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 CA090904006Wire · chafedDURING THE COURSE OF AN IMPORT, NACELLE WAS DISCOVERED TO HAVE SEVERAL DAMAGED STRUCTURAL COMPONENTS. ENTIRE SKIN WAS REMOVED FROM INBD SIDE OF THE LT NACELLE. 4 GAUAGE WIRES, RUNNING THROUGH THE NACELLE FROM THE GENERATOR TO GENERATOR RELAY AND FROM WING TOSDR CA090904007Structure · crackedTHE 27-35008-010 KEELSON CAP WAS DISCOVERED CRACKED ON LR RADIUS. THIS IS A FAIRLY COMMON DEFECT AND WHEN NACELE SKIN WAS REMOVED TO REPLACE IT, 27-35004-002 CAP WAS FOUND CRACKED AS WELL. THIS PART CAN BE INSPECTED IN SERVICE BUT WOULD BE DIFFICULT TO SEE,SDR CA090904008Drive Gear · contaminatedACFT WAS IN THE HANGAR FOR OTHER MX, ELEVATOR CONTROL WAS NOTED AS "ROUGH". INSPECTED AND DETERMINED IT WAS SAS SERVO CAUSING PROBLEM. SERVO WAS REMOVED FROM CLUTCH ASSY AND PROBLEM WENT AWAY. DISCOVERED CONTAMINATION IN FORM OF DIRT ON SERVO DRIVE GEAR, INTSDR CA090821006Potentiometer · failedAFTER APPLYING PWR ON THE TAKEOFF ROLL ON RWY 31, ACFT BECAME DIFFICULT TO CONTROL ON THE TAKEOFF ROLL. NOSE STEERING WAS BEHAVING AS IF IT WAS STILL IN FULL `PARK` MODE, WITHOUT THE PARK BUTTON BEING DEPRESSED, AND STEERING WAS VERY SENSITIVE AND ALMOST IMPOSSDR CA090811004Switch · failedON COMPLETION OF A TEST FLIGHT, COMING IN TO LAND, CREW DID NOT GET 3 GREEN DOWN AND LOCKED. RT MAIN DID NOT INDICATE DOWN AND LOCKED. GEAR WAS RECYCLED 3 TIMES. ON THIRD ATTEMPT, AFTER ABOUT 20 SECONDS THE RT MAIN WENT GREEN. CREW THEN ELECTED TO DO A LOW SDR CA090813011Skin · crackedDURING A ROUTINE TAIL INSP, THE 27-41000-103 VERTICAL STABILIZER SKIN WAS FOUND CRACKED APPROX 4-5 INCHES AT HORIZ STAB CUTOUT. CUTOUT IS DESIGNED TO ALLOW MOVEMENT OF THE HORZONTAL STABILIZER. SKIN WAS REPAIRED IAW THE SRM. IT WAS DISCOVERED THE SKIN WAS CSDR CA090728014Skin · crackedWHILE CARRYING OUT AD 2009-11-16 AND A SCHEDULED PHASE 3 INSP A LARGE CRACK AND SEVERAL SMALL CRACKS WERE DISCOVERD IN THE RT L/E, BEHIND NACELLE SKIN. AREA IS VERY DIFFICULT TO INSPECT AND WAS FOUND BY LOOKING FROM THE LANDING GEAR WELL. CRACK IS EMENATING FSDR CA090727008Regulator Valve · leaking(CAN) ON DEPARTURE, AFTER COMPLETED TAKE OFF CHECKS AND WERE CLIMBING THROUGH ABOUT 5500FT 20-25NM TO THE EAST, WING OVER HEAT LIGHT CAME ON. FOLLOWED THE DRILL, HIT THE TIMER FOR 3 MIN. REQUESTED IMMEDIATE 180 BACK TO DEPARTURE AND WERE CLEARED CONTACT APP. SDR CA090720003Shutoff Valve · failed(CAN) WHEN DOING SOME TROUBLESHOOTING ON AN ENG SNAG, THE FUEL SHUTOFF VALVE WAS FOUND TO NOT BE FUNCTIONING. IT WAS REMOVED FROM THE ACFT AND TESTED ON THE BENCH WERE IT FAILED ON A SERIES OF TESTS. VALVE, WHEN TESTED, WOULD STICK OPEN AND CLOSED ON VARIOUSSDR CA090717004Shutoff Valve · sticking(CAN) THE AIRCRAFT WAS FLYING, PILOT TRIED TO SHUTDOWN ENG WITH STOP BUTTON. ENG WOULD NOT SHUTOFF AT THAT TIME WHEN STOP BUTTON WAS PRESSED. PILOT PULLED STOP AND FEATHER BUTTON TO GET ENGINE TO STOP AT THAT TIME. PILOT WENT TO START ENGINE TO TRY AND FINDSDR CA090707005Lock · broken(CAN) 2 LATCH START LOCKS WERE FOUND UNAIRWORTHY. ONE HAD A MISSING COTTER PIN AND THE OTHER HAD COTTER PIN BUT COTTER PIN HOLE WAS ALMOST CRACKED THROUGH THE HSG.SDR CA090702009Line · cracked(CAN) MEDIVAC TRIP , 14 MINUTES AFTER TAKEOFF RT HYD LOW PRESSURE WARNING LIGHT ILLUMINATED. VECTORS BACK TO AIRPORT WERE OBTAINED AND EMERGENCY CHECKLIST WAS CONSULTED. 24 MINUTES AFTER TAKEOFF LT HYD LOW PRESSURE WARNING LIGHT ILLUMINATED AND PRESSURE GUAGE SDR CA090702008Control Cable · broken(CAN) AFTER A NORMAL ENGINE START THE CREW COMPLETED THE NECESSARY CHECKS AND STARTED TO TAXI. DURING THE TAXI IT WAS NOTICED THAT THE RT PWR LEVER FELT LOOSE. THE CREW BEGAN TO MOVE IT AND IT WAS APPARENT THE EITHER THE CABLE WAS BROKEN OR THE LINKAGE HAD CSDR CA090622016Cylinder · cracked(CAN) CYL WAS MAGNETIC PARTICLE INSP DURING STANDARD O/H PROCEDURES. NO DEFECTS WERE NOTED. CYL SENT FOR RECHROMING IAW SRM 202A VOLUME 10. OLD CHROME WAS STRIPPED AND CYL MAG PARTICLE INSPECTED FOR PREP OF NEW CHROME. CRACK DETECTED AT THIS TIME.SDR CA090302008Wire · damaged(CAN) AD2008-12-16 WAS BEING COMPLETED ON THIS ACFT AND THE RT NACELLE NR 4 BUS WIRING WAS FOUND CHAFED AND OVERHEATED AT THE RT BATTERY BOX RELAY TERMINATIONS AS THEY RUN THROUGH THE LEADING EDGE. THE DAMAGE FOUND IS INDICATIVE OF THE DAMAGE INDICATED BY THE SDR CA090226006Windshield · cracked(CAN) DURING CRUISE FLIGHT THE RT COCKPIT HEATED WINDSHIELD OUTER GLASS PANE SHATTERED. CABIN PRESSURE WAS REDUCED AND THE CREW ELECTED TO RETURN TO THE AIRPORT WITHOUT ANY FURTHER INCIDENT. MX INSPECTED THE WINDOW AND FOUND NO CAUSE FOR THE BROKEN GLASS PANSDR CA090219010Windshield · delaminated(CAN) FLIGHT CREW REPORTED THE FOLLOWING: APPROX TEN MINUTES AFTER LEVELING OFF AT 17000 FT, THE CREW NOTED THAT THE F/O SIDE WINDSHIELD HAD SEVERAL SMALL CRACKS IN THE TOP RT CORNER AS WELL AS ONE LARGER CRACK THAT LOOKED SIMILAR TO WHEN A ROCK HITS A CAR WISDR KY7A/09/D3240Fuel Sys · intermittentFUEL SHUTOFF INTERMITTENT ACTIVATION CAUSING FLAMEOUT ON LEFT ENGINE.SDR CA090105011Support Bracket · cracked(CAN) WHEN THE ENGINE WAS BEING TORN DOWN TO GET READY FOR OVERHAUL IT WAS NOTED THAT THE REAR FCU SUPPORT BRACKET WAS CRACKED ALL THE WAY THROUGH. THESE BRACKET HAVE BEEN NOTED TO BE CRACKED WHEN DOING THE ROUTINE ENGINE INSPECTIONS ALSO.SDR CA090106005Solenoid Valve · mismanufactured(CAN) MX REPLACED THE BLEED AIR VALVE SOLENOID FOR A FLIGHT SNAG. THE PN 320250-4-1 SOLENOID IS LOCATED IN THE RT WW OF THE ACFT. AFTER REPLACEMENT OF THE VALVE THE AME DID NOT NOTICE THAT THE ELECTRICAL CONNECTION FOR THE CANNON CONNECTOR ON THE VALVE WAS OSDR CA081218006Bypass Valve · leaking(CAN) THE CREW REPORTED THAT ONE TIRE HAD BLOWN DUE TO FROZEN BRAKES. AN AME WAS SENT TO CHANGE THE WHEEL AND FLY BACK TO THE BASE WITH THE AIRCRAFT. UPON RETURN TO BASE, A LARGE OIL LEAK WAS NOTED COMING FROM THE NR 2 ENGINE. IT WAS EVENTUALLY DETERMINED BSDR CA081216004Windshield · cracked(CAN) DURING TAXI AS THE CREW TURNED INTO A 35 KNOT HEADWIND THE FIRST OFFICER WINDSHIELD SHATTERED. THE WINDSHEILD HEAT WAS SELECTED TO LOW AND THE OUTSIDE AIR TEMPERATURE WAS -36 DEGREES CELCIUS. MAINTENANCE REPLACED THE WINDSHIELD IN ACCORDANCE WITH THE ASDR CA081217016Bearing · failed(CAN) STARTER GENERATOR FAILED IN FLIGHT CAUSING THE RT GEN FAIL LIGHT TO ILLUMINATE. UPON LANDING AND INSPECTION BY MAINTENANCE THE GENERATOR WAS FOUND TO HAVE DAMAGE RELATED TO COMPONENT FAILURE. THE GENERATOR WAS REPLACED AND SENT TO PERIMETER`S OVERHAUL SDR CA081201005Gasket · leaking(CAN) THIS ENG WAS NOTED TO HAVE A OIL LEAK COMING FROM THE BOTTOM OF THE DIAPHRAGM AT THE 2 BOTTOM BOLT HOLES CLOSEST TO THE CHIP DETECTOR. THE GASKET WAS NOTED TO BE STICKING OUT AND NOT SEALING PROPER. UPON FURTHER INVESTIGATION THE OLD STYLE GASKETS PN 310SDR CA081205004Control Cable · broken(CAN) DURING TAXI, CREW SELECTED SPEEDS HIGH & APPLIED POWER. AS POSITIVE TORQUES WERE CALLED TROUGH ABOUT 1200FT/LBS, A SNAP WAS HEARD & THE LT POWER LEVER ADVANCED FORWARD WITH NO FURTHER ENGINE POWER INCREASE. TAKEOFF ABORTED & CREW SLOWLY REDUCED POWER TSDR CA081124003Switch · failed(CAN) AFTER TAKEOFF CREW WAS UNABLE TO RETRACT THE ACFT LANDING GEAR. THE CREW ELECTED TO RETURN TO AIRPORT OF ORIGIN AND CONTACT MX. THE ACFT WAS FERRIED HOME WITH THE GEAR DOWN. UPON INSP FROM MX, THE MLG SAFETY SWITCH WHICH CONTROLS THE AIR/GROUND PORTION SDR CA081124006Switch · failed(CAN) ON APPROACH TO LAND THE FLIGHT CREW COULD NOT GET THE GREEN DOWN AND LOCKED LIGHT FOR THE NLG TO ILLUMINATE. THE GEAR WAS CYCLES SEVERAL TIMES AND THE EMERGENCY GEAR EXTENSION USED. AFTER SEVERAL MINUTES THE NOSE GEAR DOWN AND LOCKED GREEN LIGHT ILLUMINASDR CA081124005Switch · failed(CAN) THE CREW COULD NOT GET A NOSE GEAR DOWN AND LOCKED INDICATION AFTER SEVERAL DOZEN GEAR POSITION CYCLES OR WITH MANUAL GEAR EXTENSION. WITH THE LAST ATTEMPT IT ILLUMINATED WITH ELECTRICAL SELECTION. EMERGENCY SERVICES AT AIRPORT WERE ON STANDBY. THE ACFTSDR CA081017004Blade · damaged(CAN) IT WAS NOTICED ON A GROUND RUN AFTER THE ENGINE WAS INSTALLED THAT THERE WAS A SQUEALING NOISE COMING FROM THE ENGINE. THE ENGINE WAS REMOVED AND FORWARDED TO THE ENGINE SHOP FOR EVALUATION. UPON DISASSEMBLY THE NR 1 IMPELLER WAS FOUND TO HAVE A PIECE OFSDR CA080918004Housing · separated(CAN) DURING ENGINE START THE NR 2 ENGINE HYDRAULIC PUMP BEGAN TO LEAK SIGNIFICANTLY CAUSING A LOSS OF SYSTEM PRESSURE AND FLUID. UPON INSPECTION BY MX THE PUMP WHICH WAS JUST INSTALLED 2.5 HRS PRIOR WAS FOUND TO HAVE SEPARATED AT THE PUMP HOUSING HALVES AND SDR CA080926003Arm · cracked(CAN) FOUND 3 OF 4 RUDDER PEDAL ATTACH ARMS CRACKED ON LWR END, WHERE THE TORQUE TUBE THAT THE PEDAL IS MOUNTED TO ATTACHES TO THE CAST ARM. MATERIAL THICKNESS IS APPROX .2500 INCH IN THAT AREA. ACFT IS 17,800 TOTAL TIME, LOW FOR THIS TYPE OF ACFT. HAVE PREVSDR CA080903008Windshield · cracked(CAN) CAPTAINS WINDOW SHATTERED ON DECENT DURING FINAL LEG INTO BASE. SHORTLY AFTER ENTERING CLOUD WITH ICING. W/S HEAT WAS ON LOW. MAINT REPLACED THE WINDSHEILD. NO EXTERNAL DAMAGE COULD BE FOUND ON THE WINDOW WHICH MAY HAVE CAUSED THE FAILURE. THE TREND OF PSDR CA080903010Windshield · cracked(CAN) ON DESCENT AT APPROX 13000FT THE LT HEATED WINDSHIELD CRACKED. MAINT REPLACED THE WINDSHEILD AND NO PREXISTING DAMAGE WAS FOUND WHICH WOULD HAVE CONTRIBUTED TO THE WINDOW CRACKING. PREMATURE FAILURE OF THESE WINDOWS IS NOT UNCOMMON.SDR CA080811006Rod End · worn(CAN) THE FUEL CONTROL WAS BEING REPLACED ON THE RT ENGINE. WHEN THE STARTER GENERATOR WAS REMOVED IT WAS APPARENT THAT THE POWER LEVER, WHERE IT ATTACHES TO THE PROP PITCH CONTROL BY A ROD END, WAS SEVERELY WORN. THE TIME SINCE INSTALL IS NOT KNOWN, HOWEVER TSDR CA080808005Valve · inoperative(CAN) CREW REPORTED MINOR ISSUE WITH STIFF POWER LEVER ON ONE ENGINE. MAINT EXAMINED THE CONTROL LINKAGE AND FOUND THAT THE FUEL CONTROL`S MANUAL FUEL VALVE (MFV) WOULD NOT REACH FULL TRAVEL (APPROX 85 PERCENT OF TRAVEL) REMOVED THE UNIT FOR REPAIR.SDR CA080731001Drag Brace · cracked(CAN) DURING A DAILY INSP BY MAINT PERSONNEL, THE NR 3 LUG SECURING THE UPLOCK HOOK TORQUE SHAFT TO THE DRAG BRACE WAS FOUND CRACKED IN HALF AND SEPARATED FROM THE DRAG BRACE. REPLACED WITH A SERVICEABLE DRAG BRACE, RIGGED AND ADJUSTED WITH NO FURTHER ISSUES.SDR CA080609005Tube · leaking(CAN) THE CREW OF THE ACFT REPORTED LOW POWER FROM THE NR 1 ENGINE. DURING THE COURSE OF TROUBLESHOOTING MX SUSPECTED A BLEED AIR LEAK CAUSED BY A CRACK IN THE BELLOWS FOR THE BLEED AIR LINE. THIS FLEXIBLE JOINT IS COVERED IN A WIRE HEAT SHIELD AND UPON CUTTINSDR CA080609004Actuator · unresponsive(CAN) SHORTLY AFTER DEPARTING, AND ACCELERATING THROUGH 200KTS, THE PITCH TRIM STOPPED RESPONDING. TRIM SONALERT WAS SOUNDING WHENEVER THE TRIM SWITCH WAS USED, HOWEVER THE TRIM GAUGE WAS NOT MOVING AND THE ACFT CERTAINLY WAS NOT TRIMMING. THIS WAS ATTEMPTED OSDR CA080609006Duct · cracked(CAN) DURING A ROUTINE INSP IT WAS DISCOVERED VISUALLY THAT A BLEED AIR LINE TO THE HEAT EXCHANGER OF THE AIR CYCLE MACHINE HAD CRACKED 2 INCHES, ABOUT ONE THIRD THE CIRCUMFERENCE OF THE TUBE.SDR CA080415005Windshield · crackedDURING THE RETURN LEG TO MAIN BASE THE AIRCRAFT EXPERIENCED A RT HEATED WINDSHIELD CRACK IN A SPIDER WEB FASHION. THE AIRCRAFT DESCENDED THE CABIN DIFF WAS LOWERED AND AIRSPEED REDUCED. UPON WINDOW REMOVAL NO DISCREPANCIES WERE NOTED WITH THE PREVIOUS INSTALLSDR CA080404002Shaft · failedDURING A ROUTINE INSPECTION OF THE HYDRAULIC PUMP, THE RETAINING BOLT WHICH HOLDS THE SPLINE DRIVE INTO THE HYDRAULIC PUMP HAD SHEARED.SDR CA080326002Exhaust Duct · cracked(CAN) WHEN THE ENG WAS UNDERGOING A PHASE 6 INSP, A CRACK APPROX 3 INCH LONG WAS DISCOVERED IN THE ENGINE EXHAUST DUCT NEAR THE EGT PROBE BOSSES. IT APPEARED TO BE ON A PREVIOUS WELD. REMOVED AND REPLACED THE DUCT. (TC NR 20080326002)SDR CA080320003Frame · crackedDURING AN AGING AIRCRAFT INSPECTION A CRACK WAS DETECTED VISUALLY EXTENDING FROM THE LOWER AFT LATCH (POSITION 8). WHEN THE DOOR WAS REMOVED FOR REPAIR FURTHER CRACKS WERE DISCOVERED TO THE ATTACHING STRUCTURE FOR BOTH LOWER LATCHES (POSITIONS 7 AND 8). THISSDR CA080304009Fuel Control · failed(CAN) ENGINE HAD BEEN REMOVED IN RUNNING CONDITION FOR SCHEDULED HOT SECTION/GEARBOX INSP. ENG SENT TO ENGINE SHOP. UPON INITIAL START UP FOR THE TEST CELL RUN, THE ENGINE WOULD NOT START. FUEL CAME OUT THE DRAINS AND THE BACK OF THE ENGINE. THE FUEL PUMP PRESSDR MCC2008F00000Governor · failedWHILE TRAINING FOR A CHECK RIDE, POWER WAS PULLED BACK TO SIMULATE ENGINE AT CONDITION. WHEN POWER WAS REAPPLIED, ENGINE FAILED TO RESPOND ENGINE WAS SECURED, TROUBLESHOOTING DECIDED PROP GOV FAILED. PROP GOV WAS REPALCED WITH OVERHAULED UNIT, ALL CHECK SAT.SDR CA080220002Windshield · delaminated(CAN) DURING THE CRUISE PORTION OF FLIGHT, THE CREW WITNESSED THE RT SIDE COCKPIT HEATED WINDSHIELD PHYSICALLY DELAMINATING . THE CREW INDICATED THE AC WAS OPERATING AT A 6.0 PSI DIFFERENTIAL WHICH IS WITHIN THE MAXIMUM 7.25 PSI DIFFERENTIAL FOR THE AC. NO ACTSDR CA080124005Nut · backed out(CAN) A/C CAME IN TO THE MAINT HANGER DUE TO HAVING A CHIP LIGHT COME ON IN THE COCKPIT. INSP FROM MAINT NOTICED THAT THERE WAS METAL ON THE CHIP DETECTOR OF ENGINE P-54121. AT THAT TIME THE ENGINE WAS FORWARDED TO THE ENGINE SHOP FOR FURTHER INSP. THE ENGINE SDR CA080117005Adapter · cracked(CAN) DURING THE DAILY INSPECTION IT WAS NOTICED THAT THERE WAS OIL IN THE BOTTOM OF THE COWLING. FURTHER INSP REVEALED THAT THE (3) OF THE (4) TANGS FOR THE STUDS WHICH HOLD DOWN THE OIL FILTER ADAPTER WERE CRACKED. TOTAL TIME ON THIS PART IS UNDETERMINED BECSDR CA071218006Windshield · cracked(CAN) UPON ENGINE START AND TAXI THE F/O HEATED WINDSCREEN CRACKED. THE GLASS CRACKED FROM THE BOTTOM UP. THE CREW TURNED AROUND AND SHUTDOWN. MAINT REMOVED AND REPLACED THE WINDOW. OUR COMPANY CONTINUES TO HAVE PROBLEMS WITH THESE HEATED WINDSHIELDS AND IN SPSDR CA071116001Sensor · overheated(CAN) THE FOLLOWING WAS REPORTED BY THE FLIGHT CREW FOLLOWING THE CO-PILOTS HEATED WINDSHIELD FAILURE: (WHILE ON THE ILS FO MENTIONED A BURNING SMELL, AND NOTICED IT AS WELL.) TOOK MY FLASHLIGHT OUT BUT COULD NOT NOTICE ANY DETECTABLE SMOKE IN THE CABIN OR COC
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