CITATION 550/551 SYSTEMS TEST

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ELECTRICAL-While observing the VOLTMETER, to check the voltage on the right generator you should

	Assure right generator is ON and select VOLTAGE SEL to RH GEN
	Switch the right generator to OFF and select the VOLTAGE SEL to RH GEN
	Switch the left generator to OFF and read battery voltage
	Switch the left generator to OFF and select the VOLTAGE SEL to RH GEN

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

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

ELECTRICAL-Which of the following statements are true regarding a generator-assist start.

	It is necessary to observe a drop in amperage to below 300 before activating the second start button.
	A maximum of 49 % turbine RPM is set on the operating engine.
	The operating generators switch must be placed to OFF before the start button is activated.
	The operating engine turbine RPM must be stabilized at 49 to 50 % before the remaining start button is activated .

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

	False
	True

ELECTRICAL-The left or right generator field relay is opened by

	An overvoltage
	An internal feeder fault
	Activating the engine fire switch
	Any of the above

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

	55 minutes
	30 minutes
	1 hour
	25 minutes

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

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

ELECTRICAL-To assure both start relays have opened after a generator assisted start you should

	Check that STARTER DISENGAGE button is not illuminated.
	Check that LH START and RH START buttons are not illuminated.
	Observe equal loads on ammeters.
	Select battery switch to EMER and observe voltage drop to battery voltage.

FIRE PROTECTION-The ENG FIRE switchlight illuminates when

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

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.
	Residue in the engine inlet.
	Gauge on the fire bottle.
	Annunciator light in the cockpit.

FLIGHT CONTROLS-Regarding the elevator trim system

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

FLIGHT CONTROLS-With the battery as the only source of power and the battery switch in EMER position

	The flaps are operable.
	The flaps can be lowered only.
	The flap selector handle cannot by moved.
	The flaps are inoperable.

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

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

HYDRAULIC POWER-The Citation hydraulic system is classified as a pressure demand system.

	True
	False

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

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

ICE and RAIN-Switching on both engine anti-ice systems in flight will increase the reading on each ammeter by

	5 amps
	150 amps
	10 amps
	20 amps

LANDING GEAR-Concerning landing gear auxiliary extension, the correct statement is

	After the gear is extended using this procedure, it should be cycled in flight if hydraulic pressure is restored, to release trapped air.
	The optimum speed for this procedure is 150 KIAS.
	If three green lights are observed after yawing the airplane, it is not necessary to use the pneumatic bottle.
	The landing gear handle is placed in the down position to position the door shuttle valves.

LANDING GEAR-The gear warning horn cannot be silenced when one or more gears are not locked down and

	Airspeed is less than 150 KIAS
	Either throttle is retarded below 70% turbine RPM.
	Both throttles are retarded below 70% turbine RPM.
	Flaps are extended beyond 15 degree position

MASTER WARNING-With the battery as the only source of power, the annunciators are operative when the battery switch is in the EMER position

	False
	True

POWERPLANT-Ignition during normal engine start is activated by

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

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

	10
	-40
	0
	-50

PRESSURIZATION-If the main vacuum source to the pressurization controller is lost, the cabin pressure differential will

	Be controlled by the altitude limit valves.
	Go to maximum differential allowed by the outflow valves.
	cause the oxygen mask to drop (if armed).
	Decrease to zero

PRESSURIZATION-The tail cone is pressurized by ram air to

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

LIMITATIONS-The maximum tire groundspeed is

	200 MPH
	150 Knots
	165 MPH
	165 Knots

LIMITATIONS-The maximum allowable water/slush on runway for take-off and landing is

	0.5 inch
	0.4 inch
	1 inch
	0.7 inch