Abstract: A system for aiding piloting of an airplane during a final approach includes current roll angle sensors that measures a current roll angle of the airplane, and a maximum roll angle calculation device that calculates a limit roll angle corresponding to a maximum roll angle at which an end point of the airplane will not strike the ground. The system also includes a display for automatically presenting on a single screen a first characteristic sign illustrating the current roll angle and a second characteristic sign illustrating the limit roll angle. If a potential ground collision is presented by too high of a current roll angle, an alarm may be emitted or automatic control of the airplane may occur to correct the roll angle.

Abstract: A process and device for optimising the performance of an aircraft in the presence of a lateral dissymmetry is disclosed. The device (1) includes means (2, 3, 4, 5, 7, 9) for controlling, during a lateral dissymmetry, at least one rudder such as to generate an optimum sideslip for reducing the drag of the aircraft.

Abstract: The device (1) includes means (2, 3, 4) for observing the overall conditions of the aircraft and for determining whether the lateral behavior thereof is normal.

Abstract: Method and device for detecting an erroneous speed generated by an air data inertial reference system. The device can be configured to detect an erroneous speed provided by an air data and inertial data system and to generate a substitution speed.

Abstract: An assistance method and device for lateral control of an aircraft upon an approach phase is disclosed. The device (1) comprises means (25) to predict in flight a risk of runway lateral excursion and means (20) to advise the pilot of the aircraft about the existence of such a risk.

Abstract: A method and device for reducing on an aircraft lateral effects of a turbulence. The device (1) includes means (2, 3, 5, 7, A1, A2) for calculating and applying a roll control command and a yaw control command enabling the side effects generated by a turbulence event to be attenuated on the aircraft.

Abstract: The system (1) comprises means (5) for calculating a limit roll angle and a display (7) for automatically presenting on a screen (10) a first characteristic sign illustrating the current value of the roll angle and a second characteristic sign illustrating said limit roll angle allowing to check that an end point of the aircraft does not come into contact with the ground.