Garrett TFE731-2
Service difficulty reports · 201
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 = 'TFE7312' 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 = 'TFE7312' 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 CA060224010Swivel · leakingENGINE PYLON DUCT OVERHEAT CAS MESSAGE LIGHT ILLUMINATED 25 MINUTES INTO FLIGHT. AIRCRAFT RETURNED TO BASE. ENGINE GROUND RAN AND FOUND THAT LIGHT EXTINGUISHES WITH POWER BELOW 50%. PYLON DUCT REPLACED.SDR CA060210003Hose · collapsed(CAN) DURING APPROACH THE FLIGHT CREW NOTICED THAT THE RT OB SLAT WAS NOT SHEDDING ICE WITH THE WING ANTI-ICE ACTIVATED. UPON INSPECTION THE RT OB SLAT FLEX HOSE WAS FOUND TO BE SLIGHTLY COLAPSED INTERNALLY. ANTI-ICE SYSTEM WAS ACTIVATED 44 TIMES. (TC NR 200SDR 2006FA0000055Carbon Seal · wornPERFORMED SOAP SAMPLE DUE TO FILTER BYPASSED. SAMPLE CAME BACK NORMAL. PERFORMED ANOTHER SOAP SAMPLE 50 HOURS LATER AND FILTER FAILED DELTA P-CHECK. RESULTS CAME BACK (INSPECT THIS ENGINE IMMEDIATELY) INSTALLED LOANER ENGINE. ORIGINAL ENGINE HAD NR 1, NR 3SDR 2006FA0000056Carbon Seal · wornPERFORMED SOAP SAMBLE DUE TO FILTER BYPASSED. SAMPLE CAME BACK NORMAL. PERFORMED ANOTHER SOAP SAMPLE 50 HOURS LATER AND FILTER FAILED DELTA P-CHECK. RESULTS CAME BACK (INSPECT THIS ENGINE IMMEDIATELY). INSTALLED LOANER ENGINE. ORIGINAL ENGINE HAD NR1, NR3SDR KC82006F00000Wire · arcedPILOT REPORTED SMOKE IN THE COCKPIT. HE TURNED OF THE GLARESHIELD LIGHTING AND THE SMOKE STOPPED. FOUND GLARESHIELD FLORESCENT TUBE LEAD WIRES ARCING TO GROUND. REPLACED FLORESCENT TUBE WITH NEW FLORESCENT TUBE AND INSULTED LEAD WIRE ENDS. OPERATIONAL CHECSDR AU510001771Squat Switch · failed(AUS) RT MAIN LANDING GEAR IB SQUAT SWITCH FAILED. (OTHER CAUSE: AGE ) (CASA NR 510001771)SDR AU510001794Actuator · unserviceable(AUS) RT OB FLAP ACTUATOR WORN EXCESSIVELY IN GIMBAL TO SCREWJACK ATTACHMENT AREA. FURTHER INVESTIGATION FOUND THE ACTUATOR GIMBAL LOWER PIN MISSING. UPPER GIMBAL PIN RETAINING CLIP CORRODED. (OTHER CAUSE: MATERIAL - AGE ) (CASA NR 510001794)SDR CA051205002Engine · bird ingestionON TAKEOFF ROLL, A BIRD WAS INJESTED THROUGH THE LT ENGINE. THE CREW ABORTED TAKEOFF AND SHUTDOWN. THE ENGINE AND ENGINE INLET WILL BE REPLACED AND SENT FOR REPAIR.SDR CA051209004Pump · malfunctionedHYD NR 1 ANNUNCIATOR ILLUMINATED AFTER TAKEOFF. HYDRAULIC PRESSURE WAS LOST ON SYSTEM 1. QUANTITY WAS SUFFICIENT AND STANDBY SYSTEM WORKED NORMALLY. HYD NR 1 SYSTEM PRESSURE PUMP HAS BEEN REPLACED, P/N 40053-03, S/NOFF AH-16041A, S/NON AH-16086A. FILTER INSDR 4510311242005Switch · intermittentLT T/R RED CAS ILLUMINATED ON TAKEOFF ROLL (INDICATES T/R UNLOCK), ON TAXI BACK CAS TURNED YELLOW. MX CHECKED SWITCHES, FOUND S4 TO BE INTERMITTENT. CLEANED SWITCH ACTUATOR, PERFORMED OPERATIONAL CHECK OF SYSTEM , NO FURTHER DEFECTS NOTED.SDR 2006FA0000024Cable · damagedDURING THE INITIAL 5,000 HOUR CABLE INSPECTIONON THIS AIRCRAFT NOTED EXTENSIVE DAMAGE TO THE LOWER LEFT AFT ELEVATOR CONTROL CABLE AND PRESSURIZATION SYSTEM VACUUM LINE WAS FOUND MISROUTED CAUSING DAMAGE TO THE ELEVATOR CONTROL CABLE AND VACCUM LINE. ENGINEERSDR 2006FA0000027Torque Tube · corrodedDURING 5,000 HR INSPECTION, THE RUDDER WAS REMOVED FOR SB, REPAIR OF (RUDDER TORQUE TUBE ASSY BONDING JUMPERS) FOUND CORROSION ON TORQUE TUBE INTERNAL AND EXTERNAL. MOISTURE INGRESSION THROUGH WIRE BUNDLE HOLE. ENGINEERING EVALUATE FOR POSSIBLE INTERNAL INSPSDR 2006FA0000028Torque Tube · corrodedDURING 5,000 HOUR INSPECTION, THE RUDDER WAS REMOVED FOR SB (REPAIR OF RUDDER TORQUE TUBE ASSY BONDING JUMPERS) FOUND CORROSION ON TORQUE TUBE INTERNAL AND EXTERNAL. MOISTURE INGRESSION THROUGH WIRE BUNDLE HOLE. ENGINEERING EVALUATE FOR POSSIBLE INTERNAL INSSDR 2006FA0000026Torque Tube · corrodedDURING 5,000 HOUR INSPECTION, THE RUDDER WAS REMOVED FOR S/B (REPAIR OF RUDDER TORQUE TUBE ASSY BONDING JUMPERS) FOUND CORROSION ON TORQUE TUBE INTERNAL AND EXTERNAL. ON FURTHER INVESTIGATION (EDDY CURRENT INSP) A CRACK INDICATION WAS NOTED .020 INCH DEEP BY SDR CA051002002Gimbal Joint · damaged(CAN) FOUND LEADING EDGE OF LOWER PANEL COVERING OB FLAP ACTUATOR ON BOTH LT AND RT FLAPS DAMAGED. INVESTIGATION FOUND LOWER PIN P/N 145680-1 AND SNAP RING P/N 9-INI7437A2-70 HAD COME OUT OF THE BOTTOM OF GIMBAL ASSY. P/N 145771-1. PART OF ACTUATOR P/N 6627503SDR AU510002081Actuator · leaking(AUS) RT WING SPOILER ACTUATOR LEAKING. LOSS OF HYDRAULIC FLUID.(OTHER CAUSE: MATERIAL ) (CASA NR 510002081)SDR CA050816004Actuator · failed(CAN) DURING CLIMB-OUT AFTER AUTO-PILOT WAS ENGAGED, THE AMBER PRIMARY PITCH TRIM FAIL EICAS MESSAGE CAME ON. SECONDARY TRIM WAS SELECTED AND USED FOR REMAINDER OF FLIGHT. MAINTENANCE TROUBLESHOOTING FOUND THAT THE AUTO-PILOT TRIM ACTIVATION CAUSED FAILURE OFSDR CA050606005Coupling · misaligned(CAN) DURING CLIMB OUT AFTER TAKEOFF, THE LT PYLON BLEED AIR LEAK LIGHT CAME ON. REDUCED POWER ON LT ENGINE, LIGHT WENT OUT AFTER ABOUT 1 MINUTE, RETURNED TO AIRPORT. INSPECTION FOUND IB END OF OZONE CONVERTER IN LOW PRESSURE BLEED AIR SYSTEM, MISALIGNED ANSDR CA050603005Valve · unserviceable(CAN) ON INSPECTION, LT ANTI-SKID VALVE FOUND UNSERVICEABLE. LT ANTI-SKID VALVE REPLACED.SDR CA050518015Embellisher · crackedEMBELLISHER ON RIGHT WHEEL IS CRACKED. RT EMBELLISHER REPLACED WITH NEW UNIT.SDR CA050506012Valve · broken(CAN) DURING TROUBLESHOOTING AN APU FAULT , IT WAS DISCOVERED THAT THE APU FIRE BOTTLE HAD DISCHARGED . WHEN THE BOTTLE DISCHARGED THE OUTLET VALVE'S FLANGE NUT BROKE INTO 3 PIECES AND THE FIRE BOTTLE SUPPORT BRACKET WAS BENT, WHICH CAUSED THE FIRE BOTTLE TO SSDR CA050506002Fire Bottle · discharged(CAN) UPON AIRCRAFT ARRIVAL, THE APU FIRE EXTINGUISHER BOTTLE WAS FOUND READING (0) PSI. NEW BOTTLE ORDERED. UPON INVESTIGATION INTO WHY THE BOTTLE DISCHARGED, CALLED MFG AND WAS INFORMED THAT THIS IS A KNOWN ISSUE WITH THIS MODEL. THE APU FIRE BOTTLE HAS BESDR CA050503006Line · leaking(CAN) DURING PREFLIGHT CHECK, NOTICED FUEL SEEPING FROM LT FLEXIBLE FUEL TRANSFER HOSE LOCATED IN LT WHEEL WELL AREA. SEEPAGE APPEARS TO BE FROM HOSE MATERIAL AND NOT THE FITTING. HOSE ASSY WILL BE SENT TO MFG FOR INSPECTION. NEW HOSE WAS INSTALLED AND LEAKSDR CA050422004Skin · cracked(CAN) THE LOWER FORWARD SKIN SRM REF 53-28-00, FIG 4, ITEM 2, WAS FOUND WITH A 3 INCH LONG CRACK UNDER A FACTORY INSTALLED ADF ANTENNA THAT WAS REMOVED DURING AN AVIONICS UPGRADE. THERE IS NO SCHEDULED REQUIREMENT TO INSPECT UNDER THE ANTENNA, ALTHOUGH LEARJESDR CA050506009Relief Valve · leaking(CAN) DURING GROUND RUN WITH THE LOWER ENGINE COWLING REMOVED, THE ABOVE MENTIONED RELIEF VALVE WAS FOUND LEAKING FUEL. THIS WAS NOT NOTICEABLE WHEN THE COWLING WAS INSTALLED. THIS RELIEF VALVE HAD BEEN INSPECTED FOR S/B 73-5125 AT 1084.7 HOURS WHICH SPECIFIEDSDR CA050401009Starter Gen · failed(CAN) IN CRUISE FLIGHT, JUST PRIOR TO DESCENT FOR LANDING, THE CREW NOTICED A VIBRATION FROM REAR OF AC. THE AIRCRAFT LANDED UNEVENTFULLY. POST FLIGHT INSPECTION FOUND EXCESSIVE AMOUNTS OF BLACK STAIN (CARBON) ON BOTTOM OF LT ENGINE COWLING AFT OF STARTER/GENSDR CA050224006Torque Link · misinstalled(CAN) DURING COMPLIANCE OF SB 45-27-13, REPLACEMENT OF HORIZONTAL STAB. UPPER AND LOWER TORQUE LINK ASSYS, THE LOWER TORQUE LINK WAS FOUND INSTALLED UPSIDE DOWN AND WAS MAKING CONTACT WITH THE UPPER TORQUE LINK WHEN HORIZONTAL STAB. TRAVELS TO FULL DOWN POSITISDR CA050217002Swivel · leaking(CAN) ON CLIMB OUT THE RT ENG PYLON OVHT CAS WARNING ILLUMINATED. EMERGENCY PROCEDURES CARRIED OUT AND POWER REDUCED ON RT ENGINE. ANNUNCIATOR LIGHT EXTINGUISHED 60 TO 90 SECONDS AFTER POWER WAS REDUCED. AN UNSCHEDULED LANDING WAS CARRIED OUT. UPON INSPECTISDR CA041222008Amplifier · inoperative(CAN) DURING FLIGHT, THE CREW NOTICED THAT THE RT FUEL QUANTITY GAUGE HAD DROPPED TO ZERO. THE LOW LEVEL LIGHT DID NOT ILLUMINATE, ASSURING THE CREW THAT THIS WAS AN INDICATION PROBLEM ONLY. THE RT QUANTITY AMPLIFIER WAS REPLACED AND THE SYSTEM WAS PROPERLY CSDR CA041222009Indicator · failed(CAN) DURING CRUISE FLIGHT THE RT FUEL FLOW GAUGE FAILED. GAUGE WAS REPLACED AND SYSTEM TESTED SERVICEABLE.SDR CA041222007Sensor · open(CAN) DURING PREFLIGHT CHECKS, THE LT ENGINE FIRE WARNING FAILED TO TEST. TROUBLESHOOTING REVEALED A FAILED FIRE LOOP. FIRE LOOP WAS REPLACED WITH NEW PRIOR TO FURTHER FLIGHT.SDR 2005FA0000209Stator · erodedDURING 600/1200 HOUR INSPECTION, FOUND (9) NINE BY PASS STATOR BLADES WITH EROSION DAMAGE ON THE LEADING EDGE. BLADES WERE REMOVED AND REPALCED IAW MM. PROBABLE CAUSE: DESIGN ENGINEERING EVALUATE. (EA09200500613) (K)SDR WVE2004F00023Cable · maladjustmentLT AND RT GEAR IN TRANSIT LIGHTS REMAINED ILLUMINATED AFTER GEAR EXTENSION. THE FREEFALL CONTROL LEVER WAS BUMPED OUT OF ITS NORMAL (UP) POSITION AND WHEN THE GEAR WAS SELECTED DOWN AND IT COMPLETED ITS CYCLE THE MAIN LANDING GEAR INBOARD DOOR FREEFALL CABLE SDR 4017Actuator · slowGOING INTO STP RT MAIN GEAR LIGHT FAILED TO COME ON, PILOT DID A GO AROUND, CYCLED THE GEAR LIGHT CAME ON LANDED NO PROBLEM. REMOVED AND REPLACED RT GEAR ACTUATOR FOR BEING SLOW.SDR CA040705007Switch · out of tolerance(CAN) GEAR WOULD NOT RETRACT ON 1ST ATTEMPT, 2ND ATTEMPT WAS SUCCESSFUL FOUND ACTUATOR SWITCH OUT OF TOLERANCE ACTUATOR REPLACED WITH OVERHAULED UNIT GEAR SWINGS COMPLETED.SDR CA040705003Bellcrank · cracked(CAN) BELLCRANK CRACKED AT PIVOT POINT NEW BELLCRANK PT NR 4532103045-004 INSTALLED GEAR SWINGS COMPLETED.SDR CA040705008Power Unit · noisy(CAN) FLAP POWER UNIT NOISY/SLOW, REPLACED WITH OVERHAULED UNIT.SDR AUS20040492Shaft · cracked(AUS) LT MAIN LANDING GEAR IB DOOR GIMBAL ASSEMBLY SHAFT CRACKED FOR APPROXIMATELY 75 PERCENT OF CIRCUMFERENCE.SDR AUS20040481Manifold · cracked(AUS) LT BLEED AIR SPLITTER DUCT CRACKED AND LEAKING FROM THE MATING FLANGE RADIUS.SDR CA040527005Control Module · stiffRT POWER LEVER 'PIGGYBACK' LEVER VERY STIFF, DIFFICULT TO MOVE TO STOW POSITION. THROTTLE CONTROL MODULE REPLACED.SDR AUS20040375Actuator · damaged(AUS) LT MAIN LANDING GEAR IB DOOR ACTUATOR DAMAGED. ACTUATOR HOUSING END CAP SEPARATED FROM HOUSING DUE TO SHEARING OF THE FOUR END CAP BOLT HEADS. LOSS OF HYDRAULIC FLUID.SDR AUS20040261Hose · ruptured(AUS) NOSE LANDING GEAR RETRACTION SYSTEM HYDRAULIC HOSE RUPTURED. LOSS OF HYDRAULIC FLUID.SDR AUS20040131Pipe · fractured(AUS) HYDRAULIC PRESSURE LINE LOCATED IN RT ENGINE PYLON AREA FRACTURED AND LEAKING IN AREA OF RINGLOK SWAGE ON UPPER END OF THE LINE.SDR CA040209006Connector · failed(CAN) DURING TROUBLESHOOTING FOR GROUND POWER SNAG, NOTICED THAT 5A CURRRENT LIMITER FOR HE GROUND POWER ENERGIZATION CIRCUIT WAS BLOWN. IT SHOULD BE NOTED THAT P109A20 WAS NOT PINNED TO X AT P309, AS WAS INDICATED BY THE WIRE DIAGRAMS FOR S/N 31-102. ACFT WIRSDR JGV2004F00000Bracket · brokenAFTER ENGINE REINSTALLATION, DURING ENGINE START, NO ROTATION WAS OBSERVED ON THE LT ENGINE. FOUND STARTER/GENERATOR WIRE GROUNDING BRACKET NO LONGER ATTACHED TO THE FUSELAGE SKIN. THE BRACKET HAD OVERHEATED AND MELTED A HOLE IN THE FUSELAGE SKIN, APPROXIMASDR UO22003F00011Shaft · unserviceableENGINE WAS INSPECTED DUE TO BAD SOAP. DURING INSPECTION OF FAN GEARBOX AREA 1 EA PLANETARY GEARSHAFT WAS FOUND SHEARED THROUGH AT LARGE BEARING. NO OTHER PARTS WERE EFFECTED.SDR CA031125001Wire · broken(CAN) IN APPROACH FLIGHT CREW CANNOT EXTEND THE GEAR NORMALLY. EMERGENCY BLOW DOWN SYSTEM ACTIVATED(EMERGENCY EXTENSION). MAINTENANCE FOUND WIRE TO DIODE CR105(LOCATED ON RT INSTRUMENT PANEL NEAR EMERGENCY BATTERY SWITCH) BROKEN OFF. WIRE RECONNECTED TO DIODSDR CA031126010Controller · malfunctioned(CAN) IN CRUISE AT AN ALTITUDE IN EXCESS OF FL 40 AFTER ALTITUDE CHANGES DOWN AND UP IN EXCESS OF 1000 FEET THE PRESSURIZATION CONTROLLER FAILED TO MAINTAIN CABIN PRESSURIZATION. AN EMERGENCY DESCENT WAS INITIATED AND PASSENGER OXYGEN MASKS DEPLOYED. THE PRESDR CA030924006Shutoff Valve · failed(CAN) WHEN LT ENGINE FUEL SHUTOFF VALVE WAS SELECTED CLOSED AND AIRFRAME POWER WAS SELECTED OFF, NOISE WAS HEARD COMING FROM THE VALVE. IT WAS DISCOVERED THAT THECURRENT WAS NOT CUT OFF WHEN THE VALVE WASCLOSED.REPLACED SHUTOFF VALVE.SDR BSY2003F00023Engine · malfunctionedAFTER DEPARTING CMH, LT ENGINE OIL PRESSURE ROLLED BACK TO 18 PSI AND STAYED THERE. SHUT ENGINE DOWN, JETTISON FUEL AND LANDED BACK IN CMH. RESTARTED ENGINE, OIL PRESSURE RETURNED TO NORMAL. RESTARTED SEVERAL TIMES, ALL OK. FLEW TO HOME BASE, NO PROBLEMS.
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