Typical airframe "panels" are constructed from either 2024-T3 or 7075-T6 aluminium alloy.  They are usually coated or clad with pure aluminiun for enhanced corrosion protection.

The thickness of the panels depends on the type of aircraft the kind of structure and the structural loads it must withstand. Common thicknesses range from 0.025 in. - .2 inches.

To prevent corrosion, most structure has a surface conversion treatment applied.  These are either alodine or irridite.  Irridite can not be used on structure that requires electrical grounding,instrument panels for examlpe; it is not a good conducter.

Final finish is usually a chromate primer and a top coat, although some fuselages are left unpainted.

Hope this helps,

Nigel Waterhouse
n_a_waterhouse@hotmail.com

A licensed aircraft mechanic and graduate engineer. Attended university in England and graduated in 1996. Currenty,living in British Columbia,Canada, working as a design engineer responsible for aircraft mods and STC's.

Thank you for the helpful note. Bill B. 717-986-3040.

William H. Bernhart, P.E.

You are more than welcome, any more questions, don't hesitate to ask.

Ph 250 491 5555

Nigel Waterhouse
n_a_waterhouse@hotmail.com

A licensed aircraft mechanic and graduate engineer. Attended university in England and graduated in 1996. Currenty,living in British Columbia,Canada, working as a design engineer responsible for aircraft mods and STC's.

Ooops, I made an error, irridite is the good conductor, alodine is the bad conductor!

Nigel Waterhouse
n_a_waterhouse@hotmail.com

A licensed aircraft mechanic and graduate engineer. Attended university in England and graduated in 1996. Currenty,living in British Columbia,Canada, working as a design engineer responsible for aircraft mods and STC's.

I use MIL-STD-464 as a reference for application.
You can find it at
http://stinet.dtic.mil/str/dodiss4_fields.html

Justin Young
youngj921@asme.org