N470EV

Part: DETECTION SYS — MALFUNCTIONED (APU FIRE LOOP) · airframe 105,316 hrs

APU FIRE LOOP "B" GIVES FIRE INDICATION. APU FIRE HANDLE LIGHT ON. RESEQUENCED FIRE HANDLE WITH C/B PERFORMED WI CHECK FROM CARD FILE J5 AND J3 TO APU FIRE LOOPS BOTH REATS SAME REINSTALL J5 AND J3 CONNECTORS OP'S CHECKED OK PER 26-15-00/501.

Part: PRESSURE SWITCH — LOOSE (ENGINE OIL SYS)

NR 3 OIL QUANTITY INDICATOR DROPPED TO ZERO AT 7000, OIL PRESSURE FLUCTUATED +/- 10 PSI. ENGINE SHUTDOWN. PERFORMED ENGINE WINDMILLING INSPECTION IAW MM 72-00-00 PAGE 846. FOUND LOW OIL PRESSURE SWITCH LOOSE, RETORQUED PER MM 79-33-01. OP'S AND LEAK CHECKED NORMAL, TROUBLE SHOT AND LEAK CHECKED NORMAL PER 71-00-00 AND 71-00-44.

Part: LIGHT — FAILED (CABIN) · airframe 105,036 hrs · 23,392 cycles

STAIRWAY DOME EMERGENCY LIGHT GOES OUT AFTER 10 SECONDS. REMOVED AND REPLACED LIGHT ASSY. PER MM 33-51-07 PG 201.

Part: LIGHT — DEFECTIVE (ZONE 200)

POSSIBLE DEFECTIVE EMERGENCY LIGHT - SCHEDULED B CHECK ITEM CHANGE.

Part: FITTING — LEAKING (GEARBOX) · airframe 105,031 hrs · 23,391 cycles

ENGINE OIL PRESSURE LIGHT - SLOW LOSS OF OIL. FOUND EVIDENCE OF LEAKAGE AT THE ANGLE GEARBOX RIGHT SIDE FITTINGS, REPLACED WITH NEW SEAL PACKINGS PER MM 70-10-07 PERFORMED ENGINE WINDMILLING INSPECTION PER AMM 72-00-00. NO DEFECTS NOTED. SEAL REPLACED AT CHIP DETECTOR FITTING BASE REQUIRES ENGINE RUN & LEAK CHECK. INSTALLED BOLT THAT WAS MISSING ON THE FITTINGS PER AMM 70-50-00 LEAK CHECKED GOOD AMM 71-00-00.

Part: ACTUATOR — CONTAMINATED (LANDING GEAR) · airframe 109,883 hrs

(SECOND FLIGHT) AFTER GEAR UP, MOVING GEAR LEVER TO OFF RESULTED IN GEAR LEVER LATCH IN VIEW. F/E ANNUNCIATOR PANEL SHOWED RIGHT WING TILT LIGHT ILLUMINATED WITH BOTH PRIMARY AND ALTERNATE BUTTONS DEPRESSED. CYCLED GEAR HAD NORMAL INDICATION UNTIL GEAR UP AND SAME INDICATIONS. DIVERTED TO JFK AND DUMPED FUEL, LAND WITHOUT FURTHER INCIDENT. TARGETED RIGHT WING TILT SWITCHES, PRIMARY AND ALTERNATE. WHEN SWITCHES WERE TARGETED THE PRIMARY AND ALTERNATE LIGHTS WERE EXTINGUSHED. BLED RT WING GEAR TILT ACTUATOR PER MM 32-11-20. PERFORMED INSPECTION OF TILT INDICATION SYSTEM IAW MM 33-61-00, NO DEFECTS NOTED. DURING BLEED OF TILT ACTUATOR FOUND AIR IN SYSTEM BLED ACTUATOR IAW 32-11-20.

Part: ACTUATOR — MALFUNCTIONED (RT WLG) · airframe 10,988 hrs

AFTER GEAR UP, MOVING GEAR LEVER TO OFF RESULTED IN GEAR LEVER LATCH IN VIEW. F/E ANNUNCIATOR PANEL SHOWED RIGHT WING TILT LIGHT ILLUMINATED WITH BOTH PRIMARY AND ALTERNATE BUTTONS DEPRESSED. CYCLED GEAR HAD NORMAL INDICATION UNTIL GEAR UP AND SAME INDICATIONS. DIVERTED TO JFK AND DUMPED FUEL, LAND WITHOUT FURTHER INCIDENT. REMOVED AND REPLACED RT WING GEAR TILT ACTUATOR REF: MM 32-11-20 LEAK CHECK IS GOOD. TILT SENSOR OP'S CHECK IS GOOD REF: MM 32-61-04.

Part: SPINNER — MALFUNCTIONED (NR 2 ENGINE)

NR 2 ENGINE EXPERIENCED SURGE STALL WITH INSTANTANEOUS EGT EVENT AND SHUTDOWN, WITH VIOLENT VIBRATION PRIOR TO EVENT. CREW REPORTED VISIBLE DEBRIS IN AREA OF NR 2 INLET, DUMPED FUEL AND RETURNED TO HIK, NO FIRE REPORTED. FOUND NR 2 ENGINE SPINNER & FAN WITH FOD DAMAGE. NOSE COWL WITH FOD DAMAGE, ENGINE REPLACEMENT COMPLIED WITH CONDITIONAL INSPECTIONS PER B747 MM 5-51-06, 5-51-71. REPLACED NR 2 ENGINE AND NOSE COWL PER EIA W/C F7103, F7201 JT9 7201JT9RS, F7202, F7203, FF7204, F7205, F7207, F7209, NP7201, NP7201RS, EIA ECRA 662247-72-013-1 OP'S AND LEAK CHECK GOOD PER B747 MM 71-00-00 TEST NR 4 AND NR 8.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 103,939 hrs · 23,137 cycles

BS 2190L EMERGENCY LIGHT INOP. REMOVED AND REPLACED LIGHT ASSY PER AMM B747 33-51-07 PG 201 OP'S CHECK GOOD.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 103,939 hrs · 23,137 cycles

R5 DOOR EMERGENCY LIGHT INOP. REMOVED AND REPLACED LIGHT ASSY PER AMM B747 33-51-07 PG 201, OP'S CHECK GOOD.

Part: PIN — DAMAGED (CONNECTOR) · airframe 103,939 hrs · 23,137 cycles

L5 DOOR EMERGENCY LIGHT INOP. REPAIR PIN ON CONNECTOR PER B747 WDM 33-51-01 AND AMM 33-51-07 PG 201, OP'S CHECK GOOD.

Part: LINE — LOOSE (P2) · airframe 103,116 hrs

NR 2 ENGINE SURGED PASSING FL140 EGT AT 750 EPR AT 1.3 HAD SURGE THEN HUNG, NO THROTTLE RESPONSE. SHUT DOWN ENGINE WAITED 5 MIN, THEN RE-STARTED, AFTER 10 MIN AT FL040, RE-TARDED THROTTLE AND EXPERIENCED 2ND SURGE SHUT DOWN ENGINE WITH NO EXCEEDANCE. CARRIED OUT TSM 71-00-43 DECELERATION SURGE FLOW CHART NO DEFECTS NOTED. FAILED EVC TEST CARRIED OUT AS PER MM 71-00-42 PROCEDURE 5 ALL INDICATIONS NILL. BORESCOPE INSPECTION CARRIED OUT PER TSM 71-0043 AND 72-00-00 NO DEFECTS NOTED TANDOM BLEED SCHEDULING INSP CARRIED OUT AS PER MM 71-00-00 PROCEDURE 5 ALL INDICATIONS NILL. FOUND P2 LINE LOOSE AT PRBC TIGHTEN AS PER 71-51-01 OPS CHECKED NORMAL. (ORIGINAL SUBMISSION: 2-24-2011)

Part: BATTERY PACK — DISCHARGED (CABIN)

WITH EMERGENCY LIGHTS IN ON POSITION CREW SERVICE DOOR EMERGENCY LIGHTS DID COME ON, LEFT FWD DOOR OVERHEAD EMERGENCY LIGHTS CAME ON THEN WENT OUT. BOTH ITEMS DEFERRED TO DMI 91 AND 92 PER MEL 33-13 OPT 2. REMOVED AND REPLACED EMGER LIGHT BATTERY PACK REF. 33-51-04 SYSTEM OP CHECK IS GOOD. DMI CLEARED PLACARD REMOVED

Part: DOUBLER — CRACKED (PYLON)

NR 3 PYLON INBOARD SIDE NAC STA 252 APPROX 22 INCHES ABOVE SKIRT REPAIR DOUBLER HAS CRACK. REMOVED DAMAGE, NDT AREA FABBED REPAIR AND INSTALLED PER ECRA 470-54-309-2.

Part: SKIN — BENT (BS 426 S37R) · airframe 101,443 hrs · 22,594 cycles

BS 426 STR. 37R HAS A STR. FLANGE TO SKIN BENT. REMOVED DAMAGED AND FABRICATED REPAIR IAW SRM 51-40-3, PG 1-6.

Part: SKIN — DENTED (FUSELAGE) · airframe 101,443 hrs · 22,594 cycles

EXTERNAL SKIN DENT AT BS 380-400 STRINGER 34R TO 35R. CUT OUT DAMAGE, FABRICATED AND INSTALLED FILLER AND DOUBLER PER B747 SRM 53-30-03 PAGE 73.

Part: ENGINE — MALFUNCTIONED (NR 3) · airframe 99,604 hrs · 22,222 cycles

NR 3 ENGINE SURGE/STALL AT MAX TAKEOFF POWER. EGT EXCEEDANCE 1088 DEG CELSIUS. REMOVED AND REPLACED NR 3 ENGINE PER WORKCARDS F7201, F7204, F7207, F7209. OPS & LEAK CHECK GOOD.

Part: ACM — LEAKING (AC BAY) · airframe 1,005,748 hrs

DURING HIGH POWER SETTING (1.45 AND ABOVE) A SWEET SMELL OF OIL ENTERS AIRCRAFT. SIGNS OF OIL LEAK AT NR 1 PACK ACM AND DUCTING, DEACTIVATED NR 1 PACK, DEFERRED AS PER DDPG 21-1-2A. TRANSFERRED TO DMI 008, AS PER MEL 21-1-2C, CAT D, DUE DATE 9-8-9, INSTALLED PLACARD.

Part: DOOR — DENTED (NLG) · airframe 97,797 hrs · 21,862 cycles

REPAIR DENT IN NOSE DOOR BS 190 STR 39. REMOVED DAMAGED STRINGER, RE-CONTOURED SKIN, FABBED AND INSTALLED NEW STRINGER PER B747 SRM 53-10-03 PG 8-10H AND 51-10-02 PG 6-7.

Part: WEB — CRACKED (ZONE 800) · airframe 96,612 hrs · 21,624 cycles

L-2 DOOR LOWER HINGE FWD CUT OUT WEB FOUND CRACKED. L-2 DOOR LOWER HINGE FWD CUT OUT WEB REPAIRED PER EA 52-0061.

Part: FLOOR SUPPORT — CRACKED · airframe 96,612 hrs · 21,624 cycles

BULK CARGO STA 2025 LBL25 FLOOR SUPPORT ANGLE CRACKED. FLOOR SUPPORT REMOVED. NEW SUPPORT FABRICATED. HEAT TREATED, ALODINED AND PRIMED, AREA NDTD. NO CRACKS FOUND, INSTALLED REPAIR PER SRM 51-30-02.

Part: SEAT TRACK — CRACKED (BS 520) · airframe 96,612 hrs · 21,624 cycles

MAIN DECK STATION 520, RBL11, WL 200 SEAT TRACK FOUND CRACKED. SEAT TRACK REMOVED AS PER SRM 51-30-02 CRACKED SEAT TRACK TRIMMED OUT AS PER SRM 51-10-01 NDT CHECK CARRIED OUT AS PER 51-00-00 FIG 23. NO CRACKS REMAIN, NEW SEAT TRACK SPLICE FABRICATED AND INSTALLED PER SRM 51-30-02.

Part: BATTERY PACK — NO TEST (EMERGENCY LIGHTS) · airframe 96,612 hrs · 21,624 cycles

UPPER DECK EMERGENCY LIGHT TEST FOUND DOOR EXIT SIGN INOP. REPLACED BATTERY PACK ASSY AND OPS CHECK NORMAL PER 33-51-00.

Part: FLOOR SUPPORT — CRACKED · airframe 96,612 hrs · 21,624 cycles

BULK CARGO STA 2100, BL 0 FLOOR SUPPORT FOUND CRACKED. REMOVE FLOOR SUPPORT NDTD AREA, NO CRACKS NOTED. FABRICATED NEW FLOOR SUPPORT PER BOEING DRAWING 65B06261. HEAT TREATED, ALODINED AND PRIMED, INSTALLED REPAIR PER SRM 51-30-02.

Part: SKIN — CRACKED (BS 2130) · airframe 96,612 hrs · 21,624 cycles

BULK CARGO STA 2160 STRINGER 46R SKIN ADJ AREA CRACKED. REMOVED FASTENERS, CUT SKIN FABRICATED REPAIR AND NEW SHEAR TIE, HEAT TREATED, ALODINED AND PRIMED, INSTALLED REPAIR. COI RAISED TO ACCOMPLISH REINSPECTION IAW WITH SRM.

Part: FLOORBEAM — CRACKED (BS 228) · airframe 96,612 hrs · 21,624 cycles

MAIN DECK STA 228 UPPER CHORD AT BL L11 TO R33 FOUND CRACKED, MAIN DECK BS 228 FLOORBEAM UPPER CHORD AT LBL11 TO RBL33. REPAIRED AS PER TAECO EA 53-0062.

Part: FLOOR SUPPORT — CRACKED (BS 1990-2010) · airframe 96,612 hrs · 21,624 cycles

BULK CARGO STA 2000 RBL 50 FLOOR SUPPORT CRACKED. REMOVED FASTENERS AT CRACKED FLOOR SUPPORT, STA 1990 TO STA 2010 RBL 50, AS PER SRM 51-30-02. REMOVED DAMAGE, NDT AREA, FABRICATED NEW SUPPORT PER BOEING DRAWING 65B06261, HEAT TREATED, ALODINED AND PRIMED INSTALLED NEW SUPPORT PER SRM 51-30-02.

Part: SEAT TRACK — CRACKED (BS 1900) · airframe 96,612 hrs · 21,624 cycles

AFT CARGO LT AFT FIXED STOP TIE-DOWN TRACK CRACKED STA 1900 LBL44, SEAT TRACK REMOVED. NEW SEAT TRACK FABRICATED ALODINED AND PRIMED. INSTALLED NEW SEAT TRACK PER SRM 51-30-02.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 94,834 hrs · 21,224 cycles

FOUND UPPER DECK AFT EMERGENCY LIGHT INOP. REPLACED AFT EMERGENCY LIGHT ASSY PER B747 MM 33-51-02, SYSTEM OPS CHECKED PER 33-51-00.

Part: BATTERY PACK — DISCHARGED (CABIN) · airframe 94,834 hrs · 21,224 cycles

UPPER DECK EMERGENCY LIGHT OVER DOOR SLIDE DOES NOT TEST. REPLACED BATTERY PACK PER B747 MM 33-51-04, OPS CHECKED NORMAL.

Part: WEB — CRACKED (NLG WW) · airframe 94,618 hrs · 21,174 cycles

NOSE WHEEL WELL HAS CRACK BS 270 WL 160 NWW WEB LT SIDE. REMOVED DAMAGE, NDT AREA, FABBED AND INSTALLED REPAIR PER B747 SRM 53-10-01 FIG 116 AND FIG 120.

Part: LIGHT — INOPERATIVE (R5 DOOR) · airframe 94,617 hrs · 21,174 cycles

SOLDERBURG LIGHT ASSY AT R-5 DOOR INOP. REMOVED AND REPLACED WITH SERVICEABLE UNIT PER BOEING 747 MM 33-51-07. TESTED GOOD PER BOEING 747 MM 33-51-07 PAGE 202.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 94,115 hrs · 21,062 cycles

L1 DOOR EMERGENCY SILL LIGHTS INOP (2).

Part: TIRE — FAILED (NLG) · airframe 93,830 hrs · 20,999 cycles

ON TAKEOFF, TOWER REPORTED SMOKE FROM NOSEGEAR RETURNED TO JFK. ON WALKAROUND, FOUND DAMAGE ON RT NLG TIRE (RECAP CAME OFF). ALL NOSE TIRES REPLACED IAW.

Part: BATTERY PACK — DISCHARGED (CABIN) · airframe 93,719 hrs · 20,975 cycles

UPPER DECK EMERGENCY EXIT SIGN LIGHT INOP. REMOVED AND REPLACED BATTERY PACK, OPS CHECKED GOOD PER B747 MM 33-51-00 PAGE 501.

Part: SMOKE DETECTOR — NO TEST (CABIN) · airframe 93,276 hrs · 20,885 cycles

NR 6 LOWER DECK SMOKE DETECTOR WILL NOT TEST. REPLACED DETECTOR WHEN RELAMPING DID NOT HELP. TESTED GOOD PER MM 26-16-00.

Part: SMOKE DETECTOR — INOPERATIVE (CARGO BAY) · airframe 93,261 hrs · 20,883 cycles

MAIN CARGO DECK SMOKE DETECTOR ZONE 5, ONE DETECTOR INOP.

Part: METERING VALVE — DEFECTIVE (BRAKE SYS) · airframe 93,188 hrs · 20,870 cycles

WHEN APPLYING PARKING BRAKE, PRESSURE DROPS FROM 3000 TO 1000 ON APPROX 50 SEC, T/S IN PROGRESS WITH SHUTTLE VALVE AND BREAK MODULE. REMOVED AND REPLACED PARKING BRAKE VALVE, INTERCONNECT VALVE, LEFT AND RIGHT METERING VALVES. SYSTEM LEAK AND OPS CHK NORMAL PER MM32-41-00. NORMAL OPERATION OF SYSTEM VERIFIED ON TAXI CHECK.

Part: LAMP — INOPERATIVE (SMOKE DETECTOR) · airframe 93,014 hrs · 20,831 cycles

NR 6 SMOKE DETECTOR OF AFT CARGO COMPARTMENT WILL NOT TEST. RELAMPED PER MM 26-14-00, SYS TESTS OK.

Part: BATTERY — INOPERATIVE (EMERGENCY LIGHTS) · airframe 92,784 hrs · 20,788 cycles

UPPER DECK CREW EXIT DOOR SILL LIGHTS WILL NOT TEST, LP 295539. REPLACED UPPER DECK LIGHT BATTERY CARTRIDGE IAW MM 33-51-00, OPS CHK GOOD.

Part: SKIN — DENTED (BS 510 S23L) · airframe 92,604 hrs · 20,751 cycles

ON POST - FLIGHT INSPECTION, FOUND DENT ON FUSELAGE AFT OF L1 DOOR AT STA 510, STR 23. CUT OUT DAMAGED AREA AND INSTALLED REPAIR DOUBLER IAW B747 SRM 53-30-03, FIG 1, TABLE 1. CAT "A" PERMANENT REPAIR. DENT DIMENSIONS W=0.250", H= 1.750", O= 0.168"

Part: SKIN — GOUGED (LT WING) · airframe 92,498 hrs · 20,720 cycles

LOWER SKIN OF LEFT WING STA 1241 OUTBOARD OF BUTTERFLY FITTING, SKIN GOUGED IN 4 AREAS. FABRICATED AND INSTALLED REPAIR PER B747 SRM 57-30-01 AND ECRA 470-292-2 REV A.

Part: SKIN — CORRODED (BS 830-850 S50R) · corrosion level 2 · airframe 92,498 hrs · 20,720 cycles

SKIN CORRODED AND CRACKED BETWEEN BS 830 - 850 AT STR 50R. REPLACED DAMAGED SKIN AT BS 740 TO 850 AND STR 44L AND 44R PER ECRA 470-53-284-2.

Part: SKIN — CRACKED (BS 620-647) · airframe 92,498 hrs · 20,720 cycles

SKIN CRACK ABOVE ROW OF FASTENERS ON STR 6L AT BS 630. REPAIRED CRACKED SKIN PER B747 SRM 53-30-03; REPAIRED STRINGER 6L BETWEEN BS 630-647 PER B747 SRM 53-10-03; REPAIRED SHEAR TIES BS 620-640 PER B747 SRM 53-10-04.

Part: SPAR — CORRODED (LT WING) · corrosion level 2 · airframe 92,498 hrs · 20,720 cycles

LEFT WING LEADING EDGE SPAR WEB AT LOWER CHORD ILES 1071 HAS CORROSION. REMOVED CORROSION PER B747 SRM 51-10-01 & 57-10-01. FABRICATED AND INSTALLED REPAIR PER ECRA 470-57-284-2.

Part: STRINGER — DAMAGED (BS 825 S46R) · airframe 92,498 hrs · 20,720 cycles

STR 46R, BS 825 HAS ELONGATED HOLES.

Part: STRINGER — CRACKED (BS 800-820 S45L) · airframe 92,498 hrs · 20,720 cycles

STR 45L CRACKED BETWEEN BS 800-820. REPAIRED DAMAGED SECTION PER B747 SRM 53-10-03.

Part: STRINGER — CORRODED (BS 820-840 S47R) · airframe 92,498 hrs

STR 47R AT BS 820-840 HAS CORROSION AND ELONGATED HOLES. REPAIRED PER B747 SRM 53-10-03.

Part: STRINGER — CORRODED (BS 720-800 S47L) · airframe 92,498 hrs · 20,720 cycles

STR 47L BS 720-800 CORRODED. REPLACED STRINGER FROM BS 741-800 PER B747 SRM 51-10-01 & 51-30-05.

Part: SPAR — CORRODED (RT WING) · corrosion level 2 · airframe 92,498 hrs · 20,720 cycles

RT FRONT SPAR WEB CORRODED AT THE LOWER CHORD INTERFACE, INBOARD OF NR 4 PYLON IN 5 LOCATIONS; ILES 1027, 1037, 1059, 1066 & 1092. REMOVED CORROSION PER B747 SRM 51-10-01, FABRICATED AND INSTALLED REPAIR PER ECRA 470-57-287-2.

Part: STRINGER — ELONGATED (BS 780-820 S45R) · airframe 92,498 hrs · 20,720 cycles

STR 45R HAS ELONGATED HOLES. REMOVED DAMAGED SECTION AND REPAIRED PER B747 SRM 53-10-03.

Part: SKIN PANEL — CORRODED (RT WING) · corrosion level 2 · airframe 92,498 hrs · 20,720 cycles

RT WING LOWER SKIN, PREVIOUS REPAIR, FWD CHORD, WS 1320 - 1310 HAS EXFOLIATION CORROSION, TWO LOCATIONS. REPAIRED PER ECRA 470-57-285-2 AND B747 SRM 57-30-03.

Part: SKIN PANEL — CORRODED (BS 1090) · corrosion level 2 · airframe 92,498 hrs · 20,720 cycles

CENTER TANK LOWER SKIN ABOVE NR 3 HEAT EXCHANGER HAS EXFOLIATION CORROSION. REMOVED CORROSION AND FABRICATED REPAIR PER ECRA 470-57-291-2.

Part: SKIN — CRACKED (BS 1920 S9L) · airframe 92,498 hrs · 20,720 cycles

TWO FASTENER HOLE CRACKS AT UPPER AFT CARGO DOOR CUTOUT. FABRICATED AND INSTALLED REPAIR PER ECRA 470-53-294-2.

Part: SKIN — CRACKED (BS 1780 S9L) · airframe 92,498 hrs · 20,720 cycles

FUSELAGE SKIN CRACK AT FASTENER HOLE AT FWD UPPER CORNER OF MAIN CARGO DOOR. FABRICATED AND INSTALLED REPAIR PER ECRA 470-53-295-2.

Part: SPAR — CORRODED (LT WING) · airframe 92,498 hrs · 20,720 cycles

LEFT WING LOWER FRONT SPAR WEB FOUND CORRODED BETWEEN ILES 901-1080. REMOVED CORROSION PER SRM 51-10-01 & 57-10-01 FIG 1; FABRICATED AND INSTALLED REPAIRS PER ECRA 470-57-289-2.

Part: SPAR — CORRODED (LT WING) · airframe 92,498 hrs · 20,720 cycles

LEFT WING LEADING EDGE CAVITY SPAR WEB AT LOWER CHORD HAS CORROSION FROM OFSS 1258-1274. REMOVED CORROSION PER B747 SRM 51-10-01, FABRICATED AND INSTALLED REPAIR PER ECRA 470-57-283-2.

Part: KEELBEAM — CANNING (BS 1265-1350) · airframe 92,498 hrs · 20,720 cycles

KEEL BEAM BOX STRUCTURE AT BS 1265 TO 1350 LT & RT SIDE WEBS ARE OIL CANNING. REMOVED AND REPLACED LT & RT SIDE WEBS PER ECRA 470-53-298-2 AND BOEING DRAWING 65B15069.

Part: CIRCUIT CARD — BURNED (COCKPIT LIGHTS) · airframe 92,251 hrs · 20,635 cycles

DETECTED ODOR OF SMOKE IN COCKPIT DURING FLIGHT. FOUND CIRCUIT BREAKER POPPED ON FLIGHT ENGINEERS INDICATOR LIGHTS AND CONTROL CIRCUIT. AFTER BREAKER POPPED SMELL OF HOT ELECTRICAL WIRING DISAPPEARED. FOUND CIRCUIT CARD A6 MODULE SCORCHED AND BURNT. REMOVED AND REPLACED CIRCUIT CARD A6 OF MASTER DIM AND TEST MODULE PER MM 33-11-01.

Part: CONNECTOR — DIRTY (SMOKE DETECTOR) · airframe 92,195 hrs · 20,620 cycles

FOUND MAIN DECK CARGO COMPARTMENT SMOKE DETECTOR, ZONE 5, DET A INOPERATIVE. TXFR'D TO DMI NR 869, PLACARD ID NR 060160, PER MEL 26-11 CAT C, AND ADVISED A/C MX CONTROL. DMI CONTINUES UNTIL CLEARED. 12/25/05, AMPLIFIER FOR SMOKE DETECTOR 5A PLUG CLEANED, OPS CK CW PER MM 26-14-02, OP'S CK OK, PLACARD REMOVED.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 91,867 hrs · 20,543 cycles

EMERGENCY LIGHT AT TOP OF STAIRS INOP. REPLACED EMERGENCY LIGHT AT TOP OF STAIRS IAW MM 33-51-07, OPS CHECKED GOOD.

Part: COVER — MISSING (EMERGENCY LIGHT) · airframe 91,867 hrs · 20,543 cycles

CEILING EMERGENCY LIGHT AT L5 DOOR MISSING LIGHT COVER. REPLACED LENS COVER IAW MM 33-51-07, OPS CHECKED GOOD.

Part: LIGHT — INOPERATIVE (R5 DOOR) · airframe 91,867 hrs · 20,543 cycles

R5 DOOR FWD SILL EMERGENCY LIGHT INOP. REMOVED AND REPLACED EMERGENCY LIGHT AASY AT DOOR R5 IAW 33-51-07, OPS CHECKED GOOD.

Part: LIGHT — INOPERATIVE (R5 DOOR) · airframe 91,867 hrs · 20,543 cycles

R5 FLOOD LIGHT INOP OVER DOOR EMERGENCY LIGHT. REPLACED EMERGENCY LIGHT ASSY IAE MM 33-51-07, OPS CHECKED GOOD.

Part: COVER — MISSING (CABIN) · airframe 91,602 hrs · 20,483 cycles

M/D STA 380 & 680 & R5 EMERGENCY LIGHT COVER MISSING. REPLACED COVERS PER B747 33-51-07.

Part: COVER — MISSING (CABIN) · airframe 91,602 hrs · 20,483 cycles

R5 DOOR SILL EMERGENCY LIGHT 2 EA COVERS MISSING. REPLACED 2 EA COVERS AND OPS CHECKED GOOD PER B747 MM 33-51-00.

Part: BATTERY — DISCHARGED (CABIN) · airframe 91,602 hrs · 20,483 cycles

M/D RIGHT STA 2180 1EA EMERGENCY LIGHT INOP. RECHARGED LIGHT BATTERY AND OPS CHECKED GOOD PER B747 MM 33-51-00.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 91,602 hrs · 20,483 cycles

L5 DOOR SILL EMERGENCY LIGHT INOP. REPLACED BULB AND OPS CHECKED GOOD PER B747 MM 33-51-50.

Part: BATTERY — DISCHARGED (CABIN) · airframe 91,602 hrs · 20,483 cycles

R5 DOOR EMERGENCY LIGHT INOP. RECHARGED BATTERY AND OPS CHECKED PER B747 MM 33-51-50.

Part: BULB — INOPERATIVE (EMERGENCY LIGHT) · airframe 91,095 hrs · 20,377 cycles

R5 AND L5 AND L1 DOOR EMERGENCY EXIT LIGHTS, SILL LIGHTS, AND EXIT SIGNS WILL NOT ILLUMINATE. REMOVED AND REPLACED BULBS, LIGHT ASSY'S AND POWER SUPPLY BATTERY IAW 33-51-00. OPS CK OK.

Part: STRUCTURE — CORRODED (MLG WW) · airframe 89,121 hrs · 19,948 cycles

BS 1480 MCD, CORROSION ON WHEEL WELL CHORDS AND STRIP, LBL 98-0 - LBL 57.5, AND LBL 35.0 - RBL 21.0. REMOVED DAMAGE, FABRICATED AND INSTALLED REPAIR PER ECRA 470-53-215-2PL.

Part: PRESSURE PANEL — CORRODED (FUSELAGE) · airframe 89,121 hrs · 19,948 cycles

SURFACE CORROSION ON PRESSURE WEB COMMON TO LONGITUDINAL FLOORBEAM MATING SURFACE AT BS 1480, LBL 11.33. REMOVED DAMAGE, FABRICATED AND INSTALLED REPAIR PER ECRA 470-53-215-2PL.

Part: STRUCTURE — CORRODED (MLG WW) · airframe 89,121 hrs · 19,948 cycles

BS 1480, LBL 74.92, TOP OF MLG BOX HAS CORROSION. REMOVED DAMAGE, FABRICATED AND INSTALLED REPAIR PER ECRA 470-53-215-2P-1.

Part: SKIN — CORRODED (CENTER WING) · airframe 89,121 hrs · 19,948 cycles

BS 1180 LBL 95-100 CENTER TANK UPPER SKIN HAS CORROSION. REMOVED DAMAGE, FABRICATED AND INSTALLED REPAIR PER ECRA 470-57-270-2.

Part: SKIN — CORRODED (CENTER WING) · airframe 89,121 hrs · 19,948 cycles

BS 1200, LBL 98.5, UPPER SKIN CENTER TANK HAS CORROSION. REMOVE DAMAGE, FABRICATED AND INSTALLED REPAIR PER ECRA 470-57-270-2.

Part: SKIN — CORRODED (FUSELAGE) · airframe 89,121 hrs · 19,948 cycles

SKIN AT BS 1140, LBL 98.58, LBL 110 AT BUTT JOINT OVER MID SPAR HAS CORROSION. REMOVED DAMAGE, FABRICATED AND INSTALLED REPAIR PER ECRA 470-57-269-2.

Part: BULKHEAD — CRACKED (FUSELAGE) · airframe 89,121 hrs · 19,948 cycles

BS 1241 BULKHEAD CANTED WEB, RBL 30, HAS CRACK AT LOWER CORNER OF AIR DUCT CUTOUT. REMOVED DAMAGE, FABRICATED AND INSTALLED REPAIR PER ECRA 470-53-177-2 AND B747 SRM 51-10-01.

Part: FRAME — CRACKED (FUSELAGE) · airframe 89,121 hrs · 19,948 cycles

BS 360 RT STRINGER 15-16 RT, FOUND WEB OF LOWER FRAME CRACKED. FABRICATED AND INSTALLED REPAIR PER ECRA 470-53-267-2.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 89,121 hrs · 19,948 cycles

BS 540, UPPER DECK FLOORBEAM, UPPER FORWARD SIDE OF CHORD LBL3 THRU LBL6 HAS EXFOLIATING CORROSION. REMOVED, FABRICATED, AND INSTALLED REPLACEMENT CHORD PER B747 SRM 53-30-03, FIGURE 1, ALONG WITH MM 51-30-05 AND 51-20-02.

Part: STRAP — CORRODED (FLOORBEAM) · airframe 89,121 hrs · 19,948 cycles

UPPER DECK FLOORBEAM STRAP HAS EXFOLIATION CORROSION, STA 420R, 3 INCHES IB FUSELAGE SKIN. REPLACED STRAP IAW SRM 51-30-02, PGS 8-9, 51-30-05, FIG 4, AND 51-30-02, PGS 8-9

Part: SKIN — CORRODED (CARGO DOOR) · airframe 89,121 hrs · 19,948 cycles

AFT LWR CARGO DOOR, 3RD LWR ACCESS PANEL, INNER SKIN CORRODED. REMOVED DAMAGE AND REPAIRED PER ECRA 470-52-240-2.

Part: SUPPORT BEAM — CRACKED (RT WING) · airframe 89,121 hrs · 19,948 cycles

RT WING STA 665-685, TRAILING EDGE SUPPORT BEAM, LOWER CHORD CRACKED ON FORWARD SIDE. REPAIRED RT WING TRAILING EDGE SUPPORT BEAM, LOWER CHORD BETWEEN WS 665-685, PER ECRA 470-57-227-2, REV A.

Part: WEB — CRACKED (WHEEL WELL) · airframe 89,121 hrs · 19,948 cycles

1.1 INCH CRACK ON NOSE WHEEL WELL BOX WEB, STA. 340, RBL 15, WL 150. REMOVED DAMAGED WEB, FABBED AND INSTALLED REPLACEMENT PARTS IAW ECRA 470-53-207-2

Part: FLOORBEAM — DAMAGED (FUSELAGE) · airframe 89,121 hrs · 19,948 cycles

BS 420 FLOORBEAM UPPER DECK, UPPER CHORD FWD FLANGE. HOLE AT RBL 52.0 WAS REAMED TO MAX 0.34 DIAM, WITH CRACK INDICATIONS REMAINING. MUST BE REPAIRED PER SB. REPAIR HOLE BS 420, RBL 52.0 FWD HORIZ FLANGE PER SB 747-53-2439, FIG 9, SHT 1-6

Part: STRINGER — CRACKED (FUSELAGE) · airframe 89,121 hrs · 19,948 cycles

STR 41L STA 260-280 FOUND CRACKED DURING INSULATION BUY BACK. R&R STRINGER SECTION 41L @ STA 260-280, PER B747 SRM 51-30-02, PG 2-3 & 8-9

Part: STRINGER CLIP — CRACKED (FUSELAGE) · airframe 89,121 hrs · 19,948 cycles

STRINGER 23L CRACKED AT END CAP FITTING, STA 2360 TO AFT PRESSURE BULKHEAD. REMOVED DAMAGE, FABRICATED AND INSTALLED REPAIR PER B747 SRM 52-10-03, FIG 4

Part: FITTING — DAMAGED (FUSELAGE) · airframe 89,120 hrs · 19,948 cycles

4 EA HOLES HAVE BREAKUP CONDITION ON THE CENTER OF STRINGER END FITTING NR 25 BS 1241 RT AFT SIDE. REMOVED AND INSTALLED NEW END FITTING PER B747 SRM 51-30-02 PAGES 8-9, AT BS 1241 STR 25R. FABRICATED AND INSTALLED NEW STR 25R AT BS 1241-1265 PER B747 SRM 51-30-02 PAGED 8-9. FABRICATED AND INSTALLED NEW INTERCOSTAL WEB AT BS 1241-1258 STR 25R PER B747 SRM 51-30-02 PAGES 2-3 AND B747 SRM 51-30-02 PAGES 8-9.

Part: FITTING — DAMAGED (FUSELAGE) · airframe 89,120 hrs · 19,948 cycles

4 EA HOLES HAVE BREAKUP CONDITION ON CENTER OF STRINGER END FITTING NR 23 AT THE BS 1241 AFT RT SIDE. REMOVED AND INSTALLED NEW END FITTING PER B747 SRM 51-30-02 PAGE 8-9 AT BS 1241 STR NR 23R. FABRICATED AND INSTALLED NEW STRINGER NR 23 RT STA 1241 PER B747 SRM 51-30-02 PAGES 8-9. FABRICATED AND INSTALLED NEW INTERCOSTAL WEB AT BS 1241-1258 STR, 23R PER B747 SRM 51-30-02 PAGES 2-3 AND B747 SRM 51-30-02 PAGES 8-9, REPLACED STR 23 AT BS 1241-1265 RT.

Part: FITTING — DAMAGED (FUSELAGE) · airframe 89,120 hrs · 19,948 cycles

5 EA HOLES HAVE BREAK-UP CONDITION ON CENTER OF STRINGER END FITTING NR 23 AT THE END OF BS 1241 AFT 4H SIDE. REMOVED AND INSTALLED NEW END FITTING PER B747 SRM 51-30-02 PAGES 8-9 AT BS 1241 STR 23L. FABRICATED AND INSTALLED NEW STR NR 23L AT BS 1241-1265 PER B747 SRM 51-30-02 PAGES 8-9. FABRICATED AND INSTALLED NEW INTERCOSTAL WEB AT BS 1241-1258 STR 23L PER B747 51-30-01 PAGES 2-3 AND B747 SRM 51-30-02 PAGES 8-9.

Part: STRINGER — DAMAGED (FUSELAGE) · airframe 89,120 hrs · 19,948 cycles

STA 220-240 RT, STR 14R FOUND TO BE DAMAGED UPON REMOVAL. FABRICATED NEW STRINGER AT STR 14R FROM STA 220-240 RT PER B747 SRM 51-20-01 PAGES 11, 14-21. LOCATED DRILLED STRINGER PER B747 SRM 51-30-05 PAGE 5. ALODINED AND PRIMED STR PER B747 SRM 51-10-02 PAGES 6-7, BSOPM 21-40-02 PAGES 7-9, AND INSTALLED EAC 70-213B-02-0069.

Part: FITTING — DAMAGED (FUSELAGE) · airframe 89,120 hrs · 19,948 cycles

1 EA HOLE HAS BREAKUP CONDITION ON THE STRINGER END FITTING AT BS 2141 LEFT AFT SIDE, STR 21L LOWER. REMOVED AND REPLACED END FITTING AT BS 1241 STR 21L, LOWER. REMOVED AND REPLACED STRINGER NR 21L LOWER BS 1241-1260. REMOVED AND REPLACED INTERCOSTAL WEB AT B.S 1241-60 STR 21L LOWER PER B747 SRM 51-20-01, SRM 51-30-02 PAGES 8, 9. ALODINED PER B747 SRM 51-10-02 PAGES 7-8, PRIMED PER BSOPM 20-41-02 PAGES 7-9.

Part: STRINGER — BROKEN (FUSELAGE) · airframe 89,120 hrs · 19,948 cycles

STR 38R IS BROKEN AT STA 1000 AFT AT BATH TUB FITTING. REMOVED, FABRICATED AND REPLACED STR 38R AT STA 1000 PER SRM 53-10-03, 51-10-02, 51-10-06, 51-30-02 PAGES 2A, 2B, 3, 4, 4A, BAC 149B-147 PAGES 2-3, BAC 149B-131, AND SRM 53-11-04 PAGES 14-15.

Part: SKIN — GOUGED (NR 1 PYLON) · airframe 89,120 hrs · 19,948 cycles

PYLON NR 1 I/B SURFACE EXISTING REPAIR MISSING FASTNERS AND IS GOUGED AT AFT LOWER SECTION STA 221.90. REMOVED EXISTING REPAIR DOUBLER FROM PYLON NR 1 LOWER I/B SKIN. FABRICATED AND INSTALLED NEW REPAIR PER B747 SRM 51-30-02 PAGES 8, 9, 38 AND B747 SRM 54-30-03 FIG 35.

Part: FITTING — DAMAGED (FUSELAGE) · airframe 89,120 hrs · 19,948 cycles

1 EA HOLE HAS BREAKUP CONDITION ON CENTER OF STRINGER END FITTING NR 21L AT BS 1241 AFT LT SIDE UPPER. REMOVED AND INSTALLED NEW END FITTING PER B747 51-30-02 PAGES 8-9 AT BS 1241 STR 21L. FABRICATED AND INSTALLED NEW STR NR 21L AT BS 1241-1265 PER B747 SRM 51-30-02 PAGES 8-9. FABRICATED AND INSTALLED NEW INTERCOSTAL WEB AT BS 1241-1258 STR NR 21L PER B747 SRM 51-30-02 PAGES 2-3 AND B747 SRM 51-30-02 PAGES 8-9.

Part: FITTING — CRACKED (FUSELAGE) · airframe 89,120 hrs · 19,948 cycles

1 EA HOLE HAS BREAKUP CONDITION ON THE CENTER OF STRINGER END FITTING NR 19 BS 1241 LEFT AFT SIDE. REMOVED AND INSTALLED STR END FITTING AT BS 1241 STR 19L. REMOVED AND REPLACED STR NR 19L AT BS 1241-1265. REMOVED AND REPLACED WEB AT BS 1241-1260 STR NR 19L PER SRM 51-30-02 PAGES 8-9, SRM 51-20-01 PAGES 11, 14-20 AND SRM 51-10-02 PAGES 7-8. PRIMED PER BSOPM 20-41-02 PAGES 7-9.

Part: PRESSURE PANEL — CORRODED (FUSELAGE) · airframe 89,120 hrs · 19,948 cycles

FUSELAGE INTERIOR, STA 1420, LBL 10 TO RBL 10 CORROSION ON UPPER SURFACE OF WHEEL WELL PRESSURE DECK WEB. REMOVED DAMAGED AREA. FABRICATED REPAIR FILLER AND DOUBLERS. INSTALLED REPAIR DOUBLERS AND FILLERS PER B747 SRM 53-10-07 FIG 2.

Part: STRINGER — CRACKED (FUSELAGE) · airframe 89,120 hrs · 19,948 cycles

STR 17L IS CRACKED AT STA 2340. REMOVED FASTENERS FOR ACCESS, PERFORMED HFEC ON SURFACE. CRACKED CONTAINED BY FASTENER HOLES. FABRICATED REPAIR U-CHANNEL. TREATED, PRIMED, AND INSTALLED U-CHANNEL PER B747 SRM 53-10-03 FIG 2, 51-10-01 FIG 7, BSOPM 21-41-00 PAGES 7-9 AT STR 17L STA 2340.

Part: STRINGER — CRACKED (FUSELAGE) · airframe 89,120 hrs · 19,948 cycles

STR 25L IS CRACKED AT END CAP FITTING STA 2360, AFT PRESSURE BULKHEAD. REMOVED DAMAGED AREA, FABRICATED STR FILLER AND HAT SECTION. ALODINED, PRIMED AND INSTALLED STR FILLER AND HAT SECTION PER B747 SRM 53-10-03 FIG 4. REMOVED AND REINSTALLED FOR ACCESS END CAP FITTING PER B747 SRM 51-30-02 PAGES 12-15 AT BS 2360 STR 25L.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 89,120 hrs · 19,948 cycles

MAIN DECK FLOORBEAM (UPPER CHORD) AT STA 1720, BETWEEN RBL 11.33 AND RBL 33.99 CHORD IS CORRODED AND HAS AN OVERSIZE HOLE IN THE AFT FLANGE (APPROX 348 INCH) AND ONE OVERSIZED HOLE IN THE FORWARD FLANGE (APPROX 258 INCH). REMOVED DAMAGED FLOORBEAM CHORD AND REPLACED WITH NEW SECTION AT STA 1720 RBL 11.33 - 33.999 PER B747 SRM 53-10-07 PAGES 51-54 FIG 12, SHEET 1-4.

Part: FRAME — DAMAGED (FUSELAGE) · airframe 89,120 hrs · 19,948 cycles

STA 300 LOWER LOBE FRAME, 3 EXTRA HOLES WERE DRILLED AND PLUGGED INTO THE 141U1021-21 DOUBLER AND 1 OF THE EXTRA HOLES IS COMMON TO THE 141U1021-9 FRAME AT THE STR 27A 4H CLIP LOCATION. LOCATED AND DRILLED NEW -9 FRAME, DISCREPENT HOLES NOT DRILLED IN NEW FRAME. FRAME PER SERVICE BULLETIN 747-53-2272 REV 18 AND DRAWING 624110003 SH 3A, 4D.

Part: STRINGER — CRACKED (FUSELAGE) · airframe 89,120 hrs · 19,948 cycles

STR 24R IS CRACKED AT END CAP FITTING, STA 2360 TO AFT PRESSURE BULKHEAD. REMOVED DAMAGED AREA, FABRICATED STR FILLER AND HAT SECTION. ALODINED, PRIMED AND INSTALLED HAT SECTION AND STR FILLER PER B747 SRM 53-10-03 FIG 4 PAGES 12-13. REMOVED AND REINSTALLED FOR ACCESS END CAP FITTING PER B747 SRM 51-30-01 PAGES 12-15 AT BS 2360 STR 24R.

Part: STRINGER — CRACKED (FUSELAGE) · airframe 89,120 hrs · 19,948 cycles

STR 24L IS CRACKED AT END CAP FITTING, STA 2360 TO AFT PRESSURE BULKHEAD. REMOVED DAMAGED AREA, FABRICATED STR FILLER AND HAT SECTION, ALODINED, PRIMED AND INSTALLED STR FILLER AND HAD SECTION PER BOEING 747 SRM 51-10-03 FIG 4. REMOVED AND REINSTALLED FOR ACCESS END CAP FITTING PER 747 SRM 51-30-02 PAGES 12-15.

Part: STRINGER — DAMAGED (FUSELAGE) · airframe 89,120 hrs · 19,948 cycles

MAIN DECK STA 160 FRAME STRINGER 6L HAS 1 EA EXISTING ELONGATED HOLE AT STRINGER CLIP LOCATION (APPROX ELONG DIAMETER .350 INCH) STR 6L P/N 65B 14211-13. REMOVED AND REPLACED STR 6L AT STA 140 TO STA 200 PER B747 SRM 51-30-02 PAGES 2,3,5; FIG 7 PAGE 32.

Part: STRINGER — CRACKED (FUSELAGE) · airframe 89,120 hrs · 19,948 cycles

STR 25R IS CRACKED AT END CAP FITTING STA 2360 TO AFT PRESSURE BULKHEAD. REMOVED DAMAGED AREA, FABRICATED STR FILLER AND HAT SECTION. ALODINED, PRIMED AND INSTALLED STR FILLER AND HAT SECTION PER B747 SRM 53-10-03 FIG 1 PAGES 2A-4. REMOVED AND REINSTALLED OR ACCESS END CAP FITTING PER B747 SRM 51-30-02 PAGES 12-15 AT BS 2360 STR 25R.

Part: STRINGER — CRACKED (FUSELAGE) · airframe 89,120 hrs · 19,948 cycles

STR 23R IS CRACKED AT END CAP FITTING, STA 2360 TO AFT PRESSURE BULKHEAD. REMOVED DAMAGED AREA, FABRICATED STR FILLER AND HAT SECTION. ALODINED, PRIMED AND INSTALLED STR FILLER AND HAT SECTION PER B747 SRM 53-10-03 FIG 4. REMOVED AND REINSTALLED END CAP FITTING PER B747 SRM 51-30-02 PAGES 12-15. REMOVED FOR ACCESS SHEAR TIES AND PREPARED PER B747 SRM 53-10-04 FIG 4.

Part: SPLICE — CRACKED (FUSELAGE) · airframe 89,121 hrs · 19,448 cycles

STA 520, STR 12R, STRINGER SPLICE FOUND CRACKED ON REMOVAL. REMOVED CRACKED SPLICE, LOCATED, DRILLED AND INSTALLED NEW SPLICE IAW SRM 51-30-02, PGS 2-3 AND 8-9.

Part: STRINGER — DAMAGED (FUSELAGE) · airframe 89,121 hrs · 19,448 cycles

STR 24A BETWEEN BS 300-320 HAS ELONGATED FASTENER HOLES. REMOVE DAMAGE, FAB AND INSTALLED NEW STRINGER PER B747 SRM 51-30-02, 51-20-01, AND 51-30-02.

Part: STRINGER — CRACKED (FUSELAGE) · airframe 89,121 hrs · 19,448 cycles

STR 27A R FROM BS 320-340 HAS SEVERAL FASTENER HOLES CRACKED. REMOVE DAMAGE, FAB & INSTL NEW STRINGER PER SRM 51-20-01 & 51-30-02.

Part: FLOORBEAM — DAMAGED (FUSLEAGE) · airframe 89,121 hrs · 19,448 cycles

FLOORBEAM MAIN CABIN BS 1740 RBL 33-99 HAS 4 ELONGATED HOLES COMMON TO SEAT TRACK. REMOVE DAMAGED SECTION OF TEE CHORD BEAM BS 1740 RBL 33.99 & REPLACE WITH NEW SECTION PER B747 SRM 53-10-07 & 51-30-02

Part: PRESSURE PANEL — DELAMINATED (FUSELAGE) · airframe 89,121 hrs · 19,948 cycles

MAIN CABIN STA 1380, RBL 75.9, PRESSURE DECK WEB SHOWS EVIDENCE OF DELAMINATION. REMOVED DAMAGE, FABBED AND INSTALLED REPAIR IAW SRM 51-10-07, FIG 251-30-05 PGS 6-9, AND 51-30-02.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 89,121 hrs · 19,448 cycles

WEB BETWEEN FLOORBEAM STA 320-330, STR 12L IS CRACKED. REMOVED DAMAGED WEB, FAB & INSTL PER B747 SRM 51-30-02, 51-10-02, 51-20-01, & SOPM 20-41-02

Part: STRINGER — CRACKED (FUSELAGE) · airframe 89,121 hrs · 19,448 cycles

STR 31A CRACKED AT FS 500L. FAB & INSTL NEW STR & SPLICE CHANNELS PER B747 SRM 53-10-03, SHTS 6&7, 51-30-02, PGS 2-3 & 8-9.

Part: SKIN — CORRODED (FUSELAGE) · airframe 89,121 hrs · 19,948 cycles

STR 43L FUS STA 1900, EXISTING REPAIR CORRODED, SKIN OUTBD AND FWD OF REPAIR CORRODED AND BULGING. REPAIRED CORRODED AND BULGING SKIN. REMOVED AND REPLACED CORRODED DOUBLER, PER B747 SRM 53-30-03, FIG 36, PAGES 99-100B, AT FS 1820 STR 48L.

Part: PRESSURE PANEL — CORRODED (FUSELAGE) · airframe 89,121 hrs · 19,948 cycles

MAIN CABIN STA 1460, RBL 120 HAS SURFACE CORROSION AT UPPER MAIN WHEEL WELL PRESS WEB. REMOVED DAMAGE, FABRICATED AND INSTALLED REPAIR PER B747 SRM 53-10-07, FIG 2, PGS 4-10.

Part: SKIN — CORRODED (FUSELAGE) · airframe 89,121 hrs · 19,948 cycles

CORROSION, FS 1960 STR 46R-46L. REMOVED EXTERNAL SKIN DOUBLER, INTERNAL SKIN BONDED DOUBLER AND EXISTING STRUCTURES, INCLUDING SHEAR AND STRINGER TIES, STRINGER SPLICE AT BS 1960 FROM STR 46R-50R. NO CORROSION FOUND ON INTERNAL AND EXTERNAL SKIN FROM STR 46L-46R AT BS 1960. REINSTALLED EXTERNAL SKIN DOUBLER AND EXISTING STRUCTURES PER B-747 SRM 51-30-02, PG 8-9, AND REINSTALLED INTERNAL BONDED SKIN DOUBLER PER B747 SRM 53-30-03, FIG 38.

Part: PRESSURE PANEL — CRACKED (NLG WW) · airframe 89,121 hrs · 19,448 cycles

NOSE WHEEL WELL SIDEWALL, LT SIDE HAS 6 INCH CRACK BETWEEN BS 264.5 AND 270.5, WL 154. REMOVED DAMAGE, FABRICATED FILLERS AND DOUBLERS. INSTALLED PARTS PER B747 RM 53-10-04, FIG 116.

Part: STRINGER — CRACKED (FUSELAGE)

STRINGER 37R AT STA 300R CRACKED AT FASTENER HOLE FOR STRINGER CLIP. REMOVED AND REPLACED DAMAGED STRINGER SECTION PER B747 SRM 51-30-02, PG 32, 51-30-05, PG 5-6, 51-30-02 PG 2-3, AND 51-20-01,PG 11 AND 14-20.

Part: STRINGER — CRACKED (FUSELAGE) · airframe 89,121 hrs · 19,448 cycles

STR 28A CRACKED AT BS 500 L. FABRICATED INSTALLED NEW STRINGER SECTION PER B747 SRM 51-30-05, 51-10-02, 51-30-02, AND SOPM 20-41-02.

Part: STRUCTURE — CRACKED (FUSELAGE) · airframe 89,121 hrs · 19,948 cycles

CRACK IN OUTER RING CHORD, STA 140R AT STR 22. STOP DRILL CRACK AT STA 140R, STR 22. NDT VERIFIED NO CRACK CONDITION REMAINED. ALODINED & PRIMED. REPAIRED PER EO 53-747-1730-04 REV A & SB 747-53-2355 FIG 5, PG 52, & 70-2138-05-0715

Part: FRAME — CRACKED (FUSELAGE) · airframe 89,121 hrs · 19,448 cycles

CRACK IN OUTER RING CHORD, STA 140R AT STR 20. STOP DRILL CRACK STA 140R AT STR 20. NDT VERIFIED NO CRACK CONDITION REMAINING, ALODINED AND PRIMED. REPAIRED PER EO53-747-1730-04 REV A, AND SB 747-53-2355, FIG 5, PG 52 AND 70-2138-05-0715.

Part: SKIN — CRACKED (FUSELAGE) · airframe 89,121 hrs · 19,948 cycles

SKIN CRACKS AT BS 335-345, STR 3AL AND 9L. REMOVE DAMAGE, FAB AND INSTALLED REPAIR PER ECRA 470-53-165-2.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 89,121 hrs · 19,448 cycles

UPPER FLOORBEAM, CORROSION AT STA 720 RBL 84.0 WL 199 UNDER FLOOR BOARD. REMOVED FLOORBEAM AT STA 720 LBL TO RBL 15, PER B747 SRM 53-10-07.

Part: ACM — LEAKING · airframe 658,237 hrs · 19,303 cycles

DURING DESCENT UPPER DECK FILLED WITH LIGHT SMOKE WHEN NR 1 AC PACK SHUTDOWN, SMOKE CLEARED COMPLETELY.

Part: WEB — CORRODED (FUSELAGE) · airframe 84,303 hrs · 18,910 cycles

CORROSION WAS FOUND ON THE WING CENTER SECTION CANTED WEB AT RBL 65. THE CORROSION WAS REMOVED BY TRIMMING AWAY THE DAMAGED SECTION OF WEB. THE WEB WAS REPAIRED BY INSTALLING REPAIR DOUBLER PER EIA ECRA 470-53-129-2.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 84,303 hrs · 18,910 cycles

CORROSION WAS FOUND ON THE BS 400 FLOORBEAM UPPER FORWARD CHORD AT RBL 35. ALSO AN EXISTING REPAIR WAS FOUND COMMON TO THE FORWARD UPPER CHORD AT RBL 40. THE CORROSION WAS REMOVED BY TRIMMING AWAY THE HORIZONTAL FLANGE OF THE CHORD. THE EXISTING REPAIR WAS REMOVED FROM THE AIRCRAFT. THE FORWARD UPPER CHORD WAS REPAIRED BY CUTTING THE CHORD AT RBL 60 TO LBL 60 AND SPLICING IN A NEW SECTION OF CHORD PER EIA ECRA 470-53-134-2.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 84,303 hrs · 18,910 cycles

A DAMAGED SKIN REPAIR WAS FOUND COMMON TO THE FUSELAGE SKIN AT BS 1760, STR 33R. THE DAMAGED SKIN WAS REMOVED AND AN EXISTING BLEND WAS FOUND COMMON TO THE 1760 CHORD. THE DAMAGED SKIN REPAIR WAS REMOVED AND THE SUBJECT SKIN PANEL WAS REPAIRED. A REPLACEMENT SECTION OF SKIN AND BONDED DOUBLER WAS SPLICED IN WITH REPAIR DOUBLERS.

Part: SPAR — CRACKED (RT WING) · airframe 84,303 hrs · 18,910 cycles

A CRACK WAS FOUND COMMON TO THE UPPER CHORD OF THE RIGHT WING TRAILING EDGE AUXILIARY SPAR AT WBL 425. THIS DISCREPANCY WAS REPAIRED BY REMOVING THE DAMAGED SECTION OF CHORD AND SPLICING IN A NEW SECTION OF CHORD WITH REPAIR ANGLES PER EIA ECRA 470-57-141-02.

Part: FLAP TRACK — DAMAGED (T/E FLAP) · airframe 84,303 hrs · 18,910 cycles

CORROSION AND THREAD DAMAGE WERE FOUND COMMON TO FORWARD BOLT HOLE LOCATIONS (4 EA INBOARD AND OUTBOARD SIDES) OF NR 4 TRAILING EDGE FLAP TRACK. THREAD DAMAGE WAS COMMON TO THE FAIL-SAFE BAR OUTBOARD HOLE NR 3. THE CORROSION AND THREAD DAMAGE WERE REMOVED AND THE BOLT HOLES WERE REWORKED PER BOEING SERVICE BULLETIN 747-57-2256 AND EIA ECRA 470-57-125-2.

Part: STRINGER — GOUGED (T/E FLAP) · airframe 84,303 hrs · 18,910 cycles

FOUR GOUGES WERE FOUND COMMON TO THE PRODUCTION STRINGER ON VARIABLE CAMBER FLAP NR 21 ON THE RIGHT WING. THIS DISCREPANCY WAS CORRECTED BY TRIMMING OUT THE DAMAGED AREAS AND INSTALLING AN ANGLE DOUBLER PER EIA ECRA 470-57-150-2.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 84,303 hrs · 18,910 cycles

A GOUGE WAS FOUND NEAR THE EDGE OF THE FUSELAGE SKIN AT BS 670 BELOW STR 38R AT THE AFT EDGE OF THE FORWARD CARGO DOOR CUTOUT. THE SKIN IS AN ASSEMBLY CONSISTING OF THE SKIN AND A DOUBLER. THE DAMAGE IS CONFINED TO THE SKIN ONLY. THE DAMAGE WAS TRIMMED OUT, A HFEC INSPECTION PERFORMED, AN EXTERNAL DOUBLER INSTALLED PER EIA ECRA 470-53-120-2.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 84,303 hrs · 18,910 cycles

DAMAGE WAS FOUND IN THE FUSELAGE SKIN AT THE FORWARD EDGE OF THE BULK CARGO DOOR CUTOUT AT STA 1983, STR 36R TO STR 39R. THE SKIN IS IN FACT AN ASSEMBLY CONSISTING OF SKIN/DOUBLER/TRIPLER WHICH WERE DAMAGED AND A QUADRUPLER WHICH WAS NOT. THE DAMAGED SECTION WAS REMOVED AND EXTERNAL DOUBLERS INSTALLED.

Part: FITTING — CRACKED (FUSELAGE) · airframe 84,303 hrs · 18,910 cycles

THE BS 1480 FLOOR SUPPORT FITTING FLANGE WAS FOUND CRACKED COMMON TO THE DIAGONAL BRACE. THE FITTING WAS REPAIRED BY MACHINING THE CRACKED FLANGE PER BOEING SRM GUIDELINES, DYE PENETRANT INSPECTING THE MACHINED FLANGE AND MACHING AND INSTALLING A NEW FLANGE PER EIA ECRA 470-53-149-2.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 84,303 hrs · 18,910 cycles

CORROSION WAS FOUND ON THE BS 380 FLOORBEAM UPPER CHORD LBL 9 TO LBL 28. THE FLOORBEAM WAS REPAIRED BY REMOVING THE DAMAGED SECTION OF UPPER CHORD AND SPLICING IN A NEW SECTION BETWEEN LBL 28 AND LBL 9.2 PER BOEING DRAWING 14100044 SHEET 4 AND ECRA 470-53-133-2.

Part: FITTING — CRACKED (RT WING)

PAE - FOUND RIGHT WING LANDING GEAR SUPPORT BEAM END FITTING HAD A CRACK INDICATION ADJACENT TO LUG BUSHING. CORRODED NOTED UPON REMOVAL. REMOVED AND REPLACED FITTING. (M)

Part: FITTING — CRACKED (LT WING)

PAE - LEFT WING LANDING GEAR SUPPORT BEAM END FITTING HAD A CRACK INDICATION ADJACENT TO LUG BUSHING. CORROSION NOTED UPON REMOVAL. REMOVED AND REPLACED FITTING. (M)

Part: SKIN — CRACKED (FUSELAGE)

PAE - FOUND INSPECTION OF FUSELAGE SKIN EXTERNAL, DETECTED A CRACK IN THE SKIN. SKIN WAS ALSO PILLOWED. INTERNAL INSPECTION REVEALED INNER SKIN EXFOLIATION. PERFORMED MAJOR REPAIR ON EXTERNAL FUSELAGE SKIN AT BS 800 STRINGER 46R IAW GOODRICH ENGINEERING REPAIR NR 01-5402. (M)

Part: SKIN — CRACKED (FUSELAGE)

PAE - FOUND INSPECTION OF FUSELAGE SKIN EXTERNAL, DETECTED A CRACK IN THE SKIN. SKIN WAS ALSO PILLOWED. INTERNAL INSPECTION REVEALED INNER SKIN EXFOLIATION. PERFORMED MAJOR REPAIR ON EXTERNAL FUSELAGE SKIN AT BS 800 STRINGER 46R. (M)

Part: SMOKE DETECTOR — MALFUNCTIONED (CABIN)

KJFK - ALL MAIN DECK SMOKE DETECTOR LIGHT ILLUMINATED INTERMITTENTLY. NO SMOKE DETECTED IN AIRCRAFT. REPLACED MAIN DECK SMOKE DETECTOR MODULE. (M)

Part: BULKHEAD — CRACKED (ENGINE BAY)

HKG-HAECO - FOUND 4 CRACKS AT NR 2 ENGINE STRUT REAR ENGINE MOUNT BULKHEAD WEB, FROM FRAME WEB ADJACENT TO REPAIR ANGLE, 1 AT FORWARD SIDE AND 3 AT AFT SIDE. REPAIRED BULKHEAD WEB PER RS R-54-53-34641. CONTINUE DETAIL VISUAL AND HFEC INSPECTION OF B/H IAW SB 747-54A2202. (M)

Part: BULKHEAD — CRACKED (NR 3 NACELLE)

HKG-HAECO - NR 3 STRUT REAR ENGINE MOUNT BULKHEAD AFT SIDE OF FRAME WEB CRACKED AT OUTBOARD LOWER AREA ADJACENT TO REPAIR ANGLE, APPROX .375 INCH LENGTH. STOP DRILLED HOE PER SRM 51-10-01. INSPECT STOP DRILLED HOLE BY HFEC EVERY 600 FLT CYCLES PER SB 747-54A2202. (M)

Part: ANGLE — CRACKED (NR 3 NACELLE)

FOUND NR 3 PYLON REAR ENGINE MOUNT BULKHEAD LEFT TOP LONGERON, REPAIR ANGLE ON FRAME TOP END CRACKED. NDT INSPECTED AREA, DEFECTIVE BRACKET REPLACED PER SRM 51-10-01. (M)

Part: SHEAR TIE — CRACKED (FUSELAGE)

HKG-HAECO - FOUND THREE VERTICAL BEAM ATTACH SHEAR TIE CLIPS CRACKED, FUSELAGE RIGHT NOSE GEAR TUNNEL SIDEWALL. REPLACED DEFECTIVE SHEAR TIE CLIPS PER SRM 51-10-01. (M)

Part: BULKHEAD — CRACKED (NR 4 NACELLE)

HKG-HAECO - NR 4 STRUT REAR ENGINE MOUNT BULKHEAD FORWARD SIDE OF FRAME WEB CRACKED AT OUTBOARD LOWER AREA, ADJACENT TO REPAIR ANGLE, APPROX .375 INCH LENGTH. REPAIRED BULKHEAD WEB PER RS R-54-53-34641. CONTINUE DETAIL VISUAL AND HFEC INSPECTION PER SB 747-54A2202. (M)

Part: SPAR — CRACKED (RT WING)

HKG-HAECO - FOUND RT WING REAR SPAR WEB, WBL 445 WEB OUTBOARD VERTICAL CHANNEL CRACKED. REPLACED VERTICAL STIFFENER PER SRM 51-10-01. (M)

Part: HOUSING — CRACKED (NR 2 CSD)

RJCC - NR 2 ENGINE INDICATED OIL QTY LEAK OF APPROX 1 HAL/HR DIVERTED TO RJCC. OIL QTY DROPPED BELOW ZERO, IFSD NR 2 ENGINE. PERFORMED WINDMILL INSPECTION, NO DEFECTS. FOUND NR 2 CSD FILTER HOUSING CRACKED AND HEAT DAMAGED. REPLACED CSD AND GARLOCK SEAL. LEAK AND OP CHECKS NORMAL. (M)

Part: GARLOCK SEAL — DAMAGED (NR 2 ENGINE)

RJCC - NR 2 ENGINE INDICATED OIL QTY LEAK OF APPROX 1 HAL/HR DIVERTED TO RJCC. OIL QTY DROPPED BELOW ZERO, IFSD NR 2 ENGINE. PERFORMED WINDMILL INSPECTION, NO DEFECTS. FOUND NR 2 CSD FILTER HOUSING CRACKED AND HEAT DAMAGED. REPLACED CSD AND GARLOCK SEAL. LEAK AND OP CHECKS NORMAL. REF EIA2001012. (M)

Part: FITTING — CRACKED (FOREFLAP)

SIN-SASCO - FOUND RIGHT WING INBOARD FOREFLAP CENTER TRACK ATTACH FITTING CRACKED. NEW FITTING INSTALLED AS PER SRM 51-30-02 AND RIGHT WING INBOARD FOREFLAP REINSTALLED PER MM 27-51-02. (M)

Part: SMOKE — DETECTED (COCKPIT CONSOLE)

AT FL340, EXPERIENCED SMOKE IN THE COCKPIT COMING FROM AFT END OF CENTER CONSOLE. ACCOMPLISHED FIRE/SMOKE PROCEDURES AND RETURNED TO HNL. (M)

Part: SWITCH — OVERHEATED (COCKPIT)

KHNL - AT FL 340, EXPERIENCED SMOKE IN THE COCKPIT COMING FROM AFT END OF CENTER CONSOLE. ACCOMPLISHED FIRE/SMOKE PROCEDURES AND RETURNED TO HNL. FOUND DIMMER IN CENTER PEDISTAL (LOWER) OVERHEATED CAUSING SMOKE. REPLACED LOWER DIMMER WITH IMPROVED DIMMER P/N 2-459-04/05. NO FURTHER SMOKE OR OVERHEATING FOUND REF EO 33-747-1607-00. (M)

Part: PRESSURE SWITCH — MALFUNCTIONED (EXTIGUISHING SYS)

VHHH - APU FIRE BOTTLE DISCHARGE LIGHT ILLUMINATES INTERMITTENTLY THROUGHOUT FLIGHT. APU FIRE SWITCH IN. INSPECTED SYSTEM, CLEANED, AND RESECURED APU FIRE EXT BOTTLE PRESS SWITCH. GROUND TEST AND OPS CHECK NORMAL. (M)

Part: SKIN — DELAMINATED (TE FLAP)

HNL - ON MAINTENANCE WALKAROUND, FOUND RIGHT OUTBOARD LOWER TRAILING EDGE FLAP DELAMINATED AT INBOARD CORNER. REMOVED RIGHT OUTBOARD LOWER TRAILING EDGE FLAP FOR REPAIR. ACCOMPLISHED REPAIR PER SRM 51-40-09 AND 51-40-12. INSTALLED RIGHT OUTBOARD LOWER TRAILING EDGE FLAP PER MM 27-51-06. FLAP OPERATIONAL CHECK NORMAL. RII ACCOMPLISHED. (M)

Part: SMOKE DETECTOR — MALFUNCTIONED (CARGO BAY)

MAD - FLT 708 - ON DESCENT, FORWARD CARGO FIRE WARNING LIGHT ILLUMINATED. DISCHARGED BTL, NR 1 AND BTL NR 2. VERIFIED NO FIRE OR SMOKE. INSPECTED FORWARD CARGO COMPARTMENT, NO ABNORMALITIES FOUND. CLEANED NR 1 AND NR 2 FORWARD CARGO SMOKE DETECTORS. OPS CHECK NORMAL PER MM 26-16-00. REPLACED UPPER AND LOWER FIRE BOTTLES AND PRESS SWITCHES PER MM 26-23-0. RII ACCOMPLISHED. (M)

Part: MOUNT — DAMAGED (LT WING STRUT)

LEFT WING LG INBOARD STRUT MOUNTED DOOR HAS 2 INCH BY 3 INCH DELAMINATION AT LE OF DOOR. REPAIRED PER ECRA 470-52-112-1, PART 1. (M)

Part: SKIN — CRACKED (LT WING LE)

KHKG - FLT EIA 328 - ON WAC, FOUND 1 INCH CRACK ON OUTBOARD LEFT WING LE APPROXIMATELY WS 1510.0. INSTALLED TEMPORARY REPAIR PER SRM 57-30-04. SUBMITTER STATED PERMANENT FLUSH REPAIR MUST BE INSTALLED WITHIN 6 MONTHS. (X)

Part: PLATE — CRACKED (NR 3 PYLON)

KJFK - FLT EIA 328 - ON POST-FLIGHT WALKAROUND, FOUND 5.75 INCHES VERTICAL CRACK ON NR 3 PYLON, INBOARD SIDE BELOW PYLON VLV PLATE. REMOVED AND REPLACED NR 3 ENGINE TO FACILITATE PYLON REPAIR. STOP DRILLED CRACK, FABRICATED DOUBLER. REPAIRED AND INSTALLED PER SRM 53-30-03, FIG 17. (X)

Part: BLADE — BIRD STRIKE (NR 2 ENGINE)

JFK - ON TAKEOFF ROLL, NR 2 ENGINE INGESTED SEVERAL BIRDS. EGT TO 1232 FOR 76 SECONDS, CAT D O/H EXCEEDANCE. POST FLIGHT INSPECTION INDICATED DAMAGE TO NR 2 CANOE, LEFT OUTBOARD FORE FLAP, LEFT MID FLAP, BENT FAN BLADES. (M)

Part: ENGINE — OVERTEMP (NR 1)

ANC - NR 1 ENGINE EGT CAT D EXCEEDANCE ON TAKEOFF MAX POWER. PERFORMED NR 1 ENGINE BORESCOPE INSPECTION OF COMBUSTION SECTION, AND HI/LOW PRESSURE TURBINE, FOUND OK. PERFORMED TANDEM BLEED CHECK, OK. PERFORMED EVC TRIM CHECK FOR FLYBACK, OK. ENGINE CHANGE SCHEDULED WITHIN 80 FLT HOURS DUE TO CAT D OVERHEAT EXCEEDANCE 5-31-00. NR 1 ENGINE CHANGE ACCOMPLISHED. (M)

Part: FRAME — CRACKED (FUSELAGE)

AFT OF BULK CARGO COMPT BS 2220 BOTTOM STRINGER 37R AND STRINGER 38R BODY FRAME CRACKED. TRIMMED OFF CRACK, NDT INSPECTED AND FRAME REPAIRED PER SRM 53-10-04. (M)

Part: WEB — CRACKED (NOSE WW)

CRACKED REVEALED ON LEFT NOSE W/W TOP PANEL WEB AT LBL 21 AND BS 290 APPROX .375 INCH LONG. STOP DRILLED, NDT INSPECTED, AND REPAIRED PER BOEING MSG EVR-HKG-00-00107F/00094H AND RS R-53-18-34385. (M)

Part: FLOORBEAM — CORRODED (FUSELAGE)

C2-CHECK, FOUND FLOORBEAM CORRODED AT BS 600 LBL 55-70. CORROSION REMOVED AND FLOORBEAM REPAIRED PER SRM 51-40-04 FIG 3. (M)

Part: TIE CLIP — CRACKED (FUSELAGE)

C-2 CHECK, FOUND BS 400 STRINGER 8L FRAME ATTACH SHEAR TIE CLIP CRACKED. SHEAR TIE CLIP REPLACED PER SRM 51-10-01, SRM 51-30-02, AND SRWS 917268. (M)

Part: SKIN — CORRODED (RT WING)

C2-CHECK, FOUND BS 1050 RBL 112 WL 192 WING CENTER SECTION UPPER SKIN CORRODED. BLENDED OUT, SHOT-PEENED, AND OVERSIZE FASTENER INSTALLED PER BOEING MSG EVR-HKG-00-00105H/00089F AND RS R57-14-34381. (M)

Part: BEAM — CORRODED (ACCESS PANEL)

C2-CHECK, FOUND BS 1170 LBL 57 - RBL 17 LATERAL AIR COND BAY ACCESS PANEL SUPPORT BEAM CORROSION APPROX 1 INCH BY 5 INCH. REPAIRED SUPPORT BEAM PER SRM 51-40-04 FIG 1. (M)

Part: SUPPORT BRACKET — CORRODED (FUSELAGE)

FOUND STATION 1329 KEEL BEAM PNL SUPPORT CORROSION AT LBL 12 TO RBL 12. REPLACED KEEL BEAM BS 1329 LOWER PNL SUPPORT PER SRM 51-10-01 PAGE 18. (M)

Part: SHEAR TIE — CRACKED (FUSELAGE)

C-2 CHECK, FOUND BS 390 STRINGER 1L FRAME ATTACH SHEAR TIE CRACKED. SHEAR TIE CLIP REPLACED PER SRM 51-10-01, SRM 51-30-02, AND SRWS 917181. (M)

Part: STRINGER — CRACKED (FUSELAGE)

FOUND STRINGER 47L CORROSION AND CRACK AT STATION 840. STRINGER TRIMMED OFF, NDT INSPECTED, AND STRINGER REPAIRED PER SRM 53-10-03. (M)

Part: SEAT TRACK — CORRODED (CABIN)

C2-CHECK, FOUND BS 1416 RBL 98 SEAT TRACK INBOARD FLANGE CORROSION. BS 1265-1480 RBL 98 SEAT TRACK REPLACED PER SRM 51-10-01 PAGE 18. (M)

Part: SUPPORT BRACKET — CORRODED (FUSELAGE)

BS 1391 RBL 9 TO LBL 9 KEEL BEAM PANEL SUPPORT CORROSION. REPAIRED KEEL BEAM PANEL SUPPORT PER SRM 51-40-03 FIG 3. (M)

Part: WEB — CRACKED (FUSELAGE)

C2-CHECK, BS 440 LBL 100 FLOOR WEB CRACKED. TRIMMED OFF, NDT INSPECTED AND WEB REPAIRED PER SRM 51-40-02 AND SRWS 917263. (M)

Part: WEB — DAMAGED (AFT CARGO BAY)

C2-CHECK, AFT CARGO COMPARTMENT BS 1680 LBL 60 FLOORBEAM WEB FOUND PUNCH HOLE. TRIMMED OFF, NDT INSPECTED AND REPAIRED PER SRM 51-40-02. (M)

Part: SKIN — CORRODED (FUSELAGE)

FOUND BS 2484 SKIN CORRODED AT STRINGERS 24R-38R. BS 2480 SKIN AT STRINGERS 24R-38R BLEND OUT PER SRM 53-30-01 AND REPAIRED PER SRM 53-30-03. (M)

Part: FITTING — CORRODED (FUSELAGE)

FOUND BS 480 RBL 43 FLOORBEAM ATTACH TIE DOWN SUPPORT CORRODED. REPLACED TIE DOWN FITTING PER SRM 51-10-01 PAGE 18. (M)

Part: WEB — CRACKED (NOSE WW)

C2-CHECK, NOSE W/W SIDEWALL, BS 300, WL 175LH VERTICAL BEAM WEB FOUND CRACKED AROUND INSULATION STANDOFF HOLE. WEB CRACK TRIMMED OFF, NDT INSPECTED AND REPAIRED PER SRM 51-40-02. (M)

Part: TIE CLIP — CRACKED (FUSELAGE)

C2-CHECK, FOUND BS 380 STRINGERS 6L TO 9L FRAME ATTACH SHEAR TIE CLIPS CRACKED. SHEAR TIE CLIPS REPLACED PER SRM 51-10-01, SRM 51-30-02, AND SRWS 917265. (M)

Part: WEB — CRACKED (NOSE WW)

NOSE W/W STRUCTURE BS 320 L/R TUNNEL AREA FRAME WEB CRACKED AT RADIUS BETWEEN STRINGER 39 AND STRINGER 42. STOP DRILLED, TRIMMED OFF CRCKED FLANGE, NDT INSPECTED AND REPAIRED FRAME WEB PER BOEING MSG EVR-HKG-00-00123H/00108F AND RS R53-18-34388. (M)

Part: DOOR FRAME — CRACKED (FUSELAGE)

FOUND L1 DOOR AFT CUTOUT BS 488 FRAME INNER CHORD FASTENER HOLE CRACKED AT NR 1 STOP FITTING. TRIMMED OFF INNER CHORD AND NDT INSPECTED. STRAP REPAIRED PER BOEING MSG EVR-HKG-00-00086H/-00074F AND RS R53-12-34364. INNER CHORD TO BE REPLACED IAW SB747-53-2272/AD90-06-06 AT OR PRIOR TO 20,000 CYCLES. (M)

Part: SEAT TRACK — CRACKED (CABIN)

FOUND BS 2157 RBL 11 INBOARD SEAT TRACK FLANGE CRACKED. REPAIRED SEAT TRACK PER SRM 53-10-05 FIG 16. (M)

Part: SKIN — CORRODED (RT WING)

C2-CHECK, FOUND BS 1140 RBL 30 WL 184 WING CENTER SECTION UPPER SKIN CORRODED. BLENDED OUT, SHOT-PEENED AND OVERSIZE FASTENER INSTALLED PER BOEING MSG EVR-HKG-00-00105H/00089F AND RS R57-14-34381. (M)

Part: WEB — CORRODED (FUSELAGE)

C2-CHECK, FOUND BS 400 RBL 11-40 FLOOR SUPPORT WEB CORROSION. FLOOR SUPPORT WEB LOWER SKIN REPLACED PER SRM 51-10-01 AND SRWS 917297. (M)

Part: TIE CLIP — CRACKED (FUSELAGE)

C2-CHECK, BS 440 STRINGER 12L SHEAR TIE CLIP CRACKED. SHEAR TIE CLIP REPLACED PER SRM 51-10-01 PAGE 18 AND SRWS 917177. (M)

Part: CLIP — CRACKED (NOSE WW)

C2-CHECK, NOSE W/W SIDEWALL LEFT REAR NR 2 STIFFENER CLIP CRCKED AT BS 280. CLIP REPLACED PER SRM 51-10-01. (M)

Part: INTERCOSTAL — CRACKED (NOSE WW)

C-2 CHECK, FOUND NOSE W/W TOP PANEL INTERCOSTAL CRACKED AT BS 290 LBL 20. INTERCOSTAL REPLACED PER SRM 51-10-01. (M)

Part: FITTING — CRACKED (NR 1 NACELLE)

C2-CHECK, NR 1 NACELLE U/W DIAGONAL BRACE FITTING OUTBOARD FLANGE MOST AFT FASTENER HOLE FOUND CRACKED. FITTING REPLACED PER BSB-57-2288, BOEING MSG EVR-HKG-00-00108H, AND RS R57-04-34383. (M)

Part: SEAT TRACK — CORRODED (CABIN)

FOUND BS 610 LBL 100 SEAT TRACK CORRODED. REPAIRED BS 610 LBL 100 SEAT TRACK PER SRM 53-10-05 FIG 8. (M)

Part: WEB — CRACKED (BS 480)

FOUND BS 480 FRAME WEB CRACKED AT STRINGER 14R CUTOUT. STOP HOLE DRILLED, NDT INSPECTED AND REPAIR DOUBLER INSTALLED PER BOEING MSG EVR-HKG-00-00094H AND RS R53-12-34368. REF BSB 53A2265/AD91-11-01. TERM ACTION TO BE C/W AT OR PRIOR TO 20,000 CYCLES. (M)

Part: STRUCTURE — CRACKED (FLOORBEAM)

FOUND BS 330 RBL 66 FLOORBEAM UPPER CHORD AND WEB CRACKED. UPPER CHORD AND WEB REPAIRED PER BSB53-2272 AND RS R53-15-34365. (M)

Part: SKIN — CORRODED (FUSELAGE)

BS 835 STRINGER 46L BELLY SKIN AND INTERNAL STRAP CORRODED. SKIN AND DOUBLER TRIMMED OFF, NDT INSPECTED AND SKIN REPAIRED AT BS 800-845, STRINGER 45L TO STRINGER 47L PER BOEING MSG EVR-HKG-00-00127H/00125H/00111F AND RS R53-12-34393. (M)

Part: WEB — CRACKED (FUSELAGE)

MED 1L FRAME LOWER CORNER FOUND CRACKED AT BS 488 WEB BETWEEN DOUBLER AREA. BS 488 FRAME ATTACH WEB REPAIRED AT STRINGER 23L TO STRINGER 30L PER SRM 53-10-24. (M)

Part: FRAME — CRACKED (FUSELAGE)

FOUND BS 440 LEFT FRAME CRACKED AT STRINGERS 11L AND 12L. TRIMMED OFF DAMAGED AREA, NDT INSPECTED, DOUBLER SPLICE REPLACED, AND REPAIR DOUBLER INSTALLED PER BOEING MSG EVR-HKG-00-00095H AND RS R53-12-34371. (M)

Part: FRAME — CRACKED (FUSELAGE)

FOUND BS 360 STRINGER 7L FRAME CRACKED. TRIMMED OFF, NDT INSPECTED AND FRAME REPAIRED PER SRM 53-10-04 AND SRWS 917266. (M)

Part: STRUCTURE — CORRODED (FUSELAGE)

BS 1540 RBL 57 TO LBL 57 FAIR SUPPORT CHORD CORRODED APPROX 1 INCH BY 5 INCH. FAIRING SUPPORT CHORD REPAIRED PER SRM 53-50-04 FIG 2. (M)

Part: FRAME — CRACKED (FUSELAGE)

FOUND BS 380 STRINGER 9L FRAME CRACKED. TRIMMED OFF, NDT INSPECTED AND FRAME REPAIRED PER SRM 53-10-04 AND SRWS 917265. (M)

Part: SEAT TRACK — CORRODED (CABIN)

FOUND BS 2120 - BS 2140 RBL 33.99 SEAT TRACK CROWN AND FLANGE AREA CORRODED. BS 2110-2230 RBL 33.99 SEAT TRACK REPAIRED PER SRM 53-10-05 FIG 1A. (M)

Part: FITTING — CRACKED (FUSELAGE)

FOUND BS 280 LBL 40 SUPPORT FITTING CRACKED. TRIMMED OFF CRACK, NDT INSPECTED, REPAIRED FRAME PER SRM 53-10-04. (M)

Part: WEB — CRACKED (FUSELAGE)

FOUND BS 380 FRAME WEB CRACKED AT STRINGER 10L CUTOUT REPAIR. OVERSIZED TO REMOVE CRACK, NDT INSPECTED, AND REPAIR DOUBLER INSTALLED PER BOEING MSG EVR-HKG-00-00080F/-000093H AND RS R53-12-34369. REF SB747-53A2265/AD91-70-01. CONTINUED INSPECTION REQUIRED IAW SB747-53A2265. TERM ACTION PER SB747-53-2272 TO BE C/W AT OR PRIOR TO 20,000 CYCLES. (M)

Part: WEB — CRACKED (FUSELAGE)

FOUND BS 420 FRAME WEB CRACKED AT STRINGER 15R CUTOUT. REPAIR DOUBLER INSTALLED PER BOEING MSG EVR-HKG-00-00082F/00100H AND RS R53-12-34374. (M)

Part: SEAT TRACK — CORRODED (CABIN)

FOUND BS 1450-1460 BL RBL 74R SEAT TRACK FLANGE CORRODED. SEAT TRACK REPAIRED PER SRM 53-10-05 FIG 32 AND SRWS 917282. (M)

Part: WEB — CORRODED (FUSELAGE)

FOUND BS 460 RBL 44-90 FLOOR SUPPORT WEB CORRODED. REPAIRED FLOOR SUPPORT SHEAR WEB PER SRM 51-40-02 FIG 1. (M)

Part: BEAM — CORRODED (FUSELAGE)

FOUND STATION 1045 RBL 9 TO RBL 16 AIR COND BAY ACCESS PANEL LATERAL SUPPORT BEAM CORRODED APPROX 2 INCH BY 1 INCH. BS 1045 RBL 16 BODY FAIRING SUPPORT BEAM REPAIRED PER SRM 53-50-04 FIG 2. (M)

Part: CLIP — CRACKED (NOSE WW)

C2-CHECK, NOSE W/W SIDEWALL LEFT REAR NR 2 STIFFENER CLIP FOUND CRACKED AT BS 300. CLIP REPLACED PER SRM 51-10-01. (M)

Part: TIE CLIP — CRACKED (FUSELAGE)

C2-CHECK, BS 360 STRINGER 7L FRAME ATTACH SHEAR TIE CLIP CRACKED. SHEAR TIE CLIP REPLACED PER SRM 51-10-01 AND 51-30-02. (M)

Part: FITTING — CRACKED (RT WING)

C2-CHECK, RIGHT WING BS 1241 CENTER SECTION REAR SPAR LOWER CHORD KICK FITTING ATTACH ''O'' BOLT HOLE FOUND CRACKED. NDT INSPECTED. FREEZE PLUG AND OVERSIZE FASTENER INSTALLED PER BOEING MSG EVR-HKG-00-00077H/-00076F AND RS R57-12-34360. (M)

Part: SKIN — CORRODED (LT WING)

C2-CHECK, FOUND CORROSION AT LEFT WING NR 1 FUEL TANK LOWER SKIN AT INBOARD WS 707 BOOST PUMP ACCESS CUTOUT INTERIOR SURFACE. CORROSION BLENDED OUT, NDT INSPECTED, SHOT-PEENED AREA AND HARDENER FILLED PER BOEING MSG EVR-HKG-OO-00085F/00102H AND RS R57-26-34380. (M)

Part: STRUCTURE — CORRODED (REAR SPAR)

C2-CHECK -FX-WING CENTER CENTER BS 1241 LBL 82-87 REAR SPAR WEB LOWER CHORD AREA BOTTOM ATTACH STRAP, CORROSION FOUND. BLENDED AREA, NDT INSPECTED, FILLER FABRICATED AND TAPER SHANK FASTENERS INSTALLED PER BOEING MSG EVR-HKG-00-00089F/00091H AND RS R57-12-34370. (M)

Part: TIE CLIP — CRACKED (FUSELAGE)

C2-CHECK, FOUND COCKPIT BS 360 STRINGER 0 TO STRINGER 1L TIE CLIP CRACKED. SHEAR TIE CLIP REPLACED PER SRM 51-10-01. (M)

Part: INTERCOSTAL — CRACKED (NOSE WW)

C2-CHECK, FOUND NOSE W/W TOP PANEL INTERCOSTAL CRACKED AT BS 290 RBL 20. REPLACED INTERCOSTAL PER SRM 51-10-01 PAGE 18 AND SRWS 917286. (M)

Part: WEB — CRACKED (L2 DOOR)

C2-CHECK, FOUND CABIN L2 DOOR AFT UPPER CORNER VERTICAL FRAME WEB CRACKED AT NR 1 STOP PIN FITTING AREA, APPROX 2 INCHES LONG. STOP DRILLED AND REPAIR DOUBLER INSTALLED PER BOEING MSG EVR-HKG-00-00083F/00099H AND RS R-52-11-34376. (M)

Part: CIRCUIT BOARD — MALFUNCTIONED (COCKPIT)

KJFK - DURING CLIMB, TAKEOFF WARNING HORN AND RED GEAR LIGHT AFTER GEAR RETRACTED AND FLAPS AT 1 DEGREE. REPLACED AURAL WARNING A11 CARD. PERFORMED LANDING WARNING AND TAKEOFF WARNING CHECKS PER MM 31-26-00. (M)

Part: ENGINE — BIRD STRIKE (NR 4)

KTOL - DURING TAKEOFF ROLL, JUST PRIOR TO ROTATION, NR 4 ENGINE INGESTED A BIRD AND FAILED. DUMPED FUEL TO BELOW STRUCTURAL LIMITS AND RETURNED FOR LANDING. GROUND CHECK CONFIRMED NR 4 ENGINE AND NOSE COWL DAMAGE DUE TO BIRD STRIKE. (M)

Part: ENGINE — FLAMED OUT (NR 2)

TPE - AT FLIGHT LEVEL 410, AIRCRAFT ENCOUNTERED A THUNDERSTORM WHICH DID NOT SHOW UP ON RADAR. THE NR 2 ENGINE FLAMED OUT. AIRCRAFT THEN DESCENDED TO FLIGHT LEVEL 330 AND ACCOMPLISHED AN INFLIGHT RESTART. INSPECTION AT TPE FOUND NO DISCREPANCIES. LINE MAINTENANCE PLANNING REQUEST HAS BEEN ISSUED FOR A DETAILED INSPECTION. (M)

Part: START VLV LIGHT — ILLUMINATED (NR 4 ENGINE)

CTS - DURING CRUISE, NR 4 ENGINE START VALVE OPEN LIGHT ILLUMINATED, ALL OTHER ENGINE PERIMETERS WERE NORMAL. ENGINE WINDMILLED FOR 1.6 HOURS AT 25 PSI OIL PRESSURE. (M)

Part: SWITCH — FAILED (NR 4 ENGINE)

LAX - WHILE CLIMBING THROUGH FL330, THE NR 4 ENGINE START VALVE OPEN LIGHT ILLUMINATED. ENGINE SHUT DOWN PER ABNORMAL PROCEDURES. WINDMILLED WITH 24 PSI OIL PRESSURE. PERFORMED INSPECTION OF WING FROM PRESSURE SWITCH TO WING BODY CONNECTION AND PERFORMED RESISTANCE CHECK, NO DEFECTS NOTED. REPLACED PRESSURE SWITCH PER MM 80-11-05 CHECKED GOOD UNABLE TO DUPLICATE. PERFORMED WINDMILL INSPECTION MM 72-00-00. FILTER AND CHIP DETECTOR SERVICING. (M)

Part: FLOORBEAM — DAMAGED (BS 440)

HKG - DURING C1 CHECK, UPPER DECK FLOORBEAM HAS TEMPORARY REPAIRS AT BS 440 ON LEFT AND RIGHT SIDES. REPAIRED PER SRM 53-10-07 FIG 11, 8110-3 AND ECRA 470-53-98-1A. (M)

Part: SPLICE — CRACKED (BS 1480)

HKG - DURING C1 CHECK, RIGHT BS 1480 BULKHEAD FITTING SPLICE HAS 8 BOLT HOLES WITH CRACKS. REPAIRED PER SB 747-53A2390 FIG 23 AND EO 53-747-1513-98 REV A. (M)

Part: SWITCH — FAILED (NR 4 ENGINE)

JFK - IN CRUISE, NR 4 ENGINE START VALVE OPEN LIGHT CAME ON. SHUTDOWN ENGINE. N1 32 PERCENT, N2 24 PERCENT, OIL PRESSURE 20 PSI. REPLACED START VALVE SWITCH PER MM 80-11-05. OPS CHECK GOOD. INSPECTED ENGINE PER MM 72-00. (M)

Part: ENGINE — OVERTEMP (NR 1 NACELLE)

JFK - LOG PAGE: F73265 - EN ROUTE FROM KLCK TO KJFK, NR 1 ENGINE NACELLE TEMP WENT TO 720 DURING CLIMB, INCREASED TO 820. ACCOMPLISHED NAC OVERTEMP PROCEDURE, NO HELP. ACCOMPLISHED IN-FLIGHT SHUT DOWN CHECK LIST. WINDMILL TIME, 1 HOUR NAC TEMP, WENT TO ZERO AFTER SHUT DOWN, POSITIVE OIL PRESSURE. (X)

Part: LIGHT — SMOKING (COCKPIT)

KWRA - LOG PAGE: F67062 - CAPTAIN'S FLUORESCENT LIGHT ON GLARE SHIELD SMOKING WITH POWER ON. TRANSPORTED TO DMI 260 PER MEL 33-1 CAT C DUE 7-25-98. CAPTAIN'S FLUORESCENT LIGHT CIRCUIT BREAKER PULLED. (X)

Part: DOOR — MALFUNCTIONED (MLG)

KWRI - AFTER TAKEOFF AT ETAR, RIGHT WING LANDING GEAR DOOR FAILED TO OPEN, GEAR REMAINED DOWN AND LOCKED. REPEATED GEAR RETRACTION, NO HELP. DURING PREP TO RETURN TO ETAR, WITH GEAR HANDLE IN THE 'OFF' POSITION RIGHT BODY GEAR DOOR 'OPEN' LIGHT CAME ON. MOVED GEAR HANDLE TO THE 'UP' POSITION. RIGHT BODY GEAR DOOR LIGHTS EXTINGUISHED, RIGHT WING GEAR DOOR OPEN AND GEAR RETRACTED. DOOR CLOSED. (M)

Part: FIRE LOOP — MALFUNCTIONED (NR 1 ENGINE)

CTS - AFTER TAKEOFF NR 1 ENGINE A LOOP OFF-SCALE WITH FAULT LIGHT ILLUMINATED. SWITCHED TO B LOOP, TESTED NORMAL. THEN IN CRUISE B LOOP INDICATED FAULT. PERFORMED IN FLIGHT SHUTDOWN. OIL PRESSURE NOT BELOW 10 PSI. REPAIRED B LOOP UPPER ELEMENT CONNECTOR, OPS CHECKED GOOD PER MM 26-11-0. REPLACED A-13 CARD DUE TO PRECAUTIONARY MEASURE. PERFORMED WINDMILL INSPECTION PER MM 72-00-00, NO DEFECTS NOTED. (M)

Part: ENGINE — FAILED (NR 2)

NAN - DURING CLIMB-OUT AT APPROX 8000 FT AN EXPLOSIVE NOISE WAS HEARD AND A/C YAWED. NR 2 ENGINE S/N 662970 FAILED. AIRCRAFT RETURNED TO NAN WITH NO FURTHER INCIDENT. (M)

Part: ENGINE — FAILED (NR 2)

DURING CLIMB-OUT AT 8,000 FEET, AIRCRAFT EXPERIENCED A LOUD EXPLOSIVE NOISE PLUS HIGH EGT ON NR 2 ENGINE. AIRCRAFT AIR TURN BACK AFTER DUMPING FUEL. ON INVESTIGATION, FOUND METAL PARTICLES IN NR 2 ENGINE TAILPIPE.

Part: FITTING — CORRODED (LT/RT MLG)

HKG - DURING B-CHECK, LT AND RT BODY LANDING GEAR TRUNNION SUPPORT FITTINGS, CORROSION WAS FOUND IN THE BOLT HOLES AND BEARING SURFACES. THE LEFT INBOARD AND OUTBOARD LOWER TRUNNION CAPS ALSO HAVE CORROSION. REPAIRED TRUNNION FITTINGS PER BOEING TELEX PAO-HKG-98-0102RE/0103RE/0105RE APPROVED ON 8110-3, DATED JUNE 26, 1998, ECRA 470-53-99-1. (M)

Part: FITTING — CORRODED (RT MLG)

HKG - DURING B-CHECK, LEFT AND RIGHT BODY LANDING GEAR TRUNNION SUPPORT FITTINGS, CORROSION WAS FOUND IN THE BOLT HOLES AND BEARING SURFACES. THE LEFT INBOARD AND OUTBOARD LOWER TRUNNION CAPS ALSO HAVE CORROSION. REPAIRED TRUNNION FITTINGS PER BOEING TELEX PAO-HKG-98-0102RE/0103RE/0105RE APPROVED ON 8110-3 DATED JUN 26, 1998. (M)

Part: SKIN — CRACKED (LT DOOR)

HKG - DURING B-CHECK, L1 DOOR UPPER HINGE, DOOR SKIN CRACKED AT HINGE CUTOUT. REPAIRED DOOR SKIN PER BOEING TELEX EVR-HKG-98-0100RE AND APPROVED ON 8110-3 DATED JUNE 22, 1998. ECRA 470-52-97-1. (M)

Part: FLOORBEAM — CRACKED (BS 440)

HKG - DURING B-CHECK, BS 440 UPPER DECK FLOORBEAM WAS FOUND CRACKED AT THE UPPER CHORD, RT OUTBOARD END RUNNING INBOARD .040 INCH. ACCOMPLISHED TIME LIMITED REPAIR, PERMENANT REPAIR TO BE ACCOMPLISHED PRIOR TO 18 MONTHS OR 1500 CYCLES, WHICHEVER COMES FIRST PER TELEX EVR-HKG-98-0091TE, AD 98-09-17, ECRA 470-53-98-1 GENERATED TO TRACK REPAIR. (M)

Part: FLOORBEAM — CRACKED (BS 440)

HKG - DURING B-CHECK, BS 440 UPPER DECK FLOORBEAM WAS FOUND CRACKED AT THE UPPER CHORD, LEFT OUTBOARD END RUNNING INBOARD .040 INCH. ACCOMPLISHED TIME LIMITED REPAIR, PERMANENT REPAIR TO BE ACCOMPLISHED PRIOR TO 18 MONTHS OR 1500 CYCLES, WHICHEVER COMES FIRST PER TELEX EVR-HKG-98-0091TE, AD 98-09-17, ECRA 470-53-98-1 GENERATED TO TRACK REPAIR. (M)

Part: RETRACT MECH — MALFUNCTIONED (LT MLG)

HKG - LOG PAGE: F08753 - AFTER TAKEOFF, LEFT WING GEAR FAILED TO GO UP, RECYCLED GEAR ONCE, NO HELP. RETURNED TO HKG. RIGGING CHECK ACCOMPLISHED WITH NO ADJUSTMENTS PERFORMED, ALL TENSION WITHIN LIMITS PER MM 32-31-00. RETRACTION AND EXTENSION CHECKS CARRIED OUT AND NO FAULTS FOUND. RETURNED AIRCRAFT TO SERVICE WITH NO FURTHER PROBLEMS REPORTED. (X)

Part: INDICATOR — FAILED (COCKPIT)

ANC - LOG PAGE: F08754 - IN-FLIGHT, NR 2 EGT GAUGE FAILED, AN IN-FLIGHT SHUT DOWN WAS PERFORMED AS A PRECAUTION, OIL PRESSURE STAYED ABOVE 5 PSI AT ALL TIMES. REPLACED EGT INDICATOR PER MM 77-21-03. CARRIED OUT WINDMILL INSPECTION PER MM 72-00-00. OPS CHECKED EGT INDICATION PER MM 77-21-03 SATISFACTORY. (X)

Part: WHEEL — DEFLATED (MLG NR 9)

WHILE PARKED AT GATE, NR 9 WHEEL LOST PRESSURE SUDDENLY. SUSPECT CAUSE - FUSIBLE PLUG FAILED AND BRAKE OVERHEATED.

Part: BLADES — DAMAGED (ENGINE N1)

ON ARRIVAL NADI, FOUND FOUR N1 BLADES ON NR 1 ENGINE SEVERELY DAMAGED. SUSPECT CAUSE: INGESTION OF FOREIGN OBJECTS ON RUNWAY 02 CAUSED BY GEMINI AIR CARGO DC10-30F BLOWN WHEELS THAT LANDED EARLIER.

Part: FAN BLADES — BENT (NR 1 ENGINE)

JFK - APPROACH INTO JFK RUNWAY 22L, APPROXIMATELY 50-100 FEET, HAD BIRD STRIKE IN NR 1 ENGINE. LANDED WITHOUT INCIDENT, WITH AN OUTSIDE AIR TEMP OF 42 DEGREES F. REMOVED AND REPLACED FIVE PAIRS OF FAN BLADES PER MM 72-31-02. INSPECTED NR 1 ENGINE FOR BIRD INGESTION, AND FOUND NO CORE ENGINE DAMAGE. PERFORMED ENGINE RUN NO DEFECTS NOTED. SUBSEQUENTLY ENGINE WAS CHANGED FOR A OIL LEAK THAT WAS NOT RELATED TO THE BIRD STRIKE.

Part: BPCU — CONTAMINATED (NR 2)

JFK - AFTER TAKEOFF NR 1 GENERATOR TRIPPED OFF, UPPER YAW DAMPER LIGHT CAME ON ABOUT SAME TIME WITH SPLIT RUDDER INDICATION, SSB OPENED AND NR 3 AND NR 4 BTB'S OPENED. RETURNED TO JFK LANDING NORMAL. REMOVED WATER FROM LOWER CARGO AREA. REMOVED AND REPLACED NR 2 BPCU PER MM 24-22-02. NR 1 GCU PER MM 24-23-01, AND RESEATED UPPER YAW DAMPER COMPUTER PER MM 22-16-00 ALL AREAS OPS CHECKED GOOD. WATER APPEARED TO HAVE COME FROM PALLETS IN POSITIONS NR 1 AND 2. (M)

Part: AIR DISTRIBUTION — ODOR (COCKPIT)

KNGU - LOG PAGE F92553 - DURING CLIMB AND CRUISE, CREW NOTICED OIL SMELL IN COCKPIT. OPERATED NR 1, 2, 3 PACKS INDIVIDUALLY FOR 3.50 HOURS. NO NOTICE OF OIL SMELL. SYSTEM OPERATED NORMALLY. (X)

Part: CONTROL CABLE — BROKEN (RT TE FLAP)

JFK - LOG PAGE: F35129 - AFTER TAKEOFF AND RETRACTING FLAP FROM 5 DEGREES TO 1 DEGREE, FIRST OFFICER NOTED INBOARD LT T/E FLAP AT 1 DEGREE AND RT T/E FLAP AT 5 DEGREES. RETURNED TO JFK, NO PROBLEMS DURING LANDING. (X)

Part: SKIN — CRACKED (NR 1 PYLON)

SYZ - LOG PAGE: E04744 - ON W.A.C., FOUND CRACK IN NR 1 ENGINE PYLON OUTBOARD SKIN AT NACELLE STA 180, 2.6250 INCHES LONG. REPAIR CARRIED OUT PER B747 SRM 54-30-03 FIG 17A. (X)

Part: FITTING — CRACKED (BS 280)

MZJ - DURING C-CHECK INSPECTION, DISCOVERED A CRACK ON THE INBD ARM OF THE FITTING P/N 65B12888-6 LOCATED AT STA 280, RBL 40. ADDITIONALLY A CRACK ON THE FLOOR WEB P/N 65B07662-1021 IMMEDIATELY ABOVE THE FITTING WAS FOUND. AFFECTED AREAS WERE REPAIRED USING REINFORCEMENT ANGLES TO FIX THE INBD ARM OF THE FITTING AND TWO REPAIR DOUBLERS TO REINFORCE THE WEB. REPEAT VISUAL INSPECTION OF THE TWO REPAIRED AREAS IS REQUIRED EVERY 3,000 FLTS TARGETING FURTHER CRACK PROPAGATION OF FURTHER DAMAGE. ACCOMPLISHED IAW EIAA, ENGINEERIGN CHANGE/REPAIR AUTHORIZATION NR 470-53-077-2. (M)

Part: SKIN — CORRODED (LT WING)

MZJ - DUIRNG C-CHECK INSPECTION, DISCOVERED EXFOLIATION CORROSION ON THE UPPER SURFACE OF THE LOWER SKIN OF THE LEFT WING JUST AFT OF THE REAR SPAR LOWER CHORD. ACCOMPLISHED IAW EVERGREEN INTERNATIONAL AIRLINES, ENGINEERING CHANGE/REPAIR AUTHORIZATION NR 470-57-080-2. REPAIRED BY BLENDING AWAY CORROSION AND FABRICATING, INSTALLING REINFORCEMENT STRAP. (M)

Part: SKIN — CORRODED (BS 1050)

MZJ - DURING C-CHECK INSPECTION, DISCOVERED EXFOLIATION CORROSION ON THE WING CENTER SECTION UPPER PANEL NR 1 EXTERNAL SKIN SURFACE. THE CORROSION AREA IS LOCATED AT BS 1050 BETWEEN LBL 88.52 AND 98.52 AND EXTENDS ALONG STRINGER 27L. REPAIRED BY BLENDING AWAY CORROSION IN THE AFFECTED AREAS. REPAIRED ACCOMPLISHED IAW EIAA, ENGINEERING CHANGE/REPAIR AUTHORIZATION NR 470-57-088-2. (M)

Part: FLOORBEAM — CORRODED (BS 1450-1460)

DURING C-CHECK INSPECTION, DISCOVERED CORROSION ON THE UPPER SURFACE OF THE UPPER FLOORBEAM CHORD BETWEEN BS 1450-1460, RLB 57.7 BLEND OUT OF CORROSION EXCEEDED SRM LIMITS AND REQUIRES TRIMMING TO REMOVE CORROSION. REINFORCEMENT REPAIR ANGLES AND FILLER WERE INSTALLED. ACCOMPLISHED IAW EIAA, ENGINEERING CHANGE/REPAIR AUTHORIZATION NR 470-57-081-2. (M)

Part: SKIN — CORRODED (RT WING)

MZJ - DURING C-CHECK INSPECTION, DISCOVERED EXFOLIATION CORROSION ON THE UPPER SURFACE OF THE LOWER RIGHT HAND WING TRAILING EDGE SKIN BETWEEN WS 724.5 AND WS 740.0. AFFECTED AREAS WERE TRIMMED TO REMOVE CORROSION. FABRICATED AND INSTALLED REPAIR FILLERS WET WITH SEALANT. ACCOMPLISHED IAW ECRA 470-57-075-2 REV A. (X)

Part: WEB — CRACKED (BS 280)

MZJ - DURING C-CHECK INSPECTION, DISCOVERED A CRACK ON THE INBD ARM OF THE FITTING P/N 65B12888-6 LOCATED AT STA 280, RBL 40. ADDITIONALLY A CRACK ON THE FLOOR WEB P/N 65B07662-1021 IMMEDIATELY ABOVE THE FITTING WAS FOUND. AFFECTED AREAS WERE REPAIRED USING REINFORCEMENT ANGLES TO FIX THE INBD ARM OF THE FITTING AND TWO REPAIR DOUBLERS TO REINFORCE THE WEB. REPEAT VISUAL INSPECTION OF THE TWO REPAIRED AREAS IS REQUIRED EVERY 3,000 FLTS TARGETING FURTHER CRACK PROPAGATION OF FURTHER DAMAGE. ACCOMPLISHED IAW EIAA, ENGINEERIGN CHANGE/REPAIR AUTHORIZATION NR 470-53-077-2. (M)

Part: SEAL — WORN (NR 4 ENGINE)

VHHH - DURING CRUISE FLIGHT, NR 4 ENGINE HAD LOW OIL QTY REQUIRING PRECAUTIONARY ENGINE SHUTDOWN. OIL PRESSURE FLUCTUATED INTO CAUTION RANGE. ENGINE NR 4 WAS SHUTDOWN IN FLIGHT. INSPECTED NR 4 ENGINE FOR OIL LEAKS PER MM. FOUND HYDRAULIC PUMP DRIVE SEAL LEAKING. REPLACED SEAL PER MM, RUN UP LEAK CHECK WAS GOOD. (M)

Part: GEARBOX — FAILED (NR 2 ENGINE)

LAX - DURING CRUISE FLIGHT AT FL310, LOW OIL PRESSURE LGHT CAME ON. OIL PRESSURE GAUGE READ 'A' PSI AND N2 INDICATED ZERO PERCENT. ENGINE NR 2 WAS SHUTDOWN INFLIGHT. SUSPECT GEAR BOX FAILURE. AIRCRAFT BEING FERRIED TO JFK FOR ACCESSORY GEAR BOX REPLACEMENT. (M)

Part: SKIN — CORRODED (WS 724-740)

DURING C-CHECK INSPECTION DISCOVERED EXFOLIATION CORROSION ON THE UPPER SURFACE OF THE LOWER RIGHT WING TRAILING EDGE SKIN BETWEEN WS 724.5 AND 740. AFFECTED AREAS WERE TRIMMED TO REMOVE CORROSION. FABRICATED AND INSTALLED REPAIR FILLERS WET WITH SEALANT. ACCOMPLISHED IAW EIAA, ENGINEERING CHANGE/REPAIR AUTHORIZATION NR 470-57-075-2 REV A.

Part: SKIN — CORRODED (BS 1050)

DURING C-CHECK INSPECTION, DISCOVERED EXFOLIATION CORROSION ON THE WING CENTER SECTION UPPER PANEL NR 1 EXTERNAL SKIN SURFACE. THE CORRODED AREA IS LOCATED AT BS 1050 BETWEEN LBL 88.52 AND 98.52 AND EXTENDS ALONG STRINGER 27L. REPAIRED BY BLENDING AWAY CORROSION IN THE AFFECTED AREAS. REPAIRED IAW WITH EIAA, ENGINEERING CHANGE/REPAIR AUTHORIZATION NR 470-57-088-2. (M)

Part: SKIN — CORRODED (WS 981-985)

DURNIG C-CHECK INSPECTION DISCOVERED EXFOLIATION CORROSIO NON THE UPPER SURFACE OF THE LOWER SKIN OF THE LEFT WING JUST AFT OF THE REAR SPAR LOWER CHORD. REPAIRED BY BLENDING AWAY CORROSION AND FABRICATING, INSTALLING REINFORCEMENT STRAP. REPAIRED IAW EIAA, ENGINEERING CHANGE/REPAIR AUTHORIZATION NR 470-57-080-2. (M)

Part: FLOORBEAM — CORRODED (BS 1450-1460)

DURING C-CHECK INSPECTION, DISCOVERED CORROSION ON THE UPPER SURFACE OF THE UPPER FLOORBEAM CHORD BETWEEN BS 1450-1460, RBL 57.7. BLENDOUT OF CORROSION EXCEEDED SRM LIMITS AND REQUIRED TRIMMING TO REMOVE CORROSION. REINFORCEMENT REPAIR ANGLES AND FILLERS WERE FABRICATED AND INSTALLED. REPAIRED IAW EIAA, ENGINEERING CHANGE/REPAIR AUTHORIZATION NR 470-53-081-2.

Part: STRINGER — CRACKED (BS 985)

SAT - DURING C-6 INSPECTION, FOUND MAIN CABIN STRINGER 17L CRACKED AT FS 985. FABRICATED AND INSTALLED REPAIR SPLICE TO STRINGER 17L AT FS 960 TO FS 996 PER SRM 53-02 FIG 2 AND DAC SK933-594. (M)

Part: CRANK ROLLER — BROKEN (PAX DOOR)

ANC - CLIMBING THRU FL 10,000 FT A SOFT POPPING SOUND CAME FROM THE CARGO COMPT, A LOUD POPPING SOUND FOLLOWED. JARRING OF THE FLT DECK ACCOMP BY 'L ENTRY DOOR 1' LIGHT CAME ON. CABIN PRESS WAS NORM. VISUAL CHK'D, DOOR HANDLE IN LOCKED POSITION. NO AIR LEAKAGE NOTICED. FOUND L1 DOOR, AFT SIDE, UPPR AND LWR LATCH ROLLER CRANK BROKEN. REPLACED BOTH UPPR AND LWR LATCH ROLLER CRANK AND ASSOCIATED HARDWARE. UPPR AND LWR DOOR LATCH TORQUE TUBE HAD TO BE REMOVED AND REPLACED TO INSTALL LATCH ROLLER CRANK. SCRATCHES IND THE 2 ROLLERS WERE NOT PROPERLY ENGAGED AT TOP AFT CORNER. (M)

Part: ROLLER — DAMAGED (PAX DOOR)

ANC - CLIMBING THRU FL 10,000 FT A SOFT POPPING SOUND CAME FROM THE CARGO COMPT, A LOUD POPPING SOUND FOLLOWED. JARRING OF THE FLT DECK ACCOMP BY 'L ENTRY DOOR 1' LIGHT CAME ON. CABIN PRESS WAS NORM. VISUAL CHK'D, DOOR HANDLE IN LOCKED POSITION. NO AIR LEAKAGE NOTICED. FOUND L1 DOOR, AFT SIDE, UPPR AND LWR LATCH ROLLER CRANK BROKEN. REPLACED BOTH UPPR AND LWR LATCH ROLLER CRANK AND ASSOCIATED HARDWARE. UPPR AND LWR DOOR LATCH TORQUE TUBE HAD TO BE REMOVED AND REPLACED TO INSTALL LATCH ROLLER CRANK. SCRATCHES IND THE 2 ROLLERS WERE NOT PROPERLY ENGAGED AT TOP AFT CORNER. (M)

Part: SKIN — CRACKED (RT TE ELEVATOR)

SAT - RIGHT INBOARD ELEVATOR TE DAMAGED. REPAIRED DAMAGED AREA PER SRM 51-40-14, PARA 4N FIG 20. SEALED REPAIR PER SRM 51-40-14 AND APPLIED CONDUCTIVE COATING PER SRM 51-24-03. REAPPLIED FINISH PER MM 51-24-03 AND SRM 51-40-14, PARAGRAPH 4N, NR 18. (M)

Part: WEB — CRACKED (BS 455/520)

SAT - DURING B-CHECK INSPECTION, FOUND CABIN FLOOR WEB CRACKED AT STATION FORWARD AND AFT SIDE OF STATION 520 AND CORRODED AT STATION 455 LBL 11. REPAIRED WEB AND INSTALLED DOUBLERS PER SRM 51-20-01, 51-40-2, AND 51-10-02. REMOVED CORROSION, TREATED, ALODINED AND PRIMED PER SRM 51-10-01. (M)

Part: SEAT TRACK — CRACKED (BS 450-530)

SAT - SEAT TRACK BETWEEN STATION 480 AND 495 AND LBL 6 CRACKED AND CORRODED. REPAIRED DAMAGE SECTION OF TRACK FROM STATION 450 TO STATION 530 PER SRM 53-10-05, FIG 1 AT EXISTING SPLICES. (M)

Part: SEAT TRACK — CRACKED (CABIN)

SAT - SEAT TRACK AT STATION RBL 6 CRACKED. REMOVED DAMAGED SECTION OF THE SEAT TRACK PER SRM 51-30-2. FABRICATED REPAIR SECTION IAW SRM 53-11-25 AND 53-10-5. INSTALLED IAW 51-30-2. (M)

Part: FLOOR BEAM — CRACKED (CABIN)

SAT - FLOOR BEAM AT STATION 460, LBL 11 THROUGH 24 CRACKED. REMOVED DAMAGED SECTION OF FLOOR BEAM FROM RBL 48 TO LBL 48. FABRICATED AND INSTALLED REPAIR PARTS PER SRM 53-10-07, FIG 12. (M)

Part: SEAT TRACK — CRACKED (BS 480-510)

SAT - SEAT TRACK AT LBL 69.3, STATION 500 CRACKED AT FRAME ATTACHMENT AREA. REMOVED DAMAGED SEAT TRACK FROM STATION 480 THROUGH 510. FABRICATED AND INSTALLED REPAIR PARTS PER SRM 53-10-05, FIG 1. (M)

Part: FLOOR — CRACKED (CABIN)

SAT - CABIN FLOOR WEB CRACKED AT STATION 520 FORWARD AND AFT, AND CORRODED AT STATION 455, LBL 11. REPAIRED WEB AND INSTALLED DOUBLER PER SRM 51-20-01, 51-40-2, AND 51-10-02. REMOVED CORROSION, TREATED, ALODINED, AND PRIMED PER SRM 51-10-01. (M)

Part: FLOOR BEAM — CRACKED (CABIN)

SAT - FLOOR BEAM AT STATION 480, LBL 24, THROUGH LBL 29 CORRODED. REMOVED DAMAGED FLOOR BEAM FROM BL 0 TO LBL 72. FABRICATED AND INSTALLED REPAIR PARTS PER SRM 53-10-07, FIG 12. (M)

Part: FLOORBEAM — CORRODED (BS 480)

SAT - DURING B-CHECK INSPECTION, FOUND FLOORBEAM AT STATION 480, LBL 24 TO LBL 29 CORRODED AT PREVIOUS REPAIR. REMOVED DAMAGED SECTION OF FLOORBEAM FROM BL 0 TO LBL 72. FABRICATED AND INSTALLED REPAIR PARTS PER SRM 53-10-07, FIG 12. (M)

Part: BYPASS LIGHT — MALFUNCTIONED (NR 2 ENGINE)

LAX - ON CLIMB-OUT, NR 2 ENGINE OIL BYPASS LIGHT CAME ON AND STAYED ON EVEN AT IDLE THRUST. ENGINE SHUTDOWN, DUMPED FUEL, AND RETURNED TO LAX. OIL PRESSURE NORMAL. NR 2 ENGINE OIL FILTER INSPECTED AND FOUND TO BE CLEAN AS PER DDPG 79-3. OIL FILTER REPLACED AS A PRECAUTION. INOPERATIVE ENGINE OIL PRESSURE BYPASS WARNING LIGHT TRANSFERRED TO CAT C DMI PER MEL 79-3. OIL FILTER TO BE CHECKED EVERY 30 HOURS. (M)

Part: GCU — FAILED (NR 2 ENGINE)

HKG - AFTER TAKEOFF (5 MINS INTO FLIGHT) NR 1 AND NR 2 BUS TIE LIGHTS ILLUMINATED. ALSO, SSB OPENED. CONTINUED FLIGHT WITH LIGHTS ON. APPROXIMATELY 20 MINS LATER, NR 2 GENERATOR OPEN LIGHT AND FIELD LIGHT ILLUMINATED. COULD NOT RESET FIELD OR BUS TIE LIGHTS. GENERATOR PANEL SHOWED CONTROL NR 2 GENERATOR AND CSD NR 1 GENERATOR. NR 1 GENERATOR SHOWED 110 VOLTS AND NORMAL FREQUENCY. DUMPED FUEL AND RETURNED TO HKG. REPLACED LT BCPU AND NR 2 GCU. CHECKED NR 1 AND NR 2 CSD OIL LEVEL. BOTH FOUND NORMAL. CLEANED CANNON PLUG ON NR 1 GCU. PERFORMED ENGINE RUN ON NR 1 AND NR 2. SYSTEM CHECKED OK. INDICATIONS CHECKED GOOD ON GENERATOR VOLTS, PMG VOLTS, REQ, AND CSD RPM. (X)

Part: TIRE — FAILED (NR 9)

LAX - LOG PAGE F00612 - ON TAKEOFF ROLL, FELT SEVERE VIBRATION THROUGH AIRFRAME, ABORTED TAKEOFF, NR 9 TIRE BLOWN ON TAKEOFF. REPLACED NR 9 TIRE PER MM 32-41-15, PERFORMED AXLE INSPECTION PER MM 32-41-15, PERFORMED 'TIRE TREAD LOSS' INSPECTION PER MM 5-51-34 AND 'HIGH ENERGY STOP' INSPECTION PER MM 5-51-01. (X)

Part: LOGIC CARD — NOT SECURED (E & E COMP)

MIA - FLT 801 - ON TAKEOFF ROLL, TAKEOFF WARNING HORN CAME ON, ABORTED TAKEOFF AND RETURNED TO BASE. FOUND LOGIC CARD LOOSE IN AURAL WARNING LOGIC BOX, RE-INSERTED CARD AND PERFORMED OPS CHECK. GOOD PER BMM CHP31-50-00.