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Kilogram centimeter [kg.cm]
Inch pound [in.lb(s)]
[kg.cm] / 1.152 = [in.lbs]
Dimensions And Areas
DA20-C1 AMM
Page 2
19 Dec 1997 06-00-00 Doc # DA201-C1
Rev. 0
Figure 1: Overall Dimensions
DA20-C1 AMM
Dimensions And Areas
Doc # DA201-C1
Rev. 14 06-00-00 Page 3
30 Oct 2008
2. Dimensions
DA20-C1
Overall Dimensions
Wing span 10.87 m (35 ft 8in)
Length 7.24 m (23 ft 9in)
Height (Nominal) 2.1 m (6 ft 11in)
Wing
Airfoil Wortmann FX 63-137/20 HOAC
Wing area 11.6 m² (125 ft2)
Dihedral (Nominal) 4°
Angle of incidence 3°
Aspect ratio 10
Horizontal Tail Surfaces
Span 2.670 m (8ft 9in)
Angle of incidence -4°
Landing gear
Wheel Track 1860mm nominal
Wheel base 1.9 m (6ft 3in)
Nose wheel 5.00 - 4
Main wheel 380*150/6.00-15
5.00 - 5 (6 PLY)
Dimensions And Areas
DA20-C1 AMM
Page 4
30 Oct 2008 06-00-00 Doc # DA201-C1
Rev. 14
Figure 2: Control Surface Deflections
DA20-C1 AMM
Dimensions And Areas
Doc # DA201-C1
Rev. 15 06-00-00 Page 5
30 Apr 2009
ITEM DEFLECTION WEIGHT STATIC MOMENTS
BEFORE BALANCING AFTER BALANCING TRAILING ARM MOMENT
BALANCE EDGE
LIMITS ACTUAL LIMITS ACTUAL WEIGHT 3 LIMITS ACTUAL WEIGHT LIMITS ACTUAL
(degrees) (degrees) (Kg) (Kg) (Kg) (Kg) (Kg) (Kg) (cm) (Kg-cm) (Kg-cm)
LEFT AILERON UP 14.5° to 16.5° (1.6 to 2.1) 1 (0.65) 2.1 to 2.7 1 2.55 to
(with Trim Tab) DOWN 12.5° to 14.5° 6.71 1
RIGHT AILERON UP 14.5° to 16.5° (1.6 to 2.1) 1 (0.65) 2.1 to 2.7 1 2.55 to
DOWN 12.5° to 14.5° 6.71 1
CRUISE -1° to +1° 28.55 to
LEFT FLAP T/O 14° to 16° (3 to 4) 1 37.2 1
LAND 44° to 46°
CRUISE -1° to +1° 28.55 to
RIGHT FLAP T/O 14° to 16° (3 to 4) 1 37.2 1
LAND 44° to 46°
ELEVATOR UP 24° to 26° (2.25 to 2.75) 1 (0.79) 0 to
DOWN 14° to 16° 3.5 2
RUDDER LEFT 26° to 28° (2.0 to 2.8) 5 (1.9) 3.3 to 4.7 4 13.25 to
(with Trim Tab) RIGHT 26° to 28° 18.35 4
() Nominal Weight, may vary
1. Include hinges and control surface horn
2. Include hinges, control horn, mass balance. Do not include the vertical pushrod.
3. Include mass balance only
4. Include lower mounting bracket
5. Composite part only
Figure 3: Adjustment Report
Dimensions And Areas
DA20-C1 AMM
Page 6
30 Apr 2009 06-00-00 Doc # DA201-C1
Rev. 15
ITEM LIMITS ACTUAL
FLAP PRELOAD LEFT 3.05 to 5.10
(Kg) RIGHT Kg
DIHEDRAL LEFT 290 to 330*
(mm) RIGHT
LEADING EDGE
LEFT
SWEEP BACK
(mm)
RIGHT 20 TO 55*
SYMMETRY
LEFT
max. diff.
CHECK RIGHT 50 mm
RUDDER
CABLE TENSION
13.25 to
17.33 kg
4.5-9.0 kg
(10-20 lbs)
No Outside Handles
CANOPY
UNLATCHING
FORCE
6.8-11.3 kg
(15-25 lbs)
With Outside Handles
* measured at 4400 mm from the wing root rib
ITEM LIMITS ACTUAL
HORIZONTAL
STABILIZER -4° ± 0.5°
INCIDENCE degrees
MAIN LANDING 0° to 4°
GEAR
CAMBER
(0º to 2º
desirable)
MAIN LANDING
GEAR 0º ± 0.5º
per side
TOE IN Total Toe
(Included angle)
0º ± 0.5º
MAIN LANDING
GEAR
TRACK
1860mm
NOMINAL
NOSE GEAR 3.06 to 5.10
FRICTION Kg
Figure 4: Adjustment Report
DA20-C1 AMM
Dimensions And Areas
Doc # DA201-C1
Rev. 9 06-00-00 Page 7
29 Apr 2004
3. Adjustment Values
The measurements of the DA20-C1 are recorded on an Adjustment Report at the factory when the
aircraft is built. See Figures 2 and 3. This Report becomes part of the aircraft records.
When you measure the dimensions, use the Adjustment Report as a reference for deviations.
Note: The Static Moments given in this Chapter are trailing edge heavy.
4. Control Surface Gaps
The gaps between control surfaces and wings and stabilizers must be at least 3 mm (0.12 in) wide.
5. Weight And Static Moments Of Control Surfaces
WARNING: IF YOU REPAINT (OR DO REPAIRS) TO THE CONTROL SURFACES,
YOU MUST MAKE SURE THAT THE WEIGHTS AND STATIC
MOMENTS OF THE CONTROL SURFACES ARE NOT MORE THAN
THE VALUES IN THE ADJUSTMENT REPORT. THIS WILL PREVENT
CONTROL SURFACE FLUTTER.
To measure the static moments you must remove the control surface from the aircraft. Then
support the control surface at the hinge line. The horns remain attached to the control surface.
Refer to Chapter 51-60 for the procedures.
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