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% MÄM 40-089 6) (Aileron Mass Balance) incorporated see figure 2a
% MÄM 40-113 (LRT Rudder for Standard Version)
% incorporated
see figure 3b
% Table 2
% 4) OÄM 40-100, OÄM 40-100/a, OÄM 40-100/b, OÄM 40-100/c
% 5) OÄM 40-130 (figure 3a); OÄM 40-130/a, OÄM 40-130/b (figure 1)
% 6) MÄM 40-089, MÄM 40-089/a, MÄM 40-089/b, MÄM 40-089/c
AIRCRAFT
Standard Practices and
Structures
DA 40 Series
AMM
Page 4
20 Sep 2007 51-60-00 Doc # 6.02.01
Rev. 5
Rudder Elevator Trim Tab
Aileron Wing Flap
LH RH LH RH
weight
incl. BW
nominal
nominal
actual
actual
3.7 to 4.65 kg 5.7 to 6.9 kg 0.28 to 0.39 kg 2.6 to 3.3 kg 4.2 to 5.15 kg
balancing
weight
[kg] or [lb]
Center:
LH: RH:
P
r
residual
moment
16.3 to 21.4 kg.cm -5.0 to 0.0 kg.cm 1.0 to 1.5 kg.cm -2.5 to +0.3 kg.cm 25.5 to 33.1 kg.cm
center line horizontal center line horizontal center line horizontal upper surface horizontal upper surface horizontal
r P r P rP r P r
M = P * r
P ...[kg] or [lb]
r ...[cm] or [in]
Calculation. M = P * r Where M is the residual moment, r (cm or inches) is the distance between the hinge line
and the point where the force P (kg or lb) acts.
Notes. Positive moments are tail heavy, negative moments are nose heavy.
Rudder - weight and residual moment include lower hinge and trim plate.
Elevator - weight and residual moment include trim tab, horn, and trim tab control rods.
Aileron - weight and residual moment include horn, trim plate and hinges.
Wing flaps - Weight and residual moment include horn and hinges.
P
(8.16 to 10.25 lb) (12.57 to 15.21 lb) (0.62 to 0.860 lb) (5.73 to 7.28 lb) (9.26 to 11.35 lb)
(14.15 to 18.57 in.lb) (-4.34 to 0.00 in.lb) (0.868 to 1.302 in.lb) (-2.17 to +0.26 in.lb) (22.13 to 28.73 in.lb)
Figure 2: Weights and Residual Moments Report %%
% (valid for Lycoming Standard Version and TAE Standard Version)
AIRCRAFT
DA 40 Series
AMM
Standard Practices and
Structures
Doc # 6.02.01
Rev. 5 51-60-00 Page 5
20 Sep 2007
Rudder Elevator Trim Tab
Aileron Wing Flap
LH RH LH RH
weight
incl. BW
nominal
nominal
actual
actual
3.7 to 4.65 kg 5.7 to 6.9 kg 0.28 to 0.39 kg 2.6 to 3.15 kg 4.2 to 5.15 kg
balancing
weight
[kg] or [lb]
Center:
LH: RH:
P
r
residual
moment
16.3 to 21.4 kg.cm -5.0 to 0.0 kg.cm 1.0 to 1.5 kg.cm -5.1 to -2.0 kg.cm 25.5 to 33.1 kg.cm
center line horizontal center line horizontal center line horizontal upper surface horizontal upper surface horizontal
r P r P rP r P r
M = P * r
P ...[kg] or [lb]
r ...[cm] or [in]
Calculation. M = P * r Where M is the residual moment, r (cm or inches) is the distance between the hinge line
and the point where the force P (kg or lb) acts.
Notes. Positive moments are tail heavy, negative moments are nose heavy.
Rudder - weight and residual moment include lower hinge and trim plate.
Elevator - weight and residual moment include trim tab, horn, and trim tab control rods.
Aileron - weight and residual moment include horn, trim plate and hinges.
Wing flaps - Weight and residual moment include horn and hinges.
P
(8.16 to 10.25 lb) (12.57 to 15.21 lb) (0.617 to 0.860 lb) (5.73 to 6.94 lb) (9.26 to 11.35 lb)
(14.15 to 18.57 in.lb) (-4.34 to 0.00 in.lb) (0.868 to 1.302 in.lb) (-4.43 to -1.74 in.lb) (22.13 to 28.73 in.lb)
Figure 2a: Weights and Residual Moments Report %%
% (valid for Lycoming and TAE version with 'Aileron Mass Balance', MÄM 40-089, MÄM 40-089 /a,
% MÄM 40-089 /b, MÄM 40-089 /c installed)
AIRCRAFT
Standard Practices and
Structures
DA 40 Series
AMM
Page 6
20 Sep 2007 51-60-00 Doc # 6.02.01
Rev. 5
%
%
%
%
%
%
%
%
%
%
%
%
%
%
%
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%
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%
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%
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%
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%
%
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Figure 2b: Weights and Residual Moments Report %%
% (valid for Lycoming version with 'LRT-Rudder', MÄM 40-113 installed)
Rudder Elevator Trim Tab
Aileron Wing Flap
LH RH LH RH
weight
incl. BW
nominal
nominal
actual
actual
5.7 to 6.9 kg 0.28 to 0.39 kg 2.6 to 3.15 kg 4.2 to 5.15 kg
balancing
weight
[kg] or [lb]
Center:
LH: RH:
P
r
residual
moment
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钻石40系列AMM 2(121)
