HAWKER 800 SYSTEMS TEST

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AIR-CONDITIONING-The duct temperature limiter is inoperative when the CABIN TEMP selector is in the MANUAL position.

	False
	True

AIR-CONDITIONING-Air for heat exchanger cooling is achieved through

	A spring loaded inward opening relief door which allows air from the rear bay to enter if the dorsal intake becomes blocked.
	Either of the answers are correct.
	The dorsal intake duct by ram air when airborne.
	The dorsal intake duct by a fan driven by the cooling turbine while on the ground.

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

ELECTRICAL-The amber BATT 1 HOT or BATT 2 HOT annunciator will illuminate when it's respective battery temperature reaches

	150 degrees F (68 degrees C)
	120 degrees F (48 degrees C)
	158 degrees F (70 degrees C)
	135 degrees F (57 degrees C)

ELECTRICAL-The electrical power for windscreen heating is supplied by

	A static inverter.
	The windscreen transformer rectifier.
	Engine driven alternator.
	The engine driven generators.

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- Select the correct statement concerning the REAR BAY O/HEAT annunciator

	If it illuminates it will trigger the red MWS indicators on the glare shield.
	It will illuminate if two or more of the six thermal switches in the rear bay senses an overheat condition.
	All of the answers are correct.
	It can be extinguished by depressing either red MWS indicator on the glare shield.

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

	112
	115
	145
	125

FUEL SYSTEM - The minimum and maximum Fuel temperature is

	-58 deg C minimum to +57 deg C Maximum.
	-57 deg F minimum to +58 deg F Maximum.
	-57 deg C minimum to +58 deg C Maximum.
	-58 deg F minimum to +57 deg F Maximum.

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

	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 EMERG with Ext PWR on.
	Select the boost pump switch to ON with Ext PWR on.

FUEL SYSTEM - Fuel transfer motive flow fuel is supplied by

	Engine-driven low pressure pumps.
	Engine-driven high pressure pumps.
	Ventral tank jet pumps.
	Wing electric boost pumps.

HYDRAULIC POWER - The on-off valve in each engine-driven pump suction line is actuated by

	Bleed air.
	Electrically.
	Mechanically by the HP COCK levers.
	Automatically when pressure builds up.

HYDRAULIC POWER - If the pressure indicator cycles to 4,000 psi and the full-flow relief valve can be heard cycling, you should

	Move each power lever in turn, to identify the malfunctioning pump, and shut down the relevant engine, if practicable.
	None of the answers are correct.
	No specific action is required.
	Land immediately.

HYDRAULIC POWER - The auxiliary hydraulic reservoir is located in the nose wheel well.

	False
	True

ICE AND RAIN - Should the ALT 2 FAIL annunciator illuminate in flight

	The left windscreen will not be heated.
	Both windscreens will be heated.
	Neither windscreen will be heated.
	The right windscreen will not be heated.

ICE AND RAIN - The engine anti-icing system is DC powered from bus bar _____

	PS1
	XE
	PE
	PS2

LANDING GEAR AND BRAKES - The main gear outer doors are

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

LIMITATIONS - The maximum speed (Vmo) at 13,000 feet with auxiliary tanks empty is

	320 KIAS
	334 KIAS
	320 KIAS up to 12,000 feet less 1 knot per 600 feet to 292 KIAS up to 29,200 feet.
	300 KIAS up to 12,000 feet less 1 knot per 600 feet to 292 KIAS up to 29,200 feet.

LIMITATIONS - The maximum tailwind component for takeoff is

	15 Knots.
	20 Knots.
	10 Knots.
	25 Knots.

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

	The batteries are not charging.
	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.

MASTER WARNING - The red glareshield MWS annunciators will illuminate flashing if an amber annunciator illuminates

	True
	False

POWERPLANT - Selecting the ENG A/ICE switches to ON also selects continuous ignition

	False
	True

POWERPLANT - During a ground start of an engine, electrical power for oil pressure indication is from the

	Pe2 bus.
	AC power system.
	PS1 bus
	PE bus.

PRESSURIZATION SYSTEM - The function of the _____________ is to relieve excessive cabin pressure should normal system control fail.

	Outflow/Safety valve.
	Ram air valve
	Pressure regulator.
	Pneumatic Relay.

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

	The indicated MAIN AIR VALVE is not in the selected position(15 second delay early aircraft, or 50 second delay later aircraft) or is open with the aircraft on the ground.
	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.