N446FE

Part: SWITCH — MALFUNCTIONED (NLG) · airframe 41,461 hrs · 29,153 cycles

ON APPROACH, NO NOSE GEAR INDICATION ON NR 1 SYS (FRONT PANEL) NR 2 SYS (OVERHEAD PANEL) GOOD, DID A GO AROUND AND ON DOWNWIND, NOSE GEAR LIGHT CAME BACK AND INDICATED NORMAL. WHEN LIGHT WAS NOT INDICATING , DID ALL LIGHTS CHECK AND IT CHECKED GOOD. RELEASED FOR SERVICE IAW MEL: 32-61-01-A CATEGORY: B EXPIRATION: 27NOV09 "MEL 32-61-01-A: (IDENTIFY) FWD ON (IDENTIFY FWD OR OVERHEAD) LANDING GEAR INDICATOR PANEL- INOP, REMOVED AND REPLACED. PERFORMED OPS TEST IAW AMM 32-61-00-5. NO FAULTS NOTED. FUNCTIONAL CHECK REQUIRES GEAR SWING. INSUFFICIENT GROUND TIME TO COMPLETE. ACFT TO CONTINUE WITH ITEM ON MEL REMOVED AND REPLACED NOSE GEAR SWITCH ON TELESCOPIC DRAG STRUT 40GB MM32-00-00-4. OPS CHECKED NORMAL.

Part: SPAR — DAMAGED (HORIZONTAL STAB) · airframe 39,685 hrs · 27,927 cycles

LEFT HORIZONTAL STAB ON UPPER REAR SPAR BETWEEN RIBS 10 AND 11 REPAIR STRAP REQUIRES REMOVAL FOR MATERIAL TYPE VERIFICATION REMOVED STRAP IAW A310-200 SRM 55-11-21 PG 202. FABRICATED NEW STRAP IAW A310-200 SRM 55-11-21 FIG 214 AND PG 285. INSTALLED NEW STRAP IAW A310-200 SRM 51-40-21.

Part: SPAR — DAMAGED (HORIZONTAL STAB) · airframe 39,685 hrs · 27,927 cycles

RIGHT HORIZONTAL STAB ON UPPER REAR SPAR BETWEEN RIBS 9 AND 10 REPAIR STRAP REQUIRES REMOVAL FOR MATERIAL TYPE VERIFICATION REMOVED STRAP REF A310-200 SRM 51-40-21. FABRICATED STRAP IAW FED ED A310-200 SRM 55-11-21 FIG 215 AND PG 285. INSTALLED REPAIR STRAP IAW FED EX SRM A310-200 SRM 55-11-21 FIG 215 AND PAGE 285.

Part: SPAR — FAILED (HORIZONTAL STAB) · airframe 39,685 hrs · 27,927 cycles

LEFT HORIZONTAL STAB ON UPPER REAR SPAR BETWEEN RIBS 4/5 REPAIR STRAP IN WRONG MATERIAL TYPE. REMOVE AND REPLACE AS REQUIRED REMOVED STRAP IAW A310-200 FX SRM 55-11-21. FABRICATED NEW STRAP IAW FX A310-200 SRM 55-11-21 FIG 214 AND PG 285. INSTALLED NEW STRAP IAW FX SRM A310-200 51-40-21.

Part: STRAP — CRACKED (R1 DOOR) · airframe 39,685 hrs · 27,927 cycles

AREA IS RT FWD PAX/CREW DOOR CUTOUT, 3 5/8 INCH CRACK WITH POSSIBLE EXFOLIATION CORROSION EXISTS ALONG TOP EDGE OF AFT CORNER STRAP, BEGINNING 1" FROM FWD EDGE OF CORNER STRAP. (LOWER, AFT CORNER OF DOOR CUTOUT BEHIND FAIL/SAFE RING) AREA MARKED IN RED. SEE ATTACHMENTS FOR DETAILS. FOUND USING HFEC INSPECTION NOTE: EVIDENCE OF PREVIOUS BLENDOUT PRESENT IN SAME EXACT AREA. 09-20-07 REMOVED AFT TAPERED SHIM IAW A310-200 SRM 51-40-21 PARA 7. INSTALLED TAPERED SHIM IAW FEDEX A310-200 SRM 51-40-21 PARA 7. MAJOR REPAIR.

Part: FRAME — CRACKED (FUSELAGE) · airframe 39,685 hrs · 27,927 cycles

FRAME CRACKED IN FASTENER HOLE AT FRAME 43A LOWER HOLE COMMON TO CRUCIFORM FITTING LT SIDE SEE JOB CARD 41X5271ALI FROM CABIN SIDE 1ST LAYER RUNNING IN THE 5 O`CLOCK DIRECTION .075 DEEP AND RUNNING TO THE 2ND LAYER 100 PERCENT ON SCREEN AMPLITUDE REMOVED AND REPLACED FRAME FITTING P/N A538-70037-200 IAW A310 SRM 51-40-02.

Part: STRAP — CRACKED (L1 DOOR) · airframe 39,685 hrs · 27,927 cycles

LT FWD PAX/CREW DOOR CUTOUT, HFEC INSPECTION INDICATES CRACK/CORROSION IN 5 LOCATIONS ALONG EDGE OF LOWER CORNER STRAPS AS FOLLOWS; (1) FWD LOWER CORNER- ONE 1/2" LONG AND ONE 1.0" LONG AND, (2) AFT LOWER CORNER - ONE 2 1/4" LONG, ONE 3/8" LONG AND ONE 2" LONG. UNABLE TO VERIFY DEPTH USING ULTRASOUND PER NTM 53-30-02, 401, POSSIBLY DUE TO MINIMAL DEPTH OF DEFECTS. UNABLE TO SEE VISUALLY DUE TO PREVIOUS BUFFING OF AREA. 09-24-07 REMOVED FWD AND AFT TAPERED SHIMS, FABRICATED NEW FWD AND AFT TAPERED SHIMS, AND INSTALLED NEW FWD AND AFT TAPERED SHIMS IAW A310-200 SRM 51-20-41 AND AB DWG A53611516. ALODINED AND PRIMED IAW A310-200 MM 51-23-10-0. MAJOR REPAIR.

Part: STRAP — MISINSTALLED (HORIZONTAL STAB) · airframe 39,685 hrs · 27,927 cycles

LEFT HORIZ STAB ON UPPER REAR SPAR BETWEEN RIBS 5 AND 8 REPAIR STRAP REQUIRES REMOVAL FOR MATERIAL TYPE VERIFICATION REMOVED DOUBLER STRAP DUE INCORRECT MATL IN REF A310 SRM 55-11-21 PG 202. REPLACED STRAP DOUBLER IAW A310 SRM 55-11-21 FIG 214.

Part: FRAME — CRACKED (FUSELAGE) · airframe 39,685 hrs · 27,927 cycles

FRAME CRACKED IN FASTENER HOLE AT FRAME 42A LOWER HOLE COMMON TO CRICIFORM FITTING SEE JOB CARD 41 BY 5271ALI. RT SIDE FROM CABIN SIDE THE FIRST LAYER RUNNING IN THE 6 O`CLOCK AND 9 O`CLOCK DIRECTIONS APPROX .100 DEEP TO THE 2ND LAYER 100 PERCENT + AMPLITUDE ON SCREEN REMOVED AND REPLACED FRAME FITTING P/N A538-70037-201 IAW A310 SRM 51-40-2.

Part: STRAP — CRACKED (R1 DOOR) · airframe 39,685 hrs · 27,927 cycles

AREA IS RT FWD PAX/CREW DOOR CUTOUT. 1 1/8 INCH CRACK WITH POSSIBLE EXFOLIATION CORROSION EXISTS ALONG TOP EDGE OF FWD CORNER STRAP, BEGINNING APPROX 1 1/8 INCH FROM AFT EDGE OF CORNER STRAP, LOWER, FWD CORNER OF DOOR CUTOUT BEHIND FAILSAFE RING. AREA MARKED IN RED. FOUND USING HFEC INSPECTION. 09-20-07 REMOVED FWD TAPERED SHIM (CORNER STRAP) IAW FEDEX A310-200 SRM 51-40-21 PARA 7. INSTALLED TAPERED SHIM IAW FEDEX A310-200 SRM 51-40-21 PARA 7. MAJOR REPAIR

Part: STRINGER SPLICE — MISREPAIRED (ZONE 100) · airframe 39,685 hrs · 27,927 cycles

STGR SPLICE REPAIR BETWEEN FRAME 72/73 ON STGR 56R REQUIRES EVALUATION FOR MAJOR/MINOR DETERMINATION AND IF REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA VISUALLY INSPECTED STGR SPLICE REPAIR BETWEEN FRAME 72/73 AT STGR 56 RT AND FOUND MATERIAL TYPE FOR STGR COUPLING DID NOT CONFORM TO SRM GUIDE LINES. REMOVED AND REPLACED STGR COUPLING IAW A310 SRM 53-10-14 FIG 201.

Part: SEAT TRACK — SHEARED (ZONE 200) · airframe 39,685 hrs · 27,927 cycles

MAIN CABIN RIGHT SEAT TRACK Y-1959 AT FRAME 47 LUGS ARE BROKE OUT.

Part: SEAT TRACK — DAMAGED (ZONE 200) · airframe 39,685 hrs · 27,927 cycles

MAIN CABIN RT SEAT TRACK NR Y-1456 AT FRAME C63 LUGS BROKEN OUT. 09-11-07 REMOVED DAMAGED SECTION OF SEAT TRACK IAW A310 SRM 53-10-16. INSTALLED NEW SECTION OF SEAT TRACK AND SPLICE IAW A310 SRM 53-10-16

Part: CONTROLLER — FAILED (CABIN PRESSURE)

ON CLIMB-OUT, AIRCRAFT DID NOT PRESSURIZE. BOTH FWD AND AFT REG NR 2 VALVES WERE STUCK FULL OPEN AND SHOWING AMBER ON THE ECAM. DUPLICATED PROBLEM AT GATE, REPLACED NR 2 CABIN PRESSURE CONTROLLER PER A310-200 AMM21-31-11-4, OPERATIONAL CHECK NORMAL. PREMATURE REMOVAL/INSTALLATION OFF MFG 82010B040901, POS RH SRL 334, TAG 482A64, ON MFG 82010B040901, SRL 208,TAG 56432A.

Part: SWITCH — FAILED (MASTER ACTUATOR) · airframe 39,126 hrs · 27,563 cycles

NR 2 ENG REV UNLK LIGHT AND ECAM WARNING CAME ON AT FL 360, STAYED ON AFTER LANDING AND SHUTDOWN. REPEAT GRIP, FOUND THE MASTER ACTUATOR SECONDARY LOCK SWITCH RT SIDE FAILED CLOSED. REMOVED AND INSTALLED SAME REF A310-200 MM 78-31-16-4. OPS CHECKS GOOD SAME MM REF. LIGHT IS OUT AND T/R OPERATES NORMAL REF JRH.

Part: ENGINE — UNKNOWN (NR 2) · airframe 38,596 hrs · 27,277 cycles

ON INITIAL POWER-UP FOR TAKEOFF NUMBER 2 ENG WAS VERY SLOW TO ACCELERATE. TERMINATED THE TAKEOFF AT APPROXIMATELY 20 KTS AND CLEARED THE RUNWAY. TAXI'D BACK TO RUNWAY HELD THE BRAKES AND PUT NR 1 ENG TO 40 PERCENT N1. THE INDEX POINTER ON THE NR 1 THROTTLE WAS AT 7. PUSHED NR 2 THROTTLE UP TO 40 PERCENT N1, THE INDEX POINTER ON THE NR 2 THROTTLE WAS AT 30. CHECKED THROTTLE CONTROL LEVER BETWEEN TAKEOFF AND IDLE WHILE OBSERVING HMC POWER LEVEL MOTION PER ENG VISUAL CHECK TSM 72-00-00 FIGURE 111 ITEM 3. OPS CHECK NORMAL. RAN ENGINE NR 1 & 2 PER JRH, BOTH THROTTLES AT INDEX POINTER 7 PRODUCED SAME PERCENT N1. NO THROTTLE MISALIGNMENT FOUND. OPS CHECK NORMAL. OK FOR SERVICE.

Part: WIRE — BROKEN (THROTTLE) · airframe 37,683 hrs · 26,669 cycles

ABORTED TAKEOFF DUE TO ENG NR 2 FAILED TO STABILIZE AT 40 PERCENT POWER, WITH NR 1 ENG THROTTLE SET NORMALLY TO PRODUCE 40 PERCENT N1 THE NR 2 THROTTLE WAS THREE KNOB WIDTHS AHEAD AND STILL ONLY PRODUCING 25 PERCENT N1. FOUND WIRE BROKEN INSIDE RING TERMINAL. RE-TERMINATED WIRE 072007-18 PER STD WIRING PRACTICES. IDLE CHECK AND UP TO 40 PERCENT N1 WAS NORMAL ACCELERATION.

Part: TERMINAL BLOCK — LOOSE (NR 2 ENGINE) · airframe 37,468 hrs · 26,521 cycles

ON CLIMB-OUT, NOTICED NR 2 EGT NEEDLE/ANALOGUE GAUGE FLUCTATING-RECEIVED ECAM FOR NR 2 ENG OVERLIMITS. PULLED POWER BACK. GAUGE STABILIZED THEN STARTED TO FLUCTUATE AGAIN. RAN QRH, DECIDED TO RETURN. BURNED DOWN FUEL TO MAX LNBW. NORMAL LANDING, TAXI IN. DEBRIEFED CREW NO OTHER INDICATION ON NR 2 ENG FUEL FLOW, N1 AND N2 NORMAL. DURING SECURITY CK OF WIRE HARNESS ON ENG FOUND BOTH NUTS ON ENG TERMINAL BLOCK ON FAN CASE BEFORE CONNECTOR 4951P FINGER TIGHT. TIGHTENED NUTS PER SMP AND PROCEEDED TO CK WIRING FROM T591 JUNCTION BLOCK TO CONNECTOR 4951P. ALSO MEGGED WIRES. ACCOMPLISHED POWER RUN TO 1.3 EPR PER JRH CH 4-35.

Part: ARM — GOUGED (ZONE 300) · airframe 37,460 hrs · 26,514 cycles

NR 7 RUDDER HINGE ATTACHMENT BRACE ( A-FRAME) HAS GOUGE MARKS AND WEAR MARKS AT ATTACHMENT BOLT. REMOVED AND REPLACED NR 7 HINGE ARM IAW A310-200 AMM 55-36-47-4-01 AND 27-21-21-4-01.

Part: SKIN — CRACKED (LT WING) · airframe 37,459 hrs · 26,512 cycles

LEFT WING T/E BOTTOM SKIN HAS INDICATION OF CRACK ON I/B CORNER SIDE CUTOUT PANEL 581AB AS MARKED. COMPLIED WITH EA 6-5710-86028.

Part: STRUCTURE — CORRODED (FUSELAGE) · airframe 37,459 hrs · 26,512 cycles

CORROSION FOUND UNDER THE NR 9 LATCH ROLLER FOR FWD CARGO DOOR. COMPLIED WITH EA 6-5310-86132.

Part: SKIN — CORRODED (FUSELAGE) · airframe 37,459 hrs · 26,512 cycles

CORR B/T STR 34-35 FROM FS 39 AFT APPROX 8 IN LT REF N00850. COMPLIED WITH EA 6-5315-86078.

Part: RIB — DAMAGED (ELEVATOR) · corrosion level 2 · airframe 37,459 hrs · 26,512 cycles

UPON REMOVAL OF EXISTING REPAIR ON N/R N00817 ON RT ELEVATOR INBOARD T/E LWR SURFACE FOUND 2EA AREAS OF CORROSION .5 X .5 INCH 1 ON INBOARD SIDE OF REPAIR, 1 ON OUTBOARD SIDE OF REPAIR (RIB 5 AND RIB 9). REMOVED CORROSION PER A310-200 SRM 51-74-10, 1EA AREA INBOARD OF ORIGINAL REPAIR OUT OF LIMITS. REPAIR THIS AREA IAW SRM 55-21-11 CONFIG 1 FIG 203, 1EA AREA O/B OF ORIGINAL REPAIR NO MAT'L LOSS FOUND TO BE WITHIN LIMITS PER SRM 55-20-00 PB 101. APPLIED FILLER & FINISHED PER A310-200 SRM 51-75-10.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 37,459 hrs · 26,512 cycles

BULK PIT FLOOR SUPPORT AT FR67 FROM 12 INCHES TO LT CTR TO 36 INCHES TO LT OF CTR, 4EA AREAS OF CORROSION EXTENDING UNDER FASTENER HEADS AS MARKED. REMOVED AND REPLACED CROSS BEAM FLOOR SUPPORT IAW 51-72-10. REMOVED 4EA AREAS OF CORROSION IAW SRM 51-74-10.

Part: SKIN — CORRODED (FUSELAGE) · airframe 37,459 hrs · 26,512 cycles

AFT PIT UNDER FLOOR 16 INCH FWD OF FS 54.1, STG 47R HAS CORROSION. REMOVED CORROSION IAW A310-200 SRM 51-74-10. AREA WAS OUT OF LIMITS IAW A310-200 SRM 53-10-00. REMOVED AND REPLACED DAMAGED AREA IAW A310-200 SRM 53-10-14. TREATED, PRIMED, TOPCOATED IAW A310-200 SRM 51-21-10. SEALED AREA IAW A310-200 SRM 51-76-00.

Part: DOOR — DAMAGED (NLG) · airframe 37,459 hrs · 26,512 cycles

NOSE LANDING GEAR DOORS HAS STRUCTURAL DAMAGE REF N00748. REPAIRED RT GEAR DOORS IAW SRM 52-82-11 C1 FIG 201.

Part: RIB — CRACKED (RT WING) · airframe 37,459 hrs · 26,512 cycles

RT WING L/E UPPER SIDE OF PANEL LANDING, LANDING FOR PANEL HAS 2 EA CRACKS AT 11 IN I/B OF RIB 14 AND 11 IN O/B OF RIB 14 REF N00631. REMOVED AND REPLACED PANEL LANDING IAW SRM 51-40-21 AND DRW A57244165.

Part: FLAP TRACK — CORRODED (RT WING) · airframe 37,459 hrs · 26,512 cycles

RT WING FLAP O/B UPPER SURFACE AT NR 3 FLAP TRACK AND NR 4 FLAP TRACK HAS 2 EA AREAS OF NOTED CORROSION REF N00771. REMOVED CORR IAW SRM 51-74-10, FOUND IN LIMITS IAW SRM 57-53-12.

Part: ATTACH FITTING — CORRODED (VERTICAL STAB) · airframe 37,459 hrs · 26,512 cycles

VERTICAL STAB UPPER EDGE LEFT AND RIGHT FORE TO AFT HAS CORROSION AROUND CAP ATTACH FASTENER HOLES REF N00734. REMOVED AND REPLACED RT CHORD IAW SRM 51-40-21 AND DRW A55371360 AND REPAIRED LT CHORD IAW SRM 51-74-40 FIG 201

Part: SKIN — DAMAGED (LT ELEVATOR) · airframe 37,459 hrs · 26,512 cycles

REPAIR FUSELAGE AT LT ELEVATOR T/E AFT FROM OB END HAS NO DATA REF N00806. REMOVED AND INSTALLED CORRECT REPAIR IAW EA 6-5100-87090 REF A310 SRM 55-21-11, REPAIR NR 5 G.

Part: PANEL — DAMAGED (RT WING) · airframe 37,459 hrs · 26,512 cycles

RT WING PANEL 650JB HAS 4 EA ELONGATED REF N00522. REPAIRED PANEL 650JB IAW EA 6-5710-86051.

Part: SHEAR TIE — CORRODED (FUSELAGE) · airframe 37,459 hrs · 26,512 cycles

BULK PIT UNDER FLOOR FR 68 FWD 10 IN STR 53R HAS CORROSION AN AREA EXTENDING UNDER SHEAR TIE AND FASTENERS. REPAIRED AREA IAW SRM 53-10-00 FIG 104 AND SRM 53-10-14 REF N00749.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 37,459 hrs · 26,512 cycles

AFT PIT FLOOR FS 66 10 INCH TO RT OF CTR HAS A 5 INCH BY 2 INCH AREA OF CORROSION. REMOVED CORROSION PER A310-200 SRM 51-74-10. CORROSION OUT OF LIMITS PER SRM 51-10-00. REMOVED CORRODED FLOORBEAM AND INSTALLED NEW BEAM PER A310-200 SRM 51-72-10. REPROTECTED FASTENER HEADS AND TAILS PER A310-200 SRM 53-21-10. SCRAPPED OLD PART PER QC5-0025.

Part: PLATE — CORRODED (FUSELAGE) · airframe 37,459 hrs · 26,512 cycles

BULK CARGO DOOR CUTOUT ON LWR FWD TOP EDGE OF SCUFF PLATE SURFACE CORROSION. REMOVED SCUFF PLATE AND REMOVED CORROSION IAW SRM 51-74-10 FOUND IN LIMITS IAW SRM 53-10-00. RESTORED FINISH AND REINSTALLED SCUFF PLATE IAW SRM 53-10-18-4.

Part: SKIN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 37,459 hrs · 26,512 cycles

BULK PIT UNDER FLOOR AREA FR69 STG48L HAS AN AREA THAT EXTEND 2" FWD OF FR 69 OF CORROSION EXTENDING UNDER SHEAR TIE. REMOVED SHEAR TIE AND STRINGER SECTION IAW A310-200 SRM 53-10-14. INSTALLED SHEAR TIE AND STRINGER SECTION IAW A310-200 SRM 53-10-14.

Part: SHEAR TIE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 37,459 hrs · 26,512 cycles

BULK PIT UNDER FLOOR STG 53R FROM 1 INCH FWD OF 66 TO FR 67 HAS CORROSION EXTENDING UNDER SHEAR TIE AT FR 66 AND EXTENDING UNDER FASTENERS IN SEVERAL AREAS. REMOVED CORROSION, CHECK LIMITS MAT'L LOSS EXCEEDED LIMITS IAW A310-200 SRM 53-10-00 FIG 104. REMOVED CORROSION STG SECTION AND FAB REPAIR IAW A310-200 SRM 53-10-14 AND INSTALLED IAW A310-200 SRM 51-40-21.

Part: PANEL — DAMAGED (LT WING) · airframe 37,459 hrs · 26,512 cycles

LT WING PANEL 550HB HAS 2 EA ELONGATED HOLES REF N00520. REPAIRED HOLES IAW EA 6-5710-85051.

Part: SKIN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 37,459 hrs · 26,512 cycles

BULK PIT UNDER FLOOR AREA FS 69 STR 48 LT HAS AN AREA THAT EXTEND 2 INCHES FWD OF FS 69 OF CORROSION EXTENDING UNDER SHEAR TIE. REMOVED SHEAR TIE AND STRINGER SECTION IAW A310-200 SRM 53-10-14. INSTALLED SHEAR TIE AND STRINGER SECTION IAW A310-200 SRM 53-10-14.

Part: SHEAR TIE — CORRODED (FUSELAGE) · airframe 37,459 hrs · 26,512 cycles

BULK PIT UNDER FLOOR STR 55L FROM FR 65 TO FR 66 HAS CORROSION EXTENDS BETWEEN SPLICE ANGLE AND STR AND UNDER SHEAR TIE AT FR66 REF N00765. REPAIRED STR 55L IAW SRM 53-10-14 AND REMOVED AND REPLACED SPLICE IAW SRM 51-40-21. REMOVED CORROSION IAW SRM 51-74-10, FOUND IN LIMITS.

Part: PANEL — DAMAGED (RT WING) · airframe 37,459 hrs · 26,512 cycles

RT WING PANEL 650KB HAS 4 EA ELONGATED HOLES REF N00521. REPAIRED PANEL IAW EA 6-5710-86051.

Part: SHEAR TIE — CORRODED (FUSELAGE) · airframe 37,459 hrs · 26,512 cycles

BULK PIT UNDER FLOOR STG 55L FROM FS 65 TO FS 66 HAS CORROSION AND CORROSION. EXTENDS BETWEEN SPLICE ANGLE AND STG AND UNDER SHEAR TIE AT FS 66. REMOVED CORROSION IAW A310-200 SRM 51-74-10. STRINGER CORRODED BEYOND ALLOWABLE LIMITS AS PER A310-200 SRM 51-10-00. CUT AND REPAIRED STRINGER IAW A310-200 SRM 53-10-14. REMOVED AND REPLACED PRODUCTION SPLICE AT FRAME 65 IAW A310-200 SRM 51-72-10 AND 51-40-21.

Part: WING ROOT — CORRODED (RT WING) · airframe 37,459 hrs · 26,512 cycles

TWO AREAS OF CORROSION AT RT WING TO FUSE FILLET AREA FR 39 STR 34-35 REF N00735 & E-6-5310-7-3315 A1 PT8. C/W AIRBUS S/B A310-53-2069 AND EO 6-5310-7-3315 ERF N00735.

Part: STRUCTURE — CORRODED (CARGO FLOOR) · corrosion level 2 · airframe 37,459 hrs · 26,512 cycles

AFT PIT UNDER FLOOR FROM 12 INCH FWD OF FS 59 TO 3 INCHES FWD OF FS 59 STG44L HAS CORROSION. REMOVED CORROSION IAW A310-200 SRM 51-74-10. THE AREA WAS FOUND OUT OF LIMITS IAW A310-200 SRM 53-10-00. REPAIRED STRINGER IAW A310-200 SRM 53-10-14. TREATED, PRIMED AND TOPCOATED IAW A310-200 SRM 51-23-10.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 37,459 hrs · 26,512 cycles

MDC NR 4 SEAT TRACK RT OF CENTER AT FR19 ON I/B SPLICE HAS CORROSION ON UPPER SURFACE. REMOVED AND REPLACED SPLICE ANGLE AT FR19 IAW SRM 51-40-21.

Part: PANEL — CRACKED (RT WING) · airframe 37,459 hrs · 26,512 cycles

UPON REMOVAL OF LANDING AT RT WING HINGE PANEL ON L/E FOUND PANEL LANDING CRACKED REF N00915. REMOVED AND REPLACED PANEL LANDING IAW SRM 51-40-21 AND DRW A572-434548.

Part: ANGLE — CORRODED (HORIZONTAL STAB) · airframe 37,459 hrs · 26,512 cycles

THS ACTUATOR STRUCTURAL HOUSING HAS APPROX 12 INCH OF CORROSION (10 EA. AREAS). REMOVED CORROSION IN 10 EA AREAS ON THS ACTUATOR STRUCTURAL HOUSING. ALL AREAS WERE WITHIN LIMITS EXCEPT AREA 10 WHICH WAS OUT OF LIMITS IAW A310-200 SRM 53-10-00. REMOVED L-ANGLE IAW A310-200 SRM 51-40-21 AND INSTALLED NEW L-ANGLE IAW A310-200 SRM 51-72-10 AND DRAWING NR A534-72550.

Part: SKIN — PUNCTURED (RT WING TE FLAP) · airframe 37,459 hrs · 26,512 cycles

RT WING I/B FLAP UPPER SURFACE 3.9 IN FROM T/E AND 30 IN FROM I/B END SKIN PUNCTURED REF N00914. REPAIRED FLAP IAW SRM 57-52-12 FIG 4D.

Part: RIB — CRACKED (RT WING) · airframe 37,459 hrs · 26,512 cycles

RT WING 4 IN IB OF RIB 30 L/E AREA AFT PANEL LANDING IS CRACKED REF N00636. REMOVED AND REPLACED LANDING IAW SRM 51-40-21 AND 51-72-10 AND DRW A57243955.

Part: DOUBLER — DAMAGED (ELEVATOR) · airframe 37,459 hrs · 26,512 cycles

REPAIR ON RT ELEVATOR I/B T/E LOWER SURFACE REQUIRES EVALUATION REF N00817. REMOVED EXISTING REPAIR AND INSTALLED CORRECT REPAIR IAW SRM 55-21-11 CONF 1 FIG 203 AND EA 6-5510-86111.

Part: PANEL — DAMAGED (RT WING) · airframe 37,459 hrs · 26,512 cycles

RT WING PANEL 650HB HAS 3 EA ELONGATED HOLES REF N00523. REPAIRED PANEL 650HB IAW EA 6-5710-86051.

Part: SKIN — CRACKED (RT WING) · airframe 37,459 hrs · 26,512 cycles

RT WING T/E SKIN HAS A .4 CRACK ON IB CORNER OF CUTOUT FOR PANEL 681 AB REF N00265. REPAIRED SKIN IAW EA 6-5710-86028.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 37,459 hrs · 26,512 cycles

MDCC NR 4 SEAT TRACK RT OF CENTER FROM FR 16 TO FR 19 CORRODED REF N00517. REMOVED AND REPLACED SEAT TRACK IAW SRM 51-40-21.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 37,459 hrs · 26,512 cycles

NR 4 SEAT TRACK LT OF CENTER FROM FS 16 TO FS 18 HAS CORROSION REF N00519. REMOVED AND REPLACED SEAT TRACK FROM FS 16 TO FS 18 IAW SRM 51-40-21 AND EA 6-5310-86038.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 37,459 hrs · 26,512 cycles

BULK PIT UNDER FLOOR STG 49R FR 64 FWD 4 IN TO AFT 4 IN 1 IN I/B AND O/B OF STG HAS CORROSION EXTENDING UNDER FRAME REF N00781. REMOVED CORRODED AREA OUT OF LIMITS, REPAIRED STG IAW SRM 53-10-14.

Part: PANEL — DAMAGED (LT WING) · airframe 37,459 hrs · 26,512 cycles

LEFT WING PANEL 550GB HAS ONE ELONGATED HOLE (LANDING). REPAIRED PANEL 550GB LANDING IAW TD/JI/SI/00339/2005 AS PER FEDEX EA 6-5710-86051.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 37,459 hrs · 26,512 cycles

BULK PIT UNDER FLOOR STG 54L 10 IN AFT OF FR 67 IS AN AREA 5 X 2 OF CORROSION EXTENDING UNDER FASTENERS. REMOVED CORROSION FOUND OUT OF LIMITS, REPAIRED IAW 53-10-14.

Part: SHEAR TIE — DAMAGED (FUSELAGE) · corrosion level 2 · airframe 37,459 hrs · 26,512 cycles

BULKPIT UNDER FLOOR FR64 FWD 8 INCHES TO AFT 14 INCHES EXTENDING 1 INCH INBOARD AND OUTBOARD OF STG 47R AND EXTENDING UNDER SHEAR TIE AND FRAME. REMOVED CORROSION IAW A310-200 SRM 51-74-10. AREA WAS OUT OF LIMITS IAW A310-200 SRM 53-10-00. REMOVED AND REPLACED DAMAGED AREA IAW A310-200 SRM 53-10-14. TREATED, PRIMED AND TOPCOATED IAW A310-200 SRM 51-21-10. SEALED AREA IAW A310-200 SRM 51-76-00.

Part: SPAR — CORRODED (RT STABILIZER) · airframe 37,459 hrs · 26,512 cycles

RIGHT STAB REAR SPAR STA 812 HAS 1 INCH OF CORROSION, 1 INCH AT STA 258, 1 INCH AT STA 158. REMOVED CORROSION FOUND OUT OF LIMITS, REPAIRED SPAR IAW SRM 55-11-21.

Part: ATTACH FITTING — CORRODED (LAVATORY ATTACH) · airframe 37,459 hrs · 26,512 cycles

LAV-A LOCKDOWN FITTING IS SEVERLY CORRODED REF N000672. REMOVED AND REPLACED LAV-A LOCKDOWN FITTING IAW SRM 51-72-10.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 37,459 hrs · 26,512 cycles

BULK PIT FLOOR T-CAP BETWEEN FR65 AND FR66 24 INCHES TO RT OF CTR HAS A 6 X 1 INCHES OF CORROSION. REMOVED CORRODED SECTION & INSTALLED NEW SECTION PER A310 SRM 51-72-10 & REPROTECTED FASTENERS PER A31-200 SRM 53-21-10. T-CAP WAS CORRODED BEYOND LIMITS AS GIVEN IN A310-200 SRM 53-10-00 FIG 4. CAP HAS BEEN CORRODED UP TO 50 PERCENT MAT'L LOSS BEFORE BEING WORKED.

Part: PANEL — DAMAGED (LT WING) · airframe 37,459 hrs · 26,512 cycles

LEFT WING PANEL 550PB HAS 2 EA ELONGATED HOLES (LANDING). REPAIRED PANEL 550PB LANDING IAW TD/JI/SI/00339/2005 AS PER FEDEX EA 6-5710-86051.

Part: SPAR — CORRODED (LT STABILIZER) · airframe 37,459 hrs · 26,512 cycles

LEFT STAB REAR SPAR STA 158, 2 INCHES OF CORROSION AND STA 258 HAS 1 INCH OF CORROSION REF N00264. REMOVED CORROSION FOUND OUT OF LIMITS, REPAIRED IAW SRM 55-11-21 FIG 215.

Part: THRUST REVERSER — CRACKED (NR 2 ENGINE) · airframe 37,459 hrs · 26,512 cycles

NR 2 ENG B/B THRUST REVERSER HAS 3 EA AREAS BENT WITH POSS CRACKS 1 X .3 X .020, .3 X .2 X .009 AND .2 X .2 X .050 REF N00251. CLEANED UP DAMAGE IAW P&W JT9D-7R4 SRM 54-30-00. VERIFIED NO CRACKS IAW NTM 51-10-08.

Part: RIB — CRACKED (NR 1 PYLON) · airframe 37,459 hrs · 26,512 cycles

NR 1 PYLON 1 INCH AFT OF RIB 19 I/B SIDE WEB ATTACH POINT HAS A .5 INCH CRACK REF N00647. REMOVED AND REPLACED WEB AT RIB 19 IAW SRM 51-40-21 & 51-72-10.

Part: SUPPORT ANGLE — CRACKED (NR 1 PYLON) · airframe 37,459 hrs · 26,512 cycles

NR 1 PYLON - ACCESS 475AL- RT UPPER INTERIOR ANGLE SUPPORT CRACKED IN T-SHAPED LENGTH EA WAY 1.0 INCH REF N00449. REMOVED AND REPLACED ANGLE SUPPORT IAW SRM 54-55-51.

Part: STRINGER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 37,459 hrs · 26,512 cycles

BULKPIT UNDER FLOOR STRINGER 49R 6 INCHES AFT OF FR65 HAS AN AREA OF 0.5 X 0.5 INCH OF CORROSION. REMOVED CORROSION AT BULKPIT UNDER FLOOR FR65 STG 49R IAW A310-200 SRM 51-74-10. CHECKED MATERIAL LOSS FOUND TO BE OUT OF LIMITS IAW A310-200 SRM 53-10-00 FIG 104. REPAIRED STRINGER CONNECTING SECTION IAW A310-200 SRM 51-72-10.

Part: STRINGER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 37,459 hrs · 26,512 cycles

BULK PIT UNDER FLOOR FR 65 STG 54R HAS A 5 X 2 INCH AREA OF CORROSION ON SPLICE EXTENDING UNDER FASTENERS. REMOVED SPLICE ANGLE IAW A310-200 SRM 51-40-21. REMOVED CORROSION IAW A310-200 SRM 51-74-10. AREA OUT OF LIMITS IAW A310-200 SRM 53-10-00. REPLACED DAMAGED STRINGER IAW A310-200 SRM 53-10-14. TREATED, PRIMED, TOPCOATED IAW A310-200 SRM 51-21-10. REPLACED SPICE ANGLE IAW A310-200 SRM 51-40-21.

Part: STRUCTURE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 37,459 hrs · 26,512 cycles

BULKPIT UNDER FLOOR 5 INCHES AFT OF FR 65 STG 51R HAS AN AREA 1 X 1 INCH OF CORROSION EXTENDING UNDER FASTENERS. REMOVED CORROSION IAW A310-200 SRM 51-74-10. AREA WAS OUT OF LIMITS IAW A310-200 SRM 53-10-00. REMOVED AND REPLACED DAMAGED AREA IAW A310-200 SRM 53-10-14. TREATED, PRIMED, TOPCOATED AREA IAW A310-200 SRM 51-21-10. SEALED AREA IAW A310-200 SRM 51-76-00.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 37,459 hrs · 26,512 cycles

BULK PIT UNDER FLOOR STG 50R FROM 10 INCHES AFT OF FR 64 TO FR 65, 1 INCH INBOARD OF STG TO 2 INCHES OUTBOARD OF STG HAS CORROSION EXTENDING ON AND UNDER BRACKETS AND STG SPLICE. REMOVED CORROSION IAW A310-200 SRM 51-74-10. AREA OUT OF LIMITS IAW A310-200 SRM 53-10-00. REMOVED DAMAGED SECTION IAW A310-200 SRM 53-10-14. TREATED AND PRIMED NEW PARTS IAW A310-200 SRM 53-10-44. INSTALLED NEW PARTS IAW A310-200 SRM 51-40-21. APPLIED TOPCOAT IAW A310-200 SRM 51-21-10. APPLIED FILLET SEAL IAW A310-200 SRM 51-76-00.

Part: CROSSBEAM — CORRODED (ZONE 100) · corrosion level 2 · airframe 37,459 hrs · 26,512 cycles

FWD CARGO BETWEEN RT ROLLER TRACKS NR 1 AND NR 2, 4TH CROSS BEAM AFT HAS 3 INCHES OF CORROSION. REMOVED CORROSION FROM CROSS BEAM BETWEEN NR 1 AND NR 2 ROLLER TRACKS ON RT SIDE IAW A310-200 SRM 51-74-10, OUT OF LIMITS ON CORROSION REMOVAL IAW A310-200 SRM 53-10-00. REMOVED OLD CROSS BEAM AND INSTALLED NEW CROSS BEAM IAW A310-200 SRM 51-42-00.

Part: SKIN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 37,459 hrs · 26,512 cycles

BULK PIT UNDER FLOOR FR 63 STR 44L HAS AN AREA OF CORROSION EXTENDING UNDER FRAME AND SHEAR TIE. REMOVED DAMAGED SECTION OF STRINGER AND REPAIRED IAW A310-200 SRM 53-10-14.

Part: SEAT TRACK — CORRODED (ZONE 200) · corrosion level 2 · airframe 37,459 hrs · 26,512 cycles

MDCC NR 2 SEAT TRACK RT OF CENTER LINE FROM FRAME 15 TO FRAME 18 HAS HEAVY CORROSION. REMOVED SEAT TRACK IAW A310-200 SRM 51-40-21. INSTALLED NEW SEAT TRACK IAW A310-200 SRM 51-40-21.

Part: SEAT TRACK — BROKEN (FUSELAGE) · airframe 37,459 hrs · 26,512 cycles

SEAT TRACK L-2 AT FRAME 52 HAS A BROKEN LUG, FOUND DURING CLS RE-INSTALLATION. REMOVED AND REPLACED SEAT TRACK SECTION IAW A310-200 SRM 53-10-16.

Part: SKIN — CRACKED (TAIL CONE) · airframe 37,459 hrs · 26,512 cycles

APU TAIL CONE FR 102 RT SIDE AT 3 O'CLOCK POSITION HAS A 6 INCH VERTICAL CRACK IN THE EXTERIOR SKIN. REPAIRED APU SKIN, STOPPED DRILLED CRACK IAW A310-200 SRM 53-19-12 PG 102. PERFORMED ET INSPECTION IAW A310-200 NTM 51-10-08. FABRICATED DOUBLER IAW A310-200 SRM 53-19-12 PG 207. HEAT TREATED RIVETS IAW A310-200 SRM 51-25-00. INSTALLED DOUBLER IAW A310-200 SRM 53-19-12. ALODINED, PRIMED AND TOP COATED DOUBLER IAW A310-200 SRM 51-23-20.

Part: SEAT TRACK — CORRODED (ZONE 200) · corrosion level 2 · airframe 37,459 hrs · 26,512 cycles

MDCC NR 2 SEAT TRACK LEFT OF CENTER LINE FROM FRAME 15 TO FR 19 HAS HEAVY CORROSION. REMOVED NR 2 SEAT TRACK, SPLICE AND COUPLING IAW A310-200 SRM 51-40-21. LOCATED AND DRILLED NEW SEAT TRACK, SPLICE AND COUPLING IAW A310-200 SRM 51-40-44. INSTALLED NEW SEAT TRACK, SPLICE AND COUPLING IAW A310-200 SRM 51-40-21.

Part: STRUCTURE — DAMAGED (SLAT) · airframe 37,459 hrs · 26,512 cycles

REPAIR ON LT O/B SLAT UPPER SURFACE NEEDS EVALUATION FOR FAA APPROVED DATA AND MAJOR OR MINOR CLASSIFICATION, REF CONFORMITY INSPECTION RECORD SHEET 3 ITEM 24. REPAIR DETERMINED TO BE ACCOMPLISHED IAW A310-200 SRM 57-40-00 FIG 201. CLASSIFIED AS A MINOR REPAIR PER FEDEX GMM 6-2-100.

Part: SEAT TRACK — CRACKED (ZONE 200) · airframe 37,459 hrs · 26,512 cycles

MAIN DECK CARGO COMP ZONE 146 AT FR 43 BETWEEN SEAT TRACKS R1 AND R2 DUMMY TRACK IS CRACKED. REMOVED AND REPLACED SEAT TRACK IAW A310-200 SRM 51-40-21 AND 51-72-10.

Part: WIRE HARNESS — FIRE (COCKPIT) · airframe 36,121 hrs · 25,629 cycles

EN ROUTE RIGHT SIDE SLIDING WINDOW HEAT POWER CORD CAUGHT FIRE. SWITCH WAS TURNED OFF AND FIRE WAS EXTINGUISHED. LANDED KLCK, INSP HEAT HARNESS WIRE, FOUND BURNED AREA. REMOVED FROM TERMINAL STRIP AND COMPLIED WITH PART 1 OF EA-6-3040-72501. PER MOCC REQUEST, REPLACED WINDOW TEMP CONTROLLER 20DG, PER A310 MM 30-42-11-4. REMOVED AND REPLACED CB'S 4DG, 6DG, AND 8DG REF A310, REF WRI 30-40-6952 FOR REPAIR OF WIRING. COMPLIED WITH EA 6-3040-72501, REMOVAL AND INSTALLATION OF RETRACTABLE WIRING ASSY ON RT SLIDING WINDOW REF A310. OPS CHECK OF RT WINDOW HEAT CHECKS NORMAL REF MM 30-42-00-5.

Part: CIRCUIT BREAKER — POPPED (ELECTRICAL SYS) · airframe 35,945 hrs · 25,530 cycles

PDIS 446 24-50 0006790 27JUN03 RDU CLOSE R LOST AC BUS 2 DURING TAKE OFF ROLL AT ABOUT 40 KTS. FACT 27JUN03 11:53 RDU R FOUND 202XP BUS BAR BREAKER POPPED AND NR 2 GE HYD PUMP C/B POPPED , RESET SAME BOTH GREEN PUMPS OPERATE NORMAL, NR 2 AC BUS FAULT CLEARED , OK FOR SERVICE.

Part: SKIN — CORRODED (ELEVATOR) · airframe 35,101 hrs · 25,010 cycles

RT ELEVATOR TRAILING EDGE LOWER SKIN IS CORRODED 40 CM OUTBD OF INBOARD EDGE. CLEANED CORROSION WITHIN LIMITS IN SRM 55-20-00.

Part: HINGE — WORN (ELEVATOR) · airframe 35,101 hrs · 25,010 cycles

ELEVATOR HINGE ARM BEARING WORN BEYOND LIMITS AT ELEVATOR HINGE NR 1 RT. HINGE ARM REMOVED FOR BEARING REPLACEMENT. REMOVED AND REPLACED BEARINGS PER AMM 55-16-43-4.

Part: BEARING — WORN (ELEVATOR) · airframe 35,101 hrs · 25,010 cycles

ELEVATOR HINGE ARM BEARING WORN BEYOND LIMITS AT ELEVATOR HINGE NR 1 LT. HINGE ARM REMOVED FOR BEARING REPLACEMENT. REMOVED AND REPLACED BEARINGS & HINGE ARM PER AMM 55-16-43-4.

Part: SEAL — LEAKING (NR 1 ENGINE) · airframe 35,101 hrs · 25,010 cycles

NR 1 ENGINE, STARTER DRIVE SHAFT OIL LEAKAGE. REMOVED AND REPLACED SEAL PER AMM.

Part: SEAL — LEAKING (NR 1 ENGINE) · airframe 35,101 hrs · 25,010 cycles

NR 1 ENG STARTER DRIVE SHAFT OIL LEAKAGE. REMOVED AND REPLACED SEAL PER AMM 72-65-07-4-A.

Part: PIN — ROTATED (VERTICAL STAB) · airframe 35,101 hrs · 25,010 cycles

VERTICAL STABILIZER LEFT MID ATTACH FITTING PIN INDICATOR LINE SHOWS PIN ROTATED. REMOVED AND REPLACED PIN PER AMM 55-36-39-6.

Part: HINGE — WORN (ELEVATOR) · airframe 35,101 hrs · 25,010 cycles

ELEVATOR HINGE ARM BEARING WORN BEYOND LIMITS AT ELEVATOR HINGE NR 6 RT. HINGE ARM REMOVED FOR BEARING REPLACEMENT. REMOVED AND REPLACED HINGE ARM PER AMM 55-22-13.

Part: BEARING — WORN (ELEVATOR) · airframe 35,101 hrs · 25,010 cycles

ELEVATOR HINGE ARM BEARING WORN BEYOND LIMITS AT ELEVATOR HINGE NR 7 RT. HINGE ARM REMOVED FOR BEARING REPLACEMENT. REMOVED AND REPLACED BEARINGS & HINGE ARM PER AMM 55-10-43-4.

Part: BEARING — WORN (ELEVATOR) · airframe 35,101 hrs · 25,010 cycles

ELEVATOR HINGE ARM BEARING WORN BEYOND LIMITS AT ELEVATOR HINGE NR 5 RT. HINGE ARM REMOVED FOR BEARING REPLACEMENT. REMOVED AND REPLACED BEARING AND HINGE ARM PER AMM 55-16-45.

Part: STRINGER — CORRODED (N/A) · airframe 35,101 hrs · 25,010 cycles

N 108 STRINGER 56R AT CONNECTOR AFT OF FRAME 72. R&R STRINGER PER SRM 53-10-14.

Part: STRUCTURE — DAMAGED (LT PYLON) · airframe 35,101 hrs · 25,010 cycles

LT PYLON AFT BRACKET WHERE HYD LINES PASSES THROUGH FROM WING TO PYLON FOUND HOLES ELONGATED. REMOVED AND REPLACED HOLES PER IAW EA 26-5210-64291.

Part: STRUCTURE — DAMAGED (RT WING) · airframe 35,101 hrs · 25,010 cycles

NR 2 RT PYLON AFT FAIRING UPPER SIDE HYDRAULIC LINES HOLE ELONGATED ON THE FAIRING SIDE. REMOVED AND REPLACED HYD LINE HOLES PER EA 6-5710-64292.

Part: WARNING LIGHT — ILLUMINATED (COCKPIT)

DURING T/O, NR 1 REVERSER UNLOCK LIGHT ILLUM. RELEASE PER MEL.

Part: CONTROL UNIT — MALFUNCTIONED (T/E FLAP) · airframe 34,246 hrs · 24,566 cycles

AFT T/O FLAP RETRACT AND ECAM ALERT FLAP 1 & 2 FAULT. SFCC 1 & 2 RESET. SLAT AND FLAP CYCLE CK NORMAL.

Part: CONTROLLER — FAILED (CABIN PRESSURE) · airframe 32,902 hrs · 23,764 cycles

AIR TURNBACK, FOR MULTIPLE FAILURES. NR 1, 2 PITCH TRIM, NR 2 A.T.S, NR 1, 2 TRANSPONDERS, NR 1 CABIN PRESS, CAPT TAT WARNING, CAPT A.S. & PFD. *S/D* REMOVED AND REPLACED RLY 10XE, PROX DET UNIT, NR 2 TRANSFORMER RECTIFIER MM 24-32-00-/5, MM 32-61-00/501.

Part: ENGINE — FAILED (NR 2) · airframe 32,885 hrs · 23,753 cycles

AFT 20 MIN OF FLT, CREW HEARD LOUD BANG, NR 2 ENGINE FAILED. NO IND ON N1 OR N2 IND''S. AC RETURNED TO MEM.

Part: ENGINE — FLAMED OUT (NR 1)

NR 1 ENGINE FLAMED OUT DURING CRUISE AT 5,000 FT, NO PRIOR INDICATIONS. CONT RELIGHT PLACED ON AND ENGINE RELIT IMMEDIATELY, N1 ROLLED BACK FROM APPROX 70 PERCENT TO 40 PERCENT BEFORE RELIGHT. FAILURE OCCURRED SHORTLY OR DURING AN AUTOTHROTTLE-COMMANDED POWER INCREASE FROM IDLE. IAS 250KTS, VMC. NO PARAMETERS EXCEEDED. NORMAL ENGINE OPERATIONS FOR REMAINDER OF FLIGHT.