Diamond Aircraft DA 40 NG, Airplane Flight Manual

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DA 40 NG AFM Mass & Balance
Doc. # 6.01.15-E Rev. 3 01-Jul-2014 Page 6 - 5
6.4 FLIGHT MASS AND CENTER OF GRAVITY
The following information enables you to operate your DA 40 NG within the permissible
mass and balance limits. For the calculation of the flight mass and the corresponding CG
position the following tables and diagrams are required:
6.4.1 - MOMENT ARMS
6.4.2 - LOADING DIAGRAM
6.4.3 - CALCULATION OF LOADING CONDITION
6.4.4 - PERMISSIBLE CENTER OF GRAVITY RANGE
6.4.5 - PERMISSIBLE MOMENT RANGE
The diagrams should be used as follows:
1. Take the empty mass and the empty mass moment of your airplane from the Mass
and Balance Report, and enter the figures in the appropriate boxes under the column
marked ‘Your DA 40 NG' in Table 6.4.3 - CALCULATION OF LOADING CONDITION.
2. Read the fuel quantity indicators to determine the fuel quantity. If an indicator shows
14 US gal, up to 19.5 US gal can be in the Long Range Tank. In this case, the exact
quantity must be determined with the alternate means for fuel quantity indication.
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 total moments may
be rounded to whole numbers. The CG position is calculated by dividing the total
moment by the total mass (using row 9 for the condition with empty fuel tanks, and
%
row 11 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.