N808FD

Part: WARNING SYSTEM — MALFUNCTIONED (COCKPIT) · airframe 51,644 hrs · 17,362 cycles

AFTER EXTENDING THE LANDING GEAR, THE NOSE GEAR INDICATED UNLOCKED ON SYSTEM 1 AND 2. AFTER ABOUT 3 MINUTES, SHOWED LOCKED ON SYSTEM 1 AND 2.

Part: ARM — FAILED (NLG) · airframe 51,644 hrs · 17,362 cycles

AFTER EXTENDING THE LANDING GEAR, THE NOSE GEAR INDICATED UNLOCKED ON SYSTEM 1 AND 2. AFTER ABOUT 3 MINUTES,, SHOWED LOCKED ON SYSTEM 1 AND 2. REMOVED AND REPLACED NOSE GEAR TELESCOPIC DRAG STRUT ROCKER ARM ASSY. (40GB) ADJUSTED (49GB) IAW AMM 32-31-24-04. PERFORMED GEAR SWING IAW AMM 32-31-00-05 OPS CHECKED GOOD.

Part: SLIDE — INOPERATIVE (L1 DOOR) · airframe 50,478 hrs · 16,781 cycles

L1 DOOR SLIDE IS INOPERATIVE.

Part: SPAR — CRACKED (RT WING) · airframe 50,313 hrs · 16,690 cycles

RIGHT REAR SPAR INTERNAL ANGLE NR 63 HOLE NDT INSPECTION FOUND CRACK SIGNAL. RIGHT REAR SPAR INTERNAL ANGLE 63 HOLE NDT INSPECTION FOUND CRACK SIGNAL. REAM THE AFFECTED HOLE THROUGH ALL LAYERS STEP BY STEP WITH INCREASING DIA OF 0.4 MM IAW SRM 51-40-44, PERFORM ROTOTEST INSPECTION OF THE HOLE IAW NTM51-10-01, & NTM51-10-18 AFTER EACH STEP AND NO CRACK FOUND. RECORD THE DIAMETER OF THE HOLE WAS 14.211MM. WET INSTALLED FASTENER IAW SRM51-40-21, & EO 6-5710-7-3322 B2, PT1. MAJOR REPAIR IAW GMM 6-2-100.

Part: SPAR — CRACKED (RT WING) · airframe 50,313 hrs · 16,690 cycles

RIGHT WING REAR SPAR INTERNAL ANGLE NR 12 HOLE, NDT INSPECTION FOUND A CRACK SIGNAL. COMPLED WITH EA 6-5710-T0334453, P1. MAJOR REPAIR IAW IAW GMM 6-2-100.

Part: SPAR — CRACKED (RT WING) · airframe 50,313 hrs · 16,690 cycles

RIGHT WING REAR SPAR INTERNAL ANGLE NR 60 HOLE, NDT INSPECTION FOUND A CRACK SIGNAL. COMPLIED WITH EA 6-5710-T0334453, P1. MAJOR REPAIR IAW GMM 6-2-100.

Part: ANGLE — CRACKED (LT WING) · airframe 50,313 hrs · 16,690 cycles

LEFT REAR SPAR INTERNAL ANGLE NR 61 HOLE, NDT INSPECTION FOUND A CRACK SIGNAL. COMPLIED WITH EA 6-5710-T0334453 P1. MAJOR REPAIR IAW GMM 6-2-100.

Part: SKIN — CRACKED (RT WING) · airframe 50,313 hrs · 16,690 cycles

RIGHT WING RIB 11, CRACKED ON LOWER SKIN ACROSS A FASTENER HOLE APPROX 1.0 INCH IN LENGTH NEAR ACCESS PANEL 681AB. COMPLIED WITH EA 6-5730-T0334254 P1. MAJOR REPAIR IAW IAW GMM 6-2-100.

Part: SPAR — CRACKED (RT WING) · airframe 50,313 hrs · 16,690 cycles

RIGHT WING REAR SPAR INTERNAL ANGLE NR 35 HOLE, NDT INSPECTION FOUND A CRACK SIGNAL. REAMED THE HOLE IAW SRM 51-40-44, PERFORM ROTOTEST INSPECTION IAW NTM 51-10-01, & NTM 51-10-18 AND NO CRACK FOUND. WET INSTALLED A FASTENER IAW SRM 51-40-21, & EO 6-5710-7-3322, B2, PT1. MAJOR REPAIR IAW GMM 6-2-100.

Part: SPAR — CRACKED (RT WING) · airframe 50,313 hrs · 16,690 cycles

RIGHT WING REAR SPAR INTERNAL ANGLE NR 38 HOLE, NDT INSPECTION FOUND A CRACK SIGNAL. REAMED THE HOLE IAW SRM 51-40-44, PERFORM ROTOTEST INSPECTION IAW NTM 51-10-01, & NTM 51-10-18 AND NO CRACK FOUND. WET INSTALLED A FASTENER IAW SRM 51-40-21, & 6-5710-7-3322, B2, PT1. MAJOR REPAIR IAW GMM 6-2-100.

Part: SKIN — CRACKED (LEFT WING) · airframe 50,313 hrs · 16,690 cycles

LEFT WING RIB 11, CRACKED ON THE LOWER SKIN ACCROSS A FASTENER HOLE APPROX 1.5 INCH IN LENGTH, NEAR ACCESS PANEL 581AB. COMPLIED WITH EA 6-5730-T0334254, P1. MAJOR REPAIR IAW GMM 6-2-100.

Part: SPAR — CRACKED (LT WING) · airframe 50,313 hrs · 16,690 cycles

LEFT REAR SPAR INTERNAL ANGLE NR 35 HOLE NDT INSPECTION FOUND A CRACK SIGNAL. REAMED THE AFFECTED HOLE THROUGH ALL LAYERS IAW SRM 51-40-44, PERFORM ROTOTEST INSPECTION OF THE HOLE IAW NTM51-10-01 & NTM51-10-18 AFTER EACH STEP AND NO CRACK FOUND. WET INSTALLED A FASTENER IAW SRM 51-40-21 & EO 6-5710-7-3322 B2 PT1. MAJOR REPAIR IAW GMM 6-2-100.

Part: SPAR — CRACKED (RT WING) · airframe 50,313 hrs · 16,690 cycles

RIGHT REAR SPAR INTERNAL ANGLE NR 30 HOLE, NDT INSPECTION FOUND A CRACK SIGNAL. REAM THE HOLE IAW SRM 51-40-44, PERFORM ROTOTEST INSPECTION OF THE HOLE IAW NTM51-10-01 & NTM51-10-18 AND NO CRACK FOUND. WET INSTALLED A FASTENER IAW SRM 51-40-21 & EO 6-5710-7-3322, B2, PT1. MAJOR REPAIR IAW GMM 6-2-100.

Part: SPAR — CRACKED (RT WING) · airframe 50,313 hrs · 16,690 cycles

RIGHT REAR SPAR INTERNAL ANGLE NR 7 HOLE, NDT INSPECTION FOUND A CRACK SIGNAL. COMPLED WITH EA 6-5710-T0334453, P1. MAJOR REPAIR IAW GMM 6-2-100.

Part: ANGLE — CRACKED (LT WING) · airframe 50,313 hrs · 16,690 cycles

LEFT REAR SPAR INTERNAL ANGLE NR 53 HOLE, NDT INSPECTION FOUND A CRACK SIGNAL. REAM THE HOLE IAW SRM 51-40-44, PERFORM ROTOTEST INSPECTION OF THE HOLE IAW NTM51-10-01 & NTM51-10-18 AND NO CRACK FOUND. WET INSTALLED A FASTENER IAW SRM 51-40-21 & EO 6-5710-7-3322, B2, P1I. MAJOR REPAIR IAW GMM 6-2-100.

Part: SPAR — CRACKED (RT WING) · airframe 50,313 hrs · 16,690 cycles

RIGHT WING REAR SPAR INTERNAL ANGLE NR 16 HOLE, NDT INSPECTION FOUND CRACK SIGNAL. COMPLED WITH EA 6-5710-T0334453, P1. MAJOR REPAIR IAW GMM 6-2-100.

Part: SPAR — CRACKED (LT WING) · airframe 50,313 hrs · 16,690 cycles

LEFT WING REAR SPAR INTERNAL ANGLE NR 13 HOLE, NDT INSPECTION FOUND A CRACK SIGNAL. COMPLIED WITH EA 6-5710-T0334453 P1. MAJOR REPAIR IAW GMM 6-2-100.

Part: SPAR — CRACKED (RT WING) · airframe 50,313 hrs · 16,690 cycles

RIGHT WING REAR SPAR INTERNAL ANGLE NR 33 HOLE, NDT INSPECTION FOUND A CRACK SIGNAL. REAMED THE HOLE IAW SRM 51-40-44, PERFORM ROTOTEST INSPECTION OF THE HOLE IAW NTM51-10-01, & NTM51-10-18 AND NO CRACK WAS FOUND. WET INSTALLED A FASTENER IAW SRM 51-40-21, & EO 6-5710-7-3322, B2, PT1. MAJOR REPAIR IAW GMM 6-2-100.

Part: ANGLE — CRACKED (LT WING) · airframe 50,313 hrs · 16,690 cycles

LEFT WING REAR SPAR INERNAL ANGLE 16 HOLE FOUND CRACKED. REPAIRED IAW EA 6-5710-T0334453 P1. MAJOR REPAIR IAW GMM 6-2-100.

Part: SKIN — CORRODED (FRAME 12) · airframe 50,313 hrs · 16,690 cycles

FWD TOILET SERVICE PANEL LOWER CUTOUT SKIN DELAMINATED. INSPECTED FOUND SKIN INNER STIFFENER CORRODED AND OUT OF LIMITS IAW SRM 51-40-21, & SRM 53-12-18, FIG 2, SHEET 3, ITEM 205, REPLACEED THE STIFFENER. . MAJOR REPAIR IAW GMM 6-2-100.

Part: PUMP — INOPERATIVE (NR 2 ENGINE) · airframe 50,142 hrs · 16,599 cycles

IN CRUISE FL360 GOT GREEN HYD SYSTEM OVERHEAT. ECAM ADVISED TO TURN OFF GREEN ENGINE PUMPS 1 AND 2. ENG HYD 1 PUMP SHUT OFF NORMALLY. ENG HYD 2 GREEN PUMP TURNED OFF MOMENTARILY. ITS CB POPPED AND THE PUMP STARTED OPERATING AGAIN. CORDINATED WITH MOCC TO RESET CB. THE RESULT WAS THE SAME AND WE COULD NOT TURN OFF THE NR 2 ENGINE PUMP OVERHEAT INDICATION CONTINUED UNTIL SHORT FINAL. REMOVED & REPLACED NR 2 ENG GRN HYD SYS PUMP AS REQUIRED. UNABLE TO BLEED, LEAK AND OPS CK PUMP/SYS DUE TO STILL AWAITING NR 2 GRN SYS HP DELIVERY HYD SYS FILTER, REF WRI 2911/2876. REF AMM 29-11-32.

Part: SKIN PANEL — CORRODED (RT WING) · airframe 49,026 hrs · 15,847 cycles

CORROSION ON UPPER RT WING SKIN, APPROX 83.5" FROM WTB. CORROSION FORMED AROUND FASTENER HEAD & EXTENDS AFT, APPROX 2"X4". REMOVED VISIBLE CORROSION ON RT WING UPPER SKIN IAW SRM 51-74-10. CHECKED LIMITS BLEND AREA AND FOUND TO BE OUT OF LIMITS IAW SRM 57-20-12-101. HFEC REWORK AREA IAW NTM 51-60-00. NO CRACK OR CORROSION INDICATION NOTED. COMPLIED WITH EA 6-5730-T0323345.

Part: ENGINE — POWER LOSS (NR 2) · airframe 48,943 hrs · 15,804 cycles

DURING DESCENT BELOW PROFILE THRUST WAS APPROX 75 - 77% N1. AT PROFILE THROTTLES REDUCED TO IDLE & APPROX 60% N1, A THUMPING SOUND WAS HEARD & FELT. SUSPECT COMPRESSOR STALL. ALTITUDE 30000 FT SPEED 0.8. NO ABNORMAL ENG INDICATIONS. SUSPECT ENG NR 2. OLLOWED TSI 31-30 1377 INSPECTION IAW AMM 71-00-00-06. NO DAMAGE & NO METAL PARTICLES FOUND. PERFORMED FADEC GND TEST, BOTH ENGS IAW TSM 73-21-40, NO FAILURE RECORDED. REVIEWED THE DFDR DATA THAT AT FL 30 THE ACFT DID EXPERIENCE WIND DIRECTION & SPEED CHANGE. THEY BELIEVE THIS IS THE ROOT CAUSE OF BUFFETING THE FLIGHT CREW EXPERIENCED. THERE WAS NOT A COMPRESSOR STALL ON EITHER ENG. PERFORMED ACFT INSPECTION & CHECK IAW AMM 05-51-17-00 PHASE 1, NO DAMAGE, NO ABNORMAL FOUND.

Part: WINDSHIELD — CRACKED (COCKPIT) · airframe 481 hrs · 15,412 cycles

AT FL 370 CAPTAIN`S OUTER WINDSCREEN SHATTERED. PRESSURIZATION HELD OK, DIVERTED. R & R CAPTAIN`S WINDSHIELD PANEL IAW AMM 56-11-11-04. WINDSHIELD PANEL ANTI-ICING & DE- FOGGING OPERATIONAL TESTED SATISFACTORY.

Part: WINDOW — FAILED (COCKPIT) · airframe 479 hrs · 15,341 cycles

AFTER TAKEOFF GOT RT WINDOW HEAT FAULT. FOLLOWED QRH & RESET RT WINDOW HEAT. LATER CLIMBING THROUGH FL 280, THE LT WINDSHIELD COMPLETELY SHATTERED ON THE OUTSIDE PANE WITH NO WARNING. THERE WAS SOME ELEC ARCING AFTERWARD. LATER ON DESCENT GOT RT WINDOW HEAT FAULT AGAIN. TURNED RT WINDOW HEAT OFF FOR REMAINDER OF FLIGHT. R & R LT NEW WINDSHIELD PANEL IAW AMM 56-11-11-04. PERFORMED TEST IAW AMM 30-42-00-05. FOUND NORMAL, NO FAULTS. ACFT OK FOR SERVICE.

Part: SKIN — DAMAGED (LT WING) · airframe 478 hrs · 15,309 cycles

FOUND ONE LIGHTNING STRIKE AT THE TRAILING EDGE OF THE LT WING TIP UPPER INBD SURFACE. REPLACED THE SKIN IAW SRM 57-30-11.

Part: FITTING — CRACKED (CARGO DOOR) · airframe 478 hrs · 15,309 cycles

AFT CARGO COMPARTMENT DOOR ACTUATOR FITTING CRACKED. REMOVED THE AFT CARGO DOOR ASSEMBLY IAW AMM 52-32-11-04. REPLACED THE FRAME HEAD IAW SRM 51-40-21. INSTALLED THE AFT CARGO DOOR ASSEMBLY IAW AMM 52-32-11-04. TESTED OK.

Part: CROSSBEAM — CORRODED (FRAME 63) · corrosion level 2 · airframe 478 hrs · 15,309 cycles

AFT CARGO FLOOR FRAME 63 CROSSBEAM CORRODED BETWEEN Y140 & Y805. REPAIRED THE CROSSBEAM PER SRM 53-10-15 FIG.209.SHT.1

Part: CROSSBEAM — CORRODED (FRAME 61) · corrosion level 2 · airframe 478 hrs · 15,309 cycles

AFT CARGO FLOOR FRAME 61 CROSSBEAM CORRODED BETWEEN -Y805 & Y805. REPAIR THE CROSSBEAM PER SRM 53-10-15 FIG.209 SHT.1

Part: BLEED VALVE — MALFUNCTIONED (NR 2 ENGINE) · airframe 47,824 hrs · 15,265 cycles

FLIGHT DEPARTED WITH MEL 36-11-06-1A, NR 1 BLEED AIR VLV INOPERATIVE. DURING CLIMB OUT, WE DEVELOPED A NR 2 HP BLEED FAULT. FOLLOWED ECAM & QRH PROCEDURES. PROCEDURES LED US TO DUAL BLEED FAILURE CHECKLIST & WE COMPLIED. R & R NR 2 ENG HP BLEED VLV IAW MM 36-11-12-04-02. RAN ENG IAW JRH. OPERATIONS & LEAK CHECKED GOOD IAW MM 36-11-12-04-02.

Part: RIB — CRACKED (LT WING) · airframe 45,648 hrs · 14,194 cycles

LT WING T/E AT 284.85, SUPPORT RIB CRACKED, JUST BETWEEN SPOILER NR 5 AND SPOILER NR 6.

Part: ANGLE — CRACKED (FUSELAGE) · airframe 44,644 hrs · 13,768 cycles

LEFT FRAME40 PICK UP ANGLE FOUND CRACK EXTENDED FURTHER THAN STOP HOLE (EXTENDED CRACK LENGTH:0.2INCHES) COMPLY WITH EA 6-5310-161218, PART 1.

Part: OIL SYSTEM — OVERTEMP (NR 2 ENGINE) · airframe 44,018 hrs · 13,524 cycles

NR 2 ENG, HIGH OIL TEMP - ABOVE 180 DEG - SHUT ENG DOWN. ALL OTHER ENG PARAMETERS OK. INSPECTED NR2 ENG INLET & EXHAUST AREA; NIL ABNORMALTIES NOTED. VISUAL CK OIL QTY; NORMAL. R & R NR 2 ENGINE IAW WC 44T0105-2 AND 44T0708-2. RUN ENG IAW JRH LEAK CHECKED OK AND ALL PARAMETERS NORMAL.

Part: CABIN PRESSURE — MALFUNCTIONED · airframe 43,614 hrs · 13,338 cycles

RED CABIN ALTITUDE WARNING, PERFORMED DESCENT TO 10,000 FT ON CABIN PRESSURE SYS PAGE, BOTH OUTFLOW VALVES SHOW AMBER & FULL OPEN - NO ECAM MESSAGE, CABIN ALTITUDE 10,000 FT. UNABLE TO CONTROL CABIN ALTITUDE . PACK VALVES SHOW AMBER AND CLOSED INTERMITTENTLY ON AIR BLEED SYS PAGE - NO ECAM MESSAGE. VISUALLY INSPECTED IGNITION CONTROL SWITCH CONDITIONS FOUND SATISFACTORY. CLEANED THE SWITCH ASSY, R & R RELAY 215HB & 61GB ASSY IAW SWMP. CARRIED OUT ECAM, INPUT BITE TEST FOUND ALL NORMAL. OPS CHECKED OUTFLOW VALVE IN MANUAL MODE IAW AMM 21-31-00-5 FOUND SATISFACTORY. PERFORMED EN NR 1 & NR 2 ENGINE GROUND RUNS IAW JRH, CHECKED A/C PACKS AND OUTFLOW VALVES ALL WORKS NORMAL. ACFT OK FOR SERVICE.

Part: COMPUTER — MALFUNCTIONED · airframe 41,864 hrs · 12,398 cycles

ON CLIMB OUT, FLAPS AND SLATS UP, CAPT MAX SPEED INDICATOR (ZIPPER) REMAINED AT 245 KTS. F/O SPD LIMIT REMAINED "ON". R & R NR 2 SFCC DUE TO FAULT AND R & R NR 1 SFCC AS A PRECAUTION IAW AMM 27-51-18-4 AND TESTED IAW AMM 27-51-00-0, BITE TESTS PASS NO FAULTS NOTED ON EITHER SFCC NR 1 OR NR 2.

Part: WIRE — FAULTED (TE FLAPS) · airframe 41,247 hrs · 12,043 cycles

AFTER T/O FLAPS STUCK AT ABOUT 5 DEGREES, COMPLIED WITH QRH. NO LUCK, RETURNED TO IND FLAPS CAME DOWN OK FOUND SAME FAULT CODES AS BEFORE SFCC 1 AND 2 LT VANE OUT. INSPECTED JAM DETECTOR UNITS NO INDICATION OF CRUSHED HONEYCOMB, BROKEN SHEAR PIN, OR OTHER DAMAGE. RESET FAULTS ON SFCC OPERATED FLAPS NORMALLY, FAULTS DID NOT RETURN. SUSPECT INTERMITTENT WIRING FAULT ON ONE OF THE TWO LT VANE JAM OUT SWITCHES. CONFIRMED NO OVERWEIGHT INSPECTION REQUIRED (AMM-05-51).

Part: DAMPER — MALFUNCTIONED (LANDING GEAR) · airframe 41,024 hrs · 11,900 cycles

LANDING GEAR WOULD NOT RETRACT ON TAKEOFF ALTHOUGH AUTO THROTTLES WAS ENGAGED IT WAS INOP IN THE INITIAL CLIMB AUTO THROTTLE WORKED AGAIN ONCE SLATS WERE EXTENDED. PERFORMED BITE CHECK ON PROX BOX AT HGR RAMP AND CAME UP WITH (LB) FAULT AT THIS TIME. NO OTHER FAULTS NOTED. CPN 3212338 QTY 1 DAMPER MSN 1116800. REPLACED RT PITCH TRIM CYLINDER REF AMM 32-11-15-4. REQUIRES SERVICING AND HARDWARE TO BE SEALED. REMOVED PIVOT PIN PER MM 32-11-14 CLEANED BEARING RACES AND PIN. FOUND OUTBOARD WASHER ITEM 270 IPC 32-16-13-05A. DAMAGED AND NEEDS REPLACED. INSTALLED NEW PROX SENSORS PRECAUTIONARY, DUE TO BEING REMOVED. REF AMM 32-11-14-4.

Part: SEAT TRACK — DAMAGED (ZONE 200) · airframe 40,801 hrs · 11,746 cycles

MAIN DECK CARGO COMPARTMENT FLOOR STRUCTURE HAS SCRATCH AT FR 40 LT, BELOW FLOOR PANEL 231QH, AFT SIDE REMOVED DAMAGED SEAT TRACK AND FABRICATED AND INSTALLED REPLACEMENT TRACK AT TRACK NR 4LT BETWEEN FR 40 AND FR 45 IAW AIRBUS DRAWING A53811923 AND A310-300 SRM 51-40-21. ADJACENT DUMMY TRACK P/N Y53829790200 AND CROSS BEAM P/N A5381316820000 WERE ALSO REPLACED DUE TO DAMAGED.

Part: SEAT TRACK — CORRODED (ZONE 200) · airframe 40,801 hrs · 11,746 cycles

MDCC SEAT TRACK 4R CORRODED 2 AREAS FRAME 42 AND 44 4 SQ INCH. REMOVED LEVEL 1 CORROSION. REMOVED AND REPLACED SEAT TRACK FROM FR 40 TO 44.5 RT AT Y-1456 IAW SRM 53-10-16 FIGURE 203 SHEET 5.

Part: SEAT TRACK — CORRODED (ZONE 200) · corrosion level 2 · airframe 40,801 hrs · 11,746 cycles

MDCC SEAT TRACK 3R CORRODED 2 AREAS AT FRAME 46 4 INCH SQ IN REMOVED LEVEL 1 CORROSION ON SEAT TRACK SECTION AND INSTALLED NEW SEAT TRACK 3R FROM FRAME 44 TO 49 IAW A300-600 FREIGHTER SRM 53-10-16 FIG 102 PG 105 AND SRM 51-40- 21.

Part: SKIN — DAMAGED (ZONE 100) · airframe 40,801 hrs · 11,746 cycles

RIGHT SIDE FUSELAGE FR 37 STRINGER 30 1 LIGHTNING STRIKE REMOVED DAMAGED AREA AT FR37 RT SIDE STR 30 AND INSTALLED REPAIR DOUBLER IAW SRM 53-10-12 FIG 224 SHEET 3.

Part: SEAT TRACK — CORRODED (ZONE 200) · airframe 40,801 hrs · 11,746 cycles

MDCC SEAT TRACK NR 1 CORRODED AT FRAME 71 2 SQ IN REMOVED LEVEL 1 CORROSION. REMOVED AND REPLACED SEAT TRACK SECTION AT FR71 TO 74 AND INSTALLED NEW SECTION IAW SRM 53-10-16 FIG 208 SHEET 1, PG 247/248.

Part: FLOORBEAM — CRACKED (ZONE 200) · airframe 40,801 hrs · 11,746 cycles

MDCC FLOOR FRAME 30 HAS 1 INCH CRACK BETWEEN SEAT TRACK 2L AND 3L REMOVED CRACK AND INSTALLED FLOORBEAM REPAIR BETWEEN SEAT TRACK 2L AND 3L AT FR 30 IAW SRM 53-10-15 FIGURE 211 SHEET 1 AND 2.

Part: SEAT TRACK — DAMAGED (ZONE 200) · airframe 40,801 hrs · 11,746 cycles

MAIN DECK CARGO SEAT TRACK NR 4LT BETWEEN FR 59.2 AND FR 59.3 HAS 2 AREAS OF DAMAGED SCALLOPS REMOVED DAMAGED SECTION OF SEAT TRACK AND INSTALLED REPLACEMENT TRACK AT NR 4 LT BETWEEN FR 58 AND FR 60.5 IAW A310-300 SRM 51-40-210AND 53-17-16

Part: WIRE — DAMAGED · airframe 40,206 hrs · 11,429 cycles

AFTER START GOT OVERBOARD VALVE FAULT COMPLIED WITH ECAM QRH AND CHECKED MEL. DURING CLIMB-OUT, AIRCRAFT WOULD NOT PRESSURIZE. REMOVED AVIONICS EXTRACT VALVE TO FOM AV LINE C/B'S 60HR, 61HR PULLED AND COLLARED. FOUND WIRE BUNDLE CUT, FOR AV EXTRACT VALVE. PERFORMED WIRE SPLICE REPAIRS IN ZONE 133 STA 1715 TO WIRES 2123-5000-24, 5001-22, 5002-24, 5003-24, 5004-24, 5005-22, 5006-20, AND 5023-20 PER AIRBUS ELECTRICAL STD PRACTICES MANUAL, REINSTALLED VALVE, 2 GOOD LEGS. EXTRACT VLV PLACED ON MEL-GSO/23 , VALVE REMOVED AND REPLACED RSW/23. AFTER RECHECKING PREV SPLICE REPAIRS.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,726 hrs · 11,138 cycles

CORROSION ON STRINGER 56 LT, BETWEEN FRAME 65-66, OUT OF LIMIT AS PER SRM 53-10-00. STRINGER SPLICE REPAIR PERFORMED IAW SRM 53-10-14/FIG 201.

Part: SKIN PANEL — DAMAGED (ZONE 100) · airframe 39,724 hrs · 11,137 cycles

FOUND EXISTING SKIN REWORK IN POOR CONDITION AT FRAME 37, STRG 32, LHS. REPAIR AREA POLISHED, NDT INSPECTED WITH NIL FINDINGS AND FLAP PEENED IAW EA 6-5314-95918 AND RAS/DABRE/7005252/2006 ISSUE A (NOMINAL THICKNESS 1, 6 MM, REMAINING THICKNESS 1,01 MM).

Part: SUPPORT — DAMAGED (ZONE 100) · airframe 39,724 hrs · 11,137 cycles

CRACKED SUPPORT STRUT BETWEEN FRAME 77-78, STRG 45. REPAIR PERFORMED BY REPLACEMENT OF PART IAW SRM 51-72-10.

Part: SKIN PANEL — CORRODED (ZONE 500) · corrosion level 2 · airframe 39,726 hrs · 11,138 cycles

FOUND CORROSION ON LT WING TOP SKIN T/E AREA AT WORX439.75. REPAIR PERFORMED BY BLEND OUT THE CORROSION AND INSTALLING OVERSIZED FASTENERS IAW EA 6-5720-95931 AND RAS/BAE/1002360/2006 ISSUE A.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,726 hrs · 11,138 cycles

CORROSION ON STRINGER 54 LT BETWEEN C76-77, OUT OF LIMIT AS PER SRM 53-10-00. STRINGER SPLICE REPAIR PERFORMED IAW SRM 53-10-14.

Part: PLATE — CHAFED (ZONE 600) · airframe 39,726 hrs · 11,138 cycles

CHAFING DAMAGE (10 BY 1.5 MM) ON PYLON REINFORCING PLATE, RT WING AT FWD OUTBOARD EDGE, RIB 9. REPAIR PERFORMED BY BLEND OUT AND NDT INSPECTION IAW EA 6-5720-95909 AND RAS/BAE/1002261/2006.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,726 hrs · 11,138 cycles

CORROSION ON STRINGER 53 LT, BETWEEN FRAME 65-66, OUT OF LIMIT AS PER SRM 53-10-00. STRINGER SPLICE REPAIR PERFORMED IAW SRM 53-10-14/FIG 201.

Part: SKIN — DELAMINATED (RT ELEVATOR) · airframe 39,726 hrs · 11,138 cycles

DELAMINATION ON RT ELEVATOR LOWER SURFACE T/E NEAR TO RIB 1. REPAIR PERFORMED BY TRIM OUT THE AFFECTED SKIN, REPLACE THE CORE WHERE IT'S NECESSARY AND INSTALL A METALLIC STRAP IAW EA 6-5521-99198 AND RAS/CASA/4676/2006 ISSUE A.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,726 hrs · 11,138 cycles

FOUND CORROSION ON STRINGER 44 RT BETWEEN FRAME 47-48, OUT OF LIMIT. REPAIR PERFORMED BY BLEND OUT THE CORRODED AREAS IAW EA 6-5315-99192 AND RAS/043644/008/2006 ISSUE A.

Part: SKIN — DENTED (ZONE 100) · airframe 39,724 hrs · 11,137 cycles

DENT ON LOWER SKIN PANEL BETWEEN FRAME 1-2 WAS REPAIRED IN YEAR 1995 BY CUTTING OUT AREA AND INSTALLING AN INTERNAL DOUBLER. IN FEBRUARY 2006, REPAIR FOUND INSTALLED BETWEEN FRAME 0-1 AS PER REPAIR DRAWING AND THE DOUBLER MATERIAL WAS NOT IAW. DOCUMENTATION, MEASURED BY NDT. REPAIR RENEWED BY REINSTALLATION OF NEW DOUBLER WITH OVERSIZED FASTENERS AS PER DRW 12F53025A, APPROVED BY EA 6-5311-95926 AND RAS/AS/031/2006 ISSUE A.

Part: PANEL — FAILED (ZONE 200) · airframe 39,724 hrs · 11,137 cycles

FOUND WRONG INSTALLED FASTENERS AT CENTER WING BOX, FRAME 40-47. REPAIR PERFORMED BY INSTALLING NEW OVERSIZED BULL NOSE FASTENERS IAW EA 6-5710- 95919 AND RAS/042817/015/2006 ISSUE A.

Part: PANEL — MISPINNED (ZONE 200) · airframe 39,724 hrs · 11,137 cycles

FOUND WRONG INSTALLED FASTENERS AT CENTER WING BOX, FRAME 40-47. REPAIR PERFORMED BY INSTALLING NEW OVERSIZED BULL NOSE FASTENERS IAW EA 6-5710- 95919 AND RAS/042817/015/2006 ISSUE A.

Part: PLATE — DAMAGED (ZONE 100) · airframe 39,726 hrs · 11,138 cycles

FOUND MISDRILLED HOLES AT WEB PLATE, FRAME 86-87, STRG 33 LHS. REPAIR PERFORMED BY REPLACEMENT OF PART IAW SRM 51-72-10.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,726 hrs · 11,138 cycles

FOUND CORRODED AREAS ON FUSELAGE STRINGER OUTER FLANGE BETWEEN FRAME 76-77, STRG 56 RT AND 56 LT. REPAIR PERFORMED BY REWORK CORROSION FOLLOWING ROTO- AND HFEC INSPECTION OF AREAS AND ADJACENT HOLES WITH NIL FINDINGS IAW EA 6-5318-95920 AND RAS/DATLS/0003029/2006 ISSUE A.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,726 hrs · 11,138 cycles

FOUND CORROSION ON STRINGER 43 RT BETWEEN FRAME 47-48, OUT OF LIMIT. REPAIR PERFORMED BY BLEND OUT THE CORRODED AREAS IAW EA 6-5315-99192 AND RAS/043644/008/2006 ISSUE A.

Part: SHEAR PLATE — DAMAGED (ZONE 200) · airframe 39,724 hrs · 11,137 cycles

CRACKED SHEAR PLATES IN ZONE 170, FRAME 79, STRG 26 LHS AND RHS. REPAIR PERFORMED BY REPLACEMENT OF PARTS IAW SRM 51-72-10.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,726 hrs · 11,138 cycles

CORROSION ON STRINGER 54 LT, BETWEEN FRAME 65-66, OUT OF LIMIT AS PER SRM 53-10-00. STRINGER SPLICE REPAIR PERFORMED IAW SRM 53-10-14/FIG 201.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,726 hrs · 11,138 cycles

FOUND CORROSION ON STRINGER 50 RT BETWEEN FRAME 46-47. REPAIR PERFORMED BY REPLACEMENT OF STRINGER IAW SRM 51-72-10.

Part: PANEL — DELAMINATED (ZONE 600) · airframe 39,724 hrs · 11,137 cycles

DELAMINATION FOUND ON OUTER SHROUD BOX ON RT WING, LOWER SKIN NEAR RIB 31 AND CORROSION OF ALUMINIUM EXTRUSION ON RT WING OUTER TRAILING EDGE PANEL. REPAIR PERFORMED BY REMOVING AND REPLACING ALL DAMAGED LAYERS WITH WET LAY UP. REPLACING THE ALUMINUM T/E SECTION AND AFFECTED RIVETS IAW EA 6-5751-95922 AND RAS/BAE/1002265/2006.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,726 hrs · 11,138 cycles

CORROSION ON STRINGER 49, BETWEEN FRAME 65-66, OUT OF LIMIT AS PER SRM 53-10-00. STRINGER SPLICE REPAIR PERFORMED IAW SRM 53-10-14/FIG 201.

Part: RIB — DAMAGED (ZONE 300) · airframe 39,724 hrs · 11,137 cycles

RT ELEVATOR TIP SKIN PLATE AND RIBS DEFORMED. FOUND CRACKS (20 AND 30 MM) IN LOWER SKIN AT T/E PROFILE. REAR UPPER ANCHOR NUT OF ELEVATOR RIB ER41 CRACKED. REPAIR PERFORMED BY TRIM OUT TO REMOVE THE CRACKED AND DENTED AREA. INSTALLATION OF REPAIR ANGLE AND FILLER, REINSTALLATION OF ANCHOR NUT AND REPLACEMENT OF TIP IAW EA 6-5524-95911 AND RAS/CASA/4555/2006 ISSUE A.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,726 hrs · 11,138 cycles

CORROSION AT STRG 51, BETWEEN FRAME 20-21 LHS, OUT OF LIMIT. SPLICE REPAIR PERFORMED IAW SRM 53-10-14/FIG 201.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,726 hrs · 11,138 cycles

CORROSION ON STRINGER 54 RT BETWEEN C76-77, OUT OF LIMIT AS PER SRM 53-10-00. STRINGER SPLICE REPAIR PERFORMED IAW SRM 53-10-14/FIG 201.

Part: WEB — DAMAGED (ZONE 100) · airframe 39,724 hrs · 11,137 cycles

DAMAGED WEB AT FRAME 59 BETWEEN STRG 29-36 RHS, OUTBOARD. REPAIR PERFORMED BY REPLACEMENT OF PART IAW SRM 51-72-10.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,726 hrs · 11,138 cycles

CORROSION ON STRINGER 52, BETWEEN FRAME 65-66, OUT OF LIMIT AS PER SRM 53-10-00, STRINGER SPLICE REPAIR PERFORMED IAW SRM 53-10-14/FIG 201.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,726 hrs · 11,138 cycles

CORROSION ON STRINGER 56 LT AND RT BETWEEN C55/58-61, OUT OF LIMIT AS PER SRM 53-10-00. STRINGER SPLICE REPAIR PERFORMED IAW SRM 53-10-14/FIG 201A.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,726 hrs · 11,138 cycles

FOUND CORROSION ON STRINGER 50, BETWEEN FRAME 55/58-59 LHS, OUT OF LIMIT. STRINGER SPLICE REPAIR PERFORMED IAW SRM 53-10-14/FIG 201.

Part: VANE — CHAFED (ZONE 600) · airframe 39,724 hrs · 11,137 cycles

DENT (15 BY 30 MM) WITH CHAFING MARK FOUND AT NOSE SKIN OF INBOARD FLAP VANE RT, BETWEEN RIB 21 AND RIB 22. REPAIR PERFORMED BY SMOOTH BLEND OUT OF CHAFING AND NDT INSPECTION FOR CRACK FREE IAW EA 6-5752-95917 AND RAS/DABRE/7006243/2006 ISSUE A.

Part: BEAM — MISREPAIRED (ZONE 100) · airframe 39,724 hrs · 11,137 cycles

OLD REPAIR ON AFT CARGO COMPARTMENT DOOR SILL BEAM BETWEEN FRAME 62-63, PLATE MATERIAL IS NOT CONFORM TO SRM 53-17-18/FIG 201. REPAIR RENEWED BY INSTALLING A CORRECT PLATE IAW SRM 53-17-18/FIG 201.

Part: SKIN PANEL — CORRODED (CENTER WING) · corrosion level 2 · airframe 39,726 hrs · 11,138 cycles

HEAVY CORROSION FOUND ON CENTER WING BOX TOP SKIN AT TR5 AND TR6 RT/LT, FRAME 43-46.2. REPAIR PERFORMED IAW SRM 57-10-12/FIG 201 AND RAS/042817/015/2006 ISSUE A, EXCEPT FOR DAMAGES AT FRAME 44, BEAM 5 AND 6 LT AND RT, WHICH WAS REPAIRED BY DOUBLER IAW RAS/042972/012/2006 ISSUE A, APPROVED BY EA 6-5710-95921A.

Part: FLOORBEAM — MISREPAIRED (ZONE 100) · airframe 39,726 hrs · 11,138 cycles

OLD CROSSBEAM REPAIR AT FRAME 33 LT, NOT CONFORM TO SRM 53-10-15/FIG 207 (SPLICE MATERIAL NOT CORRECT). SPLICE REPAIR RENEWED IAW SRM 53-10-15/FIG 207.

Part: SKIN — MISREPAIRED (ZONE 800) · airframe 39,722 hrs · 11,136 cycles

FOUND OLD EXTERNAL DOUBLER REPAIR ON RT AFT PAX DOOR LOWER AFT CORNER WITHOUT ANY DOCUMENTATION. THE REPAIR WAS NOT CONFORM TO SRM 52-10-00/FIG 203 (RIVET ROW MISSING). REPAIR PERFORMED BY INSTALLING THE MISSING FASTENER ROW (MS20426-DD5) TO THE EXISTING REPAIR, APPROVED BY EA 6-5213-95906 AND RAS/DAHAM/4020451/2006 ISSUE A.

Part: FRAME — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,722 hrs · 11,136 cycles

FOUND CORROSION ON SHEAR PLATE FRAME 68-69, STRG 47-48 LHS. REPAIR WAS PERFORMED BY REPLACEMENT OF PART IAW SRM 51-72-10.

Part: SKIN — DAMAGED (ZONE 600) · airframe 39,722 hrs · 11,136 cycles

FOUND OLD DOUBLER REPAIR WITH NEW DAMAGED CORE ON RT INBOARD FLAP T/E, RIB 1, LOWER SURFACE. REPAIR PERFORMED IAW SRM 57-53-12 / FIG 208, APPROVED BY EA 6-5752-95905 AND RAS/DABRE/7006189/2006 ISSUE A.

Part: NONE — NONE · airframe 39,722 hrs · 11,136 cycles

FOUND OLD BONDED DOUBLER ON RT INBOARD FLAP, RIB 15-17, LOWER SKIN T/E, WITHOUT ANY RECORD. REPAIR RENEWED IAW SRM 57-53-12/FIG 208, APPROVED BY EA 6-5752-95905 AND RAS/DABRE/7006189/2006 ISSUE A.

Part: BRACKET — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,722 hrs · 11,136 cycles

FOUND CORROSION ON BRACKET RING BETWEEN FRAME 24-25 AND STRG 54 LT TO 54 RT. REPAIR PERFORMED BY REPLACEMENT OF PART IAW SRM 51-72-10.

Part: COUPLING — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,722 hrs · 11,136 cycles

FOUND CORROSION ON COUPLING AT FRAME 26/32, STRG 44 LHS. REPAIR PERFORMED BY REPLACEMENT OF PART IAW SRM 51-72-10.

Part: FLOOR SUPPORT — CORRODED (ZONE 200) · corrosion level 2 · airframe 39,721 hrs · 11,135 cycles

HEAVY CORRODED LONGERON BETWEEN FRAME 12A-14, Y-450, CABIN FLOOR STRUCTURE RT, OUT OF LIMIT AS PER SRM 53-10-00. REPAIR PERFORMED IAW SRM 53-12-15/FIG 207.

Part: SKIN PANEL — WORN (ZONE 600) · airframe 39,722 hrs · 11,136 cycles

ELONGATED HOLES CAUSED BY CHAFING OF HYDRAULIC LINES IN WING PYLON AFT SUPPORT BRACKET AND BOTTOM SKIN, RIB 8. REPAIR PERFORMED BY OVERSIZING HOLES AND INSTALLING ECCENTRIC BUSHES IAW R572- 49184 ISSUE C, APPROVED B EA 6-5720-95912 AND RAS/BAE/1002263/2006 ISSUE A.

Part: SKIN — MISREPAIRED (ZONE 100) · airframe 39,722 hrs · 11,136 cycles

OLD EXTERNAL DOUBLER REPAIR FOUND BETWEEN FRAME 72-73, STRG 26-27 LHS. DOUBLER THICKNESS NOT CONFORM TO SRM. DOUBLER REPAIR RENEWED IAW SRM 53-10-12/FIG 225, APPROVED BY EA 6-5318-99164.

Part: NONE — NONE · airframe 39,722 hrs · 11,136 cycles

FOUND OLD EXTERNAL RIVETED DOUBLER ON RT INBOARD FLAP, OUTBOARD EDGE RIB 21, WITHOUT ANY RECORD. REPAIR RENEWED BY CUT OUT TO A REGULAR SHAPE AND INSTALLING A NEW DOUBLER, APPROVED BY EA 6-5752-95905 AND RAS/DABRE/7006189/2006 ISSUE A.

Part: FRAME — MISREPAIRED (ZONE 100) · airframe 39,722 hrs · 11,136 cycles

FOUND OLD REPAIRS AT MANHOLE FITTING FRAME 38.1-38.2 (MORE THAN FOUR ADJACENT POCKETS AFFECTED), NOT ALLOWED IAW SRM 53-14-12/PG 228. REPAIR PERFORMED BY REPLACEMENT OF MANHOLE FITTING BETWEEN FRAME 38.1-38.2 IAW DRW R537-06164 ISSUE D, APPROVED BY EA 6-5310-99167A AND RAS/DABRE/7006403/2006 ISSUE B.

Part: FLOOR SUPPORT — CORRODED (ZONE 200) · corrosion level 2 · airframe 39,721 hrs · 11,135 cycles

HEAVY CORRODED LONGERON BETWEEN FRAME 12A-14, CABIN FLOOR STRUCTURE, OUT OF LIMIT AS PER SRM 53-10-00. REPAIR PERFORMED IAW SRM 53-12-15/FIG 207.

Part: SKIN PANEL — WORN (ZONE 500) · airframe 39,722 hrs · 11,136 cycles

ELONGATED HOLES CAUSED BY CHAFING OF HYDRAULIC LINES IN WING PYLON AFT SUPPORT BRACKET AND BOTTOM SKIN, RIB 8. REPAIR PERFORMED BY OVERSIZING HOLES AND INSTALLING ECCENTRIC BUSHES IAW R572- 49184 ISSUE C, APPROVED B EA 6-5720-95912 AND RAS/BAE/1002263/2006 ISSUE A.

Part: FRAME — DAMAGED (ZONE 200) · airframe 39,722 hrs · 11,136 cycles

FOUND TWO OLD MISDRILLED HOLES IN SHEAT WEB FRAME 75A-76, STRG 26 RT. REPAIR PERFORMED BY REPLACEMENT OF PART IAW SRM 51-72-10.

Part: FRAME — DAMAGED (ZONE 300) · airframe 39,722 hrs · 11,136 cycles

FOUND OLD REPAIR AT APU COMPARTMENT, FRAME 101 WITH AN ADDITIONAL DAMAGE (BENDED) ON SUPPORT ANGLE AND THE DOUBLER. REPAIR PERFORMED BY DRESS BACK THE BENDED FLANGE OF THE L-SECTION IAW EA 6-5339-95908 AND RAS/DAHAM/4020455/2006 ISSUE A.

Part: FRAME — MISREPAIRED (ZONE 100) · airframe 39,722 hrs · 11,136 cycles

FOUND OLD REPAIRS AT MANHOLE FITTING FRAME 23-24 (MORE THAN FOUR ADJACENT POCKETS AFFECTED), NOT ALLOWED IAW SRM 53-13-12/PG 220. REPAIR PERFORMED BY REPLACMENT OF MANHOLE FITTING BETWEEN FRAME 23-24 IAW DRW, R537-06163 ISSUE B, APPROVED BY EA 6-5310-95923A AND RAS/DABRE/7006402/2006 ISSUE B.

Part: SKIN PANEL — MISREPAIRED (ZONE 100) · airframe 39,721 hrs · 11,135 cycles

FOUND AN OLD EXTERNAL DOUBLER REPAIR ON FRAME 0-1, STRG 27 LHS, NOT CONFORM TO REPAIR INSTRUCTION AS PER SRM 53-11-12/FIG 201 (ONE RIVET ROW IS MISSING). REPAIR RENEWED WITH DEVIATIONS BY INSTALLING NEW FASTENERS IN OLD HOLES IAW EA 6-5311-95927 AND RAS 042577/018/2006 ISSUE A.

Part: SKIN — DENTED (ZONE 500) · airframe 39,722 hrs · 11,136 cycles

FOUND OLD REPAIR WITH NEW DAMAGED CORE AND DENTS ON LT INBOARD FLAP LOWER SURFACE AT T/E BETWEEN RIB 13-14. REPAIR RENEWED IAW SRM 57-53-12/FIG 208, APPROVED BY EA 6-5752-95904 AND RAS/DABRE/7006107/2006 ISSUE A.

Part: FLOOR SUPPORT — CORRODED (ZONE 200) · corrosion level 2 · airframe 39,721 hrs · 11,135 cycles

HEAVY CORRODED LONGERON BETWEEN FRAME 12A-14, CABIN FLOOR STRUCTURE, OUT OF LIMIT AS PER SRM 53-10-00. REPAIR PERFORMED IAW SRM 53-12-15/FIG 207.

Part: WINDOW FRAME — CORRODED (ZONE 200) · corrosion level 2 · airframe 39,722 hrs · 11,136 cycles

FOUND CORROSION AT WINDSHIELD FRAMEWORK BETWEEN FRAME 7-10, LT/RT. REPAIR WAS PERFORMED BY BLEND OUT THE CORROSION IAW EA 6-5311-95933 AND RAS 042711/019/2006 ISSUE A.

Part: FRAME — MISREPAIRED (ZONE 300) · airframe 39,722 hrs · 11,136 cycles

FOUND OLD EXTERNAL DOUBLER REPAIR ON FRAME 10 LH, Z-336, NOT FULLY CONFORM TO RAS/AS/359/95 ISSUE A AND OLD DELTA AIRLINES RECORD 297854-14 (WRONG RIVETS INSTALLED: HLT411-6 INSTEAD OF HL109-6). REPAIR PERFORMED BY REMOVING WRONG FASTENERS, NDT INSPECTION FOR CRACK FREE CONDITION AND INSTALLING ASNA2026V3, APPROVED BY EA 6-5312-95928 AND RAS/042710/022/2006 ISSUE A.

Part: SKIN — DENTED (TE FLAP) · airframe 39,722 hrs · 11,136 cycles

FOUND DENT ON RT INBOARD FLAP, BETWEEN RIB 15 AND TRACK 2, STRG 13-14, LOWER SKIN. DOUBLER REPAIR PERFORMED IAW EA 6-5752-95905 AND RAS/DABRE/7006189/2006 ISSUE A.

Part: FLOOR SUPPORT — CORRODED (ZONE 200) · corrosion level 2 · airframe 39,721 hrs · 11,135 cycles

HEAVY CORRODED LONGERON BETWEEN FRAME 12A-14, CABIN FLOOR STRUCTURE, OUT OF LIMIT AS PER SRM 53-10-00. REPAIR PERFORMED IAW SRM 53-12-15/FIG 207.

Part: WARNING LIGHT — FALSE ACTIVATION (CARGO SMOKE) · airframe 38,457 hrs · 10,429 cycles

IMMEDIATELY AFTER TAKEOFF RECEIVED ECAM ALERT. FWD CARGO COMPARTMENT SMOKE. COMPLIED WITH ECAM AND QRH. RETURNED TO KBDL. NO SMOKE DETECTED AND FIRE DEPT SCANNED COMPT WITH INFRA RED, OK. RELEASED FOR SERVICE PER MEL/CDL: 26-16-02-B AND 26-16-01, NO CARGO IN THIS COMPT.

Part: SMOKE DETECTOR — MALFUNCTIONED (CARGO BAY) · airframe 38,253 hrs · 10,303 cycles

AFT BULK COMPARTMENT SMOKE WARNING AFTER TAKEOFF. DISCHARGED AGENT 1 AND LANDED IMMEDIATELY. RELEASED FOR SERVICE PER MEL/CDL: 26-16-01. IDENTIFY FWD, AFT AND/OR BULK, BULK SMOKE DETECTION SYSTEM INOP. NO CARGO IS TO BE CARRIED WITH AFFECTED LOWER DECK COMPARTMENT. BOTH LOWER BULK AND AFT CARGO SMOKE DETECTORS CONNECTORS ARE DISCONNECTED. REMOVED AND REPLACED SMOKE DETECTORS IN LOWER AFT AND BULK CARGO (9WH-B, 44WH-B, 10WH-B, AND 11WH-B). OPS CHECK GOOD IAW A-310-300 MM 26-16-11-4.

Part: SMOKE DETECTOR — MALFUNCTIONED (ZONE 100) · airframe 38,251 hrs · 10,301 cycles

AFT-BULK COMPARTMENT SMOKE WARNING AFTER TAKEOFF. DISCHARGED AGENT NR 1 AND LANDED IMMEDIATELY. RELEASED FOR SERVICE PER MEL/CDL: 26-16-01. IDENTIFY FWD, AFT AND/OR BULK) BULK SMOKE DETECTION SYSTEM INOP. NO CARGO IS TO BE CARRIED WITH AFFECTED LOWER DECK COMPARTMENT." BOTH LOWER BULK AND AFT CARGO SMOKE DETECTORS CONNECTORS ARE DISCONNECTED. REMOVED AND REPLACED SMOKE DETECTORS IN LOWER AFT AND BULK CARGO (9WH-B, 44WH-B, 10WH-B, AND 11WH-B). OPS CHECK GOOD IAW A-310-300 MM 26-16-11-4. ALSO REF WRI NR 2612-0297 FOR ALL OTHER WORK PERFORMED.