N512MC

Part: SKIN — CORRODED (BS 1241) · airframe 115,322 hrs · 21,440 cycles

BS 1241 LBL 11- RBL 11 CTR SECTION UPPER SKIN CORROSION, LEVEL 1. BLENDED OUT IAW SRM 51-10-01 AND BOEING MESSAGE NUMBER 1-598402422-7.

Part: SPAR — CORRODED (RT WING) · airframe 115,322 hrs · 21,440 cycles

RIGHT WING STATION 1337 FRONT SPAR TO REAR SPAR HAS CORROSION EVIDENT. REMOVED CORROSION IAW SRM 51-10-01.

Part: FAIRING — DAMAGED (THRUST REVERSER) · airframe 115,322 hrs · 21,440 cycles

NR 3 ENGINE LT T/R AFT UPPER FAIRING FOUND TORN AND MATERIAL MISSING. REPAIRED PER EO4778A109.

Part: SKIN — DELAMINATED (NR 2 SPOILER) · airframe 115,322 hrs · 21,440 cycles

NR 2 SPOILER OUTBOARD EDGE DELAMINATED. REPAIR CARRIED OUT PER SRM 51-40-24.

Part: SEAT TRACK — CORRODED (ZONE 200) · corrosion level 2 · airframe 115,322 hrs · 21,440 cycles

MAIN DECK BS 459 LBL 64 SEAT TRACK CORROSION, LEVEL 2. REPAIRED SEAT TRACK IAW SRM 53-10-05 FIG 1A.

Part: FRAME — CRACKED (BS 1760) · airframe 115,322 hrs · 21,440 cycles

FOUND MAIN DECK STA 1760 FRAME CRACKED AT STR 13R - 14R. REPAIRED PER BOEING MESSAGE 1-542767421-2.

Part: SKIN — CORRODED (BS 1241) · airframe 115,322 hrs · 21,440 cycles

BS 1241 LBL 55- LBL 76 CTR SECTION UPPER SKIN CORROSION, LEVEL 1. BLENDED OUT IAW SRM 51-10-01 AND BOEING MESSAGE NUMBER 1-598402422-7.

Part: SKIN — DELAMINATED (NR 1 SPOILER) · airframe 115,322 hrs · 21,440 cycles

NR 1 SPOILER INBOARD EDGE DELAMINATED. REPAIR CARRIED OUT PER SRM 51-40-24.

Part: SPAR — CORRODED (RT WING) · airframe 115,322 hrs · 21,440 cycles

RIGHT WING AT WS 917- WS 1141 FRONT SPAR TO REAR SPAR HAS CORROSION EVIDENT. CORROSION REMOVED PER SRM 51-10-01.

Part: SKIN — DELAMINATED (NR 4 SPOILER) · airframe 115,322 hrs · 21,440 cycles

NR 4 SPOILER OUTBOARD CORNER DELAMINATED. REPAIR CARRIED OUT PER SRM 51-40-24.

Part: SKIN — CORRODED (BS 1241) · airframe 115,322 hrs · 21,440 cycles

BS 1241 LBL 11- LBL 33 CTR SECTION UPPER SKIN CORROSION, LEVEL 1. BLENDED OUT IAW SRM 51-10-01 AND BOEING MESSAGE NUMBER 1-598402422-7.

Part: SKIN — CORRODED (ZONE 500) · airframe 115,322 hrs · 21,440 cycles

LEFT WING UPPER SURFACE WS 807 TO STR 516 SURFACE CORROSION EVIDENT. CORROSION REMOVED AND REPROTECTED IAW SRM 51-10-01 AND 51-10-02.

Part: BEARING — CORRODED (RETRACT CYLINDER) · airframe 115,322 hrs · 21,440 cycles

RIGHT BODY GEAR RETRACT ACTUATOR LOWER END BEARING CORRODED. REMOVED CORROSION AS PER TEC - XMN-07-01832 PROPOSAL REF OHM 32-33-11.

Part: SKIN — CORRODED (ZONE 600) · airframe 115,322 hrs · 21,440 cycles

RIGHT WING SURFACE CORROSION EVIDENT AROUND FASTENER HEAD FROM WS 528 TO WS 724.5 BETWEEN MID SPAR AND REAR SPAR. CORROSION REMOVED AND REPROTECTED IAW SRM 51-10-01 AND 51-10-02.

Part: SKIN — CORRODED (RT WING) · airframe 115,322 hrs · 21,440 cycles

RIGHT WING SURFACE CORROSION EVIDENT AROUND FASTENER HEAD FROM SIDE OF BODY TO WS 528 BETWEEN MID SPAR AND REAR SPAR. CORROSION REMOVED AND REPROTECTED IAW SRM 51-10-01 AND 51-10-02.

Part: SKIN — CORRODED (ZONE 600) · airframe 115,322 hrs · 21,440 cycles

RIGHT WING SURFACE CORROSION EVIDENT AROUND FASTENER HEAD FROM SIDE OF BODY TO WS 528 BETWEEN MID SPAR AND FRONT SPAR. CORROSION REMOVED AND REPROTECTED IAW SRM 51-10-01 AND 51-10-02.

Part: FLOORBEAM — CORRODED (BS 1720) · corrosion level 2 · airframe 115,322 hrs · 21,440 cycles

MAIN DECK BS 1720 LBL 76- LBL 98 FLOORBEAM UPPER CHORD HAS LEVEL 2 CORROSION. REPAIRED PER SRM 53-10-07 FIG 2. RAM FORM AND CPCP SUBMITTED TO ENGINEERING.

Part: SKIN — CORRODED (ZONE 600) · airframe 115,322 hrs · 21,440 cycles

RIGHT WING SURFACE CORROSION EVIDENT AROUND FASTENER HEAD FROM WS 528 TO WS 724.5 BETWEEN MID SPAR AND FRONT SPAR. CORROSION REMOVED AND REPROTECTED IAW SRM 51-10-01 AND 51-10-02.

Part: SKIN — CORRODED (ZONE 600) · airframe 115,322 hrs · 21,440 cycles

RIGHT WING SURFACE CORROSION EVIDENT AROUND FASTENER HEAD FROM WS 724.5 TO WS 917 BETWEEN MID SPAR AND REAR SPAR. CORROSION REMOVED AND REPROTECTED IAW SRM 51-10-01 AND 51-10-02.

Part: SKIN — CORRODED (ZONE 600) · airframe 115,322 hrs · 21,440 cycles

RIGHT WING SURFACE CORROSION EVIDENT AROUND FASTENER HEAD FROM WS 724.5 TO WS 917 BETWEEN MID SPAR AND FRONT SPAR. CORROSION REMOVED AND REPROTECTED IAW SRM 51-10-01 AND 51-10-02.

Part: SKIN — CORRODED (ZONE 500) · airframe 115,322 hrs · 21,440 cycles

LEFT WING UPPER SURFACE WS 353 TO WS 586 REAR SPAR HAS MINOR SURFACE CORROSION EVIDENT. CORROSION REMOVED AND REPROTECTED IAW SRM 51-10-01 AND 51-10-02.

Part: SKIN — CORRODED (ZONE 600) · airframe 115,322 hrs · 21,440 cycles

RIGHT WING SURFACE CORROSION EVIDENT AROUND FASTENER HEAD FROM SIDE OF BODY TO WS 528 BETWEEN MID SPAR AND FRONT SPAR. CORROSION REMOVED AND REPROTECTED IAW SRM 51-10-01 AND 51-10-02.

Part: SPAR — CORRODED (LT WING) · airframe 115,322 hrs · 21,440 cycles

LEFT WING UPPER SURFACE MID SPAR WS 1112, WS 1280, WS 1330 AND WS 1392 HAS MINOR SURFACE CORROSION EVIDENT. CORROSION REMOVED AND REPROTECTED IAW SRM 51-10-01 AND 51-10-02.

Part: SKIN — CORRODED (RT WING) · airframe 115,322 hrs · 26,440 cycles

SURFACE CORROSION EVIDENT AROUND HEAD FROM WS 724.50 TO WS 917.00 BETWEEN REAR SPAR AND MID SPAR. SURF, CORROSION REMOVED AND REPROTECTED IAW SRM 51-10-01 AND 51-10-02.

Part: SPAR — CORRODED (ZONE 500) · airframe 115,322 hrs · 26,440 cycles

LHW UPPER SURFACE WS 353 TO WS 586 SPAR SURF CORROSION EVIDENT. CORROSION REMOVED AND REPROTECTED IAW SRM 51-10-01 AND 51-10-02.

Part: SKIN — CORRODED (LT WING) · airframe 115,322 hrs · 26,440 cycles

LHW UPPER SURFACE MID SPAR WS 1112 WS 1280 WS 1330 WS 1392 CORROSION EVIDENT. SURF CORROSION REMOVED AND REPROTECTED IAW SRM 51-10-01 AND 51-10-02.

Part: SEAT TRACK — CORRODED (BS 1980) · airframe 115,322 hrs · 26,440 cycles

BS 1980 RBL 90 SEAT TRACK FOUND CORROSION. BLEND OUT CORROSION IAW SRM 51-10-01 AND REPROTECTED IAW 51-10-02.

Part: SKIN — CORRODED (LT WING) · airframe 115,322 hrs · 26,440 cycles

LHW UPPER SURFACE WS 807 STR S16 CORROSION EVIDENT. SURF CORROSION REMOVED AND REPROTECTED IAW SRM 51-10-01 AND 51-10-02.

Part: SKIN — CORRODED (RT WING) · airframe 115,322 hrs · 26,440 cycles

RIGHT WING SURFACE CORROSION EVIDENT AROUND FASTENER HEAD. CORROSION REMOVED AND REPROTECTED IAW SRM 51-10-01 AND 51-10-02.

Part: SEAT TRACK — CORRODED (ZONE 200) · airframe 115,322 hrs · 26,440 cycles

BS 1960 LBL 99 SEAT TRACK FOUND CORROSION. BLEND OUT CORROSION IAW SRM 51-10-01 AND REPROTECTED IAW 51-10-02.

Part: SKIN — CORRODED (WING) · airframe 115,322 hrs · 26,440 cycles

SURF CORROSION EVIDENT AROUND HEAD FROM WS 528 TO WS 724.5 BETWEEN REAR SPAR AND MID SPAR. SURF CORROSION REMOVED AND REPROTECTED IAW SRM 51-10-01 AND 51-10-02.

Part: SEAT TRACK — CORRODED (BS 520) · corrosion level 2 · airframe 115,322 hrs · 26,440 cycles

U/D BS 520 RBL 46 SEAT TRACK CORROSION. REPAIR SEAT TRACK IAW SRM 53-10-05 FIG 1A.

Part: SKIN — CORRODED (ZONE 600) · airframe 115,322 hrs · 21,438 cycles

SURF CORROSION EVIDENT AROUND FASTENER HEAD FROM WS 528 TO SIDE OF FUS BODY BETWEEN FRONT SPAR AND MID SPAR. SURF CORROSION REMOVED AND REPROTECTED IAW SRM 51-10-01 AND 51-10-02.

Part: SPAR — CORRODED (ZONE 500) · airframe 115,322 hrs · 21,438 cycles

WS 317 - WS 1141, FRONT SPAR TO REAR SPAR CORROSION EVIDENCED. SURFACE CORROSION REMOVED AND REPROTECTED IAW SRM 51-10-01 AND 51-10-02.

Part: SKIN — CORRODED (ZONE 600) · airframe 115,322 hrs · 21,438 cycles

SURFACE CORROSION EVIDENT AROUND FASTENER HEAD FROM WS 724.50 TO WS 917.00 BETWEEN FRONT SPAR AND MID SPAR. SURF CORROSION REMOVED AND REPROTECTED IAW SRM 51-10-01 AND 51-10-02.

Part: SKIN — CORRODED (ZONE 600) · airframe 115,322 hrs · 21,438 cycles

RHW UPP SKIN PNL: WS1141-WS1337, FRONT SPAR TO REAR SPAR SEVERAL AREAS OF CORROSION EVIDENCED. SURF CORROSION REMOVED AND REPROTECTED IAW SRM 51-10-01 AND SOPM 20-43-03.

Part: SKIN — CORRODED (ZONE 600) · airframe 115,322 hrs · 21,438 cycles

LHW SPOILER: NR 1 SPOILER I/B EDGE DELAMINATION EVIDENCE. NR 1 SPOILER PNL REPLACED IAW AMM 27-61-02.

Part: SKIN — CORRODED (ZONE 600) · airframe 115,322 hrs · 21,438 cycles

SURF CORROSION EVIDENT AROUND FASTENER HEAD FROM WS 528 TO WS 724.5 BETWEEN FRONT SPAR AND MID SPAR. SURF CORROSION REMOVED AND REPROTECTED IAW SRM 51-10-01 AND 51-10-02.

Part: SKIN — CORRODED (LT WING) · airframe 115,322 hrs · 21,438 cycles

SURF CORROSION EVIDENT AROUND FASTENER HEAD FROM SIDE OF BODY TO WS 528 BETWEEN MID SPAR AND REAR SPAR. SURF CORROSION REMOVED AND REPROTECTED IAW SRM 51-10-01 AND 51-10-02.

Part: SKIN — DELAMINATED (NR 2 SPOILER) · airframe 115,322 hrs · 21,438 cycles

NR 2 SPOILER I/B EDGE DELAMINATION EVIDENCE. REPAIR CARRIED OUT IAW SRM 51-40-24.

Part: SKIN — CORRODED (ZONE 500) · airframe 115,322 hrs · 21,438 cycles

LHW SPOILER: NR 4 SPOILER O/B CORNER DELAMINATION EVIDENCE. REPAIR CARRIED OUT IAW SRM 51-40-24.

Part: SKIN — DELAMINATED (TE FLAP) · airframe 114,083 hrs · 21,181 cycles

RT WING O/B MID FLAP UPPER SURFACE LEADING EDGE AT WING STA 1000.00 TO WING STA 995.00 IS DELAMINATED 2.5IN WIDE 4.5IN LONG. REPAIRED RT WING O/B MID FLAP UPPER SURFACE DELAMINATION IAW SRM 51-10-01 EO4757A353.

Part: PANEL — DELAMINATED (RT WING) · airframe 112,234 hrs · 20,763 cycles

RIGHT WING, INBOARD LEADING EDGE WING PANEL AT WING STATION 248.81 TO 268.81, INNER SKIN HAS AREA OF COMPOSITE DELAMINATION 20.0 INCH LONG BY 22.0 INCH WIDE. ACCOMPLISHED INTERIM REPAIR OF AREA AS PER ATLAS XEO 57-081706. REQUIRES REPEAT INSPECTIONS AT EVERY A-CHECK UNTIL PART 3 IS ACCOMPLISHED, PERMANENT REPAIR AT NEXT C-CHECK.

Part: PANEL — CRACKED (RT WING) · airframe 112,234 hrs · 20,763 cycles

RIGHT WING FIXED TRAILING EDGE PANEL AT WBL 445.9 OUTBOARD AFT END OF PANEL HAS 1.0 INCH LONG CRACK AND LOWER AREA HAS AREA OF DETERIORATION. ACCOMPLISHED PREPREG 250 DEGREES PERMANENT REPAIR OF AREAS AS PER 747 SRM 51-40-09 AND 51-40-12.

Part: PANEL — FAILED (AUTOPILOT SYS) · airframe 112,073 hrs · 20,729 cycles

ATB, DUE TO A/P A&B WOULD NOT ENGAGE. OVERWEIGHT LANDING AT 287.8. REMOVED AND REPLACED P-10 PANEL PER AMM 22-11-06 ALL OPS OK. RAMP DOWN TEST OK PER AMM 22-10-00. ACCOMPLISHED OVERWEIGHT INSP AS PER AMM 5-51-39.

Part: VALVE — LEAKING (NR 3 ENGINE) · airframe 111,894 hrs · 20,692 cycles

WHILE CRUISING AT FL LEVEL 310, NR 3 ENG OVERHEAT LIGHT CAME ON. ACCOMPLISHED PROCEDURES AS PER FHB 3.35.5.6. OVERHEAT LIGHT EXTINGUISHES WHEN THROTTLE WAS RETARDED, ALSO WITH THE BLEED AIR VALVE SWITCH IN CLOSED POSITION VALVE LIGHT FAILED TO COME ON. THERE WAS PRESS DROP, UNTIL ENGINE WAS TOTALLY AT IDLE. THE LIGHT CAME ON, THROTTLE WAS ADVANCED AGAIN AND THE OVERHEAT LIGHT CAME ON WHEN EVER 761.N1 WAS REACHED. ALSO, THE OVERHEAT LIGHT CAME ON WHEN THE AIRCRAFT ENCOUNTERED ANY TURBULENCE. XRERRED TO DPG 83153 DMI M06-098 MEL 36-05 PER MEL 36-5-1. REMOVED AND REPLACED NR 3 ENG PYLON VLV IAW MM 36-11-06. REMOVED AND REPLACED NR 3 ENG OVERHEAT TEMP SWITCH IAW MM 36-22-01. DMI CLOSED.

Part: STRUCTURE — GROUND DAMAGE (BS 270-300) · airframe 111,498 hrs · 21,220 cycles

DURING GROUND HANDLING, AIRCRAFT WAS STRUCK ON THE RT SIDE OF THE FUSELAGE, FWD OF THE AOA SENSOR AND BEHIND THE LOWER PITOT PROBE. CAUSED A DENT 12 INCHES LONG, BY 5 INCHES WIDE. A FURTHER DENT WAS CAUSED IN THE RVSM AREA, JUST AFT OF THE LWR PITOT PROBE.

Part: SKIN — GROUND DAMAGE (FUSELAGE) · airframe 111,498 hrs · 20,710 cycles

BETWEEN STA 270 AND STA 300 ON RT SIDE, DAMAGE CAUSED TO THE SKIN BY CATERING TRUCK BOOT. THE DAMAGE IS AFT OF THE LWR PITOT PROBE TO FWD OF AOA SENSOR. AREA OF DAMAGE IS 12 INCHES BY 5 INCHES, AND A 3 INCHES BY 3 INCH DENT WITHIN THE RVSM AREA. THE SKIN WAS HFEC INSPECTED FOR CRACKS. NIL EVIDENT. A SKIN WAVINESS INSPECTION WAS CARRIED OUT AS PER SB747-53-2394 REV 1 WITH MEASUREMENTS PERFORMED AS PER AMM 51-10-00/601 XEO 53-043006 RAISED FOR DETAILED VISUAL AND HFEC.

Part: SKIN — DELAMINATED (LT WING TE FLAP) · airframe 111,084 hrs · 20,534 cycles

LT WING INBOARD T/E MID-FLAP HAS DELAMINATION BETWEEN FLAP TRACKS NR 3 AND NR 4. REPAIRED IAW OHM 57-52-35 BY REPLACEMENT OF MID-FLAP LEADING EDGE SECTION BETWEEN NR 3 AND NR 4 TRACKS.

Part: FRAME — MISDRILLED (BS 800) · airframe 111,084 hrs · 20,534 cycles

BS 800 RT FRAME FOUND WITH A MISS DRILLED HOLE ON THE FRAME INNER CHORD AT STRINGER 16R. REPAIRED ACCORDING EDF KLM-747-CC1-2006-031-R2 WITH 8100-9 APPROVAL. REFERENCE ATLAS EO 4753A630 FOR DOCUMENTATION.

Part: PANEL — ERODED (LT WING LE) · airframe 111,084 hrs · 20,534 cycles

LEFT WING LEADING EDGE PANEL VCF NR 6 LOWER SIDE OF PANEL IS EROSION DAMAGE, AND LOWER SIDE CHANNEL IS DAMAGED. REPAIRED VCF NR 6 IAW OHM 57-55-22 AND SRM 51-40-14 PARA 4N AND FIG 16.

Part: TEE FITTING — CORRODED (RT WING) · airframe 111,084 hrs · 20,534 cycles

RT WING TRAILING EDGE - LOWER T-CHORD HAS CORROSION AT REAR SPAR CAVITY WS 725. REPLACED LOWER T-CHORD IAW SRM 51-30-02.

Part: SKIN — ERODED (LT WING LE) · airframe 111,084 hrs · 20,534 cycles

LT WING LEADING EDGE VCF PANEL NR 10 UPPER SIDE HAS EROSION DAMAGE. REPAIRED PANEL NR 10 IAW OHM 57-55-22 AND SRM 51-40-14 PARA 4K AND FIG 16.

Part: SKIN — DENTED · airframe 111,084 hrs · 20,534 cycles

EXTERNAL FUSELAGE FOUND DENTS BETWEEN BS 1840 AND 1860 JUST BELOW STRINGER 34L. REPAIRED SKIN IAW SRM 53-30-03 FIG 1.

Part: FRAME — CRACKED (BS 1000) · airframe 111,084 hrs · 20,534 cycles

BS 1000 BULKHEAD LOWER CHORD HAS A CRACK BETWEEN STRINGERS 46R - 47R. REPAIRED BS 1000 BULKHEAD LOWER CHORD BY SPLICING A NEW LOWER CHORD SECTION BETWEEN STRINGERS 45L AND 45R PER EDF KLM-CC1-2006-034 R3 WITH 8100-9 APPROVAL. REPEAT INSPECTION REQUIREMENTS ARE TRACKED ON ATLAS EO 4753A685.

Part: STIFFENER — CRACKED (BS 2040) · airframe 111,084 hrs · 20,534 cycles

BULK CARGO COMPARTMENT FLOOR LONGITUDINAL STIFFENER AT BL 0 HAS A CRACK AT BS 2040. REPAIRED STIFFENER IAW SRM 53-10-07 FIG 20.

Part: SKIN — CRACKED (LT WING TE FLAP) · airframe 111,084 hrs · 20,534 cycles

LT WING OUTBOARD AFT-FLAP HAS SMALL CRACKING IN T/E UPPER AND LOWER SURFACES. REPAIRED IAW SRM 51-40-15 PARA 4N.

Part: STRUCTURE — CRACKED (RT WING TE FLAP) · airframe 111,084 hrs · 20,534 cycles

RT WING OUTBOARD T/E MID-FLAP HAS A CRACK IN COMPOSITE STRUCTURE APPROX 25 INCHES LONG. REPAIRED IAW SRM 51-40-12 PARA 4D AND FIG 11.

Part: SKIN — DELAMINATED (TE FLAP) · airframe 111,084 hrs · 20,534 cycles

LT WING OUTBOARD T/E FORE-FLAP HAS DELAMINATION BETWEEN NR 1 AND NR 2 TRACKS. REPAIRED IAW SRM 51-40-15 PARA 4N.

Part: SKIN — CORRODED (BS 1140) · corrosion level 2 · airframe 111,084 hrs · 20,534 cycles

FOUND CORROSION ON THE CENTER WING TANK UPPER SKIN UPPER SURFACE, AT BS 1140 LBL 120. REWORKED UPPER SKIN PANEL IAW SRM 51-10-01. FOUND MATERIAL LOSS WITHIN LIMITS PER SRM 57-10-01 FIG 1.

Part: STRUCTURE — CRACKED (DOOR SUPPORT) · airframe 111,084 hrs · 20,534 cycles

LT BODY GEAR WHEEL WELL - FOUND OUTBOARD STRUT DOOR SUPPORT STRUCTURE CRACKED AT SEVERAL SPOTS ON I/B AFT SIDE BS 1480. REPAIRED BY REPLACEMENT OF CHORD IAW SRM 51-30-02 FIG 3.

Part: STIFFENER — CORRODED (BS 1050) · corrosion level 2 · airframe 111,084 hrs · 20,534 cycles

CENTER WING TANK UPPER SURFACE STRINGER 27C BETWEEN LBL 96 AND LBL 127.5 HAS EXFOLIATION CORROSION. REPAIRED STRINGER SECTION IAW SRM 57-10-04 FIG 3 AND EDF KLM-747-CC1-2006-032-R4 WITH 8100-9 APPROVAL. FIRST STAGE APPROVAL IN DOCUMENTED ON EO 4757A252.

Part: SKIN — DELAMINATED (TE FLAP) · airframe 111,084 hrs · 20,534 cycles

RT WING INBOARD AFT T/E FLAP HAS DELAMINATION APPROX 15 INCHES. FLAP REPAIRED IAW SRM 51-40-14 REPAIR 4D.

Part: SHIM — BROKEN (LT MLG WW) · airframe 111,084 hrs · 20,534 cycles

LT LGW FOUND PART OF SHIM BROKEN OFF FROM OVERWING LONGERON ST BS 1241 LBL 27. ACCOMPLISHED RETORQUE OF EFFECTED FASTENERS IAW 51-30-04 PG 9. RETORQUE CHECK REQUIRED BY SRM 51-10-10 PG 3 TO BE TRACKED ON ATLAS EO XEO 53-031406.

Part: SKIN — DELAMINATED (RT TE FLAP) · airframe 111,084 hrs · 20,534 cycles

RT WING INBOARD T/E MIDFLAP HAS A LARGE SPOT OF DELAMINATION. REPAIRED IAW SRM 51-40-14 FIG 9.

Part: BOLT — CRACKED (MLG) · airframe 111,084 hrs · 20,534 cycles

LT BODY GEAR - TRUCK PIVOT BOLT FAILED MAGNETIC PARTICLE INSPECTION. REPLACED TRUCK PIVOT BOLT IAW MM 32-13-02.

Part: PANEL — CRACKED (RT WING) · airframe 111,084 hrs · 20,534 cycles

RT WING FIXED UPPER T/E PANEL HAS A SMALL CRACK. REPAIRED IAW SRM 51-40-12 REPAIR 4A AND 51-40-14 REPAIR 4L.

Part: RIB — CRACKED (WS 1516) · airframe 111,084 hrs · 20,534 cycles

RT WING DRY BAY - LOWER CHORD OF RIB AT WS 1516 IS CRACKED IN TWO PLACES. REPLACED LOWER CHORD OF RIB IAW SB 747-2221 FIG 5.

Part: INTERCOSTAL — CRACKED (BS 1265) · airframe 111,084 hrs · 20,534 cycles

DURING HFEC TEST OF BS 1265 FRAME TO RT FLOORBEAM INTERSECTION, FOUND A CRACK INDICATION IN ONE FASTENER HOLE. AFTER INVESTIGATION IT HAS BEEN FOUND THAT THE CRACK IS IN THE FLOORBEAM INTERCOSTAL UPPER CHORD. REPAIRED BY FREEZE PLUG INSTALLATION IAW SRM 51-10-08. REPAIR DOCUMENTED ON ATLAS EO 4753A693.

Part: SKIN — DELAMINATED (MLG DOOR) · airframe 111,084 hrs · 20,534 cycles

RT WING GEAR LOWER STRUT DOOR HAS DELAMINATION. DOOR REPAIRED IAW SRM 51-40-24 FIG 2.

Part: FRAME — CRACKED · airframe 111,084 hrs · 20,534 cycles

BS 800 LT FRAME, FOUND A CRACK INDICATION IN THE INNER CHORD INBOARD STRAP ABOVE STRINGER 17L. REPAIRED BY REPLACEMENT OF INNER STRAP, PER BOEING DRAWING 65B05002 AND SRM 51-30-02.

Part: PRESSURE PANEL — CRACKED (LT MLG WW) · airframe 111,084 hrs · 20,534 cycles

LT WLG WELL - FOUND A SMALL CRACK IN THE CANTED PRESSURE PANEL AT BS 1241. REPAIRED IAW SRM 53-10-07 FIG 6.

Part: RIB — CRACKED (LT WING TE) · airframe 111,084 hrs · 20,534 cycles

LT WING UPPER FIXED TRAILING EDGE PANEL OUTBOARD SUPPORT RIB HAS A CRACK IN THE WEB. REPAIRED IAW SRM 51-40-02 FIG 1.

Part: SKIN — DELAMINATED (TE FLAP) · airframe 111,084 hrs · 20,534 cycles

LT WING INBOARD T/E FORE-FLAP HAS DELAMINATION ON LOWER SIDE OF L/E BETWEEN NR 3 AND NR 4 TRACKS. REPAIRED IAW SRM 51-40-12 PARA 4C AND 51-40-14 PARA 4D.

Part: SKIN — CRACKED (BS 1480) · airframe 111,084 hrs · 20,534 cycles

LT BODY GEAR WHEEL WELL - WTB FAIRING SKIN HAS A CRACK AT BS 1480 WL 86. REPAIRED SKIN IAW SRM 51-40-02.

Part: FRAME — CRACKED (BS 800) · airframe 111,084 hrs · 20,534 cycles

BS 800 LT FRAME INNER CHORD FOUND WITH CRACK INDICATION BY HFEC INSPECTION 1 FASTENER HOLE ABOVE STRINGER 17L. REPAIRED INNER CHORD IAW SRM 53-10-04 FIG 114. REPAIR DOCUMENTED ON ATLAS EO 4753A630.

Part: PUMP — LEAKING (HYD SYSTEM)

NR 1 HYDRAULIC CONTENTS RAPIDLY DEPLETED DURING FLIGHT. APPROPRIATE DRILLS CARRIED OUT. REMOVED AND REPLACED NR 1 ENGINE EDP IAW MM 29-11-05. NO EVIDENCE OF LEAKS AFTERWARDS. SERVICED NR 1 HYDRAULIC SYSTEM TO FULL. INSPECTED PRESS AND CASE DRAIN FILTERS. SECURED ENGINE COWL AND SHUT ACCESS. (EA15200502556) (K)

Part: PUMP — LEAKING (NR 1 ENGINE)

NR 1 HYD CONTENTS RAPIDLY DEPLETED DURING FLIGHT. APPROPRIATE DRILLS CARRIED OUT. REMOVED AND REPLACED NR 1 ENGINE EDP IAW MM. NO EVIDENCE OF LEAKS AFTERWARDS. SERVICED NR 1 HYD SYSTEM TO FULL. INSPECT PRESS AND CASE DRAIN FILTERS. SECURED ENGINE COWL AND SHUT ACCESS. (K)

Part: SKIN — CRACKED (NR 2 PYLON)

DURING SCHEDULED MAINTENANCE INSPECTION, THE BULKHEAD UPPER ASSY FORWARD ANGLE FRAME OF THE NR 2 PYLON LT AND RT SIDE WERE FOUND CRACKED. FABRICATED AND INSTALLED REPAIR ANGLES ON THE FORWARD AND AFT FRAMES IN THE REPAIR AREA. INSTALLED THE REPAIR ANGLES BY PICKING-UP ALL EXISTING FASTENER LOCATIONS AFFECTED BY THE REPAIR PARTS WITH LOCK FASTENERS. CONDUCT REPEAT DETAILED VISUAL INSPECTION OF THE FORWARD FRAMES AT THE REPAIRS AND ADJACENT CHORD AREA EVERY C-CHECK OR 18 MONTHS WHICHEVER IS FIRST, FOR CRACK, LOOSE FASTENERS AND DAMAGE. EO TO BE ISSUED TO ACCOMPLISH INSPECTION AT 18 MONTH INTERVALS OR C-CHECK WHICH EVER IS FIRST.

Part: FAIRING — DELAMINATED (NR 4 PYLON)

D-CHECK, DURING SCHEDULED MAINTENANCE INSPECTION, DELAMINATION WAS FOUND ON NR 4 PYLON FAIRING ASSY. AT THE AFFECTED AREA, SKIN AND CORE WERE TRIMMED FROM BOTH IB AND OB SIDES WITH REPLACEMENT CORE, SKIN AND DOUBLERS BONDED IAW SRM 51-40-06. PERFORM DETAILED VISUAL INSPECTION INCLUDING COIN TAP OF THE FAIRINGS AT THE SUBJECT REPAIR AREAS, EVERY C-CHECK OR 18 MONTHS WHICHEVER COMES FIRST FOR DELAMINATION, CRACKING OR LOOSE FASTENERS. EO TO BE ISSUED TO ACCOMPLISH INSPECTION AT C-CHECK OR 18 MONTHS, WHICHEVER COMES FIRST.

Part: FRAME — CRACKED (NR 3 PYLON)

D-CHECK, DURING SCHEDULED MAINTENANCE INSPECTION THE NR 3 PYLON AFT ENGINE MOUNT BULKHEAD UPPER ASSY FRAMES CRACKED. STOPPED DRILLED THE CRACK ENDS IAW SRM 51-10-01. HFEC INSPECTED TO ENSURE CRACK CONTAINMENT. FABRICATED AND INSTALLED REPAIR ANGLES ON THE FORWARD AND AFT FRAMES IN THE REPAIR AREA. INSTALLED THE REPAIR ANGLES BY PICKING UP ALL EXISTINGS FASTENERS AFFECTED BY THE REPAIR PARTS WITH HI-LOK FASTENERS.

Part: FAIRING — DELAMINATED (NR 2 PYLON)

D-CHECK, DURING SCHEDULED MAINTENANCE INSPECTION, DELAMINATION WAS FOUND ON NR 2 PYLON FAIRING ASSY. AT THE AFFECTED AREA, SKIN AND CORE WERE TRIMMED FROM THE OB SKIN SIDE AND REPLACEMENT CORE AND SKIN WERE SPLICED BY BONDING IAW SRM 51-40-06. IT WAS FURTHER REINFORCED BY LOCAL DOUBLER WITH POTTED FASTENERS. PERFORM DETAIL VISUAL INSPECTION, INCLUDING COIN TAP OF THE FAIRING AT THE SUBJECT REPAIR AREAS, EVERY C-CHECK OR 18 MONTHS, WHICHEVER COMES FIRST, FOR DELAMINATION, CRACKING OR LOOSE FASTENERS. EO TO BE ISSUED TO ACCOMPLISH INSPECTION AT C-CHECK OR 18 MONTHS, WHICHEVER COMES FIRST.

Part: SPAR — CRACKED (NR 16 KRUG FLAP)

D-CHECK, DURING SCHEDULED MAINTENANCE INSPECTION, CRACKS WERE FOUND AT ENDS OF THE NR 16 KRUEGER FLAP FRONT SPAR. TRIMMED OUT CRACKED REGION OF SPAR ATTACHED FLANGES. NDT INSPECTED TRIMMED EDGES TO ENSURE CRACK AND DEFECT FREE CONDITION. INSTALLED REPAIR FILLERS AND REPAIR CHANNELS. REFINISHED SPARS TO DESIGN STANDARD. DETAIL VISUAL INSPECTION TO BE ACCOMPLISHED OF THE REPAIR AREA AT C-CHECK INTERVALS, NOT TO EXCEED 18 MONTHS, FOR SIGNS OF DEGRADATION INCLUDING CRACKS, CORROSION AND LOOSE FASTENERS. TO ISSUE EO TO ACCOMPLISH INSPECTION AT C-CHECK OR 18 MONTHS, WHICHEVER COMES FIRST.

Part: SPAR — CRACKED (KRUEGER FLAP)

D-CHECK, DURING SCHEDULED MAINTENANCE INSPECTION, CRACKS WERE FOUND AT ENDS OF THE NR 15 KRUEGER FLAP FRONT SPAR. TRIMMED OUT CRACKED REGION OF SPAR ATTACHED FLANGES. NDT INSPECTED TRIMMED EDGES TO ENSURE CRACK AND DEFECT FREE CONDITION. INSTALLED REPAIR FILLERS AND REPAIR CHANNELS. REFINISHED SPARS TO DESIGN STANDARD. DETAIL VISUALLY INSPECTION TO BE ACCOMPLISHED OF THE REPAIR AREA AT C-CHECK INTERVALS, NOT TO EXCEED 18 MONTHS, FOR SIGNS OF DEGRADATION INCLUDING CRACKS, CORROSION AND LOOSE FASTENERS. TO ISSUE EO TO ACCOMPLISH INSPECTION AT C-CHECK OR 18 MONTHS, WHICHEVER COMES FIRST.

Part: STRAP — CRACKED (NR 4 PYLON)

DURING SCHEDULED MAINTENANCE, FOUND CRACK NR 4 PYLON AT AFT MOUNT BULKHEAD FRAME STRAP. SUBJECT CRACK WAS LOCATED ALONG THE STRUT UPPER SKIN ASSY LOWER EDGE. CRACK AFT END WAS CONTAINED WITH A STOP HOLE IN THE STRAP. THE REPAIR AREA WAS NDT INSPECTED, INCLUDING HFEC INSPECTION OF ALL REPAIR HOLES. THE AREA WAS REINFORCED WITH TWO EXTERIOR 0.063 INCH THICK LAYERS OF TITANIUM DOUBLERS WITH PROFILES TO MATCH THE BULKHEAD STRAP PROFILE AND SPAN ACROSS THE SUBJECT CRACK. THE REPAIR AREA IS TO BE REPEAT DETAIL VISUAL INSPECTED EVERY 18 MONTHS OR C-CHECK INTERVAL,

Part: RIB — CRACKED (RT WING)

DURING SCHEDULED MAINTENANCE. FOUND CRACK AT RT VARIABLE CAMBER FLAP HINGE RIB ASSEMBLY. TRIMMED THE FLANGE TO REMOVE THE DAMAGE. HFEC THE AFFECTED AREA TO ENSURE DEFECT FREE CONDITION. THE REPAIR AND RESTORATION WAS ACCOMPLISHED TO RESTORE TO THE ORIGINAL STRUCTURE. DETAIL VISUAL INSPECT THE AFFECTED AREA AT C-CHECK INTERVALS NOT TO EXCEED 18 MONTH FOR SIGNS OF CORROSION, CRACKS AND DEGRATION OF SUBJECT REPAIR. EO TO ACCOMPLISH INSPECTION AT 18 MONTH INTERVALS.

Part: SPAR — CORRODED (RT WING)

FOUND DURING SCHEDULED MAINTENANCE, CORROSION ON FRONT SPAR WEB, FSS 979.27, LOWER CHORD, LEFT SIDE. BLENDED OUT CORROSION WITH 125 RT FINISH. HFEC INSPECTED OPEN FASTENER HOLES, TO ENSURE DEFECT FREE CONDITION. FLAP PEEN BLENDED SURFACES. FABRICATED AND INSTALLED A 0.071 INCH THICK 7075-T6 DOUBLERS AND A FITTED FILLER. REPLACED THE RIB POST AT WS 972. (M)

Part: FITTING — CORRODED (WING)

WHILE PERFORMING EO 4757A087, REAR SPAR UPPER CHORD AND SIDE BODY INSPECTION. CORROSION STILL EXIST ON THE UPPER REAR SPAR INTERNAL SPLICE FITTING AFTER INCORPORATING NR 5 HOLE DIA MAX OF 1.40 INCHES WITH SLEEVED BOLT REPAIR. LEVEL 1 MINOR. REAMED HOLE NR 5 TO FINAL SIZE OF 1.50 INCHES TO COMPLETELY REMOVED THE CORROSION. PERFORMED OPEN HOLE HFEC TO ENSURE HOLE IS DAMAGE FREE. INSTALLED SLEEVED BOLT REPAIR. (M)

Part: PYLON — CRACKED (NR 1)

DURING SCHEDULED MAINTENANCE, NR 1 PYLON CRACK DAMAGE WAS FOUND AT PRE-COOLER EXHAUST CUTOUT LOWER AFT CORNER AT STATION 248. THE NR 3 STIFFENER WAS REINFORCED WITH A NEW LOWER REPAIR ANGLE FROM FS 235-254. THE RIB INSTALLATION AT NACELLE STATION 248 WAS MODIFIED TO ACCOMMODATE THE NEW STEEL REPAIR ANGLE INSTALLATION ON THE NR 3 STIFFENER. NDT INSPECTION WAS ACCOMPLISHED AT EACH REAPIR AREA AND HFEC INSPECTION OF ALL TRIMMED EDGES AND ALL REPAIR FASTENER LOCATIONS TO ENSURE DEFECT FREE CONDITION. (M)

Part: PYLON — CRACKED (NR 2)

DURING SCHEDULED MAINTENANCE, NR 2 PYLON, CRACK DAMAGE WAS FOUND AT PRE-COOLER EXHAUST CUTOUT LOWER AFT CORNER AT FS 248. THE NR 3 STIFFENER WAS REINFORCED WITH A NEW LOWER REPAIR ANGLE FROM FS 235-FS 254. THE RIB INSTALLATION AT NACELLE STATION 248 WAS MODIFIED TO ACCOMMODATE THE NEW STEEL REPAIR ANGLE INSTALLATION ON THE NR 3 STIFFENER. NDT INSPECTION WAS ACCOMPLISHED AT EACH REPAIR AREA AND HFEC INSPECTION OF ALL TRIMMED EDGES AND ALL REPAIR FASTENER LOCATIONS TO ENSURE DEFECT FREE CONDITION. (M)

Part: PYLON — CRACKED (NR 4)

DURING SCHEDULED MAINTENANCE, NR 4 PYLON, CRACK DAMAGE WAS FOUND AT PRE-COOLER EXHAUST CUTOUT LOWER AFT CORNER AT FS 248. THE NR 3 STIFFENER WAS REINFORCED WITH A NEW LOWER REPAIR ANGLE FROM FS 235-FS 254. THE RIB INSTALLATION AT NACELLE STATION 248 WAS MODIFIED TO ACCOMMODATE THE NEW STEEL REPAIR ANGLE INSTALLATION ON THE NR 3 STIFFENER. NDT INSPECTION WAS ACCOMPLISHED AT EACH REPAIR AREA AND HFEC INSPECTION OF ALL TRIMMED EDGES AND ALL REPAIR FASTENER LOCATIONS TO ENSURE DEFECT FREE CONDITION. (M)

Part: BULKHEAD — CRACKED (NR 3 PYLON)

DURING SCHEDULED MAINTENANCE INSPECTION, THE BULKHEAD UPPER ASSEMBLY FORWARD ANGLE FRAMES OF THE NR 3 PYLON LHS AND RHS WERE FOUND CRACKED. STOP DRILLED THE CRACK ENDS PER 747 SRM 51-10-01. HFEC INSPECTED TO ENSURE CRACK CONTAINMENT. FABRICATED AND INSTALLED REPAIR ANGLES ON THE FORWARD AND AFT FRAMES IN THE REPAIR AREA. INSTALLED THE REPAIR ANGLES BY PICKING UP ALL EXISTING FASTENER LOCATIONS AFFECTED BY THE REPAIR PARTS WITH HI-LOK FASTENERS. (M)

Part: SPAR — CORRODED (LT WING)

DURING SCHEDULED MAINTENANCE, CORROSION WAS FOUND LEFT WING SKIN FORWARD OF FRONT SPAR OLES 1378-1387, 1410, 1438-1447. CORROSION WAS REMOVED BY BLENDING. NDT INSPECTED TO CONFIRM DAMAGE FREE CONDITION. BLENDED AREAS WERE FLAP PEENED, ALODINE 1200 AND BMS 10-11 TYPE II PRIMER APPLIED. CUSTOM FILLERS WRE INSTALLED. TO RMOVED CORROSION AT OLES 1410, THE EXISTING CUTOUT IN THE SKIN LOCATED 4 INCHES OUTBOARD IS ENLARGED. SKIN FILLER IS SEGMENTED SO AS NOT TO BE LONGER THAN 8 INCHES. THREE REPAIR PLATES WRE MADE FROM .096 INCH THICK 2024-T3 ALUMINUM. (M)

Part: SKIN — CORRODED (LT WING)

DURING SCHEDULED MAINTENANCE, FOUND CORROSION ON LEFT WING TOP SKIN UPPER SURFACE AT APPROXIMATELY WBL 143, JUST FORWARD OF STRINGER 30. THE CORROSION WAS REMOVED BY BLENDING. HFEC INSPECTED THE SKIN SURFACE TO ENSURE DAMAGE AND DEFECT FREE. FLAP PEEN THE BLENDED AREA AND PROTECTIVE FINISH APPLIED. CORROSION INHIBITING COMPOUNDS WERE APPLIED TO THE REWORKED AREA. (M)

Part: PYLON — CRACKED (NR 3)

DURING SCHEDULED MAINTENANCE, NR 3 PYLON, CRACK DAMAGE WAS FOUND AT PRE-COOLER EXHAUST CUTOUT LOWER AFT CORNER AT FS 248. THE NR 3 STIFFENER WAS REINFORCED WITH A NEW LOWER REPAIR ANGLE FROM FS 235-254. THE RIB INSTALLATION AT NACELLE STATION 248 WAS MODIFIED TO ACCOMMODATE THE NEW STEEL REPAIR ANGLE INSTALLATION ON THE NR 3 STIFFENER. NDT INSPECTION WAS ACCOMPLISHED AT EACH REPAIR AREA AND HFEC INSPECTION OF ALL TRIMMED EDGES AND ALL REPAIR FASTENER LOCATIONS TO ENSURE DEFECT FREE CONDITION. (M)

Part: FAIRING — WORN (NR 1)

DURING SCHEDULED MAINTENANCE, FOUND NR 1 MOVABLE CANOE PRIMARY DOOR FAIRING BEARINGS WORN. HOLE ELONGATION WAS FOUND IN TWO LOCATIONS. OVERSIZED THE HOLES TO A MAXIMUM DIAMETER OF .7827 INCHES. DRY PNETRANT INSPECTED THE AFFECTED AREA TO ENSURE DEFECT FREE CONDITION. INSTALLED ALUMINUM ALLOY REPAIR SLEEVE AT EACH AFFECTED HOLE, AND INSTALLED DESIGN TYPE BEARINGS USING SHRINK FIT AND ROLLER SWAGGING METHOD. THE STRUCTURE RESTORED TO ORGINAL DESIGN REQUIREMENTS. (M)

Part: ACM — MALFUNCTIONED (A/C BAY)

DIVERSION TO JFK, WHILE CLIMBING THROUGH FL350, CABIN ALT WENT OT 11,000 FEET. DIFF PRESSURE WAS 6.0. AT FL300, CABIN ALT WAS 10,400 FEET. DIFF PRESSURE WAS 6.0 AT FL290 DIFF PRESSURE WAS 6.2 CABIN ALT 7800 FEET. DIVERTED TO JFK. PRESSURIZED A/C ON GROUND, NO LEAKS. NOTED DMI M03-110 NR 1 PACK COMPLETELY LOCKED OUT. REACTIVATED AND CHANGED TO MEL 21-3-2-B. PACK TO BE OPERATED IN MANUAL IN FLIGHT ONLY WITH BYPASS IN FULL HEAT POSITION. REMOVED AND REPLACED NR 1 ACM IAW MM 21-51-04. OPS CHECK OK. (M)

Part: MODULE — LEAKING (AUTOPILOT)

NR 1 HYDRAULIC LOW QUANTITY LIGHT CAME ON AFTER TAKEOFF. HYDRAULIC QUANTITY DROPPED TO ZERO. APPROXIMATELY 30 SECONDS LATER THE EDP AND ADP PRESSURE LIGHTS BEGAN TO FLASH. SHUT SYSTEM DOWN IAW PROCEDURES. EDP PUMP SWITCH PLACED TO SUPPLY OFF POSITION AT 0800. FOUND A/P PITCH MODULE LEAKING. CHANGED A/P PITCH MODULE ACC MM. FOUND PRESSURE AND RETURN LINE INTERCHANGED. CORRECTED THE SAME. PERFORMED OPS AND LEAK CHECK. ALL SATISFACTORY.

Part: KEELBEAM — CORRODED (FUSELAGE)

DURING CURRENT C-CHECK, AT SIAEC, FOUND KEEL BEAM CHORD, INBOARD LOWER FLANGE UPPER SURFACE CORRODED, AT BS 1330/1337 AND 1397, LBL 6. REMOVED CORROSION BY BLENDING. HFEC INSPECTED AREAS OF BLEND OUT AND FASTENER HOLES FOR ADDITIONAL CORROSION/CRACKS. NO ADDITIONAL CORROSION/CRACKS FOUND. MEASURED BS 1330/37, NO MORE THAN 20 PERCENT OF THICKNESS REMOVED TO A DEPTH OF .088 REMAINING AFTER BLEND OUT. MEASURED BS 1397, ORIGINAL THICKNESS .235, AFTER BLENDING .135 REMAINING. (M)

Part: SKIN — CRACKED (NR 2 PYLON)

DURING CURRENT C-CHECK AT SIAEC, FOUND NR 2 PYLON LEFT ACCESS PLATE CUTOUT (463CL) AT NAC STATION 332 TO 350 CRACKED AT LOWER FORWARD CORNER APPROX .5 INCH. TRIMMED OUT CRACKED AREA. HFEC INSPECTED THE TRIMMED OUT AREA AND ALL FASTENER HOLES IN THE REPAIR AREA FOR ADDITIONAL CRACKING. NO CRACKS FOUND. OVERSIZED EXISTING HOLES. FABRICATED FILLER AND REPAIR DOUBLERS. BONDED REPAIR FILLER AND DOUBLERS IN PLACE. (M)

Part: KEELBEAM — CORRODED (FUSELAGE)

DURING CURRENT C-CHECK AT SIAEC, FOUND KEEL BEAM BOX, LOWER CHORD, INNER VERTICAL SURFACE CORRODED LEVEL 1, AT BS 1267 RBL 10. CORROSION REMOVED BY BLENDING. HFEC INSPECTED AREA FOR ADDITIONAL CORROSION. NO CORROSION FOUND. ORIGINAL THICKNESS BEFORE BLENDING WAS .300, AFTER BLENDING .220 REMAINING. (M)

Part: SKIN — CRACKED (NR 2 PYLON)

DURING CURRENT C-CHECK AT SIAEC, FOUND NR 2 PYLON TOP CAP SKIN CRACKED AT NAC STATION 264 INBOARD SIDE. CUTOUT CRACKED SKIN AND DOUBLER. SURFACE CORROSION LEVEL 1 REVEALED TO SANDWICHED STIFFENER. REMOVED AFT SECTION OF STIFFENER FOR CORROSION BLEND REPAIRS. HFEC INSPECTED FOR CRACKS/CORROSION IN TRIMMED AREAS, CUT OUTS AND FASTENER HOLES OF THE REPAIR AREAS. NO CRACKS, CORROSION FOUND. FABRICATED ANGLES, SPLICES, FILLERS AND DOUBLERS. (M)

Part: ENGINE — FAILED (NR 2)

AT FLT 310, NR 2 ENGINE FAILED. PROCEEDING FAILURE CREW COULD SMELL OIL SMELL, THEN ENGINE QUIT. N2 WENT TO ZERO ALSO ZERO OIL PRESSURE. N1 APPROXIMATELY 22 PERCENT. A/C DIVERTED TO BKK. (M)

Part: SKIN — CRACKED (FUSELAGE)

DURING C-CHECK, FOUND 25 INCH CRACK ON FUSELAGE SKIN STA 980L. CRACK STARTS AT STR 37L AND CONTINUES TO STR 38L. ADDITIONALLY, FOUND DRAG SPLICE FITTING CRACKED, FRONT SPAR PRESSURE BULKHEAD CHORD CRACKED, FRONT SPAR PRESSURE BULKHEAD WEB CRACKED, AND STR 38L CRACKED. ACFT REPAIRED BY REPLACING SECTION OF FUSELAGE SKIN, LOWER DRAG SPLICE FITTING, REPAIRING STR PER SRM 53-1-03, FIG NR 5, SPLICING IN NEW FRONT SPAR WEB SECTION, AND RING CHORD REPLACED BY SPLICING IN NEW SECTION PER SB747-53-2362. FORM 8110-3 ISSUED FOR ALL REPAIRS. (X)

Part: SKIN — DAMAGED (NR 2 PYLON)

DURING STRUT MODIFICATION, THE SKIN BELOW MID-SPAR CHORD BETWEEN NAC STA 286 AND NAC STA 300 ON THE RIGHT SIDE OF NR 2 ENGINE PYLON WAS FOUND WITH HEAT DAMAGE WRINKLES. THE DAMAGED AREA WAS REPAIRED AS FOLLOWS: HEAT DAMAGED SKIN AREA WAS TRIMMED AND REMOVED. REPAIR AREA WAS NDT INSPECTED, NEW DOUBLER AND TRIPLER, MADE FROM TITANIUM SHEET WERE INSTALLED TO PICK UP AFT END OF TITANIUM SKIN DOUBLER MID-SPAR CHORD, LOWER STIFFENER FRAME AT NAC STA 286 AND FRAME AT NAC STA 300. STRUCTURAL SUBSTANTIATION OF ENGINEERING FOR ABOVE REPAIR MADE BY BOEING DER ON FORM 8110-3. (X)

Part: FRAME — CRACKED (PASSENGER DOOR)

AT LOCATION, LOWER FORWARD ON DOOR, L1. FOUND CRACK 12 INCHES VERTICAL AND 8 INCHES HORIZONTAL IN CHANNEL SECTIONS.