CITATION V, 560 SYSTEMS TEST

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AIR-CONDITIONING-If on climb out, the EMER PRESS ON annunciator illuminates

	Select PRESS SOURCE selector to EMER.
	The ACM has overheated and shut down.
	Refer to the checklist for further action.
	All of the answers are correct.

AIR-CONDITIONING-When controlling the cabin temperature with the manual temperature switch, the mixing valve is positioned from full hot to full cold in approximately

	1 minute
	6 seconds
	30 seconds
	10 seconds

ELECTRICAL-Illumination of the AC FAIL annunciator and the MASTER WARNING lights indicates

	Both generators have failed.
	Both inverters have failed.
	Either inverter has failed.
	The AVIONIS switch is in the OFF position.

ELECTRICAL-The field relay is integral to the GCU (generator control unit).

	True
	False

ELECTRICAL-If one of the current limiters located between each main and the battery bus is blown before engine start

	(D) Both A and B
	(A) The respective engine start sequence will be inoperative.
	(C) The will be no indication if external power is used for start.
	(B) The annunciator panel will not test properly.

ELECTRICAL-On UNs 0032 and above, with both generators on line, if the battery switch is selected to OFF, the following conditions exist

	There is no change since the generators are supplying power
	The emergency bus is not powered
	The battery bus is not powered
	All DC buses are powered

ELECTRICAL-If the BATT O'TEMP annunciator illuminates on the ground (except for test), you should

	Not take-off until the proper maintenance procedures have been performed
	Switch generators to OFF
	Disregard if not flashing
	Select battery switch to EMER and proceed as normal

FIRE PROTECTION-The BOTTLE 1 ARMED or the BOTTLE 2 ARMED switchlights when illuminated, indicates that

	(C) The respective bottle is armed and its agent will be directed to side with the illuminated F/W SHUTOFF annunciator.
	(D) Both A and B.
	(A) The No 1 bottle is armed and is for the left engine.
	(B) The No 2 bottle is armed and is for the right engine.

FIRE PROTECTION-The proper pressure for the fire bottles can be determined by

	Use the adjacent chart to correct pressure gauge reading for temperature.
	Use the adjacent chart to correct pressure gauge reading for pressure altitude.
	Assuring that at least one gauge reads at least 500 psi.
	Use the formula PRESS X TEMP divided by 80

FLIGHT CONTROLS-The speedrakes are held in the retracted position by

	Trapped hydraulic pressure.
	Hydraulic system remains pressurized.
	Springs.
	Mechanical locks.

FUEL SYSTEM-If the L or R FUEL BOOST On annunciator illuminates without any action by the crew (operation normal), the probable cause is

	The fuel flow compensator has energized the boost pump.
	The firewall shutoff valve has closed.
	The engine driven fuel pump has failed.
	The low-pressure sensing switch has energized the pump.

FUEL SYSTEM-The transfer rate during crossfeed is approximately

	500 lbs per hour
	700 lbs per hour
	900 lbs per hour
	300 lbs per hour

HYDRAULIC POWER-The wheel brake hydraulic system is independent of the main hydraulic system.

	True
	False

HYDRAULIC POWER-Closing of a hydraulic firewall shutoff valve is indicated by

	Illumination of the applicable F/W SHUTOFF annunciator.
	A warning bell
	A warning horn.
	Illumination of the HYD PRESS ON annunciator.

ICE and RAIN-The windshield alcohol system quantity gage

	Is located in the LH NOSE baggage compartment.
	Is located on the copilots instrument panel.
	Is located in the RH NOSE baggage compartment.
	Is inoperative with loss of normal DC power.

ICE and RAIN-Regarding the windshield anti-ice system

	(D) Both A and C.
	(B) The LO position on the W/S BLEED switch regulates windshield temp to below 30 degrees C.
	(A) The W/S BLEED switch controls temperature (HI or LO).
	(C) The HI position on the W/S BLEED switch regulates windshield temp to below 45 degrees C.

ICE and RAIN-With the engine operating the T 1 probe is heated continuously

	True
	False

LANDING GEAR-With the control lock off, the tow limit (nose wheel deflection) should not exceed

	45 degrees left or right
	95 degrees left or right
	60 degrees left or right
	No limit

LANDING GEAR-The landing gear downlocks are disengaged by

	Hydraulic pressure being applied to the retract side of the actuators.
	Removing the external downlock pins.
	Mechanical linkage to the LDG GEAR handle.
	Action of the squat switches.

MASTER WARNING-The annunciator lights intensity is varied by the center panel lights rheostat.

	False
	True

POWERPLANT-If one igniter should fail during engine start

	The engine will not start
	The engine will start normally
	It will result in a hot start
	The ignition indicator will not be illuminated

POWERPLANT-Ignition during start is normally terminated by

	(B) Moving the throttle above IDLE.
	(A) Turning the ignition switches to OFF.
	(D) Both A and C.
	(C) Speed sensing switch on the generator.

PRESSURIZATION-The tail cone is pressurized by ram air to

	Provide air flow to the aircycle machine.
	To provide pressure to the hydraulic reservoir.
	To provide emergency pressurization if needed.
	Preclude entry of any external fluids

LIMITATIONS-Vmo 8,000 to 31,400 feet (12,200 lb. ZFW)

	276 KIAS
	272 KIAS
	282 KIAS
	250 KIAS

LIMITATIONS-The maximum speed with the landing gear extended (Vle) is

	250 KIAS
	200 KIAS
	Vmo
	Mmo