AD 2025-23-09
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Airbus | SAS | Airworthiness Directives; Airbus SAS Airplanes |
Unsafe Condition
Cracks on the web horizontal flange and inner cap at frame (FR) 68, left-hand (LH) and right-hand (RH) sides, at stringer (STGR) 22, and additional cracks found at the door stop fitting number 1 holes at FR 68, which could result in reduced structural integrity of the fuselage.
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Required Actions
Conduct repetitive high frequency eddy current (HFEC) inspections for cracks on the web horizontal flange, inner cap, and door stop fitting number 1 holes at FR 68. Perform applicable corrective actions, including additional inspections for cracking, inspections to determine if a certain modification or repair was done, and repair of cracking at the web horizontal flange. Update procedures as specified in the service bulletin.
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Compliance Time
Within the compliance times specified in the service bulletin, with reduced compliance times for some inspections as outlined in this AD.
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Affected Aircraft
Airbus SAS Model A318 series airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes, except those airplanes with certain modifications installed that convert the airplane to a corporate jet.
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Source: Official FAA Source ↗
Retrieved: Apr 4, 2026
Rights: U.S. Government Public Domain
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