1、A.E.C.M.A. STANDARD pr EN 23 2 O NORME A.E.C.M.A. Edition 2 A.E.C.M.A. NORM May 1985 Approved by COMITE DE NORMALISATION of A.E.C.M.A. 1984-1 1-23 ENGL - The equivalent versions in French and German languages can be supplied by B.NA.E., 8, rue Moreau-Vauthier 92100 BOULOGNE-BILLANCOURT - FRANC. - -p
2、 _ Supersedes edition 1 October 1980 SH VERSION Aerospace series Aluminium alloy 2024-T4 drawn bar a 75 mm Srie arospatiale Alliage daluminium 2024-T4 barres tires a 75 mm Luft- und Raumfahrt Aluminium-legierung 2024-T4 gezogene Stangen a 75 mm This industrial standard for the aerospace sector has b
3、een drawn up under the responsibility of AECMA (Association Europenne des Constructeurs de Matriel Arospatial). It is published on yellow paper in three equivalent versions (English, French, German). It will be submitted to CEN (European Committee for Standardization) as a draft European Standard. A
4、ECMA PREN2320 5 W LOL23L_l 0002 T W r_ _- Previous page is blank prEN2320 Page 3 Aluminium alloy 2024-T4 drawn bar a 75 rnm Chemlcal Element Composition 1 2 hethod of melting Bar Drann a 4 15 rnm arm het hod of product ion .mit dimenslons ;,I TechniCa1 specifications EN2070-1 and EN2070-3 EN2044 to
5、EW2046 i,2 Dimensional standards 2ondItion ind T4 Solution treated.495 2 5OC / Nater quench 0 5 40% + Naturally aged t 5 5 d ieat treatment 3elivery Londition and Heat treatment !Je? T4 Delivery condition Test piece Heat treatment Sampling . T4 Dimensions concerned Thickness of cladding on each face
6、 Dlrection of sample . 75 L g: biPa - ROOM temperature F 290 Temperature Proof W Stress =! Rrn kiPa 3 430 Strength Elongation A z H8 - 3 15 1) - 120 (for information) 1 Reduction I o area Hardness Shear Strength RC MPa - - J Bending impact k K - e - t oc - h Temperature Tlme MPa % - . MPa * - % Rupture Stress Elongatlon at rupture r e -=-.- *) 1 MPa= 1 N/mm2 - -_ 1) , see line 98 -_ Notes AECMA PREN2320 85 = LOL23LL O002900 2 = prEN2320 Page 4 1 Notes Typical use i) A50 mm & 14% for thicknesses a 2) in preparation. 10 mm. Y
