A rudder bar includes a main module provided at least with pedals and with all the elements subject to maintenance, the main module being one-piece and detachable relative to a support frame integrated into the floor of the cockpit of the aircraft, so as to exhibit significant flexibility with respect to its maintainability, particularly in the event of the failure of a component, by allowing quick intervention both on a local level and an overall level.

A rudder bar includes a main module provided at least with pedals and with all the elements subject to maintenance, the main module being one-piece and detachable relative to a support frame integrated into the floor of the cockpit of the aircraft, so as to exhibit significant flexibility with respect to its maintainability, particularly in the event of the failure of a component, by allowing quick intervention both on a local level and an overall level.

Systems and methods are provided for an irreversible clutch to prevent back-drive. The irreversible clutch may transfer torque and/or rotation received at a first end to a second end, but may not transfer torque and/or rotation received at the second end to the first end. The irreversible clutch may prevent unintended adjustment of one or more rudder pedals and/or a rudder pedal assembly.

Systems and methods are provided for an irreversible clutch to prevent back-drive. The irreversible clutch may transfer torque and/or rotation received at a first end to a second end, but may not transfer torque and/or rotation received at the second end to the first end. The irreversible clutch may prevent unintended adjustment of one or more rudder pedals and/or a rudder pedal assembly.

A system and method for improved system efficiency of an integrated power and control unit (IPCU) of an aircraft is disclosed. The system uses an open-loop cooling system and turbo machine power matching to provide wide operation range without over-sizing. In order to reduce the temperature of the air flow through the cooling heat exchanger, the cooling turbine need to expand further in the same time generating power but the power could be higher than the compressor could absorb so a generator that would convert the power and used in supplying the aircraft would result in more efficient system.

A pedal system includes a support base; a first lever that is pivotally mounted to the support base; a second lever that is pivotally mounted to the support base; a first pedal coupled to the first lever and configured to be engaged by a foot of a user to rotate the first lever: a second pedal coupled to the second lever and configured to be engaged by a foot of the user to rotate the second lever, and an adjustment assembly configured to adjust a default rotational orientation, about an axis of rotation, of the first and the second lever, the first and the second lever positioned at the default orientation when no external force is applied to the first and the second lever.

A pedal system includes a support base; a first lever that is pivotally mounted to the support base; a second lever that is pivotally mounted to the support base; a first pedal coupled to the first lever and configured to be engaged by a foot of a user to rotate the first lever: a second pedal coupled to the second lever and configured to be engaged by a foot of the user to rotate the second lever, and an adjustment assembly configured to adjust a default rotational orientation, about an axis of rotation, of the first and the second lever, the first and the second lever positioned at the default orientation when no external force is applied to the first and the second lever.

Systems and methods are described for changing the performance of an aircraft by customizing aircraft control system parameters based on a subjective personal preference of a pilot. The system includes a user interface for receiving the customized aircraft control system parameters from the pilot. A first aircraft control module may receive the customized aircraft control system parameters from the user interface, and also receive flight control commands from the pilot. The received flight control commands and the received customized aircraft control system parameters may be processed by the first aircraft control module to cause the aircraft to perform according to customized characteristics as determined by the pilot.

Systems and methods are described for changing the performance of an aircraft by customizing aircraft control system parameters based on a subjective personal preference of a pilot. The system includes a user interface for receiving the customized aircraft control system parameters from the pilot. A first aircraft control module may receive the customized aircraft control system parameters from the user interface, and also receive flight control commands from the pilot. The received flight control commands and the received customized aircraft control system parameters may be processed by the first aircraft control module to cause the aircraft to perform according to customized characteristics as determined by the pilot.

According to one embodiment, a method of adjusting an aircraft pedal assembly includes providing a pedal linkage coupled between a pedal and an attachment assembly situated proximate to an aircraft instrument panel. A brake cylinder is provided coupled between the pedal and the attachment assembly. The pedal linkage is rotated in response to an adjustment input. The pedal linkage is maintained approximately parallel to the brake cylinder during rotation of the pedal linkage.