General Knowledge Exam Questions Flashcards
Q1 The Battery is mounted?
C……….On a swing out tray in front of the firewall
Q2 The voltage of the Nicad Battery is?
A……….24 Volts
Q3 Immediate corrective action must be taken:
C……….Upon Illumination of the Battery overheat light
Q4 The generator control unit (GCU) controls the operation of the
C……….Starter-Generator
Q5 The Ground power monitor:
A……….Protects the electrical system from incorrect voltages
Q6 The voltammeter and its associated selector switch are used to read
D……….all of the above (generator current/alternator current/battery current)
Q7 Placing the avionics bus tie switch in the on position
C……….ties the no 1 avionics bus to the no 2 avionics bus
Q8 when the external power switch is placed in the bus position
C……….external power is applied to the main bus
Q9 the standby electrical system
C……….is powered by a belt driven alternator
Q10 the landing lights should be used during
A……….landing and takeoff
Q11 the taxi/recognition lights are located
C……….in the wing leading edges
Q12 the strobe lights are required to be used:
B……….during night operations
Q14 the flashing beacon is to be used for
D……….both a and b (anti collision and ground operations)
Q13 the courtesy lights are controlled by
B……….cabin light switch
Q15 pressing the lamp test switch
D……….illuminates all annunciators and sounds the fuel selector off warning
Q16 placing the day-night switch in the night position
D………dims all illuminated green and some amber annuniciators
Q17 Fuel flows from the wing tanks to the reservoir tank by
C……….gravity
Q18 Fuel is pumped from the reservoir tank primarily by the
A……….ejector fuel pump
Q19 if the fuel filter becomes blocked
C……….the red fuel filter bypass flag pops up
Q20 fuel rejected by the engine on shutdown
B……….drains into a fireproof fuel can on the firewall
Q21 the 2 fuel tank selectors located on the overhead panel
D……….both a and b (are both normally on in flight) (are both normally off during refuelling)
Q22 the fuel selector off warning system sounds when
D……….all of the above (both left and right fuel tank shot off valves are closed) (either the left or right fuel tank shutoff valves are closed during an engine operation) (one fuel selector is at OFF and fuel remaining in the tank being used is less than approximately 25 gallons)
Q23 the auxiliary fuel boost pump switch:
A……….Is placed in the NORM position during all normal engine operations
Q24 when the starter switch is placed in the start position
B……….the ignition system is energised if the ignition switch is in the NORM position
Q25 The propeller and pitot-static anti-ice systems are intended to be used
C……….To prevent ice accumulation
Q26 The standby electrical system
C……….is powered by a belt driven alternator
Q27 the ice detector light is used
A……….Momentarily to detect ice accumulations at night
Q28 the wing spoilers on the caravan 1 are designed to
B……….Improve lateral control of the airplane at low speeds
Q29 the rudder lock is operated by a lever beneath the rudder which
D……….is located on the centre pedestal (check this answer)
Q30 the rudder trim system
C……….operates against nosewheel steering bungee
Q31 the standby flap system is operated
B……….until the flap position indicator reaches the desired setting
Q32 the alternate static source valve for the left pitot-static system is located
D……….below the deice/anti ice switch panel
Q33 The squelch on the KX 155 NAV/COMM transceiver
D……….both B&C (set automatically) (can be overridden by pulling the volume control out)
Q34 The frequencies displayed on the front panel of KK NAV/COMM transceiver
B……….are held in nonvolatile memory when the unit is off
Q35 COMM frequency selection is accomplished by
A……….rotating the frequency select knobs and observing the STBY window
Q36 when the NAV receiver is in the RAD (radial) mode
C……….the radial to the station is digitally displayed
Q37 if the VOR signal is too weak to provide a radial readout
C……….3 dashes are displayed in the STBY/RAD window
Q38 On the KR 87 ADF Unit, when the flight timer (FLT) is displayed
A……….the STBY frequency is held in memory but not displayed
Q39 when the KK 87 ADF is in the ANT mode
B……….the loop antenna is disabled
Q40 the elapsed timer (ET) on the KR87 ADF unit
B……….is started by pressing the RST button regardless of what is displayed
Q41 On the KN 673 DME unit, when the rotary switch is placed in the HOLD position
C……….the DME is channeled to the last selected NAV1 or NAV2 frequency
Q42 the display of the marker beacon receiver shows
A……….a white light for the inner marker or airway marker
Q43 the VFR button on the KT 79 transponder
C……….Can be programmed to any transponder code
Q44 cabin ventilating air enters the aircraft through
D……….both B&C (air inlets on each side of the forward fuselage) and (air inlets in each wing at the upper ends of the wing struts)
Q45 If more cabin heating is needed during ground operations
A……….Move the fuel condition lever to high idle
Q46 Windshield defrosting can be accomplished by
A……….pulling out the defrost/forward cabin control and pushing in the aft/forward cabin control
Q47 the cabin heat firewall shutoff control should be pulled out
B……….if a fire is detected in the engine compartment
Q48 the PT6A engine is defined as
B………free turbine, turboprop engine
Q49 with the propeller control lever in the MAX position
B……….the engine delivers max torque
Q50 the torque gauge indicates the power
D……….delivered to the propeller
Q51 engine oil should be
D………. Maintained to within 2 quarts of MAX HOT or MAX COLD as appropriate
Q52 The Power turbine is mounted on a shaft that
C………. Drives the reduction gearbox
Q53 The Ignition switch should be placed in the ON position
D………. All of the above (for airstarts without starter assist/for operation on water- covered runways/during flight in heavy operation)
Q54 Air Induced into the engine
A………. Enters at the rear and is exhausted at the front
Q55 The inertial separator should be placed in the bypass position
B………. When flying through visible moisture at low temperatures
Q56 During Operations using the emergency power lever
B………. The EMERGENCY POWER LEVER annunciator light will illuminate when the level is unstowed from the NORMAL position
Q57 Loss of any pneumatic signal to the fuel control unit causes
B……….The engine to drop to idle RPM
Q58 When the starter switch is placed in the START position
B……….The ignition system is energized if the IGNITION switch is in the NORM position
Q59 During the overspeed governor test the propeller rpm should not exceed
C………. 1,750 + 60 rpm
Q60 If the nose gear has been turned past its 56 degree maximum travel
A………. The frangible stop will be sheared off
Q61 The parking brake is applied by
B………. setting the brakes with the brake pedals and pulling the parking brake handle aft.
Q62 A hot start may occur if
D………. All of the above (the GPU fails during start/the bleed air switch is on during the start/the emergency power lever is unstowed during the start)
Q63 Which is the correct flap setting for takeoff
C………. 20 degrees
Q64 How many audio alerts are there on the aircraft
C………more than 10
Q65 The imbalance between the fuel tanks should not exceed
A……… 200 lbs
