Airworthiness Directive · Amendment 39-21452 · Tail rotor control system
Airbus Helicopters
This AD applies to Airbus Helicopters Model AS350B, AS350B1, AS350B2, AS350B3, AS350BA, AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters, certificated in any category, as identified in European Union Aviation Safety Agency (EASA) AD 2017-0020R1, dated May 22, 2019 (EASA AD 2017-0020R1).
The FAA is superseding Airworthiness Directive (AD) 2018-15- 02, which applied to certain Airbus Helicopters Model AS350B, AS350B1, AS350B2, AS350B3, AS350BA, AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters. AD 2018-15-02 required repetitively inspecting the tail rotor (TR) pitch rod for a damaged elastomeric ball joint, and corrective action if necessary. This AD continues to require the repetitive inspections and allows the repetitive inspection interval to be extended under certain conditions, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD was prompted by a report of several cases of damaged TR pitch rod ball joints. 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 2017-0020R1.
(1) Where EASA AD 2017-0020R1 refers to its effective date, this AD requires using the effective date of this AD.
(2) Where EASA AD 2017-0020R1 refers to February 9, 2017 (the effective date of EASA AD 2017-0020-E, dated February 9, 2017), this AD requires using August 3, 2018 (the effective date of AD 2018-15-02).
(3) The “Remarks” section of EASA AD 2017-0020R1 does not apply to this AD.
(4) Although the service information referenced in EASA AD 2017-0020R1 specifies to discard certain parts, this AD does not include that requirement.
(5) Where EASA AD 2017-0020R1 refers to flight hours (FH), this AD requires using hours time-in-service (TIS).
(6) Where paragraph (1) of EASA AD 2017-0020R1 specifies an initial compliance time of “Before exceeding 50 FH [flight hours] since the last inspection per ALS [airworthiness limitations] chapter 04-20-00, or within 10 FH or 7 days, whichever occurs first,” for this AD, the initial compliance time is within 10 hours TIS.
(7) For the inspections specified in paragraph (1) of EASA AD 2017-0020R1: Accomplishing the actions specified in paragraphs (h)(7)(i) and (ii) of this AD before the effective date of this AD are acceptable for compliance with the inspections specified in in paragraph (1) of EASA AD 2017-0020R1. On or after the effective date of this AD, comply with the inspections as specified in paragraph (1) of EASA AD 2017-0020R1.
(i) Manually induce a flapping movement in the TR blade until the pitch change rod rotates a minimum of 10 degrees.
(ii) Inspect both faces of the blade side of the ball joint elastomer for debonding, extrusion, and cracks.
(8) Although the service information referenced in EASA AD 2017-0020R1 permits certain actions to be performed by a mechanical engineering technician or pilot, this AD requires that the actions be performed by a qualified mechanic.
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.
