AD 91-06-18
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Airbus SAS | A310-203 | Airworthiness Directives; AIRBUS INDUSTRIE Model A310-200 Series Airplanes |
| aircraft | Airbus SAS | A310-221 | Airworthiness Directives; AIRBUS INDUSTRIE Model A310-200 Series Airplanes |
| aircraft | Airbus SAS | A310-222 | Airworthiness Directives; AIRBUS INDUSTRIE Model A310-200 Series Airplanes |
Unsafe Condition
Cracks in the wing rear spar at bolt holes where the main landing gear forward pick-up fittings are attached, which could reduce structural integrity of the wings.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Perform a high frequency eddy current (HFEC) rototest inspection of the wing rear spar at specified bolt holes. Repeat inspections at intervals not exceeding 4,500 landings if no cracks are found. If cracks are found, repair prior to further flight and repeat inspections at approved intervals. Cold working of holes may extend spar life but requires subsequent inspections at 18,000 landings and then 12,000 landings intervals.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Prior to the accumulation of 12,000 landings, or within 1,000 landings after the effective date of this AD, whichever occurs later.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
AIRBUS INDUSTRIE Model A310-200 series airplanes, including A310-203, A310-221, A310-222, certificated in any category.
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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