HAWKER 700 SYSTEMS TEST

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AIR-CONDITIONING-The auxiliary heating valve must be closed for takeoff

	True
	False

AIR-CONDITIONING-Select the correct statement concerning the auxiliary heating valve

	(D) Both A and C.
	(B) Opening of the valve allows hot air from the right engine to enter the air-conditioned air supply to the cockpit.
	(A) Opening of the valve allows hot air from both engines to enter the air-conditioned air supply to the cockpit.
	(C) Emergency pressurization supply from the left engine can be obtained by opening the valve.

AIR-CONDITIONING-With the CABIN TEMP selector in the MANUAL position and the DUCT O/HEAT annunciator illuminates

	You must select the TEMP SELECTOR to AUTO in order for the duct temperature limiter to function.
	The duct temperature will be reduced automatically.
	The duct temperature has exceeded 112 degrees C.
	You must select the TEMP SELECTOR to COOL to reduce the duct temperature and extinguish the annunciator.

AIR-CONDITIONING-The heat exchanger requires______________for proper cooling

	Air flow
	Freon 22
	Freon 12
	Cbrf2

ELECTRICAL-If one of the 500A feeder cable current limiters were blown prior to engine start

	The bus tie could not be closed after start.
	The engine will not start.
	The generator could not be instated after start.
	The engine will start.

ELECTRICAL-For engine starting the ground power unit must produce

	28 volts 1500 amps
	24 volts 1100 amps
	24 volts 1000 amps
	28 volts 1000 amps

ELECTRICAL-With the PE bus bar energized, illumination of the BATTERY NO CHG light indicates that

	Either No 1 or No 2 battery is not receiving a charge.
	Both batteries are fully charged.
	Both batteries are depleted.
	Either generator is not operating.

ELECTRICAL-Either No 1 or No 2 Inverter is capable of supplying all Constant-frequency AC requirements.

	False
	True

FLIGHT CONTROLS-Concerning the rudder bias system, the actuators and solenoid valves are protected from icing by heating elements controlled by the_________ switches

	Pitot Heat.
	APR
	Engine anti-ice.
	Rudder bias.

FLIGHT CONTROLS-Take-off is permitted with one rudder bias strut inoperative

	False
	True

FLIGHT CONTROLS-The Maximum altitude for flap extension is

	15,000 ft AGL
	15,000ft MSL
	No limit
	20,000ft MSL

FUEL-During flight including take-off and landing, the maximum difference in weight between the wing tanks is ________ pounds

	Varies with gross weight.
	500
	400
	800

FUEL-If, for any reason, fuel cannot be transferred from the auxiliary tanks, you should

	Land with flaps set at 15 degrees.
	Fuel will gravity feed.
	Leave the AUX FUEL TRANSFER lever open.
	Land as soon as possible.

FUEL-Both fuel boost pumps must be operative to transfer fuel from the auxiliary tanks

	True
	False

HYDRAULIC-The first step in operating the auxiliary hydraulic system is

	Operate the auxiliary hand pump.
	Dump main system pressure.
	Pull the EMERG U/C lever.
	Check the Main system pressure is 1,000 psi or below.

HYDRAULIC-The main hydraulic quantity is _______

	2.4 U.S gallons
	2 imperial gallons
	Either of the answers are correct
	9.1 liters

ICE AND RAIN-The cockpit direct-vision (DV) windows are _____ heated

	(A) Not
	(D) Both B and C.
	(B) Electrically
	(C) Bleed air

ICE AND RAIN-The left pitot heat system is powered from the _____ bus bar. The right pitot heat system is powered from the ____ bus bar

	PE and PS2
	PS1 and PS2
	XS1 and XS2
	XE

LANDING GEAR AND BRAKES-The nose gear doors are

	Electrically operated.
	Mechanically operated.
	None of the answers are correct.
	Hydraulically operated.

MWS-To dim the annunciators to the preset intensity level after illumination, you should

	Use the DIM O/RIDE switch.
	Turn the MWS dimmer control clockwise.
	Press the face of either red MWS glareshield annunciator.
	Use the individual system dimmer controls.

MWS-The audible warnings are

	A bell
	A chime
	All of the answers are correct.
	A horn

POWERPLANT-The Fuel flow indicators receive electrical power from

	(B) An additional inverter if the normal AC power system is not available.
	(D) Both A and B.
	(A) The normal AC power system.
	(C) DC power distribution system.

PRESSURIZATION-The maximum cabin differential pressure is

	8.50 psi
	8.0 psi
	8.35 psi
	8.75 psi

PRESSURIZATION-The maximum negative cabin differential pressure is

	0.00 psi
	0.025 psi
	0.25 psi
	8.35 psi

PRESSURIZATION-Power for the fan-operated venturi motor is furnished from the

	XS1 bus
	PS1 bus
	PE bus
	XS2 bus