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162 Cards in this Set

  • Front
  • Back

What engines are on the Q-400?

Pratt & Whitney PW150A
Who manufactures the propellers for the Q-400?
Dowty
What is the maximum horsepower that the engines can develop during:

Takeoff (NTOP): ?
Automatic Uptrim (MTOP): ?
Max Takeoff Power Selected (MTOP): ?
Takeoff: 4,580 SHP
Automatic Uptrim: 5,071 SHP
Max Takeoff Power Selected: 5,071 SHP
How many compressors are in the engine?
Two (2)

Low Stage "Axial" compressor
High Stage "Centrifugal" compressor
What drives the propeller reduction gearbox?
A two (2) stage power turbine.
What are the names of the two (2) control levers for each engine?
Power Levers

Condition Levers
What do the "Power Levers" actually control?
1. Engine Power through the FADEC computer while in the "forward" range.
2. The propeller blade angle when in the "Beta" range.
What functions does the "Condition Levers" provide?
1. Controls the propeller RPM through the "Propeller Electronic Controller" (PEC).
2. Manually feathers the propellers.
3. Provides "ON/OFF" fuel control during engine start and shutdown.
Where is the engine "Accessory Gearbox" located on the engine?
On the Top/Center of the engine.
What drives the accessory gearbox?
The HP (NH) compressor.
What does the "Engine Accessory Gearbox" drive?
1. Fuel Metering Unit
2. Engine Driven Oil Pump
3. DC Starter-Generator
4. Permanent Magnet Alternator (PMA)

REMEMBER: "FOD-P"
Where is the "Propeller Reduction Gearbox" physically located on the engine?
At the front section of the engine.
What drives the Propeller Reduction Gearbox?
The HP Power Turbine Shaft.
What does the Propeller Reduction Gearbox drive?
1. Engine Driven Hydraulic Pump.
2. AC Generator
3. Propeller Control Unit (PCU)
4. Propeller Over-Speed Governor (POG)

REMEMBER: "HAP-P" (HAPPY)
What does the engine oil system provide for?
1. Lubrication of the engine bearings and gearboxes.
2. Oil supply for propeller operation.
How is the engine oil temperature controlled?
Automatically by routing the engine oil through an air cooled "oil cooler" located on the bottom of the engine nacelle.
Where does the air come from that cools the air cooled oil cooler?
Through an electrically operated oil cooler door on the bottom of the engine nacelle.
At what time will the "#1/#2 ENG OIL PRESS" warning light illuminate?
When the oil pressure drops to between 40 to 45 PSI.
On what display is the engine operating information displayed?
On the Engine Display (ED).
In what formats does the "Engine Display" show information?
Both "Digital" and "Analog" formats.
On the fuel quantity and temperature gauges how is the "digital" information shown if the data is invalid?
The digits are replaced by "white dashes".
The displayed fuel temperature on the Engine Display is shown after ______.
The fuel has been heated and filtered.
At what time will the "BALANCE" caution message illuminate on the Engine Display?
When the fuel imbalance exceeds 600 lbs.
What color is the "Torque Bug"?
Cyan
What does the "Torque Bug" indicate?
The torque commanded by the FADEC computer.
At what times is the "Torque Bug" removed from view?
1. When the actual torque "or" the torque bug parameter is no longer valid.
2. The condition lever is at the "START/FEATHER" or "SHUTOFF" position.
What conditions are required to "ARM" the "Autofeather System"?
1. The Autofeather switchlight must be selected.
2. The torque on "both" engines must be above 50%.
"AND"
3. Both Power levers must be at a "High Angle" (60% power lever angle).
What two features does the "Automatic Takeoff Power Control System" (ATPCS) provide?
1. Automatic Uptrim
2. Propeller Auto Feather
Is it possible to have an "Autofeather" occur without an "Uptrim" or vise-versa?
Yes

The two systems are independent of each other even though they "arm" under the same conditions.
At what time does the white "UPTRIM" message appear on the Engine Display?
When a power up-trim has been commanded by the FADEC computer.
If FADEC commands an "UPTRIM" what indications will show on the Engine Display?
1. "UPTRIM" is displayed.

2. The Engine Power Rating will automatically go to the next higher power rating:
- RDC TOP = NTOP
- NTOP = MTOP
When the parameter is no longer valid on the torque indication what happens to the colored arcs?
The scale will revert to a totally white arc.

The needle is removed from view.
Does the torque needle change colors?
Yes

It is normally "white" but will turn yellow or red if it enters the caution or maximum range "after 1 second".
If the torque needle reaches its "maximum" range what will occur with the "digital" torque indication?
The digital torque indication will remain accurate!
If the torque indication becomes invalid, how are the "digital" indications displayed?
The digital indication will be replaced by white dashes.
What is displayed on the Engine Display if an "Over-Speed Test" is in progress?
"OSG TEST IN PROG"
What does the "Red Triangle" indicate on the "Indicated Turbine Temperature" (ITT) gauge?
The maximum "transient" limit during engine start (920 degrees C).
Is the "Red Triangle" always visible for the ITT gauge?
No

It is only visible during engine starts.
The triangle will disappear 30 seconds following engine start.
How will the "digital" indications be displayed on the LP Gas Generator Speed indication if the parameters are no longer valid?
The digits are replaced by white dashes.
The oil temperature and pressure gauge is composed of seven (7) different colored areas. What are the colors and meanings?
WHITE ARC: Minimum needle travel
RED RADIAL: Minimum "starting" oil temperature
YELLOW ARC: Caution Range
GREEN ARC: Normal Operating Range
YELLOW ARC: Caution Range
RED RADIAL: Maximum Range
WHITE ARC: Maximum needle travel

NOTE:
The scale will revert to a totally "white arc" when the parameters are no longer valid.
What do the "Power Levers" control?
In the forward range:
- The power levers initiate fuel demands to the FADEC computer.

In the Beta range:
- The power levers control the propeller RPM through the "Propeller Electronic Control" (PEC) as well as fuel demands to the FADEC computer.
With the power levers in the "RATING" detent, what determines the appropriate horsepower rating?
Condition Lever position

1020 = NTOP
900 = MCL
850 = MCR

NOTE:
Alternate engine power ratings can be selected by using the "Rating Select Switches" on the Engine Control Panel.
What occurs when the power levers are pushed into the "Over Travel Range"?
FADEC will deliver 25% extra power!

The propeller RPM is automatically set at 1,020 RPM when the power levers are pushed past the "Rating" detent irregardless of Condition Lever setting!
What is the purpose of the "Flight Idle Gate"?
It will prevent inadvertent movement of the power levers into the "BETA" range.
What must occur in order to pull the power levers aft of the Flight Idle Gate?
The release trigger must be lifted!
What occurs when the power levers are selected to the "DISC" detent?
1. The engine will supply only minimum torque.
2. The propeller blade angle goes to "Flat Pitch".
What is the maximum horsepower that the engines will provide while operating in the "Reverse" range?
1,000 SHP
When operating in the "Reverse" range, what is the propeller RPM automatically set to?
950 RPM
What is the purpose of the "Control Lock" for the power levers?
It prevents the power levers from being advanced into the "flight range".

It also locks the aileron movement.
What is the purpose of the Condition Levers?
They control propeller RPM and provide the appropriate power settings to the FADEC computer.

The condition levers also introduce and terminate fuel during engine start and shutdown.

Provides for "Manual Feathering" of the propellers.
With the condition levers placed at the "MAX" detent position, what propeller RPM and power setting is commanded?
1,020 RPM with the power levers at the "RATING" detent.

FADEC commands "Normal Takeoff Power" (NTOP).
With the condition levers placed at the "900" detent position, what propeller RPM and power setting is commanded?
900 RPM with the power levers at the "RATING" detent.

FADEC commands "Maximum Climb Power" (MCL).
With the condition levers placed at the "MIN" detent position, what propeller RPM and power setting is commanded?
850 RPM with the power levers at the "RATING" detent.

FADEC commands "Maximum Cruise Power" (MCR).
What is required to move the condition levers "aft" of the "MIN / 850" gate?
The Condition Levers must be physically "lifted" over the MIN GATE.

There are no release triggers on the Condition Levers!
What occurs when the condition levers are moved into the "START & FEATHER" position?
The propellers are manually feathered.

The PCU will "dump" the metered oil pressure in the propeller hub to allow the constant oil pressure side to drive the props to feather!
When is fuel introduced during the engine start sequence?
When the condition levers are moved from the "Fuel Off" position into the "START & FEATHER" position.

FADEC will then control all fuel inputs for engine start!
What occurs when the condition levers are moved into the "FUEL OFF" position?
Fuel flow is shutoff to the engines.
What is the purpose of the "Fuel Metering Unit" (FMU)?
The FMU meters fuel to the engines as commanded by the FADEC computer.

The FMU also provides motive flow fuel to the fuel system ejectors.
What drives the Fuel Metering Unit?
The Engine Accessory Gearbox.

The FMU is directly mounted to the Accessory Gearbox.
How many fuel pumps are incorporated into each engines FMU?
Two (2)

Low Pressure Fuel Pump
High Pressure Fuel Pump
Where does the "Low Pressure Fuel Pump" receive its fuel from?
From the fuel tanks via the "Primary Ejector Pumps".
What occurs to the fuel from the FMU's Low Pressure Fuel Pump prior to being passed on to the High Pressure Fuel Pump?
It is "Heated and Filtered".

It runs through the engines Fuel/Oil heat exchanger prior to entering the "High Pressure" fuel pump.
Where does the FMU's "High Pressure Fuel Pump" receive its fuel supply from?
From the FMU's "Low Pressure Fuel Pump" after it has been heated and filtered.
Where does the FMU's "High Pressure Fuel Pump" deliver the fuel to?
To the "Fuel Metering Unit" and then on to the engines fuel nozzles.

A portion of the High Pressure Fuel is routed back to the fuel tanks as "Motive Flow" fuel to power the ejector pumps.
Where is the FADEC computer physically installed?
On the left side of each engines case.
Does the FADEC computer have a "single" or "dual" channel?
Each FADEC computer has a "dual" channel micro-processor to control the fuel flow.
What is the "primary" function of the FADEC computer?
To schedule fuel.
What "secondary" functions does the FADEC computer provide?
1. Controls the engine bleed valves to prevent compressor surges and stalls.
2. Prevents engine over-speeds by limiting fuel.
3. Controls automatic engine start and shutdown.
4. Supplies power to the Propeller Electronic Control (PEC).
5. Detects and indicates powerplant faults.
What powers the FADEC computer?
The "Permanent Magnet Alternator" (PMA) when the NH is above 20%.

The "Essential DC Bus" will provide 28 VDC power to the Fadec computer when:
1. Below 20% NH
2. Permanent Magnet Alternator (PMA) failure.
What is the purpose of the Engine Control Panel?
It provides an "alternate" means of selecting engine rating and propeller speed combinations.
What alternate engine ratings switchlights are located on the Engine Control Panel?
MTOP:
Maximum Takeoff Power (Alternate Action Switch)

MCL:
Maximum Climb Power (Momentary Switch)

MCR:
Maximum Cruise Power (Momentary Switch)

RDC Np LDG:
Reduced Propeller RPM Landing
Will the MTOP, MCL and MCR switches on the Engine Control Panel override the normal FADEC commands?
Yes
What is commanded if the "MTOP" switch is selected on the Engine Control Panel?
Maximum Takeoff Power is commanded if the Power Levers are set to the "RATING" detent and the Condition Levers are set at the "MAX" position.
If the "MTOP" switch is pressed on the Engine Control Panel, how can the command be cancelled?
1. Pressing the MTOP switch a second time.
2. Moving the Power Lever out of the "RATING" detent.
3. Moving the Condition Lever out of the "MAX" (1020) position.
What power rating is normally set by FADEC when the Power Levers are set to "RATING" and the Condition Levers are set to the "MIN" position?
Maximum Cruise Rating (MCR)
What occurs if the "MCL" switch is pressed on the Engine Control Panel?
Maximum Climb is commanded if the Power Levers are at the "RATING" detent and the Condition Levers are at the "MIN" positions.
If the "MCL" switch was pressed on the Engine Control Panel how can the selection be cancelled?
By pressing the "MCR" switch on the Engine Control Panel.

This will return the power selection back to the normal Maximum Cruise setting.
What power setting is normally scheduled by FADEC with the Power Levers in the "RATING" detent and the Condition Levers in the "900" position?
Maximum Climb Rating (MCL)
With the Power Levers in the "RATING" detent and the Condition Levers in the "900" position what is achieved by pressing the "MCR" switch on the Engine Control Panel?
Maximum Cruise (MCR) is alternately scheduled.

This will reduce engine torque by FADEC.
If Maximum Cruise is alternately selected by pressing the "MCR" switch on the Engine Control Panel, how can the selection be canceled?
1. By pressing the "MCR" switchlight a second time.
2. By re-positioning the Condition Levers.
What is the purpose of the "RDC NP LDG" button on the Engine Control Panel?
It will hold the propeller RPM at 850 RPM when the Condition Levers are advanced to the "MAX" position during approach.

This will reduce the propeller noise during approach and landing.

NOTE:
The Power levers must be "aft" of the "RATING" detent and the Condition Levers at the "MIN" position for the switch to function.
If the "RDC NP LDG" switch has been pressed on the Engine Control Panel, what is indicated on the Engine Display?
"REDUCED NP LANDING" message will appear.
If the "RDC NP LDG" switch has been pressed on the Engine Control Panel, at what time will the selection be canceled?
When the Power Levers are advanced to the "RATING" detent during a go-around.
What is the purpose of the "DEC" pushbutton on the Engine Control Panel?
It is used for "Reduced Takeoff Power" operations.

- Each press of the switch will decrease scheduled takeoff power by approximately 2% (actually 1.6%).
- A maximum of 10% reduced takeoff power may be commanded (5 pushes).

NOTE:
The torque indication will not show decimal percents. If the "DEC" button is pushed once (1.6%) the torque indication will indicate a 2% drop. The torque indication will "round to the nearest whole percent"!
If the takeoff power has been reduced by using the "DEC" button on the Engine Control Panel, what will occur if "Uptrim" is commanded by FADEC?
Only the "reduced takeoff power torque" will be Uptrimed by 10%.
If the power has been reduced for takeoff by using the "DEC" button on the Engine Control Panel, how can the setting be cancelled?
1. By pressing the "RESET" pushbutton.
2. By pressing the "DEC" button a sixth time starts back at zero.

This will reset any takeoff power reduction settings.
What is the purpose of the "Event Marker" pushbutton on the Engine Control Panel?
Pressing the pushbutton will store a "snapshot" of engine data parameters for 2 minutes prior to 1 minute after the event.

- Used in the event of an engine abnormality.
FADEC will monitor and report three (3) types of faults, what are they?
1. Critical Faults
2. Cautionary Faults
3. Advisory Faults
If FADEC detects a "Critical Fault" what will occur?

No action is required from the flight crew.
- FADEC may limit power to the engine to Ground Idle or Flight Idle or completely shut it down.
- The "#1/#2 ENG FADEC FAIL" (RED) warning message will be displayed.

If FADEC detects a "Cautionary Fault" what will occur?

The "#1/#2 ENG FADEC" (AMBER) caution message will be displayed.

- Crew should use caution during control inputs.

If FADEC detects a "Advisory Fault" what will occur?
Advisory Faults are automatically handled by FADEC.

- They do not require any crew input.

- No caution or warning lights will be displayed.

- The fault code is transmitted to the "Engine Monitoring Unit" (EMU) to be later diagnosed by maintenance.
What is the purpose of the "Automatic Takeoff Power Control System" (ATPCS)?
1. It provides "Uptrim" in the event of an engine failure.
2. It provides "Autofeather" of the propellers.
During an engine failure event, what sends the signal to the operating engines FADEC computer that an engine has failed?
The failed engines "Propeller Electronic Unit" (PEC).
Uptrim provides how much additional power to the operating engine?
10% additional power to either the "FADEC generated" rating or the "Reduced Takeoff Power" rating manually selected.
At what time will the "Automatic Takeoff Power Control System" (ATPCS) automatically "Arm" itself?
1. When both Power Levers are at a "High Angle".

"AND"

2. The torque on "both" engines is at or above 50% Nh.
What cockpit indications are there that an "Uptrim" has occurred?
1. A "UPTRIM" message is displayed on the Engine Display.
2. A change in the operating engines power rating from "NTOP" to "MTOP" on the Engine Display.
3. A change in the operating engines torque bug position from "NTOP" to "MTOP".
Will "Uptrim" occur on the operating engine if the autofeather system has been disabled?
Yes

- Uptrim will occur regardless of the autofeather selection.

- They are independant systems!
Under what two (2) conditions will "Uptrim" occur?
1. The torque drops below 25% on the failed engine with the Power Lever in the "RATING" detent and "MTOP" is not selected.
2. When the Power Turbine Speed (Npt) falls below 80% with the Power Levers in the "RATING" detent and "MTOP" is not selected.

Note:
Torque loss and Power Turbine Speed conditions must be confirmed by "both" sensors on the failed engine for uptrim to occur.
If "Uptrim" automatically occurs how can it be cancelled?
By moving "both" Power Levers out of the "RATING" detent.
What provides "Over-Torque" protection?
The FADEC computer.

The FADEC will reduce fuel as needed to prevent an "over-torque" condition.
FADEC "generally" limits torque to what values to prevent an over-torque condition?
Over Travel Range: 125% NH
Forward Range: 106% NH
Reverse Range: 35% NH
If a propeller was to feather at a high power setting FADEC may not be able to keep the transient torque from exceeding the over-torque limits. What will FADEC do?
FADEC will anticipate the rapidly rising torque and rapidly reduce the NH to prevent the transient condition from exceeding 135% NH.
If an engine over-speed condition occurs what will happen?
FADEC will cut off the fuel flow to the engine through the "Fuel Shutoff Solenoid" (within FADEC) when the NH input signals exceed approximately 108% NH.
Each engines "ignition system" consists of what components?
One (1) Dual Channel "Exciter Box"

Two (2) "Igniter Plugs"
What controls the engines "Ignition System"?
The FADEC computer will control the ignition system during the engine start sequence.
At what time will the FADEC system energize "both" igniter plugs in the engine?
1. During an engine failure.

2. During engine "airstarts".

3. During "ground starts" if lightoff does not occur within 8 seconds.
What is the purpose of the "#1/#2 Engine Ignition" switches on the Engine Start Control Panel?
In the "NORM" position, FADEC will control the engines ignition during the start sequence.

In the "OFF" position, FADEC will disable the engines ignition system for both flight and ground operations.
What is the purpose of the "Engine Start Select" toggle switch on the Engine Start Control Panel?
It will "arm" the engine start control circuit for the selected engine.

It will also illuminate the amber "SELECT" segment on the top half of the engine start switchlight.
How is the "Engine Start Select" toggle switch held into position?
It is magnetically held into position until the NH reaches approximately 57% during engine start.
What occurs when the "Engine Start" switchlight is pressed?
FADEC will initiate the start sequence for the selected engine.

The green "START" segment on the bottom half of the Engine Start switchlight will illuminate.
During engine "START", at what time is the Condition Lever placed in the "START & FEATHER" position?
At the first indication of NH rising.
During the engine start sequence, at what time does FADEC command the ignition to "ON"?
When the NH reaches 8%.

Only one (1) igniter is energized normally.

If ignition does not occur within 8 seconds FADEC will energize "both" igniters.
How is engine "light-off" defined?
A rise in ITT of 20 degrees C.
At what time is the automatic start sequence terminated (completed) by FADEC?
When the NH reaches 57%.
How is "start termination" indicated?
By the release of the magnetically held "Start Select" switch.
At what time will the "START" segment of the Start Select switch extinguish following engine start?
Approximately 15 seconds after start toggle resets.
What is the maximum ITT during engine start?
920 degrees C.

Limited to 20 seconds.
What will occur if an "over temperature" condition occurs during the engine start?
FADEC will limit the fuel as necessary to prevent the ITT from exceeding 920 degrees C.

Note:
FADEC limits fuel during "ground starts" only!
At what times will FADEC automatically "abort" the start sequence and shut down the engine?
1. The engine does not light off within 16 seconds of introducing fuel.
2. The ITT exceeds 920 degrees C during the start.
3. The NH does not reach 64% within 70 seconds.
When FADEC automatically terminates the engine start sequence, how is it indicated?
1. The "Start Select" switch resets.
2. The "START" segment of the switchlight extinguishes.
What difference exists while conducting an "air start"?
1. Both igniters are energized.
2. No Auto Abort capability.
3. No automatic ITT limiting.
What are the propeller blades manufactured from?
"Carbon Fiber" and "Glass" re-enforced plastic.

Blades have a light weight "foam filler".
The propeller system consists of what?
1. Propeller Electronic Control (PEC)
2. Pitch Control Unit (PCU)
3. Propeller Overspeed Governor (POG)
4. Auxiliary Feathering Pump
5. Automatic Synchrophase System
What is the purpose of the Propeller Electronic Control (PEC)?
1. Controls the propeller Pitch and speed.
2. Controls Auto-Feather and underspeed control.
3. Sends a signal to the opposite engine PEC during an engine failure event (commands uptrim).
What is the purpose of the propellers Pitch Control Unit (PCU)?
1. Meters high pressure (fine pitch) engine oil to the PEC for propeller blade re-positioning.
2. Controls the maximum blade pitch that can be obtained while in-flight.
What is the purpose of the Propeller Over-speed Governor (POG)?
It limits propeller speed.
What drives the Propeller Over-speed Governor?
The Propeller Reduction Gearbox.
What is the purpose of the "Auxiliary Feathering Pump"?
It provides a "secondary" source of oil pressure to feather the propeller.
How can the "Auxiliary Feathering Pump" be activated?
1. Automatically when auto-feather occurs.
2. Manually by selecting the "Alternate Feather" switchlight.

NOTE:
The Alternate Feather Pump will activate for 30 seconds when autofeather occurs "or" the Alternate Feather switchlight is pressed.
Where is the "Auxiliary Feathering Pump" physically installed?
On the aft section of the Propeller Reduction Gearbox.
What drives the "Auxiliary Feathering Pump"?
A 28 VDC motor drives an external gear pump.
Which propeller is the "MASTER" in the propeller synchrophase system?
Left Propeller.
How does the propeller synchrophase system measure the difference in propeller RPM?
Through a "Magnetic Pickup Unit" (MPU) installed on each propeller.
At what time is the propeller synchrophase system "not functional"?
During takeoff with the Condition Levers at the MAX 1020 gate.
How is the propeller pitch modulated?
Engine oil pressure is modulated on the "Fine Pitch" side of the "Pitch Change Mechanism" (PCM) inside the propeller hub.

Loss of Fine Pitch oil will cause the "constant" pressurized side to drive the props to feather!
Why do the propellers tend to automatically move to the feather position when oil pressure is lost to the propeller hub?
The constant oil pressure side of the propeller hub will push the props towards feather with the loss of Fine Pitch oil pressure.
"and"
Each blade has a counter-weight attached to it which tends to force the blades towards feather.
At what times are the propellers in the "Constant Speed" mode?
When the Power Levers are in one of the "forward" detents.
At what Power Lever position is the propeller "Beta" mode?
Begins just slightly ahead of the Flight Idle gate and continues to the "Max Reverse" stop.
What is considered the "Flight Beta" range?
When the Power Levers are just slightly ahead of the Flight Idle gate to the Flight Idle Gate.
What is considered the "Ground Beta" range?
The Power Levers are aft of the Flight Idle gate.

The "Propeller Ground Range" advisory lights will illuminate.
What controls the blade angle while in the "Beta" mode?
The Power Levers.
What RPM will FADEC maintain as a "minimum" when in the "Beta" mode?
660 RPM
When in the "Reverse" mode what RPM is the propeller maintained at?
660 RPM to 950 RPM
When operating in reverse what is the maximum SHP that FADEC will limit by fuel scheduling?
1,000 SHP
What are the three (3) ways to feather the propeller?
1. Auto Feather
2. Alternate Feather
3. Manual Feather using the Condition Levers
At what times is the "Auto-Feather" system selected to "ON"?
For takeoffs only!
When the Auto-Feather system is selected via the switchlight, what is displayed?
1. The "A/F SELECT" advisory message displays on the Engine Display.
2. The white "SELECT" segment will illuminate on the switchlight.
When will the "Auto-Feather" system automatically "ARM"?
1. The Auto-Feather switchlight is selected.
2. The torque on "both" engines is above 50% NH.
3. Both Power Levers are advanced beyond a 60% angle.

NOTE:
The "A/F SELECT" advisory message will be replaced by a "A/F ARM" message.
With regards to the Auto-Feather system, at what time is a mandatory abort required?
When the Auto-Feather system "A/F ARM" message does not appear prior to 80 kts.
When the Auto-Feather system has armed itself, at what time will auto-feather automatically occur?
When:

1. The system has "ARMED"
"AND"
2. The failed engines torque falls "below 25% for 3 seconds".

Note:
Must be sensed by both torque sensors!
When the propeller Auto-Feathers what is actually activated to feather the propeller?
The associated "Auxiliary Feathering Pump" will activate for 30 seconds to ensure an adequate oil supply is available to feather the propeller.

The associated "Alternate Feather" switchlight will illuminate indicating activation of the "Auxiliary Feathering Pump".
What will automatically occur when one propeller is feathered?
The auto-feather system will de-activate for the opposite side!
How can the "Auto-Feather" system be dis-armed?
1. De-selecting the "Auto-Feather" switchlight.
2. Retarding one "or" both Power Levers below the "RATING" detent.
3. Automatically after one propeller has already feathered.
At what time would you use the "Alternate Feather" switchlight?
When the Auto-Feather system has failed.
What is accomplished by pressing the respective "#1 or #2 ALT FTHR" switchlight?
The Auxiliary Feathering Pump is activated for 30 seconds.

The Auxiliary Feathering Pump is powered by the opposite sides 28 VDC Bus.
What conditions must be present for the "#1/#2 ALT FTHR" switchlights to be functional?
1. The associated Power Lever must be at Flight Idle.
"AND"
2. The associated Condition Lever must be "at or aft" of the "START & FEATHER" gate.
How is "Manual" feathering accomplished for the propellers?
By selecting the respective Condition Lever to the "START & FEATHER" gate.
The "Propeller Over-speed Governor" (POG) incorporates both a ________ and ________ section.
Hydraulic Section

Electronic Section
How does the "Hydraulic section" of the Propeller Over-speed Governor control the propeller RPM?
It hydraulically controls the blade angle when the propeller RPM exceeds 1,071 RPM by reducing the oil supply.

When the propeller RPM reduces below 1,071 RPM the propeller will return to normal operation.

This cycle will repeat until the condition is resolved.
How does the "Electronic section" of the Propeller Over-speed Governor control the propeller RPM?
It uses FADEC Np overspeed circuitry to signal the FMU to reduce fuel when the propeller speed exceeds 1,122 RPM.
At what time is the "hydraulic section" of the Propeller Over-speed Governor" locked out?
During "reverse" operations.

The "electronic section" becomes the primary protection!
How can the Propeller Over-speed Governor be tested?
It can be tested on the ground using the "PROP O'SPEED GOVERNOR" test switch located on the captain's side console.