HAWKER 800 SYSTEMS TEST

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AIR-CONDITIONING-As more air is allowed to bypass the cooling turbine, the outlet air becomes hotter

	False
	True

AIR-CONDITIONING-The cooling turbine requires______________for proper operation

	AC power
	Bleed air
	DC power
	Ram air

ELECTRICAL-When a generator is off line and the GEN FAIL and ELEC annunciators are illuminated, the generator may be reinstated by

	Position the generator switch to TRIP then to CLOSE then release.
	Reset the generator circuit breaker.
	Closing the bus-tie.
	Position the generator switch to CLOSE for 5 seconds then release.

ELECTRICAL-Control and operating power for the standby inverter is supplied from the

	PS2 bus
	No 3 battery
	PS1 bus
	PE bus

ELECTRICAL-IF the START PWR switch is selected before external power is connected the

	The engines will not start.
	EXT POWER switch will be ineffective.
	The start will be an external start.
	APU will not start.

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

	300 amps
	400 amps
	350 amps
	250 amps

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

	False
	True

FIRE PROTECTION- Select the correct statement(s) concerning the main engine fire bottles

	The pressure-relief discharge indicators are a small gauge.
	A buildup of excess thermal pressure in the bottle will cause the extinguishing agent to discharge.
	The pressure-relief discharge indicators are located under the right engine pylon on the fuselage.
	Indication of bottle discharge is a zero reading on the gauge.

FLIGHT CONTROLS - Select the correct statement(s) concerning the stall warning and identification system

	The stick shaker is automatically armed at lift-off.
	If the stick shaker is activated the auto-pilot will disengage (if engaged).
	All of the answers are correct.
	The identification system is automatically armed six seconds after lift off.

FUEL SYSTEM - Fuel from the auxiliary tank cannot be transferred if both fuel boost pumps are inoperative

	True
	False

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

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

FUEL SYSTEM - The ventral tank may be gravity fueled.

	True
	False

FUEL SYSTEM - The electrical power for the fuel quantity indicators is supplied by the _____ bus.

	PE
	XE
	PS1
	XS1

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
	XS1 and XS2
	PS1 and PS2
	XE

ICE AND RAIN - Failure of the outer glass sheet is characterized by

	A single crack.
	A pattern of small dice which will obscure vision because the particles form approximately l/4-inch squares.
	Smoke like haze, inside the windscreen.
	a pattern of large dice that will impair, but not obscure vision.

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

	Pt2 Tt2 sensor.
	Static plates.
	Inlet Cowl.
	Wings.

LANDING GEAR AND BRAKES - The landing gear is locked in the extended or retracted position by

	By initial movement of the actuators.
	By final movement of the actuators.
	By a separate actuator on each gear.
	By spring loaded capsules.

LIMITATIONS - The maximum ramp weight is

	27,400 lbs.
	25,500 lbs.
	27,520 lbs.
	26,000 lbs.

LIMITATIONS - The maximum landing gear operating speed is

	220 KIAS
	210 KIAS
	175 KIAS
	160 KIAS

MASTER WARNING - If the ANN DIM FAIL annunciator illuminates

	You should press the ANN DIM FAIL light.
	The DIM O/RIDE switch should be set to NORM.
	No action required.
	There is a dimmer circuit fault.

POWERPLANT - The N1 (fan) indicators receive electrical power from

	DC power system.
	XE bus
	The normal AC power system.
	An additional inverter if the normal AC power system is not available.

POWERPLANT - The electrical source for the oil pressure indicators is

	Battery.
	6 volt AC transformer.
	DC power system.
	115 volt AC inverter.

POWERPLANT - The Maximum ITT (NORMAL power)for takeoff is

	994 for 2 sec.
	952 for 5 min.
	All of the answers are correct.
	974 for 5 sec.

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

	PS1 bus
	PE bus
	XS2 bus
	XS1 bus

PRESSURIZATION SYSTEM - Cabin pressurization is maintained by

	Regulating cabin incoming air.
	Regulating incoming and outflow cabin air.
	Regulating cabin outflow air.
	Regulating cabin air temperature.