Abstract: A process for monitoring the validity of a speed cue of an aircraft may include computing a coefficient of lift, which is representative of the lift of the aircraft, on the basis of values of static and total pressure. A first value of angle of incidence is computed on the basis of the computed coefficient of lift, and a second value of angle of incidence is determined. The difference between the first and second values of angle of incidence is computed, and the absolute value of the difference is compared with a predetermined threshold value. Based on the comparison, the speed cue is deemed valid if the absolute value of the difference is below the threshold value and deemed invalid otherwise.

Abstract: A process for improving the landing of an aircraft may include, prior to the aircraft contacting the ground, nose-up under-deflecting the aircraft's adjustable horizontal tail plane and nose-up deflecting the elevators. This arrangement increases the maximum nosedown swing of the elevators to increase the ability of the elevators to make the nose of the aircraft tilt downwards.

Abstract: A process and device for optimization of deflection of spoiler flaps of an aircraft in flight may, in real time, compute an incidence potential available to be consumed by the spoiler flaps without endangering the aircraft and deflect the spoiler flaps toward the instructed deployed position as a function of the incidence potential.

Abstract: Process and device for the optimization of the deflection of the spoiler flaps of an aircraft in flight. According to the invention, in real time: an incidence potential (A) liable to be consumed by said spoiler flaps (7) without endangering said aircraft is computed; and said spoiler flaps (7) are deflected, towards the instructed deployed position, as a function of said incidence potential (A).

Abstract: Process for improving the landing of an aircraft. According to the invention, prior to the making of contact of the aircraft (1) with the ground, the adjustable horizontal tail plane (2) is nose-up under-deflected and the elevators (4) are nose-up deflected.

Abstract: The monitoring device (1) comprises a means (2) for considering the values of static and total pressure, used to determine the speed cue, a means (5) for computing on the basis of these values a coefficient of lift which is representative of the lift of the aircraft, a means (7) for computing on the basis of this coefficient of lift a first value of angle of incidence, a means (9) for determining a second value of angle of incidence, a means (12) for computing the difference between these first and second values of angle of incidence, a means (15) for comparing the absolute value of this difference with a predetermined threshold value, and a means (17) for deducing from this difference whether the speed cue is or is not valid.