# Service difficulty reports: Airbus A310

A list on [Airbus A310](https://openairdocs.org/model/airbus-a310.md).

Newest first. General aviation reporting is voluntary.

Page 1 of 13 · 606 reports

- [SDR CA190722001](https://openairdocs.org/sdr/CA190722001.md): Line · leaking · Jul 20, 2019 · Airbus A310 · Hydraulic System, Main
  > (CAN) PILOT REPORTS GREEN SYSTEM LOW QUANTITY MESSAGE ON ECAM, QRH HAS BEEN PERFORMED, QUANTITY LEVEL IS AT THE RED DOT, SAME. DISPATCH FOUND THAT THE AIRCRAFT CAN CONTINUE IN A NON-ETOPS ROUTE AND MAKE IT. SMALL POSSIBILITY OF DIVERTING MAINTENANCE ADVISED. H
- [SDR CA190708001](https://openairdocs.org/sdr/CA190708001.md): Actuator · faulted · Jul 5, 2019 · Airbus A310 · Landing Gear Position and Warning
  > (CAN) AT TAKEOFF PHASE, MESSAGE ON ECAM, LDG DOOR NOT CLOSE. AIRCRAFT DIVERT. AS PER INVESTIGATION, FOUND L/H NOSE DOOR UPLOCK FAULT WITH MICROSWITCHES. MICROSWITCHES REPLACED AND LH NLG DOOR UPLOCK REPLACED IAW AMM 32-31-14 PB 401 AIRCRAFT BACK IN SERVICE (T
- [SDR CA190401010](https://openairdocs.org/sdr/CA190401010.md): Control Lever · faulted · Mar 31, 2019 · Airbus A310 · Landing Gear Selector
  > (CAN) AFTER TAKEOFF L/G LEVER INTERLOCK ECAM UNABLE TO RAISE GEAR ON SYSTEM 1 AND 2 ACCOMPLISHED CB RESET #U52 AS PER QRH SYSTEM RESET AND WAS UNSUCCESSFUL ON SYSTEM 1 LDG NORMAL CTRL MICRO SW UNIT 2GA REPLACED IAW AMM 32-31-11 PB401 LANDING GEAR ELECTRO-VALVE
- [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 FDEA201705011301](https://openairdocs.org/sdr/FDEA201705011301.md): Pump · inoperative · May 1, 2017 · N808FD · Airbus A310 · Hydraulic Pump (Electric/Engine), Main
  > IN CRUISE FL360 GOT GREEN HYD SYSTEM OVERHEAT. ECAM ADVISED TO TURN OFF GREEN ENGINE PUMPS 1 AND 2. ENG HYD 1 PUMP SHUT OFF NORMALLY. ENG HYD 2 GREEN PUMP TURNED OFF MOMENTARILY. ITS CB POPPED AND THE PUMP STARTED OPERATING AGAIN. CORDINATED WITH MOCC TO RESET
- [SDR CA151223003](https://openairdocs.org/sdr/CA151223003.md): Tube · broken · Dec 21, 2015 · Airbus A310 · Engine Thrust Reverser
  > (CAN) ENGINE NR 2 THROTTLE JAMMED DUE TO A RUPTURE THRUST REVERSER AIR TUBE. THE SAME TUBE WAS INSTALLED ON SEPT 02, 2015 IN THE EXACT LOCATION FOR THE SAME REASON.
- [SDR FDEA201511083515](https://openairdocs.org/sdr/FDEA201511083515.md): Battery Pack · discharged · Nov 8, 2015 · N426FE · Airbus A310 · Emergency Lighting
  > EMERGENCY LIGHTS WILL NOT TEST IN COURIER AREA. R & R EMER POWER SUPPLY BATTERY PACK IAW AMM 33-51-14-4. OPERATIONS CHECKED GOOD. PART NAME, EMER POWER, BATTERY PACK, PN AD-3214-30 & SN 106982.
- [SDR FDEA201504141229](https://openairdocs.org/sdr/FDEA201504141229.md): Crossbeam · corroded · Apr 14, 2015 · N811FD · Airbus A310 · Fuselage Miscellaneous Structure
  > AFT CARGO CROSSBEAM RT SIDE FITTING, CORRODED AT FRAME 62. REPLACED THE RT SIDE CORRODED FITTING, CROSSBEAM, IAW SRM 51-40-21.
- [SDR FDEA201402110305](https://openairdocs.org/sdr/FDEA201402110305.md): Relay · burned · Feb 11, 2014 · N429FE · Airbus A310 · Pitot/Static Anti-Ice System
  > FIRST OFFICER`S TAT PROBE, FAULT LIGHT ON AT FL300, ECAM MONITOR. 5 MINS LATER SMELL OF ELEC ORIGIN, NO VISUAL SMOKE, ODOR GONE AFTER LANDING. FOUND DET SENSOR TEMP IN 107 VU PANEL WITH BURN HOLE IN TOP OF RELAY. WHILE CHANGING RELAY DET BASE SCREWS FELL OF
- [SDR FDEA201312102953](https://openairdocs.org/sdr/FDEA201312102953.md): Controller · failed · Dec 10, 2013 · N812FD · Airbus A310 · Cabin Pressure Controller
  > ON DESCENT TO KMDT RECEIVED CAD REG 2 FAULT, RESET NO HELP. ON LANDING, ACFT SHOWED 3300 CAB ALT, WENT TO MANUAL, TURNED OFF BLEEDS & PACKS. CABIN OUTFLOW VLVS FWD & AFT STAYED CLOSED. OVERBOARD VENT PARTIALLY OPENED, ACFT STILL PRESSURIZED. SAFETY VLV STA
- [SDR FDEA201301230166](https://openairdocs.org/sdr/FDEA201301230166.md): Adapter · damaged · Jan 23, 2013 · N410FE · Airbus A310 · Fuselage Miscellaneous Structure
  > IMPACT DAMAGE AT SCALLOP REMOVED CLEVIS ADAPTER BETWEEN SEAT TRACK 2R & 3R AT FR 54.2 IAW SRM 51-72-10 MATCH DRILLED REAMED NEW CLEVIS ADAPTER IAW SRM 51-40-44. INSTALLED NEW CLEVIS ADAPTER BETWEEN SEAT TRACK 2R & 3R AT FR 54.2 IAW A310-200 SRM 51-72-10. TOP
- [SDR CA110719003](https://openairdocs.org/sdr/CA110719003.md): Bearing · seized · Jul 18, 2011 · Airbus A310 · Trailing Edge Flap Control System
  > ON CLIMB OUT, ON FLAP RETRACTION, CREW RECEIVED A FLAP SYS 1 & 2 FAULT WITH FLAP JAM MESSAGE. ACFT RETURNED TO DEPARTURE AIRPORT AND LANDING WAS UNEVENTFUL. INVESTIGATION REVEALED THE LT WING FLAP DRIVE SYS STEADY BEARING AT POSITION FIN 275494 WAS SEIZED. S
- [SDR FDEA201101040006](https://openairdocs.org/sdr/FDEA201101040006.md): Skin · dented · Jan 4, 2011 · N450FE · Airbus A310 · Trailing Edge Flaps
  > LEFT INBOARD FLAP LOWER SKIN IS DENTED 70" FROM THE INBOARD EDGE AND 40" FROM THE TRAILING EDGE. DAMAGED AREA FOUND TO BE OUT OF LIMITS IAW A310-200 57-52-12, FIG 103. FABRICATED AND INSTALLED REPAIR IAW A310-200 SRM 57-52-12, FIG 205 PER EA 6-5750-136734
- [SDR FDEA201012034563](https://openairdocs.org/sdr/FDEA201012034563.md): Floor Support · corroded · Dec 3, 2010 · N443FE · Airbus A310 · Fuselage Miscellaneous Structure
  > FLOOR SUPPORT STRUCTURE, Y 450, HAS CORROSION FROM 6" INCHES AFT OF FR 14 TO 8" INCHES FWD OF FR 14 ON THE TOPSIDE. R & R FLOOR SUPPORT STRUCTURE Y450, FROM FR 11TO FR 15A IAW SRM 51-72-10, PAGES 1-3.
- [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 FDEA201010053934](https://openairdocs.org/sdr/FDEA201010053934.md): Lug · corroded · Oct 5, 2010 · N430FE · Airbus A310 · Wing, Landing Gear Attach Fittings
  > FOUND CORROSION IN RT MAIN LANDING GEAR FORWARD LUG AT RIB 5 DURING RIB 5 INSPECTION. REMOVED CORROSION BY OVERSIZING THE BORE AND SPOTFACING THE SURFACES, PERFORMING FINISHING CUTS, (FINAL BORE DIAMETER 5.341", FINAL LUG THICKNESS 2.220"), PERFORMING A
- [SDR FDEA201010023862](https://openairdocs.org/sdr/FDEA201010023862.md): Skin · corroded · Oct 2, 2010 · N418FE · Airbus A310 · Elevator, Plate/Skin
  > RIGHT ELEVATOR UPPER SKIN AFT EDGE FOUND CORROSIN. REMOVE TOP SKIN UNTIL THE REAR SPAR. PERFORM SRM 55-21-11 CONG-1 FIG 209 WITH THE FOLLOWING PROVISIONS: INSTALLED STRAP FILLER.
- [SDR FDEA201010013848](https://openairdocs.org/sdr/FDEA201010013848.md): Frame · corroded · Oct 1, 2010 · N445FE · Airbus A310 · Fuselage Main, Frame
  > FOUND LEVEL ONE CORROSION IN LOWER FORWARD CARGO COMPARTMENT AROUND MANHOLE COVER BETWEEN FRAME 38.1 AND FRAME 38.2, FROM STR 53L TO STR 53R. REMOVED CORRODIED POCKET REPAIRS FORM MANHOLE COVER AREA IN FORWARD LOWER CARGO COMPARTMENT SKIN AT FR 38 TO FR 3
- [SDR FDEA201009303821](https://openairdocs.org/sdr/FDEA201009303821.md): Filter · leaking · Sep 30, 2010 · N811FD · Airbus A310 · Hydraulic System, Main
  > DURING DESCENT RECEIVED ECAM GREEN HYD SYS LOW LEVEL WARNING. HYD QUANTITY ON OVERHEAD PANEL INDICATED ZERO. CONSULTED THE QRH AND MANUALLY EXTENDED THE LANDING GEAR. PERFORMED GREEN HYD SYS LEAK CHECK FOUND HYD LEAKAGE CAME FROM THE FILTER 1049 WHICH ON G
- [SDR FDEA201007292716](https://openairdocs.org/sdr/FDEA201007292716.md): Selector Valve · failed · Jul 29, 2010 · N811FD · Airbus A310 · Landing Gear Retraction/Extension System
  > L/G WOULD NOT RETRACT. COMPLIED WITH ECAM AND QRH. RETURNED TO DEPARTURE. PERFORMED PROX DETECTOR PROCESSING UNIT MEMORY RECALL IAW TSM 32-61-00. FOUND MEMORY EMPTY WITH "00" DISPLAYED. INSPECTED PITCH DAMPERS ON BOTH LANDING GEARS AND NO DEFECTS FOUND IN
- [SDR FDEA201007082404](https://openairdocs.org/sdr/FDEA201007082404.md): Unknown · multiple fail · Jul 8, 2010 · N448FE · Airbus A310 · Standard Practices/Structures
  > AFTER TAKEOFF GEAR WOULD NOT RETRACT USING SYS 2 OR SYS1. TRANSPONDER REPORTED INOP BY DEPARTURE. ACFT WOULD NOT PRESSURIZE. AUTO THROTTLES INOP. AUTOPILOTS WHEN SELECTED ON, REVERTED TO CONTROL WHEEL STEERING. BOTH CAPT AND F/O SPD TAPE WENT AWAY. WHE
- [SDR FDEA201006272203](https://openairdocs.org/sdr/FDEA201006272203.md): Autothrottle Sys · malfunctioned · Jun 27, 2010 · N426FE · Airbus A310 · Auto Throttle System
  > ON TAKE OFF WITH ONLY NR 2 ATS OPERATIVE, THE NR 2 THROTTLE KEPT TRYING TO ADVANCE TO FIREWALL AFTER 90 KNOTS, EGT WENT UP TO 940, T/0 ABORTED AT 100 KIAS, BRAKES COOLED, AUTOTHROTTLE OFF TAKEOFF ACCOMPLISHED. PERFORMED CROSSLOAD FROM NR 1 FMC. ALSO PERFOR
- [SDR FDEA200908143019](https://openairdocs.org/sdr/FDEA200908143019.md): Floor Support · corroded · Aug 14, 2009 · N802FD · Airbus A310 · Fuselage Miscellaneous Structure
  > FWD CABIN FLOOR STRUCTURE - SUPPORT FLOOR AT Y730 BTW FR12A AND 13A FOUND CORRODED. SUPPORT FLOOR REPLACED IAW SRM 51-72-10.
- [SDR FDEA200908072945](https://openairdocs.org/sdr/FDEA200908072945.md): Gearbox · leaking · Aug 7, 2009 · N405FE · Airbus A310 · Leading Edge Slat Control System
  > SLAT SYS 1 & 2 FAULT DURING ACFT CONFIGURATION REMOVED AND REPLACED LEFT WING SLAT NR 2 LINE GEARBOX PER AMM 27-84-16. REMOVED AND REPLACED RT WING SLAT IN LINE GEARBOX PER AMM 27-84-16. REMOVED AND REPLA CED RIGHT WING PPU PER AMM 27-81-14. OPEN
- [SDR FDEA200907233101](https://openairdocs.org/sdr/FDEA200907233101.md): Trunnion · damaged · Jul 23, 2009 · N802FD · Airbus A310 · Wing, Landing Gear Attach Fittings
  > LT WING - NR 1 EXTERIOR TRUNNION FOUND DAMAGED. THE AFFECTED TRUNNION WAS REPAIRED IAW CMM 57-53-12.
- [SDR FDEA200907022465](https://openairdocs.org/sdr/FDEA200907022465.md): Skin · dented · Jul 2, 2009 · N816FD · Airbus A310 · Fuselage Main, Plate/Skin
  > ON WALK AROUND FOUND DENT ON LOWER FUSELAGEAFT OF RADOME BETWEEN FRAME O AND FRAME 1 CUT OUT DAMAGED AREA IAW A310 SRM 53-11-12 FIG. 201. INSTALLED PERMANENT REPAIR IAW A310 SRM 53-11-12 FIG. 201. BETWEEN FRAME 0 AND FRAME 1 AT FUSELAGE LOWER CENTERLINE
- [SDR FDEA200903301736](https://openairdocs.org/sdr/FDEA200903301736.md): Hinge Fitting · corroded · Mar 30, 2009 · N421FE · Airbus A310 · Fuselage, Door Hinge
  > AFT CARGO DOOR HINGE FITTING WAS FOUND WITH CORROSION AT FRAME 62. THE FITTING WAS REPAIRED AS PER FEDEX EA 6-5310-129288.
- [SDR FDEA200903261074](https://openairdocs.org/sdr/FDEA200903261074.md): Floor Panel · damaged · Mar 26, 2009 · N813FD · Airbus A310 · Fuselage Floor Panel
  > CABIN FLOOR PANEL 242 LK IS BROKEN. REPAIRED PANEL 242 LK WITH THE FABRICATION OF A NEW PANEL USING THE OLD PANEL AS A TEMPLATE IAW DWG SRZ25-005; REV "H".
- [SDR FDEA200903261073](https://openairdocs.org/sdr/FDEA200903261073.md): Floor Panel · cracked · Mar 26, 2009 · N813FD · Airbus A310 · Fuselage Floor Panel
  > CABIN FLOOR BOARD 282 KF IS CRACKED. REPAIRED PANEL 282 KF WITH THE FABRICATION OF A NEW PANEL USING THE OLD PANEL AS A TEMPLATE IAW DWG SRZ25-005; REV "H".
- [SDR FDEA200903261056](https://openairdocs.org/sdr/FDEA200903261056.md): Floor Panel · damaged · Mar 26, 2009 · N813FD · Airbus A310 · Fuselage Floor Panel
  > FWD CARGO COMPARTMENT FLOOR PANEL 132 RF IS CRACKED AT THE PDU CUTOUT. REPAIRED PANEL 132 RF WITH THE FABRICATION OF A NEW PANEL USING THE OLD PANEL AS A TEMPLATE IAW DWG SRZ25-005; REV "H".
- [SDR FDEA200903261052](https://openairdocs.org/sdr/FDEA200903261052.md): Floor Panel · damaged · Mar 26, 2009 · N813FD · Airbus A310 · Fuselage Floor Panel
  > FWD CARGO COMPARTMENT FLOOR PANEL 131 RF IS BROKEN AT THE PDU CUTOUT. REPAIRED PANEL 131 RF WITH THE FABRICATION OF A NEW PANEL USING THE OLD PANEL AS A TEMPLATE IAW DWG SRZ25-005; REV "H".
- [SDR FDEA200903261070](https://openairdocs.org/sdr/FDEA200903261070.md): Sill · corroded · Mar 26, 2009 · N813FD · Airbus A310 · Fuselage Miscellaneous Structure
  > MAIN DECK, R-2 DOOR SILL AREA HAS A STRINGER ANGLE CORRODED AT FRAME 74, BS 3998 THRU 4005; STRINGER 26R. REMOVED CORROSION IN REF TO SRM 51-74-40. ORIGINAL MATERIAL THICKNESS 0.118 IAW DWG A539800712. MATERIAL REMOVED 0.026. MATERIAL REMANING 0.092 AN
- [SDR FDEA200903261069](https://openairdocs.org/sdr/FDEA200903261069.md): Floor Panel · punctured · Mar 26, 2009 · N813FD · Airbus A310 · Fuselage Floor Panel
  > AFT CARGO COMPARTMENT FLOOR PANEL 152 AF HAS MULTIPLE PUNCTURES ON THE BACK. REPAIRED PANEL 152 AF WITH THE FABRICATION OF A NEW PANEL USING THE OLD PANEL AS A TEMPLATE IAW DWG SRZ25-005; REV "H".
- [SDR FDEA200903261068](https://openairdocs.org/sdr/FDEA200903261068.md): Floor Panel · delaminated · Mar 26, 2009 · N813FD · Airbus A310 · Fuselage Floor Panel
  > AFT CARGO COMPARTMENT FLOOR PANEL 152 FF HAS DELAMINATION AND EDGE DAMAGE. REPAIRED PANEL 152 FF WITH THE FABRICATION OF A NEW PANEL USING THE OLD PANEL AS A TEMPLATE IAW DWG SRZ25-005; REV "H".
- [SDR FDEA200903261064](https://openairdocs.org/sdr/FDEA200903261064.md): Floor Panel · punctured · Mar 26, 2009 · N813FD · Airbus A310 · Fuselage Floor Panel
  > BULK CARGO COMPARTMENT FLOOR PANEL 162 DF IS PUNCTURED. FABRICATED NEW FLOOR PANEL AND TOP SHEET IAW SRZ 25-005, REV "H" & SRZ 25-055, REV "C".
- [SDR FDEA200903251742](https://openairdocs.org/sdr/FDEA200903251742.md): Skin · corroded · Mar 25, 2009 · N421FE · Airbus A310 · Wing, Plate/Skin
  > CENTER WING BOX LOWER SKIN EXTERNAL SURFACE FOUND WITH SEVERAL SPOTS OF CORROSION - REFER TO EA6-5710-129280 FOR DETAILS. REPAIR WAS ACCOMPLISHED AS PER EA 6-5710-129280.
- [SDR FDEA200903241734](https://openairdocs.org/sdr/FDEA200903241734.md): Beam · corroded · Mar 24, 2009 · N421FE · Airbus A310 · Passenger/Crew Doors
  > RT FWD PAX DOOR - SPOTS OF CORROSION AT BEAM 3. BEAM 3 WAS REPLACED AS PER SRM 51-72-10.
- [SDR FDEA200901120164](https://openairdocs.org/sdr/FDEA200901120164.md): Floor Panel · damaged · Jan 12, 2009 · N810FD · Airbus A310 · Fuselage Floor Panel
  > MAIN CARGO DECK COMPARTMENT, ZONE 231 FLOOR PANEL 231 XH HAS STRUCTURAL DAMAGES FABRICATED NEW MAIN DECK CARGO COMPARTMENT FLOOR PANEL 231 XH PER SAMPLE IAW SRZ 25-005 ON TRAVELER T8/ 773439.
- [SDR FDEA200901120163](https://openairdocs.org/sdr/FDEA200901120163.md): Floor Panel · damaged · Jan 12, 2009 · N810FD · Airbus A310 · Fuselage Floor Panel
  > MANI DECK CARGO COMPARTMENT,ZONE 251 FLOOR PANEL 251 ZH HAS STRUCTURAL DAMAGES. FABRICATED NEW MAIN DECK CARGO COMPARTMENT FLOOR PANEL 251 ZH PER SAMPLE IAW SRZ 25-005 ON TRAVELER T8/ 773454
- [SDR FDEA200901060044](https://openairdocs.org/sdr/FDEA200901060044.md): Fitting · inoperative · Jan 6, 2009 · N428FE · Airbus A310 · Fuselage, Landing Gear Attach Fittings
  > RIGHT MLG FWD TRUNNION WILL NOT TAKE GREASE. COMPLIED WITH E.A. 6-3210-123696.
- [SDR FDEA200901050031](https://openairdocs.org/sdr/FDEA200901050031.md): Floor Panel · damaged · Jan 5, 2009 · N436FE · Airbus A310 · Fuselage Floor Panel
  > MAIN DECK CARGO COMPARTMENT FLOOR PANEL IS DAMAGED BETWEEN FRAME 41 AND FRAME 43; RBL 31.0.
- [SDR FDEA200901020005](https://openairdocs.org/sdr/FDEA200901020005.md): Skin · dented · Jan 2, 2009 · N436FE · Airbus A310 · Passenger/Crew Doors
  > THE L-3 DOOR OUTER SKIN HAS 1 DENT AT FRAME 75 AND STR 25L. CHECKED DENT & FOUND IT TO BE OUT OF LIMITS IN REF TO SRM 52-10-00; FIG 102. REMOVED DAMAGED AREA & FABRICATED A REPAIR DOUBLER IN REF TO SRM 52-10-00; FIG 206. ALODINED REPAIR DOUBLER IN REF TO
- [SDR FDEA200901020004](https://openairdocs.org/sdr/FDEA200901020004.md): Skin · dented · Jan 2, 2009 · N436FE · Airbus A310 · Passenger/Crew Doors
  > THE L-3 DOOR OUTER SKIN HAS 1 SMALL DENT; AFT OF FRAME 74 AND STRINGER 26L. CHECKED DENT & FOUND IT TO BE OUT OF LIMITS IN REF TO SRM 52-10-00; FIG 102. REMOVED DAMAGED AREA & FABRICATED A REPAIR DOUBLER IN REF TO SRM 52-10-00; FIG 206. ALODINED REPAIR DOU
- [SDR FDEA200812315322](https://openairdocs.org/sdr/FDEA200812315322.md): Sensor · malfunctioned · Dec 31, 2008 · N804FD · Airbus A310 · Landing Gear Retraction/Extension System
  > AFTER T/O LANDING GEAR FAILED TO RETRACT. ECAM DISPLAYED L/G RETRACTION INOP. ACFT LOST AUTO-THROTTLES. FOUND TARGET SENSORS 9GA AND 11GA LOS SE AND OUT OF "C" DIMENSIONS OUT OF LIMITS; REMOVED AND REPLACED SENSORS 9GA AND 11GA ON LT BOGIE REF. MM 32-00-00
- [SDR FDEA200812305320](https://openairdocs.org/sdr/FDEA200812305320.md): Floor Panel · cracked · Dec 30, 2008 · N810FD · Airbus A310 · Fuselage Floor Panel
  > FWD CARGO COMPARTMENT FLOOR PANELS, ZONE 131, FLOOR PANEL 131 HG HAS STRUCTURAL DAMAGES FABRICATED NEW FWD CARGO COMPARTMENT FLOOR PANEL, IAW SAMPLE,PANEL 131 HG, IAW SRZ-25-005,ON TRAVELER, NR T8/773384.
- [SDR FDEA200812245291](https://openairdocs.org/sdr/FDEA200812245291.md): Shear Tie · corroded · Dec 24, 2008 · N428FE · Airbus A310 · Fuselage Internal Mounting Structure
  > FWD PIT BILGE FRAME NR 37 BETWEEN STRINGER 51L AND STRINGER 52L SHEAR TIE HAS CORROSION ON THE AFT SURFACE. REMOVED SHEAR TIE FROM FRAME 37 IAW SRM 51-40-21. REMOVED CORROSION IAW SRM 51-73-10. ORIGINAL MATERIAL 0.055 IAW SRM 53-14-13. REMAINING MATERIAL
- [SDR FDEA200812205246](https://openairdocs.org/sdr/FDEA200812205246.md): Floor Panel · delaminated · Dec 20, 2008 · N428FE · Airbus A310 · Fuselage Floor Panel
  > L/H TAIL COMPARTMENT FLOORBOARD IS DELAMINATED AT THE AFT CORNER ACCESS THRU 312 AR. FABBED A NEW FLOOR PANEL USING THE OLD PANEL AS A TEMPLATE. MATERIAL ID; LOCATED HOLES; COUNTERBORED HOLES; POTTED & SANDED EDGE; INSTALLED INSERTS; APPLIED ANTI-SKID & P
- [SDR FDEA200812205251](https://openairdocs.org/sdr/FDEA200812205251.md): Floor Panel · damaged · Dec 20, 2008 · N428FE · Airbus A310 · Fuselage Floor Panel
  > MAIN CABIN FLOOR PANEL 242 RJ IS DAMAGED. FABBED NEW PANEL USING THE OLD PANEL AS A TEMPLATE. MATERIAL ID; LOCATED HOLES USING THE THE OLD PANEL; COUNTERBORED HOLES; POTTED & SANDED EDGE; INSTALLED INSERTS; APPLIED ANTI-SKID & PART MARKED IAW DWG SRZ
- [SDR FDEA200812205250](https://openairdocs.org/sdr/FDEA200812205250.md): Floor Panel · dented · Dec 20, 2008 · N428FE · Airbus A310 · Fuselage Floor Panel
  > FWD CARGO PIT FLOOR PANEL 132 ZF IS DAMAGED. FABBED NEW PANEL USING THE OLD PANEL AS A TEMPLATE. MATERIAL ID; LOCATED HOLES USING THE THE OLD PANEL; COUNTERBORED HOLES; POTTED & SANDED EDGE; INSTALLED INSERTS; APPLIED ANTI-SKID & PART MARKED IAW DWG SRZ
- [SDR FDEA200812205249](https://openairdocs.org/sdr/FDEA200812205249.md): Floor Panel · dented · Dec 20, 2008 · N428FE · Airbus A310 · Fuselage Floor Panel
  > BULK CARGO PIT FLOOR PANEL 162 HF HAS SEVERAL DENTS. FABBED NEW PANEL USING THE OLD PANEL AS A TEMPLATE. MATERIAL ID; LOCATED HOLES USING THE THE OLD PANEL; COUNTERBORED HOLES; POTTED & SANDED EDGE; INSTALLED INSERTS; APPLIED ANTI-SKID & PART MARKED IA

Next page: https://openairdocs.org/model/airbus-a310/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 aircraft_model_key = 'A310'
ORDER BY difficulty_date DESC
```

This list as a web page: https://openairdocs.org/model/airbus-a310/reports

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