Airworthiness Directive · Amendment 39-18459 · Fuselage
Airbus Airplanes
Superseded. A later AD replaced this one: AD 2020-26-15. Comply with the one in force.
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.
We are adopting a new airworthiness directive (AD) for certain Airbus Model A319, A320, and A321 series airplanes. This AD is intended to complete certain mandated programs intended to support the airplane reaching its limit of validity (LOV) of the engineering data that support the established structural maintenance program. This AD was prompted by fatigue testing that determined fatigue damage could appear on clips, shear webs, and angles at certain rear fuselage sections and certain frames. This AD requires replacing the clips, shear webs, and angles, including doing all applicable related investigative actions, and repair if necessary. We are issuing this AD to prevent fatigue damage on the clips, shear webs, and angles; such damage could affect the structural integrity of the airplane.
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.
For airplanes on which the replacement of clips, shear webs, and angles specified in Airbus Service Bulletin A320-53-1266 is done before accumulating 30,000 flight cycles or 60,000 flight hours, whichever occurred first since the airplane's first flight: Within 30,000 flight cycles or 60,000 flight hours, whichever occurs first after that replacement, do the replacement specified in paragraph (g) of this AD.
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.
