Diamond DA20-C1 - Weighing Report; Weight and Balance

DA20-C1 Flight Manual Supplement 4
Doc # DA202-C1 April 06, 2010 Page S4 - 14
Revision 25 DOT Approved
6. WEIGHT AND BALANCE
Model: DA20-C1 Serial Number Registration
Data with reference to the Type Certificate Data Sheet and the Flight Manual
Reference Datum: Leading edge of wing at root rib.
Horizontal reference line: Wedge 1000:55.84, 2000mm (78.7 in) aft of the step in the fuselage at the canopy
edge
Equipment list - dated Cause for Weighing
Weight and Balance Calculations
Weight Condition:
Include brake fluid, engine oil and Unusable fuel (Type 2 system, 2 liters unusable, 3.18 lbs/1.44 Kg)
Finding Empty Weight:
Finding Arm: (Measured)
Support Gross
([kg]) (lbs)
Tare
([kg]) (lbs)
Net Weight
([kg]) (lbs)
Lever Arm
([m]) (in)
Front G
1
X
1
=
Rear G
2LH
X
2LH
=
Rear G
2RH
X
2RH
=
EMPTY WEIGHT (G)
Finding Empty - Weight Center of Gravity (X
CG
):
Empty Weight CG Formula:
(G
1
x X
1
)+(G
2LH
x X
2LH
)+(G
2RH
x X
2RH
)
X
CG
=
G
1
+ G
2LH
+ G
2RH
Finding Empty - Weight Moment:
Empty-weight Moment (M) = Empty Weight (G) x Empty-weight CG
(Positive results indicate, that CG is located aft of RD)
Finding Maximum Permitted Useful Load:
Maximum Weight [kg] (lbs) 800 kg/1764 lbs
Empty Weight [kg] (lbs)
Maximum useful Load [kg] (lbs)
Empty Weight (G):
([kg]) (lbs)
Empty-weight Moment (M):
([kg
.
m]) (in
.
lbs)
Place / Date Authorizing Stamp Authorizing Signature
Figure 6.3. Weighing Report