53-10-00
AMM
Figure 4: Fuselage Structure - Vertical Stabilizer
53-10-00
Fuselage
AMM
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.
Doc # 6.02.01 Page 9
Rev. 4 09 Jan 2003
53-10-00
AMM
Intentionally left blank
53-10-00
Fuselage
AMM
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.
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.
Doc # 6.02.01 Page 201
Rev. 4 09 Jan 2003
53-10-00
AMM
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
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：钻石40飞机维护手册 DA 40 SERIES AMM 4(53)
