AD 98-06-24
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Airbus SAS | A330-301 | Airworthiness Directives; Airbus Model A330 and A340 Series Airplanes |
| aircraft | Airbus SAS | A340-211 | Airworthiness Directives; Airbus Model A330 and A340 Series Airplanes |
| aircraft | Airbus SAS | A340-212 | Airworthiness Directives; Airbus Model A330 and A340 Series Airplanes |
| aircraft | Airbus SAS | A340-213 | Airworthiness Directives; Airbus Model A330 and A340 Series Airplanes |
| aircraft | Airbus SAS | A340-311 | Airworthiness Directives; Airbus Model A330 and A340 Series Airplanes |
| aircraft | Airbus SAS | A340-312 | Airworthiness Directives; Airbus Model A330 and A340 Series Airplanes |
| aircraft | Airbus SAS | A340-313 | Airworthiness Directives; Airbus Model A330 and A340 Series Airplanes |
Unsafe Condition
Fatigue cracking of fuselage frames at the lowest inboard bolt hole at the frame splice area and shear clip attachment on fuselage frames 48 to 53, which could result in reduced structural integrity of the airplane.
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Required Actions
Reinforce the joints of fuselage frames 53, 53.1, and 53.2 by adding two joint straps, replacing existing fasteners with new fasteners, and replacing existing clips with machined clips in accordance with specified Airbus Service Bulletins.
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Compliance Time
Prior to the accumulation of 4,100 total flight cycles, or within 500 flight cycles after the effective date of this AD, whichever occurs later (for A340 series and A330 series with Modification 43475); or prior to 4,600 total flight cycles or within 500 flight cycles after the effective date, whichever is later (for A330 series without Modification 43475).
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Affected Aircraft
Airbus Model A330 and A340 series airplanes on which Modification 42409 has not been accomplished, including specific models: A330-301, A340-211, A340-212, A340-213, A340-311, A340-312, A340-313.
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Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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