Pratt & Whitney JT12A-8
Service difficulty reports · 18
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 = 'JT12A8' 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 = 'JT12A8' 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 2008FA0000663Pump · wornAFTER TAKEOFF THE PILOT COULD NOT ADJUST THE LT ENGINE POWER OUTPUT. ENGINE REMAINED AT TAKEOFF POWER WHILE POWER LEVER WAS RETARDED TO IDLE. PILOT RETURNED TO AIRPORT AND SUCCESSFULLY SHUTDOWN THE LT ENGINE BY PLACING POWER LEVER TO CUT-OFF POSITION AND MADESDR 2008FA0000188Actuator · bypassingLT MLG ACTUATOR BYPASSING ON RETRACTION CAUSING INTERFERENCE WITH IB DOOR ROLLERS. NO EXTERNAL FAILURE INDICATION. UPON TEARDOWN, IT WAS DISCOVERED THAT THE CYLINDER WAS SCRATCHED AND THE PISTON SEAL WAS DAMAGED.SDR 2007FA0001032Duct · deformedATTACHING SLEEVE SLID OFF OF DUCT CAUSING LOSS OF PRESSURIZATION. EMERGENCY PRESSURIZATION FUNCTIONED NORMALLY. CLAMPS TIGHTENED TOO TIGHT AND DEFORMED FIBERGLASS DUCT. RECOMMEND METAL SLEEVE BE INSTALLED TO ALLEVIATE DEFORMATION. (K)SDR UVVR200600001Nut · crackedWHILE PERFORMING MAINTENANCE ON AIRCRAFT, IT WAS DISCOVERED THAT APPROXIMATELY 10 NUTS ON EACH WING THAT SECURES UPPER WING PLANK TO REAR SPAR UPPER FLANGE, FROM REAR SPAR STATION 161.1 TO 281.8 WERE CRACKED, WITH SOME MISSING PARTS OF THE NUT. AS A PRECAUTIONSDR 20010306CW009Turbine Wheel · crackedDISK TT 3140.1 TC 2697 MAX ALLOWABLE OPER. TIME IS 8000 HR AND 8000 CYCLES.DURING OVERHAUL OF ENGINE AND PERFORMING FLUORESECENT PENETRANT INSPECTION, THE SECOND STAGE TURBINE DISK PN/405802, SN/G23877 WAS FOUND TO HAVE 13 EA CRACK INDICATION INBOARD OF THE SDR 96ZZZX4331Compressor · bindingCOMPRESSOR VERY DIFFICULT TO ROTATE, IINTERNAL BINDING COULD BE FELT WHEN ROTATING BY HAND WITH SHORT SPOOL DOWN TIME. NO FOD NOTED, NO DAMAGE OR VISUAL DEFECTS NOTED IN TURBINE HOT SECTION. ALL IN-FLIGHT AND GROUND TEST PARAMETERS NORMAL. ENGINE WAS REMOVEDSDR 96ZZZX4342Lock · missingMETAL-TO-METAL CONTACT, BIND, BLADE RUB. INVESTIGATION FINDINGS: AN INDUCTION TEST RUN COULD NOT BE ACCOMPLISHED DUE TO RUBBING CONDITION. THE ENGINE AND COMRPESSOR ASSEMBLY WERE DISASSEMBLED TO IDENTIFY CAUSE OF DISCREPANCY. INVESTIGATION REVELAED THAT P/SDR 96ZZZX3906Compressor · bindingCOMPRESSOR VERY DIFFICULT TO ROTATE AND SPOOL DOWN VERY SHORT. INTERNAL BINDING COULD BE FELT WHEN ROTATING BY HAND. THIS IS A MULTI-STAGE UNIT, SO VISUAL INSPECTION/DETECTION OF A PARTICULAR PART FAILURE IS VERY DIFFICULT. NO FOD NOTED AND NO DAMAGE OR DEFSDR 96ZZZX4323Lock · missingINTERNAL BLADE RUBBING, BINDING, AND LOCKING UP. AN INDUCTION TEST RUN WAS PEFORMED ON 6-20-96. DURING THE TEST, VIBRATION OF 3.8 MIL AT 75 PERCENT WAS NOTED. (3.2 MIL IS MAXIMUM ALLOWABLE). ENGINE WAS DISASSEMBLED AS NECESSARY TO ACCESS COMPRESSOR ASSY. SDR 96ZZZX4034Compressor · bindingCOMPRESSOR VERY DIFFICULT TO ROTATE AND SPOOL DOWN VERY SHORT. INTERNAL BINDING COULD BE FELT WHEN ROTATING BY HAND. THIS IS A MULTI 9-STAGE UNIT, SO VISUAL INSPECTION/DETECTION OF A PARTICULAR PARTS FAILURE IS VERY DIFFICULT. NO FOD NOTED AND NO DAMAGE OR DSDR 96ZZZX4035Compressor · bindingCOMPRESSOR VERY DIFFICULT TO ROTATE AND SPOOL DOWN VERY SHORT. INTERNAL BINDING COULD BE FELT WHEN ROATING BY HAND. THIS IS A MULTI 9-STAGE UNIT, SO VISUAL INSPECTION/DETECTION OF A PARTICULAR PARTS FAILURE IS VERY DIFFICULT. NO FOD NOTED AND NO DAMAGE OR DSDR 96ZZZX3523Compressor · bindingCOMPRESSOR VERY DIFFICULT TO ROTATE AND SPOOL DOWN VERY SHORT. INTERNAL BINDING COULD BE FELT WHEN ROTATING BY HAND. THIS IS A MULTI-STAGE UNIT, SO VISUAL INSPECTION/DETECTION OF A PARTICULAR PARTS FAILURE IS VERY DIFFICULT. NO FOD NOTED AND NO DAMAGE OR DESDR 96ZZZX3051Blade · brokenSECOND STAGE TURBINE ROTOR BLADE FAILURE IN-FLIGHT, WITHOUT INCIDENT. ENGINE TT, 11,164.7 HRS, CYCLES, 8,081, TSO, 330.9 HRS, TTHSI, 330.9 HRS, TOTAL PART TIME 330.9 HRS. UNIT WAS OVERHAULED 4-12-95.SDR 96ZZZX3823Turbine · failedCLIMBING THROUGH 5,000 FEET, THE CREW HEARD AND FELT A LOUD REPORT FOLLOWED IMMEDIATELY BY THE LT ENGINE FIRE WARNING LIGHT. THE LT ENGINE SPEED ROLLED BACK TO APPROXIMATELY 12 PERCENT. PILOT SHUT ENGINE DOWN, DISCHARGED THE FIRE BOTTLE AND MADE A SINGLE ENGSDR 96ZZZX1359Blade · rubDURING INSPECTION OF ENGINE, SN P673149NB, A CRACKED INLET GUIDE VANE PROMPTED REMOVAL OF INLET CASE FOR REPAIRS. WITH CASE REMOVED, A COMPRESSOR BLADE RUB, WHICH RESULTED IN DETERIORATION TO A STATOR, WAS NOTED AND REPORTED. AUTHORIZATION WAS RECEIVED FROM SDR 96ZZZX1360Blade · overlapDUE TO CORROSION DMG DISCOVERED ON RT ENG, CUSTOMER ELECTED TO DISASSEMBLE LT ENG FOR CORROSION INSP, & SUBSEQUENT COMPR OVERHAUL PER P&WA. UPON DISASSEMBLY OF COMPR, SEVERE CORROSION NOTED ON STEEL COMPONENTS. CORRRODED STEEL DISK REJECTED. CUSTOMER ELECTESDR 96ZZZX1635Vane · plating peelREPORTED CAUSE FOR REMOVAL OF ENGINE FROM AIRCRAFT WAS TURBINE BLADE FAILURE. INVESTIGATION FINDINGS: ENGINE DISASSEMBLED AS NECESSARY AND REPAIRED DUE TO TURBINE BLADE FAILURE. DISCREPANCY NOTED DURING INSPECTION WAS PLATING PEELING OFF 23 EACH, PN 569551,SDR 95ZZZX5314Guide Vane · burnedENGINE RECEIVED FOR CORR & HOT SECT INSP PER SB 1508. ENG OPERATED TO 1,227 HRS TIME SINCE LAST HOT SECT INSP. ENG SUFFERED LOSS OF 3 EA NOZZLE GUIDE VANES COMPLETELY BURNED IN HALF ALLOWING INNER SHROUD HALVES TO ENTER GAS PATH & DAMAGE TURB. FAILURE RESUL
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