N451FE

Part: PRESSURE SWITCH — FAILED (NR 1 ENGINE) · airframe 57,938 hrs · 20,526 cycles

NR 1 ENG FUEL FILTER AMBER LIGHT WITH ECAM FILTER WARNING FOR NR 1 ENG COMPLIED WITH QRH. RELEASED FOR SERVICE IAW MEL: 73-36-03-02: ENGINE (IDENTIFY 1 AND/OR 2) FUEL FILTER LIGHT(S) - INOP. VERIFY AND RECORD IN A ML/EAML THAT FILTER HAS BEEN CHECKED FOR CONTAMINATION ONCE EACH FLIGHT DAY. " MEL MX PROCEDURE PERFORMED IAW AMM 73-12-03, ENG. NR 1 FUEL FILTER REMOVED AND INSPECTED, FOUND CLEAN, NO CONTAMINATION. FUEL FILTER REINSTALLED. LEAK CHECKED WITH IDLE RUN PERFORMED. FOUND OK. ACFT RELEASED IAW MEL 73-36-03-02, FUEL FILTER CHECKED FOR CONTAMINATION, ACFT OK FOR SERVICE. DIFFERENTIAL PRESSURE SWITCH CONNECTOR CHECKED AND CLEANED. LT ENG FUEL FILTER LIGHT INOP. FILTER HAS TO BE CHECKED ONCE EVERY DAY. MX PROCEDURE PERFORMED IAW AMM 73-12-03, ENG. NR 1 FUEL FILTER REMOVED AND INSPECTED, FOUND CLEAN, NO CONTAMINATION. FUEL FILTER REINSTALLED. LEAK CHECKED WITH IDLE RUN PERFORMED. FOUND OK. A/C RELEASED PER MEL 73-36-03-02, FUEL FILTER CHECKED FOR CONTAMINATI ON, A/C OK FOR SERVICE. REMOVED AND REPLACED FUEL FILTER DIFFERENTIAL PRESSURE SWITCH ON GTR 1 AS PER AMM 73-34-11-4. ENGINE RUN PERFORMED AS PER JRH. LEAK TEST PERFORMED. NO LEAK FOUND. ALL TEST PERFORMED FOUND GOOD. MEL CLOSED, STIKER REMOVED.

Part: OUTFLOW VALVE — FAILED · airframe 57,478 hrs · 20,102 cycles

DURING CLIMB, ECAM WARNING FOR EXCESS CABIN, UNABLE TO CONTROL CABIN WITH EITHER REGULATOR IN MANUAL, COMPLIED W/ECAM AND QRH. RETURNED TO LFPG T/S AND CHANGED CPC NR 2 CPC AND AFT OUTFLOW VALVE. REMOVED AND REPLACED CABIN PRESS CONTROLLER NR 2 AND REMOVED AND REPLACED NR 2 AFT OUTFLOW VALVE. OPS CHECKS OK USING ALL SYSTEMS AND CARRIED OUT CABIN PRESSURIZATION AND ALL CHECKED SATISFACTORY.

Part: SKIN — DAMAGED (RT ELEVATOR) · airframe 57,395 hrs · 20,021 cycles

RT ELEVATOR, FORMER REPAIR ON TRAILING EDGE ELEVATOR LOWER SKIN FOUND WITH DEBONDED AREAS. RT ELEVATOR WAS REPLACED.

Part: ENGINE — FAILED (NR 2) · airframe 57,063 hrs · 19,746 cycles

ECAM ADVISORY "NR 2 ENGINE OIL PSI ZERO". NO OTHER PROBLEMS, OIL QUANTITY 15 QTS, OIL TEMP 100 DEGREES. NO "LOW OIL PRESURE" OR "OIL CLOG" LIGHTS. ALL ENGINE PARAMETERS NORMAL FL 320. TAT -14 DEGREES C, SAT -44 DEGREES C. FOLLOWED QRH, NO LEFT ECAM INDICATIONS. LAX U PER PWR PLANT ENGINEERING AWAITING TRANSMITTER FOM OAK. REMOVED AND REPLACED CB FOR OIL PRESSURE SYSTEM, 14ESAS/PERFORMED SECOND GROUND RUN, PER JRH. SYSTEM OPS CHECK GOOD.

Part: BLEED VALVE — MALFUNCTIONED (NR 2 ENGINE) · airframe 56,900 hrs · 19,634 cycles

WHILE CRUISING AT FL400, BOTH AUTO PRESS REGULATORS FAULTED ALMOST SIMULTANEOUSLY. COMPLIED W/ECAM AND QRH. ATTEMPTED RESET BUT BOTH FAULTED AGAIN. SHORTLY THERE AFTER BOTH ENG BLEED 1 AND 2 FAULTED. DONNED O2 AND DESCENDED. BLEED VALVES WOULD NOT RESET. DESCENDED TO 10,000 FEET AND CONTINUED TO KMEM. O2 MASKS DEPLOYED IN LAV. REMOVED AND REPLACED NR 2 ENGINE FAN AIR VALVE IAW AMM 36-11-16-4. RAN NR 1 & 2 ENGINES AT HIGH POWER IAW JRH CHAP 5, ALL INDICATIONS NORMAL. NR 1 & 2 PERCOOLER INLET TEMPS READ 175C AND 180C RESPECTIVELY. OK FOR SERVICE.

Part: ARM — CORRODED (ZONE 300) · airframe 56,349 hrs · 19,343 cycles

NR 3 RUDDER ATTACH ARM, BOTH FWD BEARINGS WORN, LUGS FOUND TO HAVE CORROSION REMOVED AND REPLACED BEARING ASSEMBLIES IAW EA6-5540-109209 STABILIZERS-RUDDER NR 2 AND NR 3 HINGE ARM OVERSIZE BUSHING INSTALLATION-REPAIR, NR 3 HINGE ARM TO BE REINSTALLED ON FEDEX CARD 43S2082 RUDDER HINGE FITTINGS DETAILED INSPECTION.

Part: FRAME — CRACKED (FUELAGE) · airframe 56,349 hrs · 19,343 cycles

RT FRAME 47 HOLE 39 SHOWS CRACK INDICATION. THE HOLE HAS BEEN REAMED TO MAX DIAMETER PER FED EX CARD E6-5710-7-3322 PT1. COMPLIED WITH FEDEX EA 6-5710-112976 WINGS- AD2006-09-05 WING R/S INTERNAL ANGLE FASTENER HOLES 11 AND 39 RT AND 10 AND 61 LT CRACK REPAIR. REAMED HOLE TO REMOVE CRACK INDICATION.

Part: FRAME — CRACKED (BS 2612) · airframe 56,349 hrs · 19,343 cycles

RT FRAME 47 HOLE 11 SHOWS CRACK INDICATION FIG 7 SHEET 3 SAYS CONTACT AIRBUS IF CRACK IS DETECTED COMPLIED WITH FEDEX EA 6-5710-112976, WINGS -AD2006-09-05 WING R/S INTERNAL ANGLE FASTENER HOLE 11 AND 39 RT AND 10 AND 61 LT CRACK REPAIR. REAMED HOLES TO REMOVE CRACK INDICATIONS.

Part: FRAME — CRACKED (WING ROOT) · airframe 56,349 hrs · 19,343 cycles

LT FRAME 47 HOLE 61 SHOWS CRACK DAMAGE INDICATION. E6-5710-7-3322 PT1 FIG7 SHEET 3 SAYS CONTACT AIRBUS IF CRACK IS DETECTED COMPLIED WITH FEDEX EA 6-5710-112976 WINGS AD 2006-09-05 WING R/S INTERNAL ANGLE FASTENER HOLES 11 AND 39 RT 10 AND 61 LT. REAMED HOLES TO REMOVE CRACK INDICATION.

Part: FRAME — CRACKED (WING ROOT) · airframe 56,349 hrs · 19,343 cycles

LT FRAME 47 HOLE 10 SHOWS CRACK INDICATION, FIG 7 SHEET 3 SAYS CONTRACT AIRBUS IF CRACK IS DETECTED. COMPLIED WITH FEDEX EA 6-5710-112976 WINGS AD2006-09-05 WING R/S INTERNAL ANGLE FASTENER HOLES 11 AND 39 RT AND 10 AND 61 LT CRACK REPAIR. REAMED HOLES TO REMOVE CRACK INDICATION.

Part: FLOOR SUPPORT — CORRODED (CARGO BAY) · corrosion level 2 · airframe 56,349 hrs · 19,343 cycles

AFT PIT FLOOR BOARD SUPPORT ANGLE AT LBL50 FRAME 64-65 IS CORRODED FOUND SUPPORT AND FITTING CORRODED AND CRACKED OUT OF LIMITS IAW A310 SRM 53-10- 00 TABLE 102; REMOVED AND REPLACED SUPPORT AND FITTING IAW A310 SRM 51-40-21, 53-17-15 PGA13,FIG 9, 51-40-44.

Part: FRAME — CORRODED (FUSELAGE) · corrosion level 2 · airframe 56,349 hrs · 19,343 cycles

FORWARD LOWER CARGO FRAME 38.2 LBL 8 TOP CAP IS CORRODED. REMOVED CORROSION IAW A310 SRM 51-74-10, ORIGINAL THICKNESS WAS .125 REMAINING THICKNESS IS .079, OUT OF LIMITS IAW A310 SRM 53-10-00. REMOVED AND FABRICATED NEW T-CAP AND SPLICE COUPLING IAW A310 SRM 53-10-15. TREATED AND INSTALLED IAW A310 SRM 51-21-10 AND 51-23-10 AND 51-40-30.

Part: ATTACH ANGLE — DAMAGED (R-1 DOOR AREA) · airframe 56,349 hrs · 19,343 cycles

R-1 DOOR SCUFF PLATE ATTACH ANGLE HAS HOLES OUT OF ROUND AND OVERSIZED. REMOVED AND REPLACED R-1 DOOR SCUFF PLATE FITTING IAW A31-200 SRM 51-40-21 PARA 7.

Part: ATTACH ANGLE — DAMAGED (ZONE 200) · airframe 56,349 hrs · 19,343 cycles

L1 DOOR SCUFF PLATE ATTACH ANGLE HAS ALL HOLES OUT OF ROUND OVERSIZED. REMOVED AND REPLACED FITTING IAW A310-200-SRM 51-40-21 PAR 7.

Part: STRINGER SPLICE — MISREPAIRED (FUSELAGE) · airframe 56,349 hrs · 19,343 cycles

AFT PIT STRINGER SPLICE REPAIR AT STRINGER 52L FRAME 59/60 REQUIRES EVALUATION FOR MAJOR/MINOR DETERMINATION AND IF REPAIR WAS ACCOMPLISHED USING APPROVED DATA. STRINGER COUPLING MATERIAL TYPE AND MATERIAL TEMPER DID NOT CONFORM TO A310 SRM REQUIREMENTS, REMOVED AND RPLACED STRINGER COUPLING REPAIR IAW A310- 200 SRM 53-10-14 FIG 201.

Part: STRINGER SPLICE — MISREPAIRED (FUSLEAGE) · airframe 56,349 hrs · 19,343 cycles

AFT PIT STRINGER SPLICE REPAIR AT STRINGER 52L FRAME 60/61 REQUIRES EVALUATION FOR MAJOR/MINOR DETERMINATION AND IF REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. FOUND THAT STGR COUPLING MATERIAL TYPE AND MATERIAL TEMPER DID NOT CONFORM TO A310 SRM REQUIREMENTS, REMOVED AND REPLACED STRINGER COUPLING REPAIR IAW A310 SRM 53- 10-14 FIG 201

Part: FLOOR SUPPORT — CORRODED (ZONE 100) · corrosion level 2 · airframe 56,349 hrs · 19,343 cycles

ALC FLOOR SUPPORT STRUCTURE BETWEEN FRAME 64-65 LBL5 IS CORRODED REMOVED DAMAGED ALC FLOOR SUPPORT AT LBL 5 BETWEEN FRAME 64-65 IAW A310-200 SRM 51-40-21. RECEIVED NEW PROFILE, LOCATED AND DRILLED NEW PROFILE IAW A310-200 SRM 51-40-44. INSTALLED NEW PROFILE IAW A310-200 SRM 51-40-21 MAJOR REPAIR.

Part: FITTING — CORRODED (UPPER CARGO) · corrosion level 2 · airframe 56,349 hrs · 19,343 cycles

CABIN FRAME 44 TIE CLIP TO LT EMERGENCY DOOR CUT OUT FRAME AT FLOOR LEVEL IS CORRODED. REMOVED CORRODED TIE CLIP IAW FEDEX A310-200 SRM 51-40-21 PARA 7, RECEIVED, LOCATED, AND DRILLED NEW FITTING PO NR 589661.1 IAW FEDEX A31-200 SRM 51-40-30. INSTALLED NEW FITTING IAW FEDEX A310-200 SRM 51-40-21 PARA 7.

Part: FRAME — CORRODED (FUSELAGE) · corrosion level 2 · airframe 56,349 hrs · 19,343 cycles

BULK CARGO PIT T CAP AT FRAME 64 BL0 TO LBL15 IS CORRODED NO ALLOWABLE REWORK FOR T-CAP SPECIFIED IAW A310 SRM 53-10-15, REMOVED AND REPLACED T-CAP IAW A310 SRM 51-40-21.

Part: FLOOR SUPPORT — CORRODED (CARGO BAY) · corrosion level 2 · airframe 56,349 hrs · 19,343 cycles

FOUND BULK CARGO PIT AT FRAME 63 TO FRAME 64 AT LBL5 FLOOR BOARD SUPPORT ANGLE IS CORRODED. 10-16-07 REMOVED CORROSION IAW A310 SRM 51-74-10, CHECKED LIMITS IAW A310 SRM 53-17-15, ORG. THICKNESS .074, REMAINING MATERIAL IS.058, FOUND TO BE OUT OF LIMITS IAW A310 SRM 53-10-00, REMOVED FLOOR SUPPORTIAW A310 51-40-21, RECEIVED NEW FLOOR SUPPORT P/N A5347427920200, LOCATED AND DRILLED NEW FLOOR SUPPORT IAW A310 SRM 51-40-44, INSTALLED IAW A310 SRM 51-40-21.

Part: FRAME — CORRODED (AFTPIT) · corrosion level 2 · airframe 56,349 hrs · 19,343 cycles

FOUND AFT CARGO PIT AT FRAME 54.1 S-52L CORRODED. 10-29-07 REMOVED CORROSION AT STRINGER 52L FRAME 54.1 IAW A310 SRM 51-74-10, FOUND OUT OF LIMITS IAW A310 SRM 53-10-14, REMOVED STRINGER IAW A310 SRM 53-10-14, FABBRICATED NEW SRTINGER REPAIR AND 2 COUPLINGS IAW 51-10-14, ALODINED AND PRIMED REPAIR PARTS IAW A310 SRM 51-21-10 AND 51-23-10, INSTALLED STRINGER SPLICE AND COUPLINGS IAW FEDEX A310 SRM 53-10-14.

Part: STRINGER — CORRODED (AFT CARGO BAY) · corrosion level 2 · airframe 56,349 hrs · 19,343 cycles

FOUND AFT CARGO PIT AT FRAME 58 S-57 IS CORRODED. 10-16-07 REMOVED STRINGER IAW A310 SRM 51-72-10 PARA 5, RECIEVED NEW STRINGER, TRANSFERRED REPAIR PART HOLES IAW A310 SRM 53-10-14 PARA 2, INSTALLED REPAIR PARTS IAW A310 SRM 53-10-14 PARA 4, APPLIED TOP COAT TO THE FASTNERS IAW A310 AMM 51- 25-10, REMOVED AND REISTALLED TEMP SENOR COVER IAW A310 SRM 51-40-21 PARA 2.

Part: FLOORBEAM — CORRODED (CARGO BAY) · corrosion level 2 · airframe 56,349 hrs · 19,343 cycles

FOUND T CAP OF FLOORBEAM 66 IS CORRODED FROM RBL 47R TO LBL 47L. 10-18-07 REMOVED T CAP IAW A310 SRM 51-40-21, TEE CAP OUT OF LIMITS IAW A310 SRM 53-10-15, RECEIVED NEW FLOORBEAM AND TWO ANGLES, INSTALLED IAW 51-40-21

Part: SKIN — CANNING (FUSELAGE) · airframe 56,349 hrs · 19,343 cycles

LOWER AFT EXTERNAL FUSELAGE SKIN AT FRAME 79, STR 36R-37R HAS BULGE AND OIL CANS. 10-19-07 MAJOR REPAIR, REMOVED DAMAGE AREA, FABBED DOUBLER, ALODINED AND PRIMED, INSTALLED DOUBLER AND WASHERS, APPLIED CPC IAW A310-200 SRM 53-10-12 FIG 225, 51-40-50 FIG 3, 51-21-10 PAGE 62, 53-10-12 PAGE 357, 51-71-10, 51-23-20.

Part: INTERCOSTAL — CRACKED (BS 904) · airframe 56,349 hrs · 19,343 cycles

E/COMPARTMENT, INTERCOSTAL CRACKED AT COCKPIT FLOORBEAM, FRAME 7, STA 904, BL30L,-Y 760 IN WORK. 10-18-07 REMOVED INTERCOSTAL CRACKED IAW A310 SRM 51-40-21. INTERCOSTAL CRACKED REQUIRES TO REPLACE IAW A310 SRM 51-72-01 MAT ID NEW WEB.050 2024T3 IAW A310 SRM 51-31-00 PG 19/20 TABLE 3 SHEET 1. MAT EQUIVALANCE CHART ORG MAT IS CLAD 2024-742 REF A310 SRM 53-11-15. FORMED WEB REF A310 SRM 53-11-15 AND AEROSPATIALE DWG 107270, LOCATED AND DRILLED IAW A310 SRM 51-40-44. ALODINED IAW A310 SRM 51-21-10. PRIMED AND PAINTED BOTH IAW A310 SRM 51-23-10. MARKED PN IAW A310 SRM 53-11-15. INSTALLED IAW A310 SRM 51-40-21. MAJOR REPAIR

Part: STRINGER — CORRODED (AFT PIT) · corrosion level 2 · airframe 56,349 hrs · 19,343 cycles

FOUND AFT CARGO PIT BETWEEN FRAME 62 AND FRAME 63 S-56L CORRODED. 10-15-07 REMOVED CORROSION IAW A310 SRM 51-74-10, HIGH FREQ FOR ANY CRACKS OR REMAINING CORROSION PER A310 NTM 51-10-08, FABBED REPAIR PARTS AND INSTALLED IAW A310 SRM 53-10-14 PG 204A/204B FIG201A, ALODINED, PRIMED, AND PAINTED IAW A310 SRM 51-21-10,51-23-10 AND A310 AMM 51-25-10.

Part: SHEAR TIE — CORRODED (AFT CARGO BAY) · corrosion level 2 · airframe 56,349 hrs · 19,343 cycles

AFT CARGO PIT AT FRAME 54.1 BETWEEN SHEARTIE IS CORRODED AND CRACKED S-51L TO S-52L. 10-29-07 REMOVED AND REPLACED SHEAR TIE AT FRAME 54.1 BETWEEN SRINGER 51L AND 52L IAW FEDEX A310 SRM 51-40-21 PG 30.

Part: FRAME — CORRODED (CARGO BAY) · corrosion level 2 · airframe 56,349 hrs · 19,343 cycles

FOUND AFT CARGO PIT AT FRAME 61 AT S-54L IS CORRODED. 10-11-07 NO GENERAL OR SPECFIC ALLOWABLE DAMAGE FOR STRINGER IAW A310 SRM 53-17-14, REMOVED STRINGER SECTION AND COUPLINGS AND FABBED NEW STRINGER SECTION AND 2 COUPLINGS IAW A310 SRM 53-10-14 PG 203/204, ALODINED , PRIMED AND PAINTED REPAIR PARTS IAW A310 SRM 51-21-10 AND 51-23-10. INSTALLED REPAIR PARTS IAW A310 SRM 31-10-14 PG 203/204.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 56,349 hrs · 19,343 cycles

FOUND BETWEEN FRAME 67 AND FRAME 64 RBL44 FLOOR SUPPORT STRUCTURE IS CORRODED. 10-22-07 REMOVED CORROSION FOUND TO BE OUT OF LIMITS IAW A310 SRM 53-10-00; REMOVED AND REPLACED SUPPORT STRAP IAW A310 SRM 53-17-14 ITEM 1 FIG 9, AND 51-40-44 AND 51-40-21.

Part: FLOOR SUPPORT — CORRODED (CARGO BAY) · airframe 56,349 hrs · 19,343 cycles

FOUND BULK CARGO PIT BETWEEN FR 65 AND 66 AT LBL 50 FLOOR ATTACH IS CORRODED. 10-22-07 FOUND FLOOR SUPPORT TO BE CRACKED AND CORRODED OUT OF LIMITS IAW A310 SRM 53-10-00 TABLE 102; REMOVED AND REPLACED SUPPORT IAW A310 SRM 51-40-21, 51-40- 44, 53-17-15 FIG 9 ITEM 35.

Part: MOUNT — GOUGED (ENGINE) · airframe 56,349 hrs · 19,343 cycles

NR 2 PYLON TO ENGINE FORWARD INBD MOUNT PLATE HOLE GALLED INSIDE, FORWARD MOUNT. BLENDED AREA IAW A310-200 SRM 54-51-81. HOLE SIZE IS .842 WITHIN LIMITS IAW A310-200 SRM 54-51-81. CADIMUM PLATED IAW A310-200 SRM 51-21-10. ADHESION TEST PASSED IAW FEDEX A310-200 SRM 51-21-10.

Part: MOUNT — GOUGED (ENGINE) · airframe 56,349 hrs · 19,343 cycles

NR 2 PYLON TO ENGINE FWD MOUNT PLATE, AFT INBD HOLE GOUGED. BLENDED AREA IAW A310-200 SRM 54-51-81. HOLE SIZE IS .842 WITHIN LIMITS IAW A310-200 SRM 54-51-81. CADMIUM PLATED IAW A310-200 SRM 51-21-10. ADHESION TEST PASSED IAW FEDEX A310-200 SRM 51-21-10.

Part: SPLICE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 56,349 hrs · 19,343 cycles

AFT CARGO PIT AT FR 58 S-45L IS CORRODED REMOVED AND REPLACED CONNECTOR SPLICE P/N A5397331420000, IN AFT PIT AT FR 58 STRINGER 45L, IAW A310 SRM 51-40-44, 51-40-21 AND TOP COATED IAW A310 SRM 51-23-10.

Part: HYDRAULIC SYSTEM — UNKNOWN · airframe 55,411 hrs · 18,749 cycles

AFTER TAKEOFF, LANDING GEAR WOULD NOT RETRACT. INDICATION WAS THREE RED DOOR LIGHTS THREE GREEN DOWN AND LOCKED LIGHTS ON. HANDLE WOULD NOT GO ABOVE NEUTRAL POSITION. TRIED BOTH SYST NR 1 AND SYST NR 2 AS PER QRH AND C/BS. PERFORMED VISUAL INSPECTION TO PITCH DAMPER, NO LEAK DETECTED. RECTIFIED HYDRAULIC LEVEL IAW AMM 12-12-32. PERFORMED MLG TEST IAW AMM 32-31-00.

Part: HYDRAULIC SYSTEM — UNKNOWN · airframe 55,416 hrs · 18,753 cycles

AFTER TAKEOFF, LANDING GEAR WOULD NOT RETRACT INDICATION WAS THREE REDS DOOR LIGHTS THREE GREEN DOWN AND LOCKED LIGHTS ON. HANDLE WOULD NOT GO ABOVE NEUTRAL POSITION . TRIED BOTH SYST NR 1 AND SYST NR 2 AS PER QRH AND C/BS. PERFORMED VISUAL INSPECTION TO PITCH DAMPER NO LEAK DETECTED. RECTIFIED HYDRAULIC LEVEL IAW AMM 12-12-3 2. PERFORMED MLG TEST IAW AMM 32-31-00.

Part: OIL SYSTEM — UNKNOWN (NR 1 ENGINE) · airframe 55,290 hrs · 18,659 cycles

NR 1 ENG OIL QTY STARTED TO DECREASE IN CRUISE. OIL DROPPED TO 6.5 GAL, PSI 46/48 TEMP 85/85 QTY 6.5/18. ZERO OIL QTY CAME BACK UP TO 20 QTY ON TAXI IN. NR 1 ENG INSPECTED FOR OIL LEAK ACC MM 79-00-00, NO LEAK OBSERVED. ENG SERVICE TO NORMAL AND AFTER ENG RUN UP FOR 20 MIN, ALL PARAMETERS ARE CORRECT AND NO EXTERNAL LEAK OBSERVED. NOTE: MTSI OPENED FOR FURTHER TROUBLESHOOTING OF OIL INDICATION SYS.

Part: SKIN — DAMAGED (ACCESS DOOR) · airframe 54,008 hrs · 17,688 cycles

REPAIR AT STN 2135 FS 38.1 STN 2188 FS 38.2 STR 49 LT, AIR CONDITION ACCESS DOOR. REPAIR EVALUATED AND FOUND NOT TO CONFORM TO AN EXISTING SRM REPAIR. NEW REPAIR ACCOMPLISHED IN ACCORDANCE WITH SRM 51-72-10 AND 51-40-21.

Part: SKIN — MISREPAIRED (TE FLAP) · airframe 54,008 hrs · 17,688 cycles

COMPLY WITH AGING 9 - AGING INSPECTION, RT WING - REPAIR AT RT INBOARD FLAP LOWER TRAILING EDGE. REPAIR EVALUATED AND FOUND NOT TO CONFORM TO AN EXISTING SRM REPAIR. NEW REPAIR ACCOMPLISHED PER SRM 57-52-12.

Part: SKIN — MISREPAIRED (RT WING) · airframe 54,008 hrs · 17,688 cycles

COMPLY WITH AGING 9 - AGING INSPECTION, RT WING - REPAIR ON LWR SKIN SURFACE BETWEEN FRONT SPAR AND MAIN, AND BETWEEN RIB 3 AND RIB 4. REPAIR EVALUATED AND FOUND NOT TO CONFORM TO AN EXISTING SRM REPAIR. NEW REPAIR ACCOMPLISHED PER SRM 57-53-12.

Part: SKIN — MISREPAIRED (RT WING) · airframe 54,008 hrs · 17,688 cycles

COMPLY WITH AGING 9 - AGING INSPECTION, RT WING - REPAIR ON UPPER SKIN SURFACE BETWEEN TRAILING EDGE AND REAR SPAR AND BETWEEN RIB 2 AND TRACK 3. REPAIR EVALUATED AND FOUND NOT TO CONFORM TO AN EXISTING SRM REPAIR. NEW REPAIR ACCOMPLISHED IN ACCORDANCE WITH FEDEX ENGINEERING AUTHORIZATION EA 6-5710-84101.

Part: FAIRING — MISREPAIRED (TAIL CONE) · airframe 54,008 hrs · 17,688 cycles

COMPLY WITH AGING 9 - AGING INSPECTION, REPAIR AT TAIL CONE EXHAUST AREA (PLEASE EVALUATE). REPLACED THIS FAIRING IAW AMM 52-41-18.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 54,008 hrs · 17,688 cycles

MOD TYPE Y MOD NR 9-AGING-INSP REV NR PS PT1 AGING AIRPLANE SAFETY RULE (AASR). COMPLY WITH AGING 9-AGING-INSP REV NR POS PT1. FUSELAGE - REPAIR AT FR 15/16 BELOW R1 DOOR (PLEASE EVALUATE). REPAIR EVALUATED AND FOUND NOT TO CONFORM TO AN EXISTING SRM REPAIR. NEW REPAIR ACCOMPLISHED PER SRM 53-12-12, FIG 201, SHEET 1 AND 51-40-21.

Part: HOOK — DAMAGED (CARGO DOOR) · airframe 54,008 hrs · 17,688 cycles

COMPLY WITH AGING 9 - AGING INSPECTION, FUSELAGE - REPAIR AT REAR LOWER CARGO DOOR AT FWD LOCK HOOK (PLEASE EVALUATE). REMOVED/INSTALLED AFTER REPAIR PER AMM 52-30-21. REPAIRED PER SRM 51-73-10. PAINTED PER SRM 51-75-10-08. CONFORMS TO SRM 51-73-10.

Part: SKIN — MISREPAIRED (RT ELEVATOR) · airframe 54,008 hrs · 17,688 cycles

COMPLY WITH AGING 9 - AGING INSPECTION, HORIZONTAL STAB - REPAIR AT RT ELEVATOR INBOARD TRAILING EDGE. REPAIR EVALUATED AND FOUND NOT TO CONFORM TO AN EXISTING SRM REPAIR. NEW REPAIR ACCOMPLISHED PER SRM 55-21-11.

Part: REPAIR — UNKNOWN (PRECOOLER) · airframe 54,008 hrs · 17,688 cycles

COMPLY WITH AGING 9 - AGING INSPECTION, NR 2 PYLON - FERRULE PRECOOLER AT AFTER SIDE OF UPPER SIDE WITH REPAIR (PLEASE EVALUATE). REPAIR EVALUATED AND FOUND NOT TO CONFORM TO AN EXISTING SRM REPAIR. NEW REPAIR ACCOMPLISHED PER SRM 54-51-11, CONFIG 2, FIG 201 AND 51-40-21.

Part: SKIN — MISREPAIRED (LT WING) · airframe 54,008 hrs · 17,688 cycles

COMPLY WITH AGING 9 - AGING INSPECTION, LT WING - REPAIRS (2) AT LT WING LWR SURFACE (ALL SPEED AILERON) PLEASE EVALUATE. REPAIR EVALUATED AND FOUND NOT TO CONFORM TO AN EXISTING SRM REPAIR. NEW REPAIR ACCOMPLISHED PER SRM 57-61-12.

Part: SKIN — MISREPAIRED (LT WING TE FLAP) · airframe 54,008 hrs · 17,688 cycles

COMPLY WITH AGING 9 - AGING INSPECTION, LT WING - REPAIR AT LT INBOARD FLAP TRAILING EDGE, UPPER SURFACE (PLEASE EVALUATE). REPAIR EVALUATED AND FOUND NOT TO CONFORM TO AN EXISTING SRM REPAIR. NEW REPAIR ACCOMPLISHED IN ACCORDANCE WITH FEDEX ENGINEERING AUTHORIZATION 6- 5710-84099.

Part: IRU — MALFUNCTIONED (E/E BAY) · airframe 52,798 hrs · 16,888 cycles

NR 1 ATT ON PFD FROZEN, NR 1 FD FAILED, NR 1 A/P & NR 1 YAW DAMPER TRIPPED. SUSPECT NR 1 ADC FAILED. ON SHUTDOWN IRS MONITOR SHOWED NR 1 IRU, FOR DRIFT & GS. REMOVED AND REPLACED NR 1 ADC IAW MM 34-11-34-4. TESTED PER 34-10-00 P BLOCK 501. REMOVED AND REPLACED NR 1 IRU IAW MM 34-25-34-4. TESTED PER 34-25-34-5. AFS & LAND TEST PERFORMED PER MM 22-40-00-5. R/I FROM FACT PREMATURE REMOVAL/INSTALLATION OFF MFG 461600-0800-0801, POS 1 SRL 0033, TAG 998311.

Part: CABLE — CORRODED (N/A) · airframe 51,606 hrs · 16,054 cycles

ELEVATOR CONTROL CABLES AZ737114000000 (E2R1) & A2731145000000 (E2RC) AT SUPPORT PULLIES BS 4467 - FR 84 SEVERELY CORRODED. ** S/D ** COMING

Part: CYLINDER — CRACKED (LT MLG) · airframe 50,256 hrs · 15,314 cycles

LEFT MLG DOWNLOCK CYLINDER AT STRUT BRACE CTD MISSING ATTACHMENT PIN. CYLINDER CRACKED AT 2 PLACES.

Part: SMOKE WARNING — ILLUMINATED (COCKPIT) · airframe 50,191 hrs · 15,281 cycles

AFT T/O AT APPROX 300 FT, GOT SMOKE WARNING AFT MAIN DECK CARGO COMP DID ECAM PROC AND SMOKE LIGHT WENT OUT.

Part: WARNING LIGHT — ILLUMINATED (COCKPIT) · airframe 49,821 hrs · 15,113 cycles

ON T/O AS PWR WAS ADVANCED ECAM WARN AND NR 2 ENG REVR UNLOCK LIGHT ILLUM. REJECT T/O AND LIGHT AND WARN WENT AWAY AFT PWR REDUCED. THRUST REVERSER UNDER MEL 78-1.

Part: WARNING LIGHT — ILLUMINATED (COCKPIT) · airframe 49,702 hrs · 15,048 cycles

ON T/O ROLL WITH MAX POWER SET, NR 2 REVERSER UNLOCK LIGHT CAME ON WITH ECAM WARN. AC RELEASED PER MEL 78-1.

Part: IDG — OVERTEMP (NR 2) · airframe 49,719 hrs · 14,585 cycles

DURING T/O, CLB & CR ON DEP DXB NOTICED STEADY INCREASE IN THE NR 2 INTERGRATED DRIVE GENERATOR OIL TEMP EVEN THRU PREVIOUSLY DISCONNECTED PER MEL 24-1. TEMP REACH 180 DEG & CLB.