Patent ID: 7636617

Claim:
A flight control indicator for an aircraft, said flight control indicator comprising: a set of information sources; a computation unit which is connected to said set of information sources and which determines, on the basis of information emanating from said set of information sources, a mean current thrust of the current thrust of all engines of the aircraft; and a display device which is connected to said computation unit and which presents, on a display screen, a single indication of said determined mean current thrust that is associated with a thrust scale, wherein: said display device is a head-up display device which presents said indication and said thrust scale, superimposed on the environment prevailing in front of the aircraft, and wherein said thrust scale comprises: a first limit of minimum thrust of an automatic thrust control system; and a second limit of maximum thrust of the automatic thrust control system, and when the automatic thrust control system is active, said display device presents an indication of theoretical thrust commanded by said automatic thrust control system; said thrust scale furthermore includes an auxiliary limit of maximum thrust available on the basis of the engines of the aircraft; and said single indication comprises a single indicator set for representing said determined mean current thrust.