Abstract: The disclosure is related to a rotary wing aircraft with a fuselage and an at least partially non-retractable landing gear, wherein the at least partially non-retractable landing gear comprises at least three individual support legs, wherein at least one individual support leg of the at least three individual support legs is mounted pivotally to the fuselage by means of an associated pivot bearing arrangement, wherein the at least one individual support leg is further connected to the fuselage via at least one torsion element with a predetermined elastic range, and wherein the at least one torsion element is adapted to act, in the predetermined elastic range, as a torsional spring, and, outside of the predetermined elastic range, as an energy absorber.

Abstract: A mounting arrangement for mounting at least a gear box of a rotorcraft to a fuselage of a rotorcraft, the mounting arrangement comprising a gear box of a rotorcraft and at least two support plates that are rigidly attached to at least approximately opposing sides of the gear box, each one of the at least two support plates comprising at least two attachment means that are adapted to allow attachment of the at least two support plates to a fuselage of a rotorcraft by means of associated struts in order to enable transfer of induced loads occurring in operation, which are directed into a predetermined load direction, via the associated struts.

Abstract: The present invention aims at providing an arrangement for moving a door in both a swinging and a sliding manner, in which a pivoting means allows the rotation of the door around at least two axes of rotation—a slide axis around which the pivoting that allows the sliding motion takes place, and a swing axis, further passing through a swing point of a guiding means intended for allowing the door to slide over a guiding rail, around which the door swings.

Abstract: A tail assembly for a rotorcraft. The tail assembly is manufactured to include at least one transition structure provided in the tail assembly. The transition structure is longitudinally arranged between a longitudinal median boom portion and a tail fin. A power transmission shaft of the rotorcraft extends at least partly externally above a longitudinal median boom portion of the tail assembly. The transition structure includes at an entering region a cut-out elevation step, where is made a passing through opening for the power transmission shaft.

Abstract: A mounting arrangement for mounting at least a gear box of a rotorcraft to a fuselage of a rotorcraft, the mounting arrangement comprising a gear box of a rotorcraft and at least two support plates that are rigidly attached to at least approximately opposing sides of the gear box, each one of the at least two support plates comprising at least two attachment means that are adapted to allow attachment of the at least two support plates to a fuselage of a rotorcraft by means of associated struts in order to enable transfer of induced loads occurring in operation, which are directed into a predetermined load direction, via the associated struts.

Abstract: An aircraft (1) with jettison mechanism, particularly a helicopter, comprising an airframe (2), at least one door (5) movably mounted to the airframe (2), at least one door lock mechanism (9) at an interface of said at least one door (5) with the airframe (2) to releasable mount the at least one door (5) relative to the airframe (2) and actuation means (11) for the at least one door lock mechanism (9). An emergency jettison button (20, 38) is integrated into handles (11, 12) of said actuation means.

Abstract: A tail assembly for a rotorcraft. The tail assembly is manufactured to include at least one transition structure provided in the tail assembly. The transition structure is longitudinally arranged between a longitudinal median boom portion and a tail fin. A power transmission shaft of the rotorcraft extends at least partly externally above a longitudinal median boom portion of the tail assembly. The transition structure includes at an entering region a cut-out elevation step, where is made a passing through opening for the power transmission shaft.

Abstract: The present invention aims at providing an arrangement for moving a door in both a swinging and a sliding manner, in which a pivoting means allows the rotation of the door around at least two axes of rotation—a slide axis around which the pivoting that allows the sliding motion takes place, and a swing axis, further passing through a swing point of a guiding means intended for allowing the door to slide over a guiding rail, around which the door swings.

Abstract: An aircraft (1) with jettison mechanism, particularly a helicopter, comprising an airframe (2), at least one door (5) movably mounted to the airframe (2), at least one door lock mechanism (9) at an interface of said at least one door (5) with the airframe (2) to releasable mount the at least one door (5) relative to the airframe (2) and actuation means (11) for the at least one door lock mechanism (9). An emergency jettison button (20, 38) is integrated into handles (11, 12) of said actuation means.