Airworthiness Directive · Amendment 39-22394 · Fuselage
Airbus SAS Airplanes
This AD applies to Airbus SAS 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 European Aviation Safety Agency (EASA) AD 2022-0115, dated June 20, 2022 (EASA AD 2022-0115).
The FAA is superseding Airworthiness Directive (AD) 2019-18- 07, which applied to certain Airbus SAS 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. AD 2019-18-07 required repetitive rototest inspections of the open tack holes and rivet holes at the cargo floor support fittings of the fuselage, including doing all applicable related investigative actions and repair if necessary. AD 2019-18-07 also adds actions (modification) for certain airplanes. Since the FAA issued AD 2019-18-07, it was determined that certain airplanes need to do additional work. This AD continues to require the actions in AD 2019-18-07 and requires additional work for certain airplanes, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is 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 2022-0115.
(1) Where EASA AD 2022-0115 refers to January 3, 2014 (the effective date of EASA AD 2013-0310), this AD requires using October 2, 2015 (the effective date of AD 2015-17-14, Amendment 39-18247 (80 FR 52182, August 28, 2015) (AD 2015-17-14)).
(2) Where EASA AD 2022-0115 refers to November 9, 2018 (the effective date of EASA AD 2018-0233 at original issue), this AD requires using October 31, 2019 (the effective date of AD 2019-18-07).
(3) Where EASA AD 2022-0115 refers to its effective date, this AD requires using the effective date of this AD.
(4) Where paragraph (2) of EASA AD 2022-0115 specifies “contact Airbus for approved repair instructions and, within the compliance time identified therein, accomplish those instructions accordingly” if a crack is detected, for this AD if any cracking is detected, the cracking must be repaired before further flight using a method approved by the Manager, 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.
(5) The “Remarks” section of EASA AD 2022-0115 does not apply to this AD.
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, International Validation Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or responsible Flight Standards Office, as appropriate. If sending information directly to the International Validation Branch, send it to the attention of the person identified in paragraph (j) of this AD.
(i) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the responsible Flight Standards Office.
(ii) AMOCs approved previously for AD 2019-18-07 are approved as AMOCs for the corresponding provisions of EASA AD 2022-0115 that are required by paragraph (g) of this AD.
(iii) AMOCs approved previously for AD 2015-17-14 are approved as AMOCs for the corresponding provisions of EASA AD 2022-0115 that are required by paragraph (g) of this AD.
(2) Contacting the Manufacturer: For any requirement in this AD to obtain instructions from a manufacturer, the instructions must be accomplished using a method approved by the Manager, 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) Required for Compliance (RC): Except as required by paragraph (i)(2) of this AD, if any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC.
For more information about this AD, contact Todd Thompson, Aerospace Engineer, Large Aircraft Section, FAA, International Validation Branch, 2200 South 216th St., Des Moines, WA 98198; telephone 206-231-3228; email Todd.Thompson@faa.gov.
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.
