AD 2009-19-01
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Airbus | A300 B2-1C | Airworthiness Directives; Airbus Model A300 B2-1C, B2-203, B2K-3C, B4-103, B4-203, and B4-2C Airplanes |
| aircraft | Aviat | Various | Airworthiness Directives; Airbus Model A300 B2-1C, B2-203, B2K-3C, B4-103, B4-203, and B4-2C Airplanes |
Unsafe Condition
The centre hinge bracket developed a fatigue crack causing complete failure of the bracket, leading to the detachment of the centre flap inner tab and subsequent failure of the inboard and outboard links.
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Required Actions
Perform a high frequency eddy current inspection of the center hinge bracket of the center flap inner tab (on both wings) to detect fatigue cracks, in accordance with Airbus Mandatory Service Bulletin A300-57-0250, Revision 01. Replace the bracket when cracks are detected. Repeat inspections at intervals not to exceed 850 flight hours.
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Compliance Time
Within the specified intervals as outlined in Table 1 or Table 2 of the AD.
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Affected Aircraft
Airbus Model A300 B2-1C, B2-203, B2K-3C, B4-103, B4-203, and B4-2C airplanes, certificated in any category, all serial numbers, except airplanes which have been modified in accordance with Airbus Mandatory Service Bulletin A300-57-0252 (Airbus Modification 13400).
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Source: Official FAA Source ↗
Retrieved: Apr 4, 2026
Rights: U.S. Government Public Domain
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