N443FE

Part: SKIN — CORRODED (ZONE 200) · corrosion level 2 · airframe 43,995 hrs · 22,752 cycles

REAR FUSELAGE SKIN LOWER HORIZONTAL STAB CUTOUT BETWEEN FR 87-89, S27-31R FOUND CORRODED. COMPLED WITH EA6-5330-168201.

Part: SKIN — CORRODED (ZONE 200) · corrosion level 2 · airframe 43,995 hrs · 22,752 cycles

REAR FUSELAGE SKIN LOWER HORIZONTAL STAB CUTOUT BETWEEN FR 87-89, S27-31 LT FOUND CORRODED. COMPLIED WITH EA6-5330-168201.

Part: SKIN — CRACKED (CARGO DOOR) · airframe 43,995 hrs · 22,752 cycles

AFT CARGO DOOR EXTERIOR SKIN FWD LOWER CORNER EDGE CRACKED. COMPLIED WITH EA6-5230-168203.

Part: FRAME — DAMAGED (ZONE 200) · airframe 43,995 hrs · 22,752 cycles

CENTER FUSELAGE FRAME 45, RT SIDE HOLE H22: IN THE FRAME FOOT AND FRAME DOUBLER HOLE DIMENSION AT 14MM WITH NO CRACK INDICATION, IN THE FRAME HOLE DIMENSION AT 9.92 WITH NO CRACK INDICATION. COMPLIED WITH EA6-5310-168229.

Part: FRAME — DAMAGED (ZONE 200) · airframe 43,995 hrs · 22,752 cycles

CENTER FUSELAGE FRAME 44 RT HOLE H12 AND H13 DIMENSION AT 8.73MM PRESENT NO CRACK INDICATION, HOLE H10 DIMENSION AT 6.76MM PRESENT NO CRACK INDICATION, HOLE H11 DIMENSION AT 7.52MM PRESENT NO CRACK INDICATION. COMPLIED WITH EA6-5310-168229.

Part: FRAME — DAMAGED (ZONE 200) · airframe 43,995 hrs · 22,752 cycles

CENTER FUSELAGE FRAME 45, LT HOLE H15: IN THE FRAME FOOT, FRAME DOUBLER, FRAME AND BRACKET FR45 HOLE DIMENSION AT 9.92 MM WITH NO CRACK INDICATION; HOLE H22: IN THE FRAME FOOT, FRAME DOUBLER AND FRAME HOLE DIMENSION AT 9.92MM WITH NO CRACK INDICATION; HOLE H21: IN THE FRAME FOOT, FRAME DOUBLER AND FRAME HOLE DIMENSION AT 9.52 MM WITH NO CRACK INDICATION. COMPLIED WITH EA6-5310-168229.

Part: FRAME — CRACKED (ZONE 200) · airframe 43,995 hrs · 22,752 cycles

CENTER FUSELAE FRAME 44 LT SIDE HOLE H5 WITH NO CRACK INDICATION & HOLE DIMENSION IS 19MM, AND FRAME 44 LT SIDE HOLE H13 WITH SHORT EDGE DISTANCE, HOLE H13 EDGE DISTANCE IS 11.17 MM LESS THAN 12 MM REQUIRED IN THE SB53-2124. COMPLIED WITH EA 6-5310-168229.

Part: FRAME — DAMAGED (ZONE 200) · airframe 43,995 hrs · 22,752 cycles

CENTER FUSELAGE FRAME 46 RT SIDE HOLE H25 AND H27: IN THE FRAME FOOT, FRAME REINFORCING, FRAME HOLE DIMENSION AT 9.92MM PRESENT NO CRACK INDICATION, STRAP AT 7.26MM PRESENT, NO CRACK INDICATION. COMPLIED WITH EA6-5310-168229.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 43,995 hrs · 22,752 cycles

BULK CARGO STRINGER 56R CORRODED FR 65-66. CUT DAMAGE STRINGER & DEBURR SHAPE EDGES OF CUTOUT IAW SRM 53-10-14/201, PAR 4.A, FIG 201. MAKE REPAIR PARTS IAW SRM 53-10-14/201 PAR 4A, FIG 201. DRILL HOLES AND DEBURR REPAIR PARTS IAW SRM 53-10-14/201, PAR 4.A, FIG 201. APPLY ALODINE TO REPAIR PARTS IAW SRM 51-21-10. APPLY WASH PRIMER AND POLYURETHANE PRIMER TO REPAIR PARTS IAW SRM 53-10-14/201, PAR 4.A, FIG 201. WET INSTALL THE REPAIR PARTS IAW SRM 53-10-14/201, PAR 4.A, FIG 201. INSTALL THE RELEVANT FASTENERS AND PARTS IAW SRM 51-40-21. RESTORE FINISH TO REPAIR AREA IAW SRM 51-75-10.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 43,995 hrs · 22,752 cycles

BULK CARGO STRINGER 55 RT CORRODED FR 65-66. CUT DAMAGE STRINGER & DEBURR SHAPE EDGES OF CUTOUT IAW SRM 53-10-14, FIG 201. APPLY WASH PRIMER & PRIMER TO THE CUTOUT EDGES IAW SRM 53-10-14, FIG 201. MAKE REPAIR PROFILE AND REPAIR SPLICES IAW SRM 53-10-14, FIG 201. DRILL HOLES AND DEBURR REPAIR PARTS IAW SRM 53-10-14, FIG 201. APPLY ALODINE TO REPAIR PARTS IAW SRM 51-21-10. APPLY PRIMER AND TOP COAT TO THE REPAIR PARTS IAW SRM 53-10-14, FIG 201. WET INSTALL THE REPAIR PARTS AND SPLICES IAW SRM 53-10-14 FIG 201. INSTALL THE RELEVANT FASTENERS AND PARTS IAW SRM51-40-21. RESTORE FINISH TO REPAIR AREA IAW SRM 51-75-10.

Part: FRAME — DAMAGED (ZONE 200) · airframe 43,995 hrs · 22,752 cycles

CENTER FUSELAGE, THE UPPER FRAME 45 BASE-TO-ARCHES JUNCTION FOUND HOLE NR 22 WITH CRACK SIGNAL AND THE CRACK IS ELIMINATED WHEN THE HOLE DIMENSION IS 0.551" (RT SIDE). COMPLIED WITH EA6-5310-168229.

Part: FITTING — DAMAGED (ZONE 200) · airframe 43,995 hrs · 22,752 cycles

CENTER FUSELAGE UPPER FRAME 44 BASE-TO-ARCHES JUNCTION FOUND HOLE NR 5 WITH CRACK SIGNAL AND THE CRACK IS ELIMINATED WHEN THE HOLE DIMENSION IS 0.472". (LT SIDE) COMPLIED WITH EA6-5310-168229

Part: STRINGER SPLICE — CORRODED (ZONE 100) · corrosion level 2 · airframe 43,995 hrs · 22,752 cycles

BULK CARGO STRINGER SPLICE CORRODED, LOCATED AT FR65,STGR43 LT 1. REMOVED AND REPLACED CORRODED SPLICE IAW SRM 51-40-21. REPAIRED IAW SRM51-40-44.

Part: FRAME — CRACKED (ZONE 200) · airframe 43,995 hrs · 22,752 cycles

CERNTER FUSELAGE UPPER FRAME 43 BASES-TO-ARCHES JUNCTION ROTAING PROBE INSPECTION FOUND HOLE NR 2 WITH CRACK SIGNAL & THE HOLE DIMESION IS 0.313" (RT SIDE). COMPLIED WITH EA6-5310-168229.

Part: FITTING — CRACKED (ZONE 200) · airframe 43,995 hrs · 22,752 cycles

CENTER FUSELAGE, UPPER FRAME 43 BASES-TO-ARCHES JUNCTION ROTATING PROBE INSPECTION FOUND HOLE NR 2 WITH CRACK SIGNAL & THE HOLE DIMESION IS 0.313" (LT SIDE).COMPLIED WITH EA6-5310-168229.

Part: CONTROLLER — FAILED (SLATS) · airframe 43,484 hrs · 22,426 cycles

SLATS FAILED TO EXTEND ON APPROACH. CHECKED NR 1 AND NR 2 SFCCS. NR 1 SFCC FAULTS JAM, NR 2 SFCC FAULTS LT RETRACT SWITCH. ADDED MPN 49-079-05 QTY 2 EA CG, SFCC1 - SLATS JAM - SEE TSM 27-80-02 (FIRST TIME OCCURANCE) THIS CHECKS DRIVE LINE AND COMPONENTS, LUBES, FIG 101. SFCC2 - LT RETRACT SW IS A KRUEGER FLAP RETRACT SW FAULT. SEE TSM 27-80-12 FIG 101. FIN IS 49CV SEE AMM 27-89-00-00, 27-89-11-04, 27-89-12, R & R 49CV KREUGER FLAP SWITCH. PN 132-02-0260, IAW AMM 27-89-00-12. SFCC POSITIONS, LUBED BALL NUTS, IAW TSM, INSPECTED DRIVE LINE/COMPONENTS FOR DEFECTS AND POPPED TORQUE LIMITERS, NONE FOUND. SYS CHECKS OK. FINAL CLOSED.

Part: TARGET — LOOSE (PROX SENSOR) · airframe 42,582 hrs · 21,768 cycles

AFTER TAKEOFF, GEAR LEVER WOULD NOT GO PAST NEUTRAL. SWITCHED FROM SYS 1 TO SYS 2 WITH SAME RESULT. ALL 3 LANDING GEAR REMAINED DOWN AND LOCKED. AFTER APPROX 2 MINS, ALL PITCH TRIM AND LEVERS TRIPPED OFF AND WOULD NOT RESET, UNTIL AFTER LANDING. T/S FOUND NOSE GEAR PROXIMITY SENSORS 1 & 2 TARGETS ON LINK LOOSE. TIGHTENED LINK AND SAFTIED, CHECKED CLEARANCE IAW AMM 32-00-00-04-0 G.1(D). PERFORMED LANDING GEAR NORMAL EXTENSION/RETACTION FUNCTION TEST IAW AMM 32-31-00, BLOCK 501. CHECKS GOOD NO FAULTS. ACFT OK FOR CONT SERVICE. CLOSED.

Part: SUPPORT FITTING — CORRODED (ZONE 300) · airframe 42,386 hrs · 21,622 cycles

VERTICAL STABILIZER INTERIOR, RUDDER HINGE NR 4 SUPPORT FITTING AT REAR SPAR, RIB-13 HAS CORROSION ON BOTTOM EDGE , ABOUT 10 SQUARE INCHES. R & R NR 4 RUDDER HINGE SUPPORT FITTING AT REAR SPAR RIB 13 IAW A310 SRM 51-72-10, PGS 1-3.

Part: SKIN — CORRODED (ZONE 200) · airframe 42,386 hrs · 21,622 cycles

FUSELAGE TAIL SECTION EXTERNAL SKIN AT FR87, BETWEEN STR5L AND 6L, CORROSION ON SPLICE PLATE, ABOUT 4 SQUARE INCHES. REPAIRED FUSELAGE EXTERIOR SKIN AT FR87 BETWEEN STR 5L AND STR 6L IAW EA,6-5310-145562 FUSELAGE -FR87 SKIN.

Part: STRINGER — CORRODED (ZONE 200) · airframe 42,386 hrs · 21,622 cycles

AFT FUSELAGE, INTERNAL, RT STRINGER 4 END FITTING AT AFT SIDE OF FRAME 87 HAS SEVERE EXFOLIATION CORROSION APPROX 1 SQUARE INCH. R & R STR 4R END FITTING AT FR87 AFT SIDE IAW SRM 51-72-10, PGS 1-3.

Part: STIFFENER — CORRODED (ZONE 100) · airframe 42,386 hrs · 21,622 cycles

CORROSION AT LOWER END OF WASTE WATER SERVICING BOX BETWEEN PAN AND FUSELAGE SKIN. LT FUSELAGE BETWEEN FRAMES 12 AND 12A. R & R SKIN STIFFENER AT WASTE WATER SERVICING BOX CUTOUT INTERIOR FR12-12A STR36L TO STR43L IAW SRM 51-72-10, PGS 1-3.

Part: SKIN — CORRODED (ZONE 500) · airframe 42,386 hrs · 21,622 cycles

CORROSION FOUND AT LT WING UPPER SKIN AT FUEL PORT AND UNDER GROUND POINT. COMPLIED WITH E.A. 6-5730-145575 WINGS - LT OVERWING.

Part: SKIN — CORRODED (FUSELAGE) · airframe 42,386 hrs · 21,622 cycles

FUSELAGE TAIL SECTION FR 87 BETWEEN STR 2R AND 3R CORROSION. (SURFACE) ON SPLICE PLATE, ABOUT 4 SQ INCHES. REMOVED LEVEL 1 CORROSION IAW SRM 51-74-10 , CHECKED LIMITS FOUND TO BE OUT OF LIMITS IAW SRM 53-19-10, FIG 102. FABRICATED STRAP JOINT IAW DWG A53985255. INSTALLED STRAP IAW SRM 51-40-21.

Part: ANGLE — CORRODED (ZONE 100) · corrosion level 2 · airframe 42,386 hrs · 21,622 cycles

UPON REMOVAL OF LAV SERVICE BOX AND SKIN STIFFENERS, FOUND EXCESSIVE CORROSION EXTENDING UNDER FR 12A LT AT STR 37L. REMOVED LEVEL ONE CORROSION IAW SRM 51-74-10. MATERIAL LOSS WAS 100 PERCENT OF ANGLE AT FR 12A AND STR 37L, FOUND TO BE OUT OF LIMITS IAW SRM 51-10-13. FABBED ANGLE IAW DWG A53610986 AND INSTALLED ANGLE USING THE FOLLOWING SRM REF 51-71-50, STEP 4, FIG 201, SRM, 51-21-10 PG 8-9 AND 51-75-10, 51-40-44, 51-71-50, FIG 201.

Part: SPAR — CRACKED (VERICAL STAB) · airframe 42,386 hrs · 21,622 cycles

CRACK AT FRONT SPAR CONNECTING SECTION AT RIB 1,2.5 INCH LONG. REMOVED TRANSVERSE FITTING AT VERTICAL STAB FWD SPAR RIB 1 AND REMOVED CONNECTION SECTION AT RIB 1 IAW SRM 51-72-10 PG 1-3. CLEANED AREA IAW AMM 12-21-11. REPROTECTED AREA IAW SRM 51-75-10 PG 3-8. INSTALLED NEW CONNECTING SECTION AND TRANSVERSE FITTING IAW SRM 51-72-10 PG 1-3. REPROTECTED AREA PER A310 SRM 51-75-10 PG 3-8.

Part: SKIN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 42,386 hrs · 21,622 cycles

FUSELAGE TAIL SECTION EXTERNAL SKIN HAS SURFACE CORROSION AT FWD OF FR 78,BETWEEN STR 2LT AND STR 3LT,ABOUT 8 SQ INCHES. CORROSION AT FUSELAGE EXTERNAL SKIN FOUND TO BE OUT OF LIMITS IAW SRM 53-19- 12 FIG 102 PAR 5. REPAIRED AREA WITH INTERNAL DOUBLER AND FILLER IAW SRM 53-10-12 FIG 229 PG 411-412. CUT AND SPLICED STR 3L BETWEEN FR 77 AND FR 78 IAW EA 6-5310-145556 PG3, REMOVED AND RE-INSTALLED PREVIOUS REPAIR AT FR 78 EXTERNAL SKIN WITH CORRECT FILLER PIECE IAW A310 SRM 53-10-12 FIG 228 PG 403-404.

Part: BRACKET — BROKEN (FUSELAGE) · airframe 42,386 hrs · 21,622 cycles

FUSELAGE TAIL SECTION EXTERIOR GAIRING SUPPORT BRACKET BROKEN OFF AT 5 INCHES AFT OF FR 79, STR 4 RT. R & R MOUNTING BRACKET AT FUSELAGE TAIL SECTION EXTERIOR AT FR 79 AND STR 4R IAW SRM 51-72-10, PG 1-3 AND SRM 51-40-21, PARA 7, PG 24-55.

Part: FITTING — CORRODED (VERTICAL STAB) · airframe 42,386 hrs · 21,622 cycles

VERTICAL STABILIZER LT AFT FITTING HAS CORROSION ON OTBD FACE, 2 LOCALIZED AREAS ABOUT 3 SQ INCHES. REMOVED LEVEL 1 CORROSION, COMPLIED WITH EA 6-5530-145557.

Part: STRUCTURE — CORRODED (VERTICAL STAB) · corrosion level 2 · airframe 42,386 hrs · 21,622 cycles

VERTICAL STABILIZER REAR SPAR LT CHORD, RIB 10 TO RIB 16 HAS CORROSION AT 11 EA NUT PLATES LOCATIONS. REMOVED LEVEL 1 CORROSION, COMPLIED WITH EA 6-5530-145551.

Part: FINGER DOUBLER — GOUGED (FUSELAGE SKIN) · airframe 42,386 hrs · 21,622 cycles

FUSELAGE TAIL SECTION 7 INCHES AFT OF FR 87 BETWEEN STR 4 LT AND STR 5 LT FUSELAGE SKIN FINGER DOUBLER HAS A GOUGE, .010 IN DEPTH X 0.25 INCH WIDTH X 0.25 INCH LENGTH APPROX. BLENDED GOUGE ON FUSELAGE TAIL SECTION 7" AFT OF FR 87 BETWEEN STR 4L AND 5L IAW SRM 51-73-10, PG 209, PARA F. CHECKED LIMITS BEFORE 0.198 AFTER 0.158, LOSS 0.036. WITHIN LIMITS IAW SRM 53-19-12, FIG 102, PARA 5. REPROTECTED ARE IAW SRM 51-21-10, PG 2, PARA 2, 51-75-10, PG 204, PARA 4 AND PG 225, PARA 10C.

Part: STRUCTURE — CORRODED (VERTICAL STAB) · airframe 42,386 hrs · 21,622 cycles

VERTICAL STABILIZER RT CHORD BETWEEN RIB 18 AND RIB 25 HAS SURFACE CORROSION AROUND NUTPLATES, 3 PLACES, APPROX 3 SQ INCHES. REMOVED LEVEL 1 CORROSION, COMPLIED WITH EA 6-5530-145551.

Part: FITTING — CORRODED (VERTICAL STAB) · airframe 42,386 hrs · 21,622 cycles

VERTICAL STABILIZER RT CTR MOUNT FITTING HAS CORROSION OTBD SURFACE ABOUT 8 SQ INCHES. REMOVED LEVEL 1 CORROSION, COMPLIED WITH EA 6-5530-145557.

Part: SKIN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 42,386 hrs · 21,622 cycles

FUSELAGE TAIL SECTION EXTERNAL SKIN HAS SURFACE CORROSION AT FR 85 BETWEEN STR 5 RT AND STR 6 RT ABOUT 5 SQ INCHES. CLEANED FUSELAGE TAIL SECTION EXTERNAL SKIN AT FR 85, STR 5 R AND STR 6 R IAW AMM 12-21-12. UPON FURTHER INSP, NO CORROSION FOUND. REPROTECTED AREA IAW SRM 51-21-10, PG 2, PARA 2 AND 51-75-10 PG 204, PARA 4 AND PG 225, PARA 10C.

Part: SKIN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 42,386 hrs · 21,622 cycles

FUSELAGE TAIL SECTION EXTERNAL SKIN AT FR 87 BETWEEN STR 5LT AND STR 6LT, CORROSION ON SPLICE PLATE ABOUT 4 SQ INCHES. REPAIRED FUSELAGE EXTERIOR SKIN AT FR87 BETWEEN STR5L AND STR6L IAW EA 6-5310-145562.

Part: FITTING — CORRODED (VERTICAL STAB) · airframe 42,386 hrs · 21,622 cycles

VERTICAL STABILIZER RT FWD MOUNT FITTING OUTER FACE HAS CORROSION JUST AT SKIN EDGE AREA ABOUT 0.5 SQ INCHES. REMOVED LEVEL 1 CORROSION, COMPLIED WITH EA 6-5530-145557.

Part: FITTING — CORRODED (VERTICAL STAB) · corrosion level 2 · airframe 42,386 hrs · 21,622 cycles

UPON REMOVAL OF LOWER WEB AT VERTICAL STAB FOUND CORROSION ON AFT FITTING AT LT ATTACH POINT. REMOVED CORROSION ON AFT TRAVERSE FITTING ON VERT STAB AT REAR SPAR IAW SRM 51-74-10, PG 5. BEFORE THICKNESS 0.557, AFTER 0.448. LOSS OF 0.069 IS OUT OF LIMITS IAW SRM 55-30-00, FIG 101. R & R TRANSVERSE FITTING IAW SRM 51-40-21, PARA 7, PG 24-43.

Part: FITTING — CORRODED (VERTICAL STAB) · corrosion level 2 · airframe 42,386 hrs · 21,622 cycles

VERTICAL STABILIZER RT AFT MOUNT FITTING HAS CORROSION ON OTBD FACE ABOUT 10 SQ INCHES. REMOVED LEVEL 1 CORROSION, COMPLIED WITH EA 6-5530-145557.

Part: PLATE — CORRODED (VERTICAL STAB) · corrosion level 2 · airframe 42,386 hrs · 21,622 cycles

VERTICAL STABILIZER RIB 1, STRINGER 2LT TO 5LT, REAR LOWER PLATE LOWER SURFACE CORRODED APPROX 2 IN WIDE X 4 IN LENGTH JUST ABOVE LT AFT STABILZER HINGE. COMPLIED WITH EA 6-5530-145557.

Part: FINGER DOUBLER — GOUGED (FUSELAGE SKIN) · airframe 42,386 hrs · 21,622 cycles

FUSELAGE TAIL SECTION, 7 INCHES AFT OF FR 87, BETWEEN STR 5RT AND STR 4RT, FUSELAGE FINGER DOUBLER HAS A GOUGE, 0.010 INCH DEPTH X 0.25 INCH WIDTH X 0.25 INCH LENGTH APPROX. BLENDED GOUGE ON TAIL SECTION 7" AFT OF FR 87 BETWEEN STR 4R AND STR 5R IAW SRM 51-73-10, PG 209, PARA F. BEFORE THICKNESS 0.198" AFTER 0.170" LOSS 0.028", WITHIN LIMITS IAW SRM 53-19-12, FIG 102, PARA 5. REPROTECTED AREA IAW SRM 51-21-10, PG 2, PARA 2 AND 51-75-10, PG 204, PARA 4 AND PG 225, PARA 10C.

Part: STIFFENER — CORRODED (VERTICAL STAB) · corrosion level 2 · airframe 42,386 hrs · 21,622 cycles

VERTICAL STABILIZER INTERIOR REAR SPAR HORIZ STIFFENER BETWEEN RIB 9 AND RIB 10 HAS CORROSION ABOUT 3 SQ INCHES. REMOVED HORIZ STIFFNER AND DIAGONAL STIFFNER BETWEEN RIB 9 AND 10 AT VERT STAB REAR SPAR. REMOVED CORROSION ON HORIZ STIFFNER, NOMINAL 0.050, REMAINING 0.047, LOSS .003, DIAGONAL STIFFENER, NOMINAL 0.063, REMAINING 0.054, LOSS 0.009, SKIN 0.055, REMAINING 0.054, LOSS 0.001. ALL AREA WITH LIMITS IAW SRM 55-30-00, FIG 101. REPROTECTED AREA AND REINSTALLED STIFFENERS IAW SRM 51-40-21, PG 22 AND 55-60-21, PG 26.

Part: SKIN — SCRATCHED (FUSELAGE) · airframe 42,386 hrs · 21,622 cycles

FUSELAGE TAIL SECTION EXTERIOR SKIN IS SCUFFED AT 4 INCHES FWD OF FR 80/82 BETWEEN S2-3R. BLENDED AREA TO A SMOOTH CONTOUR IAW SRM 51-73-10 PG 209. CHECKED LIMITS BEFORE 0.197, AFTER 0.0191, LOSS 0.006 WHICH IS WITHIN LIMITS IAW SRM 53-19-12 FIG 102 PARA 5. REPROTECTED AREA IAW SRM 51-75-10 PG 225 PARA 10C.

Part: RIB — CORRODED (VERTICAL STAB) · corrosion level 2 · airframe 42,386 hrs · 21,622 cycles

VERTICAL STABILIZER INTERIOR DIAGONAL ANGLE AT RT JOINT OF RIB 9 AND STR 2 HAS CORROSION ABOUT 4 SQ INCHES. REMOVED DIAGONAL BRACE AT RIB 10 AND REAR SPAR ON VERTICAL STABILIZER IAW SRM 51-72-10, PG 1-3. REMOVED CORROSION IAW SRM 51-76-10, PG 205, PARA 6. NOMINAL THICKNESS 0.059, REMAINING THICKNESS 0.056. MATERIAL LOSS 0.003 IS WITHIN LIMITS IAW SRM 51-30-00 6-1, FIG 101. REPROTECTED AREA AND REINSTALLED DIAGONAL BRACE IAW SRM 51-40-21, PG 24, PARA 7.

Part: ANGLE — CORRODED (VERTICAL STAB) · corrosion level 2 · airframe 42,386 hrs · 21,622 cycles

VERTICAL STABILIZER REAR SPAR FWD FACE RIB 9, HORIZ ANGLE HAS CORROSION ABOUT 3 SQ INCHES. REMOVED HORIZONTAL ANGLE AT FWD FACE OF RIB 9 IAW SRM 51-40-21, PG 22 PARA 7. REMOVED CORROSION IAW SRM 51-74-10, PG 205, PARA 3. NOMINAL THICKNESS IS 0.063, REMAINING THICKNESS IS 0.059, MATERIAL LOSS IS 0.004. IS WITHIN LIMITS IAW SRM 55-30-00, FIG 101. REPROTECTED AREA AND REINSTALLED ANGLE IAW SRM 51-40-21, PG 22.

Part: SKIN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 42,386 hrs · 21,622 cycles

FUSELAGE TAIL SECTION EXTERNAL SKIN HAS SURFACE CORROSION AT FR 87, STR 5LT, ABOUT 3 SQ INCHES. CLEANED FUSELAGE TAIL SEC EXTERNAL SKIN IAW AMM 12-21-12. UPON FURTHER INSPECTION NO CORROSION FOUND. REPROTECTED AREA IAW SRM 51-21-10 PG 2 PARA 2 AND 51-75-10 PG 4 204 PARA 4 AND PG 225 PARA 10C.

Part: SKIN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 42,386 hrs · 21,622 cycles

FUSELAGE TAIL SECTION STR 5RT AFT OF FR 83, EXTERNAL SKIN HAS CORROSION ABOUT 4 SQ INCHES. CLEANED AREA OF FUSELAGE TAIL SECTION STR 5R AFT OF FR 83 IAW AMM 12-21-12. UPON FURTHER INSP, NO CORROSION NOTED. REPROTECTED AREA IAW SRM 51-75-10, PG 225, PARA 10C AND PG 204, PARA 4.

Part: SKIN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 42,386 hrs · 21,622 cycles

FUSELAGE TAIL SECTION EXTERNAL SKIN HAS SURFACE CORROSION BETWEEN FR 85 AND FR 86, BETWEEN STR 5 LT AND STR 6 LT. CLEANED FUSELAGE TAIL SECTION EXTERNAL SKIN BETWEEN FR 85 AND FR 86 BETWEEN STR 5L AND 6L IAW AMM 12-21-12. UPON FURTHER INSPECTION NO CORROSION FOUND. REPROTECTED AREA IAW SRM 51-21-10, P2, PARA 2 AND 51-75-10 PG 204, PARA 4 AND PG 225, PARA 10C.

Part: SKIN — DENTED (FUSELAGE) · airframe 42,386 hrs · 21,622 cycles

FUSELAGE TAIL SECTION EXTERNAL SKIN HAS DINGS ON SURFACE AT 4 INCHES AFT OF FR 87, BETWEEN RIB 2LT AND RIB 3LT ABOUT 4 SQ INCHES. BLENDED FUSELAGE TAIL SECTION SKIN SURFACE DENTS IAW SRM 51-73-10 PG 209 PARA F DEEPEST BEFORE 0.197 AFTER 0.191, LOSS 0.006. ALL WITHIN LIMITS IAW SRM 53-19-12 FIG 102 PARA 5. REPROTECTED AREAS IAW SRM 51-21-10 PG 2 PARA 2 AND 51-75-10 PG 204 PARA 4 AND PG 225 PARA 10

Part: SKIN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 42,386 hrs · 21,622 cycles

FUSELAGE TAIL SECTION EXTERNAL FUSELAGE SKIN HAS SURFACE CORROSION AT FR 84, STR 5 LT ABOUT 7 SQ INCHES. CLEANED FUSELAGE TAIL SEC EXTERNAL SKIN BETWEEN FR 85 AND FR 86 AND STR 5R AND 6R IAW AMM 12-21-12. AFTER FURTHER INSP, NO CORROSION NOTED. REPROTECTED AREA IAW SRM 51-21-10, PG 2, PARA 2 AND 51-75-10, PG 204, PARA 4 AND PG 225, PARA 10C.

Part: PLATE — CORRODED (VERTICAL STAB) · corrosion level 2 · airframe 42,386 hrs · 21,622 cycles

VERTICAL STABILIZER, RIB 1, STRINGER 2RT - 5RT REAR LOWER PLATE. LOWER SURFACE CORRODED APPROX 1IN WIDE X 2IN LENGTH JUST ABOVE RT AFT STABILIZER HINGE. R & R VERTICAL STAB RIB 1AFT LOWER PLATE IAW SRM 51-72-10, PGS 1-3.

Part: SEAT TRACK — GOUGED (ZONE 200) · airframe 42,386 hrs · 21,622 cycles

4 GOUGES ON SEAT TRACK SCALLOP ON NR 3R SEAT TRACK FRAME 54 PLUS 12" ABOUT .2500" X .5" EACH. DAMAGE TO SEAT TRACK AT 3R FR 54.2 TO 55/58 FOUND TO BE OUT OF LIMITS IAW SRM 53-10-16, FIG 101. REMOVED SEAT TRACK IAW SRM 51-72-10, PG1. FABBED NEW SEAT TRACK IAW DWG A153274259. INSTALLED SEAT TRACK IAW SRM 51-72-10, PG 1.

Part: COVER PLATE — CORRODED (DOOR FRAME) · airframe 42,386 hrs · 21,622 cycles

AT STA 40951, FR75A AFT CREW DOOR AFT FRAME TOP ON WEB CORROSION ABOUT 3 INCHES AROUND LT SIDE. REPAIRED UPPER WEB OF L-2 DOOR CUT OUT AT FR 75A IAW SRM 53-18-18 PAR 7, FIG 202, SHEET 5 AND DWG A53980302.

Part: STRINGER — CORRODED (ZONE 200) · corrosion level 2 · airframe 42,386 hrs · 21,622 cycles

REAR FUSELAGE FRAME 84 TO 85 STR 27RT CORRODED ON AFT END APROX 4 IN. REPAIRED STR 27R BETWEEN FR 84 AND FR85 IAW SRM 53-19-14, FIG 202. GENERAL REPAIR SCHEME.

Part: CROSSBEAM — CORRODED (ZONE 200) · corrosion level 2 · airframe 42,386 hrs · 21,622 cycles

REAR FUSELAGE FR 86, 5" INCHES INBD OF STR 15L, AFT CROSSBEAM HAS 2 EA PLACES OF EXFOLIATION CORROSION, APPR 2" INCHES SQUARE. R & R CROSSBEAM AT FR 86, STR 15L IAW SRM 51-72-10 PAR 5&6 AND SRM 51-40-21, PAGES 1,2,3.

Part: FLOOR SUPPORT — CORRODED (ZONE 200) · corrosion level 2 · airframe 42,386 hrs · 21,622 cycles

FLOOR SUPPORT STRUCTURE Y-770, FROM FR14 TO FR 10 IS CORRODED ON THE TOP SIDE OF THE BEAM. R & R FLOOR SUPPORT Y-770, BETWEEN FR 10 AND FR 14 IAW A310-200 SRM 51-72-10, PAGE 1-3.

Part: DUMMY RAIL — WORN (ZONE 200) · airframe 42,386 hrs · 21,622 cycles

DUMMY TRACK 4L, FR54.2 EXCEEDED THE ALLOWABLE WEAR LIMITS. REPAIR DUMMY TRACK 4L AT FR54.2 IAW EO 5310-7-3322 PT2 INSTRUCTIONS.

Part: STIFFENER — CORRODED (ZONE 100) · corrosion level 2 · airframe 42,386 hrs · 21,622 cycles

LAV SERVICE BOX AND SKIN STIFFENER HAS EXCESSIVE CORROSION EXTENDING ON FR 12 STR 37L. REMOVED CORROSION FROM SKIN STIFFENER FOUND TO BE OUT OF LIMITS IAW SRM 53-12-13 PB 201, FABRICATED 3 EA SPLICE ANGLES IAW SRM 53-12-13, PB 211-213, FIG 201, SHEET 3. R & R 3 EA SPLICE ANGLES IAW SRM 53-12-13, PB 211/212, FIG 201, SHEET 3.

Part: SEAT TRACK — CORRODED (ZONE 200) · airframe 42,386 hrs · 21,622 cycles

MAIN CARGO DECK, RT SEAT TRACK 5R, FROM FR 14 TO FR 18 HAS EXFOLIATED CORROSION. R & R SEAT TRACK 5R, Y-1959, FROM FR 14 TO FR 18 IAW SRM 51-72-10, PAGE 1-3.

Part: FLOORBEAM — CORRODED (ZONE 100) · corrosion level 2 · airframe 42,386 hrs · 21,622 cycles

AFT CARGO FLOORBEAM TOP CHORD FR 60 RT SIDE HAS CORROSION ON BOTTOM, ABOUT 58" FROM CENTERLINE,AND ABOUT 1" LONG X .5" WIDE. R & R ANGLE IN AFT CARGO COMPARTMENT AT FR 60, RT SIDE IAW SRM 51-40-21, PAR 6.

Part: CROSSBEAM — CORRODED (ZONE 100) · corrosion level 2 · airframe 42,386 hrs · 21,622 cycles

2EA PLACES OF CORROSION FOUND ON AFT CROSSBEAM IN REAR FUSELAGE FRAME 85, 5" INCHES INBD OF STRINGER 13R (2" SQUARE INCHES). R & R CROSSBEAM AT FRAME 85, STRINGER 13R IAW SRM 51-40- 21.

Part: BEAM — CORRODED (PAX DOOR) · airframe 42,386 hrs · 21,622 cycles

L-2 DOOR, AT BEAM 1 SEGMENT AT FR 74, HAS 2" SQUARE CORROSION ON AFT SIDE. REPAIRED L-2 DOOR SEGMENT AT BEAM 1 IAW DWG NR A52175214 AMD SRM 51-40-21, PAR 6.

Part: SEAT TRACK — CORRODED (ZONE 200) · corrosion level 2 · airframe 42,386 hrs · 21,622 cycles

MAIN CARGO DECK, R/T SEAT TRACK 5R, FROM FR 14 TO FR 18 HAS EXFOLIATED CORROSION. REMOVED AND REPLACED SEAT TRACK 5R, Y-1959, FROM FR 14 TO FR 18 IAW SRM 51-72 -10 ,PAGE 1-3.

Part: FLOOR SUPPORT — CORRODED (ZONE 200) · corrosion level 2 · airframe 42,386 hrs · 21,622 cycles

MAIN DECK FLOOR SUPPORT STRUCTURE Y1456, TOPSIDE IS CORRODED FROM FR 14 TO FR 12A. REMOVED AND REPLACED FLOOR SUPPORT, Y 1456, FROM FR 11 TO FR 15A IAW SRM 51-72-10, PAGE 1-THRU 3.

Part: SKIN — CRACKED (TAILCONE) · airframe 42,386 hrs · 21,622 cycles

TAILCONE HAS A CREASE WITH A DEPTH OF .010", AND A LENGTH OF 0.375", LOCATED BETWEEN FR 96 AND FR 97, BETWEEN STR 2R AND STR 3R. NDT CHECK COMPLIED WITH AND FOUND A CRACK (.375") IAW NTM 51-10-08. CUT OUT DAMAGED SECTION OF TAILCONE AND REPAIRED TAILCONE SKIN IAW SRM 53-19-12, FIG 201. USING FILLER DOUBLER REPAIR METHOD.

Part: SKIN — CRACKED (TAIL CONE) · airframe 42,386 hrs · 21,622 cycles

.5" INCH CRACK ON TAILCONE SKIN, BETWEEN FR 96 AND FR 97 AND BETWEEN STR 4R AND STR 5R. CUT OUT DAMAGED AREA WEB AND SKIN AREA BETWEEN FR 96 AND FR 97 AND BETWEEN STR 4R AND STR 5R, REPAIRED TAILCONE SKIN IAW SRM 53-19-12, FIG 202, USING WEB FILLER AND WEB DOUBLER, SKIN FILLER, SKIN DOUBLER REPAIR SCHEME.

Part: FLOOR SUPPORT — CORRODED (ZONE 200) · corrosion level 2 · airframe 42,386 hrs · 21,622 cycles

FLOOR SUPPORT STRUCTURE, Y 450, HAS CORROSION FROM 6" INCHES AFT OF FR 14 TO 8" INCHES FWD OF FR 14 ON THE TOPSIDE. R & R FLOOR SUPPORT STRUCTURE Y450, FROM FR 11TO FR 15A IAW SRM 51-72-10, PAGES 1-3.

Part: CROSSBEAM — CORRODED (ZONE 100) · corrosion level 2 · airframe 42,386 hrs · 21,622 cycles

FWD CROSSBEAM IN REAR FUSELAGE AT FR 85 AND STRINGER 13R HAS 1" INCH OF CORROSION ON TOPSIDE. R & R CROSSBEAM AT FR 85 AND STR 13R IAW SRM 51-40-21, PAR.7.

Part: CROSSBEAM — CRACKED (ZONE 200) · airframe 42,386 hrs · 21,622 cycles

CROSSBEAM BETWEEN Y 953 AND Y 450 AND FR 14 AND FR 15A HAS A 1" INCH CRACK ON TOPSIDE. R & R CROSSBEAM BETWEEN Y953 AND Y450 AND FR14 AND FR15A IAW SRM 51-72-10 PAGE 1-3.

Part: STRINGER — CORRODED (ZONE 200) · airframe 42,386 hrs · 21,622 cycles

CORROSION ON STR 44L ABOUT 10 IN AFT OF FR58 , 1 IN IN DIAMETER, REMOVED CORROSION FROM STR 44L IAW SRM 51-74-10 , CHECKED LIMITS IAW SRM 53-10-14, PAGE 202. FOUND TO BE OUT OFF LIMIT, REPAIRED STR 44L IAW SRM 53-10-14, FIG 201.

Part: FLAP SYSTEM — FAULTED (LE FLAPS) · airframe 41,998 hrs · 21,307 cycles

FLAPS STUCK AT 16DEG WITH 20DEG SELECTED WITH FLAPS SYS 1 AND 2 FAULT LIGHT. DURING GO AROUND MOMENTARY OVERSPEED AT 200 KNOTS FOR 5 SECONDS. RECYCLED HANDLE, FLAPS WORKED NORMAL. AMM 05-51-13-0 FOR INSPECTIONS AFTER FLAP/SLAT LIMITING SPEED EXCEEDED. PLEASE WORK IN CONJUNCTION WITH TSI: 31-30 0097. C/W MM 05-51-13-0 FLAP/SLAT LIMITING SPEED EXCEEDED. ALL INSP PARTS PERFORMED AND CHECKED GOOD WITH NO FAULTS OR PROBLEMS FOUND IAW CHECK. IAW REQUEST AND MEM AVSH FOUND DEFERED IAW (351206), ACFT EXCEEDED LIMITS.

Part: VALVE — MALFUNCTIONED (SPOILERS) · airframe 41,294 hrs · 20,810 cycles

DURING T/O ROLL AT APPROX 70K ECAM SHOWED "GROUND SPOILERS NOT RETRACTED" AND SPOILER PANEL 3 AND 2 FAULT. REJECTED T/O - ATTEMPTED RESET OF SPOILER PANEL WITH NO LUCK. ECAM SHOWS PANEL NR 2 EXTENDED. ACFT RELEASED FOR SERVICE IAW MEL/CDL: 27-61-01-B. TROUBLESHOT PER TSM 27-61-06 FIG. 102, EFCU 2 LOGGED FAULTS M2 4/8. CHECKED LVDT RESISTANCE AND SERVO VALVE RESISTANCE READ GOOD, R & R 2R SPOILER VALVE GROUP REF MM 27-64-12-4. OPERATED SPOILERS THROUGH VARIOUS CYCLES WITH NO FAULTS NOTED AND NO FAULTS LOGGED ON EFCU'S, DEFERRAL CLEARED.

Part: BULKHEAD — FAILED (ZONE 100) · airframe 40,469 hrs · 20,271 cycles

PREVIOUS REPAIR LOCATED AT FRAME 80/82 AFT PRESSURE BULKHEAD FORWARD SIDE CIRCUMFERENTIAL STRAP AND FRAME WEB REPAIR BETWEEN STR 48 LT AND 48 RT WITH 2 EA FRAME WEB REPAIR PLATES, 2 CIRCUMFERENTIAL REPAIR SPLICE STRAPS AND 1 CIRCUMFERENTIAL REPAIR SECTION REPAIR NOT IAW SRM REQUIREMENTS. REMOVED PREVIOUS INSTALLED LOCK FASTENER COLLARS ON REPAIR AT FR 80/82 BETWEEN STR 48 LT TO STR 48 RT CIRCUMFERENTIAL STRAP AND INSTALLED CORRECT COLLARS IAW FEDEX EA 6-5310-121308, RELEASE DATE 18 JUNE, 2008. THIS IS AN AIRBUS REPAIR AND IS A RESULT OF AGING AIRCRAFT INSPECTION.

Part: SKIN — DAMAGED (LT WING TE FLAP) · airframe 40,469 hrs · 20,271 cycles

LEFT INBOARD FLAP LOWER SKIN HAS REPAIR MISSING, BETWEEN FLAP RIB 2 AND FLAP RIB 4 REMOVED DAMAGED SKIN AND CORE, FABRICATED AND INSTALLED FLAP REPAIR DOUBLER AT LT INBD LOWER SKIN BETWEEN FLAP RIB 2 AND FLAP RIB 4 IAW FEDEX EA 6-5750-121281, RELEASE DATE 29 MAY, 2008.

Part: FLOORBEAM — CRACKED (ZONE 200) · airframe 40,469 hrs · 20,271 cycles

AFT CARGO COMPARTMENT FRAME 54.3 FLOORBEAM AFT SIDE BETWEEN SEAT TRACKS 2 RT AND 3 RT VERTICLE STIFFENER HAS 2 CRACKS .250 IN LONG EACH REMOVED DAMAGED SECTION AND INSTALLED CROSSBEAM CRACK REPAIR AT FR 54.3, BETWEEN SEAT TRACKS 2 RT AND 3 RT IAW FDEDEX EA 6-5310-121286, RELEASE DATE 3 JUNE, 2008.

Part: PANEL — DAMAGED (ZONE 500) · airframe 40,469 hrs · 20,271 cycles

CENTER WING TANK LT BOOST PUMP AREA HAS 4 FASTENERS DAMAGED AT REINFORCEMENT BETWEEN FR 46 AND FR 47 REPAIRED DAMAGED FASTENER HOLES AT CENTER TANK LT BOOST PUMP INNER REINFORCEMENT PANEL BETWEEN FR 46 AND FR 47 IAW FEDEX EA 6-5710-121292, RELEASE DATE 6 JUNE,2008

Part: SKIN — FAILED (ZONE 500) · airframe 40,469 hrs · 20,271 cycles

PREVIOUS EXTERNAL REPAIR DOUBLER LOCATED ON LEFT WING O/B FLAP UPPER MAIN SKIN UNDER RUB STRIP BETWEEN RIB 2 AND FLAP TRACK NR 3 MEASURING 6 INCH BY 5 INCH. REPAIR NOT IAW SRM REQUIREMENTS. REMOVED PREVIOUS REPAIR AND INSTALLED AN APPROVED REPAIR ON LEFT WING O/B FLAP UPPER MAIN SKIN UNDER RUB STRIP BETWEEN RIB 2 AND FLAP TRACK NR 3 IAW FEDEX EA6-5750-121298. THIS IS AN APPROVED REPAIR AND IS A RESULT OF AGING AIRCRAFT INSPECTION.

Part: SKIN — FAILED (ZONE 600) · airframe 40,469 hrs · 20,271 cycles

PREVIOUS EXTERNAL REPAIR DOUBLER LOCATED ON RIGHT WING O/B FLAP UPPER MAIN SKIN UNDER RUB STRIP BETWEEN FLAP TRACK NR 5 TO RIB 11 AND 1.4 INCH FWD OF REAR SPAR MEASURING 13.6" BY 4.3". REPAIR NOT IAW SRM REQUIREMENTS. REMOVED PREVIOUS REPAIR AND INSTALLED AN APPROVED REPAIR ON RIGHT WING O/B FLAP UPPER MAIN SKIN UNDER RUB STRIP BETWEEN FLAP TRACK NR 5 TO RIB 11 AND 1.4 INCH FWD OF REAR SPAR IAW FED EX EA6-5750-121299. THIS IS AN APPROVED REPAIR AND IS A RESULT OF AGING AIRCRAFT INSPECTION.

Part: SKIN — MISREPAIRED (ZONE 600) · airframe 40,469 hrs · 20,271 cycles

PREVIOUS EXTERNAL REPAIR DOUBLER LOCATED ON RIGHT WING O/B FLAP UPPER MAIN SKIN UNDER RUB STRIP BETWEEN RIB 3 AND FLAP TRACK NR 3 AND 5.7 INCH FWD OF REAR SPAR MEASURING 11.3 INCH BY 3.9 INCH. REPAIR NOT IAW SRM REQUIREMENTS. REMOVED PREVIOUS REPAIR AND INSTALLED AN APPROVED REPAIR ON RIGHT WING O/B FLAP UPPER MAIN SKIN UNDER RUB STRIP BETWEEN RIB 3 AND FLAP TRACK NR 3 AND 5.7 INCH FWD OF REAR SPAR IAW FEDEX EA6-5750-121299. THIS IS AN APPROVED REPAIR AND IS A RESULT OF AGING AIRCRAFT INSPECTION.

Part: SKIN — DAMAGED (ZONE 100) · airframe 40,469 hrs · 20,271 cycles

PREVIOUS EXTERNAL REPAIR DOUBLER AND TRIPLER LOCATED FWD OF BULK CARGO DOOR ON RIGHT SIDE FUSELAGE SKIN AT FRAME 67 AND BETWEEN STRINGERS 37 TO 39 RT, THE REPAIR DOUBLER MEASURES 8.7 INCH BY 6.2 INCH AND THE TRIPLER MEASURES 6.7 INCH BY 4.5 INCH. REPAIR NOT IAW SRM REQUIREMENTS. REMOVED PREVIOUS REPAIR AND INSTALLED APPROVED REPAIR IAW FEDEX EA6-5310-121293 "FUSELAGE - FR67 SKIN. REPLACE PREVIOUS REPAIR AT FWD EDGE OF BULK CARGO DOOR". THIS IS AN AIRBUS REPAIR AND IS A RESULT OF AGING AIRCRAFT INSPECTION.

Part: SKIN — DAMAGED (ZONE 500) · airframe 40,469 hrs · 20,271 cycles

PREVIOUS EXTERNAL REPAIR DOUBLER LOCATED ON LEFT WING O/B FLAP UPPER MAIN SKIN UNDER RUB STRIP BETWEEN RIB 3 AND FLAP TRACK NR 3 MEASURING 4" BY 6". REPAIR NOT IAW SRM REQUIREMENTS. REMOVED PREVIOUS REPAIR AND INSTALLED APPROVED REPAIR ON LEFT WING O/B FLAP UPPER MAIN SKIN UNDER RUB STRIP BETWEEN RIB 3 AND FLAP TRACK NR 3 IAW FEDEX EA6-5750-121298. THIS IS AN APPROVED REPAIR AND IS A RESULT OF AGING AIRCRAFT INSPECTION.

Part: SKIN — DAMAGED (ZONE 500) · airframe 40,469 hrs · 20,271 cycles

PREVIOUS EXTERNAL REPAIR DOUBLER LOCATED ON LEFT WING O/B FLAP UPPER MAIN SKIN UNDER RUB STRIP AT FLAP TRACK NR 4 MEASURING 4 INCH BY 5.7 INCH. REPAIR NOT IAW SRM REQUIREMENTS. REMOVED PREVIOUS REPAIR AND INSTALLED CORRECT REPAIR ON LEFT WING O/B FLAP UPPER MAIN SKIN UNDER RUB STRIP AT FLAP TRACK NR 4 IAW FEDEX EA6-5750-121291. THIS IS AN APPROVED REPAIR AND IS A RESULT OF AGING AIRCRAFT INSPECTION.

Part: SKIN — MISREPAIRED (ZONE 100) · airframe 40,469 hrs · 20,271 cycles

PREVIOUS EXTERNAL REPAIR DOUBLER LOCATED ON LEFT SIDE FUSELAGE SKIN AT FRAME 14 CENTER OF SKIN PANEL BETWEEN STRINGERS 34 TO 35 LT UNDER THE L-1 DOOR AREA, THE REPAIR DOUBLER MEASURES 5.3 NCH BY 4.5 INCH. REPAIR IAW SRM AND SWISSAIR DWG 912189 REQUIREMENTS. REMOVED PREVIOUS REPAIR AND RE-INSTALLED REPAIR ON LT SIDE FUSELAGE SKIN AT FRAME 14 CENTER OF SKIN PANEL BETWEEN STRINGERS 34 AND 35 LT UNDER THE L-1 DOOR AREA IAW FED EX EA6-5310-121277 AND A310-200 SRM 53-10-12 FIG 224 SHEET 3. THIS IS AN AIRBUS REPAIR AND IS A RESULT OF AGING AIRCRAFT INSPECTION.

Part: SKIN — MISREPAIRED (ZONE 600) · airframe 40,469 hrs · 20,271 cycles

PREVIOUS EXTERNAL BONDED REPAIR DOUBLER LOCATED ON RIGHT WING I/B FLAP TRAILING EDGE LOWER SKIN BETWEEN TRACK 1 TO RIB 10 AND AT THE AFT EDGE MEASURING 59 INCH BY 11.6 INCH. REPAIR NOT IAW EA6-5750-62865. REMOVED PREVIOUS REPAIR AND INSTALLED CORRECT REPAIR AT RT WING I/B FLAP TRAILING EDGE LOWER SKIN BETWEEN TRACK 1 TO RIB 10 AT THE AFT EDGE IAW FED EX EA6-5750-121270.

Part: SKIN — MISREPAIRED (ZONE 100) · airframe 40,469 hrs · 20,271 cycles

PREVIOUS EXTERNAL REPAIR DOUBLER LOCATED ON THE LEFT SIDE FUSELAGE NOSE SKIN BETWEEN FRAMES 1 TO 4 AND BETWEEN STRINGERS 28 TO 30 LT, AT AND ABOVE THE SKIN LAP SEAM, THE REPAIR DOUBLER MEASURES 12.2 INCHES BY 5.9 INCHES. REPAIR NOT IAW SRM REQUIREMENTS. REMOVED PREVIOUS REPAIR AND INSTALLED CORRECT REPAIR ON LEFT SIDE FUSELAGE NOSE SKIN BETWEEN FRAMES 1 TO 4 AND BETWEEN STRINGERS 28 TO 30 LT, AT AND ABOVE THE SKIN LAP SEAM, IAW FED EX EA 6-5310-121278. THIS IS AN AIRBUS REPAIR AND IS A RESULT OF AGING AIRCRAFT INSPECTION.

Part: MOUNT — CORRODED (ZONE 400) · corrosion level 2 · airframe 40,469 hrs · 20,271 cycles

NR 2 ENGINE FORWARD MOUNT SPIGOT HOLE CORRODED REMOVED LEVEL 1 CORROSION. ACCOMPLISHED BUSHING REPAIR ON NR 2 ENGINE FORWARD MOUNT SPIGOT HOLE PER FED EX EA6-5450-121268.

Part: SKIN — MISREPAIRED (ZONE 100) · airframe 40,469 hrs · 20,271 cycles

PREVIOUS EXTERNAL REPAIR DOUBLER LOCATED ON LEFT SIDE FUSELAGE SKIN BETWEEN FRAME 17 TO 18 AND BETWEEN STRINGERS 28 TO 31 LT AT FWD SIDE OF SKIN BUTT SEAM, THE REPAIR DOUBLER MEASURES 9.2 INCH BY 7.5 INCH. REPAIR NOT IAW DWG 912188 AND AIRBUS RAS AS.128/93 ISSUE B. REMOVED PREVIOUS REPAIR AND INSTALLED CORRECT REPAIR ON LEFT SIDE FUSELAGE SKIN BETWEEN FRAME 17 TO 18 AND BETWEEN STRINGERS 28 TO 31 LT AT FWD SIDE OF SKIN BUTT SEAM IAW FED EX EA6-5310-121274. THIS IS AN AIRBUS REPAIR AND IS A RESULT OF AGING AIRCRAFT INSPECTION.

Part: SKIN — MISREPAIRED (ZONE 100) · airframe 40,469 hrs · 20,271 cycles

PREVIOUS EXTERNAL REPAIR DOUBLER LOCATED ON LEFT SIDE FUSELAGE BETWEEN FRAME 17 TO 18 AND BETWEEN STRINGERS 33 TO 36 LT AT FWD SIDE OF SKIN BUTTSEAM, THE REPAIR MEASURES 7.8" BY 7". REPAIR NOT IAW SRM AND DWG 922269 REQUIREMENTS. REMOVED PREVIOUS REPAIR AND INSTALLED CORRECT REPAIR DOUBLER ON LT SIDE FUSELAGE BETWEEN FRAME 17 TO 18 AND STRINGERS 33 TO 36 IAW A310-200 SRM 53-10-12 FIG 216 SHEETS 1 AND 2. THIS IS AN AIRBUS REPAIR AND IS A RESULT OF AGING AIRCRAFT INSPECTION.

Part: SKIN — MISREPAIRED (TE FLAP) · airframe 40,469 hrs · 20,271 cycles

PREVIOUS EXTERNAL REPAIR DOUBLER LOCATED ON RT WING O/B FLAP UPPER MAIN SKIN UNDER RUBSTRIP BETWEEN FLAP TRACK NR 4 TO RIB 7 AND 10 INCH FWD OF REAR SPAR MEASURING 4.7 INCH BY 5.9 INCH. REPAIR NOT IAW SRM REQUIREMENTS. REMOVED PREVIOUS REPAIR AND INSTALLED CORRECT REPAIR ON RT WING O/B FLAP UPPER MAIN SKIN UNDER RUBSTRIP BETWEEN FLAP TRACK NR 4 TO RIB 7 AND 10 INCH FWD OF REAR SPAR IAW A310-200 SRM 57-53-12 FIG 210. THIS IS AN AIRBUS REPAIR AND IS A RESULT OF AGING AIRCRAFT INSPECTION.

Part: SEAT TRACK — GOUGED (ZONE 200) · airframe 40,469 hrs · 20,271 cycles

MAIN DECK CARGO SEAT TRACK NR 6LT BETWEEN FR 21 AND FR 22 HAS 1 GOUGE ON SCALLOP, .25 IN DIA BY .020 IN DEEP REMOVED DAMAGED SECTION AND INSTALLED SEAT TRACK SPLICE REPAIR AT SEAT TRACK NR 6. LT BETWEEN FR 21 AND FR 22 IAW A310-200 SRM 53-10-16, FIG 208, SHT 2

Part: SKIN — MISREPAIRED (ZONE 600) · airframe 40,469 hrs · 20,271 cycles

PREVIOUS EXTERNAL REPAIR DOUBLER LOCATED ON RT WING O/B FLAP UPPER MAIN SKIN UNDER RUB STRIP BETWEEN RIB NR 6 AND RIB NR 7 AND 2.6 IN FWD OF REAR SPAR MEASURING 4.0 IN BY 4.0 IN REPAIR NOT IAW SRM REQUIREMENTS. REMOVED PREVIOUS REPAIR AND INSTALLED OUTER SKIN REPAIR ON RT WING OUTBD FLAP UPPER SKIN BETWEEN RIB NR 6 AND RIB NR 7 IAW A310-200 SRM 57-53-12, FIG 210.

Part: SKIN — MISREPAIRED (ZONE 600) · airframe 40,469 hrs · 20,271 cycles

PREVIOUS EXTERNAL REPAIR DOUBLER LOCATED ON RT WING OUTBD FLAP LOWER SKIN AFT OF FWD SPAR BETWEEN RIB NR 3 AND RIB NR 4, MEASURING 6.9 IN BY 8.6 IN REPAIR NOT IAW SRM REQUIREMENTS. REMOVED PREVIOUS REPAIR AND INSTALLED OUTER SKIN REPAIR ON RT WING OUTBD FLAP LOWER SKIN BETWEEN RIB NR 3 AND RIB NR 4 IAW A310-200 SRM 57-53-12,FIG 210. THIS IS AN AIRBUS REPAIR AND IS A RESULT OF AGING AIRCRAFT INSPECTION.

Part: SKIN — MISREPAIRED (ZONE 500) · airframe 40,469 hrs · 20,271 cycles

PREVIOUS EXTERNAL REPAIR DOUBLER LOCATED ON LT WING OUTBD FLAP UPPER MAIN SKIN UNDER RUB STRIP BETWEEN RIB NR 6 AND RIB NR 7, MEASURING 3.9 IN BY 4.1 IN REPAIR NOT IAW SRM REQUIREMENTS. REMOVED PREVIOUS REPAIR AND INSTALLED CORRECT OUTER SKIN REPAIR ON RT WING OUTBD FLAP UPPER SKIN BETWEEN RIB NR 6 AND RIB NR 7 IAW A310-200 SRM 57-53-10, FIG 210. THIS IS AN AIRBUS REPAIR AND IS A RESULT OF AGING AIRCRAFT INSPECTION.

Part: SKIN — MISREPAIRED (ZONE 500) · airframe 40,469 hrs · 20,271 cycles

PREVIOUS EXTERNAL REPAIR DOUBLER LOCATED ON LEFT WING OUTBOARD FLAP UPPER MAIN SKIN UNDER RUB STRIP BETWEEN RIB NR 3 AND NR 4, MEASURING 3.9 IN BY 13.8 IN REPAIR NOT IAW SRM REQUIREMENTS. REMOVED PREVIOUS REPAIR AND INSTALLED CORRECT OUTER SKIN REPAIR ON LT WING OUTBD FLAP UPPER SKIN IAW A310-200 SRM 57-53-12, FIG 210, BETWEEN RIB NR 3 AND RIB NR 4. THIS IS AN AIRBUS REPAIR AND IS A RESULT OF AGING AIRCRAFT INSPECTION.

Part: SKIN — MISREPAIRED (ZONE 500) · airframe 40,469 hrs · 20,271 cycles

PREVIOUS EXTERNAL REPAIR DOUBLER LOCATED ON LEFT WING OUTBOARD FLAP UPPER MAIN RUB STRIP BETWEEN RIB 4 AND RIB 5, MEASURING 6.9 IN BY 13.0 IN REPAIR NOT IAW SRM REQUIREMENTS. REMOVED PREVIOUS REPAIR AND INSTALLED CORRECT OUTER SKIN REPAIR ON LT WING OUTBD FLAP UPPER RUB STRIP IAW A310-200 SRM 57-53-12, FIG 210, BETWEEN RIB NR 4 AND RIB NR 5. THIS IS AN AIRBUS REPAIR AND IS A RESULT OF AGING AIRCRAFT INSPECTION.

Part: SKIN — MISREPAIRED (ZONE 600) · airframe 40,469 hrs · 20,271 cycles

PREVIOUS EXTERNAL REPAIR DOUBLER LOCATED ON RT WING OUTBD FLAP UPPER MAIN SKIN UNDER RUB STRIP BETWEEN RIB 10 AND RIB 11 AND 1.1 IN FWD OF REAR SPAR MEASURING 4.8 INCH BY 10.5 INCH REPAIR NOT IAW SRM REQUIREMENTS. REMOVED PREVIOUS REPAIR AND INSTALLED CORRECT OUTER SKIN REPAIR ON RT WING OUTBD FLAP UPPER SKIN BETWEEN RIB NR 10 AND RIB NR 11 IAW A310-200 SRM 57-53-10, FIG 210. THIS IS AN AIRBUS REPAIR AND IS A RESULT OF AGING AIRCRAFT INSPECTION.

Part: SKIN — MISREPAIRED (ZONE 500) · airframe 40,469 hrs · 20,271 cycles

PREVIOUS EXTERNAL REPAIR DOUBLER LOCATED ON LT WING OUTBD FLAP UPPER MAIN SKIN UNDER RUB STRIP BETWEEN RIB NR 2 AND RIB NR 3, MEASURING 4.0 IN BY 4.7 IN REPAIR NOT IAW SRM REQUIREMENTS. REMOVED PREVIOUS REPAIR AND INSTALLED CORRECT OUTER SKIN REPAIR ON RT WING OUTBD FLAP UPPER SKIN BETWEEN RIB NR 2 AND RIB NR 3 IAW A310-200 SRM 57-53-10, FIG 210. THIS IS AN AIRBUS REPAIR AND IS A RESULT OF AGING AIRCRAFT INSPECTION.

Part: SKIN — MISREPAIRED (TE FLAP) · airframe 40,469 hrs · 20,271 cycles

PREVIOUS EXTERNAL REPAIR DOUBLER LOCATED ON RT WING OUTBD FLAP UPPER SKIN UNDER RUB STRIP BETWEEN RIB NR 3 AND RIB NR 4 AND 3.6 IN FWD OF REAR SPAR MEASURING 4.4 IN BY 14.2 IN REPAIR NOT IAW SRM REQUIREMENTS. REMOVED PREVIOUS REPAIR AND INSTALLED CORRECT OUTER SKIN REPAIR ON RT WING OUTBD FLAP UPPER SKIN BETWEEN RIB NR 3 AND RIB NR 4 IAW A310-200 SRM 57-53-10, FIG 210. THIS IS AN AIRBUS REPAIR AND IS A RESULT OF AGING AIRCRAFT INSPECTION.

Part: RUB STRIP — FAILED (ZONE 600) · airframe 40,469 hrs · 20,271 cycles

PREVIOUS EXTERNAL REPAIR DOUBLER LOCATED ON RT WING OUTBD FLAP MAIN SKIN UNDER RUB STRIP BETWEEN RIB NR 2 AND RIB NR 3, 4.4 IN FWD OF REAR SPAR MEASURING 13 IN BY 11.8 IN REPAIR NOT IAW SRM REQUIREMENTS. REMOVED PREVIOUS REPAIR AND INSTALLED CORRECT OUTER SKIN REPAIR ON RT WING OUTBD FLAP UPPER SKIN BETWEEN RIB NR 2 AND RIB NR 3 IAW A310-200 SRM 57-53-10, FIG 210. THIS IS AN AIRBUS REPAIR AND IS A RESULT OF AGING AIRCRAFT INSPECTION.

Part: SKIN — MISREPAIRED (TE FLAP) · airframe 40,469 hrs · 20,271 cycles

PREVIOUS EXTERNAL REPAIR DOUBLER LOCATED ON RT WING OUTBD FLAP UPPER MAIN SKIN UNDER RUB STRIP BETWEEN RIB NR 2 AND RIB NR 3 AND 9.6 IN FWD OF REAR SPAR MEASURING 7.5 IN BY 7.1 IN REPAIR NOT IAW SRM REQUIREMENTS. REMOVED PREVIOUS REPAIR AND INSTALLED CORRECT OUTER SKIN REPAIR ON RT WING OUTBD FLAP UPPER SKIN BETWEEN RIB NR 2 AND RIB NR 3 IAW A310-200 SRM 57-53-10, FIG 210. THIS IS AN AIRBUS REPAIR AND IS A RESULT OF AGING AIRCRAFT INSPECTION.

Part: SKIN — MISREPAIRED (ZONE 500) · airframe 40,469 hrs · 20,271 cycles

PREVIOUS EXTERNAL REPAIR DOUBLER LOCATED ON LT WING OUTBD FLAP UPPER SKIN UNDER RUB STRIP BETWEEN RIB NR 3 AND RIB NR 4, MEASURING 4.1 IN BY 11.9 IN REPAIR NOT IAW SRM REQUIREMENTS. REMOVED PREVIOUS REPAIR AND INSTALLED CORRECT OUTER SKIN REPAIR ON RT WING OUTBD FLAP UPPER SKIN BETWEEN RIB NR 3 AND RIB NR 4 IAW A310-200 SRM 57-53-10, FIG 210. THIS IS AN AIRBUS REPAIR AND IS A RESULT OF AGING AIRCRAFT INSPECTION.

Part: STRINGER — FAILED (ZONE 100) · airframe 40,469 hrs · 20,271 cycles

PREVIOUS STRINGER REPAIR LOCATED IN AFT CABIN UNDER FLOOR BEHIND BULK CARGO ON STRINGER 41 RT BETWEEN FR 72 TO FR 73, HAS 1 EA REPAIR L-ANGLE MEASURING 9.9 INCHES LONG AND 1 REPAIR SECTION MEASURING 10.3 INCHES LONG REPAIR NOT IAW SRM REQUIREMENTS. REMOVED PREVIOUS REPAIR AND INSTALLED CORRECT STRINGER SPLICE REPAIR AT STRINGER 41 RT BETWEEN FR 72 AND FR 73 IAW A310 -200 SRM 53-10-14, FIG 201. THIS IS AN AIRBUS REPAIR WITH AND IS A RESULT OF AGING AIRCRAFT INSPECTION.

Part: SEAT TRACK — CORRODED (ZONE 200) · airframe 40,469 hrs · 20,271 cycles

MAIN DECK CARGO FLOOR SEAT TRACK NR 5 LT HAS CORROSION, BETWEEN FR 16 TO FR 17, 10 SQ INCHES REMOVED LEVEL 1 CORROSION. REMOVED AND REPLACED SEAT TRACK SECTION AT TRACK NR 5 LT BETWEEN FR 16 AND FR 17 IAW A310-200 SRM 53-12-16, FIG 1, PG 4C.

Part: SEAT TRACK — DAMAGED (ZONE 200) · airframe 40,469 hrs · 20,271 cycles

MAIN CARGO DECK SEAT TRACK NR 3 RT HAS BROKEN SCALLOPS AT FR 54.2 REMOVED DAMAGED SECTION AND INSTALLED REPAIR ON NR 3 RT SEAT TRACK BETWEEN FR 54.2 AND FR 55 IAW A310-200 SRM 53-10-16, FIG 202, PAGE 209/210.

Part: OUTFLOW VALVE — MALFUNCTIONED (CABIN PRESSURE) · airframe 39,883 hrs · 19,911 cycles

AFTER T/O REC'D MASTER CAUTION LIGHT W/LEFT ECAM WARNING CABIN PRESS MAN PRESS VALVE NOT CLOSED. REC'D RIGHT CORRESPONDING ECAM PAGE. REPEAT WRITE UP MANUAL VALVE WOULD NOT CLOSE. NR 1 CABIN PRESS, MEL 21-31-04-02-A, A/C TO MEM UNPRESS FLT. MEM REMOVED AND REPLACED SWITCHES 129 AND140 HM ON 432 VU PANEL. A/C FAILED TEST FLT, MEM-/08. REMOVED AND REPLACED OUTFLOW VALVES. TEST FLT FAILED MEM/09. R&R OUTFLOW VALVES. TEST FLT FAILED MEM/09. (WIRE 2131-6301-CF22) HAS A HIGH MEG OHM TO GRD BETWEEN 39HM-A AND 817VC REF A310 AWM 21-31-07.-REPLACED WIRE FROM PLUG 39HM TO DISCONNECT 817VC. R & R'D THE FOLLOWING RELAYS: 208HM,133HM & 131HM& 139HM . TEST FLIGHT ACCOMPLISHED PER MOCC REQUEST. 2 GOOD LEGS

Part: RELAY — MALFUNCTIONED · airframe 39,883 hrs · 19,911 cycles

AFTER T/O REC'D MASTER CAUTION LIGHT W/LEFT ECAM WARNING CABIN PRESS MAN PRESS VALVE NOT CLOSED. REC'D RIGHT CORRESPONDING ECAM PAGE. REPEAT WRITE UP MANUAL VALVE WOULD NOT CLOSE. R & R 208HM,133HM, AND 131HM. RELAY139HM, REINSTALLED NR 1 & 2 CPC'S. OPS CHECK OF NR 1 AND 2 CPC'S OPS CHECKS NORMAL.

Part: ODOR — DETECTED (COCKPIT) · airframe 38,658 hrs · 19,299 cycles

REJECTED TAKEOFF KMEM RWY 18L AT 100 KIAS DUE TO HEAVY ACRID SMELL IN COCKPIT. NO SMOKE WARNINGS OR FIRE WARNINGS. RAN BOTH ENGINES, OPERATED PACKS AND PRESSURIZED ACFT. NO NOTICEABLE FUMES NOTED. ENGINE RUN IAW A310 JRH CHAPTER 5. COURIER AREA FLOOR JUST RESEALED AT B-CHECK SUSPECT CREW ENCOUNTERED FRESH SEALANT. A/C HAS NO ABNORMAL ODORS.

Part: ISOLATION VALVE — MALFUNCTIONED (A/C SYSTEM) · airframe 35,598 hrs · 17,631 cycles

ON DEPARTURE OUT OF MEM AT 3,000 VERY STRONG ODOR IN COCKPIT / TURNED BACK TO MEM. ON DESCENT TO 3,000 ODOR CAME BACK. AVIONICS FLOW LIGHT CAME ON DURING DEPT. FOLLOWED ECAM SELECTED, OVERBOARD. REMOVED AND REPLACED ISOLATION VALVE PER AIR BUS MM 21-23-12-4. OPS CHECK GOOD. R/I FROM FACT PREMATURE REMOVAL/INSTALLATION OFF MFG B38QA6505, POS P2 SRL 2014, TAG 999062 ON MFG B38QA6505 SRL 102, TAG 265720.

Part: FILLET — TORN (NR 2 ENG T/R) · airframe 34,627 hrs · 17,136 cycles

NR 2 ENG I/B THRUST REVERSER CORE UPPER AFT FILLET PANEL TORN. R/R FILLET PANEL PER IAW SRM 51-40- 2.

Part: PANEL — DELAMINATED (THRUST REVERSER) · airframe 34,627 hrs · 17,136 cycles

NR 1 ENGINE O/B T/R TRANSLATING COWL, LWR AFT LINER DELAMINATED. REMOVED AND REPLACED NR 2 ENGINE T/R TRANS COWL IAW MM 78-32-11-4-B.

Part: BRUSH HOLDER — DETACHED (RT WING AILERON) · airframe 34,627 hrs · 17,136 cycles

N 517 RT WING ALL SPEED AILERON LWR BRUSH ASSY HAS BECOME DETACHED FROM STRUCTURE. REMOVED AND REPLACED BRUSH ASSY. IAW/SRM 51-40-21 PG.7 UNDER W/O NO. 13350 FEDEX 04/04/2003.

Part: RIB — DAMAGED (NR 1 PYLON) · airframe 34,627 hrs · 17,136 cycles

NR 1 ENG PYLON HYD CASE DRAIN LINE HAS ELONGATED HOLE THRU FRAME AT RIB 20 AND HAS CHAFED THRU ADJACENT ANGLE. R & R STRAP, RIB AND DOUBLER PER IAW SRM 51-40-21

Part: RIB — DAMAGED (RT SLAT NR 2) · airframe 34,627 hrs · 17,136 cycles

COMPLY WITH EA 6-5740-68775 WINGS-RT SLAT NR 2-LEADING EDGE DAMAGE REPAIR BETWEEN RIB 2 AND RIB 3 UNDER W/O NR 13350 FEDEX N/R NR S00005. *S/D* COMPLIED WITH EA 6-5740-68775 WINGS-RT SLAT NR 2 LEADING EDGE DAMAGE REPAIR BETWEEN RIB 2 AND RIB 3.

Part: PANEL — DELAMINATED (VERTICAL STAB) · airframe 34,627 hrs · 17,136 cycles

VERTICAL STAB. LE PANEL 321AL DELAMINATED

Part: PANEL — CRACKED (NR 2 NACELLE) · airframe 34,627 hrs · 17,136 cycles

NR 2 ENG I/B TRANSLATING COWL UPPER T- TRACK SLIDER CRACKED OFF. INSTALLED NEW UPPER SLIDER WITH NEW TRANSLATING SLEEVE W/C NOO193

Part: PANEL — PEELING (THRUST REVERSER) · airframe 34,627 hrs · 17,136 cycles

NR 1 ENGINE OUTBOARD THRUST REVERSER TRANSLATING PANEL UPPER SLIDER TEFLON PEELING UP, AND SLIDER DAMAGED.

Part: RIB — CRACKED (HORIZONTAL STAB) · airframe 34,627 hrs · 17,136 cycles

LT HORIZONTAL STAB. INTERIOR RIB 5 UPPER CHORD AT REAR SPAR IS CRACKED AT HOISTING POINT WRITTEN ON FEDEX N/R N00494 UNDER MAE W/O NR 13350 CUT OUT DAMAGED SECTION IAW/SRM 51-71-50 FABRICATED REPAIR ANGLE OF 7075T6 BATCH NR 7R00115001 IAW/SRM 51-71-50 INSTALLED REPAIR ANGLE IAW/SRM 51-40-21. COMPLETED UNDER MAE W/O NR 13350 ON FEDEX NR. N00494.

Part: SPAR CAP — CORRODED (HORIZONTAL STAB) · airframe 34,627 hrs · 17,136 cycles

LT HORIZONTAL UPPER AFT SPAR CAP CORRODED APPROX. 4FT. FROM FUSELAGE. UNDER MAE W/O NO. 13350. REPAIRED AFT SPAR CAP IAW SRM 55-13-11 AND SRM 51-41-01.

Part: PITOT LINE — OBSTRUCTED (PITOT/STATIC SYS) · airframe 33,737 hrs · 16,671 cycles

MDIS- FIRST OFFICERS AIRSPEED IND INOP ON ELECTRONIC FLT INSTRUMENT SYSTEM. DISCONNECTED FIRST OFFICERS PITOT CONNECTION FOUND BLOCKAGE, CLEANED PITOT LINE AND RECONNECTED. BLEW PITOT NR 2 SYSTEM AIR LINES OUT AND RECONNECTED PITOT LINES. OPS CHECK GOOD.

Part: WARNING SYSTEM — ACTIVATED (NR 2 ENGINE) · airframe 31,525 hrs · 15,422 cycles

00-118 DURING CLIMB, NR 2 ENG NACELLE TEMP ADVISORY ACTIVATED, FOLLOWED ADVISORY PROCEDURES. BROUGHT POWER BACK TO IDLE.

Part: OUTFLOW VALVE — MALFUNCTIONED (FUSELAGE)

00-85 - COULD NOT CONTROL PRESSURIZATION WITH EITHER AUTO CONTROLLER OR IN MANUAL. RAN OUTFLOW VALVES, BOTH WORKED NORMALLY MM REF 21-31-00502. FOUND NR 2 OUTFLOW STUCK OPEN. RESET CK NORMAL.

Part: ACTUATOR — MALFUNCTIONED (TE FLAPS)

FLAPS WOULD NOT FULLY RETRACT AFT T/O. BOTH FLAPS FAULT LIGHTS ILLUM. FLAPS EXTENDED NORM FOR LAND AND RETRACT FULLY AFT LANDING. *S/D* REMOVED AND REPLACED NR 1 JACKSCREW PER A310MM 27-54-21, OPS OK.

Part: ACTUATOR — FAILED (TE FLAPS)

FLAPS STUCK AT APPROX 2 DEG WITH THE FLAP SYS NR 1 AND NR 2 FLAP FAULT LIGHTS ILLUM ON O/H PAN'L AND ECAM MSG NR 1 AND NR 2 FLAP FAULT. *S/D* REMOVED AND REPLACED NR 1 AND NR 2 SFCC'S, FLAPS HANDLE CSU, AND NR 4 LEFT FLAP JACKSCREW. OPS CHECK OK.

Part: OUTFLOW VALVE — FAILED (CABIN)

99-181 - AT BEG OF ALERT, CABIN PRESS WAS ABOUT 7.1 PSI CABIN RATE 200 FPM. GOT ECAM ALERT. REMOVED AND REPLACED NR 1 OUTFLOW VALVE AMM 21-31-12. OPS CK NORMAL. NOTE NR 2 SYS ON DEFFERAL, MEL 21-1. MACH ITEM 21-30 1817.

Part: CONNECTOR — BURNED (NR 2 ENGINE)

AFTER T/O ALL INSTR PWR BY NR 2 ENG GEN SYS START SPIKING, LIGHT FLICKER. NR 2 FUEL FLOW IND AND NR 2 N2 FLUCT. FUEL PUMPS FAIL. A/C DIVERTED TO ATL. MX FOUND BURNED PIN ON NR 2 ENG GEN FEEDER HARNESS CONNECTOR VC4955P. REPLACED THE NR 2 GEN LINE. MX FOUND ECAM FREQ IND INOP.