# Service difficulty reports: N921AT

A list on [N921AT](https://openairdocs.org/aircraft/N921AT.md).

Matched to this aircraft by N-number and event date, checked against the reported serial number, make and model. Newest first.

Page 1 of 5 · 236 reports

- [SDR DALA2026100905577](https://openairdocs.org/sdr/DALA2026100905577.md): Tail Cone · punctured · Oct 8, 2026 · N921AT · Boeing 717200 · Aerodynamic Fairings
  > TAIL CONE DECAL DAMAGED & PUNCTURED, REPLACED THE DECAL IAW MM 52-20. (9388108) (AIRCRAFT GROUNDED).
- [SDR DALA2026081004611](https://openairdocs.org/sdr/DALA2026081004611.md): Sign · loose · Aug 10, 2026 · N921AT · Boeing 717200 · Emergency Lighting
  > FWD CABIN EXIT SIGN LOOSE. SECURED FWD CABIN EXIT SIGN IAW AMM 33-51. (8801968) AIRCRAFT WAS GROUNDED.
- [SDR DALA2026080604546](https://openairdocs.org/sdr/DALA2026080604546.md): Target · loose · Aug 5, 2026 · N921AT · Boeing 717200 · Door Warning System
  > GALLEY DOOR TARGET LOOSE, RESECURED TARGET IAW AMM 52-70-01. (1739326) (AIRCRAFT GROUNDED).
- [SDR DALA2026050502825](https://openairdocs.org/sdr/DALA2026050502825.md): Girt Bar · none · Apr 29, 2026 · N921AT · Boeing 717200 · Standard Practices/Structures
  > MAIN BOARDING DOOR PARTIALLY OPENED W/GIRT BAR STILL IN FLOOR FITTINGS. REATTACHED SLIDE PACK TO COVER. CKS NORMAL (8322872) (AIRCRAFT GROUNDED)
- [SDR DALA2026031001644](https://openairdocs.org/sdr/DALA2026031001644.md): Not Reported · not reported · Mar 5, 2026 · N921AT · Boeing 717200 · Standard Practices/Structures
  > SHIP 9577 ER/A 631995-14AD REV ORIGINAL REQUIRES STAGE 2 & 3 DTA APPROVAL. REPAIR ACCOMPLISHMENT PER ER/A 631995-14AD (1480809)
- [SDR DALA2025072405585](https://openairdocs.org/sdr/DALA2025072405585.md): Battery Pack · inoperative · Jul 23, 2025 · N921AT · Boeing 717200 · Emergency Lighting
  > SHIP 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 DALA2025061104458](https://openairdocs.org/sdr/DALA2025061104458.md): Structure · damaged · Jun 10, 2025 · N921AT · Boeing 717200 · Leading Edge Devices
  > AIRCRAFT 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 FO
- [SDR DALA2025061104457](https://openairdocs.org/sdr/DALA2025061104457.md): Seal · elongated · Jun 10, 2025 · N921AT · Boeing 717200 · Leading Edge Devices
  > AIRCRAFT 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 PRI
- [SDR DALA2025061104455](https://openairdocs.org/sdr/DALA2025061104455.md): Skin · damaged · Jun 9, 2025 · N921AT · Boeing 717200 · Vertical Stabilizer, Plate/Skin
  > AIRCRAFT 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 DALA2025060804359](https://openairdocs.org/sdr/DALA2025060804359.md): Fastener · loose · Jun 7, 2025 · N921AT · Boeing 717200 · Vertical Stabilizer, Plate/Skin
  > ARCRAFT 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 DALA2025060704354](https://openairdocs.org/sdr/DALA2025060704354.md): Attach Angle · cracked · Jun 5, 2025 · N921AT · Boeing 717200 · Fuselage Main, Attach Fittings
  > AIRCRAFT 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: PERMANE
- [SDR DALA2025060704353](https://openairdocs.org/sdr/DALA2025060704353.md): Structure · cracked · Jun 3, 2025 · N921AT · Boeing 717200 · Nacelle/Pylon, Main Frame
  > AIRCRAFT 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 10039
- [SDR DALA2025060604341](https://openairdocs.org/sdr/DALA2025060604341.md): Access Panel · corroded · May 31, 2025 · N921AT · Boeing 717200 · Wing, Plate/Skin
  > SHIP 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 (0998316
- [SDR DALA2025060604340](https://openairdocs.org/sdr/DALA2025060604340.md): Skin · dented · May 31, 2025 · N921AT · Boeing 717200 · Fuselage Main, Plate/Skin
  > SHIP 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 DALA2025060604335](https://openairdocs.org/sdr/DALA2025060604335.md): Tab · delaminated · May 29, 2025 · N921AT · Boeing 717200 · Elevator, Tab Structure
  > SHIP 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 DALA2025060604326](https://openairdocs.org/sdr/DALA2025060604326.md): Support Fitting · worn · May 27, 2025 · N921AT · Boeing 717200 · Aerodynamic Fairings
  > SHIP 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 DALA2025060604322](https://openairdocs.org/sdr/DALA2025060604322.md): Frame · cracked · May 24, 2025 · N921AT · Boeing 717200 · Fuselage Main, Frame
  > SHIP 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 DALA2025060604321](https://openairdocs.org/sdr/DALA2025060604321.md): Cargo Track · corroded · May 24, 2025 · N921AT · Boeing 717200 · Fuselage, Seat/Cargo Attach Fittings
  > SHIP 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 DALA2025100807323](https://openairdocs.org/sdr/DALA2025100807323.md): Fitting · corroded · May 21, 2025 · N921AT · Boeing 717200 · Elevator Structure
  > CORROSION ON COUNTERWEIGHT FITTING OF ELEVATOR LH. COUNTERWEIGHT FITTING OF ELEVATOR LT WAS REPAIRED PER ERA 592404-14TR REV ORIGINAL SECTION I. (0977129)
- [SDR DALA2025052704028](https://openairdocs.org/sdr/DALA2025052704028.md): Door Frame · cracked · May 19, 2025 · N921AT · Boeing 717200 · Fuselage Main, Structure
  > SHIP 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 DALA2025052203938](https://openairdocs.org/sdr/DALA2025052203938.md): Fastener · loose · May 19, 2025 · N921AT · Boeing 717200 · Fuselage Main, Plate/Skin
  > SHIP 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 DALA2025052203941](https://openairdocs.org/sdr/DALA2025052203941.md): Hinge Fitting · corroded · May 19, 2025 · N921AT · Boeing 717200 · Trailing Edge Flaps
  > SHIP 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 DALA2025052203935](https://openairdocs.org/sdr/DALA2025052203935.md): Floor Support · corroded · May 18, 2025 · N921AT · Boeing 717200 · Fuselage Miscellaneous Structure
  > SHIP 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= -11
- [SDR DALA2025052203937](https://openairdocs.org/sdr/DALA2025052203937.md): Hinge Fitting · worn · May 16, 2025 · N921AT · Boeing 717200 · Trailing Edge Flaps
  > SHIP 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 DALA2025052203933](https://openairdocs.org/sdr/DALA2025052203933.md): Frame · corroded · May 16, 2025 · N921AT · Boeing 717200 · Fuselage Main, Frame
  > SHIP 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 DALA2025052203932](https://openairdocs.org/sdr/DALA2025052203932.md): Seat Track · corroded · May 16, 2025 · N921AT · Boeing 717200 · Fuselage, Seat/Cargo Attach Fittings
  > SHIP 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 DALA2025052203931](https://openairdocs.org/sdr/DALA2025052203931.md): Window Frame · cracked · May 16, 2025 · N921AT · Boeing 717200 · Fuselage Main, Structure
  > SHIP 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 DALA2025052203930](https://openairdocs.org/sdr/DALA2025052203930.md): Seat Track · corroded · May 15, 2025 · N921AT · Boeing 717200 · Fuselage, Seat/Cargo Attach Fittings
  > SHIP 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 DALA2025051503781](https://openairdocs.org/sdr/DALA2025051503781.md): Cusp Web · cracked · May 14, 2025 · N921AT · Boeing 717200 · Fuselage Miscellaneous Structure
  > CUSP 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 DALA2025051403729](https://openairdocs.org/sdr/DALA2025051403729.md): Seat Track · corroded · May 13, 2025 · N921AT · Boeing 717200 · Fuselage, Seat/Cargo Attach Fittings
  > CORROSION 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 N
- [SDR DALA2025051403728](https://openairdocs.org/sdr/DALA2025051403728.md): Structure · corroded · May 13, 2025 · N921AT · Boeing 717200 · Horizontal Stabilizer Miscellaneous Structure
  > -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 I
- [SDR DALA2025051303689](https://openairdocs.org/sdr/DALA2025051303689.md): Longeron · corroded · May 13, 2025 · N921AT · Boeing 717200 · Fuselage Main, Longeron/Stringer
  > CORROSION 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 DALA2025051303687](https://openairdocs.org/sdr/DALA2025051303687.md): Cusp Web · cracked · May 13, 2025 · N921AT · Boeing 717200 · Fuselage Miscellaneous Structure
  > CUSP 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 DALA2025051303686](https://openairdocs.org/sdr/DALA2025051303686.md): Cusp Web · corroded · May 12, 2025 · N921AT · Boeing 717200 · Fuselage Miscellaneous Structure
  > CORROSION 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 #096
- [SDR DALA2025051203680](https://openairdocs.org/sdr/DALA2025051203680.md): Hinge Fitting · corroded · May 10, 2025 · N921AT · Boeing 717200 · Horizontal Stabilizer Structure
  > FRETTING 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 LEVE
- [SDR DALA2025051203679](https://openairdocs.org/sdr/DALA2025051203679.md): Skin · cracked · May 9, 2025 · N921AT · Boeing 717200 · Fuselage Main, Plate/Skin
  > CRACKS 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 CONTROLLED
- [SDR DALA2025051203678](https://openairdocs.org/sdr/DALA2025051203678.md): Cable · worn · May 8, 2025 · N921AT · Boeing 717200 · Aerodynamic Fairings
  > TAILCONE 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 20-0
- [SDR DALA2025050803559](https://openairdocs.org/sdr/DALA2025050803559.md): Cusp Web · corroded · May 7, 2025 · N921AT · Boeing 717200 · Fuselage Miscellaneous Structure
  > CORROSION 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 DALA2025050803558](https://openairdocs.org/sdr/DALA2025050803558.md): Cusp Web · corroded · May 6, 2025 · N921AT · Boeing 717200 · Fuselage Miscellaneous Structure
  > CORROSION 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 DALA2025050603512](https://openairdocs.org/sdr/DALA2025050603512.md): Floor Support · corroded · May 5, 2025 · N921AT · Boeing 717200 · Fuselage Miscellaneous Structure
  > CORROSION 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 DALA2025050503409](https://openairdocs.org/sdr/DALA2025050503409.md): Cargo Track · corroded · May 3, 2025 · N921AT · Boeing 717200 · Fuselage, Seat/Cargo Attach Fittings
  > CORROSION 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 DALA2025050503408](https://openairdocs.org/sdr/DALA2025050503408.md): Floor Support · corroded · May 2, 2025 · N921AT · Boeing 717200 · Fuselage Miscellaneous Structure
  > CORROSION 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 DALA2025050503407](https://openairdocs.org/sdr/DALA2025050503407.md): Cusp Web · corroded · May 2, 2025 · N921AT · Boeing 717200 · Fuselage Miscellaneous Structure
  > CORROSION 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 DALA2025050103360](https://openairdocs.org/sdr/DALA2025050103360.md): Cusp Web · corroded · Apr 30, 2025 · N921AT · Boeing 717200 · Fuselage Miscellaneous Structure
  > CORROSION 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 53-00-55-1A
- [SDR DALA2025043003319](https://openairdocs.org/sdr/DALA2025043003319.md): Cusp Web · corroded · Apr 30, 2025 · N921AT · Boeing 717200 · Fuselage Miscellaneous Structure
  > CORROSION 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 DALA2025043003318](https://openairdocs.org/sdr/DALA2025043003318.md): Cusp Web · corroded · Apr 30, 2025 · N921AT · Boeing 717200 · Fuselage Miscellaneous Structure
  > CORROSION 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 DALA2025043003316](https://openairdocs.org/sdr/DALA2025043003316.md): Cusp Web · corroded · Apr 30, 2025 · N921AT · Boeing 717200 · Fuselage Miscellaneous Structure
  > CORROSION 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 DALA2025100807320](https://openairdocs.org/sdr/DALA2025100807320.md): Hinge Fitting · corroded · Apr 24, 2025 · N921AT · Boeing 717200 · Trailing Edge Flaps
  > CORROSION 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 DALA2025042503241](https://openairdocs.org/sdr/DALA2025042503241.md): Longeron · cracked · Apr 24, 2025 · N921AT · Boeing 717200 · Fuselage Main, Longeron/Stringer
  > CRACKED 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 DC
- [SDR DALA2025042403190](https://openairdocs.org/sdr/DALA2025042403190.md): Cusp Web · cracked · Apr 23, 2025 · N921AT · Boeing 717200 · Fuselage Miscellaneous Structure
  > CRACK 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.

Next page: https://openairdocs.org/aircraft/N921AT/reports.md?page=2

## The whole list in SQL

Runs in DuckDB 1.2 or later on the release's Parquet files over HTTPS:

```sql
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
```

This list as a web page: https://openairdocs.org/aircraft/N921AT/reports

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