N450FE

Part: SKIN — DENTED (LT WING TE FLAP) · airframe 42,616 hrs · 30,501 cycles

LT INBD FLAPS T/E LOWER SURFACE HAS NUMEROUS DENTS. FOUND WITHIN LIMITS IAW SRM 57-52-12, FIG 101, DETAIL IV. TWO DENTS, PUNCTURED, REPAIRED DENTS IAW SRM 57-52-12 AND SRM 51-77-12, PARA 4B. MAJOR REPAIR.

Part: SUPPORT — CORRODED (RT MLG) · corrosion level 2 · airframe 42,616 hrs · 30,501 cycles

RIGHT MLG RIB 5, FWD LUG LOWER SURFACE IS CORRODED. RT MLG RIB 5 FWD LUG CORROSION. R & R IAW REPAIR DWG R57249389, REV B IAW EA 6-5710-T0302172, PART 1. REPAIR CLASSIFIED AS MAJOR.

Part: LUG — CORRODED (MLG) · corrosion level 2 · airframe 42,616 hrs · 30,501 cycles

LEFT MLG RIB 5 FWD LUG LOWER SURFACE IS CORRODED. R & R IAW REPAIR DWG R57249389, REV B IAW EA 6-5710-T0302173. REPAIR CLASSIFIED AS MAJOR.

Part: SKIN — CORRODED (LT WING TE FLAP) · corrosion level 2 · airframe 42,616 hrs · 30,501 cycles

LEFT OTBD FLAPS T/E LOWER SURFACE HAS CORROSION LOCATED 22 INCHES INBD OF NR 5 FLAP TRACK. PERFORMED REPAIR IAW SRM 57-53-12, FIG 209. REPAIR CLASSIFIED AS MAJOR.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 42,616 hrs · 30,501 cycles

FOUND DAMAGE TO SKIN AT FRAME 87 BETWEEN STRINGERS 25-30R, REPAIRED IAW EA 6-5330-T0302997, PART 1. REPAIR CLASSIFIED AS MINOR.

Part: SKIN — DAMAGED (RT WING TE FLAP) · airframe 42,616 hrs · 30,501 cycles

RIGHT WING INBD TE FLAPS LOWER SURFACE HAS IMPACT DAMAGE. REPAIRED IAW SRM 57-52-12, PARA 4.D, FIG 204. REPAIR CLASSIFIED AS MAJOR.

Part: SKIN — CORRODED (LT ELEVATOR) · corrosion level 2 · airframe 42,616 hrs · 30,501 cycles

LEFT ELEVATOR LOWER SKIN HAS A SPOT OF CORROSION LOCATION 5 INCHES FROM T/E, 15 INCHES FROM TIP. PERFORMED REPAIR ON LT ELEVATOR SKIN IAW SRM 55-21-11, FIG 209. REPAIR CLASSIFIED AS MAJOR.

Part: SKIN — CRACKED (RT WING) · airframe 42,616 hrs · 30,501 cycles

RT WING, RIB 9 LOWER SKIN FWD EDGE CRACKED. REPAIRED SKIN IAW DWG R572-57208 & EA 6-5710-T0302280. REPAIR CLASSIFIED AS MAJOR.

Part: MOUNT — CORRODED (ENGINE) · corrosion level 2 · airframe 42,616 hrs · 30,501 cycles

TWO FWD ENGINE MOUNTS HAVE PITTING CORROSION IN BOTH FWD MOUNT HOLES AND THE AFT OTBD MOUNT HOLE. PERFORMED REPAIR IAW SRM 54-51-18 WITH FABRICATED BUSHINGS.

Part: ANGLE — BENT (FUSELAGE) · airframe 42,616 hrs · 30,501 cycles

THS BAY WEB UPPER ANGLE BENT LOCATION, STRINGER 32R, BETWEEN FRAMES 86 & 87. REPLACED WEB UPPER ANGLE IAW SRM 53-19-18.

Part: STRINGER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 42,616 hrs · 30,501 cycles

STRINGER 44R FWD OF FRAME 17 HAS CORROSION AROUND RIVET. REPAIRED STRINGER IAW SRM 53-12-14. REPAIR CLASSIFIED AS MAJOR.

Part: ANGLE — BENT (FUSELAGE) · airframe 42,616 hrs · 30,501 cycles

AFT FUSELAGE THS BAY WEB AT FRAMES 89 & 84 UPPER ANGLE BENT STRINGER 32L. REPLACED WEB UPPER ANGLE IAW SRM 51-40-21. F

Part: SKIN — DENTED (RT AILERON) · airframe 42,616 hrs · 30,501 cycles

RIGHT WING ALL SPEED AILERON BOTTOM SKIN HAS DENT LOCATION 27.5 IN FROM INBD, 17IN FROM FWD END. REPAIRED IAW SRM 57-61-12, PB 201, PARAGRAPH 4.A. REPAIR CLASSIFIED AS MAJOR.

Part: MOUNT — CORRODED (NR 2 ENGINE) · airframe 42,616 hrs · 30,501 cycles

NR 2 PYLON AFT ENGINE MOUNT HAS CORROSION ON FWD & AFT SIDES OF MOUNT, ON INBD AND OTBD, HORIZONTALLY POSITIONED BOLTS, RECESSED AREAS. REPAIRED IAW EA 6-5451-T0302401 PART 1. REPAIR CLASSIFIED AS MINOR.

Part: SEAT TRACK — DAMAGED (ZONE 200) · airframe 42,616 hrs · 30,501 cycles

SEAT TRACK DAMAGED AT FRAME 40-42, -Y1959 REPAIRED IAW SRM 53-10-16, PARA 5, FIG 203, SH 5, FABRICATED & INSTALLED SEAT TRACK IAW SRM 51-27-11 & SRM 51-40-21. REPAIR CLASSIFIED AS MAJOR.

Part: WEB — CRACKED (ZONE 300) · airframe 42,616 hrs · 30,501 cycles

FOUND WEB BETWEEN FRAMES 86 - 87 STRINGER 35R CRACKED. R & R WEB IAW SRM 51-40-21. REPAIR CLASSIFIED AS MINOR.

Part: SKIN — DAMAGED (ZONE 100) · airframe 42,616 hrs · 30,501 cycles

ACCESS DOOR 136AR EXTERNAL SKIN CUTOUT RADIUS IS OUT OF TOLERANCE. REPLACED ACCESS DOOR 136AR SKIN IAW SRM 52-41-15 & DWG 14A52475000.

Part: PROFILE — CHAFED (ZONE 100) · airframe 42,616 hrs · 30,501 cycles

AFT CABIN PROFILE TEE, FRAME 80, STR 34L, WEB CHORD CHAFED. REPLACED DAMAGED PROFILE TEE IAW SRM 51-40-21.

Part: TEE FITTING — CHAFED (ZONE 300) · airframe 42,616 hrs · 30,501 cycles

AFT CABIN FRAME 80, S34R WEB ANGLE CHAFED REPLACED DAMAGED PROFILE TEE WITH FABRICATED PROFILE TEE AT FRAME 80, STR 34R IAW SRM 51-40-21. PROFILE FABRICATED IAW SRM 53-18-18.

Part: FLOORBOARD — DAMAGED (ZONE 200) · airframe 42,616 hrs · 30,501 cycles

FWD CABIN FLOORBOARD 222DF EDGE HAS HONEYCOMB CHIPPED OFF, FABRICATED FLOORBOARD IAW SRZ-25-005 AND INSTALLED. REPAIR CLASSIFIED AS MAJOR.

Part: FLOORBOARD — DELAMINATED (ZONE 200) · airframe 42,616 hrs · 30,501 cycles

FWD MAIN DECK CARGO UTILITY AREA LAVATORY FLOORBOARD, MULTIPLE AREAS HAS DAMAGED AND DELAMINATION. FABRICATED FLOORBOARD IAW SRZ-25-005. AND INSTALLED. REPAIR CLASSIFIED AS MAJOR.

Part: SKIN — DENTED (FUSELAGE) · airframe 42,616 hrs · 30,501 cycles

LOWER FUSELAGE SKIN, FRAME 19- 20, STR 34 -35R DENTED. REPAIRED IAW SRM 53-10-12 FIG 226 (SHEET 2). REPAIR CLASSIFIED AS MAJOR.

Part: FLOORBOARD — CRACKED (ZONE 200) · airframe 42,616 hrs · 30,501 cycles

FLOORBOARD 231BG HAS A CRACK. REPLACED FLOORBOARD. FLOORBOARD FABRICATED ON TRAVELER T13/1025840 IAW DWG SRZ-25-005 & INSTALLED ON WC 230-SWC-FIT.

Part: FLOOR PANEL — CRACKED (ZONE 200) · airframe 42,616 hrs · 30,501 cycles

MAIN DECK CARGO FRAMES 60-62, BETWEEN Y953 AND Y1456 FLOOR PANEL 251UF CRACKED. REPLACED PANEL. PANEL FABRICATED IAW DWG SRZ-25-005.

Part: FLOORBOARD — DAMAGED (ZONE 200) · airframe 42,616 hrs · 30,501 cycles

FLOORBOARD 231ZF HAS DAMAGE IN SEVERAL AREAS. FABRICATED & REPLACED FLOORBOARD.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 42,616 hrs · 30,501 cycles

DURING ACCOMPLISHMENT OF STRINGER REPAIR AT FR 72 2 EA HOLES HAVE EXCESSIVE PITCH AT STRINGER 41R. ACCOMPLISHED CATEGORY B SKIN REPAIR AT FR 72 STR 41R IAW SRM 53-10-12, FIG 225SH. REPAIR CLASSIFIED AS MAJOR.

Part: FLOORBOARD — DAMAGED (ZONE 200) · airframe 42,616 hrs · 30,501 cycles

FWD CABIN FLOORBOARD 221AF, EDGE HAS HONEYCOMB PIECE CHIPPED OFF/CRACKED. REPLACED FLOORBOARD. REPAIR CLASSIFIED AS A MAJOR.

Part: FLOOR PANEL — DAMAGED (ZONE 200) · airframe 42,616 hrs · 30,501 cycles

MAIN DECK CARGO FLOOR PANEL 242JK BROKEN. FLOOR PANEL FABRICATED AND INSTALLED. REPAIR CLASSIFIED AS MAJOR.

Part: SKIN — DENTED (RT AILERON) · airframe 42,616 hrs · 30,501 cycles

RT WING ALL SPEED AILERON BOTTOM SKIN HAS DENT LOCATION 3 INCHES FROM INBD, 24 INCHES FROM T/E. REPAIRED IAW SRM 57-61-12, FIG 201, PAGE 204. REPAIR CLASSIFIED AS MAJOR.

Part: FLOOR PANEL — DAMAGED (ZONE 100) · airframe 42,616 hrs · 30,501 cycles

FLOOR PANEL 162HF, METALLIC COVER PEELED, REPLACED FLOOR PANEL. FABRICATED NEW FLOOR PANEL. INSTALLED FLOOR PANEL ON WC 160-FL-FIT. REPAIR CLASSIFIED AS MAJOR.

Part: FLOOR PANEL — GOUGED (ZONE 200) · airframe 42,616 hrs · 30,501 cycles

MAIN DECK FLOOR PANEL 222JF PUNCTURED, LOWER SIDE. FLOOR PANEL FABRICATED AND INSTALLED. REPAIR CLASSIFIED AS MAJOR.

Part: FLOOR PANEL — DAMAGED (ZONE 100) · airframe 42,616 hrs · 30,501 cycles

FLOOR PANEL 143CF LOWER EDGE COMPOSITE BROKEN. REPLACED FLOOR PANEL 143CF. FLOOR PANEL FABRICATED AND INSTALLED ON WC 130-FL-FIT. REPAIR CLASSIFIED AS MAJOR.

Part: FLOOR PANEL — DAMAGED (ZONE 100) · airframe 42,616 hrs · 30,501 cycles

FLOOR PANEL 147AF, UPPER SURFACE HAS COMPOSITE EXPOSED. REPLACED FLOOR PANEL. FLOOR PANEL FABRICATED. INSTALLED ON WC 130-FL-FIT. REPAIR CLASSIFIED AS MAJOR.

Part: FLOOR PANEL — CRACKED (ZONE 200) · airframe 42,616 hrs · 30,501 cycles

CENTER MAIN DECK CARGO , RT SIDE FLOOR PANEL 242WH BOTTOM SURFACE HAS MULTIPLE PUNCTURED & CRACKED ON INBD EDGE. NEW FLOOR PANEL FABRICATED AND INSTALLED. REPAIR CLASSIFIED AS MAJOR.

Part: FLOOR PANEL — DELAMINATED (ZONE 200) · airframe 42,616 hrs · 30,501 cycles

MAIN DECK CARGO FLOOR PANEL BETWEEN FR 32-FR 33, Y450 AROUND HOLE DELAMINATED. FABRICATED NEW FLOOR PANEL IAW SRZ-25-005 AND INSTALLED IAW SRM 51-40-21.

Part: FLOOR PANEL — GOUGED (ZONE 200) · airframe 42,616 hrs · 30,501 cycles

MAIN CARGO, FRAME 65-69 BETWEEN SEAT TRACK Y450 AND Y953 FLOOR PANEL 251ZF, PUNCTURED. FABRICATED NEW FLOOR PANEL IAW SRZ-25-005 & INSTALLED IAW SRM 51-40-21.

Part: FLOOR PANEL — DAMAGED (ZONE 200) · airframe 42,616 hrs · 30,501 cycles

FLOOR PANEL 232YF DAMAGED. FABRICATED NEW FLOOR PANEL IAW SRZ-25-005.

Part: FLOOR PANEL — DAMAGED (MAIN CARGO) · airframe 42,616 hrs · 30,501 cycles

MAIN DECK CARGO FLOOR PANEL 232TF DAMAGED. FABRICATED NEW FLOOR PANEL IAW SRZ-25-005.

Part: FLOOR PANEL — DAMAGED (ZONE 200) · airframe 42,616 hrs · 30,501 cycles

AFT MAIN CARGO FLOOR PANEL FR 77-80/82 -Y1959 IS BROKEN ON AFT END. FABRICATED NEW FLOOR PANEL IAW SRZ-25-005.

Part: FLOOR PANEL — DAMAGED (ZONE 200) · airframe 42,616 hrs · 30,501 cycles

FLOOR PANEL 242TF PUNCTURED. FABRICATED NEW FLOOR PANEL IAW SRZ-25-005.

Part: FLOORBOARD — DAMAGED (ZONE 200) · airframe 42,616 hrs · 30,501 cycles

MAIN DECK CARGO FLOORBOARD 251MK DAMAGED. FABRICATED NEW FLOORBOARD.

Part: FLOORBOARD — DAMAGED (ZONE 200) · airframe 42,616 hrs · 30,501 cycles

MAIN CARGO DECK FLOORBOARD 231TF DAMAGED. FABRICATED NEW FLOORBOARD IAW SRZ-25-005.

Part: FLOOR PANEL — PUNCTURED (ZONE 200) · airframe 42,616 hrs · 30,501 cycles

FRAME 36-38.2, FLOOR PANEL 231 VF HAS MULTIPLE DENT AND PUNCTURED. FABRICATED NEW FLOOR PANEL IAW SRZ-25-005.

Part: FLOOR PANEL — DAMAGED (ZONE 200) · airframe 42,616 hrs · 30,501 cycles

FRAMES 54.2 - 54.3 BETWEEN SEAT TRACKS Y450 AND Y953 FLOOR PANEL 251GF DAMAGED. FABRICATED NEW FLOOR PANEL IAW SRZ-25-005.

Part: FLOOR PANEL — CRACKED (ZONE 200) · airframe 42,616 hrs · 30,501 cycles

FRAMES 60-62 BETWEEN SEAT TRACKS Y450 AND Y953, FLOOR PANEL 252SF CRACKED. FABRICATED FLOOR PANEL IAW SRZ 25-005.

Part: FLOOR PANEL — DAMAGED (ZONE 200) · airframe 42,616 hrs · 30,501 cycles

FRAMES 40/41-43, SEAT TRACK -Y450 AND -Y953, FLOOR PANEL DAMAGED. FABRICATED NEW FLOOR PANEL IAW SRZ 25-005.

Part: FLOOR PANEL — DAMAGED (ZONE 200) · airframe 42,616 hrs · 30,501 cycles

FRAME 46-51 BETWEEN SEAT TRACKS -Y450 AND -Y953 FLOOR PANEL DAMAGED AS MARKED, PANEL 242ZJ. FABRICATED NEW FLOOR PANEL IAW SRZ 25-005.

Part: FLOOR PANEL — DAMAGED (ZONE 200) · airframe 42,616 hrs · 30,501 cycles

FRAMES 60-62 BETWEEN SEAT TRACK Y450 AND Y953 FLOOR PANEL 251SF DAMAGED. FABRICATED NEW FLOOR PANEL IAW SRZ-25-005.

Part: FLOOR PANEL — CRACKED (ZONE 200) · airframe 42,616 hrs · 30,501 cycles

FLOOR PANEL CRACKED. FABRICATED NEW FLOOR PANEL IAW SRZ-25-005.

Part: FLOORBOARD — CRACKED (ZONE 200) · airframe 42,616 hrs · 30,501 cycles

FLOORBOARD 252UF CRACKED, FRAMES 60-62 BETWEEN SEAT TRACK -Y953 AND -Y1456. FABRICATED NEW FLOORBOARD IAW SRZ-25-005.

Part: FLOOR PANEL — DAMAGED (CABIN) · airframe 42,616 hrs · 30,501 cycles

FRAMES 43-46 BETWEEN SEAT TRACK -Y450 AND -Y953 FLOOR PANEL DAMAGED. FABRICATED NEW FLOOR PANEL IAW SRZ-25-005.

Part: FLOOR PANEL — DAMAGED (ZONE 200) · airframe 42,616 hrs · 30,501 cycles

FRAMES 60-62, BETWEEN SEAT TRACK Y953 AND Y1456 FLOOR PANEL 251RG PUNCTURED AND DAMAGED. FABRICATED NEW FLOOR PANEL IAW SRZ-25-005.

Part: SKIN — DENTED (ZONE 100) · airframe 42,616 hrs · 30,501 cycles

FUSELAGE EXTERNAL SKIN, LT SIDE, FR 79 TO 80, S48L-S49L SKIN HAS DENT OUT. DENT MEASURES A=.550" B=.400" T=.071" D=.030", FOUND TO BE OUT OF LIMITS IAW SRM 53-18-12, DIA 102. FABRICATED REPAIR DOUBLER IAW SRM 53-10-12, FIG 225 FROM 2024-T3.071C. INSTALLED REPAIR DOUBLER IAW SRM 53-10-12, FIG 225 & SRM 51-44-10. PAINTED DOUBLER IAW SRM 51-75-10. REPAIR CLASSIFIED AS MAJOR,

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 42,616 hrs · 30,501 cycles

AFT CABIN UNDEFLOOR COMPARTMENT FRAME 70-71, STRINGER 56L CORRODED. REPAIRED IAW SRM 53-10-14 FIG 201. CLASSIFIED AS A MAJOR REPAIR.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 42,616 hrs · 30,501 cycles

AFT CABIN UNDERFLOOR COMPARTMENT FRAME 72, STRINGER 41R CORRODED. REPAIRED IAW SRM 53-10-14 FIG 201. REPAIR CLASSIFIED AS MAJOR.

Part: STRUCTURE — CORRODED (ZONE 100) · corrosion level 2 · airframe 42,616 hrs · 30,501 cycles

AFT CABIN UNDERFLOOR COMPARTMENT BETWEEN FRAMES 74-75, S55R CORRODED. REPAIRED IAW SRM 53-10-14 FIG 201. REPAIR CLASSIFIED AS MAJOR.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 42,616 hrs · 30,501 cycles

AFT CABIN UNDERFLOOR COMPARTMENT FRAME 75 STRINGER 53R CORRODED. REPAIRED IAW SRM 53-10-14 FIG 201. REPAIR CLASSIFIED AS MAJOR.

Part: SKIN — CORRODED (FUSELAGE) · airframe 42,616 hrs · 30,501 cycles

AFT LOWER FUSELAGE EMPENNAGE AREA ZONE 313/314 HAS BULGING SKIN FR 94, 5 IN FROM COMPT DOOR UPPER CUT OUT. REPAIRED IAW SRM 53-19-12 FIG 201 PG'S 204-207.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 42,616 hrs · 30,501 cycles

FUSELAGE SKIN LEFT SIDE FRAME 69, 18 INCHES ABOVE S44L DAMAGED. REPAIRED IAW SRM 53-10-12, FIG 225. TREATED, PRIMED, AND PAINTED REPAIR PARTS IAW SRM 51-21-10 AND 51-75-10.

Part: SKIN — BULGED (FUSELAGE) · airframe 42,616 hrs · 30,501 cycles

LOWER FUSELAGE FRAME 20, STR 41 -42L HAS BULGED SKIN. REPAIRED IAW SRM 53-10-12, FIG 225. REPAIR CLASSIFIED AS MAJOR.

Part: SIGNAL COND UNIT — MALFUNCTIONED (OIL QTY) · airframe 41,514 hrs · 29,720 cycles

ON CLIMBOUT LOSS OF OIL PRESSURE NR 1 ENGINE ONLY OTHER ABNORMAL INDICATION WAS INCREASE IN NR 1 OIL QUANTITY TO FULL SCALE HIGH. FOLLOWED PROCEDURES SHUT ENGINE- DOWN AND RETURNED TO AIRPORT. TROUBLESHOT IAW ASM 79-30-00 SUSPECT OIL PRESSURE TRANSMITTER T583. R & R OIL PRESSURE TRANSMITTER IAW AMM 79-33-11-04, OPS CHECKED, FAILED, FOUND NR 1 ENGINE SIGNAL CONDITION BREAKER POPPED, R & R NR 1 ENGINE SIGNAL CONDITIONAL IAW AMM 79-33-31-04, ACCOMPLISHED AMM 72-00-00-06 NR 1 ENGINE GENERAL INSP STEP 11. OPS CHECKED GOOD AND NO FAULTS NOTED ON WINDMILL, ACFT OK FOR CONT SERVICE.

Part: DAMPER — UNDERSERVICED (RT MLG) · airframe 41,465 hrs · 29,683 cycles

ATB1 ON DEPARTURE, GEAR WOULD NOT RETRACT, HANDLE WOULD NOT GO ABOVE MIDDLE DETENTON EITHER SYS 1 OR 2. SERVICED RT LANDING GEAR PITCH DAMPER T0 1600 PSI IAW PRESS/ TEMP CONVERSION CHART. (OAT 10 DEGRESS). RESET RED POP-OUT BUTTON . ACFT OK FOR SERVICE. (FINAL CLOSED)

Part: DAMPER — MALFUNCTIONED (ZONE 700) · airframe 41,465 hrs · 29,683 cycles

AFTER TAKE OFF, GEAR WOULD NOT RETRACT WITH EITHER POSITION. DETECTION SYS HAD RED UNLOCK AND GREEN DOWN AND LOCKED INDICATIONS SIMULTANEOUSLY OTHER INDICATION SAME LAST FLIGHT. BITE CHECKED PROXIMITY BOX, NO FAULTS NOTED. REPLACED MLG BOGIE BEAM PITCH DAMPER IAW AMM 32-11-15-04-01.

Part: BATTERY — FAILED (EMERGENCY LIGHT) · airframe 40,916 hrs · 29,309 cycles

ON PRE DISPATCH CK, FOUND ON COURIER COMPARTMENT EMERGENCY LT TEST INOP. R & R EMERGENCY POWER SUPPLY BATTERY. MM 33-51-14-04-0. OPS CK GOOD. OK FOR SERVICE.

Part: SKIN — DAMAGED (RT ELEVATOR) · airframe 40,758 hrs · 29,188 cycles

RT ELEVATOR LOWER SKIN SURFACE PLUG IS MISSING. REMOVED FINISH; PREPPED AREA FOR REPAIR; LAYED UP; CURED & RESTORED FINISH IAW EA 2-5520-136738; "STABILIZERS - RT ELEVATOR LOWER SKIN OPEN HOLE REPAIR BETWEEN ER 27 AND ER 28 FWD OF REAR SPAR".

Part: FIREWALL — BENT (APU BAY) · airframe 40,758 hrs · 29,188 cycles

APU FIREWALL LOWER WEB IS BUCKLED; AS VIEWED FROM THE TAIL CONE AREA. REMOVED APU AFT FIREWALL LOWER WEB IAW SRM 51-40-21. INSTALLED NEW LOWER WEB IAW SRM 51-40-21 AND SRM 51-40-44.

Part: FLOOR PANEL — DAMAGED (CARGO BAY) · airframe 40,758 hrs · 29,188 cycles

FWD CARGO COMPARTMENT FLOOR PANEL 131 YF HAS MULTIPLE AREAS OF EDGE DAMAGE. FABRICATED NEW FLOOR PANEL 131 YF IAW DWG SRZ 25-005, REV "H".

Part: SKIN — DELAMINATED (LT ELEVATOR) · airframe 40,758 hrs · 29,188 cycles

LT ELEVATOR SKIN EXTERNAL SURFACE UPPER AND LOWER IS DELAMINATED. REMOVED DAMAGED SKIN AT NOTED LOCATION AND REPAIRED IAW SRM 55-21-11, PARA 5-I; FIG 209. SEALED REPAIR IAW SRM 55-21-11, PARA 5-I. PRIMED & TOPCIATED REPAIR IAW SRM 55-21-00, PARA 5-I.

Part: FLOOR SUPPORT — CORRODED (ZONE 100) · corrosion level 2 · airframe 40,758 hrs · 29,188 cycles

FWD CARGO PIT FLOORBOARD SUPPORT STRUCTURE IS CORRODED AND RIVETS ARE SHEARED AT FRAME 38.2; LBL 54. REMOVED CORROSION IAW SRM 51-74-10 AND FOUND TO BE OUT OF LIMITS IN REF TO AMM 53-17-11. ORIGINAL THICKNESS IS 0.0125. REMAINING THICKNESS 0.061. MATERIAL REMOVED 0.064 IN REF TO SRM 53-14-15. TOOL NR T82250. FABRICATED FILLER IN REF TO SRM 53-14-15. ALODINED FILLER IN REF TO SRM 51-21-10. PRIMED AND PAINTED FILLER IN REF TO SRM 51-23-10. INSTALLED FILLER IN REF TO SRM 51-40-02.

Part: FLOOR PANEL — DAMAGED (CARGO BAY) · airframe 40,758 hrs · 29,188 cycles

FWD CARGO COMPARTMENT FLOOR PANEL 132 RF HAS A DAMAGED CORNER. FABRICATED REPLACEMENT FLOORBOARD IAW DWG SRZ 25-005, REV "H".

Part: FLOORBOARD — CORRODED (CARGO BAY) · airframe 40,758 hrs · 29,188 cycles

BULK CARGO COMPARTMENT FLOORBOARD 161GF BOTTOM SKIN IS CORRODED IN MULTIPLE LOCATIONS AND IS PUNCTURED. FABRICATED NEW FLOORBOARD 161 GF IAW DWG SRZ 25-005, REV "H". APPLIED TOP SKIN IAW DWG SRZ 25-011, REV "C"

Part: FLOOR PANEL — DAMAGED (CARGO BAY) · airframe 40,758 hrs · 29,188 cycles

FWD CARGO COMPARTMENT FLOOR PANEL 131 RF HAS MULTIPLE AREAS OF DAMAGE ON THE BOTTOM SKIN. FABRICATED REPLACEMENT FLOORBOARD IAW DWG SRZ 25-008, REV "H".

Part: FLOOR PANEL — PUNCTURED (CARGO BAY) · airframe 40,758 hrs · 29,188 cycles

FWD CARGO COMPARTMENT FLOOR PANEL 132 RF BOTTOM SKIN IS PUNCTURED. ALL WORK ACCOMPLISHED ON N/R N00699.

Part: FLOORBOARD — DAMAGED (CARGO BAY) · airframe 40,758 hrs · 29,188 cycles

AFT CARGO COMPARTMENT FLOORBOARD 152 AF UPPER SKIN IS TORN AND THE BOTTOM SKIN IS PUNCTURED. FABRICATED REPLACEMENT FLOORBOARD 152 AF IAW DWG SRZ 25-008, REV "H".

Part: FLOORBOARD — DELAMINATED (CARGO BAY) · airframe 40,758 hrs · 29,188 cycles

BULK CARGO COMPARTMENT FLOORBOARD 162 EF TOP SKIN IS SEPARATING FROM THE FLOORBOARD. FABRICATED NEW FLOORBOARD 162 EF IAW DWG SRZ 25-005, REV "H". APPLIED TOP SKIN IAW DWG SRZ 25-011, REV "C"

Part: FLOOR SUPPORT — CRACKED (ZONE 200) · airframe 40,758 hrs · 29,188 cycles

MAIN CABIN FLOOR SUPPORT IS CRACKED AT FRAME 45; RBL 37. REMOVED AND REPLACED ADAPTER IAW SRM 51-40-21, PG 7 & AMM 25-21- 20-04; PO 701316.1. INSTALLED IAW SRM 51-40-21 & PMS 01-25-44.

Part: FLOORBOARD — PUNCTURED (CARGO BAY) · airframe 40,758 hrs · 29,188 cycles

AFT CARGO COMPARTMENT FLOORBOARD 151AF BOTTOM SKIN HAS MULTIPLE PUNCTURES. FABRICATED REPLACEMENT FLOORBOARD 151 AF IAW DWG SRZ 25-008, REV "H".

Part: SKIN — GOUGED (NR 3 SLAT) · airframe 40,758 hrs · 29,188 cycles

RT WING FIXED L/E INBD OF THE PYLON AND OTBD OF THE NR 3 SLAT TRACK THERE ARE APPROX 11 GOUGES FROM BUTTON HEADS INSTALLED ON THE BOTTOM SKIN OF SLAT RIB 8. R & R SLAT IAW AMM 27-80-11-04. SLAT TEST GOOD IAW AMM 27-80-11-04. REMOVED SKIN SECTION IAW SRM 51-40-21, PARA 13. FORMED NEW SECTION IAW DWG A7244112. ALODINE, PRIMED & PAINTED IAW SRM 51-75-10-08 & 51-23-10. INSTALLED SECTION IAW SRM 51-40-21, PARA 13.

Part: SKIN — GOUGED (NR 2 SLAT) · airframe 40,758 hrs · 29,188 cycles

LT WING NR 2 SLAT, INBD END LOWER SURFACE HAS GOUGES. REMOVED AND REPLACED LEFT WING NR 2 SLAT IAW AMM 27-80-12-04. OPS CHECK GOOD.

Part: SUPPORT — CRACKED (FUSELAGE) · airframe 40,758 hrs · 29,188 cycles

CARRIER AREA UNDERNEATH FLOOR WIRING BUNDLE SUPPORT IS CRACKED AT APPROX FRAME 14, LBL 30.0. REMOVED AND REPLACED IAW SRM 51-40-21, PG 7. FORMED SUPPORT IAW DWG A92421350. ALODINED IAW SRM 51-21-10, PG 2. PRIMED & PAINTED IAW 51-23-10, PG 24. INSTALLED IAW SRM 51-40-21.

Part: FLOOR PANEL — DAMAGED (MAIN DECK) · airframe 40,758 hrs · 29,188 cycles

MAIN DECK FLOOR PANEL 251 GF IS DAMAGED. FABRICATED REPLACEMENT FLOORBOARD 251 GF IAW DWG SRZ 25-008, REV "H".

Part: FLOOR PANEL — DAMAGED (ZONE 200) · airframe 40,758 hrs · 29,188 cycles

MAIN DECK FLOOR PANEL IS DAMAGED BETWEEN FRAME 54 AND FRAME 54.2; RBL 18 TO RBL 37. FABRICATED REPLACEMENT FLOORBOARD 252 BF IAW DWG SRZ 25-008, REV "H".

Part: FLOOR PANEL — PUNCTURED (ZONE 200) · airframe 40,758 hrs · 29,188 cycles

MAIN DECK FLOOR PANEL 231, KG IS PUNCTURED. FABRICATED REPLACEMENT FLOORBOARD 231 G IAW DWG SRZ 25-008, REV "H".

Part: SKIN — DAMAGED (MLG DOOR) · airframe 40,758 hrs · 29,188 cycles

NLG WELL, LT DOOR EXTERNAL SURFACE HAS (2) AREAS WITH LIGHTNING STRIKES. DAMAGE FOUND OUT OF LIMITS IAW RM 52-82-11. T NR 8225-0. REPAIRED IAW SRM 52-82-11, FIG 201. ALODINED, PRIMED AND PAINTED IAW SRM 51-21-10.

Part: FLOOR PANEL — DELAMINATED (ZONE 200) · airframe 40,758 hrs · 29,188 cycles

MAIN CABIN FLOOR PANEL 232 JH IS DELAMINATED AT THE ADAPTOR LOCATION AT APPROX FRAME 36.0 TO FRAME 37.0; RBL 38.0. FABRICATED REPLACEMENT FLOORBOARD 232 JH IAW DWG SRZ 25-008, REV "H".

Part: FLOORBOARD — CRACKED (MAIN DECK) · airframe 40,758 hrs · 29,188 cycles

MAIN DECK FLOORBOARD 242 NJ IS CRACKED. FABRICATED REPLACEMENT FLOORBOARD 242 NJ IAW DWG SRZ 25-008, REV "H".

Part: FLOOR PANEL — DETERIORATED (MAIN DECK) · airframe 40,758 hrs · 29,188 cycles

MAIN DECK FLOOR PANEL, 231 LG POTTING IS DETERIORIATED. FABRICATED REPLACEMENT FLOORBOARD 231 LG IAW FEDEX DWG SRZ 25-005, REV "H".

Part: FLOOR PANEL — BROKEN (ZONE 200) · airframe 40,758 hrs · 29,188 cycles

MAIN CABIN FLOOR PANEL IS BROKEN AND DELAMINATED FROM FRAME 31.0 TO FRAME 34.0; LBL 67.0. FABRICATED REPLACEMENT FLOORBOARD IAW DWG SRZ 25-008, REV "H".

Part: FLOOR PANEL — DELAMINATED (MAIN DECK) · airframe 40,758 hrs · 29,188 cycles

MAIN DECK FLOOR PANEL 251 WH IS DELAMINATED. FABRICATED REPLACEMENT FLOORBOARD 251WH IAW DWG SRZ 25-008, REV "H".

Part: FLOOR PANEL — PUNCTURED (ZONE 200) · airframe 40,758 hrs · 29,188 cycles

MAIN DECK FLOOR PANEL 231 FG IS PUNCTURED. FABRICATED REPLACEMENT FLOORBOARD 231 FG IAW DWG SRZ 25-008, REV "H".

Part: FLOORBOARD — BROKEN (ZONE 100) · airframe 40,758 hrs · 29,188 cycles

AFT CARGO COMPARTMENT FLOORBOARD 151 EF HAS A BROKEN CORNER WITH BROKEN EDGE FILL IN MULTIPLE LOCATIONS. FABRICATED REPLACEMENT FLOORBOARD 151 EF IAW DWG SRZ 25-008, REV "H".

Part: FLOORBOARD — BROKEN (ZONE 100) · airframe 40,758 hrs · 29,188 cycles

AFT CARGO COMPARTMENT FLOORBOARD 151 DF HAS A BROKEN CORNER WITH MISSING EDGE FILL. FABRICATED REPLACEMENT FLOORBOARD 151 DF IAW DWG SRZ 25-008, REV "H".

Part: FLOOR PANEL — BROKEN (ZONE 200) · airframe 40,758 hrs · 29,188 cycles

MAIN CABIN FLOOR PANEL IS BROKEN FROM FRAME 78.0 TO FRAME 80.0; RBL 59.0. FABRICATED REPLACEMENT FLOORBOARD IAW DWG SRZ 25-008, REV "H".

Part: FLOOR PANEL — DELAMINATED (ZONE 200) · airframe 40,758 hrs · 29,188 cycles

MAIN CABIN FLOOR PANEL 262 MF IS DELAMINATED UNDERNEATH; FROM FRAME 73.0 TO FRAME 75.0; RBL 30.0. FABRICATED REPLACEMENT FLOORBOARD 262 MF IAW DWG SRZ 25-008, REV "H".

Part: FLOORBOARD — DAMAGED (ZONE 100) · airframe 40,758 hrs · 29,188 cycles

AFT CARGO COMPARTMENT FLOORBOARD 152 BF EDGE IS DAMAGED, HAS MISSING EDGE FILL AND THE BOTTOM IS PUNCTURED. FABRICATED REPLACEMENT FLOORBOARD 152 BF IAW DWG SRZ 25-008, REV "H".

Part: FLOOR PANEL — CRUSHED (MAIN CABIN) · airframe 40,758 hrs · 29,188 cycles

MAIN CABIN FLOOR PANEL 232 LT IS CRUSHED AT THE ADAPTOR LOCATION, 4 AREAS; FROM FRAME 37 TO FRAME 38.2; RBL 37.0. FABRICATED REPLACEMENT FLOORBOARD 232 LT IAW DWG SRZ 25-008, REV "H".

Part: FLOOR PANEL — DAMAGED (ZONE 200) · airframe 40,758 hrs · 29,188 cycles

MAIN DECK FLOOR PANEL IS DAMAGED BETWEEN FRAME 54.2 AND FRAME 55; RBL 18 TO RBL 37. FABRICATED REPLACEMENT FLOORBOARD 252 CF IAW DWG SRZ 25-008, REV "H".

Part: FLOOR PANEL — DAMAGED (ZONE 100) · airframe 40,758 hrs · 29,188 cycles

FWD CARGO COMPARTMENT FLOOR PANEL 131 QF HAS SEVERE EDGE DAMAGE IN MULTIPLE AREAS AND 2 CORNERS ARE BROKEN. FABRICATED REPLACEMENT FLOORBOARD IAW DWG SRZ 25-008, REV "H".

Part: FLOOR PANEL — DELAMINATED (MAIN CABIN) · airframe 40,758 hrs · 29,188 cycles

MAIN CABIN FLOOR PANEL 252 LG EDGE IS DELAMINATED AND MISSING HONEYCOMB UNDERNEATH FROM FRAME 71.0 TO FRAME 73.0; RBL 65.0. FABRICATED REPLACEMENT FLOORBOARD 252 LG IAW DWG SRZ 25-008, REV "H".

Part: FLOOR PANEL — CRUSHED (MAIN CABIN) · airframe 40,758 hrs · 29,188 cycles

MAIN CABIN FLOOR PANEL 242QJ IS CRUSHED AT THE ADAPTOR LOCATION, 3 AREAS; FROM FRAME 40/41 TO FRAME 43; RBL 37.0. FABRICATED REPLACEMENT FLOORBOARD 242 QJ IAW DWG SRZ 25-008, REV "H".

Part: FLOOR PANEL — BROKEN (ZONE 200) · airframe 40,758 hrs · 29,188 cycles

MAIN CABIN FLOOR PANEL 262 NF IS BROKEN AND DELAMINATED UNDERNEATH; FROM FRAME 73.0 TO FRAME 75.0; RBL 33.0. FABRICATED REPLACEMENT FLOORBOARD IAW DWG SRZ 25-008, REV "H".

Part: FLOOR PANEL — DELAMINATED (ZONE 200) · airframe 40,758 hrs · 29,188 cycles

MAIN CABIN FLOOR PANEL 232 YG IS DELAMINATED AT THE ADAPTOR LOCATION AT APPROX FRAME 34 TO FRAME 36; RBL 38.0. FABRICATED REPLACEMENT FLOORBOARD 232 YG IAW DWG SRZ 25-008, REV "H".

Part: FLOOR PANEL — DELAMINATED (ZONE 200) · airframe 40,758 hrs · 29,188 cycles

MAIN CABIN FLOOR PANEL 262 LF IS DELAMINATED AND HAS 2 EA, FIG 8 FASTENER HOLES; FROM FRAME 73.0 TO FRAME 75.0. FABRICATED REPLACEMENT FLOORBOARD 262 LF IAW DWG SRZ 25-008, REV "H".

Part: FLOOR PANEL — CRUSHED (MAIN CABIN) · airframe 40,758 hrs · 29,188 cycles

MAIN CABIN FLOOR PANEL 242 SF IS CRUSHED AT THE ADAPTOR LOCATION, 2 AREAS; FROM FRAME 38.2 TO FRAME 40/41; RBL 37.0. FABRICATED REPLACEMENT FLOORBOARD 242 VJ IAW DWG SRZ 25-008, REV "H".

Part: FLOOR PANEL — CRUSHED (MAIN CABIN) · airframe 40,758 hrs · 29,188 cycles

MAIN CABIN FLOOR PANEL 242 VJ IS CRUSHED AT THE ADAPTOR LOCATION, 4 AREAS; FROM FRAME 44.0 TO FRAME 46.0; RBL 37. FABRICATED REPLACEMENT FLOORBOARD 242 VJ IAW DWG SRZ 25-008, REV "H".

Part: FLOOR PANEL — PUNCTURED (ZONE 200) · airframe 40,758 hrs · 29,188 cycles

MAIN DECK FLOOR PANEL 231 QG IS PUNCTURED. FABRICATED REPLACEMENT FLOORBOARD 231 QG IAW DWG SRZ 25-008, REV "H".

Part: FLOOR PANEL — DAMAGED (ZONE 200) · airframe 40,758 hrs · 29,188 cycles

MAIN DECK FLOOR PANEL IS DAMAGED BETWEEN FRAME 55 AND FRAME 60; RBL 18 TO RBL 37. FABRICATED REPLACEMENT FLOORBOARD 252 RH IAW DWG SRZ 25-008, REV "H".

Part: FLOOR PANEL — DAMAGED (MAIN DECK) · airframe 40,758 hrs · 29,188 cycles

MAIN DECK FLOOR PANEL 251 PH IS DAMAGED. FABRICATED REPLACEMENT FLOORBOARD 251 PH IAW DWG SRZ 25-008, REV "H".

Part: FLOOR PANEL — DELAMINATED (MAIN DECK) · airframe 40,758 hrs · 29,188 cycles

MAIN CABIN FLOOR PANEL 241 QF EDGE IS DELAMINATED AT FRAME 51; LBL 58.0. FABRICATED REPLACEMENT FLOORBOARD 241 QF IAW DWG SRZ 25-008, REV "H".

Part: FLOOR PANEL — GOUGED (ZONE 200) · airframe 40,758 hrs · 29,188 cycles

MAIN CABIN FLOOR PANEL IS DEEPLY GOUGED FROM FRAME 28.0 TO FRAME 31.0; RBL 29.0. FABRICATED REPLACEMENT FLOORBOARD IAW DWG SRZ 25-008, REV "H".

Part: FLOORBOARD — BROKEN (ZONE 100) · airframe 40,758 hrs · 29,188 cycles

AFT CARGO COMPARTMENT FLOORBOARD 151CF HAS A BROKEN CORNER WITH BROKEN EDGE FILL IN MULTIPLE LOCATIONS AND A PUNCTURED BOTTOM. FABRICATED REPLACEMENT FLOORBOARD 151 CF IAW DWG SRZ 25-008, REV "H".

Part: FLOOR PANEL — DELAMINATED (ZONE 200) · airframe 40,758 hrs · 29,188 cycles

MAIN CABIN FLOOR PANEL 232 TG IS DELAMINATED WITH A HOLE AT APPROX FRAME 34; RBL 36.0. FABRICATED REPLACEMENT FLOORBOARD 232 TG IAW FEDEX DWG SRZ 25-008, REV "H".

Part: FLOOR PANEL — DELAMINATED (ZONE 200) · airframe 40,758 hrs · 29,188 cycles

MAIN CABIN FLOOR PANEL 232 EG IS DELAMINATED FROM APPROX FRAME 22.0 TO FRAME 23.0; RBL 12.0. FABRICATED REPLACEMENT FLOORBOARD 232 EG IAW DWG SRZ 25-008, REV "H".

Part: FLOOR PANEL — DAMAGED (ZONE 200) · airframe 40,758 hrs · 29,188 cycles

MAIN DECK FLOOR PANEL IS DAMAGED BETWEEN FRAME 60 AND FRAME 62; RBL 18 TO RBL 37. FABRICATED REPLACEMENT FLOORBOARD RBL 18 - RBL 37; FRAME 60 - FRAME 62 IAW DWG SRZ 25-008, REV "H".

Part: FLOOR PANEL — PUNCTURED (ZONE 200) · airframe 40,758 hrs · 29,188 cycles

MAIN DECK FLOOR PANEL, 231 EF IS PUNCTURED. FABRICATED REPLACEMENT FLOORBOARD 231 EF IAW DWG SRZ 25-008, REV "H".

Part: FLOORBEAM — CORRODED (CARGO BAY) · corrosion level 2 · airframe 40,758 hrs · 29,188 cycles

FWD CARGO COMPARTMENT FLOOR STRUCTURE TEE CAP AT FRAME 36; RBL 9 IS CORRODED. REMOVED 2 EA ROLLER TRACK ASSEMBLIES FOR ACCESS TO REPAIR AREA IAW AMM 25-52-21-04-0. REPAIRED CROSSBEAM UPPER FLANGE IAW SRM 53-10-15, FIG 207. CORROSION WAS REMOVED AND THE MATERIAL LOSS WAS FOUND TO EXCEED ALLOWABLE LIMITS. ORIGINAL THICKNESS WAS 0.125 AND THE REMAINING THICKNESS WAS 0.000 IAW SRM 53-10-15, FIG 101. REINSTALLED 2 EA ROLLER TRACK ASSEMBLIES IAW AMM 25-52-21-04-0.

Part: SEAT TRACK — GOUGED (ZONE 200) · airframe 40,758 hrs · 29,188 cycles

MAIN DECK, FLOOR SEAT TRACK IS GOUGED BETWEEN FRAME 60 AND FRAME 61; LBL 38. CUT OUT DAMAGED AREA OF SEAT TRACK FOUND TO BE OUT OF LIMITS IAW SRM 53-10-16, FIG 101. FABRICATED NEW SECTION OF SEAT TRACK AND 4 EA. SPLICES IAW SRM 53-10-16, FIG 208. ALODINED IAW 51-21-10. PRIMED IAW SRM 51-23-10. PAINTED IAW SRM 51-75-10. INSTALLED IAW SRM 53-10-16, FIG 208.

Part: FLAP — DENTED (ZONE 500) · airframe 40,758 hrs · 29,188 cycles

LT INBD FLAP LOWER SKIN IS DENTED 70" FROM THE INBD EDGE AND 40" FROM THE T/E. DAMAGED AREA FOUND TO BE OUT OF LIMITS IAW 57-52-12, FIG 103. FABRICATED AND INSTALLED REPAIR IAW SRM 57-52-12, FIG 205 IAW EA 6-5750-136734. ALODINED REPAIR IAW SRM 51-21-10, PG 3. PRIMED AREA IAW SRM 51-75-10. TOPCOATED REPAIR DOUBLER IAW SRM 51-23-00 & SRM 57-52-12, FIG 205. EA 6-5750-136734.

Part: SKIN — DENTED (ZONE 500) · airframe 40,758 hrs · 29,188 cycles

LEFT INBOARD FLAP LOWER SKIN IS DENTED 70" FROM THE INBOARD EDGE AND 40" FROM THE TRAILING EDGE. DAMAGED AREA FOUND TO BE OUT OF LIMITS IAW A310-200 57-52-12, FIG 103. FABRICATED AND INSTALLED REPAIR IAW A310-200 SRM 57-52-12, FIG 205 PER EA 6-5750-136734. ALODINED REPAIR IAW SRM 51-21-10, PG 3. PRIMED AREA IAW SRM 51-75-10. TOPCOATED REPAIR DOUBLER IAW SRM 51-23-00 & SRM 57-52-12, FIG 205. EA 6-5750-136734, "WINGS - LT WING INBD FLAP LOWER SKIN REPAIR BETWEEN FLAP RIB 9 & 10".

Part: ENGINE — MALFUNCTIONED (NR 2) · airframe 40,744 hrs · 29,182 cycles

AFTER TOUCHDOWN, HAD A HARD TIME PULLING REVERSER LEVERS INTO REVERSE, GOT THEM INTO REVERSE. SPOILERS INITIALLY DEPLOYED, THEN GOT ECAM ALERT FOR GROUND SPOILERS NOT DEPLOYED. THEN WE HEARD A LOUD BANG AND A FLASH ON THE RT SIDE AND THE NR 2 ENG QUIT AS WE WERE ROLLING TO A STOP. SOMEONE ON THE GROUND SAID IT LOOKED LIKE ACFT ON FIRE. SHUTDOWN ENGINE IAW ECAM PULLED FIRE HANDLE AND FIRED BOTTLE. COMPLETED TESTS FOR ALTERNATE TRIM PROCEDURE 8A. (FLYBACK USE ONLY) REF MM 71-00-00-05. PERFORMED TAKEOFF POWER CHECK REF JRH CH7, ALL PARAMETERS CHECKED NORMAL.

Part: PUSH-PULL CABLE — FROZEN (THROTTLE) · airframe 39,464 hrs · 28,212 cycles

AT TOP OF DESCENT THE NR 2 THROTTLED JAMMED FOLLOWED THE QRH AND AT AROUND 10K' THE THROTTLE WAS RECOVERED. EXPECT FREEZING OF THE PUSH-PULL ABLE AS PER QRH. THE AIRPLANE WAS SOAKED DURING THE TURN OUT OF KSHV BEGAN REMOVING THE PUSH-PULL CABLE IN REF TO AMM 76-11-41-4. REMOVED PANELS, NR 421BL, 421CL, 423BL, 423DL, 421AZ AND 423CL. COMPLIED WITH ADJUSTMENT AND TEST IAW AMM 76-11-00-5 AS REQUIRED. INSTALLED PERCOOLER, INSTALLED PYLON PANELS AS REQUIRED CLOSED NR 2 ENG T/R AND FAN COWLS IAW AMM 76-11-41-4. OPS CHECKS GOOD OK FOR SERVICE.

Part: PAN — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,160 hrs · 27,998 cycles

AFT LOWER CARGO COMPARTMENT HAS CORROSION ON THE POWER ROLLER PAN AND SUPPORT BETWEEN FRAMES 61 AND 62; LBL 14 INCH (LOWER SURFACE). REMOVED PAN AND FRAME IAW SRM 51-41-21. REMOVED CORROSION IAW SRM 51-71-10. BOTH FOUND TO BE OUT OF LIMITS IAW SRM 53-10-00. MACHINED NEW FRAME IAW DWG NR 10A25771822 REV E; 10A25771747; REV K. ALODINED IAW SRM 51-21-10. PRIMED IAW SRM 51-75-10. PAINTED IAW SRM 51-75-10. LOCATED AND DRILLED HOLES IN NEW PAN AND FRAME IAW SRM 51-40-44 AND SRM 51-72-10. PART MARKED IAW GMM 7-0-1000. INSTALLED PAN AND FRAME IAW SRM 51-40-21. INSTALLED PDU IAW AMM 25-54-26-04. OPS CHECKED.

Part: PAN — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,160 hrs · 27,998 cycles

AFT LOWER CARGO COMPARTMENT HAS CORROSION ON THE POWER ROLLER PAN & SUPPORT AT FRAME 54.2; LBL 41" (LOWER SURFACE). REMOVED PAN AND FRAME IAW SRM 51-40-21. REMOVED CORROSION IAW SRM 51-74-10. BOTH FOUND TO BE OUT OF LIMITS IAW SRM 53-10-00. MACHINED NEW FRAME IAW DWG NR 10A25771745; REV E AND 10A25771823; REV G. ALODINED IAW SRM 51-21-10. PRIMED IAW SRM 51-75-10. PAINTED IAW SRM 51-75-10. LOCATED AND DRILLED HOLES IN NEW PAN AND FRAME IAW SRM 51-40-44 AND SRM 51-72-10. PART MARKED IAW GMM 7-0-1000. INSTALLED PAN AND FRAME IAW SRM 51-40-21. INSTALLED PDU IAW AMM 25-54-26-04.

Part: FRAME — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,160 hrs · 27,998 cycles

AFT LOWER CARGO COMPARTMENT HAS CORROSION ON THE POWER ROLLER PAN AND SUPPORT BETWEEN FRAMES 61 AND 62; LBL 41 INCH (LOWER SURFACE). REMOVED FRAME IAW SRM 51-40-21. REMOVED CORROSION IAW SRM 51-74-10. BOTH FOUND TO BE OUT OF LIMITS IAW SRM 53-10-00. MACHINED NEW FRAME IAW DWG NR A25771746204. ALODINED IAW SRM 51-21-10. PRIMED IAW SRM 51-75-10. PAINTED IAW SRM 51-75-10. LOCATED AND DRILLED HOLES IN NEW PAN AND FRAME IAW SRM 51-40-44 AND SRM 51-72-10. PART MARKED IAW GMM 7-0-1000. INSTALLED PAN AND FRAME IAW SRM 51-40-21. INSTALLED PDU IAW AMM 25-54-26-04. OPS CHECK IAW AMM 25-52-26-4.

Part: FRAME — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,160 hrs · 27,998 cycles

AFT LOWER CARGO COMPARTMENT HAS CORROSION ON THE POWER ROLLER PAN AND SUPPORT AT FRAME 58; LBL 41 INCH (LOWER SURFACE). REMOVED PAN AND FRAME IAW SRM 51-41-21. REMOVED CORROSION IAW SRM 51-71-10. BOTH FOUND TO BE OUT OF LIMITS IAW SRM 53-10-00. FABRICATED NEW FRAME P/N 10A25771822-208 IAW DWG 3 10A25771822. ALODINED IAW SRM 51-21-10. PRIMED IAW SRM 51-75-10. PAINTED IAW SRM 51-75-10. LOCATED AND DRILLED HOLES IN NEW PAN AND FRAME IAW SRM 51-40-44 AND SRM 51-72-10. PART MARKED IAW GMM 7-0-1000. INSTALLED PAN AND FRAME IAW SRM 51-40-21. INSTALLED PDU IAW AMM 25-54-26-04.

Part: PAN — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,160 hrs · 27,998 cycles

AFT LOWER CARGO COMPARTMENT HAS CORROSION ON THE POWER ROLLER PAN AND SUPPORT AT FRAME 54.2, LBL 3 INCH" (LOWER SURFACE). REMOVED PAN AND FRAME IAW SRM 51-41-21. REMOVED CORROSION IAW SRM 51-71-10. BOTH FOUND TO BE OUT OF LIMITS IAW SRM 53-10-00. MACHINED NEW FRAME IAW DWG 310A25771822. ALODINED IAW SRM 51-21-10. PRIMED IAW SRM 51-75-10. PAINTED IAW SRM 51-75-10. LOCATED AND DRILLED HOLES IN NEW PAN AND FRAME IAW SRM 51-40-44 AND SRM 51-72-10. PART MARKED IAW GMM 7-0-1000. INSTALLED PAN AND FRAME IAW SRM 51-40-21. INSTALLED PDU IAW AMM 25-54-26-04. OPS CHECKED IAW AMM 25-52-26-04.

Part: TRUNNION — DAMAGED (ZONE 500) · airframe 39,160 hrs · 27,998 cycles

RIGHT MLG TRUNNION ATTACHMENT POINT HINGE ARM FITTING DOES NOT TAKE GREASE.. REMOVED GREASE SUPPLY DUCT IAW MESSIER DOWTY CMM 32-16-12. RECOMDITIONED TRUNNION PIN & SUPPLY DUCT PIN HOLE " E " IAW CMM 32-16-12. HOLE SIZE AFTER RECONDITIONING IS 1.2685. WITHIN ALLOWABLE TOLERENCE PER CMM 32-16-12. INSTALLED NEW GREASE SUPPLY DUCT & ZERK FITTING IAW CMM 32-16-12.

Part: FLOORBOARD — DAMAGED (CABIN) · airframe 39,160 hrs · 27,998 cycles

MAIN CABIN FLOORBOARD 232 LT IS BROKEN. FABRICATED NEW FLOORBOARD 232 LT IAW FEDEX DWG SRZ 25-005; REV G.

Part: FLOORBOARD — DAMAGED (CABIN) · airframe 39,160 hrs · 27,998 cycles

MAIN CABIN FLOORBOARD IS BROKEN BETWEEN FRAMES 36 & 37; BL 36R. FABRICATED NEW FLOORBOARD 232 JH IAW FEDEX DWG SRZ 25-005; REV G.

Part: FLOOR PANEL — BROKEN (ZONE 200) · airframe 39,160 hrs · 27,998 cycles

MAIN CARGO COMPARTMENT FLOOR PANEL NR 251 BH IS BROKEN. FABRICATED A NEW FLOOR PANEL NR 251 BH IAW DWG SRZ 25-005, REV "G".

Part: FLOOR PANEL — CRACKED (CABIN) · airframe 39,160 hrs · 27,998 cycles

MAIN CABIN FLOOR PANEL 252 VJ IS CRACKED. FABRICATED A NEW FLOOR PANEL 252 VJ IAW FEDEX DWG SRZ 25-005; REV G.

Part: FLOOR PANEL — CRACKED (CABIN) · airframe 39,160 hrs · 27,998 cycles

MAIN CABIN FLOOR PANEL 242 SF IS CRACKED. FABRICATED A NEW FLOOR PANEL 242 SF IAW FEDEX DWG SRZ 25-005; REV G.

Part: FLOORBOARD — DAMAGED (CABIN) · airframe 39,160 hrs · 27,998 cycles

MAIN CABIN FLOORBOARD NR 242 UG IS DAMAGED, CRACKED. FABRICATED A NEW FLOORBOARD NR 242 UG IAW DWG SRZ 25-005, REV "G".

Part: FLOOR PANEL — CRACKED (A/C BAY) · airframe 39,160 hrs · 27,998 cycles

DETERIORATED/CRACKED CORNERS OF AIR CONDITIONING BAY FLOOR PANEL 143 DF. FABRICATED A NEW FLOOR PANEL NR 143 DF IAW DWG SRZ 25-005, REV "G".

Part: FLOOR PANEL — CRACKED (CABIN) · airframe 39,160 hrs · 27,998 cycles

MAIN CABIN FLOOR PANEL 242 VJ IS CRACKED. FABRICATED A NEW FLOORBOARD 242 VJ IAW FEDEX DWG SRZ 25-005; REV G.

Part: FLOOR PANEL — CRACKED (CABIN) · airframe 39,160 hrs · 27,998 cycles

MAIN CABIN FLOOR PANEL 242 QJ IS CRACKED. FABRICATED A NEW FLOOR PANEL 242 QJ IAW FEDEX DWG SRZ 25-005; REV G.

Part: FLOOR PANEL — CRACKED (CABIN) · airframe 39,160 hrs · 27,998 cycles

MAIN CABIN FLOOR PANEL 242 YG IS CRACKED. FABRICATED A NEW FLOOR PANEL 242 YG IAW FEDEX DWG SRZ 25-005; REV G.

Part: FLOOR PANEL — CRACKED (CABIN) · airframe 39,160 hrs · 27,998 cycles

MAIN CABIN FLOOR PANEL 242 NJ IS CRACKED. FABRICATED A NEW FLOOR PANEL 242 NJ IAW FEDEX DWG SRZ 25-005; REV G.

Part: FLOOR PANEL — DAMAGED (CABIN) · airframe 39,160 hrs · 27,998 cycles

MAIN CABIN FLOOR PANEL NR 232 NG IS DAMAGED BETWEEN FRAME 26 AND FRAME 26/32, RBL 18 TO RBL 38. FABRICATED A NEW FLOOR PANEL NR 232 NG IAW DWG SRZ 25-005; REV "G".

Part: FRAME — CORRODED (FUSELAGE) · airframe 39,160 hrs · 27,998 cycles

FWD PIT, FRAME 33 LEFT HAS CORROSION UNDER THE OUTBD ROLLER TRAY AT THE FRAME. REMOVED ROLLER TRAY & TRANSITION PANEL IAW SRM 51-40-21. REMOVED CORROSION FROM CROSS BEAM IAW SRM 51-74-10. AREA FOUND TO BE OUT OF LIMITS IAW SRM 51-74-01. FABRICATED A CROSS BEAM SECTION IAW SRM 53-10-15 & DWG A53773651. ALODINED IAW SRM 51-21-10. PRIMED & PAINTED IAW SRM 51-23-10. INSTALLED ROLLER TRAY & TRANSITIONAL IAW AMM 25-52-21-4.

Part: MOUNT — CORRODED (ZONE 400) · corrosion level 2 · airframe 39,160 hrs · 27,998 cycles

NR 1 PYLON, ENGINE AFT ATTACHMENT BEAM LOWER SURFACE INBD AND OUTBD FAYING SURFACES HAVE CORROSION. ABRASIVE BLASTED ENGINE MOUNT IAW AIRBUS A310-200 SRM 51-74-10; PG 208. CONTINUED BLENDING TO REMOVE CORROSION IAW AIRBUS A310-200 SRM 51-74-10. FOUND TO BE OUT OF LIMITS IAW AIRBUS A310-200 AMM 54-51-00. MAX ALLOWABLE , 0.020. AMOUNT REMOVED, 0.080. ORDERED AND RECEIVED A NEW ENGINE MOUNT. REMOVAL AND INSTALLATION OF THE MOUNT IS ACCOMPLISHED ON NON-ROUTINE N01193. NO FURTHER ACTION IS REQUIRED.

Part: SUPPORT ANGLE — CORRODED (ZONE 200) · corrosion level 2 · airframe 39,160 hrs · 27,998 cycles

MAIN CABIN AT C 17 AND CUSP LINE AREA THE FRAME SUPPORT ANGLE HAS CORROSION ON THE LEFT SIDE. FABRICATED, ALODINED, PRIMED AND PAINTED THE NEW BRACKET SUPPORT ANGLE LEFT SIDE IAW A310-200 SRM 51-40-21; 51-22-00 AND 51-23-10.

Part: FLOORBEAM — DAMAGED (FUSELAGE) · airframe 39,160 hrs · 27,998 cycles

FUSELAGE INTERIOR MAIN CARGO DECK CROSSBEAM LOWER CAP IS DAMAGED AT FRAME C 60 AND RBL 78. REMOVED DAMAGE IAW EA 6-5310-7-123653. MILLED DOWN AREAS ON CROSSBEAM IAW EA 6-5310-123653. FABRICATED REPAIR ANGLE, REPAIR STRAP & FILLER IAW EA 6-5310-123653. ALODINED IAW SRM 51-26-10. PRIMED & PAINTED IAW SRM 51-23-10. INSTALLED REPAIR PARTS IAW EA 6-5310-123653.

Part: SKIN — DAMAGED (ZONE 200) · airframe 39,160 hrs · 27,998 cycles

EXTERIOR FUSELAGE UPPER SKIN HAS STATIC DISCHARGE AT FRAME 65; BETWEEN STRINGER 2 L AND 3 L. BLENDED AREA IAW SRM 53-10-12; FIG 220. MATERIAL THICKNESS 0.071. MATERIAL LOSS 0.005. MATERIAL REMAINING 0.066. FOUND TO BE WITHIN LIMITS IAW SRM 53-17-12. ACCOMPLISHED HFEC INSPECTION OF THE BLENDED AREA IAW NTM 51-10-08. ALODINED AND PRIMED IAW SRM 51-21-01.

Part: SEAT TRACK — DAMAGED (ZONE 200) · airframe 39,160 hrs · 27,998 cycles

SEAT TRACK IS DAMAGED AT FRAME 54; RBL 18. REMOVED THE DAMAGED TRACK & INSTALLED A NEW TRACK WITH SPLICE IAW SRM 53-10-16.

Part: SKIN — DENTED (ZONE 200) · airframe 39,160 hrs · 27,998 cycles

THE FUSELAGE SKIN IS DENTED AROUND RIVETS T FRAMES 70 - 72; STRINGER 22R. RE-EVALUATED THE AREA & FOUND TO BE OUT OF LIMITS IAW SRM 53-17-12 & SRM 53-10-00. REMOVED DAMAGED AREA IAW SRM 53-10-12. FABRICATED THE FILLER & DOUBLER REPAIR IAW SRM 53-10-12. ALODINED & PRIMED IAW SRM 53-23-10. INSTALLED DOUBLER REPAIR IAW SRM 51-40-21.

Part: SKIN — DAMAGED (ZONE 200) · airframe 39,160 hrs · 27,998 cycles

EXTERIOR FUSELAGE UPPER SKIN HAS STATIC DISCHARGE BETWEEN FRAME 69 AND FRAME 70; STR 2 L AND 3 L REMOVED DAMAGE BY WAY OF DRILLING A 5/32 HOLE IAW A310-200 SRM 53-10-12, FIG 220. ACCOMPLISHED A BHEC INSPECTION IAW NTM 51-10-01. INSTALLED A RIVET IAW A310-200 SRM 53-10-12, FIG 220.

Part: SKIN — DAMAGED (ZONE 200) · airframe 39,160 hrs · 27,998 cycles

EXTERIOR FUSELAGE UPPER SPLICE DOUBLER HAS STATIC DISCHARGE AT FRAME 33 BETWEEN STRINGER 5 L AND 6 L. REMOVED AND REPLACED FASTENER IAW A310-200 SRM 53-10-12; FIG 220. ACCOMPLISHED A BHEC INSPECTION IAW A310 NTM 51-10-01.

Part: SKIN — DAMAGED (ZONE 200) · airframe 39,160 hrs · 27,998 cycles

EXTERIOR FUSELAGE SKIN HAS STATIC DISCHARGE BETWEEN FRAME 69 AND FRAME 70 FROM STRINGER 5L AND 6L REMOVED DAMAGE BY WAY OF DRILLING A 5/32 HOLE IAW A310-200 SRM 53-10-12; FIG 220. ACCOMPLISHED A BHEC INSPECTION IAW NTM 51-10-01. INSTALLED A RIVET IAW A310-200 SRM 53-10-12, FIG 220.

Part: SKIN — DAMAGED (ZONE 200) · airframe 39,160 hrs · 27,998 cycles

EXTERIOR FUSELAGE UPPER SKIN HAS STATIC DISCHARGE AT FRAME 66 BETWEEN STRINGER 2 L AND 3 L. REMOVED AND REPLACED FASTENER IAW A310-200 SRM 53-10-12; FIG 220. ACCOMPLISHED A BHEC INSPECTION IAW NTM 51-10-01.

Part: SKIN — DAMAGED (ZONE 200) · airframe 39,160 hrs · 27,998 cycles

EXTERIOR FUSELAGE SKIN HAS STATIC DISCHARGE BETWEEN FRAME 68 AND FRAME 69, STRINGER 1 L AND 2 L. REMOVED DAMAGE BY WAY OF DRILLING A 5/32 HOLE IAW SRM 53-10-12, FIG 220. ACCOMPLISHED A BHEC INSPECTION IAW NTM 51-10-01. INSTALLED A RIVET IAW A310-200 SRM 53-10-12, FIG 220.

Part: SKIN — CORRODED (ZONE 500) · corrosion level 2 · airframe 39,160 hrs · 27,998 cycles

LEFT WING FUEL TANK DOOR CUT OUT BETWEEN RIB 21 AND RIB 22 IS CORRODED. REMOVED CORROSION AND CHECKED LIMITS. ORIGINAL THICKNESS 0.600. MATERIAL REMOVED 0.002. REMAINING THICKNESS 0.598 AND IS FOUND TO BE WITHIN LIMITS IAW A310 SRM 57-20-12; PG 68; FIG 7A AND A310 SRM 57-20-12; PARA A-1 (A), FIG 201. UT GAUGE USED T 8225T. ACCOMPLISHED PFPI IAW A310 NTM 51-90-00. ALODINED AND PRIMED IAW A310 SRM 51-20-10 AND A310 SRM 57-20-12; PG 201B PARA 3-A.

Part: SKIN — CORRODED (ZONE 500) · airframe 39,160 hrs · 27,998 cycles

LEFT WING FUEL TANK DOOR CUT OUT BETWEEN RIB 23 AND RIB 24 IS CORRODED. REMOVED CORROSION AND CHECKED LIMITS. ORIGINAL THICKNESS 0.600. MATERIAL REMOVED 0.003. REMAINING THICKNESS 0.597 AND IS FOUND TO BE WITHIN LIMITS IAW A310 SRM 57-20-12; PG 68; FIG 7A AND A310 SRM 57-20-12; PARA A-1 (A); FIG 201. ACCOMPLISHED PFPI IAW A310 NTM 51-90-00. ALODINED AND PRIMED IAW A310 SRM 51-20-10 AND A310 SRM 57-20-12; PG 201B PARA 3-A. THIS SDR WAS GENERATED IN ERROR. FOR SDR DETAILS SRR SDR TRACKING NR 08-3858 FOR N/R N00971.

Part: SKIN — CORRODED (ZONE 500) · corrosion level 2 · airframe 39,160 hrs · 27,998 cycles

LEFT WING FUEL TANK DOOR CUT OUT BETWEEN RIB 24 AND RIB 25 IN CORRODED. REMOVED CORROSION AND CHECKED LIMITS. ORIGINAL THICKNESS 0.276. MATERIAL REMOVED 0.002. REMAINING THICKNESS 0.274 AND IS FOUND TO BE WITHIN LIMITS IAW A310 SRM 57-20-12; PG 68; FIG 7A AND A310 SRM 57-20-12; PARA A-1 (A); FIG 201. UT GAUGE USED T 8225T. ACCOMPLISHED PFPI IAW A310 NTM 51-90-00. ALODINED AND PRIMED IAW A310 SRM 51-20-10 AND A310 SRM 57-20-12, PG 201B PARA 3-A.

Part: SKIN — CORRODED (ZONE 500) · corrosion level 2 · airframe 39,160 hrs · 27,998 cycles

LEFT WING FUEL TANK DOOR CUT OUT BETWEEN RIB 22 AND RIB 23 IS CORRODED. REMOVED CORROSION AND CHECKED LIMITS. ORIGINAL THICKNESS 0.600. MATERIAL REMOVED 0.003. REMAINING THICKNESS 0.597 AND IS FOUND TO BE WITHIN LIMITS IAW A310 SRM 57-20-12; PG 68; FIG 7A AND A310 SRM 57-20-12; PARA A-1 (A); FIG 201. UT GAUGE USED T 8225T. ACCOMPLISHED PFPI IAW A310 NTM 51-90-00. ALODINED AND PRIMED IAW A310 SRM 51-20-10 AND A310 SRM 57-20-12, PG 201B PARA 3-A.

Part: SKIN — CORRODED (ZONE 500) · airframe 39,160 hrs · 27,998 cycles

LEFT WING FUEL TANK DOOR CUT OUT BETWEEN RIB 23 AND RIB 24 IS CORRODED. REMOVED CORROSION AND CHECKED LIMITS. ORIGINAL THICKNESS 0.600. MATERIAL REMOVED 0.003. REMAINING THICKNESS 0.597 AND IS FOUND TO BE WITHIN LIMITS IAW A310 SRM 57-20-12; PG 68; FIG 7A AND A310 SRM 57-20-12; PARA A-1 (A); FIG 201. ACCOMPLISHED PFPI IAW A310 NTM 51-90-00. ALODINED AND PRIMED IAW A310 SRM 51-20-10 AND A310 SRM 57-20-12, PG 201B PARA 3-A.

Part: SKIN — CORRODED (ZONE 500) · corrosion level 2 · airframe 39,160 hrs · 27,998 cycles

LEFT WING FUEL TANK DOOR CUT OUT BETWEEN RIB 20 AND RIB 21 IS CORRODED. REMOVED CORROSION AND CHECKED LIMITS. ORIGINAL THICKNESS 0.600. MATERIAL REMOVED 0.002. REMAINING THICKNESS 0.598 AND IS FOUND TO BE WITHIN LIMITS IAW A310 SRM 57-20-12; PG 68; FIG 7A AND A310 SRM 57-20-12; PARA A-1 (A); FIG 201. UT GAUGE USED T 8225T. ACCOMPLISHED PFPI IAW A310 NTM 51-90-00. ALODINED AND PRIMED IAW A310 SRM 51-20-10 AND A310 SRM 57-20-12, PG 201B PARA 3-A.

Part: SKIN — DAMAGED (ZONE 200) · airframe 39,160 hrs · 27,998 cycles

EXTERIOR UPPER FUSELAGE SKIN HAS STATIC DISCHARGE BETWEEN FRAME 35 AND FRAME 36; STRINGER 1R AND STRINGER 2 R. REMOVED DAMAGE BY WAY OF DRILLING A 5/32 HOLE IAW SRM 53-10-12; FIG 220. ACCOMPLISHED A BHEC INSPECTION OF THE DRILLED HOLE IAW NTM PT 6 51-10-01. INSTALLED RIVET IAW SRM 53-10-12; FIG 220.

Part: SKIN — DAMAGED (ZONE 200) · airframe 39,160 hrs · 27,998 cycles

EXTERNAL UPPER FUSELAGE SKIN HAS STATIC DISCHARGE AT FRAME 44, STRINGER 1. REMOVED AND REPLACED STRINGER 2 R. REMOVED AND REPLACED RIVET IAW SRM 53-10-12, FIG 220. ACCOMPLISHED A BHEC INSPECTION OF THE FASTENER HOLE IAW NTM PT6 51-10-01.

Part: SKIN — DAMAGED (ZONE 200) · airframe 39,160 hrs · 27,998 cycles

EXTERIOR UPPER FUSELAGE SKIN HAS STATIC DISCHARGE BETWEEN FRAME 36 AND FRAME 37; STRINGER 1 R STRINGER 2 R. REMOVED DAMAGE BY WAY OF DRILLING A 5/32 HOLE IAW SRM 53-10-12; FIG 220. ACCOMPLISHED A BHEC INSPECTION OF THE DRILLED HOLE IAW NTM PT 6 51-10-01. INSTALLED RIVET IAW SRM 53-10-12; FIG 220.

Part: SKIN — DAMAGED (ZONE 200) · airframe 39,160 hrs · 27,998 cycles

EXTERIOR UPPER FUSELAGE SPLICE DOUBLER HAS STATIC DISCHARGE AT FRAME 33 BETWEEN STRINGER 1 R AND 2 R. REMOVED AND REPLACED RIVET IAW SRM 53-10-12; FIG 220. ACCOMPLISHED A BHEC INSPECTION OF THE FASTENER HOLE IAW NTM PT6 51-10-01.

Part: SKIN — DAMAGED (ZONE 200) · airframe 39,160 hrs · 27,998 cycles

EXTERIOR UPPER FUSELAGE SKIN HAS STATIC DISCHARGE BETWEEN FRAME 40/41 AND FRAME 42; STRINGER 2 R AND STRINGER 3 R. REMOVED AND REPLACED RIVET IAW SRM 53-10-12; FIG 220. ACCOMPLISHED A BHEC INSPECTION OF THE FASTENER HOLE IAW NTM PT6 51-10-01.

Part: STIFFENER — CRACKED (ZONE 300) · airframe 39,160 hrs · 27,998 cycles

REAR STIFFENER BETWEEN THE TRAILING EDGE OF RIB 7 & THE RIB ON THE RIGHT SIDE OF THE VERTICAL STAB IS CRACKED. REMOVED & REPLACED STIFFENER IAW SRM 51-40-21 & 51-72-10.

Part: SKIN — CORRODED (ZONE 500) · corrosion level 2 · airframe 39,160 hrs · 27,998 cycles

LEFT WING FUEL TANK DOOR CUT OUT BETWEEN RIB 25 AND RIB 26 IS CORRODED. REMOVED CORROSION AND CHECKED LIMITS. ORIGINAL THICKNESS 0.276. REMOVED MATERIAL 0.003. REMAINING THICKNESS 0.273 AND IS FOUND TO BE WITHIN LIMITS IAW SRM 57-20-12, PG 68, FIG 7A AND SRM 57-20-12, PARA A-1 (G), FIG 201. ACCOMPLISHED PFPI IAW A310 NTM 51-90-11. ALODINED AND PRIMED IAW SRM 51-20-10 AND SRM 57-20-12; PG 201B; PARA 3(A).

Part: SKIN — DAMAGED (ZONE 200) · airframe 39,160 hrs · 27,998 cycles

EXTERIOR UPPER FUSELAGE SKIN HAS STATIC DISCHARGE AT FRAMES 26/32; STRINGER 1 R AND 2 R. REMOVED AND REPLACED RIVET IAW SRM 53-10-12; FIG 220. ACCOMPLISHED A BHEC INSPECTION OF THE FASTENER HOLE IAW NTM PT6 51-10-01.

Part: SKIN — CHAFED (ZONE 200) · airframe 39,160 hrs · 27,998 cycles

LEFT OVERWING EMERGENCY EXIT; INBD UPPER FWD & AFT CORNER CHAFE STRIPS ARE MISSING WITH SKIN CHAFED. REMOVED COVER PLATE IAW SRM 51-40-21. LOCATED & DRILLED COVER PLATE IAW SRM 51-40-21. ALODINED COVER PLATE IAW SRM 51-21-10. INSTALLED 3 EA CHAFE STRIPS IAW CMM 52-23-11.

Part: FLOOR PANEL — CRACKED (ZONE 200) · airframe 39,160 hrs · 27,998 cycles

MAIN CABIN FLOOR PANEL CF AT FRAME C 11 A, LOWER SURFACE IS CRACKED. REPAIRED AS REQUIRED IAW ARM 53-10-20; FIG 202.

Part: DOOR FRAME — CRACKED (FUSELAGE) · airframe 39,160 hrs · 27,998 cycles

THE DOOR FRAME FITTING IS CRACKED, AFT CARGO LOWER FWD CORNER. COMPLIED WITH FEDEX E.A. 6-5310-123645.

Part: DOOR — DENTED (APU BAY) · airframe 39,160 hrs · 27,998 cycles

RIGHT APU COMPARTMENT DOOR HAS A DENT ON THE FWD PORTION OF THE EXTERNAL SKIN. FABRICATED REPAIR IAW SRM 52-41-00. ALODINED IAW SRM 51-21-10. PRIMED IAW SRM 51-23-10. INSTALLED REPAIR IAW SRM 51-40-20 AND SRM 52-42-11.

Part: RETAINER — CORRODED (EMERGENCY EXIT) · airframe 39,160 hrs · 27,998 cycles

RIGHT OVER WING EMERGENCY EXIT; LOWER SEAL RETAINER OUTBD SURFACE HAS CORROSION AROUND THE BOLT HEADS. RECLEANED THE LOWER SEAL RETAINERS & HARDWARE. NO DEFECTS NOTED.

Part: SEAT TRACK — CRACKED (FUSELAGE) · airframe 39,160 hrs · 27,998 cycles

MAIN CABIN SEAT TRACK AT C 17; RBL 38 IS CRACKED. REMOVED AND REPLACED THE SEAT TRACK IAW SRM 51-40-21; PARA 7 & SRM 51-40-44.

Part: BONDING STRAP — CORRODED (EMERGENCY EXIT) · airframe 39,160 hrs · 27,998 cycles

LEFT OVERWING EMERGENCY EXIT, BONDING STRAPS AND ATTACHING SCREWS (2 EA) ARE CORRODED. REMOVED ANGLE IAW SRM 51-40-01. FABBED ANGLE IAW DWG A52271077, ISSUE "A". AODINED & PRIMED ANGLE IAW SRM 51-21-10. INSTALLED ANGLE & BONDING WIRE IAW SRM 51-40-21.

Part: RETAINER — CORRODED (EMERGENCY EXIT) · airframe 39,160 hrs · 27,998 cycles

RIGHT OVERWING EMERGENCY EXIT, LOWER SEAL RETAINER OUTBD HAS THREE TEE FITTINGS WITH LIGHT CORROSION. REMOVED LOWER SEAL RETAINER TO FOM. IAW SRM 51-40-20. REMOVED THE LOWER CHANNEL AND FOUND IT TO BE CORRODED BEYOND LIMITS IAW SRM 53-10-00. RECEIVED NEW LOWER CHANNEL, INSTALLED NEW LOWER CHANNEL IAW SRM 51-40-02. REMOVED & CLEANED TEE FITTING ; NO DEFECTS NOTED. RE-INSTALLED LOWER SEAL RETAINER IAW SRM 57-40-02. RE-INSTALLED TEE FITTINGS IAW SRM 51-40-02. REMOVED & RE-INSTALLED DOOR IAW AMM 52- 23-11-4.

Part: RETAINER — CORRODED (DOOR SEAL) · airframe 39,160 hrs · 27,998 cycles

LEFT OVERWING EMERGENCY EXIT, LOWER SEAL RETAINER OUTBD SURFACE HAS CORROSION AROUND THE FASTENERS ON 3 EA SECTIONS. REMOVED THE LOWER SEAL RETAINERS IAW SRM 51-40-21. REMOVED LOWER CHANNEL IAW SRM 51-40-21. REMOVED THE CORROSION IAW SRM 51-74-10. ALODINED IAW SRM 51-21-10. PRIMED IAW SRM 51-21-10. RCEIVED & INSTALLED THE LOWER CHANNEL IAW SRM 51-40-01.

Part: BONDING STRAP — CORRODED (RT OVERWING EXIT) · airframe 39,160 hrs · 27,998 cycles

RIGHT OVERWING EMERGENCY EXIT, LOWER 2 EA BONDING STRAP SCREWS AND BONDING STRAPS HAVE CORROSION. CLEANED AREA IAW SRM 51-73-10. NO MATERIAL LOSS. ATTACHED THE BONDING STRAP TO BONDING POINT IAW SRM 51-40-21. BONDING CHECK GOOD IAW AMM 20-28-11-0.

Part: ATTACH ANGLE — CORRODED (DOOR SEAL) · airframe 39,160 hrs · 27,998 cycles

LEFT OVERWING EMERGENCY EXIT, LOWER SEAL RETAINER OUTBD, 3 EA TEES AND ATTACH ANGLES HAVE CORROSION. CENTER PROFILE ANGLE BEYOND LIMITS IAW SRM 51-40-01. CLEANED 2 EA PROFILE ANGLES IAW SRM 52-53-11. NO DEFECTS NOTED. FABBED A NEW PROFILE ANGLE IAW DWG A52241063. INSTALLED NEW PROFILE ANGLE IAW SRM 51-40-02.

Part: FITTING — CRACKED (CARGO DOOR FRAME) · airframe 39,160 hrs · 27,998 cycles

THE DOOR FRAME FITTING IS CRACKED AT THE AFT CARGO DOOR LOWER AFT CORNER. COMPLIED WITH EA 6-5310-123646.

Part: FITTING — CRACKED (RT WING TE FLAP) · airframe 39,160 hrs · 27,998 cycles

RIGHT WING INBOARD FLAP; OUTBOARD END; FOLLOW UP GUIDE FITTING IS CRACKED. REMOVED GUIDE FITTING IAW SRM 51-40-02; PG 1 & DRILLED NEW FITTING 1AW SRM 51-40-40 PG 2. INSTALLED NEW FITTING IAW SRM 51-40-02; PG 1.

Part: SUPPORT — BROKEN (NR 2 NACELLE) · airframe 39,160 hrs · 27,998 cycles

NR 2 ENGINE NOSE COWL ANTI-ICE PICCOLO TUBE SUPPORT LINK AT THE 12 O'CLOCK POSITION IS BROKEN & DISCONNECTED. REMOVED & REPLACED THE NR 2 NOSE COWL IAW AMM 71-11-00-04.

Part: FITTING — CRACKED (LT WING TE FLAP) · airframe 39,160 hrs · 27,998 cycles

LEFT WING INBOARD FLAP OUTBOARD END; FOLLOW UP GUIDE FITTING IS CRACKED. REMOVED & INSTALLED FITTING IAW SRM 51-40-30. LOCATED & DRILLED IAW SRM 51-40-40. PAINTED IAW SRM 51-23-10.

Part: SUPPORT — BROKEN (NR 1 NACELLE) · airframe 39,160 hrs · 27,998 cycles

NR 1 ENGINE NOSE COWL ANTI-ICE PICCOLO TUBE SUPPORT LINKS AT THE 7; 12 & 2 O'CLOCK POSITIONS ARE BROKEN & DISCONNECTED. (TOTAL 8 LINKS) REMOVED & REPLACED THE NR 1 ENGINE NOSE COWL IAW AMM 71-11-00-4.

Part: DOOR — OUT OF SEQUENCE (NLG) · airframe 39,160 hrs · 27,998 cycles

THERE ARE TIRE ROTATION MARKS ON THE INNER SURFACE OF BOTH NLG MAIN DOORS. SUSPECT NLG DOORS ARE OUT OF SEQUENCE. GEAR RETRACTION REQUIRED FOR FINAL SIGN OFF. TIRE ROTATION MARKS REMOVED DURING ACFT WHEEL WELL / LANDING GEAR WASH REF WORK CARD 40C0002. PERFORMED NLG & MLG RETRACTION TEST REF AMM 32-31-00, NO DISCREPANCIES NOTED. PERFORMED FREE FALL TEST REF AMM 32-33-00, NO DISCREPANCIES NOTED.

Part: PUMP — LEAKING (HYD SYSTEM) · airframe 39,068 hrs · 27,929 cycles

WHILE EN ROUTE AT FL370 GOT ECAM WARNING FOR GREEN HYD RESV LOW. RESV QUANTITY ECAM WAS IN THE RED. PRESSURE INDICATED ZERO. DIVERTED TO KPHX. GEAR EXTENDED BY GRAVITY. REMOVED AND REPLACED GREEN YELLOW POWER TRANSFER UNIT PER MM 29-23-11-4. REQUIRES BLEEDING, OPS AND LK CHECK PER STEP D.10. REMOVED AND REPLACED NR 1 ENG GREEN SYSTEM HYDRAULIC PUMP PER M/M 29-11-32-4 AND PUMP CASE DRAIN FILTER PER M/M 29-11-36-4 LEAK AND OP'S CHECK GOOD.

Part: PTU — LEAKING (HYD SYSTEM) · airframe 39,068 hrs · 27,929 cycles

WHILE ENROUTE AT FL370 GOT ECAM WARNING FOR GREEN HYD RESV LOW RESV QUANTITY ON ECAM WAS IN THE RED. PRESSURE INDICATED ZERO. DIVERTED TO KPHX. GEAR EXTENDED BY GRAVITY. REMOVED AND REPLACED GREEN YELLOW POWER TRANSFER UNIT PER MM 29-23-11-4. REQUIRES BLEEDING, OPS AND LK CHECK PER STEP D.10. REMOVED AND REPLACED NR 1 ENG GREEN SYSTEM HYDRAULIC PUMP PER M/M 29-11-32-4 AND PUMP CASE DRAIN FILTER PER M/M 29-11-36-4 LEAK AND OP'S CHECK GOOD.

Part: BLEED VALVE — FAULTED (NR 2) · airframe 38,889 hrs · 27,821 cycles

AT FL 370 BLEED VALVE NR 2 FAULTED. TURNED IT OFF AND OPENED BLEED CROSS FEED. APPROX 1 MIN LATER BLEED VALVE NR 1 FAULTED. TURNED IT OFF, TRIED RESETTING AND WOULD NOT RESET. DURING DESCENT, NR 1 BLEED VALVE DID RESET. BY 10,000 BOTH BLEED VALVES RESET AND WORKED NORMALLY. CHECKED PNEUMATIC CONTROL SYSTEM IN REF TO AMM 21-31-00-5-01. NO FAULTS WHEN BITE CHECKING EITHER PNEUMATIC SYSTEM CONTROLLER. ALSO, AFTER DOING CHECKS ON MAINT PANEL NO FAULTS WERE NOTED AND ALL SYSTEMS CHECKED AS WORKING NORMALLY.

Part: LOCK — UNKNOWN (NR 2 ENGINE) · airframe 37,775 hrs · 27,082 cycles

DURING LANDING AT KBUR, THRUST REVERSER LEVERS EXTREMELY STIFF, F/O LOWERED REVERSER OR ATTEMPTED TO STOW AND LEVERS WERE SO STIFF COULD NOT STOW REVERSERS. ALL BETWEEN 80-60 KTS, AT ABOUT 65 KTS CAPT COMMANDED F/O TO MOVE HAND FROM THROTTLE AND POUNDED AND SLAMMED REVERSERS OUT PRIOR TO GETTING REVERSERS STOWED NR 2 ENGINE COMPRESSOR STALLED AND FLAMED OUT. EXCESSIVE FORCE TO DISCONNECT AUTO BRAKES. ACCOMPLISHED HPT AND COMBUSTION CHAMBER BORESCOPE. REMOVED & REPLACED SYNCHRONOUS SHAFT LOCK ASSY. RT SIDE PER AMM 78-31-41-4. OP'S CK OK.

Part: PRESSURE SWITCH — STUCK (FIRE BOTTLE) · airframe 36,944 hrs · 26,609 cycles

FINAL 1 HOUR OF FLIGHT GOT ECAM WARNING SMOKE DISH AGENT 2 IN AMBER. AGENT 2 DISCH IN BLUE COLOR. NO INDICATION OF LOWER CARGO SMOKE ON ECAM OR OVERHEAT PRIOR TO ECAM ALERT. FOUND PRESSURE SWITCH ON BOTTLE NR 1 (5WM) BAD, STUCK OPEN. BOTH SQUIBS FOR BOTTLE NR 1 TEST NORMAL. REMOVED AND REPLACED NR 1 LOWER DECK CARGO FIRE EXTINGUISHER BOTTLE PER M/M 26-23-11-4-01. CARGO FIRE PROTECTION SYSTEM OPS CHECKS NORMAL PER M/M 26-23-00-5-01. R/I FROM FACT PREMATURE REMOVAL/INSTALLATION. CREW DECLARED EMERGENCY.

Part: STRUCTURE — CRACKED (FUSELAGE) · airframe 36,927 hrs · 26,602 cycles

COMPLY WITH AGING 9-AGING-INSP. CENTER MDCC-CABIN FLOOR TRACK FLAP CRACKED NEXT TO FR C54.2 Y=-1959 (RT). P/N R532H141320100. REPLACED PER SRM 51-72-10 AND SRM 51-40-21, REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS MAJOR.

Part: SEAT TRACK — CRACKED (FUSELAGE) · airframe 36,927 hrs · 26,602 cycles

COMPLY WITH AGING 9-AGING-INSP. AFT MDCC -CABIN FLOOR TRACK CRACKED BETWEEN FR C59 FR C62 Y=-1959. P/N A5327478621200. REPLACED PER SRM 51-72-10 AND 51-40-21, REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS MAJOR.

Part: WEDGE — DAMAGED (TE FLAP) · airframe 36,927 hrs · 26,602 cycles

COMPLY WITH AGING 9-AGING-INSP REV NR POS PT1, PREVIOUS REPAIR FOUND LOCATED ON THE LT OUTBD FLAP T/E WEDGE UPPER SURFACE OUTBD OF NUMBER THREE FLAP TRACK, WS 847-877. EXISTING REPAIR EVALUATED AND FOUND NOT TO CONFORM TO AN SRM REPAIR NEW REPAIR ACCOMPLISHED PER SRM 57-53-12 FIG. 208 REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS "MAJOR"

Part: SKIN — DAMAGED (WING) · airframe 36,927 hrs · 26,602 cycles

PREVIOUS REPAIR FOUND LOCATED ON THE LT WING UPPER SURFACE OUTBD OF OUTBD FLAP, WS 1789-1800. EXISTING REPAIR EVALUATED AND FOUND NOT TO CONFORM TO AN SRM REPAIR NEW REPAIR ACCOMPLISHED PER FEDEX E.A.6-5710-97881 REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS "MAJOR"

Part: NONE — NONE (NONE) · airframe 36,927 hrs · 26,602 cycles

COMPLY WITH AGING 9-AGING-INSP REV NR POS PT1, PREVIOUS REPAIR FOUND LOCATED ON THE LT INBD FLAP T/E WEDGE UPPER SURFACE, WS 103-116. REPAIR REQUIRES EVALUATION FOR MAJOR MINOR DETERMINATION AND IF THE REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. REPLACED TRAILING EDGE PER SRM 51-72-10 REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS "MAJOR"

Part: NONE — NONE (NONE) · airframe 36,927 hrs · 26,602 cycles

COMPLY WITH AGING 9-AGING-INSP REV NR POS PT1, PREVIOUS REPAIR FOUND LOCATED ON THE LT OUTBD FLAP LOWER SURFACE, OUTBD OF NUMBER THREE FLAP TRACK. REPAIR REQUIRES EVALUATION FOR MAJOR MINOR DETERMINATION AND IF THE REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA.

Part: NONE — NONE (NONE) · airframe 36,927 hrs · 26,602 cycles

COMPLY WITH AGING 9-AGING-INSP REV NR POS PT1, PREVIOUS REPAIR FOUND LOCATED LT FS 3938-3956, FS 73 AND STR 53-54, EXTERNAL DOUBLER. REPAIR REQUIRES EVALUATION FOR MAJOR MINOR DETERMINATION AND IF THE REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA.

Part: WEDGE — DAMAGED (TE FLAPS) · airframe 36,927 hrs · 26,602 cycles

PREVIOUS REPAIR FOUND LOCATED ON THE LT OUTBD FLAP T/E WEDGE UPPER SURFACE OUTBD OF NUMBER FIVE FLAP TRACK, WS 1468-1484. EXISTING REPAIR EVALUATED AND FOUND NOT TO CONFORM TO AN SRM REPAIR NEW REPAIR ACCOMPLISHED PER SRM 57-53-12 FIG. 208 REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS "MAJOR"

Part: NONE — NONE (NONE) · airframe 36,927 hrs · 26,602 cycles

COMPLY WITH AGING 9-AGING-INSP REV NR POS PT1, PREVIOUS REPAIR FOUND LOCATED ON LEFT SIDE MCD SEAT TRACK FS 1923-2029, FS 35-37 AND YD95. 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 53-10-16 FIG. 208 SHEET 1 REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS "MAJOR"

Part: NONE — NONE (NONE) · airframe 36,927 hrs · 26,602 cycles

COMPLY WITH AGING 9-AGING-INSP REV NR POS PT1, PREVIOUS REPAIR FOUND LOCATED ON THE LT INBD FLAP T/E WEDGE UPPER AND LOWER SURFACE, WS 40-103. REPAIR REQUIRES EVALUATION FOR MAJOR MINOR DETERMINATION AND IF THE REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. REPLACED TRAILING EDGE PER SRM 51-72-10 REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS "MAJOR"

Part: NONE — NONE (NONE) · airframe 36,927 hrs · 26,602 cycles

COMPLY WITH AGING 9-AGING-INSP REV NR POS PT1, PREVIOUS REPAIR FOUND LOCATED ON RIGHT SIDE MCD FLOORBEAM FS 1870, FS 34 AND Y56 TO Y79. 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 53-10-15 FIG.201 SHEET 2 REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS "MAJOR"

Part: NONE — NONE (NONE) · airframe 36,927 hrs · 26,602 cycles

COMPLY WITH AGING 9-AGING-INSP REV NR POS PT1, PREVIOUS REPAIR FOUND LOCATED ON THE RT OUTBD FLAP T/E WEDGE UPPER SURFACE OUTBD OF NUMBER THREE FLAP TRACK, WS 871-893. REPAIR EVALUATED AND FOUND NOT TO CONFORM TO AN EXISTING SRM REPAIR .NEW REPAIR ACCOMPLISHED PER SRM 57-53-12 FIG. 208 SHEET 2 REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS "MAJOR"

Part: REPAIR — MISINSTALLED (LT PYLON) · airframe 36,927 hrs · 26,602 cycles

COMPLY WITH AGING 9-AGING-INSP REV NR POS PT1, PREVIOUS REPAIR FOUND LOCATED ON THE LT WING LOWER SURFACE OUTBD OF PYLON. EXISTING REPAIR EVALUATED AND FOUND NOT TO CONFORM TO AN SRM REPAIR NEW REPAIR ACCOMPLISHED PER E.A.6-5710-99711 REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS "MAJOR"

Part: NONE — NONE (NONE) · airframe 36,927 hrs · 26,602 cycles

COMPLY WITH AGING 9-AGING-INSP REV NR POS PT1, PREVIOUS REPAIR FOUND LOCATED ON THE L1 DOOR UPPER AFT CORNER, EXTERNAL DOUBLER. REPAIR REQUIRES EVALUATION FOR MAJOR MINOR DETERMINATION AND IF THE REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA.

Part: REPAIR — MISINSTALLED (FUSLEAGE) · airframe 36,927 hrs · 26,602 cycles

PREVIOUS REPAIR FOUND LOCATED ON THE LT HORIZONTAL STABILIZER FRONT SPAR CAP HS 467-478, RIB 13-14. EXISTING REPAIR EVALUATED AND FOUND NOT TO CONFORM TO AN SRM REPAIR NEW REPAIR ACCOMPLISHED PER SRM 55-11-21 REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS "MAJOR"

Part: REPAIR — MISINSTALLED (FUSELAGE) · airframe 36,927 hrs · 26,602 cycles

PREVIOUS REPAIR FOUND LOCATED ON RT FUSELAGE CROWN FS 1043-1067, FS 11A-12. EXISTING REPAIR EVALUATED AND FOUND NOT TO CONFORM TO AN SRM.

Part: NONE — NONE (NONE) · airframe 36,927 hrs · 26,602 cycles

COMPLY WITH AGING 9-AGING-INSP REV NR POS PT1, PREVIOUS REPAIR FOUND LOCATED LT FS 1067-1091, FS 12-12A, FLUSH REPAIR. REPAIR REQUIRES EVALUATION FOR MAJOR MINOR DETERMINATION AND IF THE REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA.

Part: NONE — NONE (NONE) · airframe 36,927 hrs · 26,602 cycles

COMPLY WITH AGING 9-AGING-INSP REV NR POS PT1, PREVIOUS REPAIR FOUND LOCATED ON THE LT INBD FLAP T/E WEDGE LOWER OUTBD SURFACE, WS 337-427. REPAIR REQUIRES EVALUATION FOR MAJOR MINOR DETERMINATION AND IF THE REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. REPLACED TRAILING EDGE PER SRM 51-72-10 REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS "MAJOR"

Part: PANEL — DAMAGED (HORIZONTAL STAB) · airframe 36,927 hrs · 26,602 cycles

PREVIOUS REPAIR FOUND LOCATED ON THE LT HORIZONTAL STABILIZER LEADING EDGE PANEL 331BB, FLUSH REPAIR ON OUTBD LEADING EDGE. EXISTING REPAIR EVALUATED AND FOUND NOT TO CONFORM TO AN SRM REPAIR NEW REPAIR ACCOMPLISHED PER SRM 55-12-12 FIG. 203 REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS "MAJOR"

Part: PANEL — DAMAGED (HORIZONTAL STAB) · airframe 36,927 hrs · 26,602 cycles

PREVIOUS REPAIR FOUND LOCATED ON THE LT HORIZONTAL STABILIZER LEADING EDGE PANEL 331CB, FLUSH REPAIR ON OUTBD LEADING EDGE. EXISTING REPAIR EVALUATED AND FOUND NOT TO CONFORM TO AN SRM REPAIR NEW REPAIR ACCOMPLISHED PER SRM 55-12-12 REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS "MAJOR"

Part: SPAR CAP — DAMAGED (HORIZONTAL STAB) · airframe 36,927 hrs · 26,602 cycles

PREVIOUS REPAIR FOUND LOCATED ON THE LT HORIZONTAL STABILIZER FRONT SPAR CAP HS 52-98, RIB 4. EXISTING REPAIR EVALUATED AND FOUND NOT TO CONFORM TO AN EXISTING SRM REPAIR NEW REPAIR ACCOMPLISHED PER SRM 55-11-21 FIG. 206 REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS "MAJOR"

Part: NONE — NONE (NONE) · airframe 36,927 hrs · 26,602 cycles

PREVIOUS REPAIR FOUND LOCATED RT FS 1605-1658, FS 23-24, EXTERNAL DOUBLER LOCATED ON DOOR 134AR. EXISTING REPAIR EVALUATED AND FOUND NOT TO CONFORM TO AN SRM REPAIR NEW REPAIR ACCOMPLISHED PER SRM 52-41-15 FIG. 201 SHEET 1 REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS "MAJOR"

Part: NONE — NONE (NONE) · airframe 36,927 hrs · 26,602 cycles

COMPLY WITH AGING 9-AGING-INSP REV NR POS PT1, PREVIOUS REPAIR FOUND LOCATED ON THE RT OUTBD FLAP T/E WEDGE UPPER SURFACE INBD OF NUMBER THREE FLAP TRACK, WS 713-728. EXISTING REPAIR EVALUATED AND FOUND NOT TO CONFORM TO EXISTING REPAIR OF SRM 57-53-12 FIG. 208 SHEET 2 NEW REPAIR ACCOMPLISHED PER SRM 57-53-12 FIG. 208 SHEET 2 REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS MAJOR.

Part: NONE — NONE (NONE) · airframe 36,927 hrs · 26,602 cycles

COMPLY WITH AGING 9-AGING-INSP REV NR POS PT1, PREVIOUS REPAIR FOUND LOCATED ON THE RT OUTBD FLAP T/E WEDGE UPPER SURFACE OUTBD OF NUMBER THREE FLAP TRACK, WS 913-933. REPAIR EVALUATED AND FOUND NOT TO CONFORM TO AN EXISTING SRM REPAIR . NEW REPAIR ACCOMPLISHED PER FEDEX E.A. 6-5710-99706 REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS "MAJOR"

Part: NONE — NONE (NONE) · airframe 36,927 hrs · 26,602 cycles

PREVIOUS REPAIR FOUND LOCATED LT FS 3673-3673, FS 68 AND STR 34, EXTERNAL DOUBLER. REPAIR EVALUATED AND FOUND NOT TO CONFORM TO AN EXISTING SRM REPAIR NEW REPAIR ACCOMPLISHED PER SRM 53-10-12 FIG. 225 REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS "MAJOR"

Part: NONE — NONE (NONE) · airframe 36,927 hrs · 26,602 cycles

COMPLY WITH AGING 9-AGING-INSP, PREVIOUS REPAIR FOUND LOCATED RT FS 1340-1370, FS 18 AND STR 40-41, EXTERNAL 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 SRM REPAIR NEW REPAIR ACCOMPLISHED PER SRM 53-10-12 FIG.225 REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS "MAJOR"

Part: REPAIR — MISINSTALLED · airframe 36,927 hrs · 26,602 cycles

COMPLY WITH AGING 9-AGING-INSP REV NR POS PT1, PREVIOUS REPAIR FOUND LOCATED ON RT FLOOR SUPPORT STRUCTURE ABOVE DEPRESSURIZATION VALVE FS 1091, FS 12A. 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 53-12-14 FIG 2 SHEET 1. INSTALLED NEW NEW DOUBLER ITEM 80 PER SRM 51-72-10. REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS "MINOR".

Part: NONE — NONE (NONE) · airframe 36,927 hrs · 26,602 cycles

COMPLY WITH AGING 9-AGING-INSP REV NR POS PT1, PREVIOUS REPAIR FOUND LOCATED LT FS 3779-3832, FS 70-71 AND STR 27-28, EXTERNAL DOUBLER. REPAIR REQUIRES EVALUATION FOR MAJOR MINOR DETERMINATION AND IF THE REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA.

Part: REPAIR — MISINSTALLED (HORIZONTAL STAB) · airframe 36,927 hrs · 26,602 cycles

PREVIOUS REPAIR FOUND LOCATED ON THE RT NUMBER ONE SPOILER UPPER SURFACE. EXISTING REPAIR EVALUATED AND FOUND NOT TO CONFORM TO AN SRM REPAIR NEW REPAIR ACCOMPLISHED PER SRM 55-12-12 FIG. 203 REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS "MAJOR"

Part: NONE — NONE (NONE) · airframe 36,927 hrs · 26,602 cycles

COMPLY WITH AGING 9-AGING-INSP REV NR POS PT1, PREVIOUS REPAIR FOUND LOCATED ON THE RT FLAP VANE LOWER SURFACE INBD OF NUMBER TWO FLAP TRACK. 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 EXISTING SRM REPAIR NEW REPAIR ACCOMPLSHED IN ACCORDANCE W/ FEDEX E.A. 6-5740-97883 REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS "MAJOR"

Part: NONE — NONE (NONE) · airframe 36,927 hrs · 26,602 cycles

COMPLY WITH AGING 9-AGING-INSP REV NR POS PT1, PREVIOUS REPAIR FOUND LOCATED ON THE LT AILERON LOWER SURFACE WS 444-459. REPAIR REQUIRES EVALUATION FOR MAJOR MINOR DETERMINATION AND IF THE REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA.

Part: REPAIR — UNKNOWN · airframe 36,927 hrs · 26,602 cycles

COMPLY WITH AGING 9-AGING-INSP REV NR POS PT1, PREVIOUS REPAIR FOUND LOCATED ON THE LT INBD FLAP T/E WEDGE UPPER SURFACE, WS 118-170. REPAIR REQUIRES EVALUATION FOR MAJOR MINOR DETERMINATION AND IF THE REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. REPLACED TRAILING EDGE PER SRM 51-72-10 REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS "MAJOR"

Part: SPAR CAP — CORRODED (HORIZONTAL STAB) · airframe 36,927 hrs · 26,602 cycles

PREVIOUS REPAIR FOUND LOCATED ON THE LT HORIZONTAL STABILIZER FRONT SPAR CAP HS 225-267, RIB 8-9. EXISTING REPAIR EVALUATED FOUND PER SRM ,BUT CORROSION WAS FOUND ON THE SURROUNDING AREA OF REPAIR AND NEW REPAIR ACCOMPLISHED PER E.A. 6-5510-97877 REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS "MAJOR"

Part: REPAIR — MISINSTALLED · airframe 36,927 hrs · 26,602 cycles

COMPLY WITH AGING 9-AGING-INSP REV NR POS PT1, PREVIOUS REPAIR FOUND LOCATED ON LEFT SIDE BULK CARGO COMPARTMENT CROSSBEAM FS 3630-3663, FS 67-68 AND Y73. 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 51-72-10, REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS "MAJOR".

Part: NONE — NONE (NONE) · airframe 36,927 hrs · 26,602 cycles

COMPLY WITH AGING 9-AGING-INSP REV NR POS PT1, PREVIOUS REPAIR FOUND LOCATED LT FS 3998-4059, FS 74-75 AND STR 2-5, FLUSH REPAIR. 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 53-18-12 ( FIG. 1 SHEET 1, DETAIL A) AND SRM 53-18-14 (FIG.1 SHEET 3, DETAIL D) AND AIB FAX REF. 942-044699/005/2006 REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS "MAJOR"

Part: NONE — NONE (NONE) · airframe 36,927 hrs · 26,602 cycles

COMPLY WITH AGING 9-AGING-INSP REV NR POS PT1, PREVIOUS REPAIR FOUND LOCATED ON RIGHT SIDE BULK CARGO COMPARTMENT CROSSBEAM FS 3514-3567, FR 65-66 AND Y91. REPAIR REQUIRES EVALUATION FOR MAJOR MINOR DETERMINATION AND IF THE REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. REPLACEMENT OF THE SECTION LONGITUDINAL PER SRM 51-72-10 REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS "MAJOR"

Part: NONE — NONE (NONE) · airframe 36,927 hrs · 26,602 cycles

COMPLY WITH AGING 9-AGING-INSP REV NR POS PT1, PREVIOUS REPAIR FOUND LOCATED ON THE LT INBD FLAP T/E WEDGE UPPER, OUTBD SURFACE, WS 352-385. REPAIR REQUIRES EVALUATION FOR MAJOR MINOR DETERMINATION AND IF THE REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. REPLACED TRAILING EDGE PER SRM 51-72-10 REPAIR EVALUATED PER GMM 6-2-100 AND CLASSIFIED AS "MAJOR"

Part: SKIN — CRACKED (NR 2 PYLON) · airframe 36,620 hrs · 26,426 cycles

RIGHT WING UPPER SURFACE PANEL LANDINGS ABOVE NR 2 PYLON BENT & CRACKED. REMOVED AND REPLACED CLOSING RIB NR 8 IAW DWG A572-45361 AND A310-200 SRM 51-40-21. REMOVED AND REPLACED 2 ANGLE LANDINGS IAW A310-200-40-21.

Part: SKIN — DAMAGED (ZONE 200) · airframe 36,620 hrs · 26,426 cycles

PUNCTURE AND DENT TOP OF CROWN SKIN CENTERLINE ABOVE COCKPIT BETWEEN FR 7 & 8. PUNCTURE APPROX 2 X 7 INCHES JUST LEFT OF A/C CL. COMPLIED WITH EA 6-5330-94475 BY INSTALLING EXTERNAL DOUBLER.

Part: SKIN — DAMAGED (NR 1 SPOILER) · airframe 36,620 hrs · 26,426 cycles

RT WING 1 SPOILER HAS PENETRATION DAMAGE 3" BY 1". REPAIRED NR 1 SPOILER IAW A310-200 SRM 57-70-00 REPAIR.

Part: SKIN — PUNCTURED (FUSELAGE) · airframe 36,620 hrs · 26,426 cycles

PUNCTURE IN SKIN FWD OF FR 22 BETWEEN STR 12 & 13 RIGHT SIDE APPROX 4 X 3.2 INCHES HURRICANE RITA NR 7 REF N00057. REPAIRED IAW EA 6-5330-93419.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 36,620 hrs · 26,426 cycles

SCRATCHES IN SKIN APPROX FR 22-23 RIGHT STR 5-6 APPROX 14 INCHES LONG AREA HURRICANE RITA NR 9 REF N00059. REPAIRED IAW EA 6-5330-94467.

Part: SKIN — PUNCTURED (FUSELAGE) · airframe 36,620 hrs · 26,426 cycles

PUNCTURE & DENT IN SKIN APPROX RT STR 8-10 AT FR 23 PUNCTURE APPROX 11 X 6.5 INCH DENT APPROX 22 X 16 INCH HURRICANE RITA NR 8. REPAIRED IAW EA 6-5330-93417.

Part: SKIN — PUNCTURED (FUSELAGE) · airframe 36,620 hrs · 26,426 cycles

PUNCTURE IN SKIN APPROX FR 34 BETWEEN STR 10-12 RT APPROX 8.5 X 4.3 INCHES HURRICANE RITA NR 11 REF N00061. COMPLIED WITH EA 6-5330-93418.

Part: SKIN — SCRATCHED (NR 2 SLAT) · airframe 36,620 hrs · 26,426 cycles

LT WING NR 2 SLAT UPPER SURFACE HAS SCRATCHES AND A PUNCTURE APPROX 2.7 BY 3.2" (NR 39 HURRICANE RITA) REF N00089. REPAIRED NR 2 SLAT IAW EA 6-5750-94524.

Part: SKIN — DENTED (FUSELAGE) · airframe 36,620 hrs · 26,426 cycles

DEEP DENT AND PUNCTURE TOP OF CROWN SKIN ON BUTT SEAM FS 10 TO 3'" AFT DENT APPROX 14 " LONG AND 10 " WIDE PUNCTURE APPROX 2.60 " LONG DAMAGE AT CROWN C/L (HURRICANE RITA NR 4) REF N00054. REPAIRED AREA IAW EA 6-5330-94744.

Part: TRACK — WORN (RT WING) · airframe 36,620 hrs · 26,426 cycles

RT WING L/E SECTION OB OF TRACK NR 3 HAS 5 WEAR MARKS IN L/E LARGEST .400 IN DIA AND THE DEEPEST .04. ALL WEAR MARKS ARE CIRCULAR AND ARE WITHIN FOUR IN OF EACH OTHER REF N00136. REPLACED SKIN IAW DRW A57244112 AND EA 6-5741-94835.

Part: SKIN — DENTED (BS 67-68) · airframe 36,620 hrs · 26,426 cycles

FOUND DENT/GOUGE ON SKIN BETWEEN FS 67-68 AND STR 15-16 RT (HURRICANE RITA) REF N00084. REPAIRED AREA IAW A310-200 SRM 53-10-12 AND 53-10-14.

Part: SKIN — SCRATCHED (RT WING TE FLAP) · airframe 36,620 hrs · 26,426 cycles

SCARATCHES TO UPPER SURFACE OF RT WING O/B FLAP BETWEEN NR 3 AND NR 4 CANOES NR 36 HURRICANE RITA REF N00086. REPAIRED 3 EA DENTS ON RT O/B FLAP IAW A310-200 SRM 57-53-12 REPAIR NR 11.

Part: COWLING — SCRATCHED (ZONE 400) · airframe 36,620 hrs · 26,426 cycles

NR 2 ENG INLET COWL L/E HAS A 4.8" LONG SCRATCH AT 5:00 POS. REMOVED DAMAGED AREA IAW P&W SRM 54-10-00. PERFORMED HFEC IAW NTM 51-10-08. NO CRACKS NOTED. INSTALLED REPAIR DOUBLER AND FILLER IAW P&W SRM 54-10-00 REPAIR NR 10.

Part: SKIN — SCRATCHED (EMERGENCY EXIT) · airframe 36,620 hrs · 26,426 cycles

RT EMERGENCY EXIT DOOR FWD AND BELOW EXTERNAL HANDLE HAS 1 SCRATCH APPROX 7.7 INCH LONG, 1 DENT/GOUGE APPROX 3.8" LONG, AND 1 DENT/GOUGE APPROX 2.2 BY 3" LONG. BLENDED SCRATCH IAW A310-200 SRM 51-73-10 AND FOUND TO WITHIN LIMITS OF A310-200 SRM 52-20-00. CUTOUT DENT/GOUGED AREAS IAW A310-200 SRM 52-10-00 FIG 206. PERFORMED HFEC IAW NTM 51-10-08. NO CRACKS FOUND. INSTALLED DOUBLER AND FILLER IAW EA 6-5220-94441. WORK DOCUMENTED ON NRC N00067

Part: SKIN — SCRATCHED (ZONE 200) · airframe 36,620 hrs · 26,426 cycles

FUSELAGE EXTERIOR SKIN AT FS 16 RT STRINGERS 7-8 HAS SCRATCHES APPROX 1.8" LONG. REMOVED DAMAGED SECTION OF SKIN IAW A310-200 SRM 53-12-12 FIG 202. PERFORMED HFEC IAW NTM 51-10-08. NO CRACKS NOTED. INSTALLED FILLER AND DOUBLER IAW A310-200 SRM 53-12-12 FIG. 202. WORK DOCUMENTED ON NRC N00056.

Part: STRUCTURE — DAMAGED (THRUST REVERSER) · airframe 36,620 hrs · 26,426 cycles

NR 2 ENGINE IB TR AT 9:00 POS HAS COMPOSITE DAMAGE APPROX 3.8" LONG. INSTALLED EXTERNAL METAL DOUBLER IAW EA 6-5430-94492.

Part: FRAME — PUNCTURED (ZONE 200, FR44) · airframe 36,620 hrs · 26,426 cycles

FRAME 44 BETWEEN RT STRINGERS 6 AND 7 HAS PUNCTURED DAMAGE APPROX 1.00 INCH LENGTH WITH DEEP SCRATCHES. DRILLED 0.75 INCH HOLE TO REMOVE DAMAGE. DEBURRED HOLE. NDT FOR CRACKS. NO CRACKS NOTED. ALODINED AND PRIMED AREA. ALL WORK PERFORMED IAW EA 6-5310-93421 AND DOCUMENTED ON NRC N00109.

Part: SKIN — DAMAGED (ZONE 200) · airframe 36,620 hrs · 26,426 cycles

PUNCTURE, DENT, AND GOUGES IN SKIN AT FR 46 RT STRINGERS 7-9. DAMAGE AREA APPROX 11.5 INCH X 7 INCH. CUT OUT DAMAGED AREA TO SKING ANS STRINGER IAW A310-200 SRM 53-10-12 AND 53-10-14. PERFORMED HFEC IAW NTM 51-10-08. NO CRACKS NOTED. SPLICED STRINGERS IAW A310-200 SRM 53-10-14. INSTALLED SKIN DOUBLER IAW A310-200 SRM 53-10-12.

Part: SKIN — DAMAGED (ZONE 200) · airframe 36,620 hrs · 26,426 cycles

2 GOUGES IN UPPER EXTERIOR FUSELAGE SKIN AT FR61 BETWEEN RT STRINGERS 3-4. CUT OUT DAMAGED AREA OF SKIN IAW A310-200 SRM 53-27-00. PERFORMED HFEC IAW NTM 51-10-08. NO CRACKS NOTED. INSTALLED DOUBLER REPAIR IAW A310-200 SRM 53-10-12 FIG. 228.

Part: SKIN — DAMAGED (ZONE 200) · airframe 36,620 hrs · 26,426 cycles

TWO DENTS AT FR 24 JUST BELOW RT STRINGERS 15 AND 16. CUT OUT DAMAGED SECTION IAW SRM 53-27-00. PERFORMED HFEC IAW NTM 51-10-08. INSTALLED INTERNAL DOUBLER AND FILLER IAW SRM 53-10-12 FIG 229 AND 53-10-14 FIG 201.

Part: SKIN — DAMAGED (ZONE 200) · airframe 36,620 hrs · 26,426 cycles

2 DENTS AT FR 24 JUST BELOW RT STRINGERS 15 AND 16. CUT OUT DAMAGED SECTION IAW SRM 53-27-00. PERFORMED HFEC IAW NTM 51-10-08. INSTALLED INTERNAL DOUBLER AND FILLER IAW SRM 53-10-12 FIG 229 AND 53-10-14 FIG 201.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 36,620 hrs · 26,426 cycles

UPPER FUSELAGE EXTERIOR SKIN BETWEEN FS 55-56 RT STGR 5 HAS MULTIPLE MINOR SCRATCHED REF N00099. COMPLIED WITH EA 6-5330-94440.

Part: PANEL — CRACKED (RT WING) · airframe 36,620 hrs · 26,426 cycles

RT WING UPPER LE PANEL 6-7830-7-5007-402 HAS 1 EA CRACK APPROX 3.5" LONG ON IB LE REF N00123. REPAIRED APPROX 3.5 CRACK ON RT WING UPPER LE PNL 6-7830-7-5007-402 USING EPOXY RESIN AND GLASS OVERLAY IAW A310 SRM 51-77-11 PAR 4D.

Part: SKIN — GOUGED (FUSELAGE) · airframe 36,620 hrs · 26,426 cycles

FOUND ACCESS DOOR 134AR HAS 2 EA GOUGES IN SKIN REF N00122. REPAIRED IAW SRM 51-71-30. HFEC PER NTM 51-10-08. DAMAGE REMOVED, NO FURTHER DAMAGE NOTED RESTORED PROTECTIVE COATING IAW SRM 51-23-20 REF N00122.

Part: SKIN — DENTED (FUSELAGE) · airframe 36,620 hrs · 26,426 cycles

SMALL DENT LT SIDE OF FUSELAGE ABOVE CAPT FIXED WINDOW 1" FWD OF FS 9 DENT .8" LONG AND APPROX 0.150" DEEP REF N00052. CUTOUT DAMAGED AREA AND REPAIRED IAW A310 SRM 53-11-12 AND 53-27-00. REPROTECTED REPAIRED AREA IAW A310 SRM 51-21-00 AND 51-23-00.

Part: SKIN — GOUGED (FUSELAGE) · airframe 36,620 hrs · 26,426 cycles

DEEP GOUGE W/DENT TOP OF CROWN SKIN AT FS 14 Y = 12 RT APPROX 3.5" LONG AND 2 INCH WIDE AND 0.25 DEEP REF N00055. REMOVED DAMAGE FABBED DOUBLER ALODINE PRIME AND PAINTED AND INSTALLED DOUBLER IAW A310 SRM 53-12-12 NDT FOR CRACKS IAW NTM 51-10-08, NONE NOTED.

Part: SKIN — GOUGED (NR 2 SLAT) · airframe 36,620 hrs · 26,426 cycles

RT WING NR 2 SLAT IB TE HAS DENT AND GOUGE APPROX 4.7" LONG UPPER END (HURRICANE RITA NR 31) REF N00081. COMPLIED WITH EA 6-5750-93420

Part: WIRE — DAMAGED (NR 2 BATTERY) · airframe 36,456 hrs · 26,324 cycles

NR 2 BATTERY OVERHEATED DURING CRUISE. NR 2 BATT SHOWED 21V AND SWITCHED OFF FOR DURATION OF FLIGHT. VERIFIED BATTERY WAS HOT, AND PERFORMED BATT CHARGE CONT BITE TEST. ALL NORMAL. FOUND RED AND BLUE WIRES 195 AND 196 AT BAT2 SHUNT 19PE DAMAGED AND CHAFING TOGETHER. REPAIRED BOTH WIRES AND REPLACED BATTERY PER PRECAUTIONARY DUE TO OVERHEATING, TESTED BATT CONT BITE TEST AGAIN ALL NORMAL. LET BATTERIES CHARGE FOR 2 HOURS AND OPERATED NORMALLY.

Part: BATTERY — OVERHEATED (NR 2) · airframe 36,456 hrs · 26,324 cycles

NR 2 BATTERY OVERHEATED DURING CRUISE. NR 2 BATT SHOWED 21V AND WAS SWITCHED OFF FOR DURATION OF FLIGHT. VERIFIED BATTERY WAS HOT, AND PERFORMED BATT CHARGE CONT BITE TEST. ALL NORMAL. FOUND RED AND BLUE WIRES 195 AND 196 AT BAT2 SHUNT 19PE DAMAGED AND CHAFING TOGETHER. REPAIRED BOTH WIRES AND REPLACED BATTERY PER PRECAUTIONARY DUE TO OVERHEATING, TESTED BATT CONT BITE TEST AGAIN ALL NORMAL. LET BATTERIES CHARGE FOR 2 HOURS AND OPERATED NORMALLY REF SMP, MM 24-31-11-4 AND WDM 24-31-02.

Part: SWITCH — FAILED (THRUST REVERSER) · airframe 36,216 hrs · 26,175 cycles

REJECT TAKEOFF AT APPROX 100 KNOTS DUE TO NR 1 ENG REVERSE UNLOCK LIGHT ON. REMOVED & REPLACED NR 1 ENG RT TRANSLATING SLEEVE STOW SWITCH, RAN REVERSER SEVERAL TIMES OPS CK'D GOOD PER 78-31-18-4-A. CK'D RIGGING OPS CK'D GOOD PER MM 78-31-38-2-A. COMP STALL NR 2 ENG. PERFORMED BOROSCOPE AND VISUAL FUNCTIONAL CHECKS. NO DAMAGE FOUND PER EA 6-7200-87936.

Part: CONTROL UNIT — MALFUNCTIONED (HYDRAULIC SYS) · airframe 35,889 hrs · 25,964 cycles

DURING CLIMBOUT YELLOW HYDRO SERVO SYSTEM JAMMED. JAM LIGHT ILLUMINATED ON OVERHEAD PANEL. NO ECAM WARNING. FOLLOWED CHECKLIST. JAM DETECTION CONTROL UNIT REPLACED.

Part: SENSOR — FAILED (MLG) · airframe 35,718 hrs · 25,810 cycles

AFTER TAKEOFF GEAR WOULD NOT RETRACT WITH EITHER SYS, AIRCRAFT HAD SYMTEMS OF THINKING IT WAS STILL ON GROUND. AUTOPILOT INOP, CABIN PRESS REGULATORS INOP. AFTER BLOCK IN ACARS DIDN`T RECOGNIZE THAT AIRCRAFT HAD TAKEN OFF. T/S PROX BOX FAULT CODE ARE 05, 06, 07, 03, 04, 12, 13, 14, 10, 11, FAULTS ARE SYS 1 AND 2 GEAR PROX SENSORS. REMOVED AND REPLACED LANDING GEAR POSITION SENSOR SWITCH (10GB) ON 400VU PER 32-61-00-5. REPLACED BOGIE BEAM SENSORS 8GA, 9GA, 11GA AND 12GA PER M/M 32-00-00-4. PERFORMED NUMEROUS GEAR RETRACTIONS ON BOTH SYS 1 AND 2 WITH NO FAULTS. ACFT OK FOR SERVICE.

Part: MODULE — FAILED (MLG) · airframe 35,702 hrs · 25,798 cycles

PDIS 450 32-60 0006380 05AUG04 MEM CLOSE R LOGPAGES: 00675737 GEAR HANDLE WOULD NOT RAISE. TRIED BOTH POSITIONS. GOT ALL 3 RED DOOR LIGHTS. BUT GEAR INDICATIONS SHOWED ALL 3 DOWN. CHECKED CONTROL BOX FOR FAULTS,NO FAULTS LOGGED, JACKED A/C RAN LANDING GEAR IN SYSTEM 1 AND SYSTEM 2, OPERATION NORMAL. REMOVED AND REPLACED LANDING GEAR ELECTRO VALVE MODULE IN REFERENCE WITH A 300-200 AMM 32-31-11-4, OPS NORMAL. RII:020225 PREMATURE REMOVAL/INSTALLATION OFF MFG 224TS054Y POS ONL SRL 315 ON MFG 224TS05Y SRL 787 TAG 665469.

Part: SPAR — CORRODED (ZONE 300) · corrosion level 3 · airframe 35,369 hrs · 25,581 cycles

RT HORIZONTAL STAB I/B END AT RIB 3 TO RIB 4 UPPER T/E EDGE OF SPAR FOR LENGTH OF 16 INCHES HAS SEVERE CORROSION WITH EXFOLIATION. RIGHT HORIZ STAB UPPER REAR SPAR CHORD FOR RIB 3 TO RIB 4 REMOVED CORROSION BY CUTTING OUT TEE CHORD AND INSTALLING NEW TEE CHORD SECTION AND SPLICING BY INSTALLING INTERNAL AND EXTERNAL SPLICE REPAIR ANGLES IAW A310 SRM 55-11-21 FIG 219. O/B OF RIB 5 TO RIB 6 REMOVED CORROSION, TREATED, LOCATED, DRILLED AND INSTALLED REPAIR STRAP IAW A310 SRM 55-11-21 FIG 211 AND 224.

Part: IRU — MALFUNCTIONED (E/E BAY) · airframe 35,288 hrs · 25,527 cycles

ON TAKEOFF ROLL CAPT'S PFD, NAV DISPLAY, NR 1 YAW DAMPER, NR 1 IRU FAILED. REMOVED, REPLACED AND THEN OPS CHECKED NR 3 IRU AS PER A-310 M/M 34-25-00-5 AND 34-25-14 OKAY FOR SERVICE. R/I FROM FACT PREMATURE REMOVAL/INSTALLATION OFF MFG 461600-0800-0801, POS 3 SRL 0093, TAG 999804 ON MFG 461600-0800-0801 SRL 0359, TAG 999737.

Part: BULB — FAULTY (NR 1 ENGINE) · airframe 34,431 hrs · 24,937 cycles

LEVELED OFF AT FL330, OIL TEMPERATURE BEGAN INCREASING. INCREASED THRUST, ATTEMPTING TO DECREASE OIL TEMPERATURE, BUT IT CONTINUED TO CLIMB, TURNING AMBER, THEN RED UNTIL IT REACHED 165 DEGREES, SHUT DOWN NR 1 ENGINE AND DIVERTED. REMOVED AND REPLACED TEMP BULB IAW MM. RAN ENGINE FOR 1 HOUR AT VARIOUS POWER SETTINGS AND OIL TEMPERATURE NEVER CLIMBED ABOVE 100 DEGREES. OPS AND LEAK CHECK GOOD, OK FOR SERVICE.

Part: ATTACH FITTING — BROKEN (SPOILER ACTUATOR) · airframe 34,275 hrs · 24,841 cycles

#4 RH SPOILER ACTUATOR ATTACH FITTING IS BROKEN. FWD I/B SIDE OF FITTING IS MISSING. ** S/D ** COMING

Part: DAMPER — FAILED (RT MLG) · airframe 33,635 hrs · 24,452 cycles

UNABLE TO RAISE LANDING GEAR AFTER T/O. REMOVED AND REPLACED RT MLG BOGIE BEAM PITCH DAMPER PER MM 32-11-15-4 02 AND 12-12-32-0 A/C NEEDS GEAR SWING JACKED AIRCRAFT PER MM 07-11-00-0. OPS CHECK NORMAL.

Part: WARNING LIGHT — ILLUMINATED (COCKPIT)

NR 2 REVERSE UNLOCK LIGHT CAME ON AT T/O.

Part: THRUST REVERSER — MALFUNCTIONED (NR 2 ENGINE) · airframe 32,488 hrs · 23,637 cycles

REVERSE UNLOCK LIGHT ON T/O ROLL. TRIED SEVERAL TIMES TO PUT NR 2 INTO REVERSE, STAYED IN REVERSE UNLOCK. A/C RELEASE PER MEL 78-1.

Part: THRUST REVERSER — INOPERATIVE (NR 2 ENGINE)

ON T/O, AFT BRAKE RELEASE (APPROX 50 KTS) REVERSER UNLOCK LIGHT ON THE NR 2 ENGINE ILLUM. ACFT RELEASE PER MEL 78-2, NR 2 ENGINE REVERSE UNLOCK LIGHT INOP. T/REV DEACTIVATED.

Part: VALVE — FALED (PNEUMATIC SYS)

00-16 - NR 1 BLD VLV (FAN AIR VLV) DFRD, THE NR 2 BLD VLV FAULTED AND CABIN ALT START CLB. FOUND PNEU CTLR FAULT THE HP S ENSOR FOUND WIRE NR 288 BETWEEM 2354VC AND 20VC BRKN. REPAIRED WIRE MM CHAP 20 AND TESTED PER MM 36-1100. BLD SYS NOW CK NORMAL.

Part: THRUST REVERSER — INOPERATIVE (NR 3 ENGINE)

NR 2 ENGINE THRUST REVERSER UNLOCK LIGHT ILLUM ON T/O ROLL. NR 2 ENG THRUST REVERSER DEACTIVATED PER MEL 78-1. ITEM TO BE SCHEDULED FOR REPAIRS

Part: CONTROLS — SLOW RESPONSE (RUDDER)

ON T/O, THE A/C SLOW TO RESPOND TO LEFT RUDDER INPUTS. ABORTED TAKEOFF. NO FAULTS WERE NOTED ON MTP. INSPECTED STEERING, RUDDER CONTROLS AND LINKAGE, NO DEFECTS NOTED. STEERING AND RUDDER DEFLECTION CK PER WITH FILLER AND RUDDER PEDAL INPUTS, NO DEFECTS NOTED PER AMM.

Part: ENGINE — FIRE (NR 2)

97-0248 - STA-LAX - ON LAND IN REVERSE THRUST, AS THRUST LVRS BROUGHT FWD (80 KTS) ENG MADE A POP CONT. SLOW FOR TURNOFF ENG APPEAR TO FLAME OUT FROM ENG IND. NO FIRE WARN BUT TOWER INFORM US THAT ANOTHER A/C SAID THERE WAS FIRE IN NR 2 ENG OTHER A/C CONFIRM THAT TAXIED CLR OF THE RUNWAY AND ACCOMP O/H SHUTDOWN PER ECAM. NEVER ANY FIRE IND, BUT REPORT FROM OUTSIDE. DEPLOY FIRE EXTING. FND NR 2 ENG EGT MAX POINTER READ 730 WBH 32277. REMOVED NR 2 IGNITER PLUGS GEARBOX PAD/2 BORESCOPE PLUGS ON TURBINE CASE RT SIDE.