N422FE

Part: DOOR FRAME — DAMAGED (ZONE 100) · airframe 44,059 hrs · 16,919 cycles

FORWARD CARGO DOOR JAMB AT FRAME 20 AND 20A/STRINGER 38, RT FERRY F COMPLY WITH EA 6-5310-117514 REV NR POS P. MAJOR REPAIR ACCOMPLISHED REF: EA NR 6-5310-117520 P1.

Part: BEARING — EXCESS PLAY (RUDDER) · airframe 43,292 hrs · 16,469 cycles

NR 3 RUDDER HINGE ARM HAS 1 BEARING WITH PLAY (ZONE 320) REMOVED BEARING AND BUSHING ARM AS PER AIRBUS A310 SERVICE BULLETIN A310-55-2025. INSTALLED BEARING AND BUSHING IAW AIRBUS PMS 01-05-58 AND EA 6-5530-107658.

Part: SEAT TRACK — GOUGED (FUSELAGE) · airframe 43,292 hrs · 16,469 cycles

GOUGE FOUND ON SEAT TRACK NR 5 ZONE 231 LT SIDE BETWEEN FRAME 18 AND 20. REPAIRED SEAT TRACK PER A310 SRM 53-10-16.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 43,292 hrs · 16,469 cycles

FOUND SEAT TRACK AT R-5 2EA SPOTS OF CORROSION BETWEEN FR 38.2 AND 40/41. REMOVED AND REPLACED SEAT TRACK IAW A310 SRM 51-40-21 AND 53-10-16.

Part: SEAT TRACK — GOUGED (FUSELAGE) · airframe 43,292 hrs · 16,469 cycles

MDCC SEAT TRACK HAS 1 AREA GOUGED, 1 PREVIOUS REPAIR AND 6 SPOTS OF CORROSION BETWEEN FR 58-72. REMOVED SEAT TRACK IAW A310 SRM 51-72-10. FABBED REPLACEMENT SEAT TRACK IAW A310 SRM 53-10-16 AND AIRBUS DWG A53278820. INSTALLED REPLACEMENT SEAT TRACK IAW A310 SRM 51-72-10.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 43,292 hrs · 16,469 cycles

FOUND FWD CARGO COMPT, FS 38, FLOORBEAM, LBL66, (1) EA CRACK IN RADIUS 0.380 INCH LENGTH. REPAIRED FLOORBEAM PER A310-200 SRM 53-10-15.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 43,292 hrs · 16,469 cycles

FOUND FWD CARGO COMPT, FR36 FLOORBEAM LBL 66 (1) EA CRACK IN RADIUS 0.380 INCH LENGTH. REPAIRED FLOORBEAM FR36 LBL66 IAW A310-200 SRM 53-10-15 PB 201 FIG 201.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 43,292 hrs · 16,469 cycles

FOUND CORROSION IN AND AROUND FASTENER HOLE FR55/58 LT SIDE AFT CARGO COMPARTMENT MDCC FLOORBEAM. REMOVED CORROSION IAW A310-200 SRM 51-74-10 AREA WENT OUT OF LIMITS IAW A310-200 SRM 53-10-15. INSTALLED FABBED REPAIR ANGLE PARTS IAW A310-200 SRM 53-10-15. ALODINED, PRIMED AND TOP COATED PARTS IAW A310-200 SRM 51-75-10.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 43,292 hrs · 16,469 cycles

FOUND FWD CARGO COMPT, FR 38, FLOORBEAM, LBL66, (1) EA CRACK IN RADIUS 0.380 INCH LENGTH. REPAIRED FLOORBEAM PER A310-200 SRM 53-10-15.

Part: SPAR — MISREPAIRED (ZONE 300) · airframe 43,292 hrs · 16,469 cycles

PREVIOUS REPAIR LOCATED ON RT THS UPPER REAR SPAR CHORD AT RIB 4 HAS A REPAIR STRAP APPROXIMATELY 10.3" BY 1.0" LONG PREVIOUSLY INSTALLED REPAIR LOCATED AT RT THS UPPER CHORD AT RIB 4 WAS DETERMINED NOT TO BE IAW A310 SRM 55-11-21 FIG 217, DUE TO INCORRECT FASTENERS AND PITCH INSTALLED. COMPLIED WITH FED EX EA6-5510-107667.

Part: FLOORBEAM — MISREPAIRED (ZONE 200) · airframe 43,292 hrs · 16,469 cycles

PREVIOUS REPAIR LOCATED ON MAIN CABIN FLOORBEAM FRAME 37 AND BETWEEN SEAT TRACKS 4 AND 5 LT HAS 2 REPAIR ANGLES MEASURING 16.8" BY 1.7" LONG LOCATED AT THE UPPER FLANGE AREA, FWD AND AFT SIDE OF FLOORBEAM. PREVIOUSLY INSTALLED REPAIR LOCATED ON MAIN CABIN FLOORBEAM FRAME 37 BETWEEN SEAT TRACKS 4 AND 5 LT UPPER FLANGE AREA WAS DETERMINED NOT TO BE IAW A310 SRM SUPPLEMENT 53-10-15 FIG 201 SHEET 2, DUE TO MISSING 2 EACH HILOCKS AT TOP FLANGE ON FWD AND AFT CENTER ANGLES AT THE CLS ADAPTER BETWEEN THE FASTENERS WITH A PITCH OF 2.800". DRILLED, COUNTERSUNK, AND INSTALLED 2 HILOCKS PER A310 SRM SUPPLEMENT 53-10-15 FIG 201 SHEET 2.

Part: SEAT TRACK — MISREPAIRED (ZONE 200) · airframe 43,292 hrs · 16,469 cycles

PREVIOUS REPAIR LOCATED ON MAIN CABIN SEAT TRACK 5R BETWEEN FRAMES 35 TO 37 HAS A REPAIR WITH 4 EACH REPAIR ANGLES MEASURING 8.8" LONG EACH AND THE SEAT TRACK REPAIR SECTION IS 20" LONG. PREVIOUSLY INSTALLED REPAIR LOCATED AT MAIN CABIN SEAT TRACK 5R BETWEEN FRAMES 35 TO 37 WAS DETERMINED NOT TO BE IAW A310 SRM 53-10-16 FIG 208 SHEET 1, DUE TO FASTENER PITCH INCORRECT. COMPLIED WITH REPAIR PER FED EX EA6-5310-107668.

Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 43,292 hrs · 16,469 cycles

PREVIOUS REPAIR, LWR RT SIDE FUSELAGE SKIN BELOW BULK CARGO DOOR HAS EXTERNAL REPAIR DOUBLER BETWEEN FR 67 AND FR 68, STR49 RT TO STR 52 RT, MEASURING 8.8 IN BY 8.4 IN ZONE 160. REPAIR AREA WAS NOT IAW A310 SRM 53-10-12 FIG 225 SHEET 1. AREA REPAIRED CORRECTLY IAW A310 SRM 53-10-12 FIG 225 SHEET 1.

Part: AUTOTHROTTLE SYS — MALFUNCTIONED (COCKPIT) · airframe 42,679 hrs · 16,169 cycles

RTO AT 80 KTS, AUTO THROTTLES/SRS NOT ENGAGED. CHECKED MTP, NO FAULT FOUND. ADVISED BY CREW SYSTEM WENT NORMAL, CAN USE MANUAL OPS. ATS SYSTEM 1 & 2 CHECK NORMAL PER A310 AUTO THROTTLE TEST AMM 22-30-00-52, GOOD LEGS SINCE RTO.

Part: GENERATOR — MALFUNCTIONED (NR 1) · airframe 42,427 hrs · 16,059 cycles

ON TAKEOFF ROLL AT ABOUT 85 KTS THE NR 1 GEN FAULTED JUST BEFORE THE FAULT THE CAPT INSTRUMENTS (PFD & NAV) FLICKERED RESETTED GEN ON TAXI IN AND IT DID NOT FAULT AGAIN. RELEASED FOR SERVICE PER MEL/CDL: 24-11-01 CATEGORY: B EXPIRATION: 24JUN06 "MEL 24-11-01: GEN (IDENTIFY 1 OR 2) 1 - INOP. IDG DISCONNECTED. IDG AND GCU WAS REPLACED PER AMM, ENGINE RUN ACCOMPLISHED

Part: FIRE LOOP — MALFUNCTIONED (NR 1 NACELLE) · airframe 42,121 hrs · 15,907 cycles

DURING CRUISE, RECEIVED ADVISORY FOR HIGH SECTOR TEMP IN COCKPIT. NEXT, RECEIVED AVIONICS SMOKE ECAM. COMPLIED WITH ECAM/QRH. NEXT, RECEIVED MID 2 LOOP FAULT. COMPLIED W/ QRH, ALL 3 ASSOCIATED VALVES WOULD NOT RESET. RECEIVED ALL ECAM/CRC INDICATIONS AS IF WERE GROUND TEST. COMPLIED WITH ECAM/QRH. DEFINITELY HAD SOME SORT OF SMOKE IN C/P. OPENING VENT, EXTRACT REDUCED SMOKE. NEXT, RECEIVED COCKPIT ALTI ECAM. COCKPIT REACHED 12,000 FT. COMPLIED WITH QRH/ECAM. VALVES RESET AFTER 5-10 MIN. ALL INDICATIONS WENT AWAY, STILL HAD SMOKE SMELL IN C/P. RTB SFS AS PRECAUTION. REMOVED AND REPLACED NR 1 LOOP-B DETECTOR PER AMM 26-19-12-4. REMOVED APU PLENUM AND CLEANED OIL FOUND FROM OVERSERVICING.

Part: WARNING LIGHT — ILLUMINATED (BRAKES) · airframe 42,087 hrs · 15,887 cycles

BRAKE TEMP HI INDICATION ON TAKEOFF ROLL, ABORTED TAKEOFF. RETURNED TO RAMP FOR BRAKE COOLING. PROVIDED BRAKE COOLING EQUIP, C/W HOT BRAKE INSPECTION PER AMM 05-51-16. FOUND NR 8 TIRE FLAT. REMOVED AND REPLACED NR 8 MAIN GEAR TIRES PER AMM 05-51-16, AMM12-37-32-0-02 CHECKED BSCU NO FAULT FOUND. INSPECTED ALL ANOTHER BRAKES AND TIRES NML PER AMM32-40-06, PERFORMED BRAKE OPS CHK NML . A/C OK FOR SERVICE.

Part: UNKNOWN — WARNING MESSAGE · airframe 42,038 hrs · 15,865 cycles

DURING CLIMB-OUT FROM PEN MID2 'A' FAULT ILLUMINATED, FOLLOWED SHORTLY BY MID1 CARGO SMOKE LOOP FAULT. PERFORMED ECAM AND QRH PROCEDURES NO HELP. ECAM ADVISORY FOR NR 1 BLEED TEMP HIGH BEGAN FLASHING WITH TEMPERATURE CYCLING ERRATICALLY. CARGO SMOKE LIGHT MAIN DECK AND MID LIGHT ILLUMINATED. DECLARED EMERGENCY VERIFIED NIL SIGN OF SMOKE/SMELL IN MDC AREA. ALL SATISFACTORY. REMOVED AND REPLACED FAN AIR VALVE AS PER A310 MM 36-11-16-4-01. AS PRECAUTIONARY, ALSO REMOVED AND REPLACED PRECOOLER OUTLET TEMPERATURE SENSOR AS PER A310 MM 36-21-13-4. PERFORMED ENGINE RUN AS PER JRH.

Part: RESERVOIR — LOW (HYDRAULIC SYSTEM) · airframe 41,469 hrs · 15,610 cycles

LOST GREEN HYD FLUID IN CRUISE. RESERVOIR LOW PRESSURE. CRANKED GEARS MANUALLY, USED ALTERNATE. ALT-ON-POSITION FOR LANDING (ANTI-SKID).

Part: ENGINE — BIRD INGESTION (RIGHT) · airframe 40,689 hrs · 15,263 cycles

RTO AT 120 KIAS DUE TO LOUD BANG,VIBRATION,AND PULL TO THE RIGHT. F/O SAW AT LEAST TWO BIRDS MOMENTARILY BEFORE EVENT. MAX POWER DUE WET RUNWAY WINDS CALM. VIBRATION CEASED WHEN NR 2 ENGINE SHUTDOWN ON RUNWAY. REMOVED AND INSTALLED NR 2 ENG, NOSE COWL, RT THRUST REVERSER AND LT FAN COWL.

Part: PRESSURE PANEL — CORRODED (NLG WW) · airframe 40,016 hrs · 14,937 cycles

NOSE LANDING GEAR WHEEL WELL CEILING PRESSURE WEB PNL HAS CORROSION BETWEEN FR16 AND 14B BETWEEN LBL 18 TO RBL 18 REF N00114. REMOVED CORROSION AND REPAIRED IAW EA 6-5330-55395.

Part: DOUBLER — DAMAGED (FUSELAGE) · airframe 40,016 hrs · 14,937 cycles

FUSELAGE SKIN DOUBLER AT LT STA 926 AT APPROX 6:30 POS. REQUIRES FURTHER EVALUATION PER FAR 121.368. AFTER EVALUATION OF REPAIR, REPLACEMENT REQUIRED, REWORKED REPAIR IAW EA 6-5330-85452 REF N00855.

Part: STRUCTURE — CORRODED (HORIZONTAL STAB) · airframe 40,016 hrs · 14,937 cycles

HORIZONTAL STAB CENTER BOX TOP SIDE HAS APPROX 50 SQ INCH OF CORROSION ON AND UNDER FAST HEADS REF N-CARD N-00822. COMPLIED WITH EA 6-5510-84509 REMOVING FASTENERS CORROSION FLAP PEENING & REINSTALLING FASTENERS IAW A310 SRM 51-74-10, 51-29-00 & 51-40-21.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 40,016 hrs · 14,937 cycles

MCD FR 47 TO FR 53 LT NR 1 SEAT TRACK HAS 4 AREAS OF CORROSION REF N-CARD N00473. REPAIRED TRACK AT FR 46.5 TO FR 47.5 AND FR 52.5 TO FR 54 IAW SRM 53-10-16.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 40,016 hrs · 14,937 cycles

BULK CARGO COMPT FLOOR STRUCTURE FR 67 LT TO MID RT SIDE HAS MULTIPLE AREAS OF CORROSION FROM TOP SKIN TO UNDERNEATH SURFACE. REMOVED CORROSION, FOUND TO BE OUT OF LIMITS IAW SRM 53-10-00. REMOVED AND REPLACED BEAM IAW SRM 51-40-21 AT FR 67.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 40,016 hrs · 14,937 cycles

FR 38 TO FR 38.1 BILGE AREA HAS 2EA AREAS OF CORROSION ON STR 43L AND IN BETWEEN STR 44 AND 45, 48 SQ INCH REF N-CARD N00882. CLEANED AREA BETWEEN STR 44 AND 45 FOUND TO BE DIRTY, NO CORROSION EXIST IAW SRM 51-74-10. REPAIRED STR 43L FROM FR 38 TO FR 38.1 IAW SRM 53-10-14 FIG 201 & 51-40-21.

Part: SUPPORT BEAM — CORRODED (FUSELAGE) · airframe 40,016 hrs · 14,937 cycles

FR 87 LT TO RT SIDE UPPER SUPPORT BEAM HAS 70 SQ INCH OF CORROSION IN THS BAY. REMOVED CORROSION AND FOUND TO BE OUT OF LIMITS IAW SRM 53-10-00. REMOVED AND REPLACED BEAM IAW SRM 51-40-21 AND 51-74-10.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 40,016 hrs · 14,937 cycles

BULK CARGO COMPT FLOOR STRUCT FR 67 LEFT TO MID RIGHT SIDE HAS MULTIPLE AREAS OF CORROSION FROM TOP SKIN TO UNDERNEATH SURFACE. REMOVED CORROSION FOUND TO BE OUT OF LIMITS IAW SRM 53-10-00. REMOVED AND REPLACED BEAM IAW SRM 51-40-21 AT FR 67.

Part: FLOORBEAM — CORRODED (ZONE 100) · airframe 40,016 hrs · 14,937 cycles

BULK CARGO FLOOR STRUCT RT SIDE FS 64 TO 67 FLOOR STRUCTURE W/MULTIPLE CORRODED FROM TOP TO UNDERNEATH SURFACE. REMOVED AND REPLACED TEE PROFILE AT FS 63 TO FS 67 RBL 37 RT IAW A310 SRM 51-40-21.

Part: SEAT TRACK — CORRODED (ZONE 200) · airframe 40,016 hrs · 14,937 cycles

MDCC LEFT NR 5 SEAT TRACK HAS CORROSION AT FR C-54, 53, 52, 50.89, 48. REMOVED AND REPLACED SEAT TRACK IAW A310 SRM 51-40-21 AND B/P 15 A 53811922 FROM FR 54 TO FR 45 LBL 77.

Part: STRUCTURE — CORRODED (ZONE 100) · airframe 40,016 hrs · 14,937 cycles

BULK CARGO FLOOR STRUCT RT SIDE FR 64 TO 67 FLOOR STRUCT W/MULTIPLE CORROSION FROM TOP TO UNDERNEATH SURFACE. REMOVED AND REPLACED T- PROFILE AT FR63 TO FR 67 RBL 37 RT IAW A310 SRM 51-40-21.

Part: FLOOR PANEL — CORRODED (ZONE 100) · airframe 40,016 hrs · 14,937 cycles

BULK CARGO FLOOR STRUCTURE FR 69 FROM LT UP TO RT CORNER FLOOR STRUCT W/5 AREAS OF CORROSION TOP TO UNDERNEATH SURFACE. REMOVED AND REPLACED T-PROFILES AT FR 66-69 RBL 37 AND FR 66.5-69 LBL 27.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 40,016 hrs · 14,937 cycles

MDCC RIGHT NR 2 SEAT TRACK HAS CORROSION AT FR 52.8, 51.2, 50.51, 49.5 AND 48.5. REMOVED AND REPLACED SEAT TRACK FROM FR STA 46 TO FR STA 54 RBL 15.

Part: FLOOR PANEL — CORRODED (FUSELAGE) · airframe 40,016 hrs · 14,937 cycles

BULK CARGO COMPT FLOOR STRUCT FR 68 4 EA AREAS OF CORROSION TOP TO UNDERNEATH. REPLACED T PROFILE AND FITTING AT FR 66 TO 69 BL 0 AND RBL 20 FR 68 IAW A310 SRM 51-40-21.

Part: SEAT TRACK — DAMAGED (FUSELAGE) · corrosion level 2 · airframe 40,016 hrs · 14,937 cycles

LEFT SEAT TRACK NR 5 FROM FS 18 TO 21 BETWEEN FS 20 AND 21 HAS MATERIAL REMOVED OUT OF LIMITS, LOCATION B(65 INCHES) OTBD. REPAIRED BY REMOVING DAMAGED SECTION AND SPLICING IN A NEW SECTION IAW A310/200 SRM 53-10-16 FIG 208.

Part: STRINGER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 40,016 hrs · 14,937 cycles

THS BAY PROFIL STRINGER HAS 4" OF CORROSION FS 90 RT OVER TORQUE BOX. REMOVED T-PROFILE AT FS 90 ON UPPER RT EDGE BEAM THAT WAS CORRODED OUT OF LIMITS AND REPLACED IAW A310/200 SRM 51-72-10.

Part: SEAT TRACK — GOUGED (FUSELAGE) · airframe 40,016 hrs · 14,937 cycles

MAIN DECK CARGO COMPARTMENT ZONE 230 SEAT TRACK ADAPTERS, (6 EACH) AT LEFT SIDE FS 33, 35, 36, AND 37 AND ONE EA AT FS 38 IS GOUGED. BLENDED OUT GOUGES AND FOUND ANOTHER CLA GOUGED AT FS 32, ALL BLENDED OUT BEYOND LIMITS. REMOVED AND REPLACED CARGO LOADING ADAPTERS AT NOTED LOCATIONS IAW SRM 51-72-10.

Part: SEAT TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 40,016 hrs · 14,937 cycles

RT NR 3 SEAT TRACK HAS 8 AREAS OF CORROSION ON SCALLOP HOLES AND FLANGE. REMOVED CORRODED SEAT TRACK FROM FS 46.5 TO FS 54 IAW A310 SRM 51-72-10. INSTALLED NEW SEAT TRACK IAW A310 SRM 51-40-21 AND AIRBUS DWG NR 53811923200.

Part: SEAT TRACK — CORRODED (CARGO BAY) · corrosion level 2 · airframe 40,016 hrs · 14,937 cycles

MAIN DECK CARGO COMPARTMENT, RT NR 3 SEAT TRACK BETWEEN FS 37 AND FS 38 CORRODED BEYOND LIMITS. CUT SEAT TRACK BETWEEN FS 37 AND FS 38 TO END OF SEAT TRACK AT FS 38.2 IAW A310 SRM 53-10-16, FIG 208. FABRICATED NEW SEAT TRACK IAW A310 SRM 53-10-16 AND TREATED, PRIMED, AND TOP-COATED IAW A310 SRM 51-21-10. INSTALLED NEW SEAT TRACK IAW A310 SRM 51-40-21. WORK DOCUMENTED ON NRC NR N00946.

Part: SEAT TRACK — CORRODED (ZONE 200) · airframe 40,016 hrs · 14,937 cycles

MAIN CARGO DECK FR 45.5, NR 1 SEAT TRACK LEFT SIDE, WITH 1 EA AREA OF CORROSION NOTED INSIDE SCALLOP HOLES. REMOVED CORROSION IAW A310 SRM 53-10-15, AND FOUND TO BE WITHIN LIMITS IAW A310 SRM 53-10-16 PG 103 FIG 101. TREATED AND PRIMED AREA IAW A310 SRM 53-25-10.

Part: ROLLER TRAY — CORRODED (ZONE 100) · airframe 40,016 hrs · 14,937 cycles

AFT CARGO FLOOR STRUCTURE FR 60, RT SIDE ROLLER TRAY STRUCTURE NOTED CORROSION TOP TO UNDERNEATH NUTPLATES AS MARKED. REMOVED CORROSION ON RT SIDE ROLLER TRAY STRUCTURE AT FR 60 2 EA AREAS. MAX MATERIAL LOSS FOUND TO BE WITHIN LIMITS IAW A310 SRM 51-74-10 AND 53-10-15 PG 108. TREATED AND PRIMED AND TOPCOATED IAW A310 SRM 51-75-10.

Part: STRUCTURE — CORRODED (ZONE 100) · airframe 40,016 hrs · 14,937 cycles

AFT CARGO COMPARTMENT ON RT SIDE MID, FR 54 DOWN TO FR 58, 10 AREAS OF CORROSION NOTED TOP TO UNDERNEATH CLIP NUTS. REMOVED CORROSION AND CHECKED LIMITS IAW A310 SRM 53-10-15. FOUND TO BE WITHIN LIMITS AND REPROTECTED AREAS IAW A310 SRM 53-10-15 AND 51-75-10.

Part: INDICATOR — INOPERATIVE (ENGINE) · airframe 37,809 hrs · 13,903 cycles

ON TAKEOFF, N1 ON NR 1 ENG WENT TO 0, TAKEOFF WAS REJECTED AT 95KTS. AFTER REJECT ALL BRAKES WERE HOT AFTER REJECT TO 365DEG, N1 ON #1 MAY HAVE BEEN COMPRESSOR STALL FROM WATER ON RUNWAY. R & R NR 1 N1 INDICATOR PER MM 77-11-21-4. CLEANED AND PROPERLY SECURED ELECT. CONNECTOR OF N1 TACH PER SMP. RAN ENG. PER A310JRH,ALL PARAMETERS, NORMAL.

Part: LINE — LEAKING (HYD SYSTEM) · airframe 37,782 hrs · 13,893 cycles

DURING CRUISE, ECAM SIGNALED GREEN HYD RSVR LO LEVEL. GREEN HYD QUANTITY GAUGE AT RED DOT. FOLLOWED ECAM AND QRH PROCEDURES FOR HYD RSVR LO LEVEL, HYD SYS LO PR, AND L/G EXTENDED USING ALTERNATE GEAR EXTENSION. PERFORMED LEAK CHECK FOUND HYD FLUID LEAKING FROM UNION OF KRUEGER SELECTOR SOLENOID VALVE (ITEM 60 IPC 27-88-03-03/PAGE 1). PACKING ITEM 40 OF IPC 27-88-03-03 SEEKING FOR REPLACEMENT IF AVAILABLE. REF IPC 27-88-03-03 FIGURE 03 SHEET 1 ITEM 40 PACKING P/N NAS1612-6 IAW AMM 27-88-12-4 AND LEAK CHECKED OK. GREEN HYDRAULIC FLUID TOP-UP TO SERVICE LEVEL. RESTORATION OF LANDING GEAR ACTUATING SYSTEM TO NORMAL OPERATING CONDITION ACC TO AMM 32-33- 00-2.

Part: CONTROLLER — FAILED (SLAT/FLAPS) · airframe 37,615 hrs · 13,807 cycles

ON CLIMB OUT SIN. GOT "SLATS" LIGHT AND "SLATS" SYS 1 LIGHT ON OVERHEAD. DID PROCEDURE BUT NO CHANGE. RETURN TO SIN RAMP. SFCC 1 BITE SHOW SFCC FAULTED. R & R NR 1 SFCC PER MM 27-51-18-4. OPS CHECKED OK.

Part: SOLENOID VALVE — FAILED (FLAPS/SLATS) · airframe 37,615 hrs · 13,807 cycles

AFTER TAKE OFF AT SIN, RECEIVED FLAPS SYS 1 FAULT. ALSO LOST AIRSPEED HOOK ON CAPT SIDE WITH RED SPEED LIMIT SHOWING. SFCC NR 1 BITE SHOWS FLAP RT WTB. R & R RT WTB SOLENOID VALVE PER MM 27-56-13-4 AND PERFORMED SFCC BITE TEST PER MM 27-51-00 TEST OK. FOR PRECAUTIONARY REPLACED RELAY 31XC. FLAPS OPS CHECKED PER MM 27-54-00-5 CHECKED OK WITH NO SYS FAULT. PERFORMED ADS TEST PER MM 34-18-00-0 ALL TEST OK. A/C OK FOR SERVICE.

Part: FITTING — CORRODED (LT PYLON) · airframe 37,034 hrs · 13,516 cycles

LT ENGINE PYLON SPIGOT FITTING ASSEMBLY FOUND CORRODED. R&R FITTING PER SB A310-54-2020.

Part: BEARING — CORRODED (RT PYLON) · airframe 37,034 hrs · 13,516 cycles

RIGHT WING ENGINE PYLON AFT MOUNT FITTING BEARING CORRODED. R&R FITTING PER EA 6-5450-65104.

Part: SKIN — DAMAGED (RT WING) · airframe 37,034 hrs · 13,516 cycles

AFT PYLON HYD TUBES FITTING HOLES ON RIGHT WING UNDER SURFACE SKIN FOUND ELONGATED AFT OF PYLON RIB 21. R&R WING LWR SKIN PER EA 6-5710-65098.

Part: SKIN PANEL — CRACKED (LT WING) · airframe 37,034 hrs · 13,516 cycles

LEFT WING LWR SKIN PANEL NR 2 FOUND WITH EDGE CRACK JUST OUTBOARD OF RIB 11, CRACKED 1 INCH. R&R WING LWR SKIN PANEL NR 2 PER EA 6-5710-65099.

Part: FITTING — CORRODED (RT PYLON) · airframe 37,034 hrs · 13,516 cycles

CORROSION ON RIGHT WING ENGINE PYLON THRUST AND SIDE LOAD FITTING. R&R FITTING PER EA 6-5450-65103.

Part: SKIN — CORRODED (FUSELAGE) · airframe 37,034 hrs · 13,516 cycles

FUSELAGE SKIN INNER SURFACE CORRODED IN AVIONICS COMPT ON RIGHT SIDE OF ENTRY HATCH BETWEEN 8 & 9. CORROSION BLENDOUT DEPTH IS BEYOND LIMITS OF SRM 53-10-00. R&R STIFFENER PER EA 6-5330-65-66446.

Part: DOUBLER — CORRODED (FUSELAGE) · airframe 37,034 hrs · 13,516 cycles

FWD LAVATORY SERVICING PANEL DOUBLER AT LEFT SIDE OF FUSELAGE BETWEEN FRAME 12 AND 12A IS CORRODED ALONG LWR EDGE. R&R FRAME DOUBLER PER EA 6-5330-65-65906.

Part: FITTING — CORRODED (LT PYLON) · airframe 37,034 hrs · 13,516 cycles

LT PYLON AFT MOUNT FITTING FOUND CORRODED. R&R FITTING PER SB A310-54-2021 ON PYLON STRUCTURE.

Part: SKIN — CRACKED (RT WING) · airframe 37,034 hrs · 13,516 cycles

RIGHT WING OUTER LWR SKIN PANEL NR 2 AT TRAILING EDGE OF RIB 2 CRACK. R&R WING LWR SKIN PANEL NR 2 PER EA 6-5710-65100.

Part: DOUBLER — CORRODED (FUSELAGE) · airframe 37,034 hrs · 13,516 cycles

DOUBLER ON INNER FACE OF FUSELAGE SKIN CORRODED IN AVIONIC COMPT BETWEEN FRAME 16A & 17, EXTENDING FWD OF FRAME 16A OUTBD OF STR 44L & FWD OF FRAME 17 INBD OF STR 44L. R&R SKIN DOUBLER PER EA 6-5330-65-65906.

Part: SKIN — CORRODED (FUSELAGE) · airframe 37,034 hrs · 13,516 cycles

INNER FACE OF FUSELAGE SKIN CORRODED IN AVIONICS COMPT BETWEEN FRAME 16, 16A AND 17 OUTBOARD OF STRINGER 44R AND BETWEEN FRAME 16A AND 17, INBD OF STR 44R. R&R SKIN DOUBLER PER EA 6-5330-65-65906.

Part: ADC — FAULTY (NR 2) · airframe 35,749 hrs · 12,960 cycles

F/O'S AIRSPEED BECAME UNRELIABLE. REMOVED AND REPLACED NR 2 ADC PER MM 34-11-34-4.

Part: PITOT TUBE — FAULTY (PITOT/STATIC SYS) · airframe 35,749 hrs · 12,960 cycles

REJECTED T/O, F/O'S PFD HAD NO RELIABLE AIRSPEED. REMOVED AND REPLACED F/O'S PITOT PROBE PER MM 34-11-15.

Part: SENSOR — FAULTY (PITOT/STATIC SYS) · airframe 35,553 hrs · 12,882 cycles

LOSS ALL PURGE NR 1 ENGINE WITH ENG AND WING ANTI-ICE ON. CK SENSOR FAULT NIL, PERF PITOT SYS LEAK CK. OK FOR SERVICE.

Part: DETECTOR — FAILED (PROXIMITY) · airframe 35,235 hrs · 12,739 cycles

01-320 SYS 1 LAND GEAR FAIL TO RETRACT. R&R PROXIMITY DETECTOR PER 32-00-00.

Part: DOUBLER — CORRODED (FUSELAGE) · airframe 35,230 hrs · 12,735 cycles

LT & RT EXTERNAL DOUBLERS AT FWD PRESSURE BULKHEAD 6 O'CLOCK POS CORRODED. R&R BULKHEAD PER EA 6-5310-59382.

Part: WARNING LIGHT — ILLUMINATED (COCKPIT) · airframe 34,540 hrs · 12,429 cycles

AFT DEPART NR 1 GEN FAULT LIGHT CAME ON. AFT ECAM PROC AND DISCONNECT GEN IDG FAULT LIGHT ILLUM.

Part: WARNING LIGHT — ILLUMINATED (COCKPIT) · airframe 32,322 hrs · 12,329 cycles

LWR ACCESS DOOR OPEN LIGHT LIGHT CAME ON DURING FLT. RELEASE PER MEL 52-9.

Part: CROSSBEAM — CRACKED (FUSELAGE) · airframe 33,378 hrs · 11,851 cycles

FRAME 36 FOUND CROSS BEAM CRACKED AT VERTICAL MILLED WEB LOCATED .5 INCH BELOW UPPER FLANGE AT Y-700. *S/D* REMOVED AND REPLACED PER FEDEX EA 6-5100-52040 & A310 SRM SUPPLEMENTAL MANUAL 53-10-15, FIG 201.

Part: CROSSBEAM — CRACKED (FUSELAGE) · airframe 33,378 hrs · 11,851 cycles

NR 413 AT FRAME 37 FOUND CROSS BEAM CRACKED AT VERTICAL MILLED WEB LOCATED .375 INCH BELOW UPPER FLANGE AT Y-1650. *S/D* REMOVED AND REPLACED PER FEDEX EA 6-5100-52040 & A310 SRM SUPPLEMENTAL MANUAL 53-10-15, FIG 201.

Part: FLOORBEAM — CRACKED (CABIN) · airframe 33,378 hrs · 11,927 cycles

NR 414 AT FRAME 33, FOUND MAIN DECK FLOOR CROSS BEAM CRACKED AT VERTICAL MILLED WEB AT .375 INCH BELOW UPPER FLANGE AT AXIX Y - 700. *S/D* REMOVED AND REPLACED PER FEDEX EA 6-5100-52040 & A310 SRM SUPL MANUAL 53-10-15, FIG 201.

Part: CROSSBEAM — CRACKED (FUSELAGE) · airframe 33,378 hrs · 11,851 cycles

NR 407 AT FRAME 36 FOUND CROSS BEAM CRACKED AT UPPER FLANGE LOCATED .125 INCH BELOW UPPER FLANGE AT Y+900. *S/D* REMOVED AND REPLACED PER FEDEX EA 6-5100-52040 & A310 SRM SUPPLEMENTAL MANUAL 53-10-15, FIG 201.

Part: CROSSBEAM — CRACKED (FUSELAGE) · airframe 33,378 hrs · 11,851 cycles

NR 412 AT FRAME 37 FOUND CROSS BEAM CRACKED AT VERTICAL MILLED WEB, LOCATED .375 INCH BELOW UPPER FLANGE AT AXIS Y+700. *S/D* REMOVED AND REPLACED PER FEDEX EA 6-5100-52040 & A310 SRM SUPPLEMENTAL MANUAL 53-10-15, FIG 201.

Part: CROSSBEAM — CRACKED (FUSELAGE) · airframe 33,378 hrs · 11,851 cycles

NR 409 AT FRAME 36 FOUND CROSS BEAM CRACKED AT UPPER FLANGE LOCATED .125 INCH BELOW UPPER FLANGE AT AXIS Y +900. *S/D* REMOVED AND REPLACED PER FEDEX EA 6-5100-52040 & A310 SRM SUPPLEMENTAL MANUAL 53-10-15, FIG 201.

Part: CROSSBEAM — CRACKED (FUSELAGE) · airframe 33,378 hrs · 11,851 cycles

NR 410 AT FRAME 34 FOUND CROSS BEAM CRACKED AT VERTICAL MILLED WEB LOCATED .375 INCH BELOW UPPER FLANGE AT AXIS Y+700. *S/D* REMOVED AND REPLACED PER FEDEX EA 6-5100-52040 & A310SRM SUPPLEMENTAL MANUAL 53-10-15, FIG 201.

Part: CROSSBEAM — CRACKED (FUSELAGE) · airframe 33,378 hrs · 11,851 cycles

NR 411 AT FRAME 35 FOUND CROSS BEAM CRACKED AT VERTICAL MILLED WEB, LOCATED .5 INCH BELOW UPPER FLANGE AT AXIS Y+700. *S/D* REMOVED AND REPLACED PER FEDEX EA 6-5100-52040 & A310 SRM SUPPLEMENTAL MANUAL 53-10-15, FIG 201.

Part: FLOORBEAM — CRACKED (CABIN) · airframe 33,489 hrs · 11,927 cycles

FOUND FLOORBEAM AT FRAME 36 CRACKED AT THREE LOCATIONS: A) 3 INCHES LENGTH AT Y+700. B) 3 INCHES LENGTH AT Y+900. C) 1 INCH LENGTH AT Y-700. *S/D* REMOVED AND REPLACED PER FEDEX EA 6-5100-52040 & A310 SRM SUPPLEMENTAL MANUAL 53-10-15, FIG 201. THE DEFECTS RECORDED ON THIS SNRM HAVE BE TRANSFERRED TO NR 407, NR 408, NR 409 AS EACH DEFECT HAS TO BE INDIVIDUALLY RECORDED ON A SEPARATE SNRM.

Part: RETRACT MECH — MALFUNCTIONED (NLG)

NOSE DOOR WOULD NOT RETRACT WHEN GEAR HANDLE PUT IN UP POSITION.

Part: BYPASS VALVE — FAILED (NR 2 ENGINE)

T/O ABORT NR 2 ENGINE OIL TEMP WENT TO 250 DEG C, AT THROTTLE ADVANCE. TEMP REMAINED AT 185 DURING TAXI IN. ENGINE SHUT DOWN. REMOVED AND REPLACED FUEL OIL COOLER BYPASS VLV PER M/M 79-21-05, REMOVED AND REPLACED OIL TEMP SENSOR BULB PER 79-32-11. CHECKED OIL CHIP DETECTOR IS CLEAN, ALSO REMOVED AND REPLACED SYSTEM DATA ANALOG CONVERTER PER M/M 31-50-00 ENGINE RUN PER JET RUN HANDBOOK, INDICATION NORMAL. ACFT RELEASED TO SERVICE.

Part: CONTROLLER — MALFUNCTION (LANDING GEAR)

98-0178 STA-CEB: LANDING GEAR WOULD NOT RETRACT AFTER T/O. GEAR HANDLE STUCK IN MID DETENT. LANDED ASAP. PERFORMED BITE CHECK ON PROX DETECTION UNIT. NO FAULT FOUND. RESET CONTROLLER. CHECKED PROX SWS VISUALLY, GOOD CONDITION. NO EVIDENCE OF LEAKS AND ALL LANDING GEAR C/B,S IN ACFT OK TO CONTINUE PER TSM 32-30- FIG 108.

Part: COMPRESSOR — STALLED (NR 2 ENGINE)

KHH: 97-0103 UPON LANDING DURING MODERATE RAIN SHOWERS/STANDING WATER, AS A/C SLOWED TO 80 KTS IN REV THRUST, THE NR 2 ENGINE COMPRESSOR STALLED AND FLAME OUT OCCURRED. THIS ALSO CAUSED NR 2 ENGINE REV UNLOCK AND ENG FAIL INDICATIONS TO ILLUMINATE GROUND OBSERVERS NOTED EXCESSIVE WATER CAUSING COMPRESSOR STALL. ENG TAIL PIPE FIRE AFTER EXITING RUNWAY. ACCOMPLISHED OVERTEMP VISUAL INSPECTION PER M/M 72-00-00, PG 210, FOUND NML. A/C RELEASED PER EA 6-7200-29527, FOR ONE-TIME FLT TO TPE FOR HOT SECTION. ENG BORESCOPE RESULTS NML AND PLACED ON WATCH FOR 80 FLT HOURS.

Part: COMPRESSOR — STALLED (NR 2 ENGINE)

AFTER TOUCHDOWN DEPLOYED BOTH REVERSER WITH FULL THRUST. IMMEDIATELY THEREAFTER HEARD A LOUD REPORT AND SAW FLASH FROM NR 2 ENGINE AREA. NR 2 ENGINE SUBSEQUENTLY SHUT DOWN AND NEVER CAME OUT OF REVERSE. NO OTHER ABNORMAL COCKPIT OR ECAM WARNINGS. *S/D* REMOVED AND REPLACED NR 2 ENGINE PER WORK CARD NR 44T0704. COMPLIED WITH TEST IAW FEDEX WORK CARD AND ENGINE RUN UP PER JRH. ALL PARAMETERS NORMAL RII BY 212099. CLOSED AND SECURED TNG COWLINGS.

Part: PROX DETECTOR — FAILED (NLG)

PEN - AFTER T/O GEAR WOULD NOT RETRACT. NO ECAM MESSAGE. CONSULTED RED TABS. NO REFERENCE AVAILABLE, RETURNED TO PEN. LANDING OK, AFTER ROLLOUT, NO NOSE WHEEL CONTROL. A/C TOWED TO GATE. TIGHTENED CONNECTOR AT C/B 2 GB. REMOVED AND REPLACED PROX DETECTOR UNIT IAW. A310 M/M 32-31-71. PERFORMED OPS CK OF NOSE STEERING. OPS CHECK OK.

Part: PROX DETECT UNIT — MALFUNCTIONED (LANDING GEAR)

ON DEPARTURE FROM TPE, GEAR INDICATED UP AND LOCKED (GREEN AND YELLOW LIGHTS ON INDICATOR). CYCLED HANDLE AND YELLOW LIGHTS WENT OUT WITH GEAR HANDLE DOWN. UPON PLACING GEAR HANDLE UP AGAIN, HANDLE WOULD NOT COME PAST NEUTRAL; YELLOW LIGHTS ON WITH GREEN LIGHTS AND GEAR WOULD NOT RETRACT. FOUND SYS 1 RETRACT CTL 2 GB C/B POPPED. CK'D WIRING PER AWM 32-62-04 AND REMOVED AND REPLACED PROXIMITY DETECTOR PROCESSING UNIT PER M/M 32-61-00. PERFORMED SIMULATED FLT/GND CONFIGURATION TEST. ALL FUNCTIONS CK'D NORMAL PER M/M 32-00-00.

Part: MECHANISM — NOT LOCKED (RT CABIN DOOR)

DURING CLIMBOUT, RIGHT CABIN DOOR OPEN WARNING CAME ON. A/C PRESSURIZTION NORMAL. CREW BROUGHT DEADHEADS INTO COCKPIT AND MADE PRECAUTIONARY LANDING. UNABLE TO SILENCE WARNING CHIME. VISUAL INSPECTION OF DOOR LOCK INDICATOR SHOWED NOT FULLY LOCKED DISPLAYED AT WINDOW, DISARMED DOOR AND CYCLED DOOR HANDLE AND VISUAL LOCKED INDICATOR FULLY DISPLAYED IN WINDOW. ECAM INDICATION SHOWED NORMAL.

Part: SWITCH — FAILED (RT CABIN DOOR)

CLIMBING THROUGH 8,000 FEET, RIGHT CABIN DOOR INDICATED UNLOCKED. REMAINED ON UNTIL LANDING ROLL OUT. REPLACED DOOR WARNING MICROSWITCHES 8WS AND 42WS, ADJUSTED AND FUNCTIONAL TEST ON GROUND SATISFACTORY.