A rotary wing aircraft with a longitudinal axis in x-direction comprising at least: - a fuselage forwardly oriented relative to the longitudinal axis with a port side and a starboard side as lateral sides, - a main rotor arranged above the fuselage, - a tail rotor mounted on a tail, the tail being attached to a rearward oriented part of the fuselage, said tail having a rear end supporting said tail rotor, and - at least one engine for driving at least one of said rotors (2A, 5), said engine being mounted on said fuselage; whereas: the tail is provided with two beam boom elements (6A, 6B) extending to said rear end of the fuselage, one of the two beam boom elements (6A, 6B) extending from the port side and another beam boom element (6B, 6A) extending from the starboard side, a front tail boom beam element root (7A, 7B) of each of the two beam boom elements (6A, 6B) being respectively attached to the corresponding port I starboard side of the fuselage by a front attachment (13A, 13B), characterized in that the beam boom elements (6A, 6B) are canted with respect to the longitudinal axis and interconnected to each other at the rear end of said tail; and at least one of the front attachments (13A, 13B) is releasable and at least another of the front attachments (13B, 13A) is pivotable, so that the tail is pivotable about a z-direction, around at least one of the front attachments (13B, 13A). - a fuselage forwardly oriented relative to the longitudinal axis with a port side and a starboard side as lateral sides, - a main rotor arranged above the fuselage, - a tail rotor mounted on a tail, the tail being attached to a rearward oriented part of the fuselage, said tail having a rear end supporting said tail rotor, and - at least one engine for driving at least one of said rotors (2A, 5), said engine being mounted on said fuselage; whereas: the tail is provided with two beam boom elements (6A, 6B) extending to said rear end of the fuselage, one of the two beam boom elements (6A, 6B) extending from the port side and another beam boom element (6B, 6A) extending from the starboard side, a front tail boom beam element root (7A, 7B) of each of the two beam boom elements (6A, 6B) being respectively attached to the corresponding port I starboard side of the fuselage by a front attachment (13A, 13B), characterized in that the beam boom elements (6A, 6B) are canted with respect to the longitudinal axis and interconnected to each other at the rear end of said tail; and at least one of the front attachments (13A, 13B) is releasable and at least another of the front attachments (13B, 13A) is pivotable, so that the tail is pivotable about a z-direction, around at least one of the front attachments (13B, 13A). the tail is provided with two beam boom elements (6A, 6B) extending to said rear end of the fuselage, one of the two beam boom elements (6A, 6B) extending from the port side and another beam boom element (6B, 6A) extending from the starboard side, a front tail boom beam element root (7A, 7B) of each of the two beam boom elements (6A, 6B) being respectively attached to the corresponding port I starboard side of the fuselage by a front attachment (13A, 13B), characterized in that the beam boom elements (6A, 6B) are canted with respect to the longitudinal axis and interconnected to each other at the rear end of said tail; and at least one of the front attachments (13A, 13B) is releasable and at least another of the front attachments (13B, 13A) is pivotable, so that the tail is pivotable about a z-direction, around at least one of the front attachments (13B, 13A).