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. 1984-1 1-23 prEN2634 Edition 1 May 1985 - The equivalent versions in French and German languages can be supplie$ by B.N.A.E., 8, rue Moreau-Vauthier 92100 BOULOGNE-BILLANCOURT - FRANCE. ENGLISH VER
2、SION Aerospace series Aluminium alloy 201 4A-T4511 bar and section 1,2 / 235 / 235 / 260 / 270 I , 260 / 230 I I I I Strength , 345 / 370 / 400 / 410 / 400 / 370 / 12 , 14 /a $8 / 11 1 $111) % % - Elongation Reduction of area - 120 (for information) - Hardness dPa $1 Shear Strength Bending - J Impac
3、t oc - h Temperature The Stress wipe I % - Rupture Stress Elongation at rupture *I 1 MPa = 1 N/mm2 i) See line 98 T t Notes . Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted withou
4、t license from IHS-,-,-_- T AECMA PRENZb34 85 E 3012333 0003753 5 Al prm2634 Page 4 1 2 3 4 5 6 7 eipheral coarse grain I EN2070-3, level !J“ - (Tatle 5). Notes Typical use *50 mm 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-,-,-
