Airworthiness Directive · Amendment 39-22424 · Pneumatic
Airbus SAS Airplanes
Superseded. A later AD replaced this one: AD 2024-26-04. 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, -271NX, and -272NX airplanes.
The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A318 series airplanes; Model A319 series airplanes; Model A320-211, -212, -214, -216, -231, -232, -233, -251N, -252N, - 253N, -271N, -272N, and -273N airplanes; and Model A321 series airplanes. This AD was prompted by a report that certain overheat detection system (OHDS) sensing elements installed at certain positions might not properly detect thermal bleed leak events due to a quality escape during the manufacturing process. This AD requires a one-time detailed inspection of each affected part installed at an affected position and replacement if necessary, and prohibits the installation of affected parts at affected positions, 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, European Union Aviation Safety Agency (EASA) AD 2022-0147, dated July 14, 2022; corrected August 17, 2022 (EASA AD 2022-0147).
(1) Where EASA AD 2022-0147 defines “Affected part” and identifies part numbers and corresponding date codes as those “listed in Section 1.A of the VSB,” for this AD, those part numbers and corresponding date codes are listed in Section 1.A. of Kidde Aerospace & Defense Service Bulletin CFD-26-3, dated January 13, 2022; or Revision 1, dated March 29, 2022. The date codes listed in Section 1.A. of Kidde Aerospace & Defense Service Bulletin CFD-26-3, dated January 13, 2022; and Revision 1, dated March 29, 2022; do not apply to parts produced prior to November 24, 2004, or after January 31, 2021.
(2) Where EASA AD 2022-0147 refers to its effective date, this AD requires using the effective date of this AD.
(3) Where paragraph (2) of EASA AD 2022-0147 refers to “any discrepancy as defined in the SB,” for this AD, a discrepancy is an incorrect electronic centralized aircraft monitor (ECAM) alert (one not related to AIR L WING LEAK) being displayed following the inspection of any OHDS sensing element.
(4) Where the service information referenced in EASA AD 2022-0147 specifies to send an affected part to the manufacturer, this AD does not include that requirement.
(5) This AD does not adopt the “Remarks” section of EASA AD 2022-0147.
Although the service information referenced in EASA AD 2022-0147 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. 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 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, Aerospace Engineer, Large Aircraft Section, FAA, International Validation Branch, 2200 South 216th Street, Des Moines, WA 98198; 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.
