Embraer 190 - Engines

Fuel supplied by the airplane fuel tanks flows to the engine fuel pumps. Upon exiting the tanks, the fuel flows through the ____________________ and then divides into two paths. One flows through the high-pressure fuel pump and returns to the fuel tank as motive flow.

• Low-pressure pump

• High-pressure pump

The second flows through the fuel/oil heat exchanger to the ____________________ . The flow leaves the pump and passes through the fuel filter. Once filtered, the fuel flows to the FMU.

• Low-pressure fuel pump

• High-pressure fuel pump

The _______________________________ maintains the oil temperature within an acceptable range and heats the engine fuel to prevent freezing.

• Fuel-cooled oil cooler (FCOC)

• Bleed air heat exchanger

The ______________________ (FMU) , controlled by the FADEC, meters and distributes the proper amount of fuel for combustion to the injectors under all operating conditions.

The fuel filter removes contaminants from the engine fuel. The impending bypass switch indicates _______________ and an imminent bypass condition.

• Fuel filter blockage

• High fuel pressure

The Variable Stator Vanes system consists of two fuel driven actuators controlled by the FADEC via FMU. The purpose of the actuators is to optimize the position of the compressor stators as a function of corrected ____ to provide optimum compressor efficiency.

• EGT

• N2

Each engine has an independent lubrication system. The oil system lubricates and cools the turbine engine main shaft bearings and the accessory gearbox. Oil is pressurized in the _________________ , it then passes through the filter, the fuel-oil heat exchanger and is then divided into several circuits to lubricate the engine.

• Lubrication pump

• Low pressure oil pump

Oil quantity indication is provided for each engine oil tank and is displayed on the MFD. Oil quantity sensors in the __________ detect low oil quantity and trigger the low oil level caution at a specific level.

• Tank

• Line

The pump contains one supply and _____ scavenge pumping elements.

• Two

• Four

The engine starting system consists of a __________________ (ATS).

The engine starting system consists also of a __________________ (SCV).

The _______ opens the Starter Control Valve (SCV), providing bleed air from the APU, a ground source, or the opposite engine. The Air Turbine Starter (ATS) is a turbine that accelerates the engine to a self-sustaining rpm level.

• FADEC

• FMU

The FADEC closes the ______  when the starter cutout speed is reached.

• ATS (Air Turbine Starter)

• SCV (Starter Control Valve)

The FADEC energizes ...

• One igniter for on-ground engine starts and both igniters for in-flight engine starts.

• Both igniter for on-ground engine starts and on igniters for in-flight engine starts.

The FADEC initiates ignition at approximately ...

• 20% N2 and the fuel flow (metering valve opens) from 30% to 35% N2, depending on the engine start altitude.

• 7% N2 and the fuel flow (metering valve opens) from 20% to 25% N2, depending on the engine start altitude.

If no light off is detected within ...

• 15 s of fuel on, FADEC will automatically turn off ignition and fuel, continue dry motoring for 30 s, then turn on both igniters and turn on fuel again.

• 20 s of fuel on, FADEC will automatically turn off ignition and fuel, continue dry motoring for 40 s, then turn on both igniters and turn on fuel again.

Subsequently, if no light off is detected after the reintroduction of fuel, the FADEC will not turn off fuel or ignition and the start must be manually aborted ... ...

• 15 s after the reintroduction of fuel flow or start duty limit, whichever occurs first.

• 30 s after the reintroduction of fuel flow or start duty limit, whichever occurs first.

After a light off occurs, the FADEC commands the starter to cutout at approximately ________ , and commands the FMU fuel metering valve to accelerate the engine to ground idle speed.

• 40% N2

• 50% N2

• 60% N2

Engine ...

• Cross-bleed air or windmilling can be used for in flight engine starts.

• Cross-bleed air, APU bleed air, or windmilling can be used for in flight engine starts.

• APU bleed air or windmilling can be used for in flight engine starts.

An in flight cross-bleed start is identical to an on ground start, but the FADEC automatically controls fuel flow to initiate (Metering valve opens) if _____ has not reached 15% after 15 s.

• N2

• N1

For windmill starting, the SCV configures the pneumatic system. The engine start is controlled by the START/STOP selector knob and the FADEC commands ignition at 7% N2 and fuel flow at a minimum of 7.2% N2, or after _____ , whichever occurs first.

• 15 s

• 30 s

The FADEC has no protection for hot starts, hung starts or failure to light off for in flight engine starts. If no light off is detected within _____ after fuel flow is started, the start should be manually aborted.

• 15 s

• 30 s

The FADEC monitors N2 and automatically turns on both igniters and schedules the relight fuel flow in the event of an engine flameout. In addition a __________ is displayed next to the respective engine N2 and represents an auto relight actuation during the engine auto relight attempts. 

• WML icon

• LMW icon

If the engine relight does not occur within ____ or N2 falls below 7.2% , the automatic relight can be considered unsuccessful and should be manually terminated by moving the START/STOP selector knob to the STOP position.

• 60 s

• 30 s

During ground operations, auto relight attempts are terminated and fuel is shutoff if the engine rpm falls below _____ N2. 

• 52 %

• 32 %

The Thrust Reverser System is ________________ actuated and controlled from the cockpit via the thrust lever. 

The ________ provides an interlock function to protect against inadvertent thrust reverser deployment and also to protect against inadvertent thrust reverser stowing. A locking system consists of two actuator locks and the independent cowl lock. The cowl lock prevents inadvertent deployment of the thrust reverser.

• FADEC

• FMU

Thrust reverser deployment occurs only if the airplane is on the ground. The thrust reverser trigger can be lift up to ____________ after an engine inoperative condition is detected. After 30 seconds the engine inoperative condition does not release the thrust reverse trigger, so the respective thrust lever cannot be moved to reverse position. 

• 30 seconds

• 60 seconds

The FADEC has two identical but isolated channels. One operates as the in-control channel and the other as a standby. The standby channel constantly processes all the data ...

• And is always ready to take control of the engine in case the active channel fails.

• And is not always ready to take control of the engine in case the active channel fails.

The FADEC in-control channel is switched ...

• Manually.

• On every engine start.

 Above approximately 50% N2 the FADEC is powered by the ____________ _____________ ________ (PMA). Below this value or in case the PMA becomes inoperative; the airplane’s electrical system provides the backup power. 

The Automatic Takeoff Thrust Control System (ATTCS) is controlled by the FADEC and is available on ...

• Takeoff and go around.

• Takeoff only

The ATTCS automatically commands RSV whenever it is armed, thrust levers are at TOGA position, and one of following conditions occurs: 

• Difference between both engine N1 values is greater than 15%;

• One engine failure during takeoff;

• One engine failure during go-around;

• Windshear detection.

• All of above

The RSV mode is manually activated by moving the thrust levers to ______ position whenever the ATTCS is armed. 

The minimum flex takeoff thrust is limited to _____ maximum rated takeoff thrust or CLB-2 + 1% N1, whichever is higher.

• 75%

• 95%

Flexible takeoff is possible with ATTCS ...

• ON.

• OFF.

• ON or OFF.

Whenever the ATTCS is triggered, TO-x RSV automatically becomes the maximum ____ , as long as the thrust levers are set to TO/GA.

• N1

• N2

The go around mode is activated in flight whenever the ______________________ .

• Landing gear is up.

• Landing gear is down.

However the go around thrust can be achieved anytime in flight when the thrust rate mode is other than takeoff and the thrust levers are set to _______ .

• TO/GA.

• MAX.

The ________ is the highest engine thrust possible and it is to be used in extreme situations where extra thrust is required when maneuvering for landing.

• CONT

• GA RSV

The maximum continuous thrust is to be used on emergency situation where thrust higher than usual is required. It is the highest thrust the engines can operate ...

• For a given limit of time.

• Continuously without reducing the time between overhauls.

During aircraft power up, _________________________. Whenever the selected takeoff thrust is lower than CLB-1 the CLB-2 mode becomes the default until the next airplane power down / power up.

• CLB-1 is the default mode setting

• CLB- 2 is the default mode setting

Manual switching between the climb modes is possible anytime in flight on the MCDU - TRS page. On ground the CLB-1 mode is inhibited if the take off thrust selected is lower than _____ thrust.

• CLB-1

• CLB-2

The ________ modes are automatically adjusted by the FADEC in order to maintain the minimum thrust necessary to provide the required bleed pressure to the airplane.

• IDLE

• TO/GA

• MAX

Flight Idle ___ varies with altitude and can change as a function of ECS and anti-ice bleed requirements.

• N1

• N2

The idle mode selections are the following: (Check all the correct IDLE MODES) 

• Flight Idle.

• Approach Idle.

• Final Approach Idle.

• Ground Idle.

Whenever ICE CONDITION is sensed the ___ for the FLIGHT IDLE and APPROACH IDLE is automatically increased to maintain the minimum bleed pressure required for the ANTI ICE system operation.

• N1

• N2

With the _______________________ there is no N1 automatic increase but a cyan dash is displayed on both EICAS N1 dial to show the minimum thrust required to maintain the bleed pressure required by the ANTI ICE system.

• APPROACH IDLE

• FINAL APPROACH IDLE