Phenom 300 - Engine
Dry motoring required for maintenance and purging purposes can be made according to the correct selection of ENG IGNITION switch input to the FADEC. Dry motoring is performed by setting the ENG IGNITION switch to OFF, while the engine is in Shutdown state, and by setting the ENG START/STOP knob to START.
During an AUTO RELIGHT the FADEC continuously monitors the engine parameters and automatically turns on both igniters and schedules the relight fuel flow in case an engine flameout is detected, and the ENG START/STOP knob is out of STOP position. The FADEC will attempt to relight the engine until N2 drops below _____or the ENG START/STOP knob is moved to the STOP position.
The Fuel Flow Meter (FFT) is installed on the front by pass duct and receives pressurized fuel directly from the FMU proportional module. It measures flow rate per hours. In case of failure of the FFT lines:
In this condition, the FADEC commands the FMU internal valves (located upstream of the FFT lines) to close the fuel feed to the engine, thus preventing escape of excessive quantity of fuel.
The Permanent Magnet Alternator (PMA) is a dual wound, three-phase alternator, which is contained inside the Gearbox and driven by the same shaft that drives both low and high-pressure fuel pumps. It consists of a rotor assembly and a stator housing assembly.
The PMA is a dual wound, three-phase alternator, which is contained inside the Fuel Metering Unit (FMU)and driven by the same shaft that drives both low and high-pressure fuel pumps. It consists of a rotor assembly and a stator housing assembly.
MFD - The yellow boxed FAIL indication is displayed on the center of the N1 dial when one engine has been flamed out or shut down in flight by pilot action.
The yellow boxed FAIL indication is displayed on the center of the N1 dial when one engine has been flamed out or shut down without pilot action. The cyan OFF indication is displayed when the engine is shut down in flight by pilot action.
When the ENG START/STOP knob is set to START and the ENG IGNITION switch is set to OFF, the Dry Motoring is limited to:
ENG IGNITION SWITCH – What is the true statement about the ON position?
The in-flight assisted starting is identical to an on ground starting, but the FADEC automatically actuates both igniters during starting and disables the abort starting logic. In this case, the decision on whether to abort an unsuccessful starting is at the pilot’s discretion.
After an unsuccessful try of shutting down the engine, the pilot need to recycle the ENG START/STOP knob (set to the RUN then to STOP position again) and position the TLA at idle within _____.
MFD INTERTURBINE TEMPERATURE INDICATION – What is the true statement about the ITT yellow pointer?
During ground starts, if the yellow line is exceeded, the flight crew must shut the engine down.
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The Engine Fuel System consists of five major components: Fuel Metering Unit (FMU), integrated fuel manifold and nozzles assembly, Fuel/Oil Heat Exchanger (FOHE), fuel filter, and Fuel Flow Meter (FFT).
The FMU controls and meters the fuel flow from the airframe to the engine nozzles. Fuel is supplied from the airframe tank up the centrifugal boost-pump. Pressurized fuel is then ported to the externally mounted FOHE for heating and to the fuel filter for filtering. When it returns to the FMU, the fuel is forwarded by the high-pressure gear pump through the proportional module before circulation into the externally mounted fuel flow meter. After returning to the FMU, the flow divider and shutoff valve assembly provides metered fuel to the integrated fuel manifold and then to the fuel nozzles.
ENG IGNITION SWITCH – The OFF position deactivates the ignition system.
The MFD ITT red line is:
The FADEC will abort a ground starting when:
On ground starting is aborted by the FADEC if the ITT reaches 720 deg.C (1328 deg.F) to minimize risks of mechanical damages to the engine or the airplane.
The FADEC will abort a ground starting when:
TO/GA is the highest thrust rating available with all engines operating normally considering the thrust levers at TO/GA position during a takeoff or go-around and is limited to _____ during the takeoff/go-around phase.
The fuel filter removes contaminants from the engine fuel.
It is filtrated from the outside to the center core of the element and then exits the assembly to feed the high-pressure fuel pump.
ENG START/STOP KNOB - The STOP position commands:
When the starting is aborted by the FADEC, fuel flow is automatically cut off but ignition is to be turned off by the flight crew.
When the starting is aborted by the FADEC, fuel flow is cut off and ignition is turned off.
Each engine has an independent lubrication system.
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Engine indications and alerts are displayed:
On MFD reversionary mode (split screen) EIS is displayed on the top right side of the display.
The FADEC provides engine starting protection on the ground only for Hung start and Hot start.
The FADEC provides engine starting protection on the ground for Hung start, Hot start and No light off. These protections are inhibited in the air.
MFD ATR INDICATION - An ATR indication is displayed to indicate the Automatic Thrust Reserve status. What is the meaning of a Green ATR indication?
Positioning the thrust lever between TO/GA and CON/CLB selects intermediate thrust.
If the ENG START/STOP knob is moved to STOP position, but the TLA is not reduced at idle within 5 seconds, the FADEC will disregard the STOP selection and will not shutdown the engine.
This is done to prevent engine shutdown due to nuisance commands.
The inner (LP) shaft supports the LP compressor (fan) and boost rotor, which are driven by a dual stage LP turbine.
The outer (HP) shaft system is mechanically independent of the LP shaft and supports a dual axial stage and one centrifugal stage HP compressor driven by a single-stage HP turbine.
The airplane provides power to the engine mounted ignition exciters that supply the igniters. Channel A ignition exciters are connected to the:
Channel A ignition exciters are connected to the EMERGENCY BUS, which means that in case of dual in-flight shutdown the batteries will be able to provide the necessary electrical power for engine ignition. The left FADEC channel B is connected to DC BUS 1 and the right FADEC channel B to the DC BUS 2. The FADEC channel A has the capability to change the power source of the channel B exciter from the airplane DC BUS to the EMERGENCY BUS, if DC BUS is not powered.