# Service difficulty reports: N121UP

A list on [N121UP](https://openairdocs.org/aircraft/N121UP.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 · 244 reports

- [SDR IPXA2026072886251](https://openairdocs.org/sdr/IPXA2026072886251.md): Hinge · broken · Jul 27, 2026 · N121UP · Airbus A300F4622R · Fuselage, Door Hinge
  > DOOR PANEL OPENING Z831 HAS BROKEN HINGE AND HAD TO BE REMOVED DUE TO INTERFERING WITH INNER DOOR HANDLE. SEE IPC 52-11-13-28/10 DURING TROUBLESHOOTING FOUND UPPER HINGE BROKEN IN HALF, ALSO FOUND LOWER HINGE MOUNT ASSY DISBONDED FROM PANEL ASSY. REPLACED BROK
- [SDR IPXA2026041432115](https://openairdocs.org/sdr/IPXA2026041432115.md): Lamp · inoperative · Apr 3, 2026 · N121UP · Airbus A300F4622R · Emergency Lighting
  > LAVATORY EMERGENCY LIGHT INOPERATIVE. RELAMPED LAVATORY EMERGENCY - AUXILIARY BULB IAW AMM 33-51-21. OPS CHECKED GOOD.
- [SDR IPXA2026030241501](https://openairdocs.org/sdr/IPXA2026030241501.md): Power Supply · no test · Feb 27, 2026 · N121UP · Airbus A300F4622R · Emergency Lighting
  > EMERGENCY POWER SUPPLY FAILED OPS CHECK PER AMM 33-51-00-0501 REF PSM STEP 15 REMOVED AND REPLACED EMERGENCY POWER BATTERY REFA300 AMM 35-51-140/401. TEST OK
- [SDR IPXA2025040703488](https://openairdocs.org/sdr/IPXA2025040703488.md): Adapter · corroded · Mar 17, 2025 · N121UP · Airbus A300F4622R · Fuselage Main, Structure
  > LATE FIND ON FR38.2 Y 0 RH SIDE CLS ADAPTER P/N B53774136200. ROB FROM N121UP TO INSTALL ON N120UP. ACCOMPLISHED PERMANENT REPAIR IN ACCORDANCE WITH EO-93189-REQ1 AND VT-MAE EA 300-5314-27-A3856, REV. -. REVIEWED
- [SDR IPXA2025040203488](https://openairdocs.org/sdr/IPXA2025040203488.md): Adapter · corroded · Mar 17, 2025 · N121UP · Airbus A300F4622R · Fuselage Miscellaneous Structure
  > **SDR FILED OPEN** FAULT, LATE FIND ON FR38.2 Y 0 RH SIDE CLS ADAPTER P/N B53774136200. ROB FROM N121UP TO INSTALL ON N120UP. VERIFIED SDR HAS BEEN INITIATED. COMPLIED WITH STEP 14 ON PELIMINARY 1 E.A# 300-5314-27-A3856.
- [SDR IPXA2025031891419](https://openairdocs.org/sdr/IPXA2025031891419.md): Roller · frozen · Mar 6, 2025 · N121UP · Airbus A300F4622R · Passenger/Crew Doors
  > L1 DOOR CUTOUT UPPER FWD. DOOR JAMB ROLLER FROZEN DOT#58/44 DARRYL FORD 91102506. L1 DOOR CUTOUT UPPER FWD. DOOR JAMB ROLLER WAS REMOVED, CLEANED, LUBRICATED AND REINSTALLED IAW AMM 12-21-12/201, AMM 12-22-00/001, AMM 20-21-12. REVIEWED
- [SDR IPXA2025031891376](https://openairdocs.org/sdr/IPXA2025031891376.md): Roller · inoperative · Mar 6, 2025 · N121UP · Airbus A300F4622R · Passenger/Crew Doors
  > **SUPPLEMENTAL SDR** FAULT: APG Z200 L1 DOOR FWD. LOWER LATCH ROLLER LOOSE OR WORN DOT#58/43 DARRYL FORD 91102506. PERFOMED INSPECTION OF L1 DOOR FWD LOWER LATCH ROLLER, AFTER FURTHER INVESTIGATION FOUND ROLLER LOOSE. REMOVED AND REINSTALL CORRECTLY IAW A
- [SDR IPXA2025030691419](https://openairdocs.org/sdr/IPXA2025030691419.md): Roller · frozen · Mar 6, 2025 · N121UP · Airbus A300F4622R · Passenger/Crew Doors
  > L1 DOOR CUTOUT UPPER FWD. DOOR JAMB ROLLER FROZEN.
- [SDR IPXA2025030691376](https://openairdocs.org/sdr/IPXA2025030691376.md): Roller · loose · Mar 6, 2025 · N121UP · Airbus A300F4622R · Passenger/Crew Doors
  > L1 DOOR FWD. LOWER LATCH ROLLER LOOSE OR WORN.
- [SDR IPXA2025040777911](https://openairdocs.org/sdr/IPXA2025040777911.md): Floorbeam · cracked · Mar 5, 2025 · N121UP · Airbus A300F4622R · Fuselage Main, Floor Beam
  > MCD FLOOR STRUCTURE CROSSBEAM C74 Y2127 SUPPORT ANGLE HAS A CRACK. DOT 68-06. INSTALLED PANELS: 261PF, 261VF, 261JM,251TU, 261DX,261GX IAW A300 AMM 53-10-23. VERIFIED ACCOMPLISHED PERMANENT REPAIR IN ACCORDANCE WITH EO-93165-REQ1 AND VT-MAE EA 300-5318-27-A3
- [SDR IPXA2025040777848](https://openairdocs.org/sdr/IPXA2025040777848.md): Crossbeam · cracked · Mar 5, 2025 · N121UP · Airbus A300F4622R · Fuselage Main, Structure
  > MCD FLOOR STRUCTURE CROSSBEAM C74 -Y2127 SUPPORT ANGLE HAS A CRACK. DOT 68-05. INSTALL PANELS: 262PF, 262VF, 262JM, 252TU,262DX, 262GX. VERIFIED ACCOMPLISHED PERMANENT REPAIR IN ACCORDANCE WITH EO-93165-REQ1 AND VT-MAE EA 300-5318-27-A3864, REV. -.
- [SDR IPXA2025040384140](https://openairdocs.org/sdr/IPXA2025040384140.md): Seat Track · damaged · Mar 5, 2025 · N121UP · Airbus A300F4622R · Fuselage, Seat/Cargo Attach Fittings
  > MCD FLOOR STRUCTURE AT FR26/Y0 L/SIDE ADAPTER CLS HAS EXFOLIATION. DOT 34-013. VERIFIED PERMANENT REPAIR ACCOMPLISHED IAW EO-93257-REQ1 REV. 2 AND VT-MAE EA 300-5313-27-A3851.
- [SDR IPXA2025040884181](https://openairdocs.org/sdr/IPXA2025040884181.md): Adapter · broken · Mar 5, 2025 · N121UP · Airbus A300F4622R · Fuselage Miscellaneous Structure
  > **SUPPLEMENTAL SDR** FAULT: STR-Z200-MCD FLOOR STRUCTURE AT FR37 ADAPTER CLS IS BROKEN (REF PNL 241KF). DOT 34-014. VERIFIED INSTALLATION OF CLS ADAPTER USING EXISTING FASTENERS IAW A300-600 SRM 51-40-10. P/N NSA5075-6 BATCH 0004291986. REVIEWED.
- [SDR IPXA2025040484412](https://openairdocs.org/sdr/IPXA2025040484412.md): Adapter · corroded · Mar 5, 2025 · N121UP · Airbus A300F4622R · Fuselage Main, Structure
  > MDC FR57 UNDER FLOOR PANEL 251LG ADAPTER CLS HAS CORROSION.- DOT 11-008. INSTALLED ADAPTER IAW A300-600 SRM 51-40-21 WITH FASTENERS P/N: DAN8-6-14 BATCH:0004085613 AND COLLAR P/N: BACC30U4 BATCH:0001224358. REVIEWED
- [SDR IPXA2025040484376](https://openairdocs.org/sdr/IPXA2025040484376.md): Adapter · corroded · Mar 5, 2025 · N121UP · Airbus A300F4622R · Fuselage Main, Structure
  > MDC FR57.1 UNDER FLOOR PANEL 251LG ADAPTER CLS HAS CORROSION.- DOT 11-007. OK TO INSTALL CLS ADAPTER GIVEN. COMPLIED WITH STEP 10 OF PELIMINARY 2 E.A.# 300-5316-27-A3846. ACCOMPLISH PERMANENT REPAIR IN ACCORDANCE WITH EO-93187-REQ1 AND VT-MAE EA 300-5316-27-A
- [SDR IPXA2025040478227](https://openairdocs.org/sdr/IPXA2025040478227.md): Adapter · corroded · Mar 5, 2025 · N121UP · Airbus A300F4622R · Fuselage Main, Structure
  > MCD FLOOR STRUCTURE CROSSBEAM C60 AT Y0 CLS ADAPTER HAS EXFOLIATION. DOT 68-07. OK TO INSTALL CLS ADAPTER GIVEN. COMPLIED WITH STEP 10 OF PELIMINARY 2 E.A.# 300-5317-27-A3844. REVIEWED
- [SDR IPXA2025040178227](https://openairdocs.org/sdr/IPXA2025040178227.md): Adapter · corroded · Mar 5, 2025 · N121UP · Airbus A300F4622R · Fuselage Main, Structure
  > **SDR FILED OPEN** MCD FLOOR STRUCTURE CROSSBEAM C60 AT Y0 CLS ADAPTER HAS EXFOLIATION. DOT 68-07 ACCOMPLISH PERMANENT REPAIR IN ACCORDANCE WITH EO-93185-REQ1 AND VT-MAE EA 300-5317-27-A3844, REV. -.CAUTION: THE WORK INSTRUCTIONS CONTAINED WITHIN (OR APPROVED
- [SDR IPXA2025040179061](https://openairdocs.org/sdr/IPXA2025040179061.md): Adapter · corroded · Mar 5, 2025 · N121UP · Airbus A300F4622R · Fuselage Miscellaneous Structure
  > FAULT: STR-Z200-MCD FLOOR STRUCTURE CROSSBEAM C57-3 AT Y0(RH) CLS ADAPTER WITH CORROSION. DOT 68-15. VERIFIED ACCOMPLISHMENT OF STEP 11 OF EA-300-5316-27 PRELIMINARY 2. INSTALLED CLS ADAPTER PER AIRBUS DRAWING A53275477 AND PER A300-600F SRM 51-40-21. HARDWARE
- [SDR IPXA2025032884181](https://openairdocs.org/sdr/IPXA2025032884181.md): Adapter · broken · Mar 5, 2025 · N121UP · Airbus A300F4622R · Fuselage, Seat/Cargo Attach Fittings
  > MCD FLOOR STRUCTURE AT FR37 ADAPTER CLS IS BROKEN (REF PNL 241KF). OPEN
- [SDR IPXA2025032284030](https://openairdocs.org/sdr/IPXA2025032284030.md): Adapter · corroded · Mar 5, 2025 · N121UP · Airbus A300F4622R · Fuselage, Seat/Cargo Attach Fittings
  > MCD FLOOR STRUCTURE AT FR27/Y0 L/SIDE AROUND ADAPTER CLS HAS EXFOLIATION. DOT 34-012. INSTALLED 02 BRACKETS AT TRACK ADAPTER LH FR27 AT MAIN CARGO DECK WITH HARDWARE IAW SRM 51-40-21.
- [SDR IPXA2025032484021](https://openairdocs.org/sdr/IPXA2025032484021.md): Adapter · corroded · Mar 5, 2025 · N121UP · Airbus A300F4622R · Fuselage, Seat/Cargo Attach Fittings
  > MAIN DECK CARGO FR27 UNDER FLOOR PANEL 232SG ADAPTER CLS HAS EVIDENCE OF CORROSION.- DOT 11-004. INSTALLED 02 BRACKETS AT TRACK ADAPTER RH FR27 AT MAIN CARGO DECK WITH HARDWARE. NSTALLED CLS ADAPTER RH FR27 AT MAIN CARGO DECK WITH HARDWARE.
- [SDR IPXA2025032984376](https://openairdocs.org/sdr/IPXA2025032984376.md): Adapter · corroded · Mar 5, 2025 · N121UP · Airbus A300F4622R · Fuselage, Seat/Cargo Attach Fittings
  > **SDR FILED OPEN** FAULT: STR-Z200 MDC FR57.1 UNDER FLOOR PANEL 251LG ADAPTER CLS HAS CORROSION.- DOT 11-007 VERIFIED STEP 3 ON PRELIM 1 EA-300-5316-27-A3846 COMPLIED WITH ON TRAVELER T/25 1804419
- [SDR IPXA2025032684162](https://openairdocs.org/sdr/IPXA2025032684162.md): Bushing · worn · Mar 5, 2025 · N121UP · Airbus A300F4622R · Cargo/Baggage Doors
  > FWD CARGO COMPARTAMENT DOOR LOCK FITTING ECCENTRIC BOLTS.ALL 10 EA ECCENTRI BUSHING IS WORN OUT.NO DOT (DARIO CAMACHO). REMOVED AND REPLACED 10 FWD CARGO DOOR LOCK FITTINGS ECCENTRIC BUSHINGS IAW AMM 52-30-31/401.
- [SDR IPXA2025032884412](https://openairdocs.org/sdr/IPXA2025032884412.md): Adapter · corroded · Mar 5, 2025 · N121UP · Airbus A300F4622R · Fuselage Miscellaneous Structure
  > **SDR FILED OPEN**FAULT: STR-Z200 MDC FR57 UNDER FLOOR PANEL 251LG ADAPTER CLS HAS CORROSION.- DOT 11-008 E.A. #: 300-5316-27-A3845 PRELIMINARY 1 STEP 1<BR><BR>REMOVED AND DISCARTHE DAMAGED CLS ADAPTER INSTALLED AT FR57, Y0 LH. SEE FIGURE 1 FOR THE DISCREPANT
- [SDR IPXA2025032676695](https://openairdocs.org/sdr/IPXA2025032676695.md): Floorbeam · broken · Mar 5, 2025 · N121UP · Airbus A300F4622R · Fuselage Main, Floor Beam
  > MCD FLOOR STRUCTURE FR80 Y1580 SUPPORT ANGLE IS BROKEN. DOT 68-02. INSTALLED ANGLE IAW A300-600 SRM 51-40-20. P/N MS20246AD6-10 BATCH 0004366677, P/N MS20426AD6-7 BATCH 0004370836, P/N 04-001--0109 BATCH 0004355127.
- [SDR IPXA2025032683675](https://openairdocs.org/sdr/IPXA2025032683675.md): Adapter · broken · Mar 5, 2025 · N121UP · Airbus A300F4622R · Fuselage Main, Structure
  > MCD FLOOR STRUCTURE AT FR32/Y1952 HAS ADAPTER CLS BROKEN (REF. PNL 241EF). DOT 34-010. INSTALLED NEW ADAPTOR CLS IAW SRM A300/600 TASK: 51-40-21.
- [SDR IPXA2025031384144](https://openairdocs.org/sdr/IPXA2025031384144.md): Floor Panel · cracked · Mar 5, 2025 · N121UP · Airbus A300F4622R · Fuselage Floor Panel
  > FAULT: INT-Z200 MCD FLOOR PANEL 232LF HAS A CRACK.- DOT 11-005. FABRICATED FLOOR PANEL 232LF USING MATERIALS: / PN: 04-001-0012 BATCH: 004334757 QTY 1. PN: 04-001-0377 BATCH: 0004363809 QTY 1 PN: G2001B-3P BATCH: 003497365 QTY 100 PN: G2002B-3S BATCH: 00043289
- [SDR IPXA2025031384189](https://openairdocs.org/sdr/IPXA2025031384189.md): Floor Panel · broken · Mar 5, 2025 · N121UP · Airbus A300F4622R · Fuselage Floor Panel
  > FAULT: INT-Z200 MCD FLOOR PANEL 232NJ BROKEN.- DOT 11-006. FABRICATED FLOOR PANEL 232NJ USING MATERIALS: / PN: 04-001-0012 BATCH: 004334757 QTY 1 PN: 04-001-0377 BATCH: 0004363809 QTY 1 PN: G2001B-3P BATCH: 003497365 QTY 100 PN: G2002B-3S BATCH: 0004328979 QT
- [SDR IPXA2025042860851](https://openairdocs.org/sdr/IPXA2025042860851.md): Skin · cracked · Mar 4, 2025 · N121UP · Airbus A300F4622R · Fuselage Main, Plate/Skin
  > CRACK FOUND IN HOLE A ON LH FR47 HORIZONTAL JUNCTION. AREA. INSTALLED NEW FASTENER P/N: EN6114V10-42 BATCH#:0004380268 AND NUT P/N: ASNA2531-10 BATCH#: 0004377544 AND SEALANT P/N:04-001-0169 BACTH: 0004310740 IAW A300-600 SRM 51-40-21 AND E.A.#: 300-5710-27-A
- [SDR IPXA2025041060873](https://openairdocs.org/sdr/IPXA2025041060873.md): Skin · cracked · Mar 4, 2025 · N121UP · Airbus A300F4622R · Fuselage Main, Plate/Skin
  > CRACK FOUND IN HOLE E ON LH FR47 HORIZONTAL JUNCTION. AREA MARKED IN BLACK. INSTALLED NEW FASTENER P/N: EN6114T9-30 BATCH#:0003918575 AND NUT P/N: ASNA2531-9 BATCH#: 0004014715 AND SEALANT P/N:04-001-0169 BACTH: 0004310740 IAW A300-600 SRM 51-23-10 AND E.A.#
- [SDR IPXA2025032656563](https://openairdocs.org/sdr/IPXA2025032656563.md): Structure · cracked · Mar 4, 2025 · N121UP · Airbus A300F4622R · Wing Main, Frame Structure
  > FAULT: CRACK FOUND IN MIDDLE HOLE ON FR40 RH UPPER TENSION FAST. REPAIR PER A300-600F SRM REV 41 CHAP 57-10-24-201 PARA 5.A, FIG 202 AND FIG 206 SHEET 2 (REPAIR WITH BUSH).UPS CONSIDERS THIS A MINOR REPAIR PER GMM 05.04. CAUTION:THE WORK INSTRUCTIONS CONTAINED
- [SDR IPXA2025032656520](https://openairdocs.org/sdr/IPXA2025032656520.md): Frame · cracked · Mar 4, 2025 · N121UP · Airbus A300F4622R · Fuselage Main, Frame
  > FAULT: CRACK FOUND IN TOP HOLE ON FR40 LH UPPER TENSION FASTENER. REPAIR PER A300-600F SRM REV 41 CHAP 57-10-24-201 PARA 5.A, FIG 206 SHEET 1 (REPAIR WITHOUT BUSH).UPS CONSIDERS THIS A MINOR REPAIR PER GMM 05.04.CAUTION:THE WORK INSTRUCTIONS CONTAINED WITHIN (
- [SDR IPXA2025032656542](https://openairdocs.org/sdr/IPXA2025032656542.md): Frame · cracked · Mar 4, 2025 · N121UP · Airbus A300F4622R · Fuselage Main, Frame
  > FAULT: CRACK FOUND IN MIDDLE HOLE ON FR40 LH UPPER TENSION FASTENER. REPAIR PER A300-600F SRM REV 41 CHAP 57-10-24-201 PARA 5.A, FIG 202 & FIG 206 SHEET 2 (REPAIR WITH BUSH).UPS CONSIDERS THIS A MINOR REPAIR PER GMM 05.04.CAUTION: THE WORK INSTRUCTIONS CONTAIN
- [SDR IPXA2025032657484](https://openairdocs.org/sdr/IPXA2025032657484.md): Angle · broken · Mar 4, 2025 · N121UP · Airbus A300F4622R · Wing Main, Frame Structure
  > RH/WING, DEFLECTOR PANEL 672AB, METAL FINGER BROKEN DOT-008 DD5240. REPLACED ANGLE-CONDUCTOR AT RH/WING, DEFLECTOR PANEL 672AB IAW A300-600F SRM 51-40-21. REQUEST OK TO PERFORM BONDING TEST.
- [SDR IPXA2025032660192](https://openairdocs.org/sdr/IPXA2025032660192.md): Panel · broken · Mar 4, 2025 · N121UP · Airbus A300F4622R · Wing Main, Frame Structure
  > RH/WING, DEFLECTOR PANEL 672CB, METAL FINGERS BROKEN DOT-009 DD5240. REPLACED ANGLE-CONDUCTOR AT RH WING, DEFLECTOR PANEL 672 CB IAW SRM 51-40-21. REQUEST OK TO PERFORM BONDING TEST.
- [SDR IPXA2025032660374](https://openairdocs.org/sdr/IPXA2025032660374.md): Angle · broken · Mar 4, 2025 · N121UP · Airbus A300F4622R · Wing Miscellaneous Structure
  > RH/WING, DEFLECTOR PANEL 672GB, METAL FINGERS BROKEN DOT-010 DD5240. REPLACED ANGLE-CONDUCTOR AT RH WING, DEFLECTOR PANEL 672 GB IAW A300-600F SRM 51-40-21. GIVEN OK TO PERFORM BONDING TEST.
- [SDR IPXA2025032660851](https://openairdocs.org/sdr/IPXA2025032660851.md): Frame · cracked · Mar 4, 2025 · N121UP · Airbus A300F4622R · Fuselage Main, Frame
  > FAULT: CRACK FOUND IN HOLE A ON LH FR47 HORIZONTAL JUNCTION. AREA MARKED IN BLACK VERIFIED STEP 12 REAM FASTENER HOLE CONCENTRICALLY IN ALL LAYERS FROM TO 0.6235" TO 0.6250" TO THE FINAL SIZE: 0.6250" IAW SRM 51-40-44 AND E.A.#: 300-5710-27-A3836 STEP #9 PRELI
- [SDR IPXA2025032663969](https://openairdocs.org/sdr/IPXA2025032663969.md): Support Plate · broken · Mar 4, 2025 · N121UP · Airbus A300F4622R · Fuselage Miscellaneous Structure
  > MDC FLOOR STRUCTURE FR 38 RH SIDE SUPPORT PLATE BROKEN.- DOT 11-002. INSTALLED SUPPORT PLATE ON FLOOR STRUCTURE IAW SRM 51-40-21 FASTENERS 6EA.
- [SDR IPXA2025032664052](https://openairdocs.org/sdr/IPXA2025032664052.md): Support Plate · broken · Mar 4, 2025 · N121UP · Airbus A300F4622R · Fuselage Miscellaneous Structure
  > MDC FLOOR STRUCTURE FR 37 RH SIDE SUPPORT PLATE BROKEN. DOT 11-003. VERIFIED INSTALLATION OF SUPPORT PLATE ON FLOOR STRUCTURE IAW A300/600 SRM 51-40-21. INSTALLED SUPPORT PLATE ON FLOOR STRUCTURE IAW A300/600 SRM 51-40-21.
- [SDR IPXA2025032162809](https://openairdocs.org/sdr/IPXA2025032162809.md): Support Plate · broken · Mar 4, 2025 · N121UP · Airbus A300F4622R · Fuselage Miscellaneous Structure
  > MCD FLOOR STRUCTURE BTWN FR38/38.1 L/SIDE HAS SUPPORT PLATE BROKEN. DOT 34-009.THE STR-Z200-MCD FLOOR STRUCTURE BTWN FR38/38.1 L/SIDE BROKEN SUPPORT PLATE DOT 34-009 REMOVED IAW SRM 517210.INSTALLED PART P/N A53781038103821400, BATCH # 0004027717 IAW A300-600
- [SDR IPXA2025032637187](https://openairdocs.org/sdr/IPXA2025032637187.md): Doubler · punctured · Mar 3, 2025 · N121UP · Airbus A300F4622R · Wing, Plate/Skin
  > FAULT - STR - Z600 - R/H WING, I/B FLAP LOWER SKIN, BETWEEN RIB 9 AND 10, AT 1.7 IN I/B OF RIB 10, 2 PUNCTURES AT 14 AND 15 IN OF TRAILING EDGE. DOT 73-036 VERIFIED APPLICATION OF TOP COAT AT EXTERNAL PLATE (DOUBLER) ON R/H WING, I/B FLAP LOWER INNER SKIN, BET
- [SDR IPXA2025032621202](https://openairdocs.org/sdr/IPXA2025032621202.md): Skin · cracked · Mar 2, 2025 · N121UP · Airbus A300F4622R · Cargo/Baggage Doors
  > LOWER FWD CARGO DOOR INNER SKIN BTW BEAM 1-2 BTW FR 22-22A WITH CRACK-DOT 139/12-MR/139. AFT FURTHER EVAL BTWN FR 22-22A LWR FWD CGO DR INNER SKIN NO CRACK NOTED ONLY SCRATCHES. VERIFIED RMVL OF SCRATCHES BY HAND USING SCOTCH BRITE NEGLIGIBLE MATERIAL LOSS IA
- [SDR IPXA2025032623937](https://openairdocs.org/sdr/IPXA2025032623937.md): Access Panel · cracked · Mar 2, 2025 · N121UP · Airbus A300F4622R · Wing, Plate/Skin
  > R/H WING, ACCESS 613AB, FWD R/H CORNER WITH CRACK. DOT 73-028. VERIFIED INSTALLATION OF REPAIR PARTS IAW SRM 53-15-63.
- [SDR IPXA2025032610358](https://openairdocs.org/sdr/IPXA2025032610358.md): Cover · cracked · Mar 1, 2025 · N121UP · Airbus A300F4622R · Wing Main, Frame Structure
  > RH WING, FAIRING 632BB, CIRCLE PANELS ARE CRACKED (3EA) DOT 103-44. REMOVED AND REPLACED PANELS COVER 632AL 632FL AT R/H WING FAIRING 632BB IAW AMM 27-50-21.
- [SDR IPXA2025040901673](https://openairdocs.org/sdr/IPXA2025040901673.md): Skin · dented · Feb 28, 2025 · N121UP · Airbus A300F4622R · Fuselage Main, Plate/Skin
  > **SDR FILED OPEN** FAULT/ STR/ZONE 100 LOWER HALF OF FUSELAGE (EXTERNAL)R/H. FR 3 APPROXIMATELY STG44 / STG 40 THEREIA A DENT.DOT 113-20(DARIO CAMACHO) VERIFIED RESTORATION OF ALL OXYGEN SYSTEM, STORAGE BOX IAW-A300 AMM 35-11-11/401.
- [SDR IPXA2025040806386](https://openairdocs.org/sdr/IPXA2025040806386.md): Seal · damaged · Feb 28, 2025 · N121UP · Airbus A300F4622R · Wing Main, Frame Structure
  > RH WING, FAIRING 636AB HASO/B SIDE BULB SEAL DAMAGED. DOT 103-10. INSTALLED NEW I/B SIDE BULB SEAL ON R/H WING FAIRING 636AB IAW A300-600 SRM 51-40-23. P/N A5786412800200 BATCH#0004340329, CR3212-4-03, BATCH#0004217010.
- [SDR IPXA2025032604139](https://openairdocs.org/sdr/IPXA2025032604139.md): Skin · cracked · Feb 28, 2025 · N121UP · Airbus A300F4622R · Vertical Stabilizer, Plate/Skin
  > EMPENNAGE PANEL 322AL HAS A CRACK DOT 113-11(DARIO CAMACHO). INSTALLED VERTICAL STAB L/E PANEL 322AL IAW A300 AMM 55-32-11/401 P/N 04-001-0306 BATCH 0004378368.
- [SDR IPXA2025032606193](https://openairdocs.org/sdr/IPXA2025032606193.md): Cover · cracked · Feb 28, 2025 · N121UP · Airbus A300F4622R · Wing Main, Frame Structure
  > **SDR FILED OPEN**FAULT - Z600, APG, RH WING, FAIRING 635BB HAS CIRCLE PANEL CRACKED AT SCREW HOLE (2EA). DOT 103-08 APPROVED
- [SDR IPXA2025032203743](https://openairdocs.org/sdr/IPXA2025032203743.md): Bracket · cracked · Feb 28, 2025 · N121UP · Airbus A300F4622R · Fuselage Miscellaneous Structure
  > FWD CARGO AFT BULKHEAD AREA FR38.2 HAS A CRACKED BRACKET LH SIDE Y450 MARKED 07586-01. INSTALLED NEW BRACKET WITH SOLID RIVET P/N NAS1097AD5-11 BATCH #0004234792, FASTENERS P/N DAN5-5-9 BATCH #0004244667, COLLAR P/N NSA5075-5 BATCH #0004148352 AND SEALANT P/N
- [SDR IPXA2024101177207](https://openairdocs.org/sdr/IPXA2024101177207.md): Indicator · inoperative · Oct 11, 2024 · N121UP · Airbus A300F4622R · Escape Slide
  > EVACUATION SLIDE RELEASE WARNING SYSTEM LIGHT INOP PERFORMED ADJUSTMENT/TEST OF EMERGENCY ESCAPE SLIDE WARNING SYSTEM PER A300 AMM 52-73-00/001. ALL OPS NORMAL AUTH. #2826586 CLEARED PLACARD REMOVED. NO DMP

Next page: https://openairdocs.org/aircraft/N121UP/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 = 'N121UP' AND registry_match = 'registration'
ORDER BY difficulty_date DESC
```

This list as a web page: https://openairdocs.org/aircraft/N121UP/reports

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OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.