AD 2016-18-09
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Airbus | A318 | Airworthiness Directives; Airbus Airplanes |
Unsafe Condition
Chafing damage on the fuselage skin at the bottom of frame (FR) 34 junction between stringer (STR) 43 left hand (LH) side and right hand (RH) side, underneath the fairing structure, caused by contact between the fairing nut plate and the fuselage. This could lead to crack initiation and propagation, possibly resulting in reduced structural integrity of the fuselage.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Conduct repetitive detailed inspections for chafing damage on the fuselage skin at frame (FR) 34. Perform a special detailed inspection of external fuselage skin panels for any cracking, measure crack length and remaining thickness, and take corrective actions such as repair or modification of the fuselage skin panel as necessary.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within 12 months of the effective date of the AD.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Airbus Model A318, A319, and A320 series airplanes, as specified in the referenced service information.
AI-generated summary from the source AD text. Verify against the official source before acting.
Source: Official FAA Source ↗
Retrieved: Apr 6, 2026
Rights: U.S. Government Public Domain
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