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2. Description/Operation
A. integrated Engine Instrument
Figure 1 shows the VM 1000 integrated engine instrument. It is located in the instrument panel, see
Section 31-10.
Sensors/probes and transducers send electrical signals to a data processing unit (DPU). The DPU
sends the data to the VM 1000 to give a display. The VM 1000 display has these indications:
) RPM.
) Oil temperature.
) Fuel flow.
) Cylinder head temperature (CHT) for all four cylinders.
) Exhaust gas temperature (EGT) for all four exhaust down-pipes.
) Oil Pressure.
) Fuel Pressure.
) Manifold pressure.
) Main bus voltage.
) Alternator output amperage.
You cannot repair the integrated engine instrument.
AIRCRAFT
Engine Indicating DA 40 Series
AMM
Page 2
20 Sep 2007 77-40-00 Doc # 6.02.01
Rev. 5
RPM
Figure 1: VM 1000 Integrated Engine Instrument
AIRCRAFT
DA 40 Series
AMM
Engine Indicating
Doc # 6.02.01
Rev. 5 77-40-00 Page 3
20 Sep 2007
B. Transducers and Sensors
The engine indicating system uses these transducers/sensors:
) RPM sensor. The RPM sensor is mounted to the right magneto. You can replace the RPM
sensor.
) Oil temperature sensor. The oil temperature sensor attaches to a special mounting on the rear
accessory housing. You can replace the oil temperature sensor.
) Fuel flow sensor. The fuel flow sensor is located in the fuel supply hose to the fuel injector. You
can replace the fuel flow sensor.
) Cylinder head temperature (CHT) sensor. The engine has a CHT probe attached to the bottom
of each cylinder head. You can replace the CHT probe.
) Exhaust gas temperature (EGT) sensor. The engine has an EGT probe attached to the exhaust
down-pipe from each cylinder head. You can replace the EGT probe.
) Oil pressure transducer. A P-clamp attaches the oil pressure transducer to the engine-mountingframe
on the right-top side. A flexible hose connects the transducer to a connection in the
engine oil system near the oil-pressure-relief-valve. You can replace the oil pressure transducer.
) Fuel pressure transducer. The fuel pressure transducer is in the fuel supply hose to the fuel
injector. You can replace the fuel pressure transducer.
) Manifold pressure transducer. A P-clamp attaches the manifold pressure transducer to the
engine-mounting-frame, on the top-left side. A flexible hose connects cylinder no. 4 to the
manifold pressure transducer. When the LASAR control unit is installed, then a Tee-piece is
installed in the flexible hose. Another flexible hose connects the Tee-piece to the LASAR control
unit. You can replace the manifold pressure transducer.
AIRCRAFT
Engine Indicating DA 40 Series
AMM
Page 4
20 Sep 2007 77-40-00 Doc # 6.02.01
Rev. 5
Figure 2: Replace the Oil Temperature Sensor
AIRCRAFT
DA 40 Series
AMM
Engine Indicating
Doc # 6.02.01
Rev. 5 77-40-00 Page 5
20 Sep 2007
LYCOMING LYCOMING
Fuel Flow
Connector
Fuel Flow Sensor
Fuel Flow Sensor
45 Fitting 45 Fitting
Fuel Feed Hose
to Injector
Fuel Feed Hose
from Fuel Pump
Engine Sump
Electrical
Connector
Figure 3: Fuel Flow Sensor Installation
AIRCRAFT
Engine Indicating DA 40 Series
AMM
Page 6
20 Sep 2007 77-40-00 Doc # 6.02.01
Rev. 5
LYCOMING LYCOMING
CHT Spade
Connectors
CHT Spade
Connectors
CHT Probe
Cylinder Head
VIEW UNDER LEFT REAR CYLINDER HEAD
SHOWN, OTHERS SIMILAR
Figure 4: CHT Probe Installation
AIRCRAFT
DA 40 Series
AMM
Engine Indicating
Doc # 6.02.01
Rev. 5 77-40-00 Page 7
20 Sep 2007
EGT Spade
Connectors
EGT Spade
Connectors
EGT Probe
Worm-Drive
Clamp
LYCOMING LYCOMING
LEFT SIDE SHOWN
RIGHT SIDE SIMILAR
Figure 5: EGT Probe Installation
AIRCRAFT
Engine Indicating DA 40 Series
AMM
Page 8
20 Sep 2007 77-40-00 Doc # 6.02.01
Rev. 5
Oil Pressure Sensor
Electrical Connector
Adaptor
P-Clamp
Flexible Hose
Engine Mount Tube
Figure 6: Oil Pressure Sensor Installation
AIRCRAFT
DA 40 Series
AMM
Engine Indicating
Doc # 6.02.01
Rev. 5 77-40-00 Page 9
20 Sep 2007
Fuel Pressure
Sensor
Angle
Adaptor Adaptor
Electrical
Connector
Figure 7: Fuel Pressure Probe Installation
AIRCRAFT
Engine Indicating DA 40 Series
AMM
Page 10
20 Sep 2007 77-40-00 Doc # 6.02.01
Rev. 5
Intentionally left blank
　
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