N661FE

Part: VALVE — FAILED (ZONE 700) · airframe 39,819 hrs · 22,105 cycles

DURING APPROACH, LANDING GEAR WOULD NOT EXTEND AFTER MULTIPLE CYCLES AND SWITCHING SYSTEMS 1 & 2. HYDRAULICS GOOD. USED LANDING GEAR GRAVITY EXTENSION QRH PROCEDURE, GEAR EXTENDED. LANDED UNEVENTFULLY, TOWED IN FROM RUNWAY DUE TO NO NOSE WHEEL STEERING. EMERGENCY DECLARED. AMM: 32-31-12-04, AMM: 32-31-12-06, REMOVED AND REPLACED ELECTROHYDRAULIC VALVE (3GA). PERFORMED INSPECTION/CHECK OF VALVE ALL CHECKS GOOD. NO LEAKS NOTED.

Part: MONITOR — EXPIRED (CO2) · airframe 39,609 hrs · 21,969 cycles

CO2 MONITOR (S/N AREJ-2218) CALIBRATION CYCLE EXPIRED. REMOVED AND REPLACED CO2 MONITOR WITH EXPIRED CALIBRATION CYCLE.

Part: POWER SUPPLY — NO TEST (ZONE 200) · airframe 39,378 hrs · 21,818 cycles

L1 AND R1 DOOR SLIDE TEST WARNING LIGHTS DO NOT ILLUMINATE DURING TEST. BUZZERS WORK NORMALLY. L1 AND R1 CREW ENTRY DOOR ESCAPE SLIDE WARNING SYSTEM LIGHTS - INOP. MEL: 52-73-01-01 REPLACED AUTONOMOUS STANDBY POWER SUPPLY UNIT PER A.M.M. 52-73-18- 04. (REF WRI 52-70/7512) REMOVED FROM MEL.

Part: CSU — FAILED (FLAP/SLAT SYSTEM) · airframe 38,853 hrs · 21,458 cycles

AFTER TAKEOFF ON GEAR RETRACTION THE CAPTAIN RED SPD LIM APPEARED ON PFD. THE NUMBER 2 FAC WAS DEFERRED PER MEL 22-26-34-01 AND THE OP NOTES ABOUT SPEED TREND ,VSS, VLS,VMAX,F,S SPEEDS ETC WERE ALSO INDICATED AND MISSING ON CAPT PFD. EMERGENCY DECLARED. AMM 22-28-00-05 AMM 22-00-00-02 AMM 22-25-12-04 REF WRI 27-50/6772 FOR #1 AND #2 SFCC REPLACEMENT, AND WRI 27-50/6775 FOR FLAP/SLAT CSU REPLACEMENT. PERFORMED FLIGHT ENVELOPE/SPEED LIMIT CALCULATION TEST. TEST GOOD. PERFORMED FAC 1 AND FAC 2 OPS TESTED GOOD. PERFORMED AFS LAND AND AUTOLAND LIGHTS TEST. TEST GOOD.

Part: JACKSCREW — FAILED (NR 4 FLAP) · airframe 38,853 hrs · 21,458 cycles

ON DEPARTURE 15/0 CONFIGURATION AFTER AT SAFE SPEED WE RETRACTED THE SLATS AND RECEIVED ECAM WARNING OF FLAPS SYS 1 AND 2 FAULT/ FLAPS STUCK. DID NOT CYCLE BECAUSE FLAPS WERE NOT USED AND BOTH FLAPS AND SLATS WERE AT 0. DECLARED AN EMERGENCY AND PROCEED TO DESTINATION. FLAPS DID NOT EXTEND ON LANDING. SLATS WORKED NORMALLY. EMERGENCY DECLARED. INSTALLED RH #4 FLAP JACKSCREW IAW AMM 27-54-24-04. OPS CHECK PASSED.

Part: CONTROLLER — MALFUNCTIONED (SLAT/FLAP SYSTEM) · airframe 38,842 hrs · 21,450 cycles

FLAPS STUCK AT 15 ON TAKEOFF. CYCLED NO CHANGE. NO OVERSPEED. AMM 27-51-18-04. T/S PER TSM 27-50-02. RESET TORQUE LIMITERS. OPS SLATS/FLAPS THROUGH ALL DETENTS. NO FAULTS OR ANOMALIES NOTED DURING OPS. TORQUE LIMITERS OPS NORMAL. CHECKED OIL LEVEL OF FLAP PCU AND FLAP TORQUE LIMITERS PER MM 12-13-27-00. OIL LEVEL CHECKS FULL. PERFORMED BITE OF SFCC 1 AND 2 PER MM 27-51-00-05. SFCC 1 BITE TEST NORMAL. SFCC 2 BITE DID NOT GET FLAP STEADY GREEN LIGHT ON DURING BITE TEST. REMOVED AND REPLACED SFCC 2 PER MM 27-51-18-04. BITE TEST NORMAL. RAN #1 AND #2 ENGINES PER JRH, CYCLED SLATS FLAPS THROUGH ALL DETENTS 3 X'S. NO FAULTS OR ANOMALIES NOTED. COMPLIED WITH POST MX CONFERENCE CALL WITH MOCC. A/C OK FOR SERVICE.

Part: JACKSCREW — BINDING (LE FLAPS) · airframe 38,802 hrs · 21,421 cycles

FLAPS/SLATS STUCK 15/15 ON DEPARTURE. EMERGENCY DECLARED. QRH FOLLOWED. FLAPS OVERSPEED AT 15/15 TO APPROX 225 KTS. ***EMERGENCY DECLARED*** REF TSI 27-80/6666 FOR RH WING #1 SLAT SCREWJACK TORQUE INDICATOR FOUND TRIPPED. ALL SERVICING AND OTHER WORK PERFORMED ON TSI. RH WING #1 SLAT SCREWJACK MPN: CHA 1237-002A// MSN: 2413. SERVICED #1 R/H SLAT JACK SCREW PER MM OPS CHECK GOOD. REF AMM 12-13-27, 12-22-27, 27-84-00, AND TSM 27-80-02

Part: FITTING — NONE (ZONE 600) · airframe 38,767 hrs · 21,402 cycles

AIRCRAFT REPAIR ASSESSMENT : EXISTING DOUBLER REPAIRS FOUND ON RHW RIBS OF T/E STRUCTURE AT WI.AX 21.9 NEAR AFT LUG COMPLIED WITH ATTACHMENT B OF EO: E6-5100-7-5000 D7 PT1, TITLE: STRUCTURES - REPAIR CATALOG - A300/A310 REPAIR IDENTIFICATION & TRACKING REQUIREMENTS 14 CFR 121.707, INSPECTION OF EXISTING REPAIR DISCOVERED CHAFING DAMAGE ON EXISTING REPAIR DOUBLER, PFM REPAIR ACTION ON EXISTING DOUBLER WIAX 21.9 AS PER FAA APPROVED DATA: EA#6-5740-153066 A, TITLE:WINGS, ATTACH FITTINGS: AUX STRUCTURE, R/H AILERON AND SERVO CONTROL ATTACHMENT FITTINGS, HINGE RIBS, DAMAGE, REPAIR, THE REPAIR IS CATEGORY A AND CLASSIFIED AS MAJOR PER GMM6-2-100. "MAJOR REPAIR."

Part: FITTING — NONE (ZONE 600) · airframe 38,767 hrs · 21,402 cycles

AIRCRAFT REPAIR ASSESSMENT : EXISTING DOUBLER REPAIRS FOUND ON RHW RIBS OF T/E STRUCTURE AT RIB6A NEAR AFT LUG COMPLIED WITH ATTACHMENT B OF EO: E6-5100-7-5000 D7 PT1, TITLE: STRUCTURES - REPAIR CATALOG - A300/A310 REPAIR IDENTIFICATION & TRACKING REQUIREMENTS 14 CFR 121.707, INSPECTION OF EXISTING REPAIR DISCOVERED CHAFING DAMAGE ON EXISTING REPAIR DOUBLER, REPLACE EXISTING DOUBLER AT RIB6A WITH NEW REPAIR AS PER FAA APPROVED DATA: EA#6-5740-153066 A, TITLE:WINGS, ATTACH FITTINGS: AUX STRUCTURE, R/H AILERON AND SERVO CONTROL ATTACHMENT FITTINGS, HINGE RIBS, DAMAGE, REPAIR, THE REPAIR IS CATEGORY A AND CLASSIFIED AS MAJOR PER GMM6-2-100. "MAJOR REPAIR."

Part: FITTING — NONE (ZONE 600) · airframe 38,767 hrs · 21,402 cycles

AIRCRAFT REPAIR ASSESSMENT : EXISTING DOUBLER REPAIRS FOUND ON RHW RIBS OF T/E STRUCTURE AT WI.AX 13.9 NEAR AFT LUG COMPLIED WITH ATTACHMENT B OF EO: E6-5100-7-5000 D7 PT1, TITLE: STRUCTURES - REPAIR CATALOG - A300/A310 REPAIR IDENTIFICATION & TRACKING REQUIREMENTS 14 CFR 121.707, INSPECTION OF EXISTING REPAIR DISCOVERED CHAFING DAMAGE ON EXISTING REPAIR DOUBLER, REPLACE EXISTING DOUBLER AT WIAX 13.9 WITH NEW REPAIR AS PER FAA APPROVED DATA: EA#6-5740-153066 A, TITLE:WINGS, ATTACH FITTINGS: AUX STRUCTURE, R/H AILERON AND SERVO CONTROL ATTACHMENT FITTINGS, HINGE RIBS, DAMAGE, REPAIR, THE REPAIR IS CATEGORY A AND CLASSIFIED AS MAJOR PER GMM6-2-100. "MAJOR REPAIR."

Part: SKIN — NONE (LT WING TE FLAP) · airframe 38,767 hrs · 21,402 cycles

AIRCRAFT REPAIR ASSESSMENT : EXISTING DOUBLER REPAIR FOUND ON LHW CTR FLAP UPR SKIN BTW RIB12~13, T/E-13.8" COMPLIED WITH ATTACHMENT B OF EO: E6-5100-7-5000 D7 PT1, INSPECTION OF EXISTING REPAIR DETERMINED IT WAS UNDOCUMENTED REPAIR, REMOVED EXISTING REPAIR AND PFM DOUBLER REPAIR PER FAA APPROVED DATA: EA#6-5750-T0378856, THE REPAIR IS CATEGORY A AND CLASSIFIED AS MAJOR PER GMM6-2-100.

Part: NONE — NONE (NONE) · airframe 38,767 hrs · 21,402 cycles

EXISTING REPAIR FOUND ON M/D CROSSBEAM AT FR29, BTW Y1456 TO -Y1456 COMPLIED WITH ATTACHMENT B OF EO: E6-5100-7-5000 D7 PT1, TITLE: STRUCTURES - REPAIR CATALOG - A300/A310 REPAIR IDENTIFICATION & TRACKING REQUIREMENTS 14 CFR 121.707, INSPECTION OF EXISTING REPAIR DETERMINED IT TO BE CURRENT WITH FAA APPROVED DATA: EA#6-5310-149065 A, TITLE: FUSELAGE - MAINFRAME - FUSELAGE / FR29 / CROSSBEAM SPLICE REPAIR, THE REPAIR IS CATEGORY A AND CLASSIFIED AS MAJOR PER GMM6-2-100. RAISED RDR TO LIST IN MCMRT DUE TO THE PREVIOUS EA WAS MINOR AND BE UPGRADED TO MAJOR THIS TIME. "MAJOR REPAIR"

Part: SKIN — CRACKED (LT WING TE FLAP) · airframe 38,767 hrs · 21,402 cycles

PFM EA#: 6-5750-T0378801 P1 FOUND NEW CRACK AT LH WING CTR FLAP RIB26 BTWN STGR 2.7-2.8 ACCOMPLISHED THE CAT.A FLANGE REPAIR AT RIB 26 UPPER FLANGE S-2.7~S-2.8, THE REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 I.A.W FEDEX EA NO:T6-5750-T0378801 P1, SEQ NO:1119, TITLE: WINGS-FLIGHT SURFACES-LH CENTER FLAP-CRACKS IN UPPER FLANGES OF RIBS 11,12,13,20,25 AND 26, WITH OVERSIZED HOLE ON UPPER SKIN AT RIB 11-

Part: DUMMY RAIL — WORN (NR 5) · airframe 38,767 hrs · 21,402 cycles

FR54/FR54.2 LH NO.5 DUMMY SEAT TRACK FOUND GAP OVER 1.0MM AND LESS THAN 2.15MM. AUTUAL MEASUREMENT:1.14MM REPLACED DAMAGED DUMMY SEAT TRACK WITH NEW ONE. I.A.W A300-600F SRM 51-72-10-001,P2 AND 51-40-21-001 PARA7 P24~P50, THE REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100 AT MAIN DECK FR54/FR54.2 LH NO.5

Part: FITTING — CRACKED (MDC DOOR) · airframe 38,767 hrs · 21,402 cycles

THE MDC DOOR ACTUATOR AFT SUPPORT FRAME WAS FOUND CRACK ACCOMPLISHED THE REPLACEMENT OF BEARING FITTING AT MAIN DECK CARGO DOOR FR24 LONGN1~LONGN3 I.A.W FEDEX EA NO:T6-5230-T0378797 P1, SEQ NO:1121, TITLE:DOORS-CARGO DOOR /HYD SYS-MAIN CARGO ACTUATOR BEARING FITTING REPLACEMENT (FWD AND AFT), THE REPAIR CLASSIFIED AS CAT.A MAJOR PER GMM 6-2-100

Part: RIB — GOUGED (ZONE 500) · airframe 38,767 hrs · 21,402 cycles

LH WING NO.3 SPOILER LWR JACK RIB SCREW HOLE O/B EDGE DAMAGE. ACCOMPLISHED THE CAT.B HOLE REINFORCEMENT REPAIR AT LH WING NO.3 SPOILER JACK RIB AT ABX 40.425 LOWER HOLE. THE REPAIR CLASSIFIED AS MAJOR REF GMM 6-2-100. I.A.W FEDEX EA:T6-5740-T0378860 P1 SEQ NO:1107, TITLE:WINGS-ATTACH FITTINGS-LH WING#5 SPOILER JACK RIB AT STA ABX 40.425-BEAM ATTACHMENT HOLE REINFORCEMENT REPAIR-SRM DEVIATION.

Part: RIB — GOUGED (ZONE 500) · airframe 38,767 hrs · 21,402 cycles

LH WING NO.3 SPOILER UPR JACK RIB SCREW HOLE INNER SURFACE SCRATCH. ACCOMPLISHED THE CAT.B HOLE REINFORCEMENT REPAIR AT LH WING NO.3 SPOILER JACK RIB STA ABX 40.425 UPPER HOLE. THE REPAIR CLASSIFIED AS MAJOR REF GMM 6-2-100. I.A.W FEDEX EA:T6-5740-T0378860 P1 SEQ NO:1107, TITLE:WINGS-ATTACH FITTINGS-LH WING#3 SPOILER JACK RIB AT STA ABX 40.425-BEAM ATTACHMENT HOLE REINFORCEMENT REPAIR-SRM DEVIATION.

Part: FLOOR SUPPORT — CORRODED (FRMS 11-14) · airframe 38,767 hrs · 21,402 cycles

MAIN DECK COMPT - COURIER AREA FOUND 1EA SUPPORT - FLOOR CORRODED LOCATION FROM FR11 TO FR14 , Y730 REPLACED THE DAMAGE SUPPORT WITH NEW PARTS, LOCATED IN FR11 TO FR14, Y730 I.A.W A300- 600F SRM 51-72-10-001,P2 REPAIR CLASSIFIED AS MINOR PER GMM6-2-100

Part: RIB — CORRODED (ZONE 500) · airframe 38,767 hrs · 21,402 cycles

LH WING NO.5 SPOILER I/B UPPER JACK RIB SCREW HOLE O/B EDGE CORRODED. ACCOMPLISHED THE CAT.B HOLE REINFORCEMENT REPAIR AT LH WING NO.5 SPOILER JACK RIB AT ABX 175.875 UPPER HOLE. THE REPAIR CLASSIFIED AS MAJOR REF GMM 6-2-100. I.A.W FEDEX EA:T6-5740-T0378861 P1 SEQ NO:1108, TITLE:WINGS-ATTACH FITTINGS-LH WING#5 SPOILER JACK RIB AT STA ABX 175.875-BEAM ATTACHMENT HOLE REINFORCEMENT REPAIR-SRM DEVIATION.

Part: FLOOR SUPPORT — CORRODED (FRMS 11-15A) · airframe 38,767 hrs · 21,402 cycles

MAIN DECK COMPT - COURIER AREA FOUND 1EA SUPPORT - FLOOR CORRODED LOCATION FROM FR11 TO FR15A , Y953 REPLACED THE 1EA SUPPORT WITH NEW AT MAIN DECK COMPT-COURIER AREA LOCATION FROM FR11 TO FR 15A , Y953 I.A.W A300-600F SRM 51-72-10-001, PAGE2 CLASSIFIED AS MINOR PER GMM 06-2-100

Part: RIB — GOUGED (ZONE 600) · airframe 38,767 hrs · 21,402 cycles

R/H SPOILER 3 I/B JACK RIB UPR BORE EDGE DAMAGE. ACCOMPLISHED THE CAT.B HOLE REINFORCEMENT REPAIR AT RH WING NO.3 SPOILER JACK RIB AT ABX 31.675 UPPER HOLE. THE REPAIR CLASSIFIED AS MAJOR REF GMM 6-2-100. I.A.W FEDEX EA:T6-5740-T0378859 P1 SEQ NO:1106, TITLE:WINGS-ATTACH FITTINGS-RH WING#3 SPOILER JACK RIB AT STA ABX 31.675-BEAM ATTACHMENT HOLE REINFORCEMENT REPAIR-SRM DEVIATION.

Part: RIB — GOUGED (ZONE 600) · airframe 38,767 hrs · 21,402 cycles

R/H SPOILER 3 I/B JACK RIB LWR BORE EDGE DAMAGE. ACCOMPLISHED THE CAT.B HOLE REINFORCEMENT REPAIR AT RH WING NO.3 SPOILER JACK RIB AT ABX 31.675 LOWER HOLE. THE REPAIR CLASSIFIED AS MAJOR REF GMM 6-2-100. I.A.W FEDEX EA:T6-5740-T0378859 P1 SEQ NO:1106, TITLE:WINGS-ATTACH FITTINGS-RH WING#3 SPOILER JACK RIB AT STA ABX 31.675-BEAM ATTACHMENT HOLE REINFORCEMENT REPAIR-SRM DEVIATION.

Part: RIB — GOUGED (ZONE 600) · airframe 38,767 hrs · 21,402 cycles

R/H SPOILER 7 I/B JACK RIB UPR BORE EDGE DAMAGE ACCOMPLISHED THE CAT.B HOLE REINFORCEMENT REPAIR AT RH WING NO:7 SPOILER JACK RIB AT SP2X 31.675 UPPER HOLE. THE REPAIR CLASSIFIED AS MAJOR REF GMM 6-2-100. I.A.W FEDEX EA:T6-5740-T0378863 P1, SEQ NO:1109, TITLE: WINGS-ATTACH FITTINGS-RH WING #7 SPOILER JACK RIB AT STA SP2X 31.675 - BEAM ATTACHMENT HOLE REINFORCEMENT REPAIR - SRM DEVIATION.

Part: ELEVATOR — NONE (ZONE 300) · airframe 38,767 hrs · 21,402 cycles

AIRCRAFT REPAIR ASSESSMENT : EXISTING COMPOSITE REPAIR FOUND ON LH ELEVATOR UPR SKIN AT ER16-16", T/E-10.9" COMPLIED WITH ATTACHMENT B OF EO: E6-5100-7-5000 D7 PT1, TITLE: STRUCTURES - REPAIR CATALOG - A300/A310 REPAIR IDENTIFICATION & TRACKING REQUIREMENTS 14 CFR 121.707, INSPECTION OF EXISTING REPAIR DETERMINED IT TO BE CURRENT WITH FAA APPROVED DATA: A300-600F SRM55-21-12-201, PARA5.B, PAGE 211~212 FIG 202. THE REPAIR IS CATEGORY B AND CLASSIFIED AS MAJOR PER GMM 6-2-100 "MAJOR REPAIR"

Part: ELEVATOR — NONE (ZONE 300) · airframe 38,767 hrs · 21,402 cycles

00087566N00547 AIRCRAFT REPAIR ASSESSMENT : EXISTING COMPOSITE REPAIR FOUND ON R/H ELEVATOR UPR SKIN AT ER10-8", T/E-23.5" COMPLIED WITH ATTACHMENT B OF EO: E6-5100-7-5000 D7 PT1, TITLE: STRUCTURES - REPAIR CATALOG - A300/A310 REPAIR IDENTIFICATION & TRACKING REQUIREMENTS 14 CFR 121.707, INSPECTION OF EXISTING REPAIR DETERMINED IT TO BE CURRENT WITH FAA APPROVED DATA: A300-600F SRM55-21-12-201, PARA5.B, PAGE 211~212 FIG 202. THE REPAIR IS CATEGORY B AND CLASSIFIED AS MAJOR PER GMM 6-2-100 "MAJOR REPAIR"

Part: SEAT TRACK — GOUGED (FRM 62) · airframe 38,767 hrs · 21,402 cycles

MAIN DECK COMPT FLOOR - SEAT TRACK CROWN AREA GOT GOUGED LOCATION AT FR62 PLUS 2",Y1959 CUT OUT DAMAGE SEAT TRACK,CUT OUT LENGTH=53 INCH AT FR62,Y1959. FABRICATE THE NEW SEAT TRACK AND REPAIR U-SECTION AND INSTALL ALL REPAIR PARTS WET WITH FASTENERS. I.A.W A300-600F SRM 53-10-16-201 PARA.4, FIG201,P201-P208. THIS REPAIR CLASSIFIED AS MAJOR CATEGORY A REPAIR, PER GMM 06-2-100.

Part: SEAT TRACK — GOUGED (FRM 62) · airframe 38,767 hrs · 21,402 cycles

MAIN DECK COMPT FLOOR - SEAT TRACK CROWN AREA GOT GOUGED LOCATION AT FR62 PLUS 2",Y1959 CUT OUT DAMAGE SEAT TRACK,CUT OUT LENGTH=53 INCH AT FR62,Y1959. FABRICATE THE NEW SEAT TRACK AND REPAIR U-SECTION AND INSTALL ALL REPAIR PARTS WET WITH FASTENERS. I.A.W A300-600F SRM 53-10-16-201 PARA.4, FIG201,P201-P208. THIS REPAIR CLASSIFIED AS MAJOR CATEGORY A REPAIR, PER GMM 06-2-100.

Part: SUPPORT BRACKET — CRACKED (FRM 44 S51R) · airframe 38,767 hrs · 21,402 cycles

RH AIR CONDITION 144FR FAIRING LOWER SUPPORT BRACKET CRACK AT FR44,S-51R POSITION. REPLACED THE ANGLE BRACKET WITH NEW ONE IAW A300-600F SRM51-72-10-001 PAGE 2 THIS REPAIR CLASSIFIED AS MINOR PER GMM6-2-100 (AT FR44, S-51R FAIRING LOWER SUPPORT BRACKET)

Part: NONE — NONE (NONE) · airframe 38,767 hrs · 21,402 cycles

00087566N00415 AIRCRAFT REPAIR ASSESSMENT : EXISTING SPLICE REPAIR FOUND ON M/D SEAT TRACK BTW FR77 TO FR80/82, Y0 COMPLIED WITH ATTACHMENT B OF EO: E6-5100-7-5000 D7 PT1, TITLE: STRUCTURES - REPAIR CATALOG - A300/A310 REPAIR IDENTIFICATION & TRACKING REQUIREMENTS 14 CFR 121.707, INSPECTION OF EXISTING REPAIR DETERMINED IT TO BE CURRENT WITH FAA APPROVED DATA: A300-600F SRM53-10-16-201, PARA.4, PAGE 203~206, FIG.201A, THE REPAIR IS CATEGORY A AND CLASSIFIED AS MAJOR PER GMM6-2-100. "MAJOR REPAIR"

Part: SUPPORT BRACKET — CRACKED (FRM 44 S51L) · airframe 38,767 hrs · 21,402 cycles

LH AIRCONDITION 143FL FAIRING LOWER SUPPORT ANGLE BRACKET CRACK AT FR44,S-51L POSITION. REPLACED THE ANGLE BRACKET WITH NEW ONE IAW A300-600F SRM 51-72-10-001 PAGE 2 THIS REPAIR CLASSIFIED AS MINOR PER GMM6-2-100 (AT FR44, S-51L FAIRING LOWER SUPPORT BRACKET)

Part: SUPPORT — CRACKED (FRMS 60-61) · airframe 38,767 hrs · 21,402 cycles

AFT CGO COMP'T CEILING PANEL SUPPORT CRACK AT ENTRY AREA BTW FR60-FR61 POSITION. REPLACED THE HEADER WITH NEW PART I.A.W A300-600F SRM 51-72-10-001, PAGE.2 AND 51-40-21- 001, PARA6 PAGE7B~PAGE23, THIS REPAIR IS CLASSIFIED AS MINOR PER GMM 6-2-100 AND LOCATED AT AFT CARGO COMPARTMENT BETWEEN FR60~FR61.

Part: SKIN — CRACKED (LT WING TE FLAP) · airframe 38,767 hrs · 21,402 cycles

2EA CRACKS (MAX:20MM) WERE FOUND AT LH WING CENTER FLAP RIB25 AFT AREA OF TOP SURFACE RIB FLANGE. ACCOMPLISHED THE FLANGES REPAIR AT RIB25 UPPER FLANGE S-2.7~REAR SPAR AND EXTERNAL DOUBLERS REPAIR AT RIB26~25 S-2.2~REAR SPAR PLUS 10 INCHES, THE REPAIR CLASSIFIED AS CAT.A MAJOR REPAIR PER GMM 6-2-100 I.A.W FEDEX EA NO:T6-5750-T0378801 P1, SEQ NO:1119, TITLE: WINGS-FLIGHT SURFACES-LH CENTER FLAP-CRACKS IN UPPER FLANGES OF RIBS 11,12,13,20,25 AND 26, WITH OVERSIZED HOLE ON UPPER SKIN AT RIB 11-

Part: SKIN — CRACKED (LT WING TE FLAP) · airframe 38,767 hrs · 21,402 cycles

4EA CRACKS (MAX50MM) WERE FOUND AT LH WING CENTER FLAP RIB11 AFT AREA OF TOP SURFACE RIB FLANGE. ACCOMPLISHED THE FLANGE REPAIR AT RIB 11 UPPER FLANGE S-2.7~REAR SPAR AND EXTERNAL DOUBLER REPAIR AT RIB11~RIB13 S-2.2~REAR SPAR, THE REPAIR CLASSIFIED AS CAT.A MAJOR PER GMM 6-2-100 I.A.W FEDEX EA NO:T6-5750-T0378801 P1, SEQ NO:1119, TITLE: WINGS-FLIGHT SURFACES-LH CENTER FLAP-CRACKS IN UPPER FLANGES OF RIBS 11,12,13,20,25 AND 26, WITH OVERSIZED HOLE ON UPPER SKIN AT RIB 11- (NOTE: THIS SDR PART NAME TYPO, CREATE THE NEW ONE NO:24-0637)

Part: SKIN — CRACKED (LT WING FLAP) · airframe 38,767 hrs · 21,402 cycles

4EA CRACKS (MAX50MM) WERE FOUND AT LH WING CENTER FLAP RIB11 AFT AREA OF TOP SURFACE RIB FLANGE. ACCOMPLISHED THE FLANGE REPAIR AT RIB 11 UPPER FLANGE S-2.7~REAR SPAR AND EXTERNAL DOUBLER REPAIR AT RIB11~RIB13 S-2.2~REAR SPAR, THE REPAIR CLASSIFIED AS CAT.A MAJOR PER GMM 6-2-100 I.A.W FEDEX EA NO:T6-5750-T0378801 P1, SEQ NO:1119, TITLE: WINGS-FLIGHT SURFACES-LH CENTER FLAP-CRACKS IN UPPER FLANGES OF RIBS 11,12,13,20,25 AND 26, WITH OVERSIZED HOLE ON UPPER SKIN AT RIB 11-

Part: SKIN — CRACKED (LT WING TE FLAP) · airframe 38,767 hrs · 21,402 cycles

1EA CRACK (25MM) WAS FOUND AT LH WING CENTER FLAP RIB13 AFT AREA OF TOP SURFACE RIB FLANGE. ACCOMPLISHED THE FLANGE REPAIR AT RIB 13 UPPER FLANGE S-2.7~S-2.8, THE REPAIR CLASSIFIED AS CAT.A MAJOR PER GMM 6-2-100 I.A.W FEDEX EA NO:T6-5750-T0378801 P1, SEQ NO:1119, TITLE: WINGS-FLIGHT SURFACES-LH CENTER FLAP-CRACKS IN UPPER FLANGES OF RIBS 11,12,13,20,25 AND 26, WITH OVERSIZED HOLE ON UPPER SKIN AT RIB 11-

Part: SKIN — CRACKED (LT WING TE FLAP) · airframe 38,767 hrs · 21,402 cycles

1EA CRACK (75MM) WAS FOUND AT LH WING CENTER FLAP RIB20 AFT AREA OF TOP SURFACE RIB FLANGE. ACCOMPLISHED THE FLANGE REPAIR AT RIB 20 BETWEEN UPPER SKIN S-2.8 TO REAR SPAR AND EXTERNAL DOUBLER REPAIR ENCLOSED BY LOWER SKIN RIB 19 TO RIB 20 AND S-2.1 TO REAR SPAR. THE REPAIR CLASSIFIED AS CAT.A MAJOR PER GMM 6-2-100 I.A.W FEDEX EA NO:T6-5750- T0378801 P1, SEQ NO:1119, TITLE: WINGS-FLIGHT SURFACES-LH CENTER FLAP-CRACKS IN UPPER FLANGES OF RIBS 11,12,13,20,25 AND 26, WITH OVERSIZED HOLE ON UPPER SKIN AT RIB 11-

Part: SUPPORT BRACKET — CRACKED (LT MLG WW) · airframe 38,767 hrs · 21,402 cycles

LH LANDING GEAR DOOR OPEN ON GROUND PANEL INSIDE FWD SUPPORT BRACKET CRACK AT FR43, S-51L POSITION REPLACED THE DAMAGE SUPPORT WITH NEW AT FR43, S-51L I.A.W A300-600F SRM 51-72-10-001, PAGE.2 AND 51-40-21-001, PARA.7, PAGE.24-50 REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100

Part: SKIN — CRACKED (LT TE FLAP) · airframe 38,767 hrs · 21,402 cycles

3EA CRACKS (MAX70MM) WERE FOUND AT LH WING FLAP OF CENTER RIB12 AFT AREA OF TOP SURFACE RIB FLANGE. ACCOMPLISHED THE FLANGES REPAIR AT RIB12 UPPER FLANGE S-2.7~REAR SPAR, THE REPAIR CLASSIFIED AS CAT.A MAJOR PER GMM 6-2-100 I.A.W FEDEX EA NO:T6-5750-T0378801 P1, SEQ NO:1119, TITLE: WINGS-FLIGHT SURFACES-LH CENTER FLAP-CRACKS IN UPPER FLANGES OF RIBS 11,12,13,20,25 AND 26, WITH OVERSIZED HOLE ON UPPER SKIN AT RIB 11-

Part: PLATE — CRACKED (FRM 21 S43L) · airframe 38,767 hrs · 21,402 cycles

FWD CGO COMP'T UNDER FLOOR AREA LH SIDE PLATE CRACK AT S-43L~S-44L, FR21 POSITION. REPLACED THE SIDE PLATE WITH NEW PART AT FR21 AND S-43L~44L, I.A.W A300-600F SRM 51-72- 10-001, PAGE 2 & 51-40-21-001, PARA 6~7, PAGE 7B~50. REPAIR CLASSIFIED AS MINOR PER GMM 6- 2-100.

Part: SKIN — DAMAGED (RT ELEVATOR) · airframe 38,767 hrs · 21,402 cycles

1EA WATER TRAPPED AREA(70MM X 150MM) WAS FOUND AT R/H ELEVATOR UPPER SKIN PANEL T/E NO.9 SCREW AREA. ACCOMPLISHED THE CAT.A MAJOR COMPOSITE REPAIR AT RH ELEVATOR UPPER SKIN PANEL NO.9 T/E SCREW PER GMM 6-2-100 I.A.W A300-600F SRM 55-21-12-201, PARA 5J, PAGE268-274, FIG 212 (SHEET-2)

Part: SKIN — DAMAGED (RT ELEVATOR) · airframe 38,767 hrs · 21,402 cycles

1EA WATER TRAPPED AREA(110MM X 250MM) WAS FOUND AT R/H ELEVATOR UPPER SKIN PANEL T/E NO.25 SCREW AREA. ACCOMPLISHED THE CAT.A MAJOR COMPOSITE REPAIR AT RH ELEVATOR UPPER SKIN PANEL NO.25 T/E SCREW PER GMM 6-2-100 I.A.W A300-600F SRM 55-21-12-201, PARA 5J, PAGE268-274, FIG 212 (SHEET-2)

Part: SKIN — DAMAGED (RT ELEVATOR) · airframe 38,767 hrs · 21,402 cycles

1EA WATER TRAPPED AREA(110MM X 150MM) WAS FOUND AT R/H ELEVATOR UPPER SKIN PANEL T/E NO.26 SCREW AREA. ACCOMPLISHED THE CAT.A MAJOR COMPOSITE REPAIR AT RH ELEVATOR UPPER SKIN PANEL NO.26 T/E SCREW PER GMM 6-2-100 I.A.W A300-600F SRM 55-21-12-201, PARA 5J, PAGE268-274, FIG 212 (SHEET-2)

Part: SEAT TRACK — GOUGED (FRM 28) · airframe 38,767 hrs · 21,402 cycles

MAIN DECK FLOOR - SEAT TRACK CROWN AREA GOT A GOUGE LOCATION AT FR28 PLUS 3" AND - Y953 ACCOMPLISHED THE CAT.A MAJOR SEAT TRACK SPLICE REPAIR PER GMM 6-2-100 AT MAIN DECK FR 28 AND -Y953 IAW SRM 53-10-16-201, PARA.4, PAGE 203-208, FIG 201.

Part: SEAT TRACK — GOUGED (FRM 50) · airframe 38,767 hrs · 21,402 cycles

MAIN DECK FLOOR - SEAT TRACK CROWN AREA GOT SOME GOUGES LOCATION FROM FR50 TO FR50 PLUS 3" AND Y0 ACCOMPLISHED THE MAIN DECK SEAT TRACK SPLICE REPAIR AT FR49~FR54 Y0, THE REPAIR CLASSIFIED AS CAT.A MAJOR REPAIR PER GMM 6-2-100 I.A.W FEDEX EA:T6-5310-T0378817 P1, SEQ NO:1112, TITLE: FUSELAGE-MAINFRAME-MAIN CARGO SEAT TRACK SPLICE REPAIR BETWEEN FR49 AND FR50 AT Y0 & A300-600F SRM 53-10-16-201, PARA.4, FIG.201, PAGE.203~208 (THE ATA CODE TYPO IN THIS SDR; CREATE THE NEW ONE NO:24-0546)

Part: SEAT TRACK — GOUGED (FRM 50) · airframe 38,767 hrs · 21,402 cycles

MAIN DECK FLOOR - SEAT TRACK CROWN AREA GOT SOME GOUGES LOCATION FROM FR50 TO FR50 PLUS 3" AND Y0 ACCOMPLISHED THE MAIN DECK SEAT TRACK SPLICE REPAIR AT FR49~FR54 Y0, THE REPAIR CLASSIFIED AS CAT.A MAJOR REPAIR PER GMM 6-2-100 I.A.W FEDEX EA:T6-5310-T0378817 P1, SEQ NO:1112, TITLE:FUSELAGE-MAINFRAME-MAIN CARGO SEAT TRACK SPLICE REPAIR BETWEEN FR49 AND FR50 AT Y0 & A300-600F SRM 53-10-16-201, PARA.4, FIG.201, PAGE.203~208

Part: SUPPORT — CRACKED (E/E BAY) · airframe 38,767 hrs · 21,402 cycles

AVIONICS COMP'T ACCESS DOOR OMEGA STOP FITTING CRACK AT FR6 POSITION. REPLACED THE DAMAGE STOP FITTING WITH NEW PART. AT AVIOICS ACCESS DOOR I.A.W A300-600F SRM 51-72-10-001 PAGE2. THIS REPAIR IS CLASSIFIED AS MINOR PER GMM 6-2-100 (AT FR 6, Y0)

Part: SEAT TRACK — CRACKED (FRM 10) · airframe 38,767 hrs · 21,402 cycles

AVIONICS COMP'T UNDER FLIGHT DECK SEAT TRACK ANGLE CRACK AT FR10 ,Y953 POSITION. REPLACED THE ANGLE FITTING WITH NEW ONE IAW A300-600F SRM 51-72-10-001 PAGE2 THE REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100 AT FR10 ,Y953

Part: ADAPTER — GOUGED (ZONE 200) · airframe 38,767 hrs · 21,402 cycles

MAIN DECK FLOOR CLS ADAPTER CROWN GOUGE AT FR61 Y1566 REPLACED THE DAMAGE ADAPTER WITH NEW ONE AND INSTALLED WITH FASTENERS AT MAIN DECK FR61 Y1566, THE REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100 I.A.W A300-600F SRM 51- 72-10-001, PAGE 2 &51-40-21-001, PARA 7, PAGE149-156

Part: ADAPTER — GOUGED (ZONE 200) · airframe 38,767 hrs · 21,402 cycles

MAIN DECK FLOOR CLS ADAPTER CROWN GOUGE AT FR57.2 Y1736 AT F57.2 Y1736 DAMAGED ADAPTER REPLACED NEW PART,INSTALLED WITH FASTENERS.IAW A300- 600F SRM51-40-21 PARA7-PAGE24-50 AND 51-72-10-001.PAGE 2 THIS REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100.

Part: ADAPTER — GOUGED (ZONE 200) · airframe 38,767 hrs · 21,402 cycles

MAIN DECK FLOOR CLS ADAPTER CROWN GOUGE AT FR59 Y1736 REPLACED THE DAMAGE ADAPTER WITH NEW ONE AND INSTALLED WITH FASTENERS AT MAIN DECK FR59 Y1736, THE REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100 I.A.W A300-600F SRM 51- 72-10-001, PAGE 2 AND 51-40-21-001, PARA 7, PAGE24-50.

Part: FITTING — CRACKED (MDC DOOR) · airframe 38,767 hrs · 21,402 cycles

THE MDC DOOR ACTUATOR YOKE FWD SUPPORT FRAME WAS FOUND CRACK ACCOMPLISHED THE REPLACEMENT OF BEARING FITTING AT MAIN DECK CARGO DOOR FR23 LONGN1~LONGN3 I.A.W FEDEX EA NO:T6-5230-T0378797 P1, SEQ NO:1121, TITLE:DOORS-CARGO DOOR /HYD SYS-MAIN CARGO ACTUATOR BEARING FITTING REPLACEMENT (FWD AND AFT), THE REPAIR CLASSIFIED AS CAT.A MAJOR PER GMM 6-2-100

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 37,998 hrs · 20,947 cycles

PDIS 661 29-01 5576 30JUN23 MEM FACT U GREEN RESERVOIR OVERHEAT WARNING DURING CLIMB OUT. FOLLOWED THE ECAM AND QRH PROCEDURES. GRAVITY EXTENDED GEAR AND NO NOSE WHEEL STEERING AS A RESULT. OVERSPEED THE KRUGER FLAP AS A RESULT OF BEING ABOVE 300 AND .65 MACH AT THE TIME OF THE FAILURE. KRUGER FLAP WAS OVERSPEND UNTIL WE DESCENDED THROUGH FL 240 IN ORDER TO SLOW BELOW .65 MACH. OVERHEAT LIGHT EXTINGUISHED MOMENTARILY AFTER GRAVITY EXTENSION AND THEN CAME BACK ON UNTIL 10 MINUTES AFTER ENGINE SHUTDOWN.

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 37,990 hrs · 20,942 cycles

GREEN RESERVOIR OVERHEAT WARNING DURING CLIMB OUT. FOLLOWED ECAM & QRH PROCEDURES. GRAVITY EXTENDED GEAR & NO NOSE WHEEL STEERING AS A RESULT. OVERSPEED KRUGER FLAP AS A RESULT OF BEING ABOVE 300 & .65 MACH AT THE TIME OF FAILURE. KRUGER FLAP WAS OVERSPEND UNTIL DESCENDED THROUGH FL 240 IN ORDER TO SLOW BELOW .65 MACH. OVERHEAT LIGHT EXTINGUISHED MOMENTARILY AFTER GRAVITY EXTENSION & CAME BACK ON UNTIL 10 MINS AFTER ENGINE SHUTDOWN. CHECK WRI 29-11/5578 FOR #1 ENGINE GREEN EDP R/R. COMPLETED TSI STEPS 2 & 5. SEE WRI 29-11/5578. R & R #1 ENG GREEN SYS EDP IAW AMM 29-11-32-04-02. OPS & LEAK CHECK PASSED. COLLECTED HYD SAMPLE FROM GREEN SYS IAW AMM 12-32-29. FLUSHED GREEN HYD SYS & FOUND NO CLOGGING INDICATORS POPPED. NO CONTAMINATION FOUND IN GREEN SYS FILTERS. SERVICED GREEN HYD SYS TO TOP HAT. OPS & LEAK CHECK GOOD.

Part: SPOILER — FAULTED (NR 6) · airframe 37,341 hrs · 20,543 cycles

ON TAXI OUT THE NUMBER 6 SPLR FAULTED. RAN CHECK LIST. RESET CB. FAULT RETURNED. IAW AMM: 27-61-34-04, PERFORMED T/S IAW TSM27-61-00, NO BITE FAULT CODE DISPLAYED ON BOTH EFCU. UNABLE TO DUPLICATE SPOILER FAULT ON GROUND.HOWEVER, SWAPPED NR 1 EFCU WITH NR 2 EFCU FOR TROUBLESHOOTING IAW MM 27-61-34-04. FURTHER OPS TEST IAW MM 27-61-00, SATISFACTORY.

Part: SPOILER — FAULTED (NR 6) · airframe 37,341 hrs · 20,543 cycles

ON TAXI OUT THE NUMBER 6 SPLR FAULTED. RAN CHECK LIST. RESET CB. FAULT RETURNED. PERFORMED T/S PER A310 TSM27-61-00, NO BITE FAULT CODE DISPLAYED ON BOTH EFCU. UNABLE TO DUPLICATE SPOILER FAULT ON GROUND. SWAPPED NR 1 EFCU WITH NR 2 EFCU FOR TROUBLESHOOTING IAW MM 27-61-34-04. FURTHER OPS TESTED IAW MM 27-61-00, SATISFACTORY.

Part: NONE — NONE (N/A) · airframe 36,473 hrs · 20,002 cycles

UNABLE TO DISARM SLIDE L1 DOOR. FOUND FOREIGN DEBRIS NEAR GIRT BAR AT FLOOR ATTACHMENT. REMOVED DEBRIS. SLIDE ARM HANDLE NOW MOVES FREELY TO ARM AND DISARM POSITION PER MM 25-61-20-02. OK FOR SERVICE.

Part: SEAT TRACK — NONE (N/A) · airframe 36,108 hrs · 19,781 cycles

MAIN DECK FR20-FR21 Y1456 SEAT TRACK DEFORMED COMPLIED WITH EA: 6-5310-T0365068 P1. TITLE: FUSELAGE - MAINFRAME - MCD Y1456 SEAT TRACK BENT BETWEEN FR20 AND FR21 - REPAIR. REPAIRED THE MAIN DECK FR20-FR21 Y1456 DEFORMED SEAT TRACK. THIS IS A PERMANENT CATEGORY A REPAIR. MAJOR REPAIR IAW FEDEX GMM6-2-100.

Part: SEAT TRACK — NONE (N/A) · airframe 36,108 hrs · 19,781 cycles

MAIN DECK FR20-FR21 Y953 SEAT TRACK DEFORMED COMPLIED WITH EA: 6-5310-T0365066 P1. TITLE: FUSELAGE - MAINFRAME - MCD Y953 SEAT TRACK BENT BETWEEN FR20 AND FR21 - REPAIR. REPAIRED THE MAIN DECK FR20-FR21 Y953 DEFORMED SEAT TRACK. THIS IS A PERMANENT CATEGORY A REPAIR. MAJOR REPAIR IAW FEDEX GMM6-2-100.

Part: NONE — NONE (N/A) · airframe 36,108 hrs · 19,781 cycles

RH WING #5 SPOILER CENTER I/B HINGE ARM O/B SIDE FOUND DELAMINATION. SIZE: 25MM*20MM, DEPTH: 2.0MM COMPLIED WITH EA: 6-5750-T0364810 P1. TITLE: WING - FLIGHT SURFACES - RH 5# SPOILER CENTER HINGE ARM OUTSIDE SURFACE DELAMINATION. REPAIRED THE RH WING #5 SPOILER CENTER O/B HINGE ARM O/B SIDE DELAMINATION. THIS IS CATEGORY A REPAIR. MAJOR REPAIR IAW FEDEX GMM-2-100.

Part: NONE — NONE (N/A) · airframe 36,108 hrs · 19,781 cycles

LH WING #5 SPOILER CENTER O/B HINGE ARM O/B SIDE FOUND DELAMINATION. SIZE: 40MM*20MM, DEPTH: 1.0MM COMPLIED WITH EA: 6-5750-T0364812 P1. TITLE: WING - FLIGHT SURFACES - LH 5# SPOILER CENTER HINGE ARM OUTSIDE SURFACE DELAMINATION. REPAIRED THE LH WING #5 SPOILER CENTER O/B HINGE ARM O/B SIDE DELAMINATION. THIS IS CATEGORY A REPAIR. MAJOR REPAIR IAW FEDEX GMM-2-100.

Part: NONE — NONE (N/A) · airframe 36,108 hrs · 19,781 cycles

CENTER WING BOX - INSPECTION OF REAR SPAR AND BOTTOM PANEL AT JUNCTION WITH FUSELAGE FR47 RH SIDE, FASTENER "I" HOLE FOUND CRACK SIGNAL COMPLIED WITH EO 6-5710-E0342809 B P2 STEP 5.D-5.E. TITLE: WINGS - CENTER WING BOX - INSPECTION OF REAR SPAR AND BOTTOM PANEL AT JUNCTION WITH FUSELAGE. SB'S A300-57- 6049 R08, A300-57-6086 R07, A300-57-6121 IR & A300-57-6050 R03. REPAIRED THE CENTER WING BOX REAR SPAR AND BOTTOM PANEL AT JUNCTION WITH FUSELAGE FR47 RH SIDE,FASTENER "I" HOLE CRACK. THIS IS CATEGORY A REPAIR. MAJOR REPAIR IAW FEDEX GMM6-2-100.

Part: NONE — NONE (N/A) · airframe 36,108 hrs · 19,781 cycles

CENTER WING BOX - INSPECTION OF REAR SPAR AND BOTTOM PANEL AT JUNCTION WITH FUSELAGE FR47 LH SIDE, FASTENER "I" HOLE FOUND CRACK SIGNAL COMPLIED WITH EO 6-5710-E0342809 B P1 STEP 5.D-5.E. TITLE: WINGS - CENTER WING BOX - INSPECTION OF REAR SPAR AND BOTTOM PANEL AT JUNCTION WITH FUSELAGE. SB'S A300-57- 6049 R08, A300-57-6086 R07, A300-57-6121 IR & A300-57-6050 R03. REPAIRED THE CENTER WING BOX REAR SPAR AND BOTTOM PANEL AT JUNCTION WITH FUSELAGE FR47 LH SIDE, FASTENER "I" HOLE CRACK. THIS IS CATEGORY A REPAIR. MAJOR REPAIR IAW FEDEX GMM6-2-100.

Part: SKIN — GOUGED (RT WING TE FLAP) · airframe 35,870 hrs · 19,650 cycles

R/H I/B FLAP UPPER SURFACE IS GOUGED. COMPLIED WITH EA 6-2780-T0363087 L/E SLATS AND FLAPS REPAIR UPPER SKIN R/H INBD FLAP.

Part: SEAL — FAILED (DOOR EMER OPEN) · airframe 35,428 hrs · 19,360 cycles

MDIS 661 52-10 3182 DOOR 1L EMERGENCY OPERATION CYLINDER NITROGEN BOTTLE WILL NOT TAKE AIR. IT HAS A BLOWN DIAPHRAGM THAT NEEDS REPLACED PER AMM 52-10-14-03-02. REPLACED FWD DOOR DAMPER SEALS PERCUSSION MECHANISM DIAPHRAGM. REF. A300-600 M/M 52-10-14-03-2. OPS CHECKS GOOD. THIS CLEARED MEL.

Part: SMOKE DETECTOR — FALSE ACTIVATION (E/E BAY) · airframe 35,057 hrs · 19,132 cycles

AVIONICS SMOKE WARNING ON APPROACH INTO MEMPHIS MULTIPLE RESETS NO HELP SNIFFER FAN SHOWED NO SMOKE, QRH PROCEDURES, DECLARED EMERGENCY. CAPTAIN RAN BOTH ENGINES AND PRESSURIZED A/C, REF A300-600 AMM 21-31-00-05. DURING PRESSURIZATION SMELLED HYD FLUID. AFTER ENGINE SHUTDOWN AND PRESSURIZATION RECEIVED AVIONICS SMOKE WARNING, WOULD NOT CLEAR. ORDERED SMOKE DETECTORS AND COLESSER BAGS TO 843 LINESHACK. REMOVED AND REPLACED AVIONICS COMPARTMENT SMOKE DETECTORS 11WA AND 12WA, IAW AMM 26-15-12-04. OPERATIONS CHECK GOOD. PERFORMED CLEANING OF AIR CONDITIONING DUCTS, IAW AMM 21-51-00-03. NO DEFECTS NOTED.

Part: WINDOW — BURNED (COCKPIT) · airframe 35,016 hrs · 19,103 cycles

PDIS 661 56-10 2873 27OCT20 MEM OPEN U LOGPAGES:3227955 DURING DESCENT OBSERVED FLAMES ON LOWER LEFT CORNER OF FO WINDSHIELD (OUTSIDE). SHORTLY THEREAFTER FO WINDSHIELD CRACKED. FACT 27OCT20 19:16 MEM COMPLETED INSTALLATION AND SEALING OF RIGHT WINDSHIELD IAW A300-600MM 56-11-11-04. OPS CHECKS ARE GOOD

Part: UNKNOWN — ODOR (COCKPIT) · airframe 34,869 hrs · 19,011 cycles

DUSTY/METALLIC SMOKE SMELL IN COCKPIT DURING TAKEOFF ROLL UP TO 5000FT. AT THE SAME TIME THE AURAL ALTITUDE WARNING WAS CONSISTENTLY BLARING, THEN COMPLETELY STOPPED. NO AURAL WARNING ABOVE 20K. CREATED NEW WRI 22-XX-XXXX FOR ALTITUDE ALERT AURAL WARNING PORTION OF WRITE UP. OPERATED A/C PACKS AT VARIOUS TEMPS. CHECKED AVIONICS COMPARTMENT FOR ANY SIGNS OF BURNED MATERIAL, NO ODORS OR DAMAGE NOTED TO ANY EQUIPMENT. UNABLE TO REPRODUCE ANY SMELLS. A/C IS OKAY FOR SERVICE, PER STANDARD PRACTICES.

Part: FITTING — CRACKED (FUSELAGE) · airframe 33,475 hrs · 18,200 cycles

DURING PERFORMING ROTOTEST INSPECTION OF FRAME 40 TO CENTER WING JOINT AT UPPER SKIN LEVEL TENSION BOLT JUNCTION, RH UPPER HOLE FOUND CRACK SIGNAL COMPLIED WITH FEDEX EA: 6-5710-T0347502 PT1, EA TITLE: WINGS - BASIC WING STRUCTURE - CRACK IN THE UPPER HOLE AT FR40 RHS CENTER WING JOINT. REPAIRED THE FRAME 40 TO CENTER WING JOINT AT UPPER SKIN LEVEL TENSION BOLT JUNCTION, RH UPPER HOLE. THIS REPAIR CATEGORY "C". REPAIR LIFE LIMITATION: 6 MONTHS. MAJOR REPAIR IAW FEDEX GMM6-2-100.

Part: FITTING — CRACKED (ZONE 100) · airframe 33,475 hrs · 18,200 cycles

DURING PERFORMING ROTOTEST INSPECTION OF FRAME 40 TO CENTER WING JOINT AT UPPER SKIN LEVEL TENSION BOLT JUNCTION, LT MID HOLE FOUND CRACK SIGNAL COMPLIED WITH EA: 6-5710-T0347503 PT1, EA TITLE: WINGS - BASIC WING STRUCTURE - CRACK IN THE MIDDLE HOLE AT FR40 LHS CENTER WING JOINT. REPAIRED THE FRAME 40 TO CENTER WING JOINT AT UPPER SKIN LEVEL TENSION BOLT JUNCTION - LT MID HOLE. THIS REPAIR CATEGORY "C". REPAIR LIFE LIMITATION: 6 MONTHS. MAJOR REPAIR IAW GMM6-2-100.

Part: HINGE — DELAMINATED (LT SPOILER) · airframe 33,475 hrs · 18,200 cycles

SDI FOUND LT WING #3 SPOILER CENTER HINGE LOWER SURFACE FOUND DELAMINATION COMPLIED WITH EA: 6-5750-T0347580 PT1, EA TITLE: WING - FLIGHT SURFACES - LT 3# SPOILER CENTER HINGE ARM LOWER SURFACE DELAMINATION. REPAIRED LT WING #3 SPOILER CENTER HINGE ARM LOWER SURFACE. THIS REPAIR CATEGORY "A". MAJOR REPAIR IAW GMM6-2-100.

Part: SKIN — UNKNOWN

EXISTING REPAIR ON RH WING 1# SLAT LOWER SKIN BETWEEN RIB9 AND RIB10 REQUIRES EVALUATION FOR CONFORMITY THE EXISTING REPAIR ON RH WING 1# SLAT LOWER SKIN BETWEEN RIB9 AND RIB10 WAS EVALUATED AND FOUND NO REPAIR RECORD WAS AVAILABLE. THE EXISTING REPAIR PITCH WAS REMOVED AND REPAIRED THE SKIN ( RH WING 1# SLAT LOWER SKIN BETWEEN RIB9 AND RIB10 ) PER A300-600F SRM57-42-11 FIG.204. RSC TRACKING EA: 6-5750-T0347967 WAS ISSUED AND COMPLIED WITH FEDEX EA: 6-5750-T0347967 PT1, TITLE: WINGS - FLIGHT SURFACES - REPAIR TO LOWER SKIN FOR RH 1# SLAT AT RIB 9 / RIB 10 - RSC TRACKING. EO 6-5100-7-5000 D7 PT1 WAS COMPLETED. TITLE: STRUCTURES - REPAIR CATALOG - A300/A310 REPAIR IDENTIFICATION & TRACKING REQUIREMENTS 14 CFR 121.707. THE REPAIR WAS CATEGORY "B" AND WAS CLASSIFIED AS MAJOR PER GMM6-2-100.

Part: CROSSBEAM — CRACKED (FUSELAGE) · airframe 33,475 hrs · 18,200 cycles

EXISTING REPAIR ON MDCC CROSSBEAM AT FR28, BETWEEN Y-450 AND Y-953 REQUIRES EVALUATION FOR CONFORMITY THE EXISTING REPAIR ON MDCC CROSSBEAM AT FR28, BETWEEN Y-450 AND Y-953 WAS EVALUATED AND FOUND DID NOT CONFORMED TO PREVIOUS REPAIR RECORD. THE EXISTING REPAIR WAS REMOVED AND REPAIRED THE CROSSBEAM ( MDCC CROSSBEAM AT FR28, BETWEEN Y-450 AND Y-953 ) COMPLIED WITH EA: 6-5321-45406 A PT2, TITLE: FUSELAGE - MAINFRAME - REPAIR OF CRACKED MDCC CROSSBEAM STIFFENER AT FR28/Y-700 & FR30/Y-700. EO 6-5100-7-5000 D7 PT1 WAS COMPLETED. TITLE: STRUCTURES - REPAIR CATALOG - REPAIR IDENTIFICATION & TRACKING REQUIREMENTS 14 CFR 121.707. THE REPAIR WAS CATEGORY "A" AND WAS CLASSIFIED AS MAJOR PER GMM6-2-100.

Part: CROSSBEAM — CRACKED (FUSELAGE) · airframe 33,475 hrs · 18,200 cycles

EXISTING REPAIR ON MDCC CROSSBEAM AT FR30, BETWEEN Y-450 AND Y-953 REQUIRES EVALUATION FOR CONFORMITY THE EXISTING REPAIR ON MDCC CROSSBEAM AT FR30, BETWEEN Y-450 AND Y-953 WAS EVALUATED AND FOUND DID NOT CONFORMED TO PREVIOUS REPAIR RECORD. THE EXISTING REPAIR WAS REMOVED AND REPAIRED THE CROSSBEAM ( MDCC CROSSBEAM AT FR30, BETWEEN Y-450 AND Y-953 ) COMPLIED WITH EA: 6-5321-45406 A PT3, TITLE: FUSELAGE - MAINFRAME - REPAIR OF CRACKED MDCC CROSSBEAM STIFFENER AT FR28/Y-700 & FR30/Y-700. EO 6-5100-7-5000 D7 PT1 WAS COMPLETED. TITLE: STRUCTURES - REPAIR CATALOG - A300/A310 REPAIR IDENTIFICATION & TRACKING REQUIREMENTS 14 CFR 121.707. THE REPAIR WAS CATEGORY "A" AND WAS CLASSIFIED AS MAJOR PER GMM6-2-100.

Part: WEB — CRACKED (FRAME 47) · airframe 33,475 hrs · 18,200 cycles

MAIN DECK - UNDERFLOOR VERTICAL WEB CRACKED, AT FR47, BETWEEN Y953 AND Y1456 REPAIRED THE CRACKED VERTICAL WEB (MAIN DECK - UNDERFLOOR VERTICAL WEB, AT FR47, BETWEEN Y953 AND Y1456) PER A300-600F SRM53-15-15 FIGURE 201. THIS REPAIR CATEGORY "B". INSPECTION THRESHOLD FROM REPAIR EMBODIMENT 24000FC / FH NOT RELEVANT, SUBSEQUENT INSPECTION AT INTERVAL OF 3000FC / FH NOT RELEVANT. INSPECTION METHOD IS DETAILED VISUAL PER A300-600F SRI53-15-15-2-002-00. MAJOR REPAIR IAW GMM 6-2-100.

Part: STIFFENER — CORRODED (FRAMES 12-12A) · airframe 33,475 hrs · 18,200 cycles

LH LOWER FUSELAGE SKIN ATTACHED STIFFENER - FWD TOILET SERVICE PANEL FWD LWR CUTOUT CORRODED, BETWEEN FR12 AND FR12A

Part: WEB — CRACKED (FRAME 47) · airframe 33,475 hrs · 18,200 cycles

MAIN DECK - UNDERFLOOR VERTICAL WEB CRACKED, AT FR47, BETWEEN Y0 AND Y450 REPAIRED THE CRACKED VERTICAL WEB (MAIN DECK - UNDERFLOOR VERTICAL WEB, AT FR47, BETWEEN Y0 AND Y450) PER A300-600F SRM53-15-15 FIGURE 201. THIS REPAIR CATEGORY "B". INSPECTION THRESHOLD FROM REPAIR EMBODIMENT 24000FC / FH NOT RELEVANT, SUBSEQUENT INSPECTION AT INTERVAL OF 3000FC / FH NOT RELEVANT. INSPECTION METHOD IS DETAILED VISUAL PER A300-600F SRI53-15-15-2-002-00. MAJOR REPAIR IAW GMM6-2-100.

Part: WEB — CRACKED (FRAME 47) · airframe 33,475 hrs · 18,200 cycles

MAIN DECK - UNDERFLOOR VERTICAL WEB CRACKED, AT FR47, BETWEEN Y0 AND Y-450 REPAIRED THE CRACKED VERTICAL WEB (MAIN DECK - UNDERFLOOR VERTICAL WEB, AT FR47, BETWEEN Y0 AND Y-450) PER A300-600F SRM53-15-15 FIGURE 201. THIS REPAIR CATEGORY "B". INSPECTION THRESHOLD FROM REPAIR EMBODIMENT 24000FC / FH NOT RELEVANT, SUBSEQUENT INSPECTION AT INTERVAL OF 3000FC / FH NOT RELEVANT. INSPECTION METHOD IS DETAILED VISUAL PER A300-600F SRI53-15-15-2-002-00. MAJOR REPAIR IAW GMM6-2-100.

Part: FLOORBEAM — CRACKED (FRAME 32) · airframe 33,475 hrs · 18,200 cycles

MAIN DECK CARGO COMPARTMENT FLOOR STRUCTURE - CROSSBEAM CRACKED, AT FR32, BTW Y1456 AND Y1959 REPAIRED THE CRACKED CROSSBEAM (MAIN DECK CARGO COMPARTMENT FLOOR STRUCTURE - CROSSBEAM, AT FR32, BTW Y1456 AND Y1959) PER A300-600F SRM53-10-15-201 FIGURE 212. THIS REPAIR CATEGORY "A". MAJOR REPAIR IAW FEDEX GMM6-2-100.

Part: CROSSBEAM — CRACKED (FRAME 60) · airframe 33,475 hrs · 18,200 cycles

MAIN DECK CARGO COMPARTMENT FLOOR STRUCTURE - CROSSBEAM CRACKED, AT FR60, BTW Y-1456 AND Y-1959 REPAIRED THE CRACKED CROSSBEAM (MAIN DECK CARGO COMPARTMENT FLOOR STRUCTURE - CROSSBEAM, AT FR60, BTW Y-1456 AND Y-1959) PER A300-600F SRM53-10-15-201 FIGURE 211. THIS REPAIR CATEGORY "A". MAJOR REPAIR IAW FEDEX GMM6-2-100.

Part: FLOORBEAM — CRACKED (FRAME 27) · airframe 33,475 hrs · 18,200 cycles

MAIN DECK CARGO COMPARTMENT FLOOR STRUCTURE - CROSSBEAM CRACKED, AT FR27, BTW Y-450 AND Y-953 REPAIRED THE CRACKED CROSSBEAM IAW SRM 53-10-15-201 FIGURE 212. THIS REPAIR CATEGORY "A". MAJOR REPAIR IAW GMM 6-2-100.

Part: FRAME — DENTED (FRAME 58) · airframe 33,475 hrs · 18,200 cycles

MAIN DECK - FUSELAGE MAIN FRAME DEFORMED, AT FR58, BETWEEN STGR13L AND STGR14L REPAIRED THE DEFORMED FRAME(MAIN DECK - FUSELAGE MAIN FRAME, AT FR58, BETWEEN STGR13L AND STGR14L) PER A300-600F SRM53-10-13 FIGURE 202. THIS REPAIR CATEGORY "B". FIRST INSPECTION AFTER REPAIR EMBODIMENT 42500FC, SUBSEQUENT INSPECTIONS AT INTERVALS AND INSPECTION METHOD ARE TBD. PER SRI53-10-13-2-002-00. MAJOR REPAIR IAW GMM 6-2-100.

Part: FRAME — DENTED (FRAME 59) · airframe 33,475 hrs · 18,200 cycles

MAIN DECK - FUSELAGE MAIN FRAME DEFORMED, AT FR59, BETWEEN STGR13L AND STGR14L REPAIRED THE DEFORMED FRAME(MAIN DECK - FUSELAGE MAIN FRAME, AT FR59, BETWEEN STGR13L AND STGR14L) PER A300-600F SRM53-10-13 FIGURE 202. THIS REPAIR CATEGORY "B". FIRST INSPECTION AFTER REPAIR EMBODIMENT 42500FC, SUBSEQUENT INSPECTIONS AT INTERVALS AND INSPECTION METHOD ARE TBD. PER SRI53-10-13-2-002-00. MAJOR REPAIR IAW GMM6-2-100.

Part: FRAME — DENTED (FRAME 75) · airframe 33,475 hrs · 18,200 cycles

MAIN DECK - FUSELAGE MAIN FRAME DEFORMED, AT FR75, BETWEEN STGR10L AND STGR11L REPAIRED THE DEFORMED FRAME(MAIN DECK - FUSELAGE MAIN FRAME, AT FR75, BETWEEN STGR10L AND STGR11L) PER A300-600F SRM53-10-13 FIGURE 202. THIS REPAIR CATEGORY "B". FIRST INSPECTION AFTER REPAIR EMBODIMENT 42500FC, SUBSEQUENT INSPECTIONS AT INTERVALS AND INSPECTION METHOD ARE TBD PER SRI53-10-13-2-002-00. MAJOR REPAIR IAW GMM6-2-100.

Part: COUPLING — CHAFED (FUSELAGE) · airframe 33,475 hrs · 18,200 cycles

MAIN DECK - FUSELAGE MAINFRAME COUPLING CHAFFED, AT FR29, BETWEEN STR 12R AND STR 13R REPLACED THE MAINFRAME COUPLING (MAIN DECK - FUSELAGE MAINFRAME COUPLING, AT FR29, BETWEEN STR 12R AND STR 13R ) PER SRM51-40-21. THIS REPAIR CATEGORY "A". MAJOR REPAIR IAW GMM6-2-100.

Part: FLOORBEAM — CRACKED (FRAME 64) · airframe 33,475 hrs · 18,200 cycles

MAIN DECK CARGO COMPARTMENT FLOOR STRUCTURE - CROSSBEAM CRACKED, AT FR64, BTW Y-1456 AND Y-1959 REPAIRED THE CRACKED CROSSBEAM (MAIN DECK CARGO COMPARTMENT FLOOR STRUCTURE - CROSSBEAM, AT FR64, BTW Y-1456 AND Y-1959) PER SRM53-10-15 FIGURE 211. THIS REPAIR CATEGORY "A". MAJOR REPAIR IAW GMM6-2-100.

Part: FLOORBEAM — CRACKED (FRAME 66) · airframe 33,475 hrs · 18,200 cycles

MAIN DECK CARGO COMPARTMENT FLOOR STRUCTURE - CROSSBEAM CRACKED, AT FR66, BTW Y953 AND Y1456 REPAIRED THE CRACKED CROSSBEAM (MAIN DECK CARGO COMPARTMENT FLOOR STRUCTURE - CROSSBEAM, AT FR66, BTW Y953 AND Y1456) PER SRM53-10-15 FIGURE 211. THIS REPAIR CATEGORY "A". MAJOR REPAIR IAW GMM6-2-100.

Part: FLOORBEAM — CRACKED (FRAME 31) · airframe 33,475 hrs · 18,200 cycles

MAIN DECK CARGO COMPARTMENT FLOOR STRUCTURE - CROSSBEAM CRACKED, AT FR31, BTW Y1456 AND Y1959 REPAIRED THE CRACKED CROSSBEAM (MAIN DECK CARGO COMPARTMENT FLOOR STRUCTURE - CROSSBEAM, AT FR31, BTW Y1456 AND Y1959) PER SRM53-10-15-201 FIGURE 212. THIS REPAIR CATEGORY "A". MAJOR REPAIR IAW GMM6-2-100.

Part: FLOORBEAM — CRACKED (FRAME 64) · airframe 33,475 hrs · 18,200 cycles

MAIN DECK CARGO COMPARTMENT FLOOR STRUCTURE - CROSSBEAM CRACKED, AT FR64, BTW Y-953 AND Y-1456 REPAIRED THE CRACKED CROSSBEAM (MAIN DECK CARGO COMPARTMENT FLOOR STRUCTURE - CROSSBEAM, AT FR64, BTW Y-953 AND Y-1456) PER SRM 53-10-15 FIGURE 211. THIS REPAIR CATEGORY "A". MAJOR REPAIR IAW GMM 6-2-100.

Part: FLOORBEAM — CRACKED (FRAME 66) · airframe 33,475 hrs · 18,200 cycles

MAIN DECK CARGO COMPARTMENT FLOOR STRUCTURE - CROSSBEAM CRACKED, AT FR66, BTW Y-953 AND Y-1456 REPAIRED THE CRACKED CROSSBEAM (MAIN DECK CARGO COMPARTMENT FLOOR STRUCTURE - CROSSBEAM, AT FR66, BTW Y-953 AND Y-1456) PER SRM53-10-15 FIGURE 211. THIS REPAIR CATEGORY "A". MAJOR REPAIR IAW GMM6-2-100.

Part: GCU — MALFUNCTIONED (E&E BAY) · airframe 32,673 hrs · 17,760 cycles

OPERATING UNDER MEL 49-33-12 (NO APU GEN AVAILABLE) DURING TAKEOFF AT V1 FO PFD FLICKERED, ALT FLAT. AT APPROXIMATELY 1000 AGL GEN 2 FAULT AND AC BUS 2 FAIL ON ECAM AND OVERHEAD PANEL. GEN 2 DID NOT RESET AND COULD NOT POWER AC BUS 2. ATB TO KDEN. DURING ATB APPROXIMATELY 10 MINUTES AFTER FAILURE GEN 2 AND AC BUS 2 WAS POWERED AGAIN. NORMAL APPROACH AND LANDING KDEN. REMOVED AND REPLACED NR 2 GCU IAW AMM 24-22-12-04 MFG P/N 740120B S/N 1894. INSTALLED GCU MPN 764067A S/N A108. RAN BOTH ENGINES IAW JRH TRANSFERRED POWER BETWEEN NR 1 GEN AND NR 2 GEN SEVERAL TIMES NO FAULTS NOTED. CHECKED FOR WATER INTRUSION INTO E&E COMPT NO WATER FOUND.

Part: DETECTOR LOOP — MALFUNCTIONED (MAIN CARGO BAY) · airframe 32,460 hrs · 17,618 cycles

MAIN DECK CARGO SMOKE DETECTION LOOP TEST IS INOP. CYCLED DETECTION CONTROL C/B'S PER M/M 26-19-34-04. OP'S NORMAL.

Part: SMOKE DETECTOR — MALFUNCTIONED (E/E BAY) · airframe 31,180 hrs · 16,857 cycles

DURING TAKEOFF ROLL AT 50KIAS, AVIONICS SMOKE WARNING, REJECTED TAKE OFF, NO SMOKE ON SNIFFER FAN, RETURNED BACK TO GATE. REMOVED AND REPLACED AV3 SMOKE DETECTOR IAW AMM 26-15-12-04. OPS CHECKED GOOD.

Part: SMOKE WARNING — FALSE ACTIVATION (COCKPIT) · airframe 30,689 hrs · 16,569 cycles

DURING TAXI GOT MULTIPLE AVIONICS SMOKE WARNINGS WITH NO SMOKE SMELL . THE WARNING WOULD COME AND GO. DURING TAXI, RECEIVED MULTIPLE AVIONICS SMOKE WARNINGS, WITH NO SMOKE ODOR. THE WARNING WOULD COME & GO WORKED WITH MTSI 53-21/9289. WHILE ACCOMPLISHING MAIN CARGO DRAINAGE WORK CARD, FOUND ALL FUNNEL DRAINS & FUSELAGE VALVE BODY DIRTY & CLOGGED, CLEANED AND FLUSHED OUT DIRT AND WATER. REMOVED AND REPLACED 4 VALVE BODIES AND CLEANED 2 IAW AMM 51-80-21-06, FOUND EQUIP RACK 80VU PAN WITH WATER, CLEARED THE LINE AND DRAINED, ALSO FOUND AVIONICS COMP SMOKE DETECTOR FILLED WITH WATER, R & R THE SAME IAW AMM 26-15-12-04. OPERATIONAL TEST IS GOOD IAW AMM 26-15-00. ACFT OK FOR SERVICE.

Part: RIB — DAMAGED (RT NR1 SLAT) · airframe 30,209 hrs · 16,293 cycles

RIGHT NR 1 SLAT DAMAGED AT INBD END, INCLUDING THE RIB AND SEAL RETAINER. ACCOMPLISHED EA 6-5750-T0330232. MAJOR REPAIR

Part: SPAR — CRACKED (NR 1 PYLON) · airframe 30,203 hrs · 16,288 cycles

NR 1 PYLON ACCESSED THROUGH PANEL 411CL LOWER SPAR OF CANTILEVER STRUCTURE IS CRACKED. REPAIRED IAW SRM 54- 52-11 FIG 201. MAJOR REPAIR.

Part: SPAR — CRACKED (NR 2 PYLON) · airframe 30,203 hrs · 16,288 cycles

NR 2 PYLON LOWER SPAR OF CANTILEVER STRUCTURE IS CRACKED BETWEEN RIBS 8-11. REPAIRED NR 2 PYLON LOWER SPAR IAW SRM 54-52-11 FIG 201. MAJOR REPAIR.

Part: CARGO TRACK — DAMAGED (FRAMES 45-54) · airframe 30,203 hrs · 16,288 cycles

MAIN CARGO DECK LT SIDE FRAMES 47 TO 48, Y1456 CARGO TRACK HAS DAMAGE TO CROWN AREA. REMOVED AND REPLACED THE CARGO TRACK IAW SRM 53-15-16 AND SRM 51-40-21. MAJOR REPAIR

Part: FLOOR SUPPORT — CORRODED (MAIN DECK) · corrosion level 2 · airframe 30,203 hrs · 16,288 cycles

MAIN DECK BETWEEN FRAMES 12 AND 13 FLOOR SUPPORT Y1456 CORRODED. REMOVED AND REPLACED THE FLOOR SUPPORT IAW SRM 51-40-21. MAJOR REPAIR.

Part: FLOOR PANEL — DAMAGED (AFT CARGO) · airframe 30,203 hrs · 16,288 cycles

AFT CARGO FLOOR PANEL 152XF DAMAGED. FABRICATED A NEW FLOOR PANEL IAW SRZ-25-005. MAJOR REPAIR.

Part: FLOOR SUPPORT — CORRODED (MAIN DECK) · corrosion level 2 · airframe 30,203 hrs · 16,288 cycles

MAIN DECK BETWEEN FRAMES 11 AND 13, FLOOR SUPPORT Y953 CORRODED. REMOVED AND REPLACED THE FLOOR SUPPORT IAW SRM 51-40-21. MAJOR REPAIR

Part: FLOOR PANEL — BROKEN (CABIN) · airframe 30,203 hrs · 16,288 cycles

MAIN CABIN FLOOR PANEL 252VF BROKEN. FABRICATED FLOOR PANEL 252VF IAW DWG SRZ-25-005 CAT "A" MAJOR REPAIR

Part: FLOOR PANEL — BROKEN (CABIN) · airframe 30,203 hrs · 16,288 cycles

MAIN CABIN FLOOR PANEL 261QF BROKEN. FABRICATED FLOOR PANEL 261QF IAW DWG SRZ-25-005 CAT "A" MAJOR REPAIR

Part: DECK PLATE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 30,203 hrs · 16,288 cycles

MAIN DECK FROM FR30 TO FR31 BETWEEN SEAT TRACK -Y2462 AND -Y1959 DECK PLATE UPPER SURFACE CORRODED. REMOVED AND REPLACED DECK PLATE BETWEEN -Y2462 AND -Y1959, FR30 AND FR31 IAW SRM 51-40-21. MAJOR REPAIR

Part: FLOOR PANEL — CRACKED (AFT CARGO) · airframe 30,203 hrs · 16,288 cycles

AFT CARGO FLOOR PANEL 152TF CRACKED. A NEW FLOOR PANEL WAS FABRICATED IAW SRZ-25-005. MAJOR REPAIR.

Part: FLOOR PANEL — CRACKED (AFT CARGO) · airframe 30,203 hrs · 16,288 cycles

AFT CARGO FLOOR PANEL 152MF CRACKED. A NEW FLOOR PANEL WAS FABRICATED IAW SRZ-25-005. MAJOR REPAIR.

Part: SEAT TRACK — WORN (FRAMES 58-60) · airframe 30,203 hrs · 16,288 cycles

AFT MAIN DECK BETWEEN FRAMES 58 AND 59 SEAT TRACK Y 0 CROWN AREA LUG WORN. FOUND IT TO BE OUT OF LIIMITS IAW SRM 53-10-16 FIG 102. REPAIRED THE SEAT TRACK IAW SRM 53-10-16 FIG 201. MAJOR REPAIR.

Part: FLOOR PANEL — CRACKED (AFT CARGO) · airframe 30,203 hrs · 16,288 cycles

AFT CARGO FLOOR PANEL 152SF CRACKED. A NEW FLOOR PANEL WAS FABRICATED IAW SRZ-25-005. MAJOR REPAIR.

Part: FLOOR PANEL — CRACKED (AFT CARGO) · airframe 30,203 hrs · 16,288 cycles

AFT CARGO FLOOR PANEL 152PF CRACKED. A NEW FLOOR PANEL WAS FABRICATED IAW SRZ-25-005. MAJOR REPAIR.

Part: FLOOR PANEL — CRACKED (AFT CARGO) · airframe 30,203 hrs · 16,288 cycles

AFT CARGO FLOOR PANEL 152WF CRACKED. A NEW FLOOR PANEL WAS FABRICATED IAW SRZ-25-005. MAJOR REPAIR.

Part: FLOOR PANEL — CRACKED (AFT CARGO) · airframe 30,203 hrs · 16,288 cycles

AFT CARGO FLOOR PANEL 152QF CRACKED. A NEW FLOOR PANEL WAS FABRICATED IAW SRZ-25-005.

Part: FLOOR PANEL — CRACKED (FWD CARGO BAY) · airframe 30,203 hrs · 16,288 cycles

FWD CARGO FLOOR PANEL 131SG CRACKED. A NEW FLOOR PANEL WAS FABRICATED IAW SRZ-25-005. MAJOR REPAIR.

Part: FLOOR PANEL — CRACKED (FWD CARGO) · airframe 30,203 hrs · 16,288 cycles

FWD CARGO FLOOR PANEL 131NG CRACKED. A NEW FLOOR PANEL WAS FABRICATED IAW SRZ-25-005. MAJOR REPAIR.

Part: FLOOR PANEL — CRACKED (FWD CARGO) · airframe 30,203 hrs · 16,288 cycles

FWD CARGO FLOOR PANEL 131PG CRACKED. A NEW FLOOR PANEL WAS FABRICATED IAW SRZ-25-005. MAJOR REPAIR.

Part: FLOOR PANEL — CRACKED (FWD CARGO) · airframe 30,203 hrs · 16,288 cycles

FWD CARGO FLOOR PANEL 132NG CRACKED, A NEW FLOOR PANEL WAS FABRICATED IAW SRZ-25- 005. MAJOR REPAIR.

Part: DECK PLATE — CORRODED (FRAMES 25-27) · corrosion level 2 · airframe 30,203 hrs · 16,288 cycles

MAIN DECK FROM FRAMES 25 AND 27 AND BETWEEN SEAT TRACK Y450 AND Y953. DECK PLATE UPPER SURFACE CORRODED. REMOVED COROSION IAW SRM 51-74-10. CHECKED LIMITS AND FOUND TO BE OUT OF LIMITS IAW SRM 51-73-11. REMOVED AND REPLACED THE DECK PLATE IAW SRM 53-13-15. MAJOR REPAIR.

Part: FLOOR PANEL — CRACKED (FWD CARGO) · airframe 30,203 hrs · 16,288 cycles

FWD CARGO FLOOR PANEL 132SG CRACKED. FABRICATED A NEW FLOOR PANEL IAW SRZ-25-005. MAJOR REPAIR.

Part: FLOOR PANEL — CRACKED (FWD CARGO) · airframe 30,203 hrs · 16,288 cycles

FWD CARGO FLOOR PANEL 131LG CRACKED. A NEW FLOOR PANEL WAS FABRICATED IAW SRZ-25-005. MAJOR REPAIR.

Part: FLOOR PANEL — CRACKED (FWD CABIN) · airframe 30,203 hrs · 16,288 cycles

FWD CARGO FLOOR PANEL 131QG CRACKED. A NEW FLOOR PANEL WAS FABRICATED IAW SRZ-25-005. MAJOR REPAIR.

Part: FLOOR PANEL — CRACKED (FWD CARGO) · airframe 30,203 hrs · 16,288 cycles

FWD CARGO FLOOR PANEL 132RG CRACKED FABRICATED A NEW FLOOR PANEL IAW SRZ-25-005. MAJOR REPAIR.

Part: CARGO TRACK — CORRODED (FRAMES 45-50) · corrosion level 2 · airframe 30,203 hrs · 16,288 cycles

MAIN CARGO DECK LT SIDE FRAMES 45 TO 50 Y450 OTBD LIP OF CARGO TRACK HAS SLIGHT SCRATCHES. REMOVED AND REPLACED THE CARGO TRACK IAW SRM 53-15-16 AND SRM 51-40-21. CARGO TRACK FOUND OUT OF LIMITS IAW SRM 53-10-16 PG 105. MAJOR REPAIR.

Part: FLOOR PANEL — PUNCTURED (CARGO) · airframe 30,203 hrs · 16,288 cycles

BULK CARGO FLOOR PANEL 161GF HAD MULTIPLE PUNCTURES. A NEW FLOOR PANEL WAS FABRICATED IAW SRZ-25-005. MAJOR REPAIR.

Part: FLOOR PANEL — CRACKED (FWD CARGO) · airframe 30,203 hrs · 16,288 cycles

FWD CARGO FLOOR PANEL 132PG CRACKED. A NEW FLOOR PANEL WAS FABRICATED IAW SRZ-25-005. MAJOR REPAIR.

Part: FLOOR PANEL — CRACKED (FWD CARGO) · airframe 30,203 hrs · 16,288 cycles

FWD CARGO FLOOR PANEL 132QG CRACKED. A NEW FLOOR PANEL WAS FABRICATED IAW SRZ-25-005. MAJOR REPAIR.

Part: FLOOR PANEL — DAMAGED (AFT CARGO) · airframe 30,203 hrs · 16,288 cycles

AFT CARGO FLOOR PANEL 152XF SEVERELY DAMAGED. FABRICATED A NEW FLOOR PANEL IAW SRZ-25-005. MAJOR REPAIR.

Part: FLOOR PANEL — BROKEN (MAIN DECK) · airframe 30,203 hrs · 16,288 cycles

MDCC FLOOR PANEL 242GF BROKEN. FABRICATED A NEW FLOOR PANEL IAW DWG SRZ-25-005. MAJOR REPAIR.

Part: FLOOR PANEL — BROKEN (MAIN DECK) · airframe 30,203 hrs · 16,288 cycles

MDCC FLOOR PANEL 251NG BROKEN. FABRICATED A NEW FLOOR PANEL IAW DWG SRZ-25-005. MAJOR REPAIR.

Part: FLOOR PANEL — BROKEN (MAIN DECK) · airframe 30,203 hrs · 16,288 cycles

MDCC FLOOR PANEL 231VG IS BROKEN. FABRICATED A NEW FLOOR PANEL IAW DWG SRZ-25-005. MAJOR REPAIR.

Part: FLOOR PANEL — BROKEN (MAIN DECK) · airframe 30,203 hrs · 16,288 cycles

MDCC FLOOR PANEL 241SJ IS BROKEN. FABRICATED A NEW FLOOR PANEL IAW DWG SRZ-25-005. MAJOR REPAIR.

Part: FLOOR PANEL — DAMAGED (AFT CARGO) · airframe 30,203 hrs · 16,288 cycles

AFT CARGO FLOOR PANEL 151MF DAMAGED. FABRICATED A NEW FLOOR PANEL IAW SRZ-25-005. MAJOR REPAIR.

Part: FLOOR PANEL — DAMAGED (MAIN DECK) · airframe 30,203 hrs · 16,288 cycles

MDCC FLOOR PANEL 251RG BROKEN. FABRICATED FLOOR PANEL IAW DWG SRZ-25-005. MAJOR REPAIR

Part: FLOOR PANEL — DAMAGED (AFT CARGO) · airframe 30,203 hrs · 16,288 cycles

AFT CARGO FLOOR PANEL 151SF CORNER DAMAGED. FABRICATED A NEW FLOOR PANEL IAW SRZ-25-005. MAJOR REPAIR.

Part: FLOOR PANEL — DAMAGED (AFT CARGO) · airframe 30,203 hrs · 16,288 cycles

AFT CARGO BAY FLOOR PANEL 151QF SEVERELY DAMAGED. FABRICATED A NEW FLOOR PANEL IAW SRZ-25-005. MAJOR REPAIR.

Part: FLOOR PANEL — DAMAGED (MAIN DECK) · airframe 30,203 hrs · 16,288 cycles

MDCC FLOOR PANEL 232WG BROKEN. FABRRICATED A NEW FLOOR PANEL IAW DWG SRZ-25-005. MAJOR REPAIR.

Part: FLOOR PANEL — BROKEN (MAIN DECK) · airframe 30,203 hrs · 16,288 cycles

MDCC FLOOR PANEL 242UJ BROKEN. FABRICATED A NEW FLOOR PANEL IAW DWG SRZ-25-005. MAJOR REPAIR.

Part: FLOOR PANEL — BROKEN (MAIN DECK) · airframe 30,203 hrs · 16,288 cycles

MDCC FLOOR PANEL 242LK BROKEN. FABRICATED A NEW FLOOR PANEL IAW DWG SRZ-25-005. MAJOR REPAIR.

Part: FLOOR PANEL — BROKEN (MAIN DECK) · airframe 30,203 hrs · 16,288 cycles

MDCC FLOOR PANEL 242GJ BROKEN. FABRICATED A NEW FLOOR PANEL IAW DWG SRZ-25-005. MAJOR REPAIR.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 29,845 hrs · 16,060 cycles

DAMAGED AT LOWER CORNER OF FUSELAGE AT FWD SIDE OF AFT CARGO DOOR FROM A PREVIOUS DOUBLER REPAIR.

Part: FMC — MALFUNCTIONED · airframe 29,179 hrs · 15,686 cycles

BOTH FMC'S FAULTED IN FLIGHT. NAV SCREENS WENT BLANK. HAD TO RESET FMC CB TO RESET IAW QRH. THE FLIGHT CREW PULLED & RESET THE FMS SUPPLY NR 1 CB'S TO SUCCESSFULLY RESTORE FMS OPERATION.

Part: DIAPHRAGM — LEAKING (R1 DOOR) · airframe 288 hrs · 15,514 cycles

R1 WAS DISARMED. ALARM SOUNDED WHEN DOOR BEGAN TO OPEN. SLIDE GIRT BAR ENGAGED, SLIDE DID NOT ACTIVATE, AS FIRST OFFICER KEPT DOOR FROM OPENING. DIAPHRAGM SEAL FOR DOOR OPENING ASSIST WAS PUNCTURED. R & R DOOR CYLINDER DIAPHRAGM IAW AMM 52-10-14-03-02, LEAK CHECKED GOOD. OPERATED DOOR & SLIDE ARMING SYS IAW AMM FUNCTIONAL TEST 52-10-30-05-02. OPERATIONS CHECKED GOOD.

Part: WIRE — DAMAGED · airframe 287 hrs · 15,459 cycles

DURING PREFLIGHT, NR 2 ENGINE, AGENT 1 INDICATES DISCHARGED. REMOVED CONNECTOR FROM DISCHARGE HEAD & REMOVED BONDING WIRE IAW AMM 26-21-15-04. REPLACED WIRES DK20-50, DK16-61 & DK16-62 IAW WDM 26-21-03 & ESPM 20-53-31.

Part: SMOKE DETECTOR — FALSE ACTIVATION (COCKPIT) · airframe 279 hrs · 15,045 cycles

AVIONICS SMOKE WARNING HORN & ECAM INDICATION JUST AFTER LEVEL OFF. NO SMOKE FROM SNIFFER FAM. NO SMOKE OR FIRE OBSERVED BY FIRE TRUCKS AFTER LANDING. REPEAT WRITE UP. REMOVED & REPLACED COCKPIT SMOKE DETECTOR 13WA IAW MM 26-15-12-04. OPERATIONS CHECKED GOOD IAW MM 26-15-00-05.

Part: SMOKE DETECTOR — MALFUNCTIONED (E/E BAY) · airframe 278 hrs · 15,030 cycles

AVIONICS SMOKE INDICATION AT 10,000'. R & R COCKPIT SMOKE DETECTOR 13WA IAW MM 26-15-12-04. OPS CHECKED GOOD IAW MM.

Part: CONTROL UNIT — MALFUNCTIONED (LANDING GEAR) · airframe 27,663 hrs · 14,914 cycles

ON TAKEOFF ROLL THE PLANE STARTED TO STEER LEFT. TRIED RT RUDDER & THEN TILLER, NO RESPONSE, REJECTED TAKEOFF. IAW AMM 32-51-00-5 OPERATION OF NOSE WHEEL STEERING WAS NORMAL. IAW TSM 32-42-00 BITE TESTED BSCU & RESET BSCU IAW AMM 32-42-00-5. VISUALLY VERIFIED OPERATION OF ANTI-SKID & TESTED ANTI-SKID FROM MTP & ALL WAS NORMAL. OK TO CONTINUE.

Part: FITTING — CRACKED (FUSELAGE) · airframe 27,209 hrs · 14,669 cycles

FOUND FUSELAGE CTR SECTION LOWER FRAMES FITTINGS BASE. FITTING CRACK ABOUT 0.500 INCHES AT FRAME 45. PERFORMED FRAME FEET MODIFICATION BTW STATION FRAME 41 & 46 IAW EO 6-5310-7-5015 01 PART 2. TITLE FUSELAGE, CTR WING, FRAME, FRAME FEET, FRAME 41 - 46, STRINGER 35 - 37. REPAIR WAS CLASSIFIED AS MAJOR IAW GMM 6-2-100.

Part: FITTING — CRACKED (FUSELAGE) · airframe 27,209 hrs · 14,669 cycles

FOUND FUSELAGE CTR SECTION LOWER FRAMES FITTINGS BASE. FITTING CRACK ABOUT 0.375 INCHES AT FRAME 46 POSITION. PERFORMED FRAME FEET MODIFICATION BTW STATION FRAME 41 & 46 IAW EO 6-5310-7-5015 01 PART 2. TITLE FUSELAGE CTR WING, FRAME, FRAME FEET, FRAME 41 THRU 46, STRINGER 35 THRU 37. REPAIR WAS CLASSIFIED AS MAJOR IAW GMM 6-2-100.

Part: DIAPHRAGM — PUNCTURED (R1 DOOR SLIDE) · airframe 26,910 hrs · 14,507 cycles

DURING ARMING R1 DOOR, TEST BUTTON WAS PUSHED & ALARM SOUNDED. HANDLE WAS PULLED UP & SLIDE DID NOT DEPLOY BUT FELL OUT BOTTOM OF DOOR WITH GIRT BAR ATTACHED TO FLOOR SEAL. PERFORMED ADJUSTMENT AND TEST OF EMERGENCY OPERATION BOTTLE. ALL INDICATIONS NORMAL AND WITHIN LIMITS IAW MM 52-10-14-05-02. REMOVED AND REPLACED R1 ESCAPE SLIDE IAW MM 25-61-21-04 AND REPLACED PUNCTURED DOOR BOTTLE DIAPHRAGM AND SERVICED DOOR ASSIT BOTTLE, IAW MM 52-10-14-03-02. NO LEAKS NOTED. ACFT OK FOR SERVICE.

Part: WINDSHIELD — CRACKED (COCKPIT) · airframe 25,252 hrs · 13,544 cycles

RIGHT WINDOW HEAT FAULT, SELECTED OFF IAW ECAM. ABOUT 1 MINUTE LATER RT WINDSHIELD CRACKED. WINDOW ON GROUND SEEMED WARMER THAN NORMAL BUT NOT EXCESSIVE OR HOT. R & R F/O'S WINDSHIELD PANELS IAW AMM 56-11-11-04. PRECAUTIONARY, REPLACED WINDOW HEAT PROTECTION CONTROLLER IAW AMM 30-42-51-04. OPS CHECK CARRIED OUT IAW AMM 30-42-00 P BLOCK 501, SATISFACTORY.

Part: SLIDE — MALFUNCTIONED (R1 DOOR) · airframe 25,052 hrs · 13,443 cycles

RIGHT DOOR DOES NOT INDICATE "SLIDE" WHEN DOOR CLOSE AND ARMED. WHILE MX WAS WORKING ON THE RT DOOR "SLIDE" INDICATION, OPEN DOOR AND THE SLIDE FELL OUT OF THE DOOR. DOOR HAD BEEN ARMED. R & R DUAL ESCAPE SLIDE IAW AMM 25-61-21-04. ACFT OK FOR SERVICE. REPLACED ASPSU AND BOTH BATTERIES IAW AMM 52-73-18-04. BATTERY NR 1 FAILS BITE TEST. REINSTALLED 1 OF THE ORIGINAL BATTERIES AND BITE TEST GOOD. BOTH LT AND RT DOOR SLIDE ARMING FUNCTIONS TEST NORMAL IAW AMM 52-73-13-05.

Part: FITTING — CORRODED (ZONE 500) · corrosion level 2 · airframe 24,712 hrs · 13,284 cycles

RIB 5 FWD LUG CORRODED. REPAIRED IAW EA 6-5740-149059.

Part: SEAT TRACK — CORRODED (MAIN DECK) · corrosion level 2 · airframe 24,712 hrs · 13,284 cycles

CENTER MAIN DECK, FOUND RT 5TH SEAT TRACK CORROSION AREA FROM FR45 TO 54 AT -Y1959 POSITION. FABRICATE AND R & R THE SEAT TRACK IAW DWG NR A53813618 AND AB6F SRM 51-40-21. REINSTALLED THE CROSSBEAMS OF FR45-FR54 -Y1959 WITH CHECK OK FOR SERVICE IAW AMM 20-21-12 IAW GMM 6-2-100 REPAIR CLASSIFIED AS MAJOR.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 24,712 hrs · 13,284 cycles

FWD CARGO COMPT CEILING AREA OF M/D FLOORBEAM RT SIDE EDGE AREA GOT CRACK AT FR29 POSITION. REPAIRED IAW EA 6-5310-149065 WITH AB6F SRM 53-10-15. THE REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100.

Part: ADAPTER — DAMAGED (MAIN DECK) · airframe 24,712 hrs · 13,284 cycles

AFT MAIN DECK COMPT FLOOR LEVEL AREA FOUND CROSSBEAM FITTED WITH CARGO LOADING SYSTEM ADAPTER HAS EXCESS CHAFED MARKS ON CROWN AREA LOCATION AT FR58/BETWEEN Y1456 AND Y1959. TRANSFER THE HOLE FROM OLD PART TO NEW PART AND R/R ADAPTER BY FASTENER IAW SRM 51-72-10 & 51-40-21. EVALUATE THE REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100.

Part: COVER — CRACKED (LT WING) · airframe 24,712 hrs · 13,284 cycles

LT WING T/E FOUND 1EA COVER CRACKED POSITION NEAR LT MAIN LT MLG AFT TRUNNION INBD SIDE. REMOVED COVER FOR FABRICATION IAW DWG A57240775 THEN REPLACED IAW SRM 51-72-10 & 51-40-21. INSTALLED COVER AND CONDITION CHECKED GOOD. REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100.

Part: FLOOR PANEL — DAMAGED (FWD CARGO BAY) · airframe 24,712 hrs · 13,284 cycles

FWD CARGO FLOOR PANEL 131QG EDGE AREA HAS IMPACT DAMAGE. FABRICATED A NEW FLOOR PANEL IAW SRM 53-10-20. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: FLOOR PANEL — DAMAGED (MAIN DECK) · airframe 24,712 hrs · 13,284 cycles

CENTER MAIN DECK FLOOR PANEL 242EJ HAS INSERT DAMAGE.

Part: FLOOR PANEL — DAMAGED (CARGO BAY) · airframe 24,712 hrs · 13,284 cycles

CARGO BAY 162DF FLOOR PANEL EDGE AREA HAS IMPACT DAMAGE. FABRICATED NEW FLOOR PANEL IAW SRM 53-10-20. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: FLOOR PANEL — CORRODED (CARGO BAY) · airframe 24,712 hrs · 13,284 cycles

CARGO BAY 162HF FLOOR PANEL INNER SURFACE CORRODED. REMOVED FLOOR PANEL IAW AMM 53-10-35-04. FABRICATE A NEW FLOOR PANEL IAW SRM 53-10-20 & DWR.A53279962. INSTALLED FLOOR PANEL IAW AMM 53-10-35-04. PER GMM 6-2-100 REPAIR CLASSIFIED AS MAJOR.

Part: FLOOR PANEL — DEBONDED (CARGO BAY) · airframe 24,712 hrs · 13,284 cycles

CARGO BAY 161AF FLOOR PANEL EDGE AREA DEBONDED. FABRICATED NEW FLOOR PANEL IAW SRM 53-10-20 & DWG A53279966. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: FLOOR PANEL — DEBONDED (CARGO BAY) · airframe 24,712 hrs · 13,284 cycles

CARGO BAY 16HF FLOOR PANEL EDGE AREA DEBONDED. FABRICATED NEW FLOOR PANEL IAW SRM 53-10-20 & DWG A53279961. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: FLOOR PANEL — DENTED (CARGO BAY) · airframe 24,712 hrs · 13,284 cycles

CARGO BAY 162EF FLOOR PANEL UPPER SURFACE HAS SEVERAL SMALL DENTS. FABRICATED A NEW FLOOR PANEL IAW SRM 53-10-20 & DWG A53279966. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: FRAME — CRACKED (FUSELAGE) · airframe 24,712 hrs · 13,284 cycles

ONE CRACK (2MM) WAS FOUND AT FRAME 44 RT HOLE "B" AREA INBD DIRECTION. REPAIRED IAW EO E6-5310-7-5006.

Part: TIRE — DEFLATED (RT MLG) · airframe 24,611 hrs · 13,224 cycles

AFTER BLOCK-IN, INFORMED OF A DEFLATED TIRE ON RT MAIN GEAR. ALL INDICATIONS IN COCKPIT WERE NORMAL DURING TAXI IN. AFTER LANDING A "POP" WAS HEARD IN THE COCKPIT. IT APPEARED TO COME FROM UNDERNEATH CAPTS SEAT.

Part: PRIORITY VALVE — LEAKING (HYD SYSTEM) · airframe 23,363 hrs · 12,477 cycles

BLUE HYD SYS, AIR TURN BACK. LOST BLUE HYR PRESSURE AFTER TAKEOFF. ON RETURNING TO GATE FOUND HYD LEAK IN LT WHEEL WELL AFT BULKHEAD. LEAK FROM BLUE SYS MANIFOLD L/E FLAP PRIORITY VALVE. NEEDS VALVE-NIS MSN. BLED RESERVOIR PRESS AND REMOVED PRIORITY VALVE FROM MANIFOLD IAW AMM 29-12-12-04. OLD PART & HARDWARE PLACED ON WORK BENCH IN SHOP. CLEANED WHEEL WELL AREA IAW SMP. AWAITING PARTS ARRIVAL. INSPECTED BLUE HYD SYS IAW AMM 29-00-00-03 12 D. (2) OPERATION OF PUMP WITH LOW FLUID LEVEL. ALL CLOGGING PDI'S CHECKED NORMAL AND FLUID LEVEL IS ABOVE MINIMUM GAUGEABLE LEVEL. R & R BLUE L/E FLAP PRIORTY VALVE. OPS AND LEAK CK NORMAL IAW MM 29-12-12-04 AND JRH .

Part: IDG — FAILED (NR 2) · airframe 23,227 hrs · 12,381 cycles

LOST NR 2 GEN AT 80 KIAS ON TAKEOFF. RTO RESET GEN, GEN FAILED AGAIN AT 80 KIAS. PROCEEDED TO DESTINATION. REJECTED TAKEOFF AT 80 KIAS. R & R NR 2 IDG IAW AMM 24-11-11-04-01, OPS CHECK AND LEAK CHECK IS GOOD.

Part: PRESSURE SWITCH — FAILED (FUEL FILTER) · airframe 22,314 hrs · 11,871 cycles

TAKE-OFF POWER APPLIED & DURING ROLL. AT APPROX 60 KTS, NR 1 ENG FUEL FILTER CLOGG LIGHT ILLUMINATED WITH ECAM ALERT. TAKEOFF ABORTED, THROTTLES REDUCED. ECAM WARNING EXTINGUISHED, ALL ENGINE INDICATIONS NORMAL. SUBSEQUENT T/O NORMAL, BUT NR 1 ENG CLOG ECAM RETURNED DURING CLIMB. WITH NR 1 ENG POWER BELOW 100 %, WARNING LIGHT & ECAM EXTINGUISHED. PERFORMED FUEL FILTER INSP IAW MM 73-12-03-06, NO DEBRI FOUND. INSTALLED NEW FILTER IAW MM 73-12-02-04. OHMED WIRING FOR WARNING LIGHT TO FUEL FILTER DIFFERENTIAL PRESSURE SWITCH IAW WRI 73-34-01, PG 01. R & R NR 1 FUEL FILTER DIFFERENTIAL PRESSURE SWITCH IAW MM 73-34-11-4 05. LEAK CHECKED OK. OK FOR SERVICE.

Part: SKIN PANEL — CRACKED (LT WING) · airframe 22,251 hrs · 11,844 cycles

OPEN R 1 EA BOLT HOLE (POSITION G) WAS FOUND CRACKED AT THE R INBD 9 BOTTOM SKIN PANEL OF LT WING . IAW EO E6-5710-7 -5013. SKIN CRACK AREA REPAIRED IAW EA 6-5710-141607 (WINGS-AD 2008-06-18-EO 6-5710-5013 PT1- INSPECT AND MOD LOWER SKIN PANEL INBD OF RIB 9 AND AFT OF REAR SPAR)

Part: SKIN — CRACKED (RT WING SPOILER) · airframe 22,251 hrs · 11,844 cycles

RT WING T/E SPOILER SHROUD SUPPORT SKIN CRACKED, ABOUT .0625" BELOW NR 5 SPOILER INBD EDGE IAW DWG NR A57240194-200 FABRICATED. NEW SKIN SUPPORT INSTALLED IAW GMM 6-2-100.

Part: SKIN PANEL — CRACKED (LT WING) · airframe 22,251 hrs · 11,844 cycles

TPE OPEN R 1 EA CRACK WAS FOUND FROM THE FASTENER HOLE AT THE R IB 9 BOTTOM SKIN PANEL OF LT WING. THE CRACK LENGTH IS .5" IAW EO E6-5710-7-5013 PT1. SKIN CRACK AREA REPAIRED IAW EA 6-5710-141607. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100.

Part: ANGLE — CRACKED (RT WING TE FLAP) · airframe 22,251 hrs · 11,844 cycles

RT WING T/E OUTER FLAP INBD EDGE 1EA ANGLE CRACKED. REMOVED THE DAMAGED ANGLE AND INSTALL BY NEW ONE. IAW SRM 57-54-11 REPAIR CLASSIFIED AS MINOR IAW GMM 6-2-100.

Part: ANGLE — CRACKED (RT WING TE FLAP) · airframe 22,251 hrs · 11,844 cycles

RT WING T/E CENTER FLAP OTBD EDGE 1 EA ANGLE CRACKED. REMOVED THE DAMAGE ANGLE AND INSTALL BY NEW ONE IAW SRM 57-53-11. REPAIR CLASSIFIED AS MINOR IAW GMM 6-2-100.

Part: SKIN PANEL — CRACKED (LT WING) · airframe 22,251 hrs · 11,844 cycles

LT WING LWR SKIN PANEL INBD OF RIB 9 SUPPORT FLANGE CRACKED, JOGGLED SECTION. DAMAGED FLANGE CUT AND REPAIRED IAW E 6-5710-7-5013 PT5.

Part: SKIN — WORN (NR 1 SLAT) · airframe 22,251 hrs · 11,844 cycles

LT WING NR1 SLAT ERODED ABOVE NR1 PYLON, BLEND OUT THE EROSION AREA TO SMOOTH CONTOUR AND MEASURED THE AREA MAX DIMENSION IS 4" * 0.9" AND (3) LAYERS DAMAGED, THEN REPAIRED WITH FIBERGLASS AND RESIN COMPOUND. (CURE AT 180 DEGREE F) IAW EA NR 6-5750-141608. REPAIR CLASSIFIED AS MINOR IAW GMM 6-2-100.

Part: SKIN PANEL — CRACKED (RT WING) · airframe 22,251 hrs · 11,844 cycles

OPEN R 1EA BOLT HOLE (POSITION G) WAS FOUND CRACK AT THE RI B 9 BOTTOM SKIN PANEL OF RT WING. IAW EO E6-5710-7-501 PT6. SKIN CRACK AREA REPAIRED IAW EA:6-5710-141607.

Part: SKIN — CRACKED (RT WING SPOILER) · airframe 22,251 hrs · 11,844 cycles

RT WING T/E SPOILER SHROUD SUPPORT SKIN GOT CRACK ABOUT .5" BELOW NR 4 SPOILER OTBD EDGE. IAW DWG NR A57240194-201 FABRICATED. NEW SKIN SUPPORT INSTALLED IAW GMM 6-2-100.

Part: SKIN — CRACKED (NR 1 SLAT) · airframe 22,251 hrs · 11,844 cycles

RT WING NR 1 SLAT L/E PREVIOUS REPAIR FILLER CRACKED. CONFIRMED NO SKIN CRACK BUT ONLY LIMITED TO FILLER FROM A "DENT" REPAIR. REMOVED RT NR 1 SLAT ASSY IAW AMM 27-80-11-4 2. CUT-OUT DAMAGED AREA 98MM X 84MM IAW SRM 57-42-11-3. NDI WAS COMPLETED THE CUT-OUT EDGE NO CRACK WAS FOUND IAW NTM 51-10-08 P601. THE AREA PERFORMED A FLUSH REPAIR IAW EA 6-5750-141606. THE REPAIR CLASSIFIED AS MINOR IAW GMM6-2-100. REINSTALL RT NR 1 SLAT ASSY IAW 27-80-11-4.

Part: SKIN — WORN (NR 1 SLAT) · airframe 22,251 hrs · 11,844 cycles

RT WING NR1 SLAT ERODED ABOVE NR 2 PYLON. BLEND OUT (2) ERODED AREAS TO SMOOTH CONTOUR AND DAMAGE AREAS MAY DIMENSION ARE 1.1" X 1", PENETRANT TO HONEYCOMB 2. 3" X 0.7", (2) LAYERS DAMAGED, THEN REPAIR WITH FIBERGLASS AND RESIN COMPOUND (CURE AT 180 DEGREE F) IAW EA 6-5750-141608. REPAIR CLASSIFIED AS MINOR IAW GMM6-2-100.

Part: SKIN PANEL — CRACKED (RT WING) · airframe 22,251 hrs · 11,844 cycles

TPE OPEN R 1 EA CRACK WAS FOUND FROM THE FASTENER HOLE AT THE R IB 9 BOTTOM SKIN PANEL OF RT WING. THE CRACK LENGTH IS .2500" IAW EO E6-5710-7-5013 PT2. SKIN CRACK AREA REPAIRED IAW EA 6-5710-141607. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100.

Part: SMOKE DETECTOR — FAILED (AVIONICS BAY) · airframe 21,020 hrs · 11,160 cycles

ON T/O ROLL AT APPROX 80KTS RECEIVED AVIONICS SMOKE WARNING REJECTED T/O & WARNING WENT OUT. WARNING REOCCURED DURING TAXI WHEN POWER WAS PUSHED UP. INSPECTED AVIONICS BAY FOR WATER & SMOKE. NONE FOUND. RECEIVED WARNING AT GATE AVIONICS SMOKE, DISCONNECTED CONNECTOR TO SMOKE DETECTOR 13WA WARNING STOPPED. R & R SMOKE DETECTOR 13WA IAW AMM 26-15-12-4. OPS NORMAL. COMPLETED ENG RUN PER JRH ADVANCED THROTTLES SEVERAL TIMES, NO SMOKE WARNING RECEIVED. ACFT OK FOR SVC.

Part: HMU — FAILED (NR 1 ENGINE) · airframe 19,763 hrs · 10,484 cycles

NR 1 ENGINE N1 INDICATION BECAME UNSTABLE DURING CLIMB. REPEAT WRITE-UP. THEN EGT EXCEEDED LIMITS AT 952 DEG. THEN FUEL FLOW INDICATION BECAME UNSTABLE WITH SURGING AND YAW. PULLED TO IDLE N-1 AND FF INDICATION REMAINED UNSTABLE BUT SURGING STOPPED. PERFORMED FADEC BITE TEST AND PULLED FAULT CODES NOTHING ABNORMAL FOUND. REF TSM 73-21-30. BORESCOPED HPT STAGE 1 AND 2 PER 72-00-00-6, NO DEFECTS NOTED. REMOVED AND REPLACED HMU REF AMM 73-13-00-4. REMOVED AND REPLACED NR 1 CIT SENSOR REF MM 73-21-02-4. REMOVED AND REPLACED N1 SENSOR IAW MM 77-11-01-4 05. REMOVED AND REPLACED FUEL FILTER AND THE TEMP INLET SENSOR (T 1.2). REF AMM 73-12-02-4 AND 73-23-06-4. HIGH PWR RUN PER JRH.

Part: HMU — FAILED (NR 1) · airframe 19,763 hrs · 10,484 cycles

NR 1 ENGINE N1 INDICATION BECAME UNSTABLE DURING CLIMB. REPEAT WRITE-UP. THEN EGT EXCEEDED LIMITS AT 952 DEG THEN FUEL FLOW INDICATION BECAME UNSTABLE WITH SURGING AND YAW. PULLED TO IDLE N-1 AND FF INDICATION REMAINED UNSTABLE BUT SURGING STOPPED. PERFORMED FADEC BITE TEST AND PULLED FAULT CODES NOTHING ABNORMAL FOUND. BORESCOPED HPT STAGE 1 AND 2 PER 72-00-00-6. NO DEFECTS NOTED. REMOVED AND REPLACED HMU REF AMM 73-13-00-4. PERFORMED PWR RUN PER JRH, ALL PARAMETERS WERE WITHIN LIMITS PER JRH.

Part: ENGINE — UNSTABLE (NR 1) · airframe 19,763 hrs · 10,484 cycles

NR 1 ENGINE N1 INDICATION BECAME UNSTABLE DURING CLIMB. REPEAT WRITE-UP, THEN EGT EXCEEDED LIMITS AT 952 DEG. THEN FUEL FLOW INDICATION BECAME UNSTABLE WITH SURGING AND YAW. PULLED TO IDLE N-1 AND FF INDICATION REMAINED UNSTABLE BUT SURGING STOPPED. R&R N1 SENSOR, FUEL CONTROL, C.I.T. SENSOR AND BORESCOPED.

Part: SENSOR — FAILED (NR 1 ENGINE) · airframe 19,763 hrs · 10,484 cycles

NR 1 ENGINE N1 INDICATION BECAME UNSTABLE DURING CLIMB. REPEAT WRITE-UP, THEN EGT EXCEEDED LIMITS AT 952 DEG THEN FUEL FLOW INDICATION BECAME UNSTABLE WITH SURGING AND YAW. REMOVED AND REPLACED THE FUEL FILTER AND THE TEMP INLET SENSOR (T 1.2). REF AMM 73-12-02-4 AND 73-23-06-4. COMPLETED HIGH PWR RUN PER JRH ALL PARAMETERS WERE WITHIN LIMITS

Part: SENSOR — FAILED (FUEL SYSTEM) · airframe 19,763 hrs · 10,484 cycles

NR 1 ENGINE N1 INDICATION BECAME UNSTABLE DURING CLIMB. REPEAT WRITE-UP. THEN EGT EXCEEDED LIMITS AT 952 DEG THEN FUEL FLOW INDICATION BECAME UNSTABLE WITH SURGING AND YAW. REMOVED AND REPLACED THE FUEL FILTER AND THE TEMP INLET SENSOR (T 1.2). REF AMM 73-12-02-4, AND 73-23-06-4. COMPLETED HIGH PWR RUN PER JRH, ALL PARAMETERS WERE WITHIN LIMITS.

Part: WIRE HARNESS — FAILED (NR 1 ENGINE) · airframe 19,670 hrs · 10,439 cycles

SHORTLY AFTER T/O, AUTO THROTTLES DISENGAGED AND WOULD NOT RESET. SIMULTANEOUSLY, N1 FOR NUMBER 1 ENGINE FAILED (BOTH ANALOG AND DIGITAL). AUTO THROTTLE REMAINED OFF THE REST OF FLT. FOUND DUCT FOR T/R VALVE WITH A HOLE BLOWN THRU. ALSO, THE HARNESS FOR N1 SENSOR WAS BROKEN ON THE SMALL CONNECTOR, AND THE OTHER ONE WAS HEAT DAMAGED. ORDERED DUCT. REPLACED ORANGE AND RED ELECTRICAL HARNESSES ON NR 1 ENG PER M/M 71-51-01-4 05. RAN NR 1 ENG PER JRH, ALL INDICATIONS NORMAL AT IDLE.

Part: STIFFENER — CRACKED (ZONE 500) · airframe 19,409 hrs · 10,296 cycles

LEFT WING SPAR AREA, TOP SKIN STIFFENER AT WIAX 13-9 HAS A CRACK. MATERIAL ID FOR THE REPAIR IS 7075-T6 0.110 60-7018 EXTRUSION PO 566980.6 IAW A300-600 SRM 57-51-11, FIG 207 AND DWG NR A57241059. FABBED REPAIR ANGLE IAW A300-600 SRM 57-51-11, FIG 207. ALODINED AND PRIMED IAW A300-600 SRM 1-21-10, PG 3, AND 51-23-10, PG 24. INSTALLED REPAIR IAW A300-600 SRM 57-51-11, FIG 207 AND SRM 51-40-21, PG 7.

Part: SKIN — CORRODED (LT WING) · airframe 19,409 hrs · 10,296 cycles

LEFT WING TIP INBD SIDE SKIN HAS CORROSION AROUND THE STATIC WICK BASE. REMOVED STATIC WICK BASE AND REMOVED THE CORROSION. ORIGINAL THICKNESS 0.056 IAW AA300-600 SRM 57-30-11. REMOVED MATERIAL 0.014. REMAINING THICKNESS 0.042 AND IS OUT OF LIMITS IAW A300-600 SRM 57-31-11; PARA 4. MATERIAL ID FOR REPAIRS 2024-T3 IAW A300-600 SRM 51-31-00; PGD 21-24. FABBED JOINT PLATE AND FILLER IAW A300-600 SRM 57-30-11; FIG 201. INSTALLED NEW STATIC WICK BASE IAW A300-600 AMM 23-61-21-4 AND COMPLETED MEG CHECK. INSTALLED JOINT PLATE AND FILLER IAW A300-600 SRM 57-30-11; FIG 201.

Part: SEAT TRACK — CRACKED (ZONE 200) · airframe 19,409 hrs · 10,296 cycles

FOUND THE FLANGE CRACKED ON THE DUMMY SEAT TRACK LEFT NR 3 AT FRAME 38.1 TO FRAME 40. REMOVED AND REPLACED THE TRACK A5327400500053, PO NR 617643.1. LOCATED AND DRILLED THE NEW TRACK IAW A300-600 SRM 51-40-44, PG 16. INSTALLED NEW TRACK IAW A300-600 SRM 51-40-21, PG 7. REMOVAL ACCOMPLISHED ON WRI NR 53100540.

Part: FLOORBEAM — CORRODED (ZONE 100) · corrosion level 2 · airframe 19,409 hrs · 10,296 cycles

CROSSBEAM AT FRAME 52 BETWEEN RBL 20 - RBL 40 IS CORRODED. REMOVED AND REPLACED THE CROSSBEAM IAW A300 SRM 51-40-21, PARA 5.

Part: SEAT TRACK — CORRODED (ZONE 200) · corrosion level 2 · airframe 19,409 hrs · 10,296 cycles

MAIN DECK FLOOR TRACK AT FRAME 53; RBL 20 IN CORRODED IN THE CENTER OF THE TRACK. REMOVED AND REPLACED SEAT TRACK IAW A300 SRM 51-40-21, PARAGRAPHS 5, 6 AND 7.

Part: INTERCOSTAL — CORRODED (ZONE 200) · corrosion level 2 · airframe 19,409 hrs · 10,296 cycles

THE MAIN CABIN INTERCOSTAL AT FRAME 13 LBL 35 IS CORRODED ON THE UPPER SURFACE. REMOVED CORROSION IAW SRM 51-73-10 PG 209 ITEM 5. ORIGINAL MATERIAL THICKNESS IS 0.079 IAW SRM 53-12-15 CONFIG 2 PG 4-2 (B). REMAINING THICKNESS IS 0.050. FOUND TO BE OUT LF LIMITS IAW SRM 53-12-11 PGS 107-108. REMOVED SUPPORT IAW SRM 51-40-21 PG 7. LOCATED, DRILLED & DEBURRED THE NEW SUPPORT IAW DWG A53612214. INSTALLED IAW SRM 51-40-21 PGS 7 & 24.

Part: ACCESS DOOR — CHAFED (ZONE 600) · airframe 19,409 hrs · 10,296 cycles

RIGHT WING PANEL HAS NUMEROUS CHAFED SPOTS ON PANEL 675 CB. BLENDED DAMAGE AND FOUND TO BE OUT OF LIMITS IAW A300-600 SRM 57-51-12, PG 101. REMOVED PANEL IAW A300-600 SRM 51-40-21, PARA 5. REMOVED FASTENERS FROM PANEL IAW EA 6-5750-118484 AND A300-600 SRM 51-77-10. REMOVED PAINT, FABRICATED DOUBLER, PREPPED DOUBLER AND PANEL FOR BONDING. LAYED UP REPAIR DOUBLER, VACUUM BAGGED, CURED REPAIR. REMOVED FLASH, ALODINED, SEALED AND INSTALLED FASTENERS IAW EA 6-5750-188484, A300-600 SRM 51-77-10, 51-77-12 AND 51-21-10, EA 6-5750-118484, RIGHT WING ALL SPEED AILERON JACK BAY ACCESS PANEL CHAFING.

Part: FLOOR SUPPORT — CRACKED (FUSELAGE) · airframe 19,409 hrs · 10,296 cycles

THE INTERCOSTAL END FITTING IS CRACKED AT FRAME 10 IN THE FWD AVIONICS BAY; RT TUNNEL. REMOVED RT AFT COCKPIT FLOOR PANEL IAW SRM 51-40-21. REMOVED CRACKED SUPPORT ANGLE IAW SRM 51-40-21. HEAT TREAT IAW SRM 51-31-00. FABRICATED ; LOCATED & DRILLED ANGLE IAW SRM 51-40-44. ALODINED NEW ANGLE IAW SRM 51-21-10. PRIMED ANGLE IAW SRM 51-23-20. PAINTED ANGLE IAW SRM 51-23-10. INSTALLED ANGLE & FLOOR PANEL IAW SRM 51-40-21.

Part: SEAT TRACK — CRACKED (ZONE 200) · airframe 19,409 hrs · 10,296 cycles

THE SEAT TRACK ADAPTER AT FRAME 29; RBL 40 IS CRACKED. REMOVED SEAT TRACK ADAPTER IAW A300-600 SRM 51-40-21; PARA E-7. RECEIVED NEW SEAT TRACKADAPTER P/N A5378193720100 PO 577701.4. DRILLED HOLES IAW A300-600 SRM 51-40-44. INSTALLED NEW SEAT TRACK ADAPTER IAW A300-600 SRM 51-40-21; PARA E-7.

Part: WEB — CRACKED (ZONE 100) · airframe 19,409 hrs · 10,296 cycles

THE FWD CARGO PIT FROM FRAME 21 - 22 HAS A CRACKED WEB AT THE FWD UPPER AND AFT LOWER CORNERS ABOVE STRINGER 44L. REMOVED WEB & RAIL ASSEMBLY IAW SRM 51-40-21. REMOVED CRACKED WEB IAW SRM 51-40-21. INSTALLED NEW WEB IAW SRM 51-40-21. REINSTALLED WEB & RAIL ASSEMBLY IAW SRM 51-40-21.

Part: PANEL — DAMAGED (ZONE 500) · airframe 19,409 hrs · 10,296 cycles

LEFT WING T/E PANEL 590 AB AFT CORNER IS BROKEN, BLENDED CORNER ON THE LEFT T/E PANEL, SEALED EDGE AND PAINTED IAW A300-600 SRM 51-42-20.

Part: SEAT TRACK — GOUGED (ZONE 200) · airframe 19,409 hrs · 10,296 cycles

MAIN CARGO COMPARTMENT, SEAT TRACK SCALLOPS ARE GOUGED AND ELONGATED AT FRAME C 58, 15 INCH, RBL 37 INCHES. THIS SDR WAS GENERATED IN ERROR. FOR DETAILS PLEASE SEE SDR TRACKING NR 08-1664.

Part: PANEL — DEBONDED (VERTICAL STAB) · airframe 19,409 hrs · 10,296 cycles

VERTICAL STAB L/E PANEL 322 BL IS DISBONDING AROUND THE HOIST POINT AND THE UPPER LEFT CORNER. REMOVED AND REPLACED THE ERROSION STRIP IAW AMM 55-32-11-8 AND EA 6-5530-118505.

Part: SEAT TRACK — CORRODED (ZONE 200) · airframe 19,409 hrs · 10,296 cycles

MAIN CARGO COMPT HAS CORROSION ON THE BOTTOM OF THE SEAT TRACK AT RBL 38 INCHES AND FRAME 56, 10 INCHES, AND ANOTHER SPOT 20 INCHES AFT OF IT. REMOVED AND REPLACED THE SEAT TRACK SECTION REF SRM 53-10-16 SHEET 1. ORIGINAL SEAT TRACK FOUND TO BE OUT OF LIMITS REF 53-10-16 FIG 101.

Part: PANEL — DAMAGED (VERTICAL STAB) · airframe 19,409 hrs · 10,296 cycles

VERTICAL STAB L/E PANEL 322 BL IS DAMAGED ON THE LEADING EDGE. REMOVED AND REPLACED THE ERROSION STRIP IAW AMM 55-32-11-8 AND E.A. 6-5530-118505.

Part: SEAT TRACK — GOUGED (ZONE 200) · airframe 19,409 hrs · 10,296 cycles

MAIN CARGO COMPT SEAT TRACK SCALLOPS ARE GOUGED AND ELONGATED AT FRAME C 58, 15 INCHES, RBL 37 INCHES. REMOVED AND REPLACED THE SEAT TRACK SECTION IAW SRM 51-40-21 PARAGRAPH 7.

Part: PANEL — DAMAGED (VERTICAL STAB) · airframe 19,409 hrs · 10,296 cycles

VERTICAL STAB L/E PANEL 322 CL IS DAMAGED ON THE L/E 6 INCHES FROM THE LOWER END. REPAIRED ERROSION STRIP LOWER END ON VERTICAL LE PANEL 300 CL IAW AMM 55-32-11-8 & SRM 55-32-00.

Part: PANEL — ERODED (VERTICAL STAB) · airframe 19,409 hrs · 10,296 cycles

VERTICAL STAB L/E PANEL 322 CL LEFT SIDE IS ERODED JUST AFT OF THE L/E. REMOVED ERRODED PAINT FOUND NO SIGNS OF DELAMINATION IAW SRM 55-32-00.

Part: PANEL — DEBONDED (VERTICAL STAB) · airframe 19,409 hrs · 10,296 cycles

VERTICAL STAB L/E PANEL 322 CL IS DISBONDED AROUND THE HOIST POINT. REPAIRED VERTICAL SATBILIZER L / E PANEL 322 CL HOIST POINT AREA BY TRIMMING BURRS & RESEALING IAW AMM 55-32-11-8.

Part: PANEL — DAMAGED (VERTICAL STAB) · airframe 19,409 hrs · 10,296 cycles

VERTICAL STAB L/E PANEL 322 BL IS DAMAGED ON THE LEADING EDGE. REMOVED AND REPLACED THE ERROSION STRIP IAW AMM 55-32-11-8 AND E.A. 6-5530-118505.

Part: PANEL — UNSECURE (VERTICAL STAB) · airframe 19,409 hrs · 10,296 cycles

VERTICAL STAB L/E PANEL 322 CL HOIST POINT IS NOT SECURED ON THE INTERIOR SIDE. REPAIRED CRACKED POTTING WITH NEW POTTING EC 3500 MB / A IAW DWG 33-A53373311 AMM 55-32-11 AND SRM 51-35-10 PG 17.

Part: PANEL — DAMAGED (VERTICAL STAB) · airframe 19,409 hrs · 10,296 cycles

VERTICAL STAB L/E 322 AL HAD GOUGES ABOVE THE HOIST POINT ON THE LEFT AND RIGHT SIDES. REMOVED GOUGED PAINT AND REFINISHED AREA IAW SRM 55-32-00 & 51-75-10.

Part: SEAT TRACK — CORRODED (BS 1393-1658) · airframe 19,409 hrs · 10,296 cycles

MAIN CARGO COMPT SEAT TRACK AT LBL 97 HAS CORROSION SPOTS IN THE BOTTOM OF THE TRACK FROM STA 1393 TO 1658. REMOVED & REPLACED SEAT TRACK IAW SRM 51-40-21.

Part: PANEL — DAMAGED (VERTICAL STAB) · airframe 19,409 hrs · 10,296 cycles

VERTICAL STAB L/E 322 AL HAS DAMAGE. REPAIRED VERTICAL STABILIZER L/E PANEL 322 AL BY REMOVING & BONDING A NEW SECTION OF ERROSION STRIP IAW AMM 55-32-11-8.

Part: PANEL — DEBONDED (VERTICAL STAB) · airframe 19,409 hrs · 10,296 cycles

VERTICAL STAB L/E PANEL 322 CL LEADING EDGE IS DISBONDED. REPAIRED ERROSION STRIP LOWER END OF THE VERTICAL L / E PANEL 322 CL IAW AMM 55-32-11-8.

Part: SEAT TRACK — CORRODED (ZONE 200) · airframe 19,409 hrs · 10,296 cycles

MAIN DECK FLOOR AT BL 0, FRAME 44, CENTER TRACK IS CRACKED AND CORRODED. REMOVED CORROSION ; OUT OF LIMITS IAW SRM 53-10-16 FIG 101. 100% MATERIAL LOSS. REPLACED WITH A NEW SEAT TRACK P/N 5327400500053, IAW SRM 51-40-44 & 51-40-21.

Part: SEAT TRACK — CORRODED (ZONE 200) · airframe 19,409 hrs · 10,296 cycles

MAIN DECK FLOOR TRACK AT RBL 38, FRAME 52 HAS CORROSION IN THE CENTER OF THE TRACK. ORIGINAL ADAPTER WAS FOUND TO BE OUT OF LIMITS REF 53-16-10; SRM. INSTALLED NEW ADAPTER REF SRM 51-40-21; PARA 7.

Part: SEAT TRACK — CORRODED (ZONE 200) · airframe 19,409 hrs · 10,296 cycles

MAIN DECK FLOOR TRACK RBL 80, FRAME 44 HAS CORROSION AT THE UPPER CENTER OF THE TRACK. REMOVED CORRODED TRACK RAIL IAW SRM 51-72-10. LOCATED NEW TRACK RAIL IAW SRM 51-72-10 AND AIRBUS DWG 15A53813871. INSTALLED NEW TRACK RAIL IAW SRM 51-72-10 AND DWG 15A53813871. ALODINED IAW SRM 51-21-10. APPLIED PRIMER IAW SRM 51-23-10. APPLIED PAINT IAW SRM 1-23-10.

Part: SEAT TRACK — CORRODED (ZONE 200) · airframe 19,409 hrs · 10,296 cycles

MAIN DECK FLOOR TRACK AT RBL 20, FRAME 42 HAS CORROSION IN THE CENTER OF THE SEAT TRACK. REMOVED AND REPLACED SEAT TRACK IAW SRM 51-40-21 PARA 6 & 7.

Part: PANEL — ERODED (VERTICAL STAB) · airframe 19,409 hrs · 10,296 cycles

VERTICAL STAB L/E PANEL 322 AL HAS AREAS OF EROSION. REMOVED ERRODED PAINT AND REFINISHED AREA IAW SRM 55-32-00 & 51-75-10.

Part: SEAT TRACK — CRACKED (ZONE 200) · airframe 19,409 hrs · 10,296 cycles

MAIN DECK FLOOR, BL O, AT FRAME 51 THE CENTER OF THE TRACK IS CRACKED AND CORRODED. REMOVED CORROSION; OUT OF LIMITS IAW A300-600 SRM 53-10-16; FIG 101. ORIGINAL MATERIAL 0.134. MATERIAL LOSS 0.055. MATERIAL REMAINING 0.079. REMOVED AND REPLACED WITH A NEW SEAT TRACK IAW SRM 51-40-21 & 51-40-40.

Part: FRAME — GOUGED (ZONE 100) · airframe 19,409 hrs · 10,296 cycles

MAIN CABIN FRAME 40 BETWEEN STRINGERS 15R AND STRINGER 16R ARE GOUGED. SMOOTH BLEND OUT THE DAMAGED AREA IAW EA 6-5310-118485 "FUSELAGE - FRAME 40 AT STRINGER 15 AND 16 LT AND RT GOUGE REPAIR".

Part: FRAME — GOUGED (ZONE 100) · airframe 19,409 hrs · 10,296 cycles

MAIN CABIN FRAME 40 L BETWEEN STRINGER 15L AND STRINGER 16 L THE FRAME IS GOUGED. PERFORMED SMOOTH BLENDOUT FOR THE DAMAGED AREA IAW EA 6-5312-118485 "FUSELAGE FRAME 40 AT STRINGER 15L AND STRINGER 16L GOUGE REPAIR". RESTORED THE SURFACE PROTECTION IAW EA 6-5310-118485.

Part: ANGLE — CRACKED (RT WING) · airframe 19,409 hrs · 10,296 cycles

AFT OF R/WING REAR SPAR, CRACKED ANGLE AT T/E TOP PANEL SUPPORT ANGLE, OUTBD SIDE OF RIB 9, FWD OF SPOILER NR 3 INBD HINGE PIN. REMOVED CRACKED ANGLE IAW A300-600 SRM 51-40-21. RECEIVED NEW BRACKET P/N A5724007120100, P/O NR 617032.1. INSTALLED NEW BRACKET IAW A300-600 SRM 51-40-21 PARA 7.

Part: PANEL — ERODED (RT WING) · airframe 19,409 hrs · 10,296 cycles

RIGHT WING LEADING EDGE PANEL NR 623 HB IS ERODED AT THE FWD EDGE. REPAIRED ERRODED AREAS BY APPLYING FIBREGLASS OVERLAYS IAW SRM 57-41-12 & 51-77-12. REAPPLIED FOIL IAW SRM 57-41-12; FIG 208. ALODINED IAW SRM 51-21-10. PRIMED IAW SRM 51-23-10. RESTORED PAINT FINISH IAW SRM 51-75-10. INSTALLED PANEL ON THE AIRCRAFT IAW AMM 57-41-41.

Part: SKIN — DENTED (LT WING) · airframe 19,409 hrs · 10,296 cycles

LEFT WING FLAP HAS A DENT LOCATED 62 INCHES FROM THE OUTBD END AND 26 INCHES FROM THE T/E THAT HAVE BEEN FOUND TO BE OUT OF LIMITS ON N/R N00417. FABRICATED DOUBLER IAW SRM 57-50-00. LOCATED & DRILLED IAW SRM 57-50-00. ALODINED IAW SRM 51-21-10. PRIMED IAW SRM 51-23-10. INSTALLED IAW SRM 57-50-00. PAINTED & SEALED IAW SRM 51-23-10.

Part: PANEL — DAMAGED (LAVATORY) · airframe 19,409 hrs · 10,296 cycles

CABIN LAVATORY COVER PANEL IS DAMAGED. REMOVED DAMAGE. PREPPED SURFACE FOR REPAIR; POTTED; LAYED UP WET LAY-UP REPAIR & REFINISHED SURFACE IAW SRM 51-77-12.

Part: PANEL — WORN (NR 2 PYLON) · airframe 19,409 hrs · 10,296 cycles

NR 2 PYLON PANEL NR 423 CL IS WORN FROM FRETTING AT TWO LOCATIONS FRONT AND BACK. REMOVED DAMAGE REF A300-600 SRM 51-73-10. ORIGINAL THICKNESS .078. REMAINING THICKNESS .052. REMOVED .026. BEYOND LIMITS REF A300-600 SRM 54-52-51. FABRICATED DOUBLER AND FILLER REF A300-600 SRM 54-52-51, FIG 203. CUT OUT DAMAGE REF A300-600 SRM 54-52-51. ALODINED REF A300-600 SRM 51-21-10. PRIMED REF A300-600 SRM 51-23-10. INSTALLED DOUBLER AND FILLER REF A300-600 51-40-21, PARA 5. PAINTED REF A300-600 SRM 51-23-10.

Part: INTERCOSTAL — BENT (ZONE 200) · airframe 19,409 hrs · 10,296 cycles

EMPENNAGE FR 86 STRINGER 34 LT INTERCOSTAL BENT. REMOVED AND REPLACED INTERCOSTAL IAW SRM 51-72-10 AND 51-40-21.

Part: SKIN — DENTED (LT WING TE FLAP) · airframe 19,409 hrs · 10,296 cycles

LEFT WING INBD FLAP HAS TWO DENTS LOCATED 65 1/2 INCH AND 61 1/2 INCH OUTBD END AND 14 INCH AND 16 1/4 INCH FROM THE T/E THAT HAVE BEEN FOUND OUT OF LIMITS ON N/R N00417, LABELED D/E ON N/R N00417. FABRICARED DOUBLER & FILLER IAW SRM 57-50-00 FIG 205 PG 219. LOCATED & DRILLED IAW SRM 57-50-00. ALODINED IAW SRM 51-21-10. PRIMED & PAINTED IAW SRM 51-23-10. INSTALLED THE DOUBLER & FILLER IAW SRM 57-50-00.

Part: PANEL — DELAMINATED (HORIZONTAL STAB) · airframe 19,409 hrs · 10,296 cycles

PANEL 334 FT IS DELAMINATED. REPAIRED PANEL 334 FT BY DRILLING OUT DAMAGED AREA AND APPLYING ADHESIVE / FIBERGLASS OVERLAY REPAIR IAW SRM 51-77-12; PG 225 & 55-13-13 PG 215. APPLIED CONDUCTIVE COAT IAW SRM 51-23-20. PRIMED & PAINTED IAW AMM 51-23-10-0.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 19,409 hrs · 10,296 cycles

MAIN CABIN, FR14C TO FR18, LBL19, SEAT TRACK CORRODED. REMOVED DAMAGED SEAT TRACK IAW SRM 51-40-21. RECEIVED NEW SEAT TRACK, LOCATED; DRILLED & INSTALLED IAW SRM 51-40- 21.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 19,409 hrs · 10,296 cycles

MAIN CABIN, FR 15B TO FR 18, LBL 38, SEAT TRACK CORRODED. REMOVED DAMAGED SEAT TRACK IAW SRM 51-40-21. RECEIVED NEW SEAT TRACK P/N A5361252410000, PO 617268.2. LOCATED; DRILLED & INSTALLED IAW SRM 51-40- 21 & 51-72-13.

Part: PANEL — DELAMINATED (HORIZONTAL STAB) · airframe 19,409 hrs · 10,296 cycles

PANEL 344 EP DELAMINATED. REPAIRED PANEL 344 EP BY REMOVING THE DAMAGE; CLEANING; CLEANING THE AREA, POTTING REPAIR AND APPLYING A FIBERGLASS WET LAY UP REPAIR IAW SRM 51-77-12 PARA 2-A (2) FIG 202 AND SRM 51-77-10 PARA 3. RESTORED SURFACE REPAIR IAW SRM 51-77-12; PARA 2-A (2), L & SRM 51-75-10.

Part: PANEL — WORN (ZONE 600) · airframe 19,409 hrs · 10,296 cycles

RIGHT WING LEADING EDGE PANEL NR 612 BB INNER SKIN LAMINATE IS WORN/TORN AROUND THE FASTENERS. APPLIED ANTI-ERROSION TAPE 7 PRIMED IAW A300-600 SRM 51-75-10; PG 213.

Part: PANEL — WORN (RT WING) · airframe 19,409 hrs · 10,296 cycles

RIGHT WING LEADING EDGE PANEL NR 612 DB HAS LANDING AREA INTERIOR LAMINATE WORN/TORN. REPAIRED THE DAMAGED AREA BY APPLYING ALUMINUM FOIL IAW SRM 57-41-12. REMOVED & REATTACHED THE PANEL RESTRAINING CORDS REF AMM 57-41-41-4. PREPPED THE BONDING SURFACE FOR THE FOIL APPLICATION REF SRM 57-41-12. ALODINED THE SURFACE REF SRM 51-21-10. PRIMED THE SURFACE REF SRM 51-23-10.

Part: PANEL — DELAMINATED (HORIZONTAL STAB) · airframe 19,409 hrs · 10,296 cycles

PANEL 334 BT IS DELAMINATED ON THE UPPER AND LOWER SIDES. RECEIVED SERVICEABLE SLIDE TO BE INSTALLED ON W / C 68S1500CP; STEP 5B.

Part: PANEL — DELAMINATED (ZONE 300) · airframe 19,409 hrs · 10,296 cycles

PANEL 344 HT IS DELAMINATED. REPAIRED PANEL BY REMOVING THE DAMAGE ; CLEANING; PREPARING AREA; POTTING AND APPLYING A FIBERGLASS LAY-UP REPAIR IAW SRM 51-77-72; PARA 2-A; FIG 202 AND SRM 51-77-10; PARA 3. RESTORED SURFACE REPAIR IAW SRM 51-77-12; PARA 2-A (2)-L AND SRM 51-75-10.

Part: COVER — DAMAGED (R1 DOOR) · airframe 19,409 hrs · 10,296 cycles

R-1 DOOR INTERIOR HINGE MECHANISM COVER IS DAMAGED. REMOVED DAMAGE; CLEANED & PREPPED FOR WET LAY UP. LAYED UP REPAIR PLIES & STARTED CURE, COMPLETED CURE & LIGHTLY SANDED, CLEANED & PREPPED FOR FINISH COAT; APPLIED FINISH COAT IAW SRM 51-77-10 & 51-77-11.

Part: ACCESS DOOR — DELAMINATED (FUSELAGE) · airframe 19,409 hrs · 10,296 cycles

ACCESS DOOR 313 AL AFT OUTBD CORNER IS DELAMINATED. REPAIRED ACCESS DOOR 313 AL BY REMOVING THE DAMAGED SKIN PLIES & THE PREVIOUS REPAIR. APPLIED A WET LAYED UP FIBERGLASS REPAIR TO THE INNER & OUTER SURFACES & REFINISHED IAW SRM 51-77-12.

Part: PANEL — DELAMINATED (FUSELAGE) · airframe 19,409 hrs · 10,296 cycles

PANEL 344FT DELAMINATED 2 AREAS. REPAIRED PANEL 344 FT BY REMOVING THE DAMAGE; CLEANING; PREPARING THE AREA; POTTING AND APPLYING A FIBERGLASS WET LAY-UP REPAIR IAW ARM 51-77-12; PARA 2-A (2); FIG 202 AND SRM 51-77-10; PARA 3. RESTORED SURFACE REPAIR IAW SRM 51-77-12; PARA (2)-L AND SRM 51-75-10.

Part: PANEL — WORN (RT WING) · airframe 19,409 hrs · 10,296 cycles

RIGHT WING LEADING EDGE PANEL NR 612 GB HAS LANDING AREA SKIN LAMINATE WORN/TORN. REPAIRED DAMAGED AREA IAW SRM 57-41-12; FIG 208. REMOVED & RE-ATTACHED THE PANEL RESTRAINT CORDS REF AMM 57-41-41-4; PG 1.PREPARED THE BONDING SURFACE FOR THE FOIL APPLICATION IAW SRM 57-41-12; FIG 208. ALODINED SURFACE REF SRM 51-21-10. PRIMED THE SURFACE REF SRM 51-23-10.

Part: FLOOR PANEL — DAMAGED (ZONE 200) · airframe 19,409 hrs · 10,296 cycles

PANEL 121SF HAS EDGE DAMAGE. FABRICATED NEW FLOOR PANEL 121 SF; POTTED EDGES; COMPLETED CURE & SANDED EDGE POTTING; INSTALLED INSERTS; APPLIED NON-SKID & PART MARKED. REMOVED HAREWARE FROM THE OLD PANEL & REINSTALLED ON THE NEW PANEL IAW DWG SRZ 25-005; REN F & SRM 51-40-00.

Part: PANEL — DELAMINATED (HORIZONTAL STAB) · airframe 19,409 hrs · 10,296 cycles

PANEL 334 AT IS DELAMINATED AS MARKED. REPAIRED PANEL 334AT BY REMOVING THE BRUSH SEAL; CONDUCTIVE PLATE & OUTER SKIN DAMAGE IAW SRM 55-13-13 & 51-77-10. APPLIED FIBERGLASS OVERLAY REPAIR TO THE OUTER SKIN; FABBED & BONDED NEW CONDUCTIVE PLATE & WASHERS IAW SRM 55-13-13. PAINTED PANEL IAW SRM 51-75-10. THE BRUSH SEAL REINSTALLED.

Part: RUB STRIP — DAMAGED (RT WING TE FLAP) · airframe 19,409 hrs · 10,296 cycles

RIGHT WING INBD FLAP UPPER SKIN RUB STRIP IS WORN. REMOVED & REPLACED THE CHAFE / RUB STRIP IAW SRM 57-50-00.

Part: FLAP — DENTED (ZONE 500) · airframe 19,409 hrs · 10,296 cycles

LEFT WING INBD FLAP HAS TWO DENTS LOCATED 55" AND 57 1/4 " FROM THE INBD ENDAND 7 3/4 " & 5" FROM THE T / E THAT HAVE BEEN FOUND OUT OF LIMITS ON N/R N00417. LABELED A & B ON N/R N00417. FABRICATED DOUBLER IAW SRM 57-50-00; FIG 205; PG 219. LOCATED & DRILLED IAW SRM 57-50-00. ALODINED IAW SRM 51-21-10; PRIMED & PAINTED IAW SRM 51-23-10. INSTALLED DOUBLER IAW SRM 57-50-00.

Part: INTERCOSTAL — BENT (ZONE 200) · airframe 19,409 hrs · 10,296 cycles

EMPENAGE FR 86 STRINGER 34 RT INTERCOSTAL BENT. REMOVED & REPLACED INTERCOSTAL IAW SRM 51-72-10 & 51-40-21.

Part: PANEL — CRACKED (WING) · airframe 19,409 hrs · 10,296 cycles

PANEL 612 CB LEADING EDGE IS CRACKED AND ERODED. REPAIRED CRACK & ERROSION ON PANEL 612 CB L/E WITH WET LAY UP IAW SRM 57-41-12.

Part: PANEL — WORN (NR 2 PYLON) · airframe 19,409 hrs · 10,296 cycles

NR 2 PYLON PANEL NR 424 CR IS WORN FROM FRETTING AROUND THE EXTERIOR FASTENER HOLES. REMOVED DAMAGE REF A300-600 SRM 51-73-10. ORIGINAL THICKNESS .078. REMAINING THICKNESS .032. REMOVED .046. BEYOND LIMITS REF A300-600 SRM 54-52-51. FABRICATED DOUBLER AND FILLER REF A300-600 SRM 54-52-51; FIG 203. CUT OUT DAMAGE REF A300-600 SRM 54-52-51. ALODINED REF A300-600 SRM 51-21-10. PRIMED REF A300-600 SRM 51-23-10. INSTALLED DOUBLER AND FILLER REF A300-600 SRM 51-40-21, PARA 5. PAINTED REF A300-600, SRM 51-23-10.

Part: PANEL — ERODED (WING) · airframe 19,409 hrs · 10,296 cycles

PANEL 612 CB MATING SURFACES ARE ERODED. REPLACED ERRODED FOIL ON PANEL 612 CB MATING SURFACE IAW SRM 57-41-12.

Part: STRUCTURE — LOOSE (THRUST REVERSER) · airframe 19,409 hrs · 10,296 cycles

NR 2 ENGINE OUTBD T/R T/E HAS LOOSE COMPOSITE REPAIR EDGE. REPLACED THE NR 2 ENGINE OUTBOARD TRANSLATOR COWL IAW AMM 78-32-11-4. REFERRED ALL WORK TO NON-ROUTINE N01042.

Part: ATTACH ANGLE — CRACKED (NR 2 PYLON) · airframe 19,409 hrs · 10,296 cycles

NR 2 PYLON ATTACH ANGLE AND RIB 3-A (OUTBD) IS CRACKED. REMOVED SHIM IAW A300-600 SRM 51-40-21 PG 7. PART IS IDENTIFIED AS A SHIM WITH A CRACK 1 INCH LONG IAW SRM 54-52-31 FIG 2 ITEM 15. FABRICATED SHIM. SHIM IS INSTALLED IAW SRM 51-40-2 PG 7.

Part: DOOR FRAME — CRACKED (SLIDE) · airframe 19,409 hrs · 10,296 cycles

L-1 DOOR SLIDE ASSY; LOWER INTERNAL FRAME IS CRACKED AT THE FWD CORNER. NEW SERVICEABLE SLIDE RECEIVED. INSTALLED ON WIC 68S5001CP.

Part: PANEL — DELAMINATED (ZONE 100) · airframe 19,409 hrs · 10,296 cycles

AIR CONDITION EXTERNAL FAIRING PANEL NR 144 HR IS DELAMINATING ON THE INTERNAL SKIN. REPAIRED PANEL BY REMOVING THE DAMAGE AND APPLYING A WET LAY UP IAW SRM 51-77-12 AND RESTORED THE FINISH IAW SRM 51-75-10.

Part: SKIN — GOUGED (RT WING) · airframe 19,409 hrs · 10,296 cycles

RIGHT WING ROOT AREA EXTERNAL SKIN HAS NUMEROUS GOUGED PLACES BETWEEN FRAME 51 AND FRAME 52. REMOVED THE DAMAGE & FOUND SKIN TO BE OUT OF LIMITS. COMPLIED WITH E.A. 6-5310-118492.

Part: PANEL — DELAMINATED · airframe 19,409 hrs · 10,296 cycles

AIR CONDITION EXTERNAL FAIRING PANEL NR 144 GR IS DELAMINATING ON THE INTERNAL SKIN. REPAIRED PANEL 144 GR BY REMOVING THE DAMAGE AND APPLYING A WET LAY UP IAW SRM 51-77-12 AND RESTORED THE FINISH IAW SRM 51-75-10.

Part: FRAME — CRACKED (R1 DOOR) · airframe 19,409 hrs · 10,296 cycles

R-1 DOOR SLIDE ASSY, LOWER INTERNAL FRAME IS CRACKED AT THE AFT CORNER. RECEIVED SERVICEABLE SLIDE TO BE INSTALLED ON W/C 68S5001CP.

Part: CONNECTOR — MISSING (L1 DOOR SLIDE) · airframe 19,409 hrs · 10,296 cycles

L-1 DOOR SLIDE ASSY, BATTERY TEST CONNECTOR IS MISSING. RECEIVED SERVICABLE SLIDE FOR FR 15B (L-1 DOOR) TO BE INSTALLED ON WIC 68S5001CP.

Part: FAIRING — DELAMINATED (ZONE 100) · airframe 19,409 hrs · 10,296 cycles

AIR CONDITIONING EXTERNAL FAIRING NR 143 GL IS DELAMINATED. REMOVED THE DAMAGE; PREPPED AREA FOR REPAIR; APPLIED A LAY-UP REPAIR; REFINISHED SURFACE IAW SRM 51-77-12 & SRM 53-15-73.

Part: SKIN — ERODED (THRUST REVERSER) · airframe 19,409 hrs · 10,296 cycles

NR 2 ENGINE OUTBD T/R, ALL BLOCKER DOORS HAVE EXPOSED COMPOSITE CORE, SKIN IS ERODED. REPLACED THR NR 2 ENGINE THRUST REVERSER TRANSLATOR COWL IAW AMM 78-32-11-4. REFERRED ALL WORK TO NON-ROUTINE N01042.

Part: WEB — CRACKED (ZONE 100) · airframe 19,409 hrs · 10,296 cycles

LEFT AIR CONDITION FAIRING SUPPORT WEB FOR FAIRING 143 FL; AFT WEB OUTER ATTACH POINT TO BODY IS CRACKED. REMOVED SUPPORT AND WEB REF FEDEX A300-600 SRM 51-40-21. MATERIAL ID IS 2024-T3, 0.050 REF FEDEX A300-600 SRM 53-15-73. FORMED DOUBLER REF FEDEX A300-600 SRM 51-71-30; PG 202. ALODINED DOUBLER REF FEDEX A300-600 SRM 51-21-10. PRIMED AND PAINTED DOUBLER REF FEDEX A300-600 SRM 51-23-10. PART MARKED DOUBLER REF FEDEX A300-600 SRM 51-71-30. INSTALLED DOUBLER AND SUPPORT WEB REF A300-600 SRM 51-40-21.

Part: SKIN — DENTED (RT WING TE FLAP) · airframe 19,409 hrs · 10,296 cycles

RT WING INBD FLAP LWR SKIN HAS A NUMBER OF DENTS. MEASURED DEEPEST DENT TO BE D= .028 INCH DEEP AND X= .500" WIDE. FOUND TO BE WITHIN LIMITS PER SRM 57-50-00 PG 101 DEPTH GAUGE NR T8492F. GOUGE BLENDED ORIG MAT .031" REMAINING .021, REMOVED .010" FOUND TO BE OUT OF LIMITS IAW SRM 57-50-00 PG 107 GAUGE NR T8492F. FABBED AND INSTALLED DOUBLER IAW SRM 57-50-00. ALODINED .IAW SRM 51-21-10. PRIMED AND PAINTED IAW SRM 51-23-10.

Part: STRUCTURE — DAMAGED (THRUST REVERSER) · airframe 19,409 hrs · 10,296 cycles

NR 2 ENGINE OUTBD T/R TRANSLATING COWL HAS EXPOSED COMPOSITE CORE. REPLACED THE NR 2 ENGINE OUTBD THRUST REVERSER TRANSLATOR COWL IAW AMM 78-32-11-4. REFERRED ALL WORK TO NON-ROUTINE N01042.

Part: SLIDE — DAMAGED (L1 DOOR) · airframe 19,409 hrs · 10,296 cycles

L-1 DOOR SLIDE ASSY, UPPER EXTERNAL FRAME INSERTS ARE PULLED OUT OF THE BOX AT THE FWD END. NEW SERVICEABLE SLIDE RECEIVED INSTALLED ON WIC 68S5001CP.

Part: SLIDE — CRACKED (R1 DOOR SLIDE) · airframe 19,409 hrs · 10,296 cycles

R-1 DOOR SLIDE ASSY, BOX IS CRACKED ON THE OUTER SURFACE, UPPER FWD SIDE. RECEIVED SERVICEABLE SLIDE TO BE INSTALLED ON W/C 68S1500CP; STEP 5-B.

Part: STRUCTURE — LOOSE (THRUST REVERSER) · airframe 19,409 hrs · 10,296 cycles

NR 2 ENGINE OUTBD T/R UPPER T/E COMPOSITE REPAIR EDGES ARE LOOSE. REPLACED NR 2 ENGINE OUTBOARD THRUST REVERSER TRANSLATOR COWL IAW A300-600 AMM 78-32-11-4. REFERRED ALL WORK TO NON-ROUTINE N01042.

Part: FLOORBOARD — DELAMINATED (FUSELAGE) · airframe 19,409 hrs · 10,296 cycles

EMPENNAGE ACCESS THRU 312 AR, THE FLOORBOARD ON THE LEFT SIDE OF THE A/C FWD OF THE PNEUMATIC DUCT AT FRAME 84 IS DELAMINATED. FABRICATED NEW PANEL. LOCATED & DRILLED NEW HOLES USING OLD FLOORBOARD AS A TEMPLATE; INSTALLED INSERTS; POTTED & CURED BOARD EDGES; SANDED EDGES AS NEEDED. APPLIED NON-SKID & PART MARKED PANEL IAW DWG SRZ 25-005, AMM 11-00-00-00 & GMM 7-0-100. REMOVED AND INSTALLED FLOOR PANEL IAW SRM 51-40-21.

Part: FLOORBOARD — DELAMINATED (FUSELAGE) · airframe 19,409 hrs · 10,296 cycles

EMPENAGE ACCESS THRU 312 AR, THE FLOORBOARD ON THE LEFT SIDE OF THE A/C AFT OF THE PNEUMATIC DUCT AT FRAME 84 IS DELAMINATED. FABRICATED NEW PANEL; LOCATED & DRILLED NEW HOLES; INSTALLED INSERTS; POTTED & CURED BOARD EDGES. SANDED EDGES AS NEEDED; APPLIED NON-SKID & PART MARKED PANEL IAW DWG SRZ 25-005, REV F; AMM 11-00-00-00 & GMM 7-0-1000.REMOVED & INSTALLED FLOOR PANEL IAW SRM 51-40-21.

Part: SKIN — DENTED (AILERON) · airframe 19,409 hrs · 10,296 cycles

RT WING INBD AILERON HAS NUMEROUS HAIL DENTS ON UPPER SKIN. DENT FOUND TO BE OUT OF LIMITS IAW SRM 57-61-11, MAT ID 2024-T3 PO NR 605306.1 IAW SRM 57-61-11 AND 51-21-00, PAGE 23-24 TABLE 3 SHEET 3, FABBED DOUBLER AND FILLER IAW SRM 57-61-11, FIG 206. ALODINED IAW SRM 51-21-10. PRIMED AND PAINTED IAW SRM 51-23-10. INSTALLED IAW SRM 57-61-11.

Part: FAIRING — PUNCTURED (TE FLAP) · airframe 19,409 hrs · 10,296 cycles

LEFT WING FLAP FAIRING 533BB FWD SECTION IS PUNCTURED INTERNALLY. REMOVED DAMAGE FROM PANEL; FABRICATED REPLACEMENT CORE PLUG; POTTED CORE & STARTED CURE; COMPLETED CURE & SANDED; LAYED UP REPAIR PLYS UNDER VAC BAG & STARTED CURE; COMPLETED CURE & LIGHTLY SANDED.

Part: FAIRING — ERODED (TE FLAP) · airframe 19,409 hrs · 10,296 cycles

LEFT WING FLAP FAIRING 534 AB L/E IS ERODED IN 2 AREAS. REMOVED DAMAGE & LAYED UP REPAIR PLIES & STARTED CURE. COMPLETED CURE & SANDED. APPLIED ANTI-STATIC COATING; APPLIED FR PRIMER & APPLIED PAINT.

Part: PANEL — CRACKED (ZONE 100) · airframe 19,409 hrs · 10,296 cycles

AFT CARGO PANEL 151 PW IS CRACKED IN 3 PLACES. REMOVED DAMAGE, STOPPED DRILLED THE CRACKS & PREPPED AREA FOR REPAIRS TO BE LAYED UP, 3 EA FIBERGLASS WET LAY UP REPAIRS & APPLIED THE FINISH COAT IAW DWG SRZ 25-013.

Part: SKIN — BENT (APU DOOR) · airframe 19,409 hrs · 10,296 cycles

RIGHT APU DOOR SKIN IS BENT AND THE EDGE IS CRACKED AT THE CENTER LINE OF THE A/C WITH THE DOOR CLOSED. REMOVED BENT & CRACKED EDGE DAMAGE IAW SRM 51-27-00. FOUND EDGE DISTANCE TO FASTENERS TO BE 2-D & WITHIN LIMITS IAW SRM 51-40-50. PRIMED AREA IAW A300-600 SRM 51-21-10. PAINTED AREA IAW SRM 51-21-10.

Part: FAIRING — ERODED (TE FLAP) · airframe 19,409 hrs · 10,296 cycles

LEFT WING FLAP FAIRING 535 AB L/E IS ERODED IN 2 AREAS. REMOVED FINISH & DAMAGE AT 2 AREAS TOP & BOTTOM OF THE FAIRING IAW SRM 57-20-35. LAYED UP; BAGGED & CURED REPAIRS IAW SRM 57-20-35. REINSTALLED SEAL PARTIALLY REMOVED TO F.O.M. & RESTORED FINISH IAW SRM 51-75-10.

Part: PANEL — CHAFED (NR 2 NACELLE) · airframe 19,409 hrs · 10,296 cycles

NR 2 PYLON; RIGHT FWD LOWER FAIRING; PANEL 486R IS CHAFED AT THE ATTACHMENT POINTS. REMOVED PANEL AND CHECKED LIMITS. STIFFENER WAS OUT OF LIMITS. FABBED A NEW STIFFENER ON N/R N01140. INSTALLED STIFFENER IAW SRM 51-40-21; PG 7 AND REINSTALLED PANEL IAW SRM 51-40-21; PG 7.

Part: NOSE COWL — DENTED (NR 2 ENGINE) · airframe 19,409 hrs · 10,296 cycles

NR 2 ENGINE INBD FAN COWL IS DENTED. REMOVED DAMAGE, PREPPED FOR THE APPLICATION OF FILLER MATERIAL. APPLIED FILLER, CURED, SANDED & PREPPED FOR PRIMER. APPLIED PRIMER & PAINTED IAW SRM 54-10-00, SRM 54-20-00 & SRM 51-75-10.

Part: NOSE COWL — DELAMINATED (NR 1 ENGINE) · airframe 19,409 hrs · 10,296 cycles

NR 1 ENGINE NOSE COWL IS DELAMINATED AT THE FWD LOWER END. REMOVED & REPLACED THE NR 1 NOSE COWL IAW AMM 71-11-00-4. FAN COWL DOORS TO BE ADJUSTED & CLOSED ON THE NR 1 ENGINE INSTALLATION W/C 64T0700-1.

Part: PANEL — DAMAGED (ZONE 100) · airframe 19,409 hrs · 10,296 cycles

A/C FAIRING LEFT PANEL 143 FL IS DAMAGED FROM FRETTING. REMOVED DAMAGE; PREPPED THE AREA FOR REPAIR; APPLIED LAY-UP REPAIR & REFINISHED THE SURFACE IAW A300-600 SRM 51-77-12 & SRM 53-15-73.

Part: FAIRING — DENTED (TE FLAP) · airframe 19,409 hrs · 10,296 cycles

LEFT WING FLAP FAIRING 534 BB IS DENTED ON THE LOWER FWD SECTION. REMOVED DAMAGE AND APPLIED A WET LAY-UP IAW SRM 57-20-35 & RESTORED FINISH IAW SRM 57-75-10 & AMM 51-23-10-0.

Part: RUB STRIP — DELAMINATED (TE FLAP) · airframe 19,409 hrs · 10,296 cycles

RIGHT WING FLAP UPPER SKIN RUB STRIP IS DELAMINATED AT 3 SPOTS. REMOVED & REPLACED THE CHAFE / RUB STRIP IAW SRM 57-50-00; PARA 3-G FIG 207.

Part: PANEL — ERODED (TE FLAP) · airframe 19,409 hrs · 10,296 cycles

LEFT WING FLAP FAIRING 532 BB LEADING EDGE IS ERODED. REMOVED DAMAGE AND REPAIRED BY APPLYING FIBERGLASS WET LAY UP IAW SRM 57-20-35 & E.A. 6-5720-118496.

Part: PANEL — CHAFED (NR 2 NACELLE) · airframe 19,409 hrs · 10,296 cycles

NR 2 PYLON LEFT FWD LOWER FAIRING; PANEL 485BL IS CHAFED AT THE ATTACHMENT POINTS. REMOVED PANEL AND CHECKED THE LIMITE. THE STIFFENER WAS OUT OF LIMITS. FABBED A NEW STIFFENER ON N/R N01141 & INSTALLED THE STIFFENER IAW SRM 51-40-21. INSTALLED THE PANEL IAW SRM 51-40-21.

Part: FAIRING — DENTED (TE FLAP) · airframe 19,409 hrs · 10,296 cycles

LEFT WING FLAP FAIRING 536 AB RIGHT SIDE HAS A DENT. REPAIRED THE DENT BY REMOVING THE DAMAGED AREA, POTTING THE CORE, APPLYING A WET LAY UP REPAIR AND REFINISHING THE AREA IAW SRM 57-20-35.

Part: SKIN — DAMAGED (THRUST REVERSER) · airframe 19,409 hrs · 10,296 cycles

NR 2 ENGINE OUTBD T/R CORE COWL SKIN IS PEELING. REPAIRED BY REMOVING THE PEELING WIRE MESH & SEALING THE EDGES IAW CMM 78-32-02; REPAIR NR 13.

Part: DOOR — GOUGED (LT NLG DOOR) · airframe 19,409 hrs · 10,296 cycles

NLG LEFT MAIN DOOR IS GOUGED ON THE EDGE. REPAIRED LEFT NOSE; LEFT MAIN GEAR DOOR BY REMOVING DAMAGED AREA & BONDING CARBON WET LAY UP REPAIR IAW A300-600 SRM 52-82-11 & 51-77-10 PARA 3.0; FIG 209. REMOVED FINISH AT SECOND DAMAGE LOCATION AFTER FURTHER EVALUATION FOUND NO FIBER DAMAGE OR DEFECTS.

Part: FAIRING — DELAMINATED (TE FLAP) · airframe 19,409 hrs · 10,296 cycles

LEFT WING FLAP FAIRING 535 AT IS DELAMINATED. REPAIRED BY REMOVING THE DAMAGE & APPLYING A CORE; CLOSING PLIES AND A FIBERGLASS OVERLAY REPAIR IAW SRM 57-20-35. APPLIED THE ANTI-STATIC COATING IAW SRM 51-23-20. APPLIED PORE FILLER & PRIMER IAW SRM 51-75-10. PREPPED & PAINTED THE AREA IAW AMM 51-23-10-0.

Part: RUB STRIP — CHAFED (TE FLAP) · airframe 19,409 hrs · 10,296 cycles

LEFT WING INBD FLAP UPPER SURFACE CHAFING PLATE IS PEELING AND WORN. REMOVED &B REPLACED THE CHAFE STRIPS IAW SRM 57-50-00; PARA 3-G; FIG 207.

Part: FAIRING — PUNCTURED (TE FLAP) · airframe 19,409 hrs · 10,296 cycles

LEFT WING FLAP FAIRING 535 BB IS PUNCTURED ON THE FWD LOWER SECTION. REMOVED DAMAGE & APPLIED A WET LAY-UP IAW SRM 57-20-35.

Part: SKIN — CHAFED (FAN COWL) · airframe 19,409 hrs · 10,296 cycles

NR 2 ENGINE INBD FAN COWL INNER SKIN DOUBLER IS WORN AND CHAFED. REMOVED AND REPLACED DAMAGED CHAFE PLATE ITEM 9 IAW SRM 54-02-01 & 54-20-00. RESTORED THE SURFACE FINISH IAW SRM 54-20-00.

Part: COWLING — DENTED (NR 2 ENGINE) · airframe 19,409 hrs · 10,296 cycles

NR 2 ENGINE INBD FAN COWL IS DENTED. REMOVED DAMAGE, PREPED FOR THE APPLICATION OF FILLER MATERIAL. APPLIED FILLER, CURED, SANDED & PREPPED FOR PRIMER. APPLIED PRIMER & PAINTED IAW SRM 54-10-00, 54-20-00 & 51-75-10.

Part: FAIRING — DENTED (TE FLAP) · airframe 19,409 hrs · 10,296 cycles

LEFT WING FLAP FAIRING 535 AT IS DENTED. REPAIR BY REMOVING THE DAMAGE & APPLYING A CORE; CLOSING PLIES AND A FIBERGLASS OVERLAY REPAIR IAW SRM 57-20-35. APPLIED AN ANTI-STATIC COATING IAW SRM 51-23-20. APPLIED PORE FILLER & PRIMER IAW SRM 51-75-10. PREPPED & PAINTED AREA IAW AMM 51-23-10-0.

Part: SKIN — DELAMINATED (FAN COWL) · airframe 19,409 hrs · 10,296 cycles

NR 2 ENGINE INBD FAN COWL INNER SKIN IS DELAMINATED. REMOVED DAMAGED INNER SKIN AND REPAIRED IAW SRM 54-20-00. RESTORED FINISH IAW SRM 54-20-00 & SRM 51-75-10.

Part: FAIRING — DELAMINATED (TE FLAP) · airframe 19,409 hrs · 10,296 cycles

RIGHT WING FLAP FAIRING 636 AB LEFT SIDE UPPER POINT IS DELAMINATED. REMOVED FINISH AND DAMAGE IAW SRM 57-20-35. LAYED UP & CURED REPAIR PLYS IAW SRM 57-20-35 PAPAGRAPHS 5; G-M. APPLIED FINISH IAW SRM 51-75-10.

Part: PANEL — PUNCTURED (ZONE 100) · airframe 19,409 hrs · 10,296 cycles

BULK CARGO PANEL 161 BW IS PUNCTURED IN 2 PLACES. REPAIRED BY REMOVING THE DAMAGE. APPLYING A WET LAY UP, CURING THE WET LAY UP AND PAINTING THE REPAIRED SURFACE.

Part: SHEAR WEB — CRACKED (FUSELAGE) · airframe 19,409 hrs · 10,296 cycles

MAIN DECK CARGO DOOR RIGHT SIDE SHEAR WEB IS CRACKED BETWEEN FRAME 76 AND FRAME 77. REMOVED WEB IAW SRM 51-40-21. FABRICATED WEB IAW SRM 51-26-00 & MARKED IAW GMM 7-0-1001. HEAT TREATED IAW TPS 1003, REV A. ALODINED; PRIMED & PAINTED IAW SRM 51-21-10; PG 1. INSTALLED WEB IAW SRM 51-40-21; PG 7. HEAT TREAT LOAD HT050608-3.

Part: SHEAR PLATE — CRACKED (ZONE 200) · airframe 19,409 hrs · 10,296 cycles

SHEAR PLATE IS CRACKED AT FRAME 79 BETWEEN STRINGER 16L AND 17L. REMOVED AND REPLACED THE SHEAR PLATE IAW A300 SRM 51-40-21.

Part: RETAINER — GOUGED (CARGO DOOR) · airframe 19,409 hrs · 10,296 cycles

AFT CARGO DOOR AFT CUTOUT; PRESSURE SEAL DEPRESSOR IS GOUGED FROM TOP TO BOTTOM. REMOVED AND REPLACED THE DAMAGED SEAL DEPRESSOR IAW SRM 51-40-21.

Part: RETAINER — BENT (APU BAY) · airframe 19,409 hrs · 10,296 cycles

APU ACCESS CUTOUT AFT SEAL RETAINER IS BENT AND THE SEAL IS TORN. REMOVED SEAL RETAINER & ANGLE IAW SRM 51-40-21. INSTALLED ANGLE & RETAINER IAW SRM 51-40-21.

Part: DRAIN MAST — BENT (APU) · airframe 19,409 hrs · 10,296 cycles

APU DRAIN MAST RIGHT UPPER FLANGE IS BENT AND THE MAST IS DENTED AND BENT. REMOVED AND REPLACED THE DRAIN MAST IAW SRM 51-40-21.

Part: DEPRESSOR — GOUGED (CARGO DOOR) · airframe 19,409 hrs · 10,296 cycles

AFT CARGO DOOR FWD CUTOUT PRESSURE SEAL DEPRESSOR IS GOUGED FROM TOP TO BOTTOM. REMOVED & REPLACED SEAL DEPRESSOR IAW SRM 51-40-21.

Part: WIRE HARNESS — CHAFED (RT WING) · airframe 19,409 hrs · 10,296 cycles

RIGHT WING ABOVE THE NR 2 ENGINE PYLON INSIDE THE WING FIXED L/E; A WIRE BUNDLE HAS SEVERAL WIRES WITH THE INSULATION CHAFED THROUGH EXPOSING INDIVIDUAL WIRES. PREVIOUS REPAIR IS CHAFED THROUGH & TORN. INSTALLED A PROTECTIVE SLEEVE ON THE WIRES REF ESPM 20-53-51. REPOSITIONED AND RESECURED WIRE HARNESS REF ESPM 20-33-44. NO WIRING WAS DISCONNECTED OR DISTURBED.

Part: SHEAR PLATE — CRACKED (ZONE 200) · airframe 19,409 hrs · 10,296 cycles

THE SHEAR PLATE IS CRACKED AT FR 79, STRINGER 16R - STRINGER 17R. REMOVED AND REPLACED THE SHEAR WEB IAW A300-600 SRM 51-40-21; PARAGRAPH 7.

Part: PROXIMITY SENSOR — FAILED (MLG) · airframe 18,865 hrs · 10,013 cycles

AFTER T/O GEAR WOULD NOT RETRACT. SELECTED SYSTEM NR 2 STILL NO RETRACTION. HANDLE WOULD NOT GO PAST NEUTRAL POSITION. JACKED A/C REF A300-600 M/M 07-11-00-0, PERFORMED GEAR SWING AND RETRACTION REF 32-30-00-6. FOUND FAULT ON PROX BOX. REMOVED AND REPLACED PROX BOX REF A300-600 M/M 32-31-71-4. PERFORMED GEAR SWING AND RETRACTION AGAIN OPS CHECK NORMAL REF A300-600 32-30-00-6. PER MOCC REQUEST: LUBED ALL (3) LANDING GEAR AS REQUIRED PER A300-600 M/M 12-22-32-0, SWUNG THE LANDING GEAR SEVERAL TIMES USING BOTH LANDING GEAR POSITION SYSTEMS, ONE AND TWO. A/C NOW ON 4TH LEG.

Part: OIL SYSTEM — LEAKING (APU) · airframe 18,731 hrs · 9,940 cycles

DURING TAXI OUT MAIN DECK CARGO SMOKE DETECTOR "B" LOOP INDICATED SMOKE. ECAM INDICATED SMOKE IN AFT COMPARTMENT. STOPPED AIRCRAFT AND COMPLIED WITH ECAM. WARNING EXTINGUISHED WHEN NR 2 PACK VALVE TURNED OFF. RETURNED TO GATE. MAIN DECK CARGO DETECTOR AFT LOOP A INOP-PREV-MEL. AFTER BLOCK IN FOUND APU LEAKING OIL INTO APU INTAKE CAUSING SMOKE IN CABIN DURING PACK OPERATION. REMOVED AND REPLACED NR 1 AND 2 PACK COALESCER BAGS, REF MM 21-51-16-3. MEL'D APU SEE WRI 49-10/0023. RAN ENGINES AT POWER TO CLEAR PNEUMATIC DUCTS OF OIL RESIDUE PER MM 21-51-00-3. NOW BOTH AIR-CONDITIONING PACKS WORK AND SMELL NORMAL.

Part: RIB — CRACKED (ZONE 500) · airframe 18,575 hrs · 9,869 cycles

DURING COMPLIANCE WITH EO NR 6-5750-7-5000 P1, LT INBOARD FLAP RIB NR 25 WAS FOUND TO BE CRACKED. REPLACEMENT OF DAMAGED RIB NR 25.

Part: RIB — CRACKED (ZONE 600) · airframe 18,575 hrs · 9,869 cycles

DURING COMPLIANCE WITH EO NR 6-5750-7-5000 P2, RT INBD FLAP RIB 25 WAS FOUND TO BE CRACKED IN UPPER RADIUS REPLACEMENT OF DAMAGED PART.

Part: RIB — CRACKED (ZONE 600) · airframe 18,575 hrs · 9,869 cycles

DURING COMPLIANCE WITH EO NR 6-5750-7-5000 P2, RT INBD FLAP RIB 25 WAS FOUND TO BE CRACKED IN UPPER RADIUS REPLACEMENT OF DAMAGED PART.

Part: RIB — CRACKED (TE FLAP) · airframe 18,575 hrs · 9,869 cycles

DURING COMPLIANCE WITH EO NR 6-5750-7-5000 P2, RIB 7 FLANGE WAS FOUND TO BE CRACKED COMPLIANCE WITH EO NR 6-5750-7-5000 P4. REPLACEMENT OF DAMAGED RIB 7.

Part: UNKNOWN — UNKNOWN · airframe 16,683 hrs · 8,844 cycles

F/O'S ND AND PFD FAILED MOMENTARILY AT BEGINNING OF TAKEOFF ROLL- REJECTED TAKEOFF RETURNED FOR IMMEDIATE TAKEOFF WITH ALL SYSTEMS NORMAL. A/C DID NOT RETURN TO GATE MEM (FAULT CLEARED). NO HISTORY. 12JUL06 DEN R FLT CREW REPORTED FAILED LESS THEN 3 SEC'S, CAME BACK AND WORKED NORMALLY AFTERWARDS. BITE CHECKED EFIS SYSTEM, NO FAULTS FOUND. ND AND PFD OPS NORMAL. A/C OK FOR SERVICE.

Part: DAMPER — FAILED (MLG) · airframe 13,751 hrs · 7,175 cycles

AFTER TAKEOFF, GEAR WOULD NOT RETRACT, RETURNED. REMOVED AND REPLACED LT LANDING GEAR PITCH DAMPER REF MM 32-11-15-4 RII:233985, ENT BY: 274911 RPT BY: 274911, R/I 02AUG04 04:39 IAH R, FACT 02AUG04 10:38 IAH U GEAR SWING REQUIRED, JACKED A/C FOR GEAR SWING IAW MM 07-11-00-0 AT HANGER, GEAR SWING CHECKED OK IAW MM.

Part: PROXIMITY SENSOR — FAILED (MLG) · airframe 13,235 hrs · 6,843 cycles

ON TAKEOFF AT BDL GEAR WOULD NOT RETRACT, COMPLIED WITH ECAM AND QRH PROCEDURES RETURNED TO KBDL UNEVENTFULL APPROACH AND LANDING. PERFORMED BITE CHECK ON PROX BOX PER TSM 32-61-00, FOUND BOX FAULT LIGHT ON. SENSORS ALL CHECK GOOD. CHECKED BOOGIE PITCH DAMPERS FOR PROPER SERVICE FOUND TO BE GOOD PER M/M 12-12-32. REMOVED AND REPLACED PROX BOX PER M/M 32-31-71-4, OPS CHECK GOOD.

Part: PROXIMITY SENSOR — MALFUNCTIONED (MLG) · airframe 13,020 hrs · 6,718 cycles

COULD NOT RAISE HANDLE GEAR LEVER. NO LANDING GEAR RETRACTION. PERFORM ECAM PROC 2ND ATTEMP NR 2 SYSTEM TO RAISE GEAR FAILED. AFTER FURTHER T/S REPLACED PROX DETECTION UNIT PER AMM 32-31-71-4. ALSO REPLACED LANDING GEAR MICRO SWITCH PER AMM 32-31-11-4. PERFORMED ADJ & TEST WITH TEST SET PER AMM 32-31-11-4 AND GEAR RETRACTION INHIBITION TEST ON SYSTEM 1 & 2 PER AMM 32-31-00-5, ALL INDICATIONS CHECK NORMAL. CHECKED SERVICE ON LT PITCH DAMPNER PER AMM 12-12-32-0, SERVICED WITH NITROGEN. CHECKED SECURITY OF SENSORS 9GA & 11GA CHECKS NORMAL. JACKED REAR OF LT BOGIE TO POSITION SENSORS TO READ NEAR ON PROX DETECTOR CHECKS NORMAL. SYSTEM OPS CHECKS NORMAL AT THIS TIME AND OK FOR SERVICE.

Part: CROSSBEAM — CRACKED (FUSELAGE) · airframe 12,613 hrs · 6,500 cycles

CROSSBEAM AT FR29 HAS 1 INCH CRACK BETWEEN RT SEAT TRACKS R1 & R2. REPAIRED CROSSBEAM AS PER A300-600 SRM 53-10-15 FIG 206.

Part: STRUCTURE — VIBRATION (AIRFRAME) · airframe 11,749 hrs · 5,998 cycles

ON TAKE OFF, A LOUD THUMP WAS HEARD AND THE AC PULLED LT. GEAR WAS LEFT DOWN & RETURN TO LAND. ON LAND EVERYTHING SEEMED NORMAL AIRCRAFT STEERED STRAIGHT AND WITH NO PULL. NO VIBRATION OF ANY SORT. NO TIRES BLOWN. AC IN WORK FOR FUTHER TROUBLESHOOTING PERFORMED WALK AROUND INSP NO EXT DAMAGE FOUND, MOVED ALL FLT CTRLS NO DAMAGE FOUND. NEEDS MORE TROUBLESHOOTING PERF FLT CONTROL TEST PER AIRBUS 300 MM 27-00-00-5. FND, NO FAULT, NEEDS MORE TROUBLESHOOTING.

Part: HMU — FAULTY (NR 2 ENGINE) · airframe 10,970 hrs · 5,558 cycles

NR 2 ENGINE FF 2500-5000 LB FLUCTUATION- ON CLIMB OUT, NOTICED FLUCTUATING FUEL FLOW EFFECTING A SPIKE IN N1 (5-10 PERCENT) EGT TEMP VARY 3-5 DEGREES ALONG WITH A SLIGHT N2 SPIKE (2 PERCENT) NOTIFIED MECHANIC, RETURNED TO LANDING RWY 36R. TAXI IN, INSTRUMENTS APPEARED NORMAL. REMOVED AND REPLACED NR 2 HMU IAW MM. IAW MOCC REQUEST REMOVED AND REPLACED NR 2 MAIN FUEL FILTER IAW A300 MM. ALL CHECKS COMPLIED WITH NORMALLY.

Part: SWITCH — FAULTY (PAX DOOR) · airframe 9,897 hrs · 4,938 cycles

DURING CLIMB 7,000 FT RIGHT FWD CABIN DOOR NOT CLOSED WARNING ILLUM. REMOVED AND REPLACED DOOR WARNING SWITCH 8WS.

Part: ENGINE — MALFUNCTIONED (NR 2)

00-5 - NR 2 ENGINE COMPRESSOR STALLED AFT CLIMB PWR SEL FOLLOW FLEX PWR T/O ON A NON PROFILE T/O. ENG RETARD TO IDLE AND NO FURTHER ADVERSE CONDITION NOTED. AC LAND WITH NR 2 IDLE, ENG SHUTDOWN AFT LAND.