Airworthiness Directive · Amendment 39-23010 · Tail rotor head
Airbus Helicopters
This AD applies to all Airbus Helicopters Model AS332C, AS332C1, AS332L, and AS332L1 helicopters. certificated in any category.
The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Model AS332C, AS332C1, AS332L, and AS332L1 helicopters. This AD results from a report of the loss of the tail rotor pitch control due to a fracture of the tail rotor slide of the tail rotor head (TRH) assembly. This AD requires inspecting the slide of the control plate of the TRH assembly for any score, scratch, crack, or corrosion, removing corrosion and replacing the TRH assembly, slide of the control plate, or pitch control assembly if discrepancies are found, and reporting the results of the inspection. This AD prohibits installing an affected TRH assembly unless the actions of this AD are accomplished. All of these actions are 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 European Union Aviation Safety Agency (EASA) AD 2025-0001, dated January 6, 2025 (EASA AD 2025-0001).
(1) Where EASA AD 2025-0001 requires compliance in terms of flight hours, this AD requires using hours time-in-service.
(2) Where EASA AD 2025-0001 refers to its effective date, this AD requires using the effective date of this AD.
(3) Where the material referenced in EASA AD 2025-0001 specifies discarding certain parts, this AD requires removing these parts from service.
(4) Where paragraph (3.1) of EASA AD 2025-0001 specifies replacing the TRH assembly with an assembly repaired in accordance with AH instructions, this AD requires replacement in accordance with a method approved by the Manager, International Validation Branch, FAA, or EASA, or Airbus Helicopters Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA authorized signature.
(5) Where the material referenced in EASA AD 2025-0001 specifies sending the TRH to Airbus Helicopters for replacement of the slide, this AD requires replacement in accordance with a method approved by the Manager, International Validation Branch, FAA, or EASA, or Airbus Helicopters DOA. If approved by the DOA, the approval must include the DOA authorized signature.
(6) Where paragraph (4) of EASA AD 2025-0001 states to submit inspection results to AH within 30 days after that inspection, for this AD, report inspection results at the applicable times specified in paragraph (h)(6)(i) or (ii) of this AD.
(i) For an inspection done on or after the effective date of this AD: Submit the report within 7 days after the inspection.
(ii) For an inspection done before the effective date of this AD: Submit the report within 7 days after the effective date of this AD.
(7) This AD does not adopt the “Remarks” section of EASA AD 2025-0001.
