AD/A320/45 - Fuselage - Fasteners at Skin Panel to Frame 13 and 14 Joint
1AD/A320/45 - Fuselage - Fasteners at Skin Panel to Frame 13 and 14 Joint
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meta-content-style-type: text/css meta-content-type: application/xhtml+xml; charset=utf-8 meta-description: CASA Airworthiness Directive meta-generator: Aspose.Words for .NET 22.10.0 meta-keywords: 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 title: Airworthiness Directive - AD/A320/45 - Fuselage - Fasteners at Skin Panel to Frame 13 and 14 Joint
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COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Image unavailable in extracted text 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.