JASC 7250
Service difficulty reports · 3,625
Reports filed under 7250 · Turbine Section, newest first.
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 jasc_code = '7250' 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 jasc_code = '7250' 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 97UAL900187Turbine Vane · crackedDURING RIGHT ENGINE BORESCOPE, FOUND TWO HIGH PRESSURE TURBINE VANES WITH A V-TYPE CRACK. TOTAL CRACK LENGTH EXTENDS GREATER THAN .25 INCH ON EACH VANE. REPLACED RIGHT ENGINE FOR HEAVY MAINTENANCE VISIT.SDR NYBA972Turbine Assy · burnedTURBINE ASSY IS BURNED. REPLACEDSDR AU970311Engine · faulty(AUS) NO3 ENGINE VIBRATION WITH SPARKS FROM TAILPIPE - N2 SEIZED WHEN ENGINE SHUT DOWNSDR CA970319003Ct Disk · worn(CAN) DURING HSI THE CT DISK ASSEMBLY WAS FOUND RUBBING ON THE CT AIR SEAL. FURTHER INSPECTION FOUND THAT EIGHT BLADE ROOTS ON THE OPPOSITE SIDE OF THE DISK ALONG WITH THE DISK PLATFORM WERE GROOVED. THE DEPTHS OF THE GROOVES WERE TO AN UNACCEPTABLE LIMIT. THESDR AU970209Blade · separated(AUS) RH ENGINE FIRST STAGE POWER TURBINE BLADE SEPARATED - SECOND STAGE POWER TURBINE DAMAGED - METAL CONTAMINATION OF OIL SYSTEM - FAILURE WAS DUE TO LOW CYCLE FATIGUE COMBINED WITH CORROSION IN THE LIGHTENING CAVITYSDR 97ZZZX1646Gas Generator · corrosion holeWHILE TROUBLESHOOTING AN EXISTING PROBLEM WITH ONE ENGINE, THE DIFFUSER TUBES WERE FOUND TO HAVE HEAVY CORROSION WITH SEVERAL HOLES CORRODED THROUGH. SUBSEQUENT INSPECTION OF THE OTHER ENGINE RESULTED IN FINDING THE SAME PROBLEM. BOTH ENGINES WERE REMOVED ANSDR 97ZZZX1645Gas Generator · corrosion holeWHILE TROUBLESHOOTING AN EXISTING PROBLEM WITH ONE ENGINE, THE DIFFUSER TUBES WERE FOUND TO HAVE HEAVY CORROSION WITH SEVERAL HOLES CORRODED THROUGH. SUBSEQUENT INSPECTION OF THE OTHER ENGINE RESULTED IN FINDING THE SAME PROBLEM. BOTH ENGINES WERE REMOVED ANSDR HEEA979154Nozzle · crackedENGINE REMOVED DUE TO BROKEN STUD ON TURBINE MOUNT PAD. TURBINE DISASSEMBLED DUE TO HIGH VIBRATION ON TEST CELL. DISASSEMBLY INSPECTION REVEALED: CRACKED BEYOND SERVICEABLE LIMITS ON #1 NOZZLE VANES. INSTALLED A DALLAS AIRMOTIVE OVERHAULED #1 NOZZLE.SDR HEEA979153Nozzle · crackedENGINE REMOVED DUE TO HIGH OIL CONSUMPTION. UPON INSPECTION OF TURBINE PARTS NOTED: CRACKED AND BOWED BEYOND SERVICEABLE LIMITS ON #1 NOZZLE VANES. INSTALLED A NEW #1 NOZZLE.SDR HEEA979152Nozzle · crackedENGINE REMOVED DUE TO AFT T/M BORE OIL LEAK. TURBINE DISASSEMBLED DUE TO LOW POWER ON TEST CELL. UPON INSPECTION OF TURBINE PARTS NOTED: CRACKED AND BOWED BEYOND SERVICEABLE LIMITS ON #1 NOZZLE VANES. INSTALLED A NEW #1 NOZZLE.SDR AU970180Blade · separated(AUS) LH ENGINE NO3 BEARING SPALLED - 2ND STAGE TURBINE BLADE BROKEN CAUSING EXTENSIVE DAMAGE TO HOT END SECTION AND POWER TURBINE COMPONENTSSDR 97FDEA00123Turbine · failedON CLIMBOUT, THE NR 2 GENERATOR FELL OFF LINE. DURING THE DEPARTURE THE NR 2 ENGINE EGT WAS HIGH (NOT OVERTEMPED). WHEN PULLING THE THROTTLE BACK TO 80 PERCENT, N1 TO KEEP EGT AT 600 THE FUEL FLOW BECAME ERRATIC. NR 2 ENGINE THEN SHUTDOWN AS A PRECAUTION. SDR HEEA979139Wheel · defectiveTURBINE WHEEL DEFECTIVESDR HEEA979138Wheel · defectiveTURBINE REMOVED DUE TO METAL IN OIL AND HIGH CYCLED #1 AND #2 WHEELS. UPON INSPECTION OF TURBINE PARTS NOTED THE FOLLOWING: MINOR SULFIDATION ON 75% OF TRAILING EDGE OF WHEEL. SCRAPPED #1 WHEEL.SDR SIMA9700511Gas Generator · seizedOKC - FLT 3720 - AFTER TAKEOFF AT 200 FEET, CREW REPORTED A BANG OUT OF THE NR 2 ENGINE WITH AN OVERTEMP WARNING. CREW SHUT DOWN ENGINE AND PULLED FIRE T-HANDLE, TEMP WARNING WENT OUT, SO CREW DID NOT DISCHARGE BOTTLES. CAPTAIN DECLARED AN EMERGENCY AND RETUSDR 97ZZZX1384Bellows Seal · leakingCARBON BELLOWS SEAL LEAKING AFTER ONLY 23.5 HOURS.SDR 97ZZZX1378Mating Ring · leakingMATING RING LEAKING AFTER ONLY 23.5 HOURS.SDR AU970111Turbine · damaged(AUS) RH ENGINE HOT SECTION AND POWER TURBINE MODULES DAMAGED - HOT SECTION 1. 2ND STAGE TURBINE FORWARD COOLING PLATE DAMAGED2. 1ST AND 2ND STAGE TURBINE NOZZLES AND ROTOR DAMAGED POWER TURBINE SECTION 1. 3RD AND 4TH STAGE TURBINE NOZZLES AND ROTOR DAMAGED2. SDR CA970311093Seal · leaking(CAN) RESIDUAL OIL WAS REPORTED TO BE COLLECTING IN THE 4TH NOZZLE AND TAILPIPE AREA AT THE 6 O''''CLOCK POSITION. MAINTENANCE REMOVED ENGINE AND EXPOSED NR 4 AND NR 5 BEARING SEAL AREA TO CONFIRM LEAKAGE OF NR 5 BEARING SEAL. AS A PRECAUTION, NUMBERS 4 ANDSDR HEEA979120Shield · crackedRECEIVING INSPECTION REVEALED: CRACKES ON #3 NOZZLE SHIELD AS MARKED.SDR 97UAL900130Turbine Blade · fracturedNR TWO ENGINE FAILED APPROXIMATELY SEVEN MINUTES AFTER TAKEOFF. RETURNED TO FIELD. T-2 BLADE FAILED DUE TO CYCLE FATIGUE. AIRFOIL FRACTURED JUST ABOVE PLATFORM AND BLADE ENTERED THE AIRSTREAM RESULTING IN DOWNSTREAM DAMAGE IN THE TURBINE AND EXHAUST CASE.SDR 97ZZZX983Blade · separatedTHE NR 2 ENGINE WAS SHUT DOWN DURING CLIMB-OUT DUE TO EXCESSIVE VIBRATIONS. INITIAL FINDS DURING TEAR DOWN INDICATE THAT SEVERAL BLADES SEPARATED FROM THE NR 3 L.P.T. THIS CAUSED SEVERE VIBRATIONS THAT, IN TURN, CAUSED THE N2 SECTION TO RUB.SDR 97ZZZX957Turbine · nozzle damageGROUND PERSONNEL NOTICED NOISE COMING FROM ENGINE DURING START-UP AND SHUT DOWN BETWEEN 20 PERCENT AND 60 PERCENT N1 RPM. THE ENGINE RAN NORMAL AT GROUND IDLE. UPON DISASSEMBLY OF THE ENGINE, THE CAUSE OF THE NOISE WAS FOUND TO BE EXCESSIVE HEAT DAMAGE TO THSDR 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 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 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 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 CA970218003Tiebolt · fractured(CAN) THE ENGINE WAS SENT FOR REPAIR AFTER OIL WAS FOUND IN THE EXHAUST. DURING DISASSEMBLY IT WAS FOUND THAT THE 3RD STAGE TURBINE TIE BOLT HAD FRACTURED. SECONDARY DAMAGE CAUSED BY THE TIE BOLT FAILURE WAS THE HP TURBINE FRONT HUB; LP TURNBINE STAGES 3,4,5 WSDR 97ZZZX766Diffuser Case · crackedDIFFUSER CASE (RT ENG) CRACKED AT 11:00 (A.L.F.) POSITION. LENGTH OF CRACK IS 4.1250 INCHES.SDR 97ZZZX2094Engine · damagedEWR/YMX - EN ROUTE, THE LEFT ENGINE STARTED TO AUTOFEATHER. THE LEFT ENGINE TEMP STARTED TO RISE, THE FLIGHT CREW THEN MANUALLY FEATHERED THE PROP. THE CREW DECLARED AN EMERGENCY AND WAS CLEARED TO LAND IN ALB. THE PILOT TRIED TO RESTART THE ENGINE, BUT IT WSDR CA970226070Rotor · failed(CAN) PILOT REPORTED NR 3 ENGINE FAILED ON TAKEOFF. DURING SPOOL UP AND PRIOR TO N1, A LOUD BANG WAS HEARD AND THE NR 3 ENGINE PARAMETERS WENT TO ZERO. STRIP DOWN FOUND 1ST STAGE TURBINE ROTOR HAD FAILED, POSSIBLY A BLADE FAILURE, CAUSING A COMPLETE FAILURE SDR CA970213013Blade · fractured(CAN) THE ENGINE WAS SENT FOR REPAIR AFTER THE OPERATOR REPORTED AN LP TURBINE BLADE FAILURE. DISASSEMBLY OF THE ENGINE FOUND THE LP TURBINE BLADE FAILURE WAS CAUSED BY CORROSION IN THE CORE POCKETS OF 3 LP TURBINE BLADES. SECONDARY DAMAGE FROM THE FAILURE CAUSDR DL757970838Hpt Disk · failedDURING CLIMBOUT APPROX 1,500 FT NR 1 ENG FAILED ABRUPTLY. SHARP VIBRATION AND SOME SMOKE IN COCKPIT, NO FIRE WARNING. FIRST STAGE HPT DISK FAILED. REPLACED ENGINE.SDR CA970206021Blade · missing(CAN) DURING CLIMB THROUGH FL270 THE CREW HEARD A "BANG" AND FELT A VIBRATION FROM #2 ENGINE, WHILE THE ENGINE WAS STILL MAKING POWER. AIRCRAFT RETURNED TO THE POINT OF DEPARTURE. INITIAL INSPECTION REVEALED A LOW PRESSURE TURBINE BLADE MISSING. THIS ENGINE SUSDR 97ZZZX3776Spring · wornSEAL RING EXPANDER SPRING WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH 2 EACH NEW UNITS, CORRECTED PROBLEM.SDR 97ZZZX3775Seal Ring · wornSEAL RING WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH 2 EACH NEW UNITS, CORRECTED PROBLEM.SDR 97ZZZX2964Bearing · failedENGINE BEARING FAILURE. ON RUN-UP POWER TO TAKEOFF, A LOUD WHINING AND GRINDING NOISE WAS HEARD FROM THE RT SIDE OF AIRCRAFT. THIS WAS FOLLOWED BY ILLUMINATION OF THE NR 2 ENGINE CHIP LIGHT. SHORTLY AFTER THAT, THE TOT FLUCTUATED AND STARTED TO INCREASE. NSDR CA970219011Turbine Blade · missing(CAN) #2 ENGINE EXPERIENCED SUDDEN VIBRATIONS THROUGH FL270. ALL ENGINE PARAMETERS WERE FINE BUT VIBRATIONS COULD BE FELT THROUGH THE AIRCRAFT AND POWER LEVERS. ENGINE WAS SHUTDOWN AND THE AIRCRAFT RETURNED TO ITS POINT OF DEPARTURE. POST FLIGHT INSPECTION FOUSDR CA970210009Turbine Wheel · loose(CAN) AFTER GROUND RUN, THE PROPELLERS WERE PULLED THROUGH BY HAND TO AID COOLING. AN UNUSUAL NOISE WAS HEARD ON NR 2 ENGINE. ENGINE TORN DOWN AND THE RIVETS IN THE 2ND TURBINE WHEEL WERE FOUND LOOSE ALLOWING THEM TO TOUCH THE 3RD STATOR. NO DAMAGE WAS SUSTASDR 97ZZZM243Turbine · failedMIAMI - ON TAKEOFF, NR 1 ENGINE BEGAN TO STALL SEVERELY AT 400 FEET. TOWER REPORTED FLAMES OUT OF NR 1 ENGINE. ENGINE WAS SHUT DOWN. RETURNED TO MIAMI AND LANDED WITHOUT INCIDENT. INSPECTION REVEALED NO EVIDENCE OF FIRE, BUT METAL IN TAIL PIPE. REPLACED ESDR P5CA9700068Case Rail · crackedCRACK ON NR 2 ENGINE TURBINE CASE S-RAIL. WELDED CRACK PER PRATT AND WHITNEY OHM 72-53-01.SDR CA970204005Bolt · fractured(CAN) THE ENGINE WAS SENT FOR A SCHEDULED OVERHAUL. UPON DISASSEMBLY IT WAS DISCOVERED THE ENGINE HAD POWER TURBINE DAMAGE RESULTING FROM AN INTERSTAGE CASE BOLT FAILURE. THE ENGINE WAS PRE MOD 21175 AND THE LIBERATED BOLT HEAD INFLICTED IMPACT DAMAGE TO ALL TSDR 97ZZZX579Pt Shaft · chippedENGINE REJECTED DUE TO N2 SPLINE CHIPPED SHAFT. THE FRONT END OF THE SPLINE WAS CHIPPED. SUBMITTER BELIEVES THIS IS CAUSED AT INSTALLATION OF TURBINE GEARBOX.SDR CA970130020Turbine Blades · fractured(CAN) THE ENGINE HAD SUFFERED FRACTURE OF TWO LP TURBINE BLADES.SDR 97ZZZX925Spring Carrier · spalledENGINE HAD HISTORY OF CHIP LIGHT ILLUMINATION. ALWAYS BURNED OFF. VISUAL INSPECTION FOUND CHIPS EXCEEDING LIMITS IAW SB LT101-77-30-0104. REMOVED ENGINE FOR REPAIR.SDR HEEA978904Nozzle · out of specRECEIVING INSPECTION REVEALED: INNER AIRFOIL RING PARENT METAL OUT OF SPECS PER AMC-OIL 17 AND APERATURE CARDS ON #1 NOZZLE AS MARKED. ACTUAL .023 - .087 (B.P. SPECS .0495 - .0515) INSTALLED A NEW NOZZLE.SDR HEEA978903Nozzle · crackedENGINE REMOVED DUE TO METAL, COMPRESSOR STALLS AND SMOKE ON SHUTDOWN. UPON INSPECTION OF TURBINE PARTS NOTED: RUNOUT BEYOND SERVICEABLE LIMITS ON #2 NOZZLE 1ST AND 2ND STAGE TIP PATH AND CRACKED LEADING EDGE AND TRAILING EDGE AS MARKED. REPLACED WITH DALLAS SDR HEEA978902Nozzle Vane · crackedENGINE REMOVED DUE TO METAL, COMPRESSOR STALLS AND SMOKE ON SHUTDOWN. UPON INSPECTION OF TURBINE PARTS NOTED: CRACKED AND BOWED BEYOND SERVICEABLE LIMITS ON NR 1 NOZZLE VANES. REPLACED WITH NEW NR 1 NOZZLE.SDR HEEA978901Nozzle Vane · crackedNOZZLE CRACKED. ENGINE REMOVED DUE TO LOW POWER AND TURBINE CYCLES. UPON INSPECTION OF TURBINE PARTS NOTED: CRACKED AND BOWED BEYOND SERVICEABLE LIMITS ON NR 1 NOZZLE VANES. INSTALLED A NEW NR 1 NOZZLE.SDR HEEA978900Nozzle Vanes · crackedYNGINE REMOVED DUE TO TURBINE 1750 HOUR INSPECTION. UPON INSPECTION OF TURBINE PARTS NOTED: CRACKED AND BOWED BEYOND SERVICEABLE LIMITS ON NR 1 NOZZLE VANES. INSTALLED A NEW NR 1 NOZZLE.
Back to JASC 7250