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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 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
Wings DA 40 Series
AMM
Page 218
20 Sep 2007 57-10-00 Doc # 6.02.01
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Item
No.
Layers Reference No. Type Remarks
% 1 1 02037 glass 0o/90o
2, 3 1 CCC 459 Al carbon/aluminum 0°/90º - lightning protection.
6 2 8.3520.80 carbon cloth 0°/90º, 100 mm wide.
7 1 8.3520.80 carbon cloth ±45º
10 - 13 3 each 8.3520.80 carbon cloth ±45º, 200 mm x 200 mm
14, 15 3 each 8.3520.80 carbon cloth ±45º, 200 mm x 250 mm
16 3 each 8.3520.80 carbon cloth ±45º, 160 mm x 160 mm
Figure 6: Layers of Cloth in the Wing Bottom Shell - Stages 2 - 6
AIRCRAFT
DA 40 Series
AMM
Wings
Doc # 6.02.01
Rev. 5 57-10-00 Page 219
20 Sep 2007
7
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9
20 18
22
23
Item No. Layers Reference No. Type Remarks
18, 20 1 each H 60 6 mm rigid foam
22 2 8.4551.60 glass twill 2/2 ±45º, 90 mm wide.
23 1 8.4551.60 glass twill 2/2 ±45º
Figure 7: Layers of Cloth in the Wing Bottom Shell - Stages 7 - 9
AIRCRAFT
Wings DA 40 Series
AMM
Page 220
20 Sep 2007 57-10-00 Doc # 6.02.01
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Item No. Layers Reference No. Type Remarks
2, 3 1 CCC 459 Al carbon/aluminum 0°/90º - lightning protection.
6 2 8.3520.80 carbon cloth 0°/90º, 100 mm wide.
7 2 8.3520.80 carbon cloth ±45º 200 mm x 200 mm.
10 (Lyc.) 3 8.3520.80 carbon cloth ±45º 200 mm x 200 mm.
10 (TAE) 3 8.3520.80 carbon cloth ±45º 220 mm x 220 mm.
11 3 8.3520.80 carbon cloth ±45º 250 mm x 300 mm.
Figure 8: Layers of Cloth in the Wing Top Shell - Stages 2 - 6
AIRCRAFT
DA 40 Series
AMM
Wings
Doc # 6.02.01
Rev. 5 57-10-00 Page 221
20 Sep 2007
13 15
17
7
8
Item
No.
Layers Reference No. Type Remarks
13, 15 1 each H 60 6 mm rigid foam
17 1 8.4551.60 glass twill 2/2 ±45º
Figure 9: Layers of Cloth in the Wing Top Shell - Stages 7 and 8
AIRCRAFT
Wings DA 40 Series
AMM
Page 222
20 Sep 2007 57-10-00 Doc # 6.02.01
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Intentionally left blank
AIRCRAFT
DA 40 Series
AMM
Wings
Doc # 6.02.01
Rev. 5 57-50-00 Page 1
20 Sep 2007
Section 57-50
Flaps
1. General
This Section tells you about the flap structure. Refer to Section 27-50 for data about the flap control
system.
AIRCRAFT
Wings DA 40 Series
AMM
Page 2
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% Figure 1: Flap Structure and Assembly
AIRCRAFT
DA 40 Series
AMM
Wings
Doc # 6.02.01
Rev. 5 57-50-00 Page 3
20 Sep 2007
2. Description
Figure 1 shows the flap structure. Each flap has these components:
A. Bottom Shell
The bottom shell has inner and outer GFRP skins. It also has one layer of carbon fiber cloth in the
outer skin. The skins bond to a rigid plastic foam core. The leading edge of the shell bends up to
form a web. It then curves forward to form a shroud which seals the gap between flap and wing
when the flap is down.
The outboard end of the bottom shell also bends up to close the end of the flap. The leading edge,
the ends, and the area where the horn attaches have more carbon fiber cloth to give more strength
and stiffness.
B. Top Shell
The top shell has inner and outer GFRP skins. It also has one layer of carbon cloth in the outer
skin. The skins bond to a rigid plastic foam core. The top shell bonds to the bottom shell and the
　
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本文鏈接地址：鉆石40系列AMM 2(149)