A$2.$ A simplified fuselage cross$-$section is shown in Figure A$2.$ The cross$-$section is $5\mathrm{.}0m$ long, and it is

simply supported. It is loaded uniformly with a live load of $2\mathrm{.}4$kPa and assumed to be designed in one$-$

way bending. Consider the self$-$weight of the section and determine the thickness $"h"$ of the section

required $("h"$ is for all three plates$).$ Use $F_y=350$MPa.

NOTE: You may change the other dimensions if the design becomes impractical.

Figure $A-2$