Patent ID: 8223039

Claim:
A method for detecting, upon a landing, a thrust dissymmetry of an aircraft (AC) provided with at least two engines ( 3 . 1 , 3 . 2 ) individually controlled by control levers ( 4 . 1 , 4 . 2 ) able to occupy several positions each associated with an engine speed, amongst which a position ( 0 ) corresponding to the idling speed and a position (III) corresponding to a maximum take-off and go-around speed, comprising: A/ determining preliminarily a position threshold being intermediary between said idling position ( 0 ) and said maximum speed position (III), and such that, when at least one of said control levers ( 4 . 1 , 4 . 2 ) is positioned between said position threshold and said maximum speed position (III) and at least another of said control levers ( 4 . 1 , 4 . 2 ) occupies said idling position ( 0 ), a thrust dissymmetry of the engines ( 3 . 1 , 3 . 2 ) is observed; B/ checking that at least one condition relating to landing is validated; C/ detecting that at least one of said control levers ( 4 . 1 , 4 . 2 ) occupies an intermediary position comprised between said position threshold and said maximum speed position (III), as well as that at least another control lever ( 4 . 1 , 4 . 2 ) occupies said idling position ( 0 ); and D/ when said landing condition is validated and at least one of said control levers occupies said intermediary position, at least another control lever occupying said idling position, emitting at least one warning to the pilots of said aircraft (AC), so as to notify them of a position dissymmetry of the control levers ( 4 . 1 , 4 . 2 ).