N643FE

Service difficulty reports · 351

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 = 'N643FE' AND registry_match = 'registration'
  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 FDEA201108293547Hinge Bracket · corrodedRT WING OTBD FLAP INBD HINGE (WING SIDE) WING STA XW 486.403, LOWER MOUNT OTBD HOLE FOUND CORRODED HOLE EXCEEDED CMM 57-44-08 LIMITS ARC 0502-14. REPAIR BUSHING FABRICATED AND INSTALLED IAW EA NR 1-5750-154210, & EO 1-5750-7-5002. REPAIR CLASSIFIED AS MAJOR Aug 29, 2011 · N643FE · Doug MD11F · Wing, Control Surface Attach FittingsSDR FDEA201108293548Spar Cap · corrodedRT WING REAR SPAR CAP FOUND CORRODED. EXCEEDED LIMITS AT XORS 1040. CORROSION REMOVED IAW SRM 51-21-01 REV 47. ORIGINAL MATERIAL THICKNESS = 0.148"; MATERIAL, REMOVED = 0.034"; MATERIAL REMAINED = 0.114" - FOUND EXCEEDED LIMIT IAW SRM 57-00-00, REV 47, FIGAug 29, 2011 · N643FE · Doug MD11F · Wing SparSDR FDEA201108293546Longeron · corrodedLONGERON 19R BS 1219-1239. FOUND CORRODED. CORROSION REMOVED IAW SRM 51-21-01, REV 47. MATERIAL ORIGINAL THICKNESS = 0.100 INCH; MATERIAL REMOVED= 0.037 IN; MATERIAL REMAINED = 0.063 IN FOUND EXCEEDED LIMIT IAW SRM 53-00-00, REV 47, FIGURE 205. ACCOMPLISHAug 29, 2011 · N643FE · Doug MD11F · Fuselage Miscellaneous StructureSDR FDEA201108293545Longeron · corrodedLONGERON 16L BS 1199-1219 CORRODED. CORROSION EXCEEDED SRM LIMITS IAW SRM 53-00-00 REV 47, FIG 205. LONGERON REMOVED IAW SRM 51-31-01, REV 47. NEW LONGERON FABRICATED IAW DWG AEA7063, REV G AND INSTALLED SRM 51-31-01, REV 47. REPAIR CLASSIFIED AS MAJOR Aug 29, 2011 · N643FE · Doug MD11F · Fuselage Main, Longeron/StringerSDR FDEA201108293544Longeron · corrodedLONGERON 16L BS 1179-1199 CORRODED. CORROSION REMOVED IAW SRM 51-21-01, REV 47. ORGINAL THICKNESS = 0.125"; MATERIAL REMOVED = 0.065"; MATERIAL REMAINED = 0.060 INCH, FOUND EXEEDED LIMIT IAW SRM 53-00-00, REV 47, FIG 205. NEW LONGERON FABRICATED IAW DWG AAug 29, 2011 · N643FE · Doug MD11F · Fuselage Main, Longeron/StringerSDR FDEA201108293543Longeron · corrodedLONGERON 16L, BS 1179-1199 CORROSION EXCEEDED SRM LIMITS. NEW LONGERON FABRICATED IAW DWG AEA7065, REV B AND INSTALLED IAW SRM 51-31-01, REV 47. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 112.Aug 29, 2011 · N643FE · Doug MD11F · Fuselage Main, Longeron/StringerSDR FDEA201108293542Skin · crackedLT WING FIXED L/E LOWER SURFACE AT OTBD SLAT MECHANISM ACCESS DOOR 518FB STA, XOS 542. FWD CORNER FOUND SKIN WITH 1.0" CRACK. REPAIRED IAW SRM 57-40-02 REV 47, FIG 201, REPAIR 7. REPAIR CLASSIFIED AS MINOR IAW GMM 6-2-100, REV 113.Aug 29, 2011 · N643FE · Doug MD11F · Wing, Plate/SkinSDR FDEA201108293541Seat Track · corrodedMAIN DECK - CORROSION ON SEAT TRACK FLANGE AT STA 5-0 TO STA 5-53, X =75. CORROSION REMOVED IAW SRM 51-21-01, REV 47. ORIGINAL THICKNESS =0.080"; MATERIAL REMOVED =0.040"; MATERIAL REMAINED = 0.040", FOUND EXCEEDED SRM 53-00-52, REV 47, FIG 101 LIMITS. CORRAug 29, 2011 · N643FE · Doug MD11F · Fuselage, Seat/Cargo Attach FittingsSDR FDEA201108293540Seat Track · corrodedCORROSION ON SEAT TRACK FLANGE AT STA 1159 TO STA 1219, X =107. CORROSION REMOVED IAW SRM 51-21-01, REV 47. ORIGINAL THICKNESS = 0.080"; MATERIAL REMOVED = 0.038"; MATERIAL REMAINED =0.042", FOUND EXCEEDED SRM 53-00-52, REV 47, FIG 101 LIMITS. CORRODED SECAug 29, 2011 · N643FE · Doug MD11F · Fuselage, Seat/Cargo Attach FittingsSDR FDEA201108263512Longeron · corrodedCENTER CARGO COMPARTMENT STA 5-83 TO STA 5-93, RT LONGERON NR33R CORRODED. LONGERON REMOVED IAW SRM 51-21-01, REV 47. ORIGINAL MATERIAL THICKNESS= 0.060"; MATERIAL REMOVED = 0.040"; MATERIAL REMAINED = 0.030" - FOUND EXCEEDED LIMITS IAW SRM 53-00-00 REV 47, Aug 26, 2011 · N643FE · Doug MD11F · Fuselage Main, Longeron/StringerSDR FDEA201108263511Access Door · crackedRT WING FIXED L/E LOWER SURFACE AT REFUELING ACCESS DOOR INBD SIDE AREA FOUND WITH 1.2" CRACKED. CRACK TRIMMED OUT IAW SRM 57-40-02, REV 47, FIG 201, REPAIR 7. REPAIR FILLER AND DOUBLER FABRICATED AND INSTALLED IAW SRM 57-40-02, REV 47, FIG 201, REPAIR 7. RAug 26, 2011 · N643FE · Doug MD11F · Wing, Plate/SkinSDR FDEA201108253477Longeron · corrodedCORROSION ON LONGERON 12R AT BS 1239-1299. CORROSION REMOVED IAW SRM 51-21-01, REV 47. ORIGINAL THICKNESS = 0.173 INCH; MATERIAL REMOVED = 0.055 IN; MATERIAL REMAINED = 0.118 IN AND FOUND EXCEEDED LIMITS SRM 53-22-00, REV 47, FIG 205. LONGERON SECTION REMOVAug 25, 2011 · N643FE · Doug MD11F · Fuselage Main, Longeron/StringerSDR FDEA201108253476Longeron · corrodedLONGERON 18R, STA 1481-1501 FOUND CORRODED. CORROSION REMOVED IAW SRM 51-21-01 REV 47 AND FOUND CRACKED. NEW LONGERON FABRICATED IAW DWG AEA0220, REV R. CRACKED LONGERON R & R SRM 51-31-01, REV 47. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 112.Aug 25, 2011 · N643FE · Doug MD11F · Fuselage Miscellaneous StructureSDR FDEA201108253474Doubler · crackedCENTER WHEEL WELL RT SIDE FWD SPOILER MIXER CONTROL ROD CUT-OUT DOUBLER FOUND CRACKED. DOUBLER REMOVED IAW SRM 51-31-01, REV 47. NEW DOUBLER FABRICATED IAW DWG AEA0526 AND INSTALLED IAW SRM 51-33-01, REV 47. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 1Aug 25, 2011 · N643FE · Doug MD11F · Fuselage Main, StructureSDR FDEA201108253473Doubler · crackedCENTER WHEEL WELL, LT SIDE FWD SPOILER MIXER CONTROL ROD CUT-OUT DOUBLER FOUND CRACKED. REMOVED DOUBLER IAW SRM 51-31-01, REV 47. NEW DOUBLER FABRICATED IAW DWG AEA0526 AND INSTALLED IAW SRM 51-33-01, REV 47. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100,Aug 25, 2011 · N643FE · Doug MD11F · Fuselage Main, StructureSDR FDEA20110823341AWindow Frame · corrodedCOCKPIT- L2 SLIDING WINDOW CUT-OUT AT LOWER AFT FRAME SUPPORT FOUND CORRODED FOUND CORROSION EXCEEDED SRM LIMITS. COMPLIED WITH EA 1-5320-149869. REPAIR CLASSIFIED AS MINOR IAW GMM 6-2-100, REV 113.Aug 23, 2011 · N643FE · Doug MD11F · Fuselage Main, StructureSDR FDEA201108233422Longeron · corrodedLONGERON 16R STA 1361 TO 1381 FOUND WITH CORROSION. CORROSION REMOVED SRM 51-21-01, REV 47. ORGINAL THICKNESS = 0.100 INCH; MATERIAL REMOVED = 0.050 INCH; MATERIAL REMAINED = 0.050 INCH, FOUND EXEEDED LIMIT IAW SRM 53-00-00 REV 47, FIGURE 205. LONGERON SAug 23, 2011 · N643FE · Doug MD11F · Fuselage Main, Longeron/StringerSDR FDEA201108233421Longeron · corrodedLONGERON 25R BS 1381-1401. FOUND WITH CORROSION. REMOVED SRM 51-21-01, REV 47. ORIGINAL THICKNESS =0.100 INCH; MATERIAL REMOVED = 0.060 IN; MATERIAL REMAINED = 0.040 IN, AND FOUND EXCEEDED LIMITS IAW SRM 53-00-00, REV 47, FIG 205. NEW LONGERON FABRICATED Aug 23, 2011 · N643FE · Doug MD11F · Fuselage Miscellaneous StructureSDR FDEA201108233419Longeron · corrodedLONGERON 20R STA 1401 TO STA 1421 FOUND WITH CORROSION. REMOVED IAW SRM 51-21-01, REV 47. ORIGINAL THICKNESS = 0.080 INCH; MATERIAL REMOVED = 0.040 IN; MATERIAL REMAINED = 0.040 IN, AND FOUND EXCEEDED LIMITS IAW SRM 53-00-00, REV 47, FIG 205. NEW LONGERON Aug 23, 2011 · N643FE · Doug MD11F · Fuselage Main, Longeron/StringerSDR FDEA201108233417Seat Track · corrodedCORROSION ON SEAT TRACK FLANGE AT STA 6-30 TO 6-100 1661, X = 27.5. CORROSION REMOVED IAW SRM 51-21-01, REV 47. ORIGINAL THICKNESS = 0.080"; MATERIAL REMOVED = 0.045"; MATERIAL REMAINED = 0.035", FOUND EXCEEDED SRM 53-00-52, REV 47, FIG 101 LIMITS. CORRAug 23, 2011 · N643FE · Doug MD11F · Fuselage, Seat/Cargo Attach FittingsSDR FDEA201108233416Seat Track · corrodedCORROSION ON SEAT TRACK FLANGE AT STA 1561 TO 1661, X = -75, EXCEEDED SRM LIMITS.Aug 23, 2011 · N643FE · Doug MD11F · Fuselage, Seat/Cargo Attach FittingsSDR FDEA201108233415Seat Track · corrodedCORROSION ON SEAT TRACK FLANGE AT STA 1561 TO 1661, X = -75. CORROSION REMOVED IAW SRM 51-21-01, REV 47. ORIGINAL THICKNESS = 0.080"; MATERIAL REMOVED = 0.045"; MATERIAL REMAINED = 0.035", FOUND EXCEEDED SRM 53-00-52, REV 47, FIG 101 LIMITS. CORRODED SECAug 23, 2011 · N643FE · Doug MD11F · Fuselage, Seat/Cargo Attach FittingsSDR FDEA201108233413Floor Support · corrodedFLOOR SUPPORT AT RT STA 595, X = -75.25 CORRODED BEYOND SRM LIMITS. CORROSION REMOVED IAW SRM 51-21-01, REV 47. MATERIAL ORIGINAL THICKNESS = 0.075"; MATERIAL REMOVED = 0.050"; MATERIAL REMAINED = 0.025" FOUND EXCEEDED LIMIT IAW SRM 53-00-00, REV 47, FIG 20Aug 23, 2011 · N643FE · Doug MD11F · Fuselage Miscellaneous StructureSDR FDEA201108193381Longeron · corrodedCENTER CARGO COMPARTMENT - ALONG LEFT STA 1722 LONGERON 46L, FOUND CORRODED. CORROSION REMOVED IAW SRM 51-21-01, REV 47. ORIGINAL MATERIAL THICKNESS = 0.100 INCH; MATERIAL REMOVED = 0.090"; MATERIAL REMAINED = 0.010" - FOUND EXCEEDED LIMIT IAW SRM 53-00-Aug 19, 2011 · N643FE · Doug MD11F · Fuselage Main, Longeron/StringerSDR FDEA201108193380Seat Track · corrodedCORROSION ON SEAT TRACK AT RT STA 595 TO 615, X = -107.25 EXCEEDED SRM LIMITS. CORROSION REMOVED IAW SRM 51-21-01, REV 47. ORIGINAL THICKNESS = 0.080 INCH; MATERIAL REMOVED = 0.060 INCH; MATERIAL REMAINED = 0.020 INCH FOUND EXCEEDED LIMITS IAW SRM 53-00-Aug 19, 2011 · N643FE · Doug MD11F · Fuselage, Seat/Cargo Attach FittingsSDR FDEA201108193379Finger Doubler · crackedLEFT WING L/E COMPARTMENT FROM ST XORS 506 TO STA XORS 545 FOUND SEVERAL LOCATION OF FINGER DOUBLER WITH 0.375 INCH CRACKS. FINGER DOUBLER TRIMMED-OUT IAW SRM 57-40-02, REV 47, FIG 203. REPAIR 9. FILLERS DOUBLERS AND ANGLES FABRICATED AND INSTALLED IAW SRM Aug 19, 2011 · N643FE · Doug MD11F · Wing, Plate/SkinSDR FDEA201108193378Finger Doubler · crackedLEFT WING L/E COMPARTMENT AT STA XORS 595 FOUND FINGER DOUBLER WITH 0.375 INCH CRACK. TRIMMED-OUT AND REPAIR CARRIED-OUT SRM 57-40-02, REV 47, FIG 203, REPAIR 9. CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 113.Aug 19, 2011 · N643FE · Doug MD11F · Wing, Plate/SkinSDR FDEA201108193377Finger Doubler · crackedLT WING L/E COMPARTMENT AT STA XORS 665 FINGER FOUND DOUBLER WITH 0.375 INCH CRACKED. REPAIR CARRIED-OUT IAW SRM 57-40-02, REV 47, FIG 203 REPAIR 9. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100 REV 113.Aug 19, 2011 · N643FE · Doug MD11F · Wing, Plate/SkinSDR FDEA201108193376Finger Doubler · crackedLT WING L/E COMPARTMENT AT STA XORS 625 FINGER DOUBLER FOUND WITH A 0.375 INCH CRACK. FINGER DOUBLER TRIMMED-OUT AND REPAIR CARRIED-OUT IAW SRM 57-40-02, REV 47, FIGURE 203, REPAIR 9. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 113.Aug 19, 2011 · N643FE · Doug MD11F · Wing, Plate/SkinSDR FDEA201108183339Seat Track · corrodedCORROSION ON SEAT TRACK FLANGE AT STA 1159 - 1219, X = 75. CORROSION REMOVED IAW SRM 51-21-01, REV 47. ORIGINAL THICKNESS = 0.080 INCH; MATERIAL REMOVED = 0.045 INCH; MATERIAL REMAINED = 0.035 INCH, FOUND EXCEEDED SRM 53-00-52, REV 47, FIG 101 LIMITS. SEAAug 18, 2011 · N643FE · Doug MD11F · Fuselage, Seat/Cargo Attach FittingsSDR FDEA201108183358Seat Track · corrodedCORROSION ON SEAT TRACK FLANGE AT STA 1561 TO 1621, X = 107. CORROSION REMOVED IAW SRM 51-21-01, REV 47. ORIGINAL THICKNESS = 0.080"; MATERIAL REMOVED = 0.045"; MATERIAL REMAINED = 0.035", FOUND EXCEEDED SRM 53-00-52, REV 47, FIG 101 LIMITS. CORRODED SECAug 18, 2011 · N643FE · Doug MD11F · Fuselage, Seat/Cargo Attach FittingsSDR FDEA201108183357Seat Track · corrodedCORROSION ON SEAT TRACK FLANGE AT STA 1461 TO 5.0, X = 107. CORROSION REMOVED IAW SRM 51-21-01, REV 47. ORIGINAL THICKNESS=0.080 INCH; MATERIAL REMOVED=0.050 INCH; MATERIAL REMAINED =0.030 INCH, FOUND EXCEEDED SRM 53-00-52, REV 47, FIG 101 LIMITS. CORRODAug 18, 2011 · N643FE · Doug MD11F · Fuselage, Seat/Cargo Attach FittingsSDR FDEA201108183355Seat Track · corrodedCORROSION ON SEAT TRACK FLANGE AT STA 1761 TO 1821, X = -8. CORROSION REMOVED IAW SRM 51-21-01, REV 47. ORIGINAL THICKNESS=0.080"; MATERIAL REMOVED=0.045"; MATERIAL REMAINED=0.035 INCH, FOUND EXCEEDED SRM 53-00-52, REV 47, FIG 101 LIMITS. CORRODED SECTIONAug 18, 2011 · N643FE · Doug MD11F · Fuselage, Seat/Cargo Attach FittingsSDR FDEA201108183354Seat Track · corrodedCORROSION ON SEAT TRACK FLANGE AT STA 5-53 TO 1531, X = -8. CORROSION REMOVED IAW SRM 51-21-01, REV 47. ORIGINAL THICKNESS = 0.080"; MATERIAL REMOVED = 0.052"; MATERIAL REMAINED = 0.028", FOUND EXCEEDED SRM 53-00-52, REV 47, FIG 101 LIMITS. CORRODED SECAug 18, 2011 · N643FE · Doug MD11F · Fuselage, Seat/Cargo Attach FittingsSDR FDEA201108183353Seat Track · corrodedCORROSION ON SEAT TRACK FLANGE AT STA 5-32 TO 5-53, X = 8. CORROSION REMOVED IAW SRM 51-21-01, REV 47. ORIGINAL THICKNESS = 0.080"; MATERIAL REMOVED = 0.020"; MATERIAL REMAINED = 0.060", FOUND EXCEEDED SRM 53-00-52, REV 47, FIG 101 LIMITS. CORRODED SECAug 18, 2011 · N643FE · Doug MD11F · Fuselage, Seat/Cargo Attach FittingsSDR FDEA201108183350Seat Track · corrodedCORROSION ON SEAT TRACK FLANGE AT STA 1821 TO 1887, X = 75. CORROSION REMOVED IAW SRM 51-21-01, REV 47. ORIGINAL THICKNESS = 0.080 INCH; MATERIAL REMOVED = 0.050 INCH; MATERIAL REMAINED = 0.050", FOUND EXCEEDED SRM 53-00-52, REV 47, FIG 101 LIMITS. CORRAug 18, 2011 · N643FE · Doug MD11F · Fuselage, Seat/Cargo Attach FittingsSDR FDEA201108183349Skin · crackedLT WING FIXED L/E NR 3 SLAT TELESCOPIC DUCT CUT-OUT AREA FOUND CRACKED APPROX 0.250" SKIN. REPAIR FABRICATED IAW SRM 57-40-01, REV 47 AND INSTALLED IAW SRM 57-40-01, REV 47, FIGURE 201, REPAIR 10. REPAIR CLASSIFIED AS MINOR IAW GMM 6-2-100, REV 113.Aug 18, 2011 · N643FE · Doug MD11F · Wing, Plate/SkinSDR FDEA201108183348Seat Track · corrodedCORROSION ON SEAT TRACK FLANGE AT STA 1561 TO 1661, X = -8. CORROSION REMOVED IAW SRM 51-21-01, REV 47. ORIGINAL THICKNESS = 0.080 INCH; MATERIAL REMOVED = 0.045 INCH; MATERIAL REMAINED = 0.035 INCH, FOUND EXCEEDED SRM 53-00-52, REV 47, FIG 101 LIMITS. CAug 18, 2011 · N643FE · Doug MD11F · Fuselage, Seat/Cargo Attach FittingsSDR FDEA201108183347Seat Track · corrodedCORROSION ON SEAT TRACK FLANGE AT STA 1561 TO 1661, X = 8. CORROSION REMOVED IAW SRM 51-21-01, REV 47. ORIGINAL THICKNESS = 0.080"; MATERIAL REMOVED = 0.045"; MATERIAL REMAINED = 0.035 INCH, FOUND EXCEEDED SRM 53-00-52 REV 47, FIG 101LIMITS. SEAT TRACK SAug 18, 2011 · N643FE · Doug MD11F · Fuselage, Seat/Cargo Attach FittingsSDR FDEA201108183346Rib · crackedLT WING L/E COMPARTMENT AT NR 16 SLAT TRACK AREA INBD SUPPORT RIB SUSPECTED CRACKED APPROX 0.187 INCH. R & R IAW SRM 51-31-01, REV 47. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 113.Aug 18, 2011 · N643FE · Doug MD11F · Wing, Rib/BulkheadSDR FDEA201108183344Seat Track · corrodedCORROSION ON SEAT TRACK FLANGE AT STA 5.0 TO 5-53, X =107 EXCEEDED SRM LIMITS. CORROSION REMOVED IAW SRM 51-21-01, REV 47. ORIGINAL THICKNESS = 0.080 INCH; MATERIAL REMOVED =0.050 INCH; MATERIAL REMAINED = 0.030 INCH FOUND EXCEEDED LIMITS IAW SRM 53-00-52,Aug 18, 2011 · N643FE · Doug MD11F · Fuselage, Seat/Cargo Attach FittingsSDR FDEA201108183343Seat Track · corrodedCORROSION ON SEAT TRACK FLANGE AT STA 1441, 5.0, X = 75. CORROSION REMOVED IAW SRM 51-21-01, REV 47. ORIGINAL THICKNESS = 0.080"; MATERIAL REMOVED = 0.045"; MATERIAL REMAINED = 0.035 INCH, FOUND EXCEEDED SRM 53-00-52, REV 47, FIG 101 LIMITS. CORRODED SAug 18, 2011 · N643FE · Doug MD11F · Fuselage, Seat/Cargo Attach FittingsSDR FDEA201108183342Seat Track · corrodedCORROSION ON SEAT TRACK FLANGE AT STA 1361 TO 1401, X = 75. CORROSION REMOVED IAW SRM 51-21-01, REV 47. ORIGINAL THICKNESS = 0.080 INCH; MATERIAL REMOVED = 0.035 INCH; MATERIAL REMAINED = 0.045 INCH, FOUND EXCEEDED IAW SRM 53-00-52, REV 47, FIG 101 LIMIAug 18, 2011 · N643FE · Doug MD11F · Fuselage, Seat/Cargo Attach FittingsSDR FDEA201108183341Seat Track · corrodedSEAT TRACK AT MAIN DECK STA 1229 TO 1331, X = 27.5 LT, FOUND WITH CORROSION THAT EXCEEDED SRM LIMITS. CORRODED AREA REMOVED: MATERIAL THICKNESS = 0.0890 INCH, MATERIAL REMOVED = 0.040", MATERIAL REMAINED = 0.040". EXCEEDED LIMITS IAW SRM 53-02-52, REV 47, Aug 18, 2011 · N643FE · Doug MD11F · Fuselage, Seat/Cargo Attach FittingsSDR FDEA201108183340Seat Track · corrodedSEAT TRACK AT MAIN DECK STA 1229 TO 1331, X = -8.5 RT, FOUND WITH CORROSION THAT EXCEEDED SRM LIMITS AEA7325-23. CORRODED AREA REMOVED: MATERIAL THICKNESS = 0.080 INCH, MATERIAL REMOVED = 0.040 INCH, MATERIAL REMAINED = 0.040 INCH. EXCEEDED LIMITS IAW SRM Aug 18, 2011 · N643FE · Doug MD11F · Fuselage, Seat/Cargo Attach FittingsSDR FDEA201108183338Skin · crackedRT WING TELESCOPIC DUCT CUT-OUT FOUND CRACKED SKIN. REMOVED IAW AMM 27-80-30-4, REV 70.1. EXTERNAL REPAIR DOUBLER AND REPAIR FILLER FABRICATED IAW SRM 57-40-01, REV 47 AND INSTALLED IAW SRM 57-40-01, REV 47, FIG 201. RT WING L/E NR 3 SLAT ASSY RE-INSTALLEDAug 18, 2011 · N643FE · Doug MD11F · Wing, Plate/SkinSDR FDEA201108183335Seat Track · corrodedSEAT TRACK AT MAIN DECK STA 1331 TO 1531, X = -8.5 RT. FOUND WITH CORROSION THAT EXCEEDED SRM LIMITS. CORRODED AREA REMOVED, ORIGINAL THICKNESS = 0.080 INCH; MATERIAL REMOVED = 0.055 INCH; MATERIAL REMAINED = 0.025 INCH AND EXCEEDED LIMITS IAW SRM 53-00-5Aug 18, 2011 · N643FE · Doug MD11F · Fuselage, Seat/Cargo Attach FittingsSDR FDEA201108183333Seat Track · corrodedSEAT TRACK AT MAIN DECK STA 1331 TO 1531, X = 8.5 LT FOUND WITH CORRODED. CORROSION REMOVED, ORIGINAL THICKNESS = 0.080"; MATERIAL REMOVED = 0.045"; MATERIAL REMAINED = 0.035" AND EXCEEDED LIMITS IAW SRM 53-00-52, REV 47, FIG 101. NEW SEAT TRACK REPAIR Aug 18, 2011 · N643FE · Doug MD11F · Fuselage, Seat/Cargo Attach FittingsSDR FDEA201108183331Seat Track · corrodedSEAT TRACK AT MAIN DECK BS 745 TO 1119, X = -8.5 RT FOUND CORRODED. CORROSION REMOVED, ORIGINAL THICKNESS = 0.100 INCH; MATERIAL REMOVED = 0.050"; MATERIAL REMAINED = 0.050" AND EXCEEDED LIMITS IAW SRM 53-00-52, REV 47, FIG 101. NEW SEAT TRACK REPAIR CARRIAug 18, 2011 · N643FE · Doug MD11F · Fuselage, Seat/Cargo Attach FittingsSDR FDEA201108183330Seat Track · corrodedSEAT TRACK AT MAIN DECK STA 1831 TO 1887, X = 8.5 LT FLANGE. CORROSION REMOVED, ORIGINAL THICKNESS = 0.080"; MATERIAL REMOVED = 0.040"; MATERIAL REMAINED = 0.040" AND EXCEEDED LIMITS IAW SRM 53-00-52, REV 47, FIG 101. REPAIR CARRIED OUT IAW SRM 53-00-52, RAug 18, 2011 · N643FE · Doug MD11F · Fuselage, Seat/Cargo Attach Fittings
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