Airworthiness Directive · Amendment 39-23172 · Fuselage
Airbus SAS Airplanes
This AD applies to Airbus SAS Model airplanes specified in paragraphs (c)(1) through (4) of this AD, certificated in any category, as identified in European Union Aviation Safety Agency (EASA) AD 2024-0147R1, dated August 7, 2024 (EASA AD 2024-0147R1).
(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) 2016-14- 03, which applied to all Airbus SAS Model A319-111, -112, -113, -114, - 115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, - 213, -231, and -232 airplanes. AD 2016-14-03 required reinforcing the forward pressure bulkhead at a certain stringer on both the left-hand and right-hand sides and doing related investigative and corrective actions if necessary. Since the FAA issued AD 2016-14-03, new crack findings have prompted the need for repetitive inspections of the area. This AD continues to require the actions in AD 2016-14-03, adds repetitive inspections of structure at a certain frame and applicable corrective actions, provides a terminating action for the repetitive inspections, and revises the applicability by removing airplanes and adding certain airplane models. 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, EASA AD 2024-0147R1.
(1) Where EASA AD 2024-0147R1 refers to its effective date, this AD requires using the effective date of this AD.
(2) Where paragraph (2) of EASA AD 2024-0147R1 specifies “If, during any inspection as required by paragraph (1) of this AD, discrepancies are detected, before next flight, contact Airbus to obtain approved instructions for corrective action and accomplish those instructions accordingly”, this AD requires replacing that text with the following: “If, during any inspection as required by paragraph (1) of this AD, any cracking is detected, the cracking must be repaired before further flight using a method approved by the Manager, AIR-520, 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) Where EASA AD 2024-0147R1 refers to “03 October 2014 [the effective date of EASA AD 2014-0209],” this AD requires using August 12, 2016 (the effective date of AD 2016-14-03).
(4) Where paragraph (6) of EASA AD 2024-0147R1 specifies “repaired using Airbus approved instructions, accomplish the (repetitive) inspection for each repaired hole in accordance with the applicable Airbus approved instructions within the compliance time herein specified”, this AD requires replacing that text with the following: “repaired using a method approved by the Manager, AIR-520, Continued Operational Safety Branch, FAA; or EASA; or Airbus SAS's EASA DOA, provided the DOA approval includes the DOA-authorized signature: accomplish the (repetitive) inspection for each repaired hole in accordance with the applicable approved instructions within the compliance time herein specified.”
(5) This AD does not adopt the “Remarks” section of EASA AD 2024-0147R1.
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 (j) of this AD and email to: AMOC@faa.gov.
(i) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the responsible Flight Standards Office.
(ii) AMOCs approved previously for AD 2016-14-03 are approved as AMOCs for the corresponding provisions of EASA AD 2024-0147R1 that are required by paragraph (g) of this AD.
(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 Nicholas Benson, Aviation Safety Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198; phone: 206-231-3647; email: nicholas.h.benson@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.
