Abstract: A leaktight frame (10) for a window (3) suitable for securing the window (3) to a carrier structure (2), has first and second sealing gaskets (11, 12) respectively suitable for being arranged on a first periphery (3?) of the window (3) and on a second periphery (2?) of the carrier structure (2), the frame (10) being provided with releasable holder elements (20) for clamping the first and second gaskets (11, 12) onto the window (3) and the carrier structure (2).

Abstract: The present invention relates to a method and to a device for controlling and adjusting the ground clearance (h) of an aircraft (1) provided with at least one undercarriage (30), said undercarriage (30) being provided with a damper-actuator (2) for performing a damping function and a function of retracting said undercarriage (30). The method is remarkable in that control means (10) automatically activate adjustment means (11, 12) for adjusting the length of said damper-actuator (2) so as to maintain said ground clearance (h) at a predetermined value.

Abstract: The invention relates to a method of manufacturing a tail structure for a rotary wing aircraft, the structure comprising: a tubular portion or duct (63) presenting two ends and including two collars or flanges (66, 70) extending respectively from each of said two ends; and two curved fairing side walls (45, 47) extending respectively around the two collars or flanges; said two side walls being made of a composite material comprising an organic matrix and reinforcement; in a method of the invention, the side walls are united by solidifying the matrix.

Abstract: A leaktight frame (10) for a window (3) suitable for securing the window (3) to a carrier structure (2), has first and second sealing gaskets (11, 12) respectively suitable for being arranged on a first periphery (3?) of the window (3) and on a second periphery (21) of the carrier structure (2), the frame (10) being provided with releasable holder elements (20) for clamping the first and second gaskets (11, 12) onto the window (3) and the carrier structure (2).

Abstract: The present invention relates to a method and to a device for controlling and adjusting the ground clearance (h) of an aircraft (1) provided with at least one undercarriage (30), said undercarriage (30) being provided with a damper-actuator (2) for performing a damping function and a function of retracting said undercarriage (30). The method is remarkable in that control means (10) automatically activate adjustment means (11, 12) for adjusting the length of said damper-actuator (2) so as to maintain said ground clearance (h) at a predetermined value.

Abstract: The invention relates to a method of manufacturing a tail structure for a rotary wing aircraft, the structure comprising: a tubular portion or duct (63) presenting two ends and including two collars or flanges (66, 70) extending respectively from each of said two ends; and two curved fairing side walls (45, 47) extending respectively around the two collars or flanges; said two side walls being made of a composite material comprising an organic matrix and reinforcement; in a method of the invention, the side walls are united by solidifying the matrix.

Abstract: A process is proposed for the fabrication of parts with large dimensions formed of a skin (10) and stiffeners (12, 16) such as aircraft fuselage segments made of a composite material with a thermoplastic matrix. After stiffeners have been made separately by lay-up, consolidation and shaping, these stiffeners are placed on a tooling (23) and the skin (10) is simultaneously fabricated and assembled to the stiffeners (12, 16) by diffusion welding. More precisely, the skin (10) is laid up and continuously consolidated by the lay-up head (36) such that the required part is obtained directly.