Airworthiness Directive · Amendment 39-22899 · Equipment/furnishings
Airbus SAS Airplanes
This AD applies to all Airbus SAS Model airplanes identified in paragraphs (c)(1) through (4) of this AD, certificated in any category.
(1) Model A318-111, -112, -121, and -122 airplanes.
(2) Model A319-111, -112, -113, -114, -115, -131, -132, -133, -151N, -153N, and -171N airplanes.
(3) Model A320-211, -212, -214, -216, -231, -232, -233, -251N, -252N, -253N, -271N, -272N, and -273N airplanes.
(4) Model A321-111, -112, -131, -211, -212, -213, -231, -232, -251N, -251NX, -252N, -252NX, -253N, -253NX, -271N, -271NX, -272N, and -272NX airplanes.
The FAA is superseding Airworthiness Directive (AD) 2022-24- 05, which applied to all Airbus SAS Model A318, A319, A320, and A321 series airplanes. AD 2022-24-05 required repetitive inspections of certain galleys for corrosion of trolley retainer aluminum blocks and delamination of the upper panel of the trolley compartment, and applicable corrective action. This AD was prompted by the list of affected galleys being revised, and a new modification that was developed to restore the design integrity of the affected galleys. This AD continues to require the actions in AD 2022-24-05, provides optional terminating action for the repetitive inspections, revises the list of affected parts, and prohibits the installation of affected parts under certain conditions; 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, European Union Aviation Safety Agency (EASA) AD 2024-0038, dated February 5, 2024 (EASA AD 2024-0038).
(1) Where EASA AD 2024-0038 refers to “18 August 2021 [the effective date of the EASA AD 2021-0183 at original issue],” this AD requires using January 9, 2023 (the effective date of AD 2022-24-05).
(2) Where EASA AD 2024-0038 refers to its effective date, this AD requires using the effective date of this AD.
(3) This AD does not adopt the “Remarks” section of EASA AD 2024-0038.
(4) Where EASA AD 2024-0038 does not specify corrective action after a post-repair inspection that has findings of damage, this AD requires obtaining repair instructions before further flight from the FAA, EASA, or Airbus SAS's EASA Design Organization Approval (DOA), and accomplishing those actions accordingly. Any approval by the DOA must include the DOA-authorized signature.
(5) Where EASA AD 2024-0038 defines an affected part as “Forward-facing galleys, having a Part Number (P/N) as listed in Appendix 1 of this AD,” for this AD, replace that text with “Forward-facing galleys, having a Part Number (P/N) as listed in Appendix 1 of this AD, or having P/N 601891-006801.”
Although material referenced in EASA AD 2024-0038 specifies to submit certain information to the manufacturer, this AD does not include that requirement.
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 manager of the International Validation Branch, mail it to the address identified in paragraph (k) of this AD. Information may be emailed to: 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, 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 material 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 Timothy Dowling, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: 817-222-5102; email: Timothy.P.Dowling@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.
