Abstract: A system for an aircraft comprising a controller configured to obtain a first piece of information regarding whether the aircraft has achieved lift-off; to obtain a second piece of information regarding whether the aircraft is in a flight phase in an initial part of lift-off; to determine, on the basis of at least the first piece of information whether the gear is retractable, and, if the gear is retractable in an initial part of the lift-off, to trigger a landing-gear-retraction alarm taking an audio form and/or a visual form, and, if the gear is retractable after the initial part of the lift-off to optionally trigger a second landing-gear-retraction alarm taking an audio form and/or a visual form. A method implemented by the system is provided. Advantageously, an omission of the retraction of the landing gear of an aircraft is notified to its flight crew.

Abstract: A system for an aircraft comprising a controller configured to obtain a first piece of information regarding whether the aircraft has achieved lift-off; to obtain a second piece of information regarding whether the aircraft is in a flight phase in an initial part of lift-off; to determine, on the basis of at least the first piece of information whether the gear is retractable, and, if the gear is retractable in an initial part of the lift-off, to trigger a landing-gear-retraction alarm taking an audio form and/or a visual form, and, if the gear is retractable after the initial part of the lift-off to optionally trigger a second landing-gear-retraction alarm taking an audio form and/or a visual form. A method implemented by the system is provided. Advantageously, an omission of the retraction of the landing gear of an aircraft is notified to its flight crew.

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: An aircraft landing assistance system includes a processing unit configured to determine whether there is total failure of the aircraft's engines and, if yes, to determine a set of airports at which the aircraft could land from its current position, taking into account its current energy and current configuration. For each airport, the system determines a runway on which the aircraft could land and at least one possible landing direction of the aircraft on this runway and determines a reference point ahead of each runway, corresponding to a deployment point for the landing gear and a point of changing from a smooth configuration of the aircraft to a non-smooth configuration, to allow the aircraft to land on the runway. The system also commands the display, on an aircraft navigation screen, of a depiction of each of the runways and the reference points associated with these runways.