JASC 5410
Service difficulty reports · 4,119
Reports filed under 5410 · Nacelle/Pylon, Main Frame, 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 = '5410' 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 = '5410' 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 EIAA2000097Frame · damagedHAECO-HKG - C6/D-CHECK - NR 3 PYLON AFT BULKHEAD LT CHORD FOUND FASTENER HOLE OVERSIZED. PLUGGED OVERSIZED HOLE, NDT INSPECTED AND OVERSIZE FASTENER INSTALLED PER BOEING MESSAGE EVR-HKG-00-00026H-00027H AND HAECO REPAIR SCHEME R-54-53-34319. (X)SDR UPS00232512Web · crackedINSPECTION TYPE:C+SI, ENG NR 2 SUSPECT CRACK ON RT WEB AT BS 1387 OVER HORIZ FIREWALL. CRACKED WEB REPLACED IAW DRAWING REF 65-17555.SDR UPS00232481Web · crackedINSPECTION TYPE:C+SI, NR 2 ENG SUSPECT CRACK ON LT WEB AT BS 1387 OVER HORIZONTAL FIREWALL. WEB REPAIRED IAW DRAWING NR 65-17555.SDR QXEA0001182Frame · corrodedYYC- RIGHT HAND NACELLE MAIN LANDING GEAR FRAME SURFACE UNDER RETRACTION ACTUATOR FITTING HAS CORROSION. REPAIRED IAW HORIZON EA 9-54-159B.SDR C2XA00IA101Frame · crackedDURING CONTINENTAL EXPRESS AIRLINES C-CHECK, FOUND RIGHT ENGINE NACELLE, FRAME NR 1 CRACKED. REMOVED AND REPLACED RIGHT ENGINE NACELLE FRAME NR 1 IAW CONTINENTAL EXPRESS EC 5410-01034. AIRCRAFT APPROVED FOR RETURN TO SERVICE. (M)SDR AU000264Angle · cracked(AUS) ANGLE LOCATED ON THE RH OUTBOARD FORWARD SIDE OF THE HORSECOLLARASSEMBLY CRACKED. CRACK LENGTH APPROXIMATELY 38MM (1.5IN).SDR MALA000248Duct · chafedLT ENGINE EXHAUST DUCT WEARING HOLE THRU COWL. (AFT OUTBOARD SIDE) MX REMOVED AND REPLACED RT ENGINE EXHAUST DUCT EA0031, SECTION CHECKS GOOD.SDR 00FDEA00435Fitting · wornDURING A/C P-F CONV AT AERO WEAR WAS FOUND ON UPPER PORTION OF THRUST FITTING. PROBABLY CAUSED BY CONTACT WITH NR 2 ENG PRE-COOLER. THE AMOUNT OF WEAR IS NOT COVERED BY SRM 54-00. REPAIR REQUIRES INSTALL OF TWO NESTED REPAIR ANGLES FROM 0.063 THICK 6AL-4V ASDR 20000503SH007Frame · crackedFLUORESCENT PENETRANT INSPECTION INDICATED A CRACK IN RIGHT NACELLE FORWARD FRAME NR 1. POSSIBLE CAUSE IS STILL UNDETERMINED. WOULD SUSPECT ENGINE TORQUE AND VIBRATION TO BE POSSIBLE CONTRIBUTING FACTORS. SB 102-54-0036 IS BEING INCORPORATED. (X)SDR 20000424SH003Frame · crackedFLUORESCENT PENETRANT INSPECTION INDICATED A CRACK IN RIGHT NACELLE FORWARD FRAME NR 1. POSSIBLE CAUSE IS STILL UNDETERMINED. WOULD SUSPECT ENGINE TORQUE AND VIBRATION TO BE CONTRIBUTING FACTORS. SB 120-54-0036 IS BEING INCORPORATED. (X)SDR 20000424SH005Frame · crackedFLUORESCENT PENETRANT INSPECTION INDICATED CRACKS IN LT NACELLE FORWARD NR 1 FRAME. POSSIBLE CAUSE IS STILL UNDETERMINED. SUBMITTER SUSPECTED ENGINE TORQUE AND VIBRATION TO BE POSSIBLE CONTRIBUTING FACTORS. (X)SDR 20000424SH004Frame · crackedFLUORESCENT PENETRANT INSPECTION INDICATED CRACKS IN RT NACELLE FORWARD NR 1 FRAME. POSSIBLE CAUSE IS STILL UNDETERMINED. WOULD SUSPECT ENGINE TORQUE AND VIBRATION TO BE POSSIBLE CONTRIBUTING FACTORS. (X)SDR 2000ZZZX626Beam · crackedTHE LEFT ENGINE AFT BEAM ASSEMBLY IS CRACKED. CRACK IS AT THE OUTBOARD BEAM ASSEMBLY (P/N 5054030-13) ATTACHMENT POINT AT THE TOP SIDE, AFT END, EXTENDING 1.1250 INCHES. THE OUTBOARD BEAM ASSEMBLY (5054030-13) ALSO HAD 3 RIVETS WITH HEADS MISSING ON THE INBOSDR C2XA00IA057Frame · crackedDURING CONTINENTAL EXPRESS AIRLINES C-CHECK, FOUND LT NACELLE NR 1 FRAME CRACKED. REMOVED AND REPLACED NR 1 FRAME IAW EC5410-01034. AIRCRAFT APPROVED FOR RETURN TO SERVICE. ACTT: 20,855.7 HOURS. ACTC: 26,652. (X)SDR C2XA00IA056Frame · crackedDURING CONTINENTAL EXPRESS AIRLINES C-CHECK, FOUND RT NACELLE, NR 1 FRAME CRACKED. REMOVED AND REPLACED NR 1 FRAME IAW EC5410-01034. AIRCRAFT APPROVED FOR RETURN TO SERVICE. ACTT: 20,855.7 HOURS. ACTC: 26,652. (X)SDR MALA000165Nacelle · damagedA/C WAS GUIDED INTO BELT LOADER BY RAMP AGENT AT THE GATE IN STL, NR 4 ENGINE NACELLE HAS HOLE IN BOTTOM FRONT OF NACELLE. MX INSPECTED NR 4 ENGINE, FOUND DAMAGED AREA AT 6 O'CLOCK POSITION. FOUND SMALL DENT IN NOSE COWL, TEAR IN METAL BEHIND NOSE COWL, AND SDR 20000412SH006Frame · crackedRIGHT NACELLE NR 1 FRAME CRACKED AT THE ENGINE TORQUE TUBE MOUNT AREA. ENGINE VIBRATION IS A POSSIBLE CAUSE. FRAME IS BEING REPLACED WITH 4 EACH NEW FRAMES, P/N 120-540036-004, WHICH HAS A ''BEEFED'' UP WEB AREA AT THE MOUNTING POINT. (X)SDR RRXA003798Attach Angle · crackedDURING A MAINTENANCE VISIT FOUND CRACK DAMAGE TO NR 4 PYLON I/B FWD ATTACH ANGLE, DAMAGE EXCEEDED LIMITATIONS IAW DC-8 SRM. REMOVED DAMAGE, TREATED AREA IAW DC-8 SRM 51-1-8. FABRICATED PART AND INSTALLED IAW DC-8 SRM 51-1-21 & 51-3-0 & 51-1-7 & 51-1-20D.SDR C2XA00IA032Frame · crackedDURING CONTINENTAL EXPRESS AIRLINES C-CHECK, FOUND RT NACELLE NR 1 FRAME CRACKED. REMOVED AND REPLACED NR 1 FRAME IAW EC5410-01034. AIRCRAFT APPROVED FOR RETURN TO SERVICE. (M)SDR TWAA0002010Web · crackedDURING OP 16 MAINT CHECK, NR 2 PYLON HAD A CRACK IN THE WEB 9.5 INCHES OTBD OF THE FUSELAGE SKIN, TOP OF PYLON AT STA 1038. REPLACED PART PER DAC PRINT INSTALLATION 9915501, INSTALLED RIB 9915501-2.SDR ASOA00013Frame · crackedDURING C-CHECK, FOUND RIGHT SIDE FRAME NR 2 INBOARD SIDE CLEAT CRACKED. MAINTENANCE REPLACED CRACKED CLEAT IAW EMB 120 SRM 51-40-02. AIRCRAFT RETURNED TO SERVICE. (M)SDR 20000406SH002Frame · crackedLEFT NACELLE FRAME 1 CRACKED OUTBOARD OF TORQUE MOUNT. ENGINE VIBRATION/TORSION. SB 120-54-0036 IS BEING INCORPORATED. (X)SDR 20000406SH001Frame · crackedRIGHT NACELLE FRAME 1 CRACKED OUTBOARD OF TORQUE MOUNT. ENGINE VIBRATION/TORSION. SB 120-54-0036 IS BEING INCORPORATED. (X)SDR C2XA00IA006Frame · crackedDURING C-CHECK FOUND RIGHT ENGINE NACELLE FRAME NR 1 CRACKED. REMOVED AND REPLACED RIGHT ENGINE NACELLE FRAME NR 1 IAW CONTINENTAL EXPRESS ENGINEERING CHANGE REPAIR AUTHORIZATION EC5410-01034. AIRCRAFT APPROVED FOR RETURN TO SERVICE. ACTT: 20,754.3 HOURS. SDR A6WA0000003Link · chafedNR 1 PYLON TO WING LINK CHAFED, TOP END OUTBOARD SIDE. BLENDED AND POLISHED ABOVE CHAFFED AREA IN PYLON TO WING OUTBOARD LINK, AREA DETAILED VISUAL AND NDT. NO DEFECTS NOTED. BLENDED AREA ON PANEL 454BL THAT WAS RUBBING ON LINK, REF BARA/AVR/1211/99. (M)SDR 2000ZZZX79Lug · crackedA THOROUGH CRACK WAS FOUND AT AFT ENGINE MOUNT LOWER SPAR LUG OF THE NR 3 PYLON.SDR CALA9901662Stiffener · crackedINSPECTION FOUND A 1 INCH CRACK IN NR 3 ENGINE COWL NR 10 STIFFENER. THE STIFFENER WAS REMOVED AND REPLACED IAW SRM 51-20-1 AND 51-30-2.SDR CALA9901637Support · crackedINSPECTION FOUND A 1 INCH CRACK IN SECOND FRAME SUPPORT FROM AFT OF LT FORWARD NR 2 ENGINE COWL. THE FRAME SUPPORT WAS REMOVED AND A NEW FRAME SUPPORT WAS INSTALLED IAW SRM 51-30-2, 51-30-1, AND 51-10-1.SDR 2000ZZZX116Frame · crackedLEFT NACELLE UPPER FRAME NR 1 WAS FOUND CRACKED AT THE ENGINE TORQUE TUBE MOUNTING AREA. EMB SB 120-54-0036 IS BEING INCORPORATED WHICH PROVIDES A NEW FRAME WITH A BEEFED UP WEB AREA AT THE TORQUE TUBE MOUNTING AREA.SDR 2000ZZZX115Frame · crackedRIGHT NACELLE UPPER FRAME NR 1 WAS FOUND CRACKED AT THE ENGINE TORQUE TUBE MOUNTING AREA. EMB SB 120-54-0036 IS BEING INCORPORATED WHICH PROVIDES A NEW FRAME WITH A BEEFED UP WEB AREA AT THE TORQUE TUBE MOUNTING AREA.SDR 2000ZZZX78Frame · crackedC-CHECK INSPECTION REVEALED RIGHT NACELLE FRAME NR 1 CRACKED AT OUTBOARD TORQUE TUBE BOLT HOLE RISERS.SDR ASOA99133Frame · crackedDURING INSPECTION, FOUND LEFT NACELLE FRAME NR 1 CRACKED. MAINTENANCE REPAIRED CRACK IAW EO 120-54-0034 AND S/B 120-54-0036. OPERATIONAL CHECKS WERE GOOD. AIRCRAFT RETURNED TO SERVICE. (M)SDR ASOA99132Frame · crackedDURING INSPECTION, FOUND RIGHT NACELLE FRAME NR 1 CRACKED. MAINTENANCE REPAIRED CRACK IAW EO 120-54-0034 AND S/B 120-54-0036. OPERATIONAL CHECKS WERE GOOD. AIRCRAFT RETURNED TO SERVICE. (M)SDR EIA990250Structure · damagedHKG - DURING C/D CHECK, NR 1 PYLON HAS EVIDENCE OF OVERHEAT DAMAGE, PARTIALLY REPAIRED PREVIOUSLY. NR 1 PYLON SIDE FRAMES REPLACED AT NAC STATION 183 L/R, 210 L/R, 236 L/R, 253 L/R. STIFFENERS REPLACED NR 1 NAC STATION 221-265 LEFT, NR 2 STATION 193-221 L/R,SDR CA990719010Support · corroded(CAN) RIGHT SUPPORT ASSY WAS REMOVED FOR ACCESS FOR ANOTHER JOB, BUT IT WAS THEN DISCOVERED THAT THE REAR FACE WHICH BUTTS AGAINST THE FORWARD FIRE WALL WAS FOUND TO BE CORRODED BEYOND LIMITS. THIS AREA IS NOT VISIBLE DURING NORMAL MAINTENANCE.SDR 99ZZZX2104Frame · crackedDURING ROUTINE MAINTENANCE CHECKS, CRACKS WERE FOUND ON BOTH ENGINE NACELLE NR 1 FRAMES. ON THE LT FRAME, THE CRACK IS LOCATED ON THE LOWER SIDE OF THE STIFFENING WEB BETWEEN THE TOP OUTBOARD MOUNTING BOLT HOLE AND THE OUTBOARD EDGE OF THE FRAME. ON THE RT FSDR 99ZZZX861Frame · crackedDURING ROUTINE MAINTENANCE CHECKS, A CRACK WAS FOUND ON BOTH ENGINE NACELLES' FRAME 1. THE CRACK IS LOCATED ON THE LOWER SIDE OF THE STIFFENING WEB BETWEEN THE TOP OUTBOARD MOUNTING BOLT HOLE AND THE OUTBOARD EDGE OF THE FRAME. RECOMMEND REPLACING BOTH FRAMESDR AU990036Web · cracked(AUS) LEFT ENGINE PYLON TOP WEB CRACKED AT THE REAR OUTBOARD CORNER OF ONE WEB CUT-OUT. CRACK LENGTH 9.53 MM (0.375 INCH). FOUND DURING EDDY CURRENT INSPECTION.SDR UF6A981213Duct · crackedSBN - NR 2 OUTBOARD MOD 2 NACA DUCT HAS CRACK ON LEADING EDGE APPROXIMATELY 4 INCHES LONG. MAINTENANCE STOP DRILLED CRACK AND PERFORMED NDT INSPECTION. NO FURTHER DEFECTS NOTED. FABRICATED TWO DOUBLERS FROM ALCLAD 2024-T3 .063 INCH AND INSTALLED PER ENGINEESDR UF6A981212Duct · crackedSBN - MOD NR 2 NACA DUCT IS CRACKED ON OUTBOARD IGNITER PANEL ON NR 1 SIDE. MAINTENANCE STOP DRILLED CRACK AND PERFORMED NDT INSPECTION. NO FURTHER DEFECTS NOTED. FABRICATED TWO DOUBLERS FROM ALCLAD 2024-T3 .063 INCH AND INSTALLED PER ENGINEERING REPORT NR SDR 98ZZZX4748Cowl · damagedENGINE WAS RUN WITH AFT ENGINE COWL OPEN DAMAGING PAINT (BURNT) ON TAILBOOM. THERE ARE NO PRECAUTIONS IN THE FLIGHT MANUAL. THE ONLY PRECAUTION IN THE MM IS AT THE END OF 71-01-00 (ENGINE R & R). IT STATES 'OPERATION OF ENGINE WITH COWL OPEN OR UNLATCHED IS SDR 98ZZZX4143Frame · chafedON THE LEFT AND RIGHT ENGINE NACELLE'S, THE LEFT HAND, FORWARD HALF FRAME SHOWS SIGNS OF CHAFING. THIS CHAFING OCCURRED WHERE THE COWLING DOOR MADE CONTACT WITH THE FRAME. THERE IS NO ANY PROTECTION WHICH PREVENTS THE TWO SURFACES FROM RUBBING TOGETHER. THESDR 98ZZZX4059Channel · chafedDURING PHASE INSP, A CHAFED SPOT WAS NOTICED ON THE INBD UPPER ACCESS DOOR ON ENGINE COWL. INVEST REVEALED IT HAD BEEN IN CONTACT WITH ENG MOUNT CHANNEL ON THE FWD SIDE. FOUND DAMAGE TO BOTH SIDES WHICH NECESSITATED REPLACING BOTH FWD CHANNELS. UPON INSP OFSDR 98ZZZX4058Channel · chafedDURING PHASE INSP, A CHAFED SPOT WAS NOTICED ON THE INBD UPPER ACCESS DOOR ON ENGINE COWL. INVEST REVEALED IT HAD BEEN IN CONTACT WITH ENG MOUNT CHANNEL ON THE FWD SIDE. FOUND DAMAGE TO BOTH SIDES WHICH NECESSITATED REPLACING BOTH FWD CHANNELS. UPON INSP OFSDR C2XA98IA378Frame · crackedIAH - DURING C-CHECK INSPECTION, FOUND RIGHT AFT MAIN LANDING GEAR DOOR INBOARD FORWARD HINGE POINT, AFT NACELLE HALF FRAME CRACKED. MAINTENANCE REMOVED AND REPLACED THE HALF FRAME IAW EMB-120 SRM 51-40-02. THE AIRCRAFT WAS APPROVED FOR RETURN TO SERVICE. (SDR AU981209Fitting · corroded(AUS) LEFT PYLON CONTAINED EXFOLIATION CORROSION ON THE UPPER SURFACES OF THE UPPER WEB OF THE TORQUE BOX ADJACENT TO THE UPPER LINK ATTACHMENT BEAM OUTBOARD OF AND RUNNING UNDER THE STRUT FITTING. CORROSION HAD PENETRATED TO A DEPTH OF 1.778 MM (0.070 INCH) SDR AU981208Fitting · corroded(AUS) RIGHT PYLON CONTAINED EXFOLIATION CORROSION ON THE UPPER SURFACES OF THE UPPER WEB OF THE TORQUE BOX ADJACENT TO THE UPPER LINK ATTACHMENT BEAM EITHER SIDE OF AND RUNNING UNDER THE FORWARD UPPER STRUT FITTING. CORROSION HAD PENETRATED THROUGH THE WEB WISDR 98ZZZX2968Frame · crackedDURING PERFORMANCE OF C-CHECK INSPECTION TASK ON NR 1 FRAME OF ENGINE NACELLE, CRACKS VISUALLY DETECTED AROUND THE MOUNT HOLES FOR THE TORQUE MOUNT. THE LT MOUNT'S CRACKS WERE FOUND ON THE INBD AND OTBD SIDES. THE INBD SIDE WAS CRACKED IN ONE LOCATION APPROXSDR 98ZZZX2967Frame · crackedDURING PERFORMANCE OF C-CHECK INSPECTION TASKS ON THE NR 1 FRAME OF THE ENGINE NACELLE, CRACKS WERE VISUALLY DETECTED ON THE LT ENGINE'S FRAME IN THE WEB OTBD OF THE MOUNT HOLES FOR THE INBD SIDE FORWARD TORQUE MOUNT AND ON THE RT ENGINE'S FRAME ON THE OTBD SISDR 98ZZZX2969Frame · crackedDURING PERFORMANCE OF C-CHECK INSP, TASKS ON NR 1 FRAME OF ENG NACELLE, CRACKS VISUALLY DETECTED IN AREA OF MOUNT HOLES FOR TORQUE MOUNT. LT MOUNT'S CRACKS FOUND ON INBD AND OTBD SIDES. INBD SIDE CRACKED IN 2 LOCATIONS APPROX .5 INCH APART AND .25 INCH AND 5
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