A blade attachment (1, 20) for a bearingless main rotor of a helicopter, comprising: an airfoil blade having a tip end and a root end forming opposite ends thereof and having a pitch axis from said tip end to said root end; the airfoil blade having a leading edge and a rear edge; a flexbeam (3, 21) including a flexbeam body (16, 17) and a flexbeam head at an end of said flexbeam body (16, 17), said flexbeam body (16, 17) being flexible; a control cuff (4, 22) enclosing and extending along at least a predominant portion of said flexbeam (3, 21); a separable junction arrangement between said flexbeam head, said control cuff (4, 22) and said root end of said airfoil blade, said junction arrangement is mechanical between said flexbeam head, said control cuff (4, 22) and said root end of said airfoil blade characterized in that the junction arrangement comprises a main bolt and at least one supporting bolt both arranged lying perpendicular to the lead-lag pivoting plane of the airfoil blade; the main bolt and the at least one supporting bolt forming removable fasteners respectively removably connecting said root end of said airfoil blade and said control cuff (4, 22) with said flexbeam head, said main bolt and at least one supporting bolt both being asymmetric with regard to said pitch axis of said airfoil blade; and wherein:. the hole for the main bolt being in the area of a 10-30 % pitch axis of the profile section of said airfoil blade. the main bolt having a greater diameter than the supporting bolt;. the main bolt being located at 10% - 30% of the chord width of the airfoil blade;. the supporting bolt being located at 50% - 90% of the chord width of the airfoil blade; and. the distance of the main bolt from the supporting bolt being between 40% - 80% of the chord width of the airfoil blade. an airfoil blade having a tip end and a root end forming opposite ends thereof and having a pitch axis from said tip end to said root end; the airfoil blade having a leading edge and a rear edge; a flexbeam (3, 21) including a flexbeam body (16, 17) and a flexbeam head at an end of said flexbeam body (16, 17), said flexbeam body (16, 17) being flexible; a control cuff (4, 22) enclosing and extending along at least a predominant portion of said flexbeam (3, 21); a separable junction arrangement between said flexbeam head, said control cuff (4, 22) and said root end of said airfoil blade, said junction arrangement is mechanical between said flexbeam head, said control cuff (4, 22) and said root end of said airfoil blade characterized in that the junction arrangement comprises a main bolt and at least one supporting bolt both arranged lying perpendicular to the lead-lag pivoting plane of the airfoil blade; the main bolt and the at least one supporting bolt forming removable fasteners respectively removably connecting said root end of said airfoil blade and said control cuff (4, 22) with said flexbeam head, said main bolt and at least one supporting bolt both being asymmetric with regard to said pitch axis of said airfoil blade; and wherein:. the hole for the main bolt being in the area of a 10-30 % pitch axis of the profile section of said airfoil blade. the main bolt having a greater diameter than the supporting bolt;. the main bolt being located at 10% - 30% of the chord width of the airfoil blade;. the supporting bolt being located at 50% - 90% of the chord width of the airfoil blade; and. the distance of the main bolt from the supporting bolt being between 40% - 80% of the chord width of the airfoil blade.. the hole for the main bolt being in the area of a 10-30 % pitch axis of the profile section of said airfoil blade. the main bolt having a greater diameter than the supporting bolt;. the main bolt being located at 10% - 30% of the chord width of the airfoil blade;. the supporting bolt being located at 50% - 90% of the chord width of the airfoil blade; and. the distance of the main bolt from the supporting bolt being between 40% - 80% of the chord width of the airfoil blade.