# N443FE: 1984 Airbus Industrie A310-203, registration cancelled 2024-02-03

- Type: Cancelled registration (FAA registry, deregistered aircraft)
- Cancelled: February 3, 2024
- Status when cancelled: Valid registration
- Airframe: [Airbus Industrie A310-203](https://openairdocs.org/model/airbus-industrie-a310-203) (registry code 3930313)
- Engine: [GE CF6-80 series](https://openairdocs.org/engine/ge-cf6-80-series) (registry code 30025)
- Data sheets: [TCDS A35EU](https://openairdocs.org/tcds/A35EU), [TCDS E13NE](https://openairdocs.org/tcds/E13NE) (OpenAirDocs)
- Serial number: 283
- Year built: 1984
- Type of aircraft: Fixed wing multi engine
- Engine type: Turbo-fan
- Airworthiness: Standard, transport
- Airworthiness date: July 24, 1998
- Certificate issued: February 17, 1998
- Last registry action: August 25, 2023
- Mode S code: A55644
- Owner when cancelled: [Federal Express Corporation](https://openairdocs.org/faa-owner/FEDERAL%20EXPRESS%20CORPORATION)
- 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/N443FE
- FAA registry: https://registry.faa.gov/AircraftInquiry/Search/NNumberResult?nNumberTxt=443FE
- Page: https://openairdocs.org/deregistered/N443FE-2024-02-03

From the FAA registry file of November 3, 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 A310-203: https://openairdocs.org/model/airbus-industrie-a310-203.md

## Service difficulty reports (124, newest 50)

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

- [SDR FDEA201507202272](https://openairdocs.org/sdr/FDEA201507202272), Jul 20, 2015: ANGLE. CORRODED. AFT UPPER CORNER OF L1 ENTRY DOOR CORNER ANGLE CORRODED. FABRICATED IAW EA 6-5210-T0318924 AND INSTALLED IAW SRM 51-40-20.
- [SDR FDEA201305301143](https://openairdocs.org/sdr/FDEA201305301143), May 30, 2013: SKIN. CRACKED. AFT CARGO DOOR EXTERIOR SKIN FWD LOWER CORNER EDGE CRACKED. COMPLIED WITH EA6-5230-168203.
- [SDR FDEA201305301142](https://openairdocs.org/sdr/FDEA201305301142), May 30, 2013: SKIN. CORRODED. REAR FUSELAGE SKIN LOWER HORIZONTAL STAB CUTOUT BETWEEN FR 87-89, S27-31R FOUND CORRODED. COMPLED WITH EA6-5330-168201.
- [SDR FDEA201305301141](https://openairdocs.org/sdr/FDEA201305301141), May 30, 2013: SKIN. CORRODED. REAR FUSELAGE SKIN LOWER HORIZONTAL STAB CUTOUT BETWEEN FR 87-89, S27-31 LT FOUND CORRODED. COMPLIED WITH EA6-5330-168201.
- [SDR FDEA201305221067](https://openairdocs.org/sdr/FDEA201305221067), May 22, 2013: FRAME. DAMAGED. CENTER FUSELAGE FRAME 46 RT SIDE HOLE H25 AND H27: IN THE FRAME FOOT, FRAME REINFORCING, FRAME HOLE DIMENSION AT 9.92MM PRESENT NO CRACK INDICATION, STRAP AT 7.
- [SDR FDEA201305221066](https://openairdocs.org/sdr/FDEA201305221066), May 22, 2013: FRAME. DAMAGED. CENTER FUSELAGE FRAME 45, RT SIDE HOLE H22: IN THE FRAME FOOT AND FRAME DOUBLER HOLE DIMENSION AT 14MM WITH NO CRACK INDICATION, IN THE FRAME HOLE DIMENSION AT 
- [SDR FDEA201305221065](https://openairdocs.org/sdr/FDEA201305221065), May 22, 2013: FRAME. DAMAGED. CENTER FUSELAGE FRAME 45, LT HOLE H15: IN THE FRAME FOOT, FRAME DOUBLER, FRAME AND BRACKET FR45 HOLE DIMENSION AT 9.92 MM WITH NO CRACK INDICATION; HOLE H22: IN
- [SDR FDEA201305221064](https://openairdocs.org/sdr/FDEA201305221064), May 22, 2013: FRAME. DAMAGED. CENTER FUSELAGE FRAME 44 RT HOLE H12 AND H13 DIMENSION AT 8.73MM PRESENT NO CRACK INDICATION, HOLE H10 DIMENSION AT 6.76MM PRESENT NO CRACK INDICATION, HOLE H11
- [SDR FDEA201305221063](https://openairdocs.org/sdr/FDEA201305221063), May 22, 2013: FRAME. CRACKED. CENTER FUSELAE FRAME 44 LT SIDE HOLE H5 WITH NO CRACK INDICATION & HOLE DIMENSION IS 19MM, AND FRAME 44 LT SIDE HOLE H13 WITH SHORT EDGE DISTANCE, HOLE H13 EDGE
- [SDR FDEA201305211051](https://openairdocs.org/sdr/FDEA201305211051), May 21, 2013: STRINGER. CORRODED. BULK CARGO STRINGER 55 RT CORRODED FR 65-66. CUT DAMAGE STRINGER & DEBURR SHAPE EDGES OF CUTOUT IAW SRM 53-10-14, FIG 201. APPLY WASH PRIMER & PRIMER TO THE CUT
- [SDR FDEA201305211050](https://openairdocs.org/sdr/FDEA201305211050), May 21, 2013: STRINGER. CORRODED. BULK CARGO STRINGER 56R CORRODED FR 65-66. CUT DAMAGE STRINGER & DEBURR SHAPE EDGES OF CUTOUT IAW SRM 53-10-14/201, PAR 4.A, FIG 201. MAKE REPAIR PARTS IAW SRM 
- [SDR FDEA201305171014](https://openairdocs.org/sdr/FDEA201305171014), May 17, 2013: FRAME. DAMAGED. CENTER FUSELAGE, THE UPPER FRAME 45 BASE-TO-ARCHES JUNCTION FOUND HOLE NR 22 WITH CRACK SIGNAL AND THE CRACK IS ELIMINATED WHEN THE HOLE DIMENSION IS 0.551" (RT
- [SDR FDEA201305171013](https://openairdocs.org/sdr/FDEA201305171013), May 17, 2013: FITTING. DAMAGED. CENTER FUSELAGE UPPER FRAME 44 BASE-TO-ARCHES JUNCTION FOUND HOLE NR 5 WITH CRACK SIGNAL AND THE CRACK IS ELIMINATED WHEN THE HOLE DIMENSION IS 0.472". (LT SIDE
- [SDR FDEA201305140981](https://openairdocs.org/sdr/FDEA201305140981), May 14, 2013: STRINGER SPLICE. CORRODED. BULK CARGO STRINGER SPLICE CORRODED, LOCATED AT FR65,STGR43 LT 1. REMOVED AND REPLACED CORRODED SPLICE IAW SRM 51-40-21. REPAIRED IAW SRM51-40-44.
- [SDR FDEA201305080936](https://openairdocs.org/sdr/FDEA201305080936), May 8, 2013: FRAME. CRACKED. CERNTER FUSELAGE UPPER FRAME 43 BASES-TO-ARCHES JUNCTION ROTAING PROBE INSPECTION FOUND HOLE NR 2 WITH CRACK SIGNAL & THE HOLE DIMESION IS 0.313" (RT SIDE). COM
- [SDR FDEA201305080935](https://openairdocs.org/sdr/FDEA201305080935), May 8, 2013: FITTING. CRACKED. CENTER FUSELAGE, UPPER FRAME 43 BASES-TO-ARCHES JUNCTION ROTATING PROBE INSPECTION FOUND HOLE NR 2 WITH CRACK SIGNAL & THE HOLE DIMESION IS 0.313" (LT SIDE).COM
- [SDR FDEA201208233141](https://openairdocs.org/sdr/FDEA201208233141), Aug 23, 2012: CONTROLLER. FAILED. SLATS FAILED TO EXTEND ON APPROACH. CHECKED NR 1 AND NR 2 SFCCS. NR 1 SFCC FAULTS JAM, NR 2 SFCC FAULTS LT RETRACT SWITCH. ADDED MPN 49-079-05 QTY 2 EA CG, SFCC
- [SDR FDEA201106192338](https://openairdocs.org/sdr/FDEA201106192338), Jun 19, 2011: TARGET. LOOSE. AFTER TAKEOFF, GEAR LEVER WOULD NOT GO PAST NEUTRAL. SWITCHED FROM SYS 1 TO SYS 2 WITH SAME RESULT. ALL 3 LANDING GEAR REMAINED DOWN AND LOCKED. AFTER APPROX 2 
- [SDR FDEA201103171055](https://openairdocs.org/sdr/FDEA201103171055), Mar 17, 2011: SKIN. CORRODED. CORROSION FOUND AT LT WING UPPER SKIN AT FUEL PORT AND UNDER GROUND POINT. COMPLIED WITH E.A. 6-5730-145575 WINGS - LT OVERWING.
- [SDR FDEA201103171054](https://openairdocs.org/sdr/FDEA201103171054), Mar 17, 2011: SKIN. CORRODED. FUSELAGE TAIL SECTION EXTERNAL SKIN AT FR87, BETWEEN STR5L AND 6L, CORROSION ON SPLICE PLATE, ABOUT 4 SQUARE INCHES. REPAIRED FUSELAGE EXTERIOR SKIN AT FR87 BET
- [SDR FDEA201103171053](https://openairdocs.org/sdr/FDEA201103171053), Mar 17, 2011: STIFFENER. CORRODED. CORROSION AT LOWER END OF WASTE WATER SERVICING BOX BETWEEN PAN AND FUSELAGE SKIN. LT FUSELAGE BETWEEN FRAMES 12 AND 12A. R & R SKIN STIFFENER AT WASTE WATER SE
- [SDR FDEA201103171052](https://openairdocs.org/sdr/FDEA201103171052), Mar 17, 2011: SUPPORT FITTING. CORRODED. VERTICAL STABILIZER INTERIOR, RUDDER HINGE NR 4 SUPPORT FITTING AT REAR SPAR, RIB-13 HAS CORROSION ON BOTTOM EDGE , ABOUT 10 SQUARE INCHES. R & R NR 4 RUDDER HI
- [SDR FDEA201103171051](https://openairdocs.org/sdr/FDEA201103171051), Mar 17, 2011: STRINGER. CORRODED. AFT FUSELAGE, INTERNAL, RT STRINGER 4 END FITTING AT AFT SIDE OF FRAME 87 HAS SEVERE EXFOLIATION CORROSION APPROX 1 SQUARE INCH. R & R STR 4R END FITTING AT FR8
- [SDR FDEA201103130952](https://openairdocs.org/sdr/FDEA201103130952), Mar 13, 2011: SKIN. CORRODED. FUSELAGE TAIL SECTION FR 87 BETWEEN STR 2R AND 3R CORROSION. (SURFACE) ON SPLICE PLATE, ABOUT 4 SQ INCHES. REMOVED LEVEL 1 CORROSION IAW SRM 51-74-10 , CHECKED 
- [SDR FDEA201103040844](https://openairdocs.org/sdr/FDEA201103040844), Mar 4, 2011: ANGLE. CORRODED. UPON REMOVAL OF LAV SERVICE BOX AND SKIN STIFFENERS, FOUND EXCESSIVE CORROSION EXTENDING UNDER FR 12A LT AT STR 37L. REMOVED LEVEL ONE CORROSION IAW SRM 51-74-1
- [SDR FDEA201101060041](https://openairdocs.org/sdr/FDEA201101060041), Jan 6, 2011: SKIN. CORRODED. FUSELAGE TAIL SECTION EXTERNAL SKIN HAS SURFACE CORROSION AT FWD OF FR 78,BETWEEN STR 2LT AND STR 3LT,ABOUT 8 SQ INCHES. CORROSION AT FUSELAGE EXTERNAL SKIN FOU
- [SDR FDEA201101060045](https://openairdocs.org/sdr/FDEA201101060045), Jan 6, 2011: SPAR. CRACKED. CRACK AT FRONT SPAR CONNECTING SECTION AT RIB 1,2.5 INCH LONG. REMOVED TRANSVERSE FITTING AT VERTICAL STAB FWD SPAR RIB 1 AND REMOVED CONNECTION SECTION AT RIB 
- [SDR FDEA201101060044](https://openairdocs.org/sdr/FDEA201101060044), Jan 6, 2011: SKIN. CORRODED. FUSELAGE TAIL SECTION EXTERNAL SKIN HAS SURFACE CORROSION AT FR 87, STR 5LT, ABOUT 3 SQ INCHES. CLEANED FUSELAGE TAIL SEC EXTERNAL SKIN IAW AMM 12-21-12. UPON F
- [SDR FDEA201101060043](https://openairdocs.org/sdr/FDEA201101060043), Jan 6, 2011: SKIN. SCRATCHED. FUSELAGE TAIL SECTION EXTERIOR SKIN IS SCUFFED AT 4 INCHES FWD OF FR 80/82 BETWEEN S2-3R. BLENDED AREA TO A SMOOTH CONTOUR IAW SRM 51-73-10 PG 209. CHECKED LIMI
- [SDR FDEA201101060042](https://openairdocs.org/sdr/FDEA201101060042), Jan 6, 2011: SKIN. DENTED. FUSELAGE TAIL SECTION EXTERNAL SKIN HAS DINGS ON SURFACE AT 4 INCHES AFT OF FR 87, BETWEEN RIB 2LT AND RIB 3LT ABOUT 4 SQ INCHES. BLENDED FUSELAGE TAIL SECTION 
- [SDR FDEA201101060039](https://openairdocs.org/sdr/FDEA201101060039), Jan 6, 2011: BRACKET. BROKEN. FUSELAGE TAIL SECTION EXTERIOR GAIRING SUPPORT BRACKET BROKEN OFF AT 5 INCHES AFT OF FR 79, STR 4 RT. R & R MOUNTING BRACKET AT FUSELAGE TAIL SECTION EXTERIOR A
- [SDR FDEA201101060038](https://openairdocs.org/sdr/FDEA201101060038), Jan 6, 2011: SKIN. CORRODED. FUSELAGE TAIL SECTION STR 5RT AFT OF FR 83, EXTERNAL SKIN HAS CORROSION ABOUT 4 SQ INCHES. CLEANED AREA OF FUSELAGE TAIL SECTION STR 5R AFT OF FR 83 IAW AMM 12-
- [SDR FDEA201101060037](https://openairdocs.org/sdr/FDEA201101060037), Jan 6, 2011: FINGER DOUBLER. GOUGED. FUSELAGE TAIL SECTION, 7 INCHES AFT OF FR 87, BETWEEN STR 5RT AND STR 4RT, FUSELAGE FINGER DOUBLER HAS A GOUGE, 0.010 INCH DEPTH X 0.25 INCH WIDTH X 0.25 INCH L
- [SDR FDEA201101060036](https://openairdocs.org/sdr/FDEA201101060036), Jan 6, 2011: FINGER DOUBLER. GOUGED. FUSELAGE TAIL SECTION 7 INCHES AFT OF FR 87 BETWEEN STR 4 LT AND STR 5 LT FUSELAGE SKIN FINGER DOUBLER HAS A GOUGE, .010 IN DEPTH X 0.25 INCH WIDTH X 0.25 INCH 
- [SDR FDEA201101060035](https://openairdocs.org/sdr/FDEA201101060035), Jan 6, 2011: SKIN. CORRODED. FUSELAGE TAIL SECTION EXTERNAL FUSELAGE SKIN HAS SURFACE CORROSION AT FR 84, STR 5 LT ABOUT 7 SQ INCHES. CLEANED FUSELAGE TAIL SEC EXTERNAL SKIN BETWEEN FR 85 A
- [SDR FDEA201101060034](https://openairdocs.org/sdr/FDEA201101060034), Jan 6, 2011: SKIN. CORRODED. FUSELAGE TAIL SECTION EXTERNAL SKIN HAS SURFACE CORROSION AT FR 85 BETWEEN STR 5 RT AND STR 6 RT ABOUT 5 SQ INCHES. CLEANED FUSELAGE TAIL SECTION EXTERNAL SKIN 
- [SDR FDEA201101060033](https://openairdocs.org/sdr/FDEA201101060033), Jan 6, 2011: SKIN. CORRODED. FUSELAGE TAIL SECTION EXTERNAL SKIN HAS SURFACE CORROSION BETWEEN FR 85 AND FR 86, BETWEEN STR 5 LT AND STR 6 LT. CLEANED FUSELAGE TAIL SECTION EXTERNAL SKIN BE
- [SDR FDEA201101060032](https://openairdocs.org/sdr/FDEA201101060032), Jan 6, 2011: SKIN. CORRODED. FUSELAGE TAIL SECTION EXTERNAL SKIN AT FR 87 BETWEEN STR 5LT AND STR 6LT, CORROSION ON SPLICE PLATE ABOUT 4 SQ INCHES. REPAIRED FUSELAGE EXTERIOR SKIN AT FR87 B
- [SDR FDEA201101060031](https://openairdocs.org/sdr/FDEA201101060031), Jan 6, 2011: FITTING. CORRODED. VERTICAL STABILIZER LT AFT FITTING HAS CORROSION ON OTBD FACE, 2 LOCALIZED AREAS ABOUT 3 SQ INCHES. REMOVED LEVEL 1 CORROSION, COMPLIED WITH EA 6-5530-145557.
- [SDR FDEA201101060030](https://openairdocs.org/sdr/FDEA201101060030), Jan 6, 2011: FITTING. CORRODED. VERTICAL STABILIZER RT AFT MOUNT FITTING HAS CORROSION ON OTBD FACE ABOUT 10 SQ INCHES. REMOVED LEVEL 1 CORROSION, COMPLIED WITH EA 6-5530-145557.
- [SDR FDEA201101060029](https://openairdocs.org/sdr/FDEA201101060029), Jan 6, 2011: FITTING. CORRODED. VERTICAL STABILIZER RT CTR MOUNT FITTING HAS CORROSION OTBD SURFACE ABOUT 8 SQ INCHES. REMOVED LEVEL 1 CORROSION, COMPLIED WITH EA 6-5530-145557.
- [SDR FDEA201101060028](https://openairdocs.org/sdr/FDEA201101060028), Jan 6, 2011: FITTING. CORRODED. VERTICAL STABILIZER RT FWD MOUNT FITTING OUTER FACE HAS CORROSION JUST AT SKIN EDGE AREA ABOUT 0.5 SQ INCHES. REMOVED LEVEL 1 CORROSION, COMPLIED WITH EA 6-5530
- [SDR FDEA201101060027](https://openairdocs.org/sdr/FDEA201101060027), Jan 6, 2011: STRUCTURE. CORRODED. VERTICAL STABILIZER RT CHORD BETWEEN RIB 18 AND RIB 25 HAS SURFACE CORROSION AROUND NUTPLATES, 3 PLACES, APPROX 3 SQ INCHES. REMOVED LEVEL 1 CORROSION, COMPLIED
- [SDR FDEA201101060026](https://openairdocs.org/sdr/FDEA201101060026), Jan 6, 2011: STRUCTURE. CORRODED. VERTICAL STABILIZER REAR SPAR LT CHORD, RIB 10 TO RIB 16 HAS CORROSION AT 11 EA NUT PLATES LOCATIONS. REMOVED LEVEL 1 CORROSION, COMPLIED WITH EA 6-5530-145551.
- [SDR FDEA201101060025](https://openairdocs.org/sdr/FDEA201101060025), Jan 6, 2011: ANGLE. CORRODED. VERTICAL STABILIZER REAR SPAR FWD FACE RIB 9, HORIZ ANGLE HAS CORROSION ABOUT 3 SQ INCHES. REMOVED HORIZONTAL ANGLE AT FWD FACE OF RIB 9 IAW SRM 51-40-21, PG 22
- [SDR FDEA201101060024](https://openairdocs.org/sdr/FDEA201101060024), Jan 6, 2011: STIFFENER. CORRODED. VERTICAL STABILIZER INTERIOR REAR SPAR HORIZ STIFFENER BETWEEN RIB 9 AND RIB 10 HAS CORROSION ABOUT 3 SQ INCHES. REMOVED HORIZ STIFFNER AND DIAGONAL STIFFNER BE
- [SDR FDEA201101060023](https://openairdocs.org/sdr/FDEA201101060023), Jan 6, 2011: RIB. CORRODED. VERTICAL STABILIZER INTERIOR DIAGONAL ANGLE AT RT JOINT OF RIB 9 AND STR 2 HAS CORROSION ABOUT 4 SQ INCHES. REMOVED DIAGONAL BRACE AT RIB 10 AND REAR SPAR ON VE
- [SDR FDEA201101060022](https://openairdocs.org/sdr/FDEA201101060022), Jan 6, 2011: FITTING. CORRODED. UPON REMOVAL OF LOWER WEB AT VERTICAL STAB FOUND CORROSION ON AFT FITTING AT LT ATTACH POINT. REMOVED CORROSION ON AFT TRAVERSE FITTING ON VERT STAB AT REAR SPA
- [SDR FDEA201101060021](https://openairdocs.org/sdr/FDEA201101060021), Jan 6, 2011: PLATE. CORRODED. VERTICAL STABILIZER RIB 1, STRINGER 2LT TO 5LT, REAR LOWER PLATE LOWER SURFACE CORRODED APPROX 2 IN WIDE X 4 IN LENGTH JUST ABOVE LT AFT STABILZER HINGE. COMPLI
- [SDR FDEA201101050016](https://openairdocs.org/sdr/FDEA201101050016), Jan 5, 2011: PLATE. CORRODED. VERTICAL STABILIZER, RIB 1, STRINGER 2RT - 5RT REAR LOWER PLATE. LOWER SURFACE CORRODED APPROX 1IN WIDE X 2IN LENGTH JUST ABOVE RT AFT STABILIZER HINGE. R & R V

All 124: https://openairdocs.org/deregistered/N443FE-2024-02-03/reports.md

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