CITATION V, 560 SYSTEMS TEST

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

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

ELECTRICAL-Which statement is correct, With the battery switch in the OFF position

	The emergency exit lights will illuminate
	The generators will trip off line
	The battery bus is powered
	The hot battery bus is powered

ELECTRICAL-The electrical source for the entrance door flood light is

	LH main bus
	Battery bus
	The emergency batteries
	The hot battery bus

ELECTRICAL-The left or right generator field is opened by

	selecting the generator switch to OFF
	A reverse current of (10% of total load).
	Undervoltage
	Activating the engine fire switch.

ELECTRICAL-The voltage read on the voltmeter with the VOLTAGE SEL switch in BATT is sensed from the

	Hot battery bus
	Battery bus
	Emergency bus
	Left or right main bus

ELECTRICAL-For a generator assisted start

	(A) The first engine started will be a battery start.
	(B) Both engine starts will be generator assisted.
	(D) Both A and C.
	(C) Both generator switches should be in the GEN position.

ELECTRICAL-The voltmeter is inoperative when the battery switch is

	(A) In the EMER position.
	(D) Both A and B.
	(C) In the BATT position.
	(B) In the OFF position.

FIRE PROTECTION-During preflight, the indication that a fire extinguisher bottle has been discharged

	Blow out disc missing on the side of the tail cone.
	Gauge on the fire bottle.
	Residue in the engine inlet.
	Annunciator light in the cockpit.

FLIGHT CONTROLS-Regarding the elevator trim system

	Electric trim has both high and low speed positions
	The trim tab is controlled only electrically.
	A runaway electric trim condition can be stopped by pulling the PITCH TRIM circuit breaker.
	Trim tab is located on the left elevator only.

FLIGHT CONTROLS-The flaps are hydraulically operated

	False
	True

FUEL SYSTEM-With both fuel boost pump switches ON and the pumps activated, crossfeed will not occur.

	False
	True

FUEL SYSTEM-The transfer rate during crossfeed is approximately

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

HYDRAULIC POWER-The Citation hydraulic system is classified as an open center system

	True
	False

HYDRAULIC POWER-If the hydraulic system is lost with the speedbrakes extended.

	Pulling the HYD circuit breaker will retract the speedbrakes.
	The speedbrakes cannot be retracted.
	If airborne, the slipstream will blow the speedbrakes to trail when the switch is selected to retract.
	The speedbrakes will retract.

ICE and RAIN-Windshield bleed air will not be available if normal DC power fails

	True
	False

ICE and RAIN-In flight with both engines running, the inboard wing leading edge panels will be anti-iced with DC power loss.

	False
	True

ICE and RAIN-The engine anti-ice system should be switched on when

	(B) After take-off
	(C) Flight into visible moisture is immanent with OAT from +4 to -30 degrees C.
	(A) 1/2 inch accumulation of ice on the wing leading edge.
	(D) Both B and C.

LANDING GEAR-While actuating the emergency brakes you should

	Not apply pedal brakes as it could rupture the brake reservoir..
	Apply pedal brakes for directional control.
	None of the answers are correct.
	Pump the emergency brake handle to build up pressure.

MASTER WARNING-The Rotary Test Switch is inoperative in flight..

	False
	True

MASTER WARNING-The Master Warning Lights illuminate and flash when

	(B) An Amber annunciator illuminates.
	(A) A red annunciator, with the exception of ENG FIRE illuminates.
	(C) Both amber L and R GEN OFF annunciators illuminate.
	(D) Both A and C.

POWERPLANT-Power will automatically applied to the igniter box when the IGNITION switch is in the NORM position anytime

	(D) Both A and B.
	(B) The engine anti-ice switch is on.
	(C) The surface de-ice system is activated.
	(A) The start button is depressed and the throttle is out of idle cutoff.

POWERPLANT-If the engine power shaft shifts to the rear as much as .070 inches

	.070 is insignificant.
	The Master Warning will illuminate.
	The engine automatically shuts down.
	If associated with a vibration the engine decelerates.

PRESSURIZATION-The tail cone is pressurized by ram air to

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

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 flaps set to 15 degrees

	176 KIAS
	180KIAS
	210 KIAS
	200 KIAS