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simplicity and convenience.
AIRCRAFT
Manual Organization DA 40 Series
AMM
Page 6
20 Sep 2007 02-00-00 Doc # 6.02.01
Rev. 5
5 10 15 20 25 30 35 40 45 50 55 60 65 70 75 80 85 90 95 100
10
5
15
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55
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70
Foot.Pound (ft.lb.)
Newton.Metre (Nm)
9. Torque Conversion Graphs
Use Figure 1 for conversion of torque values Nm - ft.lb. Use Figure 2 for conversion of Nm - in.lb.
Figure 1: Nm - ft.lb
Find the Nm value on the horizontal axis. Move vertically to the solid black diagonal line. Then move
horizontally to the vertical axis. Read the value in ft.lb.
Example: To convert 24 Nm to ft.lb., find 24 Nm on the horizontal axis (see the dashed line). Follow
the dashed line vertically to the solid black diagonal line. Then follow the dashed line horizontally to
the vertical axis. Read the value of 17.7 ft.lb.
AIRCRAFT
DA 40 Series
AMM
Manual Organization
Doc # 6.02.01
Rev. 5 02-00-00 Page 7
20 Sep 2007
0 0.5 1.0
5
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15
20
25
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35
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1.5 2.0 2.5 3.0 3.5 4.0 4.5 5.0 5.5 6.0 6.5 7.0 7.5 8.0 8.5 9.0 9.5 10.0
Inch.Pound (in.lb.)
Newton.Metre (Nm)
Figure 2: Nm - in.lb
Find the Nm value on the horizontal axis. Move vertically to the solid black diagonal line. Then move
horizontally to the vertical axis. Read the value in in.lb.
Example: To convert 4.4 Nm to in.lb, find 4.4 Nm on the horizontal axis (see the dashed line). Follow
the dashed line vertically to the solid black diagonal line. Then follow the dashed line horizontally to
the vertical axis. Read the value of 39 in.lb.
AIRCRAFT
Manual Organization DA 40 Series
AMM
Page 8
20 Sep 2007 02-00-00 Doc # 6.02.01
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AIRCRAFT
DA 40 Series
AMM
General Description
Doc # 6.02.01
Rev. 5 03-TITLE Page 1
20 Sep 2007
CHAPTER 03
GENERAL DESCRIPTION OF THE
AIRPLANE
AIRCRAFT
General Description
DA 40 Series
AMM
Page 2
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AIRCRAFT
DA 40 Series
AMM
General Description
Doc # 6.02.01
Rev. 5 03-CONTENTS Page 1
20 Sep 2007
TABLE OF CONTENTS
CHAPTER 03
GENERAL DESCRIPTION OF THE AIRPLANE
1. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1
2. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1
3. Equipment Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4
AIRCRAFT
General Description
DA 40 Series
AMM
Page 2
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AIRCRAFT
DA 40 Series
AMM
General Description
Doc # 6.02.01
Rev. 5 03-00-00 Page 1
20 Sep 2007
CHAPTER 03
GENERAL DESCRIPTION OF THE AIRPLANE
1. General
Diamond Aircraft Industries GmbH, N. A. Otto-Straße 5, A-2700 Wiener Neustadt, Austria, make the
DA 40 airplane.
2. Description
The DA 40 is a single-engine, four seat, low-wing monoplane. It has a cantilever wing and a ‘T’ tail.
The airplane structure is fiber-reinforced plastic composite. This gives a very strong but light structure.
Figure 1: DA 40 Airplane
AIRCRAFT
General Description
DA 40 Series
AMM
Page 2
20 Sep 2007 03-00-00 Doc # 6.02.01
Rev. 5
The semi-monocoque fuselage is a glass-fiber reinforced-plastic (GFRP) shell with GFRP bulkheads
and stiffeners. Uni-directional carbon fiber bands give extra strength and stiffness in many areas. Left
and right half-shells bond together with a center section to make the fuselage. The center section
makes the bottom of the cockpit. It has the main bulkheads which connect to the spars in each wing.
The vertical stabilizer has two GFRP half-shells that are part of the fuselage shells.
The cantilever wing is a semi-monocoque structure. Each wing has two I-shaped spars with webs
made form GFRP/rigid foam sandwich and caps made from CFRP bands. Each wing has top and
bottom shells made of CFRP/GFRP/rigid foam sandwich which bond to the spars. GFRP ribs and
webs bond to the spars and shells to complete the structure.
The wings attach to the fuselage center section. Each wing has two stump-spars. Four large bolts
attach each wing to the fuselage main bulkheads. Standard ailerons and electrically operated flaps
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