Page 206 Doc # 6.02.01 09 Jan 2003 Rev. 4
52-10-00
Doors
AMM

Section 52-40
Access Panels

1. General
The DA 40 has a small number of access panels. Panels which must be used often (for example the oil filler panel), have quick-release fasteners. Other panels have the usual screws. Refer to Section
% 71-10 (Lycoming version) or 71-11 (TAE version) for data about the engine cowlings.
2. Description
Figure 1 shows the location of the access panels on the airplane.
Most panels are GFRP moldings. Screws hold the panels in position. There are no special procedures for removing or installing access panels.
Doc # 6.02.01 Page 1
Rev. 4 09 Jan 2003

52-40-00
AMM

VIEW FROM BELOW
Figure 1: Access Panel Locations
52-40-00
Fuselage
AMM

CHAPTER 53
FUSELAGE

Doc # 6.02.01 Page 1
Rev. 4 09 Jan 2003

53-TITLE
AMM

Intentionally left blank
53-TITLE
Fuselage
AMM

TABLE OF CONTENTS
CHAPTER 53
FUSELAGE

1. General ..............................................1

Section 53-10
Fuselage Structure

1.
General ..............................................1

2.
Description............................................3

Maintenance Practices
1.
General ............................................201

2.
Repair Data for the Fuselage Shells.......................201

Doc # 6.02.01 Page 1
Rev. 4 09 Jan 2003

53-CONTENTS
AMM

Intentionally left blank
53-CONTENTS
Fuselage
AMM

CHAPTER 53
FUSELAGE

1. General
The DA 40 fuselage has a semi-monocoque structure. Two GFRP half-shells make the fuselage skin. GFRP frames and webs give the fuselage strength and stiffness. The vertical stabilizer is an integral part of the fuselage.
The fuselage shells have many layers of glass cloth. Some areas have more layers of glass cloth than other areas. This gives more strength and stiffness where it is needed. Rigid foam inserts give stiffness where necessary.
The frames and webs also have many layers of glass cloth. Some areas have layers of carbon fiber cloth or tape to give extra strength. Some components also have rigid inserts of GFRP for attaching brackets or other components.
Section 53-10 gives the data for the fuselage structure.
Doc # 6.02.01 Page 1
Rev. 4 09 Jan 2003

53-00-00
AMM

Intentionally left blank
53-00-00
Fuselage
AMM

Section 53-10
Fuselage Structure

1. General
This Section gives you the data about the fuselage structure. It also includes the vertical stabilizer. See Chapter 51-00 for data about repair to the structure.
All of the main structural components are GFRP rigid moldings. Many layers of glass cloth bond together to make each molding. Some components have layers of carbon fiber cloth. This gives more strength and stiffness.
Most components have rigid GFRP inserts. The inserts give strength and stiffness for attaching other components such as brackets for controls.
Bonding paste (thickened resin) bonds components to other components. Most of the components in the fuselage also bond to the fuselage shell.
Doc # 6.02.01 Page 1
Rev. 4 09 Jan 2003

53-10-00
AMM
AIRCRAFT
Floor Panel
Right Shell

Left Shell

Top Hat Profile
Firewall

Figure 1: Fuselage Shells and Front Fuselage Structure
Page 2 Doc # 6.02.01 09 Jan 2003 Rev. 4
53-10-00
Fuselage
AMM

2. Description
Figures 1 to 4 show the fuselage structure.
A. Fuselage Shells
Two GFRP shells make the outer skin of the fuselage. The shells transmit structural loads. The shells bond to each other at the top and bottom of the fuselage. Each shell has many layers of glass cloth. Some areas have of the shell have more layers to give more strength and stiffness. Some areas have rigid foam inserts to give more stiffness.
　
中國航空網(wǎng) www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：鉆石40飛機維護手冊 DA 40 SERIES AMM 4(51)