Airworthiness Directive · Amendment 39-16018 · Wings
Airbus Model A300 B2-1C, B2-203, B2K-3C, B4-103, B4-203, and B4-2C Airplanes
This AD applies to 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).
We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as:
Unless already done, do the following actions.
(1) At the times specified in Table 1 or Table 2 of this AD, as applicable, perform a high frequency eddy current inspection to detect fatigue cracks of the center hinge bracket of the center flap inner tab (on both wings), in accordance with Airbus Mandatory Service Bulletin A300-57-0250, Revision 01, dated September 29, 2008. If no cracking is found, repeat the inspection thereafter at intervals not to exceed 850 flight cycles.
| Flight cycles accumulated since first flight as of the effective date of this AD | Compliance time |
|---|---|
| Less than 6,000 flight cycles | Prior to accumulating 6,000 flight cycles since first flight or within 90 days after the effective date of this AD, whichever occurs later. |
| 6,000 flight cycles or more, but less than 12,000 flight cycles | Within 850 flight cycles after the effective date of this AD. |
| 12,000 flight cycles or more | Within 500 flight cycles after the effective date of this AD. |
| Flight cycles accumulated since Airbus Service Bulletin A300-57-0205 modification as of the effective date of this AD | Compliance time |
|---|---|
| Less than 6,000 flight cycles | Prior to accumulating 6,000 flight cycles since Airbus Service Bulletin A300-57-0205 modification or within 90 days after the effective date of this AD, whichever occurs later. |
| 6,000 flight cycles or more, but less than 12,000 flight cycles | Within 850 flight cycles after the effective date of this AD. |
| 12,000 flight cycles or more | Within 500 flight cycles after the effective date of this AD. |
(2) If any crack is detected during any inspection required by this AD, before further flight, replace the center hinge bracket in the accordance with Airbus Mandatory Service Bulletin A300-57-0250, Revision 01, dated September 29, 2008. Within 6,000 flight cycles after replacing the center hinge bracket, do the inspection required by paragraph (f)(1) of this AD, and if no cracking is found, repeat the inspection thereafter at intervals not to exceed 850 flight cycles.
(3) Modifying the inboard tab of the center flaps in accordance with Airbus Mandatory Service Bulletin A300-57-0252, dated August 27, 2008, terminates the requirements of this AD.
(4) Actions accomplished before the effective date of this AD in accordance with Airbus Mandatory Service Bulletin A300-57-0250, dated November 2, 2007, are considered acceptable for compliance with the corresponding actions specified in this AD.
Note 1: This AD differs from the MCAI and/or service information as follows: Although the European Aviation Safety Agency AD 2007-0299R2, dated October 28, 2008 and Airbus Mandatory Service Bulletin A300-57-0250, dated November 2, 2007, specify to submit certain information to the manufacturer, this AD does not include that requirement.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
