T-6 Systems 2 Elec/fuel Review

Front 1

What electrical component allows isolation of the generator and battery buses?

Back 1

Bus tie switch

Front 2

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

Back 2

generator control unit

Front 3

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

Back 3

generator control (GEN)

Front 4

The rear cockpit avionics bus receives power through the ____.

Back 4

front cockpit avionics bus

Front 5

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

Back 5

Battery bus and generator bus circut breaker panels

Front 6

A circut breaker labeled AFT BAT on the front cockpit battery bus circut breaker panel controls the ______.

Back 6

rear cockpit battery bus

Front 7

Except for the backup UHF control head and UHF transceiver, power for all avionics and radio systems in both cockpits is furnished through _____ on the right forward switch panel in the front cockpit.

Back 7

an avionics master switch

Front 8

An amber _____ light on the annunciator panel in each cockpit will indicate an open bus tie switch.

Back 8

BUS TIE

Front 9

Circut breakers protecting systems and equipment operating from the battery bus are located on the _____ in each cockpit.

Back 9

left console panel

Front 10

Each circut breaker is marked with the _____ it will allow to pass before popping.

Back 10

Maximum current load in amperes.

Front 11

Battery power is controlled through ____ on the right forward switch panel in either cockpit.

Back 11

A battery switch

Front 12

A switch labeled AUX BAT on the front cockpit left console test panel is positioned forward to test the ____ during preflight checks.

Back 12

auxiliary battery

Front 13

External power is controlled by the _____ and distributed on the _____.

Back 13

batter switch; battery bus

Front 14

True or False. Lightning for Efis displays, the RMU, the AOA indexer and the GPS control panel is adjusted using the knob labeled INSTR PANEL on the trim control panel.

Back 14

False

Front 15

______ lights ban be detached and relocated to the right canopy rail for use as an area or map light.

Back 15

Utilty

Front 16

The landing light will only come on when the landing light switch is activated and _____.

Back 16

teh landing gear is down and locked

Front 17

When switched on, white position lights at the trailing edge of each wing tip ____.

Back 17

are constantly illuminated

Front 18

Ther generator provides 28 VDC power, and is capable of supplying _____ amps.

Back 18

300

Front 19

The generator can be controlled from either cockpit throught use of the ____.

Back 19

generator control switch

Front 20

If a component of circut malfunctions, the affected ____ will open, shutting off current flow to that component or circut.

Back 20

circut breaker

Front 21

The battery can be controlled from either cockpit through use of the ____.

Back 21

battery switch

Front 22

Light output from the instruments, control panels, and displays can be adjusted by using dimming controls located on the _____ in each cockpit.

Back 22

trim control panel

Front 23

The taxi light is located aft and inboard of the _____.

Back 23

right main landing gear strut

Front 24

A fault in the circut controlling the anit-collision lights. The COLL circut breakers will pop on the battery bus circut breaker panel located on the ____.

Back 24

left side of the front cockpit

Front 25

The starter/generator provides 28 volts DC, while the battery and auxilary battery are ____ VDC units.

Back 25

24

Front 26

The motive flow system is normally driven by the electric boost pump. True or False.

Back 26

False

Front 27

When using the primary refueling method, the toatl amount of usable fuel in the tanks is approximately _____pounds.

Back 27

1100 lbs

Front 28

The collector tank holds a maximum of approximately ______ pounds of fuel.

Back 28

40

Front 29

What is the primary method of refueling T-6A?

Back 29

single point pressure refueling

Front 30

Using a single point pressure refueling method, approximately how long does it take to refuel the aircraft?

Back 30

3 to 5 minutes

Front 31

The secondary or backup method for refueling the T-6A is called _____.

Back 31

over the wing gravity refueling

Front 32

The engine-driven higher-pressure fuel pump is fed from the ____.

Back 32

engine-driven low pressure fuel pump

Front 33

The motive flow line routes fuel to which of the following pumps?

Back 33

Primary jet pump and transfer jet pumps

Front 34

The collector tank is equipped with two fuel pumps for enginge feed operations. Which one is used AFTER engine start?

Back 34

Primary jet pump

Front 35

During inverted flight, the flip-flop valve activates, providing the engine access to fuel located in the ______.

Back 35

collector tank

Front 36

True or False. Once the engine is running and motive flow has been activated, the boost pump is automatically turned off by the low pressure switch.

Back 36

True

Front 37

True or False. The wing tanks are internally vented to each other by float valves.

Back 37

False

Front 38

The fuel system incorpates an auto balance system which maintains the fuel load in each wing tank to within ____ pounds of the other wing.

Back 38

20

Front 39

Using th eprimary refueling method, the maximum fuel quantity for one wing tank is ____ lbs.

Back 39

530

Front 40

What is the aircraft limitation for inverted flight?

Back 40

15 seconds

Front 41

Which method of refueling fills the wing tanks simultanecously?

Back 41

single point pressure refueling

Front 42

Whinch of the following maintains fuel balance by shutting off fuel flow to the light wing tank?

Back 42

transfer (solenoid) valve

Front 43

The primary and transfer jet pumps are operated by ____.

Back 43

venturi flow

Front 44

How long does it take to defuel the T-6A through the over the wing gravity refueling ports?

Back 44

The T-6A cannot be defueled through the over the wing gravity refueling ports.

Front 45

Fuel is routed from the engine-driven fuel pump to the primary jet pump through which line?

Back 45

motive flow line

Front 46

The left and right fuel quantity arrows on th AEDD turn yellow when indicated fuel quantity in the respective tank is below ____.

Back 46

150 pounds

Front 47

During normal operations, while the bus tie is closed, which electrical buses does the generator supply?

Back 47

Both generator and battery buses are powered by the generator

Front 48

The GCU is located under a side panel in which cockpit?

Back 48

The GNU is under a panel on the right side of the rear cockpit.

Front 49

Generator and battery buses are tied together through which swtich?

Back 49

Bus tie switch

Front 50

Power for aircraft avionics is supplied by which bus?

Back 50

Both generator and batter buses supply power to avoinics and radios.

Front 51

Which method of refueling fills the wing tanks simultanecously?

Back 51

single point pressure refueling

Front 52

Whinch of the following maintains fuel balance by shutting off fuel flow to the light wing tank?

Back 52

transfer (solenoid) valve

Front 53

The primary and transfer jet pumps are operated by ____.

Back 53

venturi flow

Front 54

How long does it take to defuel the T-6A through the over the wing gravity refueling ports?

Back 54

The T-6A cannot be defueled through the over the wing gravity refueling ports.

Front 55

Fuel is routed from the engine-driven fuel pump to the primary jet pump through which line?

Back 55

motive flow line

Front 56

The left and right fuel quantity arrows on th AEDD turn yellow when indicated fuel quantity in the respective tank is below ____.

Back 56

150 pounds

Front 57

During normal operations, while the bus tie is closed, which electrical buses does the generator supply?

Back 57

Both generator and battery buses are powered by the generator

Front 58

The GCU is located under a side panel in which cockpit?

Back 58

The GNU is under a panel on the right side of the rear cockpit.

Front 59

Generator and battery buses are tied together through which swtich?

Back 59

Bus tie switch

Front 60

Power for aircraft avionics is supplied by which bus?

Back 60

Both generator and batter buses supply power to avoinics and radios.

Front 61

Battery bus circut breakiers are located on which side of the cockpit?

Back 61

Battery bus circut breakers are located on the left side of the cockpit

Front 62

Control of battery power is transferable between cockpits using what?

Back 62

Battery power control is transferable using the battery switch

Front 63

True or False. The auxiliary battery will activate automatically upon failure of the primary battery.

Back 63

False. It must be activated byt the auxiliary battery switch.

Front 64

The landing and taxi lights are activated by the LDG and TAXI switches when the gear is ____.

Back 64

down and locked

Front 65

The navigation lights at the leading edge wing tips are what colors?

Back 65

red at the left wingtip and green at the right wingtip

Front 66

Using single point refueling, the T-6A's maximum usable fuel is how many pounds?

Back 66

1100 pounds

Front 67

Which refueling method allows more fuelto be pumped into the wing tanks?

Back 67

Over-the-wing gravity refueling

Front 68

The primary jet pump and transfer jet pumps are operated by what means?

Back 68

The primary jet pump and transfer jet pumps are both operated by venturi flow generated by fuel flowing in the motive flow line.

Front 69

Data from the fuel flow transmitter is displayed on what instrument?

Back 69

The AEDD(Alternate Engine Data Displays)

Front 70

AEDD fuel quantity indications are derived from how many sensors in the fuel tanks?

Back 70

7

Front 71

What is indicated if the M FUEL BAL annunciator is lighted?

Back 71

The fuel balance switch on the right forward switch panel has been set to MAN/RESET

Front 72

Tru or False. The weight of fuel in the collector tank is included in the total fuel weight on th AEDD.

Back 72

True. Collector tank fuel is split between the left and right fuel quantity indications.

Front 73

Which component prevents fuel from draining from the wing tank?

Back 73

Float valve

Front 74

If tank loads are out of balance, the auto balance system stops flow to which tank?

Back 74

Motive flow is halted to the light tank.

Front 75

The FUEL BAL annunciator will illuminate if the fuel weight difference between the left and right tanks exceeds what figure for more than two minutes?

Back 75

30 pounds

Front 76

The BOOST PUMP annunciator is cycling on and off. This could be an indication of what?

Back 76

low fuel pressure

Front 77

The generator supplies what voltage to the generator and battery buses?

Back 77

28 volts DC

Front 78

The anti-collision strobe lights are located where?

Back 78

The strobe lights are located on each wingtip near the leading edge.

Front 79

External power is distributed on which bus?

Back 79

battery bus

Front 80

Gravity refueling adds how many total pounds to the T-6A normal capacity?

Back 80

100 pounds

Front 81

True or False? Single-point refueling fills all three tanks sequentially beginning with the collector tank.

Back 81

False single-[oint refueling fills the wing tanks simultaneously

Front 82

Generator bus circut breakers are located on which side of the cockpit?

Back 82

Right side

Front 83

The control for which shutoff valve is located in the cockpit?

Back 83

The firewall valve control is located on teh left console of the front cockpit

Front 84

Which annunciator illuminates if the autobalance system has failed or if the difference in weight between the left and right tanks exceeds 30 pounds for more than two minutes?

Back 84

The FUEL BAL annunciator will illuminate in these instances.

Front 85

Which electrical component provides power for engine starts?

Back 85

the primary battery