Commonwealth legislation

AD/A320/52 - Rear Fuselage Skin Lap Joints

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legislative instrument

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Requires certain Airbus A319/A320/A321 aeroplanes (those listed in Airbus SB A320‑53‑1057 that do not have Mod 21905K2008) to undergo detailed visual or eddy‑current inspection of the upper rivet row at specified rear fuselage lap joints. Operators must inspect initially before 20,000 flights and re‑inspect every 4,000 flights if visual or every 12,000 flights if eddy‑current; completing Airbus SB A320‑53‑1056 after a crack‑free inspection cancels the recurring inspections. The directive aims to detect fatigue cracks that could cause loss of pressurisation; inspection and modification costs fall to aircraft operators.

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AD/A320/52 - Rear Fuselage Skin Lap Joints

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/A320/52 Rear Fuselage Skin Lap Joints 5/95

Applicability: A320 series aircraft, serial numbers in Airbus Industrie Service Bulletin (SB) A320- 53-1057, without Modification 21905K2008 incorporated.

Requirement: Inspect, using detailed visual or eddy current method, the upper rivet row of the longitudinal lap joints between:-

Frame 48 and Frame 64 next to stringer 6 LH and RH Frame 60 and Frame 64 next to stringer 32 LH

Frame 59 and Frame 64 next to stringer 32 RH Frame 58 and Frame 64 next to stringer 41 RH

Inspect in accordance with Airbus Industrie SB A320-53-1057.

Note: The inspection of stringer 32 RH lap joint is only applicable to aircraft SN 003, 004, 045 to 051, 056 and 057 which do not have the additional rear cargo door installed (modification number 20029).

Compliance: Initially inspect before 20 000 flights.

Re-inspect at intervals not to exceed:

4 000 flights, if last inspected visually; or,

ii. 12 000 flights, if last inspected by eddy current.

Note: Modification in accordance with Airbus Industrie SB A320-53-1056, after the inspection area has been shown to be crack free, cancels the inspection requirements of this AD.

Background: Cracks have been found in the longitudinal lap joints of the fatigue test specimen at 76000 flights. Inspections around NAS1097-5 rivets installed in upper skins which are less than 1.8 mm thick are required to prevent multi-site damage causing loss of pressurisation.

Source text

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

1 AD/A320/52 - Rear Fuselage Skin Lap Joints