N429FE

Part: PRESSURE SWITCH — MALFUNCTIONED (TE FLAP) · airframe 53,224 hrs · 24,332 cycles

ON APPROACH WHEN WE SELECTED, SLATS EXT, GOT ECAM SLATS SYS NR 1 & NR 2 FAULT. CYCLED & SLATS EXTENDED, WHEN SELECTING FLAPS 15, GOT FLAP SYS NR 1 & NR 2 FAULT. CYCLED WITH NO HELP. LANDED WITH 0 FLAPS. CYCLED FLAPS SEVERAL TIMES WITH NO HELP. TROUBLESHOOTING IN PROGRESS. FOUND SFCC'S FAULTING HIGH SPEED PSW & JAM. CHECKED JAM DETECTORS & THEY WERE BOTH POPPED. RAN NR 2 ENG & TRIED FLAP & SLAT OPERATION, ONLY SLATS ARE WORKING, FLAPS JAMMED. R & R SYS 1 & 2 HIGH SPEED PRESS SWITCHES IAW AMM CH 27-54-33-04. RESET JAM DETECTORS IAW AMM CH 27-54-12-04, RAN FLAPS & SLATS THRU MULTIPLE CYCLES WITH NO FAULTS FOUND AT THIS TIME WITH THE ELEC PUMPS ONLY & THEN WITH ENGS RUNNING.

Part: RELAY — BURNED (ANTI-ICE SYS) · airframe 53,029 hrs · 24,192 cycles

FIRST OFFICER`S TAT PROBE, FAULT LIGHT ON AT FL300, ECAM MONITOR. 5 MINS LATER SMELL OF ELEC ORIGIN, NO VISUAL SMOKE, ODOR GONE AFTER LANDING. FOUND DET SENSOR TEMP IN 107 VU PANEL WITH BURN HOLE IN TOP OF RELAY. WHILE CHANGING RELAY DET BASE SCREWS FELL OFF. PARTS NIS INDY IAW AWM 30-31-05. WHILE T/S DET RELAY 73 DA, FOUND RELAY 127 DA EXTREMELY HOT. REPLACED PRECAUTIONARY IAW ASM 30-31-00. COVER PANEL REMAINS OFF LAYING IN AREA OF RELAY PANEL. PULLED THE FOLLOWING BREAKERS FIRST OFFICER`S TAT, ALPHA STAT LT & RT STAT STBY WARN ALL ON 126 VU PANEL. REMOVED BASE & BAD RELAY 73 DA & INSPECTED WIRES & SOCKETS IAW A310-200 ESPM 20-52-12, NO FAULTS FOUND. RECEIVED RELAY 73 DA PN 306ZN01AAWBN & BASE ASSEMBLY PN NSA932844BN, INSTALLED IAW A310-200 ESPM 20-46-50 & CLOSED PANEL 107VU. PERFORMED OPERATION CHECK IAW A310-200 AMM 30-31-00-05, ALL CHECKED NORMAL.

Part: TEE FITTING — CRACKED (FUSELAGE) · airframe 52,786 hrs · 24,027 cycles

CENTER WING REAR SPAR INTERNAL ANGLE LOWER SKIN TEE FITTING LEFT FOUND CRACKED. REPAIRED IAW EA 6-5710-T0303521.

Part: TEE FITTING — CRACKED (FRAME 47) · airframe 52,786 hrs · 24,027 cycles

CENTER WING REAR SPAR INTERNAL ANGLE LOWER SKIN TEE FITTING RT SIDE FOUND CRACKED. REPAIRED IAW EA 6-5710-T0303521.

Part: FITTING — CRACKED (FRAME 45) · airframe 52,777 hrs · 24,025 cycles

FUSELAGE CENTER BOX FRAME 45, LT UPPER FRAME BASE-TO-ARCH JUNCTION FOUND CRACK AT HOLE H22 COMPLIED WITH EA 6-5310-T0303124.

Part: FITTING — CRACKED (FRAME 40) · airframe 52,777 hrs · 24,025 cycles

FRAME 40 LT UPPER CORNER FITTING FOUND CRACKED. COMPLIED WITH EA 6-5710-T0303103.

Part: FITTING — CRACKED (FRAME 44) · airframe 52,777 hrs · 24,025 cycles

FUSELAGE CENTER BOX FRAME 44 RT UPPER FRAME BASE-TO-ARCH JUNCTION FOUND CRACKS AT H5 & H13. R & R THE SUPPORT FITTING IAW SRM 51-40-21 & EA 6-5310-T0303124.

Part: FITTING — CRACKED (FRAME 40) · airframe 52,777 hrs · 24,025 cycles

FRAME 40 RT UPPER CORNER FITTING FOUND CRACKED. COMPLIED WITH EA 6-5710-0303103.

Part: FITTING — CRACKED (FRAME 43) · airframe 52,777 hrs · 24,025 cycles

FUSELAGE CENTER BOX FRAME 43 RT UPPER FRAME BASE-TO-ARCH JUNCTION FOUND CRACK AT HOLE H2. R & R NEW SUPPORT FITTING IAW SRM 51-40-21 & EA 6-5310-T0303124.

Part: FITTING — CRACKED (FRAME 45) · airframe 52,777 hrs · 24,025 cycles

FUSELAGE CENTER BOX FRAME 45 RT UPPER FRAME BASE-TO-ARCH JUNCTION FOUND CRACK AT HOLE H22 COMPLIED WITH EA 6-5310-T0303124.

Part: SUPPORT FITTING — CRACKED (FRAME 44) · airframe 52,777 hrs · 24,025 cycles

FUSELAGE CENTER BOX, FRAME 44 LT UPPER FRAME SUPPORT FITTING FOUND CRACKED. R & R NEW SUPPORT FITTING IAW SRM 51-40-21 & EA 6-5310-T0303124.

Part: FITTING — CRACKED (FRAME 43) · airframe 52,777 hrs · 24,025 cycles

FUSELAGE CENTER BOX FRAME 43, LT UPPER FRAME BASE-TO-ARCH JUNCTION FOUND CRACKED. R & R SUPPORT FITTING SRM 51-40-21 & EA 6-5310-T0303124.

Part: SKIN — CRACKED (ZONE 100) · airframe 52,777 hrs · 24,025 cycles

FUSELAGE SKIN UNDER PICKUP ANGLE AT FRAME 40 LT, FASTER HOLE 14 FOUND CRACKED. REPAIRED IAW EA 6-5310-T0303309.

Part: SEAT TRACK — CORRODED (ZONE 200) · corrosion level 2 · airframe 52,777 hrs · 24,025 cycles

MAIN DECK FRAMES 47-48 -Y953, SEAT TRACK CORRODED. SPLICE REPAIRED SEAT TRACK IAW EA 6-5315-T0303255 & SRM 53-10-16.

Part: FLOOR SUPPORT — CORRODED (ZONE 200) · corrosion level 2 · airframe 52,777 hrs · 24,025 cycles

MAIN DECK FR 12A-14 Y770, FLOOR SUPPORT CORRODED REPLACED THE CORRODED FLOOR SUPPORT IAW SRM 51-40-21.

Part: WARNING LIGHT — FALSE ACTIVATION (HYD SYSTEM) · airframe 52,187 hrs · 23,618 cycles

APPROX 10 MINUTES INTO FLIGHT, ECAM "HYD GREEN RSVR LO LEVEL" QUANTITY INDICATED. TURNED PUMPS OFF IAW ECAM. FOLLOWED QRH PROCEDURES TO EXTEND LANDING GEAR. LANDING UNEVENTFUL. CLEANED WHEEL WELL AND SERVICED GREEN SYS. HYD TO MIDDLE OF THE HAT AMM 12-12-00. OPERATED FLAPS, RAN ENGINES, FLIGHT CONTROLS, RAISED GEAR HANDLE WITH PINS AND NOSE GEAR JACK INSTALLED, STAB TRIM, NO LEAKS. TAXIED WITH NO LEAKS OR QTY DROP. DP INDICATORS ON ENGINE FILTERS NOT TRIPPED. GEAR PINS REMAIN INSTALLED. PERFORMED NORMAL GEAR RETRACT/EXTENSION SEVERAL TIMES IAW AMM 32-31-00-05. FOUND NO LEAKS, BLEED GREEN HYD SYS IAW 29-00-00-04, GREEN RESERVOIR QTY DID NOT DECREASE.

Part: SKIN — CRACKED (ZONE 500) · airframe 51,810 hrs · 23,369 cycles

LT WING FIXED L/E INBD CUT OUT FOR SHUTTER DOOR NR 1 TOP EXTERNAL SKIN CRACKED 1.25" APPROXIMATELY. REPAIRED SKIN IAW SRM 51-40-21 DWGS A57246236, A57246240 AND EA 6-5740.

Part: SKIN — CRACKED (ZONE 100) · corrosion level 3 · airframe 51,028 hrs · 22,860 cycles

EVIDENCE OF FUSELAGE SKIN CRACK UNDER LAV SERVICE DOOR. REPAIRED IAW RDAS ISSUE A AND EA 6-5330-154038 PARTS 1 AND 2.

Part: FITTING — CRACKED (FUSELAGE) · airframe 50,920 hrs · 22,783 cycles

TWO LOWER HOLES WERE FOUND INDICATION AT LT & RT SIDE OF FR43A. REMOVED LT AND RT FRAME FITTINGS. OVERSIZED LT RIB LOWER HOLE TO 0.402" DIA. PERFORMED NDI INSPECTION ON ALL SEPERATED STRUCTURE AND FOUND THE CRACK IS ONLY ON THE FRAME FITTING. FABRICATED CRACKED FITTING PER DRAWING NR A53870037203 AND DRAWING NR A53870037202. INSTALLED THE FRAME FITTING BY FASTENERS IAW SRM 51-40-21. THE REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: ANGLE — CRACKED (FUSLEAGE) · airframe 50,920 hrs · 22,783 cycles

ANGLE FOUND CRACKED. REMOVED ANGLE, OVERSIZED HOLES TO 0.199". PERFORMED NDI INSPECTION ON ALL SEPERATED STRUCTURE AND FOUND CRACK ONLY ON ANGLE. FABRICATED ANGLE PER DRAWING A53812589200. INSTALLED ANGLE IAW SRM 51-40-21. THE REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: TUBE — CRACKED (SMOKE DETECTOR) · airframe 50,920 hrs · 22,783 cycles

MAIN DECK COMPT LT LOWER SIDEWALL AREA FOUND SMOKE DETECTOR SNIFFER TUBE BROKEN AT 2EA PLACES, LOCATION BETWEEN FR 40/41 AND FR 45. IAW AMM 26-19-09 REOVED THE SNIFFER TUBE AT FR 40/41 LT. COMPLIED WITH E.A. 6-2610-149004. REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100.

Part: FLOORBEAM — CRACKED (ZONE 200) · airframe 50,920 hrs · 22,783 cycles

CENTER MAIN DECK COMPARTMENT FLOOR AREA BETWEEN R2 AND R3 SEAT TRACK FOUND 5 EA CROSSBEAM ASSY CRACKED AREA FROM FR40/411 TO FR45/-Y450 AND -Y953. R & R CENTER MAIN DECK SOMPARTMENT FR40 / 41 TO FR45 / -Y953 5 EA CROSS BEAMS IAW AMM20-21-12. THE REPAIR CLASSIFIED AS MINOR IAW GMM 6-2-100.

Part: PANEL — DEBONDED (FUSELAGE) · airframe 50,920 hrs · 22,783 cycles

1EA DISBONDED ARE WAS FOUND AT LT SIDE INTERIOR ARE (11" X 17") OF 324AT PANEL. ( 1.9" FROM LEADING EDGE AND 1.5" FROM BOTTOM EDGE.) CLEANED & EVALUATED THE DISBONDED AREA 11" X 17". REINFORCED REPAIR THE AREA WITH THE RESIN COMPOUND AND FIBERGLASS CLOTH IAW SRM 55-32-00.

Part: FLOOR PANEL — CRACKED (CARGO BAY) · airframe 50,920 hrs · 22,783 cycles

CARGO COMPARTMENT 162HF FLOOR PANEL GOT IMPACT DAMAGED. FABRICATED A NEW FLOOR PANEL FOR REPLACING IAW DRAWING 17A53279962 & SRM 53-10-20 AND MCG IRM 9701 REVISION G.

Part: PANEL — DEBONDED (BS 380-576) · airframe 50,920 hrs · 22,783 cycles

1EA DISBONDED AREA (2.5" X 1.8") WAS FOUND AT 322BL PANEL L/H SIDE. (6" FROM LEADING EDGE, 27" FROM BOTTOM EDGE.) CLEANED & EVALUATED THE DIMENSION OF THE DISBONDED AREA 9" X 8.5". REINFORCED REPAIR THE AREA WITH THE RESIN COMPOUND AND FIBERGLASS CLOTH REFER TO A310 SRM 55-32-00.

Part: PANEL — DEBONDED (VERTICAL STAB) · airframe 50,920 hrs · 22,783 cycles

1EA DISBONDED AREA (2" X 3") WAS FOUND AT 321AL PANEL R/H SIDE. ( 14" FROM LEADING EDGE AND 20" FROM BOTTOM EDGE.) CLEANED & EVALUATED THE DISBONDED AREA 3"X2.5". REINFORCED REPAIR THE AREA WITH THE RESIN COMPOUND AND FIBERGLASS CLOTH REFER TO A310 SRM 55-32-00.

Part: RIB — CRACKED (FUSELAGE) · airframe 50,920 hrs · 22,783 cycles

REMOVE HINGE SUPPORT RIB, FOUND ANOTHER SIDE RIB MATING SURFACE GOT CRACK AT RIB 20, 19 INCH. REMOVED THE CRACKED BOX RIB IAW SRM 51-40-21. FABRICATED RIB MATERIAL 7075-T7651 IAW DWG A57247040. TRANSFERED DRILL THE FASTENER'S HOLE AND ASSEMBLED RIB IAW SRM 51-40-21 AND 51-72-10. 4. WET INSTALLED RIB.

Part: DUCT — CHAFED (THRUST REVERSER) · airframe 50,920 hrs · 22,783 cycles

ENG 2, LT T/R COWL INNER DUCT AFT EDGE GOT CHAFING ATTACH TO CORE COWL AREA UPPER SIDE.

Part: RIB — CRACKED (LT WING) · airframe 50,920 hrs · 22,783 cycles

LT WING T/E BOX RIB LOWER CORNER BOTH SIDE GOT CRACKS BETWEEN NR 5 AND NR 6 SPOILER. REMOVED THE CRACKED BOX RIBS IAW SRM 51-40-21. REPLACED THE RIBS WITH NEW PARTS BY FASTENERS IAW SRM 51-72-10 AND 51-40-21. THE REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100.

Part: SKIN — CORRODED (FUSELAGE) · airframe 50,920 hrs · 22,783 cycles

FWD CARGO COMPARTMENT BILGE SKIN AREA AROUND MAIN HOLE SKIN GOT CORROSION BETWEEN FR38.1 AND FR38.2 POSITION. REMOVED THE CORROSION AREA. MEASURED THE DIMENSION 2.5"L X 2.2"W X 0.078"D OVER LIMIT REF. TO SRM 53-14-12. REPAIRED THE DAMAGE AREA WITH DOUBLER AND FASTENER REF. TO SRM 53-14-12.

Part: RIB — CRACKED (RT WING) · airframe 50,920 hrs · 22,783 cycles

RIGHT WING NR 5 SPOILER O/B HINGE SUPPORT RIB CRACKED. REMOVED CRACKED BOX RIB IAW SRM 51-40-21. FABRICATED RIB IAW DWG A57247040. TRANSFERRED HOLES AND ASSEMBLED RIB IAW SRM 51-40-21. WET INSTALLED SUPPORT RIB IAW A310 SRM 51-40-21 AND 51-72-10. THE REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100.

Part: WEDGE — DAMAGED (RT WING TE FLAP) · airframe 50,920 hrs · 22,783 cycles

RT WING T/E INBD FLAP T/E DAMAGED ABOUT 5" X 20" BETWEEN RIB 18 AND 21. REMOVED FLAP T/E WEDGE. REPLACED WITH NEW T/E WEDGE PER E.A. 6-5750-149005. 3. PAINT TOUCHED-UP. REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100.

Part: SEAT TRACK — CHAFED (FUSELAGE) · airframe 50,920 hrs · 22,783 cycles

AFT MAIN DECK COMPARTMENT FOUND L4 LONGITUDINAL SEAT TRACK FLANGE GOT A EXCESS CHAFED MARK LOCATION AT FR79 AND Y1447.8 POSITION. REMOVED THE DAMAGE SEAT TRACK. FABRICATED NEW SEAT TRACK REF. TO DRAWING NR A53279232. INSTALLED NEW TRACK WITH FASTENER REF. TO SRM 51-40-21.

Part: FITTING — CRACKED (SILL) · airframe 50,920 hrs · 22,783 cycles

FWD CARGO COMPARTMENT DOOR SILL AREA FITTING CRACKED ABOVE NR 6 LATCH FITTING. REMOVED THE CRACKED FITTING. INSTALLED THE NEW FITTING FOR REPLACING IAW SRM 51-72-10.

Part: SLAT SYSTEM — FAILED · airframe 49,530 hrs · 21,850 cycles

2 ND REPEAT: ON APPROACH SLATS WOULD NOT EXTEND (STUCK), RAN QRH AND LANDED WITH 0/40 SLATS FLAPS W/OUT INCIDENT. LANDED AT ABOUT 140 KIAS. SFCC'S 1 & 2 INDICATE JAM. NO OTHER FAULTS. EVIDENCE OF LEAK AT INBD SLAT JACKSCREW. EXTENDED SLATS WITHOUT FAULTS AND FOUND 5606 LEAKING FROM LT WING INBD SLAT, INBD JACKSCREW TRANSMISSION NR 2. CHECKED NR 1 LT JACKSCREW SERVICING PER AMM 12-13-27, NO FLUID ADDED. SUSPECT RESIDUAL FLUID FROM PREVIOUS SERVICING. FLUSHING. CHECKED SYSTEM TQ LIMITERS, FOUND RT SYS TRIPPED, LT SYS NORMAL. CHECKED ALL LT & RT JACKSCREW LOCKOUT INDICATORS. FOUND LT 2, 3, 4, 5, 6 INDICATOR STRIPPED & RT 1, 2, 5, 6 INDICATORS TRIPPED. RESET ALL TRIPPED JACKSCREW INDICATORS & RT TQ LIMITER. OPERATED SYSTEM SEVERAL TIMES WITH ENGINE DRIVEN PUMPS. ALL CHECKED NORMAL, NO FAULTS ON SFCC'S, NO FAULTS ON SYS TQ LIMITERS & NO FAULTS SET ON JACKSCREW LOCK OUT INDICATOR. RESET C/B'S AND CLOSED L/E JACKSCREW ACCESS PANELS. REPLACED RT NR 1, RT NR 3, LT NR 2, LT NR 3, & LT NR 4 SLAT JACKSCREWS REF MM 27-84-22-4 AND OPS CHECK GOOD REF MM 27-84-00 PB 501. (THIS SDR IS FOR L2 POSITION ONLY)

Part: SLAT SYSTEM — FAILED (ZONE 500) · airframe 49,530 hrs · 21,850 cycles

2 ND REPEAT: ON APPROACH SLATS WOULD NOT EXTEND (STUCK), RAN QRH AND LANDED WITH 0/40 SLATS FLAPS W/OUT INCIDENT. LANDED AT ABOUT 140 KIAS. SFCC'S 1 & 2 INDICATE JAM. NO OTHER FAULTS. EVIDENCE OF LEAK AT INBD SLAT JACKSCREW. EXTENDED SLATS WITHOUT FAULTS AND FOUND 5606 LEAKING FROM LT WING INBD SLAT, INBD JACKSCREW TRANSMISSION NR 2. CHECKED NR 1 LT JACKSCREW SERVICING PER AMM 12-13-27, NO FLUID ADDED. SUSPECT RESIDUAL FLUID FROM PREVIOUS SERVICING. FLUSHING. CHECKED SYSTEM TQ LIMITERS, FOUND RT SYS TRIPPED, LT SYS NORMAL. CHECKED ALL LT & RT JACKSCREW LOCKOUT INDICATORS. FOUND LT 2, 3, 4, 5, 6 INDICATOR STRIPPED & RT 1, 2, 5, 6 INDICATORS TRIPPED. RESET ALL TRIPPED JACKSCREW INDICATORS & RT TQ LIMITER. OPERATED SYSTEM SEVERAL TIMES WITH ENGINE DRIVEN PUMPS. ALL CHECKED NORMAL, NO FAULTS ON SFCC'S, NO FAULTS ON SYS TQ LIMITERS & NO FAULTS SET ON JACKSCREW LOCK OUT INDICATOR. RESET C/B'S AND CLOSED L/E JACKSCREW ACCESS PANELS. REPLACED RT NR 1, RT NR 3, LT NR 2, LT NR 3, & LT NR 4 SLAT JACKSCREWS REF MM 27-84-22-4 AND OPS CHECK GOOD REF MM 27-84-00 PB 501. (THIS SDR IS FOR L3 POSITION ONLY)

Part: LIMITER — FAILED (SLAT SYSTEM) · airframe 49,530 hrs · 21,850 cycles

2 ND REPEAT: ON APPROACH SLATS WOULD NOT EXTEND (STUCK), RAN QRH AND LANDED WITH 0/40 SLATS FLAPS W/OUT INCIDENT. LANDED AT ABOUT 140 KIAS. SFCC'S 1 & 2 INDICATE JAM. NO OTHER FAULTS. EVIDENCE OF LEAK AT INBD SLAT JACKSCREW. EXTENDED SLATS WITHOUT FAULTS AND FOUND 5606 LEAKING FROM LT WING INBD SLAT, INBD JACKSCREW TRANSMISSION NR 2. CHECKED NR 1 LT JACKSCREW SERVICING PER AMM 12-13-27, NO FLUID ADDED. SUSPECT RESIDUAL FLUID FROM PREVIOUS SERVICING. FLUSHING. CHECKED SYSTEM TQ LIMITERS, FOUND RT SYS TRIPPED, LT SYS NORMAL. CHECKED ALL LT & RT JACKSCREW LOCKOUT INDICATORS. FOUND LT 2, 3, 4, 5, 6 INDICATOR STRIPPED & RT 1, 2, 5, 6 INDICATORS TRIPPED. RESET ALL TRIPPED JACKSCREW INDICATORS & RT TQ LIMITER. OPERATED SYSTEM SEVERAL TIMES WITH ENGINE DRIVEN PUMPS. ALL CHECKED NORMAL, NO FAULTS ON SFCC'S, NO FAULTS ON SYS TQ LIMITERS & NO FAULTS SET ON JACKSCREW LOCK OUT INDICATOR. RESET C/B'S AND CLOSED L/E JACKSCREW ACCESS PANELS. REPLACED RT NR 1, RT NR 3, LT NR 2, LT NR 3, & LT NR 4 SLAT JACKSCREWS REF MM 27-84-22-4 AND OPS CHECK GOOD REF MM 27-84-00 PB 501.

Part: SLAT SYSTEM — STUCK · airframe 49,530 hrs · 21,850 cycles

ON APPROACH, SLATS WOULD NOT EXTEND (STUCK), RAN QRH AND LANDED WITH 0/40 SLATS FLAPS W/OUT INCIDENT. LANDED AT ABOUT 140 KIAS. MOCC UPDATE SFCC'S 1 AND 2 INDICATE JAM. NO OTHER FAULTS. EVIDENCE OF LEAK AT INBD SLAT JACKSCREW. EXTENDED SLATS WITHOUT FAULTS AND FOUND 5606 LEAKING FROM LT WING INBD SLAT, INBD JACKSCREW TRANSMISSION NR 2. CHECKED NR 1 LT JACKSCREW SERVICING IAW AMM12-13-27, NO FLUID ADDED. SUSPECT RESIDUAL FLUID FROM PREVIOUS SERVICING/FLUSHING. CHECKED SYS TQ LIMITERS, FOUND RT SYS TRIPPED, LT SYS NORMAL. CHECKED ALL LT AND RT JACKSCREW LOCKOUT INDICATORS. FOUND LT 2,3,4,5,6 INDICATORS TRIPPED AND RT 1,2,5,6 INDICATORS TRIPPED. RESET ALL TRIPPED JACKSCREW INDICATORS AND RT TQ LIMITER. OPERATED SYS SEVERAL TIMES WITH ENG DRIVEN PUMPS. ALL CHECKED NORMAL, NO FAULTS ON SFCC'S, NO FAULTS ON SYS TQ LIMITERS AND NO FAULTS SET ON JACKSCREW LOCK OUT INDICATOR. RESET C/B'S AND CLOSED L/E JACKSCREW ACCESS PANELS. REPLACED RT NR1, RT NR3, LT NR2, LT NR3, AND LT NR4 SLAT JACKSCREWS REF MM 27-84-22-4 AND OPS CHECK GOOD REF MM 27-84-00 PB 501.

Part: SLAT SYSTEM — STUCK (LE) · airframe 49,530 hrs · 21,850 cycles

ON APPROACH, SLATS WOULD NOT EXTEND (STUCK), RAN QRH AND LANDED WITH 0/40 SLATS FLAPS W/OUT INCIDENT. LANDED AT ABOUT 140 KIAS. SFCC'S 1 AND 2 INDICATE JAM. NO OTHER FAULTS. EVIDENCE OF LEAK AT INBD SLAT JACKSCREW. EXTENDED SLATS WITHOUT FAULTS AND FOUND 5606 LEAKING FROM LT WING INBD SLAT, INBD JACKSCREW TRANSMISSION NR 2. CHECKED NR1 LT JACKSCREW SERVICING IAW AMM12-13-27, NO FLUID ADDED. SUSPECT RESIDUAL FLUID FROM PREVIOUS SERVICING/FLUSHING. CHECKED SYS TQ LIMITERS, FOUND RT SYS TRIPPED, LT SYS NORMAL. CHECKED ALL LT AND RT JACKSCREW LOCKOUT INDICATORS. FOUND LT 2,3,4,5,6 INDICATORS TRIPPED AND RT 1,2,5,6 INDICATORS TRIPPED. RESET ALL TRIPPED JACKSCREW INDICATORS AND RT TQ LIMITER. OPERATED SYS SEVERAL TIMES WITH ENG DRIVEN PUMPS. ALL CHECKED NORMAL, NO FAULTS ON SFCC'S, NO FAULTS ON SYS TQ LIMITERS AND NO FAULTS SET ON JACKSCREW LOCK OUT INDICATOR. RESET C/B'S AND CLOSED L/E JACKSCREW ACCESS PANELS. REPLACED RT NR1, RT NR3, LT NR2, LT NR3, AND LT NR4 SLAT JACKSCREWS REF MM 27-84-22-4 AND OPS CHECK GOOD REF MM 27-84-00 PB 501. (THIS SDR IS FOR L4 POSITION ONLY)

Part: SLAT SYSTEM — FAULTED · airframe 49,530 hrs · 21,850 cycles

SLATS FAULTED SYSTEMS 1 & 2 ON APPROACH CYCLED PER QRH NO HELP RAN QRH AND LANDED SLATS 0 FLAPS 40 T/S PER TSM 27-80-00 NO HARD FAULTS NOTED. RAN NR 1 & 2 ENGINES PER JRH CH 5. CYCLED FLAPS & SLATS SEVERAL TIMES. ALL INDICATIONS NORMAL. NO FAULTS NOTED ON SFCC'S NR 1 & 2. NO 90 DAY HISTORY. ACFT OK TO CONTINUE FOR SERVICE.

Part: JACKSCREW — LACK OF LUBE (SLATS) · airframe 49,530 hrs · 21,850 cycles

SLATS SYS 1 & 2 FAULTED ON APPROACH, RECYCLED, LANDED SLATS 0/FLAPS 40. NO FAULTS ON SFCC NR 1 OR 2, RAN END ENGINE'S OPS. CHK SLATS 0 TO 30 THREE TIMES NO FAULTS NOTED. FOUND BOTH SYSTEM TORQUE LIMITERS ACTIVATED. RESET SAME. IAW TSM 27-80-02 BEGAN CHECKING SLATS JACKSCREW CLAW STOPS, LT WING 3 THRU 6 GOOD IAW MM 27-80-00-5. STILL IN WORK. CHECKED SCREW JACKS 1, 2, 3, & 4 ON LT AND RT WINGS FOR PROPER LUBRICATION. FOUND JACKSCREWS 1 & 3 ON RT WING CONTAMINATED WITH WATER. FOUND JACKSCREWS 2 & 3 ON LT WING CONTAMINATED WITH WATER AND JACKSCREW 4 ON LT WING WAS LOW ON LUBRICATION. FLUSHED AND SERVICED JACKSCREWS 1, 2, 3, 4 ON BOTH WINGS. REF 12-13-27. SLATS OPERATED NORMAL.

Part: COALESCER BAG — DIRTY (AC BAY) · airframe 49,186 hrs · 21,646 cycles

FAINT SMELL OF ELECTRICAL FUMES. TRANSIENT THEN DISSIPATED. RAN PACKS WITH APU AIR AND NOTICED SLIGHT INDUSTRIAL KIND OF SMELL. CONTINUING T/S. REMOVED BOTH COALESCER BAGS AND FOUND VERY DIRTY. REPLACED PER MM 21-51-16-3. OPERATED BOTH ENGINES PER JRH (AMT 204852). NO SMELLS NOTICED.

Part: HEATER — SMOKE (COCKPIT WINDOW) · airframe 49,186 hrs · 21,646 cycles

SMOKE/FUMES FROM BEHIND F/O SLIDING WINDOW. SECURED R WINDOW HEAT. SMOKE/FUMES STOPPED. FOUND WIRES AT COPILOTS SLIDING WINDOW BURNED AND MELTED WHERE WIRES ENTER BETWEEN THE WINDOW AND THE WINDOW MECHANISM COVER. PARTS REQUIRED ARE CLAMP P/N NSA5516-09V CPN 0114314 AND CORD P/N E0385HH CPN 5610228 BOTH PER IPC 56-12-11-04.

Part: UPLOCK — FAILED (NLG DOOR) · airframe 48,949 hrs · 21,492 cycles

AFTER TAKE OFF NOSE GEAR DOOR AMBER LIGHT REMAINED ILLUMINATED. NOSE GEAR DOOR NOT CLOSED ECAM. HEAVY BUFFET AND VIBRATION. SPEED NEVER EXCEEDED 210 KTS. RETURN TO MKE. UPLOCK FOUND BROKEN SPRINGS IN NOSE GEAR DOOR UPLOCK ASSY, WHICH WOULD NOT ALLOW DOOR TO FULLY CLOSE. REQUIRES DOOR UPLOCK ASSY. REMOVED AND INSTALLED RT NOSE GEAR DOOR UPLOCK ASSY, REF MM 32-31-14-4. REPRESSURIZED GREEN HYDRAULIC SYSTEM. OPS AND LEAK CHECK NORMAL, REF MM 32-31-00-5 AND 32-33-00-5. OK TO CONTINUE.

Part: FILTER — DIRTY (NR 2 ENG FUEL) · airframe 48,885 hrs · 21,437 cycles

NR 2 ENG FUEL FILTER CLOG LIGHT & ECAM INDICATION ON CLIMB-OUT PASSING 2000 FT. POWER REDUCED & ECAM INDICATIONS WENT AWAY. TRIED ADVANCING THROTTLE AGAIN & ECAM INDICATIONS BACK ON. REMOVED & INSPECTED NR 2 ENGINE FUEL FILTER FOR CONTAMINATION. FOUND SMALL AMOUNT OF FIBER MATERIAL IN FILTER, WITH NO METAL NOTED. REPLACED FUEL FILTER & RAN NR 2 ENG AT IDLE. REMOVED FILTER AGAIN & INSPECTED. FILTER CLEAN. INSTALLED NEW FILTER & LEAK CHECKED. REMOVED NR 2 ENG FUEL FILTER, INSPECTED FILTER FOR CONTAMINATION, NONE FOUND. INSTALLED NEW FUEL FILTER IAW AMM 73-12-03-2. RAN NR 2 ENG IAW JRH, FUEL CLOG LIGHT DID NOT ILLUMINATE DURING ENG RUN, OPS & LEAK CHKD GOOD. OK FOR SERVICE.

Part: DOOR FRAME — CORRODED (ZONE 200) · airframe 48,830 hrs · 21,399 cycles

L1 DOOR LT UPPER FWD FAIL/SAFE RING RADIUS BOTH LAYERS SHOW EXFOLIATION CORROSION INDICATIONS AFTER EDDY CURRENT INSPECTION, UNABLE TO VERIFY ULTRASONICALLY 1 SQ INCH AREA. REMOVED LEVEL 1 CORROSION AND REPAIRED DAMAGED AREA AT L-1 DOOR UPPER FWD CORNER FAIL/SAFE RING IAW FEDEX EA 6-5310-124179, RELEASE DATE 20 NOVEMBER, 2008.

Part: WEB — CORRODED (ZONE 100) · airframe 48,830 hrs · 21,399 cycles

FRAME 1 FWD FACE AT RADOME ACCESS HAS 4 EA AREAS OF SKIN CORROSION, APPROX 7 SQ INCHES REMOVED LEVEL 1 CORROSION AND INSTALLED REPAIR DOUBLER ON WEB FLANGE AT FRAME 1 IAW FEDEX EA 6-5310-124171, RELEASE DATE 12 NOVEMBER, 2008.

Part: FITTING — GOUGED (ZONE 100) · airframe 48,830 hrs · 21,399 cycles

AFT CARGO DOOR NR 2 DOOR LOCK FITTING HAS 1 GOUGE ON OTBD MOUNT AND 2 GOUGES ON INBD MOUNT REMOVED AND REPLACED AFT CARGO DOOR FITTING AT FR 60A IAW A310 SRM 51-40-21.

Part: SEAT TRACK — DAMAGED (ZONE 200) · airframe 48,830 hrs · 21,399 cycles

MAIN DECK NR 2 RT SEAT TRACK AT FR 46 HAS 2 ELONGATED SCALLOPS. REMOVED DAMAGED SECTION OF SEAT TRACK AND INSTALLED SEAT TRACK SPLICE REPAIR BETWEEN FR 45 AND FR 54 AT TRACK NR 2 RT IAW A310 SRM 53-10-16, FIG 202.

Part: ELECTRONIC UNIT — INOPERATIVE (MLG) · airframe 47,755 hrs · 20,812 cycles

LANDING GEAR WOULD NOT RETRACT ON EITHER SYSTEM ATTEMPTED TO INTERROGATE THE PROXIMITY ELECTRONIC UNIT. UNIT WOULD NOT TEST NOT EVEN LIGHT TEST. REMOVED AND REPLACED PROX ELEC UNIT IAW 32-31-71-4, CHECKS GOOD. MOCC REQUESTS ALT LDG GEAR RELAY TEST. R/I. PREMATURE REMOVAL/INSTALLATION OFF MFG 8-371-01A. PERFORMED FUNCTION TEST IAW M/M 32-31-00-5, STEP 3(D)(5). TEST CHECKS GOOD. PERFORMED FUNCTION TEST IAW M/M 32-31-00-5, STEP 3(D)(5). TEST CHECKS GOOD. REMOVED AND REPLACED LT MLG PITCH DAMPER PER AMM.

Part: THERMOCOUPLE — MALFUNCTIONED (NR 2 EGT) · airframe 47,710 hrs · 20,780 cycles

DURING CLIMB, NR 2 EGT (POINTER/DIGITAL) WERE FLUCTUATING +/- 50C. ALL OTHER ENGINE PARMS NML. NO YAW NOTED. PULL NR 2 THROTTLE BACK TO ABOUT 10 PERCENT, NO CHANGE. HIGHEST EGT WAS APPROX 860C. AFTER ABOUT 10 MINS EGT STAB AT ABOUT 800C AND NML REST OF FLIGHT. FLUX STARTED AGAIN AFTER LNDG. ON GND FLUX WAS ABOUT +/ - 10C. AGAIN, REMOVED AND REPLACED NR 2 ENG EGT IND PRECAUT REF AMM 77-21-21-4. RAN ENG PER JRH AT VARIOUS LOW POWER SETTINGS FOR APPROX 15 MINS. NO FLUCTUATION NOTED. FOUND WIRE HARNESS J3 FWD OF J BOX THAT UPPER AND LOWER T/C HARNESSES CONNECT HAS VISUAL DMG AND WHEN SHOOK GAVE FLUX TO EGT IND. REMOVED AND REPLACED FWD THERMOCOUPLE CABLE IAW MM 77-21-02-4-04.

Part: A/C PACK — ODOR (NR 1) · airframe 47,693 hrs · 20,767 cycles

PDIS - POWER WAS COMING UP ON TAKEOFF ROLL STARTED SMELLING STRONG ODOR WHICH WAS GETTING STRONGER. ABORTED TAKEOFF AT APPROX 80-90 KIAS- ODOR BEGAN TO DISSIPATE AS SOON AS POWER CAME BACK. THERE WERE NO ABNORMAL INDICATIONS OR ECAM WARNING. WHILE TAXIING BACK IN AS POWER WAS ADDED FOR TAXI THE ODOR STARTS AGAIN, TRIED TURNING OFF NR 1 PACK ODOR GOES AWAY. REMOVED AND REPLACED COALESCER BAGS ON PACKS 1 AND 2 RAN PACKS WITH APU SUPPLY NO ODOR NOTICED REF A310AMM 21-51-16-3. A/C OK FOR SERVICE, TSI 2150-8766. C/W THE PACK DUCT CLEANING STEP PER THE AMM 21-51-00-3, NO DEFECTS FOUND.

Part: MECHANISM — DIRTY (MLG) · airframe 47,149 hrs · 20,421 cycles

RAISING GEAR ON T/O NOSE GEAR DOOR LIGHT REMAINED ON. ILLUMINATED ON BOTH SYS AS SPEED INCREASED TO 200 KNOTS, NOISE AND VIB WAS FELT FROM THE NOSE GEAR. NOISE AND VIB REMAINED UNTIL GEAR WAS LOWERED AGAIN, AND THEN THE LIGHT WENT OUT. FOUND FWD LEFT GEAR DOOR MECHANISMS STICKY AND DRY. CLEANED AND LUBED AND CHECKED RIGGING. OPS CHECKED REF M/M 32-31-00-5 AND 32-00-00-5. OPS CHECKED GOOD AND RESTORED A/C TO NORMAL CONFIG AND IS OK FOR SERVICE.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 46,248 hrs · 19,985 cycles

MDCC AT FR 12 TO 14 HAS CORROSION AROUND SCREW HOLES TOP AND BOTTOM REF N00373. REPLACED FLOOR SUPPORT IAW A310-200 SRM 51-40-21.

Part: STRUCTURE — CORRODED (FUSELAGE) · airframe 46,248 hrs · 19,985 cycles

MDCC AT FR 13 TO 14 LT YB HAS CORROSION AROUND FASTENER HOLES TOP AND BOTTOM, SURFACE REF N00390. REMOVED CORROSION AND FOUND TO BE WITHIN LIMITS IAW A310-200 SRM 53-10-00.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 46,248 hrs · 19,985 cycles

FOUND FRAME 19 TRACK 4 RT HAS CORROSION IN TRACK. REMOVED AND REPLACED SEAT TRACK A310-200 SRM 51-40-21 AND 51-72-10.

Part: RIB — CORRODED (LT PYLON) · airframe 46,248 hrs · 19,985 cycles

LT PYLON IB SIDE RIB 16A HAS CORROSION AROUND FAST HOLES REF N00174. REMOVED CORROSION ON RIB 16A GUSSET IAW A310 SRM 51-72-10 FOUND TO BE OUT OF LIMITS. REPLACED RIB 16A GUSSET IAW A310 SRM 51-40-21.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 46,248 hrs · 19,985 cycles

MDCC AT FS 13B LT YA FLOOR BOARD SUPPORT HAS CORR AROUND FAST HOLE TOP AND BOTTOM SURFACE REF N00389. REMOVED CORROSION IAW A310 SRM 51-74-10. FOUND TO BE WITHIN LIMITS IAW A310 SRM 53-10-00, FIG 102 TABLE 102.

Part: CARGO TRACK — CORRODED (FUSELAGE) · airframe 46,248 hrs · 19,985 cycles

MDCC AT FS 11A TO 14 LT YD HAS CORROSION ON TOP AND BOTTOM SURFACE AROUND FAST HOLES REF N00397. REMOVED CORROSION IAW A310 SRM 51-74-10 FOUND TO BE WITHIN LIMITS IAW A310 SRM 53-10-00 FIG 102 TABLE 102.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 46,248 hrs · 19,985 cycles

MDCC FS 14 TO 14B AT YD FLOOR SUPPORT HAS CORROSION TOP AND BOTTOM SURFACE REF N00385. REMOVED AND REPLACED FLOOR SUPPORT IAW A310 SRM 51-40-00.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 46,248 hrs · 19,985 cycles

MDCC FS 19 LT TRACK NR 4 HAS CORROSION INSIDE AND OUTSIDE OF TRACK REF N00201. REMOVED AND REPLACED SEAT TRACK AT FS 19 IAW A310 SRM 51-72-10.

Part: RIB — CORRODED (HORIZ STAB) · airframe 46,248 hrs · 19,985 cycles

LT HORIZ STAB TE RIB AND WEBS IB OF SERVO ACTUATORS, UPPER SURFACE HAVE CORROSION AROUND FASTENER HOLES REF N00292. REMOVED CORROSION IAW A310 SRM 51-74-10, FOUND TO BE WITHIN LIMITS IAW A310 SRM 55-10-00.

Part: WINDSHIELD — CRACKED (COCKPIT) · airframe 46,233 hrs · 19,975 cycles

DURING CLIMBOUT AT 12000 FT ECAM INDICATED -R WINDOW HEAT- FAULT LIGHT RIGHT AFTER FIRST OFFICERS FRONT WINDSHIELD SHATTERED. SELECTED POWER OFF TO R WINDOW HEAT. NO FURTHER PROBLEMS. RETURNED TO ATL. REMOVED AND REPLACED FIRST OFFICERS WINDSHIELD IAW MM 56-11-11 OPS CHECK NORMAL. REMOVED AND REPLACED WINDOW HEAT CONTROLLER IAW MM 30-42-11-4 OPS CHECKED NORMAL. REMOVED AND REPLACED WINDOW HEATING PROTECTION UNIT IAW MM 30-42-51-4, OPS CHECKED GOOD PER ADJUSTMENT/TEST MM 30-42-00-5.

Part: JAM-NUT — LOOSE (MLG WW) · airframe 46,233 hrs · 19,975 cycles

FL 350 OBSERVED GREEN HYD SYS QUANTITY DECREASING. SHORTLY THEREAFTER ECAM TRIGGERED AND QUANTITY DROPPED TO -RED DOT-. FOLLOWED ECAM & QRH. MANUALLY EXTENDED GEAR ON FINAL AND GREEN HYD SYS QUANTITY RETURNED TO TOP HAT. UNEVENTFUL LANDING AND TOW-IN TO GATE. SERVICED GREEN SYSTEM AND FOUND LEAK IN MAIN GEAR WHEEL WELL AT THE LANDING GEAR SELECTOR VALVE. FOUND ONE OF THE LANDING GEAR SELECTOR VALVES HYDRAULIC UNION'S JAM NUT BACKED OFF AND THE UNION LOOSE. REPACKED UNION AND REINSTALLED. PRESSURIZED GREEN SYSTEM, NO LEAKS NOTED.

Part: BLOCK — ICED (FLAPS) · airframe 45,563 hrs · 19,641 cycles

DURING FLAP RETRACTION RECEIVED ECAM WARNING FLAP 2 FAULT, FLAP VANE JAM, FLAPS RETRACTION LIMITED, THIS ALL OCCURRED WHEN FLAP HANDLE WAS MOVED FROM 15/0 TO 0/0. FLAPS INDICATED UP, WITH NO VIBRATIONS IN FLIGHT CONTROLS. REMOVED AND REPLACED RT INBD FLAP, RT INBD FLAP VANE BUFFER IAW AMM 27-56-15-4. INSPECTED FLAP VANE AND FOUND AN EXCESSIVE AMOUNT OF ICE BUILT UP ON THE VANE FITTINGS. THAWED FLAP AND VANE, OP'S CK GOOD. ALL FAULTS CLEARED. NO BINDING OR JAMMING NOTED ON FLAP VANE.

Part: SENSOR — FAILED (T2) · airframe 43,877 hrs · 18,736 cycles

429 77-15 0006235 30JUL04 IAH CLOSE R THREE TIMES DURING CLIMB NR2 ENG, SURGED A/C YAWED TO LT N1 CLIMB LIMIT EXCEEDED (ECAM) CL N' 100 PERCENT SURGE TO 115 PERCENT A/THR TRIPPED OFF LEVEL AT FL 290 CRUISE. ENG. N1 SURGE CR N1 91 PERCENT SURGED TO 105 PERCENT WITH A/C YAW SEVERAL TIME IN CRU. N2 EGT NORMAL. REPLACED T2 SENSOR, PERFORMED PULL TEST OF VSV FEEDBACK CABLE REF-73-21-01-5-B AND FOUND CABLE BINDING REPLACED SAME.

Part: HINGE — CRACKED (NLG DOOR) · airframe 42,567 hrs · 18,008 cycles

ON GEAR RETRACTION AFTER T/O NOSE GEAR DOOR AMBER LIGHT ON, WITH VIBRATION IN THE AREA BEHIND COCKPIT DOOR. WHEN GEAR EXTENDED FOR LANDING THE NOSE GEAR WAS ON. DID MANUAL GEAR EXTENSION. ALL GEAR GREEN LIGHTS ON. REMOVED AND REPLACED R/H NOSE GEAR DOOR ACTUATOR FITTING, DOOR ACTUATOR & DOOR SEQUENCE VALVE. REF EA. 6-5300-71217. A310 MM 32-31-18 & 32-31-16, DOOR RIG AND OPS CHECK NORMAL. PERFORMED GEAR RETRACTION TEST REF 32-31-00-5 OPS CHECK NORMAL.

Part: WIRE HARNESS — DAMAGED (RIGHT ECAM) · airframe 42,546 hrs · 17,993 cycles

ON LANDING STBY PROBE HEAT, PILOTS RIGHT ECAM DISPLAY, PITCH TRIM NR 2, YAW DAMP NR 2, & ATS NR 2 ALL FAILED AT ONCE. ALSO IRU'S WENT TO INDEPENDENT OPS. ENG NR 2 N2 CB POPPED. FACT 25APR03 19:09 RNO U C/W E.A. 6-2400-70271 THE R/H ECAM WIRE WAS CAPPED AND TAPPED AND WILL BE DEFERRED UNDER A SEPARATE WRI. ON INSPECTION OF WIRE BUNDLE, THE DAMAGED AREA WAS NOT IN CONTACT WITH ANY STUCTURE/CHAFFING POINT BUT WAS NEAR TWO VERY TIGHT TYWRAPS. ALSO LOCATED IN A BEND OF THE WIRE BUNDLE. THE DAMAGED WIRES WERE ON THE OUTSIDE OF THE WIRE BUNDLE AND TURN RADIUS.

Part: PITOT LINE — LOOSE (NR 2 ADC)

TWO ADC INOP F/O AIRSPEED AND ALTITUDE ERRONEOUS. SECURED NR 2 ADC PITOT LINE AT ADC PER AMM 34-10-00-501 PG 501. GROUND TEST GOOD.

Part: OUTFLOW VALVE — FAILED (NR 2) · airframe 39,650 hrs · 16,433 cycles

00-355 UNABLE TO PRESSURIZE AC. AFT TO OUTFLOW VALVE AFT FAULTED AND REG 2 FAULTED. R&R VALV PER TSM 21-31-12. OPS CK NORMAL. OK FOR SERVICE.

Part: OUTFLOW VALVE — MALFUNCTIONED (CABIN PRESSURE) · airframe 35,651 hrs · 16,433 cycles

00-353 UNABLE TO PRESS A/C AFT T/O. OUTFLOW VALVE AFT FAULTED AND REG 2 FAULTED. DISCONNECTED C/P SHAKE TEST AND RECONNECTED.

Part: COMPUTER — FAILED (COCKPIT) · airframe 39,644 hrs · 16,427 cycles

00-348 CAPTS SGU FAILED AT 85 KTS. ** S/D ** COMING

Part: RETRACT MECH — FAILED (LANDING GEAR)

99-176 - ON T/O IN NR 2 SYS LAND GEAR WOULD NOT RETRACT, HANDLE WOULD NOT GO ABOVE HALFWAY. SWITCH TO SYS NR 1 HANDLE WENT UP BUT GEAR STAY DOWN.