N498MC

Part: ICU — FAULTED (CABIN PRESSURE) · airframe 105,870 hrs · 17,042 cycles

CABIN ALT AUTO EICAS MSG. C/W QRH. RETURNED TO ANC(<P>FOUND MX MSG 21234, CHECK FAIL. R/R ICU PER AMM 21-31-10 &AMP; IPC 21-31-10-01 ITEM 236, TEST PASSED. R/R DIODES M3349 & 47008 PER SWPM 20-00-00, TEST PASSED. DMI 240995 CLOSED.

Part: PUMP — FAULTED (ZONE 100) · airframe 105,245 hrs · 16,933 cycles

HYD OVHT SYS 4 EICAS MESSAGE. R & R TEMP TRANSMITTER IAW AMM 29-32-02. OPS/LK CHK OK. R & R EDP IAW AMM 29-11-05. OPS CHECKED OK PER AMM 29-11-05. IDLE RUN CHKS OK PER AMM 71-00-00-705-152-J00. REF IPC 29-11-05-048.

Part: SKIN — DELAMINATED (ZONE 500) · airframe 101,130 hrs · 16,253 cycles

LHW T/E I/B AFT FLAP FOUND DELAMINATION(<P>PERFORMED REPAIR AT DELAMINATION AREA IAW SRM 51-70-07 PAR 5.A (1). NO FURTHER DEFECTS NOTED.</P>)

Part: SKIN — DELAMINATED (ZONE 600 FLAP) · airframe 101,130 hrs · 16,253 cycles

RHW T/E I/B FORE FLAP FOUND DELAMINATION(<P>PERFORMED REAPIR AT DELAMINATION AREA IAW SRM 51-70-07 PAR 5.A (1). NO FURTHER DEFECTS NOTED</P>)

Part: LAMP — INOPERATIVE (ZONE 200) · airframe 101,130 hrs · 16,253 cycles

M/D - EMER LT L5735 NOT ILLUMINATE DURING OPS TEST(<P>M/D - EMER LT L5735 LAMPS REPLACED AND OPERATION TEST ' NORMAL ' IAW AMM 33-51-00, REV 110, 15 MAR 2024</P>)

Part: SKIN — DELAMINATED (ZONE 500) · airframe 101,130 hrs · 16,253 cycles

LHW T/E I/B AFT FLAP FOUND DELAMINATION(<P>PERFORMED REPAIR AT DELAMINATION AREA IAW SRM 51-70-07 PAR 5.A (1). NO FURTHER DEFECTS NOTED.</P>)

Part: SKIN — DELAMINATED (ZONE 500) · airframe 101,130 hrs · 16,253 cycles

LHW T/E I/B AFT FLAP FOUND DENT(<P>PERFORMED REPAIR AT DENT AREA IAW SRM 51-70-07 PAR 5.A (1). NO FURTHER DEFECTS NOTED.</P>)

Part: SKIN — DELAMINATED (ZONE 500) · airframe 101,130 hrs · 16,253 cycles

LHW T/E I/B MID FLAP FOUND DENT(<P>PERFORMED REPAIR AT DENT AREA IAW SRM 51-70-07 PAR 5.A (1). NO FURTHER DEFECTS NOTED.</P>)

Part: SKIN — DELAMINATED (ZONE 500) · airframe 101,130 hrs · 16,253 cycles

LHW T/E I/B MID FLAP FOUND DELAMINATION(<P>PERFORMED REPAIR AT DELAMINATION AREA IAW SRM 51-70-07 PAR 5.A (1). NO FURTHER DEFECTS NOTED</P>)

Part: SKIN — DELAMINATED (ZONE 600 FLAP) · airframe 101,130 hrs · 16,253 cycles

RHW T/E I/B MID FLAP FOUND DELAMINATION(<P>PERFORMED REPAIR AT DELAMINATION AREA IAW SRM 51-70-07 PAR 5.A (1). NO FURTHER DEFECTS NOTED.</P>)

Part: SKIN — DELAMINATED (ZONE 500) · airframe 101,130 hrs · 16,253 cycles

LHW T/E O/B AFT FLAP FOUND DELAMINATION(<P>PERFORMED REPAIR AT DELAMINATION AREA IAW SRM 51-70-07 PAR 5.A (1). NO FURTHER DEFECTS NOTED.</P>)

Part: SKIN — DELAMINATED (ZONE 500) · airframe 101,130 hrs · 16,253 cycles

LHW T/E O/B AFT FLAP FOUND DENT(<P>PERFORMED REPAIR AT DENT AREA IAW SRM 51-70-07 PAR 5.A (1). NO FURTHER DEFECTS NOTED.</P>)

Part: ATTACH ANGLE — CRACKED (ZONE 100) · airframe 101,130 hrs · 16,253 cycles

FX - RH AIRCON BAY STA 1230 CENTER TANK LWR ATT CHORD CRACK AT MOST O/B AREA ( RBL 104" )(<P>FX - RH AIRCON BAY STA 1230 CENTER TANK LWR ATT CHORD REPAIRED IAW RI-57-00-16986 REV A. NO FURTHER DEFECTS NOTED</P>)

Part: SKIN — DELAMINATED (ZONE 600 FLAP) · airframe 101,130 hrs · 16,253 cycles

RHW T/E O/B FORE FLAP FOUND DELAMINATION(<P>PERFORMED REPAIR AT DELAMINATION AREA IAW SRM 51-70-07 PAR 5.A (1). NO FURTHER DEFECTS NOTED</P>)

Part: TENSION TIE — CRACKED (ZONE 200) · airframe 101,130 hrs · 16,253 cycles

R/H BS 820 UPPER DECK TENSION TIE 1EA HOLE HOLE FOUND 2EA CRACK AT AFT CHANNEL(<P>RH BS 820 UPPER DECK TENSION TIE 1EA HOLE CRACK REPAIRED IAW SRM 53-20-30-2R-1 REPAIR 1 REV 101 DATE 20 JUN 2024. NO FURTHER DEFECTS NOTED</P>)

Part: BEAM — CORRODED (ZONE 800) · airframe 101,130 hrs · 16,253 cycles

AFT CARGO - CARGO DOOR INNER SURFACE LOWER CLOSEOUT BEAM SURFACE CORR(<P>AFT CARGO - CARGO DOOR INNER SURFACE LOWER CLOSEOUT BEAM SURFACE CORROSION CLEANED UP AS PER SRM 51-10-02 AND REPROTECTED AS PER SRM 51-20-01 AND MEASURED AFT CORR CLEANED UP WITHIN SRM 52-30-02 ALLOABLE DAMAGE 1 FIG 101 LIMIT. ALL IN SRM REV 101 20 JUN 2024</P>)

Part: TENSION TIE — CRACKED (ZONE 200) · airframe 101,130 hrs · 16,253 cycles

LH BS820 UPPER DECK TENSION TIE 1EA HOLE FOUND 1EA CRACK AT AFT CHANNEL.(<P>LH BS 820 UPPER DECK TENSION TIE 1EA HOLE CRACK REPAIRED IAW SRM 53-20-30-2R-1 REPAIR 1 REV 101 DATE 20 JUN 2024. NO FURTHER DEFECTS NOTED</P>)

Part: SKIN — DELAMINATED (ZONE 500) · airframe 101,130 hrs · 16,253 cycles

LHW T/E O/B FORE FLAP FOUND DELAMINATION(<P>PERFORMED REPAIR AT DELAMINATION AREA IAW SRM 51-70-07 PAR 5.A (1). NO FURTHER DEFECTS NOTED.</P>)

Part: SKIN — DELAMINATED (ZONE 500) · airframe 101,130 hrs · 16,253 cycles

LHW T/E O/B AFT FLAP FOUND DELAMINATION(<P>PERFOREMED REPAIR AT DELAMINATION AREA IAW SRM 51-70-07 PAR 5.A (1). NO FURTHER DEFECTS NOTED.</P>)

Part: SKIN — DELAMINATED (ZONE 600) · airframe 101,130 hrs · 16,253 cycles

RHW T/E O/B MID FLAP FOUND DELAMINATION(<P>PERFORMED REPAIR AT DELAMINATION AREA IAW SRM 51-70-07 PAR 5.A (1). NO FURTHER DEFECTS NOTED</P>)

Part: SKIN — DELAMINATED (ZONE 600 FLAP) · airframe 101,130 hrs · 16,253 cycles

RHW T/E O/B MID FLAP FOUND DELAMINATION(<P>PERFORMED REPAIR AT DELAMINATION AREA IAW SRM 51-70-07 PAR 5.A (1). NO FURTHER DEFECTS NOTED</P>)

Part: FLOORBEAM — DAMAGED (ZONE 200) · airframe 101,130 hrs · 16,253 cycles

M/D - DURING INSP P.D.U 4R AREA FOUND DAMAGED HOLE AT STA 420 RBL 31(<P>M/D STA 420 FLOOR BEAM AREA 1EA PUNCTURE DAMAGE REPAIRED IAW RI-53-10-17001 REV A. NO FURTHER DEFECTS NOTED</P>)

Part: SKIN — DELAMINATED (ZONE 500) · airframe 101,130 hrs · 16,253 cycles

LHW T/E O/B FORE FLAP FOUND DELAMINATION(<P>PERFORMED REPAIR AT DELAMINATION AREA IAW SRM 51-70-07 PAR 5.A (1). NO FURTHER DEFECTS NOTED.</P>)

Part: ATTACH ANGLE — CRACKED (ZONE 100) · airframe 101,130 hrs · 16,253 cycles

FX - LH AIRCON BAY STA 1230 CENTER TANK LWR ATT CHORD CRK AT MOST O/B AREA ( LBL 104" )(<P>FX - LH AIRCON BAY STA 1230 CENTER TANK LWR ATT CHORD REPAIRED IAW RI-57-00-16985 REV A. NO FURTHER DEFECTS NOTED</P>)

Part: SKIN — DELAMINATED (ZONE 500) · airframe 101,130 hrs · 16,253 cycles

LHW T/E I/B AFT FLAP FOUND DELAMINATION(<P>PERFORMED REPAIR AT DELAMINATION AREA IAW SRM 51-70-07 PAR 5.A (1). NO FURTHER DEFECTS NOTED.</P>)

Part: BULKHEAD WEB — CRACKED (APU BAY) · airframe 101,130 hrs · 16,253 cycles

APU COMPT FWD LH LOWER BULKHEAD STA 2658 FOUND CRACKED. APU COMPT FWD LH LOWER BULKHEAD STA 2658 REPAIR IAW RI-53-83-17004 REV A. NO FURTHER DEFECTS NOTED.

Part: SKIN — DELAMINATED (ZONE 500) · airframe 101,130 hrs · 16,253 cycles

LHW T/E I/B MID FLAP FOUND DENT(<P>PERFORMED REPAIR AT DENT AREA IAW SRM 51-70-07 PAR 5.A (1). NO FURTHER DEFECTS NOTED.</P>)

Part: FAIRING — DAMAGED (ZONE 400) · airframe 101,130 hrs · 16,253 cycles

#2 PYLON UPPER CAVITY FWD L/E FAIRING SEVERAL SCREW HOLE FOUND ELONGATED(<P>#2 PYLON UPPER CAVITY L/E FAIRING FABRICATION AND REPLACEMENT IAW RI-57-31-17019 REV A. NO FURTHER DEFECTS NOTED.</P>)

Part: SKIN — DELAMINATED (ZONE 500) · airframe 101,130 hrs · 16,253 cycles

LHW T/E I/B MID FLAP FOUND DELAMINATION(<P>PERFORMED REPAIR AT DELAMINATION AREA IAW SRM 51-70-07 PAR 5.A (1). NO FURTHER DEFECTS NOTED</P>)

Part: SKIN — DELAMINATED (ZONE 500) · airframe 101,130 hrs · 16,253 cycles

LHW T/E I/B AFT FLAP FOUND DELAMINATION(<P>PERFORMED REPAIR AT DELAMINATION AREA IAW SRM 51-70-07 PAR 5.A (1). NO FURTHER DEFECTS NOTED.</P>)

Part: TENSION TIE — CRACKED (ZONE 200) · airframe 101,130 hrs · 16,253 cycles

R/H BS 860 UPPER DECK TENSION TIE 2EA HOLE FOUND 1EA CRACK AT AFT CHANNEL(<P>R/H BS 860 UPPER DECK TENSION TIE 2EA HOLE CRACK REPAIRED IAW SRM 53-20-30-2R-1 REPAIR 1 REV 101 DATE 20 JUN 2024. NO FURTHER DEFECTS NOTED</P>)

Part: SKIN — DELAMINATED (ZONE 500) · airframe 101,130 hrs · 16,253 cycles

LHW T/E O/B AFT FLAP FOUND DELAMINATION(<P>PERFORMED REPAIR AT DELAMINATION AREA IAW SRM 51-70-07 PAR 5.A (1). NO FURTHER DEFECTS NOTED.</P>)

Part: SKIN — DELAMINATED (ZONE 500) · airframe 101,130 hrs · 16,253 cycles

LHW T/E I/B AFT FLAP FOUND DELAMINATION(<P>PERFORMED REPAIR AT DELAMINATION AREA IAW SRM 51-70-07 PAR 5.A (1). NO FURTHER DEFECTS NOTED.</P>)

Part: BEAM — CRACKED (ZONE 500) · airframe 101,130 hrs · 16,253 cycles

LHW L/E ILES #690 D BEAM WEB, UPPER CHORD, LOWER CHORD AND UPPER CHORD ATTACH STRAP FOUND CRACK(<P>LHW L/E ILES #690D BEAM WEB, UPPER CHORD, LOWER CHORD AND UPPER CHORD ATTACH STRAP REPAIRED IAW RI NO : RI-57-41-17003 REV A. NO FURTHER DEFECTS NOTED</P>)

Part: SKIN — DELAMINATED (ZONE 600 FLAP) · airframe 101,130 hrs · 16,253 cycles

RHW T/E I/B MID FLAP FOUND DENT(<P>PERFORMED REPAIR AT DENT AREA IAW SRM 51-70-07 PAR 5.A (1). NO FURTHER DEFECTS NOTED</P>)

Part: SKIN — DELAMINATED (ZONE 600 FLAP) · airframe 101,130 hrs · 16,253 cycles

RHW T/E O/B FORE FLAP FOUND DELAMINATION(<P>PERFORMED REPAIR DELAMINATION AREA IAW SRM 51-70-07 PAR 5.A (1). NO FURTHER DEFECTS NOTED</P>)

Part: SKIN — DELAMINATED (ZONE 600 FLAP) · airframe 101,130 hrs · 16,253 cycles

RHW T/E I/B FORE FLAP FOUND DELAMINATION(<P>PERFORMED REPAIR AT DELAMINATION AREA IAW SRM 51-70-07 PAR 5.A (1). NO FURTHER DEFECTS NOTED</P>)

Part: SKIN — DELAMINATED (ZONE 600 FLAP) · airframe 101,130 hrs · 16,253 cycles

RHW T/E I/B FORE FLAP FOUND DELAMINATION(<P>PERFORMED REPAIR AT DELAMINATION AREA IAW SRM 51-70-07 PAR 5.A (1). NO FURTHER DEFECTS NOTED.</P>)

Part: SKIN — DELAMINATED (ZONE 600) · airframe 101,130 hrs · 16,253 cycles

RHW T/E O/B FORE FLAP FOUND DELAMINATION(<P>PERFORMED REAPIR AT DELAMINATION AREA IAW SRM 51-70-07 PAR 5.A (1). NO FURTHER DEFECTS NOTED</P>)

Part: SKIN — DELAMINATED (ZONE 500 FLAP) · airframe 101,130 hrs · 16,253 cycles

LHW T/E I/B FORE FLAP FOUND DELAMINATION(<P>PERFORMED REPAIR AT DELAMINATION AREA IAW SRM 51-70-07 PAR 5.A (1). NO FURTHER DEFECTS NOTED</P>)

Part: STRUCTURE — ABNORMAL (NLG WW) · airframe 101,130 hrs · 16,253 cycles

ACCOMPLISH EO 4453A516 PART 3 AND PART 4 NOSE WHEEL WELL AFT CORNER SKIN PNL MOD - SB 747-53A2305 R2 AD 2010-26-07(<P>ACCOMPLISH EO 4453A516 PART 3 AND PART 4 NOSE WHEEL WELL AFT CORNER SKIN PNL MOD SB 747-53A2305 R2 AD 2010-06-07 AND REPAIRED IAW RI-53-18-17008 REV A. NO FURTHER DEFECTS NOTED</P>)

Part: SUPPORT BRACKET — DAMAGED (ZONE 600) · airframe 101,130 hrs · 16,253 cycles

RH WING LDG BEAM MID AREA T/E UPPER SURFACE SUPPORT ROD BRACKET FOUND ELONGATED(<P>RH WING LDG BEAM MID AREA T/E UPPER SURFACE SUPPORT ROD BRACKET REPLACED IAW SRM 51-10-02 AND INSTALLED IAW SRM 51-40-02 AND 69B11994U2 FITTING ASSY FABRICATED AS PER DWG AND PL AND RI-57-22-17013 REV A, SRM REV 101 DATE 20 JUN 2024. NO FURTHER DEFECTS NOTED</P>)

Part: SKIN — DELAMINATED (ZONE 500) · airframe 101,130 hrs · 16,253 cycles

LHW T/E O/B MID FLAP FOUND DELAMINATION(<P>PERFORMED REPAIR AT DELAMINATION AREA IAW SRM 51-70-07 PAR 5.A (1). NO FURTHER DEFECTS NOTED.</P>)

Part: SKIN — DENTED (ZONE 500 FLAP) · airframe 101,130 hrs · 16,253 cycles

LHW T/E I/B FORE FLAP FOUND DENT(<P>PERFORMED REPAIR AT DENT AREA IAW SRM 51-70-07 PAR 5.A (1). NO FURTHER DEFECTS NOTED.</P>)

Part: SKIN — DELAMINATED (ZONE 500) · airframe 101,130 hrs · 16,253 cycles

LHW T/E O/B AFT FLAP FOUND DENT(<P>PERFORMED REPAIR AT REPAIR AREA IAW SRM 51-70-07 PAR 5.A (1). NO FURTHER DEFECTS NOTED</P>)

Part: SKIN — DELAMINATED (ZONE 600) · airframe 101,130 hrs · 16,253 cycles

RHW T/E O/B MID FLAP FOUND DELAMINATION(<P>PERFORMED REPAIR AT DELAMINATION AREA IAW SRM 51-70-07 PAR 5.A (1). NO FURTHER DEFECTS NOTED</P>)

Part: WINDOW — CRACKED (LEFT) · airframe 100,918 hrs · 16,225 cycles

WINDOW LEFT SIDE CREW REST CRACKED IN CRUISE. LOUD BANG AND WINDOW CRACKED. PRESSURE NORMAL(<P>RPLD CABIN WINDOW PER AMM 56-21-01. OPS CHK GOOD.</P>)

Part: PITOT TUBE — FAULTED (RIGHT) · airframe 100,837 hrs · 16,213 cycles

HEAT P/S F/O EICAS &AMP; STS MSG(<P>AIRCRAFT RETURNED TO ICN. REPLACED F/O UPPER RH PITOT PROBE PER AMM 34-11-01. OPS CHK GOOD</P>)

Part: VALVE — UNKNOWN (UNKNOWN) · airframe 97,057 hrs · 15,517 cycles

E/E COOLING EXHAUST FAN FAIL & NO FLT DECK COOLING AND ZONE TEMP STATUS MESSAGE(<P>REMOVED AND REPLACED EE COOLING FAN IAW AMM21-58-01 AND FWD TRIM AIR SHUTOFF VALVE.</P>)

Part: FLOORBEAM — CORRODED · corrosion level 2 · airframe 94,172 hrs · 14,951 cycles

CORROSION ON FLOORBEAM UPPER CAP AT STA 2240 BETWEEN RBL 33.99 AND RBL 67.01 REMOVE AFFECTED FASTENERS IAW SRM 51-40-02 REV 94. 2) REPAIR DAMAGE AREA IAW SRM 53-00-51-2R-3 REPAIR 3 REV 94 AND EI T2022A53M-1653 REV 1. 3) INSTALL PARTS IAW SRM 53-00-51-2R-3 REPAIR 3 REV 94, EI T2022A53M-1653 REV 1 AND DWG 65B38112 SH14 REV-. 4) JOB COMPLETED AND CONDITION CHECK NORMAL</P>)

Part: FRAME — CORRODED · corrosion level 2 · airframe 94,172 hrs · 14,951 cycles

CORROSION - TEE LOWER FACE OF FWD LOWER FRAME STA 1239.25 LBL 30 - RBL 30 REMOVED DAMAGE PART IAW SRM 51-40-02 REV 94. 2) INSTALL THE NEW PART IAW SRM 51-40-02 REV 94 DWG 651310533 SH21 REV D; 65B10533 SH24 REV C; 65B10533 SH26 REV A; 65B10533 SH28 REV C; 65B10533 SH29 REV C; 65B10533 SH27 REV A; 65B10533 SH31 REV-; 65B10533 SH19 REV C 3) CONDITION CHECK NORMAL AND JOB COMPLETED</P>)

Part: WEB — CORRODED · corrosion level 2 · airframe 94,172 hrs · 14,951 cycles

CORROSION ON LOWER CHORD AND WEB OF WING TO BODY FAIRING FRAME ASSY (PN: 65B06749-50) AT STA 880 BETWEEN BL 0 LBL 40 REMOVED DAMAGE PARTS IAW SRM 51-40-02 REV 94. 2) REPAIRED DAMAGE AREA IAW SRM 53-00-71 REPAIR 2 REV 94 EI T2022A53M-1726 REV 1. 3) INSTALLED FASTENER IAW SRM 51-40-02 REV 94 AND DNG 65B06749 SH02 REV L AND 65B07249 SH02 REV C. 4) JOB COMPLETED AND CONDITION CHECK NORMAL</P>)

Part: CAP — CORRODED · corrosion level 2 · airframe 94,172 hrs · 14,951 cycles

CORROSION ON THE UPPER CAP (PN: 65B38075-3) OF M/D FLOOR STRUCTURE AT STA 1500, BETWEEN LBL 75.92 AND LBL 98.58 REMOVE AFFECTED FASTENERS IAW SRM 51-40-02 REV 94. 2) REPAIR DAMAGE AREA IAW SRM 53-00-51-2R-3 REPAIR 3 REV 94 AND EI T2022A53M-1662 REV 1. 3) INSTALL REPAIR PARTS IAW SRM 53-00-51-2R-3 REPAIR 3 REV 94, EI T2022A53M-1662 REV 1 AND DWG 65B38075 SH7 REV A. 4) JOB COMPLETED AND CONDITION CHECK NORMAL</P>)

Part: FLOOR SUPPORT — CORRODED · corrosion level 2 · airframe 94,172 hrs · 14,951 cycles

FOUND M/D FLOOR STRUCTURE SUPPORT CORROSION AT STA 2376 RBL 16 REMOVE DAMAGE PART IAW SRM 51-40-02 REV 94. 2) INSTALLED NEW PART IAW SRM 51-40-02 REV 94 AND DWG 65B38754 SHEET 8 REV A. 3) JOB COMPLETED</P>)

Part: SKIN — CRACKED · airframe 94,172 hrs · 14,951 cycles

LH INBD AILERON, OUTBD EDGE T/E SKIN CRACK AND CHAFING WORN PERFOM LH WING INBD AILERON OUTBD EDGE T/E WEDGE SKIN REPAIR. REFER O J/C ATTACHING SHEET 0307587. 2) CONDITION CHECK IS SATISFACTORY</P>)

Part: CAP — CORRODED · corrosion level 2 · airframe 94,172 hrs · 14,951 cycles

CORROSION ON CAP AT M/D FLOOR SUPPORT BEAM STA 2369.8 RBL 15.75 REMOVE DAMAGE PART IAW SRM 51-40-02 REV 94. 2) INSTALL NEW PART IAW SRM 51-40-02 REV 94 AND DWG 65B06154 SHEET 1 REV A 65B38754 SH8 REV A. 3) CONDITION CHECK NORMAL AND JOB COMPLETED</P>)

Part: SHEAR TIE — CRACKED · airframe 94,172 hrs · 14,951 cycles

CRACK - FOUND SHEAR TIE HAVE CRACK AT STA 1000 RBL 57.5 REMOVE DAMAGE SHEAR TIE IAW SRM 51-40-02 REV 94. 2) INSTALL NEW SHEAR TIE IAW EI T2022A53M-1601 REV 2 AND SRM 51-40-02 REV 94. 3) CONDITION CHECK NORMAL AND JOB COMPLETED</P>)

Part: ELT — FAILED INSP · airframe 94,172 hrs · 14,951 cycles

FOUND FIXED ELT SELF-TEST FAIL IAW AMM AR 23-24-01/401 REV 104 REPLACED THE EMERGENCY LOCATOR TRANSMITTER. 2) IAW AMM AR 23-24-01/401 REV 104 PERFORMED ELT INSTALLATION TEST. THE RESULT WAS SATISFACTORY</P>)

Part: FLOORBEAM — CORRODED · corrosion level 2 · airframe 94,172 hrs · 14,951 cycles

CORROSION DAMAGES ON MAIN DECK FLOORBEAM UPPER CAP AT STA 2140, NEAR LBL 61 AND 83.5(<P>1) REMOVE AFFECTED FASTENERS IAW SRM 51-40-02 REV 94. 2) REPAIR DAMAGE AREA IAW SRM 53-00-51-2R-3 REPAIR 3 REV 94 AND EI T2022A53M-1696 REV 1. 3) INSTALL REPAIR PARTS IAW SRM 53-00-51-2R-3 REPAIR 3 REV 94 EI T2022A53M-1696 REV 1 AND DWG 65B38107 SH8 REV -. 4) JOB COMPLETED AND CONDITION CHECK NORMAL</P>)

Part: SEAT TRACK — CORRODED · corrosion level 2 · airframe 94,172 hrs · 14,951 cycles

CORROSION DAMAGES ON THE MAIN DECK SEAT TRACK (PN: 65B38268-2) AT STA 2090, 2150 AND 2220, RBL 89.67(<P>1) REMOVE AFFECTED FASTENERS IAW SRM 51-40-02-REV 96. 2) REPAIR DAMAGE AREA IAW SRM 5-00-52-2R-6 REPAIR 6 REV 94 AND EI T2022A53M-1659 REV 2. 3) INSTALL REPAIR PARTS IAW SRM 53-00-52-2R-6 REPAIR 6 REV 94, EI T2022A53M-1659 REV 2 AND DWG 65B38687 SH18 REV D, 65B38251 SH35 REV A, 65B386 SH8 REV A. 4) JOB COMPLETED AND CONDITION CHECK NORMAL</P>)

Part: WEB — CRACKED · airframe 94,172 hrs · 14,951 cycles

CRACK DAMAGE ON THE WEB OF LH SIDE HST CLOSURE RIB ON STAB BL 421.50. REMOVE DAMAGE PARTS IAW SRM 51-40-02 REV 94. 2) REPAIR WEB IAW SRM 55-10-09-2R-13 REV 94 AND EI T2022A55M-1751 REV 1. 3) INSTALL NEW PARTS IAW SRM 51-40-02 REV 94 AND DWG 65B03520 SH2 REV G. 4) JOB COMPLETED AND CONDITION CHECK NORMAL</P>)

Part: WEDGE — DEBONDED · airframe 94,172 hrs · 14,951 cycles

DISBOND - AILERON, RH WING INBD AILERON OUTBD WEDGE PERFORM RH WING INBD AILERON OUTBD EDGE T/E WEDGE SKIN REPAIR. REFER TO J/C ATTACHING SHEET 0307588. 2) CONDITION CHECK IS SATISFACTORY</P>)

Part: FLOORBEAM — CORRODED · corrosion level 2 · airframe 94,172 hrs · 14,951 cycles

CORROSION ON M/D FLOORBEAM UPPER CAP AT STA 2280 LBL 73 REMOVE AFFECTED FASTENERS TO GET ACCESS IAW SRM 51-40-02 REV 94. 2) PERFORM FLOORBEAM REPAIR IAW SRM 53-40-51-2R-3 REPAIR 3 REV 94 AND EI T2022A53M-1725 REV 2. 3) INSTALL FASTENERS IAW SRM 51-40-02 REV 94 AND DWG 65B04351 SH25 REV A. 4) JOB COMPLETED AND CONDITION CHECK NORMAL</P>)

Part: POWER SUPPLY — INOPERATIVE · airframe 94,172 hrs · 14,951 cycles

FOUND EMERGENCY LIGHT (L1853, L1854, L5735) INOP IAW AMM 33-51-04-002-009-001 & 33-51-04-402-012-001 REV 104. REPLACED M5170 EMERGENCY LIGHT POWER SUPPLY AND PERFORMED POWER SUPPLY INSTALLATION TEST, THE RESULT WAS SATISFACTORY</P>)

Part: FLOORBEAM — NONE · airframe 94,172 hrs · 14,951 cycles

DEVIATION FOR SB 747-53A2443 UPPER DECK FLOORBEAM INSPECTION AND MODIFICATION(<P>1) ACCOMPLISHED JOB IAW EI T2022A53M-1591 REV 1. 2) CONDITION CHECK NORMAL AND JOB COMPLETED</P>)

Part: CAP — CORRODED · corrosion level 2 · airframe 94,172 hrs · 14,951 cycles

CORROSION ON THE UPPER CAP (PN: 65B38075-3) OF MAIN DECK FLOOR STRUCTURE AT STA 1500, BETWEEN RBL 75.92 AND RBL 98.58 REMOVE AFFECTED FASTENER IAW SRM 51-40-02 REV 94. 2) REPAIR DAMAGE AREA IAW SRM 53-00-51-2R-3 REPAIR 3 REV 94 AND EI T2022A53M-1661 REV 1. 3) INSTALL REPAIR PARTS IAW SRM 53-00-51-2R-3 REPAIR 3 REV 94, EI T2022A53M-1661 REV 1 AND DWG 65B38075 SH5 REV C. 4) JOB COMPLETED AND CONDTION CHECK NORMAL</P>)

Part: SHEAR TIE — CRACKED · airframe 94,172 hrs · 14,951 cycles

CRACK - FOUND SHEAR TIE HAVE CRACK AT STA 1000 RBL 33.99 REMOVE DAMAGE SHEAR TIE IAW SRM 51-40-02 REV 94. 2) INSTALL NEW SHEAR TIE IAW EI T2022A53M-1601 REV 2 AND SRM 51-40-02 REV 94. 3) CONDITION CHECK NORMAL AND JOB COMPLETED</P>)

Part: NONE — NONE · airframe 94,069 hrs

LOW SPEED REJECTED TAKE OFF AT APPROXIMATELY 70 KNOTS DUE TO MASTER CAUTION LIGHT FOR FLAPS PRIMARY.(<P>PERFORMED ENERGY STOP INSPECTION IN ACCORDACE WITH AMM 05-51-10.&NBSP; SATISFIED, NO DAMAGE FOUND.</P>)

Part: TRANSMISSION — MALFUNCTIONED (TE FLAPS) · airframe 87,880 hrs · 13,876 cycles

AFTER TAKE OFF THE FLAP INDICATOR COULD NOT BE VERIFIED IN THE UP (COMMANDED) POSITION, SAME ON LANDING. TROUBLESHOOTING FOUND NR 3 FLAP TRANSMISSION SLEEPING DURING LAST FEW INCHES FROM FULLY UP. NR 3 FLAP TRACK/TRANSMISSION REPLACED, IAW AMM 27-51-33 REV 99. FLAPS OPERATE NORMAL.

Part: SKIN — DELAMINATED (LT WING TE FLAP) · airframe 87,311 hrs · 13,776 cycles

LEFT HAND OUTBOARD FORE FLAP LEADING EDGE FAIRING FOUND DELAMINATION. PERFORMED PERMANENT COMPOSITE HOT BOND REPAIRS, AS PER SRM 51-70-07 PAR 5A.

Part: SKIN — DELAMINATED (RT WING TE FLAP) · airframe 86,454 hrs · 13,625 cycles

RIGHT WING INBD FORE FLAP T/E EDGE UPPER AND LOWER SURFACES WERE FOUND DELAMINATED FROM INBD 109 INCHES. PERFORMED A PERMANENT COMPOSITE REPAIR IAW SRM 51-70-07, PAR 5.A, REV 88.

Part: PANEL — DELAMINATED (LT WING) · airframe 56,454 hrs · 13,625 cycles

LEFT WING MOST INBD T/E FIXED PANEL FOUND DELAMINATED. THE PANEL WAS REPLACED IAW SRM 51-10-02.

Part: KEELBEAM — CORRODED (BS 1076) · airframe 86,454 hrs · 13,625 cycles

BS 1076 LBL 9 KEEL BEAM CHORD LWR FLANGE FOUND CORRODED. THE CORROSION WAS REMOVED AND REPROTECTED IAW SRM 51-10-02 AND SRM 51-20-01. CHECKED WITHIN SRM 53-40-12-1A-1 ALLOWABLE DAMAGE 1, FIG 102, LIMITS.

Part: SEAT TRACK — CORRODED (BS 2120) · airframe 86,454 hrs · 13,625 cycles

BS 2120, RBL 11, SEAT TRACK FOUND CORRODED. CORROSION REMOVED AND SEAT TRACK REPROTECTED IAW SRM 51-10-02, AND SRM 51-20-01. CHECKED WITHIN SRM 53-00-52 AD1 FIG 101 LIMITS.

Part: KEELBEAM — CORRODED (BS 1020) · airframe 86,454 hrs · 13,625 cycles

BS 1020, RBL 9, KEELBEAM LOWER FLANGE FOUND CORRODED. THE CORROSION WAS REMOVED AND THE KEELBEAM WAS REPROTECTED IAW SRM 51-10-02 AND SRM 51-20-01. CHECKED WITHIN SRM LIMITS.

Part: SKIN — DELAMINATED (LT WING TE FLAP) · airframe 86,454 hrs · 13,625 cycles

LEFT WING OTBD FORE FLAP L/E MID AREA FOUND DELAMINATED FROM INBD 126 INCHES. PERFORMED A PERMANENT COMPOSITE REPAIR IAW SRM 51-70-07 PAR 5.A REV 88.

Part: STRAP — CORRODED (RT WING) · corrosion level 2 · airframe 86,454 hrs · 13,625 cycles

RIGHT WING INBD L/E CAVITY AT ILES 620, FRONT SPAR UPPER CHORD LOWER ATTACH STRAP FOUND CORRODED. THE ATTACH STRAP WAS REPLACED IAW SRM 51-10-02, SRM 51-40-02, DWG 65B01684, AND DWG 112U3002.

Part: SEAT TRACK — DAMAGED (BS 2120-2160) · corrosion level 2 · airframe 86,454 hrs · 13,625 cycles

MAIN DECK, BS 2120 - 2160, LBL 11.33, SEAT TRACK SLOT BASE FOUND CORRODED AND CRACKED. THE SEAT TRACK WAS REPAIRED IAW SRM 53-00-52 -2R-12, REPAIR 12.

Part: SKIN — DELAMINATED (TE FLAP) · airframe 86,454 hrs · 13,625 cycles

LOWER OTBD FORE FLAP L/E MID AREA FOUND DELAMINATED FROM INBD 196 INCHES. PERFORMED PERMANENT COMPOSITE REPAIR IAW SRM 51-70-07, PAR 5.A REV 88.

Part: SKIN — DELAMINATED (LT WING TE FLAP) · airframe 86,454 hrs · 13,625 cycles

LEFT WING INBD AFT FLAP M/D L/E FAIRING AREA FOUND DELAMINATED. PERFORMED A PERMANENT COMPOSITE REPAIR IAW SRM 51-70-07, PAR 5.A, REV 88.

Part: SEAT TRACK — CORRODED (BS 2160) · airframe 86,454 hrs · 13,625 cycles

MAIN DECK, BS 2160, RBL 11, SEAT TRACK FOUND CORRODED. THE CORROSION WAS REMOVED AND THE SEAT TRACK REPROTECTED IAW SRM 51-10-02, AND SRM 51-20-01. CHECKED WITHIN SRM LIMITS.

Part: SKIN — DELAMINATED (LT WING TE FLAP) · airframe 86,454 hrs · 13,625 cycles

LEFT WING OTBD FLAP L/E FOUND DELAMINATED FROM OTBD 30 INCHES. PERFORMED A PERMANENT COMPOSITE REPAIR IAW SRM 51-70-07, PAR 5.A, REV 88.

Part: BATTERY — INOPERATIVE (EMERGENC LIGHTS) · airframe 86,454 hrs · 13,625 cycles

EMERGENCY LIGHT FUNCTIONAL TEST FOUND M5169 POWER SUPPLY FAILED, LOCATED AT BS 590, RBL 83, WBL 323. THE POWER SUPPLY BATTERY M5169 WAS REPLACED AND THE EMERGENCY LIGHTS TESTED NORMAL IAW AMM 33-51-04, AND 33-51-00.

Part: LONGERON — NOT REPORTED (BS 1480) · airframe 56,454 hrs · 13,625 cycles

BS 1480, LONGERON EXTENSION FITTING REPAIR PER EO 4453A818 PART 8. COMPLETED THE LONGERON EXTENSION FITTING REPAIR IAW EO 4453A818 PART 8.

Part: SUPPORT — CORRODED (LT WING) · airframe 86,454 hrs · 13,625 cycles

LEFT WING MOST INBD FIXED PANEL SUPPORT CORRODED. THE SUPPORT WAS REPAIRED IAW RI 57-51-14120, REV.A.

Part: KEELBEAM — CORRODED (BS 1076) · airframe 86,454 hrs · 13,625 cycles

BS 1076, RBL 9, KEEL BEAM LOWER FLANGE WAS FOUND CORRODED. THE CORROSION WAS REMOVED AND REPROTECTED IAW SRM 51-10-02, AND SRM 51-20-01. CHECKED WITHIN SRM 53-40-12-1A-1 ALLOWABLE DAMAGE 1, FIG 102 LIMITS.

Part: SKIN — DELAMINATED (LT WING TE FLAP) · airframe 86,454 hrs · 13,625 cycles

LEFT WING INBD FORE FLAP MID AREA OF L/E FOUND DELAMINATED. PERFORMED A PERMANENT COMPOSITE REPAIR IAW SRM 51-70-07, PAR 5.A, REV 88.

Part: ATTACH BRACKET — CORRODED (SWITCH) · corrosion level 2 · airframe 86,454 hrs · 13,625 cycles

NR 3 PACK RAM AIR EXHAUST DOOR POSITION SWITCH ATTACH BRACKET WAS FOUND CORRODED. THE SWITCH ATT BRACKET WAS REPLACED IAW SRM 51-10-02, AND FASTENER INSTALLED IAW SRM 51-40-02.

Part: SKIN — DELAMINATED (LT WING TE FLAP) · airframe 86,454 hrs · 13,625 cycles

LEFT WING OTBD FLAP, OTBD L/E WAS FOUND DELAMINATED FROM OTBD 12 INCHES. PERFORMED A PERMANENT COMPOSITE REPAIR IAW SRM 51-70-07, PAR 5.A, REV 88.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 86,454 hrs · 13,625 cycles

UPPER DECK BS 550 AISLE EMERGENCY LIGHT WAS FOUND INOPERATIVE. THE EMERGENCY LIGHT ASSY WAS REPLACED AND TESTED NORMAL IAW AMM 33-51-07.

Part: CONNECTOR — DAMAGED (WINDOW HEAT) · airframe 85,105 hrs · 13,402 cycles

AFTER TAKEOFF SMOKE IN FLIGHT DECK WITH EICAS LOSS OF BUS AND LOSS OF ILS ON APP(<P>C/O SMOKE OR FUMES IN CABIN, UNKNOWN SOURCE, FAULT ISOLATION IAW FIM 21-00, TASK 810, NO DISCREPANCY FOUND. PERFORMED ENGINE IDLE RUN IAW AMM 71-00-00, NIL DISCREPANCY FOUND. REF ITEM M2, &AMP; M4 FOR FURTHER&NBSP; ACTION. </P><P>M2: FLIGHT DECK FAN FAILED, REMOVED AND REPLACED FAN IAW AMM 21-26-06 (OFF PART: PN 605457-7, SN 108-10563), OPS TEST NORMAL. </P><P>M4: FOUND WINDOW L1 HEAT WIRE &AMP; CONNECTOR WITH HEAT DAMAGE W4495. REMOVED AND REPLACED WIRE CONNECTOR CWC01-1210 PER WDM 30-41-111-3.1 &AMP; SWPM 20-30-12. OPS CK OK.</P>)

Part: WARNING SYSTEM — FALSE ACTIVATION (COCKPIT) · airframe 83,576 hrs · 13,118 cycles

STAB TRIM CONFIG WARNING DURING TAKEOFF. 40 KNOT, LOW SPEED REJECTED TAKEOFF PERFORMED. MESSAGE EXTINGUISHED / WHEN ARRIVED BACK TO BLOCKS. PERFORMED / SUCCESSFUL CMC GROUND TESTS FOR LEFT AND RIGHT FMC'S AS PER AMM 34-61-00. PERFORMED SUCCESSFUL TEST OF TRIM INDICATING / SYSTEM AS PER AMM 27-48-00. PERFORMED / SUCCESSFUL TEST OF TAKEOFF WARNING SYSTEM AS PER AMM 31-51-00. AIRCRAFT RETURNED TO SERVICE.

Part: COMPRESSOR — STALLED (NR 2 ENGINE) · airframe 82,788 hrs · 12,982 cycles

#2 ENGINE, COMPRESSOR STALL. OPERATED ENGINE AT REDUCED POWER SETTING PER MX CONTROL.(<P>REMOVED AND REPLACED #2 ENGINE PER AMM 71-00-02/401. OPS CHECK NML. REF W/O 53069.&NBSP;</P>)

Part: PDU — BROKEN (LE SLAT) · airframe 82,450 hrs · 12,931 cycles

LOW SPEED REJECTED TAKEOFF FOR FLAPS PRIMARY ADVISORY DURING TAKEOFF ROLL. REJECTED AT 60 KTS.&NBSP;(<P>FOUND BROKEN C/P AT LE PNEUM. DRIVE UNIT, POS 2R. REMOVED AND REPLACED LE PDU IAW AMM 27-81-03.&NBSP;OPS CHECK NORMAL.</P>)

Part: WARNING MESSAGE — FALSE ACTIVATION (CONFIGURATION) · airframe 80,651 hrs · 12,610 cycles

LOW SPEED ABORTED TAKEOFF (30KTS) IN NRT DUE TO CONFIG WARNING.&NBSP; CAPT REPORTED STAB TRIM WAS ON THE EDGE OF GREEN BAND.&NBSP; SLIGHT ADJUSTMENT MADE TO&NBSP;STAB TRIM AND DEPARTED.&NBSP; &NBSP;REPORTED UPON ARRIVAL TO NGO.(<P>NGO MAINTENANCE PERFORMED TEST OF STAB INDICATION SYSTEM AND WEIGHT AND BALANCE SYSTEM.&NBSP; NO DEFECTS NOTED WITH AIRCRAFT AND ALL TESTS PASSED.<BR /></P>)

Part: SKIN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 78,807 hrs · 12,286 cycles

M/D STA 1480 STR 15R-16R FOUNDED CORRODED. INNER SKIN CORROSION AREAS REPAIRED IAW RI NO: RI-53-40-12812 REV A.

Part: SKIN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 78,807 hrs · 12,286 cycles

M/D STA 1480 STR 3R-4R FOUND CORRODED. INNER SKIN CORROSION AREAS REPAIRED IAW RI NO: RI-53-40-12812 REV A.

Part: SEAT TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 78,807 hrs · 12,286 cycles

M/D STA 1800 LBL11.33" SEAT TRACK FOUND CORRODED. M/D STA 1766.45 TO STA 1810.45 LBL11.33 SEAT TRACK CORROSION AREAS REPAIRED IAW RI NO: RI-53-60-12811 REV A.

Part: SKIN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 78,807 hrs · 12,286 cycles

M/D STA 1480 STR 7L-8L FOUND CORRODED. INNER SKIN CORROSION AREAS REPAIRED IAW RI NO: RI-53-40-12812 REV A.

Part: RIB — CRACKED (RT WING) · airframe 78,917 hrs · 12,314 cycles

RT WING BETWEEN PNL 691CB AND 691DB PNL SUPPORT CRACK. RT WING T/E WS 1351 RIB LOWER CHORD (BETWEEN PNL 691CB AND 691DB PNL) P/N: 65B08167-56 FABRICATED AND INSTALLED IAW RI NR RI-57-50-12809 REV A.

Part: SKIN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 78,807 hrs · 12,286 cycles

M/D STA 1480 STR 9L-10L FOUND CORRODED. INNER SKIN CORROSION AREAS REPAIRED IAW RI NO: RI-53-40-12812 REV A.

Part: SKIN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 78,908 hrs · 12,312 cycles

M/D STA 1480 STR 6R-7R FOUND CORRODED. INNER SKIN CORROSION AREAS REPAIRED IAW RI NO: RI-53-40-12812 REV A.

Part: SUPPORT BRACKET — CRACKED (FUSELAGE) · airframe 78,807 hrs · 12,286 cycles

FUSELAGE STA 1241 BODY FAIRING SUPPORT BRACKET CRACKED. LT STA 1235-1241 UNDERWING O/B FAIRING INTERCOSTAL CRACK AREAS REPAIRED IAW RI NO:RI-53-60-12810 REV A.

Part: FLAP — DAMAGED (LT WING) · airframe 78,906 hrs · 12,311 cycles

LT WING NR 10 VC FLAP O/B FOLDING NOSE DAMAGE. FLAP O/B FOLDING NOSE CRACK AREAS REPAIRED IAW RI NO: RI-57-40-12802 REV A.

Part: SKIN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 78,807 hrs · 12,286 cycles

M/D STA 1480 STR 1L-2L FOUND CORRODED. INNER SKIN CORROSION AREAS REPAIRED IAW NO:RI-53-40-12812 REV A.

Part: SKIN — CRACKED (APU DOOR) · airframe 78,807 hrs · 12,286 cycles

APU LT DOOR AFT EDGE FOUND CRACKED. LT APU COMPARTMENT DOOR SKIN CRACK AREAS REPAIRED IAW RI NR RI-52-40-12808 REV A.

Part: SKIN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 78,807 hrs · 12,286 cycles

M/D STA 1480 STR 7R-8R FOUND CORRODED. INNER SKIN CORROSION AREAS REPAIRED IAW RI NO: RI-53-40-12812 REV A.

Part: RIB — CRACKED (RT WING) · airframe 78,917 hrs · 12,314 cycles

RT WING T/E CAVITY 1349 UPR SURFACE FIXED PNL SUPPORT FOUND CRACK. RT WING T/E WS 1351 RIB UPPER CHORD P/N 65B08167-40 FABRICATED AND INSTALLED IAW RI NR RI 57-50-12809 REV A.

Part: SKIN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 78,807 hrs · 12,286 cycles

M/D STA 1000 STR 9R-10R FOUND CORRODED. M/D-STA 1000 STR 9R TO STR 10R INNER SKIN CORROSION AREAS REPAIRED IAW RI NR RI-53-40-12812 REV A.

Part: SKIN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 78,807 hrs · 12,286 cycles

M/D STA 1000 STR 11L-12L FOUNDED CORRODED. INNER SKIN CORROSION AREAS REPAIRED IAW RI NO: RI-53-40-12812 REV A.

Part: SKIN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 78,906 hrs · 12,311 cycles

M/D STA 1480 STR 4L-5L FOUND CORRODED. INNER SKIN CORROSION AREAS REPAIRED IAW RI NO: RI-53-40-12812 REV A.

Part: SKIN — CRACKED (LT WING) · airframe 78,807 hrs · 12,286 cycles

LT WING LWR SURFACE L/E CORNER CLOSE TO NR 6 V/C FLAP O/B T/E FOUND CRACK. LT WING LWR SURFACE (L/E NOSE SKIN) REPAIRED IAW SRM 57-41-01-2R-6 REPAIR 6.

Part: WARNING MESSAGE — FALSE ACTIVATION (STAB CONFIG) · airframe 76,217 hrs · 11,820 cycles

CONFIGURATION STAB WARNING. FIM WAS FOLLOWED IAW 31-51, TASK 807. SYSTEM TESTED NORMAL.

Part: STRUCTURE — DAMAGED (NLG DOORS) · airframe 74,805 hrs · 11,565 cycles

DAMAGE NOSE GEAR DOOR DUE TO JAMMED EQUIPMENT DURING DOOR CLOSING. REPAIRED THE DOORS IAW SRM 52-80-1A-1, REWORKED METAL SURFACES ARE TREATED AND PRIMED IAW SRM 51-20-01. FINISH RESTORED IAW AMM 51-20-00. PERFORMED COMPLETED PERMANENT REPAIR. NO FURTHER ACTION REQUIRED.

Part: WINDSHIELD WIPER — NOT REPORTED · airframe 73,491 hrs · 11,329 cycles

LEADING EDGE OF WINDSHIELD WIPERS ARE OFF WINDSHIELD APROX 12 INCHES DURING FLIGHT. REPLACED WINDSHIELD WIPER ARMS AND BLADE ASSEMBLY IAW AMM 30-42-02-404-011.

Part: CARGO TRACK — CRACKED (BS 565) · airframe 71,791 hrs · 10,979 cycles

CRACK ON CARGO TRACK AT RBL 45.5, BS 565. REPAIRED IAW EI T2016A53M-1673 REV. 1, AND SRM 53-00-52 REPAIR 10 REV. 77.

Part: WIRE — DAMAGED (NR 1 ENGINE) · airframe 71,791 hrs · 10,979 cycles

FOUND NR 1 ENG WIRES DAMAGED FROM CORE ACCELEROMETER (DT676) TO D42089. REMOVED AND REPLACED THE WIRES IAW AMM 71-00-00-705-009-JOO REV 87. OPS CHECKED GOOD.

Part: BULKHEAD WEB — CORRODED (LT MLG WW) · airframe 71,791 hrs · 10,979 cycles

CORROSION ON WEB, LT MLG WW AT BS 1241 LBL 95. REPAIRED IAW SRM 57-10-10 FIG. 101 DETAIL V REV. 77.

Part: FLOORBEAM — CORRODED (BS 1748) · corrosion level 2 · airframe 71,791 hrs · 10,979 cycles

CORRODED FLOORBEAM IN AFT CARGO BAY BS 1748 LBL 42. REPAIRED IAW DWG 65B06111 SH 4 REV. & SRM 51-40-02-0G-0 REV. 77.

Part: FLOORBEAM — CORRODED (BS 2360) · corrosion level 2 · airframe 71,791 hrs · 10,979 cycles

MAIN DECK FLOOR STRUCTURE STA 2360 LBL 10 TO RBL 10 CORRODED. REPAIRED IAW EI T2016P53M-1636 REV. 0, SRM 51-40-02-0G-0, REV. 77, DWG 65B02634 SHEET 22 REV. U, & DWG NO. 65B02634 SHEET 59 REV.

Part: ANGLE — CORRODED (BS 1241) · corrosion level 2 · airframe 71,791 hrs · 10,979 cycles

CORRODED ANGLE RT MLG WW AT BS 1241 WBL 135. REPAIRED IAW SRM 51-40-02-0G-0 REV. 77 & DWG 112U1001 SH 3 REV. F.

Part: SKIN — DAMAGED (CARGO DOOR) · airframe 71,791 hrs · 10,979 cycles

LIGHTNING STRIKE DAMAGE ON NOSE CARGO DOOR RT SIDE OUTER SKIN SURFACE BS 220 BETWEEN STRINGERS 14C - 14D. REPAIRED IAW E.I. T2016A52M-1654 REV. 1.

Part: FLOORBEAM — CORRODED (BS 460) · corrosion level 2 · airframe 71,791 hrs · 10,979 cycles

CORROSION ON FLOORBEAM UPPER TEE BS 460, LBL 94. REPAIRED IAW EI T2016A53M-1716 REV. 2 & SRM 53-00-51-2R-3 REV. 77.

Part: SKIN — CORRODED (BS 1736) · corrosion level 2 · airframe 71,791 hrs · 10,979 cycles

CORROSION ON SKIN BS 1736 STRINGER 44L. REPAIRED IAW EI T2016A53M-1637 REV. 2.

Part: WIRE — DAMAGED (FIRE DETECTOR) · airframe 71,791 hrs · 10,979 cycles

FOUND APU FIRE DETECTOR WIRE W720-452-18R AND W720-451-18R DAMAGED. REMOVED AND REPLACED THE WIRE IAW AMM 26-15-02-004-001 REV 87, AMM 26-15-02-404-020 REV 87, WDM 26-15-11- REV 41 & SWPM 26-63-13 / 21-10-11 REV 62. OPS CHECKED GOOD.

Part: FIRE DETECTOR — DAMAGED (NR 4 NACELLE) · airframe 71,791 hrs · 10,979 cycles

FOUND NR 4 ENGINE LOWER AFT FIRE DETECTOR ASSEMBLY END BRACKET CLAMP BOLT DAMAGED. REMOVED AND REPLACED THE FIRE DETECTOR ASSEMBLY IAW AMM 26-11-02-004-076-003/26-11-02-404-098-003 REV 87. OPS CHECKED GOOD.

Part: REGULATOR — FAILED (CREW OXYGEN) · airframe 71,791 hrs · 10,979 cycles

FOUND CREW OXYGEN REGULATOR FAILED. REMOVED AND REPLACED THE REGULATOR IAW AMM 35-41-07-004-001 REV 87 & AMM 35-00-00-702-079 REV 87.

Part: CABLE — DAMAGED (NR 4 PYLON) · airframe 71,791 hrs · 10,979 cycles

FOUND WIRE CABLE DAMAGED NEAR NR 4 PYLON. REPAIRED THE WIRE CABLE IAW SWPM 20-30-13 REV 62, & WDM 24-21-41 REV 41. OPS CHECKED GOOD.

Part: BRACKET — CORRODED (BS 1470) · corrosion level 2 · airframe 71,791 hrs · 10,979 cycles

CORRODED BRACKET, RT MLG W/W HYD TUBES SUPPORT AT BS 1470. REPLACED IAW DWG 65B80259 SH 5 REV. A & SRM 51-40-02-0G-0 REV 77

Part: MODULE — INOPERATIVE (APU FIRE) · airframe 71,791 hrs · 10,979 cycles

FOUND APU FIRE SHUTDOWN MODULE (M869) DISCHARGED. FUNCTIONAL CHECK FAILED. REMOVED AND REPLACED THE FIRE SHUTDOWN MODULE IAW AMM 26-15-04-004-001, &26-15-04-404-008 REV 87. .

Part: FLOORBEAM — CORRODED (BS 2240) · corrosion level 2 · airframe 71,791 hrs · 10,979 cycles

FOUND FLOORBEAM CORRODED BS 2240 LBL 73. REPAIRED IAW SRM 53-00-51 REPAIR 3 REV. 77 AND DWG 65B38112 SHEET 13 REV.

Part: SKIN — DAMAGED (BS 287-340) · airframe 71,791 hrs · 10,979 cycles

LIGHTNING STRIKE AT BS 287 - 340, STRINGERS 14 - 15R SKIN. REPAIRED IAW EI T2016A53M-1652 REV. 1.

Part: SPAR — CORRODED (LT WING TE FLAP) · corrosion level 2 · airframe 71,791 hrs · 10,979 cycles

CORROSION ON THE REAR SPAR OF THE LT WING T/E OUTBOARD MID FLAP. REPAIRED IAW EI T2016A57M-1647 REV. 2.

Part: SEAT TRACK — BROKEN (BS 1970) · airframe 71,791 hrs · 10,979 cycles

FWD SEAT TRACK BROKEN AT BS 1670, RBL 75.92. REPAIRED IAW SRM 53-00-52 REPAIR 13 REV. 77.

Part: SEAT TRACK — BROKEN (BS 1486) · airframe 71,791 hrs · 10,979 cycles

FWD SEAT TRACK BROKEN AT BS 1486, RBL 75.92. REPAIRED IAW SRM 53-00-52 REPAIR 13 REV. 77.

Part: SEAT TRACK — BROKEN (BS 1978) · airframe 71,791 hrs · 10,979 cycles

FWD SEAT TRACK BROKEN AT BS 1978, LBL 75.92. REPAIRED IAW SRM 53-00-52 REPAIR 13 REV. 77.

Part: ANGLE — CRACKED (L1 DOOR FRAME) · airframe 71,791 hrs · 10,979 cycles

FOUND ANGLE CRACKED AT L1 DOOR UPPER FRAME BS 440 STRINGER 16L. REPAIRED IAW T2016A53M-1685 REV. 1. CONDITION CHECK NORMAL.</P>)

Part: WARNING MESSAGE — FALSE ACTIVATION (MLG) · airframe 71,370 hrs · 10,905 cycles

ON GO AROUND, GEAR FAILED TO RETRACT. MAIN AND BODY GEAR REMAINED DOWN. NOSE GEAR SHOWED TRANSIT. EICAS: NOSE GEAR DOOR AND GEAR DISAGREE. GEAR LOWERED NORMALLY. COMPLIED WITH FIM PROCEDURE 32-61, TASK 866 FOR CMC MESSAGE 32676. NO DEFECTS NOTED. COMPLIED WITH FIM 32-61, TASK 886, FOR CMC 32716. NO DEFECT NOTED. COMPLIED WITH FIM PROCEDURE 32-61, TASK 869 FOR CMC 32679. NO DEFECTS NOTED. COMPLIED WITH FIM PROCEDURE 2-61 TASK 889 FOR CMC 32719. NO DEFECTS NOTED. COMPLIED WITH OPS CHECK OF NOSE DOOR SEQUENCING VALVE IAW AMM 32-34-07-404-006. OPS CHECK GOOD.

Part: ESCAPE REEL — DAMAGED · airframe 70,194 hrs · 10,712 cycles

COCKPIT DESCENT DEVICE POSITION 7G CABLE EXTENDED. R & R DESCENT DEVICE 7G IAW AMM 25-61-01.

Part: ESCAPE REEL — DAMAGED (COCKPIT) · airframe 70,194 hrs · 10,712 cycles

COCKPIT DESCENT DEVICE POSITION 6F CABLE EXTENDED. R & R DESCENT DEVICE 6F IAW AMM 25-61-01.

Part: ESCAPE REEL — DAMAGED (COCKPIT) · airframe 70,194 hrs · 10,712 cycles

COCKPIT DESCENT DEVICE POSITION 4D CABLE EXTENDED. R & R DESCENT DEVICE POSITION 4D IAW AMM 25-61-01.

Part: ESCAPE REEL — DAMAGED (COCKPIT) · airframe 70,194 hrs · 10,712 cycles

COCKPIT DESCENT DEVICE POSITION 5E, CABLE EXTENDED. R & R DESCENT DEVICE POSITION 5E IAW AMM 25-61-01.

Part: ESCAPE REEL — DAMAGED (COCKPIT) · airframe 70,194 hrs · 10,712 cycles

COCKPIT DESCENT DEVICE POSITION 3C, CABLE EXTENDED. R & R POSITION 3 DESCENT DEVICE IAW AMM 25-61-01.

Part: BRACE — BROKEN (RT WING TE FLAP) · airframe 69,565 hrs · 10,603 cycles

INSPECTION FOUND RT OTBD MID FLAP INBD SIDE ROLLER TRACK LINAGE BROKEN. ROD ASSY LINKAGE REPLACED IAW AMM 20-51-01.

Part: FLAP TRACK — WORN · airframe 69,565 hrs · 10,603 cycles

CUSTOMER REQUEST, DURING C/OUT FLAP TRACK INSPECTION, FOUND NR 8 FLAP TRACK WITH EXCESSIVE WEAR. NR 8 FLAP TRACK ASSY REPLACED IAW AMM 27-51-27.

Part: LAMP — INOPERATIVE (EMERGENCY LIGHT) · airframe 69,565 hrs · 10,603 cycles

ON CHECK, FOUND L1 DOOR EMERGENCY LIGHT INOPERATIVE. L1 DOOR EMERGENCY LIGHT RELAMPED AND OPS CHECKED SATISFACTORY IAW AMM 33-51-00.

Part: CIRCUIT CARD — MALFUNCTIONED (WARNING SYSTEM) · airframe 68,314 hrs · 10,395 cycles

TEMPORARY DISPLAY OF STATUS MESSAGE ALTITUDE ALERT SYSTEM DURING CRUISE, CMC MESSAGE 31086, FOLLOWED FIM PROCEDURE IAW 31-51 TASK 86. RESET CIRCUIT CARD. THEN TESTED OK IAW AMM 31-51-02 401. MCC REQUEST ITEM TRANSFER TO MEL 34-16-01A CAT A.

Part: RAM AIR DOOR — SEPARATED (NR 1) · airframe 64,769 hrs · 9,803 cycles

DURING CRUISE, LOUD MECHANICAL CLANKING PULSATING NOISE FROM LT MAIN DECK JUST FWD OF THE LE, LASTED FOR THREE MINUTES NO EICAS MSGS ALL SYS APPEARED NORMAL. CHECKED ON GND FOUND NR 1 AIR CONDITIONING RAM AIR DOOR FWD SECTION RIPPED OFF & MISSING IN COMM WITH MCC. TRANSFERRED ITEM TO CDL 21-62-01, INLET REMOVED.

Part: DOOR — SEPARATED (AC PACK) · airframe 64,769 hrs · 9,803 cycles

ON POST FLIGHT FOUND PACK 1 INLET DOOR MISSING & PANEL AFT OF DOOR HONEYCOMB DAMAGED. IAW EO TEMP REPAIR ACCOMPLISHED ON NR 1 PACK PANEL. INSPECTION REQUIRED EVERY 25 FLIGHT CYCLES EO 4453B034.

Part: PANEL — CRACKED (FUSELAGE) · airframe 64,018 hrs · 9,669 cycles

MD L1 DOOR FWD CUT OUT LOWER REVEAL PANEL FOUND CRACKED. REPAIRED CRACKED AREA, TRIMMED OUT IAW RI 53-10-10600 REV A & EO NR 4453B008.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 64,018 hrs · 9,669 cycles

MD STATION 1180 LBL 110 FLOOR INTERCOSTAL WEB FOUND CRACK. INTERCOSTAL WEB REPLACED IAW RI-53-41-10598 REV A.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 64,018 hrs · 9,669 cycles

MD STATION 1180 RBL 110 FLOOR INTERCOSTAL WEB FOUND CRACK. INTERCOSTAL WEB REPLACED IAW RI-53-41-10598 REV A.

Part: DOOR SILL — CRACKED (CARGO BAY) · airframe 64,018 hrs · 9,669 cycles

MD SIDE CARGO DOOR AFT DOOR SILL TOP SURFACE PANEL FOUND CRACKED. REPAIR CARRIED OUT IAW RI-25-55-10605 REV A.

Part: DOOR SILL — CRACKED (FUSELAGE) · airframe 64,018 hrs · 9,669 cycles

MD SIDE CARGO DOOR & FWD OTBD SILL ASSEMBLY & TOP SURFACE PANEL FOUND CRACKED. SURFACE REPAIR CARRIED OUT IAW RI-25-55-10605 REV A.

Part: RING — CRACKED (THRUST REVERSER) · airframe 64,018 hrs · 9,669 cycles

NUMBER 2 ENG RT THRUST REVERSER AFT CASCADE SUPPORT RING FOUND CRACKED AT NR 6 CASCADE. LOWER SUPPORT RING REPLACED IAW E0 1978A084.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 64,018 hrs · 9,669 cycles

MD STATION 1180 RBL 110 FLOOR INTERCOSTAL WEB LOWER CHORD FOUND CRACKED. LOWER CHORD REPLACED IAW RI-53-41-10598 REV A.

Part: STIFFENER — CRACKED (FUSELAGE) · airframe 64,018 hrs · 9,669 cycles

MD L5 DOOR FWD CUT OUT UPPER VERTICAL STIFFENER FOUND CRACKED. STIFFENER REPLACED IAW SRM 51-10-02.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 62,127 hrs · 9,352 cycles

NBSP MD OVERHEAD EMERGENCY LIGHT FOUND INOPERATIVE. MD OVERHEAD EMERGENCY LIGHT LAMP REPLACED & OPERATIONS TESTED NORMAL IAW AMM 33-51-07.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 62,127 hrs · 9,352 cycles

L1 DOOR OVERHEAD EMERGENCY LIGHT FOUND INOPERATIVE. L1 DOOR OVERHEAD EMERGENCY LIGHT LAMP REPLACED & OPERATIONS TESTED NORMAL IAW AMM 33-51-05.

Part: PDU — MALFUNCTIONED (CARGO BAY) · airframe 61,926 hrs · 9,307 cycles

SMOKE IN MAIN CARGO DECK DURING LOADING. SOURCE OF SMOKE FOUND TO BE FROM PDU 14L. PDU 14L DEACTIVATED & DEFERRED IAW DDG 25-53-01C. PERFORMED INSPECTION IAW 05-51-56, NO FURTHER DISCREPANCIES NOTED.

Part: PDU — MALFUNCTIONED (CARGO BAY) · airframe 61,926 hrs · 9,306 cycles

SMOKE IN MAIN CARGO DECK DURING LOADING. SOURCE OF SMOKE FOUND TO BE FROM PDU 14L. SEE LP 468640 ITEM 1M FOR DEFERRAL. PERFORMED INCP 05-51-56, SMOKE ON FUMES IN CABIN. NO FURTHER DISCREPANCIES NOTED.

Part: WIRE — CHAFED (APU FIRE LOOP) · airframe 60,512 hrs · 9,057 cycles

APU FIRE WARNING IN FLIGHT. REPLACED AFLOTS CARD, FIRE LOOP A, FIRE LOOP B, R8052 RELAY, R 7782 RELAY, MEGGED WIRING FROM D63P AND D67P TO DW3206E AND DW3205E, THEN REPLACED WIRING FROM BOTH FIRE LOOPS TO THE APU FIREWALL AFTER FINDING CHAFED WIRES UNDER THE CLAMPS.

Part: CIRCUIT CARD — MALFUNCTIONED (FIRE DETECTION) · airframe 60,501 hrs · 9,056 cycles

AT TOP OF CLIMB AND ENROUTE, FIRE APU EICAS MESSAGE DISPLAYED AND BELL SOUNDED. ACCOMPLISHED QRH PROCEDURE 8.1. INDICATION EXTINGUISHED UPON LANDING (REPLACED AFLOTS CARD, OPS NORMAL).

Part: RELAY — MALFUNCTIONED (FIRE DETECTION) · airframe 60,495 hrs · 9,055 cycles

AT ABOUT 0200, EICAS MESSAGE "FIRE APU" ILLUMINATED FOLLOWED BY FIRE WARNING BELL. COMPLETED QRH 8.1. REPLACED RELAY R7690 AND APU AFLOTS CARD.

Part: BULB — INOPERATIVE (EMERGENCY LIGHT) · airframe 57,609 hrs · 8,556 cycles

MAIN DECK ZONE A CEILING LIGHT FOUND INOPERATIVE. BULB REPLACED AND TESTED OK MM 33-51-07.

Part: SKIN — CORRODED (RT WING TE FLAP) · airframe 57,082 hrs · 8,478 cycles

RT INBT FORE FLAP LOWER SURFACE NEAR CENTER FORE FLAP TRACK AREA FOUND MINOR CORROSION. RT INBD FORE FLAP OTBD LOWER SURFACE PANEL REPLACED AND INSTALLED IAW SRM 51-10-02, SRM 51-40-02.

Part: SKIN — DAMAGED (RT WING) · airframe 57,082 hrs · 8,478 cycles

RT WING INBD MID FLAB ROLLER PLATES REPLACEMENT, SEVERAL FASTENER HOLES OF THE NOSE SKIN ARE FOUND LARGER THAN THAT CALLED OUT IN ATTACHED SB 747-57-2320, FIG 53. ALUMINUM FREEZE PLUGS INSTALLED AND FASTENERS INSTALLED IN OVERSIZED HOLE LOCATIONS IAW RS NR-57-55-37435, REV A.

Part: SKIN — DENTED (BS 670-691) · airframe 57,082 hrs · 8,478 cycles

SKIN DENT AFT OF FWD CARGO DOOR BETWEEN S38 - 39R, INSPECTION. SKIN PANEL REPAIRED IAW RS NO R53-20-37412.

Part: SHEAR TIE — DAMAGED (BS 1700) · airframe 57,082 hrs · 8,478 cycles

AFT CARGO FRAME SHEAR TIE, RIVET HOLE FOUND ELONGATED AT STA 1700 BETWEEN S-33R AND S-34R. FRAME SHEAR TIE REPAIRED IAW SRM 53-00-07-2R-3.

Part: BULKHEAD WEB — CRACKED (BS 1480) · airframe 57,082 hrs · 8,478 cycles

BS 1480, RT BULKHEAD WEB FOUND CRACKED. BULKHEAD WEB REPAIRED IAW SRM 53-40-08-2R-1, REPAIR 1, FIG 201.

Part: SKIN — DAMAGED (NR 2 NACELLE) · airframe 57,082 hrs · 8,478 cycles

NR 2 PYLON PANEL 462EL ONE BOLT HOLE ELONGATED. NR 2 PYLON PANEL 462EL PATCH REPAIRED IAW RS NR R-54-00-37414, REV A.

Part: INTERCOSTAL — CRACKED (BS 1220) · airframe 57,082 hrs · 8,478 cycles

MAIN DECK BS 1220, RBL 107 BELOW FLOOR INTERCOSTAL WEB CRACKED. INTERCOSTAL REPAIRED IAW RS-R53-40-37426.

Part: SKIN — CRACKED (BS 980 S38L) · airframe 57,082 hrs · 8,478 cycles

BS 980, STR 38L SKIN FOUND CRACK APPROX .0937" LONG. SKIN REPAIRED IAW SRM 53-20-01-2R-2, REPAIR 2, FIG 201.

Part: CHANNEL — CRACKED (BS 740) · airframe 57,082 hrs · 8,478 cycles

MAIN DECK RT BS 740 TENSION TIE AREA, ONE HOLE FOUND CRACKED AT AFT CHANNEL APPROX 0.040" RUNNING UPWARD. AFT CHANNEL REPAIRED IAW SRM 53-20-30-2R-1, REPAIR 1, FIG 201.

Part: TENSION TIE — CRACKED (BS 740) · airframe 57,082 hrs · 8,478 cycles

MAIN DECK RT BS 740 TENSION TIE AREA, ONE HOLE FOUND CRACKED AT FWD CHANNEL APPROX .040" RUNNING UPWARD. FWD CHANNEL REPAIRED IAW SRM 53-20-30-2R-1, REPAIR 1, FIG 201.

Part: CHANNEL — CRACKED (BS 720) · airframe 57,082 hrs · 8,478 cycles

MAIN DECK LT BS 720 TENSION TIE AREA, FOUND ONE HOLE CRACK AT AFT CHANNEL APPROX .030". AFT CHANNEL REPAIRED IAW SRM 53-20-30-2R-1, REPAIR 1, FIG 201.

Part: TENSION TIE — CRACKED (BS 760) · airframe 57,082 hrs · 8,478 cycles

MAIN DECK RT BS 760 TENSION TIE AREA, ONE HOLE FOUND CRACKED AT AFT CHANNEL APPROX .040" RUNNING UPWARD. AFT CHANNEL REPAIRED IAW SRM 53-20-30-2R-1, REPAIR 1, FIG 201.

Part: TENSION TIE — CRACKED (BS 760) · airframe 57,082 hrs · 8,478 cycles

MAIN DECK LT BS 760 TENSION TIE, ONE HOLE FOUND CRACKED AT AFT CHANNEL APPROX 0.060" RUNNING UPWARD. AFT CHANNEL REPAIRED IAW SRM 53-20-30-2R-1, REPAIR 1, FIG 201.

Part: FAIRING — DAMAGED (MLG DOOR) · airframe 55,864 hrs · 8,311 cycles

DURING WALKAROUND INSP, MX FOUND THE LT WING LANDING GEAR STRUT DOOR FAIRING - T/E, MEASURING 3.0 IN. X 1.0 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 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: FAIRING — DELAMINATED (RT MLG DOOR) · airframe 54,808 hrs · 8,184 cycles

DURING WALKAROUND INSPECTION, MX FOUND THE LT & AMP; RT WING GEAR DOOR FAIRINGS DELAMINATED, (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 ALLOWABLE DAMAGE. PERFORMED A TIME LIMITED REPAIR AS DESCRIBED IN PART 1 WORK INSTRUCTIONS.

Part: STRUCTURE — DAMAGED (THRUST REVERSER) · airframe 54,270 hrs · 8,120 cycles

DURING MX WALKAROUND, FOUND DAMAGE TO THE NR 2 ENGINE THRUST REVERSER ACOUSTIC MESH AND HONEYCOMB. PERFORMED A TIME LIMITED REPAIR.

Part: CONTROL PANEL — FAILED (ETL) · airframe 53,963 hrs · 8,086 cycles

LIGHTS ON ETL REMOTE PANEL FLASHING. REMOVED AND INSTALLED ETL REMOTE PANEL IAW AMM 23-24-01 OPS CHECKED GOOD.

Part: DEPRESSOR — DAMAGED (CARGO DOOR) · airframe 53,575 hrs · 8,042 cycles

DAMAGE TO THE LOWER LOBE - AFT CARGO DOOR - BS 1920 SEAL DEPRESSOR FOUND, MEASURING 6" LENGTH. DAMAGE WAS DETERMINED TO BE BEYOND THE REPAIR LIMITS IAW THE SRM 53-00-15, FIGURE 201, REPAIR 2. PERFORM A TIME LIMITED REPAIR.

Part: STRUCTURE — CRACKED (LADDER) · airframe 53,166 hrs · 7,995 cycles

MAIN DECK TO UPPER DECK STOWABLE CREW LADDER CRACKED - ACCOMPLISH REPAIR TO THE MAIN DECK TO UPPER DECK STOWABLE CREW LADDER CRACK.

Part: FLOORBOARD — DELAMINATED (BS 1720) · airframe 52,838 hrs · 7,959 cycles

DURING WALKAROUND INSPECTION, MX REPORTED DAMAGE FOUND TO MAIN DECK FLOORBOARD BS 1720 LBL 117.4 DAMAGE IS BEYOND THE SRM 53-00-50-1A-1, FIG 101. REPAIRED IAW THE SRM 53-00-50, REPAIR 1.

Part: MOTOR — BURNED (COCKPIT SEAT) · airframe 52,780 hrs · 7,952 cycles

CAPT SEAT ELECTRIC FUNCTION FAILED. SLIGHT ELECTRICAL BURN ODOR. TURNED POWER SWITCH OFF. (VERIFIED MANUAL ADJUSTMENT WORKS. ELECTRIC MOTOR BELIEVED TO BE UNSERVICEABLE. TRANSFERRED TO DMI 26719 IAW MEL 25-11-2-1.)

Part: PANEL — DEFORMED (RT WING TE FLAP) · airframe 51,904 hrs · 7,862 cycles

DURING WALK-AROUND INSP, MX REPORTED RT INBD MID FLAP -T/E OF COVE PANEL -DEFORMATION WBL435.55, MEASURING 5.0 IN. LONG X 0.250 IN. DEPTH (UPWARD DEFLECTION) (REF FIG 4). DISPOSITION WAS MADE TO PERFORM A TIME LIMITED REPAIR AS DESCRIBED IN PART 1 WORK INSTRUCTIONS; SCHEDULE REPEAT INSPECTIONS AT EVERY 5 FC IAW PART 2 AND PERMANENT REPAIR IAW PART 3 PRIOR TO THE ACCUMULATION OF 1,000 FLT HRS AFTER PART 1.

Part: PANEL — DEFORMED (TE FLAP) · airframe 51,904 hrs · 7,862 cycles

DURING WALK-AROUND INSP, MX REPORTED RT INBD MID FLAP - T/E OF COVE PANEL - DEFORMATION WBL259.55, MEASURING 10.0 IN. LONG X 0.5 IN. DEPTH UPWARD DEFLECTION REF FIG 2.

Part: PANEL — DEFORMED (TE FLAP) · airframe 51,904 hrs · 7,862 cycles

DURING WALK-AROUND INSPECTION, MX REPORTED RT INBD MID FLAP - T/E OF COVE PANEL - DEFORMATION WBL168.55, MEASURING 5.0 IN. LONG X 0.250 IN. DEPTH (UPWARD DEFLECTION) (REF FIG 1).

Part: PANEL — DEFORMED (TE FLAP) · airframe 51,904 hrs · 7,862 cycles

DURING WALK-AROUND INSPECTION, MX REPORTED RT INBD MID FLAP - T/E OF COVE PANEL - DEFORMATION (4 PLACES) WBL347.55, MEASURING 4.0 IN. LONG X 0.375 IN. DEPTH (UPWARD DEFLECTION) (REF FIG 3). (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) PER PART 2 AND PERMANENT REPAIR IAW PART 3 PRIOR TO THE ACCUMULATION OF 1,000 (FLIGHT HOURS) AFTER PART 1.)

Part: INLET — ERODED (NR 3 NACELLE) · airframe 50,864 hrs · 7,750 cycles

DURING WALK-AROUND INSP, MX FOUND THE NR 3 RT FAN COWL L/E WITH EROSION DAMAGE, MEASURING 0.350 IN. WIDE X 1.5 FT. LONG (REF FIG 1). THE DAMAGE IS BEYOND THE ALLOWABLE DAMAGE LIMITS IAW SRM 54-25-01 (ALLOWABLE DAMAGE 1). (DISPOSITION WAS MADE TO PERFORM A TIME LIMITED REPAIR AS DESCRIBED IN PART 1 WORK INSTRUCTIONS, DVI INSPECTIONS AFTER EVERY 5 FLIGHT CYCLES UNTIL ACCOMPLISHMENT OF PERMANENT REPAIR PRIOR TO THE ACCUMULATION OF 2,000 FH (FLIGHT HOURS) AFTER PART 1.)

Part: STRUCTURE — DAMAGED (RT MLG DOOR) · airframe 50,237 hrs · 7,656 cycles

DURING WALKAROUND INSP, MX FOUND THE RT WING GEAR STRUT DOOR - L/E BIRD STRIKE DAMAGE, MEASURING 2.5 IN. X 2.5 IN. (REF FIG 1). (DISPOSITION WAS MADE TO PERFORM A TIME LIMITED REPAIR AS DESCRIBED IN PART 1 WORK INSTRUCTIONS, SCHEDULE REPEAT INSPECTIONS AT EVERY 1 FC (FLIGHT CYCLE) AND PERMANENT REPAIR PRIOR TO THE ACCUMULATION OF 1,000 FH (FLIGHT HOURS) AFTER PART 1 HAS BEEN ACCOMPLISHED IAW SRM 51-70-17 OR SRM 51-70-07.)

Part: SEAT TRACK — CRACKED (BS 570) · airframe 50,021 hrs · 7,620 cycles

DURING LOADING, THE BS 570, LBL 25 LOWER LOBE SEAT TRACK WAS FOUND CRACKED ON 13MAR2011. THE DAMAGE MEASURES 7 INCHES IN LENGTH. NO CARGO MAY BE CARRIED IN THE LOWER LOBE P-11 AND P-12 POSITIONS UNITL PART 3 IS ACCOMPLISHED. (PART 1 OF THIS EO ACCOMPLISHES A TEMPORARY REPAIR OF THE DAMAGE SEAT TRACK. PART 2 OF THIS EO ACCOMPLISHES A REPETITIVE INSP OF THE TEMPORARY REPAIR TO ENSURE CONTINUED AIRWORTHINESS. PART 3 OF THIS EO ACCOMPLISHES THE PERMANENT REPAIR AT THE NEXT A-CHECK.)

Part: LENS — DAMAGED (LANDING LIGHT) · airframe 49,873 hrs · 7,598 cycles

DURING WALK-AROUND INSP AT PVG, MX FOUND THE LT OTBD LANDING LIGHT - LENS COVER ASSY DAMAGED. (DISPOSITION WAS MADE TO ACCOMPLISH TIME LIMITED REPAIR AS DESCRIBED IN PART 1 WORK INSTRUCTIONS, SCHEDULE REPEAT INSP EVERY 1 FC AND PERMANENT REPAIR BY REPLACING THE DAMAGED LENS COVER ASSY PRIOR TO THE ACCUMULATION OF 25 FC (FLIGHT CYCLES) AFTER ACCOMPLISHMENT OF PART 1.)

Part: SKIN — DAMAGED (BS 2596 S46R) · airframe 49,035 hrs · 7,455 cycles

DURING WALK-AROUND INSP BEING PERFORMED, DAMAGE WAS FOUND TO THE FUSELAGE SKIN BS 2596 ABOVE STR- 46R (TAIL JACK AREA) CONSISTING OF DENT L:1.5 IN. W:0.750 IN. D:0.0625 (REF FIG 1). THE DAMAGE IS OUT OF THE SRM 53-00-01, FIG 101. ALLOWABLE DAMAGE 1, DETAIL III. TIME LIMITED REPAIR PERFORMED AS DESCRIBED IN PART 1 WORK INSTRUCTIONS, SCHEDULE REPEAT DVIS AT EVERY 5 FC, AND PERMANENT REPAIR PRIOR TO THE ACCUMULATION OF 1,000 FH.

Part: SKIN — DAMAGED (RT WING TE FLAP) · airframe 48,208 hrs · 7,309 cycles

DURING A3 CHECK INSP OF ACFT, MX FOUND 4 EA CHAFE MARKS ON THE RT INBD AFT FLAP UPPER EXTERNAL SKIN CAUSED BY BOTTOM OF SCREWS THAT SECURE AFT SECTION OF COVE PANEL. AFTER BLENDOUT AREAS 1-4 FOUND BEYOND ALLOWABLE DAMAGE LIMITS IAW SRM 57-53-01, FIG 101, DETAIL II (SHEETS 1, 2 AND 3). THE UPPER PANEL ASSY - OUTER SKIN IS MADE FROM 0.125 IN. 7075-T6 (CHEMMILLED TO 0.012 IN MIN) ALUMINUM HONEYCOMB IAW BMS 4-4, TYPE 3-15. DETAIL DAMAGE AS FOLLOWS: WBL139.682 - 6.0 IN. LONG X 2.5 IN. WIDE X 0.016 IN. DEPTH. WBL208.682 - 6.0 IN. LONG X 3.5 IN. WIDE X 0.035 IN. DEPTH. WBL229.142 - 4.5 IN. LONG X 3.0 IN. WIDE X 0.044 IN. DEPTH. WBL359.186 - 5.0 IN. LONG X 3.75 IN. WIDE X 0.065 IN. DEPTH. HFEC INSP PERFORMED TO THE DAMAGED AREAS 1-4 IAW NDT MANUAL, PART 6 51-00-00, FIG 4, OR 23 WITH CRACK FREE CONDITION ON AREAS 1 - 3. AREA 4 (WBL359.186) REVEALED 2 EA CRACKS, REMOVED WITH A 0.5 IN. DIAM HOLE. DISPOSITION WAS MADE TO PERFORM A TIME LIMITED REPAIR AS DESCRIBED IN PART 1 WORK INSTRUCTIONS, DVI INSPECTIONS AT EVERY 1,000 FH (FLIGHT HOURS) UNTIL ACCOMPLISHMENT OF PERMANENT REPAIR PRIOR TO, OR AT THE NEXT C CHECK AFTER PART 1.

Part: HOUSING — FRACTURED (FUSELAGE) · airframe 47,298 hrs · 7,155 cycles

DURING D02+C03 CHECK OF DATUM ACFT, 3 HSG (PN: 65B63619-1/-501) FLANGE FRACTURE WERE FOUND ON MAIN DECK CARGO SYS P-29 SIDE RESTRAINT ASSY (PN: 457U1103-4) BETWEEN STA 2220 AND STA 2319 (REF FIG 1) AND MFG SERV REQ 1-1645483474. (DUE TO NO APPLICABLE REPAIR METHOD CAN BE FOUND IN CMM 25-56-65 AND SRM, AND DELIVERY DATE OF ORDERED NEW HSGS WOULD NOT SUPPORT THE SCHEDULED AIRPLANE RETURN TO SERVICE DATE, DISPOSITION WAS MADE TO ACCOMPLISH A TIME LIMITED REPAIR AS DESCRIBED IN PART 1 WORK INSTRUCTIONS, SCHEDULE INITIAL &AMP; REPEAT DVIS AT EVERY 25 FC (FLIGHT CYCLES) AND PERMANENT REPAIR PRIOR TO THE ACCUMULATION OF 180 DAYS AFTER PART 1)

Part: SEAT TRACK — CORRODED (BS 1210) · airframe 47,298 hrs · 7,155 cycles

DURING D02+C03 CHECK OF DATUM ACFT, DAMAGE WAS FOUND ON CROWN AREA OF MAIN DECK SEAT TRACK (PN: 65B16026-34) OF THE OVERWING LONGITUDINAL FLOORBEAM WEB NEAR STA1210, RBL11.33. THE LOCATION IS SHOWN IN REF FIG 1. PERMANENT REPAIR WAS PERFORMED IAW SRM 53-40-52 R3 FIG 201 AND EGAT EI T2010A53B-1591 R1. THE PURPOSE OF THIS EO IS TO RECORD A MAJOR REPAIR WITH CATEGORY B APPROVED BY FAA FORM 8100-9, FIG 4 AND SCHEDULE A DETAILED VISUAL INSP OF THE OVERWING LONGITUDINAL FLOORBEAM WEB IN THE AREA OF THE REPAIR WITH AN INITIAL INSP PRIOR TO 13,155 TFC AND REPEAT INSP AT EVERY 6,000 FC. THESE INSPECTIONS ARE BASED UPON SRM 53-40-52-2R-3, REPAIR 3- SECTION 44- STA 1050 THRU 1240- SPLICE REPAIR OF BAC 1520-1873. THIS REPAIR IS CATEGORY B REPAIR AND HAS AN EFFECT ON THE INSPECTION PROGRAM OF STRUCTURAL SIGNIFICANT ITEMS W-16 AT THE REPAIR AREA. THE INSP REQUIREMENTS IN THIS EO WILL MEET THE W-16 SSID D6-35022 INSP REQUIREMENTS FOR THE REPAIR AREA.

Part: DOUBLER — CRACKED (BS 2231) · airframe 47,298 hrs · 7,155 cycles

DURING D-CHECK INSP OF DATUM ACFT, EGAT FOUND THE REVEAL DOUBLER CRACK ABOUT 2.5 INCHES AT MAIN ENTRY DOOR NR 5 NEAR STA 2231 BETWEEN S-21L AND 22L. (REPAIR WAS ACCOMPLISHED IAW EGAT EI T2010A53B-1512 AND APPROVED BY MFG SR 1-1634841517 AND FAA 8100-9 DATED 04 AUG, 2010 (FIGURE 3). IAW FORM 8100-9, THIS REPAIR IS CATEGORY B, AND NEEDS SUPPLEMENTAL INSPECTIONS AT 16000 TFC, WITH REPEAT INTERVALS 3000 FC.)

Part: SKIN — DEFORMED (CARGO DOOR) · airframe 47,298 hrs · 7,155 cycles

DURING D-CHECK, THE LOWER LOBE FWD CARGO DOOR'S SKIN AT THE FWD LOWER CORNER WAS DEFORMED. (THE DAMAGE WAS REPAIRED WITH A DOUBLER INSTALLED IAW SRM 52-30-01, REPAIR NR 2 FIG 201, SHEET 7, DETAIL IV BY EGAT AS A CATEGORY B PERMANENT REPAIR DOCUMENTED ON EGAT NRC105. SEE FIG 1. THE DOUBLER WAS MADE FROM 0.125 INCH THICK CLAD 2024-T3 IAW SRM 52-30-01 REPAIR NR 2, FIG 201, SHEET 3, TABLE I. THE NOTED DAMAGE IS APPLICABLE TO THE SRM 52-30-01 REPAIR NR 2, FIG 201 AND THUS IS A CATEGORY B REPAIR IAW THE NOTES IN THE REPAIR. THIS CATEGORY B REPAIR HAS FAA APPROVAL WHEN THE SUPPLEMENTAL INSPECTIONS AS GIVEN IN SRM 53-20-01, REPAIR NR 2, TABLE III ARE ACCOMPLISHED. THIS REPAIR WILL HAVE AN EFFECT ON FATIGUE CRITICAL BASE LINE STRUCTURE. INCORPORATION OF THE INSP REQUIREMENTS, AS GIVEN IN THE ABOVE NOTED SRM REPAIR INTO THE AIRPLANES MX PROGRAM SATISFIES THE DAMAGE TOLERANCE ASSESSMENT OF THE REPAIR.)

Part: WEB — GOUGED (BS 1917) · airframe 47,298 hrs · 7,155 cycles

DURING D02/C03 CHECK, GOUGE DAMAGE WAS FOUND TO THE MAIN DECK BS 1917, RBL 49 WEB OF LATERAL GUIDE SUPPORT (REF FIG 1 THRU 3, PN 65B20024-65). GOUGE WAS CLEANED, BLENDED OUT AND REWORKED IAW EGAT EI T2010A53B-1513 ON WEB IAW THE SRM 53-60-53 WITHIN ALLOWABLE LIMITS AS DEFINED BY THE MFG AND ENSURED NO CRACK AT REWORKED AREA BY HFEC IAW NDT MANUAL PART 6, 51-00- 00. SURFACE FINISHED IAW SRM 51-20-01. MFG REVIEWED AND THE REPAIR PROPOSAL IS STRUCTURALLY ACCEPTABLE PROVIDED THAT A 63RHR OR BETTER SURFACE FINISH IS MAINTAINED FOR THE BLENDED WEB. (REF SR 1-1640130216 AND MFG RDR, FIGURE 4)

Part: SKIN — DAMAGED (BS 682) · airframe 47,298 hrs · 7,155 cycles

DURING D-CHECK, A DENT THAT HAD INTERIM APPROVAL AND WAS CHECKED AT EVERY "A" CHECK UNTIL A PERMANENT REPAIR COULD BE ACCOMPLISHED, WAS LOCATED AT BS 682 AND STR 37R. (DAMAGE WAS TRIMMED OUT AND A DOUBLER AND FILLER WERE INSTALLED IAW SRM 53-00-01, REPAIR NR 1 BY EGAT AS A CATEGORY B PERMANENT REPAIR IAW EGAT EI T2010A53B-1438 DOCUMENTED ON EGAT NRC1010. SEE FIG 2. THE SKIN IS MADE FROM CLAD 2024-T3 0.100 INCH THICK WITH MINIMUM CHEM-MILLED THICKNESS OF 0.063 IAW SRM 53-20-01, FIG 1, DETAIL II, ITEM 19. THE REPAIR CONSISTS OF DOUBLER 0.125 INCH THICK AND A FILLER 0.100 INCH THICK BOTH MADE FROM CLAD 2024-T3 INSTALLED WITH BACB30NW8K HI-LOKS, BACB30NW6K HI-LOKS AND BACR15CE8D RIVETS ALL PARTS INSTALLED IAW SRM 53-00-01 REPAIR NR 1, FIG 3)

Part: STIFFENER — CRACKED (BS 1265-1480) · airframe 47,298 hrs · 7,155 cycles

DURING D-CHECK INSP OF DATUM ACFT, SEVERAL LIGHT CORROSIONS WERE FOUND ON STIFFENERS AND PANELS UNDER KEEL TORQUE BOX AT STA 1265 TO STA 1480, RBL 9 TO LBL 9 (REF FIG 1). (THE CORROSION AREAS WERE BLENDED OUT, TRIMMED IAW EGAT EI T2010A53B-1516 AND APPROVED BY MFG SR 1-1637202262 AND FAA 8100-9 DATED 30 JULY, 2010 (FIGURE 2). THE REPAIR WAS CONSIDERED CATEGORY A REPAIR (PERMANENT), SO NO SUPPLEMENTAL INSPECTIONS ARE REQUIRED IAW THIS EO. (LEVEL 1 CORROSION))

Part: STIFFENER — CRACKED (NR 3 NACELLE) · airframe 47,298 hrs · 7,155 cycles

DURING D-CHECK IN TPE, THE NR 3 STRUT WAS FOUND TO HAVE A CRACK IN A STIFFENER TEE ANGLE NEAR NAC STA 298 AND NAC WL 140. FIG 1 FOR DAMAGE LOCATION. (THE DAMAGE WAS CUT OUT WITH AN ANGLE AND FILLERS BEING INSTALLED AS SHOWN IN FIG 2 AND IAW SRM 54-51-02 REPAIR NR 2 IAW EGAT EI T2010A54B-1547 DOCUMENTED ON EGAT NRC402 AND APPROVED BY BOEING ON RDR DATED 27 JULY 2010. ALL STRUT STIFFENERS ARE CONSIDERED TO BE A PSE ITEM IAW SRM 51-00-04 FIGURE 2, TABLE I, SHEET 4 OF 5. THE DAMAGED TEE IS MADE FROM AND1506-2115 2024-T62 ALUMINUM EXTRUSION IAW SRM 54-51-02 FIGURE 1, SHEET 2, ITEM 26. THE REPAIR CONSISTED OF CUTTING OUT THE DAMAGE AND INSTALLING AN ANGLE MADE FROM AND10134-1406 70475-T6 EXTRUSION AND FILLERS MADE 7075-T6 ALUMINUM SHEET AND USED BACB30MY6K FASTENERS; THIS CATEGORY A PERMANENT REPAIR HAS RDR APPROVAL DATED 27, JULY 2010 ON MESSAGE EGA-TLS-10-0078-04B AND SR 1-1642645237.)

Part: STIFFENER — CRACKED (NR 2 NACELLE) · airframe 47,298 hrs · 7,155 cycles

DURING D-CHECK, THE NR2 STRUT WAS FOUND TO HAVE A CRACK IN A STIFFENER TEE ANGLE ON THE INBD SIDE NEAR NAC STA 377 AND NAC WL 155. SEE FIG 1 FOR DAMAGE LOCATION AND REPAIR DETAILS. (THE DAMAGE WAS CUT OUT WITH AN ANGLE AND FILLERS BEING INSTALLED AS SHOWN IN FIG 2 AND IAW SRM 54-51-02 REPAIR NR2 IAW EGAT EI T2010A54B-1540 DOCUMENTED ON EGAT NRC 713 AND APPROVED BY MFG ON RDR DATED 26 JULY 2010. ALL STRUT STIFFENERS ARE CONSIDERED TO BE A PSE ITEM IAW SRM 51-00-04 FIG 2, TABLE I SHEET 4 OF 5.THE DAMAGED TEE IS MADE FROM AND1506-2115 2024-T62 ALUMINUM EXTRUSION IAW SRM 54-51-02, FIG 1, SHEET 2, ITEM 26. THE REPAIR CONSISTED OF CUTTING OUT THE DAMAGE AND INSTALLING AN ANGLE MADE FROM AND10134-1406 70475-T6 EXTRUSION AND FILLERS MADE 7075-T6 ALUMINUM SHEET AND USED BACB30MY6K FASTENERS. THIS CATEGORY A PERMANENT REPAIR HAS MFG RDR APPROVAL DATED 26 JULY 2010 ON MESSAGE EGA-TLS-10-0079-02B AND SR 1-1642701344)

Part: FLAP — DEPARTED (RT TE FLAP) · airframe 47,281 hrs · 7,154 cycles

DURING LANDING, 12 FT OF THE RT WING INBD T/E FORE FLAP OUTBD END DEPARTED THE AIRPLANE AND CAUSED DAMAGE TO THE SKIN, FRAMES AND STRINGERS FROM BS 1640 TO 1660, S-19R TO -28R.(THE DAMAGED AREA WAS REMOVED AND A TEMPORARY REPAIR WAS INSTALLED TO ALLOW ONE PRESSURIZED NON-REVENUE FERRY FLIGHT TO TPE FOR PERMANENT REPAIR. THE TEMPORARY REPAIR WAS ACCOMPLISHED IAW FRR-001 THROUGH FRR-011 AND IS APPROVED BY A MFG IAW THE FORM 8100-9 DATED 01JUL2010 AND FORM 337 DATED 01JUL2010 & NBSP; PERMANENT REPAIR IS REQUIRED IAW EO 4453A378 WITHIN ONE FLIGHT AFTER THE ACCOMPLISHMENT OF THIS EO.)

Part: FLAP SYSTEM — SEPARATED (TE FLAPS)

((F8ER)) ON APPROACH, THE RT INBD, FORE FLAP, OTBD SECTION SEPARATED FROM THE ACFT, STRIKING THE RT SIDE OF FUSELAGE AND PUNCTURING SEVERAL AREAS OF EXTERIOR SKIN CAUSING DAMAGE TO SEVERAL FUSELAGE FRAMES AND STRINGERS IN FUSELAGE SECTIOON 46 WITH DAMAGE BEING CONTAINED WITHIN THE APPROX AREAS OF B.S.1640 TO 1660 BETWEEN STRINGERS R19 AND R28. CAUSE OF INCIDENT IS UNKNOWN AND IS CURRENTLY UNDER INVESTIGATION. ACFT LANDED SAFELY WITHOUT FURTHER INCIDENT.

Part: FLAP — BROKEN (ZONE 600) · airframe 47,281 hrs · 7,154 cycles

DURING APPROACH, CREW SELECTED 25 DEGREE FLAPS AND LOUD THUMP FELT AND HEARD. ACFT ROLLED SLIGHTLY, CREW CORRECTED AND LANDING WAS UNEVENTFULL. ON POST-FLT WALKAROUND, FOUND LARGE SECTION OF RIGHT WING T/E, INBD FOREFLAP, OTBD END MISSSING (APPROX 12 FT.)SEPARATION ALSO CAUSED DAMAGE TO SEVERAL UPPER T/E WING PANELS AND FUSELAGE DAMAGE TO FRAMES, STRINGERS AND SKIN AT APPROX. BS 1600 TO 1640 , STR 18R TO 30R. TIME LIMITED REPAIR ACCOMPLISHED BY MFG IAW FRR-001 THROUGH FRR-011 TO FUSELAGE SKIN, FRAMES, & STRINGERS, BS 1640/1660, STR 19R TO STR 28R. EO 4453A377, 4457A256 ISSUED.

Part: SKIN — DELAMINATED (NACELLE) · airframe 43,275 hrs · 6,484 cycles

DURING MX WALKAROUND, THE NR4 LT FAN COWL INNER AND OUTER SKINS WERE FOUND WITH DELAMINATION. EO: 4471A055 - PART 1 - TIME LIMITED REPAIR THE PART 1 TIME LIMITED REPAIR INSTALLS THROUGH BOLTS TO RESTORE THE CAPABILITY OF THE DISBONDED AREA AND IS FAA APPROVED IAW THE FAA FORM 8110-3 DATED 10MAY2010. THE PART 2 INSP IAW THIS EO ENSURES THE CONTINUED AIRWORTHINESS OF THE PART 1 TIME LIMITED REPAIR. THE PART 3 PERMANENT REPAIR RESTORES THE SUBJECT COWL TO THE ORIGINAL DESIGN CONFIGURATION.

Part: TIRE — SEPARATED (ZONE 700) · airframe 32,488 hrs · 5,026 cycles

TIRE TREAD SEPARATED FROM NR 8 POSITION ON T/O FROM SCL, DISCOVERED AFTER LANDING AT MIA. A/C INSPECTED, FOUND 5 LOWER AFT BODY PANELS WITH DENT DAMAGE. REPAIRED PANELS PER ATLAS EO 4453A335. REPLACED TIRES NR 7 AND NR 8 POSITION PER AMM 32.45.01.

Part: AILERON — DAMAGED (RT WING) · airframe 43,275 hrs · 6,484 cycles

THE PURPOSE OF THIS EO IS TO RECORD A MAJOR REPAIR. DURING C CHECK INSPECTION BEING PERFORMED AT HKG; DAMAGE WAS FOUND TO THE RIGHT I/B AILERON, O/B AFT CORNER DELAMINATION / DAMAGE. PERMANENT REPAIR PERFORMED IN ACCORDANCE WITH THE 747-400 SRM 51-70-07 FIGURE 9.

Part: WEB — DAMAGED (RT WLG WW) · airframe 43,275 hrs · 6,484 cycles

THE PURPOSE OF THIS EO IS TO RECORD A MAJOR REPAIR. DURING C CHECK INSPECTION BEING PERFORMED AT HKG; DAMAGE WAS FOUND TO THE RIGHT WLG WHEEL WELL BS 1251 RBL 95, FWD CUTOUT WEB DENT / DAMAGE. PERMANENT REPAIR PERFORMED IN ACCORDANCE WITH THE 747-400 SRM 53-00-01 FIGURE 201, REPAIR 6.

Part: SEAT TRACK — CRACKED (FUSELAGE) · airframe 43,275 hrs · 6,484 cycles

THE PURPOSE OF THIS EO IS TO RECORD A MAJOR REPAIR. DURING C CHECK INSPECTION BEING PERFORMED AT HKG; DAMAGE WAS FOUND TO THE MAIN DECK BS 1800 LBL 11.0 SEAT TRACK CRACK (REFERENCE FIGURE 1). PERMANENT REPAIR PERFORMED IN ACCORDANCE WITH THE 747-400 SRM 53-00-52 FIGURE 201, REPAIR 12.

Part: SEAT TRACK — CRACKED (FUSELAGE) · airframe 43,275 hrs · 6,484 cycles

THE PURPOSE OF THIS EO IS TO RECORD A MAJOR REPAIR. DURING C CHECK INSPECTION BEING PERFORMED AT HKG; DAMAGE WAS FOUND TO THE MAIN DECK BS 1850 TO BS 1860, LBL 33 SEAT TRACK CROWN CRACKED (REFERENCE FIGURE 1). PERMANENT REPAIR PERFORMED IN ACCORDANCE WITH THE 747-400 SRM 53-00-52 FIGURE 201, REPAIR 6.

Part: WEB — CRACKED (FUSELAGE) · airframe 43,275 hrs · 6,484 cycles

THE PURPOSE OF THIS EO IS TO RECORD A MAJOR REPAIR. DURING C CHECK INSPECTION BEING PERFORMED AT HKG; DAMAGE WAS FOUND TO THE MAIN DECK BS 1220 LBL 103, WL 184 WEB CONSISTING OF A CRACK MEASURING 2.5 IN. X 1.0 INCH (REFERENCE FIGURE 1). PERMANENT REPAIR PERFORMED IN ACCORDANCE WITH THE 747-400 SRM 51-70-13 FIGURE 201, REPAIR 1.

Part: SKIN — DENTED (FUSELAGE) · airframe 43,275 hrs · 6,484 cycles

EO 4453A074 RECORDED A DENT TO THE FUSELAGE SKIN AFT OF FWD CARGO DOOR BETWEEN S38 - S39 (24APR2006) WITH AN INITIAL HFEC INSP AND REPEAT INSPECTIONS AT 1,500 FC. DURING C-CHECK BEING PERFORMED ON 01 - 06 JUNE, 2009; INTERIM REPAIR WAS ACCOMPLISHED TO THE FUSELAGE SKIN DENT AFT OF FWD CARGO DOOR BETWEEN S38-S39 IAW THE SRM 53-00-01, FIG 201, REPAIR 1. SUPPLEMENTAL INSP ARE REQUIRED FOR THIS REPAIR IAW PART 2 OF THE SCHEDULING INFORMATION.

Part: DUCT — CRACKED (THRUST REVERSER) · airframe 43,275 hrs · 6,484 cycles

EO NR 4478A087: DURING ROUTINE INSP OF ACFT N498MC AT HKG "C" CHECK, THE NR 3 LT THRUST REVERSER PRECOOLER DUCT WAS FOUND CRACKED. THE CRACK IS APPROX 8 INCHES IN LENGTH. THE CMM 78-32-02 REPAIR 018 PROVIDES INSTRUCTIONS FOR THE REPAIR OF CRACKS IN WELD JOINTS AND IN THE PARENT MATERIAL OF THE PRECOOLER DUCT IF THE TOTAL LENGTH OF THE CRACK IS NOT MORE THAN 4.0 INCHES. SINCE THE CRACK IS GREATER THAN 4.0 INCHES AND EXCEEDS THE LIMITS THE CMM 78-32-02 REPAIR 018, AN 8110-3 FORM IS REQUIRED. DISPOSITION IS TO ACCOMPLISH THE WELD REPAIR AS MRAS CMM 78-32-02, REPAIR 018 AND THEN REPLACE THE THRUST REVERSER HALF AT THE NEXT C-CHECK. THIS REPAIR IS CLASSIFIED AS MAJOR. THIS EO IS APPROVED BY DER VIA FAA FORM 8110-3 ISSUED JUNE 2ND, 2009.

Part: FIRE WARNING — FALSE ACTIVATION (APU BAY) · airframe 42,930 hrs · 6,532 cycles

IN FLIGHT AT FL330 APPROX 2:20 WITH THE APU SWITCH OFF AND THE APU SHUTDOWN, AN INTERMITTENT FIRE APU WARNING OCCURRED BRIEFLY AND THEN CLEARED ITSELF. THE APU HANDLE WAS PULLED AS PRECAUTION PER THE AMM. CHECKED CMC AND FOUND CMC MESSAGE INTERMITTENT. CHECKED APU COMPARTMENT FOR EVIDENCE OF FIRE, NONE FOUND. RESEATED APU AFLOTS CARD; ACCOMPLISHED APU FIRE WARNING TEST PER MM 26-11-00 AND APU OPS CHECK PER MM 49-11-00. BOTH OPS CHECKED NORMAL.

Part: SKIN — PUNCTURED (LT WING TE FLAP) · airframe 42,835 hrs · 6,402 cycles

LT WING INBOARD MID FLAP LOWER SKIN HAS ONE 0.500 INCH PUNCTURE AT WBL 198.55. PERMANENT REPAIRED AS PER N747-400 SRM 57-53-01-2R-1 AND 51-70-10-2R-1. REF: ATLAS AIR EO 4457A184.

Part: SKIN — PUNCTURED (LT WING TE FLAP) · airframe 42,835 hrs · 6,402 cycles

LT WING INBOARD AFT FLAP LOWER SKIN HAS ONE 0.750 INCH PUNCTURE AT WBL 243.30 AND ONE 0.250 INCH PUNCTURE AT WBL 251.30. PERMANENT REPAIRED AS PER B747-400 SRM 57-53-01-2R-1 AND 51-70-10-2R-1, REF, ATLAS AIR EO 4457A184.

Part: ENGINE — SEIZED (NR 2) · airframe 41,937 hrs · 6,366 cycles

ENGINE 2 FAILED IN FLIGHT. AUTO SHUTDOWN, UNABLE TO AIR START ENG. FLIGHT LEVEL 380. NORMAL FLUID QUANTITIES AND ENGINE INDICATIONS AT THE TIME JUST BEFORE SHUTDOWN. MASTER CHIP DETECTOR FOUND CLEAN. FOUND ENGINE WOULD NOT TURN. REMOVED AND REPLACE ENGINE.

Part: FIRE WARNING — FALSE ACTIVATION (APU BAY) · airframe 38,847 hrs · 5,968 cycles

EICAS MESSAGE "APU" PULLED APU FIRE SWITCH IAW QRH. INSPECTED APU COMPARTMENT. NO DEFECTS NOTED. RESET FIRE HANDLE APU, OPS NORMAL PER MM 49-11-00. OK FOR CONTINUED SERVICE.

Part: PANEL — DELAMINATED (ZONE 500) · airframe 37,833 hrs · 5,705 cycles

LT WING UPPER SURFACE FLYING PANEL AT T/E CLOSEST TO FUSELAGE HAS DELAMINATION AT OUTBOARD EDGE APPROX 18 INCHES INBOARD FROM NR 6 SPOILER. DELAMINATION REPAIRED IAW ATLAS EO NR 4457A137 AND SRM 51-70-07.

Part: SKIN — DAMAGED (LT TE FLAP) · airframe 37,833 hrs · 5,705 cycles

LT OUTBOARD T/E FORE FLAP SURFACE DAMAGE ON BULLNOSE AREA AT OUT BOARD END. REPAIRED PER SRM 51-70-07 AND ATLAS EO 4457A135.

Part: RUB STRIP — WORN (RT WING) · airframe 37,833 hrs · 5,705 cycles

RT WING INBOARD AILERON UPPER SURFACE HAS RUB STRIP WORN THROUGH. REPAIRED RUB STRIP IAW ATLAS EO 4457A136 AND SRM 57-60-01 FIG 201 AND SRM 51-70-09 AND 51-70-10.

Part: TIRE — FAILED (MLG) · airframe 37,821 hrs · 5,704 cycles

ON TAKEOFF OUT OF PVG NR 9 AND 10 WHEELS RUPTURED. THIS CAUSED DAMAGE TO STRUT DOORS WHEEL WELL DOORS AND PNEUMATIC DUCTING. BOTH TIRES RIMS AND BRAKES DAMAGED. REPLACED BRAKES WHEELS AND DOOR STRUT. PERFORMED REPAIR TO DUCT. MAINTENANCE FERRY FLIGHT TO HKG FOR PERMANENT REPAIRS.

Part: ARM — DAMAGED (LT WING TE FLAP) · airframe 37,226 hrs · 5,616 cycles

LEFT WING OUTBOARD AFT FLAP OUTBOARD SWING ARM FORWARD FITTING FOUND DAMAGED. LEFT OUTBOARD AFT FLAP OUTBOARD SWING ARM FWD FITTING AND PIN REPLACED IAW AMM 27-51-06, FLAPS OPS CHECKED OKAY.

Part: CLAMP — DAMAGED (ZONE 600) · airframe 37,226 hrs · 5,616 cycles

NR 3 ENGINE FUEL SPRAY NOZZLE MANIFOLD SUPPORT LOOP "P" CLAMPS FOUND DAMAGED AT 1 AND 9 O'CLOCK POSITIONS. REPLACED DAMAGED P CLAMPS AND BOTH LEFT AND RIGHT FUEL SUPPLY MANIFOLDS.

Part: FITTING — CRACKED (NR 5 TE FLAP) · airframe 37,226 hrs · 5,616 cycles

RIGHT WING NR 5 CANOE FAIRING DRIVE ROD MID FLAP AFT FITTING CRACKED. FITTING REPLACED PER AMM 20-51-01 AND OPS CHECKED OK.

Part: FAN — FAILED (COCKPIT) · airframe 35,657 hrs · 5,359 cycles

PRIOR TO DISPATCH BURNING SMELL IN FLIGHT DECK AND COOLING FAN AREA. ITEM TRANSFERRED TO DMI M07-066 PER 21-58-4 (E/E COOLING EXHAUST FAN FAIL MESSAGE NR 21410 DISPLAYED).

Part: SKIN — DAMAGED (CARGO DOOR) · airframe 32,341 hrs · 4,838 cycles

ON WALK AROUND FOUND LOWER FWD CARGO DOOR DAMAGED AT THE AFT BOTTOM CORNER AROUND 11 INCH LENGTH ROUND THE AFT CORNER WITH 1.25 OPEN AREA. EDDY CURRENT AND NDT INSP C/W BEFORE AND AFTER INSPECTION ON THE SKIN AND STRUCTURE OF FWD CARGO DOOR AFT BOTTOM CORNER. NO DAMAGE NOTED. REF SRM 52-30-01 AND EDDY CURRENT INSP ACCOMPLISHED IAW 51-00-00. XEO 52-11/13/06 C/W. TRANS TO DMI N06-130

Part: PDU — BURNED OUT (COCKPIT) · airframe 32,337 hrs · 4,837 cycles

MAIN DECK PDU 18L INOP. PDU DEVELOPED SMOKE. FOUND ELECTRIC MOTOR BURNED. ITEM TRANSFERRED TO DMI M01-117 MEL 25-53-1 CAT D PDU REMOVED AREA INSPECTED. NO FURTHER DAMAGE NOTED.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 31,437 hrs · 4,700 cycles

MAIN DECK ZONE-A LEFT CEILING EMERGENCY LIGHT FOUND INOP. TRANSFERRED TO DEFERRED ITEM M06-087.

Part: GENERATOR — DISINTEGRATED (APU) · airframe 31,101 hrs · 4,645 cycles

NR 1 APU GENERATOR BEARING MSG DURING T/S CHECK, BURNING SMELL INSIDE CABIN SUSPECT APU FIRE. FLT CREW FOLLOW QRH AND FIRE HANDLE PULLED AND FIRE BOTTLE DISCHARGED. APU COMPARTMENT CHECKED AND FOUND HEATING DAMAGE. NR 1 GEN DISINTEGRATED CAUSING DEBRIS IMPACT DAMAGE.

Part: SKIN — CRACKED (LT ELEVATOR) · airframe 30,445 hrs · 4,541 cycles

DURING WALKAROUND, FOUND DAMAGE ON LEFT INBOARD TRAILING EDGE ELEVATOR AS PER XEO NR 55-052106. TEMP REPAIR ACCOMPLISHED. REPEAT INSPECTION SCHEDULED EVERY FLIGHT. PERMANENT REPAIR TO BE ACCOMPLISHED AFTER 10 FLIGHT CYCLES. TRANSFERRED TO DMI PAGE 71072, DMI NR N06-062.

Part: TIRE — FAILED (ZONE 700) · airframe 29,578 hrs · 4,736 cycles

NR 4 MAIN WHEEL BLOWN OUT. REPLACED NR 3 AND NR 4 WHEEL ASSY IAW MM 32-42-01. PERFORMED CHAPTER 5-51-25 AND 5-51-20 INSPECTION. ALSO PERFORMED 5-51-34 AND DEACTIVATED NR 4 BRAKE AS A PRECAUTION.

Part: ENGINE — VIBRATION (NR 3)

FLT GT 9991 - ENGINE NR 2 VIBRATION OCCURRED DURING CLIMB-OUT AND INTERMITTENTLY DURING FLIGHT. AFTER 4 HOURS FLIGHT TIME THE LEVEL OCCASIONALLY EXCEEDED 5.0, NR 3 EGT AVERAGED ABOUT 18 DEG HIGHER THAN THE OTHER THREE. REMOVED AND REPLACED NR 3 ENGINE IAW ATLAS AIR MAINTENANCE CARD A717107 GTI REF MM 72-00-00. REF LOG PAGE 546127. (M)

Part: TRANSMITTER — FAILED (OIL PRESSURE)

NR 3 ENGINE OIL PRESSURE DROPPED TO RED LINE 30 MINUTES FROM DEPARTURE. ENGINE SHUTDOWN IAW CHECK LIST. REMOVED AND REPLACED THE OIL PRESSURE TRANSMITTER IAW AMM 79-32-01 AND REPLACED THE OIL PRESSURE SWITCH IAW AMM 79-33-01.

Part: ANTI-ICE VALVE — CONTAMINATED (COCKPIT)

GT9012 TLV/CAI: AUTO NACELLE ANTI-ICE. (ATB) APPROX 8,000 CLEAR, TEMP +27C, AUTO NACELLE ANTI-ICE COMMANDED ANTI-ICE ON. ICING WING ALSO DISPLAYED. WHEN NAC ANTI-ICE VALVE IN OFF, NAI VALVE 1,2,3 AND 4 CAME ON. ALL FOUR VALVES WERE STUCK OPEN BY CHECKLIST. CHECKED BOTH ICE DETECTORS, FOUND BOTH WITH EXCESSIVE AMOUNT OF ADHESIVE ON PROBES. CLEANED THOROUGHLY. PERFORMED ICE DETECTION SYSTEM, GROUND TEST IAW TASK 30-81-00/715-001 AND MM 30-81-00/PPG501-503, AND PERFORMED ICE DETECTION SYSTEM OPERATIONAL TEST IAW TASK 30-81-00/715-050 AND MM 30-81-00, PP503/506. ACCOMPLISHED CHECKS OK. RAN ENGINE AND CHECKED MANUAL. OPERATION OF ENGINE AND WING ANTI-ICE VALVES. OPS NORMAL. NOTE: NO FUEL DUMP.

Part: SKIN — DENTED

DENT FOUND IN THE FUSELAGE SKIN RT SIDE AT STATION 2596. ACCOMPLISHED DENT REPAIR ON FUSELAGE SKIN RT SIDE STATION 2596 STRINGER 42 AREA IAW SRM 53-00-01 FIG 215 DETAIL I. (M)

Part: ENGINE — SURGES (NR 4)

CI 351/8 ATL/ANC ATB DUE TO NR 4 ENGINE STALL: AT SPEED V2 AFTER TAKEOFF, ENGINE NR 4 BEGAN SURGING FOLLOWED BY STALLING AND AIRFRAME SHUDDER. ENGINE NR 4 THRUST LEVER WAS RETARDED TO STABILIZE THE ENGINE. FUEL DUMPED TO 302 KG AND RETURNED FOR LANDING 27R ATC. NO ENGINE EXCEEDANCE NOTED. REMOVED AND REPLACED NR 4 ENGINE IAW WO A717101GTI.

Part: SMOKE — DETECTED (RT MLG WW)

ANC/BNA - ONCE THE AIRCRAFT LANDED, GROUND CREW NOTICED WHITE SMOKE COMING FROM THE RIGHT WING GEAR AREA. A FIRE EXTINGUISHER WAS USED TO PUT OUT WHAT IT WAS THOUGHT TO BE A FIRE BY THE GROUND CREW. VISUALLY INSPECTED THE RIGHT WING GEAR AREA FOR EVIDENCE OF FIRE, NIL FOUND. INSPECTED NR 13 MOUNTING WHEEL AND BRAKE ASSEMBLY IAW MM 32-45-01 AND WASHED THE GEAR DOWN WITH WATER IN ORDER TO REMOVED THE FIRE EXTINGUISHING AGENT RESIDUE. NO DEFECTS NOTED. REMOVED AND REPLACED NR 13 WHEEL AND BRAKE ASSEMBLY AS PRECAUTIONARY. (M)

Part: ACTUATOR — FAILED (TRANSFER VALVE)

DIVERSION TO ANC, ENROUTE CREW REPORTED EICAS MESSAGE FUEL IMBALANCE 1-4. CHECKLIST COMPLETED. NR 4 CONTINUED TO DECREASE, NR 3 REMAINED CONSTANT QUANTITY. SYSTEM CONTROL ADVISED AND AIRCRAFT DIVERTED TO ANC DUE TO FUEL LEAK FROM NR 4 MAIN TANK. MAINTENANCE ADVISED FLIGHT CREW TO SHUT DOWN NR 4 ENGINE. UPON ARRIVAL THE CAPTAIN ADVISED THAT HE WAS UNABLE TO MONITOR FUEL USE AND HAD TO SHUT DOWN NR 4 ENGINE. NO FUEL DUMPED. FOUND NR 4 TRANSFER VALVE PARTIALLY OPEN. REMOVED AND REPLACED TRANSFER VALVE ACTUATOR IAW MM. CMC GROUND OPS CHECKED OK. VISUALLY VERIFIED VALVE OPERATION OK.

Part: WIRE — BURNED (WINDOW HEAT)

CAPTAINS WINDOW HEAT TURNED OFF IN FIGHT DUE TO SMOKING WIRE. STATUS MESSAGE 'WINDOW HEAT 1L.' LEFT L1 WINDOW CONTROL SENSOR TERMINAL FITTING TIGHTENED AND CLEANED. FUNCTION, OPS AND CMC TESTS PASSED. NO FAULT FOUND PER MM 30-41-00. (M)

Part: HEATER — SMOKE (WINDSHIELD)

SMOKE IN COCKPIT, 30 MINUTES AFTER TAKEOFF, ELECTRICAL LEAD ON LOWER LEFT SIDE OF CAPTAINS WINDSHIELD STARTED TO SMOKE. WINDOW HEAT LEFT WAS TURNED OFF. SMOKE STOPPED AND REMAINED OFF FOR THE REST OF THE FLIGHT. FOUND L1 WINDOW HEAT ELECTRICAL LEAD AND TERMINAL CONTACT POOR. TERMINAL CLEANED AND INSTALLED PER MM 56-11-01. WINDOW HEAT WIRE CHECK PERFORMED PER WD 30-41-11. ALL SATISFACTORY. (M)

Part: SLIDE — FAILED (UPPER DECK)

DURING C-CHECK IN FRA, THE UPPER DECK SLIDE WOULD NOT DEPLOY DURING TEST. FOUND 2 RELEASE PINS ON THE PACK BOARD LOWER HORIZONTAL BAR NOT PULLED. THE RELEASE PINS WERE ROTATED AND CAUGHT ON THE EDGE OF THE RELEASE PIN CAUSING THEM TO GET CAUGHT IN THE OPENING OF THE HOLE. REMOVED SLIDE AND INSTALLED NEW SLIDE IAW MM. (M)

Part: RIVET — SHEARED (FUSELAGE)

DURING INSPECTION OF SATCOM RACK E-42 PER ATLAS EO 4453A003, TWO RIVETS WERE FOUND SHEARED ON VERTICAL SUPPORT BRACE AT STATION 1660, FRAME ATTACHMENT END IN THE VICINITY OF STRINGER 0. RIVETS REPLACED PER SRM 51-70-11. (M)