1、AECMA PREN2678 8 U LOL23LL 0003981 O M A.E.C.M.A. STANDARD NORME A.E.C.M.A. A.E.C.M.A. NORM prEN 2698 Edition 1 March 1988 EDITE PAR LASSOCIATION EUROPEENNE DES CONSTRUCTEURS DE MATERIEL AEROSPATIAL 88, boulevard Malesherbes, 75008 PARIS -TEL. 45-63-82-85 UDC: Key words : ENGLISH VERSION Aerospace s
2、eries Aluminium alloy (7075) Solution treated, water quench, controlled stretched and artificially aged (T651 O) Extruded bar and section 1,2(aorD)lO0mm Srie arospatiale Luft- und Raumfahrt Alliage daluminium (7075) Aluminiumlegierung (7075) Mis en solution, trempe leau, traction contrle et revenu (
3、T651 O) Barres et profils fils 1,2 490 - 510 - 505 kiPa *) kPa *) % - 545 - 560 - 560 - 7 - 7 - 7 1) * 49s - 560 7 - viethod of melting =arm Bar and section Vlethod of production -mit dimensions 5.1 Technical specif cation 5.2 Dimensional standard EN 2047 to EN 2050, EN 2134 and EN 2341 Extruded 1,2
4、 5 (a or D) 5 100 m EN 2070-1 and EN 2070-3 5.3 Dimensional standard coda I 5.1 Condition and T6510 Solution treated 465 5 5C /iJQ 0 5 40aC + artificially aged 135 + 5C / 12 t 16 h or 120 7 5C / 20 7 t 30 h +1,5 5 controlled stretched 5 3Z,straightening not allowed after controlled stretchin heat tr
5、eatment delivery 5.2 Delivery condition code U :ondition ind ieat treatment J sa T65 10 Delivery condition rest piece I ieat treatment ;am pi i ng I T6510 rhlckners of :adding on each face 3irection of sample I L Temperature Proof Stress W Strength A E iongation Reduction o area Hardness Shear Stren
6、gth Bending impsct - a w W U O - Ni O Temperature Time Stresa Eiongatlon a Rupture Stress Elongation at rupture es see line 98 Electrical conductivity 1 Designation Notes Typical use . AECMA PREN2678 AA m 1012311 000378Li b m prCN 2693 Page 4 2 EN 2004-1 2, 18 5 8 i 21 : acceptable i) Aso mm for a 5 10 mm 2) In preparation.
