A system for controlling landing gear subsystems may comprise a controller and a first motor drive unit in operable communication with the controller. A first electric motor and a second electric motor may be in operable communication with the first motor drive unit. A second motor drive unit may be in operable communication with the controller. A third electric motor and a fourth electric motor may be in operable communication with the second motor drive unit. An AC/DC converter may be electrically coupled to the first drive unit and the second motor drive unit.

A braking arrangement includes a torque plate, a torque button, and a sacrificial bushing. The torque button comprises a head portion and a shaft portion, wherein the head portion is configured to extend at least partially into a torque pocket of an end plate of a brake stack and the shaft portion is configured to extend through an aperture disposed in a back leg of the torque plate. The bushing is configured to be removably coupled between the shaft portion of the torque button and the back leg of the torque plate.

A braking arrangement includes a torque plate, a torque button, and a sacrificial bushing. The torque button comprises a head portion and a shaft portion, wherein the head portion is configured to extend at least partially into a torque pocket of an end plate of a brake stack and the shaft portion is configured to extend through an aperture disposed in a back leg of the torque plate. The bushing is configured to be removably coupled between the shaft portion of the torque button and the back leg of the torque plate.

A method of taxiing an aircraft may comprise: determining, via a brake controller, whether the aircraft is taxiing with a first thrust provided from a first side of the aircraft, a second thrust from a second side of the aircraft, or both the first thrust and the second thrust; and modifying, via the brake controller, a first brake pressure supplied to a first brake disposed on the first side of the aircraft as a function of pedal deflection in response to the taxiing with the first thrust only.

A method of taxiing an aircraft may comprise: determining, via a brake controller, whether the aircraft is taxiing with a first thrust provided from a first side of the aircraft, a second thrust from a second side of the aircraft, or both the first thrust and the second thrust; and modifying, via the brake controller, a first brake pressure supplied to a first brake disposed on the first side of the aircraft as a function of pedal deflection in response to the taxiing with the first thrust only.

A method of taxiing an aircraft may comprise determining, via a controller, whether the aircraft is taxiing with fewer brakes active than a total number of brakes; and modifying, via the controller, a brake pressure supplied to an active brake of the aircraft as a function of pedal deflection in response to determining the aircraft is taxiing with fewer brakes active relative to the total number of brakes.

A method of taxiing an aircraft may comprise determining, via a controller, whether the aircraft is taxiing with fewer brakes active than a total number of brakes; and modifying, via the controller, a brake pressure supplied to an active brake of the aircraft as a function of pedal deflection in response to determining the aircraft is taxiing with fewer brakes active relative to the total number of brakes.

A landing gear system includes a wheel rotatably coupled to the axle about an axis. A motor is fixedly positioned relative to the axle with a clutch assembly operably coupled to an output shaft of the motor. The landing gear includes an actuator and a drive assembly. The actuator applies a braking force to the wheel. The drive assembly includes a pinion gear and a drive gear rotatably associated with the pinion gear. The drive gear is configured to transfer a rotational force to the wheel in order to provide autonomous taxiing capability. Both the brake assembly and the drive assembly are operably coupled to the clutch assembly so that the output shaft of the motor drives both the brake assembly and the drive assembly.

A landing gear system includes a wheel rotatably coupled to the axle about an axis. A motor is fixedly positioned relative to the axle with a clutch assembly operably coupled to an output shaft of the motor. The landing gear includes an actuator and a drive assembly. The actuator applies a braking force to the wheel. The drive assembly includes a pinion gear and a drive gear rotatably associated with the pinion gear. The drive gear is configured to transfer a rotational force to the wheel in order to provide autonomous taxiing capability. Both the brake assembly and the drive assembly are operably coupled to the clutch assembly so that the output shaft of the motor drives both the brake assembly and the drive assembly.

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.