JASC 5730
Service difficulty reports · 27,269
Reports filed under 5730 · Wing, Plate/Skin, 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 = '5730' 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 = '5730' 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 08FDEA03900Panel · chafedRIGHT WING LOWER L/E PANEL 616 HB IS CHAFED. BLENDED AREA IAW SRM 57-00-01; VOL I; FIG 1-A. ORIGINAL MATERIAL THICKNESS 0.090 IAW SRM 57-31-01; VOL III. MATERIAL LOSS 0.022. REMAINING THICKNESS 0.068 AND FOUND OUT OF LIMITS IAW SRM 57-00-01; VOL I. CUT OSDR 08FDEA03896Skin · wornFOUND ELONGATED HOLES ON RT WING BOTTOM SKIN AND PYLON SUPPORT BRACKET. REPAIR PERFORMED BY DRAWING R571-50532 (OVERSIZING THE HOLES INSTALL FREEZE PLUGS), APRROVED BY RAS/BAE/10078756/2008 ISS A AND EA 6-2900-123069.SDR 08FDEA03895Skin · damagedFOUND ELONGATED HOLES ON LT WING BOTTOM SKIN AND PYLON SUPPORT BRACKET. REPAIR PERFORMED BY DRAWING R571-50532 (OVERSIZING THE HOLES INSTALL FREEZE PLUGS), APRROVED BY RAS/BAE/10078756/2008 ISS A AND EA 6-2900-123069.SDR 08FDEA03893Skin · corrodedFOUND CORROSION ON TOP SKIN LOWER SURFACE ON OUTER SHROUD BOX , RIB 25-29 LT. REPAIR PERFORMED BY CUT OUT RIBS TO GAIN ACCESS, BLEND OUT THE CORROSION AND REPROTECT THE AREA AND INSTALL REPAIR ANGLES TO THE CUT RIBS IAW RAS/BAE/1007773/2008 ISS A, APPROVED BYSDR 08FDEA03887Skin · damagedFOUND OLD REPAIR AFT OF REAR SPAR AT RIB 9 (RAS/BAE/0081/2002 ISS C, UNREPAIRED CRACK WITH CRACK STOP HOLE IN BOTTOM SKIN). REPAIR PERFORMED BY NDT FOR CRACK FREE CONDITION (NO CRACK FOUND AFTER REMOVAL OF REPAIR PLATES) FOR EVERY HOLE AFFECTED BY THE REPAIR SDR 08FDEA03875Skin · crackedFOUND OLD REPAIR AFT OF REAR SPAR AT RIB 9 RAS/BAE/0081/2002 ISS C, UNREPAIRED CRACK WITH CRACK STOP HOLE IN BOTTOM SKIN. REPAIR PERFORMED BY DRILLING CRACK STOP HOLE, INSTALLING A CRACK STOP PLUG AND REPAIR PLATE IAW DRAWING R573-40199, APPROVED BY RAS/BAE/1SDR HNAA2009020100041Access Panel · corrodedRT WING ACCESS PANEL 622 AT (STRESS PANEL) HAS 2 HOLES CORRODED. CORROSION FOUND TO BE IN LIMIT PER RD8-57-1715. REPAIR HOLES IAW RD8-57-1715.SDR HNAA2009010900383Panel · corrodedDURING C-CHECK INSP, THE LT WING STRESS PANEL, 522AT, WAS FOUND TO HAVE CORROSION IN SOME OF THE SCREW COUNTER SINKS THAT WAS BEYOND ACCEPTABLE LIMITS. THE PANEL WAS REPLACED.SDR SWIA200820495Skin · corrodedDURING C-CHECK, LEFT WING PLANK AT WS 54 HOLE NR 1 CORRODED. REPAIRED PER REO.SDR SWIA200820494Skin · corrodedDURING C-CHECK, RIGHT WING PLANK AT WS 136 HOLE NR 8 CORRODED. REPAIRED PER REO.SDR SWIA200820493Skin · corrodedDURING C-CHECK, RIGHT WING PLANK AT WS54 HOLE NR 1 CORRODED. REPAIRED PER REO.SDR FDEA200809123854Skin · crackedLT WING L/E FOUND CRACK ON LOWER EXT SKIN L/E. REPAIRED AREA IAW SRM 57-10-00 FIG 68 SHT 2 VOL I.SDR 08FDEA03862Skin · corrodedLEFT WING FUEL TANK DOOR CUT OUT BETWEEN RIB 20 AND RIB 21 IS CORRODED. REMOVED CORROSION AND CHECKED LIMITS. ORIGINAL THICKNESS 0.600. MATERIAL REMOVED 0.002. REMAINING THICKNESS 0.598 AND IS FOUND TO BE WITHIN LIMITS IAW A310 SRM 57-20-12; PG 68; FIG 7A SDR 08FDEA03861Skin · corrodedLEFT WING FUEL TANK DOOR CUT OUT BETWEEN RIB 21 AND RIB 22 IS CORRODED. REMOVED CORROSION AND CHECKED LIMITS. ORIGINAL THICKNESS 0.600. MATERIAL REMOVED 0.002. REMAINING THICKNESS 0.598 AND IS FOUND TO BE WITHIN LIMITS IAW A310 SRM 57-20-12; PG 68; FIG 7A SDR 08FDEA03860Skin · corrodedLEFT WING FUEL TANK DOOR CUT OUT BETWEEN RIB 22 AND RIB 23 IS CORRODED. REMOVED CORROSION AND CHECKED LIMITS. ORIGINAL THICKNESS 0.600. MATERIAL REMOVED 0.003. REMAINING THICKNESS 0.597 AND IS FOUND TO BE WITHIN LIMITS IAW A310 SRM 57-20-12; PG 68; FIG 7A SDR 08FDEA03859Skin · corrodedLEFT WING FUEL TANK DOOR CUT OUT BETWEEN RIB 23 AND RIB 24 IS CORRODED. REMOVED CORROSION AND CHECKED LIMITS. ORIGINAL THICKNESS 0.600. MATERIAL REMOVED 0.003. REMAINING THICKNESS 0.597 AND IS FOUND TO BE WITHIN LIMITS IAW A310 SRM 57-20-12; PG 68; FIG 7A SDR 08FDEA03858Skin · corrodedLEFT WING FUEL TANK DOOR CUT OUT BETWEEN RIB 23 AND RIB 24 IS CORRODED. REMOVED CORROSION AND CHECKED LIMITS. ORIGINAL THICKNESS 0.600. MATERIAL REMOVED 0.003. REMAINING THICKNESS 0.597 AND IS FOUND TO BE WITHIN LIMITS IAW A310 SRM 57-20-12; PG 68; FIG 7A SDR 08FDEA03857Skin · corrodedLEFT WING FUEL TANK DOOR CUT OUT BETWEEN RIB 24 AND RIB 25 IN CORRODED. REMOVED CORROSION AND CHECKED LIMITS. ORIGINAL THICKNESS 0.276. MATERIAL REMOVED 0.002. REMAINING THICKNESS 0.274 AND IS FOUND TO BE WITHIN LIMITS IAW A310 SRM 57-20-12; PG 68; FIG 7A SDR 08FDEA03854Skin · crackedLT WING L/E FOUND CRACK ON LOWER EXT SKIN L/E.SDR 08FDEA03817Skin · corrodedLEFT WING FUEL TANK DOOR CUT OUT BETWEEN RIB 25 AND RIB 26 IS CORRODED. REMOVED CORROSION AND CHECKED LIMITS. ORIGINAL THICKNESS 0.276. REMOVED MATERIAL 0.003. REMAINING THICKNESS 0.273 AND IS FOUND TO BE WITHIN LIMITS IAW SRM 57-20-12, PG 68, FIG 7A AND SSDR 08FDEA03815Skin · dentedRT WING INBD FLAP FOUND DEEP DENT ON LOWER SKIN 0.25 INCH BY 0.25 INCH DEEP .066 INCH (SUSPECT CRACK ). REPAIRED DENT IAW SRM 57-00-01 FIG 4 SHT 2 VOL I.SDR UALA2013031301498Skin · corrodedLEFT & RIGHT OUTER WING TOP SKIN AT REFUEL PORT CUTOUT FLANGE HAVE PITTING CORROSION. REPAIR PER EVA-71896 AND REO-L01103.SDR 08FDEA03808Skin · chafedRIGHT WING LEADING EDGE LOWER SECTION AT STA XORS 372, INBOARD OF ANTI-ICE TELESCOPIC DUCT, FOUND WITH CHAFE MARKS. CHAFE MARK SMOOTHED AND REPAIR CARRIED OUT AS PER EA 1-5740-122551, THIS REPAIR IS CLASSIFIED AS MAJOR PER GMM 6-2-100.SDR 08FDEA03807Skin · chafedRIGHT WING LEADING EDGE LOWER SECTION AT APPROX STA XORS 392, OUTBOARD OF ANTI-ICE TELESCOPIC DUCT, FOUND WITH CHAFE MARKS. REPAIR CARRIED OUT AS PER EA 1-5740-122551, THIS REPAIR IS CLASSIFIED AS MAJOR PER GMM 6-2-100.SDR HNAA2009012500019Panel · corrodedSTRESS PANEL 623 AT, 522AT, 521AT, 523AT CORROSION FOUND COUNTER SINK HOLES. STRESS PANEL 623AT, 523AT CORROSION REMOVED AND RETREATED 622AT,522 AT OUT OFF LIMITS. R&R PANEL. 512 AT NEED BUSHING INSTALLATION.SDR ASM2008F00004Access Panel · leakingDURING WALK AROUND CAPTAIN FOUND A FUEL LEAK UNDER THE RIGHT WING AND ENGINE FUEL DRAIN. MAINT CONFIRMED THE FUEL LEAK THEN REMOVED AND REPLACED MAIN TANK RIGHT WING ACCESS PANEL SEAL. 112N51012, DOOR ASSY ON RIGHT SIDE AND TESTED IAW MM 28-11-11M ALL CORRECTSDR 08FDEA03778Doubler · crackedRIGHT WING COMP PROBE PANEL LAND IS CRACKED; NR 2 TANK. REMOVED & REPLACED NR 8 STRINGER IN REF TO EA 8-5720-117035. LEAK CHECK COMPLIED WITH ON NON-ROUTINE N00533 / 41533.SDR 08FDEA03775Panel · chafedLEFT WING LOWER T/E PANEL 575 FB LAND AND AIRFRAME MATING SURFACE IS CHAFFED AND HAS BARE METAL. REMOVED CAMLOCKS AND SEAL TO FOM IAW SRM 51-40-00. FABRICATED A REPAIR DOUBLER IAW EA NR 6-5720-123627. PREPPED PANEL SKIN AND DOUBLER FOR BONDING IAW SRM 51-21SDR 08FDEA03772Doubler · crackedLT WING NR 2 TANK INBD COMP PROBE PANEL LAND HAS A CRACK AT THE ATTACH BOLT HOLE. REMOVED & REPLACED NR 8 STRINGER IN REF TO EA 8-5720-117035 LEAK CHECK COMPLIED WITH ON NON-ROUTINE N00534 / 41534.SDR KCSA081449Skin · corrodedLT WING UPPER SKIN CORRODED AT FRONT SPAR, WS 380 TO 450. (K)SDR KCSA081479Skin · corrodedLT WING UPPER SKIN CORRODED AT FRONT SPAR, WS 380 TO 450. (K)SDR DHLA2008745670Skin · corrodedRT WING REAR SPAR SECTION LOWER SKIN WITH CORROSION BETWEEN WS 470 TO WS 480. REPAIRED RT WING LOWER SKIN AT REAR SPAR AND STIFFENER 4 FROM WS 472 TO WS 491 IAW COOPESA EO COO-2-57-324-08.SDR 2008UALA05623Skin · dentedLEFT WING UPPER SURFACE SKIN DENTED OUTBOARD END BETWEEN WS 780 AND WS 810. *S/D* MAJOR REPAIR ACCOMPLISHED. REMOVED DAMAGE AND INSTALLED CORE DOUBLER REPAIR.SDR 2008FA0000623Skin · crackedFOUND CRACK IN UPPER WING SKIN AS DESCRIBED IN SB MEB08-3. CRACK EXTENDS 4 INCHES FORE AND AFT PARALLEL TO LT WING MAIN LANDING GEAR ASIDE BRACE WING RIB NR 502210451 OB FLANGE. CRACK IS APPROXIMATELY CENTERED IN MLG WHEEL WELL OPENING. CRACK WAS FOUND VISUALSDR 08FDEA03731Skin · crackedRIGHT WING L/E SKIN IS CRACKED AT THE NR 3 SLAT CENTER TRACK CUT-OUT. REMOVED 2 EA PANELS TO FOM IAW SRM 51-31-01. REMOVED OLD REPAIR DOUBLER IAW SRM 51-35-02. CUT PUT DAMAGED AREAS. FABRICATED IAW SRM 57-10-00. ALODINED & PRIMED IAW SRM 51-21-01. INSTALSDR 08FDEA03712Skin · corrodedRT WING UPPER SURFACE, LIGHT CORROSION ON UPPER SKIN BEVER TAIL. REPAIRED AREA IAW EA 8-5710-120494.SDR 2008UALA05572Skin · corrodedRT WING TOP SKIN AT REFUEL PORT CUTOUT FLANGE HAVE PITTING CORROSION. REPAIRED PER UA-EVA-71896 AND REO-L01103. RECEIVED RAS-BAE-1008098-2008. TO BE REINSPECTED AT 123,500 CYCLES. CURRENT PTC 13082. INSPECTION INTERVAL AND METHOD TO BE DETERMINED BY AIRBUS ONSDR 08FDEA03655Skin · corrodedRT WING TOP SURFACE REAR SPAR AREA APPROX WS 230-345, 3 SPOTS OF CORROSION ON TOP OF WING. REPAIR CARRIED OUT BY BLENDING OUT IAW B757-200 SRM 57-20-01 TABLE 1 AND EA F- 5730-124309. REPAIR IS CLASSIFIED AS MAJOR PER GMM 6-2-100 CRITERIA.SDR UPS08M53271Splice · crackedINSPECTION TYPE:1C RT WING L/E SKIN SPLICE STRAP XFS 791 CRACKED. REMOVED, FABRICATED, AND INSTALLED SPLICE STRAP IAW DWG ARB 3954 AND MD-11 SRM 51-35-01, 51-33-01.SDR FDEA200808293635Skin · wornRT WING L/E, FOUND DEEP WEAR ON SKIN AND PANEL LOWER SIDE L/E AT STA XORS 264. REPAIR AREA IAW SRM 57-00-01 VOL 1 SHT 3 FIG 1A.SDR UPS08M53270Skin · crackedINSPECTION TYPE:1C RT WING L/E SKIN STRAP XFS 901 CRACKED. REMOVED, FABRICATED, AND INSTALLED SKIN STRAP IAW DWG ARB3954 AND MD-11 SRM 51-33-01, 51-31-01.SDR 08FDEA03635Skin · wornRT WING L/E, FOUND DEEP WEAR ON SKIN AND PANEL LOWER SIDE L/E AT STA XORS 264. REPAIR IAW SRM 57-10-00 VOL 1 FIG 15 .SDR 08FDEA03622Skin · crackedLEFT WING OUTBD TRAILING EDGE PANEL 525 AT INNER SKIN IS CRACKED. CRACKED SKIN ON THE LEADING EDGE OF PANEL 525 AT REQUIRES AN SRM DOUBLER. FABRICATED THE DOUBLER IAW SRM 57-10-00 VOL I. INSTALLED DOUBLER IAW SRM 51-31-01 VOL II & SRM 57-10-00 VOL I. APPLIEDSDR UPS08M53272Splice · crackedINSPECTION TYPE:1C LEFT WING L/E SKIN SPLICE XFS 791 CRACKED. REMOVED, FABRICATED, AND INSTALLED SKIN SPLICE STRAP IAW DWG ARB3954 AND MD-11 SRM 51-31-01, 51-33-01.SDR UALA2008111305469Skin Panel · crackedLT WING SKIN PANEL HAS 10 INCH CRACK AND DELAMINATION. SUSPECT MOISTURE CONTAMINATION. REMOVED PANEL AND ROUTED TO SHOP FOR REPAIR. RE-INSTALLED REPAIRED PANEL. AC OK FOR SERVICE.SDR UIEA200800298Panel · crackedRT WING FORWARD LEADING EDGE PANEL HAS A 2.5" CRACK LOCATED AT ILES 208.81 AND IS 18.25" FROM TOP EDGE OF PANEL. PERMANENT REPAIR ACCOMPLISHED AS PER B747-300 SRM 57-30-04 FIG. 2, SHEETS 1,2 & 3. ALSO, REFERENCE ATLAS AIR EO NO. 4757A459.SDR UIE2008F00028Panel · crackedR/H WING UPPER SURFACE LEADING EDGE PANEL HAS A 3" CRACK LOCATED AT ILES 818.5 AND 9" FROM LEADING EDGE OF PANEL. ALSO, REFERENCE ATLAS AIR EO NO. 4757A458. UIEA200800297.SDR 2008UALA05469Skin · delaminatedLT WING SKIN PANEL HAS 10 INCH CRACK AND DELAMINATION.SDR 08FDEA03574Panel · crackedRIGHT SIDE WING BOX REAR SPAR BOTTOM PANEL HOLE "U" HAS A CRACK INDICATION AT THE 6 O'CLOCK POSITION FOUND WITH BHEC. REPAIRED THE RIGHT SIDE WING BOX REAR SPAR BOTTOM PANEL HOLE "U" IAW EA 6-5710-117013 "FUSELAGE - AD 2005 -23 - 08 - S/B A300-57-0649R06 FRAMSDR UPS08M53264Skin · crackedINSPECTION TYPE:1C RT WING FIXED L/E TELESCOPE CUTOUT CRACKED ON INBOARD CORNER UPPER SURFACE. REMOVED DAMAGE, FABRICATED AND INSTALLED REPAIR DOUBLER IAW MD-11 SRM 57-10-00 FIG 43 SHEET 2, 51-33-01, 51-21-01.
Back to JASC 5730