Airworthiness Directive · Amendment 39-21686 · Fuselage
Airbus SAS Airplanes
This AD applies to Airbus SAS airplanes specified in paragraphs (c)(1) through (3) of this AD, certificated in any category, as identified in European Union Aviation Safety Agency (EASA) AD 2020-0280, dated December 14, 2020 (EASA AD 2020-0280).
(1) Model A318-111, -112, and -122 airplanes.
(2) Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes.
(3) Model A320-211, -212, -214, -231, -232, and -233 airplanes.
The FAA is correcting an airworthiness directive (AD) that was published in the Federal Register. That AD applies to certain Airbus SAS Model A318-111, -112, and -122 airplanes; Model A319-111, -112, - 113, -114, -115, -131, -132, and -133 airplanes; and Model A320-211, - 212, -214, -231, -232, and -233 airplanes. As published, the AD number specified in the preamble and regulatory text is incorrect. This document corrects this error. In all other respects, the original document remains the same.
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 2020-0280.
(1) Where EASA AD 2020-0280 refers to its effective date, this AD requires using the effective date of this AD.
(2) Where paragraph (9) of EASA AD 2020-0280 specifies if any crack is found during any inspection to “contact Airbus for approved repair instructions and accomplish those instructions accordingly,” this AD requires if any cracking is found, the cracking must be repaired before further flight using a method approved by the Manager, Large Aircraft Section, International Validation 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.
(3) Where paragraph (10) of EASA AD 2020-0280 specifies credit for actions “in accordance with the instructions of an Airbus Repair Design Approval Sheet (RDAS), [and to] accomplish the next inspection of each repaired area in accordance with the instructions of, and within the compliance time as specified in, the applicable RDAS,” this AD requires using “in accordance with repair instructions approved, and within the compliance time specified in the repair approval, using a method approved by the Manager, Large Aircraft Section, International Validation Branch, FAA; or EASA; or Airbus SAS's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature.”
(4) Where paragraph (11) of EASA AD 2020-0280 specifies terminating actions apply only if specified “in the Airbus RDAS instructions for a repaired aeroplane,” this AD requires using “in repair instructions approved using a method approved by the Manager, Large Aircraft Section, International Validation Branch, FAA; or EASA; or Airbus SAS's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature.”
(5) The “Remarks” section of EASA AD 2020-0280 does not apply to this AD.
Although the service information referenced in EASA AD 2020-0280 specifies to submit certain information to the manufacturer, this AD does not include that requirement.
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.
