C208 Caravan Multiple Choice Questions

The correct answer is 125 KIAS because the question asks for the maneuvering speed of a C208 at 6250 LBS. The maneuvering speed is the maximum speed at which full control deflection can be applied without exceeding the aircraft's structural limits. This speed is typically lower at higher weights, so at 6250 LBS, the maneuvering speed is 125 KIAS.

Lead acid batteries are commonly used in caravans as they are reliable and can provide a high current when needed. The voltage rating of a battery indicates the electrical potential difference it can provide, while the ampere-hour rating represents the amount of charge it can store. In this case, the correct answer is 24 Volt 45 Ampere-hour, indicating that the battery can provide a voltage of 24 volts and store a charge of 45 ampere-hours.

Rudder trimming is achieved through the nosewheel steering bungee, which is not a tab. The nosewheel steering bungee is responsible for adjusting the position of the rudder, allowing for fine-tuning and balancing the aircraft during flight. This mechanism ensures that the aircraft maintains its desired direction and stability.

According to the flight safety manual, if a circuit breaker (CB) pops, it should be reset after 3 minutes. This time interval allows for the CB to cool down and reset itself before attempting to restore power. Resetting the CB too soon could potentially cause damage or a repeated pop. Therefore, waiting for 3 minutes is the recommended procedure for resetting a CB after it pops.

The maximum bank angle on a C208 is 60 degrees. This means that the aircraft can safely and effectively perform turns with a maximum bank angle of 60 degrees without compromising stability or safety. A bank angle greater than 60 degrees may exceed the aircraft's design limits and could lead to loss of control or structural damage.

Refer to page 7-38 POH

external power is supplied to the Starter.
Battery power is supplied to the main Bus.(No generator power is available in this position)

494 KGS

A C208 aircraft has two elevator trim tabs. Trim tabs are small surfaces attached to the trailing edge of the elevator, which help to control the aircraft's pitch or nose-up/nose-down attitude. The presence of two trim tabs on the C208 indicates that it has a dual-channel elevator trim system, allowing for redundancy and improved control during flight.

Time limit is 5 minutes above 765 degrees celsius

page 1-12 POH

POH page 7-75

The "DOOR/PAX" switch on the Caravan's control wheel is a crucial safety feature. When in the "DOOR" position, it activates a warning light if the passenger door isn't properly closed and latched. This prevents accidental door opening during flight, which could lead to a dangerous loss of cabin pressure and potential injuries to passengers.

The GCU provides an automatic cut-off for 46% of Ng.

During the start cycle, the starter switch must be placed in the "OFF" position when the engine reaches 52% Ng. This means that the starter switch should be turned off when the engine's rotational speed reaches 52% of its maximum gas generator speed. This is a critical step in the start cycle to ensure proper engine operation and prevent any damage or malfunction.

Each light assembly contains 2 lamps.

The correct answer is 2/4 full. This means that when the "fuel reservoir Low" light comes on, the reservoir is half full.

It is possible to start, taxi, and take off with both fuel selectors off, only running off the fuel reservoir tanks. The fuel reservoir tanks are designed to provide fuel directly to the engine in case of a failure in the main fuel system. This allows the aircraft to continue operating even if the fuel selectors are turned off. However, it is important to note that this should only be done in emergency situations or if it is necessary to troubleshoot an issue with the main fuel system.

The maximum window open speed on the C208 is 175 KIAS. This means that the windows should not be opened if the aircraft is flying faster than 175 knots indicated airspeed. Opening the windows at higher speeds could result in excessive wind forces on the windows, potentially causing damage or compromising the structural integrity of the aircraft. Therefore, it is important to adhere to this limitation to ensure the safety of the aircraft and its occupants.

The starter/generator is cooled by an integral fan and a blast tube above the oil cooler, in the air inlet on the right forward cowling. These two methods work together to ensure that the starter/generator does not overheat during operation. The integral fan helps to circulate air and dissipate heat, while the blast tube directs cool air from the air inlet on the cowling towards the starter/generator. This combination of cooling mechanisms ensures efficient and effective cooling for the starter/generator.

If the "fuel selector off" annunciator comes on, it means that either one or both fuel selectors are placed in the off position. Additionally, it could also mean that the "fuel selector warning" circuit breaker is not set or the "start control" circuit breaker is not set. Therefore, both options A and B are correct explanations for the given situation.

If the C208 oil is overfilled to "MAX COLD" or "MAX COLD", the consequences might include increased oil consumption and increased oil mist passing through the engine oil breather.

The PT6A engine has only one stage of centrifugal compressor. This means that there is only one set of rotating blades that compress the incoming air before it enters the combustion chamber. Having only one stage is common in smaller turbine engines like the PT6A, where the compression ratio required can be achieved with just one stage.

When the standby power goes ON during flight and the generator is tripped and reset, the initial action to maintain comms/avionics would be to switch on both the "avionics standby power" and the "avionics bus tie." This is because the standby power alone may not be enough to power the avionics system, and the bus tie is necessary to connect the standby power to the avionics system. Therefore, both switches need to be turned on to ensure the avionics system continues to receive power and maintain communication.

The fuel gets to the reservoir manifold by both the ejector pump and the auxiliary boost pump. This means that both pumps work together to deliver fuel to the engine driven boost pump. The ejector pump uses the flow of air to create suction and draw fuel from the main tank, while the auxiliary boost pump provides additional pressure to ensure a steady flow of fuel to the engine driven boost pump.

When the "FUEL SELECT OFF WARN" CB and the "START CONT" CB are pulled, it means that the fuel selector is turned off and the start control is disabled. In this situation, the "FUEL SELECTOR OFF" annunciator will come on to indicate that the fuel selector is indeed in the off position. Therefore, the correct answer is "Yes."

The maximum glide speed of a C208 at 7500 LBS equipped with cargo pods is 87 KIAS. This means that when the aircraft is in a glide without engine power, it can maintain a maximum speed of 87 knots indicated airspeed. This speed is specific to the given weight and configuration of the aircraft, and exceeding it could potentially compromise the safety and performance of the glide.

The minimum Ng for Idle is 52%. This means that the engine's low-speed shaft speed must be at least 52% of its maximum rated speed in order for the engine to operate in idle mode.

The maximum ITT at idle power lever is 685 degrees Celsius.

The PT6A engine has 3 axial compressor stages. Axial compressors are a type of compressor that use a series of rotating airfoils to compress the incoming air. The number of stages in an axial compressor determines the level of compression achieved. In the case of the PT6A engine, 3 stages are used to achieve the desired compression ratio for efficient operation.

If the engine oil pressure drops suddenly and the props are not feathered, it means that the engine has failed. In this situation, the props will not feather themselves. Feathering the props involves adjusting the angle of the propeller blades to reduce drag and prevent windmilling, which can cause further damage to the engine. Therefore, if the props are not feathered manually, they will not automatically feather themselves.

According to the flight safety manual, the strobe light should be used strictly at night. This means that it is not recommended to use the strobe light during the day. Strobe lights are typically used on aircraft to increase visibility and alert other pilots or ground personnel of their presence. However, during daylight hours, other lighting systems such as navigation lights and landing lights are usually sufficient for visibility purposes. Therefore, the strobe light is specifically designated for nighttime operations to enhance safety and prevent confusion or distractions during daylight hours.

The purpose of the Fuel Control Unit (FCU) is to meter the fuel and direct it to the flow divider. It does not pump fuel directly. Therefore, the correct answer is A and B only.

Vy refers to the best rate of climb speed, which is the airspeed that allows an aircraft to climb most efficiently in terms of gaining altitude in the shortest amount of time. In the case of a C208 flying at sea level up to 10,000 feet, the best rate of climb speed is 104 KIas. This airspeed provides the optimal balance between climb performance and engine efficiency, allowing the aircraft to ascend quickly while minimizing excess drag.

No Red annunciators can be dimmed.

In this case the Rudder trim will only steer the nose wheel

Tq x RPM
__________

5252

The correct answer is the Ejector boost pump. The ejector boost pump is primarily responsible for pumping fuel from the reservoir tank. It uses a combination of suction and pressure to draw fuel from the tank and deliver it to the engine. This pump is commonly used in aircraft fuel systems to ensure a steady flow of fuel to the engine, especially during high-demand situations. The auxiliary boost pump and engine driven fuel pump may also play a role in fuel delivery, but they are not primarily responsible for pumping fuel from the reservoir tank. The FCU (Fuel Control Unit) is responsible for regulating the flow of fuel to the engine, but it does not directly pump fuel from the reservoir tank.

When parked on a slope, fuel will transfer from one tank to another if the higher wing tank's selector is in the "ON" position. This means that fuel will flow from the higher wing tank to the lower wing tank, taking advantage of the slope to facilitate the transfer. If the lower wing tank's selector is in the "ON" position, fuel will not transfer because there is no higher tank to transfer from. Similarly, if either the low or high wing tank's selector is in the "ON" position, fuel will not transfer because the higher wing tank's selector needs to be specifically in the "ON" position for the transfer to occur.

When the rudder pedals are fully depressed without brakes during taxiing on the ground, the steering bungee will turn the nose wheel 15 degrees either side of center.

The C208 has two fuel filters.

The maximum climb power allowed for the C208 is 765 degrees Celsius and 101.6%. This means that the aircraft can operate at a maximum temperature of 765 degrees Celsius and at 101.6% of its normal power output during climb. This ensures that the aircraft has enough power to climb efficiently and safely.

The maximum glide speed of a C208 at 8750 LBS equipped with Cargo pods is 95 KIAS. This means that when the aircraft is in a gliding state, it can maintain a maximum speed of 95 knots indicated airspeed.

The correct answer is 148 KIAS. The manuevring speed of an aircraft is the maximum speed at which it can be safely maneuvered without causing structural damage. In this case, the manuevring speed of the C208 at 8750 LBS is 148 KIAS, indicating that this is the maximum speed at which the aircraft can be safely maneuvered without exceeding its structural limitations.

If the inertial separator is in the normal position and a stone passes through the system, it will not go into the compressor section. The purpose of the inertial separator is to separate and remove larger particles, such as stones, from the airflow before it reaches the compressor section. Therefore, the stone will be captured by the inertial separator and prevented from entering the compressor section.

not-available-via-ai

The "oil pressure low" annunciator will come on when the oil pressure falls below 40 PSI. The range of 40 +/- 2 PSI means that the annunciator will come on if the oil pressure is either 38 PSI or lower. This range allows for a slight variation in the oil pressure while still ensuring that it remains above the minimum threshold for the annunciator to activate.

Maximum continuous power is used during extreme icing conditions and windshear downdraughts. In extreme icing conditions, the aircraft needs maximum power to overcome the additional drag caused by ice accumulation on the wings and other surfaces. Similarly, in windshear downdraughts, maximum power is required to maintain altitude and overcome the sudden decrease in lift caused by the downdraft. Therefore, in both these situations, the aircraft needs to operate at maximum continuous power to ensure safe and stable flight.

The maximum Tq allowable at 1900 RPM is 1865. This means that at 1900 RPM, the maximum torque that can be sustained without causing damage or exceeding the safe operating limits is 1865.

The correct answer is 137 KIAS. The manuevring speed of an aircraft is the maximum speed at which abrupt control movements can be made without exceeding the aircraft's structural limits. This speed is specific to each aircraft and is usually provided by the manufacturer. In this case, the manuevring speed of a C208 at 7500 LBS is 137 KIAS. This means that the pilot can safely make abrupt control movements up to this speed without risking damage to the aircraft's structure.

It connects the 2 avionics busses together, thus If one of the avionics busses fails (goes offline due to CB or power switch fails), the avionics bus tie switch will restore power to that Bus.

The maximum cruise power setting for the C208 is 740 degrees Celsius.

see page 5-18. The max demonstrated x-wind velocity is based on certification tests done on the C208

Not through primary filter, where filter is blocked) but downstream before Nozzles.

No, there is no battery overheat warning system when a lead-acid battery is fitted. Lead-acid batteries do not typically come with built-in temperature monitoring or warning systems. Therefore, it is important for users to be cautious and monitor the battery's temperature manually to prevent overheating, which can lead to damage or even explosion of the battery.

Selecting full reverse thrust during landing can significantly decrease the ground roll distance. By applying reverse thrust, the engines are directed to push the aircraft forward, opposite to its motion, which helps in decelerating the aircraft quickly. The reverse thrust can reduce the ground roll distance by approximately 10%.

Check valve equipped vent lines are used for fuel venting. A check valve is a device that allows the flow of fluid in only one direction, preventing backflow. In the context of fuel venting, check valve equipped vent lines ensure that fuel vapors can be released from the fuel tank but prevent any fuel from escaping through the vent lines. This helps to maintain the proper pressure and ventilation in the fuel system, preventing fuel leakage and potential hazards. Fuel caps and regular vent lines may not have the necessary check valve mechanism to achieve this function effectively.

The maximum amount of degrees you can turn before damaging the nose gear is 56 degrees. Turning beyond this angle can cause stress and potential damage to the nose gear, jeopardizing the safety and functionality of the aircraft.

The maximum OAT (Outside Air Temperature) limit for the C208 from 5000ft and above is ISA +37 degrees Celsius. This means that the aircraft can operate in temperatures up to 37 degrees Celsius above the International Standard Atmosphere (ISA) temperature at that altitude.

According to the flight safety manual, it is allowed to move the condition lever into an intermediate position between Low idle and High Idle.

The fuel quantity indicator is indicating empty, which means that there is no usable fuel left in the tanks. However, there is still 2.5 gallons of unusable fuel remaining.

The correct answer is 65%. The question is asking about the Ng (gas generator speed) when the fuel condition lever is set to High Idle. High Idle is the highest setting for the fuel condition lever, which means it provides the maximum fuel flow to the engine. This results in a higher Ng, which in this case is 65%.

The correct answer is 50 KIAS. KIAS stands for Knots Indicated Airspeed, which is the speed indicated on the aircraft's airspeed indicator. In this case, the Vso (Stall Speed in Landing Configuration) on a C208 is 50 KIAS. This means that the aircraft should not be flown at speeds below 50 KIAS during landing, as it may result in a stall.

The first 30 degrees of flaps must be retracted immediately after initiating the go-around, specifically after applying go-around power. This is because retracting the flaps reduces drag and allows the aircraft to climb more efficiently. It is important to retract the flaps promptly to ensure a smooth transition from the landing configuration to the go-around phase.

Lead acid batteries have the advantage of being able to absorb voltage spikes. This means that they can handle sudden increases in voltage without being damaged. This is important in flight safety as voltage spikes can occur during electrical system malfunctions or lightning strikes. By absorbing these spikes, lead acid batteries help to protect the aircraft's electrical systems and prevent damage or failure.

The standby electrical system (Alternator) will supply power to the system below the voltage of 27.5 volts.

Fuel quantity is measured by fuel quantity transmitters. The correct answer is 8, indicating that there are a total of 8 fuel quantity transmitters used to measure the fuel quantity.

If no ITT rise is observed within 10 seconds from the time the condition lever is moved into the Low idle position from cut off, it indicates that the engine is not starting properly. In such a case, moving the condition lever to the cut off position and aborting the engine start is the appropriate action to take.

All annunciator panel lamps can be replaced by one another, except for the "Ignition ON" annunciator. This means that the bulbs used in the other annunciator lamps (such as "Starter energized" and "oil pressure low") can be interchanged, but the "Ignition ON" annunciator has a different type of bulb that cannot be replaced by the others. This information is stated on Page 4-2 of the Flight Safety Manual.

When the "voltage Low" annunciator comes on, it indicates that the electrical system bus voltage has dropped below 24.5 volts. This means that the voltage level has fallen below the specified threshold, indicating a potential problem with the electrical system.

see Schematic Page 5-2 Flight safety

Vx refers to the best angle of climb speed, which is the airspeed that will result in the greatest gain in altitude per unit of horizontal distance traveled. In the case of a C208 aircraft, the Vx speed is 72 KIAS (Knots Indicated Airspeed). This means that when climbing from sea level to 20,000 feet, the optimal airspeed for achieving the steepest climb angle is 72 knots. Flying at this speed will allow the aircraft to maximize its rate of ascent and reach the desired altitude in the most efficient manner.

When parked in a right quartering crosswind from behind, selecting Beta mode for more than 30 seconds can cause damage. This suggests that Beta mode should only be used for a limited amount of time in this specific wind condition to avoid any potential harm.

page 2-13 POH

When the "vacuum Low" annunciator comes on, it indicates that the suction pressure has dropped below 3.0 In HG. This pressure is considered to be the threshold at which the vacuum is considered low.

A "Hot start" is defined as a start exceeding 1090 Degrees celsius ITT.

The given answer "No" suggests that there are no lights outside the C208 that are controlled by switches outside the cockpit, specifically on the left-hand side of the control column. This implies that all the lights outside the aircraft are controlled from within the cockpit, and there are no additional switches located elsewhere for this purpose.

Yes, as a pilot, you can reset the fuel filter bypass flag after it has popped out. This can be done by following the appropriate procedures outlined in the aircraft's operating manual or by consulting with the maintenance personnel. Resetting the fuel filter bypass flag ensures that the filter is functioning properly and allows for continued safe operation of the aircraft.

A Primary and a secondary exhaust pipe. See page 7-44 POH

Page 2-15 POH under section 2 Limitations

The "ON" position of the ignition switch is used for various scenarios. It is used for air start without starter assist, which means starting the engine using compressed air without the assistance of a starter motor. It is also used during operations on water-covered runways, where the ignition switch needs to be in the "ON" position to ensure proper engine operation. Additionally, during flight in heavy precipitation, the ignition switch should be in the "ON" position to prevent engine flameout. Inadvertent icing encounters with the inertial separator for 5 minutes also require the ignition switch to be in the "ON" position. Lastly, when there is a near fuel exhaustion and the "RESERVOIR FUEL LOW" warning is displayed, the ignition switch needs to be in the "ON" position.

The maximum Transient Tq on the C208 is 2400 and it is limited to 20 seconds. This means that the engine can produce a maximum transient torque of 2400 units, but this level of torque can only be sustained for a maximum of 20 seconds. After 20 seconds, the engine may experience damage or other issues if the high torque level is maintained.

Time limited to 2 secs

The maximum luggage (in pounds) that can be stored aft of the rearmost row of seats is 325.

The correct answer is 9000 ft. When using any Avgas in any way on a C208, the limitation on operating altitude is 9000 ft. This means that the aircraft should not fly above 9000 ft when using Avgas.

The maximum continuous power (ITT) for the C208 is 805 Degrees Celsius, Tq 1865ft/Lbs, 101.6%.

The maximum Tq allowable at 1800 RPM is 1970.

can cause vertigo

The question is asking whether the compressor air inlet filters air or not. The correct answer is "No" because the air inlet filter of a compressor is designed to remove contaminants and particles from the incoming air before it enters the compressor. Therefore, it does not filter air, but rather filters out impurities from the air.

An APU start is not recommended below 0 degrees Fahrenheit.

POH page 7-75

The secondary exhaust system helps to cool oil during ground operations. This system is designed to redirect the hot exhaust gases away from the engine, preventing them from coming into contact with the oil and causing it to overheat. By diverting the exhaust gases, the secondary exhaust system helps to maintain the optimal temperature of the oil, ensuring the engine operates efficiently and reducing the risk of damage or failure.

The correct answer is 2090 RPM. This is the maximum ambient propeller RPM for the C208. It indicates the highest allowed revolutions per minute for the propeller under normal atmospheric conditions. It is important to adhere to this limit to ensure safe and efficient operation of the aircraft.

The correct answer is +29 degrees Celsius. When using any Avgas in any way on a C208, the limitation on OAT for takeoff is +29 degrees Celsius. This means that the maximum outside air temperature allowed for takeoff is +29 degrees Celsius.

The correct answer is 102.6%. This indicates that the maximum ambient Ng (gas generator speed) for the C208 is 102.6%. This value represents the upper limit for the gas generator speed in relation to the ambient conditions, ensuring that the engine operates within safe parameters.

POH page 7-50. Mounted on Right hand side underneath engine

NB minimum Ng= 48% Ng at SL and increses as you increase in altitude

Page 7-45/48 Prop Governor(On accessory gearbox), prop overspeed Governor(on accessory gearbox), Power Turbine Governor