HAWKER 800XP SYSTEMS TEST

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AIR-CONDITIONING-As more air passes through the cooling turbine, the outlet air becomes hotter

	False
	True

AIR-CONDITIONING-Cooling is augmented by a freon air-conditioning system while on the ground.

	False
	True

ELECTRICAL-Either of the 2 main (INV 1 or INV 2) constant frequency inverters are capable of supplying all constant frequency AC power requirements.

	False
	True

ELECTRICAL-Either of the 3 constant frequency inverters are capable of supplying all constant frequency AC power requirements.

	False
	True

ELECTRICAL-The maximum continuous (main engine) generator load limit is

	400 amps
	300 amps
	250 amps
	350 amps

ELECTRICAL-The No 1 transformer is powered by the

	PE bus
	XE bus
	XS1 bus
	XS2 bus

ELECTRICAL-With the battery switch set to ON, the right engine running, the right generator on line, the bus tie contactor open, and the START PWR switch on

	Only the No 1 battery is being charged.
	Both batteries are being charged.
	The batteries are not being charged.
	Only the No 2 battery is being charged.

FLIGHT CONTROLS-Takeoff with the aileron/elevator gust lock installed is prevented by

	An aileron/elevator gust lock, attached to the airplane structure, when connected to the left control wheel, prevents aileron and elevator movement. Throttle lever movement is also restricted.
	Not prevented.
	A warning horn.
	The gust lock lever on the pedestal.

FLIGHT CONTROLS-The amber RUDDER BIAS annunciator will illuminate if

	One or both rudder bias switches are OFF.
	All of the answers are correct.
	The rudder bias system is activated.
	The rudder bias system is inoperative.

FUEL SYSTEM-If during normal pressure refueling, an overflow condition exists the MASTER REFUEL VALVE will CLOSE

	True
	False

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

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

FUEL SYSTEM-Which of the following statement(s) are true concerning the WING FUEL X FEED/TFR annunciator

	It is located on the center MWS panel.
	All of the answers are correct.
	Its color is white.
	The WING FUEL X FEED/TRANSFER lever is out of the closed position.

ICE and RAIN-If engine anti-ice is required, it should be switched on prior to setting take-off power.

	False
	True

ICE and RAIN-If the aircraft is cold soaked below -10 degrees C and the time requirement for windscreen heat on is not met, then a speed restriction of __________ is required.

	250 KIAS until an altitude of 10,000 feet.
	230 KIAS until an altitude of 6,000 feet.
	210 KIAS until an altitude of 10,000 feet.
	257 KIAS below 8,000 feet.

ICE and RAIN-What would cause the ICE PROT annunciator on the center Annunciator panel to flash?

	windscreen heat failure.
	Any annunciator on the ICE PROTECTION roof panel has illuminated.
	Rudder bias heat failure.
	Pitot heat amperes high.

ICE and RAIN-Which of the following components are deiced by hot bleed air?

	Inlet Cowl.
	Pt2 Tt2 sensor.
	Wings.
	Galley drains

LIMITATIONS-The maneuvering speed (Va) is

	175 KIAS
	M 0.66
	196 KIAS
	182 KIAS

MASTER WARNING SYSTEM-Steady illumination of the ELECT UP (arrow) annunciator on the center annunciator panel indicates

	There is a new electrical system annunciator illuminated on the roof panel.
	There is a previously acknowledged electrical system annunciator illuminated on the roof panel.
	The MWS is flashing.
	The batteries are not charging.

MASTER WARNING SYSTEM-The audible warnings are

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

POWERPLANT-Engine synchronization will be available when selected and

	(B) The left engine fuel computer is operating.
	(A) Both fuel computer are operating normally.
	(D) Both A and C.
	(C) The APR system is not armed.

POWERPLANT-Select the correct statement(s) concerning the automatic performance reserve system (APR)

	The APR O/RIDE switch must be depressed for takeoff.
	If electrical power is lost to the APR controller, APR will not be available.
	If operational, except for crew training flights, the APR system must be ARMED for takeoff.
	The synchronizer controller must be operational for APR operation.

PRESSURIZATION-By opening the auxiliary heat valve, the cabin altitude can be maintained to _________ feet with an aircraft altitude of _______ feet.

	10,000 and 40,000
	8,000 and 41,000
	9,000 and 40,000
	10,000 and 41,000

PRESSURIZATION-Cabin pressurization can be maintained with only one engine operating

	True
	False

PRESSURIZATION-The ram air valve is controlled

	Electrically through a microswitch in the dump lever quadrant.
	By the manual pressurization control valve.
	Mechanically by the dump lever.
	By the flood flow switch.

PRESSURIZATION-The ram air valve opening can be varied (stopped) to any position between open and closed

	False
	True