Airworthiness Directive · Amendment 39-11765 · Eurocopter France Model SA-365N1, AS-365N2, and SA-366G1 Helicopters
Eurocopter France Model SA-365N1, AS-365N2, and SA-366G1 Helicopters
Model SA-365N1, AS-365N2, and SA-366G1 helicopters, with tail rotor blade (blade), Part Number 365A12-010-all dash numbers, 365A12-0020-00, 365A33-2131-all dash numbers, or 365A12-0020-02, installed, certificated in any category.
Note 1: This AD applies to each helicopter identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For helicopters that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (c) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.
This amendment supersedes an existing airworthiness directive (AD) that applies to Eurocopter France Model SA-365N1, AS-365N2, and SA-366G1 helicopters and that currently requires initial and repetitive inspections of the tail rotor blade Kevlar tie-bar (Kevlar tie-bar) for cracks or delaminations. This amendment requires the same actions required by the existing AD and corrects an incorrectly stated part number (P/N) in the existing AD. This amendment is prompted by a report of delamination of a Kevlar tie-bar. The actions specified by this AD are intended to detect cracks that could lead to delamination of the Kevlar tie-bar, loss of tail rotor control, and subsequent loss of control of the helicopter.
To detect cracks that could lead to delamination of the tail rotor blade Kevlar tie-bar (Kevlar tie-bar), loss of tail rotor control, and subsequent loss of control of the helicopter, accomplish the following:
(a) Within 10 hours time-in-service (TIS), and thereafter at intervals not to exceed 250 hours TIS, inspect each Kevlar tie-bar for a crack or delamination in accordance with paragraph B, Operational Procedure, of Eurocopter France Service Bulletin 05.00.34, Revision 3, dated November 14, 1996.
(b) If any delamination or cracking is found during any of the inspections required by paragraph (a) of this AD, remove the blade and replace it with an airworthy blade before further flight.
