AD 2021-23-05

Except as specified in paragraph (h) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, European Union Aviation Safety Agency (EASA) AD 2021-0177R1, dated September 21, 2021 (EASA AD 2021-0177R1).

(1) Where EASA AD 2021-0177R1 refers to “06 August 2021 [the effective date of the original issue of this AD],” this AD requires using September 14, 2021 (the effective date of AD 2021-18-08).

(2) Where EASA AD 2021-0177R1 refers to its effective date, this AD requires using the effective date of this AD.

(3) Paragraph (4) of EASA AD 2021-0177R1 specifies to “contact Airbus for approved instructions and, within the compliance time(s) specified in those instructions, accomplish those instructions accordingly” as an alternative corrective action if a defect is detected during inspection of an updated rod. As of the effective date of this AD, however, for that alternative, this AD requires repair of the defect 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.

(4) The “Remarks” section of EASA AD 2021-0177R1 does not apply to this AD.

Paragraph (8) of EASA AD 2021-0177R1 allows installation of an affected part if it is serviceable and inspected within 750 flight hours after installation. The Definitions section of EASA AD 2021-0177R1 requires that a serviceable affected part pass an inspection before the next flight after installation. Therefore, this AD allows installation of an affected serviceable part after the effective date of this AD if it is inspected before further flight after installation and 750 flight hours thereafter. All other provisions of paragraph (8) and Note 2 of EASA AD 2021-0177R1 apply to this AD, including the repetitive inspection of that part as required by paragraph (1) or (2) of EASA AD 2021-0177R1.

The following provisions also apply to this AD:

(1) Alternative Methods of Compliance (AMOCs): The Manager, Large Aircraft Section, 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 Large Aircraft Section, International Validation Branch, send it to the attention of the person identified in paragraph (k) of this AD. Information may be emailed to: 9-AVS-AIR-730-AMOC@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the responsible Flight Standards Office.

(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, 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) Required for Compliance (RC): Except as required by paragraph (j)(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.