1、A.E.C.M.A. STANDARD NORME A.E.C.M.A. A.E.C.M.A. NORM prEN239 1 Edition 1 September 1981 ENGLISH VERSION ALUMINIUM ALLOY 6061-T4 TUBES FOR STRUCTURES 0,6 mm a 12,5 mrn AEROSPACE SERLES ALLIAGE DALUMINIUM 6061-T4 LUFT-UND RAUMFAHRT TUBES POUR STRUCTURES 0,6 mm a 12,5 mm ALUMINIUM-LEGIERUNG 6061-T4 SER
2、IE AEROSPATIALE KONSTRUKTIONSWOHRE 0,6 mm a 12,5 mm This industrial standard for the aerospace 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 equivalen t versions (English, French, G
3、erman). it wilt be submitted to CEN (European Committee for Standardization) as a draft European Standard. The equivalent venions in French and German languages COMITE DE NORMALISATION can be supplied by B.N.A.E., 8, rue Moreau-Vauthier I 92100 BOULOGNE-BILLANCOURT - FRANCE. Approved by of A.E.C.M.A
4、. 1980-11-21 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 PREN2341 .- Al W LO22311 00030b T - - prEN2391. Tage 3 . -! A.E.C.M.A. -STAN DARD AL
5、UMINIUM ALLOY 6061-T4 -, Tubes for structures 0,6 mm 8 a 6 12,5 mm Element I Chemical Al Others each Itotal si Fe Cu Mn Mg Cr Zn Ti I Composition min. . max. % 1 1 2 3 4 Method of melting Form Method of production Drawn tub es Wall thickness: 0,6 mmg a Q 12,5 mm I EPi2070-i and EN20704 ) . EN2257 T4
6、 Limit dimensions 5.1 Acceptance standards 5.2 Dimensional standards Condition and Heat treatment Delivery Solution treated 525 f lO“C/WQ 8 f- 40C + naturally aged/ t 3 5 d T4 Condition and Heat treatment Use Test piece Heat treatment Sampling Delivery condition Thickness of cladding on each face Di
7、rection of sample L I L I L ITemperature Room temperature 3 110 b 110 3 110 . a 205 3 205 B 205 Proof Stress Strength Elongation r! -I- A% TIT- Reduction lot area -I- Hardness HBI - 90 (for information) - -I- Shear Strength - Bending Impact Temperature Time e Stress o Elongation Rupture Stress Elong
8、ation at rupture I - 1MPa = 1 Nimm i.) In preparation. t), 3), see line 98. 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-,-,-, .-l 1. - .I- AECMA PREN23
9、41 BI m 10L2311 0003097 1 m prEN239i Page 4 1 Flattening test uotst rypicai uw 2 3 4 EN2002-10 f) Z 4 2 a (if required by order) 1) In preparation. 2) Fui1 section. 3) Cut-out section. c O O 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-,-,-
