# Service difficulty reports: N443FE, cancelled Feb 3, 2024

A list on [N443FE, cancelled Feb 3, 2024](https://openairdocs.org/deregistered/N443FE-2024-02-03.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 · 124 reports

- [SDR FDEA201507202272](https://openairdocs.org/sdr/FDEA201507202272.md): Angle · corroded · Jul 20, 2015 · N443FE · Airbus A310203 · Passenger/Crew Doors
  > 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.md): Skin · cracked · May 30, 2013 · N443FE · Airbus A310203 · Cargo/Baggage Doors
  > AFT CARGO DOOR EXTERIOR SKIN FWD LOWER CORNER EDGE CRACKED. COMPLIED WITH EA6-5230-168203.
- [SDR FDEA201305301142](https://openairdocs.org/sdr/FDEA201305301142.md): Skin · corroded · May 30, 2013 · N443FE · Airbus A310203 · Fuselage Main, Plate/Skin
  > 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.md): Skin · corroded · May 30, 2013 · N443FE · Airbus A310203 · Fuselage Main, Plate/Skin
  > 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.md): Frame · damaged · May 22, 2013 · N443FE · Airbus A310203 · Fuselage Main, Frame
  > 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 7.26MM PRESENT, NO CRACK INDICATION. COMPLIED WITH EA6-5310-168229.
- [SDR FDEA201305221066](https://openairdocs.org/sdr/FDEA201305221066.md): Frame · damaged · May 22, 2013 · N443FE · Airbus A310203 · Fuselage Main, Frame
  > 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 9.92 WITH NO CRACK INDICATION. COMPLIED WITH EA6-5310-168229.
- [SDR FDEA201305221065](https://openairdocs.org/sdr/FDEA201305221065.md): Frame · damaged · May 22, 2013 · N443FE · Airbus A310203 · Fuselage Main, Frame
  > 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 THE FRAME FOOT, FRAME DOUBLER AND FRAME HOLE DIMENSION AT 9.92MM WITH NO CRACK INDICATION; HOLE
- [SDR FDEA201305221064](https://openairdocs.org/sdr/FDEA201305221064.md): Frame · damaged · May 22, 2013 · N443FE · Airbus A310203 · Fuselage Main, Frame
  > 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 DIMENSION AT 7.52MM PRESENT NO CRACK INDICATION. COMPLIED WITH EA6-5310-168229.
- [SDR FDEA201305221063](https://openairdocs.org/sdr/FDEA201305221063.md): Frame · cracked · May 22, 2013 · N443FE · Airbus A310203 · Fuselage Main, Frame
  > 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 DISTANCE IS 11.17 MM LESS THAN 12 MM REQUIRED IN THE SB53-2124. COMPLIED WITH EA 6-5310-168229
- [SDR FDEA201305211051](https://openairdocs.org/sdr/FDEA201305211051.md): Stringer · corroded · May 21, 2013 · N443FE · Airbus A310203 · Fuselage Main, Longeron/Stringer
  > 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 CUTOUT EDGES IAW SRM 53-10-14, FIG 201. MAKE REPAIR PROFILE AND REPAIR SPLICES IAW SRM 53-10-14, FI
- [SDR FDEA201305211050](https://openairdocs.org/sdr/FDEA201305211050.md): Stringer · corroded · May 21, 2013 · N443FE · Airbus A310203 · Fuselage Main, Longeron/Stringer
  > 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 53-10-14/201 PAR 4A, FIG 201. DRILL HOLES AND DEBURR REPAIR PARTS IAW SRM 53-10-14/201, PAR 4.A,
- [SDR FDEA201305171014](https://openairdocs.org/sdr/FDEA201305171014.md): Frame · damaged · May 17, 2013 · N443FE · Airbus A310203 · Fuselage Main, Frame
  > 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 SIDE). COMPLIED WITH EA6-5310-168229.
- [SDR FDEA201305171013](https://openairdocs.org/sdr/FDEA201305171013.md): Fitting · damaged · May 17, 2013 · N443FE · Airbus A310203 · Fuselage Main, Frame
  > 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) COMPLIED WITH EA6-5310-168229
- [SDR FDEA201305140981](https://openairdocs.org/sdr/FDEA201305140981.md): Stringer Splice · corroded · May 14, 2013 · N443FE · Airbus A310203 · Fuselage Main, Longeron/Stringer
  > 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.md): Frame · cracked · May 8, 2013 · N443FE · Airbus A310203 · Fuselage Main, Frame
  > 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). COMPLIED WITH EA6-5310-168229.
- [SDR FDEA201305080935](https://openairdocs.org/sdr/FDEA201305080935.md): Fitting · cracked · May 8, 2013 · N443FE · Airbus A310203 · Fuselage Miscellaneous Structure
  > 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).COMPLIED WITH EA6-5310-168229.
- [SDR FDEA201208233141](https://openairdocs.org/sdr/FDEA201208233141.md): Controller · failed · Aug 23, 2012 · N443FE · Airbus A310203 · Leading Edge Slat Control System
  > 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, SFCC1 - SLATS JAM - SEE TSM 27-80-02 (FIRST TIME OCCURANCE) THIS CHECKS DRIVE LINE AND COMPONENT
- [SDR FDEA201106192338](https://openairdocs.org/sdr/FDEA201106192338.md): Target · loose · Jun 19, 2011 · N443FE · Airbus A310203 · Landing Gear Position and Warning
  > 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 MINS, ALL PITCH TRIM AND LEVERS TRIPPED OFF AND WOULD NOT RESET, UNTIL AFTER LANDING. T/S FOUND
- [SDR FDEA201103171055](https://openairdocs.org/sdr/FDEA201103171055.md): Skin · corroded · Mar 17, 2011 · N443FE · Airbus A310203 · Wing, Plate/Skin
  > 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.md): Skin · corroded · Mar 17, 2011 · N443FE · Airbus A310203 · Fuselage Main, Plate/Skin
  > 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 BETWEEN STR 5L AND STR 6L IAW EA,6-5310-145562 FUSELAGE -FR87 SKIN.
- [SDR FDEA201103171053](https://openairdocs.org/sdr/FDEA201103171053.md): Stiffener · corroded · Mar 17, 2011 · N443FE · Airbus A310203 · Fuselage Miscellaneous Structure
  > 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 SERVICING BOX CUTOUT INTERIOR FR12-12A STR36L TO STR43L IAW SRM 51-72-10, PGS 1-3.
- [SDR FDEA201103171052](https://openairdocs.org/sdr/FDEA201103171052.md): Support Fitting · corroded · Mar 17, 2011 · N443FE · Airbus A310203 · Vertical Stabilizer
  > 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 HINGE SUPPORT FITTING AT REAR SPAR RIB 13 IAW A310 SRM 51-72-10, PGS 1-3.
- [SDR FDEA201103171051](https://openairdocs.org/sdr/FDEA201103171051.md): Stringer · corroded · Mar 17, 2011 · N443FE · Airbus A310203 · Fuselage Main, Longeron/Stringer
  > 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 FR87 AFT SIDE IAW SRM 51-72-10, PGS 1-3.
- [SDR FDEA201103130952](https://openairdocs.org/sdr/FDEA201103130952.md): Skin · corroded · Mar 13, 2011 · N443FE · Airbus A310203 · Fuselage Main, Plate/Skin
  > 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 LIMITS FOUND TO BE OUT OF LIMITS IAW SRM 53-19-10, FIG 102. FABRICATED STRAP JOINT IAW DWG A539
- [SDR FDEA201103040844](https://openairdocs.org/sdr/FDEA201103040844.md): Angle · corroded · Mar 4, 2011 · N443FE · Airbus A310203 · Fuselage Miscellaneous Structure
  > 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 51-74-10. MATERIAL LOSS WAS 100 PERCENT OF ANGLE AT FR 12A AND STR 37L, FOUND TO BE OUT OF LIMITS IAW
- [SDR FDEA201101060041](https://openairdocs.org/sdr/FDEA201101060041.md): Skin · corroded · Jan 6, 2011 · N443FE · Airbus A310203 · Fuselage Main, Plate/Skin
  > 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 FOUND TO BE OUT OF LIMITS IAW SRM 53-19- 12 FIG 102 PAR 5. REPAIRED AREA WITH INTERNAL DOUBLER AND F
- [SDR FDEA201101060045](https://openairdocs.org/sdr/FDEA201101060045.md): Spar · cracked · Jan 6, 2011 · N443FE · Airbus A310203 · Vertical Stabilizer, Spar/Rib
  > 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 1 IAW SRM 51-72-10 PG 1-3. CLEANED AREA IAW AMM 12-21-11. REPROTECTED AREA IAW SRM 51-75-10 PG 3
- [SDR FDEA201101060044](https://openairdocs.org/sdr/FDEA201101060044.md): Skin · corroded · Jan 6, 2011 · N443FE · Airbus A310203 · Fuselage Main, Plate/Skin
  > 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 FURTHER INSPECTION NO CORROSION FOUND. REPROTECTED AREA IAW SRM 51-21-10 PG 2 PARA 2 AND 51-75-10
- [SDR FDEA201101060043](https://openairdocs.org/sdr/FDEA201101060043.md): Skin · scratched · Jan 6, 2011 · N443FE · Airbus A310203 · Fuselage Main, Plate/Skin
  > 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 LIMITS BEFORE 0.197, AFTER 0.0191, LOSS 0.006 WHICH IS WITHIN LIMITS IAW SRM 53-19-12 FIG 102 PARA 5.
- [SDR FDEA201101060042](https://openairdocs.org/sdr/FDEA201101060042.md): Skin · dented · Jan 6, 2011 · N443FE · Airbus A310203 · Fuselage Main, Plate/Skin
  > 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 SKIN SURFACE DENTS IAW SRM 51-73-10 PG 209 PARA F DEEPEST BEFORE 0.197 AFTER 0.191, LOSS 0.006.
- [SDR FDEA201101060039](https://openairdocs.org/sdr/FDEA201101060039.md): Bracket · broken · Jan 6, 2011 · N443FE · Airbus A310203 · Fuselage Main, Attach Fittings
  > 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 AT FR 79 AND STR 4R IAW SRM 51-72-10, PG 1-3 AND SRM 51-40-21, PARA 7, PG 24-55.
- [SDR FDEA201101060038](https://openairdocs.org/sdr/FDEA201101060038.md): Skin · corroded · Jan 6, 2011 · N443FE · Airbus A310203 · Fuselage Main, Plate/Skin
  > 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 12-21-12. UPON FURTHER INSP, NO CORROSION NOTED. REPROTECTED AREA IAW SRM 51-75-10, PG 225, PARA 10
- [SDR FDEA201101060037](https://openairdocs.org/sdr/FDEA201101060037.md): Finger Doubler · gouged · Jan 6, 2011 · N443FE · Airbus A310203 · Fuselage Main, Plate/Skin
  > 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 LENGTH APPROX. BLENDED GOUGE ON TAIL SECTION 7" AFT OF FR 87 BETWEEN STR 4R AND STR 5R IAW SRM 51-73
- [SDR FDEA201101060036](https://openairdocs.org/sdr/FDEA201101060036.md): Finger Doubler · gouged · Jan 6, 2011 · N443FE · Airbus A310203 · Fuselage Main, Plate/Skin
  > 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 LENGTH APPROX. BLENDED GOUGE ON FUSELAGE TAIL SECTION 7" AFT OF FR 87 BETWEEN STR 4L AND 5L IAW SRM
- [SDR FDEA201101060035](https://openairdocs.org/sdr/FDEA201101060035.md): Skin · corroded · Jan 6, 2011 · N443FE · Airbus A310203 · Fuselage Main, Plate/Skin
  > 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 AND FR 86 AND STR 5R AND 6R IAW AMM 12-21-12. AFTER FURTHER INSP, NO CORROSION NOTED. REPROTECTED
- [SDR FDEA201101060034](https://openairdocs.org/sdr/FDEA201101060034.md): Skin · corroded · Jan 6, 2011 · N443FE · Airbus A310203 · Fuselage Main, Plate/Skin
  > 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 AT FR 85, STR 5 R AND STR 6 R IAW AMM 12-21-12. UPON FURTHER INSP, NO CORROSION FOUND. REPROTECTE
- [SDR FDEA201101060033](https://openairdocs.org/sdr/FDEA201101060033.md): Skin · corroded · Jan 6, 2011 · N443FE · Airbus A310203 · Fuselage Main, Plate/Skin
  > 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 BETWEEN FR 85 AND FR 86 BETWEEN STR 5L AND 6L IAW AMM 12-21-12. UPON FURTHER INSPECTION NO CORROSION
- [SDR FDEA201101060032](https://openairdocs.org/sdr/FDEA201101060032.md): Skin · corroded · Jan 6, 2011 · N443FE · Airbus A310203 · Fuselage Main, Plate/Skin
  > 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 BETWEEN STR5L AND STR6L IAW EA 6-5310-145562.
- [SDR FDEA201101060031](https://openairdocs.org/sdr/FDEA201101060031.md): Fitting · corroded · Jan 6, 2011 · N443FE · Airbus A310203 · Vertical Stabilizer, Attach Fittings
  > 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.md): Fitting · corroded · Jan 6, 2011 · N443FE · Airbus A310203 · Vertical Stabilizer, Attach Fittings
  > 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.md): Fitting · corroded · Jan 6, 2011 · N443FE · Airbus A310203 · Vertical Stabilizer, Attach Fittings
  > 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.md): Fitting · corroded · Jan 6, 2011 · N443FE · Airbus A310203 · Vertical Stabilizer
  > 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 6-5530-145557.
- [SDR FDEA201101060027](https://openairdocs.org/sdr/FDEA201101060027.md): Structure · corroded · Jan 6, 2011 · N443FE · Airbus A310203 · Vertical Stabilizer
  > 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 WITH EA 6-5530-145551.
- [SDR FDEA201101060026](https://openairdocs.org/sdr/FDEA201101060026.md): Structure · corroded · Jan 6, 2011 · N443FE · Airbus A310203 · Vertical Stabilizer
  > 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.md): Angle · corroded · Jan 6, 2011 · N443FE · Airbus A310203 · Vertical Stabilizer, Spar/Rib
  > 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 PARA 7. REMOVED CORROSION IAW SRM 51-74-10, PG 205, PARA 3. NOMINAL THICKNESS IS 0.063, REMAIN
- [SDR FDEA201101060024](https://openairdocs.org/sdr/FDEA201101060024.md): Stiffener · corroded · Jan 6, 2011 · N443FE · Airbus A310203 · Vertical Stabilizer Miscellaneous Structure
  > 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 BETWEEN RIB 9 AND 10 AT VERT STAB REAR SPAR. REMOVED CORROSION ON HORIZ STIFFNER, NOMINAL 0.050, RE
- [SDR FDEA201101060023](https://openairdocs.org/sdr/FDEA201101060023.md): Rib · corroded · Jan 6, 2011 · N443FE · Airbus A310203 · Vertical Stabilizer, Spar/Rib
  > 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 VERTICAL STABILIZER IAW SRM 51-72-10, PG 1-3. REMOVED CORROSION IAW SRM 51-76-10, PG 205, PARA 6.
- [SDR FDEA201101060022](https://openairdocs.org/sdr/FDEA201101060022.md): Fitting · corroded · Jan 6, 2011 · N443FE · Airbus A310203 · Vertical Stabilizer
  > 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 SPAR IAW SRM 51-74-10, PG 5. BEFORE THICKNESS 0.557, AFTER 0.448. LOSS OF 0.069 IS OUT OF LIMITS IAW
- [SDR FDEA201101060021](https://openairdocs.org/sdr/FDEA201101060021.md): Plate · corroded · Jan 6, 2011 · N443FE · Airbus A310203 · Vertical Stabilizer
  > 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. COMPLIED WITH EA 6-5530-145557.
- [SDR FDEA201101050016](https://openairdocs.org/sdr/FDEA201101050016.md): Plate · corroded · Jan 5, 2011 · N443FE · Airbus A310203 · Vertical Stabilizer
  > 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 VERTICAL STAB RIB 1AFT LOWER PLATE IAW SRM 51-72-10, PGS 1-3.

Next page: https://openairdocs.org/deregistered/N443FE-2024-02-03/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 = 'N443FE' AND deregistration_id = 'N443FE-2024-02-03'
ORDER BY difficulty_date DESC
```

This list as a web page: https://openairdocs.org/deregistered/N443FE-2024-02-03/reports

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