Patent ID: 8359129

Claim:
A method for controlling the thrust of a multi-engine aircraft, said method comprising: c) determining at least one engine command, by a command determining unit, wherein said at least one engine command commands each engine of said aircraft that has not failed to deliver a thrust substantially equal to a reduced thrust value; and d) applying, by a command application unit, said command determined in step c) to each of the engines of the aircraft that has not failed, wherein, said reduced thrust value determined in step c) is determined according to: a) a parameter representative of current weight of the aircraft, in which said parameter is determined by a weight determining device; and b) a reduced thrust value FOEI, which is calculated by a thrust calculation unit, by way of a reduced thrust value, proportional to said current weight, according to the following expression: FOEI=m.g. (γ cons+ 1 /f ) in which: m.g. is said current weight, wherein m is mass and g acceleration due to gravity; γcons is a gradient value corresponding to a reference gradient; and f is a current ratio between lift and drag of the aircraft.