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Refer to Figure 1
Torque to 6.5 Nm (4.6 ft lbs)
(3) Install the nut, bolt and three washers that
attach the elevator trim actuator to the lower
mounting bracket.
Torque to 6.5 Nm (4.6 ft lbs)
(4) Connect the electrical harness to the
elevator trim actuator.
− Get access through the hole in the
vertical stabilizer and connect the
electrical harness connector.
− Install the Ty-wrap that holds the
electrical harness.
DA20-C1 AMM
Flight Controls
Doc # DA201-C1
Rev. 9 27-31-00 Page 203
29 Apr 2004
Detail Steps/Work Items Key Items
WARNING: WHEN YOU DO WORK ON THE AIRPLANE CONTROLS, YOU
MUST MAKE SURE THE AREAS AROUND THE
CONTROLS/CONTROL SURFACES ARE CLEAR OF
PERSONS/EQUIPMENT. IF YOU DO NOT DO THIS, INJURY TO
PERSONS AND DAMAGE TO CONTROL SURFACES CAN OCCUR.
(5) Install the bottom of the elevator vertical
control rod to the elevator bellcrank.
− Make sure you correctly align the fork
assembly with the spring mount
assembly.
Install the nut bolt and two washers.
Refer to Figure 1
Torque to 6.5 Nm (4.6 ft lbs)
(6) Connect the airplane battery. Refer to Chapter 24-31
(7) Do an operational check of the elevator trim
control system.
(8) Do a test for correct, full and free movement
of the elevator control system.
Refer to Chapter 27-30
(9) Install the rudder. Refer to Chapter 55-40
C. Adjust The Elevator Trim Position Indicator
Detail Steps/Work Items Key Items
(1) Remove the instrument panel cover. Refer to Chapter 25-10
(2) Remove the rudder. Refer to Chapter 55-40
WARNING: WHEN YOU DO WORK ON THE AIRPLANE CONTROLS, YOU
MUST MAKE SURE THE AREA AROUND THE
CONTROLS/CONTROL SURFACES ARE CLEAR OF
PERSONNEL/EQUIPMENT. IF YOU DO NOT DO THIS, INJURY TO
PERSONNEL AND DAMAGE TO CONTROL SURFACES CAN
OCCUR.
(3) Using the elevator trim switch set the trim to
full nose up.
(4) Mark the position of the trim actuator shaft in
the nose up position.
(5) Using the elevator trim switch set the trim to
full nose down.
Flight Controls
DA20-C1 AMM
Page 204
29 Apr 2004 27-31-00 Doc # DA201-C1
Rev. 9
Detail Steps/Work Items Key Items
(6) Mark the position of the trim actuator shaft in
the nose down position.
(7) Measure the trim actuator travel between the
marks for full nose up and full nose down
and divide this measurement by two to get
the midpoint of travel.
(8) Using the elevator trim switch set the trim
actuator to the midpoint of travel.
(9) Use a small screwdriver to adjust the
potentiometer on top of the trim position
indicator.
The two middle light emitting diodes on the
indicator must be lit.
(10) Using the elevator trim switch set the trim to
full nose up.
The top light emitting diode must be lit at
full nose up trim.
(11) Using the elevator trim switch set the trim to
full nose down.
The bottom light emitting diode must be lit
at full nose down trim.
(12) Do an operational check of the elevator trim
control system.
(13) Install the instrument panel cover. Refer to Chapter 25-10
DA20-C1 AMM
Flight Controls
Doc # DA201-C1
Rev. 9 27-50-00 Page 1
29 Apr 2004
CHAPTER 27-50
FLIGHT CONTROLS - FLAPS
1. General
The DA20-C1 has slotted flaps for landing and take-off. An electric flap actuator moves the flaps.
See Chapter 57-50 for data about the flap structure.
A three-position toggle switch controls the flaps. The switch is in the center section of the
instrument panel.
The flap position indicator has marks for CRUISE, T/O and LDG positions.
Flight Controls
DA20-C1 AMM
Page 2
19 Dec 1997 27-50-00 Doc # DA201-C1
Rev. 0
Figure 1: Flap Control System in the Fuselage
DA20-C1 AMM
Flight Controls
Doc # DA201-C1
Rev. 0 27-50-00 Page 3
19 Dec 1997
2. Description
Figure 1 shows the flap control system in the fuselage. Figure 2 shows the flap control system in
the aft control bulkhead and wing.
A. Flap Actuator
An electric actuator operates the flaps. The electric actuator is under the left seat. A mounting
bracket on the on the aft face of the T-panel holds the front of the actuator.
The electric actuator has an electric motor. The motor has a reduction gear which turns a
spindle. The spindle operates a control rod. The control rod connects to a bellcrank attached to
the aft control bulkhead.
A cam attached to the control rod operates five micro-switches. The micro-switches are part of
the flaps electronic control circuit.
　
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