1、A. E.C. M .A. STAN DARD NOR ME A. E.C. M .A. A.E.C.M.A. NORM Edition approved for publication Comments should be sent within six months after the date of publication decision 88, Bd. Malesherbes 17th October 1988 A.E.C.M.A. 75008 PARIS - FRANCE prEN 3345 Issue P 1 October 1988 C5 Chairman J. ODORICO
2、 DIT PAR LASSOCIATION EUROPENNE DES CONSTRUCTEURS DE MATRIEL AROSPATIAL 88, boulevard Malesherbes, 75008 PARIS -TL. 45-63-82-85 UDC : Key words : ENGLISH VERSION Aerospace series Aluminium alloy (71 50) Solution treated, water quenched controlled stretched and artificially aged (T651 I) Extruded bar
3、 and section (a or ) 540 - 565 _- 570 - 580 - 600 - 600 - 605 - 615 I Temperature I 0 oc Proof 1 stress - U - 7 I I Elongetlon I A I % 160 (for information) IHB I - H erdness Bendlng k- Impact K - Temperature I 6 I X Time I t h MPa *I Stress Elongation % % et rupture see Ilne98 1 lectrical MS/m ondu
4、ctiri ty L-T T-L eripheral oarse grain ractu re MPa Ym oughness 2) KIC 23 23 20 18 Designation Notes Typical use EN 2004-1 18.5 Level A of table 5 in EN 2070-3 2) EN 2002-22 I19a(50mn I 50a90m The rules governing the designation of semi-finished products are indicated in standard EN 2600. When the c
5、odified designation is used, the identification code shall be as follows : ,EN 3345llU riXX II- 1 Material standard nuinber Data concerning dimension (see EN 2600) I II I Letter code (see 6.2) I I Appropriate dimensional standard code (see 5.3) 1) Artificially aging may be carried out using the following alternative method : fieating to a temperature of 155 2 5OC at a rate riot exceeding 2OFC/h, soaking at this temperature for 10 5 t 5 12 h. 2) This test is covered by the capability clause of EN 2070-1.
