N726FD

Part: ANGLE — DAMAGED (ZONE 60) · airframe 56,540 hrs · 29,739 cycles

(6-5710-T0307446 B PT4) R/H REAR SPAR AND BOTTOM PANEL AT JUNCTION WITH FUSELAGE / FRAME 47 FASTENER HOLES "A" HAS REJECTABLE INDICATION NOTED AT BOTTOM LAYERS. REPAIRED FASTENER HOLE "A" PER EA 6-5710-T0307446 C PT8 WINGS - BASIC WING STRUCTURE - AD 2019-12-04 - REAR SPAR AND BOTTOM PANEL AT JUNCTION WITH FUSELAGE / FRAME 47 FASTENER HOLE "A" (LHS AND RHS). MAJOR REPAIR

Part: ANGLE — CRACKED (ZONE 50) · airframe 56,540 hrs · 29,739 cycles

(6-5710-T0307446 B PT4) L/H REAR SPAR AND BOTTOM PANEL AT JUNCTION WITH FUSELAGE / FRAME 47 FASTENER HOLE "G" HAS CRACK INDICATION NOTED AT 12:0'CLOCK BOTTOM LAYERS. REPAIRED FASTENER HOLE "G" PER EA T-6-5710-T0307446 C PT8 WINGS - BASIC WING STRUCTURE - AD 2019-12-04 - REAR SPAR AND BOTTOM PANEL AT JUNCTION WITH FUSELAGE / FRAME 47 FASTENER HOLES "A" (LHS AND RHS). MAJOR REPAIR

Part: NONE — NONE (N/A) · airframe 56,540 hrs · 29,739 cycles

ENTERED FOR TRAINING PURPOSES ONLY NO ACTION REQUIRED.

Part: JOINT — DAMAGED (ZONE 20) · airframe 56,540 hrs · 29,739 cycles

FWD CARGO FRAME 40 LH HAS FASTENERS WITH DAMAGED INDICATIONS HOLES A, B, AND C. COMPLIED WITH EA 6-5710-127939 PT8: WINGS - BASIC WING STRUCTURE - ALI WORKCARD 5710390-00-11 REPAIRED CRACKED HOLES IN CTR WING JOINT - FR 40 LH / RH. MAJOR REPAIR

Part: SWITCH — FAILED (HYD SYSTEM) · airframe 55,848 hrs · 29,275 cycles

RECEIVED 4 TRANSIENT ECAM GREEN HYD PR LO INDICATION DURING TAXI, WHICH ALSO CAUSED AN AUTO-BRAKE SYSTEM TO FAILURE. ANALOG AND ECAM GREEN HYD PRESSURE AND QUANTITY BOTH SHOWED GOOD WHILE ECAM MESSAGE WAS DISPLAYED. HAD TO ABORT T/O DUE TO SECOND INDICATION. REMOVED AND REPLACE GREEN HYD PRESSURE SWITCH 30WW PER AMM 31-53-51-04 OP AND LEAK CHECK GOOD. REPLACED SDAC PRECAUTIONARY DUE TO ONLY ECAM ALERT AND ALL OTHER INDICACTIONS NORMAL PER AMM 31-55-22-04 OP CHECK GOOD. PERFORMED ENGINE STATIC RUN PER JRH. NO FAULTS AND ALL IDICATIONS NORMAL.

Part: DAMPER — NO TEST (FWD GALLEY DOOR) · airframe 55,480 hrs · 29,042 cycles

DONT PASS OPERATIONAL TEST PASSENGER CREW DOOR 831 DOOR DAMPER AT FWD GALLEY AREA (1 EA). REPLACED PASSENGER CREW DOOR 831 DOOR DAMPER, IAW A300-600 AMM 52-10-14-04-01 AND A300-600 AMM 52-10-14-05-01. PERFORMED FUNCTIONAL TEST, IAW A300-600 AMM 52-10-11-05-01 ITEM 2H STEP 33 AND 34, FUNCTIONAL TEST IS OK.

Part: FLOOR PANEL — CRACKED (ZONE 100) · airframe 55,480 hrs · 29,042 cycles

CRACK FLOOR PANEL 131AG IN FWD CARGO COMPARTMENT (1 EA). REPLACED FLOOR PANEL 131AG IN FWD CARGO COMPARTMENT, IAW A300-600 AMM 06-41-53-00-09 AND A300-600 SRM 51-72-10-001 AND 51-40-21.

Part: FLOOR PANEL — CRACKED (ZONE 100) · airframe 55,480 hrs · 29,042 cycles

CRACK FLOOR PANEL 131CG IN FWD CARGO COMPARTMENT (1 EA). REPLACED FLOOR PANEL 131CG IN FWD CARGO COMPARTMENT, IAW A300-600 AMM 06-41-53-00-09 AND A300-600 SRM 51-72-10-001 AND 51-40-21.

Part: FLOOR PANEL — CRACKED (ZONE 100) · airframe 55,480 hrs · 29,042 cycles

CRACK FLOOR PANEL 131UF IN FWD CARGO COMPARTMENT (1 EA) REPLACED FLOOR PANEL 131UF IN FWD CARGO COMPARTMENT, IAW A300-600 AMM 06-41-53-00-09 AND A300-600 SRM 51-72-10-001 AND 51-40-21.

Part: FLOOR PANEL — CRACKED (ZONE 200) · airframe 55,480 hrs · 29,042 cycles

CRACK FLOOR PANEL 232TG IN MAIN DECK CARGO COMPARTMENT IN PASSENGER CABIN. REPAIRED FLOOR PANEL 232TG IN MAIN DECK CARGO COMPARTMENT IN PASSENGER CABIN, AS PER A300-600 SRM 53-10-20 PB201 PARA 9C (3)(B). TOOL USED CALIPER P/N 500-197-30 SN A18135103 DUE DATE 14-JUL-21.

Part: FRAME — CRACKED (FRM 13) · airframe 55,480 hrs · 29,042 cycles

CRACK INDICATION ON FRAME 13 OPEN FASTENER HOLE AT LEVEL OF STR 9 RT SIDE, CRACK DIRECTION IS 9 O`CLOCK AT FWD GALLEY AREA (1 EA). REPLACED STRINGER SECTION LOCATED ON FR 13 AT LEVEL STR 9 RT SIDE, IAW A300-600 SRM 51-40-20-001 AND DRAWING #A53610301 ISSUE K SHEET 1.

Part: FRAME — CRACKED (ZONE 100) · airframe 55,480 hrs · 29,042 cycles

CRACK INDICATION ON FRAME 40 TO CENTER WING JOINT AT UPPER SKIN LEVEL TENSION BOLT JUNCTION AREA OPEN FASTENER HOLES LOWER POSITION RH SIDE, CRACK DIRECTION IS 6 O CLOCK IN FWD CARGO COMPARTMENT (1EA) PERFORMED REAPIR ON FRAME 40 TO CENTER WING JOINT AT UPPER SKIN LEVEL TENSION BOLT JUNCTION AREA OPEN FASTENER HOLES LOWER POSITION RH SIDE (1EA) IAW EA # 6- 5710-127939 H PART 5 REV DATE 05 FEB 21

Part: FLOOR SUPPORT — CORRODED (ZONE 200) · corrosion level 2 · airframe 55,480 hrs · 29,042 cycles

CORROSION FLOOR STRUCTURE LOCATED BETWEEN FR 11 AND FR 15 Y1213 IN PASSENGER CABIN (MAIN DECK). REPLACED FLOOR STRUCTURE LOCATED BETWEEN FR 11 AND FR 15 Y1456 IN PASSENGER CABIN (MAIN DECK), IAW A300-600 DWG 53612310 ISSUE A AND A300-600 SRM 51-72-10.

Part: FLOOR SUPPORT — CORRODED (ZONE 200) · airframe 55,480 hrs · 29,042 cycles

CORROSION FLOOR STRUCTURE LOCATED BETWEEN FR 11 AND FR 13 Y730 IN PASSENGER CABIN (MAIN DECK). REPLACED FLOOR STRUCTURE LOCATED BETWEEN FR 11 AND FR 13 Y730 IN PASSENGER CABIN (MAIN DECK), IAW A300-600 SRM 51-72-10 AND DWG A53612214 SHEET 01 ISSUE M.

Part: SEAT TRACK — CORRODED (ZONE 200) · airframe 55,480 hrs · 29,042 cycles

CORROSION SEAT TRACK Y953 BETWEEN FR 18 TO FR 19 IN PASSENGER CABIN (MAIN DECK). REPLACED SEAT TRACK Y953 BETWEEN FR 15 TO FR 19 IN PASESENGER CABIN (MAIN DECK), IAW A300-600 SRM 51-40-20 AND DWG NR A53781051 ISSUE A SHEET 3 AND DWG A53612502 ISSUE F SHEET 1.

Part: PRESSURE DECK — CORRODED (ZONE 100) · airframe 55,480 hrs · 29,042 cycles

CORROSION INTERNAL STRUCTURE FWD FACE PRESSURE DECK AT LEVEL FR 39 LOWER AREA IN FWD CARGO COMPARTMENT PERFORMED REPAIR ON PRESSURE BULKHEAD FR39 BTW STR 53LH TO STR 55LH IAW EA# 6- 5314-T0359508 TITLE: FUSELAGE CENTER SECTION-FR39 BULKHEAD BTW S-53LH TO S-55LH- CORROSION REPAIR.

Part: FRAME — CRACKED (FRM 13) · airframe 55,480 hrs · 29,042 cycles

CRACK INDICATION ON FRAME 13 OPEN FASTENER HOLE AT LEVEL OF STR 9 LT SIDE, CRACK DIRECTION IS 3 O`CLOCK AT FWD GALLEY AREA (1 EA). REPLACED STRINGER SECTION LOCATED ON FR 13 AT LEVEL STR 9 LT SIDE, IAW A300-600 SRM 51-40-20-001 AND DWG #A53610301 ISSUE K SHEET 1.

Part: FLOOR SUPPORT — CORRODED (ZONE 200) · corrosion level 2 · airframe 55,480 hrs · 29,042 cycles

CORROSION FLOOR STRUCTURE LOCATED BETWEEN FR 11 AND FR 15 Y180 IN PASSENGER CABIN (MAIN DECK). REPLACED FLOOR STRUCTURE Y953 LOCATED BETWEEN FR 11 AND FR 15 IN (MAIN DECK), IAW A300-600 SRM 51-72-10 AND DRAWING A53612519 ISSUE AN.

Part: CROSSBEAM — CRACKED (ZONE 100) · airframe 55,480 hrs · 29,042 cycles

CRACK FRAME 15A CROSS BEAM AT ATTACHMENT FITTING OF RACK 107VU IN FWD AVIONIC COMPARTMENT PERFORMED REPAIR ON FRAME 15A CROSSBEAM ATTACHMENT FITTING OF RACK 107VU IN FWD AVIONIC COMPARTMENT IAW EA # 6-5310-T0358885 P1 EA TITLE: FUSELAGE-MAINFRAME - AD 2010-12-08 - SB A300-53-6164-CRACK, CROSSBEAM ON NLG FR15A WEB FACE AT ATTACHMENT FTG OF RACK 107VU

Part: FRAME — CRACKED (FRM 54) · airframe 55,480 hrs · 29,042 cycles

CRACK INDICATION ON FRAME 54 STGR 36 LH (1 INCH UPPER) OPEN HOLE IN AFT CARGO COMPARTMENT (1 EA)(CRACK DIRECTION 12 O CLOCK) PERFORMED REPAIR LOC ON FRAME 54, STGR 36LH (1 INCH UPPER) OPEN HOLE IN AFT CARGO COMPARTMENT IAW EA 6-5316-T0359314. TITLE: FUSELAGE CENTER SECTION-JUNCTION BETWEEN LATERAL PANEL AND S-36LH AND S-44LH AT FR54-ALI 531582-01-CRACK INDICATION

Part: FLOOR PANEL — CRACKED (ZONE 100) · airframe 55,480 hrs · 29,042 cycles

CRACK FLOOR PANEL 131TF IN FWD CARGO COMPARTMENT (1 EA). REPLACED FLOOR PANEL 131TF ON FWD CARGO COMPARTMENT, IAW A300-600 AMM 06-41-53-00-09 AND A300-600 SRM 51-72-10-001 AND 51-40-21.

Part: SKIN — CRACKED (FRAME54) · airframe 55,480 hrs · 29,042 cycles

CRACK INDICATION ON FRAME 54 (2 INCH AFT SIDE) AND STGR 44 LT (2 INCH UPPER) OPEN HOLE IN AFT CARGO COMPARTMENT (1 EA) (CRACK DIRECTION 12 O CLOCK) PERFORMED REPAIR LOC. ON FRAME 54 (2 INCH AFT SIDE) AND STGR 44 LT (2 INCHES UPPER) OPEN HOLE IN AFT CARGO COMPARTMENT IAW EA 6-5316-T0359314 TITLE: FUSELAGE CENTER SECTION - JUNCTION BETWEEN LATERAL PANEL AND S-36LT AND S-44LT AT FR 54 - ALI 531582- 01 - CRACK INDICATION.

Part: FRAME — CRACKED (FRM 54) · airframe 55,480 hrs · 29,042 cycles

CRACK INDICATION ON FRAME 54 (2 INCH AFT SIDE) AND STGR 44LT (1 INCH UPPER) OPEN HOLE IN AFT CARGO COMPARTMENT (1 EA) (CRACK DIRECTION 12 O CLOCK) PERFORMED REPAIR LOC ON FRAME 54 (2 INCH AFT SIDE) AND STGR 44LT (1 INCH UPPER) OPEN HOLE IN AFT CARGO COMPARTMENT. IAW EA 6-5316-T0359314 TITLE: FUSELAGE CENTER SECTION-JUNCTION BETWEEN LATERAL PANEL AND S-36LT AND S-44LT AT FR54-ALI 531582-01-CRACK INDICATION.

Part: WEB — CRACKED (CARGO DOOR) · airframe 55,480 hrs · 29,042 cycles

CRACK ON AFT WEB LOC AT FR61A AND BTW LONGERON 1 TO 1A, ON AFT CARGO COMPARTMENT DOOR PERFORMED REPAIR ON AFT WEB LOC AT FR61A AND BTW LONGERON 1 TO 1A ON AFT CARGO COMPARTMENT DOOR IAW EA 6-5230-T0359408. TITLE: DOORS-CARGO DOOR/ HYD SYS-AFT CARGO DOOR INNER SKINS AT FR 61A-CRACKS, PERMANENT REPAIR.

Part: DOOR — CRACKED (ZONE 800) · airframe 55,480 hrs · 29,042 cycles

CRACK ON FORWARD WEB LOC AT FR61A AND BTW LONGERON 1 TO 1A, ON AFT CARGO COMPARTMENT DOOR PERFORMED REPAIR ON FWD WEB LOC AT FR61A AND BTW LONGERON 1 TO 1A ON AFT CARGO COMPARTMENT DOOR IAW EA# 6-5230-T0359408. TITLE: DOORS-CARGO DOOR /HYD SYS-AFT CARGO DOOR INNER SKIN AT FR61A-CRACKS, PERMANENT REPAIR.

Part: SKIN PANEL — DENTED (ZONE 200) · airframe 55,480 hrs · 29,042 cycles

DENT EXTERNAL SKIN FR 66 TO FR 67 AND STR 52R TO STR 54R AT LOWER FUSELAGE PERFORMED PERMANENT REPAIR ON DENTS LOC EXTERNAL SKIN FR66 TO FR67 AND STR 52R TO STR 54R AT LOWER FUSELAGE. IAW EA 6-5317-103271 A. TITLE: FUSELAGE - FUSELAGE AFT INTERMEDIATE SECTION - OLD REPAIR AT FR65-66, STGR54-56, RHS. THIS REPAIR IS CATEGORY B. THE THRESHOLD IS 69800 FC (FH NOT RELEVANT) FROM EIS (FC=0), THE INTERVAL IS "TBD", THE METHOD OF INSPECTION IS "TBD"

Part: NONE — FAILED (ZONE 600) · airframe 55,428 hrs · 29,016 cycles

CLIMBING THRU 14000 ON DEPARTURE OUT OF KORF #2 ENGINE SLEZED EPR ROLLED BACK TO 0, NI INDICATED 13.5 % N2 WAS 0 ,EGT SPIKED TO 790 DEG, LOW OIL PRESS LIGHT ILLIMINATED. DIVIERTED TO KRIC AFTER DECLIARING EMERGENCY. #2 ENGINE REPLACEMENT.

Part: SENSING ELEMENT — FAILED (OVERHEAT) · airframe 55,348 hrs · 28,971 cycles

DURNING CLIMBOUT ENGINE NO 1 BLEED LEAK, DIVERTED INTO TPA BECAUSE WE LOST PRESSURIZATION DUE TO DEFERRED NO 2 PACK, DECLARED EMERGENCY. FACT 15NOV20 16:06 TPA. R & R MANIFOLD OVERHEAT SENSING ELEMENT ON LT WING PYLON I/R/T MM 36-22-12-04, REMOVAL P/N 35518-48-400 FENWALL, NSN, INSTALLED S/N IS BMM8825, P/N 35518-48-400 FENWALL. RAN ENGINE I/R/T JRH CHAP 5, NO DISCREPANCY'S NOTED, NO FAULTS. PREFORMED OPERATIONAL TEST I/R/T MM 39-22-00, ALL TEST GOOD.

Part: SENSOR — FAULTY (FUEL SYSTEM) · airframe 53,271 hrs · 27,683 cycles

PDIS 726 28-20 3775 18JAN19 MEM OPEN U LOGPAGES:2958677 OPERATING IN MANUEL FUEL FEED PER THE MEL, CENTER TANK PUMPS OFF, ECAM MEMO PAGE SHOWED CTR TANK FEEDING. ON SCHEMATIC PAGE, CENTER TANK RIGHT PUMP DISPLAY SHOWS ON BUT FAULTED. (OF NOTE, DURING PREFLIGHT, PRIOR TO THE DEFERRAL, WHEN BOTH CENTER TANK SWITCHES SHOWED FAULT, NO FUEL IN TANK, THE LEFT CENTER PUMP WAS GREEN/OFF ON SCHEMATIC, R CENTER PUMP SHOWED ON AND FEEDING.) PULLED PUMP CONTROL CB'S L AND R, N58 AND M59, PER MOCC IN FLIGHT. INDICATIONS RETURNED TO PREVIOUS DESCRIPTION ON WHAT WE OBSERVED ON PREFLIGHT. REMOVED & REPLACED LT CTR TK LO LVL SENSOR IAW AMM 28-46-21-04. CW OPS CHECK REF AMM 28-46-00-05-02 WITH NO DEFECTS NOTED. AC OK FOR SERVICE.

Part: PROXIMITY SENSOR — FAILED (LANDING GEAR) · airframe 53,213 hrs · 27,630 cycles

PER CREW VERBAL, GEAR WOULD NOT RETRACT IN POS DET SYS NR 1, (SYS 2 IS ON MEL). SWITCHED TO POS DET SYS NR 2 AND IT WORKED. COMPLETED INSTALL OF 8GB, AND 12GA BOGIE BEAM SENSOR INCLUDING DIMENSION CHECKS ON RT MAIN GEAR. STILL REQUIRES OPS CHECK. REMOVED AND REPLACED 9GB AND 11GB BOGIE BEAM SENSORS AND PERFORMED DIMENSION CHECKS ON LT MAIN GEAR REF 32-00-00-04. SEALED LOWER BOLTS ON BOTH GEARS AND PERFORMED NORMAL EXTENSION AND RETRACTION TEST REF 32-00-00-04 STEP 5 B. COMPLIED WITH CONTINUITY TEST OF PROX DETECTORS REF AMM 32-00-00, P BLOCK 501. ALL SYS TEST NORMAL.

Part: PROXIMITY SENSOR — INOPERATIVE (LANDING GEAR) · airframe 53,192 hrs · 27,615 cycles

DURING TAKEOFF KMDT LANDING GEAR POSITION DET, SYS2 GEAR HANDLE CAME UP TO NORMAL POSITION, SELECTED SYS 1, WOULD NOT MOVE TO UP WENT BACK TO SYSTEM 2, GEAR HANDLE CAME UP NORMAL. REMOVED REPLACED ELECTRONIC PROXIMITY UNIT IAW MM 32-31-71-04. PERFORMED NORMAL EXTENSION RETRACTION TEST IAW MM 31-31-00-5. CYCLED GEAR SEVERAL TIMES IN SYSTEM 1&2 WITH NO DISCREPANCIES NOTED.

Part: ELECTRONIC UNIT — FAILED (LANDING GEAR) · airframe 53,193 hrs · 27,616 cycles

DURING TAKEOFF KMDT LANDING GEAR POSITION DET, SYS 2 GEAR HANDLE CAME UP TO NORMAL POSITION, SELECTED SYS 1, WOULD NOT MOVE TO UP WENT BACK TO SYSTEM 2, GEAR HANDLE CAME UP NORMAL. REMOVED REPLACED ELECTRONIC PROXIMITY UNIT IAW MM 32-31-71-04. PERFORMED NORMAL EXTENSION RETRACTION TEST IAW MM 31-31-00-5. CYCLED GEAR SEVERAL TIMES IN SYSTEM 1&2 WITH NO DISCREPANCIES NOTED.

Part: DUCT — CONTAMINATED (ECS) · airframe 52,795 hrs · 27,353 cycles

J/S REPORTED AN OILY ODOR IN COURIER COMP. WITH VISIBLE OILY SMOKE. THE FIRST OFFICER STATED THAT JUMPSEATERS NOTIFIED THE CREW THAT OILY SMOKE WAS COMING UP THROUGH THE FLOOR VENTS. F/O VERIFIED THAT IT WAS NOT CONDENSATION & WAS OILY SMOKE. NO SMOKE OR ODOR WAS DETECTED IN THE COCKPIT. COMPLAINT HAPPENED JUST AFTER THE F/O CRANKED THE TEMPERATURE UP IN THE COURIER COMPARTMENT. WHEN THE F/O CRANKED IT BACK TO COOL, T/S PER TSM 21-20-00 FIG 210. PERFORMED NUMEROUS DUCT BURNOUT WITH APU & ENGINES WITH BOTH PACKS. THE LAST BURN OUT, HAD NO ODOR. A/C JUST CAME OUT OF C-CHECK. SUSPECT HYD CONTAMINATION DURING CHECK. THERE IS NO CURRENT HYD LEAKS. THERE WAS CONTAMINATION IN THE PNEUMATIC DUCTS VIUALLY.

Part: RIB — CRACKED (RT PYLON) · airframe 52,794 hrs · 27,352 cycles

RT PYLON RIB 19 HAS CRACK JUST AFT OF AFT PYLON MOUNT. COMPLIED WITH EA 6-5480-T0340823 P1 NACELLES/PYLON FILLETS/FAIRINGS-RW-HW PYLON, AFT FAIRING, RIB 19 CRACKED SRM REPAIR W/MINOR DEVIATIONS, REPAIR IS CLASSIFIED AS CAT A AND MAJOR REPAIR.

Part: SKIN — DAMAGED (TE FLAP) · airframe 52,794 hrs · 27,352 cycles

RT WING CENTER FLAP APPROX 16" FROM INBD END AND 19" FROM LEADING EDGE, LOWER SURFACE SKIN PREVIOUS REPAIR DEBONDED / CRACKS. REPLACED STRINGER SECTION, REPAIR ANGLE, PACKING PLATE, PACKING STRIPS, AND INSTALLED REPAIR FLAP SKIN DOUBLER IAW SRM 57-50-00-201 FIG 206.

Part: FLOOR PANEL — CRACKED (ZONE 200) · airframe 52,794 hrs · 27,352 cycles

MAIN CARGO FLOOR PANEL 214QH HAS CRACK. FABRICATED FLOOR PANEL 241QH ON T18/1350937 IAW DWG SRZ 25-005. CLASSIFIED AS CAT " A " REPAIR. FLOOR PANEL 241QH INSTALLED ON W/C 240-FL- FIT MAJOR REPAIR.

Part: FLOOR PANEL — CRACKED (ZONE 200) · airframe 52,794 hrs · 27,352 cycles

MAIN CARGO FLOOR PANEL 241RJ HAS CRACK. FABRICATED FLOOR PANEL 241RJ ON T18/1350935 IAW DWG SRZ 25-005. CLASSIFIED AS CAT " A " REPAIR. FLOOR PANEL 241RJ INSTALLED ON W/C 240-FL- FIT MAJOR REPAIR.

Part: FLOOR PANEL — CRACKED (ZONE 200) · airframe 52,794 hrs · 27,352 cycles

MAIN CARGO FLOOR PANEL 241WH HAS CRACK. FABRICATED FLOOR PANEL 241WH ON T18/1351638 IAW DWG SRZ 25-005. CLASSIFIED AS CAT " A " REPAIR. FLOOR PANEL 241WH INSTALLED ON W/C 240-FL- FIT MAJOR REPAIR.

Part: FLOOR PANEL — CRACKED (ZONE 200) · airframe 52,794 hrs · 27,352 cycles

MAIN CARGO FLOOR PANEL 241TH HAS EDGE CRACK. FABRICATED FLOOR PANEL 241TH ON T18/1351637 IAW DWG SRZ 25-005 CLASSIFIED AS A CAT "A" MAJOR REPAIR.

Part: FLOOR PANEL — CRACKED (ZONE 200) · airframe 52,794 hrs · 27,352 cycles

MAIN CARGO FLOOR PANEL 242EF HAS CRACK. FABRICATED FLOOR PANEL 242EF ON T18/1350939 IAW DWG SRZ 25-005. CLASSIFIED AS A CAT "A" MAJOR REPAIR.

Part: FLOOR PANEL — CRACKED (ZONE 200) · airframe 52,794 hrs · 27,352 cycles

MAIN CARGO FLOOR PANEL 251PH HAS CRACK. FABRICATED FLOOR PANEL 251PH ON T18/1351013 IAW DWG SRZ 25-005. CLASSIFIED AS CAT " A " REPAIR. FLOOR PANEL 251PH INSTALLED ON W/C 250-FL- FIT MAJOR REPAIR.

Part: FLOOR PANEL — PUNCTURED (ZONE 200) · airframe 52,794 hrs · 27,352 cycles

MAIN CARGO FLOOR PANEL 241DF HAS VARIOUS PUNCTURES. FABRICATED FLOOR PANEL 241DF ON T18/1350934 IAW DWG SRZ 25-005. CLASSIFIED AS A CAT "A" MAJOR REPAIR.

Part: FLOOR PANEL — CRACKED (ZONE 200) · airframe 52,794 hrs · 27,352 cycles

MAIN CARGO FLOOR PANEL 242XH HAS CRACK. FABRICATED FLOOR PANEL 242XH ON T18/1350938 IAW DWG SRZ 25-005. CLASSIFIED AS A CAT "A" MAJOR REPAIR.

Part: FLOOR PANEL — CRACKED (ZONE 200) · airframe 52,794 hrs · 27,352 cycles

MAIN CARGO FLOOR PANEL 251GF HAS CRACK. FABRICATED FLOOR PANEL 251GF ON T18/1350940 IAW DWG SRZ 25-005. CLASSIFIED AS CAT " A " REPAIR. FLOOR PANEL 251GF INSTALLED ON W/C 250-FL- FIT MAJOR REPAIR.

Part: FLOOR PANEL — CRACKED (ZONE 200) · airframe 52,794 hrs · 27,352 cycles

MAIN CARGO FLOOR PANEL 251WH HAS CRACK. FABRICATED FLOOR PANEL 251WH ON T18/1351014 IAW DWG SRZ 25-005. CLASSIFIED AS CAT " A " REPAIR. FLOOR PANEL 251WH INSTALLED ON W/C 250-FL- FIT MAJOR REPAIR.

Part: FLOOR PANEL — CRACKED (ZONE 200) · airframe 52,794 hrs · 27,352 cycles

MAIN CARGO FLOOR PANEL 231KG HAS CRACK. FABRICATED FLOOR PANEL 231KG ON T18/1350932 IAW DWG SRZ-25-005. CLASSIFIED AS CAT "A" MAJOR REPAIR. FLOOR PANEL 231KG INSTALLED ON WORK CARD.

Part: FLOOR PANEL — DAMAGED (ZONE 200) · airframe 52,794 hrs · 27,352 cycles

MAIN DECK COMPARTMENT FRAME 22-26, FLOOR PANEL 232KG PUNCTURED/DAMAGED. FABRICATED FLOOR PANEL 232KG ON T18/1350933 IAW DWG SRZ-25-005. CLASSIFIED AS CAT "A" MAJOR REPAIR. FLOOR PANEL 232KG INSTALLED ON WORK CARD.

Part: HINGE — DAMAGED (R1 DOOR) · airframe 52,572 hrs · 27,211 cycles

R1 DOOR WILL NOT FROM OPEN FROM OUTSIDE. PERFORMED A GVI OF DOOR AND HINGES. DOOR NEEDS TO BE LIFTED APPROX 1/4 INCH TO OPEN. REMOVED AND REPLACED DOOR SUSPENSION SUPPORT ARM PINS AND BUSHINGS IAW AMM 52-11-12-04, DOOR OPENS AND CLOSES WITHOUT LIFTING, DOOR OPS CHECKED NORMAL.

Part: VALVE — MALFUNCTIONED (BRAKE) · airframe 52,404 hrs · 27,110 cycles

DURING LANDING, THE NR 4 TIRE BLEW. BITE TEST OF BSCU SHOWS NO FAULTS. REMOVED AND REPLACED THE NR 4 BRAKE ASSY IAW MM 32-42-27-4. REMOVED AND REPLACED NR 4 MLG NORMAL BRAKE SERVO VALVE IAW MM 32-42-16-04 REMOVED AND REPLACED THE NR 4 MLG TACHOMETER IAW MM 32-42-57-04. REMOVED AND REPLACED THE NR 4 MLG TIRE ASSY 12-37-32-0-02.

Part: TACHOMETER — FAILED (NR 4) · airframe 52,404 hrs · 27,110 cycles

DURING LANDING, THE NR 4 TIRE BLEW. AT APPROX 50KTS STARTING TO BREAK FOR THE HIGH SPEED TURNOFF C TAXIWAY. BITE TEST OF BSCU SHOWS NO FAULTS. DUE TO HISTORY, REMOVED AND REPLACED THE NR 4 BRAKE ASSY IAW MM 32-42-27-4. REMOVED AND REPLACED NR 4 MLG, NORMAL BRAKE SERVO VALVE IAW MM 32-42-16-04. REMOVED AND REPLACED THE NR 4 MLG TACHOMETER IAW MM 32-42-57-04. REMOVED AND REPLACED THE NR 4 MLG TIRE ASSY IAW 12-37-32-0-02.

Part: SELECTOR VALVE — UNSERVICEABLE (LANDING GEAR) · airframe 50,633 hrs · 26,040 cycles

DURING FINAL, SELECTED GEAR DOWN AND HAD AMBER DOOR LIGHTS AND RED GEAR LIGHT FOR LONGER THAN USUAL FOLLOWED BY ECAM GEAR NOT DOWN AND LOCKED. EXECUTED GO AROUND, RAISED GEAR SUCCESSFULLY. SWITCHED POSITION DETECTOR TO SYSTEM 2 AND LOWERED GEAR HANDLE WITH AMBER DOOR LIGHTS AND RED GEAR LIGHT LONGER THAN USUAL AGAIN WITH ECAM GEAR NOT DOWN ALERT, BUT A MOMENT LATER RECEIVED A GREEN GEAR DOWN INDICATION ON INST PANEL AND OVERHEAD. INSTALLED SERVICEABLE LANDING GEAR SELECTOR VALVE, 3GA, AMM 32-31-12-04. PERFORMED A LANDING GEAR ELECTRO VALVE CHECK REF AMM 32-31-12-06, LEAK CHECK GOOD AND GEAR EXTENSION, RETRACTION ON BOTH SYS NR 1 AND NR 2 REF AMM 32-31-00--05-09, ALL TEST GOOD.

Part: SKIN — DENTED (LE SLAT) · airframe 50,512 hrs · 25,964 cycles

RT WING NR 3 LEADING SLAT INNER SURFACE FOUND 1EA DENT.

Part: FITTING — CRACKED (FUSELAGE) · airframe 50,512 hrs · 25,964 cycles

FUSELAGE INTERNAL STRUCTURE AT FRAME 46, STGR 24-28LT FRAME FOOT INBD ROW LOWER NR 2 FASTENER HOLE FOUND CRACK SIGNAL.

Part: FITTING — CRACKED (FUSELAGE) · airframe 50,512 hrs · 25,964 cycles

FUSELAGE INTERNAL STRUCTURE AT FRAME 46, STR 24-28LT FRAME FOOT INBD ROW UPR NR 2 FASTENER HOLE FOUND CRACK SIGNAL. REPAIRED THE CRACKED HOLE OF FUSELAGE INTERNAL STRUCTURE AT FRAME 46, STR 24-28 LT FRAME FOOT INBD ROW UPPER NR 2 FASTENER IAW EA 6-5315-T0326077, P1. FUSELAGE, FRAME, FOOT CRACKS, FRAME FEET ATTACHMENT HOLES AT RT SIDE FR 41-43 AND LT SIDE FR46. THIS REPAIR CATEGORY IS: C. REPAIR LIFE LIMITATION IS 6 MONTHS. MAJOR REPAIR IAW GMM 6-2-100.

Part: FITTING — CRACKED (FUSELAGE) · airframe 50,512 hrs · 25,964 cycles

FUSELAGE INTERNAL STRUCTURE AT FRAME 43, STR 24-28 RT FRAME FOOT INBD ROW LWR NR 2 FASTENER HOLE FOUND CRACKED SIGNAL. REPAIRED THE CRACKED HOLE OF FUSELAGE INTERNAL STRUCTURE AT FRAME 43, STR 24-28, RT FRAME FOOT INBD ROW LOWER NR 2 FASTENER IAW EA 6-5315-T0326077 P1. FUSELAGE, FRAME, FOOT-CRACKS, FRAME FT ATTACHMENT HOLES AT RT SIDE FRAME 41-43 AND LT SIDE FRAME 46. THIS REPAIR CATEGORY IS: C. REPAIR LIFE LIMITATION IS 6 MONTHS. MAJOR REPAIR IAW GMM 6-2-100.

Part: FITTING — CRACKED (FUSELAGE) · airframe 50,512 hrs · 25,964 cycles

FUSELAGE INTERNAL STRUCTURE AT FRAME 42, STGR 24-28 LT FRAME FOOT INBD ROW UPR NR 1 FASTENER HOLE FOUND CRACK SIGNAL. REPAIRED THE CRACKED HOLE OF FUSELAGE INTERNAL STRUCTURE AT FRAME 42, STR 24-28 LT FRAME FOOT INBD ROW UPPER NR 1 FASTENER EA 6-5315-T0326077 P1. FUSELAGE, FRAME, FOOT CRACKS, FRAME FT ATTACHMENT HOLES AT RT SIDE FRAME 41-43 AND LT SIDE FRAME 46. THIS REPAIR CATEGORY IS "C". REPAIR LIFE LIMITATION IS 6 MONTHS. MAJOR REPAIR IAW GMM 6-2-100.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 50,512 hrs · 25,964 cycles

BULK CARGO FR 64-FR 65, Y140 FLOOR SUPPORT WITH SLIGHT SURFACE CORROSION. REPLACED THE CORRODED FLOOR SUPPORT ON BULK CARGO FRAME 64-FRAME 65, Y140. MAJOR REPAIR IAW GMM 6-2-100.

Part: FITTING — CRACKED (FUSELAGE) · airframe 50,512 hrs · 25,964 cycles

FUSELAGE INTERNAL STRUCTURE AT FRAME 46, STR 24-STR 28LT FRAME FOOT INBD ROW UPR NR 1, FASTENER HOLE FOUND CRACK SIGNAL. REPAIRED THE CRACKED HOLE OF FUSELAGE INTERNAL STRUCTURE AT FRAME 46 STR 24-28 LT FRAME FOOT INBD ROW UPPER NR 1 FASTENER IAW EA 6-5315-T0326077 P1. FUSELAGE, FRAME, FOOT-CRACKS, FRAME FEET ATTACHMENT HOLES AT RT SIDE FRAME 41-43 AND LT SIDE FRAME 46. THIS REPAIR CATEGORY IS: C. REPAIR LIFE LIMITATION IS 6 MONTHS. MAJOR REPAIR IAW GMM 6-2-100.

Part: FITTING — CRACKED (FUSELAGE) · airframe 50,512 hrs · 25,964 cycles

FUSELAGE INTERNAL STRUCTURE AT FRAME 41, STR 24-28 RT FRAME FOOT INBD ROW UPR NR 1 FASTENER HOLE FOUND CRACKED SIGNAL. REPAIRED THE CRACKED HOLE OF FUSELAGE INTERNAL STRUCTURE AT FRAME 41, STR 24-28, RT FRAME FOOT INBD ROW UPPER NR 1 FASTENER IAW EA 6-5315-T0326077 P1. TITLE: FUSELAGE, FRAME, FOOT CRACKS, FRAME FEET ATTACHMENT HOLES AT RT SIDE FRAME 41-43 AND LT SIDE FRAME 46. THIS REPAIR CATEGORY IS C. REPAIR LIFE LIMITATION IS 6 MONTHS. MAJOR REPAIR IAW GMM 6-2-100.

Part: ANGLE — CRACKED (RT WING) · airframe 50,512 hrs · 25,964 cycles

RIGHT WING, CENTER SPAR AT RIB 8, STR 12, SEALING ANGLE VERTICAL WEB FOUND CRACKED. REPLACED THE CRACKED ANGLE IAW EO 6-5710-7-5002C, PT2 & REPAIR DWG R57150404. COMPLIED WITH EA 6-5710-T0326233 P1. MAJOR REPAIR IAW GMM 6-2-100.

Part: WEB — CRACKED (FUSELAGE) · airframe 50,512 hrs · 25,964 cycles

MAIN DECK FRAME 47, Y953 - Y1456, UNDERFLOOR ONE EACH WEB CRACKED. REPAIRED WEB IAW SRM 53-15-15-201, PARA 5A, FIG 201, THE REPAIR WAS CATEGORY B. THE FIRST INSPECTION THRESHOLD WAS 24000FC AFTER REPAIR EMBODIMENT. THE SUBSEQUENT INSPECTION INTERVAL WAS 3000FC, THE INSPECTION METHOD WAS DVI. MAJOR REPAIR IAW GMM6-2-100.

Part: WEB — CRACKED (ZONE 100) · airframe 50,512 hrs · 25,964 cycles

CENTER TANK, FRAME 40 CL, FRONT SPAR INTERNAL WEB SUSPECTED CRACK ACROSS A FASTENER AT THE LOWER END APPROX 2.0 INCHES IN LENGTH. REPAIRED CENTER TANK, FRAME 40 CL, FRONT SPAR INTERNAL WEB IAW SRM 57-10-21, FIG 201 AND DWG R57110271 & R57110273, MAJOR REPAIR IAW GMM6-2-100.

Part: WEB — CRACKED (ZONE 100) · airframe 50,512 hrs · 25,964 cycles

CENTER TANK, FRAME 40, -Y953, FRONT SPAR INTERNAL WEB SUSPECTED CRACK ACROSS A FASTENER AT THE LOWER END APPROX 2.0 INCHES IN LENGTH. REPAIRED CENTER TANK, FRAME 40, Y953 FRONT SPAR INTERNAL WEB IAW SRM 57-10-21, FIG 201 AND DWG R57110271 & R57110273, MAJOR REPAIR IAW GMM6-2-100.

Part: WEB — CRACKED (FRAME 40) · airframe 50,512 hrs · 25,964 cycles

CENTER TANK, FRAME 40, Y450, FRONT SPAR INTERNAL WEB SUSPECTED CRACK ACROSS A FASTENER AT THE LOWER END, APPROX 2.0 INCHES IN LENGTH. REPAIRED CENTER TANK, FRAME 40, Y450, FRONT SPAR INTERNAL WEB IAW SRM 57-10-21, FIG 201 AND DWG R57110271 & R57110273, MAJOR REPAIR IAW GMM6-2-100.

Part: FLOOR SUPPORT — CORRODED (FRAMES 11-12) · airframe 50,512 hrs · 25,964 cycles

MAIN DECK FRAMES 11 - 12A, Y730 FLOOR SUPPORT CORRODED.

Part: WEB — CRACKED (ZONE 100) · airframe 50,512 hrs · 25,964 cycles

CENTER TANK, FRAME 40, Y953, FRONT SPAR INTERNAL WEB SUSPECTED CRACK ACROSS A FASTENER AT THE LOWER END, APPROX 2.0 INCHES IN LENGTH. REPAIRED CENTER TANK FRAME 40, Y953, FRONT SPAR INTERNAL WEB IAW SRM 57-10-21, FIG 201 AND DWG, R57110271 & R57110273, MAJOR REPAIR IAW GMM 6-2-100.

Part: WEB — CRACKED (ZONE 100) · airframe 50,512 hrs · 25,964 cycles

CENTER TANK, FRAME 40, Y1456, FRONT SPAR INTERNAL WEB SUSPECTED CRACK ACROSS A FASTENER AT THE LOWER END APPROX 2.0 INCHES IN LENGTH. REPAIRED CTR TANK FRAME 40, Y1456, FRONT SPAR INTERNAL WEB IAW SRM 57-10-21, FIG 201 AND DWG R57110271 & R57110273, MAJOR REPAIR IAW GMM6-2-100.

Part: WEB — CRACKED (FUSELAGE) · airframe 50,512 hrs · 25,964 cycles

MAIN DECK FRAME 47, Y0 - Y450, UNDER FLOOR ONE EACH WEB CRACKED. REPAIRED WEB IAW SRM 53-15-15, FIG 201. THIS REPAIR WAS CATEGORY B AND IT MUST BE INSPECTED AT DEFINED INTERVALS IAW SRI 53-15-15-2-001-00. INSPECTION THRESHOLD FROM REPAIR EMBODIMENT OF 24000FC, SUBSEQUENT INSPECTION AT INTERVAL OF 3000FC. MAJOR REPAIR IAW GMM 6-2-100.

Part: RIB — CRACKED (TE FLAP) · airframe 50,512 hrs · 25,964 cycles

LEFT WING CTR FLAP, RIB 18 FOUND CRACK AT UPPER STRINGER 2.8. REPAIRED THE CRACKED RIB IAW EA 6-5750-T0325833 PT1. THIS REPAIR CATEGORY IS A MAJOR REPAIR IAW GMM 6-2-100.

Part: FLOOR SUPPORT — CRACKED (FUSELAGE) · airframe 50,512 hrs · 25,964 cycles

MAIN DECK FRAME 14, -Y953, FLOOR SUPPORT CRACKED. REPAIRED THE SUPPORT AT MAIN DECK FRAME 11-FRAME 14, Y953 IAW SRM 53-12-15-201, FIG 207. THE REPAIR WAS CATEGORY B, THE INSPECTION THRESHOLD WAS 51000FC/89000FH AFTER REPAIR EMBODIMENT, THE SUBSEQUENT INSPECTION INTERVAL AND METHOD WERE TBD. MAJOR REPAIR IAW GMM6-2-100.

Part: RIB — CRACKED (TE FLAP) · airframe 50,512 hrs · 25,964 cycles

LEFT WING CTR FLAP, RIB 26 FOUND CRACKS AT UPPER STRINGER 2.7 & 2.8 LOCATIONS. REPAIRED THE CRACKED RIB IAW EA 6-5750-T0325833, PT1. THIS REPAIR CATEGORY IS "A" MAJOR REPAIR IAW GMM 6-2-100.

Part: RIB — CRACKED (TE FLAP) · airframe 50,512 hrs · 25,964 cycles

LEFT WING CTR FLAP, RIB 17 FOUND CRACK AT UPPER STRINGER 2.8 LOCATION. REPAIRED THE CRACKED RIB IAW EA 6-5750-T0325833, PT1. THIS REPAIR CATEGORY IS: A. MAJOR REPAIR IAW GMM 6-2-100.

Part: WEB — CRACKED (FUSELAGE) · airframe 50,512 hrs · 25,964 cycles

MAIN DECK FRAME 47, -Y450 - Y0, UNDER FLOOR ONE EACH WEB CRACKED. THE CRACK LENGTH WAS 0.91", LONGER THAN 0.787", OUT OF REPAIR LIMIT IAW SRM 53-15-15, PARA 5A. REPLACED THE WEB IAW SRM 51-40-21, LOCATION: MAIN DECK FRAME 47-Y450 TO Y0 UNDERFLOOR.

Part: BOTTLE — DISCHARGED (R1 DOOR) · airframe 491 hrs · 25,188 cycles

DOOR BOTTLE BLEW WHILE INSTALLING ESCAPE SLIDE. RELEASED FOR SERVICE IAW MEL 52-XX-XX CATEGORY C, EXPIRATION 31 MAY 15. R1 CREW ENTRY DOOR INOPERATIVE. IF SLIDE TO BE RETAINED ONBOARD THEN PRIOR TO EACH DEPARTURE MX MUST VERIFY SLIDE STOWED ACCORDING TO PROCEDURES. PENDING CORRECTIVE ACTION.

Part: FITTING — CORRODED (LT WING) · corrosion level 2 · airframe 48,202 hrs · 24,628 cycles

LEFT RIB 5 MLG FWD LUG HAS CORROSION IN BORE, FWD FACE & AFT FACE. COMPLIED WITH EA 6-5710-T0310496 P1 WINGS BASIC WING STRUCTURE LT & RT RIB 5 FWD LUG CORROSION.

Part: FITTING — CORRODED (RT WING) · corrosion level 2 · airframe 48,202 hrs · 24,628 cycles

RIGHT RIB 5 MLG FITTING FWD LUG BORE, FWD FACE & AFT FACE HAVE CORROSION. COMPLIED WITH EA 6-5710-T0310496 P3 WINGS BASIC WING STRUCTURE LT & RT RIB 5 FWD LUG CORROSION.

Part: UNKNOWN — UNKNOWN (MULTIPLE) · airframe 47,991 hrs · 24,499 cycles

WHEN LEVELING AT FL 330, YAW DAMPER 1 & ATS 1 & 2 TRIPPED OFF. COMPLIED WITH ECAM & QRH & SYS WOULD NOT RESET. FLIGHT DIRECTOR 1 ALSO INOPERATIVE, AND IVSI NR 1 AMBER IVS INDICATION. NO TRIFOIL EFIS LAST FLIGHT LEG SHOWED 1 FCC & 1 TCC FAIL. MTP SHOWS ON AFS POWER UP TEST FCC 1 & TCC 1 FAIL. R & R NR 1 TCC IAW MM.22-36-34-04-01. R & R FCC NR 1 IAW MM.22-18-34-04 & 1 TAT PROBE IAW MM 34-11-18-04-01. ALL RTS & ADJUSTMENT TEST PASSED. PERFORMED AFS LAND TEST IAW MM 22-40-00-05, ALL TEST PASSED, OK FOR SERVICE.

Part: SUPPORT BEAM — CORRODED (NLG WW) · corrosion level 2 · airframe 47,845 hrs · 24,430 cycles

NLG BAY LT LATERAL PANEL LOWER SUPPORT BEAM INTERNAL SURFACE CORRODED AT AV COMPARTMENT FRAME 11A STRINGER49L, COMPLIED WITH EA 6-5310-T0307525 A. TITLE FUSELAGE, MAINFRAME, CORROSION ON KEEL LATERAL AT FRAME 11 - FRAME 11A, STRINGER 49L. REPAIRED NLG BAY LT LATERAL PANEL LOWER SUPPORT BEAM INTERNAL SURFACE CORROSION AT AV COMPARTMENT FRAME 11 - FRAME 11A STRINGER 49L. MAJOR REPAIR IAW GMM 6-2-100.

Part: FRAME — CRACKED (FRAME 40) · airframe 47,845 hrs · 24,430 cycles

CENTER WING JOINT AT FRAME 40 HAD A CRACK SIGNAL. REPAIRED IAW EA 6-5710-127939 B PART 2. MAJOR REPAIR IAW GMM 6-2-100.

Part: FRAME — CRACKED (FRAME 40) · airframe 47,845 hrs · 24,430 cycles

CENTER WING JOINT AT FRAME 40, HAS A CRACK SIGNAL. REPAIRED IAW EA 6-5710-127939 B PART 2. MAJOR REPAIR IAW GMM 6-2-100.

Part: FRAME — CRACKED (FRAME 40) · airframe 47,845 hrs · 24,430 cycles

CENTER WING JOINT AT FRAME 40 HAS A CRACK SIGNAL. REPAIRED IAW EA 6-5710-127939 B PART 2. MAJOR REPAIR IAW GMM 6-2-100.

Part: SILL — CRACKED (FRAMES 75-75A) · airframe 47,845 hrs · 24,430 cycles

RIGHT AFT PAX DOOR LOWER SILL BEAM HAS A CRACK SIGNAL AROUND FASTENER HOLE BETWEEN FRAMES 75 - 75A AT STRINGER 26R. REPAIRED IAW EA 6-5318-T0307544 PART 1. MAJOR REPAIR IAW GMM 6-2-100.

Part: SKIN — CRACKED (FRAME 13) · airframe 47,845 hrs · 24,430 cycles

FUSELAGE FRAME 13 CIRCUMFERENTIAL JOINT FWD FASTENER HOLE WITH CRACK SIGNAL AT ABOUT STRINGER 23L. REPAIRED IAW EA 6-5330-T0307377 A PART 1. MAJOR REPAIR IAW GMM 6-2-100.

Part: SKIN — CRACKED (FRAME 13) · airframe 47,845 hrs · 24,430 cycles

FUSELAGE SKIN AT FRAME 13 CIRCUMFERENTIAL JOINT MID FASTENER HOLE WITH CRACK SIGNAL AT ABOUT STRINGER 23R. REPAIRED IAW EA 6-5330-T0307377 A PART 1. MAJOR REPAIR IAW GMM 6-2-100.

Part: FITTING — CRACKED (ZONE 600) · airframe 47,845 hrs · 24,430 cycles

JUNCTION BETWEEN CENTER WING BOX & CRUCIFORM FITTING BETWEEN FRAME 40 - 44, FRAMES & STIFFENERS NDT CHECK FOUND FRAME 41 RT OTBD FASTENER HOLE WITH CRACKED SIGNAL. REPAIRED IAW 6-5710-T0307097 A PART1. MAJOR REPAIR IAW GMM 6-2-100.

Part: FRAME — CRACKED (FRAME 42) · airframe 47,845 hrs · 24,430 cycles

JUNCTION BETWEEN CENTER WING BOX & CRUCIFORM FITTING BETWEEN FRAMES 40 - 44. NDT CHECK FOUND FRAME 42 RT OTBD FASTENER HOLE WITH CRACK SIGNAL. REPAIRED IAW EA 6-5710-T0307097 A PART1. MAJOR REPAIR IAW GMM 6-2-100.

Part: SPAR — CRACKED (CENTER WING) · airframe 47,845 hrs · 24,430 cycles

CENTER WING BOX, INSPECTION OF REAR SPAR & BOTTOM PANEL FOUND WITH A CRACK SIGNAL RT SIDE. REPAIRED IAW 6-5710-T0307446 PART1. MAJOR REPAIR IAW GMM 6-2-100.

Part: SKIN — CRACKED (CENTER WING) · airframe 47,845 hrs · 24,430 cycles

CENTER WING BOX INSPECTION OF REAR SPAR & BOTTOM PANEL FOUND WITH A CRACK SIGNAL LT SIDE. REPAIRED IAW EA 6-5710-T0307446 PART1. MAJOR REPAIR IAW GMM 6-2-100.

Part: FRAME — CRACKED (FRAME 43) · airframe 47,845 hrs · 24,430 cycles

JUNCTION BETWEEN CENTER WING BOX & CRUCIFORM FITTING BETWEEN FRAMES 40 - 44. NDT CHECK FOUND FRAME 43 WITH A CRACK SIGNAL. REPAIRED IAW EA 6-5710-T0307097 A PART1. MAJOR REPAIR IAW GMM 6-2-100.

Part: FRAME — CRACKED (FRAME 41) · airframe 47,845 hrs · 24,430 cycles

JUNCTION BETWEEN CENTER WING BOX & CRUCIFORM FITTING BETWEEN FRAME 40 - 44, AT FRAMES & STIFFENERS NDT CHECK, FOUND FRAME 41 WITH A CRACK SIGNAL. REPAIRED IAW EA 6-5710-T0307097 A PART1. MAJOR REPAIR IAW GMM 6-2-100.

Part: FRAME — CHAFED (FRAME 43) · airframe 47,845 hrs · 24,430 cycles

JUNCTION BETWEEN CENTER WING BOX & CRUCIFORM FITTING BETWEEN FRAMES 40 - 44. NDT CHECK FOUND FRAME 43 RT WALL DAMAGED. REPAIRED IAW EA 6-5710-T0307097 A PART 1. MAJOR REPAIR IAW GMM 6-2-100.

Part: TERMINAL — BROKEN (PITOT HEAT) · airframe 47,635 hrs · 24,321 cycles

IMMEDIATELY AFTER TAKEOFF RECEIVED, FIRST OFFICER`S PROBE HEAT, FAULT ON ECAM WITH CORRESPONDING FIRST OFFICER`S PITOT LIGHT ON PROBE HEAT PANEL. ON LANDING THE PITOT LIGHT WENT OUT. ADDED MPN 180RU01Z01W00A, CPN 2110776 QTY 1. R & R RELAY 154GB & DETECTOR SENSOR 30DA IAW WD 30-31-04. PULLED 2 EA CB, LG PROX FLT GND SYS 1 & FLT GND SYS 2. FIRST OFFICER`S PITOT LIGHT STILL COMES ON IN FLIGHT MODE, NO HELP. IN GND MODE WORKS NORMAL. IDENTIFY FIRST OFFICER`S HEATER SYSTEM FLIGHT MODE INOPERATIVE. T/S PER TSM 30-31-00 FIG 104. FOUND BROKEN TERMINAL ON RELAY 20DA NR 1 LUG. RE-TERMINATED PER ESPM 20-48-19. PERFORMED OPS CHECK OF F/O PITOT HEAT PER MM 30-31-00-05. OPS CHECK NORMAL GND/FLT MODES. A/C OK FOR SERVICE.

Part: SWITCH — FAILED (CARGO DOOR) · airframe 47,535 hrs · 24,275 cycles

FORWARD CARGO DOOR LIGHT CAME ON AT FL320 JUST LEVELED OFF LIGHT REMAINED ON & CABIN PRESS BEGAN RISING AT 500 FT. BEGAN EMERGENCY DESCENT TO FL100. MAX CABIN PRESS REACHED WAS 9500 FT, DECLARED EMERGENCY & DIVERTED TO KPHL. UNEVENTFUL LANDING & TAXI IN. RELEASED FOR SERVICE IAW MEL 52-71-01-A CATEGORY C. DOOR CLOSED & LOCKED INDICATION ON ECAM DOOR PAGE INOPERATIVE. FWD LOWER DOOR VISUALLY CHECKED CLOSED & LOCKED PRIOR TO EACH DEPARTURE. INSTALLED SWITCH 16 WS IAW AMM 52-71-11-04-09, OPERATIONS CHECKED GOOD. IAW MTSI SWITCH 14WS WAS REPLACED. FWD LWR CARGO DOOR WARNING SYS OPERATIONS CHECKED GOOD.

Part: SWITCH — DIRTY (CARGO DOOR) · airframe 47,442 hrs · 24,217 cycles

FL 340, FWD CARGO NOT CLOSED WARNING ON ECAM. CABIN ALT WAS AT 300 FEET PER MINUTE. DESCENDED TO FL 100 & LIGHT EXTINGUISHED AT APPROXIMATELY 15,000'. CABIN ALT THEN STARTED TO DESCEND. INSPECTED FWD CARGO DOOR SEAL, NO DEFECTS NOTED. CLEANED & LUBED FWD CARGO DOOR SWITCH, NO BINDING NOTED. PERFORMED PRESSURIZATION TEST IAW AMM 05-53-00-00. OPERATIONS CHECKED GOOD, NO FAULTS FOUND. OK TO CONTINUE.

Part: PRESSURE SWITCH — FAILED (HYD SYSTEM) · airframe 46,995 hrs · 23,989 cycles

DURING CLIMBOUT, GREEN HYD SYS LOW AIR ILLUMINATED. LOW AIR WENT OFF ABOVE 5000 FT. FOLLOWED BY GREEN SYS NR 1 LOW PRESS LIGHT ON ECAM. LOW AIR ILLUMINATED AGAIN DURING DESCENT. SYS PRESSURE REMAINED NORMAL. CREW STATED NR 2 GREEN PUMP SYS PRESSURE WAS NORMAL. R & R GREEN SYS RESERVOIR PRESSURE SWITCH IAW MM 29-11-11-04. SYSTEM TESTED IAW AMM 29-14-00-05. GREEN RESERVOIR SYS AIR LIGHT OP CHECKS GOOD. ACFT OK TO CONTINUE.

Part: PANEL — MISSING (ZONE 500) · airframe 46,443 hrs · 23,703 cycles

FOUND LEFT LOWER WING PANEL 512BB MISSING AND ATTACH FITTINGS MISSING. INSTALLED PANEL IAW AMM 57-41-41-04. ACFT OK FOR SERVICE.

Part: SPAR — CRACKED (ZONE 500) · airframe 44,560 hrs · 22,652 cycles

COMPLY WITH EA 6-5710-150054 COMPLIED WITH EA 6-5710-150054 - WINGS - CTR WING BOX - AD 2005-23-08. REAR SPAR LOWER FLANGE AT FRAME 47, EXISTING CRACK REPAIR AT HOLES LT SIDE.

Part: FLAP TRACK — GOUGED (ZONE 600) · airframe 44,560 hrs · 22,652 cycles

RT WING NR3 FLAP TRACK OTBD FACE HAS INDENTATIONS AT FWD AND AFT SECTION. SECTION (EA MEASURING L=1" X W=0.25" X D=0.05") R & R RT NR3 FLAP TRACK BEAM IAW AMM 57-20-24-4. REMOVED ANR RE-INSTALLED NR3 FLAP TRACK CARRIAGES IAW AMM 27-54-27-4 TO FOM. REMOVED AND RE-INSTALLED RT CENTER FLAP IAW AMM 27-50-12-4 TO FOM. R & R RT NR 3 SCREWJACK IAW AMM 27-54-23-4 TO FOM. OPS CHECK SATISFACTORY IAW AMM 27-50-12-04 AND 27-54-23-04.

Part: SKIN — GOUGED (LT WING TE FLAP) · airframe 44,560 hrs · 22,652 cycles

LEFT WING CENTER FLAP UPPER SURFACE CHAFED & GOUGED. GOUGES APROXIMATELY .2500" DIA X .040" DEEP. REPAIRED IAW SRM 57-50-00 PB 201 PARA 4F.

Part: SKIN — CHAFED (RT WING TE FLAP) · airframe 44,560 hrs · 22,652 cycles

RT WING INBD FLAP, MOST INBD T/E UPPER SURFACE HAS A 2.5 " X .1 " X .002" CHAFE MARK. SMOOTHED & BLENDED CHAFE MARK IAW SRM 51-73-10 ORIGINAL THICKNESS OF .012 AFTER .008 FOUND TO BE OUT OF LIMITS IAW SRM 57-50-00, FIG 101. R & R SKIN ASSY AT RT INBD FLAP T/E WEDGE IAW SRM 51-40-21 AND 51-72-10.

Part: SKIN — DAMAGED (RT WING TE FLAP) · airframe 44,560 hrs · 22,652 cycles

RT WING INBD UPPER FLAP SKIN MISREPAIRED IAW SRM 57-50-00, FIG 205 REPAIRED IAW SRM 57-50-00, FIG 205, PG 219.

Part: SKIN — GOUGED (LT WING TE FLAP) · airframe 44,560 hrs · 22,652 cycles

LT WING INBD FLAP UPPER SURFACE GOUGED. LOCATED 24.5 IN. FROME OTBD END AND 22 IN AFT OF LEADING EDGE. GOUGE MEASURES 1.6IN. X .3IN. X .007IN. BLENDED GOUGED SKIN AND REPAIRED IAW EA 6-5750-156025.

Part: SKIN — DAMAGED (ZONE 300) · airframe 44,560 hrs · 22,652 cycles

RUDDER TRAILING EDGE TOP SIDE LIGHTING STRIKE RT SIDE STATIC WICK DISCH. ATTACH AREA RUDDER DAMAGE TO T/E STATIC WICK ATTACHMENT WAS REPAIRED IAW SRM 55-41-12, PARA 16B, FIG 208C AND EA 6-5540-145674.

Part: SKIN — DAMAGED (RUDDER) · airframe 44,560 hrs · 22,652 cycles

RUDDER SKIN LT SIDE GROUP OF 3 EA LIGHTNING STRIKE HOLES AT UPPER SECTION BETWEEN RIB 13-14 REPAIRED 3 EA. LIGHTNING STRIKES HOLES AT UPPER SECTION BETWEEN RIB 13-14 ON LT SKIN OF RUDDER IAW SRM 55-41-12 ( 16 A ) AND FIG 201 PARA 30 A APPLIED SURFACE PROTECTION IAW SRM 51-75-10 3C, REF EA 6-5540-156021.

Part: SKIN — DAMAGED (ZONE 300) · airframe 44,560 hrs · 22,652 cycles

RUDDER SKIN AT LT SIDE LWR 16IN . FROM BOTTOM AND 26 IN. FROM L/E SPAR HAS A 1.0 L X .75W PUNCTURE. RUDDER SKIN LT SIDE 16 IN FROM LOWER EDGE AND 26 IN FROM FWD SPAR WAS REPAIRED IAW SRM 55-41-12,PARA 30 AS SKIN REPAIR ONLY AS NO DAMAGE WAS FOUND AT THE CORE.

Part: FITTING — DAMAGED (ZONE 200) · airframe 44,560 hrs · 22,652 cycles

UPON REMOVAL AND REPLACEMENT OF FASTENERS AT FRAME 11 JUST AFT OF COCKPIT TO AVIONICS DOOR, FOUND FASTENER HOLE ELONGATED ON WEB. R & R WEB FITTING AT FRAME 11 IAW SRM 51-72-10, PAGES 1 THRU 3.

Part: FLOOR SUPPORT — CORRODED (ZONE 200) · corrosion level 2 · airframe 44,560 hrs · 22,652 cycles

MAIN DECK LONGITUTIONAL BEAM 3L BETWEEN FRAME 11 AND FRAME 13 CORRODED 4 SQ IN. R & R "T" CAP ON LONGITUTIONAL BEAM FROM FRAME 11 TO FRAME 15 IAW SRM 51-40-21, PAR 6, DUE TO CORROSION BEING OUT OF LIMITS WITH MATERIAL LOSS OF .014, STARTING AT .079 AND ENDING AT .065 IAW SRM 21-73-111.

Part: FLOOR SUPPORT — CORRODED (ZONE 200) · corrosion level 2 · airframe 44,560 hrs · 22,652 cycles

MAIN DECK FLOOR SUPPORT BETWEEN LONGITUTIONAL BEAM 3L AND 2L HAS 1.5 SQ IN CORROSION R & R "T" CAP ON FLOOR SUPPORT FROM FRAME 11 TO FRAME 12A IAW SRM 51-40-21, PARA 5, 6 & 7 AFTER CORROSION WAS FOUND TO BE OUT OF LIMITS WITH MATERIAL LOSS OF .009 WITH BEFORE .079 AND AFTER OF .070 IAW SRM 51-73-11.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 44,560 hrs · 22,652 cycles

FWD CARGO DOOR CUTOUT DENT AREA SHOWS INDICATIONS OF CRACKS AT 3 LOCATIONS. FABRICATED, LOCATED AND DRILLED REPAIR PARTS IAW SRM 53-13-12, FIG 206. ALODINED AND PRIMED IAW SRM 51-21-10 AND 51-75-10. INSTALLED REPAIR PARTS IAW SRM 53-13-12 AND 51-40-21. APPLIED EDGE SEAL IAW SRM 51-76-10. CUTOUT DAMAGED AREA FWD CARGO LOWER CORNER. APPLIED SEAL TO PART INSTALLED, REF WRI 53305331.

Part: WEB — DENTED (CARGO BAY) · airframe 44,560 hrs · 22,652 cycles

AFT CARGO COMPARTMENT FWD UPPER CORNER SUPPORT WEB DAMAGE/DENT 5" IN LENGTH. REMOVED AND REPLACED PROFILE WEB IAW SRM 51-72-10.

Part: INTERCOSTAL — CORRODED (CARGO BAY) · airframe 44,560 hrs · 22,652 cycles

AFT CARGO COMPARTMENT AT FR 63, BETWEEN FLOOR SUPPORT Y1470 AND Y805 INTERCOSTAL CORRODED INBD SIDE OF CUTOUT LINE. REMOVED LEVEL 1 CORROSION. REMOVED DAMAGED SECTION AND INSTALLED REPLACEMENT SECTION IAW SRM 53-10-15,FIG 207.

Part: FLOOR SUPPORT — BENT (CARGO BAY) · airframe 44,560 hrs · 22,652 cycles

CARGO COMPARTMENT FLOOR SUPPORT S51L BENT FROM FR 65 TO 69. R & R IAW SRM 51-40-21 AND REPROTECTED IAW SRM 51-75-10.

Part: FLOOR SUPPORT — BENT (CARGO BAY) · airframe 44,560 hrs · 22,652 cycles

CARGO COMPARTMENT FLOOR SUPPORT S44L, BENT FR64 TO FR 68. REPAIRED IAW SRM 51-40-21 AND REPROTECTED IAW SRM 51-75-10.

Part: FLOORBEAM — BENT (CARGO BAY) · airframe 44,560 hrs · 22,652 cycles

CARGO COMPARTMENT FLOORBEAM FR 67 BENT FROM LBL 46 TO 51 UP SIDE. REMOVED BENT FLOORBEAM IAW SRM 51-40-21, LOCATED AND DRILLED NEW FLOORBEAM IAW SRM 51-72-10, INSTALLED IAW 51-40-21 AND REPROTECTED IAW SRM 51-75-10.

Part: ACCESS PANEL — CRACKED (FUSELAGE) · airframe 44,560 hrs · 22,652 cycles

BOTTOM EXT FUSE EXT ELECTRICAL POWER ACCESS DOOR DOUBLER CRACKED RT SIDE UPPER .1" LENGTH. REMOVED BOTTOM EXT FUSE EXT ELECTRICAL PWR ACCESS DOOR TO FOM DOUBLER IAW SRM 51-40-21. LOCATED AND DRILLED NEW DOUBLER IAW SRM 51-72-10. ALODINED DOUBLER AND HOLES IAW SRM 51-21-10. REPROTECTED IAW SRM 51-23-10. INSTALLED DOOR IAW SRM 51-40-21.

Part: ANGLE — CRACKED (LT WING) · airframe 44,560 hrs · 22,652 cycles

LT WING INBD L/E AREA INSIDE KRUEGER FLAP WELL, OTBD SIDE OF FLAP WELL BETWEEN RIB 1 & RIB 2, 1.50" CRACK ON FIXED L/E STRUCTURE. REMOVED 3 EA PROTECTIVE COVERING IAW SRM 51-40-21. REMOVED CRACKED REINFORCING ANGLE IAW SRM 51-40-21. LOCATED AND DRILLED NEW REINFORCING ANGLE IAW SRM 51-72-10. INSTALLED NEW REINFORCING ANGLE IAW SRM 51-40-21. APPLIED TOP COAT WHERE NEEDED IAW SRM 51-23-10. INSTALLED 3EA PROTECTIVE COVERING PANELS IAW SRM 51-40- 20.

Part: FLOOR PANEL — DELAMINATED (ZONE 100) · airframe 44,560 hrs · 22,652 cycles

FLOOR PANEL 131JG HAS 30 SQ. IN. OF DELAMINATED AND MISSING SKIN IN FWD CARGO. FABRICATED REPLACEMENT PANEL 131JG IAW DWG SRZ 25-005 REV J.

Part: FITTING — DAMAGED (ZONE 100) · airframe 44,560 hrs · 22,652 cycles

CENTER WING BOX FWD FACE FR 47 LOWER EDGE FITTING IS DAMAGED CENTER TO 16" RT SIDE. R & R FITTING ON FR 47 IN CTR WING BOX IAW SRM 51-40-21, PARA 5-B.

Part: FLOOR PANEL — DAMAGED (ZONE 100) · airframe 44,560 hrs · 22,652 cycles

AFT CARGO FLOOR PANEL 152BF EXPOSE HONEYCOMB REF AMM 53-10-20-06 FABRICATED. REPLACEMENT FLOOR PANEL 152BF IAW DWG SRZ-25-005 REV J. MAJOR REPAIR IAW GMM 6-2-100.

Part: SKIN — MISREPAIRED (ZONE 100) · airframe 44,560 hrs · 22,652 cycles

FLUSH REPAIR ON RT SIDE FUSELAGE SKIN BETWEEN FRAMES 72 & 73 AND BETWEEN STRINGERS 30 & 32 RT, NOT EFFECTIVE IAW SRM 53-10-12, FIG 229. REMOVED AND REPLACED FASTENERS AND NOW IAW SRM 53-10-12,FIG 229.

Part: SKIN — MISREPAIRED (FUSELAGE) · airframe 44,560 hrs · 22,652 cycles

SKIN FLUSH REPAIR LOCATED ON RT SIDE FUSELAGE SKIN BETWEEN FRAMES 76 & 77 AND BETWEEN STRINGERS 28 & 31 RT HAS REPAIR NOT EFFECTIVE IAW SRM 53-10-12, FIG 229. REMOVED AND REPLACED REPAIR IAW SRM 53-10-12,FIG 229.

Part: RIB — CRACKED (NR 2 NACELLE) · airframe 44,560 hrs · 22,652 cycles

NR 2 PYLON OTBD SIDE RIB 3 SPLICE CRACKED. REMOVED DAMAGED SPLICE FROM NR 2 ENGINE OTBD PYLON IAW SRM 51-40-21, LOCATED AND DRILLED NEW SPLICE IAW SRM 51-40-21. LOCATED AND DRILLED NEW SPLICE IAW SRM 51-40-21 P.5-6.

Part: SKIN — MISREPAIRED (ZONE 100) · airframe 44,560 hrs · 22,652 cycles

EXTERNAL REPAIR DOUBLER LOCATED AT LOWER RT SIDE FUSELAGE SKIN BETWEEN FRAMES 30 TO 31 AND BETWEEN STRINGERS 52 RT TO 55 AT TOILET SERVICING ACCESS HAS INCORRECT RIVETS SIZE INSTALLED IN OUTER ROWS.

Part: SEAT TRACK — CORRODED (ZONE 200) · corrosion level 2 · airframe 44,560 hrs · 22,652 cycles

MAIN DECK SEAT TRACK 2R BET FR 17 AND FR 19 HAS CORROSION .250 INCH LENGTH REF AMM 53-12-00-06. REMOVED CORROSION IN BETWEEN FR17-FR19 SEAT TRACK 2 R IAW SRM 51-74-10. CHECKED LIMITS AND THEY WERE ORIGINAL MAT .028 MAT, LOSS .003, MAT. REMAINING .025 FOUND TO BE WITHIN LIMITS IAW SRM 53-10-16 ALODINED AREA IAW SRM 51-21-10 PG 8. PRIMED AND TOPCOATED AREA IAW SRM 51-75-10, PG 2036.

Part: FLOOR PANEL — DAMAGED (ZONE 100) · airframe 44,560 hrs · 22,652 cycles

BULK CARGO FLOOR PANEL 162CF EXPOSE HONEYCOMB REF. AMM 53-10-20-06. FABRICATED FLOOR PANEL IAW DWG SRZ25-005 REV. J MAJOR REPAIR IAW GMM6-2-100

Part: FLOOR SUPPORT — FAILED (ZONE 200) · airframe 44,560 hrs · 22,652 cycles

FLOOR SUPPORT MISREPAIRED. REPAIRED IAW SRM 51-72-10, PG 1TO3.

Part: SEAT TRACK — MISREPAIRED (ZONE 200) · airframe 44,560 hrs · 22,652 cycles

SEAT TRACK MISREPAIRED. R & R SEAT TRACK PER SRM 53-12-16, FIG 201, SH 1&2 PG 202-207. REPAIR IS A MAJOR PER GMM 6-2-100.

Part: FLOOR PANEL — DAMAGED (ZONE 700) · airframe 44,560 hrs · 22,652 cycles

CENTER AREA FLOOR PANEL 147AF DISBONDED AROUND INSERTS, ALSO LOOSE FASTENERS. REF 25- 50-00-06 FABRICATED REPLACEMENT FLOOR PANEL 147AF IAW DWG SRZ-02-005 REV J. MAJOR REPAIR IAW GMM 6-2-100.

Part: FLOOR PANEL — CORRODED (ZONE 100) · corrosion level 2 · airframe 44,560 hrs · 22,652 cycles

BULK CARGO FLOOR PANEL 161CF BOTTOM OF PANEL CORROSION 50 SQ IN REF AMM 53-10-20. FABRICATED REPLACEMENT PANEL 161CF IAW DWG-25-005 REV J. FABRICATED REPLACEMENT FACE PLATE IAW DWG SRZ-25-011, REV D IDENTIFIED REPLACEMENT PANEL IAW GMM 7-0-1001. MAJOR REPAIR IAW GMM6-2-100.

Part: FLOOR PANEL — DAMAGED (ZONE 200) · airframe 44,560 hrs · 22,652 cycles

MDCC FLOOR PANEL 231EF IMPACT DAMAGE. FABRICATED REPLACEMENT FLOOR PANEL 231EF IAW DWG. SRZ 25-005 REV. J.

Part: FLOOR PANEL — CRACKED (ZONE 100) · airframe 44,560 hrs · 22,652 cycles

FLOOR PANEL 151GF HAS THREE, FIVE INCH CRACKS, FABRICATED FLOOR PANEL IAW DWG SRZ 25-005. MAJOR REPAIR IAW GMM 6-2-100.

Part: FLOOR PANEL — CRACKED (ZONE 200) · airframe 44,560 hrs · 22,652 cycles

FLOOR PANEL 131ZF HAS 1 EA, 16" CRACK, FABRICATED REPLACEMENT FLOOR PANEL 131ZF IAW DWG SRZ 25-005, REV J.

Part: FLOOR PANEL — CRACKED (ZONE 100) · airframe 44,560 hrs · 22,652 cycles

FLOOR PNL 132YF HAS 10 SQ. IN OF DELAMINATION, 1EA, 4" CRACK AND 4-1" PUNCTURES. FABBED PANEL 132YF IAW DWG SRZ25-005, REV J.

Part: FLOOR PANEL — CRACKED (ZONE 200) · airframe 44,560 hrs · 22,652 cycles

MAIN DECK FLOORBOARD 261VF CRACKED ACROSS THE MIDDLE FABRICATED REPLACEMENT FLOOR PANEL 261VF IAW DWG SRZ 25-005, REV. J

Part: FLOOR PANEL — CRACKED (ZONE 100) · airframe 44,560 hrs · 22,652 cycles

FLOOR PANEL 132ZF HAS ONE 18'' CRACK. FABRICATED FLOOR PANEL IAW DWG SRZ 25-005 REV. J MAJOR REPAIR IAW GMM 6-2-100

Part: FLOOR PANEL — CRACKED (ZONE 200) · airframe 44,560 hrs · 22,652 cycles

MAIN DECK FLOOR PANEL 252ZG CRACKED AT 4EA CLEVIS CUTOUTS FABRICATED REPLACEMENT FLOOR PANEL 252ZG IAW DWG SRZ 25-005, REV J.

Part: FLOOR PANEL — CRACKED (FUSELAGE) · airframe 44,560 hrs · 22,652 cycles

FLOOR PANEL 131RF IS CRACKED ACROSS PANEL. FABRICATED REPLACEMENT PANEL 131RF IAW DWG SRZ 25-005 REV J.

Part: FLOOR PANEL — DAMAGED (ZONE 100) · corrosion level 2 · airframe 44,560 hrs · 22,652 cycles

FLOOR PANEL 131YF HAS 15" OF EDGE DAMAGE, 5" OF DELAMINATION, 20SQ." OF CORROSION FABRICATED REPLACEMENT PANEL IAW GWG SRZ-25-005 REV J IDENTIFIED REPLACEMENT PANEL IAW GMM 7-0-1001.

Part: FLOORBOARD — DAMAGED (ZONE 100) · airframe 44,560 hrs · 22,652 cycles

FLOOR PANEL 132RF HAS 50" OF EDGE DAMAGE. FABRICATED FLOOR PANEL 132RF IAW DWG, SRZ25-005 REV J.

Part: FLOOR PANEL — DAMAGED (ZONE 100) · airframe 44,560 hrs · 22,652 cycles

FLOOR PANEL 131HG HAS 10" OF EDGE DAMAGE, 10EA. PUNCTURES, 3EA. CRACKS FABRICATED REPLACEMENT PANEL 313HG IAW DWG SRZ-25-005 REV. J IDENTIFIED REPACEMENT PANEL IAW GMM 7-0-1001.

Part: FLOORBOARD — DAMAGED (ZONE 100) · airframe 44,560 hrs · 22,652 cycles

FLOORBOARD 131QF HAS 22" OF EDGE DAMAGE, 18EA .25 PUNCTURES, FABRICATED REPLACEMENT FLOORBOARD 131QF IAW DWG SRZ-25-005.

Part: PROCESSING UNIT — FAILED · airframe 44,457 hrs · 22,588 cycles

AFTER T/O HAD PITOT HEAT LIGHTS TAT LIGHT ON F/O CAP/STBY/F/O THEN ADC1 INOP. ATS 1 & 2 TRIPPED. CAB PRESS REG 2 FAULT. STATUS PAGE PROC: ENG ALTN MODE ATS-ALPHA FLOOR INOPERATIVE, PROBE HEAT PARTIALLY INOPERATIVE, CAB PRESS SYS 2 INOP. FOLLOWED ECAM PROCEDURES HAD ALL 3 PITOT HEAT OFF AS DIRECTED BY ECAM DIVERTED. REF WRI 32-30 5430 DUE TO PSEU BAD CAUSING ABOVE DESCRIPTION AND REPLACED PROXIMITY DETECTOR UNIT, CHECK OK REF AMM 32-31-71-04.

Part: VALVE — MALFUNCTIONED (LE SLATS) · airframe 43,671 hrs · 22,148 cycles

AFTER T/O ECAM INDICATED SLATS SYS 2 FAULT AND OVER-HEAD INDICATED SLATS SYS 2 FAULT LIGHT ILLUMINATED. CREW CYCLED SLATS TWICE - SLATS AND FLAPS WERE NORMAL AFTER SECOND CYCLE - LIGHT REMAINED ILLUMINATED. NR 2 SFCC FAULTED HIGH SPEED VALVE. REPLACED SLAT SYS 2 VALVE BLOCK ASSY 26CV IAW MM 27-84-33-04, OPS CHECK 27-84-00. RAN SLATS THROUGH SEVERAL TIME NO FAULTS ON OVERHEAD NR 2 SYS.

Part: VALVE — MALFUNCTIONED (NR 2) · airframe 43,549 hrs · 22,085 cycles

DURING SLAT RETRACTION ECAM IND SLAT SYS 2 FAULT WITH OVERHEAD LIGHT ON. CYCLED HANDLE NO JOY. SPFI INDICATED SLATS UP. ZIPPER AND HOOK WORKED NORMALLY, CONSULTED QRH, DID NOT COVER FAULT WITH SLATS ACTUALLY UP. WITH BOTH VISUAL AND SPFI INDICATING FLAPS UP, CONTINUED TO DESTINATION. FAULT LIGHT REMAINED ON DURING FLAP EXT, FLAPS OPERATED NORMALLY. R & R 26CV SLAT PCU VALVE BLOCK HIGH SPEED PRESSURE SWITCH, LEAKS AND OPS CHECK GOOD IAW MM.

Part: CONTROL HANDLE — INOPERATIVE (MLG) · airframe 43,516 hrs · 22,067 cycles

SELECTED THE LANDING GEAR LEVER DOWN WITH THE POSITION DET IN SYS 1. RECEIVED 3 GREEN DOWN INDICATIONS AND 3 RED UNLK INDICATIONS ON THE FWD PNL INDICATING SYS. THE INDICATING SYSTEMS ON THE OVERHEAD PNL WERE ALL GREEN. RELEASED FOR SERVICE IAW MEL: 32-61-01-B CATEGORY: B EXPIRATION: 20NOV10 "MEL 32-61-01-B: (IDENTIFY FWD) OR LANDING GEAR INDICATOR PANEL - INOP." REMOVED AND REPLACED LANDING GEAR CONTROL HANDLE UNIT 2GA REF AMM 32-31-11-04. TEST USING SIMULATOR TEST SET CHECKS NORMAL REF AMM 32-00-00-05.

Part: WIRE HARNESS — DAMAGED (THRUST REVERSER) · airframe 42,541 hrs · 21,510 cycles

NR 2 ENGINE OUT OF 15000 AT CLIMB POWER W/ANTI-ICE ON GOT GREEN REVERSER LIGHT WITH ACCOMPANYING ECAM PULLED BACK ABOUT .4 LIGHT WENT OUT PUSHED POWER BACK UP TO 230 AND LIGHT AND ECAM RETURNED. ACFT ENGINES INDICATED NORMAL AND ACFT FLEW NORMALLY. NO SIGN OF ACTUAL REVERSE. LANDING UNENVENTFUL. FOUND HARNESS 21W4076-515 CUT AND SHORTING 3 INCHES ABOVE PLUG 5010 ON NR 2 ENGINE. REPLACED HARNESS REF SMP AND WDM 78-31-04. PERFORMED HIGH POWER RUN REF JRH. NO FAULTS. REPLACED JUNCTION BOX COVER.

Part: WIRE HARNESS — DAMAGED (THRUST REVERSER) · airframe 42,527 hrs · 21,499 cycles

DURING CLIMBOUT PASSING 12000 FT, THE GREEN NR 2 THRUST REVERSER LIGHT CAME ON AND THE ECAM INDICATED ENGINE REVERSER UNLOCKED. COMPLIED WITH ECAM PROCEDURE AND REVERSER LIGHT EXTINGUISHED AFTER NR 2 THROTTLE WAS PULLED TO IDLE. CONTINUE QRH AND MEL REVIEW. SINCE MEL 78-30-01C DID NOT MENTION ECAM INDICATION AS ALLOWED, ELECTED TO RETURN TO KMEM. VERIFIED 78-30-01C WAS ACCOMPLISHED CORRECTLY. REMOVED AND REPLACED WIRE HARNESS 21W4140 PER AMM 71-51-01-4. REACTIVATED BOTH T/R HALVES. RESET CIRCUIT BREAKERS AND KEPT FAN COWLS OPEN TO FOM. PREFORMED NR 2 ENGINE T/R FUNCTIONAL TEST REF MM 78-31-00-5 06, OPS CHECKS GOOD. RAN ENGINE AT HIGH POWER NO FAULTS NOTED. SYSTEM OK FOR SERVICE.

Part: CYLINDER — WORN (MLG DOOR) · airframe 42,137 hrs · 21,289 cycles

PASSING 1000 AGL GOT AN ECAM ALERT "L/G DOOR SYS FAULT" NR1 SYS (FWD PANEL) SHOWED ALL UP, NR2 SYS (OVHD PANEL) SHOWED A NOSE GEAR DOOR FAULT. THERE WAS NO BUFFET. AT 12,500 AGL 290 KTS GOT STRONG VIBRATION, SLOWED TO 250 KTS AND DESCENDED. PULLING INTO THE GATE, THE NR1 SYS NOSE GEAR LIGHT CAME ON. VIBRATION STOPPED WHEN GEAR WAS LOWERED FOR LANDING. EMERGENCY DECLARED. SHIMMED EXCESSIVE PLAY FROM LT NOSE GEAR DOOR HINGE-REPLACED RT NOSE GEAR DOOR ACTUATOR FOR EXCESSIVE INTERNAL PLAY.

Part: SPAR — DAMAGED (WING BOX) · airframe 41,435 hrs · 20,880 cycles

CENTER WING BOX REAR SPAR FR 47 OVERSIZED HOLES. COMPLIED WITH EA 6-5710-127940.

Part: SKIN — CRACKED (ZONE 500) · airframe 41,435 hrs · 20,880 cycles

CENTER WING JOINT AT FRAME 40; LEFT SIDE AT THE UPPER SKIN LEVEL TENSION BOLT JUNCTION; ALL THREE FASTENER HOLES HAVE CRACK INDICATIONS. REMOVED DAMAGE BY REAMING, TREATED BARE METAL AND INSTALLED OVERSIZED BOLTS IAW EA 6-5710-127939 " WINGS, CENTER WING JOINT, REPAIR OF TENSION BOLT HOLES AT FRAMES 40 LT".

Part: HINGE — CHAFED (NACELLE DOOR) · airframe 41,435 hrs · 20,880 cycles

NR 2 ENGINE INBD FAN COWL DOOR AFT HINGE FITTING, FORWARD LUG HAS A CHAFING AREA. REMOVED DAMAGE IAW EA 6-7110-127945. FOUND TO BE WITHIN LIMITS IAW EA 6-7110-127945; ORIG THICKNESS 0.800. MATERIAL LOSS 0.100. MATERIAL REMAINING 0.700. PRIMED IAW A300-600 SRM 51-23-10 EA TITLE "POWER PLANT, NR 2 ENGINE INBD FAN COWL AFT HINGE".

Part: SUPPORT — CRACKED (ZONE 600) · airframe 41,435 hrs · 20,880 cycles

RIGHT WING T/E SUPPORT IS CRACKED ABOVE RIB 9. REMOVED FASTENERS AND BUTT STRAP IAW SRM 51-40-21; PG 22. LOCATED AND DRILLED NEW BUTT STRAP IAW SRM 51-40-21; PARA 7 AND SRM 51-40-44; PARA 3. INSTALLED BUTT STRAP IAW SRM 51-40-21; PARA 7. OPENED AND CLOSED PANEL 675 FB IAW PMS 10-05-17, AFTER MAINTENANCE WAS COMPLETE.

Part: INTERCOSTAL — CRACKED (ZONE 600) · airframe 41,435 hrs · 20,880 cycles

RIGHT WING T/E SUPPORT INTERCOSTAL IS CRACKED ABOVE THE NR 4 FLAP BEAM; RIB 16. REMOVED PANEL SUPPORT IAW SRM 51-40-21; PARA 6 AND 7. FORMED A NEW SUPPORT REF DWG A57240194; ISSUE "A". ALODINED AND PRIMED IAW SRM 51-2110 PARA 2-B AND SRM 51-23-20; PG 23. LOCATED AND DRILLED IAW DWG A57240194; ISSUE "A" AND SRM 51-40-21. PAINTED IAW SRM 51-23-10. INSTALLED IAW DWG A57240194; ISSUE "A".

Part: SUPPORT — CRACKED (ZONE 600) · airframe 41,435 hrs · 20,880 cycles

RIGHT WING T/E UPPER PANEL SUPPORT PLATE IS CRACKED AT RIB 9. REMOVED SUPPORT PLATE IAW SRM 51-40-21; PG 22. FORMED A NEW SUPPORT PLATE IAW DWG A57242294; MOD "B". HEAT TREATED NEW SUPPORT PLATE IAW TPS 1003, REV "A". ALODINED, PRIMED AND PAINTED NEW SUPPORT PLATE IAW AMM 51-23-10-0. PART MARKED NEW PLATE IAW GMM 7-0-1001. INSTALLED NEW SUPPORT PLATE IAW 51-40-21; PARA 6.

Part: SKIN — GOUGED (BS 3885) · airframe 41,435 hrs · 20,880 cycles

THE AFT PIT DOOR FRAME CUTOUT FWD LOWER CORNER IS GOUGED. REMOVED DAMAGE IAW A300-600 SRM 51-73-12 AND WAS FOUND TO BE OUT OF LIMITS. FABRICATED REPAIR IAW A300-600 SRM 53-17-12; FIG 202. ALODINED IAW A300-600 SRM 51-21-10. PRIMED IAW A300-600 SRM 51-21-10; PG 11. INSTALLED REPAIR IAW A300-600 SRM 51-40-21; PARA 7. SEALED DOUBLER IAW A300-600 51-24-00; OG 1.

Part: SKIN — GOUGED (ZONE 100) · airframe 41,435 hrs · 20,880 cycles

AFT LOWER FUSELAGE, FWD FRAME OF CARGO DOOR, SKIN GOUGED AND SCORED AT FRAME 58. REMOVED INTERCOSTAL AND STRAP IAW SRM 51-40-21, PARA 8. LOCATED AND DRILLED NEW STRAP IAW SRM 51-72-10. INSTALLED INTERCOSTAL AND STRAP IAW SRM 51-40-21, PARA 5.

Part: BEAM — CORRODED (ZONE 100) · corrosion level 2 · airframe 41,435 hrs · 20,880 cycles

THE BULK CARGO DOOR, LOWER CUTOUT SHIN PLATE, HAS CORROSION BELOW THE FASTENER HOLE AT FRAMES 68 - 69. REMOVED THE CORROSION ON THE LOWER CUTOUT SKIN PLATE IAW A300-600 SRM 51-74-10. MATERIAL THICKNESS IS 0.079. MATERIAL REMOVED 0.013. MATERIAL REMAINING 0.063 USING UT GAUGE T8225T. CHECKED LIMITS IAW A300-600 SRM 51-17-18 AND WAS FOUND TO BE OUT OF LIMITS. REMOVED 2 STRAPS; 2 FITTINGS AND SKIN PLATE IAW SRM 51-40-21; PARA 6 AND 7. INSTALLED 2 FITTINGS; 2 STRAPS AND A NEW SKIN PLATE, PO NR 651108.1 IAW A300-600 SRM 51-40-21, PARA 6 AND 7.

Part: FLOORBEAM — CORRODED (ZONE 100) · corrosion level 2 · airframe 41,435 hrs · 20,880 cycles

THE BULK CARGO COMPARTMENT FLOOR SUPPORT BEAM AT FRAME 67 AND RBL 46 HAS CORROSION (PITTING) IN THE AREA OF THE CARGO TIE DOWN. REMOVED CORROSION IAW SRM 51-74-10; PG 1. ANGLE WAS FOUND TO BE OUT OF LIMITS. LOCATED, DRILLED AND REPLACED NUT PLATES IAW SRM 51-72-10. INSTALLED SUPPORT ANGLE IAW SRM 51-40-21; PARA 6.

Part: BRACKET — DAMAGED (FLAP TRACK) · airframe 41,435 hrs · 20,880 cycles

LEFT WING FLAP TRACK FAIRING PANEL NR 535 BB MOUNT BRACKET SAFETY WIRE HOLES ON THE INBD SIDE IS STRIPPED OUT. SAFETIED LT WING FLAP TRACK FAIRING 535 BB, LT AND RT AFT ATTACHED BOLTS REF AMM 20-11-11-0 AND EA 6-5750-127936.

Part: BRACKET — DAMAGED (FLAP TRACK) · airframe 41,435 hrs · 20,880 cycles

LEFT WING FLAP TRACK FAIRING PANEL NR 533 BB MOUNT BRACKET SAFETY WIRE HOLES ON THE LT AND RT SIDES ARE STRIPPED OUT. SAFETIED LEFT WING FLAP TRACK FAIRING 533 BB, LT AND RT AFT ATTACHED BOLTS REF AMM 20-11-11-0 AND E.A. 6-5750-127936, REV "A".

Part: BRACKET — DAMAGED (FLAP TRACK) · airframe 41,435 hrs · 20,880 cycles

LEFT WING FLAP TRACK FAIRING PANEL NR 533 BB MOUNT BRACKET SAFETY WIRE HOLES ON THE LT AND RT SIDES ARE RIPPED OUT. SAFETIED LT WING FLAP TRACK FAIRING 532 BB, LT AND RT AFT ATTACHED BOLTS REF AMM 20-11-11-0 AND EA 6-5750-127936.

Part: BRACKET — DAMAGED (FLAP TRACK) · airframe 41,435 hrs · 20,880 cycles

LEFT WING FLAP TRACK FAIRING PANEL NR 536 BB, INBD MOUNT BRACKET SAFETY WIRE HOLE IS STRIPPED OUT. SAFETIED LT WING FLAP TRACK FAIRING 536 BB, LT AND RT AFT ATTACHED BOLTS REF AMM 20-11-11-0 AND EA 6-5750-127936.

Part: BRACKET — DAMAGED (FLAP TRACK) · airframe 41,435 hrs · 20,880 cycles

LEFT WING FLAP TRACK FAIRING PANEL NR 534 BB MOUNT BRACKET SAFETY WIRE HOLES ON THE LT AND RT SIDES ARE RIPPED OUT. SAFETIED LT WING FLAP TRACK FAIRING 534 BB, LT AND RT AFT ATTACHED BOLTS REF AMM 20-11-11-0 AND EA 6-5750-127936.

Part: INTERCOSTAL — BENT (ZONE 200) · airframe 41,435 hrs · 20,880 cycles

THE INTERCOSTAL UPPER FLANGE IS BENT AT FRAME 86 AND STRINGER 39R REMOVED INTERCOSTAL AT FRAME 86 AND STRINGER 39R IAW SRM 51-40-21; PARA 6 AND 7. INSTALLED INTERCOSTAL IAW SRM 51-40-21; PARA 6 AND 7 AND SRM 51-72-10. APPLIED CIC IAW SRM 51-23-20.

Part: FLOOR PANEL — DELAMINATED (ZONE 200) · airframe 41,435 hrs · 20,880 cycles

MAIN CARGO DECK FLOORBOARD 231 CF IS SPONGY FROM FRAMES 20-22 AND LBL Y 95 - Y 120. FABRICATED NEW FLOOR PANEL 231 CF IAW DWG SRZ 25-005; REV "H".

Part: FLOOR PANEL — DELAMINATED (ZONE 200) · airframe 41,435 hrs · 20,880 cycles

MAIN CARGO DECK FLOORBOARD 231 HF IS SPONGY FROM FRAMES 22 - 24 AND LBL Y 95 - Y 120. FABRICATED NEW FLOOR PANEL 231 HF IAW DWG SRZ 25-005; REV "H".

Part: FLOOR PANEL — CRACKED (ZONE 200) · airframe 41,435 hrs · 20,880 cycles

FLOOR PANEL 242 HK IS CRACKED. FABRICATED NEW FLOOR PANEL USING THE OLD PANEL AS A TEMPLATE. MATERIAL ID; LOCATED AND COUNTERSUNK HOLES; POTTED INSERTS; POTTED EDGES; COMPLETED CURE; SANDED; APPLIED ANTI-SKID AND PART MARKED IAW DWG SRZ 25-005; REV "H".

Part: FLOOR SUPPORT — CORRODED (ZONE 200) · airframe 41,435 hrs · 20,880 cycles

BULK CARGO COMPARTMENT FLOOR SUPPORT BETWEEN FRAME 68 AND FRAME 69 AT STRINGER 48R HAS CORROSION AROUND FASTENER HOLE. BLENDED CORROSION IAW SRM 51-74-10 AND FOUND TO BE OUT OF LIMITS IAW SRM 53-10-00. INSTALLED NEW FLOOR SUPPORT P/N A5397426300000 IAW SRM 51-40-21; PARA 6; SHEET 1.

Part: FLOOR PANEL — DENTED (CARGO BAY) · airframe 41,435 hrs · 20,880 cycles

BULK CARGO PIT FLOOR PANEL 161GF HAS SEVERAL DENTS ON TOP SIDE. FABRICATED PER DWG SRZ 25-005; REV "H" AND DWG SRZ 25-011; REV "C".

Part: FLOOR PANEL — DAMAGED (ZONE 100) · airframe 41,435 hrs · 20,880 cycles

FWD CARGO PIT FLOOR PANEL 132QF IS BROKE IN HALF. FABRICATED FWD PIT FLOOR PANEL 132QF PER A300-600 DRW SRZ-25-005 REV G.

Part: HINGE FITTING — BENT (ZONE 500) · airframe 41,435 hrs · 20,880 cycles

LT WING AT NR 2 SPOILER CENTER HINGE FITTING BENT. REMOVED COVER, ANGLE AND BRACKET. LOCEATED, DRILLED, DEBURRED & LOCATED BRACKET. INSTALLED BRACKET IAW SRM 51-40- 21 PG 7 & 133. ALSO SRM 51-40-44 PG 1.

Part: SUPPORT BRACKET — CRACKED (ZONE 400) · airframe 41,435 hrs · 20,880 cycles

NR 2 PYLON PNEUMATIC BLEED DUCT, LT SIDE LOWER END, CRACKED SUPPORT BRACKET ATTACHED TO HEAT SHIELD. WELDED CRACKED SUPPORT BRACKET IAW AEROSPATIALE DWG A36115020 AND APA 01-04- 21. REMOVED AND INSTALLED IAW A300-600 AMM 36-11-00-01.

Part: RIB — CRACKED (LT WING TE FLAP) · airframe 41,435 hrs · 20,880 cycles

LT INBD FLAP RIB 25A HAS APPROX .125 INCH CRACK RIB 25A - RIB 25A. REMOVED THE UPPER SKIN, DAMAGED RIB, TWO CLOSE OUT PANELS, SIX STIFFENERS, TWO RUB STRIPS AND THE T/E FLAP TIP. LOCATED, DRILLED & DEBURRED RIB. INSTALLED ALL PARTS IAW SRM 51-40-21 PG 7 & PG 9 ALSO SRM 51-40-44 PG 6.

Part: OUTFLOW VALVE — FAILED (CABIN AIR) · airframe 39,822 hrs · 19,933 cycles

OVBD FLOW EXTRACT FAN FAULT WENT OVERBOARD THEN LOST PRESSURIZATION. DECLARED EMERGENCY DIVERTED TO MEMPHIS, WARNING HORN BREAKER H60 PULLED FOR MAINT PURPOSES. FOUND VENT-EXTRACT FAN AND VALVES CNTL C/B TRIPPED. RESETT. C/B TRIPPED WHEN VENT EXTRACT SELECTED OFF AND OVERBOARD EXTRACT VALVE TRIED TO DRIVE CLOSED. REMOVED AND REPLACED OVERBOARD EXTRACT VALVE 75HR. IN REF TO A300-600 AMM. 21-23-13-4. OPS TEST NORMAL.

Part: RIB — CRACKED (ZONE 500) · airframe 39,722 hrs · 19,880 cycles

LT WING INBOARD FLAP RIB 25 FOUND CRACKED. REPLACED FLAP RIB 25 AND RUB AND ROLLER TRACK.

Part: RIB — CRACKED (ZONE 600) · airframe 39,722 hrs · 19,880 cycles

RT INBOARD FLAP RIB 25 FOUND CRACKED REMOVED SKIN AND STRINGERS. REMOVED DAMAGED RIB 25. INSTALLED NEW RIB 25 AND RE-INSTALLED SKIN AND STRINGERS. SEALED AND PAINTED.

Part: SKIN — DAMAGED (LT WING) · airframe 39,572 hrs · 19,791 cycles

WING BOTTOM SKIN PANEL NR 1 LT, INCOMPLETE RECORDS OF EMBODIMENT OF DRW: R572-40179 AT FWD EDGE JUST OUTBOARD OF PYLON. IN ADDITION FOUND NUMEROUS DEVIATIONS (AT HOLE 7 & 9) AND CRACK IN HOLE 23 REPAIR PERFORMED BY RE-EMBODIMENT OF DRW: R572-40179 WITH CRACK STOP HOLE NR 7 AND NR 9 IAW EA 6-5720-99219 AND RAS/BAE/1003499/2006 ISS "A".

Part: FITTING — DAMAGED (ZONE 600) · airframe 39,572 hrs · 19,791 cycles

ELONGATED HOLE IN CORNER FITTING OF CENTER WING TANK, FRAME 40, RIB 1 RHS. REPAIR PERFORMED BY REAM UP THE HOLE TO FINAL DIA 14,247-14,287 MM AND SPOT FACING IAW EA 6-5710-103331 AND RAS/047032/008/2006 ISS "A".

Part: FLOORBEAM — MISREPAIRED (ZONE 100) · airframe 39,572 hrs · 19,791 cycles

OLD TOP CAP BEAM REPAIR FRAME 63 LT NOT CONFORM TO RAS/DAHAM/11513/1999 ISS. "A". SPLICE REPAIR RENEWED IAW RAS/DAHAM/11513/1999 ISS "A".

Part: RIB — CHAFED (ZONE 600) · airframe 39,572 hrs · 19,791 cycles

CHAFING MARK AT END OF RIB 6-A, OUTBOARD SIDE RT WING T/E. REPAIR PERFORMED BY BLEND IAW EA 6-5751-103339 AND RAS/BAE/1003495/2006 ISS "A".

Part: BEAM — CHAFED (ZONE 600) · airframe 39,574 hrs · 19,792 cycles

CHAFING MARKS FOUND ON VERTICAL WEB OF FLAP TRACK BEAM 3 OUTBOARD CHANNEL LHS, BEAM 3 INBOARD CHANNEL RHS. REPAIR PERFORMED BY BLEND OUT WITH NDT INSPECTION IAW EA 6-5720-103376 AND RAS/BAE/1003599/2006 ISSUE "A".

Part: BEAM — DAMAGED (ZONE 100) · airframe 39,572 hrs · 19,791 cycles

TOOLING MARK WAS CAUSED IN THE EDGE OF FLANGE SPAR RADIUS AT BEAM 2 RT AT FRAME 42. REPAIR PERFORMED BY SMOOTH REWORK IAW EA 6-5710-103336 AND RAS/046790/014/2006 ISS "A".

Part: FRAME — CHAFED (ZONE 200) · airframe 39,572 hrs · 19,791 cycles

CHAFING MARK ON THE INNER FLANGE OF FRAME 38.2 BETWEEN STRG 14-15 LT. REPAIR PERFORMED BY BLEND OUT AND INSTALLING A REPAIR ANGLE AS PER SRM 53-10-13/FIG 202 IAW EA 6-5310-103329 AND RAS/DABRE/7006981/2006 ISS "A".

Part: STRINGER — MISREPAIRED (ZONE 100) · airframe 39,574 hrs · 19,792 cycles

FOUND SEVERAL MISDRILLED/ELONGATED HOLES BETWEEN FRAME 38.1-38.2, STGR 31, LHS. REPAIR PERFORMED WITH BUSHING REPAIR AND INSTALLING 4, 8MM DIA HI-LOKS IAW EA 6-5314-103278 AND RAS/DABRE/7006911/2006 ISS "A".

Part: FRAME — CORRODED (ZONE 300) · corrosion level 2 · airframe 39,572 hrs · 19,791 cycles

CORROSION AT CROSSBEAM FRAME 87 RT AFT FACE, OUT OF LIMIT. REPAIR PERFORMED BY REPLACEMENT OF PART IAW SRM 51-72-10.

Part: BEAM — CHAFED (ZONE 500) · airframe 39,574 hrs · 19,792 cycles

CHAFING MARKS FOUND ON VERTICAL WEB OF FLAP TRACK BEAM 2 INBOARD CHANNEL LHS. REPAIR PERFORMED BY BLEND OUT WITH NDT INSPECTION IAW EA 6-5720-103376 AND RAS/BAE/1003599/2006 ISSUE "A".

Part: BEAM — CHAFED (ZONE 600) · airframe 39,574 hrs · 19,792 cycles

CHAFING MARKS ON VERTICAL WEB OF FLAP TRACK BEAM NR 4 RT, OUTBOARD SIDE. REPAIR PERFORMED BY BLEND OUT WITH NDT INSPECTION IAW EA 6-5720-103376 AND RAS/BAE/1003599/2006 ISSUE "A".

Part: STRUCTURE — DAMAGED (ZONE 100) · airframe 39,572 hrs · 19,791 cycles

FOUND OLD TOOLING MARKS AT GANTRIES 4 AND 5 RT AND 5 LT, FRAME 47-48. REPAIR PERFORMED WITH SMOOTH REWORK AND INSTALLING CORNER ANGLES AND STRAPS IAW EA 6-5315-103326 AND RAS: 046958/010/2006 ISS "A".

Part: SKIN PANEL — MISREPAIRED (ZONE 100) · airframe 39,574 hrs · 19,792 cycles

FOUND SEVERAL MISDRILLED/ELONGATED HOLES BETWEEN FRAME 38.1-38.2, STGR 31, LHS. REPAIR PERFORMED WITH BUSHING REPAIR AND INSTALLING 4,8MM DIA HI-LOKS IAW EA 6-5314-103278 AND RAS/DABRE/7006911/2006 ISS "A".

Part: ANGLE — MISREPAIRED (ZONE 100) · airframe 39,574 hrs · 19,792 cycles

FOUND SEVERAL MISDRILLED/ELONGATED HOLES BETWEEN FRAME 38.1-38.2, STGR. 31, LHS. REPAIR PERFORMED BY REPLACEMENT OF ANGLE WITH BUSHING REPAIR AND INSTALLING 4, 8MM DIA HI-LOKS TOGETHER WITH TWO SKIN PANELS AND A STRINGER IAW EA 6-5314-103278 AND RAS/DABRE/7006911/2006 ISS "A".

Part: FRAME — DENTED (ZONE 100) · airframe 39,569 hrs · 19,790 cycles

SEVERAL DENTS IN DIAPHRAGM FRAME 47-52, TR 1-2 LT AND FRAME 51-53, TR. 2-3 RT, DENTS ACCEPTED IN STATE WITH NDT INSPECTION (CRACK FREE) IAW EA 6-5315-103290 AND RAS: 046817/006/2006 ISS."A".

Part: SKIN PANEL — DAMAGED (ZONE 100) · airframe 39,569 hrs · 19,790 cycles

TWO SCRATCHES ON FRAME C25 AND C27, STRG 35 LHS. REPAIR PERFORMED WITH CUTOUT OF DAMAGED SKIN AND EXTERNAL DOUBLER, INSTALLATION IAW EA 6-5315-103323 AND RAS/DABRE/7006935/2006.

Part: SKIN PANEL — CORRODED (ZONE 800) · corrosion level 2 · airframe 39,569 hrs · 19,790 cycles

CORROSION ON BULK CARGO DOOR SKIN PANEL (AROUND THE DOOR HANDLE), OUTSIDE. REPAIR PERFORMED BY BLEND OUT UNTIL CORROSION REMOVAL IAW EA 6-5234-103310 AND RAS/DABRE/7006925/2006 ISS "A".

Part: SKIN PANEL — UNKNOWN (ZONE 100) · airframe 39,572 hrs · 19,791 cycles

FOUND OLD DOUBLER REPAIR AT FRAME 26-27, STRG 24-26 RT. THE REPAIR WAS PERFORMED IAW DRW: R537B1730-002 BUT FOUR HOLES HAVE DIA: 7, 5MM INSTEAD OF 4,8MM. REPAIR PERFORMED BY REAM UP THE DIAMETERS TO 8, 8-9, 0MM AND INSTALL FOUR SHOULDERED BUSHES IAW EA 6-5314-103330 AND RAS/DABRE/7006980/2006 ISS. "A".

Part: BULKHEAD — DAMAGED (ZONE 100) · airframe 39,569 hrs · 19,790 cycles

HOLE FOUND ON PRESSURE BULKHEAD AT FRAME 39, Y-2244, Z-1425 CLOSE TO BRACKET A534-10096-204. REPAIR PERFORMED BY TRIMMING THE PRESSURE BULKHEAD AROUND THE DAMAGED AREA AND INSTALLATION OF REPAIR DOUBLER IAW EA 6-5314-103312 AND RAS: 046974/011/2006 ISS "A".

Part: STRUCTURE — DAMAGED (ZONE 100) · airframe 39,572 hrs · 19,791 cycles

FOUND DAMAGED HOLES (COUNTERSUNK) IAW SB A300-53-6063 AT C40-41 RT, HOLE 24, 25, 26 AND 27. REPAIR PERFORMED BY REMOVING FASTENERS, ROTO-TEST AND INSTALLING FASTENERS HL13VF10 WITH NEW COUNTERSUNK IAW EA 6-5315-103324.

Part: FRAME — CHAFED (ZONE 200) · airframe 39,572 hrs · 19,791 cycles

CHAFING MARKS ON THE INNER FLANGE OF FRAME 22 BETWEEN STRG 14-15 RT. REPAIR PERFORMED BY BLEND OUT AND INSTALLING A REPAIR ANGLE AS PER SRM53-10-13/FIG 202 IAW EA 6-5310-103329 AND RAS/DABRE/7006981/2006 ISS "A".

Part: SKIN PANEL — NONE (ZONE 100) · airframe 39,569 hrs · 19,790 cycles

EXISTING OLD EXTERNAL DOUBLER AT FRAME 17-18, STRG 39-41 LT DID NOT FIND IAW, REPAIR DRAWING R53610848. REPAIR RENEWED WITH INSTALLING OVERSIZE FASTENERS IAW EA 6-5312-103314 AND RAS/AS/143/2006 ISS "A".

Part: SKIN PANEL — DAMAGED (ZONE 100) · airframe 39,562 hrs · 19,787 cycles

MISDRILLED HOLE (DOUBLEHOLE DIA 9 MM) IN OUTER SKIN BETWEEN FRAME 38.1-38.2, STRINGER 27, LHS. REPAIR PERFORMED WITH REPAIR BUSHING DUE TO MISSDRILLED HOLE IAW SRM 53-10-12/FIG 221 AND EA 6-5314-103335.

Part: GUSSET — CORRODED (ZONE 200) · corrosion level 2 · airframe 39,562 hrs · 19,787 cycles

CORRODED GUSSET PLATE AT FRAME 79, STRG 26, LT AND RT. REPAIR PERFORMED BY REPLACEMENT OF PLATES IAW SRM 51-72-10.

Part: SKIN PANEL — DAMAGED (ZONE 100) · airframe 39,562 hrs · 19,787 cycles

FOUND SEVERAL MISDRILLED/ELONGATED HOLES BETWEEN FRAME 38.1-38.2, STGR 31, LT. REPAIR PERFORMED WITH BUSHING REPAIR AND INSTALLING 4, 8MM DIA LOCK FASTENERS IAW EA 6-5314-103278 AND RAS/DABRE/7006911/2006 ISS "A".

Part: ANGLE — CORRODED (ZONE 600) · corrosion level 2 · airframe 39,560 hrs · 19,786 cycles

DAMAGED REINFORCING ANGLE IN KRUEGER FLAP AREA RT WING. REPAIR PERFORMED BY REPLACEMENT OF REINFORCEMENT ANGLE IAW SRM 57-41-11.

Part: STRINGER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 39,562 hrs · 19,787 cycles

CORROSION ON STRG 56 LT AND RT OUTER FLANGE BETWEEN C76-77. REPAIR PERFORMED BY BLEND OUT WITHIN THE LIMITS AS PER REPAIR REF EA 6-5318-103300, APPROVED BY RAS/DATLS/0003345/2006 ISS "B".

Part: SHEAR PLATE — CRACKED (ZONE 200) · airframe 39,562 hrs · 19,787 cycles

CRACKED SHEARPLATE BETWEEN FRAME 79-80, STRG. 26, LHS. REPAIR PERFORMED BY REPLACEMENT OF SHEARPLATE IAW SRM 51-72-10.

Part: FITTING — CRACKED (ZONE 100) · airframe 39,562 hrs · 19,787 cycles

FINDING CRACKS DURING ACCOMPLISHMENT OF SB A300-57-6049 AND A300-57-6086 IN CENTER WING BOX CORNER ANGLE FITTING (HOLE A (LT/RT), Q, G , I (LT). REPAIR PERFORMED BY REAM UP UNTIL CRACK REMOVAL IAW EA 6-5710-103311 AND RAS/AS/0159/2006 ISS A AND RAS /046825/029/2006 ISS A.

Part: SKIN PANEL — DAMAGED (ZONE 100) · airframe 39,560 hrs · 19,786 cycles

WEAR MARKS ON THE FUSELAGE SKIN (KARMAN STRUCTURE AREA) BETWEEN FRAME 38.1/39 AND STRINGER 30/32 RT. REPAIR WITH SMOOTH BLEND OUT AND REINSTALLATION OF ORIGINAL OR OVERSIZED FASTENERS IAW EA 6-5314-103265 AND RAS/DA/BRE/7006916/2006 ISS "C".

Part: SILL — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,463 hrs · 19,735 cycles

HEAVY CORROSION ON UPPER FLANGE OF THE AFT CARGO DOOR SILL BEAM BTW C59-64 RT. REPAIR PERFORMED BY REPLACEMENT OF UPPER FLANGE IAW EA 6-5317-103276 AND RAS/DATLS/0003386/2006.

Part: STRUCTURE — CORRODED (DRUEGER FLAPS) · corrosion level 2 · airframe 39,463 hrs · 19,735 cycles

HEAVY CORROSION IN KRUEGER FLAP AREA LT ON FITTING P/N: A535-10217-200 RIBLET (P/N A572-41993-200) IS CRACKED. REPAIR WAS PERFORMED BY REPLACEMENT OF FITTING IAW SRM 57-45-11 AND CHANGE RIBLET IAW SRM 57-41-11/FIG 1.

Part: CROSSBEAM — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,463 hrs · 19,735 cycles

CORROSION ON CROSSBEAM AT C67 RT (-Y805 TILL -Y1470, P/N A539-74360-200) AND C56A LT (Y805 TILL Y1470, P/N A539-74268-200). AFTER BLENDING, REMAINING THICKNESS WAS OUT OF LIMIT. REPAIR PERFORMED BY INSTALLING SPLICE IAW SRM 53-10-15/FIG 207.

Part: FITTING — CORRODED (ZONE 600) · corrosion level 2 · airframe 39,463 hrs · 19,735 cycles

CORROSION ON FITTING AND DAMAGED REINFORCING ANGLE IN KRUEGER FLAP AREA RT. REPAIR WAS PERFORMED BY REPLACEMENT OF FITTING IAW SRM 57-45-11 AND REINFORCEMENT ANGLE IAW SRM 57-41-11.

Part: SKIN — DENTED (ZONE 100) · airframe 39,463 hrs · 19,735 cycles

TWO SIMILAR DEFORMATIONS ON SKIN PANEL (BOTH RHS AND LHS) BETWEEN C51 AND C52, P39-40. REPAIR PERFORMED BY DRESSING BACK THE DENTS, PERFORMING ROTOTEST AND HFEC AND INSTALLING HL11VF5 FASTENERS IAW EA 6-53-15-103318 AND RAS 046898/014/2006.

Part: CROSSBEAM — MISREPAIRED (ZONE 100) · corrosion level 2 · airframe 39,352 hrs · 19,681 cycles

FOUND CORROSION AT CROSSBEAM C58 RT ( P/N A539-74268) OUTBOARD OUT OF LIMIT AND OLD REPAIR ON CROSSBEAM C62 LT (P/N A539-70091) NOT CONFORM TO SRM REPAIR PERFORMED IAW SRM 53-10-15 FIG 207 AT CROSSBEAM C 62 LT AND 58 RT.

Part: SPAR — CRACKED (ZONE 100) · airframe 39,352 hrs · 19,681 cycles

DAMAGED HOLES (CRACKS IN HOLE 1, 2, 3, 4, 5, 6, 8) ON C44 CENTER SPAR WEB REPAIR PERFORMED BY OVERSIZING THE HOLES UNTIL CRACKS ARE REMOVED IAW EA 6-5710-103327 AND RAS 046993/014/2006 ISS A.

Part: SKIN — CHAFED (ZONE 600) · airframe 39,331 hrs · 19,670 cycles

CHAFING MARK FOUND ON LEADING EDGE NOSE SKIN, RT WING, BETWEEN TRACK 3 AND WOFX-69.00. REPAIR PERFORMED BY REWORK OF SKIN AND IS APPROVED BY EA 6-5741-103287 AND RAS/BAE/1003389/2006 ISSUE "A".

Part: FITTING — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,323 hrs · 19,667 cycles

CORROSION AT MANHOLE FITTING BETWEEN C38.1-C38.2, WHICH WAS GRINDED THROUGH THE FITTING WITH THE SKIN PANEL AFFECTED. REPAIR PERFORMED BY BLEND OUT AND INSTALLATION WASHER IN BLEND VOID AND ADDITIONAL FASTENER IAW SRM 53-14-12/FIG 208, EA 6-5334-103277 AND RAS/DATLS/0003381/2006.

Part: SUPPORT FITTING — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,323 hrs · 19,667 cycles

CORROSION ON Y-Z LATCH SUPPORT FITTING, C25A, RT. REPAIR PERFORMED IAW SRM 53-13-13 / FIG 204, SHEET 1 AND 2.

Part: BEAM — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,323 hrs · 19,667 cycles

FWD CARGO DOOR, CORROSION ON SILL BEAM AND AROUND SEVERAL FASTENER HOLES FOUND. REPAIR PERFORMED BY REWORK AND INSTALLING REPAIR ANGLE IAW EA 6-5313-103279 AND RAS/DABRE/7006910/2006 ISSUE "A".

Part: FLOORBEAM — MISREPAIRED (ZONE 100) · corrosion level 2 · airframe 39,323 hrs · 19,667 cycles

OLD CORROSION REPAIR ON TOP CAP BEAM C38.2 LT, THIS SPLICE REPAIR IN FWD CARGO COMPARTMENT IS NOT REPAIRED IAW OLD DOCUMENTATION OR ALLOWABLE SRM REFERENCE. TOP CAP BEAM WAS REPAIRED FOLLOWING PRINCIPLE OF SRM 53-10-15 / FIG 207.

Part: STRINGER — DAMAGED (ZONE 100) · airframe 39,323 hrs · 19,667 cycles

DAMAGED STRINGERS FOUND BETWEEN C28-29, STRG 53 RT AND BETWEEN C27-28, STRG 40 LT. STRINGER REPAIR PERFORMED IAW SRM 53-10-14/FIG 201.

Part: SKIN — UNKNOWN (ZONE 600) · airframe 39,323 hrs · 19,667 cycles

OLD REPAIR (FLUSH DOUBLER) REPAIR ON RT OUTBOARD SLAT NR 3 JACK RIB 6 NOT CONFORM TO SRM (FILLER MATERIAL, RIVET PITCH, USED FASTENER). REPAIR PERFORMED BY NEW FLUSH REPAIR, APPROVED BY EA 6-5744-103280 REV A AND RAS/FOK/213/2006 ISS. C.

Part: PLATE — DAMAGED (ZONE 200) · corrosion level 2 · airframe 39,323 hrs · 19,667 cycles

FRETTING MARKS ON INNER FLANGE C55 AND 57.2 LT AND C58 RT, P14-15 LT/RT, AND TOOL MARKS ON EMERGENCY EXIT TOP COVERPLATE LT/RT REPAIR PERFORMED BY BLEND OUT AND POLISHING TO SMOOTH CONTOUR IAW EA 6-5316-103275 AND RAS/DATLS/0003334/2006 ISS A AND RAS/DATLS/0003335/2006 ISS. A.

Part: DOUBLER — NONE (ZONE 100) · airframe 39,323 hrs · 19,667 cycles

OLD DOUBLER REPAIR C 19-20, P 38-40 LT, IN CONFLICT WITH P TO F CONVERSION REPAIR PERFORMED BY NEW DOUBLER INSTALLATION IAW EA 6-5313-103273 AND RAS/DABRE/7006901/2006 ISS A.

Part: DOOR — CHAFED (ZONE 800) · airframe 39,323 hrs · 19,667 cycles

FOUND OLD DOUBLER INSTALLED ON BULK CARGO DOOR FWD LOWER CORNER, WHICH WAS NOT CONFIRM TO RAS (THICKNESS AND MATERIAL) REPAIR WAS PERFORMED BY INSTALLING A NEW DOUBLER IAW EA 6-5234-103320 AND RAS/DABRE/7006375/2006 ISS A.

Part: PANEL — MISREPAIRED (ZONE 100) · airframe 39,323 hrs · 19,667 cycles

FOUND OLD DOUBLER REPAIR C19-20, P 43-44 RT, NOT CONFORM TO SRM. REPAIR PERFORMED BY NEW DOUBLER INSTALLATION IAW EA 6-5312-103293 AND RAS/AS/137/2006 ISS A.

Part: DOUBLER — MISREPAIRED (ZONE 100) · airframe 39,323 hrs · 19,667 cycles

FOUND OLD DOUBLER REPAIR , C77-78, P27 RT NOT CONFORM TO SRM REPAIR PERFORMED BY NEW DOUBLER INSTALLATION IAW SRM 53-10-12 FIG 228, APPROVED BY EA 6-5318-103319.

Part: SKIN — UNKNOWN (ZONE 100) · corrosion level 2 · airframe 39,323 hrs · 19,667 cycles

LT/RT ON SILL BEAM AND EXTERNAL SKIN, INTERNAL DOUBLER CORROSION AND DAMAGED HL, COLLARS (FOLLOWING P/N AFFECTED: A539-80110-207, A539-80071-205, A539-80071-205, A539-80108- 205, A539-81259-211, A539-80177-201, A539-80108-204, A539-81259-210, A539-80177-200). REPAIR PERFORMED BY REWORK OF STRUCTURE AND SPOT FACING IAW EA 6-5318-103295 AND RAS/DAHAM/4021175/2006 ISS A.

Part: SKIN — UNKNOWN (ZONE 600) · airframe 39,323 hrs · 19,667 cycles

OLD BONDING REPAIR RT AILERON LOWER SKIN T/E WITH NEW DELAMINATION REPAIR PERFORMED BY METAL SKINNED HONEYCOMB PATCH REPAIR IAW SRM 51-77-12 PB 200 PARA 4 AND RAS/FOK/097/ 2004 ISS A.

Part: SKIN — UNKNOWN (ZONE 500) · airframe 39,323 hrs · 19,667 cycles

OLD BONDING REPAIR LT AILERON LOWER SKIN T/E WITH NEW DELAMINATION REPAIR PERFORMED BY METAL SKINNED HONEYCOMB PATCH REPAIR IAW SRM 51-77-12 PB 200 PARA 4.

Part: SKIN PANEL — WORN (ZONE 500) · airframe 39,309 hrs · 19,658 cycles

ELONGATED HOLES ON LT WING-PYLON SUPPORT BRACKET AND BOTTOM SKIN REPAIR PERFOMED BY OVERSIZING THE HOLE AND MANUFACTURE A FREEZE PLUG IAW DWG R571- 50532, APPROVED BY EA 6-5720-103269 AND RAS/BAE/1003287/2006 ISS. A

Part: PANEL — CRACKED (ZONE 400) · airframe 39,309 hrs · 19,658 cycles

CRACK (L<25MM) ON PYLON NR 2, RIB 8, OUTBOARD SIDE DOUBLER REPAIR PERFORMED IAW SB 54-6015 AND DWG R546-10124, APPROVED BY EA 6-5451-103251.

Part: FRAME — CRACKED (ZONE 200) · airframe 39,309 hrs · 19,658 cycles

C44 RT AND C46 RT, FOUND OLD DOUBLER REPAIR ON FRAME DUE TO CRACKING FINDINGS IAW SB 53-6122 REPAIR PERFORMED BY REPLACEMENT OF FRAME C 44 (P/N A538-12310-201) AND 46 (P/N A538-12312-201) IAW SRM 51-72-10.

Part: SKIN PANEL — WORN (ZONE 600) · airframe 39,309 hrs · 19,658 cycles

ELONGATED HOLES ON RT WING-PYLON SUPPORT BRACKET AND BOTTOM SKIN, RIB 8 AREA REPAIR PERFORMED BY OVERSIZING HOLES AND MANUFACTURING FREEZE PLUGS IAW DWG R571-50532 ISS. A. APPROVED BY EA 6-5720-103269 AND RAS/BAE/1003287/2006 ISS. A