SectionSDR CA960711201Flange · broken legs(CAN) THE STARTER/GENERATOR QUICK ATTACH-DETACH FLANGE WAS FOUND TO HAVE BROKEN LEGS DURING AN INSPECTION. THE PILOT NOTED A DIFFERENT NOISE WHILE STARTING THE AIRCRAFT.Jun 18, 1996 · Piper PA31T2 · Starter-GeneratorSDR CA960708003Servo Tab · ripped(CAN) SLIGHT FLUTTER ON FINAL STAGE OF CLIMB. SEVERE FLUTTER AFTER LEVEL OUT IN CRUISE. INVESTIGATION FOUND THE RIGHT HAND ELEVATOR SERVO TAB CONNECTING ROD ARM BORKEN OFF THE SERVO TAB. TAB WAS BENT AND BROKEN BUT STILL ATTACHED. TRAILING EDGE OF ELEVATOR SKIJun 12, 1996 · Dhav DHC3 · Elevator, Tab StructureSDR CA960425102Bracket · bent(CAN)AIRCRAFT PARKED ON DOCK WITH FLIGHT CONTROL LOCKS ON. ELEVATORS NOTED IN HIGH POSITION. INSPECTION FOUND ELEVATORS MOVEMENT WAS RESTRICTED. ELEVATOR PUSH-ROD WAS HITTING STAB TRIM JACK. UPON FURTHER I NSPECTION IT WAS FOUND THAT THE ELEVATOR TORQUE TUBE PApr 6, 1996 · Dhav DHC3 · Elevator Control SystemSDR CA960515005Static Sensor · leaking(CAN) PIEZO STATIC SENSOR HOUSING LEAKING IN EXCESS OF LIMITSMar 26, 1996 · Piper PA31T2 · Pitot/Static System
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