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The purpose of the rudder is to control yaw. Answer (B) is incorrect because the ailerons control bank. Answer (C) is incorrect because pitch is controlled by the elevator.

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.

At slow speeds, the maximum available lifting force of the wing is only slightly greater than the amount necessary to support the weight of the sUAS. However, at high speeds, the capacity of the flight controls, or a strong gust, may increase the load factor beyond safe limits.Answer (A) is incorrect because the position of the CG affects the stability of the sUAS, but not the total load the wings can support. Answer (C) is incorrect because abrupt control inputs do not limit load.

Prior to each flight, the remote PIC must ensure that any object attached to or carried by the small unmanned aircraft is secure and does not adversely affect the flight characteristics or controllability of the aircraft.

Referencing Appendix 1, Figure 2, use the following steps: 1. Enter the chart at a 30 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 an approximate load factor of 1.2 Gs. 2. Multiply the aircraft weight by the load factor: 50 x 1.2 = 60 lbs. Or, working from the table: 50 x 1.154 (load factor) = 57.7 lbs.