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Referencing Appendix 1, Figure 2, use the following steps: 1. Enter the chart at a 30 degree 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 an approximate load factor of 1.2 Gs. 2. Multiply the aircraft weight by the load factor: 33 x 1.2 = 39.6 lbs. Or, working from the table: 33 x 1.154 (load factor) = 38.1 lbs.

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.

The manufacturer is the best source of performance data and information, if available.

When the angle of attack is increased to between 18 and 20 degrees (critical angle of attack) on most airfoils, the airstream can no longer follow the upper curvature of the wing because of the excessive change in direction. The airfoil will stall if the critical angle of attack is exceeded. The airspeed at which stall occurs will be determined by weight and load factor, but the stall angle of attack is the same.

A change in speed during straight flight will not produce any appreciable change in load, but when a change is made in the sUAS flight path an additional load is imposed upon the structure. This is particularly true if a change in direction is made at high speeds with rapid, forceful control movements.Answer (A) is incorrect because the load increases only as the angle of attack is changed, momentarily. Once the climb attitude has been set, the wings only carry the load produced by the weight of the aircraft. Answer (C) is incorrect because in a stall, the wings are not producing lift.