1. Engine Performance

9072. Where is the critical altitude of a supercharged reciprocating engine?. The highest altitude at which a desired manifold pressure can be obtained. Highest altitude where the mixture can be leaned to best power ratio. The altitude at which maximum allowable BMEP can be obtained.

9073. What is controlled by the waste gate of a turbocharged-reciprocating engine?. Supercharger gear ratio. Exhaust gas discharge. Throttle opening.

9068. Under normal operating conditions, which combi- nation of MAP and RPM produce the most severe wear, fatigue, and damage to high performance reciprocating engines?. High RPM and low MAP. Low RPM and high MAP. High RPM and high MAP.

9068-1. How are turbine engines classified?. The type of compressor or combination of compressors they use. The method in which the air/fuel mixture is ignited. The flow of air through the engine and how power is produced.

9058. Which place in the turbojet engine is subjected to the highest temperature?. Compressor discharge. Fuel spray nozzles. Turbine inlet.

8394. A hot start in a turbine engine is caused by. failed ignition. the engine’s failure to accelerate. too much fuel in the combustion chamber.

8394-1. What could cause a turbine engine hot start?. Lack of airflow due to insufficient turbine RPM. Inlet and compressor airflow imbalance. Insufficient fuel in the combustion chamber.

9060. The most important restriction to the operation of turbojet or turboprop engines is. limiting compressor speed. limiting exhaust gas temperature. limiting torque.

9064. What characterizes a transient compressor stall?. Loud, steady roar accompanied by heavy shuddering. Sudden loss of thrust accompanied by a loud whine. Intermittent “bang,” as backfires and flow reversals take place.

9768. What prevents turbine engines from developing compressor stalls?. Deice valves-fuel heat. TKS system. Compressor bleed valves.

9065. What indicates that a compressor stall has developed and become steady?. Strong vibrations and loud roar. Occasional loud “bang” and flow reversal. Complete loss of power with severe reduction in airspeed.

9066. Which type of compressor stall has the greatest potential for severe engine damage?. Intermittent “backfire” stall. Transient “backfire” stall. Steady, continuous flow reversal stall.

8974. Which part(s) in the turbojet engine is subjected to the high temperatures and severe centrifugal forces?. Turbine wheel(s). Turbine vanes. Compressor rotor(s) or impeller(s).

9067. What recovery would be appropriate in the event of compressor stall?. Reduce the throttle and then rapidly advance the throttle to decrease the angle of attack on the compressor blades, creating more airflow. Reduce the throttle and then slowly advance the throttle again and decrease the aircraft’s angle of attack. Advance the throttle slowly to increase airflow and decrease the angle of attack on one or more compressor blades.

9067-1. While on an ILS approach, what is the proper way to recover from an impending stall?. Engaging the autopilot. Changing flap settings. Reducing the angle of attack.

9070. Equivalent shaft horsepower (ESHP) of a turbo- prop engine is a measure of. turbine inlet temperature. shaft horsepower and jet thrust. propeller thrust only.

9071. Minimum specific fuel consumption of the turbo- prop engine is normally available in which altitude range?. 10,000 feet to 25,000 feet. 25,000 feet to the tropopause. The tropopause to 45,000 feet.

9059. What effect would a change in ambient temperature or air density have on gas-turbine-engine performance?. As air density decreases, thrust increases. As temperature increases, thrust increases. As temperature increases, thrust decreases.

9061. As outside air pressure decreases, thrust output will. increase due to greater efficiency of jet aircraft in thin air. remain the same since compression of inlet air will compensate for any decrease in air pressure. decrease due to higher density altitude.

9061-1. Low pressure air decreases aircraft performance because. the air is denser than higher pressure air. the air is less dense than high pressure air. air expands in the engine during the combustion.

9062. What effect will an increase in altitude have upon the available equivalent shaft horsepower (ESHP) of a turboprop engine?. Lower air density and engine mass flow will cause a decrease in power. Higher propeller efficiency will cause an increase in usable power (ESHP) and thrust. Power will remain the same but propeller efficiency will decrease.

9063. What effect, if any, does high ambient temperature have upon the thrust output of a turbine engine?. Thrust will be reduced due to the decrease in air density. Thrust will remain the same, but turbine temperature will be higher. Thrust will be higher because more heat energy is extracted from the hotter air.

9069. What effect does high relative humidity have upon the maximum power output of modern aircraft engines?. Neither turbojet nor reciprocating engines are affected. Reciprocating engines will experience a significant loss of BHP. Turbojet engines will experience a significant loss of thrust.