JASC 5753
Service difficulty reports · 31,521
Reports filed under 5753 · Trailing Edge Flaps, 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 = '5753' 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 = '5753' 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 04FDEA01672Hinge · corrodedRIGHT AFT (FLAP SIDE) O/B FLAP I/B HINGE I/B PIVOT BORE HOLE CORRODED. CORROSION REMOVED AS PER CMM 20-11-02, PAGES 2 - 4. ORIGINAL DIAMETER = 1.094, FINAL DIAMETER = 1.128. COMPLIED WITH FEDEX EA 1-5750-76738, WINGS - LEFT AND RIGHT OUTBOARD FLAP - INBOARD HSDR 04FDEA01671Hinge · corrodedRIGHT AFT (FLAP SIDE) O/B FLAP I/B HINGE O/B ACTUATOR BORE SPOTFACE CORRODED. CORROSION REMOVED AS PER CMM 20-11-02 PAGES 2-4. ORIG THICKNESS=0.408, REMAINING THICKNESS=0.406, MATERIAL REMOVED=0.002. REPAIR CARRIED OUT AS PER FEDEX EA 1-5750-76738, WINGS - LESDR 04FDEA01670Hinge · corrodedRIGHT AFT (FLAP SIDE) O/B FLAP I/B HINGE O/B ACTUATOR BORE HOLE CORRODED. CORROSION REMOVED AS PER CMM 20-11-02, PAGES 2 - 4. ORIGINAL DIAMETER = 1.063, FINAL DIAMETER = 1.190. COMPLIED WITH FEDEX EA 1-5750-76738, WINGS - LT AND RT OUTBOARD FLAP - INBOARD HISDR 04FDEA01669Hinge · corrodedRIGHT AFT (FLAP SIDE) O/B FLAP I/B HINGE I/B ACTUATOR BORE SPOTFACE CORRODED. CORROSION REMOVED AS PER CMM 20-11-02 PAGES 2-4. ORIG THICKNESS=0.404, REMAINING THICKNESS=0.402, MATERIAL REMOVED=0.002. REPAIR CARRIED OUT AS PER FEDEX EA 1-5750-76738, WINGS - LESDR 04FDEA01668Hinge · corrodedRIGHT AFT (FLAP SIDE) O/B FLAP I/B HINGE I/B ACTUATOR BORE HOLE CORRODED. CORROSION REMOVED AS PER CMM 20-11-02, PAGES 2 - 4. ORIGINAL DIAMETER = 1.063, FINAL DIAMETER = 1.190. COMPLIED WITH FEDEX EA 1-5750-76738, WINGS - LEFT AND RIGHT OUTBOARD FLAP - INBOARSDR 04FDEA01667Hinge · corrodedRIGHT AFT (FLAP SIDE) O/B FLAP O/B HINGE O/B PIVOT BORE SPOTFACE CORRODED. CORROSION REMOVED AS PER CMM 20-11-02 PAGES 2-4. ORIG THICKNESS=0.500, REMAINING THICKNESS=0.498, MATERIAL REMOVED=0.002. REPAIR CARRIED OUT AS PER FEDEX EA 1-5750-76739, LEFT AND RIGHSDR 04FDEA01666Hinge · corrodedRIGHT AFT (FLAP SIDE) O/B FLAP O/B HINGE O/B PIVOT BORE HOLE CORRODED. CORROSION REMOVED AS PER CMM 20-11-02, PAGES 2 - 4. ORIGINAL DIAMETER = 1.063, FINAL DIAMETER = 1.096. COMPLIED WITH FEDEX EA 1-5750-76739, LEFT AND RIGHT OUTBOARD FLAP - OUTBOARD HINGE BSDR 04FDEA01665Hinge · corrodedRIGHT AFT (FLAP SIDE) O/B FLAP O/B HINGE I/B PIVOT BORE SPOTFACE CORRODED. CORROSION REMOVED AS PER CMM 20-11-02 PAGES 2-4. ORIG THICKNESS=0.490, REMAINING THICKNESS=0.488, MATERIAL REMOVED=0.002. REPAIR CARRIED OUT AS PER FEDEX EA 1-5750-76739, LEFT AND RIGSDR 04FDEA01664Hinge · corrodedRIGHT AFT (FLAP SIDE) O/B FLAP O/B HINGE I/B PIVOT BORE HOLE CORRODED. CORROSION REMOVED AS PER CMM 20-11-02, PAGES 2 - 4. ORIGINAL DIAMETER = 1.094, FINAL DIAMETER = 1.127. COMPLIED WITH FEDEX EA 1-5750-76739, LEFT AND RIGHT OUTBOARD FLAP - OUTBOARD HINGE BSDR 04FDEA01663Hinge · corrodedRIGHT AFT (FLAP SIDE) O/B FLAP O/B HINGE O/B ACTUATOR BORE SPOTFACE CORRODED. CORROSION REMOVED AS PER CMM 20-11-02 PAGES 2-4. ORIG THICKNESS=0.404, REMAINING THICKNESS=0.402, MATERIAL REMOVED=0.002. REPAIR CARRIED OUT AS PER FEDEX EA 1-5750-76739, LEFT AND RSDR 04FDEA01662Hinge · corrodedRIGHT AFT (FLAP SIDE) O/B FLAP O/B HINGE O/B ACTUATOR BORE HOLE CORRODED. CORROSION REMOVED AS PER CMM 20-11-02 PAGES 2-4. ORIG DIA 1.063, FINAL DIA 1.189. REPAIR CARRIED OUT AND FABRICATED BUSHING INSTALLED AS PER FEDEX EA 1-5750-76739, LEFT AND RIGHT OUTBOASDR 04FDEA01661Hinge · corrodedRIGHT AFT (FLAP SIDE) O/B FLAP O/B HINGE I/B ACTUATOR BORE SPOTFACE CORRODED. CORROSION REMOVED AS PER CMM 20-11-02 PAGES 2-4. ORIG THICKNESS=0.402, REMAINING THICKNESS=0.400, MATERIAL REMOVED=0.002. REPAIR CARRIED OUT AS PER FEDEX EA 1-5750-76739, LEFT AND SDR 04FDEA01660Hinge · corrodedRIGHT AFT (FLAP SIDE) O/B FLAP O/B HINGE I/B ACTUATOR BORE HOLE CORRODED. CORROSION REMOVED AS PER CMM 20-11-02 PAGES 2-4. ORIG DIA 1.063, FINAL DIA 1.189. REPAIR CARRIED OUT AND FABRICATED BUSHING INSTALLED AS PER FEDEX EA 1-5750-76739, LEFT AND RIGHT OUTBOASDR DL73S040541Flap Track · strippedRIGHT WING O/B FLAP O/B TRACK CARRIAGE STOP ATTACH HOLES WEAR: 2 HOLES THAT ATTACH MAIN FLAP CARRIAGE STOP TO O/B FLAP O/B TRACK ASSY WERE STRIPPED IN TRACK. O/S BOLTS WERE INSTALLED ER/A 090836-14, REVISION INITIAL.SDR DL73S040540Flap Track · strippedRIGHT WING O/B FLAP I/B TRACK CARRIAGE STOP ATTACH HOLES WEAR: 2 BOLT HOLES THAT ATTACH MAIN CARRIAGE STOP TO O/B FLAP I/B TRACK ASSY WERE STRIPPED IN TRACK. O/S BOLTS WERE INSTALLED ER/A 090835-14, REVISION INITIAL.SDR 04FDEA01651Hinge · gougedCOMPLY WITH EA 8-5750-78223, WINGS INBOARD FLAP, AFT HINGE ASSY, REWORK OF GOUGED ARC2517-2 STRAP. COMPLIED BY EA 8-5750-78223, WINGS INBOARD FLAP, AFT HINGE ASSY.SDR 04FDEA01643Support Bracket · corrodedCOMPLY WITH EA 8-5750-78222 WINGS RIGHT INBOARD FLAP TRACK MOUNTING/DRIVE SUPPORT BRACKET, P/N ARC2761-2. COMPLIED WITH EA 8-5750-78222 WINGS RIGHT INBOARD FLAP TRACK MOUNTING/DRIVE SUPPORT BRACKET, P/N ARC 2761-2.SDR 2004FA0000434Flap Track · misinstalledMECHANIC HEARD (POPPING) NOISE WHEN FLAPS WERE EXTENDED OR RETRACTED. FOUND THE UPPER FLAP TRACK HARDWARE WAS HITTING THE FLAP WELL CUT OUTS. THE BOLTS WERE INSTALLED FACING OB AT THE FACTORY. REVERSED HARDWARE AND PROBLEM WENT AWAY.SDR 04FDEA01640Tee Fitting · corrodedLEFT WING - I/B FLAP VANE O/B TEE FITTING BORE FOUND CORRODED. LEFT WING - I/B FLAP VANE O/B TEE FITTING BORES CORROSION REMOVED AS PER SRM 51-21-01 VOL 2. BORES DIAMETER: FWD=0.877 INCH, CENTER=0.878 INCH, AFT=0.8785 INCH. FPI CARRIED OUT, RESULT: NO COSDR 04FDEA01639Tee Fitting · corrodedRIGHT WING - I/B FLAP VANE O/B TEE FITTING BORE FOUND CORRODED. RIGHT WING - I/B FLAP VANE O/B TEE FITTING BORES CORROSION REMOVED PER SRM 51-21-01 VOL 2. BORES DIAMETER: FWD=0.8795 INCH, CENTER=0.8775 INCH, AFT=0.8790 INCH. FPI CARRIED OUT, RESULT: NO CORRSDR 04FDEA01638Fitting · corrodedRIGHT WING - I/B FLAP VANE I/B TEE FITTING BORE FOUND CORRODED. RIGHT WING - I/B FLAP VANE I/B TEE FITTING BORES CORROSION REMOVED PER SRM 51-21-01 VOL 2. BORES DIAMETER: FWD=0.879 INCH, CENTER=0.880 INCH, AFT=0.880 INCH. FPI CARRIED OUT, RESULT: NO CORROSDR 04FDEA01637Fitting · corrodedLEFT WING - I/B FLAP VANE I/B TEE FITTING BORE FOUND CORRODED. LEFT WING - I/B FLAP VANE I/B TEE FITTING BORES CORROSION REMOVED AS PER SRM 51-21-01 VOL 2. BORES DIAMETER: FWD=0.8765 INCH, CENTER=0.877 INCH, AFT=0.880 INCH. FPI CARRIED OUT, RESULT: NO COSDR 04FDEA01634Bracket · corrodedLEFT I/B FLAP IDLER ARM ATTACH FITTING IS CORRODED. REMOVED BUSHINGS FOR ACCESS IAW M/M 20-20-07, REMOVED CORROSION BY REAMING TO 1.079, OUT OF LIMITS IAW DWG ARC2761. REMOVED AND REPLACED FITTING IAW SRM 51-35-01 AND 51-31-01. LOCATED AND DRILLED 4EA MOUNTSDR USAA040293Skin · delaminatedPIT - FOUND SKIN AND CORE DELAMINATION 2.5 INCH BY 3 INCH AREA, RT OUTBOARD T/E FLAP, INBOARD END TRAILING EDGE. INSTALLED NEW CORE MATERIAL AND TOP DOUBLER, SEAL END, PER TYP REP 57-50-39A. (M)SDR 04FDEA01628Stop Fitting · crackedLEFT WING O/B FLAP STOP FITTINGS FOUND CRACKED. LT WING O/B FLAP STOP FITTING REMOVED AS PER SRM 51-31-01 VOL II AND INSTALLED NEW FITTING AT LEFT HAND WING OUTBOARD FLAP AS PER SRM 51-33-01 VOL II.SDR 04FDEA01627Stop Fitting · crackedRIGHT WING O/B FLAP STOP FITTINGS FOUND CRACKED. RT WING O/B FLAP REMOVED AND REPLACED, REFER TO SNRM 1134.SDR IXXA060445SFitting · corrodedDURING ROUTINE C CHECK, FOUND RIGHT WING OUTBOARD FLAP HINGE FITTING CORRODED AT STATION XF340. REPAIRED PER ALL APPLICABLE DATASDR SWAA041593Structure · delaminatedDURING SCHEDULED C2 CHECK, FOUND LT WING INBOARD FOREFLAP DELAMINATED. REMOVED AND REPLACED FOREFLAP PER MM.SDR ASAA0480471Vane · gougedOKC - DURING C-CHECK, FOUND LEFT WING OUTBOARD T/E FLAP VANE IS GOUGED ON INBOARD L/E. REMOVED DAMAGE. ADDED DOUBLER AND FILLER PER SRM 51-70-2. (M)SDR ASAA0480470Vane · puncturedFOUND DURING C-CHECK, RIGHT OUTBOARD FLAP T/E INBOARD FOREFLAP IS PUNCTURED ON L/E. REMOVED DAMAGED EDGES. ADDED DOUBLER AND FILLER PER SRM 53-03. (M)SDR UIEA200400101Bearing · migratedD-CHECK, DURING MAINTENANCE INSPECTION, ELONGATION DAMAGE WAS FOUND AT OB TRAILING EDGE FLAP TRACK NR 8 MOVABLE FAIRING ASSEMBLY HINGE FITTING LUGS. OVERSIZED THE BORES. DYE PENETRANT THE BORES TO ENSURE DEFECT FREE CONDITION. REFINISHED, INSTALLED ONE PIECSDR 04FDEA01622Hinge Bracket · corrodedCOMPLY WITH EA 8-5750-78220A WINGS RIGHT INBOARD FLAP OUTBOARD HINGE BRACKET SIDE BRACE REPAIR. COMPLIED WITH EA 8-5750-78220 A WINGS RIGHT INBOARD FLAP OUTBOARD HINGE BRACKET SIDE BRACE REPAIR.SDR IXXA0400088SSkin · damagedDURING A ROUTINE C CHECK INSPECTION, FOUND LT WING OTBD FLAP LWR PART SKIN HAS INTERIM REPAIR AT XF 320.00. REPAIRS WERE ACCOMPLISHED BY PERFORMING THE FOLLOWING REPAIRS IAW DC8 SRM 57-1-0 PAGE 1, DC8 SRM 57-7-1 FIG 4 PAGE 2 OF 2. REMOVED LOWER PLATING WITH SDR SWAA041563Structure · separatedLT WING OUTBOARD AFT FLAP T/E, SEPARATED. REPAIRED LT OUTBOARD AFT T/E FLAP PER SRM.SDR SWAA041570Structure · crackedDURING SCHEDULED A1 CHECK, FOUND LT WING OUTBOARD FORE FLAP L/E, CRACKED. REMOVED AND REPLACED LT FORE FLAP PER MM.SDR 04FDEA01598Hinge · corrodedLEFT WING - OUTBOARD FLAP FORWARD OUTBOARD HINGE, FOUND OUTBOARD ACTUATOR HOLE CORRODED. CORROSION REMOVED AND FOUND EXCEEDED LIMIT AS PER CMM 57-44-09 PG. 402-407. ORIG. DIAM.: 1.187, FINAL DIAM.: 1.222, REPAIR CARRIED-OUT AS PER FEDEX EA 1-5750-76724 - WINGSDR 04FDEA01597Hinge · corrodedLEFT WING - OUTBOARD FLAP FORWARD OUTBOARD HINGE, FOUND INBOARD ACTUATOR HOLE CORRODED. CORROSION REMOVED AND FOUND EXCEEDED LIMIT AS PER CMM 57-44-09 PG. 402-407 ORIG. DIAM.:1.187 FINAL DIAM.: 1.222. REPAIR CARRIED OUT AS PER FEDEX EA 1-5750-76724 WINGS - TRSDR 04FDEA01596Hinge · corrodedLT WING - OUTBOARD FLAP FORWARD OUTBOARD HINGE, FOUND SIDE LINK MATING SURFACE CORRODED. CORROSION REMOVED AS PER CMM 57-44-08 PAGES 402 - 407. ORIGINAL THICKNESS =0.446, MATERIAL REMOVED =0.003, REMAINING THICKNESS =0.443, WITHIN LIMIT AS PER DWG NR ARC0503.SDR 04FDEA01595Hinge · corrodedRIGHT WING - OUTBOARD FLAP FORWARD INBOARD HINGE, FOUND INBOARD ACTUATOR HOLE CORRODED. CORROSION REMOVED AND FOUND EXCEEDED LIMITS AS PER CMM 57-44-08 PAGES 402 - 407. ORIGINAL DIAMETER= 1.187, FINAL DIAMETER= 1.221. COMPLIED WITH FEDEX EA 1-5750-76725, WISDR 04FDEA01594Hinge · corrodedRIGHT WING - OUTBOARD FLAP FORWARD INBOARD HINGE, FOUND OUTBOARD ACTUATOR HOLE CORRODED. CORROSION REMOVED AND FOUND EXCEEDED LIMITS AS PER CMM 57-44-08 PAGES 402 - 407. ORIGINAL DIAMETER= 1.187, FINAL DIAMETER= 1.220. COMPLIED WITH FEDEX EA 1-5750-76725, WISDR 04FDEA01593Hinge · corrodedRIGHT WING - OUTBOARD FLAP FORWARD INBOARD HINGE, FOUND LOWER MATING SURFACE CORRODED. SURFACE CORROSION REMOVED AS PER CMM 57-44-08 PAGES 402 - 407. ORIGINAL THICKNESS= 0.464, MATERIAL REMOVED= 0.031, REMAINING THICKNESS= 0.433. COMPLIED WITH FEDEX EA 1-5750SDR CA040712009Block · corroded3 HINGE BLOCKS HAD SEVERE EXFOLIATION CORROSION OVER MUCH OF THEIR SURFACE. ONE BLOCK WAS SPLIT IN HALF AT THE LEADING EDGE. THE FLAP ITSELF HAD MINOR SURFACE CORROSION. THE LEFT FLAP WAS FOUND IN NORMAL CONDITION. THE HINGE BLOCKS WILL BE REPLACED WITH NESDR AWXA200400656Wedge · debondedMCN - MAJOR REPAIR - C-04 CHECK A DISBOND AREA WAS FOUND ON LOWER SURFACE OF RT OUTBOARD FLAP AT OUTBOARD END OF NR 3 SPOILER. MAINTENANCE CUT OUT DISBONDED AREA OF LOWER SURFACE OF RT OUTBOARD FLAP; FABRICATED A CORE FILLER AND REPAIR DOUBLER; BONDED REPAIR SDR AWXA200400652Skin · debondedMCN - MAJOR REPAIR - DURING C-04 CHECK A DISBOND AREA WAS FOUND ON THE LOWER SURFACE OF THE RT INBOARD FLAP 13.5 INCH FROM THE INBOARD END. MAINTENANCE CUT OUT DAMAGE ON LOWER SURFACE OF THE RT INBOARD FLAP; FABRICATED A CORE FILLER AND EXTERNAL DOUBLER; BONDSDR 04FDEA01592Hinge · corrodedRIGHT WING - OUTBOARD FLAP FORWARD INBOARD HINGE, FOUND SIDE LINK MATING SURFACE CORRODED. CORROSION REMOVED AS PER CMM 57-44-08 PAGES 402 - 407. ORIGINAL THICKNESS= 0.418, MATERIAL REMOVED= 0.002, REMAINING THICKNESS= 0.416. COMPLIED WITH FEDEX EA 1-5750-SDR 04FDEA01591Hinge · corrodedRIGHT WING - OUTBOARD FLAP FORWARD OUTBOARD HINGE, FOUND INBOARD ACTUATOR HOLE CORRODED. CORROSION REMOVED AS PER CMM 57-44-09 PAGES 402-407. ORIGINAL DIAMETER =1.188, FINAL DIAMETER =1.252. REPAIR CARRIED OUT AS PER FEDEX EA 1-5750-76721, WINGS - TRAILING EDSDR 04FDEA01590Hinge · corrodedRIGHT WING - OUTBOARD FLAP FORWARD OUTBOARD HINGE FOUND OUTBOARD ACTUATOR HOLE CORRODED. CORROSION REMOVED AND FOUND EXCEEDED LIMIT AS PER CMM 57-44-09 PAGES 402-407. ORIGINAL DIAMETER =1.188, FINAL DIAMETER =1.217. REPAIR CARRIED OUT AS PER FEDEX EA 1-5750-7SDR 04FDEA01589Hinge · corrodedRIGHT WING - OUTBOARD FLAP FORWARD OUTBOARD HINGE FOUND SIDE LINK MATING SURFACE CORRODED. CORROSION REMOVED AS PER CMM 57-44-08 PAGES 402 - 407. ORIGINAL THICKNESS =0.426, MATERIAL REMOVED =0.002, REMAINING THICKNESS =0.424, WITHIN LIMIT AS PER DWG NR ARC050SDR 04FDEA01584Panel · damagedCOMPLY WITH EA 8-5740-77422 WINGS - INBOARD FLAP, OVERSIZED HOLE IN ROLLER FITTING SUPPORT PANEL ASSY. COMPLIED WITH EA 8-5740-77422 WINGS - FLAP, OVERSIZED HOLE IN ROLLER FITTING SUPPORT PANEL ASSY.SDR 04FDEA01574Rub Strip · damagedRIGHT INBOARD FLAP OUTBOARD HINGE FITTING FWD FAIRING CHAFE STRIP IS DAMAGED. REMOVED AND REPLACED CHAFE STRIP IAW SRM 51-31-01 AT MAE.
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