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le Ile e vxI kr : ` - '� vr 11 ax s II %I AI'A ,�,.< 2 = ^: x `C`t ukx , :E "t r- ,s zs.* .+ + r .�i�;: a.xax t . �+., .:` :-.. , x o �- , . - ' — �' . «c �. . � . '% , ' }' _ t ,` „ , K , -, ' .w.e ' '.o' c- ov. ,a .r .� -w mss a 00 Modulus of Elasticity as derived below 1 , 146 ksi Stiffness , E . I. 3 . 69E+091b - inch Yield Stress in Bending 9 . 1 ksi Weight 68 - 83 lb/ft Table 6B Structural Properties for Medium Duty CP Member Size 16 inch O . D . Modulus of Elasticity as derived below 622 ksi Stiffness , E . T. 2 . 0E+09 lb - inch Yield Stress in Bending 4 . 9 ksi Weight 61 - 74 lb/ft The following bending test is required to determine the structural properties listed in Tables 4A, 4B , 6A and 6B . The values stated in these tables are the required minimums . Determine the modulus of elasticity and yield stress for CP and SCL using the following test . The test specimens shall be full size and of manufacturers standard commercial type . Test the specimens using a three point bend test with the applied load at the center of a simply supported span . The distance between supports shall be 16 times the depth of the specimen with an overhang distance beyond each support equal to 10 % of the span length . The loading nose and supports shall have cylindrical surfaces for the SCL tests . In order to minimize excessive indentation at the nose and support locations the radius of the nose and supports shall be at least 0 . 5 " . The loading nose and supports for the CP tests shall be a saddle of same diameter as the pile and subtending an angle of 15 degrees and bearing length of 2 " . The loading shall be applied such that the deflection rate at the load location equals 2 inches/minute +- 10 % . Yield stress shall be evaluated at maximum P or at P for 1 % strain whichever is less . In the event a specimen will neither break nor show true yield point at outer fiber strains up to 3 % , the yield stress shall be evaluated using the load P at 1 % strain . Yield stress Fy = (P * L)/(4 * S ) Where : P = Load as stated above L = Span length S = Section modulus of gross section Stiffness EI = (P ' * L^3 )/(48 * delta) Where : P ' = Load that is '/z P yield L = Span length delta = Deflection at the location of load corresponding to P ' Modulus of Elasticity E = EFIg Where : EI = calculated from load deflection curve above Ig = gross moment of inertia - 240 - FPID ( S ) : 423186 - 1 - 58 -01 t 7 `4 ( E Y ,