31-04. (H) MASS AND BALANCE DETAILS OF AIRCRAFT
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1. The following results were obtained after weighing a helicopter:
Front point: 220 kg
Right rear point: 500 kg
Left rear point: 480 kg
The helicopter datum is 3,40 m forward of the rotor axis. The front point is located 2,00 m forward of the rotor axis and the rear points are located 0,50 m aft of the rotor axis. The longitudinal CG position in relation to the datum is:
2. (Refer to figure 031-57)
Referring to the Pilot’s Flight Manual for the transport helicopter TETH1, the maximum load for the aft cargo bay in section C is:
3. What is the centre of gravity position of the aircraft in the diagram, given:
Left main: 1.620 kg
Right main: 1.632 kg
Nose: 640 kg
4. The weights measured at the landing gear of an aircraft are as follows:
Nose wheel (55 inches aft of datum): 475 lbs
Right main wheel (121 inches aft of datum): 1.046 lbs
Left main wheel (121 inches aft of datum): 1.040 lbs
The CG of the aircraft is:
5. At the re-weighing of an aircraft, who is responsible for establishing the DOM?
