N482EV

Part: FIRE DETECTOR — FALSE ACTIVATION (APU BAY)

DURING DESCENT APU FIRE DET"A" LOOP LIGHT STARTED FLICKERING. SHOOK DOWN "A" LOOP AND WIRES. CAN NOT DUPUCIATE PROBLEM, CLEANED WIRE HARNESS REF AMM 20-10-04. OP'S CHECKED OK

Part: SWITCH — BURNED (LANDING LIGHT) · airframe 112,579 hrs

ON DEPARTURE, DURING THE LAST SEGMENT, A PUNGENT ODOR WAS DETECTED FOLLOWED BY VISUAL SMOKE ROLLING AND EMITTING OUT OF OVERHEAD PANEL BETWEEN LANDING LIGHT SWITCHES AND NR 1 HF RADIO. HF WAS OFF, THE LIGHTS WERE SELECTED OFF, SMOKE DISSIPATED AT THAT POINT BUT ELECTRIC SMOKE ODOR AND VERY HOT PANEL REMAINED. ACCOMPLISHED INSPECTION AS PER AMM 05-51-50 FOUND RT OUTBOARD LANDING LIGHT SWITCH AT FAULT (INTERNAL FAILURE). REPLACED RT OUTBOARD LANDING LIGHT SWITCH AS PER AMM 33-42-02 AND 33-11-04.

Part: STRUCTURE — DAMAGED (BS 540) · airframe 112,088 hrs · 25,834 cycles

DURING DOWN JACKING OF ACFT, BOARDING STAND IMPACTED AT BS 540 S23L. MAJOR REPAIR ACCOMPLISHED, REMOVED DAMAGE, NDT AREA, FABRICATED AND INSTALLED REPAIR PER SRM 53-30-03 PG. 51-54A

Part: FRAME — MISREPAIRED (BS 1810) · airframe 112,088 hrs · 25,834 cycles

AFT CARGO PIT FWD, CARGO DOOR JAMB BS 1810 STR. 39R FRAME REPAIRED INCORRECTLY. MAJOR REPAIR ACCOMPLISHED. REMOVED, REPAIR, FABRICATED NEW REPAIR AND INSTALLED PER SRM 53-10-04 FIG 70.

Part: LIGHT — INOPERATIVE (STAIRWAY) · airframe 112,088 hrs · 25,834 cycles

EMERGENCY LIGHT IN STAIRWAY DOME INOPERATIVE. REMOVED, REPAIRED AND REINSTALLED LIGHT ASSY. PER MM 33-51-07 PG. 201 - 203

Part: B-NUT — LOOSE (HYD TRANSMITTER) · airframe 112,068 hrs · 25,830 cycles

DUE TO NR 4 HYD SYSTEM LEVEL LOW PERFORMED ALT GEAR EXTENSION WING OPEN. FLUID LEVEL CAME UP SO GEAR WAS RECYCLED AND RE-EXTENDED NORMALLY WITHOUT FURTHER INCIDENT. HYD FLUID REMAINED AT 4 GAL. FOUND B-NUT ON NR 4 HYD TRANSMITTER LOOSE, REF PER CHAPTER 20 LEAK CHECKED GOOD. SERVICED NR 4 HYD QTY PER AMM 12-12-00 CHECKED GOOD.

Part: OVEN — MALFUNCTIONED (GALLEY) · airframe 122,146 hrs

OVEN WAS TURNED ON AND SMOKED. DEFERRED PER MEL 25-21-2. UNINSTALLED PLACARD. ACCOMPLISHED INSPECTION AS PER MM 05-51-50. PROCEDURES AS PER MM 21-00-01 NOT REQUIRED.

Part: OVEN — CONTAMINATED (GALLEY) · airframe 122,146 hrs

DURING INSPECTION, OVEN FOUND WITH EXCESSIVE GREASE BUILD UP ON OVEN TRAYS & OVEN INNER LINING. CLEANED OVEN & PERFORMED OPS AS PER AMM 25-31-00

Part: FIRE WARNING — FALSE ACTIVATION (COCKPIT)

DURING DESCENT AT APPROX 10,000FT APU FIRE BELL SOUNDED BRIEFLY AND "A" LOOP LIGHT ILLUMINATED. CLEANED C/P FIRE DET SYS, PERFORMED OPS TEST PER MM 26-15-00. OPERATION NORMAL, COULD NOT DUPLICATE.

Part: CIRCUIT CARD — NOT SEATED (FIRE WARNING) · airframe 11,904 hrs

APU FIRE LOOP A BEGAN TO FLICKER DURING DESCENT. RESEATED A5 CIRCUIT GOOD AS PER MM 26-11-03.

Part: SMOKE DETECTOR — FAULTY (CABIN)

MAIN DECK SMOKE DETECTOR 2 INTERMITTENTLY ILLUMINATES NO EVIDENCE OF SMOKE PRESENT. ITEM PLACED ON DMI 387 PER MEL 26-11 CAT C PLACARDS INSTALLED. SWAPPED SMOKE DETECTORS 2A AND 3A 2B AND 4A REMOVED AND REPLACED PER MM26-14-02. ZONE 2 SMOKE DETECTOR SYS. OP'S CHECK OK PER MM 26-14-02 THIS CLEARS DMI 387.

Part: SMOKE DETECTOR — FALSE ACTIVATION (MAIN DECK)

MAIN DECK SMOKE DETECTOR NR 2 COMES ON IN FLIGHT - NO SMOKE. TEST SMOKE DETECTOR IAW AMM 26-14-00. OPS OK NO DEFECTS NOTED.

Part: SMOKE DETECTOR — MALFUNCTIONED (CARGO BAY) · airframe 111,658 hrs

NR 2 MAIN DECK CARGO SMOKE DETECTOR LIGHT CAME ON NUMEROUS TIMES IN FLIGHT, VISUAL CHECK NORMAL. REPLACED MAIN DECK 2B SMOKE DETECTOR PER MM 26-14-02. ON GROUND OPS GOOD.

Part: SMOKE DETECTOR — MALFUNCTIONED (MAIN DECK) · airframe 111,658 hrs

NR 2 MAIN DECK SMOKE DETECTOR LIGHT INTERMITTENT ON AND OFF. PERIODIC CHECKS REVEALED NO SMOKE. RESEATED NR 2 MAIN SMOKE DET CP PER 26-14-01.

Part: HANDLE — OUT OF POSITION (RT MLG DOOR) · airframe 111,658 hrs

AFTER GEAR RETRACTION, BOTH LEFT AND RIGHT GEAR DOORS STAYED OPEN WITH GEAR HANDLE UP ACCOMPANIED BY GEAR DOOR LIGHT ON FWD ANNUCIATOR. ON SYSTEM CHECKOUT AND INSPECTION FOUND RT GEAR DOOR HAND RELEASE HANDLE NOT IN FULL UP DETENT POSITION. RESET MANUAL HANDLE TO FULL UP POSITION, CYCLED AND OPERATED GEAR DOORS, ALL INDICATIONS NORMAL. PERFORMED SIMULATED RETRACTING, ALL INDICATIONS NORMAL 32-12-00 REF.

Part: SMOKE DETECTOR — FAILED (MAIN DECK) · airframe 111,349 hrs

THE 3A MAIN DECK SMOKE DETECTOR WILL NOT TEST. TRANSFERRED TO DMI 352 AS PER MEL 26-11-1 CAT C DUE AUGUST 6, 2011 PLACARD INSTALLED. R&R SMOKE DETECTOR PER AMM 26-14-02. TEST OK DMI 352 CLEARD PLACARDS REMOVED.

Part: CONNECTOR — DISCONNECTED (LE SLAT) · airframe 111,057 hrs · 25,614 cycles

CREW REPORTED TO TECH CENTER THAT THE NR 3 RT LED GROUP WAS STUCK IN TRANSIT. LIGHTS ON FLIGHT ENGINEERS PANEL INDICATED GROUP IN TRANSIT WHILE ALL OTHERS INDICATED STOWED (GREEN) PERFORMED AIR TURNBACK. FOUND CONNECTOR FOR NR 3 RT GROUP DISCONNECTED. CONNECTOR WAS RECONNECTED AND NR 3 RT GROUP OPERATED NORMALLY PER MM 27-81-03.

Part: SMOKE DETECTOR — FAULTY (MAIN DECK)

NR 2 MAIN DECK SMOKE DETECTOR ILLUMINATED INTERMITTENTLY DURING FLIGHT. ITEM TRANSFERRED TO DMI 328 PER MEL 26-11 CAT C OPTION 1 PLACARDS INSTALLED. DMI 328 CLEARED FOUND DURING TROUBLESHOOTING 2B SMOKE DETECTOR LEAK. REMOVED AND REPLACED DETECTOR PER MM 26-14-01 OP'S CHECK GOOD. PLACARD REMOVED.

Part: SMOKE DETECTOR — FAULTY (CARGO BAY)

ON TAXI IN NR 2 MAIN DECK CARGO SMOKE DETECTOR ILLUMINATED. REPLACED NR 2B AND NR 3A MAIN CARGO SMOKE DETECTORS PER B747 MM 26-14-01 OP'S CHECK GOOD PER B747 MM 26-11-00. INFORMATION ON SECOND UNIT CHANGED WITH THE UNIT BELOW P/N FR2121 S/N 331.

Part: CONNECTOR — DIRTY (SMOKE DETECTOR)

NR 2 MAIN DECK CARGO SMOKE DETECTOR LIGHT FLICKERED DURING FLIGHT. CLEANED CONNECTOR ON SMOKE DETECTOR BOX OP'S CHECK OK PER MM 26-10-00.

Part: SMOKE DETECTOR — MALFUNCTIONED (MAIN DECK)

NR 5 MAIN DECK SMOKE DETECTOR ILLUMINATED AND REMAINED ON FOR APPROX 10 MINTUES COMPLIED WITH EMERGENCY PROCEDURES. PER TECH CENTER SWAPPED 5B AND 2B AND 5A AND 3A SMOKE DETECTORS PER AMM 26-14-02 AND OP'S CHECKED PER AMM 26-14-00 IN ZONE 5. OP'S CHECKED NORMAL. ALSO PLACED ON DMI 318 AS PER MEL 26-11 OPT 1 PLACARDS INSTALLED. RECONNECTED MAIN DECK SMOKE DETECTOR 2B. OP'S CHECK NORMAL PER MM 26-14-001 AND CLEARS DMI 317 PLACARDS REMOVED. RECONNECTED 3A MAIN CARGO DECK SMOKE DETECTOR OP'S CHECK NORMAL PER MM 26-14-001 AND CLEARS DMI 318 PLACARDS REMOVED.

Part: SMOKE DETECTOR — MALFUNCTIONED (CAARGO BAY)

NR 5 MAIN DECK SMOKE DETECTOR ILLUMINATED. VISUAL CHECK OF CARGO COMPARTMENT NO SMOKE NOTED. TROUBLE SHOT AND OP'S CHECK NR 5 CARGO SMOKE DETECTOR PER AMM26-14-00, OP'S CHECKED GOOD.

Part: FITTING — LOOSE (SMOKE DETECTOR)

EN ROUTE EDFH NR 5 MAIN DECK SMOKE DETECTOR ILLUMINATED. EMERGENCY PROCEDURES COMPLIED WITH. LANDED AT CYQX. CARGO AREA INSPECTED NO EVIDENCE OF SMOKE OR FIRE. NR 5 SMOKE DETECTOR INTAKE LINE FOUND LOOSE FITTING. TORQUED AND OPERATIONAL TEST OF MAIN DECK CARGO SYSTEM PERFORMED PER AMM 26-14-00 OPERATION NORMAL.

Part: SMOKE DETECTOR — FALSE ACTIVATION (CARGO BAY)

MAIN DECK CARGO FIRE ZONE 5 RED LIGHT ILLUMINATED-INTERMITTENT. ON GROUND PERFORMED MAIN DECK CARGO SMOKE DETECTOR SYS OP'S CHECK GOOD PER AMM 26-14-00

Part: SKIN — CORRODED (FUSELAGE) · airframe 110,874 hrs · 25,577 cycles

FWD CARGO PIT SKIN HAS CORROSION BS 1000 STR 40 TO 42 LT. REMOVED CORROSION, FABBED AND INSTALLED REPAIR DOUBLER PER B747 SRM 53-30-03 PGS 27-30.

Part: SKIN — CRACKED (R1 DOOR) · airframe 110,874 hrs · 25,577 cycles

R1 DOOR SKIN CRACK AT BS 480 WL 266. REMOVED DAMAGE FABBED AND INSTALLED REPAIR PER B747 SRM 52-10-02 FIG 9.

Part: FRAME — PUNCTURED (FUSELAGE) · airframe 110,874 hrs · 25,577 cycles

FWD CARGO PIT BS 720 RBL 60 HAS PUNCTURE IN FRAME WEB. REMOVED DAMAGED SECTION OF WEB, SPLICED IN NEW SECTION OF WEB AT STA 720 RBL 44-49 PER B747 SRM 53-10-04 FIG 30.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 110,874 hrs · 25,577 cycles

FWD CARGO FLOORBEAM BS 640 LBL HAS CORROSION UNDER NUT PLATE FWD SIDE OF T-CHORD. REMOVED CORROSION REPLACED T-CAP INSTALLED REPAIR ANGLES PER B747 SRM 51-40-04 FIG 2.

Part: SKIN — CRACKED (R1 DOOR) · airframe 110,874 hrs · 25,577 cycles

R1 DOOR SKIN CRACK AT BS 480 WL 210. REMOVED DAMAGE FABBED AND INSTALLED REPAIR PER B747 SRM 52-10-02 FIG 9.

Part: SKIN — CORRODED (FUSELAGE) · airframe 110,874 hrs · 25,577 cycles

FUSELAGE EXTERIOR SKIN BS 1000 STR 40L CORRODED. REMOVED CORROSION, NDT, FABBED AND INSTALLED REPAIR PER B747 SRM 53-30-03 FIG 12 AND 47.

Part: SKIN — CRACKED (FUSELAGE) · airframe 110,874 hrs · 25,577 cycles

BS 2060 ONE ROW OF FASTENERS ABOVE STR 45R HAS SKIN CRACK 1.5 INCH LONG BETWEEN AND PAST 2 FASTENERS. REMOVED DAMAGE, FABBED REPAIR DOUBLER AND FILLER AND INSTALLED PER B747 SRM 53-30-03 FIG 1.

Part: PANEL — CORRODED (NR 2 PYLON) · airframe 110,874 hrs · 25,577 cycles

NR 2 PYLON PANEL 462CL HAS CORROSION ON LOWER I/B SIDE OF PYLON IN EDGE RADIUS OF SPAR. REMOVED CORROSION AND REPAIRED PER ECRA 482-54-240-2.

Part: STRUCTURE — CORRODED (FUSELAGE) · airframe 110,874 hrs · 25,577 cycles

BS 1241 STR 14R AND 15R FWD SIDE HAS CORROSION. REMOVED CORROSION FABBED AND INSTALLED REPAIR PER SRM 53-30-03 FIG 47.

Part: FLOORBEAM — DAMAGED (FUSELAGE) · airframe 110,874 hrs · 25,577 cycles

UPPER DECK FLOOR BS 600 LBL TO LBL 77 TOP CAP ON FLOORBEAM HAS 6 EA DOUBLE DRILLED HOLES. REMOVED DAMAGE, FABBED REPAIR PARTS AND INSTALLED PER B747 SRM 53-10-07 FIG 21.

Part: SMOKE DETECTOR — FALSE ACTIVATION (CARGO BAY)

MAIN DECK CARGO SMOKE DETECTOR POSITION 4 ILLUMINATED. CONFIRMED NO SMOKE ON ENTIRE MAIN DECK. ACCOMPLISHED MAIN CARGO SMOKE DETECTOR SYS OP'S CHECK PER AMM 26-14-00 OP'S CHECK GOOD.

Part: FLOORBEAM — DAMAGED (FUSELAGE) · airframe 110,874 hrs · 25,577 cycles

FLOORBEAM UPPER CHORD INSERT DAMAGED AT BS 2220 BL 0. REMOVED DAMAGE, FABBED AND INSTALLED REPAIR PER B747 SRM 51-40-04 FIG 1.

Part: SKIN — CRACKED (R1 DOOR) · airframe 110,874 hrs · 25,577 cycles

R-1 DOOR SKIN BS 450 WL 259 HAS SKIN CRACKED AREA ABOVE UPPER HINGE DOUBLER REPAIR. REMOVED DAMAGED AREAS OF SKIN, FABBED REPAIR DOUBLER AND TRIPLER AND INSTALLED PER ECRA 482-52-250-2.

Part: SMOKE DETECTOR — FALSE ACTIVATION (CARGO BAY)

MAIN DECK CARGO SMOKE DETECTOR NR 5 SENSOR LIGHT CAME ON DURING CRUISE. VISUAL CHECK OF CARGO COMPARTMENT NO SMOKE NOTED. TROUBLESHOOT AND OP'S CHECKED NR 5 CARGO SMOKE DETECTOR PER AMM 26-14-00 OP'S CHECK GOOD.

Part: DOOR FRAME — DAMAGED (FUSELAGE) · airframe 110,874 hrs · 25,577 cycles

ELEVEN EACH DEFECTIVE HOLES AT STA 800 R2 DOOR FRAME. REAMED, CLEANED AND DEBURRED DISCREPENT HOLES PER B747 SRM 51-30-05 PG 6-9.

Part: FITTING — CORRODED (NR 4 PYLON)

NR 4 PYLON BOTH UPPER AND LOWER DUAL SIDE BRACE FITTINGS HAVE CORROSION IN THE BEARING MOUNT RACES. REPLACED DSB FITTINGS BEARING RACES PER EO 747-54-1804-05.

Part: LIGHT — INOPERATIVE (CABIN)

EMERGENCY LIGHT UPPER DECK LEFT SIDE CENTER AISLE INOP. REPAIRED LIGHT PER MFG. OHM 33-50-02 REV P.

Part: POWER SUPPLY — INOPERATIVE (FLASHLIGHT)

UPPER DECK FLASHLIGHT CHARGE LIGHT IS NOT FLASHING. ITEM TRANSFERRED TO DMI 289 25-21 DUE DATE 7-15-11 CAT D PLACARDS INSTALLED. REF DMI 289 UPPER DECK FLASHLIGHT CHARGE LIGHT IS NOT FLASHING. REMOVED AND REPLACED FLASHLIGHT POWER SUPPLY PER MM 25-64-00, OP'S CHECK GOOD. THIS CLEARS DMI 289 PLACARDS REMOVED.

Part: BATTERY — DISCHARGED (CABIN)

UPPER DECK AFT LEFT EMERGENCY LIGHT INOP. PLACED ON DMI 257 PER MEL 33-13 AFTER ONE FLIGHT OP'S CHECK NORMAL PER AMM 33-51-00 DMI CLEARED. NOTE: OP'S CHECK NORMAL AFTER RECHARGING BATTERY.

Part: LIGHT — INOPERATIVE (CABIN)

EMERGENCY LIGHT INOP, CEILING BS 2120-2140. REMOVED AND REPLACED EMERGENCY LIGHT ASSY IN CEILING AT BS 2120-2140 PER B747 MM 33-51-07 PG 201-202. OP'S CHECK GOOD.

Part: BATTERY PACK — DISCHARGED (CABIN)

UPPER DECK EMERGENCY SLIDE LIGHTS INOP. REMOVED AND REPLACED UPPER DECK SLIDE LIGHT BATTERY PACK AT 327 PER BOEING 747 MM 33-51-04 PG 203 ITEM 4 AND 5.

Part: ENGINE — MALFUNCTIONED (NR 2)

AT 3500 FEET NR 2 ENGINE HAD AN EPR, N1, EGT ROLLBACK AND ENGINE SHUT DOWN WITH OIL PRESSURE DROP BETWEEN 30 AND 35 PSI. ACCOMPANIED BY SEVERE ENGINE VIBRATION, ALL SIMULTANEOUSLY. REMOVED AND REPLACED NR 2 ENG PER EIA 7201, 7203, 7204, 7207 & 7209 OPS CK GOOD.

Part: FUEL CONTROL — MALFUNCTIONED (NR 2 ENGINE)

ON DESCENT FROM FL340 NR 2 ENGINE FAILED TO RESPOND TO THRUST LVR INPUT. NO RESPONSE AT FL300 TAT-18 PUT ANTI-ICE FUEL HEAT ON AT FL250 TAT-10 NO RESPONSE AT FL220 TAT-5, THRUST LVR STATED TO RESPOND NORMALLY TO INPUTS. ALL ENGINE PARAMETERS APPEARED NORMAL ON ALL ENGINES DURING DESCENT WITH THRUST LVR'S FULLY RETARDED. REMOVED AND REPLACED NR 2 ENGINE FUEL CONTROL, PER MM 73-21-01. REPLACED TTL PROBE PER MM 73-21-04.

Part: LIGHT — INOPERATIVE (CABIN)

ON PRE-FLIGHT FOUND EMERGENCY LIGHT OUT IN STAIRWELL DOME LIGHT ASSY. REMOVED AND REPLACED EMERGENCY LIGHT ASSY. OP'S CHECK NORMAL ON GROUND, REF MM 33-51-07 PAGE 203.

Part: DOOR FRAME — DAMAGED (FUSELAGE) · airframe 109,345 hrs · 25,234 cycles

DEFECTIVE HOLES AT RIGHT BS 2331 LOWER FORWARD R-5 DOOR CUTOUT. REMOVED DAMAGE, FABBED REPAIR PARTS AND INSTALLED PER ECRA 482-53-228-2.

Part: BULKHEAD — DAMAGED (PYLON) · airframe 109,345 hrs · 25,234 cycles

NR 3 PYLON FWD BULKHEAD FOUND 2 EA DEFECTIVE HOLES. FABBED FREEZE PLUGS TO REPAIR HOLES AND INSTALLED PER ECRA 482-54225-2.

Part: BULKHEAD — MISREPAIRED (PYLON) · airframe 109,345 hrs · 25,234 cycles

NR 3 PYLON AFT ENGINE MOUNT TORQUE BULKHEAD HAS DOUBLERS INSTALLED ON AFT SIDE OF THE BULKHEAD WHICH ARE NOT PER ANY AD OR S/B CONFIGURATION. REMOVED DOUBLERS, FABBED AND INSTALLED NEW REPAIR PARTS PER ECRA 482-54-229-2.

Part: BULKHEAD — CORRODED (LT MLG WW) · airframe 109,345 hrs · 25,234 cycles

LEFT WHEEL WELL 1241 BULKHEAD SKIN BETWEEN I/B LEG OF PICKLE FORK FITTING AND 1ST STIFFENER UPPER SECTION BEHIND HYD LINES CORRODED. REMOVED STIFFENER, REMOVED CORROSION, PRIMED AND RE-INSTALLED STIFFENER PER ECRA 482-57-230-2.

Part: BEAM — CORRODED (FUSELAGE) · airframe 109,345 hrs · 25,234 cycles

HORIZONTAL BEAM AT BS 340 LBL 22 WL 190 HAS CORROSION AND EXISTING CUT ABOUT 75 PERCENT THRU VERTICAL FLANGE. REMOVED AND REPLACED BEAM AT BS 340 LBL 22 WL 190 PER B747 SRM 51-30-02 PG 8 - 9.

Part: FUEL CONTROL — INOPERATIVE (NR 3 ENGINE)

NR 3 ENG LOSS OF THROTTLE COMMAND, RAPID RISE IN EPR, THROTTLE RETARDED TO IDLE BEFORE POWER REDUCED. REMOVED AND REPLACED NR 3 FUEL CONTROL UNIT PER MM 73-21-01, REMOVED AND REPLACED FUEL PUMP PER MM 73-11-01. ACCOMPLISHED HIGH POWER RUN UP PER MM 71-00-00 TEST 40, ALL OPS NORMAL.

Part: OIL SYSTEM — LEAKING (ENGINE) · airframe 107,378 hrs · 24,783 cycles

INFLIGHT SHUTDOWN OF ENGINE NR 1 FOR OIL LOSS. SERVICE ENG OIL, RAN AND INSPECTED ENG NR 1. FOUND OIL BEING BLOWN OUT OF RT 3.5 AND LT 3.5 UPPER BLEED VALVES. REPLACED NR 1 ENG EVC AND FILTER PER MM 75-31-09, 75-31-01. OPS CHECK NORMAL.

Part: FCU — MALFUNCTIONED (NR 4 ENGINE) · airframe 107,234 hrs · 24,756 cycles

DURING CRUISE, NR 4 ENGINE INDICATED LOSS OF THRUST. THRUST LEVER MOVEMENT CAUSED ALL ENG INDICATIONS TO FLUCTUATE. ENG NR 4 LEVER WAS REDUCED TO IDLE AN INFLIGHT START IAW COMPANY QRH PROCEDURES DURING DESCENT. S/D ENG NR 4 AS PRECAUTIONARY MEASURE DUE TO UNCOMMANDED THRUST INCREASE, EIDS SNAPSHOT WAS TAKEN OF ENG FLUCTUATION. ENG WINDMILLED FOR 30 MINUTES, OIL PRESSURE AT 10 PSI. REPLACED FCU/FUEL PUMP.

Part: BRACKET — BROKEN (CABIN) · airframe 106,970 hrs · 24,694 cycles

EMERGENCY EXIT LIGHT AT BODY STATION 2120 LT SIDE ABOVE L5 DOOR BRACKET BROKEN. LIGHT REMOVED. REMOVED THE BROKEN BRACKET AND INSTALLED NEW BRACKET ASSY 33-4-0045-93-1 AS PER DRWG 33-4-045-93-33-4-046-93 AND SRM 51-40-031.

Part: DOOR — CRACKED (MLG) · airframe 106,644 hrs · 24,623 cycles

AFTER ALL GEAR EXTENSIONS, BODY GEAR, LT AND RT, OUTBOARD SECONDARY DOORS STRUCK NR 5 AND NR 10 MWT ASSY WHILE CLOSING CAUSING DENTS AND CRACKS TO CONTACT AREA. CUT OUT OUTER SHIM AND EDGE FRAME PER SRM 52-80-01. FLUSH REPAIR THE EDGE FRAME PER SRM 51-40-03 REPAIR OUTER SKIN WITH 7075-T6 .63", 2024-T3 .53" PER SRM 52-40-01. SEALED REPAIR AND RESTORED THE FINISH PER SRM 51-10-06, AMM 51-21-00.

Part: NUT PLATE — CORRODED (CARGO DOOR) · airframe 105,915 hrs · 24,458 cycles

AFT CARGO DOOR 822D ACCESS PANEL NUT PLATE, AFT AREA FOUND CORROSION. AFT CARGO DOOR 822D ACCESS PANEL NUT PLATE, AFT AREA CORROSION REMOVED, FOUND BEYOND LIMITS. REPAIRED AS PER TEC-EVR-09-0004-05B AND EA-52-0064. REPAIR APPROVED THROUGH 8100-09 ISSUED BY BOEING.

Part: DOUBLER — CRACKED (FUSELAGE) · airframe 105,915 hrs · 24,458 cycles

FUSELAGE INTERNAL STRUCTURE UPPER LOBE DOUBLER AT BS 2517 STR 3R FOUND CRACK. STA 2517 RT SIDE CORROSION CLEARED AND CRACK STOP HOLE DRILLED. REINFORCEMENT DOUBLERS INSTALLED REF TEC-EVR-09-0002-10B STA 2517 LT SIDE, REINFORCEMENT DOUBLERS INSTALLED REF EC-EVR-09-0002-10B AND EA 53-1234. REPAIR APPROVED THROUGH 8100-9 ISSUED BY BOEING.

Part: STRINGER — CRACKED (FUSELAGE) · airframe 105,915 hrs · 24,458 cycles

STA 260 TO 280 STR 41L FOUND CRACK. STA 260 TO 280 STR 41L REPAIRED AS PER BOEING DWG 65B07658 AND B747 SRM 51-30-02.

Part: SEAT TRACK — CRACKED (FUSELAGE) · airframe 105,915 hrs · 24,458 cycles

MAIN DECK STA 495 TO 497, WL 200 LBL 11.33 SEAT TIE DOWN TRACK CRACKED. MAIN DECK STA 495 TO 497, WL 200 LBL 11.33 SEAT TIE DOWN TRACK CRACK REPAIRED PER BOEING DWG 65B11247 SHT 2 AND B747 SRM 51-30-02.

Part: FLOOR SUPPORT — CRACKED (FUSELAGE) · airframe 105,915 hrs · 24,458 cycles

BULK CARGO COMPT, BS 1980, LBL 40 FLOOR SUPPORT CRACKED. BULK CARGO COMPT, BS 1980, LBL 40 FLOOR SUPPORT REPAIRED PER SRM 53-10-07 FIG 20.

Part: POWER SUPPLY — FAILED (EMERGENCY LIGHTS) · airframe 105,915 hrs · 24,458 cycles

UPPER DECK RT DOOR EXIT LIGHT'S POWER PACK FOUND FAILED. REMOVED AND REPLACED POWER PACK AND CARRIED OUT OPS CHECK OF DOOR EXIT LIGHT, FOUND SATISFACTORY AS PER MM 33-51-00.

Part: SHEAR TIE — CRACKED (FUSELAGE) · airframe 105,915 hrs · 24,458 cycles

MAIN DECK RT SIDEWALL BS 2140, STR 20R TO 22R FRAME SHEAR TIE CRACKED. MAIN DECK RT SIDEWALL BS 2140, STR 20R TO 22R FRAME SHEAR TIE REMOVED AND REPLACED PER BOEING DWG 365B03146 AND SRM 51-30-02.

Part: FLOOR SUPPORT — CRACKED (FUSELAGE) · airframe 105,915 hrs · 24,458 cycles

BULK CARGO COMPT, BS 1960 LBL 40 FLOOR SUPPORT CRACKED. BULK CARGO COMPT, BS 1960 LBL 40 FLOOR SUPPORT REPAIRED AS PER SRM 53-10-07 FIG 20.

Part: BULKHEAD — CRACKED (BS 2160) · airframe 105,915 hrs · 24,458 cycles

LOWER COMPARTMENT STA 2160 STR L46 TO STR L47 WEB CRACKED. LOWER COMPARTMENT STA 2160 STR L46 TO STR L47 BULKHEAD WEB REPAIRED AS PER BOEING DWG 65B04345-2 B747 SRM 51-30-02.

Part: SEAT TRACK — CORRODED (FUSELAGE)

MAIN DECK BS 510-520, LBL 11 SEAT TRACK CORRODED BEYOND LIMITS. ORIG THICKNESS 0.090" REMAINING, 0.025" REMOVED DAMAGED TIE DOWN TRACK AS PER SRM 51-30-02, FABRICATED NEW TRACK PER BOEING DWG 65B38260 SHT 1 AND INSTALLED PER SRM 51-30-02.

Part: SEAT TRACK — CRACKED (FUSELAGE) · airframe 105,915 hrs · 24,458 cycles

BS 570 TO 580 WL 120, BL 25R, SEAT TIE DOWN CRACKED IN FWD COMPARTMENT. FWD CARGO BS 570 TO 580 WL 120, BL 25R, SEAT TIE DOWN REMOVED AND REPLACED PER B747 SRM 53-10-05.

Part: SHEAR TIE — CRACKED (FUSELAGE) · airframe 105,915 hrs · 24,458 cycles

BS 2080 STR 20R TO 22R, FRAME SHEAR TIE FOUND CRACKED. M/D, RT SIDEWALL BS 2080 FRAME SHEAR TIE REMOVED AND REPLACED PER BOEING DWG 69B03146 AND SRM 51-30-20.

Part: FRAME — CRACKED (FUSELAGE) · airframe 105,915 hrs · 24,458 cycles

DISCHARGE COMPARTMENT BS 2200 STR 43R-45R FRAME UPPER CHORD CRACKED. DISCHARGE COMPARTMENT BS 2200 STR 43R-45R FRAME UPPER CHORD CRACKED AREA REMOVED AND REPLACED PER BOEING DWG 65B04347 AND SRM 51-30-02.

Part: FRAME — CRACKED (FUSELAGE) · airframe 105,915 hrs · 24,458 cycles

BULK CARGO AREA, BS 2200, STR 42R - 44R FRAME CRACKED. BULK CARGO AREA, BS 2200, STR 42R - 44R FRAME REMOVED AND REPLACED PER DWG 65B04347 AND SRM 51-30-02.

Part: FRAME — CRACKED (FUSELAGE) · airframe 105,915 hrs · 24,458 cycles

BS 2220 STR 24L TO 26L WL 200-210 FRAME CRACKED. MAIN DECK BS 2220 LT STR 24L TO 26L WL 200-210 FRAME REMOVED AND REPLACED AS PER DWG 65B04348 AND SRM 53-10-04 FIG 100.

Part: SKIN — CORRODED (BS 2710-2720) · airframe 105,915 hrs · 24,458 cycles

FUSELAGE SKIN BS 2710-2720 CROWN AREA BULDGE. CORRECTIVE ACTION- FUSELAGE SKIN BULDGE AREA AT STA. 2710-2720 STR. L2 TO STR. L1 TRIMMED OFF AND REPAIRED AS PER SRM 53-30-03 FIG 4.

Part: SHEAR TIE — CRACKED (FUSELAGE) · airframe 105,915 hrs · 24,458 cycles

MAIN DECK BS 1220 RT SIDE BETWEEN STR 22 AND STR 23 FRAME SHEAR TIE CRACKED. MAIN DECK BS 1220 RT SIDE BETWEEN STR 22 AND STR 23 FRAME SHEAR TIE REMOVED AND REPLACED AS PER BOEING DWG 69B02791 AND B747 SRM 51-30-02.

Part: SHEAR TIE — CRACKED (BS 1180) · airframe 105,915 hrs · 24,458 cycles

BS 1180 LT SIDEWALL BETWEEN STR 22L AND STR 23L SHEAR TIE CRACKED. REMOVED AND REPLACED AS PER DRWG. 69B02791 AND SRM 51-30-02.

Part: SHEAR TIE — CRACKED (FUSELAGE) · airframe 105,915 hrs · 24,458 cycles

MAIN DECK BS 1080 RT SIDE WALL BETWEEN STR 22R AND STR 23R FRAME SHEAR TIE CRACKED. MAIN DECK BS 1080 RT SIDE WALL BETWEEN STR 22R AND STR 23R FRAME SHEAR TIE REMOVED AND REPLACED AS PER B747 SRM 51-30-02 AND BOEING DWG 69B02791.

Part: SHEAR TIE — CRACKED (FUSELAGE) · airframe 105,915 hrs · 24,458 cycles

MAIN DECK STA 2000 FRAME BETWEEN STR 4R AND 5R SHEAR TIE CRACKED. FABRICATED MAIN DECK STA 2000 FRAME BETWEEN STR 4R AND 5R SHEAR TIE AS PER BOEING DWG 65B09123 SHT 1 AND INSTALLED AS PER B747 SRM 51-30-02.

Part: SHEAR TIE — CRACKED (FUSELAGE) · airframe 105,915 hrs · 24,458 cycles

MAIN DECK BS 1220 LT SIDEWALL BETWEEN STR 22L AND STR 23L FRAME SHEAR TIE CRACKED. MAIN DECK BS 1220 LT SIDEWALL BETWEEN STR 22L AND STR 23L FRAME SHEAR TIE REMOVED AND REPLACED AS PER SRM 51-30-02 AND BOEING DWG 69B02791.

Part: FLOOR SUPPORT — CRACKED (BAS 1940) · airframe 105,915 hrs · 24,458 cycles

BULK CARGO COMPARTMENT STA 1940 LBL 55 HAT SECTION FLOOR SUPPORT UPPER SURFACE CRACKED. REMOVED AND REPLACED AS PER SRM 53-10-07 FIG. 20.

Part: SKIN — DENTED (FUSELAGE) · airframe 105,915 hrs · 24,458 cycles

FUSELAGE SKIN STA 2730 LT WL 36B FOUND DENT. FUSELAGE SKIN DENT AT BS 2730 WL 36B TRIMMED OFF AND REPAIRED AS PER B747 SRM 53-30-03.

Part: SHEAR TIE — CRACKED (FUSELAGE) · airframe 105,915 hrs · 24,458 cycles

MAIN DECK RT SIDEWALL BS 2120, STR 20R TO 22R FRAME SHEAR TIE CRACKED. MAIN DECK RT SIDEWALL BS 2120, STR 20R TO 22R FRAME SHEAR TIE REMOVED AND REPLACED AS PER BOEING DWG 69B03416 AND SRM 51-30-02.

Part: FRAME — CRACKED (BS 2180) · airframe 105,915 hrs · 24,458 cycles

MAIN DECK LT SIDE WALL BS 2180 S 25L FRAME CRACKED. REPAIRED AS PER SRM 53-30-029 AND 53-10-04.

Part: LIGHT — LOOSE (COCKPIT) · airframe 103,237 hrs · 23,876 cycles

DURING DESCENT, ABOUT 30 MILES OUT, 2 VISIBLE PUFFS OF SMOKE WITH ASSOCIATED ELECTRICAL ODOR UNDER F/OS GLARESHIELD. HAPPENED 2 TIMES WITHIN A 3 MINUTE PERIOD. AIRCRAFT OPERATED 15 ADDITIONAL MINUTES UNTIL LANDING WITHOUT FURTHER OCCURRENCE. ALL SYSTEMS OPERATED NORMALLY, NO C/BS TRIPPED. MAINTENANCE REMOVED F/O INSTRUMENT PANEL AND INSPECTED ALL WIRING AND ALL COMPONENTS FOR LOOSE OR DAMAGED ITEMS. NO SMOKE OR FUMES NOTED. INSPECTED FLUORESCENT LIGHT AND SURROUNDING AREA AND FOUND IT LOOSE AND SMOKE ODOR IN THAT AREA. THE LIGHT WAS DEFERRED AND ITS C/B PULLED AND COLLARED.

Part: BULB — NO TEST (EMERGENCY LIGHTS) · airframe 102,981 hrs · 23,817 cycles

R5 DOOR EMERGENCY EXIT AFT SILL LIGHT INOP. RELAMPED R5 EMERGENCY EXIT AFT SILL LIGHT PER 33-51-00. OPS CHECKED NORMAL.

Part: GUIDE VANE — SEPARATED (NR 2 ENGINE) · airframe 102,966 hrs · 23,812 cycles

ON WALK AROUND, FOUND NR 2 ENG FAN EXIT GUIDE VANE EXITED ENGINE AND DAMAGED LT INBOARD MID TRAILING EDGE FLAP. REMOVED DAMAGED GUIDE VANE AND PLACED ENGINE ON COI NR 114, AND REPLACED MID FLAP, OPS CHECKED GOOD.

Part: SKIN — DAMAGED (BS 1320) · airframe 102,521 hrs · 23,706 cycles

EXTERNAL SKIN AT BS 1320 HAS ELONGATED FASTENER HOLES JUST 4" AFT OF R3 DOOR CUT-OUT. REPAIRED EXTERNAL SKIN AT BS 1324 FASTENER HOLE AFT OF R3 DOOR CUT-OUT PER ECRA 482-53-220-2.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 102,521 hrs · 23,706 cycles

CREW SERVICE DOOR GROUND/SLIDE LIGHTS INOP MOUNTED ON DOOR JAMB. REMOVED AND REPLACED EMERGENCY BATTERY PACK PER B747 MM 33-51-04. OPS CHECKED NORMAL PER B747 MM 33-51-04 PAGE 204.

Part: LIGHT — NO TEST (SERVICE DOOR) · airframe 101,719 hrs · 23,532 cycles

BOTH CREW SERVICE DOOR EMERGENCY SILL LIGHTS INOP. REPLACED BATTERY PACK REF 33-51-00 PAGE 201. SYS OPS CKS NORMAL REF MM 33-51-00 PAGE 501.

Part: SUPPORT BEAM — CORRODED (RT WING) · airframe 101,270 hrs · 23,435 cycles

RT WING INBOARD LEADING EDGE SUPPORT BEAM FOUND WITH EXFOLIATION CORROSION. REMOVED SUPPORT BEAM HFEC INSPECTION CARRIED OUT ON CUT OUT AREA. NIL CRACKS NOTED. REPAIR CARRIED OUT PER N482EV-07-0004/SRM 51-40-04.

Part: SKIN — DEBONDED (FUSELAGE) · airframe 101,270 hrs · 23,435 cycles

FOUND FUSELAGE SKIN FWD OF STA 2460 BETWEEN 17L AND 18L DISBONDED APPROX 2"X". REPAIR CARRIED OUT PER N482EV-07-0006(SRM53-30-04 FIG 3)APPROVED PER BOEING MESSAGE 1-310403476-4.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 101,701 hrs · 23,435 cycles

FOUND STRINGER CORRODED AT CENTER ELECTRONIC COMPARTMENT CUTOUT AREA BS760-780 STRINGER 47L. DAMAGED SECTION OF STRINGER CUT AND REMOVED. REPAIR SPLICE SECTION FABRICATED PER SRM 53-10-03 FIG 1. REPAIR PARTS INSTALLED PER SRM 51-30-02 & 53-10-03 FIG 1.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 101,270 hrs · 23,435 cycles

STRINGER FOUND CORRODED AT STA 800 STRINGER 45L. DAMAGED SECTION OF STRINGER CUT AND REMOVED FABRICATED SPLICE SECTION PER SRM 53-10-03 REPAIR PARTS INSTALLED PER SRM 51-30-02/SRM 53-10-03 FIG 1.

Part: SKIN — CORRODED (FUSELAGE) · airframe 101,270 hrs · 23,435 cycles

EVIDENCE OF CORROSION FOUND AT STA 810, WL 91 BETWEEN S45R AND S46R. CORROSION REMOVED AS PER SRM 51-10-01 FOUND OUT OF LIMITS PER SRM 53-30-01. CARRIED OUT REPAIRS PER N482EV-07-003(BOEING 1-307245973)

Part: STRINGER — DAMAGED (FUSELAGE) · airframe 101,270 hrs · 23,435 cycles

FOUND STRINGER 24A BODY STATION 140-190 WITH OVERSIZE HOLES. REMOVED STRINGER AND FABRICATED AND INSTALLED PER B747 SRM 53-10-03.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 101,270 hrs · 23,435 cycles

FOUND STRINGER 47L BETWEEN BS 740 TO BS 780 CORRODED. DAMAGED SECTION OF STRINGER CUT AND REMOVED. SPLICE SECTION FABRICATED PER SRM 53-10-03 REPAIR PARTS INSTALLATION CARRIED OUT PER B747 SRM 51-30-02 & 53-10-03 FIG 1.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 101,270 hrs · 23,435 cycles

FOUND STRINGER CORRODED AT CEC CUTOUT AREA BS 760-780 STR 47L. DAMAGED SECTION OF STRINGER CUT AND REMOVED. FABRICATED PER SAMPLE. REPAIR SECTION FABRICATED PER SRM 53-10-03 FIG 1. REPAIR PARTS INSTALLATION CARRIED OUT PER B747 SRM 51-30-02, SRM 53-10-03 FIG1.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 101,270 hrs · 23,435 cycles

FOUND DOOR 5R CEILING EMERGENCY LIGHT INOPERATIVE. DOOR 5R CEILING EMERGENCY ASSY AND BATTERY ASSY REPLACED AND CHECKED SATISFACTORY PER B747 MM 33-51-00.

Part: FRAME — DAMAGED (FUSELAGE) · airframe 101,270 hrs · 23,435 cycles

NOSE GEAR WELL STA 340, LEFT WL 150 FOUND BASE AND HOLES DAMAGED 1/2" BY 1/2" BEYOND SRM 53-10-01 PAGE 3 FIG 1 LIMIT. CHORD FABRICATED BY WORKSHOP INSTALLED PER BOEING 747 SRM 51-30-02.

Part: KEELBEAM — CRACKED (FUSELAGE) · airframe 101,270 hrs · 23,435 cycles

WEB CRACKED NEAR RIVET HOLE AT STA 1002 KEEL BEAM LT SIDE SECOND ROW OF RIVETS. KEEL BEAM WEB REPAIRED PER SRM 53-10-09 FIG 4.

Part: SHEAR TIE — CRACKED (FUSELAGE) · airframe 101,270 hrs · 23,435 cycles

FOUND FRAME SHEAR TIE AT BODY STATION 220 BETWEEN STRINGER 30L AND 29L CRACKED. SHEAR TIE REMOVED AND FABRICATED PER SRM 53-10-04 INSTALLED PER SRM 51-30-02.

Part: SHEAR TIE — OUT OF LIMITS (FUSELAGE) · airframe 101,270 hrs · 23,435 cycles

FOUND FRAME SHEAR TIE AT BODY STATION 200-220 BETWEEN STRINGER 35L & 34L WITH TOO LARGE A GAP TO NEW SKIN REPLACEMENT. FABRICATED SHEAR TIE PER B747 SRM 53-10-04 INSTALLED PER SRM 51-30-02.

Part: SHEAR TIE — CRACKED (FUSELAGE) · airframe 101,270 hrs · 23,435 cycles

FOUND FRAME SHEAR TIE AT BS 180 BETWEEN STRINGER 34L AND 35L CRACKED. SHEAR TIE REMOVED AND FABRICATED PER SRM 53-10-04 AND INSTALLED PER SRM 51-30-02.

Part: STRINGER — DAMAGED (FUSELAGE) · airframe 101,270 hrs · 23,435 cycles

FOUND STRINGER 28AL BETWEEN BODY STATION 180-200 WITH OVERSIZED HOLES. REMOVED STRINGER 28AL FROM BODY STATION 180-200. FABRICATED PER B747 SRM 53-10-03 FIG 3.

Part: SEAT TRACK — DAMAGED (FUSELAGE) · airframe 101,270 hrs · 23,435 cycles

STA 543 SEAT TRACK DAMAGED AT RBL 11. SEAT TRACK REMOVED AND SENT TO WORKSHOP FOR CROWN AND FLANGE TRIMMING. PRIMER APPLIED. SEAT TRACK INSTALLED AS PER B747 SRM 51-30-02, SRM 53-10-05 FIG 4.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 101,270 hrs · 23,435 cycles

SEAT TRACK FOUND CORRODED AT LBL11 STA 470. SEAT TRACK REMOVED AS PER B747 SRM 51-30-02. SEAT TRACK TRIMMED AND PRIMER APPLIED AS PER B747 SOPM 20-41-02. SEAT TRACK INSTALLED PER B747 SRM 53-10-05 FIG 4.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 101,270 hrs · 23,435 cycles

SEAT TRACK FOUND CORRODED AT LBL 11 STA 470. SEAT TRACK REMOVED AS PER SRM 51-30-01. SEAT TRACK TRIMMED AND PRIMER APPLIED PER SOPM 20-41-01. SEAT TRACK INSTALLED PER SRM 53-10-05 FIGURE 4.

Part: ATTACH FITTING — CORRODED (WING) · airframe 101,270 hrs · 23,435 cycles

NUMBER 4 FLAP TRACK FWD FITTING MATING SURFACE OF BEARING FOUND WITH PITTING CORROSION. BEARING REMOVED AS PER SB 747-57-2325 FIG 30. FITTING HOLE FOUND PITTED AND BORING ACCOMPLISHED PER SB 747-57-2325 STEP 7. CARRIED OUT FPI NIL CRACKS FOUND. CHAMFER CARRIED OUT PER SB 747-57-2325 STEP 15 & 16. FOUND SATISFACTORY. FABRICATED BUSHING PER SB 747-57-2262 FIG 13 CADMIUM PLATED BUSHING AND INSTALLED.

Part: SPAR — CORRODED (LT WING) · airframe 101,270 hrs · 23,435 cycles

CORROSION FOUND AT TOP CHORD ASSY AT LT WING IN FRONT OF SPOILER NR 5 & NR 6. BEAM ASSY UPPER "T" CHORD REMOVED FROM WBL 285-WBL345. FABRICATED AS PER SRM 51-40-04 FIG 3. REPAIR CARRIED OUT PER B747 SRM 51-40-04 FIG 3.

Part: SHEAR TIE — MISINSTALLED (BS 240) · airframe 101,270 hrs · 23,435 cycles

FOUND FRAME SHEAR TIE AT BODY STATION 240 BETWEEN STRINGER 34A AND 36 WITH TOO BIG A GAP AFTER SKIN REPLACEMENT. SHEAR TIE REMOVED AND FABRICATED PER B747 SRM 53-10-04, INSTALLED PER SRM 51-30-02.

Part: LAMP — INOPERATIVE (SMOKE DETECTOR) · airframe 101,153 hrs · 23,411 cycles

NR 4 LOWER AFT SMOKE DETECTOR WILL NOT TEST. RELAMPED PER 12-16-02, OPS CHK GOOD.

Part: LAMP — INOPERATIVE (SMOKE DETECTOR) · airframe 100,964 hrs · 23,370 cycles

NR 4 AFT SMOKE DETECTOR INOP, LP 259652. RELAMPED NR 4 AFT SMOKE DETECTOR PER MM 26-16-02.

Part: SIGN — INOPERATIVE (EMERGENCY LIGHTS) · airframe 100,854 hrs · 23,347 cycles

FOUND DOOR 5R AND 5L EXIT IDENTIFIER SIGNS INOP. REMOVED AND REPLACED POWER SUPPLY IAW MM 33-51-00 PG 9, OPS CHECKED GOOD.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 100,854 hrs · 23,347 cycles

FOUND EMERGENCY LIGHT ON DOOR 5L INOP. REMOVED AND REPLACED LIGHT ASSEMBLY IAW MM33-51-00 PG 501, CHECKED NORMAL.

Part: LIGHT — BURNED OUT (ZONE 200)

UPPER DECK LEFT EMERGENCY EXIT LIGHT WILL NOT TEST. REPLACED EMERGENCY EXIT LIGHT ASSY PER 747 MM 33-51-09, PG 401. OP CHECKS GOOD. DO NOT SUBMIT PENDING A/C TIMES.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 100,453 hrs · 23,200 cycles

UPPER DECK EMERGENCY LIGHT AT TOP OF STAIRS INOP. REPLACED UPPER DECK STAIRS EMERGENCY LIGHT ASSY IAW MM 33-51-50 PAGE 201, OPS CHECKED OK IAW 33-51-00 PG 501.

Part: SKIN — CORRODED (FUSELAGE) · airframe 100,173 hrs · 23,182 cycles

LOWER FUSELAGE BS 1860, STR 51R HAS CORROSION IN SKIN. REMOVED CORROSION, FABBED AND INSTALLED DOUBLER PER B747 SRM 53-30-03 FIG 1.

Part: SKIN — CRACKED (L1 DOOR) · airframe 100,173 hrs · 23,182 cycles

L-1 DOOR SKIN CRACKED IN LOWER AFT CORNER APPROX 12 INCHES FWD OF AFT EDGE EXTENDING FROM FASTENER HOLES. CUT OUT DAMAGE, FABBED AND INSTALLED REPAIR PER B747 SRM 52-10-02, FIG 9.

Part: SKIN — CORRODED (FUSELAGE) · airframe 100,173 hrs · 23,182 cycles

LOWER FUSELAGE BS 1840 STR 49R HAS SKIN CORROSION. REMOVED CORROSION FABBED AND INSTALLED DOUBLER REPAIR PER B747 SRM 53-30-03 FIG 1.

Part: FITTING — CRACKED (FUSELAGE) · airframe 100,173 hrs · 23,182 cycles

LOWER BATHTUB FITTING CRACKED AT BODY STATION 1000 BELOW STRINGER 38L IN FWD BAG PIT. REMOVED AND REPLACED BATHTUB FITTING PER B747 SRM 51-30-02 PG 8, 9 & 51-30-04 PG 1-9 & EO 53-747-1072-90 REV B, PART 4.

Part: CHARGER — INOPERATIVE (EMERGENCY LIGHTS) · airframe 100,056 hrs · 23,157 cycles

CREW EXIT EMERGENCY SILL LIGHTS BOTH INOP. BATTERY CHARGER AND BATTERY PACK BOTH REPLACED PER MM 33-51-00 PAGE 201.

Part: PRESSURE SWITCH — MALFUNCTIONED (ENGINE OIL) · airframe 100,012 hrs · 23,147 cycles

DURING CRUISE NR 4 ENG OIL PRESS LIGHT CAME ON, NO OTHER SYSTEM MALFUNCTION NOTED, RAN CHECKLIST. LIGHT WENT OUT BUT LATER CAME ON INTERMITTENTLY, DIVERTED TO JFK. REPLACED LOW OIL AND DIFF PRESS SWITCHES, NO HELP. SAME OCCUPANCY NEXT FLIGHT, TIGHTENED TERMINALS ON LIGHT ASSY MOD. SYSTEM DEFERRED AND REQUIRES FURTHER TROUBLESHOOTING.

Part: CIRCUIT CARD — ODOR · airframe 98,928 hrs · 22,915 cycles

WHILE TROUBLESHOOTING NR 2 COMPASS HAD A STRONG ODOR OF ELECTRICAL BURNING COMING FROM FLIGHT DECK. FOUND MASTER DIM AND TEST CARD NR 7 AT FAULT REPLACED PER 33-11-01, OPS CHK OK.

Part: PRESSURE PANEL — CRACKED (NLG WW) · airframe 98,843 hrs · 22,896 cycles

DURING CHECK, NOSE WHEEL WELL TOP PANEL FOUND WEB CRACKED APPROX 2 INCHES. CRACK REPAIRED PER SRM 53-10-04, FIG 119.

Part: INDICATOR — INOPERATIVE (ELEVATORS) · airframe 988,065 hrs · 22,888 cycles

PRIOR TO TAKEOFF, AIRCRAFT RECEIVED A WARNING INDICATION FOR LT ELEV, VERIFIED OPERATION AND INDICATOR INOP. REPLACED SPI INDICATOR, OPS CHK GOOD PER MM 27-48-00.

Part: BULB — INOPERATIVE (INDICATOR)

FWD LOWER CARGO SMOKE DETECTOR NR 2 TEST INOP. RELAMPED TEST BULB. OPS CHK GOOD PER MM CH 26-15-00.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 984,048 hrs

UPPER DECK RIGHT SIDE EMERGENCY LIGHT FOUND INOP. REPLACED LIGHT ASSY PER MM 33-57-00, OPS CHECK GOOD.

Part: CIRCUIT BREAKER — MALFUNCTIONED (STROBE) · airframe 983,006 hrs

DURING FLIGHT, CREW SMELLED SMOKE IN COCKPIT AND NOTED THE NAV TAIL LIGHT AND BEACON STROBE C/B`S HAD POPPED. UPON ARVL AT LICZ, REMOVED AND REPLACED BOTH C/B`S IAW MM33-44-01, 33-44-03 AND MM33-43-01, OP TEST GOOD PER THE ABOVE MM.

Part: SWITCH — FAILED (EXTERIOR LIGHTS) · airframe 98,127 hrs · 22,742 cycles

DEPARTING JFK FOR DOV, DURING TAKEOFF THROUGH 400 FT, ELECTRICAL BURNING/SMOKE ODOR IN COCKPIT. STRONG ODOR FOR 2 TO 5 MINUTES. FOUND DEFECTIVE WING ILLUMINATION LIGHT SWITCH, DFRL DMI 607 PER MEL 33-10 REMAINS OPEN PENDING CORRECTIVE ACTION.

Part: SKIN — MISDRILLED (BS 180) · airframe 98,085 hrs · 22,731 cycles

MISDRILLED FASTENER HOLE IN EXTERNAL FUSELAGE SKIN AT STR 36L, BS 180. REMOVED DAMAGE, FABRICATED AND INSTALLED REPAIR PER ECRA 482-53-213-2.

Part: SKIN — GROUND DAMAGE (BS 160-220) · airframe 98,085 hrs · 22,731 cycles

DAMAGE FROM IMPACT BY GROUND EQUIPMENT AT BS 160-220, STR 23L-34L. DAMAGE REMOVED, COMPONENTS FABRICATED AND INSTALLED TO REPAIR PER ECRA 482-53-213-2, RVSM INSPECTION COMPLIED WITH PER EO 53=747-1453-96, REV A.

Part: CSD — FAILED (NR 1) · airframe 98,060 hrs · 22,726 cycles

PERFORMED INFLIGHT ENGINE SHUTDOWN DUE TO FAILURE OF NR 1 CSD TO DISCONNECT. FL 290, TAT -17, SAT -47, 312 KTS, .81 MACH, 11:08Z OIL PRESS 20 PSI, OIL TEMP 78 DEG C, DURATION 2:08. PMG VOLTS 52, N1 30 PERCENT, CSD RPM 520, N2 27 PERCENT. DFRL DMI 572 PER MEL 24-1-M, CAT "C" DUE 12/28/05. CSD AND GENERATOR REMOVED PER MM 24-11-0. (ENGINE TSOH 4656.3 CSOH 1004) PLACARD INSTALLED. REMAINS OPEN UNTIL DMI CLEARED.

Part: SKIN — CRACKED (NR 2 PYLON) · airframe 97,556 hrs · 22,612 cycles

NR 2 PYLON 463EL ACCESS PANEL CUTOUT SKIN CRACKED ON THE STRIKER PAD TWO FASTENER HOLES. NR 2 PYLON 463EL ACCESS PANEL CUT OUT SKIN REPAIR CARRIED OUT IAW SRM 54-30-03 FIG 7B.

Part: SKIN — CRACKED (NR 4 PYLON) · airframe 97,556 hrs · 22,612 cycles

NUMBER 4 PYLON SKIN CRACKED AT ACCESS PANEL 483CL CUTOUT HINGE ATTACH FASTENER HOLE. NUMBER 4 PYLON 483CL ACCESS PANEL CUTOUT SKIN REPAIR CARRIED OUT IAW SRM 54-30-03 FIG 17B.

Part: SKIN — CRACKED (FUSELAGE) · airframe 97,556 hrs · 22,612 cycles

FX SKIN BS 2598 BETWEEN S-42R AND S-46R JUST BELOW TAIL JACK SKIN CRACKED. FX SKIN BS 2588-2589 BETWEEN S-42R AND S-46R SKIN REPAIR CARRIED OUT IAW SRM 53-30-03 FIG 1A.

Part: PUMP — LEAKING (HYD SYSTEM) · airframe 96,816 hrs · 22,456 cycles

NR 1 HYD SYS SLOWLY LOST HYD QUANTITY AT TO GAGE SHOWED 9 GAL. GAGE SHOWED SLOW LOSS APPROX 2 HRS AFTER T/O. DID LEAK/LOSS PROCEDURES BUT LEAK CONTINUED, SYSTEM DEPRESSURIZED AND ADP OFF REMAINDER OF FLIGHT. REMOVED AND REPLACED NR 1 ENG HYDRAULIC PUMP PER MM 29-11-05 OPS AND LEAK CHECK OK. FOUND HYD PUMP LEAKING AT PARTING SURFACE.

Part: LIGHT — INOPERATIVE (STA 405) · airframe 96,626 hrs · 22,413 cycles

UPPER DECK EMERGENCY LIGHT AT LOCATION STA 405 INOP. LIGHT ASSY REPLACED PER MM 33-51-00 OPS CKD OK.

Part: SHEAR TIE — CRACKED (FUSELAGE) · airframe 96,389 hrs · 22,361 cycles

M/D BS 1920 STRINGER 4R TO 5R, SHEAR TIE FOUND CRACKED. CRACKED SHEAR TIE REPLACED PER SRM 51-10-01

Part: STRAP — CRACKED (FUSELAGE) · airframe 96,389 hrs · 22,361 cycles

M/D RT BS 800 FRAME STRAP BETWEEN STRINGER 25R AND 26R FRAME INNER CHORD STRAP FOUND CRACKED. RT BS 800 FRAME STRAP BETWEEN STRINGER 25R AND 26R, DOUBLER REPAIRED PER SRM 51-40-01, FIG 1.

Part: SHEAR TIE — CRACKED (FUSELAGE) · airframe 96,389 hrs · 22,361 cycles

M/D BS 1800 STRINGER 4R TO 5R SHEAR TIE FOUND CRACKED. CRACKED SHEAR TIE REPLACED PER SRM 51-10-01.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 96,389 hrs · 22,361 cycles

M/D BS 1000, LBL 33, SEAT TRACK OUTBOARD FLANGE FOUND CORROSION. M/D BS 990 TO BS 1000, LBL 33, SEAT TRACK SECTIONAL REPLACED PER SRM 53-10-05 FIG 1A.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 96,389 hrs · 22,361 cycles

CORROSION REVEALED ON UPPER DECK FLOORBEAM, UPPER CHORD AT BS 420 RBL 68, PER ATTACH FIG. UPPER DECK BEAM, UPPER CHORD REPAIRED PER SB 747-53A2452.

Part: SHEAR TIE — CRACKED (FUSELAGE) · airframe 96,389 hrs · 22,361 cycles

M/D BS 1820 STRINGER 4R TO 5R SHEAR TIE FOUND CRACKED. CRACKED SHEAR TIE REPLACED PER SRM 21-10-01.

Part: SHEAR TIE — CRACKED (FUSELAGE) · airframe 96,389 hrs · 22,361 cycles

M/D STA 1880 RT STRINGER 4 TO 5, SHEAR TIE FOUND CRACKED. CRACKED SHEAR TIE REPLACED PER SRM 51-10-01, P 9.

Part: SEAT TRACK — BROKEN (FUSELAGE) · airframe 96,389 hrs · 22,361 cycles

M/D BS 1883 RBL 11, SEAT TRACK FLANGE FOUND BROKEN. M/D BS 1870 TO BS 1950 RBL 11, SEAT TRACK REPAIRED PER SRM 53-10-05, FIG 14.

Part: BULKHEAD — CORRODED (FUSELAGE) · airframe 96,389 hrs · 22,361 cycles

FX BS 1480 KEEL BEAM BOX BULKHEAD, FWD FACE BETWEEN RBL2 AND LBL2, FOUND CORROSION. REPAIRED PER HAECO REPAIR SCHEME R-53-49-35300.

Part: RIB — CRACKED (LT WING) · airframe 96,389 hrs · 22,361 cycles

LT WING SURGE TANK WS 1516, RIB LOWER CHORD AT STRINGER 6 AREA FOUND CRACKED AS MARKED. LT WING SURGE TANK, WS 1516 RIB LOWER CHORD REPLACED AT STRINGER 6 AREA PER SRM 57-10-05, FIG 4.

Part: SHEAR TIE — CRACKED (FUSELAGE) · airframe 96,389 hrs · 22,361 cycles

M/D BS 1780 STRINGER 4R TO 5R, SHEAR TIE FOUND CRACKED. CRACKED SHEAR TIE REPLACED PER SRM 51-10-01.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 96,389 hrs · 22,361 cycles

M/D BS 996 RBL 33, SEAT TRACK, RT FLANGE FOUND CORROSION. SEAT TRACK AT BS 990 TO BS 1000, RBL 33, SECTIONAL REPLACED PER SRM 53-10-05, FIG 1A.

Part: STRINGER — DAMAGED (FUSELAGE) · airframe 96,389 hrs · 22,361 cycles

FX - DURING BS 980 LT SKIN REPAIR, FOUND STRINGER 37L AND SKIN HAD A METALLIC PLUG INSTALLED PREVIOUSLY. REPAIRED STRINGER 37L AT BS 970- BS 983, AND REPAIRED SKIN AT BS 950 TO BS 990, BETWEEN STRINGER 36L AND 39L PER HAECO REPAIR SCHEME R-53-21-35304.

Part: SHEAR TIE — CRACKED (FUSELAGE) · airframe 96,389 hrs · 22,361 cycles

M/D BS 1940 RT STRINGER 4 TO 5 SHEAR TIE FOUND CRACKED. CRACKED SHEAR TIE REPLACED PER SRM 51-10-01, P9.

Part: CARGO TRACK — CORRODED (FUSELAGE) · airframe 96,389 hrs · 22,361 cycles

M/D BS 1680-1700 LBL 11 TIE DOWN TRACK FLANGE FOUND CORROSION AS MARKED. M/D BS 1680-1730 LBL 11 TIE DOWN TRACK REPAIRED PER SRM 53-10-05, FIG 14.

Part: SKIN — CRACKED (FUSELAGE) · airframe 96,389 hrs · 22,361 cycles

NDT - LT FUSELAGE SKIN UNDER DRAG SPLICE FITTING AT BS980, STRINGER 38L. FOUND ONE EACH FASTENER HOLE CRACKED. SKIN REPAIRED AT SA 950-990, BTN STRINGER 36L AND STRINGER 39L, PER SRM 53-3-03 FIGURE 60, AND HAECO REPAIR SCHEME, R53-21-35304.

Part: SHEAR TIE — CRACKED (FUSELAGE) · airframe 96,389 hrs · 22,361 cycles

M/D BS 1860 STRINGER 4R TO 5R SHEAR TIE FOUND CRACKED. CRACKED SHEAR TIE REPLACED PER SRM 51-10-01.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 96,389 hrs · 22,361 cycles

M/D BS 1535 TO BS 1545, LBL 33, SEAT TRACK CROWN FOUND CORROSION. M/D BS 1480 TO BS 1550, SEAT TRACK SECTIONAL REPLACED PER SRM 53-10-05, FIG 1A.

Part: SEAT TRACK — UNKNOWN (FUSELAGE) · airframe 96,389 hrs · 22,361 cycles

M/D BS 610 TO BS 620 LBL 33, SEAT TRACK RT-05, FIG 1A.

Part: CONTROL MODULE — FAULTY (FIRE DETECTION) · airframe 95,829 hrs · 22,242 cycles

NR 2A FIRE LOOP FLICKERING IN FLIGHT, TESTED ALL AND NR 2A WOULD ONLY RISE TO 3/4 DEFLECTION, NR 3B DID NOT TEST DEFERRED. REPLACED FIRE DETECTION CONTROL ELECTRONIC MODULE PER MM 26-11-03, OPS CHECKED NR 2A FIRE LOOP AND 3B FIRE LOOP, OPS CHECKED OK. FLIGHT DIVERTED TO JFK FOR MAINTENANCE PURPOSES.

Part: SPAR — CRACKED (LT WING) · airframe 95,633 hrs · 22,201 cycles

LEFT WING AUX SPAR UPPER T-CHORD CRACKED ON INBOARD END. FABBED T-CHORD AND INSTALLED PER ECRA 482-57-116-2.

Part: WEB — CRACKED (LT WING) · airframe 95,633 hrs · 22,201 cycles

LEFT WING AFT SPAR AREA SUPPORT STRUCTURE WEB IS CRACKED AT WBL 285 AT LANDING GEAR BEAM. PERFORMED TYPICAL WEB REPAIR PER B747 SRM 51-40-02 PG 1-5 STEP 1-10.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT) · airframe 95,321 hrs · 22,129 cycles

FOUND CREW DOOR SILL EMERGENCY LIGHT INOP DURING SERVICE CHECK. REMOVED AND REPLACED BATTERY PACK CARTRIDGE AND BATTERY PACK PER MM 33-51-00, OP'S CHECK OK.

Part: ENGINE — FAILED (NR 2) · airframe 95,220 hrs

EN ROUTE FRA/HKG, CRUISE CONFIGURATION AT FLT LEVEL 37K, CREW NOTICED MOMENTARY VIBRATION/RUMBLE, AND OBSERVED LOSS OF NR 2 ENGINE POWER (ROLL BACK). ENGINE INSTRUMENTS AT IDLE VALUES WITH N1 RPM ZERO. REPEATED THROTTLE CYCLING PRODUCED NO ENGINE RESPONSE. PERFORMED IFSD, ENGINE WINDMILLED WITH POSITIVE OIL PRESS (+ 5 PSI) FOR APPROX 3 MINUTES. ENGINE SUCCESSFULLY RE-STARTED AND OPS CHECK OK. NORMAL ENGINE OPERATION FOR DURATION OF FLIGHT TO ORIGINAL DESTINATION. UNSUCCESSFUL SPOOL UP AFTER MAINTENANCE AND RESTART ON GROUND, REMOVED AND REPLACED NR 2 ENGINE.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 94,950 hrs · 22,056 cycles

5R EMERGENCY DOOR (BUSSEL) LIGHT INOPERATIVE. REMOVED AND INSTALLED 5R EMERGENCY LIGHT, REF: MM 33-51-06, PG 401 OPS CHK NORMAL.

Part: ENGINE — STALLED (NR 4) · airframe 93,579 hrs · 21,762 cycles

NR 4 ENGINE STALLED AT FL 370, INFLIGHT START ACCOMPLISHED AT FL 210, ALL INDICATIONS NORMAL.

Part: ENGINE — FLAMED OUT (NR 4) · airframe 93,199 hrs · 21,683 cycles

CLIMBING THROUGH 38500 FT NR 4 ENGINE FLAMED OUT. INFLIGHT RESTART NORMAL. INSPECTED INTAKE AND EXHAUST NO DEFECTS NOTED INSPECTED BLEED SCREENS NO FOREIGN OBJECTS NO DEFECTS. REPLACED MAIN FUEL FILTERS, SUMPED NR 4 FUEL DRAIN NO WATER FOUND. FUEL PUMP PRESSURE CHECKED AT FP-12 PRESSURE ABOVE 300 PSI. PERFORMED OPS CHECK OF FUEL CONDITION ACTUATOR NO DEFECT FOUND. NR 4 SYSTEM OPS CHECKED NORMAL PER MM 71-00-40, 71-00-42,71-00-46. CHECKED WATER DRAIN AT EVC PT3 NO DEFECT.

Part: BATTERY — INOPERATIVE (EMERGENCY LIGHT) · airframe 92,268 hrs · 21,495 cycles

OVERHEAD EMERGENCY LIGHT AT STA 2130 IS INOPERATIVE. REMOVED AND REPLACED BATTERY ASSY IAW BMM 33-35-01 OPS CKD GOOD.

Part: BATTERY — INOPERATIVE (EMERGENCY LIGHT) · airframe 92,268 hrs · 21,495 cycles

UPPER DECK CREW SERVICE DOOR EMERGENCY SILL LIGHTS INOPERATIVE. REMOVED AND REPLACED UPPER DECK CREW SERVICE DOOR EMERGENCY LIGHT IAW B747MM 33-51-07. OPS CHECKED GOOD.

Part: HOSE — FAILED (NR 1 ENGINE OIL) · airframe 91,952 hrs · 21,432 cycles

NR 1 ENGINE OIL QUANTITY DECREASED RAPIDLY ON CLIMB OUT FROM EROS. REDUCED NR 1 ENGINE TO IDLE AND DECREASED LESSEND , PERFORMED FUEL JETTISON AND RETURNED TO EROS. CORRECTIVE ACTION SECURED CLAMP MID POSITION NR 4 BEARING SCAVENGE LINE RETORQUED MID (B) NUT ASSY LINE. LINE CHECK GOOD AFTER ENGINE RUN IAW MM 71-00-00, 79-15-01, 12-13-03, OIL TANK SERVICE TO FULL.

Part: O-RING — LEAKING (G/B CHIP DETECT) · airframe 91,952 hrs · 21,432 cycles

NR 1 ENGINE OIL QUANTITY DECREASED TO 1 GALLON AND NR 1 ENGINE OIL PRESSURE LIGHT CAME ON, SHUT DOWN NR 1 ENGINE, NR 1 ENGINE OIL PRESSURE AT 34 PSI. REPLACED ANGLE GEARBOX CHIP DETECTOR O-RINGS, PERFORMED LEAK CHECK NO OIL LOSS ON ENGINE RUN, SERVICE ENGINE OIL TO FULL IAW MM 79-11-00.

Part: STRUCTURE — DAMAGED (CARGO DOOR) · airframe 91,805 hrs · 2,139 cycles

AFT CARGO DOOR FWD, LOWER CORNER, REPAIR DOUBLER IS CRACKED. REMOVED DAMAGED EXTERNAL DOUBLER, FABRICATED, ALODINED AND INSTALLED NEW REPAIR DOUBLER IAW ECRA 482-52-031-2 AT AFT CARGO DOOR, FWD LOWER CORNER.

Part: WEB — DAMAGED (VERTICAL STAB) · airframe 91,805 hrs · 2,139 cycles

VERTICAL STAB RT HANDSIDE ACCESS PANEL 324DR AFT WEB AND GUSSET DAMAGED. REMOVED 2 EA. GUSSETS, FABRICATED 2 EA. GUSSETS, SPLICE PLATE, FILLERS (2EA) AND WEB AND INSTALLED IAW ECRA 482-55-183-2

Part: WEB — CRACKED (NR 1 PYLON) · airframe 91,805 hrs · 21,398 cycles

NR 1 PYLON LOWER WEB CRACKED AT NAC STA 210 LT SIDE AFT OF STIFFER FOR PNEU. DUCT. STOP DRILLED CRACK AND FABBED AND INSTALLED REPAIR PLATE AND FILLERS IAW B747 SRM 54-10-03 FIG 2

Part: SPAR — CORRODED (RT WING) · airframe 91,805 hrs · 21,398 cycles

RT WING UPPERCHORD OF FIX TRAILING EDGE PANEL SUPPORT BEAM SPAR APPROX WBL 235.2-445 CORRODED. REMOVED DAMAGE, NDT AREA, FABBED AND INSTALLED REPAIR IAW ECRA 482-57-184-2

Part: SKIN — CORRODED (FUSELAGE) · airframe 91,805 hrs · 21,398 cycles

RT FUSELAGE SEC 48 EXT SKIN HAS CORROSION LOCATED BETWEEN STA 2436-2460 STR 23R-25R. REMOVED DAMAGE, NDT AREA, FABBED AND INSTALLED REPAIR IAW ECRA 482-53-165-2.

Part: SKIN — CRACKED (FUSELAGE) · airframe 91,805 hrs · 2,139 cycles

FUSELAGE BELLY SKIN CRACKING AT THE AFT EDGE OF THE EQUIPMENT COOLING OUTLET BETWEEN STRINGER 44L AND 45L AT BS 580 ( APPROX) CRACK IS BOTH FORWARD AND AFT OF COUNTER SUNK RIVET FASTNER. REMOVED DAMAGED, FABRICATED AND INSTALLED REPAIR IAW ECRA 482-53-189-2 AND SB 747-53-2386

Part: SKIN — WORN (FUSELAGE) · airframe 91,805 hrs · 21,398 cycles

FUSEALAGE SKIN WORN AT INTERFACE OF VERT STAB SEAL LT SIDE BS 2280-2416. REMOVED DAMAGED, NDT AREA, FABBED AND INSTALLED REPAIR IAW ECRA 482-53-181-2

Part: LAP JOINT — DAMAGED (FUSELAGE) · airframe 91,805 hrs · 2,139 cycles

UPON REMOVAL OF A/C DUCTS, CHAFFING WAS FOUND ON UPPER AND LOWER SKINS AND ON NUMEROUS FASTENERS AT STA. 980 STRINGER 39 LAP JOINT. REPAIRED DAMAGE ON UPPER AND LOWER SKINS AND FASTENERS AT STA. 980 STRINGER 39L, LAP JOINT IAW B747 SRM 53-30-03 FIG 13 AND B747 SRM 53-10-03, FIG 1.

Part: SKIN — WORN (FUSELAGE) · airframe 91,805 hrs · 2,139 cycles

FUSELAGE SKIN WORN AT INTERFACE OF VERTICAL STAB SEAL RT SIDE BS 2280-2416 REMOVED DAMAGED, NDT AREA, FABBED AND INSTALLED REPAIR IAW ECRA 482-53-181-2

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 91,805 hrs · 21,398 cycles

BS. 340 RT UPPERDECK FLOORBEAM UPPER CHORD TO FRAME INTERFACE CRACKED AT 2ND IB HOLE. REMOVED DAMAGED, NDT AREA, FABBED AND INSTALLED REPAIR IAW ECRA 482-53-160-1.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 91,805 hrs · 2,139 cycles

UPPER DECK FLOORBEAM WEB AT BS 440 RBL CRACKED, RBL 66 CORROSION, RBL 40 CRACKED, RBL 55 CRACKED. UPPER DECK FLOORBEAM WEB BS 440, RBL 8 TO RBL 72 REPLACED IAW ECRA 482-53-191-2

Part: SKIN — CHAFED (FUSELAGE) · airframe 91,805 hrs · 21,398 cycles

VERTICAL STAB TO FUSELAGE. AREA LT SIDE BELOW RUDDER BETWEEN STA. 2521 AND 2598 HAS A GOUGE IN FUS. REMOVED DAMAGED, NDT AREA, FABBED AND INSTALLED REPAIR IAW ECRA 482-53-181-2.

Part: STRUCTURE — DAMAGED (FUSELAGE) · airframe 91,805 hrs · 2,139 cycles

BS 1760 STR 49 RT HAS CORROSION ON STRUCTURE LOWER SURFACE. REPLACED DAMAGED STR FROM BS 1740-1770 IAW B747 SRM 53-10-03 FIG 8.

Part: SKIN — CHAFED (NR 2 PYLON) · airframe 91,805 hrs · 2,139 cycles

INSIDE LOWER SURFACE OUTBOARD SIDE NR 2 PYLON APPROX. 15 INCHES AFT OF ENGINE REAR MOUNT HAS LARGE CHAFED AREA. OB SIDE OF NR 2 PYLON SKIN REPAIRED IAW ECRA 482-54-177-2.

Part: SKIN — CHAFED (FUSLEAGE) · airframe 91,805 hrs · 2,139 cycles

VERTICAL STABILIZER TO FUSELAGE RIGHT BELOW RUDDER HAS CHAFE CONDITION FROM STA 2605-2608. REMOVED DAMAGED, NDT AREA, FABBED AND INSTALLED REPAIR IAW ECRA 482-53-181-2.

Part: BEAM — DAMAGED (VERTICAL STAB) · airframe 91,805 hrs · 2,139 cycles

VERTICAL STAB RT TRAILING EDGE BEAM FWD AND AFT WEBS DAMAGED, DO TO POWER PACK LOWER RUDDER INSTALLATION. INSTALLED FORWARD WEB DOUBLER AND 2 EA. FILLERS IAW MFG 747 SRM 51-30-02 AND ECRA 482-55-183-2

Part: FRAME — BROKEN (ACCESS PANEL) · airframe 91,805 hrs · 2,139 cycles

VERTICAL STAB RT SIDE ACCESS PANEL 324 DR AFT SECTION OF PANEL ATTACH FRAME HAS SECTION BROKEN OFF. REMOVED DAMAGED, NDT AREA, FABBED AND INSTALLED REPAIR IAW ECRA 482-55-196-2

Part: SKIN — CORRODED (FUSELAGE) · airframe 91,805 hrs · 21,398 cycles

LT OUTFLOW VALVE STA. 2240 HAS 2 SKIN BULGES AT OPPOSITE CORNERS UPPER AFT AND LWR FWD. REMOVED AND REPLACED DAMAGED SKIN IAW B747 SRM 51-30-02 AND ECRA 482-53-169-2.

Part: WEB — CORRODED (FUSELAGE) · airframe 91,805 hrs · 21,398 cycles

AFT CARGO COMPT, BS 1480 TO BS 1490 BETWEEN LBL 0 TO LBL 45.5, UPPER SURFACE OF THE WEB IS CORRODED. FABRICATED THE FOLLOWING REPAIR PARTS, (1) EA, WEB P/N 482-53-2-2, (1) EA DOUBLER P/N 482-53-188-2-3, (1) EA DOUBLER P/N 482-53-188-2-4, AND INSTALLED IAW ECRA NR 482-53-188-2, PAGES 1-4, ITEMS 1-15.

Part: FRAME — CORRODED (FUEL TANK) · airframe 91,805 hrs · 21,398 cycles

LT WING GEAR WHEEL WELL STATION 1241, LBL 88 (APPROX), BELOW LOWER CANTED FRAME HAS EXFOLIATED CORROSION ON TANK SKIN. REPAIR IAW ECRA NR 482-57-170-2.

Part: SPAR — CORRODED (FUSELAGE) · airframe 91,805 hrs · 21,398 cycles

CORROSION ON REAR SPAR WEB TO THE INBOARD SIDE AND UNDER THE LT BULKHEAD FITTING AT BS 1241 UPPER PORTION APPROXIMATELY FASTENER NR 32 AREA DOWN. REMOVED CORROSION ON REAR SPAR WEB UNDER THE LT BULKHEAD FITTING AT BS 1241, IAW EO NR 57-747-1544-99 REV A

Part: STRINGER — CORRODED (FUSLEAGE) · airframe 91,805 hrs · 21,398 cycles

AFT CARGO COMPT. BS 1790 TO 1800 STR. 51R STRINGER HAS LIGHT SURFACE CORROSION. REMOVED CORROSION FOUND OUT OF LIMITS IAW B747 SRM 53--10-01 PG2-3. REMOVED AND REPLACED DAMAGED STRINGER FROM STA. 1740-1810 AND REPAIRED IAW B747 SRM 53-10-03 FIG 8 PGS. 33-40, 51-10-02 AND BSOPM 20-41-02 PAGES 7-8.

Part: BULKHEAD — CORRODED (MLG WW) · airframe 91,805 hrs · 21,398 cycles

LT WING MLG WELL CORROSION ON BS 1241 BULKHEAD AT CANTED BULKHEAD TO 1241 BULKHEAD HORIZONTAL SPLICE LBL 96, APPROX W.L. 171. REPAIRED IAW ECRA 482-57-170-2.

Part: SHEAR TIE — CORRODED (FUSELAGE) · airframe 91,805 hrs

SHEAR TIE L-ANGLE AT BS 2220 HAS HEAVY CORROSION ON BOTTOM LOWER FLANGE STR. 37L TO 41L. REMOVED DAMAGED, FABRICATED AND INSTALLED REPAIR IAW B747 SRM 51-40-03 FIG 1, 51-10-01, 51-10-02, 51-30-02 AND BSOPM 20-41-2.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 91,574 hrs · 21,353 cycles

EMERGENCY LIGHT ASSY IN UPPER DECK DOME LIGHT INOP. DMI OPEN.

Part: CHECK VALVE — BENT (FUEL SYSTEM) · airframe 91,471 hrs · 21,331 cycles

JETTISON PUMP CHECK VALVE FOUND BENT. INSTALLED NEW VALVE. PART NUMBER 60-703137.

Part: ENGINE — BIRD INGESTION (NR 1) · airframe 91,174 hrs · 21,269 cycles

POST FLIGHT WALKAROUND FOUND BIRD STRIKE NR 1 ENGINE. FOUND 2 EACH N1 FAN BLADES DAMAGED ENGINE INSPECTED IAW MM 72-00-00. REMOVED AND REPLACED NR 1 AND NR 2 BLADES IAW WC F7208 RII ACCOMPLISHED.

Part: LINE — LEAKING (GEARBOX) · airframe 90,511 hrs · 21,129 cycles

NR 2 ENG OIL QTY BEGAN DECREASING FROM 5.0 GAL, OIL PRESS/TEMP NORMAL. LATER NR 2 OIL PRESSURE DROPPED BELOW YELLOW BAND AND OIL PRESSURE LIGHT ILLUMINATED. NR 2 ENGINE WAS SHUTDOWN, WINDMILLING OIL PRESSURE MAINTAINED 20 PSI. INSPECTED AND REPLACED MAIN OIL FILTER IAW MM 72-61-00 AND CHECKED MAIN AND ANGLE GEAR BOX CHIP DETECTORS IAW MM 72-61-00 AL CH OK. FOUND OIL LEAKING FROM ANGLE GEAR BOX ADAPTER SCAVAGE LINE. REPLACED ADAPTER IAW MM 78-21-00. LEAK GOOD. RII C/W.

Part: BATTERY — SMOKE (MAIN ELECTRICAL)

3 HOURS INTO FLIGHT, AIRCRAFT BATTERY BEGAN TO VENT SMOKE AND HAD AN ELECTRICAL ODOR. A FLIGHT TURN BACK WAS DONE.

Part: ACTUATOR — FAILED (ENG STATOR)

CBBI - AFTER NR 4 THRUST LEVER WAS RETARDED TO IDLE ON DESCENT THE NR 4 ENGINE HAD AN UNRECOVERABLE COMPRESSOR STALL. ENGINE SHUTDOWN ACCOMPLISHED. RESTART UNSUCCESSFUL. INSPECTED ENGINE. REPLACED NR 4 ENGINE EVC UNIT (P/N 7479555) AND STATOR VANE CONTROL ACTUATOR (P/N 719999-6) AND PERFORMED EVC TRIM PROCEDURE IAW MM 75-31-08, 75-31-02 AND 71-00-00. (M)

Part: FRAME — CRACKED (FUSELAGE) · airframe 87,217 hrs · 20,441 cycles

FRAME WEB CRACK, STA 1760 - STR 39L. THE CRACK LENGTH EXTENDS JUST BELOW THE FAILSAFE CHORD. THIS EXCEEDS THE 747 SRM REPAIR LIMITS. REPAIR OF THE FRAME IS ACCOMPLISHED BY USING THE 747 53-10-04 FIGURE 69. REPAIR WITH BOEING SPECIFIED CHANGES. THIS REPAIR IS AN AMOC TO THE FAA AD 86-18-01, PER ECRA 482-53-146-2.

Part: SKIN — CORRODED (HORIZ STAB) · airframe 87,217 hrs · 20,441 cycles

LEFT HORIZ STAB UPPER SKIN STA 385 HOIST ATTACH POINT. THIS REPAIR IS ACCOMPLISHED USING AN EXTERNAL DOUBLER REPAIR. THIS REPAIR IS APPROVED BY THE BOEING COMPANY PER ECRA 482-55-143-2.

Part: WEB — CORRODED (FUSELAGE) · airframe 87,217 hrs · 20,441 cycles

CANTED WEB (65B07992-110) CORROSION, BODY STATION 1245, RBL 0.00 - 33.9. THE REPAIR TO THE WEB TO ENSURE CRACK AND CORROSION FREE CONDITIONS WAS DONE BY TRIMMING OUT THE DAMAGED AREAS AND INSTALLING FILLERS AND DOUBLERS PER ECRA 482-53-147-2.

Part: SKIN — CORRODED (HORIZ STAB) · airframe 87,217 hrs · 20,441 cycles

LEFT HORIZONTAL STABILIZER UPPER SKIN CORROSION. THE REPAIR IS ACCOMPLISHED BY TRIMMING OUT CORRODED AREA OF SKIN THEN INSTALLING AN EXTERNAL DOUBLER SKIN REPAIR PER ECRA 482-55-148-2.

Part: WEB — CORRODED (FUSELAGE) · airframe 87,217 hrs · 20,441 cycles

CANTED WEB (P/N 65B07992-109) CORROSION, BODY STATION 1245, LBL 0.00-21.5. THIS REPAIR TO THE WEB WAS DONE BY TRIMMING OUT THE DAMAGED AREA AND INSTALLING FILLERS AND DOUBLERS PER ECRA 482-53-144-2.

Part: DOUBLER — CRACKED (MAIN ENTRY) · airframe 87,217 hrs · 20,441 cycles

MAIN ENTRY DOOR NR 5 REVEAL DOUBLER CRACKING. THE REPAIR IS ACCOMPLISHED BY TRIMMING SECTIONS OF THE DOUBLERS OFF AND INSTALLING REPLACEMENT SECTIONS USING SPLICE DOUBLERS PER ECRA 482-53-140-2.

Part: SPAR — CORRODED (WING) · airframe 87,217 hrs · 20,441 cycles

CENTER WING REAR SPAR WEB CORROSION. THIS REPAIR IS ACCOMPLISHED BY BLENDING OUT CORROSION AREAS. SECTION OF THE SLOPING PRESSURE DECK ANGLE WHICH WAS REMOVED TO GAIN ACCESS TO CORRODED AREAS IS ALSO REPLACED. THIS IS ACCOMPLISHED USING TWO SPLICE ANGLES. THIS ECRA PROVIDES INSTRUCTIONS TO REINSTALL 3 OF THE REAR SPAR WEB STIFFENERS USING ALTERNATE FASTENERS PER ECRA 482-57-142-2.

Part: FITTING — WORN (WING) · airframe 87,217 hrs · 20,441 cycles

THE REINSTALLATION OF THE FITTING REQUIRED THE SUBSTITUTION OF STRAIGHT SHANK FASTENERS IN LIEU OF THE TAPER SHANK FASTENERS, ORIGINALLY USED THIS REPAIR IS APPROVED BY THE BOEING COMPANY PER ECRA 482-57-141-02.

Part: BULKHEAD — CORRODED (FUSELAGE)

MZJ-EAC - DURING C-CHECK, FOUND EXFOLIATION CORROSION AT STATION 1241 BULKHEAD, RBL 46, RBL 60 AND INBOARD OF FORK FITTING ALONG UPPER CHORD WEB IN THE RIGHT WING GEAR WHEEL WELL. REPAIRED PER ECRA 482-57-142-2 AND SRM 57-10-1. (M)

Part: WEB — CORRODED (LT MLG WW)

MZJ-EAC - LEFT WHEEL WELL, STATION 1241, LBL 19, HAS AREA OF EXFOLIATION CORROSION ON WEB. REPAIRED PER ECRA 482-57-142-2. (M)

Part: SPAR — CORRODED (LT WING)

MZJ-EAC - FOUND STATION 1241 REAR SPAR WEB, LEFT SIDE WAS FOUND TO HAVE 2 LOCATIONS OF CORROSION BEHIND FITTING. CORROSION REMOVED AND REPAIRED PER SB 747-57-2263 R2, EO 57-747-1544-99A AND ECRA 482-57-141-2. (M)

Part: STRUCTURE — CORRODED (CENTER WING TANK)

MZJ-EAC - FOUND CORROSION AT STATION 1238, RBL 2, ON CENTER WING TANK SKIN. REPAIRED PER ECRA 482-57-149-2. (M)

Part: FRAME — CRACKED (FUSELAGE)

MZJ - FOUND C-CHECK, FOUND 6 INCH CRACK IN FRAME AT STATION 1760 BELOW AND INBOARD OF STRINGER 39L TIE CLIP. FABRICATED AND INSTALLED CLIP, STRAP AND DOUBLER PER ECRA 482-53-146-2. (M)

Part: FRAME — CRACKED (FUSELAGE)

MZJ-EAC - FOUND CRACK DURING HFEC INSPECTION ON FRAME STRAP AT STATION 2231 BETWEEN STRINGERS 24R AND 25R. REPAIRED PER ECRA 482-53-140-2. (M)

Part: STRINGER — CORRODED (FUSELAGE)

MZJ-EAC - FOUND CORROSION ON INSIDE AND OUTSIDE OF OUTBOARD FLANGE OF STRINGER 2L, JUST ABOVE STATION 1560 FRAME,MAIN DECK, UPPER LOBE. REPAIRED STRINGER SECTION WITH FABRICATED PARTS PER SRM 53-10-03, 51-10-02 AND 51-30-02. (M)

Part: WEB — CORRODED (LT MLG WW)

MZJ-EAC - DURING C-CHECK, FOUND CORROSION ON THE LEFT WHEEL WELL CANTED WEB. REPAIRED PER ECRA 482-53-144-2. (M)

Part: STRUCTURE — CORRODED (APU BAY)

MZJ - FOUND EXFOLIATION CORROSION AT STATION 1241 RBL 2, UNDER DOUBLER FOR APU SHROUD LINE. REPAIRED CORROSION AREA PER ECRA 482-53-147-2. (M)

Part: FRAME — CRACKED (FUSELAGE)

MZJ-EAC - FOUND TWO CRACK DURING HFEC INSPECTION ON FRAME STRAP AT STATION 2231 BETWEEN STRINGERS 24L AND 25L. REPAIRED PER ECRA 482-53-140-2. (M)

Part: WEB — CORRODED (LT MLG WW)

MZJ-EAC - FOUND LEFT WHEEL WELL STATION 1241, LBL 2, WAS FOUND TO HAVE CORROSION ON OUTSIDE OF CENTER TANK WEB AROUND SCAVENGE PUMP OPENING. REPAIRED PER ECRA 482-57-142-2. (M)

Part: PRESSURE PANEL — CORRODED (FUSELAGE)

MZJ-EAC - FOUND CORROSION AT STATION 1245, RBL 34 ON CANTED PRESSURE DECK. REPAIRED PER ECRA 482-53-147-2. (M)

Part: STIFFENER — CORRODED (FUSELAGE)

MZJ-EAC - FOUND STATION 1241, BL 0, T-STIFFENER HAS CORRODED FASTENER HOLE ON RIGHT SIDE, SECOND FROM TOP. REPAIRED PER ECRA 482-57-142-2. (M)

Part: SPAR — CORRODED (CENTER WING)

MZJ - FOUND CORROSION ON REAR SPAR WEB OF WING CENTER SECTION BS 1241 BULKHEAD FITTING. CORROSION REMOVED AND WORK ACCOMPLISHED PER SB 747-57-2263/EO 57--747-1544-99 (A).

Part: FLOORBEAM — DAMAGED (FUSELAGE)

MZJ - FOUND FLOORBEAM UPPER RETURN FLANGE AT STATION 571, RBL 25, WAS FOUND BROKEN. REMOVED DAMAGED PORTION OF FLOORBEAM AND REPAIRED PER SRM CHAPTER 51. (M)

Part: ACTUATOR — FAILED (RT AILERON)

KLAX - AFTER TAKEOFF, RIGHT OUTBOARD AILERON NOT LOCKED WITH FLAPS UP. REPLACED RIGHT AILERON LOCKOUT ACTUATOR PER MM 27-11-16. (M)

Part: DOOR — OPEN (NLG)

NOSE GEAR DOOR REMAINED OPEN AFTER GEAR RETRACTION. FOUND NOSE DOOR EXTENSION HANDLE NOT FULLY IN THE UP POSITION. EXERCISED NOSE DOOR HANDLE FROM DOWN TO UP AND OPERATED NOSE GEAR DOORS PER MM 32-61-00. LANDING GEAR SYSTEM OPS NORMAL. (M)

Part: FITTING — CORRODED (LT FLAP)

B-CHECK, FOUND LHW INBOARD TRAILING EDGE FORE FLAP MID TRACK FORWARD FITTING, FORWARD AND AFT FACE OF LOWER END AREA CORRODED. FITTING REPLACED PER SRM 51-10-01. (M)

Part: CONTROL CABLE — BROKEN (STABILIZER)

STABILIZER TRIM REPORTED INOPERATIVE BY CREW AT 500 FEET FINAL. ON INVESTIGATION, FOUND THAT STABILIZER TRIM FEEDBACK POSITION INDICATOR CABLE BROKEN. AIRCRAFT AOG. CREW REPLACED BROKEN CABLE AND CARRIED NECESSARY TESTS. AIRCRAFT RELEASED TO SERVICE BY CREW. (X)

Part: TIRE — SEPARATED (MLG)

EVERREEN B747-200F RED ALERT DECLARED, SUSPECTED BLOWN WHEEL ON TAKEOFF HNL. AIRCRAFT LANDED SAFELY WITH ALL WHEELS INFLATED. HOWEVER, NR 11 MAIN WHEEL TREAD RE-CAPPING WAS FOUND MISSING. DAMAGE TO PANELS AFT OF RT BODY GEAR WAS NOTED AND TEMPORARY REPAIRS CARRIED OUT BY EVERGREEN MECHANICS. (X)

Part: CONTROL CABLE — BROKEN (STAB TRIM)

NAN - ON FLYBY FOR LANDING GEAR CHECK, STAB TRIM QUIT WITH A SCRAPING NOISE FROM THE CENTER CONSOLE. NO MOTION FROM TRIM WHEEL THROUGH INPUT FROM CAPTAIN, F/O SWITCHES, OR MANUAL TRIM HANDLES. TRIM INDICATOR CEASED MOVEMENT AT 2.6 UNITS. AFTER LANDING AND INSPECTION, TRIM CABLE WAS FOUND BROKEN IN THE AFT END OF THE AIRCRAFT. FOUND STAB POSITIONING INDICATOR CABLE FAILED AT STAB COMPARTMENT. NEW CABLE REFITTED AS PER MM 27-48-01. STABILIZER FUNCTIONAL CHECK CARRIED OUT AS PER MM 27-48-00. NIL DEFECTS FOUND. STABILIZER JACK SCREW AND NUT LUBRICATED. STAB CHECK FOR ANY DEFECTS. NIL FOUND. CABLE RUN FROM FLT DECK TO STAB COMPARTMENT CHECKED FOR CONDITION, NIL DEFECTS FOUND. ACCOMPLISHED TEST FLIGHT FOR

Part: ENGINE — LEAKING (NR 4)

JFK - AFTER TAKEOFF, NR 4 ENGINE LOST OIL QTY AND PRESSURE. ACCOMPLISHED IN FLT SHUTDOWN. ENGINE SHUTDOWN WITH APPROX 1 GAL OIL AND 20 PSI PRESSURE 20 SECONDS AFTER PRESS DROP, WINDMILL 8 MIN. RAN NR 4 ENGINE AT IDLE COULD NOT FIND OIL LEAK. DRIVE SEAL CHECK PERFORMED, DID NOT FIND OIL LEAK. REPLACED NR 4 ENGINE. (M)

Part: LINE — SPLIT (NR 1 ENGINE OIL)

ANC - NR 1 ENGINE LOP AND QTY IN FLT SHUTDOWN, MIN PRESSURE 8-10 PSI. DURATION 30 MIN. ALL SYSTEM NORMAL PRIOR TO LOSS OF OIL QTY AND PRESS. FOUND OIL PRESS LINE FROM FILTER TO TOP OF ENGNE TO OIL PRESS TRANSMITTER SPLIT, LT SIDE OF ENGNE. REPLACED WITH FLEX LINE PER ECRA 662254-79-014-1 PT A. PERFORMED WINDMILL INSPECTION. REPLACED OIL FILTER AND INSPECTION ALL CHIP DETECTORS. FOUND NORMAL. ENGINE RUN AND LEAK CHECK NORMAL. (M)

Part: SPAR — CORRODED (BULKHEAD)

RIGHT WLG W/W BS 1241 BULKHEAD CORROSION REVEALED AT NR 7, 8, 9, 19 AND 20 RIVETS AREA MATING TO BULKHEAD FITTING. CORROSION REMOVED AND REPAIRED PER EO 57-747-1544-99. (M)

Part: FRAME — CRACKED (FUSELAGE)

HAECO-HKG - C6/D-CHECK/PYL MOD - BULK CARGO COMPT ADJACENT STR 37 STA 1920 AREA FRAME UPPER FLANGE CRACK APPROX 1.0 INCH LENGTH. CRACK LENGTH 1.2 INCHES. STOP HOLE DRILLED PER SRM 51-10-01. NDT INSPECTED PER NTM PT6 51-00-00 FIG 4. CRACK NIL BEYOND STOP DRILL. FRAME REPAIRED PER SRM 53-10-04 FIG 66. (X)

Part: SHEAR TIE — CRACKED (CENTER TANK)

HAECO-HKG - WING CENTER TANK FORWARD LBL 30 INCHES BS 1000 UPPER SHEAR TIE CRACKED. TRIMMED OFF, NDT INSPECTED OK, REPLACED CRACKED SHEAR TIE PER SRM 51-10-01. (X)

Part: DOUBLER — CRACKED (RT NACELLE)

HAECO-HKG - C6/D-CHECK - PYLON NR 1 RT, NR 3 LT, AND NR 4 LT AT NAC STA 180 DOUBLERS FOUND CRACKED. TRIMMED OFF CRACKED SKIN, NDT INSPECTED, FILLER REPAIRED, AND DOUBLERS INSTALLED PER BOEING MESSAGE EVR-HKG-00-00036H/-00037H/-00044H AND HAECO REPAIR SCHEMES R-54-51-34326, R-54-51-34325, AND R-54-51-34324. (X)

Part: FRAME — CRACKED (FUSELAGE)

FORWARD CARGO COMPARTMENT LEFT SIDEWALL FRAME FOUND CRACKED AT STATION 500 STRINGER 31L. DISCARDED OLD REPAIR PARTS. TRIMMED OFF THE CRACKED FRAME WEB. NDT INSPECTED. NEW FRAME SEGMENT INSTALLED BETWEEN THE TRIM AND THE SPLICE ABOVE STRINGER 31L. MODIFIED THE REPAIR SPLICE PLATE, AND WITH FLANGED REPAIR DOUBLER, INSTALLED PER BM EVR-HKG-OO-00025F/-00032F/-00028H/-00030H AND HAECO REPAIR SCHEME R53-12-34321. (M)

Part: FITTING — CORRODED (FUSELAGE)

FOUND CORROSION ON KICK FITTINGS AROUND BOLT HOLE AFTER LEFT BS 1241 LBL 128 SPLICE STRAP KICK FITTNGS REMOVED. KICK FITTINGS REPLACED PER BSB 53-2283R4. (M)

Part: SHEAR TIE — CRACKED (RT WING)

HAECO-HKG - C6/D-CHECK - RIGHT WING WS 669.5 RIB UPPER CHORD MOST FORWARD SHEAR TIE FOUND CRACKED. STOP HOLE DRILLED PER BSB 747-54-2273 REV 2 FIG 7, EDDY CURRENT INSP. CUT OUT PER NTM PT 6 51-00-00 FIG 4. NO CRACK BEYOND STOP DRILL HOLE. UPPER CHORD REPAIRED PER BSB 747-57-2273 REV 2 FIGS 8 AND 9. (X)

Part: FRAME — CRACKED (FUSELAGE)

HAECO-HKG - C6/D-CHECK/PLY MOD - U/D BS 460 S12L FRAME CRACKED APPROX 0.75 INCH LENGTH. BS 460 FRAME BETWEEN STR ZERO TO STR 13AL REPLACED. REF: WS NR 062 EO 53-747-1143-91D AND DWG 624U0003 SH 23B FOR FRAME INSTALLATION. (X)

Part: FRAME — CRACKED (FUSELAGE)

HAECO-HKG - C6/D-CHECK - S41 MOD AT ZONE 1 BS 380 RT FRAME AT U/D BELOW FLOORBEAM BETWEEN STR 13R - STR 14R, FOUND PREVIOUS CUT-OFF AT 2 LOCATIONS. REPLACED DEFECTIVE FRAME WITH P/N 141U1009-297. (X)

Part: FRAME — CRACKED (FUSELAGE)

HAECO-HKG - C6/D-CHECK/PLY MOD - U/D BS 500 S10AL FRAME CRACKED APPROX 0.5 INCH LENGTH. U/D BS 500 FRAME BETWEEN STR ZERO TO STR 13L REPLACED. REF: WS NR 062 EO 53-747-1143-91D AND DWG 624U0003 SHEET 25B FOR FRAME INSTALLATION. (X)

Part: FRAME — CRACKED (NR 1 PYLON)

NR 1 PYLON HOSESHOE FRAME AT NAC STATION 221.9 CRACKED AT FORWARD LOWER AREA. CRACK APPROX .075 INCH ALONG THE RADIUS OF THE FRAME. TRIMMED OFF, REINFORCED AREA, AND COMPLETED REPAIR PER EO 54-747-1046-90. (M)

Part: SKIN — CRACKED (PAX DOOR)

HAECO-HKG - C6/D-CHECK/PLY MOD - M/D L3 DOOR EXTERNAL SKIN FOUND CRACKED AT LOW BOTTOM AREA. SKIN REPAIRED PER SRM 52-00-03 FIG 4 CRACKED AREA 5 INCHES LENGTH TRIMMED OFF PER SRM 51-10-01 AND REPROTECTED PER SRM 51-10-02. NDT INSPECTED PER NTM PT6 51-00-00 FIG 4. NO FURTHER CRACKS FOUND. (X)

Part: LAP JOINT — MISINSTALLED (BS 520)

HAECO-HKG - DURING LAP JOINT MOD OF STRINGER 12L AND STRINGER 12R, BS 520-741 LOW ROW OF FASTENERS EDGE MARGIN CANNOT BE MAINTAINED. BS 520-741 STRINGER 12L AND STRINGER 12R LAP JOINT SKIN REPAIRED PER SRM 53-30-03 FIG 17 AND HAECO SRWS 916876. (M)

Part: FRAME — CRACKED (BS 1714)

HAECO-HKG - C6/D CHECK/PLY MOD - M/D RT BS 1714 STR 13 - STR 16 AREA ATTACH VERTICAL SUPPORT FRAME CRACKED APPROX 3.0 INCH LENGTH. REPLACED VERTICAL SUPPORT FRAME PER SRM 51-10-01. (X)

Part: STRUCTURE — CRACKED (NR 4 PYLON)

HAECO-HKG - NR 4 PYLON HORSESHOE FRAME UPPER HORIZONTAL ANGLE HAD CRACK AT LEFT NAC STA 221. REPLACED NR 4 PYLON HORSESHOE FRAME UPPER HORIZONTAL ANGLE PER SRM 51-10-01 AND SRM 51-30-02. (X)

Part: STRUCTURE — CRACKED (MLG WW)

HAECO-HKG - C6/D-CHECK/PLY MOD - NLG W/W FORWARD LT CORNER STRUCTURE AT STA 240 LBL 33 AREA CANTED BULKHEAD CHORD UPPER FLANGE CRACKED BY 1.25 INCHES RUNNING UPWARDS. REPAIRED NLG W/W LT FORWARD CORNER STRUCTURE PER SB 747-53-2112 DWG 141U1098 WITH HAECO SRWS NR 000266. (X)

Part: FITTING — CRACKED (PAX DOORWAY)

HAECO-HKG - C6/D-CHECK/PLY MOD - M/D L3 DOOR, NR 2, NR 3, AND NR 6 FORWARD CUT OUT FRAME STOP FITTING CRACKED, AND NR 4 RIVET HOLES AREA ELONGATED. L3 DOOR FORWARD CUT OUT FRAME STOP FITTING NR 2, NR 3, NR 4, AND NR 6 REPLACED PER EO 53-747-1542-99A. (X)

Part: FRAME — CRACKED (FUSELAGE)

HAECO-HKG - C6/D-CHECK/PLY MOD - M/D BS 1660 STR 16R AREA ATTACH BELT FRAME FOUND CRACKED NEAR R4 DOOR, SRM 51-10-01. FRAME CRACKED AREA TRIMMED OFF APPROX 1.25 INCH LENGTH. NDT INSPECTED PER NTM PT6 51-11-00 FIG 4-CRACK FREE. REPAIRED FRAME PER SRM 51-40-03 FIG 1. (X)

Part: FITTING — CRACKED (NR 4 PYLON)

DURING ACCOMPLISHMENT OF EO54-747-1042-90, NR 4 PYLON REAR ENGINE MOUNT BULKHEAD FITTING FOUND CRACKED. NR 4 PYLON REAR ENGINE MOUNT BULKHEAD FITTING REPLACED PER SRM 51-10-01 PAGE 18 AND REWORKED PER EO 54-747-1042-90. (M)

Part: FITTING — CRACKED (RT WING)

FOUND CRACK REVEALED ON RT WING RIB SUPPORT FITTING AT WS 669.5 RIB, AT MOST FORWARD UPPER HOLE, APPROX .5 INCH LONG. RIB SUPPORT FITTING REPLACED PER BOEING SB 747-57-2273 REV 2 FIG 5 AND EO 57-747-1403-95. (M)

Part: LONGERON — CORRODED (FUSELAGE)

FOUND CORROSION BS 2335-2340, STRINGER 6L. CORROSION REMOVED PER SRM 51-10-01. BLEND OUT CORROSION DEPTH .008 INCH, WIDTH 1.0 INCH, LENGTH 2.0 INCH. PRE-TREATMENT CARRIED OUT PER SRM 51-10-02. PROTECTIVE FINISHES APPLIED PER MM 51-24-11. CORROSION INHIBITOR COMPOUND APPLIED PER M 51-24-13. (M)

Part: SKIN — CRACKED (FUSELAGE)

HAECO-HKG - FOUND BS 1480 B/H AT STRINGER 34R HAS 1 CRACKED FASTENER HOLE. RIGHT AT UPPER SKIN APPROX .0625 INCH LENGTH AND .125 INCH AT ONE AND NINE O'CLOCK POSITIONS RESPECTIVELY. OVERSIZED TO REMOVE CRACKS. SKIN FREEZE PLUGGED WITH RETAINING WASHERS INSTALLED PER BOEING MESSAGE EVR-HKG-OO-00039F/00054H AND HAECO RS-53-61-34335, SRWS 000249 AND 000254. (M)

Part: FITTING — CRACKED (NR 3 PYLON)

DURING ACCOMPLISHMENT OF EO54-747-1042-90, NR 3 PYLON REAR ENGINE MOUNT BULKHEAD FITTING FOUND CRACKED. NR 3 PYLON REAR ENG MOUNT BULKHEAD FITTING REPLACED PER SRM 51-10-01 PAGE 18 AND REWORKED PER EO54-747-1042-90. (M)

Part: PANEL — CRACKED (FUSELAGE)

HAECO-HKG - C6/D-CHECK - BS 1241 CANTED BULKHEAD RT CLOSURE PANEL CRACKED. RIGHT CLOSURE PANEL REPLACED PER SB 53-2329. (X)

Part: FITTING — CORRODED (LT WING WW)

HAECO-HKG - DURING REPLACEMENT OF LEFT FORWARD OVERWING LONGERON IN LEFT WLG W/W, FOUND LONGERON ATTACH HORIZONTAL WEB HEAVY CORROSION AT BS 1301. CORROSION REMOVED PER SRM 51-10-01. BLEND OUT CORROSION DEPTH .08 INCH, WIDTH 4 INCHES, LENGTH 3 INCHES OUT OF SRM 53-10-01 LIMITS. REPAIRED LEFT LONGERON HORIZONTAL WEB PER SRM 51-40-02 FIG 1 AND HAECO SRWS 916878. (M)

Part: SPAR — CORRODED (MLG WW)

LEFT WLG W/W BS 1241 BULKHEAD WEB TO BULKHEAD FITTING MATING SURFACE CORROSION REVEALED AT NR 7, 8, 9, 19 AND 20 RIVETS. CORROSION REMOVED AND REPAIRED PER EO 57-747-1544-99. (M)

Part: SPAR — CRACKED (LT WING)

FOUND LT WING REAR SPAR TO CENTER SECTION SPLICE FITTING NR 5 FASTENER HOLE FOUND CRACK AT WING SKIN UPPER SURFACE APPROX .125 INCH IN LENGTH RUNNING FORWARD. SKIN REWORKED, BUSHING INSTALLED PER EO 57-747-1011-90A AND SB 747-57-2110 FIG 6. (M)

Part: BULKHEAD — CRACKED (FUSELAGE)

DURING ACCOMPLISHMENT OF BS 1480 BULKHEAD AND SPLICE COMPONENTS REPAIR AND MOD EO 53-747-1513-98C, BS 1480 RIGHT BULKHEAD FASTENER HOLES NR 1, 3, 5, 6 AND 22, FOUND CRACKED. CARRIED OUT CRACK REMOVAL AND INSURANCE CUT AS PER EO 53-747-1513-98C PART II AND BSB 53A2390. (M)

Part: SKIN — CORRODED (FUSELAGE)

HAECO-HKG - DURING AFT PRESSUER BULKHEAD MOD, M/D BS 2360 STRINGER 48L PRESSURE BULKHEAD FORWARD SKIN CORROSION FOUND. TRIMMED OFF AREA PER SRM 51-01-01 ON INNER AND OUTER WEB. NDT INSPECTED PER NTM PT 51-00-00 FIG 4 EVG-HKG-00-00046H/00046F/00031F/00043H. (M)

Part: PAD — DAMAGED (RT WING)

HAECO-HKG - RIGHT MAIN JACK PAD ASSEMBLY FOUND DEFORMED AND DAMAGED. JACK PAD ASSEMBLY REPLACED PER HAECO RS R-57-11-34345. (M)

Part: FRAME — DAMAGED (FUSELAGE)

HAECO-HKG - C6/D-CHECK/PLY MOD - BS 1265 LT AND RT BODY FRAMES FOUND FASTENER HOLE CRACKED AT THE FRAME WEB. BOTH BODY FRAME WEBS REPLACED PER EO 53-747-1580-00, HAECO REPAIR SCHEME R53-42-34337, AND BOEING MESSAGE EVG-HKG-00-00054F/-00055H/-00061F (X)

Part: SHEAR TIE — CRACKED (CENTER TANK)

HAECO-HKG - D6/D-CHECK - WING CENTER TANK FORWARD LBL 10 INCHES BS 1000 UPPER SHEAR TIE CRACKED. TRIMMED OFF, NDT INSPECTED OK, REPLACED CRACKED SHEAR TIE PER SRM 51-10-01. (X)

Part: SHEAR TIE — CRACKED (FUSELAGE)

FORWARD CARGO COMPARTMENT FRAME SHEAR TIE FOUND CRACKED AT BS 980 STRINGER 46L BOTTOM. REPLACED BS 980 BETWEEN STRINGER 46L-47L FRAME LOWER SHEAR TIE PER SRM 53-10-04. (M)

Part: ANGLE — CRACKED (FUSELAGE)

HKG - BULK CARGO COMPARTMENT FLOOR SUPPORT ANGLE CRACKED AT BL 0 BS 2100-2120. CRACK AREA TRIMMED AT BL 0 BS 2100-2160 AND REPROTECTED PER SRM 51-10-02. NDT INSPECTED PER NTM PT6 51-00-00 FIG 4. NO CRACK FOUND. FLOOR SUPPORT REPAIRED PER SRM 53-10-07 FIG 20. (M)

Part: FRAME — CORRODED (FUSELAGE)

HAECO-HKG - FOUND LEFT WLG W/W AREA OUTBOARD OVERWING LONGERON INBOARD ATTACHMENT VERTICAL CHORD AT BS 1306 LBL 115 AND WL 160 LWR END FOUND CORRODED. CORROSION REMOVED PER SRM 51-10-01. BLENDED OUT CORROSION DEPTH .07 INCH, WIDTH 2 INCH, LENGTH 4 INCHES OUR OF SRM 53-10-01 LIMITS. REPLACED CHORD PER SRM 51-10-01 AND HAECO SRWS 000310. (M)

Part: LONGERON — CORRODED (FUSELAGE)

HAECO-HKG - LEFT FORWARD OVERWING LONGERON FORWARD END UPPER FLANGE OUTBOARD FACE ADJACENT NR 2 BOLT HOLE (FROM FWD) LOWER AREA FOUND CORROSION DURING BS 1241 BULKHEAD SPLICE STRAPS REPLACEMENT. CORROSION REMOVED PER SRM 51-10-01 AND REPROTECTED PER SRM 51-10-02. THICKNESS HECK CARRIED OUT FROM BS 1250-1253. NDT INSPECTED PER NTM PT6 51-00-00 FIG 4, CRACK FREE. REPLACED OVERWING LONGERON PER SRM 51-10-01 PAGE 18, DWG 65B26808, AND HAECO SRWS 000312. (M)

Part: STRINGER — CORRODED (FUSELAGE)

FOUND CORROSION ON BULKHEAD CARGO COMPARTMENT BS 2160-2170 STRINGER 5L. CORROSION REMOVED PER SRM 51-10-01. BLEND OUT DEPTH .03 INCH, WIDTH 1 INCH, LENGTH 2 INCH. REPAIRED STRINGER AT BS 2159-2180 STRINGER 51L PER SRM 53-10-03 AND HAECO SRWS 916651. (M)

Part: FITTING — CRACKED (PAX DOOR)

FOUND L1 DOOR FORWARD CUTOUT NR 6 STOP FITTING FOUND CRACKED. L1 DOOR FORWARD CUTOUT NR 6 STOP FITTING REPLACED PER SRM 51-10-01. (M)

Part: SHEAR TIE — CRACKED (FUSELAGE)

FORWARD CARGO COMPARTMENT, FRAME SHEAR TIE FOUND CRACKED AT BS 680 STRINGER 47L-47R APPROX .25 INCH LENGTH. SHEAR TIE REPAIRED PER SRM 53-10-04 AND HAECO SRWS 916958. (M)

Part: FRAME — CRACKED (FUSELAGE)

HAECO-HKG - C6/D-CHECK/PLY MOD - U/D BS 500 S10AR FRAME CRACKED APPROX 0.75 INCH LENGTH. U/D BS 500 FRAME BETWEEN STR ZERO TO STR 13R REPLACED. REF WS NR 062 EO 53-747-1143-91D AND DWG 624U0003 SH 25B FOR FRAME INSTALLATION. (X)

Part: SHEAR TIE — CRACKED (CENTER TANK)

HAECO-HKG - C6/D-CHECK - WING CENTER TANK FORWARD LBL 50 INCHES BS 1000 UPPER SHEAR TIE CRACKED. TRIMMED OFF, NDT INSPECTED OK, REPLACED CRACKED SHEAR TIE PER SRM 51-10-01. (X)

Part: BULKHEAD — CRACKED (FUSELAGE)

DURING ACCOMPLISHMENT OF BS 1480 BULKHEAD AND SPLICE COMPONENTS REPAIR AND MOD EO 53-747-1513-98C, LEFT BULKHEAD FASTENER HOLES NR 3, 5 AND 24, FOUND CRACKED. CARRIED OUT CRACK REMOVAL AND INSURANCE CUT PER EO 53-747-1513-98C PAR II AND BSB 53A2390. (M)

Part: SPLICE — DAMAGED (BULKHEAD)

HAECO-HKG - FOUND BS BH LEFT OUTER CHORD SPLICE FITTING NR 7 AND NR 8 BOLT HOLE TO CLOSE TO FLANGE WEB AFTER INSURANCE CUT PER EO 53-747-1513-98 REV C. BS 1480 BULKHEAD LEFT OUTER CHORD SPLICE FITTING REPLACED PER EO 53-747-1513-98 REV C ANS SB 747-53A-2380. (M)

Part: SHEAR TIE — CORRODED (FUSELAGE)

HAECO-HKG - FORWARD CARGO COMPARTMENT BS 820 STRINGER 45R-46R SHEAR TIE HEAVILY CORRODED. CORROSION REMOVED PER SRM 51-10-01. BLEND OUT CORROSION DEPTH .03 INCH, WIDTH 1.0 INCH, LENGTH 2 INCH OUT OF SRM 53-10-01 LIMITS. REPAIRED PER SRM 51-40-04 FIG 2 AND HAECO SRWS 000313. (M)

Part: LAP JOINT — CRACKED (FUSELAGE)

HAECO-HKG - C6/D-CHECK/PLY MOD - S41 MOD AT RT BS 360 - BS 380 S6 LAP SPLICE FOUND 3 EACH HOLES CRACKED AT UPPER SKIN. RT BS 360 - BS 380 LAP SKIN S6 SPLICE 3 EACH CRACKED HOLES AT UPPER SKIN 0.25 INCH STOP HOLES DRILLED PER SRM 51-10-01. FOUND WITHIN LIMITS PER SB 747-53-2272 FIG 16 SHEET 86. (X)

Part: ANGLE — CRACKED (NR 3 PYLON)

HAECO-HKG - NR 3 PYLON UNDERWING SKIRT FAIRING OUTBOARD SKATE ANGLE FORWARD FASTENER HOLE FOUND CRACKED. NR 3 PYLON UNDERWING OUTBOARD SKATE ANGLE REPLAED PER SRM 51-10-01. (M)

Part: FRAME — CORRODED (FUSELAGE)

HAECO-HKG - AFTER LEFT WLG W/W OVERWING LONGERON REMOVED, CORROSION FOUND AT OVERWING LONGERON ATTACH INNER CHORD AT BS 1301 LBL 120. CORROSION REMOVED PER SRM 51-10-01. BLENDED OUT CORROSION DEPTH .1 INCH, WIDTH 1 INCH, LENGTH 5 INCHES OUT OF SRM 53-10-01 LIMITS. REPLACED INNER CHORD FROM BS 1241 TO BS 1347 PER SRM 51-10-01 PAGE 18 AND HAECO SRWS 000311. (M)

Part: WEB — CRACKED (NR 3 PYLON)

FOUND NR 3 PYLON MID SPAR BULKHEAD WEB NAC STATION 205 CRACKED WITH PREVIOUS STANDARD REPAIR. REF SRM 54-10-03 PAGE 30. MID SPAR WEB REPAIRED PER SRM 54-10-03 FIG 12. (M)

Part: SKIN — CORRODED (FUSELAGE)

HAECO-HKG - C6/D-CHECK/PLY MOD - M/D BS 1345 PRESSURE DECK UPPER SKIN CORRODED AT LBL 116. CORROSION REMOVED PER SRM 51-10-01. BLEND-OUT CORROSION DEPTH 0.045 INCH, WIDTH 1.0 INCH, LENGTH 2.0 INCH. CORROSION BLEND-OUT NOT WITHIN SRM 53-10-01 LIMITS. REPAIRED PER HAECO SRWS NR 916566, SRM 53-10-07 FIG 2. CORROSION INHIBITOR COMPOUND APPLIED PER 51-24-13. (X)

Part: FRAME — DAMAGED (NR 3 PYLON)

HAECO-HKG - C6/D-CHECK - NR 3 PYLON AFT BULKHEAD LT CHORD FOUND FASTENER HOLE OVERSIZED. PLUGGED OVERSIZED HOLE, NDT INSPECTED AND OVERSIZE FASTENER INSTALLED PER BOEING MESSAGE EVR-HKG-00-00026H-00027H AND HAECO REPAIR SCHEME R-54-53-34319. (X)

Part: FITTING — CRACKED (PAX DOOR)

HAECO-HKG - C6/D-CHECK/PLY MOD - M/D L1 DOOR AFT FRAME DOOR STOP FITTING NR 1 CRACKED. STOP FITTING REPLACED PER SRM 51-10-01 PG 18 AND STOP CLEARANCE CHECKED PER MM 52-11-01. (X)

Part: RIB — CRACKED (NR 4 PYLON)

HAECO-HKG - C6/D-CHECK/PLY MOD - NR 4 PYLON LEFT SIDE FRAME AT NAC STA 235, APPROX 12.0 INCHES ABOVE LOWER FIREWALL, HAD 2 CRACKS APPROX 1.0 INCH IN LENGTH. NR 4 PYLON AT NAC STA 235 LT SIDE FRAME REPLACED PER SRM 51-10-01. (X)

Part: SKIN — CORRODED (CARGO DOOR)

HAECO-HKG - C6/D-CHECK - AFT CARGO COMPT AFT CARGO DOOR INTERIOR SKIN EDGE CORROSION AT STA 1916. CORROSION REMOVED PER SRM 51-10-01, BLEND OUT CORROSION DEPTH 0.02 INCH, WIDTH 1 INCH, LENGTH 3 INCHES. REPAIRED PER SRM 51-40-02 FIG 1 AND HAECO SRWS 196966. (X)

Part: SPAR — DAMAGED (WING)

HAECO-HKG - C6/D-CHECK/PYL MOD - LHW AT FSS 688 UPPER SPAR CHORD FOUND 1 EACH CRACKED FASTENER HOLE AT WEB. OVERSIZED HOLE TO REMOVE CRACK, NDT INSPECTED, FREEZE PLUG INSTALLED PER BOEING MESSAGE EVG-HKG-00-00029H AND HAECO REPAIR SCHEME R57-21-34328. TIME LIMITED REPAIR-REINSPECTION REQUIRED AT 2,200 FLIGHT CYCLES. (X)

Part: FITTING — CRACKED (NR 1 PYLON)

DURING ACCOMPLISHMENT OF EO54-747-1042-90, NR 1 PYLON REAR ENGINE MOUNT BULKHEAD FITTING FOUND CRACKED. NR 1 PYLON REAR ENGINE MOUNT BULKHEAD FITTING REPLACED PER SRM 51-10-01 PAGE 18 AND REWORKED PER EO54-747-1042-90. (M)

Part: FRAME — CRACKED (FUSELAGE)

HAECO-HKG - C6/D-CHECK/PLY MOD - RIGHT BS 2598 BULKHEAD, CRACK FOUND AT AFT INNER CHORD BETWEEN TWO FASTENERS. CRACK AREA TRIMMED OFF PER SRM 53-10-05 FIG 72. REPROTECTED PER SRM 51-10-02. NDT INSPECTED PER NTM PT6 51-00-00 FIG 4 - CRACK FREE. RIGHT BS 2598 B/H AFT INNER CHORD AT RBL 37 WL 320 REPAIRED PER SRM 53-10-04 FIG 72. (X)

Part: KEELBEAM — CORRODED (FUSELAGE)

HAECO-HKG - C6/D-CHECK/PLY MOD - L/G - LEFT WLG W/W STA 1341 - STA 1346. LBL 1-7 AREA UPPER KEEL BEAM CORRODED. CORROSION REMOVED IAW SRM 51-10-01. BLEND-OUT CORROSION DEPTH 0.02 INCH, WIDTH 2 INCHES, LENGTH 4 INCHES. OUT OF SRM 53-10-01 LIMITS. REF: HAECO SRWS NR 916838 KEEL BEAM UPPER WEB REPAIRED AT LEFT WLG W/W BS 1350 LBL 1-7 PER SRM 51-40-02W FIG 1. (X)

Part: CASE — CRACKED (NR 3 ENG EXHAUST)

FOUND CRACK LOCATED IN NR 15 STRUT OF NR 3 ENGINE TURBINE EXHAUST CASE AT APPROX 11:30 O'CLOCK POSITION (VIEWED FROM REAR) AND EXTENDING FORWARD APPROX 5.5 INCH FROM TRAILING EDGE OF STRUT. REPLACED NR 3 ENGINE TURBINE EXHAUSE CASE PER ECRA 662499-72-006-1 AND MM 71-21-04. (M)

Part: SKIN — CRACKED (FUSELAGE)

HECO-HKG - FOUND BS 1480 B/H AT STRINGER 34L HAS 1 CRACKED FASTENER HOLE, LEFT AT UPPER SKIN APPROX .02 INCH LENGTH AND LOWER SKIN THROUGH THICKNESS 3 O'CLOCK POSITION. OVERSIZED TO REMOVE CRACKS. SKIN FREEZE PLUGGED WITH RETAINING WASHERS INSTALLED PER BOEING MESSAGE EVR-HKG-00-00039F/00054H AND HAECO RS-53-61-34335, SRWS 000249 AND 000254. (M)

Part: FRAME — CRACKED (FUSELAGE)

HAECO-HKG - C6/D-CHECK - M/D BS 500 FRAME BETWEEN STR 13L TO STR 31L REPLACED PER DIA EO 53-747-1143-9 REV D AND DWG 624U0003 SH 35B FOR FRAME INSTALLATION. (X)

Part: FITTING — CRACKED (RT WING)

HAECO-HKG - C6/D-CHECK - RIGHT WING WS 669.5 RIB INBD STRUT FITTING MOST UPPER FASTENER HOLES 2 EACH FOUND CRACKED. SUPPORT FITTING REPLACED PER BSB 747-54A2159 REV 2 FIG 45 AND EIA EO 57-747-1386-94 REV F. (X)

Part: FITTING — DAMAGED (NR 4 YPLON)

HAECO-HKG - C6/D-CHECK - NR 4 PYLON OUTBOARD UPPER LINK FITTING FASTENER HOLE HAD SHORT EDGE MARGIN. HOLE INSPECTED AND FASTENER INSTALLED PER SB. THREAD TRIMMED PER HAECO REPAIR SCHEME R-57-04-34318 AND BOEING MESSAGE EVG-HKG-00-00024H/-00027F/-00027F/-00030F/-00022H. (X)

Part: SKIN — CORRODED (FUSELAGE)

HAECO-HKG - DURING AFT PRESSURE BULKHEAD MOD, M/D BS 2360 STRINGER 48R PRESSURE BULKHEAD FORWARD SKIN CORROSION FOUND. TRIMMED OF M/D BS 2360 STRINGER 48R PRESSURE BULKHEAD FORWARD SKIN CORROSION AREA PER SRM 51-10-01 AND AFT INNER SKIN. NDT INSPECTED PER NTM 51-00-00 PT6 FIG 4. REPAIRED PER RS R53-63-34329 AND BOEING MESSAGE EVG-HKG-00046H/-00046F/-00031F/-00043H. (M)

Part: STRINGER — CRACKED (FUSELAGE)

FOUND STRINGER END CRACKED AT BS 1477, STRINGER 5R. REPLACED STRINGER 5R AT BS 1460-1477, PER SRM 53-10-03 FIG 5 AND HAECO SRWS 916879. (M)

Part: SKIN — CRACKED (PAX DOOR)

HAECO-HKG - C6/D-CHECK - M/D R3 DOOR EXTERNAL SKIN CRACKED AT LOWER MID AREA. CRACKED AREA TRIMMED OFF PER SRM 51-10-01 (8 INCH LENGTH) AND REPROTECTED PER SRM 51-10-02. JFEC INSP PER NTM PT6 51-00-00 FIG 4-OK. R3 DOOR EXTERNAL SKIN REPAIRED PER SRM 52-00-03. (X)

Part: BRAKE — OVERHEATED (MLG)

ON ARRIVAL, LT WING AND BODY GEAR WHEEL BRAKES OVERHEATED. NR 4 WHEEL ASSY IGNITED, BUT WAS IMMEDIATELY EXTINGUISHED. NR 6 AND NR 7 WHEEL ASSY THERMAL FUSE PLUGS RELIEVED AND WHEELS DEFLATED. INSP OF GEAR AREAS CARRIED OUT OK AND MAIN WHEELS REPLACED (4, 6, AND 7). (X)

Part: BRAKE — MALFUNCTIONED (MLG)

PANC - ON TAKEOFF ROLL, AIRCRAFT VEERED TO THE LEFT, COULD NOT MAINTAIN DIRECTIONAL CONTROL WITH TILLER AND ABORTED TAKEOFF. SEVERAL LEFT WING GEAR BRAKE OVERHEAT LIGHTS ON. INSPECTED ALL BRAKES, NO EVIDENCE OF OVERHEATING. AIRCRAFT TAXI NORMAL AT ALL TIMES, WITH NO PULLING. NOSE TIRE PRESSURE CHECK NORMAL. PRESSURIZED HYD AND VERIFIED LEFT BRAKES BEING APPLIED AND RELEASED. NO DEFECTS NOTED. DURING NEXT TAKEOFF, AIRCRAFT OPERATED NORMALLY AND NO FURTHER PROBLEMS. (M)

Part: SKIN — CRACKED (FUSELAGE)

HKG - DURING C-CHECK, A CRACK WAS FOUND AT RIGHT NR 1 MED LOWER HINGE CUTOUT LOWER CORNER, SKIN CRACK .25 INCH - .375 INCH APPROX, RUNNING UNDERNEATH THE EXTERNAL DOUBLER. CRACK END CAN'T BE LOCATED. CRACK STOP DRILLED PER SRM 53-30-02, REPAIRED IAW HXRS 52-11-33. (M)

Part: COMPRESSOR — STALLED (NR 4 ENGINE)

LAX - ON DESCENT, NR 4 ENGINE COMPRESSOR STALLED, EGT RISING, DID NOT EXCEED 850 DEGREES N1 DECREASING, ACCOMPLISHED ENGINE SHUTDOWN. ATTEMPT RESTART, NO FUEL FLOW INDICATED. (M)

Part: TARGET — OUT OF ADJUST (CARGO DOOR)

PPG - DURING CRUISE, THE FORWARD CARGO DOOR LIGHT CAME ON. ADJUSTED TARGET ON DOOR CLOSE SWITCH AND OPERATIONALLY CHECKED NORMAL PER MM 52-32-00. (M)

Part: FRAME — CRACKED (BS 1700)

HKG - DURING C5 CHECK, BS 1700 FRAME CRACKED AT STRINGER 12R TO 13R. REPAIRED PER SRM 51-10-01. (M)

Part: WEB — CRACKED (BS 1346-1350)

HKG - DURIGN C5 CHECK, MD BS 1346 TO 1350 AT LBL 2 PRESSURE DECK UPPER SURFACE HAS CORROSION AND CRACK. REPAIRED PER RS R53-48-33957 AND ECRA 482-99-125-1. (M)

Part: STRINGER — CRACKED (BS 1000)

HKG - DURING C5 CHECK, BS 1000 STRINGER 39R TO 40R EXTERIOR SKIN CRACKED. REPAIRED PER SRM 53-30-01 FIG 1. (M)

Part: STRINGER — CRACKED (BS 140)

HKG - DURING C5 CHECK, BS 140 AT STRINGER 47L AFT BULKHEAD ATTACH SUPPORT FRAME CRACKED. REPAIRED PER SRM 51-40-03. (M)

Part: SPLICE — CRACKED (BS 1480)

HKG - DURING C5 CHECK, MD BS 1480 STRINGER 7L SPLICE HAS CORROSION AND CRACKS. REPAIRED BY REPLACING STRINGER SPLICE FITTING PER SRM 51-10-01. (M)

Part: SPLICE — CRACKED (BS 519)

HKG - DURNING C5 CHECK, MD BS 519 STRINGER 14L SPLICE CRACKED. REPAIRED PER SRM 51-10-1. (M)

Part: SPLICE — CRACKED (BS 780-800)

HKG - DURING C5 CHECK, BS 780-800 SKIN AND INTERNAL STRAP HAVE CORROSION FROM STRINGER 46L-46R. REPAIRED BY RS R53-21-33964, 8110-3 AND ECRA 481-99-125-1. (M)

Part: SKIN — CORRODED (WS 600)

HKG - DURING C5 CHECK, RIGHT WING LOWER SKIN AT WS 600, AT TRAILING EDGE HAS EXFOLIATION CORROSION. REPAIRED PER RS R57-26-33954 AND ECRA 482-99-125-1. (M)

Part: SKIN — DELAMINATED (MLG DOOR)

HKG - DURING C5 CHECK, LEFT WING LANDING GEAR INBOARD DOOR OUTER SKIN WAS FOUND DELAMINATED. REPAIRED DOOR PER RS R52-82-33959,8110-3 AND ECRA 482-99-125-1. (M)

Part: SKIN — CRACKED (NR 3 PYLON)

HKG - DURING C5 CHECK, NR 3 PYLON SKIN AT PANEL 473EL CUTOUT IS CRACKED, AND STIFFENER BEHIND IS CRACKED. REPAIRED PER RS R54-51-33962 AND ECRA 482-99-125-1. (M)

Part: BULKHEAD WEB — CRACKED (BS 1480)

HKG - DURING C5 CHECK, BS 1480 APU DUCT CUTOUT FASTENER HOLES CRACKED ON BULKHEAD WEB. REPAIRED PER SB 747-53-2309. (M)

Part: FITTING — CRACKED (BS 2484)

HKG - DURING C5 CHECK, BS 2484 FORWARD LOWER LEFT SPLICE FITTING VERTICAL LEG 2ND OUTBOARD FASTENER HOLE CRACKED. REPLACED SPLICE FITTING PER SB 747-53-2162. (M)

Part: FRAME — CRACKED (BS 320)

HKG - DURING C5 CHECK, BS 320 RIGHT FRAME CRACKED AT STRINGER 14. REPAIRED FRAME PER RS R-53-12-33953, 8110-3, ECRA 482-99-125-1. (M)

Part: WEB — CRACKED (BS 1480)

HKG - DURING C5 CHECK, BS 1480 APU DUCT CUTOUT FASTENER HOLES CRACKED ON BULKHEAD WEB. REPAIRED PER SB 747-53-2309. (M)

Part: FRAME — CRACKED (BS 1620)

HKG - DURING C5 CHECK, AFT BAG BIN FRAME CRACKED AT BS 1620 STRINGER 39R-40R. REPAIRED FRAME PER SRM 53-10-04 FIG 69. (M)

Part: FLOORBEAM — CORRODED (FUSELAGE)

DURING C5 CHECK, M/D BS 460 AT LBL 90 FLOORBEAM LOWER TEE HAS CORROSION. REPAIRED PER SRM 51-40-04 FIG 2. (M)

Part: FLOORBEAM — CORRODED (BS 460)

HKG - DURING C5 CHECK, MD BS 460 AT LBL 90 FLOORBEAM LOWER CHORD HAS CORROSION. REPAIRED PER SRM 51-40-4 FIG 2. (M)

Part: SPLICE — CRACKED (BS 2484)

HKG - DURING C5 CHECK, BS 2484 FORWARD LOWER LEFT SPLICE FITTING VERTICAL LEG 2ND OUTBOARD FASTENER HOLE CRACKED. REPLACED SPLICE FITTING PER SB 747-53-2162. (M)

Part: SPLICE — CRACKED (BS 400)

HKG - DURING 'C5' CHECK, BS 400 NOSE LANDING GEAR WHEEL WELL AFT DOOR CUTOUT LEFT AND RT SPLICE PLATES CRACKED. REPAIRED PER SB 747-53-2305 AND DRAWING 14101099. (M)

Part: FRAME — CRACKED (BS 1620)

HKG - DURING C5 CHECK, AFT BAG BIN, FRAME CRACKED AT BS 1620 STRINGER 39R-40R. REPAIRED FRAME PER SRM 53-10-04 FIG 69. (M)

Part: SKIN — CORRODED (HORIZ STABILIZER)

HKG - DURNG C5 CHECK, LEFT HORIZONTAL STAB UPPER SKIN AT ST 310-335 AND 360-385 HAS CORROSION. REPAIRED PER RS R-55-13-33958, 8110-3 AND ECRA 482-990125-1. (M)

Part: SENSOR — MALFUNCTIONED (E/E BAY)

AMS - WHEN FLAPS WERE RETRACTED TO 1 DEGREE DURING ASSENT, STICK SHAKER ACTIVATED, NOSE OSCILLATED UP AND DOWN. SPEED INCREASED TO 300 KTS PITCH OSCILLATION CONTINUED, FLAPS EXTENDED TO 5 DEGREES, OSCILLATION STOPPED. DECLARED EMERGENCY AND PREPARED A/C FOR OVERWEIGHT LANDING. (M)

Part: BULKHEAD FRAME — CRACKED (NR 2 PYLON)

HKG - LOG PAGE: F08701 - DURING B-CHECK, NR 2 PYLON AFT MOUNT BULKHEAD OTBD WEBS (FWD AND AFT) WERE FOUND CRACKED. REPAIRED, REPLACED BULKHEAD WEB AND FRAMES PER SB 747-54-2065, RS R54-53-33775, AS APROVED ON ECRA 482-54-122-1. (X)

Part: FAIRING — CRACKED (WING BODY)

SYD - LOG PAGE: F27377 - WING TO BODY FAIRING DAMAGED BEHIND LT BODY GEAR FROM NR 8 TIRE TREAD SEPARATION. TEMP REPAIRED PER SRM 51-40-16, PERMANENT REPAIR NEXT SCHEDULED A-CHECK. REF: OPERATION CONTROL NR EIAA970195 AND 97ZZZX4781.

Part: FAIRING — CRACKED (WING BODY)

SYD - LOG PAGE: F27377 - WING TO BODY FAIRING DAMAGED BEHIND LT BODY GEAR FROM NR 8 TIRE TREAD SEPARATION. TEMP REPAIRED PER SRM 51-40-16, PERMANENT REPAIR NEXT SCHEDULED A-CHECK. REF: OPERATION CONTROL NR 97ZZZX4780 AND 97ZZZX4781. (X)

Part: FAIRING — CRACKED (WING BODY)

SYD - LOG PAGE: F27377 - WING TO BODY FAIRING DAMAGED BEHIND LT BODY GEAR FROM NR 8 TIRE TREAD SEPARATION. TEMP REPAIRED PER SRM 51-40-16, PERMANENT REPAIR NEXT SCHEDULED A-CHECK. REF: OPERATION CONROL NR EIAA970195 AND 97ZZZX4782.

Part: ACTUATOR — FAILED (NR 7 SPOILER)

JFK - DURING FLIGHT SPOILER DEPLOYMENT, THE AIRCRAFT MOMENTARILY ASSUMED A LEFT WING LOW ATTITUDE, REQUIRING A RIGHT AILERON FORCE TO MAINTAIN LEVEL FLIGHT. OPERATED SPOILERS ON THE GROUND. FOUND NR 7 PANEL ACTUATOR ATTACHMENT POINT CRACKED. REPLACED SPOILER PANEL PER MM 27-62-01 AND ACTUATOR PER 27-62-05, OPS CHECKED NORMAL AND LEAK CHECKED OK. (M)

Part: PANEL — CRACKED (NR 7 SPOILER)

JFK - DURING FLIGHT SPOILER DEPLOYMENT, THE AIRCRAFT MOMENTARILY ASSUMED A LEFT WING LOW ATTITUDE, REQUIRING A RIGHT AILERON FORCE TO MAINTAIN LEVEL FLIGHT. OPERATED SPOILERS ON THE GROUND. FOUND NR 7 PANEL ACTUATOR ATTACHMENT POINT CRACKED. REPLACED SPOILER PANEL PER MM 27-62-01 AND ACTUATOR PER 27-62-05, OPS CHECKED NORMAL AND LEAK CHECKED OK. (M)

Part: ENGINE — FAILED (NR 2)

JFK - LOG PAGE: E06131 - SHORTLY AFTER STARTING DESCENT, THE FLIGHT ENGINEER REPORTED THE NR 2 ENGINE OIL QUANTITY INDICATED ONE GALLON. APPROXIMATELY ONE MINUTE LATER, THE OIL PRESSURE LIGHT ON THE ANNUNCIATOR PANEL STARTED BLINKING AND THE OIL PRESSURE DROPPED BELOW 35 PSI. AN IN-FLIGHT ENGINE SHUT DOWN WAS ACCOMPLISHED. ENGINE OIL QUANTITY INDICATED ONE-HALF GALLON. (X)

Part: T-CHORD — CRACKED (LT/RT WING)

DURING C-CHECK INSPECTION DISCOVERED CRACKED AND BROKEN UPPER 'T' CHORDS OF BOTH THE LEFT AND RIGHT WINGS AT THE TRAILING EDGE BEAM AT WBL 235.2. RIGHT WING HAD AN 2 INCH CRACK AND THE LEFT WING HAD A BROKEN FORWARD EDGE OF THE FORWARD HORIZONTAL FLANGE OF THE 'T' CHORD. REPAIRED BY TRIMMING OUT THE DAMAGED AREAS AND SPLICING IN NEW UPPER 'T' CHORDS. ACCOMPLISHED IAW EIAA, ENGINEERING CHANGE/REPAIR AUTHORIZATION NR 482-57-116-2. (M)

Part: SKIN — CORROSION (WS 564)

DURING C-CHECK INSPECTION DISCOVERED CORROSION ON THE LEFT WING LOWER SKIN FORWARD OF THE FRONT SPAR LOWER CHORD AT APPROX WING STATION 564. REPAIRED BY SPLICING IN A NEW SECTION OF REINFORCEMENT STRAP AND INSTALLING A REPAIR DOUBLER AT THE THE LOCATION OF THE CORROSION BLENDOUTS. ACCOMPLISHED IAW EIAA, ENGINEERING CHANGE/REPAIR AUTHORIZATION NR 482-57-113-2. (M)

Part: BULKHEAD — CORRODED (BS 2360)

DURING C-CHECK INSPECTION, DISCOVERED CORROSION BETWEEN THE FUSELAGE SKIN AND THE AFT FLANGE FO THE STA 2360 PRESSURE BULKHEAD AFT OUTER CHORD. THE CORROSION EXTENDED ALONG THE ENTIRE WIDTH OF THE AFT CHORD FROM STRINGER 46R TO 51R. REPAIRED BY TRIMMING AWAY THE CORROSION, ROTOPEENED THE AFFECTED AREA AND PERFORMED STRUCTURAL REPAIR MANUAL 53-10-04 FIG 5, SHEET 10, VIEW F-F REPAIR INSTALLING REPAIR PARTS WET WITH SEALANT. ACCOMP IAW EIAA, ENGINEERING CHANGE/REPAIR AUTHORIZATION NR 482-53-114-2. (M)

Part: CONNECTOR — FAILED (L1 WINDOW)

KLAX - LOG PAGE: F27565 - STRONG ELECTRICAL FUMES IN COCKPIT, ORIGINS UNKNOWN. FOUND CONNECTOR D401 WAS ARCING AND METLED ON L-1 WINDOW. REPAIRED PER ECRA 48230-08803 CAP AND STOW CONNECTOR D405. USED CONNECTOR FROM D405 IN POSITION D401. INSPECTED WINDOW AND WIRING AND FOUND NO ADDITIONAL DAMAGE. WINDOW HEAT OP CHECKS NORMAL. (X)

Part: CIRCUIT BREAKER — CHARRED (NR 2 HF)

KLAX - LOG PAGE: F27562 - DURING CRUISE FLIGHT, A STRONG ELECTRICAL ODOR WAS NOTICED BY THE CREW EMANATING FROM THE COCKPIT. THE ODOR CAME ON INTERMITTENTLY. UNABLE TO DETERMINE THE SOURCE OR ORIGIN BY ISOLATING OR TURNING OFF CERTAIN COMPONENTS. INSPECTED BEHIND ALL CIRCUIT BREAKER PANELS. FOUND HF NR 2 AC C/B DISCOLORED AND CHARRED. REPLACED C/B. OPERATIONAL CHECKS GOOD, ALL OTHER AREAS CHECKED OK. (X)

Part: LIGHT — FAILED (LT COCKPIT)

EBBR - DURING CRUISE AT FL 330, ALL THREE CREW MEMBERS NOTICED AN ELECTRICAL ODOR. ISOLATED TO CAPTAINS MAP LIGHT RHEOSTAT. TURNED OFFLIGHT, ODOR DISSIPATED. TRANSFERRED TO DMI NR 217 AS PER MEL 33-1. PULLED MAP LIGHT C/B AND SECURED. PLACARDED MAP LIGHT 'INOP'. (M)

Part: BULKHEAD — CORRODED (BS 1480)

MZJ - DURING REPLACEMENT OF THE LT BODY GEAR ASSY, WIDESPREAD CORROSION WAS FOUND IN THE LT O/B BODY GEAR TRUNNION SUPPORT ASSY. CORROSION WAS FOUND IN THE BS 1480 BULKHEAD FWD FITTING INTERFACE SURFACE AT WL 116 AND 127. CORROSION WAS FOUND IN THE AFT SURFACE OF STA 1480 BULKHEAD, LOCATED IN THE LOWER PORTION OF THE BULKHEAD AT LBL 64, WHERE IT IS SANDWICHED BETWEEN THE SUPPORT FITTING ASSY AND THE LT O/B DAGGER FITTING. ALL OF THE CORROSION WAS BLENDED AWAY, HFEC INSPECTION AND PROPERLY TOP COATED. REPAIRED IAW EIAA ECRA 482-53-103-2. (M)

Part: VALVE — MALFUNCTIONED (LT MLG DOOR)

LAX - ON DEPARTURE, ON GEAR RETRACTION, LEFT BODY GEAR DOOR LIGHT REMAINED ILLUMINATED IN PRIMARY AND ALTERNATE. ACCOMP ABNORM CHECKLIST AND LIGHTS REMAINED ILLUMINATED. AIR TURN BACK. FOUND L/G DOOR SAFETY VLV NOT FULLY ACTUATING. LUBED ALL PUSHRODS AND ATTACHMENTS, CHECKED CABLES AS PER CAUTION IN MM 32-35-01 PAGE 501. PUT ALTERNATE EXTENSION SWITCH TO ARM POSITION TO ENSURE ELECT ACT PROPER POSITION. USING MANUAL RELEASE GEAR DOOR HANDLE ALL OPS AND IND GOOD. PINNED L/G AND CARRIED OUT OPS AND IND CHECK. ALL CHECKS USING GEAR HANDLE AT COCKPIT WERE GOOD. (M)

Part: PDU — FAILED (RT LE FLAP)

LCK - LOG PAGE: E04038 - ON DEPARTURE, GROUP NR 1 LEADING EDGE DEVICE LT WING HAD INTRANSIT LIGHT ILLUMINATE ABOUT 4 MINUTES AFTER RETRACTION. FLAP WAS RETRACTED BY THE ALTERNATE METHOD. ALTERNATE METHOD WAS USED FOR LEADING EDGE FLAPS FOR REMAINDER OF FLIGHT SUCCESSFULLY. AFTER LANDING WHEN ATTEMPTING TO RETRACT LEADING EDGE FLAPS BY ALTERNATE METHOD, GROUP NR 3 LT WING INTRANSIT LIGHT REMAINED ON AND GROUP NR 3 RT WING EXTENDED LIGHT REMAINED ON. GROUP 3 ALT L/E CIRCUIT BREAKER TRIPPED. REPLACED NR 3 R/T L/E PDU. OPS CHECK NORMAL, RII ACCOMPLISHED. (X)

Part: ENGINE — SURGED (NR 2)

AFTER TAKEOFF, WHEN POWER WAS REDUCED FOR CRUISE SETTING, NR 2 ENGINE SURGED WITH INCREASING EGT ENGINE WAS SHUT DOWN AND RESTARTED WITH ABNORMALLY HIGH EGT (720) FOR IDLE THRUST POWER SETTING AT FL 350. WITH ENGINE RESTARTED N2 AT IDLE WAS 50 PERCENT. NO LIMITATIONS EXCEEDED. ENGINE WAS SHUTDOWN AGAIN FOR HIGH EGT. PERFORMED ENGINE WINDMILLING CHECK, INSPECTION OF ALL VISIBLE VANES, BLEED AND FUEL CONTROL UNIT PLUMBING WITH NO DEFECTS EVIDENT. FULE PUMP PRESSURE CHECKED AT 600 PSI. ENGINE IDLE RUN CARRIED OUT AND ALL PARAMETERS WITHIN LIMITS. SUBSEQUENT FLT WAS NORMAL. (M)

Part: TIRE — FAILED (NR 5)

ANC - UPON LANDING AT ANC, FOUND NR 5 TIRE TREAD SEPARATED, HOWEVER, THE TIRE WAS STILL INFLATED. THE LEFT BODY MLG OUTBOARD DOOR AND ADJACENT AREA SUFFERED DAMAGE AS A RESULT. REMOVED AND REPLACED NR 5 AND NR 6 TIRE ASSEMBLY. TEMPORARY REPAIR ACCOMPLISHED ON THE LT BMLG OUTBOARD DOOR AND ADJACENT AREA PER ECRA 482-52-101-1 TO FLY AIRCRAFT TO JFK, WHERE PERMANENT REPAIR WAS ACCOMPLISHED. (X)

Part: COMPRESSOR — DAMAGED (NR 1 ENGINE)

JFK - WHILE TROUBLESHOOTING NR 1 ENGINE THROTTLE BINDING, FOUND APPROXIMATELY 1 INCH BY 6 INCH PIECE ROLLED BACK ON THE STAGE 7 COMPRESSOR CASE JUST ABOVE THE FUEL OIL COOLER ATTACH FLANGE. REMOVED AND REPLACD ENGINE NR 1. FURTHER INVESTIGATIN IS UNDERWAY. REF: CONTROL NR 96-14. (X)

Part: CARBON SEAL — LEAKING (HYD PUMP)

JFK - LOG PAGE F00707 - NR 4 ENGINE OIL QUANTITY INDICATOR STEADILY DROPPED TO APPROXIMATELY 1 GALLON, THEN PEGGED OUT. SHUT DOWN ENGINE DUE TO FLUX OIL PRESSURE AND UNKNOWN QUANTITY, MAXIMUM TEMPERATURE 110 DEGREES FOR 1 MINUTE, WINDMILLING PRESSURE, 14 PSI. OPS CHECK OF ENG, SYSTEM WORKS NORMALLY. PERFORMED ENG WINDMILLING INSP PER 72-00-00, GEARBOX STATIC LEAK CHECK CARRIED OUT, FOUND HYD PUMP SEAL DRAIN LEAKING, CHANGED CARBON SEAL. AFTER POWER RUN, FOUND NR 3 BEARING DRAIN ELBOW LEAKING. REPLACED ELBOW, FOUND COVER ON GEARBOX LEAKING, RETORQUED BOLTS. REFERENCE OPERATOR CONTROL NR 95ZZZX6633. (X)

Part: DRAIN ELBOW — LEAKING (NR 3 BEARING)

JFK - LOG PAGE F00707 - NR 4 ENGINE OIL QUANTITY INDICATOR STEADILY DROPPED TO APPROXIMATELY 1 GALLON, THEN PEGGED OFF. SHUT DOWN ENGINE DUE TO FLUX OIL PRESSURE AND UNKNOWN QUANTITY, MAXIMUM TEMPERATURE 110 DEGREES FOR 1 MINUTE, WINDMILLING PRESSURE, 14 PSI. OPS CHECK OF ENG, SYSTEM WORKS NORMALLY. PERFORMED ENG WINDMILLING INSP PER 72-00-00, GEARBOX STATIC LEAK CHECK CARRIED OUT, FOUND HYD PUMP SEAL DRAIN LEAKING, CHANGED CARBON SEAL. AFTER POWER RUN, FOUND NR 3 BEARING DRAIN ELBOW LEAKING. REPLACED ELBOW, FOUND COVER ON GEARBOX LEAKING, RETORQUED BOLTS. REFERENCE OPERATOR CONTROL NR EIAA9562. (X)

Part: ENGINE — OVERTEMP (NR 1)

CYQX - OVERTEMP NR 1 ENGINE, APPROX 1150 CELSIUS FOR 5 TO 10 SECONDS, SHUTDOWN ENGINE DURING LANDING. ACCOMPLISHED OVERTEMP INSPECTION PER B747 MM 72-00-00 PAGE 601, BORESCOPED HPT, LPT, COMBUSTION CHAMBER, NGV NO DEFECTS NOTED, VISUALLY INSPECTED ENGINE EXTERNALLY, INTAKE AND EXHAUST, NO DEFECTS NOTED. PERFORMED FULL POWER RUN. ALL PARAMETERS WITHIN LIMITS. (M)

Part: CONTROL CABLE — OUT OF ADJ (AILERONS)

JFK - LOG PAGE: F 03234 - AILERON CONTROL TO RIGHT BINDING, NO DIFFERENCE FLAPS RETRACTED/EXTENDED. RIGGED LOAD LIMIT INPUT CABLE REF M6670, RIGGED BACK DRIVE LOAD LIMIT ROD REF M6671, ADJUSTED RT AILERON INBD INPUT ROD REF 6672, OPS CHECK PER 27-11-00. (X)

Part: EEL WIRE — BROKEN (CABIN)

SBGR - RIGHT SIDE EMERGENCY LIGHTS C-ZONE INOP. NO PASSENGERS ALLOWED IN C-ZONE. ALTERNATE LIGHTS INOPERATIVE TRANSFERRED TO DMI NR 746 PER MEL 33-16-1. REPAIRED WIRING AT SEATS 22, 25, 27 AND 30. AIRCRAFT RIGHT EMERGENCY LIGHTS OPERATIONAL CHECK PER MM 33-50-00 CLEARED DMI NR 476. (M)

Part: EEL BATTERY PACK — DISCHARGED (CABIN)

JED - LOG PAGE E 0844 - ZONE 'D' EMERGENCY PATH LIGHT FAILS TO ILLUMINATE ON TEST. REPLACED ZONE 'D' EPLS BATTERY PAC IAW MM 33-51-50, TESTED OK. (X)