N431UA

Part: FUEL CAP — MISSING · airframe 85,488 hrs · 33,879 cycles

FUEL CAP FOUND MISSING UPON ARRIVAL. FUEL CAP INSTALLED SERVICABLE FUEL CAP IAW AMM 28-25-41/401 CONFIG 00.

Part: FUEL CAP — MISSING (ZONE 600) · airframe 85,004 hrs · 33,609 cycles

ACFT ARRIVED WITH REFUEL ADAPTER CAP COMPLETELY MISSING. FUELER REPORTS FUEL CAP LANYARD NOT ATTACHED AND FUEL CAP HINGE IS BROKEN. VERFIED NO LEAKS NOTED AT THIS TIME. COMPLIED WITH CDL 28A.

Part: BLEED VALVE — FAULTED (NR 1 ENGINE) · airframe 84,889 hrs · 33,539 cycles

ABORTED TAKEOFF DUE TO ECAMS NOT APPROPRIATE WITH MEL. ACP'D ON L/P 6256763.ENG1 HP VALVE INDICATES OPEN ON BLEED PAGE. ALLOTHER INDICATIONS NORMAL SECURED THE ENGINE 1 HPV CLOSED AND INSTALLED DF STICKER REF MEL 3611S. DM SUGGEST TSM 36-11-00-810-835-A, R & R NR 1 ENG HP VALVE IAW AMM 36-11-51/401 CONFIG 13 OPS CHECK GOOD NO LEAKS. 13 OPS CHECK GOOD NO LEAKS.

Part: FITTING — DAMAGED (ZONE 100) · airframe 84,860 hrs · 33,525 cycles

UPON REINSTALLATION OF RT MLG DOOR ACTUATOR, REQURIED GAP COULD NOT BE OBTAINED AFTER WASHER NAS1149C1016R INSTALLED. REPLACED RH MLG DOOR ACTUATOR FITTING FWD AND AFT AIRBUS DWG R83 370501 ISSUE F.

Part: LAMP — INOPERATIVE (ZONE 200) · airframe 84,531 hrs · 33,356 cycles

EPSU EXT LOAD EMER L R&R 11WL EMERGENCY POWER SUPPLY UNIT PER AMM 33-51-38-400-001-A, DID NOT HELP. INSTALLED BACK THE OLD EPSU AND BATTERY. FOUND ON EPSU EXTERIOR LIGHTS FAULT LIGHT ON SEE PIC. CHECKED OVERWING LIGHTS FOUND AFT LIGHT NOT WORKING P/N GE1810. RELAMPED LH THE EMERGENCY OVERWING LIGHT PER AMM 33-51-15-400-001-A. OPS CHECK GOOD. EPSU TEST PASSED.

Part: MEDICAL KIT — OUT OF DATE (COCKPIT) · airframe 84,293 hrs · 33,234 cycles

EMERGENCY MEDICAL KIT (EMK) INSPECT {A3NB-25-3-6326} - FLIGHTDECK EMK REQS CHANGE IAW 25-64-99/201 REPLACED IAW 25-64-99/201

Part: BOTTLE — NONE (ZONE 800) · airframe 84,279 hrs · 33,226 cycles

DISARMING OF THE STRIKER LEVER OF THE DOOR DAMPER AND EMERGENCY OPERATION CYLINDER TO FACILITATE SLIDE REMOVAL R1 PASSENGER DOOR REF. FIG 52-10-00-991-00300-B - REARMED STRIKER LEVER FOR THE DOOR DAMPER AND EMERGENCY OPERATION CYLINDER. SAFETIED PER AMM MED DOOR FW # 1 R/H DOOR ASSIT BOTTLE REARMED AND SAFETIED REF AMM 52-10-00-860-002-A. PETTINATO DENQC

Part: SLIDE — FAULTED (ZONE 800) · airframe 84,279 hrs · 33,226 cycles

DOOR 1L SLIDE NEEDS REMOVED FOR TROUBLESHOOTING. REMOVED DOOR 1L ESCAPE-SLIDE PACK-ASSEMBLY REFERENCE: TASK 25-62-44-000-002-A INSTALLED DOOR 1L ESCAPE-SLIDE PACK-ASSEMBLY REF. AMM 25-62-44-400-006-A. OPS CHECK GOOD. WITNESSED INSTALLATION OF DOOR 1L ESCAPE-SLIDE PACK-ASSEMBLY REF. AMM 25-62-44-400-006-A. OPS CHECK GOOD.

Part: SENSOR — FAULTED (FUEL) · airframe 84,097 hrs · 33,130 cycles

ECAM FUEL IDG 1 COOL FAULT ON PARKING/ENGINESHUTDOWN AT GATE REMOVED AND REPLACED FLSCU1, THE FAULT CONTINUED, MORE TROUBLESHOOTING NEEDED. R&R FLSCU1 REF AMM 28-46-34 PERFORMED ENGINE RUN #1, MESSAGE CLEARED AFTER START, MESSAGE RETURNED AT SHUTDOWN. CORROBORATED MESSAGE ON PFR INDICATED L INN TEMP SENSOR 29QJ1, PERFORMED TSM 28-46-00-810-813-A WITHOUT TEST EQUIPMENT AVAILABLE, CHANGED FLSCU1 PER STEP 8 REPLACED 29QJ1 REF AMM 28-46-17-400-001-A ACC TANK LEVEL SENC FUNCTIONAL BITE REF AMM28-46-00-7400-001-A. NO STATUS MESSGE AT THIS TIME.

Part: BATTERY — DISCHARGED (ZONE 200) · airframe 83,600 hrs · 32,881 cycles

CABIN EMERGENCY LIGHTING BATTERY CAPACITY OPERATIONAL CHECK {A3NB-33-3-6013} - TEST FAIL SHOWED FWD LH EPSU BATTERY. REPLACED EPSU BATTERY REF AMM TASK 33-51-38-000-002-A AND TASK 33-51-38-400-002-A. ACP EPSU BITE, BITE CHECKS OKAY. ACP CIDS POWER ON TEST, TEST CHECKS OKAY.

Part: ELEC CONNECTOR — DAMAGED (ZONE 200) · airframe 83,600 hrs · 32,881 cycles

OPERATIONAL CHECK OF CABIN EMERGENCY LIGHTS {A3NB-33-3-6012} - SEAT MOUNTED EMERGENCY LIGHT AT 22C AND 28C INOP. AT SEATS 22C & 28C, REPLACED DAMAGED PINS & SOCKETS ON LIGHT ASSY CONNECTORS IAW SWPM 20-42-01. EMERGENCY SEAT TRACK LIGHTING OPS CK'D NORMAL.

Part: FITTING — DAMAGED (LT MLG DOOR) · airframe 82,716 hrs · 32,435 cycles

LMLG DOOR FWD ACTUATOR FTG LOWER FWD HOLE AND SURROUNDING FLANGE DAMAGED COMMON TO KEEL BEAM. REMOVED & REPLACED FWD ACTUATOR FITTING AT LH DOOR MLG IAW A320 DRAWING REPAIR R533 70501 AND SRM 51-42-11/001.

Part: FITTING — DAMAGED (LH MLG DOOR) · airframe 82,716 hrs · 32,435 cycles

LH MLG DOOR FWD HINGE AND ACTUATOR FITTING HOLES FOUND WITH SHEARED FASTENERS. REVISION OF ECRA 5330-07326 ON OR BEFORE 23-AUG-25. CARIED TO ACCOMPLISH A PERMANENT REPAIR ON THE LH MLG DOOR ACTUATOR FITTING REPAIRED HOLES L3 & L9 PER PART 3 OF THE LATEST OK TO CARRY PER ECRA 5330-07326, ACCOMPLISH A PERMANENT REPAIR TOMC-APPROVAL FROM SC1ELBYC COMMENT ON THE LH MLG DOOR ACTUATOR FITTING REPAIRED HOLES L3 & L9 PER PART 3 OF THE LATEST REVISION OF ECRA 5330-07326 ON OR BEFORE 23-AUG-25. INTERIM REPAIR HAS BEEN ACCOMPLISHED AT HOLES L3 AND L9 PER PART REVIEWED 1 OF ECRA 5330-07326 WITHOUT DEVIATIONS. ORIGINAL DISCREPANCY FOUND ON LCQ NR 9296214 AND 9296238.

Part: STRINGER — CORRODED (ZONE 100) · airframe 82,716 hrs · 32,435 cycles

AFT CARGO AREA STRG 25RH BETWEEN FRM 67 CORRODED (A3NB-05-3 -6199). REMOVED AND REPALCED STRINGER SECTION @25RH BETWEEN FR67 AND 66 IAW UAL A320 SRM 53-41-13-300-004.

Part: STRINGER — CORRODED (ZONE 100) · airframe 82,716 hrs · 32,435 cycles

AFT CARGO AREA STRG 26RH CORRODED BETWEEN FRM 65 AND FRM 66 (A3 NB-05-3-6199). REMOVED AND REPALCED STRINGER SECTION 26RH BETWEEN FRAME 65 AND 66 IAW UAL A320 SRM 53-41-13-300-004.

Part: VSV — FAULTY (NR 1 ENGINE) · airframe 81,616 hrs · 31,918 cycles

COMPRESSOR VANE DISPLAYED ON UPPER ECAM SCREEN. ENGINE PARAMETERS NORMAL. - ENG 1 ENG 1 COMPRESSOR VANE DURING TAKE OFF ROLL REJECT AT 80 KNOTS COMPLETED FADEC 1A AND 1B TEST AND GROUND SCAN. FADEC 1B TEST SHOWS MSG CHB VSV ACT/HC/ EEC1. BOTH 1A AND 1B SHOW ATA 753241 MSG VSV ACT/HC/ EEC1 POST FLIGHT SHOWS 77-11 ENG 1 COMPRESSOR VANE REF TSM 75-30-00-810-852 -A AND 75-30-00-810-845-A. REPLACED VSV ACTUATOR. PERFORMED DRY MOTOR AND IDLE LEAK CHECK. NO LEAKS NO MESSAGE. REF AMM 75-32-41-400-010-A-01 ACCOMPLISHED POWER ASSURANCE TEST IAW AMM 71-00-00-710-013-C. NO FAULTS FOUND. ALL PARAMETERS WITHIN LIMITS. NO ECAM MSGS.

Part: FUEL CAP — MISSING · airframe 80,185 hrs · 31,230 cycles

PDA 2 FUELER REPORTED FUEL CAP MISSING ON AIRCRAFT 4631. ARRIVED DENVER FLIGHT 2130-5SEP2023 FROM MEM SCEPTRE SHOWS FUEL CAP M&E 31-2825-9-0001 M&E S/N 1537 MFG PART # 0727540 MFG S/N C191537. MISSING CAP WAS ADDRESSED ON LOG PAGE 5669069. REPLACED FUEL CAP REF AMM CHAP 28. ROTABLE PARTS CHANGE WAS INDICATED - TT # 1509415 SN OFF 1537 CAP, COUPLING R OFF 31-2825-9-0001 1537 ON 31-2825-9-0001 0738.

Part: LINKAGE — OUT OF ADJUST (AFT CARGO DOOR) · airframe 80,093 hrs · 31,183 cycles

HIGH SPEED REJECTED TO DUE TO AFT CARGO DOOR OPEN INDICATION. PER CREW RTO AT 100 KNOTS. TS FOUND AFT CARGO DOOR FLAP LINKAGE OUT OF ADJUSTMENT. ADJUSTED PER AMM 52-32-11-820-002. REINSTALLED AND OPERATED AFT CARGO DOOR HANDLE. OPS CK OK. INDICATION IS NORMAL. PREFORMED INSPECTION AFTERBRAKE EMERGENCY APPLICATION PER AMM 05-51-16-200-001. NO FAULTS. AC OK FOR SERVICE.

Part: FITTING — CORRODED (MLG WW) · airframe 78,372 hrs · 30,345 cycles

CORROSION REAR SPAR STOP RETRACTION JACK FITTING LOC MLG BAY ON LH WING. SEE AEROMAN NON ROUTINE 2022-360095. REQUIRED, PERFORMED SCEPTRE ENTRY ON LOGPAGE #3119101 REMOVED AND REPLACED JACK ANCHORAGE FITTING LOCATED ON MLG UPDATE SDR YES SIDE UPPER SURFACE ACTUATOR BRACKET IAW EA#577-0359-22 REV.0 AND EC/RA#5754-01244 HIS REPAIR IS CATEGORY A AND MENOR REPAIR IN ACCORDANCE WITH GMM 03-20-20.

Part: FRAME — CRACKED (FRM 35) · airframe 78,372 hrs · 30,345 cycles

CRACK INDICATION ON FRAME 35 LT SIDE IN OPEN FASTENER HOLE LOWER AND MORE AFT AT LEVEL OF STGR30, CRACK DIRECTION IS 5 OCLOCK IN FWD CARGO COMPARTMENT (1 EA) AND ANGLE FITTING AT S-30LH IAW PART 2A OF LATEST REVISION OF 104,772 TFH. ACCOMPLISHED INTERIM REPAIR ON HOLE #2 PART 1 PER ECRA 5331-02976, HFEC AND ROTO INSPECTION DONE AND CRACK-FREE AFTER REWORK. ACCOMPLISH INITIAL INSPECTIONS ON REPAIRED HOLE #2 IN THE FWD SK TOMC-APPROVAL FROM SC1ELBYC COMMENT IN, AFT SKIN, FR35 LAYER AND ANGLE FITTING AT S-30LH AS PER PART 2A OF LATEST REVISION OF EC5331-02976

Part: FITTING — CORRODED (MLG BAY ON LH WI) · airframe 78,372 hrs · 30,345 cycles

CORROSION REAR SPAR STOP RETRACTION JACK FITTING LOC MLG BAY ON LH WING. SEE AEROMAN NON ROUTINE 2022-360095. REQUIRED, PERFORMED SCEPTRE ENTRY ON LOGPAGE #3119101 REMOVED AND REPLACED JACK ANCHORAGE FITTING LOCATED ON MLG UPDATE SDR YES SIDE UPPER SURFACE ACTUATOR BRACKET IAW EA#577-0359-22 REV.0 AND EC/RA#5754-01244 HIS REPAIR IS CATEGORY A AND MENOR REPAIR IN ACCORDANCE WITH UAL GMM 03-20-20. RE INSPECTION IS NOT ADD EMP:V939073

Part: FRAME — CRACKED (FRAME 4 SIDE PO) · airframe 78,372 hrs · 30,345 cycles

CRACK INDICATION ON FRAME 4 SIDE POST UPPER ATTACHMENT LH SIDE IN OPEN FASTENER HOLE AT VERTICAL FLANGE, CRACK DIRECTION IS 9 OCLOCK IN COCKPIT (1 EA) SEE AEROMAN NON ROUTINE 2022-359865 3 OF THE LATEST REVISION OF EC/RA #5310-08051 ON OR BEFORE THE T ENGINNEERING AFTER 55,645 TOTAL AIRCRAFT FLIGHT CYCLES BY OF EC/RA # 5310-08051 ON THE REPAIR OF THE LATERAL WINDSHIELD THEREAFTER. AIRCRAFT REACHES 57,645 TATAL AIRCRAFT FLIGHT CYCLES GENERATED BEFORE 56,645 TOTAL,AIRCRAFT CYCLES FOR THE AIRCFRAFT EC/RA FRAME UPPER MODE AREA ON BEFORE THE AIRCRAFT REACHES 41,345 ANOTHER DIP LOGPAGE REFERECING THE LOGPAGE NUMBER GENERATED FOR 5310-080-51 PERMANENT REPAIR GENRATED THIRD DIP LOGPAGE TO TOTALHEREAFTERCRAFT FLIGHT CYCLES. PERFORME REPEAT THE LATERAL WIND SHIELD FRAME UPPER MODE AREA PLANNING TO CONTAC ACCOMPLISH INITIAL INSPECTION PER PART 2 OF THE LATEST REVISION INSPECTION AT INTERVALS NOT TO EXCEED 11,000 FLIGHT CYCLES INTERIM REPAIR NOSE FWD FUSELAGE-LH WINDSHEIELD FR 4 HOLE CRACK THIS REPAIR IS CATEGORY C IAW EC/RA # 5310-08051 AND EA# 53-0334-22 GENERATED A DIP LOGPAGE TO ACCOMPLISH A PERMANENT REPAIR OF THE LATERAL WINDSHIELD FRAME UPPER MODE AREA PER PART ADD EMP:V9652908 EA PER PART 3 OF THE LATEST REVISION OF ECRA 5310-0851 ON OR BEF EE LP''S 9795166 AND 9795245 FOR 2 MORE DIPS REQUIRED PER ECRA 53 ORE THE AIRCRAFT REACHES 57,645 TOTAL AIRCRAFT FLIGHT CYCLES." S 10-08051.CURRENT TOTAL AIRCRAFT FLIGHT CYCLES IS 30,345. PER PART 1 STEP 2 GENERATE A DIP TO READ AS FOLLOWS "A

Part: FITTING — DAMAGED (FRM 66) · airframe 78,372 hrs · 30,345 cycles

FOUND DISCREPANT HOLE SIZES CANNOT BE VERIFIED WITH A PREVIOUSLY APPROVED REPAIR ON LH FR 66 AFT DOOR STOP FITTING SEE AEROMAN NON ROUTINE 2022-360050 ATTACHMENT HOLES PER PART 2 OF LATEST REVISION OF ECRA 5341-01 CONTACT ENGINEERING AFTER 90,645 TOTAL FLIGHT AIRCRAFT CYCLES INDICATION FOUND.PERFORMED ROTOTEST INSPECTION ASPER NTM -333 ON OR BEFORE 92,645 TOTAL AIRCRAFT FLIGHT CYCLES.GENERATE A BUT BEFORE 91,645 TOTAL AIRCRAFT FLIGHT CYCLES FOR THE ECRA 51-10-01 IN ALL OPEN FASTENERS HOLES OF DOOR FITTING STOP AND 2ND DIP LOGPAGE REFERENCING THE ONE GENERATED FOR THE REPAIRED 5341-01333 INSPECTION REQUIREMENTS. PERFORMED HFEC EDDY CORRENT NO CRACK INDICATION FOUND HOLES ON THE LH FR 66 DOOR STOP FITTING #1 THRU #7, PLANNING TO AS PER NTM 51-10-08 ON ALL SURROUNDING AREAS AND NOT CRACK PERFORMED INTERIM REPAIR LOC. LH FR 66 DORR STOP FITTINGS 1 THRU 7 HOLES, THIS REPAIR IS CATEGORY B IAW EC/RA 5341-01333 REV A AND EA 53-0361-22. GENERATE DTA DIP LOG PAGE TO ACOMPLISH INITIAL INSPECTION AT THE LH FR 66 DOOR STEP FITTING 1 THRU 7. ACCOMPLISH INITIAL INSPECTION AT THE LH FR66 DOOR STOP REVISION OF ECRA 5341-01333 ON OR BEFORE 92,645 TOTAL AIRCRAFT FITTINGS #1 THRU #7 ATTACHMENT HOLES PER PART 2 OF THE LATEST FLIGHT CYCLES." SEE LP 9787743 FOR 2ND DIP REQUIRED. PERFORMED PART 1 INTERIM REPAIR PER AEROMAN EA-53-0361-22 REV0 AS APPENDIX A IN ECRA 5341-01333. GENERATE DTA DIP TO READ AS OK TO CARRY INITIAL INSPECTION OF REPAIR AT LH FR66 DOOR STOP.

Part: FITTING — DAMAGED (FRM 66) · airframe 78,372 hrs · 30,345 cycles

FOUND DISCREPANT HOLE SIZES CANNOT BE VERIFIED WITH A PREVIOUSLY APPROVED REPAIR ON RH FR 66 AFT DOOR STOP FITTING. SEE AEROMAN 2022-360051 ATTACHMENT HOLES PER PART 2 OF LATEST REVISION OF ECRA 5341- CONTACT ENGINEERING AFTER 90,645 TOTAL AIRCRAFT FLIGHT CYCLES STEP 05 CRACK INDICATION NOT FOUND. ROTOTEST INSPECTION 01338 ON OR BEFORE 92,645 TOTAL AIRCRAFT FLIGHT CYCLES.GENERATE BUT BEFORE 91,645 TOTAL AIRCRAFT FLIGHT CYCLES FOR THE ECRA PERFORMED AT ALL OPEN FASTENER HOLE OF THE DOOR STOP FITTING A 2ND DIP LOGPAGE REFERENCING THE ONE GENERATED FOR THE REPAIRED 5341-01338 INSPECTION REQUIREMENTS.PERFORMED HFEC ON ALL AS PER NTM 51-10-01 AND EA 53-0362-22 PART 1 STEP 6 CRACK HOLES ON THE RH66 DOOR STOP FITTING #1 THRU #7 PLANNING TO SURROUNDING AREA AS PER NTM 51-10-08 AND EA 53-0362-22 PART 1 INDICATION NOT FOUND INTERIM REPAIR LOC. RH FR66 DOOR STOP FITTING #1 THRU #7 HOLES ACCOMPLISHED THIS REPAIR IS CATEGORY B IAW EC/RA 5341-01338 AND EA 53-0362-22 REV 0. GENERATE A DIP LOGPAGE TO ACCOMPLISH INITIAL INSPECTION AT THE RH FR 66 DOOR STOP FITTING #1 THRU 7 ECRA 5341-01338 ON OR BEFORE 92,645 TOAL AIRCRAFT FLIGHT CYCLES. ALSO SEE LP 9797191 FOR REQUIRED 2ND DIP. ACCOMPLISH INITIAL INSPECTION AT THE RH FR66 DOOR STOP FITTINGS #1 THRU #7 ATTACHMENT HOLES PER PART 2 OF THE LATEST REVISION OF REF ECRA 5341-01338 PART 1 STEP 2. DIP INITIATED TO "ACCOMPLISH TOMC-APPROVAL FROM SC1ELBYC COMMENT INITIAL INSPECITON AT THE RH FR66 DOOR STOP FITTINGS #1 THRU #7 ATTACHMENT

Part: NONE — NONE (NONE) · airframe 78,372 hrs · 30,345 cycles

ADDITIONAL DATA IS NEEDED TO EVALUATED ON EXISTING DOUBLER AS PER ECRA 5330-06364 (LP 6821164) SEE AEROMAN NON ROUTINE 2022-359932 INSPECTION REQUIREMENTS FOR REINFORCING REPAIR GENERATE ANOTHER DIP THAT REFERENCE THE LOGPAGE 78,000 FC BUT BEFORE AIRCRAFT REACHES 79000FC PO:2022-152266/001 FILLER MADE WITH MATERIAL P/N:2024T3 0.080IN, REINFORCING REPAIR INSTALLED AT FR21 AND S-21LH AS PER PART 2 OF REACHES 83,645 TFC (FH NOT RELEVANT). INSTALLED AT FR21 AND 521 LH AS PER PART 2 OF GENERATED IN STEP #2 ABOVE FOR PLANNING TO CONTACT (FH NOT RELEVANT). INSPECTION REQUIREMENTS TO BE DETERMINATED PO:2022-139695/001.REPAIR BUSH MADE WITH MATERIAL P/N: THE LATEST REVISION OF ECRA 5331-02980 ON OR BEFORE AIRCRAFT LATEST REVISION OF EC 5331-02980 ON OR BEFORE ENGINEERING FOR THE INSPECTION REQUIREMENTOF PART 2 BY ENGINEERING BEFORE THE AIRCRAFT REACHES THE NOTED THRESHOLD. 2024T351 PO:2022-169992. PERFORMED HFEC INSPECTION IAW AIRCRAFT REACHES 83.645FC(FH NOT RELEVANT) OF LATEST REVISION OF EC5331-02980 AFTER AIRCRAFT REACHES DOUBLER MADE WITH MATERIAL P/N:2024T3 0.063IN, NTM 51-10-08. ACCOMPLISHED INTERIM REPAIR PER ECRA 5331-02980 PART 1 STEP 1 BY V939915. INITIATED DIP TO ACCOMPLISH INSPECTION REQUIREMENTS FOR ADD EMP:V939915 PERFORMED INTERIM REPAIT LOC FR21 AND STRG 21LH PERFORMED ROTOTEST INSPECTION IAW NTM THIS REPAIR IS CATEGORY B, IAW EC/RA 5331-02980 51-10-01 AND PERFORMED ULTRASONIC THICKNESS AND EA 53-0408-22. REPAIR PER AEROMAN EA IAW NTM 51-10-04 PB4 PERFORMED SCEPTRE EN

Part: FRAME — CRACKED (FRM 36) · airframe 78,372 hrs · 30,345 cycles

CRACK INDICATION ON FRAME 36 PRESSURE PANEL IN OPEN FASTENER HOL ES NUMBER 6, 7, 10, 11, 12, 13, 14, 17, 18 AND 19 INBOARD OF BEA M -Y1292, HOLES ARE OUTSIDE THE REPAIR ALLOWABLE CUT-OUT AREA, C ONTACT ENGINEERING FOR REPAIR INSTRUCTIONS AND REPAIR BEFORE NEX T FLIGHT IN FWD CARGO COMPARTMENT (10 EA). SEE AEROMAN NON ROUTI NE 2022-360101. AS PER PART 3 OF LATEST REVISION OF EC 5311-02910 ON OR BEFORE OR 85,000 TOTAL FLIGHT HOURS (WHICHEVER COMES FIRST). BUT 2024T351-1.25 P.O #2022-118566. PERFORMED ROTOTEST INSPECTION AIRCRAFT REACHES 36,345 TOTAL FLIGHT CYCLES OR 90,372 TOTAL BEFORE AIRCRAFT REACHES 35,000 TOTAL FLIGHT CYCLES OR 86,000 ON REAMED HOLES. CRACK INDICATIONS NO FOUND I.A.W. NTM 51-10-01 FLIGHT HOURS (WHICHEVER COMES FIRST) PLANNING TO CONTACT TOTAL FLIGHT HOURS (WHICHEVER COMES FIRST) FOR THE PERMANENT PERFORMED SCEPTRE ENTRY LOGPAGE NO.9868040 ENGINEERING AFTER AIRCRAFT REACHES 34,000 TOTAL FLIGHT CYCLES REAPIR OF EC 5311-02910. FABRICATED FREEZE PLUG MATERIAL USED ACCOMPLISHED INTERIM REPAIR LOCATED PRESSURE DECK PANEL BETWEEN FR35/36 R/H I.A.W. EC/RA# 5311-02910 AND EA#53-0370-22 COVER REVISION 0. THIS REPAIR IS CATEGORY C AND MUST BE ACCOMPLISH A PERMANENT REPAIR TO REPAIRED FR36 PRESSURE BULKHEAD WEB ADD EMP:V939838

Part: FRAME — CRACKED (FRM 36) · airframe 78,372 hrs · 30,345 cycles

CRACK INDICATION ON FRAME 36 PRESSURE PANEL IN OPEN FASTENER HOL ES NUMBER 6, 7, 10, 11, 12, 13, 14, 17, 18 AND 19 INBOARD OF BEA M -Y1292, HOLES ARE OUTSIDE THE REPAIR ALLOWABLE CUT-OUT AREA, C ONTACT ENGINEERING FOR REPAIR INSTRUCTIONS AND REPAIR BEFORE NEX T FLIGHT IN FWD CARGO COMPARTMENT (10 EA). SEE AEROMAN NON ROUTI NE 2022-360101. AS PER PART 3 OF LATEST REVISION OF EC 5311-02910 ON OR BEFORE OR 85,000 TOTAL FLIGHT HOURS (WHICHEVER COMES FIRST). BUT 2024T351-1.25 P.O #2022-118566. PERFORMED ROTOTEST INSPECTION AIRCRAFT REACHES 36,345 TOTAL FLIGHT CYCLES OR 90,372 TOTAL BEFORE AIRCRAFT REACHES 35,000 TOTAL FLIGHT CYCLES OR 86,000 ON REAMED HOLES. CRACK INDICATIONS NO FOUND I.A.W. NTM 51-10-01 FLIGHT HOURS (WHICHEVER COMES FIRST) PLANNING TO CONTACT TOTAL FLIGHT HOURS (WHICHEVER COMES FIRST) FOR THE PERMANENT PERFORMED SCEPTRE ENTRY LOGPAGE NO.9868040 ENGINEERING AFTER AIRCRAFT REACHES 34,000 TOTAL FLIGHT CYCLES REAPIR OF EC 5311-02910. FABRICATED FREEZE PLUG MATERIAL USED ACCOMPLISHED INTERIM REPAIR LOCATED PRESSURE DECK PANEL BETWEEN FR35/36 R/H I.A.W. EC/RA# 5311-02910 AND EA#53-0370-22 COVER REVISION 0. THIS REPAIR IS CATEGORY C AND MUST BE ACCOMPLISH A PERMANENT REPAIR TO REPAIRED FR36 PRESSURE BULKHEAD WEB

Part: NONE — CRACKED (FR68-69 LH) · airframe 78,372 hrs · 30,345 cycles

CRACK PLATE LOC. BTW FR68TO FR69 L/H SIDE AT AFT GALLEY AREA SEE AEROMAN NON ROUTINE 2022-359949 REPLACED NEW PLATE LOC. BTW FR 68 TO FR69 L/H SIDE AT AFT GALLY AREA IAW A320 SRM 51-42-11-001 AND A320 SRM 51-72-11-911- 001, DWG D53480019

Part: SKIN — CRACKED (RH FR35/ STR30) · airframe 78,372 hrs · 30,345 cycles

CRACK INDICATION ON FRAME 35 RH SIDE IN OPEN FASTENER HOLE LOWER AND MORE AFT AT LEVEL OF STGR30, CRACK DIRECTION IS 2 OCLOCK IN FWD CARGO COMPARTMENT (1 EA) SEE AEROMAN NON ROUTINE 2022-359824 SKIN, AND FR35 LAYARS ONLY) AND F5 AT FR35 AND F5 AT FR35 AND REPEAT INSPECTIONS AT INTERVALS NOT TO EXCEED 6,500 FLIGHT FITTING LAYER ONLY) AR FR35 AND S-30RH AS PER PART 2B OF LATEST GENERATED IN STEP 3 ABOVE FOR PIANING TO CONTACT ENGINEERING (WHICHEVER COMES FIRST) FOR THE INSPECTION REQUIREMENT OF HOLE # PERFORM DETAILED VISUAL INSPECTION IN HOLE #2 IN FWD SKIN LAYER PERFORMED HFEC INSPECTION IN THE FRAME LAYER AS PER NTM PART 1 3) INSPECTION HOLE F5 AS PER NTM 53-31-86 FORWARD FINDINGS PART 2B INSPECTION REQUIREMENTS OF HOLE #2 TO BE AND S-30RH ASPER DART 2A OF LATEST REVISION OF EC5331-02964 CYCLES OR 13,000 FLIGHT HOURS (WHICHEVER OCCURS FIRST) REVISION OF EC5331-029-64 ON OR BEFORE AIRCRAFT REACHES 98,045 AFTER AIRCRAFT REACHES 90,000 TOTAL FLIGHT CYCLES OR 200,000 #2 (IN THE ANGLE FITTING LAYER ONLY) IN PART 2B OF THE LATEST AS PER NTM51-90-00 INSPECTION AREA SHOWN IN FIGURE1 SHEET 51-10-16 FROM INSIDE C)PERFORM INSPECTION IN THE AFT SKIN LAYER FACE TO PRESSURE BULKHEAD ATTACHMENTS FR35 AROUND THE INSTALLED DETERMINED BY ENGINEERED BEFORE THE AIRCRAFT REACHES THE ON OR BEFORE AIRCRAFT REACHES 46,345 TOTAL FLIGHT CYCLES OR THERE AFTER GENERATED A DID TO ACCOMPLISHI INSPECTION FLIGHT CYCLES OR 213,772 TOTAL FLIGHT HOURS (WHICHEVER COMES TOTAL FLIGHT HOURS (WHICHEVER COMES FIR

Part: STOP FITTING — UNKNOWN (RH FR 68 AFT DOO) · airframe 78,372 hrs · 30,345 cycles

FOUND DISCREPANT HOLE SIZES CANNOT BE VERIFIED WITH A PREVIOUSLY APPROVED REPAIR ON RH FR 68 AFT DOOR STOP FITTING. SEE AEROMAN NON ROUTINE 2022-360057 FR.68 STR.22 PER PART 2.A OF THE LATES REVISION OF EC/RA #5341- INITIAL INSPECTION ON THE FASTENER HOLES AND EXTERNAL SURFACES REACHES 68,245 TOTAL AIRCRAFT (FC) GENERATED ANOTHER DTA DIP 66,245 TOOL A/C (FC) BUT BEFORE 67,245 TOTAL A/C (FC) FOR THE 51-10-01 ON OPEN FASTENER HOLES INVOLVED IN THE REPAIR AREA 01339 ON OR BEFORE THE A/C REACHES 50,045 TOTAL AIRCRAFT (FC), OF THE FRAME WEB/REPAIR PART AT THHE RF.68 STR.22 RH REPAIR LOG PAGE REFERING THE ONE GENERATED IN STEP 3 FOR THE REPAIR EC/RA #5341-01339 PART 2B INSPECTION REQUIREMENTS, ACCOMPLISH A CRACK INDICATION NOT FOUND. PERFORMED REPEAT INSPECTION NOT TO EXCEED INTERVALS OF 19,700 ALONG WITH DOOR STOP FITTING #1 TO #7 HOLES PER PART 2.B OF THE ACCOMPLISHED ON FR.68 ALONOG WITH DOOR STEP FITTING #1 TO 7 HFEC ASPER NTM 51-10-08 IN THE AREAS MARKED IN BLUE SHOWN IN (FC), THE REAFTER, GENERATE A DTA DIP LOP PAGE TO ACCOMPLISH LATES REVISION OF EC/RA #5541-01339 ON OR BEFORE THE AIRCRAFT HOLES PLANNING TO CONTACT ENGINEERING AFTER AIRCRAFT RACHES APPENIX "A" FIGURE 5, PERFORMED ROTOTEST INSPECTION ASPER NTM PERFORMED INTERIM REPAIIR LOC. FR.68 RH STR.22 WEB STIFFENER AND DOOR STOP FITTING #1 TO #7 HOLES, THIS REPAIR IS CATEGORY B IAW EC/RA #5341-01339 AND EA #53-0374-22, GENERATE A DIP LOG PAGE TO ACCOMPLISH INITIAL INSPECTION ON FRAME REPAIR AT RH ADD EMP:V939831

Part: STOP FITTING — UNKNOWN (LH FR 68 AFT DR) · airframe 78,372 hrs · 30,345 cycles

FOUND DISCREPANT HOLE SIZES CANNOT BE VERIFIED WITH A PREVIOUSLY APPROVED REPAIR ON LH FR 68 AFT DOOR STOP FITTING SEE AEROMAN NON ROUTINE 2022-360056 B. GENERATE A DIP LOGPAGE TO ACCOMPLISH REACHES 50,045 TOTAL A/C (FC) PERFOM REPEAT REVISION OF EC/RA# 5341-01337 ON OR FOR THE REPAIR ACCOMPLISHED ON LH FR68 (FC) BUT BEFORE 67,245 TOTAL A/C (FC) INITIAL INSPECTION ON FRAME REPAIR AT LH INSPECTION NOT TO EXCEED INTERVALS OF 19,700(FC) BEFORE THE A/C REACHES 68,245 STR22 ALONG WITH DOOR STOP FITTING #1 FOR THE EC/RA 5341-01337 PART B INSPECTION FR68 STR22 PER PART 2A OF THE LATES REVISION THERE AFTER. GENERATE A DIP DTA LOGPAGE TOTAL A/C (FC) GENERATED ANOTHER DTA DIP TO #7 HOLES PLANNING TO CONTACT ENGINEERING REQUIMENTS OF EC/RA 5341-01337 ON OR BEFORE THE A/C TO ACCOMPLISH INITIAL INSPECTION ON THE FASTENER HOLES LOGPAGE REFERENCING THE ONE GENERATED AFTER THE A/C REACHES 66,245 TOTAL A/C PERFORMED INTERIM REPAIR LOC FR68 AND EXTERNAL SURFACES OF THE FRAME WEB/REPAIR LH DOOR STOP FITTING FASTENER, STARTING PART MENTIONED IN PART 2B AT THE FR68 STR22 DIAMETER OUT OF TOLERANCE IAW EA#53-0368-22 REPAIR ALONG WITH DOOR STOP FIRRING AND EC/RA#5341-01337. THIS REPAIR IS CATEGORY #1 TO #7 HOLES. PER PART 2B OF THE LATES ADD EMP:V939831 ADD EMP:V939831

Part: FLANGE — CRACKED (FR.68 STR.22R) · airframe 78,372 hrs · 30,345 cycles

CRACK INDICATION FOUND ON WEB HORIZONTAL FLANGE RADII LOWER POSITION OF FR.68 STR.22R L=0.787 INCH APPROX. SEE AEROMAN NON ROUTINE 2022-359838 22 PER PART 2A OF THE LATEST REVISION EC/RA 5341-01339 ON OR INSPECTION ON THE FASTENER HOLE AND EXTERNAL SURFACES OF THE (FC) GENERATED ANOTHER DTA DIP LOG PAGE REFERENCING THE ONE FOR THE EC/RA 5341-01339 PART 2B INSPECTION REQUIREMENTS. AREA. CRACK INDICATION NOT FOUND BEFORE THE A/C REACHES 50,045 TOTAL AIRCRAFT (FC) PERFORM FRAME WEB/REPAIR PART AT THE FR 68 STR 22.REPAIR ALONG WITH GENERATED IN STEP 3.FOR THE REPAIR ACCOMPLISH ON FR 68 ALONG ACCOMPLISH A HFEC ASPER NTM 51-10-08 IN THE AREAS MARKED IN BLUE REPEAT INSPECTION NOT TO EXCEED INTERVALS OF 19,700(FC) THE RE- DOOR STOP 1 TO 7 HOLES PER PART 2B OF THE LATE REVISION OF WITH DOOR STOP 1 TO 7 HOLES PLANING TO CONTACT ENGINEERING AFTER SHOW IN APPENIX A FIGURE 5. PERFORMED ROTOTEST INPECTION AS PER AFTER GENERATE A DTA DIP LOGPAGE TO ACCOMPLISH INITIAL EC/RA 5341-01339 ON OR BEFORE THE A/C REACHES 68,245 TOTAL A/C A/C REACHES 62,245 TOTAL A/C (FC) BUT BEFORE 67,245 TOTAL (FC) NTM 51-10-01 ON OPEN FASTENERS HOLE INVOLVED IN THE REPAIR PERFORMED INTERIM REPAIR LOC. FR 68 RH STR 22 WEB STIFFENER AND DOOR STOP FITTING 1 TO 7 HOLES.THIS REPAIR IS CATEGORY B IAW EC/RA 5341-01339 AND EA 53-0374-22 GENERATE A DIP LOGPAGE TO ACCOMPLISH INITIAL INSPECTION ON FRAME REPAIR AT FR 68 STR ADD EMP:V939831

Part: FRAME — CRACKED (FR 68 R SIDE) · airframe 78,372 hrs · 30,345 cycles

CRACK INDICATION ON FRAME 68 RH SIDE IN OPEN FASTENER HOLE LOWER INBOARD AT DOOR STOP 1 POSITION, CRACK DIRECTION IS 12 OCLOCK, REPAIR BEFORE NEXT FLIGHT AT AFT GALLEY AREA (1 EA). SEE AEROMAN NON ROUTINE 2022-359849 PER PART 2.A OF THE LATES REV. EC/RA 5341-01339 ON OR BEFORE THE AND EXTERNAL SURFACE OF THE FRAME WEB/REPAIR PART AT THE FR.68 REFERENCING THE ONE GENERATED IN STEP 3 FOR THE REPAIR 5341-01339 PART 2.B INSPECTION REQUIREMENTS, ACCOMPLISHED A INDICATION NOT FOUND. A/C REACHES 50,045 TOTAL A/C "FC" PERFOR REPEAT INSPECTION NOT STR.22 REPAIR ALONG WITH DOOR STOP 1 TO 7 HOLES PER PART 2.B. ACCOMPLISHED ON FRAME 68 ALONG WITH DOOR STOP FITTING 1 TO 7 HFEC ASPER NTM 51-10-08 IN THE AREAS MARKED IN BLUE SHOWN IN TO EXCEED INTERVALS OF 19,700(FC) THE REAFTER GENERATE A DTA DIP OF THE LATES REV. OF EC/RA 5341-01339 ON OR BEFORE THE A/C HOLES PLANNING TO CONTACT ENGINEERING AFTER A/C REACHES 66,245 APPENIX A FIGURE 5 AND ROTOTEST INSPECTION ASPER NTM 51-10-01, LOG PAGE TO ACCOMPLIIS INITIAL INSPECTION ON THE FASTENERS HOLE REACHES 68,245 TOTAL A/C (FC) GENERATED ANOTHER DTA DIP LOG PAGE TOTAL A/C (FC) BUT BEFORE 67,245 TOTAL A/C (FC) FOR THE EC/RA ON OPEN FASTENERS HOLES INVOLVED IN THE REPAIR AREA, CRACK PERFORMED INTERIM REPAIR LOC. FR.68 RH STR.22 WEB STIFFENER AND DOOR STOP FITTING 1 TO 7 HOLES, THIS REPAIR IS CATEGORY "B" IAW EC/RA #5341-01339 AND EA #53-0374-22, GENERATE A DIP LOG PAGE TO ACCOMPLISH INITIAL INSPECTION ON FRAME REPAIIR AT FR.68 STR.22 ADD EMP:V939831

Part: FRAME — CORRODED (STR23R) · airframe 78,372 hrs · 30,345 cycles

CORROSION FRAME 20 AT LEVEL STR23R IN PASSENGER CABIN SEE AEROMAN NON ROUTINE 2022-359976 REPLACED FR 20 LOC BTW STR 5 TO STR 31 RH SIDE IAW EA #53-0389-22 COVER REV 0 AND EC/RA #5311-02889 THIS REPAIR IS CATEGORY A, ADDITIONAL INSPECTION IS NOT REQUIRED PERFORMED SCEPTRE ENTRY ON LOGPAGE #9589302 RII REQUIREMENTS DOCUMENTED ON NON-ROUTINE 359976

Part: FLOORBEAM — CORRODED (FR20 TO FR24) · airframe 78,372 hrs · 30,345 cycles

CORROSION FLOORBEAM Y-189 LOC.BTW F20 TO TR24 AT FWD GALLEY AREA. SEE AEROMAN NON ROUTINE 2022-359893. REPLACED FOORBEAM -Y189 LOC BTW FR20 TO FR24 AT FWD GALLEY AREA OF CORROSION ARE L=2.360 IN W=0.878 IN D=0.010 IN TOOL USED I.A.W SRM A320 51-72-11-911-001 AND DRAWING D53111406, PERFORMED DIGITAL CALIPER PN: 500-197-30 SN A18135095, DUE DATE:FEB-12-23 VISUAL INSPECTION ON AREA AND NOT FOUND DAMAGE IAW NTM 51-90-00, PERFORMED SCEPTRE ENTRY ON LOG PAGE NUMBER IS: 9185480 MEASURE SEE AEROMAN NON ROUTINE 2022-359893. FOR INSPECTIONS

Part: SEAT TRACK — CORRODED (FR12 TO FR24) · airframe 78,372 hrs · 30,345 cycles

CORROSION SEAT TRACK -Y1292 LOC. BTW FR12 TO FR24 AT FWD GALLEY AREA. SEE AEROMAN NON ROUTINE 2022-359890. REMOVED AND REPLACED SEAT TRACK-Y1292 LOC. BTW FR12 TO FR24 AT DITIONAL DAMAGE I.A.W. NTM 51-90-00. PERFORMED SCEPTRE ENTRY INE 2022-359890. FWD GALLEY AREA IN PASSENGER CABIN I.A.W. A320 SAR 51-72-11-91 ON LOGPAGE NUMBER IS:9185713. MEASURES OF CORROSION ARE: L= 1-001, SRM 51-42-11/001 AND DWG #D53110900, #D53110964 AND #D 3.716 IN, W=1.400 IN, D=0.018IN. TOOL USED CALIPER P/N:500-19 53918124. PERFORMED VISUAL INSPECTION ON AREA AND NOT FOUND AD 7-30, S/N:A18234394, DUE DATE: SEP/29-2022.SEE AEROMAN NON ROUT SEE AEROMAN NON ROUTINE 2022-359890. FOR INSPECTIONS

Part: FLOORBEAM — CORRODED (FR66 TO FR70) · airframe 78,372 hrs · 30,345 cycles

CORROSION FLOOR BEAM +Y765 LOC BTW FR66 TO FR70 AT AFT GALLEY AREA. SEE AEROMAN NON ROUTINE 2022-359946. REPLACED FLOOR BEAM STRUCTURE Y+765 LOCATED FR66 TO FR70 IAW NTM 51-90-00. PERFORMED SCEPTRE AT AFT GALLEY AREA IAW A320 SRM 51-72-11 AND ENTRY ON LOGPAGE NUMBER IS:9185695. MEASURES OF CORROSION DRAWING #D53472040 PERFORMED VISUAL INSPECTION AREA: L=1.507IN;W=1.405IN;D=0.010IN. TOOL USED ON AREA AND NOT FOUND ADDITIONAL DAMAGE CALIPER:PN:500-197-30, SN:A18135095, DUE DATE:FEB-12-2023

Part: SKIN — NONE (OTHER) · airframe 78,372 hrs · 30,345 cycles

ADDITIONAL DATA IS NEEDED TO EVALUATED ON EXISTING DOUBLER AS PER ECRA 5330-06364 (LP 6802117). SEE AEROMAN 2022-359933. ARE L=1.372IN W=1328IN, USED MATERIAL IN REPAIR DOUBLER IS CLAD INTERVALS TBD INSPECTION METHOD TBD ASPER SRI 53-11-11-205-051, 2024T3-0.056 IN AND PO 2021-I180108-1 IAW A320 SRM 53-11-11-300- ACCOMPLISHED ECRA 5330-06364, AT MEXT HMV CHECK PRIO TO 052 FIG.001 THIS REPAIR IS CATERGORY B INSPECTION THRESHOLD FROM EXCEEDING 37,500FC OR 80,000FH WICHEVER OCCURS FIRST INSTALLED TIME OF ADL FC 60,000; FH 120,000 SUBSEQUENT INSPECTION AT DOT IAW GMM 06-35-05. EVALUATED EXISTING REPAIR ON EXTERNAL SKIN FUSELAGE LH SIDE LOC, BTW FR 23 TO FR24 AND STR 22 TO STR 25 AND NOT MEET REQUIREMENTS OF SRM, REMOVED EXISTING REPAIR AND INSTALLED NEW DOUBLER IAW A320 SRM 53-11-11-300-052 FIG. 001, DIMENSIONES OF CUTOUT ADD EMP:V939207 53-11-11-300-052 FIG. 001. THIS REPAIR IS CATERGORY B (ZONE A). (WHUCHEVER COMES FIRST). SUBSEQUENT INSPECTION AT INTERVALS TBD. INSPECTION THRESHOLD FROM TIME OF ADL IS 60,000 FC OR 120,000 FH INSPECTION METHOD TBD REF SRI 53-11-11-205-051. EXISTING REPAIR DOES NOT MEET REQUIREMENTS OF SRM. REMOVED EXISTING REPAIR AND INSTALLED NEW DOUBLER IAW A320 SRM ADD EMP:V939170 RII REQUIREMENTS DOCUMENTED ON NR 359933. APPROVED TO CARRY REF SRI 53-11-11-205-051 INSPECTION TO BE TOMC-APPROVAL FROM SC1ELBYC COMMENT ACCOMPLISHED FROM REPAIR EMBODIMENT 60,000 FLIGHT CYCLES/120,000 FLIGHT HOURS SUBSEQUENT INSPECTIONS TBD QC RECORDS UPDATE QC REVIEW T/A: 60000

Part: DOUBLER — DAMAGED (FR23-24/STR22-25) · airframe 78,372 hrs · 30,345 cycles

THIS REPAIR IS CATERGORY B INSPECTION THRESHOLD FROM EXCEEDING 37,500FC OR 80,000FH WICHEVER OCCURS FIRST INSTALLED TIME OF ADL FC 60,000; FH 120,000 SUBSEQUENT INSPECTION AT DOT IAW GMM 06-35-05. EVALUATED EXISTING REPAIR ON EXTERNAL SKIN FUSELAGE LH SIDE LOC, BTW FR 23 TO FR24 AND STR 22 TO STR 25 AND NOT MEET REQUIREMENTS OF SRM, REMOVED EXISTING REPAIR AND INSTALLED NEW DOUBLER IAW A320 SRM 53-11-11-300-052 FIG. 001, DIMENSIONES OF CUTOUT ADD EMP:V939207 53-11-11-300-052 FIG. 001. THIS REPAIR IS CATERGORY B (ZONE A). (WHUCHEVER COMES FIRST). SUBSEQUENT INSPECTION AT INTERVALS TBD. INSPECTION THRESHOLD FROM TIME OF ADL IS 60,000 FC OR 120,000 FH INSPECTION METHOD TBD REF SRI 53-11-11-205-051. EXISTING REPAIR DOES NOT MEET REQUIREMENTS OF SRM. REMOVED EXISTING REPAIR AND INSTALLED NEW DOUBLER IAW A320 SRM ADD EMP:V939170

Part: FLOORBEAM — CORRODED (FR68 TO FR69) · airframe 78,372 hrs · 30,345 cycles

CORROSION FLOORBEAM -Y1292 LOC BTW FR68 TO FR69 AT AFT GALLEY AREA. SEE AEROMAN NON ROUTINE 2022-359948. REPLACED FLOOR STRUCTURE LOCATED FR68 TO FR69 -Y1292 SCEPTRE ENTRY ON LOGPAGE NUMBER IS: 9185702. MEASURES AT AFT GALLEY AREA IAW A320 SRM 51-72-11 AND DRAWING OF CORROSION ARE: L=2.357IN. W=1.260IN, D=0.018IN. D5347200000 PERFORMED VISUAL INSPECTION ON AREA AND NOT TOOL USED: DIGITAL CALIPER PN:500-197-30, SN:A18109059 FOUND ADDITIONAL DAMEGE IAW NTM 51-90-00. PERFORMED DUE DATE:AUG-05-2022 MAJOR REPAIR REPAIR YES AND SDR YES

Part: FRAME — CORRODED (STR23R) · airframe 78,372 hrs · 30,345 cycles

CORROSION FRAME 20 AT LEVEL STR23R IN PASSENGER CABIN SEE AEROMAN NON ROUTINE 2022-359976 REPLACED FR 20 LOC BTW STR 5 TO STR 31 RH SIDE IAW EA #53-0389-22 COVER REV 0 AND EC/RA #5311-02889 THIS REPAIR IS CATEGORY A, ADDITIONAL INSPECTION IS NOT REQUIRED PERFORMED SCEPTRE ENTRY ON LOGPAGE #9589302

Part: NONE — CRACKED (MAIN DOOR RH SID) · airframe 78,372 hrs · 30,345 cycles

CRACK INDICATION ON MAIN DOOR KEEL BEAM HINGE FITTING RH SIDE IN FWD LUG WEB RADIUS,CRACK LENGTH= 0.230 INCH APPROX, IN MAIN WHEEL WELL (1EA). SEE AEROMAN NON ROUTINE 2022-360084 REPLACED HINGE FITTING LOC MAIN DOOR RH SIDE KEEL BEAM AREA IAW A320 SRM 51-72-11-011 SRM A320 51-42-11-001 AND DMG D53370600 PERFORMED.

Part: PLATE — CRACKED (FR68TO FR69) · airframe 78,372 hrs · 30,345 cycles

CRACK PLATE LOC. BTW FR68TO FR69 L/H SIDE AT AFT GALLEY AREA .REPLACED NEW PLATE LOC. BTW FR 68 TO FR69 L/H SIDE AT AFT GALLY AREA.

Part: SEAT TRACK — CORRODED (FR12 TO FR24) · airframe 78,372 hrs · 30,345 cycles

CORROSION SEAT TRACK -Y765 LOC. BTW FR12 TO FR24 AT FWD GALLEY AREA. SEE AEROMAN NON ROUTINE 2022-359891. REMOVED AND REPLACED SEAT TRACK Y765 LOC.BTW FR12 TO FR24 AT FWD ION ON AREA AND NOT FOUND ADDITIONAL DAMAGE I.A.W. NTM 51-90- 2023. GALLEY AREA IN PASSENGER CABIN I.A.W A320 SRM 51-72-11-911-001 00. PERFOMED SCEPTRE ENTRY ON LOG PAGE NUMBER IS: 9185723. MEA SRM 51-72-11-911-001, SRM 51-42-11-001 AND DMG #D53110876, SURE OF CORROSION AREA: W=0.0581N L=1.640 IN, D=0.018 IN TOOL #D53918123, #D53110984 AND #D53112627. PERFOMED VISUAL INSPECT USED: CALIPER P/N:500-197-30, S/N:A18135095, DUE DATE: FEB/12/

Part: SEAT TRACK — CORRODED (FR12 TO FR24) · airframe 78,372 hrs · 30,345 cycles

CORROSION SEAT TRACK -Y1292 LOC. BTW FR12 TO FR24 AT FWD GALLEY AREA. SEE AEROMAN NON ROUTINE 2022-359890. REMOVED AND REPLACED SEAT TRACK-Y1292 LOC. BTW FR12 TO FR24 AT DITIONAL DAMAGE I.A.W. NTM 51-90-00. PERFORMED SCEPTRE ENTRY INE 2022-359890. FWD GALLEY AREA IN PASSENGER CABIN I.A.W. A320 SAR 51-72-11-91 ON LOGPAGE NUMBER IS:9185713. MEASURES OF CORROSION ARE: L= 1-001, SRM 51-42-11/001 AND DWG #D53110900, #D53110964 AND #D 3.716 IN, W=1.400 IN, D=0.018IN. TOOL USED CALIPER P/N:500-19 53918124. PERFORMED VISUAL INSPECTION ON AREA AND NOT FOUND AD 7-30, S/N:A18234394, DUE DATE: SEP/29-2022.SEE AEROMAN NON ROUT

Part: SEAT TRACK — CORRODED (FR12 TO FR24) · airframe 78,372 hrs · 30,345 cycles

CORROSION SEAT TRACK -Y765 LOC. BTW FR12 TO FR24 AT FWD GALLEY AREA. SEE AEROMAN NON ROUTINE 2022-359891. REMOVED AND REPLACED SEAT TRACK Y765 LOC.BTW FR12 TO FR24 AT FWD ION ON AREA AND NOT FOUND ADDITIONAL DAMAGE I.A.W. NTM 51-90- 2023. GALLEY AREA IN PASSENGER CABIN I.A.W A320 SRM 51-72-11-911-001 00. PERFOMED SCEPTRE ENTRY ON LOG PAGE NUMBER IS: 9185723. MEA SRM 51-72-11-911-001, SRM 51-42-11-001 AND DMG #D53110876, SURE OF CORROSION AREA: W=0.0581N L=1.640 IN, D=0.018 IN TOOL #D53918123, #D53110984 AND #D53112627. PERFOMED VISUAL INSPECT USED: CALIPER P/N:500-197-30, S/N:A18135095, DUE DATE: FEB/12/

Part: FITTING — CORRODED (CREW DR AFT GAL) · airframe 78,372 hrs · 30,345 cycles

CORROSION CENTER FITTING PASSENGER CREW DOOR AT AFT GALLEY AREA LH SIDE. SEE AEROMAN NON ROUTINE 2022-360080. REMOVED AND REPLACED CENTER FITTING PASSENGER AREA IAW NTM 51-90-00. PERFORMED SCEPTRE ENTRY ON LOGPAGE SEP-29-2022 CREW DOOR AT AFT GALLEY AREA LH SIDE IAW A320 SRM NUMBER IS: 9185735. MEASURES OF THE CORROSION ARE 51-72-11-911-001 DWG D53480048. PERFORMED VISUAL L=4.070IN; W=0.058 IN D=0.119IN TOOL USED: INSPECTION AND NOT FOUND ADDITIONAL DAMAGE ON ADJACENT DIGITAL CALIPER PN:500-197-30, SN:A18234394 DUE DATE:

Part: FITTING — CORRODED (AFT GAL LH SIDE) · airframe 78,372 hrs · 30,345 cycles

CORROSION CENTER FITTING PASSENGER CREW DOOR AT AFT GALLEY AREA LH SIDE. SEE AEROMAN NON ROUTINE 2022-360080. REMOVED AND REPLACED CENTER FITTING PASSENGER AREA IAW NTM 51-90-00. PERFORMED SCEPTRE ENTRY ON LOGPAGE SEP-29-2022 CREW DOOR AT AFT GALLEY AREA LH SIDE IAW A320 SRM NUMBER IS: 9185735. MEASURES OF THE CORROSION ARE 51-72-11-911-001 DWG D53480048. PERFORMED VISUAL L=4.070IN; W=0.058 IN D=0.119IN TOOL USED: INSPECTION AND NOT FOUND ADDITIONAL DAMAGE ON ADJACENT DIGITAL CALIPER PN:500-197-30, SN:A18234394 DUE DATE:

Part: FLOORBEAM — CORRODED (FR20-24) · airframe 78,372 hrs · 30,345 cycles

CORROSION FLOORBEAM Y-189 LOC.BTW FR20 TO FR24 AT FWD GALLEY AREA.REPLACED FOORBEAM -Y189 LOC BTW FR20 TO FR24 AT FWD GALLEY AREA OF CORROSION ARE L=2.360 IN W=0.878 IN D=0.010.

Part: THRESHOLD — CORRODED (FRAME 68) · corrosion level 2 · airframe 73,219 hrs · 28,095 cycles

AFT WET AREA AT FRAME 68, Y-1689 HAS CORROSION ON THE THRESHOLD. FOUND TO BE OUT OF LIMITS IAW SRM 53-41-14. REMOVED AND IAW SRM 51-42-11, AND DRAWING D53480019000.

Part: SHEAR WEB — CORRODED (FRAME 70) · airframe 73,219 hrs · 28,095 cycles

AFT WET AREA FRAME 70, Y-1689, HAS CORROSION ON LATERAL SHEAR PLATE WEB. REMOVED AND REPLACED THE SHEAR WEB IAW SRM 51-42-11, 2.E, 2.F, 2.M, AND DWG 18D53471124.

Part: BATTERY PACK — MALFUNCTIONED (CABIN) · airframe 71,596 hrs · 27,337 cycles

WHEN DOING CIDS TEST, MESSAGE IWT LOAD EMERG L WAS GIVEN. RESET BATTERY PACK. CIDS TEST PASS REF MM 33-51-38-401.

Part: PIN — DAMAGED (CONNECTOR) · airframe 68,726 hrs · 26,090 cycles

ENGINE THRUST LEVER DISAGREE ECAM DISPLAYED. REPLACED PINS ON J1 CONNECTOR. PIGGY BACK WIRES J7 AT EEC TO FIREWALL CONNECTOR 407VC1.

Part: SKIN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 67,476 hrs · 25,536 cycles

DURING HORIZONTAL STAB INSPECTION FOUND SKIN TO HAVE INTERGRANULAR CORROSION, FWD OF DOOR 312AR, AT APPROX STRINGER 25 RT, STATION 3366, FRAME 70 APB. ACCOMPLISHED REPAIR IAW ECRA 5330-05303 STEPS 1 A & B.

Part: SKIN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 65,889 hrs · 24,888 cycles

DURING HORIZONTAL STAB INSPECTION FOUND SKIN TO HAVE INTERGRANULAR CORROSION FWD OF DOOR 312AR AT APPROX STRINGER 25 RT, STATION 3366, FRAME 70 APB. ACCOMPLISHED REPAIR IAW ECRA 5330-05303 STEPS 1 A & B.

Part: SKIN — CORRODED (HORIZONTAL STAB) · corrosion level 2 · airframe 65,889 hrs · 24,888 cycles

DURING HORIZONTAL STABILIZER INSPECTION, FOUND SKIN TO HAVE INTERGRANULAR CORROSION FORWARD OF DOOR 312AR AT APPROXIMATE STRINGER 25 RIGHT, STATION 3366 & FRAME 70 APB. ACCOMPLISHED REPAIR IAW ECRA 5330-05303 STEPS 1 A & B. AT TIME OF CF PERMANENT REPAIR IS UNDER ENGINEERING EVALUATION IAW PART 3 & TO BE PERFORMED WITHIN 50 FLIGHT CYCLES ONCE APPROVED.

Part: SKIN — CORRODED (FUSELAGE) · airframe 65,889 hrs · 24,888 cycles

DURING HORIZONTAL STAB INSPECTION FOUND SKIN TO HAVE INTERGRANULAR CORROSION, FWD OF DOOR 312AR AT APPROX STRINGER 25 RT, STATION 3366 & FRAME 70, APB. ACCOMPLISHED REPAIR IAW ECRA 5330-05303 STEPS 1 A & B.

Part: WARNING SYSTEM — ACTIVATED (COCKPIT) · airframe 62,241 hrs · 23,414 cycles

FORWARD CARGO DOOR ECAM ON TAKEOFF ROLL. RETURNED TO BLOCK.

Part: DOOR — CRACKED (O2 STOWAGE BOX) · airframe 60,919 hrs · 22,894 cycles

REAR PART OF DOOR OVER CAPTAIN'S OXY IS CRACKED & DIFFICULT TO CLOSE WHEN STOWING. REPLACED O2 MASK STOW BOX.

Part: COWLING — DEFECTIVE (NR 1 ENGINE) · airframe 60,847 hrs · 22,865 cycles

ON POST FLIGHT MX WALK AROUND INSPECTION, FOUND NR 1 ENG INBD FAN COWLING NOT FAIRED WITH NOSE COWL, GAP APPROXIMATELY .125 INCHES. REPLACED NR 1 ENG RT FAN COWL IAW AMM. LATCH CHECK & MISMATCH CHECKED GOOD.

Part: MASTER CYLINDER — FAULTY (LT BRAKE PEDAL) · airframe 60,337 hrs · 22,661 cycles

LT BRAKE STILL VERY SENSITIVE, OVER BRAKES AT THE SLIGHTEST TOUCH MAY CAUSE PROBLEMS. LT BRAKE PEDAL MASTER CYLINDER IAW MM.

Part: COMPUTER — FAULTY (NR 1) · airframe 60,286 hrs · 22,642 cycles

ECAM F-CTL SEC 1 FAULT. REPLACED SEC 1 IAW AMM & OPERATIONS TEST IAW AMM. TESTED OKAY. ACP CAT3 IAW AMM.

Part: COVER — DELAMINATED (VERTICAL STAB) · airframe 60,200 hrs · 22,607 cycles

PROTECTIVE FILM DELAMINATING ON VERTICAL STAB LE. IAW 55-003 MX ACTION 3 NO DAMAGE HAS TAKEN PLACE, CUT AWAY ANY LOOSE PORTIONS. CHECKED LIMIT A-CHECK & REPAIR LIMIT C-CHECK.

Part: BRACKET — CRACKED (THRUST REVERSER) · airframe 59,733 hrs · 22,433 cycles

DURING MX, FOUND NR 1 ENGINE RT GUSSET BRACKET FOR THRUST REVERSER OPEN ACTUATOR LINE CRACKED. R & R GUSSET BRACKET IN REF WITH SRM 51-42-11.

Part: LIGHT — NO TEST (L2 DOOR) · airframe 59,487 hrs · 22,329 cycles

DURING TEST OF EMERGENCY LIGHT, AFTER L2 DOOR SLIDE REPLACEMENT, TEST FAULTED "BATTERY EMERGENCY L". CYCLED CIRCUIT BREAKERS P49 H5, H6, H7. OPS CHECKED OK IAW AMM 33-51-00-710-001-A.

Part: BATTERY — NO TEST (EMERGENCY LIGHT) · airframe 59,190 hrs · 22,209 cycles

CABIN EMERGENCY LIGHT CHECK FAILED. REPLACED BATTERY, OPS CHECKED GOOD.

Part: SCREW — MISSING (FUSELAGE) · airframe 59,000 hrs · 22,131 cycles

RAMP REPORTED BLOWOUT PANEL BORDER STRIP ON SECOND INBD CEILING PANEL MISSING TWO SCREWS. REPLACED MISSING SCREWS.

Part: BLOWOUT PANEL — UNSECURE (CARGO PIT) · airframe 58,721 hrs · 22,017 cycles

BLOWOUT PANEL HANGING DOWN IN AFT CARGO PIT. RESECURED PANEL.

Part: SEAT — UNSECURE (CABIN) · airframe 58,220 hrs · 21,819 cycles

SEAT ROW 37 ABC NOT ATTACHED TO FLOOR. SECURED SEAT IN PLACE PER AMM.

Part: CONTROLLER — FAULTED (COCKPIT TEMP) · airframe 58,206 hrs · 21,814 cycles

COCKPIT TEMP COMMANDING 100 DEGREES WITH CONTROL ON FULL COLD. TEMP UNCONTROLLABLE. REPLACED TEMP ZONE CONTROLLER. OP CHECKED OKAY.

Part: ANGLE — CORRODED (CARGO BAY) · corrosion level 2 · airframe 58,158 hrs · 21,789 cycles

CORROSION ON ANGLE IN FWD CARGO BAY BILGE RT STR 43 FR 33-34. INSTALLED ANGLE REPAIR.

Part: STRINGER — CORRODED (31 RIGHT) · corrosion level 2 · airframe 58,158 hrs · 21,789 cycles

STRINGER CORRODED BELOW OUTFLOW VALVE FR65-70, S31R. REPLACED STRINGER PER SRM. MAJOR REPAIR.

Part: SKIN — WORN (NR 2 NACELLE) · airframe 58,158 hrs · 21,789 cycles

NR 2 PYLON LT SIDE INSIDE PANEL 423AL BETWEEN RIBS 7 AND 8 PILLAR IS WORN. REPLACED NR 2 PYLON LT SIDE PILLAR BETWEEN RIBS 7/8 PER SRM 51-42-11.

Part: BATTERY — INOPERATIVE (EMERGENCY LIGHTS) · airframe 58,127 hrs · 21,777 cycles

EMERGENCY LIGHTS FAILED TEST, FAULTS AFT LEFT AND RIGHT BATTERIES. REPLACED BATTERY IN AFT LEFT POWER SUPPLY 13WL. RESEATED BATTERY IN RIGHT OVERWING POWER SUPPLY. TESTED OKAY.

Part: RELAY — FAULTY (FIRE DETECTION) · airframe 57,998 hrs · 21,720 cycles

APU CLASS 3 FAULT FIRE EMERGENCY STOP RELAY 6WF. RECHECK AT END OF NEXT DAYS FLYING PER TSM 26-22-00-810-807-A ITEM 4.B.(2) RECHECK \APU CLASS 3 FAULTS AFTER FIRST FLIGHT ON SUBSEQUENT DAY. RPL'D 6WF REF TSM26-22-00 -810-807A. ACPD OPS CHECK REF MM26-22-00-710-002-A.

Part: UNKNOWN — MALFUNCTIONED (SMOKE DETECTION) · airframe 57,998 hrs · 21,720 cycles

AEVC CLASS 3 FAULT 26-15-15 SMOKE DETECTOR 1WA. CFDS TEST OF ALL SMOKE DETECTORS CHECKED OKAY. SHOULD READ REPLACED SMOKE DETECTOR 1WA REF MM. CFDS TEST OF ALL SMOKE DETECTORS CHECKED OK.

Part: COMPUTER — FAULTY (NR 1) · airframe 57,789 hrs · 21,637 cycles

SUSPECT RIGHT LEADING EDGE FLAP DRIVE MECHANISM. NR 1 SFCC RPL ON DIFFERENT LOG GRIPE. REPLACED FIXED PROBLEM. PERF COMPLETE OPS CHECK OF SLATS REF AMM 27-84-00-710. NO FAULTS DETECTED. PERF ALL CFDS TESTS ON SLAT SYSTEM NO FAULTS DETECTED. REPLACE OF SFCC FIXED PROBLEM.

Part: STUD — OUT OF POSITION (SEAT) · airframe 57,735 hrs · 21,613 cycles

SEAT ROW 37DEF IS LOOSE AT FLOOR ATTACH POINT --NOT CONNECTED TO FLOOR. FOUND FRONT STUD BACKED OUT OF SEAT LEG. CHECKED STUD AND LEG THREADS ALL INTACT. REINSTALLED STUD AND ANTI RATTLE NUT. RE-INSTALLED SEAT INTO TRACK IN PROPER POSITION. SEAT IS SECURE AND SERVICEABLE.

Part: DRAIN VALVE — STUCK (POTABLE WATER) · airframe 57,600 hrs · 21,553 cycles

CREW REPORT: UNABLE TO FILL POTABLE WATER. FWD DRAIN VALVE STUCK OPEN. DURING TROUBLESHOOTING FOUND FWD WATER DRAIN VALVE FROZEN. CURRENTLY WORKING CLOSEUP. REMOVED AND REPLACED FWD DRAIN VALVE PER MM. LEAK CHECK GOOD. VALVE STILL OPERATES STIFF, SUSPECT CABLE. NIS FLL. OLD VALVE WAS DEAD. DISCONNECTED MANUAL CABLE FOR DRAIN VALVE. OPERATED VALVE ELECTRICALLY. VALVE WILL NOT CLOSE COMPLETELY. REQS NEW VALVE PCN 644-0123. REPLACED FILL DRAIN VALVE PER AMM, LEAK CHECKED OK. BUT MANUAL CABLE IS STIFF AND NEEDS REPLACED.

Part: RAM AIR TURB — LEAKING (HYDRAULIC SYS) · airframe 57,529 hrs · 21,523 cycles

HYD LEAK FROM NEW RAT AND PUMP.

Part: FLAP — DAMAGED (RT WING) · airframe 57,430 hrs · 21,484 cycles

RIGHT INBD TRAILING EDGE FLAP BIRD STRIKE OUTBD EDGE. INSPECTED AREA OF I/B FLAP FOR DAMAGE. FOUND DENT 1.25" X 1.75" X .055" LOCATED 10 INCHES FROM AFT EDGE AND 8.5" I/B OF THE CANOE. DENT IS LOCATED IN ZONE 2 AREA,TEMPORARY REPAIR NOT REQUIRED REF AIRBUS SRM. 57-52-00, FIG 117. PERFORMED NTM HFEC INSP OF AREA NO CRACKS FOUND. REPAIR CATEGORY A WITHIN 1000 FC. ACCMP'D PERMANENT CATEGORY A REPAIR REF SRM 57-52-00.

Part: ENGINE — VIBRATION (NR 1) · airframe 56,743 hrs · 21,196 cycles

NR 1 ENGINE VIBRATION UP TO 8.1 HAD TO REDUCE EPR TO 1.05 TO GET VIBRIATION UNDER 5.0. REMOVED AND REPLACED NR 1 ENGINE REF MT 71-017.

Part: PACKING — DAMAGED (GREEN HYD SYS) · airframe 56,078 hrs · 20,925 cycles

FLIGHT RECEIVED GREEN HYD RES LOW QUANTITY ECAM. FOUND GREEN SYSTEM HP MANIFOLD CHECK VALVE PACKING DAMAGED, REPLACED. SERVICED GREEN HYD SYSTEM. MANIFOLD LEAK CHECKED GOOD.

Part: BATTERY PACK — FAULTY (EMERGENCY LIGHTS) · airframe 55,607 hrs · 20,736 cycles

"INTL LOADS FWD L" FAULT MESSAGE WHEN PERFORMING EMERGENCY LIGHTS TEST. REPLACED BATTERY PACK AND GROUND CHECKED OKAY.

Part: OIL COOLER — LEAKING (NR 2 ENGINE) · airframe 55,607 hrs · 20,736 cycles

DURING ENGINE RUN, FOUND WETNESS AT BOTTOM OF FUEL OIL COOLER BOTTOM FWD CAP. UNABLE TO IDENTIFY POSITIVE SOURCE, WETNESS IS ENTIRE BOTTOM AREA OF OIL COOLER. UNABLE TO FIND LEAK ON NR 2 ENG FUEL OIL COOLER. REPLACED FUEL OIL COOLER.

Part: BEARING — STIFF (THRUST LEVER) · airframe 55,359 hrs · 20,636 cycles

STIFF THRUST LEVERS HARD TO GET OUT OF REVERSE. CYCLED BOTH REVERSE LEVERS. BOTH DEPLOY & STOWED WITH NO BIND OR STIFFNESS FELT. FOUND LARGE AMOUNT OF DUST DEBRIS CAUSING BEARINGS ON LEVER ASSY TO BE STIFF. CLEANED HOUSING ASSY AND LUBED BEARINGS. OPS CK THROTTLE AND REVERSER OPERATION FROM REV THRUST TO FWD THRUST SETTINGS SMOOTH OPERATION NOTED. ACFT REQUIRES CAT III LAND TEST. ACCOMPLISHED SATISFACTORY LAND TEST. ACFT REMAINS CAT III.

Part: LIGHT — FAULTY (CABIN) · airframe 55,343 hrs · 20,631 cycles

INT LOADS EMER L FAULT MESSAGE WHEN PERFORMING CABIN EMERGENCY LIGHTS TEST. REPLACE AFT OVERWING BULBS. GROUND CHECKS OKAY.

Part: ENGINE — CONTAMINATED (NR 2) · airframe 54,971 hrs · 20,479 cycles

LARGE OIL LEAK ON ENG 2 SAMC TEXT: IDENTIFY FLUID TYPE & LEAK SOURCE. ACP CHECK OF THE ENGINE. FOUND NO LEAK SOURCE. CHECKED OIL AT TANK, TANK IS FULL. COCKPIT INDICATION INDICATES 21 QTS. REVIEW OF PLN OIL SHOWS OIL USE AT 0.07 QTS PER HR (WELL WITHIN LIMITS), OK TO CONTINUE.

Part: CONTROL VALVE — FAILED (A/C PACK) · airframe 54,852 hrs · 20,426 cycles

PACK 2 FAIL ON LANDING ROLL OUT. REPLACED NR 1 PACK FLOW CONTROL VALVE PER MM, OPS CHECKED GOOD.

Part: ANGLE — CRACKED (EMERGENCY EXIT) · airframe 54,328 hrs · 20,184 cycles

LEFT AFT OVERWING EMER EXIT DOOR FWD AND AFT ANGLE SEGMENTS CRACKED. MAJOR REPAIR ACCOMPLISHED. REPLACED FWD AND AFT ANGLE SEGMENTS PER SRM REF NR U7369H BY 311118.

Part: ANGLE — CRACKED (EMERGENCY EXIT) · airframe 54,328 hrs · 20,184 cycles

RIGHT AFT OVERWING EMER EXIT DOOR FWD AND AFT ANGLE SEGMENTS CRACKED. MAJOR REPAIR ACCOMPLISHED. REPLACED FWD AND AFT ANGLE SEGMENTS PER SRM, REF NR U7262H AND U7261H BY 311118.

Part: ANGLE — CRACKED (EMERGENCY EXIT) · airframe 54,328 hrs · 20,184 cycles

RIGHT FWD OVERWING EMER EXIT DOOR FWD AND AFT ANGLE SEGMENTS CRACKED. MAJOR REPAIR ACCOMPLISHED. REPLACED FWD AND AFT ANGLE SEGMENTS PER SRM. REF NR U7367H BY 309368.

Part: ANGLE — CRACKED (EMERGENCY EXIT) · airframe 54,328 hrs · 20,184 cycles

LEFT FWD OVERWING EMERGENCY EXIT DOOR FWD AND AFT ANGLE SEGMENTS CRACKED. MAJOR REPAIR ACCOMPLISHED. REPLACED FWD & AFT ANGLE SEGMENTS PER SRM. REF NR U7368H BY 395787.

Part: LIGHT — IMPROPER PART (CABIN) · airframe 54,328 hrs · 20,184 cycles

LT SEAT ROW 11 OW EMERG LIGHT ON SEAT IS WRONG COLOR SHOULD BE RED. REPLACED PER AMM WITH (P/N BR9644-22) ON WU N8664L BY 311007 AND LC-19. CHECKED GOOD.

Part: RESERVOIR — FAULTY (OVERWING SLIDE) · airframe 54,271 hrs · 20,156 cycles

CIDS CAUTION LIGHT ON FWD FA PANEL. REPLACED LEFT OFFWING ESCAPE-SLIDE INFLATION RESERVOIR.

Part: AUDIO PANEL — FAULTY (COCKPIT) · airframe 53,874 hrs · 19,970 cycles

ACP 3 HAS A HOT MIKE. REPLACED OBSERVERS AUDIO PANEL.

Part: UNKNOWN — MALFUNCTIONED (FUEL SYSTEM) · airframe 53,825 hrs · 19,947 cycles

FUEL SYSTEM PROBLEM, FLIGHT DIVERTED. CENTER TANK PUMP 1 DID NOT COME ON 15 MINUTES INTO FLIGHT UNTIL AFTER THE AUTO FEED FAULT PROMPTED FLT CREW TO DESELECT AUTO FEED, PUTTING FEED SYS IN MANUAL. AUTO FEED FAULT ON ECAM AND PFR. DF STICKER APPLIED. ACCOMPLISHED BITE OF FQIS COMPUTER, NO FAULTS. ACCOMPLISHED AUTO FEED TEST, OPS CHK OKAY.

Part: HANDLE — OUT OF POSITION (L2 DOOR) · airframe 53,688 hrs · 19,892 cycles

AT DOOR 2L ARMING HANDLE DOES NOT LAY FLUSH WITH DOOR WHEN CABIN IS PRESSURED. OK ON GROUND. PRESSURED A-C TO 4 PSI. NO HANDLE MOVEMENT NOTED.

Part: SEAL DEPRESSOR — DAMAGED (CARGO BAY) · airframe 53,674 hrs · 19,887 cycles

FWD CARGO PIT AFT SIDE DEPRESSOR SEAL DAMAGED BY BELT LOADER. REPLACED UPPER SEAL SECTION AND MIDDLE SECTION.

Part: OXYGEN MASK — UNSECURE (ROW 31DEF) · airframe 53,520 hrs · 19,820 cycles

THE 31DEF O2 MASKS FELL DOWN. REPACKED O2 MASKED AND ACCOMPLISHED DROP TEST.

Part: IDG — OVERHEATED (NR 1) · airframe 53,219 hrs · 19,689 cycles

NR 1 IDG OIL OVHT ECAM, FLIGHT DIVERTED. SCREEN. - ELEC CREW COMMENTS: IDG 1 OVHT ECAM, DISCNT IDG 1 PER FM. SUCCESSFUL DISCNCT.

Part: MICROPHONE — INOPERATIVE (OXYGEN MASK) · airframe 51,907 hrs · 19,081 cycles

CAPTAIN'S O2 MASK MIC INOP. SWAPPED MASK W- NO JOY. C/P BOOM MIC AND HAND MIC WORK OK. RECONNECTED LINE TO FIRST OFFICERS OXYGEN MASK COMPARTMENT. ALSO, REPLACED FIRST OFFICERS AUDIO CONTROL PANEL.

Part: OXYGEN MASK — LEAKING (COCKPIT) · airframe 51,894 hrs · 19,073 cycles

FIRST OFFICER’S OXYGEN HARNESS FAILS TO INFLATE (IS LEAKING). REPLACED O2 STORAGE BOX AND MASK PER MM.

Part: CONNECTOR — FAULTY (EMERGENCY LIGHT) · airframe 50,336 hrs · 18,319 cycles

DURING CABIN CREW CHECK, FOUND AT SEAT 17C THE FLOOR PROXIMITY EMERGENCY ESCAPE PATH MARKING SYS LIGHT DOES NOT LIGHT UP. ALL LIGHTS ADJACENT TO SEAT 17C ARE WORKING. SPLICED IN NEW CONNECTOR, LIGHT OPS CHECKS GOOD NOW.

Part: UPLOCK SENSOR — FAULTY (NLG) · airframe 49,050 hrs · 17,735 cycles

"NOSE GEAR" INDICATION RED, RTFL. REPLACED 13GA UPLOCK NOSE SENSOR. PERFORMED FUNCTIONAL TEST OF NORMAL EXTENSION AND RETRACTION. TEST PASS.

Part: ATTACH BRACKET — BROKEN (DOOR 1L SLIDE) · airframe 46,313 hrs · 16,508 cycles

ACCOMPLISH DOOR 1 LEFT SLIDE REMOVAL INSTALLATION AND INSPECTION FOR TRAINING PURPOSES. DURING INSPECTION OF DOOR 1 LEFT SLIDE, FOUND FWD LOWER ATTACH BRACKET BROKEN. REPLACED BRACKET.

Part: MICROPHONE — SHORTED (COCKPIT) · airframe 43,171 hrs · 15,247 cycles

CAPTAIN'S OXYGEN MASK MICROPHONE IS INOPERATIVE. CREW COMMENTS: MIC IS INTERMITTANT. SHORT IN MIC/MASK. REPLACED CAPT O2 MASK ASSY.

Part: OXYGEN MASK — FAULTY (CAPTAIN'S) · airframe 42,486 hrs · 14,997 cycles

CAPTAIN'S O2 MASK RED PRESS TO TEST BUTTON MISSING SMALL PIECE OF BUTTON. MASK IS FULLY FUNCTIONAL. REPLACED CAPT O2 MASK ASSY, OPS CHECKED OK.

Part: OXYGEN BOTTLE — READS LOW (CREW) · airframe 42,088 hrs · 14,853 cycles

COCKPIT OXYGEN BOTTLE, LOW CREW COMMENTS: CREW O2 NEEDS SERVICING. SERVICED CREW O2 TO FULL, NO LEAKS WERE NOTED AT THIS TIME.

Part: SQUIB — FAULTY (FIRE BOTTLE) · airframe 42,050 hrs · 14,842 cycles

'ENG FIRE EXTINGUISHING-SQUIB' LIGHT OF 'AGENT 1' PUSHBUTTON SWITCH IS OFF DURING 'LOOP-SQUIB TEST'. SQUIB IS FAULTY. REPLACED SQUIB, ALL OPS CHECKS NORMAL.

Part: OXYGEN SYSTEM — LOW PRESSURE (CREW O2) · airframe 41,538 hrs · 14,668 cycles

COCKPIT O2 1340 PSI, WITH AMBER HALF-BOX. SERVICED CREW O2, CHECKED FOR LEAKS, NONE NOTED.

Part: ANTI-SKID SYS — MISINSTALLED (MLG) · airframe 41,163 hrs · 14,546 cycles

UPON LANDING ACFT DEVIATED FROM RUNWAY. PROBLEM WITH ANITSKID SENSING SYSTEM. AFTER INVESTIGATION IT SEEMS THAT DURING HMV LT AND RT SYSTEMS WERE INADVERTENTLY SWITCHED. A/C DOWN SEVERAL WEEKS WHILE REPAIRS WERE COMPLETED. NOTE: 2 NEW ENGINES WERE INSTALLED DUE TO THIS INCIDENT. QA INVESTIGATION ON GOING.

Part: PROXIMITY SENSOR — CONTAMINATED (NLG) · airframe 39,241 hrs · 13,853 cycles

RTFL UNDER AMBER ALERT DUE TO NLG NOT RETRACTING. [SUP 06-06-07] INITIALLY REPLACED THE NR 2 LGCIU, BUT FURTHER TROUBLESHOOTING FOUND THE NOSE LANDING GEAR PROXIMITY SENSORS TO BE COVERED IN GREASE. CLEANED PROXIMITY SENSORS 12GA, 18GA, 30GA AND 31GA.

Part: FRAME — CRACKED (NR 2 REVERSER) · airframe 38,516 hrs · 13,610 cycles

NR 2 INBOARD REVERSER AT 7:00 POS FRAME IS CRACKED IN HALF. AFT END OF CASCADE VANES ATTACH TO FRAME. [5-1-07] REPLACED FRAME DURING HMV. FRAME HAS HISTORY IN THE INDUSTRY OF CRACKING, SERVICE BULLETIN IAE V2500-NAC-78-0209 ADDRESSES PART OF THE ISSUE . THE ROOT CAUSE IS VIBRATION INDUCED FATIQUE DUE TO LOOSE LOWER AND UPPER ATTACHMENT POINTS. A THRUST REVERSER HEALTH CHECK TO CHECK THE SUPPORT BUSHINGS EVERY CCK IS BEING INSTITUTED. SERVICE BULLETIN 78-0209 IS ALSO INCORPORATED INTO THE HEALTH CHECK.

Part: ATTACH FITTING — CORRODED (FUSELAGE) · airframe 38,516 hrs · 13,610 cycles

FWD PIT HAS CORROSION ON STRINGER AND FRAME CLIP FASTENERS FROM FRAME 24 THRU 31 AND FROM STRINGER 39R TO 40L. REPLACED 1098 RIVETS.

Part: ATTACH FITTING — CORRODED (FUSELAGE) · airframe 38,516 hrs · 13,610 cycles

FWD FRAME CLIP AND STRINGER FASTENERS HAVE CORROSION FROM FRAME 31 TO 35 AND FROM STR 38R TO 38L. REPLACED 752 CORRODED RIVETS.

Part: SILL — CORRODED (FUSELAGE) · airframe 38,516 hrs · 13,610 cycles

AFT RIGHT DOOR SILL PLATE HAS CORROSION DAMAGE AT INBOARD EDGE MID POINT OF PLATE. MAJOR REPAIR. INSTALLED DOUBLER REPAIR PER SRM.

Part: SKIN — DAMAGED (RT WING) · airframe 37,599 hrs · 13,279 cycles

RT WING LOWER SKIN FUEL PLATE 640PB CUT OUT FASTENER DAMAGED. PERMANENT REPAIR ACCOMPLISHED PER EVA 60643. MAJOR REPAIR REPORTED BECAUSE A REPAIR WAS ACCOMPLISHED ON A PRINCIPLE STRUCTURAL ELEMENT.

Part: SKIN — DAMAGED (LT WING) · airframe 37,599 hrs · 13,279 cycles

LT WING LOWER SKIN FUEL PLATE 540HB FASTENER HOLE DAMAGED. PERMANENT REPAIR ACCOMPLISHED PER EVA 60643.

Part: BATTERY — FAULTY (CABIN) · airframe 37,036 hrs · 13,069 cycles

FOUND EMERGENCY BATTERY FAULT ON EMERGENCY LIGHT TEST FWD LT. REPLACED BATTERY.

Part: LIGHT — INOPERATIVE (SEAT 26C) · airframe 36,475 hrs · 12,871 cycles

FOUND EMERGENCY LIGHT INOP AT SEAT 26C. REPLACED LIGHT ASSEMBLY, OPS CHECKS OK.

Part: LIGHT — INOPERATIVE (SEAT 8C) · airframe 36,475 hrs · 12,871 cycles

FOUND EMERGENCY LIGHT INOP AT SEAT 8C. REPLACED WIRE ASSEMBLY FROM SEAT ELECTRONIC BOX TO LIGHT ASSEMBLY, ALSO REPLACED LIGHT ASSEMBLY REF MM 33-51-19, OPS CHECK OK.

Part: LIGHT — INOPERATIVE (SEATS 15-17 & 20) · airframe 34,541 hrs · 12,146 cycles

EMERGENCY LIGHTS AT SEATS 15-17, 20-23 INOPERATIVE. REPLACED EEL POWER SUPPLY.

Part: CONTROLLER — FAILED (MLG) · airframe 32,909 hrs · 11,596 cycles

NR 1 LGCIU FAULT FOLLOWED BY LOSS OF VH2 RADIO AND THRUST REVERSER. LGCIU FAULT DISPLAYED DURING CRUISE. ACP LGCIU SYSTEM GRND TEST REF MM 32-69-00. TEST OKNO FAULTS FOUND.

Part: BATTERY — DISCHARGED (EMERGENCY LIGHT) · airframe 32,842 hrs · 11,572 cycles

NUMEROUS FLOOR PROX EEL LIGHTS INOP THROUGHOUT CABIN. BPOWER SUPPLIES LOW CHARGE. REPLACED MID AND AFT PWR SUPPLIES.

Part: COFFEEMAKER — FAILED (GALLEY) · airframe 26,395 hrs · 9,248 cycles

RETURN TO FIELD DUE TO ELECTRICAL ODOR IN CABIN. REPLACED COFFEEMAKER M11 IN FORWARD GALLEY.

Part: WIRE — LOOSE (CABIN) · airframe 20,466 hrs · 6,951 cycles

EMERGENCY EXIT LIGHTS ON LAST 3 ROWS OF SEATS ARE INOP. RESECURED WIRES AT SEATS 24C AND 26C. LIGHTS OPERATIONAL CHECK NORMAL.

Part: BLADE — FAILED (COMPRESSOR) · airframe 15,707 hrs · 5,317 cycles

NR 2 ENGINE FAILED IN FLIGHT. MAX EXHAUST GAS TEMPERATURE EXCEEDED. *S/D* THE IFSD WAS CAUSED BY A FAILURE OF A HIGH PRESSURE COMPRESSOR (HPC) 4TH STAGE (C4) BLADE. THE ROOT CAUSE OF THE BLADE FAILURE WAS HIGHER-THAN-NORMAL HIGH CYCLE FATIGUE STRESS CAUSED BY NON-OPTIMAL VARIABLE STATOR VANE (VSV) SCHEDULING. THE ROOT CAUSE IS BEING CORRECTED FOR UAL'S FLEET PER AN ELECTRONIC ENGINE CONTROL SOFTWARE MODIFICATION (V2500-ENG-73-0169) FOLLOWED BY AN ULTRASONIC INSPECTION OF THE BLADE (V2500-ENG-72-0373).