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) An electrical harness that connects the ECU's to the engine, the power lever, the annunciator
panel, control buttons and some instruments.
) Sensors that measure engine parameters.
) An electrical power lever located in the center console.
) Control buttons for setting the second ECU in an emergency and testing the control system.
AIRCRAFT
Engine Controls DA 40 Series
AMM
Page 2
20 Sep 2007 76-01-00 Doc # 6.02.01
Rev. 5
RPM
OIL PRESS
OIL TEMP
COOLANT TEMP
GEARBOX TEMP
LOAD
FUEL QTY MAIN
FUEL QTY AUX
FUEL TEMP MAIN
FUEL TEMP AUX
GENERATOR
VOLT
FUEL FLOW
from
Airframe
Fuel
System
from
Electrical
System
Compact Engine Display (CED 125)
Auxiliary Throttle Engine Display (AED 125)
Injector 1
Injector 2
Injector 3
Injector 4
Crankshaft 1
Manifold Air Temp
Manifold Air Press
Crankshaft 2
Camshaft 1
Coolant Temp
Camshaft 2
Oil Press
Fuel Rail Pressure
Oil Temp
Propeller CSU
Glow Plugs Gearbox Temp
Engine Sensors
Controlled
Components
Engine Control Unit Ambient Press #1
ECU A ECU B
ECU SWAP
ECU TEST
14 VDC
14 VDC
ENGINE
ECU A
ECU B
GLOW
Annunciator
Panel
Control Buttons
WATER LEVEL
Waste Gate
Coolant Level
Ambient Press #2
Manifold Press #1
Manifold Press #2
%
%
%
%
%
%
%
%
%
%
%
%
%
%
%
%
%
%
%
%
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%
Figure 1: Engine Control System Schematic Diagram
AIRCRAFT
DA 40 Series
AMM
Engine Controls
Doc # 6.02.01
Rev. 5 76-01-00 Page 3
20 Sep 2007
A. Engine Control Units
The ECU A and ECU B are contained in one box located under the pilot’s seat in the cockpit. A
harness connects the box to the engine, the power lever and some instruments.
In the usual operation, the alternator supplies power for the system. If the alternator fails, the ECU
B automatically takes over and the ECU backup battery provides power. Refer to Section 24-33 for
more data about the electrical supply for the engine control system.
The annunciator panel at the top of the instrument panel has two amber caution lights for the
engine control system (marked ECU A and ECU B).
The ECU SWAP switch on the left of the instrument panel lets you toggle between ECU A and
ECU B. For all normal operation, the switch is set to AUTOMATIC and the ECU A controls the
engine. You should only set the system to ECU B for testing.
Note: The ECU SWAP switch only operates to change from ECU A to ECU B. If you
toggle back to AUTOMATIC, then ECU B remains in control until:
- the power lever is set to IDLE, and
- you push and hold the ECU TEST button until both ECU caution lights on the
annunciator panel go off.
The ECU TEST button on the left of the instrument panel lets you test the system. Refer to Section
71-01 for the ECU test procedure.
B. Electrical Harness
The electrical harness is an engine component. The harness connects the power lever and sensors
to the ECU A and ECU B. It also provides connections for the ECU buttons, warnings and some
engine instruments.
The electrical harness comes through the firewall on the left side. P-clamps and ty-raps attach the
electrical harness to the engine. The harness goes forward and divides to go down both sides of
the engine.
The cables on the right side pass mainly along the cylinder head. They connect to the fuel pressure
regulator, fuel pressure sensor, fuel injectors and camshaft position sensors. A cable goes to the
intercooler outlet. Cables also go forward and down to the glow plugs, waste gate, right and left
crankshaft position sensors, gearbox temperature sensor, coolant temperature sensor, and
propeller governor.
The left side of the engine has cables to the sensors for oil pressure and oil temperature and cables
for the starter and alternator.
The repair of the electrical harness is limited to damage that occurs near the ends of the cables,
outside of the isolated section. If a cable fails within the isolated section, then you must replace the
complete harness.
AIRCRAFT
Engine Controls DA 40 Series
AMM
Page 4
20 Sep 2007 76-01-00 Doc # 6.02.01
Rev. 5
Bottom
Cover Plate
Electrical
Plugs
Throttle
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钻石40系列AMM 3(79)
