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the propeller hub. Lightly oil the seal.
Refer to Figure 3.
Use clean engine oil.
(4) Move the propeller into position on the propeller
shaft flange.
Take care not to damage the propeller
O-ring seal.
Note: Make sure that the propeller is pushed into the correct position by hand. Do not
use the nuts to pull the propeller into position.
(5) Install the 6 washers and nuts.
(6) When the propeller is in the correct position, fully
tighten the nuts in opposing pairs.
Torque 45 - 47 Nm (33 - 35 ft.lb).
(7) Do a test for correct blade track. Refer to Paragraph 3.
(8) Install the spinner:
S Loosely install the screws and plastic
washers which attach the spinner to the
spinner bulkhead.
S Tighten all the attaching screws.
Align the index mark.
Torque 4 - 5 Nm (35 - 44 in.lb)
(9) Install the engine cowlings. Refer to Section 71-11.
(10) Do an engine run-up. Do a test for correct
operation of the propeller.
Refer to Section 71-01.
AIRCRAFT
Propeller
DA 40 Series
AMM
Page 204
20 Sep 2007 61-11-00 Doc # 6.02.01
Rev. 5
3. Propeller Blade Tracking Test
A. Equipment
Item Quantity Part Number
Tracking stand. 1 Commercial.
B. Procedure
Detail Steps/Work Items Key Items/References
WARNING: MAKE SURE THAT THE ENGINE IS SAFE BEFORE YOU DO ANY
WORK ON THE PROPELLER. IF THE ENGINE IS TURNED, THE
PROPELLER CAN CAUSE INJURY OR DEATH.
(1) Make sure that the engine is safe:
S Set the ELECTRIC MASTER key switch to
OFF.
S Set the ENGINE MASTER switch to OFF.
S Set the power lever to IDLE.
(2) Put the tracking stand behind the propeller. Do not move the tracking stand during
the test.
(3) Turn the propeller backwards to align a blade
with the tracking stand.
(4) Measure the distance from the stand to the blade. Measure from the stand to a point on
the trailing edge 10 cm (4 in) from the
blade tip.
(5) Do items 3 and 4 for the other blades and record
the values.
(6) The difference between any blades must not be
more than 3 mm (1/8 inch).
AIRCRAFT
DA 40 Series
AMM
Propeller
Doc # 6.02.01
Rev. 5 61-20-00 Page 1
20 Sep 2007
Section 61-20
Propeller Control - Lycoming Engine
1. General
The DA 40 with the Lycoming engine installed has a constant speed propeller and a Woodward or mt
porpeller governor. The governor controls the engine speed by changing the propeller blade angle
(pitch).
This Section gives the basic data about the propeller governor. For more data about the Woodward
governor refer to the propeller manufacturer‘s manual or the Woodward governor manual. For more
data about the MT-P420-10 governor refer to the mt-Propeller governor manual.
2. Description and Operation
The DA 40 has an mt-Propeller constant speed propeller. The propeller uses oil pressure to increase
the blade angle (pitch). In normal flight the centrifugal twisting moment (CTM) of the blade and the
return spring cause the blade to move towards fine pitch.
Figure 1 shows a schematic diagram of the propeller governor. The propeller governor connects to the
engine oil supply. The oil goes to a gear-pump in the governor. The gear pump increases the oil
pressure to 270 - 340 psi (19 - 23 bar). A relief-valve controls the maximum oil pressure.
The governor has a pilot-valve. The outlet from the pilot-valve connects to the propeller. The inlet to
the pilot-valve can connect to the oil pump, or it can connect to an oil return line back to the engine
sump, or it can be closed off.
The governor has a control lever. The control lever pushes against the speeder spring and the spring
pushes against the pilot-valve. When the governor is turning, flyweights pull the pilot-valve upwards,
against the force of the speeder spring.
In normal flight the governor will be in one of the following conditions:
A. On-Speed Condition
When the engine runs at the selected speed, the governor operates as follows:
) The propeller blades are at the correct pitch to absorb the power from the engine.
) The centrifugal force of the governor flyweights balances the speeder spring force.
) The pilot-valve closes the connection to the oil-pump and it closes the connection to the oil return
line.
) Oil cannot flow out of the propeller and the propeller blades stay at the same pitch.
) Oil from the oil-pump flows through the relief valve and returns to the pump inlet.
AIRCRAFT
Propeller
DA 40 Series
AMM
Page 2
20 Sep 2007 61-20-00 Doc # 6.02.01
Rev. 5
ON SPEED
UNDER SPEED OVER SPEED
Blade
High Pitch Low Pitch
　
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