Calculation Of Loading Condition - Diamond DA 40 Flight Manual

Mass & Balance
Moments
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.

Total Mass and CG
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 7 for the condition with empty
fuel tanks, and row 9 for the pre take-off condition). The resulting CG position must be
within the limits.
For airplanes equipped with the optional Long Range Tank,
a restricted range of permitted CG positions applies.
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.
Graphical Method
Diagram 6.4.2 - LOADING DIAGRAM is used to determine the moments. The masses
and moments for the individual items of loading are added. Then Diagram 6.4.5 -
PERMISSIBLE MOMENT RANGE is used to check whether the total moment associated
with the total mass is in the admissible range.
The result found with the graphical method is however inaccurate. In doubtful cases the
result must be verified using the exact method given above.
Page 6 - 8
CAUTION
Rev. 8 01-Dec-2010
DA 40 AFM
Doc. # 6.01.01-E