Airworthiness Directive · Amendment 39-19577 · Wings
Airbus SAS Airplanes
Superseded. A later AD replaced this one: AD 2022-14-01. Comply with the one in force.
This AD applies to Airbus SAS Model A318-111, -112, -121, and -122 airplanes, Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes, Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes, and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes, certificated in any category, as identified in the European Aviation Safety Agency (EASA) AD 2018-0218, dated October 11, 2018; corrected October 26, 2018 (“EASA AD 2018-0218”).
We are adopting a new airworthiness directive (AD) for certain Airbus SAS Model A318 and A319 series airplanes, Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes, and Model A321-111, -112, - 131, -211, -212, -213, -231, and -232 airplanes. This AD was prompted by a report that taperloks used in a certain wing-to-fuselage junction were found to be non-compliant with the applicable specification, resulting in a loss of pre-tension in the fasteners. This AD requires repetitive special detailed inspections of the center and outer wing box lower stiffeners and panels at a certain junction on the left- and right-hand sides for any cracking, and repair if necessary, as specified in an European Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also provides an optional modification, which would terminate the repetitive inspections. We are issuing this AD to address the unsafe condition on these products.
Except as specified in paragraph (h) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, EASA AD 2018-0218.
(1) For purposes of determining compliance with the requirements of this AD: Where EASA AD 2018-0218 refers to its effective date, this AD requires using the effective date of this AD.
(2) The “Remarks” section of EASA AD 2018-0218 does not apply.
(3) Where EASA AD 2018-0218 refers to instructions provided by Airbus, for this AD, the instructions must be approved using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus SAS's EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature.
Accomplishing the actions required by this AD terminates all requirements of AD 2008-02-15.
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.
