By "fudge factor" do you mean the FAA required factor of 1.5 between limit load (the load that can be applied indefinitely with no damage to the structure) and the ultimate load (the load that causes the structure to fail).
And before anyone jumps up and down about how that only applies to FAR 23 certifications, the new sport airplane consensus standard uses the same 1.5 safety factor. AND 1.5 does not apply to everything, there are additional safety factors for specific items. The list from section 5.1.2.2 of the LSA standard is: 2.0 x 1.5 = 3.0 on Castings 1.2 x 1.5 = 1.8 on Fittings 2.0 x 1.5 = 3.0 on Bearings at bolted or pinned joints subject to rotation 4.45 x 1.5 = 6.67 on control surface hinge-bearing loads except ball and roller bearing hinges 2.2 x 1.5 = 3.3 on push-pull control system joints 1.33 x 1.5 = 2 on cable control system joints, seat belt/harness fittings (including the seat if belt/harness is attached to it) ----- Original Message ----- From: "Eric Evezard" <[email protected]> To: "KRnet" <[email protected]> Sent: Sunday, September 26, 2004 1:32 PM Subject: KR> G forces etc > Hi netters, glad to see no netters mentioned the "fudge factor" of about 1 1/2 used by most designers to over design safety into the aircraft.In my young gliding days I used to "push redline" believing the design safety factor would see me through--until I came to my senses.I think this "fudge factor"must be forgotten about and the designers published figures used .The published figures can be adjusted to suit by a person who knows what he is doing---but dont bring the factor into it,-- not in my opinion. > Best Regards to all, > Eric Evezard. > _______________________________________ > to UNsubscribe from KRnet, send a message to [email protected] > please see other KRnet info at http://www.krnet.org/info.html > > >
