AD 2004-14-06
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Airbus | A310 | Airworthiness Directives; Airbus Model A310 Series Airplanes |
Unsafe Condition
Fatigue cracking and corrosion around and under chafing plates of the wing root between fuselage frame 36 and frame 39, which could result in reduced structural integrity of the airplane.
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Required Actions
Perform repetitive inspections to detect discrepancies around and under the chafing plates of the wing root, in accordance with Airbus Service Bulletin A310-53-2069, Revision 05 or earlier revisions. If any discrepancy is found, accomplish follow-on corrective actions such as removal of corrosion, corrosion protection, high frequency eddy current inspection, or x-ray inspection. Repeat inspections at intervals specified in the applicable service bulletin. Review airplane maintenance records to determine if corrosion was detected and reworked on frame 39, stringer 35, and perform an inspection for fatigue cracking if corrective actions were previously accomplished.
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Compliance Time
Within 4 years since date of manufacture, or within 12 months after June 3, 1998, whichever occurs later, for initial inspection. Repeat inspections at intervals specified in the applicable service bulletin. Review of maintenance records and fatigue cracking inspection within 30 days after the effective date of this AD.
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Affected Aircraft
Airbus Model A310 series airplanes on which Airbus Modifications 8888 and 8889 have not been accomplished, certificated in any category.
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Source: Official FAA Source ↗
Retrieved: Apr 4, 2026
Rights: U.S. Government Public Domain
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