Airworthiness directives › 2016-07-14
AD 2016-07-14 Airworthiness Directives; Airbus Airplanes
Models named: A319-111, -112, -113, -114, -115, -131, -132, -133, A320-211, -212. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
This AD applies to the airplanes identified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD, certificated in any category, all manufacturer serial numbers, except those on which Airbus Modification 30975 has been embodied in production. (1) Airbus Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes. (2) Airbus Model A320-211, -212, -214, -231, -232, and -233 airplanes. (3) Airbus Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes.
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
At the later of the times specified in paragraphs (g)(1) and (g)(2) of this AD: Replace the clips, shear webs, and angles at rear fuselage section 19, frame FR72 and FR74, and do all applicable related investigative actions before further flight, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1266, Revision 03, dated May 7, 2015. If any crack is found during any related investigative action required by this AD: Before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). (1) Before exceeding 48,000 flight cycles or 96,000 flight hours, whichever occurs first since the airplane's first flight. (2) Within 30 days after the effective date of this AD.
Unsafe condition
This AD was prompted by fatigue testing that determined that fatigue damage could appear on clips, shear webs, and angles at certain rear fuselage sections and certain frames. This AD is intended to complete certain mandated programs intended to support the airplane reaching its limit of validity of the engineering data that support the established structural maintenance program. We are issuing this AD to prevent fatigue damage on the clips, shear webs, and angles, which could affect the structural integrity of the airplane.
Affected ADs
None.
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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