Dual gain digital engine control

1. An engine control system for an aircraft, comprising:

an engine disposed within the aircraft;

a digital engine control disposed on the aircraft and being configured to receive and process inputs from the aircraft; and

a gain logic stored on the digital engine control for utilizing the inputs and transmitting command data to the engine to allow rotor speed deviations from a set point, thereby regulating the performance of the engine, the gain logic allows rotor speed deviations from the set point for a selected durational time constant.

2. The engine control system of claim 1 , wherein the durational time constant resets when the rotor speed returns to the set point.

3. The engine control system of claim 1 , wherein the gain logic returns the rotor speed to the set point when the rotor speed exceeds an operational limit.

4. The engine control system of claim 3 , wherein the operational limit is an acceptable rate of change of the rotor speed.

5. The engine control system of claim 1 , wherein the gain logic returns the rotor speed to the set point when the rotor speed exceeds a boundary limit.

6. The engine control system of claim 1 , further comprising:

a system logic stored on the digital engine control for utilizing the inputs and transmitting the command data to the engine to maintain the rotor speed at the set point;

wherein the digital engine control is programmed to selectively alternate between system logic and gain logic to regulate the performance of the engine.

7. The engine control system of claim 6 , further comprising:

a control device disposed on the aircraft, the control device being configured to allow a user to manually select between system logic and gain logic.

8. The engine control system of claim 7 , wherein the digital engine control is programmed to override the control device during critical situations.

9. The engine control system of claim 6 , wherein the selection between system logic and gain logic is performed automatically by the digital engine control.

10. The engine control system of claim 6 , wherein the command data is transmitted wirelessly to the engine.

11. The engine control system of claim 1 , wherein the digital engine control is a full authority digital engine control.

12. The engine control system of claim 1 , wherein the digital engine control is a limited authority digital engine control.

13. The engine control system of claim 1 , wherein the digital engine control is remote from the aircraft.

14. A method of controlling an engine of an aircraft, comprising:

utilizing an engine control system to control rotor speed of rotor blades of the aircraft at a selected set point;

providing a digital engine control within the engine control system;

receiving inputs within the digital engine control;

storing a gain logic on the digital engine control;

storing a system logic on the digital engine control;

processing the inputs with at least one of the gain logic and the system logic to generate command data; and

transmitting the command data from the digital engine control to the engine for permitting deviations in the rotor speed from the set point.

15. The method of claim 14 , wherein the digital engine control is programmed to alternate between the system logic and the gain logic.

16. The method of claim 15 , wherein the digital engine control is operable in either a manual mode or an automatic mode.

17. The method of claim 16 , wherein, in the manual mode, a user of the aircraft manually selects between the system logic and the gain logic.

18. The method of claim 16 , wherein, in the automatic mode, the digital engine control automatically selects between the system logic and the gain logic.