1、A.E.C.M.A. STANDARD NORME A.E.C.M.A. A.E.C.M.A. NORM . Approved by COMITE DE NORMALISATION of A.E.C.M.A. 1984-11-23 ! prEN2636 Edition 1 May 1985 The equivalent versions in Fiench and German languages can be supplied by E.N.A.E., 8, rue Moreau-Vauthier 92100 BOULOGNE-BILLANCOURT - FRANCE. ENGLISH VE
2、RSION Aerospace series Aluminium alloy 6082-T6 bar and section 1,2 . 20 * 7 150 s 200 - - 2, -li2 . : - s 20 S-f50 - - Qmensions concerned D- % Thickness of cladding on each face I L L L Direction of sample I Temperature 1 0 Room temperature 3 255 3 270 t 240 W Stress RP92 MPa *) z Strength R, MPa *
3、) W i- Proof - -I - - Elongation A % i 295 I 3 310 I 3 280 5 9 P8 $5 I Reduction 1 of area % - i00 (for information) Hardness Ha Shear Strength MPa *) Bending Impact 1KI.J Tlme th Stress U, MPa *) - - W U U Elongation a % % 1 MPa=l N/mm2 l), see line 98 Notes p- 1 AECMA PREN2636 85 PI 1012311 0003757 b = rEN2636 Page 4 1 eripheral coarse grain 2 I 3 4 .
