N901FR

Part: HOOK — DAMAGED (R2 DOOR SLIDE) · airframe 22,815 hrs · 10,141 cycles

DURING C-5 CHECK, INSPECTION REPORTED UPON INSTALLATION OF R2 DOOR SLIDE, OPEN/CLOSE HANDLE COULD BE OPERATED BEFORE DOOR WAS IN HOLE. REMOVED AND REPLACED HOOK ON DOOR LOCKING MECHANISM AND PERFORMED OPS CHECK AND RIG CHECK IAW AMM 52-13-21-400-001.

Part: HINGE FITTING — CORRODED (NR 2 NACELLE) · airframe 22,815 hrs · 10,141 cycles

DURING C-5 CHECK, INSPECTION REPORTED NR 2 PYLON T/R COWL FITTINGS AT RIB 1 AND RIB 2 CORRODED. REMOVED AND REPLACED NR 2 PYLON OTBD T/R COWL FITTINGS AT RIBS 1 AND 2 IAW AMM 54-57-17-000-003 AND 54-57-17-420-053.

Part: FLOOR PANEL — BROKEN (CABIN) · airframe 22,815 hrs · 10,141 cycles

DURING C-5 CHECK, INSPECTION REPORTED FLOOR PANEL 151PE IN AFT CARGO COMPARTMENT BROKEN INTERNALLY. REMOVED PANEL 151PE IAW SRM 51-42-11. DETERMINED PANEL TO BE BROKEN IN HALF (FULL LENGTH OF PANEL) AND OUT OF LIMITS IAW SRM 53-02-00, FIG 206, SHEET 2. REPLACED FLOOR PANEL 151PE IAW SRM 53-42-14-400-001.

Part: SHEAR PLATE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 22,815 hrs · 10,141 cycles

DURING C-5 CHECK, INSPECTION REPORTED CORROSION ON FWD CARGO COMPARTMENT FLOORBEAM AT FR 28, AND ON THE AFT DOOR SILL. CORROSION WAS CLASSIFIED AS EXFOLIATION. REMOVED AND REPLACED PROFILE PLATE IAW SRM 51-42-11-PAR 2A1.

Part: LOCK TAB — FAILED (NR 2 ENG MOUNT) · airframe 22,815 hrs · 10,141 cycles

DURING C-5 CHECK, INSPECTION REPORTED NR 2 ENG AFT MOUNT INBD LWR LOCKING TAB THAT SECURES BOLT FROM ROTATING BLOWN OUT OF ITS SECURING POSITION TO PREVENT BOLT FROM ROTATING. REMOVED AND REPLACED BEARING AT RIB 10 IAW MM 54-51-17-000-003 AND MM 54-51-17-400-003, STEPS 1-4.

Part: PIN — CORRODED (NLG CENTERING) · airframe 22,815 hrs · 10,141 cycles

DURING C-5 CHECK, INSPECTION REPORTED PITTING ON SHOULDER OF NLG TORQUE LINK CENTER PIN. REMOVED AND REPLACED NLG TORQUE LINK CENTER PIN IAW 32-21-27-420-050. PERFORMED FUNCTIONAL CHECK OF THE NORMAL EXTENSION AND RETRACTION OF THE NOSE LAND GEAR IAW AMM 32-31-00-720-003. CHECKED GOOD. PERFORMED FUNCTIONAL TEST OF THE NOSE WHEEL STEERING IAW AMM 32-51-00-720-003. CHECKED GOOD.

Part: BATTERY PACK — NO TEST (EMERGENCY LIGHTS) · airframe 22,815 hrs · 10,141 cycles

DURING C-5 CHECK, INSPECTION REPORTED LT OVERWING EMERGENCY BATTERY EPSU FAILED CAPACITY TEST. REMOVED AND REPLACED EPSU BATTERY AND PERFORMED OPS CHECK IAW AMM 33-51-38-000-002. CHECKED GOOD.

Part: BATTERY PACK — NO TEST (EMERGENCY LIGHTS) · airframe 22,815 hrs · 10,141 cycles

DURING C-5 CHECK, INSPECTION REPORTED FWD EMERGENCY BATTERY EPSU FAILED CAPACITY TEST. REMOVED AND REPLACED FWD EPSU BATTERY AND PERFORMED OPS CHECK IAW 33-51-38-000-002. CHECKED GOOD.

Part: SILL — CORRODED (FUSELAGE) · airframe 22,815 hrs · 10,141 cycles

DURING C-5 CHECK, INSPECTION REPORTED LIGHT SURFACE CORROSION ON FWD CARGO DOOR SILL WEB. REMOVED NUTPLATE AND REWORKED FOUR SMALL AREAS OF CORROSION IAW SRM 51-42-11 AND 51-74-00. EA NR A9-53R-12316 REQUIRED ACCOMPLISHMENT OF HFEC INSPECTION OF BLENDED AREAS AND ROTOPROBE OF NUTPLATE HOLE TO VERIFY NO DAMAGE PRESENT. PERFORMED HFEC AND ROTOPROBE INSPECTIONS IAW NTM 51-10-08 PART 6, AND 51-10-01 PART 6, PAGES 601-612. NO DEFECTS NOTED.

Part: BATTERY PACK — NO TEST (EMERGENCY LIGHTS) · airframe 22,815 hrs · 10,141 cycles

DURING C-5 CHECK, INSPECTION REPORTED AFT EMERGENCY BATTERY EPSU FAILED CAPACITY TEST. REMOVED AND REPLACED EPSU BATTERY AND PERFORMED OPS CHECK IAW AMM 33-51-38-400-002. CHECKED GOOD.

Part: BATTERY PACK — NO TEST (EMERGENCY LIGHTS) · airframe 22,815 hrs · 10,141 cycles

DURING C-5 CHECK, INSPECTION REPORTED RT OVERWING EMERGENCY BATTERY EPSU FAILED CAPACITY TEST. REMOVED AND REPLACED EPSU BATTERY AND PERFORMED OPERATIONAL CHECK IAW AMM 33-51-38-PB401. CHECKED GOOD.

Part: BATTERY — FAILED (CABIN) · airframe 16,966 hrs · 7,660 cycles

DURING C-4 CHECK, INSPECTION REPORTED RT OVERWING EXIT EPSU BATTERY FAILED CAPACITY CHECK. REPLACED EPSU BATTERY AT RT OVERWING EXIT. OPS CHECKED GOOD PER AMM 33-51-38-400-002 AND 33-51-38-000-002.

Part: BATTERY — FAULTED (CABIN) · airframe 16,966 hrs · 7,660 cycles

DURING C-4 CHECK, INSPECTION REPORTED FWD EPSU BATTERY FAULT. REPLACED EPSU BATTERY AT 10WL ABOVE L1 DOOR. OPS CHECKED GOOD PER AMM 33-51-38-000-002 AND 33-51-38-400-002.

Part: BATTERY — FAULTED (CABIN) · airframe 16,966 hrs · 7,660 cycles

DURING C-4 CHECK, INSPECTION REPORTED AFT EPSU BATTERY FAULT. REPLACED EPSU BATTERY AT 13WL. OPS CHECKED GOOD PER AMM 33-51-38-000-002 AND 33-51-38-400-002.

Part: BATTERY — FAULTED (CABIN) · airframe 16,966 hrs · 7,660 cycles

DURING C-4 CHECK, INSPECTION REPORTED EPSU BATTERY EMER LEFT FAULT. REPLACED EPSU BATTERY AT LT OVERWING EMERGENCY EXIT. OPS CHECKED GOOD PER AMM 33-51-38-000-002 AND 31-51-38-400-002.

Part: BEARING — CORRODED (LT MLG) · corrosion level 2 · airframe 16,966 hrs · 7,660 cycles

DURING C-4 CHECK, INSPECTION REPORTED LT MLG LWR BEARING ASSY CORRODED, PITTED AND DEFORMED. REMOVED CORROSION ON LT MLG SHOCK ABSORBER GLAND SEAL PER EA A9-32R-11439. PERFORMED FLUORESCENT PENETRANT INSPECTION PER AIRBUS NTM 51-80-00 PART 8, AND EA A9-32R-11439. NO CRACKS DETECTED.

Part: FLOOR PANEL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 16,966 hrs · 7,660 cycles

DURING C-4 CHECK, INSPECTION REPORTED CABIN FLOOR PANEL 222FF AT R1 ENTRYWAY CORRODED IN 3 AREAS. REPLACED FLOOR PANEL PER WORK CARD NR CP753-12.

Part: JOINT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 16,966 hrs · 7,660 cycles

DURING C-4 CHECK, INSPECTION REPORTED JOINT SHEET BETWEEN FR68 AND FR69, LT. SIDE JUST AFT OF L2 SILL, CORRODED. FABRICATED AND INSTALLED NEW JOINT SHEET PER SRM 53-41-14, SRM 51-42-11, AND AIRBUS DRAWING D534-80019.

Part: SUPPORT ANGLE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 16,966 hrs · 7,660 cycles

DURING C-4 CHECK, INSPECTION REPORTED SUPPORT ANGLE AT FR 69-70, RT SIDE OF AIRCRAFT UNDER WEB SUPPORT PLATE, CORRODED. REPLACED ANGLE SUPPORT AND WEB ASSY PER SRM 51-42-11 AND AIRBUS DWG D534-74180.

Part: ATTACH BRACKET — CORRODED (CABIN) · corrosion level 2 · airframe 16,966 hrs · 7,660 cycles

DURING C-4 CHECK, INSPECTION REPORTED MILD SURFACE CORROSION ON CABIN FLOORBOARD PANEL NR 262EF ATTACHMENT BRACKET. FABRICATED AND INSTALLED NEW CONNECTING BRACKET PER SRM 51-42-11 AND AIRBUS DRAWING D536-70099.

Part: FAIRING — CRACKED (NR 1 PYLON) · airframe 16,966 hrs · 7,660 cycles

DURING C-4 CHECK, INSPECTION REPORTED NR 1 ENGINE PYLON AFT LOWER FAIRING CRACKED. REPAIRED LOWER ENGINE PYLON FAIRING BY WELD PER EA A0-54T-11332. PERFORMED FLUORESCENT PENETRATE CHECK PER NDT MANUAL PART 6-51-80-00, PAGES 801-809.

Part: FLOOR PANEL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 16,966 hrs · 7,660 cycles

DURING C-4 CHECK, INSPECTION REPORTED FLOOR PANEL 221FF CORRODED ALONG INBD EDGE OF L1 DOOR THRESHOLD. REPLACED PANEL 221FF PER WORK CARD CP753-12 AND AMM 53-12-12-400-001.

Part: BUSHING — CRACKED (FUSELAGE) · airframe 16,966 hrs · 7,660 cycles

DURING C-4 CHECK, INSPECTION REPORTED I/B RT SEAT TRACK EXPANSION JOINT THROUGH BOLT BUSHING CRACKED AT FR35 TO FR36. REPLACED BOLT AND BUSHINGS PER SRM 51-42-11.

Part: BUSHING — BROKEN (FUSELAGE) · airframe 16,966 hrs · 7,660 cycles

DURING C-4 CHECK, INSPECTION REPORTED I/B LT SEAT TRACK EXPANSION JOINT THROUGH BOLT HAD BROKEN BUSHING AT FR35 TO FR36. REPLACED BOLT AND BUSHINGS PER SRM 51-42-11.

Part: FLOOR PANEL — CORRODED (CABIN) · corrosion level 2 · airframe 16,966 hrs · 7,660 cycles

DURING C-4 CHECK, INSPECTION REPORTED L2 DOOR THRESHOLD PANEL 261EF CORRODED. INSTALLED NEW FLOOR PANEL PER DRAWING D5367-1805.

Part: DUMMY RAIL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 16,966 hrs · 7,660 cycles

DURING C-4 CHECK, INSPECTION REPORTED FLOORBEAM CORRODED AT FR15, 5TH FLOORBEAM FROM LT. CENTER OF FUSELAGE ON AFT END. DUMMY RAIL AT STATION Y503.2 FOUND TO BE OUT OF LIMITS PER SRM 53-11-14, FIG. 103. REPLACED DUMMY RAIL AT STATION Y503.2 PER SRM 51-42-11 AND 53-41-14.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 16,966 hrs · 7,660 cycles

DURING C-4 CHECK, INSPECTION REPORTED CORROSION ON FLOOR SUPPORT NUT PLATE HOLES BETWEEN FRAMES 66 AND 68, AND 44 IN RIGHT OF CENTERLINE. REPLACED FLOORBEAM FR66 TO FR68 PER SRM 51-42-11 AND 51-21-00.

Part: FLOORBOARD — CORRODED (FUSELAGE) · corrosion level 2 · airframe 16,966 hrs · 7,660 cycles

DURING C-4 CHECK, INSPECTION REPORTED FLOORBEAM CORRODED AT FRAME 15, 6TH FLOORBEAM FROM RT CENTER OF FUSELAGE ON THE AFT END OF BEAM. BLENDED CORROSION AND PERFORMED HFEC PER SRM 51-75-12 AND EA A9-53R-11424.

Part: WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 16,966 hrs · 7,660 cycles

DURING C-4 CHECK, INSPECTION REPORTED CORROSION ON FLOOR WEB NEXT TO FUSELAGE BETWEEN FRAMES 69 AND 70. REPLACED SUPPORT ANGLE AND WEB PER SRM 51-42-11, ARM 51-44-11, AND AIRBUS DRAWING D534-74180.

Part: SUPPORT ANGLE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 16,966 hrs · 7,660 cycles

DURING C-4 CHECK, INSPECTION REPORTED CORROSION ON LT SIDE OF SUPPORT ANGLE THAT ATTACHES WEB SUPPORT PLATE BETWEEN FR69 AND FR70 AT FLOOR LEVEL. INSTALLED NEW WEB AND SUPPORT PER SRM 51-42-11, SRM 53-41-14, AND AIRBUS DRAWING D534-74180.

Part: WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 16,966 hrs · 7,660 cycles

DURING C-4 CHECK, INSPECTION REPORTED CORROSION ON WEB BETWEEN FR69 AND FR70, R/H NEXT TO FUSELAGE. INSTALLED NEW ANGLE AND WEB ASSY. PER SRM 51-42-11 AND DRAWING DE534-74180.

Part: SUPPORT ANGLE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 16,966 hrs · 7,660 cycles

DURING C-4 CHECK, INSPECTION REPORTED CORROSION ON SUPPORT ANGLE AT FR69 TO FR70, LT. SIDE UNDER SUPPORT WEB PLATE. REPLACED WEB AND SUPPORT ANGLE PER SRM 51-44-11, SRM 51-42-11, AND AIRBUS DRAWING D534-74180.

Part: FLOOR PANEL — CORRODED (CABIN) · corrosion level 2 · airframe 16,966 hrs · 7,660 cycles

DURING C-4 CHECK, INSPECTION REPORTED CORROSION ON THRESHOLD PANEL AT R2 DOOR. REMOVED CORROSION ON TOP AND BOTTOM SKIN PER SRM 51-22-00. ALLOWABLE SKIN REMOVED FOR CORROSION CLEAN-UP EXCEEDS LIMITS AND THRESHOLD IS BER. REPLACED PANEL.

Part: PANEL — CRACKED (LT PYLON) · airframe 16,966 hrs · 7,660 cycles

DURING C-4 CHECK, INSPECTION REPORTED LT PYLON PANEL 473AL CRACKED ON RADIUS OF INNER DOUBLER. STOP DRILLED CRACK AND WELDED PER EA A9-54R-11430. PERFORMED HFEC, NO DISCREPANCIES NOTED.

Part: BRACKET — WORN (NR 1 COWLING) · airframe 16,966 hrs · 7,660 cycles

DURING C-4 CHECK, INSPECTION REPORTED NR 1 ENGINE IB FWD COWL BRACE BRACKET WORN INTO THE ENGINE CASE. INSTALLED NEW BRACKETS AND HARDWARE ON NR 1 ENGINE CASE FOR THE FAN COWL HOLD OPEN ROD PER EA A9-72R-11428 AND CREATED RW 0000808.

Part: HOOK — WORN (L2 DOOR) · airframe 16,966 hrs · 7,660 cycles

DURING C-4 CHECK, INSPECTION REPORTED L2 DOOR GEARBOX ASSY HOOK WORN. REPLACED GEARBOX HOOK PER AMM 52-13-21-400-001, STEP 3C(17)(C) THRU (E).

Part: TIRE — FAILED (MLG) · airframe 14,078 hrs · 6,295 cycles

ON LANDING, BOTH NOSE TIRES BLEW. STOPPED ACFT ON RUNWAY. PERFORMED INSPECTION AFTER TIRE BURST. NO DAMAGE NOTED. REPLACED LT NOSE WHEEL & TIRE ASSEMBLY, P/N 3-1531-1, S/N 4964, TSI 690.80 &CSI 285 SINCE REPAIR, RT NOSE WHEEL & TIRE ASSEMBLY, P/N 3-1531-1, S/N 7017, TSI 690.8 & CSI 285 SINCE OVERHAUL, MOVED AIRCRAFT FROM RUNWAY. PERFORMED INSPECTION OF AXLE SLEEVES, NO DAMAGE NOTED. REPLACED LOWER TORSION LINK, P/N GA65227. DUE TO DAMAGE SUSTAINED FROM JACKING NOSE GEAR, PERFORMED INSPECTION AND OPERATIONAL CHECK OF NLG. NLG SLIDING TUBE LUG FOUND TO BE DAMAGED. REPLACED NLG SHOCK ABSORBER ASSY, P/N D23592020-1, S/N L1665, PERFORMED A HEAVY CHECK. PERFORMED GEAR SWING, ALL INDICATIONS NORMAL.

Part: BLOWER — SMOKE (CABIN PRESSURE) · airframe 13,519 hrs · 6,226 cycles

AIR TURNBACK, FLIGHT CREW REPORTED AVIONICS SMOKE INDICATION ON DEPARTURE. AIRCRAFT RETURNED TO CUN AND LANDED WITHOUT INCIDENT. PERFORMED OPERATIONAL CHECK OF EXTRACTION AND BLOWER FAN BY MCDU PER MM 21-26-00-710-001. NO FAULTS DETECTED.

Part: B-NUT — LOOSE (HYD SYSTEM) · airframe 21 hrs · 14 cycles

DURING TRAINING FLIGHT, FLIGHT CREW REPORTED LOSS OF GREEN HYDRAULIC SYSTEM. AN EMERGENCY WAS DECLARED AND AIRCRAFT LANDED IN PHX WITHOUT INCIDENT. AIRCRAFT WAS TOWED OFF THE RUNWAY DUE TO THE LOSS OF THE NOSE WHEEL STEERING. THE B-NUT ON THE HYDRAULIC PRESSURE LINE FOR THE RT MLG DOOR UPLOCK WAS FOUND TO BE LOOSE. THE HYDRAULIC LINE WAS RETORQUED AND THE SYSTEM WAS SERVICED.