Abstract: A propeller blade includes an aerodynamic portion and a blade shank, a hub assembly (28, 32) which provides anchoring in a hub, a blade shank assembly of the aerodynamic portion, a safety device including a safety element (24) which extends from a distal assembly in the aerodynamic portion to a proximal assembly (26, 27) in the blade shank and which is adapted to be able to anchor the aerodynamic portion in the blade shank, wherein the blade shank assembly is anchored radially outside the hub assembly, the proximal assembly is anchored to the blade shank radially inside the hub assembly, and the distal assembly and/or the proximal assembly has a strictly positive radial clearance (30).

Abstract: Rotary-shaft brake system includes a rotary braking member attached to a rotary shaft, first and second friction members arranged on either side of the rotary braking member, each friction member being moveable between a first braking position when the friction members are in contact with the rotary braking member and a second idle position away from the rotary braking member, a bracket holding the friction members and means for guiding and controlling movement of the friction members on the bracket. The control means comprises a linear actuator acting on at least a first lever and a solid elastically deformable element.

Abstract: The invention relates to a propeller blade which comprises a hollow casing (1) forming an extrados (5) and an intrados (4) which extend from a blade shank to a free end in the direction of the span, and a framework which is arranged in the hollow casing (1) and comprises a box spar (8), having a plurality of soles (9a, 9b, 10a, 10b) in surface contact with the hollow casing (1) so as to provide structural support for the hollow casing (1), and at least two cavities (15, 16) which are spaced apart in the direction of the chord (25), wherein the propeller blade further comprises at least two reinforcing spars (6, 7) which extend between the framework and the hollow casing.

Abstract: An aircraft door actuator, including: a pneumatic cylinder for the opening of the door including a chamber into which a pressurized gas is injected via a first port, means for supplying the chamber of the cylinder with pressurized gas, via a supply pipe and said first port, means for setting the chamber to atmospheric pressure when the piston is in the position for opening the door, so as to allow said door to be moved into the closing position, including: a pressurized gas exhaust pipe a gate-valve means for guiding the opening of the gate-valve via the pressurized fluid located in the chamber when the door is in the opening position, so as to open the exhaust pipe in order to set said chamber of the cylinder to atmospheric pressure in a rapid manner once the door is open.

Abstract: An aircraft hatch emergency opening actuator includes a cylinder connected to the hatch at one of its ends and at its other end to a reference frame of the aircraft. Fluid is fed to the cylinder for emergency opening of the hatch by a device able to adopt two positions. In a rest position the fluid is isolated from the cylinder, and in an active position the fluid is injected into a fluid circuit. A device for delaying the injection of the fluid into the cylinder includes a mobile element in the fluid circuit delaying opening of the circuit when the injection device is in the active position, the injection delay being determined by a time of movement of the mobile element.