Airworthiness Directive · Amendment 39-23140 · Engine controls
Airbus Helicopters
This AD applies to Airbus Helicopters Model AS350B3, EC130B4, and EC130T2 helicopters, certificated in any category.
The FAA is correcting an airworthiness directive (AD) that published in the Federal Register. That AD applies to certain Airbus Helicopters Model AS350B3, EC130B4, and EC130T2 helicopters. As published, a reference to a measurement in the regulatory text is incorrect. This document corrects that error. In all other respects, the original document remains the same.
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 2023-0187R1, dated March 20, 2025 (EASA AD 2023-0187R1).
(1) Where EASA AD 2023-0187R1 refers to the effective dates identified in paragraphs (h)(1)(i) through (iii) of this AD, this AD requires using the effective date of this AD.
(i) March 27, 2025 (the effective date of EASA AD 2023-0187R1).
(ii) November 10, 2023 (the effective date of EASA AD 2023-0187, dated October 27, 2023).
(iii) July 19, 2023 (the effective date of EASA AD 2023-0133, dated July 5, 2023).
(2) Where EASA AD 2023-0187R1 refers to April 13, 2017 (the effective date of EASA AD 2017-0059, dated April 6, 2017), this AD requires using January 30, 2019 (the effective date of AD 2018-26-02, Amendment 39-19532 (83 FR 66093, December 26, 2018)).
(3) Where EASA AD 2023-0187R1 refers to flight hours (FH), this AD requires using hours time-in-service.
(4) This AD does not adopt paragraphs (1) and (2) of EASA AD 2023-0187R1.
(5) Instead of complying with the compliance times in Table 1 in paragraph (3) of EASA AD 2023-0187R1, this AD requires the helicopters identified under the Helicopters in Pre-MOD 074699 Configuration column to accomplish the actions required by paragraph (3) of EASA AD 2023-0187R1 before the next practice autorotation, within 100 hours time-in-service, or 6 months after January 12, 2021 (the effective date of AD 2020-24-07), whichever occurs first.
(6) Where Table 2 in paragraph (4), Table 3 in paragraph (7), and Table 4 in paragraph (9) of EASA AD 2023-0187R1 state “For helicopters which operate or have operated in salt-laden atmospheric conditions”, this AD requires replacing that text with “For helicopters which operate or have operated in salt-laden atmospheric conditions, or if it cannot be determined if a helicopter has been operated in salt-laden atmospheric conditions”.
(7) Where paragraph (6) of EASA AD 2023-0187R1 states “discrepancies are detected”, this AD requires replacing that text with “marks, residue, corrosion, flaky varnish are detected; the values of the insulation test are less than 10 megaOhms; the microswitch closes in the “IDLE” position and does not open as soon as the twist grip is turned to the “FLIGHT” position; or the microswitch is open in the “FLIGHT” position and does not close as soon as the twist grip is turned to the “IDLE” position”.
(8) Where paragraph (9) of EASA AD 2023-0187R1 states “any discrepancy,” for purposes of this AD, discrepancy is defined as a nut torque that is outside allowable torque limits, or clearance between the support plate assembly and the washers that is not within 0.1 mm to 0.3 mm.
(9) This AD does not adopt the “Remarks” section of EASA AD 2023-0187R1.
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.
