N805FD

Part: STRINGER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 60,857 hrs · 14,997 cycles

AFT CARGO STRINGER 46R FRAME 63 - 64 STRINGER CORRODED. REPAIRED THE STRINGER PER A310 SRM 53-10-14 PB201 FIG201H

Part: ENGINE — FAILED (NR 1) · airframe 59,002 hrs · 13,900 cycles

UPASSING 3000 ON T/O, FELT ABNORMAL VIBRATION WITH UNUSUAL NOISE. NOTICED N1 VIB AT 1.4 AND N2 VIB AT 2.4 ON ENG 1. WHILE TROUBLESHOOTING RECEIVED ENG 1 EPR MODE FAULT AND ATS LEVER KICKED OFF. NOTICED ENG 1 EGT GAUGE INOP AT "0". ENG 1 N1 BEGAN UNCOMMANDED CLIMB TOWARD LIMIT. FINALLY NOITCED ENG 1 OIL QUANTITY AND PRESSURE AT "0" FOLLOWED BY ECAM. SHUTDOWN ENG 1 AND RTB ENG 1 WINDMILLING FOR APPROX 15 MINS WITH "0" OIL PRESSURE. REMOVED AND REPLACED NR 1 ENGINE AS PER AMM 71-00-00-04.

Part: FUEL CELL — LEAKING · airframe 58,487 hrs · 13,694 cycles

RIGHT OUTER TANK REAR SPAR, FUEL SEEPING AT NR 6 SPOILER BLOCK VALVE SUPPORT FITTING LWR RT FITTING FASTENERS. USED OPTIONAL INSPECTION METHOD WITH HIGH LEVEL FUEL SENSING. TORQUED NUT WITH APPLICABLE VALUE CLEAN UP THE FASTENERS AND SEALANT ON THE NUT IAW SRM 51-49-00. APPLIED NEW SEALANT FOR REPAIR IAW EO 6-5710-7-3304 PT3 AND EA 6-5710-149045G. THE REPAIR CLASSIFIED AS MINOR IAW GMM 6-2-100.

Part: FUEL CELL — LEAKING (LT WING) · airframe 58,487 hrs · 13,694 cycles

LEFT WING INNER TANK LOWER SURFACE 1 EA BOLT FUEL SEEPING NEAR REAR SPAR RIB 8 POSITION. USED OPTIONAL INSP METHOD WITH HIGH LEVEL FUEL SENSING. TORQUED NUT WITH APPLICABLE VALUE CLEAN UP THE FASTENERS AND RESEALANT ON THE NUT IAW SRM 51-49-00. APPLIED NEW SEALANT FOR REPAIR IAW EO 6-5710-7-3304 PT1 AND EA 6-5710-149045. THE REPAIR CLASSIFIED AS MINOR IAW GMM 6-2-100.

Part: FLOOR SUPPORT — CORRODED (MAIN DECK) · airframe 58,487 hrs · 13,694 cycles

FWD MAIN DECK, COURIER FLOOR AREA, FOUND FLOOR SUPPORT CORRODED LOCATION FROM FR 11 TO 13A AND Y-724. R & R THE FLOOR SUPPORT IAW SRM 51-72-10. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100.

Part: FLOOR PANEL — DAMAGED (MAIN DECK) · airframe 58,487 hrs · 13,694 cycles

MAIN DECK FLOOR PANEL 241NK DAMAGED. FABRICATED A NEW FLOOR PANEL IAW SRM 53-10-20. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: SKIN — DENTED (FUSELAGE) · airframe 58,487 hrs · 13,694 cycles

NOSE SECTION RT LOWER HALF SKIN PLATE EXTERNAL GOT A DENT JUST BELOW COCKPIT FLOOR LEVEL LOCATION BETWEEN FR 2 AND FR 3 POSITION.

Part: SKIN — SCRATCHED (LT WING TE FLAP) · airframe 57,751 hrs · 13,399 cycles

LEFT WING OTBD FLAP UPPER SURFACE NEAR FLAP TRACK NR 3, FOUND SURFACE WITH 8" SCRATCH MARK UNDER RUBSTRIP. REPLACED THE O/B FLAP PER AMM 27-50-12-04-0

Part: THRUST REVERSER — MALFUNCTIONED (NR 2 ENGINE) · airframe 57,217 hrs · 13,191 cycles

AT APPRX 70KTS, NR 2 THRUST REVERSER UNLOCK AMBER LIGHT ON. REJECTED T/O, AFTER STOWING THRUST REVERSER, LIGHT OUT. REVERSER APPEARED TO OPERATE NORMAL. RELEASED FOR SERVICE PER MEL. PERFORMED TROUBLESHOOTING AS PER AMM 78-30-00-02. CARRIED OUT RIGGING OF PDU IAW AMM 78-31-01-04-0. CLOSED & SECU RED FAN COWL AS PER AMM 71-13-00. PERFORMED NR 2 THRUST REVERSER FUNCTIONAL CHECK AS PER AMM 78-32-11. ALL SATISFACTORY. REACTIVED NR 2 THRUST REVERSER PER AMM 78-31-00-09-0, PERFORMED NR 2 THRUST REVERSER TRANSLATING SLEEVES OPS TEST NORMAL PER AMM 78-32-11-05.OPENED AND CLOSED NR 2 ENG FAN COWL AS PER AMM 71-13-00-03, PERFORMED NR 2 ENG HIGH POWER RUN-UP TEST PER JRH. ALL PARAMETERS NORMAL AND NO THRUST REVERSER UNLOCK AMBER LIGHT ON, ACFT OK FOR SERVICE.

Part: PRIORITY VALVE — FAILED (HYD SYSTEM) · airframe 55,667 hrs · 12,507 cycles

ON START OF T/O ROLL, RECEIVED ECAM FOR BLUE RSVR LO LEVEL, BLUE RSVR INDICATES EMPTY. TURNED OFF BLUE HYD ENG PUMP APPROX, 2 MINUTES AFTER ECAM ALERT. T/S AND FOUND ACTUALLEY BLUE RSVR HYD QTY INDICATED 1.5 G/L AND BLUE HYD MANIFOLD PRIORITY VALVE BROKEN. R & R PRIORITY VALVE AND ENG RUN AND PRESSURE & LEAK CHECKED NORMAL IAW MM 29-12-12-4 AND 29-00-00-3 AND 29-23-21-3. JRH CHAP 5 PARTS LOAN. ACFT OK FOR SERVICE. INSTALL BORROWED PART AND REMOVE PART.

Part: STRINGER — MISREPAIRED (ZONE 100) · airframe 55,057 hrs · 12,202 cycles

PREVIOUS STR REPAIR LOCATED IN AFT CABIN UNDER FLOOR BEHIND BULK CARGO ON STR 51 LT BETWEEN FRAMES 72 TO 74 HAS 2 EACH REPAIR ANGLES AND 1 EACH STR REPAIR SECTION. PREVIOUSLY INSTALLED REPAIR LOCATED IN AFT CABIN UNDER FLOOR BEHIND BULK CARGO ON STR 51 LT BETWEEN FRAMES 72 TO 74 WAS DETERMINED NOT TO IAW SRM 53-10-14, FIG 201A. DUE TO NO VALID REPAIR 51-3, BASED ON A VISUAL EVALUATION WITH THE 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 2 EA EXISTING REPAIR ANGLES AND REPAIRED THE STRINGER IAW EA 6-5310-135149 AND DWG R53070180, REV B.

Part: FAIRING — SHEARED (PYLON) · airframe 55,057 hrs · 12,202 cycles

NR 2 PYLON FAIRING 485AL INBD AFT SECTION MOUNTING RIVETS SHEARED NOT GOING THROUGH REINFORCING STRINGER REMOVED REINFORCING ANGLE. REPAIRED SKIN USING SPLICING METHOD IAW EA 6-5480-137727. REPLACED REINFORCING ANGLE IAW SRM 51-72-10.

Part: SKIN — DENTED (ZONE 100) · airframe 55,057 hrs · 12,202 cycles

LT SIDE LWR FUSELAGE SKIN AT FRAME 67 STR 50L DENT MEASURING 12 INCHES X 1 INCH X .188 DEEP. REPAIRED SKIN PN A53974208200 AT FRAME 67 BETWEEN STRINGERS 49L AND 50L USING DOUBLER AND FILLER IAW SRM 53-10-12 FIG. 225 PAGES 357 THROUGH 366.

Part: STRINGER — MISREPAIRED (ZONE 100) · airframe 55,057 hrs · 12,202 cycles

PREVIOUS STRINGER REPAIR LOCATED IN FWD CARGO ON STRINGER 36 LT BETWEEN FRAMES 20 TO 22 HAS 1 EACH REPAIR SPLICE MEASURING 7.2" LONG AND 1 EACH STRINGER REPAIR SPLICE MEASURING 24.3" LONG. PREVIOUSLY INSTALLED REPAIR LOCATED AT FWD CARGO ON STRINGER 36 LT BETWEEN FRAMES 20 TO 22 WAS DETERMINED NOT TO BE IAW SRM 53-10-14 FIG 201, DUE TO INCORRECT FASTENERS IN SKIN TO REPAIR SPLICE, BASED ON A VISUAL EVALUATION WITH 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 8 EACH RIVETS, REAMED UP HOLES, INSTALLED CORRECT HILOKS IN REPAIR SPLICE AND SKIN, REPROTECTED AREA AND TOPCOATED IAW SRM 53-10-14 FIG 201 AND SRM 51-75-10, REPAIR CLASSIFIED AS A MAJOR REPAIR IAW GMM 6-2-100. THIS IS AN AGING ACFT INSP FINDING.

Part: LIMITER — MALFUNCTIONED (SLAT TORQUE) · airframe 53,920 hrs · 11,439 cycles

DURING APPROACH WITH LANDING GEAR DOWN AND FLAPS 20/20, F/O GOT UNRELIABLE AIRSPEED ON PFD FOLLOWED BY SLATS/FLAPS SYS 1 AND 2 FAULT O/H. SLATS/FLAPS CYCLED PER QRH, THE LIGHT/FAULTS CLEARED CONFIGURED AGAIN THE SLATS STUCK AT 15 DEGREES. FOLLOWED QRH FOR SLATS STUCK LANDING. ON FINAL APPROACH FLAP HANDLE AT 40 DEGREES SLATS BROKE FREE AND WENT TO 30 DEGREES SLATS WITH 40 DEG FLAPS. THE LANDING WAS UNEVENTFUL. SLAT/FLAP RETRACT ON THE GROUND WAS NORMAL. CHECKED SLAT 0 POSITION AND INDEX OF LT APU, WW IPPU AND FPPU, CHK OK. REMOVED AND REPLACED RT APU ALL AMM 27-81-19-4. REMOVED AND REPLACED RT SLAT TORQUE LIMITER PER AMM 27-84-12-4. OPS CHECKED NORMAL PER AMM 27-84-00-5.

Part: SLAT SYSTEM — FAILED · airframe 53,916 hrs · 11,438 cycles

DURING APPROACH WITH THE LDG GEAR DN AND FLAPS 20/20, F/O GOT UNRELIABLE AIRSPEED ON PFD FOLLOWED BY SLATS/FLAPS SYS 1 AND 2 FAULT LIGHTS ON O/H. DISCONTINUED AP AND FOLLOWED QRH. WHEN THE SLATS/FLAPS CYCLED PER QRH, THE LIGHT/FAULTS CLEARED CONFIGURED AGAIN THE SLATS STUCK AT 15 DEGREES. FOLLOWED QRH FOR SLATS STUCK LNDG. ON FINAL AP FLAP HANDLE AT 40 DEGREES THE SLATS BROKE FREE AND WENT TO 30 DEGREES SLATS WITH 40 DEG FLAPS. THE LANDING WAS UNEVENTFUL AND SLAT/FLAP RETRACTON THE GROUND WAS NORMAL. REMOVED AND REPLACED SFCC'S, OFF MFG 49-079-05 POS 1 SRL 144 OFF MFG 49-079-05 POS 2 SRL 692. GEK BAE SYSTEMS AVIONICS LTD.

Part: COMPUTER — MALFUNCTIONED · airframe 53,916 hrs · 11,438 cycles

DURING APPROACH WITH THE LDG GEAR DN AND FLAPS 20/20, F/O GOT UNRELIABLE AIRSPEED ON PFD FOLLOWED BY SLATS/FLAPS SYS 1 AND 2 FAULT LIGHTS ON O/H. DISCONTINUED AP AND FOLLOWED QRH. WHEN THE SLATS/FLAPS CYCLED PER QRH, THE LIGHT/FAULTS CLEARED CONFIGURED AGAIN THE SLATS STUCK AT 15 DEGREES. FOLLOWED QRH FOR SLATS STUCK LANDING. ON FINAL AP FLAP HANDLE AT 40 DEGREES THE SLATS BROKE FREE AND WENT TO 30 DEGREES SLATS WITH 40 DEG FLAPS. THE LANDING WAS UNEVENTFUL AND SLAT/FLAP RETRACTION THE GROUND WAS NORMAL. REMOVED AND REPLACED SFCC'S,

Part: COMPUTER — FAILED · airframe 53,916 hrs · 11,438 cycles

DURING APPROACH WITH THE LANDING GEAR DOWN AND FLAPS 20/20, F/O GOT UNRELIABLE AIRSPEED ON PFD FOLLOWED BY SLATS/FLAPS SYS 1 AND 2 FAULT LIGHTS ON O/H. DISCONTINUED AP AND FOLLOWED QRH. WHEN THE SLATS/FLAPS CYCLED PER QRH, THE LIGHT/FAULTS CLEARED CONFIGURED AGAIN THE SLATS STUCK AT 15 DEGREES. FOLLOWED QRH FOR SLATS STUCK LANDING. ON FINAL AP FLAP HANDLE AT 40 DEGREES THE SLATS BROKE FREE AND WENT TO 30 DEGREES SLATS WITH 40 DEG FLAPS. THE LANDING WAS UNEVENTFUL AND SLAT/FLAP RETRACTION THE GROUND WAS NORMAL. REMOVED AND REPLACED SFCC'S, OFF MFG 49-079-05 POS 1 SRL 144 OFF MFG 49-079-05 POS 2 SRL 692.

Part: SLAT SYSTEM — MALFUNCTIONED (SLATS) · airframe 53,916 hrs · 11,438 cycles

DURING APPROACH WITH THE LDG GEAR DN AND FLAPS 20/20, F/O GOT UNRELIABLE AIRSPEED ON PFD FOLLOWED BY SLATS/FLAPS SYS 1 AND 2 FAULT LIGHTS ON O/H. DISCONTINUED AP AND FOLLOWED QRH. WHEN THE SLATS/FLAPS CYCLED PER QRH, THE LIGHT/FAULTS CLEARED CONFIGURED AGAIN THE SLATS STUCK AT 15 DEGREES. FOLLOWED QRH FOR SLATS STUCK LANDING. ON FINAL AP FLAP HANDLE AT 40 DEGREES THE SLATS BROKE FREE AND WENT TO 30 DEGREES SLATS WITH 40 DEG FLAPS. THE LANDING WAS UNEVENTFUL AND SLAT/FLAP RETRACTON THE GROUND WAS NORMAL. REMOVED AND REPLACED SFCC'S, OFF MFG 49-079-05 POS 1 SRL 144 OFF MFG 49-079-05 POS 2 SRL 692. GEK BAE SYSTEMS AVIONICS LTD.

Part: LIMITER — FAILED (SLAT TORQUE) · airframe 53,920 hrs · 11,439 cycles

DURING APPROACH WITH LANDING GEAR DOWN AND FLAPS 20/20, F/O GOT UNRELIABLE AIRSPEED ON PFD FOLLOWED BY SLATS/FLAPS SYS 1 AND 2 FAULT O/H. SLATS/FLAPS CYCLED PER QRH, THE LIGHT/FAULTS CLEARED CONFIGURED AGAIN THE SLATS STUCK AT 15 DEGREES. FOLLOWED QRH FOR SLATS STUCK LANDING. ON FINAL AP FLAP HANDLE AT 40 DEGREES SLATS BROKE FREE AND WENT TO 30 DEGREES SLATS WITH 40 DEG FLAPS. THE LANDING WAS UNEVENTFUL. SLAT/FLAP RETRACT ON THE GND WAS NORMAL. CKD SLAT 0 POSITION AND INDEX OF LT APPU, W/W IPPU AND FPPU, CHK OK. REMOVED AND REPLACED RT APPU ALL AMM 27-81-19-4. REMOVED AND REPLACED RT SLAT TORQUE LIMITER PER AMM 27-84-12-4 OPS CHK NORMAL PER AMM 27-84-00-5 OFF MFG 516A0000-02, SRL K1142, ON MFG 516A0000-03 SRL 00722.

Part: JACKSCREW — STUCK (SLATS) · airframe 53,809 hrs · 11,361 cycles

SLATS STUCK AT O DEG, C/W QRH, EMERGENCY DECLARED, LANDED UNEVENTFULLY AT SYR. REMOVED AND REPLACED RIGHT NR 2 JACKSCREW ASSY PER A310-300MM ATA 27-84-22-4.

Part: JACKSCREW — LEAKING (SLATS) · airframe 53,809 hrs · 11,361 cycles

SLATS STUCK AT 0 DEG, C/W QRH. EMERGENCY DECLARED, LANDED UNEVENTFULLY AT SYR. REMOVED AND REPLACED RIGHT NR 2 JACKSCREW ASSY PER A310-300MM ATA 27-84-22-4.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 53,219 hrs · 11,010 cycles

FWD PIT BETWEEN FR 39 AND FR 38.2 STGR 53 LT HAS CORROSION REMOVED CORROSION FOUND TO BE OUT OF LIMIT IAW SRM 53-10-14. FAB`D STRINGER DOUBLER IN T7/711755. REMOVED AND REPLACED STRG DOUBLER AND COUPLING IAW 51-40-44.

Part: STRINGER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 53,219 hrs · 11,010 cycles

FWD CARGO BETWEEN FR 38.1 AND FR 38.2 STGR 48 RT HAS CORROSION. REMOVED CORROSION FOUND TO BE OUT OF LIMITS IAW SRM 53-10-14. CUT OUT DAMAGE AREA STR 48 RT FR 37-38.1 IAW SRM 53-10-14. REMOVED SHEAR TIE TR 37 STR 47 RT. FAB STRINGER DOUBLER IAW MAE TRAVELER NR T2 / 711754. FAB STRINGER COUPLING IAW SRM 53-10-14. LOCATED AND DRILLED STRINGER DOUBLER AND STRINGER COUPLING IAW SRM 51-40- 43. INSTALLED STRINGER DOUBLER, STRINGER COUPLING, AND SHEAR TIE IAW SRM 53-10-14.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 53,131 hrs · 10,960 cycles

FOUND CORROSION AT STRINGER SEGMENT P48, C 68-69 AND C 70-71. REPAIR PERFORMED BY REPLACEMENT OF PART IAW SRM 51-72-10.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 53,131 hrs · 10,960 cycles

FOUND CORROSION AT STRINGER SEGMENT C 65, P 54 LT. REPAIR PERFORMED BY REPLACEMENT OF PART IAW SRM 51-72-10.

Part: SKIN — CORRODED (ZONE 100) · corrosion level 2 · airframe 53,131 hrs · 10,960 cycles

FOUND CORROSION AT WEDGE C 70, P56-57 RT. REPAIR PERFORMED BY REPLACEMENT OF PART IAW SRM 51-72-10.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 53,119 hrs · 10,954 cycles

FOUND CORROSION AT STRINGER SEGMENT P 56, C55/58 REPAIR PERFORMED BY REPLACEMENT OF PART IAW SRM 51-72-10.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 53,119 hrs · 10,954 cycles

FOUND CORROSION AT STRINGER SEGMENT C 72, P 48 LT. REPAIR PERFORMED BY REPLACEMENT OF PART IAW SRM 51-72-10.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 53,119 hrs · 10,954 cycles

FOUND CORROSION AT STRINGER SEGMENT P 56 LT, C 80 REPAIR PERFORMED BY REPLACEMENT OF PART IAW SRM 51-72-10.

Part: SKIN PANEL — DENTED (ZONE 100) · airframe 53,117 hrs · 10,953 cycles

FOUND OLD FLUSH REPAIR AT C20-21, P 35-37 LT NOT COMPATIBLE WITH P TO F CONVERSION. REPAIR RENEWED IAW RAS/DABRE/7004645/2004 ISS A.

Part: SKIN — WORN (ZONE 500) · airframe 53,119 hrs · 10,954 cycles

FOUND ON LT WING ON PYLON NR 1 ELONGATED HOLE AT WING TO PYLON BOTTOM SKIN ON AREA OF HYDRAULIC LINES. REPAIR PERFORMED BY REAM UP AND BUSHING INSTALLATION IAW DRAWING R572-49184, APPROVED BY EA 6-5720-81128 AND RAS/BAE/100457/2005 ISS A.

Part: FITTING — CORRODED (ZONE 100) · corrosion level 2 · airframe 53,119 hrs · 10,954 cycles

FOUND CORROSION AT CORNER FITTING C 33 LT REPAIR PERFORMED BY REPLACEMENT OF PART IAW SRM 51-72-10.

Part: SKIN — DENTED (NR 2 SLAT) · airframe 53,119 hrs · 10,954 cycles

FOUND DENT AT SLAT NR 2 LT OUT OF LIMIT. NOSE SKIN REPAIR PERFORMED IAW SRM 57-43-11 FIG 202.

Part: SKIN PANEL — CORRODED (ZONE 100) · corrosion level 2 · airframe 53,119 hrs · 10,954 cycles

FOUND CORROSION AT CENTER TANK TOP SKIN C 44-48, TRACK 3-5, LT/RT REPAIR PERFORMED BY REMOVAL OF CORROSION AND INSTALLING OF TWO DOUBLERS IAW DRAWING R573-10011 AT BEAM 4 AND 6, C 44-2 AND C 44 LT/RT IAW EA 6-5710-81129 AND RAS/AS/0036/2005 ISS A.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 53,119 hrs · 10,954 cycles

FOUND CORROSION AT STRINGER P 48 LT, C 69-70 REPAIR PERFORMED BY REPLACEMENT OF PART IAW SRM 51-72-10.

Part: CHANNEL — DENTED (CREW DOOR) · airframe 53,119 hrs · 10,954 cycles

LT AFT CREW DOOR LOWER CHANNEL HAS A NOTCH OUT OF LIMIT REPAIR PERFORMED BY REPLACEMENT OF PART IAW SRM 51-72-10.

Part: FITTING — CORRODED (ZONE 100) · corrosion level 2 · airframe 53,119 hrs · 10,954 cycles

FOUND CORROSION AT CORNER FITTING P 44 LT, C64 REPAIR PERFORMED BY REPLACEMENT OF PART IAW SRM 51-72-10.

Part: SKIN — DELAMINATED (RUDDER) · airframe 53,119 hrs · 10,954 cycles

DELAMINATION FOUND AT RUDDER SIDE PANEL IN THE AREA OF ATTACH FITTINGS REPAIR PERFORMED IAW SRM 55-41-12 FIG 216.

Part: RIB — DAMAGED (ZONE 600) · airframe 53,119 hrs · 10,954 cycles

FOUND OLD REPAIRS ON INBOARD FLAP RIB 21 (POCKET REPAIRS) NOT CONFORM TO SRM REPAIR PERFORMED BY REPLACEMENT OF END RIB 21 IAW SRM 57-2055.

Part: SKIN — DAMAGED (ZONE 600) · airframe 53,119 hrs · 10,954 cycles

RT INNER FLAP WITH SEVERAL DAMAGES, LIMITED TO 5 FLIGHTS IAW RAS/DABRE/7002673/2003. REPAIR PERFORMED IN WORKSHOP AND RELEASED IAW FAA FORM 8130-3 NR 05/1145.

Part: SKIN — WORN (ZONE 600) · airframe 53,119 hrs · 10,954 cycles

FOUND ON RT WING ON PYLON NR 2 ELONGATED HOLE AT WING TO PYLON BOTTOM SKIN ON AREA OF HYDRAULIC LINES. REPAIR PERFORMED BY REAM UP AND BUSHING INSTALLATION IAW DRAWING R572-49184, APPROVED BY EA 6-5720-81128 AND RAS/BAE/100457/2005 ISS A.

Part: FITTING — CORRODED (ZONE 100) · corrosion level 2 · airframe 53,119 hrs · 10,954 cycles

FOUND FITTING AT C13-13A, P26 LT CORRODED REPAIR PERFORMED BY REPLACEMENT OF PART IAW SRM 51-72-10.

Part: FLANGE — CORRODED (ZONE 100) · corrosion level 2 · airframe 53,119 hrs · 10,954 cycles

FOUND FLANGE C61-62, AD CORRODED REPAIR PERFORMED BY REPLACEMENT OF PART IAW SRM 51-72-10.

Part: FITTING — CORRODED (ZONE 100) · corrosion level 2 · airframe 53,119 hrs · 10,954 cycles

FOUND CORROSION AT RUN OUT FITTING P44 LT/RT, C17 REPAIR PERFORMED BY REPLACEMENT OF PART IAW DRAWING R536-10440.

Part: SKIN — MISREPAIRED (TE FLAP) · airframe 53,119 hrs · 10,954 cycles

FOUND OLD POCKET REPAIRS AT RIB 21 INBOARD FLAP LT NOT CONFORM TO SRM. REPAIR PERFORMED BY REPLACEMENT OF PART IAW SB 57-2055.

Part: SEAT TRACK — CORRODED (ZONE 100) · corrosion level 2 · airframe 53,119 hrs · 10,954 cycles

FOUND SEAT TRACK C 15A-19, Y-953 CORRODED REPAIR PERFORMED BY REPLACEMENT OF PART IAW SRM 51-72-10.

Part: FRAME — DAMAGED (ZONE 200) · airframe 53,119 hrs · 10,954 cycles

FOUND ENLARGED HOLES AT C 26/32 BETWEEN P 13-22 RT REPAIR PERFORMED BY REPLACEMENT OF PART IAW SRM 51-72-10.

Part: LUG — CORRODED (ZONE 600) · corrosion level 2 · airframe 53,119 hrs · 10,954 cycles

FOUND CORROSION ONE BEARING BORE OF RT WING PYLON OUTBOARD MOUNTING LUG REPAIR PERFORMED BY BLEND OUT CORROSION, NDT FOR DAMAGE FREE IAW EA 6-5720- 81124 AND RAS/BAE/1000347/2005 ISS A.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 53,119 hrs · 10,954 cycles

FOUND CORROSION AT STRINGER SEGMENT C 72, 45 REPAIR PERFORMED BY REPLACEMENT OF PART IAW SRM 51-72-10.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 53,116 hrs · 10,952 cycles

FOUND CORROSION AT STRINGER P54LH BETWEEN C55/58-65 STRINGER REPAIR PERFORMED IAW SRM 53-10-14 FIG 201.

Part: PANEL — DENTED (ZONE 200) · airframe 53,116 hrs · 10,952 cycles

FOUND OLD DENT AT C 8 IN 9 O'CLOCK POSITION. DOUBLER REPAIR PERFORMED IAW SRM 53-11-12 FIG 201.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 53,116 hrs · 10,952 cycles

FOUND CORROSION AT STRINGER P55LH BETWEEN C 55/58-61 STRINGER REPAIR PERFORMED IAW SRM 53-10-14 FIG 201.

Part: FLOORBEAM — CORRODED (ZONE 100) · corrosion level 2 · airframe 53,116 hrs · 10,952 cycles

FOUND CORROSION AT UPPER FLANGE OF TOP CAP BEAM C33 SPLICE REPAIR PERFORMED IAW SRM 53-10-15 FIG 207.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 53,116 hrs · 10,952 cycles

FOUND CORROSION AT STRINGER P 56LH, BETWEEN C 76-77. REPAIR PERFORMED BY BLEND OUT CORROSION AND FLAP PEENING IAW EA 6-5318-81118 AND RAS/DATLS/0002357/2005 ISS A.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 53,116 hrs · 10,952 cycles

FOUND CORROSION AT STRINGER P57 C 66. STRINGER REPAIR PERFORMED IAW SRM 53-10-14 FIG 201.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 53,116 hrs · 10,952 cycles

FOUND CORROSION AT STRINGER P56LH BETWEEN C55/58-65 STRINGER REPAIR PERFORMED IAW SRM 53-10-14 FIG 201.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 53,116 hrs · 10,952 cycles

FOUND CORROSION AT STRINGER P56 C 68-70 STRINGER REPAIR PERFORMED IAW SRM 53-10-14 FIG 201.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 53,116 hrs · 10,952 cycles

FOUND CORROSION AT STRINGER P56 RT BETWEEN C 55/58-59. STRINGER REPAIR PERFORMED IAW SRM 53-10-14 FIG 201.

Part: SKIN PANEL — DENTED (ZONE 100) · airframe 53,116 hrs · 10,952 cycles

FOUND DENT AT SKIN C63-65, P41-42 LT (AREA 1) AND P45-46 LT (AREA 2) DOUBLER REPAIR PERFORMED IN AREA 1 IAW SRM 53-10-12 FIG 228 AND LET THE DENT IN AREA 2 AS IT IS IAW EA 6-5317-81131 AND RAS/DATLS/0002418/2005 ISS A.

Part: BULKHEAD — DAMAGED (ZONE 100) · airframe 53,116 hrs · 10,952 cycles

FOUND OLD REPAIR (MISDRILLED HOLE) AT FRAME 54 BULKHEAD LT WEB, WAS ACCEPTED FOR ONLY ONE FERRY FLIGHT. REPAIR RENEWED BY REMOVING THE EXISTING DOUBLER, CUT OUT ON WEB FOOT AND INSTALLING DOUBLER AND REPAIR ANGLE IAW EA 6-5315-81126 AND RAS/AS/0248/2004 ISS B.

Part: SKIN PANEL — DENTED (ZONE 100) · airframe 53,116 hrs · 10,952 cycles

FOUND DENT DAMAGE AT SERVICE BOX PANEL C10-13 BUSH REPAIR PERFORMED IAW SRM 53-10-12 FIG 221.

Part: SKIN PANEL — DENTED (ZONE 100) · airframe 53,116 hrs · 10,952 cycles

FOUND SKIN DENT AT C72, P26-27 RT ON SKIN PANEL NR 1 REPAIR PERFORMED BY CUT OUT THE SKIN AND INSTALLING A EXTERNAL DOUBLER AND FILLER IAW DRAWING R539-70630, APPROVED BY EA 6-5318-81127 AND RAS/DAHAM/4019001/2005 ISS A.

Part: SKIN PANEL — DENTED (ZONE 100) · airframe 53,116 hrs · 10,952 cycles

FOUND DENT AT C77-78, P 27-28 LT FLUSH DOUBLER REPAIR PERFORMED IAW SRM 53-10-12 FIG 227 AND STRINGER REPAIR PERFORMED IAW SRM 53-10-14.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 53,116 hrs · 10,952 cycles

FOUND CORROSION AT STRINGER P47LT, C72 STRINGER REPAIR PERFORMED IAW SRM 53-10-14 FIG 201.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 53,116 hrs · 10,952 cycles

FOUND CORROSION AT STRINGER P 54 AND P56, LT, BETWEEN C 70-72 STRINGER REPAIR PERFORMED IAW SRM 53-10-14 FIG 201.

Part: DUCT — UNKNOWN (COCKPIT) · airframe 52,137 hrs · 10,391 cycles

AFTER TAKEOFF AT ABOUT 800 AGL "AVIONICS SMOKE" ANNUNCIATED ON ECAM WITH CRC ECAM WARNING CONTINUED FOR ABOUT 7-10 SECONDS AND THEN CANCELED ITSELF. REPLACED COCKPIT DUCT SMOKE DET 13 WA PER AMM 26-15-12-4, OPS TEST IAW MM 26-15-00-5. OPS CHECK GOOD. A/C OK FOR SERVICE. REMOVED AND INSTALLED FROM FACT PREMATURE REMOVAL/INSTALLATION OFF MFG CG7G0-11.

Part: COMPUTER — MALFUNCTIONED (TE FLAPS) · airframe 52,030 hrs · 10,335 cycles

FLAPS STUCK, BOTH FLAPS 1 AND FLAPS 2 HAD FAULT ON OVHD HYD PANEL. ECAM SHOWED SAME, SPFI HAD NO INDICATION. FOUND BOTH SFCC'S FAULTING FLAP JAM FOUND RT TORQUE LIMITER IN WHEEL WELL FAULTED, FOUND NR 1 SCREW JACK TORQUE LIMITER FAULTED, RESET BOTH TORQUE LIMITERS PER MM 27-54-19-2, LWR FLAPS INSPECTED ALL RT WING FLAP TRACKS AND JACK SCREWS NO DEFECTS NOTED, CHECKED SERVICING ON ALL RT WING CREW JACK ASSEMBLIES, ALL CHECKED GOOD EXCEPT NR 1 SCREW JACK REQUIRED APPROX 50 CC'S OF 5606 HYD FLUID. OPS CK'D FLAPS PER MM 27-54-00. NO FAULTS NOTED.