N408MC

Part: ELEC CONNECTOR — FAULTED (ZONE 100) · airframe 103,809 hrs · 17,433 cycles

ON DEPARTURE AT 1000' AGL, HYD QTY LOW 4 EICAS ADVISORY MESSAGE, RAN NNC 13.29, SECURED NR 4 HYDRAULIC SYSTEM OFF. T/S PER WDM 29-33-12-2 TO PERFORM WIRING CHKS BTWN HYQUIM D7848CA TO #4 HYD SYS TRANSMITTER DT404, CHKS GOOD & INSULATION RESISTANCE CHCKS NORMAL. R & R CONNECTOR DT404 PER SWPM 20-61-11. OPS CHK GOOD.

Part: SOLENOID — FAULTED (NR 4 ENGINE) · airframe 102,775 hrs · 17,269 cycles

ENG 4 FUEL VALVE EICAS, ENG 4 FUEL VALVE STATUS, #4 ENG WOULD NOT SHUT DOWN UPON FUEL CONTROL SWITCHING OFF POSN. L13 CB FOUND IN OUT POSITION.(<P>R/R SOLENOID FUEL SOV PER AMM 73-21-20 &AMP; IPC 73-21-14-01 ITEM 67. PFM #4 ENG IDLE RUN CHK, NO LEAK FND.</P>)

Part: SOFTWARE — FAULTED (FMC) · airframe 102,397 hrs · 17,216 cycles

L NAV WON'T ENGAGE. RELOADED ALL ASSOCIATED SOFTWARE INTO BOTH LT & RT FMC IAW AMM 34-61-00. ALL GROUND TEST PASSED. VERIFIED ALL SOFTWARE CORRECT CONFIG.

Part: STARTER — FAULTED (ZONE 400) · airframe 101,899 hrs · 17,138 cycles

ENG 1 OIL PRESS EICAS MSG. ENG 1 OIL QTY DROPPED ON INITIAL CLIMB, PRESSURE DECREASED STEADILY UNTIL ENG 1 SHUT DOWN IN FLIGHT. ENG WINDMILL FOR 15 MINUTES.(<P>FOUND PACKING ON STARTER SHAFT CUT. REPLACED PACKING. INSPECTED MCD, FOUND SMALL QTY METAL SHAVING CLEARED AND LEAK CHECKED. MCC NOTIFIED WITH FINDINGS. REMOVED &AMP; REPLACED ENG #1 STARTER IAW AMM 80-11-01/401. OPS CHECK GOOD. IDLE LEAK CHECK GOOD. PERFORMED TEST #5 IDLE LEAK CHK IAW AMM 71-00-00-7055-152-J00, OPS CHK &AMP; LEAK CHECK GOOD. HIGH POWER RUN CHK, LEAK CHK GOOD TOO, AFTER HIGH POWER RUN. NO LEAKS NOTICED. ENG OKAY TO SERVICE. ALL CHECKS GOOD AND OIL PRESSURE/TEMPERATURE WITHIN AMM SPECIFICATIONS PER 71-00-00.</P>)

Part: PANEL — DAMAGED (SPEED BRAKE) · airframe 101,754 hrs · 17,116 cycles

DURING DESCENT, A/C EXPERIENCED HIGH FREQUENCY VIBRATIONS DURING SPEED BRAKE APPLICATIONS. ONCE LANDED IN HKG, STATION NOTICED THE #6 SPEED BRAKE PANEL ASSY DAMAGED / SEPERATED IN FLIGHT.(<P>R/R #6 SPOILER IAW AMM 27-62-01 AND OPERATIONAL CHECKS NORMAL</P>)

Part: RIB — CRACKED (ZONE 300) · airframe 100,489 hrs · 16,931 cycles

EMP HORIZONTAL STABILIZER TIP MOST O/B CLOSURE RIB WEB P/N: 65B03520-60 FOUND CRACKED.(<P>EMP HORIZONTAL STABILIZER TIP MOST O/B CLOSURE RIB WEB P/N: 65B03520-60 REPAIRED IAW SRM 55-10-09-2R-13 REPAIR 13 DETAIL III. NO FURTHER DEFECTS NOTED.</P>)

Part: RIB — CRACKED (ZONE 300) · airframe 100,489 hrs · 16,931 cycles

EMP HORIZONTAL STABILIZER TIP MOST O/B CLOSURE RIB LOWER CHORD P/N: 65B03520-54 FOUND CRACKED.(<P>EMP HORIZONTAL STABILIZER TIP MOST O/B CLOSURE RIB LOWER CHORD P/N: 65B03520-54 REPAIRED IAW SRM 55-10-09-2R-13 REPAIR 13 DETAIL V. NO FURTHER DEFECTS NOTED</P>)

Part: DOUBLER — CRACKED (DOOR HINGE) · airframe 97,812 hrs · 16,456 cycles

DOOR 1 EXTERIOR LOWER HINGE DOUBLER FOUND CRACK(<P>DOOR 1 LH EXTERIOR LOWER HINGE AREA DOUBLER P/N: 65B22350-7 REPLACED AND INSTALLED IAW SRM 51-40-02 AND BOEING 65B01836 SHEET 23 REV E. NO FURTHER DEFECTS NOTED</P>)

Part: PANEL — DELAMINATED (RT WING TE FLAP) · airframe 96,869 hrs · 16,297 cycles

R/H I/B T/E FLAP MID FLAP O/B CARRIAGE ASSY UPPER COVER APNEL FOUND DELAMINATION AS MARK.(<P>R/H I/B T/E FLAP MID FLAP O/B CARRIAGE ASSY UPPER COVER PANEL DELAMINATION AREA. PERFORMED REPAIR AS PER SRM 51-70-07 PAR 5.A. NO FURTHER DEFECTS NOTED.</P>)

Part: SUPPORT — CRACKED (LT WING) · airframe 96,869 hrs · 16,297 cycles

LHW L/E CAVITY HOLES 1300 FIXED PNL SUPPORT CRACK (AFT OF #4 V/C FLAP)(<P>SUPPORT BEAM REPAIRED AS PER RI-57-41-16684 REV.A. NO FURTHER DEFECTS NOTED</P>)

Part: SUPPORT BRACKET — CRACKED (TRANSFER VALVE) · airframe 96,869 hrs · 16,297 cycles

#3 FUEL TANK JETTISON TRANSFER VALVE SUPPORT BRACKET FOUND CRACK.(<P>BRACKET REPAIRED AS PER RI NO. RI-28-21-16701 REV.A. NO FURTHER DEFECTS NOTED.</P>)

Part: BRACKET — DAMAGED (BS 2674) · airframe 96,869 hrs · 16,297 cycles

APU COMPT L/H FRAME STA 2674 WIRE BRACKET AND ATT FRAME RIVET HOLES FOUND ELONGATED(<P>WIRE BRACKET REPLACED AS PER SRM 51-10-02, NEW BRACKET HOLES TRANSFERRED AS PER SRM 51-40-05, NEW BRACKET INSTALLED AS PER SRM 51-40-02 AND FRAME REPAIRED AS PER SRM 53-80-07-2R-1 REPAIR 1 FIG 201. NO FURTHER DEFECTS NOTED.</P>)

Part: LONGERON — CRACKED (BS 1480-1540) · airframe 96,869 hrs · 16,297 cycles

FUS - 2EA CRACKS WERE FOUND ON RH BS 1480-1540 STR 32-33 LONGERON EXTENSION FITTING(<P>LONGERON EXTENSION FITTING REPLACEMENT CARRIED OUT AS PER ATLAS AIR EO 4453A818 R19 PART 4. NO FURTHER DEFECTS NOTED</P>)

Part: TENSION TIE — CRACKED (BS 840) · airframe 96,869 hrs · 16,297 cycles

RH BS 840 UPPER DECK TENSION TIE 1EA CRACK FOUND AT 1 O/C POSITION OF THE AFT CHANNEL(<P>TENSION TIE REPAIRED AS PER SRM 53-20-30-2R-1 REPAIR 1. NO FURTHER DEFECTS NOTED.</P>)

Part: SKIN — DELAMINATED (LT WING TE FLAP) · airframe 96,869 hrs · 16,297 cycles

LHW T/E I/B FLAP FLAP LOWER SURFACE L/E 47" (COUNT FROM I/B) FOUND DELAMINATION AS MARKED.(<P>LHW T/E I/B AFT FLAP LOWER SURFACE L/E 47" (COUNT FROM I/B) DELAMINATION AREA. PERFORMED HOT BOND REPAIR AS PER SRM 51-70-07 PAR 5.A.(1) AND FIG 5. NO FURTHER DEFECTS NOTED.</P>)

Part: SKIN — CORRODED (LT WING TE FLAP) · airframe 96,869 hrs · 16,297 cycles

LHW I/B AFT FLAP FOUND BULGE UP(<P>PERFORMED REPAIR AT BULGE UP AREA IAW RI-57-53-16705. NO FURTHER DEFECTS NOTED.</P>)

Part: SKIN — DENTED (LT WING TE FLAP) · airframe 96,869 hrs · 16,297 cycles

LHW I/B AFT FLAP LWR T/E SURFACE AT MID AREA FOUND 1EA DENT AS MARK (155" FROM I/B TO O/B).(<P>LHW I/B AFT FLAP LWR T/E SURFACE 155" FROM I/B DENT AREA. PERFORMED HOT BOND REPAIR AS PER SRM 51-70-07 PAR 5.A.(1) AND FIG 5. NO FURTHER DEFECTS NOTED.</P>)

Part: SKIN — DELAMINATED (RT WING TE FLAP) · airframe 96,869 hrs · 16,297 cycles

RHW T/E I/B MID FLAP LOWER SURFACE L/E 124" FOUND DELAMINATION AS MARKED (COUNT FROM TO I/B).(<P>RHW T/E I/B MID FLAP LOWER SURFACE L/E 124" (COUNT FROM TO I/B) DELAMINATION AREA. PERFORMED REPAIR AS PER SRM 51-70-07 PAR 5.A. NO FURTHER DEFECTS NOTED.</P>)

Part: PANEL — CRACKED (BS 1720) · airframe 96,869 hrs · 16,297 cycles

M/D STA 1720 L/H DADO PNL FOUND CRACK(<P>DADO PNL CRACK AREA REPAIRED AS PER RI-25-21-16675 REV.A. NO FURTHER DEFECTS NOTED.</P>)

Part: NONE — NONE (NONE) · airframe 96,869 hrs · 16,297 cycles

ACCOMPLISHMENT OF EO 4453A301 REV.11, WE FOUND ONE EACH FREEZE PLUG INSTALLED ON UPPER DECK R/H STA 880 FRAME AREA.(<P>FRAME REPAIRED AS PER RI NO. RI-53-20-16702 REV.A. NO FURTHER DEFECTS NOTED.</P>)

Part: SKIN — CORRODED (BS 1715 S45R) · corrosion level 2 · airframe 96,869 hrs · 16,297 cycles

FUSELAGE SKIN AT LOWER LOBE CIRCUMFERENTIAL SPLICE LOCATION STA 1715 S45R FOUND CORROSION APPROX 1" X 1"(<P>SKIN REPAIRED AS PER SRM 53-00-01-2R-1 REPAIR 1 FIG 201 DETAIL I. NO FURTHER DEFECTS NOTED</P>)

Part: SKIN — CORRODED (BS 1240) · corrosion level 2 · airframe 96,869 hrs · 16,297 cycles

FX - AIRCON BAY L/H STA 1240 CENTER WING LWR SURFACE CORR AT LBL 91" - LBL 102" AND LBL 105" - LBL 113".(<P>SKIN CORROSION AREA REPAIRED AS PER RI NO. RI-57-10-16704 REV.A. NO FURTHER DEFECTS NOTED.</P>)

Part: FRAME — CRACKED (BS 1480 BULKHEAD) · airframe 96,869 hrs · 16,297 cycles

FX STA 1480 RH BULKHEAD FRAME WEB FOUND CRACK(<P>FRAME WEB REPAIRED AS PER SRM 53-40-08-2R-1 REPAIR 1 FIG 201. NO FURTHER DEFECTS NOTED.</P>)

Part: SKIN — CRACKED (BS 1680 S41R) · airframe 96,869 hrs · 16,297 cycles

FX - FUSELAGE SKIN STA 1680 STR 41R FOUND CORR CRACK(<P>SKIN REPAIRED AS PER RI-53-61-16685 REV.A. NO FURTHER DEFECTS NOTED.</P>)

Part: FRAME — CRACKED (BS 2598 BULKHEAD) · airframe 96,869 hrs · 16,297 cycles

LH BS 2598 B/HEAD INNER CHORD 1EA HOLE FOUND CRACK AT 3ND LAYER (COUNTING FROM AFT) AT 5 O'CLOCK POSITION APPROX 0.050" IN DEPTH(<P>INNER CHORD CRACK AREA REPAIRED AS PER RI-53-73-16683 REV.A. NO FURTHER DEFECTS NOTED</P>)

Part: SKIN — PUNCTURED (LT WING LE FAP) · airframe 96,869 hrs · 16,297 cycles

L/H I/B FLAP FORE FLAP UPPER SURFACE FOUND 1EA PUNCH HOLE DAMAGED AS MARK.(<P>L/H I/B FLAP FORE FLAP UPPER SURFACE PUNCH HOLE DAMAGE AREA. PERFORMED HOT BOND REPAIR AS PER SRM 51-70-07 PAR 5.A.(1) AND FIG 5. NO FURTHER DEFECTS NOTED</P>)

Part: SKIN — DENTED (LT WING TE FLAP) · airframe 96,869 hrs · 16,297 cycles

LHW I/B AFT FLAP O/B LWR SURFACE FOUND 1EA DENT AS MARK (146" FROM I/B TO O/B).(<P>LHW I/B AFT FLAP O/B LWR SURFACE (146" FROM I/B TO O/B) DENT AREA. PERFORMED HOT BOND REPAIR AS PER SRM 51-70-07 PAR 5.A.(1) AND FIG 5. NO FURTHER DEFECTS NOTED.</P>)

Part: SKIN — DELAMINATED (RT WING TE FLAP) · airframe 96,869 hrs · 16,297 cycles

RHW T/E I/B MID FLAP L/E 2" (COUNT FROM I/B) FOUND DELAMINATION AS MARK.(<P>RHW T/E I/B MID FLAP L/E 2" (COUNT FROM I/B) DELAMINATION AREA PERFORMED REPAIR AS PER SRM 51-70-07 PAR 5.A. NO FURTHER DEFECTS NOTED.</P>)

Part: SKIN — DENTED (LT WING TE FLAP) · airframe 96,869 hrs · 16,297 cycles

LHW O/B T/E AFT FLAP O/B PANEL UPPER SURFACE FOUND SEVERAL AREA DENT MARK AS MARKED.(<P>METAL HOT BOND REPAIR CARRIED OUT AS PER RI-57-51-16699 REV.A. NO FURTHER DEFECTS NOTED.</P>)

Part: LADDER — CRACKED (CREW) · airframe 96,869 hrs · 16,297 cycles

M/D CREW LADDER I/B SIDE #7 & 10 STEP FOUND CRACK(<P>#7 AND #10 STEP CRACK AREA REPAIRED AS PER RI-25-50-16667 REV.A. NO FURTHER DEFECTS NOTED.</P>)

Part: SKIN — DENTED (RT WING TE FLAP) · airframe 96,869 hrs · 16,297 cycles

RHW O/B T/E AFT FLAP O/B PANEL UPPER SURFACE FOUND SEVERAL AREA DENT MARK AS MARKED.(<P>METAL HOT BOND REPAIR CARRIED OUT AS PER RI-57-51-16700 REV.A. NO FURTHER DEFECTS NOTED.</P>)

Part: SKIN — DELAMINATED (RT WING TE FLAP) · airframe 96,869 hrs · 16,297 cycles

RHW T/E I/B AFT FLAP LOWER SURFACE T/E 155" FOUND DELAMINATION AS MARKED (COUNT FROM I/B).(<P>RHW T/E I/B AFT FLAP LOWER SURFACE T/E 155" (COUNT FROM I/B) DELAMINATION AREA. PERFORMED REPAIR AS PER SRM 51-70-07 PAR 5.A. NO FURTHER DEFECTS NOTED.</P>)

Part: SKIN — DELAMINATED (LT WING TE FLAP) · airframe 96,869 hrs · 16,297 cycles

LHW T/E I/B AFT FLAP LOWER SURFACE T/E 130" FOUND DELAMINATION AS MARK. (COUNT FROM I/B TO O/B)(<P>LHW T/E I/B AFT FLAP LOWER SURFACE T/E 130" (COUNT FROM I/B TO O/B) DELAMINATION AREA. PERFORMED HOT BOND REPAIR AS PER SRM 51-70-07 PAR 5.A.(1) AND FIGURE 5. NO FURTHER DEFECTS NOTED</P>)

Part: SKIN — DAMAGED (LT WING TE FLAP) · airframe 96,869 hrs · 16,297 cycles

LHW I/B FORE FLAP LWR SURFACE FOUND DAMAGED AS MARK (156" FROM O/B TO I/B).(<P>LHW I/B FORE FLAP LWR SURFACE 156" FROM O/B TO I/B DAMAGED AREA. PERFORMED HOT BOND REPAIR AS PER SRM 51-70-07 PAR 5.A.(1) AND FIG 5. NO FURTHER DEFECTS NOTED</P>)

Part: SKIN — DELAMINATED (RT WING TE FLAP) · airframe 96,869 hrs · 16,297 cycles

RHW T/E I/B AFT FLAP LOWER SURFACE T/E 122" FOUND DELAMINATION AS MARKED (COUNT FROM I/B).(<P>RHW T/E I/B AFT FLAP LOWER SURFACE T/E 122" (COUNT FROM I/B) DELAMINATION AREA. PERFORMED REPAIR AS PER SRM 51-70-07 PAR 5.A. NO FURTHER DEFECTS NOTED.</P>)

Part: TENSION TIE — CRACKED (BS 840) · airframe 96,869 hrs · 16,297 cycles

LH BS 840 UPPER DECK TENSION TIE 1EA CRACK FOUND AT AFT CHANNEL(<P>TENSION TIE REPAIRED AS PER SRM 53-20-30-2R-1 REPAIR. NO FURTHER DEFECTS NOTED.</P>)

Part: SKIN — CORRODED (BS 1000-1003) · corrosion level 2 · airframe 96,869 hrs · 16,297 cycles

FX R/H AIRCON BAY STA 1000-1003 CENTER SECTION LOWER SURFACE CORR. AT RBL 15" - RBL 29"(<P>SKIN CORROSION AREA REPAIRED AS PER RI-57-10-16703 REV.A. NO FURTHER DEFECTS NOTED.</P>)

Part: CHANNEL — CRACKED (BS 900) · airframe 96,869 hrs · 16,297 cycles

LH BS 900 UPPER DECK TENSION TIE AFT CHANNEL 1EA HOLE FOUND CRACK(<P>TENSION TIE REPAIRED AS PER SRM 53-20-30-2R-1 REPAIR 1. NO FURTHER DEFECTS NOTED.</P>)

Part: SKIN — DELAMINATED (RT WING TE FLAP) · airframe 96,869 hrs · 16,297 cycles

RHW T/E I/B AFT FLAP LOWER SURFACE T/E 48" FOUND DELAMINATION AS MARKED (COUNT FROM I/B).(<P>RHW T/E I/B AFT FLAP LOWER SURFACE T/E 48" (COUNT FROM I/B) DELAMINATION AREA. PERFORMED REPAIR AS PER SRM 51-70-07 PAR 5.A. NO FURTHER DEFECTS NOTED</P>)

Part: SKIN — PUNCTURED (LT WING TE FLAP) · airframe 96,869 hrs · 16,297 cycles

L/H I/B FLAP AFT FLAP T/E UPPER SURFACE FOUND 1EA PUNCH DAMAGED AS MARK.(<P>LH I/B FLAP AFT FLAP T/E UPPER SURFACE PUNCH DAMAGED AREA. PERFORMED HOT BOND REPAIR AS PER SRM 51-70-07 PAR 5.A.(1) AND FIG 5. NO FURTHER DEFECTS NOTED.</P>)

Part: SKIN — DELAMINATED (LT WING TE FLAP) · airframe 96,869 hrs · 16,297 cycles

L/H I/B FLAP MID FLAP MOST O/B LWR SURFACE FOUND DELAMINATION AS MARK (15" TO O/B EDGE).(<P>L/H I/B FLAP MID FLAP MOST O/B LOWER SURFACE (15" TO O/B EDGE) DELAMINATION AREA. PERFORMED HOT BOND REPAIR AS PER SRM 51-70-07 PAR 5.A.(1) AND FIG 5. NO FURTHER DEFECTS NOTED</P>)

Part: SKIN — DELAMINATED (RT WING TE FLAP) · airframe 96,869 hrs · 16,297 cycles

RHW T/E I/B AFT FLAP LOWER SURFACE T/E 100" FOUND DELAMINATION AS MARKED (COUNT FROM I/B).(<P>RHW T/E I/B AFT FLAP LOWER SURFACE T/E 100" (COUNT FROM I/B) DELAMINATION AREA. PERFORMED REPAIR AS PER SRM 51-70-07 PAR 5.A. NO FURTHER DEFECTS NOTED.</P>)

Part: SEAT TRACK — DAMAGED (BS 1890) · airframe 96,869 hrs · 16,297 cycles

M/D STA 1890 RBL 11 SEAT TRACK CTR GUIDE STOP HOLE FOUND ELONGATED(<P>SEAT TRACK REPAIRED AS PER SRM 53-00-52-2R-12 REPAIR 12. NO FURTHER DEFECTS NOTED.</P>)

Part: FAIRING — DELAMINATED (RT WING TE FLAP) · airframe 96,869 hrs · 16,297 cycles

RHW O/B FWD FLAP FWD FAIRING 48" FOUND DELAMINATION AS MARKED (COUNT FROM O/B).(<P>RHW O/B FWD FLAP FWD FAIRING 48" (COUNT FROM O/B) DELAMINATION AREA. PERFORMED REPAIR AS PER SRM 51-70-07 PAR 5.A. NO FURTHER DEFECTS NOTED.</P>)

Part: TENSION TIE — CRACKED (BS 880) · airframe 96,869 hrs · 16,297 cycles

LH BS 880 UPPER DECK TENSION TIE 1EA CRACK FOUND AT AFT CHANNEL(<P>TENSION TIE REPAIRED AS PER SRM 53-20-30-2R-1 REPAIR 1. NO FURTHER DEFECTS NOTED.</P>)

Part: CLOSEOUT PANEL — CRACKED (BS 1241) · airframe 96,869 hrs · 16,297 cycles

M/D STA 1241 LBL 77-99 CLOSURE PNL FOUND CRACK.(<P>CLOSURE PNL REPLACED AS PER SRM 51-10-02, NEW PNL HOLES TRANSFERRED AS PER SRM 51-40-05 AND NEW PNL INSTALLED AS PER SRM 51-40-02. NO FURTHER DEFECTS NOTED.</P>)

Part: SKIN — DELAMINATED (LT WING TE FLAP) · airframe 96,869 hrs · 16,297 cycles

LHW T/E I/B AFT FLAP L/E 66" FOUND DELAMINATION AS MARKED (COUNT FROM O/B).(<P>LHW T/E I/B AFT FLAP L/E 66" (COUNT FROM O/B) DELAMINATION AREA. PERFORMED HOT BOND REPAIR AS PER SRM 51-70-07 PAR 5.A.(1) AND FIG 5. NO FURTHER DEFECTS NOTED.</P>)

Part: SKIN — CHAFED (BS 724 S0-1R) · airframe 96,869 hrs · 16,297 cycles

FX SKIN STA 724 STR 0-1R FOUND CHAFING.(<P>CHAFING AREA REPAIRED AS PER RI NO. RI-53-20-16706 REV.A. NO FURTHER DEFECTS NOTED.</P>)

Part: PANEL — DELAMINATED (LT WING TE FLAP) · airframe 96,869 hrs · 16,297 cycles

L/H O/B FLAP MID FLAP O/B CARRIAGE ASSY COVER PANEL FOUND DELAMINATION AS MARK.(<P>L/H O/B FLAP MID O/B CARRIAGE ASSY COVER PANEL DELAMINATION AREA. PERFORMED HOT BOND REPAIR AS PER SRM 51-70-07 PAR 5.A.(1) AND FIG 5. NO FURTHER DEFECTS NOTED.</P>)

Part: ACTUATOR — UNKNOWN (UNKNOWN) · airframe 96,647 hrs · 16,257 cycles

PILOT REPORTS RH BODY GEAR DOOR DROOPS IN FLIGHT. GEAR DOORS OPEN WHEN LANDING GEAR HANDLE IS IN THE OFF POSITION.(<P>REMOVED AND REPLACED R BLG UPLOCK ACTUATOR IAW B747 AMM 32-33-94. OPS CHK AND LEAK CHK GOOD.

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 94,195 hrs · 15,862 cycles

FUEL TANK #4 LEAKS INTO CENTER TANK AT A RATE OF 100 KILOS PER 11 MINUTES APPROX 600 PER HOUR UNCONTROLLABLY(<P>MX CURRENTLY INSTALLING TRANSFER PUMP &AMP; ACTUATOR IAW AP-24097, AMM 28-22-07 &AMP; FIM 28-20-00.</P>)

Part: TRANSFER VALVE — UNKNOWN (UNKNOWN) · airframe 94,195 hrs · 15,862 cycles

FUEL TANK #4 LEAKS INTO CENTER TANK AT A RATE OF 100 KILOS PER 11 MINUTES APPROX 600 PER HOUR UNCONTROLLABLY(<P>REPLACED BAD #3 MAIN TANK TRANSFER VALVE IAW 747 AMM 28-16-05. C/W LEACK CHECK, NO LEAKS FOUND AT THIS TIME. REF SUN AERO 5,0,2,3 RO25. REF LP 1768045 ITEM 9: REMOVED AND REPLACED ACTUATOR IAW747 AMM 28-16-04.PN: MAHA119-1 SN: R6681 C/W OPS CHECK. NO DEFECTS FOUND AT THIS TIME. REF SUN AERO 5.023R025. REF LP 1768046 ITEM 10: C/W ACTION PLAN 24097. REF SUN AERO 5,0,23R025.</P>)

Part: TRANSFER VALVE — UNKNOWN · airframe 94,195 hrs · 15,862 cycles

FUEL TANK #4 LEAKS INTO CENTER TANK AT A RATE OF 100 KILOS PER 11 MINUTES, APPROX 600 PER HOUR UNCONTROLLABLY.(<P>REPLACED BAD #3 MAIN TANK TRANSFER VALVE IAW 747 AMM 28-16-05. LEAK CHECKS C/W NO LEAKS FOUND AT THIS TIME.</P>)

Part: COALESCER BAG — UNKNOWN (UNKNOWN) · airframe 94,195 hrs · 15,862 cycles

DURING LANDING WITH REVERSE THRUST, EICAS SMOKE CREW REST APPEARED. HAZE NOTICED IN UPPER DECK. DISSIPATING SLOWLY AFTER REVERSERS STOWED. SUSPECT AIR CONDITIONING SYSTEM CONTAMINATION.(<P>REMOVED #3 PACK COALESCER BAG PER AMM 21-51-05-002-018 AND INSTALLED NEW COALESCER BAG PER AMM 21-51-05-400-801. OPERATED PACK 3 PER AMM 21-51-00/601, OPS CHECK GOOD AND NO VISIBLE HAZE NOTED.</P>)

Part: WINDOW — NOT REPORTED (NOT REPORTED) · airframe 93,306 hrs · 15,708 cycles

UPON ARRIVAL WALK AROUND, FOUND UPPER DECK REST AREA LH CTR PASSENGER WINDOW GLASS BROKEN, AND PART OF THE WINDOW WAS MISSING(<P>LP 1670580 M3 - R/R WINDOW &AMP; PANE ASSY PER AMM 56-21-01-404-010.&NBSP;</P> / <P>NOTE: EXTERIOR CONDITIONAL CHECK C/W PER AMM 05-51-58/201, NO DISCREPANCIES NOTED ON LP 1670582 M7</P> / <P>NOTE: CABIN PRESSURIZATION CHECK C/W PER AMM 21-31-00 WITH NO LEAKS NOTED ON LP 1670582 M9</P>)

Part: LANDING GEAR — HANDLER ERROR · airframe 93,016 hrs · 15,651 cycles

GEAR DOOR DISAGREE MSG IN FLIGHT. SHORTLY AFTER T/O, RETURNED TO STATION. REMOVED LT WING GEAR PIN, FOUND STILL INSTALLED IAW AMM 32-09-03.

Part: PRESSURE SWITCH — FAULTY · airframe 91,210 hrs · 15,334 cycles

EICAS CAUTION MSG CAME ON FOR "XFEED CONFIG," "FUEL TANK TO ENGINE," &AMP; "FUEL XFEED 4" DURING CRUISE FLIGHT. AIRCRAFT RETURNED TO ANC.(<P>2 DEFERRALS HAD BEEN PLACED ON THE A/C IN THE ANC BEFORE DEPARTURE. #4 FUEL CROSS FEED VALVE INOP ON MEL 28-22-05-01 & #3 MAIN TANK OVERBOARD JETTISON PUMP PRESS LIGHT STAYS ON MEL 28-31-02A. WITH THESE ITEMS ON DEFERRAL, THESE CAUTION MESSAGES COULD APPEAR ON THE EICAS. REPLACED THE FUEL PRESSURE SWITCH FOR THE JETTISON PUMP DEFERRAL. REPLACED THE CROSS FEED VALVE ACTUATOR FOR THE #4 FUEL CROSS FEED VALVE. AIRCRAFT WAS RETURNED TO SERVICE.</P>)

Part: NONE — NONE · corrosion level 2 · airframe 89,383 hrs · 15,011 cycles

CORROSION DAMAGE ON THE SEAT TRACK (P/N 65B38961-4) OF MAIN DECK BETWEEN STA 2100 AND STA 2110.45, RBL 98.58.(<P>REMOVED AFFECTED FASTENERS TO GET ACCESS IAW SRM 51-40-02 REV 93. REPAIRED CORROSION AREA IAW SRM 53-00-52 REPAIR 6 REV 93 AND EI NO T2022A53M-354 REV 1. INSTALLED FASTENERS IAW SRM 51-40-02 REV. 93 AND BOEING DWG NO 65B38406 SH8, REV A AND 65B38751 SH67 REV A. CONDITION CHECK NORMAL AND JOB COMPLETED.</P>)

Part: NONE — NONE · corrosion level 2 · airframe 89,383 hrs · 15,011 cycles

FOUND CORROSION DAMAGE ON MAIN DECK FLOOR BEAM UPPER CAP AT STA 2040 LBL 65.(<P>REMOVED DAMAGED PART IAW SRM 51-40-02 REV 93. REPAIRED DAMAGE AREA IAW SRM 53-00-51-2R-3 REPAIR 3 REV 93 AND EI NO T2022A53M-220 REV 1. INSTALL FASTENERS IAW SRM 51-40-00-02 REV 93 AND DWG NO 6538102 SH 09 REV -, 65B38251 SH 62 REV 1, SH 35 REV A. JOB COMPLETED AND CONDITION CHECK NORMAL.</P>)

Part: NONE — NONE · airframe 89,383 hrs · 15,011 cycles

FOUND EXISTING REPAIR DOUBLER ON FUSELAGE SKIN AT STA 500 - STA 520, S-26L - S-28L.(<P>EXISTING REPAIR DOUBLER WAS COVERED BY EO NO 4453B133 REV 1 AND EI NO T2022A53M-351 REV 1. REFER RAM FORM N408MC-22-22. JOB COMPLETED.</P>)

Part: NONE — NONE · airframe 89,383 hrs · 15,011 cycles

BROKEN - DAMAGE ON THE CRGO TRACK BETWEEN STA 1840 AND STA 1860, RBL 24.75(<P>REMOVED DAMAGED PARTS IAW SRM 51-40-02 REV 93. REPAIRED DAMAGED AREA IAW SRM 53-00-52-2R-10 REPAIR 10 REV 93 AND EI NO T2022A53M-302 REV 1. INSTALLED FASTENER IAW SRM 51-40-02 REV 93 AND DWG NO 65B06314 SHEET 14 REV G. JOB COMPLETED AND CONDITION CHECK NORMAL.</P>)

Part: SPLICE — NONE · corrosion level 2 · airframe 89,383 hrs · 15,011 cycles

CORROSION - M/D STIFFENER SPLICE AT STA 1947 LBL 75.92(<P>REMOVED DAMAGED PARTS IAW SRM 51-40-02-0G-0 , REV 93. INSTALL NEW PARTS IAW SRM 51-40-02-0G-0, REV 93 AND DWG NO 65B38251 SHEET 32 REV -. JOB COMPLETED AND CONDITION CHK NORMAL.</P>)

Part: NONE — NONE · corrosion level 2 · airframe 89,383 hrs · 15,011 cycles

CORROSION DAMAGE ON MAIN DECK OUTBD FLOOR PANEL SUPPORT BETWEEN STA 2100 AND STA 2140, RBL 117.(<P>ACCOMPLISH EI NO T2022A53-266 REV 1. REINSTALLED FASTENERS IAW SRM 51-40-02 REV 93 AND DWG NO 65B11411 SH 9 REV B AND&NBSP; 65B38687 SH 2 REV E. JOB COMPLETED AND CONDITION CHECK NORMAL.</P>)

Part: ELT — NONE · airframe 89,383 hrs · 15,011 cycles

SYSTEM INOP - FOUND THE FIXED ELT IS INOP WHEN SET THE SWITCH TO ON POSITION(<P>IAW AR AMM 23-24-01 PAGE 401, 402 REV 103 REPLACED FIXED ELT AND CONDITION CHECK NORMAL. IAW AR AMM 23-24-01 PAGE 402 REV 103 PERFORMED ELT INSTALLATION TEST AND THE RESULT WAS SATISFACTORY.</P>)

Part: NONE — NONE · airframe 89,383 hrs · 15,011 cycles

DEVIATION WAS FOUND DURING PERFORMING SB 747-53A2450.(<P>ACCOMPLISHED IAW EI NO T2022A53M-355 REV. 1. JOB COMPLETED AND CONDITION CHECK NORMAL</P>)

Part: NONE — NONE · airframe 89,383 hrs · 15,011 cycles

CRACK ON SIDE ANGLES OF NOSE WHEEL WELL TOP PANEL ASSY NEAR STA 300, LBL 30, WL 190.(<P>ACCOMPLISHED EI NO T2022A53M-087 REV 1. CONDITION CHECK NORMAL AND JOB COMPLETED.</P>)

Part: ANGLE — NONE · corrosion level 2 · airframe 89,383 hrs · 15,011 cycles

CORROSION - BRACKET, FWD WING TO BODY FAIRING INTERNAL BRACKET STA 977 TO STA 982 LBL 3.(<P>REMOVED DAMAGE PART IAW SRM 51-40-02 REV 93. INSTALL NEW PART IAW SRM 51-40-02 REV 93 AND BOEING DWG NO 65B06976 SH 2 REV G. JOB COMPLETED AND CONDITION CHECK NORMAL.</P>)

Part: NONE — NONE · corrosion level 2 · airframe 89,383 hrs · 15,011 cycles

FOUND CORROSION DAMAGE ON MAIN DECK FLOOR BEAM UPPER CAP AT STA 2040 BETWEEN RBL 75.92 AND RBL 98.58(<P>REMOVED DAMAGED PARTS IAW SRM 51-40-02 REV 93. REPAIRED THE DAMAGED AREA IAW SRM 53-00-551-2R-3 REPAIR 3 REV 93 AND EI NO T2022A53M-224 REV 1. INSTALL FASTENERS IAW SRM 51-40-02 REV 93 AND DWG NO 65B38251 SH6 REV A, SH35 REV A AND 65B38102 SH9 REV -, SH10 REV -, SH11 REV A, AND 65B38740 SH5 REV A AND 65B38288 SH4 REV B. JOB COMPLETED AND CONDITION CHECK NORMAL.</P>)

Part: NONE — NONE · airframe 89,383 hrs · 15,011 cycles

REPAIR - CORROSION DAMAGES ON INNER SURFACED OF FUSELAGE SKIN DURING PERFORMING INSPECTION PER SB 747-53A2878(<P>ACCOMPLISHED THE EI NO T2022A53M-199 REV 1. JOB COMPLETED AND CONDITION CHECK NORMAL.</P>)

Part: NONE — NONE · corrosion level 2 · airframe 89,383 hrs · 15,011 cycles

CORROSION DAMAGES ON MAIN - DECK OUTBD FLOOR PANEL SUPPORT BETWEEN STA 1900 AND STA 1920, RBL 117.(<P>ACCOMPLISHED THE REPAIR IAW EI NO T2022A53M-083 REV 2. CONDITION CHECK NORMAL AND JOB COMPLETED.</P>)

Part: NONE — NONE · corrosion level 2 · airframe 89,383 hrs · 15,011 cycles

CORROSION WAS FOUND ON THE UPPER CAP (P/N 65B04352-167) OF MAIN DECK FLOOR STRUCTURE AT STA 2300 LBL 56(<P>ACCOMPLISHED EI NO T2022A53M-203 REV 1. JOB COMPLETED AND CONDITION CHECK NORMAL.</P>)

Part: NONE — NONE · airframe 89,383 hrs · 15,011 cycles

CHAFING - SKIN, RH WING INBD AILERON TE OUTBD CAP.(<P>PERFORM PERMANENT REPAIR AT RH WING INBD AILERSON TE OUTBD CAP. REPAIR PROCESS REFER TO EGAT J/C ATTACHING SHEET NO 0345885. CONDITION CHECK IS SATISFACTORY.</P>)

Part: NONE — NONE · airframe 89,383 hrs · 15,011 cycles

CRACK ON SIDE ANGLES OF NOSE WHEEL WELL TOP PANEL ASSY NEAR STA 300 AND STA 320, RBL 30, WL 190.(<P>ACCOMPLISHED EI NO T2022A53M-088, REV 1. CONDITION CHECK NORMAL AND JOB COMPLETED.</P>)

Part: ANGLE — NONE · corrosion level 2 · airframe 89,383 hrs · 15,011 cycles

CORROSION DAMAGE WAS FOUND ON ANGLE (P/N 65B04351-334) OF M/D CGO FLOOR STRUCTURE AT STA 2280, RBL 49(<P>REMOVED DAMAGED ANGLE IAW SRM 51-40-02 REV 93. FABRICATE NEW ANGLE IAW EI NO T2022P53M-188 REV 0. INSTALL NEW ANGLE IAW SRM 51-40-02 REV 93 AND DWG 65B04351 SH 24 REV A AND DWG 457U1061 SH6 REV A. CONDITION CHECK NORMAL AND JOB COMPLETED.</P>)

Part: INTERCOSTAL — NONE · corrosion level 2 · airframe 89,383 hrs · 15,011 cycles

CORROSION DAMAGE WAS FOUND ON INTERCOSTAL (P/N 146U3014-3) OF AFT CGO COMPARTMENT NEAR S-38R AND STA 1975(<P>REMOVE THE DAMAGED PARTS IAW SRM 51-40-02 REV 93. FABRICATION NEW PART IAW EI NO T2022P53M-357 REV 0. INSTALL NEW PART IAW DWG NO 65B04652 SH1 REV J, SH2 REV D, 453U1379 SH5 REV B, 65B04153 SH13 REV B, 146U3009 SH4 REV D, 65B15813 SH2 REV C AND SRM 51-40-02 REV 93. CONDITION CHECK NORMAL AND JOB COMPLETED.</P>)

Part: NONE — NONE · corrosion level 2 · airframe 89,383 hrs · 15,011 cycles

CORROSION ON WING TO BODY FAIRING SUPPORT CHORD AT STA 987, RBL 6.(<P>REMOVED FASTENERS IAW SRM 51-40-02, REV 93. REPAIR SUPPORT CHORD IAW EI NO T2022A53M-151 REV 1. INSTALL FASTENERS IAW SRM 51-40-02 REV 93 AND BOEING DWG NO 149U7200 SHEET 8 REV C. COND CHK NORMAL AND JOB COMPLETED.</P>)

Part: NONE — NONE · airframe 89,383 hrs · 15,011 cycles

REPAIR - CRACK DAMAGE ON A FASTENER HOLE OF RH AFT INNER CHORD OF STA 2598 BULKHEAD AT RBL 37, WL 267(<P>REMOVED AFFECTED FASTENERS IAW SRM 51-40-02 REV 93. REPAIRED DAMGED AREA IAW EI NO T2022A53M-139 REV 2. INSTALL FASTENER IAW SRM 51-40-02 REV 93 AND DWG NO 65B02505 SH 07, REV 1. JOB COMPLETED AND CONDITION CHECK NORMAL.</P>)

Part: NONE — NONE · airframe 89,383 hrs · 15,011 cycles

FOUND EXISTING REPAIR DOUBLER ON FUSELAGE SKIN AT STA 1520 - 1540, S-43L - S-44L.(<P>EXISTING REPAIR DOUBLER WAS COVERED BY EI NO T2022A53M-296 REV 2. REFER RAM FORM N408MC-22-24 ISSUE.</P>)

Part: SKIN — DENTED · airframe 88,290 hrs · 14,827 cycles

FUSELAGE SKIN DENT BS 618 S-3L, 1.25" DIAMETER. INSTALLED EXTERNAL DOUBLER BS 613-624 AT S-3L

Part: WARNING MESSAGE — FALSE ACTIVATION (THRUST REVERSER) · airframe 86,752 hrs · 14,558 cycles

DURING INITIAL TAKE OFF ROLL EICAS MSG" ENG 2 REVERSER". PERFORMED LOW SPEED REJECT (&LT;80KTS). ON DIRECTION FROM MX CNTL, RETURNED TO BLOCKS(<P>PERF HIGH ENERGY STOP INSPECTION PER AMM 05-51-10. NO DEFECTS NOTED, AND PLACED #2 TR ON MEL MDDR 145762</P>)

Part: SMOKE DETECTOR — FALSE ACTIVATION (CREW REST) · airframe 85,740 hrs · 14,385 cycles

CREW REST SMOKE ALARM SOUNDED IN FLIGHT, NO SIGNS OF SMOKE. CREW VERIFIED NO SMOKE OR FUMES AND SILENCED THE ALARM. CONTINUED TO ANC THE SCHEDULED DESTINATION. MX FOUND A BAD DETECTOR AND DEACTIVATED IT AND PLACED ON DEFERRAL NR 141651 IAW MEL 26-14-02-01-02, LP 1338218: R & R LT BULK SMOKE DETECTOR. OPS CHECK OK MM 26-14-51. DMI 141651 IS CLOSED.

Part: SMOKE DETECTOR — FALSE ACTIVATION (CREW REST AREA) · airframe 85,464 hrs · 14,338 cycles

SMOKE CREW REST EICAS MESSAGE LEFT SIDE ALARM ONLY TO SOUND. CLEANED THE CREW REST SMOKE DETECTOR AND DETECTION SYSTEM, TEST OK PER AMM 26-14-20.

Part: SPLICE — CRACKED (BS 939-991) · airframe 81,911 hrs · 13,730 cycles

RHS BS 980 TO 990 STR 38R DRAG SPLICE FTG AREA ONE EACH FASTENER HOLE FOUND CRACK AND CORROSION AT SKIN LAYER.(<P>FUSELAGE SKIN IS REPAIRED AS PER SRM 53-20-01-2R-2 REPAIR 2 FIG 201 AT BS 939.5 TO BS 991.5 BETWEEN STR 37R-39R. THIS REPAIR IS A CATEGORY B REPAIR. SUPPLEMENTAL INSPECTION IS REQUIRED AS PER SRM 53-20-01-2R-2 REPAIR 2 FIG 201 TABLE III.</P>)

Part: SPLICE — CRACKED (BS 939-991) · airframe 81,911 hrs · 13,730 cycles

LHS BS 980 TO 990 STR 38R DRAG SPLICE FTG AREA ONE EACH FASTENER HOLE FOUND CRACK AND CORROSION AT SKIN LAYER.(<P>FUSELAGE SKIN IS REPAIRED AS PER SRM 53-20-01-2R-2 REPAIR 2 FIG 201 AT BS 939.5 TO 991.5 BETWEEN STR 37L-39L. THIS REPAIR IS A CATEGORY B REPAIR. SUPPLEMENTAL INSPECTION IS REQUIRED AS PER SRM 53-20-01-2R-2 REPAIR 2 FIG 201 TABLE III REV 87- 20OCT2019.</P>)

Part: FLOOR SUPPORT — CRACKED (CARGO BAY) · airframe 81,911 hrs · 13,730 cycles

BULK CARGO COMP-FLOOR SUPPORT FOUND CRACKED AT STA 2080 CTR AREA(<P>BULK CARGO COMP STA 2080 RBL 0.625" FLOOR SUPPORT CRACK AREAS REPAIRED IAW RI-53-60-13921 REV A</P>)

Part: GUIDE — CRACKED (BS 880-900) · airframe 81,911 hrs · 13,730 cycles

FWD CARGO STA 880-900 LH SIDE GUIDE RAIL FOUND CRACKED.(<P>FWD CARGO STA 880-900 LH SIDE GUIDE RAIL CRACK AREA REPAIRED IAW RI-53-00-13925 REV A.</P>)

Part: SEAT TRACK — CORRODED (BS 1830) · airframe 81,911 hrs · 13,730 cycles

M/D STA 1830 LBL 98.58" SEAT TRACK CROWN FOUND CORROSION(<P>M/D STA 1830 LBL 98.58" SEAT TRACK CROWN CORROSION REMOVED AND RE-PROTECTED IAW SRM 51-10-02 AND SRM 51-20-01. CHECK WITHIN SRM 53-00-52-1A-1 ALLOWABLE LIMIT.</P>)

Part: FLOOR PANEL — PUNCTURED (CARGO) · airframe 81,911 hrs · 13,730 cycles

BULK CARGO-STA 1980-2044 CENTER FLOOR PANEL FOUND PUNCH HOLE DAMAGED.(<P>BULK CARGO COMP STA 2026.5 LBL11" FLOOR PANEL PUNCTURE REPAIRED IAW RI-25-54-13919 REV A</P>)

Part: FLOOR SUPPORT — CRACKED (CARGO BAY) · airframe 81,911 hrs · 13,730 cycles

BULK CARGO COMP-FLOOR SUPPORT FOUND CRACKED AT STA 2080 RBL 7.625"(<P>BULK CARGO COMP STA 2080 RBL 7.625" FLOOR SUPPORT CRACK AREAS REPAIRED IAW RI-53-60-13921 REV A</P>)

Part: SKIN — CORRODED (BS 1700-1741) · corrosion level 2 · airframe 81,911 hrs · 13,730 cycles

SKIN AT LOWER LOBE CIRCUMFERENTIAL SPLICE LOCATION AT STA 1720 TO STA 1741 S45L 3 EA AREA FOUND CORROSION INDICATION.(<P>FUSELAGE SKIN BETWEEN STA 1720 TO STA 1740 STR 45L CORROSION AREAS REPAIRED IAW RI 53-00-13922 REV A.</P>)

Part: SEAT TRACK — CORRODED (BS 1810-1820) · airframe 81,911 hrs · 13,730 cycles

M/D STA 1810-1820 LBL 98.58" SEAT TRACK CROWN FOUND CORROSION(<P>M/D STA 1810-1820 LBL 98.58" SEAT TRACK CROWN CORROSION REMOVED AND RE-PROTECTED IAW SRM 51-10-02 AND SRM 51-20-01. CHECKED WITHIN SRM 53-00-52-1A-1 ALLOWABLE LIMIT.</P>)

Part: WEB — CRACKED (LT WING SPOILER) · airframe 81,911 hrs · 13,730 cycles

LHW O/B OF #5 SPOILER CONTACT SUPPORT WEB FOUND CRACKED(<P>LHW O/B OF #5 SPOILER CONTACT SUPPORT WEB CRACK P/N: 65B10865U26 FABRICATED AND REPLACED IAW RI-57-70-13928 REV A</P>)

Part: SKIN — CORRODED (FLAP) · airframe 81,911 hrs · 13,730 cycles

#26E V/C FLAP BULLNOSE EXTERIOR FOUND PITTING.(<P>RHW #26E V/C FLAP BULLNOSE EXTERIOR SKIN DAMAGED AREA REPAIRED IAW SRM 57-43-02-2R-2 REPAIR 2 FIG 201 DETAIL II.</P>)

Part: SKIN — CHAFED (FLAP) · airframe 81,911 hrs · 13,730 cycles

#7 V/C FLAP BULLNOSE EXTERIOR AREA FOUND CHAFING MARK.(<P>LHW #7 V/C FLAP BULLNOSE EXTERIOR SKIN DAMAGED AREA REPAIRED IAW RI-57-44-13920 REV A</P>)

Part: COOLING FAN — FAILED (COCKPIT) · airframe 81,419 hrs · 13,599 cycles

STRONG BURNING ODOR IN FLIGHT DECK AND MCD AREA, REPORTED BY CREW.(<P>REMOVED AND REPLACED GALLEY VENT FAN IAW AMM 21-58-01, OPS CHECK GOOD.</P>)

Part: GARLOCK SEAL — LEAKING (NR 1 ENGINE) · airframe 81,018 hrs · 13,538 cycles

ENGINE 1 OIL QTY DECREASED TO 1 IN FLIGHT.(<P>REMOVED AND REPLACED&NBSP;ENG 1 STARTER GARLOCK SEAL AND LEAK CHECKS GOOD PER AMM 72-64-01.</P>)

Part: LAMP — INOPERATIVE (EMERGENCY LIGHT) · airframe 78,173 hrs · 13,113 cycles

EMERGENCY CEILING LIGHT IN CREW REST COMPARTMENT INOP.(<P>RELAMPED CREW REST CEILING EMERGENCY LIGHT</P>)

Part: FLOORBEAM — CORRODED (BS 1960) · airframe 75,184 hrs · 12,577 cycles

CORROSION DAMAGE ON THE UPPER CAP OF MAIN DECK FLOORBEAM AT BS 1960, LBL 5 AND 21. REPAIRED IAW EI T2018A53M-933, REV 1, AND SRM 53-00-51-2R-3, REPAIR 3, REV 82. CHECKED NORMAL.

Part: ANGLE — CRACKED (RT WING) · airframe 75,184 hrs · 12,577 cycles

CRACK ON THE UPPER ANGLE OF THE RT WING FIXED T/E BEAM NEAR WBL 429. REPAIRED IAW EI T2018 A57M-926, REV 2, AND DWG 65B11630, SHEET 2, REV L, 65B07738 SH7, REV L. CHECKED NORMAL.

Part: FLOORBEAM — CORRODED (BS 860) · airframe 75,184 hrs · 12,577 cycles

CORROSION DAMAGE AT UPPER CAP OF MAIN DECK FLOORBEAM AT BS 860, BL 0. REPAIRED IAW EI T2018A53M-936, REV 1, AND SRM 53-00-51-2R-3, REPAIR 3, REV 82. CHECKED NORMAL.

Part: SUPPORT FITTING — CRACKED (NR 6 SPOILER) · airframe 75,184 hrs · 12,577 cycles

CRACK ON THE NR 6 SPOILER SUPPORT FITTING, OTBD LOWER FORWARD FLANGE. ACCOMPLISHED EI T2018A57M-825, REV 1. CHECKED NORMAL.

Part: SEAT TRACK — CORRODED (BS 1660-1700) · corrosion level 2 · airframe 75,184 hrs · 12,577 cycles

CORROSION FOUND ON THE MAIN DECK FLOOR SEAT TRACK BETWEEN BS 1660 AND 1700. LBL 11.33. ACCOMPLISH EI T2018A53M-877, REV 1. CHECKED NORMAL.

Part: POWER SUPPLY — INOPERATIVE (EMERGENCY LIGHTS) · airframe 75,184 hrs · 12,577 cycles

FOUND THE POWER SUPPLY FOR THE EMERGENCY LIGHTS M5168, CAPACITY FUNCTION NOT GOOD IAW AMM 33-51-04-002-009-001 & 33-51-04-402-012-001 REV 91. REPLACED EMERGENCY LIGHT POWER SUPPLY M5168 AND CONDITION CHECKED NORMAL. IAW AMM 33-51-021-202-012-001 REV 91. PERFORMED POWER SUPPLY TEST AND THE RESULT WAS SATISFACTORY.

Part: FEEDER CABLE — DAMAGED (WW LIGHT) · airframe 75,184 hrs · 12,577 cycles

FOUND THE W4809 POWER FEEDER WIRE DAMAGE IAW WDM 24-51-73, REV 42, & SWPM 20-50-00, 20,30-11, REV 67. REPLACED FEEDER CABLE AND CHECKED NORMAL IAW AMM 33-31-00-705-012, REV 91. PERFORMED THE MAIN WHEEL WELL LIGHT, TESTED AND FOUND SATISFACTORY.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 74,202 hrs · 12,397 cycles

UPPER DECK EMERGENCY LIGHTS INOPERATIVE IN THE CREW REST AREA AND JUST FWD OF CREW REST. REMOVED AND REPLACED THE BATTERY PACK MS169 IAW MM 33-51-04-902-001-001. OPS CHECKED GOOD IAW MM 33-51-04-712-006-001.

Part: SKIN — CRACKED (BS 1714-1717) · airframe 73,269 hrs · 12,232 cycles

ON WALK AROUND INSPECTION, FOUND A CRACK IN THE SKIN, LEFT SIDE OF FUSELAGE LBL 62, WL 106, BS 1714 TO 1717. ACCOMPLISHED A SKIN REPAIR IAW EO 4453A947.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 70,301 hrs · 11,620 cycles

EMERGENCY LIGHT AT UPPER DECK SIDE DOOR AFT SILL INOPERATIVE. TRANSFER TO MDDR 68924, MEK 33-51-01, CAT C.

Part: ACTUATOR — MALFUNCTIONED (RT BLG) · airframe 69,195 hrs · 11,354 cycles

AFTER TAKEOFF EICAS MSG, GEAR DOOR, REF ITEM 1, 3 & 4. REPLACED RT BODY GEAR ACTUATOR & SEQUENCE VLV IAW 32-33-27 & 32-37-02. RESET & RIG BODY GEAR ALT EXTEND SYS 33-35-00.

Part: SEAT TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 68,985 hrs · 11,299 cycles

FOUND MD SEAT TRACK CORROSION AT STATION 605, RBL 11.33 & STATION 612, RBL 1133. ACCOMPLISHED EI NR T2016A53B-B2 REV 2. ORIGINAL EI NR T 2016A53B-B2 REV 2 ATTACHED WITH NRC 803. JOB COMPLETED & COND CHECKED NORMAL.

Part: FITTING — CORRODED (FUSELAGE) · corrosion level 2 · airframe 689,985 hrs · 11,299 cycles

CORROSION FLOOR FITTING FWD CARGO CEILING PANEL FLOOR FITTING CORROSION, STATION 780, LBL 33. REPLACED THE DAMAGED PART WITH NEW PART IAW SRM 51-40-02 REV 75. JOB COMPLETED & COND CHECKED NORMAL.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 68,985 hrs · 11,299 cycles

FOUND MD FLOORBEAM CORROSION AT STATION 2240, LBL 69 - 86. REPAIRED DAMAGED AREA IAW SRM 53-00-51 REPAIR 3 & REV 75. JOB COMPLETED & CORROSION CHECKED NORMAL.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 68,985 hrs · 11,299 cycles

FOUND MD FLOORBEAM CORROSION AT STATION 800, RBL 100 - 101. REPAIRED DAMAGED AREA IAW SRM 53-00-51 REPAIR 3 REV 75. JOB COMPLETED & COND CHECKED NORMAL.

Part: SEAT TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 68,985 hrs · 11,299 cycles

FOUND MD SEAT TRACK CORROSION AT STATION 870, RBL 11.33. ACCOMPLISHED EI NR T 2016A53B-132 REV 2. ORIGINAL EI NR T 2016A53B-132 REV 2 ATTACH WITH NRC 803. JOB COMPLETED & COND CHECKED NORMAL.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 68,985 hrs · 11,299 cycles

FOUND MD FLOORBEAM CORROSION AT STATION 2140, LBL 92 - 97. REPAIRED DAMAGED AREA IAW 53-00-51 REPAIR 3 REV 75. JOB COMPLETED & COND CHECKED NORMAL.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 68,985 hrs · 11,299 cycles

FOUND MD SUB SEAT TRACK CRACK, STATION 1484 RBL 75. REPAIRED DAMAGE AREA IAW SRM 53-00-52-2R-13 REV 75. JOB COMPLETED & CORROSION CHECKED NORMAL.

Part: SEAT TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 68,985 hrs · 1,129,953 cycles

FOUND MD SEAT TRACK CORROSION, AT STATION 545, LBL 11.33 & STATION 620, LBL 11.33. ACCOMPLISHED EI NR T2016A53B-B2 REV 2. ORIGINAL EI NR T2016A53B-B2 REV 2 ATTACH WITH NRC 803. JOB COMPLETED & CHECKED NORMAL.

Part: TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 68,985 hrs · 11,299 cycles

FOUND MD TRACK CORROSION AT STATION 2297, RBL 11.33. ACCOMPLISHED EI NR T 2016A53B-181 REV 1. JOB COMPLETED & COND CHECKED NORMAL.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 68,985 hrs · 11,299 cycles

FOUND MD FLOORBEAM CORROSION AT STATION 980, RBL 83 - 87. REPAIR DAMAGED AREA IAW SRM 53-00-51 REPAIR 3 REV 75. JOB COMPLETED & COND CHECKED NORMAL.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 68,985 hrs · 11,299 cycles

FOUND MD FLOORBEAM CORROSION AT STATION 860, LBL 50 - 51 & RBL 83.5 - 101.5. REPAIR DAMAGED AREA IAW SRM 53-00-51 REPAIR 3 REV 75. JOB COMPLETED & COND CHECKED NORMAL.

Part: SEAT TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 68,985 hrs · 11,299 cycles

CORROSION SEAT TRACK, MD SEAT TRACK CORROSION, STATION 865, LBL 11.33. ACCOMPLISHED EI NR T 2016A53B-B2 REV 2. JOB ACCOMPLISHED & COND CHECKED NORMAL.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 68,985 hrs · 11,299 cycles

FOUND MD FLOORBEAM CORROSION AT STATION 840, RBL 88 - 91. REPAIRED DAMAGED AREA IAW SRM 53-00-51 REPAIR 3 & REV 75. JOB COMPLETED & COND CHECKED NORMAL.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 68,985 hrs · 11,299 cycles

FOUND MD SUB SEAT TRACK CRACK AT STATION 1000, LBL 75. REPAIRED DAMAGED AREA IAW SRM 53-00-52-2R-13 & REV 75. JOB COMPLETED & CONDITION CHECKED NORMAL.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 68,985 hrs · 11,299 cycles

FOUND MD FLOORBEAM CORROSION AT STATION 640, LBL 103. REPAIRED DAMAGE AREA IAW SRM 53-0051 REPAIR 3 REV 75 & EI NR T2016A 53B-142 REV 1. JOB COMPLETED & CORROSION COND CHECKED NORMAL.

Part: SEAT TRACK — CRACKED (FUSELAGE) · airframe 68,985 hrs · 11,299 cycles

FOUND MD SUB SEAT TRACK CRACK, STATION 1484, LBL 75. REPAIRED DAMAGE AREA IAW SRM 53-00-52-2R-13 REV 75. JOB COMPLETED & COND CHECKED NORMAL.

Part: STRUCTURE — CRACKED (FUSELAGE) · airframe 68,985 hrs · 11,299 cycles

CRACK ON AFT CARGO DOOR CUT OUT, FWD UPPER CORNER. REPAIR ON AFT CARGO DOOR CUT OUT, FWD UPPER CORNER IAW SRM 53-60-01 REPAIR 3 & 51-40-04 REV 75 & EI NR T 2016A53B-141 REV 2. COND CHECKED NORMAL & JOB COMPLETED.

Part: SEAT TRACK — CRACKED (FUSELAGE) · airframe 68,985 hrs · 11,299 cycles

CRACK FOUND MAIN DECK CARGO SUB SEAT TRACK CRACKED, AT STATION 980 - 1000, RBL 75. REPAIR DAMAGED AREA IAW SRM 53-00-52-2R-13 REV 75. JOB COMPLETED & COND CHECKED NORMAL.

Part: HINGE — CRACKED (RAM AIR DOOR) · airframe 68,986 hrs · 11,300 cycles

AIR RETURN, BANGING & VIBRATION FELT IN COCKPIT, ORIGINATING FROM LOWER FUSELAGE BENEATH STATION 1000. POST FLIGHT REVEALED DAMAGE TO NR 3 PACK INLET DOOR. CHECKED & FOUND THE PACK NR 3 RAM AIR INLET DOOR HINGE CRACKED. REPLACED THE RAM AIR INLET DOOR IAW AMM 21-62-02. REPLACED THE RAM AIR INLET DOOR ACTUATOR IAW AMM 21-62-03. PERFORMED THE PTC A & B GND TEST FOR THE NR 3 PACK RAM AIR INLET DOOR & ACTUATOR & ALL TESTED SATISFACTORY.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 68,028 hrs · 11,075 cycles

L1 DOOR EMER LIGHT INOPERATIVE. RELAMPED L1 DOOR EMER LIGHT. OPERATIONS CHECKED OK IAW AMM 33-51-05.

Part: OIL SYSTEM — LOW PRESSURE (NR 3 ENGINE) · airframe 67,650 hrs · 10,988 cycles

NR 3 ENGINE SHUTDOWN FOR LOW OIL QTY, 1 QT AT SD. FIRE WARNING SWITCH NOT PULLED, POS OIL P CONTINUED WITH ENG WIND MILLING. NR 3 ENGINE REPLACED IAW AM 71-00-02-004-001.

Part: UNKNOWN — MALFUNCTIONED (LANDING GEAR) · airframe 67,400 hrs · 10,936 cycles

REJECTED TAKEOFF. ON BRAKE RELEASE THE ACFT IMMEDIATELY TURNED TO THE RT & ACFT STOPPED & CONFIG GEAR, EICAS MSG DISPLAYED. PERFORMED LG & VISUAL INSPECTION. CHECKED NOSE WHEEL STEERING. OPERATIONS NORMALLY IAW MM 32-51-00. NO FAULTS NOTED.

Part: ENGINE — FAILED (NR 1) · airframe 67,107 hrs · 10,866 cycles

DURING TAKEOFF ROLL & CLIMB OUT, NR 1 ENGINE SURGED +/- 3-4 PERCENT N1 WITH 50 DEGREE INCREASE IN EGT. ACCOMPLISHED CHECK LIST. ENG 1 STABILIZED AT CRUISE. STATUS MESSAGE, NR 1 ENGINE CONTROL. BORESCOPE INSPECTION ACCOMPLISHED IAW AMM 72-00-00-206-001-J00. FOUND MULTIPLE BLADES WITH DAMAGED LE, BENT, TEARS & MID-SPAN SHROUD SHINGLING & CONTACT WITH GUIDE VANES, DAMAGE OUT OF LIMITS. MAX POWER ASSURANCE TEST ACCOMPLISHED IAW EO 1972A568.

Part: DOOR — DAMAGED (CARGO BAY) · airframe 65,908 hrs · 10,639 cycles

LOWER AFT CARGO DOOR, LOWER AFT CORNER DAMAGED. DAMAGED AREA DRESSED IAW EO 1952A135 FAA 8110-3 DATED 03 DEC 14. HFEC ACCOMPLISHED WITH NO CRACKS FOUND. REPEAT INSPECTION REQUIRED EVERY 25FC & A PERMANENT REPAIR TO BE ACCOMPLISHED PRIOR TO 1000FH.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 65,367 hrs · 10,518 cycles

L1 AFT DOOR SILL EMER LIGHT INOPERATIVE. R & R L1 AFT DOOR SILL EMER LAMP. OPERATIONS CHECKED NORMAL IAW AMM 33-51-05.

Part: WARNING SYSTEM — FALSE ACTIVATION (COCKPIT) · airframe 64,524 hrs · 10,331 cycles

ON TAKEOFF EICAS MSG DOOR AFT CARGO APPEARED. MSG REMAINED UNTIL DOOR WAS RESET ON GND. ON INSPECTION FOUND DOOR LATCHED & LOCKED. TRANSFERRED TO MDDR 49245 MEL 52-73-01.

Part: CONTROL MODULE — MALFUNCTIONED (RUDDER) · airframe 64,330 hrs · 10,282 cycles

DURING CONTROL CHECK, RUDDER SHUDDERS & SHAKES, ACFT LT & RT PEDAL DEFLECTION. R & R THE UPPER RUDDER POWER CONTROL MODULE IAW MM 27-21-17. PERFORMED OPERATIONAL TEST, ALL CHECKED GOOD, NO VIBRATION FELT, OK FOR SERVICE.

Part: ACTUATOR — FAULTY (LT BLG TRUCK) · airframe 64,128 hrs · 10,238 cycles

GEAR MONITOR STATUS MSG, ITEM 2, & GEAR TILT STATUS MSG, EICAS MSG, ITEM 3 LT BODY GEAR TRUCK POSITIONING HYD FUSE REPLACED IAW MM 32-13-15. LT BODY GEAR TRUCK POSITIONING ACTUATOR REPLACED IAW MM 32-13-15 & FUNCTIONAL CHECKED OK.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 63,550 hrs · 10,114 cycles

MAIN DECK STATION 1180 RBL 98 - 108 BELOW FLOOR, INTERCOSTAL FOUND CRACK. INTERCOSTAL REPLACED IAW R1-53-41-10445.

Part: SKIN — CRACKED (FUSELAGE) · airframe 63,550 hrs · 10,114 cycles

FX EXTERNAL SKIN STATION 1718, STRINGER 41L FOUND CORROSION CRACK. SKIN REPAIR CARRIED OUT IAW SRM 53-00-01 REPAIR 1.

Part: SKIN — CRACKED (FUSELAGE) · airframe 63,550 hrs · 10,114 cycles

FX EXTERNAL SKIN STATION 1715, STRINGER 45L FOUND CORROSION CRACK. SKIN REPAIR CARRIED OUT IAW SRM 53-00-01 REPAIR 1.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 63,550 hrs · 10,114 cycles

MAIN DECK STATION 1180, LBL 98 - 108 BELOW FLOOR, INTERCOSTAL FOUND CRACK. INTERCOSTAL REPLACED IAW R1-53-41-10445.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 63,550 hrs · 10,114 cycles

MAIN DECK STATION 1200, RBL 98 - 108 BELOW FLOOR, INTERCOSTAL FOUND CRACK. INTERCOSTAL REPLACED IAW R1-53-41-10446.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 63,550 hrs · 10,114 cycles

MAIN DECK STATION 1200, LBL 98 - 108 BELOW FLOOR INTERCOSTAL FOUND CRACK. INTERCOSTAL REPLACED IAW R1-53-41-10446.

Part: DOOR — DAMAGED (MLG) · airframe 58,000 hrs · 9,127 cycles

DURING WALKAROUND INSPECTION, MX FOUND THE LT WING LANDING GEAR SHOCK STRUT OTBD DOOR T/E DELAMINATED, WITH AREA OF MISSING MATERIAL 2.5" X 23.0" ON AFT EDGE AND AREA OF DELAMINATION ON INSIDE SKIN 3.5" X 13.0" (REF FIG 1). DAMAGE FOUND TO BE BEYOND THE SRM 52-80-02, FIGURE 101 ALLOWABLE DAMAGE 4 LIMITS IAW SRM 51-70-02, FIG 101 ALLOWABLE DAMAGE GENERAL. PERFORMED A TIME LIMITED REPAIR IAW SRM 51-70-17 OR SRM 51-70-07.

Part: SKIN — DENTED (BS 1520-1540) · airframe 56,939 hrs · 8,939 cycles

BS 1520 - 1540 STR 43L-44L SKIN DENTED. REPAIRED IAW SRM 53-00-01. REPAIR 1 FIG 201.

Part: CHANNEL — CRACKED (BS 760) · airframe 56,939 hrs · 8,939 cycles

BS 760 RT TENSION TIE AFT CHANNEL 1 EA HOLE CRACKED APPROX 0.040", STA 760 RT TENSION TIE AFT CHANNEL 1 EA CRACKED FASTENER HALF REPAIRED IAW SB 747-53-2502 REV 1, FIG 11.

Part: CHANNEL — CRACKED (BS 740) · airframe 56,939 hrs · 8,939 cycles

STA 740 LT AFT TENSION TIE CHANNEL 1 EA HOLE CRACKED APPROX 0.040 (M/D STA 740 LT AFT TENSION TIE 1 EA HOLE CRACK AREA REPAIRED IAW SB 747-53-2502, REV 1, FIG 11.

Part: DOOR — DAMAGED (MLG)

DURING WALKAROUND INSP, MX FOUND THE LT WING GEAR DOOR FAIRING - LOWER EDGE CRACKED, MEASURING 7.0 IN. X 2.0 IN. (REF FIG 1) DAMAGE FOUND TO BE BEYOND THE SRM 52-80-02, FIG 101 ALLOWABLE DAMAGE 4 LIMITS IAW SRM 51-70-02, FIG 101 (SHEET 9 OF 41) ALLOWABLE DAMAGE GENERAL. (DISPOSITION WAS MADE TO PERFORM A TIME LIMITED REPAIR AS DESCRIBED IN PART 1 WORK INSTRUCTIONS, SCHEDULE REPEAT INSPECTIONS AT EVERY 5 FC (FLIGHT CYCLES) AND PERMANENT REPAIR PRIOR TO THE ACCUMULATION OF 1,000 FH (FLIGHT HOURS) AFTER PART 1 HAS BEEN ACCOMPLISHED AFTER PART 1 IAW SRM 51-70-17 OR SRM 51-70-07.)

Part: SKIN — PUNCTURED (THRUST REVERSER) · airframe 5,500 hrs · 8,595 cycles

DURING WALKAROUND, MX FOUND THE NR 4 RT THRUST REVERSER CORE COWL HAS 2 PUNCTURES IN THE SKIN LOCATED ABOVE THE ACCESS PANEL AND BLOWOUT DOOR. DAMAGE TO THE ACCESS PANEL AND BLOWOUT DOOR HINGES, LATCHES AND LANYARDS. REPAIRED.

Part: SLEEVE — CRACKED (EXHAUST NOZZLE) · airframe 54,858 hrs · 8,568 cycles

DURING MX WALKAROUND, FOUND A CRACK ON THE EXHAUST NOZZLE OUTER SLEEVE, BETWEEN APPROX THE 9 TO 12 O'CLOCK POSITION ON THE NR 3 ENGINE. THE CIRCUMFERENTIAL CRACK IS APPROX 11" LONG AND IS JUST IN FRONT OF NAC STA 349.236. IAW SRM 54-41-30 THE LENGTH OF THE CRACK IS OUT OF LIMIT. STOP DRILLED ENDS OF THE CRACK WITH A 0.125" DIAMETER HOLE.

Part: SKIN — DAMAGED (THRUST REVERSER) · airframe 54,760 hrs · 8,552 cycles

DURING MX WALKAROUND, MX FOUND DAMAGE TO THE NR 2 ENG RT THRUST REVERSER TRANSLATING COWL EXTERNAL SKIN OUTER FINISH DAMAGE. THE DAMAGE IS LOCATED IN NEAR THE REVERSER COWL SKIN T/E (REF FIG 1-3): PERFORMED A TIME LIMITED REPAIR AS DESCRIBED IN PART 1 WORK INSTRUCTIONS.

Part: SKIN — DENTED (BS 1935 S38R) · airframe 53,242 hrs · 8,459 cycles

DURING LOADING, THE FUSELAGE SKIN AT BS 1935, S-38R WAS DENTED. THE DENT MEASURES 0.75 INCH WIDE BY 1.5 INCH LONG BY 0.0625 INCH DEEP. THERE IS ALSO A GOUGE IN THE DENT 0.003 INCH DEEP. (REMOVE THE GOUGE IN THE DENTED AREA IAW SRM 53-00-01, FIG 101, DETAIL II. PERFORM A DETAILED VISUAL INSP OF THE BLENDOUT AREA FOR CRACKS USING 10X MAGNIFICATION. ACCOMPLISH DETAILED INSP OF THE STRUCTURE INTERNALLY AND EXTERNALLY WITHIN 20 INCHES OF THE DENT IAW SRM 53-00-01, FIG 101, NOTE G. REPAIR THE SKIN DENT IAW SRM 53-00-01 OR OTHER APPLICABLE SRM REPAIR OR CONTACT ENGINEERING FOR REPAIR INSTRUCTIONS.)

Part: FAIRING — CRACKED · airframe 52,348 hrs · 8,152 cycles

DURING WALKAROUND INSP, MX REPORTED CRACK DAMAGE FOUND ON THE RT OTBD WBL1241 - L/E FIXED FAIRING. THE CRACK MEASURES 0.375 IN. LONG (REF FIG 1). THE CRACK EXCEEDS THE SRM 57-41-01, FIG 101, ALLOWABLE DAMAGE LIMITS. (DISPOSITION WAS MADE TO PERFORM TIME LIMITED REPAIRS AS DESCRIBED IN PART 1 WORK INSTRUCTIONS; FH (FLIGHT HOURS) IAW PART 2 AND PERMANENT REPAIR IAW PART 3 PRIOR TO 17JUL11.)

Part: SOLENOID — INOPERATIVE (MLG) · airframe 52,341 hrs · 8,310 cycles

GEAR LEVER WOULD NOT RETRACT. ACCOMPLISHED QRH PROCEDURES. AIR TURN BACK. (TROUBLESHOT TO BAD SOLENOID IN LANDING GEAR CONTROL PANEL. ITEM DEFERRED DDG 32-31-1)

Part: SKIN — DENTED (LT WING TE FLAP) · airframe 46,092 hrs · 7,161 cycles

DURING WALKAROUND INSP, MX REPORTED DENT DAMAGE FOUND ON THE LT OTBD FORE FLAP - WBL745 UPPER EXTERNAL SKIN PANEL. MEASURING 5.0 IN LENGTH X 3.125 IN. WIDTH & AMP; 0.625 IN. (REF FIG 1). THE DAMAGED AREA EXCEEDS THE SRM 57-53-01, FIG 101, ALLOWABLE DAMAGE 1 LIMITS. (DISPOSITION WAS MADE TO PERFORM TIME LIMITED REPAIR AS DESCRIBED IN PART 1 WORK INSTRUCTIONS; SCHEDULE REPEAT INSPECTIONS AT EVERY 25FC IAW PART 2 AND PERMANENT REPAIR IAW PART 3 PRIOR TO THE ACCUMULATION OF 4,000 FLIGHT HOURS AFTER PART 1.)

Part: SLEEVE — CRACKED (EXHAUST NOZZLE) · airframe 52,064 hrs · 8,103 cycles

DURING MX WALKAROUND OF N408MC MX FOUND A CRACK ON THE EXHAUST NOZZLE OUTER SLEEVE, STARTING AT APPROX THE 12 O'CLOCK POSITION ON THE NR3 ENGINE. THE CIRCUMFERENTIAL CRACK IS APPROX 16" LONG AND IS APPROX 13" FROM THE T/E OF THE NOZZLE. IAW SRM 54-41-30 THE LENGTH OF THE CRACK IS OUT OF LIMITS. (DISPOSITION IS TO STOP DRILL THE ENDS OF THE CRACK WITH A 0.098" DIAMETER HOLE, DVI EVERY 3 FLIGHT CYCLES; AND REMOVAL OF THE PART WITHIN 50 FC (FLIGHT CYCLES).

Part: SKIN — DAMAGED (RT WING) · airframe 51,950 hrs · 8,083 cycles

DURING WALKAROUND INSP, MX FOUND DAMAGE TO THE OTBD RT WS1585 - L/E NOSE EXTERNAL SKIN MEASURING 2.5 IN. L X 1.5 IN. W AND 0.125 IN. DEPTH (REF. FIG 1). DAMAGED AREA FOUND BEYOND THE SRM 57-41-01, FIG 101, DETAIL III ALLOWABLE DAMAGE (GENERAL) LIMITS. (DISPOSITION WAS MADE TO PERFORM TIME LIMITED REPAIR AS DESCRIBED IN PART 1 WORK INSTRUCTIONS, SCHEDULE REPEAT INSPECTIONS AT EVERY 5 (FLIGHT CYCLES) AFTER PART 2 AND PERMANENT REPAIR PRIOR TO THE ACCUMULATION OF 1,000 FH (FLIGHT HOURS) AFTER PART 1.)

Part: WEB — CRACKED (BS 1850) · airframe 51,730 hrs · 8,050 cycles

DURING WALK AROUND INSP, DAMAGE TO THE LOWER AFT CARGO COMPARTMENT - BS1850, LBL45.5 FLOOR WEB - CRACK/DAMAGE WAS FOUND MEASURING 2.0 IN. X 4.450 IN. (REF FIGURE 1). (DISPOSITION WAS MADE TO PERFORM A TIME LIMITED REPAIR AS DESCRIBED IN PART 1 WORK INSTRUCTIONS. SCHEDULE REPEAT INSPECTIONS AT EVERY 5 (FIVE) FC AND PERMANENT REPAIR PRIOR TO THE ACCUMULATION OF 1,000 FH (FLIGHT HOURS) AFTER PART 1.)

Part: SKIN — DENTED (CARGO DOOR) · airframe 51,711 hrs · 8,047 cycles

DURING WALKAROUND INSP, MX FOUND THE LWR LOBE - LWR AFT CARGO DOOR AT BS1817, LWR FWD CORNER AREA WITH A DENT/DAMAGE, MEASURING 12.5 IN. LONG X 0.150 IN. (REF FIG 1). THE DENT EXCEEDS THE SRM 52-30-01, FIG 101, DETAIL XI ALLOWABLE LIMITS. (DISPOSITION WAS MADE TO PERFORM A TIME LIMITED REPAIR AS DESCRIBED IN PART 1 WORK INSTRUCTIONS IAW SRM 51-10-02, SCHEDULE REPEAT INSPECTIONS AT EVERY 1,000 FH (FLIGHT HOURS) AND PERMANENT REPAIR PRIOR TO OR AT THE NEXT C-CHECK AFTER PART 1 HAS BEEN ACCOMPLISHED IAW SRM 52-30-01, FIG 201, REPAIR 2.)

Part: NOSE COWL — DENTED (NR 3 ENGINE) · airframe 51,295 hrs · 7,986 cycles

MX FOUND NR 3 ENGINE INLET NOSE COWL L/E DENTED AT APPROX 2 O' CLOCK POSITION MEASURING 12.0 INCHES IN LENGTH X 5.0 INCHES WIDTH AND 0.5 INCH DEPTH. AFTER DETAIL VISUAL INSP (10X MAGNIFYING GLASS) IT WAS VERIFIED THAT NO SHARP CREASES AND/OR CRACK CONDITION EXISTS. DISPOSITION WAS MADE TO PERFORM TIME LIMITED REPAIR AS DESCRIBED IN PART 1 WORK INSTRUCTIONS, INITIATE REPEAT INSPECTIONS PRIOR TO EACH FLIGHT AND SCHEDULE PERMANENT REPAIR PRIOR TO THE ACCUMULATION OF 25 FLIGHT CYCLES AFTER PART 1 BY R & R THE SUBJECT DAMAGED NOSE COWL IAW THE AMM 71-11-01 OR PERFORMING PERMANENT REPAIR IAW SRM 54-11-01, FIGURE 201, REPAIR 1 OR 2. PART 1 OF THIS EO ACCOMPLISHED TIME LIMITED REPAIR VIA FAA 8110-3 FORM ISSUED 24OCT10 SINCE THE DAMAGE EXCEEDS THE ALLOWABLE DAMAGE LIMITS IAW SRM 54-11-01 FIG 101, ALLOWABLE DAMAGE.

Part: NOSE COWL — DAMAGED (NR 3 ENGINE) · airframe 50,563 hrs · 7,864 cycles

DURING WALK AROUND INSP, IN MX, FOUND THE NR 3 ENGINE INLET NOSE COWL L/E DENTED (SUSPECTED BIRD-STRIKE) AT APPROX 4 O' CLOCK POSITION MEASURING 5.5 INCHES IN LENGTH, 3.0 INCHES WIDTH AND 0.5 INCH DEPTH. AFTER DETAIL VISUAL INSP (10X MAGNIFYING GLASS) IT WAS VERIFIED THAT NO CRACK CONDITION EXISTS. (DISPOSITION WAS MADE TO PERFORM TIME LIMITED REPAIR AS DESCRIBED IN PART 1 WORK INSTRUCTIONS, INITIATE REPEAT INSPECTIONS PRIOR TO EACH FLIGHT AND SCHEDULE PERMANENT REPAIR PRIOR TO THE ACCUMULATION OF 25 FLIGHT CYCLES AFTER PART 1 BY REMOVING AND REPLACING THE SUBJECT DAMAGED NOSE COWL IAW THE AMM 71-11-01 OR PERFORMING PERMANENT REPAIR IAW SRM 54-15-01, FIG 201, REPAIR 1 OR 2.)

Part: NOZZLE — CRACKED (EXHAUST) · airframe 46,092 hrs · 7,161 cycles

DURING MX WALK AROUND, MX FOUND (1EA) CRACK ON THE EXHAUST NOZZLE OUTER SLEEVE, STARTING AT APPROX THE 11 O'CLOCK POSITION. THE CIRCUMFERENTIAL CRACK IS APPROX 35.0 IN. LONG. IAW SRM 54-41-30 THE LENGTH OF THE CRACK IS OUT OF LIMITS. DISPOSITION IS TO STOP DRILL THE ENDS OF THE CRACK WITH A 0.125 IN. DIAMETER HOLE (DRILL BIT); DVI EVERY 3 FLIGHT CYCLES; AND REMOVAL OF THE PART PRIOR TO THE ACCUMULATION OF 25 FC (FLIGHT CYCLES) AFTER PART 1.

Part: WHEEL — DELAMINATED (MLG) · airframe 49,973 hrs · 7,932 cycles

SUSPECTED DELAMINATION OR DEFLATED NOSE TIRE. GEAR PINS INSTALLED AND ACFT TOWED TO HANGER. (ON INSP, FOUND RT NOSE TIRE, CTR TREAD MISSING. IAW MM 5-51-34-202-001, NO DAMAGE FOUND TO FUSELAGE OR ADJACENT STRUCTURE. FOUND SUPPORT ASSY FOR EXT POWER CABLE MISSING. REPLACED RT AND LT NOSE WHEELS. SUPPORT ASSY DEFERRED IAW DDPG)

Part: TIRE — FAILED (LT MLG) · airframe 49,754 hrs · 7,735 cycles

DURING WALKAROUND INSP, MX FOUND THE LT MAIN BODY GEAR NR 8 WHEEL SEVERED; DUE TO TIRE DAMAGED/BURST.

Part: SKIN — DAMAGED (BS 550 S31-32L) · airframe 49,344 hrs · 7,670 cycles

DAMAGE WAS FOUND TO THE 65B23701-6 FUSELAGE SKIN AT BS 550 BETWEEN S-31L AND -32L AFTER A BURST EQUIPMENT COOLING EXHAUST VALVE STRUCK THE S-31L STRINGER AND SKIN. REFER TO EO 4453A363 FOR THE STRINGER REPAIR. ACCOMPLISH PART 1 OF THIS EO PRIOR TO FURTHER FLIGHT ON 24 MAY2010 (7,670 TFC AND 49,344 TFH). ACCOMPLISH PART 2 OF THIS EO WITHIN 15,000 CYCLES AFTER PART 1 AND THEREAFTER AT 6,000 CYCLE INTERVALS. THE 65B23701-6 SKIN IS MADE FROM CHEMICALLY MILLED 0.080 INCH THICK 2024-T3 CLAD SHEET IAW QQ-A-250/5. IN THE AREA OF THE DAMAGE, THE SKIN PANEL IS CHEMICALLY MILLED TO 0.063 INCH THICK.PART 1 OF THIS EO REPAIRS THE FUSELAGE SKIN IAW SRM 53-00-01, FIGURE 201, REPAIR 6.THE SKIN WILL BE TRIMMED OUT AND A REPAIR INSTALLED IAW SRM 53-00-01, FIGURE 201, REPAIR 6. THE REPAIR IAW SRM 53-00-01, FIG 201, REPAIR 6 WILL CONSIST OF A 0.071 INCH THICK 2024-T3 ALUMINUM DOUBLER INSTALLED USING BACR15CE6D RIVETS.THE REPAIR IAW PART 1 OF THIS EO IS CATEGORY B AND THE SUPPLEMENTAL INSPECTIONS ARE PROVIDED IN PART 2 OF THIS EO. THE PART 1 REPAIR HAS FAA APPROVAL IF THE PART 2 INSPECTIONS ARE ACCOMPLISHED. PART 2 OF THIS EO ACCOMPLISHES THE REPETITIVE SUPPLEMENT HFEC INSPECTIONS OF THE CATEGORY B FUSELAGE SKIN REPAIR INSTALLED IAW PART 1.

Part: STRINGER — DAMAGED (BS 550 S31L) · airframe 49,344 hrs · 7,670 cycles

DAMAGE WAS FOUND TO THE 142U0086-198 STRINGER 31L AT BS 550 AFTER A BURST EQUIPMENT COOLING EXHAUST VALVE TRUCK THE S-31L STRINGER AND SKIN. REFER TO EO 4453A362 FOR THE SKIN REPAIR. THE 142U0086-198 STRINGER IS MADE FROM 0.050 INCH THICK 7075-0 SHEET PER QQ-A-250/12 HEAT TREATED TO T62 AFTER FORMING. IN THE AREA OF THE DAMAGE, STRINGER HAS A MACHINE TAPER 0.050 TO 0.040 INCH OVER 197 INCHES. PART 1 OF THIS EO ACCOMPLISHES THE TIME LIMITED REPAIR OF THE STRINGER. THE REPAIR IAW PART 1 OF THIS EO IS CATEGORY C AND REQUIRES REPETITIVE INSP IAW PART 2 OF THIS EO AT A-CHECK INTERVALS AND REPLACEMENT AT THE NEXT C-CHECK AFTER 24MAY2010 IAW PART 3 OF THIS EO. PART 2 OF THIS EO REPETITIVELY INSPECTS THE PART 1 REPAIR TO ENSURE CONTINUED AIRWORTHINESS. PART 3 OF THIS EO ACCOMPLISHES THE INTERIM REPAIR AT THE NEXT C-CHECK AFTER 24MAY2010 IAW SRM 53-00-03, FIGURE 201, REPAIR 3.

Part: STRINGER — DAMAGED (BS 550 S32L) · airframe 49,344 hrs · 7,670 cycles

DAMAGE FOUND TO STR 32L AT BS 550 AFTER A BURST EQUIPMENT COOLING EXHAUST VALVE STRUCK S-31L STR & SKIN. REFER TO EO 4453A362 FOR SKIN REPAIR.

Part: FAN — FAILED · airframe 49,342 hrs · 7,831 cycles

UPON CLIMB OUT; CREW EXPERIENCED SEVERAL EICAS MESSAGES: EQUIPMENT COOLING LOW FLOW, OXYGEN ON AND CABIN WARNING (DEPRESSURIZATION). (FOUND E/E COOLING FAN BURST, DAMAGING THE ACFT FUSELAGE. R & R EE COOLING SUPPLY FAN, EE COOLING EXHAUST VALVE AND INTERNAL SUPPLY DUCTS. COMPLIED WITH EO'S FOR REPAIR OF ACFT STRUCTURE)

Part: WARNING MESSAGE — FALSE ACTIVATION (RUDDER)

AIR TURN BACK DUE RUDDER RATIO MESSAGE DISPLAYED (SRM REPLACED AND SYS CHECKS NORMAL (MX WAS ABLE TO DUPLICATE PROBLEM ON GROUND AND CORRECTED AFTER SRM REPLACED, HOWEVER, AS PREC, REQUESTED PITOT STATIC TEST CHECKOUT OF SYS.)

Part: RIB — CRACKED (HORIZONTAL STAB) · airframe 47,704 hrs · 7,409 cycles

CRACKING WAS FOUND IN THE LT/RT HST LEADING EDGE RIBS BETWEEN LE STA 131.946 AND LE STA 527.190. REPAIRED THE 5EA CRACK AREA IAW EI NO T2010A55B-175 REV 00 AND T2010P55B-165 REV 00. CONDITION CHECK NORMAL.

Part: SKIN — WORN (VERTICAL STAB) · airframe 47,704 hrs · 7,409 cycles

PART 1-4 FOUND DAMAGE WEAR ON LT AND RT SIDE VERTICAL STAB SEAL INTERFACE SKIN AREA BETWEEN BS 2360-2390 AND BS 2521-2598 AND BS 2280- 2360. BLEND OUT DAMAGE AREA IAW SRM 53-00-01 REV 53 RESIDUAL MATERIAL THICKNESS WITHIN ALLOWABLE DAMAGE, APPLY PROTECTIVE COATING AND PRIMER, CONDITION CHECK NORMAL AND JOB COMPLETED.

Part: SKIN — DENTED (BS 695) · airframe 47,704 hrs · 7,409 cycles

DENT - SKIN UPPER SURFACE OF FWD CARGO BELOW SKIN STA. 695, S46R-S47R. REPAIRED THE DAMAGED AREA IAW 747-400F SRM 53-00-01 REPAIR 6 REV 53 REPEAT INSPECTION ON THE FOLLOWING METHOD EXTERNAL HFEC INTERVAL 6.000 FLIGHT CYCLES PER EO NR 4453A326. CONDITION CHECK NORMAL.

Part: SHIM — MIGRATED (BS 1241) · airframe 47,704 hrs · 7,409 cycles

SHIM MIGRATION WAS FOUND BETWEEN RT LONGERON FITTING AND FUSELAGE SKIN AT STA 1241, RBL 128, WL 175. REPAIR IN IAW EI NR T2010A53B-137 REV 00. CHECK CONDITION NORMAL AND JOB COMPLETED. INITIAL AND REPEAT INSPECTION AT EVERY C-CHECK NOT TO EXCEED 24 MONTHS PER EO NR 4453A323.

Part: FRAME — BROKEN (BS) · airframe 47,704 hrs · 7,409 cycles

FOUND FUSELAGE STRUCTURE FRAME BROKEN AT STA 1800 S-10R. REPAIRED THE FRAME BROKEN AREA IAW EI NR T2010A53B-166. FOLLOWED UP INSPECTION PRIOR TO 25,000 TOTAL FLIGHT CYCLES PER EO NR 4453A327.

Part: SLEEVE — DENTED (LT EXHAUST) · airframe 47,704 hrs · 7,409 cycles

A DENT WAS FOUND ON THE NR 4 ENG LT EXHAUST SLEEVE, AT THE 9 O'CLOCK LOCATION NEAR NAC STA 349-236. MANUFACTURER PROVIDED INSPECTION TIMELINE OF REF/D/AND PERFORM FPI INSPECTION PER BAC 5423 TO ENSURE NO CRACKS ARE PRESENT ON NOTED DENT. REPEAT INSPECTION EVERY 1300 FLIGHT HOURS PER EO4470A118 PART 2 UNTIL NEXT "C" CHECK.

Part: FAIRING — DAMAGED (TE FLAP) · airframe 46,520 hrs · 7,233 cycles

TRAILING EDGE I/B MID FLAP LEADING EDGE FAIRING UPPER MID AREA FOUND DAMAGED (DIMENSION 15 X 4.5 INCHES). LT WING - TRAILING EDGE I/B MID FLAP LEADING EDGE FAIRING UPPER MID AREA COMPOSITE HOT BOND REPAIR CARRIED OUT AS PER SRM 51-70-07 PAR 5.0 FIG 6.

Part: START VALVE — MALFUNCTIONED (NR 3 ENGINE) · airframe 44,702 hrs · 6,918 cycles

DIVERSION: AFTER TAKEOFF EICAS MESSAGE "START CUTOUT 3" DISPLAYED AT APPROX 11,000 FEET, ALSO STATUS MESSAGE "ENG-3 START VALVE". TRANSFERRED TO DMI M09-016 PER MEL 80-11-1. START VALVE TO BE OPERATED MANUALLY UNTIL FINAL REPAIR IS PERFORMED.

Part: SKIN — CRACKED (NR 7 FLAP) · airframe 44,191 hrs · 6,834 cycles

NR 7 VC FLAP EXTERIOR SURFACE CRACKED. NR 7 VC FLAP REPLACED IAW 27-81-02. RIGGING AND OPS CHECKED IAW 27-81-00.

Part: DOOR FRAME — CRACKED (L1 DOOR) · airframe 44,191 hrs · 6,834 cycles

L1 DOOR FORWARD UPPER FRAME CRACKED. L1 DOOR UPPER FORWARD FRAME REPAIRED AS PER SRM 51-70-06.

Part: INTERCOSTAL — CRACKED (BS 1220) · airframe 44,191 hrs · 6,834 cycles

BS 1220 LBL 106 BELOW FLOOR WEB CRACKED. FLOORBEAM INTERCOSTAL WEB REPAIRED AS PER 51-70-13 AND EO 4453A229.

Part: STRUCTURE — DAMAGED (ZONE 600) · airframe 43,668 hrs · 6,911 cycles

WHILE AIRCRAFT WAS TAXING, THE AIRCRAFT STRUCK ANOTHER AIRCRAFT THAT WAS PARKED CAUSING DAMAGE TO RIGHT WINGLET. RIGHT WINGLET REMOVED PER CDL, AREA VISUALLY INSPECTED AND AIRCRAFT RELEASED. ACFT AWAITING PERMANENT REPAIRS. OPEN

Part: FAIRING — DAMAGED (FUSELAGE) · airframe 41,688 hrs · 6,599 cycles

DURING ARRIVAL WALKAROUND INSPECTION FOUND LOWER RT AFT OF BODY GEAR FUSELAGE FAIRING DAMAGED. ACCOMPLISHED TIME LIMITED REPAIR AS PER EO 4453A188 DATED 7/8/08 ENTERED NON MEL DMI N08-037 FOR REPEAT INSPECTION OF PANEL AT EVERY A-CHECK. (A)

Part: TIRE — FAILED (RT MLG) · airframe 41,688 hrs · 6,599 cycles

DURING ARRIVAL WALK AROUND INSPECTION FOUND NR 11 TIRE SEPARATION. REPLACED NR 11 AND 12 WHEEL ASSEMBLIES. ALSO ACCOMPLISHED TIRE TREAD LOSS CONDITIONAL INSPECTION AS PER 05-51-34-202-001. (A)

Part: ENGINE — OIL CONSUMPTION (NR 3)

ENGINE NR 3 OIL QTY WENT TO 0 (3 HOURS AFTER TAKEOFF). ENGINE SHUT DOWN PRECAUTIONARY. FIM 79-00-00 FOLLOWED. INSPECTED FOR OIL LEAK. NO WETTING FOUND. REPLENISHED 22 QTS OIL AND LEAK AND OPS CHECK PERFORMED. NO LEAK FOUND. IDG AND STARTER DRAIN LINE CAPPED FOR MONITORING PER AMM 71-71-00. (A)

Part: SKIN — DELAMINATED (LT OB FOREFLAP)

FOUND DURING A-CHECK. REPAIR THE DAMAGE FOUND ON L/E OF LEFT OB FOREFLAP MEASURING 12 INCHES LONG BY 2 INCHES WIDE IAW SRM 51-70-07. REPAIR CARRIED OUT IAW EO 4457A145. (K)

Part: ACCESS PANEL — CRACKED (NR 3 PYLON) · airframe 40,399 hrs · 6,222 cycles

NR 3 PYLON ACCESS PANEL 472FL BOTH SIDES SKINS ADJACENT TO LATCH AREA HAVE CRACKED. REPAIRED PANEL PER EO 4454A055 AND RE-INSTALLED PER 54-62-02.

Part: POWERPACK — WORN (RUDDER) · airframe 33,757 hrs · 5,194 cycles

ATB:DUE TO MEDIUM/LIGHT VIBRATION IN RUDDER PEDALS. FLIGHT CONTROL VALVES OFF BY 1. YAW DAMPER OFF NO HELP, A/P OFF NO CHANGES. FOUND UPPER RUDDER HYD RETRACT LINE "B" NUT AND UNION LOOSE BY 2.5 TURN WITH HEAVY LEAK. TIGHTEN BACK IAW MM 27-21-15 OPS AND LEAK CHECK SATIS.TRANSFERED A/C TO HKG WHERE MAINTENANCE PERFORMED BOEING RECOMENDED CHECKS, FOUND LOWER RUDDER POWER CONTROL UNIT BEARING WORN, REPLACED PCU OPS CHECK OK.

Part: FIRE LOOP — MALFUNCTIONED (NR 2 ENGINE) · airframe 33,634 hrs · 5,176 cycles

IFSD: DUE TO DET FIRE/OHT 2 IN CLIMB REMAINED DISPLAY ENTIRE FLIGHT. STATUS NR 2 ENGINE FIRE LOOP B-RESET. B AND A LOOP CIRCUIT BREAKERS REDUCED, NR 2 THRUST TO IDLE, NO HELP DISPLAYED UNTIL ENGINE SHUTDOWN. ADVISORY, ENG 2 PRECAUTIONARY SHUTDOWN AT 2345, DUE TO NO FIRE/OVH DETECTION BOTH A AND B LOOPS INOP. PERFORMED NR 2 ENGINE INSPECTION NO FINDINGS, ACCOMPLISHED AIR LEAK CHECK IAW AMM 36-11-00, ALL NORMAL. REPLACED NR 2 ENGINE FIRE DETECTOR ELEMENT UPPER AND LOWER AFT A&B AS PER AMM 26-13-00.

Part: PANEL — MISSING (NR 2 PYLON) · airframe 32,216 hrs · 4,956 cycles

ON ARR, FOUND ON ENGINE NR 2 INBOARD PYLON PANEL 462RL MISSING. INSP LT FLAPS AND STABILIZER NO DAMAGE FOUND. REPLACED PANEL 462RL ON ENGINE NR 2, OK FOR SERVICE.

Part: PANEL — CHIPPED (RT WING) · airframe 32,209 hrs · 4,954 cycles

FLYING PANEL ON THE RIGHT HAND WING INBOARD TRAILING EDGE PREVIOUS REPAIR REQUIRES RE-WORK. AREA MARKED LOCATION IS APPROX WBL 220. NON ROUTINE NR 145. EXISTING REPAIR REMOVED AND A NEW REPAIR INSTALLED IAW SRM 51-70-06.

Part: SKIN — DENTED (T/E FLAP) · airframe 32,209 hrs · 4,954 cycles

RT INBOARD AFT FLAP HAS A DENT ON THE UPPER SURFACE APPROX ONE SQUARE INCH AND APPROX .250 DEEP,12 INCHES OUTBOARD OF NR 6 FLAP TRACK CANOE. FOUND DURING C-4 CHECK, N/ROUTINE NR 147. PERMANENT REPAIR CARRIED OUT TO DAMAGE AREA AS PER SRM 51-70-10 FIG 203 AND SRM 57-53-01.

Part: SKIN — GOUGED (T/E FLAP) · airframe 32,209 hrs · 4,954 cycles

RIGHT TRAILING EDGE AFT FLAP HAS A GOUGE ON THE UPPER SURFACE APPROX ONE INCH LONG, .125 INCH DEEP AND .250 WIDE. LOCATED 3 FEET OUTBOARD OF NR 7 TRACK CANOE. FOUND DURING C-4 CHECK AT PIK, N/ROUTINE NR 148. GOUGE REPAIRED IAW SRM 57-53-01 FIG 101. COVE PANEL SCREWS CHECKED AND LENGTH ADJUSTED.

Part: ENGINE — DAMAGED (NR 1) · airframe 31,541 hrs · 4,850 cycles

NR 1 ENGINE HAD EGT SPIKE TO 943* AT 5,000 MSL POWER REMAINED LOW THROUGHOUT CLIMB AND CRUISE. NR 1 N1- 20% BELOW 2-3-4. N2- 8-10% BELOW 2-3-4, EGT 50*-80* HOTTER THAN 2-3-4. N2 VIB 5.0 2-3-4 WERE 1.1-1.2. JFK NOTIFIED. NR 1 ENGINE SHUT DOWN AS PER JFK INSTRUCTION. REMOVED AND REPLACED ENGINE NR 1 AS PER AMM 71-00-02. ENGINE RUN CARRIED OUT, NO LEAK FOUND ALL SATIS.

Part: ENGINE — MALFUNCTIONED (NR 4)

NR 4 ENGINE NOT MAKING TO THRUST. (RTO) REJECTED TAKE OFF DUE TO NR 4 ENGINE NOT MAKING TAKE OFF THRUST. PERFORMED POWER ASSURANCE CHEDK (TEST 10), ALL WITHIN LIMITS IAW MM 71-00-00.

Part: ACTUATOR — INOPERATIVE (LT STEERING)

TAKEOFF WARNING (CONFIGURATION BODY GEAR) DISPLAYED DURING TAKEOFF. CMC GAVE LT GEAR OB ACTUATOR SWITCH MESSAGE 32055. DEACTIVATED ALL ACTUATORS INDICATION SYS IAW MEL AND TRANSFERRED ITEM TO DMI. (DEACTIVATED RT OB CYLINDER IAW MEL). REMOVED AND REPLACED LT OB BODY GEAR STEERING ACTUATOR IWA MM. OPERATION AND INDICATION OF BODY GEAR STEERING CHECK NORMAL.

Part: CONTROL UNIT — MALFUNCTIONED (COCKPIT WINDOW)

EICAS MESSAGE -HEAT WINDOW LT- DISPLAYED AFTER 1 HOUR CRUISE FLT AT FL330 AND SIMULTANEOUSLY L1 WINDOW CRACKED. PRESSURIZATION WAS NORMAL. REPLACED L1 WINDOW HEAT CONTROL UNIT IAW MM 30-41-00 OPERATION CHECK NORMAL. REMOVED AND REPLACED L1 WINDSHIELD IAW MM 56-11-01 AND OPERATION CHECK NORMAL. (M)

Part: RETAINER — CORRODED (MLG DOOR SEAL)

CORROSION FOUND IN PORTION OF MISSING SEAL RETAINER. FORM OF CORROSION (FLAKING, PITTING) FOUND. CORROSION CLEANED UP IAW SRM 51-10-02 ALODINE 1200 APPLIED AND REPROTECTED WITH BMS 10-11 TY1.

Part: SPINDLE — LACK OF LUBE (T/E FLAP)

ON APPROACH WHEN LANDING FLAPS 30 SELECTED, EICAS MESSAGE 'FLAPS DRIVE'. INBOARD T/E NORMAL, OUTBOARD T/E AT FLAPS 25. GO AROUND EXECUTED AND NNP ACCOMPLISHED. ON SUBSEQUENT APPROACH MESSAGE 'FLAPS DRIVE'. AFTER LANDING WHEN FLAPS RETRACTED EICAS MESSAGE 'FLAPS DRIVE' AND OUTBOARD T/E FLAPS REMAINED AT FLAPS 25. FOUND C/B FROM ELECTRIC OPERATION POPPED. RESET C/B AND ALSO FOUND ALL FLAP TRACK SPINDLE ASSEMBLIES, INBOARD AND OUTBOARD FLAPS, VERY DRY. GREASED ALL 8 SPINDLES ACC MM 27-51-00. CHECKED OPERATION AND FOUND NORMAL. (M)

Part: SMOKE WARNING — MALFUNCTIONED (LAVATORY)

10 MINUTES INTO FINAL APPROACH, LAVATORY SMOKE DETECTOR SOUNDED CONTINUOUSLY UNTIL ARRIVAL AT PARKING STAND WHEN MX RESET SMOKE DETECTOR. FIRE DEPT CONFIRMED NO SMOKE OR FIRE. LAVATORY COMPARTMENT AND COMPONENTS UNDERNEATH TOILET SHROUD INSPECTED AND FOUND NO EVIDENCE OF BURN MARKS OR SHORTED ELECTRICAL WIRES. SMOKE DETECTOR TESTED PER MM CHAPTER 26-13-01. FOUND OK. (M)

Part: HARNESS — DAMAGED (OVEN)

ON REMOVAL OF OVEN B/E AEROSPACE TYPE DF400PTC, FOUND CONNECTING POWER SUPPLY FLEX CABLE TEFLON SPIRAL WRAP MELTED DUE CONTACTING HOUSING OF HOT AIR CIRCULATING FAN. WIRE BUNDLE WAS PREVIOUSLY REPAIRED AS INDICATED BY WIRE SPLICES. BUNDLE IS APPROX 3 FT IN LENGTH WHICH IS REQUIRED SO OVEN CAN BE CONNECTED/DISCONNECTED AFTER SLIDING OUT OF OVEN COMPT C-4. ON SLIDING OVEN INTO COMPARTMENT, CABLE FREE STATE COMPRESSES AND ALLOWS CONTACT TO THE HOT AIR CIRCULATING FAN CASING CAUSING MELTING OF OUTER PROTECTIVE COVERINGS. THIS IS A BLIND AREA AND CANNOT BE CHECKED AFTER INSTALLATION. WIRES AND CASING REPAIRED AND NEW SPIRAL WRAP INSTALLED. (M)

Part: EICAS — MALFUNCTIONED (COCKPIT)

FLT AZ9162 - MXP-ORD - ON TAKEOFF ROLL AT 20 KNOTS, THE FLT CREW SAW A MOMENTARY RED FLASH ON THE EICAS. BELIEVED TO BE A FIRE WARNING MESSAGE, BUT IT WAS TOO QUICK TO READ. TAKEOFF WAS ABORTED WITHOUT EXCEEDING TAXI SPEED AND A/C RETURNED TO BLOCKS. WHEN A/C ARRIVED AT THE BLOCKS, THERE WAS NOT EICAS MESSAGE. ALSO, THERE WERE NO PRESENT LEG FAULT(PFL) MESSAGES. PERFORMED FIRE WARNING/OVERHEAT TEST AND FOUND TO BE NORMAL. AIRCRAFT VISUALLY CHECKED FOR ABNORMALITIES AND NONE FOUND. NO HISTORY MESSAGES IN THE CMC. UNABLE TO DUPLICATE THE REPORTED DISCREPANCY. (M)

Part: SAFETY WIRE — BROKEN (TE AFT FLAP)

INSPECTED A/C PER ATLAS AIR FCD 99-17, FOUND THE FOLLOWING AFT FLAP TRACK CARRIAGE BOGIE PIN ASSEMBLY WITH FAILED SAFETY WIRE ON ONE POSITION; NR 1 OUTBOARD PIN, WIRE BROKEN, TORQUE ON BOLT OK. AIRCRAFT REPAIRED PER ATLAS AIR FCD 99-17, REF IPC 27-51-28-01. (M)

Part: NOZZLE — CRACKED (NR 3 ENGINE)

EXHAUST SLEEVE CRACKED AT AFT CIRCUMFERENTIAL SEAM WELD. NR 3 ENGINE, 11 O'CLOCK POSITION 10 INCH LENGTH AND SECOND CRACK 3 O'CLOCK POSITION 1.50 INCH LENGTH. AFTER REMOVAL, FOUND SMALL 1.50 INCH CRACK INSIDE ON BULKHEAD. ITEM REPLACED. (X)