An aircraft, comprising: first and second gas turbine engines (302, 304) having a first component (26, 30, 32, 34) and a second component (42, 46, 48, 50) that is redundant with the first component (26, 30, 32, 34); and an engine health monitoring system (EHMS) coupled to the first and second gas turbine engines (302, 304), the EHMS configured to: calculate a remaining useful life (412, 414) of the first component (26, 30, 32, 34) and of the second component (42, 46, 48, 50); calculate a rate-of-life consumption of the first component and of the second component; predict when failure of the first component (26, 30, 32, 34) and failure of the second component (42, 46, 48, 50) will occur based on the RUL of each (412, 414) and based on the respective rate-of-life consumption (402, 404) of each; and provide instructions for altering operation of the aircraft that affects the RUL of the first or second component (26, 30, 32, 34), (42, 46, 48, 50), characterized in that the first component (26, 30, 32, 34) is in the first turbine engine and the second redundant component (42, 46, 48, 50) is in the second turbine engine, and the EHMS is configured to provide the instructions such that the first or second gas turbine (302, 304) having the component with the lowest RUL is operated less stringently to increase the RUL of the component with the lowest RUL. first and second gas turbine engines (302, 304) having a first component (26, 30, 32, 34) and a second component (42, 46, 48, 50) that is redundant with the first component (26, 30, 32, 34); and an engine health monitoring system (EHMS) coupled to the first and second gas turbine engines (302, 304), the EHMS configured to: calculate a remaining useful life (412, 414) of the first component (26, 30, 32, 34) and of the second component (42, 46, 48, 50); calculate a rate-of-life consumption of the first component and of the second component; predict when failure of the first component (26, 30, 32, 34) and failure of the second component (42, 46, 48, 50) will occur based on the RUL of each (412, 414) and based on the respective rate-of-life consumption (402, 404) of each; and provide instructions for altering operation of the aircraft that affects the RUL of the first or second component (26, 30, 32, 34), (42, 46, 48, 50), characterized in that the first component (26, 30, 32, 34) is in the first turbine engine and the second redundant component (42, 46, 48, 50) is in the second turbine engine, and the EHMS is configured to provide the instructions such that the first or second gas turbine (302, 304) having the component with the lowest RUL is operated less stringently to increase the RUL of the component with the lowest RUL. calculate a remaining useful life (412, 414) of the first component (26, 30, 32, 34) and of the second component (42, 46, 48, 50); calculate a rate-of-life consumption of the first component and of the second component; predict when failure of the first component (26, 30, 32, 34) and failure of the second component (42, 46, 48, 50) will occur based on the RUL of each (412, 414) and based on the respective rate-of-life consumption (402, 404) of each; and provide instructions for altering operation of the aircraft that affects the RUL of the first or second component (26, 30, 32, 34), (42, 46, 48, 50), characterized in that the first component (26, 30, 32, 34) is in the first turbine engine and the second redundant component (42, 46, 48, 50) is in the second turbine engine, and the EHMS is configured to provide the instructions such that the first or second gas turbine (302, 304) having the component with the lowest RUL is operated less stringently to increase the RUL of the component with the lowest RUL.