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 CA991004057Actuator · seized(CAN) IN PREPARATION FOR DESCENT, THE PILOT WAS UNABLE TO OPERATE THE PITCH (STABILIZER) TRIM. THE AIRCRAFT LANDED WITH NO PITCH TRIM CONTROL. MAINTENANCE DETERMINED THE TRIM ACTUATOR WAS SEIZED AND REPLACED IT.SDR CA990614032Impeller · separated(CAN) DAMAGE TO NR 1 IMPELLER , REPORT TO FOLLOW.SDR CA990430021Hinge · damaged(CAN) RIGHT MLG WOULD NOT EXTEND. AFTER APPROXIMATELY 150 ATTEMPTS, THE GEAR EXTENDED INTO A DOWN AND LOCKED POSITION. INVESTIGATION REVEALED THAT THE MISALIGNMENT OF THE INBOARD GEAR DOOR DUE TO ELONGATED HOLES IN THE HINGE BRACKETS (P/N 27-55 001-213) CAUSSDR CA990330022Actuator · malfunctioned(CAN) PITCH TRIM FAILED IN-FLIGHT. SUBSEQUENT INVESTIGATION REVEALED THAT BOTH UPLIMIT SWITCH ACTUATORS WERE STICKING. SWITCHES CLEANED AND AIRCRAFT RETURNED TO SERVICE.SDR AU990077Pump · failed(AUS) NR 2 ENGINE GEARBOX FUEL PUMP DRIVE FAILED.SDR CA990129015Mixing Valve · failed(CAN) ON DESCENT, SMOKE NOTED IN AFT CABIN FOLLOWED BY AIR CONDITIONER CIRCUIT BREAKER TRIPPING. INSPECTION SHOWED THAT THE LEFT MIXING VALVE HAD INTERNALLY SHORTED ITSELF TO GROUND DAMAGING THE PRINTED CIRCUIT BOARD ON CABIN TEMPERATURE CONTROLLER. THIS WASSDR AU990020Torque Tube · worn(AUS) DURING RUDDER REMOVAL, IT WAS FOUND THAT THE PRESSURIZATION SEAL CARRIER HAD WORN INTO THE RUDDER TORQUE TUBE. SUSPECTED CAUSE ATTRIBUTED TO THE BELLCRANK BEARING HAVING EXCESSIVE SIDE PLAY.SDR CA990311010Windshield · cracked(CAN) DURING CRUISE, A CRACK APPEARED IN PILOT'S WINDSCREEN EMANATING FROM LOWER LEFT CORNER. WINDSHIELD HAD BEEN INSPECTED IAW AD 96-20-08 212 HOURS PREVIOUS.SDR CA990311006Fcu · malfunctioned(CAN) DURING SURGE, NR 1 ENG SURGED WITH EGT INCREASE, EGT REDUCED, ALL ENG PARAMETERS NORMAL. APPROX 2 MINUTES, ENG AGAIN SURGED AND EGT RISE ENCOUNTERED, BUT POWER AND TEMPS COULD NOT BE REDUCED BY POWER LEVER. ENG WAS SHUT DOWN AND ACFT LANDED WITHOUT INSDR CA990311008Fcu · malfunctioned(CAN) DURING START OF THE NR 1 ENGINE, FLAMES WERE NOTICED FROM THE TAILPIPE, WITH THE EGT RISING TO AN OVERTEMP CONDITION. THE ENGINE START WAS ABORTED. POST ABORT, THE FUEL CONTROL UNIT WAS REPLACED, RIGGED AND TESTED SERVICEABLE. THE AIRCRAFT WAS RETURNESDR CA990311004Seal · leaking(CAN) NR 2 ENGINE HAD OIL PRESSURE FLUCTUATION IN CRUISE. ON ROLL-OUT, THE NR 2 ENGINE OIL PRESSURE DROPPED AND THE LOW OIL WARNING ILLUMINATED. THE ENGINE WAS SHUT DOWN. POST-FLIGHT INSPECTION FOUND OIL ON THE ENGINE NACELLE AND THE GEAR LEG. FURTHER INSPECSDR CA990311007Switch · sticking(CAN) NOSE LANDING GEAR FAILED TO SHOW GREEN WHEN SELECTED DOWN. INVESTIGATION REVEALED DOWN MICROSWITCH FAILED. SWITCH REPLACED.SDR CA990311009Wire · shorted(CAN) PITCH TRIM FAILED ACCOMPANIED WITH CIRCUIT BREAKER TRIPPING. WIRE NR 7715-16S FOUND SHORTED ADJACENT TO UPLIMIT SWITCH.SDR CA990111052Yoke · cracked(CAN) DURING INSPECTION FOR AD 96-19-05, TWO .25 INCH CRACKS, ONE ON THE NOSE AND THE OTHER ON THE LEFT SIDE WERE FOUND. THESE CRACKS ONLY VISIBLE WITH SPECIAL INSTRUMENTS. NOSE GEAR P/N 27-52500-007. PART TC: 14,527.SDR CA990111007Rivets · sheared(CAN) THE RIVETS WHICH FASTEN THE UPPER WING SKIN TO THE FLAP ACTUATOR CASTING ASSEMBLY WERE FOUND SHEARED AND PULLED THROUGH, AT WS 98.385 AND WS 100.635. THIS AREA IS DIRECTLY BEHIND THE EXHAUST STACK, APPEARS TO BE THE KEY FACTOR TO THE DEFECT. FLEET BEINSDR AU981540Web · cracked(AUS) CENTER SPAR WEB CRACKED. FOUND DURING INSPECTION IAW SA226/ST-UN-M002.SDR CA981109048Wire · chafed(CAN) RIGHT HAND FUEL QUANTITY INDICATOR INTERMITTENTLY ROTATES CLOCKWISE. FUEL PROBE REPLACED AT WS 115.9 AND WIRE REPAIRED BETWEEN CENTER TUBE AND THE TOP TERMINAL PROBE.SDR CA981125057Uplock · contaminated(CAN) ON APPROACH, NOSE GEAR DID NOT EXTEND WHEN SELECTED. EMERGENCY RELEASE WAS PULLED AND THE GEAR FREE-FELL TO DOWN AND LOCKED. INSPECTION FOUND THE NOSE UPLOCK LATCH ROLLER WAS COVERED IN DIRT FROM THE GRAVEL RUNWAYS. INSPECTION TO CLEAN UPLOCK ADDED TOSDR CA981125056Pump · failed(CAN) DURING CRUISE, THE NR 2 ENGINE OIL PRESSURE WAS FLUCTUATING AND ON FINAL, DROPPED TO 40 PSI, THE AIRCRAFT LANDED WITHOUT INCIDENT. POST-FLIGHT INSPECTION FOUND THE OIL LEVEL LOW DUE TO HIGH OIL CONSUMPTION, CAUSED BY THE FAILURE OF THE REAR OIL SCAVENGESDR CA981022009Line · cracked(CAN) AFTER TAKEOFF, ANNUNCIATOR PANEL INDICATION OF A HYDRAULIC LEAK. AIRCRAFT RETURNED TO AIRPORT OK. INVESTIGATION FOUND A CRACKED PIPE. 14,411.SDR AU981390Line · failed(AUS) CABIN BLEED HOSE BROKEN AT FLANGE. HOSE IS A PRE-MOD ITEM.SDR AU981280Downlock · contaminated(AUS) NOSE LANDING GEAR DOWNLOCK CONTAMINATED WITH GRIT AND SAND. AIRCRAFT HAD BEEN OPERATING ON UNSEALED RUNWAYS DURING WET WEATHER. PART TC: 13,799.SDR CA980916043Drag Link · cracked(CAN) DURING FLEET INSPECTION, FOLLOWING TSB FINDINGS ON THE MAIN LANDING GEAR DRAG LINKS, CRACK INDICATIONS WERE FOUND ON BOTH RIGHT HAND LOWER DRAG LINK ASSEMBLIES USING FLUORSCENT PENETRANT METHOD. FOUND CRACKS EMANATING FROM GREASE NIPPLE HOLE TO OUTER RASDR CA980827005Uplock · failed(CAN) ON APPROACH, LEFT GEAR DID NOT EXTEND WHEN GEAR SELECTED. NO IN-TRANSIT LIGHT NOTED, INDICATING GEAR DID NOT RELEASE FROM UPLOCK. EMERG EXTENSION CARRIED OUT BUT LEFT GEAR STILL FAILED TO EXTEND. GEAR RETRACTED AND NORMAL EXTENSION CARRIED OUT. LEFT SDR CA980811003Bushing · binding(CAN) LEFT MAIN GEAR FAILED TO EXTEND AFTER SEVERAL ATTEMPTS. GEAR MANUALLLY EXTENDED AND AIRCRAFT LANDED OK. INSPECTION REVEALED THAT THE UPPER DRAG BRACE PIVOT BUSHINGS WERE PUSHED OUT TOWARDS THE UPPER DRAG BRACE BINDING THE BRACE AND PREVENTING IT FROM SDR CA980720011Wire · broken(CAN) AFTER GEAR SELECTION, RT GEAR HAD UP POSITION SNAG. GEAR EXTENDED OK AND RETURNED TO BASE. WIRES FOUND BROKEN ON GEAR-UP LIMIT SWITCH. ALSO FOUND A BROKEN WIRE ON THE UP POSITION SWITCH. WIRES SEPARATED FROM SWITCH DUE TO AGE ACCORDING TO SUBMITTER.SDR CA980713030Wire · chafed(CAN) SHORTLY AFTER TAKEOFF, THE LEFT CHIP DETECTOR ANNUNCIATOR LIGHT CAME ON. AIRCRAFT RETURNED TO BASE. CHIP DETECTOR WIRE FOUND RUBBING AGAINST THE ENGINE NEAR THE RIGHT HAND MOUNT.SDR CA980724024Line · chafed(CAN) CREW NOTICED HYDRAULIC DRIP FROM CENTER SECTION. INVESTIGATION REVEALED THAT THE HYDRAULIC LINE HAD CHAFED THROUGH.SDR CA980707044Duct · loose(CAN) CREW NOTICED THE LEFT ESSENTIAL BUS WAS ABNORMALLY HOT, SHORTLY AFTER THE NR 1 AUDIO CIRCUIT BREAKER TRIPPED. AIRCRAFT RETURNED OK. INSPECTION REVEALED THAT THE HOT AIR DUCT IN THE LEFT ESSENTIAL BUS AREA HAD BECOME DISLODGED DIRECTING HOT AIR ONTO THSDR CA980724023Duct · loose(CAN) DURING CRUISE, THE CREW NOTED THAT THE LEFT ESSENTIAL BUS WAS ABNORMALLY HOT, SHORTLY AFTER THE NR 1 AUDIO CIRCUIT BREAKER TRIPPED. AIRCRAFT RETURNED TO BASE. INVESTIGATION FOUND THE HOT AIR DUCT IN THE LEFT ESSENTIAL BUS AREA HAD BECOME DISLODGED DIRESDR CA980707042Fuel Control · failed(CAN) DURING DESCENT, POWER WAS ADDED, BUT RIGHT ENGINE WOULD ONLY PRODUCE 1150 TO 1250 FEET/POUNDS OF TORQUE. AIRCRAFT LANDED OK. GROUND RUN DID SAME, BUT AFTER 5 TO 10 SECONDS THE TORQUE JUMPED TO 2206 FEET/POUNDS. EVENTUALLY RIGHT FCU WAS REPLACED.SDR CA980706032Nut · loose(CAN) DURING ENGINE START, THE NR 2 STOP AND FEATHER CONTROL POPPED OUT 1/4 AT 10 PERCENT RPM. START ABORTED. THE NUT ON THE V-BAND OF THE NR 2 STARTER/GENERATOR HAD BACKED OFF ALLOWING THE STARTER/GENERATOR TO ROTATE STRIKING THE ENGINE CONTROLS. V-BAND HASDR CA980602060Transponder · failed(CAN) CREW REPORTED SMOKE COMING FROM BEHIND THE LEFT HAND INSTRUMENT PANEL JUST ABOVE THE TRANSPONDER, ACCOMPANIED BY ELECTRICAL BURNING SMELL. NR 1 TRANSPONDER TURNED OFF AND SMOKE DISSIPATED. CIRCUIT BOARD OF NR 1 TRANSPONDER BADLY BURNED.SDR CA980610020Latch · out of adjust(CAN) CABIN DOOR WARNING LIGHT ON IN-FLIGHT. UPPER AFT CABIN DOOR LATCH ASSEMBLY WAS ADJUSTED.SDR CA980421009Spar Web · cracked(CAN) FAIRCHILD RECENTLY REVISED ITS AIRFRAME INSPECTION MANUAL TO INCLUDE A DETAILED INSPECTION OF THE WING CENTER SPAR INNER WEB. INSPECTION FOUND CRACKING ON THREE DIFFERENT AIRCRAFT. PART TC: 39,582. ACFT TT: 25,974 HOURS.SDR CA980421010Web · cracked(CAN) FAIRCHILD RECENTLY REVISED ITS AIRFRAME INSPECTION MANUAL TO INCLUDE A DETAILED INSPECTION OF THE WING CENTER SPAR INNER WEB. CRACKS HAVE BEEN FOUND ON THE WEB. TWO OTHER AIRCRAFT WITH SIMILAR FINDINGS.SDR CA980421008Probe · shorted(CAN) AFTER DEPARTURE, RIGHT ENGINE FIRE WARNING ON. ENGINE SHUTDOWN AND AIRCRAFT RETURNED. NOTHING FOUND. TWO DAYS LATER DURING TAXI, LIGHT ON AGAIN. COWLINGS REMOVED ONE AT A TIME AND LOWER ENGINE PROBE WAS FOUND SHORTING TO THE METAL COVERING OF AN ENGISDR CA980406040Blades · worn(CAN) WHEN COMPLETING PERIODIC BORESCOPE INSPECTION, THE NR 1 ROTOR BLADES HAD EVIDENCE OF WEAR ON THE LEADING EDGES. FURTHER INVESTIGATION INDICATED BLADES WORN BEYOND LIMITS. ROTOR RETURNED TO GARRETT.SDR CA980406041Blades · worn(CAN) DURING PERIODIC BORESCOPE INSPECTION, THE NR 1 ROTOR BLADES SHOWED EVIDENCE OF WEAR ON THE LEADING EDGES. FURTHER INVESTIGATION SHOWED DAMAGE TO BLADES BEYOND LIMITS. ROTOR RETURNED TO GARRETT.SDR CA980406042Blades · worn(CAN) DURING PERIODIC BORESCOPE INSPECTION, THE NR 1 TURBINE BLADES SHOWED EVIDENCE OF LEADING EDGE WEAR. FURTHER INVESTIGATION INDICATED THAT THE DAMAGE WAS BEYOND LIMITS.SDR CA980406043Blades · worn(CAN) DURING PERIODIC BORESCOPE INSPECTION, THE NR 1 TURBINE BLADES WERE FOUND WORN ON THE LEADING EDGES. FURTHER INVESTIGATION REVEALED THAT THE NR 1 ROTOR BLADES WERE WORN BEYOND LIMITS.SDR CA980406044Blades · worn(CAN) DURING PERIODIC BORESCOPE INSPECTION, IT WAS FOUND THAT THE NR 1 TURBINE BLADES WERE WORN ON THE LEADING EDGES. FURTHER INVESTIGATION FOUND THAT THEY WERE WORN BEYOND LIMITS.SDR CA980406045Blades · worn(CAN) DURING PERIODIC BORESCOPE INSPECTION, THE NR 1 TURBINE BLADES WERE FOUND WORN ON THE LEADING EDGES. FURTHER INVESTIGATION SHOWED THAT THEY WERE WORN BEYOND LIMITS.SDR CA980406039Sleeve · worn(CAN) WHEN NR 1 ENGINE SHUT DOWN, THE NR 1 PROPELLER FEATHERED AND COULD NOT BE PUT ON THE START LOCKS. SLEEVE PIN WORN BEYOND LIMITS AND THE INTERNAL BUSHING WAS ALSO WORN.SDR CA980331003Drag Brace · broken(CAN) ON TOUCHDOWN CREW FELT LEFT GEAR COLLAPSE & HEARD PROP BLADE STRIKING RWY.GO AROUND COMPLETED, BUT ON SUBSEQUENT LDG GEAR WAS NOT LOCKED DOWN LEFT MAIN GEAR PIVOTED REARWARDS ALLOWING LEFT WING TIP & BLADES OF LEFT PROP TO CONTACT GROUND. A/C STOPPED 50 SDR AU980281Mount · worn(AUS) LT ENGINE MOUNT TOP RT DIAGONAL BRACE HAD A HOLE WORN THROUGH BY THE TOP OF THE SWITCH ON THE ANTI-ICE VALVE P/N 319980-13-1. SIZE OF HOLE APPROXIMATELY 4.762MM (0.1875 INCH).SDR CA980317096Latch · seized(CAN) ON CLIMB PASSENGER DOOR WARNING LIGHT ON. AIRCRAFT RETURNED. INVESTIGATION FOUND THE DOOR DIFFICULT TO CLOSE WITH THE LATCH ONLY CATCHING AT ABOUT THE HALF WAY TO FULL LATCH POSITION. WHEN PANELS WEREREMOVED THE DOOR ACTUATOR SHAFT WAS BADLY CORRODED AS SDR CA980317091Fcu · malfunctioned(CAN) THE FUEL CONTROL WAS ON A FIELD EVALUATION FROM WOODWARD. THE PRESENT PROBLEM IS THAT ON START THE FUEL FLOW STARTS AT 50 PPH AND CONTINUES TO INCREASE TO 100 PPH PUTTING TOO MUCH FUEL INTO THE ENGINEON START THUS AN OVERTEMP ON START IS NOTED.SDR CA980302007Wire · damaged(CAN) ON APPROACH, THE RIGHT HAND ENGINE FIRE LIGHT ILLUMINATED BRIEFLY FOR 1 TO 2 SECONDS - THREE DIFFERENT TIMES. THEN IT CAME ON STEADY. RH ENGINE SHUTDOWN. APPROACH ABORTED. POWER WIRE FOUND DAMAGED AT THE FIRE DETECTOR BY THE OIL COOLER. PART TOTAL CYCLESDR CA971210018Collar · 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 BA
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