N920FT

Part: STARTER — FAILED (NR 3 ENGINE) · airframe 79,683 hrs · 19,291 cycles

AFTER PUSH BACK, CREW REPORTED NR 3 ENGINE WOULD NOT START. PARAMETERS INDICATE NORMAL, NR N1 OR N2 INDICATION. REPLACED STARTER IAW MM 80-10-00. OPS NORMAL.

Part: SKIN — CORRODED (LT WING) · airframe 79,587 hrs · 19,269 cycles

LEFT WING LOWER SKIN CORROSION ON OUTBOARD JACK PAD AREA AT FSS 1295. REPAIR CARRIED OUT IAW BOEING FAA FORM 8100-9. SUPPLEMENTARY JOB CARDS AFM 0147 AND AFM 1068 FOR DETAILS.

Part: BEAM — CRACKED (BS 300-320) · airframe 79,587 hrs · 19,269 cycles

FWD CARGO, FOUND CRACKS PROPAGATED FROM BLANKET HOLE AT STA 300 AND 320 AND LT NOSE WHEEL WELL VERTICAL BEAM WEB AT WL 160. REPAIR CARRIED OUT IAW LO-BY714-072 INTERIM WEB REPAIR. CONTINUE INSPECTION PER SB 747-53A2293.

Part: YAW DAMPER — MALFUNCTIONED (RUDDER) · airframe 79,161 hrs · 19,176 cycles

RUDDER WOULD NOT DEFLECT. REPLACED UPPER AND LOWER YAW DAMPER COMPUTERS PER AMM 22-16-02.

Part: ACTUATOR — MALFUNCTIONED (ELEVATOR) · airframe 78,739 hrs · 19,086 cycles

CREW RETURNED AIRCRAFT TO BLOCKS ADVISING ELEVATORS WERE STIFF DURING FLIGHT CONTROL CHECK. REPLACED ELEVATOR FEEL ACTUATOR PER MM 27-31-17. OPS CHECK PER MM 27-31-14, NO DISCREPANCIES NOTED.

Part: FUEL CONTROL — MALFUNCTIONED (NR 4 ENGINE) · airframe 78,199 hrs · 18,981 cycles

CREW REPORTED NR 4 ENGINE WOULD NOT MAKE TAKEOFF POWER. ENGINE COULD ONLY MAKE 1.24 EPR. REPLACED FUEL CONTROL. PERFORMED TRIM RUN, ALL NORMAL PER 73-21-01 AND 73-11-01.

Part: PUMP — MALFUNCTIONED (NR 4 ENGINE) · airframe 78,199 hrs · 18,981 cycles

CREW REPORTED NR 4 ENGINE WOULD NOT MAKE TAKEOFF POWER. ENGINE COULD ONLY MAKE 1.24 EPR. REPLACED FUEL PUMP. PERFORMED TRIM RUN, ALL NORMAL PER 73-21-01 AND 73-11-01.

Part: VALVE — LEAKING (FUEL JETTISON) · airframe 77,952 hrs · 18,935 cycles

DURING WALKAROUND OBSERVED FUEL LEAKING FROM RIGHT FUEL JETTISON MANIFOLD. REMOVED AND REPLACED RIGHT FUEL JETTISON NOZZLE VALVE PER BOEING MM 28-31-03. OPS CHECK OK.

Part: LINE — CHAFED (NR 3 ENG OIL) · airframe 77,783 hrs · 18,899 cycles

NR 3 ENG OIL PRESS FLUCTUATES FROM 35 TO 45 PSI. ENG OIL PRESS LIGHT BLINKS ON & OFF. ALSO OIL QTY WENT FROM 3/4 TO 1/4 AND BACK TO 1/2. FOUND UPPER ENGINE OIL LINE AT OIL FILTER HOUSING CHAFED. REPLACED CHAFED LINE, COI ISSUED/ AMM 20-11-18.

Part: ACTUATOR — FAILED (MLG) · airframe 77,630 hrs · 18,867 cycles

WHEN GEAR WAS EXTENDED A LOUD NOISE WAS HEARD AND HAD LOSS OF NR 1 HYDRAULIC SYSTEM. LANDING WAS NORMAL. FOUND EXTEND/RETRACT ACTUATOR FAILED. REPLACED EXTERNAL/RETRACT ACTUATOR PER MM 32-33-01.

Part: ACTUATOR — LEAKING (MLG) · airframe 77,630 hrs · 18,867 cycles

WHEN GEAR WAS EXTENDED A LOUD NOISE WAS HEARD AND HAD LOSS OF NR 1 HYD SYSTEM. LANDING WAS NORMAL. FOUND LEFT BODY GEAR LEVELING CYLINDER FAILED. REPLACED PER MM-13-15.

Part: ACTUATOR — FAILED (NR 1 HYD SYSTEM) · airframe 77,630 hrs · 18,867 cycles

WHEN GEAR WAS EXTENDED A LOUD NOISE WAS HEARD AND HAD LOSS OF NR 1 HYDRAULIC SYSTEM. LANDING WAS NORMAL. FOUND DOWN LOCK ACTUATOR FAILED. REPLACED ACTUATOR PER MM 32-33-15.

Part: ENGINE — FAILED (NR 1) · airframe 77,177 hrs · 18,780 cycles

ON TAKEOFF TOWER REPORTED SPARKS FROM NR 1 ENGINE DURING CLIMB.EGT HIGH (600 DEGREE) AS COMPARED TO OTHER ENGINES.N1 90% N2 94%, EXPERIENCED COMPRESSOR STALL AT FL 250 WHILE CDLIMBING TO FL 350. ENGINE REPLACED PER POLAR WORK CARD M71-00-02.

Part: ACTUATOR — MALFUNCTIONED (FUEL CONTROL) · airframe 77,136 hrs · 18,771 cycles

IN CLIMB AT 9200 FT, NR 1 ENGINE EGT WENT TO 771 FOR 18 SECOND, FOLLOWED BY A LOUD BLAST & BRIGHT FLASHES OF LIGHT FROM LT SIDE. WIND MILL TIME 50 MINUTES, OIL PRESSURE 5 PSI, N1 22 PERCENT N2 18 PERCENT, FIRE SWITCHED PULLED & NR 1 EDP SUPPLY OFF. REVIEWED EXCEEDANCE FOUND TO BE WITHIN LIMITS, ENGINE VISUAL INSPECTION ACCOMPLISHED, FOUND FUEL CONTROL ACTUATOR C/B OPEN. REPLACED FUEL CONTROL MOTOR ACTUATOR PER AMM 73-00-00, PERFORMED ENGINE RUN UP OK.

Part: ENGINE — MALFUNCTIONED (NR 1) · airframe 77,136 hrs · 18,771 cycles

IN CLIMB AT 9200 FT NR 1 ENGINE EGT WENT TO 771 FOR 18 SECOND, FOLLOWED BY A LOUD BLAST & BRIGHT FLASH OF LIGHT FROM LEFT SIDE OF A/C, WINDMILL TIME 50 MINUTES,MINIMUM OIL PRESSURE 5 PSI. REVIEWED EXCEDANCE,FOUND WITH IN LIMITS.VISUAL INSPECTION ACCOMPLISHED,FOUND FUEL CONDITION MOTOR C/B POPPED,REPLACED CONTINOUS ACTUATOR,PERFORMED ENGINE RUN.

Part: VALVE — FAILED (NR 4 ENGINE) · airframe 77,050 hrs · 18,754 cycles

NR 4 ENGINE START VALVE FAILED TO OPEN IN GROUND START, DUCT PRESSURE IS 40 PSI. NR 4 ENGINE START VALVE MANUAL OPS OK DEFERRED PER DDPG 80-2.

Part: START VALVE — FAILED (NR 3 ENGINE) · airframe 77,050 hrs · 18,754 cycles

NR 3 ENGINE START VALVE FAILED TO OPEN IN GROUND START, DUCT PRESSURE IS 40 PSI. REPLACED START VALVE NR 3 ENGINE, AMM 80-11-04, OPS CHECK OK.

Part: FUEL SYS — LEAKING (RT WING) · airframe 77,050 hrs · 18,754 cycles

A/C RETURN TO BLOCK DUE TO FUEL GOING OVERBOARD FROM RIGHT WING VENT BOX. DRAINED SURGE TANK, CHECKED FUELING SYSTEM PER AMM 28-21-00, CHECKS NORMAL WITH ALL PUMPS RUNNING & FUELING DUCTS PRESSURIZED.

Part: CONNECTOR — DIRTY (ENGINE) · airframe 77,050 hrs · 18,754 cycles

FUEL CONDITION ACTUATOR NR 1 ENGINE CIRCUIT BREAKER POPPED ON ENGINE START. REMOVED, CLEANED & REINSTALLED CONNECTOR AT J14-P, PERFORMED SYSTEM CHECK, GOOD PER AMM 76-11-00.

Part: GENERATOR — FAILED (NR 2 ENGINE) · airframe 77,050 hrs · 18,754 cycles

NR 2 ENGINE GENRATOR WILL NOT COME ON LINE. REMOVED AND REPLACED NR 2 ENGINE GENERATOR, OPS CHECK OK PER AMM 24-21-01.

Part: GENERATOR — MALFUNCTIONED (NR 1 ENGINE) · airframe 77,050 hrs · 18,754 cycles

NR 1 ENGINE GENERATOR FEEDER FAULT. REMOVED AND REPLACED NR 1 ENGINE GENERATOR PER AMM 24-21-01, SYSTEM OPS CHECK OK.

Part: GEARBOX — MALFUNCTIONED (NR 2 ENGINE) · airframe 76,940 hrs · 18,730 cycles

WHEN STARTING NR 2 ENGINE, N2 WENT 62.5 PERCENT IMMEDIATELY. NR 2 GENRATOR CAME ON LINE IMMEDIATELY, NO N1 INDICATION, OIL QTY WENT FROM FULL TO 3/4. REPLACED GEARBOX ANGLE PER AMM 72-61-03. OPERATIONAL & LEAK CHECK OK PER AMM 71-00-00.

Part: SKIN — DAMAGED (CARGO DOOR) · airframe 76,688 hrs · 18,677 cycles

PRIOR TO DEPARTURE FOUND DAMAGE ON FWD CARGO DOOR LWR SKIN. REPAIRED DAMAGE AT LWR CORNER SKIN PER SRM 52-30-06, FIGURE 1 SHEET 7.

Part: COMPUTER — MALFUNCTIONED (COCKPIT) · airframe 76,568 hrs · 18,651 cycles

AFTER T/O AFTER GEAR UP, FELT A/COLL TO THE LEFT, GOT CONTROL OF A/C THAN IT HAPPENED AGAIN. FLIGHT CONTROL SHOWING UPPER RUDDER MOVING TO THE LEFT, THEN SLOWLY GOING BACK TO CENTER. DECLARED EMERGENCY & SHUTOFF UPPER YAW DAMPER COMPUTER, PROBLEM SEEMED TO GO AWAY. REPLACED UPPER YAW DAMPER COMPUTER, ALL OPERATIONS NORMAL.

Part: ENGINE — MALFUNCTIONED (NR 1) · airframe 76,544 hrs · 18,647 cycles

NR 1 ENGINE SHUT DOWN, EGT WENT OFF SCALE, N1 WENT 20 PERCENT, N2 14 PERCENT & OIL PRESSURE 5 PSI. REPLACED NR 1 ENGINE PER WORK CARD MM 71-00-02 & 71-08-07, ALL OPS CK NORMAL.

Part: FILTER — DAMAGED (FUEL OIL) · airframe 76,475 hrs · 18,633 cycles

NR 2 ENGINE COMPRESSOR STALL. VISUAL INSPECTION, REMOVED AND REPLACED FUEL & OIL FILTER, ENGINE IDLE RUN ACCEPTABLE PER AMM 71-00-00.

Part: FRAME — CRACKED (NACELLE) · airframe 76,400 hrs · 18,618 cycles

FRETTING & CRACKS IN FRAME AFT EDGE OF HYD COMPT. CUT OUT DAMAGE AREA PER SRM 53-10-04, FABRICATED ANGLE & PLATE INSTALLED PER SRM 53-10-02.

Part: FITTING — CORRODED (FUSELAGE) · airframe 76,400 hrs · 18,618 cycles

CORROSION ON RIGHT MLG FITTING BB 1480 RBL 22. REPAIRED AREA PER SAA SK 920-001(SR)FAA FORM 811-3.

Part: PANEL — DENTED (FUSELAGE) · airframe 76,400 hrs · 18,618 cycles

MAIN CARGO RT SIDE STA 1790 FRAME PROTECTION PANEL DENTED, REMOVED AND REPLACED PANEL AND INSP FRAME FOR ANY DAMAGE. DAMAGED INSULATION MOUNT BRACKET , SEVERAL AREA OF COVERS , BLENDED AREA OUT , REPAIR IAW SRM 51-10-04, SRM 51-30-02, SRM 51-40-03.

Part: ACCESS PANEL — DELAMINATED (RT WING) · airframe 76,400 hrs · 18,618 cycles

REFUELING PANEL 521BB IS DELAMINATED INSIDE RIGHT WING. REMOVED DELAMINATED AREA PER SRM 51-40-04, REPAIRED PER SRM 51-40-15.

Part: FLOOR SUPPORT — CRACKED (FUSELAGE) · airframe 76,400 hrs · 18,618 cycles

BULK CARGO FLOOR SUPPORT IS CRACKED AT STA 240. REMOVED DAMAGED AREA, FABRICATED SUPPORT ANGLE & SPLICED IN PER SRM 57-30-02 & SRM 53-11-03, 51-10-02 & 51-10-06.

Part: SUPPORT — CORRODED (FUSELAGE) · airframe 76,400 hrs · 18,618 cycles

CORROSION ON SUPPORT STRUCTURE STA 940 LBL 3 TO RBL 3 REF KEEL BEAM AREA. REMOVE CORROSION AREA, FABRICATED WEB FLANG SRM 53-50-04, INSTALLED PER SRM 51-30-05.

Part: FLOOR PANEL — CRACKED (FUSELAGE) · airframe 76,400 hrs · 18,618 cycles

CARGO PIT FLOOR PANEL STA 1680 THRU 1780 IS CRACKED & CORRODED. CUT OUT AND REMOVED DAMAGE, NO CRACK FOUND. CUT OUT FABRICATED & INSTALLED AS PER SRM 51-40-08 & 51-10-02.

Part: FLAP TRACK — DELAMINATED (TE FLAPS) · airframe 76,400 hrs · 18,618 cycles

DELAMINATION SEVERAL AREA, I/B FORE FLAP L/E RIGHT WING B/W FLAP TRACK. CLEANED AREA & REPAIRED PER SRM 51-40-15.

Part: SUPPORT ANGLE — CORRODED (FUSELAGE) · airframe 76,400 hrs · 18,618 cycles

CORROSION AT FUSELAGE EXTERNAL STRUCTURE, AT STA 1180 AFT OF LWR BEACON. REMOVED SUPPORT ANGLE, FABRICATED NEW ANGLE & INSTALLED PER SRM 51-10-01.

Part: ANGLE — BROKEN (FUSELAGE) · airframe 76,400 hrs · 18,618 cycles

L-ANGLE BROKEN AT STA 1940, L1 BIL 20 AFT CARGO AREA. REMOVED AND REPLACED BROKEN BRACKET PER SRM 51-30-02. NEW BRACKET FABRICATED PER SRM 53-11-23.

Part: PANEL — DELAMINATED (FUSELAGE) · airframe 76,400 hrs · 18,618 cycles

PANEL NR 194 LR DELAMINATED IN SEVERAL PLACES. REMOVED DAMAGE & PREP PER SRM 51-40-15.

Part: SUPPORT ANGLE — CORRODED (FAIRING) · airframe 76,400 hrs · 18,618 cycles

CORROSION ON FWD SIDE OF WING TO BODY FAIRING SUPPORT ANGLE, AT BS 980 & AT RBL 36 AT I/B END OF PANEL 192. REMOVED CORROSION AREA PER 51-10-01 & SRM 51-30-02, FABRICATED REPAIRED.

Part: PANEL — DELAMINATED (NR 4 NACELLE) · airframe 76,400 hrs · 18,618 cycles

NR 4 ENGINE PYLON PANEL 481C HAS DELAMINATION. REMOVED DAMAGE IAW SRM 51-40-15, BONDED APPLIED PER SRM 51-40-15.

Part: PANEL — CORRODED (FUSLEAGE) · airframe 76,400 hrs · 18,618 cycles

FUSELAGE PANEL 191OA, BOTH HAVE HEAVY CORROSION. REMOVED 2 EA SPLICE PLATES IAW 51-30-01. FOUND TO BE OUT OF LIMIT, FABRICATED NEW PLATES PER BOEING DRAWING 65B3878.

Part: FAIRING — DAMAGED (WING TO BODY) · airframe 76,400 hrs · 18,618 cycles

DAMAGED TO WING TO BODY FAIRING PANEL 192RR. REMOVED DAMAGED AREA REPAIR PER SRM 51-40-15.

Part: NOSE COWL — DELAMINATED (NR 2 ENGINE) · airframe 76,400 hrs · 18,618 cycles

NR 2 ENGINE NOSE COWL T/E TO CORE COWL HAS DELAMINATION. REPAIRED PER SRM 54-31-03.

Part: SKIN — DELAMINATED (FUSELAGE) · airframe 76,400 hrs · 18,618 cycles

LWR FUSELAGE PANEL NR 1913, EXTENSION SIDE HAS DELAMINATION. REMOVED DAMAGED AREA PER SRM 51-40-15, REPAIR PER SRM 51-40-15.

Part: SKIN — CRACKED (PAX DOOR) · airframe 76,400 hrs · 18,618 cycles

CRACK IN LWR CORNER OF MAIN ENTRY DOOR. REPAIRED IN LWR FWD CORNER L1 DOOR IAW SRM 52-10-02.

Part: PANEL — WORN (NACELLE) · airframe 76,400 hrs · 18,618 cycles

PANEL 453DL AREA WORN OUT THRU & CRACKED ON BACK SIDE. FABRICATED NEW PANEL PER HARDNESS & CONDUCTIVITY & SRM 51-30-02.

Part: PANEL — DELAMINATED (FUSELAGE) · airframe 76,400 hrs · 18,618 cycles

FUSELAGE FITTED PANEL 191WL HAS DELAMINATION ON EXTERIOR SIDE. REPAIRED PANEL 191WL PER SRM 51-40-15.

Part: STOP FITTING — CORRODED (FUSELAGE) · airframe 76,400 hrs · 18,618 cycles

STOP FITTING STA 1490 L1 BL20 HAS CORROSION AFT PIT. REMOVED FASTENERS TO FOM IAW 51-40-02, REMOVED CORROSION, MAX MATERIAL REMOVED IAW 53-10-01, OK TO TREAT.

Part: PANEL — DELAMINATED (FUSELAGE) · airframe 76,400 hrs · 18,618 cycles

FUSELAGE FITTER PANEL NR 192 EER HAS DENT & DELAMINATION. REMOVED & CLEANED DAMAGED AREA PER SRM 51-40-15, APPLIED CURVED FIBERGLASS REPAIR SRM 51-40-03.

Part: PANEL — DELAMINATED (FUSELAGE) · airframe 76,400 hrs · 18,618 cycles

FUSELAGE FITTED PANEL 199BR HAS DELAMINATED. REMOVED DAMAGED AREA, REPAIRED PER SRM 51-40-15.

Part: PANEL — DELAMINATED (FUSELAGE) · airframe 76,400 hrs · 18,618 cycles

FUSELAGE FITTING PANEL 192CO DELAMINATED ON INTERIOR SIDE. REPAIRED PER SRM 51-40-15.

Part: FAIRING — DELAMINATED (NR 4 FLAP) · airframe 76,400 hrs · 18,618 cycles

FIX FAIRING NR 4 FLAP HAS AREA OF DELAMINATION. REMOVED DAMAGED AREA & BONDED PER SRM 51-40-15.

Part: PANEL — DELAMINATED (LT WING) · airframe 76,400 hrs · 18,618 cycles

DELAMINATION ON PANEL LT WING LANDING LIGHT ENTRY DOOR SPLIT & DELAMINATION 4 X 8 INCHES UNDERSPEED TAPE. REMOVED DAMAGE & REPAIRED PER SRM 51-40-13.

Part: PANEL — DELAMINATED (LT WING) · airframe 76,400 hrs · 18,618 cycles

DELAMINATION UNDER SPEED TAPE REPAIR LT WING, LOWER SERVICE WBL 175 FWD SPAR. REMOVED DAMAGE AREA RE-BONDED PER SRM 51-40-15.

Part: SKIN — DELAMINATED (MLG DOOR) · airframe 76,400 hrs · 18,618 cycles

LEFT WING GEAR STRUT LWR DOOR AFT LWR END IS DELAMINATED AT LWR SIDE HAS EXFOLIATING CORROSION. REPAIRED IAW SRM 51-40-06 & 51-10-02.

Part: FAIRING — DELAMINATED (FLAP TRACK) · airframe 76,400 hrs · 18,618 cycles

DELAMINATION ON SEVERAL AREA OF NR 3 FLAP TRACK, AFT FAIRING RT WING. REMOVED DAMAGE AREA & REBONDED PER SRM 51-40-15.

Part: ACCESS PANEL — CRACKED (RT WING) · airframe 76,400 hrs · 18,618 cycles

RIGHT WING ACCESS PANEL 672 DB HAS CRACK & DELAMINATION. REMOVED DAMAGE AREA & BONDED PER SRM 51-40-15.

Part: PANEL — DELAMINATED (HORIZONTAL STAB) · airframe 76,400 hrs · 18,618 cycles

HORIZONTAL STABLIZER RT PANEL NR 344 I/B DELAMINATED ON BACK SIDE. REMOVED AND BONDED AREA PER SRM 51-40-15.

Part: FLAP TRACK — DELAMINATED (TE FLAPS) · airframe 76,400 hrs · 18,618 cycles

DELAMINATION SEVERAL AREA O/B SIDE OF NR 2 FLAP TRACK AFT FAIRING R/W. REMOVED DAMAGED AREA PER SRM 51-40-15, BONDED REPAIRED PER SRM 51-40-12.

Part: FAIRING — DELAMINATED (NR 4 FLAP TRACK) · airframe 76,400 hrs · 18,618 cycles

DELAMINATION SEVERAL AREA OF NR 4 FLAP TRACK AFT FAIRING L/W. REMOVED DAMAGE AREA PER SRM 51-40-15, BONDED REPAIR PER SRM 51-40-15.

Part: LOGIC CARD — INOPERATIVE (LE FLAPS) · airframe 76,214 hrs · 18,569 cycles

PILOTS LEADING EDGE FLAP LIGHTS INOPERATIVE. FLIGHT ENGINEERS LEADING EDGE FLAP INTRANSIT LIGHT INOP. REPLACED A-4 CARD IN LEADING EDGE LOGIC CONTROL BOX AS PER 27-31-00.

Part: ACTUATOR — INOPERATIVE (RUDDER) · airframe 76,168 hrs · 18,557 cycles

RUDDER RATIO LIGHT ON DURING TAXI OUT, LOWER RUDDER INDICATOR INOP. REPLACED LOWER RUDDER RATIO ACTUATOR AS PER AMM 27-21-12 PAGE 201. OPS CHECK OK.

Part: TRANSMITTER — INOPERATIVE (FLAP INDICATOR) · airframe 76,158 hrs · 18,555 cycles

RIGHT INBOARD TRAILING EDGE FLAP WILL NOT EXTEND BEYOND 12 UNITS. LEADING EDGE BANK 1 & 2 FLAP INDICATION INOP ON BOTH PILOT & F/E PANEL. REMOVED & REPLACED RIGHT HAND INBOARD FLAP TRANSMITTER. RE-RACKED A4 & A8 LOGIC CARDS. OP CHECK OK ON BOTH, AS PER AMM 27-81-00.

Part: B-NUT — LOOSE (ENGINE OIL LINE) · airframe 75,842 hrs · 18,472 cycles

NR 2 ENGINE IN FLIGHT SHUTDOWN DUE TO OIL PRESSURE LOSS AND OIL QTY=0. ON ENGINE INSPECTION FOUND MAIN SUPPLY OIL LINE B-NUT LOOSE AT OIL TANK, SECURED B-NUT SERVICED OIL, PERFORMED ENGINE RUN.

Part: WARNING LIGHT — ILLUMINATED (COCKPIT) · airframe 75,691 hrs · 18,434 cycles

NR 2 INS WARNING LIGHT ON AFTER DOOR CLOSED. CLEAN AND REALIGNED INU. OPS CK NORMAL AS PER 34-41-00.

Part: SLIDE — DEPLOYED (CABIN) · airframe 75,586 hrs · 18,411 cycles

UPPER DECK CREW RH DOOR ESCAPE SLIDE DEPLOYED. SLIDE REMOVED AND DEFERRED PER MEL 25-11-3.

Part: ENGINE — MALFUNCTIONED (NR 1) · airframe 75,498 hrs · 18,388 cycles

NR 1 ENGINE UNABLE TO MAKE TAKEOFF POWER. REMOVED AND REPLACED NR 1 ENGINE IAW 71-00-11 AND MM 71-00-02. ENGINE RUN NORMAL.

Part: DOOR — BROKEN (ACM SERVICE) · airframe 75,193 hrs · 18,321 cycles

RT SIDE FORWARD NR 3 ACM SERVICE DOOR OPENED ON APPROACH. REMOVED BROKEN DOOR, REPLACED WITH SERVICEABLE DOOR IAW 52-48-01 AMM.

Part: COMPRESSOR — STALLED (NR 3 ENGINE) · airframe 75,141 hrs · 18,308 cycles

NR 3 ENG COMPRESSOR STALL. ENG SHUTDOWN. REPLACED ENG PER WIC M7100-002 / M7100-011. ENG RUN & OPS CHECK NORMAL.

Part: SEAT — FAILED (COCKPIT) · airframe 74,861 hrs · 18,241 cycles

CAPTAIN`S CHAIR WILL NOT LOCK IN POSITION, FOUND ON PUSH BACK. INSPECTED SEAT, ATTEMPTED TO ADJUST SAME - NO HELP. REMOVED CAPTAINS SEAT. OPS CK SAT OK FOR SRVC IAW MM 25-11-01.

Part: BLADE — BIRD STRIKE (NR 4 ENGINE) · airframe 74,739 hrs · 18,214 cycles

DURING POST FLT INSPECTION FOUND BIRD STRIKE DAMAGE TO NR 4 ENG. REMOVED AND REPLACED FAN BLADE SET PER WIC M 7111-001. REPLACED NOSE COWL PER WIC M 7220-001 ENG INSPECTION CARRIED OUT PER 72-00-00 NIL DEFECTS.

Part: CONNECTOR — LOOSE (COCKPIT) · airframe 74,540 hrs · 18,167 cycles

BOTH GREEN BAND & STAB TRIM GREEN BAND LIGHT CAME ON DURING TAXI BEFORE T/O. FOUND R586 LOOSE RESET R586, OPS CKS GOOD PER 27-48-00.

Part: START VALVE — FAILED (NR 4 ENGINE) · airframe 73,860 hrs · 18,018 cycles

AFTER PUSH BACK NR 4 ENG FAILED TO START WITH IGNITION SWITCH IN NR 1 OR NR 2 POS. REMOVED AND REPLACED NR 4 ENG START VALVE PER MM 80-11-01. NO LEAKS NOTED, ENG START NORMAL.

Part: SLIDE — DEPLOYED (COCKPIT) · airframe 73,670 hrs · 17,972 cycles

FLT DECK LT ESCAPE SLIDE DEPLOYED INADVERTENTLY. REPLACED SLIDE ASSY, REPLACED SLIDE GAS GENERATOR BOTTLE AND REPLACED DOOR (SLIDE) ASSIST BOTTLE.

Part: INDICATOR — FAULTY (HYD SYSTEM) · airframe 73,091 hrs · 17,847 cycles

NR 3 HYD SYS PRESSURE 2100 MAX. CONFIRMED INDICATOR AT FAULT, TRANSFERRED TO DMI 30942 (29-9).

Part: WIRE — CHAFED (PYLON) · airframe 72,842 hrs · 17,789 cycles

AFTER PUSHBACK NR 4 BLEED OVERHEATED LIGHT ILLUMINATED. FOUND CHAFED WIRE IN PYLON, REPAIRED PER MM 20-10-13, REPOSITION CLAMP & WIRE, CHECKED FOR AIRLEAKS - NONE FOUND

Part: DUCT — LEAKING (LT WING) · airframe 72,747 hrs · 17,768 cycles

PILOT REPORTED BY PHONE PATCH THAT LT WING HAD A BLEED AIR LEAK. FOUND BLOWN DUCTS ON INSPECTION. REPLACED DUCTS AND REPAIRED WING TO BODY FAIRING PNL. (191KL)

Part: SKIN — CORRODED (FUSELAGE) · airframe 72,670 hrs · 17,749 cycles

LEVEL 1 CORROSION AROUND FASTENERS HOLES COMMON TO BS 2220 FRAME INNER CHORD AND WEB BETWEEN STR 40R AND STR 42R PER REF /B/. FRAME STRAP REPLACED PER BOEING TELEX.

Part: PANEL — DELAMINATED (LT WING) · airframe 72,670 hrs · 17,749 cycles

LEFT WING TRAILING EDGE FIX PNL DELAMINATION. REPAIRED PER SRM 51-30-02 MM 51-30-02, 57-22-01.

Part: SKIN — CORRODED (FUSELAGE) · airframe 72,670 hrs · 17,749 cycles

BS 2200 S40R LEVEL 1 CORROSION. SRM 53-10-01 CLEANUP 51-10-02 REPROTECTED.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 72,670 hrs · 17,749 cycles

LEVEL 1 CORROSION SEAT TRACK STA 1046 RBL 99.0. REPAIRED PER SRM 53-10-05.

Part: PANEL — DELAMINATED (RT WING) · airframe 72,670 hrs · 17,749 cycles

RIGHT WING TRAILING EDGE FIXED PNL (DELAMINATION). REPAIRED PER SRM 51-30-02, MM 51-30-02, 57-22-01.

Part: SKIN — PUNCTURED (FUSELAGE) · airframe 72,670 hrs · 17,749 cycles

FUSELAGE SKIN PUNCTURE BS 2598 BETWEEN 525R / 526R. JACKING INCIDENT DURING C-CHECK AT SIN.

Part: SKIN — CORRODED (LT WING) · airframe 72,670 hrs · 17,749 cycles

LEVEL 1 CORROSION STA 1240 LBL 950 APPROX 3.0 X .5. REPAIR PER SRM 57-30-01 REWORK PER 8110-3 PAO-SIN-03-00017F, PAO - SIN - 0700013H.

Part: SPLICE — CRACKED (FUSELAGE) · airframe 72,670 hrs · 17,749 cycles

LT BS 1480 WEB SPLICE PLATE 16 INCH CRACK NR 18 HOLE. REPAIRED PER SRM 51-30-02.

Part: PANEL — DELAMINATED (VERICAL STAB) · airframe 72,670 hrs · 17,749 cycles

VERTICAL STAB AUX SPAR PANEL FIN STA 395 TO FIN 420 DELAMINATED. REPAIRED PER SRM 51-30-02 BOEING PAO SIN 03-00011M.

Part: PANEL — DELAMINATED (LT WING) · airframe 72,670 hrs · 17,749 cycles

LEFT WING OUTBOARD COVE LP PNL DELAMINATION INOP TRAILING EDGE. REPAIRED PER SRM 51-40-12.

Part: ENGINE — LEAKING (NR 4) · airframe 72,734 hrs · 17,851 cycles

ENGINE START NR 4 ENGINE HAS OIL LEAKING INTO TAILPIPE NR 4 FROM BEARING COMPARTMENT. REPLACED NR 4 ENGINE.

Part: DOOR FRAME — CRACKED (FUSELAGE) · airframe 72,670 hrs · 17,749 cycles

THE 5 L DOOR LWR FWD FRAME CUTOUT CRACKED. REPAIR PER SRM 51-30-02.

Part: BULKHEAD — GOUGED (NR 1 PYLON) · airframe 72,670 hrs · 17,749 cycles

NR 1 PYLON BULKHEAD NAC STA 222 AFT FACE DOUBLER AT WL 174 ON LT SIDE OF THE WEB PER REF 1. REPAIRED PER SRM 54-14-03. PAO - SIN 03-0014M, PAO - SIN 03-00015F.

Part: FRAME — CRACKED (FUSELAGE) · airframe 72,670 hrs · 17,749 cycles

FRAME CRACK STA 1660 S-12R. REPAIRED PER SRM 51-30-02.

Part: SKIN — PUNCTURED (FUSELAGE) · airframe 72,670 hrs · 17,749 cycles

FUSELAGE SKIN PUNCTURE BS 2598 BETWEEN S25R, S26R JACKING INCIDENT DURING C-CHECK AT SIN.

Part: FRAME — CRACKED (FUSELAGE) · airframe 72,670 hrs · 17,749 cycles

FRAME CRACK 1740 S13R. REPAIRED PER SRM 51-40-03.

Part: TORQUE TUBE — DEFORMED (LWR DOOR) · airframe 72,670 hrs · 17,749 cycles

THE 5 L DOOR BODY TORQUE TUBE LWR HINGE HALF FITTING DEFORMED. REMOVED AND REPLACED 51-30-02.

Part: FRAME — CRACKED (FUSELAGE) · airframe 72,670 hrs · 17,749 cycles

BS 200-S13L-S14L FRAME WEB CRACK. REPAIRED PER SRM 53-10-04 FIG 93.

Part: STRUCTURE — CRACKED (FUSELAGE) · airframe 72,670 hrs · 17,749 cycles

BS 1700 S13R - BS 1780 S13R CRACK. REPAIR PER SRM 53-10-04 FIG 88. TIME LIMIT REPAIR COI.

Part: SEAT TRACK — BROKEN (FUSELAGE) · airframe 72,670 hrs · 17,749 cycles

SEAT TRACK CROWN BROKEN OFF STA 340-360. REPAIRED PER SRM 53-10-05.

Part: SKIN — PUNCTURED (TE FLAP) · airframe 72,670 hrs · 17,749 cycles

LEFT WING INBOARD TRAILING EDGE MID FLAP UPPER PNL 577IT PUNCTURE. REPAIRED PER SRM 51-40-06 REV 96.

Part: FRAME — CORRODED (FUSELAGE) · airframe 72,670 hrs · 17,749 cycles

CORROSION BS 2200 S42L-S45L FRAME WEB. REPAIRED PER SRM 51-40-02.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 72,670 hrs · 17,749 cycles

FLOORBEAM TOP CHORD LWR SURFACE AT BS 2240 LBL 40 CORROSION. REPAIRED PER SRM 53-10 FIG 12.

Part: FRAME — CORRODED (FUSELAGE) · airframe 72,670 hrs · 17,749 cycles

LEVEL 1 CORROSION BS 220 S42R 545F FRAME WEB. REPAIRED PER SRM 51-40-02.

Part: FRAME — CRACKED (FUSELAGE) · airframe 72,670 hrs · 17,749 cycles

FRAME CRACK 1700 13R. REPAIRED FRAME PER SRM 51-40-03 FIG 2.

Part: SKIN — CORRODED (CENTER WING) · airframe 72,670 hrs · 17,749 cycles

LEVEL 1 CORROSION - WING CENTER SECTION UPPER SKIN REAR SPAR LBL 98.58. REPAIRED PER SRM 51-10-01.

Part: SKIN — DENTED (CARGO DOOR) · airframe 72,670 hrs · 17,749 cycles

AFT CARGO DOOR EXTERIOR SKIN - OIL CAN - 10 INCHES AFT AND 20 INCHES BELOW LATCH. REPAIR PER 52-00-03 FIG 4.

Part: SKIN — GOUGED (CARGO DOOR) · airframe 72,670 hrs · 17,749 cycles

AFT CARGO DOOR DEEP GOUGE 12 INCHES BELOW MASTER LATCH HANDLE. REPAIR SRM 51-40-01.

Part: SEAT TRACK — CRACKED (FUSELAGE) · airframe 72,670 hrs · 17,749 cycles

FWD CARGO AT BS 680 RBL 45.5 SEAT TRACK CRACK / TOP CHORD PUNCTURE. SEAT TRACK REPAIR SRM 53-10-05 FI 5 FLOOR STRUCTURE 51-40-03 FIG 1.

Part: SKIN — CRACKED (FUSELAGE) · airframe 72,670 hrs · 17,749 cycles

B-STA 460 ABOVE IL DOOR CUTOUT CENTER 2.5 INCH CRACK. REPAIRED PER SRM 53-10-04 5B 747 53A 2396.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 72,670 hrs · 17,749 cycles

SEAT TRACK STA 970 LBL 98.58 LEVEL 1 CORROSION. REPAIRED SRM 53-10-05 1A.

Part: SEAT TRACK — CORRODED (FUSELAEG) · airframe 72,670 hrs · 17,749 cycles

SEAT TRACK STA 1046 RBL 99.0 LEVEL 1 CORROSION. REPAIR PER SRM 53-10-05 FIG 34.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 72,670 hrs · 17,749 cycles

MAIN DECK SEAT TRACK FLANGE - LEVEL 1 CORROSION S1800 LBL 67.01. REPAIR PER SRM 53-10-05 FIG 1A.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 72,670 hrs · 17,749 cycles

SEAT TRACK STA 360 TO STA 420 LBL 91.045 LEVEL 1 CORROSION. REMOVED AND REPLACED TRACK PER SRM 53-10-05 FIG 1.

Part: SUPPORT — CORRODED (FWD CARGO BAY) · airframe 72,670 hrs · 17,749 cycles

LEVEL 1 CORROSION FWD CARGO DIVIDED / CEILING SUPPORT. REPAIR PER SRM 51-40-03.

Part: SKIN — CRACKED (ELEVATOR) · airframe 72,670 hrs · 17,749 cycles

RIGHT OUTBOARD ELEVATOR SKIN CRACK STA 360. REPAIR AS PER SRM 51-40-01.

Part: SKIN — CRACKED (FUSELAGE) · airframe 72,670 hrs · 17,749 cycles

SKIN BS 1480 CRACKED NR 9, 11 L/E, NR 11 R/S. REPAIRED PER SB 747 53A 2390 R1 CONTINUE REINSPECTION 1600 FLT CYCLES COI 920.

Part: ENGINE — FAILED (NR 2) · airframe 72,157 hrs · 17,645 cycles

AT TOP OF CLIMB 37.0, NR 2 ENG FAILED WITH NO APPARENT CAUSE. TRIED RAPID RELIGHT, NO START. CHECKED ENG INTAKE AND EXHAUST AREA, OK. PERFORMED ENG OIL FILTER AND ALL MAGNETIC PLUGS, OK PER MM 72-00-00. ALSO HI-PWR CHECKS OK BY CREW IAW GMM 6-18-3. PERFORMED FUEL PUMP PRESS, 700 PSI, WITHIN LIMITS.

Part: WEB — CRACKED (NR 2 PYLON) · airframe 70,235 hrs · 17,248 cycles

FOUR CRACKS FOUND ON NR 2 ENG PYLON, AFT ENGINE MOUNT BULKHEAD FRAME, VERTICAL WEB STATION 221.9. (1. CRACK ON FRONT OUTBOARD WEB, 3 INCHES LONG. 2. CRACK ON FRONT OUTBOARD WEB, 1 INCH LONG. 3. CRACK ON FRONT INBOARD WEB, 3.5 INCH LONG. 4. CRACK ON FRONT OUTBOARD WEB, 3 INCHES LONG). REPAIRED BY INSTALLING WEB FILLERS, WEB DOUBLERS AND ANGLE CORDS ON LEFT AND RIGHT FWD FRAME HALVES IAW PAOE020523, DRAWING 65B07582-SHT 8, SB747-54-A2202 & SB747-54-2065.

Part: WEB — CRACKED (NR 3 PYLON) · airframe 70,235 hrs · 17,248 cycles

THREE CRACKS FOUND ON NR 3 ENG PYLON, AFT ENGINE MOUNT BULKHEAD FRAME, VERTICAL WEB STATION 221.9. (1. CRACK ON FRONT OF OUTBOARD WEB, 2 INCHES LONG. 2. CRACK ON FRONT OUTBOARD WEB, 1 INCH LONG. 3. CRACK ON FRONT OUTBOARD WEB, 3 INCHES LONG). BULKHEAD LOWER ASSY REPAIRED BY INSTALLING WEB FILLERS, WEB DOUBLERS AND ANGLE CORDS ON LEFT AND RIGHT FRAME HALVES IAW PAOE020524, DRAWING 65B07582, SHT 8, SB747-54-A2202 & SB747-54-2065.

Part: WEB — CRACKED (NR 2 PYLON) · airframe 70,235 hrs · 17,248 cycles

CRACK 8 INCHES LONG FOUND NR 2 ENG PYLON FORWARD LOWER SPAR FLOOR WEB AT STA 270, MID SPAR (PANEL 452CL). COMPLETED REPAIRS IAW BOEING REPAIR SCHEME DWGS PAO-LGB-02-00056F, 55F, 54H, 53F & 52H.

Part: MOUNT — WORN (NR 2 ENGINE) · airframe 70,235 hrs · 17,248 cycles

NR 2 ENG AFT UPPER ENG MOUNT BENT ON ALIGNMENT HOLE, MOUNT ASSY WORN. REMOVED & REPLACED AFT ENG MOUNT IAW MM 71-21-03.

Part: MOUNT — CORRODED (NR 2 ENGINE) · airframe 70,235 hrs · 17,248 cycles

LEVEL 1 CORROSION FOUND ON ENG UPPER REAR MOUNT BULKHEAD FITTING LOWER LUGS WHILE REMOVING NR 2 ENG REAR UPPER MOUNT FOR REPAIRS. ACCOMPLISHED SB 747-54A2200. COATED MOUNT W/ BMS 14-4, TYPE 2. COATING IAW 747-A2200 SERMATECH ENGINEERING BULLETIN 249.

Part: WEB — CRACKED (#3 PYLON) · airframe 70,235 hrs · 17,248 cycles

CRACK 3.5" LONG FOUND #3 PYLON WEB BETWEEN RIVET HOLES BELOW STIFFNER (STA 211.42, MID SPAR WEB). DOUBLER REPAIR FABRICATED IAW SRM 54-14-03, PG 20. THE RIVETS WERE REMOVED PLUS FURTHER 3 EITHER SIDE OF CRACK. 2 OF FURTHER ROWS OF FASTENERS PITCHED FORWARD & REAR STIFFNER INCORPORATED DOUBLER ATTACHED USING HI-LOK BOLTS. DOUBLER MFG'D FROM 2024-T3 & TREATED IAW MM 51-10-02 & REPAIR SEALED IAW MM 51-31-00.

Part: GROUND WIRE — BROKEN (HYD SYSTEM) · airframe 70,235 hrs · 17,248 cycles

NR 2 ENGINE PYLON HYD S/O VALVE GROUND WIRES, PYLON STA 270, BROKEN. REPAIRED GROUND WIRES IAW SWP 20-11-15.

Part: SKIN — CRACKED (FUSELAGE) · airframe 70,235 hrs · 17,248 cycles

FOUND 1" CRACK IN LOWER SKIN FUSELAGE AT STA 2390, LBL70. FABRICATED REPAIR PLATE & DRILLED FASTENER HOLES. APPLIED ALODINE TO CUT EDGES OF REPAIR PLATE & REPAIR SKIN AREA. PRIMED FAYING SURFACES. INSTALLED REPAIR PLATE W/ FASTENERS. USED BMS 5-95 TO SEAL FAYING SURFACES & APPLIED TRIM CO'S IAW SRM 53-30-02/03.

Part: BEARING — FAILED (#2 APU GENERATOR) · airframe 70,136 hrs · 17,226 cycles

#2 APU GENERATOR BEARING FAILURE LIGHT ILLUMINATED & GRND CREW REPORTED SMOKE EMANATING FROM APU. FIRE HANDLE PULLED & BOTTLE DISCHARGED AS A PRECAUTION. VISUAL INSPECTION OF APU COMPARTMENT BY MX & F/E SHOWED DAMAGE ONLY TO THE #2 GENERATOR. NO FIRE OR DAMAGE TO OTHER COMPONENTS OR STRUCTURES. DEACTIVATED APU & DEFERRED PER MEL 49-01, DMI #29098. MX XTL LGB NOTIFIED & PLACARDS INSTALLED.

Part: SWITCH — OUT OF ADJUST (SPEED BRAKE) · airframe 69,683 hrs · 17,132 cycles

TAKEOFF WARNING HORN WHEN POWER IS ADVANCED. ADJUSTED SPEED BRAKE DOWN SWITCH IAW 31-26-05. OPS CHECK NORMAL.

Part: TRANSMITTER — FAULTY (NR 3 ENGINE) · airframe 69,496 hrs · 17,096 cycles

ON APPLICATION OF PWR AT T/O NR 3 ENG NOT ACCELERATING TO 1.58 EPR SETTING. T/O DISCONTINUED. REMOVED AND REPLACED TT2 SENSOR PER 73-21-04. LEAK CKS GOOD BUT NO HELP. ON ENG RUN IDLE TO 80 PERCENT, N1 TOOK 4.5 SECS, EPR LAGGED AND STABILIZED - TOOK 10 SECS FROM 80 PERCENT N1 TO IDLE. N1 & N2 DROPPED W/IN TIME BUT EPR WAS SLOW TO COME DOWN. STAYED AT 1.30 W/ N1 & N2 AT IDLE SPEEDS. EPR PROBLEM SUSPECTED. SWAPPED EPR GAUGES, NO HELP. REMOVED AND REPLACED EPR TRANSMITTER PER 77-11-02. ALL PARAMETERS W/IN RANGE PER 71-00-00 TEST 9.

Part: CONTROL UNIT — OUT OF RIG (NR 3 ENGINE) · airframe 69,496 hrs · 17,096 cycles

NR 3 ENG WOULD NOT ACHIEVE T/O THRUST. 1.58 MAX PWR WAS APPLIED, THRUST LEVER WAS MOVED TO FIREWALL THRUST W/ MAX EPR OF 1.38. OTHER PARAMETERS NORMAL WHEN ASSOCIATED W/ & EPR SETTING OF 1.38 ENG RUN TO MAX POWER FOR OPS CK INTO WIND (250/11). ENG SLOW TO RESPOND TO THROTTLE MOVEMENT. MAX EPR WAS 1.40. RIGGED NR 3 ENG THRUST LEVER CONTROLS IAW MM 76-11-00, SECTION 4. OPS CK OK ON ENG RUN, IAW MM 71-00-00. ALL ENG PARAMETERS NORMAL ON GROUND RUN.

Part: SWITCH — MALFUNCTIONED (#3 ENGINE) · airframe 69,447 hrs · 17,083 cycles

#3 ENGINE OIL PRESSURE LITE ON PILOT'S FWD ANNUNCIATOR PANEL ILLUMINATED. ALT PROCEDURES CHECK LIST ACCOMPLISHED - OIL PRESS, QUANTITY NORMAL - FILTER BYPASS LIGHT EXTINGUISHED. REMOVED & REPLACED LOW OIL PRESS SWITCH PER MM 79-33-01. PERFORMED WINDMILL INSPECTION PER 72-00-00. OIL STRAINED & CHIPS CLEANED . REINSTALLED. LEAK CHECK GOOD. OK FOR SERVICE.

Part: SEAL — LEAKING (#4 ENGINE) · airframe 69,358 hrs · 17,064 cycles

AT APPROX. 15 MIN. INTO CRUISE (FL 33.0), #4 OIL QTY RAPIDLY DROPPED TO ZERO. FWD CAUTION PANEL LOW OIL PRESSURE LIGHT CAME ON. PRECAUTIONARY ENG SHUTDOWN ACCOMPLISHED PER ABNORMAL PROCEDURES. UPON INSPECTION FOUND GEARBOX N2 FULL OF OIL W/ TANK EMPTY.REPAIRED BY CHANGING PUMP, OIL TANK, CDS & STARTER SEALS. CHANGED PRESSURE RELIEF VALVE AS A PRECAUTION. NIL LEAKS ON RUN UP. OIL QTY MAINTAINED W/ NO EVIDENCE OF LOSS. A/C RELEASED TO SERVICE.

Part: BEARING — WORN (L/BODY GEAR) · airframe 69,357 hrs · 17,063 cycles

L/BODY GEAR STRUT DOOR LINK ROD ATTACH FITING BEARING WORN. REMOVED & REPLACED FITTING/BEARING PER MM 32-14-06.

Part: FLAP — DELAMINATED (LT WING) · airframe 69,357 hrs · 17,063 cycles

LEFT INBOARD T/E FLAP HAS 4 AREA OF SLIGHT DELAMINATION. REPAIRED PER SRM 20-11-14.

Part: RETAINER — TORN (NR 1 PYLON) · airframe 69,357 hrs · 17,063 cycles

NR 1 ENGINE PYLON SAILBOAT DOOR, INBOARD SIDE, LOWER FWD END, HAS A 6 INCH RIP IN SEAL RETAINER. REPAIRED PER SRM 51-40-00.

Part: DOUBLER — TORN

#2 PYLON INBD SIDE, AFT END, ABOVE AFT MOUNT, HAS A 1" RIP IN DOUBLER. REPAIRED PER SRM 54-12-01 & SRM 51-40-00.

Part: TRANSFORMER — MALFUNCTIONED (COCKPIT) · airframe 68,833 hrs · 16,956 cycles

SMELLED SMOKE IN COCKPIT. FOUND PILOT'S BACKGROUND LIGHT C/B OPEN & MAIN PANEL BACKGROUND LIGHT CONTROL KNOB VERY HOT. (NEXT TO THUNDERSTORM LIGHT SWITCH). SMOKE WENT AWAY. REPLACED TRANSFORMER. OPS NORMAL.

Part: SKIN — BULGED (MIAN CARGO DOOR) · airframe 68,358 hrs · 16,846 cycles

MAIN DECK CARGO DOOR EXTERNAL SKIN BULGING AT LATCH ACCESS PANEL CUT OUT (2ND FROM FWD). DAMAGED AREA TRIMMED OUT AND A FILLER AND STRAP INSTALLED PER BOEING TELEX SIA-SIN -01-00947H FAA FORM 8110-3 DATED JUNE 21.

Part: STRUCTURE — CORRODED (FUSELAGE) · airframe 68,358 hrs · 16,846 cycles

CORROSION FOUND BEHIND ATTACHMENT FLANGE OF WING TO BODY FAIRING SUPPORT RIB AT STA 1480 LBL 75 TO LBL 90. REMOVED CHORD AND AFFECTED AREA PER IAW SRM 53-10-01 AND SRM 51-30-00.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 68,358 hrs · 16,846 cycles

CORROSION FOUND ON MAIN DECK FLOORBEAM STA 2240 RBL 54 TOP OF CHORD. REPAIR CARRIED OUT AS PER SRM 53-11-23 & SRM 51-40-04.

Part: SUPPORT — CORRODED (FUSELAGE) · airframe 68,358 hrs · 16,846 cycles

LEVEL 1 CORROSION AT STA 500 - 520 LBL 37 FLOORBEAM SUPPORT STRUCTURE SPLICE INTERCOSTAL. REPAIR CARRIED OUT AS PER SRM 53-10-05.

Part: INTERCOSTAL — CORRODED (FUSELAGE)

LEVEL 1 CORROSION - BULK CARGO FLOOR INTERCOSTAL AT STA 2040 RBL 23 FOUND CORRODED. CORROSION REMOVED AND INSPECTED. FOUND WITHIN LIMITS AS PER SRM 51-10-01 & SRM 53-10-01. BLENDED SURFACES, REPROTECTED AND REPLACED ANCHOR NUT AS PER SRM 51-10-02 & SRM 51-30-02.

Part: KEELBEAM

LEVEL 1 CORROSION - KEEL BEAM LOWER PANEL SUPPORT BEAM CORRODED AT STA 1391 LBL 15 TO RBL 15. BLENDED OUT CORROSION AS PER 53-10-01. CLEANED OUT DEPTH W/IN LIMIT OF 20% THICKNESS. RE-PROTECTED W/ ALODINE & PRIMER AS PER SRM 51-10-02. DIMENSIONS ARE MATERIAL THICKNESS 0.097", MAX ALLOWED DEPTH 0.019", CORROSION REMOVED 0.014".

Part: FLOORBEAM — CORRODED (FUSELAGE)

LEVEL 1 CORROSION, FOUND MAIN DECK FLOORBEAM CORROSION ON TOP FLANGE AT STA 2260 RBL 41. REPAIR CARRIED OUT AS PER 53-11-23 & SRM 51-40-04.

Part: SUPPORT — CORRODED (FUSELAGE) · airframe 68,358 hrs · 16,846 cycles

CORROSION FOUND ON KEEL BEAM LOWER PANEL SUPPORT STRUCTURE AT RBL 15 FROM STA 1391 TO STA 1437. BLENDED OUT CORROSION AS PER SRM 51-10-01.

Part: NUT — CORRODED (FUSELAGE) · airframe 68,358 hrs · 26,846 cycles

LEVEL 1 CORROSION FOUND ON AIRCON PANEL SUPPORT STRUCTURE AT LOWER SURFACE AT RBL 53 STA 1170 & 1152. REMOVED AND REPLACED CORRODED ANCHOR NUT, BLEND OUT CORROSION AS PER SRM 53-10-01.

Part: THRESHOLD — CORRODED (FUSELAGE) · airframe 68,358 hrs · 16,846 cycles

CORROSION FOUND AT STA 460 - 480 NR 1 RT FWD ENTRY DOOR THRESHOLD PLATE UNDERNEATH FLOORBEAM. REPAIR CARRIED OUT AS PER SRM 51-40-02.

Part: KEELBEAM

LEVEL 1 CORROSION - KEEL BEAM LOWER PANEL SUPPORT STRUCTURE CORRODED AT RBL 15 FROM STA 1273 TO 1352. INSPECT AREA AS PER SRM 51-10-01. BLENDED OUT CORROSION AS PER 53-10-01 FOUND W/IN LIMIT OF 20% THICK. AREA RE-PROTECTED W/ ALODINE & PRIMER AS PER SRM 51-10-02. MATERIAL THICKNESS 0.095", MAX ALLOWED DEPTH 0.019", CORROSION REMOVED 0.009".

Part: INTERCOSTAL — CORRODED (FUSELAGE)

LEVEL 1 CORROSION - BULK CARGO FLOOR INTERCOSTAL AT STA 2040 LBL 23 FOUND CORRODED. CORROSION REMOVED AND INSPECTED. FOUND WITHIN LIMITS AS PER SRM 51-010-01 & SRM 53-10-01. BLENDED SURFACES, RE-PROTECTED AND REPLACED ANCHOR NUT AS PER SRM 51-10-02 & SRM 51-30-02.

Part: BALANCE WEIGHT — CORRODED (ELEVATOR) · airframe 68,358 hrs · 16,846 cycles

CORROSION FOUND ON LEFT O/B ELEVATOR BALANCE WEIGHT. NUT BLAST PER 747 SL-55-07 FINISH PER 747-32-55-07.

Part: SKIN — DAMAGED (BS 1759)

FUSELAGE DAMAGE FOUND AT FWD OF AFT CARGO DOOR TO EXTERIOR SKIN AT BS 1759 STRINGER 36 TO 37 RIGHT. CUT OUT DAMAGED AREA AND REPAIRED PER SRM 53-30-03 FIG 1.

Part: DUCT — DAMAGED (RT WING)

RIGHT WING LEADING EDGE OVERHEAT LIGHT ON DURING CLIMB. USED ALTERNATE PROCEDURES PG 6-14-2. LIGHT OUT WITHIN 5 MIN. FOUND DUCT RUPTURE TO S DUCT BETWEEN L/E DUCT AND NR 4 RT KRUEGER FLAP PDU. REMOVED DAMAGED DUCT AND INSTALLED COVER PLATES. NO LEAKS PER MM 27-81-00.

Part: BATTERY PACK — DISCHARGED (CABIN)

DURING COCKPIT CHECK, FOUND UPPER DECK EMERGENCY LIGHT BATTERY PACK INOP. REMOVED AND REPLACED UPPER DECK BATTERY PACK PER MM 33-51-00.

Part: INTERCOSTAL — CRACKED (BS 380-400)

INTERCOSTAL WEB CRACKED BETWEEN BS 380 TO 400R AT STRINGER 15R. REPAIRED PER SRM 51-40-03.

Part: PANEL — DELAMINATED (LT WING)

NR 2 KNEE CAP PANEL LEFT WING DELAMINATED ON INBOARD TRAILING EDGE CORNER. REPAIRED PER SRM 51-40-15.

Part: CLIP — CRACKED (BS 520)

UPPER DECK STA 502L AT S-9R CLIP IS CRACKED. REPAIRED PER SRM 51-10-02 AND 51-30-02.

Part: FRAME — CRACKED (BS 520)

UPPER DECK STA 520 RIGHT SIDE FRAME IS CRACKED FROM STR 8R TO STR 10A. REPAIRED PER SRM 53-10-04.

Part: DOOR — CRACKED (LT MLG)

LEFT WING GEAR UPPER STRUT DOOR CRACKED AT OUTBOARD TRAILING EDGE CORNER. REPAIRED PER SRM 51-40-09.

Part: BATTERY PACK — DISCHARGED (BS 400)

RIGHT CREW DOOR EMERGENCY LIGHTS INOP. REMOVED AND REPLACED BATTERY PACK PER MM 33-51-00, OPS CHECK OK.

Part: CADC — MALFUNCTIONED (COCKPIT)

A 400 FT SPLIT IN ALTIMETERS AT 39,000 FT. REPLACED NR 1 CENTRAL AIR DATA COMPUTER PER M/M 34-11-00.

Part: INU — FAILED (NR 1/2)

NR 1 INS FAILED AT LIFTOFF. NR 2 INS RED WING LIGHT ILLUMINATED AT 2000 FT AGL AFTER TAKEOFF. JETTISONED FUEL TO LAND UNDER MAX LNDG WEIGHT. REMOVED AND REPLACED NR 1 INU IAW BACOMM34-41-03. REMOVED AND REPLACED NR 2 INU IAW BACOMM 34-41-03. OPS CK OK.

Part: SKIN — DENTED (NR 8 SPOILER)

NR 8 SPOILER HAS DENTS IN UPPER SURFACE. CUTOUT DAMAGED AREA, APPLIED FILLER AND DOUBLER AND PAINTED AREA PER SRM 51-40-06 AND 51-24-11.

Part: SKIN — DAMAGED (RT AILERON)

RT OUTBD AILERON LOWER T/E HAS DAMAGE AT CONDUCTIVE STRIP. REMOVED DAMAGED SECTION OF CONDUCTIVE STRIP AND STATIC WICK. REPAIRED CONDUCTIVE STRIP, REPLACED WICK. OHM CHECKED PER MM 57-51-03 AND 23-61-00.

Part: SKIN — DAMAGED (LT AILERON)

LT OUTBD LWR T/E AILERON HAS DAMAGE. REPAIRED AILERON T/E IAW MM 51-40-15. PAINTED REPAIRED AREA IAW MM 51-24-11.

Part: PANEL — CRACKED (LT TE MIDFLAP)

LT MIDFLAP COVE LIP PANEL INBD HAS CRACK. CLEANED/SMOOTHED DAMAGED AREA. STOP DRILLED CRACK, APPLIED FIBERGLASS OVERLAY AND PAINTED PER SRM 51-40-15 AND 51-24-11.

Part: FLOOR PANELS — DAMAGED (CABIN)

MAIN CABIN FLOOR PANELS UNDER UPPER DECK ACCESS LADDER INBD LEG DAMAGED DUE TO LADDER RESTING ON THE PANEL. FABRICATED AND INSTALLED NEW FLOOR PANEL PER SRM 51-30-02 AND 51-0-01.

Part: JAMB — GOUGED (CORGO DOORWAY)

FWD LOWER CARGO DOOR JAMB AFT LOWER SIDE LATCH PIN HOUSING IS GOUGED. BLENDED OUT GOUGE. NDT HFEC FOR CRACKS, NONE FOUND. TREATED AND PRIMED PER SRM 53-40-01 AND 51-00-02. NDT MANUAL 51-00-00.

Part: PANEL — CORRODED (LAV SERVICE)

LAV SERVICE PANEL AREA HAS LIGHT CORROSION AND BARE METAL. REMOVED CORROSION, CLEANED, TREATED AND PRIMED PER SRM 51-10-01 AND 51-10-02.

Part: SLEEVE — DAMAGED (NR 1 ENGINE TR)

NR 1 ENGINE FAN REVERSER SLEEVE DAMAGED AT THE 5 O'CLOCK POSITION. REPAIRED AS PER SRM 54-30-03.

Part: PANEL — DELAMINATED (LT WING)

CRACK AND DELAMINATION LEFT WING LEADING EDGE UPPER PANEL BY NR 12 LEADING EDGE FLAP OUTBOARD SIDE. REPAIRED PER POLAR MA 5780-01:01.

Part: SKIN — DELAMINATED (RT TE FLAP)

DELAMINATED O/B END AT THE LEADING EDGE OF THE RT INBD TRAILING EDGE FLAP. APPLIED FIBERGLASS OVERLAYS PER SRM 51-40-15.

Part: R-RAIL — CRACKED (NR 2 ENGINE)

CRACK (RADIAL OD) IN NR 2 ENG R-RAIL AT FASTENER HOLE AT 9 O'CLOCK POSITION. WELDED AND STRESS RELIEVED PER PW MM 72-51-01.

Part: SKIN — CRACKED (NR 3 PYLON)

CRACKED I/B AFT END OF PYLON EXTERNAL SKIN AT FASTENER HOLE. CUT OUT DAMAGE, FABRICATED AND INSTALLED REPAIR DOUBLER PER SRM 54-50-03.

Part: STOP FITTING — DAMAGED (CARGO DOOR)

DAMAGED LOWER AFT CARGO DOOR, FWD DOOR STOP TO A/C FRAME, FITTING OUT OF FRAME. REPLACED FWD LWR DOOR STOP FITTING PER MM 52-34-11.

Part: FITTING — CRACKED (BS 1810)

CRACKED AFT CARGO DOOR FRAME SUPPORT FITTING AT STA 1810. REMOVED DAMAGED SUPPORT FITTING, FABRICATED AND INSTALLED REPLACEMENT FITTING AS PER SRM 51-10-01.

Part: DOORFRAME — CRACKED (BS 1810)

CRACKED AFT CARGO DOOR FRAME WEB AT STA 1810. REMOVED DAMAGED SECTION, FABRICATED AND INSTALLED REPAIR FILLER AND DOUBLERS AS PER SRM 51-40-02.

Part: FAIRING — DAMAGED (NR 6 TE FLAP)

DAMAGE NR 6 FLAP CANOE FAIRING I/B SIDE AFT SECTION DUE BIRD STRIKE. REMOVED DAMAGED SECTION, POTTED AND APPLIED OVERLAY REPAIR PER SRM 51-40-09.

Part: PANEL — DAMAGED (NR 16 LE FLAP)

ON PREFLIGHT, FOUND DAMAGE TO NR 16 LEADING EDGE FLAP OUTER PANEL. REPLACED OUTER PANEL PER BOEING M/M 27-81-01 OPERATIONAL AND RIG CHECK GOOD.

Part: PRECOOLER — CRACKED (NR 3 ENGINE)

NR 3 ENGINE PRECOOLER HAS CRACK AT LOWER FWD 'V' BAND CLAMP. WELDED IAW MM 36-12-01, BAC 5975 USING 625 TIG ROD.

Part: COOLING MANIFOLD — CRACKED (NR 3 ENGINE)

NR 3 ENGINE - HPT COOLING MANIFOLD ABOVE AND AFT OF ENGINE BLEED AIR PRECOOLER 11 O'CLOCK POSITION, CRACKED. WELDED IAW MM 36-12-01, BAC 5975 USING 3475.5 TIG ROD.

Part: SLEEVE — DAMAGED (NR 4 ENGINE)

NR 4 ENGINE TRANSLATING SLEEVE IS DAMAGED ON BOTTOM AT 6 O'CLOCK POSITION. REMOVED DAMAGED AREA APPLIED FILLER AND DOUBLER AND REPAIRED IAW BOEING SRM 51-40-06. ALSO, TREATED AREA IAW MM 51-24-11.

Part: BOLT — OUT OF ADJUST (L1 DOOR)

L1 DOOR TOP HINGE ARM FUSELAGE ATTACH POINT TOO LONG AND EXTERNAL SKIN DAMAGED TWO PLACES. REPAIRED BOLT BY ADDING WASHER IAW BOEING SRM 51-30-02 AND BLENDED DAMAGED SKIN IAW BOEING SRM 51-10-01.

Part: SKIN — CORRODED (FUSELAGE)

LEVEL 1 CORROSION AROUND FORWARD MIDDLE LOW RANGE RADIO ALTIMETER ANTENNA. REMOVED CORRODED FLAME SPRAY AND APPLIED FIBERGLASS OVERLAYS AND APPLIED CONDUCTIVE COATING AND TREATED PER BOEING SRM 51-40-11, 51-24-03 AND 51-24-11.

Part: SKIN — CORRODED (FUSELAGE)

LEVEL 1 CORROSION, ON BELLY SKIN JUST AFT OF CENTER E/E ACCESS DOOR. REMOVED CORRODED FLAME SPRAY AND APPLIED FIBERGLASS OVERLAYS AND APPLIED CONDUCTIVE COATING AND TREATED PER BOEING SRM 51-40-11, 51-24-03 AND 51-24-11.

Part: PANELS — CORRODED (FUSELAGE)

LEVEL 1 CORROSION, 3 KEEL BEAM PANELS BETWEEN BODY GEAR DOORS HAVE BARE METAL AND LIGHT SURFACE CORROSION. REMOVED CORROSION ORIGINAL MATERIAL .040 LOW POINT .037, TREATED AND PRIMED AREA PER BOEING SRM 51-10-06, 51-10-02 AND 51-24-11.

Part: FAN BLADE — BIRD STRIKE (NR 2 ENGINE)

ONE FAN BLADE BENT BEYOND LIMITS DUE TO BIRD STRIKE. REPLACED BLADE AND MATCHING BLADE PER M/M 72-31-02.

Part: SKIRT — DAMAGE (RT PYLON)

NR 1 PYLON I/B SIDE, PYLON SKIRT AFT END DAMAGED. CLEANED UP DAMAGED AREA, FABRICATED REPAIR DOUBLER, FILLER AND INSTALLED THE SAME PER BOEING SRM 54-34-03.

Part: SKIRT — DAMAGED (NR 1 PYLON)

DAMAGE NR 1 PYLON INBOARD SIDE SKIRT AFT END. CLEANED UP DAMAGED AREA FABRICATED REPAIR DOUBLER AND FILLER AND INSTALLED PER BOEING SRM 54-34-03.

Part: COWL BRACKET — CRACKED (NR 1 ENGINE)

CRACKED BRACKET NR 1 ENGING OUTBOARD COWL AFT CENTER. REPAIRED PER BOEING SRM 51-10-00.

Part: COWL — DELAMINATED (NR 3 ENGINE)

DELAMINATED NR 3 ENGINE INBOARD FAN COWL CORNER. REPAIRED PER BOEING SRM 51-40-06.

Part: SEAT TRACK — CRACKED (COCKPIT)

CRACKED AFT OUTBOARD CAPTAINS SEAT TRACK. REPLACED PER BOEING MAINTENANCE MANUAL 25-11-01.

Part: CABLE GUARD — BROKEN (NLG STEERING)

BROKEN CABLE GUARD IN THE NOSE GEAR STEERING SYSTEM. REPLACED GUARD PER BAC MM 32-51-00.

Part: SKIN — BENT (NR 3 PYLON)

BENT SKIN NR 3 PYLON ABOVE EXHAUST FLANGE. REPAIRED PER BOEING SRM 51-40-01.

Part: HINGE — BROKEN (NR 1 ENGINE)

BROKEN HINGE NR 1 ENGINE CORE COWL AFT HINGE. REPLACED HINGE PER BOEING SRM 51-10-01.

Part: COWL — DELAMINATED (NR 1 ENGINE)

DELAMINATION NR 1 ENGINE INBOARD CORE COWL. REPAIRED PER BOEING SRM 51-30-02.

Part: BRACKET — CRACKED (BS 300)

CRACKED ATTACH POINTS BS 300 LEFT NOSE WHEEL WELL TUNNEL AREA 3RD AND 4TH INTERCOSTAL FROM FLOOR. FABRICATED AND REPLACED CLIPS PER BOEING SRM 51-30-02.

Part: BOOST PUMP — FAILED TEST (NR 2)

RESISTANCE CHECK REQUIRED BY AD 97-0317 FAILED ON NR 2 MAIN AFT FUEL BOOST PUMP. REPLACED FUEL BOOST PUMP PER BAC MM 28-31-01.

Part: STRAP — CORRODED (BS 2220)

LEVEL 1 CORROSION ON FRAME REINFORCEMENT STRAP AT BS 2220. REMOVED CORROSION PER BAC SRM 51-10-01.

Part: JETTISON PUMP — FAILED TEST (NR 2)

RESISTANCE CHECK REQUIRED BY AD 97-0317 FAILED ON NR 2 MAIN OUTBOARD FUEL JETTISON PUMP. REPLACED FUEL JETTISON PUMP PER BAC MM 28-31-01.

Part: REINFORCEMENT — CRACKED (BS 2200)

LEVEL 2 CORROSION AND CRACK ON FRAME REINFORCEMENT AT BS 2200, S38R. REMOVED CORROSION AND REPLACED REINFORCEMENT PER BAC SRM 51-10-01.

Part: STOP BRACKET — CRACKED (RT MLG DOOR)

CRACKED STOP BRACKET ON THE RIGHT BODY GEAR OUTBOARD DOOR. FABRICATED AND INSTALLED NEW BRACKET PER BAC SRM 51-10-01.

Part: COWL — BENT (NR 2 ENGINE)

BENT CORNER NR 2 ENGINE FAN COWL. REPAIRED PER BOEING SRM 51-10-02.

Part: COWL DOUBLER — CRACKED (NR 3 ENGINE)

CRACKED DOUBLER NR 3 ENGINE INBOARD CORE COWL AFT UPPER. REMOVED AND REPLACED DOUBLER PER BOEING SRM 51-30-02.

Part: COWLING — TORN (NR 1 ENGINE)

SKIN TORN AT #1 ENGINE OUTBOARD CORE COWL #3 LATCH AREA. REPAIRED PER BOEING SRM 54-36-07.

Part: DOORS — CRACKED (LT /RT MLG)

CRACKED RIGHT AND LEFT BODY GEAR FIXED DOORS. REMOVED DAMAGED AREAS AND APPLIED FIBERGLASS OVERLAY REPAIRS PER BAC SRM 51-40-09.

Part: EXHAUST NOZZLE — TORN (NR 1 ENGINE)

BENT AND TORN EXHAUST NOZZLE AT 12 O'CLOCK POSITION LEFT AND RIGHT SIDES. REPAIRED PER BOEING SRM 51-30-03.

Part: ANGLE — CRACKED (BS 300)

CRACKS AT FIVE RIVETS ON ANGLE CAP IN LEFT NOSE TUNNEL AREA AT BS 300. REPAIRED PER ENGINEERING AUTHORIZATION 47-5311-15-A0203.

Part: FUEL BOOST PUMP — FAILED (NR 2)

RESISTANCE CHECK REQUIRED BY AD 97-0317 FAILED ON NR 2 MAIN FORWARD BOOST PUMP. REPLACED FUEL BOOST PUMP PER BAC MM 28-31-01.

Part: SPRING — BENT (RADOME)

BENT SPRING AT ATTACH POINT INSIDE RADOME ASSY. REPAIRED PER BAC MM 20-11-32.

Part: EXHAUST CASE — CRACKED (NR 3 ENGINE)

CRACK #3 ENGINE R RAIL 2 O'CLOCK POSITION. REPAIRED PER PRATT AND WHITNEY MANUAL 72-53-01 REPAIR 14.

Part: ACCESS PANEL — CRACKED (NR 2 ENGINE)

3 CRACKS NR 2 ENGINE INBOARD CORE COWL EXTERNAL ACCESS PANEL. WELD REPAIRED PER BOEING PROCESS BAC5975905 AND SRM 51-00-00.

Part: FRAME — CRACKED (BS 320)

CRACK AT FIRST RIVET HOLE TO OUTBOARD ATTACH POINT ON CIRCUMFERENTIAL FRAME IN LEFT NOSE TUNNEL AREA AT BS 320. REPAIRED PER ENGINEERING AUTHORIZATION 47-5311-15-A0203.

Part: ANGLE — CORRODED (BS 2200)

LEVEL 1 CORROSION ON FRAME REINFORCEMENT ANGLE AT BS 2200, S42L. REMOVED CORROSION PER BAC SRM 51-10-01..

Part: FRAME — CRACKED (BS 300)

SEVERAL CRACKS AT GROMMET HOLE RIGHT NOSE WHEEL WELL TUNNEL AREA AT BS 300. REPAIRED PER BOEING SRM 51-40-02.

Part: SKIN — CRACKED (NR 2 PYLON)

CRACKED SKIN AT ACCESS PANEL 463CL AFT UPPER CORNER NACELLE STATION 195. REPAIRED PER BOEING SRM 54-30-03 PAGE 380.

Part: ENGINE — LOW POWER (NR 1)

REJECTED TAKEOFF, NR 1 ENGINE UNABLE TO REACH TAKEOFF POWER, CHARTED 1.58 COULD ONLY ACHIEVE 1.47 ALL OTHER PARAMETERS NORMAL, EXCEPT FOR N1 NR 1 ENGINE 94 PERCENT NR 4 ENGINE 99 PERCENT. REMOVED AND REPLACED NR 1 ENGINE FUEL FILTER, NO DEFECTS NOTED PER M/M 73-11-01, PERFORMED FUEL PUMP HYDRAULIC STAGE (FD12) 800 PSI WITHIN LIMITS, PERFORMED POWER CONFIDENCE RUN PER M/M 71-00-01 ACCEPTED BY POLAR AIR CARGO ENGINEERING. FULL POWER TAKEOFF COMPLETED AT HNL.

Part: BLEED CONTROL — LEAKING (NR 1 ENGINE)

AT FL 370 -33 TAT -61 SAT NR 1, ENGINE EPR 1.36, .85 N1, .845 N2 UNABLE TO OBTAIN CRUISE POWER. REMOVED AND REPLACED 3.5 BLEED CONTROL AND LINE FROM BLEED CONTROL TO CONNECTOR BLOCK. REPLACED SEAL AT FUEL LINE AT FUEL CONTROL UNIT TO 3.5 BLEED CONTROL. LEAK AND OPERATIONAL CHECK OK PER MAINTENANCE MANUAL 75-32-12 AND 75-32-18.

Part: FUEL PUMP — FAILED (NR 1 ENGINE)

LOST POWER ON NR 1 ENGINE, OIL PRESSURE LIGHT CAME ON, SHUT DOWN ENGINE. FOUND FUEL PUMP FAILED, METAL IN FUEL CONTROL UNIT, NO CONTAMINATION IN ENGINE VANE AND BLEED CONTROL FILTER. REPLACED FUEL PUMP, FUEL CONTROL AND TT2 SENSOR PER BOEING MAINTENANCE MANUAL 73-21-01, 73-11-01, 73-21-04 AND 71-00-00 TEST 09.

Part: SUPPORT — CORRODED (BS 1340)

LEVEL 1 CORROSION ON KEEL BEAM ACCESS PANEL SUPPORT BEAM AT BS 1340 LBL 12 TO RBL 12. REMOVED CORROSION PER BAC SRM 51-10-01 AND REPROTECTED PER BAC MM 51-24-11.

Part: SUPPORT — CORRODED (BS 1326)

LEVEL 1 CORROSION ON KEEL BEAM ACCESS PANEL SUPPORT BEAM AT BS 1326 LBL 12 TO RBL 12. REMOVED CORROSION PER BAC SRM 51-10-01 AND REPROTECTED PER BAC MM 51-24-11.

Part: SUPPORT — CORRODED (BS 1284)

LEVEL 1 CORROSION ON KEEL BEAM ACCESS PANEL SUPPORT BEAM AT BS 1284. LBL 12 TO RBL 12. REMOVED CORROSION PER BAC SRM 51-10-01 AND REPROTECTED PER BAC MM 51-24-11.

Part: SUPPORT — CORRODED (BS 1304)

LEVEL 1 CORROSION ON KEEL BEAM ACCESS PANEL SUPPORT BEAM AT BS 1304 LBL 12. REMOVED CORROSION PER BAC SRM 51-10-01 AND REPROTECTED PER BAC MM 51-24-11.

Part: SEAT TRACK — CORRODED (BS 420)

LEVEL 2 CORROSION ON MAIN DECK SEAT TRACK AT BS 420 LBL 11. REPLACED SEAT TRACK PER BAC SRM 51-10-07.

Part: SUPPORT — CORRODED (BS 1660)

LEVEL 1 CORROSION ON MAIN DECK FLOOR SUPPORT AT BS 1660 LBL 98 TO 110. REMOVED CORROSION PER BAC SRM 51-10-01 AND REPROTECTED PER BAC MM 51-24-11.

Part: SEAT TRACK — CORRODED (BS 1830)

LEVEL 2 CORROSION ON MAIN DECK SEAT TRACK AT BS 1830 RBL 56. REPAIRED PER BAC SRM 53-10-05 FIG. 1.

Part: SKIN — CORRODED (BS 400)

LEVEL 1 CORROSION ON FUSELAGE EXTERNAL SKIN AT BS 400 S41R TO S42R. REMOVED CORROSION PER BAC SRM 51-10-01 AND REPROTECTED PER BAC SRM 51-10-02.

Part: SEAT TRACK — CORRODED (BS 1260-1280)

LEVEL 1 CORROSION ON MAIN DECK SEAT TRACK FLANGE UNDERSIDE AT BS 1260 TO BS 1280 LBL 97. CORROSION REMOVED PER BAC SRM AND REPROTECTED PER BAC MM 51-24-11.

Part: FITTING — CORRODED (BS 1918)

LEVEL 1 CORROSION TO MAIN DECK CARGO DOOR SILL PLATE SUPPORT FITTING AT BS 1918 LBL 95 TO LBL 100. REMOVED CORROSION PER BAC SRM 51-10-01 AND REPROTECTED PER BAC MM 51-24-11.

Part: SUPPORT — CORRODED (BS 1960)

LEVEL 1 CORROSION TO UPPER AND LOWER SURFACES OF MAIN DECK FLOOR SUPPORT AT BS 1960 RBL 12 TO 14. REMOVED CORROSION PER BAC SRM 51-10-01 AND REPROTECTED PER BAC MM 51-24-11.

Part: SUPPORT — CORRODED (BS 1940)

LEVEL 1 CORROSION TO MAIN DECK FLOOR SUPPORT AT BS 1940 LBL 60 TO LBL 75. REMOVED PER BAC SRM 51-10-01 AND REPROTECTED PER BAC MM 51-24-11.

Part: SUPPORT — CORROSION (BS 400-460)

LEVEL 1 CORROSION ON MAIN DECK LONGITUDINAL FLOOR SUPPORT AT BS 400 TO 460 LEFT OUTBOARD. REMOVED CORROSION PER BAC SRM 51-10-01 AND REPROTECTED PER BAC MM 51-24-11.

Part: SUPPORT — CORRODED (BS 477)

LEVEL 1 CORROSION ON MAIN DECK LONGITUDINAL FLOOR SUPPORT UNDERSIDE AT BS 477 LEFT OUTBOARD. REMOVED CORROSION PER BAC SRM 51-10-01 AND REPROTECTED PER BAC MM 51-24-11.

Part: SUPPORT — CORRODED (BS 1920)

LEVEL 2 CORROSION ON MAIN DECK FLOOR SUPPORT AT BS 1920 RBL 100. REPAIRED PER BAC SRM 51-40-04 FIG. 3.

Part: SUPPORT — CORRODED (BS 1800)

LEVEL 1 CORROSION ON DECK FLOOR SUPPORT AT BS 1800 FROM LBL 11 TO RBL 11. REMOVED CORROSION PER BAC SRM 51-10-01 AND REPROTECTED PER BAC MM 51-24-11.

Part: SUPPORT — CORRODED (BS 1840)

LEVEL 1 CORROSION ON MAIN DECK FLOOR SUPPORT AT BS 1840 LBL 31 TO LBL 38. REMOVED CORROSION PER BAC SRM 51-10-01 AND REPROTECTED PER BAC MM 51-24-11.

Part: BEAM — CORRODED (BS 1400)

LEVEL 1 CORROSION TO POWER DRIVE UNIT SUPPORT BEAM ON MAIN DECK AT BS 1480 LBL 50. REMOVED CORROSION PER BAC SRM 51-10-01 AND REPROTECTED PER BAC MM 51-24-11.

Part: SUPPORT — CORRODED (BS 1920)

LEVEL 2 CORROSION ON MAIN DECK FLOOR SUPPORT AT BS 1920 LBL 80 TO 88. REPAIRED PER BAC SRM 51-40-04 FIG 3.

Part: FLOOR BEAM — CORRODED (BS 1860)

LEVEL 1 CORROSION ON MAIN DECK FLOOR BEAM AT BS 1860 LBL 85 TO LBL 95. REMOVED CORROSION PER BAC SRM 51-10-01 AND REPROTECTED PER BAC MM 51-24-11.

Part: SUPPORT — CORRODED (BS 1800)

LEVEL 1 CORROSION ON MAIN DECK FLOOR SUPPORT AT BS 1800 RBL 11. REMOVED CORROSION PER BAC SRM 51-10-01 AND REPROTECTED PER BAC MM 51-24-11.

Part: SUPPORT — CORRODED (BS 1420)

LEVEL 1 CORROSION TO MAIN DECK FLOOR BEAM SUPPORT AT BS 1420 LBL 57. REMOVED CORROSION PER BAC SRM 51-10-01 AND REPROTECTED PER BAC MM 51-24-11.

Part: SUPPORT — CORRODED (BS 1760-1766)

LEVEL 1 CORROSION ON MAIN DECK FLOOR SUPPORT AT BS 1760 TO 1766 RBL 105. REMOVED CORROSION PER BAC SRM 51-10-01 AND REPROTECTED PER BAC MM 51-24-11.

Part: SEAT TRACK — CORRODED (BS 300)

LEVEL 2 CORROSION ON MAIN DECK SEAT TRACK AT BS 300 LBL 42. REPLACED SEAT TRACK PER BAC SRM 51-10-07.

Part: SKIN — CORRODED (BS 400-500)

LEVEL 1 CORROSION ON FUSELAGE EXTERNAL SKIN AT BS 400 TO 500 S41R TO S44R. REMOVED CORROSION PER BAC SRM 51-10-01 AND REPROTECTED PER SRM 51-10-02.

Part: SUPPORT — CORRODED (BS 1900)

LEVEL 1 CORROSION ON MAIN DECK FLOOR SUPPORT LOWER SURFACE AT BS 1900 RBL 74. REMOVED CORROSION PER BAC SRM 51-10-01 AND REPROTECTED PER BAC MM 51-24-11.

Part: SUPPORT — CORRODED (BS 1740)

LEVEL 1 CORROSION ON MAIN DECK FLOOR SUPPORT AT BS 1740 LBL 33. REMOVED CORROSION PER BAC SRM 51-10-01 AND REPROTECTED PER BAC MM 51-24-11.

Part: FITTING — CORRODED (BS 1922)

LEVEL 1 CORROSION ON TIE DOWN TRACK FITTING ON MAIN DECK AT BS 1922 LBL 50 TO LBL 58. CORROSION REMOVED PER BAC SRM 51-10-01 AND REPROTECTED PER BAC MM 51-24-11.

Part: SEAT TRACK — CORRODED (BS 1720)

LEVEL 1 CORROSION ON MAIN DECK SEAT TRACK AT BS 1720 LBL 53 TO 58. REMOVED CORROSION PER BAC SRM 51-10-01 AND REPROTECTED PER BAC MM 51-24-11.