Airworthiness Directive · Amendment 39-22821 · Landing gear
Airbus SAS Airplanes
This AD applies to all Airbus airplanes identified in paragraphs (c)(1) through (4) of this AD, certificated in any category.
(1) Model A330-201, -202, -203, -223, and -243 airplanes.
(2) Model A330-223F and -243F airplanes.
(3) Model A330-301, -302, -303, -323, -342, -343, -841, and -941 airplanes.
(4) Model A340-312 and -313 airplanes.
The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A330-200, A330-200 freighter, A330-800, and A330-900 series airplanes; Model A330-301, -302, -303, -323, -342, and -343 airplanes; and Model A340-312 and -313 airplanes. This AD was prompted by reports of quality non-conformity on main landing gear (MLG) axles where the high velocity oxygen-fuel (HVOF) coating on the bearing journal runout areas had a coating that was thicker than allowable limits. This AD requires repetitive inspections of the affected parts (MLG axles) for any discrepancy, corrective actions, and eventual replacement of affected parts, and prohibits the installation of affected parts, 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 paragraphs (h) and (i) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, European Union Aviation Safety Agency (EASA) AD 2023-0167, dated August 30, 2023 (EASA AD 2023-0167).
(1) Where EASA AD 2023-0167 refers to its effective date, this AD requires using the effective date of this AD.
(2) Where paragraph (1) of EASA AD 2023-0167 specifies to inspect within 24 months after the part entry into service, this AD requires inspecting within 30 months after the part entry into service or 30 days after the effective date of this AD, whichever occurs later.
(3) Paragraph (3) of EASA AD 2023-0167 specifies “If, during any inspection as required by paragraph (1) of this AD, any discrepancy, as defined in the SB, is detected, before next flight, contact SAFRAN Landing Systems for approved corrective action instructions and, within the compliance time specified therein, accomplish those instructions accordingly. If no compliance time is identified in those instructions, accomplish the applicable corrective action(s) before next flight.” This AD, however, requires replacing that text with “If, during any inspection as required by paragraph (1) of this AD, any discrepancy, as defined in the SB, is detected, the discrepancy must be repaired before further flight using a method approved by the Manager, International Validation Branch, FAA; or EASA; Airbus SAS's EASA Design Organization Approval (DOA); or SAFRAN Landing Systems' DOA. If approved by the DOA, the approval must include the DOA-authorized signature.”
(4) This AD does not adopt the “Remarks” section of EASA AD 2023-0167.
(5) This AD requires replacing the text of Note 2 of EASA AD 2023-0167 with “Removal of an MLG or an assembly, including the bogie beam assembly, having an affected part installed from an aeroplane and subsequent reinstallation of that MLG or assembly, including the bogie beam assembly, on the same aeroplane, accomplished during a single maintenance visit, is not considered as installation as specified in paragraph (7) of this EASA AD.”
(6) Where the service information referenced in EASA AD 2023-0167 specifies to “remove the cover protection of the affected axle” prior to inspecting the affected part, this AD does not include that requirement.
Although the service information referenced in EASA AD 2023-0167 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 manager of the International Validation Branch, mail it to the address 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; Airbus SAS's EASA Design Organization Approval (DOA); or SAFRAN Landing System'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)(6), (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 Vladimir Ulyanov, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; 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
