N412MC

Part: ELEC CONNECTOR — DAMAGED (ZONE 400) · airframe 102,962 hrs · 16,578 cycles

NO NAI INDICATION FOR ENG 1 NAI VALVE IS ON DEFERRAL DMI 243009 AND LOCKED OPEN, & CONNECTOR IS REMOVED. RAN ENGINE IAW 71-00-00, VALVES OPS NORMAL. RESET PUSHED PIN ON PLUG 40289P PIN 15 & OPS CHK OK PER AMM 30-21-00 & 71-00-00.

Part: PUMP — FAILED (HYD SYSTEM) · airframe 102,250 hrs · 102,250 cycles

LOST #4 HYDRAULIC SYS ENROUTE TO JFK. EMERGENCY WAS DECLARED. REMOVED & REPLACED #4 ENGINE DRIVEN PUMP IAW AMM- 29-11-05. LEAK & OPS CHECK GOOD.

Part: PUMP — FAULTED (HYD SYS) · airframe 102,250 hrs · 16,475 cycles

HYD 4 QTY LOW-ADVISORY, HYD PRESS ENG 4-STATUS, HYD RESVR PRESS 4-STATUS-DURING FLIGHT. WHEN ARRIVED BLEEDING HYDRAULIC FLUID VERIFIED FROM JFK STATION TECHS. SERVICED HYD SYS AS REQ'D DUE TO ENG 4 EDP R & R REF AMM 12-12-01 R114. FOUND ENG 4 EDP HOUSING CRACKED. REMOVED AND REPLACED ENG 4 EDP REF AMM 29-11-05 R114 & AIPC REF 29-11-17-14 R90. OPS & LEAK CHKS NORMAL AMM TASK 71-00-00-705-152-J00 PERFORMED.

Part: ENGINE — FAULTED (NR 1) · airframe 101,554 hrs · 16,376 cycles

LOW SPEED REJECTED, #1 ENG 2.5-3.0 BELOW REQ T/O THRUST. EGT #1 EXCEED 952 SOLID RED BOX AROUND EGT. RED BOX FOR 5 SECONDS(<P>MX IN WORK WHILE IN AOGM FOR RTO ENG 1 EGT LIMIT. AOGM ETR: 10AUG25</P>)

Part: SMOKE DETECTOR — FALSE ACTIVATION (ZONE 200) · airframe 101,312 hrs · 16,344 cycles

EQUIPMENT SMOKE STATUS MESSAGE AFTER EQUIPMENT COOLING MESSAGE. REMOVED AND REPLACED EQUIPMENT COOLING SMOKE DETECTOR IAW AMM 26-16-51. PERFORMED GROUND TEST .</P> / <P>TEST PASSED MESSAGE CLEARED.

Part: SUPPORT FITTING — CORRODED (ZONE 100) · airframe 99,500 hrs · 16,081 cycles

UPON RH BLG RETRACT ACTUATOR REMOVED, FOUND SUPPORT FITTING O/B LEG CORROSION.(<P>WORK ACCOMPLISHED IAW EN 1005-25 REV 0. NO FURTHER DEFECTS NOTED.</P>)

Part: SKIN — GOUGED (ZONE 200) · airframe 99,500 hrs · 16,081 cycles

FUSELAGE SKIN FOUND GOUGE AT L1 DOOR AFT LOWER MID AREA(<P>GOUGE EVALUATED AND MEASURED LENGTH: 9", (A) WIDTH: 2.2", (Y) DEPTH: 0.135", A/Y = 16.29 FOUND OUT OF LIMIT AS PER B747-400F SRM 53-00-01-1A-1 ALLOWABLE DAMAGE DETAIL III REV 102. WORK ACCOMPLISHED AS PER FINAL EN 1001-25 REV 0. NO FURTHER DEFECTS NOTED.</P>)

Part: WEB — DAMAGED (ZONE 100) · airframe 99,500 hrs · 16,081 cycles

DURING HFEC INSPECTION ON NOSE WHEEL WELL SIDE AND TOP PANEL, WEB AND STIFFENER AT STA 265-280, WL 140 FOUND TWIN FASTENER AND UNABLE TO SCAN AROUND(<P>FASTENER REMOVED AND REPLACED IAW B747-400F SRM 51-40-02 REV 102. WORK ACCOMPLISHED IAW EN 1008-25 REV 0. NO FURTHER DEFECTS NOTED.</P>)

Part: FLOORBEAM — CORRODED (ZONE 200) · airframe 99,500 hrs · 16,081 cycles

MAIN DECK CARGO FLOOR BEAM UPPER CHORD AT STA 2300 LBL 63.0 TO LBL 67.0 FOUND CORROSION.(<P>WORK ACCOMPLISHED IAW EN 1002-25 REV 0. NO FURTHER DEFECTS NOTED.</P>)

Part: ADC — FAULTED (RIGHT) · airframe 96,477 hrs · 15,633 cycles

DURING FLIGHT BUFFET MARGIN AND STALL SPEED MARGIN DISPLAYS WERE DIFFERENT BY +/- 20KIAS FROM LEFT AND RIGHT DISPLAYS(<P>DFDR DATA DOWNLOADED &AMP; SENT TO HDQ PER AMM 31-31-01 REV 110. AOA SENSOR TEST OK (NO LIGHT) PER AMM 34-12-03 REV 110. AS PER REQUEST, R/R RH AOA SENSOR PER&NBSP; 34-12-03 REV 110. R/R LH AOA SENSOR PER AMM 34-12-03 REV 110. ACCOMPLISHED BOEING RECOMMENDED YLS-TLS 24--0392-02B, 1/03B &AMP; -05B. ACCOMPLISHED R/R LH &AMP; RH ADC &AMP; OPS CHECK NORMAL PER AMM 34-12-01 REV 110. R/R JETT NOZZLE VALVE &AMP; ACTUATOR PER AMM 28-31-03 &AMP; 28-31-04 ERV 110. LEAK TEST OK PER AMM 28-31-03 REV 110. ACCOMPLISHED TLS-24-0392-09B. NOTIFIED MCC &AMP; OK TO CLOSE. RETURN TO SERVICE.</P>)

Part: MODULATING VALVE — FAULTED (CABIN TEMP) · airframe 97,253 hrs · 15,746 cycles

DIVERSION: FLIGHT DECK AND UPPER DECK AREA TEMPERATURE UNCONTROLLABLE.(<P>R/R FLT DECK ZONE TRIM MOD VLV AND ZONE TEMP CONTROL MOD PER AMM 21-61-10/401 AND 21-61-01/401. OPS CHK GOOD.&NBSP;</P>)

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 94,336 hrs · 15,316 cycles

LEFT WING GEAR TILT ACTUATOR BROKE. CAUSED DAMAGE TO STRUCTURE AND WING GEAR.(<P>MX IN WORK WHILE IN AOGD FOR LH WING GEAR TILT ACTUATOR INOP. AOGD ETR: 26OCT23</P>)

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 92,338 hrs · 14,992 cycles

HYD QTY LOW #1 FOLLOWED BY HYD PRESSURE SYS #1 CAUTION ON FINAL.(<P>NOSE GEAR STEERING PRESSURE LINE AT STA 900 IN FWD PIT LEAKING. REPAIRED AND INSTALLED TEMP LINE IAW AMM 20-11-05 &AMP; GMM 3.24.1. OPS &AMP; LEAK CHECK GOOD. RE-INSPECT TEMP FLEX LINE EVERY 25 FLIGHT CYCLES. TRANSFER TO NON-MEL 184022 DUE DATE 30APR23.</P>)

Part: GEARBOX — NONE · airframe 90,907 hrs · 14,753 cycles

FLAPS DRIVE CATUION MSG ON RETRACTION. C/W QRH(<P>R/R RH OUTBOARD T/E FLAPS ANGLE GEARBOX. OPS CHECK GOOD IAW AMM 27-51-021</P>)

Part: SKIN — DENTED (RT WING TE FLAP) · airframe 8,385,932 hrs · 13,615 cycles

RHW #19 V/C FLAP I/B BULLNOSE AREA FOUND 1EA DENT MARK.(<P>RHW #19 V/C FLAP I/B BULLNOSE SKIN REPAIRED AS PER SRM 57-43-02-2R-2.</P>)

Part: SKIN — DELAMINATED (LT WING TE FLAP) · airframe 8,385,923 hrs · 13,615 cycles

LHW I/B MID FLAP FOUND DELAMINATION.(<P>LHW I/B MID FLAP 33" FROM I/B EDGE DELAMAINATED AREA PERFORMED REPAIR AS PER SRM 51-70-07 PAR 5A AND DETAIL REFER 'HX' PROCESS CARD CONTROL SEQUENCE NO: XJN509105-01.</P>)

Part: SKIN — DENTED (NLG DOOR) · airframe 8,385,932 hrs · 13,615 cycles

NLG RH DOOR EXT SURFACE SKIN AFT AREA FOUND DENT.(<P>REPAIRED IAW RI-52-80-14335 REV A. OPS CHK GOOD.</P>)

Part: SKIN — DENTED (RT WING AILERON) · airframe 8,385,923 hrs · 13,615 cycles

RHW O/B AILERON LOWER SURFACE FOUND 2EA DENTS.(<P>RHW O/B AILERON LOWER SURFACE PERFORMED REPAIR AS PER SRM 51-70-06 PAR.5A(1) AND REFER TO HX PROCESS CARD NO:XJN504858-01 AND XJN504858-02 FOR DETAIL.</P>)

Part: SEAT TRACK — CORRODED (MAIN DECK) · airframe 8,385,923 hrs · 13,615 cycles

MAIN DECK STA 1802 LBL 11" SEAT TRACK FOUND COR.(<P>MAIN DECK STA 1770-1810 LBL 11" SEAT TRACK REPAIRED AS PER SRM 53-00-52-2R-12.</P>)

Part: RETAINER — CRACKED (FLP TRK FAIRING) · airframe 8,385,932 hrs · 13,615 cycles

RHW #6 FLAP TRACK FIXED FAIRING O/B SEAL RETAINER FWD CRACK.(<P>RHW #6 FLAP TRACK FIXED FAIRING O/B SEAL RETAINER REPAIRED AS PER RI-27-51-14315 REV A</P>)

Part: SKIN — DELAMINATED (LT WING TE FLAP) · airframe 8,385,923 hrs · 13,615 cycles

LHW I/B FORE FLAP FOUND DELAMINATION.(<P>LHW I/B FORE FLAP 115.5" FROM I/B EDGE DELAMINATION AREA PERFORMED REPAIR AS PER SRM 51-70-07 PAR 5A AND DETAIL REFER 'HX' PROCESS CARD CONTROL SEQUENCE NO: XJN509097-01.</P>)

Part: SEAL DEPRESSOR — DAMAGED (THRUST REVERSER) · airframe 8,385,932 hrs · 13,615 cycles

#2 ENG RH T/R FWD LOWER BIFURCATION FOUND DAMAGE.(<P>REPAIRED AS PER RI-78-32-14338 REV B AT #2 ENG R/H T/R FWD LOWER BIFURCATION AREA.</P>)

Part: SKIN — DELAMINATED (RT AILERON) · airframe 83,859 hrs · 13,615 cycles

RHW I/B AILERON UPPER SURFACE FOUND DELAMINATION(<P>RHW I/B AILERON UPPER SURFACE PERFORMED REPAIR AS PER SRM 51-70-06 PAR.5.A REV 90 REV DATE 20OCT20 AND REFER TO HX PROCESS CARD CONTROL SEQUENCE NO XJN504866-01 FOR DETAIL.</P>)

Part: SKIN — CORRODED (HORIZONTAL STAB) · airframe 8,385,923 hrs · 13,615 cycles

H/STAB L/H T/E LOWER SKIN BL 415 FOUND COR.(<P>H/STAB L/H T/E LOWER SKIN BL 415 COR AREA REPAIRED AS PER RI-55-00-14312 REV A.</P>)

Part: SKIN — DELAMINATED (LT WING TE FLAP) · airframe 8,385,923 hrs · 13,615 cycles

LHW I/B AFT FLAP MID LOWER SURFACE FOUND DELAMINATION.(<P>LHW I/B AFT FLAP LOWER SURFACE 160" FROM O/B EDGE DELAMIATION AREA PERFORMED REPAIR AS PER SRM 51-70-07 PAR 5A AND DETAIL REFER 'HX' PROCESS CARD CONTROL SEQUENCE NO: XJN504726-01.</P>)

Part: STRUCTURE — CRACKED (NR 2 ENGINE) · airframe 8,359 hrs · 13,615 cycles

#2 ENG RH TRANSLATING AFT LOWER TAIL FOUND CRACK(<P>#2 ENG RH TRANSLATING AFT LOWER TAIL PERFORMED LAYUP REPAIR AS PER ST ENGINEERING CMM 78-32-31 PAR.5.B REV 60 REV DATE 01 SEPT 2020.</P>)

Part: BRACKET — CRACKED (ROLLER TRAY) · airframe 8,385,932 hrs · 13,615 cycles

FWD CGO COMPT STA 950 RH MID ROLLER TRAY PDU BRACKET FOUND CRACK.(<P>FWD CGO COMPT STA 950 RH MID ROLLER TRAY PDU BRACKET REPAIRED AS PER RI-25-50-14314 REV A</P>)

Part: SKIN — DELAMINATED (LT WING TE FLAP) · airframe 8,385,923 hrs · 13,615 cycles

LHW #10 V/C FLAP O/B UPPER CORNER AREA DELAM.(<P>LHW #10 V/C FLAP O/B UPPER CORNER PERFORMED REPAIR AS PER SRM 51-70-07 PAR 5G REV 90 REV DATE 20 OCT 2020 AND REFER TO HX PROCESS CARD CONTROL SEQUENCE NO: XJN507729-01 FOR DETAIL.</P>)

Part: SKIN — DELAMINATED (RT WING TE FLAP) · airframe 8,385,923 hrs · 13,615 cycles

RHW O/B MID FLAP O/B AREA FOUND DELAMINATION.(<P>RHW O/B MID FLAP L/E AREA 62" FROM O/B EDGE DELAMINATION AREA PERFORMED REPAIR AS PER SRM 51-70-07 PAR 5A AND REFER 'HX' PROCESS CARD CONTROL SEQUENCE NO:XJN504742-01 FOR DETAIL.</P>)

Part: SKIN — DELAMINATED (LT WING TE FLAP) · airframe 8,385,923 hrs · 13,615 cycles

LHW O/B FORE FLAP O/B L/E AREA FOUND DELAMINATION.(<P>LHW O/B FORE FLAP L/E AREA 11" FROM O/B EDGE DELAMINATED AREA PERFORMED REPAIR AS PER SRM 51-70-07 PAR 5A AND REFER 'HX' PROCESS CARD CONTROL SEQUENCE NO:XJN503348-01 FOR DETAIL.</P>)

Part: SEAT TRACK — CORRODED (MAIN DECK) · airframe 8,385,923 hrs · 13,615 cycles

MAIN DECK STA 1726 LBL 11" SEAT TRACK FOUND COR.(<P>MAIN DECK STA 1710-1770 LBL 11 SEAT TRACK REPAIRED AS PER SRM 53-00-52-2R-12.</P><P><BR DATA-MCE-BOGUS="1" /></P>)

Part: HYDRAULIC LINE — LEAKING (LT WLG) · airframe 81,204 hrs · 13,167 cycles

HYD QTY 4 WENT TO ZERO ON GEAR RETRACTION. FOUND HYD LINE LEAKING. LT WLG EXT ACT LINE REMOVED AND REPLACED. LEAK CHECK SATISFACTORY IAW AMM 32-32-01.

Part: TRANSMITTER — MALFUNCTIONED (ENGINE OIL QTY) · airframe 79,521 hrs · 12,906 cycles

IN CRUISE, OIL QUANTITY FELL TO 0. OIL TEMP INCREASED TO 139, ENGINE #3.(<P>AFTER ENGINE SHUTDOWN, SERVICED OIL TANK WITH 3 QTS OF OIL TO FULL. REMOVED AND REPLACED #3 ENGINE OIL QUANTITY TRANSMITTER IAW AMM 79-31-01. LEAK AND OPS CHECK GOOD.</P>)

Part: LAMP — INOPERATIVE (EMERGENCY LIGHT) · airframe 79,458 hrs · 12,894 cycles

MAIN DECK L1 DOOR - CEILING EMERGENCY LIGHT INOP.&NBSP;(<P>RELAMPED L1 MAIN DECK DOOR CEILING LIGHT IAW&NBSP;B747 AMM 33-51-07-962-001, OPS CHECK GOOD.</P>)

Part: COFFEEMAKER — FAILED (GALLEY) · airframe 76,770 hrs · 12,417 cycles

AT CRUISE, FL 330, HEARD A LOUD "POP" SOUND FROM THE GALLEY AREA. IT WAS IMMEDIATELY FOLLOWED BY AN ELECTRICAL FIRE SCENT. NO SMOKE WAS OBSERVED.(<P>INSPECTED GALLEY AND ALL ELECTRICAL APPLIANCES FOR OPERATION, ALL CHECKED NORMAL. ALL LIGHTS AND OUTLETS WORKED, NO EVIDENCE OF ELECTRICAL DAMAGE. DEFERRED COFFEE MAKER AS A PRECAUTION. NOTE, THE COFFEE MAKER WAS THE ONLY APPLIANCE IN USE. MECHANIC CONFIRMED THAT COFFEE MAKER SMELLED BURNT. REMOVED COFFEE MAKER IAW AMM 25-32-21.<BR /></P>)

Part: ACOUSTIC LINER — CORRODED (NR 1 INLET) · airframe 76,658 hrs · 12,397 cycles

BULGE ON ACOUSTIC PANEL AFT EDGE OF NO.1 ENG INLET COWL NEAR 7 O'CLOCK POSITION.(<P>1.REPAIR DAMAGE AREA I.A.W. EI NO=T2019A71M-365 REV.1 2.JOB COMPLETED AND COND. CHK NML.</P>)

Part: SEAT TRACK — CORRODED (BS 1047-1128) · airframe 76,658 hrs · 12,397 cycles

REPAIR CORROSION ON THE MAIN DECK FLOOR SEAT TRACK NEAR STA 1047 AND STA 1128,RBL 11.33.(<P>1.REPAIR SEAT TRACK I.A.W. EI NO T2019A53M-217 REV.1 2.COND CHK NML AND JOB COMPLETED.</P>)

Part: SKIN — DAMAGED (RT AILERON) · airframe 76,658 hrs · 12,397 cycles

DAMAGE SKIN,R/H WING INBD AILERON OUTBD T/E CORNER.(<P>1.REMOVE THE DAMAGE MATERIAL AND CLEAN MEASURE THE DAMAGE ARE (0.5"X0.5")X2 PLIES AT OUTBD EDGE AND AFT EDGE CORNER) BOND 4 REPAIR PLIES (6.5"X3.5") USE WET LATUP WITH RESIN CURE AT 150 DEG. F FOR MINIMUM 180 MINUTES MAINTAIN A MINIMUM VACUUM PRESSURE 22 IN/HG I.A.W. B747-400F SRM 57-60-01-2R-1 REFER TO SRM 51-70-06-0G-0 REV.84 2.CHECK CONDITION WA SATISFACTORY.</P>)

Part: SKIN — DENTED (BS 540) · airframe 76,658 hrs · 12,397 cycles

SHARP DENT ON FUSELAGE SKIN PANEL NEAR STA 540. BETWEEN S-33R AND S-34R.(<P>1.REPAIR DENT AREA I.A.W. EI NO.T2019A53M-150 REV.1.</P>)

Part: SKIN — DAMAGED (CARGO DOOR) · airframe 76,658 hrs · 12,397 cycles

SKIN&NBSP; EDGE BENDING ON FWD/AFT LOWER CORNERS OF BULK CARGO DOOR OUTER SKIN.(<P>1.PFM EI NO.T2019A53M-270. REV1 2.JOB COMPLETED AND COND CHK NML.</P>)

Part: BATTERY PACK — NO TEST (EMERGENCY LIGHTS) · airframe 76,658 hrs · 12,397 cycles

FOUND POWER SUPPLY EMERGENCY LIGHT M5170,M5168 CAPACITIY FUNCTION NOT GOOD.(<P>1.IAW AMM 33-51-04-902-001-001 REV.94 REPLACED EMERGENCY LIGHTS SUPPLY BATTERIES M5170,M5168 AND CONDTION CHECK NORMAL 2.I.A.W. AMM 33-51-04-902-001-001 REV.94 STEP 3.E PERFORMED POER SUPPLY TEST AND THE RESULT SATISFACTORY.</P>)

Part: SKIN — DENTED (RT WING TE FLAP) · airframe 76,658 hrs · 12,397 cycles

DENT-SKIN.RH WING INBD MID FLAP.INBD LOWER SURFACE SKIN ONE DENT.WBL 140.(<P>CUTOUT THE DAMAGE AREA AND CLEAN.MEASURE THE DAMAGE AREA (L-2".W-2".6.4" FROM AFT EDGE.4.5" FROM INBD EDGE AT R/H WING INBD MID FLAP LWR SURFACE.BOND REPAIR-DOUBLER (L=6",W=6") WITH FILM ADHESIVE,CURE AT 250DEG. FOR 100 MINUTES AND MAINTAIN A MINIMUM VACCUUM PRESSURE AT 20IN/HG IAW B747-400F SRM 57-53-01-2R-1 REFER TO SRM 51-70-10-2R-REV.84 2.CHECK CONDITON SATISFACTORY.</P>)

Part: SKIN — DENTED (RT WING TE FLAP) · airframe 76,658 hrs · 12,397 cycles

DENT-SKIN,RH WING INBD MID FLAP LOWER SURFACE WBL 406.(<P>1.CUT OUT THE DAMAGE MATERIAL AND CLEAN MEASURE THE DAMAGE AREA 3.2"X2.6" 33' FORM OUTBD EDGE 12" FROM THE EDGE BOND FILLER AND REPAIR DOUBLER WITH FILM ADHESIVE CURE 250DEG. FOR 100 MINUTES AND MAINTAIN A MINIMUM VACUUM PRESURE AT 22IN/HG I.A.W. 747-400F SRM 57-33-01-2R-1 REFER TO SRM 51-70-10-2R-0 REV.84 2.CHECK CONDITION WAS SATISFACTORY.</P>)

Part: BRACKET — DAMAGED (THRUST REVERSER) · airframe 76,658 hrs · 12,397 cycles

DAMAGE-BRACKET NO.4 ENG R/H T/R INNER FACE UPPER BIFURCATION FWD SIDE.(<P>IAW ATLAS J/C 1978A227(MCS8058) REPLACED 4R T/R ASSY .</P>)

Part: FRAME — CORRODED · airframe 76,658 hrs · 12,397 cycles

CORROSION-FOUND 30EA CORROSION DAMAGES WHEN PERFORM SB 747-53A2878.(<P>1.REPAIR DAMAGED AREA I.A.W. EI NO. T2019A53M319 REV.2 2.JOB COMPLETED AND COND CHK NML. 3. JACKING EI. NO.T2019A07M-315 REV.0 THAN ATTACHECHED TO NRC WO.3058015(579).</P>)

Part: DOUBLER — CORRODED (BS 979) · corrosion level 2 · airframe 76,658 hrs · 12,397 cycles

CORROSION-DOUBLER,LOWER FUSELAGE,STA 979 FORM ACCESS PNL NO.192 FFR.(<P>1.RMV CORROSION DOUBLER I.A.W. SRM 51-40-02-0G-0 REV.84 2.INSTL NEW DOUBLER I.A.W. BOEING DWG NO.140110999 SH.30 REV.- &AMP; 14244780 SH.12 REV.F &AMP; 417112400 SH2 REV.-&AMP; 65B04118 SH.2 REV.P &AMP;142110980 SH. 229 REV.- &AMP; SRM 51-40-02-0G-0 REV.84.</P>)

Part: SKIN — CORRODED (BS 1540) · airframe 76,658 hrs · 12,397 cycles

CORROSION-SKIN, R/H WING OUTBD LE CAVITY INSIDE LE LOWER PNL ATTACH PLATE,STA 1540.(<P>1.REMOVE DAMAGE PART I.A.W. SRM 51-40-02-0G-0,REV=84 2.INSTALL NEW P/N=65B11862-36 IAW SRM 51-40-02-0G-0,REV=84 AND DMG NO=65B11862 SH2 REV.F 3.JOB COMPLETED AND COND CHK SATISFIED.</P>)

Part: SKIN — CRACKED (RT WING TE FLAP) · airframe 76,658 hrs · 12,397 cycles

CRACK-SKIN R/H WING INBOARD MMID FLAP,OUTBD T/E LOWER SURFACE,WBL 430.(<P>1.CUT OUT THE CRACK MATERIAL AND CLEAN MEASURE THE DAMAGE AREA (L=2.5",W+0.75",12.5" FROM AFT EDGE AT R/H WING INBD MID FLAP OUTBD T/E LWR SURFACE,WBL 430).BOND 4 REPAIRS PLIES (L=6.5",W=5.5")USE FIBERGLASS REPAIR WITH FILM AFHESIVE CURE AT 260DEG. FOR 130 MINUTES AND MAINTAIN A MINIMUM VACCUM PRESSURE AT 22 IN/HG I.A.W. B747-400F SRM 57-53-01-2R-1 REFER TO SRM 51-40-07-0G-0 REV84 2.CHECK CONDITION WAS SATISFACTORY.</P>)

Part: SKIN — DENTED (LT WING TE FLAP) · airframe 76,658 hrs · 12,397 cycles

NON-MEL #88716,DENT,LH INBD MID FLAP,WITHIN LIMITS,REPAIR AT NEXT C CHECK.(<P>1.CUT OUT THE DAMAGE MATERIAL AND CLEAN,MEASURE THE DAMAGE AREA 3.75"X2",3.5" FROM OUTBD EDGE.17" FROM AFT EDGE.BOND FILLER AND REPAIR DOUBLER WITH FILM ADHESIVE.CURE 250 DEG. FOR 100 MINUTES AND MAINTAIN A MINIMUM VACUUM PRESSURE AT 22IN/HG I.A.W 747-400F SRM 57-53-01-2R-1 REFER TO SRM 51-70-10-2R-0 REV.84 2.CHEK CONDITION WAS SATISFACTORY.</P>)

Part: SKIN — CRACKED (CARGO DOOR) · airframe 76,658 hrs · 12,397 cycles

FOUND SKIN PANEL CRACK AT SECTION 46 LOWER LOBE CGO DOOR FOWARD UPPER CORNER.(<P>1.ACCOMPLISHED THE REPAIR I.A.W. EI NO.T21019A53M-318 REV.2 AND SRM 53-60-01-2R-3 REPAIR 3 REV.84 2.CONDITON CHECK NORMAL AND JOB COMPLETED.</P>)

Part: STRUCTURE — CORRODED (BS 1241) · airframe 69,575 hrs · 10,999 cycles

CORROSION BS 1241 LBL 91. BLEND OUT THE DAMAGED AREA. REPAIRED THE DAMAGED AREA IAW EI T2017A57M-076 REV 1.

Part: FRAME — DAMAGED (BS 1241) · airframe 69,575 hrs · 10,999 cycles

DAMAGE ON FRAME AT BS 1241-1 RBL 91. BLEND AND REPAIRED IAW EI T2017A57M-076 REV 1.

Part: SPLICE PLATE — CORRODED (LT WING) · airframe 69,575 hrs · 10,999 cycles

SPLICE PLATE OF LT WING OUTBOARD LE LOWER SKIN PANEL AT OLES 1545.50 CORRODED. REMOVED DAMAGED PART IAW SRM 51-40-02 REV 78. 2) FABRICATED PART IAW EI NO T2017P57M-067 REV 0. INSTALL FABRICATED PART IAW SRM 51-40-02 REV 78 AND DWG 65B11862 ID 0002 REV F.

Part: FLOORBEAM — CORRODED (BS 780) · airframe 69,575 hrs · 10,999 cycles

FOUND MAIN DECK FLOORBEAM CORROSION AT BS 780. RBL 43. REPLACED NEW SHIM AT MID FLOORBEAM IAW AMM TASK 20-51-01-912-008 REV 88.

Part: SPLICE PLATE — CORRODED (LT WING) · airframe 69,575 hrs · 10,999 cycles

SPLICE PLATE OF LT WING OTBD LE LOWER SKIN PANEL INSTALLATION AT OLES 1304 CORRODED. REMOVED DAMAGED PART IAW SRM 51-40-02 REV 78. FABRICATED PART IAW EI T2017P57M-068 REV O. INSTALL FABRICATED PART IAW SRM 51-40-02 REV 78. AND DWG 65B11862 ID 0002 REV F.

Part: LIMIT SWITCH — OUT OF ADJUST (STAB TRIM) · airframe 69,575 hrs · 10,999 cycles

FUNCTIONAL FAIL OF THE STABILIZER TRIM CONTROL COLUMN CUTOUT SWITCHES AND CIRCUIT. PERFORM WIRING CONTINUITY CHECK FORM SRM TO STAB TRIM CONTROL MODULE RESULT WAS SATISFACTORY IAW WDM 27-41-11 AND 27-41-24 REV 41. PERFORMED STABILIZER TRIM ELEVATOR CONTROL ACTUATED LIMIT SWITCH ADJUSTMENT IAW AMM 27-41-07-835-001 REV 88 STEP A TO E. PERFORM OPERATIONAL TEST, RESULT WAS NORMAL IAW AMM 27-41-07-835-001 REV 88 STEP E(4).

Part: SEAT TRACK — CORRODED (BS 2060-2200) · airframe 69,575 hrs · 10,999 cycles

CORROSION ON THE MAIN DECK SEAT TRACK BETWEEN BS 2060 AND 2200, LBL 11.33. REPAIRED THE SEAT TRACK IAW EI T2017A53M-172 REV 1 AND SRM 53-00-52 REPAIR 12 REV 78.

Part: SEAT TRACK — CORRODED (BS 1018-1128) · airframe 69,575 hrs · 10,999 cycles

FOUND SEAT TRACK CORRODED AT BS 1018 - 1128, LBL 12. REMOVED DAMAGED SEAT TRACK IAW SRM 51-40-02-0G-0 REV 78. INSTALLED NEW SEAT TRACK IAW SRM 51-40-02-0G-0 REV 78. AND DWG 111U0801 SH 4.3.2 REV J.E.D.

Part: SEAT TRACK — CORRODED (BS 760-980) · corrosion level 2 · airframe 69,575 hrs · 10,999 cycles

CORROSION ON THE MAIN DECK SEAT TRACK BETWEEN BS 760 AND 980, LBL 11.3. REPAIRED THE SEAT TRACK IAW EI T2017A53M-171 REV 1, AND SRM 53-00-52, REPAIR 12.

Part: MAST — CORRODED (POTABLE WATER) · airframe 69,575 hrs · 10,999 cycles

CORROSION ON FUSELAGE LT LOWER SIDE MAST AND COVER POTABLE WATER SYSTEM. REPLACED THE DRAIN MAST IAW AMM 38-31-61-004-002 REV 88 AND AMM 38-31-61-404-013 REV 88. PERFORMED A TEST OF DRAIN MAST IAW AMM 38-31-61-404-013 REV 88.

Part: SEAT TRACK — CORRODED (BS 2100-2200) · corrosion level 2 · airframe 69,575 hrs · 10,999 cycles

CORROSION ON THE MAIN DECK SEAT TRACK BETWEEN BS 2100 AND 2200, RBL 11.33. REPAIRED THE SEAT TRACK IAW EI T2017A53M-173 REV 1 AND SRM 53-00-52 REPAIR 12 78.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 67,580 hrs · 10,636 cycles

UPPER DECK EMERGENCY LIGHT INOPERATIVE. R & R UPPER DECK AFT CEILING EMERGENCY LIGHT IAW AMM 33-51-07, OPS NORMAL.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 67,580 hrs · 10,636 cycles

L-1 DOOR AFT EMERGENCY LIGHT INOPERATIVE. R & R L-1 DOOR SILL AFT EMERGENCY LAMP IAW AMM 33-51-05, OPS NORMAL.

Part: JAM-NUT — LOOSE (RT BLG) · airframe 66,851 hrs · 10,501 cycles

EICAS MSG, GEAR DOOR DISPLAYED. WHEN RAISING GEAR AFTER TAKEOFF, THERE WAS AIRFRAME VIBRATION. ACCOMPLISHED QRH PROCEDURES & EICAS MSG CLEARED & VIBRATION STOPPED. TORQUED RT BODY GEAR SHOCK STRUT, INBD DOOR LINKAGE ROD JAM NUT IAW MM 32-14-05. INSPECTED RT BODY GEAR DOOR ACTUATOR, NO DAMAGE OR LEAKS NOTED IAW MM 32-33-01. COMPLIED WITH MM 5-51-38 201 INSPECTIONS FOR VIBRATION. NO DEFECTS NOTED. ALSO REFER TO LP 531818.

Part: HYDRAULIC LINE — DAMAGED (NLG) · airframe 73,915 hrs · 12,779 cycles

GEAR DOOR EICAS MSG NOSE DOOR INDICATED NOT CLOSED. ON INSPECTION FOUND ONE HYD LINE & A SUPPORT BRACKET DAMAGED IN THE NOSE WW. NO OTHER DAMAGE NOTED. A REPLACEMENT BRACKET WAS FABRICATED & INSTALLED IAW EO 4432A109 AS A TIME LIMITED REPAIR. FOR FURTHER CORRECTIVE ACTION SEE ITEM 7, FLEX LINE INSTALL, & ITEM 13, BRACKET FABRICATION.

Part: CABLE — DAMAGED (DESCENT DEVICE) · airframe 65,718 hrs · 10,263 cycles

COCKPIT DESCENT DEVICE POS C DAMAGED CABLE PULLED FROM REEL, PN 379103D-23 & SN 16411. R & R DESCENT DEVICE IAW 25-61-01.

Part: HYDRAULIC LINE — LEAKING (HYDRAULIC SYS) · airframe 65,407 hrs · 10,204 cycles

DURING CRUISE EICAS MSG HYD QTY LOW. FOLLOWED QRH PROCEDURE, FLUID LOSS STOPPED AT ENG DRIVEN & DEMAND PUMPS ONE OFF. ON BASE LEG ENG & DEMAND PUMPS ONE WERE TURNED ON IAW QRH PROCEDURE AFTER GEAR & FLAPS DOWN QTY CONTINUED TO DROP. NOSE WHEEL & BODY GEAR STEERING WORKED TO SHUT DOWN. QTY AT SHUTDOWN WAS .02, FOUND HYD SYS NR 1 PRESS LINE TO C ELEVATOR AUTOPILOT SERVO LEAKING DUE TO PIN HOLE & CRACK. R & R LINE PN 272U4800-123 WITH FLEX HOSE ASSEMBLY IAW GMM 3.27.1 & AMM 20-11-05. SERVICED NR 1 SYS IAW AMM 12-17-01. PERFORMED HYD SYS PRESS LEAK CHECK & FILTER INSPECTION IAW AMM 29-11-07 & SYS 1 OPERATIONS CHECKED OK. AREA CLEANED A AUTOPILOT ELEVATOR SERVO. OPERATIONS CHECKED OK IAW AMM 22-15-01.

Part: LIGHT — DIM (COCKPIT) · airframe 64,781 hrs · 10,088 cycles

COCKPIT EMER LIGHT DIM. RELAMPED COCKPIT EMER LIGHT. OPERATIONS CHECKED OK IAW AMM 33-51-00.

Part: SENSOR — INOPERATIVE (CREW REST) · airframe 64,251 hrs · 9,986 cycles

CREW REST AREA TEMP UNCONTROLLABLE, GOES BETWEEN EXTREME HOT & COLD. AFT BULKHEAD HOT TO TOUCH. FOUND ZONE TEMP SENSOR FAN NOT WORKING. R & R, OPERATIONS CHECKED IAW AMM 21-61-03, ALL NORMAL.

Part: PDU — MALFUNCTIONED (CARGO BAY) · airframe 63,445 hrs · 9,839 cycles

AT APPROX 1920Z, WE SMELLED FUMES IN THE COCKPIT. INSPECTION, SMOKE OR FUMES IN CABIN, ACCOMPLISHED IAW AMM 05-51-56 & FOUND CARGO PDU 6L ON MAIN DECK BURNT OUT.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 62,895 hrs · 9,739 cycles

MAIN DECK STATION 1180 RBL 110 BELOW FLOOR INTERCOSTAL WEB FOUND CRACKED. INTERCOSTAL WEB CRACK REPAIRED IAW SRM 53-40-51 REPAIR 8.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 62,895 hrs · 9,739 cycles

MAIN DECK STATION 1200 RBL110 BELOW FLOOR INTERCOSTAL WEB FOUND CRACKED. INTERCOSTAL WEB CRACK REPAIRED IAW RI 53-40-10834 REV A.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 62,895 hrs · 9,739 cycles

MAIN DECK STATION 1220 LBL 109 BELOW FLOOR INTERCOSTAL WEB FOUND CRACKED. INTERCOSTAL WEB CRACK REPAIRED IAW SRM 53-40-51 REPAIR 5.

Part: SKIN — CRACKED (FUSELAGE) · airframe 62,895 hrs · 9,739 cycles

FX EXT FUSELAGE SKIN LT SIDE AT STATION 2658 FOUND CRACKED. BETWEEN STRINGER 11L - 13L. REPAIRED RI 53-87-10832 REV A.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 62,895 hrs · 9,739 cycles

MAIN DECK STATION 980 LBL 67 FLOORBEAM & UPPER CHORD FOUND CORROSION. REPAIRED IAW SRM 53-00-51 REPAIR 3.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 62,895 hrs · 9,739 cycles

MAIN DECK STATION 1220 RBL111 BELOW FLOOR INTERCOSTAL WEB FOUND CRACKED. INTERCOSTAL WEB CRACK REPAIRED IAW SRM 53-40-51 REPAIR 5.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 62,895 hrs · 9,739 cycles

MAIN DECK STATION 1180, LBL 111 BELOW FLOOR INTERCOSTAL WEB FOUND CRACK. REPAIRED IAW SRM 53-40-51 REPAIR 8.

Part: FIRE WARNING — FALSE ACTIVATION (COCKPIT) · airframe 62,822 hrs · 9,725 cycles

DURING TAKEOFF FIRE CARGO FWD WARNING RTO 95KTS FIRE WARNING, CLEARED AFTER 3 SECONDS. RETURNED TO GATE & VISUALLY CHECKED ALL COMPARTMENTS. NO STATUS MSG ON BLOCK IN. INSPECTED FWD CARGO, NO DEFECTS NOTED. ACCOMPLISHED CMC FIRE WARNING & TEST PASSED, NO DEFECTS NOTED IAW AMM 26-16-00.

Part: UPLOCK SENSOR — MALFUNCTIONED (LANDING GEAR) · airframe 62,513 hrs · 9,641 cycles

GEAR DISAGREE CAUTION EICAS MSG DURING GEAR RETRACTION WITH EXPANDED GEAR INDICATION SHOWING LT WING GEAR IN TRANSIT. RAN QRH PROCEDURES, CONDITIONS REMAIN. R & R PRIMARY UPLOCK SENSOR & ALTERNATE UPLOCK SENSOR & PERFORMED ADJUSTMENT TEST. OPERATES NORMAL IAW MM 32-61-21 COMPLETED WITH ACTION PLAN 10483. PSEU REPLACED AS PRECAUTION & OPERATES OK. REF LP 593142.

Part: WARNING SYSTEM — ACTIVATED (COCKPIT) · airframe 61,999 hrs · 9,550 cycles

LOW SPEED ABORT. BLEED 1 EICAS ON TAKEOFF ROLL, STATUS MSG BLEED HP ENG 1. NR 1 HPSOV DEACTIVATED IAW MEL 36-11-03. ITEM TRANSFERRED TO MDDR 52287.

Part: FILTER — FAILED (FUEL SYSTEM) · airframe 57,182 hrs · 8,616 cycles

ENGINE 4 FUEL FILTER EICAS MESSAGE AT APPROX 2000 FT, ENG 1 FUEL FILTER EICAS MESSAGE & RETURNED TO AIRPORT QRH PROCEDURES. DUMPED 40.0 KG FUEL. REPLACED NR 4 AND NR 1 ENGINE FUEL FILTERS AND LEAK CHECK, OPS CHECKS OK IAW MM.

Part: WARNING LIGHT — ILLUMINATED (BLEED SYS) · airframe 57,162 hrs · 8,618 cycles

ON TAKEOFF ROLL AT 60 KNOTS EICAS ANNUNCIATED BLEED 3. ABORTED TAKEOFF. MESSAGE WENT OUT AT IDLE THRUST AND BLEED HP ENG 3 MESSAGE DISPLAYED.

Part: STIFFENER — DAMAGED (BS 260) · airframe 56,947 hrs · 8,577 cycles

DURING WALKAROUND INSPECTION, MX FOUND DAMAGE ON BS 260, LBL10.75 RBL10.75, WL195.8 TWO CANTED BULKHEAD STIFFENERS, CONSISTING EDGE CRACKS MEASURING 1.00 AND 0.5" LONG (REF FIG 1). DAMAGE TO THE STIFFENERS EXCEEDS THE SRM 53-10-08-1A-2 ALLOWABLE DAMAGE LIMITS. PERFORMED A TIME LIMITED REPAIR.

Part: SKIN — GOUGED (FUSELAGE) · airframe 56,660 hrs · 8,522 cycles

GOUGE FOUND BY L1 DOOR, 3.80 X .125 DEEP. REPAIRED IAW EO 4453A127

Part: CHANNEL — CRACKED (BS 740) · airframe 56,660 hrs · 8,522 cycles

MAIN DECK RT STA 740, TENSION TIE AFT CHANNEL 1EA FASTENER HOLE FOUND CRACK APPROX 0.020". DETAIL IAW DWG. BS 740, RT TENSION TIE AFT CHANNEL REPAIRED IAW SRM 53-20-30-2R-1, REPAIR 1, FIG 201.

Part: CARGO TRACK — CORRODED (BS 1920) · airframe 56,660 hrs · 8,522 cycles

CARGO TRACK HAS CORROSION AT BS 1920, BL L78. CORROSION REMOVED IAW SRM 51-10-02. FOUND OUT OF LIMITS IAW SRM 53-00-52. APPLIED IAW AMM 51-24-11 CORROSION INHIBITOR COMPOUND APPLIED IAW AMM 51-24-13.

Part: CARGO TRACK — CORRODED (BS 1900-1905) · airframe 56,660 hrs · 8,522 cycles

CARGO TRACK CORROSION AT BS 1900-1905, RBL 11. REPAIRED IAW SRM FIG 53-00-52-2R-12 REPAIR 12 FIG 201, RS RI-53-25-10116 CORROSION INHIBITOR COMPOUND APPLIED IAW SRM 51-20-01.

Part: CARGO TRACK — CORRODED (BS 1953) · airframe 56,660 hrs · 8,522 cycles

MAIN DECK BS 1953, RBL 11.33 CARGO TRACK HAS CORROSION. CARGO TRACK REPAIRED IAW SRM 53-00-53 REPAIR 12 FIG 201 AND R1 RI-53-25-10117 REV A.

Part: CHANNEL — CRACKED (BS 760) · airframe 56,660 hrs · 8,522 cycles

MAIN DECK BS 760 RT TENSION TIE FWD CHANNEL TWO FASTENER HOLES FOUND CRACKED IAW NDT TEST REPORT. BS760 RT TENSION TIE FWD CHANNEL REPAIR IAW SRM 53-20-30-2R-1 REPAIR 1, FIG 201.

Part: CHANNEL — CRACKED (BS 760) · airframe 56,660 hrs · 8,522 cycles

MAIN DECK BS 760 RT TENSION TIE AFT CHANNEL 1EA FASTENER HOLE FOUND CRACKED REFER TO NDT TEST REPORT. REPAIRED IAW SRM 53-20-30-2R-1 REPAIR 1 FIG 201)

Part: BULKHEAD — CRACKED (LT MLG WW) · airframe 56,660 hrs · 8,522 cycles

BS 1241 LT MLG WW PRESSURE BULKHEAD FOUND CRACKED AT LBL 75 AREA. REPAIRED IAW RS R1-53-48-10119)

Part: CHANNEL — CRACKED (BS 720) · airframe 56,660 hrs · 8,522 cycles

M/D BS720, RT TENSION TIE AFT CHANNEL ONE FASTENER HOLE FOUND CRACKED REFER TO NDT TEST REPORT. CHANNEL REPAIRED IAW SRM 53-20-30-2R-1, REPAIR 1, FIG 201.

Part: RING — CRACKED (NR 4 ENGINE) · airframe 56,660 hrs · 8,522 cycles

NR 4 ENG RT 'C' DUCT AFT CASCADE SUPPORT RING FOUND CRACKED AT R8 CASCADE VANE NUT PLATE. REPAIRED AS PER EO 1978A067.

Part: WEB — CRACKED (BS 2331) · airframe 56,660 hrs · 8,522 cycles

WEB FOUND CRACKED AT BS 2231, STR L22. REPAIRED IAW RI NR :RI-53-62-10120)

Part: LINE — LEAKING (ENGINE OIL SYS) · airframe 56,543 hrs · 8,502 cycles

OIL QTY OF NR 4 ENGINE WENT TO ZERO. SHUTDOWN ENGINE IAW QRH. PERFORMED ENGINE INSPECTION IAW AMM 79-00-00/601. ACCOMPLISHED ENGINE WINDMILLING INSPECTION IAW AMM 72-00-00/601. DURING ENGINE INSPECTION, THE OIL PRESSURE TRANSMITTER WAS FOUND TO BE LEAKING. THE TRANSMITTER OIL LINE WAS SECURED IAW AMM 79-32-01. HIGH POWER RUN WAS ACCOMPLISHED IAW 71-00-00 AND NO LEAKS WERE NOTED. THE WINDMILL INSPECTION FOUND NO DEFECTS. ACFT DEPARTED WITH NO FURTHER INCIDENT.

Part: HEAT SHIELD — DAMAGED (NR 2 NACELLE) · airframe 55,865 hrs · 8,379 cycles

DURING REPLACEMENT OF THE NR 2 ENGINE, THE NR 2 STRUT LOWER WEB INSULATION BLANKET, "HEAT SHIELD" WAS FOUND WITH MISSING MATERIAL ON ACFT. MADE A TIME LIMITED REPAIR.

Part: SLEEVE — CRACKED (NR 3 EXHAUST) · airframe 55,329 hrs · 8,300 cycles

A CRACK WAS FOUND ON THE EXHAUST NOZZLE OUTER SLEEVE, APPROX AT 1 O'CLOCK POSITION (RT SIDE) ON THE NR 3 ENGINE. THE CRACK IS APPROX 2.5" LONG AND IS 1" FROM AFT SIDE OF EXHAUST SLEEVE JUST IN FRONT OF NAC STA 361.923. IAW SRM 54-41-30 THE DISTANCE BETWEEN THE CRACK AND THE EDGE IS OUT OF LIMITS. STOP DRILLED THE ENDS OF CRACK WITH A 0.125" DIAMETER HOLE.

Part: SKIN — DELAMINATED (RT WING) · airframe 54,571 hrs · 8,195 cycles

DELAMINATION FOUND ON L/E OF RT WING OTBD OF NR 3 ENGINE. PERFORMED TEMP REPAIR IAW EO 4457A420.

Part: BLADE — DAMAGED (NR 4 ENGINE) · airframe 54,360 hrs · 8,160 cycles

DURING BIRD STRIKE INSPECTION IAW AMM 05-51-14, ENGINE 4, FAN BLADE; 8 WAS FOUND TO HAVE DAMAGE. (FAN BLADE 8 WAS INSPECTED IAW AMM 72-31-02 AND THE DAMAGE WAS FOUND TO BE OUT OF ALLOWABLE LIMITS. FAN BLADE 8 WAS REPLACED IAW AMM 72-31-00. VIBRATION SURVEY ACCOMPLISHED IAW AMM 71-00-00.)

Part: BLADE — DAMAGED (NR 4 ENGINE) · airframe 54,360 hrs · 8,160 cycles

DURING BIRD STRIKE INSP IAW AMM 05-51-14, ENGINE 4, FAN BLADE 7 WAS FOUND TO HAVE DAMAGE. (FAN BLADE 7 WAS INSPECTED IAW AMM 72-31-02 AND THE DAMAGE WAS FOUND TO BE OUT OF ALLOWABLE LIMITS.; BLADE 7; REPLACED IAW AMM 72-31-00. VIBRATION SURVVEY ACCOMPLISHED IAW 71-00-00. )

Part: WEB — CRACKED (RT WING) · airframe 53,605 hrs · 8,032 cycles

WHILE DOING AN "A" CHECK INSPECTION OF THE RT WING FIXED T/E INBD SPOILERS SUPPORT RIBS, A 1.5 INCHES LONG CRACK WAS FOUND ON THE WEB OF THE INBD SUPPORT RIB ASSY AT WBL 255.692. THE DAMAGE EXCEEDED THE LIMITS OF THE SRM 57-51-02, FIGURE 101. CRACK REPAIRED IAW SRM 51-70-13, REPAIR 1.

Part: SKIN — DAMAGED (HORIZONTAL STAB) · airframe 53,572 hrs · 8,026 cycles

DURING WALKAROUND INSPECTION, MX REPORTED DAMAGE TO THE LT HORIZ STABILIZER L/E SKIN - SS 250 DENT - REPAIR (REF FIG 1), MEASURING 6.5" X 2.5" X 0.250". DAMAGE IS BEYOND THE SRM LIMITS IAW THE SRM 55-10-01, FIG 101, ALLOWABLE DAMAGE 1. (DISPOSITION WAS MADE TO PERFORM A TIME LIMITED REPAIR AS DESCRIBED IN PART 1 WORK INSTRUCTIONS; SCHEDULE REPEAT INSPECTIONS AT EVERY 5 FC AND PERMANENT REPAIR PRIOR TO THE ACCUMULATION OF 1,000 FH (FLIGHT HOURS) AFTER PART 1, IAW SRM 55-10-01, FIG 201)

Part: ACOUSTIC LINER — DAMAGED (THRUST REVERSER) · airframe 52,964 hrs · 7,931 cycles

DURING MX WALKAROUND, FOUND DAMAGE TO NR 2 ENGINE THRUST REVERSER ACOUSTIC MESH AND HONEYCOMB. DAMAGE IS LOCATED AT THE 5 O'CLOCK POSITION AND HAS DIMENSIONS 3' LENGTH, .3750" WIDTH AND .2500" DEPTH. REF TO FIG 1 FOR DAMAGE DETAILS. PERFORMED A TIME LIMITED REPAIR AS DESCRIBED IN PART 1 WORK INSTRUCTIONS.

Part: BEAM — DAMAGED (CARGO DOOR) · airframe 52,733 hrs · 7,897 cycles

DURING TROUBLESHOOTING ON THE AFT CARGO DOOR ACCOMPLISHED, MX FOUND DAMAGE TO THE DOOR INTERNAL BEAM (INNER CHORD OF CLOSEOUT BEAM), NEAR THE FWD HOOK PULL IN RETURN SPRINGS AT BS1810 - BS1820 WITH 2 GOUGES, MEASURING 0.187 IN. AND 0.3875 IN. FROM THE EDGE. (GOUGES WERE BLENDED OUT IAW SRM 51-10-02 (REF FIG 1). DOOR PN: 65B04250-17, SN: 001246. DISPOSITION WAS MADE TO PERFORM A TIME LIMITED REPAIR IAW SRM 51-10-02 AS DESCRIBED IN PART 1 WORK INSTRUCTIONS, 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 PER PART 3 WORK INSTRUCTIONS.)

Part: SKIN — CRACKED (RT WING) · airframe 52,655 hrs · 7,886 cycles

DURING A-CHECK INSPECTION, MX FOUND DAMAGE TO THE RT WING ILES 750 - UPPER FIXED LEADING PANEL CRACK, MEASURING 43.0" IN LENGTH; THE DAMAGE EXCEEDS THE LIMITS OF THE SRM 57-41-01, FIG 101 IAW SRM 51-70-02. ALLOWABLE DAMAGE GENERAL. PERFORMED A TIME LIMITED REPAIR.

Part: PDU — FAILED (CARGO BAY) · airframe 52,282 hrs · 7,932 cycles

DURING PROCESS OF UPLOADING ACFT, MDC PDU AT 18L FAILED (SMOKE) PDU REMOVED AND INSTALLED JUMPER AND BLACKING PLATE.

Part: SUPPORT — BROKEN (LT WING) · airframe 51,716 hrs · 7,726 cycles

FOUND SUPPORT ROD FOR LT WING T/E UPPER FIXED PANEL BROKEN AT WBL 432. REPLACED WITH NEW SUPPORT ASSY IAW AMM 57-22-01. ADJUSTED IAW AMM 57-22-01-825-001.

Part: CARRIAGE — DAMAGED (LT WING TE FLAP) · airframe 51,716 hrs · 7,726 cycles

FOUND LT INBD FLAP CARRIAGE ON OTBD TRACK CHAFED AND WORN. CARRIAGE REMOVED IAW AMM 27-51-24. INSTALLED NEW CARRIAGE IAW AMM 21-51-24.

Part: SKIN — DAMAGED (LT WING) · airframe 51,716 hrs · 7,726 cycles

FOUND LT WING T/E UPPER FIXED PANEL BETWEEN WBL 432 AND WBL 446 DAMAGED. PANEL REMOVED IAW AMM 57-22-01. LT WING T/E UPPER FIXED PANEL REPAIRED IAW EO 4457A383. REINSTALL PANEL IAW AMM 57-22-01.

Part: STRUCTURE — DAMAGED (LT WING TE FLAP) · airframe 51,716 hrs · 7,726 cycles

DURING AN A CHECK, FOUND LT INBD MID FLAP L/E INBD PART DAMAGED. VISIABLE DAMAGE AREA 1"X4.5" ALSO FOUND 3L TRACK CUTOUT WEB CRACKED. LT INBD MID FLAP REMOVED IAW AMM 27-51-01. INSTALLED NEW LT INBD MIDFLAP IAW AMM 27-51-01. ADJUST IAW AMM 27-51-01, OPS CHECKED OK.

Part: CARRIAGE — DAMAGED (LT WING TE FLAP) · airframe 51,716 hrs · 7,726 cycles

FOUND LT INBD FLAP CARRIAGE DAMAGED. LUG BROKEN AND ROLLER MISSING. CARRIAGE REMOVED IAW AMM 27-51-24. INSTALLED NEW CARRIAGE IAW AMM 27-51-24.

Part: BEARING — LOOSE (LT WING TE FLAP) · airframe 51,716 hrs · 7,726 cycles

FOUND LT OTBD FORE FLAP INBD FITTING BEARING LOOSE LT OTBD FORE FLAP IAW AMM 27-51-05. REPAIRED.

Part: SKIN — DAMAGED (AILERON) · airframe 51,716 hrs · 7,726 cycles

FOUND INBD AILERON DAMAGED IN UPPER SURFACE. LT INBD AILERON REMOVED IAW AMM 27-11-01. REPAIRED THE DAMAGED AREA REF TO SRM 51-70-11. INSTALL LT INBD AILERON AFTER REPAIR REF AMM 27-11-01. ADJUSTED AND OPS TESTED IAW AMM 27-11-00, TESTED OK.

Part: RETAINER — BROKEN (LT WING) · airframe 51,716 hrs · 7,726 cycles

FOUND LT LOWER FIXED T/E PANEL WBL129 SEAL RETAINER BROKEN. REPLACE FIXED PANEL AFT SEAL RETAINER IAW AMM 20-51-01.

Part: RIB — DENTED (AILERON) · airframe 51,716 hrs · 7,726 cycles

FOUND LT WING FIXED T/E RIB AT WBL 445.90 DENTED. AILERON REPAIRED IAW EO4457A385 PART III.

Part: STRUCTURE — DAMAGED (LT WING TE FLAP) · airframe 51,716 hrs · 7,726 cycles

DURING A CHECK INSPECTION, FOUND LT INBD FORE FLAP DAMAGED. L/E AREA DAMAGED LENGTH 1.25" FRONT SPAR WEB DAMAGE 8" X 4". LT INBD FORE FLAP REMOVED IAW AMM 27-51-02. INSTALLED NEW LT INBD FORE FLAP IAW AMM 27-51-02. ADJUST IAW AMM 27-51-01. OPS CHECKED OK.

Part: SUPPORT CHANNEL — DAMAGED (WING) · airframe 51,716 hrs · 7,726 cycles

WING RIB SUPPORT CHANNEL WAS FOUND DAMAGED AS A RESULT OF THE LT INBD T/E FLAP INCIDENT ON 412. THE DAMAGES WHICH ARE APROX 2" LONG X 0.5" DEEP AND 2.5" LONG X 0.3" DEEP ARE LOCATED ON THE OTBD AND INBD FLANGES OF THE CHANNEL. (SINCE A REPLACEMENT PART COULD NOT BE LOCATED IN TIME AND SINCE NO APPROVED DATA EXISTS TO REPAIR EXTRUDED PARTS USED AS STIFFENER ON WINGS, DISPOSITION WAS MADE TO PERFORM A TIME LIMITED REPAIR BY BLENDING OUT THE DAMAGES AND OBTAINING DER APPROVAL. HFEC INSP CONFIRMED CRACK FREE CONDITION. THE FINAL BLENDOUT DIMENSIONS ARE 3.5 IN. LONG X 0.6" DEEP AND 3.6" X 0.45" DEEP. AS SHOWN IN FIG 1.)

Part: FAIRING — CRACKED (THRUST REVERSER) · airframe 49,853 hrs · 7,433 cycles

DURING A-CHECK, ON NR2 ENGINE RT T/R TRANSCOWL, AFT FAIRING WAS FOUND WITH A CRACK APPROX 2.45 INCHES IN LENGTH. (DISPOSITION WAS MADE TO PERFORM REPAIR AS DESCRIBED IN PART 1 WORK INSTRUCTIONS. PERMANENT REPAIR AS DECRIBED IN PART 2 WILL BE PERFORMED AT 15,000 FLT HRS AFTER ACCOMPLISHMENT OF PART 1 OF THIS EO.

Part: SKIN — DAMAGED (BS 1937 S37R) · airframe 49,338 hrs · 7,363 cycles

DURING WALK-AROUND INSP, MX REPORTED DAMAGE WAS FOUND TO THE RT FUSELAGE SKIN BS1937, BELOW S37R (THE DAMAGE IS BEYOND THE SRM 53-00-01, FIGURE 101 ALLOWABLE DAMAGE 1, DETAIL III LIMITS. TIME LIMITED REPAIR ACCOMPLISHED AS DESCRIBED IN PART 1 WORK INSTRUCTIONS, SCHEDULE REPEAT DVIS AT EVERY 5 FC (IAW PART 2), SCHEDULE HFEC INSPECTION PRIOR ; ACCUMULATION OF 5 FC (FLIGHT CYCLES) AND PERMANENT REPAIR PRIOR TO THE ACCUMULATION OF 4,000 FH (FLIGHT HOURS) AFTER PART 1, AS SCHEDULE BY MX PLANNING.)

Part: SKIN — DENTED (BS 1928.5 S38R) · airframe 49,338 hrs · 7,363 cycles

DURING WALK-AROUND INSPECTION AT ANC, MX REPORTED DAMAGE WAS FOUND TO THE RT FUSELAGE SKIN BS1928.5, BELOW S38R; 1 INCH DIAMETER. EO 4453A552 (THE DAMAGE IS BEYOND THE SRM 53-00-01, FIGURE 101 ALLOWABLE DAMAGE 1, DETAIL III LIMITS. TIME LIMITED REPAIR ACCOMPLISHED AS DESCRIBED IN PART 1 WORK INSTRUCTIONS.

Part: SKIN — DAMAGED (LT WING TE FLAP) · airframe 49,338 hrs · 7,363 cycles

THE PURPOSE OF THIS EO IS TO DOCUMENT A MAJOR REPAIR. DURING WALK-AROUND INSP, MX REPORTED LT OTBD MID FLAP - WBL 597 - WBL 730 - T/E - DELAMINATION/DAMAGE (PN: 65B01925-311C / SN: 000551) - T/E MEASURING 11.0 FT. X 7.5 IN. (REF FIGURE 1). (DISPOSITION WAS MADE TO PERFORM A TIME LIMITED REPAIR AS DESCRIBED IN PART 1 WORK INSTRUCTIONS (SANDWICH TYPE W/ EXTERNAL ALUMINUM DOUBLERS (4 EA.) W/3 ROWS OF CHERRY MAX FASTENERS AROUND THE DAMAGE); SCHEDULE REPEAT INSPECTIONS AT EVERY 1 FC (FLIGHT CYCLE) IAW PART 2 AND PERMANENT REPAIR, IAW PART 3 BY REPLACING THE MID FLAP PRIOR TO THE ACCUMULATION OF 25 FLIGHT CYCLES AFTER PART 1.)

Part: WARNING MESSAGE — ILLUMINATED (MLG) · airframe 48,495 hrs · 7,342 cycles

CONFIGURATION GEAR CENTER, TAKEOFF WARNING AT APPROX 20 KTS. REJECTED TAKEOFF(BODY GEAR STEERING INDICAITON SYSTEM DEACTIVATED AND DEFERRED. BODY GEAR SYSTEM CONFIRMED DEACTIVATED)

Part: SUPPORT FITTING — DAMAGED (BS 2658) · airframe 48,153 hrs · 7,180 cycles

DURING D-CHECK INSP OF DATUM ACFT, DAMAGE (WORN HOLE) WAS FOUND ON SUPPORT FITTING OF APU LT SUPPORT LINK FWD SIDE AT STA 2658 (REFER TO FIG 1 FOR DAMAGE LOCATION). (THE REPAIR (FIG 2) WAS PERFORMED IAW EGA-TLS-11-0009 AND WAS APPROVED IAW SR 1-1777633064 AND RDR DATED JAN. 21, 2011 (FIG 3). NOTE: THE REPAIR BUSHING WAS FABRICATED DIRECTLY FROM 1.0 IN DIA 17-4PH H925 (180-200 KSI, HRC 40-43) CONDITION IAW AMS 5643.)

Part: SUPPORT — CHAFED (LT WING) · airframe 48,154 hrs · 7,180 cycles

CHAFING DAMAGE ON THE SEAL SUPPORT OF LT WING FIXED T/E SPOIL SUPPORT RIB AT WX 863.73. REPAIR IAW EI NR T201157B-154. REV 00.

Part: FRAME — DAMAGED (BS 2638) · airframe 48,154 hrs · 7,180 cycles

HEAT DAMAGE ON THE FRAME INNER CHORD AT STA 2638, WL 285 LT SIDE. REPAIRED IAW EI NR T2011 A53B-139 REV EO 00, 01,02 AND 03.

Part: STRUCTURE — DEFORMED (BS 1826) · airframe 48,153 hrs · 7,180 cycles

DURING D-CHECK INSP OF DATUM ACFT, DAMAGE (DEFORMATION) WAS FOUND ON AFT CARGO SEAT TRACK AT BS 1826, RBL25. (THE DAMAGE AREA WAS REPAIRED IAW SRM 53-00-52, REPAIR 10.)

Part: STIFFENER — DAMAGED · airframe 48,154 hrs · 7,180 cycles

DURING THE D02 PLUS C03, GENERAL DAMAGE WAS DETECTED ON STIFFENER, DEFORMED DAMAGE WAS DETECTED ON 65B04925-47 STIFFENER, AND IMPACT CRACK DAMAGE WAS DETECTED ON THE 65B04925-84 STIFFENERS (2 PLACES).( REPAIR OF GENERAL DAMAGE ON 65B04325-42 STIFFENER AT BS 1760/S-43R-44R, AS DOCUMENTED IAW EGAT NCR 694 WAS REPAIRED IAW EGAT EI T2011P53B-176. THE DAMAGED STIFFENER WAS REMOVED AND REPLACED. REPAIR OF DEFORMED DAMAGE ON 65B04925-47 STIFFENER AT BS 1640/S-47-49R, AS DOCUMENTED IAW EGAT NCR 693 WAS REPAIRED IAW EGAT EI T2011P57B-142. THE DAMAGED STIFFENER WAS R & R. REPAIR OF CRACK IMPACT DAMAGE ON 65B04925-84 STIFFENER AT BS 1640/S-49R AND BS 1720/S-49R, AS DOCUMENTED IAW EGAT NCR 692/693 WERE REPAIRED IAW EGAT EI T2011P53B-177. THE DAMAGED STIFFENERS (2 PLACES) WERE R & R.

Part: INTERCOSTAL — CRACKED (BS 2020-2080) · airframe 48,154 hrs · 7,180 cycles

CRACK ON BULK CARGO FLOOR INTERCOSTALS AT STA 2020, RBL 0.25 AND STA 2080, RBL 0.25". (REPAIRD IAW EI 2011A53B-122 REV 00 AND 01.)

Part: SKIN — DENTED (BS 2600 S42R) · airframe 48,154 hrs · 7,180 cycles

CREASE AND DENT DAMAGE ON RT FUSELAGE SKIN AT STA 2600 S-42R LWR AFT TAIL JACK PAD AREA. (REPAIRED IAW EI NO T2011 A53B-093REV.00. AND REV 01.)

Part: WEB — BROKEN (BS 1760 S43-44R) · airframe 48,154 hrs · 7,180 cycles

BROKEN WEB AFT LWR CARGO STRUCTURE AT STA 1760 BETWEEN STRINGER S43R TO S44R (REPAIR DAMAGE AREA IAW SRM 51-70-13, REV 58)

Part: SKIN — GOUGED (BS 1920-1940) · airframe 48,154 hrs · 7,180 cycles

DURING D02 PLUS C03 CHECK OF DATUM ACFT, GOUGE DAMAGE (1 IN LONG AND 0.003 IN WIDE) WAS FOUND ON THE FUSELAGE SKIN BETWEEN BS 1920-BS 1940 AND S-33L - S-34L.(THE SURFACE FINISH OF THE BLENDED AREA WAS INSPECTED AND VERIFIED TO BE 125 MICROINCHES OR BETTER. THE BLENDED AREA WAS ALSO INSPECTED AND VERIFIED TO BE FREE OF ANY DEFECTS IAW SOPM 20-20-02. THE PRE-EXISTING OPEN HOLES (3 PLACES) IN THE BLENDED AREA WERE HFEC INSPECTED AND VERIFIED TO BE FREE OF ANY DEFECTS IAW NDT MANUAL PART 6 51-00-00. THE FINAL REPAIR ACTION FOR THE BLENDED AREA WAS TO "FLAP PEEN" REWORKED WITH 0.06A INTENSITY IAW SRM 51-20-06.)

Part: PANEL — BROKEN (BS 1720) · airframe 48,154 hrs · 7,180 cycles

DAMAGE WAS FOUND ON M/D CARGO COMPARTMENT DADO PANEL (P/N 453U7023-33). AT STA 1720(REPAIR IAW EI NO T2011A53B-131 REV 00)

Part: STRUCTURE — DAMAGED (BS 1640) · airframe 48,154 hrs · 7,180 cycles

PERFORM AFT CARGO LWR CHORD STRUCTURE AT STA 1640 BETWEEN STRINGER S49R TO S47R. (REPAIR DAMAGE AREA IAW SRM 51-70-13. REV 58)

Part: FRAME — CRACKED (THRUST REVERSER) · airframe 48,154 hrs · 7,180 cycles

REPAIR NR 4 ENG RT FAN REVERSER TORQUE BOX FWD FRAME CRACK. (REPAIR IAW EI NO T2011 A78B-208 REV 00)

Part: SKIN — DAMAGED (BS 2600 S42R) · airframe 48,154 hrs · 7,180 cycles

DURING D02 PLUS C03 CHECK OF DATUM ACFT, CREASE DAMAGE AND A DENT LOCATED ON THE RT FUSELAGE SKIN AT BS 2060 AND S-42R (LOWER AFT SIDE OF TAIL JACK'S LOCATION) WERE SCHEDULED FOR A PERMANENT REPAIR. THE DAMAGED AREAS WERE PREVIOUSLY REPORTED IAW SR 1-182699542 AND APPROVED IAW FAA FORM 8100-9 (DATED 24 APRIL 2006) TO ALLOW THE DELAY OF THE REPAIR WITH REPEAT INSP UNTIL THE NEXT SCHEDULED MX. TO REMOVE THE CREASE DAMAGE AND THE DENT FROM THE 65B02707-3 SKIN, A SQUARE AREA ENCOMPASSING THE DAMAGED AREAS WAS CUT FROM BOTH THE 65B02707-3 SKIN AND THE 65B02707-5 DOUBLER. TO RESTORE THE SKIN AND DOUBLER BACK TO THEIR ORIGINAL STRENGTH, AN EXTERNAL DOUBLER WAS INSTALLED OVERLAPPING THE CUTOUT AREA AND A FILLER WAS INSTALLED INTO THE CUTOUT AREA OF THE SKIN/DOUBLER IAW THE REQUIREMENTS OF SRM 53-00-01, REPAIR 15, FIG 201. THE REPAIR CONSISTS OF AN 0.090 INCH THICK 7075-T6 AL CLAD SHEET DOUBLER AND A 7075-T6 AL CLAD SHEET FILLER WITH THICKNESS AS REQUIRED TO FILL CUTOUT AREA FLUSH WITHIN +/-0.005 INCHES OF SURROUNDING SURFACES.

Part: RIB — CRACKED (BS 1318) · airframe 48,154 hrs · 7,180 cycles

CRACKS ON LT HST L/E RIB AND CLIP AT L/E STA 1318 ( REPLACED CLIP IAW EO NO T2011P55B-188, REV 00. 2. REPAIRED CRACK RIB IAW EI NO T2011A55B-184 REV 00.)

Part: PANEL — DAMAGED (BS 1720) · airframe 48,154 hrs · 7,180 cycles

DAMAGE WAS FOUND ON M/D CARGO COMPARTMENT DADO PANEL (P/N 453U7023-33). AT STA 1720(REPAIR IAW EI NO T2011A53B-131 REV 00)

Part: FRAME — WORN (NR 4 NACELLE) · airframe 48,154 hrs · 7,180 cycles

WORN NR 4 ENG LT CORE COWL INNER FRAME WORN AT 7:00 POS. (REPAIR IAW 747-400 SRM 54-45-02. REPAIR 1. REV 58)

Part: SUPPORT — CRACKED (LT WING TE) · airframe 48,154 hrs · 7,180 cycles

REPAIR CRACK ON THE CHORD OF THE LT WING FIXED T/E LWR SUPPORT STRUCTURE AT WS 1293. (REPAIR IAW T2011A57B-157, REV 00.)

Part: FRAME — WORN (NR 4 NACELLE) · airframe 48,154 hrs · 7,180 cycles

WORN NR 4 ENG LT CORE COWL INNER FRAME WORN AT 7:00 POS. (REPAIR IAW 747-400 SRM 54-45-02. REPAIR 1. REV 58)

Part: COWLING — CHAFED (NACELLE) · airframe 48,154 hrs · 7,180 cycles

CHAFING FOUND NR 1 ENG LT CORE COWL HAD CHAFING ON INTERIOR FRAME AREA AT ABOUT 3:00. (REPAIR DAMAGE AREA IAW SRM 54-45, FIG 201, REPAIR 1. REV 58.)

Part: SKIN — DENTED (THRUST REVERSER) · airframe 48,154 hrs · 7,180 cycles

REPAIR 2 EA DENTS ON LOWER SIDE WALL FLOW PATH SKIN OF NR1 ENG; RT FAN REVERSER (REPAIR IAW EI NO. T2011A38B-155 REV 00.)

Part: SHIM — MIGRATED (BS 2517) · airframe 48,154 hrs · 7,180 cycles

SHIM MIGRATION UNDER FIN TO BODY SUPPORT FITITNG AT STA 2517 LBL/RBL 25 (IAW EO T2011A53B-135, REV 00) REPLACE NEW SHIM.

Part: PANEL — CRACKED (BS 1315) · airframe 48,154 hrs · 7,180 cycles

LT LONGERON BOX FAIRING & NBSP; PANEL CRACK (REPAIR IAW SRM 51-70-07, REV 58).

Part: PROBE — BROKEN (EGT) · airframe 47,587 hrs · 7,079 cycles

DURING ROUTINE MX "A" CHECK IN PVG, MX WAS ACCOMPLISHING EO 4477A003 AND BROKE OFF AN EGT PROBE ON NR 3, ESN 706125 AT THE 11:30 (PROBE NR 6) POSITION LEAVING THE REMAINDER OF THE PROBE IN THE LPT BOSS INACCESSABLE FOR REMOVAL. AS IAW AMM TASK 77-21-00-216-001-J00, TABLE 602 DISPATCH IS ALLOWED FOR 1EA DEACTIVATED PROBE. (DISPOSITION IS TO DEACTIVE THE EGT PROBE IAW THE AMM AND REPLACE THE ENG WITHIN 10 FLIGHT CYCLES.)

Part: SKIN — CRACKED (FUSELAGE) · airframe 46,664 hrs · 6,949 cycles

DURING A-CHECK, GOUGES AND A CRACK WERE FOUND IN THE FUSELAGE BELLY SKIN BETWEEN BS 2585 AND 2587 AND S-47L AND -47R. REFER TO FIG 1 FOR DAMAGE LOCATION AND DESCRIPTION. (THE FUSELAGE SKIN AT THE DAMAGE LOCATION IF MADE FROM A 0.050 INCH THICK SKIN WITH A 0.040 INCH THICK BONDED DOUBLER, BOTH MADE FROM 7075-T6 ALUMINUM IAW SRM 53-80-01, FIG 1, ITEM 6. PART 1 OF THIS EO REMOVES THE DAMAGE AND INSTALLED A REPAIR IAW SRM 53-00-01, FIG 201, REPAIR 1. PART 2 OF THIS EO ACCOMPLISHES THE REPETITIVE INSPECTIONS REQUIRED FOR THIS CATEGORY B REPAIR.)

Part: SEAT TRACK — DAMAGED (BS 1880) · airframe 41,720 hrs · 6,200 cycles

DURING DAILY CHECK INSP, DAMAGE TO THE LWR AFT CARGO COMPARTMENT - BS 1880, RBL 46.0 SEAT TRACK - CRACKED / DAMAGE WAS FOUND (ACCOMPLISH REPAIR TO THE LOWER AFT CARGO COMPARTMENT. REMOVE/TRIM OUT THE SEAT TRACK DAMAGED SECTION IAW THE SRM 51-10-02. APPLED A CHEMICAL CONVERSION COATING AND PRIMER TO REWORKED AREAS AS GIVEN IN SRM 51-20-01.

Part: STRUCTURE — DAMAGED (LT WING) · airframe 41,720 hrs · 6,200 cycles

DURING SPECIAL CHECK (TLW); A STORM DRAGGED A MX STAND IMPACTING THE LT WING - OTBD L/E AT OLES1580.95, OLES1606.95 &AMP; OLES1625.951. DENT AT OLES 1580.95 (11.0 IN. LONG X 1.750 IN. WIDE X 0.187 IN. DEEP)&NBSP; REFERENCE FIG 1. EXCEEDS THE LIMITS IAW SRM 57-41-01 FIG 101 TABLE I, DETAIL III (ALLOWABLE DAMAGE). PERMANENT REPAIR ACCOMPLISHED IAW THE SRM 57-41-01 FIG 201, REPAIR 4. DENT AT OLES 1606.95 (6.0 IN. LONG X 0.750 IN. WIDE X 0.062 IN. DEEP) REF FIG 2. WITHIN THE LIMITS IAW SRM 57-41-01 FIG 101, TABLE I, DETAIL III (ALLOWABLE DAMAGE). DENT MUST BE SMOOTH AND FREE FROM SHARP CREASES, GOUGES OR CRACKS AND SHOW NO SIGN OF PULLED OR LOOSE RIVETS, REF SRM 51-10-02. HFEC INSP PERFORMED IAW NDT MANUAL PART 6, 51-00-00, FIG 4 AND/OR FIG 23 W/NIL FINDINGS. DENT AT OLES 1625.95 (6.0 IN. LONG X 1.750 IN. WIDE X 0.187 IN. DEEP) REF FIG 3. WITHIN THE LIMITS IAW SRM 57-41-01, FIG 101 TABLE I, DETAIL III (ALLOWABLE DAMAGE). DENT MUST BE SMOOTH AND FREE FROM SHARP CREASES, GOUGES OR CRACKS AND SHOW NO SIGN OF PULLED OR LOOSE RIVETS, REF SRM 51-10-02. HFEC INSP PERFORMED IAW NDT MANUAL PART 6, 51-00-00, FIG 4 AND/OR FIG 23 W/NIL FINDINGS.(THE REPAIR ACCOMPLISHED IAW PART 1 (ITEM 1) WAS PERFORMED IAW SRM 57-41-01 FIG 201, REPAIR 4; WHICH IS FAA APPROVED. NO SUPPLEMENTAL INSP ARE REQUIRED.)

Part: OUTFLOW VALVE — MALFUNCTIONED (CABIN AIR) · airframe 46,036 hrs · 6,856 cycles

ACFT WOULD NOT MAINTAIN CABIN PRESSURE, ALT 310. FLIGHT CREW FOLLOWED QRH PROCEDURES; RETURNED TO STATION. (FUEL REMOVED PRIOR TO LANDING: 62.0.&NBSP; LANDING WT: 302,056) (UPON INSP, MX FOUND RT OUTFLOW VALVE AUTO MODE INOPERATIVE, MANUAL OPS NORMAL. RT OUTFLOW DEACTIVATED IN CLOSED POSITION IAW DDG AND AMM. CABIN PRESSURE CHECK NORMAL.)

Part: SKIN — CRACKED (NR 2 NACELLE) · airframe 45,181 hrs · 6,728 cycles

DURING MX WALKAROUND, MX FOUND 2EA CRACKS ON THE NR2 RT ENGINE CORE COWL OUTER SKIN. 1EA CIRCUMFERENTIAL CRACK IS APPROX 0.5 IN. LONG AND THE OTHER CRACK IS APPROX 2.0 IN. LONG. THE LENGTH AND THE SPACING OF THE CRACKS EXCEED THE SRM LIMITS. DISPOSITION IS TO STOP DRILL THE LOWER ENDS OF THE CRACK WITH A 0.250 IN. DIAMETER HOLE; DVI EVERY 3 FLIGHT CYCLES; AND PERMANENT REPAIR AT THE NEXT "A" CHECK AFTER PART 1. THIS EO IS APPROVED BY DER (DERT-710167-SW) VIA FAA 8110-3 FORM ISSUED ON 11MAY10; SINCE THE DAMAGE EXCEEDS THE SRM 54-41-01, FIG 101 LIMITS.

Part: BRAKE ASSY — FIRE (ZONE 700) · airframe 44,608 hrs · 6,646 cycles

ON TAXI, GROUND CREW NOTED FIRE COMING FROM NR 2 TIRE/BRAKE ASSY AND SMOKE COMING FROM THE NR 1 TIRE/BRAKE ASSY. R & R NR 1 AND NR 2 TIRE AND BRAKE ASSEMBLIES.

Part: ACCESS PANEL — CRACKED (NR 3 PYLON) · airframe 43,927 hrs · 6,543 cycles

CRACKS WERE FOUND IN THE NR 3 PYLON INBD ACCESS PANEL 472FL AS SHOWN IN FIGURE 1. NR 3 PYLON ACCESS PANEL 452FL CRACKED AREA REPAIRED IAW EO 4454A095.

Part: STRUCTURE — DAMAGED (LT WING TE FLAP) · airframe 42,080 hrs · 6,255 cycles

LT WING INBD MID FLAP L/E FOUND DAMAGED AT MOST INBD AREA. PERMANENT REPAIR PERFORMED IN ACFT WITH THE SRM 41-70-07 AND SRM 57-53-01 FIG 201, TABLE 1.

Part: WARNING MESSAGE — INTERMITTENT (EICAS) · airframe 41,537 hrs · 6,177 cycles

ENROUTE EICAS STARTER CUTOUT ENG 3 ON/OFF INTERMITTENTLY. ACCOMPLISHED PROCEDURES IAW FIM 80-03-11-00. MESSAGE CLEARED. NO LATCHED FAULTS.

Part: SKIN — GOUGED (LT WING TE FLAP) · airframe 43,927 hrs · 6,543 cycles

LT T/E INBD MID FLAP - INBD L/E SKIN PANEL - WBL 137.55 WITH A GOUGE HOLE/DAMAGE. (ONE FACE SKIN AND HONEYCOMB DAMAGE WITHOUT INTERNAL SKIN DAMAGE). MEASURING 1.0 IN X 10.0 IN. "EA4457A195: DISPOSITION WAS MADE TO PERFORM A TIME LIMITED REPAIR AS DESCRIBED IN PART 1 WORK INSTRUCITONS. SCHEDULE REPEAT INSPECITONS AT EVERY A CHECK AND PERMANENT REPAIR AT THE NEXT C CHECK AFTER PART 1."

Part: SKIN — DAMAGED (LT WING TE FLAP) · airframe 42,320 hrs · 6,382 cycles

LT T/E INBD MID FLAP INBD L/E SKIN PANEL WBL 137.55 WITH A GOUGE HOLE/DAMAGE (ONE FACE SKIN AND HONEYCOMB DAMAGE WITHOUT INTERNAL SKIN DAMAGE MEASURING 1.0 IN X 10.0 IN. "TIME LIMITED REPAIR AS DESCRIBED IN PART 1 WORK INSTRUCTIONS OF EO 4457A195. SCHEDULE REPEAT INSPECTIONS EVERY A-CHECK AND PERMANENT REPAIR AT THE NEXT C-CHECK AFTER PART 1. "

Part: TRAY — CRACKED (BS 1798-1800) · airframe 43,927 hrs · 6,543 cycles

TRAY CRACKED AT STA 1800 IN AFT CARGO COMPT RT SIDE. "DRILL 0.25 DIA STOP HOLE. MAKE 2 REPAIR PLATES WITH 0.071 7075 = TE CLAD SHEET. INSTALL REPAIR PLATES IAW SRM 53-00-53/206."

Part: STRUCTURE — BROKEN (LE FLAP) · airframe 43,927 hrs · 6,543 cycles

THE CORNER AT OTBD AFT L/E WING FLAP WAS BROKEN. (0.5" X 0.5"). 1. "REMOVED THE DAMAGE AS SRM 51-70-17. 2. "LAY-UP REPAIRED THE DAMAGE WITH EA9390A/B RESIN BM 59-3 TYH-2. FABRIC AS SRM 51-70-17. CURED UNDER VACUUM. 3. "SANDED SMOOTH THE REPAIR AREA AS SRM 51-70-17. 4. "RESTORED THE FINISH AS AMM 51-21-00"

Part: UNKNOWN — ODOR (CABIN) · airframe 40,370 hrs · 6,112 cycles

MULTIPLE BLEED OVHT EICAS MESSAGES, COMPLETED QRH PROCEDURES, SMELLED BURNING ODOR. CLOSED LT BLEED SHUTOFF VALVE. STATUS MESSAGE BLEED PRV ENG 2. PERFORMED ENGINE RUN WITH BLEED OFF AND ON. NO BURNING ODOR PRESENT. DISPATCHED THE ACFT WITH HIGH STAGE BLEED LOCKED OUT AND THE THRUST REVERSER STOWED AND DEACTIVATED IAW THE MEL.

Part: FLOORBOARD — DAMAGED (BS 1500) · airframe 36,935 hrs · 5,512 cycles

RT MAIN DECK BS 1500 FLOORBOARD DAMAGED. "TIME LIMITED REPAIR AS DESCRIBED IN PART 1 WORK INSTRUCTIONS OF EO 4453A238, INITIATE INSPECTIONS AT EVERY 5 FLIGHT CYCLES. SCHEDULE PERMANENT REPAIR AT THE NEXT A CHECK AFTER PART 1 IN ACC WITH THE SRM 53-00-50 FIG 201. "

Part: SKIN — GOUGED (BS 1765 S34-35R) · airframe 39,195 hrs · 5,822 cycles

BS 1765 STRINGER 34-35R SKIN GOUGED. GOUGE REPAIRED AS PER BOEING MESSAGE 1-1165-0369-47-2 AND EO4453A227.

Part: STRUCTURE — DENTED (LEADING EDGE FLA) · airframe 39,195 hrs · 5,822 cycles

NR 1 LEADING EDGE DEVICE BULLNOSE DENTED. REPAIRED AS PER SRM 57-43-02

Part: SKIN — DENTED (LE FLAP) · airframe 39,195 hrs · 5,822 cycles

NR 10 VC FLAP BULLNOSE HAS DENT. REPAIRED AS PER SRM 57-43-02.

Part: SKIN — LOOSE (LT WING LE) · airframe 39,195 hrs · 5,822 cycles

LEFT WING LEADING EDGE FAIRING AT OUTBOARD OF LANDING LIGHT FOUND LOOSE RIVETS. LEADING EDGE REPAIRED AS PER SRM 57-41-01-2R-5 REPAIR 5 FIG 201.

Part: SKIN — LOOSE (RT WING LE) · airframe 39,195 hrs · 5,822 cycles

RIGHT WING LEADING EDGE FAIRING AT OUTBOARD OF LANDING LIGHT FOUND LOOSE RIVETS. LEADING EDGE SKIN REPAIRED AS PER SRM 57-41-01-2R-5 REPAIR 5 FIGURE 201.

Part: DRIVE ASSY — FAILED (WX RADAR SYS) · airframe 39,042 hrs · 5,909 cycles

AIR TURN BACK, CREW PHONE PATCHED THAT THEY LOST NR 1 WX RADAR SYSTEM. NR 2 WX RADAR SYSTEM WAS ALREADY ON DEFERRAL. CREW RETURNED TO BKK. MAINTENANCE REMOVED AND REPLACED RADAR DRIVE ALL SYSTEMS, OPS CHECKED OK.

Part: RADAR — FAILED (WEATHER RADAR) · airframe 37,957 hrs · 5,652 cycles

RIGHT WEATHER RADAR FAILED APPROX 1 HOUR INTO FLIGHT. LEFT RADAR FAILED WHEN SELECTED. PERFORMED AIR TURNBACK. REMOVED DRIED AND REINSTALLED THE WAVE GUIDE DUE TO WATER CONDENSATION. REPLACED RADAR ANTENNA MOUNT AND RADAR CONTROL PANEL. WEATHER RADAR CONTROL PANEL RADAR TEST CARRIED OUT OKAY.

Part: IDG — CHAFED (NR 3) · airframe 33,965 hrs · 5,119 cycles

EICAS MESSAGE "ELEC GEN OFF 3" GCB RESET PER QRH, OPERATION NORMAL MOMENTARILY THEN REOCCURRENCE. DIVERTED TO NRT. FOUND CHAFF ON NR 3 IDG T2 HARNESS. PERFORMED REPAIR AS PER SWPM 20-10-13 PAGE 41 PART 2T. THIS ITEM MUST BE REPAIRED WITHIN 500 FLIGHT HOURS.

Part: SEAT TRACK — DAMAGED (BS 1550) · airframe 32,096 hrs · 4,863 cycles

MAIN DECK CARGO CTR PALLET LOCK AT STA 1550 UNABLE TO USE LOCK IN POSITION UNTIL FLOOR AND SEAT TRACK REPAIR. SEAT TRACK REPAIRED AT STA 1550 RBL 10 IAW SRM 53-00-52 AND XEO 53-081107-1 AND FLOOR BOARD AT STA 1550 RBL REPAIRED PER SRM 51-70-07.

Part: SEAT TRACK — DAMAGED (ZONE 500) · airframe 32,096 hrs · 4,863 cycles

LWR AFT CARGO COMPARTMENT SEAT TRACK CROWN DAMAGED AT STA 1880 RBL 25. DAMAGED SEAT TRACK SECTION REMOVED AND REPLACED PER SRM 53-00-53 REPAIR NR 7 AND 10 AND XEO 53-081107.

Part: CONNECTOR — DISCONNECTED (NLG STEERING) · airframe 31,802 hrs · 4,821 cycles

RTO EICAS MSG "CONFIG GEAR STR" WITH HORN AND LIGHTS. SUSPECT WARNING IS DUE TO BODY GEAR STEERING SYS MSG MEL 32-53-2 APPLIES. MAINTENANCE PROCEDURE CARRIED OUT. ELECTRICAL CONNECTORS OF BOTH STEERING ACTUATORS ON RT BODY GEAR DISCONNECTED AND STOWED. ITEM DEFERRED.

Part: PANEL — DENTED (TE FLAP) · airframe 30,721 hrs · 4,676 cycles

LT O/B AFT FLAP HAS UPPER ALUMINUM HONEYCOMB PANEL DENTS. REPAIRED IAW XEO- 57-042307-3.

Part: STRUCTURE — DAMAGED (RT AILERON) · airframe 30,721 hrs · 4,676 cycles

RIGHT INBOARD AILERON OUTBOARD AFT CORNER DAMAGED TO PREVIOUS REPAIR APPROX 3.0" BY 4.0". REPAIRED IAW XEO- 57-042307-1

Part: STRUCTURE — DAMAGED (TE FLAP) · airframe 30,721 hrs · 4,676 cycles

RIGHT OUTBOARD AFT FLAP HAS A NICK IN THE TRAILING EDGE AS MARKED 0.25" BY 0.25". REPAIRED IAW XEO- 57-042307-2.

Part: RIB — CRACKED (NR 8 SPOILER) · airframe 30,721 hrs · 4,676 cycles

RT FIXED T/E PANEL SUPPORT RIB OUTBOARD OF NR 8 SPOILER. HAS 1 CRACK IN RIB WEB APPROX 2" IN LENGTH. REPAIRED IAW XEO- 57-042307-5.

Part: DOOR — DAMAGED (MLG) · airframe 30,721 hrs · 4,676 cycles

RT WING LANDING GEAR DOOR ELEPHANT EAR FAIRING IS DAMAGED ON THE LOWER SURFACE AS MARKED. REPAIRED IAW XEO- 52-042307.

Part: FLOOR PANEL — PUNCTURED (BS 2100) · airframe 30,721 hrs · 4,676 cycles

DURING A-4 CHECK IN SYD, BULK CARGO FLOOR WAS FOUND PUNCTURED AT TWO PLACES, SIZE 1"BY 1" AND .5" BY .5" WHEN FLOOR WAS REMOVED. REPAIRED IAW XEO- 53-042407.

Part: FIRE WARNING — UNKNOWN · airframe 30,278 hrs · 4,512 cycles

ON CLIMB-OUT, FIRE WARNING BELL RANG INTERMITTENT EVERY FEW SECONDS FOR 20 MINUTES OF FLIGHT. NO OTHER INDICATION. MAWEA SYS CYCLED, MAWEA OPERATION CHECK CARRIED OUT AND FOUND NORMAL AS PER AMM 31-51-00, 715-014.

Part: PRESSURE SWITCH — DAMAGED · airframe 28,329 hrs · 4,336 cycles

RTO, DUE TO - BLEED NR 2 EICAS MSG, LOW SPEED (70 KTS) ABORT. REMOVED AND REPLACED OV PRESSURE SWITCH IAW MM 36-12-03, OPS CHECK OK.

Part: FLAP — CHAFED (LT WING) · airframe 26,492 hrs · 4,080 cycles

LEFT HAND OUTBOARD AFT FLAP END WEAR/CHAFE MARK. RANGING IN DEPTH FROM 0.002' TO 0.013'AND FROM 8"X1" IN DIAMETER TO 2"X1".

Part: COOLING FAN — CONTAMINATED (BS 589) · airframe 25,404 hrs · 3,924 cycles

ON TRANSIT FLIGHT CREW AND ENGINEERING CREW REPORT BURNING SMELL THROUGHOUT FLIGHT DECK AND NOTICEABLE IN MAIN EQUIPMENT CENTER AND FORWARD CARGO. DEFECT INVESTIGATED, SMELL ISOLATED TO EQUIPMENT COOLING SUPPLY FAN/CENTER RISER FILTER OIL CONTAMINATION. BOTH SUPPLY FAN/FILTER REPLACED, FUNCTIONALLY TESTED PER MM 21-28-00.

Part: NOSE COWL — DENTED (ENGINE)

ENGINE 1 NOSE COWL AT 4 O`CLOCK POSITION DENT AT LIP 5.6 INCHES X 4.2 INCHES X 0.224 INCH. DENTED AREA TRIMMED OUT AND SRM WAS PERFORMED. INSTALLED DOUBLER AND FILLER IAW SRM USING BLIND .1562 FASTENERS. (K)

Part: SKIN — DENTED (FUSELAGE)

STA 2660-2680, 2 DENTS FOUND ON EXT SKIN. REPORTED DENT WAS REPAIRED IAW SRM. PERFORMED HFEC INSP, NO CRACKS WERE FOUND. AFTER SECONDARY INSP FOUND DENT, CREASE, AND CHAFING 2.5 INCH X 1.5 INCH X 0.050 INCH. DOUBLER REPAIR PERFORMED IAW SRM. (K)

Part: SKIN — DENTED (FUSELAGE)

STA 1980-2000, STR 42-44, RT (2 EA) DENT (A) AND (B) WERE FOUND ON THE EXT FUSELAGE. DENT (A) STA 1980-2000, STR 42-43, RT D=0.09, W=1.15 INCH, L=3.8 INCH. DENT (B) STAT 1980-2000, STR 43-44, RT D=0.051, W=1.18, L=1.54. THE DAMAGED AREA TRIMMED OUT. A REPAIR PATCH WAS INSTALLED IAW SRM. THE REPAIR DOUBLER WAS INSTALLED WITH FASTENERS IAW SRM. PERFORMED HFEC INSPECTION AROUND CUTOUT AREA, NO CRACKS WERE FOUND. (K)

Part: B-NUT — LOOSE (NR 1 ENGINE)

EICAS MESG; ENGINE NR 1 OIL PRESSURE. CONFIRMED OIL PRESSURE BELOW 10 PSI. SHUTDOWN NR 1 ENGINE. CONFIRMED NR 1 ENGINE OIL QTY LOW, AND ON INSPECTION FOUND B-NUT LOOSE FROM OIL TUBE CONNECTED TO FRONT OF MAIN GEAR BOX AT 6 O’CLOCK POSITION. SERVICED ENGINE OIL TO FULL AND SECURED B-NUT IAW MM 79-10-00. PERFORMED INSPECTION ON MAIN OIL SCREEN, CHIP DETECTOR AND SCAVENGE SCREEN IAW MM 79-21-06 AND MM 79-21-04 NO CONTAMINATION FOUND. PERFORMED WINDMILL INSPECTION IAW MM 72-00-00, PAGE 206. NO DEFECTS NOTED. PERFORMED HIGH POWER RUN UP, ALL INDICATIONS NORMAL. REINSPECTED ALL SCREENS, ALL NORMAL.

Part: GASKET — DAMAGED (NR 4 ENGINE)

DURING CRUISE ENGINE SHUT DOWN DUE TO FUEL IMBALANCE. POSSIBILITY OF A FUEL LEAK NR 4 ENGINE. FUEL IMBALANCE BETWEEN MAIN NR 1 TANK, AND MAIN NR 4 TANKS. FUEL ENROUTE WAS 1.3 TO 1.4 TOTALIZER 22.6 WHILE CALCULATED 25.6, LEAK COULD BE DOWN STREAM OF FUEL CONTROL UNIT NR 4. LEAK CONFIRMED VISUALLY. ACCOMPLISHED ENGINE SHUT DOWN. REMOVED NR 4 ENGINE HMU CHECK FOUND GASKET SEAL BROKEN; REPLACED GASKET AND INSTALLED HMU IAW MM. PERFORMED ENGINE WET MOTOR TEST ECU ACTUATOR GROUND TEST 12. IDLE AND ENGINE RUNUP LEAK CHECK NORMAL.

Part: PACKING — DAMAGED (NR 4 ENGINE)

EICAS MESSAGE 'FUEL IMB' VISUALLY NOTED FUEL LEAK FROM NR 4 ENGINE. ACCOMPLISHED SHUTDOWN PROCEDURES FOR NR 4 ENGINE. TROUBLESHOT FOUND NR 4 ENGINE HMU PERFORMANCE PACKING BADLY DAMAGED. PACKING REPLACED IAW MM 73-21-14. GROUND RUN FOR LEAK CHECK TEST 2, ECU ACTUATOR GROUND TEST 12, AND IDLE LEAK CHECK TEST 3 IAW MM 71-00-00 PAGE 501, ALL FOUND NORMAL. A/C DIVERTED TO BKK. (M)

Part: LINE — CRACKED (NR 4 ENGINE)

PRECAUTIONARY NR 4 ENGINE SHUTDOWN DUE TO OIL QUANTITY FALLING TO 3 QUARTS AT 1825Z, FL300, MACH .835. FOUND OIL LINE TO LUBE AND SCAVENGE PUMP CRACKED IPC 79-21-03-01 ITEM 303. REPLACED LINE IAW MM 79-21-00, SERVIED ENGINE OIL IAW MM 12-13-03. PERFORMED MPA RUN UP IAW MM 72-00-00, FOUND ALL SATISFACTORY. (M)

Part: MANIFOLD — MALFUNCTIONED (OIL PRESSURE)

HKB-DXB - NR 4 ENGINE OIL CONSUMPTION HIGH, QUANITY AT ZERO APPROXIMATELY 3 HOURS INTO FLIGHT. OIL PRESSURE LOW APPROXIMATELY 2 HOURS LATER. NR 4 ENGINE SHUTDOWN AT 1758Z, FL330, MACH .813. REPLACED OIL PRESSURE TRANSMITTER MANIFOLD. CARRIED OUT LEAK CHECK PER MM 71-00-00 NIL LEAKS EVIDENT. CARRIED OUT WINDMILL INSPECTION PER MM 72-00-00, NO DAMAGE FOUND. (M)

Part: BLADE — DAMAGED (NR 1 ENGINE)

REJECTED TAKEOFF, RUNWAY ABORT, ON TAKEOFF 2 LOUD BANGS/SHAKES AT 100 KIAS. EICAS MESSAG 'BRAKE TEMP'. TAKEOFF ABORTED AT APPROXIMATELY 100 KIAS. BRAKE TEMP EXCEEDED 900 DEGREES, PER FIRE DEPARTMENT. EXTINGUISHER AGENT SPRAYED ON LT MLG DUE TO BRAKE FIRE. APPRXIMATELY 24 MILLION FOOT LBS OF BRAKE ENERGY. ENGINE BOROSCOPED AND FOUND 5TH & 6TH STAGE HPC DAMAGE ON NR 1 ENG BEYOND MM LIMITS. RAN NR 1 ENGINE IAW ATLAS AIR JC A71710/GTI AND AMM 71-00-02. LEAK AND OPS CHECK GOOD. ALL MLG TIRES REMAINED INFLATED. PERFORMED HIGH ENERGY STOP INSP IAW AMM 05-51-10. NO HEAT DAMAGE NOTED TO THE LANDING GEAR. BRAKES NR 1, NR 2 AND NR 5 REPLACED DUE TO HIGH TEMP IAW AMM 32-41-15. ALL LEAK AND OPS CHECKS GOOD. (M)

Part: COMPRESSOR WHEEL — FAILED (HP SECTION)

REJECTED TAKEOFF, LOUD BANG HEARD AT 75 KNOTS ON TAKEOFF ROLL. REJECTED TAKEOFF AND RETURNED UNDER TOW. MAX THRUST WAS SET. AIRCRAFT POSITIONED TO HIGH POWER RUN BAY. ENGINE RUN RESULTS FAILED. NR 2 ENGINE BORESCOPE INSPECTION FOUND HPC STAGE 12 AND 13 FAILED. ENGINE CHANGE REQUIRED. NR 2 ENGINE REPLACED IAW MM 71-00-02. SUBSEQUENT LEAK AND OPS CHECK OK IAW MM 71-00-00. (M)

Part: STIFFENER — CRACKED (FUSELAGE)

AFTER UNLOADING CARGO, FOUND IN AFT CARGO COMPARTMENT, FORWARD BULKHEAD DAMAGE AT STATION 1480, RIGHT BL 50. DAMAGE WAS CONFINED TO THE AFT VERTICAL FLANGE OF THE HORIZONTAL STIFFENER AT WATER LINE 134.97 AND CRACKING ON STIFFENER AT WL 146.71 IN THE RADIUS APPROX 6 INCHES IN LENGTH. PERFORMED DETAIL INSPECTION OF STATON 1480 BULKHEAD FOR DENTS, BUCKLING BROKEN FASTENERS AND CRACKS OF CLIPS, ANGLES FITTINGS ETC. DAMAGE WAS CONFINED TO THE TWO ABOVE MENTIONED STRUCTURAL ELEMENTS. REPAIRS WERE EMBODIED IAW ATLAS EO 4453A007 AND SRM 51-70-12. REF BOEING TELEXES TLS-JFK-00-00539H, TLS-JFK-00-00541H, BOEING TELCON BOE-JFK/DI NR 10/18/2000. (M)