N722FD

Part: REPAIR — NO DISCREPANCY (ZONE 600) · airframe 61,690 hrs · 33,424 cycles

EXISTING REPAIR ON RH O/B FLAP L/E SKIN BETWEEN RIB1 AND RIB2 REQUIRES EVALUATION FOR CONFORMITY THE EXISTING REPAIR ON RH O/B FLAP L/E SKIN BETWEEN RIB1 AND RIB2 WAS EVALUATED AND FOUND IN CONFORMITY WITH A300-600 SRM57-50-00-201 FIG.208. EO 6-5100-7-5000 D07 PART1 WAS COMPLETED. TITLE: STRUCTURES - REPAIR CATALOG - A300/A310 REPAIR IDENTIFICATION & TRACKING REQUIREMENTS 14 CFR 121.707. THE REPAIR WAS CATEGORY "A" AND CLASSIFIED AS MAJOR PER GMM6-2-100. THE FOLLOW UP INSPECTION WAS TRACKED BY EA 6-5750-T0383808.

Part: SKIN — CRACKED (ZONE 100) · airframe 61,690 hrs · 33,424 cycles

LWR FUSELAGE SKIN LAP JOINT AROUND FASTENER AT FR53-54, S44L FOUND CRACK. COMPLIED WITH EA:6-5330-T0383917 P1 REPAIRED LWR FUSELAGE THE CRACKED SKIN LAP JOINT AROUND FASTENER AT FR53-54,S44L. EA TITLE: FUSELAGE - PLATES & SKINS - CRACKED HOLES ON SKIN PANEL BETWEEN FR53 AND FR54 AT STGR 44LH DOUBLER REPAIR - ALI 53-15-78-01-1A. THIS IS CATEGORY B REPAIR. ENMDS IS SET FOR 6 MONTHS PENDING DTA. MAJOR REPAIR IAW FEDEX GMM 6-2-100. SEE WRI 53306080 FOR WORK DETAILS.

Part: FLAP — MISREPAIRED (ZONE 500) · airframe 61,690 hrs · 33,424 cycles

EXISTING REPAIR ON LT O/B FLAP L/E SKIN BETWEEN RIB13 AND RIB15 REQUIRES EVALUATION FOR CONFORMITY THE EXISTING REPAIR ON LH O/B FLAP L/E SKIN BETWEEN RIB13 AND RIB15 WAS EVALUATED AND FOUND NOT IN CONFORMITY WITH A300-600 SRM57-50-00-201 FIG.208. RE-REPAIRED THE EXISTING REPAIR REF A300-600 SRM57-50-00-201 FIG.208. EO 6-5100-7-5000 D07 PART1 WAS COMPLETED. THE REPAIR WAS CATEGORY "B" AND WAS CLASSIFIED AS MAJOR PER GMM6-2-100.

Part: SKIN — DELAMINATED (ZONE 600 SPOILER) · airframe 61,690 hrs · 33,424 cycles

RH WING #4 SPOILER CENTER O/B HINGE ARM OUTSIDE SURFACE SKIN FOUND DELAMINATION. SIZE: 30MM*10MM, DEPTH: 1.34MM COMPLIED WITH EA 6-5750-T0383788 P1 TO REPAIR RH WING #4 SPOILER CENTER O/B HINGE ARM OUTSIDE SURFACE SKIN DELAMINATION, EA TITLE: WING - FLIGHT SURFACES - RH #4 SPOILER CENTER HINGE ARM OUTSIDE SURFACE DELAMINATION. THIS IS CATEGORY A REPAIR. MAJOR REPAIR IAW FEDEX GMM6-2-100. SEE WRI 57506066 FOR WORK DETAILS.

Part: REPAIR — NO DISCREPANCY (ZONE 100) · airframe 61,690 hrs · 33,424 cycles

EXISTING REPAIR ON FUSELAGE STRINGER S51R BETWEEN FR67 AND 68 REQUIRES EVALUATION FOR CONFORMITY THE EXISTING REPAIR ON FUSELAGE STRINGER S51R BETWEEN FR67 AND 68 WAS EVALUATED AND FOUND IN CONFROMITY WITH A300-600 SRM53-10-14-201 FIG.201. EO6-5100-7-5000 D07 PART1 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. THE FIRST INSPECTION THRESHOLD WAS 51000FC/89000FH AFTER REPAIR EMBODIMENT. THE REPETITIVE INSPETION INTERVAL AND METHOD WERE TBD PER A300-600 SRI53-10-14-2-010-00.

Part: SKIN — DELAMINATED (ZONE 600 SPOILER) · airframe 61,690 hrs · 33,424 cycles

RH WING #3 SPOILER CENTER I/B & O/B HINGE ARMS OUTSIDE SURFACE SKIN FOUND DELAMINATION. SIZE: (1)80MM*40MM, DEPTH: 1.3MM (2)80MM*40MM, DEPTH: 1.4MM COMPLIED WITH EA 6-5750-T0383786 P1 TO REPAIR RH WING #3 SPOILER CENTER I/B & O/B HINGE ARMS OUTSIDE SURFACE SKIN DELAMINATION, EA TITLE: WING - FLIGHT SURFACES - RH #3 SPOILER CENTER HINGE ARM OUTSIDE SURFACES DELAMINATION. THIS IS CATEGORY A REPAIR. MAJOR REPAIR IAW FEDEX GMM6-2-100. SEE WRI 57506057 FOR WORK DETAILS.

Part: REPAIR — NO DISCREPANCY (ZONE 100) · airframe 61,690 hrs · 33,424 cycles

EXISTING REPAIR ON FUSELAGE STRINGER S52R BETWEEN FR67 AND 68 REQUIRES EVALUATION FOR CONFORMITY. THE EXISTING REPAIR ON FUSELAGE STRINGER S52R BETWEEN FR67 AND 68 WAS EVALUATED AND FOUND IN CONFROMITY WITH A300-600 SRM53-10-14-201 FIG.201. EO6-5100-7-5000 D07 PART1 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. THE FIRST INSPECTION THRESHOLD WAS 51000FC/89000FH AFTER REPAIR EMBODIMENT. THE REPETITIVE INSPETION INTERVAL AND METHOD WERE TBD PER A300-600 SRI53-10-14-2-010-00.

Part: REPAIR — NO DISCREPANCY (ZONE 100) · airframe 61,690 hrs · 33,424 cycles

EXISTING REPAIR ON FUSELAGE STRINGER S50R BETWEEN FR67 AND 68 REQUIRES EVALUATION FOR CONFORMITY THE EXISTING REPAIR ON FUSELAGE STRINGER S50R BETWEEN FR67 AND FR68 WAS EVALUATED AND FOUND IN CONFROMITY WITH A300-600 SRM53-10-14-201 FIG.201. EO6-5100-7-5000 D07 PART1 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. THE FIRST INSPECTION THRESHOLD WAS 51000FC/89000FH AFTER REPAIR EMBODIMENT. THE REPETITIVE INSPETION INTERVAL AND METHOD WERE TBD PER A300-600 SRI53-10-14-2-010-00.

Part: SKIN — DELAMINATED (ZONE 500 SPOILER) · airframe 61,690 hrs · 33,424 cycles

LH WING #5 SPOILER CENTER I/B HINGE ARM OUTSIDE SURFACE SKIN FOUND DELAMINATION. SIZE: 40MM*20MM, DEPTH: 1.37MM COMPLIED WITH EA 6-5750-T0383770 P1 TO REPAIR LH WING #5 SPOILER CENTER I/B HINGE ARM OUTSIDE SURFACE SKIN DELAMINATION, EA TITLE: WING - FLIGHT SURFACES - LH #5 SPOILER CENTER HINGE ARM OUTSIDE SURFACE DELAMINATION. THIS IS CATEGORY A REPAIR. MAJOR REPAIR IAW FEDEX GMM6-2-100. SEE WRI 57506058 FOR WORK DETAILS.

Part: SKIN — DELAMINATED (ZONE 500 SPOILER) · airframe 61,690 hrs · 33,424 cycles

LH WING #3 SPOILER CENTER O/B HINGE ARM OUTSIDE SURFACE SKIN FOUND DELAMINATION. SIZE: 90MM*10MM, DEPTH: 1.56MM COMPLIED WITH EA 6-5750-T0373146 A P2 TO REPAIR LH WING #3 SPOILER CENTER O/B HINGE ARM OUTSIDE SURFACE SKIN DELAMINATION, EA TITLE:WING - FLIGHT SURFACES - LH #3 SPOILER CENTER HINGE ARM OUTSIDE SURFACE DELAMINATION. THIS IS CATEGORY A REPAIR. MAJOR REPAIR IAW FEDEX GMM6-2-100. SEE WRI 57506056 FOR WORK DETAILS.

Part: CROSSBEAM — CORRODED (ZONE 100) · corrosion level 2 · airframe 61,690 hrs · 33,424 cycles

AFT CARGO FLOOR BEAM CORRODED, AT FR56,Y805-Y1470. REPAIRED THE CORRODED FLOOR BEAM AT AFT CARGO FR56,Y805-Y1470 PER A300-600 SRM53- 10-15-201 FIGURE 207 & EA 6-5321-T0383821 P1. EA TITLE:FUSELAGE - CARGO COMP FLOOR - AFT CARGO FRAME 56 CROSSBEAM - SRM REPAIR WITH MINOR DEVIATION . THIS IS CATEGORY A REPAIR. MAJOR REPAIR IAW FEDEX GMM 6-2-100. SEE WRI 53216069 FOR WORK DETAILS.

Part: FITTING — NOT REPORTED (ZONE 800) · airframe 61,690 hrs · 33,424 cycles

DOORS - CARGO DOOR/HYD SYS - DETAILED VISUAL INSPECTION OF THE MAIN DECK CARGO DOOR (MDCD) ACTUATOR BEARING FITTINGS AT FRAME 23 AND 24 - AOT A52W016-24. COMPLIED WITH EO 6-5230-E0378588 B P5. REPLACED THE MAIN DECK CARGO DOOR ACTUATOR BEARING FITTINGS. THIS IS CATEGORY B REPAIR. FOLLOW-UP INSPECTION PER EO 6-5230- E0378588 B. MAJOR REPAIR IAW FEDEX GMM6-2-100. SEE WRI 52305727 FOR WORK DETAILS.

Part: LIMIT SWITCH — DIRTY (R1 DOOR) · airframe 61,389 hrs · 33,219 cycles

R1 DOOR WILL NOT ARM. CLEANED THE 14WN LIMIT SWITCH ON THE RH DOOR IAW AMM 52-73-13-05-01. OPS CHECK GOOD AT THIS TIME. ACFT OK FOR SERVICE.

Part: POWER SUPPLY — INOPERATIVE (DOOR SLIDE) · airframe 60,983 hrs · 32,948 cycles

BOTH R1 AND L1 DOOR ESCAPE SLIDE RELEASE WARNING SYSTEM LIGHT TEST FAILED - AUDIBLE BUZZERS WORK ON BOTH DOORS. CHECKING ASPSU TEST SWITCH RESULTED IN NO LIGHTS AT ALL - BOTH BATTERIES APPEAR DISCHARGED. - REMOVED AND REPLACED BOTH BATTERIES IAW AMM 52-73-18-04 - NO HELP ASPSU LAMP TEST STILL DEAD. DEFER IAW MEL 52--XX-XX CAT : C EXP: 12JUN24 "MEL 52-XX-XX: L1 & R1 CREW ENTRY DOOR ESCAPE SLIDE WARNING SYSTEM LIGHTS - INOP. REMOVED AND REPLACED AUTONOMOUS STANDBY POWER SUPPLY UNIT (70WN) REF M/M 52-73- 18-04. TESTED REF M/M 52-73-00-05. NO FAULT LIGHTS PRESENT. ALSO CHECKED FUNCTION OF R1 SLIDE INDICATION ON ECAM REF M/M 52-73-13-05-01. OPS CHECKS GOOD OK FOR SERVICE.

Part: AILERON — DENTED (ZONE 500) · airframe 59,890 hrs · 32,237 cycles

LH WING AILERON TRAILING EDGE WEDGE UPPER SURFACE FOUND SMALL DENTS COMPLIED WITH EA: 6-5750-T0373267 P1. TITLE: WING - FLIGHT SURFACES - LH AILERON TRAILING EDGE WEDGE UPPER SURFACE REPAIR. AND REFER TO A300-600 SRM51-77-12-201 PARA.4.B FIGURE 218 & AMM57-61-00-08. REPAIRED THE LH WING AILERON TRAILING EDGE WEDGE UPPER SURFACE DENTS. THIS IS CATEGORY A REPAIR. MAJOR REPAIR IAW FEDEX GMM6-2-100.

Part: FRAME — CRACKED (ZONE 100) · airframe 59,890 hrs · 32,237 cycles

FUSELAGE INTERNAL STRUCTURE - FRAME 14 FOUND CRACK SIGNAL AT JUNCTION AREA OF MAIN DECK FLOOR BEAM AND CRUCIFORM FITTING, RH SIDE, BY ULTRASONIC INSPECTION COMPLIED WITH EA: 6-5310-T0373313 P1. TITLE: FUSELAGE - MAINFRAME - CRACK HOLE FOUND ON FRAME 14 STRG 26 RH. REPAIRED THE FUSELAGE INTERNAL STRUCTURE FRAME 14 CRACK AT JUNCTION AREA OF MAIN DECK FLOOR BEAM AND CRUCIFORM FITTING, RH SIDE. THIS IS CATEGORY B REPAIR. FOLLOW UP INSPECTION PER EA: 6-5310-T0373313. MAJOR REPAIR IAW FEDEX GMM6-2-100. SEE WRI 53-10/3829 FOR WORK DETAILS.

Part: SPOILER — DELAMINATED (ZONE 500) · airframe 59,890 hrs · 32,237 cycles

LH WING #3 SPOILER CENTER I/B HINGE ARM OUTSIDE SURFACE FOUND DELAMINATION. SIZE: 40MM*10MM, DEPTH: 1.7MM COMPLIED WITH EA: 6-5750-T0373146 P1. TITLE: WING - FLIGHT SURFACES - LH 3# SPOILER CENTER HINGE ARM OUTSIDE SURFACE DELAMINATION. REPAIRED THE LH WING #3 SPOILER CENTER I/B HINGE ARM OUTSIDE SURFACE DELAMINATION. THIS IS CATEGORY A REPAIR. MAJOR REPAIR IAW FEDEX GMM6-2-100

Part: PANEL — CRACKED (ZONE 400) · airframe 59,890 hrs · 32,237 cycles

LH PYLON I/B SIDE PANEL AT RIB8 FOUND 1EA CRACK. REPAIRED THE CRACKED LH PYLON I/B SIDE PANEL AT RIB8 PER EO: 6-5450-7-5003 I PT3 & A300-600 SRM54-51-31-201-2. EO TITLE: NACELLES/PYLONS - INSPECTION OF PYLON SIDE PANELS AT RIB8. AIRBUS SB A300-54-6015 R03 & A310-54-2018 R03. THIS IS CATEGORY B REPAIR. FOLLOW UP INSPECTION TRACKING BY EO: 6-5450-7-5003 I PT5. MAJOR REPAIR IAW FEDEX GMM6-2-100

Part: FITTING — CRACKED (ZONE 600) · airframe 59,890 hrs · 32,237 cycles

RH WING CENTER SPAR TO RIB 1 SPLICE VERTICAL FLANGE 1EA FASTENER HOLE(TYPE 5) FOUND CRACK SIGNAL BY ULTRASONIC INSPECTION COMPLIED WITH EA: 6-5710-T0373257 P1. TITLE: WINGS - BASIC WING STRUCTURE - CRACK HOLE ON FITTING RH WING CWT SPAR TO RIB1. REPAIRED THE RH WING CENTER SPAR TO RIB 1 SPLICE VERTICAL FLANGE CRACKED FASTENER HOLE. THIS IS CATEGORY B REPAIR. FOLLOW UP INSPECTION PER EA: 6-5710-T0373257. MAJOR REPAIR IAW FEDEX GMM6-2-100. SEE WRI 57-10/3826 FOR WORK DETAILS.

Part: PANEL — CRACKED (ZONE 400) · airframe 59,890 hrs · 32,237 cycles

LH PYLON O/B SIDE PANEL AT RIB8 FOUND 1EA CRACK. REPAIRED THE CRACKED LH PYLON O/B SIDE PANEL AT RIB8 PER EO: 6-5450-7-5003 I PT3 & A300-600 SRM54-51-31-201-2. EO TITLE: NACELLES/PYLONS - INSPECTION OF PYLON SIDE PANELS AT RIB8. AIRBUS SB A300-54-6015 R03 & A310-54-2018 R03. THIS IS CATEGORY B REPAIR. FOLLOW UP INSPECTION TRACKING BY EO: 6-5450-7-5003 I PT5. MAJOR REPAIR IAW FEDEX GMM6-2-100

Part: DOOR — CRACKED (ZONE 800) · airframe 59,890 hrs · 32,237 cycles

RH FWD CREW/COURIER DOOR INTERNAL STRUCTURE FRAME SEGMENT AT FR14C FOUND 2EA CRACKS REPLACED RH FWD CREW/COURIER DOOR CRACKED FRAME SEGMENT AT FR14C WITH A FABRICATED PART PER A300-600 SRM51-40-21 AND DWG: A52111406 (ISSUE.C), A52111327(ISSUE.E). TRACKING EA 6-5210-T0373255 P1 RAISED AND ACCOMPLISHED. EA TITLE: DOORS - PASSENGER /CREW - LOCAL FABRICATION AND REPLACEMENT OF FRAME SEGMENT ON R1 DOOR - RSC TRACKING. THIS IS CATEGORY A REPAIR. MAJOR REPAIR IAW FEDEX GMM6-2-100.

Part: SPAR — CRACKED (ZONE 400) · airframe 59,890 hrs · 32,237 cycles

RH PYLON LWR SPAR FOUND CRACK BETWEEN RIB6 AND RIB7 AT STIFFENER END BY EDDY CURRENT INSPECTION COMPLID WITH EA: 6-5450-T0373394 P1. TITLE: NACELLES/PYLON - WING PYLON/STRUT - #2 ENGINE PYLON LOWER SPAR CRACK BETWEEN RIB 6&7 - REPAIR. REPAIRED THE RH PYLON LWR SPAR CRACK BETWEEN RIB6 AND RIB7 AT STIFFENER END. THIS REPAIR IS DEFINED AS CATEGORY C REPAIR. REPAIR LIFE LIMITATION IS 6 MONTHS PER EA: 6-5450-T0373394. MAJOR REPAIR IAW FEDEX GMM6-2-100. SEE WRI 54-50/3831 FOR WORK DETAILS.

Part: NONE — NONE (N/A) · airframe 59,890 hrs · 32,237 cycles

LH FWD CREW/COURIER DOOR INTERNAL STRUCTURE FRAME SEGMENT AT FR14C FOUND 1EA CRACK

Part: SELECTOR VALVE — UNKNOWN (N/A) · airframe 59,075 hrs · 31,746 cycles

MDIS 722 32-44 2658 12MAY22 MEM OPEN U PER FLIGHT CREW: ON TAXI OUT, HOLDING SHORT OF RUNWAY, PARKING BRAKE WAS SET AND INDICATED PARKING BRAKE ON ON ECAM, HOWEVER WHEN BRAKE PEDALS WERE RELEASED A/C MOVED FORWARD. RECYCLED PARKING BRAKE 4 TIMES BUT PROBLEM PERSISTED. RETURNED TO GATE. FACT 12MAY22 20:36 MEM REMOVED AND REPLACED PARKING BRAKE SELECTOR VALVE (3309) REF AMM 32-45-12-04. OPS CKS AND LEAK CKS GOOD. OK FOR SERVICE. PER SDR , THE MANUFACTURER OF THE VALVE IS MESSIER - HISPANO.

Part: NONE — NONE (N/A) · airframe 58,940 hrs · 31,655 cycles

R1 CABIN DOOR DOES NOT INDICATE ARMED ON ECAM. ALL OTHER INDICATIONS ARE NORMAL. REMOVED POWER FROM ASPCU. AFTER PUTTING POWER BACK ON ASPCU, PERFORMED OPERATIONAL TEST OF R1 AND L1 DOORS ARM FUNCTION AND ALL INDICATIONS WORK PROPERLY AT THIS TIME. OKAY FOR CONTINUED SERVICE. NO PARTS REMOVED OR REPLACED

Part: NONE — LEAKING (N/A) · airframe 58,879 hrs · 31,629 cycles

ABOUT 5 TO 10 MINUTES IN CRUISE FLIGHT AT FL340 I NOTICED WITH MY OVERHEAD SCAN THAT THE GREEN HYD QUANTITY WAS MID WAY IN THE YELLOW. I THEN LOOKED AT THE GREEN HYDRAULICS ON THE ECAM AT IT SHOWED 440 PSI. FROM THERE IT WAS A FEW MINUTES AND WE GOT THE ECAM NOTIFICATION AND THE QUANTITY NEEDLE WAS AT RED DOT, WITH CORRESPONDING LOW PRESSURE. WE TURNED THE GREEN PUMPS OFF IN ABOUT 30 SECONDS AND COMPLIED WITH ALL ECAM AND QRH PROCEDURES EXCEPT THE LANDING GEAR GRAVITY EXTENSION QRH PROCEDURE WHILE AT CRUISE FLIGHT. WE CALLED RAMP AND LET THEM KNOW WE WERE INBOUND AND WE WILL BE AN EMERGENCY AIRCRAFT AND STOPPING AND SHUTTING DOWN ON RW 18R AND NEEDING A TOW TO THE RAMP. WE DECLARED AN EMERGENCY WITH CENTER FOR THE DESCENT WITH NORMAL GRAVITY EXTENSION AND LANDING. FOUND GREEEN HYD PRESSURE TRANSMITTER LEAKING.REMOVED AND INSTALLED GREEN HYDRAULIC PRESSURE TRANSMITTER PER AMM 29-11-12-04, QTY AND PRESS WITHIN LIMITS, OPS CKS NORMAL, NO LEAKS NOTED AT THIS TIME.

Part: BATTERY PACK — DISLODGED (R1 DOOR SLIDE) · airframe 57,500 hrs · 30,789 cycles

DOOR 1R SLIDE HAS BATTERY PACK FALLING OUT OF SLIDE INTERFERING WITH GIRT BAR ENGAGEMENT. REASON CODE: REMOVAL FROM A/C ONLY, NO INSTALLATION OFF MPN: D30546-509FX CPN: 2513882 POS: R1 SRL: A5756 TAG NBR: 00F514. REMOVED ESCAPE SLIDE FROM DOOR 1R, PER AMM 25-61-22-04-01. GIRT BAR AND SLIDE COVER PLACED IN COURIER AREA COAT CLOSET. RELEASED FOR SERVICE PER MEL: 52-11-01-03 CAT: C EXP: 20DEC20 MEL 52-XX-XX-XX-: CREW ENTRY DOOR ESCAPE SLIDE R1- REMOVED. INSTALL ONLY SLIDE/RAFT ASSEMBLY, IAW A300 MM CH 25-61-22-04-01.

Part: BATTERY — DETACHED (R1 DOOR SLIDE) · airframe 57,485 hrs · 30,779 cycles

CABIN DOOR R-1 NO SLIDE INDICATION ON ECAM WHEN ATTEMPTED TO ARM DOOR FOR PUSHBACK. RELEASED FOR SERVICE PER MEL: 52-XX-XX-XX CAT: C EXP: 14DEC20 "MEL 52-XX-XX-XX: CREW ENTRY DOOR ESCAPE SLIDE R1-INOPERABLE. SLIDE REMAINS INSTALLED ON DOOR. THIS MEL ITEM WAS FACT'D AND TRANSFERRED TO MEL 52-XX-XX-XX AND SLIDE PACK UNIT WAS REMOVED AFTER THE INTERNAL BATTERY PACK DETACHED FROM STOWAGE POCKET AND LODGED INTO GIRT BAR RETRACTION MECHANISM.

Part: UNKNOWN — UNKNOWN (CARGO BAY) · airframe 57,485 hrs · 30,779 cycles

DURING APPROACH WHILE DECELERATING HEARD AND FELT A THUD. SUSPECT POSSIBLE LOAD SHIFT. RAMP REPORTED CAN UNSECURED IN LOWER FORWARD BELLY, ALLOWING CAN TO SHIFT BETWEEN LOCKS, APPROXIMATELY 5 FEET FORWARD AND AFT. PERFORMED INSPECTION ON PALLET LOCKS, NO DEFECTS NOTED AT THIS TIME. ALL LOCKS OPERATE NORMALLY. NO OTHER DAMAGE NOTED AS A RESULT OF LOOSE CAN IN FORWARD BELLY, IAW AMM 25-50-00-06-01, 25-52-33-04-01, AND 25-52-33. A/C OK TO CONTINUE.

Part: FLOORBOARD — BROKEN (ZONE 200) · airframe 57,397 hrs · 30,721 cycles

ZONE 260 FLOOR BOARD 261NF IS BROKEN. FABRICATED ZONE 260 FLOOR BOARD 261NF ON VTMAE TRAVELER T20/1518281, IAW DWG SRZ-25-005R, MAJOR REPAIR.

Part: FLOOR PANEL — CRACKED (FWD CARGO) · airframe 57,397 hrs · 30,721 cycles

FWD CARGO COMPARTMENT METAL FLOOR PANEL 131NG IS CRACKED. FABRICATED FLOOR PANEL 131NG ON VTMAE TRAVELER T20/1516758, IAW DWG A53272579, PART MARKED PANEL, IAW GMM 07-0-1001, CLASSIFIED AS CAT "A" AND MAJOR REPAIR.

Part: FLOORBOARD — DAMAGED (ZONE 200) · airframe 57,397 hrs · 30,721 cycles

ZONE 240 FLOOR BOARD 241XG IS BROKEN. FABRICATED ZONE 240 FLOOR BOARD 241XG ON VTMAE TRAVELER T20/1518620, IAW DWG SRZ-25-005R, MAJOR REPAIR.

Part: FLOORBOARD — DAMAGED (CABIN) · airframe 57,397 hrs · 30,721 cycles

ZONE 230 FLOOR BOARD 232TG IS BROKEN. FABRICATED ZONE 230 FLOOR BOARD 232TG ON VTMAE TRAVELER T20/1518299, IAW DWG SRZ-25-005R, MAJOR REPAIR.

Part: FLOOR PANEL — CRACKED (FWD CARGO) · airframe 57,397 hrs · 30,721 cycles

FWD CARGO COMPARTMENT METAL FLOOR PANEL 131LG IS CRACKED. FABRICATED FLOOR PANEL 131LG ON VTMAE TRAVELER T20/1516757, IAW DWG A53272573, PART MARKED PANEL PER GMM 07-0-1001. CLASSIFIED AS CAT "A" AND MAJOR REPAIR.

Part: FLOORBOARD — BROKEN (CABIN) · airframe 57,397 hrs · 30,721 cycles

ZONE 250 FLOOR BOARD 252BH IS BROKEN. FABRICATED ZONE 250 FLOOR BOARD 252BH ON VTMAE TRAVELER T20/1518269, IAW DWG SRZ-25-005R, MAJOR REPAIR.

Part: FLOORBOARD — BROKEN (CABIN) · airframe 57,397 hrs · 30,721 cycles

ZONE 250 FLOOR BOARD 251RH IS BROKEN. FABRICATED ZONE 250 FLOOR BOARD 251RH ON VTMAE TRAVELER T20/1518289, IAW DWG SRZ-25-005R, MAJOR REPAIR.

Part: FLOORBOARD — BROKEN (CABIN) · airframe 57,397 hrs · 30,721 cycles

ZONE 260 FLOOR BOARD 261RF IS BROKEN. FABRICATED ZONE 260 FLOOR BOARD 261RF ON VTMAE TRAVELER T20/1518266, IAW DWG SRZ-25-005R, MAJOR REPAIR.

Part: FLOORBOARD — BROKEN (CABIN) · airframe 57,397 hrs · 30,721 cycles

ZONE 250 FLOOR BOARD 252VF IS BROKEN. FABRICATED ZONE 250 FLOOR BOARD 252VF ON VTMAE TRAVELER T20/1518802 IAW DWG SRZ- 25-005R, MAJOR REPAIR.

Part: FLOORBOARD — DAMAGED (CABIN) · airframe 57,397 hrs · 30,721 cycles

ZONE 250 FLOOR BOARD 252GF IS BROKEN. FABRICATED ZONE 250 FLOOR BOARD 252GF ON TRAVELER T20/1518616, IAW DWG SRZ-25-005R, MAJOR REPAIR.

Part: FLOORBOARD — DAMAGED (CABIN) · airframe 57,397 hrs · 30,721 cycles

ZONE 230 FLOOR BOARD 231SG IS BROKEN. FABRICATED ZONE 230 FLOOR BOARD 231SG ON TRAVELER T20/1518654, IAW DWG SRZ-25-005R MAJOR REPAIR.

Part: FLOOR PANEL — DAMAGED (ZONE 100) · airframe 57,397 hrs · 30,721 cycles

FWD CARGO COMPT FLOOR PANEL 132RF IS BROKEN. FABRICATED FLOOR PANEL 132RF ON VTMAE TRAVELER T20/1517566, IAW DWG SRZ-25-005R. CLASSIFIED AS CAT "A" REPAIR, MAJOR REPAIR.

Part: FLOOR PANEL — DAMAGED (CABIN) · airframe 57,397 hrs · 30,721 cycles

PANEL 151KF HAS NUMEROUS AREAS OF DAMAGE TO EDGES AND MISSING CORE. FABRICATED FLOOR PANEL 151KF ON VTMAE TRAVELER T20/1519073 IAW DWG SRZ-25-005R. CLASSIFIED AS CATAGORY "A" REPAIR, MAJOR REPAIR.

Part: FLOOR PANEL — CRACKED (ZONE 100) · airframe 57,397 hrs · 30,721 cycles

AFT CARGO FLOOR PANEL 152LF HAS CRACK AND EDGE DAMAGE. FABRICATED FLOOR PANEL 152LF ON VTMAE TRAVELER T20/1519074, IAW DWG SRZ-25-005R. CLASSIFIED AND CATAGORY "A" REPAIR, MAJOR REPAIR.

Part: FLOOR PANEL — DAMAGED (ZONE 100) · airframe 57,397 hrs · 30,721 cycles

FWD CARGO COMPT FLOOR PANEL 131RF IS BROKEN. FABRICATED FLOOR PANEL 131RF ON VTMAE TRAVELER T20/1517567, IAW DWG SRZ-25-005R. CLASSIFIED AS CAT "A" REPAIR, MAJOR REPAIR.

Part: FLOOR SUPPORT — CORRODED (FRAMES 10-15) · corrosion level 2 · airframe 57,397 hrs · 30,721 cycles

(DOT 38-79) MDC FLOOR SUPPORT Y730 BETWEEN FR 13-FR 14 CORRODED. NO ESTABLISHED LIMITS, FOUND TO BE OUT LIMITS. FABRICATED FLOOR SUPPORT ON VTMAE TRAVELER T20/1518605, P/N FX-A53612213202, IAW SRM 53-12-15, MAT. NSA 343036, BATCH 3272259. LOCATED AND DRILLED, IAW SRM 51-40-44. REMOVED AND REPLACED FLOOR SUPPORT, IAW SRM 51-40-21, FR 10-15, MAJOR REPAIR.

Part: SEAT TRACK — GOUGED (ZONE 200) · airframe 57,397 hrs · 30,721 cycles

DOT 66-59 MAIN CABIN SEAT TRACK BETWEEN FR 63-64, Y1456 HAVE GOUGED AREAS. REMOVED DAMAGE AT SEAT TRACK Y 1456 ON SCALLOP HOLE UPPER, IAW SRM 51-73-10. MAXIMUM ALLOWABLE MATERIAL REMOVE IS 0.840" AFTER REWORK IS 0.870" FOUND OUT OF LIMITS, IAW SRM 53-10-16 FIG 101, TR 88614. CUT OUT DAMAGE SEAT TRACK SECTION BETWEEN FR 63-65, IAW SRM 53-10-16 FIG 208. REMOVED AND REPLACED SEAT TRACK BETWEEN FR 63-65 Y 1456, IAW SRM 53-10-16 FIG 208, MAJOR REPAIR.

Part: SLIDE — INOPERATIVE (R1 DOOR) · airframe 57,120 hrs · 30,535 cycles

R1 MAIN CABIN ENTRY DOOR SLIDE WILL NOT ARM. DOOR ESCAPE SLIDE ARMING SYSTEM IS TO BE VERIFIED AS FULLY ARMED PRIOR TO EACH DEPARTURE." RI SLIDE ARMS NORMAL, ECAM INDICATION ONLY IS INOP. C/7233656

Part: SWITCH — WORN (R1 DOOR) · airframe 57,120 hrs · 30,535 cycles

R1 MAIN CABIN ENTRY DOOR SLIDE WILL NOT ARM. IAW TSM 52-70-00, CHECKED FOR GROUND AT R1 DOOR LIMIT SWITCHES. FOUND EXCESSIVE RESISTANCE AT PIN "E" OF LIMIT SWITCH 1 (42WS), AND OPEN FOUND AT PIN "E" OF LIMIT SWITCH 2 (8WS). NO TIME TO FURTHER TROUBLESHOOT DUE TO HIGHER PRIORITY MAINTENANCE. REMOVED AND INSTALLED BOTH 8WS AND 42WS SWITCHES IAW AMM 52-71-00-04-01, CHECKS GOOD

Part: OIL SYSTEM — LEAKING (NR 2 ENGINE) · airframe 55,960 hrs · 29,824 cycles

SHORTLY AFTER LEVEL OFF AT FL320, NOTICED ENG #2 OIL QTY SHOWING 7 QTS, WHILE ENG #1 HAD 15 QTS. WITHIN 10 MINUTES, OIL QTY CONTINUED TO DECREASE TO ZERO. DURING THAT TIME OIL PRESSURE WAS NORMAL AT 195 PSI AND OIL TEMP 140 DEGREES. RETARDED THROTTLE #2 TO IDLE AND OIL STAYED AT ZERO. EVENTUALLY OIL PRESSURE BEGAN TO FLUCTUATE /- 50 PSI WITH OIL LO PRESS WARNING LIGHT FLICKERING. SHUT DOWN #2 ENGINE AND LANDED KMEM. POST FLIGHT SHOWED QUANTITIES OF OIL LEAKING FROM ENGINE. REPLACED #2 ENGINE PER W/C 7100000-02-16.

Part: DUCT — UNKNOWN (AC SYSTEM) · airframe 55,349 hrs · 29,489 cycles

PASSING THROUGH FLIGHT LEVEL 340, CABIN ALTITUDE WARNING ON ECAM ACTIVATED. VERIFIED MANUAL GAGE PASSING THROUGH 10,000 FEET CABIN ALTITUDE. SWITCHED TO MANUAL CONTROL AND ALL OUTFLOW VALVES SHOWED CLOSED, BUT CABIN ALTITUDE STILL CLIMBED PASSING 12,000 FEET. DESCENDED TO 10,000 FEET AND RECOVERED. TURNED OFF BOTH AUTO CONTROLLERS AND TRIED TO MANUALLY CONTROL CABIN ALTITUDE WITH NO SUCCESS. FOUND BLOWN DUCT IN AIR EXTRACTION SYSTEM RESULTING IN IMPROPER PRESSURIZATION. REPLACED DUCT REF AMM 21-23-12-04 TESTED REF AMM 21-23-11-04. CHECKS GOOD ON GROUND.

Part: FRAME — CORRODED (FUSELAGE) · airframe 54,852 hrs · 29,227 cycles

FUSELAGE FR39, BETWEEN STR 52L AND STR 54L, FRAME WITH INTER-GRANULAR CORROSION. REPAIRED THE CORRODED FUSELAGE TEE BEAM AT FR39 S52L-S54L. THIS REPAIR CATEGORY IS "C", REPAIR LIFE LIMITATION IS 6 MONTHS. MAJOR REPAIR IAW GMM6-2-100.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 54,852 hrs · 29,227 cycles

MDCC - FR11-FR12, Y730, FLOOR SUPPORT WITH EXFOLIATING CORROSION. REPLACED MDCC FLOOR SUPPORT BETWEEN FR11 AND FR13A, Y730 PER SRM51-40-21. THIS REPAIR IS CATEGORY "A". MAJOR REPAIR IAW GMM6-2-100.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 54,852 hrs · 29,227 cycles

MDCC FLOOR - FR11-FR13 Y953, FLOOR SUPPORT WITH CORROSION AROUND BOLTHOLES. REPLACED MDCC FLOOR SUPPORT BETWEEN FR11 AND FR15A, Y953 PER SRM 51-40-21. THIS REPAIR IS CATEGORY "A". MAJOR REPAIR IAW GMM6-2-100.

Part: STIFFENER — CORRODED (FUSELAGE) · airframe 54,852 hrs · 29,227 cycles

LAVATORY SERVICE PANEL CUTOUT STIFFENER WITH INTER-GRANULAR CORROSION AT LOWER EDGE, BETWEEN FR12 AND FR12A. REPLACED THE CORRODED STIFFENER OF LAVATORY SERVICE PANEL CUTOUT PER SRM 51-40-21.THIS REPAIR CATEGORY IS"A" MAJOR REPAIR IAW GMM6-2-100.

Part: CONNECTOR — DAMAGED · airframe 54,648 hrs · 29,103 cycles

MULTIPLE ELECTRICAL FAILURES ON GROUND AND AIRBORNE, SOME RESET SOME DID NOT. ON GROUND ELECTRICAL SURGE DESELECTED ALL PADDLE SWITCHES, ACARS, FMS, AND FCP. 2. AIRBORNE RA 1 AND 2, TCAS, GPWS, LAND INHIBITED. VOR 1 FLAG. 3. R74 CB WAS POPED ON PREFLIGHT AS WELL AS A LEFT CENTER FUEL PUMP ON THE GROUND. REMOVED AND REPLACED CONNECTOR 2167VC IAW ESPM AND AWL 91-25-86.

Part: SLAT SYSTEM — MALFUNCTIONED · airframe 54,505 hrs · 29,021 cycles

DURING APPROACH, SELECTED SLATS & FLAPS 15/0. RECEIVED SLAT 1 AND SLAT 2 FAULTS. CYCLED THE SLAT/FLAP HANDLE, STILL HAD FAULTS. RAN QRH. LANDED WITH SLATS AT 0 DEGREES AND FLAPS AT 40 DEGREES. CHECKED BOTH THE NR 1 & 2 SFCCS AND FOUND JAMB CODE ON BOTH SFCC'S FOR SLAT SYSTEM 1 AND 2. RESET FAULTS IAW TSM 27-80-00. RAN BOTH ENGINES IAW CHECKLIST AND OPERATED FLAPS AND SLATS THROUGH SEVERAL CYCLES WITH NO FAULTS AT ANY TIME. SLATS AND FLAPS OPERATE NORMALLY IAW MM 27-84-00-5. OK FOR SERVICE.

Part: WIRE — MISINSTALLED (BRAKE) · airframe 54,115 hrs · 28,791 cycles

NR 4 MAIN TIRE BLEW ON LANDING. ANTI-SKID DID NOT RELEASE. CONNECTOR AT 18GG RECEPTICALS A & C AT CONNECTION ON NR 4 BRAKE SERVO VALVE INSTALLED IN WRONG POSITIONS. INSERTED WIRE (A)-4063 INTO A, AND INSERTED WIRE (C) -4062 INTO C IAW WDM 32-42-05, AND SCHEMATIC MANUAL 32-42-00, SCHEM 04 PG 101. PERFORMED A RIGHT MAIN GEAR BRAKES BLEEDING PROCEDURES MAIN GREEN SYSTEM AND ALT YELLOW SYST. REF AMM 32-42-00-3. ACCOMPLISHED ALL ADJUSTMENT AND TEST PROCEDURES FOR COMPONENTS REPLACED IAW AMM 32-42-00-05, NO LEAKS NOTED, REMOVED TEST EQUIPMENT FOM LEFT NOSE WHEEL REINSTALLED TACH WHEEL CAP ON LEFT NOSE TIRE IAW AMM 12-37-32-00-02. AIRCRAFT OK FOR SERVICE.

Part: BATTERY — FAILED (PAX DOOR SLIDE) · airframe 53,432 hrs · 28,326 cycles

RIGHT ENTRY DOOR SLIDE WILL NOT ARM. R1 DOOR CHECKED FOR CORRECT ARMING. NR 1 BATTERY AT POWER SUPPLY UNIT AUTOMOUS STANDBY, REMOVED AND INSTALLED BATTERY. OPS CHECKED IAW 52-73-18-04. ASPSU TESTED OK. PERFORMED SLIDE RELEASE WIRING TEST IAW AMM 52-73-00-05-01. ALL TEST PASSED. ACFT OK FOR SERVICE.

Part: CIRCUIT BREAKER — MALFUNCTIONED (R1 DOOR SLIDE) · airframe 53,216 hrs · 28,104 cycles

R1 DOOR WILL NOT INDICATE THE SLIDE ARMED ON ECAM. CIRCUIT BREAKER RESET GOOD. DOOR SLIDE INDICATION SYSTEM TESTED GOOD IAW MM 52-73-00.

Part: GCU — FAILED (NR 2) · airframe 52,978 hrs · 27,923 cycles

ON INITIAL CLIMB, NR 2 GENERATOR FAILED. REMOVED AND REPLACED THE NR 2 GCU IAW AMM 24-22-12-04, TESTED OK. RAN NR ENGINE AW JRH, GENERATOR TESTED OK.

Part: RELIEF VALVE — FAULTY (HYDRAULIC SYS) · airframe 52,886 hrs · 27,866 cycles

ON CLIMBOUT, APPROXIMATELY 2500' GOT ECAM, GROUND HYD RESERVOIR LOW AIR PRESSURE, PRESSURE WAS STEADY, ECAM CLEARED ITSELF. GOT SAME ECAM ON FINAL, APPROXIMATELY 1500' EXECUTED GO AROUND. RETURNED TO DEPARTURE. REMOVED AND REPLACED PRESSURE RELIEF VALVE PER MM 29-00-00-04-0. RAN NR 1 ENGINE TO CHECK PRESSURIZATION OF GREEN RESERVOIR OP'S CHECK GOOD. ALSO PRESSURIZED GREEN RESEVOIR USING APU AIR OP'S CHECK GOOD BOTH THE APU AND ENGINE WERE RAN PER JRH. A/C OK FOR SERVICE.

Part: BEAM — CRACKED (FUSELAGE) · airframe 52,251 hrs · 27,592 cycles

UPPER CTR WING SECTION STRUCTURE, LT BEAM NR 2 JUNCTION AT FRAME 46, LOWER HOLE WITH CRACK SIGNAL. COMPLIED WITH EA 6-5310-T0322973 P 1. DAMAGE IN HOLES OF BEAM 2 RT & BEAM 3 RT & BEAM 2 LT, MDCC FRAME 46. REPAIRED UPPER CTR WING SECTION STRUCTURE, LT BEAM NR 2 JUNCTION AT FRAME 46, LOWER HOLE. MAJOR REPAIR IAW GMM 6- 2-100.

Part: BEAM — CRACKED (FUSELAGE) · airframe 52,251 hrs · 27,592 cycles

UPPER CTR WING SECTION STRUCTURE, RT BEAM NR 2 JUNCTION AT FRAME 46, LOWER HOLE WITH CRACK SIGNAL. COMPLIED WITH EA 6-5310-T0322973 P 1. FUSELAGE - MAINFRAME - DAMAGE IN HOLES OF BEAM 2 RT & BEAM 3 RT & BEAM 2 LT, MDCC FRAME 46. REPAIRED JUNCTION AT FRAME 46 LOWER HOLE. MAJOR REPAIR IAW GMM 6-2-100.

Part: BEAM — CRACKED (FUSELAGE) · airframe 52,251 hrs · 27,592 cycles

UPPER CTR WING SECTION STRUCTURE, RT BEAM NR 3 JUNCTION AT FRAME 46, UPPER HOLE WITH CRACK SIGNAL. COMPLIED WITH EA 6-5310-T0322973 P 1. DAMAGE IN HOLES OF BEAM 2 RT & BEAM 3 RT & BEAM 2 LT, MDCC FRAME 46. REPAIRED UPPER CTR WING SECTION STRUCTURE, RT BEAM NR 3 JUNCTION AT FRAME 46, UPPER HOLE. MAJOR REPAIR IAW GMM 6-2-100.

Part: WEB — CRACKED (FUSELAGE) · airframe 52,251 hrs · 27,592 cycles

MDCC UNDER FLOOR, ONE EACH WEB, CRACKED AT FRAME 47, Y953 ~ Y1456. REPAIRED THE WEB IAW SRM 53-15-15 FIGURE 201. THE REPAIR WAS CATEGORY B & INSPECTION THRESHOLD FROM REPAIR EMBODIMENT 24000 FC & FH NOT RELEVANT. SUBSEQUENT INSPECTION AT INTERVAL OF 3000 FC & FH NOT RELEVANT. INSPECTION METHOD DETAILED VISUAL IAW SRI 53-15-15-2-001-00. MAJOR REPAIR IAW GMM 6-2-100.

Part: WEB — CRACKED (FUSELAGE) · airframe 52,251 hrs · 27,592 cycles

MDCC UNDER FLOOR, ONE EACH WEB, CRACKED AT FRAME 47, -Y953 ~ -Y1456. FABRICATED THE NEW WEB IAW DWG A53832103 & MARKED AS FX A5383210320600 IAW GMM 7-0-1001. REPLACED THE CRACKED WEB OF MDCC FRAME 47, -Y953 ~ -Y1456 IAW SRM51-40-21. MAJOR REPAIR IAW GMM 6-2-100.

Part: WEB — CRACKED (FRAME 47) · airframe 52,251 hrs · 27,592 cycles

MDCC UNDER FLOOR, ONE EACH WEB CRACKED, AT FRAME 47, Y0 -Y450. FABRICATED THE NEW WEB IAW DWG A53832100. REPLACED THE CRACKED WEB IAW SRM 51-40-21. MAJOR REPAIR IAW GMM 6-2-100.

Part: WEB — CRACKED (FUSELAGE) · airframe 52,251 hrs · 27,592 cycles

MDCC UNDER FLOOR, ONE EACH WEB CRACKED, AT FRAME 47, Y0~Y450. REPAIRED THE WEB IAW SRM 53-15-15 FIGURE 201. THE REPAIR WAS CATEGORY B & INSPECTION THRESHOLD FROM REPAIR EMBODIMENT 24000 FC & FH NOT RELEVANT. SUBSEQUENT INSPECTION AT INTERVAL OF 3000 FC & FH NOT RELEVANT. INSPECTION METHOD DETAILED VISUAL IAW SRI 53-15-15-2-001-00. MAJOR REPAIR IAW GMM 6-2-100.

Part: STRINGER — CORRODED (FRAME 11) · airframe 52,251 hrs · 27,592 cycles

AV COMPARTMENT BELOW RT FLOOR FUSELAGE INTERNAL STRUCTURE, BETWEEN FRAME 11 & 11A, FOUND CORROSION ON BOTTOM STRINGER. COMPLIED WITH EA 6-5310-T0323047 P 1. REPLACED NLG BULKHEAD, RT SIDE LATERAL KEEL BEAM AT FRAME 11 - 11A. MAJOR REPAIR IAW GMM 6-2-100.

Part: HINGE BRACKET — DAMAGED (LE SLAT) · airframe 52,251 hrs · 27,592 cycles

DURING WALK AROUND, FOUND RT FOLDING NOSE DROP A LITTLE BIT, FURTHER TROUBLESHOOTING FOUND HINGE BRACKET ASSEMBLY BROKEN APART. THE HINGE BRACKET REF TO IPC 27-81-33-01 ITEM 310.FOLDING NOSE BENT & CRACKED, NEED TO REPLACE. FURTHER INSPECTION FOUND THE LEADING WING SKIN BENEATH THE NR 1 SLAT & FOLDING NOSE WAS TEAR & CRACK ABOUT 6 INCH LONG & 2.5 INCH WIDTH. ALSO SEAL BROKEN ON THE FOLDING NOSE, RIB ALSO DAMAGED IAW SRM 57-41-11-001 FIG 4 SHEET 1 ITEM 150, STATION 5.65. RIB REPAIRED & EDGE REINFORCEMENT FABRICATED PER SRM. NEW LE D SKIN PANEL ALONG WITH RIB & EDGE FITTED. FOLDING NOSE & IT'S SPRING ROD HARDWARE - FITS & CLEARANCE INSPECTION - COMPLIED WITH SATIS. NEW FIX SKIN INSTALLED BY VENDOR PER SRM 57-41-11-201 PARAGRAPH 4A. 1. NEW SPRING ROD. 2. NOSE FOLDING ASSEMBLY. 3. NOSE FOLDING BRACKET. 4. TSI CREATED FOR GAP & WING IN-OUT STEP CHECKS BET SPRING ROD FAIRING PLATE / SLAT SURFACE / FOLDING NOSE. ITEM 1, 2. 3 PARTS AVAIL IN HAND & ALL ALONG WITH 4 - ASSIGNED TO C/OUT DURING ONGOING 'C' CHECK.

Part: HOOK AND LOOP — LOOSE (ESCAPE ROPE) · airframe 52,187 hrs · 27,564 cycles

FIRST OFFICER ESCAPE ROPE COVER KEEPS FALLING DOWN. THE VELCRO BACKING NEEDS TO BE REPLACED. R & R VELCRO BACKING FROM FIRST OFFICERS ESCAPE ROPE COVER PANEL IAW SMP, SECURED SAID PANEL. CONDITION NOW SATISFACTORY. ACFT OK FOR SERVICE.

Part: FRAME — CRACKED (FRM 17) · airframe 50,197 hrs · 26,719 cycles

NOSE WW LT AFT CUT OUT LOWER FRAME 17 HAS ONE CRACK. REPAIRED IAW EA 6-5330-T0312514 PT1. REPAIR MINOR IAW GMM 6-2-100.

Part: STRINGER — CORRODED (FRAME 63) · corrosion level 2 · airframe 50,197 hrs · 26,719 cycles

AFT CARGO BAY STRINGER 54L FOUND CORRODED AT FRAME 63. REPAIRED THE STRINGER IAW SRM 53-10-14 FIG 201. MAJOR REPAIR IAW GMM 6-2-100.

Part: FITTING — CRACKED (FRAMES 13-14) · airframe 50,197 hrs · 26,719 cycles

RT SIDE CONNECTION FITTING IN NLG BAY BETWEEN FRAMES 13A & 14 FOUND A CRACK MORE THAN 2.5 MM. REPAIRED IAW EA T6-5310-73832 P1. MAJOR REPAIR IAW GMM 6-2-100

Part: FRAME SPLICE — CRACKED (FRAME 47) · airframe 50,197 hrs · 26,719 cycles

FUSELAGE FRAME 47 SPLICE FITTING BETWEEN STRINGER 24 & 26L FOUND CRACKED. REPAIRED IAW EO 6-5310-7-5017 C PT5. MAJOR REPAIR IAW GMM 6-2-100.

Part: FLOOR SUPPORT — DELAMINATED (FRAMES 11-14) · corrosion level 2 · airframe 50,197 hrs · 26,719 cycles

MAIN DECK, FRAMES 11 - 14 Y730 FLOOR SUPPORT DELAMINATED. REPLACED THE FLOOR SUPPORT IAW SRM 51-40-21, MAJOR REPAIR IAW GMM 6-2-100.

Part: STRINGER — CORRODED (FRAMES 58-60) · corrosion level 2 · airframe 50,197 hrs · 26,719 cycles

AFT CARGO BAY STRINGER 55L, FOUND CORRODED BETWEEN FRAMES 58 & 60. REPAIRED THE STRINGER IAW SRM 53-10-14 FIG 201. MAJOR REPAIR IAW GMM 6-2-100.

Part: FLOORBEAM — CORRODED (FRAME 66) · corrosion level 2 · airframe 50,197 hrs · 26,719 cycles

BULK CARGO BAY, FRAME 66 - Y494 FLOORBEAM DELAMINATED. REPLACED THE FLOORBEAM IAW SRM 51-40-21. MAJOR REPAIR IAW GMM 6-2-100.

Part: FLOORBEAM — CORRODED (FRAME 65) · corrosion level 2 · airframe 50,197 hrs · 26,719 cycles

BULK CARGO BAY FRAME 65 - Y805 FLOORBEAM DELAMINATED. REPLACED THE FLOORBEAM IAW SRM 51-40-21 MAJOR REPAIR IAW GMM 6-2-100.

Part: FLOOR SUPPORT — CORRODED (FRAME 65) · corrosion level 2 · airframe 50,197 hrs · 26,719 cycles

BULK CARGO BAY FRAME 65 - Y805 FLOOR SUPPORT DELAMINATED. REPLACED THED FLOOR SUPPORT IAW SRM 51-40-21 MAJOR REPAIR IAW GMM 6-2-100.

Part: FRAME SPLICE — CRACKED (FRAME 47) · airframe 50,197 hrs · 26,719 cycles

FUSELAGE FRAME 47 SPLICE FITTING BETWEEN STRINGERS 24 & 26 LT HOLE C FOUND CRACK SIGNAL. REPAIRED IAW EO 6-5310-7-5017 C PT5. MAJOR REPAIR IAW GMM 6-2-100.

Part: FITTING — CRACKED (FRAME 47) · airframe 50,197 hrs · 26,719 cycles

FUSELAGE CTR WING BOX REAR SPAR & BOTTOM PANEL LT SIDE HOLE A FOUND CRACK SIGNAL. REPAIRED IAW EA 6-5710-T0312477 P1. MAJOR REPAIR IAW GMM 6-2-100

Part: FITTING — CRACKED (FRAME 47) · airframe 50,197 hrs · 26,719 cycles

FUSELAGE CTR WING BOX REAR SPAR & BOTTOM PANEL LT SIDE HOLE F FOUND CRACK SIGNAL. REPAIRED IAW EA 6-5710-T0312477 P1.

Part: FITTING — CRACKED (FRAME 47) · airframe 50,197 hrs · 26,719 cycles

FUSELAGE CTR WING BOX REAR SPAR & BOTTOM PANEL LT SIDE HOLE G FOUND CRACK SIGNAL. REPAIRED IAW EA 6-5710-T0312477 P1. MAJOR REPAIR IAW GMM 6-2-100

Part: FITTING — CRACKED (FRAME 47) · airframe 50,197 hrs · 26,719 cycles

FUSELAGE CTR WING BOX REAR SPAR & BOTTOM PANEL RT SIDE HOLE G FOUND CRACK SIGNAL. REPAIRED IAW EA 6-5710-T0312477 P1. MAJOR REPAIR IAW GMM 6-2-100.

Part: STRINGER — CORRODED (FRAMES 59-60) · corrosion level 2 · airframe 50,197 hrs · 26,719 cycles

AFT CARGO STRINGER 54L FOUND CORRODED BETWEEN FRAMES 59 & 60. REPAIRED IAW SRM 53- 10-14 FIG 201. MAJOR REPAIR IAW GMM 6-2-100.

Part: STRINGER — CORRODED (FRAME 62) · corrosion level 2 · airframe 50,197 hrs · 26,719 cycles

AFT CARGO STRINGER 54L FOUND CORRODED AT FRAME 62. REPAIRED IAW SRM53-10-14 FIG 201, SHEET 1. MAJOR REPAIR IAW GMM 6-2-100.

Part: FRAME — CRACKED (FRAME 40) · airframe 50,197 hrs · 26,719 cycles

LOWER HOLE OF CTR WING JOINT AT FRAME 40L HAS A CRACK SIGNAL. REPAIRED IAW EA 6-5710-T0312351 PT1. MAJOR REPAIR IAW GMM 6-2-100

Part: JACKSCREW — CONTAMINATED (TE FLAPS) · airframe 49,558 hrs · 26,445 cycles

AFTER DEPARTURE, WITH FLAPS 15/20, DURING RETRACTION, FLAP SYS 1 & SYS 2 FAULTED. FLAP HANDLE CYCLED, FLAP STUCK AT 15/20, IAW ECAM GPWS SWITCH TO OVERIDE. IAW QRH FLAP HANDLE SELECTED TO 30/40 FLAP WENT TO 30/40 FAULT LIGHTS EXTINGUISHED. AFTER LANDING FLAPS RETRACTED NORMALLY. INSPECTION FOUND LT & NR 2 FLAP SCREW JACK OIL CONTAMINATED. R & R NR 2 FLAP SCREW JACK IAW AMM27-54-22-04. ADJUSTED IAW AMM27-54-22-0 4 & PERFORMED TRACK FAIRING OPERATING RODS ADJUSTMENT IAW AMM27-50-21-04. FULLY EXTENDED & RETRACTED THE FLAPS IAW AMM27-50-00-3 FOR SEVERAL TIMES, CHECKED NORMAL. PERFORMED THE ENG RUN & OPERATED THE FLAPS FOR FULL RANGE 3 IAW AMM27-50-00-3, ALL NORMAL.

Part: SWITCH — FAILED (EMERGENCY LIGHT) · airframe 48,953 hrs · 26,230 cycles

EMERGENCY LIGHT TEST SWITCH AT DOOR 1L NOT WORKING. COURIER COMPARTMENT INTERIOR EMERGENCY LIGHTS TEST FUNCTION INOPERATIVE. CHECK FOUND THE TEST PBSW 25WL INTERMITTENT. R & R THE SWITCH IAW ESPM. PERFORMED EMERGENCY LIGHT TEST IAW AMM 33-51-00-05-09,TEST NORMAL.

Part: FMC — FAILED (NR 2) · airframe 47,499 hrs · 25,728 cycles

AFTER LEVEL OFF AT 9800 M, LOST NR 2 FMC COMPLETELY. FMC UNAVAILABLE MESSAGE SHOWED ON NR 2 FMC CDU. TROUBLESHOT IAW TSM34-60-00/P107, R & R NR 2 FMC IAW AMM34-68-34-04, CROSSLOADED FMC DATABASE IAW AMM 34-60-00-03-09. PERFORMED FMS OPS TEST SATIS IAW AMM34-68-34-04.

Part: SKIN — DENTED (LT WING NR 1) · airframe 47,197 hrs · 25,635 cycles

LEFT WING NR 1 SLAT LIP SKIN FOUND WITH TWO DENTS NEAR FASTENER. REPAIRED IAW SRM 51-73-10, PAR 3B.

Part: CASCADE — DAMAGED (THRUST REVERSER) · airframe 47,197 hrs · 25,635 cycles

RT ENGINE OUTBOARD THRUST REVERSER COWL CASCADE BROKEN & MISSING AT 1 O`CLOCK. REPLACED COWL CASCADE PER AMM78-32-12-04. PERFORMED AN OPS TEST OF RT THRUST REVERSER PER AMM78-32-11-05, TEST PASSED.

Part: SPAR — CRACKED (LT WING) · airframe 44,292 hrs · 24,278 cycles

ULTRASONIC INSP CARRIED OUT ON LT WING, FOUND ULTRASONIC INDICATION MORE THAN 30 PERCENT ON THE HOLE 'B' AT REAR SPAR UPPER CHORD OTBD OF RIB 9. REPAIRED AS PER E.A. 6-5730-150317 PART 1. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REVISION 112.

Part: SPAR CAP — CRACKED (WING) · airframe 44,292 hrs · 24,278 cycles

CRACK INDICATION FOUND DURING HIGH FREQUENCY EDDY CURRENT OPEN HOLE INSPECTION ON THE CTR WING BOX CTR SPAR, AT RT CUT-OUT DOUBLE RUN OUT LT UPPER HOLE SECOND LAYER AT 12 O' CLOCK POSITION LOOKING FORWARD. REPAIRED AS PER EA 6-5710-150318 PART 1. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REVISION 112.

Part: SPAR CAP — CRACKED (WING) · airframe 44,292 hrs · 24,278 cycles

CRACK INDICATION FOUND DURING HIGH FREQUENCY EDDY CURRENT OPEN HOLE INSP ON THE CTR WING BOX CTR SPAR, AT LT CUT-OUT DOUBLE RUN OUT RT UPPER HOLE SECOND LAYER AT 12 O' CLOCK POSITION LOOKING FWD. REPAIRED AS PER EA 6-5710-150318 PART 1. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REVISION 112.

Part: SKIN — DENTED (ZONE 100) · airframe 44,292 hrs · 24,278 cycles

FUSELAGE EXTERNAL SKIN BETWEEN FRAME 52 TO FRAME 53A, STRINGER 39 FOUND WITH SMALL DENT. REWORKED AND TRACKING REQUIRED AS PER EA 6-5310-149620 PART 1. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REVISION 112.

Part: SKIN — MISREPAIRED (ZONE 100) · airframe 44,292 hrs · 24,278 cycles

LT FUSELAGE SKIN BETWEEN FRAME 40 AND FRAME 41 AT STRINGER 39 TO STRINGER 40 EXTERNAL SURFACE FOUND WITH SKIN REWORKED. REWORKED AS PER EA 6-5310-149618 PART 1. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REVISION 112.

Part: SPAR CAP — CRACKED (WING) · airframe 44,292 hrs · 24,278 cycles

CRACK INDICATION FOUND DURING HIGH FREQUENCY EDDY CURRENT OPEN HOLE INSP ON THE CTR WING BOX CENTER SPAR, AT LT CUT-OUT DOUBLE RUN OUT UPPER HOLE SECOND LAYER AT 6 O' CLOCK POSITION LOOKING FWD. REPAIRED AS PER EA 6-5710-150318 PART 1. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REVISION 112.

Part: SPAR CAP — CRACKED (WING) · airframe 44,292 hrs · 24,278 cycles

CRACK INDICATION FOUND DURING HIGH FREQUENCY EDDY CURRENT OPEN HOLE INSPECTION ON THE CTR WING BOX CTR SPAR, AT RT CUT-OUT DOUBLE RUN OUT LT UPPER HOLE FIRST LAYER AT 12 O' CLOCK POSITION LOOKING FORWARD. REPAIRED AS PER EA 6-5710-150318. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REVISION 112.

Part: SPAR CAP — CRACKED (WING) · airframe 44,292 hrs · 24,278 cycles

CRACK INDICATION FOUND DURING HIGH FREQUENCY EDDY CURRENT OPEN HOLE INSPECTION ON THE CENTER WING BOX CENTER SPAR, AT RIGHT HAND CUT-OUT DOUBLER RUNOUT LEFT SIDE LOWER HOLE FIRST LAYER AT 12 O' CLOCK POSITION LOOKING FORWARD. CRACKED AT CENTER WING BOX CENTER SPAR, AT RIGHT HAND CUT-OUT DOUBLER RUNOUT LEFT HAND SIDE LOWER HOLE REPAIRED AS PER E.A. 6-5710-150318 PART 1. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REVISION 112.

Part: SPAR CAP — CRACKED (WING) · airframe 44,292 hrs · 24,278 cycles

CRACK INDICATION FOUND DURING HIGH FREQUENCY EDDY CURRENT OPEN HOLE INSPECTION ON THE CTR WING BOX CTR SPAR, AT RT CUT-OUT DOUBLE RUN OUT LT LOWER HOLE SECOND LAYER AT 12 O' CLOCK POSITION LOOKING FORWARD. REPAIRED AS PER EA 6-5710-150318 PART 1. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REVISION 112.

Part: SKIN — DENTED (ZONE 100) · airframe 44,292 hrs · 24,278 cycles

RT FUSELAGE SKIN EXTERIOR SURFACE BETWEEN FRAME 48 TO FRAME 49A AND BETWEEN STRINGER 34 TO STRINGER 36 FOUND DENTED. REPAIRED AS PER EA 6-5310-149619 PART 1. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REVISION 112.

Part: SPAR CAP — CRACKED (ZONE 100) · airframe 44,292 hrs · 24,278 cycles

CRACK INDICATION FOUND DURING HIGH FREQUENCY EDDY CURRENT OPEN HOLE INSPECTION ON THE CENTER WING BOX CENTER SPAR, AT RIGHT CUT-OUT DOUBLER RUNOUT RIGHT SIDE UPPER HOLE SECOND LAYER AT 6 O' CLOCK POSITION LOOKING FORWARD. CRACKED AT CENTER WING BOX CENTER SPAR, AT RIGHT HAND CUT-OUT DOUBLER RUNOUT RIGHT SIDE UPPER HOLE REPAIRED AS PER E.A. 6-5710-150318 PART 1. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REVISION 112.

Part: BRACKET — CRACKED (ZONE 600) · airframe 44,292 hrs · 24,278 cycles

CRACK INDICATION FOUND APPROXIMATELY 0.2 INCH IN LEGTH DURING HIGH FREQUENCY EDDY CURRENT INSPECTION ON CENTER HINGE OF RIGHT WING NR 1 SPOILER INBOARD LUG. RIGHT WING NR 1 SPOILER CENTER HINGE BRACKET REMOVED AND REPLACED AS PER EO 6-5710-7-3307 EOCN 04 PART 5. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REVISION 112.

Part: BRACKET — CRACKED (ZONE 500) · airframe 44,292 hrs · 24,278 cycles

CRACK INDICATION FOUND APPROXIMATELY 0.2 INCH IN LEGTH DURING HIGH FREQUENCY EDDY CURRENT INSPECTION ON CENTER HINGE OF LEFT WING NR 1 SPOILER OUTBOARD LUG. LEFT WING NR 1 SPOILER CENTER HINGE BRACKET REMOVED AND REPLACED AS PER EO 6-5710-7-3307 EOCN 04 PART 5. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REVISION 112.

Part: SILL — MISREPAIRED (CARGO BAY) · airframe 44,292 hrs · 24,278 cycles

REPAIR AT AFT CARGO COMPARTMENT ENTRY AREA DOOR SILL BETWEEN FRAME 62 AND FRAME 63. REPAIR EVALUATED AND FOUND FASTENERS NOT INSTALLED PER APPROVED DATA. REPAIRED AS PER E.A. 6-5310-143890 PART 1 & E.O. 6-5100-7-5000C2 PART 1. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REVISION 112.

Part: CROSSBEAM — CORRODED (ZONE 100) · corrosion level 2 · airframe 44,292 hrs · 24,278 cycles

FORWARD CARGO COMPARTMENT CROSS BEAM AT FRAME 27, Y = 40, -Z = 26 FOUND SURFACE CORROSION ALONG FASTENERS AREA. REPAIRED AS PER E.A. 6-5310-150313 PART 1. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REVISION 112.

Part: CROSSBEAM — CORRODED (CARGO BAY) · corrosion level 2 · airframe 44,292 hrs · 24,278 cycles

FORWARD CARGO COMPARTMENT CROSS BEAM AT FRAME 25, Y = 40, -Z = 26 FOUND SURFACE CORROSION ALONG FASTENERS AREA. REPAIRED AS PER E.A. 6-5310-150312 PART 1. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REVISION 112.

Part: FLOOR SUPPORT — CORRODED (ZONE 200) · corrosion level 2 · airframe 44,292 hrs · 24,278 cycles

MAIN DECK FWD UTILITY AREA, FLOOR BETWEEN FRAME 12 AND FRAME 13 LT APPROX Y700, SUPPORT STRUCTURE FOUND CORROSION. SUPPORT STRUCTURE ON MAIN DECK FORWARD UTILITY AREA FLOOR BETWEEN FRAME 12 AND FRAME 13 LEFT HAND APPROXIMATELY Y = 700, REMOVED AND REPLACED AS PER SRM 51-40-21 REVISION 75. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REVISION 112.

Part: SEAT TRACK — CORRODED (ZONE 200) · corrosion level 2 · airframe 44,292 hrs · 24,278 cycles

MAIN DECK FWD UTILITY AREA, FLOOR SEAT TRACK ALONG Y 953 BETWEEN FRAME 16 AND FRAME 19 CORROSION FOUND ON CROWN. MAIN DECK FORWARD UTILITY AREA, FLOOR SEAT TRACK ALONG Y 953 BETWEEN FRAME 16 AND FRAME 19 REMOVED AND REPLACED AS PER SRM 51-40-21 REVISION 75. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REVISION 112.

Part: SEAT TRACK — CORRODED (ZONE 200) · corrosion level 2 · airframe 44,292 hrs · 24,278 cycles

MAIN DECK FWD UTILITY AREA, SEAT TRACK ALONG Y 450 BETWEEN FRAME 16 AND FRAME 19 CORROSION FOUND ON CROWN. MAIN DECK FORWARD UTILITY AREA, SEAT TRACK ALONG Y 450 BETWEEN FRAME 16 AND FRAME 19 REMOVED AND REPLACED AS PER SRM 51-40-21 REVISION 75. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REVISION 112.

Part: SEAT TRACK — CORRODED (ZONE 200) · corrosion level 2 · airframe 44,292 hrs · 24,278 cycles

MAIN DECK FWD UTILITY AREA, FLOOR SEAT TRACK ALONG Y -450 BETWEEN FRAME 18 AND FRAME 19 CORROSION FOUND ON CROWN. MAIN DECK FORWARD UTILITY AREA, FLOOR SEAT TRACK ALONG Y -450 BETWEEN FRAME 18 AND FRAME 19 REMOVED AND REPLACED AS PER SRM 51-40-21 REVISION 75. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REVISION 112.

Part: WINDOW FRAME — CRACKED (ZONE 200) · airframe 44,292 hrs · 24,278 cycles

ONE CRACK FOUND ON LEFT FUSELAGE INTERNAL STRUCTURE FROM FRAME 2 TO 4 WINDSHIELD FRAME LOWER SECTION AT FASTENER HOLE NR 10 AFT SIDE DURING EDDY CURRENT ROTATING PROBE TEST PER NTM53-11-01. LEFT FUSELAGE INTERNAL STRUCTURE FROM FRAME 2 TO 4 WINDSHIELD FRAME LOWER SECTION AT FASTENER HOLE NR 10 REPAIRED AS PER E.A. 6-5310-150316 PART 1, REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REVISION 112.

Part: MOUNT — CORRODED (ZONE 400) · airframe 44,292 hrs · 24,278 cycles

NR 2 PYLON ENG AFT MOUNT LT FWD BOLT HOLE FOUND WITH CORROSION. REWORKED AS PER E.A. 6-5450-143900 PART 1. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REVISION 112.

Part: MOUNT — CORRODED (NR 2 ENGINE) · airframe 44,292 hrs · 24,278 cycles

NR 2 PYLON ENGINE AFT MOUNT LT AFT BOLT HOLE FOUND WITH CORROSION. REWORKED AS PER E.A. 6-5450-143900 PART 1. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REVISION 112.

Part: MOUNT — CORRODED (ZONE 400) · airframe 44,292 hrs · 24,278 cycles

NR 2 PYLON ENGINE FWD MOUNT LT AFT BOLT HOLE FOUND WITH CORROSION. REPAIRED AS PER E.A. 6-5450-150314 PART 1. REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100 REVISION 112.

Part: MOUNT — CORRODED (ZONE 400) · airframe 44,292 hrs · 24,278 cycles

NR 2 PYLON ENGINE FWD MOUNT LT FWD BOLT HOLE FOUND WITH CORROSION. REPAIRED AS PER E.A. 6-5450-150314 PART 1. REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100 REVISION 112.

Part: FRAME — CRACKED (ZONE 100) · airframe 44,292 hrs · 24,278 cycles

DURING ACCOMPLISHMENT OF WORK CARD E6-5310-7-5013C PART 1, FUSELAGE FRAME NR 47 LT RADIUS FITTING FOUND CRACKED. REPAIRED AS PER E.O. 6-5310-7-5013C PART 1 &, SERVICE BULLITINS A300-53-6029 R08 AND A300-53-6144 R01. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REVISION 112. REPETITIVE INSPECTION REQUIRED PER E.O. 6-5310-7-5013C PART 1.

Part: STIFFENER — CRACKED (ZONE 400) · airframe 44,292 hrs · 24,278 cycles

PYLON NR 2, STIFFENER END BETWEEN RIB 6 AND RIB 7 FOUND CRACKED INDICATION APPROX 0.1 INCH DURING HIGH FREQUENCY EDDY CURRENT INSP. REPAIRED AS PER E.A. 6-5450-150310 PART 1. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REVISION 112.

Part: SKIN — MISREPAIRED (ZONE 100) · airframe 44,292 hrs · 24,278 cycles

REPAIR DOUBLER FOUND AT FUSELAGE BELLY SKIN NEAR JACKPAD FRAME 87, STR 45. EVALUATED AND FOUND NOT INACCORDANCE WITH ANY REPAIR DATA. CARRIED OUT REPAIR AS PER SRM 53-10-12 FIGURE 225 REVISION 75. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REVISION 112.

Part: FITTING — CRACKED (ZONE 200) · airframe 44,292 hrs · 24,278 cycles

DURING OPEN HOLE HIGH FREQUENCY EDDY CURRENT INSP ON FRAME 47 SPLICE FITTING BETWEEN STRINGER 24 AND STRINGER 26 IAW SB A300-53-6123R04, HOLE 'J' FOUND CRACKED. REPAIRED CARRIED OUT AS PER EO 6-5310-7-5017 A5 PART 5, REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REVISION 112. REPETITIVE INSPECTION REQUIRED AS PER EO 6-5310-7-5017 A5 PART 5.

Part: FITTING — CRACKED (ZONE 200) · airframe 44,292 hrs · 24,278 cycles

DURING OPEN HOLE HIGH FREQUENCY EDDY CURRENT INSP ON FRAME 47 SPLICE FITTING BETWEEN STRINGER 24 AND STRINGER 26 IAW SB A300-53-6123R04, HOLE 'F' FOUND CRACKED. REPAIRED CARRIED OUT AS PER EO 6-5310-7-5017 A5 PART 5, REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 REVISION 112. REPETITIVE INSPECTION REQUIRED AS PER EO 6-5310-7-5017 A5 PART 5.

Part: DOOR — MISSING (MLG) · airframe 42,144 hrs · 23,109 cycles

ACFT ARRIVED, MISSING MLG DOOR FAIRING. RELEASED FOR SERVICE IAW CDL: 52-13 CATEGORY: N CDL ITEM "CDL 52-13: MLG DOOR PANEL 732 - MISSING. REFER TO CDL 52-13 FOR RESTRICTIONS. ACFT RESTRICTED FROM OPERATING INTO KNOWN OR FORECAST ICING CONDITIONS."

Part: SKIN — CORRODED (AFT CARGO DOOR) · corrosion level 2 · airframe 40,987 hrs · 22,509 cycles

AFT CARGO DOOR INTERNAL SKIN CORRODED AT FWD LWR CORNER. THIS SDR IS GEN TO REFLECT CORRECTIONS MADE IN CORRECTIVE ACTION BLOCK FROM ORIG SDR 08-4756. REMOVED CORROSION IAW A300-600 SRM 51-74-10. FOUND TO BE OUT OF LIMITS IAW A300-600 SRM 51-30-00. ORIGINAL MATERIAL 0.063. REMAINING MATERIAL 0.051. MATERIAL REMOVED 0.011. USED UT GAUGE T8225Q. REMOVED AND RE-INSTALLED PANELS 812 AR AND BR; 154 AR; BR; CR IAW A300-600 AMM 52-72-11-5. REMOVED AND RE-INSTALLED SEAL RETAINER IAW A300-600 AMM 52-30-18-4. REMOVED AND REINSTALLED CAPS AND INSTALLED NEW SKIN IAW A300-600 SRM 51-72-10. MATERIAL ID 2024-T3, 0.063, PO 633758.6 IAW A300-600 SRM 52-32-00. ALODINED IAW A300-600 SRM 51-21-10. PRIMED IAW A300-600 SRM 51-23-10. REMOVED AND RE-INSTALLED NR 1; NR 7 AND NR 8 DOOR STOPS. .

Part: FITTING — CRACKED (LT WING) · airframe 40,987 hrs · 22,509 cycles

LEFT WING HOLE " D " OF EO 6-5710-7-5005 P1 SHOWS A CRACK INDICATION APPROX 1/16 LONG. COMPLIED WITH FEDEX EA 6-5710-123673, WINGS - AD 99-16-01 - EO 6-5710-7-5005 - LT WING REAR SPAR, MLG FWD PICK-UP FITTING BOLT HOLE "D".

Part: RIB — DAMAGED (RT WING) · airframe 40,987 hrs · 22,509 cycles

RIGHT WING RIB 5; HOLE "E", THE EXISTING HOLE SIZE IS LARGER THAN THE FINAL HOLE SIZE CALLED OUT IN FEDEX EO 6-5710-7-5005 P1. COMPLIED WITH FEDEX EA 6-5710-123672, WINGS - AD 99-16-01 - EO 6-5710-7-5005, RT WING REAR SPAR MLG FWD PICK-UP FITTING BOLT "E".

Part: RIB — CRACKED (LT WING) · airframe 40,987 hrs · 22,509 cycles

LEFT WING RIB 5; HOLE "I" HAS A CRACK INDICATION. COMPLIED WITH FEDEX EA 6-5710-123674 WINGS, AD 99-16-01 - EO 6-5710-7-5005, LT WING REAR SPAR, RIB 5 FITTING BOLT HOLE "G", "I", "M", AND "O". ORIGINAL EA ATTACHED TO SNRM N00846.

Part: RIB — CRACKED (LT WING) · airframe 40,987 hrs · 22,509 cycles

LEFT WING RIB 5; HOLE "O" HAS A CRACK INDICATION. COMPLIED WITH FEDEX EA 6-5710-123674, WINGS, AD 99-16-01 - EO 6-5710-7-5005, LT WING REAR SPAR, RIB 5 FITTING BOLT HOLE "G", "I", "M", AND "O".

Part: FITTING — CRACKED (RT WING) · airframe 40,987 hrs · 22,509 cycles

RIGHT WING RIB 5; HOLE "L" SHOWS A CRACK INDICATION APPROX , WINGS - AD 99-16-01 EO 6-5710-7-5005-RT WING REAR SPAR, RIB 5 FITTING BOLT HOLE "L".

Part: RIB — CRACKED (LT WING) · airframe 40,987 hrs · 22,509 cycles

LEFT WING RIB 5; HOLE "M" HAS A CRACK INDICATION. COMPLIED WITH FEDEX EA 6-5710-123674, WINGS - AD 99-16-01 - E.O. 6-5710-7-5005, LT WING REAR SPAR, RIB 5 FITTING BOLT HOLE "G", "I", "M" AND "O". ORGINAL EA IS ATTACHED TO SNRM N00846.

Part: RIB — CRACKED (LT WING) · airframe 40,987 hrs · 22,509 cycles

LEFT WING RIB 5; HOLE "G" HAS A CRACK INDICATION. COMPLIED WITH FEDEX EA 6-5710-123674 WINGS - AD 99-16-01 - EO 6-5710-7-5005 - LT WING REAR SPAR, RIB 5 FITTING BOLT HOLE "G", "I", "M", AND "O". ORIGINAL EA ATTACHED TO SNRM N00846.

Part: SKIN — CRACKED (ZONE 600) · airframe 40,987 hrs · 22,509 cycles

RT WING LWR SKIN CRACKED APPROX 3/16 INCH BEYOND PREVIOUS STOP PLUG REPAIR. CRACK IS PROGRESSING AFT TOWARD FASTENER HOLE NR 19 AND TRANSITION RADIUS BETWEEN RIBS 8 AND 9. COMPLIED WITH EA 6-5730-123509 PART 1, WINGS CRACK IN RT BOTTOM SKIN AT FRONT SPAR, 632BB RIB 8 - 9 REPAIR.

Part: SKIN — CRACKED (TE FLAP) · airframe 40,987 hrs · 22,509 cycles

LT WING INBD FLAP AT RIB 25A, UPPER SKIN IS CRACKED. FABRICARED SKIN P/N A57960007200 & DOUBLER P/N A57960007202 IN REF TO FEDEX EA 6-5750-123671.

Part: SKIN — CORRODED (CARGO DOOR) · corrosion level 2 · airframe 40,987 hrs · 22,509 cycles

AFT CARGO DOOR INTERIOR SKIN IS CORRODED AT THE AFT LOWER CORNER. REMOVED CORROSION IAW SRM 51-74-01. FOUND TO BE OUT OF LIMITS IAW SRM 52-30-00. ORIGINAL MATERIAL 0.063. REMAINING MATERIAL 0.052. MATERIAL REMOVED 0.011. THE SKIN WAS REPLACED ON WORK CARD N00380.

Part: FLOOR PANEL — DELAMINATED (FUSELAGE) · airframe 40,987 hrs · 22,509 cycles

BULK PIT FLOOR PANEL IS DELAMINATED. REMOVED PANEL IAW AMM 53-10-35-4. FABRICATED NEW PANEL IAW DWG SRZ 25-005. FABRICATED TOP SHEET IAW DWG SRZ 25-011. PART MARKED IAW GMM 7-0-1000. INSTALLED PANEL IAW AMM 53-10-35-4.

Part: FLOOR PANEL — PUNCTURED (FUSELAGE) · airframe 40,987 hrs · 22,509 cycles

BULK CARGO FLOOR PANEL DELAMINATED AND PUNCTURED. REMOVED PANEL IAW AMM 53-10-35-4. FABRICATED NEW PANEL. FABRICATED IAW DWG SRZ 25-005. PART MARKED IAW GMM 7-0-1000. INSTALLED PANEL IAW AMM 53-10-35-1.

Part: FLOOR PANEL — DELAMINATED (FUSELAGE) · airframe 40,987 hrs · 22,509 cycles

BULK CARGO FLOOR PANEL IS DELAMINATED. REMOVED PANEL IAW AMM 53-10-35-4. FABRICATED NEW PANEL. FABRICATED TOP SHEET IAW DWG SRZ 25-011. PART MARKED IAW GMM 7-0-1000. INSTALLED PANEL IAW AMM 53-10-35-4.

Part: FLOOR PANEL — DELAMINATED (FUSELAGE) · airframe 40,987 hrs · 22,509 cycles

BULK CARGO FLOOR PANEL IS DELAMINATED. REMOVED PANEL IAW AMM 53-10-35-4. FABRICATED NEW PANEL IAW DWG SRZ 25-005. FABRICATED TOP SHEET IAW DWG SRZ 25-011. PART MARKED IAW GMM 7-0-1000. INSTALLED PANEL IAW AMM 53-10-35-4.

Part: FLOOR PANEL — DELAMINATED (FUSELAGE) · airframe 40,987 hrs · 22,509 cycles

BULK PIT FLOOR PANEL IS DELAMINATED. REMOVED PANEL IAW AMM 53-10-35-4. FABRICATED NEW PANEL IAW FEDEX DWG SRZ 25-005. FABRICATED TOP SHEET IAW DWG SRZ 25-011. PART MARKED IAW GMM 7-0-1000. INSTALLED PANEL IAW AMM 53-10-35-4.

Part: FLOOR PANEL — DELAMINATED (FUSELAGE) · airframe 40,987 hrs · 22,509 cycles

BULK CARGO FLOOR PANEL IS DELAMINATED. REMOVED PANEL IAW AMM 53-10-35-4. FABRICATED NEW PANEL. FABRICATED TOP SHEET IAW DWG SRZ 25-011. PART MARKED IAW GMM 7-0-1000. INSTALLED PANEL IAW AMM 53-10-35-4.

Part: FLOOR PANEL — DELAMINATED (FUSELAGE) · airframe 40,987 hrs · 22,509 cycles

BULK CARGO FLOOR PANEL IS DELAMINATED. REMOVED PANEL IAW AMM 53-10-35-4. FABRICATED NEW PANEL. FABRICATED TOP SHEET IAW DWG SRZ 25-011. PART MARKED IAW GMM 7-0-1000. INSTALLED PANEL IAW AMM 53-10-35-4.

Part: FLOOR PANEL — DELAMINATED (FUSELAGE) · airframe 40,987 hrs · 22,509 cycles

BULK CARGO FLOOR PANEL IS DELAMINATED AND PUNCTURES. REMOVED PANEL IAW AMM 53-10-35-4. FABRICATED A NEW PANEL IAW FEDEX DWG SRZ 25-005. PART MARKED IAW GMM 7-0-1000.

Part: FLOOR PANEL — DELAMINATED (FUSELAGE) · airframe 40,987 hrs · 22,509 cycles

BULK CARGO FLOOR PANEL IS DELAMINATED. REMOVED PANEL IAW AMM 53-10-35-4. FABRICATED NEW PANEL. FABRICATED TOP SHEET IAW DWG SRZ 25-011. PART MARKED IAW GMM 7-0-1000. INSTALLED PANEL 161 BF IAW AMM 53-10-35-4.

Part: WEB — CRACKED (ZONE 500) · airframe 40,987 hrs · 22,509 cycles

LEFT WING INBD FLAP AT RIB 25A THE WEB PLATE IS CRACKED. REMOVED AND REPLACED -218 WEB PLATE IN REF TO A300-600 SRM 51-40-21, PARA 7, PARA 14 AND FOKKER DWG A57960114, ISSUE E.

Part: WEB — CRACKED (ZONE 500) · airframe 40,987 hrs · 22,509 cycles

LEFT WING INBD FLAP AT RIB 25A, WEB PLATE IS CRACKED. REMOVED AND REPLACED THE -220 WEB PLATE IN REF TO A300-600 SRM 51-40-21; PARA 7; PARA 14 AND FOKKER DWG A57960114, ISSUE E.

Part: WEB — DAMAGED (LT WING TE FLAP) · airframe 40,987 hrs · 22,509 cycles

LEFT WING INBD FLAP AT RIB 25A, WEB PLATE IS CRACKED AND MISDRILLED. REMOVED & REPLACED THE WEB PLATE IN REF TO SRM 51-40-21& DWG A57960114.

Part: CARRIAGE — CORRODED (LT WING TE FLAP) · corrosion level 2 · airframe 40,987 hrs · 22,509 cycles

LEFT WING CENTER FLAP NR 3 TRACK CARRIAGE UPPER FLANGE ASSY IS CORRODED AT THE LUGS. REMOVED AND REPLACED THE LEFT NR 3 FLAP TRACK FWD CARRIAGE UPPER BRIDGE REF A300-600 AMM 27-54-27-4.

Part: STRUCTURE — CRACKED (THRUST REVERSER) · airframe 40,987 hrs · 22,509 cycles

NR 2 ENGINE INBD T/R, CORE COWL SECTION HAS A CRACK AT THE AFT UPPER SECTION ABOVE THE LOCK HANDLE. MATERIAL ID PER P/W CMM 78-32-34, 0.050, PO 607468.1. HEAT TREAT IAW TPS 1003; REV "A" (HT102408.2). STOP DRILL THE CRACK TO 0.0625 PER P/W CMM 78-32-34. LOCATED, DRILLED AND INSTALLED SPLICE PLATE PER P/W CMM 78-32-34. ALODINED AND PRIMED PER P/W SRM 54-02-03.

Part: ATTACH FITTING — CRACKED (FUSELAGE) · airframe 40,987 hrs · 22,509 cycles

THE 3RD LEFT SEAT TRACK INBD TRACK SUPPORT IS CRACKED AT FRAME 49. REMOVED & REPLACED THE TRACK LINK FITTING IN REF TO SRM 51-40-21. APPLIED TOP COAT IN REF TO SRM 51-73-10.

Part: ATTACH FITTING — CRACKED (FUSELAGE) · airframe 40,987 hrs · 22,509 cycles

THE 3RD LEFT SEAT TRACK INBD TRACK SUPPORT IS CRACKED AT FRAME 48. REMOVED & REPLACED THE TRACK LINK FITTING IN REF TO SRM 51-40-21. APPLIED TOP COAT IN REF TO SRM 51-23-10.

Part: ATTACH FITTING — CRACKED (FUSELAGE) · airframe 40,987 hrs · 22,509 cycles

THE 3RD LEFT SEAT TRACK INBD TRACK SUPPORT LINK IS CRACKED AT FRAME 48. REMOVED & REPLACED THE TRACK LINK FITTING IN REF TO SRM 51-40-21. APPLIED TOP COAT IN REF TO SRM 51-73-10.

Part: SKIN — GOUGED (RT WING TE FLAP) · airframe 40,987 hrs · 22,509 cycles

RIGHT OUTBD FLAP L/E INBD END IS GOUGED IN THE EXTERNAL SKIN.

Part: FRAME — GOUGED (FUSELAGE) · airframe 40,987 hrs · 22,509 cycles

MAIN CABIN FRAME 33 IS GOUGED AT APPROXIMATELY LONGERON 15 L.

Part: SUPPORT — CRACKED (NR 1 PYLON) · airframe 40,987 hrs · 22,509 cycles

NR 1 PYLON INBD SIDE PANEL SUPPORT IS CRACKED AT RIB 8A, (PANEL 414CR). REMOVED & REPLACED PYLON SIDE PANEL SUPPORT REF SRM 51-40-21. LOCATED & DRILLED FASTENER HOLES IN THE NEW PYLON SIDE PANEL SUPPORT REF SRM 51-40-44.

Part: SKIN — GOUGED (ZONE 500) · airframe 40,987 hrs · 22,509 cycles

LEFT OUTBD FLAP L/E IS GOUGED AT THE INBD END OF THE FLAP. BLENDED GOUGE SMOOTH IAW SRM 51-73-10. LT WING OUTBD FLAP LE NOSE SKIN BETWEEN RIB NR 1 & 2 FOUND TO BE OUT OF LIMITS IAW SRM 57-50-00. FABBED & INSTALLED OUTBD FLAP LE REPAIR IAW SRM 57-50-00. TOP COAT PAINTED IAW SRM 51-23-10.

Part: SKIN — CORRODED (CARGO DOOR) · airframe 40,987 hrs · 22,509 cycles

AFT CARGO DOOR INTERNAL SKIN IS CORRODED AT THE FWD LOWER CORNER. REMOVED CORROSION IAW A300-600 SRM 51-74-10. FOUND TO BE OUT OF LIMITS IAW A300-600 SRM 51-30-00. ORIGINAL MATERIAL 0.063. REMAINING MATERIAL 0.051. MATERIAL REMOVED 0.011. USED UT GAUGE T8225Q. REMOVED & RE-INSTALLED PANELS 812 AR & BR 154 AR, BR, CR IAW A300-600 AMM 52-72-11-5. REMOVED & RE-INSTALLED SEAL RETAINER IAW A300-600 AMM 52-30-18-4. REMOVED & RE-INSTALLED CAPS & SKIN IAW A300-600 SRM 51-72-10. MATERIAL ID 2024-T3, 0.063, PO 633758.6 IAW A300-600 SRM 52-32-00. ALODINED IAW A300-600 SRM 51-21-10. PRIMED IAW A300-600 SRM 51-23-10. REMOVED & RE-INSTALLED NR 1; NR 7 & NR 8 DOOR STOPS.

Part: CUSP WEB — CRACKED (FUSELAGE) · airframe 40,987 hrs · 22,509 cycles

MAIN CARGO DECK LT CUSP 4 INCHES AFT OF FRAME 79, WEB IS BENT & CRACKED. REMOVED CRACKED WEB IAW SRM 51-40-21 & INSTALLED NEW WEB IAW DWG NR A53981113.

Part: SKIN — GOUGED (LT WING TE FLAP) · airframe 40,987 hrs · 22,509 cycles

LEFT CENTER FLAP L/E HAS A GOUGE IN THE EXTERNAL SURFACE LOCATED APPROX MIDWAY BETWEEN NR 3 & 4 FLAP TRACKS. REPAIRED LEFT CENTER FLAP L/E FROM RIB 16 TO RIB 17 IAW SRM 57-50-00.

Part: CUSP WEB — CRACKED (FUSELAGE) · airframe 40,987 hrs · 22,509 cycles

MAIN CARGO DECK RT CUSP 4 INCHES AFT OF FRAME 79, WEB IS CRACKED. REMOVED CRACKED WEB IAW SRM 51-40-21 & INSTALLED A NEW WEB IAW SRM 51-40-21 & DWG A53981113.

Part: FRAME — CRACKED (HORIZONTAL STAB) · airframe 40,987 hrs · 22,509 cycles

LEFT HORIZONTAL STAB L / E PANEL 341 AB OUTBD BOTTOM FORMER IN CRACKED. STOP DRILLED THE CRACK IAW SRM 51-23-10. HFEC STOP DRILL PER NTW 51-10-08. VERIFIED THE CRACK STOPS. FABRICATED & INSTALLED REPAIR ANGLES IAW SRM 55-12-19.

Part: STIFFENER — CRACKED (RT WING) · airframe 40,987 hrs · 22,509 cycles

RIGHT WING AILERON ACTUATOR BEAM STIFFENER IS CRACKED JUST OUTBD OF RIB 6A INSIDE PANEL 675 BB. REMOVED & REPLACED STIFFENER IAW SRM 51-40-21; PARA 5 & 7 AND DWG 25A57246859.

Part: STIFFENER — CRACKED (LT WING) · airframe 40,987 hrs · 22,509 cycles

LEFT WING AILERON ACTUATOR BEAM STIFFENER IS CRACKED JUST OUTBD OF RIB 6A. REMOVED LEFT WING AILERON ACTUATOR BEAM UPPER ATTACH STIFFENER JUST OUTBD OF RIB 6A IAW A300-600 SRM 51-40-21. FABRICATED A NEW STIFFENER IAW FEDEX EA 6-5720-123668. LEFT WING AILERON ACTUATOR SUPPORT BEAM. INSTALLED NEW STIFFENER IAW A300-600 SRM 51-40-21.

Part: COMPUTER — FAULTED (NR 2) · airframe 39,140 hrs · 21,493 cycles

ATB - AFTER T/O - ECAM AND OVH SYS 2 FLAP FAULT. UNABLE TO CLEAR FAULT. FOUND NR 2 SFCC FAULTING MAIN CONTROL VALVE UPON ARRIVAL. RESET SFCC AND RAN FLAPS, AGAIN FAULTED MAIN CONTROL VALVE. BOTH TIMES NR 2 FLAP SYS FAULT LIGHT ON OVERHEAD CAME ON AND WOULD NOT RESET. SWAPPED NR 2 AND NR 1 SFCC AND RAN FLAPS. FLAP SYS NR 1 BEGAN FAULTING. PUT BOXES BACK IN ORIGINAL POSITION. PLACING BOX ON ORDER. RAN NR 2 ENG AND TIMED FLAPS WITH NR 2 SFCC BREAKERS PULLED PER AMM 27-54-00-5. ALL TIMES WERE WITHIN LIMITS AND FLAPS MOVED SYMMETRICALLY ON SYSTEM NR 1. REPLACED NR 2 SFCC FLAP/SLAT SYSTEM TEST OK PER MM 27-51-18-4 27-51-00-5.

Part: SKIN — DAMAGED (LT WING) · airframe 38,062 hrs · 20,915 cycles

LEFT WING LOWER SURFACE PANEL 550NB PANEL LAND HAS ONE EA DRILL START NEXT TO HOLE COMPLIED WITH EA 6-5730-104975, OPENED HOLE TO 0.402, COLD WORKED AND FINAL REAMED TO 0.418. FABBED AND INSTALLED BUSHING AND DRILLED NEW HOLE IAW TD/J1/S1/03541/2006.

Part: WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 38,062 hrs · 20,915 cycles

FWD CARGO WEB, BETWEEN FRAMES 38 - 38.1 AT STR 43 LT CORRODED FWD AND AFT CORNERS. REMOVED AND REINSTALLED DUCT AFTER WEB REPAIR IAW A300-600 AMM 36-12-00-4. REMOVED CORROSION AND FOUND A 4" CRACK IN WEB IAW NTM 51-10-08. REMOVED AND REPLACED WEB IAW SRM 51-40-21.

Part: PLATE — CRACKED (HORIZ STAB) · airframe 38,062 hrs · 20,915 cycles

RT HORIZONTAL STAB COMPARTMENT BETWEEN FS 87 AND 86 WEB AT STR 36R IS DENTED AND CRACKED. REMOVED AND REPLACED PLATE AND L-SECTION AT RT HORIZONTAL STAB COMPARTMENT BETWEEN FS 87 AND 86 AT STR 36R IAW A300-600 SRM 51-72-10.

Part: TRACK — MISREPAIRED (CARGO BAY) · airframe 38,062 hrs · 20,915 cycles

AFT CARGO COMP, L/R ROLLER TRACK NR 3 BETWEEN FS 62-63 HAS PREVIOUS REPAIR, 2 SPLICES ANGLE DOUBLER AT BOTTOM W/APPROX MEASUREMENTS 18 BY 2". PREVIOUSLY INSTALLED REPAIR LOCATED AT AFT CARGO LT SIDE ROLLER TRACK NR 3 BETWEEN FS 62-63 WAS DETERMINED NOT TO BE IAW A300-600 SRM 53-10-15 FIG 203 DUE TO INCORRECT REPAIR ANGLE SHAPES, FASTENER PITCH AND REPAIR DOUBLER ON WRONG SIDE OFTRACK, BASED ON VISUAL EVALUATION WITH THE REPAIR INSTALLED. REMOVED EXISTING ROLLER TRACK REPAIR, CUT AND SPLICED IN A 42" SECTION OF ROLLER TRACK PER A300-600 SRM 53-10-15 FIG 203.

Part: SHEAR PLATE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 38,062 hrs · 20,915 cycles

WEB CORRODED IN FWD CARGO BETWEEN FS 38.1 TO 38.2 AT STR 43L, REMOVED AND REPLACED SHEAR PLATE IAW A300-600 SRM 51-72-10.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 38,062 hrs · 20,915 cycles

BULK CARGO FRAME 67 LEFT SIDE FLOOR LEVEL FLOOR BOARD SUPPORT HAS 2 EACH AREAS OF CORROSION AROUND TIE DOWN ADAPTER. CORROSION FOUND TO BE OUT OF LIMITS, REMOVED AND REPLACED FLOOR SUPPORT IAW A300-600 SRM 53-10-15.

Part: STRUCTURE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 38,062 hrs · 20,915 cycles

BULK CARGO COMPT UNDER FLOOR STRUCTURE BETWEEN FS 63 AND 64 AT STR 54 HAS CORROSION UNDER NUTPLATE. REMOVED AND REPLACED PROFILE LONGITUDINAL IAW A300-600 SRM 51-40-21.

Part: CROSSBEAM — MISREPAIRED (FUSELAGE) · airframe 38,062 hrs · 20,915 cycles

BULK CARGO FLOOR STRUCTURE CROSS BEAM FS 64 RT SIDE MID HAS PREVIOUS REPAIR 2 EACH SPLICES ANGLE DOUBLER WITH APPROX MEASUREMENTS OF 2X9". PREVIOUS INSTALLED REPAIR LOCATED AT BULK CARGO FLOOR STRUCTURE CROSS BEAM FRAME 64 RIGHT SIDE MID, WAS DETERMINED THAT THE TWO REPAIR ANGLE SPLICES WERE MADE OF INCORRECT MATERIAL PER A300-600 SRM 53-10-15 FIG 207. REMOVED THE REPAIR ANGLES, FABRICATED NEW REPAIR ANGLES AND REPAIRED CROSS BEAM PER A300-600 SRM 53-10-15 FIG 207. THIS REPAIR IS CORRECT BASED ON THE CORRECT LOCATION, SHAPE, SIZE, FASTENER SPACING, EDGE MARGIN, NUMBER, MATERIAL THICKNESS AND TYPE AND GENERAL WORKMANSHIP OF PREVIOUS INSTALLATION.

Part: BEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 38,062 hrs · 20,915 cycles

AFT CARGO UNDER FLOOR AT FS 60 UNDER ROLLER TRACK NR 1 HAS EXFOLIATING CORROSION ON FWD AND AFT SIDE OF THE SUPPORT STRUCTURE REMOVED AND REPLACED BEAM ASSY IAW A300-600 SRM 53-10-15.

Part: PLATE — DAMAGED (CARGO DOOR) · airframe 38,062 hrs · 20,915 cycles

FWD CARGO DOOR, FWD LOWER CORNER DENTED AND GOUGED. REMOVED AND REPLACED CORNER PLATE IAW A300-600 SRM 51-40-21 AND 51-72-10.

Part: WEB — DAMAGED (FUSELAGE) · airframe 38,062 hrs · 20,915 cycles

WEB CRACKED AND PUNTURED JUST AFT OF CLS BEAR CLAW AT FS 37 REMOVED AND REPLACED WEB IAW A300-600 SRM 51-72-10.

Part: SHEAR PLATE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 38,062 hrs · 20,915 cycles

FWD CARGO PIT, WEB CORRODED BETWEEN FRAME 36 AND 37 AT STR 43 RT FWD AND AFT LOWER CORNERS. REMOVED AND REPLACED SHEAR PLATE BETWEEN FRAME 36 AND 37 AT STR 43 RT IAW A300-600 SRM 51-72-10.

Part: ANGLE — CRACKED (FUSELAGE) · airframe 38,062 hrs · 20,915 cycles

AVIONICS COMPARTMENT ZONE 122, MAIN CABIN FLOOR CROSS BEAM RIB 10 RT SIDE HAS CRACKED FITTING. REMOVED AND REPLACED ANGLE ON MAIN CARGO FLOOR CROSS BEAM AT RIB 10 IAW A300-600 SRM 51-72-10.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 38,062 hrs · 20,915 cycles

BULK CARGO FRAME 67 FLOOR LEVEL CENTERLINE, 1 AREA OF CORROSION ON THE FLOORBEAM. REMOVED CORROSION, MATERIAL LOSS FOUND TO BE OUT OF LIMITS IAW A300-600 SRM 53-10-00 FIG 104, TABLE 108. REMOVED FLOORBEAM AT FS 67, FABBED AND INSTALLED NEW FLOORBEAM IAW A300-600 SRM 53-10-15 FIG 207.

Part: STRUCTURE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 38,062 hrs · 20,915 cycles

AFT CARGO COMP UNDER FLOOR SUPPORT STRUCTURE AT FS 56 UNDER ROLLER TRACK NR 1 HAS EXFOLIATING CORROSION ON THE AFT SIDE. REPLACED AFT CARGO UNDER FLOOR SUPPORT STRUCTURE AT FS 56 UNDER ROLLER TRACK NR 1 IAW A300-600 SRM 53-10-15 FIG 207.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 38,062 hrs · 20,915 cycles

BULK CARGO COMP UNDER FLOOR STRUCTURE AT FRAME 67 BETWEEN STR 44 AND 48 HAS EXFOLIATION CORROSION, RT SIDE. REMOVED AND REPLACED FLOORBEAM AT FRAME 67 BETWEEN STR 44R AND STR 44L IAW A300-600 SRM 53-10-15.

Part: CROSSBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 38,062 hrs · 20,915 cycles

CORROSION ON CROSS BEAM AT FRAME 16 BETWEEN SEAT TRACK 4R AND 5R IN UPPER MAIN DECK CARGO COMP ZONE 220. REMOVED AND REPLACED FLANGE DUE TO CORROSION BLENDED OUT OF LIMITS IAW A300-600 SRM 51-74-10, 53-21-15, AND 51-72-10.

Part: FLOORBEAM — MISREPAIRED (FUSELAGE) · airframe 38,062 hrs · 20,915 cycles

AFT CARGO COMP FLOOR CROSSBEAM FS 63 LT SIDE BETWEEN LT ROLLER TRACK 2-3, HAS PREVIOUS REPAIR 2 EACH SPLICES ANGLE DOUBLER WITH APPROX MEASUREMENTS 9 BY 2.75". REPAIR WAS FOUND TO BE INCORRECT PER A300-600 SRM 53-10-15 FIG 207, SPLICES ARE MADE OF INCORRECT MATERIAL. REMOVED 2 EACH REPAIR SPLICES, FABRICATED NEW REPAIR ANGLE SPLICES AND REPAIRED FLOOR CROSS BEAM PER A300-600 SRM 53-10-15 FIG 207. THIS REPAIR IS CORRECT BASED ON CORRECT LOCATION, SHAPE, SIZE, FASTENER SPACING, NUMBER, MATERIAL THICKNESS, MATERIAL TYPE AND GENERAL WORKMANSHIP OF PREVIOUS INSTALLATION.

Part: TRACK — MISREPAIRED (FUSELAGE) · airframe 38,062 hrs · 20,915 cycles

FWD CARGO COMP LT ROLLER TRACK NR 2 BETWEEN FRAME 38.1 TO 38.2 HAS PREVIOUS REPAIR, A FLAT DOUBLER INSIDE ROLLER TRACK COVERING THE DRAIN PORT WITH APPROX MEASUREMENTS 8X4". THIS REPAIR AT FWD CARGO LT SIDE ROLLER TRACK NR 2 BETWEEN FS 38.1 TO 38.2 WAS FOUND NOT TO BE IAW A300-600 SRM 53-10-15 FIG 203 BASED ON A VISUAL EVALUATION WITH THE REPAIR INSTALLED. CUT OUT AND REPLACED A 50" SECTION OF ROLLER TRACK AND REPAIRED PER A300-600 SRM 53-10-15 FIG 203, AMM 25-52-21-4, 25-52-54-4, 25-52-24-4 AND 25-54-80-2.

Part: UPLOCK — MALFUNCTIONED (RT MLG) · airframe 37,719 hrs · 20,737 cycles

AFTER GEAR RETRACTION RT MAIN GEAR DOOR LIGHT STAYED ILLUMINATED. PERFORMED QRH PROCEDURES. THE INBOUND CREW REPORTED THE RT GEAR DOOR OPEN PRIMARY AND SECONDARY INDICATIONS DID FLICKER ON AND OFF INDIVIDUALLY AT DIFFERENT TIMES ONLY TO STAY ILLUMINATED MOST OF THE FLIGHT. REMOVED AND REPLACED THE RT MLG DOOR UPLOCK, PERFORMED OPS AND LEAK CHECKS PER A300-600 MM 32-31-33-4. RII:097942. FLT TEST SATISFACTORY.

Part: SWITCH — FAILED (RT MLG DOOR) · airframe 37,677 hrs · 20,710 cycles

RIGHT MLG DOOR OPEN AFTER T/O AFTER RETRACT. SWITCHED POS DET TO SYS 1 WITH SAME INDICATION ON ECAM DOOR LIGHT REMAINED ON OVERHEAD. REMOVED AND REPLACED RT GEAR DOOR SWITCH 28GB IN REF TO A300-600 AMM 32-00-00-4. PERFORMED LANDING GEAR INDICATION FUNCTIONAL TEST MULTIPLE TIMES REF A300-600 AMM 32-61-00-5. ALL INDICATION NORMAL AT THIS TIME.

Part: HOSE — LEAKING (APU) · airframe 36,170 hrs · 19,889 cycles

MAIN DECK CARGO SMOKE CAME ON DURING CLIMBOUT. RETURNED, LANDED, F/O SMELLED ODOR JUST PRIOR TO MAIN DECK CARGO SMOKE INDICATION AND THE SCENT DISAPPEARED AFTER NR 2 PACK WAS TURNED OFF. FOUND OIL ON BOTH PACK COALESCER BAGS. OIL LEAK AT APU BEING INJESTED INTO APU INLET. FOUND APU LOW OIL PRESSURE FLEX HOSE LEAKING. MPN 399-506-9010, CPN 4911201, QTY 1 HOSE, MSN 930258.

Part: ALTIMETER — MALFUNCTIONED (COCKPIT) · airframe 34,575 hrs · 18,909 cycles

AT AROUND 60 - 70 KTS ON FIRST TAKEOFF, GOT A NAV ADC FAILURE ON ECAM. AFTER CLEARING RUNWAY FAILURE WENT AWAY. A SECOND TAKEOFF INITIATED AND UNABLE TO TOGA AND GOT A RUNWAY POSITION ERROR. CHECKED MTP AT BLOCK-IN, NO FAULTS OR LIGHTS SET. PERFORMED BITE TESTS OF BOTH ADC'S IAW M/M 34-10-00-5. CREW RE-INITIALIZED FMS, ALL SYS'S NORMAL.

Part: FRAME — CRACKED (FUSELAGE) · airframe 29,554 hrs · 16,734 cycles

CRACK IN UPPER RADIUS RT FRAME.