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 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
5、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 !52 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 melti
6、ng Die forgings a 6 150 mn - EN7082-1; EN2082-2; EN2082-3 I - -arm Aethod of production .mit dimensions 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
7、treatment 3 el ivery iondirion and Heat treatment U se T736 Delivery condition Test piece Heat treatment 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 n
8、gati on 3 71 4th -I- - Hardness Shear Srrengrh Bending -I- Impact KI - a w w U u - - Temperature Time Stress 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 1_ - _I- - - - - STD-AECMA PREN
9、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 direction 7 Rp0,2 4, + 70 MPa Additional ageing at 175OC may be given to meet requirements Rpo, 2
10、 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 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
