Airworthiness Directive · Amendment 39-23046 · Fuselage
Airbus SAS Airplanes
This AD applies to all Airbus SAS airplanes specified in paragraphs (c)(1) through (6) of this AD, certificated in any category.
(1) Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes.
(2) Model A320-211, -212, -214, -216, -231, -232, -233, -251N, -252N, -253N, -271N, -272N, and -273N airplanes.
(3) Model A321-211, -212, -213, -231, -232, -251N, -251NX, -252N, -252NX, -253N, -253NX, -253NY, -271N, -271NX, -272N, and -272NX airplanes.
(4) Model A330-201, -202, -203, -223, -243, -301, -302, -303, -321, -322, -323, -341, -342, -343, -841, and -941 airplanes.
(5) Model A350-941 and -1041 airplanes.
(6) Model A380-841, -842, and -861 airplanes.
The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; Model A320 series airplanes; Model A321-211, -212, -213, - 231, -232, -251N, -251NX, -252N, -252NX, -253N, -253NX, -253NY, -271N, -271NX, -272N, and -272NX airplanes; Airbus SAS Model A330-200 series airplanes; Model A330-300 series airplanes; Model A330-800 series airplanes; Model A330-900 series airplanes; Model A350-941 and -1041 airplanes; and Model A380-800 series airplanes. This AD was prompted by a report of corrosion and cracks on the broadband antenna adapter plate during an inspection. This AD requires repetitive general visual inspections of the broadband antenna adapter plate, skirt, vents, and attachment fittings, and applicable corrective actions, and limits the installation of affected parts under certain conditions. 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 2024-0199, dated October 18, 2024 (EASA AD 2024-0199).
(1) Where Appendix A in “the applicable SB” identified in EASA AD 2024-0199 specifies a compliance time “from SB publication date,” this AD requires using the effective date of this AD.
(2) Where EASA AD 2024-0199 specifies “14 June 2024 [the effective date of EASA AD 2024-0106],” this AD requires using the effective date of this AD.
(3) This AD does not adopt the “Remarks” section of EASA AD 2024-0199.
(4) Where paragraph (2) of EASA AD 2024-0199 specifies “any crack and/or corrosion are detected on an affected part”, this AD requires replacing that text with “any crack or corrosion is detected on an affected part”.
(5) Paragraph (4) of EASA AD 2024-0199 specifies to report inspection results to Airbus within a certain compliance time. For this AD, report inspection results at the applicable time specified in paragraph (h)(5)(i) or (ii) of this AD.
(i) If the inspection was done on or after the effective date of this AD: Submit the report within 30 days after the inspection.
(ii) If the inspection was done before the effective date of this AD: Submit the report within 30 days after the effective date of this AD.
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, AIR-520, Continued Operational Safety 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 AIR-520, Continued Operational Safety Branch, send it to the attention of the person identified in paragraph (j) of this AD and email 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, AIR-520, Continued Operational Safety Branch, FAA; or EASA; or Airbus SAS's EASA 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 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 Thusa Dinh, Aviation Safety Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198; phone: 562-627-5839; email: Thusa.T.Dinh@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.
