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TEO-540-A1A Engine Installation and Operation Manual
EECS Architecture
The EECS architecture consists of:
• Primary components (Figure 3):
o Engine Control Unit (ECU) (also identified as
ACU) - is a dual channel unit which contains
system processors, input signal conditioning,
output actuator drive stages, and aircraft
communication interfaces. The ACU Controller
Area Network (CAN) bus communications
linked to a host personal computer can be used
to monitor the system and upload logged data.
o Power Box - a dual channel unit which supplies
regulated primary and secondary 14V power
over to the EECS. Airframe power at start-up or
when engine speed is below 1000 rpm supplies
power to the power box regulators. When engine
rpm is above 1000 rpm, a dedicated Permanent
Magnet Alternator (PMA) (mounted on the
engine accessory drive) supplies power to the
power box.
o Data Logger (ADL) - a single channel unit that
records data received from the ACU via the
CAN bus communication.
• Secondary components:
o Engine harness
o Sensors
o Actuators.
The ECU and Power Box are connected by two
wiring harnesses; the engine-to-firewall
harness (Figure 4) and the airframe-supplied
interface harness. Two channels on the ECU
communicate with each other through a CAN
bus (CAN1). Each channel has input
processing, a microprocessor and output
processing which control the engine
independently of each other. Sensors connected
to the engine harness send inputs to the ECU to
control the engine through output to the
actuators. The actuators also are connected to
the ECU by the same wiring harnesses. Refer
to Figure 5 for a general EECS overview.
NOTICE: The ECU software is unique to each engine and is not to be installed on any other
engine unless it has been re-configured.
© 2018 Avco Corporation. All Rights Reserved
October 2018
EECS Primary Components
Figure 4
Engine-to-Firewall Wiring Harness
Figure 3
System Description
Page 3
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