Airworthiness Directive · Amendment 39-22931 · Wings
Airbus SAS Airplanes
This AD applies to Airbus SAS airplanes identified in paragraphs (c)(1) through (5) of this AD, certificated in any category, as identified in European Union Aviation Safety Agency (EASA) AD 2024-0145, dated July 23, 2024 (EASA AD 2024-0145).
(1) Model A300 B4-2C, B4-103, and B4-203 airplanes.
(2) Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes.
(3) Model A300 B4-605R and B4-622R airplanes.
(4) Model A300 C4-605R Variant F airplanes.
(5) Model A300 F4-605R and F4-622R airplanes.
The FAA is superseding Airworthiness Directive (AD) 2022-11- 01, which applied to certain Airbus SAS Model A300 series airplanes; Model A300 B4-600, B4-600R, and F4-600R series airplanes; and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes). AD 2022-11-01 required a detailed inspection (DET) of the main landing gear (MLG) support rib 5 lower flange, a fluorescent penetrant inspection (FPI) around the spot facing of certain fastener holes if necessary, and applicable corrective actions. This AD was prompted by the determination that additional airplanes are affected by the unsafe condition. This AD continues to require the actions in AD 2022-11-01 and adds airplanes to the applicability, 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 2024-0145.
(1) Where EASA AD 2024-0145 refers to August 31, 2021 (the effective date of EASA AD 2021-0190), this AD requires using July 5, 2022 (the effective date of AD 2022-11-01, Amendment 39-22051 (87 FR 32292, May 31, 2022)).
(2) Where EASA AD 2024-0145 refers to its effective date, this AD requires using the effective date of this AD.
(3) Where paragraph (3) of EASA AD 2024-0145 specifies to “accomplish those instructions accordingly” if any crack is detected, for this AD if any crack is detected, the crack must be repaired before further flight 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.
(4) This AD does not adopt the “Remarks” section of EASA AD 2024-0145.
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, AIR-520, Continued Operational Safety 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 Continued Operational Safety Branch, send it to the attention of the person identified in paragraph (j) of this AD and email to: 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) Airbus Statement of Airworthiness Compliance (ASAC) 80955386/006/2021, Issue 1, dated August 25, 2021; and ASAC 80955386/024/2022, Issue 1, dated February 25, 2022, are approved as AMOCs for the corresponding provisions of this AD for the airplanes identified in those ASACs only.
(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, AIR-520, Continued Operational Safety 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 paragraph (i)(2) of this AD, if any material referenced in EASA AD 2024-0145 contains paragraphs that are labeled as RC, the instructions in RC paragraphs, including subparagraphs under an RC paragraph, must be done to comply with this AD; any paragraphs, including subparagraphs under those paragraphs, that are not identified as RC are recommended. The instructions in paragraphs, including subparagraphs under those paragraphs, 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 instructions identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to instructions identified as RC require approval of an AMOC.
For more information about this AD, contact Dan Rodina, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; phone: 206-231-3225; email: Dan.Rodina@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.
