Aircraft engine controls
provide a means for the pilot to control and monitor the operation of the aircraft's powerplant. This article describes controls used with a basic internal-combustion engine
driving a propeller
. Some optional or more advanced configurations are described at the end of the article. Jet turbine engines
use different operating principles and have their own sets of controls and sensors.
Basic Controls and Indicators
- Master Switch - Most often actually two separate switches, the Battery Master and the Alternator Master. The Battery Master activates a relay (sometimes called the battery contactor) which connects the output of the battery to the aircraft's main electrical bus. The alternator master activates the alternator by applying power to the alternator field circuit. These two switches provide electrical power to all the systems in the aircraft.
- Throttle - Sets the desired engine power level. The throttle controls the volume of fuel/air mixture delivered to the cylinders.
- Pitch Control - Adjusts the Constant Speed Unit, which in turn adjusts the propeller pitch & regulates the engine load as necessary to maintain the set R.P.M.
- Mixture Control - Sets the amount of fuel added to the intake airflow. At higher altitudes the air pressure (and therefore the oxygen level) declines so the fuel volume must also be reduced to give the correct air/fuel mixture. This process is known as "leaning".
- Ignition Switch - Activates the magnetos by opening the grounding or 'p-lead' circuit; with the p-lead ungrounded the magneto is free to send its high-voltage output to the spark plugs. In most aircraft the ignition switch also applies power to the starter motor during engine start. In piston aircraft engines, the battery does not generate the spark for combustion. This is accomplished using devices called magnetos. Magnetos are connected to the engine by gearing. When the crankshaft turns, it turns the magnetos which mechanically generate voltage for spark. In the event of an electrical failure, the engine will continue to run. The Ignition Switch has the following positions:
Tachometer - A gauge to indicate engine speed in revolutions per minute (RPM) or percentage of maximum
Manifold Pressure Gauge – Used to measure the pressure in the intake manifold.
Oil Temperature Gauge - Indicates the engine oil temperature
Oil Pressure Gauge - Indicates the supply pressure of the engine lubricant.
Exhaust Gas Temperature Gauge – Indicates the temperature of the exhaust gas just after combustion. Used to set the fuel/air mixture (leaning) correctly.
Cylinder Head Temperature Gauge - Indicates the temperature of at least one of the cylinder heads. Used to set the fuel/air mixture.
Carburetor Heat Control - Controls the application of heat to the carburetor venturi area to remove or prevent the formation of ice in the throat of the carburetor as well as bypassing the air filter in case of impact icing.
Alternate Air - Bypasses the air filter on a fuel-injected engine
- Off - Both magnetos are connected to electrical ground.
- Right - The right magneto is connected to its spark plugs. The left magneto is grounded.
- Left - The left magneto is connected to its spark plugs. The right magneto is grounded.
- Both - Both magnetos are connected to their spark plugs. This is the normal operating configuration.
- Start - The pinion gear on the starter motor is engaged with the flywheel and the starter motor runs to turn the engine over.
- Fuel Primer Pump - A manual pump to add a small amount of fuel at the cylinder intakes to assist in starting a cold engine. Fuel injected engines do not have this control. For fuel injected engines, a fuel boost pump is used to prime the engine prior to start.
- Fuel Quantity Gauge - Indicates the amount of fuel remaining in the identified tank. One per fuel tank.
- Fuel Select Valve - Connects the fuel flow from the selected tank to the engine.
If the aircraft is equipped with a fuel pump:
- Fuel Pressure Gauge - Indicates the supply pressure of fuel to the carburetor (or in the case of a fuel injected engine, to the fuel controller.)
- Fuel Boost Pump Switch - Controls the operation of the auxiliary electric fuel pump to provide fuel to the engine before it starts or in case of failure of the engine powered fuel pump.
If the aircraft is equipped with adjustable-pitch or constant-speed propeller:
- Propeller Control - Sets the desired R.P.M. of the propeller governor, which turn regulates the engine load as necessary to maintain the set R.P.M. Once the R.P.M. is set by the pilot, the governor adjusts engine load by increasing or decreasing propeller pitch by using engine oil pressure to move a piston in the propeller hub.
- Manifold Pressure Gauge - Indicates the absolute pressure in the engine intake manifold between the throttle and the cylinders.
If the aircraft is equipped with adjustable Cowl Flaps:
- Cowl Flap Position Control - Cowl Flaps are opened during high power/low airspeed operations like takeoff to maximize the volume of cooling airflow over the engine's cooling fins.
- Cylinder Head Temperature Gauge - Indicates the temperature of all cylinder heads or on a single CHT system, the hottest head. A Cylinder Head Temperature Gauge has a much shorter response time than the oil temperature gauge, so it can alert the pilot to a developing cooling issue more quickly. Engine overheating may be caused by:
- Running too long at a high power setting.
- Poor leaning technique
- Restricting the volume of cooling airflow too much.
- Insufficient delivery of lubricating oil to the engine's moving parts.