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(10) Do a test for correct, full and free movement of
the trim control. If necessary, adjust the trim
control.
Refer to Section 27-31.
(11) Install the horizontal stabilizer fairing.
S Install 4 screws.
AIRCRAFT
Stabilizers
DA 40 Series
AMM
Page 204
20 Sep 2007 55-10-00 Doc # 6.02.01
Rev. 5
1 5
2 6
3 7
4
1
2
3
4
5
6
7
8
Item No. Layers Reference No. Type Remarks
1 1 8.4548.60 Glass twill 2/2 0/90º
2 1 8.4551.60 Glass twill 2/2 0/90º
3, 4, 5 1 each 8.4525.60 Glass uni-directional 0/180º
6, 7 8 each 8.4525.60 uni-directional 0/180º, 50 mm x 500 mm
stepped 20 mm
8 2 8.4551.60 Glass twill 2/2 0/90º
Figure 3: Layers of Cloth in the Horizontal Stabilizer Bottom Shell
AIRCRAFT
DA 40 Series
AMM
Stabilizers
Doc # 6.02.01
Rev. 5 55-10-00 Page 205
20 Sep 2007
3. Repair Data for the Horizontal Stabilizer Shells
Figures 3 and 4 show the layers of glass fiber cloth in the horizontal stabilizer shells. Use this data
when you need to repair the horizontal stabilizer.
The Figures show the main layers of cloth. The cross-hatching on the Figure shows the orientation of
the fibers. The orientation is also given in the related table. When you repair the horizontal stabilizer,
you must use the same type of cloth with the same fiber orientation.
The numbers in circles beside each drawing give the order in which the layers are applied (‘Stages’).
The first stage (0 for the horizontal stabilizer) is a layer of filler and is not shown. Stage 1 is the outer
face of the shell.
Always do a burn test on a piece of composite from the damaged area before you do a repair. Refer
to Section 51-20 for the burn test.
AIRCRAFT
Stabilizers
DA 40 Series
AMM
Page 206
20 Sep 2007 55-10-00 Doc # 6.02.01
Rev. 5
1
2 5
3 6
4
1
2
3
4
5
6
Item No. Layers Reference No. Type Remarks
1 1 8.4548.60 Glass twill 2/2 0/90º
2 2 8.4551.60 Glass twill 2/2 0/90º
3, 4, 5 1 each 8.4525.60 Glass uni-directional 0/180º
6 2 8.4551.60 Glass twill 2/2 0/90º
Figure 4: Layers of Cloth in the Horizontal Stabilizer Top Shell
AIRCRAFT
DA 40 Series
AMM
Stabilizers
Doc # 6.02.01
Rev. 5 55-20-00 Page 1
20 Sep 2007
Section 55-20
Elevator
1. General
The DA 40 has the usual elevator. The elevator attaches to the rear web of the horizontal stabilizer.
See Section 27-30 for data about the elevator controls.
AIRCRAFT
Stabilizers
DA 40 Series
AMM
Page 2
20 Sep 2007 55-20-00 Doc # 6.02.01
Rev. 5
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Figure 1: Elevator Structure
AIRCRAFT
DA 40 Series
AMM
Stabilizers
Doc # 6.02.01
Rev. 5 55-20-00 Page 3
20 Sep 2007
2. Description
Figure 1 shows the elevator structure. Figure 2 shows the installation of the elevator on the horizontal
stabilizer. Figure 3 shows the trim tab installation.
The elevator has top and bottom shells. Each shell has GFRP skins with a rigid foam core. The leading
edge of each shell has a curve. The shells bond together where the curves overlap. The shells also
bond together at the ends and at the trailing edge.
The elevator has a horn rib in the middle. It is a strong box with an open front. The elevator horn goes
into the horn rib. Two bolts attach the horn to the elevator.
The horn has a hole with a bush for the elevator push rod. The front of the horn has elevator mass
balance weight. More mass balance weight is attached at the front of the elevator tips.
Five bearings hold the elevator. The elevator horn has a plain bearing. A bolt and spacer attach the
elevator horn to the trailing edge webs of the horizontal stabilizer.
A small bearing rib at mid-span on each side holds an elevator hinge assembly. The hinge assembly
has an eye-end with a plain shank. The eye-end has a spherical bearing. The shank engages in a
bush in the trailing edge web.
The outer end of the elevator on each side has an end bearing. A reinforcing block holds a bonded
bush. The bush aligns with a bonded bush in the horizontal stabilizer trailing edge web. A pivot pin
goes through both bushes to make the outer bearing. A roll pin locks the pivot pin in the bonded bush.
　
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