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2.
Using the Weight & Balance Diagram (see Figure 6.6) determine the mom ent for each part to be loaded, and enter it in the respective column in Figure 6.7.
3.
Add the weights and the moments of each column (point 4 and point 6 in F igure 6.7) and enter the sum in Figure 6.8 "Permissible CG Range and Permissible Flight-Weight-Moment" to check if the values are within the permissible lim its of the loading range.
4.
Figure 6.5 Loading Plan
Example: Pilot and Passenger: 359 lbs. (163 kg) Fuel 14.0 US gal. / 52.9 liters: 93 lbs. (42 kg)
(6.01 lbs. per US gal./0.72 kg per liter)
Result: Moment of Pilot and Passenger: 2021 in. lbs. (24.4 kgm) Moment of Fuel: 3017 in. lbs. (34.8 kgm)
Figure 6.6. Weight & Balance Diagram
Calculation of the Load Limits DA20-C1 (Example) Your DA20-C1
Weight [lbs] (Weight [kg]) Moment [in.lbs] ([kgm]) Weight [lbs] (Weight [kg]) Moment [in.lbs] ([kgm])
1. Empty Weight (use the data for your airplane recorded in the equipment list, including unusable fuel and lubricant). 1153 (523) 12562 (144.740)
2. Pilot and Passenger: Lever Arm: 0.143 m (5.63 in) 359 (163) 2021 (23.286)
3. Baggage: Max. Wt. 44 lbs (20 kg) Lever Arm: 0.824 m (32.44 in) --(--) --(--)
4. Baggage Compartment Extension: Max. Wt. 44 lbs (20 kg) Lever Arm: 1.575 m (62.0 in) --(--) --(--)
5. *Combined Baggage Max. Wt. 44 lbs (20 kg) Lever Arm: 1.20 m (47.22 in) --(--) --(--)
6. Total Weight and Total Moment with empty fuel tank (sum of 1. - 3.) 1512 (686) 14583 (168.026)
7. Usable Fuel Load (6.01 lbs. per US gal./0.72 kg per liter) Lever Arm (32.44 in) (0.824 m) 93 (42) 3017 (34.762)
8. Total Weight and Total Moment, taking fuel into account (sum of 6. and 7.) 1605 (728) 17600 (202.788)
9. Find the values for the total weight (1512 lbs and 1605 lbs) and the total moment (14583 in lbs and 17600 in. lbs) in the center of gravity diagram. Since they are within the limitation range, the loading is permissible.
Figure 6.7. Calculation of Loading Condition
* Combined Ba ggage: For convenience of c l culation use this line if b aggage is to be located in
a both the bagga ge compartment and the baggage exte nsion. The combined total of the baggage must not exceed 44 lbs (20 kg).
Doc # DA202-C1 April 16, 2009 Page 6 - 10
Revision 24 DOT Approved
See example calculat ion of loadin g condition Figure 6.7. Change in center of gravity is due to fuel consumption
Figure 6.8. Permissible Center of Gravity Range and Permissible Flight-Weight-Moment
6.5. EQUIPMENT LIST
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