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 Copyright Association Europeene des Cons
4、tructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-p- 1 AECMA PREN2636 85 PI 1012311 0003757 b = rEN2636 Page 4 1 eripheral coarse grain 2 I 3 4 . Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-
