Abstract: A process for managing the activating of emission of a given warning message in an aircraft comprises transmission, from a monitoring system to an authorization-issuing system, of an emission authorization request. The request has a priority attribute known as request priority attribute. The process also includes transmission, from the authorization-issuing system to the monitoring system, of an emission authorization. The transmission of the emission authorization is effected if the request priority attribute is higher than a current priority threshold. In addition, the process includes activation of emission of the given warning message. The activation may be effected if an alert condition associated with the given warning message is detected and if a priority attribute associated with the alert condition is higher than or equal to the request priority attribute.

Abstract: A method and a device for accessing the documentation of an aircraft according to alarms generated therein, where the documentation includes at least one document that is modifiable independently of the manufacturer of the aircraft. After having received at least one indication relating to at least one alarm generated by the avionics of the aircraft, at least one datum relating to the at least one alarm, including a link to at least one element of the documentation, is extracted and displayed.

Abstract: A method and a device for detecting a thrust dissymmetry of an aircraft during a landing are disclosed. The detection device (6) comprises means (7) for detecting, upon a landing, that at least one of the engine control levers occupies an intermediary position comprised between a position threshold and a maximum speed position, as well as at least another engine control lever occupies an idling position, and means (9, 13) for triggering a warning when a landing condition is validated and at least one of the control levers occupies said intermediary position, at least another control lever occupying said idling position.

Abstract: A method for managing an interruption of emission, in an aircraft, of an acoustic message including an information item about a state of part of the said aircraft and/or about its environment, wherein the acoustic message is structured into one or more successive acoustic fragments each representative of the information item, the method includes the steps of: delaying, starting from a given moment, the execution of a decision to interrupt the emission of the acoustic message until the end of emission of an acoustic fragment that is in the course of emission at the given moment; and executing the interruption decision.

Abstract: The invention relates to a method for producing an audible warning when an aircraft autopilot is deactivated. The method includes a) transmitting a first sound in the aircraft cockpit during a time ranging from a first predetermined value and a second predetermined value and b) transmitting a second sound in the aircraft cockpit. The invention also relates to an audible warning device having a monitoring unit for monitoring the deactivation of the aircraft autopilot and an activation unit for emitting an audible warning in the cockpit, where the activation unit is constructed such that it activates the first sound emission whose length ranges from the first predetermined value and a second predetermined value and a second sound when the monitoring unit detects the deactivation of the autopilot.

Abstract: The invention in particular has as an object a method and a device for accessing the documentation of an aircraft according to alarms generated therein, the documentation comprising at least one document modifiable independently of the manufacturer of the aircraft. After having received (305) at least one indication relating to at least one alarm generated by the avionics of the said aircraft, at least one datum relating to the said at least one alarm, comprising a link to at least one element of the said documentation, is extracted (315) and displayed (325).

Abstract: A method and a device for detecting a thrust dissymmetry of an aircraft during a landing are disclosed. The detection device (6) comprises means (7) for detecting, upon a landing, that at least one of the engine control levers occupies an intermediary position comprised between a position threshold and a maximum speed position, as well as at least another engine control lever occupies an idling position, and means (9, 13) for triggering a warning when a landing condition is validated and at least one of the control levers occupies said intermediary position, at least another control lever occupying said idling position.

Abstract: The invention relates to a method for producing an audible warning when an aircraft autopilot (2) is deactivated consisting: a) in transmitting a first sound in the aircraft cockpit during a time ranging from a first predetermined value (d1) and a second predetermined value (d2) and b) in transmitting a second sound in the aircraft cockpit. Said invention also relates to an audible warning device (1) comprising first means (10) for monitoring the deactivation of the aircraft autopilot (2) and means (12) for emitting an audible warning in the cockpit, wherein said second means is constructed in such a way that it activates the first sound emission whose length ranges from the first predetermined value (d1) and a second predetermined value (d2) and a second sound when the first means detects the deactivation of the autopilot.

Abstract: The invention relates to a method for managing an interruption of emission, in an aircraft, of an acoustic message comprising an information item about a state of part of the said aircraft and/or about its environment, characterized in that, the acoustic message being structured into one or more successive acoustic fragments each representative of the said information item, the said method comprises the steps: of delaying (E3), starting from a given moment, the execution of a decision to interrupt the emission of the acoustic message until the end of emission of an acoustic fragment that is in the course of emission at the said given moment, and of executing (E4) the said interruption decision.

Abstract: The invention relates to a process for managing the activating of emission of a given warning message in an aircraft, characterized in that it comprises the following successive steps: transmission (E2), from an alert system (10) to an authorization-issuing system (20), of an emission authorization request, the said request having a priority attribute known as request priority, transmission (E3), from the said authorization-issuing system (20) to the said alert system (10), of an emission authorization, the transmission of the said emission authorization being effected if the said request priority attribute is higher than a current priority threshold, activation of emission of the given warning message, the said activation being effected if an alert condition associated with the given warning message is detected and if a priority attribute associated with the said alert condition is higher than or equal to the said request priority attribute.