N455FE

Part: ACTUATOR — FAILED (LT MLG) · airframe 38,912 hrs · 18,435 cycles

UPON GEAR RETRACTION, RECEIVED A LT MAIN GEAR RED UNLOCK INDICATION WITH AN AMBER LT DOOR LIGHT. COMPLIED WITH ECAM EXTENDED GEAR & LANDED. WE DID HAVE A LOUD WIND NOISE WITH THE PROBLEM, PRETTY SURE DOOR WAS OPEN. DEBRIEFED CREW & VERIFIED THEY DID ATTEMPT GEAR RETRACTION IN BOTH SYS NR 1 & 2 WITH SAME RESULTS. LT MLG FAILED TO RETRACT. REMOVED LT MLG RETRACT ACT IAW MM 32-31-46-04AMM SMP. REPLACED LT MLG RETRACT ACTUATOR IAW A310-200. PERFORMED NORMAL LG RETRACTION & EXTENSION TEST, NO DEFECTS NOTED IAW MM 32-31-00-05.

Part: SEQUENCE VALVE — FAULTY (LT MLG) · airframe 38,893 hrs · 18,413 cycles

DURING CLIMB OUT AT GEAR RETRACTION, LT MAIN GEAR DID NOT APPEAR TO RETRACT & DOOR SHOWED OPEN. ECAM INDICATED LG RETRACTION INOPERATIVE. FUEL CONSUMPTION INCREASED. SELECTED OPPOSITE SYS & CYCLED THE GEAR, NO HELP. COMPLIED WITH ECAM & QRH. DECLARED AN EMER. SEE NEXT PAGE. AMM TROUBLESHOOT. R & R LT MLG SEQUENCE VLV IAW MM. OPERATIONS CHECKED GOOD. GEAR SWING PERFORMED. OK FOR SERVICE.

Part: VALVE — FAILED (SLAT SYSTEM) · airframe 38,682 hrs · 18,268 cycles

NR 1 SLAT SYS FAULT LIGHT DURING FINAL. RECYCLING DID NOT CORRECT, QRH PROCEDURES ACCOMPLISHED. SLAT FAULT LIGHT REMAINED ON, BUT SPFI SHOWED SLATS & FLAPS 30 & 40 LANDING NORMAL. DECLARED LANDING EMERGENCY. LANDING NORMAL. REMOVED AND REPLACED PCU VALVE.

Part: SWITCH — FAILED (THRUST REVERSER) · airframe 38,525 hrs · 18,155 cycles

ACCELERATING ABOVE 10,000 & 250 KTS, NR 1 ENGINE THRUST REVERSER UNLOCK ILLUMINATED STEADY. ALL OTHER INDICATIONS NORMAL. TROUBLESHOT IAW TSM 78-31-00, FOUND THE RT MASTER ACTUATOR SECONDARY LOCK SWITCH INOPERATIVE. REMOVED AND REPLACED THE NR 1 ENGINE RT MASTER ACTUATOR SECONDARY LOCK SWITCH IAW MM 78-31-16-04, OPS CHECKED GOOD.

Part: BRAKE SYS — MALFUNCTIONED · airframe 37,960 hrs · 17,758 cycles

ACFT LOST BRAKES. THEY HAD WORKED NORMALLY ON INITIAL TAXI AND HOLD SHORT CROSSING RWY 27. APPROACHING 36C ON TAXIWAY D, GOT NO BRAKING WITH NORMAL. RELEASED BRAKES, WENT TO ALT ON. AGAIN NO BRAKING. WENT TO IDLE REVERSE. RELEASED PEDALS AND TRIED ALT OFF, NO BRAKES. F/O GOT NO BRAKES EITHER. APPLIED PARKING BRAKE AT ABOUT 8-10 KTS AS. ACFT STOPPED AS ADVERTISED. NO HYD LEAKS NOTED. FACT 09MAY13 07:10 CVG U TOWED ACFT FROM RWY. MX CHECKED ACFT FOR HYD LEAKS, NO LEAKS NOTED. ALL HYD QUANTITIES AND PRESSURES NORMAL. OPERATED BRAKE SYS IN NORMAL ON, ALT ON, AND ALT OFF, WHILE VISUALLY CHECKING BRAKE ACTUATION ON ALL 8 BRAKE UNITS AND WHILE MONITORING INDICATED PRESSURES MANY TIMES. AT NO TIME WAS MX ABLE TO DUPLICATE ANY BRAKE MALFUNTION. CHECKED BSCU FOR FAULT CODES. NO FAULT CODES NOTED. PERFORMED BITE AND OPS CHECK OF ANTI-SKID SYS. NO FAULTS NOTED. BRAKE SYS OPS NORMALLY IAW AMM 32-42-00-00, 32-43-00-00, 32-44-00-00, AND 32-45-00-00. ACFT OK FOR CONTINUED SERVICE. FINAL CLOSED.

Part: VALVE — MALFUNCTIONED (MLG) · airframe 37,853 hrs · 17,683 cycles

LANDING GEAR FAILED TO EXTEND IN POSITION NR 1 OR NR 2. COMPLIED W/ QRH - MANUAL EXTENSION OK. EMERGENCY DECLARED. T/S IAW TSM 32-61-00. PREFORMED BITE TEST PROX DET. BOX FOUND FAULT CODES P2, P4. (EXTERNAL PWR SUPPLY BUS). IAW MM 32-33-00-02 RESTORED FREEFALL EXTENSION SYS TO NORMAL OPERATING CONDITION. GEAR DOORS CLOSED AND GEAR PINS INSTALLED. GEAR PINS REMOVED AND STOWED IN COCKPITS FOR FLIGHT. CHECKED WIRING AT LANDING GEAR SELECTOR VALVE REF AWM 32-31-01. ALL CHECKS NORMAL. R & R ELECTRO HYD VALVE 3GA REF MM 32-31-12-04. VALVE LEAKS CHECKS GOOD. PERFORMED OPS/INSPECTION CHECK REF MM 32-31-12-06. OPS CHECK OF GEAR AND LIGHTS NORMAL.

Part: SHUTOFF VALVE — MALFUNCTIONED (THRUST REVERSER) · airframe 37,618 hrs · 17,543 cycles

DURING CLIMBOUT PASSING 10000 FT, ECAM INDICATED THRUST REV NR 1 UNLOCKED. THIS INDICATION CYCLED IN AND OUT MULTIPLE TIMES. NO OTHER ENGINE INDICATIONS PRESENT. R & R NR 1 THRUST REVERSER PRSOV IAW MM 78-31-05-04. LEAK CHECKED OK. PERFORMED OPS CHECK OF THRUST REVERSER IAW JRH 7-48 NR 1 THRUST REVERSER OPS CHECKED NORMAL.

Part: HANDLE — STICKING (PARKING BRAKE) · airframe 37,488 hrs · 17,455 cycles

AS POWER WAS INCREASING AFTER TOGA ON TAKE OFF, RECEIVED A CRC FOR "PARKING BRAKE SET" EVEN THOUGH PARKING BRAKE HANDLE WAS DOWN. SECOND TAKE OFF ATTEMPT OK. INSPECTED PARK BRAKE LINKAGE FOR CORRECT OPERATION NO DEFECTS NOTED, CLEANED CONNECTOR AT 7GG, FOUND UPPER SHAFT OF PARK BRAKE HANDLE STICKY, CLEANED AND LUBED HANDLE AS REQUIRED, UNABLE TO DUPLICATE FAULT ON THE GROUND.

Part: PRESSURE SWITCH — FAILED (NR 1 ENGINE OIL) · airframe 37,213 hrs · 17,250 cycles

DESCENDING OUT OF FL310 WE GOT AN OIL CLOG LIGHT ON NR 1 ENGINE. COMPLIED WITH PROCEDURES, SHUTDOWN NR 1 ENGINE. ALL OIL PRESSURES INDICATED NORMAL BEFORE AFTER SHUTDOWN. AFTER ENGINE SHUTDOWN NR 1 OIL CLOG LIGHT REMAINED ON. T/S IAW TSM 79-00-00, FIG 109, REMOVED CONNECTOR FROM S299 NR 1 OIL DIFFERENTIAL PRESSURE SWITCH AND OIL CLOG LIGHT WENT OUT. R & R NR 1 ENGINE OIL DIFFERENTIAL PRESSURE SWITCH IAW A310 AMM 79-35-11-04. RAN NR 1 ENGINE IAW A310 JRH. SWITCH LEAK CHECKED OK. OIL CLOG LIGHT STAYED OFF DURING RUN AND OIL PRESSURE WAS NORMAL. ACFT OK FOR SERVICE.

Part: OIL SYSTEM — LOW PRESSURE · airframe 36,780 hrs · 16,975 cycles

YELLOW OIL PRESSURE LIGHT ILLUMINATED DURING TAKE OFF ROLL AT 110 KTS. ABORTED TAKE OFF, COMPLIED WITH QRH. RAN ENGINES AT POWER, OIL PRESSURE STAYED AT 52 PSI IN THE NORMAL RANGE IAW JRH. SUSPECTED COLD ENGINE OIL ON COLD SOAKED ENGINE THAT LAYED OVERNIGHT IN SUB-FREEZING TEMPERATURES. CREW VERBALLY INDICATED THAT IT WAS THE NR1 ENGINE OIL PRESSURE LIGHT.

Part: TRANSMITTER — INOPERATIVE (OIL PRESSURE) · airframe 36,679 hrs · 16,904 cycles

DURING T/O ROLL THE HIGH OIL PRESSURE (NR 1) ENG, CAME ON AT 80 KTS. R & R THE NR 1 ENG OIL PRESS TRANSMITER IAW MM 79-33-11-04, RAN ENG IAW JRH, CHECKS GOOD. ACFT OK TO CONTINUE.

Part: HMU — FAILED (NR 2 ENGINE) · airframe 36,664 hrs · 16,891 cycles

ON TAKEOFF, NR 2 ENGINE WOULD NOT RESPOND TO THROTTLE MOVEMENT. R & R NR 2 ENGINE HMU IAW AMM 73-21-01-04. CHECKED GOOD. PERFORMED IDLE LEAK CHECK AND POWER TRIM RUN IAW MM 71-00-00-05 LEAK CHECKS GOOD AND POWER RUNUP CHECKS GOOD.

Part: WIRE HARNESS — DAMAGED (ENGINE) · airframe 36,652 hrs · 16,882 cycles

REJECTED T/O, SET BOTH ENGINES TO 40 PERCENT N1, TOGA'D AND ENGINE NR1 IMMEDIATELY POWERED UP AND ENGINE 2 STOPPED ACCELERATING AT 50 PERCENT N1. MADE 2ND ATTEMPT BUT REJECTED DUE TO ENGINE 2 WOULD NOT ACCELERATE ABOVE 50 PERCENT N1 EVEN WITH PILOT ATTEMPTED ASSIST ON THROTTLE. R & R'D NR 2 ENGINE TT2 SENSOR REF M/M 73-21-02-04 THRU STEP 3 E (3) REF AWD 71-00-11,, AND WSP 20-25-41 REPLACED PLUG D4972P AND SECURED. COMPLIED WITH GROUND TEST OF NR 2 ENG TT2 SENSOR AT IDLE POWER. NO DEFECTS NOTED ON GROUND AT THIS STATION REF MM 73-21-02-04. SECURED NR 2 ENGINE WIRE HARNESS AND ALL CONNECTORS THAT WERE DISCONNECTED.

Part: SELECTOR VALVE — MALFUNCTIONED (MLG) · airframe 36,469 hrs · 16,753 cycles

LANDING GEAR WOULD NOT EXTEND NORMALLY AFTER GEAR HANDLE PLACED IN DOWN POSITION. MANUALLY EXTENDED GEAR. QRH COMPLIED WITH, UNEVENTFUL LANDING MADE. R & R LANDING GEAR SELECTOR VALVE 3GA IAW MM 32-31-12-04.

Part: LATCH — MALFUNCTIONED (PAX DOOR) · airframe 36,386 hrs · 16,686 cycles

CLIMBING THRU FL 310 ECAM INDICATED "R FWD CABIN DOOR NOT CLOSED". CABIN PRESSURIZATION INCREASED RATE OF CLIMB FROM 300-400 FPM TO 800 FPM AND CABIN ALTITUDE WAS 8000. SHOULD USUALLY BE AROUND 5600 FPM OR SO. CABIN DOOR SHOWED UNLOCKED ON ECAM BUT LATER SHOWED LOCKED. VISUALLY CONFIRMED LOCKED. REMOVED AND REPLACED R-1 DOOR SWTICHES 8WS AND 42 WS IAW AMM 52-71-11-04 AND -05. REINSTALLED ALL REMOVED DOOR LININGS REF AMM 25-23-41-04 AND ADJUSTED ACCORDINGLY. PERFORMED GVI OF ALL LATCHING MECHANISMS AND FOR FREE PLAY IN DOOR MECHANISMS REF 52-10-20-06, WITH NO DEFECTS NOTED. PERFORMED PRESSURIZATION TEST REF AMM 05-53-00-00-9, WITH NO ABNORMALITIES OR LEAKS NOTED. DOOR OPERATES NORMALLY REFERNCE AMM 52-71-00-05. OK FOR SERVICE.

Part: SELECTOR VALVE — INOPERATIVE (MLG) · airframe 36,173 hrs · 16,530 cycles

LANDING GEAR WOULD NOT EXTEND WHEN HANDLE WAS PLACED DOWN. PERFORMED "GRAVITY EXTENSION" IAW QRH. EMERGENCY DECLARED AND ACFT WAS STOPPED ON THE RUNWAY BECAUSE OF NWS. LOOKED AT BOTH SYS 1 & 2 BEFORE EXTENDING GEAR MANUALLY. R & R LANDING GEAR SELECTOR VALVE IAW AMM 32-31-12-04, ALL TESTS AND LEAK CHECK GOOD. ACFT OK FOR SERVICE.

Part: FLAP SYSTEM — MALFUNCTIONED (TE FLAPS) · airframe 36,143 hrs · 16,509 cycles

GOT FLAP VANE JAM AND FLAP FAULT ECAM INDICATIONS WHILE EXTENDING FLAPS. THEY STUCK AT LESS THAN 15 DEGREE (APPROX 5 DEGREE). CYCLE TO NO AVAIL WENT AROUND AND REATTEMPTED ON DOWNWIND. SECOND ATTEMPT WAS SUCCESSFUL. FACT ADJUST/TEST FLAP VANE SYS. OP'S CHECK GOOD IAW MM 27-56-15-05-0. ALSO RAN ENGINE TO GET SYS PRESSURE 3000 PSI IAW JRH. ACFT GOOD FOR SERVICE. FINAL CLOSED.

Part: CABLE — GOUGED (THRUST REVERSER) · airframe 36,134 hrs · 16,502 cycles

NR1 PYLON LOWER SIDE OF NACELLE LT & RT THRUST REVERSER INTERLOCK CABLES GOUGED THRU CABLE INSULATION. MARKED, R & R NR1 PYLON LT INTERLOCK CABLE IAW AMM 76-11-41-04, REMOVED NR1 PYLON RT INTERLOCK CABLE IAW AMM, REPAIRED RT INTERLOCK CABLE IAW EA 6-7611-136727 PT1, INSTALLED RT INTERLOCK CABLE IAW AMM 76-11-41-04. OPS CHECK GOOD IAW AMM 78-32-11-05. EA 6-7611-136727 TITLED ENGINE CONTROLS - T/R INTERLOCK FEED BACK CABLE.

Part: DOOR FRAME — GOUGED (ZONE 800) · airframe 36,134 hrs · 16,502 cycles

LT MLG DOOR TOP AFT INNER MATING SURFACE IS GOUGED. REMOVED GOUGE AND FOUND TO BE OUT OF LIMITS. MATERIAL LOSS 0.022 FROM 0.078., 0.056 MATERIAL REMAINING. FABBED DOUBLER IAW EA 6-5280-136728, " DOORS - LT MLG MAIN DOOR UPPER FRAME". ALODINED AND PRIMED IAW SRM 51-21-10 THEN INSTALLED IAW EA 6-5280-136728. COMPLIED WITH EA 6-5280-136728, "DOORS - LT MLG MAIN DOOR UPPER FRAME".

Part: TEE FITTING — CRACKED (CARGO DOOR) · airframe 36,134 hrs · 16,502 cycles

BULK CARGO DOOR TEE PROFILE IS CRACKED AT FRAME 68, BEAM 3. REMOVED TEE PROFILE REF SRM 51-40-21, PARA 6. MACHINED NEW TEE PROFILE REF DWG A52378044. LOCATED HOLES ON NEW TEE PROFILE REF SRM 51-40-44. ALODINED NEW TEE PROFILE REF SRM 51-21-10, PG 6. PRIMED AND PAINTED NEW TEE PROFILE REF SRM 51-23-10. INSTALLED NEW TEE PROFILE REF SRM 51-40- 21, PARA 7.

Part: BRACKET — CRACKED (CARGO DOOR) · airframe 36,134 hrs · 16,502 cycles

BULK CARGO DOOR STAY BRACKET IS CRACKED AT FRAME 68, BEAM 3. ACQUIRED MATERIAL ID FOR NEW STAY BRACKET IAW SRM 52-34-00, PO 680480.1. FORMED NEW STAY IAW SRM 51-26-00. ALODINED NEW STAY IAW SRM 51-21-10, PARA 4, PG 6. PRIMED & PAINTED NEW STAY IAW SRM 51-23-10, PG 2.

Part: ANGLE — CRACKED (ZONE 400) · airframe 36,134 hrs · 16,502 cycles

NR1 PYLON ACCESS PANEL 475 AL (STRINGER), RT SIDE, CTR SECTION OF PANEL "T" ANGLE IS CRACKED. REMOVED CRACKED FRAME AND FABBED NEW FRAME FROM 0.063, 2024-0, PO NR673099.1 IAW SRM 54-55-51, FIG 3. HEAT TREATED TO 2024-T3 IAW AMS 2770, REV "H". FIT AND DRILLED FRAME IAW SRM 51-40-40. ALODINED AND PRIMED IAW SRM 51-21-10 AND SRM 51-23-10. PART MARKED IAW GMM 7-0-1001. INSTALLED FRAME IAW SRM 51-40-21, PGS 7 & 24.

Part: STOP FITTING — CRACKED (ZONE 200) · airframe 36,134 hrs · 16,502 cycles

RT AFT PAX / CREW DOOR STOP FITTING IS CRACKED AT THE INBD LOWER FASTENER; LOWER AFT DOOR FRAME STOP FITTING IN THE DOOR CUTOUT. REPLACED RT AFT PAX DOOR STOP FITTING IAW SRM 51-72-10 AND SRM 51-40-21, PG 5-7.

Part: FLOOR SUPPORT — CRACKED (ZONE 100) · airframe 36,134 hrs · 16,502 cycles

FWD PIT, AFT FLOOR SUPPORT, RT SIDE IS CRACKED BETWEEN FRAME 38.2 AND FRAME 39. REMOVED AND REPLACED AFT FLOOR SUPPORT, R/H SIDE AT FRAME 38.2 IAW SRM 51-40-21, PARA 5 AND 6.

Part: PRESSURE PANEL — CORRODED (CARGO FLOOR) · corrosion level 2 · airframe 36,134 hrs · 16,502 cycles

FWD CARGO COMPARTMENT HORIZ PRESSURE DECK UPPER SURFACE AT FRAME 40/41 IS CORRODED AT THE SPLICE. REPAIRED PER FEDEX EA 6-5310-136722, TITLE " FUSELAGE - PRESSURIZED FLOOR BETWEEN FR 39 AND FR 40 AT Y-95.3". REMOVED AND RE-INSTALLED 1 EA. SUPPORT BRACKET AT FR 40 IN THE A/C BAY IAW SRM 51-40-21, PARA'S 5, 6 AND 7. REMOVED AND RE-INSTALLED WING CENTER BOX BOTTOM SKIN VAPOR SEAL ; RT FWD SIDE IAW SRM 51-40-21, PARA 5. REMOVED AND RE-INSTALLED 2 EA. VAPOR SEAL STRAPS; RT UPPER AND CENTER IAW AMM 28-13-21-04, PG 4. INSTALLED 2 EA. VAPOR SEAL LOWER CENTER STRAPS REF AMM 28-13-21-01. PERFORMED EXTERNAL VENTILATION TEST IAW AMM 28-13-00-05. TESTED GOOD.

Part: FITTING — CORRODED (NACELLE) · corrosion level 2 · airframe 36,134 hrs · 16,502 cycles

NR 2 ENG PYLON SPIGOT RECEPTICAL FITTING BALL JOINT FLANGE IS PITTED AT THE UPPER AND LOWER FLANGE PLATES INCLUDING THE BEARING BORE. COMPLIED WITH EA 6-5450-136723; " NACELLES / PYLON - SB A310-54-2020 - NR1 AND NR2 PYLON SPIGOT FITTING BORE CORROSION".

Part: FITTING — CORRODED (ZONE 400) · corrosion level 2 · airframe 36,134 hrs · 16,502 cycles

NR1 ENGINE PYLON SPIGOT RECEPTICAL FITTING BALL JOINT FLANGE IS PITTED AT THE UPPER AND LOWER PLATES INCLUDING THE BEARING BORE. COMPLIED WITH EA 6-5450-136723; " NACELLES / PYLON - SB A310-54-2020 - NR 1 AND NR2 PYLON SPIGOT FITTING BORE CORROSION".

Part: PANEL — DAMAGED (CARGO BAY) · airframe 36,134 hrs · 16,502 cycles

BULK CARGO COMPARTMENT SIDE WALL PANEL 162 CW HAS MULTIPLE DENTS ON THE TOP SURFACE. FABRICATED NEW SIDEWALL PANEL 162 CW IAW DWG 25-005, REV "H" AND DWG 25-011, REV "C".

Part: FLOORBOARD — DAMAGED (ZONE 200) · airframe 36,134 hrs · 16,502 cycles

MAIN CABIN FLOORBOARD UPPER SKIN IS CRUSHED AND BROKEN FROM FRAME 60 TO FRAME 62, RBL 57 TO RBL 77. FABRICATED NEW FLOORBOARD 252 UF IAW DWG 25-005, REV "H".

Part: PANEL — CORRODED (ZONE 100) · corrosion level 2 · airframe 36,134 hrs · 16,502 cycles

BULK CARGO COMPARTMENT SIDEWALL PANEL 162 AW BOTTOM SKIN IS CORRODED AND BOTH SKINS ARE DISBONDED. FABRICATED NEW SIDEWALL PANEL 162 AW IAW DWG 25-005, REV "H" AND DWG 25-011, REV "C".

Part: SIDEWALL PANEL — DENTED (ZONE 100) · airframe 36,134 hrs · 16,502 cycles

BULK CARGP COMPARTMENT SIDEWALL PANEL 161 AW HAS MULTIPLE DENTS AND IS PUNCTURED ON THE FRONT. FABRICATED NEW SIDEWALL PANEL 161 AWIAW FEDEX DWG 25-005, REV "H" AND FEDEX DWG 25-011, REV "C".

Part: FLOOR PANEL — DENTED (ZONE 100) · airframe 36,134 hrs · 16,502 cycles

BULK CARGO COMPARTMENT FLOOR PANEL 162 HF TOP SURFACE IS DENTED AND CRUSHED. FABRICATED NEW FLOOR PANEL 162 HF IAW DWG 25-005, REV "H" AND DWG 25-011, REV "C".

Part: FLOORBOARD — DAMAGED (ZONE 100) · airframe 36,134 hrs · 16,502 cycles

AFT CARGO FLOORBOARD 151 FF HAS A BROKEN CORNER. FABRICATED NEW FLOORBOARD 151 FF IAW DWG 25-005, REV "H".

Part: FLOORBOARD — DAMAGED (ZONE 200) · airframe 36,134 hrs · 16,502 cycles

MAIN DECK FLOORBOARD BETWEEN FRAME 53 AND FRAME 54, LBL 78 AND LBL 98 IS BROKEN OFF AT THE AFT END. FABRICATED NEW FLOOR PANEL IAW DWG 25-005, REV "H".

Part: FLOORBOARD — TORN (ZONE 100) · airframe 36,134 hrs · 16,502 cycles

FWD CARGO COMPARTMENT FLOORBOARD 132 QF IS TORN AND PUNCTURED. FABRICATED NEW FLOORBOARD 132 QF IAW DWG 25-005, REV "H".

Part: ATTACH FITTING — CORRODED (MLG ACTUATOR) · airframe 36,134 hrs · 16,502 cycles

LT MLG DOOR ACTUATOR ATTACH FITTING IS CORRODED. REMOVED WORN JACK FITTING REF SRM 51-40-21, PAPR 7. INSTALLED NEW JACK FITTING REF SRM 51-40-21, PAPR 7. ALODINED AND PRIMED TOP SKIN REF SRM 51-21-10. APPLIED TOP COAT REF SRM 51-21-11.

Part: SKIN — CORRODED (FUSELAGE) · airframe 36,134 hrs · 16,502 cycles

FUSELAGE INTERNAL STRUCTURE FWD CARGO COMPARTMENT AFT DOOR CUTOUT AT THE LOWER CORNER, THE SKIN IS CORRODED FROM FRAME 26 TO FRAME 27, STR 25R TO STR 26R.

Part: FLOOR PANEL — CRACKED (ZONE 200) · airframe 36,134 hrs · 16,502 cycles

MAIN CABIN FLOOR PANEL 242 EK IS CRACKED. FABRICATED NEW FLOOR PANEL 242 EK IAW DWG SRZ 25-005, REV "H".

Part: FLOOR PANEL — CRACKED (ZONE 200) · airframe 36,134 hrs · 16,502 cycles

MAIN CABIN FLOOR PANEL 242 ZJ IS CRACKED.

Part: FLOOR PANEL — CRACKED (ZONE 200) · airframe 36,134 hrs · 16,502 cycles

MAIN CABIN FLOOR PANEL 252 GF IS CRACKED. FABRICATED NEW FLOOR PANEL 252 GF IAW DWG SRZ 25-005, REV "H".

Part: FLOOR PANEL — CRACKED (ZONE 200) · airframe 36,134 hrs · 16,502 cycles

MAIN CABIN FLOOR PANEL 252 BF IS CRACKED. FABRICATED NEW FLOOR PANEL 252 BF IAW DWG SRZ 25-005, REV "H".

Part: FLOOR PANEL — CRACKED (ZONE 100) · airframe 36,134 hrs · 16,502 cycles

MAIN CABIN FLOOR PANEL 232 SF IS CRACKED. FABRICATED NEW FLOOR PANEL 232 SF IAW DWG SRZ 25-005, REV "H".

Part: FLOOR PANEL — CRACKED (ZONE 200) · airframe 36,134 hrs · 16,502 cycles

MAIN CABIN FLOOR PANEL 232 YH IS CRACKED. FABRICATED NEW FLOOR PANEL 232 YH IAW DWG SRZ 25-005, REV "H".

Part: FLOOR PANEL — DELAMINATED (ZONE 100) · airframe 36,134 hrs · 16,502 cycles

MLG BAY CTR OTBD FLOOR PANEL IS DELAMINATED AT THE EDGE. REMOVED OLD PANEL 148 BF REF SRM 51-40-21, PARA 5. FABBED NEW MLG OTBD FLOOR PANEL 148 BF IAW DWG SRZ 25-005, REV. INSTALLED NEW FLOOR PANEL 148 BF REF SRM 51-40-21, PARA 5.

Part: FLOOR PANEL — CRACKED (ZONE 200) · airframe 36,134 hrs · 16,502 cycles

MAIN CABIN FLOOR PANEL 252 PH IS CRACKED. FABRICATED NEW FLOOR PANEL 252 PH IAW DWG SRZ 25-005, REV "H".

Part: FLOOR PANEL — CRACKED (ZONE 200) · airframe 36,134 hrs · 16,502 cycles

MAIN CABIN FLOOR PANEL 252 UH IS CRACKED. FABRICATED NEW FLOOR PANEL 252 UH IAW DWG SRZ 25-005, REV "H".

Part: FLOOR PANEL — CRACKED (ZONE 200) · airframe 36,134 hrs · 16,502 cycles

MAIN CABIN FLOOR PANEL 231 AH IS CRACKED. FABRICATED NEW FLOOR PANEL 231 AH IAW DWG SRZ 25-005, REV "H".

Part: FLOOR PANEL — CRACKED (ZONE 200) · airframe 36,134 hrs · 16,502 cycles

MAIN CABIN FLOOR PANEL 242 QJ IS CRACKED. FABRICATED NEW FLOOR PANEL 242 QJ IAW DWG SRZ 25-005, REV "H".

Part: FLOOR PANEL — CRACKED (ZONE 100) · airframe 36,134 hrs · 16,502 cycles

MAIN CABIN FLOOR PANEL 232 XH IS CRACKED. FABRICATED NEW FLOOR PANEL 232 XH IAW DWG SRZ 25-005, REV "H".

Part: FLOOR PANEL — CRACKED (ZONE 100) · airframe 36,134 hrs · 16,502 cycles

MAIN CABIN FLOOR PANEL 232 LT IS CRACKED. FABRICATED NEW FLOOR PANEL 232 LH IAW DWG SRZ 25-005, REV "H".

Part: FLOOR PANEL — CRACKED (ZONE 200) · airframe 36,134 hrs · 16,502 cycles

MAIN CABIN FLOOR PANEL 242 UJ IS CRACKED. FABRICATED NEW FLOOR PANEL 242 UJ IAW DWG SRZ 25-005, REV "H".

Part: FLOOR PANEL — CRACKED (ZONE 200) · airframe 36,134 hrs · 16,502 cycles

MAIN CABIN FLOOR PANEL 231 BH IS CRACKED. FABRICATED NEW FLOOR PANEL 231 BH IAW DWG SRZ 25-005, REV "H".

Part: RIB — DAMAGED (NR 2 PYLON) · airframe 35,947 hrs · 16,369 cycles

DURING EO 6-5450-7-5003A P2 COMPLIANCE A .375" CRACK WAS FOUND PROPAGATING FROM A SCREW HOLE AT RIB NR 8 ON THE OTBD SIDE OF THE NR 2 PYLON. REPAIRED SRM 54-51-31 AND EO 6-5450-7-5003A P2 INSTRUCTIONS.

Part: TRANSDUCER — FALSE ACTIVATION (ANTI SKID SYS) · airframe 35,723 hrs · 16,208 cycles

AFTER T/O GOT A ANTI-SKID ECAM FAULT. ECAM DIRECTED TURNING BRAKE ANTI SKID TO ALTN OFF. INFLT RESELECTED BRAKE /ANTI SKID TO NORM ON. NO FURTHER FAULTS NOTED. ON LANDING ROLLOUT HAD NO APPARENT BRAKING WITH LT BRAKE/RUDDER PEDAL. SELECTED ALTN OFF AND BRAKING RETURNED. R & R LT NORMAL BRAKE MASTER VALVE 89GG IAW AMM 32-42-19, LEAK CHECKED GOOD. R & R LT NORMAL BRAKE PRESSURE TRANSDUCERS 91GG AND 93GG IAW AMM 32-42-21, LEAK CHECKED GOOD. TAXI TESTED ACFT.

Part: SLIDE — FAILED (ZONE 800) · airframe 35,723 hrs · 16,208 cycles

AT BLOCK IN JUMP SEATER OPENED R1 DOOR HANDLE FROM INSIDE WITH SLIDE ARMED. SLIDE DID NOT DEPLOY BUT REAR COVER RELEASE CABLE SNAPPED. R & R R1 ESCAPE SLIDE IAW AMM 25-61-21, DISARM PIN REMOVED. R & R R1 DOOR EMERGENCY OPERATION DAMPER IAW 25-10-14, DOOR WARNING SYS OPS CHECKED, OK. (NO COMPONENT FAILURE, PERSONNEL ERROR)

Part: HOUSING — DAMAGED (WARNING SWITCH) · airframe 34,033 hrs · 15,398 cycles

AFT CARGO DOOR OPEN LIGHT IN FLIGHT. RETURNED TO KUL. VISUALLY CHECKED CLOSED AND LOCKED. VERIFIED INTEGRITY OF AFT CARGO DOOR CLOSING AND LOCKING MECHANISM, ALL SATISFACTORY. SUSPECT FAULTY SWITCH CAUSING ERRONEOUS DOOR INDICATION. APPLIED MEL 52-71-01. FOUND AFT CARGO DOOR LIMIT SW 32WS HOUSING BROKEN. REMOVED AND REPLACED AFT CARGO DOOR LIMIT SW 32WS AND HOUSING.

Part: SWITCH — FAULTY (AFT CARGO DOOR) · airframe 34,033 hrs · 15,398 cycles

AFT CARGO DOOR OPEN LIGHT IN FLIGHT. RETURNED TO KUL. VISUALLY CHECKED CLOSED AND LOCKED. VERIFIED INTEGRITY OF AFT CARGO DOOR CLOSING AND LOCKING MECHANISM. ALL SATISFACTORY. SUSPECT FAULTY MICROSWITCH CAUSING ERRONEOUS DOOR INDICATION. APPLIED MEL 52-71-01.

Part: SWITCH — DAMAGED (CARGO DOOR) · airframe 34,033 hrs · 15,398 cycles

AFT CARGO DOOR OPEN LIGHT IN FLIGHT. ACN RELEASED FOR SERVICE PER MEL/CDL, 52-71-01 CARRIED OUT OVERWEIGHT LANDING INSPECTION PER AMM 05-51-11-0, NO ABNORMALITIES NOTED. OLD CONTROL NUMBER: , REMOVED AND REPLACED AFT CARGO DOOR LIMIT SWITCH 32WS AND HOUSING AS PER MM 52-71-11-4. PERFORMED SWITCH ADJUSTMENT/TEST AS PER MM 52-71-11-5, NORMAL. REMOVED PLACARD AND CLEARED MEL.

Part: SUPPORT BRACKET — CORRODED (RT WING) · corrosion level 2 · airframe 33,700 hrs · 15,236 cycles

RT WING, REAR SPAR RIB 1-RIB-4, HYD TUBE SUPPORT BRACKET WITH INNER-GRANULAR CORROSION. REMOVED THE CORRODED TUBE SUPPORT BRACKET. FABRICATED A NEW BRACKET PER AIRCRAFT DRAWING 25 A935-40675. INSTALLED THE NEW BRACKET AND HYD TUBES PER AMM 20-21-12-0 AND AMM 20-23-11-0. PERFORMED LEAK CHECK PER AMM 29-00-00-6. NO LEAK FOUND.

Part: SUPPORT BRACKET — CORRODED (LT WING) · corrosion level 2 · airframe 33,700 hrs · 15,236 cycles

LT WING, REAR SPAR SURFACE 1, RIB 4, HYD TUBE SUPPORT BRACKET WITH INNER- GRANULAR CORROSION (DELAMINATED). REMOVED THE CORRODED TUBE SUPPORT BRACKET. FABRICATED A NEW BRACKET PER AIRCRAFT DRAWING 25 A935-40675. INSTALLED THE NEW BRACKET AND HYD TUBES PER AMM 20-21-12-0 AND AMM 20-23-11-0. PERFORMED LEAK CHECK PER AMM 29-00-00-6. NO LEAK FOUND.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 33,700 hrs · 15,236 cycles

MAIN DECK FLOOR LEVEL FR 15 TO FR 19 Y450 FLOOR TRACK WITH EXFOLIATION CORROSION. REPLACED THE FLOOR TRACK PER SRM 51-40-21. RESTORED FINISH PER SRM 51-75-10. APPLIED CIC TO THE REWORKED AREA PER AMM 51-22-00-0. MINOR REPAIR AS PER GMM 6-2-100.

Part: FITTING — CORRODED (PAX DOOR HINGE) · airframe 33,700 hrs · 15,236 cycles

MAIN DECK RT FWD PAX/CREW DOOR LOWER HINGE ARM/FITTING WITH EXFOLIATION CORROSION. REPLACED RT FWD PAX/CREW DOOR LOWER CONNECTION LINK PER AMM 52-11-21/4.OPERATION TEST THE RT CREW DOOR PER AMM 52-11-21/4.TEST OK.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 33,700 hrs · 15,236 cycles

MAIN DECK FLOOR TRACK WITH EXFOLIATION CORROSION BETWEEN FR 15 TO FR 17 Y50. REPLACED THE FLOOR TRACK PER SRM51-40-21.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 33,700 hrs · 15,236 cycles

MAIN DECK FLOOR TRACK WITH EXFOLIATION CORROSION BETWEEN FR 15-FR 19 -Y1550. REPLACED THE FLOOR TRACK PER SRM51-40-21.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 33,700 hrs · 15,236 cycles

MAIN DECK FLOOR TRACK WITH EXFOLIATION CORROSION BET FR 15 TO FR 17 Y50. REPLACED THE FLOOR TRACK PER SRM51-40-21.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 33,700 hrs · 15,236 cycles

MAIN DECK FLOOR TRACK WITH EXFOLIATION CORROSION FR15 - FR17 -Y50. REPLACED THE FLOOR TRACK PER SRM 51-40-21.

Part: SEAT TRACK — CORRODED (ZONE 200) · airframe 33,700 hrs · 15,236 cycles

MAIN DECK FLOOR LEVEL COURIER COMPT TRACK BETWEEN FR 15A-FR 16A, -Y950 WITH EXFOLIATION CORROSION. REPLACED THE SEAT TRACK PER SRM 51-40-21 & DWG A53611640200. RESTORED FINISH PER SRM 51-75-10

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 33,700 hrs · 15,236 cycles

MAIN DECK FLOOR LEVEL COURIER COMPT TRACK BETWEEN FR 15A - FR 16A Y950 WITH EXFOLIATION CORROSION. REPLACED THE SEAT TRACK PER SRM 51-75-10.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 33,700 hrs · 15,236 cycles

MAIN DECK COURIER COMPT TRACK AT FLOOR LEVEL BETWEEN FR 16A-FR 19, Y1560 WITH EXFOLIATION CORROSION. REPLACED THE SEAT TRACK PER DWG A53610 798202 & SRM 51-40-21. RESTORED FINISH PER SRM 51-75-10.

Part: SEAT TRACK — CORRODED (ZONE 200) · airframe 33,700 hrs · 15,236 cycles

MAIN DECK FLOOR LEVEL COURIER COMPT TRACK BETWEEN FR 15A - FR 16A, -Y450 WITH EXFOLIATION CORROSION. REMOVED CORROSION PER SRM51-74-10.MATERIAL LOSS WITHIN LIMIT PER SRM53-10-16/103.

Part: PACKING — DAMAGED (CHARGE VALVE) · airframe 33,297 hrs · 15,067 cycles

LANDING GEAR WOULD NOT RETRACT AFTER TAKEOFF WITH BOTH SELECTOR. GEAR HANDLE WOULD NOT COME PASSED THE NORMAL POSITION. T/S FOUND PITCH DAMPER AIR CHARGE VALVE PACKING DAMAGED. REMOVED AND REPLACED PACKING AND SERVICING PITCH DAMPER WITH NITROGEN PER AMM 12-12-30-0. INSPECTED NOT LEAK, FOUND. A/C OK FOR SERVICE, NO FUTHER REPORTS.

Part: PITCH LINK — DAMAGED (MLG) · airframe 33,290 hrs · 15,064 cycles

LANDING GEAR WOULD NOT RETRACT AFTER TAKEOFF WITH BOTH SELECTOR. GEAR HANDLE WOULD NOT COME PASSED THE NORMAL POSITION. PRESSURE INDICATOR POP OUT. T/S IN PROGRAM. NEED PART. T/S FOUND PITCH DAMPER AIR CHARGE VALVE PACKING DAMAGED. REMOVED AND REPLACED PACKING AND SERVICING PITCH DAMPER WITH NITROGEN PER AMM 12-12-30-0. INSPECTED NOT LEAK FOUND. A/C OK FOR SERVICE.

Part: FLAP SYSTEM — MALFUNCTIONED (TE FLAPS) · airframe 33,213 hrs · 15,029 cycles

WHEN SELECTED FLAPS 15 ON APPROACH SFPI SHOWED FLAPS LIGHT AND FLAPS WOULD NOT EXTEND, RE-CYCLED FLAPS AND ON SECOND ATTEMPT FLAPS EXTENDS NORMALLY. PERFORMED WIRING CHECK HIGH SPEED SOL V/V, ENABLE V/V AND RETRACT SOL V/V ALL RESISTANCE VALUE WITHIN LIMIT. CHECKED BOTH TORQUE LIMIT ARE NO FAULTS NOTED, ALL SCREW JACK TORQUE LIMITER NO JAM NOTED. RAN NR 2 ENG AGAIN AND FLAP/SLAT SYS OPS CHECKED ALL IND SYS WORKS OK. CARRIED OUT BITE CHK OF SFCC NR1/NR 2, NO FAULT NOTED PER AMM 27-50-00-0/5, JRH CHAP 5.

Part: ACTUATOR — FAILED (NLG) · airframe 33,149 hrs · 15,004 cycles

AFTER TAKEOFF HAD NOSE LDG GEAR DOOR NOT CLOSED ANNUNCIATION ON ECAM. BOTH FWD LDG GEAR INDICATOR AND OVERHEAD INDICATOR SHOWED AMBER NOSE DOOR ANNUNCIATION, BOTH SYSTEM 1 AND 2. R AND I LT NLG DOOR ACTUATOR PER MM 32-31-16-4 AND DOOR OPS CHK PER MM 32-31-00 AND LEAK CHK OK. A/C OK FOR SERVICE.

Part: COMPUTER — FAILED (TE FLAPS) · airframe 31,766 hrs · 14,370 cycles

FLAPS STUCK AT 20 DEG/20 DEG DURING EMERG CHKLIST. FIRST STUCK AT 20DEG/15DEG WITH BOTH SYS 1 AND SYS 2 LIGHT ON. CHCKD FAULT CODE ON SFCC FOUND HIGH SPEED PRESS SWITCH ON NR 1 SFCC AND MAIN CONTROL VALVE ON NR 2 SFCC. CHECKED WIRE INTEGRITY AND PHYSICAL CONDITION OF PRESS SWITCH AND MAIN CONTROL VALVE, NO DEFECT NOTED. FURTHER VISUAL INSPECTION FOUND RT TORQUE LIMITER POP-OUT AND NO ENOUGH LUBRICATION ON FLAP SCREW JACK. PROPERLY LUBRICATED AND SERVICED GEAR BOXES PER MM27-50-00-3 AND REPLACED BOTH SFCC FOR PRECATIONARY PER MM27-51-18. RAN ENGINE PER A310-JRH AND PERFORMED FLAPS OPERATIONAL CHK SEVERAL TIMES, SATISFACTORY AND NO FAULT FOUND.

Part: HYDRAULIC SYSTEM — LEAKING (YELLOW SYSTEM) · airframe 31,129 hrs · 14,084 cycles

CLIMBING FROM 8000' TO 14000', YELLOW HYDRAULIC LOW PRESSURE INDICATION FOLLOWED BY LOSS OF YELLOW SYSTEM FLUID. FOLLOWED QRH PROCEDURES AND RETURNED TO BASE. PART NIS. ORDERED NEW POWER CONTROL UNIT FROM SFS CANNED FILTER ASSY FROM NEW POWER CONTROL UNIT AND INSTALLED SAME. RAN BOTH ENGINES PER A310 JRH. NO LEAKS NOTED.

Part: ENGINE — UNKNOWN (NR 2) · airframe 30,845 hrs · 13,957 cycles

NR 2 ENG HI OIL TEMP ALERT TEMP CLIMB DURING CLIMB AND CONTINUE TO CLIMB ABOVE SHUT DOWN LIMITS. ENG SHUT DOWN AT THAT POINT, MAX OIL TEMP 190 DEG C. T/S IN PROGRESS. REPLACED THE FUEL /OIL COOLER, THE FUEL INTI-ICE VALVE, THE OIL TEMP SENSOR AND THE DIGITAL TO ANALOG CONVERTER, RAN THE ENGINE , TEMP NOW NORMAL.

Part: SKIN — CORRODED (FUSELAGE) · airframe 30,444 hrs · 13,738 cycles

A/C BAY FWD RIGHT SIDE FROM FS 40-42 FROM STRINGER 48R TO 43R STRUCTURE HAS 40 SQ IN OF CORROSION REF N0059. REMOVED CORROSION IAW A310-200 SRM 51-74-10 CHECKED LIMITS FOUND 1 AREA ON FUSELAGE SKIN BETWEEN FS 40-42 BETWEEN STRGS 42R AND 43R OUT OF LIMITS. REPAIRED IAW EA 6-5315-98992.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 30,444 hrs · 13,738 cycles

RT A/C BAY STRG 44 HAS NUMEROUS SPOTS OF CORROSION AROUND RIVETS, SIDE TOP OF VERTICAL FLANGE BETWEEN FS 44-47, REF N00729. REMOVED CORROSION IAW A310-200 SRM 51-74-10 FOUND 2 AREAS OUT OF LIMITS. REPAIRED IAW EA 6-5315-98992.

Part: SKIN — CORRODED (BS 37-45) · airframe 30,444 hrs · 13,738 cycles

RT A/C BAY BETWEEN FS 44-45 BETWEEN STR 37-45 HAS NUMEROUS SPOTS OF CORROSION ON SKIN AROUND RIVETS. REF. N00728. REMOVED CORROSION IAW A310-200 SRM 51-74-10. FOUND 1 AREA OF SKIN BETWEEN FS 44 AND 45 TO BE OUT OF LIMITS. REPAIRED IAW EA 6-5315-98992.

Part: REPAIR — UNKNOWN · airframe 30,444 hrs · 13,738 cycles

AT FS 83 STRINGER 35L REPAIR REQUIRES EVALUATION FOR MAJOR MINOR DETERMINATION AND IF REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. REPAIR WAS DETERMINED NOT IN COMPLIANCE WITH APPROVED DATA DUE TO INCORRECT REPAIR MATERIAL. REMOVED EXISTING REPAIR AND REPAIRED IAW A310-200 SRM 53-10-12 FIG 228 SHT 1 AND A310-200 SRM 53-10-13. RESTORED PROTECTIVE COATING IAW A310-200 SRM 51-75-10.

Part: SKIN — CORRODED (FUSELAGE) · airframe 30,444 hrs · 13,738 cycles

A/C BAY RIGHT SIDE FS 42-43 STRINGERS 40R THRU 48R STRUCTURE HAS 35 SQ IN OF CORROSION INCLUDING CUTOUT FOR REFUEL DEFUEL PNL. REF N00594. REMOVED CORROSION IAW A310-200 SRM 51-74-10. FOUND 1 AREA OUT OF LIMITS. REPAIRED IAW EA 6-5315-98992.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 30,444 hrs · 13,738 cycles

RT A/C BAY STRG 40 BETWEEN FS 44-47 HAS NUMEROUS SPOTS OF CORROSION ON SKIN AROUND RIVETS AND ON TOP OF VERTICAL FLANGE REF N00733. REMOVED CORROSION IAW A310-200 SRM 51-74-10. FOUND 1 AREA OUT OF LIMITS, REPAIRED IAW EA 6-5315-98992.

Part: PRESSURE PANEL — CORRODED (MLG WW) · airframe 30,444 hrs · 13,738 cycles

FOUND MAIN WHEEL WELL LT SIDE FS 48-54 WEB HAS 50 SQ IN OF CORROSION. REMOVED CORROSION IAW A310-200 SRM 51-74-10 FOUND 3 SPOTS OUT OF LIMITS. REPAIRED IAW EA 6-5315-98983.

Part: BULKHEAD — CORRODED (FUSELAGE) · airframe 30,444 hrs · 13,738 cycles

REAR PRESSURE BULKHEAD INTERIOR SIDE STRG 27 TO 27 FS 80/82 HAS 6 AREAS OF CORROSION AT APPROX STRG 27R, 33-34R, 43R AND 23L AND 31R ON THE INNER RIM ANGLE. REMOVED CORROSION IAW A310-200 SRM 51-74-10. FOUND ALL AREAS OUT OF LIMITS. REPAIRED IAW EA 6-5330-97550.

Part: SKIN — CORRODED (FUSELAGE) · airframe 30,444 hrs · 13,738 cycles

BELLY OF A/C EXTERIOR SKIN AT FS 82 20 SQ IN OF CORROSION AROUND FASTENER. REMOVED CORROSION IAW A310-200 SRM 51-74-10 FOUND OUT OF LIMITS REPAIRED IAW EA 6- 5330-97550.

Part: SKIN — CORRODED (FUSELAGE) · airframe 30,444 hrs · 13,738 cycles

RT A/C BAY BETWEEN FS 43-44 FROM STRG 37 AND BETWEEN STRG 41 TO STRG 51 HAS NUMEROUS SPOTS OF CORROSION ON SKIN AROUND RIVETS FASTENERS ADJACENT AREAS. REMOVED CORROSION IAW A310-200 SRM FOUND 5 AREAS OUT OF LIMITS. REPAIRED IAW EA 6-5315-98992.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 30,444 hrs · 13,738 cycles

LT A/C BAY L-STR 40 HAS NUMEROUS SPOTS OF CORROSION ALONG RIVETED AREAS, TOP SIDE SKIN OF VERTICAL FLANGE BETWEEN FS 40, 41, 42, 43, 44, 45, 46, 47, 48. REMOVED CORROSION IAW A310-200 SRM 51-74-10, FOUND 1 AREA OUT OF LIMITS. REPAIRED 1 AREA 2 INCHES AFT OF FS 44 STR 40 LT IAW EA 6-5315-98983.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 30,444 hrs · 13,738 cycles

A/C BAY LT STR 42 AND STIFFENERS HAVE NUMEROUS SPOTS OF CORROSION ALONG RIVETED AREAS TOP SIDE SKIN OF VERTICAL FLANGE BETWEEN FR 39-42. REMOVED CORROSION IAW A310-200 SRM 51-74-10 FOUND 1EA AREA OUT OF LIMITS, 2 INCHES AFT OF FR 40/41 STR 42 LT REPAIRED IAW EA 6-5315-98983.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 30,444 hrs · 13,738 cycles

LT A/C BAY STR 48 HAS NUMEROUS SPOTS OF CORROSION ALONG RIVETED AREAS, TOP SIDE SKIN OF VERTICAL FLANGE BETWEEN FR 42, 43, 44. REMOVED CORROSION ON STR 48 LT IAW A310-200 SRM 51-74-10 FOUND 1EA AREA OUT OF LIMITS 3 INCHES FWD OF FR 42 STR 48 LT. COMPLIED WITH EA 6-5315-98983.

Part: KEELBEAM — CORRODED (FUSELAGE) · airframe 30,444 hrs · 13,738 cycles

FOUND WHEEL WELL AREA FS 48-49 INSIDE KEEL BEAM BOX STRINGER 53L HAS 32 EACH CORRODED RIVETS. REMOVED CORROSION IAW A310-200 SRM 51-74-10, FOUND 1 AREA OUT OF LIMITS IAW A310-200 SRM 53-10-00 FIG 103 TABLE 102. COMPLIED WITH EA 6-5315-98983.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 30,444 hrs · 13,738 cycles

A/C BAY LT STR 44 HAS NUMEROUS SPOTS OF CORROSION ALONG RIVETED AREA ON TOP SIDE SKIN OF VERTICAL FLANGE BETWEEN FS 39, 40, 41, 42, 43 AND 44. REMOVED CORROSION IAW A310-200 SRM 51-74-10. FOUND 2 AREAS OUT OF LIMITS IAW A310-200 SRM 53-10-00 FIG 103 TABLE 102. REPAIRED IAW EA 6-5315-98983.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 30,444 hrs · 13,738 cycles

LT A/C BAY STR 50 HAS NUMEROUS SPOTS OF CORROSION ALONG RIVETED FASTENER AREA TOP SIDE SKIN OF VERTICAL FLANGE BETWEEN FR 39, 40, 41, 42, 43 AND 44. REMOVED CORROSION IAW A310-200 SRM 51-74-10. FOUND 4 EACH AREAS OUT OF LIMITS PER A310-200 SRM 53-10-00 FIG 103 TABLE 102. REPAIRED IAW EA 6-5315-98983 PART 1.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 30,444 hrs · 13,738 cycles

A/C BAY LT STR 47 HAS NUMEROUS AREAS OF CORROSION ALONG RIVETED SURFACE, TOP SKIN AND VERTICAL FLANGE BETWEEN FR 39-44.5. REMOVED CORROSION IAW A310-200 SRM 51-74-10, FOUND 8EA AREAS OUT OF LIMITS. REPAIRED IAW EA 6-5315-98983.

Part: SKIN — CORRODED (FUSELAGE) · airframe 30,444 hrs · 13,738 cycles

A/C BAY LT AIR CONDITIONER CUTOUT HAS NUMEROUS SPOTS OF LIGHT CORROSION AROUND DOUBLER SKIN AND ADJACENT AREA BETWEEN FR 44-46. REMOVED CORROSION IAW A310-200 SRM 51-74-10 FOUND 1 AREA OUT OF LIMITS. REPAIRED IAW EA 6-5315-98983.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 30,444 hrs · 13,738 cycles

A/C BAY LEFT STR 41 HAS NUMEROUS AREAS OF CORROSION ALONG RIVETED AREA TOP SIDE OF VERTICAL FLANGE BETWEEN FR 39, 40, 41, 42, 43, 44. REMOVED CORROSION AT DISCREPANCY AREAS FOUND 1 EACH AREA OUT OF LIMITS 6 INCHES AFT OF FR 42 ON STR 41 LT REPAIRED IAW EA 6-5315-98983 PART 1.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 30,444 hrs · 13,738 cycles

LT A/C BAY STR 49 HAS NUMEROUS SPOTS OF CORROSION ALONG RIVETED AREAS, TOP/SIDE SKIN OF VERTICAL FLANGE BETWEEN FR 39-40/41-42-43-44 AS MARKED. REMOVED RIVETS AND BRACKETS TO ACCESS CORROSION PER A310 SRM 51-40-21, REMOVED CORROSION ON STRINGER 49 LT PER A310 SRM 51-74-10, MEASURE MAT'L LOSS, CHECKED LIMITS FOUND 1 SPOT OUT OF LIMITS AND ALL OTHER AREAS WITHIN LIMITS PER A310 SRM 53-10-00 FIG 103 TABLE 102. REPAIRED 1 SPOT LOCATION NR 1 DETAIL H PER FEDEX EA6-5315-98983, REINSTALLED ALL RIVETS AND BRACKETS PER A310 SRM 51-40-21, ALODINED, PRIMED AND TOP COATED ALL AREAS PER A310 SRM 51-75-10.

Part: DOUBLER — CORRODED (FUSELAGE) · airframe 30,444 hrs · 13,738 cycles

FRAME 17 LT SIDE TO FRAME 16A AT STR 42 INTERNAL DOUBLER HAS CORROSION. REMOVED CORROSION IAW A310-200 SRM 51-40-10, 1EA AREA FOUND TO BE WITHIN LIMITS IAW A310-200 SRM 53-10-00 FIG 102, 1EA AREA FOUND TO OUT OF LIMITS IAW A310-200 SRM 53-10-00 FIG 102 REPAIRED IAW EA 6-5310-99022 PART 1.

Part: STRINGER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 30,444 hrs · 13,738 cycles

LEFT A/C BAY L-STR 44 HAS NUMEROUS SPOTS OF CORROSION ALONG RIVETED AREAS, TOP/SIDE SKIN OF VERTICAL FLANGE AS MARKED BETWEEN FR44-45-46-47. REMOVED AND REINSTALLED FASTENERS TO ACCESS CORROSION PER SRM 51-40-21. REMOVED CORROSION PER A310 SRM 51-74-40 MEASURED MATERIAL LOSS, CHECKED LIMITS, FOUND 8 EACH AREAS OUT OF LIMITS AND ALL OTHER AREAS WITHIN LIMITS PER A310 SRM 53-10-00 FIG 103 TABLE 102, FABRICATED 1 EACH ANGLE DUE TO STRINGER REPAIR PER DRAWING A53410162, REPAIRED STRINGER 44 LT WITH 2 EACH REPAIR ANGLES FOR LOCATION 20 DETAIL Q AND 21, 22, 23, 24, 25, 26 AND 27 DETAILS R, S, T AND U PER FEDEX EA6-5315-98983, ALODINED, PRIMED AND TOP COATED PER A310 SRM 51-75-10.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 30,444 hrs · 13,738 cycles

A/C BAY LT STR 41 HAS NUMEROUS SPOTS OF CORROSION ALONG RIVETED AREAS TOP SIDE SKIN OF VERTICAL FLANGE AS MARKED ON BETWEEN FR 44-45-46-47 -2 EA ELEC CLAMP BRACKET BETWEEN FR 46-47. REMOVED AND REINSTALLED FASTENERS TO ACCESS CORROSION REMOVAL PER A310 SRM 51-40-21. REMOVED CORROSION ON STRINGER 41 LT PER A310 SRM 51-74-10, MEASURED MATERIAL LOSS, CHECKED LIMITS FOUND 1 EACH AREA OUT OF LIMITS BETWEEN FR44 & FR45 ON STRINGER 41 LT ALL OTHER AREAS WITHIN LIMITS PER A310 SRM 53-10-00 FIG 103 TABLE 102. REPAIRED STRINGER 41 LT AT LOCATION 18 DETAIL O. ALODINED, PRIMED AND TOP COATED ALL AREAS PER A310 SRM 51-75-10 AND FEDEX EA 6-5315-98983 FOR 1 REPAIR.

Part: KEELBEAM — CORRODED (FUSELAGE) · airframe 30,444 hrs · 13,738 cycles

LT AC BAY STR 51 SIDE OF KEEL BEAM BETWEEN FR 39-40/41-42-43-44 HAS NUMEROUS SPOTS OF CORROSION AS MARKED. REMOVED & REINSTALLED FASTENERS TO ACCESS CORROSION. REMOVAL PER A310 SRM 51-42-21. REMOVED CORROSION ON STR 51 LT & WEB PER A310 SRM 51-74-10, MEASURED MAT'L LOSS, CHECKED LIMITS FOUND 3 EACH AREAS OUT OF LIMITS & ALL OTHER AREAS WITHIN LIMIT PER A310 SRM 53-10-00 FIG 103 TABLE 102, REPAIRED 1 EACH AREA ON WEB BETWEEN FRAMES 40/41 AND 42 PER A310 SRM 51-71-30, REPAIRED 2EA AREAS AT LOCATION 5 DETAIL E & 6 DETAIL F TABLE 3 PER FEDEX EA6-5315-98983, FABRICATED NEW DOUBLER ANGLE BRACKET DUE TO WEB REPAIR PER DRAWING A53811458. ALODINED, PRIMED & TOP COATED ALL AREAS PER A310 SRM 51-75-10.

Part: SKIN — CORRODED (FUSELAGE) · airframe 30,444 hrs · 13,738 cycles

FWD OF LT AIR COND CUT OUT EXTERNAL DOUBLER HAS NUMEROUS SPOTS OF CORROSION ON SKIN AND AROUND FASTENERS. REMOVED CORROSION IAW A310-200SRM 51-74-10 ALL AREAS FOUND TO BE WITHIN LIMITS IAW A310-200 SRM 53-15-12 PROTECTED ALL AREAS IAW A310-200 SRM 51-75-10.

Part: ATTACH FITTING — CORRODED (VERTICAL STAB) · airframe 30,444 hrs · 13,738 cycles

VERTICAL LEADING EDGE LOWER LEFT ATTACH FITTING HAS CORROSION REF N00327. REPAIRED FITTING IAW EA 6-5530-99020.

Part: SKIN — CORRODED (FUSELAGE) · airframe 30,444 hrs · 13,738 cycles

LT A/C BAY BETWEEN FS 39-41 HAS NUMEROUS SPOTS OF CORROSION ON SKIN FS STRG 37- 47. REMOVED CORROSION IAW A310-200 SRM 51-74-10, ALL AREAS WITHIN LIMITS IAW A310-200 SRM 53-15-12. ALODINED PRIMED AND TOP COATED ALL AREAS IAW A310-200 SRM 51-75-10.

Part: REPAIR — UNKNOWN · airframe 30,444 hrs · 13,738 cycles

REPAIR LOC, LT HORIZ STAB REQUIRES EVALUATION FOR MAJOR/MINOR DETERMINATION AND IF REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. REPAIRED IAW EA 6-5510-97564 DUE TO EXISTING REPAIR MATERIAL NOT PER A310-200 55-12-12.

Part: FLOOR SUPPORT — CRACKED (FUSELAGE) · airframe 30,444 hrs · 13,738 cycles

FOUND BULK CARGO BAY LEFT SIDE FLOOR SUPPORT BETWEEN FS 65 AND 66 IS CRACKED. REMOVED AND REPLACED SUPPORT SECTION IAW A310-200 SRM 51-72-10.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 30,444 hrs · 13,738 cycles

BULK CARGO FLOOR STRUCTURE BEAM AT FR. 66 CENTER TOP BEAM HAS EXFOLIATED CORROSION MEASURING 2 INCH BY 3 IN. REMOVED AND REPLACED FLOORBEAM IAW A310-200 SRM 51-72-10

Part: SKIN — CORRODED (RT WING) · airframe 30,444 hrs · 13,738 cycles

FOUND RIGHT WING T/E LOWER SKIN AT T/E OF NR 2 PYLON HAS 3 AREAS OF EXFOLIATED CORROSION. COMPLIED WITH EA 6-5730-99016 PART 1.

Part: FRAME — CORRODED (FUSELAGE) · airframe 30,444 hrs · 13,738 cycles

FOUND NOSE LANDING GEAR WHEEL WELL FWD WALL HAS NUMEROUS SPOTS OF CORROSION ON FR 11. COMPLIED WITH EA 6-5310-97511 PART 1 AND PART 2.

Part: STRUCTURE — DAMAGED (UNKNOWN) · airframe 30,444 hrs · 13,738 cycles

FOUND VERTICAL LEADING EDGE RIGHT SIDE ATTACH LANDING HAS ELONGATED FASTENER HOLE AT APPROXIMATELY RIB 14. COMPLIED WITH EA 6-5530-97607 PART 1.

Part: REPAIR — UNKNOWN · airframe 30,444 hrs · 13,738 cycles

REPAIR LOC, AT FS 87 STRG 34R REQUIRES EVALUATION FOR MAJOR/MINOR DETERMINATION AND IF REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. COMPLIED WITH EA 6-5330-97506 PART 1.

Part: REPAIR — UNKNOWN · airframe 30,444 hrs · 13,738 cycles

REPAIR LOC, ON R1 DOOR UPPER EDGE REQUIRES EVALUATION FOR MAJOR/MINOR DETERMINATION AND IF REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. COMPLIED WITH EA 6-5210-97507.

Part: SKIN — CORRODED (FUSELAGE) · airframe 30,444 hrs · 13,738 cycles

RT A/C BAY BETWEEN FS 45-46 BETWEEN STRG 37- 45 HAS NUMEROUS SPOTS OF CORROSION ON SKIN AROUND RIVETS FASTENERS AND SIDE OF 3 ANGLE WEB. REMOVED CORROSION IAW A310-200 SRM 51-74-10 MATERIAL LOSS WITHIN LIMITS EXCEPT 1. PICKUP ANGLE IAW A310-200 SRM 310-200 53-10-00. REMOVED AND REPLACED ANGLE IAW A310-200 SRM 51-40-21.

Part: REPAIR — UNKNOWN · airframe 30,444 hrs · 13,738 cycles

REPAIR LOC, ON LT O/B FLAP UPPER SURFACE 48 INCH FROM I/B END REQUIRES EVALUATION FOR MAJOR/MINOR DETERMINATION AND IF REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. COMPLIED WITH EA 6-5750-97513 PART 1.

Part: ACCESS PANEL — DAMAGED (VERTICAL STAB) · airframe 30,444 hrs · 13,738 cycles

VERTICAL STAB L/E FRONT SPAR ACCESS PNL ON RT SIDE HAS 2 HOLES DOUBLE DRILLED. COMPLIED WITH EA 6-5530-97607 PART 1.

Part: SKIN — CORRODED (FUSELAGE) · airframe 30,444 hrs · 13,738 cycles

BELLY OF A/C EXTERIOR SKIN FROM FS 86 TO 90 HAS 25 SQ IN OF CORROSION AROUND FASTENERS. REMOVED CORROSION IAW A310-200 SRM 51-74-10 MATERIAL WITHIN LIMITS IAW A310-200 SRM 1. AREA OUT OF LIMITS IAW SRM A310-200 53-10-00 NOTED AS NR 1 STEP 5 OF JPF. REPAIRED AREA IAW A310-200 SRM 53-10-12.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 30,444 hrs · 13,738 cycles

BULK CARGO FLOOR LEVEL BETWEEN FR 63 AND 64 LEFT SIDE FLOORBOARD SUPPORT ANGLE HAS 2 SQ INCH OF CORROSION AROUND 2EA HOLES. REMOVED AND REPLACED DAMAGED ANGLE IAW A310-200 SRM 51-72-10 AND 51-40-21.

Part: ATTACH ANGLE — CORRODED (VERTICAL STAB) · airframe 30,444 hrs · 13,738 cycles

UPPER FUSELAGE RT FWD ATTACH ANGLE FOE DORSAL FIN HAS CORROSION. REMOVED AND REPLACED ANGLE IAW A310-200 SRM 51-72-10 AND A310-200 SRM 51-40-21.

Part: ATTACH ANGLE — CORRODED (VERTICAL STAB) · airframe 30,444 hrs · 13,738 cycles

UPPER FUSELAGE RT FWD ATTACH ANGLE FOR DORSAL FIN HAS CORROSION. REMOVED AND REPLACED ATTACH ANGLE IAW A310-200 SRM 51-72-10 AND A310-200 SRM 51-40-21.

Part: REPAIR — DENTED (RT WING) · airframe 30,444 hrs · 13,738 cycles

TWO FILLER REPAIRS LOCATED ON RT WING NR 1 SLAT L/E REQUIRES EVALUATION. REMOVED DENT'S FILLER REPAIRED DENTS IAW A310-200 SRM 57-40-00 PG 201 PG 216 AND A310-200 SRM 51-73-10 PARA C.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 30,444 hrs · 13,738 cycles

BULK CARGO FLOOR LEVEL BETWEEN FR 63 AND 64 LEFT SIDE FLOORBOARD SUPPORT ANGLE HAS 2 SQ INCH OF CORROSION AROUND 2EA HOLES. REMOVED AND REPLACED DAMAGED ANGLE IAW A310-200 SRM 51-72-10 AND 51-40-21.

Part: SUPPORT BRACKET — CORRODED (FUSELAGE) · airframe 30,444 hrs · 13,738 cycles

A/C BAY AIR CON CUTOUT AT KEEL BEAM WALL 1AE, SUPPORT STRUT BRACKET HAS EXFOLIATION ON LT SIDE OF BAY. REMOVED AND REPLACED BRACKET IAW A310-200 SRM 51-72-10.

Part: FRAME — CORRODED (FUSELAGE) · airframe 30,444 hrs · 13,738 cycles

BULK CARGO FLOOR LEVEL RIGHT SIDE AT FRAME 67 ANGLE HAS 1 EACH AREA OF CORROSION. REMOVED AND REPLACED IAW A310-200 SRM 51-72-10.

Part: SUPPORT — CORRODED (FUSELAGE) · airframe 30,444 hrs · 13,738 cycles

REAR FUSELAGE ZONE 312 FR 84 UPPER SUPPORT HAS CORRSION REF N00639. REMOVED CROSS STUT, REPLACED WITH NEW CROSS STRUT P/N A539884242500 IAW A310-200 SRM 51-40-21.

Part: REPAIR — UNKNOWN · airframe 30,444 hrs · 13,738 cycles

THREE REPAIRS LOCATED ON LEFT I/B FLAP UPPER SURFACE T/E REQUIRES EVALUATION FOR MAJOR/MINOR CLASSIFICATION AND APPROVED DATA REF BN00770. REPAIR IAW EA 6-5750-97510.

Part: ANGLE — CORRODED (L2 DOOR) · airframe 30,444 hrs · 13,738 cycles

UPON REMOVAL OF L2 DOOR FOR EO 6-5310-7-3318 FOUND UPPER ANGLE IN MIDDLE UPPER END INTERIOR SIDE HAS CORROSION. REMOVED OLD PROFILE (OUT OF LIMITS) AND REPLACED IAW A310-200 SRM 51-72-10.

Part: FITTING — CORRODED (FUSELAGE) · airframe 30,444 hrs · 13,738 cycles

LEFT A/C BAY FR 46 HAS NUMEROUS SPOTS OF CORROSION ON FWD & AFT FACE FITTING AND DOUBLE BETWEEN STR 37-45 AND LT CORROSION ON ANGLE BRACKET BETWEEN STR 51-52 REF N00679. REMOVED CORROSION FROM FR 46 AREA AND SPLICE ANGLE, FR46 WITHIN LIMITS AND SPLICE ANGLE OUT OF LIMITS IAW A310-200 53-10-00 FIG 103 & TABLE 102. REPLACED SPLICE ANGLE IAW A310-200 SRM 51-75-10.

Part: SKIN — DELAMINATED (T/E FLAP) · airframe 30,444 hrs · 13,738 cycles

LT OB FLAP HAS 10 OF DELAMINATION UPPER SIDE TE OB END REF N00478. REPAIRED LT OB FLAP UPPER SKIN IAW A310-200 SRM 57-53-12 REPAIR NR 11.

Part: ATTACH FITTING — CORRODED (FUSELAGE) · airframe 30,444 hrs · 13,738 cycles

UPPER FUSELAGE VERTICAL T/E ACCESS PANEL ATTACHMENT STRUCTURE HAS CORROSION AT 4 EA LOCATION LT SIDE REF N00745. EXFOLIATED CORROSION BEYOND LIMITS ON STRIP AND CONNECTING PROFILE IAW SRM 55-30-00. REMOVED AND REPLACED STRIP AND PROFILE IAW SRM 51-72-10. AREAS ON PROFILE EDGE AND PROFILE L-SECTION WITHIN LIMITS OF SRM 55-30-00.

Part: REPAIR — UNKNOWN (TE FLAP) · airframe 30,444 hrs · 13,738 cycles

REPAIR LOCATED ON LEFT I/B FLAP LOWER SURFACE T/E REQUIRES EVALUATION FOR MAJOR MINOR DETERMINATION AND APPROVED DATA REF N00771. REPAIR WAS DETERMINED TO BE IAW EA 6-5750-97510.

Part: DOOR — CORRODED (CONTROL BOX) · airframe 30,444 hrs · 13,738 cycles

FWD PIT CARGO LOADING SYSTEM CONTROL BOX DOOR HAS CORROSION ON THE INNER ATTACH BRACKET FOR THE OPEN ASSIT ROD REF N00031. REMOVED CORROSION IAW A310-200 SRM 51-74-10, CHECKED LIMITS IAW SRM TABLE 102 CODE C AND FOUND BRACKET OUT OF LIMITS. REMOVED AND REPLACED BRACKET IAW A310-200 SRM 51-72-10.

Part: REPAIR — NONE (NR 2 SLAT) · airframe 30,444 hrs · 13,738 cycles

REPAIR LOCATED ON RT WING NR 2 SLAT L/E REQUIRES EVALUATION FOR MAJOR/MINOR DETERMINATION AND IF REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. PREVIOUS INSTALLED REPAIR ON NR 2 SLAT L/E WAS DETERMINED TO BE COMPLIED WITH IAW EA 6-5743-94774 AND S00007 NOV 05.

Part: REGULATOR — OUT OF ADJUST (NR 1 OIL SYS) · airframe 30,424 hrs · 13,727 cycles

RTO DUE TO AMBER OIL PRESSURE HIGH LIGHT ON NR 1 ENG. SWAPED NR 1 AND 2 OIL SIGNAL COND. R & R NR 1 OIL PRESS SIGNAL CONDITIONER IAW MM 79-33-31 , RAN ENG - NO HELP OIL PRESS AT IDLE STILL 54 PSI. REINSTALLED ORIGIONAL. R & R NR 1 OIL PRESS TRANSMITTER IAW MM 79-33-11-4 03 - NO HELP. ADJUSTED NR 1 MAIN OIL PRESS REGULATOR IAW MM 71-00-00-5 03. RAN ENG NR 1, AFTER 5 MIN WARMUP PER MM, OIL PRESS AT IDLE 46PSI. ALL ENG RUNS PERFORMED IAW JRH CH 5A

Part: LANDING GEAR — MALFUNCTIONED (LEFT) · airframe 30,262 hrs · 13,631 cycles

AFTER TAKEOFF THE LEFT MAIN GEAR WAS A GOOD BIT SLOWER TO SHOW UP AND LOCKED AFTER THE GEAR WAS RETRACTED. WHILE THE NOSE GEAR AND RIGHT MAIN SHOWED UP AND LOCKED WITH LIGHTS OUT, THE LEFT MAIN HAD A AMBER DOOR LIGHT AND RED UNLOCK LIGHT ILLUMINATED. THERE WAS ALSO A ECAM WARNING ON THE LEFT ECAM SAYING LEFT MAIN NOT UP AND LOCKED. AFTER ABOUT 5 TO 7 SECONDS THE LIGHTS ON THE FORWARD INDICATOR PANEL WENT OUT AND THE ECAM WARNING WENT AWAY. REMOVED AND REPLACED LEFT AND RIGHT MAIN GEAR SEQUENCE VALVES IN REFERENCE TO A310 M/M 32-31-37-4 OPS CHECKS GOOD IN REFERENCE TO A310 M/M 32-31-00-5.

Part: HMU — FAILED (NR 1 ENGINE) · airframe 30,022 hrs · 13,501 cycles

DURING TAKEOFF ROLL, CREW HEARD AT LEAST 3 VERY LOUD BANGS FROM THE LEFT SIDE OF THE AIRCRAFT. THERE WAS ALSO SOME LEFT YAW ASSOCIATED WITH THE NOISE. REJECTED TAKEOFF WAS PERFORMED AT APPROXIMATELY 110 KNOTS. ENGINE INSTRUMENTS INDICATED NOTHING ABNORMAL. REJECTED TAKEOFF WAS PERFORMED ON RUNWAY 25 AT SFS. ALSO, THERE WERE NO ECAM INDICATIONS. PERFORMED WHEELS AND BRAKES ON LT MAIN GEAR INSPECTION CHECK AS PER A310 MM 32-40-00-6. REMOVED AND REPLACED NR 1 ENGINE HMU 73-21-01-4.

Part: COMPUTER — FAILED (FLT DIRECTOR) · airframe 29,323 hrs · 13,192 cycles

AFTER TAKEOFF THE FMS'S WENT INTO INDEPENDENT OPERATION COMPLIED WITH QRH WITHOUT SUCCESS. F/O FLT DIR NR 2 LOST 34-73/3234. F/O LOST EFIS/SGU, DIA LINE ON NA & PFD. REPLACED AND CORRECTION FOR ALL 3 WRI'S. PERFORMED ADJ/TEST PER RELATED AMM WDM 34-73-01, 34-65,01 FOUND CHAFFING AT 22XU TRANSFORMER CURRENT GEN. 2 REPAIRED CHAFING PER SMP AND "A" REPLACED BURNED PIN & CONNECTOR ON IDG FEEDER CABLE AT PYLON CONNECTION OPS CHECK ALL SYSTEMS ON ENGINE RUN.

Part: TRANSMITTER — MALFUNCTIONED (OIL PRESSURE) · airframe 29,186 hrs · 13,128 cycles

RTO RPLB RWY 25 AT 95 KTS WITH A OIL PRESSURE HIGH INDICATION ON LOWER FORWARD INSTRUMENT PANEL. LIGHT OUT AFTER SEVERAL SECONDS. DRAINED ENG NR 1 OIL TANK PERFORMED SNIFF CHECK, NO FUEL CONTAMINATION NOTED. REMOVED AND REPLACED OIL PRESS TRANSMITTER PER AMM 79-33-11-4. RAN NR 1 ENGINE PER A310 JRH AT TAKEOFF POWER, EPR = 1.27 AT 24 DEG C, ALL PARAMETERS NORMAL; NO HIGH OIL PRESSURE WARNING LIGHTS, ILLUMINATED. A/C OK FOR SERVICE. AMT'S 354575, 366556, 472875 AND 559576. PREMATURE REMOVAL/INSTALLATION OFF MFG VT0304S POS P1 SRL 480 TAG A41053 ON MFG VT0304S SRL 671 TAG 787111.

Part: REGULATOR VALVE — MALFUNCTIONED (NR 1 OIL PRESS) · airframe 29,186 hrs · 13,128 cycles

APPROX 80-90 KNOTS GOT ECAM RED LIGHT FOR "HIGH OIL PRESS" NR 1 ENG DID RTO LIGHT WENT OUT. AT IDLE NR 1 ENG = 54 PSI, NR 2 ENG = 44 PSI. REMOVED AND REPLACED NR 1 OIL PRESS REGULATOR VALVE PER AMM 79-21-04-4. PERFORMED ENG RUN PER JRH. ALL PARAMETERS NORMAL. R/I FROM FACT PREMATURE REMOVAL/INSTALLATION OFF MFG 793739 POS 1 SRL A28440 TAG A28440 ON MFG 793739 SRL MG9205 TAG 939367.

Part: UPLOCK HOOK — DAMAGED (MLG) · airframe 29,162 hrs · 13,117 cycles

NOSE LANDING GEAR DOOR AMBER LIGHT ILLUMINATE ON BOTH PANELS FOLLOWED ECAM. QRH DECLARED EMERGENCY FOR OVERWEIGHT LANDING. LANDING WEIGHT 289.0 AND 250 FPM RATE OF DESCENT. NOTICEABLE VIBRATION FROM NOSE GEAR DOOR. FURTHER T/S FOUND RT UPLOCK ASSY-NLG DOOR HOOK ALWAYS SPRING BACK. REMOVED AND REPLACED RT NLG DOOR UPLOCK ASSY.

Part: LINE — LEAKING (HYD SYSTEM) · airframe 29,025 hrs · 13,053 cycles

HYDRAULIC GREEN SYSTEM FAILURE (LOW FLUID), FOLLOWED ECAM AND QRH. EXTENDED LANDING GEAR MANUALLY. DECLARED EMERGENCY LANDED MANILA. REPLACED HYDRAULIC LINE WITH TEMPORARY FLEX LINE AND SERVICE WITH HYDRAULIC FLUID. REPLACED TEMPORARY FLEX LINE P/N A292192180000 PER STD PRACTICES 20-23-11 PARAGRAPH -F-. NOTED THAT HYDRAULIC FLUID QUANTITY DID NOT GO BELOW LOW QUANTITY MARK. LEAK CHECK PERFORMED, TWO TEMP FLEXIBLE HOSES INSTALLED TO FLAP CTL OIL REFERENCE: AMM SUP 20-23-11-0, MPN A2901075800000, CPN 2910934.

Part: CONTROL UNIT — FAILED (AUTO BRAKES) · airframe 27,938 hrs · 12,567 cycles

BRAKES BINDING ON TAKEOFF CLEARANCE. A/C WOULD NOT ROLL EVEN AT 45 PERC. FLASHING AUTO BRAKE FAIL, TRIED TO BITE TEST ON BSCU AND SHOWED FAULT CODE 223 & 222. REMOVED AND REPLACED NR 6 BRAKE ASSY PER MM 32-42-27-4. REMOVED AND INSTALLED BRAKE SYS CONTROL UNIT AND TESTED OK AS PER AMM 32-42-72-4. REMOVED AND INSTALLED FROM FACT PREMATURE REMOVAL/INSTALLATION. OFF MFG C20101304-201.

Part: ENGINE — INOPERATIVE (NR 2) · airframe 27,332 hrs · 12,186 cycles

TAKEOFF WAS ABORTED AT 70 KTS DURING TAXI NR 2 ENG HAD TO BE VWD OF NR 1 ENG BY 1 1/2 THROTTLE WIDTHS TO MAKE 40 PERCENT N1. DURING TAKEOFF NR 2 ENG WOULD ONLY MAKE 75 PERCENT PWR WITH THROTTLE ALL THE WAY FWD. NO ENG PARAMETERS WERE CLOSE TO THE LIMITS. POWERPLANT ENG HAS APPROVED THIS NR 2 ENG FOR CHANGE.

Part: CONTROL UNIT — FAILED (BRAKE SYSTEM) · airframe 25,569 hrs · 11,163 cycles

DURING BLOCK IN WITH PEDALS FULLY DEPRESSED, A/C WOULD NOT STOP. USED PARKING BRAKE TO STOP. BRAKE ANTI-SKID SEL IN NORMAL/ON. REMOVED AND REPLACED BRAKE CONTROL UNIT (29GG) MM 32-42-72-4.