Airworthiness Directive · Amendment 39-22076 · Fuselage
Airbus SAS Airplanes
This AD applies to the Airbus SAS airplanes identified in paragraphs (c)(1) through (3) of this AD, certificated in any category, as identified in European Union Aviation Safety Agency (EASA) AD 2021-0233, dated October 27, 2021 (EASA AD 2021-0233).
(1) Model A330-201, -202, -203, -223, and -243 airplanes.
(2) Model A330-223F and -243F airplanes.
(3) Model A330-301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes.
The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A330-200 series airplanes, Model A330-200 Freighter series airplanes, and Model A330-300 series airplanes. This AD was prompted by a determination that certain service information specified in AD 2018-20-19 contained instructions that could be misleading, resulting in a necessary inspection not being accomplished on certain airplanes. This AD requires a rototest for certain modified airplanes for any crack around the right-side upper and lower bulk door support or door latch fitting holes at certain bulk cargo door frames, or repetitive inspections for any crack at certain fittings, and on- condition actions, 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 2021-0233.
(1) Where EASA AD 2021-0233 refers to its effective date, this AD requires using the effective date of this AD.
(2) The “Remarks” section of EASA AD 2021-0233 does not apply to this AD.
(3) Where paragraph (4) of EASA AD 2021-0233 specifies to “accomplish those instructions accordingly” if discrepancies are detected, for this AD a discrepancy is any cracking, and if any cracking is detected, the cracking must be repaired before further flight using a method approved by the Manager, Large Aircraft Section, 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) Where paragraph (4) of EASA AD 2021-0233 specifies to “contact Airbus for approved repair instructions,” for this AD use “accomplish corrective actions in accordance with the instructions of the SB and contact the Manager, Large Aircraft Section, International Validation Branch, FAA; or EASA; or Airbus SAS's EASA DOA for approved repair instructions. If approved by the DOA, the approval must include the DOA-authorized signature”
(5) Although the service information referenced in EASA AD 2021-0233 specifies to do a check of the aircraft records for accomplishment of certain service information, and specifies that action as “RC,” (required for compliance), this AD does not include that requirement.
(6) Where the Applicability section of EASA AD 2021-0233 refers to “defects,” for this AD “defects” are cracks.
Although the service information referenced in EASA AD 2021-0233 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, Large Aircraft Section, 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 Large Aircraft Section, 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, Large Aircraft Section, 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(s) (h)(3) and (4), (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.
