CITATION 550/551 SYSTEMS TEST

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AIR-CONDITIONING-In otherwise normal conditions and no action has been taken by the crew the EMER PRESS ON annunciator illuminates

	If on the ground the air to the ACM will be shutoff.
	All of the answers are correct.
	If in the air, the cabin pressurization source will be emergency pressurization and the ACM has shutdown.
	The ACM has overheated.

AIR-CONDITIONING-The AIR DUCT O'HEAT annunciator light illuminates when the

	Temperate of the air in the duct to the cabin is excessive.
	EMER source is selected.
	Aircycle machine shuts down.
	Temperate of the air going to the windshield is excessive.

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

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

ELECTRICAL-The hot battery bus is the power source for which of the following?

	Emergency battery pack
	All of the answers are correct
	Ignition (start only)
	Emergency exit floodlights

ELECTRICAL-With the battery switch selected to EMER a good battery should supply power to the hot battery and emergency for approximately

	30 minutes
	1 hour
	55 minutes
	25 minutes

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

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

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

	(C) The second engine started will be a generator assisted start.
	(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.

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

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

FLIGHT CONTROLS-Regarding the elevator trim system

	(A) The elevator trim tab may be actuated either manually or electrically.
	(C) The trim tab position indicator is unreliable without AC power.
	(B) Runaway electric trim may be alleviated by holding the manual trim wheel until the circuit breaker opens.
	(D) Both A and B.

FLIGHT CONTROLS-The flaps are hydraulically operated

	True
	False

FUEL SYSTEM-If fuel crossfeed has been selected and normal DC electrical power is lost

	(A) The crossfeed valves will fail closed.
	(C) The motive flow valve will fail open.
	(D) Both A and C.
	(B) The boost pumps will be energized.

FUEL SYSTEM-After engine start, the fuel boost pump is deenergized by the

	A time delay relay
	Fuel boost pump switch.
	Discontinuing crossfeed.
	Start circuit termination.

HYDRAULIC POWER-Hydraulic reservoir fluid level below 0.2 gallon is indicated by illumination of the

	HYD PRESS ON annunciator.
	Dolls eye on the reservoir.
	HYD LEVEL LO annunciator.
	L or R HYD PRESS LO annunciator

HYDRAULIC POWER-While the hydraulic system is not under pressure, the hydraulic reservoir is pressurized to

	By engine bleed air.
	2.7-4 PSI by an internal spring.
	Nonel of the answers are correct.
	4-6 PSI by an internal spring.

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

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

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

	(C) The WINDSHIELD BLEED AIR valves should be partially closed to reduce air flow.
	(D) Both B and C.
	(A) The pressure in the duct has exceeded 5 psi, indicating a partially opened or leaking Windshield bleed air solenoid valve.
	(B) The Windshield bleed air solenoid valve has been energized closed due to a bleed air temperature of above 146 degrees C.

LANDING GEAR-Prior to towing

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

LANDING GEAR-The landing gear downlocks are disengaged by

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

MASTER WARNING-An annunciator light when illuminated, will extinguish when

	The rotary test switch is reset to OFF.
	The annunciator is depressed.
	The Master Warning Switchlight is depressed.
	The fault is corrected.

POWERPLANT-The N1 tape will supply a reliable indication above 50% when electrical power is lost

	False
	True

POWERPLANT-Ignition during normal engine start is activated by

	Automatically when engine turbine speed reaches 10%
	Turning the ignition switches on at 8 to 10 % turbine speed.
	Depressing the start button
	Moving the throttle to idle at 8 to10 % turbine speed

LIMITATIONS-Mmo above Vmo altitude is

	.750 Mach
	.705 Mach
	277 KIAS
	.805 Mach

LIMITATIONS-The maximum tire groundspeed is

	200 MPH
	165 MPH
	150 Knots
	165 Knots

LIMITATIONS-The minimum temperature for take-off and landing is

	ISA -54 degrees C
	ISA -25 degrees C
	ISA -45 degrees C
	ISA -35 degrees C

LIMITATIONS-The maximum enroute operating altitude is

	41,000 feet
	35,000 feet
	45,000 feet
	43,000 feet