Garrett TPE331-12UHR
Service difficulty reports · 287
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 = 'TPE33112UHR' 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 = 'TPE33112UHR' 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 AU000128021Nut · not safetied(AU) THE LEFT ENGINE DID NOT RESPOND WHEN THE SPEED LEVER WAS ADVANCED FOR TAKEOFF. THE SPEED LEVER CONTROL CABLE WAS FOUND DISCONNECTED FROM THE BALL JOINT. THE RIGHT ENGINE SPEED LEVER CABLE WAS FOUND TO BE MISSING THE JAM NUT AND THE REMAINING NUT WAS NOT SDR AU991088Engine · seized(AUS) LEFT ENGINE HARD TO TURN. METAL CONTAMINATION OF ENGINE OIL SYSTEM. FURTHER INVESTIGATION FOUND PROPELLER AND OIL COOLER ALSO METAL CONTAMINATED.SDR AU990988Engine · overtemp(AUS) NR 2 ENGINE OVERTEMPED TO 700 DEGREES CELSIUS. INSPECTION IAW GARRETT MM. FOUND NO DEFECTS. EGT CONNECTOR (2KR31) FOUND TO HAVE A DISLODGED PIN.SDR AU990924Pipe · loose(AUS) LEFT FUEL FILTER BYPASS LINE 'B' NUT LOOSE AT FUEL FILTER END.SDR AU990928O Ring · damaged(AUS) LEFT MAIN LANDING GEAR INBOARD BRAKE UNIT O-RING SEAL LEAKING. SUBMITTER SUSPECTED CAUSED BY BRAKE OVERHEATING DURING TAXI.SDR AU990908Wire · worn(AUS) ENGINE FUEL BYPASS VALVE WIRE WORN AND SHORT CIRCUITING.SDR AU990880Spar · cracked(AUS) WING SPAR WEB CRACKED IN THE AREA BETWEEN STRINGER NR 14 CUT-OUT AND THE ADJACENT TRIM CABLE CUT-OUT. CRACK LENGTH 1.016 MM (0.040 INCH).SDR AU990926Brake · overheated(AUS) NR 2 BRAKE PACKING BINDING AND OVERHEATING. WATER ALSO FOUND IN BRAKE MASTER CYLINDERS.SDR AU990108Connector · contaminated(AUS) LT ENGINE EGT SYSTEM CONNECTION CONTAMINATED WITH MOISTURE.SDR AU990107Engine · malfunctioned(AUS) LT ENGINE LOST POWER AND DID NOT RESPOND TO THE LT POWER LEVER. EXTENSIVE INSPECTION AND GROUND RUN FOLLOWED BY A TEST FLIGHT COULD FIND NO FAULTS. ENGINE HAS OPERATED SATISFACTORILY SINCE. DEFECT NOT CONFIRMED.SDR AU990026Tailpipe · cracked(AUS) ROGHT ENGINE TAIL PIPE ASSEMBLY AFT END HAD EXCESSIVE ORBITAL MOVEMENT. THE PIPE WAS REMOVED AND IT WAS DISCOVERED THAT THE PIPE HAD CRACKED THE AFT END WAS SEPARATING FROM THE FORWARD FLANGED END FOR 99.5 PERCENT OF ITS CIRCUMFERENCE. THE CAUSE WAS FOUSDR SABA980050Engine · failedRDU - FLT 5215 - RIGHT ENGINE LOST RPM AND OIL PRESSURE. SHUT THE ENGINE DOWN. CREW DECLARED EMERGENCY. AIRCRAFT LANDED SAFELY NO INCIDENTS. REMOVED AND REPLACED RIGHT ENGINE IAW JE32 MM ATA 71-00-01. (M)SDR SABA980016P3 Line · looseCLT - FLT 5167 - ON FLIGHT FROM LEX TO CLT, PILOT REPORTED TO DISPATCH THAT THE RIGHT ENGINE STARTED LOOSING POWER. THE ENGINE FINALLY SHUT ITSELF DOWN. AIRCREW DECLARED AN INFLIGHT EMERGENCY AND LANDED SAFELY AT CLT. MAINTENANCE FOUND THE P3 LINE ON THE RTSDR SABA980013Engine · failedFAY - FLT 5078 - ON FLIGHT FROM OAJ TO CLT, PILOT STATED THERE WAS A SLIGHT ENGINE SURGE AND RAPIDLY FOLLOWED BY A RT ENGINE SHUTDOWN. ALL ENGINE INDICATIONS NORMAL PRIOR TO SHUTDOWN OF RT ENGINE. AIRCREW DECLARED AN IN-FLIGHT EMERGENCY. AIRCREW ALSO TRIED SDR 98ZZZX122Bleed Line · looseHOT/SAT - FLT 9907 - ACFT FERRIED HOT/SAT FOR HORIZ STAB EXCESSIVE PLAY. AT 80 KTS DURING TAKEOFF ROLL, EGT AND TORQUE SPLIT NOTED. AT V1, EGT SPLIT WAS 70 DEG AND TORQUE 10 PERCENT LOWER ON LT ENG. SIMULTANEOUS WITH ROTATION, LT ENG FIRE WARNING. AT 400 SDR 97ZZZX771Seal · crackedSEAL CRACKED AT FLANGE. SB 72-0840 AUTHORIZES INSTALLATION OF THIS PART TO PROVIDE INCREASED SEAL PLATE TENSION AGAINST THE 1ST STAGE ROTOR ASSY. INCREASED TENSION CAUSES CRACKING AT FLANGE. THIS IS A CRITICAL LIFE-LIMITED COMPONENT. LIMIT 20,000 CYCLES. SDR 97ZZZX772Seal · crackedSEAL FOUND CRACKED AT SEALING FLANGE. SB 72-0840 AUTHORIZES INSTALLATION OF THIS PART TO PROVIDE INCREASED SEAL TENSION AGAINST FIRST ROTOR ASSY. INCREASED TENSION RESULTS IN CRACKING AT FLANGE. PART IS A CRITICAL LIFE LIMITED ROTATING GROUP COMPONENT. LIMSDR 97ZZZX6191Bearing · failedENGINE RECEIVED FROM AIR CARRIER FOR THIS REPAIR. REPAIR STA NOT SURE IF THERE WAS AN IN-FLIGHT SHUT DOWN OCCURRENCE. REPAIR OF ENGINE WAS TO REPLACE ACCESSORY GEAR ASSEMBLY WITH OVERHAULED UNIT OF SAME PART NUMBER, CONTAINING NEW 3103035-1 BEARINGS. THESE BSDR 97ZZZX770Bearing · failedREAR TURBINE BEARING FAILED RESULTING IN MOVEMENT OF MAIN ROTATING GROUP. SECONDARY DAMAGE INCLUDED SEVERE RUBBING OF ALL ROTATING COMPONENTS DUE TO FREE MOVEMENT OF MAINSHAFT CAUSED BY BEARING FAILURE. IMPACT DAMAGE ALSO AFFECTED EXHAUST GAS TEMPERATURE HARSDR 96ZZZM1172Idler Gear · failedAFTER TAKEOFF FROM WDG, THE CREW GOT A CHIP LIGHT ON THE RIGHT ENGINE. THE CAPTAIN DECIDED TO RETURN TO WDG AND MAKE A PRECAUTIONARY SHUTDOWN OF THE RIGHT ENGINE. DURING THE PRE-SHUTDOWN CHECKS, THE ENGINE FLAMED OUT. THE CREW THEN MADE A LANDING AT WDG WITSDR 96ZZZM1021Bearing · failedAFTER LANDING AT ROW, THE CHIP DETECTOR LIGHT CAME ON. THE PILOT COMPLETED A NORMAL SHUTDOWN WITH NO FURTHER INDICATIONS. AFTER INSPECTING THE CHIP DETECTOR, IT WAS DETERMINED A FAILURE HAD TAKEN PLACE IN THE GEARBOX. AFTER INSPECTING THE GEARBOX, IT WAS FOSDR 96ZZZM1022Idler Drive Assy · strippedAFTER STARTING ENGINES AND TAXIING FOR TAKEOFF, THE RIGHT ENGINE SHUTDOWN WITHOUT WARNING. THE AIRCRAFT TAXIED BACK TO THE GATE. UPON INSPECTION OF THE GEARBOX, THE ACCESSORY GEAR ASSEMBLY WAS FOUND TO BE STRIPPED IN THE CENTER OF THE GEAR. THIS GEAR, P/N 3SDR 96ZZZM1023Gear Assy · strippedAFTER STARTING ENGINES AND TAXIING FOR TAKEOFF, THE RIGHT ENGINE SHUTDOWN WITHOUT WARNING. THE AIRCRAFT TAXIED BACK TO THE GATE. UPON INSPECTION OF THE GEARBOX, THE ACCESSORY GEAR ASSEMBLY WAS FOUND TO BE STRIPPED IN THE CENTER OF THE GEAR. THIS GEAR, P/N 3SDR 96ZZZX1729Seal · flange crackedDURING SCHEDULED CAM INSPECTION, FOUND AIR SEAL CRACKED AT FLANGE. CRACKING RESULTED IN DEFLECTION OF SEALING SURFACE OF .040 INCH CAUSING LOSS OF COOLING AIR FOR TURBINE SECTION. THIS IS A CRITICAL LIFE-LIMITED COMPONENT. LIFE-LIMIT IS 20,000 CYCLES. SUBMSDR 96ZZZX1730Seal · flange crackedDURING SCHEDULED CAM INSPECTION, FOUND ROTATING AIR SEAL CRACKED AT FLANGE. THIS IS A CRITICAL LIFE-LIMITED COMPONENT. LIFE-LIMIT IS 20,000 CYCLES. SUBMITTER STATES THIS IS THE 29TH MALFUNCTION/DEFECT REPORT SUBMITTED BY THIS FACILITY ON THIS DISCREPANCY. SDR 96ZZZX1727Seal · flange crackedDURING SCHEDULED CAM INSPECTION, FOUND AIR SEAL CRACKED AT FLANGE. THIS IS A CRITICAL LIFE-LIMITED COMPONENT. LIFE-LIMIT IS 20,000 CYCLES. SUBMITTER SUGGESTS THIS IS THE 26TH MALFUNCTION/DEFECT REPORT ON THIS PART BY THIS FACILITY. PART TOTAL CYCLES, 7,435SDR 96ZZZX1728Seal · flange crackedDURING INSPECTION FOR BIRD INGESTION, FOUND AIR SEAL CRACKED AT FLANGE. THIS IS A CRITICAL LIFE-LIMITED COMPONENT. LIMIT - 20,000 CYCLES. SUBMITTER STATES THIS IS THE 27TH MALFUNCTION/DEFECT REPORT ON THIS PART BY THIS FACILITY. PART TOTAL CYCLES, 9,859.SDR 96ZZZX1726Seal · flange crackedDURING INSPECTION FOR METAL CONTAMINATION, FOUND AIR SEAL CRACKED AT SEALING FLANGE. THIS IS A CRITICAL LIFE-LIMITED COMPONENT. LIFE-LIMIT IS 20,000 CYCLES. SUBMITTER STATES THIS IS THE 24TH MALFUNCTION/DEFECT REPORT SUBMITTED ON THIS PART BY THIS REPAIR STSDR 96ZZZX1724Seal · flange crackedDURING SCHEDULED HOT SECTION INSPECTION, FOUND AIR SEAL CRACKED AT SEALING FLANGE. THIS IS A CRITICAL LIFE-LIMITED COMPONENT. LIFE-LIMIT IS 20,000 CYCLES. SUBMITTER SUGGESTS ALLIED SIGNAL ENGINEERING DETERMINE/CORRECT CAUSE OF CRACKING. THIS IS THE 22ND MSDR 96ZZZX1725Seal · flange crackedDURING SCHEDULED HOT SECTION INSPECTION, FOUND AIR SEAL CRACKED AT FLANGE. THIS IS A CRITICAL LIFE-LIMITED COMPONENT. LIFE-LIMIT - 20,000 CYCLES. SUBMITTER SUGGESTS ALLIED SIGNAL ENGINEERING DETERMINE AND CORRECT CAUSE OF CRACKING. THIS IS THE 23RD MALFUNCTSDR 96ZZZX1723Seal · flange crackedDURING SCHEUDLED CAM INSPECTION, FOUND AIR SEAL CRACKED AT FLANGE. THIS IS A MAIN ROTATING GROUP. CRITICAL LIFE-LIMIT IS 20,000 CYCLES. SUBMITTER SUGGESTS ALLIED SIGNAL ENGINEERING DETERMINE AND CORRECT THE CAUSE OF THIS PROBLEM. THIS IS THE 21ST MALFUNCTISDR 96ZZZX1721Seal · flange crackedDURING REPAIR, FOUND AIR SEAL CRACKED AT SEAL FLANGE. CRACK RESULTED IN .025 INCH DEFLECTION OF SEALING FLANGE AND CORRESPONDING LOSS OF TURBINE SECTION COOLING AIR AROUND ENTIRE DIAMETER OF SEAL CAUSING SECONDARY DAMAGE TO TURBINE SECTION COMPONENTS. THIS ISDR 96ZZZX1720Seal · flange crackedDURING SCHEDULED HOT SECTION INSPECTION, FOUND AIR SEAL CRACKED AT FLANGE APPROXIMATELY 19 PLACES. SUGGEST ALLIED SIGNAL ENGINEERING REVIEW PROBLEM. SUBMITTER STATED THIS IS A CRITICAL LIFE-LIMITED COMPONENT. LIFE LIMIT - 20,000 CYCLES. THIS IS THE 16TH ROSDR 96ZZZX1719Seal · flange crackedDURING SCHEDULED INSPECTION, FOUND SEAL CRACKED AT FLANGE. SB 72-0840 AUTHORIZES INSTALLATION OF THIS PART TO PROVIDE INCREASED TENSION AGAINST THE FIRST STAGE ROTOR. THIS INCREASED TENSION RESULTS IN CRACKING AT THE SEAL FLANGE. SUBMITTER STATED THIS IS A SDR 96ZZZX1722Seal · flange crackedFOUND SEAL FLANGE CRACKED. SB 72-0840 AUTHORIZES INSTALLATION OF THIS PART TO INCREASE TENSION AGAINST 1ST STAGE ROTOR. INCREASED TENSION RESULTS IN CRACKING AT THE SEAL FLANGE. SUBMITTER STATES THIS IS A CRITICAL SERVICE, LIFE-LIMITED COMPONENT. LIMIT - 2SDR 96ZZZX1717Seal · flange crackedDURING INSPECTION/REPAIR FOR LOW POWER, FOUND SEAL PLATE CRACKED. SB 72-0840 AUTHORIZES INSTALLATION OF THIS PART TO INCREASE SEAL PLATE TENSION AGAINST FIRST STAGE ROTOR ASSY. INCREASED TENSION ON THE SEAL FLANGE RESULTS IN CRACKING AT THE EDGE PROPAGATING SDR 96ZZZX1718Seal · flange crackedFOUND SEAL CRACKED AT FLANGE APPROXIMATELY 14 PLACES. THIS IS A CRICITAL LIFE-LIMITED COMPONENT. LIMIT - 20,000 CYCLES. SUBMITTER SUGGESTS ALLIED SIGNAL ENGINEERING DETERMINE/CORRECT CAUSE. THIS IS THE 12TH SEAL PLATE FOUND CRACKED AT THIS FACILITY. PART
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