N579FE
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.
254 reports on file, 2004-01-12 – 2013-11-19.
Part: SENSOR — FAILED (LE SLAT) · airframe 67,246 hrs · 14,725 cycles
UPON CONFIGURATION AT 15 DEG FLAPS, LEVEL 2 SLAT DISAGREE ILLUMINATED, GO AROUND. RAN CHECKLIST ON EXTENDED DOWNWIND. DURING GO AROUND THERE WAS SOME FEEL THAT CONFIGURATION WAS OFF. LANDED SLAT STOW FLAPS 28 DEGREES AT 185KTS & MAX BRAKES. RAN SLATS VERIFIED SLAT DISAGREE. BRAKE & TIRE TEMPS ALL RETURNED TO NORMAL. IAW FIM 31-71-07-00 FIG 107 PERFORMED SYS TEST OF PSEU, FAILED STEP 7 WITH THE TARGET 02 SHOWING SENSOR FAILED. SWAPPED PSEU VERIFIED SAME FAULT & REINSTALLED ORIGINAL PSEU IAW MM 31-71-01-2. R & R LT NR SLAT POSITION SENSOR 02B IAW MD 11 MM 27-84-03-4, ALL OPERATIONS CHECKED NORMAL IAW MM 27-84-00-5.
Part: WHEEL — FAILED (NR 10) · airframe 66,639 hrs · 14,455 cycles
LEVEL 2 TIRE FAIL ON LANDING ROLL, R & R NR 10 MAIN WHEEL ASSY IAW 32-41-01-4 UP TO STEP 5F(6).
Part: SWITCH — FAILED (L1 DOOR PRESSURE) · airframe 66,582 hrs · 14,431 cycles
SLIDE PRESSURE LIGHT IN L1 DOOR WAS INOPERATIVE, REPLACED LIGHT SWITCH ASSY IAW MM 25-61-04-4. OPS CHECKED NORMAL.
Part: TRANSMITTER — MALFUNCTIONED (FUEL FLOW) · airframe 65,950 hrs · 14,187 cycles
PASSING THRU FL 260 RECEIVED A LEVEL 2 FUEL QTY/USED CHECK. FUEL USED ON ALL THREE ENGINES TOTALED WITH FUEL ONBOARD TOTALED 58.8 VICE FOB OF 56.4 AT TAKEOFF. RAN CHECK LIST AND DECIDED TO LEAVE ALL THREE ENG RUNNING. DURING DESCENT FUEL USED ON ENGINE 1 WAS INCREASING RAPIDLY TO MATCH ENG 2 & 3 FUEL USED. RETURNED AND LANDED WITHOUT INCIDENT. NO EVIDENCE OF FUEL LEAK AT NR 1 ENGINE UPON ARRIVAL. TROUBLESHOT IAW FIM 28-14. R & R NR 1 ENGINE FUEL FLOW TRANSMITTER IAW AMM 73-31-02-4-2. FFEU CHECKED OK IAW AMM 73-31-03-7-8. RAN ENGINE IAW JRH - LEAK CHECKED OK. CHECKED OK IAW AMM 71-02-03-7-8. OK FOR SVC.
Earlier reports · 2004–2012 · 250 reports
2012
Part: SKIN — LOOSE (LT WING TE FLAP) · airframe 65,254 hrs · 13,965 cycles
LEFT WING INBD FLAP UPPER SURFACE AT XIFH= 171 RIVETS FOUND LOOSE. REPAIRED IAW SRM 57-50-01 FIGURE 201 REPAIR 4 REVISION 51 AND EA 1-5750-163534 STEP 5 PART 1. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100 REVISION 115.
Part: BULKHEAD — MISREPAIRED (NLG WW) · airframe 65,254 hrs · 13,965 cycles
NLG HORIZONTAL PRESSURE PANEL, LT SIDE, AT BS 495 TO 515, "X"=42 TO "X"=47 MISREPAIRED. REPAIRED IAW EA 1-5310-163550. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100 REVISION 115.
Part: FLOORBEAM — MISREPAIRED (ZONE 100) · airframe 65,254 hrs · 13,965 cycles
FLOORBEAM LOWER FLANGE AT BS 5-53 MISREPAIRED. REPAIRED IAW EA 1-5310-163551. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100 REVISION 115.
Part: HINGE BRACKET — CORRODED (RT WING TE FLAP) · corrosion level 2 · airframe 65,254 hrs · 13,965 cycles
RT WING, OTBD FLAP, INBD FORWARD HINGE BRACKET, LOWER MOUNT INBD BORE FOUND CORRODED. REWORKED AND FOUND WITHIN LIMIT AS PER CMM 57-44-08 REVISION 74. EXISTING HOLE DIAMETER: 0.705", FINAL HOLE DIAMETER: 0.709", MAXIMUM HOLE: 0.709". REPAIR BUSHING FABRICATED AND INSTALLED AS PER CMM 57-44-08 REVISION 74. REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100 REVISION 115.
Part: BULKHEAD — MISREPAIRED (NLG WW) · airframe 65,254 hrs · 13,965 cycles
NLG HORIZONTAL PRESSURE PANEL, LT SIDE, BS 495 TO 515, "X"=30 TO "X"=39 MISREPAIRED. REPAIRED IAW EA 1-5310-163550. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100 REVISION 115.
Part: HINGE BRACKET — CORRODED (LT WING TE FLAP) · corrosion level 2 · airframe 65,254 hrs · 13,965 cycles
LT WING OTBD FLAP, OTBD FORWARD HINGE BRACKET SIDE LOAD FITTING LOWER BORE SURFACE CORRODED. REWORKED AS PER CMM 20-10-6 REVISION 74. EXISTING THICKNESS: 0.452", MATERIAL REMOVED: 0.004", REAMINING THICKNESS: 0.448" FOUND ACCEPTABLE PER EA 1-5750-162399 PART 1 PAGE 6 FOR 18. REPAIR CARRIED OUT AS PER EA 1-5750-162399 STEPS 1, 2, 3 AND 6 PART 1. REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100 REVISION 115.
Part: HINGE BRACKET — CORRODED (LT WING TE FLAP) · corrosion level 2 · airframe 65,254 hrs · 13,965 cycles
LEFT WING OTBD FLAP, OTBD FWD HINGE BRACKET SIDE LOAD FITTING UPPER BORE SURFACE FOUND CORRODED. REWORKED AS PER CMM 20-10-6 REVISION 74. EXISTING THICKNESS: 0.452", MATERIAL REMOVED: 0.004", REAMINING THICKNESS: 0.448" FOUND ACCEPTABLE PER EA 1-5750-162399 PART1 PAGE 6 OF 18. REPAIR CARRIED OUT AS PER E.A. 1-5750-162399 STEPS 1, 2, 3 AND 6 PART 1. REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100 REVISION 115.
Part: SKIN — LOOSE (RT WING TE FLAP) · airframe 65,254 hrs · 13,965 cycles
RIGHT WING INBD FLAP UPPER SURFACE RIVETS XIFH 261 FOUND LOOSE. REMOVED AND REPAIR ACCOMPLISHED PER SRM 57-50-01, FIGURE 201, REPAIR 4, REVISION 51 AND EA 1-5750-163535. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100, REVISION 115.
Part: STOP FITTING — CRACKED (DOOR FRAME) · airframe 65,254 hrs · 13,965 cycles
ON REMOVAL OF R1 MED DUST COVER NR 3 DOOR BEAM AFT STOP FITTING FOUND CRACKED. STOP FITTING REMOVED AND REPLACED AS PER SRM 51-31-01 REVISION 51 AND EA 1-5210-163538. REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100 REVISION 115.
Part: STOP FITTING — CRACKED (DOOR FRAME) · airframe 65,254 hrs · 13,965 cycles
ON REMOVAL OF R1 MED DUST COVER NR 2 DOOR BEAM AFT STOP FITTING FOUND CRACKED. STOP FITTING REMOVED AND REPLACED AS PER SRM 51-31-01 REVISION 51 AND EA 1-5210-163538. REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100 REVISION 115.
Part: FRAME — CRACKED (THRUST REVERSER) · airframe 65,254 hrs · 13,965 cycles
NR 1 ENGINE THRUST REVERSER AFT CASCADE SUPPORT FRAME AT POSITION 6 FOUND CRACKED AT NUTPLATE AREA. REMOVED AND REPLACED NR 1 ENGINE THRUST REVERSER SUPPORT FRAME AS PER EA 1-7830-163531. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100, REVISION 115.
Part: SKIN — LOOSE (RT WING TE FLAP) · airframe 65,254 hrs · 13,965 cycles
RIGHT WING INBD FLAP UPPER SURFACE AT "XIFH" = 269 FOUND LOOSE RIVETS. REMOVED AND REPAIRED ACCOMPLISHED PER SRM 57-50-01, FIGURE 201, REPAIR 4, REVISION 51 AND EA 1-5750-163535. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100, REVISION 115.
Part: SEAT TRACK — CORRODED (ZONE 200) · corrosion level 2 · airframe 65,254 hrs · 13,965 cycles
BS 1385, "X"= 8.5. SEAT TRACK FOUND CORRODED. REPAIRED IAW SRM 53-00-52 FIGURE 201 REPAIR 1 REVISION 51. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100 REVISION 115.
Part: SEAT TRACK — CORRODED (ZONE 200) · corrosion level 2 · airframe 65,254 hrs · 13,965 cycles
BS 1641, "X"=-8.5, SEAT TRACK FOUND CORRODED. REPAIRED IAW SRM 53-00-52, FIGURE 201, REPAIR 1, REVISION 51. REPAIR CLASSIFIED MAJOR AS IAW GMM 6-2-100 REVISION 115.
Part: SEAT TRACK — CORRODED (ZONE 200) · corrosion level 2 · airframe 65,254 hrs · 13,965 cycles
BS 1884 TO 1887, "X"=-8.5 SEAT TRACK FOUND CORRODED. REPAIRED IAW SRM 53-00-52, FIGURE 201, REPAIR 1, REVISION 51. REPAIR CLASSIFIED MAJOR IAW GMM 6-2-100 REVISION 115.
Part: SKIN — CORRODED (ZONE 300) · corrosion level 2 · airframe 65,254 hrs · 13,965 cycles
AFT ACCESSORY COMPARTMENT, FUSELAGE RT SIDE, SKIN AT STATION 2163 TO 2140, BETWEEN LONGERON 33 RIGHT AND 35 RIGHT, FOUND SURFACE CORROSION ON INTERIOR AREA COMMON TO EXISTING EXTERIOR REPAIR DOUBLER. REPAIRED IAW SRM 51-21-01 REVISION 51. FOUND EXCEEDED LIMIT IAW SRM 53-70-01, FIGURE 201, REPAIR 3, REVISION 51.
Part: SEAT TRACK — CORRODED (ZONE 200) · corrosion level 2 · airframe 65,254 hrs · 13,965 cycles
BS 1451, "X"= 8.5, SEAT TRACK FOUND CORRODED. REPAIRED AS PER SRM 53- 00-52 FIGURE 201 REPAIR 1 REVISION 51. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100 REVISION 115.
Part: WEB — CANNING (ZONE 700) · airframe 65,254 hrs · 13,965 cycles
CENTER LANDING GEAR LT KEEL WEB AT BS 1431 OIL CANNING FOUND EXCEED SRM ALLOWABLE LIMITS. REPAIRED IAW EA 1-5310-163532. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100 REVISION 115.
Part: SKIN — MISREPAIRED (ZONE 100) · airframe 65,254 hrs · 13,965 cycles
SKIN MISREPAIRED AT BS 1846, LONGEON 42 TO 44 RIGHT. REPAIRED IAW EA 1-5330-163536. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REVISION 115.
Part: FRAME — CRACKED (BS 555) · airframe 65,254 hrs · 13,965 cycles
FRAME END CAP AT BS 555, NEAR LONGERON 32R, IN AIR CONDITION PACK NR 3 COMPARTMENT, FOUND CRACKED. REMOVED AND REPLACED IAW SRM 51-35- 01, REVISION 51.. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REVISION 115.
Part: WEB — CRACKED (ZONE 100) · airframe 65,254 hrs · 13,965 cycles
RT OBSERVER SEAT, LOWER FLOOR WEB FOUND EDGE CRACKED. REPAIR CARRIED OUT IAW SRM 53-10-51, REPAIR 1, FIGURE 202, REVISION 51. REPAIR PARTS INSTALLED IAW SRM 51-35-01, REVISION 51. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REVISION 115.
Part: HINGE BRACKET — CORRODED (RT WING TE FLAP) · corrosion level 2 · airframe 65,254 hrs · 13,965 cycles
RIGHT WING INBD FLAP, FORWARD HINGE BRACKET PIVOT LUG BORE INBD AND OTBD SPOT FACE FOUND CORRODED. REWORKED AND FOUND EXCEEDED LIMITS AS PER CMM 57-44-07 REVISION 74. REPAIR ACCOMPLISHED AS PER EA 1-5750-163542, PART 1. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REVISION 115.
Part: HINGE BRACKET — CORRODED (RT WING TE FLAP) · corrosion level 2 · airframe 65,254 hrs · 13,965 cycles
RIGHT WING OTBD FLAP, INBD FORWARD HINGE BRACKET ACTUATOR ATTACH OTBD LUG BORE FOUND EXCEEDED LIMIT AFTER BUSHING REMOVED. REPAIRED IAW EA 1-5750-75980 REVISION A PART 2. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100 REVISION 115.
Part: HINGE BRACKET — CORRODED (RT WING TE FLAP) · corrosion level 2 · airframe 65,254 hrs · 13,965 cycles
RIGHT WING OTBD FLAP, OTBD FORWARD HINGE BRACKET SIDE LOAD FITTING UPPER BORE FOUND CORRODED. REWORKED AND FOUND EXCEEDED LIMITD AS PER CMM 57-44-09 REVISION 74. . REPAIRED PER EA 1-5750-162400 PART 1, STEP 1, 2, 3, 4, 5, 7, 9 AND 10. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REVISION 115.
Part: HINGE BRACKET — CORRODED (RT WING TE FLAP) · corrosion level 2 · airframe 65,254 hrs · 13,965 cycles
RIGHT WING OTBD FLAP, OTBD FORWARD HINGE BRACKET SIDE LOAD FITTING UPPER BORE SURFACE FOUND CORRODED. REWORKED AS PER CMM 20-10-6 REVISION 74. REPAIRED PER EA 1-5750-162400 PART 1, STEP 1, 2, 3, 4, 5, AND 10. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REVISION 115.
Part: HINGE BRACKET — CORRODED (RT WING TE FLAP) · corrosion level 2 · airframe 65,254 hrs · 13,965 cycles
RIGHT WING OTBD FLAP INBD FORWARD HINGE BRACKET SIDE LOAD FITTING SURFACE FOUND CORRODED. REWORKED IAW CMM 20-10-6 REVISION 74. FOUND ACCEPTABLE IAW EA 1-5750-162398 PART 1. SHIM FABRICATED AND INSTALLED IAW CMM 57-44-08 REVISION 74. REPAIR CARRIED OUT PER EA 1-5750-162398 PART 1, STEPS 1, 2, 3 AND 4. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REVISION 115.
Part: RIB — CRACKED (ZONE 600) · airframe 65,254 hrs · 13,965 cycles
ON REMOVAL OF RT WING NR 8 SLAT, CRACKS FOUND ON RIB AT STATION XOS =1135.6. REMOVED AND REPLACED IAW DRAWING ARB1954 REVISION NC AND EA 1-5750-163529 STEP 5 THRU STEP 10. REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100 REVISION 115.
Part: HINGE BRACKET — CORRODED (LT WING TE FLAP) · corrosion level 2 · airframe 65,254 hrs · 13,965 cycles
DURING BUSHING REMOVAL, LEFT WING INBD FLAP, AFT OTBD HINGE BRACKET PIVOT OTBD LUG BORE FOUND CORRODED BEYOND LIMITS. ACCOMPLISHED BUSHING REPAIR PER EA 1-5750-162394 PART 1. REPAIR CLASSIFIED A MAJOR PER GMM 6-2-100 REVISION 115.
Part: SKIN — LOOSE (LT WING TE FLAP) · airframe 65,254 hrs · 13,965 cycles
LEFT WING INBD FLAP UPPER SURFACE RIVETS FOUND LOOSE. REPAIRED IAW SRM 57-50-01, FIGURE 201, REPAIR 4, REVISION 51 AND EA 1-5750-163534, STEP 4, PART 1. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REVISION 115.
Part: HINGE BRACKET — SCRATCHED (LT WING TE FLAP) · airframe 65,254 hrs · 13,965 cycles
LEFT WING INBD FLAP FORWARD HINGE BRACKET PIVOT BORE OTBD SPOT FACE FOUND SCRATCHED. REWORKED AND FOUND EXCEEDED LIMITS AS PER CMM 57-44-07, REVISION 74. REPAIR ACCOMPLISHED PER EA 1-5750-162397, PART 1. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REVISION 115.
Part: HINGE BRACKET — CORRODED (RT WING TE FLAP) · corrosion level 2 · airframe 65,254 hrs · 13,965 cycles
RIGHT WING OTBD FLAP, INBD FORWARD HINGE BRACKET LOWER MOUNT OTBD BORE FOUND CORRODED. REWORKED AND FOUND EXCEEDED LIMITS IAW CMM 57-44-08 REVISION 74. REPAIRED IAW EA 1-5750-162398 PART 1. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100 REVISION 115.
Part: HINGE BRACKET — CORRODED (RT WING TE FLAP) · corrosion level 2 · airframe 65,254 hrs · 13,965 cycles
RIGHT WING OTBD FLAP, OTBD FORWARD HINGE BRACKET SIDE LOAD FITTING LOWER BORE FOUND CORRODED. REWORKED AND FOUND EXCEEDED LIMITS AS PER CMM 57-44-09 REVISION 74. REPAIRED PER EA 1-5750-162400 PART 1, STEP 1, 2, 3, 4, 5, 7, 9 AND 10. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REVISION 115.
Part: FITTING — CORRODED (RT WING TE FLAP) · corrosion level 2 · airframe 65,254 hrs · 13,965 cycles
RIGHT WING OTBD FLAP, OTBD FWD HINGE BRACKET SIDE LOAD FITTING LOWER BORE SURFACE FOUND CORRODED. REWORKED AS PER CMM 20-10-6 REVISION 74. REPAIRED IAW EA 1-5750-162400 PART 1, STEP 1, 2, 3, 4, 5, AND 10. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REVISION 115.
Part: SKIN — CHAFED (BS 889) · airframe 65,254 hrs · 13,965 cycles
SKIN CHAFED AT BS 889, LONGERON 40 - 41R. REPAIRED AS PER SRM 53-00-15 FIGURE 202 REPAIR 8 REVISION 51. REPAIR CLASSIFIED MAJOR AS PER GMM 6-2-100 REVISION 115.
Part: SKIN — LOOSE (RT WING TE FLAP) · airframe 65,254 hrs · 13,965 cycles
RIGHT WING INBD FLAP UPPER SURFACE RIVETS FOUND LOOSE. REMOVED AND REPAIRED PER SRM 57-50-01, FIGURE 201, REPAIR 4, REVISION 51 AND EA 1-5750-163535. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100, REVISION 115.
Part: RIB — CRACKED (ZONE 600) · airframe 65,254 hrs · 13,965 cycles
ON REMOVAL OF RT WING NR 8 SLAT, CRACKS FOUND ON RIB AT STATION XOS =1152.4. REMOVED AND REPLACED IAW DRAWING ARB1955 REVISION D AND EA 1-5750-163529 STEP 5 THRU STEP 10. REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100 REVISION 115.
Part: HINGE BRACKET — CORRODED (RT WING TE FLAP) · corrosion level 2 · airframe 65,254 hrs · 13,965 cycles
RIGHT WING INBD FLAP, OTBD AFT HINGE BRACKET PIVOT OTBD LUG BORE OTBD SPOT FACE FOUND CORRODED. REWORKED AND FOUND EXCEED LIMIT IAW CMM 57-52-03, REV 74. EXISTING THICKNESS: 0.263", MATERIAL REMOVED: 0.078", REMAINING THICKNESS: 0.185", MINIMUM THICKNESS: 0.205". REPAIR ACCOMPLISHED IAW EA 1-5750-162395 PART 1. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 115.
Part: RIB — CRACKED (ZONE 600) · airframe 65,254 hrs · 13,965 cycles
ON REMOVAL OF RT WING NR 8 SLAT, CRACKS FOUND ON RIB AT STATION XOS =1146.8. REMOVED AND REPLACED AS PER DRAWING ARB1954 REVISION NC AND E.A. 1-5750-163529 STEP 5 THRU STEP 10. REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100 REVISION 115.
Part: RIB — CRACKED (ZONE 600) · airframe 65,254 hrs · 13,965 cycles
ON REMOVAL OF RT WING NR 8 SLAT, CRACKS WERE FOUND ON RIB AT STATION XOS =1141.2. R & R IAW DWG ARB1954 REV NC AND EA 1-5750-163529, STEP 5 THRU STEP 10. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 115.
Part: HINGE BRACKET — CORRODED (RT WING TE FLAP) · corrosion level 2 · airframe 65,254 hrs · 13,965 cycles
RIGHT WING OTBD FLAP, OTBD FORWARD HINGE BRACKET ACTUATOR ATTACH OTBD LUG BORE FOUND CORRODED. REWORKED AND FOUND EXCEEDED LIMITS IAW CMM 57-44-09 REVISION 74. REPAIRED IAW EA 1-5750-162400 PART 1, STEP 1, 2, 3, 4, 5, 6, 9 AND 10. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REVISION 115.
Part: HINGE BRACKET — DAMAGED (RT WING TE FLAP) · corrosion level 2 · airframe 65,254 hrs · 13,965 cycles
RIGHT WING OTBD FLAP, INBD FORWARD HINGE BRACKET ACTUATOR ATTACH INBD LUG BORE FOUND EXCEEDED LIMITS AFTER BUSHING REMOVED. REPAIRED PER EA 1-5750-75980 REVISION A PART 2. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REVISION 115.
Part: HINGE BRACKET — CORRODED (RT WING TE FLAP) · corrosion level 2 · airframe 65,254 hrs · 13,965 cycles
RT WING OTBD FLAP, OTBD FORWARD HINGE BRACKET LOWER MOUNT INBD BORE FOUND CORRODED. REWORKED AND FOUND EXCEEDED LIMITS AS PER CMM 57-44- 09 REVISION 74. . REPAIRED PER EA 1-5750-162400 PART 1, STEPS 1, 2, 3, 4, 5, 8, 9 AND 10. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REVISION 115.
Part: SKIN — CHAFED (BS 1009) · airframe 65,254 hrs · 13,965 cycles
SKIN CHAFED BS 1009, LONGERON 40 - 41R. REPAIRED AS PER SRM 53-00-15 FIGURE 202 REPAIR 8 REVISION 51. EO 1-5100-7-5001 B2 PART 1. REPAIR CLASSIFIED MAJOR AS PER GMM 6-2-100 REVISION 115.
Part: HINGE BRACKET — CORRODED (RT WING TE FLAP) · corrosion level 2 · airframe 65,254 hrs · 13,965 cycles
RIGHT WING OTBD FLAP, OTBD FORWARD HINGE BRACKET ACTUATOR ATTACH INBD LUG BORE FOUND CORRODED. REWORKED AND FOUND EXCEEDED LIMITS AS PER CMM 57-44-09 REVISION 74. REPAIRED IAW EA 1-5750-162400 PART 1, STEP 1, 2, 3, 4, 5, 6, 9 AND 10, . WASHER AT OUTBOARD HINGE BRACKET ACTUATOR ATTACH LUG INSTALLED AS PER AMM 27-52-02-4 REVISION 74.1. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REVISION 115.
Part: LONGERON — CRACKED (L3L) · airframe 65,254 hrs · 13,965 cycles
X-RAY INSPECTION FOUND CRACKED INDICATION APPROX 2" IN LENGTH AT CABIN, STATION 5-123, LONGERON 3 LT AFT SECTION EDGE. REPAIRED AS PER SRM 53-00-05 FIGURE 202 REPAIR 1 REVISION 51. NEW LONGERON SEGMENT FABRICATED AS PER DRAWING AFA7771 REVISION C AND INSTALLED PER SRM 51-31-01 REVISION 51. REPAIR CLASSIFIED MAJOR AS PER GMM 6-2-100 REVISION 115.
Part: HINGE BRACKET — CORRODED (LT WING TE FLAP) · corrosion level 2 · airframe 65,254 hrs · 13,965 cycles
LEFT WING OTBD FLAP, INBD FORWARD HINGE BRACKET ACTUATOR ATTACH OTBD LUG BORE FOUND CORRODED. REWORKED AND FOUND EXCEEDED LIMITS AS PER CMM 57-44-08 REVISION 74. REPAIRED PER EA 1-5750-163540 PART 1. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REVISION 115.
Part: BRACKET — CORRODED (LT WING TE FLAP) · corrosion level 2 · airframe 65,254 hrs · 13,965 cycles
LEFT WING OTBD FLAP, OTBD FORWARD HINGE BRACKET ACTUATOR ATTACH INBD LUG BORE FOUND CORRODED. FOUND EXCEEDED LIMITS AS PER CMM 57-44-09 REVISION 74. EXISTING HOLE DIAMETER = 1.224 INCH, FINAL HOLE DIAMETER = 1.228 INCH, MAXIMUM HOLE DIAMETER = 1.220 INCH. REPAIRED PER EA 1-5750-162399 PART 1. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REVISION 115.
Part: BRACKET — CORRODED (LT WING TE FLAP) · airframe 65,254 hrs · 13,965 cycles
LT WING OTBD FLAP, OTBD FORWARD HINGE BRACKET ACTUATOR ATTACH OTBD LUG BORE FOUND CORROSION. FOUND EXCEEDED LIMIT AS PER MD-11 CMM 57-44-09 REVISION 74. EXISTING HOLE DIAMETER = 1.223 INCH, FINAL HOLE DIAMETER = 1.226 INCH, MAXIMUM HOLE DIAMETER = 1.220 INCH. REPAIR ACCOMPLISHED PER EA 1-5750-162399 PART 1. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REVISION 115.
Part: HINGE BRACKET — CORRODED (LT WING TE FLAP) · corrosion level 2 · airframe 65,254 hrs · 13,965 cycles
LT WING OTBD FLAP, INBD FORWARD HINGE BRACKET ACTUATOR ATTACH INBD LUG BORE FOUND CORRODED. REWORKED AND FOUND EXCEEDED LIMIT AS PER CMM 57-44-08 REVISION 74. REPAIRED PER EA 1-5750-163540 PART 1. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REVISION 115.
Part: SKIN — MISREPAIRED (ZONE 500) · airframe 65,254 hrs · 13,965 cycles
LT WING INBD FLAP UPPER SURFACE LOWER SKIN BETWEEN XIFH 269 AND XIFH 293 MISREPAIRED. REPAIRED IAW SRM 57-00-01 FIGURE 201 REPAIR 2 REVISION 51 AND E.A. 1-5750-163534 STEP 7 PART 1.
Part: SEAT TRACK — CORRODED (BS 1890) · airframe 65,254 hrs · 13,965 cycles
LEFT BS 1890, X = 3 SEAT TRACK FOUND CORRODED.
Part: VANE — DELAMINATED (RT WING TE FLAP) · airframe 65,254 hrs · 13,965 cycles
RT WING INBD FLAP VANE LOWER SURFACE FOUND DELAMINATED. REMOVED AND REPLACED AS PER AMM 27-50-22-4 REVISION 74.1. ADJUSTMENT AND TEST CARRIED OUT PER AMM 27-50-00-5 REVISION 74.1 FOUND SATISFACTORY. REPAIR CLASSIFIED MINOR PER GMM 6-2-100 REVISION 115.
Part: SKIN — MISREPAIRED (LT WING TE FLAP) · airframe 65,254 hrs · 13,965 cycles
LT WING NR 2 SLAT INNER SKIN AT XIS 275 MISREPAIRED. REPAIRED PER SRM 57-40-01 FIGURE 201 REPAIR 1 REVISION 51 AND EA 1-5750-163553. REPAIR CLASSIFIED MAJOR AS PER GMM 6-2-100 REVISION 115.
Part: SKIN — MISREPAIRED (ZONE 500) · airframe 65,254 hrs · 13,965 cycles
LT WING INBD FLAP LOWER SURFACE LOWER SKIN BETWEEN XIFH 269 AND XIFH 288 MISREPAIRED. REPAIRED IAW SRM 57-50-01 FIGURE 201 REPAIR 1 REVISION 51 AND EA 1-5750-163534 STEP 11 PART 1. REPAIR CLASSIFIED MAJOR AS PER GMM 6-2-100 REVISION 115.
Part: SEAT TRACK — CORRODED (BS 1890) · corrosion level 2 · airframe 65,254 hrs · 13,965 cycles
BS 1890, X = -3 SEAT TRACK FOUND CORRODED. R & R IW SRM 51-31-01, REV 51. SEAT TRACK FABRICATED IAW DWG AGA7080 REVISION S. REPAIR CLASSIFIED MAJOR IAW GMM 6-2-100, REV 115.
Part: SKIN — MISREPAIRED (LT WING TE FLAP) · airframe 65,254 hrs · 13,965 cycles
LT WING INBD FLAP UPPER SURFACE CENTER BOX BETWEEN XIFH 281 AND XIFH 288 MISREPAIRED. REPAIRED IAW SRM 57-00-01 FIGURE 201 SHEET 2 REPAIR 1 REVISION 51 AND EA 1-5750-163534 STEP 2 PART 1. REPAIR CLASSIFIED MAJOR AS PER GMM 6-2-100 REVISION 115.
Part: SKIN — MISREPAIRED (NR 3 SLAT) · airframe 65,254 hrs · 13,965 cycles
LT WING NR 3 SLAT ASSY UPPER SKIN XOS 429.446 MISREPAIRED. REPAIRED IAW EA 1-5750-163527. REPAIR CLASSIFIED MAJOR IAW GMM 6-2-100 REV 115.
Part: FRAME — MISREPAIRED (BS 535) · airframe 65,254 hrs · 13,965 cycles
FRAME MISREPAIRED AT CABIN LT BS 535, 9G NET LOWER SUPPORT YOKE AT LONGERON 24 LT. CARRIED OUT REPAIR IAW SRM 53-20-07, FIG 201, REPAIR 1, REV 51. REPAIR CLASSIFIED MAJOR IAW GMM 6-2-100 REV 115.
Part: SKIN — CRACKED (NR 8 SLAT) · airframe 65,254 hrs · 13,965 cycles
RT WING NR 8 SLAT LOWER SURFACE FOUND CRACKED. REPAIRED IAW SRM 57-40-01, FIG 201 REPAIR 3, REV 51 AND EA 1-5750-163529. REPAIR CLASSIFIED MAJOR IAW GMM 6-2-100, REV 115.
Part: FRAME — MISREPAIRED (BS 535) · airframe 65,254 hrs · 13,965 cycles
FRAME MISREPAIRED AT CABIN LT BS 535, 9G NET UPPER SUPPORT YOKE AT LONGERON 18 LT. REPAIRED IAW SRM 53-20-07, FIG 202, REPAIR 1, REV 51. REPAIR CLASSIFIED MAJOR IAW GMM 6-2-100 REV 115.
Part: SEAT TRACK — CORRODED (BS 1805) · corrosion level 2 · airframe 65,254 hrs · 13,965 cycles
BS 1805 'X' = -8.5 SEAT TRACK FOUND CORRODED. REPAIRED IAW SRM 53-00-52, FIGURE 201, REPAIR 1, REVISION 51. REPAIR CLASSIFIED MAJOR IAW GMM 6-2-100 REVISION 115.
Part: SEAT TRACK — CORRODED (BS 1611) · corrosion level 2 · airframe 65,254 hrs · 13,965 cycles
BS 1611 'X' = -8.5 SEAT TRACK FOUND CORRODED. REPAIRED IAW SRM 53-00-52, FIGURE 201, REPAIR 1, REVISION 51. REPAIR CLASSIFIED MAJOR IAW GMM 6-2-100 REVISION 115.
Part: SEAT TRACK — CORRODED (BS 1351) · corrosion level 2 · airframe 65,254 hrs · 13,965 cycles
BS 1351 'X' = 8.5 SEAT TRACK FOUND CORRODED. REPAIRED IAW SRM 53-00-52, FIG 201, REPAIR 1, REV 51. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 115.
Part: SEAT TRACK — CORRODED (BS 1611) · corrosion level 2 · airframe 65,254 hrs · 13,965 cycles
BS 1611 'X' = 8.5 SEAT TRACK FOUND CORRODED. REPAIRED IAW SRM 53-00-52, FIGURE 201, REPAIR 1, REVISION 51. REPAIR CLASSIFIED MAJOR IAW GMM 6-2-100 REVISION 115.
2010
Part: FIRE WARNING — FALSE ACTIVATION (CARGO BAY) · airframe 61,280 hrs · 12,994 cycles
LEVEL 3 CARGO FIRE LOWER AFT IN FLT DISC BOTTLES, ALERT CONTINUED, CAME ON DURING DESCENT. FOLLOWED QRH. RELEASED FOR SERVICE PER MEL: 26-22-01-01-B. FIRE EXTINGUISHER CYLINDER NR 2 INOP. ALL LOWER CARGO COMPARTMENTS MUST REMAIN EMPTY. ON ARRIVAL CHECKED CTR AND AFT BULK CARGO COMPT'S - NO SIGNS OF FIRE OR SMOKE DAMAGE. CARGO FIRE TEST C/W - NO FAULTS FOUND. BOTH FIRE BOTTLES WERE DISCHARGED AND AGENT LOW LIGHTS ILLUM. R & R CARGO COMPT NR 2 FIRE EXTINGUISHER BOTTLE PER AMM 26-22-01-4-0, INSTALLED 2 EA DISCHERGE HEAD PER AMM 26-22-03-4-0, R&R'D 2 EA CARTRIDGE PER AMM 26-22-04-4-0. LOWER CARGO FIRE EXTINGUISHER CIRCUIT TESTED OK PER 26-22-07-05-0, A/C OK FOR SERVICE.
Part: SKIN — CORRODED (LT WING) · airframe 59,485 hrs · 12,532 cycles
SURFACE CORROSION - LT WING UPPER SKIN AFT OF NR 3 SLAT AT XORS 361 STR NR 6. REPAIR CARRIED OUT IAW EA NR1-5730-137587, REPAIR CLASSIFIED AS MINOR IAW GMM 6-2-100 REVISION 109.
Part: SEAT TRACK — CORRODED (BS 1385) · airframe 59,485 hrs · 12,532 cycles
CABIN - RT STA 1385 X = -8.5 SEAT TRACK FOUND CORROSION. CORROSION REMOVED IAW SRM 51-21-01, REVISION 42 AND FOUND EXCEEDED LIMIT IAW SRM 53-00-52 FIGURE 101 REVISION 42. REPAIR CARRIED OUT IAW SRM 53-00-52, FIGURE 201, REPAIR 1 REVISION 42. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100 REVISION 109.
Part: SKIN SPLICE — CRACKED (BS 1992 L48L) · airframe 59,485 hrs · 12,532 cycles
AFT CARGO COMPARTMENT BILGE AREA FOUND LONGERON SKIN SPLICE CRACK AT STA 1992 LONGERON 48L. SPLICE REPLACED AS PER SRM51-31-01 REV42.
Part: SKIN — CRACKED (ZONE 500) · airframe 59,485 hrs · 12,532 cycles
LT WING ANTI-ICE TELESCOPIC DUCT DOOR CUTOUT FOUND INBD AND OTBD CORNER CRACKED. CARRIED OUT REPAIR AT LT WING ANTI-ICE TELESCOPIC DUCT DOOR CUTOUT IAW SRM 57-40-01, FIGURE 101, REVISION 42. REPAIR CLASSIFIED MINOR IAW GMM 6-2-100 REVISION 109.
Part: LONGERON — CORRODED (BS 1771-1781) · airframe 59,485 hrs · 12,532 cycles
CTR CARGO COMPARTMENT BILGE AREA FOUND CORROSION ON LONGERON AT STA 1771 TO STA 1781, LONGERON 46R. REPAIRED IAW SRM 53-00-05 FIG 203 REV 42.
Part: BEAM — CRACKED (DOOR FRAME) · airframe 59,485 hrs · 12,532 cycles
CTR CARGO DOOR CUTOUT UPPER LONGERON FRAME FOUND CRACK AT DOOR ACTUATOR VICINITY. REPAIR CARRIED OUT IAW EA NR 1-5310-137586, TITLE: FUSELAGE -MAIN FRAME-CTR CARGO DOOR UPPER JAMB BEAM CRACK REPAIR AT STA 1746.925. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REVISION 109.
Part: SEAT TRACK — CORRODED (BS 495-525) · airframe 59,485 hrs · 12,532 cycles
CABIN - LT STA 495 TO STA 525 X = 27.5 SEAT TRACK FOUND CORROSION. CORROSION REMOVED IAW SRM 51-21-01 REVISION 42 AND FOUND EXCEEDED LIMIT IAW SRM 53-00-52, FIGURE 101, REVISION 42. REPAIR CARRIED OUT IAW SRM 53-00-52, FIGURE 201, REVISION 42. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REVISION 109.
2009
Part: SWITCH — MALFUNCTIONED (THRUST REVERSER) · airframe 57,184 hrs · 11,981 cycles
NR 1 ENGINE U/L RED LIGHT IN EPR GAUGE ILLUMINATED AT IDLE DESCENDING THROUGH FL 280 RAN QRH AND CONTINUED. AT 8000 FT U/L LIGHT COME ON AGAIN WITH VIBRATIONS, RAN QRH AND SHUT ENGINE DOWN. DFDR DATA RETRIEVED SHOWS AN INTERMITTENT U/L DETECTED IN FLIGHT (MATCHING CREW REPORT). ADJUSTMENT WAS OUT OF LIMIT. ADJUSTED RT LWR STOW SWITCH AND OPS CHECK ALL NORMAL PER MM78-34-01-4. ALSO PERFORMED OPS TEST OF THRUST REVERSER SEVERAL TIMES AND OPS ALL NORMAL PER 78-30-00-5.
2008
Part: VALVE — FAILED (TE FLAPS) · airframe 55,877 hrs · 11,661 cycles
ACFT HAD AN ATB FOR FLAPS SLOW TO RETRACT AND ON GROUND FLAPS ARE STUCK AT 28 DEG. REMOVED AND REPLACED FLAP LIMITER DUPLEX ACTUATOR, IAW AMM 27-56-01-4. REMOVED AND REPLACED INBOARD FLAP CONTROL VALVE IAW AMM 27-52-03-4. REMOVED AND REPLACED SYS 2 INLINE RESTRICTOR VALVE IAW AMM 27-52-09-4.
Part: FLAP SYSTEM — STUCK (TE FLAPS) · airframe 55,877 hrs · 11,661 cycles
ACFT HAD AN ATB FOR FLAPS SLOW TO RETRACT AND ON GROUND FLAPS ARE STUCK AT 28 DEG.
Part: LONGERON — CORRODED (ZONE 100) · corrosion level 2 · airframe 55,403 hrs · 11,564 cycles
AFT CARGO, RIGHT LONGERON 42 AT STA 1955 FOUND CORROSION. AFT CARGO, RIGHT LONGERON 42 AT STA 1955 CARRIED OUT REPAIR AS PER SRM 53-10-00 FIGURE 2 VOLUME I. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100. LONGERON REPAIR WAS ALSO CARRIED OUT IN REFERENCE TO FEDEX EA NR 1-5310-124322, TITLE, FUSELAGE, MAINFRAME, REPAIR RIGHT LONGERON 42L AT STATION 1953.0.
Part: LONGERON — CRACKED (ZONE 700) · airframe 55,403 hrs · 11,564 cycles
01 EACH FASTENER HOLE FOUND CRACK AT 5 AND 9 O'CLOCK POSITIONS (APPROXIMATELY 1/8 INCH LENGTH) AT NOSE LANDING GEAR LEFT SIDE TRUNNION FITTING LOWER LONGERON. CRACK LOWER LONGERON AT NOSE LANDING GEAR LEFT SIDE TRUNNION FITTING REMOVED AND REPLACED AS PER SRM 51-31-01 VOLUME II. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.
Part: SEAT TRACK — CORRODED (ZONE 200) · corrosion level 2 · airframe 55,403 hrs · 11,564 cycles
MAIN DECK SEAT TRACK AT STA 1887 TO STA 1853, X = 8 FOUND CORROSION. MAIN DECK CORRODED SEAT TRACK REPAIRED BY SECTIONAL SEAT TRACK REPLACEMENT AS PER SRM 53-70-00 FIGURE 1 VOLUME I. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.
Part: SEAT TRACK — CORRODED (ZONE 200) · airframe 55,403 hrs · 11,564 cycles
MAIN DECK SEAT TRACK AT STA 1421, X = -8 FOUND CORROSION. MAIN DECK CORRODED SEAT TRACK AT STA 1421, X = -8 REPAIRED BY SECTIONAL SEAT TRACK. REPLACEMENT FROM STA 1411 TO STA 1431, X = -8 AS PER SRM 53-70-00 FIGURE 1 VOLUME I. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.
Part: SEAT TRACK — CORRODED (ZONE 200) · airframe 55,403 hrs · 11,564 cycles
MAIN DECK SEAT TRACK AT STA 1481, X = 8 FOUND CORROSION. MAIN DECK CORRODED SEAT TRACK AT STA 1481, X = 8 REPAIRED BY SECTIONAL SEAT TRACK REPLACEMENT FROM STA 1471 TO STA 1531, X = 8 AS PER SRM 53-70-00 FIGURE 1 VOLUME I. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.
Part: SEAT TRACK — CORRODED (ZONE 200) · corrosion level 2 · airframe 55,403 hrs · 11,564 cycles
MAIN DECK SEAT TRACK AT STA 1259, X = -27 FOUND CORROSION. MAIN DECK CORRODED SEAT TRACK REPAIRED BY SECTIONAL SEAT TRACK REPLACEMENT AS PER SRM 53-70-00 FIGURE 1 VOLUME I. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.
Part: SKIN — CRACKED (ZONE 600) · airframe 55,403 hrs · 11,564 cycles
13 EACH FASTENER HOLES FOUND CRACK INDICATION DURING HFEC OPEN HOLE INSPECTION AT RT WING LOWER SKIN ACCESS DOOR CUTOUT BETWEEN STA XORS 690 AND STA XORS 700. RT WING LOWER SKIN ACCESS DOOR CUTOUT BETWEEN STA XORS 690 AND STA XORS 700, 13 EACH CRACKED FASTENER HOLES REPAIRED AS PER EA NR1-5710-124332, REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100.
Part: SPAR — DAMAGED (ZONE 600) · airframe 55,403 hrs · 11,564 cycles
RIGHT WING, DURING ACCOMPLISHMENT OF EA NR 1-5710-105596C PART 2, REAR SPAR LOWER CHORD FORWARD AND AFT TENSION TIES AT STA XORS 1088 FOUND FASTENER HOLE ELONGATED. ELONGATED HOLE AT REAR SPAR LOWER CHORD FORWARD AND AFT TENSION TIES AT STA XORS 1088. REPAIRED AS PER EA NR 1-5710-124327, REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.
Part: SKIN — CRACKED (ZONE 500) · airframe 55,403 hrs · 11,564 cycles
06 EACH FASTENER HOLES FOUND CRACK INDICATION DURING HFEC OPEN HOLE INSPECTION AT LEFT WING LOWER SKIN ACCESS DOOR CUTOUT BETWEEN STA XORS 690 AND STA XORS 700. LEFT WING LOWER SKIN ACCESS DOOR CUTOUT BETWEEN STA XORS 690 AND STA XORS 700 06 EACH CRACKED FASTENER HOLES REPAIRED AS PER EA NR 1-5710-124333, REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100.
Part: SEAT TRACK — DAMAGED (ZONE 200) · airframe 55,403 hrs · 11,564 cycles
MAIN DECK SEAT TRACK AT STA 755, X = 47.5 FOUND DAMAGED. MAIN DECK DAMAGED SEAT TRACK AT STA 755, X = 47.5 REPAIRED BY SECTIONAL SEAT TRACK. REPLACEMENT FROM STA 725 TO STA 765, X = 47.5 AS PER SRM 53-70-00 FIGURE 1 VOLUME I. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.
Part: SEAT TRACK — CORRODED (BS 1531) · airframe 55,403 hrs · 11,564 cycles
MAIN DECK SEAT TRACK AT STA 1531, X = -75.5 FOUND CORROSION. MAIN DECK SEAT TRACK AT STA 1531, X = -75.5 CORROSION REMOVED AS PER SRM 51-21-01 VOLUME II. ORIGINAL MATERIAL THICKNESS = 0.100", REMAINING THICKNESS = 0.096 INCH, MATERIAL REMOVED = 0.004 INCH AND FOUND WITH LIMIT AS PER SRM 53-70-00 FIGURE 3 VOLUME I. REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100.
Part: SUPPORT FITTING — CRACKED (ZONE 200) · airframe 55,403 hrs · 11,564 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, B, C AND D. MAIN CARGO DOOR LOWER JAMB CRACKED NR 1 SUPPORT FITTING REMOVED AND REPLACED AS PER SRM 51-31-01 VOLUME II. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.
Part: DOOR FRAME — CRACKED (ZONE 200) · airframe 55,403 hrs · 11,564 cycles
CRACK INDICATION FOUND ON SECOND LAYER DURING HFEC OPEN HOLE INSPECTION ON 0.520 INCH HOLE AT MAIN CARGO DOOR NR 7 LOWER JAMB AT HOLE B. MAIN CARGO DOOR NR 7 LOWER JAMB AT HOLE B, CRACKED SECOND LAYER REPAIRED AS PER FEDEX EA NR 1-5310-124330, TITLE: FUSELAGE, MAINFRAME, MAIN CARGO DOOR LOWER JAMB BORE HOLES AT STA 757.708. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.
Part: SUPPORT FITTING — CRACKED (ZONE 200) · airframe 55,403 hrs · 11,564 cycles
CRACK INDICATION FOUND DURING HFEC OPEN HOLE INSPECTION ON 0.460 INCHES HOLES AT MAIN CARGO DOOR LOWER JAMB NR 7 SUPPORT FITTING AT HOLES A, B, C AND D. MAIN CARGO DOOR LOWER JAMB CRACKED NR 7 SUPPORT FITTING REMOVED AND REPLACED AS PER SRM 51-31-01 VOLUME II. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.
Part: BEAM — CRACKED (CARGO DOOR) · airframe 55,403 hrs · 11,564 cycles
CRACK INDICATION FOUND SECOND LAYER DURING HFEC OPEN HOLE INSPECTION ON 0.520 INCH HOLE AT MAIN CARGO DOOR NR 7 LOWER JAMB AT HOLE C. MAIN CARGO DOOR NR 7 LOWER JAMB AT HOLE C, CRACKED SECOND LAYER REPAIRED AS PER FEDEX EA NR 1-5310-124330, TITLE: FUSELAGE, MAINFRAME, MAIN CARGO DOOR LOWER JAMB BORE HOLES AT STA 757.708. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.
Part: TRUNNION — CRACKED (NLG) · airframe 55,403 hrs · 11,564 cycles
NOSE LANDING GEAR WHEEL WELL LEFT TRUNNION FITTING FOUND CRACKED. TRIMMED OUT AND REPAIR CARRIED OUT AS PER SRM 53-40-00 FIGURE 23 VOLUME I. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.
Part: DOOR FRAME — CRACKED (ZONE 200) · airframe 55,403 hrs · 11,564 cycles
CRACK INDICATION FOUND ON FIRST LAYER DURING HFEC OPEN HOLE INSPECTION ON 0.520" HOLE AT MAIN CARGO DOOR NR 6 LOWER JAMB AT HOLE C. MAIN CARGO DOOR NR 6 LOWER JAMB AT HOLE C, CRACK ON FIRST LAYER REPAIRED AS PER FEDEX EA NR 1-5310-124331, REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.
Part: SUPPORT FITTING — CRACKED (ZONE 200) · airframe 55,403 hrs · 11,564 cycles
CRACK INDICATION FOUND DURING HFEC OPEN HOLE INSPECTION ON 0.460 INCHES HOLES AT MAIN CARGO DOOR LOWER JAMB NR 4 SUPPORT FITTING AT HOLES A, B, C AND D. MAIN CARGO DOOR LOWER JAMB CRACKED NR 4 SUPPORT FITTING REMOVED AND REPLACED AS PER SRM 51-31-01 VOLUME II. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.
Part: SUPPORT FITTING — CRACKED (ZONE 200) · airframe 55,403 hrs · 11,564 cycles
CRACK INDICATION FOUND DURING HFEC OPEN HOLE INSPECTION ON 0.460 INCH HOLES AT MAIN CARGO DOOR LOWER JAMB NR 3 SUPPORT FITTING AT HOLES A, B, C AND D. MAIN CARGO DOOR LOWER JAMB CRACKED NR 3 SUPPORT FITTING REMOVED AND REPLACED AS PER SRM 51-31-01 VOLUME II. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.
Part: FITTING — CRACKED (ZONE 200) · airframe 55,403 hrs · 11,564 cycles
CRACK INDICATION FOUND DURING HFEC OPEN HOLE INSPECTION ON 0.460" HOLES AT MAIN CARGO DOOR LOWER JAMB NR 6 SUPPORT FITTING AT HOLES A, B, C AND D. MAIN CARGO DOOR LOWER JAMB CRACKED NR 6 SUPPORT FITTING REMOVED AND REPLACED AS PER SRM 51-31-01 VOLUME II. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.
Part: SUPPORT FITTING — CRACKED (ZONE 200) · airframe 55,403 hrs · 11,564 cycles
CRACK INDICATION FOUND DURING HFEC OPEN HOLE INSPECTION ON 0.460" HOLES AT MAIN CARGO DOOR LOWER JAMB NR 5 SUPPORT FITTING AT HOLES A, B, C AND D. MAIN CARGO DOOR LOWER JAMB CRACKED NR 5 SUPPORT FITTING REMOVED AND REPLACED AS PER SRM 51-31-01 VOLUME II. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.
Part: SPAR CAP — DAMAGED (ZONE 500) · airframe 55,403 hrs · 11,564 cycles
LEFT WING, UPPER SPAR CAP FASTENER HOLE AT STA XORS 878 FOUND ELONGATED. LEFT WING UPPER SPAR CAP STA XORS 878 ELONGATED HOLE REPAIRED AS PER FEDEX EA NR 1-5710-124328, TITLE: WINGS BASIC WING STRUCTURE, LEFT WING UPPER SPAR STA XORS = 878, ELONGATED HOLE REPAIR. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.
Part: SUPPORT FITTING — CRACKED (ZONE 200) · airframe 55,403 hrs · 11,564 cycles
CRACK INDICATION FOUND DURING HFEC OPEN HOLE INSPECTION ON 0.460 INCH HOLES AT MAIN CARGO DOOR LOWER JAMB NR 2 SUPPORT FITTING AT HOLES A, B, C AND D. MAIN CARGO DOOR LOWER JAMB CRACKED NR 2 SUPPORT FITTING REMOVED AND REPLACED AS PER SRM 51-31-01 VOLUME II. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.
2007
Part: A/C PACK — CONTAMINATED · airframe 53,058 hrs · 10,951 cycles
AT 100KTS ON T/O ROLL RECEIVED LEVEL-3 CABIN SMOKE ALERT. TAKEOFF ABORTED. LIGHT REMAINED ON 3 SECONDS AND NEVER REILLUMINATED. ALL OTHER INDICATIONS OF FIRE NEGATIVE. COMPLIED WITH RTS ON ESC ALL RTS PASS. A/C WAS DEICED PRIOR TO A/C DEPERATURE SUSPECT DEICING FLUID INGESTED INTO PACKS. ALL SYSTEM CHECK GOOD. A/C OK FOR SERVICE.
Part: SEAT TRACK — CORRODED (ZONE 100) · airframe 52,666 hrs · 10,859 cycles
AFT CARGO COMPARTMENT, SEAT TRACK AT STA 1846, X= 20 CORRODED. REPAIRED AS PER SRM 53-70- 00 VOLUME I FIGURE 1. REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100.
Part: FITTING — CORRODED (ZONE 500) · airframe 52,666 hrs · 10,859 cycles
LT WING OUTBOARD TRAILING EDGE FLAP FITTING ARC4009 FASTENER HOLES CORROSION BEYOND LIMIT. LT WING OUTBOARD FLAP REMOVED AND REPLACED AS PER AMM 27-50-30. P/N ON: NRC6753-503, S/N ON: 098 REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100.
Part: DOUBLER — CORRODED (ZONE 600) · airframe 52,666 hrs · 10,859 cycles
RT WING UPPER SURFACE DOUBLER AT XORS 264 FOUND CORROSION. REPAIRED AS PER FEDEX E.A. 1-5710-105593, REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.
Part: STRUCTURE — CRACKED (ZONE 700) · airframe 52,666 hrs · 10,859 cycles
LANDING GEAR: LT LDG AT FLIPPER DOOR FWD SIDE FOUND CRACKED. LANDING GEAR, LT LDG AT FLIPPER DOOR FWD SIDE REPAIRED AS PER SRM 52-10-00 VOLUME I, FIGURE 18. REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100.
Part: SKIN — CORRODED (ZONE 600) · airframe 52,666 hrs · 10,859 cycles
RT WING UPPER SURFACE TRAILING EDGE MOST INBD FOUND CORROSION. REPAIRED AS PER FEDEX E.A. 1-5710-107764, THIS REPAIR IS CLASSIFIED AS MAJOR PER GMM 6-2-100.
Part: SKIN — DELAMINATED (ZONE 600) · airframe 52,666 hrs · 10,859 cycles
RIGHT WING, INBOARD FLAP VANE LOWER INBOARD SURFACE FOUND DELAMINATED. REPAIRED AS PER FEDEX E.A. 1-5750-105603, REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100.
Part: SKIN — DELAMINATED (ZONE 500) · airframe 52,666 hrs · 10,859 cycles
LEFT WING, INBOARD FLAP VANE LOWER OUTBOARD SURFACE FOUND DELAMINATED. REPAIRED AS PER FEDEX E.A. 1-5750-105602, REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100.
Part: DOUBLER — CRACKED (ZONE 600) · airframe 52,666 hrs · 10,859 cycles
FOUND RIGHT WING, FIXED LEADING EDGE FINGER DOUBLER AT XOS= 584 CRACKED. REMOVED CRACKED FINGER DOUBLER SHIM AND FABRICATED NEW DOUBLER SHIM AS PER SRM 57-00-01 VOLUME I. INSTALLED NEW DOUBLER SHIM AT RIGHT HAND WING FIXED LEADING EDGE FINGER DOUBLER SHIM AT XOS = 584 AS PER SRM 51-31-01 VOLUME II. REPAIR CLASSIFIED MINOR PER GMM 6-2-100.
Part: FRAME — DENTED (ZONE 200) · airframe 52,666 hrs · 10,859 cycles
MAIN DECK CARGO COMPARTMENT: MAIN FRAME STA 1781 LONGERON 12R FOUND DENTED. REPAIR CARRIED OUT AS PER SRM 53-30-00 VOLUME I FIGURE 1. INITIAL INSPECTION REQUIRED AT 14,500 CYCLES AND REPETITIVE INSPECTION REQUIRED EVERY 9,500 CYCLES THEREAFTER AS PER SRM 53-30-00 VOLUME I FIGURE 1. REPAIR CLASSSIFIED AS MAJOR PER GMM 6-2-100.
Part: DOUBLER — CRACKED (ZONE 500) · airframe 52,666 hrs · 10,859 cycles
FOUND LEFT WING, FIXED LEADING EDGE BEADED DOUBLER AT XOS= 665 CRACKED. REPAIRED AS PER SRM 57-10- 00 VOLUME I, FIGURE 25. REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100.
Part: FRAME — DENTED (ZONE 200) · airframe 52,666 hrs · 10,859 cycles
MAIN DECK CARGO COMPARTMENT MAIN FRAME STA 1701 LONGERON 12L FOUND DENTED. REPAIR CARRIED OUT AS PER SRM 53-30-00 VOLUME I FIGURE 1. INITIAL INSPECTION REQUIRED AT 14,500 CYCLES AND REPETITIVE INSPECTION REQUIRED EVERY 9,500 CYCLES THEREAFTER AS PER SRM 53-30-00 VOLUME I FIGURE 1. REPAIR CLASSSIFIED AS MAJOR PER GMM 6-2-100.
Part: FRAME — DENTED (ZONE 200) · airframe 52,666 hrs · 10,859 cycles
MAIN DECK CARGO COMPARTMENT: MAIN FRAME STA 1661 LONGERON 12L AREA EXISTING REPAIR DOUBLER FOUND DAMAGED. REPAIR CARRIED OUT AS PER SRM 53-30-00 VOLUME I FIGURE 1. INITIAL INSPECTION REQUIRED AT 14,500 CYCLES AND REPETITIVE INSPECTION REQUIRED EVERY 9,500 CYCLES THEREAFTER AS PER SRM 53-30-00 VOLUME I FIGURE 1. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100. OIL CONTOL NO.: 304445, WRI: 53-10/5267
Part: SKIN — DELAMINATED (ZONE 500) · airframe 52,666 hrs · 10,859 cycles
LEFT WING, INBOARD FLAP VANE LOWER OUTBOARD SURFACE FOUND DELAMINATED. REPAIRED AS PER FEDEX E.A. 1-5750-105602, REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100.
Part: SLAT TRACK — CRACKED (ZONE 600) · airframe 52,666 hrs · 10,859 cycles
RIGHT WING FIXED LEADING EDGE SLAT TRACK 14 CUT-OUT FOUND CRACKED. REPAIRED AS PER SRM 57-10-00 FIGURE 21 VOLUME I. REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100.
Part: SLAT TRACK — CRACKED (ZONE 600) · airframe 52,666 hrs · 10,859 cycles
RIGHT WING FIXED LEADING EDGE SLAT TRACK 12 CUT-OUT FOUND CRACKED. REPAIRED AS PER SRM 57-10-00 FIGURE 21 VOLUME I. REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100.
Part: KEELBEAM — DENTED (ZONE 700) · airframe 52,666 hrs · 10,859 cycles
CENTER LANDING GEAR, RT SIDE KEEL BEAM WEB AT DRAG BRACE FOUND BEAM CORRODED. CORROSION REMOVED ON BOOTSTRAP AT CENTER LANDING GEAR RIGHT HAND SIDE KEEL BEAM WEB AS PER SRM 53-00-01 VOLUME I FIGURE 1A AND MACHINED NEW BOOTSTRAP AS PER DWG AEA7131. NEW BOOTSTRAP INSTALLED AS PER SRM 51-33-01 VOLUME II. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100
Part: SPAR CAP — CORRODED (ZONE 500) · airframe 52,666 hrs · 10,859 cycles
LT WING, TRAILING EDGE REAR SPAR UPPER CAP LOWER SURFACE AT XORS= 1047 WAS FOUND WITH CORROSION. COMPLIED WITH FEDEX E.A. 1-5710-105595, REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.
Part: SKIN — CORRODED (ZONE 600) · airframe 52,666 hrs · 10,859 cycles
RT WING UPPER SKIN LOWER SURFACE FOUND CORROSION AT XORS= 720 TO XORS= 726. COMPLIED WITH FEDEX E.A 1-5720-106578, REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.
Part: SEAT TRACK — CORRODED (ZONE 200) · airframe 52,666 hrs · 10,859 cycles
MAIN DECK CARGO COMPARTMENT: SEAT TRACK STA Y = 1356, X = -27.5 FOUND CORRODED. REPAIR CARRIED OUT AS PER SRM 53-70-00 FIGURE 1 VOLUME I. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.
Part: SEAT TRACK — CORRODED (ZONE 200) · airframe 52,666 hrs · 10,859 cycles
MAIN DECK CARGO COMPARTMENT: SEAT TRACK STA Y = 1356, X = -8.5 FOUND CORRODED. REPLACEMENT AS PER SRM 53-70-00 FIGURE 1 VOLUME I. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.
Part: SEAT TRACK — CORRODED (ZONE 200) · airframe 52,666 hrs · 10,859 cycles
MAIN DECK CARGO COMPARTMENT: SEAT TRACK STA Y = 1185, X = -8.5 FOUND CORRODED. REPLACEMENT FROM STA 1811 TO STA 1885, X= -8.5 AS PER SRM 53-70-00 FIGURE 1 VOLUME I. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.
Part: SPAR CAP — CORRODED (RT WING) · airframe 52,666 hrs · 10,859 cycles
RT WING REAR SPAR UPPER CAP LOWER SURFACE FOUND CORROSION AT X0RS= 1047 TO X0RS= 1053. COMPLIED WITH FEDEX E.A.# 1-5710-105597, REPAIR IS CLASSIFIED AS MAJOR PER GMM 6-2-100.
Part: SEAT TRACK — CORRODED (ZONE 200) · airframe 52,666 hrs · 10,859 cycles
MAIN DECK CARGO COMPARTMENT, SEAT TRACK STA Y = 1149, X = -8.5 FOUND CORRODED. REPAIRED AS PER SRM 53-70-00 FIGURE 1 VOLUME 1. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.
Part: SEAT TRACK — CORRODED (ZONE 200) · airframe 52,666 hrs · 10,859 cycles
MAIN DECK CARGO COMPARTMENT: SEAT TRACK STA Y = 1189, X = -8.5 FOUND CORRODED. REPLACEMENT CARRIED OUT FROM STA 1129 TO STA 1229, X= 8.5 AS PER SRM 53-70-00 FIGURE 1 VOLUME 1. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.
Part: LONGERON SPLICE — CRACKED (ZONE 100) · airframe 52,666 hrs · 10,859 cycles
CAC: LEFT COMPARTMENT AT APPROX LONGERON 38L FOUND LONGERON SPLICE CRACKED. COMPLIED WITH FEDEX E.A. 1-5310-106576, REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100.
Part: SKIN — CHAFED (ZONE 100) · airframe 52,666 hrs · 10,859 cycles
FWD CARGO DOOR CUT-OUT, FWD DOOR JAMB FUSELAGE SKIN FOUND WITH SCRATCHES AT LONGERON 41R. REPAIRED AS PER SRM 53-50-00 VOLUME I FIGURE 16. REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100.
Part: SKIN — CORRODED (ZONE 600) · airframe 52,666 hrs · 10,859 cycles
RIGHT WING UPPER SURFACE CORROSION AT XORS 1011. COMPLIED WITH FEDEX E.A.# 1-5710-105601, REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100.
Part: SPAR CAP — CORRODED (ZONE 600) · airframe 52,666 hrs · 10,859 cycles
RIGHT WING REAR SPAR CAP UPPER SURFACE FOUND CORROSION AT XORS=1046. COMPLIED WITH FEDEX E.A. 1-5710-105597, REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.
Part: SKIN — CHAFED (ZONE 100) · airframe 52,666 hrs · 10,859 cycles
CENTER CARGO DOOR CUTOUT, AFT DOOR JAMB FUSELAGE SKIN FOUND WITH SCRATCHES AT LONGERON 40R. REPAIRED AS PER SRM 53-50-00 VOLUME 1 FIGURE 16. REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100.
Part: SPAR — CORRODED (ZONE 500) · airframe 52,666 hrs · 10,859 cycles
LT WING, TRAILING EDGE REAR SPAR LOWER CHORD AT XORS 1042 TO 1070 FOUND WITH CORROSION. COMPLIED WITH FEDEX E.A. 1-5710-105594, REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.
Part: SPAR CAP — CORRODED (ZONE 600) · airframe 52,666 hrs · 10,859 cycles
RT WING REAR SPAR LOWER CAP UPPER SURFACE FOUND CORROSION AT XORS 1075 TO 1082. COMPLIED WITH FEDEX E.A. 1-5710-105596, REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2- 100.
Part: SPAR CAP — CORRODED (ZONE 600) · airframe 52,666 hrs · 10,859 cycles
RT WING REAR SPAR LOWER CAP UPPER SURFACE FOUND CORROSION AT XORS 1062 TO 1072. COMPLIED WITH FEDEX E.A. 1-5710-105596, REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.
Part: SKIN — CHAFED (ZONE 600) · airframe 52,666 hrs · 10,859 cycles
RT WING FIXED LEADING EDGE OUTBOARD OF NR 8 SLAT FOUND WITH CHAFE MARKS. REPAIR CARRIED OUT AS PER FEDEX E.A. 1-5720-105587, REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100.
Part: SPAR CAP — CORRODED (ZONE 600) · airframe 52,666 hrs · 10,859 cycles
RT WING REAR SPAR LOWER CAP UPPER SURFACE FOUND CORROSION AT XORS 1050 TO 1059. REPAIRED AS PER FEDEX E.A. 1-5710-105596, REPAIR IS CLASSIFIED AS MAJOR PER GMM 6-2-100.
2006
Part: STRINGER — CRACKED (LEFT WING) · airframe 52,666 hrs · 10,859 cycles
HFEC INSPECTION CARRIED OUT AND FOUND CRACK AT LT WING S-11 END WITH LENGTH OF APPROX 10.5". REPAIR CARRIED OUT AS PER SRM 57-20-00 FIG. 10 VOL.I. FABRICATED & INSTALLED REPAIR PARTS AS PER SRM 57-20-00 FIG.10 VOL.I REPAIR CLASSIFIED AS MAJOR AS PER FEDEX GMM 6-2-100
Part: STRINGER — CRACKED (ZONE 500) · airframe 52,666 hrs · 10,859 cycles
HFEC INSPECTION CARRIED OUT AND FOUND CRACK AT LT WING S-41 END WITH LENGTH OF APPROX 1.5". HFEC INSPECTION CARRIED OUT AND FOUND CRACK AT LH WING S-41 END WITH LENGTH OF APPROX. 1.5" REPAIRED AS PER SRM 57-20-00 VOLUME I FIGURE 10. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.
Part: DUCT — CRACKED (ZONE 600) · airframe 52,666 hrs · 10,859 cycles
RT WING FIXED LEADING EDGE TELESCOPIC DUCT CUTOUT FOUND CRACKED. REPAIR CARRIED OUT AT RIGHT HAND WING FIXED LEADING EDGE TELESCOPIC DUCT CUTOUT AS PER FEDEX E.A.1-5730-105586, REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100.
Part: STRINGER — CRACKED (ZONE 500) · airframe 52,666 hrs · 10,859 cycles
CRACK FOUND APPROX 2 INCHES IN LENGTH DURING HFEC INSPECTION ON LT WING TANK AT THE END OF STRINGER 12. REPAIRED AS PER SRM 57-20-00 VOLUME I FIGURE 10. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.
Part: STRINGER — CRACKED (ZONE 600) · airframe 52,666 hrs · 10,859 cycles
HFEC INSPECTION CARRIED OUT AND FOUND CRACK AT RT WING S-43 END WITH LENGTH OF APPROX 1". REPAIRED AS PER SRM 57-20-00 VOLUME I FIGURE 10. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.
Part: STRINGER — CRACKED (ZONE 500) · airframe 52,666 hrs · 10,859 cycles
CRACK FOUND APPROX 11 INCHES IN LENGTH DURING HFEC INSPECTION ON LT WING TANK AT THE END OF STRINGER 14. CRACK FOUND APPROX. 11 INCHES IN LENGTH DURING HFEC INSPECTION ON LH WING TANK AT THE END OF STRINGER 14 REPAIRED AS PER SRM 57-20-00 VOLUME I FIGURE 10. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.
Part: STRINGER — CRACKED (ZONE 500) · airframe 52,666 hrs · 10,859 cycles
CRACK FOUND APPROX 3 INCHES IN LENGTH DURING HFEC INSPECTION ON LT WING TANK AT THE END OF STRINGER 44. CRACK FOUND APPROX. 3 INCHES IN LENGTH DURING HFEC INSPECTION ON LT WING TANK AT THE END OF STRINGER 44 REPAIRED AS PER SRM 57-20-00 VOLUME I FIGURE 10. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.
Part: STRINGER — CRACKED (ZONE 600) · airframe 52,666 hrs · 10,859 cycles
HFEC INSPECTION CARRIED OUT AND FOUND CRACK AT RT WING S-42 END WITH LENGTH OF APPROX 1". REPAIRED AS PER SRM 57-20-00 VOLUME I FIGURE 10. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.
Part: STRINGER — CRACKED (ZONE 500) · airframe 52,666 hrs · 10,859 cycles
CRACK FOUND APPROX 2 INCHES IN LENGTH DURING HFEC INSPECTION ON LT WING TANK AT THE END OF STRINGER 43. REPAIRED AS PER SRM 57-20-00 VOLUME I FIGURE 10. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.
Part: STRINGER — CRACKED (ZONE 600) · airframe 52,666 hrs · 10,859 cycles
HFEC INSPECTION CARRIED OUT AND FOUND CRACK AT RT WING S-44 END WITH LENGTH OF APPROX 1". REPAIRED AS PER SRM 57-20-00 VOLUME I FIGURE 10. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.
Part: STRINGER — CRACKED (ZONE 500) · airframe 52,666 hrs · 10,859 cycles
CRACK FOUND APPROX 12 INCHES IN LENGTH DURING HFEC INSPECTION ON LT WING TANK AT THE END OF STRINGER 42. CRACK FOUND APPROX. 2 INCHES IN LENGTH DURING HFEC INSPECTION ON LT WING TANK AT THE END OF STRINGER 42 REPAIRED AS PER SRM 57-20-00 FIGURE 10 VOLUME I. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.
2005
Part: DOUBLER — CRACKED (KEELBEAM) · airframe 47,942 hrs · 9,821 cycles
CTR LANDING GEAR FWD BULKHEAD, LT SIDE WALL, KEEL BEAM DOUBLER FOUND CRACKED. CTR LANDING GEAR FWD BULKHEAD LH SIDEWALL KEEL BEAM DOUBLER REMOVED AND REPLACED AS PER SRM 51-33-01 VOL.II. THIS REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2- 100.
Part: SKIN — CORRODED (ZONE 600) · airframe 47,942 hrs · 9,821 cycles
RIGHT HAND WING UPPER SURFACE TRAILING EDGE FORWARD OF NR 2 SPOILER SKIN BULGE AT XORS 536 STRINGER 1. RHW UPPER SURFACE TRAILING EDGE FORWARD OF NR 2 SPOILER XORS 536 STRINGER 1 SKIN BULGE AREA CORROSION REMOVED. MAT'L REMOVED: 0.032"; ORIG. THICKNESS: 0.310"; MAT'L REMAINED: 0.278"; FOUND EXCEED LIMIT AS PER SRM 57-10-00 FIG. 32 VOL.I. AREA REPAIR CARRIED OUT AS PER FEDEX EA 1-5710-87562 - WINGS - RH UPPER WING SKIN - CORROSION REPAIRS AT XORS = 531 THRU XORS = 536 & XORS = 540. THIS REPAIR CLASSIFIED AS MAJOR AS PER GMM 6 -2-100.
Part: SKIN — CORRODED (ZONE 600) · airframe 47,942 hrs · 9,821 cycles
RIGHT HAND WING UPPER SURFACE TRAILING EDGE FORWARD OF NR 2 SPOILER SKIN BULGE AT XORS 538.49 STRINGER 1. RT WING UPPER SURFACE TRAILING EDGE FORWARD OF NR 2 SPOILER XORS 538.49 STRINGER 1 SKIN BULGE AREA CORROSION REMOVED. MAT'L REMOVED: 0.035"; ORIG. THICKNESS: 0.310"; MAT'L REMAINED: 0.275"; FOUND EXCEED LIMIT AS PER SRM 57-10-00 FIG. 32 VOL.I. AREA REPAIR CARRIED OUT AS PER FEDEX EA 1-5710-87562 - WINGS - RH UPPER WING SKIN - CORROSION REPAIRS AT XORS = 531 THRU XORS = 536 & XORS = 540. THIS REPAIR CLASSIFIED AS MAJOR AS PER GMM 6 -2-100.
Part: SKIN — CORRODED (ZONE 600) · airframe 47,942 hrs · 9,821 cycles
RIGHT HAND WING UPPER SURFACE TRAILING EDGE FORWARD OF OUTBOARD AILERON SKIN BULGE FOUND AT XORS 989. RTW UPPER SURFACE T/E FWD OF O/B AILERON XORS 989 SKIN BULGE AREA CORROSION REMOVED. MAT'L REMOVED:0.035"; ORIGINAL THK: 0.150"; MAT'L REMAINED: 0.115"; FOUND EXCEED LIMIT PER SRM 57-10-00 FIG 32 VOL I. AREA REPAIR C/O PER FEDEX EA:1-5710-87559 - WINGS R/H UPPER WING SKIN CORROSION REPAIRS AT XORS 845,XORS 979, XORS 989, COMMON TO THE T/E. REPAIR CLASSIFIED AS MAJOR PER GMM6-2-100.
Part: SKIN — CORRODED (ZONE 600) · airframe 47,942 hrs · 9,821 cycles
RIGHT HAND WING UPPER SURFACE TRAILING EDGE FORWARD OF OUTBOARD AILERON SKIN BULGE FOUND AT XORS 850.33. RHW UPPER SURFACE T/E FWD OF O/B AILERON XORS 850.33 SKIN BULGE AREA CORROSION REMOVED. MAT'L REMOVED: 0.023"; ORIG. THK:0.150"; MAT'L REMAINED: 0.127" FOUND EXCEED LIMIT PER SRM 57-10-00 FIG 32 VOL I.AREA REPAIR C/O PER FEDEX EA: 1-5710-87559-WINGS RT UPPER WING SKIN CORROSION REPAIRS AT XORS 845, XORS 979,AND XORS 989 COMMON TO THE T/E. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.
Part: SKIN — CORRODED (ZONE 600) · airframe 47,942 hrs · 9,821 cycles
RIGHT HAND WING UPPER SURFACE TRAILING EDGE FORWARD OF OUTBOARD AILERON SKIN BULGE FOUND AT XORS 979. RTW UPPER SURFACE T/E FWD OF O/B AILERON XORS 979 SKIN BULGE AREA CORROSION REMOVED. MAT'L REMOVED:0.031"; ORIGINAL THK: 0.150"; MAT'L REMAINED: 0119"; FOUND EXCEED LIMIT PER SRM 57-10-00 FIG 32 VOL I. AREA REPAIR C/O PER FEDEX EA:1-5710-87559 - WINGS R/H UPPER WING SKIN CORROSION REPAIRS AT XORS 845,XORS 979, XORS 989, COMMON TO THE T/E. REPAIR CLASSIFIED AS MAJOR PER GMM6-2-100.
Part: SKIN — CORRODED (ZONE 600) · airframe 47,942 hrs · 9,821 cycles
RIGHT HAND WING UPPER SURFACE TRAILING EDGE FORWARD OF NR 2 SPOILER SKIN BULGE AT XORS 538.49 STRINGER 4. RT WING UPPER SURFACE TRAILING EDGE FORWARD OF NR 2 SPOILER XORS 538.49 STRINGER 4 SKIN BULGE AREA CORROSION REMOVED. MAT'L REMOVED: 0.024"; ORIG. THICKNESS: 0.330"; MAT'L REMAINED: 0.306"; AREA REPAIR CARRIED OUT AS PER FEDEX EA 1-5710-87562 - WINGS - RT UPPER WING SKIN - CORROSION REPAIRS AT XORS = 531 THRU XORS = 536 & XORS = 540. THIS REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100.
Part: LONGERON — CORRODED (ZONE 100) · airframe 47,942 hrs · 9,821 cycles
CENTER CARGO STATION 5-93 TO STATION 5-113 LONGERON 46R CORROSION FOUND AT TWO LOCATION AS MARKED. CORRODED LONGERON AT 46R CTR CARGO STA 5-93 TO STA 5-113 ON TWO LOCATION CARRIED OUT REPAIR AS PER SRM 53-10-00 FIG. 2. VOL. I. AND FEDEX EA 1-5310-87568 (TITLE: FUSELAGE - LONGERON L46 RH - INSTALLATION OF AN SRM TYPE SPLICE REPAIR WITH BOEING APPROVAL). REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100.
Part: LONGERON — CORRODED (ZONE 100) · airframe 47,942 hrs · 9,821 cycles
CENTER CARGO BILGE STATION 1751 LONGERON 46R CORROSION FOUND AS MARKED. CORROSION ON CENTER CARGO BILGE STATION 1751 LONGERON 46 R/H REMOVED AS PER SRM 51-21-01 VOL II AND FOUND EXCEEDED LIMIT AS PER SRM 53-00-01, FIG 3, VOL I. ORIGINAL THICKNESS=0.145", THICKNESS REMOVED=0.053" & THICKNESS REMAINING=0.092". REPAIR CARRIED OUT ON EXCEEDED LIMIT AREA AS PER SRM 53-10-00, FIG 2A, VOL I. THIS REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100.
Part: LONGERON — CORRODED (ZONE 100) · airframe 47,942 hrs · 9,821 cycles
CENTER CARGO BILGE STATION 1661 LONGERON 48L FOUND CORRODED. CORROSION AT CENTER CARGO BILGE STATION 1661 LONGERON 48L CARRIED OUT REPAIR AS PER SRM 53-10-00 FIG. 2 SHT 5 VOL. II. REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100.
Part: LONGERON — CORRODED (ZONE 100) · airframe 47,942 hrs · 9,821 cycles
CENTER CARGO BILGE STATION 1601 LONGERON 45R CORROSION FOUND AS MARKED. CORRODED LONGERON ON CENTER CARGO STATION 1601 LONGERON 45RH TRIMMED OUT AT STATION 1591 AND STATION 1611 AND REPAIR CARRIED OUT AS PER SRM 53-10-00 FIGURE 1 VOLUME I AND FEDEX EA 1-5310-87566
Part: SPLICE — CRACKED (ZONE 100) · airframe 47,942 hrs · 9,821 cycles
CENTER CARGO, STA 1531 L44R LONGERON SPLICE FOUND CRACKED. CRACKED LONGERON SPLICE ON CENTER CARGO STA 1531 LONGERON 44R REMOVED AND REPLACED AS PER SRM 51-33-01 VOL. II. THIS REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2- 100.
Part: LONGERON — CORRODED (ZONE 100) · airframe 47,942 hrs · 9,821 cycles
FORWARD CARGO: BILGE AREA STA 6-10 L51L LONGERON FOUND CORRODED. CORROSION AT LONGERON END FWD CARGO BILGE STA 6-10 L51R TRIMMED OUT AND CARRIED OUT REPAIR AS PER SRM 53-10-00 VOL. I FIG. 2. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.
Part: SPLICE — CRACKED (ZONE 100) · airframe 47,942 hrs · 9,821 cycles
CENTER CARGO, STA 1531 L45L LONGERON SPLICE FOUND CRACKED. CORRECTIVE ACTION: SRNM N1037: NEW LONGERON SPLICE FABRICATED AS PER DRAWING NO. A5A7116. CRACKED LONGERON SPLICE ON CTR CARGO STA. 1531 LONGERON 45 LH REMOVED AND REPLACED AS PER SRM 51-33-01 VOL. II. THIS REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100.
Part: SPLICE — CRACKED (ZONE 100) · airframe 47,942 hrs · 9,821 cycles
CENTER CARGO, STA 1531 L46L LONGERON SPLICE FOUND CRACKED. NEW LONGERON SPLICE FABRICATED AS PER DWG A5A7114 AND FEDEX EA 1- 5310-89959 (TITLE: FUSELAGE - MAIN FRAME - LONGERON 46L SPLICE REPLACEMENT AT STA. 1531) CRACKED LONGERON SPLICE ON CENTER CARGO STA. 1531 LONGERON 46 LH AREA REMOVED AND REPLACED AS PER SRM 51-33-01 VOL. II. THIS REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100.
Part: SPLICE — CORRODED (ZONE 100) · airframe 47,942 hrs · 9,821 cycles
FORWARD CARGO: BILGE AREA STA 830 L52 LONGERON SPLICE FOUND CORRODED. REMOVED AS PER SRM 51-33-01 VOL. II. NEW SPLICE MACHINED AS PER DWG ADA7225. FPI CARRIED OUT AS PER DPS 4.707 AND NO CRACK INDICATION FOUND ON NEW SPLICE. NEW SPLICE INSTALLED AS PER SRM 51-33-01 VOL.II. THIS REPAIR CLASSIFIED AS MAJOR REPAIR AS PER GMM 6-2-100.
Part: SPLICE — CRACKED (FUSELAGE) · airframe 47,942 hrs · 9,821 cycles
CENTER CARGO LEFT SIDEWALL STATION 1531 L34 LONGERON SPLICE. SUSPECT CRACKED AS MARKED. NEW LONGERON SPLICE FABRICATED AS PER DWG A5A7112. CRACKED LONGERON SPLICE ON CTR CARGO LH SIDEWALL LONGERON 34 LH REMOVED AND REPLACED AS PER SRM 51-33-01 VOL. II. THIS REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100.
Part: SKIN — CHIPPED (ZONE 200) · airframe 47,942 hrs · 9,821 cycles
FORWARD CABIN - R1 DOOR EXTERIOR UPPER EDGE FOUND CHIPPED. CORRECTIVE ACTION: SNRM N0241: EXISTING REPAIR ON FWD CABIN - R1 DOOR EXTERIOR EVALUATED AND FOUND NOT IAW SRM 52-10-00, FIG.4, SHT 1, VOL. I CHIPPED EXISTING REPAIR DOUBLER REMOVED AS PER SRM 51-35-01 VOL. II AND NEW REPAIR CARRIED OUT AS PER SRM 52-10-00, FIG. 4, SHT 1, VOL. I. THIS REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100.
Part: FRAME — DENTED (ZONE 200) · airframe 47,942 hrs · 9,821 cycles
MAIN DECK CARGO - LEFT HAND FRAME FOUND DENTED MARK AT STATION 1701 LONGERON 12. CORRECTIVE ACTION: SNRM N0599: MAIN DECK CARGO - LH FRAME AT STA 1701 LONGERON 12 CARRIED OUT REPAIR AS PER SRM 53-30-00 VOL. I. REFER TO FEDEX EA 1-5330-87565 - FUSELAGE - FRAME - TRACKING SRM FRAME REPAIR AT STA Y = 1701 AT LONGERON 12 LEFT HAND FOR REPETITIVE INSPECTION TRACKING.
Part: SKIN — CORRODED (ZONE 600) · airframe 47,942 hrs · 9,821 cycles
RIGHT HAND WING UPPER SURFACE TRAILING EDGE FORWARD OF OUTBOARD AILERON SEVERAL SKIN BULGE FOUND AS MARKED. CORROSION REMOVED AND FOUND WITHIN LIMIT - REFER TO SNRM N1244, N1245, N1246 AND N1247 FOR WORK DETAILS AND 03 EA AREA CORROSION REMOVED AND FOUND EXCEED LIMIT REFER TO SNRM 1241, N1242 AND N1243 FOR WORK DETAILS.
Part: SKIN — CORRODED (ZONE 500) · airframe 47,942 hrs · 9,821 cycles
LT WING UPPER SURFACE FORWARD OF FUEL TANK PANEL 533AT 1 EACH SKIN BULGE FOUND AS MARKED. CORROSION ON LTW UPPER SURFACE FWD OF FUEL TANK PANEL 533AT REMOVED AS PER SRM 51-21-01 VOL. II. ORIGINAL THICKNESS: 0.749"; THK. REMOVED: 0.033"; THK. REMAINED: 0.716". AREA FOUND WITHIN LIMIT AS PER FEDEX 1-5730-89960 (TITLE: WINGS - LT WING UPPER SKIN BLEND AT XORS 281, STRINGER 9). THIS REPAIR CLASSIFIED AS MINOR AS PER GMM 6-2- 100.
Part: SKIN — CORRODED (ZONE 600) · airframe 47,942 hrs · 9,821 cycles
RIGHT HAND WING UPPER SURFACE TRAILING EDGE FORWARD OF NR 2 SPOILER 4 EACH SKIN BULGE FOUND AS MARKED. CORROSION REMOVED AND FOUND WITHIN LIMIT REFER TO SNRM N1237 FOR WORK DETAILS AND 03 EA AREA CORROSION REMOVED AND FOUND EXCEED LIMIT REFER TO SNRM N1236, SNRM N1238 AND N1240 FOR WORK DETAIL.
Part: INTERCOSTAL — DAMAGED (ZONE 200) · airframe 47,942 hrs · 9,821 cycles
SNRM N0706: MAIN DECK CARGO - ATTIC AREA STATION 1906 RIGHT HAND LONGERON 4 FOUND INTERCOASTAL DAMAGED. REMOVED AND REPLACED AS PER SRM 51-35-01 VOL. II. THIS REPAIR CLASSIFIED AS MINOR AS PER GMM 6-2-100.
Part: SKIN — CORRODED (ZONE 500) · airframe 47,942 hrs · 9,821 cycles
LEFT HAND WING UPPER SURFACE MOST INBOARD FOUND 1 EACH SKIN BULGE. LH WING UPPER SURFACE MOST INBD 01 EA. SKIN BULGE AREA CORROSION REMOVED AND REPROTECTED AS PER SRM 51-21-01 VOL. II. MAT'L REMOVED 0.042"; ORIG. THICKNESS 0.241"; MAT'L REMAINED 0.199"; FOUND EXCEEDED LIMIT AS PER SRM 57-10-00 FIG. 32 VOL. I. AREA REPAIR CARRIED OUT AS PER FEDEX EA 1-5710-87558 - WINGS - LEFT HAND UPPER WING SKIN - CORROSION REPAIR AT XORS 108 AND STRINGER 13. THIS REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100.
2004
Part: UNLOCK CYLINDER — INOPERATIVE (ZONE 700) · airframe 45,705 hrs · 9,323 cycles
ON TAKEOFF RIGHT MAIN GEAR UNSAFE INDICATION BOTH SYSTEM, COULD FEEL DRAG. CYCLED GEAR OPERATED NORMALLY. T/S RIGHT MLG RETRACT FUNCTION AS PER FIM 32-30-00 FIG 103, WITH A/C ON JACKS AND LANDING GEAR SWING TEST AS PER MM 32-31-00-5 & 07-11-00. PHYSICAL CHECK RIGHT GEAR DOOR LATCH, GEAR POSITION FOLLOW-UP CABLES AND PUSH RODS ALL CONDITION NORMAL PER 32-34-05-5 AND 32-31-00-5. TEST LANDING GEAR RETRACT TIME PASSED AS PER TASK 32-31-00-700-804. CONTINUE OPS LANDING GEARS FOR TWO HOURS MORE THAN FORTY TIMES, STILL UNABLE TO DUPLICATE PROBLEM. REMOVED AND REPLACED RT MLG UNLOCK CYLINDER PER MM 32-33-02-4. LUBRICATED RT LANDING GEAR/DOOR PER MM 12-21-00. A/C OK FOR SERVICE.
Part: LONGERON — CORRODED (ZONE 100) · airframe 43,179 hrs · 8,728 cycles
FWD CARGO - EXFOLIATION CORROSION FOUND AT STA Y= 1019 LONGERON 46R. FWD CARGO - STA Y= 1019 LONGERON 46R REPAIRED AS PER SRM 53-10-00 VOL I.
Part: HINGE — CRACKED (ZONE 700) · airframe 43,179 hrs · 8,728 cycles
RIGHT MAIN LANDING GEAR, DOOR HINGE FOUND CRACKED. RT MAIN LANDING GEAR - CRACKED DOOR HINGE REMOVED AND REPLACED AS PER DWG ANB7093 AND SRM 51-35-01 VOL II
Part: SKIN — CORRODED (ZONE 500) · airframe 43,179 hrs · 8,728 cycles
LT WING, CORROSION OBSERVED ON UPPER SKIN SURFACE FROM XORS 264 TO 317 AND BETWEEN STRINGERS S10 TO S21. REMOVED PER SRM 57-10-00 VOL I FIG 32
Part: RIB — CORRODED (ZONE 300) · airframe 43,179 hrs · 8,728 cycles
UPON REMOVAL OF RIGHT DETACHABLE ELEVATOR LOWER INBOARD ACCESS PANEL NR 345BB FOUND STA XE53.50 LOWER INBOARD MOUNTING FLANGE CRACKED. COMPLIED WITH FEDEX EA 1-5520-75973, STABILIZERS - ELEVATORS RT INBOARD ELEVATOR RIB REPAIR.
Part: FRAME — DENTED (ZONE 200) · airframe 43,179 hrs · 8,728 cycles
FUSELAGE TRANSVERSE FRAME DENTED AT FS Y= 1721 BETWEEN LONGERONS 12L AND 13L. COMPLIED WITH FEDEX EA 1-5310-76001, FUSELAGE - MAINFRAME - REPAIR TRACKING (TYPE B) OF SRM REPAIRS FOR DAMAGE TOLERANCE ASSESSMENT PER EO NR 1-2520-7-3380.
Part: FRAME — DENTED (ZONE 200) · airframe 43,179 hrs · 8,728 cycles
FUSELAGE TRANSVERSE FRAME DENTED AT FS Y=1601 BETWEEN LONGERONS 12L AND 13L. REPAIRED PER SRM 53-30-00 VOL I FIG 1. COMPLIED WITH FEDEX EA 1-5310-75999, REPAIR TRACKING (TYPE B) OF SRM REPAIRS FOR DAMAGE TOLERANCE ASSESSMENT PER EO 1-2520-7-3308.
Part: FRAME — DENTED (ZONE 200) · airframe 43,179 hrs · 8,728 cycles
FUSELAGE TRANSVERSE FRAME DENTED AT FS Y= 1701 BETWEEN LONGERONS 12L AND 13L. COMPLIED WITH FEDEX EA 1-5310-76001, FUSELAGE - MAINFRAME - REPAIR TRACKING (TYPE B) OF SRM REPAIRS FOR DAMAGE TOLERANCE ASSESSMENT PER EO NR 1-2520-7-3380.
Part: FRAME — DENTED (ZONE 200) · airframe 43,179 hrs · 8,728 cycles
FUSELAGE TRANSVERSE FRAME DENTED AT FS Y= 1661 BETWEEN LONGERONS 12R AND 13R. MID CABIN FRAME AT STA Y= 1661 BETWEEN STR 12R AND 13R DENT REPAIRED PER SRM 53-30-00 VOL I FIG 1. COMPLIED WITH FEDEX EA 1-5310-75999, FUSELAGE - MAINFRAME - REPAIR TRACKING (TYPE B) OF SRM REPAIRS FOR DAMAGE TOLERANCE ASSESSMENT PER EO 1-2520-7-3308.
Part: FRAME — DENTED (ZONE 200) · airframe 43,179 hrs · 8,728 cycles
FUSELAGE TRANSVERSE FRAME DENTED AT FS Y= 1681 BETWEEN LONGERONS 12L AND 13L. COMPLIED WITH FEDEX EA 1-5310-76001, FUSELAGE - MAINFRAME - REPAIR TRACKING (TYPE B) OF SRM REPAIRS FOR DAMAGE TOLERANCE ASSESSMENT PER EO NR 1-2520-7-3380.
Part: FRAME — DENTED (ZONE 200) · airframe 43,179 hrs · 8,728 cycles
FUSELAGE TRANSVERSE FRAME DENTED AT FS Y= 1741 BETWEEN LONGERONS 12L AND 13L. COMPLIED WITH FEDEX EA 1-5310-76001, FUSELAGE - MAINFRAME - REPAIR TRACKING (TYPE B) OF SRM REPAIRS FOR DAMAGE TOLERANCE ASSESSMENT PER EO NR 1-2520-7-3380.
Part: HINGE — CORRODED (ZONE 500) · airframe 43,179 hrs · 8,728 cycles
LEFT WING, OUTBOARD FLAP, OUTBOARD AFT HINGE ACTUATOR ROD END HOLE OUTBOARD CORRODED. COMPLIED WITH FEDEX EA 1-5750-75970, WINGS - TRAILING EDGE AND TRAILING EDGE DEVICES - LT OUTBOARD FLAP/ OUTBOARD SUPPORT BRACKET CORROSION REMOVAL AND REPAIR.
Part: FRAME — DENTED (FUSELAGE) · airframe 43,179 hrs · 8,728 cycles
FUSELAGE TRANSVERSE FRAME DENT AT FS Y= 1761 BETWEEN LONGERON 12L AND LONGERON 13L. COMPLIED WITH FEDEX EA 1-5310-76001, REPAIRED TRACKING (TYPE B) OF SRM REPAIRS FOR DAMAGE TOLERANCE ASSESSMENT PER EO NR 1-2520-7-3380.
Part: FRAME — DENTED (ZONE 200) · airframe 43,179 hrs · 8,728 cycles
FUSELAGE TRANSVERSE FRAME DENTED AT FS Y= 1661 BETWEEN LONGERONS 12L AND 13L. COMPLIED WITH FEDEX EA 1-5310-76001, FUSELAGE - MAINFRAME - REPAIR TRACKING (TYPE B) OF SRM REPAIRS FOR DAMAGE TOLERANCE ASSESSMENT PER EO 1-2520-7-3380.
Part: FRAME — DENTED (ZONE 200) · airframe 43,179 hrs · 8,728 cycles
FUSELAGE TRANSVERSE FRAME DENTED AT FS Y= 1761 BETWEEN LONGERONS 12R AND 13R. COMPLIED WITH FEDEX EA 1-5310-75999, REPAIR TRACKING (TYPE B) OF SRM REPAIRS FOR DAMAGE TOLERANCE ASSESSMENT PER EO (NR 1-2520-7-3308)
Part: ROD END — CORRODED (ZONE 500) · airframe 43,179 hrs · 8,728 cycles
LEFT WING OUTBOARD FLAP, INBOARD FWD HINGE ACTUATOR ROD END HOLE NR 8 INBOARD CORRODED. COMPLIED WITH FEDEX EA 1-5740-75923, LEFT OUTBOARD FLAP INBOARD HINGE BRACKET ASSEMBLY.
Part: FRAME — DENTED (ZONE 200) · airframe 43,179 hrs · 8,728 cycles
FUSELAGE TRANSVERSE FRAME DENTED AT FS Y= 5-113 BETWEEN LONGERONS 12L AND 13L. COMPLIED WITH FEDEX EA 1-5310-76001, FUSELAGE - MAINFRAME - REPAIR TRACKING (TYPE B) OF SRM REPAIRS FOR DAMAGE TOLERANCE ASSESSMENT PER EO 1-2520-7-3380.
Part: LONGERON — CRACKED (WING TO FUSELAGE) · airframe 43,179 hrs · 8,728 cycles
RIGHT WING TO FUSELAGE AT STA Y= 1491, LONGERON SPLICE FOUND CRACKED. RT WING TO FUSELAGE AT STA Y= 1491, CRACKED LONGERON SPLICE. REMOVED AND NEW SPLICE INSTALLED AS PER SRM 53-10-00 VOL 1 FIG 2
Part: LONGERON — CORRODED (ZONE 100) · airframe 43,179 hrs · 8,728 cycles
FWD CARGO BILGE AREA, LONGERON NR 52 AT STA 919 TO 939 CORRODED. FWD CARGO BILGE AREA, LONGERON 52 AT STA 919 TO 939 REPAIRED AS PER SRM 53-10-00 VOL I FIGURE 1 AND FIGURE 2.
Part: HINGE — CORRODED (ZONE 500) · airframe 43,179 hrs · 8,728 cycles
LEFT WING, INBOARD FLAP, OUTBOARD AFT HINGE PIVOT HOLE OUTBOARD CORRODED. COMPLIED WITH FEDEX EA 1-5750-75974, TRAILING EDGE & TRAILING EDGE DEVICES - LT INBOARD FLAP HINGE BRACKET REPAIR.
Part: LONGERON — CRACKED (ZONE 100) · airframe 43,179 hrs · 8,728 cycles
LEFT WING TO FUSELAGE AT STA Y= 1491, LONGERON SPLICE FOUND CRACKED. LT WING TO FUSELAGE AT STA Y= 1491, CRACKED LONGERON SPLICE REMOVED AND NEW SPLICE INSTALLED AS PER SRM 53-10-00 VOL 1 FIG 2
Part: HINGE — CORRODED (ZONE 600) · airframe 43,179 hrs · 8,728 cycles
RT WING INBOARD FLAP, OUTBOARD HINGE PIVOT HOLE SPOTFACE FOUND WITH CORROSION. COMPLIED WITH FEDEX WITH EA 1-5750-75978, TRAILING EDGE DEVICES RT INBOARD FLAP OUTBOARD HINGE BRACKET REPAIRS.
Part: HINGE — CORRODED (ZONE 500) · airframe 43,179 hrs · 8,728 cycles
LEFT WING OUTBOARD FLAP, INBOARD HINGE, BARREL NUT HOLE NR 28 MATING SURFACE CORRODED. COMPLIED WITH FEDEX EA 1-5740-75923, LT OUTBOARD FLAP INBOARD HINGE BRACKET ASSEMBLY.
Part: HINGE — CORRODED (ZONE 600) · airframe 43,179 hrs · 8,728 cycles
RIGHT WING, OUTBOARD FLAP, OUTBOARD AFT HINGE ACTUATOR ROD INBOARD HOLE CORRODED. COMPLIED WITH FEDEX EA 1-5750-75976, TRAILING EDGE & TRAILING EDGE DEVICES. RT OUTBOARD FLAP OUTBOARD SUPPORT BRACKET CORROSION REMOVAL AND REPAIR.
Part: HINGE — CORRODED (ZONE 600) · airframe 43,179 hrs · 8,728 cycles
RIGHT WING OUTBOARD FLAP, OUTBOARD HINGE ACTUATOR ROD END OUTBOARD HOLE CORRODED. COMPLIED WITH FEDEX EA 1-5750-75976, TRAILING EDGE AND TRAILING EDGE DEVICES, RT OUTBOARD FLAP OUTBOARD SUPPORT BRACKET CORROSION REMOVAL AND REPAIR.
Part: HINGE — CORRODED (ZONE 600) · airframe 43,179 hrs · 8,728 cycles
RIGHT WING OUTBOARD FLAP, OUTBOARD AFT HINGE PIVOT HOLE INBOARD CORRODED. COMPLIED WITH FEDEX EA 1-5750-75976, WINGS - TRAILING EDGE & TRAILING EDGE DEVICES. RT OUTBOARD FLAP OUTBOARD SUPPORT BRACKET CORROSION REMOVAL AND REPAIR.
Part: WEB — CANNING (ZONE 700) · airframe 43,179 hrs · 8,728 cycles
LEFT VERTICAL WEBS IN CENTER LANDING GEAR WHEEL WELL FOUND OIL CANNING AT: (1) Y= 1391 TO Y= 1401, Z= -100 TO Z= -90, DEPTH= 0.074 INCH (2) Y= 1401 TO Y= 1411, Z= -100 TO Z= -90, DEPTH= 0.061 INCH (3) Y= 1411 TO Y= 1421, Z= -100 TO Z= -90, DEPTH= 0.069 INCH (4) Y= 1421 TO Y= 1431, Z= -90 TO Z= -70, DEPTH= 0.070 INCH. COMPLIED WITH FEDEX WITH EA 1-5310-75984, FUSELAGE - MAINFRAME - KEEL WEB / CENTER LANDING GEAR INSPECTION REQUIREMENTS.
Part: HINGE — CORRODED (ZONE 500) · airframe 43,179 hrs · 8,728 cycles
LT WING, OUTBOARD FLAP, OUTBOARD FORWARD HINGE, BARREL NUT HOLE NR 7 MATING SURFACE CORRODED. LT WING, OUTBOARD FLAP, OUTBOARD FORWARD HINGE, BARREL NUT HOLE NR 7 MATING SURFACE CORROSION REMOVED AND FOUND WITHIN LIMITS AS PER CMM 57-44-09 AND DWG ARC0503 SHEET 2 ZONE 22.
Part: HINGE — CORRODED (ZONE 600) · airframe 43,179 hrs · 8,728 cycles
RIGHT WING OUTBOARD FLAP, OUTBOARD FORWARD HINGE ACTUATOR ROD END HOLE NR 8 INBOARD CORRODED. COMPLIED WITH FEDEX EA 1-5750-75979, TRAILING EDGE & TRAILING EDGE DEVICES. RT OUTBOARD FLAP OUTBOARD HINGE BRACKET REPAIRS
Part: STRAP — CORRODED (ZONE 600) · airframe 43,179 hrs · 8,728 cycles
RT WING, INBOARD FLAP OUTBOARD AFT HINGE OUTBOARD STRAP OUTBOARD SIDE SURFACE CORRODED. REMOVED AND REPLACED AS PER SRM 51-33-01 VOL II
Part: HINGE — CORRODED (ZONE 600) · airframe 43,179 hrs · 8,728 cycles
RIGHT WING OUTBOARD FLAP INBOARD AFT HINGE OUTBOARD PIVOT HOLE SPOTFACE CORRODED. COMPLIED WITH FEDEX EA 1-5750-75975, TRAILING EDGE AND TRAILING EDGE DEVICES. RT OUTBOARD FLAP INBOARD SUPPORT BRACKET CORROSION REMOVAL AND REPAIR.
Part: HINGE — CORRODED (ZONE 600) · airframe 43,179 hrs · 8,728 cycles
RT WING, OUTBOARD FLAP, OUTBOARD FORWARD HINGE BARREL NUT HOLE NR 7 MATING SURFACE CORRODED. CORROSION REMOVED AND FOUND WITHIN LIMITS AS PER CMM 57-44-09 AND DWG ARC0503 SHEET 2 ZONE 22.
Part: HINGE — CORRODED (ZONE 500) · airframe 43,179 hrs · 8,728 cycles
LT WING, OUTBOARD FLAP, INBOARD FORWARD HINGE, LOWER MOUNT HOLE NR 7, MATING SURFACE CORRODED. LT WING, OUTBOARD FLAP, INBOARD FORWARD HINGE, LOWER MOUNT HOLE NR 7, MATING SURFACE CORROSION REMOVED AND FOUND WITHIN LIMITS AS PER CMM 57-44-08 AND DWG ARC0502 SHEET 4 ZONE 40.
Part: HINGE — CORRODED (ZONE 600) · airframe 43,179 hrs · 8,728 cycles
RIGHT WING OUTBOARD FLAP, INBOARD AFT HINGE ACTUATOR ROD END HOLE OUTBOARD SPOTFACE CORRODED. COMPLIED WITH FEDEX EA 1-5750-75975, TRAILING EDGE AND TRAILING EDGE DEVICES. RT OUTBOARD FLAP INBOARD SUPPORT BRACKET CORROSION REMOVAL AND REPAIR.
Part: ROD END — CORRODED (ZONE 500) · airframe 43,179 hrs · 8,728 cycles
LEFT WING - OUTBOARD FLAP, INBOARD FWD HINGE, ACTUATOR ROD END HOLE NR 8 INBOARD CORRODED. COMPLIED WITH FEDEX EA 1-5740-75923, LT OUTBOARD FLAP INBOARD HINGE BRACKET ASSY.
Part: HINGE — CORRODED (ZONE 600) · airframe 43,179 hrs · 8,728 cycles
RIGHT WING, OUTBOARD FLAP, INBOARD FORWARD HINGE, BARREL NUT HOLE NR 2B MATING SURFACE CORRODED. COMPLIED WITH FEDEX EA 1-5750-75980, TRAILING EDGE & TRAILING EDGE DEVICES - RT OUTBOARD FLAP INBOARD HINGE BRACKET REPAIR.
Part: HINGE — CORRODED (ZONE 600) · airframe 43,179 hrs · 8,728 cycles
RIGHT WING OUTBOARD FLAP, INBOARD AFT HINGE ACTUATOR ROD END INBOARD HOLE CORRODED. COMPLIED WITH FEDEX EA 1-5750-75975, TRAILING EDGE AND TRAILING EDGE DEVICES. RT OUTBOARD FLAP INBOARD SUPPORT BRACKET CORROSION REMOVAL AND REPAIR.
Part: HINGE — CORRODED (ZONE 600) · airframe 43,179 hrs · 8,728 cycles
RIGHT WING OUTBOARD FLAP, OUTBOARD AFT HINGE PIVOT HOLE OUTBOARD CORRODED. COMPLIED WITH FEDEX EA 1-5750-75976, TRAILING EDGE & TRAILING EDGE DEVICES. RT OUTBOARD FLAP OUTBOARD SUPPORT BRACKET CORROSION REMOVAL AND REPAIR.
Part: HINGE — CORRODED (ZONE 600) · airframe 43,179 hrs · 8,728 cycles
RIGHT WING, OUTBOARD FLAP, INBOARD AFT HINGE INBOARD PIVOT HOLE SPOTFACE CORRODED. COMPLIED WITH FEDEX EA 1-5750-75975, TRAILING EDGE AND TRAILING EDGE DEVICES. RT OUTBOARD FLAP INBOARD SUPPORT BRACKET CORROSION REMOVAL AND REPAIR.
Part: MOUNT — CORRODED (ZONE 600) · airframe 43,179 hrs · 8,728 cycles
RT WING OUTBOARD FLAP, INBOARD FORWARD HINGE LOWER MOUNT HOLE NR 7 MATING SURFACE CORRODED. CORROSION REMOVED AND FOUND WITHIN LIMITS AS PER CMM 57-44-08 AND DWG ARC0502 SHEET 4 ZONE 40.
Part: BRACKET — CORRODED (ZONE 500) · airframe 43,179 hrs · 8,728 cycles
LEFT WING, OUTBOARD FLAP, OUTBOARD FORWARD HINGE, ACTUATOR ROD END HOLE NR 8 OUTBOARD CORRODED. COMPLIED WITH FEDEX EA 1-5740-75913, WINGS LEFT OUTBOARD FLAP, OUTBOARD HINGE BRACKET ASSEMBLY CORROSION.
Part: HINGE — CORRODED (ZONE 600) · airframe 43,179 hrs · 8,728 cycles
RIGHT WING OUTBOARD FLAP, INBOARD HINGE ACTUATOR ROD END OUTBOARD HOLE CORRODED. COMPLIED WITH FEDEX EA 1-5750-75975, TRAILING EDGE AND TRAILING EDGE DEVICES. RT OUTBOARD FLAP INBOARD SUPPORT BRACKET CORROSION REMOVAL AND REPAIR.
Part: WEB — CANNING (ZONE 700) · airframe 43,179 hrs · 8,728 cycles
RT VERTICAL WEBS IN CENTER LANDING GEAR WHEEL WELL FOUND OIL CANNING AT: (1) Y= 1390 TO Y= 1401, Z= -100 TO Z= -90, DEPTH= 0.0090 INCH (2) Y= 1401 TO Y= 1411, Z= -100 TO Z= -90, DEPTH= 0.0070 INCH (3) Y= 1411 TO Y= 1421, Z= -100 TO Z= -90, DEPTH= 0.0072 INCH (4) Y= 1421 TO Y= 1431, Z= -90 TO Z= -70, DEPTH= 0.0068 INCH (4) Y= 1421 TO Y= 1431, Z= -90 TO Z= -70, DEPTH= 0.0180 INCH. COMPLIED WITH FEDEX EA 1-5310-75984, FUSELAGE - MAINFRAME - KEEL WEB / CENTER LANDING GEAR INSPECTION REQUIREMENTS.
Part: HINGE — CORRODED (ZONE 600) · airframe 43,179 hrs · 8,728 cycles
RT WING OUTBOARD FLAP, INBOARD AFT HINGE INBOARD PIVOT HOLE CORRODED. COMPLIED WITH FEDEX EA 1-5750-75975, TRAILING EDGE AND TRAILING EDGE DEVICES. RT OUTBOARD FLAP INBOARD SUPPORT BRACKET CORROSION REMOVAL AND REPAIR.
Part: HINGE — CORRODED (ZONE 500) · airframe 43,179 hrs · 8,728 cycles
LEFT WING OUTBOARD FLAP, OUTBOARD FORWARD HINGE, ACTUATOR ROD END NR 8 CORRODED. COMPLIED WITH FEDEX EA 1-5740-75913, WINGS - LEFT OUTBOARD FLAP OUTBOARD HINGE BRACKET ASSEMBLY CORROSION
Part: SKIN — CORRODED (ZONE 500) · airframe 43,179 hrs · 8,728 cycles
CORROSION OBSERVED ON UPPER SKIN SURFACE FROM XORS 197 TO 264 AND BETWEEN STRINGERS S11 TO S21. LEFT WING XORS 197 TO 264 AND BETWEEN STRINGERS S11 TO S21 UPPER SKIN SURFACE CORROSION REMOVED AS PER SRM 57-10-00 VOL I FIG 32.
Part: HINGE — CORRODED (TE FLAP) · airframe 43,179 hrs · 8,728 cycles
RIGHT WING, OUTBOARD FLAP, INBOARD FWD HINGE, ACTUATOR ROD END HOLE NR 8 OUTBOARD CORRODED. COMPLIED WITH FEDEX EA 1-5750-75980, TRAILING EDGE & TRAILING EDGE DEVICES - RT OUTBOARD FLAP INBOARD HINGE BRACKET REPAIR.
Part: HINGE — CORRODED (ZONE 600) · airframe 43,179 hrs · 8,728 cycles
RIGHT WING OUTBOARD FLAP, OUTBOARD AFT HINGE PIVOT HOLE OUTBOARD SPOTFACE CORRODED. COMPLIED WITH FEDEX EA 1-5750-75976, TRAILING EDGE & TRAILING EDGE DEVICES. RT OUTBOARD FLAP OUTBOARD SUPPORT BRACKET CORROSION REMOVAL AND REPAIR.
Part: ROD END — CORRODED (ZONE 500) · airframe 43,179 hrs · 8,728 cycles
LEFT WING OUTBOARD FLAP, INBOARD FORWARD HINGE, ACTUATOR ROD END HOLE NR 8 OUTBOARD FOUND CORRODED. COMPLIED WITH FEDEX EA 1-5740-75923, LT OUTBOARD FLAP INBOARD HINGE BRACKET ASSEMBLY CORROSION.
Part: HINGE — CORRODED (ZONE 600) · airframe 43,179 hrs · 8,728 cycles
RT WING, OUTBOARD FLAP, INBOARD FORWARD HINGE ACTUATOR ROD END HOLE NR 8 INBOARD CORRODED. COMPLIED WITH FEDEX EA 1-5750-75980, WINGS - TRAILING EDGE & TRAILING EDGE DEVICES - RT OUTBOARD FLAP INBOARD HINGE BRACKET REPAIR.
Part: HINGE — CORRODED (ZONE 600) · airframe 43,179 hrs · 8,728 cycles
RT WING, OUTBOARD FLAP, OUTBOARD FORWARD HINGE BARREL NUT HOLE NR 7 MATING SURFACE CORRODED. CORROSION REMOVED AND FOUND WITHIN LIMITS AS PER CMM 57-44-09 AND DWG ARC0503 SHEET 2 ZONE 22
Part: HINGE — CORRODED (ZONE 600) · airframe 43,179 hrs · 8,728 cycles
RIGHT WING, OUTBOARD FLAP, INBOARD AFT HINGE OUTBOARD PIVOT HOLE CORRODED. COMPLIED WITH FEDEX EA 1-5750-75975, TRAILING EDGE AND TRAILING EDGE DEVICES. RT OUTBOARD FLAP INBOARD SUPPORT BRACKET CORROSION REMOVAL AND REPAIR.
Part: HINGE — CORRODED (ZONE 600) · airframe 43,179 hrs · 8,728 cycles
RIGHT WING OUTBOARD FLAP, OUTBOARD FORWARD HINGE ACTUATOR ROD END HOLE NR 8 OUTBOARD CORRODED. COMPLIED WITH FEDEX EA 1-5750-75979, TRAILING EDGE & TRAILING EDGE DEVICES. RT OUTBOARD FALP OUTBOARD HINGE BRACKET REAPAIRS.
Part: HINGE — CORRODED (ZONE 600) · airframe 43,179 hrs · 8,728 cycles
RIGHT WING OUTBOARD FLAP, OUTBOARD AFT HINGE ACTUATOR ROD END HOLE INBOARD SPOTFACE CORRODED. COMPLIED WITH FEDEX EA 1-5750-75976, TRAILING EDGE & TRAILING EDGE DEVICES. RT OUTBOARD FLAP OUTBOARD SUPPORT BRACKET CORROSION REMOVAL AND REPAIR.
Part: HINGE — CORRODED (ZONE 600) · airframe 43,179 hrs · 8,728 cycles
RIGHT WING OUTBOARD FLAP, OUTBOARD AFT HINGE ACTUATOR ROD END HOLE OUTBOARD SPOTFACE CORRODED. COMPLIED WITH FEDEX EA 1-5750-75976, TRAILING EDGE & TRAILING EDGE DEVICES. RT OUTBOARD FLAP OUTBOARD SUPPORT BRACKET CORROSION REMOVAL AND REPAIR.
Part: HINGE — CORRODED (ZONE 600) · airframe 43,179 hrs · 8,728 cycles
RIGHT WING OUTBOARD FLAP, OUTBOARD AFT HINGE PIVOT HOLE INBOARD SPOTFACE CORRODED. COMPLIED WITH FEDEX EA 1-5750-75976, TRAILING EDGE & TRAILING EDGE DEVICES. RT OUTBOARD FLAP OUTBOARD SUPPORT BRACKET CORROSION REMOVAL AND REPAIR.
Part: ROD END — CORRODED (ZONE 500) · airframe 43,179 hrs · 8,728 cycles
LT WING OUTBOARD FLAP, INBOARD AFT HINGE ACTUATOR ROD END HOLE INBOARD SPOTFACE CORRODED. COMPLIED WITH FEDEX EA 1-5750-75275, TRAILING EDGE AND TRAILING EDGE DEVICES - LT OUTBOARD FLAP/ INBOARD SUPPORT BRACKET CORROSION REMOVAL AND REPAIR.
Part: ROD END — CORRODED (ZONE 500) · airframe 43,179 hrs · 8,728 cycles
LT WING - OUTBOARD FLAP, OUTBOARD AFT HINGE ACTUATOR ROD END OUTBOARD HOLE SPOTFACE CORRODED. COMPLIED EA 1-5750-75970, WINGS - TRAILING EDGE AND TRAILING EDGE DEVICES - LT OUTBOARD FLAP/ OUTBOARD SUPPORT BRACKET CORROSION REMOVAL AND REPAIR
Part: HINGE — CORRODED (ZONE 500) · airframe 43,179 hrs · 8,728 cycles
LT WING - OUTBOARD FLAP, OUTBOARD AFT HINGE INBOARD PIVOT HOLE CORRODED. COMPLIED WITH FEDEX EA 1-5750-75970, WINGS - TRAILING EDGE AND TRAILING EDGE DEVICES - LT OUTBOARD FLAP/ OUTBOARD SUPPORT BRACKET CORROSION REMOVAL AND REPAIR.
Part: HINGE — CORRODED (ZONE 500) · airframe 43,179 hrs · 8,728 cycles
LEFT WING OUTBOARD FLAP, INBOARD AFT HINGE INBOARD PIVOT HOLE CORRODED. COMPLIED WITH FEDEX EA 1-5750-75275, WINGS - TRAILING EDGE AND TRAILING EDGE DEVICES - LT OUTBOARD FLAP INBOARD SUPPORT BRACKET CORROSION REMOVAL AND REPAIR.
Part: ROD END — CORRODED (ZONE 500) · airframe 43,179 hrs · 8,728 cycles
RT WING OUTBOARD FLAP, INBOARD AFT HINGE ACTUATOR ROD END HOLE INBOARD SPOTFACE CORRODED. COMPLIED WITH FEDEX EA 1-5750-75975, TRAILING EDGE AND TRAILING EDGE DEVICES. RT OUTBOARD FLAP INBOARD SUPPORT BRACKET CORROSION REMOVAL AND REPAIR.
Part: SPLICE — CORRODED (ZONE 100) · airframe 43,179 hrs · 8,728 cycles
LONGERON SPLICE FOUND CORRODED AT STA 6-100 RIGHT LONGERON 45. COMPLIED WITH FEDEX EA 1-5310-75998, FUSELAGE - MAIN FRAME - CAC COMPARTMENT BODY STATION 6-100, LONGERON 45 RT SPLICE REPAIR
Part: HINGE — CORRODED (ZONE 500) · airframe 43,179 hrs · 8,728 cycles
LT WING OUTBOARD FLAP, INBOARD AFT HINGE OUTBOARD PIVOT HOLE CORRODED. COMPLIED WITH FEDEX EA 1-5750-75275, WINGS - TRAILING EDGE AND TRAILING EDGE DEVICES - LT OUTBOARD FLAP/ INBOARD SUPPORT BRACKET CORROSION REMOVAL AND REPAIR.
Part: HINGE — CORRODED (ZONE 500) · airframe 43,179 hrs · 8,728 cycles
LT WING - OUTBOARD FLAP, OUTBOARD AFT HINGE OUTBOARD PIVOT HOLE CORRODED. COMPLIED WITH FEDEX EA 1-5750-75970, WINGS - TRAILING EDGE AND TRAILING EDGE DEVICES - LT OUTBOARD FLAP/ OUTBOARD SUPPORT BRACKET CORROSION REMOVAL AND REPAIR.
Part: ROD END — CORRODED (ZONE 500) · airframe 43,179 hrs · 8,728 cycles
LEFT WING - OUTBOARD FLAP, INBOARD AFT HINGE ACTUATOR ROD END HOLE INBOARD CORRODED. COMPLIED WITH FEDEX EA 1-5750-75970, WINGS - TRAILING EDGE AND TRAILING EDGE DEVICES - LT OUTBOARD FLAP/ OUTBOARD SUPPORT BRACKET CORROSION REMOVAL AND REPAIR.
Part: HINGE — CORRODED (ZONE 500) · airframe 43,179 hrs · 8,728 cycles
LT WING - OUTBOARD FLAP, OUTBOARD AFT HINGE INBOARD PIVOT HOLE SPOTFACE CORRODED. COMPLIED WITH FEDEX EA 1-5750-75970, WINGS - TRAILING EDGE AND TRAILING EDGE DEVICES - LT OUTBOARD FLAP/ OUTBOARD SUPPORT BRACKET CORROSION REMOVAL AND REPAIR
Part: ROD END — CORRODED (ZONE 500) · airframe 43,179 hrs · 8,728 cycles
LEFT WING - OUTBOARD FLAP, OUTBOARD AFT HINGE ACTUATOR ROD END INBOARD HOLE SPOTFACE CORRODED. COMPLIED WITH FEDEX EA 1-5750-75970, WINGS - TRAILING EDGE AND TRAILING EDGE DEVICES - LT OUTBOARD FLAP/ OUTBOARD SUPPORT BRACKET CORROSION REMOVAL AND REPAIR.
Part: HINGE — CORRODED (ZONE 500) · airframe 43,179 hrs · 8,728 cycles
RT WING OUTBOARD FLAP, INBOARD AFT HINGE OUTBOARD PIVOT HOLE SPOTFACE CORRODED. COMPLIED WITH FEDEX EA 1-5750-75275, TRAILING EDGE AND TRAILING EDGE DEVICES - LT OUTBOARD FLAP/ INBOARD SUPPORT BRACKET CORROSION REMOVAL AND REPAIR.
Part: ROD END — CORRODED (ZONE 500) · airframe 43,179 hrs · 8,728 cycles
LT WING OUTBOARD FLAP, INBOARD AFT HINGE ACTUATOR ROD END HOLE INBOARD CORRODED. COMPLIED WITH FEDEX EA 1-5750-75275, TRAILING EDGE AND TRAILING EDGE DEVICES - LT OUTBOARD FLAP/ INBOARD SUPPORT BRACKET CORROSION REMOVAL AND REPAIR.
Part: HINGE — CORRODED (ZONE 500) · airframe 43,179 hrs · 8,728 cycles
LEFT WING - OUTBOARD FLAP, OUTBOARD AFT HINGE, OUTBOARD PIVOT SPOTFACE CORRODED. COMPLIED WITH FEDEX EA 1-5750-75970, WINGS - TRAILING EDGE AND TRAILING EDGE DEVICES - LT OUTBOARD FLAP/ OUTBOARD SUPPORT BRACKET CORROSION REMOVAL AND REPAIR.
Part: ROD END — CORRODED (ZONE 500) · airframe 43,179 hrs · 8,728 cycles
LT WING OUTBOARD FLAP, INBOARD AFT HINGE ACTUATOR ROD END HOLE OUTBOARD CORRODED. COMPLIED WITH FEDEX EA 1-5750-75275, WINGS - TRAILING EDGE AND TRAILING EDGE DEVICES - LT OUTBOARD FLAP/ INBOARD SUPPORT BRACKET CORROSION REMOVAL AND REPAIR.
Part: ROD END — CORRODED (ZONE 600) · airframe 43,179 hrs · 8,728 cycles
RT WING OUTBOARD FLAP, INBOARD AFT HINGE ACTUATOR ROD END OUTBOARD HOLE CORRODED. COMPLIED WITH FEDEX EA 1-5750-75975, TRAILING EDGE AND TRAILING EDGE DEVICES. RT OUTBOARD FLAP INBOARD SUPPORT BRACKET CORROSION REMOVAL AND REPAIR.
Part: HINGE — CORRODED (ZONE 600) · airframe 43,179 hrs · 8,728 cycles
RT WING OUTBOARD FLAP, INBOARD AFT HINGE ACTUATOR ROD END HOLE OUTBOARD SPOTFACE CORRODED. COMPLIED WITH FEDEX EA 1-5750-75975, TRAILING EDGE AND TRAILING EDGE DEVICES. RT OUTBOARD FLAP INBOARD SUPPORT BRACKET CORROSION REMOVAL AND REPAIR.
Part: HINGE — CORRODED (ZONE 500) · airframe 43,179 hrs · 8,728 cycles
LEFT WING OUTBOARD FLAP, INBOARD AFT HINGE INBOARD PIVOT HOLE WITH SPOTFACE CORRODED. COMPLIED WITH FEDEX EA 1-5750-75275, WINGS - TRAILING EDGE AND TRAILING EDGE DEVICES - LT OUTBOARD FLAP/ INBOARD SUPPORT BRACKET CORROSION REMOVAL AND REPAIR.
Part: HINGE — CORRODED (ZONE 600) · airframe 43,179 hrs · 8,728 cycles
RIGHT WING OUTBOARD FLAP, INBOARD AFT HINGE INBOARD PIVOT HOLE SPOTFACE CORRODED. COMPLIED WITH FEDEX EA 1-5750-75975, TRAILING EDGE AND TRAILING EDGE DEVICES. RT OUTBOARD FLAP INBOARD SUPPORT BRACKET CORROSION REMOVAL AND REPAIR.
Part: HINGE — CORRODED (ZONE 600) · airframe 43,179 hrs · 8,728 cycles
RIGHT WING OUTBOARD FLAP, INBOARD AFT HINGE INBOARD PIVOT HOLE CORRODED. COMPLIED WITH FEDEX EA 1-5750-75975, TRAILING EDGE AND TRAILING EDGE DEVICES - RT OUTBOARD FLAP INBOARD SUPPORT BRACKET CORROSION REMOVAL AND REPAIR.
Part: HINGE — CORRODED (ZONE 500) · airframe 43,179 hrs · 8,728 cycles
LT WING OUTBOARD FLAP, INBOARD AFT HINGE ACTUATOR ROD END HOLE OUTBOARD SPOTFACE CORRODED. COMPLIED WITH FEDEX EA 1-5750-75275, WINGS - TRAILING EDGE AND TRAILING EDGE DEVICES - LT OUTBOARD FLAP/ INBOARD SUPPORT BRACKET CORROSION REMOVAL AND REPAIR.
Part: HINGE — CORRODED (ZONE 600) · airframe 43,179 hrs · 8,728 cycles
RT WING OUTBOARD FLAP, INBOARD AFT HINGE OUTBOARD PIVOT HOLE CORRODED. COMPLIED WITH FEDEX EA 1-5750-75975, WINGS - TRAILING EDGE AND TRAILING EDGE DEVICES. RT OUTBOARD FLAP INBOARD SUPPORT BRACKET CORROSION REMOVAL AND REPAIR.
Part: ROD END — CORRODED (ZONE 600) · airframe 43,179 hrs · 8,728 cycles
RIGHT WING, FOUND OUTBOARD FLAP, INBOARD AFT HINGE ACTUATOR ROD END INBOARD HOLE CORRODED. COMPLIED WITH FEDEX EA 1-5750-75975, TRAILING EDGE AND TRAILING EDGE DEVICES - RT OUTBOARD FLAP / INBOARD SUPPORT BRACKET CORROSION REMOVAL AND REPAIR.
Part: SKIN — CRACKED (ZONE 500) · airframe 43,179 hrs · 8,728 cycles
LT WING FIXED LEADING EDGE LOWER SURFACE SKIN AT XORS 759 CRACKED. LT WING FIXED LEADING EDGE LOWER SURFACE SKIN AT XORS 759 SMOOTH END AND FOUND WITHIN LIMITS AS PER SRM 57-00-01 VOL 1 FIG 3 HFEC INSPECTION CARRIED OUT AS PER NDT SPM PART 06-10-01.001 REV 11.
Part: SEAT TRACK — CORRODED (ZONE 200) · airframe 43,179 hrs · 8,728 cycles
MAIN DECK - SEAT TRACK AT STA Y = 6-10 TO 6-90 (X= -8.50), FOUND WITH CORROSION. MAIN DECK - STA Y = 6-10 TO 6-90 (X= -8.50), NEW SEAT TRACK FABRICATED AS PER DWG AGA7082. CORRODED SEAT TRACK REMOVED AND REPLACED AS PER SRM 51-31-01 VOL 2.
Part: FIRE DETECTOR — CHAFED (NR 3 ENGINE) · airframe 42,753 hrs · 8,614 cycles
NR 3 ENGINE FIRE WARNING AT T/O 5 MINUTES. WARNING WAS INTERMITTENT. TESTED FIRE WARNING SYSTEM, TEST GOOD. INSPECTED NR 3 ENGINE FIRE LOOPS WIRE HARNESSES, FOUND A LOOP WIRE HARNESS CHAFED AND SHORTING OUT. REMOVED A LOOP WIRE HARNESS. REMOVED A AND B LOOP PYLON DETECTORS PER MM 26-11-03-4. INSTALLED NR 3 ENGINE FIRE DETECTORS "A" AND "B" PYLON LOOPS IAW MM 26-11-03-4. OPS CHECKS AND R-T-S-PASS FOR FDCU 3. NR 3 ENGINE COWLS CLOSED IAW MM 71-10-00.