Garrett TPE331-10UA
Service difficulty reports · 375
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 = 'TPE33110UA' 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 = 'TPE33110UA' 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 CA971219031Bearings · damaged(CAN) IN CRUISE, THE LEFT GENERATOR STOPPED CHARGING. BEARINGS WERE FOUND BADLY DAMAGED.SDR CA971128004Collar · loose(CAN) ON INSP A NO OF FAILED COMPONENTS WERE FOUND IN BOTH WHEEL WELL AREAS.COLLAR P/N27-35012-001 WAS FOUND LOOSE & MOVED WITH FORE & AFT PRESSURE ON LOWER GEAR LEG.P/N27-35011-007(DOUBLER).DUE TO MOVEMENT OF- ABOVE FITTING,FASTENERS THAT ATTACH FITTING TO BASDR CA971028003Blade · failed(CAN) ENGINE MADE A THUMP ON TAKEOFF AND LOST TORQUE. TOWER COMMUNICATED THAT SMOKE WAS COMING FROM RT ENGINE. TAKEOFF ABORTED. ONE BLADE MISSING FROM NR 1 TURBINE WHEEL AND SEVERAL BLADES DAMAGED. BLADES DAMAGED ON NR 2 AND NR 3 WHEELS, VARIOUS PARTS DAMAGESDR CA971024002Bearing · failed(CAN) GROUND PERSONNEL NOTICED THAT THE RIGHT NOSE WHEEL WAS NOT TURNING. NOSE WHEEL WAS SEVERELY FLAT SPOTTED. INNER BEARING WAS FOUND SEIZED ONTO THE AXLE. WHEEL HAD BEEN INSTALLED JUNE 97 AND LUBRICATED AS PART OF PHASE INSPECTION IN SEPTEMBER 97. SUBMITTERSDR CA971024003Door · damaged(CAN) ON ARRIVAL BACK AT BASE, CREW NOTIFIED THAT THE NOSE GEAR DID NOT COMPLETELY RETRACT, WITH A NOSE GEAR IN TRANSIT WARNING ON. GEAR CIRCUIT BREAKER PULLED AND RESET. GEAR THEN LOCKED UP. INVESTIGATION FOUND THAT THE LEFT NOSE DOOR WAS DAMAGED AT ABOUT 12 SDR 97ZZZX4563Engine · bird strikeMAINTENANCE REPORTED EVIDENCE OF A BIRD STRIKE ON LEFT PROPELLER AT SAT. MAINTENANCE PERFORMED A BIRD STIRKE INSPECTION OF THE LEFT ENGINE AND PROPELLER. THERE WAS NO EVIDENCE OF ANY BIRD MATTER INGESTION.SDR CA971020007Combustion Liner · cracked(CAN) DURING ROUTINE BORESCOPE INSPECTION, CONCURRENT WITH FUEL NOZZLE CHANGE, A CRACK WAS DISCOVERED IN THE COMBUSTION LINER. THE ENGINE WAS REMOVED FROM THE AIRCRAFT AND THE COMBUSTION LINER WAS REPLACED.SDR CA971020008Nozzle · failed(CAN) FIRST STAGE STATOR BURN THROUGH DUE NOZZLE FAILURE. PART TC: 3,501.SDR CA971014002Line · cracked(CAN) FLIGHT CREW REPORTED A TOTAL HYDRAULIC FAILURE. MAINTENANCE CREW FOUND A LOOSE HYDRAULIC FITTING AND CRACKED LINE. PART NUMBER OF LINE NOT IDENTIFIED IN IPC. IT IS THE LINE THAT TERMINATES IN A 'T' BEFORE TWO FLEX LINES FOR THE DOWN ACTUATION OF THE MLG SDR CA971014003Pinion Assembly · primary failure(CAN) AIRCRAFT WAS IN-FLIGHT WHEN THE L/H CHIP LIGHT ILLUMINATED, OIL PRESSURE DROPPED 50 PSI, TORQUE FLUCTUATED, FEATHERED ENGINE. TEARDOWN REVEALED THAT ROTATING GROUP COULD NOT BE TURNED. FORWARD BEARINGIN THE HIGH SPEED PINION BEARING ASSEMBLY HAD FAILED. SDR 97ZZZX4560Engine · bird strikeDURING POST-FLIGHT INSPECTION AT PHX, THE PILOT NOTED AND REPORTED EVIDENCE OF A BIRD STRIKE ON THE LEFT ENGINE AND LEFT PROPELLER. MAINTENANCE VISUALLY INSPECTED THE LEFT ENGINE AND PROPELLER AND NO DISCREPANCIES WERE NOTED. AN ENGINE RUN WAS ACCOMPLISHED SDR CA970815006Speed Switch · failed(CAN) DURING AN INTENTIONAL ENGINE SHUTDOWN ON A TRAINING FLIGHT, THE LEFT ENGINE CAME UP TO SPEED BUT THE IGNITION AND FUEL FLOW WERE NOT EVIDENT. THE NR1 START CONTROL CIRCUIT BREAKER WAS FOUND POPPED. THE CB WAS RESET, BUT NO START AND CB POPPED AGAIN. ENGISDR CA970820006Power Cable · defective(CAN) ON APPLYING TAKEOFF POWER THE RIGHT HAND ENGINE DID NOT PRODUCE FULL POWER. TAKEOFF ABORTED. INVESTIGATION FOUND THAT THE PAL NUTS THAT HOLD THE POWER CABLE AGAINST THE ROD END HAD BACKED OFF. NUTS AND PAL NUTS ADJUSTED AND TORQUED.SDR CA970620009Duct · cracked(CAN) ON APPROACH THE LEFT WING OVERHEAT WARNING LIGHT CAME ON. LEFT BLEED AIR TURNED OFF AND AFTER TWO MINUTES THE LIGHT WENT OUT. AFTER SHUT DOWN WING LEADING EDGE NOTED AS QUITE HOT. INVESTIGATION FOUND THAT THE BLEED AIR DUCT WAS CRACKED CIRCUMFERENTIALLY SDR 97ZZZX2631Gasket · failedSCAVENGE PUMP GASKET WENT BAD CAUSING SLOW LOSS OF ENGINE OIL. ALSO, THIS CAUSED VIBRATION TO BREAK OIL JET AT PUMP ASSY. NEW STYLE GASKET NOW INSTALLED.SDR CA970501002Line · cracked(CAN) HYDRAULIC FLUID FOUND DRIPPING FROM THE LEFT WING, AND LEFT CENTRE SECTION AFTER AIRCRAFT RETURNED FROM FLIGHT. MAINTENANCE FOUND THAT THE HYDRAULIC LINE HAD A CRACK AT THE POINT WHERE IT PASSED THROUGH A LINE CLAMP BLOCK. LINE REPLACED WITH A STAINLESS SDR CA970422026Wire · shorted(CAN) CREW INTENTIONALLY SHUT DOWN LEFT ENGINE. ON ATTEMPTED START THE ENGINE WOULD UNFEATHER AND RPM WOULD INCREASE TO 15 PERCENT BUT FUEL FLOW AND IGNITION WERE NOT EVIDENT. LEFT SPEED SWITCH 10 PERCENT FUNCTION FOR IGNITION AND FUEL FLOW WAS SUSPECT. SWITCHSDR CA970318008Wheel Assembly · cracked(CAN) WHEEL ASSEMBLY, FOUND MISSING AT #2 POSITION, LEFT INBOARD DURING POST FLIGHT INSPECTION. WHEEL BEARING HAD FAILED AND ALLOWED WHEEL ASSEMBLY TO MOVE OVER NUT. NUT, WASHER AND SPLIT PIN WERE INSTALLED CORRECTLY AND FOUND ON AXLE INTACT.SDR CA970210009Turbine Wheel · loose(CAN) AFTER GROUND RUN, THE PROPELLERS WERE PULLED THROUGH BY HAND TO AID COOLING. AN UNUSUAL NOISE WAS HEARD ON NR 2 ENGINE. ENGINE TORN DOWN AND THE RIVETS IN THE 2ND TURBINE WHEEL WERE FOUND LOOSE ALLOWING THEM TO TOUCH THE 3RD STATOR. NO DAMAGE WAS SUSTASDR AU970074Cylinder · cracked(AUS) MAIN LANDING GEAR UPPER STRUT CYLINDER CRACKED - FOUND DURING INSPECTION IAW AD/SWSA226/78 (SB 226-32-033)SDR CA970115008Clevis Pin · fretting(CAN) IN REFERENCE TO SERVICE DIFFICULTY ADVISORY AV-96-06, INSPECTION CARRIED OUT ON THE CLEVIS PIN IN THE POWER LEVER SYSTEM. THE PINS IN THE LEFT AND RIGHT ENGINES WERE NOTICEABLY WORN, AND THE COTTER PIN HOLES ELONGATED. BOTH CLEVIS AND COTTER PINS WERE RESDR CA961220011Torque Tube · cracked(CAN) AS PART OF 8000 BLOCK INSPECTION THE ELEVATORS ARE REMOVED FOR INSPECTION. THE ELEVATOR TORQUE TUBES ARE NOT SPECIFICALLY IDENTIFIED AS REQUIRING SPECIAL ATTENTION. HOWEVER, INSPECTION FOUND THAT THE LEFT ELEVATOR TORQUE TUBE ASSEMBLY WAS CRACKED AT THE SDR CA961126005Switch · intermittent(CAN) REFERENCE SB 226-32-025, ACCOMPLISHED IN JULY 1995. AN UPGRADE TO A 'MORE RELIABLE SWITCH'. AFTER UPGRADE OPERATOR HAD PROBLEMS WITH ONGOING GEAR INDICATION PROBLEMS. EVERYTHING CHECKED. SWITCHES REMOVED AND TESTED. INTERNAL RESISTANCE FOUND TO VARY FROMSDR CA961112027Nut Tubes · failed(CAN) DURING PERIODIC INSPECTION, PITCH TRIM NOTED MAKING LOUD GRINDING NOISES. ACTUATOR REPLACED. TEAR DOWN INDICATED THAT THE NUT TUBES WERE REPLACED AT OVERHAUL. AD 93-15-02R2 REQUIRES THAT THE OPERATOR DETERMINE IF THE NUT TUBE ASSEMBLY WAS REPLACED AND IFSDR CA961104008Combustor · cracked(CAN) ON INSPECTION, AFTER ENGINE REMOVED TO FACILITATE REMOVAL OF NR 3 ROTOR, THE COMBUSTOR LOWER SKIRT WAS FOUND CRACKED CIRCUMFERENTIALLY APPROXIMATELY 22 INCHES OR 3/4 OF THE CIRCUMFERENCE. GARRETT TO INVESTIGATION WELD FAILURE.SDR CA961114008Combustor · cracked(CAN) COMBUSTOR LOWER SKIRT WAS FOUND CRACKED CIRCUMFERENTIALLY APPROXIMATELY 22 INCHES OR 3/4 OF THE CIRCUMFERENCE. GARRETT INVESTIGATING FAILURE. PART TC: 3,117.SDR CA961021010Yoke · cracked(CAN) ULTRASONIC INSPECTION OF LANDING GEAR YOKES AS PER AD 96-19-05. OF 41 YOKES INSPECTED 12 HAD CRACKS. ALL 12 HAD BEEN FOUND OK ONE YEAR PREVIOUS. ALL ARE FAIRLY HIGH TIME. SUBMITTER SUGGESTS THAT CRACKING NOT ENTIRELY RELATED TO FATIGUE AS SOME NEW YOKES SDR CA961022003Yoke · cracked(CAN) ULTRASONIC INSPECTION OF LANDING GEAR YOKES AS PER AD 96-19-05. OF 41 YOKES INSPECTED 12 HAD CRACKS. ALL 12 HAD BEEN FOUND OK ONE YEAR PREVIOUS. ALL ARE FAIRLY HIGH TIME. SUBMITTER SUGGESTS THAT CRACKING NOT ENTIRELY RELATED TO FATIGUE AS SOME NEW YOKES SDR CA961022004Yoke · cracked(CAN) ULTRASONIC INSPECTION OF LANDING GEAR YOKES AS PER AD 96-19-05. OF 41 YOKES INSPECTED 12 HAD CRACKS. ALL 12 HAD BEEN FOUND OK ONE YEAR PREVIOUS. ALL ARE FAIRLY HIGH TIME. SUBMITTER SUGGESTS THAT CRACKING NOT ENTIRELY RELATED TO FATIGUE AS THEY HAVE RECEISDR CA961022005Yoke · cracked(CAN) ULTRASONIC INSPECTION OF LANDING GEAR YOKES AS PER AD 96-19-05. OF 41 YOKES INSPECTED 12 HAD CRACKS. ALL 12 HAD BEEN FOUND OK ONE YEAR PREVIOUS. ALL ARE FAIRLY HIGH TIME. SUBMITTER SUGGESTS THAT CRACKING NOT ENTIRELY RELATED TO FATIGUE AS SOME NEW YOKES SDR CA961022007Yoke · cracked(CAN) ULTRASONIC INSPECTION OF LANDING GEAR YOKES AS PER AD 96-19-05. OF 41 YOKES INSPECTED 12 HAD CRACKS. ALL 12 HAD BEEN FOUND OK ONE YEAR PREVIOUS. ALL ARE FAIRLY HIGH TIME. SUBMITTER SUGGESTS THAT CRACKING NOT ENTIRELY RELATED TO FATIGUE AS SOME NEW YOKES SDR CA961022008Yoke · cracked(CAN) ULTRASONIC INSPECTION OF LANDING GEAR YOKES AS PER AD 96-19-05. OF 41 YOKES INSPECTED 12 HAD CRACKS. ALL 12 HAD BEEN FOUND OK ONE YEAR PREVIOUS. ALL ARE FAIRLY HIGH TIME. SUBMITTER SUGGESTS THAT CRACKING NOT ENTIRELY RELATED TO FATIGUE AS SOME NEW YOKES SDR CA961022009Yoke · cracked(CAN) ULTRASONIC INSPECTION OF LANDING GEAR YOKES AS PER AD 96-19-05. OF 41 YOKES INSPECTED 12 HAD CRACKS. ALL 12 HAD BEEN FOUND OK ONE YEAR PREVIOUS. ALL ARE FAIRLY HIGH TIME. SUGGESTS THAT CRACKING NOT ENTIRELY RELATED TO FATIGUE AS SOME NEW YOKES HAVE BEEN SDR CA961022010Yoke · cracked(CAN) ULTRASONIC INSPECITON OF LANDING GEAR YOKES AS PER AD 96-19-05. OF 41 YOKES INSPECTED 12 HAD CRACKS. ALL 12 HAD BEEN FOUND OK ONE YEAR PREVIOUS. ALL ARE FAIRLY HIGH TIME. SUBMITTER SUGGESTS THAT CRACKING NOT ENTIRELY RELATED TO FATIGUE AS SOME NEW YOKES SDR CA961007009Housing · damaged(CAN) PART HAD BEEN SENT OUT FOR REWORK AND MOD SB 331-72-0462. AFTER RETURN, IT WAS FOUND THAT THREE OF THE FLANGE HOLES WERE BADLY ELONGATED AND HAD DEEP SURFACE WEAR. THE POINT OF WEAR IS THE ATTACH POINT FOR THE FCU SUPPORT BRACKET P/N 868767-1 AND THE ISDR CA961003005Balance Weight · cracked(CAN) LEFT AILERON 2ND FROM INBOARD BALANCE WEIGHT FOUND BROKEN AT 2 ATTACH HOLES. 6 OTHER AIRCRAFT SIMILAR IN FLEET OF 12.SDR CA961003006Balance Weight · broken(CAN) RIGHT AILERON BALANCE WEIGHT FOUND BROKEN AT CENTRE ATTACH HOLE. 6 OTHERS OF 12 AIRCRAFT FOUND WITH SAME PROBLEM.SDR CA961003007Balance Weight · cracked(CAN) LEFT AILERON ALL 3 BALANCE WEIGHTS FOUND CRACKED AT CENTRE HOLE. 6 OTHERS OF 12 AIRCRAFT FOUND WITH SAME PROBLEM.SDR CA961003008Balance Weight · cracked(CAN) RIGHT AILERON INBOARD BALANCE WEIGHT FOUND CRACKED AT CENTRE AND OUTBOARD ATTACH HOLES. 6 OF 12 OTHER AIRCRAFT FOUND WITH SAME PROBLEM.SDR CA961003009Balance Weight · cracked(CAN) RIGHT AILERON INBOARD BALANCE WEIGHT FOUND CRACKED AT ATTACH HOLE. 6 OF 12 OTHER AIRCRAFT FOUND WITH SAME PROBLEM.SDR CA960923010Tie Bolt Nut · wrong part(CAN) ON MORNING WALK-AROUND, ENGINE WAS STIFF TO ROTATE. ENGINE REPLACED. ENGINE WAS DIS-ASSEMBLED BY FIELD REP AND FOUND THAT NR 2 TURBINE WHEEL TIE BOLT NUT WAS NOT THE ONE STATED IN THE LATEST SB (331-72-0592, 9/88). NUT P/N SHOULD HAVE BEEN 3108066-1 NSDR CA960919005Connector · faulty(CAN) CREW REPORTED THAT THE PITCH TRIM ACTUATOR WAS FAULTY AS THE CAPTAINS PITCH TRIM COULD BE ACTIVATED USING ONLY ONE SWITCH SWITCH IS A SPLIT SWITCH THAT NORMALLY REQUIRES BOTH SWITCHES TO BE ACTIVATED TO OPERATE PITCH TRIM. SUBSEQUENT INVESTIGATION FOUNDSDR BDHA9600022Fuel Control · malfunctionedMSP - FLT 434 - THE LEFT ENGINE WAS FUEL LIMITED ON TAKEOFF. THE MAX POWER WAS TURNED UP AND A RUN PERFORMED. THE ENGINE WAS VERY ERRATIC. INSPECTION OF THE FUEL CONTROL FOUND THE MANUAL FUEL VALVE WAS BINDING INSIDE. THE FUEL CONTROL WAS CHANGED AND ENGINSDR CA960916009Balance Weight · loose(CAN) DURING DAILY INSPECTION THE RIGHT HAND AILERON BALANCE WEIGHT WAS FOUND LOOSE, BENT AND HANGING BY THE OUTBOARD BOLTWEIGHT HAD BEEN LOOSE FOR SOME TIME TWO HOLES HAD BEEN SWAGED COMPLETELY THROUGH AND THE LAST HOLE WAS 1/2 WAY THROUGH. WEIGHT WAS BENT ASDR CA960723013Door · bent(CAN) CREW HAD TROUBLE GETTING RIGHT MLG TO EXTEND USING EITHER NORMAL OR EMERGENCY SYSTEM. AFTER RESETTING THEY GOT IT TO EXTEND WITH NORMAL SYSTEM. INVESTIGATION FOUND THAT THE RIGHT HAND OUTBOARD GEAR DOOR WOULD HANG UP ON THE NACELLE. THE GEAR DOOR WAS REWSDR CA960719001Line · cracked(CAN) CAPTAIN REPORTED A SMALL HYDRAULIC LEAK IN AREA OF HYDRAULIC FILTER IN NOSE WHEEL WELL. INSPECTION FOUND SHORT HIGH PRESSURE LINE ATTACHED TO NOSE STEERING FILTER CRACKED AND LEAKING. HYDRAULIC ACCUMULATOR WAS FLAT. A FLAT ACCUMULATOR CAN CAUSE A 'BUZZ' SDR CA960722006Panel · jams aileron(CAN) ON PREFLIGHT CREW FOUND AILERONS JAMMED. INVESTIGATION FOUND THAT THE RIGHT HAND BELLY PANEL (PANEL 612) THAT COVERS THE AILERON PUSH PULL RODS AND THE FLAP INTERCONNECT WAS BULGED INWARDS AND WAS FOULING THE AILERON SWING LINK. A HOLE HAD DEVELOPED IN TSDR CA960625005Indicator · stuck(CAN) ON APPROACH, CREW DID NOT GET RH GEAR DOWN AND LOCKED INDICATION. EMERGENCY EXTENSION USED OKAY. INVESTIGATION FOUND THAT THE RIGHT GEAR WAS FUNCTIONING NORMALLY BUT THAT THE RIGHT GEAR INDICATOR WAS STICKING AND NEEDED TO BE TAPPED. GAUGE REPLACED.SDR CA960910005Lock Pin · sheared(CAN) ACTUATOR HAD REFURBISHED NUTS AND SHAFTS INSTALLED AT PREVIOUS OVERHAUL INSPECTION AT 3000 HOURS FOUND RH SHAFT FREE END PLAY AT MID POINT OF TRAVEL WAS APPROXIMATELY 0 010, LEFT SHAFT FREE END PLAY NEGLIGIBLE, LEFT ROD END ASSEMBLY INNER SHAFT COULD BESDR CA960610007Pin · fallen out(CAN)ON DESCENT CREW UNABLE TO REDUCE POWER ON RH ENGINE BELOW 70 PERCENT. POWER LEVER JAMMED, BUT ABLE TO MOVE FREELY BETWEEN 70 AND 100 PERCENT. ENGINE SHUTDOWN, BUT PROP WOULD NOT FEATHER. AIRCRAFT LANDED OK AT HIGHER THAN NORMAL SPEED. INSPECTION FOUND PIN
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