31-05. DETERMINATION OF CG POSITION
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1. Using the data given in the load and trim sheet, determine from the following the correct values for the Takeoff Mass and the position of the centre of gravity at that mass if the fuel index correction to be applied is given as -0,9.
2. The CG of an aircraft is at 25% MAC and MAC is 1 m. The aircraft has 2 holds, hold 1 is 7 m aft of the datum and hold 2 is 22 m aft of the datum. If the aircraft mass is 38.000 kg, what load must be transferred from hold 1 to hold 2 to move the CG to 40% MAC?
3. With respect to a multi-engine piston powered aeroplane, determine the CG location at takeoff in the following conditions: Basic Empty Mass: 3.210 lbs Basic arm: 88,5 in One pilot: 160 lbs Front seat passenger: 200 lbs Centre seat passengers: 290 lbs (total) One passenger rear seat: 110 lbs Baggage in zone 1: 100 lbs Baggage in zone 4: 50 lbs Zero Fuel Mass: 4.120 lbs Moment at Zero Fuel Mass: 377.751 Ibs.in Block Fuel: 100 US Gal Trip Fuel: 55 US Gal Fuel for start up and taxi (included in Block Fuel): 3 US Gal Fuel density: 6 lbs/US Gal
4. A loaded aircraft weighs 4.200 lbs with a CG at 9 inches AFT of the datum. An extra 200 lbs is loaded into the aircraft 40 inches FWD of the datum. The new CG position is:
5. The planned Takeoff Mass of an aeroplane is 190.000 kg, with its centre of gravity located at 29% MAC (Mean Aerodynamic Cord). Shortly prior to engine start, the local staff informs the flight crew that an additional load of 4.000 kg must be loaded in cargo 4. After loading this cargo, the new centre of gravity location will be:
