N430FE

Part: SKIN — CRACKED (ZONE 100) · airframe 47,592 hrs · 23,420 cycles

NDT INSPECTION OF LT FRAME 54, SKIN JOINT BETWEEN S36 AND 37L, SHOWS SIX HOLES WITH POSITIVE CRACK INDICATIONS. INDICATIONS ARE AT MULTIPLE CLOCK POSITIONS. POSITIVE HOLES ARE 1, 5, 6, 8, 11 AND 13. REF ALI 53-15-90. COMPLIED WITH EA 6-5315-T0300240, REV.

Part: SHEAR TIE — DAMAGED (ZONE 100) · airframe 47,592 hrs · 23,420 cycles

WHILE ACCOMPLISHING WC E6-5310-7-5020 A PT2, FOUND FR 43 SHEAR TIE HAS SHORT E.D. REMOVED AND REPLACED IAW SRM 51-72-10 AND DWG 57112116

Part: SEAT TRACK — DAMAGED (ZONE 200) · airframe 47,592 hrs · 23,420 cycles

DUMMY TRACK 4L FR 54 / 54.2 FAILED GAP CHECK. REMOVED, REPAIRED AND INSTALLED DUMMY TRACK IAW SRM 53-15-16, FIG 203.

Part: SEAT TRACK — LOOSE (ZONE 200) · airframe 47,592 hrs · 23,420 cycles

DUMMMY TRACK 3R FR 38.2 /40 FAILS GAP CHECK. REMOVED DUMMY TRACK AT FR 38.2 /40 IAW SRM 51-40-21, PAR 5 & PAR 7. REPAIRED DUMMY TRACK IAW SRM 53-15-16 PG 209 -216, REINSTALLED TRACK AT FR 38.2 /40 IAW SRM 51-40-21, PAR 5-7. REPROTECTED AREA IAW SRM 51-75-10, PG 203-204.

Part: SEAT TRACK — WORN (FUSELAGE) · airframe 47,592 hrs · 23,420 cycles

DUMMY TRACK 2R FR 54 TO 54.2 FAILS GAP CHECK. REMOVED DUMMY TRACK 2R FR 54/54.2 IAW SRM 53-15-16. REPAIRED DUMMY TRACK 2R FR 54/54.2 IAW SRM 53-15-16. INSTALLED REPAIRED DUMMY TRACK 2R FR 54/54.2 IAW SRM 51-40-21 AND SRM 53-15-16.

Part: FLOORBEAM — CORRODED (ZONE 200) · airframe 47,592 hrs · 23,420 cycles

UPON REMOVAL OF SEAT TRACK SECTION, FOUND CORROSION ON FLOORBEAM UPPER TEE TOP SURFACE AT FR 16A, Y1959 (5L)(APPROX 1 SQ IN TOTAL)

Part: SEAT TRACK — CORRODED (ZONE 200) · airframe 47,592 hrs · 23,420 cycles

SEAT TRACK 5L AT FR 18 HAS CORROSION ON TOP SURFACE. REMOVED CORROSION, FOUND TO BE OUT OF LIMITS. REMOVED, FABRICATED IAW DWG. A53610798, AND REPLACED SEAT TRACK IAW SRM 51-40-21 PARA. 6 AND 13.

Part: FLOOR PANEL — DAMAGED (ZONE 200) · airframe 47,592 hrs · 23,420 cycles

FLOOR PANEL 252GF CRUSHED. FABRICATED REPLACEMENT FLOOR PANEL IAW DWG SRZ 25-005 REV. J.

Part: FLOOR PANEL — DAMAGED (ZONE 200) · airframe 47,592 hrs · 23,420 cycles

FLOOR PANEL 252MF CRUSHED. FABRICATED REPLACEMENT FLOOR PANEL IAW DWG SRZ25-005 REV J. REMOVED AND INSTALLED FLOOR PANEL IAW AMM 53-10-25-04

Part: ANGLE — CRACKED (ZONE 100) · airframe 47,592 hrs · 23,420 cycles

UPON INSP/NDT OF HOLES H1 AND H2 AT ARCH FITTING AT FR43 LT SHOWS INDICATION OF CRACK ON BRACKET SIDE. REMOVED AND REPLACED ANGLE IAW SRM 51-72-10.

Part: ATTACH ANGLE — CRACKED (ZONE 100) · airframe 47,592 hrs · 23,420 cycles

FOUND UPPER ATTACH ANGLE TO BE VISIBLY CRACKED. R & R FR 43 UPPER FWD ATTACH ANGLE AT ARCH FITTING IAW SRM 51-72-10.

Part: FLOOR PANEL — DAMAGED · airframe 47,592 hrs · 23,420 cycles

PANEL 232XH CRUSHED AT CLS. FABRICATED REPLACEMENT PANEL232XH IAW DWG SRZ-25-005, REV Z.

Part: FLOORBOARD — DAMAGED (ZONE 200) · airframe 47,592 hrs · 23,420 cycles

FLOORBOARD 242UJ CRUSHED AT CLS CUTOUT. FABRICATED REPLACEMENT FLOORBOARD IAW DWG SRZ 25-005, REV J.

Part: FLOORBOARD — DAMAGED (ZONE 200) · airframe 47,592 hrs · 23,420 cycles

FLOORBOARD 232SF IS CRUSHED AT CLS CUTOUT. FABRICATED FLOORBOARD IAW DWG SRZ 25-005, REV J.

Part: FLOOR PANEL — DAMAGED (CABIN) · airframe 47,592 hrs · 23,420 cycles

FLOOR PANEL 252BF CRUSHED AT CUTOUT. FABRICATED REPLACEMENT FLOOR PANEL IAW DWG SRZ-25-005, REV J.

Part: FLOOR PANEL — CRACKED (ZONE 200) · airframe 47,592 hrs · 23,420 cycles

FLOOR PANEL 252 UF HAS 10 INCH CRACK. FABRICATED REPLACEMENT FLOOR PANEL IAW DWG SRZ 25-005 REV. J.

Part: FLOOR PANEL — DAMAGED (ZONE 200) · airframe 47,592 hrs · 23,420 cycles

FLOOR PANEL 242QJ CRUSHED AT CLS CUTOUT. FABRICATED FLOOR PANEL IAW DWG SRZ 25-005, REV J.

Part: FLOORBOARD — DELAMINATED (ZONE 200) · airframe 47,592 hrs · 23,420 cycles

FLOORBOARD 232LT IS CRUSHED AT CLS CUTOUT. FABRICATED REPLACEMENT FLOORBOARD IAW DWG SRZ 25-005, REV J.

Part: FLOOR PANEL — CRACKED (ZONE 200) · airframe 47,592 hrs · 23,420 cycles

FLOOR PANEL 251GF HAS 12 INCH CRACK. FABRICATED REPLACEMENT FLOOR PANEL IAW DWG SRZ25-005 REV J. REMOVED AND REPLACED FLOOR PANEL IAW AMM 53-10-25-04.

Part: FLOOR PANEL — DAMAGED (CABIN) · airframe 47,592 hrs · 23,420 cycles

FLOOR PANEL 252SF CRUSHED AT CUTOUTS. FABRICATED REPLACEMENT FLOOR PANEL IAW DWG SRZ-25-005, REV J.

Part: FLOOR PANEL — CRUSHED (CABIN) · airframe 47,592 hrs · 23,420 cycles

FLOOR PANEL 242EK CRUSHED AT CUTOUT. FABRICATED REPLACEMENT FLOOR PANEL IAW DWG SRZ-25-005, REV J.

Part: FLOOR PANEL — CRUSHED (CABIN) · airframe 47,592 hrs · 23,420 cycles

FLOOR PANEL 242ZJ CRUSHED AT CUTOUT. FABRICATED REPLACEMENT PANEL IAW DWG SRZ-25-005, REV J.

Part: FLOOR PANEL — DAMAGED (CABIN) · airframe 47,592 hrs · 23,420 cycles

FLOOR PANEL 241NK IS BROKEN IN HALF AT CLS CUTOUT. FABRICATED REPLACEMENT FLOOR PANEL IAW DWG SRZ-25-005 REV. J.

Part: FLOOR PANEL — DAMAGED (CABIN) · airframe 47,592 hrs · 23,420 cycles

FLOOR PANEL 147AF EDGE SEALANT SOFTENED & MISSING BY A PERIMETER LENGTH OF 50". FABRICATED REPLACEMENT FLOOR PANEL IAW DWG SRZ 25-005, REV J.

Part: PRESSURE SWITCH — FAILED (NR 2 ENGINE) · airframe 46,823 hrs · 22,923 cycles

NR 2 ENGINE FUEL FILTER CLOG ECAM/ MASTER CAUTION IMMEDIATELY AFTER TAKE OFF. ECAM CAUTION EXTINGUISHED AROUND 80 PERCENT N1 WHEN THROTTLES RETARDED. REMOVED AND INSPECTED NR 2 ENGINE FUEL FILTER. NO DEBRIS FOUND. INSTALLED NEW FILTER IAW MM 73-12-03-02. R & R NR 2 ENGINE FUEL FILTER DIFFERENTIAL PRESSURE SWITCH IAW MM 73-34-11-04. RAN ENG IDLE & LEAK CHECKED GOOD. RAN ENG AT TAKE OFF POWER, NO CLOG LIGHT OR MESSAGE. ACFT OK FOR SERVICE.

Part: FRAME — CRACKED (E/E BAY DOORWAY) · airframe 45,799 hrs · 22,287 cycles

AVIONICS COMPARTMENT FORWARD DOOR INT SIDE, AFT FRAME IS CRACKED IN 2 PLACES AT LIGHTENING HOLES. CRACKED DOOR FRAME WAS REMOVED PER SRM 51-40-21, PARA 6. NEW FRAME WAS FABRICATED PER DWG A52110744, ISSUE "F". FRAME WAS ALODINED PER SRM 51-21-10, PAGE 2. PRIMED AND PAINTED PER SRM 51-32-10 PAGE TABLE 1. INSTALLED PER SRM 51-72-10, PAGE 2.

Part: TRANSITION PANEL — CORRODED (ZONE 100) · corrosion level 2 · airframe 45,799 hrs · 22,287 cycles

FWD CARGO COMPARTMENT TRANSITION PANEL 132 WF HAS MULTIPLE AREAS OF CORROSION, FRONT AND BACK. TRANSITION PANEL WAS CORRODED AND FOUND TO BE OUT OF LIMITS IAW SRM 51-74-10. PANEL WAS REMOVED AND FABRICATED IAW DWG A53272783 AND SRM 51-71-40. PARTS WERE ALODINED IAW SRM 51-21-10, PARA 2-B. PRIMED AND PAINTED IAW SRM 51-23-10, PARA 2-B. REASSEMBLED IAW SRM 51-40-21, PARA 6 AND DWG A53272783.

Part: TRANSITION PANEL — CORRODED (ZONE 100) · corrosion level 2 · airframe 45,799 hrs · 22,287 cycles

FWD CARGO COMPARTMENT TRANSITION PANEL 131 WF HAS MULTIPLE AREAS OF CORROSION ON THE FRONT. TRANSITION PANEL WAS CORRODED AND FOUND TO BE OUT OF LIMITS IAW SRM 51-74-10. PANEL WAS REMOVED AND FABRICATED IAW DWG A53272783 AND SRM 51-71-40. PARTS WERE ALODINED IAW SRM 51-21-10, PARA 2-B. PRIMED AND PAINTED IAW SRM 51-23-10, PARA 2-B. REASSEMBLED IAW SRM 51-40-21, PARA 6 AND A53272783.

Part: SKIN — DENTED (LT WING TE FLAP) · airframe 45,799 hrs · 22,287 cycles

LT WING INBD FLAP SKIN IS DENTED. BLENDED AREA NOTED; FOUND 100 PERCENT MATERIAL THICKNESS GONE IAW SRM 57-52-12, FIG 107. REMOVED DAMAGED SKIN AND REPAIRED IAW SRM 57-52-10, FIG 204 & PARA 4-D. ALODINED BARE SURFACES, SEALED DOUBLER & PRIMED IAW SRM 57-52-12, PARA 4-D (3) & SRM 51-75-10. REFINISHED TOP COAT IAW SRM 57-52-12, PARA 4-D (3) & SRM 51-23-10. EA 6-5750-136744, "WINGS - LT WING INBD FLAP T/E LOWER SKIN REPAIR BETWEEN RIB 8 AND 9".

Part: STRUCTURE — DAMAGED (LT WING) · airframe 45,799 hrs · 22,287 cycles

LT WING T/E THROUGH HOLES FOR HYD LINES ARE ELONGATED AT WS OWS 1083.

Part: ARM — WORN (ELEVATOR HINGE) · airframe 45,799 hrs · 22,287 cycles

RT ELEVATOR AT 2 HINGE ARM LOWER FWD BEARING SWAGE LOOSE IN ARM - INBD TO OTBD MOVEMENT AS SEEN FROM THE TOP OF STAB. REMOVED RT ELEVATOR NR 2 HINGE ARM; R & R 2 EA FWD BEARINGS AND REINSTALLED RT NR 2 ELEVATOR HINGE ARM; FUNCTIONAL CHECK GOOD OF NR 2 ELEVATOR HINGE ARM IAW AMM 55-16-44-04; AMM 55-22--13-04; AMM 55-16-11-08; AMM 27-31-00-5; PMS 01-05-10; NTM 51-10-08, PT 6 AND EA 6-5550-136742, "STABILIZERS - RT ELEVATOR, NR 2 HINGE ARM LUG REPAIR".

Part: WEB — CRACKED (ZONE 100) · airframe 45,799 hrs · 22,287 cycles

FWD CARGO COMPARTMENT UNDER FLOOR VERTICAL WEB IS CRACKED BETWEEN FRAME 37 & FRAME 38; LBL 56. REMOVED AND REINSTALLED PALLET LATCH AT FRAME 37, RBL 33 IAW AMM 25-52-34- 04, PARA 2B1 & 2E2. REMOVED AND REINSTALLED PDU TRAY AT FRAME 37 TO 38 RT IAW SRM 51-40-21, PARA 5. REMOVED WEB IAW SRM 51-40-21, PARA 6D. LOCATED AND DRILLED WEB PN A5377833820890 IAW SRM 51-72-10, PG 2. INSTALLED WEB IAW SRM 51-72-10, PARA 6.

Part: WEB — CRACKED (ZONE 100) · airframe 45,799 hrs · 22,287 cycles

FWD CARGO COMPARTMENT UNDER FLOOR VERTIVAL WEB IS CRACKED BETWEEN FRAME 36 & FRAME 37; LBL 56. UPPER AND LOWER WEBS WERE REMOVED IAW SRM 51-40-21, PARA 6. NEW WEBS LOCATED AND DRILLED IAW SRM 51-40-44, PAGE 1. BOTH WEBS INSTALLED IAW SRM 51-40-21, PARA 7.

Part: WEB — DENTED (ZONE 100) · airframe 45,799 hrs · 22,287 cycles

FWD CARGO COMPARTMENT UNDER FLOOR VERTICAL WEB IS DENTED BETWEEN FRAME 34 - FRAME 35; LBL 56. REMOVED WEB IAW SRM 51-40-21, PARA 6. DISPLACED, CAPPED AND STOWED WIRING THROUGH WEB IAW AMM 20-33-22. LOCATED & DRILLED NEW WEB IAW SRM 51-40-44, PG 1. INSTALLED NEW WEB IAW SRM 51-40-21, PARA 7.

Part: FLOOR PANEL — DELAMINATED (ZONE 100) · airframe 45,799 hrs · 22,287 cycles

TAIL COMPARTMENT WORK PLATFORM IS SPONGY AND HAS EXPOSED CORE - DIRECTLY INBD OF ACCESS DOOR 312 AR CUTOUT. REPAIRED TAIL COMPARTMENT WORK PLATFORM WITH THE FABRICATION OF A NEW FLOOR PANEL USING THE OLD FLOOR PANEL AS A TEMPLATE IAW DWG SRZ 25-005, REV "H". INSTALLED PANEL 132 BF IAW AMM 20-21-12-00.

Part: ANGLE — DAMAGED (ZONE 100) · airframe 45,799 hrs · 22,287 cycles

AFT PIT SHEAR PLATE TOP "L" ANGLE HAS PREVIOUS DOUBLE DRILLED HOLES BETWEEN FRAME 65 AND FRAME 66; STRINGER 44LT. REMOVED ANGLE IAW SRM 51-40-21, PARA 6. FABRICATED NEW ANGLE IAW DWG A53974254, ISSUE "D". ALODINED IAW SRM 51-21-10, PG 1. PRIMED IAW SRM 51-75-10, PG 1. INSTALLED IAW SRM 51-40-21, PARA 7.

Part: ANGLE — DAMAGED (ZONE 100) · airframe 45,799 hrs · 22,287 cycles

AFT PIT SHEAR PLATE TOP "L" ANGLE HAS PREVIOUSLY DOUBLE DRILLED HOLES BETWEEN FRAME 64 AND FRAME 65; STRINGER 44L. REMOVED ANGLE IAW SRM 51-40-21, PARA 6. FABBED NEW ANGLE IAW DWG A53974252, ISSUE "G". ALODINED IAW SRM 51-21-10, PG 1. PRIMED IAW SRM 51-23-10, PG 1. PAINTED IAW SRM 51-75-10, PG 1. INSTALLED IAW SRM 51-40-21, PARA 7.

Part: SEAT TRACK — CORRODED (ZONE 200) · corrosion level 2 · airframe 45,799 hrs · 22,287 cycles

MAIN CABIN SEAT TRACK BETWEEN FRAME 72 AND 73 LBL 34 IS CORRODED. REMOVED CORROSION IAW SRM 53-10-16. CHECKED LIMITS, ORIGINAL THICKNESS 0.140. MATERIAL LOSS 0.041. MATERIAL REMAINING 0.099. FOUND TO BE OUT OF LIMITS. REMOVED SEAT TRACK SECTION, MATERIAL ID A53274005, PO NR 686863.1, FABRICATED, LOCATED & DRILLED SEAT TRACK IAW SRM 53-10-16 & SRM 51-72-10. ALODINED IAW SRM 51-21-10. PRIMED & PAINTED IAW SRM 51-23-10. INSTALLED SEAT TRACK IAW SRM 53-10-16.

Part: SPAR — CRACKED (LT NACELLE) · airframe 45,799 hrs · 22,287 cycles

LT PYLON HORIZ HEAT SHIELD BELOW THE LOWER SPAR IS CRACKED AND MISSING PIECES. WELD REPAIRED IAW EA 6-5750-136739.

Part: SEAT TRACK — CORRODED (ZONE 200) · corrosion level 2 · airframe 45,799 hrs · 22,287 cycles

MAIN DECK SEAT TRACK IS CORRODED BETWEEN FRAME 75 AND FRAME 76; LBL 30. REMOVED CORROSION IAW SRM 51-74-10. CHECKED LIMITS, ORIGINAL THICKNESS 0.0140. MATERIAL REMOVED 0.058. MATERIAL REMAINING 0.082. FOUND TO BE OUT OF LIMITS IAW SRM 51-31-20 & SRM 53-10-16, FIG 101. TOOL NR T8401B. REMOVED SEAT TRACK SECTION IAW SRM 53-10-16. LOCATED AND DRILLED PARTS IAW SRM 53-10-16. ALODINED IAW SRM 51-21-10. PRIMED AND PAINTED IAW SRM 51-23-10. INSTALLED SEAT TRACK & IAW SRM 51-10-16.

Part: SPAR — CRACKED (NR 2 NACELLE) · airframe 45,799 hrs · 22,287 cycles

NR 2 PYLON HORIZ HEAT SHIELD BELOW THE LOWER SPAR IS CRACKED AND MISSING PIECES. WELD REPAIRED IAW EA 6-5750-136739.

Part: FLOORBOARD — CORRODED (ZONE 100) · corrosion level 2 · airframe 45,799 hrs · 22,287 cycles

BULK CARGO COMPARTMENT FLOORBOARD 162 HF METAL TOP IS CORRODED. REMOVED TOP SHEET IAW DWG SRZ 25-011, REV "C". TOP SHEET MATERIAL ID 2024-T3 IAW DWG SRZ 25-011, REV "C". FABRICATED TOP SHEET IAW DWG SRZ 25-011, REV "C". BONDED TOP SHEET TO FLOORBOARD IAW DWG SRZ 25-011, REV "C". APPLIED ANTI-SKID COATING IAW DWG SRZ 25-011, REV "C".

Part: SEAT TRACK — CORRODED (ZONE 200) · corrosion level 2 · airframe 45,799 hrs · 22,287 cycles

MAIN DECK SEAT TRACK IS CORRODED BETWEEN FRAME 75 & FRAME 76; LBL 43. REPAIRED MAIN DECK SEAT TRACK BETWEEN FRAME 74 TO FRAME 76 WITH 35 INCHES OF SEAT TRACK SECTION AND SPLICE IAW SRM 53-10-16, FIG 208, SHEET 1, LBL 43.

Part: SKIN — CORRODED (CARGO DOOR) · corrosion level 2 · airframe 45,799 hrs · 22,287 cycles

FWD CARGO DOOR INNER SKIN IS CORRODED UNDER THE LOWER SEAL RETAINER. REMOVED AND REPLACED SECTION OF SKIN IAW A310-200 SRM 51-40-21, PARA 6, 7 & 13.

Part: SKIN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 45,799 hrs · 22,287 cycles

FUSELAGE INTERGAL PLATE HAS CORROSION AT FRAME 38.2; STRINGER 52R. REMOVED CORROSION PER SRM 51-74-10. FOUND TO BE OUT OF LIMITS PER SRM 53-14-12, FIG 101. FABRICATED REPAIR PARTS PER SRM 53-14-12, REPAIRS 4 & 5. ALODINED PER SRM 51-21-10. PRIMED PER SRM 51-23-10. INSTALLED REPAIR PER A310-200 SRM 53-14-12 REPAIRS 4 AND 5. SEALED PER SRM 51-76-10.

Part: FLOOR PANEL — DAMAGED (CABIN) · airframe 45,799 hrs · 22,287 cycles

MAIN CABIN FLOOR PANEL FROM FRAME 40- FRAME 41; LBL 85. FABRICATED NEW FLOOR PANEL 241 VJ IAW DWG SRZ 25-005, REV "H".

Part: FLOORBOARD — DAMAGED (CARGO BAY) · airframe 45,799 hrs · 22,287 cycles

FWD CARGO COMPARTMENT FLOORBOARD 132 RF, MULTIPLE CORNERS ARE BROKEN, THE EDGES ARE DAMAGED AND MISSING EDGE FILLER. FABRICATED NEW FLOORBOARD 132 RF IAW DWG SRZ 25-005, REV "H".

Part: SKIN — DAMAGED (CARGO BAY) · airframe 45,799 hrs · 22,287 cycles

AFT CARGO COMPARTMENT FLOORBOARD 151 CF FASTENER HOLE IS BROKEN AND THE BOTTOM SKIN IS TORN. FABRICATED NEW FLOORBOARD 151 CF IAW DWG SRZ 25-005, REV "H".

Part: FLOOR PANEL — CRACKED (MAIN CABIN) · airframe 45,799 hrs · 22,287 cycles

MAIN CABIN FLOOR PANEL 241 NK IS CRACKED ; ZONE 240. FABRICATED NEW FLOOR PANEL 241 NK IAW DWG SRZ 25-005, REV "H".

Part: FLOOR PANEL — CRACKED (MAIN CABIN) · airframe 45,799 hrs · 22,287 cycles

MAIN CABIN FLOOR PANEL 231 R IN ZONE 230 IS CRACKED. FABRICATED NEW FLOOR PANEL 231 RG IAW DWG SRZ 25-005, REV "H".

Part: FLOORBOARD — DAMAGED (MAIN CABIN) · airframe 45,799 hrs · 22,287 cycles

MAIN CABIN FLOORBOARD HAS A BROKEN OFF OTBD FWD CORNER FROM FRAME 25-FRAME 27; RBL 78 TO RBL 100. FABRICATED NEW FLOORBOARD 231 VG IAW DWG SRZ 25-005, REV "H".

Part: FLOORBOARD — CRACKED (CARGO BAY) · airframe 45,799 hrs · 22,287 cycles

FWD CARGO COMPARTMENT FLOORBOARD 131 HG IS CRACKED ON THE BACK AND THE EDGE IS BROKEN. FABRICATED NEW 131 HG IAW DWG SRZ 25-005, REV "H".

Part: FLOOR PANEL — CRACKED (MAIN CABIN) · airframe 45,799 hrs · 22,287 cycles

MAIN CABIN FLOOR PANEL 241 YN IN ZONE 240 IS CRACKED. FABRICATED NEW FLOOR PANEL 241 YN IAW DWG SRZ 25-005, REV "H".

Part: FLOORBOARD — CRACKED (CARGO BAY) · airframe 45,799 hrs · 22,287 cycles

FWD CARGO COMPARTMENT FLOORBOARD 131 RF IS CRACKED ON AND THE CORNERS ARE DAMAGED. FABRICATED NEW FLOOR BOARD 131 RF IAW DWG SRZ 25-005, REV "H".

Part: FLOORBOARD — DELAMINATED (CARGO BAY) · airframe 45,799 hrs · 22,287 cycles

AFT CARGO COMPARTMENT FLOORBOARD 152 BF TOP SKIN IS DELAMINATED. FABRICATED NEW FLOORBOARD 152 BF IAW DWG SRZ 25-005, REV "H".

Part: SKIN — CRACKED (CARGO BAY) · airframe 45,799 hrs · 22,287 cycles

AFT CARGO COMPARTMENT FLOORBOARD 152 AF TOP SKIN IS CRACKED. FABRICATED NEW FLOORBOARD 152 AF IAW DWG SRZ 25-005, REV "H".

Part: FLOORBOARD — DAMAGED (CARGO BAY) · airframe 45,799 hrs · 22,287 cycles

AFT CARGO COMPARTMENT FLOORBOARD 151EF TOP SKIN IS TORN AND THE CORNER IS CRUSHED. FABRICATED NEW FLOORBOARD 151 EF IAW DWG SRZ 25-005, REV "H".

Part: FLOORBEAM — CORRODED (ZONE 100) · airframe 45,799 hrs · 22,287 cycles

AFT CARGO COMPARTMENT RT FLOORBEAM STRUCTURE HAS DOUBLE DRILLED HOLES AND IS CORRODED AT THE NUTPLATES. CROSSBEAM WAS REMOVED PER SRM 51-40-21, PARA 6 & 7. DRILLED AND INSTALLED NEW PART PER SRM 51-72-10, PG 2

Part: FLOORBEAM — DAMAGED (ZONE 100) · airframe 45,799 hrs · 22,287 cycles

BULK CARGO COMPARTMENT FLOORBEAM T-CAP HAS 2 DRILL STARTS ON THE UPPER SURFACE AT FRAME 66, LBL 3". DAMAGE REMOVED PER SRM 51-40-21 AND NEW T-CAP WAS FITTED AND DRILLED PER SRM 51-40-44 AND INSTALLED PER SRM 51-40-21; PARA 6 & 7.

Part: RETAINER — CRACKED (ZONE 100) · airframe 45,799 hrs · 22,287 cycles

AFT CARGO COMPARTMENT DOOR CEILING PANEL RETAINER IS CRACKED BETWEEN FRAME 60 AND FRAME 61; STRINGER 21R TO STRINGER 23R. REMOVED AFT CARGO COMPARTMENT DOOR CEILING PROFILE IAW SRM 51-40-21, PARA 5. LOCATED AND DRILLED IAW SRM 51-40-44. INSTALLED CEILING PANEL PROFILE IAW SRM 51-40-21, PARA 7.

Part: PLATE — CRACKED (ZONE 100) · airframe 45,799 hrs · 22,287 cycles

AFT CARGO COMPARTMENT DOOR CUTOUT CEILING STRUCTURE SEAL PLATE IS CRACKED BETWEEN FRAME 60 AND FRAME 61. TRIMMED OUT DAMAGED AREA IAW SRM 51-71-40, PG 202. FABRICATED REPAIR DOUBLER AND FILLER IAW SRM 51-71-40. DRILLED IAW SRM 51-40-44. ALODINED FILLER AND DOUBLER IAW SRM 51-21-10. PRIMED AND TOP COATED IAW SRM 51-23-10, PG 1. INSTALLED IAW SRM 51-40-21, PARA 6.

Part: BRAKE — SMOKE (MLG) · airframe 45,555 hrs · 22,115 cycles

AFTER LANDING, TOWER REPORTED SMOKE COMING FROM RT MAIN GEAR. TAXIED CLEAR, STOPPED AND HAD FIRE DEPT CHECK ORIGIN. THEY REPORTED FLUID DRIPPING ONTO GEAR. SHUTDOWN AND TOWED BACK TO RAMP. BRAKE TEMPS APPROX 280 DEG MAX (NR3, 150 DEG) IDENTIFIED SMOKE COMING FROM EXCESS GREASE ON BRAKE ASSY NR3 & NR4 . CLEANED BRAKE ASSY AND STRUT. OPERATED BRAKES NO LEAKS, BRAKES OPERATED NORMAL. THIS IS FIRST FLT SINCE MX CHECK (GEAR CHANGE) BRAKE TEMPS AND BRAKE DIFFERNTIAL TEMPS WITHIN NORMAL RANGE REF AMM 32-40-00-06-0.

Part: LUG — CORRODED (LT MLG) · corrosion level 2 · airframe 45,554 hrs · 22,114 cycles

DURING RIB 5 INSPECTION, CORROSION WAS FOUND IN L/H MAIN LANDING GEAR RIB 5, FORWARD LUG. CORROSION WAS REMOVED BY OVERSIZING THE BORE DIAMETER TO 5.015" AND REWORKING THE LUG TO THICHNESS OF 2.237". THE LUG WAS CONFIRMED FREE OF CORROSION BY NDT INSPECTION (NIL FINDINGS), REPROTECTED LUG, OVERSIZED BUSHES, FABRICATED AND INSTALLED ALL IN ACCORDANCE WITH OPERATOR REPORTS AND REPAIR INSTRUCTIONS. THE OPERATOR DEVIATED FROM THE REPAIR INSTRUCTIONS BY MANUFACTURING LARGER DIAMETER BUSHES AND WORKED IT IAW EA 6-5710-142077 WING GEAR RIB 5 LUG BORE REWORK (LHS), SB A310-57-2090, EO 6-5710-7-5010. REF WORK INSTRUCTIONS R572-49121 ISSUE D AND REF MANUFACTURES RAS/BAE/1013736/2010. THIS A MAJOR REPAIR IAW FEDEX GMM 6-2-100.

Part: LUG — CORRODED (RT MLG) · corrosion level 2 · airframe 45,554 hrs · 22,114 cycles

FOUND CORROSION IN RT MAIN LANDING GEAR FORWARD LUG AT RIB 5 DURING RIB 5 INSPECTION. REMOVED CORROSION BY OVERSIZING THE BORE AND SPOTFACING THE SURFACES, PERFORMING FINISHING CUTS, (FINAL BORE DIAMETER 5.341", FINAL LUG THICKNESS 2.220"), PERFORMING ACID ETCHING AND NDT INSPECTIONS (NO FINDING), MANUFACTURING AND INSTALLING A REPAIR PINTLE PIN AND REPAIR BUSHES, ALL IAW TECHNICAL DISPOSITION, REPAIR INSTRUCTIONS AND OPERATOR'S DAMAGE REPORTS. REPAIR INSTRUCTIONS IAW R572-58980 ISSUE B, R572-49121 ISSUE D, R321-49006 ISSUE B, AND R527-49365 ISSUE B. REF MANUFACTURES RAS/BAE/1013737/2010 ISSUE A. THIS WOK IS ON FILE UNDER WO 00048888. THIS REPAIR IS A MAJOR IAW FEDEX GMM 6-2-100.

Part: SKIN — DENTED (AFT PAX DOOR) · airframe 44,014 hrs · 21,028 cycles

RT AFT CREW DOOR LOWER AFT CORNER HAS DENT 1.5 IN LONG BY 2 IN W BY .033 IN DEEP CUT OUT DAMAGE AND INSTALLED SKIN REPAIR ON RT AFT DOOR LOWER AFT CORNER IAW A310-200 SRM 52-10-00, FIG 204, PG 217/218.

Part: SKIN — DAMAGED (RT WING TE FLAP) · airframe 44,014 hrs · 21,028 cycles

PREVIOUS EXTERNAL REPAIR DOUBLER LOCATED ON RT WING OUTBD FLAP LOWER MAIN SKIN AT MAIN SPAR TO REAR SPAR AND FROM THE INBD EDGE TO BETWEEN RIB 2 AND TRACK NR 3, MEASURING 47.7 IN BY 19.9 IN. REMOVED EXISTING REPAIR AND REPAIRED IAW SRM 57-53-12,FIG 210, PG 259/260. THIS IS AN REPAIR AND IS A RESULT OF AGING AIRCRAFT INSPECTION.

Part: FLOORBEAM — CRACKED (ZONE 100) · airframe 44,014 hrs · 21,028 cycles

BULK CARGO DOOR ENTRY FLOOR T-CAP ON INTERCOSTAL HAS 4 IN CRACK BEGINNING AT FR 68 REMOVED DAMAGED T-CAP AND SPLICE STRIPS AND INSTALLED NEW PARTS AT BULK CARGO DOOR FLOOR ENTRY BETWEEN FR 67 AND FR 69 IAW A310-200 SRM 51-40-21 AND 51-72-10.

Part: SKIN — DAMAGED (LT WING) · airframe 44,014 hrs · 21,028 cycles

SKIN AFT OF REAR SPAR LT AT RIB 11 HAS PREVIOUS .5 IN CRACK REPAIR REMOVED PREVIOUS DOUBLER AND RE-INSTALLED IAW FEDEX EA 6-5710-73485, REV NO B, POS PT, RELEASE DATE 11/14/03.

Part: SEAT TRACK — CRACKED (ZONE 200) · airframe 44,014 hrs · 21,028 cycles

MD CARGO COMPT CLS ADAPTER AT FR 43 BETWEEN SEAT TRACK 2RT AND 3 RT HAS 2 INCH CRACK. REMOVED AND REPLACED MDCC CLS ADAPTER AT FR 43 BETWEEN SEAT TRACK 2RT AND 3RT IAW A310-200 SRM 21-72-10.

Part: SKIN — DENTED (ZONE 100) · airframe 44,014 hrs · 21,028 cycles

DENT ON FUSELAGE SKIN LOCATED AT FR 68 ABOVE LT STRINGER 44 MEASURING 4 IN BY 1.5 IN BY .025 DEEP CUT OUT DAMAGED AREA AND INSTALLED SKIN REPAIR AT LONGITUDINAL LAP JOINT BETWEEN FR 68 AND FR 69, STR 44 LT IAW A310-200 SRM 53-10-12, FIG 216 SHT 1.

Part: FITTING — MISREPAIRED (ZONE 200) · airframe 44,014 hrs · 21,028 cycles

PREVIOUS REPAIR LOCATED ON FUSELAGE CUTOUT AT L-1 FORWARD PAX DOOR FAILSAFE RING LOWER SECTION HAS 2 EACH EXTERNAL REPAIR DOUBLERS, AT FRAMES 14 AND 16A BETWEEN BEAMS 2 AND 5, EACH REPAIR DOUBLER MEASURES 16.1" INCHES LONG AND 3.1" INCHES WIDE. REPAIR NOT IAW SRM REQUIREMENTS. REMOVED EXTERNAL REPAIR DOUBLERS AND INSTALLED CORRECT EXTERNAL REPAIR DOUBLERS AT FRAMES 14 AND 16A BETWEEN BEAMS 2 AND 5 IAW SRM 53-12-81 FIG 203 AND AIRBUS DWG R53610175.

Part: SKIN — MISREPAIRED (ZONE 500) · airframe 44,014 hrs · 21,028 cycles

PREVIOUS EXTERNAL REPAIR DOUBLER LOCATED ON LT WING OUTBOARD FLAP UPPER MAIN SKIN UNDER RUB STRIP AREA BETWEEN RIBS 7 TO 8 MEASURES 4" BY 5.6" INCHES. REPAIR NOT IAW SRM REQUIREMENTS. REMOVED PREVIOUS REPAIR AND INSTALLED CORRECT EXTERNAL REPAIR DOUBLER LOCATED ON LT WING OUTBOARD FLAP UPPER MAIN SKIN UNDER RUB STRIP AREA BETWEEN RIBS 7 TO 8 IAW SRM 57-53-12 FIG 210.

Part: STRINGER — MISREPAIRED (ZONE 100) · airframe 44,014 hrs · 21,028 cycles

PREVIOUS STRINGER REPAIR LOCATED IN AFT CARGO ON STRINGER 52 LT BETWEEN FRAMES 59 TO 60 HAS 1 EACH REPAIR SECTION MEASURING 29 INCHES LONG AND 1 EACH REPAIR SPLICE MEASURING 7.3 INCHES LONG. REPAIR NOT IAW SRM REQUIREMENTS. REMOVED PREVIOUS STRINGER REPAIR AND INSTALLED CORRECT STRINGER REPAIR LOCATED IN AFT CARGO ON STRINGER 52 LT BETWEEN FRAMES 59 TO 60 IAW SRM 53-10-14 FIG 201.

Part: SKIN — MISREPAIRED (ZONE 100) · airframe 44,014 hrs · 21,028 cycles

PREVIOUS EXTERNAL REPAIR DOUBLER LOCATED ON LEFT SIDE FUSELAGE SKIN BETWEEN FRAMES 80/82 TO 84 AND BETWEEN STRINGERS 29 TO 32 LT, THE REPAIR DOUBLER MEASURES 10.1 INCHES BY 12 INCHES WITH A SKIN CUTOUT MEASURING 2.5 INCHES BY 2.1 INCHES. REPAIR NOT IAW SRM REQUIREMENTS. REMOVED REPAIR RIVETS AND INSTALLED CORRECT REAPAIR. REPAIR RIVETS ON REPAIR DOUBLER LOCATED ON LEFT SIDE FUSELAGE SKIN BETWEEN FRAMES 80/82 TO 84 AND BETWEEN STRINGERS 29 TO 32 LT IAW SRM 53-10-12 FIG 203 AND FIG 225 SHEET 1.

Part: ADAPTER — WORN (ZONE 200) · airframe 44,014 hrs · 21,028 cycles

MDCC BETWEEN SEAT TRACK 2R AND 3R FRAME 38 CARGO LOADING SYSTEM ADAPTER HAS 2 EACH AREAS OF WORN SCALLOPS. REMOVED WORN CLS ADAPTER AND INSTALLED NEW CLS ADAPTER BETWEEN SEAT TRACK 2R AND 3R FRAME 38 IAW A310-200 SRM 51-40-21 AND SRM 51-72-10.

Part: SKIN — FAILED (LT WING AILERON) · airframe 44,014 hrs · 21,028 cycles

PREVIOUS EXTERNAL REPAIR DOUBLER LOCATED ON LEFT WING AILERON LOWER SKIN BETWEEN RIBS 12 TO 16 MEASURES 18.5 X 11.3 INCHES REPAIR NOT IAW SRM REQUIREMENTS. REMOVED 3 EACH FASTENERS FROM PREVIOUS REPAIR DOULBLER AND INSTALLED 3EACH CORRECT FASTENERS ON LEFT WING AILERON LOWER SKIN BETWEEN RIBS 12 TO 16 IAW A310-200 SRM 57-61-12 FIG 201.

Part: SEAL — CRACKED (THRUST REVERSER) · airframe 43,131 hrs · 20,530 cycles

DURING SCHEDULED B CHECK INSPECTION NR 1 LT THRUST REVERSER LIP SEAL WAS FOUND TO BE CRACKED. REPLACEMENT OF DAMAGED REVERSER.

Part: UNKNOWN — MULTIPLE FAIL · airframe 43,103 hrs · 20,513 cycles

AFTER TAKEOFF CLIMBING OUT OF 3000' ECAM ALERTED AVIONICS SMOKE. NO SNIFFER FAN SMOKE OBSERVED, ECAM CLEANED THE WARNING, AND A FEW SECONDS LATER. ADVISED AGAIN AVIONICS SMOKE. THIS SECOND ECAM ALERT PROMPTED EMERGENCY RETURN AND LANDED SAFELY 26L CYVR. INSPECTED AVIONIC BAY FOR PRESENCE OF FIRE OR BURNED COMPONENTS, NO FAULT FOUND. REMOVED AND REPLACED BOTH COALESCER BAGS. REMOVED AND REPLACED SMOKE DETECTOR POSITION 11WA, 12WA, 13WA.

Part: BATTERY — OVERHEATED (NR 2) · airframe 41,421 hrs · 19,608 cycles

NR 2 BATTERY OVERHEAT IN FLIGHT. RESET WITH SECOND OVERHEAT. KEPT BATT NR 2 OFF. REMOVED AND REPLACED NR 2 BATTERY PER A300 AMM 24-31-11-4 AND PERFORMED TEST PER AMM 24-31-00-5. OPS CK GOOD. R/I FROM FACT PREMATURE REMOVAL/INSTALLATION OFF MFG 33082-001. NOTE THAT NR 3 BATT WAS ON MEL. WRI 24-60/7923.

Part: FAILSAFE — CORRODED (FUSELAGE) · airframe 41,168 hrs · 19,486 cycles

FWD PASS CREW DOOR RING RT FAILSAFE RING CORRODED AT UPPER FWD CORNER AT CENTRAL UPPER AREA AND AT AFT LOWER CORNER. REPLACED FAILSAFE RING PER DWG. R53610899 AND FEDEX EA 6-5340-95697 AND AIRBUS T.D. REF. 942-042678/03/2006 AND SRM 51-72-10 AND SRM 51-40-21 REPAIR WAS EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS MAJOR

Part: FITTING — CRACKED (FUSELAGE) · airframe 41,168 hrs · 19,486 cycles

COMPLY WITH AGING 9-AGING-INSP, FWD MDCC UTILITY AREA SUSPECTED OF CRACK AT FLOORBEAM CONNECTION FITTING AT FRAME 12A RT.

Part: SEAT TRACK — CRACKED (FUSELAGE) · airframe 41,168 hrs · 19,486 cycles

COMPLY WITH AGING 9-AGING-INSP REV POS PT1. CRACK FOUND ON RT WING LOADING EDGE NEAR SLAT RAILS NR 5 AND NR 6 POSITIONS. REPAIRED PER SRM 57-41-12.

Part: FITTING — CRACKED (FUSELAGE) · airframe 41,168 hrs · 19,486 cycles

FWD MDCC UTILITY AREA SUSPECT A CRACK AT FLOORBEAM CONNECTION FITTING AT FRAME 12A LT.

Part: REPAIR — NONE (DOOR) · airframe 41,168 hrs · 19,486 cycles

FOUND REPAIR LOCATED LT PAX DOOR L1. EXTERNAL DOUBLER LWR AFT CORNER. REPAIR REQUIRES EVALUATION FOR MAJOR MINOR DETERMINATION AND IF REPAIR ACCOMPLISHED USING FAA APPROVED DATA. EXISTING REPAIR WAS PREVIOUSLY ACCOMPLISHED RAS/AS/027/2006 REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS MAJOR.

Part: SKIN PANEL — UNKNOWN (LT AILERON) · airframe 41,168 hrs · 19,486 cycles

FOUND REPAIR LOCATED LT AILERON WS 513-538. LOWER SURFACE. REPAIR REQUIRES EVALUATION FOR MAJOR MINOR DETERMINATION AND IF THE REPAIR ACCOMPLISHED USING FAA APPROVED DATA.

Part: REPAIR — NONE (FUSELAGE) · airframe 41,168 hrs · 19,486 cycles

COMPLY WITH AGING 9-AGING-INSP REV POS PT1. FOUND REPAIR LOCATED RT FS 3567 - FS 3587, FR66, STR 32 - STR 33 EXT DOUBLER. REPAIR REQUIRES EVALUATION FOR MAJOR MINOR DETERMINATION AND IF THE REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. EXISTING REPAIR EVALUATED AND FOUND TO CONFORM TO SRM 53-10-12 FIG 225. REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS MAJOR.

Part: REPAIR — MISINSTALLED (LT WING) · airframe 41,168 hrs · 19,486 cycles

FOUND REPAIR LOCATED ON LT INBD FLAP, LT WS 236-276. REPAIR REQUIRES EVALUATION FOR MAJOR MINOR DETERMINATION AND IF THE REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. REPLACED TRAILING EDGE ASSY PER SRM 51-72-10 AND FEDEX EA 6-5710-95695 REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS MAJOR.

Part: REPAIR — NONE (FUSELAGE) · airframe 41,168 hrs · 19,486 cycles

COMPLY WITH AGING 9-AGING-INSP REV POS PT1. FOUND REPAIR LOCATED LT FS 1184, FR14 ON THE FWD L1 DOOR FRAME EXT DOUBLER. REPAIR REQUIRES EVALUATION FOR MAJOR MINOR DETERMINATION AND IF THE REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. EXISTING REPAIR EVALUATED AND FOUND TO CONFORM TO SRM 53-12-81 FIG 203. REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS MAJOR.

Part: REPAIR — NONE (FUSELAGE) · airframe 41,168 hrs · 19,486 cycles

COMPLY WITH AGING 9-AGING-INSP REV POS PT1. FOUND REPAIR LOCATED LT FS 1305, FR16A ON THE AFT L1 DOOR FRAME EXT DOUBLER. REPAIR REQUIRES EVALUATION FOR MAJOR MINOR DETERMINATION AND IF THE REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. EXISTING REPAIR EVALUATED AND FOUND TO CONFORM TO SRM 53-12-81 FIG 203. REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS MAJOR.

Part: REPAIR — MISINSTALLED (TE FLAP) · airframe 41,168 hrs · 19,486 cycles

FOUND REPAIR LOCATED ON RT INBD FLAP, RT WS 347-349. REPAIR REQUIRES EVALUATION FOR MAJOR MINOR DETERMINATION AND IF THE REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. REPLACED TRAILING EDGE ASSY PER SRM 51-72-10 AND FEDEX E:A: 6-5710-95695 REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS MAJOR

Part: REPAIR — MISINSTALLED (BS 1534-1554) · airframe 41,168 hrs · 19,486 cycles

COMPLY WITH AGING 9-AGING-INSP REV POS PT1. FOUND REPAIR LOCATED RT FS 1534 - FS 1554, FR22 ON THE LOWER CARGO DOOR EXT DOUBLER. REPAIR REQUIRES EVALUATION FOR MAJOR MINOR DETERMINATION AND IF THE REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. EXISTING REPAIR EVALUATED AND FOUND NOT TO CONFORM TO AN EXISTING SRM REPAIRED PER FEDEX EA 6-3230-95692. REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS MAJOR.

Part: REPAIR — MISINSTALLED (TE FLAP) · airframe 41,168 hrs · 19,486 cycles

FOUND REPAIR LOCATED ON RT OUTBD FLAP, RT WS 935-950. REPAIR REQUIRES EVALUATION FOR MAJOR MINOR DETERMINATION AND IF THE REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. REPAIR EVALUATED AND FOUND NOT TO CONFORM TO AN EXISTING SRM REPAIR NEW REPAIR ACCOMPLISHED PER SRM 57-53-12 FIG. 208 (SHEET 4) REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS MAJOR.

Part: REPAIR — NONE (FUSELAGE) · airframe 41,168 hrs · 19,486 cycles

COMPLY WITH AGING 9-AGING-INSP REV POS PT1. FOUND REPAIR LOCATED RT FS 766 - FS 794, FR 1 - FR 2 EXT DOUBLER. REPAIR REQUIRES EVALUATION FOR MAJOR MINOR DETERMINATION AND IF THE REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. EXISTING REPAIR EVALUATED AND FOUND TO CONFORM TO SRM 53-11-12 FIG 201. REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS MAJOR.

Part: REPAIR — UNKNOWN (TE FLAP) · airframe 41,168 hrs · 19,486 cycles

FOUND REPAIR LOCATED ON RT INBD FLAP, RT WS 359-409. REPAIR REQUIRES EVALUATION FOR MAJOR MINOR DETERMINATION AND IF THE REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. REPLACED TRAILING EDGE ASSY PER SRM 51-72-10 AND FEDEX EA 6-5710-95695 AND RAS/DABRE/7006301/2006A REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS MAJOR.

Part: REPAIR — MISINSTALLED (TE FLAP) · airframe 41,168 hrs · 19,486 cycles

FOUND REPAIR LOCATED ON LT INBD FLAP, LT WS 277 - WS 289. REPAIR REQUIRES EVALUATION FOR MAJOR MINOR DETERMINATION AND IF THE REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. REPAIR EVALUATED AND FOUND NOT TO CONFORM TO AN EXISTING SRM REPAIR NEW REPAIR ACCOMPLISHED PER FEDEX EA 6-5750-95693. REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS MINOR.

Part: REPAIR — MISINSTALLED (TE FLAP) · airframe 41,168 hrs · 19,486 cycles

FOUND REPAIR LOCATED ON RT INBD FLAP, RT WS 110-119. REPAIR REQUIRES EVALUATION FOR MAJOR OR MINOR DETERMINATION AND IF THE REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. REPLACED TRAILING EDGE ASSY PER SRM 51-72-10 AND FEDEX E:A: 6-5710-95695 REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS MAJOR

Part: REPAIR — MISINSTALLED (LT FLAP) · airframe 41,168 hrs · 19,486 cycles

FOUND REPAIR LOCATED ON LT INBD FLAP, LT WS 346-400. REPAIR REQUIRES EVALUATION FOR MAJOR OR MINOR DETERMINATION AND IF THE REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. REPLACED TRAILING EDGE ASSY PER SRM 51-72-10 AND FEDEX EA 6-5710-95695 REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS MAJOR.

Part: REPAIR — MISINSTALLED (FUSELAGE) · airframe 41,168 hrs · 19,486 cycles

FOUND REPAIR LOCATED ON L/H INBD FLAP, LT WS128-WS176. REPAIR REQUIRES EVALUATION FOR MAJOR MINOR DETERMINATION AND IF THE REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. REPLACED TRAILING EDGE ASSY PER SRM 51-72-10 AND FEDEX E:A: 6-5710-95695 REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS MAJOR.

Part: REPAIR — MISINSTALLED (TE FLAP) · airframe 41,168 hrs · 19,486 cycles

FOUND REPAIR LOCATED ON LT INBD FLAP, LT WS 134-182. REPAIR REQUIRES EVALUATION FOR MAJOR MINOR DETERMINATION AND IF THE REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. REPLACED TRAILING EDGE ASSY PER SRM 51-72-10 AND FEDEX EA 6-5710-95695 REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS MAJOR.

Part: REPAIR — NONE (FUSELAGE) · airframe 41,168 hrs · 19,486 cycles

COMPLY WITH AGING 9-AGING-INSP REV POS PT1. FOUND REPAIR LOCATED RT FS 2982 - FS 2294, FR38-FR40 FLUSH REPAIR. REPAIR REQUIRES EVALUATION FOR MAJOR MINOR DETERMINATION AND IF THE REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. PERMANENT REPAIR PERFORMED BY AIRBUS BEFORE DELIVERY REF CONCESSION 2475 REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS MAJOR.

Part: SWITCH — MALFUNCTIONED (LE K FLAPS) · airframe 40,755 hrs · 19,253 cycles

AFTER T/O TRIED TO RETRACT FLAPS BUT GOT A KRUGER LIGHT. RECYCLED 2 TIMES RAN QRH. KRUGER REMAINED EXTENDED. RETURNED TO OAK AND AFTER LANDING KRUGERS RETRACTED. FOUND FAULT BALL SHOWS ON SFCC 1, LT RETRACT SW. REMOVED AND REPLACED LT RETRACT SWITCH PER MM 27 89 12 4, OPS CHECK FOUND NORMAL, RAN ENGINE 2 PER JRH AND RAN FLAPS SLATS UP AND DOWN COUPLE OF TIMES KRUEGER FLAPS WORKED NORMALLY.

Part: FILTER — CONTAMINATED (FUEL SYSTEM) · airframe 40,359 hrs · 19,029 cycles

DURING TAKEOFF, APPROACHING 80 KTS, FUEL CLOG LIGHT, ECAM AND SINGLE CHIME FOR 1 ENGINE; REJECTED TAKEOFF AND ACCOMPLISHED RTO CHECKLIST. PULLED FUEL FILTER, FOUND DEBRIS IN FILTER. REPLACED FILTER, RAN ENGINE 15 MINS, REMOVED AND INSPECTED FILTER, NO DEBRIS NOTED. REINSTALLED NEW FILTER, LEAK CHECK GOOD, CLOSED COWL DOORS. OK TO CONTINUE. REF MM 73-12-03-2-B.

Part: FLAP TRACK — CRACKED (ZONE 500) · airframe 38,474 hrs · 18,035 cycles

LT WING TE, MIDPOINT BETWEEN NR 1 O/B PYLON AND I/B NR 3 FLAP TRACK EVIDENCE OF CRACK AT RIVET HEAD TO EDGE LWR SKIN. REQUEST NDT TO CONFIRM. REMOVED FASTENER IAW A310 SRM 51-40-21, ROTO TESTED HOLE IAW NTM 51-10-00-01 NO CRACKS FOUND, FABRICATED REPAIR PARTS IAW EA6-5710-73485A DWG R57249152. INSTALLED REPAIR PARTS IAW EA6-5710-73485A DWGR 57249152. DOME SEALED FASTENER IAW A310 SRM 51-76-20, LEAK CHECK IAW AMM A310-28-11-00-5.

Part: TAILPIPE — DAMAGED (NR 2 ENGINE) · airframe 37,515 hrs · 17,545 cycles

SIGNIFICANT TAIL PIPE FIRE DAMAGE FOUND ON POSTFLIGHT WALKAROUND, ON INBOARD AILERON, AND BOTH CANOE FAIRINGS ADJACENT TO THE AILERON ON THE NR 2 ENGINE SIDE (INWORK) WORKING IN CONJUNCTION WITH WRI 73-10/4991, CHECKED COMBUSTER DRAIN VALVE IAW M/M. NO DEFECTS NOTED. REMOVED AND REPLACED COMBUSTOR DRAIN VALVE PRECAUTIONARY IAW M/M. NO FUEL NOTED IN DRAIN LINE. IAW MOCC, NR 2 ENG MEC REQUIRES CHANGING PRIOR TO NEXT ENGINE START.

Part: COALESCER BAG — DIRTY (A/C BAY) · airframe 36,392 hrs · 16,902 cycles

MAIN DECK CARGO SMOKE WARNING ALERT LIGHT AND FUMES. CHECK A/C FOR SIGNS OF FIRE AND SMOKE ALL CLEAR. REMOVED AND REPLACED COALESCER BAGS. ALL OK.

Part: CONTROLLER — MALFUNCTIONED (PNEUMATIC SYS) · airframe 35,622 hrs · 16,397 cycles

AT 2000 ON AP W/E & W ANTI-ICE ON, FLAPS DOWN, WHEN THROTTLES CAME BACK NR 2 BLD INLINE FOR ANTI-ICE. AT 500 23 SEC LATER MDC SMOKE RED ECAM WARN. *S/D* REMOVED AND REPLACED NR 2 PACK COALESCER BAG PER MM 21-51-16-3. REPLACED NR 1 CONTROLLER PER MM 36-11-19-4. NR 2 SYS NEEDS CONTROLLER (P/N 627248-1).

Part: IRU — INOP (NR 2)

NR 2 IRU WARNING, NR 3 EUR ALREADY ON DEFERRAL. REMOVED AND REPLACED NR 2 IRU PER MM 34-25-14. ACCOMPLISHED OPER CK PER 34-25-00.

Part: PACK — OVERHEAT (NR 2)

STA-BOI - NR 2 PACK OVERHEAT WITHIN MAIN DECK CARGO SMOKE AND FIRE BELL WARNING. C/W BITE TEST ON PNEUMATIC CONTROLLER, PACK CONTROLLERS, ZONE CONTROLLERS, CARGO SMOKE DET CONTROLLERS. NO FAULTS FOUND. CLEANED AND INSPECTED WATER SEPARATOR SOCK. FOUND OK FOR REUSE PER AMM 21-51-16. SYSTEMS ALL CHECK GOOD. SUSPECT RELATED TO HIGH AMBIENT TEMP ON GROUND. OK FOR SERVICE.

Part: COMPRESSOR — STALLED (ENGINE)

97-0203, DURING CLIMB-OUT THROUGH FL 180 A LOUD BANG WAS HEARD, AND THE A/C BEGAN TO SHUTTER. THE MAIN DECK SMOKE DETECTION CAME ON, ENGINE WAS SHUTDOWN. EMERGENCY RETURN TO MEMPHIS, OVERWEIGHT LANDING.