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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)
Front G1
Rear G2LH
Rear G2RH
EMPTY WEIGHT (G)
Lever Arm
([m]) (in)
X1 =
X2LH =
X2RH =
Finding Empty - Weight Center of Gravity (XCG):
Empty Weight CG Formula: (G1 x X1)+(G2LH x X2LH)+(G2RH x X2RH)(XCG) = G1 + G2LH + G2RH
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) 750 kg/1653 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
Doc # DA202-C1 April 06, 2010 Page 6 - 5
Revision 25 DOT Approved
6.3. WEIGHTAND BALANCE REPORT
The empty weight and Empty Weight CG position data determined prior to delivery of the airplane is the first entry in the Weight and Balance Report. Each change of the installed equipment as well as each repair affecting the empty weight, the CG position of the empty weight or the empty weight moment must be entered in the Weight and Balance Report included at the back of this manual. The following Sample W eight and Balance Report (see Figure 6.4) is for reference only.
using the lat st weight and b alance information when performing a weightEnsure that you are e and balance calculation.
6.4. FLIGHT WEIGHT AND CENTER OF GRAVITY
The following data enables the pilot to operate the DA20-C1 within the required weight and center of gravity limitations.
The following diagrams,
Figure 6.5 Loading Plan
Figure 6.6 Weight & Balance Diagram
Figure 6.7 Calculation of Loading Condition
Figure 6.8 Permissible Center of Gravity Range
and permissible Flight-Weight-Moment
are to be used for calculations of the flight-weight and the center of gravity as follows:
1.
The empty weight and the empty-weight-moment of the airplane should be taken from the weighing report or from the weight & balance report and entered into the form "Calculation of Loading Condition" (see Figure 6.7) in the columns identified with "Your DA20-C1".
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