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 DALA2019081214700Combust Chamber · crackedCRACK COMBUSTION SECTION PLATE INBOARD SIDE LOC AT 6 OCLOCK APROX ON ENGINE 1. REPAIRED AND INSTALLED COMBUSTION SECTION PLATE INBOARD SIDE LOC AT 6 OCLOCK APROX ON ENGINE 1 AS PER ERA 564620-14MA REV. ORIGINAL AND CFM56-5A ESM 71-00-01-440-024-0.SDR QEMY201906140001Bolt · wornWHEN THE ENGINE WAS GOING THROUGH ITS INSPECTION PROCESS, ALL THE BOLTS GOING THROUGH THE STAGE ONE NOZZLE SUPPORT INTO THE COMBUSTION CHAMBER WERE FOUND LOOSE AND WORN. TYPICALLY THE BOLTS ARE TIGHT AND OFTEN SHEAR WHEN DISASSEMBLY IS ATTEMPTED. LOOSE BOLSDR CA190609001Blades · damaged(CAN) DURING ROUTINE #1 ENGINE BORESCOPE INSPECTION, FOUND LP TURBINE BLADE DAMAGE BEYOND LIMITS. #1 ENGINE REPLACED. (TC# 20190609001)SDR CA190526001Combustion Liner · damaged(CAN) DURING CRUISE FLIGHT A LOUD HUMMING NOISE BECAME AUDIBLE. NO POWER LOSS OR ABNORMAL INDICATIONS OCCURRED AT THIS TIME ALTHOUGH IT WAS NOTED THAT TOT WAS A LITTLE HIGHER THAN NORMAL. THE PILOT LANDED THE AIRCRAFT AND DROPPED OFF PASSENGERS AND CONTINUED SDR CA190424006Liner · burned(CAN) L/H ENGINE COMBUSTION CHAMBER BORESCOPE INSPECTION. LINER SEGMENT BURN THROUGH DAMAGE, ENGINE TO BE REPLACED WITHIN 10 FC L/H ENGINE REPLACED (TC# 20190424006)SDR CA190412006Duct · cracked(CAN) DURING A REGULARLY SCHEDULED BORESCOPE INSPECTION, DAMAGE WAS NOTED ON THE LARGE EXIT DUCT (LED). UPON FURTHER INSPECTION, A CRACK WAS FOUND ON THE INNER LINING AND NUMEROUS CRACKS WERE FOUND ON THE OUTER LINING ALONG THE WELD SEAM. (TC# 20190412006)SDR CA190412007Engine · damaged(CAN) DURING A NON-SCHEDULED HOT SECTION INSPECTION, THE BOLTS (PART NUMBER MS9574-06) SECURING THE CONTAINMENT RING TO POWER TURBINE VANE RING AT FLANGE D WERE FOUND LOOSE. THE LOCKWIRE WAS INTACT, BUT THERE WAS EVIDENCE OF FRETTING FOUND UNDERNEATH THE HEADSSDR CA190327001Gas Generator · damaged(CAN) ENGINE RECEIVED FOR INVESTIGATION AND REPAIR AFTER THE OPERATOR REPORTED A CRACKED GAS GENERATOR CASE WHICH WAS FOUND AFTER A HIGH INTER-TURBINE TEMPERATURE INDICATION. (TC# 20190327001)SDR CA190627003Case · cracked(CAN) CREW REPORTED TO HAVE SMOG IN CABIN AND COCKPIT DURING CRUISE. AS PER MM, VISUAL INSPECTION OF BOTH ENGINE EXTERNAL OIL LEAKS CHECK C/O. NL SENSOR PACKING CONDITION CHECKED FOR OCM INSPECTION BUT NO ABNORMALITY FOUND. ALSO, AS PER MM CHECKED ENGINE SWITCSDR QEMY20190313211Combustion Case · crackedESN P550467 AT THE FACILITY AS THE INCOMING INSPECTION PROCESS. ONE OFF CRACK INDICATION AT BOLT HOLE 128 FWD FLANGE. CRACK INDICATION IS IN A CONTAINMENT VESSEL. FIRST TIME THIS DEFECT HAS BEEN SEEN IN THIS LOCATION. SFC 00859755 HAS BEEN SUBMITTED TO ADVISE SDR CA190308009Combust Chamber · damaged(CAN) COMBUSTOR INSPECTION PERFORMED ON BOTH ENGINES L/H ENGINE BSI PERFORMED WITH NO ABNORMAL FINDINGS R/H ENGINE BSI REVEALED DAMAGES BEYOND LIMITS.SDR CA190301005Case · cracked(CAN) ENGINE WAS REMOVED DUE TO HIGHER THAN NORMAL ITT. AN APPROXIMATELY 4 INCH CRACK WAS FOUND ADJACENT TO THE NO. 1 FUEL NOZZLE IN THE GAS GENERATOR CASE.SDR CA190319023Gear · failed(CAN) ENGINE WAS SENT FOR REPAIR WITH THE OPERATOR REPORTING OIL SYSTEM CONTAMINATION.SDR QMLA2019012319011Gas Generator · abnormalPILOT REPORTED LOSS OF FLI INDICATION ON APPROACH TO THE BASE. AFTER LANDING AND ROLLING THE THROTTLE TO IDLE, A FLASHING AMBER GOV LIGHT WAS ILLUMINATED. UPON INSPECTION OF THE T4 HARNESS , I FOUND THE T4 HARNESS WAS DAMAGED. AFTER GETTING A VIDEO SCOPE TOSDR CA190212017Shaft · broken(CAN) DESCRIPTION FROM THE DEFECT ENTERED IN OUR MAINTENANCE SYSTEM: WHILE DOING #1 ENGINE UNBALANCE ACQUISITION ON THE GROUND AS PER TASK 77-32-34-860-043-A FELT SOMETHING LET GO/SHUTTER THAN BOOM AND AUTO SHUTDOWN OF THE ENGINE. SUBTIANTIAL DAMAGES TO THE LPSDR VNAA20181112101None · noneON TAKEOFF ABOUT 600 FEET THE CREW OBSERVED A LARGE BIRD GO PAST AND HEARD A "THUMP" AND BEGAN TO RECEIVE ENGINE INDICATIONS THAT THE BIRD MADE IMPACT WITH THE RIGHT HAND ENGINE. THE AIRCRAFT RETURNED TO FIELD AND CURRENTLY UNDER MAINTENANCE INSPECTION. THE AISDR QEMY2018101600001Diffuser · damagedCOMBUSTOR DIFFUSER ASSEMBLY HAS MULTIPLE INDICATIONS NOTED IN FPI PROCESS UP TO 0.450" IN LENGTH. PART IS AN LLP AND REMOVED FROM SERVICE EARLY. PART TO BE REMOVED FROM SERVICE AS ITS AFFECTED BY SB72-0784.SDR CA181004007Engine · smoke(CAN) DURING TAXI, BLACK SMOKE WAS SEEN BY OTHER AIRCRAFT FOLLOWING BEHIND, COMING OUT FROM THE RIGHT HAND ENGINE. EVEN THOUGH ALL ENGINE PARAMETERS WERE NORMAL, THE ENGINE WAS PRECAUTIONARY SHUT DOWN AND AIRCRAFT WAS TAXIED BACK TO BASE.SDR CA180907017Filler · out of date(CAN) AS PER TLM TASK 05-00-03-800-001 (SUBTASK 05-00-03-870-004) MAXIMUM APPROVED LIVES FOR FILLERS P/N BRR19433 IS 4500 CYCLES. AS PER RECORDS AVAILABLE, THE ACTUAL LIFE OF QTY 3 ANNULUS FILLERS P/N BRR19433 IS 4867 CYCLES. THESE ANNULUS FILLERS HAVE EXCEESDR CA180907016Filler · out of date(CAN) AS PER TLM TASK 05-00-03-800-001 (SUBTASK 05-00-03-870-004), MAXIMUM APPROVED LIVES FOR ANNULUS FILLERS P/N BRR19433 IS 4500 CYCLES. AS PER RECORDS AVAILABLE, THE ACTUAL LIFE OF ANNULUS FILLERS P/N BRR19433 IS 4887 CYCLES. THIS ANNULUS FILLER HAS EXCEESDR CA180510013Duct · damaged(CAN) DURING ENGINE REPAIR, DAMAGE WAS NOTED ON THE LARGE EXIT DUCT (LED). THE LED HAD 818.5 HOURS AND 1806 CYCLES SINCE REPAIR. THE FOLLOWING WAS REPORTED BY THE REPAIR SHOP: SYMPTOMS: INSPECTION FINDING CRACKING AT OUTER SEAM WELD. CRACKING/BURNING AT SMSDR CA180510006Turbine Wheel · damaged(CAN) DURING AN INTERVENTION TO REPLACE THE T2 WHEEL AFFECTED BY SB 0849, T1 RUB WAS DETECTED AT THE 5-6 & 9 CLOCK ANGLE OF THE SHROUD. MEASUREMENTS WERE TAKEN OF THE DAMAGE BY THE SAFRAN TECH AND MYSELF AND FOUND BEYOND LIMITS. REPORT OF THE DAMAGE SENT TOSDR AALA20170702008Plug · blownTHE AIRCRAFT WAS GROUNDED. AT FL250 ON CLIMBOUT, RT ENGINE EGT WENT INTO RED ZONE WITH A HIGH EGT. DET FIRE ENG R EICAS MESSAGE. RT EGT INDICATED, THEN INDICATED A LOW EGT OF 346 DEG. THE FLIGHT DECLARED AN EMERGENCY AND RETURNED TO KMIA WITHOUT FURTHER INSDR JYDR20170628176Turbine Blades · missingPILOT RETURNED TO LANDING REPORTING NOISE AND VIBRATION IN NR 1 ENGINE. AFTER SEPARATING FREE TURBINE FROM ENGINE DISCOVERED ONE EACH SECOND STAGE N1 TURBINE BLADE MISSING FROM ROOT OUT. DOWNSTREAM DAMAGE IN FREE TURBINE. BOTH COMPRESSOR AND FREE TURBINE REPLASDR IPXA2017050916940Bracket · crackedINSPECTION TYPE: C-10, NR 1 ENGINE OTBD COMBUSTION SECTION ATTACH BRACKET TO BREATHER CRACKED. REMOVED & REPLACED THE BRACKET IAW SRM 51-40-02SDR ASAA2017040220336Combust Chamber · crackedNR 1 ENGINE BORESCOPE INSPECTION OF THE COMBUSTION CHAMBER. FOUND FIVE OUTER LINER PANELS THAT HAD ONE CONTINUOUS AXIAL CRACK WITH COOLING RIB 5 CRACKED THROUGH TO COLD SIDE JUST BELOW RT MAIN IGNITER. FOUND BURNED THROUGH AREA IN OUTER LINERS NR 4 & 5 PANELSSDR IAVA201704050001Combustion Case · crackedOUTER COMBUSTION CASE HAS A CRACK ABOUT 270 DEGREES AROUND FUEL NOZZLE BOSS.SDR EVCA201702261Combustion Case · crackedOUTER COMBUSTION CASE FOUND TO BE CRACKED WHILE PERFORMING CEB 72-3303SDR COEA2016070715917Landing · corrodedHEAVY CHECK COE/MINOR REPAIR. RT ENGINE OTBD LATERAL PANEL AFT LANDING HAS LEVEL 2 CORROSION. REPLACED WITH OEM PART.SDR COEA2016070714917Landing · corrodedHEAVY CHECK COE/MINOR REPAIR, RT ENGINE INBD LATERAL PANEL AFT LANDING HAS LEVEL 2 CORROSION. REPLACED LATERAL REBATE WITH OEM PART.SDR Z3EY2016040100155Hub · damagedTHIS ENGINE IS UNDERGOING MAINTENANCE. DURING ENGINE TEARDOWN THE T2 HUB COULD NOT BE REMOVED FROM THE T1 HUB DUE TO SEVERE DISTORTION OF THE T2 HUB SNOUT. SUSPECTED OIL LEAK FROM THE NR 4 BEARING AREA WHICH HAS ALLOWED OIL TO ACCUMULATE IN THE HPT, STAGE 1 SDR CA160226008Combust Chamber · cracked(CAN) COMBUSTION CAN FOUND CRACKED DURING 300 HR ENGINE INSPECTION. CRACK FOUND IN ARMPIT AREA EXTENDING INTO BRAZED PATCH.SDR CA160203023Burner Can · cracked(CAN) PILOT NOTED HIGHER THEN NORMAL TOT TEMPERATURES IN FLIGHT, PILOT LANDED AT THE HANGER AND UPON FURTHER INVESTIGATION FOUND RT BURNER CAN ARMPIT CRACKED.SDR HEER20150819592Case · leakingENGINE REMOVED 8-9-15 FOR TURBINE O/H. OUTER COMBUSTION CASE LEAKING AT ARMPITS WHEN PRESSURE TESTED. REPLACED WITH NEW COMBUSTION CASE.SDR CA150817020Combustion Case · cracked(CAN) CRACKED COMBUSTION CAN AROUND FUEL NOZZLE BOSS WELD.SDR CA150831010Duct · cracked(CAN) DURING A SCHEDULED HOT SECTION INSPECTION, THE LARGE EXIT DUCT (LED) WAS FOUND CRACKED IN MULTIPLE LOCATIONS ALONG THE OUTER SEAM WELD. THE TSO OF THE LED IS 1687.8 HOURS. THIS OPERATOR HAS HAD NUMEROUS PREVIOUS INSTANCES OF CRACKED LED`S.SDR VIB420150805001Vane · brokenTHIRD STAGE VANE AND SHROUD FAILURE IN NR 1 ENGINE.SDR CA150717004Combustion Liner · cracked(CAN) PILOT REPORTED THAT ITT STARTED TO CLIMB DURING RETURN LEG, PILOT REDUCED POWER TO KEEP ITT WITHIN A/C TEMP LIMITATIONS. UPON LANDING MAINTENANCE WAS BROUGHT OUT TO INSPECT AIRCRAFT, COMPRESSOR BLADES WERE BORESCOPE WITH NO ABNORMAL WEAR FOUND, COMPRESSOSDR CA150624003Case · cracked(CAN) THE ENG WAS REMOVED FROM SERVICE DUE TO AN INTERNAL OIL LEAK, CAUSING OIL SMELLS IN THE CABIN. THE OPERATOR INFORMED THAT THE OIL LEAK WAS NOTED ON THE REAR OF THE NR 5 BEARING VIA BORESCOPE OF THE P3 PLENUM. DURING INVESTIGATION, THE GAS GEN CASE WAS SDR CA150618008Combust Chamber · damaged(CAN) NUMBER 2 ENG WAS ISSUED A CNR ON MAY 5TH, 2015 WITH A 7 DAY COMPLIANCE TO INSPECT IAW SB 72-0239. AN ENG CHANGE WAS PLANNED MAY 12TH TO CARRY OUT INSPECTION OFF WING. THIS WAS DONE TO MINIMIZE THE GROUND TIME FOR THE ACFT. INSPECTION REVEALED EARLY SIGSDR CA141110012Bolt · damaged(CAN) DURING ROUTINE MAINTENANCE A PORTION OF BOLT 6924B1 WAS FOUND IN THE COWLING MISSING ITS HEAD (9 O CLOCK POSITION BOLT). THIS BOLT IS ONE OF 3 THAT LOCATE THE COMBUSTION CHAMBER IN THE COMBUSTION CASE ASSEMBLY. UPON REMOVAL OF THE 2 REMAINING BOLTS, ONE SDR CA141202032Combust Chamber · cracked(CAN) THERE HAVE OCCURRENCES OF FATIGUE CRACKING IN THE ENGINE GAS GENERATOR CASES DISCOVERED AT MAINTENANCE. NO SUCH EVENT HAS RESULTED IN ENGINE OPERABILITY ISSUE TO DATE. SERVICE BULLETIN SB35310 HAS BEEN PUBLISHED TO RECOMMEND PERIODIC, ON-WING INSPECTION SDR CA141110008Case · cracked(CAN) CRACKS OBSERVED ON SEVEN GAS GEN. CASES DURING SHOP INSPECTION.SDR FTYRN201410180001Combustion Case · crackedNOTED A HIGH TOT INDICATION ON APPROACH TO LAND AT HOME STATION. VISUALLY INSPECTED AND FOUND CRACK IN OUTER COMBUSTION CASE ASSEMBLY.SDR WI5R201410210001Seal · buckled(D-ILHB) PERFORMED CHECK 5 MAINTENANCE. DURING THE CUSTOMER'S FLIGHT TEST TO RETURN THE ACFT TO SERVICE, THE ENGINE WAS PURPOSELY SHUTDOWN TO TEST THE RELIGHT CAPABILITY. DURING THIS TESTING, THE N2 SPOOL COULD NOT BE TURNED BY WINDMILL OR STARTER ASSIST ANSDR 2014FA0000598Combustion Case · crackedPILOT STATED THE TOT HAS INCREASED 30+ DEGREES C FROM THE NORMAL CRUISE OPERATING TEMPERATURE. NO DEGRADATION IN POWER WAS MENTIONED OR NOTED. ON INSPECTION, FOUND A 2.75 INCH CRACK ON THE RT SIDE OF THE OUTER COMBUSTION CASE JUST BELOW THE SPLIT WELD LINE WSDR 2A6R201407110002Combustion Liner · crackedDURING 800 HOUR BORESCOPE INSPECTION OF ENG CRACKS WERE FOUND IN THE COMBUSTION CHAMBER LINER ASSEMBLY. REPLACED LINER ASSEMBLY WITH A NEW ONE.SDR 2A6R20140711001Combustion Liner · crackedDURING 800 HOUR BORESCOPE INSPECTION OF ENG CRACKS WERE FOUND IN THE COMBUSTION CHAMBER LINER ASSEMBLY. REPLACED LINER ASSEMBLY WITH A NEW ONE.SDR CA140627015Combust Chamber · cracked(CAN) AME NOTICED CRACK IN RT ARMPIT AREA OF OUTER COMBUSTION LINER DURING DAILY INSPECTION, PRIOR TO NEXT DAY`S FLYING. CRACK IS 2.0" LONG, RUNNING HORIZONTALLY INTO WIRE MESH PATCH AREA. CONFIRMED ON ENGINE RUN UP, BLOWING AIR. ENGINE PERFORMANCE CHECKS HSDR Y3AR2014FA0000403Combustion Case · leakingOUTER COMBUSTION CASE FOUND TO BE LEAKING AT WIRE MESH PATCH COVERING BUTT WELD DURING OUTER COMBUSTION CASE PRESSURE TEST.
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