Pressurized reserve lubrication system for a gas turbine engine

1. A lubrication system, comprising:

a main lubrication subsystem;

a reserve lubrication subsystem; and

a control subsystem operable to selectively communicate lubricant from said reserve lubrication subsystem under a pressure to supplement lubricant from said main lubrication subsystem in response to identification of a prolonged reduced-G condition.

2. The lubrication system as recited in claim 1 , wherein said pressure is provided via a gas.

3. The lubrication system as recited in claim 2 , wherein said gas is an inert gas.

4. The lubrication system as recited in claim 1 , wherein said pressure is provided via a liquid.

5. The lubrication system as recited in claim 1 , wherein said main lubrication subsystem and said reserve lubrication subsystem are in communication with a geared architecture of a gas turbine engine.

6. The method as recited in claim 5 , wherein said pressure provides lubricant to a journal pin of the geared architecture from said reserve lubrication subsystem to supplement lubricant from said main lubrication subsystem to the journal pin.

7. The lubrication system as recited in claim 1 , further comprising:

a main lubricant tank solenoid valve in communication with said control subsystem and said main lubrication subsystem, said control subsystem is operable to close said main lubricant tank solenoid valve in response to the prolonged reduced-G condition; and

a reserve lubricant tank solenoid valve in communication with said control subsystem, said control subsystem operable to open said reserve lubricant tank solenoid valve in response to the prolonged reduced-G condition.

8. The lubrication system as recited in claim 1 , wherein said control subsystem operable to selectively communicate lubricant from said reserve lubrication subsystem under a pressure to supplement lubricant from said main lubrication subsystem in response to a sensor operable to identify the prolonged reduced-G condition.

9. A gas turbine engine, comprising:

a geared architecture;

a main lubrication subsystem in communication with said geared architecture;

a reserve lubrication subsystem in communication with said geared architecture; and

a control subsystem operable to selectively communicate lubricant from said reserve lubrication subsystem under a pressure in response to identification of a prolonged reduced-G condition;

wherein said reserve lubrication subsystem includes a pressurized reserve lubricant tank that selectively communicates the lubricant.

10. The gas turbine engine as recited in claim 9 , wherein said geared architecture drives a fan at a lower speed than a low spool.

11. The gas turbine engine as recited in claim 9 , wherein said pressurized reserve lubricant tank is within at least one of a nacelle, an engine pylori and an aircraft wing.

12. The gas turbine engine as recited in claim 9 , further comprising a multiple of pressurized reserve lubricant tanks.

13. The gas turbine engine as recited in claim 9 , wherein said pressurized reserve lubricant tank is pressurized via a gas.

14. The gas turbine engine as recited in claim 13 , wherein said gas is an inert gas.

15. The gas turbine engine as recited in claim 9 , wherein said pressurized reserve lubricant tank is pressurized via a liquid.

16. A method of reducing lubrication starvation from a lubrication system with a main lubrication subsystem and a reserve lubrication subsystem, the main lubrication system in communication with a geared architecture of a gas turbine engine comprising:

communicating lubricant under a pressure to the geared architecture in response to identifying a prolonged reduced-G condition.

17. The method as recited in claim 16 , further comprising:

providing the pressure via a gas.

18. The method as recited in claim 16 , further comprising:

providing the pressure via a liquid.

19. The method as recited in claim 16 , further comprising:

communicating the lubricant under the pressure to a journal pin of the geared architecture.