N643FE

Service difficulty reports · 350

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 FDEA201110014244Panel · corrodedCOROSION ON CTR WING AUX TANK TOP PANEL SURFACE AT STA 1239 TO STA 1256, X =98 TO X =107. CORROSION REMOVED AS PER SRM 51-21-01 REV 47. ORIGINAL MATERIAL THICKNESS = 0.247 INCH; MATERIAL REMOVED = 0.017 INCH; MATERIAL REMAINED = 0.230 INCH - FOUND EXCEEDED LIOct 1, 2011 · N643FE · Doug MD11F · Fuel StorageSDR FDEA201110014243Panel · corrodedCOROSION ON CTR WING AUX TANK TOP PANEL SURFACE AT STA 1256 TO 1273, X =98 TO X =107. COROSION REMOVED AS PER SRM 51-21-01 REV 47. ORIGINAL MATERIAL THICKNESS = 0.285 INCH; MATERIAL REMOVED = 0.045 INCH; MATERIAL REMAINED = 0.240 INCH - FOUND EXCEEDED LIMIT AOct 1, 2011 · N643FE · Doug MD11F · Fuel StorageSDR FDEA201110014240Panel · corrodedCOROSION ON CTR WING AUX TANK TOP PANEL SURFACE AT STA 1219 TO 1239, X = 47.5 TO X =75. COROSION REMOVED AS PER SRM 51-21-01 REV 47. ORIGINAL MATERIAL THICKNESS = 0.172 INCH; MATERIAL REMOVED = 0.027 INCH; MATERIAL REMAINED = 0.145 INCH - FOUND EXCEEDED LIMITOct 1, 2011 · N643FE · Doug MD11F · Fuel StorageSDR FDEA201110014239Panel · corrodedCOROSION ON CENTER WING AUX TANK TOP PANEL SURFACE AT STA 1219 TO 1239, X = 27.5 TO X = 47.5. COROSION REMOVED AS PER SRM 51-21-01 REV 47. ORIGINAL MATERIAL THICKNESS = 0.172 INCH; MATERIAL REMOVED = 0.043 INCH; MATERIAL REMAINED = 0.129 INCH - FOUND EXCEEDEOct 1, 2011 · N643FE · Doug MD11F · Fuel StorageSDR FDEA201110014238Panel · corrodedCOROSION ON CENTER WING AUX TANK TOP PANEL SURFACE AT BS 1219 TO 1239, X = 8 TO X = 27.7. COROSION REMOVED AS PER SRM 51-21-01 REV 47. ORIGINAL MATERIAL THICKNESS = 0.172 INCH; MATERIAL REMOVED = 0.052 INCH; MATERIAL REMAINED = 0.120 INCH - FOUND EXCEEDED LIMOct 1, 2011 · N643FE · Doug MD11F · Fuel StorageSDR FDEA201110014237Panel · corrodedCOROSION ON CTR WING AUX TANK TOP PANEL SURFACE AT STA 1199 TO STA 1219, X = 8 TO X = 27.5. COROSION REMOVED AS PER SRM 51-21-01 REV 47. ORIGINAL MATERIAL THICKNESS = 0.172 INCH; MATERIAL REMOVED = 0.013 INCH; MATERIAL REMAINED = 0.159 INCH - FOUND EXCEEDED Oct 1, 2011 · N643FE · Doug MD11F · Fuel StorageSDR FDEA201110014236Panel · corrodedCABIN - COROSION ON CTR WING AUX TANK TOP PANEL SURFACE AT STA 1219 TO STA 1239, X = 8 TO X = -8. COROSION REMOVED AS PER SRM 51-21-01 REV 47. ORIGINAL MATERIAL THICKNESS = 0.172 INCH; MATERIAL REMOVED = 0.035 INCH; MATERIAL REMAINED = 0.137 INCH - FOUND EXCOct 1, 2011 · N643FE · Doug MD11F · Fuel StorageSDR FDEA201110014235Panel · corrodedCABIN - COROSION ON CTR WING AUX TANK TOP PANEL SURFACE AT STA 1219 TO STA 1239, X = -8 TO X = -27.5. CORROSION REMOVED AS PER SRM 51-21-01 REV 47. ORIGINAL MATERIAL THICKNESS = 0.172 INCH; MATERIAL REMOVED = 0.041INCH; MATERIAL REMAINED = 0.131 INCH - FOUNDOct 1, 2011 · N643FE · Doug MD11F · Fuel StorageSDR FDEA201110014234Panel · corrodedCOROSION ON CENTER WING AUX TANK TOP PANEL SURFACE AT STA 1219 TO STA 1239, X = -27.5 TO X = -47.5. CORROSION REMOVED AS PER MD-11 SRM 51-21-01 REV 47. ORIGINAL MATERIAL THICKNESS = 0.172 INCH; MATERIAL REMOVED = 0.041INCH; MATERIAL REMAINED = 0.131 INCH - Oct 1, 2011 · N643FE · Doug MD11F · Fuel StorageSDR FDEA201110014233Panel · corrodedCABIN - COROSION ON CTR WING AUX TANK TOP PANEL SURFACE AT STA 1219 TO STA 1239, X = -47.5 TO X = -75. CORROSION REMOVED AS PER SRM 51-21-01 REV 47. ORIGINAL MATERIAL THICKNESS = 0.172 INCH; MATERIAL REMOVED = 0.030 INCH; MATERIAL REMAINED = 0.142 INCH - FOUOct 1, 2011 · N643FE · Doug MD11F · Fuel StorageSDR FDEA201110014232Fuel Cell · corrodedCOROSION ON CTR WING AUX TANK TOP PANEL SURFACE AT BS 1219-1239, X = -75 TO X = -107. CORROSION REMOVED AS PER SRM 51-21-01 REV 47. ORIGINAL MATERIAL THICKNESS = 0.172 INCH; MATERIAL REMOVED = 0.048 INCH; MATERIAL REMAINED = 0.124 INCH - FOUND EXCEEDED LIMIT Oct 1, 2011 · N643FE · Doug MD11F · Fuel StorageSDR FDEA201110014231Fuel Cell · corrodedCOROSION ON CTR WING AUX TANK TOP PANEL SURFACE AT BS 1199-1219, X = -75 TO X = -107. CORROSION REMOVED AS PER SRM 51-21-01 REV 47. ORIGINAL MATERIAL THICKNESS = 0.172 INCH; MATERIAL REMOVED = 0.028 INCH; MATERIAL REMAINED = 0.144 INCH - FOUND EXCEEDED LIMITOct 1, 2011 · N643FE · Doug MD11F · Fuel StorageSDR FDEA201110014230Fuel Cell · corrodedCORROSION ON CENTER WING AUX TANK TOP PANEL SURFACE AT BS 1199-1219, X = -75 TO X = -107. CORROSION REMOVED AS PER MD-11 SRM 51-21-01 REV 47. ORIGINAL MATERIAL THICKNESS = 0.247 INCH; MATERIAL REMOVED = 0.014 INCH; MATERIAL REMAINED = 0.233 INCH - FOUND Oct 1, 2011 · N643FE · Doug MD11F · Fuel StorageSDR FDEA201109264123Longeron · corrodedLONGERON 16 RT BETWEEEN BS 1441-1461 FOUND CORRODED. CORROSION REMOVED IAW SRM 51-21-01, REV 47 AND FOUND CRACKED. NEW LONGERON FABRICATED IAW DWG AEA0220 REV R. LONGERON REMOVED AND REPLACED IAW SRM 51-31-01, REV 47. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2Sep 26, 2011 · N643FE · Doug MD11F · Fuselage Main, Longeron/StringerSDR FDEA201109264122Longeron · crackedLONGERON 16 RT BETWEEEN BS 1239-1256 FOUND CORRODED. CORROSION REMOVED PER SRM 51-21-01, REV 47 AND FOUND CRACKED. LONGERON REMOVED AND REPLACED AS PER SRM 51-31-01 REV 47. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REV 112.Sep 26, 2011 · N643FE · Doug MD11F · Fuselage Main, Longeron/StringerSDR FDEA201109224038Longeron · corrodedSTA 1079 TO 1099 LONGERON 45R SURFACE CORROSION FOUND EXEEDED LIMITS. CORROSION ON LONGERON REMOVED AS PER SRM 51-21-01 REV 47. MATERIAL MEASURED THICKNESS 0.096 INCH; MATERIAL REMOVED = 0.040 INCH; MATERIAL REMAINED = 0.056 INCH. FOUND EXCEEDED LIMIT Sep 22, 2011 · N643FE · Doug MD11F · Fuselage Main, Longeron/StringerSDR FDEA201109213995Longeron · corrodedFORWARD CARGO AT STA 6-68 TO 6-72 LONGERON 51 FOUND WITH CORROSION, CORROSION REMOVED IAW SRM 51-21-01, REV 47. ORIGINAL THICKNESS = 0.062"; MATERIAL REMOVED = 0.041"; MATERIAL REMAINED = 0.021" FOUND OUT OF LIMITS IAW SRM 53-00-00, REV 47, FIG 205 LIMITS. Sep 21, 2011 · N643FE · Doug MD11F · Fuselage Main, Longeron/StringerSDR FDEA201109203973Longeron Splice · corrodedLONGERON SPLICE AT BS 1219-1239, LONGERON 12R. FOUND CORRODED. CORRODED LONGERON SPLICE AREA REMOVED AS PER SRM 51-31-01 REV 47. NEW SPLICE FABRICATED AS PER DWG AEA0650 REV E AND INSTALLED AS PER SRM 51-31-01 REV 47. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2Sep 20, 2011 · N643FE · Doug MD11F · Fuselage Main, Longeron/StringerSDR FDEA201109173915Floorbeam · misrepairedCARGO FLOORBEAM STA 1701 MISREPAIRED. REPAIR CARRIED OUT AS PER EA 15310-14875.Sep 17, 2011 · N643FE · Doug MD11F · Fuselage Main, Floor BeamSDR FDEA201109173917Longeron · corrodedAFT CARGO BS 1902, LONGERON 43R FOUND WITH CORROSION. CORROSION REMOVED AND FOUND EXCEEDED LIMITS IAW SRM 53-00-00, REV 47, FIG 205. LONGERON TRIMMED OUT IAW SRM 53-00-05, REV 47, FIG 202, REPAIR 1. NEW LONGERON AND 2 REPAIR SPLICES FABRICATED AND INSTALLEDSep 17, 2011 · N643FE · Doug MD11F · Fuselage Main, Longeron/StringerSDR FDEA201109173916Arm · corrodedDURING LT WING NR 3 SLAT ASSY REMOVAL, OTBD ATTACHMENT ARM HOLE AT STA XORS 455 FOUND CORRODED. REPAIRED IAW EA 1-5740-149880. CLASSIFIED AS MINOR IAW GMM 6-2-100, REV 113.Sep 17, 2011 · N643FE · Doug MD11F · Wing Main, Frame StructureSDR FDEA201109173914Longeron · corrodedCENTER CARGO COMPARTMENT: STA 5-83 TO 5-93, RT LONGERON 33R CORRODED. CORROSION REMOVED IAW SRM 51-21-01, REV 47. ORIGINAL MATERIAL THICKNESS = 0.060"; MATERIAL REMOVED = 0.030"; MATERIAL REMAINED = 0.030" - FOUND OUT OF LIMITS IAW SRM 53-00-00, REV 47, FISep 17, 2011 · N643FE · Doug MD11F · Fuselage Main, Longeron/StringerSDR FDEA201109123852Seat Track · corrodedCORRSION ON SEAT TRACK EXCEEDED LIMIT AT BS 899-919, X = 75. CORROSION REMOVED AS PER SRM 51-21-01 REV 47. ORIGINAL THICKNESS = 0.100 INCH; MATERIAL REMOVED = 0.060 INCH; MATERIAL REMAINED = 0.060 INCH, REPAIR FABRICATED AS PER SRM 53-00-52, REV 47 Sep 12, 2011 · N643FE · Doug MD11F · Fuselage, Seat/Cargo Attach FittingsSDR FDEA201109093795Door Frame · chafedNR 2 ENGINE LT LOWER DOOR JAMB LOWER OUTER SURFACE FOUND WITH CHAFE MARK EXCEED LIMITS. DAMAGED SKIN PORTION REMOVED AND REPAIR PORTION OF SKIN, 2 ANGLES, STRAPS AND SPLICE FABRICATED AND INSTALLED IAW SRM 54-20-15, REV 47, REPAIR 1, FIG 201. REPAIR CLASSIFISep 9, 2011 · N643FE · Doug MD11F · Nacelle/Pylon, Main FrameSDR FDEA201109093794ALongeron · corrodedFORWARD CARGO BETWEEN STA 6-10 TO STA 6-50 LONGERON 38R FOUND CORRODED. CORROSION AT FWD CARGO LONGERON BETWEEN STA 6-10 TO STA 6-50, LONGERON 38R. REMOVED IAW SRM 51-21-01, REV 47 AT STA 6-48. MATERIAL ORIGINAL THICKNESS = 0.170"; MATERIAL REMOVED = 0.81"; MSep 9, 2011 · N643FE · Doug MD11F · Fuselage Main, Longeron/StringerSDR FDEA201109093794Door Frame · corrodedNR 2 ENGINE LT LOWER DOOR JAMB LOWER OUTER SURFACE FOUND WITH CHAFE MARK EXCEED LIMITS 0.024 IN, ORIGINAL THICKNESS= 0.065 IN.Sep 9, 2011 · N643FE · Doug MD11F · Nacelle/Pylon, Main FrameSDR FDEA201109093790Longeron · corrodedFWD CARGO STA 6-68 TO STA 6-72 LONGERON 51R FOUND CORRODED. CORROSION REMOVED PER SRM 51-21-01 REV 47. ORIGINAL THICKNESS = 0.062 INCH; MATERIAL REMOVED = 0.041 INCH; MATERIAL REMAINED = 0.021 INCH FOUND EXCEEDED SRM 53-00-00 REV 47, FIGURE 205 LIMITS. LSep 9, 2011 · N643FE · Doug MD11F · Fuselage Main, Longeron/StringerSDR FDEA201109093796Hinge Bracket · corrodedRIGHT WING OTBD FLAP INBD HINGE (FLAP SIDE) STA XW486.403 PIVOT INBD HOLE FOUND CORRODED. HOLE SIZE EXEED LIMITS IAW CMM 57-52-04. REWORKED AND FOUND EXCEED LIMIT IAW CMM 57-52-04, REV 70. ORIGINAL DIAMETER = 1.202 INCH; MAX ALLOWABLE DIAMETER = 1.150 IN; FSep 9, 2011 · N643FE · Doug MD11F · Trailing Edge FlapsSDR FDEA201109093797Stringer · crackedLT WING TANK STRUCTURE STRINGER NR 10 END SUSPECTED TO BE CRACKED. REPAIRED IAW SRM 57-00-03, REV 47, REPAIR 5, FIG 202 AND EA 1-5710-154208. CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 113.Sep 9, 2011 · N643FE · Doug MD11F · Wing, Longeron/StringerSDR FDEA201109093793Longeron · corrodedCORROSION ON LONGERON 51L AT BS 6-73.5. REMOVED CORROSION IAW SRM 51-21-01 REV 47. ORIGINAL THICKNESS = 0.090 INCH; MATERIAL REMOVED = 0.032"; MATERIAL REMAINED = 0.058 INCH, FOUND EXCEEDED LIMIT IAW SRM 53-00-00, REV 47, FIG 205. FABRICATED NEW LONGERON ISep 9, 2011 · N643FE · Doug MD11F · Fuselage Main, Longeron/StringerSDR FDEA201109093792Longeron · corrodedFWD CARGO - AT STA 1129 TO STA 6-10 LOGERON 51L FOUND CORRODED. CORROSION REMOVED IAW SRM 51-21-01 REV 47. ORIGINAL THICKNESS = 0.090"; MATERIAL REMOVED= 0.052"; MATERIAL REMAINED = 0.038", FOUND EXCEEDED LIMIT IAW SRM 53-00-00, REV 47, FIG 205. FABRICATED Sep 9, 2011 · N643FE · Doug MD11F · Fuselage Main, Longeron/StringerSDR FDEA201109093791Skin · crackedLEFT WING FIXED L/E AT NR 3 SLAT TELESCOPIC DUCT UPPER CUT-OUT AREA. FOUND CRACKED. EXTERNAL DOUBLER AND REPAIR FILLER FABRICATED IAW SRM 57-40-01, REV 47 AND INSTALLED IAW SRM 57-40-01, REV 47, FIG 201, REPAIR 10. REPAIR CLASSIFIED AS MINOR IAW GMM 6-2-100Sep 9, 2011 · N643FE · Doug MD11F · Wing, Plate/SkinSDR FDEA201109093789Longeron · corrodedCENTER ACCESSORY COMPARTMENT, BETWEEN STA 6-90 TO STA 1159, LONGERON 47 RT, FOUND CORRODED. CORRSION REMOVED IAW SRM 51-21-01, REV 47. ORIGINAL MATERIAL THICKNESS = 0.090"; MATERIAL REMOVED = 0.049 INCH, FOUND EXCEEDED LIMIT IAW SRM 53-00-00, REV 47, FIG 20Sep 9, 2011 · N643FE · Doug MD11F · Fuselage Main, Longeron/StringerSDR FDEA201109093788Floor Support · corrodedFORWARD CARGO AFT BULKHEAD AT STA 6-73.5, X = 8.0 FLOOR SUPPORT FOUND CORRODED. FLOOR SUPPORT R & R IAW SRM 51-31-01, REV 47. REPAIR CLASSIFIED AS MINOR IAW GMM 6-2-100, REV 113.Sep 9, 2011 · N643FE · Doug MD11F · Fuselage Miscellaneous StructureSDR FDEA201109093787Floor Support · corrodedFWD CARGO, AFT BULKHEAD AT STA 6-73.5, X = -8.0, FLOOR SUPPORT FOUND CORRODED. FLOOR SUPPORT REMOVED IAW SRM 51-31-01, REV 47 AND FABRICATED IAW DWG A6A7094, REV E. FABRICATED FLOOR SUPPORT AND INSTALLED IAW SRM 51-31-01, REV 47. REPAIR CLASSIFIED AS MINORSep 9, 2011 · N643FE · Doug MD11F · Fuselage Miscellaneous StructureSDR FDEA201109073729Longeron · chippedBS 1253, LONGERON 43L, FOUND THE EDGE CHIPPED-OFF. REMOVED IAW SRM 51-21-01, REV 47. EDGE MATERIAL REMOVED 0.050" BY L = 2" AND FOUND IN LIMITS IAW SRM 53-00-00, REV 47, FIG 202. REWORKED AREA NDT HFEC INSP CARRIED OUT. NO CRACK EVIDENT IAW NDTSPM, REV Sep 7, 2011 · N643FE · Doug MD11F · Fuselage Main, Longeron/StringerSDR FDEA201109063707Skin · misrepairedREPAIR AT AFT FUSELAGE SKIN BS 1661-1681 LONGERON 51 - 52 RT. FOUND NOT ACCOMPLISHED IAW APPROVED DATA. REPAIR DOUBLER REMOVED AND NEW REPAIR ACCOMPLISHED IAW SRM 53-00-01 REV 47, FIGURE 201 SHEET 1, 2, AND 3, REPAIR 1. ACCOMPLISHED EO 1-5100-7-5001A5 PARTSep 6, 2011 · N643FE · Doug MD11F · Fuselage Main, Plate/SkinSDR FDEA201109063709Longeron · crackedLOWER AUX CTR TANK - BS 1273 LONGERON 43L, (RIB 8 FROM FWD) FOUND CRACK ON THE CLIP ANGLE. REMOVED AND REPLACED AS PER SRM51-31-01 REV 47. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REV 112.Sep 6, 2011 · N643FE · Doug MD11F · Fuselage Main, Longeron/StringerSDR FDEA201109063708Longeron · crackedBS 1273 ALONG LONGERON 43R, FOUND CRACKED. R & R IAW SRM 51-31-01. REPAIR CLASSIFIED AS MINOR IAW GMM 6-2-100, REV 113.Sep 6, 2011 · N643FE · Doug MD11F · Fuselage Main, Longeron/StringerSDR FDEA201109043661Seat Track · corrodedCABIN - CORROSION ON SEAT TRACK FLANGE AT STA 1761 TO STA 1811, X = 8. CORROSION REMOVED AS PER SRM 51-21-01 REV 47. ORIGINAL THICKNESS = 0.080 INCH; MATERIAL REMOVED = 0.045 INCH; MATERIAL REMAINED = 0.035 INCH, EXCEEDED SRM LIMITS. SEAT TRACK SECTION Sep 4, 2011 · N643FE · Doug MD11F · Fuselage, Seat/Cargo Attach FittingsSDR FDEA201109013616Hinge Bracket · corrodedLEFT WING, OTBD FLAP, INBD HINGE (WING SIDE) STA XW 486.403, ACTUATOR OTBD HOLE FOUND CORRODED. REWORKED AND FOUND EXCEEDED LIMIT AS MER CMM 57-44-08 REV 70. ORIGINAL DIAMETER = 1.2055 INCH; MAX ALLOWABLE DIAMETER =1.220 INCH; FINAL DIAMETER = 1.250 INCH.Sep 1, 2011 · N643FE · Doug MD11F · Wing, Control Surface Attach FittingsSDR FDEA201109013615Hinge Bracket · corrodedLT WING OTBD FLAP INBD HINGE (WING SIDE) STA XW 486.403, ACTUATOR INBD HOLE FOUND CORRODED. (HOLE SIZE EXCEEDED LIMIT). REWORKED AND FOUND EXCEEDED LIMIT AS PER SRM CMM 57-44-08 REV 70. ORGINAL DIAMETER = 1.2035 INCH; MAX ALLOWABLE DIAMETER = 1.220 INCH; Sep 1, 2011 · N643FE · Doug MD11F · Wing, Control Surface Attach FittingsSDR FDEA201109013618Spar Cap · corrodedLT WING REAR SPAR UPPER CAP XORS 1042 FOUND CORRODED. CORROSION REMOVED IAW SRM 51-21-01, REV 47. ORIGINAL MATERIAL THICKNESS = 0.145"; MATERIAL REMOVED= 0.032"; MATERIAL REMAINED = 0.113" - FOUND OUT OF LIMITS IAW SRM 57-00-10, REV 47, FIG 101. ACCOMPLISHSep 1, 2011 · N643FE · Doug MD11F · Wing SparSDR FDEA201109013617Spar Cap · corrodedLT WING REAR SPAR UPPER CAP FORWARD OF NR 4 SPOILER FOUND CORRODED. CORROSION REMOVED IAW SRM 51-21-01 AND FOUND OUT OF LIMITS IAW SRM 57-00-10, REV 47, FIG 201. ORIGINAL MATERIAL THICKNESS = 0.290"; MATERIAL REMOVED = 0.060"; MATERIAL REMAINED = 0.230". RSep 1, 2011 · N643FE · Doug MD11F · Wing SparSDR FDEA201109013614Doubler · corrodedRADIO ALTIMETER ANTENNA FUSELAGE MATING SURFACE, 4 LOCATIONS FOUND CORRODED. DOUBLERS REMOVED IAW SRM 51-31-01, REV 47. NEW DOUBLERS INSTALLED IAW SRM 51-31-01, REV 47. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 113.Sep 1, 2011 · N643FE · Doug MD11F · Fuselage Main, Plate/SkinSDR FDEA201109013613Fuel Cell · crackedLT FUEL TANK STRUCTURE STRINGER END NR 10 SUSPECTED CRACKED. REPAIRED IAW SRM 57-00-03, REV 47, REPAIR 5 FIG 202 AND EA 1-5710-154208. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 113.Sep 1, 2011 · N643FE · Doug MD11F · Fuel StorageSDR FDEA201108313591Hinge · corrodedLOWER AFT CARGO DOOR HINGE FOUND RUSTY. RUST REMOVED IAW SRM 51-21-01, REV 47 AND FOUND WITHIN LIMITS IAW SRM 52-30-16, REV 47, FIG 101. REPAIR CLASSIFIED AS MINOR IAW GMM 6-2-100, REV 113.Aug 31, 2011 · N643FE · Doug MD11F · Fuselage, Door HingeSDR FDEA201108313590Hinge · corrodedLOWER CENTER CARGO DOOR HINGE FOUND RUSTY. RUST REMOVED IAW SRM 51-21-01, REV 47 AND FOUND WITHIN LIMITS IAW SRM 52-30-16, REV 47, FIG 101. REPAIR CLASSIFIED AS MINOR IAW GMM 6-2-1.Aug 31, 2011 · N643FE · Doug MD11F · Fuselage, Door HingeSDR FDEA201108313589Hinge · corrodedLOWER FWD CARGO DOOR HINGE ASSY FOUND RUSTY. RUST REMOVED IAW SRM 51-21-01, REV 47 AND FOUND WITHIN LIMITS IAW SRM 52-30-16, REV 47, FIG 101. REPAIR CLASSIFIED AS MINOR IAW GMM 6-2-100, REV 113.Aug 31, 2011 · N643FE · Doug MD11F · Fuselage, Door HingeSDR 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 Fittings
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