Abstract: The invention provides a nacelle for a bypass turbojet, the nacelle comprising: an aerodynamic fairing; a maintenance cover fastened to the aerodynamic fairing by means of at least one connection hinged about a longitudinal axis of the nacelle; a cold stream inner shroud and a cold stream outer shroud placed concentrically inside the aerodynamic fairing so as to define between them a flow passage for a cold stream, the inner shroud having at least one opening closed by a removable access hatch; and the outer shroud includes at least one opening closed by a removable access hatch that is fastened on the maintenance cover.

Abstract: A turbomachine including at least one thrust reverser and a device for actuating the thrust reverser, which includes at least one hydraulic engine supplied with pressurized fluid by a fuel circuit of the turbomachine, is disclosed.

Abstract: The invention provides a nacelle for a bypass turbojet, the nacelle comprising: an aerodynamic fairing; a maintenance cover fastened to the aerodynamic fairing by means of at least one connection hinged about a longitudinal axis of the nacelle; a cold stream inner shroud and a cold stream outer shroud placed concentrically inside the aerodynamic fairing so as to define between them a flow passage for a cold stream, the inner shroud having at least one opening closed by a removable access hatch; and the outer shroud includes at least one opening closed by a removable access hatch that is fastened on the maintenance cover.

Abstract: The invention relates to a pneumatic unit for activating a plurality of discharge valves of a turbomachine, the pneumatic unit having activation outlets corresponding to the number of discharge valves forming said plurality of discharge valves, and a single control input receiving a single control signal from an electronic control unit, the control signal serving to act on a control winding of a manifold means having outlets that form said activation outlets.

Abstract: Turbomachine, comprising at least one thrust reverser and means for actuating this thrust reverser which comprise at least one hydraulic engine supplied with pressurised fluid by a fuel circuit of the turbomachine.

Abstract: For constant-speed synchrophasing of the propellers (14) of the propulsion units (10) of an aircraft each equipped with an electronic control circuit (20) connected to a communications network (32) of the aircraft, each control circuit of a propulsion unit includes a clock delivering a clock signal at a frequency representing a rotational speed of the propulsion unit propeller corresponding to said constant speed, the control circuit clocks are kept substantially synchronous by communication via the communications network of the aircraft, and in each propulsion unit, the offset between the clock signal and a signal produced from a propeller rotational speed sensor is measured and compared to a determined propeller phase value assigned to the propulsion unit and, depending on the result of the comparison, an instantaneous variation of the propeller rotational speed is applied as necessary so as to bring the measured offset to the determined value.

Abstract: The invention relates to a pneumatic unit for activating a plurality of discharge valves of a turbomachine, the pneumatic unit having activation outlets corresponding to the number of discharge valves forming said plurality of discharge valves, and a single control input receiving a single control signal from an electronic control unit, the control signal serving to act on a control winding of a manifold means having outlets that form said activation outlets.