HAWKER 800XP SYSTEMS TEST

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

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

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

	True
	False

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

ELECTRICAL-If during external charging, the batteries become isolated due to abnormal ground power supply voltage

	Charging will resume if and when the voltage drops to a safe level.
	The bus-tie switch must momentarily held to CLOSE after the power unit problem has been rectified before attempting to reinstate power.
	The EXTernal BATTery CHG switch must be selected to OFF then to ON.
	The EXT POWER switch must be switched to OFF then ON.

ELECTRICAL-The standby inverter is located

	The rear equipment bay.
	Behind the copilots seat.
	The forward avionics compartment.
	The forward baggage compartment.

ELECTRICAL-Under otherwise normal conditions, failure of the No 2 inverter will result in

	Standby inverter operation to power the XS2 bus.
	Loss of power on the XS2 bus.
	Illumination of the XS2 FAIL annunciator.
	A supply to the XS2 bus from INV 1.

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

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

FIRE PROTECTION-The cockpit indication of a depleted main engine fire bottle is

	The fire bell silences.
	The associated EXT 1 (or 2) FIRED indicator turns red.
	The fire warning light extinguishes.
	The gauge reads zero.

FUEL SYSTEM-A fuel anti-icing additive is required for fuel temperatures below _______.

	-32 deg F.
	-40 deg C.
	-40 deg F.
	-32 deg C.

FUEL SYSTEM-During flight including take-off and landing, the maximum allowable difference in weight between the wing tanks is ________ pounds

	Varies with gross weight.
	400
	500
	800

FUEL SYSTEM-The LP valves must be in the open position for refueling any tank.

	True
	False

FUEL SYSTEM-The Refuel panel Power Switch must be ON or the PE bus should be powered during pressure refueling.

	True
	False

HYDRAULIC-The auxiliary hydraulic pump is a

	Engine driven pump.
	Air driven pump.
	Electrically powered.
	Hand pump.

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

	True
	False

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

	(C) Bleed air
	(B) Electrically
	(D) Both B and C
	(A) Not

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

	PS1
	PS2
	PE2
	PE

LANDING GEAR and BRAKES-The green standby main gear down lights on the right console are powered by the

	PS1 bus
	PE bus
	PS2 bus
	PE2 bus

LANDING GEAR and BRAKES-The landing gear horn sounds if the gear is not locked down and

	(C) Start power is selected.
	(D) Either or both A and B.
	(B) Either or both throttles are retarded to below 60% N1 and the airspeed is below 150 +/- 3 KIAS.
	(A) The flaps are selected to the approach position or beyond.

LIMITATIONS-The maximum speed with the flaps at 25 degrees is

	210 KIAS
	220 KIAS
	160 KIAS
	175 KIAS

LIMITATIONS-The maximum tailwind component for takeoff is

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

POWER PLANT-Deployment of either thrust reverser is restricted to ground operation only

	False
	True

POWER PLANT-Electrical power for the thrust reverser system I provided by the _____ Busbar

	PE2
	PS2
	PS1
	PE

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

	XS1 and XS2 respectively.
	DC power system.
	XE bus
	An additional inverter if the normal AC power system is not available.

POWERPLANT-The planetary gear performs one of the following functions

	Maintains a 1.8 to 1 ratio between the FAN and the LP compressor.
	Maintains the LP compressor to fan rpm ratio.
	Maintains the HP compressor to LP compressor rpm ratio.
	Drives the airplane and engine accessories.

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

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