N449FE

Part: SHUTOFF VALVE — INOPERATIVE (THRUST REVERSER) · airframe 39,055 hrs · 28,025 cycles

AFTER LIFTOFF(KATL) ENG1 THRUST REVERSER SHOWED "UNLOCKED". ON T/O ROLL, LIGHT FLICKERED MOMENTARILY THEN WENT OUT. FOLLOWED QRH AND ECAM PROC AND DECLARED EMERGENCY MEL 14AUG07. ACN RELEASED FOR SERVICE PER MEL/CDL: 78-30-01-C CATEGORY: C EXP: 17AUG07 "MEL 78-30-01-C: ENGINE (IDENTIFY 1 OR 2) 1 THRUST REVERSER, INOP. THRUST REV IS DEACT IN FWD THRUST POSITION." REPLACED NR 1 THRUST REVERSER PRESSURE REGULATOR/SHUTOFF VALVE PER A310-200 AMM 78-31-05-4 03 AND VALVE CONNECTOR DH9 PER AIRBUS ESPM. NR 1 REVESER OPS CHECKS GOOD.

Part: SHUTOFF VALVE — INOPERATIVE (THRUST REVERSER) · airframe 39,054 hrs · 28,024 cycles

AFTER LIFTOFF (KATL) ENG NR 1 THRUST REVERSER SHOWED "UNLOCKED". ON TAKEOFF ROLL LIGHT FLICKERED MOMENTARILY THEN WENT OUT. FOLLOWED QRH AND ECAM PROCEDURE AND DECLARED EMERGENCY. REPLACED NR 1 THRUST REVERSER PRESSURE REGULATOR SHUTOFF VALVE PER A310-200 AMM 78-31-05-4 03 AND VALVE CONNECTOR DH9 PER AIRBUS ESPM. NR 1 REVESER OPS CHECKS GOOD.

Part: RECTIFIER — FAILED (NR 1) · airframe 38,947 hrs · 27,948 cycles

FOUND NR 1 TRANSFORMER RECTIFIER FAULTED ON MAINT PANE (MULTIPLE FAULTS IN FLT- TRANSPONDER, AUTO-THROTTLE, PITCH TRIM). REMOVED AND REPLACED NR 1 TRANSFORMER RECTIFIER IAW AIRBUS M/M 24-32-11-4. OPS CHECKED NORMAL PER AIRBUS M/M 24-32-00-5. ALL OTHER FAULTED SYSTEMS TESTED OK. THIS BUSS PROBLEM APPEARED TO BE THE ROOT CAUSE, SEE 34-54/9169 (TRANSPONDER), 22-10/9170 (PITCH TRIM) AND 22-30/9171 (AUTO-THROTTLE).

Part: CONNECTOR — LOOSE (THRUST REVERSER) · airframe 38,926 hrs · 27,934 cycles

ON TAKEOFF REC'D NR 1 REVERSER UNLOCKED LIGHT AT 2 SEPARATE TIMES. ONCE DURING ENG OVERTEMP AND AFTER THROTTLE WAS REDUCED. ON TAKEOFF, ECAM NR 1 ENG OVERTEMP, FOLLOWED QRH A/C IN WORK. FOUND CONNECTOR DS307 LH REVERSER STOW CONNECTOR VERY LOOSE. CLEANED CONNECTOR AND SECURED. A/C OK FOR SERVICE

Part: UNKNOWN — UNKNOWN · airframe 38,831 hrs · 27,876 cycles

SHORTLY AFTER T/O A/C ACTED AS IF THERE WAS GROUND SENSING PROBLEM, MALFUNCTIONS TO INCLUDE; ATS 1, PITCH TRIM 1, ALL THREE PITOT PROBE, CAPT TAT, BOTH PRESS CONTROLERS: GEAR WOULD NOT RETRACT SYS 1, A/P 1&2 INOP. INSTALLED NEW NOSE STRUT SENSOR 55GB PROBE HEAT AND PRESSURIZATION CONTROLLERS CHECK OK. ENGAGED BOTH AP. EACH AP ENGAGES.

Part: OUTFLOW VALVE — MALFUNCTIONED (CABIN PRESS SYS) · airframe 38,684 hrs · 27,789 cycles

NR 2 AUTO PRESSURIZATION SYSTEM FWD AND AFT VALVES WOULD NOT CLOSE. NR 1 SYSTEM COULD NOT CONTROL AIRCRAFT PRESSURE. ATTEMPTED TO CONTROL PRESSURIZATION MANUALLY. STILL COULD NOT CONTROL PRESSURIZATION WITH THE NR 2 FWD AND AFT VALVES IN THE OPEN POSITION ITEM CLOSED WITH OPS CK OK. REMOVED AND REPLACED FWD AND AFT OUTFLOW VALVES AND SYS 2 CONTROLLER, PRESSURIZED A/C AND CHECKED OPERATION.

Part: UNKNOWN — UNKNOWN (AILERONS) · airframe 38,542 hrs · 27,699 cycles

IN FLIGHT AIRCRAFT WANTED TO TURN RIGHT. REQUIRED 3 UNITS AILERON DEFLECTION TO FLY STRAIGHT. REQUIRED 14 UNITS OF RIGHT RUDDER TRIM TO LEVEL OUT AILERONS. NO CHANGES FROM CLIMB POWER TO IDLE POWER. NO CHANGE YAW DAMPERS ON OR OFF. NO CHANGES AUTOPILOT ON OR OFF. FUEL TANKS AND FOUND FUEL LOAD TO BE SYMMETRICAL. RUDDER NEUTRAL AND FOUND AT ZERO. CHECKED AILERON CABLE TENSION AND ADJUSTMENT AND FOUND OK. CHECKED AILERON DROOP, AILERON TRIM ADJUSTMENT AND FOUND ALL WITHIN PARAMETERS. CHECKED AILERON NEUTRAL AND FOUND TO BE OK REF A310-200AMM 27-11-00-5. OPERATED AILERON SYSTEM SEVERAL TIMES WITH NO DEFECTS NOTED. REMOVED AND REPLACED LT DROOP ACTUATOR PER A310-200 MM 27-11-71-4 , OPS CHECK AND L

Part: FRAME — UNKNOWN (CENTER WING BOX) · airframe 38,388 hrs · 27,603 cycles

UPON DETAILED SPECIAL INSP (SDET) OF CENTER WING BOX LOWER SKIN BETWEEN FRAME 40/41AND 47/48 LT SIDE AT FRAME 44.2 OB MOST FWD HOLE SHOWS POSITIVE INDICATION DUE TO A BUSHING INSTALLED IN THE HOLE COMPLIED WITH EA 6-5710-106250 PT1.

Part: STRINGER — MISREPAIRED (FUSELAGE) · airframe 38,388 hrs · 27,603 cycles

PREVIOUS REPAIR AFT CARGO UNDER FLOOR STRINGER 49 LT HAS A STRINGER REPAIR BETWEEN FS 59/60 WITH 1 EA STRINGER SECTION AND 1 EA REPAIR SPLICE PREVIOUSLY INSTALLED REPAIR NOT TO BE IAW A310 SRM 53-10-14 FIG 201. REPAIRED PER FEDEX EA6-5310-105014.

Part: SPAR — CORRODED (FUSELAGE) · airframe 38,388 hrs · 27,603 cycles

29 AREAS OF CORROSION AROUND FASTENERS ALONG FRAME 40 AT CTR WING TANK LOWER SPAR CHORD BETWEEN STGR 3L AND 5L (EXTERNAL OF TANK) REPAIRED PER FEDEX EA6-5730-105024.

Part: STRINGER — MISREPAIRED (FUSELAGE) · airframe 38,388 hrs · 27,603 cycles

PREVIOUS REPAIR BULK CARGO UNDER FLOOR STGR 50 LT HAS A STGR REPAIR BETWEEN FS 65 AND 66 WITH 1EA STGR SECTION AND 1EA REPAIR SPLICE. PREVIOUSLY INSTALLED REPAIR FOUND NOT TO BE IAW A310SRM 53-10-14. REPAIRED STRINGER PER FEDEX EA6-5310-105015

Part: SUPPORT — CORRODED (WING) · airframe 38,388 hrs · 27,603 cycles

4 AREAS OF CORROSION AROUND FASTENERS ON HORIZONTAL LOWER SURFACE OF STRINGER SUPPORT STRAP AT FS 40 STRG 1 C/W FEDEX EA6-5730-105024.

Part: SUPPORT — CORRODED (WING) · airframe 38,388 hrs · 27,603 cycles

13 AREAS OF CORROSION AROUND FASTENERS ON HORIZONTAL LOWER SURFACE OF STRINGER SUPPORT STRAP AT FRAME 40 STRINGER 3R C/W FEDEX EA6-5730-105024.

Part: STRINGER — MISREPAIRED (FUSELAGE) · airframe 38,388 hrs · 27,603 cycles

PREVIOUS REPAIR BULK CARGO UNDER FLOOR STRG 53 LT HAS A STGR REPAIR BETWEEN FS 66/70 WITH 4 STGR SECTIONS AND 4 REPAIR SPLICES PREVIOUSLY INSTALLED REPAIR FOUND NOT TO BE IAW A310SRM 53-10-14 FIG 201. REPAIRED STRG PER FEDEX EA6-5310-105016.

Part: SKIN — MISREPAIRED (CARGO DOOR) · airframe 38,388 hrs · 27,603 cycles

PREVIOUS REPAIR BULK CARGO DOOR EXTERIOR SKIN HAS AN EXTERNAL REPAIR DOUBLER MEASURING 6.25" BY 15.1" AT THE LOWER AFT CORNER PREVIOUSLY INSTALLED REPAIR LOCATED AT BULK CARGO DOOR WAS DETERMINED NOT TO BE IAW A310 SRM 52-30-00 FIG 207 DUE TO INCORRECT MATERIAL THICKNESS OF REPAIR DOUBLER BASED ON A VISUAL EVALUATION WITH THE REPAIR INSTALLED. VISUAL EVALUATION CONSISTED OF, CORRECT LOCATION SHAPE SIZE FASTENER SPACING AND EDGED MARGIN FASTENER TYPE AND NUMBER MATERIAL THICKNESS MATERIAL TYPE AND GENERAL WORKMANSHIP OF PREVIOUS INSTALLATION REMOVED EXISTING REPAIR AND REPAIRED IAW A310SRM 52-30-00 FIG 207.

Part: SPAR — CORRODED (CENTER WING) · airframe 38,388 hrs · 27,603 cycles

33 AREAS OF CORROSION AROUND FASTENERS ALONG FS 40 AT CTR WING TANK LOWER SPAR CHORD BETWEEN STRINGER 1 AND 5R (EXTERNAL OF TANK) C/W FEDEX EA6-5730-105024.

Part: SUPPORT — CORRODED (FUSELAGE) · airframe 38,388 hrs · 27,603 cycles

4 AREAS OF CORROSION AROUND FASTENERS ON HORIZONTAL LOWER SURFACE OF STRINGER SUPPORT STRAP AT FS 40 5L. REPAIRED PER FEDEX EA6-5730-105024.

Part: STRAP — CORRODED (FUSELAGE) · airframe 38,388 hrs · 27,603 cycles

12 AREAS OF CORROSION AROUND FASTENERS ON HORIZONTAL LOWER SURFACE OF STRINGER SUPPORT STRAP AT FS 40 STRINGER 3L. REPAIRED IAW WITH FEDEX EA6-5730-105024.

Part: SUPPORT — CORRODED (FUSELAGE) · airframe 38,388 hrs · 27,603 cycles

SEVEN AREAS OF CORROSION AROUND FASTENERS ON HORIZONTIAL LOWER SUFACE OF STRINGER SUPPORT AT FS 40 STRINGER 2L. REPAIRED IAW FEDEX EA6-5730-105024.

Part: STRINGER — DAMAGED (FUSELAGE) · airframe 38,388 hrs · 27,603 cycles

PREVIOUS REPAIR BULK CARGO UNDER FLOOR STRINGER 55 LT HAS A STRG REPAIR BETWEEN FS 66 AND 70 WITH 4 STRINGER SECTIONS AND 4 REPAIR SPLICES REPAIRED PER FEDEX EA6-5310-105016.

Part: FRAME — DAMAGED (FUSLEAGE) · airframe 38,388 hrs · 27,603 cycles

UPON REMOVAL OF WEB BETWEEN FS 12 - FS 13 FOUND 3 HOLES ELONGATED DOUBLE DRILLED FLOOR LEVEL LT SIDE AT FS 13 REPAIRED FRAME AT FS-13, IAW A310 SRM 53-12-31 FIG 201 SEE JPF FOR JOB TASK STEPS.

Part: FRAME — DAMAGED (FUSELAGE) · airframe 38,388 hrs · 27,603 cycles

UPON REMOVAL OF WEB RT BETWEEN FS 12 AND FS 13 3 HOLES ARE ELONGATED DOUBLE DRILLED FLOOR LEVEL AT FS 13 REPAIRED FRAME AT FS 13 RT IAW A310SRM 53-12-13 FIG 201 SEE JPF FOR JOB TASK STEP.

Part: STRINGER — MISREPAIRED (FUSELAGE) · airframe 38,388 hrs · 27,603 cycles

PREVIOUS REPAIR BULK CARGO UNDER FLOOR STRINGER 49 LT HAS A STRINGER REPAIR BETWEEN FRAMES 65 AND 66 WITH 1 STRINGER SECTION AND 1 REPAIR SPLICE PREVIOUSLY INSTALLED REPAIR LOCATED AT FRAME 65-66 ON STRINGER 49 LT WAS DETERMINED NOT TO BE IAW A310SRM 53-10-14 FIG 201 DUE TO INCORRECT STRINGER THICKNESS BASED ON A VISUAL EVALUATION WITH THE REPAIR INSTALLED VISUAL EVALUATION CONSISTED OF CORRECT LOCATION SHAPE SIZE FASTENER SPACING AND EDGE MARGIN FASTENER TYPE AND NUMBER MATERIAL THICKNESS MATERALTYPE AND GENERAL WORKMANSHIP OF PREVIOUS INSTALLATION REPAIRED STRINGER PER FEDEX EA6-5310-105015.

Part: SPAR — MISREPAIRED (HORIZONTAL STAB) · airframe 38,388 hrs · 27,603 cycles

PREVIOUS REPAIR, RT REAR UPPER SPAR CHORD HAS A STRAP REPAIR 13.5" LONG BETWEEN RIB 21 TO THE END OF THE SPAR CHORD. PREVIOUSLY INSTALLED REPAIR LOCATED AT RT THS REAR THS REAR UPPER SPAR CHORD BETWEEN RIB 21 TO O/B END OF SPAR CHORD WAS DETERMINED NOT TO BE IAW A310 SRM 55-11-21 FIG 212. INCORRECT AMOUNT OF HILOCKS BETWEEN EACH NUTPLATE BASED ON A VISUAL EVALUATION. THE REPAIR INSTALLED, VISUAL EVALUATION CONSISTED OF CORRECT LOCATION SHAPE SIZE FASTENER SPACING EDGE MARGIN FASTENER TYPE AND NUMBER MATERIAL THICKNESS MATERIAL TYPE GENERAL WORKMASHIP OF PREVIOUS INSTALLATION DRILLED AND INSTALLED ADDITIONAL HILOCK HOLES 4EA BETWEEN NUTPLATES TO CORRECT THE REPAIR PER A310SRM 55-11-21 FIG 212.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 38,388 hrs · 27,603 cycles

22 AREAS OF CORROSION AROUND FASTENERS ALONG STIFFENER 3 AFR43 BETWEEN CENTER WING TANK LOWER SKIN STRINGERS 2L AND 5L (EXTERNAL OF TANK). REPAIRED IAW FEDEX EA6-5730-105024.

Part: SPAR — CORRODED (HORIZ STAB) · corrosion level 2 · airframe 38,388 hrs · 27,603 cycles

AFTER REMOVAL OF LEADING EDGE OF LT HORIZONTAL STAB, FOUND CORROSION ON UPPER CHORD OF FORWARD SPAR NEAR RIB 10 REMOVED CORROSION IAW A310 SRM 51-74-10, CHECKED MATERIAL LOSS FOUND TO BE OUT OF LIMITS IAW A310 SRM 55-10-00 FIG 101 TABLE 101. INSTALLED STRAP REPAIR IAW A310 SRM 55-11-21 FIG 205 AND 206, REPROTECTED AREA IAW A310 SRM 51-75-10 AND 51-21-10.

Part: TRUNNION — CRACKED (LT MLG WW) · airframe 38,386 hrs · 27,602 cycles

FOUND LT GEAR AFT TRUNNION FWD SUPPORT FITTING CRACKED WHILE PERFORMING GEAR LUBE DURING B CHECK. AIRBUS FIELD TEAM REMOVED AND REPLACED LT GEAR TRUNNION.

Part: SUPPORT FITTING — CRACKED (LT MLG) · airframe 38,386 hrs · 27,602 cycles

FOUND LEFT GEAR AFT TRUNNION FWD SUPPORT FITTING CRACKED WHILE PERFORMING GEAR LUBE DURING B-CHECK.

Part: PANEL — DAMAGED (WING) · airframe 36,551 hrs · 26,453 cycles

PANEL LAND 650 KB HAS 1 EA ELONGATED HOLE. COMPLIED WITH EA 6-5730-55328A PT1.

Part: PANEL — DAMAGED (WING) · airframe 36,551 hrs · 26,453 cycles

PANEL 550HB HAS 2 EA ELONGATED HOLES. REPAIRED 1 EA HOLE IAW A310/200 SRM 51-40-44 FIG 1 CHAMBER CODE-J, COMPLIED WITH EA 6-5730-55328A PT 1 ON 1EA HOLE.

Part: IDG — INOPERATIVE (NR 2) · airframe 33,151 hrs · 24,432 cycles

DURING CLIMBOUT, NR 2 IDG TEMP CONT TO CLIMB. VERIFIED NR 2 IDG DEFERRED CORRECTLY. VERIFIED PROPER SERVICE ACCOMPLISH. NO FAULTS NOTED. IDG TEMP WITHIN LIMITS REF MM 24-11-00-001. AC OK FOR SERVICE. NR 2 IDG REMAINS DEFERRED.

Part: INDICATOR — ILLUMINATED (NR 1 ENGINE OIL) · airframe 33,029 hrs · 24,348 cycles

REJECTED T/O DUE TO AN OIL PRESSURE LIGHT ILLUMINATED ON NR 1 ENGINE.

Part: CONTROLLER — FAILED (CABIN PRESSURE) · airframe 32,920 hrs · 24,283 cycles

NR 1 CABIN PRESSURE FAILED AFT T/O, SEL NR 2 CABIN PRESSURE AC FAILED TO PRESSURIZE.

Part: DAMPER — FAILED (RH MLG) · airframe 32,399 hrs · 23,982 cycles

AFT TO LANDING GEAR WOULD NOT RETRACT IN SYS 1 OR 2. RECYCLED TWICE EACH SYS. REMOVED AND REPLACED RT MLG PITCH DAMPER IAW AMM 32-11-15. OPS CK PER IAW AMM 32-31-00-5.

Part: LANDING GEAR — MALFUNCTIONED (FUSELAGE) · airframe 32,399 hrs · 23,981 cycles

LANDING GEAR WON''T RETRACT. SERVICE RT PITCH DAMPER AND REPLACED PRESSURE DROP IND PER FEDEX AC MX WORK CARD NR 47B402.

Part: COMPUTER — INOPERATIVE (FUEL QUANTITY)

99-297 - ECAM AND MASTER SHOW CHECK FUEL MGMT. REMOVED AND REPLACED FUEL QTY COMPUTER PERFORM BITE CK.

Part: SWITCH — OUT OF ADJUST (NR 1 ENGINE TR)

NR 1 ENG REV UNLOCK LIGHT CAME ON AT APPROX 55 KTS ON T/O ROLL. ABORTED T/O. NR 1 THRUST REVERSER WAS DEFERRED MEL 78-1 CTRL NR 61783. ADJUSTED STOW SWITCHES PER A310 MM 78-31-00 PG 513. REACTIVATED T/R'S AND CLOSED FOA COWL DOORS PER A 310 MM 71-13-00. RAN NR 1 ENG TO OPS CHECK T/R AND ALL PARAMETERS MET PER JRH.

Part: FITTING — CRACKED (RT MLG DOOR ACT)

TWO MAIN CROSSBEAMS THAT RUN ACROSS THE LANDING GEAR BAY AND HOLD BOTH MLG DOOR ACTUATORS UPPER ATTACH ARE BROKEN. RT MLG DOOR ACTUATOR ATTACH FITTING WAS PULLED AWAY FROM MAIN CROSSBEAM. *S/D* REPAIRED PER EA 6-5310-42321.

Part: HYD ELEC PUMP — SHORTED (GREEN HYD SYST)

BURNT 101 VU WIRING CAUSED BY GREEN HYDRAULIC PUMP INTERNALLY SHORTED. C/B DID NOT POP. THIS CAUSED WIRING BEHIND 101 VU PANEL TO SMOKE AND BURN UP. REPLACED GREEN ELECTRIC HYDRAULIC PUMP. REPLACED 50 AMP CIRCUIT BREAKER, REPAIRED BURNT WIRING.