N577FE
Operators of this aircraft
Who operated this tail, and how firmly we know it.
No operator established for this aircraft.
Accident & incident history
No NTSB accidents or incidents on file for this aircraft.
Maintenance disclosures
Service Difficulty Reports filed with the FAA for this airframe. Filing is largely voluntary — the number of reports is not a measure of reliability. To verify a report, search its control number at the FAA SDRS site.
256 reports on file, 2004-11-25 – 2013-10-02.
Part: WINDOW — LOOSE (ESCAPE ROPE) · airframe 64,360 hrs · 14,248 cycles
LEFT SIDE COCKPIT ESCAPE ROPE VIEWING DOOR GLASS IS LOOSE. CORRECTLY INSTALLED VIEWING GLASS.
Earlier reports · 2004–2012 · 255 reports
2012
Part: SKIN — MISREPAIRED (NR 8 SLAT) · airframe 60,991 hrs · 13,172 cycles
RT WING NR 8 SLAT UPPER SURFACE STATION XORS 995 MISREPAIRED. REPAIRED IAW EA 1-5750-160031 PART 1. CLASSIFIED MAJOR IAW GMM 6-2-100 REVISION 114.
Part: SKIN — MISREPAIRED (NR 5 SLAT) · airframe 60,991 hrs · 13,172 cycles
RT WING NR 5 SLAT AFT SURFACE OTBD LOWER CORNER STA XORS 682 MISREPAIRED. REPAIRED IAW EA 1-5750-160032. CLASSIFIED MAJOR IAW GMM 6-2-100 REVISION 114.
Part: SKIN — MISREPAIRED (ZONE 400) · airframe 60,991 hrs · 13,172 cycles
NR 2 PYLON EXTERIOR APPROX STA Y = 2334 FOUND MISREPAIRED. REPAIRED IAW EO E1-5100-7-5001B PT1. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 114.
Part: SKIN — MISREPAIRED (NR 3 SLAT) · airframe 60,991 hrs · 13,172 cycles
LT WING SKIN AT NR 3 SLAT LOWER SURFACE XORS 372. REPAIRED IAW EA1-5750-159830. REPAIR CLASSIFIED MAJOR IAW GMM 6-2-100, REV 114.
Part: SKIN — MISREPAIRED (BS 2147-2160) · airframe 60,991 hrs · 13,172 cycles
SKIN AT BS 2147 - 2160, L33L MISREPAIRED. REPAIRED IAW SRM 53-70-01 FIGURE 201 REPAIR 3 REVISION 49 & EO E1-5100-7-5001B PT1. MAJOR REPAIR.
Part: ATTACH FITTING — CRACKED (MLG TRUNNION) · airframe 60,991 hrs · 13,172 cycles
DURING HIGH FREQUENCY EDDY CURRENT INSPECTION AROUND STOP DRILL HOLE OF LT NOSE LANDING GEAR TRUNNION FITTING FOUND ONE NEW ADDITIONAL CRACK PROPAGATED FROM THE STOP DRILL HOLE TOWARDS THE LOWER EDGE, APPROX 0.25". REPAIR CARRIED OUT AT LT NLG TRUNNION FITTING CRACKED AREA IAW SRM 53-10-14, REPAIR 2, FIG 202 REV 49. INITIAL INSP TO BE CARRIED OUT EVERY 1500 FLIGHT CYCLES AND REPETITIVE INSP EVERY 1500 FLIGHT CYCLES. INITIAL AND REPETITIVE INSP TO BE CARRIED OUT IAW SRM 53-10-14, TABLE 201, REPAIR 2 WORK INSTRUCTION. REPAIR CLASSIFIED MAJOR IAW GMM 6-2-100, REV 114.
Part: LONGERON — CRACKED (ZONE 200) · airframe 60,991 hrs · 13,172 cycles
FOUND LONGERON 49 LT FASTENER HOLE (COMMON TO NLG TRUNNION FITTING) CRACKED , APPROX 0.025". LONGERON REMOVED IAW SRM 51-31-01, REV 49. NEW LONGERON FABRICATED IAW DWG ACA 3796 REV A. NEW FABRICATED LONGERON INSTALLED IAW SRM 51-31-01, REV 49. REPAIR CLASSIFIED MAJOR IAW GMM 6-2-100 REV 114.
Part: SKIN — CORRODED (ZONE 200) · corrosion level 2 · airframe 60,991 hrs · 13,172 cycles
MAIN DECK UPPER CARGO COMPARTMENT UNDER FLOOR AT CENTER WING TANK BETWEEN STATION 1219 TO STATION 1239, "X" = -75.25. FOUND SURFACE CORROSION AT FASTENERS AREA. CORROSION REMOVED IAW SRM 51-21-01, REV 49. ORIGINAL MATERIAL THICKNESS = 0.171", REMAINING THICKNESS = 0.134", MATERIAL REMOVED = 0.037" AND FOUND ACCEPTABLE AS IAW EA 1-5730-160022. REPAIR CLASSIFIED AS MINOR IAW GMM 6-2-100, REV 114.
Part: SKIN — MISREPAIRED (RT WING TE FLAP) · airframe 60,991 hrs · 13,172 cycles
RT WING INBD FLAP UPPER SURFACE MISREPAIRED. REPAIRED IAW SRM 57-00-01, FIG 201, REPAIR 1, REV 49.
Part: SKIN — CORRODED (BS 1219-1239) · corrosion level 2 · airframe 60,991 hrs · 13,172 cycles
MAIN DECK UPPER CARGO COMPARTMENT, UNDER FLOOR AT CENTER WING TANK BETWEEN STATION 1219 TO STATION 1239, "X" = -27.5 FOUND SURFACE CORROSION AT FASTENERS AREA. CORROSION REMOVED IAW SRM 51-21-01, REV 49. ORIGINAL MATERIAL THICKNESS = 0.175", REMAINING THICKNESS = 0.145", MATERIAL REMOVED = 0.030" AND FOUND ACCEPTABLE IAW EA 1-5730-160022. REPAIR CLASSIFIED AS MINOR GMM 6-2-100, REV 114.
Part: LONGERON — CORRODED (ZONE 100) · corrosion level 2 · airframe 60,991 hrs · 13,172 cycles
CENTER CARGO COMPARTMENT, BILGE AREA BS 1646 LONGERON 50 LT FOUND WITH SURFACE CORROSION. REPAIR CARRIED OUT AT CENTER CARGO COMPARTMENT BILGE AREA STA 1646, LONGERON 50L IAW EA 1-5310-159838. REPAIR CLASSIFIED MAJOR IAW GMM 6-2-100, REV 114.
Part: FRAME — MISREPAIRED (ZONE 200) · airframe 60,991 hrs · 13,172 cycles
FRAME STA 535 AT LONGERON 19 LT MISREPAIRED. REPAIRED IAW SRM 53-20-07, FIG 202, REPAIR 1, REV 49. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 114.
Part: SKIN — CORRODED (ZONE 300) · corrosion level 2 · airframe 60,991 hrs · 13,172 cycles
AFT ACCESSORY COMPARTMENT, FOUND CORROSION ON RT SKIN BS 2163 BODY FAIRING CUTOUT LOCATION. CORROSION REMOVED IAW SRM 51-21-01, REV 49. ORIGINAL THICKNESS: 0.95", MATERIAL REMOVED: 0.80", REMAINING 0.015" AND FOUND EXCEED LIMIT IAW SRM 53-70-01, FIG 201, REPAIR 3, REV 49. REPAIR CARRIED OUT IAW SRM 53-70-01, FIG 201, REPAIR 3 REV 49. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 114.
Part: SKIN — CORRODED (ZONE 200) · corrosion level 2 · airframe 60,991 hrs · 13,172 cycles
MAIN DECK UPPER CARGO COMPARTMENT UNDER FLOOR AT CENTER WING TANK BETWEEN BS 1219 TO 1239, "X" = -75.25 TO "X" = -90 FOUND SURFACE CORROSION AT FASTENERS AREA. CORROSION REMOVED IAW SRM 51-21-01, REV 49. ORIGINAL MATERIAL THICKNESS = 0.168", REMAINING THICKNESS = 0.148", MATERIAL REMOVED = 0.020" AND FOUND ACCEPTABLE IAW EA 1-5730-160022. REPAIR CLASSIFIED AS MINOR IAW GMM 6-2-100, REV 114.
Part: LONGERON — CORRODED (ZONE 100) · airframe 60,991 hrs · 13,172 cycles
CENTER CARGO COMPARTMENT BS 1676 LONGERON 51 LT FOUND WITH SURFACE CORROSION. REPAIRED IAW SRM 53-00-05, FIG 201, REPAIR 1, REV 49. REPAIR CLASSIFIED MAJOR IAW GMM 6-2-100, REV 114.
Part: SKIN — CORRODED (ZONE 200) · airframe 60,991 hrs · 13,172 cycles
MAIN DECK UPPER CARGO COMPARTMENT, UNDER FLOOR AT CTR WING TANK BETWEEN BS 1219 TO 1239, "X" = -8.5 TO "X = -27.5. FOUND SURFACE CORROSION AT FASTENERS AREA. CORROSION REMOVED IAW SRM 51-21-01, REV 49. ORIGINAL MATERIAL THICKNESS = 0.182", REMAINING THICKNESS = 0.139", MATERIAL REMOVED = 0.043" AND FOUND ACCEPTABLE IAW EA 1-5730-160022. REPAIR CLASSIFIED AS MINOR IAW GMM 6-2-100, REV 114.
Part: SKIN — CRACKED (VERTICAL STAB) · airframe 60,991 hrs · 13,172 cycles
LOWER VERTICAL STABILIZER FOUND RT SIDE REAR CENTER SPAR TO REAR SPAR LOWER PANEL CRACKED. REPAIR CARRIED OUT IAW SRM 55-30-02, FIG 201, REPAIR 2, REV 49. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 114. NR 2 ENGINE FIRE DETECTION CONTROL UNIT CARRIED OUT BITE TEST IAW AMM 26-11-02-700-801, REV 72.0. NR 2 ENGINE GROUND IDLE RUN CARRIED OUT IAW AMM 71-02-03-700-870, REV 72.0 FOUND SATISFACTORY.
Part: SKIN — CORRODED (ZONE 200) · corrosion level 2 · airframe 60,991 hrs · 13,172 cycles
MAIN DECK UPPER CARGO COMPARTMENT UNDER FLOOR AT CENTER WING TANK BETWEEN BS 1219 TO 1239, "X" = -90 TO "X" = -107.5 FOUND SURFACE CORROSION AT FASTENERS AREA. CORROSION REMOVED IAW SRM 51-21-01, REV 49. ORIGINAL MATERIAL THICKNESS = 0.180", REMAINING THICKNESS = 0.136", MATERIAL REMOVED = 0.044" AND FOUND ACCEPTABLE IAW EA 1-5730-160022. REPAIR CLASSIFIED AS MINOR IAW GMM 6-2-100 REV 114.
Part: FRAME — MISREPAIRED (ZONE 200) · airframe 60,991 hrs · 13,172 cycles
CABIN AT FRAME BS 535, LONGERON 23L FOUND MISREPAIRED. REPAIRED IAW SRM 53-20-07, FIG 201 REPAIR 1, REV 49. CLASSIFIED MAJOR IAW GMM 6-2-100, REV 114.
Part: HINGE FITTING — CORRODED (ZONE 500) · corrosion level 2 · airframe 60,991 hrs · 13,172 cycles
LT WING (WING SIDE) OTBD FLAP, OTBD HINGE LOWER MOUNT, OTBD HOLE FOUND CORRODED. BUSHING REMOVED IAW CMM 20-20-07, REV 72. OTBD BORE REWORKED AND FOUND EXCEEDED LIMIT IAW CMM 57-44-09, REV 72. EXISTING HOLE DIAMETER 0.581", FINAL HOLE DIAMETER 0.596", MAXIMUM ALLOWABLE DIAMETER: 0.584". REPAIR ACCOMPLISHED IAW EA 1-5750-160020, PART 1, STEPS 3, 4, 7, 8 AND 10. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 114.
Part: HINGE FITTING — CORRODED (ZONE 500) · airframe 60,991 hrs · 13,172 cycles
LT WING (WING SIDE) OTBD FLAP, INBD HINGE SIDE LOAD FITTING SURFACE FOUND CORRODED. REWORKED IAW CMM 20-11-02, REV 72. UPPER EXISTING THICKNESS: 0.400", MATERIAL REMOVED: 0.004", REMAINING THICKNESS: 0.396". LOWER EXISTING THICKNESS: 0.387", MATERIAL REMOVED: 0.004", REMAINING THICKNESS: 0.383". REPAIR ACCOMPLISHED IAW EA 1-5750-160021, PART 1, STEPS 5, 6 AND 8. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100 REV 114.
Part: BUSHING — WORN (ZONE 500) · airframe 60,991 hrs · 13,172 cycles
LT WING (WING SIDE) OTBD FLAP, OTBD HINGE, INBD ACTUATOR HOLE BUSHING WORN. BUSHING REMOVED IAW CMM 20-20-07, REV 72. BORE DIAMETER 1.251" AND FOUND EXCEEDED LIMIT IAW CMM 57-44-09, REV 72. MAXIMUM ALLOWABLE DIAMETER: 1.220". REPAIR ACCOMPLISHED EA 1-5750-160020, PART 1, STEPS 1, 2, 7, 9, 10 AND 11. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 114.
Part: BUSHING — WORN (RT WING TE FLAP) · airframe 60,991 hrs · 13,172 cycles
RT WING (FLAP SIDE) OTBD FLAP, OTBD HINGE, OTBD PIVOT HOLE BUSHING FOUND WORN. BUSHING REMOVED IAW CMM 20-20-07, REV 72. BORE MEASURED DIAMETER 1.152" AND FOUND EXCEED LIMIT IAW CMM 57-52-04, REV 72. MAXIMUM ALLOWABLE DIAMETER 1.150". REPAIR ACCOMPLISHED IAW EA 1-5750-160024, PART 1. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 114.
Part: HINGE FITTING — CORRODED (ZONE 500) · corrosion level 2 · airframe 60,991 hrs · 13,172 cycles
LT WING (WING SIDE) OTBD FLAP, OTBD HINGE SIDE LOAD FITTING SURFACE FOUND CORROSION. REWORKED IAW CMM 20-11-02, REVISION 72. UPPER EXISTING THICKNESS: 0.425", MATERIAL REMOVED: 0.009", REMAINING THICKNESS: 0.416". LOWER EXISTING THICKNESS: 0.413", MATERIAL REMOVED: 0.010", REMAINING THICKNESS: 0.403". REPAIR ACCOMPLISHED IAW EA NR 1-5750-160020 PART 1, STEPS 5, 7 AND 8. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100 REV 114.
Part: HINGE FITTING — DAMAGED (LT WING TE FLAP) · airframe 60,991 hrs · 13,172 cycles
LEFT WING (FLAP SIDE), INBD FLAP OTBD HINGE, OTBD PIVOT HOLE, FOUND STEP HOLE. BUSHING REMOVED IAW CMM 20-20-07, REV 72. BORE MEASURED, OTBD LUG DIAMETER 1.254", OTBD STRAP DIAMETER 1.190" AND FOUND EXCEED LIMIT IAW CMM 57-52-03, REV 72. MAXIMUM ALLOWABLE DIAMETER 1.220". REPAIR ACCOMPLISHED IAW EA 1-5750-160025, PART 1. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 114.
Part: HINGE FITTING — DAMAGED (ZONE 600) · airframe 60,991 hrs · 13,172 cycles
RT WING (WING SIDE) OTBD FLAP, INBD HINGE, INBD ACTUATOR HOLE BUSHING WORN. BUSHING REMOVED IAW CMM 20-20-07, REV 72. BORE MEASURED DIAMETER 1.253" AND FOUND EXCEED LIMIT IAW CMM 57-44-08, REV 72. MAXIMUM ALLOWABLE DIAMETER 1.220", REPAIR ACCOMPLISHED IAW EA 1-5750-160028, PART 1, STEPS 1, 5, 6, 8 AND 9. REPAIR. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 114.
Part: BUSHING — WORN (ZONE 600) · airframe 60,991 hrs · 13,172 cycles
RT WING (WING SIDE) OTBD FLAP, INBD HINGE, OTBD ACTUATOR HOLE BUSHING WORN. BUSHING REMOVED IAW CMM 20-20-07, REV 72. BORE MEASURED, DIAMETER 1.252" FOUND EXCEED LIMIT IAW CMM 57-44-08, REV 72. MAXIMUM ALLOWABLE DIAMETER: 1.220". REPAIR ACCOMPLISHED IAW EA 1-5750-160028 PART 1, STEPS 1, 5, 6 AND 8. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100 REV 114.
Part: HINGE FITTING — CORRODED (ZONE 600) · corrosion level 2 · airframe 60,991 hrs · 13,172 cycles
RT WING (WING SIDE) OTBD FLAP, OTBD HINGE LOWER MOUNT, INBD HOLE FOUND CORRODED. BUSHING REMOVED IAW CMM 20-20-07, REV 72. INBOARD HOLE REWORKED AND FOUND EXCEEDED LIMIT IAW CMM 57-44-09, REV 72. EXISTING BORE DIAMETER = 0.581", FINAL BORE DIAMETER 0.612", MAXIMUM ALLOWABLE DIAMETER 0.584". REPAIR ACCOMPLISHED IAW EA 1-5750-160026, PART 1, STEPS 2, 3, 4, 5 AND 7. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100 REV 114.
Part: HINGE FITTING — DAMAGED (RT WING TE FLAP) · airframe 60,991 hrs · 13,172 cycles
RT WING (FLAP SIDE) INBD FLAP, OTBD HINGE, INBD PIVOT HOLE FOUND STEP HOLE. BUSHING REMOVED IAW CMM 20-20-07, REV 72. BORE MEASURE, INBD LUG DIAMETER 1.252 IN, INBD STRAP DIAMETER 1.218" AND FOUND EXCEED LIMIT IAW CMM 57-52-03, REV 72. MAXIMUM ALLOWABLE DIAMETER 1.220". REPAIR ACCOMPLISHED IAW EA 1-5750-160023. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 114.
Part: BUSHING — WORN (ZONE 500) · airframe 60,991 hrs · 13,172 cycles
LT WING (WING SIDE) OTBD FLAP, INBD HINGE, INBD ACTUATOR HOLE BUSHING FOUND WORN. BUSHING REMOVED IAW CMM 20-20-07, REV 72. BORE MEASURED, DIAMETER = 1.231" AND FOUND EXCEEDED LIMIT IAW CMM 57-44-08, REV 72. MAXIMUM ALLOWABLE DIAMETER 1.220". REPAIR ACCOMPLISHED IAW EA 1-5750-160021, PART 1, STEPS 1, 6, 7, 9 AND 10. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 114.
Part: HINGE FITTING — CORRODED (ZONE 500) · corrosion level 2 · airframe 60,991 hrs · 13,172 cycles
LT WING (WING SIDE) OTBD FLAP, OTBD HINGE, SIDE LOAD FITTING LOWER HOLE FOUND CORRODED. BUSHING REMOVED IAW CMM 20-20-07, REV 72. BORE REWORKED AND FOUND EXCEEDED LIMIT CMM 57-44-09, REV 72. EXISTING HOLE DIAMETER 0.389", FINAL HOLE DIAMETER 0.408", MAXIMUM ALLOWABLE DIAMETER: 0.391". REPAIR ACCOMPLISHED IAW EA 1-5750-160020 PART 1, STEPS 6, 7, 8 AND 10. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 114.
Part: HINGE FITTING — CORRODED (ZONE 600) · corrosion level 2 · airframe 60,991 hrs · 13,172 cycles
RT WING (WING SIDE) OTBD FLAP, OTBD HINGE, OTBD ACTUATOR HOLE FOUND CORRODED. REWORKED AND FOUND EXCEED LIMIT IAW CMM 57-44-09, REV 72. EXISTING BORE DIAMETER 1.222". FINAL BORE DIAMETER 1.246", MAXIMUM ALLOWABLE DIAMETER 1.220". REPAIR CARRIED OUT EA 1-5750-160026, PART 1, STEPS 1, 4, 5, 6 AND 7. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 114.
Part: HINGE FITTING — CORRODED (ZONE 500) · airframe 60,991 hrs · 13,172 cycles
LT WING (WING SIDE) OTBD FLAP, INBD HINGE LOWER MOUNT OTBD HOLE FOUND CORRODED. BUSHING REMOVED IAW CMM 20-20-07, REV 72. BORE REWORKED AND FOUND EXCEEDED LIMIT IAW CMM 57-44-08, REV 72. EXISTING HOLE DIAMETER :0.707", FINAL HOLE DIAMETER 0.713", MAXIMUM ALLOWABLE DIAMETER 0.709". REPAIR ACCOMPLISHED IAW EA 1-5750-160021 PART 1, STEPS 3, 6, 8 AND 9. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100 REV 114.
Part: HINGE FITTING — CORRODED (ZONE 500) · airframe 60,991 hrs · 13,172 cycles
LT WING (WING SIDE) OTBD FLAP, INBD HINGE, OTBD ACTUATOR HOLE FOUND CORRODED. REWORKED AND FOUND EXCEEDED LIMIT IAW CMM 57-44-08, REV 72. ORIGINAL BORE DIAMETER = 1.2295", FINAL BORE DIAMETER 1.236", MAXIMUM ALLOWABLE DIAMETER 1.220". REPAIR ACCOMPLISHED EA 1-5750-160021, PART 1, STEPS 2, 6, 7, 8 AND 9. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100 REV 114.
Part: HINGE FITTING — CORRODED (ZONE 600) · corrosion level 2 · airframe 60,991 hrs · 13,172 cycles
RT WING (WING SIDE) OTBD FLAP, INBD HINGE LOWER MOUNT OTBD HOLE, FOUND CORRODED. BUSHING REMOVED IAW CMM 20-20-07, REV 72. LOWER MOUNT OTBD BORE REWORKED AND FOUND EXCEED LIMIT IAW CMM 57-44-08, REV 72. EXISTING BORE DIAMETER 0.708", FINAL BORE DIAMETER 0.708", MAXIMUM ALLOWABLE DIAMETER 0.709". REPAIR ACCOMPLISHED IAW EA 1-5750-160028 PART 1, STEPS 2, 5, 7 AND 8. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 114.
Part: HINGE FITTING — CORRODED (RT WING) · corrosion level 2 · airframe 60,991 hrs · 13,172 cycles
RT WING (WING SIDE) OTBD FLAP, INBD HINGE SIDE LOAD FITTING SURFACE, FOUND CORRODED. REWORKED IAW CMM 20-11-02 REV 72. UPPER EXISTING THICKNESS: 0.412", MATERIAL REMOVED: 0.005", REMAINING THICKNESS: 0.407". LOWER EXISTING THICKNESS: 0.403", MATERIAL REMOVED: 0.006", REMAINING THICKNESS: 0.397". REPAIR ACCOMPLISHED IAW EA NR 1-5750-160028, PART 1, STEPS 3, 4, 5 AND 7. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 114.
Part: HINGE FITTING — CORRODED (ZONE 600) · corrosion level 2 · airframe 60,991 hrs · 13,172 cycles
RT WING (WING SIDE) OTBD FLAP, OTBD HINGE, LOWER MOUNT, OTBD HOLE FOUND CORRODED. BUSHING REMOVED IAW CMM 20-20-07, REV 72. OTBD BORE REWORKED AND FOUND EXCEEDED LIMIT IAW CMM 57-44-09, REV 72. EXISTING BORE DIAMETER = 0.597", FINAL BORE DIAMETER 0.612", MAXIMUM ALLOWABLE DIAMETER 0.584". REPAIR ACCOMPLISHED IAW EA 1-5750-160026, PART 1, STEPS 2, 3, 4, 5 AND 7. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 114.
Part: HINGE FITTING — CORRODED (ZONE 500) · corrosion level 2 · airframe 60,991 hrs · 13,172 cycles
LT WING (WING SIDE) OTBD FLAP, OTBD HINGE SIDE LOAD FITTING UPPER HOLE FOUND CORRODED. BUSHING REMOVED IAW CMM 20-20-07, REV 72. UPPER HOLE REWORKED AND FOUND EXCEEDED LIMIT IAW CMM 57-44-09, REV 72. EXISTING HOLE DIAMETER 0.389", FINAL HOLE DIAMETER 0.408", MAXIMUM ALLOWABLE DIAMETER: 0.391". REPAIR ACCOMPLISHED IAW EA 1-5750-160020, PART 1, STEPS 6, 7, 8 AND 10. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 114.
Part: HINGE FITTING — DAMAGED (RT WING TE FLAP) · airframe 60,991 hrs · 13,172 cycles
RT WING (FLAP SIDE) INBD FLAP, OTBD HINGE, OTBD PIVOT HOLE, FOUND STEP HOLE. BUSHING REMOVED IAW CMM 20-20-07, REV 72. BORE MEASURED, OTBD LUG DIAMETER 1.250", OTBD STRAP DIAMETER 1.21" AND FOUND EXCEED LIMIT IAW CMM 57-52-03, REV 72. MAXIMUM ALLOWABLE DIAMETER 1.220". REPAIR ACCOMPLISHED IAW EA NR 1-5750-160023, PART 1. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 114.
Part: HINGE FITTING — CORRODED (ZONE 600) · corrosion level 2 · airframe 60,991 hrs · 13,172 cycles
RT WING (WING SIDE) OTBD FLAP, INBD HINGE LOWER MOUNT INBD HOLE FOUND CORRODED. BUSHING REMOVED IAW CMM 20-20-07, REV 72. LOWER MOUNT INBD BORE REWORKED AND FOUND EXCEED LIMIT IAW CMM 57-44-08, REV 72. EXISTING BORE DIAMETER 0.705", FINAL BORE DIAMETER 0.714", MAXIMUM ALLOWABLE DIAMETER 0.709". REPAIR ACCOMPLISHED IAW EA 1-5750-160028, PART 1, STEPS 2, 5, 7 AND 8. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 114.
Part: LONGERON — CORRODED (ZONE 100) · airframe 60,991 hrs · 13,172 cycles
CENTER ACCESSORY COMPARTMENT STA 6-95, LONGERON 43 RT FOUND WITH CORROSION. REPAIRED IAW EA 1-5310-157171, PART 1. REPAIR CLASSIFIED MAJOR IAW GMM 6-2-100, REV 114.
Part: HINGE FITTING — CORRODED (ZONE 500) · corrosion level 2 · airframe 60,991 hrs · 13,172 cycles
LT WING (WING SIDE) OTBD FLAP, OTBD HINGE LOWER MOUNT INBD HOLE FOUND CORRODED. BUSHING REMOVED IAW CMM 20-20-07, REV 72. INBD BORE REWORKED AND FOUND EXCEEDED LIMIT IAW CMM 57-44-09, REV 72. EXISTING HOLE DIAMETER 0.580", FINAL HOLE DIAMETER 0.5975", MAXIMUM ALLOWABLE DIAMETER: 0.584". REPAIR ACCOMPLISHED IAW EA 1-5750-160020, PART 1, STEPS 3, 4, 7, 8 AND 10. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 114.
Part: HINGE FITTING — CORRODED (ZONE 600) · corrosion level 2 · airframe 60,991 hrs · 13,172 cycles
RT WING (WING SIDE) OTBD FLAP, OTBD HINGE, INBD ACTUATOR HOLE FOUND CORRODED. REWORKED AND FOUND EXCEEDED LIMIT IAW CMM 57-44-09, REV 72. EXISTING BORE DIAMETER = 1.2215", FINAL BORE DIAMETER 1.246", MAXIMUM ALLOWABLE DIAMETER 1.220". REPAIR ACCOMPLISHED EA 1-5750-160026, PART 1, STEPS 1, 4, 5, 6, 7 AND 8. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 114.
Part: HINGE FITTING — DAMAGED (LT WING TE FLAP) · airframe 60,991 hrs · 13,172 cycles
LEFT WING (FLAP SIDE) INBD FLAP, OTBD HINGE, INBD PIVOT HOLE, FOUND STEP HOLE. BUSHING REMOVED IAW CMM 20-20-07, REV 72. BORE MEASURE, INBD LUG, DIAMETER 1.283", INBD STRAP DIAMETER 1.217" AND FOUND EXCEED LIMIT IAW CMM 57-52-03, REV 72. MAXIMUM ALLOWABLE DIAMETER 1.220". REPAIR ACCOMPLISHED IAW EA 1-5750-160025 PART 1. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 114.
Part: SKIN — CRACKED (ZONE 600) · airframe 60,991 hrs · 13,172 cycles
HIGH FREQUENCY EDDY CURRENT OPEN HOLE INSP ON RT WING FUEL TANK LOWER ACCESS DOOR PANEL NR 636AB CUTOUT AND FOUND CRACK INDICATION ON 06 EACH FASTENER HOLES. REPAIR CARRIED OUT IAW EA 1-5710-157168 PART 1. REPAIR CLASSIFIED MAJOR PER GMM 6-2-100 REVISION 114
Part: SKIN — CRACKED (ZONE 500) · airframe 60,991 hrs · 13,172 cycles
HIGH FREQUENCY EDDY CURRENT OPEN HOLE INSP ON LT WING FUEL TANK LOWER ACCESS DOOR PANEL NR 536AB CUTOUT AND FOUND CRACK INDICATION ON 04 EACH FASTENER HOLES. REPAIR CARRIED OUT IAW EA 1-5710-157169 PART 1. REPAIR CLASSIFIED MAJOR PER GMM 6-2-100 REVISION 114.
Part: SKIN — CRACKED (ZONE 600) · airframe 60,991 hrs · 13,172 cycles
RIGHT WING LOWER FIXED L/E AT REFUELING PANEL CUTOUT INBD FORWARD CORNER AREA FOUND CRACKED. REPAIR CARRIED OUT IAW SRM 57-40-02. REPAIR 7 FIG 201 REV 49. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REVISION 114.
Part: SKIN — CRACKED (ZONE 500) · airframe 60,991 hrs · 13,172 cycles
LEFT WING FIXED L/E LOWER SURFACE AT NR 14 SLAT TRACK LOWER CUTOUT CRACKED. REPAIR CARRIED OUT IAW SRM 57-40-02, REPAIR 7, FIG 201, REV 49. REPAIR CLASSIFIED AS MAJOR GMM 6-2-100, REV 114.
Part: SKIN — CRACKED (ZONE 600) · airframe 60,991 hrs · 13,172 cycles
RT WING FIXED L/E LOWER SURFACE AT NR 14 SLAT TRACK LOWER CUTOUT FOUND CRACKED. REPAIR CARRIED OUT AT RT WING FIXED L/E LOWER SURFACE AT NR 14 SLAT TRACK LOWER CUTOUT IAW SRM 57-40-02. REPAIR 7, FIG 201, REV 49. REPAIR CLASSIFIED MAJOR IAW GMM 6-2-100, REVISION 114.
Part: FINGER DOUBLER — CRACKED (ZONE 500) · airframe 60,991 hrs · 13,172 cycles
LEFT WING L/E REFUELING ACCESS PANEL COMPARTMENT AT STA XORS 525 FOUND UPPER FINGER DOUBLER CRACKED. REPAIR CARRIED OUT IAW SRM 57-40-02, REPAIR 9, FIG 203, REV 49. REPAIR CLASSIFIED MAJOR IAW GMM 6-2-100, REV 114.
Part: SKIN — MISREPAIRED (ZONE 500) · airframe 60,991 hrs · 13,172 cycles
LT WING DROOP L/E UPPER SURFACE FOUND MISREPAIRED IAW SRM 57-40-01, REPAIR 5, FIGURE 201. REPAIRED IAW EA 1-5730-159836, CLASSIFIED MAJOR IAW GMM 6-2-100, REV 114.
Part: LONGERON — CORRODED (ZONE 100) · airframe 60,991 hrs · 13,172 cycles
CENTER CARGO BAY, LONGERON 50 RT, STA 5-128 FOUND WITH CORROSION. CORROSION REMOVED IAW SRM 51-21-01, REV 49. ORIGINAL THICKNESS: 0.156", MATERIAL REMOVED: 0.060", REMAINING THICKNESS: 0.096" FOUND EXCEED LIMITS IAW SRM 53-00-00, FIG 205, REV 49. REPAIR CARRIED OUT IAW EA NR 1-5310-159829. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 114.
Part: LONGERON SPLICE — CRACKED (BS 1531-1542) · airframe 60,991 hrs · 13,172 cycles
CENTER CARGO COMPARTMENT BILGE AREA BETWEEN STA 1531-1542 AT LONGERON 50R. FOUND LONGERON SPLICE CRACKED. LONGERON REMOVED IAW SRM 51-33-01, REV 49. NEW LONGERON SPLICE FABRICATED IAW DWG A5A7114, REV E AND INSTALLED IAW SRM 51-33-01, REV 49. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 114.
Part: VANE — DELAMINATED (LT WING TE FLAP) · airframe 60,991 hrs · 13,172 cycles
LEFT WING INBD FLAP VANE LOWER SURFACE FOUND DELAMINATED. R & R IAW AMM 27-50-22-4, REV 72.0. ADJUSTMENT AND TEST CARRIED OUT IAW AMM 27-50-22-5, REV 72.0. FOUND SATISFACTORY. REPAIR CLASSIFIED MINOR IAW GMM 6-2-100 REV 114.
2010
Part: SKIN — BULGED (LT WING) · airframe 55,452 hrs · 11,861 cycles
BULGED SKIN FOUND AT LT WING UPPER SKIN SURFACES XORS 376 STR 4. REPAIRED IAW EA1-5730-137967.
Part: SKIN — BULGED (LT WING) · airframe 55,452 hrs · 11,861 cycles
BULGED SKIN FOUND AT LT WING UPPER SKIN SURFACES XORS412 T/E AREA. REPAIR IAW EA1-5730-137967.
Part: LONGERON SPLICE — CRACKED (L1R) · airframe 55,452 hrs · 11,861 cycles
CRACK (APPROX 0.25") - LONGERON SPLICE AT STA6-0, LONGERON-1R. LONGERON SPLICE REPLACED IAW SRM 51-33-01, REV 43 (MAJOR REPAIR).
Part: SKIN — CRACKED (LT WING) · airframe 55,452 hrs · 11,861 cycles
(06 EACH) FASTENER HOLES FOUND CRACK INDICATING DURING HFEC OPEN HOLE INSP AT LT WING LOWER SKIN ACCESS DOOR CUTOUT BETWEEN STA XORS 690 AND XORS 700. REPAIRED IAW EA 1-5710-137963.
Part: SKIN — CRACKED (ZONE 600) · airframe 55,452 hrs · 11,861 cycles
(12 EACH) FASTENER HOLES FOUND CRACK INDICATING DURING HFEC OPEN HOLE INSP AT RT WING LOWER SKIN ACCESS DOOR CUTOUT BETWEEN STA XORS 690 AND XORS 700. REPAIRED IAW EA 1-5710-137964.
Part: FRAME — DENTED (ZONE 200) · airframe 55,452 hrs · 11,861 cycles
CABIN - LT STA 1701 LONGERON 12 FRAME FOUND DENT. FRAME REPAIR AS PER SRM 53-00-07 FIG 201 REPAIR 2 REV 43 (MAJOR REPAIR).
Part: FRAME — DENTED (ZONE 200) · airframe 55,452 hrs · 11,861 cycles
CABIN - LT STA 1721 LONGERON 12 FRAME FOUND DENTED. FRAME REPAIR IAW SRM 53-00-07, FIG 201, REPAIR 2, REV 43 (MAJOR REPAIR).
Part: FRAME — DENTED (ZONE 200) · airframe 55,452 hrs · 11,861 cycles
CABIN - LT STA 1741, LONGERON 12 FRAME FOUND DENT. FRAME REPAIR IAW SRM 53-00-07, FIG 201, REPAIR 2, REV 43 (MAJOR REPAIR).
Part: FRAME — DENTED (ZONE 200) · airframe 55,452 hrs · 11,861 cycles
CABIN - RT STA 1681 LONGERON 12 FRAME FOUND DENTED. FRAME REPAIR IAW SRM 53-00-07, FIG 201, REPAIR 2, REV 43 (MAJOR REPAIR).
Part: CAP — CRACKED (ZONE 100) · airframe 55,452 hrs · 11,861 cycles
LT FUSELAGE LOWER CTR UNDERWING BARREL CHORD AT STA 1305.250 FOUND CRACKED. REPAIRED IAW EA1-5710-137957.
Part: FRAME — DENTED (ZONE 200) · airframe 55,452 hrs · 11,861 cycles
CABIN - LT STA 1781, LONGERON 12, FRAME FOUND DENT. FRAME REPAIR IAW SRM 53-00-07, FIG 201, REPAIR 2, REV 43 (MAJOR REPAIR).
Part: FRAME — DENTED (ZONE 200) · airframe 55,452 hrs · 11,861 cycles
CABIN - RT STA 1701, LONGERON 12 FRAME FOUND DENTED. FRAME REPAIR IAW SRM 53-00-07, FIG 201, REPAIR 2, REV 43 (MAJOR REPAIR).
Part: FRAME — DENTED (ZONE 200) · airframe 55,452 hrs · 11,861 cycles
CABIN - RT STA 1721, LONGERON 12 FRAME FOUND DENTED. FRAME REPAIR IAW SRM 53-00-07, FIG 201. REPAIR 2 REV 43 (MAJOR REPAIR).
Part: FRAME — DENTED (ZONE 200) · airframe 55,452 hrs · 11,861 cycles
CABIN - LT STA 1681, LONGERON 12, FRAME FOUND DENTED. FRAME REPAIR IAW SRM 53-00-07, FIG 201, REPAIR 2, REV 43 (MAJOR REPAIR).
Part: LONGERON SPLICE — CRACKED (ZONE 200) · airframe 55,452 hrs · 11,861 cycles
CRACK FOUND DURING X-RAY INSP AT STA 6-100 LONGERON 1L SPLICE. CRACK LENGTH IS APPROX 1.3750". LONGERON SPLICE REPLACED IAW SRM 51-33-01, REV 43 (MAJOR REPAIR).
Part: FITTING — CRACKED (LT PYLON) · airframe 55,452 hrs · 11,861 cycles
CRACK INDICATION FOUND DURING ULTRASONIC INSP ON SECOND FASTENER HOLE ON LT SIDE PYLON CARRY THROUGH CAP COMMON TO AFT FLANGE OF NR 4 BANJO. REPAIR IAW EA 1-5530-137966 TITLE: "STABILIZERS - VERTICAL STABILIZER - NR 4 BANJO FITTING (REAR SPAR) AND CARRY THROUGH CAP RAPAIR" (MAJOR REPAIR).
Part: SKIN — CRACKED (LT WING) · airframe 55,452 hrs · 11,861 cycles
CRACK - LT WING ANTI ICE TELESCOPIC DUCT DOOR CUTOUT AT XOS464. REPAIR IAW SRM 57-40-01, FIG 201, REV 43. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 110.
2009
Part: CONTROL PANEL — FAILED (COCKPIT) · airframe 52,654 hrs · 11,249 cycles
ALL FIRE TONES AND LIGHTS ANNUNCIATED FOR 10 SEC THEN APU FIRE WITH TONE STAYED ON FOLLOWED BY SMOKE FROM APU PANEL, PULLED APU FIRE HANDEL & DISCHARGED BOTH BOTTLES. APU NOT RUNNING. DECLARED EMERGENCY INTO HKG. FIRE ALERT REMAINS. REMOVED APU FIRE CONTROL PANEL, FOUND SMOKE ODOR FROM PANEL PER MM 49-04-01 & ALSO UNLATCHED ALL SURROUNDING PANELS FOR VISUAL INSPECTION WITH ELECTRICAL POWER ON, NO SIGN OF BURNING FOUND. APU FIRE DET RESISTANCE CHECKED PER SSM 26-12-0, BOTH LOOPS WITHIN LIMITS. APU FIRE CONTROL PANEL FROM ANOTHER ACFT CHECKED OK, R&R APU FIRE CONTROL PANEL PER MM 49-04-01, AFTER REPLACEMENT APU FIRE HANDLE RED LIGHT STAY ON, R&R APU FDCU PER MM 26-12-04 PASSED & LIGHT CHECKED NORMAL. R&R BOTH NR 1 & 2 APU/ENG 2 BOTTLE CONTAINER PER MM 26-21-01-4 & TESTED OK PER MM 26-21-01-5. INSPECTED APU COMP ALL NORMAL. RAN APU & 3 ENG PER JRH. ALL IND NORMAL.
2008
Part: SUPPORT FITTING — CRACKED (ZONE 200) · airframe 49,774 hrs · 10,621 cycles
CRACK INDICATION FOUND DURING HFEC OPEN HOLE INSPECTION ON EXISTING 0.460 INCH HOLES AT MAIN CARGO DOOR LOWER JAMB NR 6 SUPPORT FITTING AT HOLES A, B, C AND D. MAIN CARGO DOOR LOWER JAMB NR 6 SUPPORT FITTING AT HOLES A, B, C AND D BUSHING REPAIR CARRIED OUT AS PER SRM 53-50-00 FIG. 10 VOL. 1. SUPPORT FITTING REMOVED AND REPLACED AS PER SRM 51-33-01 VOL. II. REPAIR CLASSIFIED AS MAJOR AS PER FEDEX GMM 6- 2-100.
Part: SUPPORT FITTING — CRACKED (ZONE 200) · airframe 49,774 hrs · 10,621 cycles
CRACK INDICATION FOUND DURING HFEC OPEN HOLE INSPECTION ON EXISTING 0.460 INCH HOLES AT MAIN CARGO DOOR LOWER JAMB NR 2 SUPPORT FITTING AT HOLES B, C AND D. MAIN CARGO DOOR LOWER JAMB NR 2 SUPPORT FITTING AT HOLES B, C, AND D BUSHING REPAIR CARRIED OUT AS PER SRM 53-50-00 FIG 10 VOL 1. REPAIR CLASSIFIED AS MAJOR AS PER FEDEX GMM 6-2-100.
Part: FITTING — CRACKED (ZONE 200) · airframe 49,774 hrs · 10,621 cycles
CRACK INDICATION FOUND DURING HFEC OPEN HOLE INSPECTION ON EXISTING 0.460 INCH HOLES AT MAIN CARGO DOOR LOWER JAMB NR 5 SUPPORT FITTING HOLES A, B, C AND D. MAIN CARGO DOOR LOWER JAMB NR 5 SUPPORT FITTING AT HOLES A, B, C AND D BUSHING. REPAIR CARRIED OUT AS PER SRM 53-50-00 FIG 10 VOL 1. SUPPORT FITTING REMOVED AND REPLACED AS PER SRM 51-33-01 VOL II. REPAIR CLASSIFIED AS MAJOR AS PER FEDEX GMM 6-2-100.
Part: SUPPORT FITTING — CRACKED (ZONE 200) · airframe 49,774 hrs · 10,621 cycles
CRACK INDICATION FOUND DURING HFEC OPEN HOLE INSPECTION ON 0.460 INCH HOLES AT MAIN CARGO DOOR LOWER JAMB NR 1 SUPPORT FITTING AT HOLES A, C AND D. MAIN CARGO DOOR LOWER JAMB NR 1 SUPPORT FITTING AT HOLES A, C AND D BUSHING REPAIR CARRIED OUT AS PER SRM 53-50-00 FIG 10 VOL 1. SUPPORT FITTING REMOVED AND REPLACED AS PER SRM 51-33-01 VOL II. REPAIR CLASSIFIED AS MAJOR AS PER FEDEX GMM 6-2-100.
Part: SUPPORT FITTING — CRACKED (ZONE 200) · airframe 49,774 hrs · 10,621 cycles
CRACK INDICATION FOUND DURING HFEC OPEN HOLE INSPECTION ON EXISTING 0.460 INCH HOLES AT MAIN CARGO DOOR LOWER JAMB NR 4 SUPPORT FITTING AT HOLES A, B, C AND D. MAIN CARGO DOOR LOWER JAMB NR 4 SUPPORT FITTING AT HOLES A, B, C AND D BUSHING. REPAIR CARRIED OUT AS PER SRM 53-50-00 FIG 10 VOL I. SUPPORT FITTING REMOVED AND REPLACED AS PER 51-33-01 VOL II. REPAIR CLASSIFIED AS MAJOR AS PER FEDEX GMM 6-2-100.
Part: SUPPORT FITTING — CRACKED (ZONE 200) · airframe 49,774 hrs · 10,621 cycles
CRACK INDICATION FOUND DURING HFEC OPEN HOLE INSPECTION ON EXISTING 0.460 INCH HOLES AT MAIN CARGO DOOR LOWER JAMB NR 3 SUPPORT FITTING AT HOLES A, B, C AND D. MAI. REPAIR CARRIED OUT AS PER SRM 53-50-00 FIG 10 VOL 1. REPAIR CLASSIFIED AS MAJOR AS PER FEDEX GMM 6-2-100.
Part: SUPPORT FITTING — CRACKED (ZONE 200) · airframe 49,774 hrs · 10,621 cycles
CRACK INDICATION FOUND DURING HFEC OPEN HOLE INSPECTION ON EXISTING 0.460 INCH HOLES AT MAIN CARGO DOOR LOWER JAMB NR 7 SUPPORT FITTING AT HOLES A, B, C AND D. MAIN CARGO DOOR LOWER JAMB NR 7 SUPPORT FITTING AT HOLES A, B, C AND D BUSHING. REPAIR CARRIED OUT AS PER SRM 53-50-00 FIG 10 VOL 1. SUPPORT FITTING REMOVED AND REPLACED AS PER SRM 51-33-01 VOL II. REPAIR CLASSIFIED AS MAJOR AS PER FEDEX GMM 6-2-100.
Part: SKIN — CRACKED (ZONE 600) · airframe 49,774 hrs · 10,621 cycles
RT WING DROOP LEADING EDGE TOP SURFACE FOUND CRACKED. REPAIR CARRIED OUT AT RT WING DROOP LEADING EDGE TOP SURFACE AS PER SRM 57-10-00 FIG 30 VOL I. REPAIR CLASSIFIED AS MINOR AS PER FEDEX GMM 6-2-100.
2007
Part: FRAME — DAMAGED (ZONE 200) · airframe 45,408 hrs · 9,667 cycles
UPPER CARGO COMPARTMENT, FRAME STA 535 FOUND WITH SCRATCHES AT LONGERON 23 LT. [4-27-07] REPAIR CARRIED OUT AS PER SRM 53-5-03. REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100.
Part: FRAME — DAMAGED (ZONE 200) · airframe 45,408 hrs · 9,667 cycles
UPPER CARGO COMPARTMENT, FRAME STA 535 FOUND WITH SCRATCHES AT LONGERON 19 LT. [4-27-07] REPAIR CARRIED OUT AT UPPER CARGO COMPARTMENT, FRAME STA 535 AT LONGERON 19 LT AS PER SRZ 53-503. REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100.
Part: SKIN — CRACKED (RT WING) · airframe 45,408 hrs · 9,667 cycles
RIGHT WING, NR 4 LEADING EDGE SLAT O/B TRACK LOWER CUTOUT I/B CORNER FOUND CRACKED. [SUP 04-30-07] REPAIR CARRIED OUT AS PER SRM 57-10-00 FIGURE 21 VOLUME I. REPAIR CLASSIFIED AS MINOR AS PER GMM 6-2-100.
Part: STRINGER — CRACKED (ZONE 500) · airframe 45,408 hrs · 9,667 cycles
CRACK FOUND AT STRINGER END 10L (XORS 760), APPROX 9" LENGTH ON LT WING TANK DURING HFEC INSPECTION. LT WING TANK STRINGER END 10L (XORS 760) REPAIR CARRIED OUT AS PER SRM 57-20-00 FIG.10 VOL I. REPAIR CLASSIFIED AS MAJOR REPAIR AS PER FEDEX GMM 6-2-100.
Part: STRINGER — CRACKED (ZONE 600) · airframe 45,408 hrs · 9,667 cycles
CRACK FOUND AT STRINGER END 41R (XORS 704) APPROX 1" IN LENGTH IN BETWEEN 2ND AND 3RD FASTENER ON RT WING TANK DURING HFEC INSPECTION. RT WING TANK STRINGER END 41R (XORS 704) REPAIR CARRIED OUT AS PER SRM 57-20-00 FIG. 10 VOL I. REPAIR CLASSIFIED AS MAJOR AS PER FEDEX GMM 6-2-100.
2006
Part: CABLE — CONTAMINATED (MLG) · airframe 42,036 hrs · 8,927 cycles
ON DEPARTURE, HKG GEAR RETRACTION NG AND LT MLG SLOW RETRACTION (45 SEC). ARRIVAL ANC GEAR EXTENSION WOULD NOT GO DOWN. LIFTED GEAR HANDLE W/FORCE, EXTENDED GEAR. LANDED UNEVENTFULLY. FOUND FAIRLEAD PULLED OUT OF PRESSURE SEAL AND STUCK TO LANDING GEAR RETRACTION/EXTEND CONTROL CABLE DUE TO EXCESSIVE CORROSION PREVENTATIVE COMPOUND HARDENED AND BALLED UP ON CABLE. CLEANED 4 CABLES, FAIRLEADS AND PRESSURE SEALS ON LANDING GEAR CONTROL CABLES ABOVE RT WHEELWELL LUBED SAME. PERFORMED LANDING GEAR CONTROL EXTENSION/TEST ALL TESTS NORMAL PER MM GEAR HANDLE MOVED FREELY WITH NO BINDING DURING EXTEND OR RETRACT POSITION. RETURNED TO SERVICE.
2005
Part: STRUCTURE — CORRODED (RT WING) · airframe 40,789 hrs · 8,609 cycles
DURING PASSENGER TO FRIEGHT CONVERSION, FOUND THE SEQUENT PUFFIN CORROSIONS ON THE UPPER RIGHT WING SKIN IN THE FOLLOWING ZONE: FROM WING CROSS-SECTION STA XORS 402 TO XORS 433. NOTE: THE UPPER MENTIONED CORROSIONS HAVE BEEN INDIVIDUALIZED IN 2 POINT. BLENDOUT ALL EVIDENCE OF CORROSION AS PER SRM 57-10-00 FIG 32. MEASURE AND RECORD REWORKED POSITION, DIMENSIONS AND SKIN RESIDUAL THICKNESS. REWORKED IS IN LIMITS FOR SRM 57-10-00 FIG 32. PROTECT AREA PER SRM 51-21-02.
Part: STRUCTURE — CORRODED (LT WING) · airframe 40,789 hrs · 8,609 cycles
DURING PASSENGER TO FRIEGHT CONVERSION, FOUND THE SEQUENT PUFFIN CORROSIONS ON THE UPPER LEFT WING SKIN IN THE FOLLOWING ZONES: FROM WING CROSS-SECTION STA XORS 97 TO XORS 1042. NOTE: THE UPPER MENTIONED CORROSIONS HAVE BEEN INDIVIDUALIZED IN 38 POINT. BLENDOUT ALL EVIDENCE OF CORROSION AS PER SRM 57-10-00 FIG 32. MEASURE AND RECORD REWORKED POSITION, DIMENSIONS AND SKIN RESIDUAL THICKNESS. REWORKED AREA ARE ACCEPTABLE PER SRM 57-10-00 FIG 32 AND BOEING MESSAGE N 1-111785997-4. PROTECT AREA PER SRM 51-21-02.
Part: SEAT TRACK — CHAFED (ZONE 200) · airframe 40,776 hrs · 8,606 cycles
STA 939 TO 969 RT MOST OUTBOARD SEAT TRACK AREAS FOUND CHAFED MARKS. FABRICATED & REPAIRED AS PER SRM 53-70-00 FIG 1 VOL I.
Part: SKIN — CHAFED (NR 3 SLAT) · airframe 40,776 hrs · 8,606 cycles
LEFTHAND WING NR 3 SLAT, LOWER SURFACE, MOST LOWER, FAIRING FOUND CHAFING DAMAGE AGAINST THE FAIRING DOOR OF THE ANTI-ICE TELESCOPIC DUCT. LEFTHAND WING NR 3 SLAT, LOWER SURFACE REPAIRED AS PER FEDEX EA 1-5740-78105. TITLE: WINGS - LEADING EDGE AND LEADING EDGE DEVICES, NR 3 SLAT SKIN / XOS=467.100 / REPAIR.
Part: BULKHEAD — CORRODED (ZONE 100) · airframe 40,776 hrs · 8,606 cycles
WASTE TANK COMPT - AFT PRESSURE BULKHEAD CORRODED 16 INCHES BELOW CABIN FLOOR LBL 62, IMMEDIATELY BELOW FUEL LINE FEED THROUGH. WASTE TANK COMPT - AFT PRESSURE BULKHEAD BELOW CABIN FLOOR LBL 62, IMMEDIATELY BELOW FUEL LINE FEED THROUGH CORRODED PANEL REMOVED AS PER SRM 51-35-01 VOL II & SRM 51-33-01 VOL II. FABRICATED PANEL AS PER DRAWING AJC7238 AND INSTALLED AS PER SRM 51-35-01 VOL II & SRM 51-33-01 VOL II.
Part: SKIN — DAMAGED (ZONE 100) · airframe 40,776 hrs · 8,606 cycles
STA 595 BELOW LONGERON 38 RT SKIN SPLICE LOCK FASTENER HOLES FOUND MOUNTED WITH A DOUBLER & 06 EA NUT PLATES. SKIN PANEL REPLACEMENT WAS COMPLIED WITH.
Part: SKIN — DAMAGED (ZONE 100) · airframe 40,776 hrs · 8,606 cycles
EXTERIOR SURFACE STRAP AT STA 5-121, L48R EXISTING FASTENER HOLE FOUND ELONGATED. REPAIRED AS PER FEDEX EA 1-5310-78111.
Part: SKIN — DAMAGED (ZONE 100) · airframe 40,776 hrs · 8,606 cycles
STA 595 BELOW LONGERON 42 RT SKIN SPLICE FOUND MOUNTED WITH A 01EA DOUBLER & 06 EA NUT PLATES. SKIN PANEL REPLACEMENT WAS COMPLIED WITH.
Part: SKIN — DAMAGED (ZONE 100) · airframe 40,776 hrs · 8,606 cycles
STA 595 BETWEEN LONGERON 45 RT TO 46 RT NOSE JACK FITTING HI-LOK FASTENER HOLES FOUND MOUNTED WITH 06 EA NUT PLATES. SKIN PANEL REPLACEMENT WAS COMPLIED WITH.
Part: SKIN — DAMAGED (ZONE 100) · airframe 40,776 hrs · 8,606 cycles
STA Y=595 FORWARD OF LONGERON 48R END SPLICE LOWER FUSELAGE SKIN. FOUND WITH A "FIGURE 8" OVERSIZE FASTENER HOLE.
Part: SEAT TRACK — CORRODED (ZONE 200) · airframe 40,776 hrs · 8,606 cycles
MAIN DECK SEAT TRACK LBL 107 CORRODED AT STA 1966. REMOVED AND REPLACED WITH NEW SEAT TRACK FROM STA 1531 TO STA 2007 LBL 107 AS PER SRM 51-33-01 VOL II AND SRM 51-35-01 VOL II.
Part: LONGERON — CRACKED (ZONE 100) · airframe 40,776 hrs · 8,606 cycles
CENTER CARGO LONGERON CRACKED AT STA 1538 L45L. REPAIR CARRIED OUT AT CENTER CARGO LONGERON AT STA 1538 L45L AS PER SRM 53-10-00 FIG 1 VOL I.
Part: SKIN — DAMAGED (ZONE 100) · airframe 40,776 hrs · 8,606 cycles
APU EXHAUST AREA UPPER DOOR HINGE FUSELAGE SKIN FOUND WITH REPAIR. EXISTING REPAIR ON APU EXHAUST AREA UPPER DOOR HINGE FUSELAGE SKIN REMOVED AS PER SRM 51-35-01 VOL I. NEW REPAIR DOUBLERS FABRICATED AND INSTALLED AS PER SRM 53-20-00, FIG 4 VOL I & SRM 53-00-01 FIG 5 VOL II.
Part: LONGERON — CORRODED (ZONE 100) · airframe 40,776 hrs · 8,606 cycles
CENTER CARGO LONGERON 47 LT CORRODED AT STA 5-111 TO 5-121. CENTER CARGO LONGERON 47 LT CORRODED AT STA 5-111 TO 5-121 LONGERON REPAIR CARRIED OUT AS PER SRM 53-10-00 FIG 1, VOL I.
Part: SKIN — CHAFED (ZONE 400) · airframe 40,776 hrs · 8,606 cycles
APU EXHAUST DOOR ACTUATOR AT CUTOUT FOUND PREVIOUS REPAIR CHAFED. PREVIOUS REPAIR ON APU EXHAUST DOOR ACTUATOR AT CUTOUT AREA EVALUATED AND FOUND NOT IAW SRM 53-00-01 FIG 5 VOL I. EXISTING DOUBLER FOR REPAIRED APU SKIN AT APU EXHAUST DOOR ACTUATOR CUTOUT AREA REMOVED AND REPLACED AS PER SRM 51-35-01 VOL II.
Part: SEAT TRACK — WORN (ZONE 200) · airframe 40,776 hrs · 8,606 cycles
MAIN DECK SEAT TRACK RBL 107 FOUND WITH SCRATCHES AT STA 1189 TO STA 1223. DAMAGED SEAT TRACK AT MAIN DECK STA 1189 TO STA 1223 RBL 107 CUT AS PER SRM 53-70-00 FIG 1 VOL I & REMOVED AS PER SRM 51-31-01 VOL II. REPAIR SEAT TRACK & SPLICE, FABRICATED AND INSTALLED AS PER SRM 53-70-00 FIG 1 VOL I & SRM 51-31-01 VOL II.
Part: SEAT TRACK — DAMAGED (ZONE 200) · airframe 40,776 hrs · 8,606 cycles
CABIN SEAT TRACK AT STA 791 LBL 27.5 FOUND TO HAVE BOLTS INSTALLED WRONGLY. SEAT TRACK AT STA 740 TO STA 815 REMOVED AS PER SRM 51-31-01 VOL II. REPAIR SEAT TRACK & SPLICE FABRICATED AND INSTALLED AS PER SRM 53-70-00 FIG 1 VOL I & SRM 51-31-01 VOL II.
Part: SEAT TRACK — DAMAGED (ZONE 200) · airframe 40,776 hrs · 8,606 cycles
SEAT TRACK AT CABIN STA 791 LBL 41.5 HAVE BOLTS INSTALLED WRONG. SEAT TRACK AT CABIN STA 791 LBL 41.5 REMOVED AS PER SRM 53-70-00 FIG 1 VOL I & SRM 51-31-01 VOL II. REPAIR SEAT TRACK & SPLICE, FABRICATED & INSTALLED AS PER SRM 53-70-00 FIG 1 VOL I & SRM 51-31-01 VOL II.
Part: SEAT TRACK — WORN (ZONE 200) · airframe 40,776 hrs · 8,606 cycles
MAIN DECK SEAT TRACK RBL 107 FOUND WITH SCRATCHES AT STA 5-70 TO STA 1531. DAMAGED SEAT TRACK AT MAIN DECK RBL 107, STA 5-70 TO STA 1531 REMOVED AS PER SRM 51-31-01 VOL II. REPAIR SEAT TRACK, FABRICATED AS PER DWG A5A7084 & INSTALLED AS PER SRM 53-70-00 FIG 1 VOL I & SRM 51-31-01 VOL II.
Part: SEAT TRACK — DAMAGED (ZONE 100) · airframe 40,776 hrs · 8,606 cycles
SEAT TRACK AT CABIN STA 791 LBL 8.5 HAVE BOLTS INSTALLED WRONG. SEAT TRACK AT CABIN STA 745 TO STA 815 LBL 8.5 REMOVED AS PER SRM 51-31-01 VOL II. REPAIR SEAT TRACK, FABRICATED & INSTALLED AS PER SRM 53-70-00 FIG 1 VOL I & SRM 51-31-01 VOL II.
Part: INTERCOSTAL — CORRODED (ZONE 200) · airframe 40,776 hrs · 8,606 cycles
FLOOR STRUCTURE INTERCOSTAL LOWER CHORD CORRODED AT STA 1821 TO STA 1841, LBL 27. REMOVED AS PER SRM 51-35-01 VOL II. NEW INTERCOSTAL FABRICATED AS PER DWG ACA7582 AND INSTALLED AS PER SRM 51-35-01 VOL II.
Part: SPLICE — CORRODED (ZONE 100) · airframe 40,776 hrs · 8,606 cycles
LONGERON 49 SPLICE LT CORRODED AT STA 5-119. CORROSION REMOVED AS PER SRM 51-21-01 VOL II.
Part: LONGERON — DAMAGED (ZONE 100) · airframe 40,776 hrs · 8,606 cycles
CENTER ACCESSORY COMPARTMENT FORWARD OF DOOR AT LONGERON L46 LONGERON SPLICE FOUND DAMAGED. CENTER ACCESSORY COMPARTMENT FORWARD OF DOOR AT LONGERON L46 DAMAGED LONGERON SPLICE REMOVED AS PER SRM 51-33-01 VOL II AND SRM 53-00-01 VOL I. LONGERON SPLICE FABRICATED AS PER SRM 53-10-00 VOL I AND INSTALLED AS PER SRM 51-33-01 VOL II AND SRM 53-00-01 VOL I.
Part: LONGERON — CORRODED (ZONE 100) · airframe 40,776 hrs · 8,606 cycles
CENTER ACCESSORY COMPARTMENT LONGERON RT 47 UNDER STEP IS CORRODED THROUGH. REPAIR LONGERON AND SPLICE FABRICATED AS PER SRM 53-10-00 VOL I FIG 2 AND INSTALLED AS PER SRM 53-10-00 VOL I FIG 2.
Part: SPLICE — DAMAGED (ZONE 100) · airframe 40,776 hrs · 8,606 cycles
CENTER ACCESSORY COMPARTMENT FORWARD OF DOOR AT LONGERON L47 LONGERON SPLICE DAMAGED. CENTER ACCESSORY COMPARTMENT FORWARD OF DOOR AT LONGERON L47 DAMAGED LONGERON SPLICE REMOVED AS PER SRM 51-33-01 VOL II AND SRM 51-35-01 VOL II. LONGERON SPLICE FABRICATED AS PER SRM 53-00-01 FIG 2 VOL I AND INSTALLED AS PER SRM 51-33-01 VOL II AND SRM 51-35-01 VOL II.
Part: LONGERON — CORRODED (ZONE 100) · airframe 40,776 hrs · 8,606 cycles
CENTER ACCESSORY COMPARTMENT AT STA 6-90 LONGERON R49 INSIDE STEP HAS CORROSION. CENTER ACCESSORY COMPARTMENT AT STA 6-90 LONGERON R49 INSIDE STEP REMOVED AS PER SRM 51-33-01 VOL II AND SRM 51-35-01 VOL II. LONGERON SPLICE FABRICATED AS PER DRAWING AGA7026 AND INSTALLED AS PER SRM 51-33-01 VOL II AND SRM 51-35-01 VOL II.
Part: STIFFENER — CORRODED (ZONE 200) · airframe 40,776 hrs · 8,606 cycles
FUSELAGE EXTERIOR, STIFFENER STA 1256 TO STA 1301 ON FUSELAGE SKIN FOUND CORRODED. COMPLIED WITH FEDEX EA 1-5310-78117.
Part: SKIN — CORRODED (ZONE 300) · airframe 40,776 hrs · 8,606 cycles
RT HORIZONTAL STABILIZER, STA XE159 TO 176.5 RIB 12 TO 13 INTERSPAR LOWER MID PLANK FOUND CORRODED. CORROSION REMOVED AS PER SRM 51-21-01. OUT OF LIMITS AS PER SRM 55-00-01. REPAIRED AS PER EA 1-5510-78108.
Part: SKIN — DAMAGED (ZONE 500) · airframe 40,776 hrs · 8,606 cycles
LT WING, NR 2 SLAT EXTERIOR, FOUND 2EA DOUBLER REPAIR AND 1EA CUTOUT REPAIR. REMOVED AND REPLACED AS PER AMM 27-80-20 AND FUNCTIONAL CHECK CARRIED OUT AS PER AMM 27-80-00, FOUND SATISFACTORY.
Part: SKIN — MISREPAIRED (ZONE 100) · airframe 40,776 hrs · 8,606 cycles
FORWARD CARGO STA 602 TO STA 615 BETWEEN LONGERON LT 44 AND LT46 IS A REPAIR THAT DOES NOT LOOK TO BE FROM THE SRM. REPAIR EVALUATED AND FOUND NOT CONFORMING TO SRM CHAPTER 53. REPAIR CARRIED OUT AS PER FEDEX EA 1-5330-77979.
Part: SPAR — CORRODED (ZONE 300) · airframe 40,776 hrs · 8,606 cycles
RIGHT HAND HORIZONTAL STABILIZER: STA XE159 RIB NR 12 LOWER FRONT TO REAR SPAR FOUND CORRODED. REPAIRED IAW FEDEX EA 1-5510-78109.
Part: LONGERON — CORRODED (ZONE 100) · airframe 40,776 hrs · 8,606 cycles
WASTE TANK COMPT LONGERON 41A LT CORRODED AT STA 1965 - 1967. REMOVED AND REPLACED AS PER SRM 51-31-01 VOL II.
Part: PANEL — CORRODED (ZONE 300) · airframe 40,776 hrs · 8,606 cycles
LT HORIZONTAL STAB LEADING EDGE ACCESS PANEL 331BT LOWER OUTBOARD MOUNTING LUG FOUND WITH SURFACE CORROSION. CORROSION REPAIRED AS PER FEDEX EA 1-5510-78106,
2004
Part: SKIN — MISREPAIRED (ZONE 100) · airframe 40,776 hrs · 8,606 cycles
FORWARD CARGO RT APPROX STA 620, A REPAIR THAT GOES FROM LONGERON 49R TO 40R NEEDS INVESTIGATION. EVALUATED AND FOUND NOT CONFORMING TO SRM CHAPTER 53. REPAIR CARRIED OUT AS PER FEDEX EA 1-5330-77979,
Part: SKIN — DELAMINATED (ZONE 300) · airframe 40,776 hrs · 8,606 cycles
RIGHT HAND INBOARD ELEVATOR OUTBOARD UPPER AND LOWER SURFACES (TRAILING EDGE) FOUND DELAMINATED. REMOVED AND RE-INSTALLED AFTER REPAIR AS PER AMM 27-30-20. ELEVATOR RANGE OF MOVEMENT TEST CARRIED OUT AS PER AMM 27-30-00 FOUND SATISFACTORY.
Part: STRUCTURE — DELAMINATED (ZONE 700) · airframe 40,776 hrs · 8,606 cycles
CENTER LANDING GEAR WORK PLATFORM AFT CENTER JOINT PIECE (UPPER) FOUND DELAMINATED. REPAIRED AS PER SRM 51-43-01 VOL II AND PAINTED AS PER SRM 51-21-02 VOL II. INSTALLED AS PER AMM 32-17-06.
Part: CHANNEL — DAMAGED (ZONE 500) · airframe 40,776 hrs · 8,606 cycles
LEFT HAND WING NR 2 TANK NR 531 AT CUTOUT GANG CHANNEL FOUND DAMAGED. REMOVED DAMAGED GANG CHANNEL AS PER SRM 51-31-01 VOL II. FABRICATED BUSHING AS PER SRM 51-73-00 VOL II AND INSTALLED AS PER SRM 51-73-00 VOL II. INSTALLED NEW GANG CHANNEL AS PER SRM 51-42-04.
Part: STRUCTURE — BROKEN (CENTER CARGO BAY) · airframe 40,776 hrs · 8,606 cycles
CENTER CARGO FLOOR STRUCTURE BROKEN AT STA 1701 LBL 32. REPAIRED AS PER SRM 53-00-01 VOL I FIG 7 SHEET 7, REPAIR ANGLE AND FILLER FABRICATED AS PER SRM 53-00-01 FIG 7 SHEET 7 VOL I AND DOUBLER INSTALLED AS PER SRM 51-33-01 VOL II.
Part: BULKHEAD — MISDRILLED (ZONE 200) · airframe 40,776 hrs · 8,606 cycles
MAIN DECK, BULKHEAD HEAD'S WEB AT STA 2007 FOUND WITH EXISTING HOLES AT LBL 27.5 AFTER TEE CHORD REMOVED FOR REPLACEMENT. EXISTING DOUBLE HOLES AT LBL 20 AFTER TEE CHORD EVALUATED AND FOUND NOT IN ACCORDANCE WITH SRM CHAPTER 53. REPAIR CARRIED OUT AS PER FEDEX EA 1-5310-78099.
Part: RUB STRIP — CORRODED (ZONE 500) · airframe 40,776 hrs · 8,606 cycles
LEFT HAND WING - NR 2 TANK NR 531 AT CUTOUT RUB STRIP FOUND CORRODED. REMOVED DAMAGED RUB-STRIP AS PER SRM 51-31-01 VOL II AND INSTALLED NEW RUB-STRIP AS PER SRM 51-42-04 VOL II AND SRM 51-35-01 VOL II AT LT WING NR 2 TANK 531AT CUT-OUT.
Part: SPAR CAP — CORRODED (HORIZ STAB) · airframe 40,776 hrs · 8,606 cycles
HORIZONTAL STABILIZER RIGHT HAND UPPER FORWARD SPAR CAP NR 1R BARREL NUT BORE CORROSION REWORKED FOUND EXCEEDED LIMIT. REPAIRED AS PER FEDEX EA 1-5510-78096.
Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 40,776 hrs · 8,606 cycles
STA Y=832 TO 919 RIGHT HAND NR 3 SEAT TRACK AREAS FOUND WITH CORROSION. REPIARED IAW SRM 53-70-00 FIG 1 VOL I.
Part: SEAT TRACK — SCRATCHED (FUSELAGE) · airframe 40,776 hrs · 8,606 cycles
MAIN DECK, SEAT TRACK RBL 107 FOUND WITH SCRATCHES AT STA 1391 TO STA 1471. REPAIRED SEAT TRACK & SPLICE FABRICATED AS PER SRM 53-70-00.
Part: SEAT TRACK — SCRATCHED (FUSELAGE) · airframe 40,776 hrs · 8,606 cycles
MAIN DECK, SEAT TRACK RBL 107 FOUND WITH SCRATCHES AT STA 1544 TO STA 5-93.
Part: SEAT TRACK — SCRATCHED (FUSELAGE) · airframe 40,776 hrs · 8,606 cycles
MAIN DECK, SEAT TRACK RBL 107 FOUND WITH SCRATCHES AT STA 1541 TO STA 5-73. REMOVED AS PER SRM 51-31-01 VOL II. REPAIR SEAT TRACK FABRICATED AS PER DRAWING A5A7084 & INSTALLED AS PER SRM 53-70-00 FIG 1 VOL I & SRM 51-31-01 VOL II.
Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 40,776 hrs · 8,606 cycles
MAIN DECK, SEAT TRACK RBL 77 CORRODED AT STA 1841 TO STA 1887. CORRODED SEAT TRACK REMOVED AS PER SRM 53-70-00. FABRICATED REPAIR SEAT TRACK AND SPLICE AS PER FIG 1 & FIG 7 OF SRM 53-70-00 AND INSTALLED AS PER SRM 51-31-01& 53-70-00.
Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 40,776 hrs · 8,606 cycles
MAIN DECK, SEAT TRACK RBL 107 CORRODED AT STA 1421. REPAIRED AS PER SRM 53-70-00 FIG I & SRM 51-31-01 VOL II. REFER TO SNRM N2547 FOR WORK DETAILS.
Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 40,776 hrs · 8,606 cycles
MAIN DECK, SEAT TRACK RBL 107 CORRODED AT STA 1310 TO STA 1361. REMOVED AS PER SRM 51-31-01.
Part: SPAR CAP — CORRODED (HORIZ STAB) · airframe 40,776 hrs · 8,606 cycles
EMPENNAGE: HORIZONTAL STABILIZER RIGHT HAND UPPER SPAR CAP NR 36R BARREL NUT BORE CORROSION REWORKED FOUND EXCEEDED LIMIT. REPAIRED AS PER FEDEX EA 1-5510-78096.
Part: SPAR CAP — CORRODED (HORIZ STAB) · airframe 40,776 hrs · 8,606 cycles
EMPENNAGE: HORIZONTAL STABILIZER LEFT HAND UPPER FORWARD SPAR CAP NR 1L BARREL NUT BORE CORROSION REWORKED FOUND EXCEEDED LIMIT.
Part: SKIN PANEL — CORRODED (FUSELAGE) · airframe 40,776 hrs · 8,606 cycles
AFT ACCESSORY COMPT: STA Y=2140 TO 2158, X50, 6 EACH NUT PLATES ATTACHMENT FUSELAGE SKIN PANELS FOUND WITH CORROSION. CORROSION ON SKIN PANEL BLENDED THRU AS PER SRM 51-21-01, VOL II AND FOUND EXCEEDED LIMIT AS PER SRM 53-00- 01 FIG 1A VOL I.
Part: DOOR FRAME — CORRODED (FUSELAGE) · airframe 40,776 hrs · 8,606 cycles
AFT CARGO DOOR AFT JAMB CORRODED AROUND FASTENERS 5 PLACES. AFT CARGO DOOR AFT JAMB CORRODED AREA REPAIR CARRIED OUT AS PER SRM 53-00-01 VOL I.
Part: SKIN PANEL — CORRODED (FUSELAGE) · airframe 40,776 hrs · 8,606 cycles
AFT ACCESSORY COMPT: STA Y=2157 TO 2163, X50, 2 NUT PLATE ATTACHMENT FUSELAGE SKIN PANELS FOUND WITH CORROSION. REPAIR CARRIED OUT AS PER FEDEX EA 1-5330-78102.
Part: SEAT TRACK — DAMAGED (ZONE 200) · airframe 40,776 hrs · 8,606 cycles
MAIN DECK, SEAT TRACK RBL 107 FOUND WITH SCRATCHES AT STA 1665 TO STA 1721. REPLACEMENT CARRIED OUT AT MAIN DECK RBL 107 STA 1531 TO STA 2007
Part: SPAR CAP — CORRODED (HORIZ STAB) · airframe 40,776 hrs · 8,606 cycles
EMPENNAGE: HORIZONTAL STABILIZER RIGHT HAND UPPER SPAR CAP NR 36R BARREL NUT BORE CORROSION REWORKED FOUND EXCEEDED LIMIT. REPAIRED AS PER FEDEX EA 1-5510-78096.
Part: SEAT TRACK — DAMAGED (ZONE 200) · airframe 40,776 hrs · 8,606 cycles
STA 836 LT NR 3 SEAT TRACK EXISTING FLANGE REPAIR FOUND NOT CONFORMING TO SRM STANDARD. REPAIRED SEAT TRACK & SPLICE FABRICATED AS PER SRM 53-70-00.
Part: SEAT TRACK — MISREPAIRED (ZONE 200) · airframe 40,776 hrs · 8,606 cycles
STA 840 RT NR 1 SEAT TRACK EXISTING FLANGE EXISTING REPAIR FOUND NOT CONFORMING TO SRM STANDARD.
Part: TRUNNION — CRACKED (NLG) · airframe 40,776 hrs · 8,606 cycles
UPON REMOVAL OF NOSE LANDING GEAR FOR BULKHEAD 595 REPAIR FOUND LEFT HAND TRUNNION FITTING (LOWER INBOARD-FORWARD OF BUSHING AREA) WITH A HAIR LINE CRACK. CRACKED AREA REPAIRED AS PER SRM 53-40-00 VOL I FIG 22.
Part: SEAT TRACK — CORRODED (ZONE 200) · airframe 40,776 hrs · 8,606 cycles
STA Y = 840 TO 899 LT NR 2 SEAT TRACK & FLANGE AREAS FOUND WITH CORROSION. REPAIRED IAW SRM 53-70-00 FIG 1 VOL I.
Part: SEAT TRACK — CORRODED (ZONE 200) · airframe 40,776 hrs · 8,606 cycles
STA 840 TO 879 RT NR 1 SEAT TRACK & FLANGE AREAS FOUND WITH CORROSION. CORRODED SEAT TRACK REPAIRED AS PER SRM 53-70-00 FIG 1 VOL I. FABRICATED REPAIR SEAT TRACK PARTS AS PER SRM 53-70-00 FIG 1 VOL I.
Part: SEAT TRACK — CORRODED (ZONE 200) · airframe 40,776 hrs · 8,606 cycles
MAIN DECK - SEAT TRACK RBL 27 CORRODED AT STA 1831 TO STA 1887. SEAT TRACK CUT AND REMOVED AS PER SRM 53-70-00 FIG 1 VOL I. FABRICATED REPAIR SEAT TRACK AND SPLICE AS PER SRM 53-70-00 FIG 1 VOL I AND REPROTECTED AS PER SRM 51-21-01 VOL II. INSTALLED REPAIR SEAT TRACK AND SPLICE AS PER SRM 53-70-00 FIG 1 VOL I & SRM 51-31-01 VOL II..
Part: TRUNNION — CRACKED (NLG) · airframe 40,776 hrs · 8,606 cycles
UPON REMOVAL OF NOSE LANDING GEAR FOR BULKHEAD 595 REPAIR FOUND RIGHT HAND TRUNNION FITTING (LOWER INBOARD-FORWARD OF BUSHING AREA) WITH A HAIR LINE CRACK. REMOVED AS PER SRM 51-33-01 VOL II AND NEW TRUNNION FITTING INSTALLED AS PER SRM 51-33-01 VOL II.
Part: SEAT TRACK — CORRODED (ZONE 200) · airframe 40,776 hrs · 8,606 cycles
STA 859 TO 879 LT MOST OUTBOARD SEAT TRACK FOUND WITH EVIDENCE OF CORROSION. TRIMMED OFF AS PER SRM 53-70-00 FIG 1 VOL I. SEAT TRACK AND SPLICES FABRICATED AS PER SRM 53-70-00 FIG 1 VOL I AND INSTALLED AS PER SRM 53-70-00 FIG 1 VOL I AND SRM 51-31-01 VOL II.
Part: LONGERON — CRACKED (ZONE 100) · airframe 40,776 hrs · 8,606 cycles
CENTER CARGO - LONGERON SPLICE CRACKED AT L46R STA 1531, FOUND AFTER SPLICE REMOVAL. LONGERON SPLICE REMOVED, FABRICATED AND REPLACED AS PER DWG A5A7116 AND SRM 51-33-01 VOL II.
Part: SEAT TRACK — CORRODED (ZONE 200) · airframe 40,776 hrs · 8,606 cycles
STA 832 TO 899 RT NR 2 SEAT TRACK AREAS FOUND WITH CORROSION. REMOVED SEAT TRACK FASTENERS AT MAIN DECK: STA Y = 810 TO STA 910 AS PER SRM 51-31-01 VOL II. SEAT TRACK AT RT NR 2 STA 810 AND STA 910 CUT OUT AS PER SRM 53-70-00 FIG 1 VOL I. FABRICATED REPAIR SEAT TRACK AND SPLICE AS PER SRM 53-70-00 FIG 1 VOL I AND REPROTECTED AS PER SRM 51-21-01 VOL II. INSTALLED REPAIR SEAT TRACK AND SPLICE AS PER SRM 53-70-00 FIG 1 VOL I AND SRM 51-31-01 VOL II.
Part: SEAT TRACK — MISREPAIRED (ZONE 200) · airframe 40,776 hrs · 8,606 cycles
STA 836 LT NR 1 SEAT TRACK EXISTING FLANGE REPAIR FOUND NOT CONFORMING TO SRM STANDARD. REMOVED AS PER SRM 53-70-00 FIG 1 VOL I. FABRICATED REPAIR SEAT TRACK AND SPLICE AS PER SRM 53-70-00 FIG 1 VOL I AND REPROTECTED AS PER SRM 51-21-01 VOL II. REPAIR SEAT TRACK AND SPLICE INSTALLED AS PER 53-70-00 FIG 1 VOL I AND SRM 51-31-01 VOL II.
Part: SEAT TRACK — CORRODED (ZONE 200) · airframe 40,776 hrs · 8,606 cycles
SEAT TRACK RBL 107 CORRODED AT STA 1929 TO STA 2000. REMOVED AND REPLACED WITH NEW SEAT TRACK AS PER SRM 51-31-01 VOL II.
Part: SEAT TRACK — CORRODED (ZONE 200) · airframe 40,776 hrs · 8,606 cycles
MAIN DECK: STA Y = 859 RT NR 2 SEAT TRACK FLANGE EXISTING DOUBLER REPAIR FOUND WITH CORROSION. DOUBLER EVALUATED & FOUND EXCEEDED LIMIT AS PER SRM 53-70-00 FIG.1 VOL I. EXISTING DOUBLER AT MAIN DECK STA Y = 859 RT NR 2 SEAT TRACK FLANGE REMOVED & REPAIRED AS PER SRM 53-70-00 FIG.1 VOL I.
Part: SEAT TRACK — DAMAGED (ZONE 200) · airframe 40,776 hrs · 8,606 cycles
MAIN DECK: STA Y = 859 LT NR 2 SEAT TRACK FLANGE EXISTING REPAIR DOUBLER FOUND WITH KNIFE EDGE. REPAIRED AS PER 53-70-00.
Part: CHANNEL — CORRODED (ZONE 200) · airframe 40,776 hrs · 8,606 cycles
MAIN DECK, HAT SECTION CORRODED AT STA 1821 TO STA 1887, LBL 36. REMOVED AND REPLACED AS PER SRM 51-31-01 VOL II.
Part: CHANNEL — CORRODED (ZONE 200) · airframe 40,776 hrs · 8,606 cycles
MAIN DECK, FLOOR STRUCTURE HAT SECTION CORRODED AT STA 1910 TO STA 2007, RBL 57. REMOVED FROM STA 1887 TO STA 2007, RBL 57 & REPLACED AS PER SRM 51-31-01 VOL II. FOR WORK DETAILS, REFER TO SNRM N3008.
Part: CHANNEL — CORRODED (ZONE 200) · airframe 40,776 hrs · 8,606 cycles
MAIN DECK, HAT SECTION CORRODED AT STA 1887 TO STA 2007, LBL 57. REMOVED AS PER SRM 51-31-01 VOL II. NEW HAT SECTION FABRICATED AS PER DWG AGA 7496 AND INSTALLED AS PER SRM 51-31-01 VOL II.
Part: CHANNEL — CORRODED (ZONE 200) · airframe 40,776 hrs · 8,606 cycles
MAIN DECK, HAT SECTION CORRODED AT STA 1887 TO STA 2007, RBL 24. REMOVED AS PER SRM 51-31-01 VOL II. NEW HAT SECTION FABRICATED AS PER DWG AGA7497 & INSTALLED AS PER SRM 51-31-01 VOL II.
Part: CHANNEL — CORRODED (FUSELAGE) · airframe 40,776 hrs · 8,606 cycles
MAIN DECK, HAT SECTION CORRODED AT STA 1875 TO STA 1887, RBL 36. REMOVED AND REPLACED AS PER SRM 51-31-01 VOL II.
Part: CHANNEL — CORRODED (ZONE 200) · airframe 40,776 hrs · 8,606 cycles
MAIN DECK, FLOOR STRUCTURE HAT SECTION CORRODED AT STA 1821 TO STA 1887, LBL 36. REMOVED AND REPLACED AS PER SRM 51-31-01 VOL II. DUPLICATE OF SNRM N3170.
Part: CHANNEL — CORRODED (FUSELAGE) · airframe 40,776 hrs · 8,606 cycles
MAIN DECK, HAT SECTION CORRODED AT STA 1887 TO STA 1921, RBL 57. REMOVED AS IAW SRM 51-31-01 VOL II. NEW HAT SECTION FABRICATED AS PER DWG AGA 7496 AND INSTALLED IAW SRM 51-31-01 VOL II.
Part: SEAT TRACK — CORRODED (ZONE 200) · airframe 40,776 hrs · 8,606 cycles
MAIN DECK - SEAT TRACK RBL 27 CORRODED AT STA 457 TO STA 467.
Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 40,776 hrs · 8,606 cycles
MAIN DECK - SEAT TRACK RBL 8 CORRODED AT STA 535 TO STA 575. REMOVED AS PER SRM 51-21-01 VOL II. MATERIAL THICKNESS=0.100, MATERIAL REMOVED=0.034, MATERIAL REMAINED=0.066 AND FOUND OUT OF LIMIT AS PER SRM 53-70-00 FIG 3 VOL I. DAMAGED TRACK CUT AS PER SRM 53-70-00 FIG 1 VOL I AND REMOVED AS PER SRM 51-31-01 VOL II. REPAIR SPLICE AND REPAIR SEAT TRACK FABRICATED AS PER SRM 53-70-00 FIG 1 VOL I. REPAIR PARTS INSTALLED AS PER SRM 53-70-00 FIG 1 VOL I AND SRM 51-31-01 VOL II.
Part: LONGERON — CRACKED (ZONE 100) · airframe 40,776 hrs · 8,606 cycles
CENTER CARGO LONGERON 52 SPLICE, AT STA 5-123 FOUND CRACKED. REMOVED AND REPLACED AS PER SRM 51-33-01 VOL II.
Part: STRUCTURE — CORRODED (HORIZ STAB) · airframe 40,776 hrs · 8,606 cycles
EMPENNAGE, HORIZONTAL STAB LEFT HAND UPPER FORWARD PLANK NR 5L, BARREL NUT BORE CORROSION REWORKED. FOUND EXCEEDED LIMIT. REPAIRED AS PER FEDEX EA 1-5510-78096.
Part: SKIN — DAMAGED (FUSELAGE) · airframe 40,776 hrs · 8,606 cycles
FUSELAGE PLATES AND SKIN, BS 595.000 THROUGH 623.000. LONGERONS 36 THROUGH 48 LT AND RT, SKIN SPLICE REPAIR.
Part: BULKHEAD — DAMAGED (FUSELAGE) · airframe 40,776 hrs · 8,606 cycles
FUSELAGE MAIN FRAME BODY STATION 595.00 BULKHEAD REPAIR. REPAIR CARRIED OUT TO COMPLY WITH FEDEX EA 1-5310-77978.
Part: ANGLE — CORRODED (FUSELAGE) · airframe 40,776 hrs · 8,606 cycles
MAIN DECK, TEE ANGLE ON BULKHEAD STA 2007 CORRODED AT RBL 8.
Part: ANGLE — CORRODED (FUSELAGE) · airframe 40,776 hrs · 8,606 cycles
MAIN DECK, TEE ANGLE ON BULKHEAD STA 2007 CORRODED AT LBL 75. REPLACEMENT OF TEE ANGLE AT STA 2007.
Part: ANGLE — CORRODED (ZONE 200) · airframe 40,776 hrs · 8,606 cycles
MAIN DECK, TEE ANGLE ON BULKHEAD STA 2007 CORRODED AT LBL 36. MAIN DECK, CORRODED TEE ANGLE ON BULKHEAD AT STA 2007 LBL 36. REMOVED AND NEW TEE ANGLE INSTALLED AS PER SRM 51-31-01 VOL II.
Part: HINGE — CORRODED (ZONE 600) · airframe 40,776 hrs · 8,606 cycles
RIGHT HAND WING - INBOARD FLAP OUTBOARD HINGE (WING SIDE), PIVOT HOLE SPOT FACE FOUND CORRODED. CORROSION REMOVED AND FOUND EXCEEDED LIMIT AS PER CMM 57-44-07 PAGES 403 TO 404.
Part: HINGE — CORRODED (RT WING) · airframe 40,776 hrs · 8,606 cycles
RT WING OUTBOARD FLAP OUTBOARD HINGE (WING SIDE), STOP BOLT ATTACHMENT, BARREL NUT BORE FOUND CORRODED. CORROSION REMOVED BY HAND-CLEAN AS PER CMM 20-11- 01.
Part: HINGE — CORRODED (ZONE 600) · airframe 40,776 hrs · 8,606 cycles
RT WING INBOARD FLAP OUTBOARD HINGE (FLAP SIDE), PIVOT PIN ATTACHMENT OUTBOARD BORE FOUND CORRODED. BORE CORROSION REMOVED AND FOUND EXCEEDED LIMIT AS PER CMM 57-52-03. REPAIR CARRIED OUT AS PER FEDEX EA 1-5750-78057.
Part: HINGE — CORRODED (T/E FLAP) · airframe 40,776 hrs · 8,606 cycles
RT WING INBOARD FLAP OUTBOARD HINGE (FLAP SIDE), PIVOT PIN ATTACHMENT INBOARD BORE FOUND CORRODED. CORROSION REMOVED AND FOUND EXCEEDED LIMIT AS PER CMM 57-52-03. REPAIR CARRIED OUT AS PER FEDEX EA 1-5750-78057.
Part: HINGE — CORRODED (T/E FLAP) · airframe 40,776 hrs · 8,606 cycles
RT WING INBOARD FLAP OUTBOARD HINGE (FLAP SIDE), PIVOT PIN ATTACHMENT OUTBOARD HOLE SPOT FACE FOUND CORRODED. SPOT FACE CORROSION REMOVED AND FOUND EXCEEDED LIMIT AS PER CMM57-52-03. REPAIR CARRIED OUT AS PER FEDEX EA 1-5750-78057.
Part: HINGE — CORRODED (ZONE 500) · airframe 40,776 hrs · 8,606 cycles
LT WING INBOARD FLAP OUTBOARD HINGE (WING SIDE), PIVOT HOLE SPOT FACE FOUND CORRODED. CORROSION REMOVED AND FOUND EXCEEDED LIMIT AS PER CMM 57-44-07 PAGES 403- 404.
Part: SPAR — CORRODED (ZONE 500) · airframe 40,776 hrs · 8,606 cycles
LT WING OUTBOARD AILERON OUTBOARD SIDE AT APPROX XORS 1048 FOUND CORROSION AT LOWER CHORD REAR SPAR CAVITY. REPAIR CARRIED OUT IAW FEDEX EA 1571081640.
Part: SPLICE — CORRODED (FUSELAGE) · airframe 40,776 hrs · 8,606 cycles
CENTER CARGO LONGERON SPLICE FOUND CORRODED AT STA 1711 L49R. REMOVED AND REPLACED NEW SPLICE AS PER DWG AFA7102 AND REPLACED AS PER SRM 51-33-01 VOL II.
Part: HINGE — CORRODED (T/E FLAP) · airframe 40,776 hrs · 8,606 cycles
LT WING, INBOARD FLAP OUTBOARD HINGE (FLAP SIDE), PIVOT PIN ATTACHMENT OUTBOARD BORE FOUND CORRODED. CORROSION REMOVED AND FOUND EXCEEDED LIMIT AS PER CMM 57-52-03 PAGES 442-443.
Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 40,776 hrs · 8,606 cycles
MAIN DECK, SEAT TRACK LBL 107 CORRODED AT STA 425 TO STA 450. CORROSION REMOVED AS PER SRM 51-21-01. FOUND OUT OF LIMIT AS PER SRM 53-70-00. REPLACED AS PER SRM 51-31-01.
Part: SPAR CAP — CORRODED (LT WING) · airframe 40,776 hrs · 8,606 cycles
LEFT WING, REAR SPAR AT APPROX XORS 1042 UPP CAP FOUND CORROSION. REPAIRED AS PER FEDEX EA 1-5710-81640.
Part: HINGE — CORRODED (T/E FLAP) · airframe 40,776 hrs · 8,606 cycles
LEFT WING, INBOARD FLAP OUTBOARD HINGE (FLAP SIDE), PIVOT PIN ATTACHMENT INBOARD BORE FOUND CORRODED. REPAIR CARRIED OUT AS PER FEDEX EA1-5750-78058,
Part: LONGERON — CORRODED (FUSELAGE) · airframe 40,776 hrs · 8,606 cycles
FWD CARGO AT STA 979 LONGERON 51 IS CRACKED 2 INCHES. TRIMMED OUT AS PER SRM 53-10-00 VOL I. REWORKED NEW LONGERON AS PER DWG ADA8091 AND MACHINED REPAIR SPLICES AS PER SRM 53-10-00 VOL I. REPAIR PARTS INSTALLED AS PER SRM 51-33-01 VOL II.
Part: SKIN — BULGED (LT WING) · airframe 40,776 hrs · 8,606 cycles
LEFT WING, UPPER SURFACE AT APPROX STA 980 XORS FORWARD OF OUTBOARD AILERON TOP SURFACE FIXED PANEL BULGING. REPAIR CARRIED AT LT WING FORWARD UPPER SURFACE OF OUTBOARD AILERON AT APPROX. STA 980 XORS AS PER SRM 57-20-00 FIG 16 VOL I.
Part: HINGE — CORRODED (ZONE 600) · airframe 40,776 hrs · 8,606 cycles
RIGHT HAND WING - OUTBOARD FLAP INBOARD HINGE (FLAP SIDE), PIVOT PIN ATTACHMENT INBOARD HOLE SPOT FACE FOUND CORRODED. CORROSION REMOVED AS PER CMM 20-11-02.
Part: HINGE — CORRODED (ZONE 600) · airframe 40,776 hrs · 8,606 cycles
RIGHT HAND WING - OUTBOARD FLAP INBOARD HINGE (FLAP SIDE), PIVOT PIN ATTACHMENT INBOARD BORE FOUND CORRODED. CORROSION REMOVED AS PER CMM 20-11-02.
Part: HINGE — CORRODED (ZONE 600) · airframe 40,776 hrs · 8,606 cycles
RIGHT HAND WING - OUTBOARD FLAP INBOARD HINGE (FLAP SIDE), PIVOT PIN ATTACHMENT OUTBOARD BORE FOUND CORRODED. CORROSION REMOVED AS PER CMM 20-11-02.
Part: LONGERON — CORRODED (ZONE 100) · airframe 40,776 hrs · 8,606 cycles
CENTER CARGO LONGERON CORRODED - 50L AT STA 1681. CENTER CARGO LONGERON 50L AT STA 1681 REPAIR CARRIED OUT AS PER SRM 53-10-00 VOL I.
Part: HINGE — CORRODED (ZONE 600) · airframe 40,776 hrs · 8,606 cycles
RT WING OUTBOARD FLAP INBOARD HINGE (FLAP SIDE), PIVOT PIN ATTACHMENT OUTBOARD HOLE SPOT FACE FOUND CORRODED. CORROSION REMOVED AS PER CMM 20-11-02.
Part: STRUCTURE — CRACKED (RT MLG DOOR) · airframe 40,776 hrs · 8,606 cycles
RIGHT MAIN LANDING GEAR WHEEL WELL MAIN GEAR DOOR FOUND CRACKED AT HOLE PLUG AREA. CRACK REPAIRED AS PER SRM 52-10-00 FIG 13 VOL I. REPAIR DOUBLER FABRICATED AS PER SRM 52-10-00 FIG 13 VOL I.
Part: SKIN — DELAMINATED (FLAP VANE) · airframe 40,776 hrs · 8,606 cycles
LEFT INBOARD FLAP VANE LOWER SURFACE FOUND DELAMINATED. REPAIRED AS PER FEDEX EA 1575079794.
Part: LONGERON — CORRODED (FUSELAGE) · airframe 40,776 hrs · 8,606 cycles
CENTER CARGO LONGERON CORRODED 47L STA 1562. CARRIED OUT REPAIR AS PER SRM 53-10-00 VOL I FIG 1 AT CENTER CARGO LONGERON 47L AT STA 1562.
Part: HINGE — CORRODED (T/E FLAP) · airframe 40,776 hrs · 8,606 cycles
RIGHT WING, OUTBOARD FLAP INBOARD HINGE (FLAP SIDE), ACTUATOR ATTACHMENT INBOARD BORE FOUND CORRODED. CORROSION REMOVED AS PER CMM 20-11-02.
Part: HINGE — CORRODED (ZONE 600) · airframe 40,776 hrs · 8,606 cycles
RIGHT HAND WING OUTBOARD FLAP INBOARD HINGE (FLAP SIDE), ACTUATOR ATTACHMENT OUTBOARD HOLE SPOT FACE FOUND CORRODED. CORROSION REMOVED AS PER CMM 20-11-02. CORROSION REMOVED AS PER CMM 20-11-02.
Part: HINGE — CORRODED (T/E FLAP) · airframe 40,776 hrs · 8,606 cycles
RIGHT WING, OUTBOARD FLAP INBOARD HINGE (FLAP SIDE), ACTUATOR ATTACHMENT OUTBOARD BORE FOUND CORRODED. CORROSION REMOVED AS PER CMM 20-11-02.
Part: HINGE — CORRODED (ZONE 600) · airframe 40,776 hrs · 8,606 cycles
RIGHT HAND WING - OUTBOARD FLAP INBOARD HINGE (FLAP SIDE), ACTUATOR ATTACHMENT INBOARD HOLE SPOT FACE FOUND CORRODED. CORROSION REMOVED AS PER CMM 20-11-02.
Part: HINGE — CORRODED (ZONE 500) · airframe 40,776 hrs · 8,606 cycles
LEFT HAND WING - OUTBOARD FLAP OUTBOARD HINGE (WING SIDE), SIDE LINK ATTACHMENT SPOT FACE FOUND CORRODED. CORROSION REMOVED AS PER CMM 57-44-09 PAGES 402-407,
Part: HINGE — CORRODED (ZONE 500) · airframe 40,776 hrs · 8,606 cycles
LEFT HAND WING - OUTBOARD FLAP OUTBOARD HINGE (WING SIDE), ACTUATOR ATTACHMENT OUTBOARD BORE FOUND CORRODED. CORROSION REMOVED AND FOUND EXCEEDED LIMIT IAW CMM 57-44-09. REPAIRED AS PER FEDEX EA 1-5750-77984.
Part: HINGE — CORRODED (ZONE 500) · airframe 40,776 hrs · 8,606 cycles
OUTBOARD FLAP OUTBOARD HINGE (WING SIDE), ACTUATOR ATTACHMENT INBOARD BORE FOUND CORRODED. CORROSION REMOVED AND FOUND EXCEEDED LIMIT AS PER CMM 57-44-09.
Part: SPLICE — CORRODED (ZONE 100) · airframe 40,776 hrs · 8,606 cycles
CENTER ACCESSORY COMPARTMENT FORWARD OF DOOR AT LONGERON R49 HARDWARE ON LONGERON SPLICE FOUND CORRODED. REMOVED AND REPLACED AS PER SRM 51-33-01 VOL II.
Part: SUPPORT BRACKET — CORRODED (ZONE 600) · airframe 40,776 hrs · 8,606 cycles
RT WING OUTBOARD FLAP OUTBOARD HINGE (FLAP SIDE), PIVOT PIN ATTACHMENT INBOARD BORE FOUND CORRODED. CORROSION REMOVED AS PER CMM 20-11-02 PAGES 2-4. ORIGINAL DIAMATER = 1.094, FINAL DIAMETER = 1.149, AND FABRICATED BUSHING INSTALLED AS PER FEDEX EA 1-5750-77983.
Part: HINGE — CORRODED (LT WING) · airframe 40,776 hrs · 8,606 cycles
LEFT WING, OUTBOARD FLAP INBOARD HINGE (WING SIDE), LOWER ATTACHMENT SPOT FACE FOUND CORRODED. CORROSION REMOVED AS PER CMM 57-44-08 PAGES 402-407.
Part: LONGERON — CORRODED (ZONE 100) · airframe 40,776 hrs · 8,606 cycles
CENTER CARGO LONGERON 46 RT CORRODED AT STA 5-93. REPAIR CARRIED OUT AT LONGERON 46RH AT STA 5-93 AS PER SRM 53-10-00 VOL I.
Part: FITTING — CORRODED (ZONE 500) · airframe 40,776 hrs · 8,606 cycles
LEFT HAND INBOARD FLAP OUTBOARD FITTING OUTBOARD STRAP PIVOT HOLE SURROUNDING AREA OF HOLE SURFACES FOUND PITTING CORROSION OUT OF LIMIT. LEFT HAND INBOARD FLAP OUTBOARD FITTING OUTBOARD STRAP REPLACED BY NEW STRAP AS PER SRM 51-33-01 VOL II.
Part: HINGE — CORRODED (ZONE 600) · airframe 40,776 hrs · 8,606 cycles
RT WING, OUTBOARD FLAP INBOARD HINGE (WING SIDE), ACTUATOR ATTACHMENT INBOARD BORE FOUND CORRODED. CORROSION REMOVED AND FOUND EXCEEDED LIMIT AS PER CMM 57-44-08. REPAIR CARRIED OUT AS PER FEDEX EA 1-5750-77986.
Part: LONGERON — CRACKED (ZONE 100) · airframe 40,776 hrs · 8,606 cycles
CENTER CARGO COMPT - LONGERON 45 LT FOUND CRACKED AT STA 5-111 TO 5-121. REPAIR CARRIED OUT AT STA 5-111 TO 5-121 LONGERON 45 LT AS PER SRM 53-10-00 VOL I FIG 1.
Part: HINGE — CORRODED (ZONE 600) · airframe 40,776 hrs · 8,606 cycles
RIGHT WING, OUTBOARD FLAP INBOARD HINGE (WING SIDE), ACTUATOR ATTACHMENT OUTBOARD BORE FOUND CORRODED. CORROSION REMOVED AND FOUND EXCEEDED LIMIT AS PER CMM 57-44-08. REPAIR CARRIED OUT AS PER FEDEX EA 1-5750-77986.
Part: HINGE — CORRODED (ZONE 600) · airframe 40,776 hrs · 8,606 cycles
RIGHT WING, OUTBOARD FLAP INBOARD HINGE (WING SIDE), LOWER ATTACHMENT SPOT FACE FOUND CORRODED. CORROSION REMOVED AS PER CMM 20-11-02.
Part: HINGE — CORRODED (T/E FLAP) · airframe 40,776 hrs · 8,606 cycles
RIGHT HAND WING - OUTBOARD FLAP OUTBOARD HINGE (FLAP SIDE), PIVOT PIN ATTACHMENT OUTBOARD BORE FOUND CORRODED. CORROSION REMOVED AS PER CMM 20-11-02 PAGES 2-4.
Part: HINGE — CORRODED (LT WING) · airframe 40,776 hrs · 8,606 cycles
LEFT WING, OUTBOARD FLAP INBOARD HINGE (WING SIDE), SIDE LINK ATTACHMENT SPOT FACE FOUND CORRODED. CORROSION REMOVED AS PER CMM 57-44-08.
Part: SUPPORT BRACKET — CORRODED (ZONE 600) · airframe 40,776 hrs · 8,606 cycles
RT WING OUTBOARD FLAP OUTBOARD HINGE (FLAP SIDE), PIVOT PIN ATTACHMENT INBOARD HOLE SPOT FACE FOUND CORRODED. CORROSION REMOVED AS PER CMM 20-11-02 PAGES 2-4. ORIGINAL THICKNESS=0.505, REMAINING THICKNESS=0.495, MATERIAL REMOVED=0.010 AND REPAIRED AS PER FEDEX EA 1-5750-77983.
Part: HINGE — CORRODED (ZONE 600) · airframe 40,776 hrs · 8,606 cycles
RIGHT HAND WING - OUTBOARD FLAP OUTBOARD HINGE (WING SIDE), SIDE LINK ATTACHMENT SPOT FACE FOUND CORRODED. CORROSION REMOVED AS PER CMM 57-44-09 PAGES 402-407.
Part: HINGE — CORRODED (T/E FLAP) · airframe 40,776 hrs · 8,606 cycles
RIGHT WING, OUTBOARD FLAP OUTBOARD HINGE (FLAP SIDE), ACTUATOR PIN ATTACHMENT OUTBOARD HOLE SPOT FACE FOUND CORRODED. CORROSION REMOVED AS PER CMM 20-11-02.
Part: SKIN — CORRODED (ZONE 600) · airframe 40,776 hrs · 8,606 cycles
RIGHT HAND WING - REAR SPAR UPPER SKIN AT STA XORS 980 FOUND CORRODED. REPAIR CARRIED OUT AT RT WING REAR SPAR UPPER SKIN AT STA XORS 980 AS PER EA 1-5710-79795.
Part: SKIN — CORRODED (ZONE 600) · airframe 40,776 hrs · 8,606 cycles
RIGHT HAND WING - REAR SPAR UPPER SKIN AT STA XORS 1042 FOUND CORRODED. REPAIR CARRIED OUT AT RIGHT HAND WING - REAR SPAR UPPER SKIN AT STA XORS 1042 AS PER EA 1-5710-79795.
Part: HINGE — CORRODED (ZONE 600) · airframe 40,776 hrs · 8,606 cycles
RIGHT HAND WING - OUTBOARD FLAP OUTBOARD HINGE (FLAP SIDE), ACTUATOR PIN ATTACHMENT INBOARD HOLE SPOT FACE FOUND CORRODED. CORROSION REMOVED AS PER CMM 20-11-02.
Part: HINGE — CORRODED (ZONE 500) · airframe 40,776 hrs · 8,606 cycles
LEFT WING, OUTBOARD FLAP INBOARD HINGE (WING SIDE), ACTUATOR ATTACHMENT INBOARD BORE FOUND CORRODED. CORROSION REMOVED AND FOUND EXCEEDED LIMIT AS PER CMM 57-44-08 PAGES 402-407, ORIGINAL DIAMETER=1.187, FINAL DIAMETER=1.232, MAXIMUM ALLOWABLE DIAMETER=1.190. REPAIR CARRIED OUT AS PER FEDEX EA 1-5750-77985.
Part: HINGE — CORRODED (ZONE 600) · airframe 40,776 hrs · 8,606 cycles
RIGHT HAND WING - OUTBOARD FLAP OUTBOARD HINGE (WING SIDE), ACTUATOR ATTACHMENT INBOARD BORE FOUND CORRODED. BORE CORROSION REMOVED AND FOUND EXCEEDED LIMITS AS PER CMM 57-44-09. REPAIRED AS PER EA 1-5750-78056.
Part: HINGE — CORRODED (ZONE 600) · airframe 40,776 hrs · 8,606 cycles
RT WING OUTBOARD FLAP OUTBOARD HINGE (WING SIDE), LOWER ATTACHMENT OUTBOARD BORE FOUND CORRODED. CORROSION REMOVED AND FOUND EXCEEDED LIMIT AS PER CMM 57-44-09, PAGES 402-407.
Part: HINGE — CORRODED (LT WING) · airframe 40,776 hrs · 8,606 cycles
LT WING, OUTBOARD FLAP INBOARD HINGE (WING SIDE), ACTUATOR ATTACHMENT OUTBOARD BORE FOUND CORRODED. CORROSION REMOVED AND FOUND EXCEEDED LIMIT AS PER CMM 57-44-08 PAGES 402-407, ORIGINAL DIAMETER=1.187, FINAL DIAMETER=1.229, MAXIMUM ALLOWABLE DIAMETER=1.190. REPAIR CARRIED OUT AS PER FEDEX EA 1-5750-77985.
Part: SUPPORT BRACKET — CORRODED (ZONE 600) · airframe 40,776 hrs · 8,606 cycles
RIGHT HAND WING OUTBOARD FLAP OUTBOARD HINGE (FLAP SIDE), ACTUATOR PIN ATTACHMENT OUTBOARD BORE FOUND CORRODED. CORROSION REMOVED AS PER CMM 20-11-02 PAGES 2-4. ORIGINAL DIAMATER=1.191, FINAL DIAMETER=1.219, AND FABRICATED BUSHING INSTALLED AS PER FEDEX EA 1-5750-77983.
Part: SUPPORT BRACKET — CORRODED (ZONE 600) · airframe 40,776 hrs · 8,606 cycles
RT WING OUTBOARD FLAP OUTBOARD HINGE (FLAP SIDE), ACTUATOR PIN ATTACHMENT INBOARD BORE FOUND CORRODED. CORROSION REMOVED AS PER CMM 20-11-02 PAGES 2-4.
Part: SUPPORT BRACKET — CORRODED (ZONE 600) · airframe 40,776 hrs · 8,606 cycles
RT WING OUTBOARD FLAP OUTBOARD HINGE (FLAP SIDE), PIVOT PIN ATTACHMENT OUTBOARD HOLE SPOT FACE FOUND CORRODED. CORROSION REMOVED AS PER CMM 20-11-02 PAGES 2-4. ORIGINAL THICKNESS=0.510, REMAINING THICKNESS=0.506, MATERIAL REMOVED=0.004 AND REPAIRED AS PER FEDEX EA 1-5750-77983.
Part: HINGE — CORRODED (ZONE 600) · airframe 40,776 hrs · 8,606 cycles
RT WING OUTBOARD FLAP OUTBOARD HINGE (WING SIDE), ACTUATOR ATTACHMENT OUTBOARD BORE FOUND CORRODED. BORE CORROSION REMOVED AND FOUND EXCEEDED LIMITS AS PER CMM 57-44-09. REPAIR CARRIED OUT AS PER EA 1-5750-78056.
Part: HINGE — CORRODED (ZONE 600) · airframe 40,776 hrs · 8,606 cycles
RT WING, OUTBOARD FLAP INBOARD HINGE (WING SIDE), SIDE LINK ATTACHMENT SPOT FACE FOUND CORRODED. CORROSION REMOVED AS PER CMM 20-11-02 PAGES 2-4.
Part: HINGE — CORRODED (ZONE 500) · airframe 40,776 hrs · 8,606 cycles
LT WING OUTBOARD FLAP INBOARD HINGE (FLAP SIDE), ACTUATOR ATTACHMENT OUTBOARD BORE FOUND CORRODED. CORROSION REMOVED AS PER CMM 20-11-02.
Part: HINGE — CORRODED (ZONE 500) · airframe 40,776 hrs · 8,606 cycles
LEFT HAND WING - OUTBOARD FLAP OUTBOARD HINGE (FLAP SIDE), PIVOT PIN ATTACHMENT INBOARD HOLE SPOT FACE FOUND CORRODED. CORROSION REMOVED AS PER CMM 20-11-02.
Part: HINGE — CORRODED (ZONE 500) · airframe 40,776 hrs · 8,606 cycles
LEFT WING, OUTBOARD FLAP INBOARD HINGE (FLAP SIDE), PIVOT PIN ATTACHMENT INBOARD HOLE SPOT FACE FOUND CORRODED. CORROSION REMOVED AS PER CMM 20-11-02.
Part: HINGE — CORRODED (ZONE 500) · airframe 40,776 hrs · 8,606 cycles
LEFT HAND WING - OUTBOARD FLAP INBOARD HINGE (FLAP SIDE), ACTUATOR ATTACHMENT OUTBOARD HOLE SPOT FACE FOUND CORRODED. CORROSION REMOVED AS PER CMM 20-11-02. CORROSION REMOVED AS PER CMM 20-11-02.
Part: HINGE — CORRODED (ZONE 500) · airframe 40,776 hrs · 8,606 cycles
LEFT WING, OUTBOARD FLAP INBOARD HINGE (FLAP SIDE), PIVOT PIN ATTACHMENT INBOARD BORE FOUND CORRODED. CORROSION REMOVED AS PER CMM 20-11-02.
Part: HINGE — CORRODED (ZONE 500) · airframe 40,776 hrs · 8,606 cycles
LEFT HAND WING - OUTBOARD FLAP OUTBOARD HINGE (FLAP SIDE), PIVOT PIN ATTACHMENT OUTBOARD BORE FOUND CORRODED. CORROSION REMOVED AS PER CMM 20-11-02.
Part: HINGE — CORRODED (ZONE 500) · airframe 40,776 hrs · 8,606 cycles
LEFT HAND WING - OUTBOARD FLAP OUTBOARD HINGE (FLAP SIDE), PIVOT PIN ATTACHMENT OUTBOARD HOLE SPOT FACE FOUND CORRODED. CORROSION REMOVED AS PER CMM 20-11-02.
Part: HINGE — CORRODED (ZONE 500) · airframe 40,776 hrs · 8,606 cycles
LEFT WING, OUTBOARD FLAP OUTBOARD HINGE (FLAP SIDE), ACTUATOR ATTACHMENT INBOARD BORE FOUND CORRODED. CORROSION REMOVED AS PER CMM 20-11-02.
Part: HINGE — CORRODED (ZONE 500) · airframe 40,776 hrs · 8,606 cycles
LT HAND WING, OUTBOARD FLAP INBOARD HINGE (FLAP SIDE), ACTUATOR ATTACHMENT INBOARD BORE FOUND CORRODED. CORROSION REMOVED AS PER CMM 20-11-02.
Part: HINGE — CORRODED (ZONE 600) · airframe 40,776 hrs · 8,606 cycles
RT WING OUTBOARD FLAP OUTBOARD HINGE (WING SIDE), LOWER ATTACHMENT INBOARD BORE FOUND CORRODED. CORROSION REMOVED AND FOUND EXCEEDED LIMIT AS PER CMM 57-44-09, PAGES 402-407.
Part: HINGE — CORRODED (ZONE 500) · airframe 40,776 hrs · 8,606 cycles
LEFT HAND WING - OUTBOARD FLAP INBOARD HINGE (FLAP SIDE), ACTUATOR ATTACHMENT INBOARD HOLE SPOT FACE FOUND CORRODED. CORROSION REMOVED AS PER CMM 20-11-02.
Part: HINGE — CORRODED (ZONE 500) · airframe 40,776 hrs · 8,606 cycles
LEFT WING, OUTBOARD FLAP OUTBOARD HINGE (FLAP SIDE), ACTUATOR ATTACHMENT OUTBOARD HOLE SPOT FACE FOUND CORRODED. CORROSION REMOVED AS PER CMM 20-11-02.
Part: HINGE — CONTAMINATED (ZONE 500) · airframe 40,776 hrs · 8,606 cycles
LEFT WING, OUTBOARD FLAP INBOARD HINGE (FLAP SIDE), PIVOT PIN ATTACHMENT OUTBOARD HOLE SPOT FACE FOUND CORRODED. CORROSION REMOVED AS PER CMM 20-11-02.
Part: HINGE — CORRODED (ZONE 500) · airframe 40,776 hrs · 8,606 cycles
LEFT HAND WING, OUTBOARD FLAP OUTBOARD HINGE (FLAP SIDE), ACTUATOR ATTACHMENT OUTBOARD BORE FOUND CORRODED. CORROSION REMOVED AS PER CMM 20-11-02.
Part: HINGE — CORRODED (ZONE 500) · airframe 40,776 hrs · 8,606 cycles
LEFT WING, OUTBOARD FLAP INBOARD HINGE (FLAP SIDE), PIVOT PIN ATTACHMENT OUTBOARD BORE FOUND CORRODED. CORROSION REMOVED AS PER CMM 20-11-02.
Part: HINGE — CORRODED (ZONE 500) · airframe 40,776 hrs · 8,606 cycles
LEFT WING, OUTBOARD FLAP OUTBOARD HINGE (FLAP SIDE), ACTUATOR ATTACHMENT INBOARD HOLE SPOT FACE FOUND CORRODED. CORROSION REMOVED AS PER CMM 20-11-02.
Part: HINGE — CORRODED (ZONE 500) · airframe 40,776 hrs · 8,606 cycles
LEFT HAND WING - OUTBOARD FLAP OUTBOARD HINGE (FLAP SIDE), PIVOT PIN ATTACHMENT INBOARD BORE FOUND CORRODED. CORROSION REMOVED AS PER CMM 20-11-02.
Part: SPLICE — CRACKED (FUSELAGE) · airframe 40,776 hrs · 8,606 cycles
CENTER CARGO, LONGERON SPLICE CRACKED AT STA 1531/5-123 LONGERON 38L. REMOVED AS PER SRM 51-31-01 VOL II. FABRICATED NEW LONGERON SPLICE AS PER DRAWING A5A7114. FPI CARRIED OUT AS PER DPS 4.707 ON NEW LONGERON SPLICE AND FOUND NO CRACK EVIDENT. INSTALLED NEW LONGERON SPLICE AS PER SRM 51-33-01 VOL II.
Part: SPLICE — CRACKED (ZONE 100) · airframe 40,776 hrs · 8,606 cycles
CENTER CARGO - LONGERON SPLICE CRACKED AT STA 1531/5-123 LONGERON 37L. CENTER CARGO BETWEEN STA 5-123 TO STA 1531 LONGERON 37L CRACK LONGERON SPLICE REMOVED AND REPLACED AS PER SRM 51-33-01 VOL II WITH NEW SPLICE FABRICATED AS PER DRAWING A5A7114 P/N FXA5A7114-519.
Part: SPLICE — CRACKED (FUSELAGE) · airframe 40,776 hrs · 8,606 cycles
CENTER CARGO, LONGERON SPLICE CRACKED AT STA 1531/5-123 LONGERON 44R. REMOVED AND REPLACED WITH NEW SPLICE AS PER SRM 51-33-01 VOL II.
Part: SPLICE — CRACKED (FUSELAGE) · airframe 40,776 hrs · 8,606 cycles
CENTER CARGO, LONGERON SPLICE CRACKED AT STA 1531/5-123 LONGERON 45R. REMOVED AS PER SRM 51-31-01 VOL II. FABRICATED NEW LONGERON SPLICE AS PER DRAWING A5A7116. FPI CARRIED OUT AS PER DPS 4.707 ON NEW LONGERON SPLICE AND FOUND NO CRACK EVIDENT. INSTALLED NEW LONGERON SPLICE AS PER SRM 51-33-01 VOL II.
Part: SPLICE — CRACKED (FUSELAGE) · airframe 40,776 hrs · 8,606 cycles
CENTER CARGO LONGERON SPLICE CRACKED AT STA 1531/5-123 LONGERON 45L. REMOVED AS PER SRM 51-33-01 VOL II. FABRICATED NEW SPLICE AS PER DWG A5A7116 AND INSTALLED AS PER SRM 51-33-01 VOL II.
Part: RIB — CRACKED (ZONE 500) · airframe 40,776 hrs · 8,606 cycles
LT WING RIB 16 INBOARD FOUND CRACKED. REMOVED AND INSTALLED AS PER SRM 51-33-01 VOL II. REFER TO WORKCARD 27X8403 FOR CABLES ADJUSTMENT.
Part: SPLICE — CRACKED (FUSELAGE) · airframe 40,776 hrs · 8,606 cycles
CENTER CARGO, LONGERON SPLICE CRACKED AT STA 1531/5-123 LONGERON 39L. REMOVED AS PER SRM 51-33-01 VOLUME II AND NEW LONGERON SPLICE INSTALLED AS PER SRM 51-33-01 VOLUME II, NEW LONGERON SPLICE MACHINED AS PER DWG A5A7114. FPI CARRIED OUT ON NEW LONGERON SPLICE AS PER DPS 4.707 AND FOUND NO CRACK EVIDENT.
Part: FITTING — CRACKED (ZONE 500) · airframe 40,776 hrs · 8,606 cycles
LT HAND WING OUTBOARD FLAP INBOARD STOP FITTING FOUND CRACKED. REMOVED AND REPLACED AS PER SRM 51-33-01 VOL II AND DWG ARC4125.
Part: SPLICE — CRACKED (ZONE 100) · airframe 40,776 hrs · 8,606 cycles
CENTER CARGO, LONGERON SPLICE CRACKED AT STA 1531/5-123 LONGERON 38R. REMOVED AS PER SRM 51-33-01 VOL II.
Part: FITTING — CRACKED (ZONE 600) · airframe 40,776 hrs · 8,606 cycles
RIGHT HAND WING - OUTBOARD FLAP INBOARD STOP FITTING FOUND CRACKED. OUTBOARD FLAP REMOVED AND REPLACED AS PER ARM 51-33-01 VOL II AND DRAWING ARC4125.
Part: STRUCTURE — CRACKED (LT MLG DOOR) · airframe 40,776 hrs · 8,606 cycles
LEFT MAIN LANDING GEAR WHEEL WELL MAIN GEAR DOOR FOUND CRACKED AT HOLE PLUG AREA OF STRUT FITTING. CRACK REPAIRED AS PER SRM 52-10-00 FIG 13 VOL I. REPAIR DOUBLER FABRICATED AS PER SRM 52-10-00 FIG 13 VOL I.
Part: STRUCTURE — CRACKED (LT MLG DOOR) · airframe 40,776 hrs · 8,606 cycles
LEFT MAIN LANDING GEAR WHEEL WELL MAIN GEAR DOOR FOUND CRACKED AT FORWARD OF STRUT FITTING NEAR HINGE AREA. CRACK REPAIRED AND REPAIR DOUBLER FABRICATED AS PER SRM 52-10-00 FIG 13 VOL I.