Airworthiness Directive · Amendment 39-22478 · Landing gear
Airbus SAS Airplanes
This AD applies to all Airbus SAS airplanes identified in paragraphs (c)(1) through (5) of this AD; certificated in any category.
(1) Model A330-201, -202, -203, -223, -223F, -243 and -243F airplanes.
(2) Model A330-301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes.
(3) Model A340-211, -212, and -213 airplanes.
(4) Model A340-311, -312, and -313 airplanes.
(5) Model A340-541 and -642 airplanes.
The FAA is superseding Airworthiness Directive (AD) 2013-07- 03, which applied to all Airbus SAS Model A330-200, A330-200 Freighter, A330-300, A340-200, and A340-300 series airplanes; and Model A340-541 and A340-642 airplanes. AD 2013-07-03 required repetitive inspections for degradation of the bogie pivot pins and for any cracks and damage of the pivot pin bushes of the main and central landing gear; an inspection of the affected bogie pivot pins for corrosion and base metal cracks; and repairing or replacing bogie pivot pins and pivot pin bushes, if necessary. This AD was prompted by development of a modification that address the unsafe condition and a determination that a parts installation prohibition is necessary. This AD continues to require certain actions in AD 2013-07-03, add an optional modification that would terminate the repetitive inspections, and add a parts installation prohibition, as specified in a European Union Aviation Safety Agency (EASA), 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 2022-0025R2, dated August 9, 2022 (EASA AD 2022-0025R2).
(1) Where EASA AD 2022-0025R2 refers to March 1, 2022 (the effective date of EASA AD 2022-0025, dated February 15, 2022), this AD requires using the effective date of this AD.
(2) Where EASA AD 2022-0025R2 refers to April 13, 2012 (the effective date of EASA AD 2012-0053, dated March 30, 2012), this AD requires using May 15, 2013 (the effective date of AD 2013-07-03).
(3) Where paragraph (4) of EASA AD 2022-0025R2 specifies corrective actions for the non-destructive test (NDT) inspection, replace the text “the base metal of the affected part is found corroded” with “the bogie pivot pin is found corroded or the base metal is found cracked.”
(4) This AD does not adopt the “Remarks” section of EASA AD 2022-0025R2.
(5) For the terminating modification specified in paragraph (7) of EASA AD 2022-0025R2, replacement of the unmodified main landing gear (MLG) with MLG that has been previously modified off the airplane is acceptable for compliance, provided the modification was done as specified in the applicable Safran Landing Systems Service Bulletin A33/34-32-315, dated November 28, 2017; A33/34-32-319, dated September 13, 2018; or A33/34-32-320, dated September 13, 2018; and the test after the modification was done as specified in AMM task 32-11-11-400-801-A.
Although the service information referenced in EASA AD 2022-0025R2 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 2013-07-03 are approved as AMOCs for the corresponding provisions of EASA AD 2022-0025R2 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 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 Vladimir Ulyanov, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY; telephone 206-231-3229; email vladimir.ulyanov@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.
Aircraft
