GAS TURBINE ENGINE HAVING FIRST AND SECOND LUBRICATION SYSTEMS AND ASSOCIATED METHOD

A gas turbine engine for an aircraft that comprises a shaft fixed to a compressor of the gas turbine engine; at least one of a turboprop and a turbofan; a power gearbox having a power output shaft fixed to the at least one of the turboprop and the turbofan, wherein the power gearbox receives an input rotation from the shaft; an auxiliary gearbox having an auxiliary output shaft powering at least one auxiliary component of the gas turbine engine; a first lubrication system; and a second lubrication system that is separated from the first lubrication system. The first lubrication system circulates a first lubricant through the power gearbox and the second lubrication system circulates a second lubricant through the auxiliary gearbox. A method is also disclosed.