An aircraft wheel braking arrangement may comprise a landing gear structure, a torque tube extending in an outboard direction from the landing gear structure, and an actuator housing disposed outboard from the torque tube. An actuator piston may extend in an inboard direction from the actuator housing for applying a force to a brake stack surrounding the torque tube. In various embodiments, a back plate is non-integral to the torque tube and may be disposed inboard of an end plate of the brake stack or the landing gear structure itself may act as the back plate. The back plate and/or the end plate may provide a direct thermal path from the brake stack to a landing gear structure.

The invention relates to a strut for the landing gear, preferably the nose landing gear, of an aircraft, which strut comprises a structure branched in a Y shape, wherein the Y-shaped structure is produced as a multi-piece structure and comprises at least two bars, wherein a first bar forms the first branch of the structure and a second bar forms the second branch of the structure and wherein both bars are composed partially or completely of a fiber composite material.

The invention relates to a strut for the landing gear, preferably the nose landing gear, of an aircraft, which strut comprises a structure branched in a Y shape, wherein the Y-shaped structure is produced as a multi-piece structure and comprises at least two bars, wherein a first bar forms the first branch of the structure and a second bar forms the second branch of the structure and wherein both bars are composed partially or completely of a fiber composite material.

An aircraft assembly having a first region, a second region spaced from the first region by a flexible region, and a deflection sensor. The first region has greater positional stability than the second region such that the second region deflects further from its default position than the first region during in-use loads. The deflection sensor includes a first gyroscope at the first region to generate a first signal representing rotation of the first region about one or more orthogonal axes, and a second gyroscope at the second region to generate a second signal representing rotation of the second region about the one or more axes. The second gyroscope is synchronised in time with the first. A controller subtracts one of the first and second signals from the other to obtain a differential signal representing deflection of the second region relative to the first due to flexing of the flexible region.

A metallic/composite joint may comprise a composite member having a flared end or an angled end, a liner perimetrically surrounding the composite member, and a metallic member perimetrically surrounding the liner. A first side of the liner contacts the composite member and a second side of the liner contacts the metallic member. The liner perimetrically surrounds at least a portion of the flared end. A through-thickness compressive stiffness of the liner may be less than a similar stiffness of the composite member.

Method of device for installation of avionics cabinets, electrical master boxes and IFE bays includes relocating at least some of the systems cabinets toward the front of the aircraft by making use of the space available in the area around the landing gear compartment. To do so, systems cabinets are used which incorporate a structural function. The use of such system cabinet designs thus allows a reduction in the aerodynamic drag and mass of the aircraft, thereby positively impacting fuel consumption and performance of the aircraft.

Method of device for installation of avionics cabinets, electrical master boxes and IFE bays includes relocating at least some of the systems cabinets toward the front of the aircraft by making use of the space available in the area around the landing gear compartment. To do so, systems cabinets are used which incorporate a structural function. The use of such system cabinet designs thus allows a reduction in the aerodynamic drag and mass of the aircraft, thereby positively impacting fuel consumption and performance of the aircraft.

An aircraft landing gear having a male part interlocked with a female part along an interlocking direction is provided. The external contact surface of the male part, when it is observed along the interlocking direction, can be an exclusively convex closed surface having external contact surface portions in the form of rounded lobes that form obstacles to the pivoting of the female part with respect to the male part about the interlocking direction. The aircraft landing gear is suitable for use with an aircraft.

An aircraft landing gear having a male part interlocked with a female part along an interlocking direction is provided. The external contact surface of the male part, when it is observed along the interlocking direction, can be an exclusively convex closed surface having external contact surface portions in the form of rounded lobes that form obstacles to the pivoting of the female part with respect to the male part about the interlocking direction. The aircraft landing gear is suitable for use with an aircraft.

A landing gear is provided. The landing gear includes a composite strut tube having a first lug and a second lug thereon. A first brace is coupled to the composite strut tube with a first two-force member via the first lug and a second brace is coupled to the composite strut tube with a second two-force member via the second lug. A method for assembling the landing gear is also provided.