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

Airworthiness Directive - AD/A320/45 - Fuselage - Fasteners at Skin Panel to Frame 13 and 14 Joint Airworthiness Directive - AD/A320/45 - Fuselage - Fasteners at Skin Panel to Frame 13 and 14 Joint CASA Airworthiness Directive Jurisdiction:Commonwealth of Australia;CorporateName:Civil Aviation Safety Authority; Issue 5/1995,Aircraft above 5700 kg,Airbus Industrie A319, A320 and A321 Series Aeroplanes,Fuselage - Fasteners at Skin Panel to Frame 13 and 14 Joint,45 DellaCa, Donna 2 0 2022-10-27T03:32:00Z 2022-10-27T03:32:00Z 1 147 840 Office of Parliamentary Counsel 7 1 986 16.0000 2006-09-22T00:00:00Z Toolkit http://www.activepdf.com 2022-10-27T00:00:00Z 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.