Airworthiness Directive · Amendment 39-22011 · Fuselage
Airbus SAS Airplanes
Superseded. A later AD replaced this one: AD 2025-20-15. Comply with the one in force.
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 2021-0227, dated October 11, 2021 (EASA AD 2021-0227).
(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 adopting a new airworthiness directive (AD) for 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. This AD was prompted by reports that, during inspections accomplished as specified in certain airworthiness limitation items (ALIs), cracks were detected in the double joggle areas at frame (FR) 16 and FR20 in the nose forward fuselage. This AD requires repetitive special detailed inspections of certain areas and applicable on-condition actions, 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, EASA AD 2021-0227.
(1) Where EASA AD 2021-0227 refers to its effective date, this AD requires using the effective date of this AD.
(2) The “Remarks” section of EASA AD 2021-0227 does not apply to this AD.
(3) Where paragraph (2) of EASA AD 2021-0227 specifies to “contact Airbus for approved repair instructions and, within the compliance time specified therein, accomplish those instructions accordingly” if any cracks are detected, for this AD if any cracking is detected, the cracking must be repaired before further flight using a method approved by Airbus SAS's EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature.
(4) Where paragraphs (3) and (4) of EASA AD 2021-0227 specify “Airbus approved repair instructions,” or “post-repair inspection instructions approved by Airbus,” for this AD, to be acceptable for credit, the repair instructions must be approved by Airbus SAS's EASA DOA. If approved by the DOA, the approval must include the DOA authorized signature.
Although the service information referenced in EASA AD 2021-0227 specifies to submit certain information to the manufacturer, this AD does not include that requirement.
Accomplishing the initial inspections required by this AD terminates ALI Tasks 531153-02-1, 531153-02-2, 531155-02-1 and 531155-02-2, as required by paragraph (i) of AD 2020-20-05 only for the airplanes identified in paragraph (c) of this AD.
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, Large Aircraft Section, 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 Large Aircraft Section, International Validation Branch, send it to the attention of the person identified in paragraph (l) of this AD. Information may be emailed to: 9-AVS-AIR-730-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, Large Aircraft Section, International Validation 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 paragraphs (h)(3), (i), and (k)(2) of this AD, if any service information 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.
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.
