Abstract: A method is provided for operating an aircraft engine in a fire-induced emergency state. The engine is housed in a nacelle defining a nacelle bypass duct having a first outlet fluidly connected to an inlet of the engine and a second outlet fluidly connected to an environment external to the nacelle. An indication of a fire of the aircraft engine is received. In response to receiving the indication, an emergency shutdown sequence of the engine is initiated. In response to the initiating the emergency shutdown sequence, a volume of air entering the inlet of the aircraft engine is increased by restricting air flow through the second outlet of the nacelle bypass duct. The volume of air entering the inlet is used to drive a rotor of the engine. The rotor is used to drive an oil pump to circulate oil through a main oil conduit of the engine.

Abstract: A method is provided for operating an aircraft engine in a fire-induced emergency shutdown state. An indication of a fire in a fire zone of the aircraft engine is received. In response to the receiving the indication of the fire in the fire zone of the aircraft engine, an emergency shutdown sequence of the aircraft engine is initiated. In response to the initiating the emergency shutdown sequence of the aircraft engine, an auxiliary oil pump positioned outside of the fire zone of the aircraft engine and distinct from a main oil pump of the aircraft engine is activated. Once activated, the auxiliary oil pump circulates oil through a main oil conduit of the aircraft engine.

Abstract: A system, method and apparatus for monitoring the performance of a gas turbine engine. A counter value Indicative of the comparison between the engine condition and the threshold condition is adjusted. The aircraft operator is warned of an impending maintenance condition based on the counter value and determines an appropriate course of action.