Pratt & Whitney JFTD12A-4A
Service difficulty reports · 108
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 = 'JFTD12A4A' 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 = 'JFTD12A4A' 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 2005FA0001553Stator · sheared(REF NR MDR05-080) INSPECTION WAS PERFORMED ON 1ST STAGE STATOR AND SHOWED SIGNS OF FOD. UPON FURTHER INSPECTION IST WAS DETERMINED THAT TWO RIVETS (MFG HEAD) HAD SHEARED ON STIFFENER RING OF THE 1ST STATOR AND WERE INGESTED CAUSING MINOR DAMAGE TO THE LATER SDR CA050824011Line · cracked(CAN) AC WAS INVOLVED IN LOGGING OPS. AS AC WAS APPROACHING LOG LANDING, PILOTS WERE NOTIFIED THAT WHITE SMOKE WAS COMING FROM NR 2 ENG. AC PROCEEDED TO SERVICE LANDING TO HAVE MAINT CREW LOOK AT PROBLEM. ENROUTE, COPILOT NOTICED WHITE SMOKE COMING FROM ENSDR H3V2005F00000Stator · damagedFOD DAMAGE FROM RIVETS OF THE 1ST STAGE STATOR REAR AIRSEAL (2ND STAGE) DAMAGED THE COMPRESSOR BLADES. THIS CAUSED A STALL AND THE T5 TEMP ROSE TO 1000 DEGREES C INSTANTLY, CAUSING SEVERE TURBINE AND FREE TURBINE BLADES, VANES, AND SEALS DAMAGE. THE AIRCRAFTSDR CA050711003Engine · failedA/C INVOLVED IN AERIAL GRAPPLE LOGGING OPS ON DOWN WIND APPROACH TO LOG LANDING WITH A 15,000 LB SINGLE LOG LOAD. PILOT REDUCED POWER TO 30% TQ. UPON ACTION CREW HEARD SOUND OF ENG SPOOLING DOWN FOLLOWED BY LOW RPM AUDIO WARNING HORN & ILLUM OF WARNING LIGHTSDR 2005FA0000819Gear · crackedTGB AND SERVO ASSY REMOVED FROM ACRFT FOR MAKING METAL. GEARBOX DISASSEMBLED AND DURING VISUAL INSP OF OUTPUT GEAR, ONE TOOTH FOUND CRACKED. FRIVE SIDE OF TOOTH SHOWS THE MAJORITY OF CRACKING, STARTING FROM IB TO ALMOST MIDWAY ON TOOTH EXTENDING ACROSS TIP LSDR 2005FA0000339Axle · cracked(MDR05-073) FOUND CRACKED DURING NDT INSPECTION. CRACK IS APPROXIMATELY 1 INCH IN LENGTH AND IS IN THE KEY GROOVE. THIS IS FIRST KNOW DEFECT OF THIS TYPE FOR THIS PART. CAUSE IS UNKNOWN AND NO RECOMMENDATIONS TO PREVENT RECURRENCE AT THIS TIME. (K)SDR 2005FA0000341Spar · cracked(MDR05-074) THE SPAR IS CRACKED ON THE BOTTOM SIDE OF THE BLADE BETWEEN POCKET LOCATIONS NR 5 AND NR 6. CRACK IS APPROXIMATELY .300 INCH IN LENGTH .650 INCH FROM THE BACKWALL RUNNING CHORDWISE TO .950 INCH FROM THE BACKWALL. BLADE HAD A BIM INDICATION AND WASDR 2005FA0000000Bevel Gear · crackedDURING NDT INSPECTION, GEAR WAS MPI`D AND REJECTED FOR CRACKS. LOCATION OF CRACKS WERE IN ATTACHMENT FLANGE BOLT HOLES (18 EACH). EVERY HOLE HAS APPROXIMATELY .1250 INCH LONG CRACK STARTING ON THE GEAR TO SHAFT ATTACHMENT SIDE EXTENDING DOWN INTO THE HOLE. SDR 2005FA0000001Duct · wrong partDURING TEARDOWN OF F/T ASSEMBLY, A BROKEN EPR PROBE WAS FOUND AND THE INLET DUCT WAS SITTING LOW WHICH WOULD ALLOW MORE AXIAL TRAVEL OF INLET DUCT DURING OPERATION. AFTER REMOVING INLET DUCT, FOUND THE OVERALL HEIGHT OF INLET DUCT TO BE SHORT. THIS CAUSED WESDR MDR04060Spacer · crackedCOMPRESSOR, SN 672543, CAME INTO THE SHOP AND DURING THE PRELIMINARY TEST RUN, THE VIBES WERE AT 1.7 MILS. WITH THE VIBES EXCEEDING THE LIMITS, THE COMPRESSOR HAD TO BE DISASSEMBLED FOR BALANCE. DURING THE VISUAL INSPECTION OF THE 3-4 SPACER, THERE APPEARED SDR 2004F00335Seal · brokenCOMPRESSOR ASSY REMOVED FROM A/C FOR A 1000 TSO SCHED HOT SECTION INSP. DURING INSP, EVIDENCE RUBBING BETWEEN OUTER SHROUD OF 1ST STAGE N1 BLADES & 1ST STATE OUTER AIRSEAL KNIFE EDGES. 1 BLADE BROKEN OUTER SHROUD. CONTACT BETWEEN DAMAGED TO OUTER SHROUD OF BSDR CA040623002Dump Valve · malfunctioned(CAN) AS COLLECTIVE WAS LOWERED FLIGHT CREW HEARD A (WHOOSH) SOUND FOLLOWED BY AN ENG N1 UNDER-SPEED WARNING AUDIO. FLIGHT CREW VERIFIED ENG, IMMEDIATELY EXECUTED AN IN-FLIGHT SHUTDOWN OF NR 1 ENG TO PREVENT OVER-TEMP CONDITION. WITH NR 1 ENG SHUTDOWN, AC RETUSDR CA040603003Dump Valve · malfunctioned(CAN) PILOT BEGAN DESCENT, HEARD (WHOOSH) SOUND TYPICAL OF SOFT STALLING ENG. FOLLOWED BY N1 UNDERSPEED AUDIO, INDICATOR LIGHT WARNING. FLT CREW VERIFIED NR 1 ENG AS BEING AT FAULT. COPILOT SHUTDOWN ENG, BEGAN TO MOTOR TO DECREASE T5 TEMP WHILE PILOT RELEASEDSDR CA040519005Pump · failed(CAN) THE FLIGHT CREW WAS ALERTED BY THE ILLUMINATION OF THE ENGINE OIL PRESSURE WARNING LIGHT FOR NR 1 ENGINE. A CHECK OF THE CORRESPONDING OIL PRESSURE INDICATOR RELIEVED ZERO PSI. THE CREW IMMEDIATELY SHUT DOWN THE SUBJECT ENGINE, RETURNED TO THE SERVICE SDR CA040527004Duct · failedA/C WAS INVOLVED IN HELICOPTER LOGGING OPERATIONS IN THE AREA OF POWER RIVER BRITISH COLUMBIA. DURING THE FIRST LOGGING CYCLE OF THE DAY THE FLIGHT CREW NOTICED WHAT APPEARED TO BE SMOKE IN THE COCKPIT. AN IMMEDIATE A CHECK OF ALL SYSTEMS AND CIRCUIT BREAKERSDR MDR04050Support Beam · crackedIN THE COURSE OF A POST FLIGHT INSPECTION, THE FIELD MAINTENANCE CREW DISCOVERED A CRACK IN THE RT MGB SUPPORT BEAM APPROXIMATELY STA 333. SL 199 AND RBL 20. THIS IS ON THE FORWARD TOP SIDE OF THE BEAM. OVERALL CRACK LENGTH APPROXIMATELY 3 INCHES. PROBABLESDR JYD2004F00000Rotor Head · crackedDURING NORMAL AIRCRAFT INSPECTION, THE FOLLOWING WAS FOUND: TWO SPANWISE CRACKS EXIST AT THE T/E ON THE OB SIDE. THE FIRST CRACK IS 7.25 INCHES FROM OB END OF THE POCKET AND IS 1.25 INCHES IN LENGTH. THE SECOND CRACK IS 14.5 INCHES FROM THE OB END OF THE POCSDR JYD2004F00002Rotor Head · crackedDURING NORMAL AC INSPECTION, THE FOLLOWING WAS FOUND; THE OB SIDE OF THE POCKET IS CRACKED 1.8125 INCH FROM THE TRAILING EDGE AND .25 INCH FROM THE TIP END. THE CRACK IS RUNNING SPAN WISE AND IS 6875 INCH LONG. PROBABLE CAUSE UNKNOWN. (MDR04-042)SDR JYD2004F00003Compressor Wheel · crackedA CRACK WAS FOUND IN THE BLADE RETENTION HOLE OF THE 2ND STAGE COMPRESSOR DISK. COMPRESSOR, SN 677782, WAS REMOVED FOR HSI/OVERHAUL. DURING THE INSPECTION PROCESS, NDT DETECTED A CRACK IN THE BLADE RETENTION HOLE, CENTER LAND USING EDDY CURRENT. THE CRACK WSDR MDR04040Blade · crackedDURING NORMAL AIRCRAFT INSPECTION, THE FOLLOWING WAS FOUND: TWO SPANWISE CRACKS EXIST AT THE TRAILING EDGE ON THE OB SIDE. THE FIRST CRACK IS 7.25 INCH FROM OB END OF THE POCKET AND IS 1.25 INCH IN LENGTH. THE SECOND CRACK IS 14.5 INCHES FROM THE OB END OF SDR MDR04042Blade · crackedDURING NORMAL AIRCRAFT INSPECTION, THE FOLLOWING WAS FOUND; THE OB SIDE OF THE POCKET IS CRACKED 1.8125 INCHES FROM THE TRAILING EDGE AND .25 INCH FROM THE TIP END. THE CRACK IS RUNNING SPAN WISE AND IS .6875 INCH LONG. PROBABLE CAUSE IS UNKNOWN.SDR MDR04043Compressor Wheel · crackedA CRACK WAS FOUND IN THE BLADE RETENTION HOLE OF THE 2ND STAGE COMPRESSOR DISK. COMPRESSOR SN 677782, WAS REMOVED FOR HSI/OVERHAUL. DURING THE INSPECTION PROCESS, NDT DETECTED A CRACK IN THE BLADE RETENTION HOLE, CENTER LAND USING EDDY CURRENT. THE CRACK WASDR MDR03021Housing · crackedTHE TGB CENTER HOUSING WAS FOUND CRACKED WHILE INSTALLED ON AIRCRAFT. IT WAS REMOVED PREMATURELY, HAVING TSO 89.0 HOURS. THE SHOP DETECTED THE CRACK VISUALLY. THE CRACK BEGAN AT THE SECOND ROSAN STUD, CLOCKWISE FROM THE ROSAN SEAT PAD LOCATED 34 DEGREES FROSDR MDR03029Housing · crackedTGB CTR HSG FOUND CRACKED WHILE INSTALLED ON AC. IT WAS REMOVED PREMATURELY HAVING A TSO OF 974.7 HR. VISUALLY DETECTED INDIC IN OB WEB OF LT MOUNTING LUG. HSG WAS LOCALLY FPI INSPECTED TO VERIFY. NO IND WAS NOTED. AREA WAS STRIPPED, LIGHTLY ABRADED WITH SSDR MDR03035Housing · crackedTGB CENTER HOUSING WAS FOUND CRACKED WHILE INSTALLED ON THE AIRCRAFT. IT WAS REMOVED PREMATURELY ON OCTOBER 20, 2000. THE SHOP DETECTED THE CRACK VISUALLY. THE CRACK BEGAN AT THE SECOND ROSAN STUD CLOCKWISE FROM THE ROSAN SEAT PAD LOCATED 34 DEGREES FROM CSDR MDR03036Housing · crackedTHE TGB CENTER HOUSING WAS FOUND CRACKED WHILE INSTALLED ON THE AIRCRAFT. IT WAS REMOVED PREMATURELY ON DECEMBER 20, 2000. THE SHOP DETECTED THE CRACK VISUALLY. THE CRACK BEGAN AT THE SECOND ROSAN STUD CLOCKWISE FROM THE ROSAN SEAT PAD LOCATED 34 DEGREES FRSDR MDR03037Housing · crackedTHE TGB CENTER HOUSING WAS FOUND CRACKED WHILE INSTALLED ON THE AIRCRAFT. IT WAS REMOVED PREMATURELY ON SEPTEMBER 3, 2000. THE SHOP DETECTED THE CRACK VISUALLY. THE CRACK BEGAN AT THE SECOND ROSAN STUD CLOCKWISE FROM THE ROSAN SEAT PAD LOCATED 34 DEGREES FRSDR MDR03034Gear · crackedTAIL ROTOR GEARBOX WAS REMOVED FROM AC FOR MAKING METAL. TAIL ROTOR GEARBOX WAS DISASSEMBLED IN THE OVERHAUL SHOP AND VISUALLY FOUND A CRACKED GEAR TOOTH ON THE OUTPUT GEAR. DURING THE MPI INSPECTION, WAS CONFIRMED THE TOOTH WAS CRACKED AND NO OTHER CRACKS WESDR JYD2004F00004Compressor Wheel · cracked2ND STAGE COMPRESSOR DISK (PN 670802, SN H63817) WAS FOUND CRACKED DURING OVERHAUL INSPECTION. COMPRESSOR (SN 672571) WAS REMOVED FROM SERVICE DUE TO REACHING ITS O/H INTERVAL, HAVING A TSO OF 2987.9 HOURS AND A TT OF 5978.0 HOURS. DURING O/H INSPECTION, FIVSDR MDR03024Fitting · crackedUPON POST-FLIGHT INSPECTION, FIELD MAINTENANCE PERSONNEL DISCOVERED THE LOWER FITTING TGB, PN 6420-66345-101, CRACKED AT THE AFT LOWER LEFT-HAND CORNER. THE CRACK IS APPROXIAMTELY .5000 INCH IN LENGTH AND TRAVELS THROUGH THE THICK WEB AND TURNS TOWARDS THE LOSDR MDR03025Compressor Wheel · crackedONE EACH CRACK INDICATION FOUND BY EDDY CURRENT INSPECTION. INDICATION IS IN THE LOCATION OF THE BLADE RETENTION PIN HOLE, ON THE CENTER FLANGE. INDICATION COULD NOT BE DETECTED BY FPI WHICH IS THE METHOD OF INSPECTION CALLED FOR IN THE OVERHAUL MANUAL. CAUSDR MDR03018Strap · crackedTHE STRAP IS CRACKED N THE OUTBOARD SIDE OF THE BLADE, APPROXIMATELY 9.125 INCHES FROM THE TRAILING EDGE. THE CRACK STARTS AT THE CUFF END OF THE BLADE AND EXTENDS APPROXIMATELY 1.25 INCHES TOWARDS THE TIP END OF THE BLADE. THE CRACK STARTS WHERE THE BACK WASDR MDR03016Housing · crackedMGB, UPPER HOUSING, CRACKED UNDER NR 1 INPUT, LT SIDE. THE FIELD CREW NOTICED OIL LEAKING FROM MGB UPPER HOUSING UNDER NR 1 INPUT. INITIAL INSPECTION BY SHOP INDICATED OIL RESIDUE IN AREA, BUT NO CRACK WAS NOTICED. FPI INDICATED NO CRACK. HEAT GUNS WERE USSDR CA030702002Fcu · malfunctioned(CAN) A/C HAD JUST DROPPED A 15,000 LB LOAD OF LOGS AT LOG LANDING IN AN UP HILL YARD. PILOT MADE A LT PEDAL TURN TO DEPART LOG LANDING. COLLECTIVE LOWERED TO DESCEND BACK DOWN TO CUT BLOCK, NR 2 ENG N1 UNDER-SPEED WARNING SOUNDED & WITH WARNING LIGHTS, INDICSDR CA030609005Valve · failed(CAN) A/C PICKED UP A 15,000 LB LOAD OF LOGS. PILOT MADE A LT PEDAL TURN TO DEPART FROM LOGGING CUT BLOCK & LOWERED COLLECTIVE TO DESCEND TO LOG LANDING. CREW HEAR A SWOOSH SOUND AT WHICH TIME NR 2 ENG N1 UNDER-SPEED WARNING SOUNDED & WARNING LIGHTS ILLUMINATESDR CA030331006Line · frozen(CAN) A/C WAS COVERED IN SNOW AND ICE & REQUIRED EXTENSIVE PREHEATING. ENGS WERE STARTED & NR 1 ENG TOOK LONGER TO LIGHT OFF. ONCE ALL WAS IN GREEN, A/C LIFTED OFF. APPROX. 10 MINS INTO 1ST CYCLE, CREW NOTICED ENGS WERE UNMATCHED. ATTEMPTED TO MATCH THEM USDR CA030102002Connector · loose(CAN) WITH FUEL QTY GAUGES INDICATING 550 LBS IN THE FWD TANK & 500 LBS IN THE AFT TANK & LOW LEVEL WARNING LIGHTS ILLUMINTED, FLT CREW FELT THEY HAD ENOUGH FUEL REMAINING TO RETURN TO THE LOGGING AREA FOR ONE MORE TURN. WHILE PICKING UP THE LAST TURN, BOTH OFSDR CA021122007Fuel Control · failed(CAN) A/C DEPARTED WITH A 13,000 LB LOAD OF LOGS, COLLECTIVE WAS LOWERED TO DECREASE ENGINE POWER. CREW HEARD A SWOOSH SOUND & NR 2 ENG N1 UNDER-SPEED WARNING SOUNDED & WARNING LIGHTS ILLUMINATED INDICATING A SOFT STALL. JETTISONED LOAD AND EXECUTED INFLIGHT SDR JYD2002F00002Disk · crackedCRACK FOUND IN BLADE PIN RETENTION HOLE OF 2ND STAGE COMPRESSOR DISK. COMPRESSOR (SN 677810) REMOVED FOR OVERHAUL. DURING INSPECTION PROCESS, NDT DETECTED A CRACK IN BLADE PIN RETENTION HOLE, CENTER LAND, USING EDDY CURRENT. CRACK VERIFIED BY FMPI. HOLDINGSDR JYD2002F00000Spar · crackedCRACK WAS FOUND ON THE TIP END OF MAIN ROTOR BLADE SPAR (PN 641520504102/ SN 64-65325910). DURING POST FLIGHT INSPECTION, FIELD CREW VISUALLY DETECTED A CRACK INDICATION ON TOP SIDE OF SPAR. TOTAL CRACK LENGTH IS APPROX. 2 INCHES LONG WITH 1.5 INCHES EXTENDSDR JYD2002F00006Compressor Wheel · crackedSECOND STAGE COMPRESSOR DISK WAS FOUND CRACKED DURING OVERHAUL INSPECTION. COMPRESSOR WAS REMOVED FROM SERVICE DUE TO REACHING ITS OVERHAUL INTERVAL, HAVING A TSO OF 2987.9 HOURS AND TT OF 5978.0 HOURS. DURING OVERHAUL INSPECTION, FIVE CRACKS WERE DETECTED BSDR JYD2003F00002Hub · crackedFRONT HUB (PN 712701, SN 3V4176) FOUND CRACKED DURING OVERHAUL INSP. COMPRESSOR (SN 672571) WAS REMOVED FROM SERVICE DUE TO REACHING ITS OVERHAUL INTERVAL, HAVING A (TSO 2987.9 HOURS), (TT OF 5978.0 HOURS). DURING OVERHAUL INSPECTION, TWO CRACKS WERE DETECTESDR JYD2002F00005Compressor Wheel · crackedFRONT HUB, FOUND CRACKED DURING OVERHAUL INSPECTION. COMPRESSOR WAS REMOVED FROM SERVICE DUE TO REACHING ITS OVERHAUL INTERVAL, HAVING A TSO OF 2987.9 HOURS AND TT OF 5978.0 HOURS. DURING OVERHAUL INSPECTION, TWO CRACKS WERE DETECTED BY CURRENT INSPECTION. SDR JYD2001F00003Compressor Wheel · crackedCOMPRESSOR, PN JFTD12A4A, SN 672491 HAVING A TOTAL TIME OF7090.9 AND A TIME SINCE OVERHAUL OF 3147.9 WAS REMOVED FOR OVERHAUL. DURING INSPECTION, 14 CRACKS WERE DETECTED IN THE 3RD STAGE COMPRESSOR DISK PN670403, SN M103AA0069 BY LIQUID PENETRANT INSPECTION. SDR JYD2001F00004Bevel Gear · crackedMAIN GEARBOX PN 643520400063, SN A6032 WAS REMOVED FROM SERVICE WITH A TOTAL TIME OF 3683.8 AND A TIME SINCE OVERHAUL OF 1172.0 FOR AN OVER TEMP CONDITION. DURING OVERHAUL INSPECTION, THIRTEEN CRACKS WERE DETECTED BY FLUORESCENT PENETRANT INSPECTION, EXTENDINSDR CA011012008Servo Valve · failed(CAN) A/C IN LOGGING OPS NEAR SAYWARD, BC. AS PILOT MADE HIS APPROACH TO LOG LDG& INITIATED FLARE TO SLOW DOWN HIS APPROACH, A/C'S NOSE ABRUPTLY PITCHED UP & CONTINUED TO DO SO EVEN WITH FULL FWD CYCLIC APPLIED. A/C FINALLY LEVELED OFF THEN BEGAN VIOLENTLY PITSDR JYD2001F00000Hinge Pin · crackedS-64F MAIN ROTOR HEAD HINGE PINS DO OCCASIONALLY CRACK FROM DAMPER NUT SAFETY HOLES (APPROX 15 PER CENT OF THE TIME), BUT TYPICALLY THE CRACKS TRAVEL OUTBOARD TO THE EDGE OF THE HINGE PIN. HINGE PIN SN A04100236 CRACKED INBOARD THROUGH THE THREADS INTO THE THSDR 20010427CW007Shaft · crackedDURING OVERHAUL, MAGNETIC PARTICLE INSPECTION REVEALED MULTIPLE INDICATION IN THE LOWER SPLINE AREA OF MAIN ROTOR SHAFT. LONGEST INDICATION MEASURED APPROX .500 INCH IN LENGTH, BEGINNING IN THE ROOT AREA EXTENDING OVER SPLINE FACE, DOWN TO THE NEXT ADJACENT RSDR 20010427CW008Seal · crackedENGINE DISASSEMBLED FOR REPAIR OF COMPRESSOR. AT DISASSEMBLY, 9TH STAGE DISK DOUBLE LIPPED REAR ROTATING AIRSEAL, WAS FOUND TO BE CRACKED IN 3 PLACES, APPROXIMATELY 0 , 30, AND 120 DEGREES. ENGINE WAS OPERATED UNDER NORMAL CONDITIONS AND NO ABNORMALITIES SDR CA000614013Gearbox · stripped(CAN) COPILOT NOTICED NR 2 ENGINE OIL PRESSURE IND FLUCTUATING THEN FOLLOWED BY ILLUMINATION OF ENGINE OIL PRESSURE WARNING LIGHT. PILOT BROUGHT ENGINE BACK TO FLT IDLE WHERE ENG OIL PRESSURE STABILIZED AT 38 PSI. ON FINAL APPROACH, ENG OIL PRESSURE DROPPED
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