N806FD

Part: SEQUENCE VALVE — OUT OF RIG (MLG) · airframe 50,941 hrs · 15,861 cycles

GEAR LEVER RAISED, RT MAIN GEAR DID NOT RETRACT. GREEN DOWN INDICATION, GEAR DOOR AMBER. PUT GEAR HANDLE BACK DOWN ALL INDICATIONS BACK TO NORMAL FOR DOWN & LOCKED. JACKED ACFT, SWUNG RT MAIN GEAR, GEAR DID NOT RETRACT. FOUND RT MAIN GEAR SEQUENCE VALVE OUT OF RIG BY 1 HOLE. ADJUSTED SEQUENCE VALVE IAW MM 32-31-37-04. SWUNG GEAR THREE TIMES, OPS CHECKED GOOD. R & R SEQUENCE VALVE IAW MM32-31-37-04. OPS CHECKED NORMAL IAW MM 32-31-37-04, NO LEAKS FOUND.

Part: ACTUATOR — FAULTED (NR 1 ENGINE) · airframe 48,823 hrs · 14,857 cycles

PRIOR TO THRUST SET FOR TAKEOFF, RECEIVED NR 1 ENGINE FADEC CHANNEL A FAULT AND FADEC CHANNEL B FAULT. REJECTED TAKEOFF AT 45-50 KNOTS. FOLLOWED QRH PROCEDURES. SHUTDOWN AND RESTARTED NR 1 ENGINE, ATTEMPTED TAKEOFF AND RECEIVED SAME FAULTS AT SLIGHTLY HIGHER SPEED (60 KNOTS). R & R STATOR VANE ACTUATOR IAW AMM75-31-03-04, AND ADJUSTED IAW AMM 75-31-03-05. PERFORMED NR 1 ENGINE IDLE POWER TEST AND FADEC IDLE TEST IAW AMM 71-00-00-05, TESTED NORMAL, ALL PARAMETER SATISFACTORY, AND LEAK CHECKED OK. PERFORMED HIGH POWER TEST IAW AMM 71-00-00-05 AND NO WARNING MESSAGE FOR NR 1 ENGINE FADEC CHANNELS A & B FAULT FOUND. ACFT OK FOR SERVICE.

Part: SKIN — CRACKED (NR 1 NACELLE) · airframe 48,719 hrs · 14,816 cycles

NR 1 ENGINE PYLON RT SIDE LOWER SKIN PANEL CRACKED POSITION NEAR AFT ENGINE MOUNT. REPAIRED IAW SRM 51-40-21 AND SRM 54-56-10 C2. THE REPAIR CLASSIFIED AS MINOR IAW GMM 6-2-100.

Part: SKIN — CRACKED (NR 1 NACELLE) · airframe 48,719 hrs · 14,816 cycles

NR 1 ENGINE PYLON LT SIDE LOWER SKIN PANEL CRACKED POSITION NEAR AFT ENGINE MOUNT. REPAIRED IAW SRM 51-40-21 AND SRM 54-56-10 C2. THE REPAIR CLASSIFIED AS MINOR IAW GMM 6-2-100.

Part: SKIN — CRACKED (RT WING) · airframe 48,719 hrs · 14,816 cycles

ONE CRACK FOUND, LENGTH 13MM AT RT WING BOTTOM SKIN LANDING PLATE AREA. REPAIRED. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: FLOOR SUPPORT — CORRODED (MAIN DECK) · airframe 48,719 hrs · 14,816 cycles

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

Part: FLOOR PANEL — DAMAGED (CARGO BAY) · airframe 48,719 hrs · 14,816 cycles

BULK CARGO BAY FLOOR PANEL 161JF HAS IMPACT DAMAGED. REMOVED FLOOR PANEL IAW AMM 53-10-35- 04. FABRICATED A NEW FLOOR PANEL IAW SRM 53-10-20 AND DWG 17 A53279960. REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS MINOR. INSTALLED FLOOR PANEL TO NORMAL CONDITION IAW AMM 53-10-35-04.

Part: FLOOR PANEL — DAMAGED (AFT CARGO BAY) · airframe 48,719 hrs · 14,816 cycles

AFT CARGO COMPARTMENT FOUND FLOOR PANEL 151AF HAS IMPACT DAMAGE. REMOVED FLOOR PANEL IAW AMM 53-10-33- 04. FABRICATED NEW FLOOR PANEL IAW SRM 53-10-20, AND DWG 10 A25772831. REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS MINOR. INSTALLED FLOOR PANEL TO NORMAL CONDITION IAW AMM 53-10-33-04.

Part: FLOOR PANEL — DAMAGED (E/E BAY) · airframe 48,719 hrs · 14,816 cycles

AVIONICS BAY FLOOR PANEL 122PF HAS IMPACT DAMAGE. REMOVED FLOOR PANEL IAW AMM 53-10-27- 04. FABRICATED NEW FLOOR PANEL IAW SRM 53-10-20, AND DWG 12 A53210216. REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS MINOR. INSTALLED FLOOR PANEL IAW AMM 53-10-27-04.

Part: FLOOR PANEL — DAMAGED (CARGO BAY) · airframe 48,719 hrs · 14,816 cycles

BULK CARGO BAY FLOOR PANEL 162HF HAS IMPACT DAMAGE. REMOVED FLOOR PANEL IAW AMM 53-10-35-04. FABRICATED NEW FLOOR PANEL IAW SRM 53-10-20, AND DWG 17 A53279962. REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS MINOR. INSTALLED FLOOR PANEL IAW AMM 53-10-35-04.

Part: FLOOR PANEL — DAMAGED (FWD CARGO BAY) · airframe 48,719 hrs · 14,816 cycles

FWD CARGO BAY FLOOR PANEL 132RF HAS IMPACT DAMAGED. REMOVED FLOOR PANEL, FABRICATED A NEW FLOOR PANEL IAW SRM 53-10-20, AND DWG A53272792. REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS MINOR. INSTALLED FLOOR PANEL TO NORMAL CONDITION IAW AMM 53-10-29-04.

Part: TRANSMITTER — LEAKING (HYD SYSTEM) · airframe 47,310 hrs · 14,195 cycles

LOST YELLOW SYS HYD ENROUTE. COMPLIED WITH ECAM & QRH. HYD FLUID LEAKING FROM YELLOW HYD SYS PRESSURE TRANSMITTER 16WV HSG CAP & CGO DOOR HYD SELECTOR VALVE 10MJ THE CONTROL SHAFT. R & I 16WV & 10MJ ASSY, REPLENISH YELLOW HYD RESERVOIR & LEAK CHECKED OK, IAW AMM 29-32-13-04 AND AMM 52-33-12-04-0. CYCLED ALL FLIGHT CONTROL SYS. FOUND SATIS IAW AMM 27-11-00.

Part: SKIN — MISREPAIRED (ZONE 200) · airframe 46,117 hrs · 13,665 cycles

AN EXISTING FUSELAGE SKIN REPAIR IS AT FR52-53, BELOW STRINGER 18L. THERE ARE 5 ROWS OF 11 RIVETS ATTACHING THE SKIN (A53870003220) TO THE PLATE (A53870004218). THERE IS NO CUTOUT OR DOUBLER. IAW EA 6-5330-141519, REMOVED RIVETS IAW SRM 51-40-21 AND ROTO-TEST HOLES IAW NTM 51-10-01. INSTALLED NEW RIVETS (NAS1097DD5) IAW SRM 51-40-21. PERFORMED RESONANCE FREQUENCY TEST IAW NTM 51-50-00 TO CHECK FOR BOND DEFECTS.

Part: SEAT TRACK — DAMAGED (ZONE 200) · airframe 44,091 hrs · 12,415 cycles

MAIN DECK CARGO FLOOR SEAT TRACK NR 1 RT SIDE, FR 61 HAS DAMAGE ON LOWER SURFACE, .545 IN ROUND BY .045 IN DEEP. REMOVED DAMAGED SEAT TRACK SECTION FROM FR 60.5 TO FR 61.5 AND REPAIRED IAW A310 SRM 53-10-16,FIG 208

Part: WINDSHIELD — CRACKED (COCKPIT) · airframe 43,937 hrs · 12,324 cycles

A/C HAS DIVERTED INTO CUN DUE F/O WINDSHIELD HAS SHATTERED. REMOVED AND REPLACED F/O WINDSHIELD A310-300 M/M 56-11-11-4, OPN CHECK IS GOOD. OK FOR SVC. REPLACED WINDSHIELD TEMP REGULATOR AS A PRECAUTION AMM 30-42-11-4 REPLACED WINDOW HEAT PROTECTION CONTROLLER AS A PRE AUTION AMM 30-42-51-4

Part: DOUBLER — CORRODED (ZONE 100) · corrosion level 2 · airframe 43,729 hrs · 12,209 cycles

FOUND CORROSION AT DOUBLER C71-72, P 47-48 LT REPAIR PERFORMED BYREWORK OF CORROSION, NDT FOR CRACK FREE AND FLAP PEENING IAW EA 6-5317-82856 AND RAS/DATLS/0002522/2005 ISS B.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 43,729 hrs · 12,209 cycles

FOUND CORROSION BETWEEN C 39-47 AT STRINGERS BETWEEN P 38-49, LT AND RT. REPAIR PERFORMED BY SMOOTH REWORK OF CORROSION IAW EA 6-5315-82855 AND RAS/AS/0095/2005 ISS A.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 43,729 hrs · 12,209 cycles

FOUND CORROSION BETWEEN C 39-47 AT STRINGERS BETWEEN P 38-49, LT AND RT. REPAIR PERFORMED BY SMOOTH REWORK OF CORROSION IAW EA 6-5315-82855 AND RAS/AS/0095/2005 ISS A.

Part: SKIN PANEL — DENTED (ZONE 100) · airframe 43,729 hrs · 12,209 cycles

FOUND NICK ON SKIN PANEL NR 3 C 18-19, P 33 RT REPAIR PERFORMED BY BLEND OUT TO SMOOTH CONTOUR IAW EA 6-5313-82859 AND RAS/DABRE/7005143/2005 ISS A.

Part: FLANGE — CORRODED (ZONE 100) · corrosion level 2 · airframe 43,729 hrs · 12,209 cycles

FOUND CORRODED FLANGE AT C61-62, P 56 RT-56 LT REPAIR PERFORMED BY REPLACEMENT OF PART IAW SRM 51-72-10.

Part: SPAR — DAMAGED (ZONE 600) · airframe 43,729 hrs · 12,209 cycles

SHOULDERED BOLTS FOUND DURING EMBODIMENT OF SB A310-57-2079 AT HOLE NR 21 AND NR 14 RT REAR SPAR AREA OF SPOILER NR 3 RT REPAIR PERFORMED BY REPLACEMENT OF BUSH IAW EA 6-5720-82852 AND RAS /BAE/1000689/2005 ISS A.

Part: STRINGER — DAMAGED (ZONE 100) · airframe 43,729 hrs · 12,209 cycles

FOUND MISDRILLED HOLES AT STRINGER 41 LT, C33-34 STRINGER REPAIR PERFORMED IAW SRM 53-10-14 FIG 201.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 43,729 hrs · 12,209 cycles

FOUND CORRODED STRINGER SEGMENT P 57 AT C 72 REPAIR PERFORMED BY REPLACEMENT OF PART IAW SRM 51-72-10.

Part: FLOORBEAM — CORRODED (ZONE 100) · corrosion level 2 · airframe 43,729 hrs · 12,209 cycles

FOUND CROSSBEAM C 63 CORRODED. REPAIR PERFORMED BY REPLACEMENT OF PART IAW SRM 51-72-10.

Part: FITTING — CHAFED (ZONE 400) · airframe 43,729 hrs · 12,209 cycles

FOUND CHAFING MARKS AT PYLON TO WING FITTING RIB 18, PYLON NR 2 REPAIR PERFORMED BY REPLACEMENT OF PART IAW SRM 51-72-10.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 43,729 hrs · 12,209 cycles

FOUND CORROSION AT STRINGER P52 LT, C70-71. STRINGER REPAIR PERFORMED IAW SRM 53-10-14 FIG 201.

Part: PANEL — CRACKED (NR 2 PYLON) · airframe 43,729 hrs · 12,209 cycles

FOUND CRACK (ABOUT 6MM) AT PYLON NR 2 RIB 8 OUTBOARD SIDE WALL DOUBLER REPAIR PERFORMED IAW SRM 54-51-31 FIG 201.

Part: FITTING — CRACKED (ZONE 100) · airframe 43,729 hrs · 12,209 cycles

FITTING AT P 48, C78 LT CRACKED (ABOUT 8MM). REPAIR PERFORMED BY REPLACEMENT OF PART IAW SRM 51-72-10.

Part: FLOORBEAM — DAMAGED (ZONE 100) · airframe 43,729 hrs · 12,209 cycles

FOUND OLD MISDRILLED HOLE AT CROSSBEAM C 64 REPAIR PERFORMED BY REPLACEMENT OF PART IAW SRM 51-72-10.

Part: FITTING — DAMAGED (ZONE 100) · airframe 43,729 hrs · 12,209 cycles

FOUND MISDRILLED HOLES IN CORNER FITTING C59, P 44 RT REPAIR PERFORMED BY REPLACEMENT OF PART IAW SRM 51-72-10.

Part: FITTING — CORRODED (ZONE 100) · corrosion level 2 · airframe 43,729 hrs · 12,209 cycles

FOUND CORROSION AT FITTING C 63, P44-46 LT REPAIR PERFORMED BY REPLACEMENT OF PART IAW SRM 51-72-10.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 43,729 hrs · 12,209 cycles

FOUND CORROSION BETWEEN C 39-47 AT STRINGERS BETWEEN P 38-49, LT AND RT. REPAIR PERFORMED BY SMOOTH REWORK OF CORROSION IAW EA 6-5315-82855 AND RAS/AS/0095/2005 ISS A.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 43,729 hrs · 12,209 cycles

FOUND CORROSION BETWEEN C 39-47 AT STRINGERS BETWEEN P 38-49, LT AND RT. REPAIR PERFORMED BY SMOOTH REWORK OF CORROSION IAW EA 6-5315-82855 AND RAS/AS/0095/2005 ISS A.

Part: SKIN — DELAMINATED (ZONE 300) · airframe 43,729 hrs · 12,209 cycles

FOUND AT RUDDER TRAILING EDGE LOWER CORNER DELAMINTION NEAR RIB 0 REPAIR PERFORMED IAW SRM 55-41-12 FIG 208A.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 43,729 hrs · 12,209 cycles

FOUND CORROSION BETWEEN C 39-47 AT STRINGERS BETWEEN P 38-49, LT AND RT. REPAIR PERFORMED BY SMOOTH REWORK OF CORROSION IAW EA 6-5315-82855 AND RAS/AS/0095/2005 ISS A.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 43,729 hrs · 12,209 cycles

FOUND CORRODED STRINGER P 21 LT, BETWEEN 55/58-60 STRINGER REPAIR PERFORMED IAW SRM 53-10-14 FIG 201.

Part: SKIN PANEL — DAMAGED (ZONE 100) · airframe 43,729 hrs · 12,209 cycles

FOUND DURING P TO F CONVERSION A CUT (10MM) AT SKIN PANEL C 35, P 35 LT REPAIR PERFORMED BY CUT OUT THE SKIN AND INSTALLING A FLUSH REPAIR WITH NEW STRAP AND COUPLING IAW EA 6-5314-82877 AND RAS/DABRE/7005190/2005 ISS A.

Part: SKIN — CHAFED (ZONE 600) · airframe 43,724 hrs · 12,206 cycles

FOUND ON OLD NOSE SKIN REPAIR IAW SRM 57-41-12/FIG 203, 204, CHAFING MARKS BETWEEN SLAT TRACK 5 AND SLAT TRACK 6, LEADING EDGE SKIN, RT WING. NEW REPAIR SKIN INSERT INSTALLED IAW SRM 57-41-12/FIG 203, 204.

Part: PLATE — CRACKED (ZONE 500) · airframe 43,724 hrs · 12,206 cycles

FOUND CRACKED REINFORCING PLATE ON SLAT TRACK NR 7, FWD OF FRONT SPAR, UPPER SKIN, LT WING. REPLACEMENT OF REINFORCING PLATE ON TRACK 7 LT IAW SRM 51-72-10.

Part: SKIN — CHAFED (ZONE 600) · airframe 43,724 hrs · 12,206 cycles

FOUND CHAFING MARKS BETWEEN SLAT TRACK 6 AND JACK 4, LEADING EDGE SKIN, RT WING. REPAIR PERFORMED BY INSTALLATION OF NEW SKIN INSERT IAW SRM 57-41-12/FIG 203, 204.

Part: PLATE — CRACKED (ZONE 500) · airframe 43,724 hrs · 12,206 cycles

FOUND CRACKED REINFORCING PLATE ON SLAT TRACK NR 6, FWD OF FRONT SPAR, UPPER SKIN, LT WING. REPLACEMENT OF REINFORCING PLATE ON TRACK 6 LT IAW SRM 51-72-10.

Part: SKIN PANEL — MISINSTALLED (ZONE 200) · airframe 43,723 hrs · 12,205 cycles

FOUND OLD EXTERNAL DOUBLER REPAIR ON FUSELAGE SKIN BETWEEN FRAME 11-12, STGR 25-26 LT IAW RAS 031880/026/2004 ISSUE A THIS REPAIR WAS ONLY AUTHORIZED FOR ONE FERRY FLIGHT TO DRESDEN BECAUSE OF SOME DEVIATIONS AGAINST SRM 53-12-12/FIG 202. REPAIR PERFORMED BY INSTALLATION OF NEW DOUBLER IAW EA 6-5312-82857 AND RAS 031880/039/2004 ISSUE A.

Part: SKIN — CHAFED (ZONE 600) · airframe 43,724 hrs · 12,206 cycles

FOUND ON OLD NOSE SKIN REPAIR IAW SRM 57-41-12/FIG 204, CHAFING MARKS BETWEEN JACK 3 AND SLAT TRACK 5, LEADING EDGE SKIN, RT WING. NEW REPAIR SKIN INSERT INSTALLED IAW SRM 57-41-12/FIG 203, 204.

Part: SKIN — CHAFED (ZONE 600) · airframe 43,724 hrs · 12,206 cycles

FOUND ON OLD NOSE SKIN REPAIR IAW SRM 57-41-12/FIG 203, 204, CHAFING MARKS BETWEEN SLAT TRACK 1 AND SLAT TRACK 2, LEADING EDGE SKIN, RT WING. NOSE SKIN REPAIR RENEWED, NEW REPAIR SKIN IAW SRM 57-41-12/FIG 203, 204.

Part: PLATE — DAMAGED (ZONE 100) · airframe 43,724 hrs · 12,206 cycles

DAMAGED WEB PLATES BETWEEN FRAME 86-87, STGR 39 LT AND RT. REPLACEMENT OF WEB PLATES LT AND RT IAW SRM 51-72-10

Part: FITTING — CORRODED (ZONE 100) · corrosion level 3 · airframe 43,724 hrs · 12,206 cycles

CORROSION ON UPPER RUN OUT FITTING BETWEEN FRAME 16A-17, STRG 44 RT, AFTER REWORK NO REMAINING THICKNESS WAS EXISTED. REPLACEMENT OF UPPER RUN OUT FITTING IAW. REPAIR DRW R536-10440 ISSUE C.

Part: SKIN — CHAFED (ZONE 600) · airframe 43,724 hrs · 12,206 cycles

FOUND SCRATCHES ON NOSE SKIN OF SLAT NR 2 RT WING, RIB 24-27. NOSE SKIN REPAIR PERFORMED IAW SRM 57-43-11/FIG 202/SHEET 11. REFER TO NON ROUTINE DR0399, AT RIB 27 OTHER ASNA0081A FASTENERS ARE INSTALLED ACC TO DRW A578-44242/SHEET 16, IAW AI-STATEMENT 942-037611/005/2005.

Part: SKIN — CORRODED (ZONE 600) · airframe 43,723 hrs · 12,205 cycles

OLD DOUBLER REPAIR AT RT WING-LET TO STATIC DISCHARGER NO. V, FINAL REPAIR IS NECESSARY. AFTER REMOVAL OF DOUBLER FOUND ADDITIONAL CORROSION AND A MISDRILLED HOLE ON THE SKIN OF INBOARD PANEL OF RT FENCE. REPAIR PERFORMED BY SKIN CUTOUT AND INSTALLING FABRICATED REPAIR DOUBLER AND FILLER IAW EA 6-5730-82863 AND RAS/FOK/080/2005 ISSUE A.

Part: PLATE — CRACKED (ZONE 600) · airframe 43,724 hrs · 12,206 cycles

FOUND CRACKED REINFORCING PLATE ON SLAT TRACK NR 7, FWD OF FRONT SPAR, UPPER SKIN, RT WING. REPLACEMENT OF REINFORCING PLATE ON TRACK 7 RT IAW SRM 51-72-10.

Part: SKIN — CHAFED (ZONE 500) · airframe 43,724 hrs · 12,206 cycles

FOUND CHAFING MARKS BETWEEN JACK 3 AND SLAT TRACK 5, LEADING EDGE SKIN, LT WING. NOSE SKIN REPAIR PERFORMED SRM 57-41-12/FIG 203, 204.

Part: SKIN — FAILED (ZONE 600) · airframe 43,723 hrs · 12,205 cycles

EXISTING EXTERNAL REPAIR DOUBLER ON NOSE SKIN OF OUTBOARD RT FLAP, RIB 10.5 (PANAM EA X3157J518). PERMANENT REPAIR WAS CARRIED OUT ON 25-APR-1994 BY REPLACING THE INSTALLED DOUBLER WITH A 1,8MM THICK ONE AND THE EXISTING FASTENERS WITH BLIND RIVETS CR3552-P6 TO ELIMINATE KNIFE EDGES. FOUND NO RAS FOR THIS REPAIR. REPLACEMENT OF NOSE-RIB 10.5. REPAIR PATCH RENEWED AND RE-INSTALLED WITH CR3552- P6 FASTENERS IAW RAS/DABRE/7005095/2005 FOR TRACKING HAS BEEN WRITTEN EA 6-5753-82850.

Part: SKIN — CHAFED (ZONE 500) · airframe 43,724 hrs · 12,206 cycles

FOUND CHAFING MARKS BETWEEN SLAT TRACK 5 AND SLAT TRACK 6, LEADING EDGE SKIN, LT WING. REPLACEMENT OF CHAFED NOSE SKIN IAW SRM 51-72-10.

Part: PLATE — DAMAGED (ZONE 100) · airframe 43,724 hrs · 12,206 cycles

DAMAGED WEB PLATES BETWEEN FRAME 86-87, STGR. 33 LT REPLACEMENT OF WEB PLATE IAW SRM 51-72-10.

Part: SKIN PANEL — WORN (ZONE 600) · airframe 43,719 hrs · 12,204 cycles

ELONGATED HYDRAULIC FITTING HOLE NR 1 ON RT WING LOWER SKIN, PYLON SUPPORT BRACKET, RIB 8. REPAIR OF HOLE NR 1 PERFORMED BY OVERSIZING AND BUSHING IAW EA 6-5720-82851 AND RAS/BAE/1000639/2005 ISSUE A.

Part: SKIN — CORRODED (ZONE 200) · corrosion level 2 · airframe 43,719 hrs · 12,204 cycles

CORROSION ON FAIL/SAFE RING PAX DOOR NR 1 LT FUSELAGE SKIN PANEL AT FRAME 14, FWD UPPER CORNER. REPAIR PERFORMED BY BLENDING CORROSION AND HFEC INSPECTION IN THE AREA IAW EA 6-5312-82849 AND RAS/036735/006/2005 ISSUE A.

Part: SKIN — CORRODED (ZONE 200) · corrosion level 2 · airframe 43,719 hrs · 12,204 cycles

CORROSION ON FAIL/SAFE RING PAX DOOR NR 1 LT FUSELAGE SKIN PANEL AT FRAME 16A, AFT UPPER CORNER. REPAIR PERFORMED BY BLENDING CORROSION AND HFEC INSPECTION IN THE AREA IAW EA 6-5312-82849 AND RAS/036735/006/2005 ISSUE A.

Part: SKIN — FAILED (RT TE FLAP) · airframe 43,716 hrs · 12,203 cycles

FOUND OLD REPAIR ON CLOSING RIB 21, INNER FLAP RT FINAL REPAIR ON FLAP BY REPLACEMENT OF END RIB 21 IAW SB A310-57-2055/PARA 2 F.

Part: SKIN — CORRODED (ZONE 200) · corrosion level 2 · airframe 43,719 hrs · 12,204 cycles

CORROSION ON FAIL/SAFE RING PAX DOOR NR 1 FUSELAGE SKIN PANEL AT FRAME 14, STGR 25 RT, AROUND THREE FASTENERS. REPAIR PERFORMED BY BLENDING CORROSION, HFEC INSPECTION IN THE AREA, ROTOTEST OF HOLES FOR NIL CRACK FINDINGS WITH OVERSIZING HOLES FOR TRANSITION FIT IAW EA 6-5312-82936 AND RAS/AS/069/2005 ISSUE A.

Part: SKIN — DELAMINATED (ZONE 300) · airframe 43,716 hrs · 12,203 cycles

FOUND DELAMINATIONS ON RUDDER SIDE PANEL IN AREA OF HINGE ATTACHMENTS AT ALL GFRP-FITTINGS LT AND RT: BR1, BR2, BR4 LOWER, BR4 CENTER, BR4 UPPER, BR5, BR6 AND BR7. DELAMINATION REPAIR OF GFRP FITTING CONNECTION AT ALL HINGE FITTINGS PERFORMED IAW SRM 55-41-12/FIG 216.

Part: SKIN — FAILED (ZONE 600) · airframe 43,716 hrs · 12,203 cycles

FOUND OLD DOUBLER REPAIR ON LOWER PANEL, CENTER BOX OF INBOARD FLAP RT, RIB 9-11, NOT IAW SRM 57-52-12/FIG 205, DOUBLER EDGES, LENGTH OF DOUBLER SHEET NOT ALLOWED. REPAIR RENEWED AS PER SRM 57-52-12/FIG 205, RIB 9. REPAIRED AS PER SRM 51-40-51/FIG 202, ALL IAW EA 6-5752-82935 AND RAS/DABRE/7005009/2005 ISSUE A.

Part: TRANSMITTER — MALFUNCTIONED (HYD PRESSURE) · airframe 43,381 hrs · 12,001 cycles

LOST GREEN SYSTEM FLUID IN DESCENT. FOLLOWED ECAM PR OC AND QRH, GRAVITY EXTENDED THE GEAR PER QRH. AFTER PRESSURIZING GREEN HYD SYS DISCOVERED FLUID LEAKING FROM THE TOP OF THE GREEN SYS MANIFOLD AT THE PRESS XMITTER BASE. THE REST OF THE STORY: AFTER TALKING WITH THE CREW THEY REPORTED A FEW MINUTES AFTER MANUALLY LOWERING THE GEAR THE GREEN SYS HYD INDICATION CAME BACK AND IS READING IN THE MIDDLE OF THE HAT ON THE INDICATION. THE INDICATOR ON THE RESERVOIR WAS GOOD AS WELL ON WALK AROUND. FOUND DAMAGED HYD PRESSURE TRANSMITTER LT WHEEL WELL. REMOVED AND REPLACED HYD PRESSURE TRANSMITTER ASSY PER MM 29-32-13-4. LEAK AND OPS CK GOOD. RESET GRAVITY EXTEND SYS AND STOWED CRANK HANDLE. RETURN TO SERVICE

Part: ENGINE — UNKNOWN (NR 2) · airframe 42,965 hrs · 11,753 cycles

NR 2 ENG DOES NOT RESPOND TO THROTTLE MOVEMENT, ATS LEVER OFF. REPLACED NR 2 EEC PER MM 73-21-01-4-06 AND WAS NO HELP. CHECKED FADEC FAULTS AND HAD NONE. RAN ENGINE WITH NO EPR MODE FAULTS OR COMMAND POINT, ER FAULTS, ALL ENGINE INDICATIONS GOOD. INSTALLED NEW TCC NO HELP REINSTALLED ORIGINAL. CHECKED PB SENSE LINE FOUND OK. FOUND TR SLEEVE POSITION AT 16. 1 PERCENT CHA AND 16.2 PERCENT CH B. ADDED MPN 3M3-212A. REINSTALLED ORIGINAL EEC ADJUSTED LT RVDT PER A310-300 MM 78-31-40-4 ENGINE RUN C/W PER JRH THROTTLE RESPONSE NORMAL.

Part: THRUST REVERSER — INOPERATIVE (NR 2) · airframe 42,534 hrs · 11,522 cycles

NR 2 T/R UNLOCK WHEN POWER ADDED FOR T/O ACN RELEASED FOR SERVICE IAW MEL/CDL: 78-30-01-C THRUST REVERSER IS DEACTIVATED IN FORWARD THRUST POSITION. REMOVED AND REPLACED NR 2 ENG T/R PRSOV AS REQUIRED PER A310-300MM78-31-05-4.OPS CHECK GOOD.

Part: STEERING SYS — MALFUNCTIONED (NLG) · airframe 42,126 hrs · 11,293 cycles

ON TAKEOFF ROLL, AFTER ENG HAD BEEN STABILIZED AT 40 PERCENT N1 AND THEN TAKEOFF POWER APPLIED AIRCRAFT BEGAN TO VEER SHARPLY TO THE LEFT AND COULD NOT BE STRAIGHTEND USING FULL RIGHT RUDDER PEDAL. T/O WAS REJECTED AT APPROX 25 KTS AND AIRCRAFT WAS BROUGHT BACK TO CENTERLINE USING TILLER. ON TAXI BACK TO THE GATE THERE WAS STIFFNESS IN STEERING. PERFORMED INSPECTION CHECK OF NOSE GEAR AND STEERING CONTROL UP TO A310-300 AMM 32-51-00-6, LUBRICATED NOSE GEAR, C/W CABLE TENSION CHECK. CYCLED STEERING USING TILLER AND RUDDER PEDALS USING GREASE PLATES & FOUND NO DEFECTS. PERFORMED TAXI CHECK, OPS CHECK GOOD AT THIS TIME.