AD 2014-25-07 Airworthiness Directives; Airbus Airplanes

Models named: A320-211, -212, -214, -231, -232, -233. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to Airbus Model A320-211, -212, -214, -231, -232, and -233 airplanes, certificated in any category, all manufacturer serial numbers, except those on which Airbus Modification 31012 has been embodied in production.

Comply with this AD within the compliance times specified, unless already done.

At the applicable time specified in paragraph (g)(1), (g)(2), or (g)(3) of this AD: Do a special detailed inspection (rototest) for cracking of both sides of the splice plate of the FR47 butt joint crossing area, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1260, dated December 19, 2012. Repeat the inspection thereafter at intervals not to exceed 14,800 flight cycles or 29,600 flight hours, whichever occurs first. (1) For airplanes that, as of the effective date of this AD, have accumulated 44,000 or more total flight cycles or 88,000 or more total flight hours since first flight of the airplane: Do the inspection within 1,500 flight cycles or 3,000 flight hours after the effective date of this AD, whichever occurs first. (2) For airplanes that, as of the effective date of this AD, have accumulated 27,700 or more total flight cycles or 55,400 or more total flight hours, but fewer than 44,000 total flight cycles or 88,000 total flight hours since first flight of the airplane: Do the inspection within 3,000 flight cycles or 6,000 flight hours after the effective date of this AD, without exceeding 45,500 total flight cycles or 91,000 total flight hours since first flight of the airplane, whichever occurs first. (3) For airplanes that, as of the effective date of this AD, have accumulated fewer than 27,700 total flight cycles and less than 55,400 total flight hours since first flight of the airplane: Do the inspection before the accumulation of 30,700 total flight cycles or 61,400 total flight hours since first flight of the airplane, whichever occurs first.

This AD was prompted by a report of cracking at the splice plate of the frame (FR) 47 butt joint crossing area found during full-scale fatigue testing. We are issuing this AD to detect and correct fatigue cracking of the splice plate of the FR47 butt joint crossing area, which could result in reduced structural integrity of the airplane.

None.