Doc # 6.02.01 Page 201
Rev. 4 09 Jan 2003
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AMM
B. Install a Flap
DA 40 Series
Detail Steps/Work Items Key Items/References
(1) Make sure that the hinge pins are clean and not damaged.
(2) Put the flap into position on the airplane.
(3) Install the 6 hinge pins in the hinges and flap horn: S Push the hinge pins into position from the inboard side. S Align the holes in the hinges with the holes in the hinge pins and install the roll pins. Make sure that there is a gap of 0.5 -2.5 mm (0.002 - 0.010 in) between the faces of the hinge at the horn and a gap of 1 - 3 mm (0.004 - 0.012 in) between the faces at the other hinges.
(4) Install the bolt which attaches the flap push rod to the flap horn: S Install a washer on the bolt. S Push the bolt through the horn and the push rod. S Install the washer and the nut on the bolt.
(5) Do a test for correct adjustment of the flaps. Refer to Section 27-50.
(6) If necessary for your Airworthiness Authority, do a second inspection of the flap controls.
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AMM
3. Repair Data for the Flap Shells.
Figures 2 and 3 show the layers of glass/carbon fiber cloth in the flap shells. Use this data when you need to repair the flap.
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 flap, 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 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.
Doc # 6.02.01 Page 203
Rev. 4 09 Jan 2003
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Item No. Layers Reference No. Type Remarks
2 1 8.4548.60 glass Twill 2/2 ±45o
3 1 8.3520.8 carbon ±45o
4 1 8.3520.8 carbon ±45o, 80 mm x 270 mm.
5 1 H 60 3 mm rigid foam
7 1 8.3520.8 carbon ±45o, 70 mm x 230 mm.
8 1 8.3520.8 carbon ±45o, 90 mm wide.
9 - 14 1 each 8.3520.8 carbon ±45o, 30 mm x 70 mm.
15 1 8.4548.60 glass Twill 2/2 ±45o
Figure 2: Layers of Cloth in the Flap Bottom Shell
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AMM
3
7
Item No. Layers Reference No. Type Remarks
2 1 8.4548.60 glass twill 2/2 ±45o
3 2 8.3520.8 carbon ±45o, 80 mm x 80 mm.
4 1 8.3520.8 carbon ±45o
5 1 H 60 3 mm rigid foam
7 1 8.3520.8 carbon ±45o
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本文鏈接地址：鉆石40飛機維護手冊 DA 40 SERIES AMM 4(72)
