Airworthiness Directive · Amendment 39-14458 · Airbus Model A310-203, -204, and -222 Airplanes, and Model A310-300 Series Airplanes
Airbus Model A310-203, -204, and -222 Airplanes, and Model A310-300 Series Airplanes
Superseded. A later AD replaced this one: AD 2009-18-16. Comply with the one in force.
This AD applies to Airbus Model A310-203, -204, and -222 airplanes, and Model A310-304, -322, -324, and -325 airplanes; certificated in any category; except those airplanes on which Airbus Modification 13023 has been accomplished in production.
The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A310-203, -204, and -222 airplanes, and Model A310-300 series airplanes. This AD requires a one-time rototest inspection for cracking of the frame foot and adjacent frames and skin in the area surrounding the frame foot run-outs from fuselage frames (FR) 43 through FR 46, and repair if necessary. This AD also requires modification of certain fastener holes. This AD results from a structural evaluation of Model A310 airplanes for widespread fatigue damage of the frame foot run-outs from FR 43 through FR 46. The evaluation revealed that, on in-service airplanes, undetected cracking in this area can lead to the rupture of the frame foot and subsequent cracking of the adjacent frames and fuselage skin. We are issuing this AD to prevent fatigue cracking of the frame foot run-outs, which could lead to rupture of the frame foot and cracking in adjacent frames and skin, and result in reduced structural integrity of the fuselage.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
At the later of the times specified in paragraphs (f)(1) and (f)(2) of this AD, perform a one-time rototest inspection for cracking of the frame foot and adjacent frames and skin in the area surrounding the frame foot run-outs from fuselage frame FR 43 through FR 46 by doing all the applicable actions specified in the Accomplishment Instructions of Airbus Service Bulletin A310-53-2124, dated April 4, 2005. Except as required by paragraph (g) of this AD, repair any cracking before further flight in accordance with the Accomplishment Instructions of the service bulletin. Before further flight after performing the inspection, modify the fastener holes located between FR 43 and FR 46 on the center box and on the upper fuselage bent sections in accordance with the Accomplishment Instructions of the service bulletin.
(1) Before the accumulation of the total flight-cycle or flight-hour threshold, whichever is first, specified in the Accomplishment Timescale table in paragraph 1.E.(2), “Compliance” of the service bulletin.
(2) At the earlier of the times specified in paragraphs (f)(2)(i) and (f)(2)(ii) of this AD.
(i) Before the accumulation of the total flight-cycle or flight-hour threshold, whichever is first, specified in Notes 01, 02, and 03 in paragraph 1.E.(2), “Compliance” of the service bulletin, after the effective date of this AD.
(ii) Within 3,000 flight cycles after the effective date of this AD.
For any cracking found during any inspection required by this AD for which the service bulletin specifies to contact the manufacturer for an appropriate repair: Before further flight, repair in accordance with a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the DGAC (or its delegated agent).
