N803FD

Part: FLAP — STUCK (WING) · airframe 430 hrs · 16,343 cycles

FLAP SYS 1 & 2 FAULT, FLAPS STUCK. REMOVED TWO BOLTS FROM RT TORQUE LIMITED COUPLER TO FOM. DRAINED FLUID FROM RT WING NR 1 FLAP DRIVE GEAR BOX FOR INSPECTION PURPOSE. GPS OVERRIDE SWITCH IN COCKPIT, CAPTAINS RIGHT KNEE, REQUIRES SAFETY. FOUND JAM FAULTS ON SFCC'S 1 & 2. RESET BOXES BUT FLAPS WOULD NOT DEPLOY & FAULTS RETURNED. RT TORQUE LIMITER INDICATOR IS POPPED. UNABLE TO RESET & TORQUE TUBES ARE BOUND FROM LIMITER TO NR 1 GEARBOX. SCREW JACKS 2, 3 & 4 WERE NOT BOUND UP & NO LOCKOUT INDICATORS WERE TRIPPED. NR 1 GEAR BOX APPEARED TO BE PROPERLY SERVICED WITH NO WATER PRESENT. SPANNER WRENCHES ORDERED & ARE INBOUND ON MORNING FLIGHT.

Part: STRINGER — DAMAGED (FUSELAGE) · airframe 428 hrs · 16,221 cycles

REMOVED STRINGER 44 AT FRAME 19 - 20 TO FOM. REMOVED SHEAR TIE & COUPLING. COUPLING & STRINGER FOUND TO BE DAMAGED. FABRICATED NEW STRINGER ON T15 1157203. RECEIVED NEW COUPLING, INSTALLED SHEAR TIE, COUPLING & STRINGER 44 AT FRAME 19 - 20 IAW SRM 51-40-21. MAJOR REPAIR.

Part: CROSSBEAM — CORRODED (FRAME 67) · airframe 427 hrs · 16,187 cycles

BULK CARGO FRAME 67 -Y-940, CROSSBEAM WITH INNER GRANULAR CORROSION. REPLACED THE CORRODED CROSSBEAM OF BULK CARGO IAW SRM 51-40-21. THIS REPAIR CATEGORY A, MAJOR REPAIR IAW GMM6-2-100.

Part: SKIN — DELAMINATED (TE FLAP) · airframe 42,784 hrs · 16,187 cycles

AGEING INSPECTION, EXISTING REPAIR ON RT OUTER FLAP UPPER SKIN OUT OF RIB 10 REQUIRES EVALUATION FOR CONFORMITY. THE EXISTING REPAIR WAS EVALUATED & FOUND IN CONFORMITY WITH APPROVED DATA. BUT INSPECTION FOUND DELAMINATION ON OLD REPAIR. REPAIRED THE DAMAGE IAW EA 6-5750-T0313790. THE REPAIR WAS CATEGORY A & CLASSIFIED AS MINOR IAW GMM 6-2-100 REVISION 127.

Part: SKIN — CRACKED (RT WING) · airframe 427 hrs · 16,187 cycles

RIGHT WING FIXED TE LOWER SKIN AT RIBS 11 - 12 CRACKED 1 INCH. REPAIRED IAW EA 6-5730-T0318078 & R57249152. MAJOR REPAIR IAW GMM 6-2-100.

Part: REPAIR — DELAMINATED (TE FLAP) · airframe 42,784 hrs · 16,187 cycles

AGEING INSPECTION, EXISTING REPAIR ON RT OUTER FLAP, UPPER SKIN OUT OF RIB 10 REQUIRES EVALUATION FOR CONFORMITY. THE EXISTING REPAIR WAS EVALUATED & FOUND IN CONFORMITY WITH APPROVED DATA. BUT INSPECTION FOUND DELAMINATION ON OLD REPAIR. REPAIRED THE DAMAGE IAW EA 6-5750-T0313790. THE REPAIR WAS CATEGORY A & CLASSIFIED AS MINOR IAW GMM 6-2-100 REVISION 127 EO 6-5100-7-5000 PART 1, THE REPAIR WAS COMPLETED.

Part: REPAIR — DELAMINATED (TE FLAP) · airframe 42,784 hrs · 16,187 cycles

AGEING INSPECTION, EXISTING REPAIR ON RT OUTER FLAP, UPPER SKIN OUT OF RIB 10 REQUIRES EVALUATION FOR CONFORMITY. THE EXISTING REPAIR WAS EVALUATED & FOUND IN CONFORMITY WITH APPROVED DATA. BUT INSPECTION FOUND DELAMINATION ON OLD REPAIR. REPAIRED THE DAMAGE IAW EA:6-5750-T0313790. THE REPAIR WAS CATEGORY A & CLASSIFIED AS MINOR IAW GMM 6-2-100 REVISION 127. EO 6-5100-7-5000 PART 1 WAS COMPLETED.

Part: FLOOR SUPPORT — CRACKED (FRAME 15) · airframe 427 hrs · 16,187 cycles

MAIN DECK CARGO FRAME 15A Y1456 FLOOR SUPPORT CRACKED APPROX 1.0 INCH IN LENGTH. REPAIRED IAW SRM 53-12-15-201 PARA 5G. MAJOR REPAIR IAW GMM6-2-100.

Part: WINDSHIELD — CRACKED (COCKPIT) · airframe 42,034 hrs · 15,722 cycles

EN ROUTE LT WINDOW HEAT FAULT, FOLLOWED BY WINDSHIELD CRACKING. NUMEROUS CRACKS IN LOWER RT CORNER. QRH FOLLOWED, DIVERTED. REMOVED L1 WINDSHIELD IAW MM 56-11-11-04.

Part: THRUST REVERSER — DAMAGED (NR 1 ENGINE) · airframe 41,843 hrs · 15,603 cycles

NUMBER 1 ENG THRUST REVERSER OTBD TRANSLATING SLEEVE AFT 8 INCHES IS MISSING TOP TO BOTTOM, WHITE COWL. ALL COCKPIT THRUST REVERSER LIGHTS EXTINGUISHED, NORMAL. NR 1 ENG OIL SERVICE DOOR WAS OPEN & BOTTOM HINGE PIN MISSING. INNER BARREL MESH IS MISSING & HAS DENTS. INSPECTED EXTENDED FLAPS & SLATS FULLY, NO DAMAGE. FOUND RETRACTED FLAPS & SLATS. INSPECTED TOP OF BOTH WINGS, NO DAMAGE FOUND. OPENED MLG DOORS, NO DAMAGE FOUND, CLOSED GEAR DOORS. R & R NR 1 OTBD THRUST REVERSER IAW AMM CH 71-13-03-04. COMPLETED RIG & OPS CHECK OF NR 1 ENG REVERSER IAW MM 78-31-00-5. ALL OPERATIONS CHECKED MFG 221-4126-519-3-375 IS OVERSIZE & WILL NOT FIT BOX 5C.

Part: SENSOR — MALFUNCTIONED (NR 2 ENG OIL) · airframe 41,696 hrs · 15,517 cycles

DURING CRUISE FLIGHT, NR 2 RT ENGINE OIL TEMP BEGAN TO FLUCTUATE FROM NORMAL CRUISE TEMP OF 116C UP TO 230C. STAYED ABOVE 160C FOR MORE THAN 9 MINUTES BUT CONTINUED TO FLUCTUATE BETWEEN NORMAL & A HIGH OF 230 C. FINALLY TEMP STAYED ABOVE 160 C FOR MORE THAN 4 MINUTES. REMOVED CONNECTOR & NO SIGNS OF DAMAGE OR CORROSION. RECONNECTED CONNECTOR & SHOOK WIRES & NO TEMP CHANGE. NR 2 ENGINE OIL TEMP ON THE GROUND IS 30 DEGREES LESS THAN NR 1 ENG. CONNECTOR REMOVED FROM TEMP SENSOR.

Part: COMPUTER — MALFUNCTIONED (THRUST) · airframe 41,568 hrs · 15,441 cycles

DURING TAKEOFF, TOGA WOULD NOT ENGAGE. NO OTHER WARNINGS, COULD MANUALLY ADVANCE THROTTLES WITH NO RESTRICTIONS. REMOVED AND REPLACED TCC COMPUTOR IAW AMM 22-36-34-04-01 AND REPFORMED A AFS/LAND TEST. ALL SYSTEM TESTED NORMAL.

Part: FLOORBOARD — DELAMINATED (ZONE 100) · airframe 40,849 hrs · 14,986 cycles

AFT CARGO BAY FLOORBOARD BETWEEN 1R AND 2R RAIL TRACKS, 2 FEET FWD OF BALL MAT HAS 24"OF DELAMINATION. FLOORBOARD WAS DAMAGED BEYOND ECONOMICAL REPAIR. FABRICATED A REPLACEMENT FLOORBOARD IAW DWG SRZ-25-005, REV J.

Part: FERRULE — CRACKED (NR 2 NACELLE) · airframe 40,849 hrs · 14,986 cycles

NR 2 PYLON FERRULE IS CRACKED COMPLIED WITH EA 6-5450-T0300139 REV NR PS P1 - NACELLES/PYLON PRECOOLER FERRULE CRACK ON NR 2 PYLON REF WR 54-50 6954.

Part: FRAME — CORRODED (BULKHEAD) · airframe 40,849 hrs · 14,986 cycles

FUSELAGE AFT PRESSURE BULKHEAD FWD FACE LWR RIM FR 80/82 HAS 3 EA AREAS OF EXFOLIATED CORROSION & 1 EA AREA OF CORROSION EXTENDING INTO THE CLEAT PROFILE. DEFECT MEASURES 15"SQ. AFTER REMOVAL OF LEVEL 1 CORROSION, FOUND ANGLES TO BE OUT OF LIMITS IAW SRM 53-19-17, FIG 104. R & R 3EA DOWN-HOLDERS AND 1EA CONNECTING SECTION IAW SRM 51-72-10, PGS 1-3. FABRICATED 1EA REPLACEMENT DOWN-HOLDER AND INSTALLED IAW DWG A53981823 AND SRM 51-72-10, PGS 1-3.

Part: SKIN — DENTED (ZONE 600) · airframe 40,849 hrs · 14,986 cycles

RT WING OTBD FLAP L/E APPROX WING RIB 25 HAS A DENT WITH FIELD REPAIR APPROX 1.5 X 1.5 X .200D. CUT OUT DAMAGED AREA. FABRICATED, HEAT TREATED, LOCATE AND DRILLED REPAIR PARTS IAW SRM 57-53-12, FIG 213. PROTECTED REPAIR PARTS AND THE CUT OUT AREA ON RT FLAP L/E IAW SRM 51-75-10. INSTALLED REPAIR PARTS IAW SRM 57-53-12 PARA B, PG 274. TOP COATED IAW SRM 51-75-10 AND PERFOMRED TRACKING IAW EA 6-5750-T0300171, REV NR PS P1.

Part: FLOORBOARD — DELAMINATED (ZONE 700) · airframe 40,849 hrs · 14,986 cycles

MLG BAY LT AFT WALKWAY PANEL 148 BF HAS 60 SQ" AREA OF DELAMINATION. FABRICATED REPLACEMENT PANEL 148 BF IAW DWG SRZ 25-005, REV J.

Part: POWER SUPPLY — FAILED (EMERGENCY LIGHTS) · airframe 38,846 hrs · 13,663 cycles

EMERGENCY LIGHTS FAIL OPS CHECK FROM COURIER AREA TEST SWITCH. R & R THE POWER SUPPLY UNIT AND BATTERY IAW AMM 33-51-14-04. PERFORMED A SATISFACTORY TEST OF THE EMERGENCY LIGHTS IAW AMM 33-51-14-04.

Part: RIB — DAMAGED (LT WING) · airframe 38,846 hrs · 13,663 cycles

LT WING T/E RIB AT WIAX 62.70 HAS EDGE DAMAGE ON THE SPAR ATTACH FLANGE. REMOVED DAMAGE FROM THE SPAR AREA IAW EA 6-5730-136705.

Part: SUPPORT — CRACKED (RT WING AILERON) · airframe 38,846 hrs · 13,663 cycles

RT WING ALL SPEED AILERON ACTUATOR UPPER PANEL SUPPORT IS CRACKED ON THE OTBD SIDE. PARTIALLY REMOVED OTBD UPPER AILERON PANEL AND REMOVED CRACKED LANDING. INSTALLED NEW PANEL LANDING PN A5724275920300, PO 691739.5 AND RE-INSTALLED OTBD UPPER AILERON PANEL IAW SRM 51-40-21 AND DWG A57242821, REV "G".

Part: FAIRING — CRACKED (NR 1 NACELLE) · airframe 38,846 hrs · 13,663 cycles

NR 1 PYLON INBD APRON FAIRING SKIN IS CRACKED. INSTALLED REPAIR DOUBLER ON THE NR1 PYLON INBD APRON FAIRING IN REF TO SRM 54-56-10, FIG 201.

Part: SKIN — GOUGED (HORIZONTAL STAB) · airframe 38,846 hrs · 13,663 cycles

LEFT HORIZONTAL STAB LOWER EXTERIOR SKIN IS GOUGED AT THE FUEL ACCESS PANEL 333 FB CUTOUT. SMOOTHED AREA. ORIGINAL 0.268. REMAINING 207. FOUND IN LIMITS IAW EA 6-510-136714 REV "A"; HORIZONTAL STABILIZER - LOWER PANEL GOUGED AROUND ACCESS HOLE BETWEEN RIB 17 AND 18 (LHS)". ALODINED, PRIMED AND PAINTED IAW SRM 51-75-10.

Part: SUPPORT — CRACKED (ZONE 100) · airframe 38,846 hrs · 13,663 cycles

FUSELAGE UNDER THE LT AIR CONDITIONING AFT FAIRING THE AFT INBD EXHAUST SHIELD SUPPORT IS CRACKED. REMOVED SUPPORT BRACKET IAW SRM 51-40-21. RECEIVED NEW SUPPORT BRACKET FROM STORES, PO 693873.1. INSTALLED NEW BRACKET IAW SRM 51-72-10, PAGES 1-3.

Part: FLOOR PANEL — DELAMINATED (ZONE 100) · airframe 38,846 hrs · 13,663 cycles

AIR CONDITIONING COMPARTMENT FLOOR PANEL 143 DF HAS A LARGE CORNER THAT IS DELAMINATED AND CONTAMINATED. FABRICATED NEW AIR CONDITIONING COMPARTMENT FLOOR PANEL 143 DF IAW DWG SRZ 25-005, REV "H".

Part: SLEEVE — CRACKED (THRUST REVERSER) · airframe 38,846 hrs · 13,663 cycles

NR 2 ENG RT THRUST REVERSER SLEEVE IS CRACKED AND DAMAGED JUST BELOW THE NR 6 BLOCKER DOOR. REPAIRED NR 2 THRUST REVERSER JUST BELOW THE NR 6 BLOCKED DOOR BY CLEANING EXISTING POTTING AND RE-POTTING DAMAGED AREA AND CURING IAW SRM 54-05- 01, PARA 9.

Part: SKIN — DENTED (ZONE 100) · airframe 38,846 hrs · 13,663 cycles

LOWER FUSELAGE LEFT EXTERNAL SURFACE IS DENTED BETWEEN FRAME 38.2 & FRAME 39; STRINGER 35-36L. CUT OUT DENT, FABRICATED DOUBLER, DRILLED , DEBURRED, ALODINED, PRIMED INSTALLED AND SEALED IAW SRM 53-10-12, 51-21-10 & 51-40-21.

Part: FLOOR PANEL — CRACKED (ZONE 200) · airframe 38,846 hrs · 13,663 cycles

MAIN CABIN FLOOR PANEL 222 CF IS CRACKED ACROSS THE BOTTOM. FABRICATED NEW FLOOR PANEL, POTTED EDGES AND INSTALLED INSERTS IAW DWG SRZ 25-005, REV "H".

Part: FLOOR PANEL — CRACKED (ZONE 200) · airframe 38,846 hrs · 13,663 cycles

MAIN CABIN FLOOR PANEL NR232 RG HAS THE FWD RT EAR CRACKED. FABRICATED NEW PANEL, POTTED EDGES AND INSTALLED INSERTS IAW DWG SRZ 25-005, REV "H".

Part: FLOOR PANEL — CRACKED (ZONE 200) · airframe 38,846 hrs · 13,663 cycles

FUSELAGE INTERNAL STRUCTURE, MAIN DECK FLOOR PANEL 241 PG IS CRACKED FROM FRAME 53 TO FRAME 54. FABRICATED NEW FLOOR PANEL, POTTED EDGES AND INSTALLED INSERTS IAW DWG SRZ 25-005, REV "H".

Part: FLOOR PANEL — CRACKED (ZONE 200) · airframe 38,846 hrs · 13,663 cycles

FUSELAGE INTERNAL STRUCTURE, MAIN DECK FLOOR PANEL 242 QF IS CRACKED FROM FRAME 47 TO FRAME 51. FABRICATED NEW FLOOR PANEL, POTTED EDGES AND INSTALLED INSERTS IAW DWG SRZ 25-005, REV "H".

Part: FLOOR PANEL — DAMAGED (ZONE 200) · airframe 38,846 hrs · 13,663 cycles

MAIN CABIN FLOOR PANEL NR251 RG IS CRUSHED FROM APPROX FRAME 60 - FRAME 62; LBL 60. FABRICATED NEW FLOOR PANEL, POTTED EDGES AND INSTALLED INSERTS IAW DWG SRZ 25-005, REV "H".

Part: FLOOR PANEL — CRACKED (ZONE 200) · airframe 38,846 hrs · 13,663 cycles

MAIN CABIN FLOOR PANEL NR261 LF IS CRACKED FROM FRAME 74 - FRAME 75; LBL 12. FABRICATED NEW FLOOR BOARD, POTTED EDGES AND INSTALLED INSERTS IAW DWG SRZ 25-005, REV "H".

Part: FLOORBOARD — CRACKED (ZONE 200) · airframe 38,846 hrs · 13,663 cycles

MAIN DECK FLOORBOARD 242 BR IS CRACKED AT FRAME 39. FABRICATED NEW FLOORBOARD, POTTED EDGES, INSTALLED INSERTS, APPLIED ANTI-SKID AND PART MARKED IAW DWG SRZ 25-005, REV "H".

Part: FLOORBOARD — CRACKED (CABIN) · airframe 38,846 hrs · 13,663 cycles

MAIN DECK FLOORBOARD NR 241 YF IS CRACKED AT FRAME 54. FABRICATED NEW FLOORBOARD, POTTED EDGES AND INSTALLED INSERTS IAW DWG SRZ 25-005, REV "H".

Part: SEAT TRACK — GOUGED (ZONE 200) · airframe 38,846 hrs · 13,663 cycles

SEAT TRACK AT FRAME 54, RBL 48 HAS SCALLOPS GOUGED OUT OF LIMITS. R & R SEAT TRACK IAW SRM 53-10-15, FIG 201.

Part: SKIN — CORRODED (LT WING) · airframe 38,846 hrs · 13,663 cycles

LT WING TOP SKIN SURFACE IS CORRODED AT THE REAR SPAR AREA FROM RIB 4 - RIB 5. REMOVED 2 EA FASTENERS LT WING TOP SKIN UPPER SURFACE REAR SPAR BETWEEN RIB 17 AND RIB 18 IAW SRM 51-40-21. BLENDED CORROSION IAW SRM 51-74-10. FOUND TO BE WITHIN LIMITS IAW SRM 57-20-12, PGS 13 & 110. FLAP PEENED AREA IAW SRM 51-29-00, PG 201. ALODINED, PRIMED AND PAINTED AREA IAW SRM 51-21-10, PG 3; SRM 51-73-10, PG 203 & SRM 51-23-00, PG 24. INSTALLED 2 EA FASTENERS IAW SRM 51-40-21.

Part: SKIN — CORRODED (LT WING) · airframe 38,846 hrs · 13,663 cycles

LT WING TOP SKIN SURFACE IS CORRODED 2 EA PLACES AT THE REAR SPAR AREA FROM RIB 12 - RIB 13. REMOVED CORROSION IAW SRM 57-00-00, PG 212 AT THE LT WING TOP SKIN UPPER SURFACE T/E BETWEEN RIBS 12-13. FOUND TO BE WITHIN LIMITS IAW SRM 57-20-12, PGS 9 & 111. FLAP PEENED AREA IAW SRM 51-29-00, PG 201. ALODINED AND PRIMED IAW SRM 51-21-10, PG 3 & SRM 51-75-10, PG 203. INSTALLED 2 EA. FASTENERS IAW SRM 51-40-21.

Part: SKIN — CORRODED (RT WING) · airframe 38,846 hrs · 13,663 cycles

RT WING TOP SKIN SURFACE FRONT SPAR AREA SKIN IS CORRODED FROM RIB 17 - RIB 18. REMOVED 5 EA FASTENERS RT WING TOP SKIN UPPER SURFACE FRONT SPAR BETWEEN RIB 17 AND RIB 18. BLENDED CORROSION IAW SRM 51-74-10. FOUND TO BE WITHIN LIMITS IAW SRM 57-20-12, PGS 13 & 110. FLAP PEENED AREA IAW SRM 51-29- 00, PG 201. INSTALLED 5 EA FASTENERS IAW SRM 51-40-21. ALODINED, PRIMED AND PAINTED AREA IAW SRM 51-21-10, PG 3; SRM 51-73-10, PG 203 & SRM 51-23-00, PG 24.

Part: SKIN — CORRODED (LT WING) · airframe 38,846 hrs · 13,663 cycles

LT WING TOP SKIN SURFACE IS CORRODED AT THE REAR SPAR AREA FROM RIB 15-RIB 16. REMOVED CORROSION ; LT WING TOP SKIN T/E AREA BETWEEN RIBS 15-16 IAW SRM 57-20-12, PG 9. FOUND TO BE WITHIN LIMITS IAW SRM 57-20-12, PGS 9 & 111. TOOL T8285D. FLAP PEENED AREA IAW SRM 51-29-00, PG 201. ALODINED & PRIMED AREA IAW SRM 51-21-01, PG 3 & SRM 51-75-10, PG 203. INSTALLED 2 EA FASTENERS IAW SRM 51-40-21.

Part: SKIN — CORRODED (RT WING) · airframe 38,846 hrs · 13,663 cycles

RT WING TOP SKIN UPPER SURFACE, REAR SPAR AREA SKIN IS CORRODED FROM RIB 23 TO RIB 24. REMOVED FASTENER RIGHT WING TOP SKIN UPPER SURFACE REAR SPAR BETWEEN RIB 23 AND RIB 24. BLENDED CORROSION IAW A310-300 SRM 51-74-10. FOUND TO BE WITHIN LIMITS IAW SRM 57-20-12, PGS 13 & 110. FLAP PEENED AREA IAW A310-300 SRM 51-29-00, PG 201. INSTALLED FASTENER IAW A310-300 SRM 51-40-21. ALODINED, PRIMED AND PAINTED AREA IAW SRM 51-21-10, PG 3; SRM 51-73-10, PG 203 & SRM 51-23-00, PG 24.

Part: SKIN — CORRODED (RT WING) · airframe 38,846 hrs · 13,663 cycles

RT WING TOP SKIN UPPER SURFACE, REAR SPAR AREA SKIN IS CORRODED FROM RIB 4 TO RIB 5. REMOVED 2 EA FASTENERS RT WING TOP SKIN UPPER SURFACE AT REAR SPAR IAW SRM 51-40-21. BLENDED CORROSION IA SRM 51-74-10. FOUND TO BE WITHIN LIMITS IAW SRM 57-20-12, PGS 13 & 110. FLAP PEENED AREA IAW SRM 51-29-00, PG 201. INSTALLED 2 EA FASTENERS IAW SRM 51-40-21. ALODINED, PRIMED AND PAINTED AREA IAW SRM 51-21-10, PG 3; SRM 51-73-10, PG 203 & SRM 51-23-00, PG 24.

Part: SKIN — CRACKED (LT WING) · airframe 38,846 hrs · 13,663 cycles

LT WING BOTTOM SKIN LOWER SURFACE T/E AREA SKIN IS CRACKED FROM RIB 11 TO RIB 12. COMPLIED WITH EA 6-5730-136705.

Part: SKIN — CORRODED (RT WING) · airframe 38,846 hrs · 13,663 cycles

RT WING TOP SKIN UPPER SURFACE, SKIN IS CORRODED FROM RIB 10 TO RIB 11. REMOVED FASTENER RT WING TOP SKIN UPPER SURFACE REAR SPAR BETWEEN RIB 10 AND RIB 11. BLENDED CORROSION IAW SRM 51-74-10. FOUND TO BE WITHIN LIMITS IAW SRM 57-20-12, PGS 13 & 110. FLAP PEENED AREA IAW SRM 51-29-00, PG 201. INSTALLED FASTENER IAW SRM 51-40-21. ALODINED, PRIMED AND PAINTED AREA IAW SRM 51-21-10, PG 3; SRM 51-73-10, PG 203 & SRM 51-23-00, PG 24.

Part: PANEL — DENTED (CARGO BAY) · airframe 38,846 hrs · 13,663 cycles

BULK CARGO SLANT PANEL 162 CW HAS DENT DAMAGE. FABRICATED NEW PANEL, POTTED EDGES AND INSTALLED INSERTS REF DWG SRZ 25- 005, REV "H". FABRICATED, TRIMED AND BONDED A METAL PLATE REF DWG SRZ 25-011, REV "C".

Part: FLOOR PANEL — PUNCTURED (CARGO BAY) · airframe 38,846 hrs · 13,663 cycles

BULK CARGO SLANT PANEL 161 CW IS PUNCTURED AND DENTED IN NUMEROUS PLACES. FABRICATED NEW FLOOR PANEL, POTTED EDGES AND INSTALLED INSERTS IAW DWG SRZ 25-005, REV "H". TRIMMED AND BONDED METAL PLATE IAW DWG SRZ 25-011, REV "C".

Part: FLOOR PANEL — CRACKED (MAIN CABIN) · airframe 38,846 hrs · 13,663 cycles

MAIN CABIN FLOOR PANEL 251 EH HAS A CRACKED CORNER. FABRICATED NEW FLOOR PANEL, POTTED EDGES AND INSTALLED INSERTS IAW DWG SRZ 25-005, REV "H".

Part: FLOOR PANEL — DELAMINATED (CARGO BAY) · airframe 38,846 hrs · 13,663 cycles

BULK PIT FLOOR PANEL 161 AF IS DELAMINATED. FABRICATED NEW PANEL, POTTED EDGES AND INSTALLED INSERTS IAW DWG SRZ 25-005, REV "H". FABRICATED, TRIMED AND BONDED A METAL PLATE IAW DWG SRZ 25-011, REV "C".

Part: FLOOR PANEL — CRACKED (MAIN CABIN) · airframe 38,846 hrs · 13,663 cycles

MAIN CABIN FLOOR PANEL 232 MH IS CRACKED. FABRICATED NEW FLOOR PANEL, POTTED EDGES AND INSTALLED INSERTS IAW DWG SRZ 25-005, REV "H".

Part: FLOOR PANEL — PUNCTURED (CARGO BAY) · airframe 38,846 hrs · 13,663 cycles

BULK PIT FLOOR PANEL 162 DF IS PUNCTURED. FABRICATED NEW FLOOR PANEL, POTTED EDGES AND INSTALLED INSERTS IAW DWG SRZ 25-005, REV "H". TRIMMED AND INSTALLED METAL PLATE IAW DWG SRZ 25-011, REV, "C"

Part: FLOOR PANEL — CRACKED (MAIN CABIN) · airframe 38,846 hrs · 13,663 cycles

MAIN CABIN FLOOR PANEL 231 LG IS CRACKED. FABRICATED NEW FLOOR PANEL, POTTED EDGES AND INSTALLED INSERTS IAW DWG SRZ 25-005, REV "H".

Part: FLOOR PANEL — PUNCTURED (CARGO BAY) · airframe 38,846 hrs · 13,663 cycles

BULK PIT FLOOR PANEL 162 EF IS PUNCTURED. FABRICATED NEW PANEL, POTTED EDGES AND INSTALLED INSERTS IAW DWG SRZ 25-005, REV "H". TRIMMED AND INSTALLED METAL PLATE IAW DWG SRZ 25-011, REV, "C"

Part: FLOOR PANEL — PUNCTURED (MAIN CABIN) · airframe 38,846 hrs · 13,663 cycles

MAIN CABIN FLOOR PANEL 231 QG IS PUNCTURED ON THE TOP SURFACE. FABRICATED NEW FLOOR PANEL, POTTED EDGES AND INSTALLED INSERTS IAW DWG SRZ 25-005, REV "H".

Part: FLOOR PANEL — CRACKED (MAIN CABIN) · airframe 38,846 hrs · 13,663 cycles

MAIN CABIN FLOOR PANEL 241 ZJ IS CRACKED. FABRICATED NEW FLOOR PANEL, POTTED EDGES AND INSTALLED INSERTS IAW DWG SRZ 25-005, REV "H".

Part: FLOOR PANEL — DELAMINATED (ZONE 100) · airframe 38,846 hrs · 13,663 cycles

AFT PIT FLOOR PANEL 152 AF IS DELAMINATED. FABRICATED NEW FLOOR PANEL, POTTED EDGES AND INSTALLED INSERTS IAW DWG SRZ 25-005, REV "H".

Part: FLOOR PANEL — CRACKED (MAIN CABIN) · airframe 38,846 hrs · 13,663 cycles

MAIN CABIN FLOOR PANEL 252 BH HAS AN EAR CRACKED OFF THE AFT END OF THE PANEL. FABBED NEW FLOOR PANEL, POTTED EDGES AND INSTALLED INSERTS IAW DWG SRZ 25-005, REV "H".

Part: FLOOR PANEL — CRACKED (MAIN CABIN) · airframe 38,846 hrs · 13,663 cycles

MAIN CABIN FLOOR PANEL 252 BG IS CRACKED. FABRICATED NEW FLOOR PANEL, POTTED EDGES AND INSTALLED INSERTS IAW DWG SRZ 25-005, REV "H".

Part: FLOOR PANEL — DELAMINATED (CARGO BAY) · airframe 38,846 hrs · 13,663 cycles

BULK PIT FLOOR PANEL 162 HF IS DELAMINATED. FABRICATED NEW FLOOR PANEL, POTTED EDGES AND INSTALLED INSERTS IAW DWG SRZ 25-005, REV "H". TRIMED AND BONDED A METAL PLATE IAW DWG SRZ 25-011, REV "C".

Part: FLOOR PANEL — DELAMINATED (CARGO BAY) · airframe 38,846 hrs · 13,663 cycles

AFT PIT FLOOR PANEL 152 BF IS DELAMINATED. FABRICATED NEW FLOOR PANEL, IAW DWG SRZ 25-005, REV "H". POTTED EDGES AND INSTALLED INSERTS IAW DWG SRZ 25-005, REV "H".

Part: FLOOR PANEL — CRACKED (MAIN CABIN) · airframe 38,846 hrs · 13,663 cycles

MAIN CABIN FLOOR PANEL 251 PH IS CRACKED ON THE BOTTOM SIDE. FABRICATED NEW FLOOR PANEL, POTTED EDGES AND INSTALLED INSERTS IAW DWG SRZ 25-005, REV "H".

Part: FLOOR PANEL — DELAMINATED (CARGO BAY) · airframe 38,846 hrs · 13,663 cycles

AFT PIT FLOOR PANEL 152 DF IS DELAMINATED. FABRICATED NEW FLOOR PANEL, POTTED EDGES AND INSTALLED INSERTS IAW DWG SRZ 25-005, REV "H".

Part: PANEL — DENTED (CARGO BAY) · airframe 38,846 hrs · 13,663 cycles

BULK PIT SIDEWALL PANEL 161 GW IS DENTED. FABRICATED NEW FLOOR PANEL, POTTED EDGES AND INSTALLED INSERTS IAW DWG SRZ 25-005, REV "H". TRIMMED AND BONDED METAL PLATE IAW DWG SRZ 25-011, REV "C".

Part: FLOOR PANEL — DELAMINATED (CARGO BAY) · airframe 38,846 hrs · 13,663 cycles

BULK PIT FLOOR PANEL 161 HF IS DELAMINATED. FABRICATED NEW FLOOR PANEL, POTTED EDGES AND INSTALLED INSERTS IAW DWG SRZ 25-005, REV "H". TRIMMED AND BONDED METAL PLATE IAW DWG SRZ 25-011, REV "C".

Part: FLOOR PANEL — PUNCTURED (CARGO BAY) · airframe 38,846 hrs · 13,663 cycles

BULK PIT FLOOR PANEL 161 BF IS PUNCTURED. FABRICATED NEW FLOOR PANEL, POTTED EDGES AND INSTALLED INSERTS IAW DWG SRZ 25-005, REV "H". TRIMMED AND INSTALLED METAL PLATE IAW DWG SRZ 25-011, REV, "C"

Part: PANEL — DELAMINATED (CARGO BAY) · airframe 38,846 hrs · 13,663 cycles

AFT PIT CEILING PANEL 152 DC IS DELAMINATED. REPAIRED AFT PIT CEILING PANEL BY REMOVING THE METAL DOUBLER DAMAGE, FIBERGLASS DAMAGE ON THE EXTERIOR AND INNER SURFACE, CLEANING, FABRICATING METAL DOUBLER, PREPPING AREA TO BOND METAL AND FIBERGLASS REPAIR PLIES AND APPLYING FIBERGLASS WET LAY UP REPAIR AND BONDING THE METAL DOUBLER IAW AMM 25-00-00-8 AND DWG SRZ 25-013. CURED REPAIRS ON THE EXTERIOR AND INNER SURFACE AND CURED METAL DOUBLER REPAIR IAW AMM 25-00-00-8 AND DWG SRZ 25-013. PAINTED INNER SURFACE IAW SRM 51-75-10.

Part: FLOOR PANEL — PUNCTURED (CARGO BAY) · airframe 38,846 hrs · 13,663 cycles

BULK PIT FLOOR PANEL 161 GF IS PUNCTURED. FABRICATED NEW FLOOR PANEL, POTTED EDGES & INSTALLED INSERTS IAW SRZ 25-005, REV "H". TRIMMED & BONDED METAL PLATE IAW SRZ 25-011, REV "C".

Part: FLOOR PANEL — CRACKED (CARGO BAY) · airframe 38,846 hrs · 13,663 cycles

FWD CARGO COMPARTMENT FLOOR PANEL 132 RF IS CRACKED AND HAS EDGE DAMAGE IN NUMEROUS PLACES. FABRICATED NEW FLOOR PANEL, POTTED EDGES AND INSTALLED INSERTS IAW DWG SRZ 25-005, REV "H".

Part: FLOOR PANEL — CRACKED (MAIN CABIN) · airframe 38,846 hrs · 13,663 cycles

MAIN CABIN FLOOR PANEL 241 PK IS CRACKED. FABRICATED NEW FLOOR PANEL, POTTED EDGES, INSTALLED INSERTS, APPLIED ANTI-SKID AND PART MARKED IAW DWG SRZ 25-005, REV "H".

Part: SKIN — CORRODED (RT WING) · airframe 38,846 hrs · 13,663 cycles

RT WING BOTTOM SKIN, LOWER SURFACE IS CORRODED AT RIB 31. REAR SPAR AREA. REMOVED CORROSION. ORIGINAL MATERIAL 0.150. MATERIAL REMAINING 0.091. MATERIAL LOSS 0.059 OUT OF LIMITS IAW SRM 57-20-12. RERPAIR AREA IAW EA 6-5710-136708, "WINGS - RT WING LOWER SKIN AT RIB 31 AND REAR SPAR - CORROSION". REMOVED AND INSTALLED PANEL AT RIB 31 INSIDE FUEL TANK IAW SRM 51-40-21, PARA 5. GENERATED RFTS N803FD-1-44118. RECEIVED FINAL RFTS N803FD-1-44118 WITH EA 6-5710-136708, "WINGS - RT WING LOWER SKIN AT RIB 31 AND REAR SPAR - CORROSION". FLAP PEENED AREA AT RIB 31, INTENSITY .006/ .012 TC 330 AT 3200 RPM FOR 3 MINUTES IAW SRM 51-29-00, FIG 202.

Part: INDICATOR — INTERMITTENT (FUEL QTY) · airframe 38,497 hrs · 13,420 cycles

SHORTLY AFTER LEVELOFF AT 380 LT OUTER FUEL INDICATED "XX" WITH TOTAL FUEL READING "XX" AND ALSO GW AND CG READING "XX" ON ECAM. LT OUTER FUEL QUANTITY ON OVERHEAD WAS BLANK. MEL 28-21-09 ALREADY HAD AUTO FUEL FEED SYSTEM DE-ACTIVATED FUEL ON LT INNER TANK MATCHED RT INNER TANK THRU-OUT FLIGHT ATB TO MEM READINGS RETURNED TO NORMAL ON DOWN WIND LEG, ABEAM KMEM. PERFORMED ADJ/TEST OF FQI IAW AMM 28-42-38-5. FOUND FAULT CODES 502-CADENSICON COMPENSATOR LO.311,L OUTER TANK PROBES HIGH. NO FAULTS ON CGCC. ALSO AFTER RETURNING TO ACFT ALL LT OUTER TANK INDICATIONS BLANK ON OVERHEAD AND REFUEL PANEL. AMBER XX ON ECAM. PERFORMED CAP/RESISTANCE CHECK PER 28-42-00-5. CHECKS WERE NORMAL. REVISITED PREVIOUS WIRE REPAIR ON 26QT1 WIRE 2842-5023. SPLICE CHECKS NORMAL. SYSTEM MONITOR/FQIS TEST NORMAL. NO LEFT OUTER F/QTY HISTORY SINCE HARNESS REPLACEMENT IN MEM ON 27DEC09. FAULT HISTORY SHOWED INTMT CODE 311-LEFT OUTER PROBES HIGH. CHECKED LEFT OUTER SUMP FOR WATER CONTAMINATION. FOUND A SIGNIFICANT AMOUNT. SUMPED LEFT OUTER TANK. FQIS SYSTEM TESTS NORMAL. REF FIM 28-42, AMM 28-42-00-5. SPAR TO FQIC WIRES OK PER ASM 28-42-00. ITEM OK FOR SERVICE.

Part: PITOT TUBE — MALFUNCTIONED (PITOT STATIC SYS) · airframe 38,186 hrs · 13,217 cycles

NO AIRSPEED INDICATION AT 80/KTS. REJECTED TAKEOFF, RETURNED TO GATE FOR FUEL. SUSPECT BAD ADC. FAC ORDERED TO MSN 1151676 AND THE ADC IS ORDERED TO MSN 1151673. NOTE THAT THE INFORMATION ON F/O SIDE IS GOOD. THE STANDBY AIRSPEED INDICATORS INFORMATION AND DISPLAY IS GOOD. THE STANDBY AIRSPEED INDICATORS INFORMATION & DISPLAY IS GOOD. FOUND CAPTAINS PITOT PROBE PLUGGED. REMOVED SOME TYPE OF CRUSTED MATERIAL FROM PROBE, CHECKED AGAIN WITH REVERSE FLOW AIR PRESSURE. STILL HAD SOME RESTRICTION. R & R CAPTAINS PITOT PROBE IAW MM 34-11-15-4. PURGED ENTIRE PITOT SYS FROM ADS COMPUTER TO PROBE, CHECKS GOOD. PERFORMED PITOT LEAK & CALIBRATION CHECK, CHECKS GOOD. SYS OPS CHECKS NORMAL PER MM 34-11-15-6.

Part: DRAIN LINE — CRACKED (NR 2 ENGINE) · airframe 36,785 hrs · 12,321 cycles

NR 2 ENGINE DRAIN MANIFOLD TUBE CRACKED REMOVED DRAIN MANIFOLD IAW FEDEX AMM 71-70-14-4. WELDED DRAIN MANIFOLD IAW EA 6-7170- 118466, POWER PLANT, DRAIN MANIFOLD ASSEMBLY CRACK, REPAIR. REINSTALLED DRAIN MANIFOLD IAW FEDEX AMM 71-70-14-4.

Part: WEB — CORRODED (ENTRY DOOR) · airframe 36,785 hrs · 12,321 cycles

LEFT AFT ENTRY DOOR HAS CORROSION ON THE VERTICAL WEB AROUND A GROMMET HOLE. REMOVED AND REPLACED LT VERTICAL WEB ON THE AFT ENTRY DOOR IAW SRM 51-40-21 PG 7.

Part: LINER — CORRODED (CARGO DOOR) · corrosion level 2 · airframe 36,785 hrs · 12,321 cycles

CORROSION AROUND THE AFT CARGO DOOR LINER FASTENER RECEPTACLE BETWEEN FRAME 62 AND FRAME 63 ON THE DOOR FRONT AND BACK SIDE OF THE DOOR. REMOVED CORROSION IAW A310-300SRM 51-22-00 AND FOUND TO BE OUT OF LIMITS IAW A310-300 SRM 52-30-00. MATERIAL ID 2024-T3 PO 602303.2 IAW A310-300 SRM 52-30-00; PG 35 AND 51-31-00; PGS 21 AND 22. CUT OUT DAMAGE AND FABBED DOUBLER IAW A310-300 SRM 51-70-10. ALODINED IAW A310-300 SRM 51-21-00. PRIMED IAW A310-300 SRM 51-21-10. PAINTED IAW A310-300 SRM 51-23-10. INSTALLED DOUBLER IAW A310-300 SRM 51-70-10.

Part: PANEL — DAMAGED (RUDDER) · airframe 36,785 hrs · 12,321 cycles

LEFT RUDDER PANEL, 25TH FASTENER FROM THE TOP OF THE RUDDER HAS 1 CELL OF WATER, MARKED IN WHITE MARKER. REPAIRED LT RUDDER PANEL 25TH FASTENER FROM TOP BY REMOVING DAMAGE & BONDING A NEW CORE & LAY-UP REPAIR PLIES IAW EA 6-5540-118453.

Part: LINER — CORRODED (CARGO DOOR) · airframe 36,785 hrs · 12,321 cycles

EXFOLIATED CORROSION AROUND THE AFT CARGO DOOR LINER FASTENER INSERT BETWEEN FRAME 59 AND FRAME 60 ON THE DOOR; FRONT AND BACK SIDE OF THE FRAME. MATERIAL ID 2024-T3 0.050 PO 602303.2 IAW A310-300 SRM 52-32-00; PG 35 AND 51-31-00; PG 21- 22. CUT OUT DAMAGE AND FABBED REPAIR IAW A310-300 SRM 51-70-10. ALODINED IAW A310-300 SRM 51-21-00. PRIMED IAW A310-300 SRM 51-21-10. PAINTED IAW A310-300 SRM 51-23-10. INSTALLED DOUBLER IAW A310-300 SRM 51-70-10.

Part: PANEL — DAMAGED (RUDDER) · airframe 36,785 hrs · 12,321 cycles

LEFT RUDDER PANEL, 2ND FASTENER FROM THE TOP HAS WATER IN 7 CONNECTED CELLS; 5 CONNECTED CELLS AND 5 INDIVIDUAL CELLS, (MARKED IN WHITE MARKER) AND DELAMINATION 3.3 INCH BY 1.9 INCH. REPAIRED LT RUDDER PANEL 2ND FASTENER FROM TOP BY REMOVING THE DAMAGED AREA & BONDING NEW CORE & PAY UP REPAIR PLIES IAW EA 6-5540-118453.

Part: DOOR FRAME — CORRODED (CARGO DOOR) · corrosion level 2 · airframe 36,785 hrs · 12,321 cycles

CORROSION AROUND THE AFT CARGO DOOR LINER FASTENER RECEPTICAL; LOWER PART OF FRAME 60 ON THE DOOR FRONT AND BACK SIDE OF THE DOOR. REMOVED CORROSION IAW A310-300 SRM 51-22-00 AND FOUND TO BE OUT OF LIMITS IAW A310-300 SRM 51-21-00. MATERIAL ID 2024-T3 0.050 PO 602303.2 IAW A310-300 SRM 52-32-00; PG 35 AND 51-31-00; PGS 21 AND 22. CUT OUT DAMAGE AND FABBED REPAIR IAW A310-300 SRM 51-70-10. ALODINED IAW A310-300 SRM 51-21-00. PRIMED IAW A310-300 SRM 51-21-10. PAINTED IAW A310-300 SRM 51-23-10. INSTALLED DOUBLER IAW A310-300 SRM 51-70-10.

Part: PANEL — DAMAGED (RUDDER) · airframe 36,785 hrs · 12,321 cycles

LEFT RUDDER PANEL, 3RD FASTENER FROM THE TOP OF THE RUDDER HAS WATER IN 7 CONNECTED CELLS; 4 CONNECTED CELLS; 2 CONNECTED CELLS AND 5 INDIVIDUAL CELLS, DELAMINATION 3.4 INCH BY 2.8 INCH. REPAIRED REMOVING DELAMINATED AREA & BONDING A NEW CORE & LAY UP REPAIR PLIES IAW EA 6-5540-118453.

Part: PANEL — DAMAGED (RUDDER) · airframe 36,785 hrs · 12,321 cycles

LEFT RUDDER PANEL, 4TH FASTENER FROM THE TOP OF THE RUDDER HAS WATER IN 5 CONNECTED CELLS; 2 INDIVIDUAL CELLS AND DELAMINATION 1.8" BY 1.7", MARKED IN WHITE MARKER. REPAIRED LT RUDDER PANEL SKIN 4TH FASTENER FROM TOP BY REMOVING DELAMINATED AREA & APPLIED REPAIR PLIES IAW EA 6-5540-118453.

Part: FITTING — CORRODED (FUSELAGE) · airframe 36,785 hrs · 12,321 cycles

EDDIE CURRENT AND VISUAL INSPECTIONS INDICATE SURFACE CORROSION AT APPROX 45 PLACES ON THE SCUFF PLATE RETAINER BETWEEN FR 14B AND FR 16A; LT FWD DOOR CUTOUT. SEE ATTACHED FOR LOCATIONS. MARKED IN BLUE ON THE RETAINER. REMOVED CORROSION IAW A310-SRM 53-10-18; FIG 101. ORIGINAL MATERIAL .500. MATERIAL LOSS .010. MATERIAL REMAINING .490. CENTER SECTION FOUND TO BE OUT OF LIMITS DUE TO A CRACK IAW A310 SRM 53-10-18; FIG 101. REMOVED AND REPLACED WITH NEW CENTER SECTION P/N A5361068856702; PO 611668.1 IAW A310 SRM 53-12-18; FIG 1 SHEET 2; 51-40-40; 51-40-21, PG 7; 51-21-10 AND 51-23-10.

Part: PAINT — PEELING (RT WING) · airframe 36,785 hrs · 12,321 cycles

PANEL 613 JR RT WING LEADING EDGE HAS PEELING PAINT. REMOVED DAMAGE; MATERIAL ID; CLEANED & PREPPED FOR REPAIR. FILLED DAMAGED AREAS; CURED; SANDED & APPLIED FOIL REPAIR. ALODINED, PRIMED & RESTORED FINISH IAW SRM 57-41-12 & SRM 51-75-10 PARA 5-A (5) & 5-C. INSTALLED IAW SRM 51-40-21; PG 7. MINOR REPAIR

Part: DRAIN LINE — CRACKED (NR 1 PYLON) · airframe 36,785 hrs · 12,321 cycles

NR 1 PYLON HYD/FUEL DRAIN PAN HAS A 3/4 INCH CRACK ON THE DRAIN TUBE AT 837. REMOVED DRAIN PAN REF A310-300 SRM 51-40-21; PG 7. WELD REPAIRED REF AEROSPATIALE DWG IA-546-10805 AND INSTALLED DRAIN PAN REF A310-300 SRM 51-40-21; PG 7.

Part: SKIN — CORRODED (RT WING) · airframe 36,785 hrs · 12,321 cycles

RIGHT WING UPPER SURFACE SKIN HAS AREAS OF CORROSION ALONG FRONT SPAR ATTACH ROW STA 556-565. REMOVED CORROSION IAW SRM 51-74-10 & WAS FOUND TO BE OUT OF LIMITS. ACCOMPLISHED HFEC OF HOLES IAW NTM 51-10-01. FLAT PEENED AREA IAW SRM 51-25-00. ALODINED IAW SRM 51-21-10. PRIMED IAW SRM 51-21-00. PAINTED IAW 51-21-00. REPLACED FASTENERS IAW SRM 51-40-21. MINOR REPAIR.

Part: FITTING — DAMAGED (L1 DOOR) · airframe 36,785 hrs · 12,321 cycles

L-1 LOWER AFT SEALING SECTION CORNER HAS A DOUBLE DRILLED HOLE. REMOVED AND REPLACED WITH NEW FITTING PART NR A5361155629804; PO 611014.1 IAW A310 SRM 51-40-21; PG 7.

Part: ACCESS PANEL — CRACKED (NR 1 NACELLE) · airframe 36,785 hrs · 12,321 cycles

NR 1 PYLON, LEFT SIDE THRU ACCESS PANEL 413EL THE INTERNAL WEBBING IS CRACKED AT A PREVIOUS WELD. REMOVED INTERNAL DOUBLER IAW SRM 51-40-21; PG 7. PART MARKED IAW GMM 7-0-1001. INSTALLED IAW SRM 51-40-21; PG 7. MINOR REPAIR

Part: SEAL DEPRESSOR — DAMAGED (CARGO BAY) · airframe 36,785 hrs · 12,321 cycles

FWD LWR CARGO PIT SEAL DEPRESSOR SCRATCHED AND WORN FWD AND AFT SIDES UPPER PORTION IN WORK.

Part: SKIN — CRACKED (NR 2 PYLON) · airframe 36,785 hrs · 12,321 cycles

NR 2 ENGINE AFT PYLON FAIRING; INBD MID SKIN IS CRACKED AT THREE PLACES. REMOVED DAMAGED SKIN AND DOUBLER. FABRICATED DOUBLER FROM .063 2024-0, PO 597274.1 IAW A310-300 SRM 51-26-10 AND 51-26-20; LOCATED HOLES IAW A310-300 SRM 51-40-40. ALODINED AND PRIMED IAW A310-300 SRM 51-21-10 AND 51-23-10. INSTALLED NEW SKIN AND DOUBLER IAW A310-300 SRM 51-40-21; PARAGRAPH 6.

Part: GUIDE — WORN (AILERON CABLES) · airframe 36,785 hrs · 12,321 cycles

IN LT MLG AREA; ALL CABLE GUIDES INBD OF THE LT TRUNNION FOR THE AILERON CABLES ARE WORN. REMOVED AND INSTALLED 3 NEW CABLE GUIDES ON THE INBD SIDE OF THE LT MLG TRUNNION FOR THE AILERON CABLES IAW A310-300 AMM 20-21-12 AND AMM 27-10-00-6.

Part: PANEL — CRACKED (NR 1 NACELLE) · airframe 36,785 hrs · 12,321 cycles

PYLON NR 1 LEFT SIDE LOWER SHIRT CLOSE OUT AT RIB 9 AND JUST FWD OF RIB 8, SHIRT IS CRACKED. REMOVED RUB STRIP, COVER PLATE, SHIRT PANEL AND ATTACH ANGLE IAW FEDEX A310-300 SRM 51-40-21, PG 6. LOCATED, DRILLED AND DEBURRED CLOSE OUT PANEL P/N A5461081160000, PO 558144.5; IAW A310-300 SRM 51-40-44. INSTALLED RUBSTRIP, COVER PLATE, SHIRT PANEL, CLOSE OUT PANEL AND ANGLE IAW A310-300 SRM 51-40-21, PG 7 AND PG 133.

Part: PANEL — CHAFED (NR 1 NACELLE) · airframe 36,785 hrs · 12,321 cycles

L/E NR 1 PYLON TOP PANEL P/N A572-44103-000 BACK SIDE HAS CHAFING MARKS IN NUMEROUS PLACES. BLENDED CHAFE MARKS IAW SRM 57-41-12 PG 102. MAT THICKNESS IS .035 IAW SRM 57-41-12, ITEM 60. MAT LOSS .006; MAT REMAINING .024, CHECKS TO BE OUT OF LIMITS IAW SRM 57-41-12. PAINTED NEW PANEL NR A57244103000; PO 610703.2 IAW SRM 51-23-10.

Part: FAIRING — CRACKED (NR 1 NACELLE) · airframe 36,785 hrs · 12,321 cycles

NR 1 ENGINE AFT PYLON FAIRING; AFT WELDED SKIN IS CRACKED. STOP DRILLED THE CRACK IAW SRM 54-55-51 FIG 201.FABRICATED REPAIR IAW SRM 54-55-51 FIG 201 & EA 06-5480-118441. INSTALLED REPAIR IAW SRM 54-55-51 FIG 201 & EA 06-5480-118441. MINOR REPAIR.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 36,785 hrs · 12,321 cycles

THE FLOORBEAM IS CORRODED AT THE CONNECTION TO FRAME 14 RT SIDE, Y - 1958. REMOVED DAMAGED SECTION OF THE FLOORBEAM IAW SRM 53-12-15. REMOVED FLOORBEAM END CONNECTORS, ATTACH ANGLES AND THE DUCT ATTACH BRACKET IAW SRM 53-12-15. RECEIVED MACHINED SECTION OF FLOORBEAM & NR 1 SPLICE ANGLES. FABRICATED DOUBLER, DOUBLER, SHIM & FILLER IAW SRM 53-12-15 FIG 203. ALODINED IAW SRM 51-21-10. PRIMED & APPLIED GRAY TOP COAT IAW SRM 51-23-10. INSTALLED NEW FLOORBEAM SECTION, ATTACH ANGLES, DUCT ATTACH BRACKET AND & REPAIR PARTS IAW SRM 53-12-15 FIG 203.

Part: DRAIN PAN — CRACKED (NR 2 NACELLE) · airframe 36,785 hrs · 12,321 cycles

NR 2 ENGINE PYLON HYDRAULIC/FUEL DRAIN PAN IS CRACKED IN 4 PLACES ON THE BOTTOM SIDE OF THE PAN. REMOVED DRIP PAN IAW AIRBUS A310 SRM 51-40-21; PG 7, WELD REPAIRED CRACKS IAW AEROSPATIALE DWG 41A54610805. REINSTALLED DRIP PAN IAW AIRBUS A310 SRM 51-40-21; PG 7.

Part: FRAME — CORRODED (FUSELAGE) · airframe 36,785 hrs · 12,321 cycles

FWD CARGO COMPT AT FR 36 AT RBL 29 FRAME CROSSBEAM IS CORRODED UNDER AND AROUND NUTPLATE. REMOVED CORROSION IAW SRM 51-74-10. BLENDED AREA FOUND TO BE OUT OF LIMITS. REMOVED CENTER GUIDE; ROLLER TRAY AND LATERIAL WEB TO FOM IAW SRM 51-40-21. WEIGH DAMAGE & FABBED REPAIR PARTS IAW SRM 53-10-15. ALODINED IAW SRM 51-21-10. PRIMED & PAINTED REPAIR PARTS IAW SRM 51-23-10. INSTALLED REPAIR PARTS IAW SRM 53-10-15. REINSTALLED CENTER GUIDE; LATERIAL GUIDE & LATERIAL WEB IAW SRM 51-40-21. MINOR REPAIR.

Part: PANEL — CORRODED (RT WING) · airframe 36,785 hrs · 12,321 cycles

RT WING PANEL 650 MB; INTERIOR SURFACE HAS FRETTING AROUND THE FASTENER HOLES. CLEANED AREAS AROUND THE FASTENER HOLES; CHECKED THE LIMITS AND FOUND TO BE OUT OF LIMITS IAW A310-300 SRM 57-20-16; PAGE 108; FIG 103. REPLACED WITH NEW PART A5735003900000; PO610289.2. INSTALLED ON JOB CARD 46S5109CP.

Part: PANEL — CORRODED (RT WING) · airframe 36,785 hrs · 12,321 cycles

RT WING VENT TANK PANEL 650 LB, HAS FRETTING AT THE INTERIOR FASTENER HOLES. CLEANED FRETTING AROUND THE FASTENER HOLES; CHECKED LIMITS AND FOUND TO BE OUT OF LIMITS IAW A310-300 SRM 57-20-16; PAGE 108; FIG 103. REPLACED WITH NEW PART A5735003900000 PO 610289.1. INSTALLED ON JOB CARD 46S5109CP.

Part: CHANNEL — FRACTURED (NR 2 PYLON) · airframe 36,785 hrs · 12,321 cycles

NR 2 PYLON AFT POWER FAIRING 485 AL AFT SUPPORT CHANNEL HAS A FRACTURE AT THE OUTBD EDGE. REMOVED CHANNEL & FABRICATE WEB & CHANNEL ON OPS 00748 & 00749. ASSEMBLED & INSTALLED TO NR 2 PYLON IAW SRM 51-40-01 PG 7.

Part: ATTACH ANGLE — CRACKED · airframe 36,785 hrs · 12,321 cycles

PYLON NR 1 LEFT SIDE, FWD ATTACH ANGLE FOR PANEL 413 CL IS CRACKED. REMOVED AND REPLACED BRACKET PER A310-300 SRM 51-40-21, PG 7.

Part: SKIN — CRACKED (NR 1 NACELLE) · airframe 36,785 hrs · 12,321 cycles

ON THE NR 1 ENG AFT PYLON FAIRING, O/B MID SKIN PANEL ASSY IS CRACKED AT THE MID FRAME. REMOVED MID FRAME IAW SRM 51-40-21; PGS 22 & 23; PARA 6. MATERIAL ID 2024- O .063 FOR THE PATCH & 2024-0 .071 FOR THE DOUBLER IAW SRM 54-55-51; PG 202. HEAT TREATED IAW TPS 1003 REV A. CUTOUT THE DAMAGE IAW SRM 54-55-51. FABRICATED DOUBLER & PATCH IAW SRM 54-55-51. ALODINED IAW SRM 51-21-10. PRIMED IAW SRM 51-23-10. INSTALLED DOUBLER & PATCH IAW SRM 54-55-51 & SRM 51-41-21; PARA 6HEAT TREAT LOAD NR HT0229081.

Part: FAIRING — TORN (EMPENNAGE) · airframe 36,785 hrs · 12,321 cycles

EMPENNAGE RT LOWER FAIRING IS TORN. REMOVED AND REPLACED THE FAIRING IAW MM 55-15-11-4. MINOR REPAIR.

Part: ANGLE — BENT (INTERCOSTAL) · airframe 36,785 hrs · 12,321 cycles

EMPENNAGE FR 87 TO 88 APPROX STRINGER 29, THE INTERCOSTAL IS BENT. REMOVED INTERCOSTAL FOR FOM IAW SRM 51-40-21. REMOVED DAMAGED ANGLE FROM THE INTERCOSTAL IAW SRM 51-40-21. RECEIVED ANGLE. INSTALLED ANGLE AND INTERCOSTAL IAW SRM 51-40-21. MINOR REPAIR.

Part: ANGLE — BENT (INTERCOSTAL) · airframe 36,785 hrs · 12,321 cycles

EMPENNAGE FR 87 TO FR 88 APPROX AT STRINGER 26, THE INTERCOSTAL IS BENT. REMOVED INTERCOSTAL FOR FOM IAW SRM 51-40-21. REMOVED DANAGED ANGLE FROM THE INTERCOSTAL IAW SRM 51-40-21. RECEIVED NEW ANGLE. INSTALLED NEW ANGLE & INTERCOSTAL IAW SRM 51-40-21. MINOR REPAIR

Part: STRUCTURE — CORRODED (LT ELEVATOR) · airframe 36,785 hrs · 12,321 cycles

LEFT ELEVATOR LEADING EDGE INTERIOR; FWD OF THE OUTBOARD ACTUATOR IS CORRODED. REMOVED AND REPLACED IAW AMM 27-31-24. PERFORMED A FUNCTIONAL TEST OF THE ELEVATOR REF AMM 27-31-00; TEST GOOD. REMOVED AND REINSTALLED ACCESS PANELS 335AB; 335BB; 335CB; 335DB AND 3356EB REF A310-300 AMM 55-22-13.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 36,785 hrs · 12,321 cycles

.25 INCH CRACK IN MAIN CABIN INTERCOSTAL BETWEEN FRAME 79 AND FRAME 80/82 AND STRINGER 26L. REMOVED AND REPALCED WEB IAW A310-300 SRM 51-20-41. MINOR REPAIR

Part: SEAT TRACK — GOUGED (BS 2984-3090) · airframe 36,785 hrs · 12,321 cycles

MAIN CABIN FLOOR BETWEEN FS 54.2 AND FS 54.3; 37 INCHES RIGHT OF CENTER LINE SEAT TRACK IS GOUGED/WORN. REPAIRED SEAT TRACK IAW A310-300 SRM 53-10-16; FIG 101.

Part: LUG — CORRODED (HORIZONTAL STAB) · airframe 36,785 hrs · 12,321 cycles

RT HORIZIONTAL STAB NR 6 ELEVATOR HINGE ARM LUG AT THE ELEVATOR IS CORRODED UPPER INBD. REMOVED AND REPLACED IAW AMM 55-16-45-1. FUNCTIONAL TEST GOOD IAW AMM 27-31-11.

Part: STRINGER — CRACKED (NR 2 NACELLE) · airframe 36,785 hrs · 12,321 cycles

NR 2 ENG AFT PYLON FAIRING (STRINGER), OUTBD SIDE, AFT CORNER IS CRACKED. REMOVED EXISTING DOUBLER FROM THE ADJACENT AREA TO FOM IAW SRM 51-40- 10. FABRICATED NEW REPAIR IAW SRM 54-55-51; FIG 201 & EA 06-5480-118441. STOP DRILLED THE CRACK & REMOVED THE DAMAGE IAW SRM 54-55-51; FIG 201. INSTALLED BOTH REPAIRS, EXISTING AND NEW IAW SRM 54-55-51; FIG 201 & EA 06-5480-118446. MINOR REPAIR.

Part: STRINGER — CRACKED (NR 2 NACELLE) · airframe 36,785 hrs · 12,321 cycles

NR 2 ENG AFT PYLON FAIRING (STRINGER), INBD INTERNAL, AFT SIDE AT NUTPLATES HAS 5 CRACKS. RECEIVED FROM STOCK P/N A545152411500 PO 569792.1. NEW MEMBER TO BE INSTALLED ON CARD 44T0512-2.

Part: RELAY — INOPERATIVE (FIRE DETECTION) · airframe 36,785 hrs · 12,321 cycles

DISCHARGE AGENT 2 LIGHT FOR THE CARGO FIRE BOTTLES FAILS TEST. DISCHARGE AGENT 2 LIGHT DID NOT ILLUMINATE UNTIL 75 MINUTES. REMOVED AND REPLACED RELAY 14WM REF ESPM 20-46-50. DISCHARGE AGENT 2 REMINDER LIGHT OPS CHECK GOOD REF AMM 26-23-00-5.

Part: FLAP TRACK — CRACKED · airframe 36,785 hrs · 12,321 cycles

PARTS RACK, FLAP TRACK FAIRING 632 CB, AFT WEB IS CRACKED. REMOVED AND REINSTALLED WEB ASSEMBLY AND REPLACED WEB IAW A310-300 SRM 51-40-21.

Part: SKIN — CORRODED (FUSELAGE) · airframe 36,785 hrs · 12,321 cycles

EXTERIOR SKIN AT THE AFT EDGE OF THE NOSE WW CUTOUT TRIPLER IS CORRODED AT FR 17, BETWEEN STR 55 R AND STR 54 R. BLENDED AFT EDGE OF THE NOSE W/W CUTOUT TRIPLER IAW SRM 51-74-10. FOUND TO BE WITHIN LIMITS IAW SRM 53-12-12, DIAGRAM 102. ALODINED IAW SRM 51-21-10. PRIMED IAW SRM 51-23-10. INSTALLED FASTENERS IAW SRM 51-40-21. PAINTED IAW SRM 51-23-10. MINOR REPAIR.

Part: SUPPORT ANGLE — CORRODED (NR 2 NACELLE) · airframe 36,785 hrs · 12,321 cycles

NR 2 PYLON, ACCESS PANEL 484 BR CUTOUT, 2 AFT VERTICAL SUPPORT ANGLES HAVE CORROSION AROUND THE NUTPLATES AND FASTENER HOLES. REMOVED AND REPLACED GUSSET IN REF TO SRM 51-40-21; PG 7.

Part: SKIN — DELAMINATED (RT ELEVATOR) · airframe 36,785 hrs · 12,321 cycles

RT ELEVATOR UPPER SURFACE IS DELAMINATED APPROX 8 INCHES FROM TE TO TE FROM NR 1 HINGE ARM TO NR 6 HINGE ARM APPROX 8 FT. UPON FURTHER INSPECTION; THE ELEVATOR WAS FOUND TO BE SERVICEABLE. THE AREA NOTED IN THE DISCREPANCY IS NOT DELAMINATED.

Part: BEAM — CORRODED (ZONE 100) · corrosion level 2 · airframe 36,313 hrs · 12,040 cycles

FOUND CORROSION ON AFT CARGO DOOR SILL BEAM BETWEEN FRAME 59-60. AREA IS UNDER FRAME 59A. REPAIR PERFORMED BY CUT OUT SILL BEAM WEB AND INSTALLING REPAIR ANGLE AND FILLER IAW EA 6-5317-82915 AND RAS/DAHAM/4019686/2005 ISSUE A.

Part: FRAME — CORRODED (ZONE 100) · corrosion level 2 · airframe 36,313 hrs · 12,040 cycles

HEAVY CORROSION ON FRAME 37 BETWEEN STRG 54 LT AND 53 RT. FRAME SPLICE REPAIR PERFORMED IAW SRM 53-10-13/FIG 203.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 36,313 hrs · 12,040 cycles

CORROSION ON STRINGER 43 LT AT FRAME 38. STRINGER SPLICE REPAIR PERFORMED IAW SRM 53-10-14/FIG 201.

Part: FITTING — CORRODED (ZONE 800) · corrosion level 2 · airframe 36,313 hrs · 12,040 cycles

FOUND CORROSION SPOT ON LT FWD PAX DOOR FITTING AT XP715 BETWEEN BEAMS 3 AND 5. REPAIR PERFORMED BY CUTTING-OUT THE FITTING WEB IN ORDER TO REMOVE CORROSION AND PERFORMING HFEC INSPECTION OF THE REWORKED AREA, INSTALLING REPAIR DOUBLER WITH MONEL RIVETS IAW EA 6-5211-92150 AND RAS/AS/0178/2005 ISSUE A.

Part: FRAME — CRACKED (ZONE 800) · airframe 36,313 hrs · 12,040 cycles

CRACKED VERTICAL FRAME SEGMENT 3.1 ON RT EMERGENCY EXIT DOOR BETWEEN FRAME 42A-43A, BETWEEN BEAM 5 AND 6. REPLACEMENT ON FRAME SEGMENT IAW SRM 51-72-10.

Part: WEB — DAMAGED (ZONE 100) · airframe 36,313 hrs · 12,040 cycles

DAMAGED WEB PLATE BETWEEN FRAME 86-87, STRG 39 RT. REPLACEMENT OF WEB IAW SRM 51-72-10.

Part: SKIN PANEL — MISREPAIRED (ZONE 100) · airframe 36,313 hrs · 12,040 cycles

EXISTING INTERNAL SKIN FLUSH DOUBLER REPAIR BETWEEN FRAME 83-84, STRG 38 RT- 40 RT, NOT CONFORM TO SRM 53-10-12/FIG 227. DOUBLER THICKNESS OF ONLY 1,8MM. INSTALLED FLUSH REPAIR IS ACCEPTABLE AS PERMANENT REPAIR, REPLACEMENT OF RIVETS LN9198-4000 ON EACH SIDE OF THE STRINGER FOOT TO SKIN BY HI-LOKS (HL18-6) ACC TO SRM 53-19-14/FIG 201, IAW EA 6-5318-92146 AND RAS/DAHAM/4019725/2005 ISSUE B.

Part: FRAME — CORRODED (ZONE 100) · corrosion level 2 · airframe 36,313 hrs · 12,040 cycles

HEAVY CORROSION ON CROSS STRUT FRAME 87 LT, AFT SIDE. REPLACEMENT OF CROSS STRUT IAW SRM 51-72-10.

Part: SKIN — DAMAGED (RUDDER) · airframe 36,313 hrs · 12,040 cycles

FOUND DAMAGED AREA ON RUDDER, TRAILING EDGE, LOWER SIDE. REPAIR PERFORMED BY LAMINATING THE EDGE IAW SRM 55-41-12/FIG 208A WITH GLASFABRIC.

Part: ANGLE — CORRODED (ZONE 100) · corrosion level 2 · airframe 36,313 hrs · 12,040 cycles

HEAVY CORROSION ON CONNECTING ANGLE FRAME 64, STRG 36 RT. REPLACEMENT OF ANGLE IAW SRM 51-72-10.

Part: SKIN PANEL — CORRODED (ZONE 100) · corrosion level 2 · airframe 36,313 hrs · 12,040 cycles

THREE CORROSION SPOTS ON INNER SKIN PANEL BETWEEN FRAME 18-19 AND BETWEEN STRG 49-51 LHS. REPAIR PERFORMED BY LOCAL CUT OUT AF SKIN PANEL BETWEEN STRG 49-50 AND SMOOTH REWORK OF REMAINING CORRODED AREAS, HFEC-, ROTOTEST INSPECTION AND INSTALLING EXTERNAL SKIN DOUBLER IAW EA 6-5312-92140 AND RAS/AS/135/2005 ISSUE A.

Part: SKIN — DELAMINATED (ZONE 600) · airframe 36,313 hrs · 12,040 cycles

FOUND EXISTING REPAIRS ON THE STOP-SURFACES ON SPOILER NR 4 RT, MONEL RIVETS NSA5414-32 AND WASHERS WERE USED INSTEAD OF NSA1919-M FASTENERS ON TOP SKIN RIB 01 AND 19, DELAMINATION ON TOP SKIN AT STOP-FITTING AREAS. REPAIR PERFORMED BY FABRICATE BOND AN ANGLE CARBON PRE-CURED DOUBLER AND INSTALLING BLIND RIVETS MONEL NSA1919-M04S-W ON DELAMINATED AREAS AT TOP SKIN IAW. EA 6-5773-82925 AND RAS 038772/012/2005 ISSUE A.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 36,313 hrs · 12,040 cycles

HEAVY CORROSION ON STRINGER 44 LHS, BETWEEN FRAME 20-23. STRINGER SPLICE REPAIR PERFORMED IAW SRM 53-10-14/FIG 201.

Part: SKIN PANEL — CORRODED (ZONE 100) · corrosion level 2 · airframe 36,313 hrs · 12,040 cycles

TWO CORROSION SPOTS OUT OF SRM LIMITS ON INTERNAL SKIN BETWEEN FRAME 19-20, STRG 51-52 LHS. REPAIR PERFORMED BY CORROSION REMOVAL, FLAP PEENING, NDT INSPECTION FOR CRACK FREE CONDITION AND INSTALLATION OF ENLARGED FILLER AND FINGER STRAP IAW EA 6-5313-82909 AND RAS/DABRE/7005417/2006 ISSUE A.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 36,313 hrs · 12,040 cycles

HEAVY CORROSION ON STRG 27 RT, BETWEEN FRAME 74-75 AND FRAME 75-75A. PARTIAL REPLACEMENT OF STRINGER 27 RT, C74-76 WITH THREE COUPLINGS BETWEEN FRAME 73A-74, FRAME 74-75 AND FRAME 75A-76 IAW EA 6-5318-82912 AND RAS/DAHAM/4019688/2005 ISSUE A.

Part: SKIN — DAMAGED (ZONE 100) · airframe 36,313 hrs · 12,040 cycles

ENLARGED HOLES IN FUSELAGE SKIN AT BEAM 10 BETWEEN FRAME 68-69 AND AT FRAME 67 BETWEEN STRINGER 43-44 RT, BULK CARGO DOOR CUT OUT. REPLACEMENT OF BEAM 10 IAW SRM 51-72-10.

Part: SKIN — DELAMINATED (ZONE 500) · airframe 36,313 hrs · 12,040 cycles

FOUND EXISTING REPAIRS ON THE STOP-SURFACES ON SPOILER NR 4 LT, MONEL RIVETS NSA5414-32 AND WASHERS WERE USED INSTEAD OF NSA1919-M FASTENERS ON TOP SKIN RIB 01 AND 19, DELAMINATION ON TOP SKIN AT STOP-FITTING AREAS. REPAIR PERFORMED BY FABRICATE BOND AN ANGLE CARBON PRE-CURED DOUBLER AND INSTALLING BLIND RIVETS MONEL NSA1919-M04S-W ON DELAMINATED AREAS AT TOP SKIN IAW EA 6-5773-82925 AND RAS 038772/012/2005 ISSUE A.

Part: SUPPORT FITTING — CORRODED (ZONE 300) · corrosion level 2 · airframe 36,313 hrs · 12,040 cycles

FOUND CORROSION ON THS SUPPORT FITTING, STA 93, RIB3 LT. REPLACEMENT OF FITTING IAW SRM 51-72-10.

Part: WEB — DAMAGED (ZONE 100) · airframe 36,313 hrs · 12,040 cycles

FOUND DAMAGED WEB PLATE BETWEEN FRAME 86-87, STRG 33 RT. REPLACEMENT OF WEB IAW SRM 51-72-10.

Part: WEB — DAMAGED (ZONE 100) · airframe 36,313 hrs · 12,040 cycles

DAMAGED WEB PLATE BETWEEN FRAME 85-86, STR 33 RT. REPLACEMENT OF WEB IAW SRM 51-72-10.

Part: STRUT — CORRODED (ZONE 800) · corrosion level 2 · airframe 36,307 hrs · 12,034 cycles

CORROSION ON U-STRUT AT UPPER EDGE OF AFT PAX DOOR LT, BETWEEN FRAME 73A-75A. REPLACEMENT OF STRUT IAW SRM 51-72-10.

Part: FAILSAFE — DAMAGED (ZONE 200) · airframe 36,308 hrs · 12,035 cycles

FOUND MISDRILLED FASTENER HOLES AT FRAME-FAIL-SAFE-RING, FUSELAGE SKIN BETWEEN FRAME 73-76, STRG 26-27 RHS. REPAIR PERFORMED BY OVERSIZING HOLES AND INSTALLATION HL13VF8 (DAN8-8) FASTENERS IAW EA 6-5318-82891 AND RAS/DAHAM/4019615/2005 ISSUE A.

Part: FRAME — CORRODED (ZONE 100) · corrosion level 2 · airframe 36,307 hrs · 12,034 cycles

CORROSION ON WEB AND INNER FLANGE OF FRAME 75A RT, AFT PAX DOOR BETWEEN STRG 26-27 RT. REPAIR PERFORMED BY SMOOTH BLEND OUT, HFEC INSPECTION AND FLAP PEENING IAW EA 6- 5318-82893 AND RAS/DAHAM/4019630/2005 ISSUE A.

Part: WEB — DAMAGED (ZONE 100) · airframe 36,308 hrs · 12,035 cycles

DAMAGED WEB PLATE AT STRG 36 RT, BETWEEN FRAME 86-87. REPLACEMENT OF WEB IAW SRM 51-72-10.

Part: SKIN — CHAFED (ZONE 600) · airframe 36,307 hrs · 12,034 cycles

FOUND CHAFING MARKS ON LEADING EDGE SKIN BETWEEN SLAT TRACK 7-8 OF RT WING. NOSE SKIN REPAIR PERFORMED IAW SRM 57-41-12/FIG 203, 204.

Part: BEAM — CORRODED (ZONE 800) · corrosion level 2 · airframe 36,307 hrs · 12,034 cycles

HEAVY CORROSION ON BEAM NR 5 AT EMERGENCY EXIT DOOR RT, ZONE 844. REPLACEMENT OF BEAM NR 5 IAW SRM 51-72-10.

Part: PLATE — CORRODED (ZONE 100) · corrosion level 2 · airframe 36,307 hrs · 12,034 cycles

CORRODED SHEAR PLATE BETWEEN FRAME 36-37 LT, STRG 44. REPLACEMENT OF SHEAR PLATE IAW SRM 51-72-10.

Part: PLATE — CORRODED (ZONE 100) · corrosion level 2 · airframe 36,307 hrs · 12,034 cycles

CORRODED SHEAR PLATE BETWEEN FRAME 36-37 LT, STRG 44. REPLACEMENT OF SHEAR PLATE IAW SRM 51-72-10.

Part: PANEL — CRACKED (ZONE 300) · airframe 36,308 hrs · 12,035 cycles

TWO CRACKS AT LEADING EDGE ACCESS PANEL NR 2 OF RUDDER INNER SKIN, HONEYCOMP CORE AND OUTER SKIN CRACKED AT ACCESS HOLE EDGES, MAX CRACK LENGTH = 75MM. REPAIR PERFORMED BY WET-LAY-UP REPAIR AS PER TD/K4/S1/19611/2005/A, APPROVED BY EA 6-5542-82890 AND RAS/DAHAM/4019611/2005 ISSUE A.

Part: CROSSBEAM — CORRODED (ZONE 200) · corrosion level 2 · airframe 36,308 hrs · 12,035 cycles

FOUND CORROSION ON CROSS STRUT AT FRAME 87, STRG 15 RT AFT SIDE. REPLACEMENT OF CROSS STRUT IAW SRM 51-72-10.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 36,308 hrs · 12,035 cycles

CORROSION ON STRINGER 52 LT, BETWEEN FRAME 35-38.1. STRINGER SPLICE REPAIR PERFORMED IAW SRM 53-10-14/FIG 201.

Part: SKIN PANEL — CORRODED (ZONE 100) · corrosion level 2 · airframe 36,307 hrs · 12,034 cycles

CORROSION ON INTERNAL SKIN BETWEEN FRAME 37-38, STRG 53 RT - 54 LT. REPAIR PERFORMED BY BLEND OUT, HFEC/ROTOTEST INSPECTION AND FLAP PEENING IAW EA 6-5314-82916 AND RAS/DATLS/0002629/2005 ISSUE A.

Part: FITTING — CORRODED (ZONE 800) · corrosion level 2 · airframe 36,308 hrs · 12,035 cycles

CORROSION ON FITTING AT FWD PAX DOOR LT. REPLACEMENT OF FITTING IAW SRM 51-72-10.

Part: FITTING — CORRODED (ZONE 800) · corrosion level 2 · airframe 36,308 hrs · 12,035 cycles

CORROSION ON FITTING AT FWD PAX DOOR LT. REPLACEMENT OF FITTING IAW SRM 51-72-10.

Part: PLATE — CORRODED (ZONE 200) · corrosion level 2 · airframe 36,308 hrs · 12,035 cycles

HEAVY CORROSION ON SHEAR PLATE BETWEEN FRAME 79-80, STRG 26 RT. REPLACEMENT OF CONN SEGMENT IAW SRM 51-72-10.

Part: COUPLING — DAMAGED (ZONE 200) · airframe 36,307 hrs · 12,034 cycles

DAMAGED COUPLING AT STRG 4 LT BETWEEN FRAME 87-88. REPLACEMENT OF COUPLING IAW SRM 51-72-10.

Part: STRINGER SPLICE — CORRODED (ZONE 100) · corrosion level 2 · airframe 36,307 hrs · 12,034 cycles

HEAVY CORROSION ON STRINGER SPLICE 32 RT, BETWEEN FRAME 64-65. REPLACEMENT OF STRINGER SPLICE IAW SRM 51-72-10.

Part: PLATE — CORRODED (ZONE 100) · corrosion level 2 · airframe 36,307 hrs · 12,034 cycles

CORRODED SHEAR PLATES AT FOLLOWING AREAS: BETWEEN FRAME 32-33 RT, 33-34 RT, 32- 33 LT AND 33-34 LT. REPLACEMENT OF SHEAR PLATES IAW SRM 51-72-10.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 36,307 hrs · 12,034 cycles

CORRODED STRINGER 54 RT BETWEEN FRAME 37-38. PARTIAL STRINGER INSTALLATION WITH TWO STRINGER SPLICE REPAIRS BETWEEN FRAME 36-37 AND 37-38 PERFORMED IAW SRM 53-10-14/FIG 201.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 36,308 hrs · 12,035 cycles

CORROSION ON STRINGER 51 LT, BETWEEN FRAME 37-38.1. STRINGER SPLICE REPAIR PERFORMED IAW SRM 53-10-14/FIG 201.

Part: SKIN PANEL — DAMAGED (ZONE 100) · airframe 36,307 hrs · 12,034 cycles

DAMAGES ON SKIN PANEL AT FRAME 33 BETWEEN STRG 38-39 RT. REPAIR PERFORMED BY REWORK DAMAGES TO A SMOOTH CONTOUR. MINIMUM THICKNESS FOLLOWING REWORK IS 1.37MM, NDT INSPECTION FOR CRACK FREE CONDITION AND ENLARGE THE INNER STRAP TO ACT AS A REPAIR DOUBLER IAW DD-0378007 ISSUE A, APPROVED BY EA 6-5314-92144 AND RAS/DABRE/7005386/2005 ISSUE A.

Part: FRAME — CORRODED (ZONE 800) · corrosion level 2 · airframe 36,307 hrs · 12,034 cycles

HEAVY CORROSION ON FRAME SEGMENT AT EMERGENCY EXIT DOOT RT, BETWEEN BEAM 4-5. REPLACEMENT OF FRAME SEGMENT IAW SRM 51-72-10.

Part: FLANGE — CORRODED (ZONE 100) · corrosion level 2 · airframe 36,308 hrs · 12,035 cycles

CORROSION ON OUTER FLANGE AT FRAME 91, BETWEEN STRG 45 LT-AD. REPLACEMENT OF OUTER FLANGE BETWEEN STRG 37 RT-37 LT IAW SRM 51-72-10.

Part: SUPPORT FITTING — CRACKED (ZONE 100) · airframe 36,308 hrs · 12,035 cycles

CRACKED SUPPORT FITTING BETWEEN FRAME 16A-17, STRG 44 RHS. REPLACEMENT OF FITTING IAW SRM 51-72-10.

Part: FITTING — DAMAGED (ZONE 600) · airframe 36,308 hrs · 12,035 cycles

AREAS OF IMPACT DAMAGE FOUND ON THE AFT FACE OF THE OUTBOARD LUG ON THE RT WING PYLON MOUNTING (ATTACH FITTING), RIB 8-9. REPAIR PERFORMED BY BLENDING DAMAGE TO REMOVE ALL SHARP EDGES, HFEC INSPECTION AND INSTALLING NEW SELF-LUBRICATING BEARING IAW EA 6-5720-82880 AND RAS/BAE/1000883/2005 ISSUE A.

Part: CROSSBEAM — CORRODED (ZONE 200) · corrosion level 2 · airframe 36,308 hrs · 12,035 cycles

CORROSION ON CROSS STRUT AT FRAME 86, STRG 15 RT FRONT SIDE. REPLACEMENT OF CROSS STRUT IAW SRM 51-72-10.

Part: FRAME — CORRODED (ZONE 100) · corrosion level 2 · airframe 36,308 hrs · 12,035 cycles

HEAVY CORROSION ON CONNECTING SEGMENT FRAME 70, STRG 44 RT. REPLACEMENT OF CONN SEGMENT IAW SRM 51-72-10.

Part: WEB — FAILED (ZONE 100) · airframe 36,307 hrs · 12,034 cycles

IN AUGUST 1198: SEVERAL SPOTS OF CORROSION HAD BEEN FOUND ON VERTICAL WEB (SEGMENT) OF PRESSURE BULKHEAD AT FRAME 39, Y=0. REPAIRS HAD BEEN PARTIALLY PERFORMED IN ACCORDANCE WITH TD 582.0939/98 ISSUE A IN JULY 2005: NEW CORROSION FINDINGS HAVE BEEN REPORTED, HOLE D WAS ALSO REPORTED NOT REPAIRED IAW TD 582.0939/98 ISS A. REPAIR PERFORMED IAW TD 582.0939/98 ISSUE A AT HOLE D AND IAW TD 942.001478/023/1998 ISSUE B AT HOLE B, APPROVED BY EA 6-5315-82897 AND RAS/AS/0130/2005 ISSUE A.

Part: WEB — CORRODED (ZONE 200) · corrosion level 2 · airframe 36,307 hrs · 12,034 cycles

HEAVY CORROSION ON TWO SHEAR WEBS AT STRINGER 26 LT AND RT, BETWEEN FRAME 75A-76. REPLACEMENT OF BOTH SHEAR WEBS LT AND RT IAW SRM 51-72-10.

Part: SKIN PANEL — FAILED (ZONE 200) · airframe 36,307 hrs · 12,034 cycles

EXISTING FLUSH REPAIR ON SKIN BETWEEN FRAME 2-3 AD, CAUSED BY A FLIGHT TEST INSTALLATION CONFORM TO DRW A536-11822, GOT IN CONFLICTS WITH PTOF CONVERSION. REPAIR MODIFIED WITH A THIRD FASTENER ROW THROUGH ALL LAYERS CONFORM TO REPAIR DRW A536-11822 IAW. EA 6-5311-82922 AND RAS/DABRE/7005422/2005 ISSUE A.

Part: SKIN PANEL — CHAFED (ZONE 100) · airframe 36,307 hrs · 12,034 cycles

CHAFING MARK FOUND ON LOWER INNER SKIN BETWEEN FRAME 46-47 AND STRG 44-45. REPAIR PERFORMED BY SMOOTHLY REWORK, DVI-HFEC-ROTOTEST INSPECTION AND INSTALLATION OF R1 OVERSIZED FASTENERS IF NECESSARY IAW EA 6-5315-82917 AND RAS 038213/011/2005 ISSUE A.

Part: CROSSBEAM — CORRODED (ZONE 200) · corrosion level 2 · airframe 36,308 hrs · 12,035 cycles

CORROSION ON CROSS STRUT AT FRAME 84, STRG 15 RT FRONT SIDE. REPLACEMENT OF CROSS STRUT IAW SRM 51-72-10.

Part: SKIN PANEL — CORRODED (ZONE 200) · corrosion level 2 · airframe 36,305 hrs · 12,032 cycles

CORROSION ON THE INTEGRAL SKIN PANEL BETWEEN FRAME 76-80, STRG 6 LT - 6 RT AND BETWEEN FRAME 80-91, STRG 8 LT - 8 RT. REPAIR PERFORMED BY CUT OUT SOME AREAS (OUT OF SRM LIMIT) AND INSTALLATION OF FIVE EXTERNAL DOUBLERS IAW EA 6-5319-82905 AND RAS/DAHAM/4800124/2005 ISSUE B.

Part: SKIN PANEL — CORRODED (ZONE 200) · corrosion level 2 · airframe 36,305 hrs · 12,032 cycles

CORROSION ON UPPER SIDE (FRAME 14, STRG 11) ) OF THE FWD RT PAX DOOR FAIL/SAFE RING. REPAIR PERFORMED BY SMOOTH REWORK, HFEC/ROTOTEST INSPECTION AND OVERSIZING HOLES IN CORRODED AREA IAW EA 6-5312-82879 AND RAS/AS/151/2005 ISSUE A.

Part: FLOORBEAM — CORRODED (ZONE 100) · corrosion level 2 · airframe 36,305 hrs · 12,032 cycles

HEAVY CORROSION ON CROSSBEAM FRAME 63 LT, CARGO COMP FLOOR STRUCTURE. CROSSBEAM SPLICE REPAIR PERFORMED IAW SRM 53-10-15/FIG 207.

Part: SKIN PANEL — WORN (ZONE 600) · airframe 36,305 hrs · 12,032 cycles

ELONGATED HYDRAULIC FITTING HOLES ON PYLON NR 2 SUPPORT BRACKET, BOTTOM WING SKIN PANEL 2. REPAIR PERFORMED BY OVERSIZING HOLES AND INSTALLING BUSHINGS IAW EA 6-5720-82887 AND RAS/BAE/1000947/2005 ISSUE A.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 36,305 hrs · 12,032 cycles

CORROSION ON STRINGER 53 LT BETWEEN FRAME 70-71 AND STRINGER 56 LT BELOW FRAME 70. STRINGER SPLICE REPAIR PERFORMED IAW SRM 53-10-14/FIG 201.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 36,305 hrs · 12,032 cycles

CORROSION ON STRINGER 51 RT BETWEEN FRAME 76-77. STRINGER REPAIR PERFORMED IAW FREIGHTER A300-600 SRM 53-10-14/FIG 206, APPROVED BY EA 6-5318-82875 AND RAS/DAHAM/4019558/2005 ISSUE A.

Part: SKIN PANEL — CORRODED (ZONE 200) · corrosion level 2 · airframe 36,305 hrs · 12,032 cycles

CORROSION ON FAIL/SAFE RING, LT FWD PAX DOOR, SOME AREAS OUT OF LIMIT. REPAIR PERFORMED BY SMOOTH REWORK AND HFEC/ROTOTEST INSPECTION IAW EA 6-5312-82878 AND RAS 037837/015/2005 ISSUE A.

Part: STRINGER — MISREPAIRED (ZONE 100) · airframe 36,305 hrs · 12,032 cycles

DURING CHANGING OLD DOUBLER REPAIR BETWEEN FRAME 72-73, STRG 29-32 LT FOUND LESS EGDE MARGING IN STRINGER 32 LT. STRINGER SPLICE REPAIR PERFORMED IAW SRM 53-10-14/FIG 201.

Part: SKIN — DELAMINATED (NR 2 SPOILER) · airframe 36,305 hrs · 12,032 cycles

FOUND DELAMINATION ON SPOILER NR 2 LT, LOWER SKIN (100 BY 30 MM). REPAIR PERFORMED IAW SRM 57-70-00/201/PARA 12.

Part: SKIN PANEL — FAILED (ZONE 100) · airframe 36,305 hrs · 12,032 cycles

FOUND OLD SMALL FLUSH DOUBLER REPAIR BETWEEN FRAME 72-73, STRG 41-42 LHS, NOT CONFORM TO SRM. REPAIR PERFORMED BY INSTALLING NEW EXTERNAL DOUBLER IAW SRM 53-10-12/FIG 227.

Part: SKIN — CHAFED (ZONE 500) · airframe 36,305 hrs · 12,032 cycles

FOUND CHAFING MARKS ON LEADING EDGE SKIN BETWEEN SLAT TRACK NR 5 AND 6 LT WING. REPLACEMENT OF DAMAGED NOSE SKIN IAW SRM 51-72-10.

Part: SKIN PANEL — WORN (ZONE 500) · airframe 36,305 hrs · 12,032 cycles

ELONGATED HYDRAULIC FITTING HOLES ON PYLON NR 1 SUPPORT BRACKET, BOTTOM WING SKIN PANEL 2. REPAIR PERFORMED BY OVERSIZING HOLES AND INSTALLING BUSHINGS IAW EA 6-5720-82887 AND RAS/BAE/1000947/2005 ISSUE A.

Part: SKIN PANEL — CORRODED (ZONE 200) · corrosion level 2 · airframe 36,305 hrs · 12,032 cycles

CORROSION ON FWD DOOR FRAME PANEL, RT FWD PAX DOOR, BETWEEN FRAME 13-14C, STRG 9-14, SOME AREAS OUT OF LIMIT. REPAIR PERFORMED BY SMOOTH REWORK AND HFEC/ROTOTEST INSPECTION IAW EA 6-5312-82923 AND RAS 037817/008/2005 ISSUE A.

Part: RIB — CORRODED (ZONE 300) · corrosion level 2 · airframe 36,305 hrs · 12,032 cycles

FOUND CORRODED RIB 54 ON RUDDER. REPLACEMENT OF RIB 54 IAW SRM 55-41-19.

Part: FRAME — CORRODED (ZONE 100) · corrosion level 2 · airframe 36,305 hrs · 12,032 cycles

CORROSION ON MILLED FRAME 63A BETWEEN STRG 32-35 AND STRG 39-41 RT. REPAIR PERFORMED BY SMOOTH BLEND OUT, HFEC INSPECTION FOR NIL FINDINGS AND FLAP PEENING IAW EA 6-5317-82874 AND RAS/DAHAM/4019554/2005 ISSUE A.

Part: BOX BEAM — CRACKED (ZONE 200) · airframe 36,305 hrs · 12,032 cycles

TWO CRACKS IN HOLE (EACH 10MM) FOUND IN THE UPPER TORSION BOX IN BEAM AT FRAME 75, STRG 11 LT. REPAIR PERFORMED BY CUT OUT OF DAMAGED AREA, INSTALLATION OF FILLER AND REPAIR ANGLE IAW EA 6-5318-82894 AND RAS/DAHAM/4019625/2005 ISSUE A.

Part: SILL — CORRODED (ZONE 100) · corrosion level 2 · airframe 36,305 hrs · 12,032 cycles

CORROSION ON THE UPPER FLANGE AFT CARGO DOOR SILL BEAM BETWEEN FRAME 59-59A RT, OUT OF LIMIT. REPAIR PERFORMED BY BLEND OUT AND FLAP PEENING IAW EA 6-5317-82872 AND RAS/DATLS/0002588/2005 ISSUE A.

Part: SKIN — CHAFED (ZONE 500) · airframe 36,305 hrs · 12,032 cycles

CHAFING MARK ON INBOARD FLAP VANE LT, CAUSED BY NOT INSTALLED PROTECTIVE PLATE AT VANE-NOSE-SKIN FOR JAM RETRACTED MICROSWITCH STRIKER, RIB 2-22. REPAIR PERFORMED BY SMOOTH BLEND OUT CHAFING MARK IAW EA 6-5752-82885 AND RAS/DABRE/7005373/2005 ISSUE B AND INSTALLATION OF PROTECTION PLATE IAW SRM 57-52-12/201/PARA 4 C.

Part: FRAME — CORRODED (ZONE 100) · corrosion level 2 · airframe 36,305 hrs · 12,032 cycles

OLD REPAIRS WITH NEW CORROSION AT FRAME 40 BETWEEN 51-52 LT, 54-55 LT, 54-55 RT AND 50-51 RT. REPAIR PERFORMED BY REMOVE EXISTING REPAIR ANGLES AND INSTALLING NEW FABRICATED ANGLES IAW EA 6-5315-82860 AND RAS 037936/008/2005 ISSUE A.

Part: SKIN PANEL — FAILED (ZONE 200) · airframe 36,305 hrs · 12,032 cycles

FOUND EXISTING REPAIR DOUBLER ON FUSELAGE SKIN AFT OF FRAME 78 BETWEEN STRG 1LH - 1RH, NOT CONFORM TO SRM. OLD REPAIR REMOVED AND RENEWED IAW SRM 53-10-12/FIG 226.

Part: SKIN — DELAMINATED (ZONE 500) · airframe 36,305 hrs · 12,032 cycles

FOUND SEVERAL DELAMINATIONS TO TRAILING EDGE ON UPPER AND LOWER SKIN OF INBOARD FLAP LT. REPLACEMENT OF LT INBOARD FLAP TRAILING EDGE PER DRW A579-70868, SOLID FASTENERS ARE REPLACED BY BLIND FASTENERS. REPAIR APPROVED BY EA 6-5752-92147 AND RAS/DABRE/7005328/2005 ISSUE A.

Part: SKIN — DELAMINATED (TE FLAP) · airframe 36,305 hrs · 12,032 cycles

FOUND DELAMINATION AROUND OLD REPAIR ON TRAILING EDGE OF INNER FLAP RT, UPPER AND LOWER SKIN. REPLACEMENT OF RT INBOARD FLAP TRAILING EDGE PER DRW A579-70868, SOLID FASTENERS ARE REPLACED BY BLIND FASTENERS. REPAIR APPROVED BY EA 6-5752-92147 AND RAS/DABRE/7005360/2005 ISSUE A.

Part: SKIN — MISREPAIRED (ZONE 200) · airframe 36,305 hrs · 12,032 cycles

FOUND OLD EXTERNAL DOUBLER REPAIR ON FUSELAGE SKIN AT BUTT-JOINT FRAME 18 BETWEEN STRG 22-26 LT, NOT CONFORM TO SRM (RIVET SIZE). FOUND CORROSION AFTER REMOVAL. NEW DOUBLER REPAIR PERFORMED IAW DRW R536-11046 ISSUE B, HFEC AND ROTOTEST INSPECTION PERFORMED. REPAIR APPROVED BY EA 6-5312-82883 AND RAS 037833/025/2005 ISSUE A.

Part: SKIN PANEL — CORRODED (ZONE 200) · corrosion level 2 · airframe 36,305 hrs · 12,032 cycles

CORROSION ON FAIL/SAFE RING, LT FWD PAX DOOR, SOME AREAS OUT OF LIMIT. REPAIR PERFORMED BY SMOOTH REWORK AND HFEC/ROTOTEST INSPECTION IAW EA 6-5312-82878 AND RAS 037837/015/2005 ISSUE A.

Part: FITTING — UNKNOWN (ZONE 100) · airframe 36,305 hrs · 12,032 cycles

OLD REPAIR, FRAME 17, STR 44 LT WITH NO OLD RECORDS FOR RUN OUT FITTING REPLACEMENT OR PERMANENT REPAIR. STRUCTURE REPAIR PERFORMED IAW INSTRUCTION R536-10440 ISSUE C.

Part: SKIN — DELAMINATED (NR 2 SPOILER) · airframe 36,305 hrs · 12,032 cycles

FOUND DELAMINATION ON SPOILER NR 2 RT, LOWER SKIN (100 BY 30 MM). REPAIR PERFORMED IAW SRM 57-70-00/201/PARA 12.

Part: PANEL — DAMAGED (ZONE 400) · airframe 36,305 hrs · 12,032 cycles

FOUND DAMAGED HOLES ON BUTTERFLY REPAIR DOUBLERS AT INBOARD AND OUTBOARD SIDEWALL PANEL, PYLON NR 1 LT. REPAIR PERFORMED BY INSTALLING NEW DOUBLERS ON SIDEWALL PANELS IAW SRM 54-51-31/FIG 201.

Part: SKIN PANEL — FAILED (ZONE 100) · airframe 36,305 hrs · 12,032 cycles

OLD DOUBLER REPAIR BETWEEN FRAME 72-73, STRG 29-32 LT IS NOT CONFORM TO SRM 53-10-12/FIG 225/SH 2, DOUBLER THICKNESS IS 1,6MM INSTEAD OF 1,8MM. REPAIR PERFORMED BY INSTALLING NEW SKIN DOUBLER IAW SRM 53-10-12/FIG 228/SH 2.

Part: FITTING — CRACKED (ZONE 100) · airframe 36,305 hrs · 12,032 cycles

CRACKED FITTING BETWEEN STRG 45-47 RT AT FRAME 67, CARGO COMP FLOOR STRUCTURE. REPLACEMENT OF FITTING IAW SRM 51-72-10.

Part: ATTACH FITTING — GOUGED (ZONE 300) · airframe 36,305 hrs · 12,032 cycles

DEEP GOUGE ON LT MIDDLE VERTICAL STABILIZER TO FUSELAGE ATTACH FITTING, OUTBOARD SIDE AFT AREA. REPAIR PERFORMED BY SMOOTH BLEND OUT AND NDT INSPECTION FOR CRACK FREE CONDITION IAW EA 6-5319-82881 AND RAS/DAHAM/4019574/2005 ISSUE A.

Part: PANEL — DAMAGED (NR 2 NACELLE) · airframe 36,305 hrs · 12,032 cycles

FOUND DAMAGED HOLES ON BUTTERFLY REPAIR DOUBLER AT INBOARD SIDEWALL PANEL, PYLON NR 2 RT. REPAIR PERFORMED BY INSTALLING NEW DOUBLER ON SIDEWALL PANEL IAW SRM 54-51-31/FIG 201.

Part: FRAME — CORRODED (ZONE 100) · corrosion level 2 · airframe 36,305 hrs · 12,032 cycles

HEAVY CORROSION ON MILLED FRAME 59A BETWEEN STRG 40-42 RT. REPAIR PERFORMED BY CUT OUT DAMAGED PORTION AND PARTIAL REPLACEMENT OF FRAME IAW DRW R539-70138 ISSUE F, APPROVED BY EA 6-5317-82873 AND RAS/DAHAM/4019557/2005 ISSUE A.

Part: SKIN PANEL — DAMAGED (ZONE 800) · airframe 36,304 hrs · 12,031 cycles

FOUND GROOVES ON OUTER SKIN PANEL, AFT LOWER CORNER AT AFT PAX DOOR LT, ZONE 833 AND ON SKIN PANEL, LOWER EDGE AREA AT AFT PAX DOOR RT, ZONE 843. REPAIR PERFORMED BY INSTALLING EXTERNAL DOUBLER AS PER SRM 52-11-00/PB 235/PAR 5F/FIG 206 ON LT PAX DOOR AND IAW SRM 52-11-00/PB 217/PAR 5C/FIG 203 ON RT PAX DOOR.

Part: HINGE FITTING — CORRODED (ZONE 800) · corrosion level 2 · airframe 36,304 hrs · 12,031 cycles

NEW CORROSION ON OLD REPAIR, FOUND ON FWD PAX DOOR RT ON DOOR HINGE FITTING (LOWER ARM WEB - BOTTOM SIDE). CORROSION REMOVED (TOTAL OF 53 PERCENT REMOVED), FILLER AND OLD REPAIR DOUBLER INSTALLED IAW EA 6-5211-82884 AND RAS/AS/115/2005 ISSUE A.

Part: SMOKE DETECTOR — MALFUNCTIONED (E/E BAY) · airframe 35,251 hrs · 11,408 cycles

ON TAKEOFF, AT 1000FT AVIONICS SMOKE INDICATION COMPLIED W/QRA. NO OBSERVED SMOKE NOTED FROM SNIFFER FAN. RETURNED TO MEMPHIS. SMOKE WARNING DID GO OUT AFTER APPROX 7 MINUTES. WAS NOT OVERWEIGHT ON LANDING. PERFORMED TEST REF 26-15-00. TESTED GOOD. FOUND NO EVIDENCE OF HYDRAULIC LEAKAGE. FOUND EVIDENCE OF MOISTURE AT SMOKE DETECTORS 11WA AND 12WA. REMOVED AND REPLACED SMOKE DETECTOR 11WA AND 12WA REF MM 26-15-12-4, OPS CK GOOD. ACFT OK TO CONTINUE.

Part: PROBE — FAULTED (FUEL QTY) · airframe 34,529 hrs · 11,000 cycles

CLIMBING THRU 310 TO 370 THE FUEL INDICATION TOTAL BECAME A PROBLEM. TOTAL FUEL QUANTITY AND FIMS SHOWED US LANDING AT MAKE WITH 10,700 LBS. THERE WAS ZERO FUEL IN CTR AND TRIM TANK WITH INDICATION OF FUEL BEING TRANSFERRED TO TRIM. INDICATION RUNNING OUT OF FUEL. REMOVED AND REPLACED OF ISOLATION VALVE ACTUATOR. REMOVED AND REPLACED FUEL QUANTITY PROBES IN TRIM, TANK PROBES NR 15 AND NR 8. REMOVED AND REPLACED OF FUEL TRIM TANK HARNESS. REPLACED NR 8 FUEL PROBE.