N416FE

Part: CONTROLLER — MALFUNCTIONED (FUEL QTY) · airframe 43,728 hrs · 22,179 cycles

BEFORE DESCENT, NOTICED R INNER TANK QTY WAS DEPLEATING AT A MUCH HIGHER RATE THAN THE LT INNER TANK. SUSPECTED A FUEL LEAK AND CONSULTED THE QRH. IAW QRH PROCEDURE ACCOMPLISHED AN INFLIGHT SHUTDOWN. PERFORMED INSP ON NR 2 ENG FOR FUEL LEAK AND WET MOTORING LEAK CK, NO EVIDENCE OF FUEL LEAK FOUND, PERFORMED IN FLIGHT SHUTDOWN INSP CHECK ON NR 2 ENG IAW AMM72-00-00-06, ALL NORMAL, RAN ENG FOR 10 MINS OBSERVED FUEL FLOW AND FUEL USED SAME FOR NR1 AND NR2 ENG IAW JRH, REFUELED ACFT AND CHECKED FOR FUEL QTY INDICATION NORMAL. FOR PRECAUTIONARY R & R FQIC (15QT) IAW AMM28-42-38-4, PERFORMED FUEL IND TEST IAW AMM28-42- 38-5, TEST SATIS.

Part: SKIN — GOUGED (FUSELAGE) · airframe 43,421 hrs · 22,040 cycles

FUSELAGE SKIN EXTERNAL SURFACE HAD A GOUGE AT FR47/48 AND STR 50R. DO THE REPAIR IAW EA 6-5330-140169.

Part: SUPPORT BEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,418 hrs · 22,036 cycles

CORROSION FOUND ON SUPPORT BEAM UNDER SURFACE OF FR35 YD PERFORMED REPAIR SRM 51-74-10 AND EA 6-5310-139554.

Part: CROSSBEAM — CRACKED (FUSELAGE) · corrosion level 2 · airframe 43,418 hrs · 22,036 cycles

A CRACK FOUND ON THE CROSSBEAM OF FR38 BETWEEN YB AND YC PERFORMED REPAIR IAW SUPPLEMENT SRM 53-10-15, FIG 203 AND EA 6-5310-140124.

Part: ACTUATOR — LEAKING (NR 6 SPOILER) · airframe 43,418 hrs · 22,036 cycles

LT WING NR 6 SPOILER ACTUATOR LEAK. PRESSURED THE HYD SYS CK LEAKAGE IAW AMM 29-10-00-3. REPLACED THE LT NR 6 SPOILER ACTUATOR IAW AMM 27-64-14-4, RESULT:10 DROPS/10MIN CARRIED OUT OPS TEST OF ROLL TEST IAW AMM27-11-00-5 AND LEAK CHECK. TEST OK AND NO LEAKAGE MINOR REPAIR IAW GMM6-2-100.

Part: ACTUATOR — WORN (MLG) · airframe 43,094 hrs · 21,888 cycles

LDG GEAR WOULD NOT RETRACT AFTER T/O. REMOVED AND REPLACED LT MLG BOGIE BEAM PITCH DAMPER ACTUATOR IAW AMM 32-11- PERFORMED JACKING FOR ACFT MX OPERATION FOR LANDING GEAR EXTENSION AND RETRACTION TEST ON SYS 1 AND SYS 2. RET/EXT SATISFACTORY IAW AMM 07-11-00-0. RELEASED ACFT FOR SERVICE.

Part: UNKNOWN — UNKNOWN (SPOILERS) · airframe 42,007 hrs · 21,393 cycles

LOST SPOILER NR 7 FOLLOWED BY BLUE HYD PRESSURE/FLUID LOSS ON INITIAL T/O ROLL. RTO AT 50KTS. ON BLOCK PERFORM INSPECTION FOR SIGN OF LEAKAGE, NO LEAK FOUND. COCKPIT CHK BLUE HYD INDICATION AT LOWER BAND OF SVC RANGE. SERVICE TO TOP HAT RANGE AS PER SMP. PERFORM BOTH ENG GROUND RUN FOR APPROX 10 MINS AND OPS CHECK SPOILER LT AND RT ALL NORMAL. RESET EFCU AND NIL FAULT FOUND. AS PER AMM 32-40-00-6, PERFORM RTO INSP ON WHEELS AND BRAKES, ALL CONDITION NORMAL. AIRCRAFT OK FOR SERVICE.

Part: SKIN — CHAFED (ZONE 400) · airframe 40,357 hrs · 20,549 cycles

NR 1 ENGINE INBOARD THRUST REVERSER INTERIOR SKIN CHAFED JUST BELOW DEOILER EXHAUST PORT, NAC STATION 385 ,4:00 POSITION. REPAIRED PER EA NR 6-7800-113019 , EXHAUST, NR 1 ENGINE INBOARD T/R AFT BARREL SKIN DOUBLER, REPAIR.

Part: PANEL — WORN (THRUST REVERSER) · airframe 40,357 hrs · 20,549 cycles

NR 2 ENGINE OUTBOARD T/R UPPER BIFURCATION DUCT INNER PANEL HAS WEAR COMPLIED WITH FED EX EA6-7830-7-113013. NR 2 ENGINE OUTBOARD T/R UPPER BIFURCATION HEAT SHIELD REPAIR.

Part: SKIN — CRACKED (RWS 1713) · airframe 40,357 hrs · 20,549 cycles

RIGHT WING SLAT NR 6 SCREWJACK CUT OUT, WING STATION 1713, CRACKED. REMOVED FASTENERS AT DAMAGED AREA IAW FEDEX A310-200 SRM 51-40-21 PAGE 22. CUT OUT SKIN DAMAGE AT LEADING EDGE WING STATION 1713 IAW FEDEX A310-200 SRM 57-41-12 PAGE 209 FIGURE 203. INSTALLED REPAIR PARTS IAW FEDEX A310-200 SRM 57-41-12 PAGE 209 FIGURE 203 AND A310-200 SRM 51-40-21 PAGE 22.

Part: TIP CAP — CRACKED (HORIZONTAL STAB) · airframe 40,357 hrs · 20,549 cycles

LT HORIZONTAL STAB TIP, TRAILING EDGE, CRACKED. REMOVED DAMAGE & APPLIED FIBERGLASS WET LAY UP IAW 55-14-11 FIGURE 203, DWG A551- 76100 & EA 6-5510-113014.

Part: BRACKET — CORRODED (HORIZ STAB) · corrosion level 2 · airframe 40,357 hrs · 20,549 cycles

THS LEFT UPPER BODY FAIRING FWD ATTACH BRACKET ANGLE CORRODED, CENTER BOX AREA, ANGLE IS PART OF LEADING EDGE. REMOVED AND REINSTALLED UPPER APRON IAW A310-200 SRM 51-40-21. REMOVED AND REINSTALLED RIB ASSY IAW A310-200 51-40-21. REMOVED UPPER ATTACH PLATE IAW A310-200 SRM 51-40-21. REMOVED CORROSION ORIGINAL THICKNESS .252 REMOVED .050 REMAINING THICKNESS .200, FOUND TO BE OUT OF LIMITS IAW A310-200 55-12-28 (NO REPAIR AUTHORIZED). RECEIVED NEW PART P/N A5517860720000 P/O 604175.1. INSTALLED NEW BRACKET IAW A310-200 SRM 51-40-21.

Part: BRACKET — CORRODED (HORIZ STAB) · corrosion level 2 · airframe 40,357 hrs · 20,549 cycles

THS LEFT LOWER BODY FAIRING FWD ATTACH BRACKET ANGLE CORRODED LOWER SURFACE, CENTER BOX AREA, ANGLE IS PART OF LEADING EDGE. REMOVED AND REINSTALLED LOWER APRON IAW A310-200 SRM 51-40-21. REMOVED AND REINSTALLED RIB ASSY IAW A310-200 SRM 51-40-21. REMOVED LOWER ATTACH PLATE IAW A310-200 SRM 51-40-21. REMOVED CORROSION ORIGINAL THICKNESS .252 REMOVAL .060 REMAINING THICKNESS .192. FOUND TO BE OUT OF LIMITS IAW A310-200 SRM 55-12-28 (NO REPAIR AUTHORIZED). RECEIVED NEW PART P/N A5517860720200 P/O 604456.1. INSTALLED NEW BRACKET IAW A310-200 SRM 51-40-21.

Part: SEAT TRACK — CRACKED (FUSELAGE) · airframe 40,357 hrs · 20,549 cycles

NR 4 LT ARTICULATING SEAT TRACK IS CRACKED. REMOVED AND REPLACED LT NR 4 ARTICULATING SEAT TRACK PO NR 602215.2 REF FEDEX A310-200 W/C E-6-5310-7-3322 PT2 SEAT AND DUMMY TRACKS ATTACHMENT FITTINGS INSPECTION.

Part: SEAT TRACK — CRACKED (FUSELAGE) · airframe 40,357 hrs · 20,549 cycles

NR 4 LT ARTICULATING SEAT TRACK IS CRACKED. REMOVED AND REPLACED LT NR 4 ARTICULATING SEAT TRACK PO NR 602215.2 REF FEDEX A310-200 W/C E-6-5310-7-3322 PT2 SEAT AND DUMMY TRACKS ATTACHMENT FITTINGS INSPECTION.

Part: HEAT SHIELD — CRACKED (NR 1 NACELLE) · airframe 40,357 hrs · 20,549 cycles

PYLON NR 1 FWD ENG MOUNT, HEAT SHIELD CRACKED (MKD). REMOVED HEAT SHIELD NR 1 ENG PYLON IAW FEDEX A310-200 SRM 51-40-21 PAGE 1. RECEIVED NEW HEAT SHIELD P/N A2611501200200 S/N IC673554 PO 605041.1 FROM SUPPLY. INSTALLED NEW HEAT SHIELD IAW FEDEX A310-200 SRM 51-40-21 PAGE 7.

Part: SKIN — CORRODED (RT ELEVATOR) · corrosion level 2 · airframe 40,357 hrs · 20,549 cycles

RT ELEVATOR APPROX STA 529 TOP SURFACE SKIN CORRODED. REPAIRED RT ELEVATOR UPPER SKIN CORROSION BY REMOVING DAMAGED SKIN, AND FABING SKIN PLUG AND DOUBLER, BONDING SKIN PLUG AND DOUBLER, EDGE SEALING REPAIR, AND REFINISHING IAW A310-200 SRM 51-77-12 FIG 224.

Part: SKIN — CORRODED (RT ELEVATOR) · airframe 40,357 hrs · 20,549 cycles

RT ELEVATOR APPROX STA 529 TOP SURFACE SKIN CORRODED. REPAIRED RT ELEVATOR UPPER SKIN CORROSION BY REMOVING DAMAGED SKIN, AND FABING SKIN PLUG AND DOUBLER, BONDING SKIN PLUG AND DOUBLER, EDGE SEALING REPAIR, AND REFINISHING IAW A310-200 SRM 51-77-12 FIG 224.

Part: SKIN — CORRODED (RT ELEVATOR) · corrosion level 2 · airframe 40,357 hrs · 20,549 cycles

RT ELEVATOR APPROX STA 623 LOWER SKIN CORRODED.

Part: SKIN — CORRODED (RT ELEVATOR) · corrosion level 2 · airframe 40,357 hrs · 20,549 cycles

RT ELEVATOR APPROX STA 623 LOWER SKIN CORRODED. REPAIRED RT ELEVATOR LWR SKIN CORROSION BY REMOVING DAMAGED SKIN, AND FABING SKIN PLUG AND DOUBLER, BONDING SKIN PLUG AND DOUBLER, EDGE SEALING REPAIR, AND REFINISHING IAW A310-200 SRM 51-77-12 FIG 224.

Part: RIB — CRACKED (ZONE 600) · airframe 40,357 hrs · 20,549 cycles

CRACKED, R/WING SPOILER NR 3 IBD BOX HINGE RIB. REMOVED PANEL IAW A310-200 SRM 51-40-21 PG 7. CUT AND REMOVED CRACKED END RIB IAW A310-200 SRM 57-51-11 PG 227 AND 228. LOCATED, DRILLED AND DEBURRED ITEM 1, ITEM 2, AND ITEM 3 IAW A310-200 SRM 57-51-11 PG 222 STEP 3 (A) - 3(K), PG 223 3(L)- 3(V), PG 227, 228 AND 229. INSTALLED ITEM 1 RIB INSERT, ITEM 2 SPLICE CHANNEL, ITEM 3 JOINT STRAP AND PANEL IAW A310-200 SRM 57-51-11 PG 223 AND A310-200 SRM 51040-21 PG 7.

Part: SILL — CORRODED (ZONE 100) · corrosion level 2 · airframe 40,357 hrs · 20,549 cycles

BULK CARGO DOOR CUTOUT LOWER SILL CORROSION AFT SECTION. MARKED REMOVED AND REPLACED LOWER SILL BEAM IAW A310-200 SRM 53-17-18 FIG 6 SHT 8 AND 51-40-21.

Part: SKIN — MISREPAIRED (ZONE 100) · airframe 40,357 hrs · 20,549 cycles

EVALUATION OF FUSELAGE NOSE REPAIR (AERODYNAMIC BODY FILLER) BETWEEN FRAMES 3 AND 4 CENTERLINE, JUST AFT OF LOWER EDGE OF RADOME. EVALUATED REPAIR, FOUND REPAIR NOT TO CONFORM TO FEDEX SRM. REMOVED DAMAGED AREA IAW 53-11-12 FIG 201. FABRICATED AND INSTALLED REPAIR IAW SRM 53-11-12 FIG 201. MATERIAL P/N A57210234200.

Part: SPAR — CORRODED (ZONE 600) · corrosion level 2 · airframe 40,357 hrs · 20,549 cycles

CORROSION ON RIGHT WING REAR SPAR DOUBLER AROUND SPOILER NR 7 ACTUATOR REMOVED CORROSION IAW A310-200 SRM 51-74-10 ITEM 3. ORIGINAL THICKNESS .206 IAW AIRBUS DRAWING N : A 571-50824. REMOVED .002, REMAINING THICKNESS .204. WITHIN LIMITS IAW A310-200 SRM 57-51-11 PAGE 102. ALODINED IAW A310-200 SRM 51-21-10 PAGE 3, PRIMED IAW A310-200 SRM 51-23-10 PAGE 24, PAINTED IAW A310-200 SRM 51-23-10 PAGE 24.

Part: ATTACH FITTING — CRACKED (ZONE 100) · airframe 40,357 hrs · 20,549 cycles

ONE HALF INCH CRACK IN UPPER FLANGE RADIUS OF AFT CARGO DOOR ACTUATOR ATTACH FITTING. CRACK MARKED AND IN APPROX CENTER OF RADIUS BETWEEN FORE AND AFT EDGE OF FITTING. COMPLIED WITH EA 6-5230-113011--AFT CARGO DOOR FRAME 61A EXISTING REPAIR.

Part: SUPPORT ANGLE — CRACKED (ZONE 500) · airframe 40,357 hrs · 20,549 cycles

LEFT WING UPPER SURFACE TRAILING EDGE PANEL NR 575BT CUTOUT SUPPORT ANGLE CRACKED AT STATION 490. CLEANED AREA IAW FEDEX A310-200 SRM 51-23-10 PG 1. ACCOM. HFEC INSP. PER A310 NTM 51-10-08. VERIFIED AREA IS CRACKED. USED TOOL TWS 8209A. UNABLE TO MARK END OF CRACK DUE TO CRACK RUNS TO BOTTOM OF WING T/E. RECEIVED FINAL RFTS N416FE-7-36189 W/ EA6-5750-113009. ACCOMPLISHED HFEC OF ADJACENT SKIN AREA IAW A310 NTM 51-10-08 USING T8257A. NO CRACKS NOTED. INSTALLED FASTENERS IAW A310-200 SRM 51-40-21 PG 24 AND PG 90.

Part: BEAM — CORRODED (NR 2 PYLON) · airframe 40,357 hrs · 20,549 cycles

NR 2 ENGINE PYLON AFT BEAM ATTACHMENT MOUNT HAS SEVERE RUST ON BOTTOM FACE OF MOUNT. CLEANED BEAM ASSY. IAW AMM 54-51-00-6.5 B-1. REMOVED CORROSION FROM BEAM SURFACE IAW 54-51-00-6.5 B-1 & SRM 51-74-10 ITEM 7 B-2, ITEM 5 A-5 & PMS 01-01-14-1. POLISHED REWORKED AREA IAW AMM 54-51-00-6. PERFORMED PFPI IAW NTM 51-90-00 ON BLENDED AREA (NO CORROSION NOTED). CLEANED BEAM ASSY. IAW AMM 54-51-00-6 PG. 4. CALCULATED AMP HRS. IAW 51-21-10. ADHESION TEST OF DEPOSIT IAW SRM 51-21-10 (ADHESION GOOD IN BOTH AREAS) & PRIMED REWORKED AREAS IAW AMM 54-51-00-6 01 PG. 5 (HIGH TEMP PRIMER).

Part: MOUNT — CORRODED (NR 1 ENGINE) · airframe 40,357 hrs · 20,549 cycles

NR 1 ENGINE PYLON AFT ENGINE MOUNT LOWER SURFACE LIGHT CORROSION AROUND LEFT AND RIGHT OUTBOARD SIDES. CLEANED ASSY IAW AMM 54-51-00 6.5 B.P1 REMOVED CORRSION FROM ASSY SURFACE IAW SRM 51-74-10 ITEM 7 B-2 & PMS 01-01-14-1, POLISHWED REWORK AREA IAW AMM 54-51-00-6. PERFORMED PFPI IAW NTM 51-90-00 ON BLENDED AREA ONLY. NO CORROSION NOTED. CLEANED REWORKED AREA IAW AMM 54-51-00- 6 P4. PRIMED REWORKED AREA IAW AMM 54-51-00-6 P4.

Part: BEAM — CORRODED (NR 2 PYLON) · airframe 40,357 hrs · 20,549 cycles

NR 2 ENGINE PYLON AFT BEAM ATTACHMENT MOUNT AFT SIDE , 2 PLACES, UPPER END EMITTING RUST. REMOVED & REPLACED NR 2 ENG. MOUNT SHIM REF AMM 54-54-86-4 2B-3. PRIMED SHIM REF AMM 54-51-00-6 PG. 5. MATCH DRILLED SHIM REF SRM 51-4-44. REMOVED & REINSTALLED PRE COOLER REF AMM 36-11-15-4. REMOVED & REINSTALLED PRE COOLER INLET DUCT REF AMM 36-11-00-4. LEAK CHECK TO BE ACP. ON FEDEX J/C 40C0503 JPF STEP 9.

Part: SELECTOR VALVE — MALFUNCTIONED (THRUST REVERSER) · airframe 38,109 hrs · 19,511 cycles

SHORTLY AFTER T/O, NR 2 REVERSER UNLOCK LIGHT ILLUMINATED WITH ECAM WARNING LIGHT STAYED ON FOR APPROX 30 SEC, FLICKERED AND WENT OUT. THE LIGHT AND ECAM WARNING CAME ON AGAIN A FEW SECONDS LATER IT STAYED ILLUMINATED FOR SEVERAL MINUTES AND WENT OUT, AT NO TIME DID THE A/C YAW OR SHOW ANY SIGNS OF HAVING A REVERSER UNLOCKED. REMOVED AND REPLACED SOLENOID SELECTOR VALVE A310MM 78-31-10-4-03. OPERATED NR 2 REVERSER SEVERAL TIMES, OPS CHECK GOOD. VERIFIED UNLOCK LIGHT GOES OUT WHEN REV NR 2 IS STOWED.

Part: SENSOR — DIRTY (AIR CONDITIONING) · airframe 33,925 hrs · 16,718 cycles

REACHING 350 ECAM ADVISED OF VENT BLOWERS LO FLOW FOLLOWED ECAM SELECTED ALTN AND ECAM REAPPEARED LO FLOW. RESET BLOWER SWITCH AFTER 5 MINS AND PRESSED ON IT, REOCCURRED AND DECIDED TO RETURN TO OMDB. CLEANED FLOW SENSOR 79HQ CK BLOWER FANS FOR OPS CHECK SATISFACTORY. CHECKED DUST EXTRACTOR FOUND CLEAN, CHECKED OVERBOARD EXTRACTOR VALVE 75 HR FOR CLOSING AND OPENING SATISFACTORY. TROUBLESHOT PER TSM 21-20-00 NIL FAULTS AND CND OVER A THREE HR PERIOD. THEN A/C ARRIVED DXB ALT SYS WORKING NORMALLY AND NO ECAM ADVISORY.

Part: WARNING SYSTEM — ACTIVATED (COCKPIT) · airframe 33,764 hrs · 16,632 cycles

ON CLIMBOUT NR 1 EGT PEGGED AT MAX GAUGE NOSE GEAR SHOW UNSAFE.

Part: FIRE WARNING — ACTIVATED (COCKPIT) · airframe 33,274 hrs · 16,368 cycles

ENGINE FIRE WARN AFTER T/O.

Part: FIRE WARNING — MALFUNCTIONED (NR 1 ENGINE) · airframe 33,274 hrs · 16,368 cycles

ON CLIMBOUT NR 1 ENG FIRE WARNING. COMPLETED ECAM FIRE PROC, SHUTDOWN ENG. FIRED BOTTLES. REMOVED BOTH FIRE BOTTLES AND SQUIBS. RAN ENG AT HIGH POWER CK DUCTS, NO LEAKS NOTED.

Part: CONTACTOR — DIRTY (PNEUMATIC SYS) · airframe 33,153 hrs · 16,310 cycles

BOTH BLD VLVS FAULTED RESULTING IN LOSS OF PRESSURE. CLEANED CONTACTS OF PSC'S AND INTERCHANGED THE SAME. SECURED PSC'S AND RAN ENG PER A310 JRH. NO FAULT NOTED.

Part: FIRE WARNING — ILLUMINATED (COCKPIT) · airframe 33,108 hrs · 16,929 cycles

NR 1 ENG FIRE WARNING LIGHT ILLUM DURING CLIMBOUT. PERFORMED PROC BOTH FIRE BOTTLES FIRED.

Part: SLAT — MALFUNCTIONED (WING) · airframe 32,612 hrs · 16,048 cycles

ON APPROACH RECD SLAT FAULT AS HANDLE WAS MOVED TO EXTEND SLATS. RECYCLED, NO HELP. BOTH SFCC 1 & 2 SHOW JAM ON SLATS. SFCC''S RESET FLAPS AND SLAT CYCLED. NO FURTHER FAULTS. JACK SCREWS SERVICED PER IAW AMM 12-13-27-0 PG 30. NO EVIDENCE OF WATER CONTAMINATION.

Part: CONTROLLER — FAILED (CABIN PRESSURE) · airframe 32,566 hrs · 1,602 cycles

A/C WOULD NOT PRESSURIZE AFTER T/O.

Part: FLOORBEAM — CRACKED (CABIN) · airframe 32,064 hrs · 15,764 cycles

NR 36 AT FRAME 34 FOUND FLOOR CROSS BEAM CRACKED AT RHS Y-700, .5 INCH BELOW UPPER FLANGE. *S/D* REMOVED AND REPLACED PER A310 SRM MANUAL 53-10-15, FIG 201 & FEDEX EA 6-5100-52821.

Part: FLOORBEAM — CRACKED (CABIN) · airframe 32,064 hrs · 15,764 cycles

NR 35 AT FRAME 36 FOUND FLOOR CROSS BEAM CRACKED AT RHS Y-700, .5 INCH BELOW UPPER FLANGE. *S/D* REMOVED AND REPLACED PER A310 SRM SM 53-10-15, FIG 201 & FEDEX EA 6-5100-52821.

Part: FLOORBEAM — CRACKED (CABIN) · airframe 32,064 hrs · 15,764 cycles

NR 34 AT FRAME 36 FOUND FLOOR CROSS BEAM CRACKED AT RHS BETWEEN Y-850 TO -950, BELOW UPPER FLANGE. *S/D* REMOVED AND REPLACED PER A310 SRM SM 53-10-15, FIG 201 & FEDEX EA 6-5100-52821.

Part: FLOORBEAM — CRACKED (CABIN) · airframe 32,064 hrs · 15,764 cycles

NR 37 AT FRAME 35 FOUND FLOOR CROSS BEAM CRACKED AT RHS Y-700, .5 INCH BELOW UPPER FLANGE. *S/D* REMOVED AND REPLACED PER A310 SRM MANUAL 53-10-15, FIG 201 & FEDEX EA 6-5100-52821.

Part: FLOORBEAM — CRACKED (CABIN) · airframe 32,064 hrs · 15,764 cycles

NR 66 AT FRAME 36 FOUND FLOOR CROSS BEAM CRACKED AT LHS Y+700, .5 INCH BELOW UPPER FLANGE. *S/D* REMOVED AND REPLACED PER A310 SRM MANUAL 53-10-15, FIG 201 & FEDEX EA 6-5100-52821.

Part: ELBOW — RUPTURED (NR 1 ENGINE) · airframe 32,058 hrs · 15,761 cycles

PDIS- NR 1 ENGINE FIRE DURING CLIMB. REMOVED AND REPLACED BLOWN PNEUMATIC SYS 8TH STAGE ELBOW. REMOVED AND REPLACED PYLON FIRE EXTINGUISHER PER AMM 26-21-15. ACCOMPLISH SQUIB CK PER AMM 26-21-13 AND REPLACED NR 1 ENG LEFT CORE COMPT FIRE DETECTOR PER AMM 26-12-00.

Part: WARNING LIGHT — ILLUMINATED (THRUST REVERSER) · airframe 31,902 hrs · 15,690 cycles

A/C HAD A AIR TURNBACK DUE TO THE NR 1 T/REV UNLOCK LIGHT ON IN FLIGHT.

Part: THRUST REVERSER — UNLOCKED (NR 1 ENGINE) · airframe 31,896 hrs · 15,685 cycles

DURING T/O ROLL, THROTTLES ADVANCED NR 1 THRUST REVERSER UNLOCKED LIGHT ILLUM. RETURNED TO GATE. REVERSER DEACTIVATED AND A/C RELEASED PER MEL 78-1.

Part: LINE — LEAKING (HYDRAULIC SYS) · airframe 31,766 hrs · 15,614 cycles

YELLOW HYD SYS FAILURE, QTY IND ZERO. REPLACED BROKEN DRAIN LINE WITH FLEX HOSE PER IAW MM 29-00-00-3.

Part: FRAME — CRACKED (FUSELAE) · airframe 31,462 hrs · 15,435 cycles

INSPECTED TWO CRACKS ON HOLE J LOCATED BETWEEN STR 42 & 44 ON AFT FLANGE OF FR 47, RT SIDE.

Part: SKIN — DELAMINATED (TE FLAP) · airframe 31,462 hrs · 15,435 cycles

THE LT INBOARD FLAP, TRAILING EDGE LOWER SKIN WAS FOUND DELAMINATED.

Part: PRESSURE CONTL — FAILED (NR 2 BLEED AIR)

NR 2 BLEED AIR FAULTED, X BLEED MANIFOLD AND SHORTLY NR 1 BLEED FAULTED. REMOVED AND REPLACED NR 2 PRESSURE CONTROLLER PER MM 36-11-19, ENG RUN PERF OPS CHECK NORM. ENG RUN PER OPS CHECK NORM AT N1 40 PERCENT TEMP WAS 175 AND STABLE, MATCH NR 1 BLEED CHECK GOOD.

Part: TR UNLOCK LIGHT — MALFUNCTION (NR 2 ENGINE)

DURING INITIAL CLIMB, ENG NR 2 REV GREEN UNLOCK LIGHT ILLUMINATED WITH ASSOCIATED ECAM PROCEDURE ENGINE PARAMETERS NORMAL. PHYSICALLY CHECKED ALL STOW AND DEPLOY SWITCHES FOR LOOSENESS, CHECKED ALL CABLES AND HOSES FOR CONDITION, AND RE-RIGGED THRUST REVERSER. ALL CK'D GOOD. COMPLIED WITH FUNCTIONAL CHECK AND ENG GROUND RUN-UP OPS CK. ALL CHECKED NORMAL.

Part: THRUST REVERSER — MALFUNCTIONED (NR 2 ENGINE)

KUL, ECAM ALERT THRUST REV 2, UNLOCKED AT FL 270, NO TURBULANCE. THRUST INDICATOR WENT OUT, SPEED BELOW 280 KTS. DEFERRED NR 2 THRUST REV PER THE MEL.

Part: ENGINE — VIBRATION (NR 1)

ON CLIMBOUT, THE A/C STARTED TO VIBRATE AND THE NR 1 ENG INSTRUMENTS, N1 WAS FLUCTUATING 4 TO 6 PERCENT AND THE VIBRATION ON ECAM SHOWED AN ENG PROBLEM. N1 WAS FLUCTUATING 4 TO 6 PERCENT AND THE VIB ON THE ECAM SHOWED 3.6 ON N1. WHEN POWER WAS REDUCED TO IDLE VIB DECREASED, ADDING POWER VIB INCREASED. RETURNED TO IND WITH ENG IN REDUCED POWER.

Part: STRUCTURE — VIBRATION (AIR FRAME)

AFTER TAKEOFF WITH GEAR UP, A/C STARTED VIBRATING. GEAR WAS CYC DOWN & UP WITH NO PROBLEMS. VIB CONTD. LEVEL OFF AT 5000 FEET. FLAPS/SLATS RETRACTED, VIBRATION STOPPED AT PWR REDUCTION (VIB WAS MOD). RETND FOR LANDING WITH NORMAL SLAT/FLAP EXTENSION & NO VIB AT REDUCED PWR. PERFORMED WALKAROUND INSP OF RUDDER, LANDING GEAR, STABILIZER, FLAPS AND SLATS, AILERONS, SPOILERS, ELEVATORS ALL CK'D OK FROM GROUND. PERFORMED HI-PWR ENG RUN PER MM 71-00-00, PG A588 IN CONJUNCTION WITH A300 FLT MANUAL, REF 5-3-2. PARAM CK'D WITH PUBLISHED LIMITS FOR WEATHER CONDITIONS. 1.489 NR 1 ENG N1=1.2, N2=.6, NR 2 ENG N1=.4, N2=6. VISUALLY INSP ENG SHROUDS, BLADE TIPS, & RUB STRIPS PER MM 72-23-01, PG 601-606, CK'D GOOD.