N804FD

Part: BRACKET — DAMAGED (N/A) · airframe 432 hrs · 17,214 cycles

ON POST FLIGHT FOUND FUELING DOOR 144DR MISSING WITH DAMAGE TO RT PACK INLET FAIRING. REPLACED BROKEN COOLING DUCT SUPPORT BRACKET IAW SRM 51-72-10. REMOVED AND REPLACED R/H AIR INLET FAIRINGS DUCT AND REFUELING PANEL DOOR ASSY IAW MM 53-15-73-04 AND 52-42-17-04. FUELING DOOR SW 23QU WILL BE REPLACED REF. WRI 52-40-2047 DUE TO MISSING WIRE.

Part: ACTUATOR — LEAKING (RT SPOILER) · airframe 432 hrs · 17,190 cycles

BLUE RESERVOIR LO LEVEL ECAM WITH ASSOCIATED SPOILERS FAULTS. FOLLOWED ECAM & QRH, RETURNED FOR UNEVENTFUL LANDING. FOUND NR 3 RT SPOILER ACTUATOR, SIDE CAP BLOWN OUT, REQUIRES ACTUATOR PART. R & R NR 3 RT SPOILER ACTUATOR IAW AMM 27-64-14-04. OPERATIONAL TEST IS NORMAL. SERVICED BLUE HYD SYS IAW AMM 12-12-29.

Part: COMPUTER — FAILED (WARNING SYS) · airframe 432 hrs · 17,191 cycles

DURING LANDING, GEAR EXTENSIONS WITH POSITION DETECTOR, SYS NR 2 SELECTED, GOT ECAM, LG DOOR SYS INOPERATIVE UNTIL ALL GEARS WERE DOWN & LOCKED. SYS NR 1 MEL'D, INOPERATIVE. R & R NR 2 FLIGHT WARNING COMPUTER IAW AMM 31-53-34-04. PERFORMED ECAM & LG WARNING TEST. ALL CHECKED GOOD IAW AMM 32-61-00-05.

Part: SLIDE — UNWANTED DEPLOY (R1 DOOR) · airframe 424 hrs · 16,812 cycles

DOOR R1 SLIDE DEPLOYED ACCIDENTALLY AT BLOCK. REMOVED AND REPLACED THE R1 SLIDE IAW MM 25-61-22-04-02, ARMED THE R1 SLIDE OPS TEST IAW MM 52-73-00-05. REMOVED AND REPLACED THE DIAPHRAGM AND SERVICED THE EMERGENCY OPERATION CYLINDER OF R1 DOOR IAW AMM 52-10-14-03, OPENED AND CLOSED R1 DOOR, NO LEAK FOUND.

Part: SKIN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 41,903 hrs · 16,512 cycles

AV COMPARTMENT FUSELAGE SKIN FRAME 16A - 17 STRINGER 44 - 45 RT INNER SURFACE FOUND CORROSION. COMPLIED WITH EA 6-5310-T0310792 P1 EA TITLE FUSELAGE MAIN FRAME CORROSION INTERNAL DOUBLER AT FRAME 16A - 17. MAJOR REPAIR IAW GMM 6-2-100.

Part: REPAIR — DEBONDED (TE FLAP) · airframe 41,903 hrs · 16,512 cycles

AGING INSPECTION - EXISTING REPAIR ON LT WING I/B FLAP TRAILING EDGE RIB8-10 UPR & LWR SURFACE. REPAIR PATCH DISBONDED. REPORTED TO ENGINEER. REMOVED THE OLD REPAIR PATCH & REPAIRED THE DAMAGE PER A310 SRM 57-52-12 FIG 204 EO 6-5100-7-5000 PART1 WAS COMPLETED. TITLE: STRUCTURES-REPAIR CATALOG- A300/A310 REPAIR IDENTIFICATION & TRACKING REQUIREMENT 14 CFR 121.707 THE REPAIR WAS CATEGORY "A" AND WAS CLASSIFIED AS MAJOR PER GMM6-2-100 REVISION 123. TRACKING EA:6-5750-T0311096 WAS ISSUED.TITLE:WINGS FLIGHT SURFACES. LT INBD FLAP TRAILING EDGE RIB8-10 LOWER & UPPER SKIN DELAMINATION REPAIR.

Part: FASTENER — MISSING (FUSELAGE) · airframe 41,903 hrs · 16,512 cycles

AGING INSPECTION EXISTING REPAIR ON AFT CARGO DOOR SILL BEAM BETWEEN FRAME 59 & 64 REQUIRES EVALUATION FOR CONFORMITY. THE REPAIR WAS EVALVATED AND FOUND THE REPAIR WAS MISSING A FASTENER, WAS FOUND COMPARED WITH EA 6-5317-81082 TITLE:FUSELAGE -DEVIATION FROM SRM REPAIR CH 53-17-18 FIG 207-AFT CARGO DOORSILL BEAM REPURTED TO ENGINEER INSTALLED THE MISSING FASTENER PER EA 6-5317- 81082 & SRM51-40-44 AND COMPLETED EO 6-5100-7-5000 PART 1 WAS COMPLETED TITLE : STRUCTURES-REPAIR CATALOG-A300/A310 REPAIR IDENTIFICATION & TRACKING REQUIREMENTS 14 CFR 121.707 THE REPAIR WAS CATEGORY "A" AND WAS CLASSIFIED AS MAJOR PER GMM6-2-100 REVISION123

Part: REPAIR — CORRODED (FUSELAGE) · airframe 41,903 hrs · 16,512 cycles

AGING INSPECTION EXISTING REPAIR ON AV COMPARTMENT STRINGER 44 RT BETWEEN FRAME 16 & 17 REQUIRES EVALUATION FOR CONFORMITY. THE REPAIR WAS FOUND CORRODED HEVAILY. THE REPAIR ANGLE FITTING WAS REPLACED IN SNRM:N00360 AND COMPLETED TITLE: AV COMPT- STRINGER 44 RT FOUND HEVAY CORROSION AT FR16 LOCATION EO:6-5100-7-5000 PART1 WAS COMPLETED TITLE: STRUCTRES-REPAIR CATALOG-A300/A310 REPAIR IDENTIFICATION & TRACKING REQUIREMENT 14 CFR 121.707

Part: REPAIR — DEBONDED (TE FLAP) · airframe 41,903 hrs · 16,512 cycles

AGING INSPECTION EXISTING REPAIR ON RT WING INBD FLAP TE RIB 3 - 5 LOWER SURFACE, REQUIRES EVALUATION FOR CONFORMITY. THE REPAIR WAS EVALUATED AND FOUND THE OLD REPAIR PATCH DISBONDED. REMOVED OLD REPAIR PATCH & DAMAGE CORE REPORTED TO ENGINEER. REPAIRED THE DAMAGE PER A310 SRM 57-52-12 FIG 204. EO 6-5100-7-5000 PART1 WAS COMPLETED. TITLE:STRUCTURES-REPAIR CATALOG- A300/A310 REPAIR IDENTIFICATION & TRACKING REQUIREMENT 14 CFR 121.707 THE REPAIR WAS CATEGORY "A" AND WAS CLASSIFIED AS MAJOR PER GMM6-2-100 REVISION 122 RSC TRACKING EA:6-5750-T0310889A WAS ISSUED.TITLE:WINGS FLIGHT SURFACES. RT INBD FLAP TRAILING EDGE LOWER SKIN DELAMINATION REPAIR.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 41,903 hrs · 16,512 cycles

AGING INSPECTION EXISTING REPAIR ON AV COMPARTMENT STRINGER 44 RT BETWEEN FRAME 15A & 16 REQUIRES EVALUATION FOR CONFORMITY. THE REPAIR WAS EVALVATED AND FOUND THE STRINGER CORRODED HEVAILY. THE OLD REPAIR AND STRINGER WAS REMOVED AND RE-REPAIRED WITH A NEW STRINGER IN SNRM:N00360 AND COMPLETED TITLE:AV COMPT-STRINGER 44 RT FOUND HEVAY CORROSION AT FR16 LOCATION EO:6-5100-7-5000 PART1 COMPLETED. TITLE:STRUCTURES-REPAIR CATALOG- A300/A310 REPAIR IDENTIFICATION & TRACKING REQUIREMENTS 14 CFR 121.707

Part: REPAIR — DEBONDED (TE FLAP) · airframe 41,903 hrs · 16,512 cycles

AGING INSPECTION EXISTING REPAIR ON RT WING INBD FLAP TE RIB 5 - 7 LOWER SURFACE, REQUIRES EVALUATION FOR CONFORMITY. THE REPAIR PATCH DISBONDED REMOVED OLD REPAIR PATCH & DAMAGE CORE IT EXCEEDED THE REPAIRABLE LIMIT PER A310SRM57-52-12 FIG 204 REPORTED TO ENGINEER EA 6-5750-T0310889A WAS ISSUED AND COMPLETED. TITLE:WINGS FLIGHT SURFACES: RT INBD FLAP TRAILING EDGE LOWER SKIN DELAMINATION REPAIR EO:6-5100-7- 5000PART 1 WAS COMPLETED TITLE:STRUCTURES-REPAIR CATALOG-A300/A310 REPAIR IDENTIFICATION & TRACKING REQUIREMENTS 14 CFR 121.707 THE REPAIR WAS CATEGOR "A" AND WAS CLASSIFIED AS MAJOR PER GMM 6-2-100 REVISON122

Part: STRINGER — CORRODED (FUSELAGE) · airframe 41,903 hrs · 16,512 cycles

AV COMPARTMENT STRINGER 44 RT FOUND HEAVY CORROSION AT FRAME 16 LOCATION. COMPLIED WITH EA 6-5310-T0310620 PART 1 TITLE :FUSELAGE MAINFRAME SECTION 12. CORROSION ON STRINGER S-44 RH AT FR 16. THE REPAIR WAS CATEGORY "B' AND WAS CLASSIFIED AS MAJOR PER GMM 6-2-100 REVISION .123 THE INSPECTION THRESHOLD WAS 40000FC AFTER REPAIR EMBODIMENT. THE REPETITIVE INSPECTION INTERVALS AND METHOD WERE TED

Part: COMPUTER — FAILED (FUEL SYSTEM) · airframe 41,888 hrs · 16,505 cycles

PASSING 10000 FT TRIM TANK PUMPS ECAM MSG FUEL QTY SHOWED 34K TOTAL, 64.2 TAKEOFF FUEL. ECAM MSG SELF-CLEARED & FUEL SLOWLY ROSE AGAIN, FUEL WAS GOOD. AFTER TAKEOFF PLUS 45 MIN TOTAL LOSS OF FUEL QTY SYS. RTB SENSOR STATUS SHOWED FQ 3 FAIL. R & R FQIC IAW AMM 28-42-38-04 & CARRIED OUT FQIC OPERATIONS TEST SATISFACTORY IAW AMM28-42-38-05 ALL FUEL INDICATION NORMAL ON BOTH OVERHEAD FUEL INDICATORS & ECAM FUEL PAGE. PERFORMED TRIM TANK PUMP TEST IAW AMM 28-27-00-05 ALL SATISFACTORY ACFT OK FOR SERVICE.

Part: PULLEY — DEFECTIVE (RT AILERON) · airframe 41,815 hrs · 16,469 cycles

ON DEPARTURE CLIMB WITH AUTO PILOT NR 2 ON WHEN THE SLATS WERE RETRACTED THE ACFT GAVE VERY HARD TO THE RT. THE AILERONS COMPENSATED BY GOING LT 6 UNITS. AT THIS POINT WE CHECKED THE FLIGHT CONTROL POS PAGE & SPOILERS 7, 6 & 5 ON THE LT WING WERE UP. AFTER DISCONNECTING THE AUTO PILOT EVENTUALLY THE SPOILERS CAME DOWN. BUT THE AILERONS STILL SHOWED HANDS LT. CONSULTED QRH & DECIDED TO RETURN FOR AN OVERWEIGHT LANDING. REMOVED AND REPLACED THE PULLEY AT RT WING ROOT (IPC 27-11-05-2/ITEM90, P/N:NSA8121-11) PER AMM 20-29-11-00, PERFORMED ADJUSTMENT OF CONTROL CABLE TENSION PER AMM27-10-00-05, CHECKED NML, PERFORMED OPERATIONAL TEST PER AMM 27-11-00-05 SATIS. FLIGHT TEST SATISFACTORY.

Part: RIB — CORRODED (RT WING) · corrosion level 2 · airframe 41,695 hrs · 16,414 cycles

RIGHT RIB 5 FWD LUG HAS CORROSION IN BORE, FWD & AFT FACES. COMPLIED WITH EA 6-5710-T0307941 P-2, WING BASIC WING STRUCTURE, LT & RT RIB 5 FWD LUG CORROSION. MAJOR REPAIR.

Part: RIB — CORRODED (ZONE 500) · corrosion level 2 · airframe 41,695 hrs · 16,414 cycles

LEFT RIB 5 FWD LUG HAS CORROSION IN BORE, FWD & AFT FACES. COMPLIED WITH EA 6-5710-T0307941 P-1. MAJOR REPAIR.

Part: TRU — FAULTED (E&E BAY) · airframe 41,372 hrs · 16,267 cycles

ESS TR INDICATED 4A NUMEROUS TIMES IN CRUISE. FOUND ONLY 4A ON ESS TR & I ESS TRANSFORMER RECTIFIER IAW MM 24-32-11-04. OPERATIONS CHECK SATISFACTORY RUN NR 2 ENG IAW A310JRH. GOOD DC LOAD DISTRIBUTION, ACFT OK FOR SERVICE.

Part: SPAR — DAMAGED (RT NACELLE) · airframe 38,883 hrs · 15,033 cycles

RT PYLON SPIGOT RECEPTACLE FITTING FOUND A MISDRILLED BOLT HOLE. REPAIRED IAW AMM 54-50-00 AND AMM 20-21-12

Part: SKIN — CONTAMINATED (RUDDER) · airframe 38,883 hrs · 15,033 cycles

TWO WATER TRAPPED AREAS WERE FOUND AT RT RUDDER NR 27 SCREW (5.5" X 5") AND NR 38 SCREW (3" X 1.5") (EO 6-5530-7-5004, PART 2) NDT INSPECT L/E AND T/E. THE OUTER SKIN AND EVLUATED THE DIMENSION OF THE DAMAGED AREA ARE 5.5"X5" (NR 27 SCREW) AND 3"X1.5" (NR 38 SCREW). REPAIRED THE AREA WITH NEW HONEYCOMB CORE, LAMINATING RESIN, CARBON FIBER AND FIBERGLASS CLOTH IAW SRM 55-41-12. THE REPAIR EVLUATED PER GMM 6-2-100 AND CLASSIFIED AS MINOR.

Part: SKIN — CORRODED (LT WING) · airframe 38,883 hrs · 15,033 cycles

LEFT WING BOTTOM SKIN UPPER SURFACE CORRODED AT RIB 5 REINFORCING BEHIND REAR SPAR AREA. REMOVED CORROSION IAW EA 6-5730-149035. REPAIR CLASSIFIED AS MINOR IAW GMM 6-2-100.

Part: SKIN — CORRODED (RT WING) · airframe 38,883 hrs · 15,033 cycles

RIGHT WING UPPER SKIN NEAR REAR SPAR FOUND CORROSION POSITION BETWEEN RIB 4 AND RIB 6. PERFORMED THE REPAIR IAW EA 6-5730-1490. REPAIR EVALUATED IAW GMM 6-2-100 AND CLASSIFIED AS MINOR.

Part: SKIN — DENTED (BS 794-815) · airframe 38,883 hrs · 15,033 cycles

NOSE SECTION RT LOWER HALT SKIN PLATE EXTERNAL HAS A DENT JUST BELOW COCKPIT FLOOR LEVEL LOCATION BETWEEN FR2 AND FR3 POSITION 1. PAIN REMOVED IAW SRM 51-75-20. CUT OUT THE DAMAGED AREA. REPAIRED THE REWORK AREA WITH FASTENERS AND DOUBLER REFER TO SRM 53-11-12. FIRST INSP AFTER REPAIR EMBODIMENT 40,000 FC/ 116,000 FH ( 55,033 FC / 154,883 FH ). THE REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100. PAINT TOUCHED UP IAW SRM 51-75-10.

Part: SKIN — CORRODED (RT WING) · airframe 38,883 hrs · 15,033 cycles

RIGHT WING UPPER SKIN NEAR REAR SPAR FOUND CORROSION POSITION BETWEEN RIB 25 AND RIB 26. BLENDED OUT TO A SMOOTH POLISHED PROFILE AND MEASURE DAMAGE AND FOUND WITHIN ALLOWABLE LIMITS IAW SRM 57-20-12. RESTORED THE SURFACE PROTECTION IAW SRM 51-49-00 AND 51-21-10. REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS MINOR.

Part: SKIN — CORRODED (RT WING) · airframe 38,883 hrs · 15,033 cycles

RIGHT WING UPPER SKIN NEAR MIDDLE SPAR FOUND CORROSION POSITION BETWEEN RIB 8 AND RIB 9. BLENDED OUT TO A SMOOTH POLISHED PROFILE AND MEASURE THE DAMAGE AND FOUND WITHIN ALLOWABLE LIMITS IAW SRM 57-20-12. RESTORED THE SURFACE PROTECTION IAW SRM 51-49-00 AND 51-21-10. REPAIR EVLUATED PER GMM 6-2-100 AND CLASSIFIED AS MINOR.

Part: SKIN — CORRODED (RT WING) · airframe 38,883 hrs · 15,033 cycles

RIGHT WING UPPER SKIN NEAR REAR SPAR FOUND CORROSION POSITION AT RIB 7. BLENDED OUT TO A SMOOTH POLISHED PROFILE AND MEASURE THE DAMAGE AND FOUND WITHIN ALLOWABLE LIMITS IAW SRM 57-20-12. RESTORED THE SURFACE PROTECTION IAW SRM 51-49-00 AND 51-21-10. REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS MINOR.

Part: SKIN — CORRODED (RT WING) · airframe 38,883 hrs · 15,033 cycles

RIGHT WING UPPER SKIN NEAR FRONT SPAR FOUND CORROSION POSITION BETWEEN RIB 8 AND RIB 9. BLENDED OUT TO A SMOOTH POLISHED PROFILE AND MEASURE DAMAGE AND FOUND WITHIN THE ALLOWABLE DAMAGE LIMIT IAW SRM 57-20-12. RESTORED SURFACE PROTECTION IAW SRM 51-49-00 AND 51-21-10. THE REPAIR EVALUATED IAW GMM 6-2-100 AND CLASSIFIED AS MINOR.

Part: SKIN — CORRODED (RT WING) · airframe 38,883 hrs · 15,033 cycles

RT WING UPPER SKIN FOUND CORROSION POSITION ABOUT RIB 27 BESIDE THE OTBD JET FUEL PANEL. BLENDED OUT TO A SMOOTH POLISHED PROFILE AND MEASURED THE DAMAGE AND FOUND WITHIN ALLOWABLE LIMITS IAW SRM 57-20-12. RESTORED THE SURFACE PROTECTION IAW SRM 51-49-00 AND 51-21-10. REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100.

Part: SKIN — CORRODED (RT WING) · airframe 38,883 hrs · 15,033 cycles

RT WING UPPER SKIN NEAR REAR SPAR FOUND CORROSION POSITION BETWEEN RIB 28 AND RIB 29. BLENDED OUT TO A SMOOTH POLISHED PROFILE AND MEASURED THE DAMAGE AND FOUND WITHIN THE ALLOWABLE DAMAGE LIMITS IAW SRM 57-20-12. RESTORED THE SURFACE PROTECTION IAW SRM 51-49-00 AND 51-21-10. REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS MINOR.

Part: FLOOR SUPPORT — CORRODED (MAIN DECK) · airframe 38,883 hrs · 15,033 cycles

FWD MAIN DECK COURIER FLOOR AREA FOUND FLOOR SUPPORT CORRODED FROM FR 12 TO FR 14 BETWEEN Y 383 AND Y 953. REPLACED WITH NEW SUPPORT IAW SRM 51-40-21 AND 51-72-10. THE REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: SKIN — CORRODED (RT WING) · airframe 38,883 hrs · 15,033 cycles

RIGHT WING UPPER SKIN NEAR FRONT SPAR FOUND CORROSION POSITION BETWEEN RIB 20 AND RIB 21. BLENDED OUT TO A SMOOTH POLISHED PROFILE AND MEASURE THE DAMAGE AND FOUND WITHIN ALLOWABLE LIMITS IAW SRM 57-20-12. RESTORED SURFACE PROTECTION IAW SRM 51-49-00 AND 51-21-10. THE REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS MINOR.

Part: SKIN — CORRODED (RT WING) · airframe 38,883 hrs · 15,033 cycles

RIGHT WING UPPERSKIN NEAR FRONT SPAR FOUND CORRODED, POSITION BETWEEN RIBS 16 AND 17. BLENDED OUT TO A SMOOTH POLISHED PROFILE AND MEASURE THE DAMAGE AND FOUND WITHIN ALLOWABLE LIMITS IAW SRM 57-20-12. RESTORED THE SURFACE PROTECTION IAW SRM 51-49-00 AND 51-21-10. THE REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS MINOR.

Part: SEAT TRACK — CHAFED (MAIN DECK) · airframe 38,883 hrs · 15,033 cycles

MAIN DECK SEAT TRACK CHAFED BETWEEN FR 54.2 AND FR 54.3, Y1456. FABRICATED THE SEAT TRACK IAW SRM 51-40-21 AND DWG NR 16, A53274256. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100.

Part: SEAT TRACK — CHAFED (MAIN DECK) · airframe 38,883 hrs · 15,033 cycles

MAIN DECK SEAT TRACK CHAFED BETWEEN FR 54.2 AND FR 54.3, Y0. FABRICATED THE SEAT TRACK IAW SRM 51-40-21 AND DWG NR 16 A53274256. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100.

Part: ENGINE — FAILED (NR 2) · airframe 38,564 hrs · 14,898 cycles

CLIMBING THRU FL300 F/O FELT SLIGHT VIBRATION, BUT NO INDICATIOINS OR ECAM AT FL 355, THERE WAS A YAW AND LOUD BANGING, EPR HAD DROPPED TO BELOW 1, OTHER ENGINE INSTRUMENTS LOOKED NORMAL, BUT THE LOUD BANGING CONTINUED WITH THROTTLE AT IDLE. OIL PRESSURE WAS 2 PSI AFTER ENGINE SHUTDOWN AND NR 1 AGENT WAS DISCHARGED, AFTER FIRE HANDLE WAS PULLED, IAW QRH, DUE CONTINUED BANGING AND SUSPECTED DAMAGE. CHECKED EXHAUST AREA FOUND SOME METAL DEBRIS AND FADEC REPORT FAULT CODE ON NR 2 CHANNEL A & B 350-0010. REMOVED AND REPLACED NR 2 ENGINE.

Part: DAMPER — LEAKING (MLG) · airframe 36,868 hrs · 14,172 cycles

LANDING GEAR WOULD NOT RETRACT ON DEPARTURE, RETURNED TO RPVM, HAD LANDING GEAR RETRACTION FAULT PROX. DETECTION BOX FAULTED TO "BR" - BOGIE RIGHT FAIL. ON INSPECTION RT MAIN GEAR, FOUND PITCH DAMPER BUTTON POPPED OUT. FAILED RETRACTION ON BOTH SYSTEMS. COMPLETED RH MAIN GEAR PITCH DAMPER REPLACEMENT IAW AMM 32-11-15-04. CHARGE PITCH DAMPER NITROGEN CHAMBER PER AMM 12-12-32 P. BLK 501. PROX BOX RESETTED, AND AIRCRAFT OK FOR SERVICE.

Part: SELECTOR VALVE — FAILED (MLG) · airframe 36,868 hrs · 14,171 cycles

LOWERED MLG HANDLE (WITH SYS 2, POSITION DET SELECTED) GOT UNLOCK LIGHTS BUT NO MLG DOWN, SELECTED SYS 1, NO CHANGE, RAISED MLG HANDLE, LIGHTS WENT OUT, LOWERED MLG AGAIN IN SYS 2, AND MLG CAME DOWN NORMALLY. BITE ON PROX BOX, NO FAULT REGISTERED, FOLLOWED TSM 32-30-00 PG 111, SELECTOR VALVE CONFIRMED 28VDC BET PINS E & F ON CONNECTOR 3GA-A, R & R 3GA MLG SELECTOR VALVE IAW AMM 32-31-12 AND 2GA. MLG SWITCHING CONTROL LEVER UNIT IAW 32-31-11-04 AND CARRIED OUT MLG FLT SIM TEST BOX IAW AMM 32-00-00. ALL TESTED GOOD EXCEPT RT NLG DOOR. R & R NLG DOOR ACTUATING CYLINDER IAW 32-31-16-04, USE TEST BOX FOR SIM OF NLG DOOR SWING & UNLOCK LIGHTS IN FLT MODE IAW AMM 32-00-00 P. BLK 501, CHECKED GOOD. OK FOR SERVICE.

Part: CONNECTOR — DIRTY (TEST SWITCH) · airframe 36,823 hrs · 14,151 cycles

CLIMBING THROUGH FL330 GOT RT R1 DOOR NOT CLOSED COMPLIED WITH QRH AND DESCENTED BELOW 10,000. GOING THROUGH FL200 THE WARNING WENT AWAY. ATC WOULD NOT LET US CONTINUE AT 10,000 SO RETURNED TO DEPARTURE. CABIN PRESSURE WAS GOOD. ALL NORMAL, CLEANED THE CONNECTORS OF 2 SWITCH (42WS ADN 8WS), AND PERFORMED THE TEST OF SWITCH IAW AMM52-71-11-05, TEST PASSED, CARRIED OUT THE TEST OF CABIN PRESSURIZATION IAW AMM 21-31-00-5, PRESSURIZED CABIN PRESSURE TO 8PSI, CHECKED DOOR STATUS, ALL NORMAL. R & R 181VD AND FWC NR2 PRECAUTIONARY .

Part: PITOT HEAD — CONTAMINATED · airframe 36,727 hrs · 14,103 cycles

F/O A/S INOP DURING T/O ROLL ABORTED T/O. PVG U CHECKED F/O PITOT TUBE FOUND A BUG INSIDE, CLEARED PITOT TUBE AND PERFORMED THE PITOT TUBE INSP ALL OK IAW AMM 34-11-15-6, PERFORMED AUTO LAND SYS TEST PASSED IAW AMM 22-00-00, ACFT REMAINED CAT 3III, ACFT OK FOR SVC. FINAL CLOSED.

Part: SKIN — MISREPAIRED (ZONE 500) · airframe 35,615 hrs · 13,583 cycles

PREVIOUS FLUSH REPAIR LOCATED ON LT WING NR 2 SLAT UPPER NOSE SKIN BETWEEN RIBS 14 TO 17 MEASURES 11.7 INCHES X 9.8 INCHES. PREVIOUSLY INSTALLED REPAIR LOCATED AT LT WING NR 2 SLAT UPPER NOSE SKIN BETWEEN RIBS 14 TO 17 WAS DETERMINE NOT TO BE IAW EA6-5710-81010A DUE TO 16 EACH FASTENERS WITH NO LOCKING RINGS, BASED ON A VISUAL EVALUATION WITH THE REPAIR INSTALLED. VISUAL EVALUATION CONSISTED OF CORRECT LOCATION, SHAPE, SIZE, FASTENER TYPE, NUMBER, SPACING AND EDGE MARGIN, MATERIAL THICKNESS AND TYPE ALSO GENERAL WORKMANSHIP OF PREVIOUS INSTALLATION. REMOVED AND REPLACED 16 EACH FASTENERS IAW EA 6-5750-135145, THIS REPAIR IS ACCEPTABLE IAW RAS/SA/291/2009 ISSUE A PERMANENT. REPAIR IS CLASSIFIED AS A MAJOR REPAIR IAW GMM 6-2-100. THIS IS AN AGING ACFT INSPECTION FINDING.

Part: SKIN — MISREPAIRED (ZONE 100) · airframe 35,615 hrs · 13,583 cycles

PREVIOUS EXTERNAL REPAIR DOUBLER LOCATED AT RT SIDE FUSELAGE SKIN AT FRAME 74 AND BETWEEN STRINGERS 39 TO 41 RT MEASURES 9 INCHES X 7.2 INCHES, WITH A SKIN CUTOUT BETWEEN STRINGERS 39 AND 40 RT MEASURES 2.7 INCHES X 1.7 INCHES. PREVIOUSLY INSTALLED REPAIR LOCATED AT RT SIDE FUSELAGE SKIN AT FRAME 74 AND BETWEEN STRINGERS 39 TO 41 RT WAS DETERMINED NOT TO BE IAW SRM 53-10-12 FIG 225 SHEET 2, DUE TO OUTER FASTENER ROW IS 5/32 RIVETS. REPAIR IS DONE IAW SRM 53-10-12 FIG 205 WHICH IS NOT EFFECTIVE ANYMORE, BASED ON A VISUAL EVALUATION OF REPAIR INSTALLED. VISUAL EVALUATION CONSISTED OF, CORRECT LOCATION, SHAPE, SIZE, FASTENER TYPE, NR, SPACING AND EDGE MARGIN, MATERIAL THICKNESS AND TYPE ALSO GENERAL WORKMANSHIP OF PREVIOUS INSTALLATION. REMOVED AND REPLACED OUTER FASTENER ROW WITH NAS1097DD 6 RIVETS IAW SRM 53-10-12 FIG 225 SHEET 2. THIS IS A MAJOR REPAIR IAW GMM 6-2-100. FOLLOW UP TRACKING IAW EA6-5318-81085 THIS IS AN AGING ACFT INSPECTION FINDING.

Part: SKIN — CORRODED (ZONE 500) · corrosion level 2 · airframe 35,608 hrs · 13,578 cycles

LT WING UPPER SURFACE GRAVITY FUEL PORT INBD HAS LEVEL 1 CORROSION AROUND CUT-OUT EXTENDING UNDER SKIN APROX 1" TO 1.5" REPAIRED UPPER WING SKIN AROUND LT UPPER FUEL PORT IAW EA NR 6-5730-135142 AND A/B DWG R57349265 AND RAS NR RAS/BAE/1011485/2009 ISSUE 'A DUE TO LEVEL 1 CORROSION BEING OUT OF LIMITS IAW SRM 57-20-12.

Part: SENSOR — MALFUNCTIONED (MLG) · airframe 34,957 hrs · 13,118 cycles

AFTER T/O LANDING GEAR FAILED TO RETRACT. ECAM DISPLAYED L/G RETRACTION INOP. ACFT LOST AUTO-THROTTLES. FOUND TARGET SENSORS 9GA AND 11GA LOS SE AND OUT OF "C" DIMENSIONS OUT OF LIMITS; REMOVED AND REPLACED SENSORS 9GA AND 11GA ON LT BOGIE REF. MM 32-00-00-4. JACKED ACFT AND PERFORMED GEAR SWING REF MM 32-31-00 IN BOTH SYSTEMS 1 AND 2, OPS CHECK NORMAL, NO DEFECTS NOTED AT THIS TIME.

Part: SELECTOR VALVE — FAILED (MLG) · airframe 34,633 hrs · 12,902 cycles

LDG GEAR DID NOT EXTEND WITH GEAR HANDLE, GRAVITY EXTENSION OK PER CREW DEBRIEF, WHEN GEAR HANDLE CYCLED THERE WAS NO ASSOCIATED AUDIABLE SOUND NORMALLY HEARD DURING GEAR EXTENSION. CREW DID NOT TRY SELECTING LDG GEAR POSITON DET SYSTEM TO "2" DURING ATTEMPTS TO EXTEND GEAR. FOUND THE LANDING GEAR SELECTOR VALVE BAD GND. REMOVED AND REPLACED THE LANDING GEAR SELECTOR VALVE PER MM 32-31-12-4. ALL OPS AND LEAK CHECKS WERE NORMAL OK FOR SERVICE.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 33,706 hrs · 12,343 cycles

FOUND PITTING CORROSION ON STRINGER 44 RT, BETWEEN FRAME 54-55/58. REPAIR PERFORMED BY REPLACEMENT OF STRINGER PORTION AS LONG AS POSSIBLE BY USING ADDITIONAL COUPLINGS AS PER SRM 53-10-14/FIG 201 AND IAW SRM 51-72-10.

Part: STRINGER SPLICE — CORRODED (ZONE 100) · corrosion level 2 · airframe 33,706 hrs · 12,343 cycles

FOUND FIVE CORRODED STRINGER COUPLINGS AT FRAME 55/58 BETWEEN STRG 45 AND 49 LT. REPLACEMENT OF THE FIVE COUPLINGS IAW SRM 51-72-10.

Part: STRINGER SPLICE — CORRODED (ZONE 100) · corrosion level 2 · airframe 33,706 hrs · 12,343 cycles

FOUND CORRODED STRINGER COUPLING AT FRAME 55/58, STRG 50 LT. REPLACEMENT OF COUPLING IAW SRM 51-72-10.

Part: RIB — DAMAGED (ZONE 600) · airframe 33,706 hrs · 12,343 cycles

FOUND DAMAGE (NICK) ON RT WING TRAILING EDGE AILERON HINGE RIB, WITH MINIMUM REMAINING THICKNESS OF 2,2MM. REPAIR PERFORMED BY BLEND OUT DAMAGE, HFEC INSPECTION AND FLAP PEENING IAW EA 6-5751-81123 AND RAS/BAE/1272/2004 ISSUE A.

Part: SPAR — CORRODED (ZONE 400) · corrosion level 2 · airframe 33,706 hrs · 12,343 cycles

CORROSION FOUND ON THE UPPER SURFACE OF THE LT PYLON LOWER SPAR BETWEEN RIBS 4-8, FURTHER TO HYDRAULIC FLUID CONTAMINATION. REPAIR PERFORMED BY BLENDING OUT CORROSION, CUTTING OUT THE MOST DAMAGED AREAS AND INSTALLING A DOUBLER TO REINFORCE THE AREA IAW EA 6-5451-81096 AND RAS 034151/024/2004 ISSUE A.

Part: COUPLING — CORRODED (ZONE 100) · corrosion level 2 · airframe 33,706 hrs · 12,343 cycles

FOUND CORRODED STRINGER COUPLING AT FRAME 55/58, STRG 52 RT. REPLACEMENT OF COUPLING IAW SRM 51-72-10.

Part: STRINGER SPLICE — CORRODED (ZONE 100) · corrosion level 2 · airframe 33,706 hrs · 12,343 cycles

FOUND TWO CORRODED STRINGER COUPLINGS AT FRAME 55/58, STRG 48 AND 49 RT. REPLACEMENT OF BOTH COUPLINGS IAW SRM 51-72-10.

Part: SKIN PANEL — WORN (ZONE 600) · airframe 33,706 hrs · 12,343 cycles

ELONGATED WING TO PYLON HYDRAULIC FITTING HOLES IN LOWER WING SKIN PANEL NR 2 RT WING. REPAIR PERFORMED BY OVERSIZING HOLES AND INSTALLING BUSHES IAW R572-49184 ISSUE C, APPROVED BY EA 6-5720-81095 AND RAS/BAE/1000166/2005 ISSUE A.

Part: FLAP — UNKNOWN (ZONE 500) · airframe 33,706 hrs · 12,343 cycles

FOUND OLD REPAIR ON INNER FLAP LT AT RIB 21, POCKET REPAIRS AS PER SB A310-57-2054. REPLACEMENT OF END RIB AS PER SB A310-57-2055, ISSUED AND APPROVED PER EA 6-5752-81084.

Part: FLOORBEAM — CORRODED (ZONE 100) · corrosion level 2 · airframe 33,706 hrs · 12,343 cycles

HEAVY CORROSION ON CROSSBEAM AT FRAME 65 RT, CARGO COMPARTMENT FLOOR STRUCTURE, CARGO DOOR AREA. REPLACEMENT OF CROSSBEAM IAW SRM 51-72-10.

Part: STRINGER SPLICE — CORRODED (ZONE 100) · corrosion level 2 · airframe 33,706 hrs · 12,343 cycles

FOUND CORRODED STRINGER COUPLING AT FRAME 55/58, STRG 51 RT. REPLACEMENT OF COUPLING IAW SRM 51-72-10.

Part: WEB — DAMAGED (ZONE 200) · airframe 33,706 hrs · 12,343 cycles

CRACKED SHEAR WEB BETWEEN FRAME 74-75, STRG 26 RT. REPLACEMENT OF SHEAR WEB IAW SRM 51-72-10.

Part: STRINGER SPLICE — CORRODED (ZONE 100) · corrosion level 2 · airframe 33,706 hrs · 12,343 cycles

FOUND CORRODED STRINGER COUPLING AT FRAME 55/58, STRG 51 LT. REPLACEMENT OF COUPLING IAW SRM 51-72-10.

Part: SKIN — DENTED (TE FLAP) · airframe 33,706 hrs · 12,343 cycles

DENT ON LT WING OUTBOARD FLAP OUTER SKIN LOWER SIDE BETWEEN RIB 1-2. REPAIR PERFORMED BY CUT OUT OF DAMAGED SKIN AND CORE AND INSTALLING FABRICATED REPAIR DOUBLER IAW SRM 51-77-12/FIG 217.

Part: STRINGER SPLICE — CORRODED (ZONE 100) · corrosion level 2 · airframe 33,706 hrs · 12,343 cycles

FOUND TWO CORRODED STRINGER COUPLINGS AT FRAME 55/58, STRG 53 AND 54 LT. REPLACEMENT OF BOTH COUPLINGS IAW SRM 51-72-10.

Part: FLOORBEAM — CORRODED (ZONE 100) · corrosion level 2 · airframe 33,706 hrs · 12,343 cycles

HEAVY CORROSION ON CROSSBEAM AT FRAME 67 RT, AFT CARGO COMPARTMENT FLOOR STRUCTURE, CARGO DOOR AREA. REPLACEMENT OF CROSSBEAM IAW SRM 51-72-10.

Part: COUPLING — CORRODED (ZONE 100) · corrosion level 2 · airframe 33,706 hrs · 12,343 cycles

FOUND CORRODED COUPLING AT FRAME 55/58, STRG 44 LT. REPLACEMENT OF COUPLING IAW SRM 51-72-10.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 33,706 hrs · 12,343 cycles

HEAVY CORROSION ON STRINGER 53 LT AND RT BETWEEN FRAME 54-54.2. AFFECTED STRINGERS REPLACED IAW EA 6-5316-81072, APPROVED BY RAS/DATLS/0002275/2004 ISSUE A.

Part: COUPLING — DAMAGED (ZONE 100) · airframe 33,706 hrs · 12,343 cycles

FOUND OLD MISDRILLED HOLES IN COUPLING AT FRAME 73, BETWEEN STRG 33-36 LT. REPLACEMENT OF COUPLING IAW SRM 51-72-10.

Part: STRINGER SPLICE — CORRODED (ZONE 100) · corrosion level 2 · airframe 33,706 hrs · 12,343 cycles

FOUND CORRODED STRINGER COUPLING AT FRAME 55/58, STRG 52 LT. REPLACEMENT OF COUPLING IAW SRM 51-72-10.

Part: BEAM — CORRODED (ZONE 100) · corrosion level 2 · airframe 33,706 hrs · 12,343 cycles

HEAVY CORROSION ON BEAM 10 BETWEEN FRAME 67-69, STRG 45-47 RT, BULK CARGO COMPARTMENT DOOR. REPLACEMENT OF BEAM IAW SRM 51-72-10.

Part: COUPLING — CORRODED (ZONE 100) · corrosion level 2 · airframe 33,706 hrs · 12,343 cycles

FOUND CORRODED STRINGER COUPLING AT FRAME 55/58, STRG 56 LT AND RT SIDE. REPLACEMENT OF BOTH COUPLINGS IAW SRM 51-72-10.

Part: SKIN PANEL — CORRODED (ZONE 600 - RH) · corrosion level 2 · airframe 33,706 hrs · 12,343 cycles

FOUND SEVERAL OLD REPAIRS OF THE WING TOP SKIN PANEL BETWEEN RIB 9-23 RT WITH NEW CORROSIONS SPOTS. REPAIR PERFORMED BY BLEND OUT CORROSION, FLAP PEENING REWORKED AREAS IAW EA 6-5720-81120, RAS/BAE/0203/2000 ISSUE A AND RAS/BAE/1409/2004 ISSUE A.

Part: COUPLING — CORRODED (ZONE 100) · corrosion level 2 · airframe 33,706 hrs · 12,343 cycles

FOUND CORRODED COUPLING AT FRAME 55/58, STRG 55 LT AND RT SIDE. REPLACEMENT OF COUPLING IAW SRM 51-72-10.

Part: FLOORBEAM — CORRODED (ZONE 100) · corrosion level 2 · airframe 33,706 hrs · 12,343 cycles

HEAVY CORROSION ON CROSSBEAM AT FRAME 61 RT, CARGO COMPARTMENT FLOOR STRUCTURE, CARGO DOOR AREA. REPLACEMENT OF CROSSBEAM IAW SRM 51-72-10.

Part: SKIN PANEL — WORN (ZONE 500) · airframe 33,706 hrs · 12,343 cycles

ELONGATED WING TO PYLON HYDRAULIC FITTING HOLES IN LOWER WING SKIN PANEL NR 2. REPAIR PERFORMED BY OVERSIZING HOLES AND INSTALLING BUSHES IAW R572-49184 ISSUE C, APPROVED BY EA 6-5720-81095 AND RAS/BAE/1000166/2005 ISSUE A.

Part: RIB — DAMAGED (ZONE 600) · airframe 33,706 hrs · 12,343 cycles

FOUND DAMAGE (NICK) ON RT WING TRAILING EDGE AILERON HINGE RIB (INBOARD), WITH A MINIMUM REMAINING THICKNESS OF 1,7MM (NOMINAL 2,3MM). REPAIR PERFORMED BY BLEND OUT DAMAGE, HFEC INSPECTION AND FLAP PEENING IAW EA 6- 5751-81123 AND RAS/BAE/1272/2004 ISSUE A.

Part: PROFILE — CORRODED (ZONE 100) · corrosion level 2 · airframe 33,706 hrs · 12,343 cycles

HEAVY CORROSION ON WEDGE PROFILE AT FRAME 63 BETWEEN STRG 37-41 LT, REPLACEMENT OF WEDGE IAW SRM 51-72-10.

Part: FLAP — UNKNOWN (ZONE 600) · airframe 33,706 hrs · 12,343 cycles

FOUND OLD REPAIR ON INNER FLAP RT AT RIB 21, POCKET REPAIRS AS PER SB A310-57-2054. REPLACEMENT OF END RIB AS PER SB A310-57-2055, ISSUED AND APPROVED PER EA 6-5752-81084.

Part: SKIN PANEL — CORRODED (ZONE 500) · corrosion level 2 · airframe 33,706 hrs · 12,343 cycles

FOUND OLD BLEND OUT REPAIRS WITH NEW CORROSION SIGNS ON LT WING UPPER SKIN BETWEEN RIB 3 TO 5 NEAR THE REAR SPAR AND BETWEEN RIB 7 TO 8 AND RIB 10 TO 11 AT THE FRONT SPAR. THE CORRODED AREAS HAVE BEEN REPAIRED IAW WITH SRM 57-00-00/PG 201/PARA 4C PART B AND TD/B/2004/0443 ISSUE B, APPROVED BY EA 6-5720-81121 AND RAS/BAE/1409/2004 ISSUE A.

Part: STRINGER SPLICE — CORRODED (ZONE 100) · corrosion level 2 · airframe 33,706 hrs · 12,343 cycles

FOUND CORRODED STRINGER COUPLINGS AT FRAME 55/58, STRG 53 AND 54 RT. REPLACEMENT OF BOTH COUPLINGS IAW SRM 51-72-10.

Part: STRINGER SPLICE — CORRODED (ZONE 100) · corrosion level 2 · airframe 33,706 hrs · 12,343 cycles

FOUND CORRODED STRINGER COUPLING AT FRAME 55/58, STRG 50 RT. REPLACEMENT OF COUPLING IAW SRM 51-72-10.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 33,706 hrs · 12,343 cycles

FOUND PITTING CORROSION ON FOLLOWING STRINGER: 48 AND 50 RT AND STRG 46, 47, 48, 50 AND 51 LT, BETWEEN FRAME 54-55/58. REPAIR PERFORMED BY REPLACEMENT OF STRINGER PORTION AS LONG AS POSSIBLE BY USING ADDITIONAL COUPLINGS AS PER SRM 53-10-14/FIG 201 AND IAW SRM 51-72-10.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 33,706 hrs · 12,343 cycles

FOUND PITTING CORROSION ON FOLLOWING MILLED STRINGER: 52, 53 AND 54 RT AND STRG 52, 53, 54 AND 56 LT, BETWEEN FRAME 54.1-55/58. REPAIR PERFORMED BY REPLACEMENT OF STRINGER PORTIONS AS LONG AS POSSIBLE BY USING ADDITIONAL COUPLINGS AS PER SRM 53-10-14/FIG 201A AND IAW SRM 51-72-10.

Part: STRUT — CORRODED (ZONE 200) · corrosion level 2 · airframe 33,706 hrs · 12,343 cycles

CORRODED CROSS STRUTS FWD OF FRAME 86 RT, STRG 15. REPLACEMENT OF CROSS STRUT IAW SRM 51-72-10.

Part: ANGLE — CORRODED (ZONE 100) · corrosion level 2 · airframe 33,706 hrs · 12,343 cycles

CORRODED COUPLING ANGLE AT FRAME 69, STRINGER 49-51 RHS. REPLACEMENT OF COUPLING ANGLE IAW SRM 51-72-10.

Part: PLATE — CORRODED (ZONE 100) · corrosion level 2 · airframe 33,706 hrs · 12,343 cycles

CORRODED SHEAR PLATES AT FWD CARGO COMPARTMENT BETWEEN FRAME 38.2-39, STRG 43-44 LT AND RT. REPLACEMENT OF SHEAR PLATES IAW SRM 51-72-10.

Part: FITTING — CORRODED (ZONE 100) · corrosion level 2 · airframe 33,706 hrs · 12,343 cycles

HEAVY CORROSION ON CLIP AT FRAME 60, BETWEEN STRG 55-56 LT. REPLACEMENT OF CLIP IAW SRM 51-72-10.

Part: LONGERON — CORRODED (ZONE 100) · corrosion level 2 · airframe 33,706 hrs · 12,343 cycles

CORROSION ON LONGITUDINAL PROFILE AT BULC CARGO COMPARTMENT FLOOR STRUCTURE BETWEEN FRAME 67-69, STRG 45-47 RT. REPLACEMENT OF LONGITUDINAL PROFILE IAW SRM 51-72-10.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 33,706 hrs · 12,343 cycles

HEAVY CORROSION ON STRINGER 54 BETWEEN FRAME 65-58 LT. STRINGER SPLICE REPAIRS PERFORMED IAW SRM 53-10-14/FIG 201.

Part: PLATE — CORRODED (ZONE 100) · corrosion level 2 · airframe 33,706 hrs · 12,343 cycles

CORRODED SHEAR PLATE AT FWD CARGO COMPARTMENT BETWEEN FRAME 22-23, STRG 43-44 LT. REPLACEMENT OF SHEAR PLATE IAW SRM 51-72-10.

Part: SEAT TRACK — CORRODED (ZONE 200) · corrosion level 2 · airframe 33,706 hrs · 12,343 cycles

HEAVY CORROSION ON SEAT TRACK BETWEEN FRAME 14-19, Y-450 RT. REPLACEMENT OF SEAT TRACK IAW SRM 51-72-10.

Part: WEB — DAMAGED (ZONE 100) · airframe 33,706 hrs · 12,343 cycles

DAMAGED WEB PLATES BETWEEN FRAME 86-87, STRG 36 RT. REPLACMENT OF WEB PLATE IAW SRM 51-72-10.

Part: WEDGE — CORRODED (RT ELEVATOR) · corrosion level 2 · airframe 33,706 hrs · 12,343 cycles

FOUND CORROSION ON RT ELEVATOR TRAILING EDGE WEDGE, BETWEEN RIB ER12-ER28. REPAIR OF ELEVATOR TRAILING EDGE WEDGE IAW SRM 55-21-11/CONFIG 2/PG 1-3.

Part: STRUT — CORRODED (ZONE 200) · corrosion level 2 · airframe 33,706 hrs · 12,343 cycles

CORRODED CROSS STRUTS FWD OF FRAME 84 LT, STRG 15. REPLACEMENT OF CROSS STRUT IAW SRM 51-72-10.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 33,706 hrs · 12,343 cycles

HEAVY CORROSION ON FOLLOWING STRINGER RT, STRINGER 48 BETWEEN FRAME 55/58-63, STRINGER 49 BETWEEN FRAME 55/58-63, STRINGER 50 BETWEEN FRAME 55/58-61, STRINGER 51 BETWEEN FRAME 55/58-65, STRINGER 52 BETWEEN FRAME 55/58-65, STRINGER 53 BETWEEN FRAME 55/58-63, STRINGER 54 BETWEEN FRAME 55/58-67 AND STRINGER 55 BETWEEN FRAME 55/58-61. STRINGER SPLICE REPAIRS PERFORMED IAW SRM 53-10-14/ FIG 201.

Part: FITTING — CORRODED (ZONE 100) · corrosion level 2 · airframe 33,706 hrs · 12,343 cycles

HEAVY CORROSION ON CLIP AT FRAME 69, BETWEEN STRG 56-57 LT. REPLACEMENT OF CLIP IAW SRM 51-72-10.

Part: PLATE — CORRODED (ZONE 100) · corrosion level 2 · airframe 33,706 hrs · 12,343 cycles

CORRODED SHEAR PLATE AT FWD CARGO COMPARTMENT BETWEEN FRAME 38.1-38.2, STRG 43-44 LT. REPLACEMENT OF SHEAR PLATE IAW SRM 51-72-10.

Part: FITTING — CORRODED (ZONE 100) · corrosion level 2 · airframe 33,706 hrs · 12,343 cycles

HEAVY CORROSION ON CLIP AT FRAME 71, BETWEEN STRG 55-56 LT. REPLACEMENT OF CLIP IAW SRM 51-72-10.

Part: WEB — DAMAGED (ZONE 100) · airframe 33,706 hrs · 12,343 cycles

FOUND DAMAGED WEB PLATES BETWEEN FRAME 85-86, STRG 33 RT. REPLACMENT OF WEB PLATE IAW SRM 51-72-10.

Part: FITTING — CORRODED (ZONE 100) · corrosion level 2 · airframe 33,706 hrs · 12,343 cycles

HEAVY CORROSION ON CLIP AT FRAME 70, BETWEEN STRG 55-56 LT. REPLACEMENT OF CLIP IAW SRM 51-72-10.

Part: PLATE — CORRODED (ZONE 100) · corrosion level 2 · airframe 33,706 hrs · 12,343 cycles

CORRODED SHEAR PLATE AT FWD CARGO COMPARTMENT BETWEEN FRAME 21-22, STRG 43-44 LT. REPLACEMENT OF SHEAR PLATE IAW SRM 51-72-10.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 33,706 hrs · 12,343 cycles

HEAVY CORROSION ON FOLLOWING STRINGER LT, STRINGER 46 BETWEEN FRAME 55/58-65, STRINGER 50 BETWEEN FRAME 55/58-65, STRINGER 51 BETWEEN FRAME 55/58-65, STRINGER 52 BETWEEN FRAME 55/58-65 AND STRINGER 53 BETWEEN FRAME 55/58-61. STRINGER SPLICE REPAIRS PERFORMED IAW SRM 53-10-14/FIG 201.

Part: PROFILE — CORRODED (ZONE 100) · corrosion level 2 · airframe 33,706 hrs · 12,343 cycles

HEAVY CORROSION ON LONGITUDINAL PROFILE AT BULK CARGO COMP FLOOR STRUCTURE BETWEEN FRAME 63-64, Y-805, RT. REPLACEMENT OF LONGITUDINAL PROFILE IAW SRM 51-72-10.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 33,706 hrs · 12,343 cycles

HEAVY CORROSION ON STRINGER 56 LT AND RT BETWEEN FRAME 55/58-65. STRINGER SPLICE REPAIRS PERFORMED IAW SRM 53-10-14 / FIG 201A.

Part: FLANGE — CORRODED (ZONE 100) · corrosion level 2 · airframe 33,706 hrs · 12,343 cycles

HEAVY CORROSION ON FLANGE BETWEEN FRAME 61-62, STRG 56 LT TO 56 RT. REPLACEMENT OF FLANGE IAW SRM 51-72-10.

Part: FITTING — CORRODED (ZONE 100) · corrosion level 2 · airframe 33,706 hrs · 12,343 cycles

HEAVY CORROSION ON CLIP AT FRAME 61, BETWEEN STRG 55-56 LT. REPLACEMENT OF CLIP IAW SRM 51-72-10.

Part: FITTING — CORRODED (ZONE 100) · corrosion level 2 · airframe 33,706 hrs · 12,343 cycles

HEAVY CORROSION ON CLIP AT FRAME 71, BETWEEN STRG 55-56 LT. REPLACEMENT OF CLIP IAW SRM 51-72-10.

Part: PROFILE — CORRODED (ZONE 100) · corrosion level 2 · airframe 33,706 hrs · 12,343 cycles

HEAVY CORROSION ON LONGITUDINAL PROFILE AT BULK CARGO COMP FLOOR STRUCTURE BETWEEN FRAME 64-67, Y-805, RT. REPLACEMENT OF LONGITUDINAL PROFILE IAW SRM 51-72-10.

Part: PLATE — CORRODED (ZONE 100) · corrosion level 2 · airframe 33,706 hrs · 12,343 cycles

CORRODED SHEARPLATES AT FWD CARGO COMPARTMENT BETWEEN FRAME 36-37 AND FRAME 38.1-38.2 RT, STRG 43-44. REPLACEMENT OF SHEAR PLATES IAW SRM 51-72-10.

Part: WEB — DAMAGED (ZONE 200) · airframe 33,706 hrs · 12,343 cycles

DAMAGED WEB PLATES BETWEEN FRAME 86-87, STRG 23 LT. REPLACMENT OF WEB PLATE IAW SRM 51-72-10.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 33,706 hrs · 12,343 cycles

CORROSION ON STRINGER 51, BETWEEN FRAME 36-37 LT, AFTER BLENDING IS THE REMAINING THICKNESS OUT OF LIMIT IAW SRM 53-10-00. STRINGER SPLICE REPAIR PERFORMED IAW SRM 53-10-14/FIG 201.

Part: FRAME — FAILED (ZONE 100) · airframe 33,706 hrs · 12,343 cycles

FOR REPLACEMENT OF STRINGER 50 LT AND RT FROM THE COUPLING FWD OF FRAME 55 (NON ROUTINE DR106) IT IS NECESSARY TO CUT FRAME 54.2 BETWEEN STRG 50-51, LT AND RT FRAME SPLICE REPAIR PERFORMED ON BOTH SIDES LT AND RT AS PER A300-600 FREIGHTER SRM 53-10-13/ FIG 203, WITH 1-2 MM GAP AFTER STRINGER INSTALLATION, APPROVED BY EA 6-5316-81081 AND RAS/DAHAM/4018801/2004 ISSUE A.

Part: FITTING — CORRODED (ZONE 100) · corrosion level 2 · airframe 33,706 hrs · 12,343 cycles

CORRODED FITTING AT FRAME 63, STRG 44 LT OF CARGO COMPARTMENT FLOOR STRUCTURE. REPAIR PERFORMED BY REPLACEMENT OF FITTING IAW SRM 51-72-10.

Part: BEAM — CORRODED (ZONE 100) · corrosion level 2 · airframe 33,706 hrs · 12,343 cycles

SEVERAL CORRODED AREAS ON SILLBEAM OF AFT CARGO COMPARTMENT CUT OUT. REPAIR PERFORMED BY REPLACEMENT BY INSTALLING AIRFRAME AND HARDWARE KIT: SR5317-99A00500 AND SR5317-99H01200 IAW SRM 53-17-18/FIG 207 / TB. 203. DEVIATIONS FROM SRM 53-17-18/FIG 207. INSTALLING SOME FASTENERS AT FRAME 61 AND 63) COVERED BY EA 6-5317-81082 AND RAS/DATLS/0002249/2004 ISSUE A (NON ROUTINE DR334).

Part: FLOORBEAM — CORRODED (ZONE 100) · corrosion level 2 · airframe 33,706 hrs · 12,343 cycles

CORROSION ON CROSSBEAM AT FRAME 63 LT, CARGO COMPARTMENT FLOOR STRUCTURE. CROSSBEAM SPLICE REPAIR PERFORMED IAW SRM 53-10-15/FIG 207.

Part: SKIN — MISREPAIRED (ZONE 200) · airframe 33,706 hrs · 12,343 cycles

FOUND OLD REPAIR DOUBLER ON AFT PAX DOOR RT OUTER SKIN LOWER EDGE, NOT CONFORM TO SRM 52-10-00/FIG 204. REPAIR RENEWED AS PER SRM 52-10-00/FIG 204.

Part: SUPPORT — MISREPAIRED (ZONE 200) · airframe 33,706 hrs · 12,343 cycles

OLD ANGLE REPAIR ON LONGERON (SUPPORT) BETWEEN FRAME 13B-16A, Y-953, FLOOR STRUCTURE, NOT CONFORM TO SRM 53-12-15 / FIG 207. REPAIR OF SUPPORT LONGERON PERFORMED IAW SRM 53-12-15/FIG 207.

Part: FLOORBEAM — CORRODED (ZONE 100) · corrosion level 2 · airframe 33,706 hrs · 12,343 cycles

CORROSION ON CROSSBEAM AT FRAME 66 RT, CARGO COMPARTMENT FLOOR STRUCTURE. CROSSBEAM SPLICE REPAIR PERFORMED IAW SRM 53-10-15/FIG 207.

Part: PROFILE — CORRODED (ZONE 100) · corrosion level 2 · airframe 33,706 hrs · 12,343 cycles

CORRODED CORNER PROFILE (FITTING) BETWEEN FRAME 63-64 LT, CARGO COMPARTMENT FLOOR STRUCTURE. REPAIR PERFORMED BY REPLACEMENT OF CORNER PROFILE (FITTING) IAW SRM 51-72-10.

Part: FLOORBEAM — CORRODED (ZONE 100) · corrosion level 2 · airframe 33,706 hrs · 12,343 cycles

HEAVY CORROSION ON CROSSBEAM FRAME 60 LT, CARGO COMPARTMENT FLOOR STRUCTURE. SPLICE REPAIR AT CROSSBEAM PERFORMED IAW SRM 53-10-15/FIG 207.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 33,706 hrs · 12,343 cycles

HEAVY CORROSION ON THE FLANGE OF STRINGER 51 RT, BETWEEN FRAME 45-46, REMAINING THICKNESS AFTER BLENDING IS OUT OF LIMIT. REPAIR PERFORMED BY CUTTING OUT DAMAGED PART AND INSTALLING A REPAIR ANGLE (4 MM THICK) IAW EA 6-5318-81086 AND RAS 034265/005/2004 ISSUE A.

Part: POWER UNIT — FAILED (FLAP/SLATS) · airframe 33,640 hrs · 12,300 cycles

ON APPROACH, SLATS FAULT, BOTH SLATS ON O/H, NO SLATS ON SFPI, PER QRH, CYCLED FLAP/SLAT HANDLE TO 0/0, BACK 15/0 WITH SAME. APPLIED QRH PROCEED, LANDED "0'/40'." CHECKED FAULTS SFCC1 IS 10000 SFCC2 IS 10000, (LT ASYM PPU FAIL FAULT) ISOL 27-80-08 FIG 102 RESET SFCC OPD SEVERAL TIMES NO FAULTS TSM 27-80-08, BOTH SFCC SAME FAULT CODE. SUSPECT ASSY PPU 31CV. REPLACE IS PER M/M 27-86-11-4 OUT ON WING TIP NOT ABLE P/N 9028A0002-01PER MOCC REQUEST CHECKED MOUNT AND C/P OF BOTH PPU'S. ALL PANEL FOR OUTBOARD PPU, REINSTALLED LOOSELY WITH 2 FASTENERS, PARTS ON FXF905. OPD SLATS SEVERAL MORE TIMES NO FAULTS. REMOVED AND REPLACED LEFT ASYM POS PICK-OFF UNIT/A310-3 M/M 27-86-11-4. OPS CK OK, NO FAULTS.

Part: STRUCTURE — CONTAMINATED (AFT) · airframe 31,487 hrs · 11,082 cycles

PILOT REPORT ACFT WILL TAKE AN ATTITUDE OF 3 DEGREES NOSE UP AT ALL PHASES OF FLIGHT ANY TIME. THE AUTO PILOT IS DISCONECTED. OPEN T.H.S ACCESS PANEL AND NOTICED ACCUMULATION OF WATER ABOUT 14 INCHES HIGH RIGHT BEHIND PRESSURE BULKHEAD. UNPLUGED DRAIN IN ORDER TO CLEAR WATER OF THE COMPARTMENT. APPROXIMATELY 75 GALLONS OF WATER WERE DRAINED. TAKING INTO ACCOUNT A GALLON OF WATER WEIGHTS 8.3 LBS IT WOULD BE APPROX 622LBS OF WEIGHT PLUS ARM LEVERAGE THAT IS THE MOST PROBABLE CAUSE FOR THE NOSE UP ATTITUDE OF THE AIRPLANE.