JASC 7250
Service difficulty reports · 3,624
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 20001129SH013Seal · separatedLP FORWARD STATIC SEAL HAD INSUFFICCIENT CLEARANCE BETWEEN THE SEAL AND STAGE 2 HPT ROTOR DISC AFT FACE. POSSIBLE CAUSE IS THE SEPARATION OF THE 2-PIECE STATOR SEAL. PROBLEM FOUND BY BORESCOPE INSPECTION PER SB CFE 738-A72-8041. (X)SDR 20001129SH012Seal · separatedLP FORWARD STATIC SEAL HAD INSUFFICCIENT CLEARANCE BETWEEN THE SEAL AND STAGE 2 HPT ROTOR DISC AFT FACE. POSSIBLE CAUSE IS THE SEPARATION OF THE 2-PIECE STATOR SEAL. PROBLEM FOUND BY BORESCOPE INSPECTION PER SB CFE 738-A72-8041. (X)SDR 20001129SH011Seal · separatedLP FORWARD STATIC SEAL HAD INSUFFICIENT CLEARANCE BETWEEN THE SEAL AND STAGE 2 HPT ROTOR DISC AFT FACE. POSSIBLE CAUSE IS THE SEPARATION OF THE 2-PIECE STATOR SEAL. PROBLEM FOUND BY BORESCOPE INSPECTION PER SB CFE 738-A72-8041. (X)SDR 20001129SH010Seal · separatedLP FORWARD STATIC SEAL HAD INSUFFICIENT CLEARANCE BETWEEN THE SEAL AND STAGE 2 HPT ROTOR DISC AFT FACE. POSSIBLE CAUSE IS THE SEPARATION OF THE 2-PIECE STATOR SEAL. PROBLEM FOUND BY BORESCOPE INSPECTION PER SB CFE 738-A72-8041. (X)SDR AALA20001602Blade · brokenMEM - FLT 622 - EN ROUTE DFW-BWI, NR 1 ENGINE FAILED. ACCOMPLISHED FIRE/SEVERE DAMGE CHECKLIST, DUMPED APPROXIMTELY 6000 LBS OF FUEL, AIR INTERRUPTED, AND LANDED MEM WITHOUT INCIDENT. REPLACED NR 1 ENGINE. REPLACED NR 1 ENGINE HIGH PRESSURE TURBINE BLADE. SYSDR R7MR32899Seal · leakingLEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM.SDR R7MR32898Seal · leakingLEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM.SDR R7MR32886Shroud · damagedEXCESSIVE GP BLADE TIP RUB. REPLACED WITH NEW UNIT, CORRECTED PROBLEM.SDR R7MR32881Spring · wornWORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM.SDR R7MR32880Seal Ring · wornWORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNITS, CORRECTED PROBLEM.SDR USAABB00100Turbine Wheel · failedPHL - ON ENGINE RUN-UP AFTER IDG MAINTENANCE, ONE OF THE LEFT ENGINE TURBINES FAILED. MECHANICS DISCHARGED BOTH BOTTLES WHICH PROVED INEFFECTIVE IN BATTLING THE FIRE. CFR WAS CALLED TO EXTINGUISH THE FIRE. DAMAGE INCLUDES THE WING, PYLON, FLAP AND AILERON ASDR 20001108SH040Turbine Wheel · damagedDURING APPROACH TO LAND, PILOT EXPERIENCED A LOUD CONTINUOUS NOISE COMING FROM THE ENGINE. ALL ENGINE INSTRUMENTS WERE NORMAL. ENGINE WAS INSPECTED BY MAINT, NO OBVIOUS MALFUNCTIONS WERE NOTED. DURING ENGINE RUN-UP TO ISOLATE ENGINE NOISE, THE ENGINE CHIP DSDR AU000842Turbine · inaccurate(AUS) FIRST STAGE TURBINE WHEEL AND THIRD STAGE STATOR SERIAL NUMBERS DID NOT MATCH THE SERIAL NUMBERS IN THE LOGBOOK OR LOG CARDS. (X)SDR 20001214SH038Turbine Wheel · wornROTOR ASSY, INSERTABLE BLADED, POWER TURBINE RETENTION PLUG WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X)SDR R7MR32500Structure · crackedCRACKED BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM.SDR CA001214017Blade · damaged(CAN) PILOT REPORTED THAT BLADE RUBBING NOISE WAS COMING FROM POWER TURBINE SECTION WHEN THE PROPELLER WAS TURNED BY HAND ON THE LEFT HAND ENGINE. LEFT HAND POWER SECTION WAS REPLACED AND SENT TO ENGINE SHOP FOR REPAIR.TC: EXPECT FOLLOW UP FROM OPERATOR IF SISDR CA001020008Shaft · corroded(CAN) DURING A SCHEDULED ENGINE VISIT AT RRC, THE HP TURBINE STUB SHAFT WAS FOUND TO BE EXCESSIVELY CORRODED AROUND BOLT HOLES. RRC LAB REPORT CONFIRMED CORROSION AND THE STUB SHAFT WAS SCAPPED AND A NEW REPLACEMENT FITTED.SDR AU000682Turbine Nozzle · corroded(AUS) LT ENGINE FIRST STAGE NOZZLE AND INNER BAFFLE ASSEMBLY BURNED, CRACKED AND CORRODED. SEAL PLATE WARPED AND CRACKED. FIRST STAGE TURBINE BLADE TIPS ERODED. SUSPECT CAUSED BY SULPHURISATION CORROSION OF THE NOZZLE COMPINED WITH STREAKING FUEL INJECTORS.SDR AU000681Gas Generator · seized(AUS) RT ENGINE GAS GENERATOR MODULE AND POWER SECTION SEIZED.SDR AU000677Turbine · making metal(AUS) NR 2 ENGINE REAR BEARING MAGNETIC PLUG CONTAIN A SMALL SLIVER OF METAL. THE ENGINE WAS INSPECTED IAW THE MANUFACTURERS INSTRUCTIONS BEFORE BEING GROUND RUN AND FLIGHT TESTED WITH NOFURTHER PROBLEMS. AIRCRAFT RETURNED TO SERVICE.SDR AU000631Turbine Nozzle · failed(AUS) NR 2 ENGINE FAILED ON TAKEOFF WITH THE TGT EXCEEDING 1000 DEGREESC. SUSPECT CAUSED BY FAILURE OF THE SECOND STAGE HP TURBINE NOZZLE.SDR AU000626Turbine Nozzle · separated(AUS) RT ENGINE NOZZLE GUIDE VANE SEGMENT SEPARATED. DAMAGE TO FIRST, SECOND AND THIRD STAGE NOZZLE ASSEMBLIES AND TURBINE WHEELS CAUSED BY FOD.SDR DHL2000707031Turbine · failedNR 3 ENGINE FAILED ON T/O, ENGINE SHUT DOWN (POWER LOSS). EMERGENCY DECLARED, RETURNED TO BWI. INITIAL INSPECTION INDICATES TURBINE FAILURE.SDR 20000913SH020Turbine · lightning strikeTHE AIRCRAFT WAS BROUGHT INTO MAINTENANCE FOR A SCHEDULED INSPECTION. UPON INSPECTION OF THE LEFT ENGINE, A HOLE WAS FOUND IN THE POWER SECTION CASE. THE HOLE CAUSED DAMAGE TO EXTERNAL WIRING AND TRANSFER TUBES. SUBMITTER STATED CAUSED BY A LIGHTING STRIKE.SDR 20001215SH010Seal · leakingNR 2 BEARING SEAL LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X)SDR R7MR32995Shroud · damagedEXCESSIVE GP BLADE TIP RUB. REPLACED WITH NEW UNIT, CORRECTED PROBLEM.SDR R7MR32990Spring · wornWORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNITS, CORRECTED PROBLEM.SDR R7MR32989Seal Ring · wornWORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNITS, CORRECTED PROBLEM.SDR AU000984Turbine · overheated(AUS) LEFT ENGINE UNCOMMANDED TORQUE REDUCTION COUPLED WITH HIGH EGT INDICATION. HOT SECTION OVERTEMP DAMAGE. (X)SDR 20000907SH030Seal · separatedLP FORWARD STATIC SEAL HAS INSUFFICIENT CLEARANCE BETWEEN THE SEAL AND THE STAGE 2 HPT ROTOR DISK AFT FACE. POSSIBLE CAUSE IS THE SEPARATION OF THE 2-PIECE STATOR SEAL. PROBLEM FOUND BY BORESCOPE INSPECTION PER CFE FIELD ENGINEERING INSTRUCTIONS NR CFE 738-FSDR 20000907SH029Seal · separatedLP FORWARD STATIC SEAL HAS INSUFFICIENT CLEARANCE BETWEEN THE SEAL AND THE STAGE 2 HPT ROTOR DISK AFT FACE. POSSIBLE CAUSE IS THE SEPARATION OF THE 2-PIECE STATOR SEAL. PROBLEM FOUND BY BORESCOPE INSPECTION PER CFE FIELD ENGINEERING INSTRUCTIONS NR CFE 738-FSDR 20000907SH028Seal · separatedLP FORWARD STATIC SEAL HAS INSUFFICIENT CLEARANCE BETWEEN THE SEAL AND THE STAGE 2 HPT ROTOR DISK AFT FACE. POSSIBLE CAUSE IS THE SEPARATION OF THE 2-PIECE STATOR SEAL. PROBLEM FOUND BY BORESCOPE. INSPECTION PER DFE FIELD ENGINEERING INSTRUCTIONS NR CFE 738SDR 20000907SH027Seal · separatedLP FORWARD STATIC SEAL HAS INSUFFICIENT CLEARANCE BETWEEN THE SEAL AND THE STAGE 2 HPT ROTOR DISK AFT FACE. POSSIBLE CAUSE IS THE SEPARATION OF THE 2-PIECE STATOR SEAL. PROBLEM FOUND BY BORESCOPE. INSPECTION PER DFE FIELD ENGINEERING INSTRUCTIONS NR CFE 738SDR 20000831SH023Seal · separatedLP FWD STATIC SEAL HAD INSUFFICIENT CLEARANCE BETWEEN THE SEAL AND THE STAGE 2 HPT ROTOR DISK AFT FACE. POSSIBLE CAUSE IS THE SEPARATION OF THE 2-PIECE STATOR SEAL. PROBLEM FOUND BY BORESCOPE INSPECTION PER CFE FIELD ENGINEERING INSTRUCTION NR CFE 738-FEI-00SDR 20000831SH022Seal · separatedLP FORWARD STATIC SEAL HAD INSUFFICIENT CLEARANCE BETWEEN THE SEAL AND THE STAGE 2 HPT ROTOR DISK AFT FACE. POSSIBLE CAUSE IS THE SEPARATION OF THE 2-PIECE STATOR SEAL. PROBLEM FOUND BY BORESCOPE INSPECTION PER CFE FIELD ENGINEERING INSTRUCTION NR CFE 738-FESDR AC2A0000089Turbine Wheel · contaminatedFIELD MAINT REPORTED NR 1 ENGINE HAD FOREIGN OBJECT DAMAGE TO NR 1 ENG COMPRESSOR. MECH EXAMINED TURBINE FOR DAMAGE PER MAINT INSTRUCTIONS. DAMAGE FOUND ON TURBINE NR 1 WHEEL AND ENG REMOVED AND RETURNED FOR REPAIR. UPON TEARDOWN, FOUND NR 1 TURB WHEEL HAD SDR 20001102SH032Turbine · damagedENGINE DISASSEMBLED 10/4/00. EXTENSIVE DAMAGE TO POWER SECTION OF ENGINE DUE TO ENGINE OPERATION AFTER FIRST KNOWLEDGE OF MALFUNCTION. POSSIBLE CAUSE, LINK ROD BROKE AT LINK PIN AND DUE TO METAL FATIGUE. (X)SDR 2000UALA00456Bearing · failedNUMBER 2 ENGINE HAD VIBRATION. *S/D* THE ENGINE WAS REPLACED.SDR CA000809007Seal · failed(CAN) DURING PRE-INSTALLATION INSPECTION, IT WAS NOTICED THAT THERE WAS EXCESSIVE GAP BETWEEN THE SEAL AND THE ROTOR. GAP WAS MEASURED AT 0.022 INCHES. IRM 72-IR-15 R9 STATES THAT THE GAP SHOULD BE NO LARGER THAN 0.010 INCHES.SDR CA001017011Turbine Wheel · broken(CAN) ENGINE REMOVED FOR HIGH TAXI AND GROUND IDLE SNAG. DISASSEMBLY REVEALED NR 1 COMPRESSOR IMPELLER HAD A PIECE BROKEN OUT OF THE TRAILING EDGE OF 1 BLADE .085 INCH UP FROM THE PLATE .480 INCH FROM THE OUTER RIM OF THE PLATE. THE RESULTING DAMAGE DOWN STRESDR 00FDEA00468Heat Shield · crackedDURING ROUTINE INSPECTION, NR 3 ENGINE PRE-COOLER HEAT SHIELD FOUND CRACKED ON UPPER I/B SIDE. STOP DRILLED CRACK, FAB, AND INSTALLED PER IAW SRM 51-40-2.SDR TWAA0011102Blade · failedTHE RT ENGINE FAILED WITH A BANG. CREW ACCOMPLISHED ENGINE SHUT DOWN PROCEDURE AND MADE AN UNSCHEDULED LANDING AT IAD. FOUND TURBINE FAILURE. CHECK-C 2-22-00 STL. EXCESSIVE CROSS NOTCH WEAR OF THIRD STAGE TURBINE BLADES WAS THE ROOT CAUSE OF THE FAILURE.SDR CA000724008Turbine · failed(CAN) ON CLIMB OUT NR 2 ENGINE N2 EXCEEDED LIMITS, THEN SHUT DOWN. CREW DECLARED AN EMERGENCY AND MADE AN UNEVENTFUL LANDING. AFTER INVESTIGATION MAINTENANCE REPORT LPT (LOW PRESSURE TURBINE SECTION) CASE PENETRATION (PRIMARILY AT THE 7-8 OCLOCK POSITION). THESDR CA000724013Turbine · seized(CAN) AFTER LANDING, DURING ROLLOUT, THE CREW DEPLOYED THE THRUST REVERSER AND THE RT ENGINE SHUTDOWN. THE AIRCRAFT CONTINUED TO THE HANGAR AND AN INITIAL EVALUATION OF THE ENGINE REVEALED THAT THE TURBINE WHEEL HAD SEIZED.FURTHER DETAILS OF THE ENGINE INSPECTSDR 20000803SH010Vane · inaccurateA TREND HAS DEVELOPED INDICATING PROCEDURES, TECHNIQUES, OR WORKMANSHIP OF OVERHAULED VANE RINGS IS RESULTING IN PREMATURE FAILURE OF PN 3032651 WHICH RESULTS IN UNSATISFACTORY ENGINE PERFORMANCE AND POSSIBLE ENGINE FAILURE. (X)SDR 20001214SH048Seal · leakingNR 3 BEARING SEAL LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X)SDR 20001214SH047Seal · leakingNR 2 BEARING SEAL LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. (X)SDR R7MR32938Seal · leakingLEAKING BEYOND SERVICEABLE LIIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM.SDR R7MR32937Seal · leakingLEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM.SDR R7MR32917Spring · wornWORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNITS, CORRECTED PROBLEM.
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