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T-6 Systems > Propulsion > Flashcards

Propulsion Flashcards

1
Q

What is the purpose of the engine cowling?

A

Protect engine components, decrease drag, and provide engine air intake

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2
Q

What kind of engine does the T-6 have?

A

PT-6A-68 free turbine, reverse flow design, turboprop

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3
Q

What does Free Turbine refer to?

A

The compressor and power turbines are not physically connected. Air movement from one turbine to the other provides power to the propeller

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4
Q

What does Reverse Flow Design refer to?

A

The flow of air through the engine. Air enters at the rear and moves forward during the combustion cycle

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5
Q

What three elements are necessary for engine operations?

A

Air, fuel, and heat

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6
Q

What are the major sections of the engine?

A

Accessory compartment, gas generation section, and power turbine section

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7
Q

What items are found in the accessory compartment?

A

Accessory gearbox, oil tank, starter/generator, and battery

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8
Q

What turns the compressor turbine and compressor initially?

A

The starter

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9
Q

What is contained in the gas generation section?

A

Compressor inlet, compressor, combustion chamber, compressor turbine

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10
Q

Where does inlet air flow into first?

A

Compressor inlet

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11
Q

What is inlet air compressed by?

A

Four-stage axial flow compressor and single stage centrifugal flow compressor

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12
Q

Where does air go after the compressor?

A

Combustion chamber

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13
Q

What happens in the combustion chamber?

A

Compressed air is mixed with fuel and ignited

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14
Q

What drives the compressor turbine?

A

Expanded gasses from the combustion chamber

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15
Q

What components are in the Power Turbine Section?

A

Power turbine, exhaust case, reduction gearbox, propeller shaft

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16
Q

What is the purpose of the Power Turbine Section?

A

Produce horsepower from the gasses generated by the gas generation section

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17
Q

What drives the reduction gearbox?

A

The power turbine

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18
Q

What drives the propeller shaft?

A

The reduction gearbox

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19
Q

What components are in the Engine Exhaust System?

A

Exhaust ports and exhaust stacks

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20
Q

What happens to the air after it comes off the power turbine?

A

It moves through the exhaust ports, followed by the exhaust stacks

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21
Q

What kind of ignition does the T-6 use?

A

A dual spark ignition system

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22
Q

What does the starter provide?

A

Initial air flow

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23
Q

What does the Fuel Management Unit (FMU) provide on startup?

A

Fuel (duh)

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24
Q

What does the ignition system provide on startup?

A

Initial heat source

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25
Q

What components make up the Ignition System?

A

An ignition exciter, two high voltage igniter cables, and two spark igniters

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26
Q

What does the ignition exciter receive to create a spark?

A

A low voltage input signal from the battery bus

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27
Q

What does the ignition exciter do with the input signal?

A

Transforms it into a high voltage output signal?

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28
Q

What do the ignition cables do?

A

Carry the high voltage signal to the spark igniters

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29
Q

What do the spark igniters do?

A

Provides a spark to the air/fuel mixture in the combustion chamber

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30
Q

What happens when the ignition switch is set to NORM and the starter switch is moved to AUTO/RESET?

A

The igniters will initiate

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31
Q

What does the Power Management Unit (PMU) do during startup?

A

Enerrgize and de-energize the igniters

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32
Q

Which annunciator lights up during the engine start sequence?

A

Green IGN SEL

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33
Q

What provides power for the ignition system?

A

The circuit breaker labeled IGN, located on the battery bus CB panel in the front cockpit

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34
Q

What does the PCL do?

A

Controls fuel flow to the engine

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35
Q

What is the PCL connected to mechanically and electrically?

A

The Fuel Management Unit

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36
Q

What three positions does the PCL have?

A

OFF, IDLE, and MAX

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37
Q

Where do you move the PCL to for start?

A

Between OFF and IDLE, when the green ST READY annunciator illuminates

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38
Q

What prevents inadvertent engine shutdown?

A

PCL cutoff gate

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39
Q

Where is the Power Management Unit located?

A

Under the engine in the accessory compartment

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40
Q

What does the Power Management Unit do?

A

Processes power requests from the PCL and keeps engine and propeller within operating limits

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41
Q

What does an amber PMU STATUS annunciator in flight mean?

A

Indicates a fault in either of, or a mismatch between the weight-on-wheels switches. The PMU will not revert to ground mode upon landing

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42
Q

What accompanies a PMU STATUS annunciator?

A

Yellow MASTER CAUTION light and an aural tone

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43
Q

What does a red PMU FAIL annunciator mean?

A

The PMU is nonfunctional

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44
Q

What accompanies a PMU FAIL annunciator?

A

MASTER WARN and MASTER CAUTION, and an aural tone

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45
Q

Where does power for the Power Management Unit come from?

A

A Permanent Magnet Alternator mounted on the reduction gearbox

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46
Q

What does the Permanent Magnet Alternator provide to the Power Management Unit?

A

32 VAC, which the PMU converts to DC

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47
Q

If the Permanent Magnet Alternator fails, where does the Power Management Unit get power?

A

From the 28 VDC battery bus

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48
Q

Where is the starter/generator located at?

A

Attached to the accessory gearbox

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49
Q

What is the accessory gearbox attached to?

A

The compressor section via a shaft

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50
Q

During engine start, what does the starter/generator do?

A

The starter motor turns the compressor section. This generates air flow and compression until the engine starts and is able to run at idle speed

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51
Q

What does the starter/generator do after engine start?

A

Becomes a generator, which provides 28 VDC to many aircraft systems, and charges battery and aux battery to 24 VDC

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52
Q

What three positions does the starter switch have?

A

AUTO/RESET, NORM, and MANUAL

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53
Q

How is power provided for the starter?

A

A circuit breaker labeled START on the battery bus C/B panel

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54
Q

What is the purpose of the oil system?

A

Provides a steady flow of filtered oil to the engine bearings, reductions gears, accessory drives, and propeller

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55
Q

What components make up the oil system?

A

Pressure system, scavenge system, and cooling system

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56
Q

How is oil pressurized?

A

The pressure pump

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57
Q

What ensures oil can flow, even during inverted or negative G flight?

A

There is a normal pickup in the center of the oil pump, and an inverted pickup near the top of the tank

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58
Q

What does the scavenge system do?

A

Returns oil to the tank after being used in the bearings, reductions gears, accessory drives, and propeller

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59
Q

What does the oil system use to scavenge oil back to the tank?

A

Several pressure and scavenge pumps throughout the oil system

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60
Q

What does the oil cooler do?

A

Cools the oil before it’s returned to the oil tank

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61
Q

What filters the oil?

A

There is a main oil filter in the oil tank. There are also oil strainers in the power, compressor, and accessory drive areas

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62
Q

What happens if the mail oil filter gets clogged?

A

The oil travels through a filter bypass valve that allows unfiltered oil to continue lubricating the engine

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63
Q

Where is the chip detector located at?

A

In the reduction gearbox

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64
Q

What does the chip detector do?

A

Detects metallic particles in the oil and warns pilot of possible gear damage

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65
Q

What happens if the chip detector detects metal particles?

A

Red CHIP annunciator illuminates, MASTER WARNING illuminates, and an aural tone sounds

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66
Q

What is the purpose of the Signal Conditioning Unit (SCU)?

A

Illuminates the central warning system under certain oil pressure conditions

67
Q

What pressure should oil be during steady state operations?

A

90 to 120 psi

68
Q

What should oil pressure be during aerobatic flight?

A

40 to 130 psi

69
Q

When at IDLE, when will the OIL PX amber annunciator illuminate?

A

Between 15 to 40 psi

70
Q

When above IDLE, when will the OIL PX amber annunciator illuminate?

A

Between 40 to 90 psi for 10 seconds

71
Q

When at IDLE, when will the OIL PX red annunciator illuminate?

A

Below 15 psi, or when between 15 to 40 psi for more than 5 seconds

72
Q

Where is power for the oil system transducer provided from?

A

The OIL TRX circuit breaker on the battery bus circuit breaker panel in the front cockpit

73
Q

What is the purpose of the propeller?

A

To provide thrust

74
Q

What kind of propeller does the T-6 use?

A

Four blade, variable pitch, constant speed

75
Q

What two components controller propeller speed (Np)?

A

The Power Management Unit and Propeller Interface Unit

76
Q

What speed is the propeller held to?

A

2,000 rpm

77
Q

How are varying levels of thrust provided?

A

By adjusting the propeller pitch

78
Q

What altitude is 100% torque available for?

A

From sea level to between 12,000 and 16,000 MSL

79
Q

What happens to torque above 16,000 MSL?

A

There will be a decrease in max torque

80
Q

What is the propeller driven by?

A

The power turbine, through the reduction gearbox

81
Q

What speed is the power turbine spun at?

A

30,000 rpm

82
Q

What is propeller speed (Np) measured by?

A

The phase shift torque probe

83
Q

What monitors the phase shift torque probe?

A

The Power Management Unit

84
Q

What directs the Propeller Interface Unit to maintain propeller rpm?

A

The Power Management Unit

85
Q

What does the Propeller Interface Unit use to restrict rpm?

A

An electronic governor

86
Q

What happens if the electronic governor fails?

A

There is a backup mechanical governor

87
Q

What does the backup mechanical governor hold the propeller to?

A

106% torque, or 2120 rpm

88
Q

What changes propeller pitch?

A

Changes in oil pressure

89
Q

What are the three basic blade pitch angles base upon?

A

The angle between the plane of rotation and the chord line of the propeller

90
Q

What are the three basic pitch conditions?

A

Feathered, high pitch (coarse), and low pitch (flat or fine)

91
Q

What is the default condition of the propeller?

A

The feathered position

92
Q

What does the feathered position provide?

A

The least amount of drag and no thrust

93
Q

What pitch will the propeller usually be in?

A

High pitch

94
Q

What does a low pitch propeller provide?

A

Some thrust and the most drag

95
Q

What controls the oil flow to the propeller?

A

The Propeller Interface Unit

96
Q

What happens as oil pressure is increased in the propeller?

A

The blades move from the feathered position to high pitch, then to low pitch

97
Q

What PCL position causes the prop to feather?

A

OFF

98
Q

What happens if there is any residual oil pressure in the system if the engine fails?

A

The prop might not feather

99
Q

When the engine fails and the PCL is placed in off to feather, what happens in the system?

A

Two valves are activated in the Propeller Interface Unit, the feather dump solenoid valve, and an oil pressure release valve. This allows the prop to feather

100
Q

What circuit breaker controls the feather dump solenoid valve?

A

The PROP SYS circuit breaker on the battery bus circuit breaker panel

101
Q

Where is the Engine Data Manager located?

A

In the left avionics bay

102
Q

What engine related tasks does the Engine Data Manager do?

A

Drives primary, alternate, and engine/system displays, and illuminates advisory, caution, or warning annunciators when appropriate

103
Q

What non-engine related tasks does the Engine Data Manager do?

A

Fuel balancing, fuel quantity indications, activation of nose wheel steering annunciator, display of DC volts, amps, hydraulic pressure, cockpit pressure altitude, and cockpit pressure differential

104
Q

What provides power to the Engine Data Manager?

A

Two EDM circuit breakers. One on the battery bus circuit breaker panel, and one on the generator bus circuit breaker panel in the front cockpit

105
Q

What is the Primary Engine Data Display (PEDD)?

A

An electronic instrument display that presents engine information from the Engine Data Manager

106
Q

What processes the information from various sensors around the engine?

A

The Power Management Unit

107
Q

What monitors engine parameters and passes the information to the Primary Engine Data Display?

A

The Engine Data Manager

108
Q

What does the Primary Engine Data Display do during abnormal engine operations?

A

Changes the color of the scales

109
Q

What is the normal operating range color?

A

White or green

110
Q

What is the cautionary operating range color?

A

Amber

111
Q

What is the exceeding operating limits color?

A

Red

112
Q

What information is provided on the Primary Engine Data Display?

A

Torque, Inter-Turbine Temp, Propeller RPM (Np), and Indicated Outside Air Temp (IOAT)

113
Q

What are the in-limits for torque?

A

0 to 100%

114
Q

What are out-of-limits for torque?

A

Anything more than 100%

115
Q

What does ITT indicate on the Primary Engine Data Display?

A

The temp between the compressor turbine and power turbine

116
Q

What are ITT operating limits during start sequence?

A

400° to 1000°C

117
Q

After start sequence, what are the ITT operating limits?

A

400° to 820°C

118
Q

What are out-of-limits for ITT?

A

Above 820°C

119
Q

What does the N1 indication on the Primary Engine Data Display indicate?

A

Gas generator speed

120
Q

What are normal operating limits for N1?

A

60 to 104%

121
Q

What are out-of-limits readings for N1?

A

Above 104%

122
Q

What are the ground operation limits for Np?

A

0 to 61% and 81 to 100%

123
Q

What percentage of Np is prohibited on the ground?

A

62 to 80%

124
Q

What is out-of-limits for Np in flight?

A

Above 102%

125
Q

What circuit breaker controls the PEDD?

A

PRI ENG DIS on the generator bus circuit breaker panel

126
Q

What does the Alternate Engine Data Display do?

A

Provides each cockpit with a backup visual indication of engine operations

127
Q

Except for torque, what displays information for the Alternate Engine Data Display?

A

The Engine Data Manager

128
Q

What does the Alternate Engine Data Display show?

A

Raw ITT, Torque, Gas Generator Speed (N1), Cockpit pressure altitude, Cockpit differential pressure, fuel flow, and fuel quantity

129
Q

What happens if your cockpit altitude exceeds 19,000 feet?

A

The Cockpit Alt information on the AEDD is boxed in yellow, and an amber CKPT ALT annunciator illuminates, along with an aural tone

130
Q

What happens if the differential pressure exceeds 3.9 to 4.0?

A

The differential pressure readout is outline in a red box, and a red CKPT PX annunciator is illuminated, along with an aural tone

131
Q

How is the AEDD powered?

A

ALT ENG DIS circuit breaker on the battery bus circuit breaker panel

132
Q

What does the engine/system display show?

A

Oil, hydraulic, and electrical system data

133
Q

What are the normal operating limits for oil temp?

A

10° to 105°C

134
Q

What are the cautionary operating limits for oil temp?

A

105° to 110°C

135
Q

What is the out-of-limits readings for oil temp?

A

Above 110°C

136
Q

What powers the engine/systems display?

A

ENG SYS DIS on the generator bus circuit breaker panel

137
Q

What does the Firewall Shutoff Handle do?

A

Shuts of hydraulic fluid and fuel flow to the engine, as well as bleed air flow from the engine

138
Q

What provides power for the Fire #1 warning system?

A

FIRE 1 circuit breaker panel on the battery bus circuit breaker panel

139
Q

What provides power for the Fire #e warning system?

A

FIRE 2 circuit breaker panel on the generator bus circuit breaker panel

140
Q

What are possible indications of a Hot Start?

A
  • High/rapidly rising ITT
  • Lower N1
  • Lower Np
141
Q

What are possible causes of a Hot Start?

A
  • PMU failure
  • FMU failure
  • Incorrect air/fuel mixture
  • Low battery
142
Q

What are possible indications of a Hung Start?

A
  • Slow rising ITT
  • Lower N1
  • Lower Np
143
Q

What are possible causes of a Hung Start?

A
  • PMU failure
  • FMU failure
  • Incorrect air/fuel mixture
  • Ignition system failure
  • Starter failure
  • Low battery
144
Q

What are possible indications of a No Start?

A
  • No ITT indication
  • Lower N1
  • No Np indication
  • No torque indication
145
Q

What are possible causes of a No Start?

A
  • PMU failure
  • FMU failure
  • Starter failure
  • Ignition system failure
  • Incorrect air/fuel mixture
146
Q

What are initial indications of Engine Failure In-Flight?

A
  • Loss of power and airspeed
  • Rapid decay of N1, torque and ITT
  • MASTER WARN light and tone
  • Propeller moves toward feather
147
Q

What are accompanying indications of Engine Failure In-Flight?

A
  • Rapidly decreasing ITT, Np
  • Lower than normal oil pressure
  • Engine noise
  • GEN, FUEL PX, OIL PX, OBOGS FAIL annunciators
  • Possibly PMU FAIL and CKPT ALT annunciators
148
Q

What are possible causes of Engine Failure In-Flight?

A
  • Fuel starvation
  • Mechanical failure
  • Compressor stall
149
Q

What should you do if you experience an engine failure in-flight?

A

Proceed with appropriate emergency procedure

150
Q

What are possible indications of a PMU Failure?

A
  • Power step change
  • PMU Fail and PMU STATUS annunciators
  • MASTER WARN light
  • Aural tone
151
Q

What are possible causes of a PMU Failure?

A
  • System failure

- System malfunction

152
Q

What is the appropriate procedure for a PMU Failure?

A

Proceed with PMU failure procedure

153
Q

What are possible indications of Uncommanded Power Changes/Loss of Power?

A
  • Reduction in power/thrust
  • Lower than expected fuel flow
  • Uncommanded decrease in N1
  • High raw ITT on AEDD
  • With oil/engine/fuel system contamination, additionally:
    • Power surges
    • Uncontrollable high power
154
Q

What are possible causes of Uncommanded Power Changes/Loss of Power?

A
  • Engine rollback due to PMU scheduling

- Oil/engine/fuel system contamination

155
Q

What are possible indications of Uncommanded Feather?

A
  • Rapid loss of power
  • High torque
  • Lower Np
  • Possible PMU FAIL/PMU STATUS annunciators
  • Engine vibration
  • Engine noise
156
Q

What are possible causes of Uncommanded Feather?

A
  • Feather dump solenoid malfunction

- Loss of oil pressure to propeller pitch control mechanism

157
Q

What are possible indications of Prop Sleeve Touchdown?

A
  • Np fluctuations
  • Increasing torque
  • Decreasing thrust
  • Engine vibrations
  • Possible CHIP detector warning light
158
Q

What are possible causes of Prop Sleeve Touchdown?

A

Loss of oil pressure to propeller pitch control mechanism from momentary contact between oil transfer sleeve and propeller shaft

159
Q

What is the appropriate procedure for Pro Sleeve Touchdown?

A
  • Proceed with uncommanded propeller feather procedures
160
Q

What are possible indications of Engine Fire In-Flight?

A
  • FIRE annunciator
  • MASTER WARN light
  • Aural tone
161
Q

What is the FEVER check for Engine Fire?

A
  • Fluctuating oil pressure, oil temp, or hydraulic pressure
  • Excessive turbine temp
  • Visual indications (smoke or flames)
  • Erratic engine operation
  • Roughness or vibration
162
Q

What are possible cause of Engine Fire In-Flight?

A
  • Fuel or oil leaks

- Fire getting outside of engine

163
Q

What procedure should you take for Engine Fire In-Flight?

A

Proceed with fire warning in-flight procedure

164
Q

What does an amber PMU STATUS annunciator after landing mean?

A

The PMU has accommodated a fault that needs to be cleared by maintenance

T-6 Systems (12 decks)

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