N34315

Part: SKIN — CRACKED (FUSELAGE) · airframe 55,431 hrs · 28,839 cycles

INSPECTION FOUND A 2.5 INCH CRACK IN RIGHT FUSELAGE SKIN JUST AFT OF AFT WING FAIRING, 27 INCHES AFT OF STA 727E. THE SKIN WAS REPAIRED IAW SRM 53-00-01, FIGURE 229, SHEET 21.

Part: CROSSBEAM — CRACKED (CARGO DOOR) · airframe 54,844 hrs · 28,530 cycles

INSPECTION FOUND A 2 INCH RACK AT LOWER FORWARD END OF AFT CARGO DOOR NR 5 CROSS BEAM TEE EXTRUSION. THE AFT CARGO DOOR WAS REMOVED AND A NEW DOOR WAS INSTALLED AND ADJUSTED. OPERATIONAL CHECKS WERE GOOD IAW MM 52-30-00.

Part: SKIN — DAMAGED (CARGO DOOR) · airframe 54,844 hrs · 28,529 cycles

IN PREPARATION FOR INSTALLING A PERMANENT REPAIR, A TEMPORARY REPAIR DOUBLER ON THE INNER SKIN OF THE AFT CARGO DOOR ABOVE THE DOOR HANDLE CUTOUT WAS REMOVED AND A SMALL AREA OF DAMAGE TO THE INNER SKIN WAS DISCOVERED. A REPAIR DOUBLER WAS INSTALLED AS A PERMANENT REPAIR IAW ECRA 5232-01044.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 54,844 hrs · 28,529 cycles

INSPECTION FOUND FLOOR SUPPORT CORRODED AT STA 277, BL 0. THE CORROSION WAS REMOVED AND A REPAIR WAS INSTALLED IAW ECRA 5321-01169.

Part: ANGLE — CORRODED (FUSELAGE) · airframe 54,844 hrs · 28,529 cycles

INSPECTION FOUND RT LOWER SURFACE OF PRESSURE DECK ANGLE CORRODED IN WHEEL WELL AT STA 706, RBL 64. A DOUBLER WAS INSTALLED IAW SRM 51-40-11 AND 51-40-02 AND DRAWING PL65-50733.

Part: FLANGE — CORRODED (FUSELAGE) · airframe 54,844 hrs · 28,529 cycles

INSPECTION FOUND THE UPPER SURFACE OF THE FORWARD FLANGE OF THE ZEE FRAME CORRODED AT STA 270, BL 0.0. THE FRAME WAS REPAIRED IAW ECRA 5321-01169.

Part: BEAM — CRACKED (LT WING T/E) · airframe 54,844 hrs · 28,529 cycles

INSPECTION FOUND A 2 INCH CRACK IN LT WING T/E BEAM (IN FRONT OF AILERON CENTER HINGE). REMOVED AND REPLACED BEAM IAW SRM 51-10-02.

Part: ANGLE — CORRODED (FUSELAGE) · airframe 54,844 hrs · 28,529 cycles

INSPECTION FOUND R-1 DOOR Z-ANGLE CORRODED BETWEEN STA 277 AND 380 AT RBL 54. THE ANGLE WAS REMOVED AND REPLACED IAW SRM 51-40-02.

Part: ANGLE — CORRODED (FUSELAGE) · airframe 54,844 hrs · 28,529 cycles

INSPECTION FOUND FLOOR ANGLE CORRODED AT STA 303, RBL 54. THE ANGLE WAS REMOVED AND REPLACED IAW SRM 51-10-02.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 54,844 hrs · 28,529 cycles

INSPECTION FOUND MAIN CABIN FLOOR RIGHT I/B AND O/B SEAT TRACKS CORRODED AT STA 917-927. THE CORRODED SECTIONS OF SEAT TRACK WERE REMOVED AND REPLACED IAW SRM 53-00-52, FIGURE 204.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 54,844 hrs · 28,529 cycles

INSPECTION FOUND MAIN CABIN FLOORBEAM UPPER AND LOWER SURFACES CORRODED AROUND SCREW HOLES AT STA 986.5, RBL 0 TO RBL 50. THE CORRODED SECTION OF FLOORBEAM UPPER CHORD WAS REMOVED AND A NEW REPAIR CHORD WAS INSTALLED IAW ECRA 5310-03851.

Part: SUPPORT — CORRODED (FUSELAGE) · airframe 54,844 hrs · 28,529 cycles

INSPECTION FOUND UPPER AND LOWER SURFACES OF MAIN CABIN FLOOR LAV WALL SUPPORT CORRODED AT STA 993 FROM RBL 16 TO RBL 46. THE SUPPORT WAS REMOVED AND A NEW SUPPORT CHANNEL WAS INSTALLED IAW SRM 51-40-02.

Part: ANGLE — CORRODED (FUSELAGE) · airframe 54,844 hrs · 28,529 cycles

INSPECTION FOUND MAIN CABIN FLOOR Z-ANGLE CORRODED FROM STA 956-997, RBL 50. THE Z-ANGLE WAS REMOVED AND REPLACED IAW SRM 51-40-02.

Part: SKIN — CRACKED (STA 727A) · airframe 52,311 hrs · 27,173 cycles

INSPECTION FOUND A 3" CRACK IN R/H FUSELAGE SKIN JUST AFT OF R/H WHEEL WELL WING TO BODY FAIRING AT STA 727A, S23R. A REPAIR DOUBLER/TRIPLER WAS INSTALLED IAW ECRA 5330-03185.

Part: FASTENER — CRACKED (NR 1 L/E SLAT) · airframe 50,521 hrs · 26,200 cycles

INSPECTION FOUND NR 1 LEADING EDGE SLAT FASTENERS CRACKED ON LOWER SKIN. INSTALLED REPAIR IAW SRM 57-43-01.

Part: WEB — CRACKED (BS 590) · airframe 50,521 hrs · 26,200 cycles

INSPECTION FOUND FOUR 1/2" CRACKS AT AFT LOWER BOLT HOLES OF WEB AT SECONDARY HEAT EXCHANGER CUTOUT, BS 590, LBL 41(WING CENTER SECTION). REPAIRED IAW ECRA 5712-01003.

Part: SPAR — CRACKED (L/W UPPER) · airframe 50,509 hrs · 26,194 cycles

INSPECTION FOUND A 0.2" CRACK IN L/H WING UPPER SPAR AT #4 HOLE FROM THE I/B SIDE COMMOM TO THE SUPPORT FITTING. AN OVERSIZED BOLT WAS INSTALLED IAW ECRA 5743-01050. A DETAILED VISUAL INSPECTION OR HFEC INSPECTION WILL BE PERFORMED ON THE SPAR VERTICAL FLANGE BELOW AND ABOVE FOOTPRINT OF MLG FITTING IAW ECRA 5743-01050 EVERY 4500 CYCLES.

Part: STRINGER — CORRODED (BS 500D)

INSPECTION FOUND STRINGER 27R CORRODED AT BS 500D. THE CORROSION WAS REMOVED AND A REPAIR WAS INSTALLED IAW SRM 53-00-03, FIGURE201.

Part: SKIN — GOUGED (BS 867 - 887)

INSPECTION FOUND FUSELAGE SKIN GOUGED AT BS 867-887, STRINGER 1. THE DAMAGED AREA WAS CUT OUT AND REPAIRED IAW SRM 53-00-01.

Part: FLOORBEAM — CORRODED (BS 312)

INSPECTION FOUND FLOORBEAM CORRODED AT STA 312, LBL 12 TO RBL 12. A T-CHORD REPAIR WAS INSTALLED IAW SRM 53-10-51, FIGURE 205.

Part: FLOORBEAM — CORRODED (BS 328)

INSPECTION FOUND FLOORBEAM T-CHORD CORRODED AT CABIN FORWARD ENTRY, STA 328, LBL 20 TO RBL 48. A NEW T-CHORD WAS INSTALLED IAW SRM 53-40-02 AND 53-10-51, FIGURE 205.

Part: FLOORBEAM — CORRODED (BS 344)

INSPECTION FOUND FLOORBEAM CORRODED AT FASTENER HOLES, STA 344, LBL 18-RBL 10. A CHORD WAS INSTALLED IAW SRM 53-10-51.

Part: ENGINE — FLAMED OUT (NR 1)

WHILE PULLING POWER BACK FROM CLIMB POWER IN RESPONSE TO A TCAS WARNING AFTER DEPARTING PHL, THE NR 1 ENGINE FLAMED OUT. THE ENGINE WAS RESTARTED AND THE AIRCRAFT WAS DIVERTED TO EWR WHERE IT LANDED WITHOUT INCIDENT. AN ENGINE FLAME OUT INSPECTION OF THE NR 1 ENGINE WAS PERFORMED IAW MM 71-00-42 AND NO FAULTS WERE NOTED. THE MAIN FUEL FILTER WAS REMOVED AND REPLACED AS A PRECAUTIONARY MEASURE. THE NR 1 ENGINE WAS OPERATED AT TAKEOFF POWER FOR SEVERAL MINUTES AND OPERATION CHECKED GOOD.

Part: BATTERY PACK — DISCHARGED (CABIN)

THE FORWARD LEFT ENTRY DOOR EMERGENCY LIGHT FAILED FUNCTIONAL CHECK. THE BATTERY PACK WAS REMOVED AND REPLACED.

Part: SKIN — GOUGED (BS 1016)

INSPECTION FOUND A GOUGE IN FUSELAGE SKIN AT STA 1016, S27R. A DOUBLER PLATE WAS INSTALLED IAW SRM 53-60-01.

Part: LIGHT — INOPERATIVE (CABIN)

INSPECTION FOUND R-2 DOOR EXTERIOR EMERGENCY EXIT LIGHT INOPERATIVE DURING B-CHECK. THE EMERGENCY EXIT LIGHT ASSEMBLY WAS REPLACED.

Part: FCU — INOPERATIVE (APU)

THE APU WOULD NOT START DURING FLIGHT. MAINTENANCE FOUND THE APU FUEL CONTROL UNIT AT FAULT. THE APU FCU WAS REMOVED AND REPLACED IAW MM 49-31-11. APU LEAK AND OPERATIONAL CHECKS WERE GOOD.

Part: FUSE — BLOWN (BATTERY PACK)

INSPECTION FOUND CENTER SECTION OF EMERGENCY SEAT TRACK LIGHTS INOPERATIVE DURING A PREFLIGHT CHECK. MAINTENANCE FOUND LOWER FUSE BLOWN ON THE AFT EMERGENCY BATTERY PACK. THE FUSE WAS REPLACED AND OPERATION OF THE SEAT TRACK LIGHTS WAS RESTORED.