AD 2017-07-07
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Airbus | A330-200 | Airworthiness Directives; Airbus Airplanes |
Unsafe Condition
Cracking at fastener holes located at frame 40 on the lower shell panel junction, which could lead to 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 rototest inspections of 10 fastener holes at frame 40 lower shell panel junction on both left-hand and right-hand sides. Accomplish corrective actions, including oversizing, installing fasteners, and repairs, as necessary. Perform related investigative actions, such as rototest inspections for cracking after oversizing.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within 20,000 flight cycles or 65,400 flight hours to 20,800 flight cycles or 68,300 flight hours, depending on airplane utilization and configuration.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Airbus Model A330-200, A330-300, A340-200, and A340-300 series airplanes post-modification 44360 and pre-modification 55792 (fuselage reinforcement at frame 40 in production).
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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