Abstract: A programmable electronic computer embedded in an avionics environment on board an aircraft for implementing at least one critical function and associated electronic device, method and computer program are disclosed. In one aspect, the electronic computer includes at least one control module configured to implement a respective critical function and configured to deliver at least one output data item associated with the critical function, and at least one monitoring module of a control module of another electronic computer. Each monitoring module configured to implement the same respective critical function as the one implemented by the monitored control module.

Abstract: A backup actuation control unit for controlling an actuator dedicated to a given surface. The backup actuation control unit comprises a processing unit operatively connected to one of a flight control computer and a backup flight control computer, to an actuator used for actuating a given surface and to at least one primary actuation control unit, each of the at least one primary actuation control unit for controlling a corresponding actuator used for actuating the given surface, wherein the processing unit receives a surface position command signal from one of the flight control computer and the backup flight control computer and an actuator position signal received from the actuator and provides a corresponding command signal to the actuator if an engagement signal is received from the flight control computer or the backup flight control computer and from the at least one primary actuation control unit.

Abstract: A backup actuation control unit for controlling an actuator dedicated to a given surface. The backup actuation control unit comprises a processing unit operatively connected to one of a flight control computer and a backup flight control computer, to an actuator used for actuating a given surface and to at least one primary actuation control unit, each of the at least one primary actuation control unit for controlling a corresponding actuator used for actuating the given surface, wherein the processing unit receives a surface position command signal from one of the flight control computer and the backup flight control computer and an actuator position signal received from the actuator and provides a corresponding command signal to the actuator if an engagement signal is received from the flight control computer or the backup flight control computer and from the at least one primary actuation control unit.

Abstract: A programmable electronic computer embedded in an avionics environment on board an aircraft for implementing at least one critical function and associated electronic device, method and computer program are disclosed. In one aspect, the electronic computer includes at least one control module configured to implement a respective critical function and configured to deliver at least one output data item associated with the critical function, and at least one monitoring module of a control module of another electronic computer. Each monitoring module configured to implement the same respective critical function as the one implemented by the monitored control module.