Embraer 190 - Engines

The correct answer is General Electric CF34-10E. This engine is specifically designed for use on regional jet aircraft, such as the Embraer E190 and E195. It is a high-bypass turbofan engine that provides the necessary power to propel the airplane.

The FADEC (Full Authority Digital Engine Control) system has two channels, one serving as the active or in-control channel and the other as the standby channel. The standby channel continuously processes data and is prepared to assume control of the engine if the active channel fails. This redundancy ensures that there is always a backup channel ready to take over in case of any failure, enhancing the safety and reliability of the engine control system.

The FADEC (Full Authority Digital Engine Control) in-control channel is switched on every engine start. This means that every time the engine is started, the FADEC system activates the in-control channel, which is responsible for controlling and managing the engine's performance. This ensures that the engine is properly controlled and monitored during operation.

The FADEC (Full Authority Digital Engine Control) opens the Starter Control Valve (SCV), providing bleed air from the APU, a ground source, or the opposite engine. The FADEC system is responsible for controlling and monitoring various engine functions, including starting the engine. In this case, it opens the SCV to allow bleed air from the APU, ground source, or opposite engine to flow into the Air Turbine Starter (ATS), which is a turbine that accelerates the engine to a self-sustaining rpm level.

The impending bypass switch indicates that there is a fuel filter blockage and an imminent bypass condition. This means that the fuel filter is becoming clogged with contaminants, which can restrict the flow of fuel to the engine. When the filter becomes too blocked, the impending bypass switch is triggered, indicating that the filter needs to be replaced or cleaned to prevent damage to the engine.

The oil quantity sensors in the tank detect low oil quantity and trigger the low oil level caution at a specific level.

If no light off is detected within 15 seconds of fuel being turned on, the FADEC (Full Authority Digital Engine Control) system will automatically turn off the ignition and fuel. It will then continue dry motoring (running the engine without fuel) for 30 seconds. After the dry motoring period, the FADEC system will turn on both igniters and turn on the fuel again. This process is likely a safety measure to prevent any potential issues or malfunctions that may occur if the engine does not start properly within the initial 15-second period.

The FADEC (Full Authority Digital Engine Control) system is responsible for controlling the ignition of the engine. During on-ground engine starts, only one igniter is energized to ignite the engine. However, during in-flight engine starts, both igniters are energized to ensure a reliable ignition in the air. This is because in-flight engine starts can be more challenging due to factors like high altitude and cold temperatures. Therefore, the correct answer is that one igniter is used for on-ground engine starts, and both igniters are used for in-flight engine starts.

The correct answer is WML icon. The WML icon is displayed next to the respective engine N2 when an auto relight actuation occurs during engine auto relight attempts. This icon indicates that the FADEC has automatically turned on both igniters and scheduled the relight fuel flow in response to an engine flameout.

The FADEC (Full Authority Digital Engine Control) system is responsible for controlling and monitoring the engine's parameters, including the thrust reverser. It provides an interlock function to prevent accidental deployment or stowing of the thrust reverser. This is achieved through the use of actuator locks and the independent cowl lock, which work together to ensure that the thrust reverser can only be operated intentionally and safely.

The FADEC (Full Authority Digital Engine Control) system provides engine start protection on the ground by monitoring various parameters. In the case of a hot start, the FADEC prevents the engine from starting if the temperature exceeds a certain limit, preventing damage to the engine. In a hung start, the FADEC detects abnormal engine acceleration and takes corrective actions to ensure a smooth start. Similarly, in the case of no light-off, the FADEC detects if the engine fails to ignite and takes appropriate measures to prevent any damage. Therefore, the FADEC provides protection against hung start, hot start, and no light-off during engine start on the ground.

The second flow of fuel passes through the fuel/oil heat exchanger and then goes to the high-pressure fuel pump. From there, it will continue its journey through the fuel system.

The fuel-cooled oil cooler (FCOC) is responsible for maintaining the oil temperature within an acceptable range and heating the engine fuel to prevent freezing. This component uses the fuel as a cooling medium to regulate the temperature of the oil, ensuring it does not overheat. Additionally, it heats the engine fuel to prevent it from freezing in cold temperatures, which could lead to engine malfunctions. Therefore, the FCOC plays a crucial role in maintaining the proper functioning of the engine by controlling the oil temperature and preventing fuel freezing.

The correct answer is "Takeoff and go around." This means that the Automatic Takeoff Thrust Control System (ATTCS) is used during both the takeoff phase and the go-around phase of a flight. It is controlled by the Full Authority Digital Engine Control (FADEC) system.

The correct answer is 7% N2 and the fuel flow (metering valve opens) from 20% to 25% N2, depending on the engine start altitude. This means that the FADEC (Full Authority Digital Engine Control) system initiates ignition when the engine reaches 7% N2 and adjusts the fuel flow by opening the metering valve to increase the N2 level from 20% to 25%, depending on the altitude at which the engine is started. This ensures proper fuel-air mixture for ignition and optimal engine performance based on the altitude.

Whenever ice conditions are detected, the N1 (fan speed) for the flight idle and approach idle is automatically increased to maintain the minimum bleed pressure required for the anti-ice system to operate effectively. This is necessary to prevent ice from forming on critical parts of the aircraft, such as the engine inlets, which could disrupt airflow and potentially cause engine damage. Increasing the N1 helps to maintain the necessary pressure and ensure the anti-ice system functions properly in icy conditions.

The Variable Stator Vanes system uses fuel driven actuators controlled by the FADEC via FMU to optimize the position of the compressor stators. This optimization is done based on the corrected N2, which is the rotational speed of the high-pressure compressor. By adjusting the position of the stators, the system can provide optimum compressor efficiency, leading to improved engine performance.

The Fuel Metering Unit (FMU), controlled by the FADEC, is responsible for measuring and distributing the correct amount of fuel for combustion to the injectors in all operating conditions. The FMU ensures that the engine receives the appropriate fuel-air mixture for efficient and safe operation.

The correct answer is Air Turbine Starter. The engine starting system consists of an Air Turbine Starter (ATS). An ATS is a device that uses compressed air to start an engine. It is commonly used in aircraft engines and other large engines. The ATS spins the engine's turbine, which in turn starts the engine. It provides a reliable and efficient way to start engines, especially in situations where electric starters may not be suitable or available.

After an engine inoperative condition is detected, the thrust reverser trigger can be lifted up to 30 seconds. However, if after 30 seconds the engine inoperative condition is still present, the thrust reverse trigger will not release, and the respective thrust lever cannot be moved to the reverse position.

If the engine relight does not occur within 30 seconds 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.

The FADEC (Full Authority Digital Engine Control) system is responsible for controlling the fuel flow during engine ground starts. To ensure safe operation, the FADEC will not allow fuel flow if the ITT (Interstage Turbine Temperature) is above a certain temperature. In this case, the FADEC will not allow fuel flow if the ITT is above 120°C. When the pilot sets the START/STOP selector to START, the start control valve opens, but the fuel flow will only begin when the ITT drops below 120°C.

An in-flight cross-bleed start is similar to an on-ground start, with the only difference being that the FADEC (Full Authority Digital Engine Control) automatically regulates the fuel flow to initiate the start if N2 (the rotational speed of the high-pressure spool) has not reached 15% after 15 seconds. N1 (the rotational speed of the low-pressure spool) is not relevant in this context.

After a light off occurs, the FADEC commands the starter to cutout at approximately 50% N2, and commands the FMU fuel metering valve to accelerate the engine to ground idle speed.

The FADEC (Full Authority Digital Engine Control) closes the Starter Control Valve (SCV) when the starter cutout speed is reached. This means that once the engine reaches a certain speed, the SCV is closed, indicating that the starter is no longer needed to start the engine. This helps to ensure the safe and efficient operation of the engine.

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The go around mode is activated in flight whenever the landing gear is down. This means that when the aircraft is in the process of landing and the landing gear is extended, the go around mode can be activated to abort the landing and initiate a climb back into the air.

The engine starting system consists also of a starter control valve (SCV). The SCV is responsible for controlling the flow of fuel to the engine during the starting process. It ensures that the correct amount of fuel is delivered to the engine to facilitate a smooth start. Without the SCV, the engine may not start properly or may experience issues such as flooding or stalling. Therefore, the SCV is an essential component of the engine starting system.

The fuel supplied by the airplane fuel tanks flows through the low-pressure pump before dividing into two paths. One path goes through the high-pressure fuel pump and returns to the fuel tank as motive flow. Therefore, the correct answer is the low-pressure pump.

The IDLE mode is automatically adjusted by the FADEC (Full Authority Digital Engine Control) to maintain the minimum thrust necessary to provide the required bleed pressure to the airplane. This means that when the engine is in idle mode, the FADEC system will automatically adjust the engine's thrust to ensure that the minimum amount of power is being used to maintain the necessary bleed pressure.

The term "GA RSV" refers to the "Go-Around Reserve" thrust. This is the highest engine thrust setting that can be used in emergency situations during landing maneuvers. It is reserved for extreme situations where additional thrust is needed to safely maneuver the aircraft during landing.

When the ATTCS (Autothrust Takeoff/Go-Around Thrust Control System) is activated and the thrust levers are set to TO/GA (Takeoff/Go-Around), the TO-x RSV (Thrust Rating Select Variable) is automatically set to the maximum N1 (Low Pressure Compressor Speed) value. This means that the engine will provide maximum power output for takeoff or go-around operations. N1 represents the rotational speed of the low-pressure compressor in the engine, and setting it to the maximum ensures optimal performance during these critical phases of flight.

The minimum flex takeoff thrust is limited to 75% of the maximum rated takeoff thrust or CLB-2 + 1% N1, whichever is higher. This means that the flex takeoff thrust cannot be lower than 75% of the maximum rated takeoff thrust.

The correct answer is 15 s. The explanation for this answer is that the FADEC (Full Authority Digital Engine Control) commands ignition at 7% N2 and fuel flow at a minimum of 7.2% N2. The phrase "whichever occurs first" suggests that either the ignition or the fuel flow will occur first. Therefore, if the fuel flow reaches a minimum of 7.2% N2 before 15 seconds, the engine start will be controlled by the FADEC. If not, the engine start will be controlled by the START/STOP selector knob.

The correct answer is N1. N1 refers to the low-pressure compressor speed, which is a measure of the engine power output. In flight, the N1 setting can vary with altitude and can change based on the requirements of the aircraft's environmental control system (ECS) and anti-ice bleed. Therefore, N1 is the correct answer as it accurately reflects the statement provided.

During aircraft power up, the default mode setting for thrust is CLB-1. However, if the selected takeoff thrust is lower than CLB-1, the default mode setting becomes CLB-2 until the next power down/power up of the airplane.

During engine start, if the ITT (Interstage Turbine Temperature) reaches its limit, the FADEC (Full Authority Digital Engine Control) system automatically shuts off the fuel flow to abort the start sequence. However, the start control valve is not automatically closed in this situation. Therefore, pilot intervention is required to manually close the starter control valve by selecting the START/STOP switch to STOP. This ensures that the fuel flow is completely stopped and prevents any potential damage to the engine. The correct answer is SCV, which stands for starter control valve.

Whenever N2 reaches 102%, the FADEC automatically commands an engine shutdown. This indicates that the engine is operating at a speed beyond its maximum limit, which can lead to potential damage or failure. Therefore, the FADEC system intervenes to protect the engine by shutting it down.

The correct answer is "all of above". This means that the ATTCS (Autothrust Takeoff and Go-Around Control System) will automatically command the RSV (Reverse Thrust) in all of the mentioned conditions. These conditions include a difference between both engine N1 values greater than 15%, one engine failure during takeoff or go-around, and windshear detection. In each of these situations, the ATTCS will activate the RSV to ensure the appropriate response and control of the aircraft.

The correct answer is 1200. The Final Approach Idle is active when the altitude is lower than 1200 feet above ground level (AGL), landing flaps are deployed, and the landing gear is down. This setting is used during the final approach phase of landing.

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The Thrust Reverser System is hydraulically actuated and controlled from the cockpit via the thrust lever. This means that the system uses hydraulic power to activate and control the thrust reversers, which are used to redirect the thrust of the engines during landing to help slow down the aircraft. The pilot can control the activation and intensity of the thrust reversers by manipulating the thrust lever in the cockpit.

The explanation for the correct answer "ON or OFF" is that flexible takeoff is possible with ATTCS in either of these two modes. The system can be turned on or off depending on the specific requirements or conditions of the takeoff. This flexibility allows for greater adaptability and customization in the takeoff process, ensuring optimal performance and safety.

Above approximately 50% N2, the FADEC (Full Authority Digital Engine Control) is powered by the Permanent Magnet Alternator (PMA). Below this value, or if the PMA becomes inoperative, the airplane's electrical system provides the backup power.

The maximum continuous thrust is the highest level of thrust that the engines can operate at continuously without reducing the time between overhauls. This means that the engines can maintain this level of thrust for an extended period of time without causing any damage or reducing their overall lifespan. It is important to have this capability in emergency situations where a higher level of thrust is needed for a sustained period of time.

During ground operations, auto relight attempts are terminated and fuel is shut off if the engine rpm falls below 52% N2.

The correct answer is TO/GA. The question is asking for the condition in which the go around thrust can be achieved anytime in flight. The answer is TO/GA, which stands for Takeoff/Go-Around. This means that when the thrust rate mode is not in takeoff mode and the thrust levers are set to TO/GA, the go around thrust can be achieved.

During final approach idle, there is no automatic increase in N1 (fan speed) but a cyan dash is displayed on both EICAS N1 dials. This cyan dash indicates the minimum thrust required to maintain the bleed pressure needed for the ANTI ICE system. This means that the engines are operating at a low power setting to maintain the necessary pressure for the anti-ice system without any automatic increase in thrust. Therefore, the correct answer is "FINAL APPROACH IDLE".

The ITT limit, which is controlled by the FADEC, is not a fixed value but rather varies depending on the phase of engine operation. This means that the ITT limit can change during engine start and throughout engine operation. The specific values for the ITT limit are specified in the aircraft operating limitations, ensuring that the engine operates within safe temperature limits for each phase of operation.

If three consecutive overspeed detection events occur within 30 seconds, the Full Authority Digital Engine Control (FADEC) will not relight the engine. This indicates that the engine has experienced a potentially dangerous overspeed condition, and the FADEC system is designed to prevent further damage by not relighting the engine.