1、A.E.C.M.A. STANDARD prEN2392 NORME A.E.C.M.A. Edition 1 A. E.C.M.A. NORM September i981 ENGLISH VERSION ALUMINIUM ALLOY 6061-T6 TUBES FOR STRUCTURES 0,6 mm a 123 rnm AEROSPACE SERIES ALLIAGE DALUMINIUM 6061-T6 LUFT-UND RAUMFAHRT TUBES POUR STRUCTURES 0,6 mm a 12,5 mm ALUMINIUM-LEGIERUNG 6061-T6 SER
2、I E AE ROSPATIALE KONSTRUKTIONSROHRE 0,6 mm a 123 mm This industrial standard for the aerospace sector has been drawn up under the responsibility of AECMA (Association Europenne des Constructeurs de Ma triel Arospa tiall. It is published on yell0 wpaper in three equivalent venions (English, French,
3、German). lt wili be submitted to CEN (European Committee for Standardization) as a draft European Standard. . f Approved by The equivalent versions in French and German languages COMITE DE NORMALISATION can be supplied by B.N.A.E., 8, rue Moreau-Vauthier of A.E.C.M.A. 1980-11-21 921M) BOULOGNE-BILLA
4、NCOURT - FRANCE. 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-,-,-t. Chemical Composition Element min. si 0,40 Al Others Fe Cu i.ln Mg Cr Zn Ti - O,l5 -
5、 0,8 O,O4 - - - - pemai toa AECflA PREN2392 BL LIIL2311 0003079 5 W A. E C.M .A. STANDARD - prEN2392 Page 3 ALUMINIUM ALLOY 6061-T6 Tubes for structures 0,6 mm4 a 4 12,5 mm % I max. 1 2 3 4 Aethod of melting :arm hod of production -itnit dimensions Drawn tubes Wall thickness : 0,6 mm s a s 12,5 mm E
6、N207-1 4, and EN2070-41 EN2257 T6 - 5.2 Dimensicinal standards :ondition ind Solution treated 525 * + artificially aged i60 * or i Sr& 5“C/ 8 h t 12 h or g5 i 5“C/ 3 h t 6 h T6 ieat treatment 3el ver y :ondition ind ieat treatment Jse rest piece ieat treatment Sampling Delivery condition 3imensins :
7、oncerned . I a I mm 0,6 4 a d 1,2 I rhicknecs of :laddina on each face L L 3irection of sample Room temperature HPa*l B 240 t 240 I + 240 Proof Stress Strength Elongation =! i- Lu MFal 2, 290 3 290 I 2, 290 A % Reduction I of area Z % Hardness HB 120 (for information) RC - k MPa - Shear Strength Ben
8、ding K - e - t J Oc h - - Impact Temperature Time Rupture Stress MPa* % - - A - % - Elongation at rupture _ *) 1MPa = 1N/mm2 i) In preparation. 2), 3), see line 98. _- Notes Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for Resa
9、leNo reproduction or networking permitted without license from IHS-,-,-prEN2392 Page 4 AECMA PREN2372 81 W 10123LL 0003LOO 8 M 1 Flattening test uotm rypicat um I I 2 3 .4 EN2002-10 ) Z d 3 a (if required byorder) 1) In preparation. 2) Fullcection. 3) Cut-out section, e 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-,-,-
