N808FR

ATA 3520

Part: SOLENOID — FAILED (OXYGEN SYSTEM) · airframe 6,276 hrs · 3,245 cycles

REFERENCE NON-ROUTINE 104851. DURING COMPLIANCE OF ENGINEERING ORDER A8-25EO-20453, BE AEROSPACE 120 PASSENGER SEAT CABIN CONFIGURATION, THE OXYGEN CONTAINER AT THE SECOND ROW OF SEATS ON THE RIGHT FAILED DROP TEST. MAINTENANCE REMOVED AND REPLACED THE OXYGEN CONTAINER PER AMM 35-21-10-000-001 AND AMM 35-21-41-400-001. OPERATIONAL CHECK PERFORMED WITH SATISFACTORY RESULTS IN ACCORDANCE WITH AMM 35-23-00-710-001.

ATA 3520

Part: SOLENOID — FAILED (OXYGEN SYSTEM) · airframe 6,276 hrs · 3,245 cycles

REFERENCE NON-ROUTINE 104853. DURING COMPLIANCE OF ENGINEERING ORDER A8-25EO-20453, BE AEROSPACE 120 PASSENGER SEAT CABIN CONFIGURATION, THE OXYGEN CONTAINER AT THE TWELFTH ROW OF SEATS ON THE LEFT FAILED DROP TEST. MAINTENANCE REMOVED AND REPLACED THE OXYGEN CONTAINER PER AMM 35-21-10-000-001 AND AMM 35-21-41-400-001. OPERATIONAL CHECK PERFORMED WITH SATISFACTORY RESULTS IN ACCORDANCE WITH AMM 35-23-00-710-001.

ATA 3520

Part: SOLENOID — FAILED (OXYGEN SYSTEM) · airframe 6,276 hrs · 3,245 cycles

REFERENCE NON-ROUTINE 104852. DURING COMPLIANCE OF ENGINEERING ORDER A8-25EO-20453, BE AEROSPACE 120 PASSENGER SEAT CABIN CONFIGURATION, THE OXYGEN CONTAINER AT THE FIFTEENTH ROW OF SEATS ON THE LEFT FAILED DROP TEST. MAINTENANCE REMOVED AND REPLACED THE OXYGEN CONTAINER PER AMM 35-21-10-000-001 AND AMM 35-21-41-400-001. OPERATIONAL CHECK PERFORMED WITH SATISFACTORY RESULTS IN ACCORDANCE WITH AMM 35-23-00-710-001.

ATA 5321

Part: FLOOR PANEL — DAMAGED (CARGO BAY) · airframe 5,912 hrs · 3,051 cycles

DURING C1 C-CHECK, INSPECTION NOTED FWD CARGO BAY FLOOR PANEL 131EG HAS PUNCTURES AND TEARS. MX REPAIRED THE FLOOR PANEL IAW THE REQUIREMENTS OF A318 SRM 53-02-00, FIGURE 204. UPON COMPLETION OF THE REPAIR, IT WAS INSPECTED AND FOUND ACCEPTABLE.

ATA 5321

Part: FLOOR PANEL — DAMAGED (CARGO BAY) · airframe 5,912 hrs · 3,051 cycles

DURING C1 C-CHECK, INSPECTION NOTED FWD CARGO BAY TRANSITION PANEL 132EG HAS PUNCTURES AND TEARS. MX REPAIRED THE FLOOR PANEL IAW THE REQUIREMENTS OF A318 SRM 53-02-00 PARA 8F AND EO A0-53F-12307. UPON COMPLETION OF THE REPAIR, IT WAS INSPECTED AND FOUND ACCEPTABLE.

ATA 5321

Part: FLOOR PANEL — DAMAGED (CARGO BAY) · airframe 5,912 hrs · 3,051 cycles

DURING C1 C-CHECK, INSPECTION NOTED FWD CARGO BAY FLOOR PANEL 131CG HAS PUNCTURES AND TEARS. MX REPAIRED THE FLOOR PANEL IAW THE REQUIREMENTS OF A318 SRM 53-02-00, FIGURE 204. UPON COMPLETION OF THE REPAIR, IT WAS INSPECTED AND FOUND ACCEPTABLE.

ATA 5321

Part: FLOOR PANEL — DAMAGED (CARGO BAY) · airframe 5,912 hrs · 3,051 cycles

DURING C1 C-CHECK, INSPECTION NOTED FWD CARGO BAY FLOOR PANEL 131DG HAS PUNCTURES AND TEARS. MX REPAIRED THE FLOOR PANEL IAW THE REQUIREMENTS OF A318 SRM 53-02-00, FIGURE 204. UPON COMPLETION OF THE REPAIR, IT WAS INSPECTED AND FOUND ACCEPTABLE.

ATA 5321

Part: FLOOR PANEL — DEBONDED (FUSELAGE) · airframe 5,912 hrs · 3,051 cycles

DURING C1 C-CHECK, INSPECTION NOTED THE TOP SKIN OF FLOOR PANEL 151CH WAS DISBONDED FROM THE CORE. DAMAGE WAS FOUND TO BE BEYOND REPAIRABLE LIMITS. MX REMOVED AND REPLACED THE FLOOR PANEL IAW THE REQUIREMENTS OF A318 AMM 53-42-14-400-001. UPON COMPLETION OF THE REPAIR, IT WAS INSPECTED AND FOUND ACCEPTABLE.

ATA 5321

Part: FLOOR PANEL — DEBONDED (FUSELAGE) · airframe 5,912 hrs · 3,051 cycles

DURING C1 C-CHECK, INSPECTION NOTED THE TOP SKIN OF FLOOR PANEL 151DH WAS DISBONDED FROM THE CORE. DAMAGE WAS FOUND TO BE BEYOND REPAIRABLE LIMITS. MX REMOVED AND REPLACED THE FLOOR PANEL IAW THE REQUIREMENTS OF A318 AMM 53-42-14-400-001. UPON COMPLETION OF THE REPAIR, IT WAS INSPECTED AND FOUND ACCEPTABLE.

ATA 5321

Part: FLOOR PANEL — DAMAGED (CARGO BAY) · airframe 5,912 hrs · 3,051 cycles

DURING C1 C-CHECK, INSPECTION NOTED FWD CARGO BAY FLOOR PANEL 131BF HAS PUNCTURES AND TEARS. MX REPAIRED THE FLOOR PANEL IAW THE REQUIREMENTS OF A318 SRM 53-02-00, FIGURE 204. UPON COMPLETION OF THE REPAIR, IT WAS INSPECTED AND FOUND ACCEPTABLE.

ATA 5321

Part: FLOOR PANEL — DAMAGED (CARGO BAY) · airframe 5,912 hrs · 3,051 cycles

DURING C1 C-CHECK, INSPECTION NOTED FWD CARGO BAY FLOOR PANEL 131AF HAS PUNCTURES AND TEARS. MX REPAIRED THE FLOOR PANEL IAW THE REQUIREMENTS OF A318 SRM 53-02-00, FIGURE 204. UPON COMPLETION OF THE REPAIR, IT WAS INSPECTED AND FOUND ACCEPTABLE.

ATA 5321

Part: FLOOR PANEL — DEBONDED (FUSELAGE) · airframe 5,912 hrs · 3,051 cycles

DURING C1 C-CHECK, INSPECTION NOTED THE TOP SKIN OF FLOOR PANEL 151BH WAS DISBONDED FROM THE CORE. DAMAGE WAS FOUND TO BE BEYOND REPAIRABLE LIMITS. MX REMOVED AND REPLACED THE FLOOR PANEL IAW THE REQUIREMENTS OF A318 AMM 53-42-14-400-001. UPON COMPLETION OF THE REPAIR, IT WAS INSPECTED AND FOUND ACCEPTABLE.

ATA 5321

Part: FLOOR PANEL — DAMAGED · airframe 5,335 hrs · 2,726 cycles

LINE MAINT NOTED THE AFT CARGO COMPARTMENT FLOOR PANEL 151DH WAS DAMAGED. MAINT REPAIRED FLOOR PANEL 151DH IAW SRM 53-02-00 FIGURE 204. UPON COMPLETION OF THE REPAIR IT WAS INSPECTED AND FOUND ACCEPTABLE. (A)

ATA 5321

Part: FLOOR PANEL — DAMAGED (FUSELAGE) · airframe 5,335 hrs · 2,726 cycles

LINE MAINT NOTED THE AFT CARGO COMPARTMENT TRANSITION PANEL 151FH WAS DAMAGED. MAINT REPAIRED TRANSITION PANEL 151FH IAW SRM 53-02-00 FIGURE 204. UPON COMPLETION OF THE REPAIR IT WAS INSPECTED AND FOUND ACCEPTABLE. (A)

ATA 5321

Part: FLOOR PANEL — DAMAGED (FUSELAGE) · airframe 5,335 hrs · 2,726 cycles

LINE MAINT NOTED THE AFT CARGO COMPARTMENT FLOOR PANEL 151CH WAS DAMAGED. MAINT REPAIRED FLOOR PANEL 151CH IAW SRM 53-02-00 FIGURE 204. UPON COMPLETION OF THE REPAIR IT WAS INSPECTED AND FOUND ACCEPTABLE. (A)

ATA 2120

Part: UNKNOWN — SMOKE (COCKPIT/CABIN) · airframe 3,979 hrs · 2,036 cycles

DURING LANDING ROLL OUT, THE FLIGHT CREW REPORTED WHITE/GRAY SMOKE AND ACRID ODOR IN THE COCKPIT AND PASSENGER CABIN. MAINTENANCE PERFORMED IDLE LEAK CHECK OF BOTH ENGINES IN ACCORDANCE WITH THE REQUIREMENTS OF AMM 71-00-00-710-006 AND PERFORMED A CHECK OF THE PACK SYSTEM OPERATION IAW AMM 21-26-00-710-001-01. A FOD INSPECTION WAS CONDUCTED OF BOTH ENGINES IAW MP 72400-01. ALL SYSTEMS CHECK NORMAL AND THE ACFT RETURNED TO SERVICE. ENGINEERING NOTED THIS SITUATION HAS OCCURRED IN THE PAST AND HAS BEEN LINKED TO DE-ICING FLUID ON THE RUNWAY BEING INGESTED INTO THE AIR HANDLING SYSTEM ON LANDING.