Commonwealth legislation

AD/A320/50 - Fuselage - Lower Forward Corner of Cockpit Sliding Window Frame

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Commonwealth

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legislative instrument

Plain English Summary

3/10 complexity

This Airworthiness Directive requires operators of specified Airbus A319/A320/A321 serial-numbered aircraft to inspect the lower forward corner of the cockpit sliding-window frame at fuselage frame 4 using high-frequency eddy-current testing. Initial inspection is required before 15,000 flights and then at 15,000-flight intervals; frames with cracks follow a service‑bulletin reinspection schedule.

Operators must follow Airbus Service Bulletin A320‑53‑1082, bear inspection costs, and may remove the inspection obligation by completing the modification in Service Bulletin A320‑53‑1044. The AD responds to cracks found in a fatigue test.

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AD/A320/50 - Fuselage - Lower Forward Corner of Cockpit Sliding Window Frame

COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY

SCHEDULE OF AIRWORTHINESS DIRECTIVES

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Airbus Industrie A319, A320 and A321 Series Aeroplanes

AD/A320/50 Fuselage - Lower Forward Corner of

Cockpit Sliding Window Frame

5/95

Applicability: Airbus Industrie A320 aircraft serial number 002 to 008, 010 to 014, 016 to 078 and 080 to 098 inclusive. This AD is applicable to aircraft serial number 003 and 004 on the left hand window frame only and for serial number 023 applicable to the right hand window frame only.

Requirement: Inspect, using high frequency eddy current, the lower forward corner of the sliding window frame at fuselage frame 4. Inspect, in accordance with Airbus Industrie Service Bulletin A320-53-1082, around the five fasteners specified in Fig 1.

Note: DGAC AD 94-166-056(B) refers.

Compliance: Initially inspect before 15000 flights.

Re-inspect frames without cracks at 15000 flight intervals.

Re-inspect frames with cracks in accordance with the schedule specified in paragraph B(2)(b) of Airbus Industrie Service Bulletin A320-53-1082.

Note: Modification in accordance with Airbus Industrie Service Bulletin A320-53- 1044 cancels the inspection requirements of this AD.

This AD is effective from 27 April 1995.

Background: Cracks were found on the lower forward corner of the sliding window frame at frame 4 during the full scale fatigue test.

Source text

Sourced from the Federal Register of Legislation (legislation.gov.au), CC BY 4.0.

1 AD/A320/50 - Fuselage - Lower Forward Corner of Cockpit Sliding Window Frame