N858FT

Part: TIRE — FAILED (MLG) · airframe 80,599 hrs · 19,134 cycles

ON TAXI INTO BLOCKS NR 10 AND 12 THERMALED. REPLACED NR 9, 10, 11 AND 12 TIRES IAW MM 32-45-01.

Part: ACTUATOR — MALFUNCTIONED (NR 1 ENGINE) · airframe 80,372 hrs · 19,086 cycles

AFTER ENGINE START, NR 1 ENGINE RAN FOR APPROX 3 MINUTES THEN SHUT DOWN. REPLACED NR 1 ENGINE SPAR VALVE ACTUATOR, MM 28-22-01.

Part: VALVE — LEAKING (FUEL SYSTEM) · airframe 80,349 hrs · 19,080 cycles

FUEL LEAKING OUT OF LEFT WING OUTBOARD FRONT SPAR. RESEATED POPPED VALVE ON LEFT SPAR. INSPECTED OK NO LEAKS, OPS OK PER MM 28-11-04.

Part: CONNECTOR — LOOSE (FIRE SQUIB) · airframe 80,267 hrs · 19,061 cycles

NR 2 ENGINE SQUIB TEST FAILED ON FLIGHT ENGINEER PREFLIGHT. CLEANED AND RESEATED NR 2 ENGINE RT FIRE EXTINGUISHER BOTTLE SQUIB PLUG PER MM 26-11-00.

Part: BOLT — SHEARED (MLG) · airframe 79,945 hrs · 18,990 cycles

RIGHT WING LANDING GEAR SUPPORT BEAM GATE BEARING ATTACHMENT SUPPORT UPPER VERTICAL BOLT SHEARED AND MIGRATED. REF IPC 57-15-05-0 ITEM 290. SHEARED BOLT REMOVED AND NEW BOLT /WASHERS/ NUT INSTALLED AND TORQUED IAW SRM 51-30-04 FIG 1 SHT 2 TABLE AND MM 57-15-00 FIG 201.

Part: LINE — LEAKING (FUEL SYSTEM) · airframe 79,945 hrs · 18,990 cycles

NR 2 ENGINE FUEL LEAK. REPLACED NR 2 ENGINE FUEL LINE (DRY BAY AREA). LEAK CHECK OK PER MM 28-22-00.

Part: ENGINE — FAILED (NR 1) · airframe 79,801 hrs · 18,961 cycles

AFTER TAKEOFF, NR 1 ENGINE FELT LARGE BANG ALONG WITH EGT OFF SCALE HIGH. SHUT DOWN ENGINE. REMOVED AND REPLACED NR 1 ENGINE MM 71-00-02.

Part: WARNING SYSTEM — INOPERATIVE (COCKPIT) · airframe 79,318 hrs · 18,854 cycles

ON PRE-FLIGHT, FOUND NO T/O WARNING ALTITUDE SELECT OR AUTOPILOT DISCONNECT WARNINGS. REPLACED AURAL WARNING DEVICE. OPS CHECK NORMAL IAW 31-26-02.

Part: SMOKE — DETECTED (AIR CON SYS) · airframe 78,812 hrs · 18,748 cycles

CREW REPORTED WHEN POWER WAS REDUCED FOR DESCENT. SMOKE WAS SEEN COMING FROM AIR CONDITIONING SYSTEM. GRADUALLY REDUCED TO NOTHING OVER 15 MINUTES TIME. INSPECTED AIR CONDITIONING SYSTEM AND ACM’S. PERFORMED OPERATION CK PER 21-20-00. NO DEFECTS NOTED. OPS NORMAL.

Part: ACTUATOR — MALFUNCTIONED (RUDDER) · airframe 78,774 hrs · 18,742 cycles

INBOUND CREW REPORTED RUDDER RATIO LIGHT ON STEADY. T/S FOUND LOWER RUDDER ACTUATOR STUCK IN HIGH SPEED MODE. REMOVED AND REPLACED LOWER RUDDER RATIO ACTUATOR AND CONTROLLER PER MM 27-21-12. ALL OPS NORMAL.

Part: ANTI-ICE SYSTEM — NO TEST (PITOT PROBE) · airframe 81,014 hrs · 19,227 cycles

DURING CREW PRE-FLIGHT, FOUND LT UPPER PITOT STATIC PROBE HEAT WOULD NOT TEST. REPLACED PITOT PROBE IAW AMM 34-11-01.

Part: WARNING LIGHT — ILLUMINATED (NR 4 ENG FIRE) · airframe 78,509 hrs · 18,688 cycles

DURING FULL THRUST T/O AT 650', NR4 ENGINE FAILED WITH FIRE INDICATION. SHUT DOWN ENGINE AND FIRED BOTTLES. REPLACED LEFT AND RIGHT FIRE BOTTLES PER MM 26-21-03. ALL TESTS OK.

Part: ENGINE — FAILED (NR 4) · airframe 78,509 hrs · 18,688 cycles

DURING FULL THRUST T/O 650' NR 4 ENGINE FAILED WITH FIRE INDICATION. SHUT DOWN ENGINE AND FIRED BOTTLES. REPLACED NR 4 ENG PER WC 7100-002. RUN UP OK.

Part: PUMP — LEAKING (NR 4 ENGINE) · airframe 78,486 hrs · 18,683 cycles

NR 4 HYDRAULIC QUANTITY WENT TO ZERO IN CLIMB. FOUND HYDRAULIC LEAK ON NR 4 ENG EDP. REMOVED EDP AND INSTALLED HYDRAULIC PUMP FROM THE NR 3 ADP POSITION. OPS AND LEAK CHECK OK. NR 3 ADP DEACTIVATED PER MEL 29-2A.

Part: TIRE — LEAKING (NR 4) · airframe 78,444 hrs · 18,675 cycles

NR 4 TIRE FOUND WITH SCREW IMBEDDED AND LEAKING AIR. REPLACED WHEEL ASSY PER MM 32-45-01. SPIN & LEAK CHECK OK.

Part: MODULE — MALFUNCTIONED (ANTI-SKID SYS) · airframe 78,377 hrs · 18,659 cycles

AFTER LANDING TOWER REPORTED SUSPECTED BLOWN TIRES. AT BLOCKS, FOUND NR 10 & 12 TIRES BLOWN. ON CONDITIONAL INSPECTION FOUND DAMAGE TO RT UPPER AFT WING/BODY FAIRING BETWEEN STA 1540 AND 1580. ALSO FOUND DAMAGE TO RT INBD TRAILING EDGE MID FLAP. REPLACED NR 10 & 12 TIRES. REPLACED NR 9 & 11 TIRES DUE ON SAME AXLES AS FAILED TIRES. REPAIRED RT UPPER AFT WING/BODY FAIRING PANEL PER SRM 53-40-12. REPAIRED RT INBD MID FLAP PER 51-40-12. REPLACED ANTI-SKID CONTROL MODULE PER MM 32-42-02. OPS & LEAK CHECK OK.

Part: CHAIN — CONTAMINATED (STAB TRIM WHEEL) · airframe 78,278 hrs · 18,637 cycles

DURING STAB TRIM CHECK STAB TRIM BINDING IN BOTH ELECTRICAL & MANUAL. CLEANED DEBRIS ON STAB TRIM CONTROL WHEEL CHAIN, INDICATIONS CHECKED NORMAL.

Part: WINDOW — CRACKED (COCKPIT) · airframe 78,159 hrs · 18,609 cycles

ON CLIMBOUT FROM ANCHORAGE THE R1 WINDOW STARTED ARCING & CRACKING. A 15 INCH CRACK DEVELOPED ON THE TOP EDGE OF THE WINDOW. FUEL WAS JETTISONED & A/C RETURNED TO ANCHORAGE. REMOVED & REPLACED R1 WINDOW.

Part: SEAL — FAILED (NR 1 ENGINE) · airframe 78,140 hrs · 18,605 cycles

DURING CRUISE AT FL 36.0, NR 1 ENGINE OIL PRESSURE FLUCTUATING 40-35 PSI WITH OIL PRESSURE LIGHT DOING SAME. OIL PRESSURE WENT TO 25 PSI WITH STEADY LOW OIL PRESSURE LIGHT ON, ENGINE SHUTDOWN, WINDMILLING OIL PRESSURE 15-20 PSI. REPLACED STARTER SEAL PER AMM 80-11-02 & 80-11-00, PERFORMED ENGINE RUN UP, LEAK CHECK NORMAL PER AMM 71-00-00.

Part: SKIN — DELAMINATED (RT WING) · airframe 78,122 hrs · 18,599 cycles

RT WING FIXED L/E UPPER SKIN B/W WING STATION 570 AND 600 LWR SURFACE DELAMINATED. REMOVED PANEL REPAIRED AND REINSTALLED IAW SRM 51-30-02.

Part: STRINGER — CRACKED (FUSELAGE) · airframe 78,122 hrs · 18,599 cycles

AFT CARGO COMPARTMENT LT BS 1600 STRINGER 39L AND STRINGER 40L CRACKED. STOP DRILLED, FABRICATED DOUBLER AND INSTALLED IAW SRM 53-10-04.

Part: SKIN — CORRODED (RT WING) · airframe 78,122 hrs · 18,599 cycles

RT WING UPPER SKIN HAS CORROSION AT WING STATION 697 MID SPAR. BLENDED OUT CORROSION, WITHIN LIMITS IAW SRM 57-30-01 AND 57-30-03.

Part: FLAP TRACK — CORRODED (NR 6) · airframe 78,122 hrs · 18,599 cycles

NR 6 FLAP TRACK AFT ATTACHMENT IB BLOCK OB HOLE CORRODED ON WING AT STA 353. REMOVED CORROSION, OPEN HOLE HFEC PERFORMED OK, REPAIRED IAW SRM 51-10-01.

Part: STRINGER — CRACKED (FUSELAGE) · airframe 78,122 hrs · 18,599 cycles

FUSELAGE STRINGER 9R HAS CRACKS AT BODY STATIONS 1372 AND 1394. REMOVED SHEAR TIE CLIPS, REMOVED STRINGER 11R FOR ACCESS, REMOVED STRINGER INSTALLATION AND INSTALLED NEW STRINGER IAW SRM 51-30-02 , REMOVE STRINGERS AND SHEAR TIE CLIPS.

Part: SKIN — DELAMINATED (LT WING) · airframe 78,122 hrs · 18,599 cycles

LEFT WING STATION 382 UPPER SURFACE ON TOP PANEL BY STRUT DELAMINATED & CRACKED. REMOVE PANEL & REBONDED, REINSTALLED PER SRM 51-10-09.

Part: SKIN — CANNING (FUSELAGE) · airframe 78,122 hrs · 18,599 cycles

BS 2360 TO 2380 STRINGER LEFT IS OIL CANNING. PERFORM HFEC, NO CRACKS. REMOVED AND REPLACED SKIN PER SRM 51-10-02.

Part: ATTACH FITTING — CRACKED (RT WING) · airframe 78,122 hrs · 18,599 cycles

RIGHT WING L/E AFT ATTACHED FRAME (FSSI) TO WING FRONT SPAR UPPER CHORD HAS CRACKED AFT FSSI 335. REMOVED CRACK T-ANGLE & INSTALLED NEW T-ANGLE PER SRM 51-30-02.

Part: FRAME — CRACKED (FUSELAGE) · airframe 78,122 hrs · 18,599 cycles

MAIN DECK CEILING AREA FRAME WEB STA 960 STR 5R CRACKED. STOP DRILL CRACK PER SRM 51-30-02, 53-10-04, 51-00-00.

Part: SKIN — DELAMINATED (RT ELEVATOR) · airframe 78,122 hrs · 18,599 cycles

RIGHT I/B ELEVATOR LWR SURFACE SKIN HAS DELAMINATION. REMOVED DAMAGE AREA, INSTALLED NEW PER SRM 51-40-04.

Part: FRAME — CRACKED (FUSELAGE) · airframe 78,122 hrs · 18,599 cycles

AFT CARGO COMPT SECONDARY FRAME B/W STA 1740 & 1760 LBL 30 IS CRACKED. REMOVED DAMAGE FRAME & INSTALLED NEW FRAME PER SRM 51-30-02.

Part: PANEL — CRACKED (RT WING) · airframe 78,122 hrs · 18,599 cycles

RIGHT WING I/B FIXED T/E LWR PNL, I/B EXTENDED CHORD HAS CRACK 2 INCHES LONG AT WS 440. REMOVE CHORD INSTALLED NEW CHORD AS PER SRM 51-30-02.

Part: STRINGER — CRACKED (FUSELAGE) · airframe 78,122 hrs · 18,599 cycles

FUSELAGE STRINGER AT 10R HAS CRACK B/W STA 1372-1392. REMOVED DAMAGE AREA, REPLACED WITH NEW STRINGER AS PER SRM 53-10-03.

Part: SKIN — DELAMINATED (RT WING) · airframe 78,122 hrs · 18,599 cycles

RT WING L/E UPPER SKIN BETWEEN WING STATIONS 445-476 LOWER SURFACE IS DELAMINATED. REMOVED PANEL & SENT TO COMPOSITE SHOP, REPAIRED & REINSTALLED PER SRM 51-40-09.

Part: SPAR — CORRODED (LT WING) · airframe 78,122 hrs · 18,599 cycles

LT WING REAR SPAR LWR FIXED T/E PANEL I/B LWR BEAM AT WBL 128 HAS CORROSION AT FWD TENSION TRES. REMOVE CORRODED DOUBLER, INSTALLED NEW DOUBLER, TREATED & PRIMED PER SRM 51-40-02.

Part: SKIN — CORRODED (HORIZONTAL STAB) · airframe 78,122 hrs · 18,599 cycles

RT HORIZONTAL STAB T/E UPPER SURFACE ENTIRE LENGTH SKIN SEVERAL AREA HAS CORROSION. REMOVE CORROSION FROM SEVERAL AREAS, TREATED & PRIMED PER SRM 51-10-01, 55-10-01, 51-10-02.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 78,122 hrs · 18,599 cycles

BULK CARGO COMPT FLOORBEAM LBL 30 STA 1980 & 2000 IS CRACKED. REMOVED DAMAGE AREA, REPAIR ANGLE, TREATED & PRIMED PER SRM 51-40-03.

Part: RIB — CRACKED (HORIZONTAL STAB) · airframe 78,122 hrs · 18,599 cycles

RT HORIZONTAL STAB O/B RIB ASSY AT STAB BL 421.50 IS CRACKED. REMOVED CRACK AREA, NO FURTHER DEFECT FOUND. TREATED & PRIMED PER SRM 55-10-01 & 51-10-02.

Part: BEAM — CRACKED (FUSELAGE) · airframe 78,122 hrs · 18,599 cycles

BULK CARGO COMPT, LONGITUDNAL BEAM AT STA 2040-2060-2080 LBL 30 IS CRACKED. REMOVED DAMAGE SECTION, FABRICATED NEW PART & INSTALLED PER SRM 51-40-04.

Part: FRAME — CRACKED (FUSELAGE) · airframe 78,122 hrs · 18,599 cycles

MAIN DECK CARGO COMPT SUPPORT FRAME AT STRINGER 10R, BODY STATION 1660, RBL 28 IS CRACKED. REMOVE FRAME, INSTALLED NEW SUPPORT FRAME, TREATED & PRIMED PER SRM 51-30-01 & 51-30-02.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 78,122 hrs · 18,599 cycles

BULK CARGO COMPT FLOORBEAM LBL 38 STA 1980 IS CRACKED. REMOVED DAMAGE AREA, REPAIRED ANGLE, PRIMED & TREATED PER SRM 51-40-03.

Part: SKIN — CRACKED (FUSELAGE) · airframe 78,122 hrs · 18,599 cycles

APU EXHAUST AREA SKIN CRACKED BS 2742. CUT OUT DAMAGED AREA, INSTALLED NEW DOUBLER, TREATED & PRIMED PER SRM 53-30-03.

Part: FLOOR SUPPORT — CRACKED (FUSELAGE) · airframe 78,122 hrs · 18,599 cycles

BULK CARGO COMPT FLOOR LONGITUDINAL BEAM AT STA 1960-2080 AT LBL 38 IS CRACKED. REMOVED DAMAGE AREA, INSTALLED NEW PARTS PER SRM 51-40-03, TREATED & PRIMED.

Part: SKIN — CORRODED (RT WING) · airframe 78,122 hrs · 18,599 cycles

RIGHT UPPER WING SKIN HAS CORROSION ALONG FWD OF MID SPAR. BLENDED OUT CORROSION, TREATED & PRIMED.

Part: BULKHEAD — CORRODED (FUSELAGE) · airframe 78,122 hrs · 18,599 cycles

BULKHEAD EXIT SIDE UNDER RADOME LT SIDE 3RD BEAM DOWN FROM TOP HAS CORROSION. REMOVED CORROSION, TREATED & PRIMED.

Part: SKIN — CRACKED (NR 2 PYLON) · airframe 78,122 hrs · 18,599 cycles

LEFT WING UPPER SURFACE O/B NR 2 PYLON L/E AREA 3 PLACES OF CRACKED SKIN. REMOVED SPLICE PLATE CRACK, FABRICATED SPLICE PLATE, TREATED & PRIMED.

Part: SKIN — CORRODED (LT WING) · airframe 78,122 hrs · 18,599 cycles

LEFT WING UPPER SKIN 24 INCHES FWD OF SPAN WISE BEAM NR 2 HAS CORROSION. REMOVED CORROSION, TREATED & PRIMED.

Part: SKIN — CORRODED (LT WING TE FLAP) · airframe 78,122 hrs · 18,599 cycles

LT WING MID FLAP ENTIRE CENTER SECTION PANEL HAS SEVERAL CORROSION SPOTS. REMOVED SURFACE CORROSION , PRIMED AND TREATED.

Part: FRAME — CORRODED (FUSELAGE) · airframe 78,122 hrs · 18,599 cycles

BULK CARGO COMPT FUSELAGE FRAME, UPPER CHORD TOP & BOTTOM HAS SURFACE CORROSION. REMOVE CORROSION, ORIGINAL MATERIAL IS 0.085, AFTER REWORK 0.083 WITHIN LIMITS.

Part: STRINGER — CORRODED (CARGO BAY) · airframe 78,122 hrs · 18,599 cycles

AFT CARGO COMPT STRINGER 51R HAS CORROSION. REMOVED LITE CORROSION MATERIAL, TREATED & PRIMED.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 78,122 hrs · 18,599 cycles

CABIN LEFT SEAT TRACK HAS CORROSION SPOTS. REMOVED CORROSION .020 MATERIAL WITHIN LIMITS.

Part: KEELBEAM — CORRODED (FUSELAGE) · airframe 78,122 hrs · 18,599 cycles

KEEL BEAM APPROX STA 1093 HAS BOTTOM SURFACE CORROSION. REMOVED CORROSION, AFTER WORK IT IS 0.061, OK PER SRM 52-10-01.

Part: SKIN — CORRODED (FUSELAGE) · airframe 78,122 hrs · 18,599 cycles

FUSELAGE SKIN JOINT HAS SURFACE CORROSION. REMOVED CORROSION, TREATED & PRIMED.

Part: BULKHEAD — CORRODED (FUSELAGE) · airframe 78,122 hrs · 18,599 cycles

AFT BULKHEAD UNDER FLOOR & WEB CORRODED. REMOVED STIFFENER & WEB FROM FLOORBEAM, INSTALLED NEW ONE.

Part: FRAME — PUNCTURED (FUSELAGE) · airframe 78,122 hrs · 18,599 cycles

BULK CARGO COMPT FUSELAGE FRAME WEB BELOW THE UPPER CHORD IS PUNCTURED. CUT OUT DAMAGED AREA, FABRICATED DOUBLER & FILLER, REINSTALLED, TREATED & PRIMED.

Part: KEELBEAM — CORRODED (FUSELAGE) · airframe 78,122 hrs · 18,599 cycles

KEEL BEAM BOX BOTTOM SURFACE HAS CORROSION LEFT & RIGHT SIDE. REMOVED FASTENER, REMOVED CORROSION & REINSTALLED FASTENER, TREATED & PRIMED.

Part: FLOOR SUPPORT — CRACKED (FUSELAGE) · airframe 78,122 hrs · 18,599 cycles

BULK CARGO COMPT LONGITUDINAL FLOOR SUPPORT CRACKED. REMOVED AND REPLACED DAMAGE AREA.

Part: FRAME — CORRODED (FUSELAGE) · airframe 78,122 hrs · 18,599 cycles

CTR CARGO COMPT FRAME TOP OF UPPER CHORD AT STA 1740 RBL 40 IS CORRODED. REMOVED CORROSION FOUND OUT OF LIMITS, INSTALLED NEW CHORD.

Part: FLOOR PANEL — CRACKED (CARGO BAY) · airframe 78,122 hrs · 18,599 cycles

BULK CARGO LEFT SIDE FLOOR PANEL BS 2040-2160 DENTED & CRACKED. CUT OUT DAMAGE AREA, FABRICATED & INSTALLED DOUBLER, PRIME & TREATED.

Part: KEELBEAM — CORRODED (FUSELAGE) · airframe 78,122 hrs · 18,599 cycles

KEEL BEAM FROM STA 1075-1095 HAS CORROSION LEFT & RIGHT SIDE. REMOVED CORROSION & TREATED PER SRM 53-10-01.

Part: FAIRING — DELAMINATED (WING TO BODY) · airframe 78,122 hrs · 18,599 cycles

WING TO BODY FAIRING 1916L HAS DELAMINATION. CLEANED AREA & REBONDED.

Part: SKIN — CORRODED (CARGO DOOR) · airframe 78,122 hrs · 18,599 cycles

FWD CARGO DOOR/LWR AFT SKIN HAS CORROSION. REMOVED CORROSION, FABRICATED DOUBLER & FILLER.

Part: KEELBEAM — CORRODED (FUSELAGE) · airframe 78,122 hrs · 18,599 cycles

KEEL BEAM BOX, PANEL SUPPORT STRUCTURE INNER LIP HAS CORROSION. REMOVED CORROSION, TREATED & PRIMED.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 78,122 hrs · 18,599 cycles

BULK CARGO COMPT FLOORBEAM CRACKED. REMOVED & REPLACED DAMAGED AREA.

Part: FRAME — CORRODED (CARGO BAY) · airframe 78,122 hrs · 18,599 cycles

CENTER CARGO COMPT FRAME UPPER CHORD HAS CORROSION. REMOVED CORROSION, TREATED & PRIMED.

Part: SKIN — CORRODED (FUSELAGE) · airframe 78,122 hrs · 18,599 cycles

AFT FUSELAGE HAS SKIN CORROSION. REMOVED CORROSION, TREATED & PRIMED.

Part: JACKSCREW — CORRODED (TE FLAPS) · corrosion level 2 · airframe 78,122 hrs · 18,599 cycles

LEFT WING NR 2 TRACK JACKSCREW HAS PITTED CORROSION. REMOVED AND REPLACED LEFT WING JACKSCREW AS PER MM 27-51-41.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 78,122 hrs · 18,599 cycles

LEFT CENTER SEAT TRACK DIRTY & CORRODED. REMOVED MINOR CORROSION FROM TRACK, TREATED & PRIMED.

Part: STRINGER — CORRODED · airframe 78,122 hrs · 18,599 cycles

AFT CARGO COMPT STRINGER 50L B/W STA 1680-1700 CORRODED. REMOVED LIGHT CORROSION, PRIMED & TREATED.

Part: SKIN — CORRODED (FUSELAGE) · airframe 78,122 hrs · 18,599 cycles

EXTERNAL SKIN AT STA 255 STR 32L AT LAP JOINT DELAMINATION. REMOVED BULGE, NO CORROSION FOUND, REMOVED FASTENER, INSTALLED NEW FASTENER, TREATED & PRIMED.

Part: PANEL — CRACKED (CARGO BAY) · airframe 78,122 hrs · 18,599 cycles

AFT CARGO COMPT WALKWAY PANEL STA 1775-1795 LBL 22-45 HAS CRACKS, & CORROSION. REMOVED CORROSION, BLENDED & CUTOUT CRACK, FABRICATED DOUBLER, TREATED & PRIMED.

Part: FITTING — CORRODED (FUSELAGE) · airframe 78,122 hrs · 18,599 cycles

LEFT NOSE WELL BULKHEAD O/B SIDE OF NLG LWR STR FITTING IS CORRODED. REMOVED CORROSION, PRIMED & TREATED.

Part: WEB — CRACKED (FUSELAGE) · airframe 78,122 hrs · 18,599 cycles

FWD CARGO COMPARTMENT WEB CRACKED. REMOVED CRACKED WEB, FABRICATED NEW WEB AND INSTALLED.

Part: SKIN — CORRODED (FUSELAGE) · airframe 78,122 hrs · 18,599 cycles

LEFT MAIN LANDING GEAR FWD CUTOUT EXTERNAL PANEL SKIN FROM LBL 21 - LBL 10 HAS CORROSION. REMOVED CORROSION, CORROSION WITHIN LIMITS, PRIMED & TREATED.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 78,122 hrs · 18,599 cycles

MAIN DECK CARGO COMPT SEAT TRACK HAS CORROSION. REMOVED CORROSION, PRIMED & TREATED.

Part: FLOOR PANEL — CORRODED (CARGO BAY) · airframe 78,122 hrs · 18,599 cycles

FWD CARGO FLOOR PANEL HAS CORROSION. REMOVED SURFACE CORROSION, TREATED AND PRIMED.

Part: SKIN — CORRODED (RT WING) · airframe 78,122 hrs · 18,599 cycles

RIGHT WING UPPER SKIN HAS SURFACE CORROSION. REMOVED LITE CORROSION, TREATED & PRIMED.

Part: WEB — CRACKED (NOSE WHEEL WELL) · airframe 77,649 hrs · 18,543 cycles

NOSE WHEEL WELL - BS320, RIGHT VERTICAL BEAM WEB, 2" LONG CRACK AT 2ND INSULATION HOLE FROM FLOOR BEAM CHORD. REPAIRED BY REMOVING EXISTING FASTENERS, CUTTING OUT DAMAGE, INSTALLING DOUBLER, SPLICE FILLER, SHIM & (2) EA. "T" SECTIONS IAW BOEING TELEX PAO-LGB-01-00155H & MA #A510-33-01.

Part: WEB — CRACKED (NOSE WHEEL WELL) · airframe 77,649 hrs · 18,543 cycles

NOSE WHEEL WELL - BS320, LEFT VERTICAL BEAM WEB - (3) CRACKS 1/8" LONG EA. LOCATED AT 2ND, 3RD & 5TH INSULATION HOLES FROM FLOOR BEAM CHORD. OPENED HOLE TO 9/16". H.F.E.C. NO INDICATIONS. INSTALLED REPAIR DOUBLERS AS PER BOEING TELEX PAO-LGB-01-00155H & MA #A510-33-01.

Part: WEB — CRACKED (NOSE WHEEL WELL) · airframe 77,649 hrs · 18,543 cycles

NOSE WHEEL WELL - BS300, LEFT VERTICAL BEAM WEB, 1/8" LONG CRACK AT 3RD INSULATION HOLE FROM FLOOR BEAM CHORD. OPENED HOLE TO 9/16". H.F.E.C. NO INDICATIONS. INSTALLED REPAIR DOUBLERS AS PER BOEING TELEX PAO-LGB-01-00155H & MA #A5310-33-10.

Part: WEB — CRACKED (NOSE WHEEL WELL) · airframe 77,649 hrs · 18,543 cycles

NOSE WHEEL WELL - BS 300, RIGHT VERTICAL BEAM WEB, 1" LONG CRACK AT 3RD INSULATION HOLE FROM FLOOR BEAM CHORD. REPAIRED BY REMOVING EXISTING FASTENERS & BRACKETS, CUTTING OUT DAMAGED SECTION, INSTALLING DOUBLERS & (2) EA. "T" SECTIONS IAW BOEING TELEX PAO-LGB-01-00155G & MA #A510-33-01.

Part: AILERON — HUNG UP (WING) · airframe 77,540 hrs · 18,482 cycles

WITH FLAPS UP, AILERON LOCKED UP WHILE TRYING TO MAKE A RIGHT TURN. WITH FLAPS 5 DEGREES, AILERON LOCKED AT LEFT BANK +/- 20 DEGREES (IAS 250 KNOTS). CLEANED LEFT AND RIGHT AILERON PROGRAMMERS AND LUBRICATED PER 12-21-16. FLIGHT CONTROL CHECK OF AILERONS OPERATION OK.

Part: LINK — BROKEN · airframe 77,520 hrs · 18,478 cycles

R.H. O/B FORE FLAP, MOST O/B SUPPORT LINK BROKEN. REMOVED & REPLACED LINK ASSY. OPS CHECK O.K.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 77,519 hrs · 18,477 cycles

EMERGENCY LIGHTS IN UPPER DECK DO NOT TEST. REMOVED AND REPLACED U/D DOME EMERGENCY LIGHT PER MM 33-51-00. ALL OPS OK.

Part: BUSHING — CRACKED (RT TRUNNION) · airframe 75,032 hrs · 17,909 cycles

RIGHT BODY LANDING GEAR INBOARD TRUNNION BUSHING CRACKED. REPLACED RT BODY LANDING GEAR INBOARD AND OUTBOARD TRUNNION FITTING. BORE REWORKED AND NEW REWORKED BUSHINGS INSTALLED PER SRM 53-10-08 FIG 1 & 2 AND POLAR CARD M3213-001.

Part: FRAME — CRACKED (FUSELAGE) · airframe 75,001 hrs · 17,904 cycles

MAIN DECK BS 2231 S-24L AND S-25L DOOR CUTOUT REVEAL CRACKED (DOOR 5L). REPAIRED PER SRM 53-10-04 FIG 91 AND BOEING INSTRUCTION PAO-HKG-00-00023H.

Part: THRUST REVERSER — MALFUNCTIONED (NR 2 ENGINE) · airframe 74,899 hrs · 17,881 cycles

ON TAKEOFF ROLL AT APPROX 25 KTS, NR 2 THRUST REVERSER UNLOCKED LIGHT ILLUMINATED. TAKEOFF ABORTED. TRANSFEREDTO MEL 78-2-A CAT C DMI NR 25184 AS PER MX CONTROL AXLE VERIFICATION INSPECTION C/W AS PER DDPG 78-2-A.

Part: ENGINE — STALLED (NR 2) · airframe 74,892 hrs · 17,880 cycles

NR 2 ENGINE STALLED LOST POWER AND WAS SHUTDOWN PER IAW POLAR PROCEDURES. LOG PAGE NR 098103. REMOVED AND REPLACED NR 2 ENGINE AS PER POLAR W/C 7100-002, OPS CHECKS GOOD.

Part: LINE — CRACKED (NR 4 HYD SYST)

FOUND HYDRAULIC LEAK FROM NR 4 SYSTEM RETURN LINE AT TOP OF LOWER AFT CARGO COMPARTMENT NEAR DOOR ACTUATOR. PERMANENT REPAIRED LINE (1 INCH DIAMETER) BY DEUTSCH PERMASWAGE REPAIR KIT. LEAK CHECKED OK. SERVICED NR 4 SYSTEM PER MM 29-11-00.

Part: FLOORBEAM — DAMAGED (BS1800)

FOUND FLOORBEAM AFT CARGO PIT STA 1800R DAMAGED. REPAIRED PER SRM 51-30-02 AND SRM 51-10-02.

Part: PANEL — CRACKED (RT WING)

FOUND RIGHT WING FLYING PANEL CRACKED. REPAIRED PER SRM 51-40-03.

Part: COWL — DAMAGED (NR 3 ENGINE)

FOUND NR 3 INBD POWER COWL FWD END CENTER STIFFENER ATTACH ANGLE BROKEN. REPAIRED PER SRM 51-10-01 AND 51-30-02.

Part: COWL — CRACKED (NR 3 ENGINE)

NR 3 INBD POWER COWL NR 4 LATCH AREA FOUND TEAR. REPAIRED PER SRM 54-30-03.

Part: COWL — CRACKED (NR 4 ENGINE)

NR 4 INBOARD POWER COWL EXTERNAL DOUBLER REPAIR FOUND 2 INCH CRACK. REPAIRED DOUBLER PER SRM 51-30-02.

Part: COWL — CRACKED (NR 3 ENGINE)

NR 3 OUTBOARD POWER COWL IS CRACKED AT PREVIOUS WELD AREA. REPAIRED PER SRM 51-30-02.

Part: FITTING — CRACKED (NR 1 ENGINE)

FOUND NR 1 ENGINE STRINGER ASSY ATTACH FITTING CRACKED. REPAIRED PER SRM 51-10-01 AND MM 78-11-01.

Part: FRAME — CRACKED (BS 1780)

AFT CARGO PIT AREA BS 1780 STR 25R T CAP SECTION CRACKED. REPAIRED PER SRM 51-40-03 AND 51-30-02.

Part: FRAME — DAMAGED (NR 3 ENGINE COWL)

NR 3 INBOARD POWER COWL NR 3 LATCH AREA HAS FRAME/OUTER SKIN DAMAGE. REPAIRED PER SRM 54-30-03.

Part: DOUBLER — CRACKED (NR 3 ENGINE)

NR 3 OUTBOARD POWER COWL INNER DOUBLER FOUND CRACKED. REPAIRED PER SRM 54-30-03.

Part: STRINGER — BROKEN (BS 1618)

DURING HIGH WINDS AIRCRAFT BOUNCED OFF TAIL JACK AND A HOLE WAS PUNCTURED IN THE OUTER SKIN OF BS1618. REPAIRED FUSELAGE SKIN IAW BACO SRM 53-30-03. REPAIRED STRINGER 49 AND 50 AT STA 1618 PER BACO SRM 53-10-03.

Part: DOOR — NOT SEALED (L5 DOOR)

DISCOVERED PRESSURIZATION LEAK AT L5 DOOR. REPAIRED PER MM 52-09-00.

Part: DOOR — CRACKED (L4 DOOR)

L-4 DOOR LOWER AFT CORNER FOUND CRACK. REPAIRED DAMAGED SECTION PER SRM 52-10-02 AND 51-10-02.

Part: VALVE — LEAKING (HYDRAULIC SYSTEM)

HNL/NAN - DURING CRUISE, NR 3 SYSTEM HYDRAULIC QUANTITY DECREASED IN-FLIGHT. ON ARRIVAL NAN, NR 3 SYSTEM FLIGHT CONTROL SOV FOUND UNSERVICEABLE. PART REPLACED AND AIRCRAFT RELEASED TO SERVICE.

Part: VALVE — LEAKING (RT WING)

INFLIGHT NR 3 HYDRAULIC QUANTITY DECREASED AT 1 GAL PER HOUR RATE. DEPRESSURIZED SYSTEM, FLUID LOSS STOPPED. SYSTEM DEPRESSURIZED UNTIL DESCENT. TROUBLESHOOTING CONFIRMED LEAK IN RIGHT HAND FLIGHT CONTROL SHUTOFF VALVE. VALVE REPLACED IAW BMM 27-13-01 PG 401, SYSTEM TESTED SATISFACTORY IAW BMM 27-13-01 PG 501.

Part: FAN BLADES — BROKEN (NR 2 ENGINE)

DURING TRANSIT CHECK AT DXB FOUND BIRD STRIKE DAMAGE TO NR 2 ENGINE. VARIOUS FAN BLADES BROKEN OFF AT TIPS AND BLADES ALSO BENT. TOTAL 8 BLADES DAMAGED. CARRIED OUT FOD (BIRD STRIKE) INSP PER MM 72-00-00. NO DAMAGE EVIDENT ADJACENT TO CORE, ONLY FAN BLADES. FAN BLADES REPLACED PER MM 72-31-02 PG 401. ENGINE IDLE RUN CARRIED OUT SATISFACTORY.

Part: STRINGER — CORRODED (BS 1720)

LEVEL 1 CORROSION ON STRINGER S48 BS 1720 TO 1740 AFT CARGO AREA RIGHT SIDE. CORROSION REMOVED AND REPROTECTED PER SRM 51-10-01 AND 51-10-02.

Part: SKIN — DELAMINATED (RT TE FOREFLAP)

RT WING INBOARD FOREFLAP LOWER SURFACE FOUND DELAMINATED. REPAIRED AREA OF FIBERGLASS DELAMINATION PER SRM 51-40-12.

Part: SUPPORT — CRACKED (CARGO COMPT)

BULK CARGO COMP BELOW FLOOR STRUCTURE TIE DOWN SUPPORT HAT SECTION CRACKED AND DEFORMED AT LT NR 2 I/B ONE FROM BS 1960 TO BS 1970. HAT SECTION REPAIRED PER SRM 51-40-03 FIG 1. REPROTECTED PER MM 51-24-11.

Part: PANEL — DELAMINATED (RT WING)

RT WING UPPER SURFACE ALONG FRONT SPAR CHORD SEVERAL AREAS OF FIBERGLASS LAYERS CRACKED. FIBERGLASS REPAIRED PER SRM 51-40-18.

Part: WEB — CRACKED (CARGO COMPT)

BULK CARGO AREA STA 1940 S40 LT SUPPORT WEB FOUND CRACKED. SUPPORT WEB REPAIRED PER SRM 51-40-02 FIG 1. HFEC INSP PER NDT PART 6, 51-00-00 FIG 4. STOP DRILLED CRACK, NO CRACK BEYOND STOP DRILL. PROTECTED PER MM 51-24-11.

Part: FLOOR — CORRODED (CARGO COMPT)

BULK CARGO FLOOR PANELS 1920 TO 2040 LT TO RT FOUND CORROSION ON LOWER EDGE AREA. CORROSION REMOVED AND REPROTECTED IAW SRM 51-10-01 AND 51-10-02.

Part: RIBS — CRACKED (BS 2160-2200)

BULK CARGO COMPART LEFT SIDE RIBS ATTACHED TO BULKHEAD BETWEEN BS 12160 TO 2200 FOUND CRACKED AND DEFORMED. REPAIRED PER SRM 51-40-03 AND REPROTECTED PER SRM 51-24-11.

Part: STRUT — CORRODED (RT MLG)

RT BODY GEAR SHOCK STRUT SURFACE CORROSION AT FORWARD FACE OF SHOCK STRUT. CORROSION REMOVED PER SRM 51-10-01. SHOT PEENING CARRIED OUT PER OHM 20-10-03. STYLUS CADMIUM PLATING APPLED PER OHM 32-10-21.

Part: RIVETS — LOOSE (BS 2664)

APU COMPARTMENT LT SIDEWALL STA 2664 AND STA WL 305 VERTICAL FRAME SUPPORT ANGLE ATTACH RIVETS LOOSE. RIVETS REPLACED PER 51-30-02.

Part: FRAME — CORROSION (BS 1350)

LEVEL 1 CORROSION LT WING GEAR WHEEL WELL AT TOP OF FRAME AT STA 1350 LBL 10. CORROSION REMOVED AND REPROTECTED PER SRM 51-01-01 AND 51-10-02.

Part: SILL — CHAFED (CARGO DOORWAY)

FUSELAGE LT STA 1780 MAIN DECK SIDE CARGO DOOR LOWER FWD ATTACH DOOR SILL CHAFING MARK. CHAFE MARKS SMOOTHED OUT AND REPROTECTED PER SRM 51-01-01 AND 51-10-02, WITHIN SRM LIMITS 53-30-01.

Part: SKIN — CORRODED (RT WING)

LEVEL 1 CORROSION FOUND ON RT WING LOWER SKIN FWD OF FRONT SPAR. THE AREA HAS BEEN PREVIOUSLY BLENDED. CORROSION REMOVED AND REPROTECTED PER HAECO REPAIR SCHEME NR R57-26-33785.

Part: FAIRING — CORRODED (FUSELAGE)

LEVEL 1 CORROSION FOUND ON BODY FAIRING PANEL 191 BBL ANTENNA CUTOUT AREA. CORROSION REMOVED AND REPROTECTED PER SRM 51-10-01 AND 51-10-02.

Part: ANGLE — CRACKED (BS 2718)

APU RT COMPARTMENT SIDEWALL STA 2718 WL 305 VERTICAL FRAME SUPPORT ANGLE CRACKED. REPLACED VERTICAL FRAME SUPPORT ANGLE PER SRM 51-10-01.

Part: SKIN — CORRODED (BS 600)

LOWER FUSELAGE SKIN SURFACE CORROSION AT BS 600 LEFT. CORROSION REMOVED AND REPROTECTED PER SRM 51-10-01 AND 51-10-02.

Part: SKIN — CORRODED (LT HORIZ STAB)

LT HORIZONTAL STAB TOP SURFACE MINOR CORROSION ALONG STAB TORQUE BOX SKIN AREA FROM L/E TO T/E. CORROSION REMOVED AND REPROTECTED PER SRM 51-10-01 AND 51-10-02.

Part: RIVETS — LOOSE (BS 2669)

APU COMPARTMENT RT SIDEWALL STA 2664 AND STA 2669 WL 305 VERTICAL FRAME SUPPORT ANGLE ATTACH RIVETS LOOSE. RIVETS REPLACED PER SRM 51-30-02.

Part: DOOR — CORROSION (RT MLG)

RT BODY GEAR CORROSION ON FORWARD SIDE OF O/B STRUT DOOR. CORROSION REMOVED AND REPROTECTED PER SRM 51-10-01 AND 51-10-02.

Part: SKIN — CORRODED (RT MLG DOOR)

RT BODY GEAR INBD STRUT DOOR SURFACE CORROSION AT AFT EDGE AND MID AREA OF DOOR. CORROSION REMOVED AND REPROTECTED PER SRM 51-01-01 AND 51-10-02.

Part: WEB — CRACKED (EMER EXIT)

COCKPIT OVERHEAD EMERGENCY HATCH AFT HINGE WEB CRACKED. REPAIRED HINGE WEB PER SRM 51-40-03.

Part: SHEAR TIE — CRACKED (BS 1720)

STATION 1720 AFT CARGO AREA RT S48-49 SHEAR TIE FOUND CRACKED. REPAIRED AS PER SRM 53-10-04.

Part: DOOR — CORRODED (RT MLG)

RIGHT WING GEAR OUTBOARD STRUT DOOR FOUND CORROSION AT FASTENERS ON LOWER SIDE OF UPPER DOOR. CORROSION REMOVED AND AREA REPROTECTED AS PER SRM 51-10-01 AND 51-10-02.

Part: STRINGER — CORRODED (BS 1820)

LEVEL ONE CORROSION FOUND AT AFT CARGO AREA STA 1820 TO 1840 STRINGER S46L. CORROSION REMOVED AND AREA REPROTECTED AS PER SRM 51-10-01 AND 51-10-02.

Part: SKIN — CORRODED (TAIL CONE)

TAIL CONE AREA CORROSION REVEALED AT FORWARD AREA OF APU BATTERY ACCESS DOOR STA 2600. CORROSION AREA REMOVED AND REPROTECTED PER SRM 51-10-01 AND 51-10-02.

Part: SKIN — CORRODED (BS 940)

LEVEL ONE CORROSION FOUND AT SATELLITE COMMUNICATIONS ANTENNA SURROUNDING SKIN AT FS 940. CORROSION REMOVED AND AREA REPROTECTED AS PER SRM 51-10-01 AND 51-10-02.

Part: SUPPORT — CORRODED (BS 1860-1920)

LEVEL ONE CORROSION FOUND AT STA 1860 TO 1920 AFT CARGO AREA FLOOR PANEL SUPPORT STRUCTURE. CORROSION REMOVED AND AREA REPROTECTED AS PER SRM 51-10-01 AND 51-10-02.

Part: STRINGER — CORRODED (BS 1700)

LEVEL ONE CORROSION FOUND AT AFT CARGO AREA STA 1700 TO 1720 STRINGER 43L LOWER SURFACE. CORROSION REMOVED AND AREA REPROTECTED AS PER SRM 51-10-01 AND 51-10-02.

Part: PANEL — CORRODED (FUSELAGE)

LEVEL ONE CORROSION FOUND AT PANEL 191G. CORROSION REMOVED AND AREA REPROTECTED AS PER SRM 51-10-01 AND 51-10-02.

Part: PLATE — CORRODED (BS 1283)

MAIN DECK BS 1283 BL 100L FLOOR SUPPORT PLATE FOUND CORRODED. CORROSION REMOVED AND AREA REPROTECTED IAW SRM 51-10-01 AND 51-10-02.

Part: BRACKET — CORRODED (BS 1000-1235)

FUSELAGE STATION 1000 TO 1235 KEEL BEAM AREA LOWER ACCESS PANEL SUPPORT BRACKET FOUND CORRODED. CORROSION AND AREA REPROTECTED AS PER SRM 51-10-01 AND 51-10-02.

Part: FITTING — CORRODED (R1 DOORWAY)

MAIN DECK R1 DOOR SILL FLOOR SUPPORT FITTING FOUND CORRODED. CORROSION REMOVED AND AREA REPROTECTED AS PER SRM 51-10-01 AND 51-10-02.

Part: ANGLE — CORROSION (R3 DOORWAY)

MAIN DECK R3 DOOR SILL FLOOR SUPPORT ANGLE FOUND CORRODED. CORROSION REMOVED AND AREA REPROTECTED AS PER SRM 51-10-01 AND 51-10-02.

Part: SEAT TRACK — CORROSION (BS 2280)

LEVEL 1 CORROISON ON MAIN DECK SEAT TRACK UPPER SURFACE AT BS 2280. REMOVED AND REPROTECTED PER SRM 51-10-01 AND 51-10-02.

Part: KEEL BEAM — CORROSION (BS 1427)

LEVEL 1 CORROSION ON KEEL BEAM CHORD UPPER EDGE BS 1427 BL 10. CORROSION REMOVED AND REPROTECTED PER SRM 51-10-01 AND 51-10-02.

Part: STRINGER — CORRODED (BS 1720)

LEVEL ONE CORROSION FOUND AT BS 1720 STRINGER 47L. CORROSION REMOVED AND AREA REPROTECTED AS PER SRM 51-10-01 AND 51-10-02.

Part: SKIN — CORROSION (BS 2460-2484)

RT UPPER TAIL CONE AREA CORROSION REVEALED AT STA 2460 TO 2484. CORROSION REMOVED AND REPROTECTED PER SRM 51-10-01 AND 51-10-02.

Part: SKIN — DAMAGED (BS 1740)

FUSELAGE RIGHT HAND STATION 1740 AT S44 FOUND SKIN DAMAGED. SKIN REPAIRED AS PER SRM 53-30-03.

Part: PANEL — CORROSION (FUSELAGE)

LEVEL ONE CORROSION FOUND AT FUSELAGE ACCESS PANEL 193P INNER FACE. CORROSION REMOVED AND AREA REPROTECTED AS PER SRM 51-10-01 AND 51-10-02.

Part: PANEL — CORRODED (FUSELAGE)

FUSELAGE BODY FAIRING NR 191BB FOUND CORRODED IN DRAIN LINE AREA. CORROSION REMOVED AND AREA REPROTECTED AS PER SRM 51-10-01 AND 51-10-02.

Part: SKIN — CORROSION (RT HORIZ STAB)

RT HORIZONTAL STAB UPPER SURFACE CORROSION REVEALED. CORROSION REMOVED AND REPROTECTED PER SRM 51-10-01 AND 51-10-02.

Part: SKIN — CORRODED (HORIZ STAB)

LT HORIZONTAL STAB LOWER SURFACE CORROSION REVEAL AT AREA JUST BELOW AFT OF LOWER AIR GATE SEAL FAIRING STA 2600. CORROSION REMOVED AND REPROTECTED PER SRM 51-10-01 AND 51-10-02.

Part: STRINGER — CORRODED (BS 1720)

LEVEL ONE CORROSION FOUND AT STA 1720 TO 1740 AFT CARGO AREA LEFT HAND STRINGER 47. CORROSION REMOVED AND AREA REPROTECTED AS PER SRM 51-10-01 AND 51-10-02.

Part: STIFFENER — CORRODED (BS 1014)

LEVEL 1 CORROSION ON KEEL BEAM VERTICAL STIFFENER. REMOVED AND RETREATED CORROSION IAW SRM 51-10-01 AND 51-10-02.

Part: DOOR — CORROSION (RT MLG)

RT WING O/B STRUT DOOR LOWER SURFACT AREA CORROSION. TREATED AREA AND REPROTECTED PER SRM 51-10-01 AND 51-10-02.

Part: RIVET — MISSING (BS 960)

FOUR RIVETS FOUND NOT INSTALLED AT FWD CARGO COMPT STA 960 FLOORBEAM UPPER CHORD, BL 0 AND BL 6. INSTALLED RIVETS AS PER SRM 51-30-02.

Part: PANEL — CORRODED (FUSELAGE)

LEVEL ONE CORROSION FOUND AT PANEL 191J UPPER SURFACE. CORROSION REMOVED AND AREA REPROTECTED AS PER SRM 51-10-01 AND 51-10-02.

Part: STRINGER — CORRODED (BS 1700)

LEVEL ONE CORROSION FOUND AT STA 1700 TO 1720 AFT CARGO AREA S51L. CORROSION REMOVED AND AREA REPROTECTED AS PER SRM 51-10-01 AND 51-10-02.

Part: RIVET — SHEARED (BS 920)

FWD CARGO COMPARTMENT STA 920 FLOORBEAM WEB VERTICAL SUPPORT FOUND 3 RIVETS SHEARED. REPLACED RIVETS AS PER SRM 51-30-03.

Part: STRINGER — CORRODED (BS 1900)

LEVEL ONE CORROSION FOUND AT AFT CARGO AREA STA 1900 TO 1920 STRINGER 46L. CORROSION REMOVED AND AREA REPROTECTED AS PER SRM 51-10-01 AND 51-10-02.

Part: SEAT TRACK — CORROSION (BS 600)

LEVEL 1 CORROSION AT UPPER DECK SEAT TRACK BS 600 BL 46L. REMOVED AND REPROTECTED SEAT TRACK PER SRM 51-10-01 AND 51-10-02.

Part: SEAT TRACK — CORROSION (BS 2276)

LEVEL ONE CORROSION FOUND AT MAIN DECK SEAT TRACK STATION 2276. CORROSION REMOVED AND AREA REPROTECTED AS PER SRM 51-10-01 AND 51-10-02.

Part: SKIN — CORRODED (RT HORIZ STAB)

LEVEL ONE CORROSION FOUND ON RIGHT HAND HORIZONTAL STABILIZER LOWER SURFACE AT LEADING EDGE STA 260. CORROSION REMOVED AND AREA REPROTECTED AS PER SRM 51-10-01 AND 51-10-02.

Part: SEAT TRACK — CORRODED (BS 480-630)

LEVEL ONE CORROSION FOUND AT UPPER DECK SEAT TRACK BS 480 TO 630 LBL 64. CORROSION REMOVED AND AREA REPROTECTED IAW SRM 51-10-01 AND 51-10-02.

Part: PANEL — CORRODED (BS 1112)

LEVEL ONE CORROSION FOUND AT PANEL 191EL LOWER SURFACE. CORROSION REMOVED AND AREA REPROTECTED AS PER SRM 51-10-01 AND 51-10-02.

Part: BRACKET — CRACKED (BS 2080)

STATION 2080 AFT FRAME SUPPORT BRACKET FOUND CRACKED. BRACKET REPLACED PER SRM 51-10-01.

Part: FASTENER — RUSTY (BS 140)

FUSELAGE STATION 140 STR 23L FOUND 6 FASTENERS RUSTY. FASTENERS REPLACED AS PER SRM 51-30-02.

Part: POSITION IND — FAILED (LT TE FLAP)

ON CLIMB WHEN FLAPS UP SELECTED, LT INBD T/E FLAPS SHOWED 1 DEGREE, RT INBD T/E FLAPS SHOWED UP. AIRCRAFT RETURNED TO ORD. INSP FLAPS NO DEFECT NOTED, FOUND LT INBD POS IND STUCK AT 1 DEGREE POS. REPLACED INBD FLAP POS IND CHK OK PER MM 27-57-00. FLAP POS IND OP CK THRU SEVERAL CYC PER MM 27-57-00.

Part: PCU — FAILED (LT ELEVATOR)

LOST 1.5 GALS FLUID FROM NR 1 HYDRO SYSTEM AT TOP OF DESCENT. FOUND LT OUTBOARD ELEVATOR PCU FILTER AREA LEAKING. REMOVED AND REPLACED LT ELEVATOR OUT BOARD PCU PER MM 27-31-08 SERVICED HYD FLUID. LEAK CHECK OK, OPS CHECK NORMAL.

Part: PANEL — CRACKED (RT WING)

RIGHT WING TRAILING EDGE FIXED PANEL - FLYING PANEL- IS CRACKED. REMOVED AND REPLACED PER SRM 51-30-02, 51-10-01 AND MM 57-22-01.

Part: PANEL — DAMAGE (NR 1 PYLON)

NR 1 PYLON UPPER AFT END HAS FIBERGLASS PANEL DAMAGE. REPAIRED PER SRM 51-40-09, 52-24-11.

Part: FRAME — CRACKED (NR 3 COWL)

NR 3 INBD CORE COWL AFT FRAME CRACKED AT BOTTON. REPAIRED PER SRM 51-10-01.

Part: FRAME — CRACKED (NR 3 COWL)

NR 3 POWER COWL OUTBD SIDE NR 3 LATCH FRAME CRACKED. REPARIED PER SRM 51-10-01.

Part: RETAINER — DAMAGED (NR 4 COWL)

NR 4 ENGINE INBD POWER COWL RETAINER DAMAGED. REMOVED AND REPLACED PER SRM 51-10-01.

Part: DOOR — DENTED (IL PAX DOOR)

NR 1 LEFT MAIN ENTRY DOOR DENTED UPPER HINGE AREA. REPAIRED PER SRM 51-30-02 AND SRM 52-11-14.

Part: COWL — DAMAGED (NR 1 ENGINE)

NR 1 OUTBD POWER COWL HINGE AREA DAMAGED. REPAIRED PER SRM 54-30-01.

Part: RACK — DAMAGED (E/E COMPT)

E AND E COMPARTMENT VERTICAL CANNON PLUGS RACK STATION 460 HAS 8 DAMAGED STANCHION. REMOVED AND REPLACED PER SRM 51-10-01.

Part: FRAME — CRACKED (NR 1 COWL)

NR 1 LT POWER COWL NR 5 LATCH FRAME CRACKED. REPAIRED PER SRM 51-10-01, 51-30-02.

Part: RIB — DAMAGED (NR 4 COWL)

NR 4 RT POWER COWL NR 3 RIB ASSY DAMAGED. REPAIRED PER SRM 51-10-01.

Part: DOUBLER — DAMAGED (NR 1 COWL)

NR 1 POWER COWL LEFT SIDE DOUBLER DAMAGED. REMOVED AND REPLACED DOUBLER PER SRM 51-30-02.

Part: STIFFENER — CORROSION (BS 1030)

HORIZONTAL STIFFENER IS CORRODED AT STA 1030 IN KEEL BEAM AREA. REMOVED AND REPLACED STIFFENER PER SRM 51-30-02.

Part: BULKHEAD BOLT — MISSING (AFT PRESS BLKHD)

AFT PRESSURE BULKHEAD LONGERON 8R BOLT MISSING. REMOVED AND REPLACED BOLT PER SRM 51-30-02, 51-30-04.

Part: FRAME — CRACKED (NR 1 COWL)

NR 1 POWER COWL LEFT SIDE LWR FRAME CHAFE/CRACK. REMOVED AND REPLACED FRAME PER SRM 51-10-01.

Part: STIFFENER — CORROSION (BS 1350)

HORIZONTAL STIFFENER CORRODED AT STA 1350 AT KEEL BEAM AREA. REMOVED AND REPLACED STIFFENER ASSY AT STA 1350 KEEL BEAM AREA PER SRM 51-10-01, 51-30-02.

Part: ANGLE — BROKEN (NR 2 PYLON)

NR 2 PYLON, LEFT SIDE ATTACH ANGLE BROKEN SLOT SEAL AREA. REMOVED AND REPLACED PER SRM 51-30-02.

Part: CANOE ASSY — HOLE (RT WING)

RT WING NR 7 CANOE ASSY HOLE OUTBD SIDE. REPAIRED PER SRM 51-40-09.

Part: SKIN — DAMAGED (CARGO DOOR)

FWD CARGO DOOR SKIN DAMAGED AT LWR AFT CORNER. REPAIRED PER SRM 52-30-00, 51-30-02, 51-10-02.

Part: RETAINER — BROKEN (RT TE MIDFLAP)

RT WING INBD MIDFLAP SEAL RETAINER BROKEN. REPAIRED PER SRM 51-30-02.

Part: GUIDE PIN — WORN (NR 1 COWL)

NR 1 ENGINE POWER COWL OUTBD SIDE WORN GUIDE PIN. REMOVED AND REPLACED OUTBD ASSY PER SRM 51-10-01.

Part: FASTENERS — MISSING (NR 1 COWL LATCH)

NR 1 POWER COWL FWD LATCH FASTENER LOOSE MISSING FASTENERS. REMOVED AND REPLACED PER SRM 51-30-02.

Part: RIVETS — MISSING (NR 4 COWL)

NR 4 ENGINE INBD POWER COWL NR 3 LATCH RETAINING PLATE RIVETS MISSING. REMOVED AND REPLACED PER SRM 51-30-02.

Part: SKIN — GOUGED (CARGO DOOR)

BS 580 FWD LOWER CARGO DOOR GOUGED. REPAIRED PER SRM 51-30-01 DETAIL 1.

Part: COWL — DAMAGED (NR 4 ENGINE)

NR 4 ENGINE INBD MAIN POWER COWL DAMAGED. REPAIRED PER SRM 51-30-03, 51-10-01.

Part: RETAINER — DAMAGED (NR 3 COWL)

NR 3 INBD POWER COWL SEAL RETAINER DAMAGED. REPAIRED PER SRM 51-01-01.

Part: FASTENERS — MISSING (NR 3 COWL)

NR 4 ENGINE INBD POWER COWL FLANGE PIN BRACKET HAS 2 HI-LOK FASTENERS MISSING. REMOVED AND REPLACED PER SRM 51-30-02.

Part: FASTENERS — MISSING (NR 4 COWL)

NR 4 ENGINE INBD MAIN COWL 2 FASTENERS MISSING. REMOVED AND REPLACED FASTENERS PER SRM 51-30-02.

Part: FASTENERS — LOOSE (CREW LADDER)

CREW LADDER 5 STEPS LOOSE FASTENERS. REMOVED AND REPLACED PER SRM 51-30-02.

Part: COWL — GOUGED (NR 1 ENGINE)

NR 1 ENGINE FAN COWL OUTBD SIDE AT 7 O'CLOCK GOUGED. REPAIRED PER SRM 51-40-06.

Part: FASTENERS — MISSING (NR 3 COWL LATCH)

NR 3 POWER COWL 5 LATCH ASSY MISSING FASTENERS. REMOVED AND REPLACED PER SRM 51-30-02.

Part: FASTENERS — MISSING (NR 3 COWL)

NR 3 ENGINE OUTBD MAIN COWL PERVIOUS REPAIR FASTENERS MISSING. REMOVED AND REPLACED FASTENERS PER SRM 51-30-02.

Part: FASTENERS — LOOSE (NR 3 COWL)

NR 3 ENGINE OUTBD MAIN COWL U-BOLT FASTENERS LOOSE. REPAIRED PER SRM 51-30-02.

Part: FASTENERS — LOOSE (NR 3 COWL)

NR 3 ENGINE INBD MAIN COWL AFT BOTTOM PRECOOLER DOOR BRACKET LOOSE FASTENERS. REMOVED AND REPLACED PER SRM 51-30-02.

Part: FASTENERS — LOOSE (NR 3 COWL)

NR 3 ENGINE INBD COWL PRECOOLER DOOR BRACKET LOOSE FASTENERS. REMOVED AND REPLACED FASTENERS PER SRM 51-30-02.

Part: PANEL — CRACKED (LT TE MIDFLAP)

LT WING OUTBD MIDFLAP ASSY COVE LIP PANEL HAS 10 FT CRACK. REMOVED AND REPLACED LT MIDFLAP ASSY COVE LIP PANEL PER MM 27-51-31.

Part: FRAME — GOUGE (BS 1920)

GOUGE ON PRODUCTION SPLICE MAIN DECK FUSELAGE CIRCUMFERENTIAL FRAME AT FS 1920 BETWEEN STRINGERS 11 AND 12. REMOVED AND REPLACED DAMAGED PRODUCTION SPLICE AS PER SRM 51-10-01.

Part: DOUBLER — CRACKED (NR 3 PYLON)

CRACKED DOUBLER NR 3 PYLON I/B SIDE AFT OF AFT MOUNT. REPAIRED PER POLAR MA 5430-07:01.

Part: RIVETS — SHEARED (BS 1900)

SHEARED RIVETS ON TIE CLIPS, MAIN DECK FUSELAGE CIRCUM FRAME AT FS 1900 STRINGERS 10, 11, 12, 13, AND 14. REPAIRED PER POLAR AIR MA 5310-23:01.

Part: FRAME — CRACKED (BS 1900)

CRACKED MAIN DECK FUSELAGE CIRCUMFERENTIAL FRAME AT FS 1900 BETWEEN STRINGERS 11 AND 12. REPAIRED PER POLAR AIR MA 5310-23:01.

Part: RIVETS — SHEARED (BS 1920)

SHEARED RIVETS ON TIE CLIPS, MAIN DECK FUSELAGE CIRCUM FRAME AT FS 1920 STRINGERS 11 AND 12. REPAIRED PER POLAR AIR MA 5310-23:01.

Part: FRAME — CRACKED (BS 1900)

FRAME AT STA 1900 BETWEEN STR 11R AND 12R FOUND TO BE CRACKED AS A RESULT OF CARGO LOADING. THE CRACK SEVERED THE FRAME JUST ABOVE THE PRODUCTION SPLICE. REPAIRED PER POLAR AIR CARGO MA 5310-23:01.

Part: SKIN — BUCKLED (WS 1060)

BUCKLED SKIN LEFT WING LEADING EDGE WS 1060 TOP SIDE OF NOSE BEAM. REPAIRED PER BOEING SRM 57-20-03 FIG 7, 57-20-03 AND 51-10-01.

Part: SKIN — BUCKLED (WS 1250)

BUCKLED SKIN LEFT WING LEADING EDGE WS 1250 TOP SIDE OF NOSE BEAM AFT OF NR 5 LEADING EDGE FLAP. REPAIRED PER BOEING SRM 57-20-03, 51-40-03, 57-30-04 FIG. 2 AND 51-10-01.

Part: PANEL — CRACKED (WS 920)

CRACKED UPPER WING FIBERGLASS PANEL AT WS 920. REPAIRED PER BOEING SRM 51-40-09 AND 51-10-01.

Part: SKIN — BUCKLED (WS 920)

BUCKLED SKIN LEFT WING LEADING EDGE WS 920 TOP SIDE OF NOSE BEAM AFT OF NR 8 LEADING EDGE FLAP. REPAIRED PER BOEING SRM 57-20-03 AND 51-10-01.

Part: PANEL — CRACKED (WS 1250)

CRACKED FIBERGLASS PANEL LEFT WING UPPER SURFACE AT LEADING EDGE WS 1250. REPAIRED PER BOEING SRM 51-40-09 AND 51-10-01.

Part: PANEL — MISSING (LT WING)

LEFT WING BLOW OUT PANEL FOUND MISSING ON WALK-AROUND INSPECTION. REPLACED PANEL PER BOEING SRM 51-10-01.

Part: CLIPS — CRACKED (NR 1 PYLON)

CRACKED SUPPORT CLIPS ON FORWARD AND AFT INNER WEB ON NR 1 PYLON. FABRICATED AND INSTALLED REPLACEMENT CLIPS PER BAC SRM 51-30-01 AND 51-30-03.

Part: FLOORBEAM — CRACKED (BS 1860)

CRACK ON UPPER CAP ON FLOORBEAM AT STA 1860, BL 58. FABRICATED AND INSTALLED UPPER CAP PER BAC SRM 51-30-00.

Part: SUPPORT — BROKEN (NR 6 LE FLAP)

BROKEN LEFT WING LEADING EDGE SUPPORT ROD AFT OF NR 6 LEADING EDGE FLAP. REPLACED SUPPORT ROD PER BAC MM 57-21-00.

Part: FLANGE — CRACKED (NR 3 ENGINE)

CRACK ON NR 3 ENGINE TURBINE EXHAUST CASE R-FLANGE (RAIL) AT 6 O'CLOCK. WELDED AND STRESS RELIEVED CRACK PER PWA ENGINE MANUAL 72-53-01.

Part: FLANGE — CRACKED (NR 2 ENGINE)

CRACK ON NR 2 ENGINE TURBINE EXHAUST CASE S-FLANGE (RAIL) AT 2 O'CLOCK. WELDED AND STRESS RELIEVED CRACK PER PWA ENGINE MANUAL 72-53-01.

Part: LOCK LINKAGE — OUT OF TRACK (COCKPIT DOOR)

UNABLE TO OPEN CREW OVERHEAD EMERGENCY ESCAPE HATCH. FOUND LOCK LINKAGE OUT OF TRACK. REINSTALLED PROPERLY AND DOOR OPEN AND CLOSED OK. LATCH PIN REINSTALLED IAW OVERHAUL MANUAL 52-22-11 AND M/M 52-21-01.

Part: WARNING LIGHT — ILLUMINATED (CARGO DOOR)

WARNING LIGHT FOR LOWER AFT CARGO DOOR ILLUMINATED AFTER TAKEOFF. DUMPED FUEL AND RETURNED TO DEPARTURE STATION WITH LIGHT EXTINGUISHING WHEN LANDING GEAR EXTENDED. INSPECTED DOOR WITH NO DEFECTS NOTED. CHECKED AND ADJUSTED DOOR SWITCHES PER BAC MM 52-71-00 AND OPERATIONAL CHECK NORMAL.

Part: WARNING LIGHT — ILLUMINATED (CARGO DOOR)

SECOND INCIDENT, WARNING LIGHT FOR LOWER AFT CARGO DOOR ILLUMINATED AFTER TAKEOFF DURING FLAP RETRACTION. DUMPED FUEL AND RETURNED TO DEPARTURE STATION. WHEN FLAPS EXTENDED TO 20 UNITS LIGHT WENT OUT THEN BACK ON. LIGHT EXTINGUISHED DURING LANDING GEAR EXTENTION. INSPECTED DOOR WIRING FOR SWITCH, DOOR RIG.

Part: ALTIMETER — MALFUNCTIONED (CAPTAINS)

FLUCTUATION ON CAPTAINS ALTIMETER FROM 25,000 FT TO NEGATIVE 800 FT. REPLACED CAPTAINS ALTIMETER PER BAC MM 34-13-04 AND OPERATIONAL CHECK OK.

Part: TIRE TREAD — MISSING (NR 4)

ON POST FLIGHT INSPECTION, FOUND NR 4 TIRE WITH TREAD MISSING, TIRE DID NOT DEFLATE. TREAD HAD DAMAGED LEFT INBOARD FLAP. REPLACED TIRE ASSEMBLY PER M/M 32-45-01. REPAIRED FLAP PER BOEING SRM 51-40-09, 51-40-06 AND POLAR MA 5750-06:01.

Part: WIRE — BROKEN (NR 4 PYLON)

RIGHT WING OVERHEAT LIGHT ON. ISOLATED RIGHT WING IAW CHECKLIST LIGHT DID NOT GO OUT WITH EITHER NR 3 OR NR 4 ENGINE AT IDLE. WITH NR 3 ENGINE OF AND NR 4 ENGINE AT IDLE LIGHT WENT STEADY ON. FOUND WIRES TO AFT OVERHEAT SENSOR IN NR 4 PYLON BROKEN FROM SENSOR. REINSTALLED TERMINAL ENDS PER WIRING STANDARD PRACTICE MANUAL 20-60-06, OPERATIONAL CHECK PER 26-18-02.

Part: DUCT — DAMAGED (NR 3 PYLON)

RIGHT WING OVERHEAT LIGHT ON AFTER TAKEOFF. FOUND FLEXIBLE PNEUMATIC DUCT LEAKING DUE TO INTERNAL DAMAGE. REPLACED DUCT LEAK, CHECKED PER MAINTENANCE MANUAL 36-11-00.

Part: CLAMP — LOOSE (NR 3 PYLON)

RIGHT WING OVERHEAT LIGHT ON CLIMBOUT. PER MAINTENANCE MANUAL 36-11-00 ACCOMPLISHED DUCT LEAK CHECK AND PNEUMATIC DECAY CHECK. NOTED DUCT LEAK AT AFT CLAMP TO PYLON VALVE. REMOVED CLAMP AND INSPECTED DUCT, VALVE AND CLAMP, NO DEFECTS NOTED. REINSTALLED CLAMP LEAK CHECK NORMAL. VISUAL INSPECTION OF ENGINE AND PYLON DUCTS ACCOMPLISHED, NO LEAKS FOUND. REMOVED PYLON GAP COVER PLATES AND VISUALLY INSPECTED FOR LEAKS PER MAINTENANCE MANUAL 36-11-00, NO LEAKS NOTED.

Part: O-RING — PINCHED (NR 4 ENGINE)

NR 4 ENGINE OIL QUANTITY DECREASED TO ZERO IN FLIGHT, RATE OF DECREASE 1.5 GALLONS PER HOUR. LOW OIL PRESSURE LIGHT ILLUMINATED WITH LOW OIL PRESSURE INDICATED ENGINE SHUT DOWN. REPLACED PINCHED O-RING ON MAIN OIL FILTER HOUSING PER MAINTENANCE MANUAL 72-61-05. LEAK CHECK OK PER MAINTENANCE MANUAL 71-00-00.

Part: BRACE — DAMAGED (NR 3 PYLON)

NR 3 ENG PYLON DIAGONAL BRACE DAMAGED AND CHAFING ON O/B SAIL PLANE DOOR AT LOWER O/B SIDE. BLENDED OUT CHAFED AREA IAW BOEING SRM 54-40-01 FIG 5 MATERIAL WITHIN LIMITS.

Part: WEB — CRACKED (RUDDER)

LOWER RUDDER JUST BELOW ACTUATOR, CRACK IN WEB. REPLACED/INSTALLED IAW SRM 51-30-02 AND 51-10-01.

Part: INTERCOSTAL — CORRODED (BS 1460)

LEVEL 2, INTERCOSTAL IN KEEL BEAM AREA HAS SEVERE CORROSION AT APPX BS 1460. REMOVED AND REPLACED INTERCOSTAL IAW BOEING SRM 51-30-02.

Part: BATTERY PACK — DISCHARGED (CABIN)

UPPER DECK EMERGENCY LIGHT INOPERABLE. REMOVED AND CHARGED BATTERY PACK PER OHM 33-50-02 AND REINSTALLED BATTERY PACK PER MM 33-51-00.

Part: PANEL — DELAMINATED (FUSELAGE)

KEEL BEAM FUSELAGE PANEL BETWEEN WING GEAR INBD DOORS BULGED. REMOVED PANEL AND FABRICATED NEW PANEL, WORK DONE ON TRAVELER NR 78603.

Part: BRACE — DAMAGED (NR 4 PYLON)

NR 4 ENG PYLON DIAGONAL BRACE DAMAGED AND CHAFING ON O/B SAIL PLANE DOOR LOWER O/B SIDE. BLENDED OUT CHAFED AREA IAW BOEING SRM 54-40-01 FIG 5 MATERIAL WITHIN LIMITS.

Part: COWL SKIN — CRACKED (NR 3 ENGINE)

NR 3 ENG OUT/BD CORE COWL SKIN CRACKED/PUNCTURED. REPAIRED IAW BOEING SRM 54-30-02.

Part: COWL — CRACKED (NR 1 ENGINE)

NR 1 ENGINE IN/BD CORE COWL SKIN CRACKED AT AFT LWR EDGE. REMOVED DAMAGED AREA, FABRICATED REPAIR DOUBLER FILLERS AND INSTALLED AND TREATED IAW BOEING SRM 54-30-03 AND 51-30-02.

Part: COWL SKIN — DENTED (NR 3 ENGINE)

NR 3 ENG OT/BD CORE COWL SKIN DENTED. CUT OUT DAMAGED AREA AND REPAIRED IAW BOEING SRM 54-30-02.

Part: HEAT EXCHANGER — CRACKED (NR 3 PACK)

NR 3 A/C PACK HEAT EXCHANGER IS CRACKED. REINSTALLED NR 3 HEAT EXCHANGER IAW MM 21-51-03, WELDED CRACKED AREA IAW BAC5975.

Part: COWL — DAMAGED (NR 1 ENGINE)

NR 1 ENG OT/BD CORE COWL FWD UPPER EDGE DAMAGED. REMOVED DAMAGED AREA IAW BOEING SRM 54-10-02 AND REPAIRED IAW BOEING SRM 54-20-02.

Part: INSERT — STRIPPED (NR 4 ENGINE)

NR 4 ENGINE SHUT DOWN DUE TO LOW OIL QUANTITY AND LOW OIL PRESSURE. ENGINE WINDMILLED WITH N1 30 PERCENT, N2 2 PERCENT, OIL PRESSURE 10 PSI, OIL TEM 50 DEGREES. FOUND ANGLE GEAR BOX COVER LOOSE REPLACED MOUNT BOLT BUSHING PER M/M 72-61-00. PERFORMED GEAR BOX PRESSURIZATION, LEAK CHECK GOOD. ALSO, PERFORMED THE WINDMILLED ENGINE INSPECTION. PERFORMED ENGINE RUN PER M/M 71-00-00. MAG PLUGS CHECKED, NO METAL FOUND. FILTER REPLACED, NO METAL.

Part: O-RING — LEAKING (NR 4 ENGINE)

NR 4 ENGINE OIL QUANTITY DROPPED TO 0 AND OIL PRESSURE LIGHT CAME ON. SHUT DOWN ENGINE, WINDMILL TIME 22 MINUTES WITH ZERO OIL PRESSURE AND QUANTITY. FOUND PACKING LEAKING AT BOTTOM OF TOWER SHAFT REPLACED PACKING PER M/M 72-61-00 PAGE 1, COMPLIED WITH WINDMILL INSPECTION PER M/M 72-00-00 PAGES 680 O AND P. LEAK CHECK OK PER M/M 71-00-00.

Part: SKIN — DAMAGED (RT WING)

#3 PYLON TO RIGHT WING LEADING EDGE PULLED RIVETS ON REPAIR. REPLACED FASTENERS PER BOEING SRM 51-30-02.

Part: UNION — DISTORTED (NR 4 PYLON)

NR 4 HYDRAULIC SYSTEM WENT FROM 8.5 GALLONS TO 2.5 GALLONS, AS PER ALTERNATE PROCEDURES DEPRESSURIZED EDP AND ADP QUANTITY STABILIZED AT 2.5 GALLONS. RETURNED TO MIA. FOUND NR 4 EDP PRESSURE LINE BULKHEAD FITTING AT VERTICAL FIREWALL DISTORTED. REMOVED AND REPLACED FITTING PER BOEING MAINTENANCE MANUAL 20-11-05. LEAK CHECK OK AT 3,000 PSI.

Part: MODULE — FAILED (ANTI-SKID SYST)

AUTO BRAKE LIGHT ON IN FLIGHT, AUTO BRAKE WILL NOT ENGAGE. ON ROLL OUT, 3 TIRES BLOWN. CONFIRMED AUTO BRAKE FAILED IN OPEN DEFERRED PER MEL 32-23, TESTED ANTI-SKID. FOUND THAT BRAKES 9, 11, 12, AND 13 FAILED CHECK PER MAINTENANCE MANUAL 32-42-00. REPLACED MODULE PER 32-42-02. TIRES 9, 10, 11, 12 AND 13 REPLACED PER 32-45-01.

Part: FUEL QTY IND — FROZE (COCKPIT)

IN CRUISE, NR 3 MAIN FUEL QTY INDICATOR FROZE AT 61,000 LBS, 5 HOURS INTO FLIGHT, NR 3 FORWARD BOOST PUMP LOW PRESSURE LIGHT CAME ON. DUE TO WEATHER IN JFK, DIVERTED TO ORD. TRANSFERED TO DMI PER MEL 28-11. INDICATOR CHANGED AT JFK, CALIBRATED PER MAINTENANCE MANUAL 28-41-00.

Part: SKIN — DAMAGE (LT PYLON DOOR)

NR 3 SAILBOAT INBOARD DOOR INTERNAL SKIN PUNCTURED. ROUTED OUT AND SMOOTHED PUNCTURED AREA, FABRICATED FILLER AND DOUBLER, AND BONDED REPAIR MEMBERS I/A/W SRM 51-10-06.

Part: RUB STRIP — GOUGED (RT TE FLAP)

RIGHT INBOARD AFT FLAP RUB STRIP GOUGED. BLENDED OUT GOUGE AND FILLED I/A/W SRM 51-41-01.

Part: PANEL — CHAFED (RT PYLON)

NR 4 PYLON 1/2 MOON SHAPED RT ENGINE MOUNT ACCESS PANEL CHAFED THROUGH. FABBED NEW PART AND REPLACED ACCESS PANEL I/A/W 51-10-01.

Part: FLANGE — BROKEN (NR 2 PYLON)

NR 2 PYLON DUCT ATTACH FLANGE BROKEN. REPAIRED BY WELDING FLANGE I/A/W WD 85SFT9701A.

Part: SPINNER — DELAMINATED (NR 3 ENGINE)

NR 3 ENGINE INTAKE SPINNER AND CAP PROTECTIVE COATING CHIPPED AND DELAMINATED. SANDED AND CLEANED SPINNER AND CAP APPLY FIBERGLASS OVERLAYS I/A/W 72-31-01 AND PROTECTIVE COATING.

Part: SKIN — PUNCTURED (LT PYLON DOOR)

NR 1 LT SAILBOAT DOOR, TWO PUNCTURES IN OUTER SKIN. POTTED PUNCTURED ALUMINUM HONEYCOMB CORE AND BONDED REPAIR DOUBLER TO OUTER SKIN I/A/W SRM 51-40-06.

Part: DOOR — DAMAGED (LT MLG)

LEFT WING GEAR DOOR WHEELWELL INBOARD DOOR, 3RD FROM FWD HINGE, PUNCTURE IN DOOR STRUCTURE AT KEEL BEAM AREA. ALSO, BONDING WIRE BROKEN. REMOVED AND FABRICATED NEW FITTING AND INSTALLED FITTING I/A/W SRM 51-10-01.

Part: COWL — CRACKED (NR 4 ENGINE)

NR 4 ENGINE RT CORE COWL HAS CRACKED PIN GUIDE CHANNEL. REMOVED AND REPLACED NR 4 ENG CORE COWL GUIDE PIN CHANNEL I/A/W SRM 51-10-01.

Part: BRACKET — CRACKED (LT WING)

PROPULSION POD COWL SUPPORT INSTL AFT BRACKET ASSY CRACKED. REMOVED AND REPLACED PROPULSION POD SUPPORT BRACKET I/A/W M.M. 70-50-00.

Part: SKIN — CORRODED (BS 1900-1960)

EVIDENCE OF PILLOWING AROUND RIVETS FROM STA 1900 TO 1960 STR 46L TO 46R ON OUTER FUSELAGE SKIN (CORROSION FOUND). REPAIRED AREA FROM 1900 TO 1960 CTR 46L TO 46R I/A/W EA 47-5330-15-A0165 AND SRM 53-30-03, 53-10-02 AND 53-10-04.

Part: DOOR — CRACKED (LT MLG)

LEFT WING LANDING GEAR AFT LOWER CORNER OF FLYING DOOR CRACKED. REMOVED AND REPLACED LEFT W/L/G INBD DOOR I/A/W M.M. 32-12-06.

Part: TR SLEEVE — DAMAGED (LT ENGINE)

SEVERAL LAYERS OF METAL DAMAGED NR 4 ENGINE T/R SLEEVE L/E 8 O'CLOCK POSITION. SMOOTHED DAMAGED METAL LAYERS, TREATED CORROSION AND REBONDED METAL LAYERS I/A/W PRATT AND WHITNEY MANUAL 70-34-00 AND PAINTED PER SRM 51-24-11.

Part: SKIN — DELAMINATED (RT WING)

RIGHT WING INBOARD MID FLAP LEADING EDGE OUTBOARD END DELAMINATED. REPAIRED PER BOEING SRM 51-40-09, PAINTED PER 51-24-11.

Part: TORQUE BOX — CRACKED (RT HORIZ STAB)

HORIZONTAL STABILIZER TORQUE - BOX RT L/E CHAFE BUMPER SUPPORT TUBE CRACKED. REMOVED AND REPLACED HORIZ STAB TORQUE BOX RT SUPPORT TUBE I/A/W M.M. 55-10-00.

Part: TR SLEEVE — DAMAGED (NR 3 ENGINE)

NR 3 ENGINE EXTERIOR SKIN ON T/R SLEEVE IS DAMAGED (SCRATCHES AND GOUGES) RT SIDE AT 4:30 AND 5 O'CLOCK POSITION. SANDED AND CLEANED OUT SCRATCHES ABD GOUGES I/A/W SRM 54-00-02.

Part: PANEL — DELAMINATED (LT WING)

LEFT WING UPPER PANEL T/E FORWARD OF INBOARD FLYING PANEL, SEVERAL DELAMINATED SPOTS. REPAIRED PER BOEING SRM 51-40-12.

Part: SKIN — CRACKED (NR 2 PYLON)

NR 2 PYLON SKIN CRACKED - OUTBOARD SIDE AT CORNER DOUBLER BELOW TEXAS DOUBLER. REPAIRED PER BOEING SRM 54-30-03.

Part: TR SLEEVE — DAMAGED (NR 3 ENGINE)

NR 3 ENGINE - T/R EXTERIOR SKIN DAMAGED (GOUGE/SCRATCHES) AT 210 DEGREES. REPAIRED PER BOEING SRM 54-00-02.

Part: SKIN — CRACKED (RT PYLON DOOR)

NR 4 OUTBOARD - SAILBOAT DOOR - 484AR EDGE CRACKED BETWEEN BOTH FORWARD LOCK BRACKETS. REPAIRED PER BOEING SRM 51-40-06.

Part: FAIRING — CRACKED (NR 4 PYLON)

NR 4 PYLON, AFT FAIRING PAN CRACKED. REPLACED PER BOEING SRM 51-10-01.

Part: SKIN — DELAMINATED (RT TE MID FLAP)

R/W I/B FLAP L/E OF MID FLAP DELAMINATED. REPAIRED PER BOEING SRM 51-40-09.

Part: SKIN — DAMAGE (RT SPOILER)

R/W O/B GROUND SPOILER LOWER SKIN DENTED. REPAIRED PER BOEING SRM 51-40-06.

Part: PANEL — DELAMINATION (RT WING)

DELAMINATION FOUND ON NR 26 L/E PANEL. REPAIRED PER BOEING SRM 51-24-11.

Part: PANEL — DELAMINATED (LT WING)

L/W UPPER SURFACE T/E PANELS FORWARD OF INBD AILERON DELAMINATED. REPAIRED PER BOEING SRM 51-40-09.

Part: PANEL — DELAMINATION (RT WING)

R/W UPPER L/E PANEL DELAMINATED 12 INCHES FROM WING TO BODY FAIRING. REPAIRED PER BOEING SRM 51-40-09.

Part: SKIN — DELAMINATED (LT ELEVATOR)

ELEVATOR DELAMINATED. REPAIRED PER BOEING SRM 51-40-09.

Part: PANEL — DAMAGED (RT WING)

R/W UPPER FIBERGLASS PANEL PUNCTURE 1 FT FROM FUSELAGE. REPAIRED PER BOEING SRM 51-40-09.

Part: PULLEY — CRACKED (NR 3 FLAP TRACK)

CRACKED PULLEY FLAP POSITION INDICATOR SYSTEM AT NR 3 FLAP TRACK. REPLACED PULLEY PER BOEING MAINTENANCE MANUAL 20-11-03.

Part: SKIN — DAMAGE (NR 4 PYLON)

NR 4 PYLON RT SIDE LOWER SKIN REPAIR STRAP GOUGED ALONG LOWER EDGE. REPAIRED PER BOEING SRM 53-30-01.

Part: FAIRING — DAMAGE (NR 1 PYLON)

FAIRING ON L/E FWD OF NR 1 PYLON BROKEN. REPAIRED PER BOEING SRM 51-40-09.

Part: WINDOW — DELAMINATED (FUSELAGE)

NR 3R WINDOW DELAMINATED AT BOTTOM. REPLACED PER MM 56-11-02.

Part: PANEL — DAMAGE (WS 1364)

R/W PANEL 691 CB HOLE. REPAIRED PER SRM 51-40-06.

Part: SKIN — DAMAGE (LT WING)

R/W NR 14 L/E FLAP PUNCTURE IN FIBERGLASS PANEL JUST AFT NR 14 FLAP PANEL LOWER SURFACE. REPLACED PER BOEING SRM 51-40-09.

Part: SKIN — DAMAGE (LT WING)

PUNCTURE IN L/W TOP L/E PANEL O/B NR 2 ENGINE. REPAIRED PER BOEING SRM 51-40-09.

Part: PANEL — DAMAGE (LT WING)

L/W UPPER PANEL FWD OF GROUND SPOILER, BROKEN AND DAMAGED. REPAIRED PER BOEING SRM 51-40-09.

Part: SKIN — DAMAGE (LT FLAP)

LT O/B FWD FLAP PUNCTURE AT L/E I/B OF NR 2 TRACK. REPAIRED PER BOEING SRM 51-40-09.

Part: FAIRING — PUNCTURED (WING/FUSELAGE)

HOLE IN WING TO FUSELAGE FAIRING, LEFT SIDE. REPAIRED PER BOEING SRM 51-40-09.

Part: FAIRING — CRACKED (LT PYLON)

NR 2 PYLON, MULTIPLE CRACKED BRACKETS FOR ATTACH FITTINGS AND FAIRINGS. REPAIRED PER BOEING SRM 51-10-01.

Part: FLAP — DAMAGED (RT WING)

R/W I/B FLAP T/E FLAP PREVIOUS REPAIRS COMING LOOSE. REPAIRED PER BOEING SRM 51-40-09.

Part: SKIN — DAMAGE (RT TE AFT FLAP)

R/W O/B AFT FLAP UPPER SIDE HAS A HOLE. REPAIRED PER BOEING SRM 51-40-15.

Part: SKIN — DELAMINATED (RT AILERON)

R/W I/B AILERON LOWER AFT SURFACE DELAMINATED. REPAIRED PER BOEING SRM 51-40-09.

Part: FAIRING — DAMAGE (FUSELAGE)

RT BODY FAIRING, 194DR HAS HOLE. REPAIRED PER BOEING SRM 51-40-09.

Part: PANEL — DAMAGE (RT WING)

R/W L/E UPPER SURFACE FIBERGLASS PANEL PUNCTURED. REPAIRED PER BOEING SRM 51-40-09.

Part: FAIRING — CRACKED (LT PYLON)

NR 1 PYLON, STAINLESS STEEL FAIRING STRIP CRACKED IN 6 PLACES. REPLACED PER BOEING SRM 51-10-01.

Part: SKIN — DELAMINATED (NR 12 SPOILER)

R/W NR 12 SPOILER INBD EDGE DELAMINATED. REPAIRED PER BOEING SRM 51-40-06.

Part: AILERON — DAMAGED (RT WING)

R/W O/B AILERON BAD REPAIR ON O/B ENG. REPAIRED PER BOEING SRM 51-40-09.

Part: PANEL — DELAMINATED (LT WING)

L/W L/E PANEL DELAMINATED, UPPER MOST INBD. REPAIRED PER BOEING SRM 51-40-12.

Part: PYLON — CRACKED (NR 2 PYLON)

NR 2 PYLON UPPER FWD CORNER CRACK IN PANEL. REPAIRED WELDED PER BAC 5975.

Part: FAIRING — DAMAGE (NR 3 TE FLAP)

NR 3 T/E FLAP TRACK FAIRING PUNCTURE. REPAIRED PER BOEING SRM 51-40-09.

Part: TR SLEEVE — DELAMINATION (LT ENGINE)

NR 4 T/R SLEEVE INTERNAL SKIN DELAMINATED. REPAIRED PER PRATT AND WHITNEY MM 71-10-06.

Part: SKIN — GOUGED (NR 4 PYLON)

GOUGES IN NR 4 PYLON LEFT SIDE NAC STA 145. REPAIRED PER BOEING SRM 53-30-01 AND 51-10-02.

Part: PANEL — DAMAGE (RT WING)

RIGHT WING UPPER FIBERGLASS PANEL PUNCTURE ABOUT 4 FT FROM FUSELAGE. REPAIRED DAMAGED LEADING EDGE PANEL IAW SRM 51-40-09.

Part: SKIN — DELAMINATED (LT TE FLAP)

TWO SOFT SPOTS ON LEADING EDGE OF THE LEFT WING INBOARD FLAP OUTBOARD END OF THE FORE FLAP. REPAIRED PER BOEING SRM 51-40-12.

Part: PANEL — DAMAGE (LT WING)

PANEL NR 572EB LEFT WING CORNER BROKEN OFF. POTTED, APPLIED FILLERS AND DOUBLERS AND REPAIRED PER SRM 51-40-09 AND PAINTED PER SRM 51-24-11.

Part: PANEL — DELAMINATED (T-WING)

DELAMINATED PANEL LEFT WING UPPER AFT INBOARD WING. REPAIRED PER BOEING SRM 51-40-09 AND PAINTED PER 51-24-11.

Part: SKIN — DAMAGE (NR 2 PYLON)

NR 2 PYLON UPPER SKIN FLANGE IS CHAFED. REMOVED AND REPLACED WITH NEW STRAP IAW SRM 51-30-02.

Part: FAIRING — CRACKED (RT FUSELAGE)

RT BODY FAIRING 194DR DELAMINATED AND CRACKED AT EDGE. ALSO, 2 INCHES INBD OF EDGE. SANDED DAMAGED AREA SMOOTH, CLEANED, APPLIED FIBERGLASS OVERLAYS AND STOP DRILLED CRACK IAW SRM 51-40-09.

Part: SKIN — DAMAGE (BS 1780-1800)

FUSELAGE SKIN AT BS 1780 TO 1800 BETWEEN STR'S 15R AND 16R SKIN BULGED. REPAIRED PER SRM 53-30-03 FIG 1A AND 53-30-01 FIG 1A, 51-10-01, 51-10-02 AND 51-30-00.

Part: SKIN — DELAMINATION (LT TE FLAP)

LEFT WING I/B FLAP LWR SURFACE HAS SEVERAL DELAMINATIONS. CLEANED, SANDED AND REMOVED DELAMINATED SKIN IN 3 AREAS. APPLIED CORE FILLERS WHERE NEEDED AND REPAIRED USING FIBERGLASS OVERLAYS IAW SRM 51-70-04 AND 51-24-11.

Part: FAIRING — CRACKED (NR 3 PYLON)

NR 3 PYLON CLOSE OUT FAIRING CRACKED EXISTING WELDS. CLOSE OUT FAIRING WELDED ON TRAVELER NR 67277 PER BAC 5975.

Part: SAILBOAT — DELAMINATION (NR 2 PYLON)

NR 2 PYLON I/B SAILBOAT INNER SURFACE DELAMINATED ALONG EDGE. REMOVED DELAMINATED AREA, CLEANED, PRIMED, FABRICATED DOUBLER AND HOT BONDED IAW SRM 51-40-06.

Part: PANEL — DAMAGE (NR 1 PYLON)

PANEL NR 531 AB NR 1 PYLON O/B TRIANGLE PANEL HAS ENLARGED SCREW HOLES. ALSO, FORWARD EDGE ERODED. REPAIRED BY APPLYING FIBERGLASS OVERLAYS AND PAINTED PER SRM 51-40-15 AND 51-24-11.

Part: BRACKET — CORRODED (RT TE FORE FLAP)

LEVEL 2 CORROSION RIGHT WING I/B FOREFLAP I/B BOOMERANG FITTING MOUNT BRACKET. REMOVED AND REPLACED RIGHT WING FOREFLAP MOUNT BRACKET IAW SRM 51-30-02.

Part: SKIN — DENTED (NR 5 LT DOOR)

2 DENTS ON NR 5 LEFT DOOR LOWER EXTERNAL SKIN. REPAIRED PER BOEING SRM'S 52-10-02 AND 51-24-11.

Part: SKIN — DELAMINATED (LT WING)

REPAIR COMING LOOSE ON WING UNDERSIDE TRAILING EDGE JUST INBOARD OF INBOARD AILERON. REPAIRED PER BOEING SRM 51-40-09, PAINTED PER 51-24-11.

Part: SKIN — DAMAGE (RUDDER)

UPPER RUDDER LT SMALL PUNCTURE ON SURFACE STA 157.7. REPAIRED IAW SRM 51-40-09 BY APPLYING FIBERGLASS OVERLAYS AND PAINTED IAW SRM 51-24-11.

Part: STIFFENERS — CORRODED (FUSELAGE)

NUMEROUS AREAS OF CORROSION ON ALL STIFFENERS ON PANEL NR 191MM. REMOVED CORROSION AND TREATED AREAS WITH NEG MAT LOSS IAW SRM 51-10-01 AND 51-10-02.

Part: SKIN — PUNCTURED (RT TE MID FLAP)

DEEP PUNCTURE ON RIGHT WING OUTBOARD MID-FLAP LEADING EDGE SKIN. REPAIRED PER BOEING SRM'S 51-40-09 AND 51-24-11.

Part: FAIRING — DAMAGE (NR 1 PYLON)

1 PYLON AFT FIXED FAIRING MOUNTING FLANGE WORN AND CRACKED. REPLACED PYLON FAIRING IAW SRM 51-10-03 AND FABRICATED MOUNTING BRACKET.

Part: FAIRING — DELAMINATED (WING/FUSELAGE)

PANEL NR 194FR WING TO BODY FAIRING DELAMINATED. REPAIRED PER BOEING SRM 51-40-09 AND 51-24-11.

Part: PANEL — CORRODED (FUSELAGE)

CORROSION ON PANEL NR 191HH. REMOVED MINOR SURFACE CORROSION AND TREATED WITH NEG MAT LOSS PER SRM 51-10-01 AND 51-10-02.

Part: PANEL — PUNCTURED (RT WING)

PUNCTURE ON RIGHT WING UPPER SURFACE SMALL PANEL ON INBOARD SECTION. REPAIRED PANEL PER BOEING SRM'S 51-40-09 AND 51-24-11.

Part: DOOR — CRACKED (RT MLG)

CRACK IN LEADING EDGE OF THE RIGHT WING LANDING GEAR FLYING DOOR. REPAIRED PER BOEING SRM'S 51-40-06 AND 51-24-11.

Part: PANEL — DELAMINATED (FUSELAGE)

PANEL NR 193GL DELAMINATED. REPAIR PANEL AND PAINTED PER SRM 51-40-09 AND 51-24-11.

Part: PANEL — CORRODED (FUSELAGE)

LIGHT CORROSION ON PANEL NR 191BB. SANDED OFF CORROSION, APPLIED FIBERGLASS OVERLAYS AS REQUIRED AND PAINTED PER SRM 51-40-09 AND 51-24-11.

Part: FAIRING — DAMAGE (NR 2 TE FLAP)

NR 3 FIXED FWD FLAP TRACK FAIRING HAS DEEP PUNCTURE. REPAIRED PER SRM 51-40-15 AND PAINTED PER SRM 51-24-11.

Part: BRACKET — CRACKED (APU)

APU SURGE BLEED VALVE BRACKET CRACKED. WELDED BRACKET IAW BAC 5975, DYE CHECKED PER SOPM 20-20-02, NO CRACKS NOTED. INSTALLED BRACKET PER MM 49-53-01.

Part: DOOR — DAMAGE (NR 4 PYLON)

NR 4 I/B SAILBOAT DOOR, TWO CHAFED HOLES ON INNER SURFACE. REMOVED DAMAGED SURFACE METAL AND DAMAGED HONEYCOMB MAT, FABRICATED HONEYCOMB CORE PLUGS, DOUBLERS AND BONDED REPAIR MEM IAW SRM 51-40-06.

Part: FAIRING — PUNCTURED (RT WING/ FUS)

HOLE IN PANEL NR 292CR RIGHT FORWARD WING TO BODY FAIRING. REPAIRED PER BOEING SRM 51-40-09 AND PAINTED PER BOEING SRM 51-40-11.

Part: FAIRING — DELAMINATED (RT WING/FUS)

RT FWD WING TO BODY FAIRING PANEL 292AR DELAMINATED AT PREVIOUS REPAIR. REMOVED OLD REPAIR, SANDED AND CLEANED, APPLIED FIBERGLASS FILLERS AND OVERLAYS, PAINTED PER SRM 51-40-09 AND 51-24-01.

Part: FAIRING — PUNCTURED (RT WING/FUS)

HOLE IN PANEL NR 292BR RIGHT FORWARD WING TO BODY FAIRING. REPAIRED PER BOEING SRM 51-40-09.

Part: WEB — DAMAGE (VERT STAB)

GOUGES/CRACK ON WEB AT STA 82-8 LT VERTICAL STAB. BLENDED GOUGES SRM 51-10-01. REMOVED DAMAGE AND INSTALLED DOUBLER PER SRM 51-40-02.

Part: FAIRING — DAMAGE (NR 2 TE FLAP)

NR 2 FIXED FWD FLAP TRACK FAIRING HAS HEAVY WIND EROSION AND HOLES. SANDED DAMAGED AREA, SMOOTH POTTED HOLES, APPLIED FIBERGLASS OVERLAYS AND PAINTED PER SRM 51-40-15 AND 51-24-11.

Part: PANEL — DENTED (FUSELAGE)

DENT IN PANEL NR 191XL. SANDED AND REMOVED DAMAGED AREA, APPLIED FIBERGLASS FILLER OVERLAYS IAW SRM 51-40-09 AND SEALED APPLIED CONDUCTIVE COATING AND PAINTED PER SRM 51-40-11 AND 51-24-11.

Part: BRACKETS — CRACKED (NR 4 TE FLAP)

NR 4 FLAP AFT I/B BOGIE ASSY CRACKED. REMOVED AND REPLACED BROKEN BOGIE ASSY BRACKETS AS PER OHM 27-51-81.

Part: PANEL — WORN (FUSELAGE)

EDGE OF PANEL 294BR WORN THROUGH. REPAIRED PER BOEING SRM 51-40-09 AND 51-24-11.

Part: SKIN — DELAMINATION (RT WING)

RIGHT WING UPPER T/E SKIN PANEL IS DELAMINATED IN SEVERAL AREAS FWD OF O/B AILERON I/B END. SANDED AREA, APPLIED FIBERGLASS OVERLAYS AS REQUIRED IAW SRM 51-40-09 AND PAINTED SRM 51-24-11.

Part: PANEL — GOUGED (L-1 DOOR)

GOUGED PANEL L-1 DOOR LOWER HINGE. REPLACED PANEL PER BOEING SRM 51-30-02.

Part: PANEL — CORRODED (FUSELAGE)

KEEL BEAM PANEL FOR ROTATING BEACON HAS CORROSION AT BASE OF ROTATING BEACON. REMOVED MINOR SURFACE CORROSION AND TREATED WITH NEG MAT LOSS PER SRM 51-10-01 AND 51-10-02.

Part: ANGLE — CRACKED (RT ENGINE COWL)

NR 2 ENG I/B CORE COWL AFT HINGE ARM ATTACH ANGLE IS CRACKED AND FASTENERS LOOSE. REMOVED AND REPLACED ATTACH ANGLE IAW SRM 51-30-02.

Part: BULKHEAD — CORRODED (FWD FUSELAGE)

FWD PRESSURE BULKHEAD HAS LIGHT SURFACE CORROSION DIRT THROUGHOUT. NEEDS CLEANING AND CORROSION PREVENTATIVE TREATMENT. REMOVED CORROSION AND CLEANED DIRT IAW SRM 51-10-01 NEG MAT LOSS AREA TREATED AS REQUIRED PER SRM 51-10-02.

Part: RIB — DAMAGE (RT HORIZ STAB)

DAMAGED RIB ON RT HORIZ STAB AT ELEV STA 356.8 AT L/F OF ELEVATOR. REMOVED AND REPLACED RIB IAW SRM 51-10-02.

Part: STRAP — DAMAGED (NR 1 PYLON)

NR 1 PYLON RT SIDE LOWER EDGE PREVIOUS REPAIR STRAP CHAFED. REMOVED PREVIOUS REPAIR INSTALLED NEW DOUBLER IAW SRM 51-30-02.

Part: DOOR — CRACKED (LT PYLON)

NR 3 I/B SAILBOAT DOOR, AFT COWL LOCK CRACKED IN RADIUS. FABRICATED AND INSTALLED NEW ANGLE IAW SRM 51-10-01.

Part: SKIN — PUNCTURED (LT MLG DOOR)

HOLE AND LEVEL 1 CORROSION ON LEFT WING LANDING GEAR INBOARD LOWER DOOR. REMOVED LOWER FRAME SECTION AND REMOVED CORROSION, TREATED AND REPAIRED PER BOEING SRM 51-40-02 AND 51-10-02.

Part: DOOR — CRACKED (LT PYLON)

NR 3 I/B SAILBOAT DOOR, FWD BLOW OUT DOOR HINGE CRACKED. REMOVED AND REPLACED HINGE IAW SRM 51-10-01.

Part: STIFFENER — DAMAGE (WS 1020)

STIFFENER GOUGED AT WS 1020 FWD SPAR I/B OF NR 4 PYLON AS VEIWED FROM SLAT CAVITY. BLENDED DAMAGE AND TREATED IAW SRM 57-10-01 AND 51-10-02 ORG MAT .125 AFTER REWORK .114 WITHIN LIMITS IAW SRM 57-10-01 FIG 1.

Part: COVER — CORRODED (LT WING/PYLON)

NR 3 PYLON TO WING GAP COVER ERODED AT FWD END. SANDED AND CLEANED, APPLIED FILLER AND OVERLAYS IAW SRM 51-40-09.

Part: BRACKET — CRACKED (LT TE FLAP)

CRACKED OUTBOARD YOKE SUPPORT BRACKET AT NR 2 FLAP TRACK CARRIAGE AFT BOGGIE. INSTALLED NEW SUPPORT BRACKET PER OVERHAUL MANUAL 27-51-75.

Part: BOLT — CORRODED (NR 7 TE FLAP)

NR 7 FLAP TRACK CARRIAGE UPPER ATTACH FITTING BRACKET ATTACH BOLTS CORRODED LEVEL 1. REMOVED AND REPLACED 2 BOLTS PER OVERHAUL MANUAL 27-51-75.

Part: SKIN — CRACKED (LT WING)

LT UPPER WING PANEL 571BT FWD OF INBD GROUND SPOILER, BULGED. FOUND CRACK ON BACK SIDE OF PANEL CAUSING BULGE. REPAIRED PER SRM 51-40-01 AND TREATED PER SRM 51-24-11.

Part: SKIN — DAMAGED (RT TE MID FLAP)

RT I/B FLAP MID FLAP PANEL 587 PUNCTURED ON OUTSIDE SKIN. REMOVED DAMAGED AREA, POTTED CORE, APPLIED FIBERGLASS FILLERS AND OVERLAYS PER SRM 51-40-09.

Part: SKIN — CRACKED (LT TE MID FLAP)

CRACK LEFT WING INBOARD FLAP MID-FLAP LEADING EDGE OUTBOARD OF NR 3 FLAP TRACK. REPAIRED PER BOEING SRM 51-40-12.

Part: HINGE — CRACKED (LT MLG DOOR)

CRACKED HINGE LEFT WING LANDING GEAR WHEELWELL INBOARD DOOR SECOND FROM FORWARD HINGE AT KEEL BEAM AREA. REPLACED BROKEN HINGE ON STRUCTURE PER BOEING MAINTENANCE MANUAL 32-12-02.

Part: SKIN — CRACKED (BS 370-375)

CRACKS UNDER 2 RIVETS S19R BS 370 TO BS 375 TOP ROW LAP. REPAIRED PER BOEING SRM 53-30-03.

Part: ANGLE — CRACKED (RT HORIZ STAB)

CRACKED UPPER CHORD ANGLE RIGHT HORIZONTAL STABILIZER TRAILING EDGE REAR SPAR AREA STA 406.8. REMOVED FABRICATED AND INSTALLED A NEW CHORD ANGLE PER BOEING SRM 51-10-01, 53-30-02 AND 51-24-11.

Part: DOOR — DENTED (APU)

DENT IN RIGHT APU DOOR INTERIOR. REPAIRED PER BOEING SRM 52-40-02 FIGURE 2.

Part: SKIN — LIGHTNING STRIKE (NR 2 RT DOOR)

LIGHTNING STRIKE NR 2 RIGHT CABIN DOOR IN LOWER AFT EDGE SKIN. BLENDED OUT AREA ORIGINAL SKIN THICKNESS .100 INCH AFTER REWORK 0.084 INCH PER SRM 53-30-03. TREATED AREA PER 51-10-02.

Part: DOOR — SEPARATION (APU)

SEPARATION IN SKIN LAYERS ON LEFT APU DOOR AT FORWARD EDGE. REPAIRED PER BOEING SRM 52-10-02.

Part: SHELF — CORRODED (RT MLG WW)

LEVEL 1 CORROSION RIGHT BODY GEAR WHEELWELL INBOARD FORWARD SHELF BELOW FORWARD DIAGONAL BRACE (BARE METAL AND FLAKING PAINT). CORROSION REMOVED AND TREATED PER BOEING SRM'S 51-10-01 AND 51-10-02.

Part: DOOR — DENTED (APU)

DENT IN LEFT APU DOOR IN THE FORWARD EDGE. REPAIRED PER BOEING SRM 52-10-02 FIGURE 9.

Part: ANGLE — CRACKED (LT HORIZ STAB)

CRACKED UPPER CHORD ANGLE LEFT HORIZONTAL STABILIZER TRAILING EDGE REAR SPAR AREA STA 331.8. REMOVED FABRICATED AND INSTALLED A NEW CHORD ANGLE PER BOEING SRM 51-10-01, 53-30-02 AND 51-24-11.

Part: SKIN — LIGHTNING STRIKE (NR 2 RT DOOR)

LIGHTNING STRIKE NR 2 RIGHT CABIN DOOR IN LOWER CENTER SKIN. BLENDED OUT AREA ORIGINAL SKIN THICKNESS .063 INCH AFTER REWORK 0.055 INCH PER SRM'S 53-30-03 AND 51-24-11. TREATED AREA PER 51-10-02.

Part: SKIN — CORRODED (FUSELAGE)

LEVEL 1 CORROSION AROUND FASTENER HEADS IN APU SURROUNDING STRUCTURE EXTERIOR SKIN. REMOVED CORROSION PER BOEING SRM 51-10-01. TREATED PER BOEING SRM 51-10-02.

Part: COWL — CRACKED (NR 2 ENGINE)

CRACK UNDER RIVET NR 2 ENGINE CORE COWL AT OUTBOARD LATCH. REPLACED CHANNEL PER BOEING SRM'S 51-10-01 AND 51-10-02.

Part: BULL NOSE — CORRODED (NR 2 LE FLAP)

LEVEL 1 CORROSION ON LEFT WING NR 12 LEADING EDGE SLAT BULL NOSE INBOARD END. REPAIRED PER BOEING SRM'S 51-10-01 AND 51-10-02.

Part: SKIN — CRACKED (BS 460-480)

CRACK UNDER RIVET HEAD S14R LAP BETWEEN BS 460 AND BS 480 CENTER ROW. REMOVED FASTENER, REAMED HOLE TO .261 INCH. HIGH FREQUENCY EDDY CURRENT CONFIRMED CRACK REMOVAL PER NDT MANUAL 51-00-00. INSTALLED FASTENER PER BOEING SRM 51-30-02.

Part: SKIN — CORRODED (FUSELAGE)

LEVEL 1 CORROSION ON SKIN FORWARD OF NOSE WHEEL WELL. REMOVED CORROSION AND TREATED PER BAC SRM 51-10-01 AND SRM 51-10-02.

Part: PANEL — CORRODED (FUSELAGE)

LEVEL 1 CORROSION ON LOWER CENTER FUSELAGE PANEL BETWEEN LANDING GEAR DOORS. REMOVED CORROSION PER BAC SRM 51-10-01.

Part: RIB — CRACKED (NR 4 ENGINE COWL)

CRACK ON NR 4 ENGINE LEFT COWL LOWER RIB AT LATCH CUTOUT. BLENDED OUT CRACK PER BAC SRM 51-10-01.

Part: DOUBLER — CHAFED (NR 4 ENGINE COWL)

CHAFING ON NR 4 ENGINE LEFT COWL INNER DOUBLER ABOVE UPPER ACCESSORY EXHAUST CUTOUT. REPLACED DOUBLER PER BAC SRM 51-10-01.

Part: THRESHOLD — CORRODED (CARGO DOOR)

LEVEL 1 CORROSION UNDER BULK CARGO DOOR THRESHOLD PANELS, FORE AND AFT LOWER CORNERS. REMOVED CORROSION AND TREATED AREA PER BAC SRM 51-10-01 AND SRM 51-10-02.

Part: GEAR DOOR — CORRODED (RT MLG)

LEVEL 1 CORROSION TO THE SURFACE OF THE UPPER SKIN OF THE RIGHT MAIN BODY GEAR DOOR LOWER HALF. REMOVED CORROSION AND TREATED PER BAC SRM 51-10-01 AND SRM 51-10-02.

Part: DOUBLER — DAMAGE (NR 4 ENGINE COWL)

NR 4 LT COWL INTO DOUBLER BETWEEN THE 2ND AND 3RD RIBS BACK IS CHAFED. REMOVED AND REPLACED DOUBLER IAW SRM 51-30-02.

Part: OVERBOARD VENT — CRACKED (NR 4 COWL)

CRACK ON LOWER CENTER OVERBOARD VENT OF NR 4 RIGHT COWL. BLENDED CRACK PER BAC SRM 51-10-01 AND INSPECTED PER BAC NDTM 51-00-00, PT 6 FIG 4.

Part: SHELF PANEL — CORRODED (RT MLG WW)

LEVEL 1 CORROSION ON SHELF PANEL IN INBOARD RIGHT BODY GEAR WHEEL WELL. REMOVED CORROSION AND REPAINTED AREA PER BAC SRM 51-10-01.

Part: KEEL BEAM — CORRODED (BS 1100)

LEVEL 1 CORROSION ON BOX BEAM STIFFENER ON THE RIGHT KEEL BEAM BOX WEB AT BS 1100. BLENDED OUT CORROSION PER BAC SRM 51-10-01 AND TREATED AREA PER SRM 51-10-02.

Part: FLOORBEAM — CORRODED (BS 460)

LEVEL 1 CORROSION ON UPPER DECK FLOORBEAM AT BS 460 AT APPROX RBL 60. REMOVED CORROSION AND TREATED AREA PER BAC SRM 51-10-01 AND 51-10-02.

Part: SKIN — DAMAGED (RT MLG DOOR)

DAMAGED SKIN, DENTED AND TORN ON RIGHT BODY GEAR DOOR AT AFT INBOARD CORNER. REMOVED TORN SKIN AND STRAIGHTENED DENTED AREAS PER BAC SRM 51-40-01.

Part: SUPPORT — CORRODED (BS 1100)

RT LWR FUSELAGE BS 1100 ACCESS PANEL STRUCTURE SUPPORT HAS CORROSION. BLENDED OUT CORROSION IAW SRM 51-10-01, MIN MAT LOSS AND TREATED IAW SRM 51-10-02.

Part: WINDOW FRAME — CORRODED (FUSELAGE)

RT EXTERIOR FUSELAGE, 2 WINDOWS JUST FWD OF NR 3 CABIN DOOR HAVE LIGHT CORROSION AND BARE METAL AROUND WINDOW FRAMES. REMOVED CORROSION AT BOTH WINDOW FRAMES MINIMAL MAT LOSS TREATED AND PRIMED IAW SRM 51-10-01 AND 51-10-02.

Part: DOUBLER — DAMAGED (NR 4 ENG COWL)

DAMAGED DOUBLER AT UPPER FORWARD CORNER ON NR 4 ENGINE RIGHT COWL. FABRICATED AND REPLACED DAMAGED DOUBLER PER BAC SRM 51-30-02.

Part: SEAT TRACK — CORRODED (BS 420)

LEVEL 1 CORROSION ON SEAT TRACK INBOARD OF L1 DOOR AT BS 420. REMOVED CORROSION AND TREATED AREA PER BAC SRM 51-10-01 AND SRM 51-10-02.

Part: COWL — CHAFED (NR 4 ENGINE)

CHAFED AREA ON AFT SECTION UPPER EDGE OF NR 4 LEFT COWL. FABRICATED AND INSTALLED DOUBLER PER BAC SRM 51-40-02.

Part: COWL — CRACKED (NR 3 ENGINE)

NR 3 I/B FAN COWL LWR T/E CORNER IS BENT, CRACKED AND SEPARATING. BLENDED OUT CORNER PER SRM 51-10-01. REMOVED OUT CRACKS PER SRM 51-10-01 AND REINFORCED LAMINATED AS PER SRM 51-40-01.

Part: WINDOW FRAME — CORRODED (BS 1490)

LT EXTERIOR FUSELAGE FS 1490 CORROSION AND BARE METAL ON WINDOW FRAME. REMOVED CORROSION AND TREATED PER SRM 51-10-01 AND 51-10-02 MINIMAL MAT LOSS.

Part: KEEL BEAM — CORRODED (BS 1100)

KEEL BEAM LOWER WEB HAS LIGHT SURFACE CORROSION AT APPROX BS 1100. REMOVED LIGHT SURFACE CORROSION IAW SRM 51-10-01, TREATED AND PRIMED IAW SRM 51-10-02.

Part: WINDOW FRAME — CRACKED (BS 1370)

LT EXTERIOR FUSELAGE FS 1370 WINDOW FRAME CORRODED. REMOVED CORROSION AND TREATED PER SRM 51-10-01 AND 51-10-02 MINIMAL MAT LOSS.

Part: SKIN — CORRODED (L3 DOOR)

LT NR 3 CABIN DOOR, EXTERIOR SKIN CORRODED AT REPAIR ON LOWER DOOR. REMOVED CORROSION TREATED IAW SRM 51-10-01 MIN MAT LOSS.

Part: WINDOW FRAME — CORRODED (BS 560)

LT EXTERIOR FUSELAGE FS 560 3RD WINDOW FRAME AFT OF FWD ENTRY DOOR CORRODED. REMOVED CORROSION AND TREATED PER SRM 51-10-01 AND 51-10-02 WITH MINIMAL MAT LOSS.

Part: SKIN — CORRODED (BS 2700)

CORROSION ON FUSELAGE SKIN STA 2700 APPROX ABOVE RT ELEVATOR. BLENDED CORROSION IAW SRM 51-10-01. TREATED IAW SRM 51-10-02 NEGLIGIBLE MAT LOSS.

Part: STEPS — BROKEN (BS 2484)

TWO JACK SCREW AREA OF HORIZ STAB MAINTS STEPS BROKEN PUNCTURED AND DELAMINATED STA 2484. REMOVED AND REPLACED HORIZ STAB MAINTS STEPS IAW SRM 51-10-01, L/H/S.

Part: SKIN — CORRODED (WS 1398)

RT WING FWD LWR WING SKIN CORRODED AT WS 1398. REMOVED CORROSION, TREATED IAW SRM 57-30-01, 51-10-01 AND 51-10-02 ORG MAT .149 AFTER REWORK .117 AFTER REWORK 21 PERCNET LOSS.

Part: SKIN — CORRODED (WS 1350)

RT WING FWD LWR WING SKIN CORRODED WS 1350. REMOVED CORROSION TREATED IAW SRM 57-30-01, 51-10-01 AND 51-10-02 ORG MAT .275 AFTER REWORK .200 APPROX MAT LOSS 27 PERCENT.

Part: SKIN — CORRODED (WS 1388)

RT WING LOWER SKIN CORRODED AT WS 1388. REMOVED CORROSION, TREATED IAW SRM 57-30-01, 51-10-01 AND 51-10-02 ORG MAT .155 AFTER REWORK .110 APPROX MAT LOSS 29 PERCENT.

Part: SKIN — CORRODED (RT WING)

RT WING FORWARD LOWER WING SKIN CORRODED AFT OF SLAT 25. REMOVED CORROSION AND TREATED I/A/W SRM 57-30-01, 51-10-01 AND 51-10-02. ORG MAT, .224 INCH. AFTER REWORK, 32 PERCENT LOSS.

Part: SKIN — CORRODED (WS 1034)

RIGHT WING FWD LWR WING SKIN CORRODED AT WS 1034. REMOVED CORROSION AND TREATED IAW SRM 57-30-01, 51-10-01 AND 51-10-02 ORG MAT .330 AFTER REWORK .318 APPROX 4 PERCENT LOSS.

Part: SKIN — CORRODED (FUSELAGE)

NUMEROUS AREAS OF CORROSION LT TAIL SECTION ON EXTERNAL SKIN UNDER ELEVATOR AS MARKED. BLENDED OUT CORROSION AND TREATED WITH NEGLIGIBLE MAT LOSS IAW SRM 51-10-01 AND 51-10-02.

Part: DOOR — CORRODED (L4)

LT NR 4 CABIN DOOR EXTERIOR LWR AFT CORNER HAS LIGHT SURFACE CORROSION. REMOVED CORROSION AND TREATED PER SRM 51-10-01 AND 51-10-02.

Part: HINGE — CORRODED (R3 DOOR)

RT NR 3 CABIN DOOR, HINGE COVER PANEL HAS LIGHT CORROSION. REMOVED CORROSION RT NR 3 CABIN DOOR HINGE PANEL IAW SRM 51-10-01 MIN MAT LOSS AND TREATED SRM 51-10-02.

Part: SKIN — CORRODED (RT WING)

RT WING L/E WING UPPER SKIN CORRODED NR 13 L/E FLAP. REMOVED CORROSION FOUND NEGLIGENT MAT LOSS IAW SRM 51-10-01 AND 51-10-02.

Part: SKIN — CORRODED (WS 642-972)

NUMEROUS AREAS OF BARE METAL/LIGHT SURFACE CORROSION LT WING TOP WS 642 TO WS 972. REMOVED SURFACE CORROSION IAW 51-10-01 AND TREATED IAW SRM 51-10-02.

Part: SKIN — CORRODED (FUSELAGE)

CORROSION ON RT FUSELAGE SKIN TAIL SECTION UNDER RT ELEVATOR. BLENDED OUT CORROSION AND TREATED WITH NEGLIGIBLE MAT LOSS IAW SRM 51-10-01 AND 51-10-02.

Part: SKIN — CORRODED (WS 1328)

RIGHT WING FORWARD LOWER WING SKIN CORRODED W/S 1328. REMOVED CORROSION I/A/W SRM 57-30-01, 51-10-01 AND TREATED SRM 51-10-02. ORG MAT.190 INCH, AFTER REWORK, .170 INCH. APPROXIMATELY 10 PERCENT LOSS.

Part: COWL — CORRODED (NR 1 ENGINE)

LIGHT PITTING ON T/E LIP 3 AND 5 O'CLOCK POSITION NR 1 ENG NOSE COWL. BLENDED CORROSION AND TREATED PER SRM 51-10-01 AND 51-10-02.

Part: SKIN — CORRODED (WS 1300)

RT WING FWD LOWER WING SKIN CORRODED WS 1300. REMOVED CORROSION AND TREATED IAW SRM 51-30-01, 51-10-01 AND 51-10-02, MAT LOSS APPROX 12 PERCENT ORG MAT .195 AFTER REWORK .172.

Part: SKIN — CORRODED (WS 1382)

RT FORWARD WING LOWER SKIN CORRODED AT W/S 1382. REMOVED CORROSION, TREATED I/A/W SRM 57-30-01, 51-10-01 AND 51-10-02. ORG MAT, .251 INCH. AFTER REWORK, .200 INCH. APPROXIMATE MAT. LOSS, 20 PERCENT.

Part: SKIN — DAMAGE (LT TE FORE FLAP)

LEFT WING O/B FLAP, O/B END OF FORE FLAP HAS TWO ERODED AREAS ON L/E. REMOVED DAMAGED AREA, APPLIED FIBERGLASS FILLERS AND DOUBLES PER SRM 51-40-06 AND 51-24-11.

Part: SKIN — CORRODED (WS 1382)

RT FORWARD WING LOWER SKIN CORRODED AT W/S 1382. REMOVED CORROSION AND TREATED I/A/W SRM 57-30-01, 51-10-01 AND 51-10-02. ORG MAT, .163 INCH. AFTER REWORK, .135 INCH. APPROXIMATELY 17 PERCENT LOSS.

Part: ANGLE — CORRODED (RT ELEVATOR)

EXCESSIVE AMOUNTS OF CORROSION ON I/B VERTICAL ANGLE LOWER SPAR CAP AND WEB ELEV STA 2568, RT ELEVATOR. BLENDED OUT CORROSION IAW B747 SRM 51-10-01, NEG MAT LOSS TREATED AND PRIMED IAW SRM 51-10-02.

Part: COWL DOUBLER — DAMAGE (NR 3 ENGINE)

NR 3 LT COWL ATTACH ANGLE AND DOUBLER BETWEEN THE UPPER AND LOWER EXHAUST CUT OUTS IS CHAFED. FABRICATED AND INSTALLED NEW PART IAW SRM 51-10-01.

Part: SKIN — CORRODED (R2 DOOR)

RT NR 2 CABIN DOOR SKIN HAS LIGHT CORROSION AND BARE METAL. REMOVED CORROSION AND TREATED PER SRM 51-10-01 AND 51-10-02.

Part: SKIN — CORRODED (BS 2658)

LEVEL 1 CORROSION ON LOWER EXTERNAL SKIN AT BS 2658. REMOVED CORROSION AND TREATED AREA PER BAC SRM 51-10-01 AND SRM 51-10-02.

Part: SKIN — CRACKED (NR 3 ENGINE COWL)

NR 3 RT COWL SKIN IS CRACKED IN EXISTING HOLE JUST FWD OF THE AFT U-BOLT. BLENDED OUT CRACK IAW SRM 51-10-01.

Part: PANEL — CORRODED (LT WING)

LEFT WING I/B UPPER WING PANEL TRAILING EDGE HAS LIGHT CORROSION IN SEVERAL SPOTS. HAND CLEANED PANEL REMOVED SURFACE CORROSION AND TREATED IAW SRM 51-10-01 AND 51-10-02.

Part: SKIN — CORRODED (L2 DOOR)

LT NR 2 CABIN DOOR EXTERIOR SKIN HAS BARE METAL WITH SURFACE CORROSION. REMOVED CORROSION AND TREATED PER SRM 51-10-01 AND 51-10-02.

Part: RIB — CHAFED (NR 4 ENG COWL)

CHAFED AREA ON NR 4 ENGINE LEFT COWL RIB AT LOWER ACCESSORY EXHAUST CUTOUT. REPLACED RIB PER BAC SRM 51-10-01.

Part: COWL — DAMAGE (LT ENGINE)

NR 2 O/B CORE COWL IS GOUGED JUST INSIDE SKIN, AFT OF LATCH. REPAIRED PER SRM 51-30-02.

Part: SKIN — DELAMINATION (RT TE FORE FLAP)

RIGHT WING I/B FORE FLAP LOWER SURFACE IS DELAMINATED IN SEVERAL AREAS. REMOVED DELAMINATED AREAS POTTED DAMAGE CORE AND APPLIED FIBERGLASS OVERLAYS IAW SRM 51-40-09.

Part: SKIN — DELAMINATION (RT WING)

RIGHT WING UPPER L/E SKIN PNL IS DELAMINATED I/B OF NR 4 PYLON. SANDED AND CLEANED AREA APPLY FIBERGLASS OVERLAYS IAW SRM 51-40-09.

Part: SKIN — CORRODED (WS 1044)

RIGHT WING FWD LWR WING SKIN IS CORRODED WS 1044. REMOVED CORROSION AND TREATED IAW SRM 57-30-01, 51-10-01 AND 51-10-02. ORG MAT .334 AFTER REWORK .300 APPROX MAT LOSS 10 PERCENT.

Part: SKIN — CORRODED (WS 1405)

RT WING FWD LWR WING SKIN IS CORRODED AT WS 1405. REMOVED CORROSION AND TREATED IAW SRM 57-30-01, 51-10-02 AND 51-10-01 ORG MAT .149 AFTER REWORK .117 APPROX 21 PERCENT LOSS.

Part: SKIN — CORRODED (RT LE SLAT)

LIGHT CORROSION/BARE METAL ON SLAT NR 22 AS MARKED LOWER EDGE OF EXTERIOR SKIN. REMOVED CORROSION IAW 51-10-01 AND 51-10-02.

Part: SKIN — CORRODED (FUSELAGE)

RT EXTERIOR FUSELAGE HAS LIGHT CORROSION AND BARE METAL JUST ABOVE NR 2 RT CABIN DOOR. REMOVED CORROSION AND TREATED IAW SRM 51-10-01 AND 51-10-02.

Part: SKIN — CORRODED (WS 1343)

RIGHT WING FORWARD LOWER WING CORRODED AT W/S 1343 SKIN. REMOVED CORROSION AND TREATED I/A/W SRM 57-30-01, 51-10-01 AND 51-10-02. ORG. MAT .275 INCH. AFTER REWORK, .205 INCH. APPROXIMATELY 25 PERCENT LOSS.

Part: SKIN — DENTED (BS 1950)

DENT IN FUSELAGE SKIN AT BS 1950 BETWEEN S39R AND S40R. REPAIRED PER BAC SRM 53-30-03.

Part: COWL — CHAFED (NR 4 ENGINE)

LEADING EDGE LIP CHAFED THROUGH ON NR 4 ENGINE LEFT COWL. REPAIRED PER BOEING SRM 51-10-02 AND 51-40-03.

Part: SKIN — DENTED (RT HORIZ STAB)

DENT ON RIGHT HORIZONAL STABILIZER LEADING EDGE. REPAIRED DENT PER BAC SRM 51-10-01 AND PERFORMED NDT INSPECTION PER BAC NDTM 51-00-00, PART 6 FIG 4.

Part: SKIN — DELAMINATED (RT TE FORE FLAP)

RIGHT WING I/B FORE FLAP O/B L/E IS DELAMINATED. REMOVED DELAMINATED SKIN AND CORE, FABRICATED REPLACEMENT CORE, INSTALLED CORE, APPLIED FIBER GLASS OVERLAYS PER SRM 51-40-09.

Part: SKIN — DELAMINATED (RT TE FLAP)

RIGHT WING I/B T/E FLAP, T/E IS DELAMINATED AND DAMAGED TWO AREAS. REMOVED DAMAGED AND DELAMINATED MATERIAL, POTTED CORE AND APPLIED FIBERGLASS OVERLAYS PER SRM 51-40-09.

Part: SKIN — CORRODED (FUSELAGE)

RT EXTERIOR FUSELAGE NR 2 RT CABIN DOOR CORRODED AROUND WINDOW FRAME. REMOVED CORROSION IAW SRM 51-10-01.

Part: WINDOW FRAME — CORRODED (BS 1770)

RT EXTERIOR FUSELAGE FS 1770 CORROSION AROUND WINDOW FRAME. REMOVED CORROSION IAW SRM 51-10-01.

Part: SKIN — DELAMINATION (RT TE MID FLAP)

RIGHT WING MID FLAP UPPER SURFACE O/B END HAS AREAS OF DELAMINATION. REMOVED DELAMINATION APPLIED FIBERGLASS FILLERS AND OVERLAYS AS REQUIRED IAW SRM 51-40-09.

Part: COWL — CRACKED (NR 4 ENGINE)

CRACKED VENT SCOOP ON NR 4 ENGINE OUTBOARD RIGHT COWL. CRACK WELDED PER BAC SRM 51-10-01.

Part: PANEL — DAMAGED (LT LE FLAP)

DAMAGED METAL ON NR 1 LEFT LEADING EDGE PANEL BULLNOSE. BURNISHED AND TRIMMED PANEL PER BAC SRM 51-40-01.

Part: COWL — DAMAGE (NR 3 ENGINE)

NR 3 RT COWL CENTER SECTION OF THE L/E LIP IS CHAFED. REMOVED AND REPLACED RETAINER IAW SRM 51-10-01.

Part: SKIN — PUNCTURED (RT TE FLAP)

RIGHT WING T/E FLAP LWR SURFACE IS PUNCTURED. POTTED PUNCTURED SKIN AND CORE SANDED REPAIR AREA AND APPLIED FIBER GLASS OVERLAYS SRM 51-40-09.

Part: FRAME — CRACKED (LT MLG DOOR)

LT WING GEAR DOOR I/B LWR DOOR AFT FRAME ASSY UPPER SECTION WITH SUPERFICIAL CRACK AND ASSOCIATED WITH SURFACE CORROSION. BLENDED OUT CRACKS AND CORROSION IAW SRM 51-10-01.

Part: COWL — DAMAGE (NR 3 ENGINE)

NR 3 LT COWL EXISTING FWD UPPER ANGLE IS ROLLED BACK AND CHAFED. REMOVED AND REPLACED DAMAGED ANGLE IAW SRM 51-10-01.

Part: PANEL — CRACKED (NR 4 ENGINE COWL)

CRACKED AND DELAMINATED FORWARD LOWER INTERIOR WEB PANEL ON NR 4 LEFT COWL. REPLACED WEB PANEL PER BAC SRM 51-10-01, 51-10-02, AND 51-30-02.

Part: SKIN — CRACKED (RT TE MID FLAP)

RIGHT WING O/B MID FLAP I/B END UPPER SURFACE IS DELAMINATED AND CRACKED. STOP DRILLED CRACK APPLIED FIBERGLASS OVERLAYS AS REQUIRED IAW SRM 51-40-09.

Part: WINDOW FRAME — CORRODED (BS 1570)

RT EXTERIOR FUSELAGE FS 1570 CORROSION AROUND WINDOW FRAME. REMOVED CORROSION AND TREATED PER SRM 51-10-01 AND 51-10-02 WITH MINIMAL MAT LOSS.

Part: SPRING — CRACKED (AILERON CONTL)

ON TAXI IN, FIRST OFFICERS CONTROLS STIFF. FOUND AILERON LOAD LIMITER SPRING BROKEN. REPLACED AILERON LOAD LIMITER AND OPERATIONAL CHECKED PER BOEING MAINTENANCE MANUAL 27-11-05.

Part: AIR SPEED IND — MALFUNCTIONED (COCKPIT)

CAPTAIN'S AIR SPEED INDICATOR FROZE AT 70 KNOTS INDICATED AIR SPEED DURING TAKEOFF ABORTED TAKEOFF AT APPROXIMATELY 90 TO 100 KNOTS INDICATED AIR SPEED. REMOVED AND REPLACED CAPTAIN'S AIR SPEED INDICATOR PER MAINTENANCE MANUAL 34-13-05. OPERATIONAL CHECK OK, NO LEAKS. FOUND PER MAINTENANCE MANUAL 34-11-00.

Part: FAN BLADE — BENT (NR 1 ENGINE)

ON PREFLIGHT, FOUND 5 DAMAGED 1ST STAGE FAN BLADES. BLENDED 2 BLADES PER MAINTENANCE MANUAL 72-31-02, REPLACED 3 BLADES AND MATCHED SET PER MAINTENANCE MANUAL 72-31-02.

Part: SKIN — CRACKED (NR 1 PYLON)

CRACK ON PLATE 453DR ON NR 1 PYLON. FABRICATED AND INSTALLED DOUBLER PER BAC SRM 51-30-02 AND 51-40-02.

Part: TURBINE CASE — CRACKED (NR 2 ENGINE)

CRACKED S-RAIL NR 2 ENGINE, TWO PLACES 5 O'CLOCK AND 7 O'CLOCK. WELDED, STRESS RELIEVED AND FLAP PEENED PER PRATT AND WHITNEY MAINTENANCE MANUAL 72-53-01.

Part: DOOR — DELAMINATED (RT MLG)

DELAMINATION ON RIGHT WING LANDING GEAR LOWER STRUT DOOR AFT BOTTOM EDGE. REPAIRED PER BOEING SRM 51-040-09.

Part: SILL LOCK — BROKEN (CARGO COMPT)

BROKEN SILL LOCK AFT CARGO DOOR MOST FORWARD. REPLACED PER BOEING MAINTENANCE MANUAL 25-54-00.

Part: ROLLER TRAY — DAMAGED (AFT CARGO)

ROLLER TRAY DAMAGED AFT CARGO COMPARTMENT. REPLACED DAMAGED SECTION PER BOEING SRM 51-10-01.

Part: S-RAIL — CRACKED (NR 4 ENGINE)

CRACKED S-RAIL NR 4 ENGINE AT 10 O'CLOCK POSITION. WELD REPAIRED STRESS RELIEVED AND FLAP PEENED PER PRATT AND WHITNEY MAINTENANCE MANUAL 72-53-01.

Part: DOOR — DELAMINATED (RT PACK)

DELAMINATED RIGHT AFT PACK SERVICE DOOR. REPAIRED PER BOEING SRM 51-40-09 AND 51-40-12.

Part: STRUT — CORRODED (RT MLG)

LEVEL 1 CORROSION ON FORWARD BASE PORTION OF RIGHT WING GEAR STRUT. REMOVED CORROSION AND REPAINTED PER BAC SRM 51-10-01.

Part: DUCT — CRACKED (NR 3 PACK)

CRACKED DUCT AT NR 3 PACK SECONDARY HEAT EXCHANGER AT SEAL RETAINER. REPLACED DUCT PER BOEING MAINTENANCE MANUAL 21-51-06.

Part: PRECOOLER — CRACKED (NR 1 ENGINE)

CRACK ON NR 1 ENGINE PRECOOLER. WELDED CRACK PER BAC PROCESS 5975.

Part: LOCK ASSY — BROKEN (AFT CARGO)

BROKEN PALLET LOCK AFT CARGO COMPARTMENT. REMOVED AND REPLACED LOCK ASSEMBLY PER BOEING MAINTENANCE MANUAL 25-54-00.

Part: RETAINER — BROKEN (RT TE FLAP)

BROKEN WOBBLE RETAINER FOR OUTBOARD FLAP TORQUE TUBE IN RIGHT BODY GEAR WHEEL WELL. REPLACED PER BOEING MAINTENANCE MANUAL 27-51-20.

Part: STOP — BROKEN (CARGO DOOR)

BROKEN LOWER AFT STOP ON FORWARD LOWER LOBE CARGO DOOR. REPLACED STOP PER BAC MM 52-34-00.

Part: WHEEL — CRACKED (LT MLG)

CRACKED INNER HUB BETWEEN LIGHTENING HOLES WITH BEARING RACE SEPARATED FROM REST OF ASSEMBLY,(WHEEL HALVES DID NOT SEPARATE. REPLACED WHEEL AND TIRE ASSEMBLY PER BAC MM 32-45-01.

Part: SHAFT — WORN (NR 2 LE FLAP)

ON ARRIVAL, FOUND NR 2 LEADING EDGE GROUP TORQUE TUBE SPLINES COMPLETELY WORN OUT, WOULD NOT DRIVE NR 2 LEADING EDGE GROUP. REPLACED SHAFT PER BOEING MAINTENANCE MANUAL 27-81-05.

Part: PANEL — CRACKED (WS 499)

CRACKED FLYING PANEL TOP LEFT WING NEAR OLD REPAIR WS 499. REPAIRED PER BOEING SRM 51-40-09.

Part: TIRE — BLOWN (NR 11)

NR 11 TIRE BLOWN ON LANDING. PERFORMED BLOWN TIRE INSPECTION PER MAINTENANCE MANUAL 05-51-25, FOUND DAMAGE TO RT ADF SENSE ANTENNA PANEL, 3 WIRES BROKEN ON RIGHT BODY GEAR AND NR 11 AND NR 12 BRAKE SYSTEMS FAILED LOCKED WHEEL PROTECTION STEPS. REPLACED NR 11 AND NR 12 TIRES PER BOEING MAINTENANCE MANUAL 32-45-01, INTERIM REPAIR DOUBLER INSTALLED ON ADF SENSE PANEL PER POLAR ENGINEERING, DEACTIVATED NR 11 AND NR 12 BRAKES PER MEL 32-5. INTERIM REPAIR ON 3 BROKEN WIRES DEFERRED, ITEM INITIATED.

Part: SKIN — HOLES (APU DOOR)

DURING APU CHANGE FOUND 2 HOLES THROUGH SKIN ON LEFT APU ACCESS DOOR. REPAIRED PER BOEING SRM 51-40-02.

Part: FRAME — CRACKED (APU DOOR)

DURING APU CHANGE FOUND RIGHT APU ACCESS DOOR 2ND FRAME FROM FRONT EDGE CHORD CRACKED. REPAIRED PER BOEING SRM 51-40-03.

Part: DOOR — DENTED (APU)

DURING APU CHANGE FOUND DENT IN APU ACCESS DOOR. REPAIRED PER BOEING SRM 51-40-02.

Part: ROD END — WRONG PART (RT MLG DOOR)

WITH GEAR RETRACTED AND GEAR HANDLE IN OFF POSITION RED DOOR OPEN LIGHT ON FORWARD PANEL ILLUMINATED AND AMBER BODY DOOR OPEN LIGHT ON FE PANEL ILLUMINATED, IN BOTH PRIMARY AND ALTERNATE POSITIONS. REPLACED RIGHT BODY GEAR DOOR ACTUATOR IAW MM 32-33-27, LEAK CHECKED OK BUT DID NOT FIX PROBLEM. FOUND BODY GEAR DOOR LINKAGE ROD END WRONG PART NUMBER AND WOULD NOT ALLOW ADJUSTMENT. REPLACED ROD AND RIGGED PER BOEING MAINTENANCE MANUAL 32-33-27 PG 401-405, 32-14-10, 32-14-00.

Part: CONTROL CABLE — FAILED (BS 410)

RIGHT WHEEL WELL FORWARD BULKHEAD BS 1283 CABLE FOUND LOOSE. UPON INVESTIGATION FOUND CABLE BIRD CAGED BY PULLEY AT BS 410 RBL 90 WL 210. REPLACED CONTROL CABLE PER BOEING MAINTENANCE MANUAL 20-11-03 AND 27-11-00.

Part: CONTROL CABLE — FRAYED (WS 435)

LEFT WHEEL WELL AILERON CONTROL CABLE AA-9 HAS BROKEN STRAND AT REAR SPAR WS 435. REPLACED CABLE PER BOEING MAINTENANCE MANUAL 20-11-03 AND 27-11-00.

Part: FIRE WIRE — WORN (NR 3 ENGINE)

WIRES WORN THROUGH ON NR 3 ENGINE FIRE LOOP AT HYDRAULIC LINE BOX FORWARD BRACKET AT 3 O'CLOCK POSITION. REPLACED WIRING PER BOEING WIRING STANDARD PRACTICES MANUAL 20-10-13.

Part: NUT — SLIPPAGE (NR 4 ENGINE)

NR 4 ENGINE LEFT TANGENTIAL LINK AND RIGHT TANGENTIAL LINK SLIPPAGE MARK NOT IN ALIGNMENT. REPLACED NUT AND RETORQUED PER P AND W MAINTENANCE MANUAL 71-21-04.

Part: ANTI-ICE DUCT — CRACKED (NR 3 ENGINE)

NR 3 ENGINE NOSE COWL ANTI-ICE DUCT CRACKED NEAR PRESSURE SWITCH SENSE LINE ATTACHMENT INSIDE PYLON. REPLACED DUCT PER BOEING MAINTENANCE MANUAL 30-21-06.

Part: SKIN — DELAMINATED (RT ELEVATOR)

DELAMINATION ON RIGHT OUTBOARD ELEVATOR OUTBOARD AFT CORNER. REPAIRED PER BOEING SRM 51-40-15.

Part: TE WEDGE — DELAMINATED (RT ELEVATOR)

DELAMINATED TRAILING EDGE WEDGE RIGHT INBOARD ELEVATOR 3 FOOT BY 6 INCH AREA. REPAIRED PER BOEING SRM 51-40-15.

Part: PANEL — DELAMINATED (LT WING)

DELAMINATED LEFT WING TRAILING EDGE PANEL AFT OF NR 1 PYLON. REPAIRED PER BOEING SRM 51-40-09.

Part: SKIN — CRACKED (LT ELEVATOR)

CRACK LEFT INBOARD ELEVATOR ON UPPER SURFACE AT OUTBOARD END. REPAIRED PER BOEING SRM 51-40-15.

Part: PANEL — PUNCTURED (LT WING)

LEFT WING TRAILING EDGE LOWER SURFACE PUNCTURE IN PANEL 581HB. REPAIRED PER BOEING SRM 51-40-15.

Part: ELEVATOR — DELAMINATED (LT ELEVATOR)

LEFT INBOARD ELEVATOR TRAILING EDGE HAS SMALL DELAMINATION AT PREVIOUS REPAIR. REPAIRED PER BOEING SRM 51-40-09.

Part: DUCT — CRACKED (NR 1 ACM)

CRACKED Y-DUCT AT NR 1 AIR CYCLE MACHINE PACKAGE INBOARD FORWARD. REPLACED DUCT PER BOEING MAINTENANCE MANUAL 36-11-01.

Part: TORQUE LINK — GOUGED (NLG STEERING)

GOUGED NOSE LANDING GEAR TORQUE LINK ON RIGHT TOP SIDE. REPAIRED PER BOEING SRM 51-10-02 AND 51-10-01.

Part: BATTERY COMPT — BENT (APU)

OUTBOARD FLANGE BENT APU BATTERY COMPARTMENT. REPAIRED PER BOEING SRM 51-30-02 AND 51-10-01.

Part: STATIC WICK — NOT BONDED (LT ELEVATOR)

LEFT OUTBOARD ELEVATOR OUTBOARD STATIC WICK NOT BONDED TO ELEVATOR. REPAIRED PER BOEING SRM 51-10-01 AND MAINTENANCE MANUAL 51-60-00.

Part: FLOOR — CRACKED (BS 1680)

CRACKED FLOOR PANEL AFT CARGO COMPARTMENT BS 1680 AT CENTER LOCK. REPAIRED PER BOEING SRM 51-30-02.

Part: CONTACT PLATE — CRACKED (NLG)

NOSE LANDING GEAR SQUAT SWITCH CONTACT PLATE FASTENERS LOOSE AND PLATE BENT. ALSO, REINFORCEMENT PLATE CRACKED. REMOVED FABRICATED AND REINSTALLED CONTACT PLATE AND REINFORCEMENT PLATE PER BOEING SRM 51-10-01.

Part: SKIN — DAMAGED (NR 3 PYLON)

NR 3 PYLON RIGHT SIDE AFT MOUNT AREA SKIN DAMAGED BY SIDE COWLING. INSTALLED DOUBLER AND FILLER PER BOEING SRM 54-30-03.

Part: TURBINE EXHAUST — CRACKED (NR 2 ENGINE)

NR 2 ENGINE TURBINE EXHAUST CASE R-RAIL RADIAL CRACK AT 6 O'CLOCK POSITION. WELDED AND STRESS RELIEVED PER PRATT AND WHITNEY MAINT MANUAL 72-53-01.

Part: EXHAUST CASE — CRACKED (NR 1 ENGINE)

NR 1 ENGINE TURBINE EXHAUST CASE S-RAIL CRACKED AT 10 O'CLOCK. WELDED AND STRESS RELIEVED PER PRATT AND WHITNEY MAINT MANUAL 72-53-01.

Part: FAIRING — WORN (NR 4 PYLON)

NR 4 PYLON INBOARD SIDE AFT FAIRING SECTION WORN NAC STA 270. FABRICATED AND INSTALLED NEW PART PER BOEING SRM 54-30-03.

Part: SKIN — LOOSE RIVETS (FUSELAGE)

FUSELAGE EXTERIOR ABOVE LEFT APU ACESS DOOR WORKING FASTENERS. REPLACED FASTENERS PER BOEING SRM 51-30-02.

Part: SKIN — LOOSE RIVETS (NR 1 TE MIDFLAP)

FASTENERS LOOSE LEFT WING OUTBOARD MIDFLAP UPPER SURFACE LEADING EDGE AREA BY NR 2 FLAP TRACK. REPLACED OR RESET RIVETS PER BOEING SRM 51-30-02.

Part: RACEWAY — CRACKED (NR 4 ENGINE)

NR 4 ENGINE RIGHT SIDE RACEWAY BRACKET CRACKED ALONG WELD JOINT 2 TO 3 O'CLOCK POSITION. WELDED AND STRESS RELIEVED PER PRATT AND WHITNEY MAINT MANUAL 72-53-01.

Part: BRACKET — CRACKED (FUSELAGE)

LEFT BODY GEAR FORWARD DOOR UPPER STOP PAD, BRACKET CRACKED ON FORWARD SIDE. REPLACED BRACKET PER BOEING SRM 51-30-02.

Part: SKIN — CRACKED (BS 2700)

FUSELAGE SKIN CRACKED, LEFT SIDE ABOVE INBOARD ELEVATOR BS 2700. REPAIRED PER BOEING SRM 53-30-03.

Part: SEAL DEPRESSOR — CRACKED (CARGO DOOR)

FORWARD CARGO COMPARTMENT AFT DOOR SEAL DEPRESSOR, PREVIOUS REPAIR CRACKED. REPLACED SEAL DEPRESSOR PER BOEING SRM 51-10-01.

Part: SKIN — PUNCTURED (BS 3266)

FUSELAGE SKIN PUNCTURED BELOW AFT JACK PAD BS 2366 WL 220. REPAIRED PER BOEING SRM 53-30-03 FIG 1 A.

Part: INLET PANEL — DENTED (NR 1 ENGINE)

NR 1 ENGINE INLET ACOUSTIC PANEL DENTED AT 4 O'CLOCK. REPAIRED PER BOEING SRM 54-34-03.

Part: TURBINE EXHAUST — CRACKED (NR 2 ENGINE)

NR 2 ENGINE S-RAIL CRACKED 5 TO 7 O'CLOCK. WELDED AND STRESS RELIEVED PER PRATT AND WHITNEY MAINT MANUAL 72-53-01.

Part: STATIC WICK — LOOSE (LT ELEVATOR)

BASE LOOSE ON INBOARD STATIC WICK LEFT OUTBOARD ELEVATOR. REMOVED AND REPLACED FASTENERS PER BOEING SRM 51-30-02.

Part: FRAME — CHAFED (NR 3 PYLON)

NR 3 PYLON UPPER LINK CHAFED AT 12:00 O'CLOCK POSITION. REMOVED DAMAGE AND SHOT PEENED SURFACE, TREATED DEPTH .021 INCH WITHIN LIMITS PER BOEING SRM 54-40-01.

Part: SKIN — WORN (NR 3 PYLON)

NR 3 PYLON WORN WHERE HIT BY SIDE COWLING. BLENDED AREA PER BOEING SRM 54-10-01.

Part: WEDGE — LOOSE FASTENERS (LT HORIZ STAB)

LOOSE TRAILING EDGE WEDGE ON LEFT OUTBOARD HORIZONTAL STABILIZER BOTTOM AND TOP. REPLACED FASTENERS PER BOEING SRM 51-30-02.

Part: SKIN — GOUGED (NR 3 PYLON)

NR 3 PYLON GOUGED BY ENGINE SIDE COWL ON LEFT SIDE. REPAIRED PER BOEING SRM 54-30-03.

Part: DOOR — CORRODED (RT MLG)

LEVEL 1 CORROSION AT TRAILING EDGE RIGHT BODY GEAR INBOARD WHEELWELL DOOR. REMOVED CORROSION AND TREATED PER BOEING SRM 51-10-01.

Part: DOOR — CORRODED (RT MLG)

LEVEL 1 CORROSION ON AFT EDGE OF RIGHT BODY GEAR OUTBOARD DOOR. REMOVED CORROSION, TREATED AND FOUND WITHIN LIMITS PER BOEING SRM 51-10-01.

Part: SKIN — WORN (NR 3 PYLON)

NR 3 PYLON RIGHT SIDE RIVETS PULLED THROUGH SKIN. REPLACED RIVETS PER BOEING SRM 51-30-02.

Part: COWLING — DAMAGED (NR 3 ENGINE)

NR 3 ENGINE COWLING AND THRUST REVERSER TRANSLATING SLEEVE DAMAGED WHEN NR 3 THRUST REVERSER OPERATED WITH CORE COWL OPEN. REPLACED CORE COWL AND REPAIRED TRANSLATING SLEEVE PER BOEING SRM 54-30-03 FIG. 21 AND SRM 51-40-06 FIG. 12.

Part: FLOW CONTL UNIT — LEAKING (PAX OXY SYSTEM)

DURING MAINTENANCE, FOUND PASSENGER O2 LOW. FOUND ELECTRO-PNEUMATIC FLOW CONTROL UNIT LEAKING INTERNALLY. REPLACED SAME IAW MM 35-21-00. ALSO, REPLACED AFT PASSENGER O2 BOTTLE, (P/N 801307-00), (S/N 962110) NO LEAKS NOTED.

Part: FIRE WARNING — ACTIVATED (APU)

ON CLIMBOUT, FL 28.0 IAS 320 KTS, APU FIRE WARNING LIGHT AND BELL CAME ON. ALSO, ON PILOT'S OVERHEAD PANEL. DISCHARGED APU FIRE BOTTLE, LIGHT WENT OUT IN APPROX 8 SECONDS. ON LANDING, NO EVIDENCE OF FIRE IN APU AREA. WIRES INSPECTED AND FIRE TEST NORMAL PER MM 26-15-00. PLACARDED APU FIRE BOTTLE AND DEFERRED PER MEL 26-8, DUE BOTTLE FIRED.

Part: COUPLING — LEAKING (PAX OXY SYSTEM)

DURING MAINTENANCE, FOUND LEAK IN PASSENGER OXYGEN SYSTEM. REMOVED AND REPLACED COUPLING IAW MM 35-21-00, LEAK CHECK NORMAL.

Part: OXY CONTROL UNIT — LEAKING (COCKPIT)

DURING MAINTENANCE, DISCOVERED LEAK IN CREW OXYGEN SYSTEM. REMOVED AND REPLACED CONTROL UNIT IAW MM 35-11-00, LEAK CHECK OK.

Part: COMP BLADES — BIRD STRIKE (NR 1 ENGINE)

UPON INSPECTION OF NR 1 ENGINE DURING MAINTENANCE, FOUND EVIDENCE OF BIRD STRIKE ON FAN BLADES AND FAN EXIT DIAPHRAGM. COMPLIED WITH CONDITIONAL INSPECTION PER 5-51-14 AND BORESCOPE INSPECTION PER MM 72-00-00. FOUND 6 EACH 5TH STAGE COMPRESSOR BLADES BENT BEYOND LIMITS. REMOVED AND REPLACED ENGINE, RUNUP CHECK NORMAL PER MM 71-00-0.

Part: LIGHT ASSY — INOPERATIVE (CABIN)

FOUND EMERGENCY LIGHT ABOVE CREDENZA LIGHT INOP. REMOVED AND REPLACED EMERGENCY LIGHT ASSY IAW MM 33-51-00, OPS CHECKS NORMAL.

Part: LIGHT — MALFUNCTIONED (CABIN)

EMERGENCY LIGHT ABOVE CREW SERVICE DOOR ILLUMINATES WITH EMERGENCY LIGHT SWITCH IN OFF POSITION. REMOVED AND REPLACED EMERGENCY LIGHT ASSEMBLY IAW MM 33-51-00, OPS CHECK NORMAL.

Part: SKIN — CORRODED (BS 480)

FOUND DISHED RIVETS, POUCHED SKIN, AND CORRODED CLIP AT BS 480 BETWEEN STR 42R AND STR 43R, LOWER RT FUSELAGE. REMOVED DISHED RIVETS, CUT OUT SKIN AND REPLACED WITH FILLER AND DOUBLER PER SRM 53-30-03. BLENDED OUT CORROSION, REMOVED AND REPLACED NEW CLIP PER SRM 53-30-03. APPLIED CPC TO AREA. LEAK CHECK OK.

Part: PRBC LINE — LEAKING (NR 4 ENGINE)

AT TOP OF DESCENT, NR 4 ENGINE COMPRESSOR STALLED WITH EGT RISE, SHUTDOWN ENGINE AND RESTARTED. ENGINE STARTED AND STABILIZED NORMALLY, USED ENGINE FOR REMAINDER OF FLIGHT, OPS NORMAL. PERFORMED BLEED CHECK, BORESCOPE AND PT2 LEAK CHECK, FOUND FLEX LINE FROM PRBC LEAKING. REPLACED SAME IAW MM 77-11-03, OPS CHECK NORMAL.

Part: WIRE — SHORTED (NR 2 LED SWITCH)

WHEN LEADING EDGE DEVICES WERE EXTENDED, THE NR 2 INDICATED AMBER. AIRCRAFT RETURNED TO BLOCKS. FOUND WIRING AT THE NR 2 POSITION SWITCH WAS SHORTING TO GROUND. REPAIRED IAW STANDARD WIRING PRACTICES 20-10-13.

Part: EGT INDICATION — HIGH (NR 3 ENGINE)

ON TAKEOFF, NR 3 EGT WENT TO 920 DEGREES FOR APPROX 45 SECONDS. ALL OTHER INDICATIONS NORMAL AND NO ABNORMAL PERFORMANCE FOR REST OF FLIGHT. PERFORMED REQUIRED INSPECTIONS FOR CATEGORY A ITEMS PER MM 72-00-00 PG 680L 3 B, SATISFACTORY.

Part: ENGINE — FAILED (NR 4)

ON CLIMBOUT, NR 4 FILTER BYPASS LIGHT CAME ON LEAVING 5,000 FEET. THE NR 4 THROTTLE RETARDED TO IDLE, OIL QTY WENT TO ZERO, OIL TEMP TO 150, SHUTDOWN ENGINE, DUMPED FUEL AND RETURNED TO CALI. ENGINE DID NOT SURGE, TAKEOFF EGT WAS NORMAL, ZERO OIL PRESSURE DURING 45 MINUTES WINDMILL. ENGINE DETERMINED UNSERVICEABLE SINCE RESERVICED OIL EXITED ENGINE IMMEDIATELY VIA TAILPIPE ON GROUND MOTORING. ENGINE REPLACED IAW WORK CARDS MA7100-001 AND MA7100-002.

Part: FUEL FILTER — CONTAMINATED (NR 2 ENGINE)

AFTER LEAVING BLOCKS, WHILE ADVANCING POWER, NR 2 ENGINE FLAMED OUT. INSPECTED ENGINE, FOUND MAIN FUEL FILTER CONTAMINATED WITH DIRT, PAINT AND DEBRIS. REPLACED FUEL FILTER IAW MM 73-21-02, FUEL PUMP AND FCU IAW MM 73-11-01, OPS CHECK NORMAL. AS PRECAUTIONARY CHANGED FILTERS ON NR 1, NR 3, NR 4 ENGINES, SCHEDULED REPLACEMENT OF ALL 4 FILTERS IN 50 FLIGHT HOURS.

Part: FITTING — CRACKED (STRINGER 11)

FOUND CRACK ON SPLICE FITTING AT STRINGER 11 FWD AREA, NO OTHER DEFECTS. REPLACED FITTING WITH (P/N 654U6039-112) IAW SB 53-A2280.

Part: LIMITER — INTERMITTENT (RUDDER)

DURING PUSHBACK, RUDDER RATIO LIGHT CAME ON. FOUND RUDDER TRAVEL LIMITED. ACTUATED TEST SWITCH ON UPPER RUDDER CONTROL UNIT, LIGHT EXTINGUISHED AND BOTH RUDDERS MOVE FULL TRAVEL.

Part: RETRACT MECH — MALFUNCTIONED (LANDING GEAR)

AFTER SUCCESSFUL LANDING GEAR RETRACTION, BOTH LT AND RT WING LANDING GEAR CAME OUT OF THE WHEEL WELLS. BOTH GEAR FULLY LOCKED IN THE DOWN POSITION AND BOTH DOORS REMAINED OPEN, RETURNED TO HKG. CHECKED RIGGING AND CABLE TENSIONS OF WING GEAR SELECTOR VALVE, WING GEAR SELECTOR VALVE QUADRANT, WING GEAR DOOR OPERATED SEQUENCE VALVE ALTERNATE GEAR EXTENSION ELECTRIC MOTORS AND CABLES. ALL CHECKS FOUND SATISFACTORY WITHIN MAINTENANCE MANUAL LIMITS. ACCOMPLISHED GEAR SWING, COULD NOT DUPLICATE CONDITION AND AIRCRAFT RELEASED.