Abstract: An aircraft control system 100 including a control assembly 110 having control units, including a first control unit 130 for controlling actuation of the aircraft component during a first time period, using electrical resource 512 from a first electrical resource device 510, and a second control unit 140 for controlling actuation of the aircraft component during a second time period, and a switch mechanism 120 for switching control of the actuation of the aircraft component between the first and second control units, wherein the switch mechanism has a first electrical resource device status input 513 for indicating the status of the first electrical resource device 510 and wherein, the switch mechanism is configured to switch control between the first 130 and second 140 control units based on the first electrical resource device status input 513.

Abstract: An aircraft system for an aircraft, the aircraft system including a controller configured, during a take-off procedure, to receive a first signal indicative of a climb rate of the aircraft and, when the controller determines, on the basis of the first signal, that the climb rate of the aircraft is positive, cause a retraction alert to be issued to a flight crew of the aircraft, the retraction alert indicative that a landing gear of the aircraft is retractable.

Abstract: An aircraft system for an aircraft, the aircraft system including a controller configured, during a take-off procedure, to determine that a one engine inoperative condition is met and determine that a predetermined take-off criterion is met. The controller is configured, on the basis of a determination that the one engine inoperative condition is met, and prior to receiving a command to retract a landing gear of the aircraft, to initiate automatic opening of a landing gear bay door associated with the landing gear from a closed position towards an open position when the controller determines that the predetermined take-off criterion is met, and inhibit the automatic opening when the controller determines that the predetermined take-off criterion is not met.

Abstract: An aircraft system for an aircraft is disclosed having a controller that is configured, during a take-off procedure, to initiate, prior to receiving a command to retract a landing gear, automatic opening of a landing gear bay door associated with the landing gear from a closed position towards an open position, on the basis of a determination, made when a speed of the aircraft is determined by the controller to be equal to or greater than a first threshold speed, that a one engine inoperative condition is met.

Abstract: The invention relates to a method of diagnosing non-alcoholic steatohepatitis (NASH) using molecular markers. The inventive method consists in detecting and quantifying, in vitro in a hepatic tissue sample, the levels of a protein which can be used as a NASH molecular marker and which is selected from apolipoprotein A1, sub-unit ? of the mitochondrial ATPase, leukotriene A4 hydrolase, keratin 18, guanidine acetate N-methyltransferase, superoxide dismutase, albumin, antioxidant protein 2 (isoform 1), prohibitin 1, methionine adenosyl transferase, long-chain acyl CoA dehydrogenase, selenium binding protein, antioxidant protein 2 (isoform 2), and combinations of same. The invention further consists in comparing the results obtained with the normal values of said proteins in healthy hepatic tissue. Said method can be used to diagnose NASH and/or to assess a patient's potential risk of developing NASH.