FAA TURBINE ENGINE AIR SYSTEMS

What engine instrument indications may shift when a turbofan engine anti-icing (bleed air) system is turned on?. Tachometer, fuel flow indicator, and EGT. Fuel flow indicator, EGT, and EPR. Tachometer, EGT, and EPR.

The purpose of an engine/inlet anti-ice system is primarily to. remove ice from engine and/or inlet areas. prevent ice formation in engine and/or inlet areas. remove ice from engine and/or inlet areas and prevent ice formation in engine and/or inlet areas.

When an engine with a subsonic divergent type inlet duct is running in place at high speed on the ground, the air pressure within the inlet is. negative. positive. ambient.

Vortex dissipator systems are generally activated by. a landing gear switch. a fuel pressure switch anytime an engine is operating. an engine inlet airflow sensor.

The component(s) in a turbine engine that operate(s) at the highest temperatures is/are the. first stage turbine nozzle guide vanes. turbine disks. exhaust cone.

The vortex dissipators installed on some turbine-powered aircraft to prevent engine FOD utilize. variable inlet guide vanes (IGV) and/ or variable first stage fan blades. variable geometry inlet ducts. a stream of engine bleed air blown toward the ground ahead of the engine.

Which statement is true regarding the air passing through the combustion section of a jet engine?. Most is used for engine cooling. Most is used to support combustion. A small percentage is frequently bled off at this point to be used for air-conditioning and/or other pneumatic powered systems.