Airworthiness Directive · Amendment 39-21439 · Tail rotor blades
Airbus Helicopters
This AD applies to Airbus Helicopters Model AS350B, AS350BA, AS350B1, AS350B2, AS350D, AS355E, AS355F, AS355F1, AS355F2, and AS355N helicopters, certificated in any category, with a tail rotor (T/R) blade part number (P/N) listed in Appendix 1, Table 1, of European Union Aviation Safety Agency (EASA) AD 2020-0224R1, dated November 11, 2020 (EASA AD 2020-0224R1) (pre-mod 075580).
The FAA is adopting a new airworthiness directive (AD) for certain Airbus Helicopters Model AS350B, AS350BA, AS350B1, AS350B2, AS350D, AS355E, AS355F, AS355F1, AS355F2, and AS355N helicopters. This AD was prompted by two reports of debonding of the tail rotor (T/R) blade leading edge protection shields. This AD requires repetitively inspecting certain T/R blades and depending on the inspection results, replacing the T/R blade, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference (IBR). This AD also prohibits installing certain T/R blades. 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 2020-0224R1.
(1) Where EASA AD 2020-0224R1 refers to flight hours (FH), this AD requires using hours time-in-service.
(2) Where EASA AD 2020-0224R1 refers to October 20, 2020 (the effective date of the original issuance of its AD (EASA AD 2020-0224-E, dated October 16, 2020)) and its effective date, this AD requires using the effective date of this AD.
(3) Where paragraph (1) of EASA AD 2020-0224R1 specifies visually inspecting each T/R blade leading edge protection shield with instructions in the service information, this AD requires visually checking each T/R blade leading edge protection shield and bonding strip for a distortion, dent, and scratch; visually checking the area surrounding each T/R blade leading edge protection along the skin length for a gap; and visually checking the area surrounding the bonding strip for a crack. These visual checks may be performed by the owner/operator (pilot) holding at least a private pilot certificate and must be entered into the aircraft records showing compliance with this AD in accordance with 14 CFR 43.9(a)(1) through (4) and 14 CFR 91.417(a)(2)(v). The record must be maintained as required by 14 CFR 91.417, 121.380, or 135.439.
(4) Where paragraph (5) of EASA AD 2020-0224R1 specifies the modification of replacing each affected part with a serviceable part, this AD does not require this modification.
(5) The “Remarks” section of EASA AD 2020-0224R1 does not apply to this AD.
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.
