Primary Systems 2

Which of the following are correct major components of the electrical system?

Starter/generator, 24 VDC auxiliary battery

3 multiple choice options

True/False: The aircraft electrical system includes a 28 VDC 300 amp starter/generator, 24 VDC lead acid battery, 24 VDC auxiliary battery, and an external power receptacle

True

1 multiple choice option

True/False: The aircraft electrical system includes a 28 VDC 300 amp starter/generator, 28 VDC battery, 28 VDC auxiliary battery, and an external power receptacle

False

1 multiple choice option

The primary aircraft electrical power is powered by the ________

Generator

3 multiple choice options

The generator output provides ________ VDC, and is capable of supplying __________ amps

28; 300

3 multiple choice options

The starter/generator is regulated and monitored by a _________ located under a panel in the aft cockpit

Generator Control Unit

3 multiple choice options

Generator power is controlled by the ________ switch located on the right forward switch panel in each cockpit

Generator control (GEN)

3 multiple choice options

When the occupant of either cockpit moves the generator control switch to ON, the switch in the other cockpit (if already selected ON) _________

is tripped to the off position

3 multiple choice options

The ability to control the generator control switch is:________

transferable between cockpits

3 multiple choice options

Under normal operating conditions, aircraft electrical power is distributed across the ________ and the __________

generator bus; battery bus

3 multiple choice options

The BUS TIE switch on the right forward switch panel in the front cockpit is used to _______

tie the battery bus and generator bus together for normal operations

3 multiple choice options

Circuit breakers labeled FWD AVI and AFT AVI control front and rear avionics buses and are located on front cockpit ______

battery bus and generator bus circuit panels

3 multiple choice options

The battery powers select aircraft systems if the generator is not available, and provides power for _______

engine starts

3 multiple choice options

The aircraft battery is rated to provide _______ VDC

24

3 multiple choice options

The _______ switch must be set to ON for external power to be available to the aircraft

battery

3 multiple choice options

External aircraft lighting for the aircraft is controlled by four individual switches which are the _________ switches located on the trim control panel in the front cockpit

LDG, TAXI, ANTI-COLL, and NAV

3 multiple choice options

The landing light will come on _______

only when the LDG switch is on and the landing gear are down and locked

3 multiple choice options

True/False: Knee board lights mounted on the front of each forward and aft glareshield, intensity for these lights are controlled by the FLOOD light rheostat on the trim control panel in each cockpit

False

1 multiple choice option

When using the primary T-6B refueling method, the aircraft fuel system provides approximately _________ of usable fuel (JP-8)

1100 pounds

3 multiple choice options

When using the primary refueling method, the maximum fuel quantity for one wing tank is ________

530 pounds

3 multiple choice options

True/False: The aircraft can hold a maximum of 1200 pounds of usable fuel (JP-8) stored between the left and right wing tanks as well as a collector tank.

True

1 multiple choice option

What is the primary method of refueling for the aircraft

Single point pressure refueling

3 multiple choice options

Which method of refueling allows the wing tanks to be filled simultaneously?

Single point pressure refueling

3 multiple choice options

True/False: The collector tank normally remains full since most flights will not use the total volume of fuel. However, during ground refueling operations, if it is depleted; fuel will gravity feed to the collector tank from the wing tanks.

True

1 multiple choice option

The ___________ provides fuel for initial engine start and acts as a backup to the engine-driven low pressure fuel pump

Electric boost pump

3 multiple choice options

Fuel is directed to the collector tank from each wing tank by _________, keeping the collector tank pressurized

two transfer jet pumps

3 multiple choice options

Fuel is directed from the collector tank to engine driven low pressure fuel pump by _________

primary jet pump

3 multiple choice options

True/False: The fuel is pumped through the engine feed line to the fuel filter, which prevents contaminants from reaching the main fuel pumps or engine. If the filter becomes restricted the engine will flame out due to fuel starvation.

False

1 multiple choice option

During operation of the fuel system, fuel routed from the engine-driven low pressure pump down the motive flow line is used to drive the ________ and ________

primary jet pump; transfer jet pumps

3 multiple choice options

A pressure switch in the motive flow line activates the ________ anytime fuel pressure drops below 10psi.

electric boost pump

3 multiple choice options

The fuel gauging system uses seven fuel probes inside the fuel tanks to __________

send a signal to the engine indicating and Crew Alerting System (EICAS) for visual display of fuel quantity

3 multiple choice options

The left and right fuel quantity tanks on the EICAS turn yellow when indicated fuel quantity is the respective tank is below________

150 pounds

3 multiple choice options

True/False: The fuel low level sensors light the "L FUEL LO" or "R FUEL LO" messages on the EICAS when the fuel level falls below 150 pounds in the respective tank.

False

1 multiple choice option

Display of the FUEL BAL message may indicate an imbalance exceeding _________ pounds for more than two minutes between the left and right fuel tanks, or a failure of the autobalance system

30

3 multiple choice options

the fuel system incorporates an auto balance system which maintains the fuel load in each wing tank to within ______ pounds of the other wing

20

3 multiple choice options

The fuel balance switch has two positions; _________ or ___________ and is located ______

MAN/RESET or AUTO; right front side in forward cockpit

3 multiple choice options

True/False: Wing tanks are vented to the atmosphere as well as each other through vent lines which provide vacuum and pressure relief for the tanks

True

1 multiple choice option

If a fuel imbalance is detected by the _______ of 20 pounds or more for more than 30 seconds, the appropriate transfer (solenoid) valve is activated to close the motive flow line to the lighter tank

Engine Data Manager (EDM)

3 multiple choice options

If the auto balance system shuts off without reducing fuel imbalance to 30 pounds or less, the auto balance system may be reset to provide an additional ________ to balance the fuel load

2 minutes

3 multiple choice options

What three elements are necessary for engine operations?

Air, fuel, and heat

3 multiple choice options

The engine cowling performs all of the following functions except _________

secure engine to aircraft airframe

3 multiple choice options

What are the two major components of the propulsion system?

Engine and propeller

3 multiple choice options

What are the three sections of the engine?

Accessory compartment, gas generation section, and power turbine section

3 multiple choice options

After combustion occurs in the combustion chamber, the expanding gases_________

drive the compressor turbine, then the power turbine

3 multiple choice options

The aircraft is equipped with a free turbine, reverse flow design turboprop engine, what is meant by the term "free turbine"?

Air flow from the compressor drives the power turbine, as they are not physically connected

3 multiple choice options

When starting the aircraft, the power control lever (PCL) should be ____________

pushed forward until a green ST READY message is illuminated on the EICAS display

3 multiple choice options

True/False: Friction control settings made to the front cockpit power control lever (PCL) has no effect on the rear cockpit PCL.

False

1 multiple choice option

The front cockpit power control lever (PCL) is _______ connected to the fuel management unit (FMU) by a flexible cable as well as ________ connected to the FMU by way of the power management unit (PMU)

mechanically; electrically

3 multiple choice options

The PMU performs the following functions, except:

a. maintains engine and propeller within operating limits

b. keep fuel balance within limits

c. determines available power and provides a near linear response between PCL idle and max positions

d. fine tunes the power request and sends an electronic signal to the FMU

keep fuel balance within limits

3 multiple choice options

The primary power source for the PMU comes from the ________

Permanent Magnet Alternator (PMA)

3 multiple choice options

The power management unit (PMU) ____________

keeps the engine and propeller within operating limits

3 multiple choice options

The starter/ generator ___________ until the engine starts and is able to sustain itself

turns the compressor

3 multiple choice options

True/False: Once the engine is started, and the ignition switch is in the ON position, igniters are automatically energized and de energized by the PMU.

False

1 multiple choice option

Once the engine start sequence is completed, the starter functions _________

as a 28VDC generator

3 multiple choice options

The oil system provides filtered oil to all of the following systems, except ____________

wheel brakes

3 multiple choice options

True/False: Scavenge pumps are designed to return oil from the engine bearings, reduction gears, accessory drives and propeller back to the main oil tank. This scavenged oil is first routed through an oil cooler before the oil is returned

True

1 multiple choice option

During steady state conditions, normal oil pressure should be between __________ (green area on the gauge)

90-120 psi

3 multiple choice options

With a loss of oil pressure to the pitch change mechanism, the __________ and ___________ move the propeller to feather

counterweights; feathering spring

3 multiple choice options

Which propeller position will the propeller be in during most flight conditions?

High propeller pitch

3 multiple choice options

The ________ and the ___________ control propeller speed to maintain a constant propeller speed of 2000RPM and achieve varying levels of thrust by automatically adjusting propeller pitch

PMU; propeller interface unit

3 multiple choice options

The engine data manager performs all of the following, except ____________

monitors and processes AOA data

3 multiple choice options

True/False: All of the functions performed by the engine data manager (EDM) are engine related

False

1 multiple choice option

The engine data manager (EDM) also performs non-engine related functions such as _____________

All of the above

3 multiple choice options

The engine indication and crew alerting display provides _________ with a visual indication of _________

each cockpit; engine and auxiliary instrument information

3 multiple choice options

The engine and crew alerting system (EICAS) ___________

provides each cockpit with a visual indication of engine operations

3 multiple choice options

On the engine indication and crew alerting system (EICAS) display, △P measures _____________

the difference between cockpit pressure and outside pressure

3 multiple choice options

The middle column of the engine indication and crew alerting system (EICAS) display contains what information?

All of the above

3 multiple choice options

The right side (column) of the engine indication and crew alerting system (EICAS) display contains all the following information, EXCEPT ___________

fuel flow

3 multiple choice options

The left side (column) of the engine indication and crew alerting system (EICAS) display contains what information?

Fuel quality, Bingo, fuel flow, indicated outside air temperature, current amperage draw, bus voltage, cockpit altitude, and differential pressure

3 multiple choice options

In the event of an out of limits torque indication, the EICAS display will warn the pilot by all of the following methods, EXCEPT

flashing MASTER CAUT switchlight

3 multiple choice options

True/False: Pressing the MASTER WARN or MASTER CAUT switchlight in either cockpit extinguishes the lamp and re-arms the mechanism for additional malfunctions or failures, Acknowledge advisories remain on steady on the CAS display until the malfunction or failure is corrected

True

1 multiple choice option

The bottom portion of the engine indication and crew alerting system (EICAS) serves as the crew alerting system (CAS). This panel is reserved for ___________

warnings, cautions, status and condition advisories

3 multiple choice options

The engine fire warning system monitors ____________

average and discrete engine exterior temperatures

3 multiple choice options

True/False: The aircraft is equipped with a fire warning system. This system is designed to monitor both average and discrete temperatures exterior of the engine.

True

1 multiple choice option

True/False: The aircraft is equipped with a fire warning system. This system is designed to monitor the internal temperatures of the engine to warn of a possible engine overtemp.

False

1 multiple choice option

The engine fire warning system consists of a core element, a sensor tube, and ____________

a responder assembly

3 multiple choice options

The fire warning system consists of a core element, sensor tube, and responder assembly. The sensor tubes are built such that ___________ don't affect system reliability

kinks, twists, or dents

3 multiple choice options

If temperatures reach or exceed the preset fire warning point on the exterior of the engine, ___________

The MASTER WARN light and FIRE switch lights will illuminate

3 multiple choice options

The environmental control panel is located ____________

front cockpit right side console

3 multiple choice options

What is the only environmental control located in the rear cockpit on the engine/electrical switch panel?

Evaporator blower control switch

3 multiple choice options

Which environmental component does not require the use of engine bleed air?

Air conditioning

3 multiple choice options

The ________ controls provide power to the front and rear cockpit blowers which supply airflow through the air conditioning vents

evaporator blower

3 multiple choice options

The _________ control switch controls the position of the bi-level control and shutoff valve

bleed air inflow

3 multiple choice options

Which control switch operates the motor drive heat exchanger bypass valve?

Temperature control

3 multiple choice options

True/False: Fresh air ventilation is available for the cockpit during ground operations and unpressurized flight.

True

1 multiple choice option

Fresh air ventilation is controlled by the fresh air valve through the position of ram air flow switch, the switch is ______________

overridden and fresh air valve closes as the aircraft reaches an altitude of 8,000 feet MSL

3 multiple choice options

The front cockpit vent control lever will direct air flow to __________

defog vents, foot warmer, or both (lever in mid-range position)

3 multiple choice options

The cockpit air temperature is automatically adjusted between ___________ with the TEMP CONTROL switch set to autopilot

60 - 90 degrees F

3 multiple choice options

Engine bleed air for the cockpit heating is supplied from the __________

right side engine compressor P3 port

3 multiple choice options

Moving the TEMP CONTROL switch toward HOT causes the heat exchanger bypass valve to ________ allowing ___________ warm air to bypass the heat exchanger

open; more

3 multiple choice options

True/False: Controls for the defogging system are located in the front and rear cockpit environmental control panel and on the vent control panel.

False

1 multiple choice option

Placing the defog switch to ON opens the ___________ which causes a higher volume of bleed air to pass through the heating system ejector

bi-level flow control bypass valve

3 multiple choice options

If the bleed air temperature in the environment system ducting exceeds _______ at any time, the yellow DUCT TEMP caution message will illuminate

300 degrees F

3 multiple choice options

True/False: The air conditioning system only operates when the engine is on and functioning, generator on-line, and the AIR COND switch or DEFOG switch is place ON

True

1 multiple choice option

Which component of the air conditioning system converts the vaporized refrigerant to a high pressure liquid?

Condenser

3 multiple choice options

True/False: The AIR COND switch is available in both cockpits and is used to activate the air conditioner compressor

False

1 multiple choice option

A control valve regulator located in the aft pressure bulkhead monitors the _______ and automatically adjust the position of the ___________

cockpit pressure; control valve

3 multiple choice options

The ___________ monitors cockpit differential pressure and will send a signal to the safety valve if the cockpit differential pressure exceeds _____________

Delta P regulator; 4.0 psi

3 multiple choice options

Which component of the pressurization system automatically prevents cockpit over pressurization?

Safety valve

3 multiple choice options

True/False: Starting at 8,000 feet pressure altitude, the pressurization control valve maintains cockpit pressure at 8,000 feet until a cockpit pressure differential of 3.6 +/- 0.2 psi is reached at 18,069 feet

True

1 multiple choice option