A drill-elastic and flexurally rigid rod element (10) for supporting and guiding a movable flap (24) relatively to a wing (26) of an aircraft, wherein the rod element encompasses a cross-shaped profile cross section and first and second fastening sections (20, 22) and is made of a fiber composite material and the rod element can be fastened to the wing in a fixed manner via the first fastening sections (20) and to the flap (24) via the second fastening sections (22). The rod element and the fastening sections are laminated from a plurality of unidirectional, preimpregnated fibrous layers--prepreg layers--which are bonded to one another in the area of the fastening sections as well as in the cross-shaped cross section core area (28) and which are separated from one another in each case by a separating film inserted between the prepreg layers outside of the areas.
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