Boeing B737 MAX - Engines

Any time the REVERSER light illuminates for more than _____, a malfunction has occured and the MASTER CAUTION and ENG system annunciator lights illuminate.

15 seconds

10 seconds

12 seconds

20 seconds

Correct! Wrong!

Engine Fail (ENG FAIL) Alert is displayed amber when:

Engine operating below sustainable idle (less than 56% N2 in flight).

Engine operating below sustainable idle (less than 50% N2 in flight / 60% on ground).

Engine operating below sustainable idle (less than 50% N2); and engine start lever in IDLE position.

Engine malfunction is detected by the EEC.

Correct! Wrong!

The EEC drives all engine indications except:

Oil temperature, pressure & quantity indications.

Oil quantity & engine vibration

Oil temperature & engine vibration

Fuel flow & oil pressure

Correct! Wrong!

Following shutdown of both engines, the EGT box turns amber to remind the crew of the exceedance.

False.

True

Correct! Wrong!

Following shutdown of both engines, the EGT box turns red to remind the crew of the exceedance.

If an impending hot start is detected by _____, the white box surrounding the EGT digital readout flashes white.

anEGT approaching the start limit, or a compressor stall occurs

A rapid rise in EGT or EGT approaching the start limit, or a compressor stall occurs

EGT approaching the start limit

a rapid rise in EGT or EGT approaching the start limit, or a compressor stall occurs or a fire.

Correct! Wrong!

What does the REVERSER LIMITED light on the engine panel indicate?

Thrust reverser will not deploy or reverse thrust will be limited if commanded.

Thrust reverser will not deploy or reverse thrust will be limited to idle if commanded.

Thrust reverser will deploy but reverse thrust will be limited to idle if commanded.

Correct! Wrong!

Thrust reverser - A pause of approximately _____ engages the electro-mechanical lock and prevents the thrust reverserrnsleeves from further movement. Cycling the thrust reversers may clear the fault and restore normal operation.

10 seconds

8 seconds

5 seconds

18 seconds

Correct! Wrong!

The thrust reverser can be deployed when:

Either radio altimeter senses less than 10 feet altitude, or when the air/ground safety sensor is in the ground mode.

Radio altimeter senses less than 20 feet altitude, and when the air/ground safety sensor is compressed.

Either radio altimeter senses less than 20 feet altitude, or when the air/ground safety sensor is in the ground mode (main landing gear on ground).

Radio altimeter senses less than 10 feet altitude, and when the air/ground safety sensor is in the ground mode.

Correct! Wrong!

Movement of the reverse thrust levers is mechanically restricted until the forward thrust levers are in the idle position.

The full rated takeoff thrust for the installed engine is available at a thrust lever position equals to the forward stop.

True.

False.

Correct! Wrong!

The full rated takeoff thrust for the installed engine is available at a thrust lever position less than the forward stop.

The EEC provides N1 and N2 redline overspeed protection in both normal and alternate modes. The EGT limit must be observed by the crew because the EEC does not provide EGT redline exceedance protection.

False.

True.

Correct! Wrong!

Primary and secondary engine indications are displayed in compact format on the upper DU when the secondary engine indications are selected for display (manually or automatically) and the lower DU is unavailable.

True.

False.

Correct! Wrong!

Thrust reverser - Any time the REVERSER light illuminates for more than approximately _____, a malfunction has occurred and the MASTER CAUTION and ENG system annunciator lights illuminate.

15 seconds

12 seconds

20 seconds

5 seconds

Correct! Wrong!

An auto-relight capability is provided for flame-out protection. Whenever the EEC detects an engine flameout, both igiters are activated. A flameout is detected when:

An uncommanded rapid decrease in N1 occurs or N2 is below idle RPM or EGT is below 200 deg.C

An uncommanded rapid decrease in N2 occurs or N2 is below idle RPM

An uncommanded rapid decrease in N1 occurs or N2 is below idle RPM

An uncommanded rapid decrease in N1 occurs

Correct! Wrong!

During battery start with no power on the airplane, only N1 and oil quantity are available.

True.

False.

Correct! Wrong!

During battery start with no power on the airplane, only N1, N2, and oil quantity are available.

The Starter Cutout speed i

Approximately 50%.

25%.

Approximately 56%.

46%.

Correct! Wrong!

Once activated, the DC operated fuel pump operates automatically until:

Once the APU is at governed speed, ready to acceptable load

An AC fuel pump pressurizes the manifold

The completion of the APU start cycle

APU shutdown

Correct! Wrong!

If blinking, the START VALVE OPEN alert indicates:

that the respective engine start valve is open and air is supplied to starter.

an uncommanded closing of start valve or air is not supplied to the starter.

Air is not supplied to the starter.

An uncommanded opening of start valve.

Correct! Wrong!

Secondary Engine Indications - Secondary engine indications are displayed when CDS initially receives power when selected by the Multi-Function Display (MFD) but also when:

In flight when an engine start lever moved to CUTOFF / when an engine fails or when a secondary engine parameter exceeds normal operating range.

In flight when an engine start lever moved to CUTOFF or when a secondary engine parameter exceeds normal operating range.

A secondary engine parameter exceeds normal operating range.

An engine start lever moved to CUTOFF or when a secondary engine parameter exceeds normal operating range.

Correct! Wrong!

The EEC automatically selects ground minimum idle, flight minimum idle and approach idle. Approach idle is selected in flight:

If flaps are greater than 1 or engine & wing anti-ice are ON

Below approximately 12000 ft

If flaps are in landing configuration or engine anti-ice is ON for either engine

Below 1500 ft, f flaps are greater than 1 or engine anti-ice is ON

Correct! Wrong!

This higher % RPM improves engine acceleration time in the event of a go-around.

Approach idle is maintained:

Until 84 KIAS

Until after touchdown, when ground minimum idle is selected.

- Until after touchdown (60 KIAS)

Until Reverser selection

Correct! Wrong!

What does the REVERSER AIR/GRD light on the engine panel indicate?

The air/ground thrust reverser logic has failed.

The air/ground thrust reverser logic has failed and thrust reversers will deploy in flight if commanded.

The air/ground thrust reverser logic has failed and thrust reversers will not deploy on ground if commanded.

Correct! Wrong!

When the engine Start Levers are placed in the CUTOFF position:

t closes both spar and engine fuel shutoff valves.rnIt also deenergizes the EECs.

It closes the engine fuel shutoff valves and it de-energizes the EECs.

It closes both spar and engine fuel shutoff valves.

It closes both spar and engine fuel shutoff valves.and de-energizes ignition system.

Correct! Wrong!

Electronic Engine Control (EEC) Switches - Both ON and ALTN may be in view if EEC has automatically switched to soft alternate mode.

False.

True.

Correct! Wrong!

An oil quantity indication as low as zero is normal if windmilling N2 RPM is below approximately 8%.

False.

True.

Correct! Wrong!

Ignition is normally OFF. Both igniters are activated when engine start lever is in IDLE and:

An uncommanded rapid decrease in N2 occurs or N2 is between idle and 8%.

An uncommanded rapid decrease in N2 occurs or, N2 is between idle% and 10%.

An uncommanded rapid decrease in N2 occurs or in flight only N2 is between idle and 5%.

An uncommanded rapid decrease in N2 occurs or, N2 is between 57% and 50% or, in flight N2 is between idle and 5%.

Correct! Wrong!

Idle Operation - The EEC automatically selects ground minimum idle, flight minimum idle, and approach idle. In flight, if a fault prevents the EEC from receiving flap or anti-ice signals, approach idle schedule begins:

Below 10,000 feet MSL.

Below 15,000 feet MSL.

Below 5,000 feet MSL.

Below 20, 000 feet MSL.

Correct! Wrong!

The ENGINE CONTROL Light is illuminated (amber). Light operates when:

Engine is operating and, airplane is either on ground or in flight but below 2500 ft RA.

Engine is operating and, airplane is either on ground with a speed at or less of 80 kt or in flight but below 2500 ft RA.

Engine is operating and, airplane on ground and is below 80 kts prior to takeoff or, approximately 30 seconds after touchdown.

Engine is operating and, airplane is either on ground or in flight but below 500 ft RA.

Correct! Wrong!

The EEC must receive electrical power to supply engine operating data to the flight deck engine indications. When the EEC is not powered, N1, N2, oil quantity and engine vibration are displayed directly from the engine sensors.

True.

False.

Correct! Wrong!

The EEC provides redline overspeed protection for:

N1 and N2 in the normal mode only

N1 only in both the normal and alternate modes

N2 only in both the normal and alternate modes

N1 & N2 in both the normal and alternate modes.

Correct! Wrong!

The REVERSER light, located on the aft overhead panel, illuminates when the thrust reverser is commanded to stow and extinguishes 10 seconds later when the isolation valve closes.

True

False

Correct! Wrong!

The EGT display, both box & dial, turn red and the EEC automatically turns off ignition and shut off fuel to the engine if:

An impending hot start is detected during ground starts

An impending hot start is detected during ground starts or in flight starts

The EGT exceeds the starting limit during ground or in flight starts.

The EGT exceeds the starting limit during ground starts

Correct! Wrong!

After a LOSS THRUST ON BOTH ENGINES, in moderate to heavy rain, it may take up to ______ to accelerate to idle.

3 minutes

30 seconds

2 minutes

60 seconds

Correct! Wrong!

Any engine crew alert on the inboard DU will blink when?

For 10 seconds.

For 10 seconds and then the alert only will remain steady until the condition no longer exists.

Until the condition no longer exists.

Correct! Wrong!

Electronic Engine Control (EEC) Switches - When ALTN is in view (amber), what does it mean?

This indicates that EEC has automatically switched to alternate control mode.

This indicates that EEC has been manually switched to alternate control mode.

This indicates that EEC has automatically switched to alternate control mode or it has been selected manually.

This indicates that EEC has automatically switched to alternate control mode or it has been selected manually. EEC provides rated thrust or higher.

Correct! Wrong!

Thrust reverser - A pause in movement of the reverse thrust levers past detent No. 1 toward the stow position may cause MASTER CAUTION and ENG system annunciator lights to illuminate.

True.

False.

Correct! Wrong!

Engine oil pressure is in the yellow band at idle power. Which of the following is true?

Undesirable, and permitted obly for the completion of the flight, preferably at reduced thrust setting

Unsafe and requires that the engine be shut down as soon as possible.

Acceptable, no action is necessary.

Normal, but requires continuous monitoring of the oil temperature

Correct! Wrong!

Auto-relight is provided for flameout protection, with the EEC activating both igniters. Which of the following situations would cause Flameout Protection to operate?

Rapid decrease in N2 and N2 below idle RPM

Rapid decrease in N2, or N2 below idle RPM

Rapid decrease in N2, and low oil pressure

Rapid decrease in N2

Correct! Wrong!

EEC alternate mode thrust is always equal to or greater than normal mode thrust for the same thrust lever position.

False

True

Correct! Wrong!

Movement of reverse thrust lever into reverse thrust engages locking pawl preventing forward thrust lever from moving. Terminating reverse thrust removes locking pawl and restores forward thrust lever movement ability.

True.

False.

Correct! Wrong!

During an engine start , when the engine start lever is positioned to IDLE detent,the SPAR VALVE CLOSED light transitions from dim, to bright and then extinguishes.

False

True

Correct! Wrong!

OIL FILTER BYPASS Alert - Blinking is inhibited:

During takeoff from 80 knots to 400 feet RA, or 30 seconds after reaching 80 knots, whichever occurs first. During landing below 200 feet RA until 30 seconds after touchdown.

During takeoff from 80 knots to 400 feet RA. During landing below 200 feet RA until 30 seconds after touchdown.

During takeoff from 80 knots to 400 feet RA

During takeoff from 80 knots to 400 feet RA, or 30 seconds after reaching 80 knots.

Correct! Wrong!

During periods when blinking is inhibited, alerts illuminate steady.

If the ENGINE CONTROL Light is illuminated (amber), engine control system is degraded due to faults in system but it is still dispatchable.

True.

False.

Correct! Wrong!

The DUAL BLEED light illuminates whenever the APU bleed air valve is open and the position of the engine bleed air switches and isolation valve would permit possible backpressure of the APU. Therefore, thrust must be limited to idle with the DUAL BLEED light illuminated.

False.

True.

Correct! Wrong!

EEC Alternate Mode - The EEC can operate in either of two alternate modes, soft or hard. If required signals are not available to operate in the normal mode, the EEC automatically changes to the soft alternate mode. The soft alternate mode remains until the hard alternate mode is entered by:

Either retarding the thrust lever to idle or manually selecting ALTN with the EEC switch on the aft overhead panel.

Manually selecting ALTN with the EEC switch on the aft overhead panel.

Manually selecting ALTN with the EEC switch on the aft overhead panel before retarding the thrust lever to idle.

Retarding the thrust lever to idle and manually selecting ALTN with the EEC switch.

Correct! Wrong!

If the Exhaust Gas Temperature (EGT) readout is white-blinking Displayed EEC senses conditions that may lead to hot start orrnstall during ground starting.

False.

True.

Correct! Wrong!

During a normal engine start:

The EEC is not powered until the engine accelerates to a speed greater that 15% N2

Only round dials are visible for engine indications prior to placing the engine start switch to GND

Only N1, N2, oil quantity and engine vibration are available prior to placing the engine start switch to GND

Only oil quantity and engine vibration are available prior to placing the engine start switch to GND

Correct! Wrong!

If a MOTORING indication appears on the N2 display during engine start:

This is normal and Bowed Rotor Motoring logic is active during engine start on the ground

Move the start lever to CUTOFF and motor the engine for 60 seconds.

Move the start lever to CUTOFF and after N2 decreases below 20% motor the engine for 60 seconds.

Correct! Wrong!

During battery start, when does the EEC become energized?

Above 25% N1

When positioning the start switch to GND

N2 greater than 15%

When start lever is raised to idle

Correct! Wrong!

Thrust Reverser - When the standby system is used, the affected thrust reverser deploys and retracts at a normal rate, but some thrust asymmetry can be anticipated.

False.

True.

Correct! Wrong!

When the standby system is used, the affected thrust reverser deploys and retracts at a slower rate and some thrust asymmetry can be anticipated.

Which hydraulic system normally powers the thrust reversers?

System A

System B

System A for engine No.1 and system B for Engine No.2

System A for engine No.2 & system B for Engine No.1

Correct! Wrong!

The EEC is not powered until the engine accelerates to a speed greater than _____.

15% N2 or 25% N1

15% N2.

15% N1.

25% N1.

Correct! Wrong!

CONT provides ignition to selected igniters when engine is operating and engine start lever is in IDLE.

In flight CONT provides ignition to both igniters when N2 is below idle.

In flight CONT provides ignition to both igniters when N2 is below idle and engine start lever is in IDLE.

CONT provides ignition to both igniters when N2 is below idle and engine start lever is in IDLE.

CONT provides ignition to both igniters at all time.

Correct! Wrong!

FLT = provides ignition to both igniters when engine start lever is in IDLE.

Oil Pressure (OIL PRESS) Readout displays engine oil pressure in psi. It is displayed amber when the operating limit is reached.

True.

False.

Correct! Wrong!

It is displayed amber to show a caution range. It is displayed red when the operating limit is reached.

Inflight Starting - If crossbleed starting is required, the X-BLD indication (XB for the compact engine display) is displayed above the N2 dial. This indication is based on:

Airplane altitude, airspeed and N2.

Airplane altitude, airspeed, N2 and temperature.

Airplane altitude, airspeed, N2, altitude pressure and temperature.

airplane altitude, airspeed, N2 and altitude pressure

Correct! Wrong!

The crew alert of FUEL FLOW on the inboard DU when steady indicates:

Engine fuel flow is abnormally low when compared to the FMC expected fuel flow.

Engine fuel flow is abnormally high or low when compared to the FMC expected fuel flow.

Engine fuel flow is abnormally high when compared to the FMC expected fuel flow.

Correct! Wrong!

Inflight Starting - If only the EGT redline is shown, this is the inflight start EGT limit. If both the EGT redline and the EGT start limit redline are shown, the start limit redline is the inflight start EGT limit for all engine starts.

False.

True.

Correct! Wrong!

Reverse thrust lever is blocked at reverse idle position until related thrust reverser is more than _____ deployed.

50%

30%

60%

25%

Correct! Wrong!

The REVERSER COMMAND light on the engine panel indicates:

The reverse thrust lever is not in the commanded position.

That reverse thrust must not be selected.

The reverse thrust lever is not in the down position in flight.

Correct! Wrong!

EEC Alternate Mode - Loss of either DEU results in a loss of signal to either a single or both EECs. The EEC ALTN lights illuminate and each EEC reverts to the alternate mode to prevent the engines from operating on a single source of data.

True.

False.

Correct! Wrong!

Loss of either DEU results in a loss of signal to either a single or both EECs.

The airborne vibration monitoring (AVM) system monitors engine vibration levels. Its primary function is the display of low and high pressure rotor synchronous vibration on the secondary engine display. The AVM is also used to balance the low pressure rotor. Balancing reduces high vibration indication or audible noise and tactile vibration.

False.

True

Correct! Wrong!

What are the indications that the engine starter has disengaged?

Start switch rotates to OFF and N2 RPM is stabilized (FUEL LOW PRESSURE extinguishes).

The start switch automatically returns to OFF, and the START VALVE OPEN light extinguishes

The fuel LOW PRESSURE lights extinguish with N1 RPM 56%

An immediate increase in the N1 indication due to closure of the compressor bleed valves

Correct! Wrong!

The crew alert of THRUST on the inboard DU when steady indicates:

The thrust is less than the commanded thrust.

The thrust is more or less than the commanded thrust.

The thrust is more than the commanded thrust.

Correct! Wrong!

Each engine has two igniter plugs. The EEC arms the igniter plug(s) selected by the ignition select switch. The left igniter plug receives power from the associated AC transfer bus. The right igniter plug receives power from the AC standby bus.

False.

True.

Correct! Wrong!

At low N2 values, the oil scavenge pump may not provide enough pressure to return oil to the tank, causing a low quantity indication. Normal oil quantity should be indicated after start.

True.

False.

Correct! Wrong!

The amber DUAL BLEED light is illuminated before starting engines. What should the flight crew do?

Use a pneumatic ground cart for starting engines.

Do not start the engines and call maintenance.

Shut down the APU or disconnect the pneumatic ground cart.

Nothing, this is normal condition.

Correct! Wrong!

Electronic Engine Control (EEC) Switches - When ON is not in view, this means that the EEC has been autmotically switched to the alternate mode.

False.

True.

Correct! Wrong!

When ON is not in view, this means that the EEC has been manually selected to the alternate mode.

Each engine has two igniter plugs. The EEC arms the igniter plug(s) selected by the ignition select switch. The Left igniter plug receives power from the DC Standby bus while the Right igniter plug receives power from the AC standby bus.

False

True

Correct! Wrong!

The Left igniter receives power from the associated transfer bus.

Engine Start Levers - IDLE position

Energizes ignition system through FADEC. Electrically opens spar fuel shutoff valve in the wing leading edge outboard of the pylon. Electrically opens engine mounted fuel shutoff valve via the EEC.

Energizes ignition system through EEC. Electrically opens spar fuel shutoff valve in the wing leading edge outboard of the pylon. Electrically opens engine mounted fuel shutoff valve via the EEC.

Energizes ignition system through FADEC. Electrically opens spar fuel shutoff valve and engine mounted fuel shutoff valve.

Energizes ignition system through EEC. Electrically opens spar fuel shutoff valve in the wing leading edge outboard of the pylon.

Correct! Wrong!

If the Electronic Engine Control (EEC) switch as a white ON in view, this means that:

EEC has been manually selected to the alternate mode

EEC has automatically switched to alternate control mode or it has been selected manually

Normal control mode is selected. Engine ratings calculated by EEC are from sensed atmospheric conditions and bleed air demand.

EEC has been automatically selected to the alternate mode

Correct! Wrong!

If a wet start is detected, the EEC will automatically turn off ignition & shut off fuel to the engine:

10 seconds on the ground or 30 seconds in flight after the start lever is moved to idle

No automatic shutdown is provided for a wet start.

15 seconds after the start lever is moved to idle during ground starts

15 seconds after the start valve opens during ground starts

Correct! Wrong!

A wet start occurs if the EGT does not rise after the start lever is moved to IDLE.

Boeing 737 Max - Engines

Quiz

Boeing B737 MAX - Engines

Any time the REVERSER light illuminates for more than _____, a malfunction has occured and the MASTER CAUTION and ENG system annunciator lights illuminate.

Engine Fail (ENG FAIL) Alert is displayed amber when:

The EEC drives all engine indications except:

Following shutdown of both engines, the EGT box turns amber to remind the crew of the exceedance.

If an impending hot start is detected by _____, the white box surrounding the EGT digital readout flashes white.

What does the REVERSER LIMITED light on the engine panel indicate?

Thrust reverser - A pause of approximately _____ engages the electro-mechanical lock and prevents the thrust reverserrnsleeves from further movement. Cycling the thrust reversers may clear the fault and restore normal operation.

The thrust reverser can be deployed when:

The full rated takeoff thrust for the installed engine is available at a thrust lever position equals to the forward stop.

The EEC provides N1 and N2 redline overspeed protection in both normal and alternate modes. The EGT limit must be observed by the crew because the EEC does not provide EGT redline exceedance protection.

Primary and secondary engine indications are displayed in compact format on the upper DU when the secondary engine indications are selected for display (manually or automatically) and the lower DU is unavailable.

Thrust reverser - Any time the REVERSER light illuminates for more than approximately _____, a malfunction has occurred and the MASTER CAUTION and ENG system annunciator lights illuminate.

An auto-relight capability is provided for flame-out protection. Whenever the EEC detects an engine flameout, both igiters are activated. A flameout is detected when:

During battery start with no power on the airplane, only N1 and oil quantity are available.

The Starter Cutout speed i

Once activated, the DC operated fuel pump operates automatically until:

If blinking, the START VALVE OPEN alert indicates:

Secondary Engine Indications - Secondary engine indications are displayed when CDS initially receives power when selected by the Multi-Function Display (MFD) but also when:

The EEC automatically selects ground minimum idle, flight minimum idle and approach idle. Approach idle is selected in flight:

Approach idle is maintained:

What does the REVERSER AIR/GRD light on the engine panel indicate?

When the engine Start Levers are placed in the CUTOFF position:

Electronic Engine Control (EEC) Switches - Both ON and ALTN may be in view if EEC has automatically switched to soft alternate mode.

An oil quantity indication as low as zero is normal if windmilling N2 RPM is below approximately 8%.

Ignition is normally OFF. Both igniters are activated when engine start lever is in IDLE and:

Idle Operation - The EEC automatically selects ground minimum idle, flight minimum idle, and approach idle. In flight, if a fault prevents the EEC from receiving flap or anti-ice signals, approach idle schedule begins:

The ENGINE CONTROL Light is illuminated (amber). Light operates when:

The EEC must receive electrical power to supply engine operating data to the flight deck engine indications. When the EEC is not powered, N1, N2, oil quantity and engine vibration are displayed directly from the engine sensors.

The EEC provides redline overspeed protection for:

The REVERSER light, located on the aft overhead panel, illuminates when the thrust reverser is commanded to stow and extinguishes 10 seconds later when the isolation valve closes.

The EGT display, both box & dial, turn red and the EEC automatically turns off ignition and shut off fuel to the engine if:

After a LOSS THRUST ON BOTH ENGINES, in moderate to heavy rain, it may take up to ______ to accelerate to idle.

Any engine crew alert on the inboard DU will blink when?

Electronic Engine Control (EEC) Switches - When ALTN is in view (amber), what does it mean?

Thrust reverser - A pause in movement of the reverse thrust levers past detent No. 1 toward the stow position may cause MASTER CAUTION and ENG system annunciator lights to illuminate.

Engine oil pressure is in the yellow band at idle power. Which of the following is true?

Auto-relight is provided for flameout protection, with the EEC activating both igniters. Which of the following situations would cause Flameout Protection to operate?

EEC alternate mode thrust is always equal to or greater than normal mode thrust for the same thrust lever position.

Movement of reverse thrust lever into reverse thrust engages locking pawl preventing forward thrust lever from moving. Terminating reverse thrust removes locking pawl and restores forward thrust lever movement ability.

During an engine start , when the engine start lever is positioned to IDLE detent,the SPAR VALVE CLOSED light transitions from dim, to bright and then extinguishes.

OIL FILTER BYPASS Alert - Blinking is inhibited:

If the ENGINE CONTROL Light is illuminated (amber), engine control system is degraded due to faults in system but it is still dispatchable.

The DUAL BLEED light illuminates whenever the APU bleed air valve is open and the position of the engine bleed air switches and isolation valve would permit possible backpressure of the APU. Therefore, thrust must be limited to idle with the DUAL BLEED light illuminated.

EEC Alternate Mode - The EEC can operate in either of two alternate modes, soft or hard. If required signals are not available to operate in the normal mode, the EEC automatically changes to the soft alternate mode. The soft alternate mode remains until the hard alternate mode is entered by:

If the Exhaust Gas Temperature (EGT) readout is white-blinking Displayed EEC senses conditions that may lead to hot start orrnstall during ground starting.

During a normal engine start:

If a MOTORING indication appears on the N2 display during engine start:

During battery start, when does the EEC become energized?

Thrust Reverser - When the standby system is used, the affected thrust reverser deploys and retracts at a normal rate, but some thrust asymmetry can be anticipated.

Which hydraulic system normally powers the thrust reversers?

The EEC is not powered until the engine accelerates to a speed greater than _____.

CONT provides ignition to selected igniters when engine is operating and engine start lever is in IDLE.

Oil Pressure (OIL PRESS) Readout displays engine oil pressure in psi. It is displayed amber when the operating limit is reached.

Inflight Starting - If crossbleed starting is required, the X-BLD indication (XB for the compact engine display) is displayed above the N2 dial. This indication is based on:

The crew alert of FUEL FLOW on the inboard DU when steady indicates:

Inflight Starting - If only the EGT redline is shown, this is the inflight start EGT limit. If both the EGT redline and the EGT start limit redline are shown, the start limit redline is the inflight start EGT limit for all engine starts.

Reverse thrust lever is blocked at reverse idle position until related thrust reverser is more than _____ deployed.

The REVERSER COMMAND light on the engine panel indicates:

EEC Alternate Mode - Loss of either DEU results in a loss of signal to either a single or both EECs. The EEC ALTN lights illuminate and each EEC reverts to the alternate mode to prevent the engines from operating on a single source of data.

What are the indications that the engine starter has disengaged?

The crew alert of THRUST on the inboard DU when steady indicates:

Each engine has two igniter plugs. The EEC arms the igniter plug(s) selected by the ignition select switch. The left igniter plug receives power from the associated AC transfer bus. The right igniter plug receives power from the AC standby bus.

At low N2 values, the oil scavenge pump may not provide enough pressure to return oil to the tank, causing a low quantity indication. Normal oil quantity should be indicated after start.

The amber DUAL BLEED light is illuminated before starting engines. What should the flight crew do?

Electronic Engine Control (EEC) Switches - When ON is not in view, this means that the EEC has been autmotically switched to the alternate mode.

Each engine has two igniter plugs. The EEC arms the igniter plug(s) selected by the ignition select switch. The Left igniter plug receives power from the DC Standby bus while the Right igniter plug receives power from the AC standby bus.

Engine Start Levers - IDLE position

If the Electronic Engine Control (EEC) switch as a white ON in view, this means that:

If a wet start is detected, the EEC will automatically turn off ignition & shut off fuel to the engine: