# Service difficulty reports: N718FD, cancelled Mar 2, 2024

A list on [N718FD, cancelled Mar 2, 2024](https://openairdocs.org/deregistered/N718FD-2024-03-02.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 · 130 reports

- [SDR FDEA201305150999](https://openairdocs.org/sdr/FDEA201305150999.md): Spring · failed · May 15, 2013 · N718FD · Airbus A300B4622 · Wing Miscellaneous Structure
  > ACCESS PANEL 572CB INBD SPRING ROD ASSY DAMAGED. SPRING ASSY FOUND TO HAVE FAILED INSIDE FLAP SHROUD BOX, THIS HAD CAUSED STRUCTURAL DAMAGE TO THE FWD WEB AND FLAP DRIVE TORQUE SHAFT. REPAIRED IAW EA 6-5751-167417.
- [SDR FDEA201210033548](https://openairdocs.org/sdr/FDEA201210033548.md): Spar · damaged · Oct 3, 2012 · N718FD · Airbus A300F4622R · Wing Spar
  > RT FR47 REAR SPAR HOLE, UNKNOWN IF BUSH EXISTS IN REAR FITTING. BORE OK AFT FACE OF HOLE, SURFACE FINISH REMOVED IAW SRM 51-75-20, NO BUSH PRESENT. NEW BOLT FITTED IAW SRM 51-40-21 SURFACE FINISH RESTORED IAW SRM 51-23-10 AND EO 6-5710- 7-3305 P2.
- [SDR FDEA201210033547](https://openairdocs.org/sdr/FDEA201210033547.md): Spar · damaged · Oct 3, 2012 · N718FD · Airbus A300F4622R · Wing Spar
  > RT FR47 REAR SPAR HOLE, UNKNOWN IF BUSH EXISTS IN REAR FITTING. BORE OK AFT FACE OF HOLE WITH SURFACE FINISH REMOVED IAW SRM 51-75-20, NO BUSH PRESENT. NEW BOLT FITTED IAW SRM 51-40-21 SURFACE FINISH RESTORED IAW SRM 51-23-10 AND EO 6-5710- 7-3305 P2.
- [SDR FDEA201210013525](https://openairdocs.org/sdr/FDEA201210013525.md): Structure · damaged · Oct 1, 2012 · N718FD · Airbus A300B4622 · Spoilers
  > RT WING NR 2 SPOILER FWD POINT OF OTBD EDGE WORN. REPAIRED ON EA6-5771-157943, CAT B.
- [SDR FDEA201210013522](https://openairdocs.org/sdr/FDEA201210013522.md): Skin · dented · Oct 1, 2012 · N718FD · Airbus A300F4622R · Fuselage Main, Plate/Skin
  > SHALLOW DENT EVIDENT BETWEEN AFT CARGO DOOR AND BULK CARGO DOOR FR 66, STR 38R-39R, FRAME 66 RT BETWEEN STR 38-39 DENT REPAIRED IAW SRM 53-10-12, FIG 228 MAJOR REPAIR WITH SMR REQUIRMENTS CAT B IAW SRI 53-10-12-2-009-00.
- [SDR FDEA201209283504](https://openairdocs.org/sdr/FDEA201209283504.md): Skin · damaged · Sep 28, 2012 · N718FD · Airbus A300F4622R · Wing, Plate/Skin
  > RT WING LOWER SKIN HOLE 'S' BUSHINGS TO BE FABRICATED IAW ORIGINAL RAS INSTRUCTION. RT HOLE 'S' REWORKED IAW JPF STEP 2 IAW SRM 51-40-21. 3 BUSHINGS INSTALLED AT 19.1MM DIA IAW RDAS 70566845-003-2012 INSTRUCTION FOR RT SIDE HOLE NR1.
- [SDR FDEA201209283501](https://openairdocs.org/sdr/FDEA201209283501.md): Skin · cracked · Sep 28, 2012 · N718FD · Airbus A300F4622R · Wing, Plate/Skin
  > LEFT WING LOWER SKIN HOLE G SHOWS EVIDENCE OF A CRACK INDICATION AND MECHANICAL DAMAGE IN THE MAIN BORE. THIS IS A PREVIOUSLY REWORKED HOLE. HOLE G REWORKED UNTIL MECHANICAL DAMAGE REMOVED AND NO CRACK INDICATION STARTING AT A BORE DIAMETER OF 0.530"/13.462M
- [SDR FDEA201209283500](https://openairdocs.org/sdr/FDEA201209283500.md): Skin · damaged · Sep 28, 2012 · N718FD · Airbus A300F4622R · Wing, Plate/Skin
  > LEFT WING LOWER SKIN HOLE 'S' SHOWS EVIDENCE OF MECHANICAL DAMAGE FROM STEEL BUSHES THROUGH THE FULL BORE DEPTH. THIS IS A PREVIOUSLY REWORKED HOLE. HOLE 'S' REWORKED UNTIL MECHANICAL DAMAGE REMOVED STARTING AT A BORE DIAMETER OF 0.751"/19.075MM TO FINAL D
- [SDR FDEA201209283499](https://openairdocs.org/sdr/FDEA201209283499.md): Spar · damaged · Sep 28, 2012 · N718FD · Airbus A300F4622R · Wing Spar
  > LEFT WING FRM 47 HOLE C, MECHANICAL DAMAGE FOUND IN INTERNAL BORE OF FASTENER HOLE. MECHANICAL DAMAGE REMOVED IAW SRM 51-40-30 FINAL HOLE C DIAMETER IS 0.561"/14.249MM. REWORKED IAW EA 6-5710-162973, PAGE 2.
- [SDR FDEA201209283497](https://openairdocs.org/sdr/FDEA201209283497.md): Skin · cracked · Sep 28, 2012 · N718FD · Airbus A300F4622R · Wing, Plate/Skin
  > LEFT WING LOWER SKIN HOLE F SHOWS EVIDENCE OF A CRACK INDICATION. THIS HOLE IS A PREVIOUSLY DIA 0.529 HOLE F REWORKED UNTIL CRACK REMOVED IAW SRM 51-40-30 AND EA 6-5710-162973, PAGE 3. HOLE F FINAL DIAMETER IS 0.561"/14.249MM.
- [SDR FDEA201209283496](https://openairdocs.org/sdr/FDEA201209283496.md): Spar · damaged · Sep 28, 2012 · N718FD · Airbus A300F4622R · Wing Spar
  > RT WING FR47 REAR SPAR HOLE V POSSIBLE BUSH WITH X4 IMPACT DAMAGE MARKS IN REAR FITTING. NO BUSH WAS FOUND AND HOLE V REMOVED. MECHANICAL DAMAGE IAW SRM 51-40-30 AND EA 6-5710-162973, PAGE 11. FINAL DIAMETER IS 0.584"/14.834 MM.
- [SDR FDEA201209283495](https://openairdocs.org/sdr/FDEA201209283495.md): Spar · cracked · Sep 28, 2012 · N718FD · Airbus A300F4622R · Wing Spar
  > RIGHT WING HOLE L CRACK INDICATED BY NDT INSP CRACK IS ASSESSED AS A CORNER CRACK IN THE FRM AT THE INTERFACE WITH REAR ANGLE FITTING AT 1 O'CLOCK POSITION HOLE L REWORKED UNTIL NO CRACK INDICATION IAW SRM 51-40-30. FINAL HOLE DIAMETER 0.624"/15.849 AS DE
- [SDR FDEA201209283494](https://openairdocs.org/sdr/FDEA201209283494.md): Frame · damaged · Sep 28, 2012 · N718FD · Airbus A300F4622R · Fuselage Main, Frame
  > RIGHT FRAME 47 REAR SPAR HOLE H SHOWS EVIDENCE OF MECHANICAL DAMAGE AT 9 O'CLOCK THROUGH REAR SPAR DEPTH. MECHANICAL DAMAGE REMOVED FROM HOLE IAW SRM 51-40-30 FINAL BORE DIAMETER -0.499" AND THE MAXIMUM ALLOWED IN EO 6-5710-7-3305, PT 2 IS 0.499" REFER TO R
- [SDR FDEA201209283493](https://openairdocs.org/sdr/FDEA201209283493.md): Frame · damaged · Sep 28, 2012 · N718FD · Airbus A300F4622R · Fuselage Main, Frame
  > RIGHT FRAME 47 REAR SPAR HOLE 'G' SHOWS EVIDENCE OF A CRACK INDICATION. THIS IS A PREVIOSULY REWORKED HOLE. MATERIAL REMOVED UNTIL CRACK INDICATION REMOVED STARTING AT BORE DIAMETER 0.259" TO FINAL BORE DIAMETER 0.560" IAW SRM 51-40-30 AND EA 6-5710-16297
- [SDR FDEA201209283491](https://openairdocs.org/sdr/FDEA201209283491.md): Frame · damaged · Sep 28, 2012 · N718FD · Airbus A300F4622R · Fuselage Main, Frame
  > LEFT FRAME 47 REAR SPAR HOLE 'I' SHOWS EVIDENCE OF MECHANICAL DAMAGE AT 12 O'CLOCK THROUGH THE FULL BORE DEPTH. HOLE "I" REWORKED MECHANICAL DAMAGE REMOVED STARTING AT A BORE DIAMETER OF 0.531"/13.487MM TO 0.561"14.249MM IAW SRM 51-40-30 AND EA 6-5710-162
- [SDR FDEA201209283490](https://openairdocs.org/sdr/FDEA201209283490.md): Frame · damaged · Sep 28, 2012 · N718FD · Airbus A300F4622R · Fuselage Main, Frame
  > LEFT FRAME 47 REAR SPAR HOLE 'N' SHOWS EVIDENCE OF MECHANICAL DAMAGE AT 5 O'CLOCK THROUGH THE FORWARD FITTING AND MAIN SPAR DEPTHS. MECHANICAL DAMAGE REMOVED FROM HOLE "N" IAW SRM 51-40-30 AND THE FINAL BORE DIAMETER IS 0.5605". THE MAXIMUM ALLOWED IN EO 6-
- [SDR FDEA201209283489](https://openairdocs.org/sdr/FDEA201209283489.md): Frame · damaged · Sep 28, 2012 · N718FD · Airbus A300F4622R · Fuselage Main, Frame
  > LEFT FRAME 47 REAR SPAR HOLE 'M' SHOWS EVIDENCE OF MECHANICAL DAMAGE AT 11 O'CLOCK THROUGH THE FULL BORE DEPTH. MECHANICAL DAMAGE REMOVED FROM HOLE M STARTING AT A BORE DIAMETER OF 0.5295"/13.449MM TO FINAL DIAMETER OF 0.561"/14.249 MM IAW SRM 51-40-30 AND
- [SDR FDEA201209283488](https://openairdocs.org/sdr/FDEA201209283488.md): Frame · damaged · Sep 28, 2012 · N718FD · Airbus A300F4622R · Fuselage Main, Frame
  > LEFT FRAME 47 REAR SPAR HOLE 'H' SHOWS EVIDENCE OF MECHANICAL DAMAGE AT 6 O'CLOCK AND 12 O'CLOCK THROUGH THE FULL BORE DEPTH. MECHANICAL DAMAGE REMOVED IAW SRM 51-40-30. DAMAGE REMOVAL IN LIMITS WITH EO 6-5710-7-3305 P1 CARD 11 OF 42 ITEM 10.
- [SDR FDEA201209273480](https://openairdocs.org/sdr/FDEA201209273480.md): Angle · cracked · Sep 27, 2012 · N718FD · Airbus A300F4622R · Fuselage Miscellaneous Structure
  > LEFT MLG BAY FWD CUTOUT ANGLE CRACKED, REF SRM 53-15-13 FIG 4 ITEM 40. REPLACED ANGLE WITH NEW ANGLE FABRICATED IAW DWG A538122522 AND FITTED IAW SRM 51-40-21.
- [SDR FDEA201209233413](https://openairdocs.org/sdr/FDEA201209233413.md): Frame · cracked · Sep 23, 2012 · N718FD · Airbus A300B4622 · Fuselage Main, Frame
  > FR 51 RT BODY FRAME FOUND CRACKED AT S26R BOLT HOLE. FRAME REPLACED IAW SRM 51-40-21 AND EA 6-5315-162967.
- [SDR FDEA201209223395](https://openairdocs.org/sdr/FDEA201209223395.md): Frame · cracked · Sep 22, 2012 · N718FD · Airbus A300B4622 · Fuselage Main, Frame
  > FRAME 49 FOUND CRACKED, REWORKED AND SHOULDERED BUSHING FITTED IAW EA 6-5315-162967 AND SRM 51-40-21.
- [SDR FDEA201209223394](https://openairdocs.org/sdr/FDEA201209223394.md): Frame · cracked · Sep 22, 2012 · N718FD · Airbus A300B4622 · Fuselage Main, Frame
  > FRAME 48 FOUND CRACKED AT S26R. UPPER FRAME SECTION REPLACED IAW EA 6-5315-162967 AND SRM 51-40-21.
- [SDR FDEA201209223393](https://openairdocs.org/sdr/FDEA201209223393.md): Frame · damaged · Sep 22, 2012 · N718FD · Airbus A300B4622 · Fuselage Main, Frame
  > RIGHT FRAME 48, BOLT HOLE 2 FOUND EXCEED STANDARD SIZE. REWORKED IAW EA 6-5315-162967.
- [SDR FDEA201209223392](https://openairdocs.org/sdr/FDEA201209223392.md): Frame · damaged · Sep 22, 2012 · N718FD · Airbus A300B4622 · Fuselage Main, Frame
  > RT FRAME 51, BOLT HOLE 2 FOUND EXCEED STANDARD SIZE. BOLT HOLE REWORKED IAW EA 6-5315-162967.
- [SDR FDEA201209223391](https://openairdocs.org/sdr/FDEA201209223391.md): Frame · damaged · Sep 22, 2012 · N718FD · Airbus A300B4622 · Fuselage Main, Frame
  > RT FRAME 53, BOLT HOLE 3 FOUND EXCEED STANDARD SIZE. HOLE REWORKED IAW EA 6-5315-162967, STAGES 35-40 REF.
- [SDR FDEA201209223390](https://openairdocs.org/sdr/FDEA201209223390.md): Frame · cracked · Sep 22, 2012 · N718FD · Airbus A300B4622 · Fuselage Main, Frame
  > FR 51 BOLT HOLE 4 FOUND CRACKED AND BOLT HOLE 1-3. FOUND EXCEED STANDARD LT FRAME 51 HOLE 4 FOUND CRACKED AND HOLES 1,2 AND 3 FOUND TO EXCEED STANDARD SIZE HOLES. REWORKED IAW EA 6-5315-162967, STAGES 10 TO 34 REF.
- [SDR FDEA201209193356](https://openairdocs.org/sdr/FDEA201209193356.md): Frame · damaged · Sep 19, 2012 · N718FD · Airbus A300F4622R · Fuselage Main, Frame
  > FRAME 79 S44R FOUND DAMAGED AT FASTENER HOLE, REPAIRED IAW SRM 53-10-13, FIG 202. REPAIR CLASSIFIED AS MAJOR.
- [SDR FDEA201209183350](https://openairdocs.org/sdr/FDEA201209183350.md): Skin · delaminated · Sep 18, 2012 · N718FD · Airbus A300F4622R · Elevator, Plate/Skin
  > RT ELEVATOR TOP AND BOTTOM SKIN INBD AFT CORNER, DELAMINATING & PAINT CRACKING. REPAIRED IAW AE 6-5520-162959, RAS 70566197/003/2012. MAJOR REPAIR CAT A.
- [SDR FDEA201209183351](https://openairdocs.org/sdr/FDEA201209183351.md): Crossbeam · damaged · Sep 18, 2012 · N718FD · Airbus A300F4622R · Fuselage Main, Structure
  > AFT CARGO HOLD, ROLLER TRACK REPLACEMENT RT -Y1470 AT FR57 CROSSBEAM AND FRAME SUPPORT FITTING FOUND WITH EXTRA X2 HOLES AND CLOSE TO EXISTING STRUCTUAL FASTENERS DUE TO UNAUTHORIZED TRACK REPAIR. INVESTIGATE AND RECTIFY IAW RELEVANT MANUAL SRM. AFT CARGO H
- [SDR FDEA201209173340](https://openairdocs.org/sdr/FDEA201209173340.md): Intercostal · cracked · Sep 17, 2012 · N718FD · Airbus A300F4622R · Fuselage Miscellaneous Structure
  > INTERCOSTAL AT FR46-47, STR 42L CRACKED. REMOVED, REPLACED AND FITTED IAW SRM 51-40-21, MINOR REPAIR TO SECONDARY STRUCTURE.
- [SDR FDEA201209173338](https://openairdocs.org/sdr/FDEA201209173338.md): Skin · dented · Sep 17, 2012 · N718FD · Airbus A300F4622R · Fuselage Main, Plate/Skin
  > IMPACT DAMAGE OBSERVED IN THE LOWER FUSELAGE SKIN POCKET FWD OF TAIL STEADY LOCATION FR 85 REPAIR C/OUT IAW SRM 53-10-12, FIG 225.
- [SDR FDEA201209163334](https://openairdocs.org/sdr/FDEA201209163334.md): Skin · misrepaired · Sep 16, 2012 · N718FD · Airbus A300F4622R · Fuselage Main, Plate/Skin
  > SKIN AFT OF FR 80/82 MISREPAIRED. REMOVED REMAINING DAMAGE. REPAIRED IAW EA 6-5319-162972 CLASSIFIED AS MAJOR
- [SDR FDEA201209153329](https://openairdocs.org/sdr/FDEA201209153329.md): Skin · misrepaired · Sep 15, 2012 · N718FD · Airbus A300F4622R · Fuselage Main, Plate/Skin
  > SKIN BETWEEN FRAMES 30-31, STRINGERS 41- 42, MISREPAIRED. REPAIRED IAW SRM 53-10-12 FIG 225, SH1.
- [SDR FDEA201209143325](https://openairdocs.org/sdr/FDEA201209143325.md): Stringer · misrepaired · Sep 14, 2012 · N718FD · Airbus A300F4622R · Fuselage Main, Longeron/Stringer
  > AFT CARGO BAY STRINGER 52L MISREPAIRED FR 59-61. REPAIRED IAW SRM 53-10-14, FIG 201. REPAIR CLASSIFED AS A MAJOR
- [SDR FDEA201209113289](https://openairdocs.org/sdr/FDEA201209113289.md): Frame · dented · Sep 11, 2012 · N718FD · Airbus A300F4622R · Fuselage Main, Frame
  > DENT FOUND ON FRAME AT FR 20A RT AFT FACE AND BETWEEN STR 40 TO 41, LOWER SECTION, DENT AT FR 20A RT AFT FACE BETWEEN STR 40 TO STR 41 FOUND ACCEPTABLE IAW EA 6-5300-157946 AND RAS 70566040/003/2012. JPF ATTACHED, SHEET 1, STAGES 1-3.
- [SDR FDEA201209103347](https://openairdocs.org/sdr/FDEA201209103347.md): Skin · misrepaired · Sep 10, 2012 · N718FD · Airbus A300F4622R · Fuselage Main, Plate/Skin
  > SKIN AT FR 77, STR 53-56, MISREPAIRED. REPAIRED IAW SRM 53-10-12, FIG 228, SH3.
- [SDR FDEA201209063242](https://openairdocs.org/sdr/FDEA201209063242.md): Door · cracked · Sep 6, 2012 · N718FD · Airbus A300F4622R · Vertical Stabilizer
  > STABILIZER BAY DOOR 313AL CRACKED REPAIR IAW EA6-5241-157940 AND SRM 51-71-11, PARA 4D.
- [SDR FDEA201209043222](https://openairdocs.org/sdr/FDEA201209043222.md): Floor Support · corroded · Sep 4, 2012 · N718FD · Airbus A300F4622R · Fuselage Miscellaneous Structure
  > AFT HOLD FLOOR SUPPORT BETWEEN FR63 AND FR 64 LT FROM CENTER FOUND CORRODED. REPLACED IAW SRM 51-40-21.
- [SDR FDEA201209043218](https://openairdocs.org/sdr/FDEA201209043218.md): Floor Support · corroded · Sep 4, 2012 · N718FD · Airbus A300F4605R · Fuselage Miscellaneous Structure
  > AFT HOLD FLOOR SUPPORT BETWEEN FR63 AND FR64 SECOND FROM LT SIDE FOUND CORRODED AT ANCHOR NUT LOCATIONS. AFT HOLD SUPPORT BEAM AT FR63 AND FR64 SECOND FROM LT SIDE, REPLACED IAW SRM 51-40-21.
- [SDR FDEA201208253163](https://openairdocs.org/sdr/FDEA201208253163.md): Floor Support · corroded · Aug 25, 2012 · N718FD · Airbus A300F4622R · Fuselage Miscellaneous Structure
  > UPPER DECK FLOOR SUPPORT AT Y730 AND BETWEEN FRAMES 11 TO 14 FOUND CORRODED. REPLACED IAW SRM 51-40-01 AND DWG A53612214.
- [SDR FDEA201208163032](https://openairdocs.org/sdr/FDEA201208163032.md): Roller Track · misrepaired · Aug 16, 2012 · N718FD · Airbus A300F4622R · Fuselage Miscellaneous Structure
  > CARGO BAY FLOOR ROLLER TRACK NR 2 LT SPLICE MISREPAIRED. REPLACED IAW SRM 51-40-21, SRM 51-72-10 AND AMM 25-52-21-04-01 CLASSIFIED AS MAJOR.
- [SDR FDEA201208153015](https://openairdocs.org/sdr/FDEA201208153015.md): Bulkhead · corroded · Aug 15, 2012 · N718FD · Airbus A300F4622R · Fuselage Main, Plate/Skin
  > REAR PRESSURE BULKHEAD FOUND CORRODED. ANGLE REPLACED ON EA 6-5300-157937 AND IAW DWG R53970640.
- [SDR FDEA201208072875](https://openairdocs.org/sdr/FDEA201208072875.md): Skin · misrepaired · Aug 7, 2012 · N718FD · Airbus A300F4622R · Fuselage Main, Plate/Skin
  > SKIN FR 57.1-57.2 S35-37R MISREPAIRED. REPAIRED IAW SRM 53-10-12, PARA 9, FIG 228. REPAIR CLASSED AS MAJOR WITH CAT B
- [SDR FDEA201106272456](https://openairdocs.org/sdr/FDEA201106272456.md): Rib · cracked · Jun 27, 2011 · N718FD · Airbus A300B4622 · Wing, Rib/Bulkhead
  > LT WING RIB 5 LOWER FLANGE CRACK EVIDENT AT HOLE LOCATION 47, 5 MM IN LENGTH WITHIN SPOT FACE. REPAIR CARRIED OUT IAW EA 6-5710-150903. INTERIM REPAIR INSTALLED, RIB 5 TO BE REPLACED.
- [SDR FDEA201106272455](https://openairdocs.org/sdr/FDEA201106272455.md): Rib · cracked · Jun 27, 2011 · N718FD · Airbus A300B4622 · Wing, Rib/Bulkhead
  > LT WING RIB 5 LOWER FLANGE CRACK EVIDENT AT HOLE LOCATION 54 12MM IN LENGTH WITHIN SPOT FACE REPAIR CARRIED OUT IAW EA 6-5710-150903. INTERIM REPAIR INSTALLED, RIB 5 TO BE REPLACED BY 42500 FC.
- [SDR FDEA201106272454](https://openairdocs.org/sdr/FDEA201106272454.md): Rib · cracked · Jun 27, 2011 · N718FD · Airbus A300B4622 · Wing, Rib/Bulkhead
  > RT WING RIB 5 LOWER FLANGE CRACK EVIDENT AT HOLE LOCATION 47 10 MM IN LENGTH WITHIN SPOT FACE REPAIR CARRIED OUT IAW EA 6-57-10-150903. INTERIM REPAIR INSTALLED, RIB 5 TO BE REPLACED.
- [SDR FDEA201003200949](https://openairdocs.org/sdr/FDEA201003200949.md): Panel · delaminated · Mar 20, 2010 · N718FD · Airbus A300B4622 · Wing, Plate/Skin
  > RT WING T/E NR 2 DEFECTOR PANEL RUBBED TAPE LOOSE AND PEELING REPAIRED IAW EA 6-5720-136631. REMOVED T/E NR 2 DEFLECTOR TO FOM. REMOVED DAMAGED FOIL. APPLIED NEW ALUMINUM FOIL. INSTALLED HARDWARE IAW EA 6-5720-136631, N/R N00389 FOR ORIGINAL EA N/R N01255
- [SDR FDEA201003200948](https://openairdocs.org/sdr/FDEA201003200948.md): Deflector · delaminated · Mar 20, 2010 · N718FD · Airbus A300B4622 · Wing Miscellaneous Structure
  > RT WING T/E COVE PANEL NR 4 LOWER SURFACE METAL TAPE PEELING/MISSING REPAIRED IAW EA 6-5720-136631. REMOVED PANEL TO FOM. REMOVED ALUMINUM FOIL AND HARDWARE. APPLIED NEW ALUMINUM FOIL AND INSTALLED HARDWARE IAW EA 6-5720-136631,"WINGS - WING FLAP HINGE DE
- [SDR FDEA201003200947](https://openairdocs.org/sdr/FDEA201003200947.md): Deflector · delaminated · Mar 20, 2010 · N718FD · Airbus A300B4622 · Wing Miscellaneous Structure
  > RT WING T/E COVE PANEL NR 3 LOWER SURFACE METAL TAPE PEELING/MISSING REPAIRED IAW EA 6-5720-136631. REMOVED AND REINSTALLED HARDWARE IAW SRM 51-40-00. N/R N00389 FOR ORIGINAL EA. N/R N01255 FOR THE APPLICATION OF THE WITNESS MARK.
- [SDR FDEA201003200946](https://openairdocs.org/sdr/FDEA201003200946.md): Panel · delaminated · Mar 20, 2010 · N718FD · Airbus A300B4622 · Wing, Plate/Skin
  > RT WING T/E NR1 DEFLECTOR PANEL RUBBED TAPE LOOSE AND PEELING REPAIRED IAW EA 6-5720-136631. R & R WS HARDWARE IAW SRM 51-40-00. REMOVED AND INSTALLED OF RT WING T/E NR 1 DEFLECTOR PANEL ACCOPMPLISHED IAW AMM 27-54-41-4. NR N01255 FOR THE APPLICATION OF THE

Next page: https://openairdocs.org/deregistered/N718FD-2024-03-02/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 = 'N718FD' AND deregistration_id = 'N718FD-2024-03-02'
ORDER BY difficulty_date DESC
```

This list as a web page: https://openairdocs.org/deregistered/N718FD-2024-03-02/reports

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