T-6 Systems 2 Propulsion

Front 1

The engine cowling does all the following except ____.

Back 1

secures the engine to the frame

Front 2

The purpose of the inertial separator is to _____.

Back 2

Keep debris away from the engine

Front 3

The compressor and power turbines are physically connectrd.True or False.

Back 3

False

Front 4

What three elements are necessary for engine operation?

Back 4

1. Air
2. fuel
3. Heat

Front 5

True or False. As exhaust is released, additional thrust is provided.

Back 5

True.

Front 6

True or 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.

Back 6

False

Front 7

The primary purpose of the ignition system is to ___.

Back 7

ignite the air and fuel mixture in the combustion chamber

Front 8

Tru or False. Friction control settings made to the front PCL affect the aft PCL.

Back 8

True

Front 9

When starting the T-6A, the PCL should be _______.

Back 9

pushed forward until a green ST READY annunciator is illuminated

Front 10

The PMU is located ____.

Back 10

underneath the engine, in the accessory compartment.

Front 11

The PMU performs the following functions, except:

Back 11

releases the correct amount of fuel

Front 12

The PMU STATUS annunciator illuminates after landing when the PMU ___.

Back 12

needs maintenance

Front 13

After engine start, the starter becomes a generator. True or False.

Back 13

True

Front 14

True or False. The MANUAL starter switch position will be used under normal circumstances.

Back 14

False

Front 15

For aircraft NOT modified by TCTO IT-6T-554/TD AVC-5266, with the engineabove IDLE power a red OIL PX annunciator illuminates when oil pressure falls below ____ psi.

Back 15

40

Front 16

For aircraft modified by TCTO 1T-6A-554/TD AVC-5266, if oil pressure remains between 15 and 40 psi at IDLE power for more than 5 seconds, _____ will be illuminated.

Back 16

both the amber and red OIL PX annunciators

Front 17

The chip detector sensor is located _____.

Back 17

in the reduction gearbox

Front 18

The oil system provides filtered oil to all of the following systems, EXCEPT ______.

Back 18

wheel brakes

Front 19

The reduction gearbox reduces engine output from _____ RPM to propeller speeds of _____RPM.

Back 19

30,000; 2000

Front 20

The phase shift torque probe monitors _______.

Back 20

propeller speed

Front 21

The PIU ____.

Back 21

regulates oil pressure to the pitch change mechanism.

Front 22

If the propeller pitch change mechanism loses oil pressure, the propeller will automatically move towards the _____position.

Back 22

feathered

Front 23

Varying levels of thrust are achieved by ______.

Back 23

changing propeller pitch

Front 24

The PMU ____.

Back 24

keeps the engine and propeller within operating limits.

Front 25

If the oil filter gets clogged ____.

Back 25

the system uses unfiltered oil

Front 26

In straight-and-level flight, for PCL positions above IDLE, oil pressure should be maintained between ____ and _____.

Back 26

90; 120 psi

Front 27

The phase shift torque probe is located _____.

Back 27

in the reduction gearbox.

Front 28

Propeller pitch refers to _____.

Back 28

the angle of the propeller blades

Front 29

Which propeller position produces the least amount of drag?

Back 29

Feather

Front 30

The propeller picth change mechanism is able to change propeller blade angel by ____.

Back 30

oil pressure

Front 31

The PMU directs the PIU to maintain propeller RPM at ____.

Back 31

2000

Front 32

The power turbine is driven by _____.

Back 32

expanding gases

Front 33

During aerobatic flight, oil pressure should be maintained at or above _____.

Back 33

40 psi

Front 34

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

Back 34

False

Front 35

The EDM is located _____.

Back 35

in the left avoinics bay

Front 36

True or False. All primary engine data is processed by the PMU prior to being displayed.

Back 36

True.

Front 37

In the event of abnormal engine operation, the primary engine data diplays will warn the pilot by _____.

Back 37

changing color

Front 38

In order to prevent possible damage due to ground resonance, what is the Np stabilized operation prohibited range while on the ground?

Back 38

62-80%

Front 39

True or False. All data provided to th ealternate engine data display is first processed by th PMU.

Back 39

False

Front 40

On the alternate engine data displays, /\P measures ____.

Back 40

the difference between cockpit pressure and outside pressure

Front 41

The engine/systems/NACWS displays provide ______.

Back 41

oil temp., oip pressure, hydraulic pressure, NACWS traffic alerts, DC volts and DC amps

Front 42

To view the NACWS diplay, _____.

Back 42

depress the trigger swtich on the control stick to the second detent

Front 43

True or False. Shutoff valves activated by the Firewall Shutoff Handle may be reset by pushing handle back in.

Back 43

True

Front 44

When testing the intregrity of th fire warning system, you will know the system is working properly if ______ and teh aural tone sounds.

Back 44

the FIRE and MASTER WARN annunciators illuminate

Front 45

The engine data manger does not _____.

Back 45

control all electronic displays in the cockpit

Front 46

The primary engine data displays system _______.

Back 46

provides each cockpit with a visual indicatin of engine operations

Front 47

The engine data manager is located ______.

Back 47

in the left avionics bay

Front 48

True or False. The alternate engine data display serves as a backup to the primary engine data displays, and therefore display some of the same data

Back 48

True

Front 49

The primary enging data display provides _____.

Back 49

torque,ITT, N1 NP and IOAT

Front 50

The engine/system/NACWS display does not ______.

Back 50

diplay outside environmental conditions in each cockpit

Front 51

True or False. All data presented on the alternate engine data display is processed by the PMU.

Back 51

False.

Front 52

The FIRE switch located in the front cockpit is used to _____.

Back 52

test the integrity of fire waring system

Front 53

What three elements are necessary for engine operations?

Back 53

Air, fuel, and heat

Front 54

Given indications of abnormal start, what should you do?

Back 54

Begin abort start procedure

Front 55

What are the types of abnormal start?

Back 55

Hot, hung, no start

Front 56

What are the indications of a hot start?

Back 56

High/rapidly rising ITT, lower N1, lower Np

Front 57

What are the indications of a hung start?

Back 57

Slow rising ITT,lower N1, lower Np

Front 58

What are the indications of no start?

Back 58

No ITT indication, lower N1, no Np indication, no torque indication

Front 59

What are some possible displays indications of engine failure in-flight?

Back 59

A. Initail indications: Loss of power and airspeed; rapid decay of N1, torque, and ITT; MASTER WARN Lights and tone; propeller moves towards feather
B. Accompanyiny indications: Rapidly decreasing ITT, Np; lower than normal oil pressur; engine noise; GEN, FUEL PX, OIL PX, OBOGS FAIL annunciators; Possibly PMU FAIL and CKPT ALT annunciators

Front 60

What are the indications of PMU failure?

Back 60

Power step change, PMU FAIL annunciator MASTER WARN light, aural tone

Front 61

What are teh indications of uncommanded propeller feather?

Back 61

Rapid loss of power, high torque, lower Np, possible PMU FAIL/PMU STATUS annunciators, engine/airframe vibration, engine noise

Front 62

What are some sensory indications of engine fire in-flight?

Back 62

See smoke or flames, smell oil burning, hear unusal sounds, feel engine vibration or roughness

Front 63

The power turbine is driven by _____.

Back 63

expanding gases

Front 64

What does FEVER stand for?

Back 64

Fluctuating oil pressure, oil temp. or hydraulic pressure,
Excessive turbine temp.
Visual indications(smoke),
Erratic engine operation
Roughness or vibration

Front 65

What are the three engine sections?

Back 65

Accessory compartment, gas generation section, and power turbine section

Front 66

What unctions are performed by the PMU?

Back 66

Maintaining operating limits, process power requests, control engine and propeller, provide near linear power response

Front 67

What is the purpose of PIU?

Back 67

Regulate oil pressure to the pitch change mechanism

Front 68

What are possible causes of engine failure in-flight?

Back 68

Fuel starvation, mechanical failure, compressor stall

Front 69

What are the engine fire warning indicators?

Back 69

FEVER, FIRE annunciator, MASTER WARNING light, aural tone

Front 70

What are some possible causes of uncommanded power loss?

Back 70

Enging rollback due to PMU scheduling, Oil/engine/fuel system contamination

Front 71

What are some possible indications of engine fire in-flight that may be seen on the engine displays?

Back 71

High ITT; Fluctuating; oil temp and pressure, hydraulic pressure.