N458MC

Part: AUTOPILOT SYS — MALFUNCTIONED (COCKPIT) · airframe 65,794 hrs · 13,859 cycles

DESCENDING ACFT ABRUPTLY PITCHED UP & STARTED TO CLIMB ON AUTOPILOT. DISCONNECT AUTOPILOT & RE-ENGAGED LATER & OPERATIONS WERE NORMAL. VERIFIED NO CMC ACTIVE FAULTS. PERFORMED AUTO LAND UNIQUE TEST & PASSED IAW AMM 27-00-00.

Part: LAMP — BURNED OUT (EMERGENCY LIGHT) · airframe 64,197 hrs · 13,539 cycles

EMERGENCY LIGHT IN STAIRWELL TO UPPER DECK DOES NOT ILLUMINATE. RELAMPED EMERGENCY LIGHT IN STAIRWELL TO UPPER DECK IAW AMM 33-51-07-962-001. TEST GOOD.

Part: STRUCTURE — CHAFED (LT WING TE FLAP) · airframe 63,316 hrs · 13,379 cycles

LT WING L/E NR 9 L/C FLAP BULLNOSE INBD EDGE FOUND CHAFED. LT WING L/E NR 9 L/C FLAP BULLNOSE INBD EDGE REPAIRED IAW R1-57-44-16155, REV A.

Part: STIFFENER — CRACKED (LT WING) · airframe 63,316 hrs · 13,379 cycles

LEFT WING OTBD REFUELING PANEL, ATTACH STIFFENING ANGLE OTBD CORNER FOUND CRACKED. LT WING OTBD REFUELING PANEL, ATTACH STIFFENING ANGLE REPLACED IAW R1-52-49-10154, REV A.

Part: STRUCTURE — CHAFED (LT WING TE FLAP) · airframe 63,316 hrs · 13,379 cycles

LT WING L/E NR 10 L/C FLAP BULL NOSE OTBD EDGE FOUND CHAFED. LT WING L/E NR 10 L/C FLAP BULL NOSE OTBD EDGE REPAIRED IAW R1-57-44-10156, REV A.

Part: STOWAGE BOX — DAMAGED (OXYGEN MASK) · airframe 61,512 hrs · 13,044 cycles

CREW OXYGEN WAS FOUND TO BE LOW. ON INSPECTION AND LEAK CHECK AFTER BOTTLE REPLACEMENT IAW AMM 12-15-08, THE CAPTAIN'S OXYGEN MASK STOWAGE BOX WAS FOUND TO BE DAMAGED AND LEAKING. THE CAPTAIN'S OXYGEN MASK STOWAGE BOX WAS REPLACED IAW AMM 35-11-18. LEAK AND OPS CHECKED OK.

Part: STRUCTURE — DAMAGED (THRUST REVERSER) · airframe 60,173 hrs · 12,800 cycles

DURING MX WALKAROUND, FOUND DAMAGE TO THE NR 2 ENGINE THRUST REVERSER CORE COWL AFT EXTRUSION.

Part: SEAL — PUNCTURED (TE FLAP) · airframe 59,531 hrs · 12,689 cycles

DURING A-3 CHECK AT BFM, MX FOUND DAMAGE TO THE LT INBD T/E MID FLAP-RUBBING SHEET/STRIP (PN 65B08436-35) OF THE COMPRESSION SEAL AT WBL 129.30, MEASURING 2.3 INCHES WIDE; X 15" LONG. A PUNCTURE DAMAGE (0.5 " WIDE X 0.8 " LONG) WAS ALSO FOUND ON THE BODY RIB ASSY (PN 65B08465-39) WHERE THE RUBBING STRIP ATTACHES TO THE SEAL ASSY. THE INBD T/E MID FLAP PN 65B02025-35, SN 000320. (DISPOSITION IS TO PERFORM A TIME LIMITED REPAIR AS DESCRIBED IN PART 1 WORK INSTRUCTIONS EO 4457A394; DVI EVERY 20 FLIGHT CYCLES; AND REPLACE THE SEAL ASSY (PN 65B08436-55) PRIOR TO THE ACCUMULATION OF 1,000 FH (FLIGHT HOURS) AFTER PART 1.)

Part: INSULATION — DELAMINATED (THRUST REVERSER) · airframe 59,026 hrs · 12,592 cycles

DURING WALKAROUND, MX FOUND THE NR 4 RT T/R INSULATION DAMAGE AS FOLLOWS (REF FIG 1) DELAMINATIONS AND PUNCTURE OF INSULATION FROM HONEYCOMB STRUCTURE IS AS FOLLOWS: DELAMINATED AREA IS 19.0" FROM FRAME TO FRAME AND 35.0" TOP TO BOTTOM. THE PUNCTURE IN THE MIDDLE IS 2.0" LONG X .7500" WIDE. THE SECOND DELAMINATED AREA ON BOTTOM IS 4.0" X 6.0" SIZE. (DISPOSITION WAS MADE TO PERFORM A TIME LIMITED REPAIR AS DESCRIBED IN PART 1 WORK INSTRUCTIONS, VISUAL INSPECTIONS AFTER EVERY (2) FLIGHT CYCLES, AND PERMANENT REPAIR WITHIN 10 CALENDAR DAYS.)

Part: LANDING GEAR — MISINSTALLED · airframe 56,635 hrs · 12,173 cycles

DURING D-CHECK AT SIN, LANDING GEARS WERE REPLACED; UPON OPS CHECKS, MX FOUND THE LT AMP; RT BODY GEARS- UPPER JURY STRUT PLATES MOUNTING BOLTS BEING INSTALLED TOO LONG, RESULTING IN RIDING CONDITION AGAINST THE DOWNLOCK SENSORS (REF FIGURE 1). (DISPOSITION WAS MADE TO PERFORM A TIME LIMITED REPAIR AS DESCRIBED IN PART 1 WORK INSTRUCTIONS BY TRIMMING OFF (USING A FILE) THE END OF THE BOLTS (4 EA) TO RELIEVE THE RIDING CONDITION.PART 2 OF THIS EO REPEAT INSPECTIONS WILL BE SCHEDULED AT EVERY 1,000 FH (FLIGHT HOURS) AND PERMANENT REPAIR IAW PART 3 AT THE NEXT C CHECK AFTER PART 1, BY R & R THE BOLTS IAW SRM 51-40-02.)

Part: FRAME — UNKNOWN (BS 1220) · airframe 56,635 hrs · 12,173 cycles

DURING SB 747-53A2507 INSP AT BS 1220, S8L LOCATION COMMON TO FRAME WEB, FRAME DOUBLER AND FRAME CHORD. (THE REPAIR WAS ACCOMPLISHED IAW RI NR N458MC-11-002 IAW REPAIR INSTRUCTIONS PROVIDED BY IN SR 1-1817615622. THE REPAIR WAS APPROVED BY FAA FORM 8100-9)

Part: FRAME — CRACKED (BS 1160) · airframe 56,635 hrs · 12,173 cycles

DURING D INSPECTION OF DATUM ACFT IAW EO 4453A197, CRACK WAS FOUND ON FRAME AT BS 1160 (RT AT STR 9). (THE DAMAGED FRAME WAS REPAIRED IAW PART 5 OF EO 4453A197, REV D (SRM 53-40-07, REPAIR 3). IAW PART 5 OF EO, THE FRAME CRACKS THAT CANNOT BE REMOVED BY DOING THE OVERSIZE HOLE REPAIR, SHOULD BE REPAIRED AS GIVEN IN SRM 53-40-07.)

Part: FRAME — CRACKED (THRUST REVERSER) · airframe 56,635 hrs · 12,173 cycles

THE LT NR 4 FAN REVERSER EXHIBITED A CRACK ON THE TORQUE BOX FWD FRAME. (IN THIS INSTANCE THE CRACK HAD BEEN STOP DRILLED AND REGULARLY INSPECTED BY THE PRIOR OPERATOR JAL. AS THE ACFT WAS IN HEAVY CHECK, SIAEC WAS ADVISED TO PERFORM A PERMANENT REPAIR IAW SB 78-061, REV 7 BUT THE REPAIR DID NOT EXTEND INTO THE CRACK AREA. THIS EO AUTHORIZES INSP OF THE LT FAN REVERSER FOR CRACK PROPAGATION WITHIN 1000 FLIGHT HOURS AND EVERY 1000 FLIGHT HOURS THEREAFTER. EWIS)

Part: SKIN — DAMAGED (BS 385 S31L) · airframe 27,173 hrs · 1,500 cycles

THE LIGHTNING STRIKE DAMAGE TO 65B07656-259 SKIN WAS DETECTED AT BS 385 AND S31AL. THE DEPTH OF LIGHTNING STRIKE DAMAGE WAS .015 INCHES AS RECORDED IAW SIAEC NRC 005380. (THE LIGHTNING STRIKE DAMAGED AREA WAS LOCALIZED IN 65B07656-259 SKIN ONLY. THE LIGHTNING STRIKE DAMAGED AREA WAS TRIMMED FROM THE .063 INCH THICK 65B07656-259 SKIN BY ENCOMPASSING THE LIGHTNING STRIKE DAMAGE IN A FWD TO AFT RECTANGLE MEASURING, APPROX 2.0 INCHES IN LENGTH AND 1.2 INCHES IN WIDTH. FOR EASE OF REMOVING THE DAMAGED AREA FROM 65B07656-259 SKIN, THE SAME ADJACENT AREA WAS ALSO TRIMMED FROM THE .071 INCH THICK 65B07656-237 DOUBLER.

Part: SKIN — DAMAGED (BS 345) · airframe 56,635 hrs · 12,173 cycles

FUSELAGE SKIN INSP DURING "D-CHECK", FOUND LIGHTNING STRIKE ON CROWN SKIN AT STA 345 BETWEEN STR 1R AND 2R (SOLID FASTENER REPAIR CARRIED OUT IAW B744SF SRM 53-00-01. REPAIR 9 SECTION I, PAR S.)

Part: SKIN — DAMAGED (BS 345) · airframe 56,635 hrs · 12,173 cycles

DURING D-CHECK OF THE DATUM AIRPLANE, A LIGHTNING STRIKE DAMAGE WAS FOUND ON RT FUSELAGE SKIN AT BS 345, S1R-2R . DAMAGE WAS FOUND TO BE BEYOND THE ALLOWABLE LIMIT IAW SRM 53-00-01, FIG 101. (THE DAMAGE WAS REPAIRED IAW SRM 53-00-01, FIG 201, REPAIR 9 AND IAW SIAEC, NRC 359. SOLID FASTENER REPAIR CARRIED OUT ON DAMAGED AREA )

Part: SKIN — DAMAGED (BS 385) · airframe 56,635 hrs · 12,173 cycles

LIGHTNING STRIKE DAMAGE FOUND AT STA 385 LT, S-31A, DEPTH FOUND APPROX 0.015, LENGTH APPROX 1" TO C/OUT FUSELAGE SKIN EXTERNAL REPAIR IAW SRM 53-00-01. CAT B REPAIR CARRIED OUT IAW MSG SEP-TLS-11-0036-02B. EXTERNAL DOUBLER AND TRIPLER FABRICATED.