JASC 7240
Service difficulty reports · 509
Reports filed under 7240 · Turbine Engine Combustion 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 = '7240' 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 = '7240' 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 HEEA059983Liner · crackedPART IS CRACKED. ENGINE REMOVED DUE TO TURBINE OVERHAUL. UPON INSPECTION OF TURBINE PARTS NOTED: CRACKED BEYOND SERVICEABLE LIMITS ON COMBUSTION LINER AS MARKED.SDR CA990203018Combustion Can · failed(CAN) ENGINE INDUCTED IN THE SHOP FOR 12 STAGE HP COMPRESSOR DISC BEING TX'D. DISASSEMBLY OF THE ENGINE FOUND TWO COMBUSTION CANS (IGNITER CANS) WERE SHOWING SIGNS OF EXTREME BRITTLENESS AND AN EXCESSIVE NUMBER OF INTERGRANULAR CRACKS. THE TWO CANS WERE SCRASDR CA990125017Seal · worn(CAN) ENGINE WAS HARD TO START, WITH A BALL OF FIRE OUT OF THE TAILPIPE AND RAPID RISE IN ITT. BORESCOPE INSPECTION REVEALED HP TURBINE BLADE DAMAGE AT THE TIPS. DURING DISASSEMBLY, THE COMBUSTION OUTER SEAL RING ASSEMBLY REAR FLANGE WAS FOUND SEPARATED FROMSDR CA990115033Combustion Liner · damaged(CAN) THE ENGINE WAS REMOVED FROM WING AFTER THE OPERATOR FOUND DAMAGE TO THE OUTER COMBUSTION LINER AND THE HP SHROUD SEGMENTS. DISASSEMBLY OF THE ENGINE FOUND THE OUTER COMBUSTION LINER HAD SEVERAL SECTIONS OF THE CENTER COOLING RING MISSING AND CLEAR EVIDESDR CA990115032Ring · missing(CAN) THE ENGINE WAS SENT FOR REPAIR AND INVESTIGATION AFTER A BORESCOPE INSPECTION FOUND THE OUTER COMBUSTION LINER DAMAGED. DISASSEMBLY FOUND THE ENGINE HAD A 1.25 INCH LONG SECTION OF THE MAIN COOLING RING MISSING FROM THE OUTER COMBUSTION LINER. THE INNESDR CA990111018Liner · failed(CAN) DURING FLIGHT, NR 1 ENGINE SURGED AND A BANG WAS HEARD, BUT ALL ENGINE PARAMETERS WERE NORMAL. THE CABIN THEN FILLED WITH SMOKE, BLEED AIR VALVES WERE CLOSED. THERE WERE TWO MORE SURGES AND BANGS WITH THE FUEL FLOW RISING. THE ENG WAS SHUTDOWN AND ACFSDR AU981680Plenum · cracked(AUS) COMBUSTION CHAMBER (PLENUM) CASE CRACKED 11.1 MM (0.44 INCH) IN LENGTH BETWEEN THE 3RD AND 4TH FUEL NOZZLE, ADJACENT TO THE TURBINE SUPPORT DUCT MOUNTING FLANGE.SDR AU981704Case · fractured(AUS) ENGINE COMBUSTOR OUTER COWL FOUND WITH TWO SECTIONS OF COWL APPROXIMATELY 12.9 SQUARE CM (2 SQUARE INCHES) MISSING. ALSO, THE LIBERATED COWL PIECES HAD FRETTED SIGNIFICANTLY AGAINST THE ADJACENT FUEL NOZZLE STEMS. FOUND IAW CFMI SB 72-536. PART TC: 1SDR 99ZZZX1695Seal · wornSEAL WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM.SDR 98UAL900521Combustor · crackedNINE INCH CIRCUMFERENTIAL CRACK IN NR 5 COMBUSTION CHAMBER CAN OF NR 2 ENGINE. *S/D* SHOP INSPECTION OF THE NR 5 BURNER CAN REVEALED THE CRACK TO BE IN THE 2-3 LINER UNDER THE AIR SCOOP. CRACKING IN THIS AREA IS NOT UNCOMMON, ALTHOUGH AT 10,964 HOURS THE CRACSDR 99ZZZX1696Seal · wornSEAL WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM.SDR 99ZZZX1804Curl · burntCURL ASSY HAS EXCESSIVE BURN IN SOME AREAS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM.SDR HEEA0016122Tube · mismanufacturedRECEIVING INSPECTION REVEALED: PISTON RING AREA OVERSIZED. PART OVERHAULED ON WO NR L1742524.SDR 99ZZZX1797Seal · wornSEAL WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM.SDR CA981019025Combustion Case · cracked(CAN) DURING ENGINE DISASSEMBLY THE COMBUSTION OUTER CASE WAS FOUND CRACKED IN THE REAR FLANGE AT THREE DIFFERENT LOCATIONS. THE CRACKS WERE FROM THE HOLES AT THE INNER DIAMETER AND CONTINUED TOWARDS THE OUTER CASE WALL. THE COMBUSTION OUTER CASE WAS REPLACESDR 99ZZZX902Housing · crackedHOUSING CRACKED AT 6 O'CLOCK STRUT. REMOVED AND REPLACED.SDR 98ZZZX3706Combustion Case · crackedDURING DAILY INSPECTION, ARM PIT AREA OF COMBUSTION CASE FOUND CRACKED, APPROXIMATELY 2.50 INCHES LONG. PILOTS NOTED APPROXIMATELY 20 DEGREES TOT INCREASE ON THAT ENGINE ON PRIOR FLIGHT. REPLACED PART.SDR 99ZZZX226Diffuser · damagedTEC TECH REP AT FACILITY TO C/W TU 202. SECOND STAGE NOZZLE INSTALLATION AFTER REMOVAL OF MODULES 2 AND 3 HEARD PIECES INSIDE ENGINE. UPON TEAR-DOWN OR SEPARATION OF MODULES 2 AND 3 FOUND DIFFUSER TO HAVE HOLE IN IT, 2 INCHES BY 6 INCHES. PARTS HAD LIBERATESDR HEEA0015996Housing · mismanufacturedRECEIVING INSPECTION REVEALED: UNABLE TO OBTAIN IMPELLER TO SHROUD HOUSING THROAT CLEARANCE. TRIED SHROUD HOUSING ON SEVERAL IMPELLERS. INSTALLED A DALLAS AIRMOTIVE OVERHAULED SHROUD HOUSING.SDR CA980916051Flame Tube · cracked(CAN) DURING A REGULAR SCHEDULED FUEL BURNER WIPE ON THE NR 5 COMBUSTION CAN, THE BURNER TOOL BRUSH WOULD NOT CONTACT THE FUEL NOZZLE. THE CAN WAS REMOVED AND THE FLAME TUBE DOME END, WHERE THE SWIRL VANE IS LOCATED, WAS FOUND CRACKED APART WAY AROUND THE CIRSDR 98ZZZX4113Rotor Assy · damagedFAILED SB LT101-72-10-0153 (Q-ROTOR INSPECTION). EXCESSIVE IBPT BLADE SHIFT. REPLACED WITH USED UNIT, CORRECTED PROBLEM. PART TC: 3,518.5.SDR 99ZZZX248Combustor · crackedCRACKED PORTION OF COMBUSTOR WORE THROUGH FUEL NOZZLE STEM CAUSING LEAKAGE WHICH CAUSED BURN-THROUGH OF COMBUSTION CASE.SDR CA980908001Case Gas Gen · cracked(CAN) AFTER POWER SECTION FAILED, ENGINE WAS BORESCOPED AND INTERNAL DAMAGE WARRANTED ENGINE REMOVAL. SUBSEQUENTLY, THE GAS GENERATOR CASE WAS FOUND CRACKED. PART TC: 3,086.SDR 98ZZZX4111Rotor Assy · damagedROTOR ASSY FAILED SB LT101-72-10-0153 (FAILED Q-ROTOR INSPECTION). EXCESSIVE IBPT BLADE SHIFT. REPLACED WITH USED UNIT, CORRECTED PROBLEM. PART TC: 1,730.6.SDR 98ZZZX4110Rotor Assy · damagedROTOR ASSY FAILED SB LT101-72-10-0153 (FAILED Q-ROTOR INSPECTION). EXCESSIVE IBPT BLADE SHIFT. REPLACED WITH USED UNIT, CORRECTED PROBLEM. PART TC: 4,011.2.SDR 99ZZZX1690Seal · wornSEAL WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM.SDR 98ZZZX3161Liner · crackedLINER HAS SEVERAL CRACKS ON LINER FINS. REMOVED FROM AIRCRAFT AND SENT FOR REPAIR.SDR 99ZZZX233Bearing · failedFORCED LANDING AT BRIGANTINE BAY, NJ. NR 1 BEARING FAILED. NO CHIP LIGHT. COMPRESSOR ROTOR DAMAGED. PARTS OF BEARING CAGE WERE LODGED IN OIL PORT. THIS MAY HAVE STOPPED OIL SUPPLY. NO SIGN OF OIL IN BEARING AREA OR ON COMPRESSOR ROTOR. NO BALL BEARINGS SDR 98ZZZX2571Combustion Can · crackedDURING A SCHEUDLED INSPECTION, THE NR 1 COMBUSTION CAN ASSY ON THE LEFT ENGINE WAS REJECTED DUE TO AN OUTER CASING BURN-THROUGH NEAR THE AFT END. UPON CAN REMOVAL, THE FLAME TUBE WAS FOUND CRACKED 360 DEGREES AND SEPARATED APPROXIMATELY 4 INCHES - 5 INCHES FRSDR 98ZZZX4112Rotor Assy · damagedFAILED SB LT101-72-10-0153 (FAILED Q-ROTOR INSPECTION). EXCESSIVE IBPT BLADE SHIFT. REPLACED WITH USED UNIT, CORRECTED PROBLEM. PART TC: 9,744.4.SDR CA980707069Seal · leaking(CAN) NR 1 SEAL LEAKING ON THE COMPRESSOR SECTION.SDR 99ZZZX1686Seal · wornSEAL WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM.SDR CA980707071Liner · cracked(CAN) HIGH ENGINE TEMP AT HIGH POWER SETTINGS. COMBUSTION LINER FOUND CRACKED AND UNZIPPED. ALSO, THE 3RD STAGE NOZZLE VANE DAMAGED. THERE WAS TRAILING EDGE EROSION ON 2 VANES. ON THE COMBUSTION LINER THERE WAS SEPARATION BETWEEN LINER END AND INNER LINER.SDR CA980707070Nozzle · damaged(CAN) HIGH ENGINE TEMP AND HIGH POWER SETTINGS. 3RD STAGE NOZZLE VANE DAMAGED WITH TRAILING EDGE EROSION ON 2 VANES. ALSO COMBUSTION LINER CRACKED AND UNZIPPED. PART TC: 32,000.SDR 98ZZZX3381Curl · burntCURL ASSY HAS EXCESSIVE BURN IN SOME AREAS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. CORE SCRAPPED LOCALLY.SDR 99ZZZX1699Seal · wornSEAL WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. PART TC: 6,926.0.SDR CA980513003Mount · cracked(CAN) DURING INSPECTION OF THE DIFFUSER, THERE WERE CRACKS FOUND IN THE STRUTS.SDR 98ZZZX3380Curl · burntCURL ASSY HAS EXCESSIVE BURN IN SOME AREAS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM.SDR 98ZZZX1526Combustion Liner · distortedUPON TEARDOWN OF THE ENGINE FOR AN UNRELATED ISSUE, IT WAS DISCOVERED THE COMBUSTION LINER WAS DISTORTED DUE TO BLOCKED COOLING HOLES. SUSPECT PLASMA COATING OVERSPRAY DURING OVERHAUL. INVESTIGATION IS ONGOING. SERVICE BULLETIN IS PENDING.SDR 98ZZZX2014Combustion Case · crackedHIGHER THAN NORMAL MGT INDICATION BY PILOT WAS REPORTED. INSPECTED AND PERFORMED TEST OF MEASURED GAS TEMPERATURE SYSTEM. NO ANOMALLY OBSERVED. UPON FURTHER INSPECTION FOUND SEAM WELDS AROUND FUEL NOZZLE BOSS CRACKED ALLOWING COOLING AIR TO ESCAPE.SDR 98ZZZX1246Combustion Case · failedDURING T/O, PILOT HEARD A 'POOF' SOUND. NOTICED THE COWLING PAINT DISCOLORED AND THE OIL FILLER DOOR OPEN. TAKEOFF ABORTED, AND ENG EMERG SHUTDOWN. INVEST DETERMINED THE LT ENG COMBUSTION CASE (PLENUM) HAD FAILED. ENG REMOVED FOR REPAIR, ENG COMPARTMENT DSDR TWAA9803402Chamber · crackedRDU - FLT 503 - RT ENGINE INJESTED BIRD ON ROTATION FOR TAKEOFF. EGT ROSE TO 620 DEGREES. N1 AND N2 STEADY. NO VIBRATION. REDUCED POWER AND RETURNED TO RDU. REPLACED ENGINE. S/D: EXAMINATION OF THE ENGINE SHOWED SEA GULL WAS INGESTED CAUSING STALLS. THSDR 98ZZZX1250Nozzle Shield · crackedUPON DISASSEMBLY OF TURBINE FOR REPAIR DUE TO BLOWING OIL OUT OF EXHAUST, FOUND DOME AND SHIELD HAD HEAVY OIL STAINS AND DOME PART SEPARATED FROM INNER BAND AND CRACKED. SUBMITTER SUGGESTED POSSIBLY DUE TO TIGHT FIT TO NEW NR 1 FLOATING DIAPHRAGM NOZZLE AND PSDR 98ZZZX2572Combustion Case · crackedFPI INSPECTION OF THIS CASE FOUND A 360 DEGREE CIRCUMFERENTIAL CRACK INDICATION ON THE FRONT FLANGE. EDDY CURRENT INSPECTION FOUND AN INDICATION AROUND 20 PERCENT OF THE CIRCUMFERENCE. P & W HAVE BEEN ASKED TO INVESTIGATE THIS CASE AS PROPAGATION OF THIS CRASDR HEEA0012381Combustion Liner · crackedRECEIVING INSPECTION REVEALED: CRACKED BEYOND SERVICEABLE LIMITS ON COMB. LINER INNER SKIRT. INSTALLED A DALLAS AIRMOTIVE OVERHAULED COMB. LINER.SDR 98ZZZX3827Seal Ring · failedSECONDARY DAMAGE DUE TO BEARING FAILURE. REPLACED WITH NEW UNIT, CORRECTED PROBLEM.SDR 98ZZZX559Diffuser Vane · failedDURING HOT SECTION INSPECTION, FOUND DIFFUSER VANE P/N 3102173-1 BROKEN IN SEVERAL PIECES LYING ON TOP OF THE OUTER TRANSITION LINER AND WEDGED BETWEEN THE COMPRESSOR HOUSING AND BOTTOM OF TRANSITION LINER. FURTHER INVESTIGATION REVEALED THAT RECOMMENDED GARRSDR 97ZZZX4851Plenum · failedENG FAILURE AT T/O. CREW HEARD A LOUD POP, THE RT ENG ITT TEMP ROSE AND FLAMES FROM THE RT ENG. UNABLE TO KILL THE ENG USING THE EMERG CUTOFF LEVER, LEVER WAS JAMMED. THE ENG WAS SHUT DOWN USING THE FIREWALL SOV. FIRE BOTTLE WAS DISCHARGED AND FIRE WAS PUTSDR AU971377Heat Shield · cracked(AUS) NO1 ENGINE HEAT SHIELD CRACKED.SDR HEEA0011599Valve · brokenDRAIN VALVE BROKE IN COMBUSTION CASE DRAIN BOSS. REPLACED WITH SERVICEABLE DRAIN VALVE. SCRAPPED BROKEN DRAIN VALVE.
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