Airworthiness Directive · Amendment 39-23075 · Main rotor control
Airbus Helicopters
This AD applies to Airbus Helicopters Model AS-365N2, AS 365 N3, EC 155B, EC155B1, SA-365N, and SA-365N1 helicopters, certificated in any category.
The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Model AS-365N2, AS 365 N3, EC 155B, EC155B1, SA- 365N, and SA-365N1 helicopters. This AD was prompted by reports of loss of tightening torque between the upper ball bearing end and the main rotor (MR) servo-control. This AD requires inspecting the tightening torque and, depending on the results, taking corrective action. This AD also requires reporting information. 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 AD 2024-0110, dated June 6, 2024 (EASA AD 2024-0110).
(1) Where EASA AD 2024-0110 defines “the ASB”, this AD requires replacing that definition with “Airbus Helicopters Alert Service Bulletin (ASB) AS365-67-30-0001, AS366-67-30-0001, or EC155-67-30-0001, each Issue 2 and dated May 15, 2024, as applicable for the model helicopter. For compliance with this AD, Model SA-365N and SA-365N1 helicopters are to use ASB AS365-67-30-0001, Issue 2, dated May 15, 2024”.
(2) Where EASA AD 2024-0110 requires compliance in terms of flight hours, this AD requires using hours time-in-service.
(3) Where EASA AD 2024-0110 refers to its effective date, this AD requires using the effective date of this AD.
(4) Where paragraph (1) of EASA AD 2024-0110 and the material referenced in EASA AD 2024-0110 specify “check”, this AD requires replacing that text with “inspect” or “inspection” as applicable.
(5) Where the material referenced in EASA AD 2024-0110 specifies discarding parts, this AD requires removing those parts from service.
(6) Where the material referenced in EASA AD 2024-0110 specifies hard point, for this AD a hard point may be indicated by resistance, ratcheting, blocking, or difficulty when turning the ball bearing end into the upper end fitting of the MR servo-control by hand.
(7) Where paragraph (3) of EASA AD 2024-0110 specifies reporting inspection results (including no findings) to AH [Airbus Helicopters] within 7 days after the inspection required by paragraph (1) of EASA AD 2024-0110, this AD requires reporting that information at the applicable time in paragraph (h)(7)(i) or (ii) of this AD.
(i) If the inspection was done on or after the effective date of this AD: Submit the report within 30 days after the inspection required by paragraph (1) of EASA AD 2024-0110.
(ii) If the inspection was done before the effective date of this AD: Submit the report within 30 days after the effective date of this AD.
(8) This AD does not adopt the “Remarks” section of EASA AD 2024-0110.
