Airworthiness directives › 2014-19-04
AD 2014-19-04 Airworthiness Directives; Airbus Airplanes
Models named: A320-111, -211, -212, -231. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
This AD applies to Airbus Model A320-111, -211, -212, and -231 airplanes, certificated in any category, all manufacturer serial numbers.
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
This paragraph restates the requirements of paragraph (b) of AD 2004-03-19, Amendment 39-13463 (69 FR 5922, February 9, 2004). For Model A320-111, -211, and -231 airplanes on which the modification specified in AD 98-12-18, Amendment 39-10573 (63 FR 31345, June 9, 1998), has not been done: Do the applicable inspections specified in paragraphs (g)(1) and (g)(2) of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1028, Revision 01, dated February 12, 2002. (1) For airplanes on which the inspections required by AD 98-12-18, Amendment 39-10573 (63 FR 31345, June 9, 1998), have been done: Within 12,000 flight cycles after accomplishment of the last inspection required by AD 98-12-18, do a detailed inspection of the transition angle and a rotating probe inspection of the pick-up angle in the lower part of the center fuselage area for cracking. (2) For airplanes on which the inspections required by AD 98-12-18, Amendment 39-10573 (63 FR 31345, June 9, 1998), have not been done: At the later of the times specified in paragraphs (g)(2)(i) and (g)(2)(ii) of this AD, do a detailed inspection of the transition angle and a rotating probe inspection of the pick-up angle in the lower part of the center fuselage area for cracking. (i) Before the accumulation of 10,400 total flight cycles, or 24,600 total flight hours, whichever is first. (ii) Before the accumulation of 16,000 total flight cycles, or within 3,500 flight cycles after March 15, 2004 (the effective date of AD 2004-03-19, Amendment 39-13463 (69 FR 5922, February 9, 2004), whichever is first.
Unsafe condition
This AD was prompted by the determination that the modification must be accomplished in order to address the unsafe condition. We are issuing this AD to prevent fatigue cracking in the transition and pick-up angles of the lower part of the center fuselage, which could result in reduced structural integrity of the wing-fuselage support and fuselage pressure vessel.
Affected ADs
This AD replaces AD 2004-03-19, Amendment 39-13463 (69 FR 5922, February 9, 2004).
Read the original on the Federal Register →
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The directive text above is reproduced from the Federal Register, a work of the United States government and in the public domain. The separation into applicability, compliance and required actions is TrackAD's.*1