Gas turbine engine system wear reduction

A method of engine system control, the method comprising:

• operating a first gas turbine engine with a sub-idle fuel burn schedule based on detecting landing of an aircraft, the sub-idle fuel burn schedule comprising a reduction of an idle fuel burn schedule;
• operating a second gas turbine engine with the idle fuel burn schedule based on detecting landing of the aircraft;
• tracking a sub-idle time of the first and second gas turbine engines;
• and
• alternating the designation of the first gas turbine engine and the second gas turbine engine to substantially balance the sub-idle time of the first and second gas turbine engines for the aircraft.

An engine system for an aircraft, the engine system comprising:

• a first gas turbine engine;
• a second gas turbine engine;
• a control system configured to:
• operate the first gas turbine with a sub-idle fuel burn schedule based on detecting landing of the aircraft, the sub-idle fuel burn schedule comprising a reduction of an idle fuel burn schedule;
• and
• operate the second gas turbine engine with the idle fuel burn schedule based on detecting landing of the aircraft, wherein at least one engine bleed schedule is adjusted corresponding to the sub-idle fuel burn schedule to control a compressor work distribution during sub-idle operation, and adjustment to the at least one engine bleed schedule increases an engine bleed flow to at least one environment control system of the aircraft during sub-idle operation.