Pratt & Whitney JT9D-7R4E
Service difficulty reports · 68
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 = 'JT9D7R4E' 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 = 'JT9D7R4E' 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 AU000590Compressor · contaminated(AUS) HP COMPRESSOR DISCS (STG. 8, 10, 12 AND 14) FOUND WITH SILVER PLATE CONTAMINATION CAUSED BY USE OF SILVER PLATED NUTS FITTED AT TIE ROD LOCATIONS.SDR AU000549Pin · missing(AUS) LT INBOARD AILERON LOWER HALF PCA SUMMING LEVER/INPUT ROD PIVOT LINK PIN MISSING.SDR AU000233Wire · burned(AUS) CARGO HOLD FLOOR WIRING AND INSULATION BLANKET BURNT.SDR AU000069Switch · faulty(AUS) CABIN PRESSURE SELECTOR PANEL SWITCH FAULTY.SDR AU000029Spring · broken(AUS) ENTRY DOOR L1 COUNTER BALANCE SPRING BROKEN.SDR 99FDEA00514Computer · inoperative99-297 - ECAM AND MASTER SHOW CHECK FUEL MGMT. REMOVED AND REPLACED FUEL QTY COMPUTER PERFORM BITE CK.SDR AU991008Line · loose(AUS) RIGHT ENGINE T2 SENSOR PTT2 FUEL LINE LOOSE AND LEAKING FUEL.SDR AU991002Fuse Pin · cracked(AUS) NR 2 ENGINE STRUT INBOARD MID-SPAR FUSE PIN CRACKED. CRACK LENGTH 0.508 MM (0.020 INCH). NR 2 ENGINE OUTBOARD MID-SPAR FUSE PIN CRACKED. CRACK LENGTH 38.1 MM (1.5 INCH). FOUND DURING INSPECTION IAW QANTAS ENGINEERING INSTRUCTION EI 767-054-0026.SDR AU981638Apu · failed(AUS) DURING ENGINE START, A SHUDDER WAS FELT THROUGHOUT THE AIRCRAFT. THIS WAS ACCOMPANIED BY A LOUD NOISE. INVESTIGATION FOUND THE APU HAD FAILED WITH MANY METAL PIECES BEING EJECTED FROM THE TAILPIPE ONTO THE GROUND.SDR AU981135Turbine Disc · cracked(AUS) RIGHT ENGINE FIRST STAGE HIGH PRESSURE TURBINE BLADE TIPS CRACKED. FURTHER INVESTIGATION FOUND A RADIAL CRACK ON THE FORWARD FACE OF THE FIRST STAGE DISC. THE LENGTH OF THE CRACK WAS APPROXIMATELY 100 MM (4 INCHES) EXTENDING APPROXIMATELY 50.8 MM (2 INSDR AU981081Loom · worn(AUS) WIRING LOOM LOCATED IN THE AREA ABOVE DOOR L1 WORN THROUGH DUE TO CHAFING ON THE AIRCRAFT STRUCTURE.SDR AU980842Line · improper part(AUS) ENGINE NR 18 PRIMARY FUEL NOZZLE SUPPLY LINE WAS AN INCORRECT PART. THE LINE WAS CHAFING AGAINST THE NR 17 PRIMARY FUEL NOZZLE SUPPLY LINE. UNAPPROVED PART. PERSONNEL/MAINTENANCE ERROR.SDR 98FDEA00311Comp Blade · damaged98-0110 - STA-DFW - AFTER ROTATION AND DURING CLIMB, EXPERIENCED A SEVERE VIBRATION FROM NR 1 ENG. WHEN POWER PULLED BACK BELOW 1.2 EPR, VIBRATION WOULD STOP, NO ABNORMAL READING NOTED ON VIBRATION METER. NOTICED NEED FOR RUDDER TRIM DURING CLIMB. REMOVED NSDR AU971420Switch · failed(AUS) LH SIDE NO1 DOOR CLOSE SWITCH FAULTY. THE DOOR WAS UNABLE TO BE OPENED EITHER BY MANUAL OR ELECTRICAL MEANS.SDR 97FDEA00262Compressor · stalledAFTER TOUCHDOWN DEPLOYED BOTH REVERSER WITH FULL THRUST. IMMEDIATELY THEREAFTER HEARD A LOUD REPORT AND SAW FLASH FROM NR 2 ENGINE AREA. NR 2 ENGINE SUBSEQUENTLY SHUT DOWN AND NEVER CAME OUT OF REVERSE. NO OTHER ABNORMAL COCKPIT OR ECAM WARNINGS. *S/D* RESDR 97FDEA00185Duct · separatedNR 2 ENG TEMP ADV IN CRUISE WITH NR 2 NAC TEMP = 270 DEGREES C, FOLLOWED BY NR 2 THROTTLE WOULD NOT MOVE, FOLLOWED BY NR 2 BLEED FAULT. SHUT DOWN ENG NR 2 TO LAND, ALL OTHER ENG PARAMETERS PRIOR TO SHUTDOWN NORMAL. NR 2 OIL PRESS WAS NOT OBSERVED PAST SHUTDOSDR AU960741Slide · faulty(AUS) LH OFF WING SLIDE FAULTY - SLIDING SURFACE DEFECTIVESDR DL312951605Hpc Blade · damagedDURING BORESCOPE INSPECTION, NR 1 ENGINE WAS FOUND WITH ONE 5TH STAGE HPC BLADE WITH FOD DAMAGE 0.080 INCH TO 0.090 INCH DEEP APPROXIMATELY .25 INCH FROM TIP. THIS WAS OUT OF LIMITS, ENGINE WAS REMOVED AND ROUTED TO SHOP.
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