# Service difficulty reports: N809FD, cancelled Mar 2, 2024

A list on [N809FD, cancelled Mar 2, 2024](https://openairdocs.org/deregistered/N809FD-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 · 115 reports

- [SDR FDEA201909112203](https://openairdocs.org/sdr/FDEA201909112203.md): Gearbox · failed · Sep 11, 2019 · N809FD · Airbus A310324 · Leading Edge Slat Control System
  > 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 REILLUMINATED. FOLLOWED ECAM AND QRH PROCEDURES. DECLARED EMERGENCY IN SAT. LANDED WITHOUT
- [SDR FDEA201909102197](https://openairdocs.org/sdr/FDEA201909102197.md): Computer · faulty · Sep 10, 2019 · N809FD · Airbus A310324 · Leading Edge Slat Control System
  > 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 IMMEDIATELY GOT SLATS 1&2 FAULT. THE SLATS WERE STUCK AT 0 DEGREES. FOLLOWED QRH AND LAN
- [SDR FDEA201811053107](https://openairdocs.org/sdr/FDEA201811053107.md): Tee Fitting · cracked · Nov 5, 2018 · N809FD · Airbus A310324 · Wing Miscellaneous Structure
  > 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 RIB1 INTERNAL ANGLE/TEE FITTING AT FR44 RH SIDE FWD HOLE(#34A). MAJOR REPAIR IAW FEDEX GMM6-2-
- [SDR FDEA201811053106](https://openairdocs.org/sdr/FDEA201811053106.md): Tee Fitting · cracked · Nov 5, 2018 · N809FD · Airbus A310324 · Wing Miscellaneous Structure
  > 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 RIB1 INTERNAL ANGLE/TEE FITTING AT FR44 LH SIDE MID HOLE(#35A). CATEGORY "B" REPAIR.FIRST INSPE
- [SDR FDEA201810202960](https://openairdocs.org/sdr/FDEA201810202960.md): Support Beam · damaged · Oct 20, 2018 · N809FD · Airbus A310324 · Fuselage Miscellaneous Structure
  > 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 SUPPORT BEAM AT MDCC FWD UTILITY AREA BETWEEN FR14-FR17. THIS IS CATEGORY "B" REPAIR AND MUST BE INSPECT A
- [SDR FDEA201706011556](https://openairdocs.org/sdr/FDEA201706011556.md): Indication Sys · intermittent · Jun 1, 2017 · N809FD · Airbus A310324 · Door Warning System
  > 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 SLIDE ARM INDICATION CHECKS NORMAL ON ECAM IAW ASM 52-73-00. ACFT OK FOR SERVICE.
- [SDR FDEA201704261272](https://openairdocs.org/sdr/FDEA201704261272.md): Power Supply · inoperative · Apr 26, 2017 · N809FD · Airbus A310324 · Emergency Equipment
  > 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 CHECKS OK IAW AMM 52-73-00.
- [SDR FDEA201703040774](https://openairdocs.org/sdr/FDEA201703040774.md): Line · leaking · Mar 4, 2017 · N809FD · Airbus A310324 · Hydraulic System, Main
  > 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 PIN HOLE IN LT GREEN HYD RETURN LINE, REMOVED AND REPLACED THE LINE IAWSMP 20-23-11-00, & 20-23-12-
- [SDR FDEA201612064330](https://openairdocs.org/sdr/FDEA201612064330.md): Flap System · malfunctioned · Dec 6, 2016 · N809FD · Airbus A310324 · Trailing Edge Flap Control System
  > 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 SYSTEM TORQUE LIMITER TRIPPED. SRM 27-50-02 FIG 101 BLOCK 2, ALL SCREW JACK TORQUE LIMITERS INSP
- [SDR FDEA201603100888](https://openairdocs.org/sdr/FDEA201603100888.md): Gcu · malfunctioned · Mar 10, 2016 · N809FD · Airbus A310324 · AC Inverter
  > 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 CONTROL UNIT IAW AMM 24-22-12-04. RAN NR 2 ENG IAW JRH WITH NO FAULTS NOTED. ALSO PERFORMED ADJUSTME
- [SDR FDEA201602120510](https://openairdocs.org/sdr/FDEA201602120510.md): Sequence Valve · faulty · Feb 12, 2016 · N809FD · Airbus A310324 · Landing Gear Retraction/Extension System
  > 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 AMM 32-33-00-2. INSPECTED MAIN LG DOOR & WW AREA & NO DEFECT FOUND. JACKED UP ACFT IAW AMM 07-1
- [SDR FDEA201601130138](https://openairdocs.org/sdr/FDEA201601130138.md): Skin · delaminated · Jan 13, 2016 · N809FD · Airbus A310324 · Rudder, Plate/Skin
  > 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 TAP TEST AROUND THE DAMAGE AREA TO MAKE SURE NO DELAMINATION IAW NTM 51-10-19, NO DAMAGE. PERFORM
- [SDR FDEA201601120125](https://openairdocs.org/sdr/FDEA201601120125.md): Fitting · cracked · Jan 12, 2016 · N809FD · Airbus A310324 · Fuselage Main, Attach Fittings
  > 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 FOUND. WET INSTALLED THE BUSHES, WASHER & FASTENER IAW EA 6-5710-T0322510. THIS IS A MAJOR REPAIR
- [SDR FDEA201601120124](https://openairdocs.org/sdr/FDEA201601120124.md): Fitting · cracked · Jan 12, 2016 · N809FD · Airbus A310324 · Fuselage Main, Attach Fittings
  > 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 FOUND. WET INSTALLED THE FASTENER IAW EA 6-5710-T0322510. THIS IS A MAJOR REPAIR IAW GMM 6-2-100.
- [SDR FDEA201601120123](https://openairdocs.org/sdr/FDEA201601120123.md): Fitting · cracked · Jan 12, 2016 · N809FD · Airbus A310324 · Fuselage Main, Attach Fittings
  > 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 FOUND. WET INSTALLED THE BUSHES, WASHER & FASTENER IAW EA 6-5710-T0322510. THIS IS A MAJOR REPAIR I
- [SDR FDEA201601120122](https://openairdocs.org/sdr/FDEA201601120122.md): Fitting · cracked · Jan 12, 2016 · N809FD · Airbus A310324 · Fuselage Main, Attach Fittings
  > 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 FOUND. WET INSTALLED THE BUSHES, WASHER & FASTENER IAW EA 6-5710-T0322510. THIS IS A MAJOR REPAIR I
- [SDR FDEA201601120121](https://openairdocs.org/sdr/FDEA201601120121.md): Fitting · cracked · Jan 12, 2016 · N809FD · Airbus A310324 · Fuselage Main, Attach Fittings
  > 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 FOUND. WET INSTALLED THE BUSHES, WASHER & FASTENER IAW EA 6-5710-T0322510. THIS IS A MAJOR REPAIR IA
- [SDR FDEA201601120120](https://openairdocs.org/sdr/FDEA201601120120.md): Fitting · cracked · Jan 12, 2016 · N809FD · Airbus A310324 · Fuselage Main, Attach Fittings
  > 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 FOUND. WET INSTALLED THE BUSHES, WASHER & FASTENER IAW EA 6-5710-T0322510. THIS IS A MAJOR REPAIR I
- [SDR FDEA201601120119](https://openairdocs.org/sdr/FDEA201601120119.md): Fitting · cracked · Jan 12, 2016 · N809FD · Airbus A310324 · Fuselage Main, Attach Fittings
  > 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 FOUND. WET INSTALLED THE FASTENER IAW EA 6-5710-T0322510. THIS IS A MAJOR REPAIR IAW GMM 6-2-100.
- [SDR FDEA201601120118](https://openairdocs.org/sdr/FDEA201601120118.md): Fitting · cracked · Jan 12, 2016 · N809FD · Airbus A310324 · Fuselage Main, Attach Fittings
  > 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 FOUND. WET INSTALLED FASTENER IAW EA 6-5710-T0322510. THIS IS A MAJOR REPAIR IAW GMM 6-2-100.
- [SDR FDEA201601120117](https://openairdocs.org/sdr/FDEA201601120117.md): Fitting · cracked · Jan 12, 2016 · N809FD · Airbus A310324 · Fuselage Main, Attach Fittings
  > 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 CHECK, NO CRACK FOUND. WET INSTALLED THE BUSHES, WASHER & FASTENER IAW EA 6-5710-T0322510. THIS IS A
- [SDR FDEA201601040021](https://openairdocs.org/sdr/FDEA201601040021.md): Stringer · corroded · Jan 4, 2016 · N809FD · Airbus A310324 · Fuselage Main, Longeron/Stringer
  > 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.md): Stringer · corroded · Jan 4, 2016 · N809FD · Airbus A310324 · Fuselage Main, Longeron/Stringer
  > 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.md): Beam · corroded · Dec 30, 2015 · N809FD · Airbus A310324 · Fuselage Main, Structure
  > 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 51-74-10. THE DAMAGE WAS OUT OF THE DESIGN THICKNESS TOLERANCE IAW DWG A57112070. REPLACED IAW SRM
- [SDR FDEA201512304105](https://openairdocs.org/sdr/FDEA201512304105.md): Stringer · corroded · Dec 30, 2015 · N809FD · Airbus A310324 · Fuselage Main, Longeron/Stringer
  > 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.md): Stringer Splice · corroded · Dec 30, 2015 · N809FD · Airbus A310324 · Fuselage Main, Longeron/Stringer
  > 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 6-2-100.
- [SDR FDEA201512264080](https://openairdocs.org/sdr/FDEA201512264080.md): Stringer · corroded · Dec 26, 2015 · N809FD · Airbus A310324 · Fuselage Main, Longeron/Stringer
  > EXISTING REPAIR ON FUSELAGE STRINGER 55 LT SIDE, BETWEEN FRAME 59 & 61 REQUIRES EVALUATION FOR CONFORMITY. THE EXISTING REPAIR WAS EVALUATED & CORROSION WAS FOUND AT THE REPAIR AREA. THE EXISTING SPLICE REPAIR WAS REMOVED & PERFORMED AGAIN IAW SRM 53-10-14 F
- [SDR FDEA201512013845](https://openairdocs.org/sdr/FDEA201512013845.md): Door · departed · Dec 1, 2015 · N809FD · Airbus A310324 · Service Doors
  > ON DEPARTURE, MAIN WW FWD LEFT & CENTER DOORS DEPARTED ACFT.
- [SDR FDEA201506231983](https://openairdocs.org/sdr/FDEA201506231983.md): Proximity Sensor · failed · Jun 23, 2015 · N809FD · Airbus A310324 · Landing Gear Position and Warning
  > 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.md): Sensor · failed · May 3, 2015 · N809FD · Airbus A310324 · Landing Gear Retraction/Extension System
  > 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 HEAT, MULTIPLE TIMES. THE JET THOUGHT IT WAS STILL ON THE GND. ALSO CABIN PRESSURE NR 1 FAULT. ALSO
- [SDR FDEA201405281215](https://openairdocs.org/sdr/FDEA201405281215.md): Support · corroded · May 28, 2014 · N809FD · Airbus A310324 · Wing, Landing Gear Attach Fittings
  > 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 5.
- [SDR FDEA201405281214](https://openairdocs.org/sdr/FDEA201405281214.md): Support · corroded · May 28, 2014 · N809FD · Airbus A310324 · Wing, Landing Gear Attach Fittings
  > 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 5.
- [SDR FDEA201311122736](https://openairdocs.org/sdr/FDEA201311122736.md): Skin · corroded · Nov 12, 2013 · N809FD · Airbus A310324 · Wing, Plate/Skin
  > 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 WAS CLASSIFIED AS MINOR IAW GMM 6-2-100.
- [SDR FDEA201311012663](https://openairdocs.org/sdr/FDEA201311012663.md): Beam · cracked · Nov 1, 2013 · N809FD · Airbus A310324 · Fuselage Main, Structure
  > 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 E6-5310-7-3314, PT3. DRILLED OUT AFFECTED FASTENER AND CUT OUT DAMAGE PORTION OF BEAM FLANGE. NDI WAS
- [SDR FDEA201310152506](https://openairdocs.org/sdr/FDEA201310152506.md): Limiter · tripped · Oct 15, 2013 · N809FD · Airbus A310324 · Trailing Edge Flap Control System
  > 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 TRIPPED. RESET LIMITER. INSPECTED RT WING FLAP TRANSMISSION TORQUE LIMITERS NOT TRIPPED. NR 1 SF
- [SDR FDEA201106062200](https://openairdocs.org/sdr/FDEA201106062200.md): Battery · inoperative · Jun 6, 2011 · N809FD · Airbus A310324 · Emergency Lighting
  > 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 UNIT 29WL1 BAD. R & R PWR SUPPLY MM 33-55-00-05. NO HELP, SUSPECT BATTERY. PREMATURE REMOVAL/I
- [SDR FDEA201105292020](https://openairdocs.org/sdr/FDEA201105292020.md): Skin · delaminated · May 29, 2011 · N809FD · Airbus A310324 · Rudder, Plate/Skin
  > 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 6-5540-150322.
- [SDR FDEA201105141841](https://openairdocs.org/sdr/FDEA201105141841.md): Stringer · corroded · May 14, 2011 · N809FD · Airbus A310324 · Fuselage Main, Longeron/Stringer
  > 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 RIGHT HAND STGR 31 STRINGER END CORRODED PART REMOVED AND REPALCED PER A310-300 SRM 51-40-21 AND SR
- [SDR FDEA201105141840](https://openairdocs.org/sdr/FDEA201105141840.md): Stringer · corroded · May 14, 2011 · N809FD · Airbus A310324 · Fuselage Main, Longeron/Stringer
  > FUSELAGE AFT PRESSURE BULKHEAD FORWARD FACE AT RIGHT HAND STGR28 FOUND STRINGER END TOP SURFACE WITH CORROSION FUSELAGE AFT PRESSURE BULKHEAD FORWARD FACE AT RIGH HAND STGR28 CORRODED STRINGER END REMOVED AND REPLACED GER SRM 51-40-21 AND 51-72-10 REV 79.
- [SDR FDEA201010194103](https://openairdocs.org/sdr/FDEA201010194103.md): Warning Message · false indication · Oct 19, 2010 · N809FD · Airbus A310324 · Central Warning
  > 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. ABORTED TAKEOFF, COMPLETED APPROPRIATE CHECKLISTS AND RETURNED TO BLOCKS. ACCOMPLISHED AFS/LAND TE
- [SDR FDEA201009303820](https://openairdocs.org/sdr/FDEA201009303820.md): Pickup · malfunctioned · Sep 30, 2010 · N809FD · Airbus A310324 · Trailing Flap Position Indicating System
  > 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 20 DEG -40 DEG. COMPLIED WITH QRH AND ECAM. REPLACED LT APPU 29CV PER AMM 27-56-11-04. PERFORMED O
- [SDR FDEA201009143386](https://openairdocs.org/sdr/FDEA201009143386.md): Jackscrew · damaged · Sep 14, 2010 · N809FD · Airbus A310324 · Trailing Edge Flap Control System
  > 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. RAN QRH AND LANDED AT SLAT/FLAPS 20/17. ALL HYD'S WERE GOOD. REPLACED NR 3 FLAP JACKSCREW IAW AMM
- [SDR 08FDEA04951](https://openairdocs.org/sdr/08FDEA04951.md): Frame · corroded · Nov 21, 2008 · N809FD · Airbus A310324 · Fuselage Main, Frame
  > 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. FOUND TO BE OUT OF LIMITS IAW SRM 53-10-00, FIG 105 AND TABLE 102. REMOVED THE FLANGE IAW SRM 51-40-
- [SDR 08FDEA04898](https://openairdocs.org/sdr/08FDEA04898.md): Floor Panel · cracked · Nov 17, 2008 · N809FD · Airbus A310324 · Fuselage Floor Panel
  > 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 NON-SKID TAPE & PART MARKED PANEL IAW FEDEX DWG SRX 25-005; REV "G".
- [SDR 08FDEA04897](https://openairdocs.org/sdr/08FDEA04897.md): Floor Panel · cracked · Nov 17, 2008 · N809FD · Airbus A310324 · Fuselage Floor Panel
  > 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 NON-SKID TAPE & PART MARKED PANEL IAW FEDEX DWG SRX 25-005; REV "G".
- [SDR 08FDEA04871](https://openairdocs.org/sdr/08FDEA04871.md): Floor Panel · delaminated · Nov 13, 2008 · N809FD · Airbus A310324 · Fuselage Floor Panel
  > 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.md): Fitting · cracked · Nov 12, 2008 · N809FD · Airbus A310324 · Cargo/Baggage Doors
  > 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 A5237807900000 IAW A310-300 SRM 51-72-10.
- [SDR 08FDEA04853](https://openairdocs.org/sdr/08FDEA04853.md): Floor Panel · damaged · Nov 11, 2008 · N809FD · Airbus A310324 · Fuselage Floor Panel
  > 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 25-005. PART MARKED IAW GMM 7-0-1000.
- [SDR 08FDEA04834](https://openairdocs.org/sdr/08FDEA04834.md): Failsafe · corroded · Nov 10, 2008 · N809FD · Airbus A310324 · Passenger/Crew Doors
  > 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 FROM SCUFF PLATE AREA & FAILSAFE RING IAW SRM 51-74-10. ALODINE AND PRIME ACCOMPLISHED ON W/C 41X5067A
- [SDR 08FDEA04833](https://openairdocs.org/sdr/08FDEA04833.md): Failsafe · corroded · Nov 10, 2008 · N809FD · Airbus A310324 · Passenger/Crew Doors
  > 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 ENTRY DOOR FRAME, FAILSAFE RING IAW SRM 53-18-12 FIG. 102 & 5140-47. ALODINE & PRIME APPLICATION REFE

Next page: https://openairdocs.org/deregistered/N809FD-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 = 'N809FD' AND deregistration_id = 'N809FD-2024-03-02'
ORDER BY difficulty_date DESC
```

This list as a web page: https://openairdocs.org/deregistered/N809FD-2024-03-02/reports

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