N921AT
Service difficulty reports · 236
Matched to this aircraft by N-number and event date, checked against the reported serial number, make and model. 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 n_number = 'N921AT' AND registry_match = 'registration' 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 n_number = 'N921AT' AND registry_match = 'registration' 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 DALA2026100905577Tail Cone · puncturedTAIL CONE DECAL DAMAGED & PUNCTURED, REPLACED THE DECAL IAW MM 52-20. (9388108) (AIRCRAFT GROUNDED).SDR DALA2026081004611Sign · looseFWD CABIN EXIT SIGN LOOSE. SECURED FWD CABIN EXIT SIGN IAW AMM 33-51. (8801968) AIRCRAFT WAS GROUNDED.SDR DALA2026080604546Target · looseGALLEY DOOR TARGET LOOSE, RESECURED TARGET IAW AMM 52-70-01. (1739326) (AIRCRAFT GROUNDED).SDR DALA2026050502825Girt Bar · noneMAIN BOARDING DOOR PARTIALLY OPENED W/GIRT BAR STILL IN FLOOR FITTINGS. REATTACHED SLIDE PACK TO COVER. CKS NORMAL (8322872) (AIRCRAFT GROUNDED)SDR DALA2026031001644Not Reported · not reportedSHIP 9577 ER/A 631995-14AD REV ORIGINAL REQUIRES STAGE 2 & 3 DTA APPROVAL. REPAIR ACCOMPLISHMENT PER ER/A 631995-14AD (1480809)SDR DALA2025072405585Battery Pack · inoperativeSHIP 9577 DURING SVC CHECK FOUND EMERGENCY LIGHT ABOVE R1 WOULD COME ON THEN IMMEDIATELY EXTINGUISH. CORRECTIVE ACTION: REMOVED AND REPLACED BATTERY ASSY B5-259. REF B717 AMM 33-51-04. OPS CHECK GOOD (7321200)SDR DALA2025061104458Structure · damagedAIRCRAFT 9577, AFTER REMOVAL OF RH LEADING EDGE SLAT SEALS, ELONGATION ON FASTENER HOLES AND MISDRILLS ON COUNTERSINKS WERE FOUND ON SLAT 1 AND 5. CORRECTIVE ACTION: RH LEADING EDGE SLAT SEALS, ELONGATION ON FASTENER HOLES AND MISDRILLS ON COUNTERSINKS WERE FOSDR DALA2025061104457Seal · elongatedAIRCRAFT 9577, AFTER REMOVAL OF LH LEADING EDGE SLAT SEALS, ELONGATION ON FASTENER HOLES AND MISDRILLS ON COUNTERSINKS WERE FOUND ON SLAT 1 TO 5. CORRECTIVE ACTION: ELONGATION ON FASTENER HOLES AND MISDRILLS ON COUNTERSINKS ON SLAT 1 TO 5 WERE REPAIRED PER PRISDR DALA2025061104455Skin · damagedAIRCRAFT 9577, VERT STAB LEADING EDGE SKIN, B717 - REPAIR, RII IN REF PER AMDS 5530-01048-03. CORRECTIVE ACTION: VERT STAB LEADING EDGE SKIN, B717 - REPAIR, RII WAS ACCOMPLISHED PER AMDS 5530-01048-03. (LP 1014363)SDR DALA2025060804359Fastener · looseARCRAFT 9577, LOOSE FASTENERS ON RH/LH LEADING EDGE SPLICE (MOVABLE), STA ZFS=52.267 AT VERTICAL STABILIZER. VERTICAL LEADING EDGE (MOVABLE) ON STA ZFS = 52.267 AT VERTICAL STABILIZER WAS REPAIRED PER SERVICE GENERAL DRAWING SG95550001 REV. B IN ACORDANCE TO SDR DALA2025060704354Attach Angle · crackedAIRCRAFT 9577, CRACK ON ANGLE ATTACHET WING BOX TO UPPER SKIN PANEL BTW STA Y=710 TO STA Y=720 -X=44. CORRECTIVE ACTION: ANGLE ATTACHET WING BOX TO UPPER SKIN PANEL BTW STA Y=710 TO STA Y=720 -X=44 WAS REPAIRED PER ER/A 625883-14AD REV ORIG, SECTION I: PERMANESDR DALA2025060704353Structure · crackedAIRCRAFT 9577, AFTER REMOVED METALLIC SEAL ALONG UPPER EDGES OF APRON HINGE AT LH PYLON, CRACK ON FWD UPPER CORNER SKIN OF APRON WAS FOUND. CORRECTIVE ACTION: FWD UPPER CORNER SKIN OF APRON LH PYLON WAS REPAIRED PER B717-200 SRM 54-50-01-2R REPAIR 2. (LP 10039SDR DALA2025060604341Access Panel · corrodedSHIP 9577 IN REFERENCE NRC S/N:00617: CORROSION OUT OF LIMITS ON FUEL ACCESS PLATE COUNTERSINK 620DT PER B717-200 SRM 57-10-01-2R PROCEDURE 2. DOOR CAN NOT BE REPAIRED UNDER CONDITION I OR II. CORRECTIVE ACTION: REPAIRED PER B717 AMM 57-11-02- 300-801 (0998316SDR DALA2025060604340Skin · dentedSHIP 9577 INITIAL INSPECTION: DENT ON EXTERNAL FUSELAGE SKIN ON STA Y=213 BTW LONG= 18L AND LONG=19L AT LOWER FUSELAGE. CORRECTIVE ACTION: REPAIRED PER ER/A 625868-14 REV ORIGINAL (0996949)SDR DALA2025060604335Tab · delaminatedSHIP 9577 IN REFERENCE TO NRC 00033: AFTER REMOVAL PAINT ON ELEVATOR CONTROL TAB (LH) AREAS WERE FOUND DELAMINATED. CORRECTIVE ACTION: REPAIRED PER 625939. (0994012)SDR DALA2025060604326Support Fitting · wornSHIP 9577 WEAR ON SUPPORT FITTING AND BUSHING ALSO RUSTED HARDWERE OF SPRING RELEASE MECHANISM AT TAILCONE. REPAIRED PER B717-200 SRM 51-41-01-0G (0988292)SDR DALA2025060604322Frame · crackedSHIP 9577 IN REFERENCE TO NRC 00291; CRACK ON FRAME CANT "CAP" STA Y=1178 AND PROJECTION OF LONGERON 17R AT AFT ACCESSORIES COMPARTMENT. CORRECTIVE ACTION: REPAIRED PER B-717-200 SRM 53-00-00-2R REP.1 (0983728)SDR DALA2025060604321Cargo Track · corrodedSHIP 9577 IN REFERENCE NRC 269: CORROSION OUT OF LIMITS (ORIGINAL THICKNESS 0.060 IN AND REMAINING THICKNESS 0.005 IN IN FLANGE AREA) OF AFT CARGO TIE TRACK LOCATED BETWEEN Y= 813 AND Y= 1022; L-27L L-28L. CORRECTIVE ACTION: REPAIRED PER B717-200 SRM 51-41-05-SDR DALA2025100807323Fitting · corrodedCORROSION ON COUNTERWEIGHT FITTING OF ELEVATOR LH. COUNTERWEIGHT FITTING OF ELEVATOR LT WAS REPAIRED PER ERA 592404-14TR REV ORIGINAL SECTION I. (0977129)SDR DALA2025052704028Door Frame · crackedSHIP 9577 CRACKED LOWER RH AND LH JAMB REPAIR REINFORCEMENTS AT NLG WHEEL WELL. CORRECTIVE ACTION: LOWER RH AND LH JAMB REPAIR REINFORCEMENTS AT NLG WHEEL WELL PER ER/A 495600-14MA (0973673)SDR DALA2025052203938Fastener · looseSHIP 9577 AFTER INSPECTION ON PREVIOUS REPAIR DOUBLER ON FUSELAGE SKIN STA Y= 1037 BTW LONG 13 RH TO LONG 14RH WERE FOUND LOOSE FASTENERS ON REPAIR DOUBLER AND NEAR TO REAPOIR DOUBLER. CORRECTIVE ACTION: DAMAGED AREA REPAIRED PER ER/A 14-568647 (0975044)SDR DALA2025052203941Hinge Fitting · corrodedSHIP 9577 AFTER SEALANT REMOVAL CORROSION WAS FOUND ON ( OTBD LOWER ATTACHING BOLT ) MID FLAP HINGE FITTING STA XW= 251.6 AT RH WING. CORRECTIVE ACTION: STUDS WERE REPLACED AND CENTER WING FLAP HINGE WAS REPLACED BY SERVICEABLE CENTER WING FLAP HINGE PER B717 SDR DALA2025052203935Floor Support · corrodedSHIP 9577 AFTER REMOVED CORROSION, GALLEY FLOOR SUPPORT FITTING STA Y=218 - 200 AND STA X= -11 WAS MEASURED AND EVALUATED AND WAS FOUND OUT OF LIMITS. CORRECTIVE ACTION: DAMAGED AREA REPAIRED PER CORROSION LEVEL 2, SUPPORT FITTING ON STA Y=218 - 200 STA X= -11SDR DALA2025052203937Hinge Fitting · wornSHIP 9577 ELONGATED BORE OF INB LUG AND WEAR ON BUSHINGS AND HARDWARE OF OUTBD FLAP HINGE FITTING STA XRS 383 AT RH WING. CORRECTIVE ACTION: DAMAGED AREA REPAIRED PER ERA 625998-14 REV ORIGINAL AND PRI 625998-14 REV 2. (0969698)SDR DALA2025052203933Frame · corrodedSHIP 9577 IN REFERENCE TO NRC 00217: OUT OF LIMITS AFTER BLENDED OUT FRAME STA Y=889 BTWEN L29L TO L29R. CORRECTIVE ACTION: DAMAGED AREA REPAIRED PER B717-200 SRM 53-20-07-2R PROCEDURE 3 REPAIR 3. (0969661)SDR DALA2025052203932Seat Track · corrodedSHIP 9577 CORROSION OUT OF LIMITS PASSENGER CABIN SEAT TRACK (X=- 44; Y= 200 - 256). CROWN WITH ORIGINAL THICKNESS IS 0.115IN. REMAINING THICKNESS IS 0.070IN. CORRECTIVE ACTION: DAMAGED AREA REPAIRED PER B-717-200 SRM 53-20-52 (0969326)SDR DALA2025052203931Window Frame · crackedSHIP 9577 CRACKS 3 EA AROUND FASTENER HOLE OF THE LH COCKPIT WINDOW RETAINER STA Y=148. CORRECTIVE ACTION: DAMAGED AREA REPAIRED PER ER/A 626178 -14 REV ORIGINAL (0968634)SDR DALA2025052203930Seat Track · corrodedSHIP 9577 IN REFERENCE TO NRC 385 WIP 4 CORROSION ON SEAT TRACK X=-22 BTW STA Y=200 TO STA Y=200 TO STA Y=256 ,STA Y=275, AT PASSENGER CABIN, ORIGINAL THICKNESS ON CROWN IS 0.115IN AND THE MINIMUN REMAINING THICKNESS IS 0.046IN; AND WITH ORIGINAL THICKNESS ON SDR DALA2025051503781Cusp Web · crackedCUSP WEB LOCATED BETWEEN Y=237 AND Y=256; X=-44 AND X=-58 WAS FOUND CRACKED. SUMMARY OF NRC 00817: CUSP WEB LOCATED BETWEEN Y=237 AND Y=256; X=-44 AND X=-58 WAS REPAIRED PER B717-200 SRM 53-00-55-2R PROCEDURE 4, REPAIR 4, FIGURE 215. (LP #0966489)SDR DALA2025051403729Seat Track · corrodedCORROSION ON SEAT TRACK X=22 Y=200 TO Y= 210 (ON SEAT TRACK LOWER FLANGES). ORIGINAL THICKNESS BOTTOM IS 0.100 IN AND MINIMUM REMAINING THICKNESS IS 0.030 IN THEREFORE AREA IS OUT OF LIMITS PER B717 SRM 53-20-52-1A PROCEDURE 1 PAR 4 FIG 101. AND DC-MD/BOEING NSDR DALA2025051403728Structure · corroded-AD- CORROSION WAS FOUND ON BORES 31, 33, ALSO ON HOLE #10 (VERTICAL AND TRANSVERSAL). SUMMARY OF NRC 667: CORROSION LEVEL 2. BORES 10, 31, AND 33 OF HORIZONTAL STABILIZER BARREL NUTS WERE REPAIRED PER PRI 625941-14 REV 1 & ER/A 625941-14AD REV ORIG. SECTION ISDR DALA2025051303689Longeron · corrodedCORROSION OUT OF LIMIT ON LONGERON 26L BTW STA Y=962/967 AND BTW STA Y=974/988 AT AFT CARGO COMPARTMENT. SUMMARY OF NRC 00792: CORROSION LEVEL 2. LONGERON 26L BTW STA Y= 962/967 AND BTW STA Y=974/988 WAS REPAIRED PER B717-200 SRM 53-00-05-2R REPAIR 3 PAR 4 A (SDR DALA2025051303687Cusp Web · crackedCUSP WEB LOCATED BETWEEN Y=218 AND Y=237; X=-44 AND X=-58 WAS FOUND CRACKED. SUMMARY OF NRC 00816: CUSP WEB BETWEEN STA Y=218 AND Y=237; STA X=-44 AND X=-58, WAS REPAIRED PER B717-200 SRM 53-00-55-2R PROCEDURE 4 REPAIR 4 PAR 5 FIGURE 21. (LP #0963051)SDR DALA2025051303686Cusp Web · corrodedCORROSION OUT LIMITS ON PASSENGER CABIN CUSP WEB LOCATED Y=427 - 446; X=-56. SUMMARY OF NRC 00769: CORROSION LEVEL 2. PASSENGER CABIN CUSP WEB LOCATED Y=427 - 446; X=-56 WAS REPAIRED PER B717-200 SRM 53-00-55-2R PROCEDURE 4 REP 4 FIG 211 CONFIG. 7017. (LP #096SDR DALA2025051203680Hinge Fitting · corrodedFRETTING CORROSION (UT) THICKNESS MEASUREMENT WAS ACCOMPLISHED PLATE RH OUTBD ON VERTICAL STABILIZER SPAR HINGE. FITTINGS WITH ORIGINAL THICKNESS =0.250" AND MINIMUM REMAINING THICKNESS IS 0.212" THEREFORE IT IS OUT LIMITS. SUMMARY OF NRC 00820: CORROSION LEVESDR DALA2025051203679Skin · crackedCRACKS ON FUSELAGE SKIN ON STA Y=1087 AND LONG 14R AT AFT FUSELAGE. SUMMARY OF NRC 00025: FUSELAGE SKIN ON STA Y=1087 AND LONG 14R AT AFT FUSELAGE WAS REPAIRED PER ER/A 625728-14 REV ORIG SECTION I: PERMANENT REPAIR AND PER PRI 625728-14 REV 3. TIME CONTROLLEDSDR DALA2025051203678Cable · wornTAILCONE EMERGENCY RELEASE HANDLE CABLE ASSEMBLY WAS FOUND WORN. THIS COULD PREVENT THE PROPER OPERATION OF THE ESCAPE PATH AND IT IS NOT IN COMPLIANCE WITH 14 CFR PART 121.703. SUMMARY OF NRC 00623: RELEASE HANDLE CABLE ASSEMBLY WAS REPLACED PER B717 AMM 20-0SDR DALA2025050803559Cusp Web · corrodedCORROSION ON PASSENGER CABIN CUSP WEB PREVIOUS REPAIR LOCATED Y=541 - 580; X=-56. SUMMARY OF NRC 00768: CORROSION LEVEL 2. PREVIOUS REPAIR LOCATED ON PASSENGER CABIN CUSP WEB STA Y=541 - 580; X=-56, WAS REPLACED PER B717-200 SRM 53-00-55-2R PROCEDURE 4 PAR 5, SDR DALA2025050803558Cusp Web · corrodedCORROSION OUT LIMITS ON PASSENGER CABIN CUSP WEB PREVIOUS REPAIR LOCATED Y=256; X=-56. SUMMARY OF NRC 00770: PREVIOUS REPAIR ON CUSP WEB LOCATED Y=256; X=-56 AT PASSENGER CABIN WAS REPLACED DUE CORROSION LEVEL 2 PER B717-200 SRM 53-00-55-2R PROCEDURE 4 PAR 5, SDR DALA2025050603512Floor Support · corrodedCORROSION ON PASSENGER CABIN FLOOR SUPPORTS (2 EA) BETWEEN Y=148 - 200, X=7 AND X=-7. SUMMARY OF NRC 00637: CORROSION LEVEL 2. FLOOR SUPPORTS (2 EA) BETWEEN Y=148 - 200, X=7 AND X=-7, WERE FABRICATED PER DWG 9936534 REV BW, AND REPLACED PER B717-200 SRM 51-41-SDR DALA2025050503409Cargo Track · corrodedCORROSION ON TIE TRACK STA 898.5-954 L27R TO L28R IN AFT CARGO COMPARTMENT. ORIGINAL THICKNESS 0.060IN AND MINIMUM REMAINING THICKNESS 0.05IN; FLANGE AREA IS OUT OF LIMITS. SUMMARY OF NRC 00771: CORROSION LEVEL 2. AFT CARGO COMPARTMENT TIE TRACK STA 898.5-954 SDR DALA2025050503408Floor Support · corrodedCORROSION PER (UT) MEASUREMENT THICKNESS WAS ACCOMPLISHED PER DC/MD/BOEING NDT SPM, PART 4 04- 00-07, PAR 4 FIG 9, FLOORS SUPPORT AT LAVATORIES ZONES: [1 EA; BETWEEN Y=1053 - 1022, X=-44]. WITH ORIGINAL THICKNESS =0.125" AND MINIMUM REMAINING THICKNESS =0.062"SDR DALA2025050503407Cusp Web · corrodedCORROSION ON PASSENGER CABIN CUSP WEB PREVIOUS REPAIR LOCATED Y=503 - 522; X=-56. SUMMARY OF NRC 00767: CORROSION LEVEL 2. PREVIOUS REPAIR LOCATED Y=503 - 522; X=-56 ON PASSENGER CABIN CUSP WAS REPLACED PER B717-200 SRM 53-00-55-2R PROCEDURE 4. (LP #0945857)SDR DALA2025050103360Cusp Web · corrodedCORROSION IN REFERENCE TO (UT) MEASUREMENT THICKNESS WAS ACCOMPLISHED ON CUSP MEMBRANE WEB X=58, STA Y=340, STA Y=868 C PAX (LH). ORIGINAL THICKNESS IS 0.020IN AND MINIMUM REMAINING THICKNESS IS 0.012IN., THEREFORE IT IS OUT LIMITS PER B717-200 SRM 53-00-55-1ASDR DALA2025043003319Cusp Web · corrodedCORROSION ON PASSENGER CABIN CUSP WEB PREVIOUS REPAIR LOCATED Y=484 - 503; X=-56. SUMMARY OF NRC 00766: CORROSION LEVEL 2. PASSENGER CABIN CUSP WEB PREVIOUS REPAIR LOCATED Y=484 - 503; X=-56 WAS REPLACED PER B717-200 SRM 53-00-55-2R, REPAIR 4. (LP #0940885)SDR DALA2025043003318Cusp Web · corrodedCORROSION ON PASSENGER CABIN CUSP WEB PREVIOUS REPAIR LOCATED Y=465 - 484; X=-56. SUMMARY OF NRC 00765: CORROSION LEVEL 2. PASSENGER CABIN CUSP WEB PREVIOUS REPAIR LOCATED Y=465 - 484; X=-56 WAS REPLACED PER B717-200 SRM 53-00-55-2R, REPAIR 4. (LP #0940877)SDR DALA2025043003316Cusp Web · corrodedCORROSION ON PASSENGER CABIN CUSP WEB PREVIOUS REPAIR LOCATED Y=446 - 465; X=-56. SUMMARY OF NRC 00764: CORROSION LEVEL 2. CABIN CUSP WEB (PREVIOUS REPAIR) LOCATED Y=446 - 465; X=-56 WAS REPLACED PER B717-200 SRM 53-00-55-2R REPAIR 4. (LP #0940714)SDR DALA2025100807320Hinge Fitting · corrodedCORROSION ON FLAP FWD HINGE FITTING XRS=267 OF REAR SPAR AREA AT LH WING. REPLACED PER SERVICEABLE LT CENTER WING FLAP HINGE FITTING (0931308)SDR DALA2025042503241Longeron · crackedCRACKED LONGERONS 6R, 4L, AND 8R LOCATED AT RH LAVATORY ZONE Y=1022. SUMMARY OF NRC 00417: LONGERON 6R AND 8R STA Y=1022 AT RH AFT LAVATORY ZONE WERE REPAIRED PER B717-200 SRM 53-00-05-2R PROCEDURE 2 REPAIR 2 FIG 201. NO CRACKS WERE FOUND ON LONGERON 4L PER DCSDR DALA2025042403190Cusp Web · crackedCRACK ON CUSP WEB RH BTW STA Y=715 AT PASSENGER CABIN. CUSP WEB RH BTW STA Y=715 AT PASSENGER CABIN WAS REPAIRED PER B-717-200 SRM 53-00-55-2R PROCEDURE 4 REPAIR 4 FIG 203.
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