1、L C O ;-7 I I: AECMA PREN2687 85 O LO22333 0003753 2 - A.E.C.M.A. STANDARD prEN2689 NORME A.E.C.M.A. Edition I A.E.C.M.A. NORM May 1985 ENGLISH VERSION Aerospace series Aluminium alloy 7050-T73651 plate 6 a d 150 mm Srie arospatiale Luft- und Raumfahrt Alliage daluminium 7050-T7365 1 6 a 150 mm Alum
2、inium-legirung 7050-T73651 6 a 150 rnm tles paisses Platten This industrial standard for the aerospace sector has been drawn up under the responsibility of AEGMA (Association Europenne des Constructeurs de Matriel Arospatial). It is published on yellow paper in three equivalent versions (English, Fr
3、ench, German). It will be submitted to CE“ (European Committee for Standardization) as a draft European Standard. . Approved by The equivalent versions in Fiench and German languages COMITEDE NORMALISATION can be supplied by B.N.A.E., 8, rue Moreau-Vauthier , of A.E.C.M.A. 1984-1 1-23 . 92100 BOULOG
4、NE-BILLANCOURT - 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-,-,- - prEN2689 Page 3 Previous page - - is blank Aluminium alloy 7050-T73651 plat
5、e 6a150mm 0,lO 2,6 0,04 Element Chemical Composition I min. I max. % 0,12 I0,15 1 2 I 3 I 4 1 1 5 6 L. 1 vlethod of melting Rolled plate 6 . a4 150 mm EM2070-1 and EN2070-2 EN2131 and EN2433 T73651 - Solution treat 475 _t 5OC / Water quench + Control stretched : 1,5 to 3% + Artificial .ageing220 f 5
6、OC / 3 to 14 h + 180_+ 5OC 7 6 to 7 h 0 s 4OoC or 165 2 5% / 20 to 30 h 1) T73651 -orm Wethod of production Llrnit dimensions 5,1 Technical sDecifications 5,2 Dimensional standards Condition and Heat treatment Delivery Condition and Heat treatment U se Test piece Heat treatment Sampling . Dimensions
7、 concerned Thickness of cladding on each face Direction of sample 6cas50 50 a 4 75 75 a 5 100 100 c a s 125 125 L a $150 - L 1 LT I ST( L ILT I STI L I LT IST I L ILT IST I L 1 LT I ST g: Room temperature Proof Stress MPa *) VIPs - %- Strength % % - - E I on gat1 on Reduction of area 2, 145 Hardness
8、 Shear Strength MPa *I - - J Bending Impact - o. W W U u - oc h - Temperature Time MPa *) % - Stress Elongation Rupture Stress MPa *) % - Elongation at rupture ) 1 MPa = 1 N/mm2 I), 2), y: see line 98 Notes Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS und
9、er license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-1 . AECMA PREN2689 85 m L0123LL 0003753 b m . prEN2689 Page 4 1 Electrical conductivity Stress . corroiion Fracture toughness .I . :xfoliation corrosion .- ypical USB 2 3 4 I 5 I 6 EN2004-1 3) , 3
10、 23,2 EN20044 3, ST direction : 50%. Rp0,2 LT : 20 d.,. I I . . . .- : . EN2002-22 3, 50 4 a $150 L ,- T T-L s-L I 24,2 24,2 26,4 c . 1) Artificial ageing may also be carried out by heating at a rate Q 200C/h, to a temperature of 180 2 b0C and soaking at this temperature 6 to 7 h, or 165 5 5OC and soaking at this temperature 20 to 30 h. 2) Minimum values. - 3) n,preparation,: -. I c 1 i 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-,-,-
