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Total range is dependent on both fuel available and specific range. When range and economy of operation are the principle goals, the remote pilot must ensure that the sUAS is operated at the recommended long-range cruise condition. By this procedure, the sUAS will be capable of its maximum design-operating radius, or can achieve lesser flight distances with a maximum of fuel reserve at the destination.

Refer to Figure 2 and use the following steps: 1. Enter the chart at a 60 degrees angle of bank and proceed upward to the curved reference line. From the point of intersection, move to the left side of the chart and read a load factor of 2 Gs. 2. Multiply the aircraft weight by the load factor: 10 x 2 = 20 lbs. Or, working from the table: 10 x 2.0 (load factor) = 20 lbs.

Any mounted equipment should be balanced in a manner that does not adversely affect the CG or result in unsafe performance.

Stall speed increases in proportion to the square root of the load factor. Thus, with a load factor of 4, an aircraft will stall at a speed which is double the normal stall speed.Answer (B) is incorrect because an airplane's tendency to spin does not relate to an increase in load factors. Answer (C) is incorrect because an airplane's stability determines its controllability.

To determine altitude, with the sUAS on the ground, the remote pilot and VO should pace off 400 feet from the sUAS to get a visual perspective of the sUAS at that distance, wherein the remote pilot and VO maintain that visual perspective or closer while the sUAS is in flight.Answer (B) is incorrect because a person may not operate or act as a remote PIC or VO in the operation of more than one UA at the same time. Answer (C) is incorrect because the remote PIC needs to adhere to wire strike avoidance procedures when operating near towers, which are likely to have guy wires.