Ultimate Aircraft Systems Quiz

A turn coordinator is an instrument that provides pilots with information about the movement of the aircraft around the yaw and roll axes. It helps them determine whether the aircraft is turning or rolling, and provides a visual indication of the rate of turn. This information is crucial for maintaining control and stability during flight.

The vacuum system is the power source that spins the gyro in the Attitude Indicator. The Attitude Indicator is a flight instrument that displays the aircraft's pitch and roll attitude relative to the horizon. It relies on a gyroscope to function properly, and the gyroscope is powered by the vacuum system. The vacuum system creates suction that drives the gyroscope, allowing it to accurately indicate the aircraft's attitude.

The pitot system provides impact pressure for the airspeed indicator. The airspeed indicator measures the speed of the aircraft by comparing the impact pressure created by the forward motion of the aircraft to the static pressure of the surrounding air. This is done by using a pitot tube, which is a small tube that faces forward and collects the impact pressure. This pressure is then displayed on the airspeed indicator, allowing the pilot to know the current speed of the aircraft.

The red radial line is the correct answer because in aviation, the red radial line on the airspeed indicator represents the never exceed speed, also known as Vne. This is the maximum speed that an aircraft should never exceed, as going beyond this speed can result in structural damage or loss of control. The red color is used to highlight the importance and danger associated with exceeding this limit.

Filling the fuel tanks after the last flight of the day is considered a good operating procedure because it prevents moisture condensation by eliminating airspace in the tanks. When there is empty space in the tanks, moisture can accumulate and condense, which can lead to water contamination in the fuel. This can cause engine problems and affect performance. By filling the tanks completely, there is no room for moisture to accumulate, reducing the risk of condensation and ensuring the fuel remains clean and free from water contamination.

The auxiliary electric driven pump is used in the event the engine-driven fuel pump fails. This is necessary to ensure a continuous supply of fuel to the aircraft's engine, preventing loss of power and maintaining proper functioning of the aircraft.

The attitude indicator, heading indicator, and turn coordinator all utilize a gyro. The attitude indicator uses a gyro to determine the aircraft's pitch and roll, the heading indicator uses a gyro to determine the aircraft's heading, and the turn coordinator uses a gyro to indicate the rate of turn. These instruments rely on the gyroscopic properties of a spinning wheel to provide accurate and reliable information to the pilot.

After starting an aircraft engine, the first action should be to adjust for proper RPM and check for desired indications on the engine gauges. This is important to ensure that the engine is running at the correct speed and that all the engine parameters are within the desired range. It allows the pilot to monitor the engine's performance and detect any abnormalities or malfunctions early on. Realigning the magnetic compass and using the electric-driven pump are not the first actions that need to be taken after starting the engine.

To properly purge water from the fuel system of an aircraft, it is necessary to drain fuel from the fuel strainer drain and the fuel tank sumps. This is because water can accumulate in these areas and can contaminate the fuel, which can lead to engine problems or failure. By draining the fuel from the fuel strainer drain and the fuel tank sumps, any water present in the system can be removed, ensuring that only clean fuel is being used in the aircraft's engine.

VFE represents the maximum flap extended speed. This is the highest speed at which an aircraft can safely extend its flaps. Flaps are used to increase the lift and drag of an aircraft during takeoff and landing. Operating the flaps above the VFE speed can cause damage to the aircraft's structure. Therefore, it is important for pilots to adhere to the VFE speed limit to ensure the safe operation of the aircraft.

The red line on the airspeed indicator represents the "never exceed speed." This is the maximum speed at which the aircraft should never exceed, as going beyond this speed can cause damage to the aircraft's structure or lead to loss of control. It serves as a safety limit to prevent the aircraft from being operated beyond its design capabilities.

The pilot should determine the direction of bank from an attitude indicator by observing the relationship of the mini plane to the deflected horizon bar. The attitude indicator displays the aircraft's pitch and bank attitude relative to the horizon. If the mini plane is tilted to the left of the deflected horizon bar, it indicates a left bank, and if it is tilted to the right, it indicates a right bank. This allows the pilot to accurately determine the direction of bank and maintain proper control of the aircraft.

The heading indicator uses a gyro to determine the aircraft's heading. However, the gyro tends to drift over time, so it needs to be realigned periodically with the magnetic compass to ensure accuracy. This is because the magnetic compass provides the true heading reference, and by realigning the gyro with it, the heading indicator can provide accurate indications during flight. Connecting the instrument to the vacuum system or aligning it with the turn coordinator are not necessary for receiving accurate indications from the heading indicator.

The dual ignition system on an aircraft engine improves engine performance by providing redundancy and ensuring a more efficient combustion process. Having two spark plugs per cylinder increases the likelihood of ignition, especially in high-altitude or adverse conditions. This leads to a more complete and consistent burn of the fuel-air mixture, resulting in increased power output, smoother operation, and better fuel economy. Additionally, the dual ignition system helps prevent engine misfires and reduces the risk of engine failure, enhancing overall performance and safety.

The DA20-C1 uses AVGAS 100LL or 100 as its fuel type.

The top of the green arc refers to the maximum speed at which the airplane can be safely operated in smooth air. This means that flying at or below this speed ensures that the aircraft is within its safe operating limits. Going beyond this speed could potentially put the aircraft at risk of structural damage or loss of control. Therefore, the top of the green arc is the correct answer as it indicates the maximum safe operating speed.

An abnormally high engine oil temperature indication may be caused by the oil level being too low. When the oil level is low, there is not enough lubrication to properly cool down the engine components, resulting in increased friction and heat. This can lead to higher oil temperatures and potentially damage the engine. It is important to regularly check and maintain the proper oil level to prevent overheating and ensure the engine's optimal performance.

If the engine oil temperature and cylinder head temperature gauges have exceeded their normal operating range, it suggests that the engine is running too hot. This could be due to the pilot operating the aircraft with too much power, causing the engine to generate excessive heat. Additionally, if the mixture is set too lean, it means that there is not enough fuel being supplied to the engine, which can also contribute to higher temperatures. Therefore, the correct answer is that the pilot may have been operating with too much power and with the mixture set too lean.

The yellow arc represents the caution range of the airplane. This means that when the airplane operates within this range, pilots need to exercise caution and be aware of potential risks or limitations. Operating outside of this range may result in unsafe conditions or performance issues.

Flying through rain can cause several negative effects on an aircraft's performance. Rain can increase the drag on the aircraft, making it harder to maintain speed and altitude. Additionally, water ingestion can lead to engine issues such as reduced power output and increased risk of overheating. Therefore, it is reasonable to conclude that flying through rain reduces aircraft performance.

Excessively high engine temperatures can cause loss of power, excessive oil consumption, and possible permanent internal engine damage. When the engine temperature is too high, it can lead to a decrease in power output, as the engine may not be able to function optimally. Additionally, high temperatures can cause the engine oil to break down more quickly, leading to excessive oil consumption. Moreover, prolonged exposure to high temperatures can cause permanent damage to the internal components of the engine, which may require costly repairs or even engine replacement.

The white arc is used to identify the normal flap operating range. This means that when the flaps are within the white arc, they are in the appropriate range for normal operation.

When an engine is overheating during a climb, reducing the rate of climb and increasing airspeed can help in cooling the engine. By reducing the rate of climb, the pilot decreases the workload on the engine, allowing it to cool down. Increasing airspeed helps in increasing the airflow over the engine, which aids in dissipating the heat generated. This combination of actions helps in preventing further overheating and potential damage to the engine.

The extent of the white arc represents the full flap operating range of a plane. The white arc on the airspeed indicator indicates the speeds at which the flaps can be fully extended or retracted. This range is typically between the top of the white arc and the lower limit of the white arc. Therefore, the correct answer is "The extent of the white arc."

During level flight, the proper adjustment to make on the attitude indicator is to align the mini airplane to the horizon bar. This ensures that the aircraft is flying straight and level. By aligning the mini airplane with the horizon bar, the pilot can maintain a constant pitch and roll attitude, resulting in a stable flight. This adjustment helps in keeping the aircraft on the desired flight path and prevents any unintentional climb or descent.

The automatic mixture control is part of the engine driven fuel pump. This means that the automatic mixture control system, which regulates the fuel-to-air ratio in the engine, is integrated within the engine driven fuel pump.

When the altimeter setting is changed from 30.11 to 29.96, the indication on the altimeter will decrease by 0.15. Since each unit change in the altimeter setting corresponds to a change of 1,000 feet in altitude, the approximate change in indication will be 0.15 multiplied by 1,000, which equals 150 feet lower.

The maximum flaps extended speed is indicated by the top of the white arc on the airspeed indicator. This means that flying at or below this speed is safe when the flaps are fully extended. Going beyond this speed can cause damage to the flaps or compromise the aircraft's stability.

When the altimeter is set from 29.15 to 29.85, there is a 700 foot increase in the indicated altitude. This means that the altimeter will now show a higher altitude reading compared to the previous setting.

The maximum structural cruising speed refers to the highest speed at which an aircraft can safely operate without causing damage to its structure. The "top of green arc" is typically indicated on the airspeed indicator and represents the upper limit of the safe cruising speed range. Therefore, the correct answer is "Top of green arc."

The fuel mixture in the DA20 is controlled by the engine-driven fuel pump. This pump is directly connected to the engine and is responsible for delivering the fuel from the fuel tank to the engine. It ensures that the correct amount of fuel is mixed with the air in the engine for optimal combustion and performance. The engine-drive fuel pump is a crucial component in controlling the fuel mixture and maintaining the proper functioning of the aircraft's engine.

The correct answer is the Vacuum system. The vacuum system is responsible for providing the necessary power to spin the gyro in the Heading Indicator. This system uses engine-driven vacuum pumps to create a vacuum that powers various instruments, including the Heading Indicator. The spinning gyro in the Heading Indicator allows the pilot to accurately determine the aircraft's heading.

A circuit breaker may be reset only once. After it trips or detects an overload, it needs to be manually reset by flipping the switch back to its original position. Resetting it multiple times without addressing the underlying issue could lead to further damage or electrical hazards. Therefore, it is important to identify and resolve the cause of the overload before resetting the circuit breaker.

Enriching the mixture refers to increasing the amount of fuel in the air-fuel mixture in the engine. This procedure can help cool an overheating engine because a richer mixture provides more fuel to burn, which in turn produces more power and increases the cooling effect. By enriching the mixture, the engine runs cooler as it generates more power and dissipates heat more efficiently.

The correct answer is 300 to 420 degrees Fahrenheit. This is the normal operating range for the cylinder head temperature (CHT). It is important for the CHT to stay within this range to ensure proper engine performance and prevent overheating or damage.

The lower limit of the white arc on an aircraft's airspeed indicator represents the power-off stalling speed with wing flaps and landing gear in the landing configuration. This means that when the aircraft is flying at or below this speed, it is at risk of stalling if the power is reduced and the flaps and landing gear are extended. Therefore, the lower limit of the white arc serves as a visual reference for pilots to ensure they maintain a safe speed during landing.

The maximum allowable weight in the baggage compartment of the DA20-C1 is 44 lbs. This means that the total weight of the baggage that can be placed in the compartment should not exceed 44 lbs.

The correct answer is that air enters the system through the air filter behind the left side of the instrument panel. This means that the air filter is located on the left side of the instrument panel and is responsible for filtering the air that enters the vacuum system.

Air cooled engines rely on the circulation of lubricating oil for internal cooling. The oil helps to dissipate heat from the engine components, such as the cylinders and pistons, by absorbing and carrying away the excess heat. Without proper oil circulation, the engine would overheat and potentially suffer from damage or failure. Therefore, the circulation of lubricating oil is crucial for maintaining the optimal operating temperature of air cooled engines.

The items connected to the static port on the pitot-static probe are the airspeed indicator, altimeter, vertical speed indicator, and transponder mode C. The static port provides static pressure to these instruments, which are necessary for accurate measurements of airspeed, altitude, vertical speed, and transponder information. Transponder mode C specifically requires static pressure information for altitude reporting.

The attitude indicator and heading indicator are connected to the vacuum system. The attitude indicator relies on the vacuum system to provide the necessary suction to operate, while the heading indicator also uses the vacuum system to power its gyroscopic mechanism. These instruments are crucial for maintaining the aircraft's orientation and heading, and their connection to the vacuum system ensures their proper functioning.

Using fuel that has a lower-than-specified fuel rating can lead to incomplete combustion in the engine, causing the engine to run hotter than normal. This increase in engine temperature can result in the cylinder head temperature and engine oil temperature gauges exceeding their normal operating ranges.

If the ignition switch ground wire becomes disconnected, it may continue to fire because the magneto generates its own power and does not rely on the ignition switch for grounding. The magneto produces high voltage pulses to create sparks in the spark plugs, which ignite the fuel-air mixture in the engine. Even without the ground wire connected, the magneto can still generate the necessary voltage to create sparks and continue firing.

In the given scenario, the correct answer is "Experience avionics equipment failure." This means that during the flight, there is a failure in the electrical system, specifically the battery and alternator. This failure would directly impact the avionics equipment, which includes instruments, communication systems, and navigation aids. The pilot would experience a loss or malfunction of these electronic systems, requiring them to assess the situation and take appropriate action to ensure the safety of the flight. However, it is important to note that this failure does not necessarily result in a total electrical failure of the aircraft.

The fuel pressure normal operating range in the DA20-C1 is 3.5-32.5 psi. This means that the fuel pressure should ideally be within this range for the aircraft to operate efficiently. If the pressure is too low or too high, it can lead to engine performance issues or even engine failure. Therefore, it is important to monitor and maintain the fuel pressure within this specified range during flight.

The electrical system powers the gyro in the Turn Coordinator. This means that the gyro is spun using electricity, allowing it to accurately measure and display the aircraft's rate of turn. The electrical system provides the necessary energy to keep the gyro spinning and functioning properly.

When the flaps are in the LDG (Landing) position in the DA20, they are extended 23 degrees.

The lower limit of the green arc is the color that identifies the power off stalling speed in a specified configuration.