1、 AECMA - PREN20A5 BO iiE! 1012311 0002072 2 m _ DRAFT prEN2085 A. E.C.M. A. STANDARD NORME A.E.C.M.A. A. E.C.M.A. NORM Edition 1 October 1980 Approved by COMIT DE NORMALISATION Of A.E.C.M.A. 1979-1 2-1 O ENGLISH VERSION The equivalent versions in French and German languages can be supplied by B.N.A.
2、E., 8, rue Moreau-Vauthier 92100 BOULOGNE-BILLANCOURT - FRANCE. ALUMINIUM ALLOY 2618A - T6 FORGINGS a ondition T6 ind ieat treatment Delivery 1 6 :ondition ind -teat treatment Jse 7 I I I Delivery condition Delivery condition .E artificially aged 203 f 5“C/ 2.0 h t C 24 h I T6 I integral or cut up t
3、est T6 - forgings rest piece ieat treatment ;ampling 8 rorged test piece I I almm 3imensions :oncerned i50 I Thickness of :laddina on each face Direction of sample Temperature -I- Proof MPa MPa Yi II _ Rm A z % Reduction Hardness H RC - Shear Strength ending ir = k x 01 k K - e t J OC h - Impact tim
4、e oa MPa* 8 % MPa z Rupture Stress Elongation *i IMP = i/mm 1) In preparation 2) By orcler n Notes a 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-,-_I _
5、 . AECMA PREN2085 80 IB 2012312 0002074 b = , 3 1 4 5 Ilectrical :pnduct iv ity Notes 2 21 (for infornacion) i Typical use 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-,-
