AD 99-02-08
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Airbus | A330-301 | Airworthiness Directives; Airbus Model A330-301, -321, -322, -341, -342, and A340-211, -212, -213, -311, -312, and -313 Series Airplanes |
| aircraft | Airbus | A330-321 | Airworthiness Directives; Airbus Model A330-301, -321, -322, -341, -342, and A340-211, -212, -213, -311, -312, and -313 Series Airplanes |
| aircraft | Airbus | A330-322 | Airworthiness Directives; Airbus Model A330-301, -321, -322, -341, -342, and A340-211, -212, -213, -311, -312, and -313 Series Airplanes |
| aircraft | Airbus | A330-341 | Airworthiness Directives; Airbus Model A330-301, -321, -322, -341, -342, and A340-211, -212, -213, -311, -312, and -313 Series Airplanes |
| aircraft | Airbus | A330-342 | Airworthiness Directives; Airbus Model A330-301, -321, -322, -341, -342, and A340-211, -212, -213, -311, -312, and -313 Series Airplanes |
| aircraft | Airbus | A340-211 | Airworthiness Directives; Airbus Model A330-301, -321, -322, -341, -342, and A340-211, -212, -213, -311, -312, and -313 Series Airplanes |
| aircraft | Airbus | A340-212 | Airworthiness Directives; Airbus Model A330-301, -321, -322, -341, -342, and A340-211, -212, -213, -311, -312, and -313 Series Airplanes |
| aircraft | Airbus | A340-213 | Airworthiness Directives; Airbus Model A330-301, -321, -322, -341, -342, and A340-211, -212, -213, -311, -312, and -313 Series Airplanes |
| aircraft | Airbus | A340-311 | Airworthiness Directives; Airbus Model A330-301, -321, -322, -341, -342, and A340-211, -212, -213, -311, -312, and -313 Series Airplanes |
| aircraft | Airbus | A340-312 | Airworthiness Directives; Airbus Model A330-301, -321, -322, -341, -342, and A340-211, -212, -213, -311, -312, and -313 Series Airplanes |
Unsafe Condition
Fatigue cracking of the inner flange of the rear fuselage frame FR73A between beams 5 and 6, which could result 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 high-frequency eddy current inspections to detect cracking; perform corrective actions (reworking, replacing affected area, or modifying with reworking, flap peening, and reinforcing strap installation) if necessary. Optional terminating actions include modifications to eliminate repetitive inspections.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Effective February 3, 1999.
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Affected Aircraft
Airbus Model A330-301, -321, -322, -341, -342, and A340-211, -212, -213, -311, -312, and -313 series airplanes.
AI-generated summary from the source AD text. Verify against the official source before acting.
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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