Assisted piloting method and device for an aircraft for use in the event of a first limit indicator breaking down

1. A method of assisting piloting of an aircraft having at least two engines, each engine having a plurality of parameters (Ng, T4, Tq) and each parameter having a limit, the method comprising:

displaying, from a first limit indicator for a pilot to view, information relating to a limiting parameter of said engines, the limiting parameter being the parameter amongst the parameters (Ng, T4, Tq) of the engines that is the closest to its limit; and

activating an assisted piloting mode in which the engines are automatically controlled without pilot intervention to keep each parameter (Ng, T4, Tq) of the engines below a respective predetermined threshold whenever said first limit indicator is no longer in a position to display said information.

2. The method according to claim 1 , wherein said engines are turbine engines, each having a free turbine and a gas generator, and said monitoring parameters (Ng, T4, Tq) comprise the speed (Ng) of the gas generator of each engine, the engine torque (Tq) of each engine, and the gas ejection temperature (T4) at the inlet to the free turbine of each engine.

3. The method according to claim 1 , wherein said engines are capable of operating at a plurality of ratings, and said predetermined thresholds is being modified as a function of current ratings of the engines.

4. The method according to claim 1 , wherein each parameter (Ng, T4, Tq) is maintained below the respective predetermined threshold by putting ceilings on said parameters (Ng, T4, Tq).

5. The method according to claim 1 , wherein each parameter (Ng, T4, Tq) is maintained below the respective predetermined threshold by putting a ceiling on the rate at which fuel is fed to said engines.

6. The method according to claim 1 , wherein a pilot activates said assisted piloting mode by manually requesting said assisted piloting mode for some minimum duration.

7. The method according to claim 1 , wherein the operation of said first limit indicator is monitored, and said assisted piloting mode is activated automatically when a breakdown of said first limit indicator is detected.

8. The method according to claim 1 , wherein the pilot of said aircraft is informed when said assisted piloting mode is activated.

9. The method according to claim 1 , wherein said aircraft is a rotorcraft provided with at least one lift rotor driven at a speed of rotation, and said assisted piloting mode is deactivated when said speed of rotation drops below a predetermined limit speed.

10. The method according to claim 1 , wherein said aircraft is a rotorcraft provided with at least one lift rotor driven at a speed of rotation, and said assisted piloting mode is deactivated when said lift rotor is subjected to deceleration greater than a predetermined limit deceleration.

11. An assisted piloting device for a rotorcraft having at least two engines, each engine having a plurality of parameters (Ng, T4, Tq) and each parameter having a limit, said device comprising:

a first limit indicator configured to display information relating to a limiting parameter of said engines, the limiting parameter being the parameter amongst the parameters (Ng, T4, Tq) of the engines that is the closest to its limit; and

a control member suitable for maintaining the parameters (Ng, T4, Tq) of said engines below predetermined thresholds when an assisted piloting mode is activated upon said first limit indicator being no longer in a position to display said information.

12. The assisted piloting device according to claim 11 , wherein said rotorcraft includes control means for commanding emergency conditions when an engine breaks down, and when the engines are operating normally, said control means serve to activate said assisted piloting mode during which the control member maintains the parameters (Ng, T4, Tq) of said engines below predetermined thresholds.

13. The assisted piloting device according to claim 11 , wherein said rotorcraft includes first control means for commanding a first emergency rating (OE130″) and second control means for commanding a second emergency rating (OEI2′) when an engine has broken down, and while the engines are operating normally, said first control means serve to activate an assisted piloting mode in which the control member maintains the parameters (Ng, T4, Tq) of said engines below predetermined first predetermined thresholds for a first normal operation rating, and said second control means enable an assisted piloting mode to be activated during which the control member maintains the parameters (Ng, T4, Tq) of said engines below second predetermined thresholds for a second normal operation rating.

14. The assisted piloting device according to claim 11 , wherein said control member is incorporated in a regulator member for the engines.

15. The assisted piloting device according to claim 11 , wherein said control member is incorporated in said first limit indicator.

16. A system for assisting piloting of an aircraft having an engine, the engine having a plurality of parameters and each parameter having a limit, the system comprising:

a first limit indicator configured to display information relating to a limiting parameter of the engine, the limiting parameter being the parameter amongst the parameters of the engine that is the closest to its limit; and

a controller configured to activate an assisted piloting mode in which the engine is automatically controlled to maintain the parameters of the engine below respective predetermined thresholds, which are respectively below the limits of the parameters, whenever the first limit indicator is unable to display the information relating to the limiting parameter of the engine.

17. The system of claim 16 wherein the aircraft has a plurality of engines, each engine having a plurality of parameters and each parameter having a limit, wherein:

the limiting parameter is the parameter amongst the parameters of the engines that is the closet to its limit and the controller is further configured to automatically control the engines to maintain the parameters of the engines below respective predetermined thresholds, which are respectively below the limits of the parameters of the engines, whenever the first limit indicator is unable to display the information relating to the limiting parameter of the engines.