Cessna 208 Series Cat A
This quizz is designed to test the engineer's knowledge and to promote the use of the manuals to refresh understanding of aircraft systems.
- 1.
The Cessna 208 Caravan can be described as:
- A.
A high wing cabin class turboprop all metal aircraft
- B.
A high wing cabin class turboprop all metal aircraft of monocoque construction
- C.
A high wing cabin class turboprop all metal aircraft of semi-monocoque construction
Correct Answer
C. A high wing cabin class turboprop all metal aircraft of semi-monocoque constructionExplanation
The Cessna 208 Caravan is a high wing cabin class turboprop all metal aircraft of semi-monocoque construction. This means that the aircraft has a high wing configuration, making it more stable and easier to control. It is also a cabin class aircraft, meaning it is designed to carry passengers in comfort. The aircraft is made entirely of metal, which provides strength and durability. The semi-monocoque construction refers to the structural design of the aircraft, where the skin of the aircraft provides a significant portion of the structural strength, along with internal framework and stringers. This design allows for a lighter and more efficient aircraft.Rate this question:
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- 2.
An emergency exit door is installed:
- A.
All doors can be used as emergency exits
- B.
On the left fuselage at the forward end of the passenger compartment
- C.
On the right fuselage at the rear end of the passenger compartment
Correct Answer
A. All doors can be used as emergency exitsExplanation
All doors can be used as emergency exits because in case of an emergency, passengers need to be able to quickly and safely exit the aircraft. Therefore, all doors on the aircraft are designed and equipped to function as emergency exits to ensure the passengers' safety.Rate this question:
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- 3.
The fuel system includes two integral fuel tanks and a fuel reservoir. The two integral fuel tanks:
- A.
Interconnect with direct plumbing between the two systems
- B.
Interconnect with a crossfeed system
- C.
Allows flow by gravity from each tank to the fuel reservoir
Correct Answer
C. Allows flow by gravity from each tank to the fuel reservoirExplanation
The fuel system in this scenario consists of two integral fuel tanks and a fuel reservoir. These two integral fuel tanks are designed to allow flow by gravity from each tank to the fuel reservoir. This means that fuel can naturally flow from each tank to the fuel reservoir without the need for any external force or assistance. This setup ensures a continuous and reliable fuel supply to the aircraft's engine.Rate this question:
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- 4.
The primary danger areas around the aircraft are:
- A.
The propellers and engine exhaust plume
- B.
The propellers and radar emissions from the radome
- C.
The propellers, engine exhaust plume, and radar emissions from the radome
Correct Answer
C. The propellers, engine exhaust plume, and radar emissions from the radomeExplanation
The primary danger areas around the aircraft are the propellers, engine exhaust plume, and radar emissions from the radome. The propellers can cause serious injuries or even death if a person comes into contact with them while they are in motion. The engine exhaust plume can be extremely hot and can cause burns or ignite flammable materials. Radar emissions from the radome can be harmful to human health if there is prolonged exposure. Therefore, it is important to exercise caution and maintain a safe distance from these areas to avoid any potential dangers.Rate this question:
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- 5.
The operating limitations for the aircraft can be obtained from:
- A.
The training manual
- B.
The applicable maintenance and operating manuals
- C.
The foreman in the workshop
Correct Answer
B. The applicable maintenance and operating manualsExplanation
The applicable maintenance and operating manuals provide information about the operating limitations for the aircraft. These manuals contain detailed instructions and guidelines on how to operate and maintain the aircraft safely and efficiently. They cover topics such as weight and balance limits, speed limitations, fuel capacity, and other important operational parameters. Pilots and maintenance personnel rely on these manuals to ensure compliance with regulations and to maximize the performance and safety of the aircraft.Rate this question:
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- 6.
The aircraft may be towed with:
- A.
Control locks fitted and park brake released
- B.
Control locks removed and park brake released
- C.
Control locks removed and static ground cables fitted
Correct Answer
B. Control locks removed and park brake releasedExplanation
When towing an aircraft, it is important to remove the control locks to ensure that the control surfaces are free to move and respond to any external forces. Additionally, the park brake should be released to allow the aircraft to move freely. This combination of removing the control locks and releasing the park brake ensures that the aircraft can be safely towed without any hindrance or resistance from the control surfaces or brakes.Rate this question:
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- 7.
The propeller may windmill even in light winds. A windmilling propeller:
- A.
Is a safety hazard
- B.
Can result in bearing damage
- C.
Both A and B
Correct Answer
C. Both A and BExplanation
A windmilling propeller can be a safety hazard because it can create drag and cause the aircraft to lose control. Additionally, it can result in bearing damage because the propeller is spinning freely without power, which can put stress on the bearings and cause them to wear out or fail.Rate this question:
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- 8.
A handle in the lower passenger door operates the door locking mechanism. The inside and outside handles:
- A.
Are mechanically interconnected
- B.
Operate independently from one another
- C.
Are electrically interconnected
Correct Answer
A. Are mechanically interconnectedExplanation
The correct answer is that the handles are mechanically interconnected. This means that when one handle is used to operate the door locking mechanism, it will also affect the other handle. In other words, if the handle on the inside is used to lock or unlock the door, it will also affect the handle on the outside and vice versa. This mechanical connection allows for convenient operation of the door locking mechanism from both the inside and outside of the vehicle.Rate this question:
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- 9.
A tail stand:
- A.
Must be used when servicing airplane inside tail section
- B.
Must be strong enough to support the whole airplane
- C.
Both A and B
Correct Answer
C. Both A and BExplanation
A tail stand must be used when servicing an airplane inside the tail section because it provides support and stability to prevent the aircraft from tipping over. Additionally, the tail stand must be strong enough to support the entire weight of the airplane to ensure safety during maintenance procedures. Therefore, both options A and B are correct.Rate this question:
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- 10.
The wing features two spars:
- A.
The front spar incorporates a special forged fitting and formed channel assembly for lift strut attachment
- B.
The wing is attached to the fuselage with attach fittings on the front and rear spar at each side of the fuselage
- C.
Both A and B
Correct Answer
C. Both A and BExplanation
The correct answer is Both A and B. This means that both statements A and B are true. Statement A explains that the front spar of the wing includes a special forged fitting and formed channel assembly for lift strut attachment. Statement B explains that the wing is attached to the fuselage with attach fittings on the front and rear spar at each side of the fuselage. Therefore, both statements A and B are correct.Rate this question:
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- 11.
The bleed air to operate the pneumatic systems in the aircraft are bled of at:
- A.
The third stage of the engine turbine (P3 air) to supply all systems
- B.
The third stage of the engine compressor (P3 air) to supply all systems
- C.
The third stage of the engine compressors (P3 air) and supplies no aircraft systems
Correct Answer
B. The third stage of the engine compressor (P3 air) to supply all systemsExplanation
The correct answer is that the bleed air to operate the pneumatic systems in the aircraft is bled off at the third stage of the engine compressor (P3 air) to supply all systems. This means that the air is taken from the third stage of the engine compressor and used to power all of the pneumatic systems in the aircraft.Rate this question:
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- 12.
The vacuum system features:
- A.
A flapper valve to split the airflow between the pressurisation and instrument air users
- B.
A bleed air pressure regulator providing regulated bleed air for the vacuum system
- C.
A check valve to stop airflow to the systems in event of an engine failure
Correct Answer
B. A bleed air pressure regulator providing regulated bleed air for the vacuum systemExplanation
The vacuum system requires regulated bleed air to function properly. This is achieved through a bleed air pressure regulator, which controls the flow of bleed air into the vacuum system. The regulator ensures that the air pressure is maintained at the appropriate level for the system to operate effectively. Without this regulator, the vacuum system may receive too much or too little bleed air, leading to improper functioning or failure of the system.Rate this question:
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- 13.
The vacuum ejector:
- A.
Allows bleed air flow through an orifice to create the necessary suction to operate instruments
- B.
Sense ambient pressure and bleed air temperature
- C.
Sense bleed air pressure and ambient temperature
Correct Answer
A. Allows bleed air flow through an orifice to create the necessary suction to operate instrumentsExplanation
The vacuum ejector allows bleed air flow through an orifice to create the necessary suction to operate instruments. This means that it uses the flow of air to create a vacuum, which is then used to power the instruments. It does not sense ambient pressure or bleed air temperature, nor does it sense bleed air pressure and ambient temperature. Its main function is to create suction for instrument operation.Rate this question:
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- 14.
What warns the pilot/engineer of a possible low vacuum condition?
- A.
Ambient sense
- B.
Ejector flow control actuator
- C.
A warning switch illuminating the red vacuum low warning light
Correct Answer
C. A warning switch illuminating the red vacuum low warning lightExplanation
The correct answer is the warning switch illuminating the red vacuum low warning light. This switch serves as an indicator for the pilot or engineer to be alerted of a possible low vacuum condition. When the vacuum level drops below a certain threshold, the switch is triggered and the red warning light is illuminated, indicating the need for attention and potential troubleshooting.Rate this question:
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- 15.
The primary ventilation system receives:
- A.
Pressurised air (P2.5 and P3) and connects to the central plenum located in the cockpit headliner area
- B.
Allows fresh air into the cockpit through small inlet doors located on the left and right side of the forward fuselage
- C.
Ram air at the upper end of each wing strut
Correct Answer
C. Ram air at the upper end of each wing strutExplanation
The primary ventilation system receives ram air at the upper end of each wing strut. This means that the system is designed to take in air that is forced into the aircraft by the forward motion of the aircraft. This air enters the cockpit through small inlet doors located on the left and right side of the forward fuselage. The ram air provides a source of fresh air for the cockpit, ensuring proper ventilation and air circulation.Rate this question:
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- 16.
The temperature limiter switch in the compressor bleed air heater system:
- A.
Is installed in the cabin heat firewall shutoff valve
- B.
Will open and de-energise the gate valve solenoid if the bleed air temperature exceeds certain values
- C.
Regulates the control pressure at the gate valve
Correct Answer
B. Will open and de-energise the gate valve solenoid if the bleed air temperature exceeds certain valuesExplanation
The temperature limiter switch in the compressor bleed air heater system is responsible for monitoring the temperature of the bleed air. If the temperature exceeds certain values, the switch will open and de-energize the gate valve solenoid. This action is taken to prevent any potential damage or overheating in the system. The switch acts as a safety measure to regulate the temperature and ensure that it remains within acceptable limits.Rate this question:
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- 17.
The pressure regulator assembly in the compressor bleed air heater:
- A.
Reduce P3 compressor outlet bleed air control pressure to set values (18 PSI)
- B.
Reduce engine RPM to regulate bleed air pressure
- C.
Increase P5 compressor outlet bleed air control pressure to set values (22 PSI)
Correct Answer
A. Reduce P3 compressor outlet bleed air control pressure to set values (18 PSI)Explanation
The pressure regulator assembly in the compressor bleed air heater is responsible for reducing the P3 compressor outlet bleed air control pressure to the desired set values of 18 PSI. This helps in maintaining a consistent and controlled pressure in the bleed air system.Rate this question:
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- 18.
The valve assembly – air diverter (mixing air valve):
- A.
Has two doors mechanically linked together, with both doors operated by a single MIXING AIR control
- B.
In the GRD PULL position, P2.5 interstage compressor bleed air provides heat at power settings below 89% Ng
- C.
Both A and B
Correct Answer
C. Both A and BExplanation
The valve assembly - air diverter (mixing air valve) has two doors that are mechanically linked together. These doors are operated by a single MIXING AIR control. In the GRD PULL position, P2.5 interstage compressor bleed air provides heat at power settings below 89% Ng. The correct answer is that both A and B are true statements.Rate this question:
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- 19.
The entire heat system is inoperative. What is the probable cause?
- A.
The circuit breaker tripped
- B.
Insufficient bleed air available
- C.
Check valve remains open
Correct Answer
A. The circuit breaker trippedExplanation
The circuit breaker tripping can cause the entire heat system to become inoperative. When the circuit breaker trips, it cuts off the flow of electricity to the heat system, leading to its malfunction. This can result in a loss of heat and the system not functioning properly.Rate this question:
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- 20.
As the angle of attack of an airfoil increases, the centre of pressure will:
- A.
Move towards the trailing edge
- B.
Move towards the leading edge
- C.
Remain stationary because both lift and drag components increase proportionally to increase angle of attack
Correct Answer
B. Move towards the leading edgeExplanation
As the angle of attack of an airfoil increases, the centre of pressure will move towards the leading edge. This is because an increase in angle of attack causes an increase in lift and a decrease in pressure on the upper surface of the airfoil. This shift in pressure distribution causes the centre of pressure to move towards the leading edge of the airfoil.Rate this question:
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- 21.
If the travel of the aircraft’s controls is correct but the cables are rigged exceptionally tight, what probable effect will this have when flying the aircraft?
- A.
It will cause stable response to autopilot signals
- B.
The aircraft will be heavy on the controls
- C.
The pilot will be unable to control the aircraft in flight
Correct Answer
B. The aircraft will be heavy on the controlsExplanation
If the cables are rigged exceptionally tight, it will cause the aircraft to be heavy on the controls. This means that the pilot will need to exert more force and effort to maneuver the aircraft. The tight cables restrict the movement of the controls, making it difficult for the pilot to make precise and smooth adjustments. This can potentially make the aircraft less responsive and more challenging to control during flight.Rate this question:
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- 22.
Roll control is accomplished by:
- A.
Aileron system
- B.
Aileron and spoiler system
- C.
Rudder system
Correct Answer
B. Aileron and spoiler systemExplanation
The correct answer is Aileron and spoiler system. The aileron system is responsible for controlling the roll of an aircraft by changing the lift on the wings. It does this by raising or lowering the ailerons on the wings, which in turn changes the amount of lift generated by each wing. The spoiler system, on the other hand, is used to assist in roll control by creating drag on the wings. By deploying the spoilers on one wing, the lift on that wing is reduced, causing the aircraft to roll in the opposite direction. Therefore, the aileron and spoiler system together provide effective roll control for an aircraft.Rate this question:
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- 23.
What controls the flap system travel during normal operation?
- A.
The flap motor circuit breaker
- B.
The flap control circuit breaker
- C.
The flap switch actuator by means of the flap control lever
Correct Answer
C. The flap switch actuator by means of the flap control leverExplanation
The flap switch actuator controls the flap system travel during normal operation by means of the flap control lever. This means that the position of the flap control lever determines the movement of the flaps.Rate this question:
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- 24.
The pilot reports a low fuel pressure. What is the probable cause?
- A.
Main (engine driven) boost pump defective
- B.
Standby boost pump defective
- C.
Fuses blown
Correct Answer
A. Main (engine driven) boost pump defectiveExplanation
A low fuel pressure can be caused by a defective main (engine driven) boost pump. This pump is responsible for supplying fuel to the engine, and if it is not functioning properly, it can result in decreased fuel pressure. This issue can potentially lead to engine failure or other fuel-related problems.Rate this question:
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- 25.
The pilot reports no fuel transferring from the reservoir fuel tank, however there is no low fuel pressure warning. What is the probable cause?
- A.
Defective boost pump
- B.
Defective transfer jet pump
- C.
The float check valve is open
Correct Answer
A. Defective boost pumpExplanation
The probable cause for no fuel transferring from the reservoir fuel tank, despite the absence of a low fuel pressure warning, is a defective boost pump. The boost pump is responsible for transferring fuel from the reservoir tank to the engine, and if it is defective, it will not be able to perform this function effectively. This would explain why there is no fuel transferring despite the absence of a low fuel pressure warning, as the boost pump is not able to generate enough pressure to transfer the fuel.Rate this question:
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- 26.
LEFT FUEL LOW or RIGHT FUEL LOW indicates
- A.
The respective fuel tank is at its low level
- B.
Fuel level in the reservoir tank is at its low level
- C.
Either standby pump not operating Either standby pump not operating
Correct Answer
A. The respective fuel tank is at its low levelExplanation
The correct answer is "The respective fuel tank is at its low level." The indicators "LEFT FUEL LOW" or "RIGHT FUEL LOW" are used to notify the pilot that the fuel level in the respective tank is low. This is important information for the pilot to ensure that they have enough fuel for the duration of the flight and to plan for refueling if necessary. The other options mentioned, such as the fuel level in the reservoir tank or the standby pump, are not directly related to the fuel level in the respective tank.Rate this question:
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- 27.
Spongy brakes are usually a result of:
- A.
Air in the system
- B.
Internal leakage
- C.
External leakage
Correct Answer
A. Air in the systemExplanation
Spongy brakes are usually a result of air in the system. When air gets trapped in the brake lines, it causes the brake pedal to feel soft and spongy. This happens because air is compressible, unlike brake fluid, which is designed to transfer force from the brake pedal to the brake calipers. As a result, when the brakes are applied, the air compresses instead of transferring the force effectively, leading to a spongy feeling. To fix this issue, the brake system needs to be bled to remove the air and ensure proper brake performance.Rate this question:
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- 28.
The hydraulic brake reservoir is located:
- A.
In the cockpit
- B.
In the engine compartment on the right top corner of the firewall
- C.
In the engine compartment on the lower left corner of the firewall
Correct Answer
C. In the engine compartment on the lower left corner of the firewallExplanation
The correct answer is "In the engine compartment on the lower left corner of the firewall." This location is commonly used for the hydraulic brake reservoir because it allows for easy access and maintenance. Placing it in the engine compartment ensures that it is close to the brake system components, making it convenient for checking the fluid levels and topping up if necessary. The lower left corner of the firewall is also a suitable location as it provides a secure and stable mounting point for the reservoir.Rate this question:
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- 29.
The main wheels:
- A.
Are fabricated of magnesium and are designed to used with tubeless tires
- B.
Are fabricated of aluminium and are designed to be used with tires and tubes
- C.
Either A or B
Correct Answer
B. Are fabricated of aluminium and are designed to be used with tires and tubesExplanation
The correct answer is "Are fabricated of aluminium and are designed to be used with tires and tubes." This means that the main wheels are made of aluminum and are specifically designed to be used with tires and tubes.Rate this question:
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- 30.
The nose wheels:
- A.
Are fabricated of aluminium and are designed to be used with tires and tubes
- B.
Are fabricated of magnesium and are designed to used with tubeless tires
- C.
Either A or B
Correct Answer
A. Are fabricated of aluminium and are designed to be used with tires and tubesExplanation
The correct answer is "Are fabricated of aluminium and are designed to be used with tires and tubes." This means that the nose wheels are made of aluminum and are specifically designed to be used with tires and tubes. The answer excludes the possibility of the nose wheels being made of magnesium or designed for use with tubeless tires.Rate this question:
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- 31.
The nose gear steering
- A.
Is accomplished by a steering wheel in the cockpit
- B.
Is accomplished by the pilot’s rudder pedals
- C.
Is accomplished by differential braking combined with a free moving nose wheel
Correct Answer
B. Is accomplished by the pilot’s rudder pedalsExplanation
The correct answer is that the nose gear steering is accomplished by the pilot's rudder pedals. This means that the pilot can control the direction of the aircraft's nose wheel by using the rudder pedals, which are located on the floor of the cockpit. By pressing on the appropriate pedal, the pilot can steer the nose wheel left or right, allowing for precise ground maneuvering during taxiing, takeoff, and landing.Rate this question:
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- 32.
How is wheel alignment corrected on the main wheels?
- A.
Special shims are utilised which change wheel camber
- B.
Up lock switches failing to open
- C.
Down lock switches failing to open
Correct Answer
A. Special shims are utilised which change wheel camberExplanation
Special shims are used to adjust the wheel camber during wheel alignment correction. These shims are placed between the wheel and the suspension to change the angle of the wheel in relation to the road surface. By adjusting the camber, the technician can ensure that the wheels are properly aligned and perpendicular to the ground, which helps in maintaining optimal tire contact and prevents uneven tire wear.Rate this question:
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- 33.
The fire detection system:
- A.
Test the bleed air warning system
- B.
Is installed in the engine compartment
- C.
Fire the extinguisher bottle to test installation
Correct Answer
B. Is installed in the engine compartmentExplanation
The correct answer is "Is installed in the engine compartment." This means that the fire detection system is placed in the engine compartment of the aircraft. This location is crucial as it allows for early detection of any potential fires in the engine area, which is a critical part of the aircraft. By having the system installed in this specific location, it ensures that any fire can be detected promptly, allowing for appropriate actions to be taken to extinguish the fire and prevent further damage or risks to the aircraft and its occupants.Rate this question:
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- 34.
The fire warning system:
- A.
Provides visual warning of an eminent cockpit fire
- B.
Consists of a flexible closed loop consisting of three sections with high resistance at normal operating temperature
- C.
Provides visual warning of no bleed air available to the systems
Correct Answer
B. Consists of a flexible closed loop consisting of three sections with high resistance at normal operating temperatureExplanation
The fire warning system consists of a flexible closed loop consisting of three sections with high resistance at normal operating temperature. This means that the system is designed to detect any increase in temperature, indicating a possible fire in the cockpit. The high resistance in the loop ensures that the system is sensitive enough to detect even small changes in temperature. This feature allows the system to provide visual warning of an imminent cockpit fire and ensures the safety of the aircraft and its occupants. Additionally, the system also provides visual warning if there is no bleed air available to the systems, indicating a potential problem with the aircraft's air supply.Rate this question:
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