# Service difficulty reports: N803FD, cancelled Mar 2, 2024

A list on [N803FD, cancelled Mar 2, 2024](https://openairdocs.org/deregistered/N803FD-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 5 · 205 reports

- [SDR FDEA201706291786](https://openairdocs.org/sdr/FDEA201706291786.md): Actuator · failed · Jun 29, 2017 · N803FD · Airbus A310 · Aircraft Fuel Distribution System
  > DURING CLIMB. RIGHT OUTER TANK DECREASEED TO 3.32 LBS AND RIGHT INNER INCREASEDTO 14.4. LEFT OUTER WAS 6.13 & LEFT INNER WAS 11.91. WAS ABLE TO STOP R/O DECREASE BY TRINING OFF R/O PUMPS., BUT RIGHT INNER DID NOT DECREASE. AT 37000 LEVEL OFF L/O 6.16 L/I
- [SDR FDEA201706201716](https://openairdocs.org/sdr/FDEA201706201716.md): Pitot Tube · obstructed · Jun 20, 2017 · N803FD · Airbus A310324 · Pitot/Static System
  > DURING TAKEOFF, FIRST OFFICER`S AIRSPEED TAPE SHOWED BETWEEN 40 - 45 KNTS, WITH CAPTAIN`S AIRSPEED TAPE AND STANDBY AIRSPEED BETWEEN 100 - 110 KNTS. ABORTED SHORTLY THERE AFTER. PERFORMED RTO CHECK LIST, NO OTHER DESCRPENCIES NOTED. INSPECTED THE FIRST
- [SDR FDEA201701170209](https://openairdocs.org/sdr/FDEA201701170209.md): Jackscrew · fluid loss · Jan 17, 2017 · N803FD · Airbus A310324 · Leading Edge Slat Control System
  > SLATS 1 AND 2 FAULTED OFF DURING SLATS EXTENSION. SLATS REMAINED AT THE RETRACT POSITION AND DID NOT MOVE WHEN THE HANDLE WAS RECYCLED. COMPLIED WITH QRH AND LANDED WITH SLATS RETRACTED AND FLAPS 40. FOUND RIGHT WING INBOARD JACKSCREW EMPTY OF FLUID, REMO
- [SDR FDEA201701160199](https://openairdocs.org/sdr/FDEA201701160199.md): Computer · failed · Jan 16, 2017 · N803FD · Airbus A310324 · Leading Edge Slat Control System
  > DURING APPROACH WHEN EXTENDING SLATS, NO MOVEMENT. CYCLED, RAN QRH, LANDED WITH SLATS UP AND FLAPS 40. REMOVED & REPLACED BOTH NR 1 & 2 SFCC'S IAW AMM 27-51-18-04 & BOTH OPS CHECKED GOOD IAW AMM 27-51-00-05.
- [SDR FDEA201511213745](https://openairdocs.org/sdr/FDEA201511213745.md): Flap · stuck · Nov 21, 2015 · N803FD · Airbus A310324 · Trailing Edge Flap Control System
  > FLAP SYS 1 & 2 FAULT, FLAPS STUCK. REMOVED TWO BOLTS FROM RT TORQUE LIMITED COUPLER TO FOM. DRAINED FLUID FROM RT WING NR 1 FLAP DRIVE GEAR BOX FOR INSPECTION PURPOSE. GPS OVERRIDE SWITCH IN COCKPIT, CAPTAINS RIGHT KNEE, REQUIRES SAFETY. FOUND JAM FAULTS O
- [SDR FDEA201508252695](https://openairdocs.org/sdr/FDEA201508252695.md): Stringer · damaged · Aug 25, 2015 · N803FD · Airbus A310324 · Fuselage Main, Longeron/Stringer
  > REMOVED STRINGER 44 AT FRAME 19 - 20 TO FOM. REMOVED SHEAR TIE & COUPLING. COUPLING & STRINGER FOUND TO BE DAMAGED. FABRICATED NEW STRINGER ON T15 1157203. RECEIVED NEW COUPLING, INSTALLED SHEAR TIE, COUPLING & STRINGER 44 AT FRAME 19 - 20 IAW SRM 51-40-21
- [SDR FDEA201506181846](https://openairdocs.org/sdr/FDEA201506181846.md): Crossbeam · corroded · Jun 18, 2015 · N803FD · Airbus A310324 · Fuselage Miscellaneous Structure
  > BULK CARGO FRAME 67 -Y-940, CROSSBEAM WITH INNER GRANULAR CORROSION. REPLACED THE CORRODED CROSSBEAM OF BULK CARGO IAW SRM 51-40-21. THIS REPAIR CATEGORY A, MAJOR REPAIR IAW GMM6-2-100.
- [SDR FDEA201506151817](https://openairdocs.org/sdr/FDEA201506151817.md): Repair · delaminated · Jun 15, 2015 · N803FD · Airbus A310324 · Trailing Edge Flaps
  > AGEING INSPECTION, EXISTING REPAIR ON RT OUTER FLAP, UPPER SKIN OUT OF RIB 10 REQUIRES EVALUATION FOR CONFORMITY. THE EXISTING REPAIR WAS EVALUATED & FOUND IN CONFORMITY WITH APPROVED DATA. BUT INSPECTION FOUND DELAMINATION ON OLD REPAIR. REPAIRED THE DAMAG
- [SDR FDEA201506151816](https://openairdocs.org/sdr/FDEA201506151816.md): Repair · delaminated · Jun 15, 2015 · N803FD · Airbus A310324 · Trailing Edge Flaps
  > AGEING INSPECTION, EXISTING REPAIR ON RT OUTER FLAP, UPPER SKIN OUT OF RIB 10 REQUIRES EVALUATION FOR CONFORMITY. THE EXISTING REPAIR WAS EVALUATED & FOUND IN CONFORMITY WITH APPROVED DATA. BUT INSPECTION FOUND DELAMINATION ON OLD REPAIR. REPAIRED THE DAMAG
- [SDR FDEA201506151815](https://openairdocs.org/sdr/FDEA201506151815.md): Skin · delaminated · Jun 15, 2015 · N803FD · Airbus A310324 · Trailing Edge Flaps
  > AGEING INSPECTION, EXISTING REPAIR ON RT OUTER FLAP UPPER SKIN OUT OF RIB 10 REQUIRES EVALUATION FOR CONFORMITY. THE EXISTING REPAIR WAS EVALUATED & FOUND IN CONFORMITY WITH APPROVED DATA. BUT INSPECTION FOUND DELAMINATION ON OLD REPAIR. REPAIRED THE DAMAGE
- [SDR FDEA201506151812](https://openairdocs.org/sdr/FDEA201506151812.md): Skin · cracked · Jun 15, 2015 · N803FD · Airbus A310324 · Wing, Plate/Skin
  > RIGHT WING FIXED TE LOWER SKIN AT RIBS 11 - 12 CRACKED 1 INCH. REPAIRED IAW EA 6-5730-T0318078 & R57249152. MAJOR REPAIR IAW GMM 6-2-100.
- [SDR FDEA201506101748](https://openairdocs.org/sdr/FDEA201506101748.md): Floor Support · cracked · Jun 10, 2015 · N803FD · Airbus A310200 · Fuselage Miscellaneous Structure
  > MAIN DECK CARGO FRAME 15A Y1456 FLOOR SUPPORT CRACKED APPROX 1.0 INCH IN LENGTH. REPAIRED IAW SRM 53-12-15-201 PARA 5G. MAJOR REPAIR IAW GMM6-2-100.
- [SDR FDEA201407171832](https://openairdocs.org/sdr/FDEA201407171832.md): Windshield · cracked · Jul 17, 2014 · N803FD · Airbus A310324 · Flight Compartment Windows
  > EN ROUTE LT WINDOW HEAT FAULT, FOLLOWED BY WINDSHIELD CRACKING. NUMEROUS CRACKS IN LOWER RT CORNER. QRH FOLLOWED, DIVERTED. REMOVED L1 WINDSHIELD IAW MM 56-11-11-04.
- [SDR FDEA201405090992](https://openairdocs.org/sdr/FDEA201405090992.md): Thrust Reverser · damaged · May 9, 2014 · N803FD · Airbus A310324 · Engine Thrust Reverser
  > NUMBER 1 ENG THRUST REVERSER OTBD TRANSLATING SLEEVE AFT 8 INCHES IS MISSING TOP TO BOTTOM, WHITE COWL. ALL COCKPIT THRUST REVERSER LIGHTS EXTINGUISHED, NORMAL. NR 1 ENG OIL SERVICE DOOR WAS OPEN & BOTTOM HINGE PIN MISSING. INNER BARREL MESH IS MISSING &
- [SDR FDEA201403190525](https://openairdocs.org/sdr/FDEA201403190525.md): Sensor · malfunctioned · Mar 19, 2014 · N803FD · Airbus A310324 · Engine Oil Indicating System
  > DURING CRUISE FLIGHT, NR 2 RT ENGINE OIL TEMP BEGAN TO FLUCTUATE FROM NORMAL CRUISE TEMP OF 116C UP TO 230C. STAYED ABOVE 160C FOR MORE THAN 9 MINUTES BUT CONTINUED TO FLUCTUATE BETWEEN NORMAL & A HIGH OF 230 C. FINALLY TEMP STAYED ABOVE 160 C FOR MORE THA
- [SDR FDEA201401230181](https://openairdocs.org/sdr/FDEA201401230181.md): Computer · malfunctioned · Jan 23, 2014 · N803FD · Airbus A310324 · Auto Throttle System
  > DURING TAKEOFF, TOGA WOULD NOT ENGAGE. NO OTHER WARNINGS, COULD MANUALLY ADVANCE THROTTLES WITH NO RESTRICTIONS. REMOVED AND REPLACED TCC COMPUTOR IAW AMM 22-36-34-04-01 AND REPFORMED A AFS/LAND TEST. ALL SYSTEM TESTED NORMAL.
- [SDR FDEA201303030491](https://openairdocs.org/sdr/FDEA201303030491.md): Floorboard · delaminated · Mar 3, 2013 · N803FD · Airbus A310324 · Fuselage Floor Panel
  > AFT CARGO BAY FLOORBOARD BETWEEN 1R AND 2R RAIL TRACKS, 2 FEET FWD OF BALL MAT HAS 24"OF DELAMINATION. FLOORBOARD WAS DAMAGED BEYOND ECONOMICAL REPAIR. FABRICATED A REPLACEMENT FLOORBOARD IAW DWG SRZ-25-005, REV J.
- [SDR FDEA201302270475](https://openairdocs.org/sdr/FDEA201302270475.md): Ferrule · cracked · Feb 27, 2013 · N803FD · Airbus A310324 · Nacelle/Pylon, Main Frame
  > NR 2 PYLON FERRULE IS CRACKED COMPLIED WITH EA 6-5450-T0300139 REV NR PS P1 - NACELLES/PYLON PRECOOLER FERRULE CRACK ON NR 2 PYLON REF WR 54-50 6954.
- [SDR FDEA201302190374](https://openairdocs.org/sdr/FDEA201302190374.md): Frame · corroded · Feb 19, 2013 · N803FD · Airbus A310324 · Fuselage Main, Frame
  > FUSELAGE AFT PRESSURE BULKHEAD FWD FACE LWR RIM FR 80/82 HAS 3 EA AREAS OF EXFOLIATED CORROSION & 1 EA AREA OF CORROSION EXTENDING INTO THE CLEAT PROFILE. DEFECT MEASURES 15"SQ. AFTER REMOVAL OF LEVEL 1 CORROSION, FOUND ANGLES TO BE OUT OF LIMITS IAW SRM
- [SDR FDEA201302080306](https://openairdocs.org/sdr/FDEA201302080306.md): Skin · dented · Feb 8, 2013 · N803FD · Airbus A310324 · Trailing Edge Flaps
  > RT WING OTBD FLAP L/E APPROX WING RIB 25 HAS A DENT WITH FIELD REPAIR APPROX 1.5 X 1.5 X.200D. CUT OUT DAMAGED AREA. FABRICATED, HEAT TREATED, LOCATE AND DRILLED REPAIR PARTS IAW SRM 57-53-12, FIG 213. PROTECTED REPAIR PARTS AND THE CUT OUT AREA ON RT FLAP
- [SDR FDEA201302060288](https://openairdocs.org/sdr/FDEA201302060288.md): Floorboard · delaminated · Feb 6, 2013 · N803FD · Airbus A310324 · Fuselage Floor Panel
  > MLG BAY LT AFT WALKWAY PANEL 148 BF HAS 60 SQ" AREA OF DELAMINATION. FABRICATED REPLACEMENT PANEL 148 BF IAW DWG SRZ 25-005, REV J.
- [SDR FDEA201012204727](https://openairdocs.org/sdr/FDEA201012204727.md): Power Supply · failed · Dec 20, 2010 · N803FD · Airbus A310324 · Emergency Lighting
  > EMERGENCY LIGHTS FAIL OPS CHECK FROM COURIER AREA TEST SWITCH. R & R THE POWER SUPPLY UNIT AND BATTERY IAW AMM 33-51-14-04. PERFORMED A SATISFACTORY TEST OF THE EMERGENCY LIGHTS IAW AMM 33-51-14-04.
- [SDR FDEA201012164699](https://openairdocs.org/sdr/FDEA201012164699.md): Rib · damaged · Dec 16, 2010 · N803FD · Airbus A310324 · Wing, Rib/Bulkhead
  > LT WING T/E RIB AT WIAX 62.70 HAS EDGE DAMAGE ON THE SPAR ATTACH FLANGE. REMOVED DAMAGE FROM THE SPAR AREA IAW EA 6-5730-136705.
- [SDR FDEA201011044253](https://openairdocs.org/sdr/FDEA201011044253.md): Support · cracked · Nov 4, 2010 · N803FD · Airbus A310222 · Wing Miscellaneous Structure
  > RT WING ALL SPEED AILERON ACTUATOR UPPER PANEL SUPPORT IS CRACKED ON THE OTBD SIDE. PARTIALLY REMOVED OTBD UPPER AILERON PANEL AND REMOVED CRACKED LANDING. INSTALLED NEW PANEL LANDING PN A5724275920300, PO 691739.5 AND RE-INSTALLED OTBD UPPER AILERON PANEL
- [SDR FDEA201010254167](https://openairdocs.org/sdr/FDEA201010254167.md): Fairing · cracked · Oct 25, 2010 · N803FD · Airbus A310324 · Nacelle/Pylon Miscellaneous Structure
  > NR 1 PYLON INBD APRON FAIRING SKIN IS CRACKED. INSTALLED REPAIR DOUBLER ON THE NR1 PYLON INBD APRON FAIRING IN REF TO SRM 54-56-10, FIG 201.
- [SDR FDEA201010144081](https://openairdocs.org/sdr/FDEA201010144081.md): Skin · gouged · Oct 14, 2010 · N803FD · Airbus A310324 · Horizontal Stabilizer, Plate/Skin
  > LEFT HORIZONTAL STAB LOWER EXTERIOR SKIN IS GOUGED AT THE FUEL ACCESS PANEL 333 FB CUTOUT. SMOOTHED AREA. ORIGINAL 0.268. REMAINING 207. FOUND IN LIMITS IAW EA 6-510-136714 REV "A"; HORIZONTAL STABILIZER - LOWER PANEL GOUGED AROUND ACCESS HOLE BETWEEN RIB
- [SDR FDEA201010134042](https://openairdocs.org/sdr/FDEA201010134042.md): Support · cracked · Oct 13, 2010 · N803FD · Airbus A310324 · Fuselage Miscellaneous Structure
  > FUSELAGE UNDER THE LT AIR CONDITIONING AFT FAIRING THE AFT INBD EXHAUST SHIELD SUPPORT IS CRACKED. REMOVED SUPPORT BRACKET IAW SRM 51-40-21. RECEIVED NEW SUPPORT BRACKET FROM STORES, PO 693873.1. INSTALLED NEW BRACKET IAW SRM 51-72-10, PAGES 1-3.
- [SDR FDEA201010124021](https://openairdocs.org/sdr/FDEA201010124021.md): Floor Panel · delaminated · Oct 12, 2010 · N803FD · Airbus A310324 · Fuselage Floor Panel
  > AIR CONDITIONING COMPARTMENT FLOOR PANEL 143 DF HAS A LARGE CORNER THAT IS DELAMINATED AND CONTAMINATED. FABRICATED NEW AIR CONDITIONING COMPARTMENT FLOOR PANEL 143 DF IAW DWG SRZ 25-005, REV "H".
- [SDR FDEA201009303818](https://openairdocs.org/sdr/FDEA201009303818.md): Sleeve · cracked · Sep 30, 2010 · N803FD · Airbus A310324 · Engine Thrust Reverser
  > NR 2 ENG RT THRUST REVERSER SLEEVE IS CRACKED AND DAMAGED JUST BELOW THE NR 6 BLOCKER DOOR. REPAIRED NR 2 THRUST REVERSER JUST BELOW THE NR 6 BLOCKED DOOR BY CLEANING EXISTING POTTING AND RE-POTTING DAMAGED AREA AND CURING IAW SRM 54-05- 01, PARA 9.
- [SDR FDEA201009273750](https://openairdocs.org/sdr/FDEA201009273750.md): Floor Panel · cracked · Sep 27, 2010 · N803FD · Airbus A310324 · Fuselage Floor Panel
  > MAIN CABIN FLOOR PANEL NR232 RG HAS THE FWD RT EAR CRACKED. FABRICATED NEW PANEL, POTTED EDGES AND INSTALLED INSERTS IAW DWG SRZ 25-005, REV "H".
- [SDR FDEA201009273746](https://openairdocs.org/sdr/FDEA201009273746.md): Floorboard · cracked · Sep 27, 2010 · N803FD · Airbus A310324 · Fuselage Floor Panel
  > MAIN DECK FLOORBOARD 242 BR IS CRACKED AT FRAME 39. FABRICATED NEW FLOORBOARD, POTTED EDGES, INSTALLED INSERTS, APPLIED ANTI-SKID AND PART MARKED IAW DWG SRZ 25-005, REV "H".
- [SDR FDEA201009273743](https://openairdocs.org/sdr/FDEA201009273743.md): Floor Panel · cracked · Sep 27, 2010 · N803FD · Airbus A310324 · Fuselage Floor Panel
  > MAIN CABIN FLOOR PANEL 222 CF IS CRACKED ACROSS THE BOTTOM. FABRICATED NEW FLOOR PANEL, POTTED EDGES AND INSTALLED INSERTS IAW DWG SRZ 25-005, REV "H".
- [SDR FDEA201009273749](https://openairdocs.org/sdr/FDEA201009273749.md): Floor Panel · damaged · Sep 27, 2010 · N803FD · Airbus A310324 · Fuselage Floor Panel
  > MAIN CABIN FLOOR PANEL NR251 RG IS CRUSHED FROM APPROX FRAME 60 - FRAME 62; LBL 60. FABRICATED NEW FLOOR PANEL, POTTED EDGES AND INSTALLED INSERTS IAW DWG SRZ 25-005, REV "H".
- [SDR FDEA201009273748](https://openairdocs.org/sdr/FDEA201009273748.md): Floor Panel · cracked · Sep 27, 2010 · N803FD · Airbus A310324 · Fuselage Floor Panel
  > MAIN CABIN FLOOR PANEL NR261 LF IS CRACKED FROM FRAME 74 - FRAME 75; LBL 12. FABRICATED NEW FLOOR BOARD, POTTED EDGES AND INSTALLED INSERTS IAW DWG SRZ 25-005, REV "H".
- [SDR FDEA201009273745](https://openairdocs.org/sdr/FDEA201009273745.md): Floor Panel · cracked · Sep 27, 2010 · N803FD · Airbus A310324 · Fuselage Floor Panel
  > FUSELAGE INTERNAL STRUCTURE, MAIN DECK FLOOR PANEL 242 QF IS CRACKED FROM FRAME 47 TO FRAME 51. FABRICATED NEW FLOOR PANEL, POTTED EDGES AND INSTALLED INSERTS IAW DWG SRZ 25-005, REV "H".
- [SDR FDEA201009273744](https://openairdocs.org/sdr/FDEA201009273744.md): Floor Panel · cracked · Sep 27, 2010 · N803FD · Airbus A310324 · Fuselage Floor Panel
  > FUSELAGE INTERNAL STRUCTURE, MAIN DECK FLOOR PANEL 241 PG IS CRACKED FROM FRAME 53 TO FRAME 54. FABRICATED NEW FLOOR PANEL, POTTED EDGES AND INSTALLED INSERTS IAW DWG SRZ 25-005, REV "H".
- [SDR FDEA201009273739](https://openairdocs.org/sdr/FDEA201009273739.md): Skin · dented · Sep 27, 2010 · N803FD · Airbus A310222 · Fuselage Main, Plate/Skin
  > LOWER FUSELAGE LEFT EXTERNAL SURFACE IS DENTED BETWEEN FRAME 38.2 & FRAME 39; STRINGER 35-36L. CUT OUT DENT, FABRICATED DOUBLER, DRILLED, DEBURRED, ALODINED, PRIMED INSTALLED AND SEALED IAW SRM 53-10-12, 51-21-10 & 51-40-21.
- [SDR FDEA201009273747](https://openairdocs.org/sdr/FDEA201009273747.md): Floorboard · cracked · Sep 27, 2010 · N803FD · Airbus A310324 · Fuselage Floor Panel
  > MAIN DECK FLOORBOARD NR 241 YF IS CRACKED AT FRAME 54. FABRICATED NEW FLOORBOARD, POTTED EDGES AND INSTALLED INSERTS IAW DWG SRZ 25-005, REV "H".
- [SDR FDEA201009213600](https://openairdocs.org/sdr/FDEA201009213600.md): Seat Track · gouged · Sep 21, 2010 · N803FD · Airbus A310324 · Fuselage, Seat/Cargo Attach Fittings
  > SEAT TRACK AT FRAME 54, RBL 48 HAS SCALLOPS GOUGED OUT OF LIMITS. R & R SEAT TRACK IAW SRM 53-10-15, FIG 201.
- [SDR FDEA201009173529](https://openairdocs.org/sdr/FDEA201009173529.md): Skin · corroded · Sep 17, 2010 · N803FD · Airbus A310324 · Wing, Plate/Skin
  > RT WING TOP SKIN SURFACE FRONT SPAR AREA SKIN IS CORRODED FROM RIB 17 - RIB 18. REMOVED 5 EA FASTENERS RT WING TOP SKIN UPPER SURFACE FRONT SPAR BETWEEN RIB 17 AND RIB 18. BLENDED CORROSION IAW SRM 51-74-10. FOUND TO BE WITHIN LIMITS IAW SRM 57-20-12, PGS 13
- [SDR FDEA201009173528](https://openairdocs.org/sdr/FDEA201009173528.md): Skin · corroded · Sep 17, 2010 · N803FD · Airbus A310324 · Wing, Plate/Skin
  > LT WING TOP SKIN SURFACE IS CORRODED AT THE REAR SPAR AREA FROM RIB 4 - RIB 5. REMOVED 2 EA FASTENERS LT WING TOP SKIN UPPER SURFACE REAR SPAR BETWEEN RIB 17 AND RIB 18 IAW SRM 51-40-21. BLENDED CORROSION IAW SRM 51-74-10. FOUND TO BE WITHIN LIMITS IAW SRM
- [SDR FDEA201009173527](https://openairdocs.org/sdr/FDEA201009173527.md): Skin · corroded · Sep 17, 2010 · N803FD · Airbus A310324 · Wing, Plate/Skin
  > LT WING TOP SKIN SURFACE IS CORRODED 2 EA PLACES AT THE REAR SPAR AREA FROM RIB 12 - RIB 13. REMOVED CORROSION IAW SRM 57-00-00, PG 212 AT THE LT WING TOP SKIN UPPER SURFACE T/E BETWEEN RIBS 12-13. FOUND TO BE WITHIN LIMITS IAW SRM 57-20-12, PGS 9 & 111.
- [SDR FDEA201009173525](https://openairdocs.org/sdr/FDEA201009173525.md): Skin · corroded · Sep 17, 2010 · N803FD · Airbus A310324 · Wing, Plate/Skin
  > LT WING TOP SKIN SURFACE IS CORRODED AT THE REAR SPAR AREA FROM RIB 15-RIB 16. REMOVED CORROSION; LT WING TOP SKIN T/E AREA BETWEEN RIBS 15-16 IAW SRM 57-20-12, PG 9. FOUND TO BE WITHIN LIMITS IAW SRM 57-20-12, PGS 9 & 111. TOOL T8285D. FLAP PEENED AREA IA
- [SDR FDEA201009163505](https://openairdocs.org/sdr/FDEA201009163505.md): Skin · corroded · Sep 16, 2010 · N803FD · Airbus A310324 · Wing, Plate/Skin
  > RT WING TOP SKIN UPPER SURFACE, SKIN IS CORRODED FROM RIB 10 TO RIB 11. REMOVED FASTENER RT WING TOP SKIN UPPER SURFACE REAR SPAR BETWEEN RIB 10 AND RIB 11. BLENDED CORROSION IAW SRM 51-74-10. FOUND TO BE WITHIN LIMITS IAW SRM 57-20-12, PGS 13 & 110. FLAP
- [SDR FDEA201009163504](https://openairdocs.org/sdr/FDEA201009163504.md): Skin · corroded · Sep 16, 2010 · N803FD · Airbus A310324 · Wing, Plate/Skin
  > RT WING TOP SKIN UPPER SURFACE, REAR SPAR AREA SKIN IS CORRODED FROM RIB 4 TO RIB 5. REMOVED 2 EA FASTENERS RT WING TOP SKIN UPPER SURFACE AT REAR SPAR IAW SRM 51-40-21. BLENDED CORROSION IA SRM 51-74-10. FOUND TO BE WITHIN LIMITS IAW SRM 57-20-12, PGS 13 &
- [SDR FDEA201009163503](https://openairdocs.org/sdr/FDEA201009163503.md): Skin · corroded · Sep 16, 2010 · N803FD · Airbus A310324 · Wing, Plate/Skin
  > RT WING TOP SKIN UPPER SURFACE, REAR SPAR AREA SKIN IS CORRODED FROM RIB 23 TO RIB 24. REMOVED FASTENER RIGHT WING TOP SKIN UPPER SURFACE REAR SPAR BETWEEN RIB 23 AND RIB 24. BLENDED CORROSION IAW A310-300 SRM 51-74-10. FOUND TO BE WITHIN LIMITS IAW SRM 5
- [SDR FDEA201009163502](https://openairdocs.org/sdr/FDEA201009163502.md): Skin · cracked · Sep 16, 2010 · N803FD · Airbus A310324 · Wing, Plate/Skin
  > LT WING BOTTOM SKIN LOWER SURFACE T/E AREA SKIN IS CRACKED FROM RIB 11 TO RIB 12. COMPLIED WITH EA 6-5730-136705.
- [SDR FDEA201009143397](https://openairdocs.org/sdr/FDEA201009143397.md): Floor Panel · delaminated · Sep 14, 2010 · N803FD · Airbus A310324 · Fuselage Floor Panel
  > AFT PIT FLOOR PANEL 152 AF IS DELAMINATED. FABRICATED NEW FLOOR PANEL, POTTED EDGES AND INSTALLED INSERTS IAW DWG SRZ 25-005, REV "H".
- [SDR FDEA201009143413](https://openairdocs.org/sdr/FDEA201009143413.md): Floor Panel · punctured · Sep 14, 2010 · N803FD · Airbus A310324 · Fuselage Floor Panel
  > MAIN CABIN FLOOR PANEL 231 QG IS PUNCTURED ON THE TOP SURFACE. FABRICATED NEW FLOOR PANEL, POTTED EDGES AND INSTALLED INSERTS IAW DWG SRZ 25-005, REV "H".
- [SDR FDEA201009143412](https://openairdocs.org/sdr/FDEA201009143412.md): Floor Panel · cracked · Sep 14, 2010 · N803FD · Airbus A310324 · Fuselage Floor Panel
  > MAIN CABIN FLOOR PANEL 231 LG IS CRACKED. FABRICATED NEW FLOOR PANEL, POTTED EDGES AND INSTALLED INSERTS IAW DWG SRZ 25-005, REV "H".

Next page: https://openairdocs.org/deregistered/N803FD-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 = 'N803FD' AND deregistration_id = 'N803FD-2024-03-02'
ORDER BY difficulty_date DESC
```

This list as a web page: https://openairdocs.org/deregistered/N803FD-2024-03-02/reports

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