N14358

Part: STIFFENER — CRACKED (BS 540) · airframe 45,337 hrs · 43,520 cycles

A 2 INCH CRACK WAS FOUND TO THE WING CENTER SECTION REAR SPAR AT STA 540, RBL 6.15 VERTICAL STIFFENER DURING A WALKAROUND INSPECTION. AN INTERIM REPAIR WAS INSTALLED PER EA 5714-01002, REV C, OP 8 AND ECRA 5714-01011. A DIP WAS ISSUED TO REINSPECT THE STIFFENER EVERY 4500 FLIGHT CYCLES AND TO REPLACE BOTH STIFFENERS (RBL 6.15 AND LBL 6.15) WITHIN 15,000 FLIGHT CYCLES.

Part: SKIN — CRACKED (FUSELAGE) · airframe 44,173 hrs · 42,953 cycles

WALK AROUND FOUND 3.5 IN CRACK IN STA 767 LOWER LAP SKIN, S25L. REPAIRED IAW SRM 53-00-01, FIGURE 229. DIP WAS ISSUED TO REINSPECT REPAIR EVERY 60,000 CYCLES.

Part: TRU — SMOKE (NR 2) · airframe 43,583 hrs · 42,655 cycles

DURING CRUISE, ELECTRICAL SMOKE IN COCKPIT AND CABIN. REPLACED NR 2 TRANSFORMER RECTIFIER PER AMM 24.

Part: SKIN — CRACKED (L1 DOOR) · airframe 42,837 hrs · 42,314 cycles

INSPECTION FOUND A .75 INCH CRACK IN L-1 DOOR SKIN AT UPPER AFT INSPECTION HOLE. THE SKIN WAS REPAIRED IAW ECRA 5210-01812.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 42,837 hrs · 42,314 cycles

INSPECTION FOUND RT APU TORQUE BOX CORRODED ON TOP STRINGER 14R AT AIR INLET CUTOUT, STA 1121-1156. THE UPPER APU TORQUE BOX STRINGER WAS REMOVED AND REPLACED IAW SRM 51-40-02.

Part: ANGLE — CORRODED (FUSELAGE) · airframe 42,837 hrs · 42,314 cycles

INSPECTION FOUND L-2 DOOR THRESHOLD ZEE ANGLE CORRODED AT STA 907-1006, LBL 58. THE ZEE ANGLE WAS REMOVED AND REPLACED IAW SRM 51-10-02.

Part: STRINGER — CRACKED (FUSELAGE) · airframe 42,837 hrs · 42,314 cycles

INSPECTION FOUND A .5 INCH CRACK AT FASTENER OF STRINGER 4L SPLICE, STA 907. REPLACED STRINGER SPLICE IAW SRM 51-10-02.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 42,837 hrs · 42,314 cycles

INSPECTION FOUND SEAT TRACK BELOW G-1 GALLEY CORRODED AT STA 290. THE SEAT TRACK WAS REMOVED AND A NEW SEAT TRACK WAS INSTALLED IAW SRM 51-40-02 AND BOEING DRAWING 69-45834.

Part: SKIN — LIGHTNING STRIKE (RUDDER) · airframe 40,428 hrs · 41,044 cycles

INSPECTION FOUND LIGHTNING STRIKE DAMAGE ON RUDDER T/E APPROXIMATELY 30 INCHES BELOW STATIC WICK. REPAIRED IAW ECRA 5540-01171.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 40,428 hrs · 41,044 cycles

INSPECTION FOUND STRINGERS 26R AND 27R IN FORWARD CARGO AREA CORRODED AT STA 535-539. A STRINGER SECTION REPAIR WAS INSTALLED IAW SRM 53-00-03.

Part: FRAME — CRACKED (FUSELAGE) · airframe 40,428 hrs · 41,044 cycles

INSPECTION FOUND A 2 INCH CRACK IN BELTFRAME FITTING JUST BELOW CABIN FLOOR AT BOTTOM TWO FASTENERS, STA 616, W/ 200, LT SIDE. REPAIRED IAW ECRA 5311-01158.

Part: FRAME — CRACKED (FUSELAGE) · airframe 40,428 hrs · 41,044 cycles

INSPECTION FOUND A 1 INCH CRACK IN FRAME INNER CHORD AT STA 616, WL 200, RT SIDE. THE INNER CHORD WAS REPAIRED IAW ECRA 5311-01158.

Part: SKIN — CRACKED (STA 727D-727E) · airframe 38,655 hrs · 40,061 cycles

INSPECTION FOUND A 1.5" CRACK IN FUSELAGE SKIN BETWEEN STA 727D +9.9 AND STA 727E JUST ABOVE S23L. THE SKIN WAS REPAIRED IAW ECRA 5330-03205.

Part: FRAME — DENTED (STA 787) · airframe 35,218 hrs · 38,262 cycles

INSPECTION FOUND FRAME DENTED AT STA 787, S25R. A REPAIR DOUBLER WAS INSTALLED IAW SRM 51-70-11, FIGURE 1.

Part: SKIN — CRACKED (C-2 DOOR) · airframe 35,218 hrs · 38,262 cycles

INSPECTION FOUND A 0.375" CRACK IN SKIN AT C-2 DOOR LIGHTENING HOLE ABOVE INTERIOR HANDLE. A DOUBLER WAS INSTALLED IAW ECRA 5230-01613.

Part: STOP FITTING — GOUGED (C-2 DOOR) · airframe 35,218 hrs · 38,262 cycles

INSPECTION FOUND C-2 DOOR FORWARD LOWER STOP FITTING GOUGED. THE STOP FITTING WAS REMOVED AND REPLACED IAW SRM 51-40-2.

Part: SPAR — CRACKED (LT WING) · airframe 35,218 hrs · 38,262 cycles

INSPECTION FOUND A CRACK INDICATION IN NR 2 HOLE OF LT WING REAR SPAR UPPER CHORD AT GEAR BEAM CASTING ATTACH POINT. THE HOLE WAS REAMED AND THE CRACK WAS FOUND TO EXCEED 0.500 INCH MAX REAM LIMIT. THE REAR SPAR UPPER CHORD WAS REMOVED AND REPLACED FROM INBOARD END TO RSS 284 USING A SPLICE REPAIR IAW ECRA 5720-01855 AND ECRA 5360-01059.

Part: SKIN — DENTED (C-2 DOOR) · airframe 35,218 hrs · 38,262 cycles

INSPECTION FOUND C-2 DOOR EXTERNAL SKIN DENTED AT LOWER AFT CORNER. A REPAIR DOUBLER WAS INSTALLED IAW SRM 52-00-01, FIGURE 203.

Part: SKIN — CRACKED (STA 138.7) · airframe 35,218 hrs · 38,262 cycles

INSPECTION FOUND A 1.6" CRACK IN L/H HORIZONTAL STABILIZER LOWER SKIN ALONG REAR SPAR AREA AT STA 138.7. THE SKIN WAS REPAIRED IAW ECRA 5510-01586.

Part: SKIN — DENTED (BS 219) · airframe 35,218 hrs · 38,262 cycles

INSPECTION FOUND FUSELAGE SKIN DENTED AT BS 219, S23L, TEN INCHES ABOVE L/H SIDE OF FORWARD ACCESSORY DOOR AT EDGE OF BONDED DOUBLER. THE DENTED SKIN WAS REMOVED AND A DOUBLER WAS INSTALLED IAW SRM 53-00-01.

Part: SKIN — CRACKED (R/H HOR STAB) · airframe 35,218 hrs · 38,262 cycles

INSPECTION FOUND A 1" CRACK IN R/H HORIZONTAL STABILIZER LOWER SKIN FORWARD OF AFT SPAR AT I/B ELEVATOR BALANCE PANEL. THE SKIN WAS REPAIRED IAW ECRA 5510-01585 AND SRM 55-10-01.

Part: ANGLE — CORRODED (BS 270) · airframe 35,218 hrs · 38,262 cycles

INSPECTION FOUND COCKPIT FLOOR Z-ANGLE CORRODED AT BS 270, LBL 10 TO RBL 10. A REPAIR WAS INSTALLED IAW ECRA 5320-01683.

Part: SKIN — DENTED (FWD CARGO DR) · airframe 35,218 hrs · 38,262 cycles

INSPECTION FOUND TWO DENTS IN FORWARD CARGO DOOR EXTERNAL SKIN AT CENTER OF DOOR AND 14" FROM AFT EDGE OF DOOR. A DOUBLER WAS INSTALLED IAW SRM 52-00-01.

Part: SKIN — DENTED (STA 917) · airframe 35,218 hrs · 38,262 cycles

INSPECTION FOUND EXTERIOR FUSELAGE SKIN DENTED AT STA 917, S19L. A DOUBLER WAS INSTALLED IAW SRM 53-00-01.

Part: SKIN — DENTED (C-1 DOOR) · airframe 35,218 hrs · 38,262 cycles

INSPECTION FOUND THREE DENTS ON C-1 DOOR EXTERNAL SKIN. THE DENTS WERE LOCATED 12 INCHES FROM FORWARD EDGE OF DOOR. A REPAIR DOUBLER WAS INSTALLED IAW SRM 52-00-01, FIGURE 203.

Part: ACCESS PANEL — CRACKED (NR 1 PYLON) · airframe 35,218 hrs · 38,262 cycles

INSPECTION FOUND A .5 INCH CRACK IN NR 1 ENGINE PYLON ACCESS PANEL 5727. A DOUBLER WAS INSTALLED IAW ECRA 5430-01230.

Part: SKIN — DAMAGED (STA 807) · airframe 35,218 hrs · 38,262 cycles

INSPECTION FOUND FUSELAGE SKIN "DAMAGED" AT STA 807, S28L TO S26R. THE DAMAGE WAS REMOVED AND FILLER AND DOUBLER WERE INSTALLED IAW SRM 53-00-01.

Part: FLOORBEAM — CORRODED (STA 344) · airframe 35,218 hrs · 38,262 cycles

INSPECTION FOUND FLOORBEAM CORRODED AT STA 344, BL 0 TO LBL 59. THE FLOORBEAM WAS REMOVED AND A NEW FLOORBEAM WAS INSTALLED IAW SRM 53-10-51.

Part: FLOORBEAM — CORRODED (STA 328) · airframe 35,218 hrs · 38,262 cycles

INSPECTION FOUND FLOORBEAM CORRODED AT STA 328, LBL 49. THE CORRODED SECTION OF FLOORBEAM WAS REMOVED AND A NEW SECTION WAS INSTALLED IAW SRM 53-10-51.

Part: FLOORBEAM — CORRODED (BS 986.5)

INSPECTION FOUND CABIN FLOORBEAM CORRODED ON UPPER CHORD LOWER SURFACE FORWARD AND AFT OF STA 986.5, RBL 25-35. REPAIRED IAW ECRA 5310-03851.

Part: WIRE — PINCHED (ROW 12)

ROW 7 TO 12 EMERGENCY LIGHTS INOP. FOUND WIRE PINCHED IN SEAT TRACK AT ROW 12. REPAIRED WIRE, OPS CHECK GOOD.

Part: FRAME — CORRODED (BS 1121)

INSPECTION FOUND BELTFRAME WEB AND CHORD CORRODED AT STA 1121R. THE WEB AND CHORD WERE REPLACED IAW SRM 51-10-02.

Part: ANGLE — CORRODED (BS 947.5-986.5)

INSPECTION FOUND Z-ANGLE AT L-2 DOOR LOWER JAMB CORRODED FROM STA 947.5 TO 986.5. THE ANGLE WAS REPLACED IAW SRM 51-10-2.

Part: FLOORBEAM — CORRODED (BS 1016)

INSPECTION FOUND FLOORBEAM CORRODED UNDER LEFT AFT LAV AT STA 1016. THE FLOORBEAM WAS REMOVED AND REPLACED IAW SRM 53-00-51, PAGES 207 TO 211.

Part: WEB — CORRODED (BS 1016-1040)

INSPECTION FOUND WEB UNDER LEFT AFT LAV CORRODED AT STA 1016 TO 1040. THE WEB WAS REMOVED AND REPLACED IAW SRM 51-10-02.

Part: ANGLE — CORRODED (BS 1121)

INSPECTION FOUND ANGLE CORRODED AT STA 1121R, WL 240. THE ANGLE WAS REPLACED IAW SRM 51-10-02.

Part: STRINGER — CRACKED (BS 500)

INSPECCTION FOUND A .5 INCH CRACK IN STRINGER 16L AT STA 500C. THE CRACKED AREA OF STRINGER WAS REMOVED, REPAIR DOUBLER, FILLER, AND CHANNEL WERE FABRICATED AND INSTALLED IAW ECRA 5330-02541.

Part: WEB — CORRODED (BS 1016-1040)

INSPECTION FOUND WEB CORRODED UNDER RIGHT LAV FROM STA 1016 TO 1040. THE WEB WAS REPLACED IAW SRM 51-10-2.

Part: FLOORBEAM — CORRODED (BS 986.5)

INSPECTION FOUND FLOORBEAM CORRODED AT STA 986.5. THE CORRODED AREA WAS CUT OUT, A REPAIR WAS FABRICATED AND INSTALLED IAW ECRA 5310-03450.

Part: ANGLE — CORRODED (BS 947.5-1006)

INSPECTION FOUND Z-ANGLE AT LOWER R-2 DOOR JAMB CORRODED FROM STA 947.5 TO 1006. THE ANGLE WAS REMOVED AND A NEW ANGLE WAS FABRICATED AND INSTALLED IAW SRM 53-30-11 AND 51-40-02.

Part: SUPPORT — CORRODED (BS 328-344)

INSPECTION FOUND FLOOR SUPPORT CORRODED AT STA 328 TO 344, BBL 0 TO LBL 45. THE FLOOR SUPPORT WAS REPLACED IAW SRM 51-10-2.

Part: SUPPORT — CORRODED (BS 228-312)

INSPECTION FOUND FLOOR SUPPORT CORRODED AT STA 228L TO 312L, LBL 26.75. THE FLOOR SUPPORT WAS REPLACED IAW SRM 51-10-2.

Part: SUPPORT — CORRODED (BS 312)

INSPECTION FOUND FLOOR SUPPORT CORRODED AT STA 312L TO 312R. THE FLOOR SUPPORT WAS REMOVED AND REPLACED IAW SRM 53-10-51.

Part: ANGLE — CORRODED (BS 276-300)

INSPECTION FOUND FLOOR ANGLE CORRODED AT STA 276R TO 300R. THE FLOOR ANGLE WAS REPLACED IAW SRM 51-40-02.

Part: HYD LINE — LEAKING (NLG ACTUATOR)

THE A-SYSTEM HYDRAULIC FLUID QUANTITY WENT TO ZERO WHILE ON FINAL APPROACH TO EWR. THE AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE NOSE GEAR ACTUATOR HYDRAULIC PRESSURE LINE LEAKING. THE HYDRAULIC PRESSURE LINE WAS REMOVED AND REPLACED. THE GEAR HANDLE WAS CYCLED SEVERAL TIMES AND NO LEAKS WERE NOTED.