N229NV

Part: CONTROL VALVE — FAULTED (CABIN AIR) · airframe 76,404 hrs · 29,593 cycles

(AIRCRAFT NOT GROUNDED) (EMERGENCY DECLARED) AIR PACK 1&2 FAULT, CREW DECLARED AN EMERGENCY AND EXPEDITED DESCENT TO 10,000. PASSENGER OXYGEN MASK DID NOT DEPLOY. / AIR PACK 2 FAULT IS DUE TO MEL 21-52-01-C. REMOVED AND REPLACED PACK 1 FLOW CONTROL VALVE IAW AMM 21-51-51-400-001-A. OPS AND LEAK CHECK GOOD. PACK 1 FAULT MSG CLEARED AT THIS TIME."

Part: POWER SUPPLY — FAILED (EMERGENCY LIGHTS) · airframe 75,826 hrs · 29,332 cycles

REF. W/O # 501776-3, DURING OPERATIONAL TEST OF THE EMERGENCY LIGHTING SYSTEM, EPSU UNIT FWD L FAILED. / "

Part: DOOR FRAME — CRACKED (FRM 68) · airframe 75,752 hrs · 29,296 cycles

(MAJOR REPAIR- DISCREPANCY NOTED DURING HEAVY MX VISIT) PASSENGER COMPARTMENT, FR68 WEB LH SIDE, CRACK FOUND AT STOP FITTING #1 LOWER INBD HOLE. / PASSENGER COMPARTMENT, FR68 WEB LH SIDE AT STOP FITTING #1 LOWER INBD. HOLE PERMANENTLY REPAIRED PER SRM 53-41-12-300-010 REV.148. REPAIR CATEGORY B, SEE SRI 53-41-12-205-009 TABLE 2 REV.148 FOR INSPECTION REQUIERMENTS: INSPECTION THRESHOLD FROM TIME OF REPAIR EMBODIMENT: 24500FC (FH NOT RELEVANT), SUBSEQUENT INSPECTIONS: 10700FC (FH NOT RELEVANT), INSPECTION METHOD: HFEC (REFER TO NTM CHAPTER 51-10-08) AND ROTOTEST (REFER TO AMM TASK 53-41-00-220-813) INSPECTION APPLICABILITY: FOR HOLE REPAIRED BY BUSHES WITHOUT REMOVING BUSH, DO HFEC AT THE FRAME WEB AROUND THE HOLES AND DO ROTOTEST AT INNER HOLE OF THE BUSHING. SEE AWS FOR DETAILS."

Part: DOOR FRAME — DAMAGED (FRM 68) · airframe 75,752 hrs · 29,296 cycles

(MAJOR REPAIR- DISCREPANCY NOTED DURING HEAVY MX VISIT) PASSENGER COMPARTMENT, FR68 WEB LH SIDE, CRACK FOUND AT STOP FITTING #1 LOWER INBD HOLE. / PASSENGER COMPARTMENT, FR68 WEB LH SIDE AT STOP FITTING #1 LOWER INBD. HOLE PERMANENTLY REPAIRED PER SRM 53-41-12-300-010 REV.148. REPAIR CATEGORY B, SEE SRI 53-41-12-205-009 TABLE 2 REV.148 FOR INSPECTION REQUIERMENTS: INSPECTION THRESHOLD FROM TIME OF REPAIR EMBODIMENT: 24500FC (FH NOT RELEVANT), SUBSEQUENT INSPECTIONS: 10700FC (FH NOT RELEVANT), INSPECTION METHOD: HFEC (REFER TO NTM CHAPTER 51-10-08) AND ROTOTEST (REFER TO AMM TASK 53-41-00-220-813) INSPECTION APPLICABILITY: FOR HOLE REPAIRED BY BUSHES WITHOUT REMOVING BUSH, DO HFEC AT THE FRAME WEB AROUND THE HOLES AND DO ROTOTEST AT INNER HOLE OF THE BUSHING. SEE AWS FOR DETAILS. M313 - CONTROL #990002292"

Part: FITTING — CORRODED (GIRT BAR) · airframe 75,752 hrs · 29,296 cycles

(MAJOR REPAIR- DISCREPANCY NOTED DURING HEAVY MX VISIT) R1 DOOR CUTOUT, LOWER SILL BEAM, FWD GIRT BAR FITTING AREA CORROSION FOUND AROUND ALL FOUR HOLES AND AFT GIRT BAR FITTING AREA CORROSION FOUND AROUND FWD OUTBD HOLE AND FWD AND AFT INBD. HOLES. / R1 DOOR CUTOUT LOWER SILL BEAM FWD GIRT BAR FITTINGS AREA AROUND ALL FOUR HOLES AND AFT GIRT BAR FITTINGS AREA AROUND FWD OUTBOARD HOLE, FWD / AFT INBOARD HOLES, PERMANENTLY REPAIRED AS PER SRM 53-11-14-283-005 REV 148. ALLOWABLE TASK (REPAIR) CLASSIFIED REPAIR CATEGORY B WITH FITURE INSPECTIONS REQUIRED AS PER SRI 53-11-14-205-001 REV 148. FROM AIRCRAFT FIRST FLIGHT THRESHOLD: 60 000FC / FH NOT RELEVANT, INTERVAL: TBD AND INSPECTION METHOD: TBD. SEE AWS FOR DETAILS AND NDT REPORT MWO: 57523-9. SEE EO E5311-0020 REV 00 FOR GIRT BAR FITTINGS ASSY INSTALLATION."

Part: DOOR SILL — CORRODED (R1 DOOR) · airframe 75,752 hrs · 29,296 cycles

(MAJOR REPAIR- DISCREPANCY NOTED DURING HEAVY MX VISIT) R1 DOOR CUTOUT, LOWER SILL BEAM, FWD GIRT BAR FITTING AREA CORROSION FOUND AROUND ALL FOUR HOLES AND AFT GIRT BAR FITTING AREA CORROSION FOUND AROUND FWD OUTBD HOLE AND FWD AND AFT INBD. HOLES. / R1 DOOR CUTOUT LOWER SILL BEAM FWD GIRT BAR FITTINGS AREA AROUND ALL FOUR HOLES AND AFT GIRT BAR FITTINGS AREA AROUND FWD OUTBOARD HOLE, FWD / AFT INBOARD HOLES, PERMANENTLY REPAIRED AS PER SRM 53-11-14-283-005 REV 148. ALLOWABLE TASK (REPAIR) CLASSIFIED REPAIR CATEGORY B WITH FITURE INSPECTIONS REQUIRED AS PER SRI 53-11-14-205-001 REV 148. FROM AIRCRAFT FIRST FLIGHT THRESHOLD: 60 000FC / FH NOT RELEVANT, INTERVAL: TBD AND INSPECTION METHOD: TBD. SEE AWS FOR DETAILS AND NDT REPORT MWO: 57523-9. SEE EO E5311-0020 REV 00 FOR GIRT BAR FITTINGS ASSY INSTALLATION."

Part: LIGHT — FAULTED (ZONE 200) · airframe 75,572 hrs · 29,221 cycles

EMERGENCY EXIT LIGHTS FOR OVERWING DOORS NOT WORKING (12WL AND 11WL). PERFORMED OPS TEST OF OVERWING EMERGENCY LIGHTS IAW A320 AMM 33-51-15-400-001-A. OPS CHECK GOOD, NO DEFECTS NOTED.

Part: EPSU — UNKNOWN (UNKNOWN) · airframe 75,471 hrs · 29,179 cycles

REPORTED BY FLT CREW, EMER LIGHT BETWEEN R/H EMER EXIT WINDOWS INOP. / ACCOMPLISHED BITE IAW AMM 33-51-00-710-001A, R EPSU 12WL FAULTED. REMOVED & REPLACED EPSU 12WL IAW AMM 33-51-38-000-001A AND 33-51-38-400-001A. OPS CHECK NORMAL."

Part: EPSU — UNKNOWN · airframe 74,310 hrs · 28,603 cycles

LEFT EMERGENCY BATT (11WL) AND AFT EPSU BATT (13WL) FAILED EPSU TEST. / REPLACED LEFT EMERGENCY EPSU BATT (11WL) AND AFT EPSU BATT (13WL) W/REF TO AMM 33-51-38 PB 401. OPS CHECK GOOD."

Part: LGCIU — UNKNOWN (UNKNOWN) · airframe 74,260 hrs · 28,577 cycles

(EMERGENCY DECLARED) UPON GEAR RETRACTION NOTICED RT RED GEAR LT WITH UNLOCKED CONFIRMED WITH SECONDARY INDICATION WITH WHEEL STATUS. PERFORMED ECAM PROCEDURE AND CYCLED GEAR UNDER 220 KTS. WITH GEAR CYCLE COMPLETE MAJOR RUMBLING FROM GEAR AND STILL SHOWING RT SIDE RED. LOWERED GEAR AND LANDED SMOOTH AND NO ABNORMALS.//PERFORMED TSM 32-31-00-810-837-A AND TSM 32-31-00-810-867-A CLEANED SEALANT FROM PROX SENSOR 8GA, PERFORMED GEAR SWING IAW AMM 32-31-00-720-002-A FOUND LGCIU 1 (5GA1) AT FAULT , REPLACED LGCIU #1 IAW AMM 32-31-71-PB-401 OPS CHECK GOOD."

Part: SKIN PANEL — CORRODED (ZONE 600) · airframe 73,852 hrs · 28,378 cycles

DURING THE INSPECTION PER EWIS TASK IT WAS FOUND THE RH WING, EXTERNAL TOP SKIN PANEL BETWEEN RIB3 AND RIB4, 130MM TO THE REAR SPAR, SKIN WITH CORROSION. THE AREA WAS REPAIRED IAW AIRBUS DOSSIER 81172750. SEE COOPESA WORK ORDER A1N017, 6-33 FOR FURTHER DETAILS.

Part: SKIN PANEL — CORRODED (ZONE 500) · airframe 73,852 hrs · 28,378 cycles

DURING THE INSPECTION PER EWIS TASK IT WAS FOUND THE LH WING, EXTERNAL TOP SKIN PANEL BETWEEN RIB24 AND RIB25 ON TRAILING EDGE OVERHANG PANEL SKIN WITH CORROSION. THE AREA WAS REPAIRED IAW AIRBUS DOSSIER 81173299. SEE COOPESA WORK ORDER A1N017, 5-33 FOR FURTHER DETAILS.

Part: SKIN PANEL — CORRODED (ZONE 500) · airframe 73,852 hrs · 28,378 cycles

DURING THE INSPECTION PER EWIS TASK IT WAS FOUND THE LH WING, EXTERNAL TOP SKIN PANEL 2 BETWEEN RIB10 AND RIB11 ON STRINGER16, SKIN WITH CORROSION. THE AREA WAS REPAIRED IAW AIRBUS DOSSIER 81173299. SEE COOPESA WORK ORDER A1N017, 5-22 FOR FURTHER DETAILS.

Part: FLOORBEAM — CORRODED (ZONE 200) · airframe 73,852 hrs · 28,378 cycles

DURING THE CORROSION TASK INSPECTION IT WAS FOUND AT UPPER FUSELAGE, AFT ENTRY CABIN, WET AREA AT FR68, -Y1292, THE FLOOR BEAM WITH CORROSION. THE DAMAGED PART WAS REPLACED BY A NEWONE PER SRM 51-72-11-911-001 AND AIRBUS DRAWING D53472780. SEE COOPESA WORK ORDER A1N017, 2-29 FOR FURTHER DETAILS.

Part: SKIN PANEL — CORRODED (ZONE 600) · airframe 73,852 hrs · 28,378 cycles

DURING THE INSPECTION PER EWIS TASK IT WAS FOUND THE RH WING, EXTERNAL TOP SKIN PANEL 2 BETWEEN RIB12 AND RIB13 ON STRINGER14, SKIN WITH CORROSION. THE AREA WAS REPAIRED IAW AIRBUS DOSSIER 81172750. SEE COOPESA WORK ORDER A1N017, 6-20 FOR FURTHER DETAILS.

Part: SKIN PANEL — CORRODED (ZONE 600) · airframe 73,852 hrs · 28,378 cycles

DURING THE ACCOMPLISHMENT OF ALLEGIANT ZL-500-03-1-002_P1-OP-UP/0 EWIS TASK, IT WAS FOUND THE RH WING, EXTERNAL TOP SKIN PANEL 2, AT THE STG 14RH BETWEEN RIB 12 AND RIB 13 SKIN WITH CORROSION. DUE TO THERE IS NOT SRM AVAILABLE TO PERFORM PERMANENT REPAIR, AIRBUS WAS CONTACTED REQUESTING REPAIR INSTRUCTIONS AND FINAL APPROVAL, UNDER AIRBUS DOSSIER 81172750 AND COOPESA JOB A1N017 ITEM 6-20

Part: SKIN PANEL — CORRODED (ZONE 600) · airframe 73,852 hrs · 28,378 cycles

DURING THE ACCOMPLISHMENT OF ALLEGIANT ZL-500-03-1-002_P1-OP-UP/0 EWIS TASK, IT WAS FOUND THE RH WING, EXTERNAL TOP SKIN PANEL 2 AT THE REAR SPAR BETWEEN RIB 4 AND RIB 5 SKIN WITH CORROSION. DUE TO THERE IS NOT SRM AVAILABLE TO PERFORM PERMANENT REPAIR, AIRBUS WAS CONTACTED REQUESTING REPAIR INSTRUCTIONS AND FINAL APPROVAL, UNDER AIRBUS DOSSIER 81172750 AND COOPESA JOB A1N017 ITEM 6-33

Part: SKIN PANEL — CORRODED (ZONE 600) · airframe 73,852 hrs · 28,378 cycles

DURING THE ACCOMPLISHMENT OF ALLEGIANT ZL-500-03-1-002_P1-OP-UP/0 EWIS TASK, IT WAS FOUND THE RH WING, EXTERNAL TOP SKIN PANEL 2 AT THE STG 16RH BETWEEN RIB 11 AND RIB 12 SKIN WITH CORROSION. DUE TO THERE IS NOT SRM AVAILABLE TO PERFORM PERMANENT REPAIR, AIRBUS WAS CONTACTED REQUESTING REPAIR INSTRUCTIONS AND FINAL APPROVAL, UNDER AIRBUS DOSSIER 81172750 AND COOPESA JOB A1N017 ITEM 6-18

Part: SKIN PANEL — CORRODED (ZONE 600) · airframe 73,852 hrs · 28,378 cycles

DURING THE ACCOMPLISHMENT OF ALLEGIANT ZL-500-03-1-002_P1-OP-UP/0 EWIS TASK, IT WAS FOUND THE RH WING, EXTERNAL TOP SKIN PANEL 2 AT THE STG 15RH BETWEEN RIB 11 AND RIB 12 SKIN WITH CORROSION. DUE TO THERE IS NOT SRM AVAILABLE TO PERFORM PERMANENT REPAIR, AIRBUS WAS CONTACTED REQUESTING REPAIR INSTRUCTIONS AND FINAL APPROVAL, UNDER AIRBUS DOSSIER 81172750 AND COOPESA JOB A1N017 ITEM 6-43

Part: SKIN PANEL — CORRODED (ZONE 600) · airframe 73,852 hrs · 28,378 cycles

DURING THE ACCOMPLISHMENT OF ALLEGIANT ZL-500-03-1-002_P1-OP-UP/0 EWIS TASK, IT WAS FOUND THE RH WING, EXTERNAL TOP SKIN PANEL 2, AT STG 16RH BETWEEN RIB 14 AND RIB 16 SKIN WITH CORROSION. DUE TO THERE IS NOT SRM AVAILABLE TO PERFORM PERMANENT REPAIR, AIRBUS WAS CONTACTED REQUESTING REPAIR INSTRUCTIONS AND FINAL APPROVAL, UNDER AIRBUS DOSSIER 81172750 AND COOPESA JOB A1N017 ITEM 6-23

Part: SKIN PANEL — CORRODED (ZONE 600) · airframe 73,852 hrs · 28,378 cycles

DURING THE ACCOMPLISHMENT OF ALLEGIANT ZL-500-03-1-002_P1-OP-UP/0 EWIS TASK, IT WAS FOUND THE RH WING, EXTERNAL TOP SKIN PANEL 2 FROM AT THE STG 14RH BETWEEN RIB 10 AND RIB 11 SKIN WITH CORROSION. DUE TO THERE IS NOT SRM AVAILABLE TO PERFORM PERMANENT REPAIR, AIRBUS WAS CONTACTED REQUESTING REPAIR INSTRUCTIONS AND FINAL APPROVAL, UNDER AIRBUS DOSSIER 81172750 AND COOPESA JOB A1N017 ITEM 6-17

Part: SKIN PANEL — CORRODED (ZONE 600) · airframe 73,852 hrs · 28,378 cycles

DURING THE ACCOMPLISHMENT OF ALLEGIANT ZL-500-03-1-002_P1-OP-UP/0 EWIS TASK, IT WAS FOUND THE RH WING, EXTERNAL TOP SKIN PANEL 2 AT THE STG 15RH BETWEEN RIB 11 AND RIB 12 SKIN WITH CORROSION. DUE TO THERE IS NOT SRM AVAILABLE TO PERFORM PERMANENT REPAIR, AIRBUS WAS CONTACTED REQUESTING REPAIR INSTRUCTIONS AND FINAL APPROVAL, UNDER AIRBUS DOSSIER 81172750 AND COOPESA JOB A1N017 ITEM 6-19

Part: SKIN PANEL — CORRODED (ZONE 500) · airframe 73,852 hrs · 28,378 cycles

DURING THE ACCOMPLISHMENT OF ALLEGIANT ZL-500-03-1-002_P1-OP-UP/0 EWIS TASK, IT WAS FOUND THE LH WING, EXTERNAL TOP SKIN PANEL 2 FROM BETWEEN RIB 25 AND RIB 26 ON TRAILING EDGE OVERHANG SKIN WITH CORROSION. DUE THIS CONDITION WAS REPORTED TO AIRBUS. AIRBUS PROVIDED REPAIR INSTRUCTIONS UNDER DOSSIER 81173299 AND REPAIR WAS DOCUMENTED UNDER COOPESA JOB A1N017 ITEM 5-39).

Part: SKIN PANEL — CORRODED (ZONE 500) · airframe 73,852 hrs · 28,378 cycles

DURING THE ACCOMPLISHMENT OF ALLEGIANT ZL-500-03-1-002_P1-OP-UP/0 EWIS TASK, IT WAS FOUND THE LH WING, EXTERNAL TOP SKIN PANEL 2 FROM BETWEEN BETWEEN RIB 13 AND RIB 14 ON STGR16 SKIN WITH CORROSION. DUE THIS FACT THIS CONDITION WAS REPORTED TO AIRBUS. AIRBUS PROVIDED REPAIR INSTRUCTIONS UNDER DOSSIER 81173299 AND REPAIR WAS DOCUMENTED UNDER COOPESA JOB A1N017 ITEM 5-23).

Part: SKIN PANEL — CORRODED (ZONE 500) · airframe 73,852 hrs · 28,378 cycles

DURING THE ACCOMPLISHMENT OF ALLEGIANT ZL-500-03-1-002_P1-OP-UP/0 EWIS TASK, IT WAS FOUND THE LH WING, EXTERNAL TOP SKIN PANEL 2 FROM BETWEEN RIB 18 + 270MM ON FRONT SPAR SKIN WITH CORROSION. DUE THIS CONDITION WAS REPORTED TO AIRBUS. AIRBUS PROVIDED REPAIR INSTRUCTIONS UNDER DOSSIER 81173299 AND REPAIR WAS DOCUMENTED UNDER COOPESA JOB A1N017 ITEM 5-39).

Part: FITTING — CRACKED (ZONE 200) · airframe 73,852 hrs · 28,378 cycles

DURING THE ACCOMPLISHMENT OF ALLEGIANT EO E5316-002 RELATED TO AD 2022-02-11 PARAGRAPH G AND SB53-1330, IT WAS FOUND THE FWD SERVICE DOOR AND FWD ENTRY DOOR WITH CRACK INDICATION AT FR20 R/H DOOR STOP FITTING #1 AND WEB AREA WITH CRACK INDICATION. DUE TO THERE IS NOT SRM AVAILABLE TO PERFORM PERMANENT REPAIR, AIRBUS WAS CONTACTED REQUESTING REPAIR INSTRUCTIONS AND FINAL APPROVAL, UNDER AIRBUS DOSSIER 81171398 AND COOPESA JOB A1N017 ITEM 2-26

Part: SKIN PANEL — CORRODED (ZONE 500) · airframe 73,852 hrs · 28,378 cycles

DURING THE ACCOMPLISHMENT OF ALLEGIANT ZL-500-03-1-002_P1-OP-UP/0 EWIS TASK, IT WAS FOUND THE LH WING, EXTERNAL TOP SKIN PANEL 2 FROM BETWEEN BETWEEN RIB 13 AND RIB 14 ON STGR16 SKIN WITH CORROSION. DUE THIS CONDITION WAS REPORTED TO AIRBUS. AIRBUS PROVIDED REPAIR INSTRUCTIONS UNDER DOSSIER 81173299 AND REPAIR WAS DOCUMENTED UNDER COOPESA JOB A1N017 ITEM 5-23).

Part: SKIN PANEL — CORRODED (ZONE 500) · airframe 73,852 hrs · 28,378 cycles

DURING THE ACCOMPLISHMENT OF ALLEGIANT ZL-500-03-1-002_P1-OP-UP/0 EWIS TASK, IT WAS FOUND THE LH WING, EXTERNAL TOP SKIN PANEL 2 FROM BETWEEN RIB 15 AND RIB 16 AND 50MM + STGR16 SKIN WITH CORROSION. DUE THIS FACT THIS CONDITION WAS REPORTED TO AIRBUS. AIRBUS PROVIDED REPAIR INSTRUCTIONS UNDER DOSSIER 81173299 AND REPAIR WAS DOCUMENTED UNDER COOPESA JOB A1N017 ITEM 5-24).

Part: SKIN PANEL — CORRODED (ZONE 500) · airframe 73,852 hrs · 28,378 cycles

•DURING THE ACCOMPLISHMENT OF ALLEGIANT ZL-500-03-1-002_P1-OP-UP/0 EWIS TASK, IT WAS FOUND THE LH WING, EXTERNAL TOP SKIN PANEL 2 FROM BETWEEN RIB 24 AND RIB 25 ON TRAILING EDGE OVERHANG SKIN WITH CORROSION. DUE THIS CONDITION WAS REPORTED TO AIRBUS. •AIRBUS PROVIDED REPAIR INSTRUCTIONS UNDER DOSSIER 81173299 AND REPAIR WAS DOCUMENTED UNDER COOPESA JOB A1N017 ITEM 5-33).

Part: FITTING — CRACKED (ZONE 200) · airframe 73,852 hrs · 28,378 cycles

DURING THE ACCOMPLISHMENT OF ALLEGIANT EO E5316-002 RELATED TO AD 2022-02-11 PARAGRAPH G AND SB53-1330, IT WAS FOUND THE FWD SERVICE DOOR AND FWD ENTRY DOOR WITH CRACK INDICATION AT FR16 R/H DOOR STOP FITTING #7 WITH CRACK INDICATION. DUE TO THERE IS NOT SRM AVAILABLE TO PERFORM PERMANENT REPAIR, AIRBUS WAS CONTACTED REQUESTING REPAIR INSTRUCTIONS AND FINAL APPROVAL, UNDER AIRBUS DOSSIER 81171398 AND COOPESA JOB A1N017 ITEM 2-24

Part: SKIN PANEL — CORRODED (ZONE 500) · airframe 73,852 hrs · 28,378 cycles

DURING THE ACCOMPLISHMENT OF ALLEGIANT ZL-500-03-1-002_P1-OP-UP/0 EWIS TASK, IT WAS FOUND THE LH WING, EXTERNAL TOP SKIN PANEL 2 FROM BETWEEN BETWEEN RIB 9 AND RIB 10 ON TRAILING EDGE OVERHANG SKIN WITH CORROSION. DUE THIS CONDITION WAS REPORTED TO AIRBUS. AIRBUS PROVIDED REPAIR INSTRUCTIONS UNDER DOSSIER 81173299 AND REPAIR WAS DOCUMENTED UNDER COOPESA JOB A1N017 ITEM 5-26).

Part: FRAME — CRACKED (ZONE 200) · airframe 73,852 hrs · 28,378 cycles

DURING THE ACCOMPLISHMENT OF ALLEGIANT EO E5316-002 RELATED TO AD 2022-02-11 PARAGRAPH G AND SB53-1330, IT WAS FOUND THE FWD SERVICE DOOR AND FWD ENTRY DOOR WITH CRACK INDICATION AT FR20 L/H DOOR STOP FITTING #1 AREA WITH CRACK INDICATION. DUE TO THERE IS NOT SRM AVAILABLE TO PERFORM PERMANENT REPAIR, AIRBUS WAS CONTACTED REQUESTING REPAIR INSTRUCTIONS AND FINAL APPROVAL, UNDER AIRBUS DOSSIER 81171398 AND COOPESA JOB A1N017 ITEM 2-27

Part: SKIN PANEL — CORRODED (ZONE 500) · airframe 73,852 hrs · 28,378 cycles

DURING THE ACCOMPLISHMENT OF ALLEGIANT ZL-500-03-1-002_P1-OP-UP/0 EWIS TASK, IT WAS FOUND THE LH WING, EXTERNAL TOP SKIN PANEL 2 FROM BETWEEN BETWEEN RIB 12 ON STGR14 SKIN WITH CORROSION. DUE THIS CONDITION WAS REPORTED TO AIRBUS. AIRBUS PROVIDED REPAIR INSTRUCTIONS UNDER DOSSIER 81173299 AND REPAIR WAS DOCUMENTED UNDER COOPESA JOB A1N017 ITEM 5-40

Part: SKIN PANEL — CORRODED (ZONE 500) · airframe 73,852 hrs · 28,378 cycles

DURING THE ACCOMPLISHMENT OF ALLEGIANT ZL-500-03-1-002_P1-OP-UP/0 EWIS TASK, IT WAS FOUND THE LH WING, EXTERNAL TOP SKIN PANEL 2 FROM BETWEEN RIB 14 + 350MM ON REAR SPAR SKIN SKIN WITH CORROSION. DUE THIS FACT THIS CONDITION WAS REPORTED TO AIRBUS. AIRBUS PROVIDED REPAIR INSTRUCTIONS UNDER DOSSIER 81173299 AND REPAIR WAS DOCUMENTED UNDER COOPESA JOB A1N017 ITEM 5-43).

Part: EPSU — FAILED · airframe 72,017 hrs · 27,464 cycles

FOWARD EMERGENCY LIGHTS WONT TURN ON / REPLACED EPSU BATTERY IAW AMM 33-51-38. OPS CHECK GOOD."

Part: NONE — NONE · airframe 71,960 hrs · 27,434 cycles

SEVERAL EMERGENCY EXIT LIGHTS INOP AT LT AND RT OVERWING EXITS, R2, AND L2 DOORS. / REPLACED INOP LIGHTS AT LT AND RT OVERWING EXITS, R2, AND L2 DOORS IAW AMM 33-51-16, OPERATIONAL CHECK SATISFACTORY."

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 70,320 hrs · 26,587 cycles

ROW 12 EXIT SIGNS LIGHTS INOP. / REMOVED AND REPLACED EMERGENCY BATTERY @ POSITION 11WL W/REF TO AMM 35-51-38 PB 401. OPS CHECK GOOD . OK FOR SERVICE."

Part: BULB — INOPERATIVE (EMERGENCY LIGHT) · airframe 69,531 hrs · 26,186 cycles

EMERGENCY EXIT SIGN ON EMERGENCY EXIT ROW A/C RIGHT HAS BULBS INOPERABLE. REPLACED AFFECTED BULBS, REF AMM 33-51-16.

Part: BULB — INOPERATIVE (EMERGENCY LIGHT) · airframe 69,531 hrs · 26,186 cycles

R2 DOOR EMERGENCY EXIT SIGN HAS BULBS INOPERABLE. REPLACED AFFECTED BULBS, REF AMM 33-51-16.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 68,955 hrs · 25,890 cycles

DURING WEEKLY EMERGENCY LIGHT CHECK THROUGH CFDS FOUND EPSU BATTERY AFT L FAULT MESSAGE. / REF TSM 33-51-00-810-802-A REMOVED AND REPLACED AFT CABIN EPSU BATTERY PER AMM 33-51-38-000-002 AND 33-51-38-400-002. OPS CHECK GOOD. FAULT MESSAGE EXTINGUISHED."

Part: BATTERY PACK — DISCHARGED (CABIN) · airframe 68,273 hrs · 25,557 cycles

EPSU FAILED EMERGENCY LIGHTING R TEST / REPLACED EMERGENCY BATTER PACK "

Part: BATTERY PACK — DISCHARGED (CABIN) · airframe 68,273 hrs · 25,557 cycles

EPSU FAILED EMERGENCY LIGHTING L TEST / REPLACED EMERGENCY BATTER PACK "

Part: LIGHT — INOPERATIVE (CABIN) · airframe 68,074 hrs · 25,464 cycles

EMERGENCY EXIT LIGHT DAMAGED AND REMOVED / REPLACED R/H FWD EMERGENCY EXIT LIGHT"

Part: EPSU — INOPERATIVE (EMERGENCY LIGHTS) · airframe 68,074 hrs · 25,464 cycles

EMERGENCY LIGHTING ACTIVATION FAILED TEST/REPLACED BATTERIES"

Part: CIDS — MALFUNCTIONED · airframe 65,765 hrs · 24,333 cycles

EMERGENCY EVACUATION HORN STARTED SPURIOUSLY. R & R THE NR 2 CIDS DIRECTOR.

Part: UNKNOWN — ODOR (CABIN & COCKPIT) · airframe 64,573 hrs · 23,723 cycles

DIRTY SOCK SMELL IN COCKPIT AND FORWARD CABIN. ACCOMPLISHED ECS DECONTAMINATION, R&R PLENUM SEALS, AND PACK PLENUM CHAMBER.

Part: APU — CONTAMINATED · airframe 64,313 hrs · 23,584 cycles

DIRTY SOCK ODOR DURING DESCENT. FOUND APU COMPLETELY SOAKED IN OIL. PERFORMED AND COMPLETED A DECONTAMINATION OR THE ENVIRONMENTAL CONTROL SYSTEM. REPLACED BOTH RECIRCULATION FILTERS.

Part: SKIN — CORRODED (HORIZONTAL STAB) · airframe 60,815 hrs · 21,888 cycles

LEFT HORIZONTAL STABILIZER UPPER SKIN CORRODED. REPLACED THE SKIN SRM 55-13-11 AND SRM 51-77-11-026.

Part: SKIN — CORRODED (HORIZONTAL STAB) · airframe 60,815 hrs · 21,888 cycles

RIGHT HORIZONTAL STABILIZER UPPER SKIN CORRODED IN SEVERAL AREAS. REMOVED CORRODED SKIN AREAS SRM 51-77-13-911-013 AND SRM 55-13-11, FABRICATED AND INSTALLED A REPAIR FOR SKIN AREAS AND REPAIR DOUBLERS IAW SRM 51-77-13-911-013 AND SRM 55-13-11.

Part: SKIN — CRACKED (FRAME 47) · airframe 60,815 hrs · 21,888 cycles

FRAME 47 FUSELAGE SKIN AND SPLICE CRACKED. REPAIRED IAW ERO R533-00010.

Part: PUMP — LEAKING (APU) · airframe 45,915 hrs · 21,853 cycles

FA'S REPORT FOUL SMELL FROM VENTILATION SYSTEM WHEN AIRCRAFT IS BELOW 10,000 FT. FOUND APU OIL PUMP ASSY LEAKING. R & R THE APU OIL PUMP.

Part: STRUCTURE — VIBRATION (FUSELAGE) · airframe 57,459 hrs · 20,191 cycles

CLIMBING THROUGH FL300 AT .77 WE ENCOUNTERED AIRFRAME VIBRATION. IAW QRH 56.18 WE DISCONNECTED AUTOPILOT 1 & APPLIED LT RUDDER, WHICH DAMPENED THE VIBRATION. UPON DELETION OF VIBRATION WE RE-CONNECTED AUTOPILOT 1 WHILE CRUISING AT FL 250 & M.78 WE RE-ENCOUNTERED VIBRATION & APPLIED PREVIOUSLY MENTIONED PROCEDURE. THIS OCCURRED TWO DIFFERENT TIMES. PERFORMED POST FLIGHT INSPECTION OF AIRFRAME, CHECKED WINGS, ENGS FUSELAGE & TAIL SECTION FOR APPARENT LOSS OF DAMAGED PANELS. NO DEFECTS NOTED AT THIS TIME. ACFT OK FOR RETURN TO SERVICE IAW AMM 05-50-00.

Part: FLASHLIGHT — INOPERATIVE (CABIN) · airframe 57,444 hrs · 20,184 cycles

AFT FLIGHT ATTENDANT RT FLASHLIGHT, LIGHT NOT BLINKING. DEFERRED TO MEL 25-60-08A DMI 20650, PLACARD INSTALLED.

Part: FLASHLIGHT — NO TEST (CABIN) · airframe 57,392 hrs · 20,160 cycles

FORWARD FLIGHT ATTENDANT FLASHLIGHT WILL NOT TEST. TRANSFERRED FWD FLIGHT ATTENDANT FLASHLIGHT TO MEL 25-60-08A CAT C DMI 20466, PLACARD INSTALLED.

Part: BATTERY — DISCHARGED (FLASHLIGHT) · airframe 57,254 hrs · 20,090 cycles

FORWARD FLIGHT ATTENDANT FLASHLIGHT INOPERATIVE. PLACED ON MEL 25-60-08A CAT C, PLACARDS INSTALLED. REPLACED BATTERY & OPERATIONS CHECKED GOOD IAW MM 25-65-53-400-002-A. THIS TERMINATES MEL 25-60-08A & PLACARDS REMOVED.