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Note: Equipment which is certified for installation in the DA 40 is listed in Section 6.5 of
the Airplane Flight Manual. Such equipment may be installed in accordance with
the Airplane Maintenance Manual.
Any equipment which is not listed in Section 6.5 of the Airplane Flight Manual is
called "Additional Equipment". The installation of Additional Equipment is a
modification which must be handled in accordance with national regulations or a
Service Bulletin.
2. Description
The DA 40 has the usual flight controls. An elevator attached to the horizontal stabilizer gives
longitudinal control. Ailerons attached to the trailing edge of each wing give lateral control. The rudder
attached to the vertical stabilizer gives yaw control. Flaps attached to the trailing edge of each wing
give extra lift for landing and for take-off.
The DA 40 has a control stick for each pilot. The pilot can set the elevator trim with a control wheel in
the center console.
Each pilot has a rudder pedal assembly. The assembly attaches to the cockpit floor. The pilot can
adjust the position of the rudder pedals with an adjuster handle on the rudder pedal assembly.
The pilot moves each primary control through a system of push-rods and bellcranks. Cables operate
the rudder. An electric actuator operates the flaps.
3. Push-rods
The push-rods used in the DA 40 have standard end fittings. Also most rods use a standard diameter
tube. Only the length of the rods is special. Some rods have one fixed fork end and one adjustable
eye-end fitting. Other rods have two adjustable eye-end fittings.
Figure 1 shows an example of a standard push-rod. The rod has one adjustable end fitting. The end
fitting has an eye-end with a threaded shaft. The eye-end has a spherical bearing. A jam-nut on the
threaded shaft locks the eye-end in position. A toothed washer locks the nut. You can turn the eye-end
to adjust the length of the rod.
AIRCRAFT
Flight Controls DA 40 Series
AMM
Page 2
20 Sep 2007 27-00-00 Doc # 6.02.01
Rev. 5
Control Rod
Safety Test Hole
Eye-End Fitting
with Spherical Bearing
Jam-Nut
Toothed Washer
Threaded End Fitting
Welded into Place
Fixed Fork-End Fitting
Welded into Place
Figure 1: Standard Push-rod
A steel tube connects the end fittings. A threaded insert is welded into the steel tube to take the eyeend.
A safety hole is drilled in the end of the steel tube with the adjustable end fitting. The safety hole
shows you if the installation of the eye-end to the insert in the steel tube is correct. If you can push the
safety wire through the hole to the other side, the eye-end installation is not correct. But, if you cannot
push the safety wire through the hole, the eye-end installation is correct.
A fixed fork-end is welded to the steel tube.
Refer to Maintenance Practices in this Section for the procedures for adjusting push-rods.
4. Control Rigging
The flight controls of the DA 40 have been designed to make correct rigging as easy as possible. All
levers and bellcranks have holes for rigging pins. The rigging pins lock the levers in the neutral
position.
AIRCRAFT
DA 40 Series
AMM
Flight Controls
Doc # 6.02.01
Rev. 5 27-00-00 Page 201
20 Sep 2007
Maintenance Practices
1. General
These Maintenance Practices tell you how to do procedures (such as push-rod adjustment) which
apply to all of the control systems.
2. Push-rod Adjustment
WARNING: IF YOU DO AN ADJUSTMENT OF A PUSH-ROD, YOU MUST MAKE
SURE THAT THE PUSH-ROD IS STILL IN SAFETY. IF YOU DO NOT DO
THIS, THE PUSH-ROD CAN DISCONNECT. THIS CAN CAUSE DEATH
OR INJURY TO PERSONS.
Detail Steps/Work Items Key Items/References
(1) Release the bolt attaching the push-rod to the
lever or bellcrank.
At the end with an adjustable end fitting.
(2) Loosen the jam-nut on the adjustable end fitting. Refer to Figure 1.
(3) Turn the eye-end to adjust the length of the rod. Turn clockwise to make the rod shorter.
Turn counter-clockwise to make the rod
longer.
(4) Do a test for safety of the eye-end. Push a piece
of lock-wire through the safety test hole.
The wire must not go through the hole
and out the other side.
(5) Tighten the jam-nut. Torque: 16 Nm (11.8 ft.lb.).
(6) Put the end-fitting in position in the lever or
bellcrank.
(7) Install the bolt, washer and self-locking nut. Torque: 6.4 Nm (4.7 ft.lb). You must
always use a new self-locking nut.
(8) Do an inspection of the control that you have
adjusted.
S If necessary for your airworthiness authority,
do a second inspection of the control.
AIRCRAFT
　
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