> The FAA did not say anything different to what has been explained to you by me and by FAR Part 25.
> As the FAA correctly points out, "Ultimate load = Limit load x a factor of safety (1.5) thus Ult. = Limit x 1.5 "
It takes real chutzpah to claim that that's what you have "explained" to me, since it's precisely what I've been saying since my first post about your video, and which you have been trying to deny based merely on your own inability to comprehend what "load" means in this context, much less "limit load."
> Notice he doesn't say Ultimate "case" = Limit "case" x a factor of safety (1.5) thus .....
Just when I thought you might be grasping it, again you get lost with just the terminology. A "case" is a condition or situation that the designer must analyze, such as those cases specified in FAR 25.305 about withstanding vibration and buffeting at Vd/Md. The loads calculated for the limit cases are what are multiplied by 1.5.
> As you have finally understood after I have repeatedly tried to explain it to you (and realizing not even Beachy is supporting your BS interpretations of FAR Part 25), Vd is not a limit load it is a speed.
What nerve; what I actually have said is still there, Balsamo. I have never claimed that Vd is a "limit load." That is another misconception based on your own confusion about the subject matter. I have claimed that the conditions in FAR 25.305 are limit cases, so an engineer is required by FAR 25 to take the loads imposed by those conditions as limit loads, and therefore they are required to multiply those loads by 1.5 and then design a structure that should withstand those ultimate loads.
Regardless of your inability to comprehend it, Mr. Johnson unequivocally confirmed that the conditions in FAR 25.305 are limit cases, not ultimate cases, so those calculated loads -- all of them, not just flight loads -- must be multiplied by 1.5. You are simply wrong; you do not know what you're talking about even after the FAA explains it to you.
Regardless of you inability to comprehend why, the reserve strength that results from that 1.5 factor means there is an unknown margin of safety when flying beyond Vd, depending on how accurately the engineers estimated those limit loads and structural strength. You are simply wrong; you don't know what you're talking about.
You're busted.
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