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6.4.3 - 'CALCULATION OF LOADING CONDITION'.
5.
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 8 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.
6.
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 permissible 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.
Doc. No. 7.01.05-E Rev. 5 15-Nov-2007 Page 6 - 7
6.4.1 MOMENT ARMS
The most important lever arms aft of the Datum Plane:
Item Lever Arm
[m] [in]
Occupants on front seats 2.30 90.6
Occupants on rear seats 3.25 128.0
Fuel in main tanks 2.63 103.5
in auxiliary tanks 3.20 126.0
De-Icing Fluid (if equipmentinstalled, O.M 42-053 orO.M 42-054) 1.00 39.4
Baggage in Compartments nose 0.60 23.6
cabin 3.89 153.1
extension 4.54 178.7
Page 6 - 8 Rev. 5 15-Nov-2007 Doc. No. 7.01.05-E
DA 42 AFM
Mass and Balance
6.4.2 LOADING DIAGRAM
Doc. No. 7.01.05-E
Rev. 5 15-Nov-2007
Page 6 - 9
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