N938FR

Part: UNKNOWN — ODOR (CABIN) · airframe 46,507 hrs · 23,063 cycles

DIVERTED TO ABQ F/A'S SMELLED ODOR IN MID TO AFT CABIN. ODOR WAS DESCRIBED AS DIRTY SOCKS. STRONGEST IN AFT PART OF AIRCRAFT. PERFORMED TSM 71-00-00-810-802-A, RAN ENG'S 1 & 2, APU NO LEAKS NOTED, NO SMELLS NOTED AT THIS TIME. OK FOR SERVICE.

Part: BATTERY — FAILED (EMERGENCY LIGHTS) · airframe 43,203 hrs · 21,486 cycles

EPSU 10WL BATTERY FAILED TO TEST. REMOVED & REPLACED THE BATTERY AND OPERATIONAL CHECKED OK IAW AMM 33-51-38, PAGE BLOCK 401.

Part: HMU — FAILED (NR 1 ENGINE) · airframe 37,264 hrs · 18,682 cycles

NUMBER 1 ENG ROLL BACK TO FLIGHT IDLE AT CRUISE FL320. UNABLE TO GET ENG TO RESPOND. SHUTDOWN ENG. DESENDED TO FL260 UNSUCCESSFUL ATTEMPT TO RESTART ENG. EMER DECLARED, DIVERTED. TROUBLESHOOTING REVEALED FAILED HMU, REPLACED HMU IAW LP960754.

Part: BATTERY — FAILED (CABIN) · airframe 34,492 hrs · 17,289 cycles

DISCREPANCY, RT EMER EXIT LIGHT POWER SUPPLY BATTERY FAILED EMER LIGHT TEST. R & R RT EMER EXIT LIGHT POWER BATTERY IAW AMM 33-51-38-000-002-A & AMM 33-51-38-400-002-A. OPERATIONAL CHECK WAS GOOD.

Part: UPLOCK — MALFUNCTIONED (NLG) · airframe 34,147 hrs · 17,129 cycles

LANDING GEAR DOORS NOT CLOSED. ECAM AFTER TAKEOFF & LG NOT UPLOCKED. R & R NLG UPLOCK ASSEMBLY 2530GM. OPERATIONS TESTED GOOD.

Part: BATTERY — FAILED (CABIN) · airframe 33,883 hrs · 17,007 cycles

EPSU BATTERIES 10WL & 13WL REQUIRE REPLACEMENT. REMOVED EPSU BATTERIES 10WL & 13WL IAW AMM 33-51-38-400-002-A. OPERATIONS CHECKED GOOD.

Part: BATTERY — FAILED (CABIN) · airframe 33,883 hrs · 17,007 cycles

EPSU BATTERIES 10WL & 13WL REQUIRE REPLACEMENT. REMOVED EPSU BATTERIES 10WL & 13WL IAW AMM 33-51-38-400-002-A. OPERATIONS CHECKED GOOD.

Part: FAN — FAILED (ZONE 100) · airframe 28,537 hrs · 14,105 cycles

BLOWER FAN VIBRATION NOTED IN FLIGHT, BURNING ELECTRICAL ODOR AS WELL. BLOWER FAN TURNED OFF, VIBRATION AND ODOR DISSIPATED. R & R AVIONICS VENT FAN (FIN 18HQ). OPS CHECK NORMAL. IAW AMM 21-26-51 PB 401. NO MORE ELECTRICAL BURNING ODOR TROUBLESHOT IAW TSM 24-00-00-810-823-A.

Part: LIGHT — BURNED OUT (CABIN) · airframe 27,484 hrs · 13,549 cycles

OVERWING EXIT HANDLE LIGHT INOPERATIVE. RT OVERWING EXIT HANDLE LIGHT INOPERATIVE. REPLACED LIGHT ASSY, OP'S NORMAL IAW AMM 33-51-11 PB 401.

Part: BATTERY — DISCHARGED (EMERGENCY LIGHT) · airframe 21,544 hrs · 10,520 cycles

C-CHECK: NON ROUTINE NR 61090; EMERGENCY LIGHT EPSU (12WL) BATTERY FAILS SYS TEST. R & R EMERGENCY LIGHT BATTERY 12WL IAW AMM 33-51-38, PB 401. PERFOMED OPS CHECK IAW AMM 33-51-710-001. OPS TEST GOOD.

Part: BATTERY — DISCHARGED (EMERGENCY LIGHTS) · airframe 21,544 hrs · 10,520 cycles

C-CHECK: NON ROUTINE NR 61089; EMERGENCY LIGHT EPSU (11WL) BATTERY FAILS SYS TEST. R & R EMERGENCY LIGHT BATTERY 11WL IAW AMM 33-51-38 PB 401. PERFOMED OPS CHECK IAW AMM 33-51-710-001. OPS TEST GOOD.

Part: LINK — BUCKLED (MLG) · airframe 20,513 hrs · 10,016 cycles

PILOT REPORT, LP 551794 ITEAM P-1, ECAM MESSAGE ON FLIGHT, FO PROPES FAULT, LP 551794 ITEAM P-2, ECAM MESSAGE IN FLIGHT REVERSER NR 1 FAULT. LP 551795 ITEM P-1, ECAM MESSAGE AFTER LANDING, LANDING GEAR SYS DISAGREE FAULT LP 551795 P-2, ECAM MESSAGE AFTER LANDING , BRAKES/NOSE WHEEL STEERING MINOR FAULT. REVERSER ONE FAULT TROUBLESHOT TO RT MLG UPPER SLAVE LINK DAMAGED. REPLACED THE LINK IAW CMM 32-12-25 P. 739. CHECKED ADJUSTMENT OF PROXIMITY SENSOR (20GA) IAW AMM 32-31-73-820-002. ECAM MESSAGE FOR FO PROBES , LANDING GEAR SYS DISAGREE AND BRAKES/NOSE WHEEL STEERING WERE INITILLY CLEARED BEFORE FERRY FLIGHTBY PERFORMING RESET AND BITE CHECK OF NR ONE LGCIU. MESSAGES WERE ONCE AGAIN GENERATED DURING FERRY FLIGHT. AFTER FERRY FLIGHT RT MLG SLAVE LINK WAS REPLACED AND ADJUST OF PROXIMITY SENSOR (20GA)WAS ACCOMPLISHED. OPS TEST OF THE SYS RELATED TO ECAM MESSAGE WERE PERFORM WITH NO FAULTS NOTED.

Part: VALVE — FAILED (CABIN AIR) · airframe 19,463 hrs · 9,494 cycles

DUAL BLEED FAILURE. REPLACED NR 1 AND NR 2 ENGINE FAN AIR VALVES. REF AMM 36-11-54-400-001. REPLACED NR 1 ENGINE FAN AIR VALVE THERMOSTAT. REF AMM 36-11-43-400-001. FAN AIR VALVE THERMOSTAT PN 342B040000, SN 05587. FAN AIR VALVE NR 1 ENGINE PN 6730F010000, SN 6730-03664. FAN AIR VALVE NR 2 ENGINE PN 6730F010000, SN 6730-03663.

Part: ROD — LOOSE (NLG DOOR) · airframe 17,672 hrs · 8,667 cycles

MX NOTED THE RT FWD NLG DOOR IS CRACKED TOP TO BOTTOM AFT END OF DOOR AND FOUND AFT DOOR ROD ASSY WAS COMING UNSCREWED ALLOWING THE AFT DOOR TO HANG DOWN AND THE FWD DOOR CAUGHT ON THE AFT DURING GEAR RETRACTION DAMAGING THE FWD DOOR. MX REMOVED AND REPLACED BOTH ROD ASSEMBLIES ON THE RT FWD NLG AND ROD ASSEMBLIES WERE RIGGED AND THE NLG RETRACT TESTED NORMAL IAW AMM 32-31-00-720-003.

Part: FLOOR PANEL — CORRODED (ZONE 200) · airframe 16,687 hrs · 8,214 cycles

DURING C3 C-CHECK, INSP NOTED THAT FLOOR PANEL 261FF WAS CORRODED BEYOND ALLOWABLE LIMITS. MX REMOVED AND REPLACED THE FLOOR PANEL IAW C-CHECK TASK CARD.

Part: BLANKING PLATE — CORRODED (ZONE 200) · airframe 16,687 hrs · 8,214 cycles

DURING C3 C-CHECK, INSP NOTED THE L2 DOOR FWD BLANKING PLATE WAS CORRODED ON THE UPPER SURFACE. MX INSTALLED NEW BLANKING PLATE IAW AMM 52-13-31-400-007.

Part: FLOOR PANEL — CORRODED (ZONE 200) · airframe 16,687 hrs · 8,214 cycles

DURING C3 C-CHECK, INSP NOTED THAT FLOOR PANEL 262FF WAS CORRODED BEYOND ALLOWABLE LIMITS. MX REMOVED AND REPLACED THE FLOOR PANEL IAW C-CHECK TASK CARD.

Part: BLANKING PLATE — CORRODED (ZONE 200) · airframe 16,687 hrs · 8,214 cycles

DURING C3 C-CHECK, INSP NOTED THE L2 DOOR AFT BLANKING PLATE WAS CORRODED ON THE UPPER SURFACE. MX INSTALLED NEW BLANKING PLATE IAW AMM 52-13-31-400-007.

Part: BLANKING PLATE — CORRODED (ZONE 200) · airframe 16,687 hrs · 8,214 cycles

DURING DEN C3 C-CHECK, INSPECTION THE R2 DOOR FWD BLANKING PLATE WAS CORRODED. MX INSTALLED NEW BLANKING PLATE IAW AMM 52-13-31-400-007.

Part: BLANKING PLATE — CORRODED (ZONE 200) · airframe 16,687 hrs · 8,214 cycles

DURING C3 C-CHECK, INSPECTION NOTED THE R2 DOOR AFT BLANKING PLATE WAS CORRODED. MX INSTALLED NEW BLANKING PLATE IAW AMM 52-13-31-400-007.

Part: FLOORBEAM — CORRODED (ZONE 100) · airframe 16,687 hrs · 8,214 cycles

DURING C3 C-CHECK, INSP NOTED CORROSION ON FLOORBEAM -Y1292, AFT OF FRAME 68 COUPLING SPLICE POINT. MX REMOVED AND REPLACED THE FLOORBEAM IAW SRM 53-00-14, 51-44-11 AND 51-42-11.

Part: FLOORBEAM — CORRODED (ZONE 200) · airframe 16,687 hrs · 8,214 cycles

DURING C3 C-CHECK INSP NOTED, THE AFT GALLEY HAS CORROSION AROUND THE NUT CLIP HOLES FLOORBEAM 1292, LT SIDE BETWEEN FRAME 66 AND FRAME 68. MX REMOVED AND REPLACED FLOORBEAMS IAW SRM 51-42-11, SRM 53-00-14 AND SRM 51-72-11.

Part: SHEAR PLATE — CORRODED (ZONE 200) · airframe 16,687 hrs · 8,214 cycles

DURING C3 C-CHECK, INSP NOTED AFT GALLEY LT LATERAL SHEAR PLATE CORRODED BETWEEN FRAME 68 AND FRAME 70. MX REMOVED AND REPLACED SHEAR PLATE IAW SRM 51-42-11, SRM 51-44-11 AND SRM 51-72-11.

Part: SHEAR PLATE — CORRODED (ZONE 200) · airframe 16,687 hrs · 8,214 cycles

DURING C3 C-CHECK, INSP NOTED AFT GALLEY RT LATERAL SHEAR PLATE CORRODED BETWEEN FRAME 68 AND FRAME 70. MX REMOVED AND REPLACED SHEAR PLATE IAW SRM 51-42-11 AND SRM 51-44-11.

Part: SUPPORT — CRACKED (NR 2 NACELLE) · airframe 16,687 hrs · 8,214 cycles

REFERENCE NON-ROUTINE C071806. DURING DEN C3 C-CHECK, INSP NOTED THE NR 2 ENG OTBD PYLON RIB SUPPORT WAS CRACKED ABOUT RIB 7. MX REMOVED AND REPLACED SUPPORT IAW SRM 51-42-11, SRM 51-44-11, SRM 51-26-00, SRM 54-52-12 AND SRM 51-42-00.

Part: FLOORBEAM — CORRODED (ZONE 100) · airframe 16,687 hrs · 8,214 cycles

DURING C3 C-CHECK, INSP, NOTED CORROSION AROUND THE NUT CLIP HOLES ON FLOORBEAM 1292 (RT) BETWEEN FRAME 66 AND FRAME 68. MX REMOVED AND REPLACED THE FLOORBEAM IAW SRM 53-00-14, 51-42-11 AND 51-44-11.

Part: BUSHING — UNSECURE (R1 DOOR) · airframe 12,219 hrs · 5,955 cycles

FLIGHT CREW NOTED THE R1 DOOR WOULD NOT LATCH IN THE OPEN POSITION. MAINTENANCE RESECURED THE GUST LOCK BUSHING IN ACCORDANCE WITH AMM 52-11-00 PB 501.

Part: BUSHING — UNSECURE (R1 DOOR)

FLIGHT CREW NOTED THE R1 DOOR WOULD NOT LATCH IN THE OPEN POSITION. MAINT RESECURED THE GUST LOCK BUSHING IAW THE AMM 52-11-00-PB501. UPON COMPLETION OF THE REPAIR. IT WAS INSPECTED AND FOUND ACCEPTABLE. (K)

Part: FRAME — DAMAGED (FUSELAGE) · airframe 11,484 hrs · 5,590 cycles

DURING C2 C CHECK INSPECTION NOTED FRAME 73 DAMAGED FROM STRINGER 26 LEFT TO 26 RIGHT. MAINTENANCE REPAIRED FRAME IN ACCORDANCE WITH THE REQUIREMENTS OF EA A9-53R-30262 AND SRM 51-42-11 PARAGRAPH 6. UPON COMPLETION OF THE REPAIR IT WAS INSPECTED AND FOUND ACCEPTABLE.

Part: SHEAR TIE — DAMAGED (FUSELAGE) · airframe 11,484 hrs · 5,590 cycles

DURING C2 C CHECK INSPECTION NOTED FRAME 75 ALL SHEAR TIES FROM STRINGER 22 LEFT TO STRINGER 22 RIGHT NEED GENERAL VISUAL INSPECTION AND HFEC IF NEEDED. MAINTENANCE INSTALLED ALL NEW SHEAR TIES AT FRAME 75 IN ACCORDANCE WITH THE REQUIREMENTS OF EA A9-53R-30262 AND SRM 51-42-11. UPON COMPLETION OF THE REPAIR IT WAS INSPECTED AND FOUND ACCEPTABLE.

Part: STRINGER — DAMAGED (FUSELAGE) · airframe 11,484 hrs · 5,590 cycles

DURING C2 C CHECK INSPECTION NOTED STRINGER 34 AT FRAME 74 CAP IS CUT FOR FRAME CLEARANCE. MAINTENANCE CUT STRINGER 34 AND INSTALLED REPAIR COUPLER STRINGER 34 IN ACCORDANCE WITH THE REQUIREMENTS OF EA A9-53R-30262 AND SRM 51-42-11.UPON COMPLETION OF THE REPAIR IT WAS INSPECTED AND FOUND ACCEPTABLE.

Part: FRAME — DAMAGED (FUSELAGE) · airframe 11,484 hrs · 5,590 cycles

DURING C2 C CHECK INSPECTION NOTED FRAME 72 DAMAGED AT STRINGER 27 RIGHT. MAINTENANCE REPAIRED IN ACCORDANCE WITH THE REQUIREMENTS OF EA A9-53R-30262 REV A AND SRM 51-42-11 PARAGRAPH 6. UPON COMPLETION OF THE REPAIR IT WAS INSPECTED AND FOUND ACCEPTABLE.

Part: FRAME — DAMAGED (FUSELAGE) · airframe 11,484 hrs · 5,590 cycles

DURING C2 C CHECK INSPECTION NOTED FRAME 74 DAMAGED FROM STRINGER 26 LEFT TO STRINGER 26 RIGHT. MAINTENANCE REPAIRED FRAME IN ACCORDANCE WITH THE REQUIREMENTS OF EA A9-53R-30262 AND SRM 51-42-11 PARAGRAPH 6. UPON COMPLETION OF THE REPAIR IT WAS INSPECTED AND FOUND ACCEPTABLE.

Part: SHEAR TIE — DAMAGED (FUSELAGE) · airframe 11,484 hrs · 5,590 cycles

DURING C2 C CHECK INSPECTION NOTED FRAME 72 SHEAR TIE BETWEEN STRINGER 27 LEFT AND 28 LEFT REQUIRES REMOVAL AND REPLACEMENT. MAINTENANCE FABRICATED NEW SHEAR TIE, TREATED, PRIMED AND INSTALLED NEW SHEAR TIE IN ACCORDANCE WITH THE REQUIREMENTS OF AIRBUS DRAWING D53571131258, SRM 53-51-12 FIGURE 2, SRM 51-42-11 AND SRM 51-75-12. UPON COMPLETION OF THE REPAIR IT WAS INSPECTED AND FOUND ACCEPTABLE.

Part: FLOOR PANEL — DAMAGED (FUSELAGE) · airframe 11,484 hrs · 5,590 cycles

DURING C2 C CHECK INSPECTION NOTED AFT PIT FLOOR PANEL 151ZE DAMAGED. MAINTENANCE FABRICATED NEW FLOOR PANEL IN ACCORDANCE WITH THE REQUIREMENTS OF SRM 53-02-00 PAGE BLOCK 201 8.G AND 8.H. UPON COMPLETION OF THE REPAIR IT WAS INSPECTED AND FOUND ACCEPTABLE.

Part: BEARING — LOOSE (RT MLG DOOR) · airframe 11,484 hrs · 5,590 cycles

DURING C2 C CHECK INSPECTION NOTED RIGHT MAIN LANDING GEAR DOOR HINGE SPHERICAL BEARING IS LOOSE IN THE HOUSING. MAINTENANCE INSTALLED REPAIR SLEEVE AND NEW BEARING IN ACCORDANCE WITH THE REQUIREMENTS OF EA A9-52R-30264. UPON COMPLETION OF THE REPAIR IT WAS INSPECTED AND FOUND ACCEPTABLE.

Part: SHEAR TIE — MISALIGNED (FUSELAGE) · airframe 11,484 hrs · 5,590 cycles

DURING C2 C CHECK INSPECTION NOTED FRAME 72 SHEAR TIE BETWEEN STRINGER 24 RIGHT AND 25 RIGHT HOLES DO NOT ALIGN WITH REPAIR. MAINTENANCE FABRICATED NEW SHEAR TIE IN ACCORDANCE WITH THE REQUIREMENTS OF AIRBUS DRAWING D53571161. INSTALLATION OF NEW SHEAR TIE WAS ACCOMPLISHED ON NON ROUTINE C043414. UPON COMPLETION OF THE REPAIR IT WAS INSPECTED AND FOUND ACCEPTABLE.

Part: FRAME SPLICE — BENT (FUSELAGE) · airframe 11,484 hrs · 5,590 cycles

DURING C2 C CHECK INSPECTION NOTED FRAME COUPLING FOR FRAME 72 AND BETWEEN STRINGER 27 LEFT TO 28 LEFT HAS BEEN BENT WHILE REMOVING RIVETS. MAINTENANCE REMOVED AND FABRICATED AND REPLACED COUPLING IN ACCORDANCE WITH THE REQUIREMENTS OF AIRBUS DRAWING D53571131 AND SRM 51-75-12. UPON COMPLETION OF THE REPAIR IT WAS INSPECTED AND FOUND ACCEPTABLE.

Part: SHEAR TIE — DAMAGED (FUSELAGE) · airframe 11,484 hrs · 5,590 cycles

DURING C2 C CHECK INSPECTION NOTED SHEAR TIE AT FRAME 75 FROM STRINGER 32 RIGHT TO STRINGER 33 RIGHT IS DAMAGED. MAINTENANCE FABRICATED NEW SHEAR TIE AND INSTALLED SHEAR TIE IN ACCORDANCE WITH THE REQUIREMENTS OF AIRBUS DRAWING D53571554, EA A9-53R-30262 SRM 51-26-11 PARAGRAPH 2 AND SRM 51-42-11 PARAGRAPH 6. UPON COMPLETION OF THE REPAIR IT WAS INSPECTED AND FOUND ACCEPTABLE.

Part: SHEAR TIE — CRACKED (FUSELAGE) · airframe 11,484 hrs · 5,590 cycles

DURING C2 C CHECK INSPECTION, FOUND CRACK INDICATION IN CIRCLED HOLES ON SHEAR TIE FOR FRAME 72 STRINGER 34 RIGHT AND STRINGER 33 RIGHT. MAINTENANCE REMOVED AND REPLACED SHEAR TIES IN ACCORDANCE WITH THE REQUIREMENTS OF EA A9-53R-30262. UPON COMPLETION OF THE REPAIR IT WAS INSPECTED AND FOUND ACCEPTABLE.

Part: COUPLING — DAMAGED (FUSELAGE) · airframe 11,484 hrs · 5,590 cycles

DURING C2 C CHECK INSPECTION NOTED HOLES OUT OF ROUND AND SHOW CRACK INDICATIONS IN CIRCLED HOLES ON FRAME COUPLING FOR FRAME 72 STRINGER 27 LEFT TO 28 LEFT. MAINTENANCE INSTALLED NEW FRAME COUPLING ON FRAME 72 AT STRINGER 27 LEFT AND 28 LEFT IN ACCORDANCE WITH THE REQUIREMENTS OF EA A9-53R-30262. UPON COMPLETION OF THE REPAIR IT WAS INSPECTED AND FOUND ACCEPTABLE.

Part: PAD — DAMAGED (FUSELAGE) · airframe 11,484 hrs · 5,590 cycles

DURING C2 C CHECK INSPECTION NOTED TO REMOVE AIRCRAFT JACK PAD ASSEMBLY BETWEEN FRAME 73 AND FRAME 74 STRINGER 34. MAINTENANCE FOUND JACK PAD ASSEMBLY BAD AND REPLACED JACK PAD ASSEMBLY IN ACCORDANCE WITH THE REQUIREMENTS OF EA A9-53R-30262. UPON COMPLETION IT WAS INSPECTED AND FOUND ACCEPTABLE.

Part: CONTROL CABLE — RUPTURED (R1 DOOR) · airframe 11,484 hrs · 5,590 cycles

DURING C2 C CHECK, INSPECTION REPORTED THE R1 DOOR FLEXIBLE CONTROL CABLE FOR THE EMERGENCY DOOR SYSTEM ARM/DISARM HANDLE WAS RUPTURED. MAINTENANCE REMOVED AND REPLACED THE RUPTURED CABLE IN ACCORDANCE WITH THE REQUIREMENTS OF AMM 52-11-22-020 AND AMM 52-11-22-020-51. UPON COMPLETION OF THE INSTALLATION OF THE CABLE, IT WAS INSPECTED AND FOUND ACCEPTABLE.

Part: STRINGER — DAMAGED (FUSELAGE) · airframe 11,484 hrs · 5,590 cycles

DURING C2 C CHECK INSPECTION NOTED STRINGER 33 RIGHT IS DAMAGED BETWEEN FRAME 72 AND FRAME 74 DAMAGE LOCATED 2.0 INCH FORWARD OF FRAME 74. MAINTENANCE REPAIRED DAMAGED SECTION OF STRINGER WITH SPLICE AND INSTALLED REPAIR IN ACCORDANCE WITH THE REQUIREMENTS OF EA A9-53R-30262. UPON COMPLETION OF THE REPAIR IT WAS INSPECTED AND FOUND ACCEPTABLE.

Part: FRAME — DAMAGED (FUSELAGE) · airframe 11,484 hrs · 5,590 cycles

DURING C2 C CHECK INSPECTION NOTED FRAME 75 DAMAGED STRINGER 26 LEFT AND STRINGER 26 RIGHT. MAINTENANCE REPLACED FRAME 75 AND ALL ATTACHING SHEAR TIES IN ACCORDANCE WITH THE REQUIREMENTS OF EA A9-53R-30262. UPON COMPLETION OF THE REPAIR IT WAS INSPECTED AND FOUND ACCEPTABLE.

Part: SHEAR TIE — DAMAGED (FUSELAGE) · airframe 11,484 hrs · 5,590 cycles

DURING C2 C CHECK INSPECTION NOTED FRAME 72 SHEAR WEBS DAMAGED IN THE AREA OF STRINGER 32 LEFT. MAINTENANCE REMOVED DAMAGED SHEAR TIES FROM STRINGER 32 LEFT TO 31 LEFT. REMOVED FRAME 72 FROM STRINGER 24 RIGHT TO 28 LEFT. FABRICATED NEW ANGLES IN ACCORDANCE WITH THE REQUIRMENTS OF EA A9-53R-30262, SRM 51-42-11 FIGURE 8 AND SRM 53-51-12. INSTALLATION WAS ACCOMPLISHED ON NR C043414. UPON COMPLETION OF THE REPAIR IT WAS INSPECTED AND FOUND ACCEPTABLE.

Part: STRINGER — DAMAGED (FUSELAGE) · airframe 11,484 hrs · 5,590 cycles

DURING C2 C CHECK INSPECTION NOTED STRINGER 32 RIGHT IS DAMAGED BETWEEN FRAME 72 AND THRU FRAME 74. MAINTENANCE REPLACED THE STRINGER SECTION FROM AFT BULKHEAD TO FRAME 72 IN ACCORDANCE WITH THE REQUIREMENTS OF EA A9-53R-30262. UPON COMPLETION OF THE REPAIR IT WAS INSPECTED AND FOUND ACCEPTABLE.

Part: STRINGER — DAMAGED (FUSELAGE) · airframe 11,484 hrs · 5,590 cycles

DURING C2 C CHECK INSPECTION NOTED STRINGER 33 LEFT IS DAMAGED BETWEEN FRAME 72 THRU FRAME 74. MAINTENANCE REPLACED STRINGER SECTION IN ACCORDANCE WITH THE REQUIREMENTS OF EA A9-53R-30262. UPON COMPLETION OF THE REPAIR IT WAS INSPECTED AND FOUND ACCEPTABLE.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 11,484 hrs · 5,590 cycles

REFERENCE NON ROUTINE C043440. DURING C2 C-CHECK INSPECTION NOTED: WHILE JACKING THE AIRCRAFT, THE TAIL JACK STAND WAS NOT REMOVED FROM THE TAIL JACK PAD WHICH CAUSED DAMAGE TO THE AIRCRAFT SKIN, STRINGERS, FRAMES 72 TO 75 AND BETWEEN STRINGERS 26 LT AND 26 RT. MAINT PERFORMED REPAIR TO AC SKIN AND STRUCTURE IAW THE REQUIREMENTS OF EA A9-53R-30262. UPON COMPLETION OF THE REPAIR IT WAS INSPECTED AND FOUND ACCEPTABLE.

Part: STRINGER — CRACKED (FUSELAGE) · airframe 11,484 hrs · 5,590 cycles

DURING C2 C CHECK INSPECTION NOTED STRINGER 32 LEFT IS CRACKED AT FRAME 73. MAINTENANCE REPLACED STRINGER SECTION IN ACCORDANCE WITH THE REQUIREMENTS OF EA A9-53R-30262. UPON COMPLETION OF THE REPAIR IT WAS INSPECTED AND FOUND ACCEPTABLE.

Part: FRAME — DAMAGED (FUSELAGE) · airframe 11,484 hrs · 5,590 cycles

DURING C3 S1 C CHECK INSPECTION NOTED FRAME 72 DAMAGED AT STRINGER 26 LEFT. MAINTENANCE REMOVED AND REPLACED FRAME 72 IN ACCORDANCE WITH THE REQUIREMENTS OF SRM 51-42-11 FIGURE 8. UPON COMPLETION OF THE REPAIR IT WAS INSPECTED AND FOUND ACCEPTABLE.

Part: FLOOR PANEL — DAMAGED (CARGO BAY) · airframe 11,484 hrs · 5,590 cycles

DURING C2 C CHECK INSPECTION NOTED AFT PIT FLOOR PANEL 151PE DAMAGED. MAINTENANCE REMOVED AND REPLACED PANEL IN ACCORDANCE WITH THE REQUIREMENTS OF AMM 53-42-17-400-001. UPON COMPLETION OF THE REPAIR IT WAS INSPECTED AND FOUND ACCEPTABLE.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 11,484 hrs · 5,590 cycles

DURING C2 C CHECK INSPECTION NOTED FIVE DENTS ON TAIL FUSELAGE IN STRINGER AREA 3 AND 6 FRAME 82 AND 83. MAINTENANCE REPAIR IN ACCORDANCE WITH THE REQUIREMENTS OF EA A9-53R-30256. UPON COMPLETION OF THE REPAIR IT WAS INSPECTED AND FOUND ACCEPTABLE.

Part: FLOOR PANEL — DAMAGED (FUSELAGE) · airframe 11,484 hrs · 5,590 cycles

DURING C2 C CHECK INSPECTION NOTED AFT PIT FLOOR PANEL 151CE DAMAGED. MAINTENANCE REMOVED AND REPLACED THE PANEL IN ACCORDANCE WITH THE REQUIREMENTS OF AMM 53-42-14-400-001. UPON COMPLETION OF THE REPAIR IT WAS INSPECTED AND FOUND ACCEPTABLE.

Part: TAT PROBE — INOPERATIVE · airframe 10,791 hrs · 5,272 cycles

ON CLIMB-OUT, THE FLIGHT CREW REPORTED AN ECAM MESSAGE (15052) INDICATING THE CAPTAIN'S TAT SENSOR WAS INOPERATIVE. DESTINATION AIRPORT REQUIRED TAT INFORMATION FOR ANTI-ICING OPERATIONS. THE FLIGHT CREW RETURNED TO THE DEPARTURE AIRPORT AND MADE AN UNEVENTFUL LANDING. MAINTENANCE REMOVED AND REPLACED THE CAPTAINS TAT SENSOR IN ACCORDANCE WITH THE REQUIREMENTS OF AMM 34-11-18 PB 401. OPERATIONS TEST WAS ACCOMPLISHED IN ACCORDANCE WITH AMM 30-31-00-710-001 AND TESTED GOOD.

Part: MOTOR — INOPERATIVE (BLEED VALVE) · airframe 8,915 hrs · 4,376 cycles

FLIGHT CREW REPORTED ENG 1 COMPRESSOR VANE ECAM MILD COMPRESSOR STALLS DURING DESCENT. CONTINUED FLIGHT WITH AUTOTHRUST OFF. REPLACED NR 1 ENGINE BLEED VALVE FUEL GENERATOR MOTOR ASSY. PERFORMED FADEC MOTORING TEST, NO FAULTS NOTED. NO LEAKAGE NOTED ON MIN IDLE LEAK CHECK IAW AMM 75-31-10, PB 401 AND TSM 75-30-00-810-801. ACCOMPLISHED BORESCOPE IAW AMM 72-31-00-290-002. NO DAMAGE NOTED. INSPECTED BLADES IAW AMM 72-31-290-051. NO DAMAGE NOTED.

Part: BUSHING — LACK OF LUBE (L2 DOOR) · airframe 5,896 hrs · 2,871 cycles

DURING C-1 CHECK, INSPECTION REPORTED THE L2 DOOR GUST LOCK INTERMITTENT WITH DOOR IN THE "OPEN" POSITION. TROUBLESHOT GUSSET LOCK ON L2 DOOR IAW TSM 52-13-00. FOUND PLASTIC BUSHING IN THE PUSHBUTTON SWITCH ASSY TO BE INSUFFICIENTLY LUBRICATED. LUBRICATED BUSHING AND OPS CHECKED GOOD IAW AMM 52-13-12-400-001.