1、STC-AECilA PREN 2b8L-ENGL 1778 LOL23LL OflLLilLB ZTO AECMA STANDARD prEN 2681 NORME AECMA Edition 2 AECMA NORM April 1998 PUBLISHED BY THE EUROPEAN ASSOCIATION OF AEROSPACE INDUSTRIES (AECMA) Gulledelle 94 - B-1200 BRUXELLES - Tel. (+32) 2 775 81 10 - Fax. (+32) 2 775 81 11 ICs : Supersedes edition
2、1 Descriptors : November 1984 Declassification approved 1998-04-30 ENGLISH VERSION The equivalent versions in French and German languages can be supplied by B.N.A.E. - Technopolis 54 - 199, rue Jean-Jacques Rousseau 921 38 ISSY - LES - MOULINEAUX CEDEX - FRANCE Aerospace series Aluminium alloy 701 0
3、-T736 Die forgings a I 150 mm Srie arospatiale Alliage daluminium 701 O-T736 Pices matrices a I 150 mm Luft- und Raumfahrt Aluminium-legierung 701 0-T736 Gesenkschmiedestcke a I 150 mm This “Aerospace series“ Standard has been drawn up under the European Association of Aerospace industries). It is p
4、ublished on yell0 w paper in three equivale It will be submitted as a draft European Stan for formai vote. of AECMA fThe tandardiza tion) Replace page 1 of the previous edition by this page aecma 1998 Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under lic
5、ense with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Si - ,12 Others 1. “ li Zr Each Total - Fe Cu Cn Mq Cr Ni - 1,5 - Z,! - - 5,7 - 0,lO - - 0,15 2,O 0,lO 2,6 0,05 0,05 6,7 0,06 0,16 0,05 0,15 -57. . . - - _ - - - - 4 75 75 a 6 100 !OO a 6 125 125 a 6 !5
6、2 L IT ST L IT ST L LT ST L LT ST 490 465 465 485 455 455 480 450 7 3 3 7 3 3 7 3 Aluminium alloy 701 0-T736 Die forgings a 150 mm Element C hem Ica1 Compo sit i on 1 min. 1 2 3 4 5 Aethod of melting Die forgings a 6 150 mn - EN7082-1; EN2082-2; EN2082-3 I - -arm Aethod of production .mit dimensions
7、 5.1 Technical Specifications 5.2 Dimensional standards :ondirion and - T736 Solution treat 475 2 SOC Water quench Q = 70 + 10C Artificial age11 110 to 12OOC 8 to 24 i. + i75 2 5OC/ 8 to 16 h ieat treatment 3 el ivery iondirion and Heat treatment U se T736 Delivery condition Test piece Heat treatmen
8、t Sampl ing Dimensions concerned Thickness of claddina on each face Direction of samole I I Temperature Room temperature 425 I 400 I 400 I 420 I 395 I 395 I 410 I 390 39C i5c _ Proof Stress E I o ngati on 3 71 4th -I- - Hardness Shear Srrengrh Bending -I- Impact KI - a w w U u - - Temperature Time S
9、tress El ongatlon Rupaire Stress E longat ion at rupture -_ -I.- -I- U, MPa * Ti, -1- 1 1 1 MPa= 1 N/mrn2 I I i), 2), 3), see line 98 Previous page is blank Notes J Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo repr
10、oduction or networking permitted without license from IHS-,-,-1_ - _I- - - - - STD-AECMA PREN ZbBL-ENGL 1778 1012311 UC14370 757 1 Electrical conductivity Stress corrosion Y 6 MS/m MPa 20d - lotos yplcal use 2 3 4 I 5 L 1 1- EN2004-1 3) a 23,2 I Rp0,2 L direction Q Rp0,2 4, + 70 MPa Acceotable L dir
11、ection 7 Rp0,2 4, + 70 MPa Additional ageing at 175OC may be given to meet requirements Rpo, 2 23,2 Not acceptable Rp0,2 L direction 7 Rp0,2 4, + 70 MPa Additional ageing at 175OC may be given to meet requirements 23,2 Not acceptable EN20044 i) ST direction : 240 i ) In preparation. 2) Alternatively
12、 artiicially ageby heating at a rate 6 200C/h up to 175 -+ 50C 3) Minimum values. - and maintain at this temperature for 8 to 16 h. . “ r; 4) Value indicated in line 13. I 1 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-,-,-
