Abstract: A device including an angle of attack reduction unit is disclosed having a computation unit for computing, after a stall warning has been transmitted and in the event of a lack of response from the crew, a nose down pitch command, and a display unit for displaying, on a vertical display system of the aircraft (AC), an indicator representing the nose down pitch command, a roll control unit including a computation unit for computing a roll command and a display unit for displaying, on a lateral display system of the aircraft (AC). An indicator representing the roll command, and a stabilization unit including a computation unit for computing a nose up pitch command and a display unit for displaying, on the vertical display system, an indicator representing the nose up pitch command, the device assisting the crew of the aircraft (AC) in quickly and efficiently recovering the aircraft (AC) from the stall condition.

Abstract: A device for lateral control of an aircraft includes a calculating unit for automatically applying, if conditions for turning of the aircraft are met, a symmetrical braking value at a brake assembly. Subsequently, in the course of the turn, the device automatically distributes this symmetrical braking value in differential braking between a braking device of the left main landing gear and a braking device of the right main landing gear of the aircraft. Distribution of the symmetrical breaking is performed as a function of current directional command orders in such a way as to maintain a constant overall braking level for, at least for directional command orders below a predetermined threshold.

Abstract: Energy protection device for an aircraft. The device (1) comprises units (12, 14, 15) for automatically deactivating an energy protection function, if a return of the aircraft to an operational flight domain is detected after the activation of this protection function, and for automatically managing an autothrust (2), if at least one of the following conditions is satisfied: a relaxing of a control member is detected, and the angle of attack of the aircraft is below a predetermined threshold.

Abstract: Energy protection device for an aircraft. The device (1) comprises units (12, 14, 15) for automatically deactivating an energy protection function, if a return of the aircraft to an operational flight domain is detected after the activation of this protection function, and for automatically managing an autothrust (2), if at least one of the following conditions is satisfied: a relaxing of a control member is detected, and the angle of attack of the aircraft is below a predetermined threshold.

Abstract: The device includes, but is not limited to a calculating unite for automatically applying, if conditions for turning of the aircraft are met, a symmetrical braking value at a brake assembly, then in the course of the turn automatically distributing this symmetrical braking value in differential braking between braking device of the left main landing gear and braking device of the right main landing gear of the aircraft, as a function of current directional command orders, in such a way as to maintain a constant overall braking level, at least for directional command orders below a predetermined threshold.