CITATION 500/501 SYSTEMS TEST

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ELECTRICAL-On UNs 274 and below, which of the following statements are true?

	Illumination of the RAD AC PWR FAIL annunciator will trigger the MWS flasher.
	The No 1 inverter normally powers the radar AC bus.
	Illumination of the F/D AC PWR FAIL annunciator will trigger the MWS flasher.
	The No 2 inverter normally powers the flight director AC bus.

ELECTRICAL-On UNs 274 and below, the battery is disconnected during an EPU (external power unit) start

	True.
	False.

ELECTRICAL-The STARTER DISENGAGE button when illuminated, indicates that

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

ELECTRICAL-With an external power unit on line, the battery will receive a charge when?

	All of the answers are correct.
	The battery switch is in the OFF position.
	The battery switch is in the BATT position.
	The battery switch is in the EMER position.

ELECTRICAL-What conditions of the electrical system will trigger the MASTER WARNING flasher?

	(C) LH GEN fail and RH GEN fail lights.
	(B) LH GEN fail or RH GEN fail.
	(A) The Annunciator test switch not in the OFF position.
	A and C.

ELECTRICAL-The standard battery is a/

	28 volt Nickel Cadmium.
	40 ampere-hour lead acid.
	24 volt Nickel Cadmium.
	gel cell hydroxide.

FLIGHT CONTROLS-The speedbrakes are held in the extended position by

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

FLIGHT CONTROLS-The trim tab position indicators are inoperative with the battery switch in the EMER position.

	False
	True

FLIGHT CONTROLS-Which statement is true regarding the rudder, elevator and aileron trim tabs

	There are two aileron trim tabs.
	The rudder tab is a servo tab.
	All have electrical tab position indicators.
	All are electrically and mechanically actuated.

FUEL SYSTEM-With the respective fuel boost inoperative

	All of the answers are correct.
	The engine will not start.
	The engine will flameout if the primary ejector pump becomes clogged.
	The engine will flameout if running.

HYDRAULIC POWER-The Citation hydraulic system is classified as a

	None of the answers are correct.
	Constant pressure system
	Pressure demand system.
	Open center system.

HYDRAULIC POWER-The hydraulic reservoir is pressurized by

	By an accumulator.
	Engine bleed air.
	By ram air while airborne.
	By the hydraulic system when the system is pressurized and by a spring when the system is not pressurized.

ICE and RAIN-If the W/S AIR O'HEAT annunciator illuminates with the W/S BLEED switch in the ON position.

	All of the answers are correct
	The Windshield bleed air solenoid valve has been energized closed due to a bleed air temperature of above 146 degrees C.
	The WINDSHIELD BLEED AIR valves should be partially closed to reduce air flow.
	The light will extinguish when the temperate drops.

ICE and RAIN-Which is the correct statement concerning the surface DE-ICE system

	(B) It should not be activated if OAT is suspected to be below -40 degrees C.
	(A) It should be activated prior to entering icing conditions.
	(D) Both B and C
	(C) Should not be activated until ice accumulation reaches 1/2 inch.

ICE and RAIN-If the W/S AIR O'HEAT annunciator illuminates with the W/S BLEED switch in the OFF position.

	There is an overtemperature in the duct.
	You should open a manual WINDSHIELD BLEED AIR valve.
	It is an annunciator malfunction.
	The pressure in the duct has exceeded 5 psi, indicating a partially opened or leaking Windshield bleed air solenoid valve.

ICE and RAIN-Regarding the P/S HTR OFF light

	All of the answers are correct
	It will illuminate if the PITOT&STATIC switch is OFF.
	If power is lost to both the static ports on the pilots system, the light will illuminate.
	Illumination of the light could indicate loss of electrical power to one of the pitot tubes.

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

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

LANDING GEAR-Prior to towing

	The downlock pins must be inserted in the landing gear.
	The control lock must be engaged.
	The control lock must be disengaged.
	The downlock pin must be in the nose gear only.

LANDING GEAR-At retraction, if the nose gear does not lock up, the indication on the gear panel will be

	Red light on, green LH and RH lights on.
	Red light out, green LH and RH lights on.
	All four lights out.
	Red light on, all three green lights out.

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

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

POWERPLANT-The ENGINE SYNC switch should be on for takeoff

	True
	False

POWERPLANT-The ENGINE SYNC switch should be OFF for

	All of the answers are correct
	Power changes
	Takeoff
	Landing

LIMITATIONS-The Maximum speed for autopilot operation is

	Vmo\Mmo
	110 KIAS
	.60 Mach
	No Limit

LIMITATIONS-The Maximum altitude for take-off and landing is

	10,000 ft
	14,000 ft
	9,000 ft
	No Limit

LIMITATIONS-For take-off and landing, the maximum water/Slush on runway is

	0.25 inch
	0.75 inch
	0.50 inch
	1.0 inch