Loading Quiz

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.

Before any flight, verify that the unmanned aircraft is correctly loaded by determining the weight and balance condition. Review any available manufacturer weight and balance data and follow all restrictions and limitations.

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.

Excessive weight reduces the flight performance in almost every respect, including a shorter endurance. In addition, operating above the maximum weight limitation can compromise the structural integrity of an unmanned aircraft.

It is the responsibility of the remote PIC to use the most current weight and balance data when planning a flight and operating the sUAS.