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TEO-540-A1A Engine Installation and Operation Manual
The engine fuel pump supplies the correct amount of fuel (through all operating ranges under all
flight and atmospheric conditions) to the six fuel injectors. The ECU controls fuel injection. The
ECU times and sets fuel injection sequentially and proportionally with the induction airflow. A fuel
regulator adapter manifold assembly controls fuel pressure in the fuel rails connected to the fuel
injectors. Only the correct amount of fuel (calculated from sensor input) is injected into the engine at
a time identified by the ECU.
The ECU calculates the air/fuel ratio necessary for engine operation, given the operating conditions.
The ECU controls the amount of fuel flow through each fuel injector based on the measured airflow
rate. The fuel injectors supply atomized fuel into the intake port of each cylinder sequentially.
The electronic fuel system supplies priming fuel for engine start.
Electronic Ignition System
The Electronic Ignition System (Figure 8) has an all-weather shielded, braided wire-type ignition
harness and coil box with 12 electronic ignition coils connected to 12 radio-shielded spark plugs.
The long-reach spark plugs are the all-weather type. There are two spark plugs for each of the six
cylinders.
The ignition system is a redundant inductive discharge system for start-up and continued in-flight
operation. This system has separate sources of power sent through two electrical circuits.
The main source of power for the EECS is the gear-driven PMA on the accessory housing. The
aircraft battery is used to start the engine.
The EECS controls ignition and spark plug operation. The ECU is connected to 12 ignition coils, six
coils for each ECU channel.
Figure 8
Electronic Ignition System
System Description
© 2018 Avco Corporation. All Rights Reserved
Page 10
October 2018
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