# Service difficulty reports: N456FE, cancelled Apr 23, 2020

A list on [N456FE, cancelled Apr 23, 2020](https://openairdocs.org/deregistered/N456FE-2020-04-23.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 2 · 79 reports

- [SDR FDEA201204011216](https://openairdocs.org/sdr/FDEA201204011216.md): Actuator · failed · Apr 1, 2012 · N456FE · Airbus A310222 · Drag Control Actuator
  > REJECTED TAKEOFF FOR SPEED BRAKE GROUND SPOILER DEPLOYMENT AT 110KTS. GROUND SPOILER NR1 ON LT WING SHOWED DEPLOYED AMBER CHEVRON AFTER REJECT. TROUBLESHOOTING BACK AT GATE SHOWED NR 1 GROUND SPOILER DEPLOYED ON ECAM BUT STOWED ON ACFT. ACFT HAD A PRIOR SP
- [SDR FDEA201112035135](https://openairdocs.org/sdr/FDEA201112035135.md): Pressure Switch · failed · Dec 3, 2011 · N456FE · Airbus A310222 · Engine Oil Pressure
  > REJECTED TAKE OFF AT 85KTS DUE TO ECAM WARNING WARNING, LOW OIL PRESSURE ENGINE NR 2. WARNING WENT AWAY WHEN THROTTLES RETARDED. CHECKED ALL ENGINE PARAMENTERS PRIOR TO 2ND TAKE OFF. ALL NORMAL, 2ND TAKE OFF NORMAL. R & R NR 2 ENGINE OIL PRESSURE TRAMSMI
- [SDR FDEA201012054591](https://openairdocs.org/sdr/FDEA201012054591.md): Regulator Valve · failed · Dec 5, 2010 · N456FE · Airbus A310222 · Engine Oil Pressure
  > GOT HIGH OIL PRESSURE NR 2 ENG ON T/O ROLL. REJECTED T/O AT LOW SPEED. SECOND TAKEOFF NORMAL. 1ST T/O 62PSI, 2ND T/O 58 PSI. R & R 2 ENGINE OIL PRESSURE REGULATOR VALVE REF AMM 79-21-04-04-0. PERFORMED OIL PRESSURE TEST NR 7, REF 71-00-00, RAN NR2 ENGINE IAW
- [SDR FDEA201012034558](https://openairdocs.org/sdr/FDEA201012034558.md): Oil Cooler · false activation · Dec 3, 2010 · N456FE · Airbus A310222 · Engine Oil Cooler
  > GOT HIGH ENG OIL PRESSURE NR 2 ENG ON T/O ROLL. REJECTED T/O INDICATIONS WERE BACK TO NORMAL AFTER EXITING RUNWAY. RAN NR 2 ENG IAW JRH. NO DEFECTS NOTED. OIL NEVER ROSE ABOVE 58 PSI WITH THROTTLE ADVANCED AND WAS 50 TO 52 PSI AT IDLE. OIL TEMP WAS ALSO WI
- [SDR FDEA201011164395](https://openairdocs.org/sdr/FDEA201011164395.md): Skin · damaged · Nov 16, 2010 · N456FE · Airbus A310222 · Trailing Edge Flaps
  > LT WING - INBD FLAP - T/E SKIN FOUND DAMAGED. DUE TO NON APPROVED EXISTING REPAIRS THE T/E HAD TO BE REPLACED.
- [SDR FDEA201011154373](https://openairdocs.org/sdr/FDEA201011154373.md): Profile · misrepaired · Nov 15, 2010 · N456FE · Airbus A310222 · Wing Miscellaneous Structure
  > PREVIOUS REPAIR FOUND AT T/E PROFILE BTW RIB11/15 NOT TO CONFORM WITH FAA APPROVED DATA. T/E WAS REPLACED IAW EA 6-5750-144066 INSTRUCTIONS.
- [SDR FDEA201011154372](https://openairdocs.org/sdr/FDEA201011154372.md): Profile · misrepaired · Nov 15, 2010 · N456FE · Airbus A310222 · Wing Miscellaneous Structure
  > PREVIOUS REPAIR FOUND AT T/E PROFILE BTW RIB4/5 NOT TO CONFORM WITH FAA APPROVED DATA. T/E WAS REPLACED IAW EA 6-5750-144066 INSTRUCTIONS.
- [SDR FDEA201011154371](https://openairdocs.org/sdr/FDEA201011154371.md): Profile · misrepaired · Nov 15, 2010 · N456FE · Airbus A310222 · Wing Miscellaneous Structure
  > PREVIOUS REPAIR FOUND AT T/E PROFILE BETWEEN RIB13/15 NOT TO CONFORM WITH FAA APPROVED DATA. T/E WAS REPLACED IAW EA 6-5750-144066 INSTRUCTIONS.
- [SDR FDEA201011124326](https://openairdocs.org/sdr/FDEA201011124326.md): Skin · damaged · Nov 12, 2010 · N456FE · Airbus A310222 · Trailing Edge Flaps
  > PREVIOUS REPAIR FOUND AT LT INBD FLAP LOWER SKIN BTW STGR 13 & REAR SPAR AND RIBS 12/14. NEW REPAIR PERFORMED IAW EA 6-5750-144069. REPAIR NR2.
- [SDR FDEA201011124320](https://openairdocs.org/sdr/FDEA201011124320.md): Skin · corroded · Nov 12, 2010 · N456FE · Airbus A310222 · Cargo/Baggage Doors
  > FWD CARGO COMPARTMENT DOOR - LOWER INTERNAL SKIN FOUND CORRODED. PANEL SKIN WAS REPLACED AS PER SRM 51-72-10.
- [SDR FDEA201011104311](https://openairdocs.org/sdr/FDEA201011104311.md): Skin · cracked · Nov 10, 2010 · N456FE · Airbus A310222 · Cargo/Baggage Doors
  > FWD CARGO DOOR - CRACK FOUND AT INNER PLATE AT LOWER AFT CORNER. INNER SKIN REPAIRED IAW 6-5230-144190.
- [SDR FDEA201010284186](https://openairdocs.org/sdr/FDEA201010284186.md): Crossbeam · corroded · Oct 28, 2010 · N456FE · Airbus A310222 · Fuselage Main, Structure
  > AFT CARGO COMPT FLOOR - TRANSVERSAL BEAM AT FR58 FOUND CORRODED. CROSSBEAM WAS REPLACED IAW 51-72-10.
- [SDR FDEA201010254163](https://openairdocs.org/sdr/FDEA201010254163.md): Fitting · corroded · Oct 25, 2010 · N456FE · Airbus A310222 · Passenger/Crew Doors
  > FITTING LOCATED AT L1 DOOR FOUND CORRODED. REPLACED BY A NEW ONE.
- [SDR FDEA201010254162](https://openairdocs.org/sdr/FDEA201010254162.md): Crossbeam · damaged · Oct 25, 2010 · N456FE · Airbus A310222 · Fuselage Main, Structure
  > FWD CARGO COMPARTMENT - CROOSBEAM UPPER FLANGE AT FR36 DAMAGED BTW Y480 & Y- 480. CROSSBEAM WAS REPAIRED IAW SRM 53-10-15 FIGURE207.
- [SDR FDEA201010254161](https://openairdocs.org/sdr/FDEA201010254161.md): Crossbeam · damaged · Oct 25, 2010 · N456FE · Airbus A310222 · Fuselage Main, Structure
  > FWD CARGO COMPARTMENT - CROSSBEAM UPPER FLANGE AT FR25 DAMAGED BTW Y480 & Y- 480. CROSSBEAM WAS REPAIRED IAW SRM 53-10-15 FIG 207.
- [SDR FDEA201010214133](https://openairdocs.org/sdr/FDEA201010214133.md): Skin · dented · Oct 21, 2010 · N456FE · Airbus A310 · Trailing Edge Flaps
  > PREVIOUS REPAIRED DENTS NOT LISTED IN THE MCMRT AT RT FLAP INBD LOWER SKIN. DENT 1 - BTW RIB 5 & RIB 6 AND BTW FRONT SPAR & STRINGER 9. DENT 2 AND DENT 3 - BTW RIB 10 & RIB 11 AND STRINGER 11 & REAR SPAR. REPAIR OF THE DENTS IAW EA 6-5710-50143.
- [SDR FDEA201010214132](https://openairdocs.org/sdr/FDEA201010214132.md): Frame · misrepaired · Oct 21, 2010 · N456FE · Airbus A310222 · Fuselage Main, Frame
  > FWD CARGO COMPARTEMENT - PREVIOUS REPAIR FOUND AT FR20A NOT IAW FAA APPROVED DATA. NEW REPAIR TO THE FR20A PERFORMED IAW EA 6-5310-144063.
- [SDR FDEA201010184101](https://openairdocs.org/sdr/FDEA201010184101.md): Fitting · misrepaired · Oct 18, 2010 · N456FE · Airbus A310222 · Fuselage Main, Attach Fittings
  > MAIN DECK FLOOR STRUCTURE - PREVIOUS REPAIR FOUND AT FITTING LOCATED BTWN FR11 & FR15A AT Y 1500. REPAIR DOES NOT CONFORM WITH AN EXISTING SRM REPAIR. FLOOR FITTING WAS REPLACED IAW SRM 51-72-10.
- [SDR FDEA201010144063](https://openairdocs.org/sdr/FDEA201010144063.md): Skin · dented · Oct 14, 2010 · N456FE · Airbus A310222 · Leading Edge Devices
  > RT WING - SLAT NR1 L/E - PREVIOUS DENT FOUND AT RIB 4. EVALUATED AND FOUND TO BE CONFORM WITH EA 6-5710-50155. DENT WAS FILLED USING THE GUIDELINES OF SRM 51-73-10.
- [SDR FDEA201010144062](https://openairdocs.org/sdr/FDEA201010144062.md): Seat Track · corroded · Oct 14, 2010 · N456FE · Airbus A310222 · Fuselage, Seat/Cargo Attach Fittings
  > SEAT TRACK Y954 FOUND CORRODED BTW FR18 & FR19. SEAT TRACK REPLACED BY A NEW ONE.
- [SDR FDEA201009303810](https://openairdocs.org/sdr/FDEA201009303810.md): Skin · corroded · Sep 30, 2010 · N456FE · Airbus A310222 · Horizontal Stabilizer, Plate/Skin
  > RT THS TOP SKIN - CONNECTION PART AT THE INTERIOR OF THE SPAR BOX AT STGR9 FOUND CORRODED BTW RIB3 & RIB4. CONNECTION WAS REPLACED IAW 51-72-10 AFTER FABRICATION.
- [SDR FDEA201009303809](https://openairdocs.org/sdr/FDEA201009303809.md): Skin · corroded · Sep 30, 2010 · N456FE · Airbus A310222 · Horizontal Stabilizer, Plate/Skin
  > RT THS TOP SKIN - CONNECTION PART AT THE INTERIOR OF THE SPAR BOX AT STGR10 FOUND CORRODED BTW RIB3 & RIB4. CONNECTION WAS REPLACED IAW 51-72-10 AFTER FABRICATION.
- [SDR FDEA201009303808](https://openairdocs.org/sdr/FDEA201009303808.md): Skin · corroded · Sep 30, 2010 · N456FE · Airbus A310222 · Horizontal Stabilizer, Plate/Skin
  > LT THS BOTTOM SKIN - CONNECTION PART AT THE INTERIOR OF THE SPAR BOX AT STGR11 FOUND CORRODED BTW RIB3 & RIB4. CONNECTION WAS REPLACED IAW 51-72-10 AFTER FABRICATION.
- [SDR FDEA201009303807](https://openairdocs.org/sdr/FDEA201009303807.md): Skin · corroded · Sep 30, 2010 · N456FE · Airbus A310222 · Horizontal Stabilizer, Plate/Skin
  > RT THS BOTTOM SKIN - CONNECTION PART AT THE INTERIOR OF THE SPAR BOX AT STGR9 FOUND CORRODED BTW RIB3 & RIB4. CONNECTION WAS REPLACED IAW 51-72-10 AFTER FABRICATION.
- [SDR FDEA201009303806](https://openairdocs.org/sdr/FDEA201009303806.md): Skin · corroded · Sep 30, 2010 · N456FE · Airbus A310222 · Horizontal Stabilizer, Plate/Skin
  > RIGHT THS TOP SKIN - CONNECTION PART AT THE INTERIOR OF THE SPAR BOX AT S11 FOUND CORRODED BTW RIB 3 & RIB 4. CONNECTION WAS REPLACED IAW 51-72-10 AFTER FABRICATION.
- [SDR FDEA201009303805](https://openairdocs.org/sdr/FDEA201009303805.md): Skin · misrepaired · Sep 30, 2010 · N456FE · Airbus A310222 · Cargo/Baggage Doors
  > BULK CARGO DOOR - PREVIOUS REPAIR FOUND AT INTERNAL SKIN, LOCATED BTW FR67 & FR69 AND BTW BEAM1 & BEAM4, NOT CONFORM WITH SRM. NEW REPAIR WAS PERFORMED IAW SRM 52-30-00, FIG 206.
- [SDR FDEA201009273738](https://openairdocs.org/sdr/FDEA201009273738.md): Skin · debonded · Sep 27, 2010 · N456FE · Airbus A310222 · Trailing Edge Flaps
  > RT OTBD FLAP - LOWER SKIN BTW RIB2 AND RIB3 FOUND DEBONDED. REPAIRED IAW E.A. 6-5750-144062.
- [SDR FDEA201009273737](https://openairdocs.org/sdr/FDEA201009273737.md): Skin · debonded · Sep 27, 2010 · N456FE · Airbus A310222 · Trailing Edge Flaps
  > FLAP OTBD RT - LOWER SKIN SURFACE BTW RIB7 AND RIB 9 FOUND DEBONDED. FLAP OUTBOARD DISBONDED AREA WAS REPAIR IAW EA 6-5750-144062.
- [SDR FDEA201009273736](https://openairdocs.org/sdr/FDEA201009273736.md): Spacer · cracked · Sep 27, 2010 · N456FE · Airbus A310222 · Wing Miscellaneous Structure
  > RIGHT MLG W/W - SPACER WITH CRACK LOCATED AT FR54 AND AT Y-450 AND Z-1357. AFTER HFEC AND ROTOTEST THE CRACKS REPORTED BY THE VISUAL INSP WERE NOT CONFIRMED. IT WAS JUST A FLAW IN THE SURFACE PROTECTION SYS.
- [SDR FDEA201009153656](https://openairdocs.org/sdr/FDEA201009153656.md): Skin · misrepaired · Sep 15, 2010 · N456FE · Airbus A310222 · Trailing Edge Flaps
  > FLAP INBD LT LOWER SKIN - PREVIOUS REPAIR FOUND BETWEEN RIB13/14 AND STGR 8/11. REPAIR WAS EVALUATED AND FOUND NOT TO CONFORM TO THE SRM. NEW REPAIR ACCOMPLISHED IAW EA 6-5750-144069 INSTRUCTIONS.
- [SDR FDEA201009154251](https://openairdocs.org/sdr/FDEA201009154251.md): Skin · damaged · Sep 15, 2010 · N456FE · Airbus A310222 · Elevator, Plate/Skin
  > RIGHT ELEVATOR BOTTOM SKIN - PREVIOUS REPAIR FOUND AT T/E AT STA 144/ER1. REPAIR REQUIRES EVALUATION. PREVOUS REPAIR FOUND DAMAGED (DEBONDED) AND IT WAS REMOVED. NEW REPAIR HAS BEEN ACCOMPLISHED IAW SRM 55-21-11, FIG 210.
- [SDR FDEA201009144250](https://openairdocs.org/sdr/FDEA201009144250.md): Skin · damaged · Sep 14, 2010 · N456FE · Airbus A310222 · Elevator, Plate/Skin
  > RT ELEVATOR TOP SKIN FOUND WITH DEBONDING AT T/E STA473/ER19. RT ELEVATOR HAS BEEN REPAIR IAW SRM 55-21-11, FIG 210.
- [SDR FDEA201009143614](https://openairdocs.org/sdr/FDEA201009143614.md): Skin · dented · Sep 14, 2010 · N456FE · Airbus A310222 · Fuselage Main, Plate/Skin
  > FUSELAGE SKIN - PREVIOUS DENT FOUND LOCATED BTW FR 2-3 IN LOWER SECTION. DENT WAS CUT-OFF AND REPAIRED IAW THE SRM 53-11-12, FIG 201 AND 53-10-12 FIG217.
- [SDR FDEA201009133658](https://openairdocs.org/sdr/FDEA201009133658.md): Vane · misrepaired · Sep 13, 2010 · N456FE · Airbus A310222 · Trailing Edge Flaps
  > LT INBD FLAP VANE - T/E BOTTOM SKIN - PREVIOUS REPAIR FOUND BTW RIB 9-10. REPAIR WAS REMOVED AND FOUND NOT TO CONFORM TO AN SRM REPAIR. FLAP VANE WAS REPLACED IAW AMM 27-50-15.
- [SDR FDEA201009133657](https://openairdocs.org/sdr/FDEA201009133657.md): Vane · misrepaired · Sep 13, 2010 · N456FE · Airbus A310222 · Trailing Edge Flaps
  > LT INBD FLAP VANE - L/E SKIN WITH PREVIOUS REPAIR FOUND BETWEEN RIB 9-10. REPAIR WAS REMOVED AND FOUND NOT TO BE IAW THE SRM. FLAP VANE REPLACED AS PER AMM 27-50-15.
- [SDR FDEA201009133615](https://openairdocs.org/sdr/FDEA201009133615.md): Skin · misrepaired · Sep 13, 2010 · N456FE · Airbus A310222 · Fuselage Main, Plate/Skin
  > FUSELAGE SKIN - PREVIOUS REPAIR FOUND LOCATED AT FR25A BTW S48-50R. EXISTING REPAIR WAS NOT IN COMPLIACE WITH THE SRM. NEW REPAIR ACCOMPLISHED IAW SRM 53-10-12, FIG 228.
- [SDR FDEA201009094249](https://openairdocs.org/sdr/FDEA201009094249.md): Skin · damaged · Sep 9, 2010 · N456FE · Airbus A310222 · Elevator, Plate/Skin
  > RT ELEVATOR - TOP SKIN FOUND DEBONDED AT THE T/E STA 323/ER11. RT ELEVATOR HAS BEEN REPAIRED IAW SRM 55-21-11, FIG 210.
- [SDR FDEA201005241624](https://openairdocs.org/sdr/FDEA201005241624.md): Lug · corroded · May 24, 2010 · N456FE · Airbus A310222 · Wing, Landing Gear Attach Fittings
  > RT MLG RIB 5 FWD LUG EXCEEDED ALLOWABLE LIMITS IAW DWG AFTER REMOVAL OF LEVEL 1 CORROSION. FABRICATED AND INSTALLED NEW BUSHING IAW EA 6-5710-135199.
- [SDR 08FDEA03641](https://openairdocs.org/sdr/08FDEA03641.md): Pressure Switch · failed · Aug 28, 2008 · N456FE · Airbus A310222 · Hydraulic Power Accumulator, Main
  > YELLOW HYD PUMP FAILED AT FLAP RETRACTION. PERFORMED NR 2 ENGINE RAN,VERIFIED YELLOW HYD SYS PRESSURE IS 2900 PSI ON ECAM, YELLOW SYS LOW PRESS LIGHT FLICKER MOMENTARILY DURING FLAPS EXTENSION AND RETRACTION, NEED PRESS SWITCH CPN 0030767, MPN BSG0001-5505 N
- [SDR 08FDEA02965](https://openairdocs.org/sdr/08FDEA02965.md): Skin · delaminated · Jul 17, 2008 · N456FE · Airbus A310222 · Trailing Edge Flaps
  > RT WING, INBD FLAP TRAIL EDGE UPPER AND LOWER SURFACE DELAMINATED AT 15.0 INCH FROM INBD EDGE, MEASURING 5.0 BY 2.0 INCH REPAIRED THE DELAMINATED WEDGE PER EA NR 6-5720-117366.
- [SDR 08FDEA02640](https://openairdocs.org/sdr/08FDEA02640.md): Longeron · corroded · Jul 3, 2008 · N456FE · Airbus A310222 · Passenger/Crew Doors
  > LT PAX/CREW DOOR LONGERON POSITION NR 2 WITH MILD/EXFOLIATION CORROSION BETWEEN FR15A-16. REMOVED CORROSION PER SRM 51-74-10. APPLIED ALODINE TO THE REWORKED AREA PER SRM 51-21-10. MEASURED REMAINING THICKNESS PER NTM 51-10-04. THE ORIGINAL THICKNESS IS 0
- [SDR 08FDEA02641](https://openairdocs.org/sdr/08FDEA02641.md): Floor Support · corroded · Jul 3, 2008 · N456FE · Airbus A310222 · Fuselage Miscellaneous Structure
  > FR 12 - FR 12A Y1456 LONGERON FOR SUPPORTING OF MAIN DECK FLOOR CORRODED. REPAIRED THE DAMAGE PER EA NR 5310-117358.
- [SDR 08FDEA02618](https://openairdocs.org/sdr/08FDEA02618.md): Roller · inoperative · Jul 2, 2008 · N456FE · Airbus A310222 · Trailing Edge Flaps
  > RT INBD FLAP TRACK NR 2, UPON REMOVAL OF INBD FLAP FOUND 2 FRONT CARRIAGE ROLLER AND 1 REAR CARRIAGE ROLLER SEIZED. DISASSEMBLED ROLLERS PER CMM 27-51-54, CLEANED AND INSPECTED, FOUND ROLLERS WITH SURFACE CORROSION ON MATING SURFACE. REMOVED THE ROLLERS PE
- [SDR 08FDEA02588](https://openairdocs.org/sdr/08FDEA02588.md): Floorbeam · corroded · Jul 1, 2008 · N456FE · Airbus A310222 · Fuselage Main, Floor Beam
  > MAIN DECK CROSSBEAM C14(FR14) -Y1220 TO -Y1300 LOWER FREE FLANGE WITH EXFOLIATION CORROSION. REMOVED THE PULLEY BRACKET PER AMM 20-29-11-0. REMOVED CORROSION PER SRM 51-74-10. APPLIED ALODINE TO THE REWORKED AREA PER SRM 51-21-10. MEASURED REMAINING THICKN
- [SDR 08FDEA02587](https://openairdocs.org/sdr/08FDEA02587.md): Arm · corroded · Jul 1, 2008 · N456FE · Airbus A310222 · Rudder Structure
  > NR 1 RUDDER HINGE ARM FORWARD ATTACH AREA FORWARD OF BEARINGS EXFOLIATED. REMOVED CORROSION AND POLISHED REWORK AREA PER SRM 51-76-10, APPLIED ALODINE TO THE REWORK AREA PER SRM 51-21-10. PERFORM HFEC TO REWORK AREA FOR CRACK, NO CRACK FOUND PER NTM 51-10-09
- [SDR 08FDEA02491](https://openairdocs.org/sdr/08FDEA02491.md): Web · cracked · Jun 26, 2008 · N456FE · Airbus A310222 · Nacelle/Pylon Miscellaneous Structure
  > WEB CRACKED OUTBOARD OF PRECOOLER NR 1 PYLON. DRILLED CRACK STOP HOLES PER SRM 54-52-31. REMOVED THE RELATED FASTENERS PER SRM 51-40-21. MANUFACTURED THE DOUBLER AND BROKE SHARP EDGES PER SRM 51-26-20. DRILLED FASTENER HOLES TO THE WEB AND THE DOUBLER PER
- [SDR 08FDEA02489](https://openairdocs.org/sdr/08FDEA02489.md): Rib · cracked · Jun 26, 2008 · N456FE · Airbus A310222 · Nacelle/Pylon, Frame/Spar/Rib
  > WEB CRACKED LOWER END FORWARD OF RIB 18 RIGHT SIDE NR 2 PYLON. DRILLED CRACK STOP HOLES PER SRM 54-52-31. REMOVED THE RELATED FASTENERS PER SRM 51-40-21. MANUFACTURED THE DOUBLERS AND BROKE SHARP EDGES PER SRM 51-26-20. DRILLED FASTENER HOLES TO THE WEB AN
- [SDR 08FDEA02488](https://openairdocs.org/sdr/08FDEA02488.md): Rib · cracked · Jun 26, 2008 · N456FE · Airbus A310222 · Nacelle/Pylon, Frame/Spar/Rib
  > WEB CRACKED LOWER END FORWARD OF RIB 18 LEFT SIDE NR 2 PYLON. DRILLED CRACK STOP HOLES PER SRM 51-40-21. REMOVED THE RELATED FASTENERS PER SRM 51-40-21. MANUFACTURED THE DOUBLER AND BROKE SHARP EDGES PER SRM 51-26-20. DRILLED FASTENER HOLES TO THE WEB AND
- [SDR 08FDEA02492](https://openairdocs.org/sdr/08FDEA02492.md): None · none · Jun 26, 2008 · N456FE · Airbus A310222 · Standard Practices/Structures
  > NR 2 PYLON REPAIR INSTALLED ON PRECOOLER WEB DOES NOT MEET REQUIREMENTS PER SRM. REMOVED THE ORIGINAL REPAIR PART PER SRM 51-40-21. DRILLED CRACK STOP HOLES (4.8MM) PER SRM 54-52-31. FABRICATED REPAIR PART PER SRM 54-52-31. DRILLED FASTENER HOLES TO THE RE
- [SDR 08FDEA02500](https://openairdocs.org/sdr/08FDEA02500.md): Floorbeam · corroded · Jun 26, 2008 · N456FE · Airbus A310222 · Fuselage Main, Floor Beam
  > MAIN DECK CROSSBEAM C14, LBL 55.0, INNERGRANULAR CORROSION ON LOWER FLANGE. REMOVED CORROSION PER SRM 51-74-10. MEASURED REMAINING THICKNESS PER NTM 51-10-04. FOUND WITHIN LIMIT (REMAINING THICKNESS: 0.096 INCH). APPLIED FLAP PEENING PER SRM 51-29-00. REP

Next page: https://openairdocs.org/deregistered/N456FE-2020-04-23/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 = 'N456FE' AND deregistration_id = 'N456FE-2020-04-23'
ORDER BY difficulty_date DESC
```

This list as a web page: https://openairdocs.org/deregistered/N456FE-2020-04-23/reports

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