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measurements in the original Control
Surfaces Adjustment Report supplied
with the airplane.
(8) If necessary, adjust the aileron stop bolts in the
torque tube assembly:
S Release the jam-nut on the stop bolt.
S Adjust the stop bolt to give the correct range
of movement.
S Tighten the jam-nut on the stop bolt.
Refer to Figure 1.
The aileron positions must be the
distances shown in the Control
Surfaces Adjustment Report.
(measured from the neutral position).
AIRCRAFT
DA 40 Series
AMM
Flight Controls
Detail Steps/Work Items Key Items/References
Doc # 6.02.01
Rev. 5 27-10-00 Page 205
20 Sep 2007
(9) Do an inspection of the controls that you have
adjusted.
S If necessary for your airworthiness authority,
do a second inspection of the controls.
(10) Install these items:
S Pilots’ seats.
S Passenger seat.
S Push-rod access panels under the center
section.
S Aileron bellcrank access panels under each
wing.
Refer to Section:
25-10
52-40
4. Aileron Push-Rod Access
Aileron Push-Rod Remove/Install Access References
Between the control stick and the
bellcrank at the control bulkhead.
Pilots’ seats. Refer to Section 25-10.
Between the bellcrank at the control
bulkhead and the idler lever at the
front main bulkhead.
Pilots’ seats. Refer to Section 25-10.
Between the idler lever at the front
main bulkhead and the bellcrank at
the rear main bulkhead.
Pilots’ seats.
Passenger seat.
Refer to Section 25-10.
Between the bellcrank at the rear
main bulkhead. and the wing root
rib.
Passenger seat.
Center section access panels.
Refer to Section 25-10.
Refer to Section 52-40.
Between the wing root rib and the
bellcrank in the left/right wing.
Center section access panels.
Aileron bellcrank access
panels under each wing.
Refer to Section 52-40.
Between the bellcrank in the
left/right wing and the aileron.
Aileron bellcrank access
panels under each wing.
Refer to Section 52-40.
AIRCRAFT
Flight Controls DA 40 Series
AMM
Page 206
20 Sep 2007 27-10-00 Doc # 6.02.01
Rev. 5
5. Aileron Bellcrank and Lever Access
Aileron Bellcrank/Lever Remove/Install Access References
Bellcrank at the control bulkhead. Pilots’ seats. Refer to Section 25-10.
Idler lever at the front main
bulkhead.
Pilots’ seats. Refer to Section 25-10.
Bellcrank at the rear main bulkhead. Passenger seat. Refer to Section 25-10.
Bellcrank in the wing. Aileron bellcrank access
panels under each wing.
Refer to Section 52-40.
AIRCRAFT
DA 40 Series
AMM
Flight Controls
Doc # 6.02.01
Rev. 5 27-20-00 Page 1
20 Sep 2007
Section 27-20
Flight Controls - Rudder
1. General
The DA 40 has the usual rudder control system. Each pilot has a rudder pedal assembly. The pilot can
adjust the pedal position. Control cables connect the pedal assembly to the rudder. A fixed trim tab
gives a small amount of adjustment to the rudder trim. You can only adjust the fixed trim tab on the
ground.
AIRCRAFT
Flight Controls DA 40 Series
AMM
Page 2
20 Sep 2007 27-20-00 Doc # 6.02.01
Rev. 5
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Figure 1: Rudder Control System
AIRCRAFT
DA 40 Series
AMM
Flight Controls
Doc # 6.02.01
Rev. 5 27-20-00 Page 3
20 Sep 2007
2. Description
The DA 40 has a set of rudder control pedals for each pilot. The pedal assembly can be adjusted.
Figures 1, 3, and 4 show you the rudder control system. Figure 2 shows you the rudder pedal
% assembly. Figure 3 shows the rudder pedal assembly with electrical pedal adjustment (optional
% equipment; OÄM 40-251).
The system has these parts:
) A rudder pedal assembly for each pilot at the front of the cockpit. The forward part of each pedal
connects to a brake master cylinder (refer to Section 32-40).
% ) An adjuster handle for each pilot, attached to the aft face of the rudder pedal assembly, or, as
% optional equipment (OÄM 40-251 incorporated), an adjuster switch for each pilot, located at the rear
% wall of the leg room.
) A yoke (a “T”-shaped lever) assembly in the fuselage below the center console. The yoke attaches
to the bottom of the control bulkhead and to the fuselage shell.
　
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