A method of removing hydraulic fluid from an aircraft hydraulic system is disclosed including a hydraulically actuated mechanism that is actuated by an electrohydraulic servo valve, a hydraulic fluid port through which hydraulic fluid can escape, and a hydraulic fuse with a closed state and an open state between the electrohydraulic servo valve and the hydraulic fluid port. The hydraulic fluid port is opened, and then the activation of the electrohydraulic servo valve is controlled to force hydraulic fluid to escape from the hydraulic system via the hydraulic fluid port, the control being so that the hydraulic fuse does not enter and remain in the closed state.

An oxidation protection system disposed on a substrate is provided, which may comprise a boron layer comprising a boron compound disposed on the substrate; a silicon layer comprising a silicon compound disposed on the boron layer; and at least one sealing layer comprising monoaluminum phosphate and phosphoric acid disposed on the silicon layer.

An oxidation protection system disposed on a substrate is provided, which may comprise a boron layer comprising a boron compound disposed on the substrate; a silicon layer comprising a silicon compound disposed on the boron layer; and at least one sealing layer comprising monoaluminum phosphate and phosphoric acid disposed on the silicon layer.

An aircraft controller 5, aircraft braking system 13 and method for determining braking parameters. The aircraft controller 5 is configured to determine information associated with an aircraft taxiing route associated with an aircraft 1. On the basis of the information, the aircraft controller 5 determines a first braking parameter for a first main landing gear 8 of the aircraft 1 and a second braking parameter for a second main landing gear 9 of the aircraft 1 during a landing event. The first and second braking parameters are determined to result in asymmetrical braking between the first 8 and second 9 main landing gears during the landing event.

An aircraft controller 5, aircraft braking system 13 and method for determining braking parameters. The aircraft controller 5 is configured to determine information associated with an aircraft taxiing route associated with an aircraft 1. On the basis of the information, the aircraft controller 5 determines a first braking parameter for a first main landing gear 8 of the aircraft 1 and a second braking parameter for a second main landing gear 9 of the aircraft 1 during a landing event. The first and second braking parameters are determined to result in asymmetrical braking between the first 8 and second 9 main landing gears during the landing event.

A brake cooling system of the present disclosure includes an external cooling apparatus located externally from an aircraft (e.g., available on the ground at the gate during parking of the aircraft). The external cooling apparatus is in electronic communication with the aircraft via a communication channel such that the external cooling apparatus receives live data from the aircraft for intelligent aircraft brake cooling. The live data includes measured brake temperature. The brake cooling system further includes a controller for collecting aircraft data and generating a cooling apparatus control signal.

A brake cooling system of the present disclosure includes an external cooling apparatus located externally from an aircraft (e.g., available on the ground at the gate during parking of the aircraft). The external cooling apparatus is in electronic communication with the aircraft via a communication channel such that the external cooling apparatus receives live data from the aircraft for intelligent aircraft brake cooling. The live data includes measured brake temperature. The brake cooling system further includes a controller for collecting aircraft data and generating a cooling apparatus control signal.

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 system, and associated method, for reducing oxidation of a friction disk may include a braking assembly comprising the friction disk and a coolant loop coupled to the braking assembly, with the coolant loop being configured to circulate liquid coolant from the braking assembly. That is, the coolant loop may be configured to reduce the temperature of the braking assembly, thus reducing the rate/extent of oxidation of the friction disks and potentially enabling the concentration of oxygen around the braking assembly to be reduced.