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ExErcoupeGuy,
I just sent you a PM. Alex |
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Before further flight ??
Before further flight ??
If you have less than 100 hours why would you need to check before further flight if it is OK to fly it for 100 hours after you check it ? Unless Vans thinks that the crack may be associated with the bending process of the HS-1202 Spars ? I think this is possible ? If there is no cracks I wonder if the patch on top of the skin is necessary? This will look like a Patch in my View. Joe Dallas |
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The premise is that if no cracking was induced during the first 100 hours, then it is likely that nothing serious would happen after another 100 hrs. The patch on the top of the AST skin has nothing to do with the S.B. for the stabilator spar. They just happened to be published at about the same time. I am pretty sure the AST S.B. is clear in saying that the skin doubler is only required if pre-existing cracks are found at inspection. Otherwise just the change in ribs is required. |
Scott,
Regarding the stabilator SB, does the HS-01231C gusset (figure 4) fit beneath the skin or on top? Thanks, Alex |
I too am having some difficulty visualizing all this from the drawings.
Photos from the first people will be valuable. Quote:
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Scott
Figure shows the patch on the top adding as shear connection to the hinge bracket , in my view Joe Dallas Quote:
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The doubler on the top and bottom of the stabilator is an important component for longevity and crack avoidance. Call it a patch if you want, but it is a doubler.... just like all of the triangular doublers that are on the exterior of the fuselage belly. |
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