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Recent content by B767

  1. B767

    Fatigue Loading for SSI in Shear

    LiftDivergence, great input into this conversation, Thank You! Also, thank you all again for your thoughts. A two DER's with huge experience are involved already, a great opportunity for me to increase my knowledge and confidence.
  2. B767

    Fatigue Loading for SSI in Shear

    WKTaylor, it is a 1 piece, machined down from 0.750' thick plate
  3. B767

    Fatigue Loading for SSI in Shear

    rb1957, you're right, in Rooke&Cartwright, Fig 9, gives detail for stress intensity KII/Ko for Mode II cracks. Thanks a lot for that hint!
  4. B767

    Fatigue Loading for SSI in Shear

    ...my apology, SSI - Structural Significant Item
  5. B767

    Fatigue Loading for SSI in Shear

    ...well, I don't think pressure component is in the picture. and this a a plane over 100,000 lbs MTOW, so 14 CFR 337 and 341, for gust and maneuver, in this case maneuver is leading factor 2.5g
  6. B767

    Fatigue Loading for SSI in Shear

    didn't go there yet, but yes, GAG, once per flight cycle, and limit is maybe too conservative!
  7. B767

    Fatigue Loading for SSI in Shear

    ...yes, it is a web repair, absolutely not taking it lightly!!!
  8. B767

    Fatigue Loading for SSI in Shear

    Thank you rb1957 for your thoughts. Yeah, the plane is 737, 2.5g plane, at STA 540 bulkhead, (which is the center wing front spar, so it is not fwd or aft pressure bulkheads. Was thinking to come up with material capability based stress, I think principal stresses approach is valuable. Thanks again!
  9. B767

    Fatigue Loading for SSI in Shear

    Good morning, Trying to come up with a fatigue loading on a bulkhead web(not pressurized). As we know, the web is primarily designed for shear, so the fatigue cracks would be more like Mode II (in-plane shear) or Mode III (out-of-plane shear, transverse shear), but not the favorite Mode I where...
  10. B767

    Thickness Correction Factor Kt for Fastener Joints

    Oo, thanks LiftDivergence, that's a good one, agree on your thoughts, and usually I am referring the joint strength data which is different than actual fastener strength, Boeing have a pretty good data, Northrop and Lockheed and MMPDS as well present these data. So, in Niu's first book is the...
  11. B767

    Thickness Correction Factor Kt for Fastener Joints

    I have requested more clarification what do they mean for that factor, and you said unless they show reliable data and reference so I can be based on, I will not include this factor in the report. But that make sense for me, since you and LiftDivergence were inclined towards bolt bending idea...
  12. B767

    Thickness Correction Factor Kt for Fastener Joints

    Thanks rb1957, still digging and thinking over it, but if can not find a reliable reference for this factor, will not included, fitting factor 1.15 would be good enough. Thanks for your inputs and thoughts!
  13. B767

    Thickness Correction Factor Kt for Fastener Joints

    Thanks LiftDivergence, that make sense, thanks a lot, will think about it!
  14. B767

    Thickness Correction Factor Kt for Fastener Joints

    ...more details of the design, a 1" wide flange of a unit 0.125" thick is fastened joint to a .071"2024-T3 Alclad sheet using AN3 bolt, and have been asked why material thickness correction factor (Kt) is not included. Never used this material thickness correction factor before for a...
  15. B767

    Thickness Correction Factor Kt for Fastener Joints

    Good Morning Colleagues, My question is about thickness correction factor Kt and please correct me if I am wrong - when analyzing bolt or rivet joints, this Kt is the one responsible for the aluminum sheet being joint and Kt take care for the hole diameter mismatch, and when D/T ratio is higher...
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