AD/A320/45 - Fuselage - Fasteners at Skin Panel to Frame 13 and 14 Joint

Administered by Department of Infrastructure, Transport, Regional Development, Communications, Sport and the Arts

Legislation au F2006B01935 In force Legislative Instrument

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

SCHEDULE OF AIRWORTHINESS DIRECTIVES

 


Airbus Industrie A319, A320 and A321 Series Aeroplanes

 

AD/A320/45 Fuselage - Fasteners at Skin Panel to Frame 13 and 14 Joint

Applicability: A320 series aircraft MSN 005 to 030 inclusive.


5/95

 

Requirement: Perform an external detailed visual inspection for missing or broken rivet heads at fuselage frames 13 and 14 on the left and right hand sides between stringers 1 and 7. Inspect in accordance with Airbus Industrie SB A320-53-1036.

 

Note: DGAC AD 92-199-028(B) refers.

 

Compliance: Inspect before 10000 flights or before 27 May 1995, whichever is the later. Repeat inspections at intervals not exceeding 6000 flights.

 

Modification in accordance with Airbus Industrie SB A320-53-1010 cancels the requirement of this AD.

 

Background: A number of damaged or missing rivet heads were found on the fatigue test article.

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

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Sourced from the Federal Register of Legislation at 26 August 2026. For the latest information on Australian Government law please go to https://www.legislation.gov.au.