N721FD

Part: SLIDE — DISLODGED (ZONE 800) · airframe 55,984 hrs · 30,640 cycles

LEFT FORWARD ENTRY DOOR WILL NOT DISARM. THE LEVER WILL NOT MOVE ALL THE WAY TO THE DISARM POSITION. MEL: 52-11-01-02 ESCAPE SLIDE CAME LOOSE FROM L1 DOOR, ESCAPE SLIDE REMOVED FROM DOOR, BUT REMAINS ONBOARD IN HAZMAT CONTAINER.

Part: DOOR — FAULTED (ZONE 800) · airframe 55,984 hrs · 30,640 cycles

L1 DOOR WILL NOT DISARM. REVERSED MEL 52-11-01-01. FOUND WITH LOWER COVER REMOVED DOOR DISARMS AND ARMS NORMALLY. REINSTALLED LOWER COVER AND DOOR CONTINUES TO OPERATE NORMALLY. LOWER COVER WAS DAMAGED AND PLACED ON OIL REF WRI 52-10/5586.

Part: SLIDE — FAULTED (ZONE 800) · airframe 55,984 hrs · 30,640 cycles

LEFT FORWARD ENTRY DOOR WILL NOT DISARM. THE LEVER WILL NOT MOVE ALL THE WAY TO THE DISARM POSITION. THIS ITEM WAS ON MEL 52-11-01-01. THE ESCAPE SLIDE HAS COME LOOSE FROM THE STORE, TRANSFERRING WRI 52-10/5579 TO THIS WRI AND PLACING ITEM ON MEL 52-11-01-02, SLIDE REMOVED FROM DOOR, STORED ONBOARD. AMM 25-61-22-04-01, REMOVED L1 SLIDE FROM AIRCRAFT AND INSTALLED NEW ONE. OPS CHECK FAILED. SLIDE WILL NOT DISARM AFTER IT IS ARMED. SUSPECT STIRRUPS/GIRT BAR FITTINGS REQUIRE ADJUSTMENT. CREATING NEW WRI TO PLACE SLIDE ON MEL.

Part: O-RING — FAILED (HYD LINE) · airframe 55,681 hrs · 30,445 cycles

DURING DESCENT THROUGH FL200 ECAM INDICATED LOSS OF GREEN HYDRAULIC QUANTITY BELOW RED DOT. HYD RESV LOW. COMPLIED WITH ECAM AND QRH. PERFORMED MANUAL GEAR EXTENSION AND LANDED WITH NO FURTHER ISSUES. AFTER THE GEAR WAS EXTENDED GREEN HYDRAULIC SYSTEM RESTORED TO FULL CAPACITY. AMM 12-12-29-00 AMM: 32-33-00-02, AMM: 20-23-16-00. R & R LT NOTCH FLAP RETURN LINE O-RING, IAW MM 20-23-00-00, 20-23-16-00, 29-00-00-04, CYCLED SLATS REF MM 27-80-00. OPS & LEAK CHKD NORMAL AMM 25-66-20-02-01. REINSTALLED THE DECOMPRESSION PANELS THAT WERE REMOVED TO GAIN ACCESS TO THE NOTCH FLAPS TO ACCOMPLISH MX TASKS IAW AMM 25-66-20-02-01 FWD CARGO COMPARTMENT DECOMPRESSION PANELS - MAINTENANCE PRACTICES. A/C TO CONTINUE.

Part: RIB — CRACKED (ZONE 600) · airframe 55,456 hrs · 30,302 cycles

RH WING CENTER FLAP PERFORM EA NO.:6-5750-T0381883 P1 STEP 4.A. DVI FOUND RIB 27 FLANGE CRACK BETWEEN STRINGER 2.7 AND REAR SPAR AREA. PERFORMED CUT OUT DAMAGED FLANGES AND INSTALLED REPAIR ANGLES AT RH WING CENTER FLAP RIB27, S-2.7~REAR SPAR AND EXTERNAL PLATE AT RIB26~27,S-2.2~REAR SPAR FOR REPAIR I.A.W FEDEX EA NO:T6-5750-T0381883P1, SEQ NO:XXX TITLE :WINGS - FLIGHT SURFACES - RH CENTER FLAP-CRACKS IN UPPER FLANGES OF RIB 26 AND 27-ALI 575306-01-1A. THIS REPAIR IS CLASSIFIED AS CAT A AND MAJOR REPAIR PER GMM 6-2-100.

Part: STRINGER SPLICE — WORN (ZONE 100) · airframe 55,456 hrs · 30,302 cycles

SPLICE HOLE ELONGATION AT FR54 STGR 44RH SIDE. REPLACED THE DAMAGED SPLICE WITH NEW FABRICATED SPLICE AT LOWER FUSELAGE FR54, S- 44R. I.A.W A300-600 SRM 51-72-10-001, PAGE.2& AIRBUS DWG NO:A53812405, REV.C00& FEDEX GMM 07-0-1001. THIS REPAIR IS CLASSIFIED AS CAT.A MAJOR PER GMM 06-2-100. (THE SPLICE REMOVED AND INSTALLED STEP, PLEASE REFERENCE FEDEX EA NO:T6-5330-T0369235 A P2, STEP.2& 7)

Part: FITTING — NOT REPORTED (ZONE 100) · airframe 55,456 hrs · 30,302 cycles

REPLACE MAIN DECK CARGO DOOR ACTUATOR BEARING FITTING AT FRAME 24 PER EO NO: E6- 5230-E0378588 B P5 REPLACED MAIN DECK CARGO DOOR ACTUATOR BEARING FITTING AT FRAME 24, LONGN1~3. I.A.W FEDEX EO NO: E6-5230-E0378588 B P5, SEQ NO:981, TITLE: DOORS-CARGO DOOR/HYD SYS- DETAILED VISUAL INSPECTION OF THE MAIN DECK CARGO (MDCD) ACTUATOR BEARING FITTINGS AT FRAME 23 AND 24-AOT A52W016-24. THIS REPAIR IS CLASSIFIED AS MAJOR PER GMM 06-2-100

Part: FITTING — NOT REPORTED (ZONE 800) · airframe 55,456 hrs · 30,302 cycles

REPLACE MAIN DECK CARGO DOOR ACTUATOR BEARING FITTING AT FRAME 23 PER EO NO: E6- 5230-E0378588 B P5 REPLACED MAIN DECK CARGO DOOR ACTUATOR BEARING FITTING AT FRAME 23, LONGN1~3. I.A.W FEDEX EO NO: E6-5230-E0378588 B P5, SEQ NO:981, TITLE: DOORS-CARGO DOOR/HYD SYS- DETAILED VISUAL INSPECTION OF THE MAIN DECK CARGO (MDCD) ACTUATOR BEARING FITTINGS AT FRAME 23 AND 24-AOT A52W016-24. THIS REPAIR IS CLASSIFIED AS MAJOR PER GMM 06-2-100

Part: RIB — GOUGED (ZONE 600) · airframe 55,456 hrs · 30,302 cycles

THE LWR BORE GOUGE ON OUTBD JACK RIB OF R4 SPLR. ACCOMPLISHED THE REINFORCEMENT REPAIR AT R4 SPOILER OUTBD JACK RIB LWR BORE I.A.W FEDEX EA NO:T6-5740-T0382065 P1, SEQ NO:1013, TITLE:WING-ATTACH FITTINGS-RH WING #4 SPOILER JACK RIB AT STA ABX112.525-BEAM ATTACHMENT HOLE REINFORCEMENT REPAIR-SRM DEVIATION. THE REPAIR CLASSIFIED AS CAT.A MAJOR PER GMM 6-2-100.

Part: RIB — GOUGED (ZONE 600) · airframe 55,456 hrs · 30,302 cycles

THE UPPER BORE GOUGE ON INBD JACK RIB OF R6 SPLR. ACCOMPLISHED THE REINFORCEMENT REPAIR AT R6 SPOILER INBD JACK RIB UPPER BORE I.A.W FEDEX EA NO:T6-5740-T0382066 P1, SEQ NO:1014, TITLE:WINGS-ATTACH FITTINGS-RH WING #6 SPOILER JACK RIB AT STA SP1X31.675 AND SP1X40.425-BEAM ATTACHMENT HOLE REINFORCEMENT REPAIR-SRM DEVIATION. THE REPAIR CLASSIFIED AS CAT.A MAJOR PER GMM 6- 2-100.

Part: RIB — GOUGED (ZONE 600) · airframe 55,456 hrs · 30,302 cycles

THE UPPER BORE GOUGE ON OUTBD JACK RIB OF R6 SPLR. ACCOMPLISHED THE REINFORCEMENT REPAIR AT R6 SPOILER OUTBD JACK RIB UPPER BORE I.A.W FEDEX EA NO:T6-5740-T0382066 P1, SEQ NO:1014, TITLE:WINGS-ATTACH FITTINGS-RH WING #6 SPOILER JACK RIB AT STA SP1X31.675 AND SP1X40.425-BEAM ATTACHMENT HOLE REINFORCEMENT REPAIR-SRM DEVIATION. THE REPAIR CLASSIFIED AS CAT.A MAJOR PER GMM 6- 2-100.

Part: RIB — CRACKED (ZONE 600) · airframe 55,456 hrs · 30,302 cycles

1EA CRACK (15MM) WAS FOUND AT R/H WING CENTER FLAP RIB26 AFT AREA OF TOP SURFACE RIB FLANGE. PERFORMED CUT OUT DAMAGED FLANGE AND INSTALLED REPAIR ANGLE AT RH WING CENTER FLAP RIB26, S-2.8~REAR SPAR AND EXTERNAL PLATE AT RIB26~27,S-2.2~REAR SPAR FOR REPAIR I.A.W FEDEX EA NO:T6-5750-T0381883P1, SEQ NO:XXX TITLE :WINGS - FLIGHT SURFACES - RH CENTER FLAP-CRACKS IN UPPER FLANGES OF RIB 26 AND 27-ALI 575306-01-1A. THIS REPAIR IS CLASSIFIED AS CAT A AND MAJOR REPAIR PER GMM 6-2-100.

Part: STRINGER — DEFORMED (ZONE 100) · airframe 55,456 hrs · 30,302 cycles

TAIL STRUCTURAL FOUND S-36R STRAP DEFORM AT FR86 PLUS 10" AREA. REPLACED THE DAMAGE SECTION-L WITH NEW AT TAIL STRUCTURAL FR 86 PLUS 10" S-36R AREA I.A.W A300-600 SRM 51-72-10-001, PAGE 2. THIS REPAIR CLASSIFIED AS MINOR PER GMM 06-2-100.

Part: ANGLE — CRACKED (ZONE 100) · airframe 55,456 hrs · 30,302 cycles

RA COAXIAL CABLE SUPPORT BRACKET CRACK AT FR64, STGR 50RH~51RH REPLACED THE CRACKED RA COAXIAL CABLE SUPPORT BRACKET, AT FR64, STGR 50RH~51RH. I.A.W A300-600 SRM 51-72-10-001, PAGE 2. THIS REPAIR IS CLASSIFIED AS MINOR, PER GMM 6-2-100

Part: ANGLE — CRACKED (ZONE 200) · airframe 55,456 hrs · 30,302 cycles

RA COAXIAL CABLE SUPPORT BRACKET CRACK AT FR58~59, STGR 44RH SIDE. REPLACED THE CRACKED RA COAXIAL CABLE SUPPORT BRACKET, AT FR58~59, STGR 44RH SIDE. I.A.W A300-600 SRM 51-72-10-001, PAGE 2. THIS REPAIR IS CLASSIFIED AS MINOR. PER GMM 6-2- 100.

Part: SEAT TRACK — WORN (ZONE 200) · airframe 55,456 hrs · 30,302 cycles

MAIN DECK CARGO COMPARTMENT WAS FOUND SEAT TRACK CROWN WORN AT FR58 PLUS 1", - Y1959 CUT THE DAMAGED SEAT TRACK, FABRICATED THE NEW REPAIR SEAT TRACK AND WET INSTALLED REPAIR PARTS WITH FASTENERS I.A.W A300-600 SRM 53-10-16-201, PARA 10, FIG 208, PAGE 243-250 (POSITION:MAIN DECK FR58, -Y1959). THIS REPAIR CLASSIFIED AS MINOR PER GMM 06-2-100.

Part: ANGLE — DAMAGED (ZONE 200) · airframe 55,456 hrs · 30,302 cycles

MAIN DECK CARGO COMPARTMENT AFT PRESSURE BULKHEAD RH LOWER AREA WAS FOUND 1EA SUPPORT ANGLE BROKEN AS MARKED,FR80/82 REPLACED THE BROKEN SUPPORT ANGLE, AT MAIN DECK CARGO COMPARTMENT AFT PRESSURE BULKHEAD RH LOWER AREA FR80/FR82. I.A.W A300-600 SRM 51-72-10-001, PAGE 2. THIS REPARI IS CLASSIFIED AS MINOR, PER GMM 6-2-100.

Part: SKIN — DAMAGED (ZONE 300 RUDDER) · airframe 55,456 hrs · 30,302 cycles

2EA WATER TRAPPED AREAS WERE FOUND AT LH RUDDER T/E SCREW LINE NO.19(30MM*40MM) FASTENER AND RH RUDDER T/E SCREW LINE NO.39(20MM*80MM) FASTENER. ACCOMPLISHED THE COMPOSITE REPAIR AT LH SKIN SCREW LINE #19 AND RH SKIN SCREW LINE #39 OF RUDDER I.A.W A300-600 SRM 55-41-12-201, PARA.31, PAGE.313~319, FIG.222 & SRI:55-41-12- 201, IIR:55-41-12-2-006-00, PARA.3F, TABLE.207. THE REPAIR CLSSSIFIED AS CAT.B MAJOR PER GMM 6-2-100.

Part: SKIN — DAMAGED (ZONE 300) · airframe 55,456 hrs · 30,302 cycles

1EA WATER TRAPPED AREA(80MM*80MM) WAS FOUND AT RH ELEVATOR LOWER SKIN PANEL T/E FASTENER NO.9. *COUNTING FASTENER FROM I/B TO O/B * ACCOMPLISHED THE COMPOSITE REPAIR AT RH ELEVATOR LOWER SKIN T/E FASTENER #9 I.A.W A300-600 SRM 55-21-12-201, PARA.5B, PAGE.209~212, FIG.202 & SRI:55-21-12-201, IIR:55-21-12-2-001- 00, PAGE.3A, TABLE.202. THE REPAIR CLASSIFIED AS CAT.B MAJOR PER GMM 6-2-100.

Part: SKIN — DAMAGED (ZONE 300) · airframe 55,456 hrs · 30,302 cycles

2EA WATER TRAPPED AREAS(100MM*130MM ,70MM*150MM) WERE FOUND AT LH ELEVATOR LOWER SKIN PANEL T/E FASTENER NO.18 AND NO.24. *COUNTING FASTENER FROM I/B TO O/B * ACCOMPLISHED THE COMPOSITE REPAIRS AT LH ELEVATOR LOWER SKIN T/E FASTENERS #18 AND #24 I.A.W A300-600 SRM 55-21-12-201, PARA.5B, PAGE.209~212, FIG.202 & SRI:55-21-12-201, IIR:55-21-12-2-001-00, PAGE.3A, TABLE.202. THE REPAIR CLASSIFIED AS CAT.B MAJOR PER GMM 6-2- 100.

Part: PROFILE — CRACKED (ZONE 200) · airframe 55,456 hrs · 30,302 cycles

MAIN DECK FLOOR STRUCTURE WAS FOUND PROFILE-Z CRACK AT FR80/82,Y1447 REPLACED THE DAMAGED PART WITH NEW ONE AND INSTALLED WITH FASTENERS. I.A.W A300-600 SRM 51-72-10-001, PAGE 2 AND SRM 51-40-21-001, PARA 6, PAGE 7B~PAGE23. THIS REPAIR IS CATEGORY A AND CLASSIFIED AS MINOR PER GMM 06-2-100. AT MAIN DECK FLOOR STRUCTURE FR80/82, Y1447

Part: PLATE — CRACKED (ZONE 100) · airframe 55,456 hrs · 30,302 cycles

SIDE PLATE CRACK AT FWD CARGO COMPT FRAME 20 TO 21, Y1420 LH UNDER FLOOR POSITION. REPLACED THE CRACK WALL WITH NEW PART AT FWD CARGO COMPARTMENT BETWEEN FR20 TO FR21, Y1420 I.A.W A300-600 SRM 51-72-10-001, PAGE.2 AND 51-40-21-001, PARA.6, PAGE.7B~23. THIS REPAIR IS CLASSIFIED AS MINOR PER GMM 6-2-100.

Part: FLOOR SUPPORT — CRACKED (ZONE 200) · airframe 55,456 hrs · 30,302 cycles

MAIN DECK FLOOR STRUCTURE WAS FOUND PROFILE-Z CARCK AT FR80/82,-Y1447 REPLACED DAMAGE PROFILE-Z WITH NEW ONE AT MAIN DECK FLOOR STRUCTURE FR80/82, - Y1447. I.A.W A300-600 SRM 51-40-21-001, PARA 6 PAGE 7B - PAGE 23 & 51-72-10-001, PAGE 2. THIS REPAIR IS CLASSIFIED AS MINOR PER G.M.M 6-2-100

Part: SHEAR PLATE — CRACKED (ZONE 200) · airframe 55,456 hrs · 30,302 cycles

MAIN DECK FLOOR STRUCTURE WAS FOUND PLATE SHEAR CRACK AT FR79 PLUS 4", S-26L REPLACED THE DAMAGE PART WITH NEW ONE AND INSTALLED WITH FASTENERS. I.A.W A300-600 SRM 51-72-10-001, PAGE 2 AND SRM 51-40-21-001, PARA 7, PAGE 24~50. THIS REPAIR IS CATEGORY A AND CLASSIFIED AS MINOR PER GMM 06-2-100. AT MAIN DECK FLOOR STRUCTURE FR79 PLUS 4", S-26L

Part: INDICATOR — FAILED (UNKNOWN) · airframe 54,696 hrs · 29,797 cycles

ENGINE FIRE AND MULTIPLE SYSTEMS WARNINGS AND CAUTIONS AFTER ROTATION IN LIGHT RAIN. ENGINE TEMPERATURE INDICATIONS WERE NORMAL AUTOPILOT AUTOMATION WAS NOT AVAILABLE. EMERGENCY DECLARED. INDICATOR WERE ALL REPLACED AND ALL OPS CHECKS BEING SATISFACTORY. A GVI WAS PERFORMED OF ENGINES AND FOUND NO EVIDENCE OF A FIRE OR PNEUMATIC LEAK DAMAGE. OPS CHECKS GOOD. OK FOR SERVICE.

Part: CONTROL BOX — FAILED (PROXIMITY) · airframe 54,677 hrs · 29,786 cycles

AFTER TAKEOFF, AT GEAR RETRACT, COULDN`T RAISE MLG PAST NEUTRAL IN SYS #1, SWITCHED TO SYS #2, GEAR RETRACTED NORMAL, SEVERAL SYS FAULTED IMMEDIATELY. CABIN PRESSURE REGULATOR #1, BOTH ENGINE PER MODES FAULTED, ATS 1&2 FAULTED, PITCH TRIM #1 FAULTED, ALL PROBE HEATS FAULTED, CAPTS ADC & FD, & FUEL AFT TRANSFER FAULTED. COMPLIED WITH ECAM DIDN`T RESOLVE ISSUES. QRH COMPLIED WITH, DIDN`T FIX ISSUES. RETURNED TO KMSY DUE TO WX IN KMEM. GEAR & FLAPS EXTENDED NORMAL DURING APPROACH. ACCOMP BITE OF POSITION DETECT UNIT. FAULT CODES 02, 23, 24 AS WELL AS RED BOX FAIL LIGHT. INDICITIVE OF INTERNAL CIRCUIT FAILURE IAW TSM. R & R FAULTY UNIT IAW AMM. TEST PASSED. NO FAULTS NOTED. A/C OK FOR SERVICE.

Part: PROXIMITY SENSOR — FAILED · airframe 53,558 hrs · 29,040 cycles

AFTER TAKEOFF KMEM 18R. GEAR WOULD NOT RETRACT. HANDLE CAME UP. BUT AFTER DELAY ECAM DISPLAY OF GEAR WOULD NOT RETRACT. FOLLOWED ECAM AND QRH. RETURNED TO KMEM 18C. LANDING UNEVENTFUL REPLACED 64GB PROX SENSOR REF AMM 32-00-00-04. OPS CHECK GOOD. PERFORMED NORMAL GEAR EXTENSION AND RETRACTIONTEST IAW AMM 32-31-00-05, OPS CHECK GOOD. PERFORMED PSEU OPS TEST REF AMM 32-31-71-04, OPS CHECK GOOD.

Part: NONE — UNKNOWN (ZONE 100) · airframe 53,413 hrs · 28,947 cycles

AIRCRAFT REPAIR ASSESSMENT : EXISTING FLOOR BEAM REPAIR FOUND ON AFT CARGO COMPARTMENT AT FR 59, BTW -Y805 ~ -Y1470 POSITION. COMPLIED WITH ATTACHMENT B OF EO: E6-5100-7-5000 D7 PT1, TITLE: A300/A310 RPR IDENT&SUPPLEMENTAL MX REQ(SMR) TRK, INSPECTION OF EXISTING REPAIR DETERMINED IT TO BE CURRENT WITH FAA APPROVED DATA: A300-600 SRM 53-10-15-201, PARA.9, PAGE 237-242, FIG.207, THIS REPAIR IS CLASSIFIED AS MAJOR CATEGORY A REPAIR."MAJOR REPAIR"

Part: NONE — UNKNOWN (ZONE 400) · airframe 53,413 hrs · 28,947 cycles

AIRCRAFT REPAIR ASSESSMENT:EXISTING EXTERNAL DOUBLER REPAIR FOUND ON #1 PYLON O/B SIDE, AT RIB 8 POSITION. COMPLIED WITH ATTACHMENT B OF EO: E6-5100-7-5000 D7 PT1, TITLE: A300/A310 RPR IDENT&SUPPLEMENTAL MX REQ(SMR) TRK, INSPECTION OF EXISTING REPAIR DETERMINED IT TO BE CURRENT WITH FAA APPROVED DATA A300-600 SRM 54-51-31-201-2, PARA.5.A, FIG.201, PAGE.203-207, THIS REPAIR IS CLASSIFIED AS MAJOR CATEGORY B REPAIR, REF TO SRI 54-51-31- 201, IIR 54-51-31-2-001-00, PARA.3.A, TABLE.202, FIG.201, PAGE.202-205. "MAJOR REPAIR"

Part: SKIN — UNKNOWN (ZONE 600) · airframe 53,413 hrs · 28,947 cycles

AIRCRAFT REPAIR ASSESSMENT:EXISTING EXTERNAL DOUBLER REPAIR FOUND AROUND RH WING LWR SKIN L/E 613AB PANEL AT FWD O/B CUT OUT AREA. COMPLIED WITH ATTACHMENT B OF EO: E6-5100-7-5000 D7 PT1, TITLE: A300/A310 RPR IDENT&SUPPLEMENTAL MX REQ(SMR) TRK, INSPECTION OF EXISTING REPAIR DETERMINED IT TO BE CURRENT WITH FAA APPROVED DATA A300-600 SRM 53-15-63-201, PARA.5.A, PAGE 201-214, FIG.201, THIS REPAIR IS CLASSIFIED AS MAJOR CATEGORY A REPAIR."MAJOR REPAIR"

Part: SKIN — UNKNOWN (ZONE 500) · airframe 53,413 hrs · 28,947 cycles

AIRCRAFT REPAIR ASSESSMENT:EXISTING EXTERNAL DOUBLER REPAIR FOUND AROUND LH WING LWR SKIN L/E 513AB PANEL AT FWD O/B CUT OUT AREA. COMPLIED WITH ATTACHMENT B OF EO: E6-5100-7-5000 D7 PT1, TITLE: A300/A310 RPR IDENT&SUPPLEMENTAL MX REQ(SMR) TRK, INSPECTION OF EXISTING REPAIR DETERMINED IT TO BE CURRENT WITH FAA APPROVED DATA : A300-600 SRM 53-15-63-201, PARA.5.A, PAGE 201-214, FIG.201, THIS REPAIR IS CLASSIFIED AS MAJOR CATEGORY A REPAIR."MAJOR REPAIR"

Part: SKIN — UNKNOWN (ZONE 100) · airframe 53,413 hrs · 28,947 cycles

AIRCRAFT REPAIR ASSESSMENT:EXISTING EXTERNAL DOUBLER REPAIR FOUND ON FUSELAGE SKIN AT FR85,BTW STGR41L-44L. COMPLIED WITH ATTACHMENT B OF EO: E6-5100-7-5000 D7 PT1, TITLE: A300/A310 RPR IDENT&SUPPLEMENTAL MX REQ(SMR) TRK, INSPECTION OF EXISTING REPAIR DETERMINED IT TO BE CURRENT WITH FAA APPROVED DATA A300-600 SRM 53-19-12-001, PAGE.25 & 36, ITEM.150 & 53- 10-12-201, PARA.5, FIG.224(SHEET.3), PAGE.343-346 & 351/352, THIS REPAIR IS CLASSIFIED AS MAJOR CATEGORY B REPAIR, REF TO SRI 53-10-12-201, IIR 53-10-12-2-004-00, PARA.3.D, TABLE.208, FIG.204, PAGE.223-226. "MAJOR REPAIR"

Part: FLOOR PANEL — DAMAGED (ZONE 200) · airframe 53,413 hrs · 28,947 cycles

MAIN DECK CARGO COMPT #242QH FLOOR PANEL WAS FOUND 2 EA INSERTS DAMAGED. REPLACED THE DAMAGED INSERTS WITH NEW PARTS I.A.W FEDEX DRAWING NO:SRZ-25-005

Part: NONE — UNKNOWN (ZONE 400) · airframe 53,413 hrs · 28,947 cycles

AIRCRAFT REPAIR ASSESSMENT:EXISTING EXTERNAL DOUBLER REPAIR FOUND ON #1 PYLON I/B SIDE, AT RIB8 POSITION. COMPLIED WITH ATTACHMENT B OF EO: E6-5100-7-5000 D7 PT1, TITLE: A300/A310 RPR IDENT&SUPPLEMENTAL MX REQ(SMR) TRK, INSPECTION OF EXISTING REPAIR DETERMINED IT TO BE CURRENT WITH FAA APPROVED DATA A300-600 SRM 54-51-31-201-2, PARA.5.A, FIG.201, PAGE.203-207, THIS REPAIR IS CLASSIFIED AS MAJOR CATEGORY B REPAIR, REF TO SRI 54-51-31- 201, IIR 54-51-31-2-001-00, PARA.3.A, TABLE.202, FIG.201, PAGE.202-205. "MAJOR REPAIR"

Part: FLOOR PANEL — DAMAGED (ZONE 100) · airframe 53,413 hrs · 28,947 cycles

AFT CARGO COMPT #151LF FLOOR PANEL WAS FOUND INSERTS DAMAGED. REPLACED THE DAMAGED INSERTS WITH NEW PARTS I.A.W FEDEX DRAWING NO:SRZ-25-005

Part: NONE — UNKNOWN (ZONE 400) · airframe 53,413 hrs · 28,947 cycles

AIRCAFT REPAIR ASSESSMENT EXISTING EXTERNAL DOUBLER REPAIR FOUND ON #2 PYLON O/B SIDE, AT RIB 8 POSITION COMPLIED WITH ATTACHMENT B OF EO: E6-5100-7-5000 D7 PT1, TITLE: A300/A310 RPR IDENT&SUPPLEMENTAL MX REQ(SMR) TRK, INSPECTION OF EXISTING REPAIR DETERMINED IT TO BE CURRENT WITH FAA APPROVED DATA A300-600 SRM 54-51-31-201-2, PARA.5.A, FIG.201, PAGE.203-207, THIS REPAIR IS CLASSIFIED AS MAJOR CATEGORY B REPAIR, REF TO SRI 54-51-31- 201, IIR 54-51-31-2-001-00, PARA.3.A, TABLE.202, FIG.201, PAGE.202-205. "MAJOR REPAIR"

Part: NONE — CRACKED (ZONE 100) · airframe 53,413 hrs · 28,947 cycles

1EA CRACK INDICATION WAS FOUND AT RIGHT SIDE FR54 STGR44 FASTENER HOLE. ACCOMPLISHED THE WORK BY REAMING THE HOLE THIS IS CATE.B REPAIR I.A.W EA NO:6-5330- T0369235 P1, SEQ NO:000909, TITLE:FUSELAGE-PLATES & SKINS-RH JUNCTION BETWEEN LATERAL SKIN PANEL AND STRINGER S-44R AT FR54 ECCENTRIC BUSHING REPAIR-ALI 531582- 01-1A & A300-600 SRM 51-40-21-001, PARA.7, PAGE.24-50

Part: SEAT TRACK — CORRODED (ZONE 200) · corrosion level 2 · airframe 53,413 hrs · 28,947 cycles

MAIN DECK SEAT TRACK FOUND CORROSION NEAR FR 17 , Y 450 REMOVED DAMAGE PARTS & NEW TRACK INSTALLED WORK INSTRUCTION IAW A600-600 SRM 51- 40-21-001 PARA.6 , PAGE.7B-23 & SRM 51-76-20-201 PARA.4E , PAGE.210~211 , FIG.204.

Part: NONE — NONE (ZONE 100) · airframe 53,413 hrs · 28,947 cycles

THE LH LOWER FUSELAGE SKIN WAS FOUND DENT FR67 STGR35 ACCOMPLISHED THE CATE.B DOUBLER REPAIR TO THE LH FUSELAGE SKIN I.A.W A300-600 SRM 53- 10-12-201 PARA.5 PAGE.343-346 FIG.224(SHEET-4) & 53-17-12-001 PAGE.42-43 & SRI:53-10-12-201 IIR:53-10-12-2-004-00 PARA.3D TABLE.208

Part: SEAT TRACK — CORRODED (ZONE 200) · corrosion level 2 · airframe 53,413 hrs · 28,947 cycles

MAIN DECK SEAT TRACK FOUND CORROSION NEAR FR 12A 2" , Y 700 REPLACED THE SEAT TRACK WITH NEW ONE I.A.W A300-600 SRM 51-72-10-001 PAGE.2 & 51-40-21- 001 PARA.6 , PAGE.7B~23 .

Part: SEAT TRACK — CORRODED (ZONE 200) · corrosion level 2 · airframe 53,413 hrs · 28,947 cycles

MAIN DECK SEAT TRACK FOUND CORROSION NEAR FR 15C , Y 950 REPLACED THE SEAT TRACK WITH NEW ONE I.A.W A300-600 SRM 51-72-10-001 PAGE.2 & 51-40-21- 001 PARA.6 , PAGE7B-23.

Part: STIFFENER — CORRODED (ZONE 100) · airframe 53,413 hrs · 28,947 cycles

WASTE WATER SERIVE PANEL COMP'T LOWER CUTOUT STIFFENER AREA CORROSION AT FR12A POSITION. REPLACED THE SIFFENER WITH NEW ONE I.A.W A300-600 SRM 51-72-10-001 , PAGE.2 .

Part: ACTUATOR — NONE (N/A) · airframe 52,576 hrs · 28,427 cycles

PDIS 721 29-02 1252 06OCT21 MEM OPEN U GREEN SYSTEM HAD HYD LOW PRESSURE. COMPLIED WITH QRH. INFO 06OCT21 04:43 MC1 R LOST GREEN HYD SYSTEM QUANTITY DOWN TO BOTTOM OF YELLOW BAND. FOLLOWED BY LOSS OF SYSTEM PRESSURE. COMPLIED WITH QRH. MANUAL GEAR EXTENSION WAS USED. SHGN 06OCT21 05:18 MEM U PER CREW DEBRIEF, GREEN SYS LOW QTY AFTER LEVEL OFF, SYSTEM QTY CAME BACK UP AFTER GEAR EXTENSION. RESERVOIR CURRENTLY SHOWING 3 GALLONS ON GAUGE. FOUND EXCESSIVE FLUID IN GEARWELL AND ON DOORS. SUSPECT LEAK IN SAME AREA. FACT 06OCT21 16:25 MEM REMOVED AND REPLACED MLG DOOR ACT CYLINDER IN REF TO A300-600 AMM 32-31-35- 04. PERFORMED OPS AND LEAKS CHECKS. ALL CHECKS GOOD. A/C OK FOR SERVICE.

Part: ALTIMETER — FAILED (STANDBY) · airframe 52,387 hrs · 28,316 cycles

AT FL 360 THE STANDBY ALTIMETER WAS READING 300 FEET HIGHER THAN THE CAPTAIN AND FO ALTIMETERS. AT LOWER ALTITUDES IT RETURNED TO NORMAL. REF GMM 12-7-600. STANDBY ALTIMETER, CREW REPORTED MAIN ALTIMETERS OPS NORMAL. REMOVED AND REPLACED STANDBY ALTIMETER IAW M/M 34-12- 22-04. OPS CHECKS NORMAL AT THIS TIME. OK FOR SERVICE.

Part: ADC — MALFUNCTIONED (NR 2) · airframe 52,369 hrs · 28,304 cycles

ON GROUND F/O, CAPT , STBY ALTIMETER W/IN 50 FEET. AT 290 F/O AND CAPT ALTIMETER AGREED . AT 330 F/O READ 32.6 AND STBY READ 330 . F/O AIRSPEED WAS 10 TO 15 KTS SLOWER THAN CAPTAIN R/I 07AUG21 01:33 SNA U REASON CODE : PREMATURE REMOVAL/INSTALLATION OFF MPN: 4045053-914 POS: 2 SRL: 87020534 TAG NBR: H56414 ON MPN: 4045053-914 CPN: 3412889 SRL: 94081751 TAG NBR: 596458 FACT 07AUG21 01:33 SNA U PERFORMED AIR DATA SYSTEM BITE TEST PER TSM 34-10-00NOT ABLE TO DUPLICATE THE PILOT REPORT, ALL READING ARE NORMAL. R/R #2 ADC PER MM 34-11-34 AND #2 MAIN ALTIMETER PER MM 34-12-21 ADS BITE TEST ALL READINGS NORMAL A/C OK FOR SERVICE PERFORMED AIR DATA SYSTEM BITE TEST PER TSM 34-10-00. NOT ABLE

Part: VALVE — CONTAMINATED (MLG) · airframe 52,118 hrs · 28,131 cycles

ON APPROACH SELECTED GEAR DOWN. THE LEFT MAIN GEAR AND DOOR WERE SLOW ENOUGH TO CAUSE A GEAR NOT DOWN ECAM, BUT CANCELLED A FEW MOMENTS LATER AS THE CYCLE COMPLETED. NORMAL OPS THEEAFTER. DISCOVERED MATERIAL IN L/H MLG RESTRICTOR VALVE. REMOVED AND REPLACED RESTRICTOR VALVE IAW AMM A300-600 32-31-57-04. PERFORMED NORMAL EXTENSION AND RETRACTION TEST WITH SYS 1 AND SYS 2 IAW AMM 32-31-00-5. OPS CHECKED GOOD. NO LEAKS NOTED ON RESTRICTOR VALVE.

Part: SKIN — CORRODED (LT WING) · airframe 50,631 hrs · 27,253 cycles

L/H WING LOWER SKIN T/E OUTBRD AT RIB 28, INSIDE PANEL 590BB UPPER SKIN CORRODED (STREAMER) L/H WING LOWER SKIN T/E OUTBRD AT RIB28 REPAIRED PER FDX EA 6-5720-T0352251 P1; TITLED: WING-SECONDARY WING STRCT-LW UPPER SKIN,TRAILING EDGE OVERHANG, RIB 24- 29, CORROSION. TRAILING EDGE RIB 2, REPAIRED PER FDX EA 6-5720-T0352251 P2 TITLED: WING-SECONDARY WING STRCT-LW UPPER SKIN,TRAILING EDGE OVERHANG, RIB 24-29, CORROSION

Part: SKIN — GOUGED (RT WING TE FLAP) · airframe 50,631 hrs · 27,253 cycles

RW INBD FLAP UPPER SURFACE, FWD OTBD CORNER IS GOUGED. COMPLIED WITH EA #:6-5750-T0352296 (P1) TITLE: WING-FLIGHT SURFACES-RH WING INBOARD FLAP UPPER SKIN, EXISTING REPAIR DAMAGED FLAP UPPER SKIN, EXISTING REPAIR DAMAGED

Part: SHEAR PLATE — CRACKED (FRAME 38) · airframe 50,631 hrs · 27,253 cycles

FWD CARGO PIT RH SIDE BELOW FLOOR LEVEL AT FRAME 38 INTERCOSTAL LWR FWD CORNER IS CRACKED REMOVED AND REPLACED FWD CARGO INTERCOSTAL AT FR38 RH SIDE PER A300-600 SRM 51-40-21

Part: ATTACH FITTING — CORRODED (WING TO PYLON) · airframe 50,631 hrs · 27,253 cycles

#1 PYLON TO WING ATTACH FITTING @ RIB 12, O/B LOWER LUG, FWD SHACKLE PITTED #1 PYLON TO WING ATTACH FTG AT RIB 12, O/B LOWER LUG FWD SHACKLE REPAIRED PER FDX FDX FDX EA 6-5450-T0351950 P1, TITLED: NECELLES/PYLON-WING PYLON/STRUT-#1 PYLON, RIB12, OUTBD WING-TO-PYLON FITTING, PITTING

Part: ROLLER TRAY — CORRODED (FWD CARGO) · airframe 50,631 hrs · 27,253 cycles

FWD PIT R/H OUTBD ROLLER TRAY FWD OUTBD MOUNT HOLE FOR DBL LATCH CORRODED REPAIRED ROLLER TRAY IAW A300-600 SRM 53-10-15 FIG 202, REMOVED AND REINSTALLED ROLLER TRAY PER A300-600 SRM AMM 25-52-24-04, REMOVED CORROSION AND FOUND TO BE OUT OF LIMITS PER A300-600 SRM 53-10-15 ORIG .125 REMAINING .085 MATL LOSS .040, FABRICATED REPAIR DOUBLER PER A300-600 SRM 53- 10-15 FIG 202, INSTALLED REPAIR DOUBLER PER A300-600 SRM 53-10-15 FIG 202, ALODINED AND PRIMED REPAIR DOUBLER PER A300-600 SRM 51-21-10, TOP COATED REPAIR DOUBLER PER A300-600 SRM 51-75-10, PART MARKED ROLLER TRAY IAW A300-600 GMM 07-1000 (FED EX DAN 68-01 HAECO GSO 11 FEB 20).

Part: INTERCOSTAL — CRACKED (FRAMES 20-21) · airframe 50,631 hrs · 27,253 cycles

FWD CARGO BELOW THE FLOOR LEVEL UNDER THE BALL MAT AREA FWD L/H CORNER BETWEEN FRAMES 20 AND 21 APPROX LBL56 THE STRUCTURAL INTERCOSTAL HAS 2EA CRACKS (AFT LOWER CORNER AND FWD UPPER CORNER) REMOVED AND REPLACED INTERCOSTAL IAW A300-600 SRM 51-40-21

Part: PLATE — CORRODED (NR 2 NACELLE) · airframe 50,631 hrs · 27,253 cycles

#2 ENGINE PYLON FAIRING O/B SKIN SPLICE PLATE CORRODED REMOVED WORN SPLICE PLATE, REFERENCE A300-600 SRM 54-55-51, ALODINED & PRIMED NEW SPLICE PLATE, REFERENCE A300-600 SRM 51-21-10, INSTALLED NEW SPLICE PLATE, REFERENCE A300-600 SRM 51-40-21

Part: STRUCTURE — CRACKED (LT AILERON) · airframe 50,631 hrs · 27,253 cycles

LW ALL-SPEED AIL FWD O/B FLANGE HAS CRACK STREAMER ATTACH REMOVED LT. WING AILERON O/B SKIN PANEL IAW A300-600 SRM 51-40-21, FABRICATED SKIN PANEL IAW EA 6-5750-T0352219. INSTALLED SKIN PANEL IAW A300-600 SRM 51-40-21 AB DWG A57661001

Part: STRUCTURE — CRACKED (LT AILERON) · airframe 50,631 hrs · 27,253 cycles

LW ALL-SPEED AIL FWD O/B FLANGE HAS CRACK STREAMER ATTACH REMOVED LT. WING AILERON O/B SKIN PANEL IAW A300-600 SRM 51-40-21, FABRICATED SKIN PANEL IAW EA 6-5750-T0352219. INSTALLED SKIN PANEL IAW A300-600 SRM 51-40-21 AB DWG A57661001

Part: LONGERON — CRACKED (NR 2 NACELLE) · airframe 50,631 hrs · 27,253 cycles

#2 PYLONAFT FAIRING, FWD I/B "U" CHANNEL CRACKED AT LOWER HOLE REMOVED WORN CHANNEL REFERENCE A300-600 SRM 51-40-21, FABRICATED NEW CHANNEL, REFERENCE A300-600 SRM 54-55-51, 51-40-44 & FED-X GMM 07-0-1001, ALODINED & PRIMED NEW CHANNEL, REFERENCE A300-600 SRM 51-21-10 INSTALLED NEW CHANNEL, REFERENCE A300-600 SRM 51-40-21

Part: SKIN — CORRODED (RT WING) · airframe 50,631 hrs · 27,253 cycles

RIGHT WING LOWER SKIN HAS CORROSION @ FRONT SPAR AREA BETWEEN RIB 22 AND RIB 23. REMOVED CORROSION BETWEEN RIB 22 AND 23 IAW A300-600 SRM 51-74-10 AND REPAIRED AREA IAW FEDEX EA: 6-5730-T0351926, P1. TITLE: WINGS - PLATES AND SKIN - RH WING LOWER SKIN RIB 20 TO 23 CORROSION.

Part: SKIN — CORRODED (RT WING) · airframe 50,631 hrs · 27,253 cycles

RIGHT WING LOWER SKIN HAS CORROSION BETWEEN RIB 20 AND RIB 21. REMOVED CORROSION BETWEEN RIB 20 AND 21 IAW A300-600 SRM 51-74-10 AND REPAIRED AREA IAW FEDEX EA: 6-5730-T0351926, P1. TITLE: WINGS - PLATES AND SKINS - RH WING LOWER SKIN RIB 20 TO 23 CORROSION.

Part: PAN — CRACKED (ROLLER TRAY) · airframe 50,631 hrs · 27,253 cycles

AFT CARGO BELOW FLOOR FR 58 RBL 45 THE POWER ROLLER TRAY IS CREASED/CRACKED IN THE CORNER REMOVED PDU PER FDX A300-600 AMM 25-22-26-04, REMOVED AND REPLACED TRAY PER FDX A300- 600 SRM 51-40-21, REINSTALLED PDU PER FDX A300-600 AMM 25-52-26-04, OPS CHECK GOOD

Part: FLOOR PANEL — DAMAGED (NOT REPORTED) · airframe 50,631 hrs · 27,253 cycles

FLOOR PANEL 131ZF HAS AREAS OF MISSING EDGE FILL AND EDGE DAMAGED. FABRICATED A NEW FLOOR PANEL IAW SRZ-25-005 REVISION R.

Part: STRUCTURE — GOUGED (LT WING SLAT) · airframe 50,631 hrs · 27,253 cycles

LEFT WING, #1 SLAT, AFT FACE, OVER PYLON, AREA GOUGED. REPAIRED GOUGE ON LEFT WING, #1 SLAT, AFT FACE, OVER PYLON IAW FEDEX EA# 6-2780- T0351873 P1 AND A300-600-SRM-51-77-12 PARA. 4.B. REMOVED AND REINSTALLED L/H WING FOLDING NOSE IAW A300-600 27-81-33-04 AND TESTED GOOD IAW A300-600 AMM 27-80-00-0301. NO CONTACT OR CHAFING NOTED BETWEEN BONDED DOUBLERS AND L/E SKIN IAW FEDEX EA# 6-2780-T0351873 P1; 6-2780-T0351873-P1 FLIGHT CONTROL - L/E SLATS & FLAPS - #1 SLAT, TRAILING EDGE WEDGE, LOWER SKIN, GOUGE REPAIRS MAJOR REPAIR DOT REMOVED

Part: BRACKET — CHAFED (CARGO DOOR) · airframe 50,631 hrs · 27,253 cycles

BULK CARGO DOOR INTERNAL STRUCTURAL BRACKET HAS DRILL START REMOVED AND REPLACED BRACKET IAW 51-40-21/AIRBUS DWG A52378159

Part: FRAME — CORRODED (FRAME 40) · airframe 50,631 hrs · 27,253 cycles

R/H SIDE LOWER HOLE AT FR40 HAS CRACK INDICATION, IN BORE, SHOWING AT THE 3 O'CLOCK POSITION LOOKING OUTBOARD, HOLE DEPTH MEASURES FROM 0.921" TO 0.990" FROM EDGE OF RECESS REAMED HOLE TO .6324 PER A300-600 SRM 51-40-44. INSTALLED BUSHES(3EA), WASHERS (2EA), AND NEW BOLT PER FDX EA# 6-5710-T0314674 B P3 TITLE: WINGS - BASIC WING STRUCTURE - CRACK HOLES IN CENTER WING JOINT - FR 40 LH/RH

Part: STRINGER — CORRODED (FUSELAGE) · airframe 50,631 hrs · 27,253 cycles

BULK CARGO COMPARTMENT INTERNAL BELLY SKIN STRINGER IS CORRODED BS 63 - BS 64 LBL 12. REPAIRED STRINGER CORRODED BS 63 - BS 64, LBL 12 PER SRM 53-10-14 FIG 201.

Part: FLOOR PANEL — DELAMINATED (ZONE 100) · airframe 50,631 hrs · 27,253 cycles

MLG WHEEL WELL FLOORBOARD PANEL 147CF DELAMINATED ON LOWER SIDE OF PANEL FABRICATED NEW MLG WHEEL WELL FLOORBOARD PANEL 147CF TAW FED EX STANDARD REPAIR DRAWING-FLOOR PANEL REPLACEMENT SRZ 25-005 REV R

Part: FLOOR PANEL — DAMAGED (MLG WW) · airframe 50,631 hrs · 27,253 cycles

MLG WHEEL WELL FLOOR PANEL 147AF PUNCTURED ON LOWER SIDE OF PANEL FABRICATED NEW MLG WHEEL WELL FLOOR PANEL 147AF IAW STANDARD REPAIR DRAWING. FLOOR PANEL REPLACED IAW SRZ 25-005 REV R.

Part: FLOOR PANEL — DAMAGED (ZONE 100) · airframe 50,631 hrs · 27,253 cycles

MLG WHEEL WELL FLOOR PANEL 147EF DELAMINATED ON UPPER SIDE OF PANEL. FABRICATED NEW MLG WHEEL WELL FLOOR PANEL 147EF IAW STANDARD REPAIR DRAWING- FLOOR PANEL REPLACEMENT SRZ25-005 REV R

Part: FLOOR PANEL — DELAMINATED (FWD CARGO) · airframe 50,631 hrs · 27,253 cycles

PANEL 131QF HAS AREAS OF MISSING EDGE FILL AND EDGE DAMAGE FABRICATED NEW FLOOR PANEL 131QF FOR FWD CARGO COMP IAW A300-600 SRZ 25-005 REV R

Part: FLOOR PANEL — DELAMINATED (FWD CARGO) · airframe 50,631 hrs · 27,253 cycles

PANEL 131YF HAS AREAS OF MISSING EDGE FILL AND EDGE FABRICATED NEW PANEL 131YF FOR FWD CARGO FLOOR IAW A300-600 SRZ 25-005 REV R

Part: FLOOR SUPPORT — CORRODED (FRAME 38) · airframe 50,631 hrs · 27,253 cycles

FWD CARGO BELOW THE FLOOR LEVEL AT FRAME 38.1 APPROX RBL56 STRUCTURAL INTERCOSTAL IS CRACKED AND CORRODED AT THE SAME LOCATION REMOVED AND REPLACED NEW INTERCOSTAL IAW A300-600 SRM 51-40-21/SRM 51-40-44/AIRBUS DWG A53778330 & A53778329

Part: BRACE — CRACKED (FRAME 38) · airframe 50,631 hrs · 27,253 cycles

FWD CARGO COMPARTMENT R/H SIDE JUST BELOW THE MAIN CABIN FLOOR LEVEL AT APPROX RBL105 BETWEEN FRAMES 38.1 AND 38.2 SUB-STRUCTURAL BRACE IS CRACKED . FABRICATED NEW SUPPORT PER DWG A53781038 ISSUE G, REMOVED AND REPLACED SUPPORT PER DWG A53781962 ISSUE E AND SRM 51-40-21.

Part: FLOOR SUPPORT — CRACKED (FRAME 38) · airframe 50,631 hrs · 27,253 cycles

FWD CARGO BELOW THE FLOOR LEVEL AT FRAME 38.1 APPROX RBL56 STRUCTURAL INTERCOSTAL IS CRACKED AND CORRODED AT THE SAME LOCATION REMOVED AND REPLACED NEW INTERCOSTAL IAW A300-600 SRM 51-40-21 AND SRM 51-40-44

Part: BRACE — CRACKED (FRAME 38) · airframe 50,631 hrs · 27,253 cycles

FWD CARGO COMPARTMENT L/H SIDE JUST BELOW THE MAIN CABIN FLOOR LEVEL AT APPROX LBL105 BETWEEN FRAMES 38.1 AND 38.2 SUB STRUCTURAL BRACE IS CRACKED FABRICATED NEW SUPPORT PER DWG A53781038 ISSUE G, REMOVED AND REPLACED SUPPORT PER DWG A53781962 ISSUE E AND SRM 51-40-21.

Part: BRACE — CRACKED (FRAME 38) · airframe 50,631 hrs · 27,253 cycles

FWD CARGO COMPARTMENT R/H SIDE JUST BELOW THE MAIN CABIN FLOOR LEVEL AT APPROX RBL105 BETWEEN FRAMES 38 AND 38.1 SUB-STRUCTURAL BRACE IS CRACKED (STREAMER ATTACHED) FABRICATED NEW SUPPORT PER AIRBUS DWG A53781038 ISSUE G, REMOVED AND REPLACED SUPPORT PER AIRBUS DWG A53781962 ISSUE E AND A300-600 SRM 51-40-21, PART MARKED PER FEDEX GMM 07-0-1001

Part: WEB — CORRODED (FRAMES 11-14) · airframe 50,631 hrs · 27,253 cycles

FLOOR SUPPORT STRUCTURE UNDER LAV CORRODED @ LBL30 BETWEEN FRAMES 11-14 FABRICATED NEW WEB PER AIRBUS DWG A53612214 ISSUE N, REMOVED AND REPLACED WEB AND SUPPORT PER SRM 51-40-21 AND DWG A53612214 ISSUE N.

Part: BUSHING — CORRODED (FLAP ATTACH LINK) · airframe 50,631 hrs · 27,253 cycles

RW CENTER FLAP O/B AFT LINK UPPER ATTACH LINK BUSHING IS CORRODED AND WORN REMOVED AND REPLACED IAW CMM 57-53-25

Part: BUSHING — CORRODED (FLAP ATTACH LINK) · airframe 50,631 hrs · 27,253 cycles

RW CENTER FLAP I/B AFT ATTACH LINK UPPER END BUSHING IS PITTED REMOVED AND REPLACED IAW CMM 57-53-25

Part: SUPPORT FITTING — DAMAGED (LT HORIZ STAB) · airframe 50,631 hrs · 27,253 cycles

LEFT HORIZ STAB 333AT UPPER APRON SUPPORT FITTING BROKEN. REMOVED AND REPLACED SUPPORT FITTING IAW SRM 51-40-21.

Part: SUPPORT FITTING — DAMAGED (RT HORIZ STAB) · airframe 50,631 hrs · 27,253 cycles

RIGHT HORIZ STAB 343AT FWD APRON SUPPORT FITTING BROKEN. REMOVED AND REPLACED SUPPORT FITTING IAW SRM 51-40-21.

Part: SUPPORT — CRACKED (RT WING) · airframe 50,631 hrs · 27,253 cycles

RW BETWEEN #4 AND #5 SPOILERS OTBD OF SPOILER HINGE RIB, WEB FWD LWR CORNER IS CRACKED. REMOVED AND REPLACED DAMAGED RIB IAW A300-600 SRM 51-40--21 AND AIRBUS DWG A57240681 ISSUE P

Part: SHEAR PLATE — CRACKED (FUSELAGE) · airframe 50,631 hrs · 27,253 cycles

AFT CARGO FR54.2 - FR54.3 STR 44R SHEAR PLATE IS CRACKED. REMOVED AND REPLACED SHEAR PLATE IAW SRM 51-40-21.

Part: ANGLE — CORRODED (FUSELAGE) · airframe 50,631 hrs · 27,253 cycles

FWD CARGO BELOW THE FLOOR LEVEL BETWEEN FRAMES 38.1 AND 38.2 APPROX RBL56 ROLLER TRAY MOUNT STRUCTURE IS CORRODED AT FASTENER HOLE. REMOVE AND REPLACE ANGLE IAW SRM 51-40-21.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 50,631 hrs · 27,253 cycles

BULK CARGO COMPARTMENT FLOORBEAM UPPER SURFACE IS CORRODED BS 66 - BS 66 BL32 RBL42. REMOVE AND REPLACE CROSSBEAM IAW SRM 51-40-21.

Part: SHEAR TIE — CORRODED (FUSELAGE) · airframe 50,631 hrs · 27,253 cycles

AFT CARGO COMPARTMENT RIGHT SIDE SHEAR TIE IS CORRODED BELOW FLOOR BS 58 - RBL55. REMOVED AND REPLACED SHEAR TIE IAW SRM 51-40-21.

Part: ATTACH BRACKET — CRACKED (FUSELAGE) · airframe 50,631 hrs · 27,253 cycles

FWD CARGO PIT RT SIDE BELOW FLOOR LEVEL AT FRAME 37 INTERCOSTAL LWR FWD ATTACH BRACKET IS CRACKED. REMOVED AND INSTALLED NEW CLIP (BRACKET) IN FWD CARGO PIT RT SIDE BELOW FLOOR LEVEL AT FRAME 37 IAW SRM 51-40-21.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 50,631 hrs · 27,253 cycles

BULK CARGO COMPARTMENT FLOORBEAM UPPER SURFACE IS CORRODED BS 67 - BS 67, BL29 RBL39 REMOVED AND REPLACED CROSSBEAM IAW SRM 51-40-21

Part: NUT PLATE — CORRODED (FUSELAGE) · airframe 50,631 hrs · 27,253 cycles

AFT CARGO COMPARTMENT RIGHT SIDE FLOOR SUPPORT IS CORRODED AT 2 NUT PLATES BELOW FLOOR BS 58-RBL 55. REMOVED AND REPLACED NUT PLATES IAW SRM 51-40-21, REMOVE CORROSION IAW SRM 51-74-10, MATERIAL NOMINAL 0.130, MATL REMOVED 0.010, REMAINING 0.120, MINIMUM MATL ALLOWED 0.085, IN LIMITS IAW SRM 53-10-15, ALODINE AND PRIMED AREA IAW SRM 51-21-10, TOP COATED AREA IAW SRM 51-75-10, INSTALLED SPLICE AND TRAY AND SIDE SLANT SUPPORT IAW SRM 51-40-21.

Part: FITTING — CRACKED (FUSELAGE) · airframe 50,631 hrs · 27,253 cycles

FWD CARGO BELOW THE FLOOR LEVEL AT FRAME 38.1 APPROX LBL56 STRUCTURAL INTERCOSTAL L ANGLE CLIP CRACKED. REMOVED AND INSTALLED NEW CLIP IN FWD CARGO BELOW THE FLOOR LEVEL AT FRAME 38.1 APPROX LBL56 IAW SRM 51-40-21.

Part: FITTING — CRACKED (FUSELAGE) · airframe 50,631 hrs · 27,253 cycles

THE CARGO BELOW THE FLOOR LEVEL AT FRAME 38 APPROX LBL56 STRUCTURAL INTERCOSTAL L ANGLE CLIP IS CRACKED. REMOVED AND INSTALLED NEW CLIP IN FWD CARGO BELOW THE FLOOR LEVEL AT FRAME 38 APROX LBL56 IAW SRM 51-40-21.

Part: SUPPORT ANGLE — CRACKED (FUSELAGE) · airframe 50,631 hrs · 27,253 cycles

AFT CARGO PIT CEILING AREA FWD BULKHEAD AT FR54 BL0, LINER SUPPORT ANGLE IS CRACKED. REMOVED AND REPLACED LINER SUPPORT ANGLE ON AFT PIT FWD BULKHEAD AT BL0 IAW DWG A5341012A REV A.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 50,631 hrs · 27,253 cycles

FWD CARGO BELOW THE FLOOR LEVEL BETWEEN FRAMES 37 AND 38 APPROX LBL56 STRUCTURAL INTERCOSTAL IS CRACKED AT THE FWD CORNER. REMOVED AND INSTALLED NEW INTERCOSTAL IN FWD CARGO BELOW THE FLOOR LEVEL BETWEEN FRAMES 37 AND 38 APPROX APPROX LBL56 IAW SRM 51-40-21 AND 51-40-44.

Part: BRACKET — CORRODED (FUSELAGE) · airframe 50,631 hrs · 27,253 cycles

FWD CARGO BELOW THE FLOOR LEVEL AT FRAME 26 APPROX LBL56 ROLLER TRAY MOUNT STRUCTURE IS CORRODED AT FASTENER HOLE. INSTALLED NEW BRACKET IAW SRM 51-40-21.

Part: ATTACH BRACKET — CRACKED (FUSELAGE) · airframe 50,631 hrs · 27,253 cycles

FWD CARGO PIT R/H SIDE BELOW FLOOR LEVEL AT FRAME 38 INTERCOSTAL LOWER FWD ATTACH BRACKET IS CRACKED REMOVED AND REPLACED ATTACH BRACKET IAW A300-600 SRM 51-40-21

Part: ANGLE — CORRODED (FUSELAGE) · airframe 50,631 hrs · 27,253 cycles

FWD CARGO PIT R/H SIDE BELOW FLOOR LEVEL AT FRAME 30 OUTBD FLOOR SUPPORT LOWER SURFACE CORRODED REMOVED AND REPLACED NEW ANGLE IAW A300-600 SRM 51-40-21

Part: FRAME — CORRODED (ROLLER TRAY) · airframe 50,631 hrs · 27,253 cycles

AFT CARGO BELOW FLOOR FR57.2 RBL40 THE ROLLER TRAY ON THE BOTTOM SIDE HAS MULTIPLE NUT PLATES WITH CORROSION UNDERNEATH REPAIRED PDU ROLLER FRAME ASSY IAW EA 6-2550-T0351712-P1

Part: INTERCOSTAL — DEFORMED (FUSELAGE) · airframe 50,631 hrs · 27,253 cycles

FWD CARGO BELOW THE FLOOR LEVEL AT FRAME 33 APPROX LBL56 STRUCTURAL INTERCOSTAL IS DEFORMED AT THE FWD FWD CORNER. REMOVED AND INSTALLED NEW INTERCOSTAL IAW SRM 51-40-21 AND SRM 51-40-44.

Part: SUPPORT FITTING — CRACKED (RT HORIZ STAB) · airframe 50,631 hrs · 27,253 cycles

RIGHT HORIZONTAL STAB APRON (434AT) SUPPORT FITTING CRACKED REMOVED AND REPLACED SUPPORT FITTING RIGHT HORIZONTAL STAB APRON PANEL 434AT IAW A300-600 SRM 51-40-21

Part: SUPPORT ANGLE — CRACKED (FUSELAGE) · airframe 50,631 hrs · 27,253 cycles

AFT CARGO CEILING AREA, FWD BULKHEAD FR54 @ RBL77, THE SUPPORT ANGLE FOR THE LINER IS CRACKED REMOVED AND REPLACED DAMAGED SUPPORT ANGLE IAW A300-600 SRM 51-40-21

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 50,631 hrs · 27,253 cycles

MAIN CABIN FLOOR PANEL 242MF DELAMINATED IN TWO PLACES, MARKED FABRICATED NEW FLOOR PANEL 242MF IAW DWG-SRZ-25-005 REV. R AND GMM 07-0-1000.

Part: FLOOR PANEL — DAMAGED (CABIN) · airframe 50,631 hrs · 27,253 cycles

MAIN CABIN FLOOR PANEL 242EK IS DAMAGED AT AFT END AND HAS DAMAGED INSERTS. FABRICATED NEW FLOOR PANEL 242EK IAW DWG-SRZ-25-005 REV. R AND GMM 07-0-1000.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 50,631 hrs · 27,253 cycles

251VF HAS DELAMINATED SKIN ON THE BOTTOM SIDE FABRICATED NEW FLOOR PANEL 251VF IAW DWG-SRZ-25-005 REV. R AND GMM 07-0-1000.

Part: FLOORBOARD — DAMAGED (CABIN) · airframe 50,631 hrs · 27,253 cycles

FLOOR PANEL 222RF SECTION OF SKIN MISSING FABRICATED NEW FLOOR PANEL 222RF IAW DWG-SRZ-25-005 REV. R AND PART MARKED PANEL IAW GMM 07-0-1000

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 50,631 hrs · 27,253 cycles

MAIN CABIN FLOOR PANEL 242GF HAS CRUSHED CORE AND DELAMINATED FABRICATED NEW FLOOR PANEL 242GF IAW DWG-SRZ-25-005 REV. R AND GMM 07-0-1000.

Part: FLOOR PANEL — DELAMINATED (NOT REPORTED) · airframe 50,631 hrs · 27,253 cycles

FLOOR PANEL 252YH HAD 4 DAMAGED INSERTS AND DELAMINATED SKIN ON THE BOTTOM SIDE. FABRICATED A NEW FLOOR PANEL IAW DWG SRZ-25-005, REV R, AND GMM 07-0-1000.

Part: FLOOR PANEL — PUNCTURED (MAIN CABIN) · airframe 50,631 hrs · 27,253 cycles

MAIN CABIN FLOOR PANEL 241MH HAD 2 PUNCTURES THRU PANEL. FABRICATED A NEW FLOOR PANEL IAW DWG SRZ-25-005, REV R, AND GMM 07-0-1000.

Part: FLOOR PANEL — DAMAGED (MAIN CABIN) · airframe 50,631 hrs · 27,253 cycles

MAIN CABIN FLOOR PANEL 241DF HAS SEVERAL AREAS OF CRUSHED CORE FABRICATED NEW FLOOR BOARD PANEL 241DF IAW A300-600 SRZ-25-005 REV. R .

Part: FLOOR PANEL — DAMAGED (CABIN) · airframe 50,631 hrs · 27,253 cycles

FLOOR PANEL 262KF HAS CORNER PIECE BROKEN OFF. FAB NEW PANEL 262KF, LOCATED AND DRILLED HOLES INSTALLED INSERTS AND APPLIED EDGE POTTING, RESTORED FINISH, AND PART MARKED IAW SRZ 25-005 REV R, AMM 51-75-10, GMM 07-0-1000.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 50,631 hrs · 27,253 cycles

FLOOR PANEL 261KF HAS BROKEN INSERT AND DELAMINATION ON THE BOTTOM SIDE. FAB NEW PANEL 261KF, LOCATED AND DRILLED HOLES, INSTALLED INSERTS AND APPLIED EDGE POTTING, RESTORED FINISH AND PART MARKED IAW SRZ 25-005 REV R, AMM 51-75-10, GMM 07-0-1000.

Part: FLOOR PANEL — CRACKED (CABIN) · airframe 50,631 hrs · 27,253 cycles

MAIN DECK FLOOR PANEL 232TG IS CRACKED FABRICATED NEW PANEL 232TG LOCATED AND DRILLED HOLES INSTALLED INSERTS AND APPLIED EDGE POTTING RESTORED FINISH PART MARKED IAW A300-600 SRZ 25-005 REV. R, AMM 51-75-10, GMM 07-0-1000

Part: FLOORBOARD — TORN (MAIN DECK) · airframe 50,631 hrs · 27,253 cycles

MAIN DECK FLOOR PANEL 231JG IS TORN AT FASTENER HOLE. FABRICATED NEW PANEL 231JG, LOCATED AND DRILLED HOLES INSTALLED INSERTS AND APPLIED EDGE POTTING RESTORED FINISH AND PART MARKED IAW SRZ 25-005 REV R, AMM 51-75-10, GMM 07-0-1000.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 50,631 hrs · 27,253 cycles

MAIN DECK FLOOR PANEL 231DH IS DELAMINATED FABRICATED NEW PANEL 231DH LOCATED AND DRILLED HOLES, INSTALLED INSERTS AND APPLIED EDGE POTTING RESTORED FINISH. PART MARKED IAW A300-600 SRZ 25-005 REV. R, AMM 51-75-10, GMM 07-0-1000

Part: FLOOR PANEL — TORN (CABIN) · airframe 50,631 hrs · 27,253 cycles

MAIN CABIN FLOOR PANEL 241TH BOTTOM SIDE OF PANEL TORN. FABRICATED NEW FLOOR PANEL 241TH IAW DWG SRZ-25-005 REV R AND GMM 07-0-1000.

Part: FLOORBOARD — BROKEN (MAIN CABIN) · airframe 50,631 hrs · 27,253 cycles

MAIN CABIN FLOOR PANEL 241XK HAS A BROKEN CORNER, FWD IB, MARKED FABRICATED NEW FLOOR PANEL 241XK IAW FEDEX DWG SRZ-25-005 REV. R AND GMM 7-0-1000

Part: FLOORBOARD — DELAMINATED (MAIN CABIN) · airframe 50,631 hrs · 27,253 cycles

MAIN CABIN FLOOR PANEL 241RH HAS CRUSHED CORE / DELAM FABRICATED NEW FLOOR PANEL 241RH IAW FEDEX DWG SRZ-25-005 REV. R AND GMM 7-0-1000

Part: HYDRAULIC LINE — WORN (TE FLAP) · airframe 49,866 hrs · 26,781 cycles

AFTER T/O FROM KBFM, SELECTED GEAR HANDLE TO RETRACT (SYS2) AND GREEN SYSTEM HYDRAULIC PRESSURE LO LIGHTS CAME ON. HYDRAULIC QUANTITY WENT TO ZERO, COMPLIED WITH ECAM AND QRH. HAND CRANK GEAR, 3 DOWN, NORMAL LANDING. INSTALLED NOTCH FLAP ACTUATOR REF MM 27-88-15-04, OPS AND LEAK CHECK GOOD. REPLACED BOTH HYDRAULIC LINES TO ACTUATOR DUE TO DAMAGE, REPLACED BY PART A2783161500400 AND PART A2783161500500 AND NOTCH FLAP ACTUATOR PART #747892-302 SERIAL # 130.

Part: DIAPHRAGM — LEAKING (L1 ASSIST BOTTLE) · airframe 48,260 hrs · 25,813 cycles

L1 DOOR ASSIST BOTTLE DISCHARGE DISK RUPTURED. REPLACED DIAPHRAM AND REACTIVATED L1 DOOR CYLINDER. OPS AND LEAK CHECKED GOOD. ACFT OK FOR SERVICE.

Part: FLOOR PANEL — CRACKED (MAIN CARGO) · airframe 47,733 hrs · 25,492 cycles

MAIN CARGO FLOOR PANEL 261KF HAS CRACK. FABRICATED A NEW FLOOR PANEL IAW DWG SRZ 25-005, MAJOR REPAIR.

Part: FLOOR PANEL — DELAMINATED (AFT CARGO) · airframe 47,733 hrs · 25,492 cycles

AFT CARGO FLOOR PANEL 151FF DAMAGED, AFT EDGE DELAMINATED. A NEW FLOOR PANEL WAS FABRICATED IAW DWG SRZ 25-005. MAJOR REPAIR.

Part: FLOOR PANEL — CRACKED (MAIN CARGO) · airframe 47,733 hrs · 25,492 cycles

MAIN CARGO FLOOR PANEL 241KG CRACKED. FABRICATED A NEW FLOOR PANEL IAW DWG SRZ 25-005. MAJOR REPAIR.

Part: FLOOR PANEL — DELAMINATED (BULK CARGO) · airframe 47,733 hrs · 25,492 cycles

BULK CARGO FLOOR PANEL 161GF DAMAGED, & DELAMINATED. A NEW FLOOR PANEL WAS FABRICATED IAW DWG SRZ 25-005. MAJOR REPAIR.

Part: FLOOR PANEL — CRACKED (MAIN CARGO) · airframe 47,733 hrs · 25,492 cycles

MAIN CARGO FLOOR PANEL 251YG CRACKED . FABRICATED A NEW FLOOR PANEL IAW DWG SRZ 25-005. MAJOR REPAIR.

Part: FLOOR PANEL — CRACKED (MAIN CARGO) · airframe 47,733 hrs · 25,492 cycles

MAIN CARGO FLOOR PANEL 241TJ CRACKED. FABRICATED A NEW FLOOR PANEL IAW DWG SRZ 25-005. MAJOR REPAIR.

Part: FLOOR PANEL — DAMAGED (BULK CARGO) · airframe 47,733 hrs · 25,492 cycles

BULK CARGO FLOOR PANEL 161AF FOUND DAMAGED, AND DELAMINATED. A NEW FLOOR PANEL WAS FABRICATED IAW DWG SRZ 25-005. MAJOR REPAIR.

Part: FLOOR PANEL — DELAMINATED (AFT CARGO) · airframe 47,733 hrs · 25,492 cycles

AFT CARGO FLOOR PANEL 151KF DAMAGED, AND DELAMINATED. A NEW FLOOR PANEL WAS FABRICATED IAW DWG SRZ 25-005. MAJOR REPAIR.

Part: FLOOR PANEL — DELAMINATED (BULK CARGO) · airframe 47,733 hrs · 25,492 cycles

BULK CARGO FLOOR PANEL 162HF DAMAGED, AND DELAMINATED. A NEW FLOOR PANEL WAS FABRICATED IAW DWG SRZ 25-005. MAJOR REPAIR.

Part: FLOOR PANEL — DELAMINATED (AFT CARGO) · airframe 47,733 hrs · 25,492 cycles

AFT CARGO FLOOR PANEL 151DF DAMAGED, AND DELAMINATED AT THE CORNER OF PANEL. A NEW FLOOR PANEL WAS FABRICATED IAW DWG SRZ 25-005. MAJOR REPAIR.

Part: FLOOR PANEL — DAMAGED (AFT CARGO) · airframe 47,733 hrs · 25,492 cycles

AFT CARGO FLOOR PANEL 152GF DAMAGED ON THE CORNER EDGE. A NEW FLOOR PANEL WAS FABRICATED IAW DWG SRZ 25-005. MAJOR REPAIR.

Part: FLOOR PANEL — DAMAGED (AFT CARGO) · airframe 47,733 hrs · 25,492 cycles

AFT CARGO FLOOR PANEL 152KF DAMAGED, INBD EDGE AT THE CORE. A NEW FLOOR PANEL WAS FABRICATED IAW DWG SRZ 25-005. MAJOR REPAIR.

Part: FLOOR PANEL — DELAMINATED (AFT CARGO) · airframe 47,733 hrs · 25,492 cycles

AFT CARGO FLOOR PANEL 151LF DAMAGED, TOP FWD CORNER SKIN DELAMINATED. A NEW FLOOR PANEL WAS FABRICATED IAW DWG SRZ 25-005. MAJOR REPAIR.

Part: SKIN — CRACKED (FRAMES 98-99) · airframe 47,733 hrs · 25,492 cycles

EMPENNAGE RIGHT SIDE AT BUTTJOINT BETWEEN FRAMES 98 AND 99 HAS A THREE INCH CRACK IN SKIN. TRIMMED CRACK AND FABRICATED A REPAIR IAW SRM 57-19-12, AND SRM 53-19-12. MAJOR REPAIR.

Part: COMPUTER — FAILED (AUTOLAND) · airframe 47,538 hrs · 25,371 cycles

DURING TAKE OFF ROLL AUTO PILOT DISCONNECTED WITH AURAL HORN & RED ECAM. NO AUTOPILOT ENGAGED AT THE TIME. REPEATED SEVERAL TIMES DURING TAXI BACK TO GATE. CONDUCTED AUTOLAND TEST AND TEST FAILED FOR NR 2 FCC. R & R THE NR 2 FCC AND OPS CHECKED GOOD MM 22-18-34-04 AND CONDUCTED AUTOLAND TEST IAW MM 22-40-00-05. ALL TESTS PASSED 30 DAY AUTOLAND TIMER TO BE RESET.

Part: FLOOR SUPPORT — CORRODED (FRAMES 65-66) · corrosion level 2 · airframe 45,103 hrs · 23,853 cycles

AFT CARGO BAY FRAMES 65 - 66, FLOOR SUPPORT CORRODED AT -Y805. REPLACED THE FLOOR SUPPORT IAW SRM 51-40-21.

Part: CROSSBEAM — CORRODED (FRAME 65) · corrosion level 2 · airframe 45,103 hrs · 23,853 cycles

AFT CARGO BAY FRAME 65 CROSSBEAM CORRODED ON THE RT SIDE. REPLACED THE CROSSBEAM IAW SRM 51-40-21.

Part: CROSSBEAM — DAMAGED (FRAME 67) · corrosion level 2 · airframe 45,103 hrs · 23,853 cycles

AFT CARGO BAY CROSSBEAM CORRODED & SCRATCHED. REPLACED THE CROSSBEAM IAW SRM 51-40-21.

Part: ATTACH FITTING — CRACKED (FRAME 61) · airframe 45,103 hrs · 23,853 cycles

NDT INSPECTION OF AFT CARGO DOOR ACTUATOR ATTACH FITTING AT FRAME 61A SHOWS A CRACK 5CM IN LENGTH. REPLACED THE CRACKED ATTACH FITTING AT FR61A ON AFT CARGO DOOR IAW SRM51-40-21. ADJUSTED AND TESTED THE AFT CARGO DOOR IAW AMM52-32-11-05-01. TEST PASSED. MAJOR REPAIR IAW GMM6-2-100.

Part: FRAME — CRACKED (FRM 40) · airframe 45,103 hrs · 23,853 cycles

CENTER WING JOINT AT FRAME 40, SDI FOUND RT SIDE MIDDLE HOLE CRACKED. REPAIRED IAW EA 6-5710-T0314674 P1.

Part: FRAME — CRACKED (FRM 40) · airframe 45,103 hrs · 23,853 cycles

CENTER WING JOINT AT FRAME 40, SDI FOUND LT SIDE UPPER HOLE CRACKED. REPAIRED IAW EA6-5710-T0314674 P1.

Part: ATTACH FITTING — CRACKED (FRAME 40) · airframe 45,103 hrs · 23,853 cycles

CENTER WING JOINT AT FRAME 40, FOUND LT SIDE CRACKED. REPAIRED IAW EA 6-5710-T0314674 P1.

Part: FRAME — CRACKED (FRM 40) · airframe 45,103 hrs · 23,853 cycles

CENTER WING JOINT AT FRAME 40, SDI FOUND RT SIDE LOWER HOLE CRACKED. REPAIRED IAW EA 6-5710-T0314674 P1.

Part: FRAME — CRACKED (FRM 40) · airframe 45,103 hrs · 23,853 cycles

CENTER WING JOINT AT FRAME 40, SDI FOUND RT SIDE UPPER HOLE CRACKED. REPAIRED IAW EA 6-5710-T0314674 P1.

Part: FITTING — CRACKED (FUSELAGE) · airframe 44,037 hrs · 23,402 cycles

DURING ACFT SPECIAL VISIT FOR EO6-5310-7-5028 PT 1 TITLE, FUSELAGE, MAIN FRAME CTR SECTION FRAME 41 - 46 AREA 2, ONE CRACK WAS FOUND AT FRAME 46 FRAME FOOT AREA 1 BTW STRINGER 35R - STRINGER 37R. REPAIRED THE FRAME 46, STRINGER 37R LOWER FITTING IAW EA 6-5310-T0307713. TITLE, FUSELAGE, MAIN FRAME, FRAME FOOT CRACK REPAIR AT FRAME 46,STRINGERS 35R - 37R 53-6111R5. THIS REPAIR WAS CLASSIFIED AS MAJOR IAW GMM 6-2-100.

Part: TERMINAL — DAMAGED (ENGINE TEMP) · airframe 42,758 hrs · 22,944 cycles

AFTER TAKEOFF, NR 2 OIL TEMP WAS AT 142, 16 MINUTES AFTER, DURING CLIMBOUT REACHED 162 AND WAS CONTINUING TO INCREASE. MAX TEMP REACHED 168. TOTAL TIME ABOVE 163 WAS 9 MINUTES AND 30 SECONES, OIL DELTA TEMP ON ECAM WAS AT 0. ALL OTHER ENGINE PARAMETERS NORMAL. TERMINAL BLOCK 204VT/7-C & 204VT/6-B NEW CONTACT PIN REPLACED. HIGH POWER RUN PERFORMED AND PARAMETERS NORMAL.

Part: ADC — UNKNOWN (ZONE 100) · airframe 42,731 hrs · 22,935 cycles

AT APPROXIMATELY 80 KNOTS DURING TAKEOFF, CAPTAIN`S AIRSPEED FAILED, PITCH TRIM 1 TRIPPED, YAW DAMPER 1 TRIPPED, ATS 1 TRIPPED, AND ATS 2 TRIPPED. ECAM BITE TEST SHOWED ADC NR 1 FAULT, FCC NR 1 FAULT. FOUND NO FAULTS ON ADC NR 1&2. INSPECTED PITOT TUBE, PURGED PITOT LINES, NORMALISED PITOT PROBES. R & R ADC NR 1. COMPLIED WITH 34-1-00-02. AGAIN C/O ECAM SYS TEST IAW AMM: 31-51-00-05-01. ALL TEST PASSED. C/W ADS SYS TEST. TEST PASSED. C/W AFS/LAND TEST.

Part: PANEL — MISSING (CARGO DOOR) · airframe 42,591 hrs · 22,892 cycles

DURING POST FLIGHT INSPECTION OF EXTERIOR, FOUND PANEL 811AR MISSING ON LOWER HINGE PORTION OF FWD CARGO DOOR. REPLACED PANEL.

Part: SKIN — CONTAMINATED (ZONE 300) · airframe 42,589 hrs · 22,891 cycles

LEFT ELEVATOR HAS SUSPECT WATER INGRESS. REPAIRED IAW EA 6-5521-167453.

Part: NOZZLE — GOUGED (NR 2 ENG EXHAUST) · airframe 42,589 hrs · 22,891 cycles

EXHAUST NOZZLE OUTER SKIN GOUGED APPROXIMATELY 8.5 INCHES LONG VERTICALLY. REPAIRED IAW EA6-7810-167489.

Part: FRAME — DAMAGED (STRUCTURE) · airframe 42,589 hrs · 22,891 cycles

DURING ACCOMPLISHMENT OF EO: 6-5710-7-3305 D3 PT3, WRI: 57101122, POST REMOVAL OF FASTENER "B" IN CTR WING BOX REAR SPAR FR 47 LT JUNCTION WITH FUSELAGE SCORE DAMAGE FOUND IN WALL OF HOLE. HOLE "B" EXISTING DIA= 0.591 IN. REAMED TO REMOVE SCORE AND HOLE NDT CARRIED OUT, NIL FINDING AND FASTENER INSTALLED IAW REPAIR INSTRUCTION OF EA: 6-5710-167454. AIB RDAS 70579170/005/2013, ISSUE B, REFERS MAJOR REPAIR, CAT B.

Part: FRAME — DAMAGED · airframe 42,589 hrs · 22,891 cycles

DURING ACCOMPLISHMENT OF EO: 6-5710-7-3305 D3 PT3, WRI: 57101122, POST REMOVAL OF FASTENER "G" IN CTR WING BOX REAR SPAR FR 47 LT JUNCTION WITH FUSELAGE SCORE DAMAGE FOUND IN WALL OF HOLE. HOLE "G" EXISTING DIA= 0.529 IN. FASTENER "G" HOLE REAMED TO REMOVE SCORES AND HOLE NDT CARRIED OUT, NIL FINDING AND FASTENER INSTALLED IAW REPAIR INSTRUCTION OF EA 6-5710-167454. RDAS 70579170/005/2013 ISSUE B REFERS MAJOR REPAIR CAT B.

Part: FRAME — DAMAGED (FUSELAGE) · airframe 42,589 hrs · 22,891 cycles

DURING ACCOMPLISHMENT OF EO: 6-5710-7-3305, D3, PT3, WRI: 57101122, POST REMOVAL OF FASTENER "D" IN CTR WING BOX REAR SPAR, FR.47 LT JUNCTION WITH FUSELAGE SCORE DAMAGE FOUND IN WALL OF HOLE. "D" HOLE EXISTING DIA= 0.591 IN. FASTENER "D" HOLE REAMED TO REMOVE SCORE, HOLE NDT CARRIED OUT, NIL FINDING AND FASTENER INSTALLED IAW REPAIR INSTRUCTION OF EA6-5710-167454. RDAS:70579170/005/2013, MAJOR REPAIR , CAT B.

Part: PANEL — DAMAGED · airframe 42,589 hrs · 22,891 cycles

DURING ACCOMPLISHMENT OF EO: 6-5710-7-3305, D3, PT4, WRI: 57101121, POST REMOVAL OF FASTENER "E" IN CTR WING BOX REAR SPAR FR 47, RT JUNCTION WITH FUSELAGE SCORE DAMAGE FOUND IN WALL OF HOLE. HOLE "E" EXISTING DIA= 0.529 IN. FASTENER "E" HOLE REAMED TO REMOVE SCORES AND HOLE NDT CARRIED OUT, NIL FINDINGS. FASTENER INSTALLED IAW REPAIR INSTRUCTION : EA 6-5710-167455. RDAS: 70579170/005/2013 ISSUE B REFERS. MAJOR REPAIR CAT 'B'

Part: PANEL — DAMAGED · airframe 42,589 hrs · 22,891 cycles

DURING ACCOMPLISHMENT OF EO: 6-5710-7-3305, D3, PT4, WRI: 57101121, POST REMOVAL OF FASTENER "D" IN CTR WING BOX REAR SPAR FR 47 RT JUNCTION WITH FUSELAGE SCORE DAMAGE FOUND IN WALL OF HOLE. HOLE "D" EXISTING DIA= 0.639 IN. FASTENER "D" HOLE REAMED TO REMOVE SCORES AND HOLE NDT CARRIED OUT, NIL FINDINGS. FASTENER INSTALLED IAW REPAIR INSTRUCTION : EA 6-5710-167455. AIB RDAS: 70579170/005/2013, ISSUE B REFERS. MAJOR REPAIR CAT "B".

Part: SKIN — DAMAGED · airframe 42,589 hrs · 22,891 cycles

DURING ACCOMPLISHMENT OF EO: 6-5710-7-3305, D3, PT4, WRI: 57101121, POST REMOVAL OF FASTENER "B" IN CTR WING BOX REAR SPAR FR 47 RY JUNCTION WITH FUSELAGE SCORE DAMAGE FOUND IN WALL OF HOLE. HOLE "B" EXISTING DIA= 0.591". FASTENER HOLE B REAMED TO REMOVE SCORE AND HOLE NDT CARRIED OUT, NIL FINDINGS. FASTENER INSTALLED IAW REPAIR INSTRUCTION: EA 6-5710-167455. AIRBUS RDAS 70579170/005/2013 ISSUE B, REFERS. MAJOR REPAIR, CAT B.

Part: FRAME — DAMAGED (FUSELAGE) · airframe 42,589 hrs · 22,891 cycles

DURING ACCOMPLISHMENT OF EO: 6-5710-7-3305 D3 PT3, WRI: 57101122, POST REMOVAL OF FASTENER "A" IN CTR WING BOX REAR SPAR, FR 47, LT JUNCTION WITH FUSELAGE SCORE DAMAGE FOUND IN WALL OF HOLE. A-HOLE EXISTING DIA= 0.591 IN. FASTENER "A" HOLE REAMED TO REMOVE SCORES, HOLE NDT CARRIED OUT, NIL FINDING AND FASTENER INSTALLED IAW REPAIR INSTRUCTION OF EA:6-5710-167454. AIB RDAS:70579170/005/2013 ISSUE B, REFERS. MAJOR REPAIR, CAT B.

Part: PANEL — DAMAGED · airframe 42,589 hrs · 22,891 cycles

DURING ACCOMPLISHMENT OF EO: 6-5710-7-3305, D3, PT4, WRI: 57101121, POST REMOVAL OF FASTENER "C" IN CTR WING BOX REAR SPAR FR.47 RT JUNCTION WITH FUSELAGE SCORE DAMAGE FOUND IN WALL OF HOLE. HOLE "C" EXISTING DIA= 0.529 IN. FASTENER "C" HOLE REAMED TO REMOVE SCORES AND HOLE NDT CARRIED OUT, NIL FINDINGS. FASTENER INSTALLED IAW REPAIR INSTRUCTION: EA 6-5710-167455. AIB RDAS: 70579170/005/2013 ISSUE B, REFERS. MAJOR REPAIR CAT "B".

Part: PANEL — DAMAGED · airframe 42,589 hrs · 22,891 cycles

DURING ACCOMPLISHMENT OF EO: 6-5710-7-3305 D3 PT4, WRI: 57101121, POST REMOVAL OF FASTENER "S" IN CTR WING BOX REAR SPAR FR 47 RT JUNCTION WITH FUSELAGE SCORE DAMAGED FOUND IN WALL OF HOLE. HOLE "S" EXISTING DIA= 0.653 IN. FASTENER "S" HOLE REAMED TO REMOVE SCORES, NDT CARRIED OF HOLE CARRIED OUT, NIL FINDINGS. FASTENER INSTALLED IAW REPAIR INSTRUCTION: EA 6-5710-167455. AIB RDAS: 70579170/005/2013, ISSUE B REFERS. MAJOR REPAIR CAT "B".

Part: FRAME — DAMAGED · airframe 42,589 hrs · 22,891 cycles

DURING ACCOMPLISHMENT OF EO: 6-5710-7-3305, D3, PT3, WRI: 57101122, POST REMOVAL OF FASTENER "Q" IN CTR WING BOX REAR SPAR FR 47 LT JUNCTION WITH FUSELAGE SCORE DAMAGE FOUND IN WALL OF HOLE. HOLE "Q" EXISTING DIA= 0.653 IN. FASTENER "Q" HOLE REAMED TO REMOVE SCORES AND HOLE NDT CARRIED OUT, NIL FINDING, UPPER SURFACE DAMAGE REMOVED BY SPOT FACING AND FASTENER INSTALLED IAW REPAIR INSTRUCTION EA 6-5710-167454 RDAS 70579170/005/2013 ISSUE B. MAJOR REPAIR CAT B.

Part: FRAME — DAMAGED · airframe 42,589 hrs · 22,891 cycles

DURING ACCOMPLISHMENT OF EO: 6-5710-7-3305 D3 PT3, WRI: 57101122, POST REMOVAL OF FASTENER "C" IN CTR WING BOX REAR SPAR, FR 47 LT JUNCTION WITH FUSELAGE SCORE DAMAGE FOUND IN WALL OF HOLE. HOLE "C" EXISTING DIA= 0.529 IN. FASTENER "C" HOLE REAMED TO REMOVE SCORED HOLE NDT CARRIED OUT, NIL FINDING AND FASTENER INSTALLED IAW REPAIR INSTRUCTIONS OF EA:6-5710-167454, RDAS 70579170/005/2013 ISSUE B REFERS. MAJOR REPAIR CAT B.

Part: PANEL — DAMAGED · airframe 42,589 hrs · 22,891 cycles

DURING ACCOMPLISHMENT OF EO: 6-5710-7-3305 D3 PT4, WRI: 57101121, POST REMOVAL OF FASTENER "F" IN CTR WING BOX REAR SPAR FR 47 RT JUNCTION WITH FUSELAGE SCORE DAMAGE FOUND IN WALL OF HOLE, HOLE "F" EXISTING DIA= 0.529 IN. HOLE "F" SCORES REMOVED BY REAMING, HOLE NDT, NIL FINDINGS AND FASTENER INSTALLED IAW REPAIR INSTRUCTION OF EA 6-5710-167455. AIB RDAS: 70579170/005/2013 ISSUE B REFERS. MAJOR REPAIR CAT "B".

Part: FRAME — DAMAGED (`) · airframe 42,589 hrs · 22,891 cycles

DURING ACCOMPLISHMENT OF EO: 6-5710-7-3305, D3, PT3, WRI: 57101122, POST REMOVAL OF FASTENER "F" IN CTR WING BOX REAR SPAR FR 47 LT JUNCTION WITH FUSELAGE SCORE DAMAGE FOUND IN WALL OF HOLE. HOLE "F" EXISTING DIA= 0.529 IN. FASTENER 'F' HOLE REAMED TO REMOVE SCORES, HOLE NDT CARRIED OUT, NIL FINDING, UPPER SURFACE IMPACT DAMAGE SPOTFACE TO REMOVE DAMAGE AND FASTENER INSTALLED IAW REPAIR INSTRUCTION OF EA 6-5710-167454 AIB RDAS 7057917/005/2013 ISSUE B, REFS MAJOR REPAIR. CAT B.

Part: PANEL — DAMAGED · airframe 42,589 hrs · 22,891 cycles

DURING ACCOMPLISHMENT OF EO: 6-5710-7-3305, D3, PT4, WRI: 57101121, POST REMOVAL OF FASTENER "Q" IN CTR WING BOX REAR SPAR FR 47 RT JUNCTION WITH FUSELAGE SCORE DAMAGED. FOUND IN WALL OF HOLE. HOLE "Q" EXISTING DIA= 0.653 IN. FASTENER "Q" HOLE REAMED TO REMOVE SCORES AND HOLE NDT CARRIED OUT, NIL FINDINGS. FASTENER INSTALLED IAW REPAIR INSTRUCTION: EA 6-5710-167455. AIB RDAS: 70579170/005/2013 ISSUE B REFERS. MAJOR REPAIR CAT "B".

Part: PANEL — DAMAGED · airframe 42,589 hrs · 22,891 cycles

DURING ACCOMPLISHMENT OF EO: 6-5710-7-3305 D3 PT4, WRI: 57101121, POST REMOVAL OF FASTENER "G" IN CTR WING BOX REAR SPAR FR 47 RT JUNCTION WITH FUSELAGE SCORE DAMAGE FOUND IN WALL OF HOLE. HOLE "G" EXISTING DIA= 0.529 IN. FASTENER "G" HOLE REAMED TO REMOVE SCORES AND HOLE NDT CARRIED OUT, NIL FINDINGS. FASTENER INSTALLED IAW REPAIR INSTRUCTIONS OF EA 6-5710-167455. AIB RDAS: 70579170/005/2013 ISSUE B REFERS. MAJOR REPAIR CAT "B".

Part: PANEL — DAMAGED · airframe 42,589 hrs · 22,891 cycles

DURING ACCOMPLISHMENT OF EO: 6-5710-7-3305, D3, PT4, WRI: 57101121, POST REMOVAL OF FASTENER "A" IN CTR WING BOX REAR SPAR FR.47 RT JUNCTION WITH FUSELAGE SCORE DAMAGE FOUND IN WALL OF HOLE AND SCRATCH IN UPPER SURFACE AROUND HOLE. HOLE "A" EXISTING DIA= 0.591 IN. FASTENER "A" HOLE REAMED TO REMOVE SCRATCH DAMAGE, NDT CARRIED OUT, NIL FINDINGS AND UPPER SURFACE SCRATCHES REMOVED BY SPOTFACING. FASTENER INSTALLED IAW REPAIR INSTRUCTION: EA 6-5710-167455. AIB RDAS: 70579170/005/2013 ISSUE B REFERS. MAJOR REPAIR CAT "B".

Part: FRAME — DAMAGED · airframe 42,589 hrs · 22,891 cycles

DURING ACCOMPLISHMENT OF EO: 6-5710-7-3305 D3 PT3, WRI: 57101122, POST REMOVAL OF FASTENER "E" IN CTR WING BOX, REAR SPAR, FR 47 LT JUNCTION WITH FUSELAGE SCORE DAMAGE FOUND IN WALL OF HOLE. HOLE "E" EXISTING DIA= 0.529 IN. FASTENER "E" HOLE REAMED TO REMOVE SCORES, HOLE NDT CARRIED OUT, NIL FINDING AND FASTENER INSTALLED IAW REPAIR INSTRUCTION OF EA 6-5710-167454. RDAS 70579170/005/2013 ISSUE B REFERS MAJOR REPAIR CAT B.

Part: ELEVATOR — UNKNOWN (ZONE 300) · airframe 42,589 hrs · 22,891 cycles

RT ELEVATOR HAS SUSPECT WATER INGRESS. CARRY OUT REQUIREMENTS OF EA 6-5521-197477 REQUIREMENTS OF EA 6-5521-167477 CARRIED OUT.

Part: FITTING — CRACKED (ZONE 100) · airframe 42,589 hrs · 22,891 cycles

DURING REPLACMENT OF RT MLG MAIN DOOR FITTING. JOINT FITTING BEHIND RT MLG KEEL BEAM PANEL AT FR 50 RT, FOUND TO HAVE IMPACT DAMAGE CAUSING DENT AND CRACKING IAW SRM 53-15-15-4-150. REPAIRED IAW EA 6-5300-167469.

Part: SKIN — DAMAGED (LT WING) · airframe 42,589 hrs · 22,891 cycles

LEFT WING TOP SKIN FWD SPAR AREA APPROX RIB 9-10 HAS INCORRECTLY FITTED FASTENER AND SUSPECT DAMAGE AROUND THE HOLE. REPAIRED IAW EA 6-5700-167463, CAT A REPAIR CLASSED AS MAJOR.

Part: SKIN — DAMAGED (CARGO DOOR) · airframe 42,589 hrs · 22,891 cycles

BULK CARGO BAY DOOR EXTERNAL SKIN AROUND OPERATING HANDLE HAS VARIOUS DENTS AND DAMAGE. REPAIRED IAW EA6-5230-197462.

Part: SKIN — DAMAGED (DOOR CUTOUT) · airframe 42,589 hrs · 22,891 cycles

FWD CARGO BAY RT SIDE AT THE DOOR CUT OUT, DAMAGE ON THE L/E OF THE FRAME 25A BETWEEN STRINGERS 33 AND 35. REPAIRED IAW EA 6-5300-167464. CAT "A" REPAIR.

Part: SKIN — DENTED (ZONE 600) · airframe 42,589 hrs · 22,891 cycles

DENT NOTED TO BOTTOM SKIN OF RT AILERON APROX CENTER OF AILERON. FOUNT OUT OF LIMITS AREA REPAIRED IAW SRM 57-61-11 PB201 FIG 206 PARA 4.F CAT A REPAIR CLASSIFIED AS A MAJOR REPAIR. AREA REPROTECTED IAW SRM 51-75-10.

Part: SKIN — DENTED (LT WING AILERON) · airframe 42,589 hrs · 22,891 cycles

LT WING DENT IN AILERON T/E AREA BOTTOM SKIN 1.5" IN/BD OF RIB 1 AND 4.0" FWD OF T/E AFT EDGE. FOUND TO BE OUT OF LIMITS. REPAIRED IAW SRM 57-61-11 PARA 4G & 51-77-12 PARA 4C.

Part: SKIN — DENTED (LT WING AILERON) · airframe 42,589 hrs · 22,891 cycles

LEFT WING DENT IN AILERON T/E AREA BOTTOM SKIN 2.5" INBD OF RIB 1 AND 10.0" FWD OF T/E AFT EDGE. FOUND TO BE OUT OF LIMITS. REPAIRED IAW SRM 57-61-11 PARA 4G & 51-77-12, PARA 4C.

Part: FITTING — CORRODED (ZONE 600) · corrosion level 3 · airframe 42,589 hrs · 22,891 cycles

CORROSION FOUND ON BORE OF RT MLG RIB 5 FITTING FWD LUG. CORROSION REMOVED, REPLACEMENT BUSHES FABRICATED AND INSTALLED IAW REPAIR DWG R57240425 ISSUE B AND RT MLG INSTALLED IAW INSTRUCTION OF EA 6-5710-167452 AND RDAS 70579091/003/2013 ISSUE A. MAJOR REPAIR CATC.

Part: UPLOCK — MISWIRED (MLG BAY) · airframe 42,589 hrs · 22,891 cycles

LT MLG DOOR UPLOCK FREE FALL INPUT ROD FOUND TO BE WIRED TO UPLOCK IN CLOSED POSITION THROUGH RIGGING PIN HOLE. CARRIED OUT UPLOCK FREEFALL INPUT ROD REMOVED CABLE CONNECTION AND RIG CHECK AND FOUND TO BE CORRECT. MANUAL GROUND DOOR OPENING AND CLOSING TEST CARRIED OUT AND FREEFALL DOOR OPENING TEST CARRIED OUT SATISFACTORY IAW AMM 32-31-36-09, 32-12-11 PB 30, 32-33-00, PB 501, PARA 2D.

Part: RIB — CORRODED (ZONE 500) · corrosion level 3 · airframe 42,589 hrs · 22,891 cycles

CORROSION FOUND ON BORE AND AFT FACE OF LT MLG RIB 5, FITTING FWD LUG. RIB REPLACED IAW EA 6-5710-167482.

Part: SKIN — DAMAGED (NR 2 SLAT) · airframe 42,589 hrs · 22,891 cycles

DAMAGE FOUND TO BACK SIDE OF NR 2 SLAT, 12 INCHES FROM INBD END OF SLAT ON RT WING. FOUND TO BE OUT OF LIMITS. REPAIRED IAW SRM 57-43-11 PB201 PARA 4.B, FIG 202.

Part: FUEL TANK — DAMAGED · airframe 42,589 hrs · 22,891 cycles

DURING ACCOMPLISHMENT OF O: 6-5310-7-5013 C 1 PT2, POST REMOVAL OF FASTENER THROUGH CENTER TANK UPPER SKIN AT FR 47 BORE OF HOLE FOUND WITH SEVERAL SCRATCHES IN UPPER SPLICE PLATE. REF FIG 6, SHEET 2 OF 3 ITEM 6. REAMED & FASTENER INSTALLED IAW EA 6-5710-167461. MAJOR REPAIR, CAT A.

Part: WEB — CRACKED · airframe 42,589 hrs · 22,891 cycles

NDT INSPECTION OF CENTER WING BOX, CENTER SPAR AT CUTOUT DOUBLER RUNOUT L/H AT FR. 44, CRACK FOUND AT R/H LOWER HOLE 4 , INDICATION 25 PERCENT FSH 10MM FROM AFT FACE AT APPROXIMATE VERTICAL POSITION. REPAIRED OUT IAW EA 6-5710-167465.

Part: ANGLE — CRACKED (ZONE 600) · airframe 42,589 hrs · 22,891 cycles

RIGHT WING KREUGER FLAP CAVITY AT FIXED L/E HAS A SUSPECTED CRACK AT RIB, 8 AT OTBD OF KREUGER ACTUATOR. REPAIRED IAW SRM 51-72-10 REF DWG A57241993.

Part: SPAR — CRACKED (CENTER WING) · airframe 42,589 hrs · 22,891 cycles

NDT INSPECTION OF CENTER WING BOX, CENTER SPAR AT CUTOUT DOUBLER RUNOUT RT AT FR 44, CRACK FOUND AT RT UPPER HOLE 7 I, INDICATION 25 PERCENT FSH 10MM FROM AFT FACE AT APPROXIMATE VERTICAL POSITION. REPAIRED IAW EA 6-5710-167466.

Part: FRAME — CHAFED (ZONE 100) · airframe 42,589 hrs · 22,891 cycles

RT GEAR DOOR ACTUATOR UPPER FITTING AFT FRAME SCOURED & CHAFED ON INNER FWD FACE. REPLACED IAW SRM 51-72-10, REF DWG A53810931 & A53810771.

Part: RIB — CRACKED (LT WING) · airframe 42,589 hrs · 22,891 cycles

LT WING KREUGER FLAP CUTOUT CAVITY AT FIXED L/E SUPPORT, RIB CRACKED APPROX 8" OTBD OF KREUGER ACTUATOR. REPLACED IAW SRM 51-72-10 AND DWG A57241993.

Part: HYDRAULIC SYSTEM — MALFUNCTIONED · airframe 42,336 hrs · 22,809 cycles

AFTER DEPARTING, GREEN HYD QTY BEGAN TO SLOWLY DECREASE. ON RETURN, QTY DECREASED TO RED DOT ON QTY GAUGE. ECAM DISPLAY CONFIRMED LOW QTY . FOLLOWED ECAM AND QRH AND PERFORMED GRAVITY EXTENSION OF LANDING GEAR. AFTER GEAR WAS EXTENDED, HYD QTY ROSE BACK INTO THE MIDDLE OF GREEN ARC. AFTER ARRIVAL FOUND GREEN SYS HYD QTY BACK IN ARC UPPER HAT. RESET GEAR EXTENSION IAW AMM 32-33-00-02. GREEN SYS HYD DE-PRESSURIZED AND GREEN RESERVOIR DE-PRESSURIZED IAW 29-10-00-03 AND 29-14-00-03 . PRESSURIZED GREEN HYD RESERVE BACK TO 45 PSI. GREEN HYD SYS SERVICED TO TOP OF ARC IAW AMM 12-12-29-00. VISUALLY INSPECTION OF MAIN WHEEL WELL AREA, NOSE WHEEL WELL AREA WITH HYD SYS PRESSURIZED. NO LEAKS FOUND, RAN BOTH ENGINES AND OPERATED ALL FLT CONTROL SURFACES SEVERAL TIMES FOR COMPLETE 35 MINS OF ENG RUN DURATION. PRESSURE FOR ALL 3 HYD SYS SUSTAINED NORMAL AND NO ABNORMAL PARAMETERS. WITH HYD SYS PRESSURIZED, PERFORMED WHEEL WELL INSPECTION, FLAP SLAT IN DOWN POSITION , NO LEAKS FOUND. AFTER ENG SHUTDOWN INSPECTION THE FLEX HOSE REPLACED EARLIER IAW 29-02/1097, NO LEAK IN THE AREA. ALL 3 HYD SYS QTY NORMAL AFTER ENG SHUTDOWN. VERIFIED RESERVOIR RETURN FILTER AND EDP FILTERS NOT POPPED. ALL NORMAL CONDITION AND ACFT IS RELEASED TO SERVICE.

Part: HOSE — LEAKING (HYD SYSTEM) · airframe 42,336 hrs · 22,809 cycles

AFTER TAKEOFF LOST ALL GREEN HYD FLUID. GAUGES INDICATED ZERO QTY ON OVERHEAD PANEL AND ECAM. COMPLETED QRH AIR TURN BACK, TROUBLESHOOTING FOUND THE RT AILERON ACTUATOR PRESSURE HOSE RUPTURED. R & R THE HOSE . PERFORMED LEAK CHECK, NO LEAKS FOUND, SERVICED HYD GREEN SYS.

Part: PITOT HEAD — MALFUNCTIONED (ZONE 100) · airframe 39,857 hrs · 21,501 cycles

ALTITUDE ALERT ON CONTINUOSLY IN LEVEL FLT. ALTITUDE NEVER OFF BY 50FT AND LIGHT & HORN ACTIVATED & HAD TO BE MANUALLY CORRECTED TO ALTITUDE WITH EITHER AUTOPILOT ON. USED NR 2 REMAINDER OF FLT DUE TO LOSS OF CAPT FD/ADC. REPLACED CAPT'S, F/O'S & STANDBY PITOT PROBES IAW MM34-11-15-04. R & R NR 1 & 2 FLT AUG COMPUTERS IAW MM 22-26-34-04. R & R NR 1 & 2 FEEL LIMIT COMPUTERS IAW AMM 27-23-26-04, OPS CHECKED NORMAL. PERFORMED HEATING TEST IAW AMM 34-11-15-04, 34-10-00-03. PERFORMED INSPECTION OF WATER TRAPS IAW AMM 12-24-34-00, NO CONTAMINATION FOUND. PERFORMED PITOT SYS LEAK DOWN TEST IAW MM 4-10-00-05, TESTED GOOD. NO ABNORMAL OR ERRATIC INDICATIONS DURING TESTING.

Part: SLAT TRACK — CHAFED (LT WING) · airframe 39,610 hrs · 21,381 cycles

LT WING NR 8 SLAT TRACK, ON THE TRACK FWD LOWER OTBD RADIUS, THERE IS CHAFING MARKED REPAIRED IAW EA 6-5740-146827, WINGS,ATTACH FITTINGS: LT WING NR 8 SLAT TRACK CHAFING, PERMANANT REPAIRS.

Part: RIB — CORRODED (RT MLG ATTACH) · airframe 39,610 hrs · 21,381 cycles

CORROSION FOUND ON RT MLG RIB 5, FWD LUG. COMPLIED WITH EA 6-5710-145558.

Part: WEB — CRACKED (CARGO DOOR) · airframe 39,610 hrs · 21,381 cycles

FWD CARGO DOOR WEB CRACKED .5" INCH AT DOOR ACTUATOR MOUNT. FABRICATED DRILLED AND INSTALLED REPAIR DOUBLER IAW EA 6-5230-145552. ROUTED OUT CRACK. NDT AREA OF REMOVAL, NO CRACKS FOUND, REPROTECTED AREA IAW SRM 51-75-10 FWD CARGO DOOR INNER WEB AT ACTUATOR MOUNT.

Part: JACKSCREW — DAMAGED (SLAT SYSTEM) · airframe 38,880 hrs · 20,948 cycles

SLAT 1 & SLAT 2 FAULT ON ECAM. FOLLOWED QRH SLAT WOULD NOT MOVE. PLEASE WORK IN CONJUNCTION WITH TSI 27-80/7759. R & R NR 3 LT SLAT SCREWJACK.

Part: JACKSCREW — BINDING (NR 2 SLAT) · airframe 38,880 hrs · 20,948 cycles

SLAT 1 & SLAT 2 FAULT ON ECAM. FOLLOWED QRH SLAT WOULD NOT MOVE. PLEASE WORK IN CONJUNCTION WITH TSI 27-80/7759. R & R NR 3 LT SLAT SCREWJACK IAW MM 27-84-22-4. ACCOMPLISHED OPS TEST OF L/E SLATS IAW MM 27-84-00-5 WITH NO FAULTS NOTED.

Part: SLAT SYSTEM — MALFUNCTIONED · airframe 38,667 hrs · 20,827 cycles

DURING SLAT EXTENSION, SLATS STUCK AT 0 DEGREES. BOTH OVERHEAD SLAT FAULT LIGHTS CAME ON. CYCLED HANDLE AND SLATS STAYED STUCK. DURING TAXI IN CYCLED HANDLE AND SLATS WORKED NORMALLY. BITE TEST OF SFCC 1 SHOWED "MAIN CONT VLV" ON ARRIVAL, SLATS WORKING NORMAL. SFCC 2 SHOWED "JAM". FAULT CLEARED & SLAT SYS FUNCTIONED NORMAL WITH NO FURTHER FAULTS. FOUND LT TORQUE LIMITER TRIPPED. RESET OF TORQUE LIMITER CUTOUT. LT SLAT SCREW JACKS SERVICED IAW AMM 12-13-27. ALL GEAR BOXES OIL FOUND WITHIN LIMITS. PERFORMED GREASING OF LT SCREW JACK BALL NUTS IAW AMM 12-22-27. SLAT SYS FUNCTIONED AGAIN WITH NO FAULTS NOTED. ACFT OK FOR SERVICE.

Part: SHUTOFF VALVE — MALFUNCTIONED (THRUST REVERSER) · airframe 37,431 hrs · 20,109 cycles

GOT REVERSER UNLOCK ON NR 1 ENG AT 60 KTS. ATTEMPTED SECOND T/O SAME RESULTS. R&R PRSOV PER AMM 78-32-11-5

Part: SMOKE DETECTOR — FAILED · airframe 37,270 hrs · 19,967 cycles

AT 8000 AFTER TAKEOFF FROM EGSS GOT SMOKE/FUME ALERT FROM MAIN DECK SMOKE DETECTOR MID 2A. STAYED ON FOR ABOUT 8 MINS, WENT OFF JUST BEFORE LANDING. MID 1B, MID 2B, AND AFT A WERE ALL READY DEFERRED. ACN RELEASED FOR SERVICE PER MEL/CDL: 26-17-01-B CATEGORY: C EXPIRATION: 11NOV08 "MEL 26-17-01-B: MAIN DECK (IDENTIFY MID 1, MID 2 AN D/OR AFT), 2A SMOKE DETECTOR(S) INOP. NO CARGO INSTEAD OF 12-13 SECONDS FOR ALL THE OTHER ONES, AMM REF:26-19-00 PAGE 504, ACTION NR 1. REMOVED AND REPLACED SMOKE DETECTOR 10 WU AS PER AMM:26-19-12 P401. PERFORMED TEST AS PER PREVIOUS AMM REF: TEST PASSED.

Part: SMOKE DETECTOR — MALFUNCTIONED (CARGO BAY) · airframe 37,270 hrs · 19,967 cycles

AT 8000 AFTER TAKEOFF FROM EGSS GOT SMOKE/FUME ALERT FROM MAIN DECK SMOKE DETECTOR MID 2A. STAYED ON FOR ABOUT 8 MINS, WENT OFF JUST BEFORE LANDING. REACTIVATED ALL MDC LOOPS ALREADY DEFERRED (AFT A, MID 1B AND MID 2B). NO MORE FAULT DISPLAYED ON MDC SMOKE DETECTION PANEL. CARRIED OUT MDC SMOKE. R & R SMOKE DETECTOR 10 WU AS PER AMM, 26-19-12 P401. PERFORMED TEST AS PER PREVIOUS AMM REF, TEST PASSED.

Part: FITTING — CORRODED (TE FLAP) · corrosion level 2 · airframe 37,044 hrs · 19,756 cycles

RT WING, INTERIOR FITTING AT FRONT CARRIAGE NR 3 FLAP TRACK WITH CORROSION, DETECTED ON ACCOMPLISHMENT OF NR 0599. A NEW FITTING WAS FABRICATED SO AS TO REPLACE THE EXISTING ONE.

Part: FITTING — CORRODED (FLAP TRACK) · corrosion level 2 · airframe 37,044 hrs · 19,756 cycles

LT WING NR 3 TRACK FRONT CARRIAGE INTERIOR FITTING WITH CORROSION, DETECTED WHILE PERFORMING N0800. THE NR 3 TRACK FRONT CARRIAGE WAS REPLACED BY ONE FABRICATED AS PER FEDEX EA 6-5740-120510.

Part: FRAME — GOUGED (ZONE 100) · airframe 37,044 hrs · 19,756 cycles

FUSELAGE, FR 47 HOLE K REF TO EO 6-5310-7-5017 PT4, FOUND DAMAGED. HOLE K REPAIRED AS PER FEDEX EA 6-5310-121645.

Part: STRINGER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 37,044 hrs · 19,756 cycles

AFT CARGO COMPT, STRINGER 54 LT WITH CORROSION BETWEEN FR 65 AND FR 66. STRINGER 54 LT WAS REPAIRED AS PER SRM 53-10-14 FIG 201.

Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 37,044 hrs · 19,756 cycles

AFT CARGO COMPT, STRINGER 53 LT WITH CORROSION NEXT TO RIVETS BETWEEN FR 65 AND FR 66. STRINGER 53 LT WAS REPLACED AS PER SRM 53-10-14 FIG 201.

Part: CARGO TRACK — CORRODED (CARGO BAY) · corrosion level 2 · airframe 37,044 hrs · 19,756 cycles

FWD CARGO COMPT ROLLER TRACK NR 3 BETWEEN FR27-32 WITH CORROSION. NEW ROLLER TRACK INSTALLED AS PER AMM 25-52-21-4 01.

Part: CARGO TRACK — CORRODED (CARGO BAY) · corrosion level 2 · airframe 37,044 hrs · 19,756 cycles

FWD CARGO COMPT ROLLER TRACK NR 4 BETWEEN FR 27-32 WITH CORROSION. NEW ROLLER TRACK INSTALLED AS PER AMM 25-52-51-4-01.

Part: BULKHEAD — CRACKED (AFT) · airframe 37,044 hrs · 19,756 cycles

AFT PRESSURE BULKHEAD - CRACK IN THE SKIN AT INTERIOR OF A HOLE (AT 3 O'CLOCK) IN THE APU DUCT FLANGE ATTACHMENT. AFT PRESSURE BULKHEAD SKIN WAS REPAIRED AS PER EA 6-5310-121644.

Part: SEAT TRACK — WORN (ZONE 100) · airframe 37,044 hrs · 19,756 cycles

SEAT-TRACK AT Y-1959 WORN AT FRAME 29. SEAT-TRACK WAS REPAIRED AS PER FEDEX EA 6-5310-117332.

Part: SKIN — CORRODED (LT WING) · airframe 37,044 hrs · 19,756 cycles

LT WING, WING TOP SKIN FOUND WITH CORROSION NEXT TO REAR SPAR, BETWEEN RIBS 27 AND 28. REPAIRED AS PER EA 6-5710-121647.

Part: SEAT TRACK — DAMAGED (FUSELAGE) · airframe 37,044 hrs · 19,756 cycles

CABIN FLOOR, SEAT-TRACK Y-1959 DAMAGED AT FR 29.

Part: SKIN — MISREPAIRED (RT WING TE FLAP) · airframe 37,044 hrs · 19,756 cycles

PREVIOUS REPAIR FOUND LOCATED ON INBD FLAP RT, RIB 24B, LOWER AND TOP SKIN T/E. REPAIR REQUIRES EVALUATION FOR MAJOR MINOR DETERMINATION AND IF THE REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. REPAIR EVALUATED AND FOUND NOT TO CONFORM TO EXISTING SRM REPAIR. NEW REPAIR WAS ACCOMPLISHED IAW EA 6-5710-121641.

Part: FITTING — WORN (NR 2 PYLON) · airframe 37,044 hrs · 19,756 cycles

PYLON NR 2, WING/PYLON AFT ATTACH FITTING AT RIB 18 WITH PLAY AT BEARING HOUSING. THE FEDEX EA 6-5451-117329 WAS ACCOMPLISHED.

Part: SEAT TRACK — CORRODED (ZONE 100) · corrosion level 2 · airframe 37,044 hrs · 19,756 cycles

CABIN FLOOR, CORROSION ON SEAT-TRACK Y953 BETWEEN FRAMES 11 AND 12. SEAT-TRACK REPLACED IN ACCORDANCE WITH SRM 51-72-10.

Part: SEAT TRACK — CORRODED (ZONE 100) · corrosion level 2 · airframe 37,044 hrs · 19,756 cycles

CABIN FLOOR, CORROSION ON TRACK Y730 BETWEEN FR 11-11A. TRACK REPLACED AS PER SRM 51-72-10.

Part: SKIN — MISREPAIRED (ZONE 300) · airframe 37,044 hrs · 19,756 cycles

PREVIOUS REPAIR FOUND LOCATED ON RUDDER RT STA 270-869 RIB BR 2-7, OUTER SKIN. REPAIR REQUIRES EVALUATION FOR MAJOR MINOR DETERMINATION AND IF THE REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. EXISTING REPAIR WAS FOUND IAW FEDEX EA-6-118158R.

Part: SEAT TRACK — CORRODED (N/A) · corrosion level 2 · airframe 37,044 hrs · 19,756 cycles

CABIN - FLOOR - SEAT-TRACK Y953 WITH CORROSION NEXT TO FRAME 15A. REPLACED IAW SRM 51-72-10.

Part: NONE — NONE (IAW SRM) · airframe 37,044 hrs · 19,756 cycles

PREVIOUS REPAIR FOUND LOCATED ON RUDDER RT STA270-869 RIB BR2-7, OUTER SKIN. REPAIR REQUIRES EVALUATION FOR MAJOR MINOR DETERMINATION AND IF THE REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. PERMANENT REPAIR WAS PERFORMED IAW FEDEX EA 6-5540-118158R. NOT AN SDR.

Part: SKIN — MISREPAIRED (ZONE 500) · airframe 37,044 hrs · 19,756 cycles

PREVIOUS REPAIR FOUND LOCATED ON LT WING, RIB 4-5, AT SHROUD BOX TOP SKIN. REPAIR REQUIRES EVALUATION FOR MAJOR/MINOR DETERMINATION AND IF REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. EXISTING REPAIR NOT IN ACCORDANCE WITH APPROVED DATA. NEW REPAIR INSTALLED AS PER FEDEX EA 6-5710-121643.

Part: SKIN — MISREPAIRED (ZONE 100) · airframe 37,044 hrs · 19,756 cycles

PREVIOUS REPAIR FOUND LOCATED ON FUSELAGE LT STA 1212-1260, STGR 28-30 LT, FR 15-16A, BELOW FWD LT DOOR. REPAIR REQUIRES EVALUATION FOR MAJOR/MINOR DETERMIANTION AND IF THE REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. REPAIR EVALUATED AND FOUND NOT TO CONFORM TO APPROVED DATA. NEW REPAIR ACCOMPLISHED AS PER FEDEX EA 6-5330-117334.

Part: SEAT TRACK — CORRODED (BS 1163-1232) · corrosion level 2 · airframe 37,044 hrs · 19,756 cycles

PREVIOUS REPAIR FOUND LOCATED ON SEAT-TRACK LT, STA Y953, FRAME 14-14C. REPAIR REQUIRES EVALUATION FOR MAJOR/MINOR DETERMINATION AND IF THE REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. PREVIOUS REPAIRED PART REPLACED BY NEW SEAT-TRACK Y953 IN ACCORDANCE WITH SRM 51-72-10.

Part: SEAT TRACK — DEFORMED (FUSELAGE) · airframe 37,044 hrs · 19,756 cycles

CABIN FLOOR, DEFORMATION ON SEAT-TRACK Y1959 BETWEEN FR 20 AND 21.

Part: SKIN — MISREPAIRED (ZONE 100) · airframe 37,044 hrs · 19,756 cycles

PREVIOUS REPAIR FOUND LOCATED ON LT FUSELAGE, STA 4415-4521 AT FR 68-70 BETWEEN STGR 36-44 LT. REPAIR REQUIRES EVALUATION FOR MAJOR/MINOR DETERMINATION AND IF THE REPAIR WAS ACCOMPLISHED USING FAA APPROVED DATA. EXISTING REPAIR NOT IN ACCORDANCE WITH PREVIOUS APPROVED DATA. FEDEX EA 6-5330-121637, ISSUED TO COVER THE DISCREPANCIES, WAS COMPLIED WITH.

Part: STRUCTURE — DAMAGED (FUSELAGE) · airframe 37,044 hrs · 19,756 cycles

FWD CARGO COMPT, SCRATCHES AND DEFORMATIONS AT FRAME 20A BETWEEN STGR 39-41 RT.

Part: AUTOTHRUST SYS — FAILED · airframe 36,612 hrs · 19,407 cycles

ON TAKEOFF ROLL LIMC 17R ACCELERATED TO 120KTS CAPTS PFD WENT TOTALLY BLANK, FOLLOWED BY BOTH ATS SWITCHES DISENGAGING. HIGH SPEED ABORT FOLLOWED BY RTO V LIST. TAXI BACK TO GATE. ACN RELEASED FOR SERVICE PER MEL/CDL: 22-30-01-C ATS 1 AND 2 - INOP. ALL THRUST SETTINGS MUST BE MANUALLY SET. NO OPS WITHIN METRIC AIR. SWAPPED CAPTAIN'S PFD WITH RT ECAM DISPLAY AS PER MM 34-74-22-4. ALL TEST PASSED. R&R AS REQUESTED FAC/ATS ENGAGE UNIT AS PER AMM: 22-25-12-4.AFS/LAND TEST PERFORMED. ALL PASSED. STICKER REMOVED.

Part: CONTROL UNIT — JAMMED (ZONE 100) · airframe 34,814 hrs · 18,371 cycles

GREEN SYSTEM SERVO CONTROL JAMMED. T/S AND REMOVED AND REPLACED JAMMING DECTECTION CONTROL UNIT (4CB) PERFORMED OP`S TEST AND NO HELP REINSTALLED OLD UNIT BACK ON A/C. ALL WORK DONE IAW AMM 27-14-17-4. STILL TROUBLESHOOTING AT THIS TIME. REMOVED AND REPLACED GREEN SYSTEM JAMMING DETECTION MICROSWITCH ON THS ACTUATOR

Part: WEB — BENT (ZONE 100) · airframe 34,055 hrs · 17,959 cycles

W/O 00030954, NR N00541, HORIZ STAB COMPT 2 WEBS BETWEEN FRAMES C85 AND C87 BENT 12TH STRINGER UP FROM 0 BL STRINGER AND 1 WEB BETWEEN FRAME C86 AND C87 11TH STRINGER UP FROM O BL STRINGER ("FROM BOTTOM STRINGERS"). REMOVED 3 WEBS, INSTALLED 3 WEBS IAW SRM 51-40-21. FABRICATED 3 WEBS ON TRAVELERS T5/560850, T5/560848, AND T5/560849. FABRICATED 3 STIFFENERS ON TRAVELERS T5/560847 AND T5/560846. TREATED AND PRIMED IAW SRM 51-21-10 PAINTED WEBS AND STIFFENERS IAW SRM 51-75-10.

Part: ANGLE — CORRODED (ZONE 100) · corrosion level 2 · airframe 34,055 hrs · 17,959 cycles

FWD CARGO COMPT BELOW ROLLER TRAY SUPPORT ANGLE EXFOLIATED 1" FWD OF FRAME C33 RBL 56". REMOVED AND REPLACED ANGLE SUPPORT IAW SRM 51-40-2. FABRICATED SUPPORT ANGLES (2 EACH) PER MAE TRAVELER T5/559357 AND T5/560339. FABRICATED WED (SHEAR WALL) T5/560340 LOCATED AND DRILLED IAW SRM 51040-44, PREP'D AND PAINTED AREA IAW SRM 51-75-10.

Part: FITTING — INTERFERENCE (ZONE 100) · airframe 34,055 hrs · 17,959 cycles

COMPLY WITH EA6-5310-92354, FUSELAGE-SB53-6111- FR46 FITTING/DOUBLER INTERFERENCE. COMPLIED WITH EA 6-5310-92354.

Part: RIB — CRACKED (NR 1 PYLON) · airframe 34,055 hrs · 17,959 cycles

NR 1 PYLON FAIRING 475CL INNER BODY NR 5 AND NR 6 RIBS ARE CRACKED.

Part: ATTACH ANGLE — CRACKED (NR 1 SLAT) · airframe 34,055 hrs · 17,959 cycles

LT WING IB FIXED L/E PNL IB SUPPORT WEB LWR ATTACH ANGLE HAS CRACK AT JUNCTION OF KRUEGER AND NR 1 SLAT.

Part: FLOORBEAM — CRACKED (BS 10) · airframe 34,055 hrs · 17,959 cycles

AVIONICS COMPT FLOORBEAM FS 10 RBL 40 ANGLE IS CRACKED.

Part: BRACKET — CRACKED (NR 1 PYLON) · airframe 34,055 hrs · 17,959 cycles

NR 1 PYLON FAIRING 475CL RT FWD BRACKET CRACKED.

Part: FRAME — CRACKED · airframe 32,657 hrs · 17,733 cycles

CRACK IN UPPER RADIUS RH. ** S/D ** COMING