# N809FD: Airbus Industrie A310-324, registration cancelled 2024-03-02

- Type: Cancelled registration (FAA registry, deregistered aircraft)
- Cancelled: March 2, 2024
- Status when cancelled: Valid registration
- Airframe: [Airbus Industrie A310-324](https://openairdocs.org/model/airbus-industrie-a310-324) (registry code 3930318)
- Data sheets: [TCDS A35EU](https://openairdocs.org/tcds/A35EU) (OpenAirDocs)
- Serial number: 449
- Type of aircraft: Fixed wing multi engine
- Certificate issued: April 13, 2005
- Last registry action: October 20, 2023
- Mode S code: AB03CD
- Owner when cancelled: [Federal Express Corp](https://openairdocs.org/faa-owner/FEDERAL%20EXPRESS%20CORP)
- Location: [Memphis, TN](https://openairdocs.org/faa-place/TN/Memphis)
- Owner type: Corporation
- Owner's area on the map: 35.0351° N, 89.9272° W: Placed by OpenAirDocs at the center of ZIP code 38118, within about 3 miles (OpenAirDocs). The owner's mailing address, not where the aircraft was based
- The mark today: https://openairdocs.org/aircraft/N809FD
- FAA registry: https://registry.faa.gov/AircraftInquiry/Search/NNumberResult?nNumberTxt=809FD
- Page: https://openairdocs.org/deregistered/N809FD-2024-03-02

From the FAA registry file of October 29, 2026, cancelled registrations. Owners' street addresses are left out. The Mode S code belongs to the N-number, not the airframe.

ADs and bulletins for the Airbus Industrie A310-324: https://openairdocs.org/model/airbus-industrie-a310-324.md

## Service difficulty reports (115, newest 50)

Matched to this aircraft by N-number and event date, checked against the reported serial number, make and model.

- [SDR FDEA201909112203](https://openairdocs.org/sdr/FDEA201909112203), Sep 11, 2019: GEARBOX. FAILED. PDIS 809 27-80 2171 11SEP19 SAT OPEN U LOGPAGES:2553291 DURING EXTENSION OF FLAPS AT 40 DEGREES, RECEIVED SLATS FAULT SYS 1 AND 2. CYCLED PER ECAM, FAULT REILLU
- [SDR FDEA201909102197](https://openairdocs.org/sdr/FDEA201909102197), Sep 10, 2019: COMPUTER. FAULTY. PDIS 809 27-80 2168 10SEP19 AFW OPEN U DURING ARRIVAL TO KAFW WHILE EXTENDING THE SLATS HAD SLATS 1&2 FAULT. SLATS WERE STUCK AT 5 DEGREE. RETRACTED SLATS AND I
- [SDR FDEA201811053107](https://openairdocs.org/sdr/FDEA201811053107), Nov 5, 2018: TEE FITTING. CRACKED. CNTR WING INSP REAR SPAR INTERNAL ANGLE/TEE FITTING FR44 RT SIDE FWD HOLE WITH CRACK SIGNAL. COMPLIED WITH EA:6-5710-T0343040 PT1 REPAIRED CENTER WING REAR SPAR
- [SDR FDEA201811053106](https://openairdocs.org/sdr/FDEA201811053106), Nov 5, 2018: TEE FITTING. CRACKED. CNTR WING INSP REAR SPAR INTERNAL ANGLE/TEE FITTING FR44 LT SIDE MID HOLE WITH CRACK SIGNAL. COMPLIED WITH EA:6-5710-T0343040 PT1 REPAIRED CENTER WING REAR SPAR
- [SDR FDEA201810202960](https://openairdocs.org/sdr/FDEA201810202960), Oct 20, 2018: SUPPORT BEAM. DAMAGED. MDCC FWD UTILITY AREA FR14-FR17, -Y1456 LONGITUDINAL SUPPORT BEAM FOUND 1EA HOLE ENLARGED REFER TO SRM 53-12-15 FIG. 207 REPAIRED THE -Y1456 LONGITUDINAL SUPPOR
- [SDR FDEA201706011556](https://openairdocs.org/sdr/FDEA201706011556), Jun 1, 2017: INDICATION SYS. INTERMITTENT. R1 ENTRY DOOR SLIDE ARMED INDICATOR DOES NOT SHOW ARMED ON ECAM. CLEANED CONNECTOR ON 14WN RT DOOR ESCAPE SLIDE ARM SWITCH. CLOSED AND ARMED R1 DOOR SLIDE AND S
- [SDR FDEA201704261272](https://openairdocs.org/sdr/FDEA201704261272), Apr 26, 2017: POWER SUPPLY. INOPERATIVE. R1 DOOR SLIDE FAIL TO ARM. REMOVED AND REPLACED AUTONOMOUS STANDBY POWER SUPPLY UNIT 70WN AND BATTERY 1 IAW AMM 52-73-18-04, BITE TESTED OK, R1 SLIDE INDICATION
- [SDR FDEA201703040774](https://openairdocs.org/sdr/FDEA201703040774), Mar 4, 2017: LINE. LEAKING. LOST ALL GREEN SYSTEM HYD FLUID LEAVING FL 320. USED LANDING GEAR GRAVITY EXTENTION PROCEDURE. HYD SYS CIRCUIT BREAKERS HAVE BEEN COLLARED IN E/E BAY. FOUND A P
- [SDR FDEA201612064330](https://openairdocs.org/sdr/FDEA201612064330), Dec 6, 2016: FLAP SYSTEM. MALFUNCTIONED. FLAPS STUCK AT 0 DURING APPROACH. COMPLIED WITH ECAM & QRH. NO RELIEF IN CYCLE. LANDED SLATS 30 FLAPS 0. TSM 27-50, BOTH SFCC'S INDICATE FLAP JAMB, LEFT FLAP SY
- [SDR FDEA201603100888](https://openairdocs.org/sdr/FDEA201603100888), Mar 10, 2016: GCU. MALFUNCTIONED. REJECTED TAKE OFF AT 90 KNOTS, AC BUS 2 OFF, GEN 2 FAULT. PERFORMED BITE CHECK ON GND POWER CONTROL UNIT & FOUND, RT GEN POWER SYS, FAULTED. R & R NR 2 GEN CONT
- [SDR FDEA201602120510](https://openairdocs.org/sdr/FDEA201602120510), Feb 12, 2016: SEQUENCE VALVE. FAULTY. RIGHT MLG DID NOT EXTEND DURING NORMAL EXTENSION. GEAR EXTENDED TO DOWN & LOCKED WITH MANUAL EXTENSION. FREE FALL EXTENSION SYS RETURNED TO NORMAL CONDITION IAW
- [SDR FDEA201601130138](https://openairdocs.org/sdr/FDEA201601130138), Jan 13, 2016: SKIN. DELAMINATED. RIGHT SIDE RUDDER PANEL, FOUND DELAMINATED AT TE RR 48 - RR 49, APPROX 6" X 6". REMOVE THE OUTER SKIN IN THE DAMAGED AREA IAW SRM 55-41-12 PARA 31. PERFORM A TA
- [SDR FDEA201601120125](https://openairdocs.org/sdr/FDEA201601120125), Jan 12, 2016: FITTING. CRACKED. CENTER WING INSPECTION, REAR SPAR INTERNAL ANGLES & TEE FITTING, HOLE NR 60 WITH CRACK SIGNAL, RT SIDE. REPAIRED IAW EA 6-5710-T0322510. NDT CHECK, NO CRACK FOU
- [SDR FDEA201601120124](https://openairdocs.org/sdr/FDEA201601120124), Jan 12, 2016: FITTING. CRACKED. CENTER WING INSPECTION, REAR SPAR INTERNAL ANGLES & TEE FITTING, HOLE NR 62 WITH CRACK SIGNAL, LT SIDE. REPAIRED IAW EA6-5710-T0322510. NDT CHECK, NO CRACK FOUN
- [SDR FDEA201601120123](https://openairdocs.org/sdr/FDEA201601120123), Jan 12, 2016: FITTING. CRACKED. CENTER WING INSPECTION, REAR SPAR INTERNAL ANGLES & TEE FITTING, HOLE NR 60 WITH CRACK SIGNAL, LT SIDE. REPAIRED IAW EA 6-5710-T0322510. NDT CHECK, NO CRACK FOU
- [SDR FDEA201601120122](https://openairdocs.org/sdr/FDEA201601120122), Jan 12, 2016: FITTING. CRACKED. CENTER WING INSPECTION REAR SPAR INTERNAL ANGLES & TEE FITTING, HOLE NR 46 WITH CRACK SIGNAL, LT SIDE. REPAIRED IAW EA 6-5710-T0322510. NDT CHECK, NO CRACK FOUN
- [SDR FDEA201601120121](https://openairdocs.org/sdr/FDEA201601120121), Jan 12, 2016: FITTING. CRACKED. CENTER WING INSPECTION REAR SPAR INTERNAL ANGLES & TEE FITTING, HOLE NR 41 WITH CRACK SIGNAL, LT SIDE. REPAIRED IAW EA 6-5710-T0322510. NDT CHECK, NO CRACK FOUN
- [SDR FDEA201601120120](https://openairdocs.org/sdr/FDEA201601120120), Jan 12, 2016: FITTING. CRACKED. CENTER WING INSPECTION, REAR SPAR INTERNAL ANGLES & TEE FITTING, HOLE NR 31 WITH CRACK SIGNAL, LT SIDE. REPAIRED IAW EA 6-5710-T0322510. NDT CHECK, NO CRACK FOU
- [SDR FDEA201601120119](https://openairdocs.org/sdr/FDEA201601120119), Jan 12, 2016: FITTING. CRACKED. CENTER WING INSPECTION REAR SPAR INTERNAL ANGLES & TEE FITTING, HOLE NR 14 WITH CRACK SIGNAL, RT SIDE. REPAIRED IAW EA 6-5710-T0322510. NDT CHECK, NO CRACK FOUN
- [SDR FDEA201601120118](https://openairdocs.org/sdr/FDEA201601120118), Jan 12, 2016: FITTING. CRACKED. CENTER WING INSPECTION REAR SPAR INTERNAL ANGLES & TEE FITTING, HOLE NR 62 WITH CRACK SIGNAL, RT SIDE. REPAIRED IAW EA 6-5710-T0322510. NDT CHECK, NO CRACK FOUN
- [SDR FDEA201601120117](https://openairdocs.org/sdr/FDEA201601120117), Jan 12, 2016: FITTING. CRACKED. CENTER WING INSPECTION REAR SPAR INTERNAL ANGLES & TEE FITTING, HOLE NR 61 WITH CRACK SIGNAL, RT SIDE. REPAIRED THE CRACKED HOLE IAW EA6-5710-T0322510. NDT CHEC
- [SDR FDEA201601040021](https://openairdocs.org/sdr/FDEA201601040021), Jan 4, 2016: STRINGER. CORRODED. AFT CARGO BAY STRINGER 54R, FOUND CORRODED BETWEEN FRAMES 59 - 63. REPAIR THE STRINGER IAW SRM 53-10-14-201 FIG 201 VIEW F & G. MAJOR REPAIR IAW GMM 6-2-100.
- [SDR FDEA201601040020](https://openairdocs.org/sdr/FDEA201601040020), Jan 4, 2016: STRINGER. CORRODED. AFT CARGO BAY, STRINGER 55R, FOUND CORRODED BETWEEN FRAMES 64 - 65. REPAIRED THE STRINGER IAW SRM 53-10-14-201 FIG 201 VIEW F & G. MAJOR REPAIR IAW GMM 6-2-100.
- [SDR FDEA201512304106](https://openairdocs.org/sdr/FDEA201512304106), Dec 30, 2015: BEAM. CORRODED. CENTER WING FUEL TANK, BOTTOM SKIN LONGITUDINAL BEAM 4RT OTBD ATTACHED SPLICE FITTING, CORRODED AT FRAME 40. BLENDED OUT & SMOOTHED THE CORRODED AREA IAW SRM 51
- [SDR FDEA201512304105](https://openairdocs.org/sdr/FDEA201512304105), Dec 30, 2015: STRINGER. CORRODED. FORWARD CARGO COMPARTMENT STRINGER 44R CORRODED BETWEEN FRAMES 38 - 38.1. REPAIRED THE STRINGER IAW SRM 53-10-14-201 FIG 201. MAJOR REPAIR IAW GMM 6-2-100.
- [SDR FDEA201512304104](https://openairdocs.org/sdr/FDEA201512304104), Dec 30, 2015: STRINGER SPLICE. CORRODED. AFT CARGO BAY STRINGER 54L, STRINGER SPLICE FITTING FOUND CORRODED AT FRAME 65. REPLACED THE SPLICE FITTING IAW SRM 51-40-21. THIS IS A MAJOR REPAIR IAW GMM 6-2
- [SDR FDEA201512264080](https://openairdocs.org/sdr/FDEA201512264080), Dec 26, 2015: STRINGER. CORRODED. EXISTING REPAIR ON FUSELAGE STRINGER 55 LT SIDE, BETWEEN FRAME 59 & 61 REQUIRES EVALUATION FOR CONFORMITY. THE EXISTING REPAIR WAS EVALUATED & CORROSION WAS FOU
- [SDR FDEA201512013845](https://openairdocs.org/sdr/FDEA201512013845), Dec 1, 2015: DOOR. DEPARTED. ON DEPARTURE, MAIN WW FWD LEFT & CENTER DOORS DEPARTED ACFT.
- [SDR FDEA201506231983](https://openairdocs.org/sdr/FDEA201506231983), Jun 23, 2015: PROXIMITY SENSOR. FAILED. LANDING GEAR WOULD NOT RETRACT USING SYSTEM 1. REMOVED AND REPLACED THE LEFT MAIN GEAR TORQUE LINK PROXIMITY DETECTOR IAW AMM 32-00-00-04.
- [SDR FDEA201505031377](https://openairdocs.org/sdr/FDEA201505031377), May 3, 2015: SENSOR. FAILED. MLG WOULD NOT COME UP DURING DEPARTURE IN SYS 1 & SWITCHED TO SYS 2 & STILL WOULD NOT COME UP. ALSO HAD ADC 1 FAULT, PITCH TRIM NR 1 FAULT, CAPTAIN PROBABLY HEA
- [SDR FDEA201405281215](https://openairdocs.org/sdr/FDEA201405281215), May 28, 2014: SUPPORT. CORRODED. LEFT MLG RIB 5 FWD LUG HAS CORROSION IN BORE & FWD FACE. COMPLIED WITH EA 6-5710-T0308476 P1 WINGS BASIC WING STRUCTURE LT & RT RIB 5 FWD LUG CORROSION, LT RIB 
- [SDR FDEA201405281214](https://openairdocs.org/sdr/FDEA201405281214), May 28, 2014: SUPPORT. CORRODED. RIGHT MLG RIB 5 FWD LUG HAS CORROSION IN BORE & FWD FACE. COMPLIED WITH EA 6-5710-T0308476 P2 WINGS BASIC WING STRUCTURE LT & RT RIB 5 FWD LUG CORROSION, RT RIB
- [SDR FDEA201311122736](https://openairdocs.org/sdr/FDEA201311122736), Nov 12, 2013: SKIN. CORRODED. LEFT WING UPPER SKIN INBD JET FUEL GROUND CONNECTOR POINT AROUND AREA HAS SLIGHT CORROSION AT STR 7 AND STR 8 POSITION. REPAIRED IAW EA 6-5720-T0303769. REPAIR 
- [SDR FDEA201311012663](https://openairdocs.org/sdr/FDEA201311012663), Nov 1, 2013: BEAM. CRACKED. ONE CRACK WAS FOUND ON THE NR 33 FASTENER OF THE INNER LONGERON BEAM FLANGE AT STRINGER 11 BETWEEN FRAMES 73A AND 75A (LT SIDE). CRACK LENGTH IS 1INCH IAW E6-53
- [SDR FDEA201310152506](https://openairdocs.org/sdr/FDEA201310152506), Oct 15, 2013: LIMITER. TRIPPED. DURING FINAL, TRIED LOWERING FLAPS AND RECEIVED A FLAPS 1/2 SYS FAULT. CYCLED HANDLE NO FLAPS EXTENDED. FOUND WHEEL WELL TORQUE LIMITER FOR RT WING FLAP DRIVE T
- [SDR FDEA201106062200](https://openairdocs.org/sdr/FDEA201106062200), Jun 6, 2011: BATTERY. INOPERATIVE. COURIER COMPARTMENT EMERGENCY LIGHT TEST INOP. R & R 29WL1 POWER SUPPLY BATTERY IAW MM 33-55-00-05, NO HELP, REINSTALLED ORIGINAL BATTERY, SUSPECT POWER SUPPLY 
- [SDR FDEA201105292020](https://openairdocs.org/sdr/FDEA201105292020), May 29, 2011: SKIN. DELAMINATED. THERMOGRAPHY AND ULTRASONIC INSP CARRIED OUT FOUND TRAPPED WATER ON RT RUDDER SKIN AT T/E BELOW NR 37 SCREW LINE AREAS APPROX 600 SQ MM. ACCOMPLISHED EA 6-5540-
- [SDR FDEA201105141841](https://openairdocs.org/sdr/FDEA201105141841), May 14, 2011: STRINGER. CORRODED. FUSELAGE AFT PRESSURE BULKHEAD FORWARD FACE AT RIGHT HAND STGR 31 FOUND STRINGER END TOP SURFACE WITH CORROSION FUSELAGE AFT PRESSURE BULKHEAD FORWARD FACE AT R
- [SDR FDEA201105141840](https://openairdocs.org/sdr/FDEA201105141840), May 14, 2011: STRINGER. CORRODED. FUSELAGE AFT PRESSURE BULKHEAD FORWARD FACE AT RIGHT HAND STGR28 FOUND STRINGER END TOP SURFACE WITH CORROSION FUSELAGE AFT PRESSURE BULKHEAD FORWARD FACE AT RI
- [SDR FDEA201010194103](https://openairdocs.org/sdr/FDEA201010194103), Oct 19, 2010: WARNING MESSAGE. FALSE INDICATION. ON TAKEOFF ROLL APPROX 80 KTS GOT ECAM WARNING FOR PITCH FEEL SYS 1 AND 2 AND RUDDER TRAVEL SYS 1 AND 2 FAULTS. ALL 4 LIGHTS WERE ILLUMINATED ON OVHD PANEL. ABO
- [SDR FDEA201009303820](https://openairdocs.org/sdr/FDEA201009303820), Sep 30, 2010: PICKUP. MALFUNCTIONED. ON FINAL APPROACH, WHEN FLAPS WERE SELECTED TO 40 DEG RECEIVED ECAM. FLAPS STUCK. ALSO RECEIVED SYS 1 AND 2 FAULT LIGHT ON OVERHEAD PANEL. FLAPS STUCK BETWEEN 2
- [SDR FDEA201009143386](https://openairdocs.org/sdr/FDEA201009143386), Sep 14, 2010: JACKSCREW. DAMAGED. ON FINAL SLATS/FLAPS STUCK 20/17: RECYCLED AND SLAT/FLAP STUCK LIGHT EXTINGUISHED. SELECTED SLAT/FLAP 20/20 TO LAND AND LIGHT REILLUMINATED, THE SECOND TIME. RA
- [SDR 08FDEA04951](https://openairdocs.org/sdr/08FDEA04951), Nov 21, 2008: FRAME. CORRODED. EMPENNAGE FRAME 84 AT STRINGER 13 L, THE FRAME LOWER CHORD IS CORRODED AT AND UNDER THE CROSSBEAM. REMOVED CORROSION FROM THE FRAME FLANGE IAW SRM 51-74-10. FOU
- [SDR 08FDEA04898](https://openairdocs.org/sdr/08FDEA04898), Nov 17, 2008: FLOOR PANEL. CRACKED. FLOOR PANEL 232 LG IS CRACKED. FABBED NEW FLOOR PANEL 231 LG USING THE OLD PANEL AS A TEMPLATE. POTED & CURED INSERTS; POTTED; CURED & SANDED THE EDGES. APPLIED
- [SDR 08FDEA04897](https://openairdocs.org/sdr/08FDEA04897), Nov 17, 2008: FLOOR PANEL. CRACKED. FLOOR PANEL 232 TG IS CRACKED. FABBED NEW FLOOR PANEL 232 TG USING THE OLD PANEL AS A TEMPLATE. POTED & CURED INSERTS; POTTED; CURED & SANDED THE EDGES. APPLIED
- [SDR 08FDEA04871](https://openairdocs.org/sdr/08FDEA04871), Nov 13, 2008: FLOOR PANEL. DELAMINATED. FWD CARGO PIT FLOOR PANEL NR 131QF IS DAMAGED FABRICATED NEW PANEL FWD CARGO PIT FLOOR PNL 131QF PER DWG SRZ 25-005 REV G AND AMM 20-31-00-0 PG 58.
- [SDR 08FDEA04877](https://openairdocs.org/sdr/08FDEA04877), Nov 12, 2008: FITTING. CRACKED. BULK CARGO DOOR FITTING UNDERNEATH SPRING MECHANISM IS CRACKED. REMOVED CRACKED FITTING IAW A310-300 SRM 51-72-10. LOCATED; DRILL & INSTALLED NEW FITTING P/N A5
- [SDR 08FDEA04853](https://openairdocs.org/sdr/08FDEA04853), Nov 11, 2008: FLOOR PANEL. DAMAGED. BULK CARGO PIT FLOOR PANEL NR 161 GF IS DAMAGED. FABRICATED NEW PANEL IAW DWG. SRZ 25-005. FABBED TOP SHEET IAW SRZ DWG. 25-005. ATTACHED TOP SHEET IAW DWG SRZ 
- [SDR 08FDEA04834](https://openairdocs.org/sdr/08FDEA04834), Nov 10, 2008: FAILSAFE. CORRODED. LEFT AFT PASSENGER DOOR EXTERNAL SKIN IN THE SCUFF PLATE AREA AND FAIL/SAFE RING HAS SEVERAL AREAS OF CORROSION. REMOVED LIGHT SURFACE CORROSION AS REQUIRED FRO
- [SDR 08FDEA04833](https://openairdocs.org/sdr/08FDEA04833), Nov 10, 2008: FAILSAFE. CORRODED. RIGHT AFT PAX DOOR FAIL/SAFE RING LOWER SECTION HAS CORROSION ON THE SKIN AROUND THE FASTENER HEADS. REMOVED LIGHT SURFACE CORROSION AS REQUIRED ON R/H AFT ENTR

All 115: https://openairdocs.org/deregistered/N809FD-2024-03-02/reports.md

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