Cessna Grand Caravan C208 Questions

Ground School Cessna Grand Caravan

CARAVAN 208/208B/EX G1000 PILOT TRAINING MANUAL Questions

1 / 67

Operation of the air conditioner can cause compass deviation of more than:

a) 10°

b) 15°

c) 18°

d) 20°

2 / 67

The ground power monitor:

a) Protects the electrical system

b) Controls the external generator

c) Senses operation of the starter generator

d) Regulates generator output

3 / 67

If the fuel filter becomes blocked:

a) Fuel starvation occurs and the engine stops.

b) A CAS message appears.

c) The red fuel filter bypass flag appears.

d) The fuel filter bypass horn sounds.

4 / 67

What must be accomplished when operating the air conditioning on the ground if ITT threatens to exceed 700°C:

a) Advance the condition lever

b) Open outside air vents

c) Position AC FANS to HIGH

d) Position the BLEED AIR HEAT switch to ON

5 / 67

The standby flap system is operated:

a) Until the flaps reach their stops

b) Until the flap position indicator reaches the desired setting

c) By using the crank on the overhead panel

d) Hydraulically

6 / 67

The anti-ice fluid tank has a capacity of:

a) 15 gallons

b) 20.8 gallons

c) 11.7 gallons

d) 9.3 gallons

7 / 67

If the pilot PFD fails, the MFD:

a) Automatically goes into reversionary mode whether or not the Reversionary button on the audio panel is pressed.

b) Automatically go into reversionary mode on the pilot PFD but not the copilot PFD

c) Either reversionary button on the pilot or copilot audio panel must be pressed

d) Are blank and the pilot must declare an emergency and land the aircraft immediately

8 / 67

The standby electrical system:

a) Is powered by the battery

b) Is powered by the engine-driven generator

c) Is powered by a belt-driven alternator

d) Is actuated by the ground power monitor

9 / 67

The rudder pedals can be used to steer the nose gear approximately:

a) 50°eithersideofcenter

b) 26° either side of center

c) 15° either side of center

d) 10° either side of center

10 / 67

The minimum de-ice fluid level for dis-patch into forecast icing conditions is:

a) 20 gallons

b) 15 gallons

c) 11.7 gallons

d) 9.3 gallons

11 / 67

The wing spoilers:

a) Are used as speed reduction devices

b) Improve lateral control of the aircraft at low speeds

c) Increase the effectiveness of the flaps.

d) Balance control forces in the aileron system

12 / 67

During the overspeed governor test, the propeller rpm should not exceed:

a) 1,900±60rpm

b) 1,250 ± 60 rpm

c) 1,750 ± 60 rpm

d) 2,000 ± 60 rpm

13 / 67

The CWS button on the control yoke:

a) Momentarily disengages the autopilot, but leave the servos engaged

b) Momentarily disengages the roll and pitch servos, but not the autopilot

c) Disengages the yaw damper

d) Discontinues the pitch mode of the autopilot

14 / 67

The inertial separator should be positioned to the bypass position:

a) To increase engine rpm

b) When flying through visible moisture at low temperatures

c) For all takeoffs

d) During all operations above 5,000 feet

15 / 67

The PLAY key on the audio panel allows:

a) Playback of the previously recorded 2.5-minute block of a received audio transmission

b) Playback of the last audio transmission on the No. 2 NAV

c) Receipt of the last PA request from the passengers

d) Playback of the XM radio song that is being uploaded

16 / 67

If the nose gear is turned past the maximum placarded travel limit:

a) The frangible stop will be sheared off

b) The entire nose gear must be replaced.

c) No damage has been done.

d) The aircraft must not be moved.

17 / 67

The two FUEL TANK SELECTOR knobs on the overhead panel:

a) Are both normally ON in flight

b) Are both normally OFF during refueling

c) Are OFF during ground operations

d) Both A and B

18 / 67

The lead-acid battery case is vented to prevent:

a) Concentrated accumulation of hydrogen gas in the airframe

b) Pressure differential in the battery

c) Contamination from ambient air

d) Overcharging of the battery

19 / 67

The maximum endurance level with a fully serviced anti-ice fluid tank in MAX FLOW AIRFRAME is:

a) 1 hour

b) 40 minutes

c) 30 minutes

d) 15 minutes

20 / 67

The torque indication indicates the power:

a) Developed by the gas generator

b) Delivered by the propeller

c) Of the combined gas generator and power turbine

d) Delivered to the propeller

21 / 67

The two GDC 72 air data computers supply information to which instruments?

a) Standby airspeed indicator, standby altimeter, and standby attitude indicator

b) PFD attitude indicator and horizontal direction indicator

c) PFD airspeed indicators, altimeters, and vertical speed indicators

d) MFD XM weather information system

22 / 67

Fuel flows from the wing tanks to the reservoir tank by:

a) Fuel boost pump pressure

b) Ejector pump pressure

c) Gravity

d) Fuel control unit pressure

23 / 67

The battery is:

a) In the tail cone

b) Under the right front seat

c) On a swing out tray in front of the firewall

d) On the floor behind the pilot seat

24 / 67

Loss of any pneumatic signal to the fuel control unit causes:

a) The engine to shut down

b) The engine to drop to idle rpm

c) The engine rpm to increase rapidly

d) A complete stoppage of fuel flow

25 / 67

The rudder lock:

a) Must be pulled out during engine start

b) Must be pushed in to lock the rudder

c) Must be released before towing the aircraft

d) Is on the center pedestal

26 / 67

The rudder trim system:

a) Operates a trim tab on the rudder

b) Is operated electrically

c) Moves only the rudder

d) Is controlled by a knob on the instrument panel

27 / 67

The standby electrical power system is required to be installed and functional for:

a) IMC conditions

b) Night operations

c) Commercial operations

d) Icing conditions

28 / 67

The flashing beacon is used for:

a) Anticollision protection

b) Recognition during ground operations

c) Operation in instrument conditions

d) Both A and B

29 / 67

The taxi/recognition lights are:

a) On the nose gear

b) On the wingtips

c) In the wing leading edges

d) In the front of the engine cowl

30 / 67

The air conditioning system is:

a) Powered by the propeller reduction system

b) Electrically operated

c) Belt operated by the engine accessory section

d) Extracts energy from exhaust gases as its power source

31 / 67

The BARO MIN setting on the PFD is:

a) The height above ground level for the minimums of an approach

b) The desired altitude at which the aircraft levels when climbing to a selected altitude

c) The desired altitude at which the aircraft descends when reaching the minimums of an approach

d) The decision height altitude or mini- mum descent altitude on an approach

32 / 67

Air induced into the engine:

a) Enters at the rear and is exhausted at the front

b) Enters at the front and is exhausted at the rear

c) Passes from the power turbine to the compressor wheels

d) Must be cooled by the compressor section

33 / 67

The voltmeter and its associated selector button are used to read:

a) Generator current

b) Alternator current

c) Battery current

d) All of the above

34 / 67

The IGNITION switch should be positioned to ON:

a) For airstarts without starter assist

b) For operation on water-covered runways

c) During flight in heavy precipitation

d) All of the above

35 / 67

While operating the GWX weather radar system on the ground, ensure that:

a) The gain is calibrated properly

b) The radar system has been tested

c) The No. 2 COM is set to theATIS

d) No one is within 10 feet of the radar antenna if the weather is activated while on the ground

36 / 67

The strobe lights are required:

a) In instrument conditions

b) During night operations

c) Whenever the engine is operating

d) Only when taxiing

37 / 67

The CABIN HEAT FIREWALL SHUTOFF knob:

a) Activates an engine fire extinguisher

b) Secures the firewall if an engine fire occurs

c) Turns off the bleed-air heat if the passengers are too hot

d) Deactivates the engine fire extinguisher

38 / 67

During operations using the emergency power lever:

a) Extreme caution should be used when advancing the EMERG PWR LVR

b) The EMERG PWR LVR CAS message appears when the lever is not stowed in the NORMAL position and engine not running.

c) Only partial engine power is available.

d) Engine response may be slower than when using the power lever.

39 / 67

Fuel is pumped from the reservoir tank primarily by the:

a) Main ejector pump

b) Boost pump

c) Engine-driven fuel pump

d) Fuel control unit

40 / 67

Pressing the ALERTS softkey for the crew alert system displays the:

a) ALERTS window

b) Status of scheduled maintenance

c) Next waypoint in the flight plan

d) Hazardous weather detected within 100 NM of the aircraft position

41 / 67

When the EXTERNAL POWER switch is positioned to BUS:

a) External power is applied to the starter

b) External power is applied to the avionics bus

c) External power is applied to the main bus

d) Power is sent from the main bus to the external power receptacle

42 / 67

The generator control unit (GCU) controls operation of the:

a) Generator only

b) Starter only

c) Starter-generator

d) Standby electrical system

43 / 67

The in-flight ice protection equipment provides:

a) Unlimited ability to operate in icing conditions

b) Ice protection through use of bleed air

c) Adequate ice protection during normal icing conditions

d) The ability to de-ice the aircraft on the ramp

44 / 67

With the propeller control lever positioned to MAX:

a) The propeller speed is governed at 1,900 rpm.

b) The engine delivers maximum torque.

c) The propeller governor is bypassed.

d) The gas generator rpm is at maximum.

45 / 67

A WARNING ALERT accompanied by a continuous chime indicates a condition that:

a) Is advisory in nature

b) Is normal during takeoff and landing

c) Requires immediate attention

d) The warning system is in error

46 / 67

The maximum endurance level with a fully serviced anti-ice fluid tank in NORMAL is:

a) 5 hours

b) 3 hours 25 minutes

c) 2 hours

d) 1.5 hours

47 / 67

The oxygen system controls are:

a) In the overhead console.

b) On the instrument panel.

c) On the center console.

d) On the left sidewall switch and CB panel.

48 / 67

According to the “Engine Fire in Flight” checklist, a red ENGINE FIRE CAS annunciation and warning chime:

a) Requires activation of the FIRE DETECT switch

b) Requires declaration of an emergency

c) Requires considering the five memory items associated with the “Engine Fire in Flight” checklist

d) Requires activation of the fire extinguisher

49 / 67

The power turbine is on a shaft that:

a) Drives the gas generator

b) Drives the accessory section

c) Drives the reduction gear

d) Both A. and B. above

50 / 67

The fire-detection test function assures:

a) Fire wall is intact

b) Fire detection loop has proper integrity

c) No fire exists in the engine compartment

d) Fire detection system cannot give false warnings

51 / 67

The auxiliary fuel boost pump switch:

a) Is positioned to NORM during all normal engine operations

b) Is positioned to OFF except in emergency fuel situations

c) Is positioned to ON at all times to prevent fuel starvation

d) Is positioned to OFF during all normal engine operations

52 / 67

When the STARTER switch is positioned to START:

a) The IGNITION switch must be positioned to ON

b) The ignition system is energized

c) The starter-generator functions as a generator

d) The ignition system is deenergized

53 / 67

The ice detector light is used:

a) Momentarily to detect ice accumulations at night

b) At all times during flight in icing conditions

c) Only when visible moisture is present

d) Also as a courtesy light on the ground

54 / 67

When the pilot chooses a lateral or vertical mode on the mode controller, the AFCS status box indicates:

a) Green for standby and white for active

b) Magenta for standby and white for active

c) White for standby and green for active

d) Both white for standby and for active

55 / 67

The courtesy lights are controlled by:

a) Exterior lighting switch

b) Cabin light switch

c) Landing light switch

d) Battery switch

56 / 67

When operating with the anti-ice fluid control switch in NORMAL, a green readout on the MFD indicates that at least:

a) 20 minutes of fluid remain

b) 15 minutes of fluid remain

c) 10 minutes of fluid remain

d) 5 minutes of fluid remain

57 / 67

Positioning the AVIONICS BUS TIE switch to ON:

a) Ties the avionics bus to the battery

b) Ties the No. 1 avionics bus to the generator

c) Ties the No. 1 avionics bus to the No.2 avionics bus

d) Disconnects the avionics buses from each other

58 / 67

The fuel-selector-off warning system sounds when:

a) Both left and right fuel tank shutoff valves are closed.

b) Either the left or right fuel tank shutoff valves are closed during an engine start operation.

c) One fuel selector is at OFF and fuel remaining in the tank being used is less than 25 gallons.

d) All of the above.

59 / 67

Fuel rejected during engine shutdown:

a) Drains onto the ground from the manifold

b) Drains into a fireproof fuel can on the firewall

c) Drains into the reservoir tank

d) Is pumped into the left wing tank

60 / 67

The parking brake is applied by:

a) Pumping the parking brake handle until the brakes are set

b) Setting the brakes with the rudder pedals and pulling the parking brake handle aft

c) Pressing the toe brakes and pulling the parking brake handle aft

d) None of the above

61 / 67

Use landing lights during:

a) Landing and takeoff

b) Landing only

c) Taxiing

d) Cruising

62 / 67

The fire-detection system warns of excessive temperature in the engine compartment

a) True

b) False

63 / 67

When the anti-ice fluid control switch operates in MAX FLOW AIRFRAME, a red readout on the MFD indicates:

a) 10 minutes or less of fluid remain

b) 5 minutes or less of fluid remain

c) 2.5 minutes or less of fluid remain

d) 1 minute or less of fluid remains

64 / 67

The minimum Ng when operating the air conditioning on the ground is:

a) 70%

b) 65%

c) 56%

d) 55%

65 / 67

The PT6A-140 engine is defined as a:

a) Fixed-shaft,constant-speedengine

b) Free-turbine, turboprop engine

c) Single-spool, variable-speed engine