AD 96-07-08
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Airbus | A320-111 | Airworthiness Directives; Airbus Model A320-111 Series Airplanes |
Unsafe Condition
Fatigue cracking can initiate from the bolt holes in the splicing cap at nose forward Frame 8, leading to structural integrity compromise and potential rapid depressurization.
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Required Actions
Modify the splicing cap at Frame 8 by cold expansion of the fastener holes and installation of oversize fasteners in accordance with Airbus Service Bulletin A320-53-1005, Revision 1.
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Compliance Time
Prior to the accumulation of 16,000 total flight cycles, or within 6 months after the effective date of this AD (April 16, 1996), whichever occurs later.
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Affected Aircraft
Airbus Model A320-111 series airplanes with manufacturer's serial numbers 005, 006, 007, 008, 010, 011, and 012.
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Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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