Patent ID: 8548714

Claim:
A method for facilitating the standardization of a thrust control for a plurality of turbo-engines ( 3 ) of an aircraft (AC) provided with at least two turbo-engines ( 3 ) being symmetrical compared to the fuselage ( 1 ), speeds of said turbo-engines ( 3 ) being individually controlled by throttle control levers ( 4 ), respectively associated with said turbo-engines ( 3 ) and able to occupy several positions, each one of said levers ( 4 ) being associated with artificial force gradient means and with at least one position sensor (S), comprising: A/ a current position of each one of said throttle levers is determined by the at least one position sensor (S); B/ a mean of said current positions is calculated by a calculating means ( 19 ) and C/ for each one of said levers ( 4 ): i) a corresponding current position is compared with said calculated mean, by a comparison means ( 21 ); ii) when the deviation between said current position and said mean is at least equal to a predetermined threshold value, the intensity of the artificial force gradient produced by said force gradient means ( 9 a ) associated with said lever ( 4 ) as a function of said deviation, is adjusted by servo control means ( 25 ); and iii) said corresponding current position is manually modified, via an intentional action, so as to align, at least approximately, a position of said throttle lever ( 4 ) on said calculated mean position, said alignment being facilitated via an adjustment of the intensity of an artificial force gradient by said servo control means ( 25 ).