Garrett TFE731 series
Service difficulty reports · 742
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 = 'TFE731' 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 = 'TFE731' 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 ZH92005F00000Switch · shortedWHILE RETURNING TO AIRPORT, THE COPILOTS ALTIMETER BREAKER POPPED, WHICH IN TURN DISABLED THE NR2 ALTIMETER/ADDU. THE AC LANDED 10 MINUTES LATER WITHOUT INCIDENT AND THE NR2 ALTIMETER FAILURE WAS REPORTED TO MAINTENANCE. WHEN THIS PROBLEM WAS INVESTIGATED ITSDR 2005FA0000462Bolt · brokenA BROKEN BOLT WAS NOTICED DURING A TIRE PRESSURE CHECK. THE WHEEL COVER WAS REMOVED TO INVESTIGATE. ALL TEN BOLTS WERE NDT`D BY PAG PARTICLE INSP AND 3 OTHER BOLTS WERE FOUND CRACKED. PART CYCLES (LANDINGS) SINCE O/H IS 176 CSO. (K)SDR DJFA2005064Warning Light · false indicationCREW REPORTED, AFTER TAKEOFF, BAGGAGE FIRE WARNING LIGHT BEGAN TO FLASH APPROX 3 TO 5 TIMES, THEN QUIT. 2 MIN LATER LIGHT BEGAN TO FLASH AGAIN, THEN QUIT. AFTER EACH SERIES OF FIRE LIGHTS, AN OPS CHECK OF CIRCUITS WAS MADE BY CREW. OPS CHECKS WERE NORMAL. AFSDR MXI2005F00002Motor · failedTHE COCKPIT FAN MOTOR FAILED AND CAUSED SMOKE TO COME OUT OF THE OVERHEAD AIR VENTS. AFTER REPLACEMENT IT WAS NOTED THE FAN MOTOR WAS VERY HARD TO TURN. THERE IS NO TIME CHANGE FOR THIS MOTOR LISTED IN CHAPTER 5. (EA21200504524) (K)SDR 2005FA0000226Power Supply · failedCREW HAD POWER ON AIRCRAFT AND NOTICED AN ELECTRICAL BURNING SMELL COMING FROM THE CABIN. AFTER INVESTIGATING THEY FOUND THE CABIN INDIRECT LIGHTING CIRCUIT BREAKER POPPED. THE MAINTENANCE FACILITY TROUBLESHOT THE PROBLEM TO A POWER SUPPLY THAT HAD BURNED UPSDR 2005FA0000197Throttle Cable · damagedAFTER TAKEOFF, THROTTLE WOULD NOT COME BACK. THROTTLE HAD TO BE FORCEABLY PULLED BACK OUT OF TAKEOFF SETTING. CABLE WAS FOUND BAD. (GL11200507568) (K)SDR CA050210001Control Unit · failed(CAN) WHILE TAXIING THE AIRCRAFT. (NORM BRAKE FAIL) MESSAGE CAME ON. EMERGENCY BRAKE USED ON THE WAY BACK TO THE MAINTENANCE FACILITY. BRAKE CONTOL UNIT REPLACED, AIRCRAFT RETURN TO SERVICE.SDR 2005FA0000124Housing · failedIN FLIGHT, PILOT NOTICED FLUCTUATING OIL PRESSURE AND TORQUE. PRECAUTIONARY LANDING MADE, FOLLOWING TROUBLESHOOTING ENGINE WAS DISASSEMBLIED GEARBOX SCAVENGE OIL PUMP WAS CRACKED. APPROXIMATELY 7 HOURS PRIOR, THE NR 8 STAINLESS OIL SCAV. LINE CRACKED. APPROSDR N382005F00001Fire Loop · defectiveLT ENGINE FIRE T-HANDLE WAS FLASHING. NO OTHER INDICATIONS OF FIRE. PERFORMED RESISTANCE CHECK OF LT ENGINE FIRE LOOPS AND FOUND CENTER CONDUCTOR RESISTANCE OF ACCESSORY GB LOOP READING HIGH. REPLACED LT ENGINE ACCESSORY GB LOOP. FUNCTIONAL CHECK AND GROUNSDR UG82005F00003Spacer · missingLANDING GEAR UNLOCK LIGHT WOULD NOT EXTINGUISH WHEN RETRACTING. FOUND LT MAIN GEAR UPLOCK HOOK ACTUATOR MOUNTING ATTACH BOLT SPACER, PN 6217107-3 PREVIOUSLY NOT INSTALLED. REF. CE-650 IPC 32-30-00-02, ITEM 82. THIS CONDITION ALLOWED HORIZONTAL SHIFTING OF USDR 2005FA0000217Control Cable · failedPRIMARY FLIGHT CONTROL CABLES ARE FAILING INSP, DUE TO WEAR ON CONTROL CABLE FAIRLEADS IN FUSELAGE AND EMPANNAGE. DETAILED INSP IS PERFORMED AT 4800 HRS. FOLLOWING CABLES FAILE AT 1780.3 HRS. FUSELAGE AILERON CABLES, RUDDER CABLES, ELEVATOR CABLES. CAUSE ISDR 2005FA0000222Control Cable · wornAILERON, ELEVATOR, AND RUDDER SYSTEMS PRIMARY CONTROL CABLES ARE DUE INSPECTION AT 600 HOURS IAW MM, AS A PORTION OF PHASE B REQUIREMENTS. ALIERON, ELEVATOR AND RUDDER SYSTEMS PRIMARY CONTROL CABLES ARE DUE REMOVAL AND DETAILED INSPECTION AT 4,800 HOURS IAW MSDR AJC2005F00000Uplock Switch · out of adjustAC DEPARTED, ENROUTE. AFTER RETRACTING THE GEAR ON CLIMB OUT, THE CREW NOTED THE RED UNSAFE LIGHT IN THE LANDING GEAR HANDLE WAS ILLUMINATED. THE CREW EXTENDED THE GEAR AND GOT THREE GREEN DOWN AND LOCKED LIGHTS. THE AIRCRAFT RETURNED AND LANDED SAFELY WITHSDR 2005FA0000210Anti-Ice Valve · failedDURING TROUBLESHOOTING FOR (HIGHER THAN NORMAL) GASPER AIR TEMPERATURE, FOUND THE TURBOFAN TURBINE ANIT-ICE VALVE DISASSEMBLED BETWEEN THE VALVE AND THE MOTOR. NO DAMAGE CAN BE SEEN ON THE VALVE. THE 2 THREADED PARTS WERE FOUND UNTHREADED. THE DYSFUNCTIONALSDR 2005FA0000016Fitting · damagedFOLLOWING DAMAGE WAS FOUND WHILE LT IB SLAT (PN F50B133B8, SN 133000 WAS AT THIS FACILITY FOR REPAIR. MILLED FITTING, (PN F50B133014) IS ATTACH POINT FOR NR 4 (OB) RAIL. SIX FASTENERS WERE IMPROPERLY INSTALLED THROUGH INNER SKIN OF SLAT. FOUR BLIND FASTENESDR JV2R200400001Computer · failedDURING MAINTENANCE ENGINE RUN, THE LT COMPUTER FAIL LIGHT ILLUMINATED AT 92 PERCENT AND THE SYSTEM WENT TO MANUAL. THE ENGINE OPERATOR RESET THE SYSTEM PER MANUAL AND PERFORMED A SECOND ENGINE RUN. LEFT COMPUTER FAIL LIGHT ILLUMINATED AT IDLE ON THE SECOND ESDR JV2R200400003Eec · defectiveOPERATOR REPORTED LEFT DIGITAL ELECTRONIC ENGINE CONTROL COMPUTER FAIL LIGHT ILLUMINATED DURING CLIMB PUTTING THE SYSTEM IN MANUAL. THE OPERATOR REPORTED ATTEMPTING RESET ONE TIME, SYSTEM FAILED AGAIN AND OPERATOR RETURNED TO BASE. HONEYWELL WAS CONTACTED.SDR 2005FA0000096Bolt · corrodedBOLT SHEARED AT THREADS DURING REMOVAL. SIGNS OF INTERNAL CORROSION ON BOLT.SDR 2005FA0001254Transducer · failedNORMAL APPROACH WITH A GOOD ANTI-SKID CK, AC WENT OFF END OF 6000 FT WET RUNWAY. INSP OF TIRE MARKS AFTER ACCIDENT, NO EVID OF BRAKING ACTION. NO CAUSE OF FAILURE. ON TEST FLT AFTER REPAIR, RT ANTI-SKID WOULD NOT TEST IN AIR. ANTI-SKID WAS LEFT ON LANDING,SDR KNI2005F00000Line · failedCREW REPORTED THAT LANDIND GEAR EXTENSION TOOK LONGER THAN NORMAL TO EXTEND. WHEN DOWN AND LOCKED WAS ACHIEVED, CREW NOTICED COMPLETE LOSS OF HYDRAULIC PRESSURE. NORMAL LANDING WAS MADE USING EMERGENCY BRAKES. JACKED AIRCRAFT AND PERFORMED GEAR SWINGS. FOUSDR N382005F00002Hydraulic System · lowWHILE ARRIVING, NOTICED LOW HYDRAULIC QUANTITY. CREW DIVERTED, DUE TO INCREASED RUNWAY LENGTH. (EA25200504599)SDR 2005FA0001121Static Port · cloggedAIRSPEED DISPARITY DURING IFR APPROACH, WATER IN LT STATIC PORT. FIRST TIME OCCURRENCE W/ THIS AC OUTSIDE DURING RAINSTORM LASTING 3 HOURS. STATIC DRAINS DRY, WATER ACCUMULATED JUST INSIDE STATIC PORT. DID NOT KNOW WHY STATIC PORT HEATER DID NOT REMOVE THE SDR XNOA1207Controller · uncontrollableNR 2 AIRCRAFT PRESSURIZATION SYSTEM IS UNCONTROLABLE BOTH AUTO AND MANUAL MODE. (STATUS:ORIG/OPEN)SDR 2005FA0000228Wire Harness · chafedRT ENGINE FAIL CAS AMBER LIGHT ILLUMINATED AND RT ENGINE FIRE RED WARNING LIGHT ILLUMINATED IN FLIGHT ON FINAL APPROACH TO PNE. PROBLEM: SEVERAL WIRES WERE CHAFED THOUGH ON THE P133 WIRING HARNESS. FOUND CHAFED ON FRAME NEAR THE TAIL CONE RELAY PANEL. REPAISDR 2005FA0001127Light · damagedTHE AIRCRAFT WAS ON MFG SPI RAMP. THE CABIN LED LIGHT STRIP IN AFT CABIN BECAME WARM CAUSING HEAT DAMAGE TO THE LIGHT STRIP. THE LIGHT BOARD WAS SENT TO EMTEQ LIGHTING FOR EVALUATION. EMTEQ DETERMINED THE CAUSE OF THE FAILURE TO BE ELECTRO STATIC DISCHARGE SDR 2005FA0000206Line · chafed2 HYDRAULIC PIPES WERE CHAFING AGAINST EACH OTHER IN THE RT ENGINE PYLON. THE 2 PIPES WERE REMOVED AND REPLACED, ENSURING NO CONTACT BETWEEN THEM. (GL19200501324) (K) (NR1 OF 2 )SDR 2005FA0000227Pipe · chafed2 HYDRAULIC PIPES WERE CHAFING AGAINST EACH OTHER IN THE RT ENGINE PYLON. THE 2 PIPES WERE REMOVED AND REPLACED ENSURING NO CONTACT BETWEEN THEM. (GL19200501324). (K) (NR 2 OF 2)SDR QFY2004F00000Link · inadequateLT FRONT WING LINK NOT SAFETYED FROM FACTORY. UPON PERFORMING WING LINK INSPECTION TO RID AIRCRAFT OF CLUNKING NOISE, FOUND LINK NOT SAFETYED. THE BOLT WAS STILL TIGHT AT THIS POINT, BUT THE WING LINK INSPECTION WAS BEING ACCOMPLISHED 3 YEARS EARLIER AS WELLSDR WVE2004F00022Window · crackedDURING ROUTINE MAINTENANCE THE CABIN WINDOW IN THE EMERGENCY EXIT WAS FOUND CRACKED BEYOND LIMITS. NEW WINDOW SN 5754 RECEIVED FOR REPLACEMENT, INSTALLED IAW MM, SEALANT INTRUDED BETWEEN THE WINDOW PLIES AT THREE HI-LOCKS. WINDOW AGAIN WAS REPLACED. REPLACESDR 2004FA0000700Sign · burnedSMOKE WAS OBSERVED IN THE CABIN AFTER START OF TAXI TO ACTIVE RUNWAY. THE CREW SHUT DOWN ENGINES, SHUTOFF ALL POWER AND DISCONNECTED BATTERIES. FOUND SOURCE OF SMOKE TO BE FROM A NO SMOKING/SEATBELT SIGN LOCATED IN THE LT SIDE OF CABIN AT FRAME 20. THE AIRCSDR 2005FA0000230Sign · burnedSMOKE WAS OBSERVED IN THE CABIN AFTER START OF TAXI TO ACTIVE RUNWAY, THE CREW SHUT DOWN ENGINES, SHUT OFF ALL POWER AND DISCONNECTED BATTERY. FOUND SOURCE OF SMOKE TO BE FROM A NO SMOKING/SEATBELT SIGN LOCATED IN THE LT SIDE OF CABIN AT FRAME 20. THE AIRCRASDR 2004FA0000892Trunnion · crackedDURING A 1200 HOUR SCHEDULED INSPECTION, THE OUTER STRUT BODY OF THE NOSE LANDING GEAR UPPER TRUNNION WAS FOUND TO HAVE A CRACK IN THE OUTER BARREL STARTING FROM THE UPPER THREAD LOCK BORE EXTENDING DOWN 5.75 INCHES.SDR 2004FA0000757Pressure Switch · leakingAPPROX 5-10 MINUTES AFTER TAKEOFF, PILOTS NOTED NR 2 HYDRAULIC SYSTEM LOSING FLUID. SYSTEM CONTINUED TO LOSE FLUID SO NR 2 ENGINE WAS SHUT DOWN AND AIRCRAFT LANDED. MAINTENANCE FOUND NR 2 HYDRAULIC SYSTEM PRESSURE SWITCH LEAKING. INSTALLED NEW PRESSURE SWITSDR PRI2004F00000Pump · inoperativeNR 2 ENGINE DRIVEN HYDRAULIC PUMP FAILED IN FLIGHT. UPON REMOVAL OF FAILED PUMP. INSPECTION FOUND ONE PLUG O-RING HANGING OUT ALLOWING FLUID TO ESCAPE. (WP19200407082)SDR FE62004F00000Software · malfunctionedTHE SANDEL TAWS/RMI SHOWS SIGNIFICANT BEARING ERRORS ON HEADINGS GREATER THAT 359 DEGREES OR LESS THAN 0 DEGREES. THIS PROBLEM WAS DISCOVERED IN FLIGHT AND VALIDATED THROUGH GROUND TEST OF NUMEROUS UNITS. PROBABLE CAUSE OF MALFUNCTION IS THE SOFTWARE. THE SSDR FE62004F00001Indicator · inaccurateTHE SANDEL TAWS/RMI SHOWS SIGNIFICANT BEARING ERRORS ON HEADINGS GREATER THAN 350 DEGREES OR LESS THAN 0 DEGREE. THIS PROBLEM WAS DISCOVERED IN FLIGHT AND VALIDATED THROUGH GROUND TESTING OF NUMEROUS UNITS. PROBABLE CAUSE OF MALFUNCTION IS SOFTWARE. THE ST3SDR 2004FA0000607Nut · splitWHILE CLEANING AIRCRAFT DISCOVERED NR 4 MAIN WHEEL 1 EACH TIE-BOLT NUT SPLIT IN HALF. REPLACED ALL WHEEL TIE BOLTS P/N: EWB22-5-16 AND NUTS P/N: FN22A524 WITH NEW PARTS. TIME ON PART SINCE REPAIR UNKNOWN.SDR CA040715004Battery · inoperativeDURING ENGINE START WITH GROUND POWER UNIT AND AVIONICS ON, ALL 4 DISPLAY UNITS WENT BLACK AND THEN LIT UP AGAIN AFTER ENGINE STARTED. MAINTENANCE DISCOVERED WITH A CAPACITY CHECK ON THE EMERGENCY BATTERY THAT 1 CELL HAD FAILED WHICH CAUSED THE VOLTAGE TO DROSDR 2005FA0000229Tube · leakingTUBE LEAKING THRU SEVERAL PIN HOLES, SUSPECT INTERNAL CORROSION. SLOW EVACUATION OF HYDRAULIC FLUID PREVENTED ACTUATION OF HYDRAULIC FUSE. TAKEOFF WITH GEAR (UP) SELECTION REVEALED SLOW ACTUATION AND A RETURN TO BASE. GEAR (DOWN) SLOW BUT CAME DOWN AND LOCKSDR MQK2004F00000Line · misinstalledNR 1, LT EMERGENCY BRAKE RIGID LINE FROM OUTER SHUTTLE VALVE TO INNER SHUTTLE VALVE STRIKING LT MAIN LANDING GEAR STRUT HOUSING WHEN STRUT IS COMPRESSED. (DURING LANDING, NOT WHILE AC IS PARKED) LINE IS MISROUTED/ NOT PROPERLY BENT. NO VISIBLE DAMAGE DONE TSDR JGV2004F00007Stud · shortedACCOMPLISHED A MODIFICATION TO THE POWER DISTRIBUTION PANEL TO SUPPORT AN AVIONICS MOD. THE SYSTEM WAS CHECKED OK AND INSPECTED THE TERMINAL STUD FOR SECURITY. THE STUD WAS TIGHT AND THE CONNECTION WAS SECURE. AFTER DELIVERY THE AC HAD ELECTRICAL PROBLEMS. SDR 2004FA0000570Shutoff Valve · leakingTHIS VALVE INSTALLED PREVIOUSLY TO COMPLY WITH REQURIEMENTS OF AD 2003-11-07. FOUND DURING INSPECTION THAT VALVE WILL NOT SHUT OFF OXYGEN FLOW WHEN TURNED TO CLOSED. REPLACED VALVE WITH NEW PN 27550-3, THIS CORRECTED PROBLEM.SDR AJC2004F00002Position Switch · damagedDURING TAKEOFF, ENROUTE, THE LANDING GEAR HORN SOUNDED WHEN GEAR LEVER WAS PLACED IN UP POSITION, BOTH WITH FLAPS IN 15 DEGREE AND 0 DEGREE POSITION. CREW PLACED GEAR LEVER IN DOWN POSITION AND HORN SILENCED. CREW CIRCLED AND BURNED OFF FUEL AND RETURNED TO SDR UO22004F00006Lever · misinstalledPARKING BRAKE HANDLE WOULD NOT GO INTO THE FIRST DETENT WHICH ALLOWS USE OF THE EMERGENCY BRAKE SYSTEM AND USE OF THE PARKING BRAKE. ACCESSED PARKING BRAKE SYSTEM IN COCKPIT AND DETERMINED THAT THE SPLINED LEVER ASSEMBLY HAD COME OFF THE SPLINED SHAFT THAT GOSDR QU22004F00000Inlet · cracked(REGISTRATION NR CHANGE FROM 888MF). DURING INSPECTION, A FLUSH PATCH APPROXIMATELY .5 INCH BY 2 INCHES WAS NOTED IN THE ENGINE INLET. THIS IS NOT AN APPROVED REPAIR. MFG REQUIREMENTS ARE TO RESKIN THE INNER INLET.SDR AUS20040416Actuator · leaking(AUS) LT WING SPOILER ACTUATOR PRESSURE SWIVEL FAILED. LOSS OFHYDRAULIC FLUID.SDR 2004FA0000433Valve · failedDURING CLIMBOUT FROM MLI, THE RT EMERGENCY PRESSURIZATION VALVE OPENED ALLOWING HIGH PRESSURE BLEED AIR TO ENTER THE CABIN. THIS CAUSED THE CABIN TEMP TO RISE AND A LOUD AUDIBLE RUSH OF AIR TO BE HEARD IN THE CABIN. THE FLIGHT CREW ELECTED TO RETURN TO POINTSDR BAQA094408Brake Assy · wornBRAKE ASSY WORN TO LIMITS. REPLACED WITH SERVICABLE UNIT. 05/06/2004SDR BAQA094409Brake Assy · wornBRAKE ASSY WORN TO LIMITS. REPLACED WITH SERVICABLE UNIT. 05/06/2004SDR BAQA094410Brake Assy · wornBRAKE ASSY WORN TO LIMITS. REPLACED WITH SERVICABLE UNIT. 05/06/2004
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