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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 D' in Table 6.4.3 - ‘CALCULATION OF LOADING CONDITION’. % 2. Read the fuel quantity indicators to determine the fuel quantity. If an indicator shows % 15 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 mean 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 5 for the condition with empty fuel tanks, and row 7 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. % Doc. No. 6.01.05-E Revision 2 30-Apr-2003 Page 6 - 5
Doc. No. 6.01.05-E Revision 1 03-Mar-2003 Page 6 - 6
% Doc. No. 6.01.05-E 6.4.3 CALCULATION OF LOADING CONDITION |