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9/8/98 AC 43.13-1B TABLE 4-9. Number of rivets required for splices (single-lap joint) in bare 2014-T6, 2024-T3, 2024-T36, and 7075-T6 sheet, clad 2014-T6, 2024-T3, 2024-T36, and 7075-T6 sheet, 2024-T4, and 7075-T6 plate, bar, rod, tube, and extrusions, 2014-T6 extrusions. Thickness “t” in inches No. of 2117-T4 (AD) protruding head rivets required per inch of width “W” No. of Bolts Rivet size 3/32 1/8 5/32 3/16 1/4 AN-3 .016 .020 .025 .032 .036 .040 .051 .064 .081 .091 .102 .128 6.5 4.9 6.9 4.9 8.6 4.9 11.1 6.2 12.5 7.0 13.8 7.7 - 9.8 - 12.3 - - 10.2 - - 11.4 - - 12.8 - - - 11.2 - - - - - - - - - - - - 2.4 - 2.4 3.3 2.5 3.3 3.1 3.3 3.9 3.3 4.4 3.3 4.9 3.4 6.2 3.2 3.9 3.9 3.9 4.5 5.0 6.4 8.1 3.3 3.3 3.5 4.5 5.6 7.1 7.9 8.9 NOTES: c. For single lap sheet joints, 75 percent of the number shown may be used. ENGINEERING NOTES: a. The load per inch of width of material was calculated by assuming a strip 1 inch wide in tension. b. Number of rivets required was calculated for 2117-T4 (AD) rivets, based on a rivet allowable shear stress equal to 40 percent of the sheet allowable tensile stress, and a sheet allowable bearing stress equal to 160 percent of the sheet allowable tensile stress, using nominal bolt diameters for rivets. c. Combinations of sheet thickness and rivet size above the underlined numbers are critical in (i.e., will fail by) bearing on the sheet; those below are critical in shearing of the rivets. d. The number of AN-3 bolts required below the underlined number was calculated based on a sheet allowable tensile stress of 70,000 psi and a bolt allowable single shear load of 2,126 pounds. a. For stringers in the upper surface of a wing, or in a fuselage, 80 percent of the number of rivets shown in the table may be used. b. For intermediate frames, 60 percent of the number shown may be used. Par 4-58 Page 4-37PDF Image | AFS-640
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