While setting up a loads analysis for a part 23 aircraft we selected to use some parts of the simplified method from the part 23 appendix. In order to understand the context of the entire simplified loads-analysis we set up all of the methods for the aircraft loads, control surfaces, tab and flap loads in our standard spreadsheet form.
These methods generate the design speeds, the V-n diagrams. The spreadsheets also calculate the load per unit span and the moment per unit span around a reference axis for the aileron, elevator, rudder, tabs and flaps.
These methods are only applicable to simple, traditional aircraft configurations. Part 23 Appendix A should be read in its entirety to fully understand the context of these loads methods.
We have created a spreadsheet that contains the integrated method:
and broken out the individual components into separate sheets:
Hope you get some use out of the sheets – let us know what you think!