In some examples, an assembly includes a rotor drive key configured to fit around a wheel boss defined by a wheel. The rotor drive key includes a support structure. The assembly further includes a fastener configured to extend the wheel boss and the support structure in a substantially axial direction of the wheel when the rotor drive key fits around the wheel boss, where the fastener is configured to limit movement of the rotor drive key relative to the wheel boss. The fastener may be rotated to establish and/or increase a contact pressure between the fastener and the rotor drive key to help the fastener limit movement of the rotor drive key relative to the wheel boss.

A brake assembly for landing gear of an aircraft includes a caliper member and a carrier member. The caliper member includes a gas inlet configured to receive a cooling gas supplied by an on board fuel inerting gas supply system of the aircraft, and a manifold fluidly coupled to the gas inlet. The manifold is configured to distribute the cooling gas to one or more outlet ports of the caliper member. The carrier member is configured to be coupled to the caliper member. The carrier member includes a cylindrical section configured to receive a stacked arrangement of stators and rotors. The cylindrical section defines one or more interior passages configured to fluidly couple the outlet ports of the caliper member to one or more outlet ports of the cylindrical section. The outlet ports of the cylindrical section are arranged proximate the stacked arrangement of stators and rotors to facilitate forced convective cooling of the stacked arrangement of stators and rotors with the cooling gas supplied by the on board fuel inerting gas supply system.

A brake assembly for landing gear of an aircraft includes a caliper member and a carrier member. The caliper member includes a gas inlet configured to receive a cooling gas supplied by an on board fuel inerting gas supply system of the aircraft, and a manifold fluidly coupled to the gas inlet. The manifold is configured to distribute the cooling gas to one or more outlet ports of the caliper member. The carrier member is configured to be coupled to the caliper member. The carrier member includes a cylindrical section configured to receive a stacked arrangement of stators and rotors. The cylindrical section defines one or more interior passages configured to fluidly couple the outlet ports of the caliper member to one or more outlet ports of the cylindrical section. The outlet ports of the cylindrical section are arranged proximate the stacked arrangement of stators and rotors to facilitate forced convective cooling of the stacked arrangement of stators and rotors with the cooling gas supplied by the on board fuel inerting gas supply system.

A cable-linked brake pedal assembly for an airplane. The assembly includes a first cable assembly with a first end attached to a pilot-side brake pedal and a second end attached to a first bell crank assembly, and a second cable assembly with a first end attached to a copilot-side brake pedal and a second end attached to a second bell crank assembly. A first connecting rod with a first rod end is attached to the first bell crank assembly and a second rod end is attached to the second bell crank assembly. The connection between the first and second cable assemblies, first and second bell crank assemblies, and first connecting rod is configured such that depressing the pilot-side brake pedal moves the first cable assembly, first connecting rod, and second cable assembly in such a way as to cause a corresponding depression of the copilot-side brake pedal.

A cable-linked brake pedal assembly for an airplane. The assembly includes a first cable assembly with a first end attached to a pilot-side brake pedal and a second end attached to a first bell crank assembly, and a second cable assembly with a first end attached to a copilot-side brake pedal and a second end attached to a second bell crank assembly. A first connecting rod with a first rod end is attached to the first bell crank assembly and a second rod end is attached to the second bell crank assembly. The connection between the first and second cable assemblies, first and second bell crank assemblies, and first connecting rod is configured such that depressing the pilot-side brake pedal moves the first cable assembly, first connecting rod, and second cable assembly in such a way as to cause a corresponding depression of the copilot-side brake pedal.

An architecture that provides automatic monitoring of brake conditions making use of a wear pin on a brake. The disclosure makes use of the fact that a wear pin is required to be provided on an aircraft brake, by integrating monitoring functions such as displacement sensors and/or temperature sensors, into the pin. This means that the automatic monitoring components are not taking up more space on the brake than is already taken up by the compulsory wear pin.

An architecture that provides automatic monitoring of brake conditions making use of a wear pin on a brake. The disclosure makes use of the fact that a wear pin is required to be provided on an aircraft brake, by integrating monitoring functions such as displacement sensors and/or temperature sensors, into the pin. This means that the automatic monitoring components are not taking up more space on the brake than is already taken up by the compulsory wear pin.

A method of controlling a braking device includes receiving a braking torque instruction, on the basis of the received braking torque instruction, setting a first braking torque set point for a first brake and a second braking torque set point for a second brake, measuring a first value of a first parameter representative of the first braking torque and modifying the first braking torque set point as a function of the first value with the aid of a first servocontrol loop, and measuring a second value of a second parameter representative of the second braking torque and modifying the second braking torque set point as a function of the second value with the aid of a second servocontrol loop.

A method of controlling a braking device includes receiving a braking torque instruction, on the basis of the received braking torque instruction, setting a first braking torque set point for a first brake and a second braking torque set point for a second brake, measuring a first value of a first parameter representative of the first braking torque and modifying the first braking torque set point as a function of the first value with the aid of a first servocontrol loop, and measuring a second value of a second parameter representative of the second braking torque and modifying the second braking torque set point as a function of the second value with the aid of a second servocontrol loop.

In some examples, a drive insert comprises a clip and a retainer. The clip is configured to be slidable over a surface adjacent to a drive slot of a brake disc in a tangential direction of the brake disc. The retainer is configured to be slidable over the clip when the clip is positioned over the surface to secure the clip to the brake disc. In some examples, the clip may comprise a body section and first and second arms extending from the body section. The retainer may comprise first and second legs configured to contact the first arm and the second arm of the clip when the retainer is positioned over the clip. The first and second legs may be resiliently biased to provide an inward clamping force on the clip when the retainer is positioned over the clip.