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stabilizer. It has holes for the rudder control cables and trim control.
AIRCRAFT
Fuselage
DA 40 Series
AMM
Page 8
20 Sep 2007 53-10-00 Doc # 6.02.01
Rev. 5
Vertical Stabilizer
Front Web
Vertical Stabilizer
Front Lower Rib
Vertical Stabilizer
Rear Lower Rib
Vertical Stabilizer
Rear Web
Reinforcing Rib
Figure 4: Fuselage Structure - Vertical Stabilizer
AIRCRAFT
DA 40 Series
AMM
Fuselage
Doc # 6.02.01
Rev. 5 53-10-00 Page 9
20 Sep 2007
K. Vertical Stabilizer Front Lower Rib
The vertical stabilizer front lower rib is a rigid GFRP molding. It bonds to the fuselage shell at the
bottom of the vertical stabilizer. It also bonds to the vertical stabilizer front web. It has a hole for the
flexible control cable for the elevator trim-tab.
L. Vertical Stabilizer Rear Lower Rib
The vertical stabilizer rear lower rib is a rigid GFRP molding. It bonds to the fuselage shell at the
bottom of the vertical stabilizer. It also bonds to the vertical stabilizer front and rear webs. It has a
large slot for the elevator control push-rod.
M. Vertical Stabilizer Front Web
The vertical stabilizer front web is a rigid GFRP molding. It bonds to the fuselage shell. It also
bonds to the vertical stabilizer lower ribs and to the top of the rear web.
The top of the front web is a rigid channel section. GFRP inserts give strength to the area where
the horizontal stabilizer mounts attach.
N. Vertical Stabilizer Rear Web
The vertical stabilizer rear web is a rigid GFRP molding. It bonds to the fuselage shell and it bonds
to the vertical stabilizer front web. The top of the rear web has the top mounting for the rudder. It
also has a reinforcing rib bonded to the rear face.
The vertical stabilizer rear web closes the rear of the vertical stabilizer.
AIRCRAFT
Fuselage
DA 40 Series
AMM
Page 10
20 Sep 2007 53-10-00 Doc # 6.02.01
Rev. 5
Intentionally left blank
AIRCRAFT
DA 40 Series
AMM
Fuselage
Doc # 6.02.01
Rev. 5 53-10-00 Page 201
20 Sep 2007
Maintenance Practices
1. General
This Section gives repair data for the fuselage. Use it to give the data about the fuselage structure.
Refer to Chapter 51 for standard repair procedures.
2. Repair Data for the Fuselage Shells
Figures 5 to 11 show the layers of glass fiber or carbon fiber cloth in the fuselage shells. Use this data
% when you need to repair the fuselage. Contact Diamond Aircraft customer support department if more
% detailed information (such as further layup plans) is needed.
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 fuselage, you must
use the same type of cloth with the same fiber orientation.
In many areas, uni-directional carbon fiber tape is used. In these cases, the length of the tape is given.
The numbers in circles beside each drawing give the order in which the layers are applied (‘Stages’).
The first stage is a layer of filler and is not shown. Stage 1 is the outer face of the shell.
Where dimensions of layers are given in millimeters (mm), divide by 25.4 to obtain the dimension in
inches (in).
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
Fuselage
DA 40 Series
AMM
Page 202
20 Sep 2007 53-10-00 Doc # 6.02.01
Rev. 5
3 4
4 5
7 6 8
5 6
Item No. Layers Reference No. Type Remarks
4 1 8.4548.60 Glass 92110 twill 2/2 0º/90º Overall
5 2 8.4551.60 Glass 92125 twill 2/2 ±45º
6 1 8.4551.60 Glass 92125 twill 2/2 0°/90º
7 2 8.4551.60 Glass 92125 twill 2/2 15º/105º
8 2 8.4551.60 Glass 92125 twill 2/2 0°/90º
Figure 5: Layers of Cloth in the Fuselage Shells - Stages 3 - 6
AIRCRAFT
DA 40 Series
AMM
Fuselage
Doc # 6.02.01
Rev. 5 53-10-00 Page 203
20 Sep 2007
9
9 9
11 10 12 13
RIGHT FUSELAGE SHELL
13 12 10 11
LEFT FUSELAGE SHELL
8
Item No. Layers Reference No. Type Remarks
% 9 2 8.4525.60 Glass 92146 uni-directional 0º/90º
10 2 8.4551.60 Glass 92125 twill 2/2 ±45º, 250 mm * 600 mm
11 3 KDU 1034 Carbon 100 mm uni-directional 750 mm
12 3 KDU 1034 Carbon 100 mm uni-directional 3250 mm
% 13 2 8.4525.60 Glass 92146 uni-directional 17º/107º
Figure 6: Layers of Cloth in the Fuselage Shells - Stages 7 & 8
　
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