Pratt & Whitney JFTD12A-5A
Service difficulty reports · 32
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 = 'JFTD12A5A' 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 = 'JFTD12A5A' 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 JYDR20201013282Attach Bolt · brokenPILOTS SUDDENLY FELT A VIBRATION AND HEARD A HOWLING NOISE. THEY RETURNED TO THE LANDING SITE AND SHUT DOWN. AT INSPECTION, MAINTENANCE FOUND 1 OF 3 NAS628-15 BOLT BROKEN IN HALF ON THE NR 2 HIGH SPEED SHAFT ON THE FORWARD END, WHERE IT ATTACHES TO THE FREE SDR JYDR20201008218Engine · overtempAIRCRAFT WAS ON SHORT FINAL AT 50 FT AGL WHEN NR 1 ENGINE LOW SPEED CHIME CAME ON. PILOT NOTED DECREASING N1 RPM WITH RISING T% (ROLLBACK). PROPER ENGINE IDENTIFIED AND SHUT DOWN. RECORDING T5 INDICATOR CHECKED AND FOUND ENGINE HAD REACHED 784C FOR 4 SECONDSDR JYDR20180713190Disc · crackedDURING INSPECTION IAW AD 97-02-13 USING AMOC LETTER. 6 CRACKS WERE FOUND AT THE TIE BOLT THROUGH HOLES. CRACKS WERE FOUND WITH BOTH FPI AND EDDY CURRENT. AD STATES THAT DISK IS TO BE INSPECTED AT OR BEFORE 3000 HOURS TT AND 1500 HOURS THEREAFTER. THIS DISK HASDR JYDR20160422098Bearing Race · crackedFOUND HORIZONTAL HINGE PIN INNER BEARING RACE CRACKED DURING REPAIR. MRH HAD 292.3 HRS. REMAINING TO O/H. MFG HAS BEEN INFORMED.SDR CA150511015Solenoid · defective(CAN) UNCOMMANDED INADVERTENT RELEASE OF LOWER HOOKS.SDR JYDR2013110800239Servo · wornDURING A SCHEDULED MAIN GEAR BOX CHANGE, THE LT LATERAL PRIMARY SERVO WAS FOUND TO HAVE A SEVERELY WORN BOLT AND BUSHING AT THE LOWER PIVIT FOLLOW UP ARM. SERVO WAS REMOVED FROM SERVICE AND RETURNED TO THE REPAIR STATION FOR INVESTIGATION. THE MFG IS PARTISIPSDR JYDR2013110801239Servo · wornDURING A SCHEDULED MAIN GEAR BOX CHANGE, THE LT LATERAL PRIMARY SERVO WAS FOUND TO HAVE A SEVERELY WORN BOLT AND BUSHING AT THE LOWER PIVIT FOLLOW UP ARM. SERVO WAS REMOVED FROM SERVICE AND RETURNED TO THE REPAIR STATION FOR INVESTIGATION. THE MFG IS PARTICIPSDR 2009FA0000042Nut · crackedDURING THE DISASSEMBLY OF THE MRH, 1 NUT WAS FOUND CRACKED. THE NUT IS CRACKED THROUGH ON ONE SIDE AND RUNS THE LENGTH OF THE NUT. THE UNT IS ONE OF (2) THAT SECURES THE DAMPER BRACKET TO THE MRH LOWER PLATE. THE CAUSE OF THE CRACK IS BEING INVESTIGATED. (SDR 2006FA0000951Axle · cracked(REF NR: MDR06-091) UPON DISASSEMBLY, AXLE WAS FOUND TO BE CRACKED AND RUNS AROUND THE CIRCUMFERENCE. THE TRACTURE APPEARS TO ROIGINATE IN THE WELD ON THE CENTER OF THE AXLE SHAFT. THE AXLE WAS FRACTURED UNDER THE SOCKET, PN 6425-50202-101, AS EVIDENCED BY ASDR JYD2006F00000Bearing · spalledBEARING OUTER RACE SPALLED AND CRACKED. SPALLING AND CRACK ARE ON NR1 BEARING ROW ONLY. CRACK IS APPROXIMATELY 2.25 INCHES LONG. PROBABLE CAUSE IS UNKNOWN. THE BEARING RACE WILL BE ANALYZED TO DETERMINE THE CAUSE. THERE ARE NO RECOMMENDATIONS TO PREVENT RESDR 2005FA0000820Turbine Blades · brokenCOMPRESSOR ASSY WAS REMOVED FROM AC FOR FAILING VIBRATION ANALYSIS. DURING THE PRELIMINARY INSPECTION IT WAS NOTED THAT A PIECE OF 2ND STAGE TURBINE BLADE OUTER SHROUD KNIFE EDGE WAS MISSING. THE MISSING PIECE WAS APPROXIMATELY .500 INCH LONG AND FROM THE AFSDR 2005FA0000818Duct · crackedNR 1 ENGINE REMOVED FROM ACFT, DUE TO 5 INCH AXIAL BULGE AT OUTER TURBINE CASE, 2-3 OCLOCK POSITION WITH APPROX .5625 INCH HORIZONTAL CRACK RUNNING THROUGH CENTER MOST PORTION OF THE BULGED AREA. UPON REMOVAL OF ENGINE HOT SECTION, TURBINE OUTLET DUCT FOUNSDR 2005FA0000817Thrust Washer · wornMAIN GEAR BOX, SN A6051 REMOVED FOR BRASS CONTAMINATION. UPON DISASSEMBLY DISCOVERED BRASS MATERIAL WAS FROM SECOND STAGE PLANETARY THRUST WASHERS. 34 OUT OF 36 THRUST WASHERS WORN ON ID BEYOND MAX SERVICEABLE LIMITS. 18 EA BEARINGS HAD SHARP EDGES INNER RACSDR 2005FA0000340Bearing Race · cracked(MDR05-072) THE MRH SLEEVE AND SPINDLE ASSY DEVELOPED AN OIL LEAK WHILE ON AIRCRAFT AND WAS NOTED DURING ROUTE INSPECTION. UPON REMOVAL AND REPLACEMENT WITH A SERVICEABLE ASSY, A CRAK WAS FOUND ON THE INNER RACE. VISUAL INSPECTION SHOWS WEAR AND CORROSION TYSDR JYDRMDR04069Housing · crackedMGB WAS REMOVED FOR MAIN SHAFT REPLACEMENT AND OVERHAUL. AFTER DISASSEMBLY OF GEAR BOX, THE UPPER HOUSING WAS LOCALLY BLENDED, ETCHED UNDER THE INPUTS AND INSPECTED BY FPI. THE HOUSING WAS REJECTED FOR CRACKS ON THE LT AND RT SIDE. POOR REWELD QUALITY OF CASDR MDR03032Bleed Valve · obstructedNR 1 ENG OIL PRESS WAS INDICATING LOWER THAN NR 2 ENG. PRESS INDICATED 45 PSI. ADJUSTED PRESS VALVE TO INCREASE CHECK AT NEXT FLT. NR 1 ENG WAS STARTED, INDICATED NML GROUND IDLE. ACCELERATING TO 70 PERCENT N2, OIL PRESS DROPPED OFF, CAUTION LIGHT ILLUM, PSDR 2004F00286Duct · crackedDURING DISASSEMBLY OF N1 SECTION, IT WAS NOTICED THAT THERE WAS A LARGE PIECE OF MATERIAL WEDGED IN BETWEEN TWO 1ST STAGE BLADES. UPON FURTHER DISASSEMBLY/INVESTIGATION THE OUTLET DUCT ASSEMBLY WAS FOUND TO BE MISSING A LARGE SECTION OF THE OUTER DUCT APPROXISDR MDR03039Attach Angle · crackedDURING A SCHEDULED INSPECTION, LT ATTACH ANGLE, PN 6420-66340-105, WAS FOUND CRACKED AT STA 767.8 LBL 5.5, WL 177.1. THE CRACK ORIGINATED AT THE BOTTOM HUCK FASTENER AND TRAVELED DOWN TO THE EDGE OF THE ANGLE. THESE ANGLES ATTACH THE INTERCOSTALS TO THE CANTSDR 98ZZZX2255Blade · fracturedON 4-24-98, AIRCRAFT WAS ON A FIRE FIGHTING MISSION. DURING CLIMB-OUT, A LOUD 'BANG' SOUND OCCURRED, FOLLOWED BY A LEFT YAW. THE LOAD OF WATER WAS JETTISONED AND PILOTS PUSHED MAXIMUM BEEP ON BOTH ENGINES. THE NR 1 ENG WAS CARRYING THE LOAD. THE NR 2 ENG RSDR 98ZZZX68Case · crackedWHILE INSTALLED, AFT FLANGE OF CASE SN 225 FRACTURED 360 DEGREES WITHIN THE FLANGE WELD JOINT. FRACTURING OF AFT FLANGE ASSY ELIMINATED THE AFT MOUNT FROM ENG SUPPORT. ENG FREE TO MOVE VERTICALLY, LATERALLY, AND FORE AND AFT, UNRESTRAINED BY AFT MOUNT. THISSDR 97ZZZX4464Bearing · failedBEARING REMOVED FROM ENG DURING OVERHAUL WITH TT OF 1691.6 HRS. DURING OVERHAUL, BEARING WAS INSPECTED AND 2 UNUSUAL CONDITIONS FOUND: BALLS EXHIBITED SEVERE SCRATCHES AND RETAINER SHOWED SMEARED SILVER PLATING IN THE BALL RETENTION AREA. AFTER ANALYSIS, RSDR 970326Air Seal · crackedON MARCH 13, 1997, COMPRESSOR ASSY S/N 677775 WAS SCHEDULED FOR AN OVERHAUL, W.O. NR 25419. TEAR DOWN WAS COMPLETED ON MARCH 14, 1997, WITH NO PROBLEMS. THE AIR SEAL ON THE REAR OF THE 7TH STAGE DISK WAS NOTED TO HAVE A CRACK COMPLETELY THROUGH IT AND ANOTHSDR 97ZZZX853Bevel Gearshaft · crackedFOUND CRACK INDICATIONS DURING FMPI INSIDE SQUARE DRIVE OF GEARSHAFT. INDICATORS APPEAR SHARP. A WELL DEFINED CRACK-TYPE INDICATION IS SEEN INSIDE CORNERS OF SHAFT. OUTSIDE DIAMETER SHOWS BROAD FUZZY INDICATIONS THAT CORRESPOND DIRECTLY TO INSIDE INDICATIOSDR 97ZZZX854Bevel Gearshaft · crackedFOUND CRACK INDICATIONS DURING FMPI INSIDE SQUARE DRIVE OF GEARSHAFT. INDICATORS APPEAR SHARP. A WELL DEFINED CRACK-TYPE INDICATION IS SEEN INSIDE CORNERS OF SHAFT. OUTSIDE DIAMETER SHOWS BROAD FUZZY INDICATIONS THAT CORRESPOND DIRECTLY TO INSIDE INDICATIOSDR 97ZZZX855Bevel Gearshaft · crackedFOUND CRACK INDICATIONS DURING FMPI INSIDE SQUARE DRIVE OF GEARSHAFT. INDICATORS APPEAR SHARP. A WELL DEFINED CRACK-TYPE INDICATION IS SEEN INSIDE CORNERS OF SHAFT. OUTSIDE DIAMETER SHOWS BROAD FUZZY INDICATIONS THAT CORRESPOND DIRECTLY TO INSIDE INDICATIOSDR 97ZZZX856Bevel Gearshaft · crackedFOUND CRACK INDICATIONS DURING FMPI INSIDE SQUARE DRIVE OF GEARSHAFT. INDICATORS APPEAR SHARP. A WELL DEFINED CRACK-TYPE INDICATION IS SEEN INSIDE CORNERS OF SHAFT. OUTSIDE DIAMETER SHOWS BROAD FUZZY INDICATIONS THAT CORRESPOND DIRECTLY TO INSIDE INDICATIOSDR 96ZZZX5190Tablock · missingTABLOCK FOUND MISSING AT POST-FLIGHT INSPECTION ON 6-25-96. THE LAST OVERHAUL WAS PERFORMED BY SABRELINER. WHEN INSPECTING THE COMPRESSOR THROUGH THE INLET, CONTACT OF 3RD STAGE BLADE NOTED ON FACE OF 4TH STAGE STATOR NEAR CENTERLINE OF ENGINE (ROOT END OF BSDR 96ZZZX5191Tablock · missingTABLOCK FOUND MISSING AT PRE-FLIGHT INSPECTION CONDUCTED ON 4-26-96. THE LAST OVERHAUL PERFORMED BY EAC ON 8-4-94. WHEN INSPECTING THE COMPRESSOR THROUGH THE INLET, CONTACT OF 3RD STAGE BLADE WAS NOTED ON FACE OF 4TH STAGE STATOR NEAR CENTERLINE OF ENGINE (RSDR 96ZZZX5313Tablock · missingTABLOCK FOUND MISSING AT HIDDEN DAMAGE INSPECTION CONDUCTED ON COMPRESSOR BEING PROCESSED INTO THE REPAIR STATION ON 1-26-96. THE LAST OVERHAUL WAS PERFORMED BY EAC ON 8-4-94. WHEN INSPECTING THE COMPRESSOR THROUGH THE INLET, CONTACT OF 3RD STAGE BLADE NOTEDSDR 96ZZZX5192Tablock · missingENGINE FAILED INTERNALLY AT FIRST LIFT-OFF OF THE DAY. TABLOCK FOUND MISSING 12-2-95. THE LAST OVERHAUL PERFORMED BY EAC ON 1-6-94. WHEN INSPECTING COMPRESSOR THROUGH INLET, CONTACT OF 3RD STAGE BLADE NOTED ON FACE OF 4TH STAGE STATOR NEAR CENTERLINE OF ENGSDR 96ZZZX5193Tablock · missingENGINE REMOVED FOR HSI. TABLOCK FOUND MISSING AT HIDDEN DAMAGE INSPECTION CONDUCTED ON COMPRESSOR BEING INDUCTED IN REPAIR STATION ON 8-22-95. THE LAST OVERHAUL PERFORMED BY EAC ON 10-7-94. WHEN INSPECTING COMPRESSOR THROUGH INLET, CONTACT OF 3RD STAGE BLADSDR 95ZZZX2154Disk · pittedP AND W SB 1508, REQUIRES ALL ENGINES TO BE COMPLETELY DISASSEMBLED TO CONDUCT A CORROSION INSPECTION EVERY 7 YEARS. SERIOUS CORROSION PITTING FOUND WHEN CONVERTING MILITARY T73-P-1 OR T73-P-700 ENGINES TO COML. USE. DISK FAILURE CAN OCCUR IF CORROSION INSPE
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