Patent ID: 8374732

Claim:
A device for control of a plurality of support subsystems in an aircraft, the device comprising: a filtering unit configured to determine at least one command associated with at least one support subsystem of the plurality of support subsystems according to at least one context parameter, the at least one support subsystem relating to at least one of a generation and a distribution of an electrical capacity, a generation and a distribution of a hydraulic capacity, a generation of a pneumatic capacity, air conditioning and a pressurization, a fuel management and an auxiliary power engine; a display unit that displays at least one representation of the at least one determined command, the at least one representation of the at least one determined command comprising an indication relating to a state of the at least one support subsystem controlled by the at least one determined command; a selection unit that selects the at least one representation, wherein the selection unit employs a predetermined hierarchical structure to control the at least one support subsystem, when the at least one representation is selected, a first command accesses a plurality of representations of commands of a lower level of the predetermined hierarchical structure, and if the at least one representation is selected, a second command activates or deactivates all of the commands of the lower level of the predetermined hierarchical structure; and an activation unit that transmits the at least one determined command to the at least one support subsystem in response to an activation of the at least one selected representation.