Patent ID: 6904340

Claim:
A flight control indicator for an aircraft, intended to supply the thrust (THR) generated by at least one engine of the aircraft, said flight control indicator ( 1 ) comprising: information sources ( 2 ) supplying at least information relating to a control parameter of the engine; means ( 3 ) for processing information received from said information sources ( 2 ); and display means ( 4 ) able to present information relating to said engine on at least one viewing screen ( 5 ), wherein said information processing means ( 3 ) determine, for said engine, at least: the maximum thrust which is available for the current phase of flight, as a function of the current configuration of the aircraft and for the current anemometric conditions; the prescribed thrust; and the actual thrust, said prescribed and actual thrusts being expressed as a percentage of said maximum thrust, and wherein said display means ( 4 ) present, on said viewing screen ( 5 ), a dial ( 6 ) which is graduated in percentage, whose maximum represents said maximum thrust, and which is furnished with first and second characteristic signs ( 7 , 8 ) whose positions on said dial ( 6 ) respectively represent said prescribed and actual thrusts.