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Cooling
Doc # 6.02.01
Rev. 5 75-00-00 Page 203
20 Sep 2007
Detail Steps/Work Items Key Items/References
(5) Attach the tie-bars at the bottom of the baffle at
the left side and at the right side.
(6) Install the fuel flow divider drain tube:
S Move the tube into position through the
rubber grommet in the baffle.
S Connect the tube to the fuel flow divider
drain.
Refer to Section 71-70.
(7) Install the propeller governor control cable:
S Move the cable into position through the
rubber grommets in the baffle.
S Connect the cable to the governor.
Refer to Section 61-20.
(8) Do a test for freedom and range of movement, on
the propeller control system.
Refer to Section 61-20.
(9) Install the mixture control cable:
S Move the cable into position through the
rubber grommets in the baffle.
S Connect the cable to the fuel injector.
Refer to Section 76-00.
(10) Do a test for freedom and range of movement, on
the mixture control system.
Refer to Section 76-00.
(11) Install the cables for the top spark plugs of No’s 1
and 3 cylinders:
S Move the cables forward through the hole in
the rear of the baffle.
S Move the cable feed thru into the correct
position.
S Install the bolts, washers and nuts which
attach the feed-thru to the baffle.
S Connect the spark plug cables to the spark
plugs.
Torque to 12.4 to 13.6 Nm (110 - 120
in.lb).
AIRCRAFT
Cooling DA 40 Series
AMM
Page 204
20 Sep 2007 75-00-00 Doc # 6.02.01
Rev. 5
Detail Steps/Work Items Key Items/References
(12) Install the cables for the top spark plugs of No’s 2
and 4 cylinders:
S Move the cables into position through the
holes in the baffle.
S Connect the spark plug cables to the spark
plugs.
Torque to 12.4 to 13.6 Nm (110 - 120
in.lb).
(13) Connect the airplane battery. Refer to Section 24-31.
(14) If necessary, for your airworthiness authority, do
a second inspection of the mixture control system
and the propeller control system.
(15) Install the engine cowlings. Refer to Section 71-10.
(16) Do an engine run-up. Refer to the DA 40 Airplane Flight
Manual.
AIRCRAFT
DA 40 Series
AMM
Cooling
Doc # 6.02.01
Rev. 5 75-01-00 Page 1
20 Sep 2007
Radiator
Cabin Heat
Heat-
Exchanger
Thermostat Valve
Bleed Screw
Bleed Screw
Coolant Tank
TAE 125 Engine
Pump
Main Circuit
Bypass
Circuit
Drain Plug
Overflow Line
to Exterior
Restrictor
Section 75-01
Liquid Cooling - TAE 125 Diesel Engine
1. General
This Section gives you the data for the liquid cooling system for airplanes with the TAE 125 Diesel
engine installed. It gives you the maintenance practices to remove/install the system components.
Figure 1 shows the liquid cooling system schematic diagram. Figure 2 shows the installation in the
airplane.
Figure 1: Liquid Cooling System Schematic Diagram
AIRCRAFT
Cooling DA 40 Series
AMM
Page 2
20 Sep 2007 75-01-00 Doc # 6.02.01
Rev. 5
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To Cabin-Heat
Heat-Exchanger
From Cabin-Heat
Heat-Exchanger
Thermostat Valve with
Temperature Sensor
Hot Coolant
to Radiator
Cool Coolant
from Radiator
Radiator
Overflow Line
Bleed Points
Coolant Tank with
Coolant Level Sensor
Coolant
Drain Plug
To Coolant
Bypass Pipe
Coolant
Bypass Pipe
AIRCRAFT
DA 40 Series
AMM
Cooling
Doc # 6.02.01
Rev. 5 75-01-00 Page 3
20 Sep 2007
2. Description
The engine has a water-based liquid cooling system. The liquid coolant is a mixture of distilled water
and antifreeze. Refer to the Airplane Flight Manual for approved coolants.
The engine has an integral coolant pump. The coolant pump is located at the rear of the engine, below
the coolant tank. The flat-belt at the rear of the engine operates the coolant pump. An automatic
tensioner keeps the belt tension at the correct value. The coolant flows through passages inside the
crankcase and cylinder head and becomes hot. The coolant leaves the engine through a thermostat
valve at the top, front left of the crankcase.
A temperature sensor at the rear of the thermostat valve connects to the engine control system. The
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钻石40系列AMM 3(67)
