CESSNA CITATION SERIE 500-550-560

Illumination of the HYD PRESS ON light indicates: The open center bypass valve has energized closed. Fluid is circulating between the hydraulic pumps and the reservoir at approximately 60 psi. Hydraulic pressure is available to the aircraft brake system. The hydraulic reservoir is pressurized at 2.7 to 4.0 psi.

Leakage around hydraulic fittings and nuts that have static seals can be: Corrected by light tapping on the affected part. Corrected by increasing the torque to 50% above specified limit. Corrected by applying correct torque and/or replacing the seal. Acceptable as long as the leak does not exceed one drop per minute or one drop in five complete cycles.

Before adding fluid to the hydraulic reservoir, verify that the: Speed brakes and flaps are retracted. Landing gear is extended. Thrust reverses are stowed. All of the above.

The hydraulic fluid used to service the 560 aircraft is: Mineral based. Phosphate ester based. Compatible to Mil-H-5606. Designed to be used as a leak detector in the aircraft fuel system.

When servicing the hydraulic system, after installing a new hydraulic open center bypass valve, you should: Not operate the hydraulic system because the system is self-bleeding. Cycle fluid through the system two to five minutes to bleed air from the system. Pump the brake pedals twelve times with the battery switch in BATT. Inspect and clean the hydraulic return and pressure filters.

If the green ignition light does not illuminate during start, a probable cause would be: The engine anti-ice circuit breaker is pulled. An igniter not operating. An igniter not operating. A blown 5 amp fuse.

If an overspeed of N2 occurs it will be indicated by: (Units 0001-0259). The MASTER WARNING lights flashing. Loss of N2 indication. A red light under the digital display illuminating and a flashing digital display. The engine shutting down; caused by the automatic fuel shutoff valve.

On engine start, ITT increased to 750º C for one second. Corrective action would be: (JT15D engines). Perform an HIS prior to the next flight. Engine overhaul must be accomplished prior to the next flight. Drain and flush the oil system because of possible coking. Unnecessary.

With the thrust reverser emergency stow switch in EMER, what light (s) will be illuminated?. ARM. HYD PRESS ON and ARM. ARM and LOCKED. ARM, UNLOCKED and MASTER WARNING.

The fuel oil heat exchanger maintains oil temperature to a maximum of: (Units 0539 and on). 132.2° C. 500° C. 113° F. 250° F.

During engine operation, the motive flow valve will: Not operate in crossfeed. Energize close. Stop fuel flow to the ejector pump. Allow fuel flow to the ejector pump.

The solenoid on the bleed valve actuator: (JT15D engines). Acts as a fuel shutoff valve to shut the engine down. Controls high pressure pneumatic to control the bleed valve. Controls high pressure fuel to control the bleed valve. Meters fuel from the engine fuel pump to the FCU.

Leaks of Pc air to the FCU will cause: Slow acceleration to idle speed. Incorrect idle speed. The engine to fail to accelerate form idle speed. All of the above.

The automatic fuel shutoff valve actuates when: Maximum N1 is exceeded. Maximum N2 is exceeded. The inner shaft rearward. The high turbine shaft shifts rearward.

If the oil filter becomes clogged, bypass will occur causing: The oil pressure relief valve to increase oil pressure. The OIL PRESS WARN light to illuminate. The OIL FLTR BY PASS light to illuminate. Unfiltered oil to pass through to the engine.

Instrument lights are powered by: 40-60 VAD inverters. 28 VED form the R/H main DC bus. 5 volt inverters. 26 VAC from the AC inverters.

The engine instrument floodlight located on the fire tray, illuminates full bright during engine start; what is the power source for this light during start?. The standby gyro battery pack located in the nose avionics bay. The emergency battery pack located in the cockpit overhead. The nickel-cadmium battery pack located in the tailcone. The nickel-cadmium battery pack located in the nose baggage compartment.

The emergency battery pack located in the cockpit overhead contains ni-cad batteries. How are these batteries recharged?. The batteries are recharged by the DC electrical system. The batteries cannot be recharged, they must be replaced every 12 months. The batteries must be removed, charged and reinstalled every 90 days. These batteries are connected to the AC inverter circuit 26 VAC bus.

Electroluminescent panels are powered by: 5 Volt inverters located in the “J” box on the forward pressure bulkhead. AC inverters in the tailcone. 28 VDC from the emergency bus. A 40-60 VAC inverter in the nose.

Where are the control switches for the map lights found?. Pilot’s instrument panel at the lower edge. Below the toggle switch on the throttle quadrant. Forward side of the left and right side consoles. Above rheostat on the pilot’s instrument panel.

If DIM is selected with the indirect lighting switch, what will be the results when the lights first illuminate?. The indirect lights must be selected to the BRIGHT position for 5 minutes before DIM is selected. The lights initially go bright; after 5 seconds will dim. The lights will illuminate dim. The lights will not illuminate if DIM is selected.

The main entrance door and emergency exit lights are controlled by a: Switch at the cabin entrance door. 5 G microswitch at the emergency battery in the cockpit overhead. Passenger advisory switch on the left panel in the cockpit. All of the above.

What is the purpose of the wing inspection lights?. For visual inspection of the wing leading edge for ice accumulation. Visual inspection of the wheel well area. Illuminates the wing trailing edge for damage inspection. Illuminates lower surface of wing to check for gear down and locked.

Using the wiring diagram of the recognition light circuitry on page 33-30, figure 33-23, answer the following question. With the recognition light switch On, the right recognition light will not operate, but the left recognition light will. A probable cause could be?. CB 261 is popped. Loss of ground on the recognition switch. K93 not operating. K90 not operating.

The tail flood lights are controlled by the: Navigational light switch. Recognition light switch. Beacon/BCN/TL light switch. Landing light switches.

Cockpit indications of a fire in the left engine nacelle are: The MASTER WARNING light flashes and the fire bell rings. The LH ENG FIRE warning light illuminates, the MASTER WARNING light flashes and the optional fire bell rings for approximately two seconds. Both ENG FIRE warning lights illuminate and the optional fire bell rings for two seconds. Only the LH ENG FIRE warning light will illuminate and the optional fire bell rings for approximately two seconds.

Depressing the LH ENG FIRE warning indicator light will: Illuminate the Bottle 1 and Bottle 2 ARMED lights on the fire tray. Close the left hydraulic and left firewall shutoff valves. De-energize the LH starter generator. All of the above.

Minimum allowable pressure for an engine fire bottle at a temperature of 70ºF is: 575 PSI. 540 PSI. 610 PSI. 500 PSI.

When performing a fire extinguishing system functional check, you should: Disconnect one explosive cartridge at a time to ensure the fire bottle is reconnected correctly. Advance the rotary test switch to the fire warning position. This will disable the explosive cartridges and a continuity check can be done without disconnecting any wires at eh fire bottles. Disconnect all four explosive cartridges to avoid accidental firing of the fire bottles. Disconnect wiring to both cartridges on Bottle 1 and perform a continuity check, then reconnect and repeat this procedure for bottle 2.

If the fire loop is not properly grounded, the detect system will: Not test and not detect. Test properly, but will not detect. Not test, but could possible detect. Work normally, because the fire loop does not require a ground.

Using a volt ohm meter, you check from pin 5 of the fire detect control connector to ground, you should read: 28.5 volts. 47 ohms. 100 ohms. An open circuit.

The fire loop is a temperature sensitive element, constructed in such a way that when the temperature increases the resistance in the fire loop decreases. When the temperature reaches 500ºF, the resistance in the fire loop is approximately: 200 Ohms. 47 ohms. 100 ohms. 0 ohms and a fire warning light will illuminate inn the cockpit.

The pilot reports that the BLD AIR GND annunciator light went out as he increased the throttles past 70% N2 and the aircraft’s ACM shut off. To correct this condition, you should replace the left gear squat switch. To correct this condition, you should replace the right gear squat switch. No action need be taken, since this is normal operation of the Hamilton Standard ACM when the source selector is selected to the NORMAL position. No action need be taken, since this is normal operation of the Hamilton Standard ACM when the source selector is selected to the GND position.

During the engine run-up, the maintenance technician placed the pressure source selector in the EMER position. The EMERG PRESS ON annunciator light illuminated and the cabin began to pressurize. This condition is normal and no action is required. Replaced of the left hand gear squat switch is necessary. Apparently there is no electrical power to the emergency pressurization valve and it has “failed” open. Either answer B or C could be correct.

With the pressure source selector placed in the NORMAL position and only the right engine running: Both left and right flow control valves are energized open. The right flow control valve is energized open both the left flow control valve will be closed regardless of the source selector position. The left flow control valve will remain closed because the valve requires 7-10 psi of air to open. Answers B and C are correct.

The 23 +/- 1 pressure regulator regulates pressure to the: (Units 001-538). Pneumatic de-ice boots. Cabin door seal. RH and LH temperature control valves. All of the above.

Bleed air temp control on the Citation Encore is accomplished by: Ram air in the pylon across the precooler. Ram air in the nacelle across a heat exchanger. Bypass air from the engine across a precooler. Bypass air flow from the engine across a nacelle heat exchanger.

With the pressure source selector in the GND position, an the right engine running: Both flow control valves are energized open. The ground valve is de-energized open. The ACM is receiving 9 PPMF from the ground valve. The ground valve is motored open.

Opening the cockpit footwarmer outlet valve will also: Close the W/S bleed air control valve. Open the side window defog valve. Open the W/S defog valve. Increase the volume of air for windshield defog.

The pilot reported that with the pressure source selector in the GND position and with both engines running that when the RH throttle is advanced to 75% N2, the BLD AIR GND annunciator light extinguished: The 38 psi pressure switch caused the ground shutoff valve to motor closed. The ground valve is a solenoid operated valve and fails closed, causing the BLD AIR GND light to extinguish. In this configuration, further advancement of the throttle to 85% N2 or above, will cause the 42 psi switch to open the emergency pressurization valve. This is normal operation. The 38 psi switch causes the ground valve to close and because the throttles are at 75% N2 or above, will cause the 42 psi switch to open the emergency pressurization valve.

The 42 psi pressure switch located downstream of the ground valve: Causes the solenoid operated ground valve to open and dump air overboard when pressure is above 42 psi. Causes the motor operated ground valve to open and dump air overboard when pressure is above 42 psi. Will only operate in flight. Will cause the ground valve to close and the ACM O´PRESS light to illuminate.

In a Citation 560, if the bleed air temperature between the ACM`s compressor and the turbine reaches 450º F, which of the following lights will illuminate?. ACM O`PRESS. EMERG PRESS ON. ACM O`HEAT. None of the above.

The bypass mixing valve on the Hamilton Standard ACM: Mixes hot conditioned air with cool ram air for temperature control. Is plumbed to the emergency pressurization system to mix conditioned cabin air with hot bleed air whenever the emergency pressurization valve is open. Mixes hot bleed air with conditioned air form the ACM. Does not operate in the manual temperature position.

The 315ºF switch located near the water separator will cause the: ACM O`HEAT light to illuminate and the ACM to shutdown. AIR DUCT O`HEAT light to illuminate, both flow control valves to close and the emergency pressurization valve to open. ACM O`HEAT light to illuminate and automatically close they bypass mixing valve. AIR DUCT O`HEAT light to illuminate.

The Citation 560 incorporates a 410 º F switch at the ACM. The purpose for this switch is to: Send a signal to the cabin temperatures controller preventing an ACM overheat condition. Open the bypass valve to add cool ram air to the conditioned air. Illuminate the AIR DUCT O`HEAT light. Close both flow control valves and open the emergency pressurization valves due to an ACM overheat.

The coalescer sock in the water separator of the Hamilton Standard ACM is to be: Replaced every phase 5 inspection. Installed with the smooth side inward. Installed with the NAP (FURRY) side inward. Answers A and B are correct.

Which of the following components prevents the information of ice in the water separator on a Hamilton Standard ACM?. The supply duct temperature sensor and controller. The low limit sensor. The bleed air ejector nozzle. The primary and secondary heat exchangers.

With the pressure source selector in the OFF position, the aircraft climbs from sea level to 10,000 ft.; pressure in the cabin will: Increase. Remain unchanged. Decrease. Cause the cabin altitude limiters to close the outflow valves so the cabin will pressurize.

What component(s) will influence the outflow valves to maintain normal cabin pressurization operation? (Units 0001-0538). Controller. Pneumatic relay. Vacuum jet pump and regulator. All of the above.

Maximum differential pressure will be controlled by: The outflow valves when the cabin altitude is greater than atmospheric altitude. By the cabin altitude limit controller when the cabin altitude reaches 13,000 +/- 1,500 ft. The outflow valves at a preset pint when cabin pressure is lower the atmospheric pressure. The outflow valves at a preset pint when cabin pressure is greater than atmospheric pressure.

In the cabin pressurization system, which solenoid(s) will be open with the aircraft on the ground and both throttles below 85% N2? (Units 0001- 0538). Solenoid A. Solenoid B. Solenoid C. All three solenoids will be open.