N308NV

Part: FRAME — CRACKED (ZONE 200) · airframe 54,236 hrs · 33,916 cycles

DURING ACCOMPLISHMENT OF THE ALLEGIANT TASK A32X-534123-01-2-001, UPPER FUSELAGE FR68 RH AT DOORSTOP 6 LEVEL FRAME INNER CAP JOINT TO GUSSET PLATE FASTENER HOLE WITH CRACK INDICATION DUE MISSED HOLE.PERFORMED GUSSET PLATE ATTACHMENT HOLES REPAIR AND GUSSET REPLACMENT LEVEL STOP 6 IAW COOPESA # COO-EO-2025-22851-R00 AND A319 SRM TASK 53-41-12-300-018 PARAG 2A FIG 001 SHEET 1,2 AND AIRBUS MESSAGE 81648810/004. THIS REPAIR WAS CLASSIFIED AS MAJOR AND COVERED IN THE COOPESA JOB A1Q171 ITEM 2-19

Part: FITTING — CRACKED (ZONE 200) · airframe 54,236 hrs · 33,916 cycles

DURING ACCOMPLISHMENT OF THE ALLEGIANT TASK A32X-53-210-003-WINDSHIELD, UPPER FUSELAGE COCKPIT WINDSHIELD CENTER POST LOWER ATTACHMENT ARE CONTINUITY FITTINGS LH AND RH WITH CRACK. THE BOTH FITTINGS WERE REPLACED FOLLOW THE ALLEGIANT ENGINEERING ORDER # A32X-STR-53ERO-00375-R00. THIS JOB WAS DOCUMENTED UNDER COOPESA JOB A1Q171 ITEM 2-21.

Part: DOOR FRAME — CRACKED (ZONE 200) · airframe 54,236 hrs · 33,916 cycles

DURING ACCOMPLISHMENT OF THE ALLEGIANT TASK A32X-534123-01-2-001, UPPER FUSELAGE FR66 RH AT DOORSTOP 4 LEVEL FRAME INNER CAP JOINT TO GUSSET PLATE FASTENER HOLE WITH CRACK INDICATION DUE MISSED HOLE.PERFORMED GUSSET PLATE ATTACHMENT HOLES REPAIR AND GUSSET REPLACEMENT AT FR66RH LEVEL STOP 4 IAW COOPESA EO # COO-EO-2025-22851-R00 AND A319 SRM TASK 53-41-12-300-018 PARAG 2.A FIG 001 SHEET 1,2 AND AIRBUS MESSAGE REF. 81648810/004. THIS REPAIR WAS CLASSIFIED AS MAJOR AND IS COVERED UNDER COOPESA JOB A1Q171 ITEM 2-18.

Part: WINDOW FRAME — CRACKED (ZONE 200) · airframe 54,236 hrs · 33,916 cycles

DURING ACCOMPLISHMENT OF THE ALLEGIANT A32X-53-210-003-WINDSHIELD, UPPER FUSELAGE COCKPIT LH WINDSHIELD CENTER POST LOWER HORIZONTAL FLANGE OPEN FASTENER HOLE WITH CRACK DETECTED DURING ROTOTEST INSPECTION OF THE CONTINUITY FITTINGS REPLACE PROCEDURE AS PER AIRBUS R53112919 FLAG NOTE 3.PERFORMED PERMANENT BUSH HOLE # D REPAIR ON COCKPIT WINDSHIELD LH FRAMING IAW COOPESA EO # COO-EO-2025-23038-R00 APPROVED AND DOCUMENTED ON AIRBUS RDAF 81638703/014/2025 # A AND ALLEGIANT ERO # A32X-STR-53ERO-00376-R00. THIS REPAIR WAS DOCUMENTED UNDER COOPESA JOB A1Q171 ITEM 2-27.

Part: SEAL — BROKEN (PBE) · airframe 52,969 hrs · 33,310 cycles

(AIRCRAFT NOT GROUNDED) AFT PBE SEAL BROKEN / INSTALLED SERVICABLE AFT PBE SEAL IAW ALLEGIANT PROCEDURES"

Part: GLOWSTRIP — DAMAGED (ZONE 200) · airframe 52,079 hrs · 32,924 cycles

DURING ACCOMPLISHMENT OF THE ALLEGIANT TASK 533187-01-1-001, UPPER FUSELAGE PAX CABIN CENTER SECTION EVACUATION PHOTOLUMINESCENSE STRIPS 2 EA DAMAGED.THE DAMAGE STRIP WERE REPLACED IAW A319 AMM TASK 33-51-21-000-001A AND TASK 33-51-21-400-001A. THIS REPAIR WAS DOCUMENTED IN COOPESA JOB A1P187 ITEM 2-63.

Part: FRAME — CRACKED (ZONE 200) · airframe 52,079 hrs · 32,924 cycles

DURING ACCOMPLISHMENT OF THE WORK CARD 53-260-003, UPPER FUSELAGE AFT PASSENGER CREW DOOR FR68 LHS DOOR STOP FITTING HOLES AT STOP FITTING # 1 INBOARD LOWER HOLE WITH CRACK WAS FOUND. PERFORMED PERMANENT REPAIR AT FR 68 LH DOOR STOP FITTING # 1 IAW ENGINEERING ORDER COO-EO-2024-20740-R00 AND RDAF 81454090/004/2024 ISSUE A AND APPROVED ERO R5341-0150-R00 THIS IS A MAJOR PERMANENT REPAIR CAT B. THIS REPAIR WAS DOCUMENTED UNDER JOB A1P187 ITEM 2-56.

Part: HINGE ARM — CORRODED (ZONE 300) · airframe 52,079 hrs · 32,924 cycles

DURING ACCOMPLISHMENT OF THE ALLEGIANT WORK CARD ZL325-01-1-001, EMPENNAGE VERTICAL STABILIZER TRAILING EDGE CORROSION WAS FOUND COMMON TO ATTACHMENT HOLES AT THE TRAILING EDGE PANEL ATTACHMENT FLANGES OF THE HINGE ARM 6 LH /RH SIDE. PERFORMED REPAIR AT VERTICAL STABILIZER TAIL HINGE ARM BR 6 LH AND RH FLANGE AND ATTACHMENT HOLES IAW EO # COO-EO-2024-20707-R01 AND AIRBUS RDAF 81450182/004/2024 ISSUE A.APPROVED UNDER ERO R5536-0059-R00,THIS IS MAJOR TEMPORARY REPAIR.

Part: SKIN PANEL — DAMAGED (ZONE 200) · airframe 52,079 hrs · 32,924 cycles

DURING ACCOMPLISHMENT OF THE ALLEGIANT ENGINEERING ORDER E5311-0019, UPPER FUSELAGE FR16 LHS DOUBLE JOGGLE AREA AT LEVEL OF DOOR STOP # 1 HOLES #10,#12,#14;#15,#17 THRU #19 WERE FOUND GREATER THAN THE STARTING HOLE DIAMETER FOR COLD WORK PROCESS WERE FOUND. PERFORMED PERMANENT REPAIR AT UPPER FUSELAGE FR16 LHS DOUBLE JOGGLE AREA IAW EO COO-EO-2024-20736-R02 AND RDAF 81452785/004/2024 # A APPROVED UNDER ERO # R5311-035-R00. THIS IS A MAJOR REPAIR PERMANENT CAT B. THIS REPAIR WAS DOCUMENTED UNDER JOB A1P187 ITEM 2-64.

Part: SKIN PANEL — CORRODED (ZONE 600) · airframe 52,079 hrs · 32,924 cycles

DURING ACCOMPLISHMENT OF THE WORK CARD ZL-500-03-1-002 RH WING AT FRONT SPAR AREA BETWEEN RIB 1/2 TOP SKIN PANEL WITH CORROSION WAS FOUND, PERFORMED PERMANENT REPAIR AT RH WING TOP SKIN PANEL 1 UPPER SURFACE RIBS 1 AND 2 FRONT SPAR L.E OVERHANG IAW ENGINEERING ORDER # COO-EO-2024-2017-R00 AND RDAF 80963545/035/2024 ISSUE A APPROVED UNDER ERO R5721-0220-R00 THIS IS MAJOR PERMANENT REPAIR CAT B. THIS REPAIR WAS DOCUMENTED UNDER JOB A1P187 ITEM 6-11.

Part: FRAME — CRACKED (ZONE 200) · airframe 52,079 hrs · 32,924 cycles

DURING ACCOMPLISHMENT OF THE WORK CARD 53-260-003, UPPER FUSELAGE AFT PASSENGER CREW DOOR FR68RHS DOOR STOP FITTING HOLES AT STOP FITTING # 1 INBOARD AND OUTBOARD LOWER HOLES WITH CRACK WERE FOUND. PERFORMED PERMANENT REPAIR AT RH REAR FUSELAGE FR68 DOOR STOP FITTING # 1 IAW EO COO-EO-2024-20788-R00 AND RDAF 81457102/004/2024 ISSUE A. APPROVED ERO R5341-0152-R00. THIS IS A MAJOR PERMANENT REPAIR CAT B.THIS REPAIR WAS DOCUMENTED UNDER JOB A1P187 ITEM 2-58.

Part: SKIN PANEL — CRACKED (ZONE 200) · airframe 52,079 hrs · 32,924 cycles

DURING ACCOMPLISHMENT OF THE ENGINEERING ORDER E5311-0019, UPPER FUSELAGE FR 16 LHS LOWER DOUBLE JOGGLE AREA HOLE # 14 WITH SKIN CRACKED WAS FOUND.PERFORMED PERMANENT REPAIR AT UPPER FUSELAGE FR16 LH DOUBLE JOGGLE IAW ENGINEERING ORDER COO-EO-2024-20736-R02 AND AIRBUS RDAF REF 81452785/004/2024 ISSUE A APPROVED UNDER ERO R5311-035-R00. THIS IS MAJOR PERMANENT REPAIR CAT B.THIS REPAIR WAS DOCUMENTED UNDER JOB A1P187 ITEM 2-61

Part: DOOR FRAME — CRACKED (ZONE 200) · airframe 52,079 hrs · 32,924 cycles

DURING ACCOMPLISHMENT WORK CARD 53-260-003, UPPER FUSELAGE AFT PASSENGER/CREW DOOR FR 68RH SIDE DOOR STOP FITTING HOLES AT STOP FITTING # 6 INBOARD LOWER HOLE WITH CRACK WAS FOUND.PERMANENT REPAIR AT FR68 RHS STOP FITTING # 6 (FREEZE PLUG AND OVERSIZE BOLT INSTALLATION) IAW SRM 53-41-12-300-010, THIS REPAIR WAS DOCUMENTED UNDER OB A1P187

Part: FRAME — CRACKED (ZONE 200) · airframe 52,079 hrs · 32,924 cycles

DURING ACCOMPLISHMENT ENGINEERING ORDER E5311-0119, UPPER FUSELAGE FR 16 LHS UPPER DOUBLE JOGGLE AREA HOLE # 7 WITH CRACK WAS FOUND. PERFORMED PERMANENT REPAIR AT UPPER FUSELAGE FR16LH DOUBLE JOGGLE AREA IAW EO COO-EO-2024-20736-R02 AND RDAF REF 81452785/004/2024 ISSUE A APPROVED UNDER ERO R5311-035-R00. THIS REPAIR IS MAJOR CAT B. THIS REPAIR WAS DOCUMENTED UNDER JOB A1P185 ITEM 2-60

Part: MECHANISM — MALFUNCTIONED (DOOR SLIDE) · airframe 52,079 hrs · 32,924 cycles

(AIRCRAFT NOT GROUNDED) REF: NRI 2-11 - DURING FUNCTIONAL TEST OF THE RELEASE MECHANISM OF THE EMERGENCY ESCAPE SLIDE, FOUND AFT RH DOOR EMERGENCY CONTROL HANDLE OUT OF LIMITS. / PERFORMED LUBRICATION OF SAFETY PIN GUIDE FITTING AND DOOR ARMING / DISARMING MECHANISM IAW A319 AMM TASK 12-22-52-640-014-A AND PERFORMED TEST OF THE RELEASE MECHANISM OF THE EMERGENCY ESCAPE SLIDE IAW A-319 AMM TASK 52-10-00-720-005-A. COOPESA A1P187 2-11. CALIBRATED TOOL USED S/N: R12928, DUE DATE: 11/11/2024.

Part: MECHANISM — FAULTED (DOOR SLIDE) · airframe 52,079 hrs · 32,924 cycles

(AIRCRAFT NOT GROUNDED) REF: NRI 2-12 - DURING FUNCTIONAL TEST OF THE RELEASE MECHANISM OF THE EMERGENCY ESCAPE SLIDE, FOUND AFT LEFT DOOR EMERGENCY CONTROL HANDLE OUT OF LIMITS. / PERFORMED LUBRICATION OF SAFETY PIN GUIDE FITTING AND DOOR ARMING / DISARMING MACHANISM IAW A319 AMM TASK 12-22-52-640-014-A AND PERFORMED TEST OF THE RELEASE MECHANISM OF THE EMERGENCY ESCAPE SLIDE IAW A319 AMM TASK 52-10-00-720-005-A, SATISFACTORY CONDITION. COOPESA A1P187 2-12. CALIBRATED TOOL USED S/N: R13615, DUE DATE: 11/30/2024.

Part: MEGAPHONE — NO TEST (ZONE 200) · airframe 51,932 hrs · 32,868 cycles

(AIRCRAFT NOT GROUNDED) FWD CABIN MEGAPHONE INOP. / REMOVED AND REPLACED FWD CABIN MEGAPHONE IAW AMM 25-65-51-920-001-A."

Part: EPSU — UNKNOWN (UNKNOWN) · airframe 50,696 hrs · 32,313 cycles

EPSU 13WL FAILED CABIN EMERGENCY LIGHTING TEST / REMOVED AND REPLACED EPSU 13WL IAW AMM 33-51-38-000-001-A AND 33-51-38-400-001-A"

Part: MEGAPHONE — UNKNOWN (UNKNOWN) · airframe 50,512 hrs · 32,199 cycles

FWD MEGA PHONE MISSING VOLUME KNOB. / REMOVED AND REPLACED FWD MEGA PHONE IAW LOPA."

Part: EPSU — UNKNOWN (UNKNOWN) · airframe 50,495 hrs · 32,192 cycles

DURING EMERGENCY LIGHT BITE TEST, FAILURE MESSAGE ''BAT/EPSU(13WL)AFT L''. / EPSU 13WL BATTERY REPLACED AND TESTED SERVICEABLE IAW AMM 33-51-38-400-002A"

Part: EPSU — UNKNOWN (UNKNOWN) · airframe 50,495 hrs · 32,192 cycles

DURING EMERGENCY LIGHT BITE TEST, FAILURE MESSAGE ''BAT/EPSU(13WL)AFT L''. / EPSU 13WL BATTERY REPLACED AND TESTED SERVICEABLE IAW AMM 33-51-38-400-002A"

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 50,495 hrs · 32,192 cycles

REINSPECT TEMP REPAIR AT EVERY SERVICE CHECK, FOUND LH ELEVATOR UPPER SKIN WITH COMPOSITE DAMAGE 74'' FROM OUTBOARD EDGE , 134'' FROM INBOARD EDGE, 6'' FROM LEADING EDGE AND 17'' FROM TRAILLING EDGE. MEASUREMENTS L=2.5'' W=2'' MAX D 0.244'' INSPECTED LH ELEVATOR UPPER SKIN COMPOSITE DAMAGE AND FOUND WITHIN ALLOWABLE DAMAGE LIMITS PER SRM 55-21-11-283-007. TEMP REPAIR ACCOMPLISHED ON UPPER SKIN APPLYING SPEED TAPE IAW SRM 51-77-12-911-001. M313 SUBMITTED. REINSPECT INTERVAL EVERY SERVICE CHECK. 99001517/1 (THIS NRC IS OPENED FOR TRACKING PERMANENT REPAIR STEPS ONLY) REF 4002318-3000-0010. / EVALUATED LH ELEVATOR UPPER SKIN WITH COMPOSITE DAMAGE 74'' FROM OUTBOARD EDGE , 134'' FROM INBOARD EDGE, 6'' FROM LEADING EDGE AND 17'' FROM TRAILLING EDGE AS PER SRM 55-21-11-283-007 PARA 2. TABLE 002,REV 145 AND REPAIRED AS PER SRM TASK 55-21-11-300-019 PARA.2. FIG 001, REV 145, DAMAGE DIMENSIONS: L = 2.45 IN X W = 1.77 IN, DEPTH = 0.114 IN. THIS REPAIR TASK IS PERMANENT CATEGORY A, ASSESSMENT OF THE WEIGHT OF THE ELEVATOR PERFORMED AS PER SRM TASK 55-20-00-283-001 REV 145, SEE AWS -9 FOR PERTINENT DETAILS. THE NEW TOTAL ELEVATOR WEIGHT (WT) = 52.8KG. MATERIAL USED CARBON FIBER P/N F38282-T/42, P.O.: 1734978, ADHESIVE P/N EA9396 P.O.: 2007761. SEE AWS FOR REPAIR STEPS."

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 50,413 hrs · 32,147 cycles

(EMERGENCY DECLARED) CAB PR SYS 1 FAULT IN FLIGHT, EXCESSIVE CABIN ALT MASTER WARNS SHORTLY AFTER, OUTFLOW VALVE SHOWED 1/4 OPEN ON SYSTEM PAGE. CABIN ALTTUDE EXCEEDED 25000, O2 MASK DROPPED. SYSTEM WAS IN AUTO ECAMS COMPLIED WITH. / CPC1 (11HL) WAS NOT RESPONDING. REMOVED AND REPLACED CPC1 (11HL) IAW AMM 21-31-34-000-001-A AND 21-31-34-400-001-A. PERFORMED OPS TEST OF PRESSURE CONTROL AND MONITORING IAW AMM 21-31-00-710-002-A. PERFORMED OPS TEST OF MANUAL MODE SELECTION AND MANUAL MODE PRESSURE CONTROL IAW AMM 21-31-00-710-003-A. PRESSURIZED CABIN IAW AMM 05-53-00-780-002-A01. ALL SYSTEMS OPERATING NORMALLY, OPS CHECK GOOD.

Part: EPSU — UNKNOWN · airframe 49,861 hrs · 31,892 cycles

BATTERY CAPACITY CHECK FAULTED 10WL, 11WL, 12WL BATTERY. / R & R'D LEFT EMERGENCY EXIT EPSU 10WL,11WL,12WL BATTERY IAW AMM 33-51-38-000-002-A AND 33-51-38-400-002-A."

Part: FITTING — CRACKED (ZONE 200) · airframe 46,606 hrs · 30,241 cycles

DURING THE STRUCTURE INSPECTION WE FOUND AT COCKPIT WINDSHIELD AREA, INNER SIDE OF THE UPPER ATTACHMENT OF THE SIDE POST AT FR4, T FITTING AT LH SIDE, INNER HOLE WITH CRACK INDICATION. CORRECTIVE ACTION: THE FITTING WAS REPAIRED AS PER AIRBUS INSTRUCTIONS AST STATED IN COOPESA ENGINEERING ORDER NUMBER: COO-EO-201-13720 R01 AND SEE COOPESA JOB: A1K268, ITEM 2-23 FOR DETAILS.

Part: MEGAPHONE — INOPERATIVE · airframe 48,542 hrs · 31,284 cycles

FA REPORTED FWD CABIN MEGAPHONE WEAK / REMOVED AND REPLACED MEGAPHONE PER AIRBUS A320 LOPA A1250001L03, OPS CHECK GOOD"

Part: EPSU — FAILED (13WL) · airframe 46,867 hrs · 30,372 cycles

AFTER STARTING EPSU BAT CAP TEST, FAILURE ""BAT/EPSU(13WL)AFT L"" APPEARED. / REF. TSM 33-51-00-810-857, R & R'D EPSU BATTERY (13WL) AFT L IAW AMM 33-51-38."

Part: FITTING — CRACKED (ZONE 200) · airframe 46,606 hrs · 30,241 cycles

PER CUSTOMER INSPECTION TASK, IT WAS FOUND ON LH AND RH WINDSHIELD SIDE POST UPPER ATTACHMENT FITTING - 2 EA HOLES WITH CRACK INDICATION. DUE TO THIS FACT DETAILS WERE SENT TO AIRBUS ASKING FOR REPAIR INSTRUCTIONS AND FINAL APPROVAL.

Part: BATTERY PACK — NO TEST (EMERGENCY LIGHTS) · airframe 46,052 hrs · 29,927 cycles

R/H (12WL) EMERGENCY LIGHT BATTERY PACK DISPLAYS FAILED ON EMERGENCY LIGHT TEST / REMOVED AND REPLACED R/H (12WL) EMERGENCY LIGHT BATTERY PACK PER AMM 33-51-38-000-002-A AND 33-51-38-400-002-A."

Part: BATTERY PACK — NO TEST (EMERGENCY LIGHTS) · airframe 46,052 hrs · 29,927 cycles

FWD L/H (10WL) EMERGENCY LIGHT BATTERY PACK DISPLAYS FAILED ON EMERGENCY LIGHT TEST / REMOVED AND REPLACED FWD L/H (10WL) EMERGENCY LIGHT BATTERY PACK PER AMM 33-51-38-000-002-A AND 33-51-38-400-002-A OPS CHECK GOOD."

Part: COVER — BROKEN (EMERGENCY LIGHT) · airframe 45,498 hrs · 29,649 cycles

RH WALL LIGHT EMERGENCY SIGN COVER BOTTOM LEFT & RIGHT COVER TABS BROKEN / REMOVED AND REPLACED RH BOTTOM LEFT & RIGHT WALL LIGHT EMERGENCY SIGN COVER IAW AMM 33-51-13-000-001-A & 33-51-13-400-001-A. THIS CLEARS M313 CONTROL # 05330001

Part: EPSU — NO TEST (EMERGENCY LIGHTS) · airframe 44,723 hrs · 29,231 cycles

EPSU 11WL FAULT DURING WEEKLY CHECK. C/W TSM 33-51-00-810-855-A. REMOVED AND REPLACED 11WL EPSU BATTERY, AS PER A319 AMM 33-51-38 PB401. OPS CHECKS GOOD, FAULT CLEARED.

Part: BATTERY — FAILED (CABIN) · airframe 44,304 hrs · 28,970 cycles

EMERGENCY LIGHT BATTERY FIN 11WL FAILED CAPACITY CHECK. REPLACED EMERGENCY LIGHT BATTERY FIN 11WL IAW AMM 33-51-38. OPS CHECK GOOD.

Part: BATTERY — DISCHARGED (CABIN) · airframe 44,032 hrs · 28,824 cycles

EPSU BATTERY FIN# 13WL FAILED EPSU BAT CAP TEST / REPLACED EPSU BATTERY"

Part: BLOWER — ODOR (CABIN) · airframe 41,679 hrs · 27,617 cycles

ELECTRICAL ODOR FROM VENTILATION SYSTEM. R&R BLOWER FAN".

Part: NOT REPORTED — LEAKING (HYDRAULIC SYS) · airframe 40,264 hrs · 26,916 cycles

STRONG DIRTY SOCK SMELL NOTICED DURING DESCENT, HYDRAULIC LEAK FOUND AT SERVICING BAY. R&R CHECK VALVE, RECIRC FILTERS, WATER INJECTORS, OZONE FILTERS AND PERFORMED DECONTAMINATION OF ECS.

Part: CONTROL UNIT — FAILED (MLG) · airframe 37,752 hrs · 25,763 cycles

DURING LANDING GEAR EXTENSION, ECAM DISPLAYED L/G LGCU 1&2 FAULT. ECAM PROCEDURE COMPLETED AND LANDING GRAVITY EXTENSION PROCEDURE COMPLETED. REMOVED AND REPLACE NLG SENSING MECHANISM AND PROX SENSOR 24GA & 25GA AND TARGETS PER MM 32-21-45-400-801A,32-31-73-200-002A. GEAR SWING CHECK GOOD PER MM 32-31-00720-002A. REMOVED AND REPLACED LGCUI 2 PER MM 32-31-71-400-001A POS CHECK GOOD PER MM 32-31-71-000-001A ALL WORK ACCOMPLISHED ON AERSALE W/O 000869 CARD 20002, 20004

Part: PROXIMITY SENSOR — FAILED (NLG) · airframe 37,752 hrs · 25,763 cycles

DUAL LGCIU FAILURE. EMERGENCY DECLARED. R & R THE NLG FLIGHT GROUND SENSING MECHANISM, PROXIMITY SENSOR, AND TARGETS.

Part: INTERFACE UNIT — FAILED (LANDING GEAR) · airframe 37,752 hrs · 25,763 cycles

EMERGENCY DECLARED, DUAL LGCIU FAILURE. CORRECTIVE ACTION PENDING-AC AOG.