Airworthiness Directive · Amendment 39-22683 · Fuselage
Airbus SAS Airplanes
This AD applies to Airbus SAS Model A318-111, -112, -121, and -122 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; certificated in any category, all manufacturer serial numbers, except the airplanes specified in paragraphs (c)(1) through (3) of this AD.
(1) Airplanes on which Airbus SAS modification 161255 has been embodied in production.
(2) Model A319 series airplanes on which Airbus SAS modifications 28238, 28162, and 28342 have been concurrently embodied in production.
(3) Model A318 series airplanes on which Airbus SAS modification 39195 has been embodied in production.
The FAA is superseding Airworthiness Directive (AD) 2018-14- 09, which applied to certain Airbus SAS Model A318 series airplanes; Model A319 series 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 2018-14-09 required repetitive inspections for cracking of the fastener holes in certain fuselage frames, and depending on airplane configuration, provides an optional terminating action to the repetitive inspections. This AD was prompted by reports of early cracking on the four holes of the crossbeam splicing at certain fuselage frames (FR). This AD continues to require the actions in AD 2018-14-09 at modified compliance times, requires further inspections, and provides optional terminating actions for certain airplanes; as specified in 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, European Union Aviation Safety Agency (EASA) AD 2023-0150, dated July 20, 2023 (EASA AD 2023-0150).
(1) Where EASA AD 2023-0150 refers to “28 July 2016 [the effective date of EASA AD 2016-0139],” this AD requires using August 23, 2018 (the effective date of AD 2018-14-09).
(2) Where EASA AD 2023-0150 refers to its effective date, this AD requires using the effective date of this AD.
(3) Where rows B and C of the “Threshold” column in Table 1 of EASA AD 2023-0150 refer to “54 800 FH,” for this AD, replace that text with “54 900 FH.”
(4) Where paragraph (5) of EASA AD 2023-0150 refers to “valid within the EASA system,” for this AD, replace that text with “approved by the FAA, EASA, Airbus SAS's EASA Design Organization Approval (DOA), or an EASA DOA (other than Airbus SAS's EASA DOA).”
(5) Where paragraph (5) of EASA AD 2023-0150 specifies “contact that design approval holder (DAH) for assessment and repair instructions, obtain EASA AMOC approval and accomplish those instructions accordingly, as applicable,” for this AD, replace that text with “modify the repair using a method approved by the Manager, 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.”
(6) Where the service information referenced in paragraphs (8) and (9) of EASA AD 2023-0150 refers to actions when an existing hole diameter is “more than or equal to the minimum starting hole diameter,” for this AD, replace that text with “more than or equal to the maximum starting hole diameter.”
(7) This AD does not adopt the “Remarks” section of EASA AD 2023-0150.
Although the service information referenced in EASA AD 2023-0150 specifies 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, 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 International Validation Branch, send it to the attention of the person identified in paragraph (k) of this AD. Information may be emailed to: 9-AVS-AIR-730-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 2018-14-09 are approved as AMOCs for the corresponding provisions of EASA AD 2023-0150 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, 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 paragraphs (i) and (j)(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.
For more information about this AD, contact Timothy Dowling, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 817-222-5102; 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.
