Patent ID: 8660770

Claim:
A system for controlling at least one engine ( 1 ) of an aircraft (AC), comprising a specific moving control lever ( 5 ), said lever ( 5 ) being able to occupy two extreme positions (I, IV) corresponding to an idle speed (I) and to a maximum speed (IV) of said engine ( 1 ), as well as an intermediary range of automatic regulation of the speed of said engine ( 1 ), a lower limit of said intermediary range being defined by the extreme position (I) corresponding to the idle speed, wherein: said intermediary range ( 6 ) comprises a single marked position (II), corresponding to an upper limit thereof, with which there are associated at least one engine speed corresponding to a climbing phase of said aircraft (AC) and at least one automatic speed corresponding to said automatic regulation, following the climbing phase; said lever ( 5 ) is able to occupy another take-off and go-around marked position (III), with which there are associated a take-off speed and a go-around speed; and said system ( 4 ) further comprising: a processor ( 7 ) for determining a usual flight phase of said aircraft (AC); and a controller ( 8 ) for automatically controlling the speeds of said engine ( 1 ) associated with each one of said marked positions (II, III), wherein the speed corresponding to the climbing phase of said aircraft (AC), associated with said marked position (II) of the intermediary range ( 6 ), as well as said take-off speed and said go-around speed, associated with said take-off and go-around marked position (III), are automatically determined.