N804FR

Part: HINGE FITTING — DAMAGED (NR 4 SPOILER) · airframe 15,198 hrs · 7,857 cycles

DURING C CHECK INSPECTION, THE CENTER HINGE ANTI-ROTATION LUG FOR THE RIGHT NUMBER 4 SPOILER ACTUATOR BOLT WAS FOUND DAMAGED. MAINTENANCE REMOVED THE DAMAGED ASSEMBLY AND PERFORMED A "MAJOR REPAIR" IN ACCORDANCE WITH THE REQUIREMENTS OF EA A8-57R-12379. UPON COMPLETION OF THE REPAIR, THE NUMBER 4 SPOILER WAS RE-INSTALLED, INSPECTED, TESTED AND FOUND TO BE ACCEPTABLE.

Part: PRESSURE SWITCH — INOPERATIVE (CABIN PRESSURE) · airframe 15,198 hrs · 7,857 cycles

DURING C CHECK AND FUNCTIONAL TEST, THE ALTITUDE PRESSURE SWITCH FAILED ITS FUNCTIONAL TEST. MAINTENANCE REMOVED AND REPLACED THE ALTITUDE PRESSURE SWITCH IN ACCORDANCE WITH THE REQUIREMENTS OF AMM 35-23-15 PB 401. FOLLOWING ITS INSTALLATION AND INSPECTION, IT OPERATIONALLY CHECKED GOOD.

Part: HINGE FITTING — DAMAGED (NR 4 SPOILER) · airframe 15,198 hrs · 7,857 cycles

DURING C CHECK INSPECTION, THE CENTER HINGE ANTI-ROTATION LUG FOR THE LEFT NUMBER 4 SPOILER WAS FOUND DAMAGED. MAINTENANCE REMOVED THE DAMAGED ASSEMBLY AND PERFORMED A "MAJOR REPAIR" ON ACCORDANCE WITH THE REQUIREMENTS OF EA A8-57R-12379. UPON COMPLETION OF THE REPAIR THE NUMBER 4 SPOILER WAS RE-INSTALLED, INSPECTED, TESTED AND FOUND TO BE ACCEPTABLE.

Part: HINGE BRACKET — DAMAGED (NR 2 SPOILER) · airframe 15,198 hrs · 7,857 cycles

DURING C CHECK INSPECTION, THE CENTER HINGE ANTI-ROTATION BRACKET FOR THE LEFT NUMBER 2 SPOILER WAS FOUND DAMAGED. MAINTENANCE REMOVED THE DAMAGED ASSEMBLY AND PERFORMED A "MAJOR REPAIR" IN ACCORDANCE WITH THE REQUIREMENTS OF EA A8-57R-12381. UPON COMPLETION OF THE REPAIR, THE NUMBER 2 SPOILER WAS RE-INSTALLED, INSPECTED, TESTED AND FOUND TO BE ACCEPTABLE.

Part: HINGE FITTING — DAMAGED (NR 3 SPOILER) · airframe 15,198 hrs · 7,857 cycles

DURING C CHECK INSPECTION, THE CENTER HINGE ANTI-ROTATION LUG FOR THE RIGHT NUMBER 3 SPOILER WAS FOUND DAMAGED. MAINTENANCE REMOVED THE DAMAGED ASSEMBLY AND PERFORMED A "MAJOR REPAIR" IN ACCORDANCE WITH THE REQUIREMENTS OF EA A8-57R-12379. UPON COMPLETION OF THE REPAIR, THE NUMBER 3 SPOILER WAS RE-INSTALLED, INSPECTED, TESTED AND FOUND TO BE ACCEPTABLE.

Part: HINGE FITTING — DAMAGED (NR 3 SPOILER) · airframe 15,198 hrs · 7,857 cycles

DURING C CHECK INSPECTION, THE CENTER HINGE ANTI-ROTATION LUG FOR THE LEFT NUMBER 3 SPOILER WAS FOUND DAMAGED. MAINTENANCE REMOVED THE DAMAGED ASSEMBLY AND PERFORMED A "MAJOR REPAIR" IN ACCORDANCE WITH THE REQUIREMENTS OF EA A8-57R-12379. UPON COMPLETION OF THE REPAIR, THE NUMBER 3 SPOILER WAS RE-INSTALLED, INSPECTED, TESTED AND FOUND ACCEPTABLE.

Part: PRESSURE SWITCH — FAILED (CABIN PRESSURE) · airframe 15,198 hrs · 7,857 cycles

DURING C CHECK INSPECTION AND FUNCTIONAL TEST, THE CABIN PRESSURE SWITCH (16WR) FAILED TO DROP THE OXYGEN MASKS. MAINTENANCE REMOVED AND REPLACED THE CABIN PRESSURE SWITCH (16WR) IN ACCORDANCE WITH THE REQUIREMENTS OF AMM 35-23-15-400-001. FOLLOWING ITS INSTALLATION AND INSPECTION IT WAS TESTED AND FOUND OKAY.

Part: RELEASE CABLE — INOPERATIVE (ESCAPE HATCH) · airframe 15,198 hrs · 7,857 cycles

DURING C CHECK INSPECTION AND FUNCTIONAL TESTING, THE LEFT, OVERWING, EMERGENCY ESCAPE HATCH RELEASE CABLE WAS BINDING AND WOULD NOT RETRACT. MAINTENANCE REMOVED AND REPLACED THE CABLE IN ACCORDANCE WITH THE REQUIREMENTS OF AMM 25-62-43-400-001. UPON REPLACEMENT OF THE CABLE, IT WAS TESTED AND INSPECTED AND FOUND TO OPERATE IN ACCORDANCE WITH THE REQUIREMENTS OF AMM 52-21-00 PB 501.

Part: RELEASE CABLE — INOPERATIVE (ESCAPE HATCH) · airframe 15,198 hrs · 7,857 cycles

DURING C CHECK INSPECTION AND FUNCTIONAL TESTING, THE RIGHT, OVERWING, EMERGENCY ESCAPE HATCH RELEASE CABLE WAS BINDING AND WOULD NOT RETRACT. MAINTENANCE REMOVED AND REPLACED THE CABLE IN ACCORDANCE WITH THE REQUIREMENTS OF AMM 25-62-43-400-001. UPON REPLACEMENT OF THE CABLE, IT WAS TESTED AND INSPECTED AND FOUND TO OPERATE IN ACCORDANCE WITH THE REQUIREMENTS OF AMM 52-21-00 PB 501.

Part: FLOOR PANEL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 15,198 hrs · 7,857 cycles

DURING C CHECK INSPECTION, CARGO FLOOR PANEL 262FF, LOCATED BETWEEN FRAMES 66 AND 68, WAS FOUND TO HAVE CORROSION ON ITS LOWER SURFACE. MAINTENANCE REMOVED AND REPLACED THE FLOOR PANEL IN ACCORDANCE WITH THE REQUIREMENTS OF AMM 53-42-12 PB 401. FOLLOWING THE COMPLETION OF THE INSTALLATION, THE NEW FLOOR PANEL WAS INSPECTED AND FOUND ACCEPTABLE.

Part: FLOOR PANEL — CORRODED (FUSELAGE) · airframe 15,198 hrs · 7,857 cycles

DURING C CHECK INSPECTION, CARGO FLOOR PANEL 261FF, LOCATED BETWEEN FRAMES 66 AND 68, WAS FOUND TO HAVE CORROSION ON ITS LOWER SURFACE. MAINTENANCE REMOVED AND REPLACED THE FLOOR PANEL IN ACCORDANCE WITH THE REQUIREMENTS OF AMM 53-42-12 PB 401. FOLLOWING THE COMPLETION OF THE INSTALLATION, THE NEW FLOOR PANEL WAS INSPECTED AND FOUND ACCEPTABLE.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 15,198 hrs · 7,857 cycles

DURING C CHECK INSPECTION, THE FLOOR SUPPORT AT Y1292, BETWEEN FRAME 66 THROUGH FRAME 69, HAS CORROSION AT VARIOUS NUT CLIP HOLE LOCATIONS. MAINTENANCE REMOVED AND REPLACED THE FLOOR SUPPORT IN ACCORDANCE WITH THE REQUIREMENTS OF SRM 51-42-11, PARAGRAPH 7. INSTALLATION OF HARDWARE WAS DONE IN ACCORDANCE WITH THE REQUIREMENTS OF EA A8-53R-12360. UPON COMPLETION OF THE INSTALLATION, IT WAS INSPECTED AND FOUND ACCEPTABLE.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 15,198 hrs · 7,857 cycles

DURING C CHECK INSPECTION, CORROSION WAS FOUND ON THE INBOARD, RIGHT SIDE OF THE FLOORBEAM, FORWARD OF THE SPLICE AT FRAME 68 AND -Y1292, AT THE SECOND NUT PLATE HOLE. MAINTENANCE REMOVED AND REPLACED THE FLOORBEAM AND RELATED COUPLINGS IN ACCORDANCE WITH THE REQUIREMENTS OF SRM 51-42-11, PARAGRAPH 7. THE MAINTENANCE ACTION REQUIRED TWO FLOORBEAMS, PART NUMBERS D5347217220500 AND D5347217220390. UPON COMPLETION OF THE MAINTENANCE ACTION, THE INSTALLATION WAS INSPECTED AND FOUND ACCEPTABLE.

Part: DUMMY RAIL — CORRODED · corrosion level 2 · airframe 15,198 hrs · 7,857 cycles

DURING C-CHECK INSPECTION, CORROSION WAS FOUND ON THE DUMMY RAIL SURFACE AND IN NUT CLIP HOLE AT STATION Y503.2 (LT SIDE) JUST FORWARD OF FRAME 16 ON THE IB SIDE OF THE BEAM. DRILLED A NEW DUMMY RAIL IAW THE REQUIREMENTS OF SRM 51-44-11 AND INSTALLED THE DUMMY RAIL IAW THE REQUIREMENTS OF SRM 51-42-11. AFTER THE MAINTENANCE ACTION WAS COMPLETED IT WAS INSPECTED AND FOUND ACCEPTABLE. REFERENCE NON-ROUTINE C035856.

Part: THRESHOLD — CORRODED (FUSELAGE) · corrosion level 2 · airframe 155,198 hrs · 7,857 cycles

DURING C CHECK INSPECTION, CORROSION WAS FOUND ON THE BOTTOM SIDE OF THE R1 THRESHOLD STRIP. MAINTENANCE REMOVED AND REPLACED THE THRESHOLD STRIP IN ACCORDANCE WITH THE REQUIREMENTS OF AMM 53-12-12 PB 401. UPON COMPLETION OF THE INSTALLATION OF THE THRESHOLD STRIP, IT WAS INSPECTED AND FOUND TO BE ACCEPTABLE.

Part: SHEAR PLATE — DAMAGED · airframe 15,198 hrs · 2,051 cycles

DURING C CHECK INSPECTION, THE AFT SHEAR PLATE ON THE LEFT SIDE OF THE FUSELAGE, JUST AFT OF FRAME 69, HAD FOUR BLIND FASTENERS SHEARED. MAINTENANCE REMOVED THE SHEARED FASTENERS, REPLACED THE SHEAR PLATE AND INSTALLED A NEW SHEAR PLATE AND FASTENERS IN ACCORDANCE WITH THE REQUIREMENTS OF SRM 51-42-11. FOLLOWING THE COMPLETION OF THE MAINTENANCE ACTION, THE SHEAR PLATE INSTALLATION WAS INSPECTED AND FOUND TO BE ACCEPTABLE.

Part: SILL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 15,198 hrs · 7,857 cycles

DURING C CHECK INSPECTION, THE L2 DOOR SILL, AFT, OUTBOARD NUTPLATE HOLE FOR THE GIRT BAR BLANKING PLATE SHOWED SIGNS OF CORROSION. MAINTENANCE REMOVED THE L2 DOOR SILL IN ACCORDANCE WITH THE REQUIREMENTS OF SRM 51-52-11. A NEW DOOR SILL WAS INSTALLED IN ACCORDANCE WITH THE REQUIREMENTS OF SRM 51-42-11. UPON COMPLETION OF THE REPLACEMENT OF THE L2 DOOR SILL, THE INSTALLATION WAS INSPECTED AND FOUND ACCEPTABLE.

Part: SHEAR PLATE — CORRODED (FRAME) · corrosion level 2 · airframe 15,198 hrs · 7,857 cycles

DURING C-CHECK INSPECTION, AFT SHEAR PLATE ON THE RT, AFT SIDE OF FRAME 69 HAD CORROSION AT THE NUT PLATE CLIP HOLES. MAINTENANCE REPLACED THE SHEAR PLATE IAW THE REQUIREMENTS OF SRM 51-72-11, PARAGRAPH 6 AND SRM 51-42-11, PAGES 6 AND 7. FOLLOWING COMPLETION OF THE MAINTENANCE ACTION, THE REPLACEMENT WAS INSPECTED AND FOUND ACCEPTABLE. REFERENCE NON-ROUTINE C035788.

Part: FLOOR PANEL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 15,198 hrs · 2,051 cycles

DURING C CHECK INSPECTION, FLOOR PANEL 222FF WAS FOUND TO HAVE CORROSION ON THE BOTTOM SIDE. THE FLOOR PANEL WAS REMOVED AND REPLACED IN ACCORDANCE WITH THE REQUIREMENTS OF SRM 51-42-11, PARAGRAPH 7. FOLLOWING THE COMPLETION OF THE INSTALLATION OF THE FLOOR PANEL, THE INSTALLATION WAS INSPECTED AND FOUND ACCEPTABLE.

Part: SHEAR PLATE — LOOSE · airframe 15,198 hrs · 7,857 cycles

DURING C CHECK INSPECTION, THE FORWARD SHEAR PLATE, JUST AFT OF FRAME 68, HAD 7 SOLID RIVETS SHEARED WHERE THE PLATE ATTACHES TO THE FLOORBEAM. MAINTENANCE REMOVED THE SHEARED RIVETS AND REPLACED THEM WITH LOCK FASTENER IN ACCORDANCE WITH THE REQUIREMENTS OF EA A8-53R-12360. UPON COMPLETION OF THE MAINTENANCE ACTION, THE SHEAR PLATE WAS INSPECTED AND FOUND TO BE ACCEPTABLE.

Part: THRESHOLD — CORRODED (FUSELAGE) · corrosion level 2 · airframe 15,198 hrs · 7,857 cycles

DURING C CHECK INSPECTION, CORROSION WAS FOUND ON THE BOTTOM SIDE OF THE L1 THRESHOLD STRIP. MAINTENANCE REMOVED AND REPLACED THE THRESHOLD STRIP IN ACCORDANCE WITH THE REQUIREMENTS OF AMM 53-12-12 PB 401. UPON COMPLETION OF THE INSTALLATION OF THE THRESHOLD STRIP IT WAS INSPECTED AND FOUND TO BE ACCEPTABLE.

Part: SHEAR PLATE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 15,198 hrs · 7,857 cycles

DURING C CHECK INSPECTION, CORROSION WAS FOUND ON THE BOTTOM OF THE AFT SHEAR PLATE AT FRAME 69, ON THE LEFT SIDE OF THE FUSELAGE. MAINTENANCE REMOVED AND REPLACED THE AFT SHEAR PLATE IN ACCORDANCE WITH THE REQUIREMENTS OF SRM 51-42-11. FOLLOWING COMPLETION OF THE INSTALLATION, THE AFT SHEAR PLATE WAS INSPECTED AND FOUND TO BE ACCEPTABLE.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 15,198 hrs · 7,857 cycles

DURING C-CHECK MAINTENANCE ACTIONS, PREVIOUS, TEMPORARILY REPAIRED LIGHTENING STRIKE DAMAGE WAS PERMANENTLY REPAIRED. THE REPAIR WAS ACCOMPLISH IAW TDI/RW 0000838 ON THE LT FORWARD FUSELAGE. THE REPAIR WAS ACCOMPLISHED IAW THE REQUIREMENTS OF EA A8-53R-10670, REV E. THIS ACTION CLOSES OUT TDI/RW 000478. HOLES 1, 2 AND 3 WILL BE PERMANENTLY REPAIRED WITHIN 4680 LANDINGS. SEE NON-ROUTINE C035074.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 14,749 hrs · 7,636 cycles

MAINTENANCE REPORTED SEAT-MOUNTED EMERGENCY LIGHTS AT ROW 22 ABC INOPERATIVE. REMOVED AND REPLACED SEAT-MOUNTED EMERGENCY LIGHTS AT ROW 22 ABC IAW AMM 33-51-19, PB401. OPS CHECK GOOD.

Part: LIGHT — INOPERATIVE (ROW 15ABC) · airframe 14,388 hrs · 7,455 cycles

DURING HEAVY SERVICE CHECK, INSPECTION REPORTED 1 LAMP INOPERATIVE IN SEAT ROW 15ABC EMERGENCY SEAT MOUNTED LIGHT. REMOVED AND REPLACED SEAT MOUNTED EMERGENCY LIGHT ASSY AT ROW 15ABC IAW AMM 33-51-19-PB401. OPS CHECK GOOD.

Part: LAMP — INOPERATIVE (EMERGENCY LIGHT) · airframe 14,388 hrs · 7,455 cycles

DURING HEAVY SERVICE CHECK, INSPECTION REPORTED 1 LAMP TOP INOPERATIVE IN L1 DOOR LOWER EMERGENCY EXIT SIGN. RELAMPED WALL MOUNTED EXIT SIGN BY L1 DOOR IAW AMM 33-51-13-PB401. OPS CHECKED GOOD.

Part: ELECTRICAL BOX — BURNED OUT (ENTERTAIN SYS) · airframe 10,541 hrs · 5,467 cycles

FLT CREW REPORTED A STRONG ELECTRICAL-TYPE ODOR NEAR ROW 17 & AFT GALLEY AREA ENROUTE FOR LAST 30 MINS OF FLT & AFTER LANDING. FOUND SEB ON ROW 17 DEF BAD. DEFERRED LIVE TV SYS PER MEL 44-20-01AA, SEB AT 17E REPLACED PER LTV AMM 44-25-00 AND OPS CHECKED GOOD. PERFORMED SYS INTEGRITY CHK PER LTV AMM 44-25-00. NO DEFECTS NOTED. A REPORT WAS RECEIVED FROM LIVE TV ON THE INVESTIGATION INTO THE FAILURE OF SEB. AN INTERNAL SHORT WITHIN SEB TRANSFORMER T2 CAUSED +15VDC TO BE DELIVERED TO +5VDC CIRCUIT. THIS OVER-VOLTAGE TO +5VDC CIRCUIT CAUSED SEVERAL CAPACITORS LOCATED ON UNIT CIRCUIT CARD ASSY TO BE THERMALLY STRESSED. ELECTRICAL ODOR EXPERIENCED ON ACFT ATTRIBUTED TO THERMAL STRESS OF THE CAPACITORS.

Part: PRESSURE SWITCH — INOPERATIVE (FUEL SYSTEM) · airframe 10,288 hrs · 5,339 cycles

AIR TURNBACK. FLIGHT CREW REPORTED ENGINE 2 FUEL FILTER CLOG INDICATION. REPLACED NR 2 ENGINE MAIN FUEL FILTER AND FUEL DIFFERENTIAL PRESSURE SWITCH. RAN NR 2 ENGINE, FAULT CLEARED. OPS AND LEAK CHECKED NORMAL PER 73-34-15 PB 401 AND 73-11-10 PB 301.

Part: DUCT — MISINSTALLED (WATER EXTRACTOR) · airframe 4,248 hrs · 2,148 cycles

ON ARRIVAL, CREW REPORTED FUMES IN COCKPIT. F/A REPORTED SMELL IN AFT CABIN. A/C RETURNED TO MDW & LANDED W/O INCIDENT. REMOVED BELLY FAIRINGS FOR ACCESS TO LT PACK. INSPECTED PACK DUCTING & FOUND VASELINE ON DUCT SEALS & JOINTS. REMOVED WATER EXTRACTOR SEALS & JOINTS, REMOVED VASELINE, & RENSTALLED WATER EXTRACTOR. REMOVED DUCT BETWEEN MAIN HEAT EXCHANGER & ACM. CLEANED SEALS & JOINTS & REMOVED VASELINE. REINSTALLED DUCT. REMOVED ANTI-ICE VALVE/PRIMARY HEAT EXCHANGER BYPASS DUCT. CLEANED VASELINE FROM SEALS & JOINTS. REINSTALLED DUCT. REMOVED REHEATER DUCTING. CLEANED RESIDUE FROM SEALS & DUCTS. REINSTALLED REHEATER DUCTING. PERFORMED OPS CHECK OF LT PACK USING APU BLEED. OPS TEST NORMAL.

Part: COMPUTER — INOPERATIVE (ELAC 2) · airframe 3,258 hrs · 1,730 cycles

AIR TURNBACK. FLIGHT CREW REPORTED FLIGHT CONTROL RIGHT AILERON FAULT ON ECAM. PERFORMED OVERWEIGHT LANDING AND LANDED IN DEN WITHOUT INCIDENT. CABIN CREW REPORTED HYDRAULIC FLUID COMING FROM LT WING AND AN ELECTRICAL SMOKE ODOR WHEN LANDING GEAR WAS EXTENDED. REPLACED NR 1 ELAC AND CHECKED OKAY. COMPLIED WITH OVERWEIGHT INSPECTION PER ANM 05-51-11-991-016 FIG 602.1. REPLACED LEAKING NR 2 SPOILER SERVO PER AMN 27-64-51-400-004. PERFORMED ENGINE RUN. RAN PACKS OFF ENGINE BLEED. NO SMOKE ODOR NOTED. COULD NOT DUPLICATE REPORTED ODOR.

Part: COMPUTER — INOPERATIVE (FLT CONTROL) · airframe 2,482 hrs · 1,340 cycles

ON CLIMB OUT, FLIGHT CREW REPORTED ECAM: FLT CNT. FLT CTR 1 NR 2. RAN ECAM. RETURNED TO DEN WITHOUT INCIDENT AND LANDED OVERWEIGHT. TROUBLESHOT FLT CONT 1 AND 2 IAW TSM 27-93-00-810-949. REPLACED ELAC 1 IAW AMM 27-93-34-000-001. ELAC NR 1 OPS CHECKED NORMAL IAW AMM 27-93-00-710-001. PERFORMED OVERWEIGHT LANDING INSPECTION IAW AMM 05-51-11-991-016. CHECKED OKAY.