Diamond DA 40, Flight Manual

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DA 40 AFM Mass & Balance
Doc. # 6.01.01-E Rev. 8 01-Dec-2010 Page 6 - 5
6.4 FLIGHT MASS AND CENTER OF GRAVITY
The following information enables you to operate your DA 40 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, taking the fuel tank size into account:
Empty Mass
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' in Table 6.4.3 - CALCULATION OF LOADING CONDITION.
Oil
The difference between the actual amount of oil in the engine (check with dipstick) and
the maximum oil quantity is called ‘Oil not added’; this mass and its related moment are
counted as negative. The empty mass of the airplane is established with the maximum
amount of oil in the engine, thus the ‘missing’ oil must be subtracted. If the airplane is
flown with maximum oil, the ‘Oil not added’ entry should be zero.
In our example 6.0 qts have been measured on the dip-stick. We are thus 2.0 qts short
of the maximum, which equates to 1.9 liter. Multiplying this quantity by the mass density
of 0.89 kilograms per liter gives a mass of ‘Oil not added’ of 1.7 kg. (in US units: 2.0 qts
multiplied by the mass density of 1.86 lb/qts gives a mass of 3.7 lb).