HAWKER 800 SYSTEMS TEST

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AIR-CONDITIONING-Air-conditioning is available on the ground, provided

	The right engine is running and the right MAIN AIR VALVE switch is in the OPEN position.
	The APU is running and the APU AIR switch is in the OPEN position.
	The left engine is running and the left MAIN AIR VALVE switch is in the OPEN position.
	Either or all of answers are correct.

AIR-CONDITIONING-The auxiliary heat valve will move from closed to full open in approximately

	22 seconds.
	5 seconds.
	1 minute.
	10 seconds.

AIR-CONDITIONING-When the CABIN TEMP selector is in the MANUAL range it is spring loaded to the center (off) position

	True
	False

ELECTRICAL-For ease of isolating in case of smoke or fire, the circuit breakers protecting unswitched PE circuits are identified by

	Fluorescent paint.
	A white background.
	A grouping at the upper left corner of panel A.
	A grid of numbers and letters.

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

	250 amps
	400 amps
	300 amps
	350 amps

ELECTRICAL-If both main inverters should fail

	The standby inverter will assume the AC electrical load.
	The standby inverter, if armed, will assume the constant-frequency AC electrical load.
	The standby inverter, if armed, will assume the essential constant-frequency AC electrical load.
	Constant-frequency AC power will be lost.

FIRE PROTECTION- If an APU overheat condition is detected by any one or more of the detector switches, a signal is transmitted to

	Ring the fire bell.
	Shut down the APU.
	All of the answers are correct.
	Illuminate the FIRE warning indicator

FLIGHT CONTROLS - The rudder bias system must be on and operable for takeoff.

	False
	True

FLIGHT CONTROLS - In flight, if one Rudder Bias strut has failed or is isolated, the Vmca is ________KIAS.

	125
	145
	115
	112

FUEL SYSTEM - The ENG 1 and ENG 2 LO PRESS annunciators illuminate when the fuel pressure in the engine fuel lines falls below

	6 to 7 psi
	2 to 3 psi
	12 to 15 psi
	10 to 12 psi

FUEL SYSTEM - Fuel carried in the ventral tank must be transferred into the wing tanks when the fuel level in the wing tanks fall to __________ pounds.

	3,600
	3,300
	2,500
	3,000

FUEL SYSTEM - In order for the boost pumps to receive power from the PE bus

	Select the boost pump switch to EMERG with Ext PWR on.
	Select the boost pump switch to the EMERG position or ON or EMERG with start power switch set to START.
	Select the boost pump switch to the ON position.
	Select the boost pump switch to ON with Ext PWR on.

FUEL SYSTEM - To feed both engines from the right tank, the right boost pump must be operative

	True
	False

HYDRAULIC POWER - The auxiliary hydraulic pump is a

	air driven pump.
	Electrically powered.
	Hand pump.
	Engine driven pump.

ICE AND RAIN - The deicing fluid pump is powered by the _____ bus

	PS2
	PS1
	PE2
	PE

ICE AND RAIN - The cockpit windscreens (2) are _____ heated

	Radiantly.
	Bleed air
	Not
	Electrically

LANDING GEAR AND BRAKES - Inadvertent landing gear retraction is prevented while the aircraft is on the ground by

	Hydraulic pressure is not sufficient to retract the landing gear with the aircraft on the ground.
	Squat switch circuitry controlling the solenoid-operated landing gear selector valve is not completed.
	All of the answers are correct.
	A solenoid operated pawl engaging the selector lever.

LANDING GEAR AND BRAKES - Nose gear steering with the nose gear retracted is prevented by

	A hydraulic on-off valve.
	A mechanical lock that prevents the handwheel from being moved.
	The nose gear strut centering mechanism.
	All of the answers are correct.

LIMITATIONS - The maneuvering speed (Va) is

	196 KIAS
	M 0.66
	182 KIAS
	175 KIAS

LIMITATIONS - The maximum and minimum airport altitude for takeoff is _______ and ________.

	8,000 and -1000 feet.
	12,000 and -1000 feet.
	9,000 and -2000 feet.
	8,000 and -2000 feet.

MASTER WARNING - The master warning system is powered by the

	PS1 bus
	XE bus
	PE bus
	PS2 bus

MASTER WARNING - To extinguish an illuminated annunciator on the center annunciator panel

	Press either red MWS glareshield annunciator.
	Position the DIM O/RIDE switch to NORM.
	Press the test switch.
	The fault must be corrected.

POWERPLANT - Engine synchronization will be available when selected and

	Full throttle is not used.
	All of the answers are correct.
	Both fuel computers are operating normally.
	The APR system is not armed.

POWERPLANT - Engine cranking is provided by a

	Starter-generator through the planetary gearbox.
	Pneumatic starter.
	DC starter motor through the transfer gearbox.
	Starter-generator through the accessory gearbox.

PNEUMATIC SYSTEM - Electrical power for the HP BLEED on-off valves is supplied by the

	PS1 and PS2 bus respectively.
	PE Bus.
	PS2 Bus.
	XE Bus.