1、:AECMA PREN333q 88 = 10bZ3Ll 3015_461i b A.E.C. M.A. STANDARD NORME A.E.C.M.A. A.E.C.M.A. NORM prEN 3334 Issue P 1 October 1988 DITE PAR LASSOCIATION EUROPENNE DES CONSTRUCTEURS DE MATERIEL AROSPATIAL 88, boulevard Malesherbes, 75008 PARIS -TEL. 45-63-82-85 UDC : Key words : ENGLISH VERSION Aerospac
2、e series Aluminium alloy (7050) Solution treated, controlled stretched and artificially aged (T7651) Plate 6 450 - 450 - 445 - 445 - 400 - 520 - 525 - 515 - 515 - 485 Temperature Proof Stress Strength A Z HB - - - 7 - 5 - 7 - 5 - 2,5 - 145 (for information only) Eiongatlon Reduction of area i ardnes
3、s ihear Strength RC MPa *) 3 end Ing k mpact - a UI W K U Ni Temperature The Stresa Elongation a “R A _ UPS *) Rupture Stress Elongation at rupture % as see line 98 Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo repr
4、oduction or networking permitted without license from IHS-,-,-1 lectrical 8 MS/m onductivi ty tress MPa orrosion 20 days racture ,oughnecs 2) KIC MPa Ym iotch tensile/tensi le yield atio Rp/Rp0,2 Designation Notes typical use 2 EN 2004-1 Acceptable Rp0,2 23 22,5 5 8 23 LT i Rp0,2 min. + 70 MPa accep
5、table If these conditions are not satisfied an additional aging of 172 5 5C for 6 5 t 5 15 h may be necessary EN 2004-4 25a60mn ST directon : 175 MPa EN 2002-22 125 a 5 40 I 40 a 5 60 L-T I 25 I 25 T-L I 24 I 24 test pieces L I 1,lO I 1,05 dianieter 26,9 mn LT 0,96 0,96 test pieces L 1 1,40 I - diam
6、eter 12,7 nm LT 1,30 Other values for notch yield ratio may be agreed between the manufacturer and the purchaser if the relationship to the specified KIC values has been established The rules governing the designation of semi-finished products are indicated in standard EN 2600. When the codified des
7、ignation is used, the identification code shall be IS follows : Material standard number Letter code (see 6.2) Appropriate dimensional standard code (see 5.3) Data concerning dimension (see EN 2600) 1) Artificially aging may be carried out using the following alternative method : heating to a temper
8、ature of 172 2 5OC at a rate not exceeding 20C/h and soaking at this temperature for 6 5 t 5 15 h. 2) Subject to the “capability clause“ defined in EN 2070-1. 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-,-,-
