Abstract: Disclosed is a method and device for detecting lateral dissymmetry of an aircraft. A control parameter determination unit is used to determine a current value of a control parameter representative of all roll control surfaces of the aircraft, and a control parameter comparison unit is used to compare the determined current value with a predetermined reference value. A current deflection angle of a lateral stick of the aircraft is also determined, and the determined current deflection angle is compared with a predetermined angle value. A visual alarm signal is output, when the current value of the roll control surfaces of the aircraft is greater than a predetermined reference value and the lateral stick is at a deflection angle that is greater than a predetermined angle value.

Abstract: Method and device for detecting a lateral dissymmetry of an aircraft. The detection device (1) comprises a means (7) for detecting a lateral dissymmetry, as a function of the cement value of a control parameter which is representative of the roll control surfaces of the aircraft, and of a current angle of deflection of a lateral stick of the aircraft.

Abstract: According to the invention, prior to the resource, the adjustable horizontal tailplane (2) is nose-up deflected and the elevators (4) are nose-down deflected.

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: Process for reducing the aerodynamic loads applied to the elevators of an aircraft during takeoff. According to the invention, prior to the rotation, the adjustable horizontal tailplane (2) is nose-up overdeflected and the elevators (4) are nose-down deflected.

Abstract: A process and device are disclosed for detecting the lift-off of an aircraft during the course of take-off. Both during a phase of rolling down the runway and a take-off phase, the quantity A=K.h+&thgr; is calculated. In this equation, &thgr; is the longitudinal attitude of the aircraft, h is the height of the aircraft's tail skid, and K is a constant. After the value of A is calculated for the rolling phase, it is stored. The take-off phase of the aircraft is determined by detecting a particular difference between the stored value of A and a current calculation of A.

Abstract: Process and device for detecting the lift-off of an aircraft in the course of take-off.