N811FD

Part: CIRCUIT BREAKER — BURNED (BUSS NR 2) · airframe 54,349 hrs · 17,379 cycles

811 24-50 4376 15DEC18 MEM FACT LOGPAGES:3011783 DURING APPROACH PHASE, RECEIVED "BUS 2 FAIL". COMPLIED WITH QRH. FOUND HEAT DAMAGE ON C/B 2XN. R&R'D C/B 2XN PART NUMBER NSA 931323-501 AMENDMENT A. REF A300 ESPM 20-46-10. NEED ENGINE RUN TO TEST BUS SYSTEM 2. REF AWM 24-51-03 AND 24-58-15.CHECKED LOAD SIDE OF WIRES OF 2XN FOR SHORTS TO GROUND AND SHORTS TO EACH OTHER USING A MEGGER, REF ESPM NO DEFECTS NOTED. TURNED ON ALL USERS OF BUS 202XP TO LOAD IT UP AND C.B 2XN STAYED IN. ENGINE RUN PERFORMED SATISFACTORY.

Part: STIFFENER — CORRODED (FUSELAGE) · airframe 53,210 hrs · 16,767 cycles

LOWER SKIN STIFFENER CORRODED BETWEEN FRAMES 43 & 46, Y1456. COMPLIED WITH EA6-5710-T0335320 P1. MAJOR REPAIR IAW GMM6-2-100.

Part: STIFFENER — CORRODED (FRAMES 43-47) · airframe 53,210 hrs · 16,767 cycles

LOWER SKIN STIFFENER CORRODED,BETWEEN FRAMES 43 AND 47, Y-1456. COMPLIED WITH EA 6-5710-T0335320 P1. MAJOR REPAIR IAW GMM6-2-100.

Part: STRINGER — DAMAGED (FUSELAGE) · airframe 53,210 hrs · 16,767 cycles

AFT CABIN UNDERFLOOR COMPT FR74-FR75, S45R STRINGER 1EA FASTENER HOLE DAMAGED. AFT CABIN UNDERFLOOR COMPT FR74-FR75,S-45R STRINGER 1EA FASTENER HOLE DAMAGED. REPAIRED THE DAMAGED STRINGER PER SRM53-10-14 FIG 201 SHT 2 VIEW H & J.

Part: FRAME ANGLE — CRACKED (FRM 47) · airframe 53,210 hrs · 16,767 cycles

RIGHT REAR FRAME INTERNAL ANGLE NR 23 HOLE, NDT INSPECTION FOUND A CRACK. REPAIRED IAW EA:6-5710-T0335292 P1. MAJOR REPAIR IAW GMM 6-2-100.

Part: SPAR — CRACKED (LT WING) · airframe 53,210 hrs · 16,767 cycles

LEFT REAR SPAR INTERNAL ANGLE NR 1 HOLE FOUND CRACKED DURING AN NDT INSPECTION. REPAIRED IAW EA 6-5710-T0335292 P1. MAJOR REPAIR IAW GMM 6-2-100.

Part: SPAR — CRACKED (RT WING) · airframe 53,210 hrs · 16,767 cycles

RIGHT REAR SPAR INTERNAL ANGLE NR 2 HOLE FOUND CRACKED DURING AN NDT INSPECTION. REPAIRED IAW EA 6-5710-T0335292 P1. MAJOR REPAIR IAW GMM 6-2-100.

Part: SPAR — CRACKED (LT WING) · airframe 53,210 hrs · 16,767 cycles

LEFT REAR SPAR INTERNAL ANGLE NR 60 HOLE FOUND CRACKED DURING AN NDT INSPECTION. REPAIRED IAW EA:6-5710-T0335292 P1. MAJOR REPAIR IAW GMM 6-2-100.

Part: SPAR — CRACKED (LT WING) · airframe 53,210 hrs · 16,767 cycles

LEFT REAR SPAR INTERNAL ANGLE NR 4 HOLE FOUND CRACKED DURING AN NDT INSPECTION. REPAIRED IAW EA 6-5710-T0335292 P1. MAJOR REPAIR IAW GMM 6-2-100.

Part: SPAR — CRACKED (RT WING) · airframe 53,210 hrs · 16,767 cycles

RIGHT REAR SPAR INTERNAL ANGLE, NR 14 HOLE FOUND CRACKED DURING AN NDT INSPECTION. REPAIRED IAW EA:6-5710-T0335292 P1. MAJOR REPAIR IAW GMM 6-2-100.

Part: SPAR — CRACKED (LT WING) · airframe 53,210 hrs · 16,767 cycles

LEFT REAR SPAR INTERNAL ANGLE NR 52 HOLE FOUND CRACKED DURING AN NDT INSPECTION. REPAIRED IAW EA 6-5710-T0335292 P1. MAJOR REPAIR IAW GMM 6-2-100.

Part: SPAR — CRACKED (RT WING) · airframe 53,210 hrs · 16,767 cycles

RIGHT REAR SPAR INTERNAL ANGLE NR 8 HOLE FOUND CRACKED DURING AN NDT INSPECTION. REPAIRED IAW EA:6-5710-T0335292 P1. MAJOR REPAIR IAW GMM 6-2-100.

Part: SPAR — CRACKED (LT WING) · airframe 53,210 hrs · 16,767 cycles

LEFT REAR SPAR INTERNAL ANGLE NR 62 HOLE FOUND CRACKED DURING AN NDT INSPECTION. REPAIRED IAW EA 6-5710-T0335292 P1. MAJOR REPAIR IAW GMM 6-2-100.

Part: SPAR — CRACKED (LT WING) · airframe 53,210 hrs · 16,767 cycles

LEFT REAR SPAR INTERNAL ANGLE NR 10 HOLE FOUND CRACKED DURING AN NDT INSPECTION. REPAIRED IAW EA 6-5710-T0335292 P1. MAJOR REPAIR IAW GMM 6-2-100.

Part: AOA — MALFUNCTIONED · airframe 52,824 hrs · 16,541 cycles

DURING CLIMB THRU FL 340, PROBES & STAT ALPHA CONTROL CIRCUIT BREAKER TRIPPED. MULTIPLE PROBE HT FAILS. FOLLOWED ECAM & QRH PROCEDURES. ATS LEVER TRIPPED OFF IN SEQUENCE WITH THE NR 2 ENGINE LIGHT. R & R RELAY LT 213 IAW WDM 30-31-04. DURING OPS CHECK IAW MM 30-31-00-05, STEP 3, SUB STEP 2, OPENING MLG PROXIMITY DETECTOR & RELAYS SYS 1, FLT-GND CIRCUIT BREAKER, ALL LIGHTS AND ALERTS CAME ON, BUT ALSO RECEIVED A NR 1 AND 2 ENGINE LIGHTS ILLUMINATE ON PITOT HEAT PANEL AND MM DOES NOT CALL FOR THIS LIGHT TO ILLUMINATE. WHEN THE SAME CIRCUIT BREAKER IS PULLED FOR THE NR 2SYS, THE SYSTEM FUNCTIONS AS DESCRIBED IN THE MM. SUSPECT THIS PROBLEM LIES IN THE NR 1 AIR-GND SYSTEM AND IS POSSIBLY A STUCK RELAY THAT HAS NOT BEEN CHANGED YET. REMOVED AND REPLACED PT 2, TT 2 PROBE FOR THE NR 2 ENGINE. OPS CHECKED NORMAL. R & R THE STANDBY ALPHA PROBE (27CC) IAW AMM 22-27-39-4. OPS CHECKED GOOD. OK FOR SERVICE.

Part: SWITCH — MALFUNCTIONED (R1 DOOR SLIDE) · airframe 52,638 hrs · 16,417 cycles

R1 SLIDE INDICATOR WAS BLINKING ON & OFF AT BLOCK IN PRIOR TO DISARMING. R & R THE R1 DOOR LIMIT SWITCH 14WN.

Part: LIMIT SWITCH — FAILED (R1 DOOR) · airframe 52,635 hrs · 16,415 cycles

WHILE TROUBLE SHOOTING R1 DOOR ARMING PROBLEM, SLIDE TRIED TO DEPLOY. REMOVED AND REPLACED RI DOOR LIMIT SWITCH 14WN AND TESTED IAW AMM 52-73-13-04-09.

Part: SLIDE — UNKNOWN (R1 DOOR) · airframe 52,638 hrs · 16,417 cycles

DURING TROUBLESHOOTING OF THE R1 DOOR ARMING PROBLEM, THE SLIDE TRIED TO DEPLOY. COMPLIED WITH R1 SLIDE REMOVAL ONLY IAW EA 6-5210-T0330666 PART 1.

Part: RELAY — FAILED (SLIDE WARNING) · airframe 52,629 hrs · 16,412 cycles

R1 SLIDE INDICATION FLASHES CONTINUOUSLY WHEN SLIDE IS ARMED ON RIGHT ECAM. RELEASED FOR SERVICE PER MEL 52-30-04. REMOVED AND REPLACED RELAYS 9ES AND 10ES REF ESPM 20-46-50. PERFORMED ADJUSTMENT TEST OF ESCAPE SLIDE WARNING REF MM 52-73-00-05. OPS CK OK ON GROUND. OK FOR SERVICE.

Part: LIMIT SWITCH — INOPERATIVE (R1 DOOR) · airframe 52,540 hrs · 16,355 cycles

AFTER PARKING, THE R1 DOOR SLIDE INDICATION WAS FLASHING. R & R THE DOOR LIMIT SWITCH IAW AMM 52-73-13-04-09 OPS CHECKED GOOD IAW 73-13-05-09.

Part: BATTERY PACK — INOPERATIVE (R1 DOOR SLIDE) · airframe 52,517 hrs · 16,343 cycles

DURING LANDING, SLIDE INDICATION ON ECAM FOR R1 WAS FLASHING. REMOVED AND REPLACED ASPU BATTERY NR 1 IAW AMM 52-73-18-04, ASPU BITE CHECKED GOOD. SLIDE INDICATION TEST CHECKED GOOD SEVERAL TIMES IAW AMM 52-73-00-5. ACFT OK FOR SERVICE.

Part: BOTTLE — LOW PRESSURE (R1 DOOR) · airframe 52,506 hrs · 16,335 cycles

R1 DOOR SLIDE ARMED INDICATION FLASHING WHILE TAXING IN AFTER LANDING. RT DOOR DAMPER AND EMERGENCY OPERATING CYLINDER PRESSURE FOUND TO BE LOW. SERVICED CYLINDER IAW AMM 52-10-14-03-09. ARMED R1 DOOR, RECEIVED SLIDE INDICATION ON ECAM. CYCLED R1 DOOR ARMED LEVER. OPS CHECK GOOD. ACFT OK FOR SERVICE.

Part: RELAY — FAILED · airframe 52,429 hrs · 16,293 cycles

AT FL 370 , THE NR 2 LEFT INNER PUMP FAULTED. PUMP FAULTED AND STRONG ACRED ODOR IN THE COCKPIT AND THE AVIONICS COMPARTMENT, ON DESCENT THE REMAINING THREE INNER PUMPS FAULTED AND FUEL FEED RESORTED TO OUTER TANK TO ENGINE. ACCESSED THROUGH THE COCKPIT FLOOR. NO SMOKE WAS PRESENT IN THE COCKPIT OR THE AVIONICS COMPARTMENT. REMOVED AND REPLACED LEFT INNER TANK PUMP 2 POWER SUPPLY RELAY 35QA IAW ESPM 20-46-50. PERFORMED AN OPS TEST IAW AMM 28-21-00-05, CHECKED OK. AIRCRAFT OK FOR SERVICE

Part: SELECTOR VALVE — MALFUNCTIONED (ZONE 700) · airframe 51,424 hrs · 15,758 cycles

AFTER TAKEOFF, LG RETRACTION FAULT SYS NR 1, GEAR REMAINED DOWN. RETURNED FOR LAND. CANNOT OPEN THE LT LG DOOR ON GND. RT LG DOOR OPENED OK ON GND. R&R LG NORMAL CONTROL MICROSWITCH UNIT 2GA PER AMM 32-31-11-04. R&R LANDING GEAR SELECTOR VALVE 3GA PER AMM 32-31-12-04. PERFORMED LG ELECTROVALVE 3GA INSPECTION/CHECK WITH THE SIMULATOR TEST SET PER AMM 32-31-12-06 FOUND SATIS. ALL LG DOORS OPENED AND CLOSED CORRECTLY, NO LEAK. PERFORMED LG WARNING TEST & ANNUCIATOR LIGHT TEST PER AMM 32-61-00-05 FOUND SATIS. ITEM CLOSED. A/C OK SERVICE.

Part: HYDRAULIC LINE — LEAKING (ZONE 700) · airframe 507 hrs · 15,460 cycles

EN-ROUTE, GREEN HYD LEVEL DECREASING SLOWLY. DESCENDING THRU FL 150, ECAM WARNING, HYD LEVEL LO, RAN QRH. LEAK FOUND AT LT MAIN GEAR FLEX HOSE PN 00624AE711082-4 FOR STRUT BRACE ACTUATOR. REPLACED WITH ALTN FROM HYD SPARE KIT PN 24060610-0240. PERFORMED PRESSURIZED LEAK CHECK, NO LEAK FOUND.

Part: SKIN — CRACKED (WING ROOT) · airframe 506 hrs · 15,389 cycles

RIGHT WING ROOT REAR SPAR BOTTOM SKIN FOUND ONE EACH FASTENER HEAD POPPED OUT. REMOVED THE HEAD POPPED OUT FASTENER IAW SRM 51-40-21. CARRIED OUT ROTOTEST INSPECTION TO FASTENER HOLE IAW NTM 51-10-18, FOUND CRACK. REAMED THE HOLE TO REMOVE CRACK IAW SRM 51-40-44. FURTHER OVERSIZED THE DISCREPANT HOLE BY REAMING ALL LAYERS TO 15.836-15.876MM. WET INSTALLED WITH FASTENER NSA 5350-10 IAW EA 6-5710-T0317253. MAJOR REPAIR IAW GMM 6-2-100.

Part: RIB — CRACKED (RT WING) · airframe 506 hrs · 15,389 cycles

RIGHT WING TIP FENCE FAIRING AROUND FASTENER HOLES CRACKED AT WY501. REPLACED IAW SRM 51-40-21.

Part: FRAME — CORRODED (FRAME 17) · airframe 506 hrs · 15,389 cycles

AV COMPARTMENT FOUND FRAME 17 CORRODED BETWEEN STRINGER 42 & 43L. BLENDED OUT THE CORROSION IAW SRM 51-74-10 & EA 6-5310-T0317322 P1.

Part: FAIRING — CRACKED (RT WING) · airframe 506 hrs · 15,389 cycles

RIGHT WING TIP FENCE FAIRING RIB CRACKED, WY495. REPLACED THE CRACKED RIB OF RT WING TIP FENCE FAIRING AT WY 501 IAW SRM 51-40-21.

Part: FRAME — NICKED (FRAME 34) · airframe 506 hrs · 15,389 cycles

MDCC LT FRAME 34 SURFACE FOUND NICK BETWEEN STRINGER 12LT & 22LT. BLEND OUT & SMOOTHED THE NICK AREA IAW SRM51-73-10. APPLIED ALODINE IAW SRM 51-21-10. NO CRACK FOUND IAW NTM 51-10-08. COMPLIED WITH EA6-5310-T0317082.

Part: DOOR FRAME — CRACKED (CARGO DOORWAY) · airframe 506 hrs · 15,389 cycles

FORWARD CARGO DOOR ACTUATOR ATTACH FITTING. SDI FOUND CRACK WITH A HFEC INSPECTION. REMOVED THE FWD CARGO DOOR IAW AMM 52-31-11-04. REPLACED THE CRACKED FRAME OF FWD CARGO DOOR IAW SRM 51-40-21. INSTALLED THE FWD CARGO DOOR IAW AMM 52-31-11-04 & TESTED OK. MAJOR REPAIR IAW GMM 6-2-100.

Part: FITTING — CRACKED (CARGO DOOR) · airframe 506 hrs · 15,389 cycles

AFT CARGO COMPARTMENT DOOR ACTUATOR FITTINGS. FOUND CRACK WITH A HFEC INSPECTION. REPLACED THE CRACKED FRAME OF AFT CARGO DOOR AT FRAME 61A IAW SRM 51-40-21. INSTALLED THE AFT CARGO DOOR IAW AMM 52-31-11-04 & TESTED OK. MAJOR REPAIR IAW GMM 6-2-100.

Part: CROSSBEAM — CORRODED (FRAME 62) · airframe 506 hrs · 15,389 cycles

AFT CARGO CROSSBEAM RT SIDE FITTING, CORRODED AT FRAME 62. REPLACED THE RT SIDE CORRODED FITTING, CROSSBEAM, IAW SRM 51-40-21.

Part: WINDSHIELD — CRACKED (COCKPIT) · airframe 49,599 hrs · 14,866 cycles

CAPTAIN`S COCKPIT WINDOW CRACKED AT FLIGHT LEVEL 340, ARCING BEGAN IMMEDIATELY. NORMAL QRH PROCEDURES STOPPED THE ARCING. REMAINDER OF FLIGHT NORMAL. R & R CAPTAIN'S WINDSHIELD IAW AMM 56 -11-11-04, PERFORMED WINDSHIELD PANEL ANTI-ICING & DEFOGGING. OPERATIONS TESTED IAW AMM, ALL CHECKED NORMAL.

Part: ENGINE — STALLED (NR 1) · airframe 49,515 hrs · 14,825 cycles

NR 1 ENGINE HAD A SUSPECTED STALL ON ROLLOUT. TOWER REPORTED LT ENGINE ON FIRE. STOWED THRUST REVERSERS BY 60 KIAS & STOPPED ACFT, SHUTDOWN ENGINE, NO OTHER FIRE INDICATIONS, VISUALLY CONFIRM NO SMOKE. ON SHUTDOWN IN RAMP ADC 1 FAULT OCCURRED & STAYED ON. VISUAL CHECK ON NR 1 ENGINE INLET & EXHAUST PIPE ARE OK. INSPECTION COMPLIED WITH IAW TSM 72-00-40 FIGURE 132, NO DEFECT FOUND. PERFORMED BORESCOPE INSPECTION ON 5TH,6TH AND 10 STAGES OF HPC. EXAMINED 1ST STAGE VANES OF HIGH PRESSURE TURBINE. ALSO PERFORMED INSPECTION THROUGH AP-4,AP-6, AND AP-7. INSPECTED CONDITION OF HPC BLADES. ALL INSPECTIONS ARE SATISFACTORY. INSPECTION CARRIED OUT IAW 72-00-00-06. RAN NR 1 ENGINE IAW JRH. ALL PARAMETERS ARE NORMAL.

Part: SMOKE DETECTOR — MALFUNCTIONED (CARGO BAY) · airframe 49,273 hrs · 14,707 cycles

IAW WRI 26-22 8151 FWD CARGO COMPARTMENT DET INDICATION. AGENT 1 DISCH, NO SECONDARY INDICATION, NO SMOKE INDICATION IN THE COCKPIT. TESTED BOTH SMOKE DET OK & TESTED 26-16-00-05-01, ACFT OK FOR SERVICE. R & R 42WH SMOKE DETECTOR.

Part: SKIN — DENTED (ZONE 100) · airframe 48,814 hrs · 14,494 cycles

FUSELAGE SKIN DENTED ON BELLY FWD OF FRAME 4. REPAIRED DENT IAW EA 6-5330-T0302970A.

Part: JACKSCREW — WORN (TE FLAPS) · airframe 48,683 hrs · 14,429 cycles

AFTER TAKEOFF DURING FLAP RETRACTION, RECIEVED A WARNING BELL AND FLAP SYS 1, FLAP SYS 2FAULT. FLAPS WERE STUCK BETWEEN 15-20, CYCLED HANDLE AND DID NOT CLEAR RAN QRH AND RTB. DURING AFTER LANDING CHECK, FLAPS RETRACTED. REVIEWED FAULT CODE FORM NR 1 SFCC, GOT "FLAP JAM" MESSAGE. RECEIVED HIGH SPEED V MESSAGE FROM NR 2 SFCC. FOUND RT WING NR 3 AND NR 4 FLAP JACKSCREW JAM DETECTOR TRIPPED OUT. R & R HIGH SPEED SOLENOID VALVEK. FOUND RT NR 3 & 4 FLAP JACKSCREW WORN OUT. R & R RT WING NR 3 FLAP JACKSCREW. R & R THE RT WING NR 4 FLAP JACKSCREW.

Part: UNKNOWN — UNKNOWN (TE FLAPS) · airframe 48,682 hrs · 14,428 cycles

ON APPROACH, FLAPS SYS 1 AND 2 FAULTED. RECYCLED FLAPS, RETRACTED BUT ON EXTENSION STOPPED AT APPOX 18. RAN QRH AND ON FINAL WITH FLAP HANDLE EXTENSION TO 30/40 SLATS EXTEND TO 30 BUT FLAPS REMAINED LESS THAN 20'. BITE TEST ON SFCC NR 1 GOT FAULT CODE 01111 JAM AND ON SFCC NR 2 GOT FAULT CODE 01110 HIGH SPEED DV IAW TSM 27-50-00. FOUND RT TORQUE LIMITER INDICATOR POPPED OUT AND FURTHER CHECK FOUND OIL LEVEL LOW. R & R RT TORQUE LIMITER 5514. CHECKED ALL FLAP SCREWJACK AND GEARBOX DRAINED OIL QTYS ARE IN THE LIMIT, SERVICED ALL DRAINED SCREWJACK. DUE TO FAULT CODE 01110 HIGH SPEED DV AT SFCC NR 2, FOLLOWED TSM27-50-06, FIG 101, WIRING CHECK FOUND RESISTANCE VALUE OF HIGH SPEED SOLENOID VALVE WAS 81 OHMS (WITHIN LIMIT), AND NO SHORT CIRCUIT FOUND BETWEEN SFCC NR 2 AND SOLENOID OF HIGH SPEED SOL VALVE. PERFORMED OPS TEST OF FLAP SYS IAW AMM27-54-00-05, TEST SLATS.

Part: COMPUTER — FAILED · airframe 48,659 hrs · 14,416 cycles

DURING TAKEOFF ROLL, APPROX 10 SECONDS INTO ROLL, ATS LEVER TRIPPED OFF. ENGINE NR 2 EPR MODE FAULTED, ENGINE NR 2, N1 MODE, ATS OFF ON ECAM. CLEARED RUNWAY. RESET CIRCUIT BREAKER ON OUH 31 PANEL AS DIRECTED BY MX. ALSO RESET NR 2 ENGINE EPR MODE FAULT, AS DIRECTED BY MX. ALL FAULTS CLEARED AND ATS LEVER RESET, ATTEMPTED SECOND TAKEOFF AND WITH SAME FAULTS. RETURNED TO RAMP. PERFORM FADEC GROUND TEST IAW TSM 73-21-40. NO FAULT CODE FOUND, ALSO NO CURRENT FAULT IN MTP. AS A PRECAUTION, R & R THRUST CONTROL COMPUTER IAW AMM 22-36-34-04. PERFORM AFS TEST AND LAND TEST IAW 22-40-00-5, ALL PASSED. PERFORMED ENG RUN WITH MAX POWER IAW JRH, ALL PARAMETERS NORMAL. PERFORM FADEC BITE TEST IAW TSM 73-21-40. NO FAULT CODE FOUND, AND NO FAULT HISTORY FOUND. ALSO CHECK MTP NO FAULT FOUND. PERFORMED OPS CHECK OF TAT& PITOT PROBES HEAT WARNING IN FLIGHT CONFIGURATION AND PERFORMED TEST OF PT2 PROBE HEATING SYS IAW AMM30-31-00-05, ALL TEST NORMAL. ACFT OK FOR SVC.

Part: WIRE — DAMAGED (THRUST REVERSER) · airframe 48,555 hrs · 14,362 cycles

WHEN SETTING TAKEOFF POWER, NR 1 ENGINE REVERSE UNLOCK LIGHT ILLUMINATED. DURING REACTIVATION OF NR 1 THRUST REVERSER, FOUND WIRE CHAFING IN WIRING BUNDLE 21W4082-509 NEXT TO CONNECTOR DS307, FOUND THE WIRE ROUTING TO PIN 4 ON DS307 TO NR 1 THRUST REVERSER UNLOCK WARNING LIGHT 9KM, REPAIRED WIRE IAW ESPM. PERFORMED NR 1 THRUST REVERSER OPS CHECK IAW AMM78-31-00-05 WITH SATIFACTORY.

Part: LIMIT SWITCH — FAILED (CRGO DOOR HANDLE) · airframe 48,462 hrs · 14,316 cycles

CLIMBING THROUGH 5,100 METERS RECEIVED ECAM ALERT. FORWARD CARGO DOOR UNLOCK, PROCEEDED ACCORDING WITH ECAMS SET LANDING ELEVATION AT 10,000 ALERT WENT AWAY AND CAME BACK IN FINAL AGAIN. EXECUTED OVER WEIGHT LANDING IAW QRH. GROUND CHECKED THE FWD CARGO DOOR WAS CLOSED AND LOCKED AND THE FWD CARGO DOOR INDICATION ON ECAM WAS NORMAL. PERFORMED WIRING CHECK IAW FIM52-70-00 AND ASM 52-71-00. FOUND HANDLE LIMIT SWITCH 16WS FAULTY. R & R LIMIT SWITCH IAW AMM 52-71-11-4. PERFORMED DOOR WARNING ADJUSTMENT & TEST IAW AMM 52-71-00-5. ALL SATISFACTORY, ALSO PRESSURIZED ACFT IAW AMM 21-31-00-5 AND EVERYTHING NORMAL. ACFT OK FOR SERVICE.

Part: CONTROLLER — INOPERATIVE (CABIN PRESSURE) · airframe 46,228 hrs · 13,341 cycles

ACFT CABIN PRESS CLIMB ABOVE 10000. REQUESTED LOWER ALTITUDE FROM ATC. BRIEFING WITH FLIGHT CREW, NO WARNING MESSAGE DISPLAYED ON ECAM. PERFORMED CPC 1 AND CPC 2 OPS TEST SATIS IAW AMM21-31-00-05-0. R & R THE NR 2 CPC IAW AMM21-31-11-04-0, AND PERFORMED THE NR 2 CPC BITE TEST NORMAL IAW AMM 21-31-00-05-0. RAN ENGINES IAW JRH,AND PERFORMED THE PRESSURIZATION TEST OF FUSELAGE SATIS IAW AMM05-53-00-00-09. ACFT OK FOR SERVICE.

Part: BATTERY — INOPERATIVE (R1 DOOR SLIDE) · airframe 46,020 hrs · 13,251 cycles

R1 DOOR WILL NOT ARM. R & R THE EMERGENCY POWER SUPPLY BATTERY NR 1 AND NR 2, AND THE AUTO STANDBY UNIT IAW AMM 52-73-18-04-0, AND PERFORMED THE TEST IAW AMM 52-73-00, P BLOCK 501, TESTED NORMAL. ECAM SLIDE DOOR R1 INDICATION NORMAL. AC OK FOR SVC. R & R BATTERIES AND ASPU'S.

Part: CONTROLLER — FAILED (CABIN PRESSURE) · airframe 45,718 hrs · 13,108 cycles

AT ALTITUDE CABIN PRESSURE INDICATED 20460 AND COMMANDED DESCENT. DONED MASKS AND DESCENDED TO 10K, DIVERTED. CABIN PRESS INDICATIONS DELTA P XX (ORANGE) V/S= 2950 (ORANGE) CABIN ALTITUDE 20460 (RED) WHEN EVENT OCCURRED BOTH CREW HAD EARS POP. BELL SOUNDED REMINDER OF FLIGHT. AT SHUTDOWN, CABIN FILLED WITH DENSE CONDENSATION. VISIBILITY ZERO FOR SEVERAL SECONDS. (SAFETY VALVE OPENED). CHECKED CPC CABIN PRESSURE CONTROLLER. CABIN ALT INDICATED AT 80 FT AT ALL TIME. R & R NR 2 CPC IAW MM 21-31-11-04 AND BITE TEST OK. PERFROMED CABIN PRESSURE CHECK WITH APU AIR TO 8.3 PSI. SAFETY VALVE CRACK OPEN AND CLOSE AS THE PRESSURE INCREASED AND DECREASED AROUND 8.3 PSI. SAFETY VALVE FUNCTION CHECK NORMAL. ACFT RELEASED FOR SERVICE.

Part: INDICATOR — FAILED (CABIN PRESSURE) · airframe 45,718 hrs · 13,108 cycles

AT ALTITUDE CABIN PRESSURE INDICATED 20460 AND COMMANDED DESCENT. DONED MASKS AND DESECNDED TO 10K, DIVERTED. CABIN PRESS INDICATIONS DELTA P XX (ORANGE) V/S= 2950 (ORANGE) CABIN ALTITUDE 20460 (RED) WHEN EVENT OCCURRED BOTH CREW HAD EARS POP. BELL SOUNDED REMINDER OF FLIGHT. AT SHUTDOWN CABIN FILLED WITH DENSE CONDENSATION. VISIBILITY ZERO FOR SEVERAL SECONDS. (SAFETY VALVE OPENED). CHECKED CPC CABIN PRESSURE CONTROLLER. CABIN ALT INDICATED AT 80 FT AT ALL TIME. R & R NR 2 CPC IAW MM 21-31-11-04 AND BITE TEST OK. PERFROMED CABIN PRESSURE CHECK WITH APU AIR TO 8.3 PSI. SAFETY VALVE CRACK OPEN AND CLOSE AS THE PRESSURE INCREASED AND DECREASED AROUND 8.3 PSI. SAFETY VALVE FUNCTION CHECK NORMAL. ACFT RELEASED FOR SVC. DUPLICATE SDR- SEE 11-3195 FOR CORRECT FILING.

Part: FILTER — LEAKING (HYD SYSTEM) · airframe 44,726 hrs · 12,675 cycles

DURING DESCENT RECEIVED ECAM GREEN HYD SYS LOW LEVEL WARNING. HYD QUANTITY ON OVERHEAD PANEL INDICATED ZERO. CONSULTED THE QRH AND MANUALLY EXTENDED THE LANDING GEAR. PERFORMED GREEN HYD SYS LEAK CHECK FOUND HYD LEAKAGE CAME FROM THE FILTER 1049 WHICH ON GRN SERVO CONTROL 1150,CHECK GREEN HYD SYS RESERVOIR WITH HYD QTY INDICATES 4.6 GALLON,ALSO CHECK FOUND GREEN HYD QTY INDICATION ON OVERHEAD PANEL, FOUND NIDDLE IN THE MIDDLE OF THE TOPHAT, REFER TO AMM 29-11-42-03.

Part: FILTER — LEAKING (HYD SYSTEM) · airframe 44,726 hrs · 12,675 cycles

DURING DESCENT RECEIVED ECAM GREEN HYD SYS LOW LEVEL WARNING. HYD QTY ON OVERHEAD PANEL INDICATED ZERO. CONSULTED THE QRH AND MANUALLY EXTENDED THE LANDING GEAR. FOUND HYD LEAKAGE CAME FROM THE GREEN SERVO CONTRO FILTER. REMOVED AND REPLACED THE PUMP DELIVERY FILTER ASSY, REMOVED AND REPLACED THE NR 1 AND 2 GREEN ENGINE PUMP AS PER AMM 29-11-32-04.

Part: ACTUATOR — MALFUNCTIONED (MALFUNCTIONED) · airframe 44,667 hrs · 12,651 cycles

ON FINAL TO 15L ICN SELECTING FLAPS 40 HAD AMBER SPOILER 5 FAULT, REPEAT HAPPENED 2 TIMES. DID MISSED APPROACH AND WHILE DOING QRH PROCEDURE ACFT COMMANDED 15 DEG LT TURN WITH CONTROL WHEEL. SELECTED FLIGHT CONTROLS AND NOTED SPOILERS LT 5,6,7 WERE ALL UP AND WOULD NOT RETRACT. DECLARED EMERGENCY AND REQUESTED NO LT TURNS, ON FINAL GOT LT 5,6,7 SPOILERS OFF IAW QRH. LT 5,6,7 SPOILERS. R & R BOTH EFCU IAW AMM 27-61-34-04-0, LT NR5 OUTER GROUP SPOILER VALVE IAW AMM 27-64-13-04-0 AND LT NR5 SPOILER ACTUATOR IAW AMM 27-64-14-04-0 AND THEN SPOILER ROLL TEST AND SPOILER/SPEEDBRAKE SYS OPS CHECKED NORMAL IAW AMM 27-11-00-05, 27-61-00-05. ACFT OK FOR SERVICE.

Part: SELECTOR VALVE — FAILED (MLG) · airframe 44,463 hrs · 12,569 cycles

L/G WOULD NOT RETRACT. COMPLIED WITH ECAM AND QRH. RETURNED TO DEPARTURE. PERFORMED PROX DETECTOR PROCESSING UNIT MEMORY RECALL IAW TSM 32-61-00. FOUND MEMORY EMPTY WITH "00" DISPLAYED. INSPECTED PITCH DAMPERS ON BOTH LANDING GEARS AND NO DEFECTS FOUND IN REF MM 32-10-00-06. R & R LDG GEAR CONTROL SELECTOR VALVE (3GA) AS PER AMM32-31-12-04. R & R LDG CONTROL LEVER AS PER AMM 32-31-11-04. PERFORMED LDG SWING CK WITH DET SYS 1 AND 2 SEVERAL TIMES . ALL TIMES WORKS NORMAL AS PER MM32-30-06-0. A/C OK FOR SERVICE

Part: PRESSURE PANEL — CRACKED (ZONE 100) · airframe 41,705 hrs · 10,947 cycles

A CRACK WAS FOUND AT NLG ROOF PANEL AT STIFFENER C-5 IN AREA OF FRAME 14. REPAIR PERFORMED BY BLENDING OUT THE CRACKED STIFFENER AND INSTALLING REINFORCED ANGLES AND SHIMS IAW EA 6-5312-103289 AND RAS/AS/139/2006 ISS A.

Part: SKIN PANEL — MISREPAIRED (ZONE 100) · airframe 41,705 hrs · 10,947 cycles

FOUND OLD REPAIR DOUBLER AT FRAME 74-75, STRG 38-39 LT. THE REPAIR DOES NOT CONFORM TO SRM 53-10-12/FIG 205, AS IT ENDS ON THE STRINGER. DOUBLER REPAIR RENEWED IAW SRM 53-10-12/FIG 225 APPROVED BY EA 6-5318-103343.

Part: FRAME — DAMAGED (ZONE 100) · airframe 41,704 hrs · 10,946 cycles

FOUND 3 DRILLING MARKS AT FRAME 12 LH OF NLG-WELL. REPAIR PERFORMED BY SMOOTH REWORK OF DRILLING MARKS IAW EA 6-5312-101328 AND RAS/046631/007/2006 ISS A.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 41,704 hrs · 10,946 cycles

CORROSION AT STRG 46, BETWEEN FRAME 39-42 LT. REMAINING THICKNESS OUT OF LIMIT. STRINGER REPAIR PERFORMED WITH PRINCIPLE DESCRIBED IN SRM 53-10-14/FIG 201A, APPROVED BY EA 6-5315-103260 AND RAS/046453/012/2006 ISS "A".

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 41,704 hrs · 10,946 cycles

CORROSION AT STRG 45, BETWEEN FRAME 39-42 LT. REMAINING THICKNESS OUT OF LIMIT. STRINGER REPAIR PERFORMED WITH PRINCIPLE DESCRIBED IN SRM 53-10-14/FIG 201A, APPROVED BY EA 6-5315-103260 AND RAS/046453/012/2006 ISS "A".

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 41,704 hrs · 10,946 cycles

CORROSION AT STRG 46, BETWEEN FRAME 39-42 RT. REMAINING THICKNESS OUT OF LIMIT. STRINGER REPAIR PERFORMED WITH PRINCIPLE DESCRIBED IN SRM 53-10-14/FIG 201A, APPROVED BY EA 6-5315-103260 AND RAS/046453/012/2006 ISS "A".

Part: FRAME — DAMAGED (ZONE 100) · airframe 41,703 hrs · 10,945 cycles

OLD MISDRILLED MARK ON THE CONNECTION SECTION FRAME 64-65, STRG 37 RT. REMAINING THICKNESS AFTER REMOVING OUT OF LIMIT. REPLACEMENT OF CONNECTING SECTION IAW SRM 51-72-10.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 41,704 hrs · 10,946 cycles

CORROSION AT STRG 50, BETWEEN FRAME 46-47 LT. REMAINING THICKNESS OUT OF LIMIT. STRINGER REPAIR PERFORMED WITH PRINCIPLE DESCRIBED IN SRM 53-10-14/FIG 201A, APPROVED BY EA 6-5315-103260 AND RAS/046453/012/2006 ISS "A".

Part: FRAME — DAMAGED (ZONE 200) · airframe 41,703 hrs · 10,945 cycles

TOO SMALL EDGE MARGIN AT TEE-FITTING, CABIN FLOOR STRUCTURE FRAME 18, Y-2462. REPAIR PERFORMED BY REPLACING TEE-FITTING IAW SRM 51-75-10.

Part: SKIN PANEL — DENTED (ZONE 100) · airframe 41,703 hrs · 10,945 cycles

TOOLING MARK (DENT) IN SKIN 240MM BEHIND FRAME 26/32 BETWEEN STRG 50-51 LHS. DENT REPAIR PERFORMED WITH SKIN REPAIR BUSH PER SRM 53-10-12/FIG 221/SH 1 AND 2.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 41,704 hrs · 10,946 cycles

CORROSION AT STRG 49, BETWEEN FRAME 39-44 LT. REMAINING THICKNESS OUT OF LIMIT. STRINGER REPAIR PERFORMED WITH PRINCIPLE DESCRIBED IN SRM 53-10-14/FIG 201A, APPROVED BY EA 6-5315-103260 AND RAS/046453/012/2006 ISS "A".

Part: FRAME — CORRODED (ZONE 100) · corrosion level 2 · airframe 41,703 hrs · 10,945 cycles

CORRSOSION IN UPPER CORNER FITTING AT FRAME 88, STRG 15-17 RHS. REPAIR PERFORMED BY CUTTING AND INSTALLING DOUBLER IAW EA 6-5319-103257.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 41,704 hrs · 10,946 cycles

CORROSION AT STRG 48, BETWEEN FRAME 40-44 RT. REMAINING THICKNESS OUT OF LIMIT. STRINGER REPAIR PERFORMED WITH PRINCIPLE DESCRIBED IN SRM 53-10-14/FIG 201A, APPROVED BY EA 6-5315-103260 AND RAS/046453/012/2006 ISS "A".

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 41,704 hrs · 10,946 cycles

CORROSION AT STRG 50, BETWEEN FRAME 39-43 RT. REMAINING THICKNESS OUT OF LIMIT. STRINGER REPAIR PERFORMED WITH PRINCIPLE DESCRIBED IN SRM 53-10-14/FIG 201A, APPROVED BY EA 6-5315-103260 AND RAS/046453/012/2006 ISS "A".

Part: BUTTSTRAP — DAMAGED (ZONE 100) · airframe 41,704 hrs · 10,946 cycles

DRILLING MARK FOUND ON BUTT STRAP AT FRAME 65, STRG 37 RHS. REPAIR PERFORMED BY CUT OUT DAMAGE AND INSTALLING NEW BUTT STRAP PORTION IAW EA 6-5317-103259 AND RAS/DAHAM/4021137/2006 ISS "A".

Part: SUPPORT — CRACKED (ZONE 200) · airframe 41,703 hrs · 10,945 cycles

THE SUPPORT ANGLE AT FRAME 101, BETWEEN STRG 15 RT TO STRG 15 LT IS DEFORMED AND CRACKED. REPLACEMENT OF SUPPORT ANGLE IAW SRM 51-72-10.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 41,704 hrs · 10,946 cycles

CORROSION AT STRG 49, BETWEEN FRAME 39-44 LH. REMAINING THICKNESS OUT OF LIMIT, STRINGER REPAIR PERFORMED WITH PRINCIPLE DESCRIBED IN SRM 53-10-14/FIG 201A, APPROVED BY EA 6-5315-103260 AND RAS/046453/012/2006 ISS "A".

Part: FRAME — CORRODED (ZONE 100) · corrosion level 2 · airframe 41,703 hrs · 10,945 cycles

CORRSOSION IN UPPER CORNER FITTING AT FRAME 88, STRG 15-17 RHS. REPAIR PERFORMED BY CUTTING AND INSTALLING DOUBLER IAW EA 6-5319-103257.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 41,704 hrs · 10,946 cycles

CORROSION AT STRG 40-41, BETWEEN FRAME 40-45 RT. REMAINING THICKNESS OUT OF LIMIT. STRINGER REPAIR PERFORMED WITH PRINCIPLE DESCRIBED IN SRM 53-10-14/FIG 201A, APPROVED BY EA 6-5315-103260 AND RAS/046453/012/2006 ISS "A".

Part: SKIN PANEL — CRACKED (ZONE 400) · airframe 41,703 hrs · 10,945 cycles

CRACKED HOLE ON PYLON NR 2 AT RIB 8 UPPER SPAR. REPAIR PERFORMED IAW SRM 54-51-31/FIG 20. INSPECTION PROGRAM IAW EA 6-5451-103288.

Part: FITTING — CRACKED (ZONE 100) · airframe 41,704 hrs · 10,946 cycles

FOUND SEVERAL HOLES WITH CRACKS AT C47 REAR SPAR INTERNAL ANGLE FITTING. REPAIR PERFORMED BY REAM UP THE HOLES UNTIL CRACK REMOVAL, INSTALLING BUSHINGS AND CUT OUT THE LT INTERNAL ANGLE FITTING IN AREA OF HOLE NR 1 LT IAW EA 6-5710-101281 AND RAS/046699/025/2006 ISS A.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 41,704 hrs · 10,946 cycles

CORROSION AT STRG 44, BETWEEN FRAME 40-45 RT. REMAINING THICKNESS OUT OF LIMIT. STRINGER REPAIR PERFORMED WITH PRINCIPLE DESCRIBED IN SRM 53-10-14/FIG 201A, APPROVED BY EA 6-5315-103260 AND RAS/046453/012/2006 ISS "A".

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 41,704 hrs · 10,946 cycles

CORROSION AT STRG 46 AND 50, BETWEEN FRAME 39-42 LT. REMAINING THICKNESS OUT OF LIMIT. STRINGER REPAIR PERFORMED WITH PRINCIPLE DESCRIBED IN SRM 53-10-14/FIG 201A, APPROVED BY EA 6-5315-103260 AND RAS/046453/012/2006 ISS "A".

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 41,704 hrs · 10,946 cycles

CORROSION AT STRG 44, BETWEEN FRAME 39-44 LT. REMAINING THICKNESS OUT OF LIMIT. STRINGER REPAIR PERFORMED WITH PRINCIPLE DESCRIBED IN SRM 53-10-14/FIG 201A, APPROVED BY EA 6-5315-103260 AND RAS/046453/012/2006 ISS "A".

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 41,704 hrs · 10,946 cycles

CORROSION AT STRG 48, BETWEEN FRAME 39-42 LT. REMAINING THICKNESS OUT OF LIMIT. STRINGER REPAIR PERFORMED WITH PRINCIPLE DESCRIBED IN SRM 53-10-14/FIG 201A, APPROVED BY EA 6-5315-103260 AND RAS/046453/012/2006 ISS "A".

Part: SPAR — CRACKED (ZONE 500) · airframe 41,704 hrs · 10,946 cycles

FOUND CRACKS AT HOLE H NR 11 AND H NR 24 IN REAR SPAR AT SPOILER NO:NR 3 LT ACTUATOR FITTING. REPAIR PERFORMED BY REAM UP UNTIL CRACK REMOVAL OF HOLES IAW EA 6-5720-103316 AND RAS/BAE/1003422/2006 ISS "A".

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 41,704 hrs · 10,946 cycles

CORROSION AT STRG 47, BETWEEN FRAME 39-42 RT. REMAINING THICKNESS OUT OF LIMIT. STRINGER REPAIR PERFORMED WITH PRINCIPLE DESCRIBED IN SRM 53-10-14/FIG 201A, APPROVED BY EA 6-5315-103260 AND RAS/046453/012/2006 ISS "A".

Part: DOUBLER — CORRODED (ZONE 100) · airframe 41,703 hrs · 10,945 cycles

CORRODED INTERNAL DOUBLER AT GROUND CONNECTING DOOR 121DL, FRAME 18-19, STRG 54 LH - 54 RH. REPAIR PERFORMED BY FABRICATING AND INSTALLATION OF NEW DOUBLER ACCORDING TO DRW A524-10178.

Part: SKIN PANEL — MISREPAIRED (ZONE 100) · airframe 41,704 hrs · 10,946 cycles

OLD REPAIR DOUBLER FOUND AT FRAME 69-70, STRG 47-48 LHS WITH MISDRILLED LOWER RIVET ROW. DOUBLER REPAIR WAS RENEWED IAW EA 6-5317-103313 ISS "A" AND RAS/DAHAM/4021212/2006 ISS "B".

Part: PANEL — DELAMINATED (ZONE 600) · airframe 41,703 hrs · 10,945 cycles

DELAMINATION FOUND ALONG THE EDGE LANDING OF L/E PANEL A572-46071, BETWEEN TRACK 7-8 ON RT WING. REPAIR PERFORMED BY REMOVING THE DAMAGED LAYERS AND PERFORMING A HOT BOND REPAIR AND RESTORING THE ALUMINIUM LAYER ON THE INTERNAL SURFACE IAW EA 6-5741-103258 AND RAS/BAE/1003272/2008 ISS "A".

Part: FRAME — CORRODED (ZONE 100) · corrosion level 2 · airframe 41,703 hrs · 10,945 cycles

CORRSOSION IN UPPER CORNER FITTING AT FRAME 88, STRG 15-17 RHS. REPAIR PERFORMED BY CUTTING AND INSTALLING DOUBLER IAW EA 6-5319-103257.

Part: FRAME — CORRODED (ZONE 200) · corrosion level 2 · airframe 41,703 hrs · 10,945 cycles

CORROSION ON CROSS STRUT FRAME 86, STRG 15 RHS. REMAINING THICKNESS OUT OF LIMIT. CROSS STRUT REPLACED IAW SRM 51-72-10.

Part: SKIN — DAMAGED (ZONE 100) · airframe 41,704 hrs · 10,946 cycles

FOUND OLD PLUGGING RIVET CLOSE TO HOIST POINT ON RT KARMAN STRUCTURE, EXTERNAL SKIN C36-37, P31-32 RT. REPAIR PERFORMED BY REMOVE THE DOUBLE HOLE AND REAM UP AND INSTALLING A BUSH IAW EA 6-5314-103261 AND RAS/DABRE/7006900/2006 ISS A.

Part: SKIN PANEL — MISREPAIRED (ZONE 100) · airframe 41,704 hrs · 10,946 cycles

DURING REMOVAL OF OLD DOUBLER FRAME 69-70, STRG 41-42 RHS, FOUND AN OLD MISDRILLED HOLE BETWEEN OUTER SKIN AND INNER CLIP. REPAIR PERFORMED BY REMOVE THE AFFECTED CLIP, PERFORM COUNTERSINKING OF AFFECTED HOLE IN THE SKIN, REWORK OF CLIP OUTER FLANGE AND REINSTALLATION OF CLIP IAW EA 6-5317-103328 AND RAS/DAHAM/4021214/2006 ISS "A".

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 41,701 hrs · 10,944 cycles

CORROSION ON STRG 56 LHS BETWEEN FRAME 72-73, REMAINING THICKNESS OUT OF LIMIT. STRINGER SPLICE REPAIR PERFORMED IAW SRM 53-10-14/FIG 201.

Part: DOUBLER — CORRODED (ZONE 100) · corrosion level 2 · airframe 41,701 hrs · 10,944 cycles

CORROSION ON INTERNAL WASTE PANEL DOUBLER BETWEEN FRAME 71-72 AND STRG 47-48 RHS. REPAIR PERFORMED BY SMOOTH BLEND OUT AND FLAP PEENING IAW EA-5317-101267 AND RAS/DATLS/0003300/2006.

Part: FITTING — DAMAGED (ZONE 100) · airframe 41,701 hrs · 10,944 cycles

ENLARGED HOLE IN CORNER FITTING AT FRAME 34,38 AND 38.1 LHS BETWEEM STRG 40-41. REPAIR PERFORMED BY REPLACMENT OF CORNER FITTINGS IAW. SRM 51-72-10.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 41,701 hrs · 10,944 cycles

CORROSION ON STRG 59 BETWEEN FRAME 55/58-59, REMAINING THICKNESS OUT OF LIMIT. CONNECTING SECTION REPAIRED IAW SRM 53-10-14/FIG 201.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 41,701 hrs · 10,944 cycles

CORROSION FOUND ON STRG 56 LT AND RT OUTER FLANGE BETWEEN FRAME 76-77. REPAIR PERFORMED BY CUT STRINGER OUTER FLANGES P56 LT, ROTO TEST OF OPEN FASTENER HOLES, CORROSION REMOVAL ON SKIN, FLAP PEENING AT SKIN REWORKED AREAS AND INSTALLING REPAIR ANGLE IAW EA 6-5318-103256 AND RAS/DAHAM/4021169.

Part: STRUCTURE — WORN (ZONE 800) · airframe 41,701 hrs · 10,944 cycles

DAMAGED LATERAL PART ON BULK CARGO DOOR, THE HOLES FROM LOCKING BOLT ARE WORN OUT. REPLACEMENT OF PART IAW SRM 51-52-10.

Part: FITTING — CORRODED (ZONE 100) · corrosion level 2 · airframe 41,701 hrs · 10,944 cycles

DEEP CORROSION AT FITTING FRAME 63, STRG 43 LHS. REPLACEMENT OF FITTING IAW. SRM 51-72-10.

Part: STRUCTURE — WORN (ZONE 800) · airframe 41,701 hrs · 10,944 cycles

DAMAGED LATERAL PART ON BULK CARGO DOOR, THE HOLES FROM LOCKING BOLT ARE WORN OUT. REPLACEMENT OF PART IAW SRM 51-52-10.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 41,701 hrs · 10,944 cycles

CORROSION ON STRG 55 LHS BETWEEN FRAME 75-76, REMAINING THICKNESS OUT OF LIMIT. STRINGER SPLICE REPAIR PERFORMED IAW SRM 53-10-14/FIG 201.

Part: FRAME SPLICE — CORRODED (ZONE 100) · corrosion level 2 · airframe 41,701 hrs · 10,944 cycles

CORROSION ON CONNECTION SECTION FRAME 69-70 BETWEEN STRG 45-48 LT, REMAINING THICKNESS IS OUT OF LIMIT. REPAIR PERFORMED BY REPLACEMENT OF AFFECTED PARTS IAW SRM 51-72-10.

Part: FRAME — CRACKED (ZONE 100) · airframe 41,697 hrs · 10,940 cycles

CRACK FOUND IN FRAME 43 LT, STR 26-27 LT REPAIR PERFORMED BY REPLACEMENT OF FITTING IAW SRM 53-15-18/FIG 1 AND EA 6-5315-03255.

Part: SKIN PANEL — WORN (ZONE 600) · airframe 41,698 hrs · 10,941 cycles

ELONGATED HYDRAULIC FITTING HOLES IN LOWER SKIN PANEL RT. REPAIR PERFORMED BY OVERSIZING AND BUSHING OF AFFECTED HOLES IAW EA 6-5720-101266 AND RAS/BAE/1003250/2006 ISS "A".

Part: SHEAR PLATE — CORRODED (ZONE 100) · corrosion level 2 · airframe 41,698 hrs · 10,941 cycles

CORRODED SHEAR PLATE ANGLE IN BILGE AREA FRAME 54.2-55/58, STRG.45 RT REPAIR PERFORMED BY REMOVING CORROSION AND REPLACEMENT OF ANGLE IAW SRM 51-52-10.

Part: FRAME — CRACKED (ZONE 100) · airframe 41,697 hrs · 10,940 cycles

CRACKED HOLE (H22) IN UPPER FRAME FEET AT FRAME 45, STRG 26-27 RT REPAIR PERFORMED BY OVERSIZING, COLD WORKING AND INSTALLATION OF FASTENER WITH HIGH INTERFERENCE FIT IAW EA 6-5315-103254 AND RAS: 046149/010/2006 ISS "A"

Part: FRAME — DAMAGED (ZONE 200) · airframe 41,699 hrs · 10,942 cycles

DEFORMED FRAME CAP STRIP ON FRAME 74, STRG 26 RHS REPAIR PERFORMED BY INSTALLING NEW PARTS IN ZONE 170.

Part: SKIN PANEL — CHAFED (ZONE 100) · airframe 41,699 hrs · 10,942 cycles

DENTED AND SCRATCHED FUSELAGE SKIN BETWEEN FRAME 19-21, STRG 47-48 RHS. REPAIR PERFORMED BY BLEND OUT SCRATCHES PER SRM 53-10-12 AND IS IN LIMIT IAW. DIAGRAMM 111/112, NDT FOUND NO CRACKS. REPAIR IS COVERED BY EA 6-5313-101263.

Part: FRAME — CRACKED (ZONE 100) · airframe 41,697 hrs · 10,940 cycles

CRACK IN DOUBLER FOUND IN HOLE H22 ON FRAME 45, STRG 26-28 LT REPAIR PERFORMED BY OVERSIZING, COLD WORKING AND INSTALLING NSA5359-5 FASTENER WITH HIGH INTERFERENCE FIT IAW EA 6-5315-103255 AND RAS: 046120/021/2006 ISS "A".

Part: FRAME — CRACKED (ZONE 100) · airframe 41,697 hrs · 10,940 cycles

CRACK FOUND IN HOLE H27 OF AFT FRAME 46, STRG 27-28 LT REPAIR PERFORMED BY OVERSIZING COLD WORKING AND INSTALLING NSA5357-5 FASTENER WITH HIGH INTERFERENCE FIT IAW EA 6-5315-103255 AND RAS: 046120/021/2006 ISS "A".

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 41,698 hrs · 10,941 cycles

HEAVY CORROSION AT STR 50, FRAME 64 LHS. STRINGER REPAIR PERFORMED IAW SRM 53-10-14 FIG 201.

Part: FRAME — CRACKED (ZONE 100) · corrosion level 2 · airframe 41,697 hrs · 10,940 cycles

DAMAGES, CRACKS AND CORROSION IN HOLE H4, H5, AND H6 AND MISDRILLED HOLE IN FITTING AND FRAME 44, BETWEEN STRG 26-27 LT REPAIR PERFORMED BY OVERSIZING HOLES, COLD WORKING, REPLACEMENT OF FITTING AND INSTALLING FASTENERS (NSA5357-5) WITH HIGH INTERFERENCE FIT. MISDRILLED HOLE IS OVERSIZED WITH FASTENER ASNA2027V5. WORKS COVERED BY EA 6-5315-103255 AND RAS: 046120/021/2006 ISS "A".

Part: FRAME — CRACKED (ZONE 100) · airframe 41,697 hrs · 10,940 cycles

TWO CRACKED HOLES (H1, H2) WERE FOUND AT FRAME 43, STRG 26-27 RT, REPAIR PERFORMED BY REPLACING FITTING AND APPLY SB A310-53-2124 ON THE NEW FITTING HOLES IAW EA 6-5315-103254.

Part: SKIN — WORN (ZONE 500) · airframe 41,698 hrs · 10,941 cycles

ELONGATED HYDRAULIC FITTING HOLES IN LOWER SKIN PANEL LT. REPAIR PERFORMED BY OVERSIZING AND BUSHING OF AFFECTED HOLES IAW EA 6-5720-101266 AND RAS/BAE/1003250/2006 ISS "A".

Part: BRACKET — CRACKED (ZONE 100) · airframe 41,698 hrs · 10,941 cycles

CRACKED HYDRAULIC BRACKET AT FRAME 55/58-59 BETWEEN STRG 52-53 RT REPLACEMENT OF BRACKET IAW SRM 51-52-10.

Part: VANE — DAMAGED (ZONE 500) · airframe 41,696 hrs · 10,939 cycles

OLD REPAIR ON FLAP VANE OF INBOARD FLAP LT REPAIR PERFORMED WITH HFEC INSPECTION THAT DENTED AREA IS FREE OF CRACKS, CUT OUT ON LOWER SKIN IS FILLED WITH RESIN AS PER SRM 57-53-12/FIG 206 AND INSTALLING AN EXTERNAL DOUBLER AS PER PRINCIPLES GIVEN IN SRM 57-53-12/FIG 207. REPAIR COVERED IN EA 6-5752-101278 AND RAS/DABRE/7006846/2006 ISS "B".

Part: RIB — DAMAGED (ZONE 500) · airframe 41,696 hrs · 10,939 cycles

SEVERAL OLD REPAIRS ON LT INBOARD FLAP, AT T/E AND RIB 9 AND 10 POSITION. REPAIRS PERFORMED BY REPLACEMENT OF TRAILING EDGE, REPAIR OF DAMAGED RIB FLANGE IAW SRM 57-52-11/FIG 202 AND REPAIR OF FLAP CENTER WING BOX DAMAGE WITH EXTERNAL DOUBLER IAW SRM 57-52-12/FIG 205. REPAIRS COVERED IN EA 6-5752-101278 AND RAS/DABRE/7006846/2006 ISS "B".

Part: FLOORBEAM — CORRODED (ZONE 100) · corrosion level 2 · airframe 41,696 hrs · 10,939 cycles

HEAVY CORROSION ON TOP CAP BEAM AT FRAME 33, OUT OF LIMIT. SPLICE REPAIR PERFORMED IAW SRM 53-10-15 / FIG 207.

Part: SKIN — MISREPAIRED (ZONE 800) · airframe 41,696 hrs · 10,939 cycles

OLD REPAIR DOUBLER ON AFT PAX DOOR RT (ZONE 843) THIS ONES MATERIAL DOES NOT CONFORM TO SRM 52-10-00/FIG 204. REPAIR PERFORMED BY RENEWING SKIN REPAIR IN ACCORDING SRM 52-10-00/FIG 204.

Part: FITTING — DAMAGED (ZONE 100) · airframe 41,696 hrs · 10,939 cycles

DAMAGED EXTERNAL FITTING ON FRAME 38, STRG 29 LT. REPAIR PERFORMED BY REPLACEMENT OF PART IAW SRM 51-72-10.

Part: SKIN — MISREPAIRED (ZONE 600) · airframe 41,696 hrs · 10,939 cycles

FOUND OLD BONDED REPAIR ON RT OUTBOARD FLAP WITH NEW DISBONDING AND DOUBLER DIMENSION NOT IAW TO SRM. REPAIR RENEWED IAW SRM 57-53-12 / FIG 208.

Part: FLOOR SUPPORT — CORRODED (ZONE 100) · corrosion level 2 · airframe 41,696 hrs · 10,939 cycles

CORROSION FOUND ON PRESSURIZED FLOOR FRAME 39-40 LT. REPAIR PERFORMED BY BLEND OUT THE CORROSION AND OVERSIZING FASTENER HOLE IAW EA 6-5314-103252 AND RAS/AS/0136/2006 ISS "A".

Part: BULKHEAD — CORRODED (ZONE 100) · corrosion level 2 · airframe 41,696 hrs · 10,939 cycles

FOUND CORROSION ON PRESSURE BULKHEAD AT T-SECTION FRAME 39 LOWER AREA BETWEEN STRG 52 LT TO 52 RT. REPAIR PERFORMED BY CUT OUT THE BEAM AND INSTALL A NEW LOWER BEAM PORTION WITH A SPLICE APPROVED BY EA 6-5314-101269 AND RAS: 046044/048/2006 ISS "A".

Part: PLATE — CORRODED (ZONE 800) · corrosion level 2 · airframe 41,696 hrs · 10,939 cycles

CORROSION BETWEEN PLATE SHEET METAL AND SLIDING PROTECTION AT FWD CREW DOOR 831 LT. REPAIR PERFORMED BY REPLACEMENT OF PART IAW SRM 51-72-10.

Part: SKIN PANEL — MISREPAIRED (ZONE 100) · airframe 41,696 hrs · 10,939 cycles

FOUND OLD UNIDENTIFIABLE RIVET IN THE SKIN NEAR FRAME 68 BETWEEN STRG 45-46, LHS. REPAIR PERFORMED REMOVING FASTENER AND INSTALLING A FREEZE PLUG IAW. SRM 51-40- 51 APPROVED BY EA 6-5317-101277 AND RAS/DATLS/0003278/2006 ISS "A".

Part: SKIN PANEL — CORRODED (ZONE 600) · corrosion level 2 · airframe 41,696 hrs · 10,939 cycles

CORROSION AROUND OVERWING REFUELING PORT RT OUTER WING BETWEEN RIB 27-28, STRG 12-13. REPAIR PERFORMED BY BLEND OUT CORROSION, NDT INSPECTION FOR CRACK FREE IAW EA 6-5720-103253 AND RAS/BAE/1003233/2006 ISS "A".

Part: FRAME — CORRODED (ZONE 100) · airframe 41,696 hrs · 10,939 cycles

CORROSION FOUND ON REEINFORCING ANGLE FRAME 38.1-39, STRG 54 LT. REPAIR PERFORMED BY REPLACEMENT OF ANGLE WITHOUT CUTTING OF FRAME IAW EA 6- 5314-101270 AND RAS/DABRE/7006844/2006 ISS "A".

Part: DOOR — MISSING · airframe 41,200 hrs · 10,611 cycles

UPON LANDING INTO PWM DISCOVERED FUELING PANEL MISSING. FOUND PANEL ON RUNWAY. REPLACED R/COOLING AIR INLET FAIRING CTR SECTION ASSY IAW AMM 53-15-73-4.

Part: ACCESS PANEL — MISSING (FUSELAGE) · airframe 41,182 hrs · 10,600 cycles

AFTER FLIGHT ARRIVAL DURING WALK AROUND, FOUND FUELING PANEL MISSING AND WIRE EXPOSED. DOOR BROKEN OFF APPROX 2 IN BELOW HINGE POINT. REFUEL/DEFUEL PANEL DOOR MISSING. CDL PERFORMANCE LIMITING WEIGHT PENALTY IS NEGLIGIBLE. COMPLIED WITH EA 6-5350-107589 TAPED AS REQUIRED. THE EXACT CAUSE IS UNKNOWN, MISSING PANEL NOT FOUND.