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

AIR-CONDITIONING-If the ACM overheat switch has actuated, it may reset by momentarily placing the PRESS SOURCE selector to the

	GND position.
	EMER position.
	BOTH position.
	LH or RH position.

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

	False
	True

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

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

ELECTRICAL-The STARTER DISENGAGE button when illuminated, indicates that

	A starter is engaged
	The motive flow pressure switch is defective
	A start relay did not disengage at the completion of start cycle
	The panel lights are turned on

ELECTRICAL-In flight, with both generators on line, the battery is isolated from any charging source when the battery switch is in the

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

ELECTRICAL-With an EPU (external power unit) start, with both generator switches in the GEN position

	(D) Both B and C.
	(A) The first engine started will be a battery start.
	(B) The first engine started will be a EPU start.
	(C) The second engine started will be a generator assisted start.

ELECTRICAL-When using a EPU (external power unit) the voltage and amps of the unit should be regulated to

	27.5 volts and 1200 amps
	28.5 volts and 800 to 1200 amps
	28.5 volts and 1200 amps
	28.5 volts and 800 to 1000 amps

ELECTRICAL-With the battery as the power source starter limitations are

	Three engine starts per 30 minutes. Three cycles of operation with a 30 second rest period between cycles is permitted.
	Three engine starts in one hour with a 45 second rest between starts
	Three engine starts in one hour with a 3 minute rest between starts
	Three engine starts in one hour with a 30 second rest between starts

FIRE PROTECTION-The ENG FIRE switchlight illuminates when

	An engine fire or overheat condition exists.
	The firewall shutoff valve is closed.
	It is depressed.
	The fire extinguisher is discharged.

FUEL SYSTEM-Maximum altitude for flight with aviation gasoline (Avgas) is

	18,000 feet
	35,000 feet
	41,000 feet
	15,000 feet

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

	True
	False

FUEL SYSTEM-Fuel anti-icing additive is mandatory when

	At all times.
	When ambient temperature is below freezing.
	When flight is anticipated at temperatures below ISA -20
	Flight into known icing conditions.

HYDRAULIC POWER-The wheel brake hydraulic system is pressurized by the main hydraulic system.

	True
	False

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

	True
	False

ICE and RAIN-The inboard wing leading edge panel is heated by bleed air

	False
	True

ICE and RAIN-The ENGINE ICE FAIL annunciator will illuminate when

	The cowl temperature exceeds 104 degrees C.
	The engine anti-ice switch is off.
	The inboard wing leading edge bleed air temp is low.
	The bleed air valve to the nose cone closes.

ICE and RAIN-The amber ENG ANTI-ICE light advises that

	Left and/or Right engine nacelle temperature is low.
	The temperature of the bleed air to the inboard wing leading edge panel is low.
	The stator valve is not full open.
	Any of the answers are correct.

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

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

LANDING GEAR-In flight, when the LDG GEAR handle is positioned UP or DOWN.

	The HYD PRESS ON annunciator light extinguishes.
	The hydraulic bypass valve is not affected.
	The hydraulic bypass valve is energized open.
	The hydraulic bypass valve is energized closed.

POWERPLANT-The minimum oil temp (degrees C) for starting is

	-50
	10
	0
	-40

POWERPLANT-The ENGINE SYNC switch should be OFF for

	All of the answers are correct
	Power changes
	Takeoff
	Landing

PRESSURIZATION-The emergency dump valve

	Is electrically controlled.
	Fails to the open position if electrical power is lost.
	Is intended for ground use only.
	Is manually controlled.

PRESSURIZATION-Select the correct statement(s) concerning the cabin pressurization system

	Loss of vacuum causes the cabin to go to a maximum differiential pressure of 8.9 psi.
	All of the answers are correct.
	DC power is not required for controller operation in flight.
	Cabin altitude limit valves operate at 13,000 plus or minus 1,500 feet.

LIMITATIONS-The maximum take-off weight is

	14,000
	15,100
	15,900
	16,000