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  Safety Publications Tool

2023-0194R1 : Fuselage – Main Gearbox Suspension Bar Fittings and Screws – Life Limit / Replacement / Modification

Number 2023-0194R1
Issued by Europe  Europe
Issue date 2025-03-19
Effective date 2025-03-26
EASA approval number
ATA Chapter 53
Approval Holder
/ Type Designation
  • AIRBUS HELICOPTERS
    • SA 330 / AS 332 / EC 225
      • AS 332 C
      • AS 332 C1
      • AS 332 L
      • AS 332 L1
Revision This AD revises EASA AD 2023-0194 dated 08 November 2023.
Correction Not applicable
Supersedure The original issue of this AD superseded EASA AD 2018-0260 dated 03 December 2018.
Publication(s) and related information AH ASB AS332-01.00.90 original issue dated 21 November 2018, or Revision 1 dated 02 March 2020, or Revision 2 dated 28 September 2023. AH AS332-53.02.13 original issue dated 28 September 2023, or Revision 1 dated 05 April 2024 or Revision 2 dated 13 March 2025. The use of later approved revisions of the above-mentioned documents is acceptable for compliance with the requirements of this AD.
PAD number 23-108
Remarks 1. If requested and appropriately substantiated, EASA can approve Alternative Methods of Compliance for this AD. 2. The original issue of this AD was posted on 10 October 2023 as PAD 23-108 for consultation until 07 November 2023. No comments were received during the consultation period. 3. Enquiries regarding this AD should be referred to the EASA Safety Information Section, Certification Directorate. E-mail: ADs[at]easa.europa.eu. 4. Information about any failures, malfunctions, defects or other occurrences, which may be similar to the unsafe condition addressed by this AD, and which may occur, or have occurred on a product, part or appliance not affected by this AD, can be reported to the EU aviation safety reporting system. This may include reporting on the same or similar components, other than those covered by the design to which this AD applies, if the same unsafe condition can exist or may develop on an aircraft with those components installed. Such components may be installed under an FAA Parts Manufacturer Approval (PMA), Supplemental Type Certificate (STC) or other modification.