HAWKER 700 SYSTEMS TEST

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

	False
	True

AIR-CONDITIONING-The auxiliary heating valve is controlled by the

	Automatic temperature controller.
	Temperate switch in the main duct.
	F/DECK HEAT VALVE switch.
	MAIN AIR VALVE switch.

AIR-CONDITIONING-Air from the auxiliary heating valve, when opened

	(C) Can provide emergency pressurization air.
	(A) Bypasses all other air-conditioning ducts in the rear bay.
	(B) Supplies additional heated air to the pilots foot outlets only.
	(D) Both A and C.

ELECTRICAL-During external charging, the batteries will automatically isolated for which of the following conditions?

	(A) The batteries have received a full charge.
	(C) Ground supply voltage become abnormal.
	(B) Either battery hot.
	(D) Both B and C.

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

	True
	False

ELECTRICAL-With both main inverters operating with the standby inverter switch in the ARMED position

	The No 1 inverter supplies the XS1 and XE buses.
	The No 1 inverter supplies the XS1, XS2 and XE buses.
	The standby inverter supplies the XE bus.
	The No 1 inverter supplies the XS1 bus only.

ELECTRICAL-If both the No 1 and No 2 inverters are operating and either the No 1 or the No 2 inverter should fail

	The remaining inverter will automatically assume the load if the standby inverter is armed.
	The standby inverter assumes the failed inverters load.
	The remaining inverter will automatically assume the load.
	The remaining inverter will assume the load when reset.

ELECTRICAL-In flight, should the BATT HOT annunciator illuminate, the batteries will automatically be isolated

	False
	True

FIRE PROTECTION-Both fire bottles may be discharged to same engine

	False
	True

FUEL-The fuel filter will bypass should it become clogged

	False
	True

FUEL-Which of the following statement(s) are true concerning the amber REFUEL ON annunciator

	(D) Both A and B.
	(B) At least one refuel valve is open.
	(A) You should not take-off.
	(C) The fuel quantity is low.

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

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

FUEL-The total usable fuel capacity, as listed in the crew manual is

	8,160 pounds
	9,640 pounds
	9,440 pounds
	9,330 pounds

FUEL-The electrical power for the fuel quantity indicators is supplied by the PE bus

	False
	True

LANDING GEAR AND BRAKES-The nose gear doors are

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

LANDING GEAR AND BRAKES-When all landing gear are up and locked the position indicators will be

	No red, no green annunciators illuminated.
	Three green, no red annunciators illuminated.
	A green light in the handle.
	Three red, three green annunciators illuminated.

LANDING GEAR AND BRAKES-The main landing gear inboard doors are closed.

	Only when the gear is extended.
	When the gear is in either the extended or retracted position.
	Only when the gear has been retracted using the auxiliary system.
	Only when the gear is retracted.

LANDING GEAR AND BRAKES-During emergency brake operation, after selecting emergency brakes, anti-skid (maxaret) protection is available

	True
	False

LIMITATIONS-The maximum mach number (Mmo) is

	440 KIAS
	0.82
	0.80
	0.78

PRESSURIZATION-The function of the _____________ is close the Outflow/Safety valves should the cabin altitude become excessive

	Outflow/Safety valves.
	Pressure regulator.
	Ram air valve
	Pneumatic Relays.

PRESSURIZATION-Under manual control, the venturi extracts air from the

	Outflow/Safety valve.
	Pneumatic relays.
	Controller.
	Pressure regulators.

PRESSURIZATION-Either one of the pressure regulators is calibrated to limit cabin altitude to approximately

	To within .35 psi of airplane altitude.
	8.34 psid
	13,500 feet
	10,000 feet

PRESSURIZATION-The function of the fan-operated venturi in the pressurization system is to

	Provide pre-pressurization prior to lift-off.
	Determine control pressure during the flight mode.
	Determine reference pressure for the automatic controller.
	Provide a vacuum to hold the outflow valves open on the ground.

PRESSURIZATION-The MAIN AIR VALVE indicators, when illuminated indicates that

	The indicated MAIN AIR VALVE is open.
	You should position the indicated MAIN AIR VALVE switch to OPEN.
	Power is not available to the indicated MAIN AIR VALVE.
	The indicated MAIN AIR VALVE does not match the switch position (15 second time delay).

PRESSURIZATION-If the fan-operated venturi motor is activated in flight

	There will be no effect.
	The ground test valve should be selected to the GROUND TEST position.
	Pressurization will be lost.
	Control of the cabin pressure will be sluggish.