Abstract: The invention pertains to a method and apparatus for verifying the consistency of the values given by an angle of attack probe of an aircraft. The method and apparatus verifies the proper operation of the angle of attack probe by using the aircraft's vertical load factor measurement provided by an accelerometer to estimate the angle of attack and then comparing the estimated angle of attach with the measure angle of attack.

Abstract: A reference value is arbitrarily selected from a range of possible aircraft rotation speeds. A position of a trimmable horizontal stabilizer is angled in accordance with a centering of the reference value. A deviation between the reference value and an accelerating speed value of the aircraft is determined. Elevators or the horizontal stabilizer are controlled, prior to rotation, in accordance with the determined deviation.

Abstract: A reference value VRef is arbitrarily selected from the range of possible rotation speeds, the position of the trimmable horizontal stabiliser is angled at least in accordance with the centring, for said value VRef, the deviation between said reference value and the accelerating aircraft speed value VC is determined, and the elevators and/or the trimmable horizontal stabiliser of the aircraft are controlled, prior to rotation, in such a way that said deviation is taken into account.

Abstract: A process and a device for verifying the consistency of the measurements made by an angle-of-attack probe (2) mounted on an aircraft. The device (1) includes:first system (3) for computing a first coefficient of lift of the aircraft from a measurement from the probe (2) and from data relating to the aircraft;second system (5) for computing a second coefficient of lift from information about the aircraft;system (6) for computing the difference between the first and second coefficients of lift and for deducting therefrom that the measurement is or is not consistent.

Abstract: According to the invention, attenuator means (8) are provided, making it possible to limit the rate of rotation of the airplane on takeoff, so as to avoid the tail of the airplane striking the ground and to reduce the dispersion of the rotation rates.

Abstract: System for control of an aerodynamic surface (1) of an aircraft, comprising an intentional actuation member (5) and a hydraulic jack (2) intended to deflect said aerodynamic surface (1).According to the invention, the system comprises means (14) for detecting the difference in pressures prevailing in said jack (2), on either side of the piston (2C) of the latter, and calculation means (11) comprising:a computer delivering values of a coefficient which is a decreasing function of said difference in pressures; anda multiplier receiving an electrical signal (dp) representing a demanded deflection and said coefficient and addressing a first deflection command (C2) formed by the product of said signal and said coefficient to said servovalve.

Abstract: A system for reducing the forces applied to the wings of an aircraft in flight includes an accelerometer for measuring the vertical acceleration of the aircraft and generators for generating signals to control the aerodynamic surfaces in the wings of the aircraft as a function of the acceleration measured by the accelerometer. The control signal generator is not activated except when the vertical acceleration exceeds a predetermined value.