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Correct control surface balance is critical to flight safety. You must remove a control surface to weigh
and balance it after:
) Any repair to the control surface.
) Painting the control surface.
) Any report of control vibration or flutter in flight.
You can use any convenient method to weigh a control surface. If you use anything to connect the
control surface to the weighing device, (for example, a sling) you must weigh it separately. Then
subtract its weight from the total value. For example, you use a rope sling to lift an aileron with a spring
balance:
) Weight of the aileron and the rope sling = 3.8 kg
) Weight of the rope sling = 0.7 kg
) Weight of the aileron = 3.8 kg - 0.7 kg = 3.1 kg
When you balance a control surface, the pivot angle of the control must be as shown in the Weights
and Residual Moments Report.
We recommend that for balancing the flaps, aileron, elevator and elevator trim tab, you put a suitable
size rod through the hinge bearings. Support the rod at 2 points to keep it horizontal.
To balance the rudder it must be supported at the top pivot pin and the bottom mounting bracket. The
center line of the rudder must be horizontal.
% A. SN’s 40.363 and subsequent, D4.110 and subsequent
% From serial number 40.363 (DA40 with Lycoming engine) and D4.110 (DA40 with TAE 125 engine)
% and subsequent (MÄM 40-113/a incorporated) the Weights and Residual Moments Report shown in
% Figure 1 is applicable for the following Versions of the DA40:
% ) DA40 with Lycoming Engine
% ) DA40 with Lycoming Engine and Long Range Tank (OÄM 40-071)
% ) DA40D with Thielert Engine - DA40 D (OÄM 40-100)
% ) DA40D with Thielert Engine and Long Range Tank (OÄM 40-130)
AIRCRAFT
Standard Practices and
Structures
DA 40 Series
AMM
Page 2
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
3.5 to 4.4 kg 5.7 to 6.9 kg 0.28 to 0.39 kg 2.6 to 3.15 kg 4.0 to 4.8 kg
balancing
weight
[kg] or [lb]
Center:
LH: RH:
P
r
residual
moment
35.6 to 45.8 kg.cm -5.0 to 0.0 kg.cm 1.0 to 1.5 kg.cm -5.1 to -2.0 kg.cm 23.4 to 31.1 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
(7.72 to 9.7 lb) (12.57 to 15.21 lb) (0.617 to 0.860 lb) (5.73 to 6.94 lb) (8.82 to 10.58 lb)
(30.9 to 39.75 in.lb) (-4.34 to 0.00 in.lb) (0.868 to 1.302 in.lb) (-4.43 to +1.74 in.lb) (20.31 to 26.99 in.lb)
% Figure 1: Weights and Residual Moments Report (refer to Table 1 or 2) MÄM 40-113 or LRT
% (OÄM 40-071, OÄM 40-071a, OÄM 40-071b, OÄM 40-071c, OÄM 40-130a, OÄM 40-130b)
% incorporated.
AIRCRAFT
DA 40 Series
AMM
Standard Practices and
Structures
Doc # 6.02.01
Rev. 5 51-60-00 Page 3
20 Sep 2007
% B. Earlier S/N’s
% For earlier serial numbers (MÄM 40-113a NOT incorporated) table 1 shows the Weights and Residual
% Moments Reports for different versions of the DA40 with the Lycoming engine installed. Table 2
% shows the Weights and Residual Moments Reports for different versions of the DA40 with the TAE
% 125 engine installed (OÄM 40-100).
% DA 40 with Lycoming IO360 M1A
% Weights and Residual Moments Report
% Standard Version see figure 2
% OÄM 40-0711) (Long Range Tank) incorporated see figure 1
% MÄM 40-0892) (Aileron Mass Balance)
% incorporated
see figure 2a
% MÄM 40-113 3) (LRT Rudder for Standard
% Version) incorporated
see figure 2b
% Table 1
% 1) OÄM 40-071, OÄM 40-071/a, OÄM 40-071/b, OÄM 40-071/c
% 2) MÄM 40-089/b, MÄM 40-089/c
% 3) MÄM 40-113
%
% DA 40 with TAE 125
% Weights and Residual Moments Report
% Standard Version 4) (OÄM 40-100) see figure 2
% OÄM 40-130 5) (Long Range Tank) incorporated see figure 3a or 1 5)
　
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