The invention provides a control system and method of the anti-skid computers of an aircraft. The control system comprises two IMA computers (231, 232), comprising each one an Avionics Computer Control Device (241, 242), an Avionics Computer Monitoring Dev...

Flow evacuation system for an aircraft engine comprising an engine nozzle (31) that conveys the engine exhaust flow (11) and an eductor (33) receiving said engine exhaust flow (11) and the engine ventilation flow (13), the engine nozzle (31) having a final...

An Electrical Power System for supplying electrical power to the loads of a vehicle comprising a Power Generation Area (11); a Primary Distribution Area (13); a Secondary Distribution Area (15) including Electrical Power Load Management Units (EPLMUs) (17,...