DV 20 E AFM Mass and Balance
Doc. No. 4.01.25-E Rev. 2 22-Mar-2022 Page 6 - 7
3. Multiply the individual masses by the moment arms quoted to obtain the moment for
every item of loading and enter these moments in the appropriate boxes in Table
6.4.3 - CALCULATION OF LOADING CONDITION.
4. Add up the masses and moments in the respective columns. The CG position is
calculated by dividing the total moment by the total mass (using row 4 for the condition
with empty fuel tank, and row 6 for the pre take-off condition). The resulting CG position
must be inside the limits.
As an illustration, the total mass and the CG position are entered on Diagram 6.4.4 -
PERMISSIBLE CENTER OF GRAVITY RANGE. This checks graphically that the
current configuration of the airplane is within the permissible range.
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