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

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.