N355MC

Part: ROD END — BROKEN (MLG) · airframe 72,706 hrs · 14,158 cycles

AFTER LANDING PERFORMED, 180 DEGREE TURN AND THE RT BODY UNLOCK LIGHT ILLUMINATED AND ACFT WOULD NOT MOVE. WENT OUT FOR VISUAL INSP AND FOUND 1 ALT ROD END BROKEN. (R & R RT BODY GEAR ACTUATOR IAW AMM 32-13-15. OPS CK SATIS. NO LEAKS FOUND.)

Part: FRAME — CRACKED (BS 420 S10R) · airframe 71,995 hrs · 14,018 cycles

EO 4753A448, A CRACK WAS FOUND IN THE BS 420, S-10R FRAME WEB . THE DAMAGE WAS TRIMMED OUT AND REPAIRED IAW NRC 500789 AND SRM 53-10-04, FIGURE 11. PART 1 OF THIS EO DOCUMENTS THE FRAME WEB REPAIR IAW NRC 500789 AND SRM 53-10-04, FIGURE 11. THE REPAIR CONSISTS OF ONE 0.063 INCH THICK DOUBLER MADE FROM 2024-T42 ALUMINUM. THE REPAIR PARTS ARE INSTALLED USING BAC415BB5D AND BACR15ET7AD RIVETS. REFER TO SRM 53-10-04, FIG 11. THE REPAIR IAW PART 1 OF THIS EO IS INTERIM AND ACCEPTABLE PROVIDED THAT INSPECTION IAW SB 747-53A2265 CONTINUE AFTER THE REPAIR IAW PART 1 OF THIS EO AT 3,000 CYCLE INTERVALS. THIS REQUIREMENT IS COMPLIED WITH IAW EO 4753A448, THEREFORE NO ACTION IS REQUIRED IAW THIS EO.

Part: TIRE — DAMAGED (MLG) · airframe 71,470 hrs · 13,922 cycles

AFTER LANDING DISCOVERED NR 14 TIRE FLAT SPOTTED. REPLACED NR 14 TIRE AND REPLACED NR 13 TIRE PRECAUTIONARY DUE OVERLOAD AND REPLACED NR 14 WHEEL TRANSDUCER. PRECAUTIONARY REPLACED, ANTI-SKID CONTROL VALVE, ANTI-SKID SERVO VALVE AND ANTI-SKID BOX DUE HISTORY ITEMS. OPS CHECKS NORMAL, AIRCRAFT RELEASED FOR FLIGHT. NO REPEAT INCIDENTS NOTED ON NEXT LEG.

Part: FAILSAFE — CRACKED (FUSELAGE) · airframe 71,342 hrs · 13,897 cycles

FUSELAGE - BS 860, S6-7R FRAME FAIL-SAFE CHORD CRACK REPAIR SRM 53-30-1 FIGURE 1, DETAILS I AND II. REPEAT REQ: PERMANENT.

Part: DOOR — DAMAGED (LANDING GEAR) · airframe 7,142 hrs · 13,897 cycles

DOOR - RT BODY GEAR DOOR DAMAGE. REPAIRED PER SRM 52-80-01, FIG 3, SH 6 ITEM 3, SRM 51-40-02, SRM 51-40-03. REPEAT REQUIREMENT: PERMANENT.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 71,342 hrs · 13,897 cycles

FUSELAGE: BS 680, BL28-30 FLOORBEAM WEB CRACK REPAIR SRM 53-10-07, FIG 11, COMPLETED.

Part: STRAP — CRACKED (FUSELAGE) · airframe 71,342 hrs · 13,897 cycles

FUSELAGE - BS 1241, LT BULKHEAD - SPLICE STRAP AND FORGING CRACK - REPAIR 747-53-2283, REV 4.

Part: SKIN — DENTED (FUSELAGE) · airframe 71,342 hrs · 13,897 cycles

FUSELAGE - BS 1520 - 1540, S43L-44L SKIN DENT REPAIR SRM 53-30-03, FIG 1. REPEAT REQ: PERMANENT.

Part: SKIN — DENTED (FUSELAGE) · airframe 71,342 hrs · 13,897 cycles

FUSELAGE - BS 2060-2080, S39L-40L SKIN DENT REPAIR SRM 53-30-03, FIG 1. REPEAT REQ: PERMANENT.

Part: BEAM — CRACKED (FUSELAGE) · airframe 71,342 hrs · 13,897 cycles

FUSELAGE - BS 540-560, RBL 45 LONGITUDINAL BEAM CRACK REPAIR SRM 53-10-05 FIG 5. REPEAT REQ: PERMANENT.

Part: SKIN — DENTED (FUSELAGE) · airframe 71,342 hrs · 13,897 cycles

FUSELAGE - BS 740-755, S46L; 46R SKIN DENT REPAIR SRM 53-30-03, FIG 1. REPEAT REQ: I-15,000 FC. R-6,000 FC.

Part: BEAM — CRACKED (FUSELAGE) · airframe 71,342 hrs · 13,897 cycles

FUSELAGE - BS 570-580, RBL 25 LONGITUDINAL BEAM CRACK REPAIR SRM 53-10-05 FIG 5. REPEAT REQ: PERMANENT.

Part: SKIN — CORRODED (FUSELAGE) · airframe 71,342 hrs · 13,897 cycles

FUSELAGE - BS 1960-2180, S46L LAP JOINT SKIN CORROSION REPAIR SRM 53-10-01 FIG 1, DETAILS I AND II. REPEAT REQ: PERMANENT.

Part: STRINGER — CORRODED (BS 760 S47R) · airframe 71,342 hrs · 13,897 cycles

FUSELAGE - BS 760, S47R STRINGER CORROSION REPAIR SRM 53-10-03 FIG 1, REPEAT REQ: 1-20,000TFC R-6,000 FC.

Part: SKIN — DENTED (FUSELAGE) · airframe 71,342 hrs · 13,897 cycles

FUSELAGE - BS 700 - 720, S46-47R SKIN DENT REPAIR 8100-9 SRM 51-40-03 OR 51-40-04, SRM 53-10-21, FIG 25, DETAIL XII. REPEAT REQ: 2ND STAGE 22,000 TFC.

Part: FRAME — CRACKED (FUSELAGE) · airframe 71,342 hrs · 13,897 cycles

FUSELAGE - BS 1540, S5;-S6L FRAME CRACK REPAIR. 8100-9 SRM 53-10-04 FIG 1, 2ND STAGE 25,000 TFC.

Part: SKIN — CRACKED (FUSELAGE) · airframe 71,342 hrs · 13,897 cycles

FUSELAGE - BS 780-800, S-46L SKIN CRACK. REPAIRED PER SRM 53-30-00, FIG 1, DETAIL 1. REPEAT REQUIREMENT: PERMANENT.

Part: SKIN — CRACKED (FUSELAGE) · airframe 71,342 hrs · 13,897 cycles

FUSELAGE - BS 1860-1880, S-41-42L SKIN CRACK REPAIR. REPAIRED PER SRM 53-30-00 FIG 1, DETAIL 1. REPEAT REQUIREMENT: PERMANENT.

Part: DOOR — DAMAGED (LANDING GEAR) · airframe 71,342 hrs · 13,897 cycles

DOOR - RT BODY GEAR DOOR DAMAGE. REPAIRED PER SRM 52-80-01, FIG 3, SH 6 ITEM 3, SRM 51-40-02, SRM 51-40-03. REPEAT REQUIREMENT: PERMANENT.

Part: DOUBLER — DAMAGED (CARGO DOOR) · airframe 71,342 hrs · 13,897 cycles

DOOR - AFT CARGO DOOR LWR AFT AND FWD CORNER DOUBLER. REPAIRED PER 8110-9 SRM 52-30-06, FIG 1, DET III. REPEAT REQUIREMENT: 1ST STAGE APPROVAL.

Part: PANEL — DELAMINATED (RT WING) · airframe 71,331 hrs · 13,896 cycles

RT WING FIXED UPPER L/E PANEL AT ILES 700.72 AND 30.0 INCHES FROM FRONT OF PANEL HAS AN AREA OF A PREVIOUS REPAIR 22.00 BY 15.0 INCHES OF DELAMINATION. PERMANENT REPAIR ACCOMPLISHED IAW SRM 51-40-09 SHEET 2 AND 5, PREPREG 250 DEGREES F CURE IAW SRM 51-40-12.

Part: BEAM — SEVERED (NR 4 PYLON) · airframe 71,331 hrs · 13,896 cycles

NR 4 PYLON LT SPRING BEAM FORWARD JOURNAL END SEVERED. NR 4 ENGINE REMOVED FOR FERRY FLIGHT TO ROW. ALL REQUIRED INSPECTIONS ACCOMPLISHED. AS PER RECOMMENDATIONS AS PER SB 747-54A2214 AND SB 747-54A2182.

Part: APU — LEAKING (ZONE 200) · airframe 69,430 hrs · 13,557 cycles

ON TAXI IN APU OIL CONSUMPTION WAS HIGH AND THERE WAS A STRONG ODOR OF OIL WHEN USING THE APU. THE APU WAS PLACED ON MEL DEACTIVATED PER 49-01.

Part: RELIEF VALVE — FAILED (NR 3 ENGINE)

AIR TURN BACK. DURING CLIMB AT APPROX FL 230, NR 3 ENGINE FIRE HANDLE ILLUMINATED. ACCOMPLISHED FHB ENGINE FIRE PROCEDURES. LIGHT EXTINGUISHED AFTER THRUST LEVER SET TO IDLE. INCREASE IN NACELLE TEMP INSPECTION CARRIED OUT IAW AMM. FOUND PRESSURE RELIEF AT FAULT. REMOVED AND REPLACED VALVE OPS CHECKED AND LEAK CHECKED OK. (K)

Part: PANEL — CRACKED (RT WING)

R/H WING UPPER SURFACE LEADING EDGE PANEL HAS A 3" CRACK LOCATED AT ILES 818.5 AND 9" FROM LEADING EDGE OF PANEL. ALSO, REFERENCE ATLAS AIR EO NO. 4757A458. UIEA200800297.

Part: PANEL — CRACKED (RT WING)

RT WING FORWARD LEADING EDGE PANEL HAS A 2.5" CRACK LOCATED AT ILES 208.81 AND IS 18.25" FROM TOP EDGE OF PANEL. PERMANENT REPAIR ACCOMPLISHED AS PER B747-300 SRM 57-30-04 FIG. 2, SHEETS 1,2 & 3. ALSO, REFERENCE ATLAS AIR EO NO. 4757A459.

Part: BEAM — CORRODED (CARGO DOOR) · airframe 67,448 hrs · 13,068 cycles

FORWARD CARGO DOOR INNER WEB LOWER BEAM FOUND SURFACE LEVEL ONE CORROSION AT RT STATION 560-670 STRINGER 40R. CLEANED CORROSION PER SRM 51-30-02 AND BOEING DRAWING 65B04697.

Part: BEAM — CORRODED (CARGO DOOR) · airframe 67,448 hrs · 13,068 cycles

AFT CARGO DOOR INNER WEB LOWER BEAM FOUND SURFACE LEVEL ONE CORROSION AT RT STATION 1810-1920 STRINGER 40R. LOWER BEAM WEB REMOVED AND REPLACED AS PER SRM 51-30-02 AND BOEING DRAWING 65B04719.

Part: BUSHING — CRACKED (NLG TRUNNION) · airframe 67,448 hrs · 13,068 cycles

NOSE LANDING GEAR TRUNNION FITTING LEFT SIDE BUSHING CRACKED. REPLACED BUSHING IAW ATLAS EO 4753B122.

Part: BUSHING — WORN (MLG TRUNNION) · airframe 67,448 hrs · 13,068 cycles

NOSE LANDING GEAR TRUNNION FITTING RIGHT SIDE BUSHING WORN. REPLACED BUSHING IAW ATLAS EO 4753B122.

Part: SEAT TRACK — CORRODED (BS 1720-1740) · airframe 67,448 hrs · 13,068 cycles

MAIN DECK STA 1720 TO 1740 RBL 11 SEAT TRACK FOUND LEVEL 1 CORROSION. CORROSION REMOVED IAW SRM 51-10-01.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 67,448 hrs · 12,068 cycles

MAIN DECK STA 2040 TO 2060 LBL 90 SEAT TRACK HAS CORROSION. SEAT TRACK REPAIRED PER SRM 53-10-05 FIG 1A.

Part: STRUCTURE — CRACKED (KRUEGER FLAP) · airframe 67,448 hrs · 12,068 cycles

NR 11 KRUEGER FLAP OUTBOARD END INNER FACE CRACKED. DAMAGE TRIMMED OFF AND REPAIR CARRIED OUT WITH FIBERGLASS AS PER SRM 51-40-14 PARA 4H.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 67,448 hrs · 12,068 cycles

MAIN DECK STA 1700 LBL 75 SEAT TRACK HAS LEVEL 1 CORROSION. CORROSION REMOVED AND TREATED IAW SRM 51-10-01.

Part: STRUCTURE — CORRODED (FUSELAGE) · airframe 67,448 hrs · 12,068 cycles

MAIN DECK STA 1680 TO 1700 RBL 11 BEAM UPPER CHORD HAS LEVEL 1 CORROSION. CORROSION REMOVED AND TREATED IAW SRM 51-10-01.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 67,448 hrs · 12,068 cycles

MAIN DECK STA 1640 TO 1690 LBL 33 SEAT TRACK HAS LEVEL 1 CORROSION. CORROSION REMOVED AND TREATED IAW SRM 51-10-01.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 67,448 hrs · 12,068 cycles

MAIN DECK STA 2020 RBL 62 FLOORBEAM CRACKED. REPLACED FLOORBEAM LOWER SUPPORT FITTING IAW SRM 51-10-01.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 67,448 hrs · 12,068 cycles

MAIN DECK STA 1680 TO 1700 RBL 11 SEAT TRACK HAS LEVEL 1 CORROSION. CORROSION REMOVED AND TREATED IAW SRM 51-10-01.

Part: SEAT TRACK — BROKEN (FUSELAGE) · airframe 67,448 hrs · 12,068 cycles

MAIN DECK STA 1840 TO 1900 LBL 11 SEAT TRACK FOUND BROKEN. SEAT TRACK REPAIRED PER SRM 53-10-05.

Part: DOOR FRAME — CRACKED (ZONE 800) · airframe 67,448 hrs · 13,068 cycles

MAIN DECK L5 DOOR CUTOUT FWD UPPER REVEAL PANEL FOUND CRACKED. REPAIRED PER SRM 53-10-04.

Part: FRAME — CRACKED (L4 DOOR) · airframe 67,448 hrs · 13,068 cycles

MAIN DECK L4 DOOR AFT LOWER CORNER FRAME CRACKED. CRACKED AREA REPAIRED PER SRM 52-10-02.

Part: SKIN — CORRODED (LT WING) · airframe 67,448 hrs · 12,068 cycles

LEFT WING UPPER SKIN REAR SPAR CORRODED LEVEL 1. CORROSION CLEANED UP AND REPROTECTED IAW SRM 51-10-01 AND 51-10-02.

Part: STRUCTURE — CRACKED (NR 6 SPOILER) · airframe 67,448 hrs · 12,068 cycles

NR 6 SPOILER LOWER FACE DOUBLER CRACKED NEAR ACTUATOR FITTING. DAMAGED SPOILER REMOVED AND REPLACED WITH SERVICEABLE SPOILER IAW AMM 27-62-01.

Part: STRINGER — CRACKED (BS 480 S10R) · airframe 67,448 hrs · 13,068 cycles

CABIN AND FLIGHT DECK UPPER DECK STA 480 STRINGER S-10 R FOUND CRACKED. REPAIRED STRINGER PER BOEING SERVICE BULLETIN 747-53A2484.

Part: SPAR — CORRODED (RWS 610-615) · airframe 67,448 hrs · 13,068 cycles

RIGHT WING STA 610 TO WING STA 615 UPPER FACE REAR SPAR LEVEL 1 CORROSION EVIDENT. CORROSION CLEANED UP AND REPROTECTED IAW SRM 51-10-01 AND 51-10-02.

Part: UNKNOWN — UNKNOWN · airframe 67,055 hrs · 12,990 cycles

DURING CLIMB WITH AUTOTHROTTLES ENGAGED AND CLIMB THRUST SET AT APPROX FL10.5 NR 4 ENGINE ROLLED BACK TO IDLE THRUST AFTER ABOUT 10 SECONDS NR 4 ENGINE RETURNED TO CLIMB THRUST. THE THRUST LEVER NEVER MOVED. THE ENGINE OPERATED NORMAL FOR THE REMAINDER OF THE FLIGHT. INSPECTED INLET AND EXHAUST PER AMM 71-00-00, NO DEFECTS NOTED. FOLLOW TROUBLESHOOTING CHART ON AMM 71-00-42, BLEW OUT THE CDP LINE AND CHECKED FOR LEAKS. NO LEAKS OR DEFECTS NOTED. CHECKED AND FOUND FUEL FILTER CLEAN. REPLACED FILTER AS A PRECAUTION. PERFORMED ENGINE RUN TEST 3, THE ENGINE OPS CHECKED OKAY. INSPECTED VSV FEEDBACK CABLE.

Part: FRAME — CRACKED (BS 1140) · airframe 66,869 hrs · 12,950 cycles

FRAME AT STATION 1140 RT HAS A CRACK AT STRINGER 10 AND 10A LOCATION. CRACK AT STR 10A 0.500 INCH LONG AND STR 10 IS 0.750 IN LONG. PERMANENT REPAIR ACCOMPLISHED AS PER B747-300 SRM 53-10-04 FIG 123 AND BOEING MESSAGE NUMBER 1-711332103-6 AND FAA FORM 8100-9. ALSO, REFERENCE ATLAS AIR XEO NR 53-121307.

Part: FRAME — CRACKED (BS 1140) · airframe 66,869 hrs · 12,950 cycles

FRAME AT STATION 1140 LT HAS A CRACK AT STRINGER 10 AND 10A LOCATION. CRACK AT STR 10A 0.875 INCH LONG AND STR 10 IS 0.760 INCH LONG. PERMANENT REPAIR ACCOMPLISHED AS PER B747-300 SRM 53-10-04 FIG 123 AND BOEING MESSAGE NUMBER 1-711332103-6 AND FAA FORM 8100-9. ALSO, REFERENCE ATLAS AIR XEO NR 53-121307.

Part: TENSION TIE — CRACKED (BS 1220) · airframe 66,869 hrs · 12,950 cycles

TENSION TIE LOCATED AT FUSELAGE STATION 1220 LT SIDE AT STRINGER 9 LOCATION HAS A CRACK. INTERIM REPAIR ACCOMPLISHED AS PER B747-300 SRM 53-10-11, FIG 1 AND BOEING MESSAGE NUMBER 1-711332103-6 AND FORM 8100-9. ALSO, REFERENCE ATLAS AIR XEO NO. 53-121307.

Part: STRUCTURE — CRACKED (MLG DOOR) · airframe 66,869 hrs · 12,950 cycles

LT WING GEAR INBOARD STRUT DOOR HAS FORWARD EDGE COMPOSITE CRACK. PERMANENT REPAIR ACCOMPLISHED AS PER B747-300 SRM 51-40-09, FIG 12, SHEETS 1, 2 AND 3.

Part: SKIN — DELAMINATED (LE FLAP)

ON WALKAROUND AFTER FLIGHT OF GT5421, FOUND NR 11 L/E DEVISE DELAMINATED AT AFT I/B CORNER. PERFORMED INTERIM REPAIR PER XEO57-082707. REPETITIVE INSPECTIONS FOR CONDITION AND SECURITY TO BE ACCOMPLISHED EVERY OTHER FLIGHT CYCLE UNTIL PERMANENT REPAIR OR PART REPLACEMENT ACCOMPLISHED.

Part: STARTER — FAILED (NR 2 ENGINE) · airframe 65,710 hrs · 12,705 cycles

BLOCK TURN BACK, NR 2 ENGINE STARTER WOULD NOT GIVE INDICATION OF ROTATION. THE PYLON BLEED VALVE AND STARTER VALVE LIGHT WERE ON. REPLACED STARTER, OPS CHECKED OKAY.

Part: DOOR — DELAMINATED (MLG) · airframe 65,569 hrs · 12,675 cycles

MATERIAL SEPARATING ON FORWARD EDGE OF LT WING GEAR INBOARD DOOR. AREA IS 15.0 INCH LONG BY 1.0 INCH WIDE. PERMANENT REPAIR ACCOMPLISHED AS PER B747-300 SRM 51-40-09, FIG 12, SHEETS 1, 2, AND 3, TABLE II, 250*F CURE AND SRM 51-40-12, REFERENCE ATLAS AIR XEO NR 52-071907.

Part: FAIRING — CRACKED (MLG DOOR) · airframe 65,569 hrs · 12,675 cycles

RT WING GEAR INBOARD STRUT DOOR FAIRING HAS A COMPOSITE CRACK AT AFT SIDE TOP SKIN AND CHAFE STRIP DAMAGED. PERMANENT REPAIR ACCOMPLISHED AS PER B747-300 SRM 51-40-09, FIG 12, SHEETS 1, 2, AND 3, TABLE I, 250*F CURE AND SRM 51-40-12, CHAFE STRIP REPLACED AS PER B747-300 SRM 51-30-02, REFERENCE ATLAS AIR XEO NR 52-071907.

Part: FIRE WARNING — FALSE ACTIVATION (APU) · airframe 65,053 hrs · 12,572 cycles

APU FIRE LIGHT AND BELL IN FLIGHT. COMPLIED WITH FHB SECTION 3. INSPECTED APU NIL FAULTS FOUND. REMOVED AND REPLACED FIRE BOTTLE AND SQUIB ASSY PER AMM 26-22-01 SQUIB TEST OKAY.

Part: SKIN — CORRODED (RT WING) · airframe 62,240 hrs · 12,403 cycles

RIGHT WING LOWER SKIN FOUND WITH CORROSION JUST INBOARD OF OUTBOARD MIDSPAR FUSE PIN FITTING OF NR 4 PYLON. CORROSION ON SAID WING LOWER SKIN REMOVED PER SRM 51-10-00. HFEC ACCOMPLISHED, NO DEFECTS. SKIN SHOT PEENED AND REPROTECTED.

Part: STRINGER — CRACKED (BS 500 S10L) · airframe 62,240 hrs · 12,403 cycles

STRINGER FOUND CRACKED AT STATION 500 STR 10L. STRINGER AT STATION 500 STRINGER 10L REPAIRED PER SB 747-53A2484 FIGURE 20 AND DEVIATION PER 8100-9.

Part: SKIN — CRACKED (NR 3 NACELLE) · airframe 62,240 hrs · 12,403 cycles

NR 3 PYLON PRECOOLER EXHAUST CUT-OUT CRACKED AT LOWER AFT SIDE. THE SKIN ASSEMBLY CRACKS WERE REMOVED BY TRIMMING. THE NR 3 STIFFENER WAS REINFORCED WITH A SUPPLEMENTARY STEEL LOWER ANGLE FROM NAC STATION 235 TO 254. THE RIB INSTALLATION AT NAC STATION 248 WAS MODIFIED TO ACCOMMODATE THE STEEL REPAIR ANGLE INSTALLED ON THE NR 3 STIFFENER. REPAIRED AREAS WERE NDT INSPECTED.

Part: SKIN — CRACKED (NR 2 NACELLE) · airframe 62,240 hrs · 12,403 cycles

NR 2 PYLON PRECOOLER EXHAUST CUT-OUT CRACKED AT LOWER AFT CORNER AT NAC 248. THE SKIN ASSEMBLY CRACKS WERE REMOVED BY TRIMMING. THE NR 3 STIFFENER WAS REINFORCED WITH A SUPPLEMENTARY STEEL LOWER ANGLE FROM NAC STATION 235 TO 254. THE RIB INSTALLATION AT NAC STATION 248 WAS MODIFIED TO ACCOMMODATE THE STEEL REPAIR ANGLE INSTALLED ON THE NR 3 STIFFENER. REPAIRED AREAS WERE NDT INSPECTED.

Part: SKIN — CRACKED (NR 1 NACELLE) · airframe 62,240 hrs · 12,403 cycles

NR 1 PYLON PRECOOLER EXHAUST CUT-OUT CRACKED AT AFT CORNER STATION 248. THE SKIN ASSEMBLY AND WINDOW STRAPS WERE TRIMMED TO REMOVE CRACKS. NET FIT ALUMINUM FILLERS WERE INSTALLED AT ALL TRIMMED AREAS. REPAIR WAS NDT INSPECTED. THE NR 3 STIFFENER WAS REINFORCED WITH A NEW STEEL LOWER REPAIR ANGLE FROM NAC STATION 235 TO 259. THE RIB INSTALLATION AT NAC STATION 248 WAS MODIFIED TO ACCOMMODATE THE NEW LOWER STEEL REPAIR ANGLE INSTALLATION ON THE MODIFIED STIFFENER.

Part: FLAP TRACK — GOUGED (NR 5 FLAP) · airframe 62,240 hrs · 12,403 cycles

NR 5 FLAP TRACK FORWARD FITTING OUTBOARD SURFACE FOUND WITH GOUGE. REPAIRED GOUGED AREA, BLENDED AND SMOOTHED PER SRM 51-10-00. DETAIL VISUAL AND HFEC INSPECTED. FOUND NO DEFECTS. AREA PROTECTED AND PAINTED. FOUND WITHIN SERVICEABLE LIMITS.

Part: SKIN — CRACKED (NR 4 NACELLE) · airframe 62,240 hrs · 12,403 cycles

NR 4 PYLON PRECOOLER EXHAUST CUT-OUT CRACKED AT LOWER AFT SIDE. THE SKIN ASSEMBLY AND WINDOW STRAP WERE TRIMMED TO REMOVE CRACKS. NET FIT ALUMINUM FILLERS WERE INSTALLED AT ALL THE SUBJECT TRIMMED AREAS TO FACILITATE ALL REPAIR PARTS AND FASTENER INSTALLATION. REPAIRED AREAS WERE NDT INSPECTED. THE NR 3 STIFFENER WAS REINFORCED WITH NEW STEEL LOWER REPAIR ANGLE FROM NAC STATION 235 TO 259. THE RIB INSTALLATION AT NAC STATION 248 WAS MODIFIED TO ACCOMMODATE THE NEW LOWER STEEL REPAIR ANGLE ON THE NR 3 STIFFENER.

Part: FRAME — CRACKED (BS 420) · airframe 62,240 hrs · 12,403 cycles

CRACK FOUND ON DOUBLER NEAR MAIN DECK FRAME WEB STRINGER CUT-OUT AT STATION 420R STRINGER 14 RT. REPAIRED, REMOVED STRINGER CLIPS AND PERFORMED DVI. ALL HOLES NDT INSPECTED. FABRICATED AND INSTALLED FLAT REPAIR DOUBLER AND INSTALLED PER BOEING MESSAGE 1-273634952-2.

Part: SKIN — WORN (NR 3 NACELLE) · airframe 62,240 hrs · 12,403 cycles

NR 3 PYLON ACCESS PANEL CUT-OUT SKIN FOUND WORN AT PANEL 472AR. REPAIR: THE EFFECTED INNER DOUBLER WAS TRIMMED. THE TRIMMED EDGE WAS NDT INSPECTED. REPAIR SKIN WAS INSTALLED WITH HILOCK FASTENERS TO RESTORE THE TRIMMED OUT AREA. A MODIFIED STEEL WEAR PLATE WAS INSTALLED ON THE SKIN ASSEMBLY SURFACE TO PROVIDE FOR ACCESS DOOR LATCH ENGAGEMENT.

Part: CADC — MULTIPLE FAIL (NR 2) · airframe 64,126 hrs · 12,382 cycles

AFTER TAKEOFF AT 2000 FT AGL, THERE WAS A TRANSPONDER FAIL LIGHT, 1&2 MODE -C- INOPERATIVE, YELLOW FLAG IN SAT. TCAS INOP, & F/O PRIMARY ALTIMETER FAILURE. REPLACED NR 2 CADC PER MM 34-12-00. OPS CHECK OK.

Part: PANEL — FAILED (IGNITION SYS) · airframe 63,946 hrs · 12,345 cycles

NR 3 ENGINE WOULD NOT START DUE TO NO IGNITION, FUEL FLOW NORMAL. TROUBLESHOT AND FOUND THE NR 3 AND NR 4 IGNITION PANEL AT FAULT. REMOVED AND REPLACED IGNITION PANEL PER AMM 74-11-00. ALL OPS NORMAL.

Part: RELAY — NOT SEATED (NR 3 ENGINE) · airframe 63,810 hrs · 12,317 cycles

ATTEMPTED TO START NR 3 ENGINE 2 TIMES. AFTER SECOND ATTEMPT FUEL FLOW INDICATED IN EXCESS OF 1100 KGPH. ENGINE WOULD NOT START. CHECKED CONDITION ACTUATOR, RESEATED RELAYS YBEK12 AND YBEK08, OPS CHECKED OK. ENGINE STARTED ON FIRST ATTEMPT.

Part: CONNECTOR — UNSECURE (EXCITER BOX) · airframe 63,772 hrs · 12,310 cycles

NR 3 ENGINE WOULD NOT START. RESEATED BOTH CONNECTORS ON NR 1 AND NR 2 EXCITER BOXES.

Part: ACTUATOR — LEAKING (SPOILER) · airframe 63,650 hrs · 12,285 cycles

NR 2 HYDRAULIC SYSTEM QUANTITY LOW. QUANTITY DECREASED 1.5 GAL THIS LEG. REMOVED AND REPLACED NR 7 OUTBOARD SPOILER ACTUATOR PER MM 27-61-02. OPS AND LEAK CHECKS NORMAL.

Part: PUMP — MALFUNCTIONED (HYD SYSTEM) · airframe 63,643 hrs · 12,283 cycles

AFTER ENGINE START, NR 4 ADP INOP WITH ADP NR 4 SWITCH IN AUTO OR CONTINUOUS. RUN LIGHT EXTINGUISHED AND ADP PRESSURE LIGHT ILLUMINATED. RESET NR 4 ADP OVERSPEED SWITCH AND SERVICED NR 4 ADP PER MM 29-11-04 AND 12-13-09. TEST OK.

Part: ROTARY SWITCH — FAILED (AC BUSS) · airframe 63,316 hrs · 12,213 cycles

DURING DEPARTURE CHECKS, ESSENTIAL AC BUSS SELECTOR SWITCH ON ESSENTIAL AC BUSS CONTROL MODULE WAS VERY DIFFICULT TO ROTATE. TRIED SEVERAL TIMES TO LUBE AND FREE UP SWITCH WITH NO HELP. REPLACED ESSENTIAL AC BUSS CONTROL MODULE PER MM 24-27-03, ALL OPERATIONS NOW NORMAL.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 63,134 hrs · 12,176 cycles

DURING MAINTENANCE, FOUND FLOORBEAM LOWER FUSELAGE UPPER CHORD DAMAGED (CRACKED) AT STA 1780, WL 118 LBL 54. CUT OUT DAMAGED SECTION FROM LBL 40 AND SPLICED IN NEW SECTION OF CHORD PER SRM 51-40-04 FIG 1 AND ATLAS E04753A637.

Part: WIRE — LOOSE (ENGINE) · airframe 62,744 hrs · 12,095 cycles

FLIGHT CREW REPORTED NR 3 ENGINE EGT INOP. FOUND LOOSE WIRE AT HARNESS END (PYLON CONNECTION). SECURED WIRE, ALL OPS AND INDICATIONS NORMAL IAW MM 77-00-00.

Part: COMPUTER — INOPERATIVE (AUTOPILOT) · airframe 61,944 hrs · 11,875 cycles

"A" AUTOPILOT ALT HOLD INOP. "B" AUTOPILOT ON DEFERRAL WILL NOT ENGAGE. REPLACED "A" PITCH COMPUTER PER MM 22-12-01. DMI CONTINUES.

Part: COMPUTER — FAILED (NR 1 ADC) · airframe 61,926 hrs · 11,870 cycles

"A" AUTOPILOT ALTITUDE HOLD INOP. "B" AUTO PILOT WOULD NOT ENGAGE. AIRCRAFT DIVERTED TO AMS. REPLACED NR 1 AIR DATA COMPUTER AND DEFERRED "B" AUTOPILOT MM 34-12-01.

Part: ODOR — UNKNOWN (CABIN)

INBOUND CREW REPORTED SMELL OF ELECTRICAL SMOKE IN COCKPIT DURING APPROACH. PERFORMED VISUAL INSPECTION OF ELECTRONIC COMPARTMENT SHELVES. NO EVIDENCE OF SMOKE OR DAMAGE NOTED. VISUALLY INSPECTED AREA UNDER PILOT'S YOKE AND CENTER PEDESTAL, NO DAMAGE FOUND.

Part: VALVE — STUCK (NR 1 ENGINE) · airframe 61,412 hrs · 11,754 cycles

ON TAKEOFF NR 1 ENGINE A-FIRE LOOP WENT TO 4.0. B-FIRE LOOP WENT TO 5.0 AND STAYED THERE UNTIL THROTTLES WERE RETARDED FOR DESCENT. FOUND NR 1 ENGINE HIGH STAGE VALVE STUCK OPEN, LOCKED CLOSED, OPENED MEL 36-01-3B.

Part: WIRE — BROKEN (WARNING HORN) · airframe 61,332 hrs · 11,738 cycles

CREW REPORTED STAB TRIM GREEN BAND AMBER LIGHT ON PILOT’S CENTER PANEL AND GREEN BAND LIGHT ON CONTROL STAND. CAME ON AFTER APL NOSE UP SELECTED. ACCORDING TO WEIGHT AND BALANCE CALCULATION. NO TAKEOFF WARNING HORN WITH FLAPS 20 DEGREES. FOUND BROKEN WIRE ADJACENT TO CONNECTOR D8113. REPAIRED BROKEN WIRE PER MM 20-10-13, INDICATION NORMAL.

Part: CONTROL PANEL — INOPERATIVE (AUTOPILOT SYS) · airframe 61,072 hrs · 11,678 cycles

ON PRE-FLIGHT CREW REPORTS UNABLE TO ENGAGE EITHER -A- OR -B- AUTOPILOT. REPLACED P10 MODE CONTROL PANEL. OPS NORMAL PER MM 22-11-06.

Part: VALVE — LEAKING (HYD SYSTEM) · airframe 60,913 hrs · 11,645 cycles

NR 2 ENGINE HYDRAULIC SUPPLY C/B POP’S. REPLACED SUPPLY VALVE, OPS AND LEAK CHECK OK PER MM 29-11-04.

Part: LINE — LEAKING (FUEL CROSSFEED) · airframe 60,873 hrs · 11,636 cycles

FUEL MIGRATING INTO NR 1 MAIN FUEL TANK. FOUND CROSS FEED LINE LEAKING AT FWD BULKHEAD COUPLING. RESEALED AND RETORQUED COUPLING OPS AND LEAK CK OK PER MM 28-22-07 AND 28-11-02.

Part: CHECK VALVE — MALFUNCTIONED (FUEL SYSTEM) · airframe 60,866 hrs · 11,634 cycles

DURING CROSS FEED FROM CENTER WING AND NR 2 AND NR 3 MAIN TANKS, ALL CROSS FEED VALVES OPEN AND NR 1 AND NR 4 TANKS BOOST PUMP OFF. NR 1 MAIN TANK QTY INCREASES 1000 KGS PER HOUR. REPLACED CHECK VALVE AT AFT BOOST PUMP NR 1. VERIFIED OPERATION OF DISCHARGE CHECK VALVE OK PER MM 28-22-06. TRANSFERRED FUEL INTO NR 1 MAIN LEAK CHECKED AND SYSTEM OPS OK.

Part: MODULE — MALFUNCTIONED (NLG STEERING) · airframe 60,230 hrs · 11,495 cycles

BODY GEAR STEERING LIGHT ILLUMINATED, PRIMARY AND ALTERNATE. REPLACED BGS MODULE PER MM 32-53-00. ALL OPS & IND, OK PER 32-53-00.

Part: A/C PACK — ODOR (NR 2) · airframe 60,021 hrs · 11,448 cycles

NR 2 A/C PACK HAS LOUD NOISE AND STRONG SMELL DURING OPERATION (ELECTRICAL). DEACTIVATED NR 2 A/C PACK PER MEL NR 21-1-2C. ITEM TRANSFERRED TO DMI CONTROL NR 33592.

Part: CADC — INGESTED (NR 1) · airframe 59,610 hrs · 11,352 cycles

NR 1 CADC INOPERATIVE. REPLACED NR 1 CADC, OPS CHECK OK PER AMM 34-12-01.

Part: SENSOR — MALFUNCTIONED (AOA) · airframe 59,416 hrs · 11,311 cycles

STICK SHAKER ACTIVATING INTERMITTENTLY IN STEADY STATE CRUISE FLIGHT, C/B PULLED. REPLACED LT AOA SENSOR PER AMM 27-32-01, OPS CHECK OK PER AMM 27-32-00.

Part: IGNITER — FAILED (NR 3 ENGINE) · airframe 59,332 hrs · 11,291 cycles

NR 3 ENGINE IGNITION INOP ON START. REPLACED BOTH IGNITER PLUGS PER AMM 74-21-02 & SYSTEM OPS TEST OK PER AMM 74-00-00/501.

Part: DUCT — RUPTURED (NR 4 ENGINE) · airframe 59,312 hrs · 11,286 cycles

NR 4 ENGINE FIRE/FAULT LOOPS A&B BOTH SHOWED A CONTINUOUS RISE IN TEMP, CLOSED BLEED AIR VALVE, TEMPRATURE DROPPED TO NORMAL. RETARDED THROTTLE TO IDLE. T/S & FOUND S-DUCT IN PYLON RUPTURED. REPLACED DUCT & CLAMPS PER AMM 36-11-00, NO LEAKS NOTED.

Part: WARNING LIGHT — ACTIVATED (WX RADARS) · airframe 59,081 hrs · 11,233 cycles

(ANT FAULT): MESSAGE ON BOTH NR 1 AND NR 2 WX RADARS. TRANSFERED TO DMI NR 33183 IAW MEL NR 34-23B.

Part: CONTROLLER — OUT OF ADJUST (NR 1 ENGINE) · airframe 58,698 hrs · 11,141 cycles

NR 1 ENGINE WOULD NOT MAKE TAKEOFF POWER. ADJUSTED MAIN ENGINE CONTROL PER AMM 73-00-00.

Part: PDU — INOPERATIVE (LE FLAPS) · airframe 58,305 hrs · 11,052 cycles

NR 4 LEADING EDGE (AMBER) TRANSIT LIGHT ON WITH FLAPS EXTENDED. REMOVED AND REPLACED NR 4 EDGE PDU IAW MM 27-81-01, OPS CHECK NORMAL, ALSO REPLACED PDU ELECTRICAL CONNECTOR.

Part: SWITCH — DIRTY (TE FLAPS) · airframe 58,301 hrs · 11,051 cycles

AFTER START AND TAXI, LE FLAPS NR 4L WOULD NOT EXTEND FROM AMBER, ALT SYSTEM ATTEMPTED, STILL REMAINED AMBER. NR 4L LE FLAP IND GREEN UNTIL TAKEOFF POWER SETTING APPLIED, IND WENT AMBER, ALSO TAKEOFF WARNING HORN SOUNDED. INSPECTED CLEANED IND SWITCH ASSEMBLY CYCLED, LE FLAPS OPS CHECK NORMAL. FOUND CARD A-5 IN LE FLAP POSITION MODULE LOOSE, RESEAT CARD, OPS CHECKS GOOD, ALL IAW MM 27-81-01 AND 27-88-01.

Part: ACTUATOR — INOPERATIVE (CARGO DOOR) · airframe 58,249 hrs · 11,038 cycles

BEFORE DEPARTURE COULD NOT LOCK LATCHES ON MAIN CARGO DOOR. REPLACED LATCH ACTUATOR, OPS CHECK OK AS PER MM 52-32-09.

Part: COUPLER — DAMAGED (COMPASS) · airframe 58,186 hrs · 11,025 cycles

CAPTAIN COMPASS SYSTEM WOULD NOT SYNC. REPLACED COMPASS COUPLER, OPS CHECK NORMAL AS PER AMM 34-21-00.

Part: RELIEF VALVE — LEAKING (NR 4 ENGINE) · airframe 57,987 hrs · 10,983 cycles

DURING A/C CLIMBOUT AT 23,000 FT, NR 4 ENGINE NACELLE TEMPERATURE WAS INDICATING 8 UNITS. ACCOMPLISHED PROCEDURE FOR ABNORMAL NACELLE TEMPERATURE RETURNED TO NORMAL. NACELLE TEMPERATURE FLUCTUATED WITH THROTTLE MOVEMENT. REMOVED AND REPLACED PRESSURE REGULATING VALVE, HIGH STAGE VALVE AND PRESSURE RELIEF VALVE PRECAUTIONARY.

Part: LINE — LOOSE (BLEED AIR) · airframe 57,986 hrs · 10,982 cycles

DURING CLIMBOUT NR 4 ENGINE FIRE LIGHT ILLUMINATION AND FIRE BELL SOUNDED. ENGINE SHUT DOWN, BOTTLES NOT FIRED. FOUND SENSE LINE OFF PRV. SECURED LINE & CHANGED UNION PER MM 36-11-19. OPERATIONAL CHECK OK.

Part: INU — MALFUNCTIONED (NAV SYSTEM) · airframe 57,841 hrs · 10,951 cycles

AFTER TAKEOFF, POSITION ERROR IN INS, UNABLE TO UPDATE MANUALLY OR AUTOMATICALLY. INS SYSTEM OPERATIONAL CHECK NORMAL AS IAW MM 34-41-00, DME SYSTEM OPERATIONAL CHECK NORMAL IAW MM 34-55-00.

Part: ROD — LOOSE (NR 3 ENG T/R) · airframe 575,864 hrs · 10,892 cycles

NR 3 ENG HAS ROD STICKING OUT OF T/R SLEEVE AT 3:00 POSITION. REMOVED DAMAGED ROD, INSPECTED AREA, FOUND NO FURTHER DAMAGE. DEACTIVATED PER MEL 78-01-05.

Part: BLEED VALVE — FAILED (APU) · airframe 57,464 hrs · 10,864 cycles

APU BLEED AIR VALVE FAILED ON PUSHBACK ENGINE START. DEFERRED APU BLEED AIR IAW MEL 49-1-1.

Part: CABLE — DISCONNECTED (NR 1 ENGINE) · airframe 57,379 hrs · 10,845 cycles

NR 1 ENGINE ACCELERATES EXTREMELY SLOW. THE N2, EGT, AND FUEL FLOW ARE NOT ALIGNED WITH OTHER ENGINES. N1 GAUGE REMAINED AT IDLE. CORRECTIVE ACTION: DISCONNECTED MEC VSB/VBV, FEEDBACK CABLES EXERCISED MEC. RECONNECTED VSV/VBV FEEDBACK CABLES. PERFORMED ENGINE RUN, CK OK.

Part: CONTROL PANEL — SMOKE (VHF NAV) · airframe 57,379 hrs · 10,845 cycles

SPARKS AND SMOKE CAME FROM BEHIND FO VOR ON LANDING. R & R NR 2 VHF CONTROL PANEL.

Part: CIRCUIT CARD — LOOSE (INDICATOR LIGHTS) · airframe 56,978 hrs · 10,763 cycles

INDICATOR LIGHTS PILOTS AND FLT ENGINEERS CIRCUIT BREAKER POPS AND WILL NOT RESET. RESEATED THE A-10 CARD IN THE MASTER DIM AND TEST BOX. SYS CKS OK IAW MM.

Part: SENSOR — FAILED (AOA) · airframe 56,896 hrs · 10,746 cycles

ON TAKEOFF AND TO CRUISE ALT 31.0, STICK SHAKER ON. RESET C/B, NO CHANGE. SHAKER STOPPED AT FL 31.0, AT CRUISE MACH, SAME ON APPROACH. REMOVED AND REPLACED AOA SENSOR, LT, IAW MM 27-37-01. OPS CK NORMAL.

Part: CONTROL PANEL — INOPERATIVE (COCKPIT) · airframe 55,704 hrs · 10,509 cycles

ON PREFLIGHT, F/O'S VHF NAV PANEL LIGHTS INOP. REPLACED F/O'S VHF NAV CONTROL PANEL, TESTS NORMAL PER MM 34-31-01.

Part: EXCITER — INOPERATIVE (NR 4 ENGINE) · airframe 55,553 hrs · 10,476 cycles

NR 4 ENG START NO INGITION. REPLACED NR 4 ENG NR 1 EXCITER BOX: DEFERRED NR 4 ENG NR 2 IGNITION SYS.

Part: BULB — SHORTED (CAUTION PANEL) · airframe 55,483 hrs · 10,462 cycles

ON PUSHBACK THE INDICATOR AND DIGITAL DISPLAY CIRCUIT BREAKER POPPED AND WOULD NOT RESET. REPEAT CAME BACK TO BLOCKS. FOUND SHORTED BULB ON CAPT'S CAUTION PANEL GEAR PER NOT CENTERED LIGHT, RELAMPED OPS CK GOOD PER 33-10-00 GROUND OPS GOOD PER 33-10-00. GROUND OPS BODY GEAR PER 32-60-00, NO FAULTS.

Part: WIRE — GROUNDED (ELECTRICAL POWER) · airframe 55,483 hrs · 10,462 cycles

INDICATOR AND DIGITAL DISPLAY CIRCUIT BREAKER ON PG PANEL POPPED AND WOULD NOT RESET. PILOTS INDICATION LIGHTS WENT OUT. FOUND PWR WIRE GROUNDED TO CASE ON CAPT'S PNL CNTRL DIMMER SWITCH. REPOSITION WIRES AND OPERATION CK GOOD PER MM 33-11-11.

Part: PLATE — DEFECTIVE (CONTROL COLUMN) · airframe 55,207 hrs · 10,401 cycles

DURING FLT CNTRL CK, FELT A THUMP AND CLICK IN LEFT TURN - FORE AND AFT MOVEMENTS. REMOVED CAPT CONTROL COLUMN -REMOVED AND REPLACED PLATE ASSY - REINSTALLED COLUMN AND TESTED NRML IAW AMM 27-31-04/05.

Part: SWITCH — MALFUNCTIONED (HORIZ STAB) · airframe 551,649 hrs · 10,392 cycles

RETURNED TO BLOCKS - TAKEOFF WARING HORN SOUNDED WHEN THROTTLES ADVANCED - UNABLE TO SELECT APL NOSE DOWN ON STAB TRIM GREEN BAND SELECTOR (TRIM 3.5). REPLACED STAB SWITCH S334.

Part: THROTTLE — STUCK (# 4 ENG) · airframe 105,751 hrs · 19,832 cycles

# 4 ENG. SHUT DOWN ON DESCENT INTO PIK - THROTTLE STUCK AT 2.0 ON THROTTLE QUANDRANT ENG PARAMETERS NORMALS 75% M ONE MORE THIS HAPPENED ON DESCENT OIL PRESSURE AT LAST FEW MIN. OF FLT THROTTLE OK AFTER LANDING. ENG SHUT DOWN CHECKLIST COMPLIED WITH A/C CURRENTLY IN A-CK CORRECTIVE ACTION TO FOLLOW.

Part: FRAME — CRACKED (NR 3 ENGINE) · airframe 53,522 hrs · 10,146 cycles

A 2 INCH CRACK FOUND, NR 3 ENGINE, TURBINE MID FRAME HOT SECTION AT NR 7 TIME (10 O'CLOCK POSITION). CRACK WELDED IAW GE SOPM 70-41-00. REF EDA 7254E001.

Part: SKIN — DELAMINATED (RT WING) · airframe 53,522 hrs · 10,046 cycles

DELAMINATION FOUND ON RT WING UPPER SURFACE LEADING EDGE COVER (NU-CAP) PANEL AT WING STATION 557 & HAS 3 FEET X 6 INCHES OF EXPOSED HONEYCOMB. REPLACEMENT PANEL INSTALLED IAW SRM 51-30-02. FILLET SEAL APPLIED TO EDGE OF PANEL IAW SRM 51-10-06.

Part: PANEL — DAMAGED (FAIRING) · airframe 52,358 hrs · 9,809 cycles

FOUND 6 INCH CRACK IN HONEYCOMB OF PANEL 193 AFT OF LT BODY GEAR FAIRING PANEL. REPAIRED PANEL AFT OF LT BODY GEAR BS 1620 TO BS 1660 AS PER B747 SRM 51-40-07. LT BODY GEAR O/B STRUT DOOR DAMAGED. DOOR REMOVED, INSTALLED NEW DOOR ASSY. REINSTALLED LEFT BODY GEAR SHOCK STRUT USING ORIG ROD IAW MM 32-14-00. INSTALLED PUTTY TO DOOR STOPS. REQ CHK & MEASURE ON NEXT LEG IAW MM 32-14-00, PG 519, CHAP H. FOUND HOLE IN WING TO BODY FAIRING BEHIND LEFT GEAR STRUT. REMOVED & REPLACED BODY GEAR FAIRING PANEL JUST AFT OF LEFT BODY GEAR AS PER B747 SRM 51-10-01. ALL DAMAGE OCCURRED DUE TO FOD ON RUNWAY DURING TAKEOFF OR LANDING.

Part: FLAP TRACK — CORRODED (WING)

DURING CURRENT (D) CHECK AT SIAEC, THE NR 5 FLAP TRACK O/B LOWER FLANGE IN THE MID SECTION WAS FOUND WITH LEVEL 1 CORROSION FOR APPROX 10 INCHES. CORROSION MACHINED OUT AND BLENDED MAINTAINING A 100 TO 1 BLEND RATIO TO ENSURE A SMOOTH FLAT SURFACE. AREA MAGNETIC PARTICLE INSPECTED TO ENSURE NO CRACKING DURING PROCESS. NO DEFECTS FOUND. AREA MEASURED AND RECORDED.

Part: FRAME — CRACKED (FUSELAGE)

DURING CURRENT (D) CHECK, SIAEC, FOUND STA 440L FRAME CRACKED AT CUTOUT OF STR 10A. CRACK LENGTH .1875. STOP DRILLED CRACK, FABRICATED REPAIR DOUBLER AND INSTALLED PER SRM. FRAME IS SUBJECT TO RECURRENT INSPECTIONS.

Part: FRAME — CRACKED (FUSELAGE)

DURING CURRENT D-CHECK AT SIAEC, FOUND STATION 440L FRAME CRACKED AT CUT OUT OF STRINGER 10A. CRACK LENGTH .1875. STOP DRILLED CRACK, FABRICATED REPAIR DOUBLRS AND INSTALLED PER SRM 53-10-20 AND 53-10-04. FRAME IS SUBJECT TO RECURRENT INSPECTIONS PER SB 747-53A2265 AT 3000 CYCLES. (M)

Part: FLAP TRACK — CORRODED (T/E FLAP)

DURING CURRENT D-CHECK AT SIAEC, THE NR 5 FLAP TRACK OUTBOARD LOWER FLANGE IN THE MID SECTION WAS FOUND WITH LEVEL 1 CORROSION FOR APPROX 10 INCHES. CORROSION MACHINED OUT AND BLENDED MAINTAINING A 100 TO 1 BLEND RATION TO ENSURE A SMOOTH FLAT SURFACE. AREA MAGNETIC PARTICLE INSPECTED TO ENSURE NO CRACKING DURING PROCESS. NO DEFECTS FOUND. AREA MEASURED AND RECORDED. SURFACE TREATED AND REFINISHED. REWORK PERFORMED IAW SOPM 20-10-01/02. (M)

Part: PUMP — FAILED (NR 4 ENGINE)

SHORTLY AFTER LEVEL OF AT 39.0, NR 4 ENGINE FIRE WARNING LIGHT ILLUMINATED. BOTH A/B FIRE LOOPS INDICATED FIRE. ACCOMPLISHED EMERGENCY FIRE PROCEDURES. AIRCRAFT RETURNED TO MIA. FOUND NR 4 EDP AT FAULT. REMOVED AND REPLACED EDP P/N 6506606. OPS AND LEAK CHECK OK. ALSO, FOUND 8TH STAGE DUCT CLAMP LEAKING NEAR FIRE WARNING ELEMENT. REPLACED CLAMP, PERFORMED OPS AND LEAK CHECK. ALL OK. (M)

Part: FRAME — CRACKED (FUSELAGE)

WHILE INSPECTION FRAME STATION 1265 BELOW FORWARD END OF MAIN ENTRY DOOR NR 3 CUT OUT AT WL 199, EDDY CURRENT CHECK INDICATED CRACK INDICATIONS L/S HOLE NR 10 AND R/S AT THE 10 O'CLOCK POS. HOLES REWORKED AND CRACKS STOP HOLED AS REQUIRED. REPAIR ANGLES, DOUBLERS AND NEW INTERCOSTAL INSTALLED PER SB747-A2416 BOTH LEFT AND RIGHT SIDES. REPAIR TO BE RE-INSPECTED AT 2000 FLIGHTS. (M)

Part: BOLT — CORRODED (CARGO DOOR)

WHILE REMOVING SEALER ON THE MAIN DECK CARGO DOOR LATCH FITTINGS, 5 EACH BROKEN BACB3DTR ''K'' BOLTS WERE FOUND. (3 BOLTS COMMON TO NR 8. 2 BOLTS COMMON TO NR 9 LATCH FITTING). NOTE: IPC CALL OUT FOR THESE BOLTS IS BAC3B3D MT ''K''. ALL 10 LATCH FITTINGS WERE REMOVED. INSPECTION REVEALED CORROSION UNDER THE NR''S, 7, 8, 9, AND 10 FITTINGS COMMON TO THE SILL PLATE, BUT NO ADDITIONAL BROKEN BOLTS. ALL BOLTS COMMON TO LATCH FITTINGS HAVE BEEN REPLACED WITH BACB3DU5 ''K'' BOLTS. (X)