Airworthiness Directive · Amendment 39-22908 · Landing gear
Airbus SAS Airplanes
Superseded. A later AD replaced this one: AD 2026-17-04. Comply with the one in force.
This AD applies to all Airbus SAS airplanes, certificated in any category, as identified in paragraphs (c)(1) through (4) of this AD.
(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, -252N, -253N, -271N, -272N, -251NX, -252NX, -253NX,-253NY, -271NX, and -272NX airplanes.
The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A318 series airplanes; Model A319-111, -112, -113, - 114, -115, -131, -132, -133, -151N, -153N, and -171N airplanes; Model A320 series airplanes; and Model A321 series airplanes. This AD was prompted by reports of jamming of, or inability to open, the main landing gear (MLG) door during maintenance operations. This AD requires repetitive inspection of the MLG doors, and, depending on findings, accomplishment of applicable corrective actions, and prohibits the installation of affected parts 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 paragraphs (h) and (i) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, European Union Aviation Safety Agency (EASA) AD 2024-0216, dated November 15, 2024 (EASA AD 2024-0216).
(1) Where EASA AD 2024-0216 refers to its effective date, this AD requires using the effective date of this AD.
(2) This AD does not adopt the “Remarks” section of EASA AD 2024-0216.
(3) Where EASA AD 2024-0216 defines a serviceable part as an “MLG actuator, eligible for installation in accordance with Airbus instructions, which is not an affected part,” this AD requires replacing that text with “MLG actuator, eligible for installation, which is not an affected part.”
(4) Where paragraph (1) of EASA AD 2024-0216 specifies to accomplish an inspection “in accordance with the instructions of the AOT” this AD requires replacing that text with “in accordance with step 5.6.2 of the instructions of the AOT.”
(5) Where paragraph (2) of EASA AD 2024-0216 states “any discrepancy on an affected MLG door is detected, as defined in the AOT” this AD requires replacing the text with a “any MLG door actuator that does not meet all the results specified in the table in paragraph 5.6.2.2 in the referenced AOT is detected”.
(6) This AD does not adopt the requirements specified in paragraph (3) of EASA AD 2024-0216.
Although the material referenced in EASA AD 2024-0216 specifies to submit certain information and send removed parts 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, send it to the attention of the person identified in paragraph (k) 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, 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 P. Dowling, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 206-231-3667; 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.
