1、A.E,C.M.A. STANDARD NORME A.EG.M.A. A.E.C.M.A. NORM - - - Approved by The equivalent versions in French and German languages I prEN2319 Edition 2 May 1985 COMITE DE NORMALISATION of A.E.C.M.A. 1984-1 1-23 I- - Supersedes edition 1 October 1980 can be supplied by B.N.A.E., 8, rue Moreau-Vauthier 9210
2、0 BOULOGNE-BILLANCOURT - FRANCE. - ENGLISH VERSION Aerospace series Aluminium alloy 2024-T351 O drawn bar a 75 mm Srie arospatiale Alliage daluminium 2024-T351 O barres tires a 75 mm Luft- und Raumfahrt Aluminium-legierung 2024-T351 O gezogene Stangen a 75 mm This industrial standard for the aerospa
3、ce sector has been 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 GEN (European Committee for Standardization) as a draft Europ
4、ean Standard. 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-,-,-AECMA PREN2317 85 10L2311 0002896 4 .I prEN231Q Page Previous page . is blank Aluminium a
5、lloy 2024-T3510 drawn bar a 75 mm Element Chernlcal Others Ci I Fe 1 Co 1 Mn I Mg 1 Cr I Ni 1 Zn 1 Ti Ti+& - 7 3,8 0,30 1,2 - AI each total -1 - - - - - Rem. . i,50 0.50 4,s 0.9 I 1.8 0.10 - I 0,25 a,i5 0,2u op 0.15 Composition min. 1 ma. % 1 2 I hethod of melting Bar Drawn a 6 75 mm EN2070-I and EN
6、2070-3 - orm ulethbd of production -mit dimensions 5,i Technical specifications 5.2 Dimenslonal standards -i EN2044 to EN2046 I T3510 ondition nd Solution treated 895 -+ 5OC / Water auench 8 Q 4OoC + 1,5_ s controlled stretched & 3% /-Straightening is not authorised after controlled stretching + Nat
7、urally aged t 35 d 13510 Delivery condition T3510 ieat treatment lelivery ondit ion nd leat treatment I se est piece ieat treatment Lampling . s 75 )imensions hickness of ladding on each face - i L lireetion of sample I- Temperatu re I Room temperature -I- Proof w Stress J $ Strength I- - W Elongati
8、on R,qz MPa R, MPa A% z s Ha - - - - - 5 315 o 440 3 13 - iardness I i20 (for information) - -I- Shear Strength 51“ k 3ending -I- Impact -I- temperatu re - KJ 81, -I- I Tlme -I- Stress -I- - Rupture Stress Elongation 1. at nipture -I- - -I- L-?L *) 1 MPa = 1 N/mm* Notes ), see line 98 . I u=, -, .-
9、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-,-,-AECMA PREN2319 85 1012311 0002897 b m prEN2319 Page 4 1 I 1 Electrical conductivity I I Notes iypicsi use . 17 i y& 20 : acceptable i) A50 mm 7 12% for thicknesses a e 10 mm. 2) In preparation. 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-,-,-
