# Service difficulty reports: N894AT

A list on [N894AT](https://openairdocs.org/aircraft/N894AT.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 3 · 119 reports

- [SDR DALA2024071807236](https://openairdocs.org/sdr/DALA2024071807236.md): Coax · loose · Jul 13, 2024 · N894AT · Boeing 717200 · Instrument System Wiring
  > SHIP 9554 -ATO- THE FLIGHT CREW ABORTED THE TAKEOFF AT 130 KTS DUE TO THE #1 PRIMARY FLIGHT DISPLAY AND MULTI-FUNCTIONAL DISPLAY BLANKING OUT. CORRECTIVE ACTION: MAINTENANCE FOUND 2 EACH COAX CABLES LOOSE ON VIA #1 SPLITTERS AND REPLACED BOTH DISPLAY UNITS. (L
- [SDR DALA2023092207784](https://openairdocs.org/sdr/DALA2023092207784.md): Unknown · unknown · Sep 21, 2023 · N894AT · Boeing 717200 · Emergency Lighting
  > DOOR R1 EXIT SIGN IS MISSING. MAINTENANCE REPLACED AND INSTALLED THE MISSING LENS COVER IAW B717 AMM 33-51. LIGHT OPERATIONAL CHECK WAS GOOD. THE AIRCRAFT IS OK FOR SERVICE. (LP #4579222)
- [SDR DALA2023071805821](https://openairdocs.org/sdr/DALA2023071805821.md): Unknown · unknown · Jul 18, 2023 · N894AT · Boeing 717200 · Fuselage Miscellaneous Structure
  > CRACKS ON LH CUSP WEB AROUND RING BTW STA 652 AND 655. SUMMARY OF NRC 00668: LH CUSP WEB AROUND RING BTW STA 652 AND 655 WAS REPAIRED PER B717 SRM 53-00-55-2R-4 PAR 5. B. FIGURE 211. (LP #2863892)
- [SDR DALA2025013000727](https://openairdocs.org/sdr/DALA2025013000727.md): Skin · corroded · Mar 15, 2023 · N894AT · Boeing 717200 · Fuselage Main, Plate/Skin
  > -AD- CENTER WING BOX LOWER SKIN XCW=20 TO XCW=42 REAR SPAR TO STRINGER #12 HAS CORROSION AND ELONGATED HOLES. REPAIR APPROVAL IS LIMITED TO 24 MONTHS FROM 14MAR23. ADDITIONAL ENGINEERING AUTHORIZATION (ER/A REVISION) IS REQUIRED FOR CONTINUED SERVICE OF THIS R
- [SDR DALA2023031401845](https://openairdocs.org/sdr/DALA2023031401845.md): Unknown · unknown · Mar 9, 2023 · N894AT · Boeing 717200 · Entrance Stairs
  > CORROSION WAS FOUND ON FWD PASSENGER DOOR STAIRWELL INTERNAL STRUCTURE IN REF NRC 2060-1001. SUMMARY OF NRC 00572: CORROSION LEVEL 2. FWD PASSENGER DOOR STAIRWELL WAS REPLACED WITH SERVICEABLE STAIRWELL PER B717-200 AMM 52-63-01. TOOL USED CALIBRATED STD DUE D
- [SDR DALA2023030201555](https://openairdocs.org/sdr/DALA2023030201555.md): None · none · Mar 1, 2023 · N894AT · Boeing 717200 · Fuselage Main, Plate/Skin
  > SKIN PANELS BTW STA 954 TO STA 974 LONG 30 TO R29 ARE CORRODED OUT OF LIMITS. WITH ORIGINAL THICKNESS OF 0.071 IN. AND THE MAXIMUM REMOVED MATERIAL FOUND IS 0.033 IN. THEREFOR AREA IS OUT OF LIMITS IN REF NRC 00192 AT AFT CARGO (C2). SUMMARY OF NRC 00512: CORR
- [SDR DALA2023030101525](https://openairdocs.org/sdr/DALA2023030101525.md): None · none · Feb 27, 2023 · N894AT · Boeing 717200 · Aileron Tabs
  > SEVERAL DENTS ON AFT MOVABLE FLAP VANE (LOWER SURFACE) AT LH WING (AI). SUMMARY OF NRC 00160: DENTS (26 EAS) ON AFT MOVABLE FLAP VANE (LOWER SURFACE) AT LH WING WERE FOUND AND EVALUATED AS FOLLOWS, WHERE, L=LENGTH, W=WIDTH, Y=DEPTH, AND W/Y MUST BE 10 OR MORE,
- [SDR DALA2023022401415](https://openairdocs.org/sdr/DALA2023022401415.md): None · none · Feb 22, 2023 · N894AT · Boeing 717200 · Fuselage Floor Panel
  > CORROSION ON SEAT TRACKS STA Y=200-237 X=-22, STA Y=200-218 X=-44.5 AND STA Y=200 X=22 (CPAX)( W1). SUMMARY OF NRC 00425: CORROSION LEVEL 2. CORROSION WAS REMOVED ON SEAT TRACKS STA Y=200-237 X=-22, STA Y=200-218 X=-44.5 AND STA Y=200 X=22 PER B717-200 SRM 51-
- [SDR DALA2023022401414](https://openairdocs.org/sdr/DALA2023022401414.md): None · none · Feb 22, 2023 · N894AT · Boeing 717200 · Cargo/Baggage Doors
  > CRACK ON PAN, FWD/UPPER INNER SIDE NEAR TO BEAM 5 OF FWD CARGO COMPARTMENT DOOR. (C1) SUMMARY OF NRC 00541: PAN FWD/UPPER OF FWD CARGO DOOR WAS REPAIRED PER B717-200 SRM 52-30-02-2R PROCEDURE 1 REPAIR 1 FIGURE 201. (LP #2640421)
- [SDR DALA2023022201326](https://openairdocs.org/sdr/DALA2023022201326.md): None · none · Feb 22, 2023 · N894AT · Boeing 717200 · Fuselage Structure (General)
  > CORROSION ON FLOOR SUPPORT 4 (EA) STA Y=218 AND X=0 TO X=13.5, STA Y=200 X=16 TO X=-6, STA Y=200-210 X=-10.5 (CPAX)(W1). SUMMARY OF NRC 00433: CORROSION LEVEL 2. FLOOR SUPPORT 4 (EA) STA Y=218 AND X=0 TO X=13.5, STA Y=200 X=16 TO X=-6, STA Y=200-210 X=-10.5 WE
- [SDR DALA2023022001254](https://openairdocs.org/sdr/DALA2023022001254.md): None · none · Feb 17, 2023 · N894AT · Boeing 717200 · Fuselage Main, Longeron/Stringer
  > CRACK ON LONGERON 2RH ON STA Y=1144 AT AFT ACCESSORIES COMPARTMENT (CAT). SUMMARY OF NRC 00414- LONGERON 2RH ON STA Y=1144 AT AFT ACCESSORIES COMPARTMENT WAS REPAIRED PER B717-200 SRM 53-00-05- 2R REPAIR 2. (LP #2633164)
- [SDR DALA2023021701231](https://openairdocs.org/sdr/DALA2023021701231.md): None · none · Feb 16, 2023 · N894AT · Boeing 717200 · Fuselage Main, Frame
  > A.A. A.D. CRACK WAS FOUND OF 0.250" LENGTH ON FRAME STA Y=737 RH SIDE IN REF CARD 5310-01439-01D JOB# 094-0004 STEP: 4. SUMMARY NRC 00154: OVER WING FRAME STA Y=737 BTW LONG 8 TO 18 RH WAS REPLACED PER WORK CARD 5310-01439-02B. ASSOCIATED AA 5310-01439 ADDED F
- [SDR DALA2023021701229](https://openairdocs.org/sdr/DALA2023021701229.md): None · none · Feb 16, 2023 · N894AT · Boeing 717200 · Fuselage Main, Frame
  > CRACK ON INTERCOSTAL BTW STA 1002 TO STA 1022, X=22 TO X=-22, PASSENGER CABIN. SUMMARY OF NRC 00442: INTERCOSTAL BTW STA 1002 TO STA 1022, X=22 TO X=-22 WAS REPAIRED PER B717-200 SRM 51-70-11-2R-1. (LP #2631096)
- [SDR DALA2023021701228](https://openairdocs.org/sdr/DALA2023021701228.md): None · none · Feb 15, 2023 · N894AT · Boeing 717200 · Fuselage Main, Frame
  > SEVERAL HIDDEN CRACKS ON RH CUSP WEB UNDER RH SEAT TRACK RBL 44 BTW STA Y=674 AND Y=715 IN REF NRC 00154. SUMMARY OF NRC 00514: RH CUSP WEB UNDER RH SEAT TRACK RBL 44 BTW STA Y=674 AND Y=715 WAS PERMANENTLY REPAIRED PER B717-200 SRM 53-00-55-2 R REP 4 PAR 5 FI
- [SDR DALA2023021501180](https://openairdocs.org/sdr/DALA2023021501180.md): None · none · Feb 13, 2023 · N894AT · Boeing 717200 · Fuselage Floor Panel
  > CORROSION OUT OF LIMITS ON FLOOR SUPPORT AT STA Y=200 X=-9 TO X=-44. ORIGINAL THICKNESS WAS 0.070 IN AND MINIMUM REMAINING THICKNESS IS 0.045 IN, THEREFORE THE AREA IS OUT OF LIMITS IN REF NRC 00431 AT PAX CABIN (CPAX)(W1). SUMMARY OF NRC 00484: CORROSION LEVE
- [SDR DALA2023021501179](https://openairdocs.org/sdr/DALA2023021501179.md): None · none · Feb 13, 2023 · N894AT · Boeing 717200 · Fuselage Floor Panel
  > IN REFERENCE TO NRC 00066, AFTER REMOTION OF RETAINER SEALS, CRACK WAS FOUND ON PAN STRUCTURE AFT CARGO DOOR, FWD EDGE BTW CL STOP #1 AND CL STOP #2. SUMMARY OF NRC 00511: PAN STRUCTURE AFT CARGO DOOR, FWD EDGE BTW CL STOP #1 AND CL STOP #2 WAS REPAIRED PER B7
- [SDR DALA2023021401136](https://openairdocs.org/sdr/DALA2023021401136.md): Unknown · unknown · Feb 11, 2023 · N894AT · Boeing 717200 · Fuselage Main, Frame
  > CORRODED DIAPHRAGM ON STA Y=200 X=-22. ORIGINAL THICKNESS WAS 0.020 IN AND MINIMUM REMAINING THICKNESS IS 0.012 IN, THEREFORE IT IS OUT LIMITS IN REF NRC 00424 AT PAX CABIN (CPAX)(W1). SUMMARY OF NRC 00510: CORROSION LEVEL 2. DIAPHRAGM (WEB) ON STA Y=200 X=-22
- [SDR DALA2023021401134](https://openairdocs.org/sdr/DALA2023021401134.md): Unknown · unknown · Feb 11, 2023 · N894AT · Boeing 717200 · Fuselage Floor Panel
  > CORRODED FLOOR SUPPORT STA Y=157-200 AND X=44.5, STA Y=180 AND X=12 TO X=38. ORIGINAL THICKNESS WAS 0.070 IN AND MINIMUM REMAINING THICKNESS IS 0.035 IN, THEREFORE THE AREA IS OUT LIMITS IN REF NRC 00434 AT PAX CABIN (CPAX)(W1). SUMMARY OF NRC 00485: CORROSION
- [SDR DALA2023021401129](https://openairdocs.org/sdr/DALA2023021401129.md): Unknown · unknown · Feb 10, 2023 · N894AT · Boeing 717200 · Fuselage Main, Frame
  > CRACK ON WEB OF FUSELAGE DOOR FRAME, STA. 208, OVER LONGERON 11 LH AND LONGERON 15 LH. (CPAX). SUMMARY OF NRC 00394: WEB OF FUSELAGE DOOR FRAME, STA. 208, OVER LONGERON 11 LH AND LONGERON 15 LH WAS REPAIRED PER B717-200 SRM 53-10-15-2R PROCEDURE 1 REPAIR 1. (L
- [SDR DALA2023021401127](https://openairdocs.org/sdr/DALA2023021401127.md): Unknown · unknown · Feb 10, 2023 · N894AT · Boeing 717200 · Passenger/Crew Doors
  > CRACKS (2EAS, FWD AND AFT SIDES) WERE FOUND ON BEAM 1 DURING THE WORK PROCESS ON NRC 00081 AT L1 PASSENGER DOOR. (PTAS). SUMMARY OF NRC 00487: FWD AND AFT SIDES OF BEAM 1 AT L1 PASSENGER DOOR WERE REPAIRED PER B717-200 SRM 52-10-02-2R PROCEDURE 7 REPAIR 7. (LP
- [SDR DALA2023021401126](https://openairdocs.org/sdr/DALA2023021401126.md): Unknown · unknown · Feb 10, 2023 · N894AT · Boeing 717200 · Fuselage Main, Frame
  > CORROSION IS OUT OF LIMITS AT THE LH CUSP WEB MEMBRANE AT STA 395 X=54 TO X=59. ORIGINAL THICKNESS WAS 0.020 INCHES AND REMAINING THICKNESS AT STA 395 IS 0.008 INCHES. THEREFOR AREA IS OUT LIMITS. REF NRC 00293 AT PAX CABIN (CPAX). SUMMARY OF NRC 00509: CORROS
- [SDR DALA2023021401125](https://openairdocs.org/sdr/DALA2023021401125.md): Unknown · unknown · Feb 9, 2023 · N894AT · Boeing 717200 · Fuselage Main, Frame
  > PUNCTURES (2EA) WERE FOUND ON FLOOR WEB STA Y=128 AND X=17 AT FLIGHT DECK IN REF CARD 2060-1007. SUMMARY OF NRC 00503: WEB STA Y=128 AND X=17 AT FLIGHT DECK WAS REPAIRED PER B717-200 SRM 51-70-10-2R PROCEDURE 2. (LP #2622123)
- [SDR DALA2023021401121](https://openairdocs.org/sdr/DALA2023021401121.md): Unknown · unknown · Feb 9, 2023 · N894AT · Boeing 717200 · Fuselage Main, Frame
  > SCRATCH (2 EA) ON DIAPHRAGM STA Y=189 AND X=45 (CPAX) (W1). SUMMARY OF NRC 00423: DIAPHRAGM STA Y=189 AND X=45 WAS PERMANENTLY REPAIRED PER B717-200 SRM 51-70-10-2R PROCEDURE 2 PAR. 4 FIG. 201 (SHEET 2). (LP #2621668)
- [SDR DALA2023021401119](https://openairdocs.org/sdr/DALA2023021401119.md): Unknown · unknown · Feb 8, 2023 · N894AT · Boeing 717200 · Fuselage Main, Frame
  > ELONGATED AND BENT HOLE ON RH CUSP WEB STA Y=715 TO 756 X-44 TO X-60 IN REF NRC 00154. SUMMARY OF NRC 00446: RH CUSP WEB STA Y=715 TO 756 X-44 TO X-60 WAS REPAIRED PER B717-200 SRM 53-00-55-2R REP. 4 FIGURE 221. (LP #2620447)
- [SDR DALA2023021401118](https://openairdocs.org/sdr/DALA2023021401118.md): Unknown · unknown · Feb 8, 2023 · N894AT · Boeing 717200 · Fuselage Floor Panel
  > CORROSION ON FLOOR SUPPORT BTW STA 1022 TO STA 1053, X=44.5 LAVORATORY FLOOR STRUCTURE (PAX CAB) (W2). SUMMARY OF NRC 00445: CORROSION LEVEL 2. FLOOR SUPPORT BTW STA 1022 TO STA 1053, X=44.5 LAVORATORY FLOOR STRUCTURE WAS REPLACED PER B717-200 SRM 53-20-51-0I,
- [SDR DALA2023020800983](https://openairdocs.org/sdr/DALA2023020800983.md): Not Reported · not reported · Feb 7, 2023 · N894AT · Boeing 717200 · Fuselage Floor Panel
  > SECONDARY NRC 00428: FLOOR SUPPORT STA Y=180 AND X=-9 TO X=-43 HAS CORROSION. ORIGINAL THICKNESS IS 0.070 IN AND MINIMUM REMAINING THICKNESS IS 0.020 IN, THEREFORE THE AREA CORROSION IS OUT LIMITS AT PAX CABIN. (CPAX)(W1). SUMMARY OF NRC 00489: CORROSION LEVEL
- [SDR DALA2023020800982](https://openairdocs.org/sdr/DALA2023020800982.md): Not Reported · not reported · Feb 7, 2023 · N894AT · Boeing 717200 · Fuselage Floor Panel
  > CORROSION ON FLOOR SUPPORTS (3 EA) STA Y=196 TO 200 FROM X=16 TO X=55.5 AT PAX CABIN FLOOR STRUCTURE. CPAX. SUMMARY OF NRC 00435: CORROSION LEVEL 2. FLOOR SUPPORTS (3 EA) AT STA Y=196 TO 200 FROM X=16 TO X=55.5 WERE REPLACED PER B717-200 SRM 51-41-05 PAR 8, 51
- [SDR DALA2023020700925](https://openairdocs.org/sdr/DALA2023020700925.md): Not Reported · not reported · Feb 7, 2023 · N894AT · Boeing 717200 · Fuselage Main, Frame
  > CRACK ON RH CUSP WEB MEMBRANE AT STA 655 TO 674 & X=-54 TO X=-59 PASSENGER CABIN FLOOR (CPAX). SUMMARY OF NRC 00292: RH CUSP WEB MEMBRANE AT STA 655 TO 674 & X=-54 TO X=-59 WAS PERMANENTLY REPAIRED PER B717-200 SRM 53-00-55-2R PROCEDURE 4 FIG 216. (LP #2618034
- [SDR DALA2020112303837](https://openairdocs.org/sdr/DALA2020112303837.md): Battery Pack · inoperative · Nov 23, 2020 · N894AT · Boeing 717200 · Emergency Lighting
  > BOTH THE L1 AND R1 LOWER EXIT SIGNS WILL NOT ILLUMINATE. MAINTENANCE REPLACED THE BATTERY PACK ABOVE SEAT 2CD, IAW B717 AMM 33 -51. OPERATIONAL CHECK WAS GOOD.
- [SDR 2020F00248](https://openairdocs.org/sdr/2020F00248.md): Spoiler · delaminated · Feb 26, 2020 · N894AT · Boeing 717200 · Spoilers
  > DISBONDED
- [SDR DALA2020011600323](https://openairdocs.org/sdr/DALA2020011600323.md): Stringer · corroded · Jan 15, 2020 · N894AT · Boeing 717200 · Fuselage Main, Longeron/Stringer
  > AFT CARGO COMPARTMENT STRINGER 30, BETWEEN STA 948- 954 IS CORRODED. NRC 040-0008:5331-2001/004 00196: CORROSION LEVEL 1, SPLICED NEW SECTION OF LONGERON FROM STA 937-965 REF SRM 53-20-05-2R PROC 1.
- [SDR DALA2020011600322](https://openairdocs.org/sdr/DALA2020011600322.md): Stringer · corroded · Jan 15, 2020 · N894AT · Boeing 717200 · Fuselage Main, Longeron/Stringer
  > AFT CARGO COMPARTMENT STRINGER 30, STA 986 IS CORRODED. NRC 040-0008:5331-2001/001 00193: CORROSION LEVEL 1, SPLICED NEW SECTION OF LONGERON FROM STA 965-1012 REF SRM 53-20-05-2R PROC 1.
- [SDR DALA2020010700089](https://openairdocs.org/sdr/DALA2020010700089.md): Doubler · damaged · Jan 6, 2020 · N894AT · Boeing 717200 · Fuselage Main, Plate/Skin
  > RAMP REPORTS DAMAGE AT AFT LOWER EDGE OF C1 CARGO DOOR. DAMAGE IS TO EXISTING DOUBLER EDGE. REMOVED, FABRICATED, AND DRILLED UP NEW DOUBLER AND TRIMED DAMAGE IAW B717 SRM 53-20-15-2R-5 OPTION 2. INSTALLED REPAIR DOUBLER PER B717 SRM 53-20-15 FIG 202 OPT. 2. AL
- [SDR 2019F00174](https://openairdocs.org/sdr/2019F00174.md): Skin · delaminated · Mar 29, 2019 · N894AT · Boeing 717200 · Spoilers
  > INB SPOILER HAS DELAMINATION BOTTON SURFACE. LARGE DELMINATION AREA.
- [SDR DALA2018120306972](https://openairdocs.org/sdr/DALA2018120306972.md): Cover · missing · Dec 2, 2018 · N894AT · Boeing 717200 · Horizontal Stabilizer, Plate/Skin
  > HORIZONTAL STABILIZER BEARING AND CENTER SECTION ACCESS DOORS - MEL NUMBER ADDED FOR DISPATCH RELEASE, LOG REDEFERRAL REQUIRED. ON WALK AROUND FOUND HORIZONTAL STAB BEARING COVER MISSING. DEFERRED ITEM. WILL NEED A SUPPLEMETAL SDR ONCE REAPIR IS COMPLETE. REPO
- [SDR DALA2018070404359](https://openairdocs.org/sdr/DALA2018070404359.md): Light · broken · Jul 3, 2018 · N894AT · Boeing 717200 · Emergency Lighting
  > FOUND EMERGENCY LIGHT L2-938 BROKEN AFT COMPARTMENT. REPLACED TERMINALS NEEDS LIGHT ASSY MOUNTED. MOUNTED LIGHT ASSY CKS GOOD.
- [SDR DALA2018030901588](https://openairdocs.org/sdr/DALA2018030901588.md): Latch · damaged · Mar 9, 2018 · N894AT · Boeing 717200 · Escape Slide
  > TAIL CONE SLIDE COVER WAS FOUND NOT SECURE. REPLACED A DAMAGED LATCH ON THE SLIDE COVER IAW AMM 25-61-02 AND RIG SLIDE IAW TASK CARD 2561-9006.
- [SDR DALA2018030601404](https://openairdocs.org/sdr/DALA2018030601404.md): Frame · gouged · Mar 6, 2018 · N894AT · Boeing 717200 · Fuselage Main, Frame
  > GOUGE ON THE UPPER SURFACE OF THE AFT HORIZONTAL LEG OF CANTED FRAME STA 1145 RT SIDE APPROX RBL 4-6. NRC 001-0253:5300-2004/005 00214: 566363-14 REV 1 AND ER/A 566363-14 REV O MATCH WORK COMPLIED WITH PER ER/A 566363-14 REV O.
- [SDR DALA2018030601403](https://openairdocs.org/sdr/DALA2018030601403.md): Frame · gouged · Mar 6, 2018 · N894AT · Boeing 717200 · Fuselage Main, Frame
  > GOUGE ON THE UPPER SURFACE OF THE AFT HORIZONTAL LEG OF CANTED FRAME STA 1145 LT SIDE APPROX LBL 4-7. NRC 001-0253:5300-2004/004 00213: PRI 566363-14 REV 1 AND ER/A 566363-14 REV O MATCH. WORK WAS PERFORMED PER ER/A 566363-14 REV O.
- [SDR DALA2018030401383](https://openairdocs.org/sdr/DALA2018030401383.md): Bearing · loose · Mar 3, 2018 · N894AT · Boeing 717200 · Spoilers
  > RIGHT INBD SPOILER PANEL CENTER HINGE BEARING LOOSE IN BORE. THE SPOILER PANEL WAS REPLACED.
- [SDR DALA2018021901529](https://openairdocs.org/sdr/DALA2018021901529.md): Lens · damaged · Feb 18, 2018 · N894AT · Boeing 717200 · Emergency Lighting
  > EMERGENCY LIGHT LENS DAMAGED. REPLACED THE DAMAGED LENS.
- [SDR DALA2018030801530](https://openairdocs.org/sdr/DALA2018030801530.md): Bracket · damaged · Jul 28, 2017 · N894AT · Boeing 717200 · Emergency Lighting
  > FOUND EMERGENCY LIGHT AT ESCAPE RAMP PANEL IN POOR CONDITION. REPLACED THE BRACKETS IAW SRM 51-40-02.
- [SDR DALA2017032802517](https://openairdocs.org/sdr/DALA2017032802517.md): Charger · inoperative · Mar 28, 2017 · N894AT · Boeing 717200 · Emergency Lighting
  > ON SVC FOUND EMERG BATT PACK INOPERATIVE. R&R BATT CHARGER / BATT B5-235 REF AMM 33-51, WDM 33-51. CHECKS GOOD. OK FOR SVC.
- [SDR DALA2016040502626](https://openairdocs.org/sdr/DALA2016040502626.md): Power Supply · inoperative · Apr 5, 2016 · N894AT · Boeing 717200 · Emergency Lighting
  > DURING LINE CHECK, MAINTENANCE FOUND THAT THE EMERGENCY LIGHTING IN THE VENTRAL STAIRWAY SIDEWALL WERE INOPERATIVE. MAINTENANCE REPLACED THE POWER SUPPLY AND THE LIGHTS RETURNED TO AN OPS CONDITION.
- [SDR DALA2016040502568](https://openairdocs.org/sdr/DALA2016040502568.md): Cusp Web · corroded · Apr 4, 2016 · N894AT · Boeing 717200 · Fuselage Miscellaneous Structure
  > RIGHT CUSP WEB BS 389-503 UPPER AND LOWER SURFACES, HAS SEVERAL AREAS OF CORROSION. INSTALLED NEW CUSP WEB IAW SRM 51-41-02, SRM 51-41-01 AND SRM 51-41-05.
- [SDR DALA2016040502567](https://openairdocs.org/sdr/DALA2016040502567.md): Cusp Web · corroded · Apr 4, 2016 · N894AT · Boeing 717200 · Fuselage Miscellaneous Structure
  > LEFT OUTER CUSP WEB HAS CORROSION AROUND SEVERAL FASTENER HEADS BETWEEN BS 813 & 832. REPAIRED THE CUSP WEB IAW SRM 53-00-55, PG 101, 102 AND 104, AND FIG 216, REPAIR 4.
- [SDR DALA2016032902390](https://openairdocs.org/sdr/DALA2016032902390.md): Spar · corroded · Mar 28, 2016 · N894AT · Boeing 717200 · Wing Spar
  > LEFT CENTER TANK UPPER REAR SPAR CORRODED AT XCW 13, 18, 52, & 59L. CORROSION ON UPPER CENTER TANK WAS REPAIRED IAW ER/A 543586-14, FASTENER HOLES DAMAGED COMMON TO CORROSION BLENDOUT AREA. WERE REPAIRED IAW PRI, REV 3, 543589-14 AND ER/A 543589-14, REV ORIG
- [SDR DALA2016032702329](https://openairdocs.org/sdr/DALA2016032702329.md): Skin · cracked · Mar 26, 2016 · N894AT · Boeing 717200 · Fuselage Main, Plate/Skin
  > BS 1087 ABOVE STRINGER 14R, SKIN HAS A 2 DIRECTIONAL CRACK, VERTICAL LEG.5" & HORIZONAL LEG.1250". HFEC VERIFIED IAW NDT SPM 06-10-01.001 REQUEST ENGINEERING DISPOSITION. REPAIRED CRACK AT BS 1087, 514R IAW ER/A 543584-14 ASSOCIATED ER/A 00-543584 ADDED
- [SDR DALA2016032202228](https://openairdocs.org/sdr/DALA2016032202228.md): Skin · cracked · Mar 21, 2016 · N894AT · Boeing 717200 · Fuselage Main, Plate/Skin
  > BS 1022, STRINGER 14R, SKIN HAS A TWO INCH HORIZONTAL CRACK HFEC VERIFIED IAW NDT SPM 06-10-01.001 PROCEDURE 1. INSTALLED REPAIR IAW PRI 543585-14, REVISION 2, AND ER/A 543585-14 REV.
- [SDR DALA2016030901764](https://openairdocs.org/sdr/DALA2016030901764.md): Skin · cracked · Mar 7, 2016 · N894AT · Boeing 717200 · Fuselage Main, Plate/Skin
  > BS 1133, 1.5" OTBD OF STR 2L HAS.1250 INCH SKIN CRACK AT SHEAR TIE FASTENER LOCATION. HFEC VERIFIED IAW NDTSPM 06-10-01, 001 PROCEDURE, 1 REF ORNRC 0300-0005. REMOVED CRACK FROM FUSELAGE SKIN AT BS 1133, OTBD OF STR 2L AND REPAIRED IAW EA 543582-14AD.

Next page: https://openairdocs.org/aircraft/N894AT/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 = 'N894AT' AND registry_match = 'registration'
ORDER BY difficulty_date DESC
```

This list as a web page: https://openairdocs.org/aircraft/N894AT/reports

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