N443FE, cancelled Feb 3, 2024

Service difficulty reports · 124

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

Query with SQL
duckdb -csv -c "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"

Prints the whole list as CSV. It reads the release’s Parquet files over HTTPS, so there’s nothing to download first. Install DuckDB to run it.

SDR FDEA201507202272Angle · corrodedAFT UPPER CORNER OF L1 ENTRY DOOR CORNER ANGLE CORRODED. FABRICATED IAW EA 6-5210-T0318924 AND INSTALLED IAW SRM 51-40-20.Jul 20, 2015 · N443FE · Airbus A310203 · Passenger/Crew DoorsSDR FDEA201305301143Skin · crackedAFT CARGO DOOR EXTERIOR SKIN FWD LOWER CORNER EDGE CRACKED. COMPLIED WITH EA6-5230-168203.May 30, 2013 · N443FE · Airbus A310203 · Cargo/Baggage DoorsSDR FDEA201305301142Skin · corrodedREAR FUSELAGE SKIN LOWER HORIZONTAL STAB CUTOUT BETWEEN FR 87-89, S27-31R FOUND CORRODED. COMPLED WITH EA6-5330-168201.May 30, 2013 · N443FE · Airbus A310203 · Fuselage Main, Plate/SkinSDR FDEA201305301141Skin · corrodedREAR FUSELAGE SKIN LOWER HORIZONTAL STAB CUTOUT BETWEEN FR 87-89, S27-31 LT FOUND CORRODED. COMPLIED WITH EA6-5330-168201.May 30, 2013 · N443FE · Airbus A310203 · Fuselage Main, Plate/SkinSDR FDEA201305221067Frame · damagedCENTER 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.May 22, 2013 · N443FE · Airbus A310203 · Fuselage Main, FrameSDR FDEA201305221066Frame · damagedCENTER 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.May 22, 2013 · N443FE · Airbus A310203 · Fuselage Main, FrameSDR FDEA201305221065Frame · damagedCENTER 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; HOLEMay 22, 2013 · N443FE · Airbus A310203 · Fuselage Main, FrameSDR FDEA201305221064Frame · damagedCENTER 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.May 22, 2013 · N443FE · Airbus A310203 · Fuselage Main, FrameSDR FDEA201305221063Frame · crackedCENTER 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 6-5310-168229May 22, 2013 · N443FE · Airbus A310203 · Fuselage Main, FrameSDR FDEA201305211051Stringer · corrodedBULK 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, FIMay 21, 2013 · N443FE · Airbus A310203 · Fuselage Main, Longeron/StringerSDR FDEA201305211050Stringer · corrodedBULK 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, May 21, 2013 · N443FE · Airbus A310203 · Fuselage Main, Longeron/StringerSDR FDEA201305171014Frame · damagedCENTER 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.May 17, 2013 · N443FE · Airbus A310203 · Fuselage Main, FrameSDR FDEA201305171013Fitting · damagedCENTER 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 EA6-5310-168229May 17, 2013 · N443FE · Airbus A310203 · Fuselage Main, FrameSDR FDEA201305140981Stringer Splice · corrodedBULK 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.May 14, 2013 · N443FE · Airbus A310203 · Fuselage Main, Longeron/StringerSDR FDEA201305080936Frame · crackedCERNTER 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.May 8, 2013 · N443FE · Airbus A310203 · Fuselage Main, FrameSDR FDEA201305080935Fitting · crackedCENTER 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.May 8, 2013 · N443FE · Airbus A310203 · Fuselage Miscellaneous StructureSDR FDEA201208233141Controller · failedSLATS 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 COMPONENTAug 23, 2012 · N443FE · Airbus A310203 · Leading Edge Slat Control SystemSDR FDEA201106192338Target · looseAFTER 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 FOUNDJun 19, 2011 · N443FE · Airbus A310203 · Landing Gear Position and WarningSDR FDEA201103171055Skin · corrodedCORROSION FOUND AT LT WING UPPER SKIN AT FUEL PORT AND UNDER GROUND POINT. COMPLIED WITH E.A. 6-5730-145575 WINGS - LT OVERWING.Mar 17, 2011 · N443FE · Airbus A310203 · Wing, Plate/SkinSDR FDEA201103171054Skin · corrodedFUSELAGE 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.Mar 17, 2011 · N443FE · Airbus A310203 · Fuselage Main, Plate/SkinSDR FDEA201103171053Stiffener · corrodedCORROSION 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.Mar 17, 2011 · N443FE · Airbus A310203 · Fuselage Miscellaneous StructureSDR FDEA201103171052Support Fitting · corrodedVERTICAL 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.Mar 17, 2011 · N443FE · Airbus A310203 · Vertical StabilizerSDR FDEA201103171051Stringer · corrodedAFT 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.Mar 17, 2011 · N443FE · Airbus A310203 · Fuselage Main, Longeron/StringerSDR FDEA201103130952Skin · corrodedFUSELAGE 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 A539Mar 13, 2011 · N443FE · Airbus A310203 · Fuselage Main, Plate/SkinSDR FDEA201103040844Angle · corrodedUPON 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 Mar 4, 2011 · N443FE · Airbus A310203 · Fuselage Miscellaneous StructureSDR FDEA201101060041Skin · corrodedFUSELAGE 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 FJan 6, 2011 · N443FE · Airbus A310203 · Fuselage Main, Plate/SkinSDR FDEA201101060045Spar · crackedCRACK 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 3Jan 6, 2011 · N443FE · Airbus A310203 · Vertical Stabilizer, Spar/RibSDR FDEA201101060044Skin · corrodedFUSELAGE 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 Jan 6, 2011 · N443FE · Airbus A310203 · Fuselage Main, Plate/SkinSDR FDEA201101060043Skin · scratchedFUSELAGE 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.Jan 6, 2011 · N443FE · Airbus A310203 · Fuselage Main, Plate/SkinSDR FDEA201101060042Skin · dentedFUSELAGE 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. Jan 6, 2011 · N443FE · Airbus A310203 · Fuselage Main, Plate/SkinSDR FDEA201101060039Bracket · brokenFUSELAGE 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.Jan 6, 2011 · N443FE · Airbus A310203 · Fuselage Main, Attach FittingsSDR FDEA201101060038Skin · corrodedFUSELAGE 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 10Jan 6, 2011 · N443FE · Airbus A310203 · Fuselage Main, Plate/SkinSDR FDEA201101060037Finger Doubler · gougedFUSELAGE 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 51-73Jan 6, 2011 · N443FE · Airbus A310203 · Fuselage Main, Plate/SkinSDR FDEA201101060036Finger Doubler · gougedFUSELAGE 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 SRMJan 6, 2011 · N443FE · Airbus A310203 · Fuselage Main, Plate/SkinSDR FDEA201101060035Skin · corrodedFUSELAGE 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. REPROTECTEDJan 6, 2011 · N443FE · Airbus A310203 · Fuselage Main, Plate/SkinSDR FDEA201101060034Skin · corrodedFUSELAGE 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. REPROTECTEJan 6, 2011 · N443FE · Airbus A310203 · Fuselage Main, Plate/SkinSDR FDEA201101060033Skin · corrodedFUSELAGE 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 CORROSIONJan 6, 2011 · N443FE · Airbus A310203 · Fuselage Main, Plate/SkinSDR FDEA201101060032Skin · corrodedFUSELAGE 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.Jan 6, 2011 · N443FE · Airbus A310203 · Fuselage Main, Plate/SkinSDR FDEA201101060031Fitting · corrodedVERTICAL 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.Jan 6, 2011 · N443FE · Airbus A310203 · Vertical Stabilizer, Attach FittingsSDR FDEA201101060030Fitting · corrodedVERTICAL STABILIZER RT AFT MOUNT FITTING HAS CORROSION ON OTBD FACE ABOUT 10 SQ INCHES. REMOVED LEVEL 1 CORROSION, COMPLIED WITH EA 6-5530-145557.Jan 6, 2011 · N443FE · Airbus A310203 · Vertical Stabilizer, Attach FittingsSDR FDEA201101060029Fitting · corrodedVERTICAL STABILIZER RT CTR MOUNT FITTING HAS CORROSION OTBD SURFACE ABOUT 8 SQ INCHES. REMOVED LEVEL 1 CORROSION, COMPLIED WITH EA 6-5530-145557.Jan 6, 2011 · N443FE · Airbus A310203 · Vertical Stabilizer, Attach FittingsSDR FDEA201101060028Fitting · corrodedVERTICAL 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.Jan 6, 2011 · N443FE · Airbus A310203 · Vertical StabilizerSDR FDEA201101060027Structure · corrodedVERTICAL 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.Jan 6, 2011 · N443FE · Airbus A310203 · Vertical StabilizerSDR FDEA201101060026Structure · corrodedVERTICAL 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.Jan 6, 2011 · N443FE · Airbus A310203 · Vertical StabilizerSDR FDEA201101060025Angle · corrodedVERTICAL 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, REMAINJan 6, 2011 · N443FE · Airbus A310203 · Vertical Stabilizer, Spar/RibSDR FDEA201101060024Stiffener · corrodedVERTICAL 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, REJan 6, 2011 · N443FE · Airbus A310203 · Vertical Stabilizer Miscellaneous StructureSDR FDEA201101060023Rib · corrodedVERTICAL 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. Jan 6, 2011 · N443FE · Airbus A310203 · Vertical Stabilizer, Spar/RibSDR FDEA201101060022Fitting · corrodedUPON 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 IAWJan 6, 2011 · N443FE · Airbus A310203 · Vertical StabilizerSDR FDEA201101060021Plate · corrodedVERTICAL 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.Jan 6, 2011 · N443FE · Airbus A310203 · Vertical StabilizerSDR FDEA201101050016Plate · corrodedVERTICAL 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.Jan 5, 2011 · N443FE · Airbus A310203 · Vertical Stabilizer
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