Compression inside of bend Tension outside of bend Shear along imaginary line (dotted) Bent structural member A. Tension B. Compression D. Shear E. Bending (the combination stress) C. Torsion Figure 1-14.  The five stresses that may act on an aircraft and its parts.  the inside of the bend and stretched on the outside of the bend.  A single member of the structure may be subjected to  a combination of stresses. In most cases, the structural  members are designed to carry end loads rather than side  loads. They are designed to be subjected to tension or  compression rather than bending.  Strength or resistance to the external loads imposed during  operation may be the principal requirement in certain  structures. However, there are numerous other characteristics  in addition to designing to control the five major stresses that  engineers must consider. For example, cowling, fairings, and  similar parts may not be subject to significant loads requiring  a high degree of strength. However, these parts must have  streamlined shapes to meet aerodynamic requirements, such  as reducing drag or directing airflow. The fuselage is the main structure or body of the fixed-wing  aircraft. It provides space for cargo, controls, accessories,  passengers, and other equipment. In single-engine aircraft,  the fuselage houses the powerplant. In multiengine aircraft,  the engines may be either in the fuselage, attached to the  fuselage, or suspended from the wing structure. There are two  general types of fuselage construction: truss and monocoque. A truss is a rigid framework made up of members, such as  beams, struts, and bars to resist deformation by applied loads.  The truss-framed fuselage is generally covered with fabric.  The truss-type fuselage frame is usually constructed of steel  Fixed-Wing Aircraft Fuselage Truss-Type 1-8