1、A, E.C.M.A. STANDARD NORME A.E.C.M.A. A. E.C.M.A. NORM - Approved by The equivalent venions in French and German languages COMITE DE NORMALISATION can be supplied by B.N.A.E., 8, rue Moreau-Yuthier of A.E.C.M.A. 1980-1 1-21 92100 BOULOGNE-BILLANCOURT - FRANCE. prEN2390 Edition 1 September 1981 - _I
2、ENGLISH VERSION ALUMINIUM ALLOY 6082-T6 TUBES FOR STRUCTURES 0,6 mm a 12,5 mm AEROSPACE SERIES ALL I AG E DALUMINIUM 6082-T6 TUBES POUR STRUCTURES 0,6 rnm a Q 12,5 mm LUFT-UND RAUMFAHRT ALUMINIUM-LEGIERUNG 6082-T6 SERIE AEROSPATIALE KONSTRUKTIONSROHRE 0,6 mm a 12,5 mrn This industrial standard for t
3、he 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 equivalent wersions (English, French, German). It will be submitted to CEN (European Committee for Standardization) as a d
4、raft European 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-,-,-SI Fe I CU I kln I Mg Cr Al Zn Ti ach total 097 i,3 - O,40 O,6 - - - - - Remi d
5、er 0,50 o,io i,o 1,2 0,2s 0,20 o,io 0,05 0,25 L L L =! z I- W - Proof Stress p0,2 MPa) Strength , MPa) Elongation A 46 - - - Impact temperature Time n Stress j- o Elongation KJ 6 32 th U, MPa*) - - - - a % Rupture Stress Elongation at ruDture UR MPa*) A 96 - AECMA PREN2340 81 m 1012312 O003093 4 A.E
6、.c.M.A. STANDARD 1 1- _. - I .-. , ALUMINIUM ALLOY 6082 -T6 Tubes for structures 0,6 mm s a 4 12,5 mm prEEu239 Page 3 Element Chemical Composition I min. % I max. 1 2 I 3 4 Method of melting Form Method of production Limit dimensions Drawn tubes Wall thickness: 0,6 mm d a & 12,5 mm 5.1 Acceptance st
7、andards 5.2 Dinensional standards EN207D-11 and EN20704 dl . _-. Condition and Heat treatment Delivery T6 Solution treated 525 f 10C/WQ 0 s 40C t- artificially aged 175 f 5OC/ 5 h & t G 12 h or 185 i. 5OC/ 3 h 4 t d 6 h Condition and Heat treatment Use T6 Delivery condition Test piece Heat treatment
8、 Sampling Dimensions . I a I %m concerned Thickness of cladding on each face 0,6 ,c a d 1,2 I 1,2 4 a c 6 I 6 C a & 12,5 Direction of sample !Temperature I I OC 3 255 I 3 255 I 2, 240 I Reduction 171% of area Hardness HB - Shear Strength /FIG Bending lkl- ) tMPe=lN/mm* 1) In preparation. ?), 31, see
9、 line 98. Notes 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-,-,-F- prEN2390 Page 4 AECMA PREN2390 BL H LOL23Ll 000309i.1 b , .e?- 1 Flattening test JOt
10、W yplcal U# 2 3 4 EN2002-10 Ir) Z 5 2 a (if.required by order) 1) in preparation. 2) Full section, 3) Cut-out section. a C 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-,-,-
