1.For example, let's examine the pitching moment imposed on a wing cross-section, caused by an aileron deflection movement downward. Assume the centroid is at the midpoint of the wing chord (not including the aileron). Using the examples provided in the presentation slides, what will be the pitching moments for the following upward forces: 20 lbs., 30 lbs., 40 lbs., and 50 lbs.? Can you now see why a wing needs a certain amount of rigidity? Please explain.

2.Consider a main landing gear strut of an aircraft weighing 40,000 lbs. Using the examples provided in the presentation slides, what will be the axial stress (compression) of a solid strut with a diameter of 4 in.? Assume the nose wheel has not yet touched down and that the aircraft weight is evenly distributed between both of the main landing gear. Also, assume the landing force is equivalent to twice the aircraft weight.

3.From an earlier presentation (Module 2B) we learned how to calculate g-loading from a known bank angle (). Consider an aircraft weighing 40,000 lbs. and using the examples provided in the presentation slides, what will be the imposed load on the aircraft wings for the following bank angles: 15, 30, 45, and 60? If we desire to include a Factor of Safety of 1.50, what will be the allowable stress (material strength required) for the overall wing structure that experiences a 60 bank angle?

4.Consider a steel bar with the dimensions of 2 in. wide, 1 in. thick, and a length of 3 ft. Imagine that this bar is affixed at one end from a hoist and the other end has a weight attached and suspended on it. Using the examples provided in the presentation slides, what will be the axial stress (tension) of this bar if the weight is 1,000 lbs.? For 3,300 lbs.? For 5,000 lbs.? Assume the weight of the bar is negligible.

5.Explain in your own words, the different types of riveted-joint failures and identify analyses used.