N809FD

Part: TEE FITTING — CRACKED (RT WING) · airframe 49,635 hrs · 18,186 cycles

CNTR WING INSP REAR SPAR INTERNAL ANGLE/TEE FITTING FR44 RT SIDE FWD HOLE WITH CRACK SIGNAL. COMPLIED WITH EA:6-5710-T0343040 PT1 REPAIRED CENTER WING REAR SPAR RIB1 INTERNAL ANGLE/TEE FITTING AT FR44 RH SIDE FWD HOLE(#34A). MAJOR REPAIR IAW FEDEX GMM6-2-100.

Part: TEE FITTING — CRACKED (LT WING) · airframe 49,635 hrs · 18,186 cycles

CNTR WING INSP REAR SPAR INTERNAL ANGLE/TEE FITTING FR44 LT SIDE MID HOLE WITH CRACK SIGNAL. COMPLIED WITH EA:6-5710-T0343040 PT1 REPAIRED CENTER WING REAR SPAR RIB1 INTERNAL ANGLE/TEE FITTING AT FR44 LH SIDE MID HOLE(#35A). CATEGORY "B" REPAIR.FIRST INSPECTION IS 6560FC/18380FH WHICHEVER COMES FIRST AFTER REPAIR EMBODIED.INTERNAL INSPECTION IS 6560FC/18380FH WHICHEVER COMES FIRST .INSPECTION METHOD IS ROTATIVE PROBE INSPECTION AS PER NTM51-10-01 AFTER FASTENER AND BUSHES REMOVAL. MAJOR REPAIR IAW FEDEX GMM6-2-100

Part: SUPPORT BEAM — DAMAGED (FUSELAGE) · airframe 49,635 hrs · 18,186 cycles

MDCC FWD UTILITY AREA FR14-FR17, -Y1456 LONGITUDINAL SUPPORT BEAM FOUND 1EA HOLE ENLARGED REFER TO SRM 53-12-15 FIG. 207 REPAIRED THE -Y1456 LONGITUDINAL SUPPORT BEAM AT MDCC FWD UTILITY AREA BETWEEN FR14-FR17. THIS IS CATEGORY "B" REPAIR AND MUST BE INSPECT AT DEFINED INTERVALS PER SRI53-12-15-2-002-00. FIRST INSPECTION AFTER REPAIR EMBODIMENT IS 40000FC, SUBSEQUENT INSPECTION AND INSPECTION METHOD ARE TBD. MAJOR REPAIR IAW GMM6-2-100.

Part: INDICATION SYS — INTERMITTENT (R1 DOOR) · airframe 48,724 hrs · 17,622 cycles

R1 ENTRY DOOR SLIDE ARMED INDICATOR DOES NOT SHOW ARMED ON ECAM. CLEANED CONNECTOR ON 14WN RT DOOR ESCAPE SLIDE ARM SWITCH. CLOSED AND ARMED R1 DOOR SLIDE AND SLIDE ARM INDICATION CHECKS NORMAL ON ECAM IAW ASM 52-73-00. ACFT OK FOR SERVICE.

Part: POWER SUPPLY — INOPERATIVE (R1 DOOR ARMING) · airframe 48,671 hrs · 17,585 cycles

R1 DOOR SLIDE FAIL TO ARM. REMOVED AND REPLACED AUTONOMOUS STANDBY POWER SUPPLY UNIT 70WN AND BATTERY 1 IAW AMM 52-73-18-04, BITE TESTED OK, R1 SLIDE INDICATION CHECKS OK IAW AMM 52-73-00.

Part: LINE — LEAKING (HYD SYSTEM) · airframe 48,530 hrs · 17,511 cycles

LOST ALL GREEN SYSTEM HYD FLUID LEAVING FL 320. USED LANDING GEAR GRAVITY EXTENTION PROCEDURE. HYD SYS CIRCUIT BREAKERS HAVE BEEN COLLARED IN E/E BAY. FOUND A PIN HOLE IN LT GREEN HYD RETURN LINE, REMOVED AND REPLACED THE LINE IAWSMP 20-23-11-00, & 20-23-12-00, LEAK CHECKED GOOD.

Part: FLAP SYSTEM — MALFUNCTIONED (N/A) · airframe 48,313 hrs · 17,337 cycles

FLAPS STUCK AT 0 DURING APPROACH. COMPLIED WITH ECAM & QRH. NO RELIEF IN CYCLE. LANDED SLATS 30 FLAPS 0. TSM 27-50, BOTH SFCC'S INDICATE FLAP JAMB, LEFT FLAP SYSTEM TORQUE LIMITER TRIPPED. SRM 27-50-02 FIG 101 BLOCK 2, ALL SCREW JACK TORQUE LIMITERS INSPECTED, ONLY ONE TORQUE LIMITER IS ACTIVATED ON SCREW JACK 1, TORQUE LIMITER TRIPPED IN RETRACT POSITION. ALL OTHERS OK COMPLIED WITH TSM 27-50-02 BLOCKS 1,2,3,4,5 AND 6, INDICATORS RESET FOR LEFT FLAP SYSTEM TORQUES LIMITER AND LEFT #1 JACK SCREW, VERIFIED NO WATER PRESENT IN GEAR BOX, NO OIL LEAKAGE, RESERVICED OIL IAW AMM AMM 12-13-27-00, ,COMPLIED WITH GREASING OF JACK SCREW AND FLAP TRACK CARRIAGE AND ROLLER INSPECTED AND GREASED IAW AMM 27-22-27-00. INSPECTED FLAP TRACK FAIRINGS IAW AMM 27-50-21,27-50-22 AND 27-50-23, VERIFIED RETRACT CLAW STOP WITHIN LIMITS OF AMM 27-50-00-05, FLAP TRACK TRANSMISSION SHAFT INSPECTED IAW AMM 27-54-19-06.

Part: GCU — MALFUNCTIONED (NR 2) · airframe 47,672 hrs · 16,900 cycles

REJECTED TAKE OFF AT 90 KNOTS, AC BUS 2 OFF, GEN 2 FAULT. PERFORMED BITE CHECK ON GND POWER CONTROL UNIT & FOUND, RT GEN POWER SYS, FAULTED. R & R NR 2 GEN CONTROL UNIT IAW AMM 24-22-12-04. RAN NR 2 ENG IAW JRH WITH NO FAULTS NOTED. ALSO PERFORMED ADJUSTMENT & TEST ON ACFT BUS 2 IAW AMM 24-27-00-05 WITH NO FAULTS FOUND. ACFT OK FOR SERVICE.

Part: SEQUENCE VALVE — FAULTY (RT MLG) · airframe 47,597 hrs · 16,859 cycles

RIGHT MLG DID NOT EXTEND DURING NORMAL EXTENSION. GEAR EXTENDED TO DOWN & LOCKED WITH MANUAL EXTENSION. FREE FALL EXTENSION SYS RETURNED TO NORMAL CONDITION IAW AMM 32-33-00-2. INSPECTED MAIN LG DOOR & WW AREA & NO DEFECT FOUND. JACKED UP ACFT IAW AMM 07-11-00-00. CARRIED OUT LG NORMAL EXTENSION & RETRACTION OPERATIONS TEST IAW AMM32-31-00-05. FOUND RT MLG DOOR OPERATION NORMAL, BUT GEAR DID NOT RETRACT. R & R RT MLG SEQUENCE VLV IAW AMM 32-31-37-04. LEAK CHECKED & FOUND NO HYD LEAKAGE. PERFORMED LG NORMAL EXTENSION & RETRACTION OPERATIONS TEST. ALL INDICATION & OPERATION CHECKED NORMAL IAW AMM 32-31-00-05. LOWERED ACFT IAW AMM 07-11-00-00.

Part: SKIN — DELAMINATED (RUDDER) · airframe 47,583 hrs · 16,854 cycles

RIGHT SIDE RUDDER PANEL, FOUND DELAMINATED AT TE RR 48 - RR 49, APPROX 6" X 6". REMOVE THE OUTER SKIN IN THE DAMAGED AREA IAW SRM 55-41-12 PARA 31. PERFORM A TAP TEST AROUND THE DAMAGE AREA TO MAKE SURE NO DELAMINATION IAW NTM 51-10-19, NO DAMAGE. PERFORM A DVI FOR CORE OF DAMAGE IAW NTM 51-70-00, NO FINDINGS. INSTALLED REPAIR DOUBLER IAW SRM 55-41-12 PARA 31. PERFORM A TAP TEST TO MAKE SURE THE DOUBLER IS OK IAW NTM 51-10-19, NO DELAMINATION. MAJOR REPAIR IAW GMM 6-2-100.

Part: FITTING — CRACKED (FRAME 47) · airframe 47,583 hrs · 16,854 cycles

CENTER WING INSPECTION, REAR SPAR INTERNAL ANGLES & TEE FITTING, HOLE NR 31 WITH CRACK SIGNAL, LT SIDE. REPAIRED IAW EA 6-5710-T0322510. NDT CHECK, NO CRACK FOUND. WET INSTALLED THE BUSHES, WASHER & FASTENER IAW EA 6-5710-T0322510. THIS IS A MAJOR REPAIR IAW GMM 6-2-100.

Part: FITTING — CRACKED (FRAME 47) · airframe 47,583 hrs · 16,854 cycles

CENTER WING INSPECTION, REAR SPAR INTERNAL ANGLES & TEE FITTING, HOLE NR 60 WITH CRACK SIGNAL, RT SIDE. REPAIRED IAW EA 6-5710-T0322510. NDT CHECK, NO CRACK FOUND. WET INSTALLED THE BUSHES, WASHER & FASTENER IAW EA 6-5710-T0322510. THIS IS A MAJOR REPAIR IAW GMM 6-2-100.

Part: FITTING — CRACKED (FRAME 47) · airframe 47,583 hrs · 16,854 cycles

CENTER WING INSPECTION REAR SPAR INTERNAL ANGLES & TEE FITTING, HOLE NR 62 WITH CRACK SIGNAL, RT SIDE. REPAIRED IAW EA 6-5710-T0322510. NDT CHECK, NO CRACK FOUND. WET INSTALLED FASTENER IAW EA 6-5710-T0322510. THIS IS A MAJOR REPAIR IAW GMM 6-2-100.

Part: FITTING — CRACKED (FRAME 47) · airframe 47,583 hrs · 16,854 cycles

CENTER WING INSPECTION, REAR SPAR INTERNAL ANGLES & TEE FITTING, HOLE NR 62 WITH CRACK SIGNAL, LT SIDE. REPAIRED IAW EA6-5710-T0322510. NDT CHECK, NO CRACK FOUND. WET INSTALLED THE FASTENER IAW EA 6-5710-T0322510. THIS IS A MAJOR REPAIR IAW GMM 6-2-100.

Part: FITTING — CRACKED (FRAME 47) · airframe 47,583 hrs · 16,854 cycles

CENTER WING INSPECTION REAR SPAR INTERNAL ANGLES & TEE FITTING, HOLE NR 41 WITH CRACK SIGNAL, LT SIDE. REPAIRED IAW EA 6-5710-T0322510. NDT CHECK, NO CRACK FOUND. WET INSTALLED THE BUSHES, WASHER & FASTENER IAW EA 6-5710-T0322510. THIS IS A MAJOR REPAIR IAW GMM 6-2-100.

Part: FITTING — CRACKED (FRAME 47) · airframe 47,583 hrs · 16,854 cycles

CENTER WING INSPECTION, REAR SPAR INTERNAL ANGLES & TEE FITTING, HOLE NR 60 WITH CRACK SIGNAL, LT SIDE. REPAIRED IAW EA 6-5710-T0322510. NDT CHECK, NO CRACK FOUND. WET INSTALLED THE BUSHES, WASHER & FASTENER IAW EA 6-5710-T0322510. THIS IS A MAJOR REPAIR IAW GMM 6-2-100.

Part: FITTING — CRACKED (FRAME 47) · airframe 47,583 hrs · 16,854 cycles

CENTER WING INSPECTION REAR SPAR INTERNAL ANGLES & TEE FITTING, HOLE NR 14 WITH CRACK SIGNAL, RT SIDE. REPAIRED IAW EA 6-5710-T0322510. NDT CHECK, NO CRACK FOUND. WET INSTALLED THE FASTENER IAW EA 6-5710-T0322510. THIS IS A MAJOR REPAIR IAW GMM 6-2-100.

Part: FITTING — CRACKED (FRAME 47) · airframe 47,583 hrs · 16,854 cycles

CENTER WING INSPECTION REAR SPAR INTERNAL ANGLES & TEE FITTING, HOLE NR 61 WITH CRACK SIGNAL, RT SIDE. REPAIRED THE CRACKED HOLE IAW EA6-5710-T0322510. NDT CHECK, NO CRACK FOUND. WET INSTALLED THE BUSHES, WASHER & FASTENER IAW EA 6-5710-T0322510. THIS IS A MAJOR REPAIR IAW GMM6-2-100.

Part: FITTING — CRACKED (FRAME 47) · airframe 47,583 hrs · 16,854 cycles

CENTER WING INSPECTION REAR SPAR INTERNAL ANGLES & TEE FITTING, HOLE NR 46 WITH CRACK SIGNAL, LT SIDE. REPAIRED IAW EA 6-5710-T0322510. NDT CHECK, NO CRACK FOUND. WET INSTALLED THE BUSHES, WASHER & FASTENER IAW EA 6-5710-T0322510. THIS IS A MAJOR REPAIR IAW GMM 6-2-100.

Part: STRINGER — CORRODED (FRAMES 64-65) · airframe 47,583 hrs · 16,854 cycles

AFT CARGO BAY, STRINGER 55R, FOUND CORRODED BETWEEN FRAMES 64 - 65. REPAIRED THE STRINGER IAW SRM 53-10-14-201 FIG 201 VIEW F & G. MAJOR REPAIR IAW GMM 6-2-100.

Part: STRINGER — CORRODED (FRAMES 59-63) · airframe 47,583 hrs · 16,854 cycles

AFT CARGO BAY STRINGER 54R, FOUND CORRODED BETWEEN FRAMES 59 - 63. REPAIR THE STRINGER IAW SRM 53-10-14-201 FIG 201 VIEW F & G. MAJOR REPAIR IAW GMM 6-2-100.

Part: STRINGER — CORRODED (FRAME 38) · airframe 47,583 hrs · 16,854 cycles

FORWARD CARGO COMPARTMENT STRINGER 44R CORRODED BETWEEN FRAMES 38 - 38.1. REPAIRED THE STRINGER IAW SRM 53-10-14-201 FIG 201. MAJOR REPAIR IAW GMM 6-2-100.

Part: STRINGER SPLICE — CORRODED (FRAME 65) · airframe 47,583 hrs · 16,854 cycles

AFT CARGO BAY STRINGER 54L, STRINGER SPLICE FITTING FOUND CORRODED AT FRAME 65. REPLACED THE SPLICE FITTING IAW SRM 51-40-21. THIS IS A MAJOR REPAIR IAW GMM 6-2-100.

Part: BEAM — CORRODED (FUEL TANK) · airframe 47,583 hrs · 16,854 cycles

CENTER WING FUEL TANK, BOTTOM SKIN LONGITUDINAL BEAM 4RT OTBD ATTACHED SPLICE FITTING, CORRODED AT FRAME 40. BLENDED OUT & SMOOTHED THE CORRODED AREA IAW SRM 51-74-10. THE DAMAGE WAS OUT OF THE DESIGN THICKNESS TOLERANCE IAW DWG A57112070. REPLACED IAW SRM 51-40-21. THIS IS A MAJOR REPAIR IAW GMM 6-2-100.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 47,583 hrs · 16,854 cycles

EXISTING REPAIR ON FUSELAGE STRINGER 55 LT SIDE, BETWEEN FRAME 59 & 61 REQUIRES EVALUATION FOR CONFORMITY. THE EXISTING REPAIR WAS EVALUATED & CORROSION WAS FOUND AT THE REPAIR AREA. THE EXISTING SPLICE REPAIR WAS REMOVED & PERFORMED AGAIN IAW SRM 53-10-14 FIG 201. EO6-5100-7-5000 D1P 1. THE REPAIR WAS CATEGORY B & CLASSIFIED AS MAJOR IAW GMM 6-2-100 REV 130. IT SHOULD BE INSPECTED IAW SRI 53-10-14-2-009-00. THE FIRST INSPECTION IS 40000FC & 116000FH AFTER REPAIR EMBODIMENT. THE INTERVALS & METHOD ARE TBD.

Part: DOOR — DEPARTED · airframe 475 hrs · 16,851 cycles

ON DEPARTURE, MAIN WW FWD LEFT & CENTER DOORS DEPARTED ACFT.

Part: PROXIMITY SENSOR — FAILED (MLG) · airframe 472 hrs · 16,562 cycles

LANDING GEAR WOULD NOT RETRACT USING SYSTEM 1. REMOVED AND REPLACED THE LEFT MAIN GEAR TORQUE LINK PROXIMITY DETECTOR IAW AMM 32-00-00-04.

Part: SENSOR — FAILED (MLG) · airframe 470 hrs · 16,464 cycles

MLG WOULD NOT COME UP DURING DEPARTURE IN SYS 1 & SWITCHED TO SYS 2 & STILL WOULD NOT COME UP. ALSO HAD ADC 1 FAULT, PITCH TRIM NR 1 FAULT, CAPTAIN PROBABLY HEAT, MULTIPLE TIMES. THE JET THOUGHT IT WAS STILL ON THE GND. ALSO CABIN PRESSURE NR 1 FAULT. ALSO THE AIRSPEED HOOK WAS DRASTICALLY DIFFERENT FROM CAPTAIN TO FIRST OFFICER. THE 1ST OFFICER HOOK WAS PROBABLY MORE ACCURATE. ON BLOCK IN, INSPECTED BOTH PITCH DAMPENERS, NEITHER INDICATOR POPPED & NONE OF THE GEAR PINS INSTALLED. LT MLG SENSOR 65GB. FOUND CONNECTOR LOOSE ON 65GB HARNESS. R & R LT MLG SENSOR 65GB. OPS & BITE CHECKED NORMAL. MLG RETRACTION & EXTENSION CHECK & TEST OF SYS 1 & SYS 2. LG INDICATING & WARNING TEST, NO DEFECTS NOTED.

Part: SUPPORT — CORRODED (RT WING) · corrosion level 2 · airframe 46,350 hrs · 15,971 cycles

RIGHT MLG RIB 5 FWD LUG HAS CORROSION IN BORE & FWD FACE. COMPLIED WITH EA 6-5710-T0308476 P2 WINGS BASIC WING STRUCTURE LT & RT RIB 5 FWD LUG CORROSION, RT RIB 5.

Part: SUPPORT — CORRODED (LT WING) · corrosion level 2 · airframe 46,350 hrs · 15,971 cycles

LEFT MLG RIB 5 FWD LUG HAS CORROSION IN BORE & FWD FACE. COMPLIED WITH EA 6-5710-T0308476 P1 WINGS BASIC WING STRUCTURE LT & RT RIB 5 FWD LUG CORROSION, LT RIB 5.

Part: SKIN — CORRODED (ZONE 500) · corrosion level 2 · airframe 45,871 hrs · 15,684 cycles

LEFT WING UPPER SKIN INBD JET FUEL GROUND CONNECTOR POINT AROUND AREA HAS SLIGHT CORROSION AT STR 7 AND STR 8 POSITION. REPAIRED IAW EA 6-5720-T0303769. REPAIR WAS CLASSIFIED AS MINOR IAW GMM 6-2-100.

Part: BEAM — CRACKED (ZONE 200) · airframe 45,871 hrs · 15,684 cycles

ONE CRACK WAS FOUND ON THE NR 33 FASTENER OF THE INNER LONGERON BEAM FLANGE AT STRINGER 11 BETWEEN FRAMES 73A AND 75A (LT SIDE). CRACK LENGTH IS 1INCH IAW E6-5310-7-3314, PT3. DRILLED OUT AFFECTED FASTENER AND CUT OUT DAMAGE PORTION OF BEAM FLANGE. NDI WAS COMPLETED. NO CRACK FOUND IAW NTM 51-10-01 AND 51-10-08. MANUFACTURE REPAIR AND FILLER. INSTALLED REPAIR IAW SRM 53-18-18 FIG 205B. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: LIMITER — TRIPPED (TE FLAPS) · airframe 45,857 hrs · 15,681 cycles

DURING FINAL, TRIED LOWERING FLAPS AND RECEIVED A FLAPS 1/2 SYS FAULT. CYCLED HANDLE NO FLAPS EXTENDED. FOUND WHEEL WELL TORQUE LIMITER FOR RT WING FLAP DRIVE TRIPPED. RESET LIMITER. INSPECTED RT WING FLAP TRANSMISSION TORQUE LIMITERS NOT TRIPPED. NR 1 SFCC DID DETECT A JAM, RESET BOX. SERVICED FLAP JACKSCREW BALLNUTS IAW AMM 12-22-27-00. PREFORMED OPS TEST OF FLAP SYSTEM WITH ELECTRIC HYD PUMPS AND ENGINE DRIVEN HYDRAULIC PUMPS IAW AMM 27-50-0-05. OPS TESTED SERVICEABLE WITH NO FAULTS.

Part: BATTERY — INOPERATIVE (EMERGENCY LIGHTS) · airframe 43,399 hrs · 14,270 cycles

COURIER COMPARTMENT EMERGENCY LIGHT TEST INOP. R & R 29WL1 POWER SUPPLY BATTERY IAW MM 33-55-00-05, NO HELP, REINSTALLED ORIGINAL BATTERY, SUSPECT POWER SUPPLY UNIT 29WL1 BAD. R & R PWR SUPPLY MM 33-55-00-05. NO HELP, SUSPECT BATTERY. PREMATURE REMOVAL/INSTALLATION. BATTERY AND POWER SUPPLY PREVIOUSLY CHANGED. PERFORMED BITE TEST ON POWER SUPPLY AND NO FAULTS NOTED. PERFORMED EMERGENCY LIGHTS TEST IAW AMM 33-51-00-05-0. OPS CHECKS NORMAL. REPLACED 29WL1 POWER SUPPLY BATTERY.

Part: SKIN — DELAMINATED (RUDDER) · airframe 43,363 hrs · 14,256 cycles

THERMOGRAPHY AND ULTRASONIC INSP CARRIED OUT FOUND TRAPPED WATER ON RT RUDDER SKIN AT T/E BELOW NR 37 SCREW LINE AREAS APPROX 600 SQ MM. ACCOMPLISHED EA 6-5540-150322.

Part: STRINGER — CORRODED (ZONE 100) · airframe 43,363 hrs · 14,256 cycles

FUSELAGE AFT PRESSURE BULKHEAD FORWARD FACE AT RIGHT HAND STGR28 FOUND STRINGER END TOP SURFACE WITH CORROSION FUSELAGE AFT PRESSURE BULKHEAD FORWARD FACE AT RIGH HAND STGR28 CORRODED STRINGER END REMOVED AND REPLACED GER SRM 51-40-21 AND 51-72-10 REV 79. REPAIR CLASSIFIED AS MAJOR PER FEDEX GMM 6-2-100 REV 112.

Part: STRINGER — CORRODED · airframe 43,363 hrs · 14,256 cycles

FUSELAGE AFT PRESSURE BULKHEAD FORWARD FACE AT RIGHT HAND STGR 31 FOUND STRINGER END TOP SURFACE WITH CORROSION FUSELAGE AFT PRESSURE BULKHEAD FORWARD FACE AT RIGHT HAND STGR 31 STRINGER END CORRODED PART REMOVED AND REPALCED PER A310-300 SRM 51-40-21 AND SRM 51-72- 10 REV 79. REPAIR CLASSIFIED AS MAJOR PER FEDEX GMM 6-2-100 REV 112

Part: WARNING MESSAGE — FALSE INDICATION · airframe 42,830 hrs · 13,895 cycles

ON TAKEOFF ROLL APPROX 80 KTS GOT ECAM WARNING FOR PITCH FEEL SYS 1 AND 2 AND RUDDER TRAVEL SYS 1 AND 2 FAULTS. ALL 4 LIGHTS WERE ILLUMINATED ON OVHD PANEL. ABORTED TAKEOFF, COMPLETED APPROPRIATE CHECKLISTS AND RETURNED TO BLOCKS. ACCOMPLISHED AFS/LAND TEST. NO FAULTS NOTED. ALL TESTS PASS. (CLOSED)

Part: PICKUP — MALFUNCTIONED (TE FLAPS) · airframe 42,801 hrs · 13,866 cycles

ON FINAL APPROACH, WHEN FLAPS WERE SELECTED TO 40 DEG RECEIVED ECAM. FLAPS STUCK. ALSO RECEIVED SYS 1 AND 2 FAULT LIGHT ON OVERHEAD PANEL. FLAPS STUCK BETWEEN 20 DEG -40 DEG. COMPLIED WITH QRH AND ECAM. REPLACED LT APPU 29CV PER AMM 27-56-11-04. PERFORMED OPERATIONAL TEST PER AMM 27-54-00-05 FOUR TIMES ALL GOOD. AFTERWARDS CHECKED BOTH SFCC'S FOR FAULTS NONE FOUND. DID BITE TEST ON BOTH SFCC'S BOTH GOOD.

Part: JACKSCREW — DAMAGED (TE FLAPS) · airframe 42,783 hrs · 13,848 cycles

ON FINAL SLATS/FLAPS STUCK 20/17: RECYCLED AND SLAT/FLAP STUCK LIGHT EXTINGUISHED. SELECTED SLAT/FLAP 20/20 TO LAND AND LIGHT REILLUMINATED, THE SECOND TIME. RAN QRH AND LANDED AT SLAT/FLAPS 20/17. ALL HYD'S WERE GOOD. REPLACED NR 3 FLAP JACKSCREW IAW AMM 27-54-23-04. OPS AND LEAK CHECK GOOD.

Part: FRAME — CORRODED (ZONE 200) · corrosion level 2 · airframe 41,219 hrs · 12,840 cycles

EMPENNAGE FRAME 84 AT STRINGER 13 L, THE FRAME LOWER CHORD IS CORRODED AT AND UNDER THE CROSSBEAM. REMOVED CORROSION FROM THE FRAME FLANGE IAW SRM 51-74-10. FOUND TO BE OUT OF LIMITS IAW SRM 53-10-00, FIG 105 AND TABLE 102. REMOVED THE FLANGE IAW SRM 51-40-21. FABRICATED A NEW FLANGE CHORD IAW AIRBUS DWG A53988401. ALODINED IAW SRM 51-21-10. PRIMED AND IAW SRM 51-23-10. INSTALLED FLANGE IAW SRM 51-40-21.

Part: FLOOR PANEL — CRACKED (FUSELAGE) · airframe 41,219 hrs · 12,840 cycles

FLOOR PANEL 232 LG IS CRACKED. FABBED NEW FLOOR PANEL 231 LG USING THE OLD PANEL AS A TEMPLATE. POTED & CURED INSERTS; POTTED; CURED & SANDED THE EDGES. APPLIED NON-SKID TAPE & PART MARKED PANEL IAW FEDEX DWG SRX 25-005; REV "G".

Part: FLOOR PANEL — CRACKED (FUSELAGE) · airframe 41,219 hrs · 12,840 cycles

FLOOR PANEL 232 TG IS CRACKED. FABBED NEW FLOOR PANEL 232 TG USING THE OLD PANEL AS A TEMPLATE. POTED & CURED INSERTS; POTTED; CURED & SANDED THE EDGES. APPLIED NON-SKID TAPE & PART MARKED PANEL IAW FEDEX DWG SRX 25-005; REV "G".

Part: FLOOR PANEL — DELAMINATED (ZONE 100) · airframe 41,219 hrs · 12,840 cycles

FWD CARGO PIT FLOOR PANEL NR 131QF IS DAMAGED FABRICATED NEW PANEL FWD CARGO PIT FLOOR PNL 131QF PER DWG SRZ 25-005 REV G AND AMM 20-31-00-0 PG 58.

Part: FITTING — CRACKED (CARGO DOOR) · airframe 41,219 hrs · 12,840 cycles

BULK CARGO DOOR FITTING UNDERNEATH SPRING MECHANISM IS CRACKED. REMOVED CRACKED FITTING IAW A310-300 SRM 51-72-10. LOCATED; DRILL & INSTALLED NEW FITTING P/N A5237807900000 IAW A310-300 SRM 51-72-10.

Part: FLOOR PANEL — DAMAGED (CARGO BAY) · airframe 41,219 hrs · 12,840 cycles

BULK CARGO PIT FLOOR PANEL NR 161 GF IS DAMAGED. FABRICATED NEW PANEL IAW DWG. SRZ 25-005. FABBED TOP SHEET IAW SRZ DWG. 25-005. ATTACHED TOP SHEET IAW DWG SRZ 25-005. PART MARKED IAW GMM 7-0-1000.

Part: FITTING — CRACKED (HORIZONTAL STAB) · airframe 41,219 hrs · 12,840 cycles

RIGHT HORIZONTAL STABILIZER, OTBD FWD HOIST POINT IS CRACKED. REMOVED OUTBD FWD HOIST POINT FITTING IAW SRM 51-40-21. INSTALLED REPAIR PLUG IAW EO 6-5510-7-5001. INSTALLED FITTING IAW SRM 51-40-21. SEALED FITTING FASTENERS IAW SRM 51-74-00. INSTALLED COVER PLUG IAW EO 6-5510-7-5001.

Part: FAILSAFE — CORRODED (PAX DOOR) · corrosion level 2 · airframe 41,219 hrs · 12,840 cycles

RIGHT AFT PAX DOOR FAIL/SAFE RING LOWER SECTION HAS CORROSION ON THE SKIN AROUND THE FASTENER HEADS. REMOVED LIGHT SURFACE CORROSION AS REQUIRED ON R/H AFT ENTRY DOOR FRAME, FAILSAFE RING IAW SRM 53-18-12 FIG. 102 & 5140-47. ALODINE & PRIME APPLICATION REFER TO W/C 41X5067ALI J.P.F. STEP 7 - 10.

Part: FITTING — CRACKED (ZONE 300) · airframe 41,219 hrs · 12,840 cycles

LEFT HORIZONTAL ACCESS 333 BB REAR HOIST POINT FITTING IS CRACKED. REMOVED INBD REAR HOIST POINT FITTING IAW SRM 51-40-21. INSTALLED REPAIR PLUG IAW EO 6-5510-7-5001. INSTALLED FITTING IAW SRM 51-40-21. SEALED FITTING FASTENERS IAW SRM 51-74-00. INSTALLED COVER PLUG IAW EO 6-5510-7-5001.

Part: FITTING — CRACKED (HORIZONTAL STAB) · airframe 41,219 hrs · 12,840 cycles

RIGHT HORIZONTAL STAB, OTBD AFT HOIST POINT IS CRACKED. REMOVED INBD REAR HOIST POINT FITTING IAW SRM 51-40-21. INSTALLED REPAIR PLUG IAW EO 6-5510-7-5001. INSTALLED FITTING IAW SRM 51-40-21. SEALED FITTING FASTENERS IAW SRM 51-74-00. INSTALLED COVER PLUG IAW EO 6-5510-7-5001. INSTALLED FITTING IAW SRM 51-40-21. SEALED FITTING FASTENERS IAW SRM 51-74-00. INSTALLED COVER PLUG IAW EO 6-5510-7-5001; PARA 12. 2-B.

Part: FAILSAFE — CORRODED (PAX DOOR) · corrosion level 2 · airframe 41,219 hrs · 12,840 cycles

LEFT AFT PASSENGER DOOR EXTERNAL SKIN IN THE SCUFF PLATE AREA AND FAIL/SAFE RING HAS SEVERAL AREAS OF CORROSION. REMOVED LIGHT SURFACE CORROSION AS REQUIRED FROM SCUFF PLATE AREA & FAILSAFE RING IAW SRM 51-74-10. ALODINE AND PRIME ACCOMPLISHED ON W/C 41X5067ALI.

Part: FLOOR PANEL — CRACKED (ZONE 200) · airframe 41,219 hrs · 12,840 cycles

FLOOR PANEL 241 UJ IS CRACKED. FABRICATED NEW PANEL FROM STOCK MATERIAL, INSTALLED INSERTS, POTTED EDGES, APPLIED NONSKID, PART ID MARKED IAW SRZ 25-005 REV G.

Part: FLOOR PANEL — DAMAGED (ZONE 200) · airframe 41,219 hrs · 12,840 cycles

FLOOR PANEL 241 AJ IS CRACKED. FABRICATED NEW PANEL FROM STOCK MATERIAL, INSTALLED INSERTS, POTTED EDGES, APPLIED NONSKID, PART ID MARKED IAW SRZ 25-005 REV G.

Part: SKIN — CRACKED (NR 2 NACELLE) · airframe 41,219 hrs · 12,840 cycles

NR 2 PYLON LOWER SPAR, LOWER SIDE; 12 INCHES FWD OF THE AFT ATTACH BEAM, SKIN IS CRACKED. COMPLIED WITH EA E 6-5410-7-3000 A5 PTPT 4.

Part: FLOOR PANEL — CRACKED (ZONE 200) · airframe 41,219 hrs · 12,840 cycles

FLOOR PANEL 231 NH IS CRACKED. FABRICATED NEW PANEL FROM STOCK MATERIAL, INSTALLED INSERTS, POTTED EDGES, APPLIED NONSKID, PART ID MARKED IAW SRZ 25-005 REV G.

Part: FLOOR PANEL — CRACKED (ZONE 200) · airframe 41,219 hrs · 12,840 cycles

FLOOR PANEL 231 QH IS CRACKED. FABRICATED NEW PANEL FROM STOCK MATERIAL, INSTALLED INSERTS, POTTED EDGES, APPLIED NONSKID, PART ID MARKED, IAW SRZ 25-005 REV G.

Part: FLOOR PANEL — CRACKED (ZONE 200) · airframe 41,219 hrs · 12,840 cycles

FLOOR PANEL 241 QJ IS CRACKED. FABRICATED NEW PANEL FROM STOCK MATERIAL, INSTALLED INSERTS, POTTED EDGES, APPLIED NONSKID, PART ID MARKED IAW SRZ 25-005 REV G.

Part: FLOOR PANEL — CRACKED (ZONE 200) · airframe 41,219 hrs · 12,840 cycles

FLOOR PANEL 241 NK IS CRACKED. FABRCATED NEW PANEL FROM STOCK MATERIAL, INSTALLED INSERTS, POTTED EDGES, APPLIED NONSKID, PART ID MARKED IAW SRZ25-005 REV G.

Part: FLOOR PANEL — DAMAGED (ZONE 200) · airframe 41,219 hrs · 12,840 cycles

MAIN DECK FLOOR PANEL AT FRAME 55, LBL 36 IS BROKEN. FABRICATED NEW PANEL FROM STOCK MATERIAL, INSTALLED INSERTS, POTTED EDGES, APPLIED NONSKID, PART ID MARKED IAW SRZ 25-005 REV G.

Part: FLOOR PANEL — CRACKED (ZONE 200) · airframe 41,219 hrs · 12,840 cycles

FLOOR PANEL 252 YG IS CRACKED. FABRICATED NEW PANEL FROM STOCK MATERIAL, INSTALLED INSERTS, POTTED EDGES, APPLIED NONSKID, PART ID MARKED IAW FEDEX DWG SRZ 25-00-05 REV G.

Part: FLOOR PANEL — CRACKED (ZONE 200) · airframe 41,219 hrs · 12,840 cycles

FLOOR PANEL 241 LK IS CRACKED. FABRICATED NEW PANEL FROM STOCK MATERIAL, INSTALLED INSERTS, POTTED EDGES, APPLIED NONSKID, PART ID MARKED IAW SRZ 25-005 REV G.

Part: FLOOR PANEL — DAMAGED (ZONE 200) · airframe 41,219 hrs · 12,840 cycles

MAIN DECK FLOOR PANEL AT FRAME 75 TO FRAME 77, LBL 76 TO LBL 64 IS BROKEN. FABRICATED NEW PANEL FROM STOCK MATERIAL, INSTALLED INSERTS, POTTED EDGES, APPLIED NONSKID, PART ID MARKED IAW SRZ 25-005 REV G.

Part: FLOOR PANEL — CRACKED (ZONE 200) · airframe 41,219 hrs · 12,840 cycles

FLOOR PANEL 241 WH IS CRACKED. FABRICATED NEW PANEL FROM STOCK MATERIAL, INSTALLED INSERTS, POTTED EDGES, APPLIED NONSKID, PART ID MARKED, IAW SRZ25-005 REV G.

Part: STRAP — BROKEN (ESCAPE ROPE) · airframe 41,219 hrs · 12,840 cycles

F/O'S FWD EMERGENCY ESCAPE ROPE TAMPER RESISTANT STRAPS, UPPER AND LOWER ARE BROKEN. REMOVED & REPLACED F/O'S FWD EMERGENCY DESCENT DEVICE PER AMM 25-61-13-4.

Part: SKIN PANEL — DENTED (ZONE 100) · airframe 39,728 hrs · 11,946 cycles

DENT ON SKIN BETWEEN C74-75, P46-47 LT HFEC INSPECTION PERFORMED, ROTOTEST PERFORMED AROUND 6 FASTENER HOLES IN THIS AREA, NO FURTHER DAMAGES FOUND. DENT STAY AS IT IS IAW EA 6-5318-101329 AND RAS/DATLS/0003251/2006 ISS. A

Part: SKIN — DAMAGED (ZONE 200) · airframe 39,728 hrs · 11,946 cycles

TOOLING MARK AT C 33, P22-23 RT REPAIR PERFORMED BY REMOVAL OF TOOLING MARK IAW EA 6-5314-101248 AND RAS/DABRE/7006470/2006 ISS.A.

Part: PRESSURE PANEL — DENTED (ZONE 200) · airframe 39,728 hrs · 11,946 cycles

DENT ON HORIZONTAL PRESSURIZED FLOOR C39/40 Y=450 AND Y=953 LT REPAIR PERFORMED BY INSTALLING A SHIM AND DOUBLER IAW EA 6-5315-99231 AND RAS 044539/005/2006 .

Part: SKIN — CRACKED (ZONE 100) · airframe 39,728 hrs · 11,946 cycles

INNER SKIN DAMAGE (NOTCH, CRACK -10MM) C26/32 P37 LT REPAIR PERFORMED BY SKIN/STRINGER REPAIR IAW EA 6-5314-101316 AND RAS/DABRE/7006560/2006.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,728 hrs · 11,946 cycles

CORROSION ON STRINGER P30 AND P31, C88-91 STRINGER REPAIR PERFORMED IAW SRM 53-10-14 FIG 201.

Part: SKIN PANEL — CORRODED (ZONE 600) · corrosion level 2 · airframe 39,728 hrs · 11,946 cycles

RT WING TOP SKIN PANEL NR 2, TRAILING EDGE AREA CORRODED, RIB 26-31 REPAIR PERFORMED BY BLEND OUT IAW EA 6-5720-101256 AND RAS/BAE/1002866/2006 ISS. A

Part: FITTING — MISALIGNED (ZONE 100) · airframe 39,605 hrs · 11,869 cycles

DURING MANHOLE FITTING REPLACEMENT AT C23-C24 FOUND TWO PILOT HOLES (P49 RT, P54 LT) NOT IN ACCORDANCE WITH THE OLD HOLES ON EXTERNAL SKINS REPAIR PERFORMED BY BUSHING REPAIR AT P49RH AND P54 LT AND PLUG THE TWO HOLES WITH FASTENER NAS1097AD5 IAW EA 6-5310-99203 AND RAS7006670/2006 ISS A.

Part: STRINGER SPLICE — MISALIGNED (ZONE 100) · airframe 39,604 hrs · 11,868 cycles

DUE TO INSTALLATION OF A STRINGER CONNECTING SECTION FOUND THAT THE NEW SECTION IS NOT POSSIBLE TO INSTALL. REPAIR PERFORMED BY FABRICATION OF A LONGER CONNECTING SECTION PER DWR A539-74482, APPROVED BY EA 6-5317-99210 AND RAS/DAHAM/4030706/2006 ISS A.

Part: STRINGER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 39,603 hrs · 11,867 cycles

CORROSION ON STRINGER P48 AND 55 LT (A539-86217, A539-86218) AT C59-60 AND P56 LT (A539-74267-202) AT C62-64 STRINGER REPAIR PERFORMED IAW SRM 53-10-14 FIG 201/201A.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,604 hrs · 11,868 cycles

FOUND CORROSION AT STRINGER P54, 55, 56 LT, C70-72, STRINGER REPAIR PERFORMED IAW SRM 53-10-14.

Part: FAIRING — CRACKED (ZONE 500) · airframe 39,604 hrs · 11,868 cycles

A 200 MM CRACK IN INNER FACE NEAR PIVOT POINT AT NR 4 LT MOVEABLE FAIRING BONDING REPAIR PERFORMED IAW EA 6-5720-99195 AND RAS/FOK/069/2006 ISS A.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,603 hrs · 11,867 cycles

FOUND CORROSION IN AIR CONDITIONING COMPARTMENT ON KEEL BEAM C45/46, P51 LT, PANEL C40/42, P50- 51 LT, STRINGER P 50 LT, C43-44. REPAIR PERFORMED BY BLEND OUT THE CORROSION ON KEEL BEAM AND PANEL IAW SRM 51-74-10 AND STRINGER REPAIR ON P50, C43-44 IAW TD 044433/004/2006 ISS C, APPROVED BY EA 6-5315-99214 AND RAS 044433/005/2006 ISS A.

Part: FRAME — CORRODED (ZONE 200) · corrosion level 2 · airframe 39,603 hrs · 11,867 cycles

EXFOLIATION CORROSION AT C49, P14-15 LT REPAIR PERFORMED BY BLEND OUT THE CORROSION IAW. SRM 51-74-10 AND FLAP PEENING IAW. SRM 51-29-00, APPROVED BY EA 6-5315-99194 AND RAS/DATLS/0003112/2006 ISS. A

Part: RIB — DAMAGED (ZONE 500) · airframe 39,603 hrs · 11,867 cycles

SLAT NR 2 LT DENT ON LEADING EDGE OVER RIB 52 REPAIR PERFORMED BY CUT OUT AND FLUSH DOUBLER INSTALLATION IAW SRM 57-43-11 FIG 202.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,604 hrs · 11,868 cycles

CORROSION AT STRINGER P48 LT, C71-72 REPAIR PERFORMED BY REPLACEMENT OF PART IAW SRM 51-72-10.

Part: SKIN — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,604 hrs · 11,868 cycles

CORROSION AT CENTER WING BOX TOP SKIN AT TRACK 5-6 LT ON C46.2-47, 5-6 RT ON C47 REPAIR PERFORMED BY BLEND OUT AND OVERSIZING IAW EA 6-5710-99188 AND RAS/43898/038/2006 ISS. A

Part: DOUBLER — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,603 hrs · 11,867 cycles

CORROSION FOUND ON DOUBLER A539-80911-202, C72-73, P41-43LHS REPAIR PERFORMED BY BLEND OUT AND FLAP PEENING IAW SRM 51-29-00, APPROVED BY EA 6-5318-99190 AND RAS/DAHAM/4020661/2006 ISS A.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,604 hrs · 11,868 cycles

CORROSION AT STRINGER P56, C66-70; LT STRINGER REPAIR PERFORMED IAW SRM 53-10-14 FIG 201.

Part: DOOR — CORRODED (ZONE 200) · corrosion level 2 · airframe 39,604 hrs · 11,868 cycles

EMERGENCY EXIT CORROSION AT C42A-43A, P26 LT/RT REPAIR PERFORMED BY BLEND OUT IAW SRM 51-74-00 AND FLAP PEENING IAW SRM 51-29-00, APPROVED BY EA 6-5220-99215 AND RAS/DATLS/0003162/2006 ISS B.

Part: BUSHING — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,604 hrs · 11,868 cycles

CORROSION AT NLG RH ATTACHMENT LUG (BUSHING A536-10580-203) REPAIR PERFORMED BY BUSHING REMOVAL IAW SB A300-53-0130, APPROVED BY EA 6-5312-101314 AND RAS 043643/005/2006 ISS A.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,603 hrs · 11,867 cycles

FOUND CORROSION ON STRINGER P44 RT, C54-54.2 STRINGER REPAIR PERFORMED IAW SRM 53-10-14 FIG 201.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,604 hrs · 11,868 cycles

FOUND CORROSION AT STRINGER P45 LT, C71-72 REPAIR PERFORMED BY REPLACEMENT OF PART IAW SRM 51-72-10.

Part: SKIN — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,603 hrs · 11,867 cycles

CORROSION ON CENTER WING BOX TOP SKIN TRACK 4-5 LT, C 42-47; TRACK 3-4 LT, C46.1-47; TRACK 2-3 RT, C47; TRACK 4-5, C47; TRACK 4 RT, C40 REPAIR PERFORMED BY BLEND OUT CORROSION AND INSTALLING OVERSIZE FASTENER IN ALL AREA AND IN ADDITION INSTALLING A REPAIR DOUBLER BETWEEN TRACK 4-5, C44.1-45 AND 42.2-43.2, APPROVED BY EA 6-5710-99188 AND RAS 043898/038/2006 ISS.A.

Part: CHANNEL — DENTED (ZONE 800) · airframe 39,604 hrs · 11,868 cycles

AFT PAX DOOR LOWER DOOR CHANNEL DAMAGED (DEFORMATION) REPAIR PERFORMED BY REPLACEMENT OF PARTS (LOWER CHANNEL P/N A521-75271-202, SEGMENT P/N A521-75325-332).

Part: FITTING — DAMAGED (ZONE 100) · airframe 39,603 hrs · 11,867 cycles

FOUND OLD MISDRILLED HOLES HOLES ON CORNER FITTING C 23, 24, 25 LT. REPAIR PERFORMED BY REPLACEMENT OF PART A537-73644-204 (2) AND A537-73644-208 IAW SRM 51-72-10.

Part: BEAM — DAMAGED (ZONE 100) · airframe 39,603 hrs · 11,867 cycles

OLD GROOVES ON LONGITUDINAL BEAM C73A-75A, P26 RT REPAIR PERFORMED BY REPLACEMENT OF PART IAW SRM 51-72-10.

Part: STRUCTURE — MISREPAIRED (ZONE 100) · airframe 39,603 hrs · 11,867 cycles

DEVIATIONS DURING EMBODIMENT OF SB A310-57-2047 REV 2, SEVERAL HOLES WERE FOUND WITH DAMAGES: HOLE 63 RT (MISDRILLED PILOT HOLE), HOLE 35A, 42 RT (TOOLING MARK), HOLE 18LH (TOOLING MARK). REPAIR PERFORMED BY REAM UP THE HOLES IAW EA 6-5710-99209 AND RAS/044239/010/2006 ISS. A.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,603 hrs · 11,867 cycles

FOUND CORROSION AT STRINGER P52 LT, C54.3-C55/58 AND P56L, C54.2-55/58 STRINGER REPAIR PERFORMED ON P56 LT, C54.2-55/58 IAW SRM 53-10-14 FIG 201 AND BLEND OUT THE CORROSION AT P53LH, C54.3-55/58 IAW EA 6-5316-99233 AND RAS/DATLS/0003124/2006 ISS. A.

Part: TRACK — DAMAGED (ZONE 600) · airframe 39,592 hrs · 11,860 cycles

SEVERAL DAMAGES (IMPACTS) ON L/E TRACK NR 2 RT. REPAIR PERFORMED BY BLEND OUT IAW SRM 51-74-10 AND INSTALLING AN INFILL-PLATE IAW EA 6-5741-101246 AND RAS/BAE/1002809/2006 ISSUE "A".

Part: BEAM — DENTED (ZONE 800) · airframe 39,592 hrs · 11,860 cycles

FOUND DENT 40 BY 35 BY 1MM AT FWD CARGO COMPARTMENT DOOR, BEAM C22-C22A. REPAIR PERFORMED BY REPLACEMENT OF PART IAW SRM 52-32-00/PB 200.

Part: FRAME — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,591 hrs · 11,859 cycles

CORROSION ON FRAME CONNECTION , C80, P`36 REPAIR PERFORMED BY REPLACEMENT OF CORRODED SECTIONS (A539-87426-212/-211) AND INSTALLING BOLTS NAS 6603-5 INSTEAD OF RIVETS, APPROVED BY EA 6-5319-99170 AND RAS/DAHAM/4020596/2006 ISSUE A.

Part: FLAP — DENTED (ZONE 600) · airframe 39,592 hrs · 11,860 cycles

SEVERAL DAMAGES (DENTS, CORRODED CORE) ON RT INBOARD FLAP AT LOWER AND UPPER SURFACE BETWEEN RIB2-9. REPAIR PERFORMED IAW SRM 57-53-12/FIG 208/209, APPROVED BY EA 6-5753-99189 AND RAS/DABRE/7006468/2006 ISSUE "B".

Part: ACCESS PANEL — MISREPAIRED (ZONE 100) · airframe 39,592 hrs · 11,860 cycles

FOUND FOUR NON RECORDED POCKET REPAIRS ON MANHOLE FITTING C23-C24. REPAIR PERFORMED BY REPLACEMENT OF MANHOLE FITTING IAW DRW: R537-06163 ISSUE "B", APPROVED BY EA 6-5310-99203 AND RAS/DABRE/7006670/2006 ISSUE "A".

Part: FRAME — MISREPAIRED (ZONE 200) · airframe 39,591 hrs · 11,859 cycles

4 PLUGGED HOLES IN FRAME SEGMENT REPAIR PERFORMED BY REPLACEMENT OF FRAME SEGMENT C71 LT BETWEEN P4-5 AND P18-22 IAW SRM 51-72-10.

Part: KEELBEAM — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,592 hrs · 11,860 cycles

CORROSION IN AIR CONDITIONING COMPARTMENT RT, KEEL BEAM (A538-11587-201, A538-11200-200): P'51, C44-45; P'51, C45-46; STRINGER (A538-11380-201, A538-11597-200): P'48, C40; P'51, C42. REPAIR PERFORMED BY BLEND OUT IAW SRM 51-74-10 AND INSTALLING OVERSIZE FASTENERS IAW SRM 51-40-30, APPROVED BY EA 6-5315-99214 AND RAS 044433/005/2006 ISSUE "A".

Part: SPLICE — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,591 hrs · 11,859 cycles

CORROSION AT SPLICE C19, P46 LT REPAIR PERFORMED BY REPLACEMENT OF PART IAW SRM 51-72-10.

Part: ACCESS PANEL — MISREPAIRED (ZONE 100) · airframe 39,592 hrs · 11,860 cycles

FOUND MORE THAN FOUR OLD NON RECORDED POCKET REPAIRS ON MANHOLE FITTING, C38.1-C38.2. THIS IS NOT ALLOWED IAW SRM 53-14-12 / PG 228. REPAIR PERFORMED BY REPLACEMENT OF MANHOLE FITTING IAW DRW: R537-06164 ISSUE "D", APPROVED BY EA 6-5310-101336 AND RAS/DABRE/7006671/2006 ISSUE "A".

Part: FLOORBEAM — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,591 hrs · 11,859 cycles

TOP CAP BEAM C33 CORRODED SPLICE REPAIR OF TOP CAP BEAM PERFORMED IAW SRM 53-10-15 FIG 207.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,592 hrs · 11,860 cycles

THE FOLLOWING CONNECTING SECTION WERE HEAVY CORRODED: P46, P48, P49, P50, P51, P53, P55, P56 AND P57 AT C65; AND STRINGER P47 AND P48 AT C65-66. REPAIR PERFORMED BY REPLACEMENT OF ALL CONNECTION SECTIONS IAW SRM 51-72-10 (P/N: A539-74232-200, A539-74228-200, A539-74229-200, A539-73303-200, A539-73925-200) AND STRINGER REPAIR IAW SRM 53-10-14/ FIG 201 (A539-86212).

Part: STRUCTURE — DENTED (ZONE 600) · airframe 39,592 hrs · 11,860 cycles

DENT IN FOLDING NOSE, KRUEGER FLAP RT. REPAIR PERFORMED BY FILLING THE DENT IAW SRM 51-73-10, APPROVED BY EA 6-5745-99186 AND RAS/SA/040/2006 ISSUE "A".

Part: PROFILE — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,591 hrs · 11,859 cycles

AT FWD CARGO DOOR CUT OUT, C20A SEALING SECTION CORRODED REPAIR PERFORMED BY REPLACE THE PART IAW SRM 51-72-10.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,592 hrs · 11,860 cycles

FOUND THE FOLLOWING STRINGER CORRODED: P52, C67-70 LT (P/N A539-73320-201); P49, C67-69 LT (P/N A539-74203-216); P48, C67-70 LT (P/N A539-74203-212); P46, C65-68 LT (P/N A539-74203-208) AND P53, C66-68 LT (P/N A539-74203-222). CLIP C67, P56-57 LT (P/N A539-74223-214) IS ALSO CORRODED. STRINGER REPAIR PERFORMED IAW SRM 53-10-14/FIG 201 AND REPLACEMENT OF CLIP (A539-74223-214) IAW SRM 51-72-10.

Part: STRINGER — CORRODED (ZONE 100) · airframe 39,592 hrs · 11,860 cycles

FOUND THE FOLLOWING STRINGER CORRODED: P52, C67-70; P49, C67-69; P48, C67-70; P46, C65-68 AND P53, C66-68. CLIP C67, P56-57 IS ALSO CORRODED. STRINGER REPAIR PERFORMED IAW SRM 53-10-14 / FIG 201 AND REPLACEMENT OF CLIP (A539-74223-214) IAW SRM 51-72-10.

Part: SKIN PANEL — CORRODED (ZONE 300) · corrosion level 2 · airframe 39,580 hrs · 11,854 cycles

CORROSION AT SKIN PANEL (A539-89559-386) AT C92 AND SEVERAL PARTS C91/92 BILGE AREA. REPAIR PERFORMED BY REPLACEMENT IAW SRM 51-72-10 OF FOLLOWING PARTS: T-SECTION A539-89317-208 / -209 / -206, SUPPORT SECTION A539-89330-216, PROFILE A539-89317-228, ANGLES A539-89317-229 / -224 / -225 / -222 / -223 / -246, ANGLES A539-89579-200 / -201 / -202 / -203, BUTT STRAP A539-89317-246, STIFFENER A539-89155-214, FLANGE A539-89155-204 / -236, SEALING STRIP A539-87435-200 / -201, WEB PLATE A539-89317-202. REPAIR OF SKIN PANEL PERFORMED BY BLEND OUT AND FLAP PEENING IAW EA 6-5319-99196 AND RAS/DATLS/0003123/2006 ISSUE "B".

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 39,580 hrs · 11,854 cycles

CORROSION FOUND ON STRINGER BETWEEN C70-C71, P49 LT. REPAIR PERFORMED IAW SRM 53-10-14 FIG 201.

Part: SKIN — CHAFED (RT WING) · airframe 39,580 hrs · 11,854 cycles

ELONGATED HOLES ON PYLON SUPPORT BRACKET AND WING BOTTOM SKIN, RIB 8-9 RT. REPAIR PERFORMED BY OVERSIZING AND INSTALLING BUSHES IAW DRW R572-49184, APPROVED BY EA 6-5720-99169 AND RAS/BAE/1002502/2006 ISSUE "A".

Part: STRINGER — DAMAGED (ZONE 100) · airframe 39,580 hrs · 11,854 cycles

FOUND OLD STRINGER REPAIR C60-61, P49, IS NOT PERFORMED IAW SRM. REPAIR RENEWED IAW SRM 53-10-14 FIG 201.

Part: LONGERON — CORRODED (ZONE 200) · corrosion level 2 · airframe 39,580 hrs · 11,854 cycles

HEAVY CORROSION ON LONGERON BETWEEN C11-C15 CABIN FLOOR STRUCTURE. REPAIR PERFORMED IAW SRM53-12-15 / FIG 207.

Part: SKIN — DAMAGED (WING) · airframe 39,569 hrs · 11,848 cycles

ELONGATED HOLES AT PYLON SUPPORT BRACKET AND BOTTOM WING SKIN, LT/RT WING. REPAIR PERFORMED BY OVERSIZING HOLES AND INSTALLING BUSHES IAW EA 6-5720-66169 AND RAS/BAE/1002502/2006.