Airworthiness Directive · Amendment 39-23192 · Fuselage
Airbus SAS Airplanes
This AD applies to Airbus SAS Model airplanes identified in paragraphs (c)(1) through (4) of this AD, certificated in any category, as identified in European Union Aviation Safety Agency (EASA) AD 2024-0210, dated October 29, 2024 (EASA AD 2024-0210).
(1) Model A318-111, -112, -121, and -122 airplanes.
(2) Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes.
(3) Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes.
(4) Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes.
The FAA is superseding Airworthiness Directive (AD) 2022-15- 05, which applied to certain Airbus SAS Model A318 series airplanes; 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 2022-15-05 required repetitive high frequency eddy current (HFEC) inspections for cracks on the web horizontal flange and inner cap, and applicable corrective actions. Since the FAA issued AD 2022-15-05, additional cracks have been found at the door stop fitting number 1 holes at frame (FR) 68, after disassembly of the door stop fitting as part of the inspections required by AD 2022-15-05. This AD continues to require the actions in AD 2022-15-05, but with reduced compliances times for some inspections, and requires an additional inspection at door stop fitting number 1. 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, EASA AD 2024-0210.
(1) Where EASA AD 2024-0210 refers to “22 November 2021 [the effective date of EASA AD 2021-0242]”, this AD requires using August 31, 2022 (the effective date of AD 2022-15-05).
(2) Where EASA AD 2024-0210 refers to its effective date, this AD requires using the effective date of this AD.
(3) Where paragraph (1) of EASA AD 2024-0210 refers to “the SDI”, this AD requires replacing that text with “the applicable inspections”.
(4) This AD does not adopt the “Remarks” section of EASA AD 2024-0210.
(5) This AD does not adopt paragraphs (2) and (3) of EASA AD 2024-0210.
(6) Where paragraph (4) of EASA AD 2024-0210 states “discrepancies”, this AD requires replacing that word with “conditions”.
(7) Where paragraph (4) of EASA AD 2024-0210 states “within the compliance time specified therein”, this AD requires replacing that text with “before further flight”.
(8) Where paragraph (6) of EASA AD 2024-0210 specifies “the instructions provided by Airbus”, for this AD, those instructions must be approved by the FAA, EASA, or Airbus SAS's EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature.
(9) Where the material referenced in EASA 2024-0210 states to use consumable material list (CML) code 12ABC1, this AD also allows using CML code 12ADB1 instead.
Although paragraph (7) of and the material referenced in EASA AD 2024-0210 specify 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, 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 the Continued Operational Safety 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, Continued Operational Safety 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 paragraphs (h), (i), and (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 Tim Dowling, Aviation Safety Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198; phone: 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.
