Editing Fuselage (section)

=== Semi-monocoque ===
{{Multiple image
| header = Monocoque and semi-monocoque design<ref name="phak">{{cite web |title=Pilot's Handbook of Aeronautical Knowledge |url=https://www.faa.gov/regulations_policies/handbooks_manuals/aviation/phak |publisher=[[Federal Aviation Administration]] |access-date=16 January 2023 |date=August 24, 2016}}</ref>{{rp|3-9}}
| image1 = Monocoque fuselage design.png
| caption1 = Monocoque construction uses stressed skin to support almost all loads much like an aluminum beverage can.
| image2 = Semimonocoque fuselage design.png
| caption2 = Semi-monocoque construction, partial or one-half, uses a substructure to which the airplane's skin is attached.
}}

[[File:Fuselage-747.jpg|thumb|upright|Sectioned fuselage of a [[Boeing 747]] showing formers, [[Stringer (aeronautics)|stringers]] and skin all made of [[aluminium]]]]

This is the preferred method of constructing an all-[[aluminium|aluminum]] fuselage. First, a series of [[former]]s in the shape of the fuselage cross sections are held in position on a [[Fixture (tool)|rigid fixture]]. These formers are then joined with lightweight longitudinal elements called [[longeron|stringers]]. These are in turn covered with a skin of sheet aluminum, attached by [[rivet]]ing or by bonding with special adhesives. The fixture is then disassembled and removed from the completed fuselage shell, which is then fitted out with wiring, controls, and interior equipment such as seats and luggage bins. Most modern large aircraft are built using this technique, but use several large sections constructed in this fashion which are then joined with [[fastener]]s to form the complete fuselage. As the accuracy of the final product is determined largely by the costly fixture, this form is suitable for series production, where many identical aircraft are to be produced. Early examples of this type include the Douglas Aircraft [[Douglas DC-2|DC-2]] and [[Douglas DC-3|DC-3]] civil aircraft and the Boeing [[B-17 Flying Fortress]]. Most metal light aircraft are constructed using this process.

Both monocoque and semi-monocoque are referred to as "stressed skin" structures as all or a portion of the external load (i.e. from wings and empennage, and from discrete masses such as the engine) is taken by the surface covering. In addition, all the load from internal [[Cabin pressurization|pressurization]] is carried (as ''skin tension'') by the external skin.

The proportioning of loads between the components is a design choice dictated largely by the dimensions, strength, and elasticity of the components available for construction and whether or not a design is intended to be "self jigging", not requiring a complete fixture for alignment.