An in-flight wing is composed of three stringers and three skins. The origin of the structural coordinate frame is located at the cross-section centroid (yc = zc = 0) and the cross-section properties of the entire wing section in this reference frame are (A = 4 in2, Iyy = 8 in4, Izz = 600 in4, and Iyz = 9 in4). As a result of aerodynamic loading, the stress resultants at the wing root (x = 0 inch) are determined to be (Vx = 0 lb, Vy = 500 lb, Vz = 2,000 lb, Mx = -20,000 lb-in, My = -159,088 lb-in, and Mz = 59,672 lb-in). The stringer material has a tension allowable stress (σxx* = 40,000 lb/in2) and a compression allowable stress of (σxx* = -35,000 lb/in2). Calculate the margin of safety (MS) in the lower stringer (#2).