1、 - - - - STD-AECMA PREN 2b88-ENGL 1998 m 1O1231L 001Li35b 589 AECMA STANDARD prEN 2688 NORME AECMA Edition 2 AECMA NORM April 1998 PUBLISHED BY THE EUROPEAN ASSOCIATION OF AEROSPACE INDUSTRIES (AECMA) Gulledelle 94 - B-1200 BRUXELLES - Tel. i+32) 2 775 81 10 - Fax. (+32) 2 775 81 11 ICs : Supersedes
2、 edition 1 August 1984 Descriptors : 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 92138 ISSY - LES - MOULINEAUX CEDEX - FRANCE Aluminium alloy 7050-T736 Die fo
3、rgings a I 150 mm Aerospace series Alliage daluminium 705O-T36 Pices matrices a I 150 mm Srie arospatiale Luft- und Raumfahrt Aluminium-legierung 7050-T736 Gesenkschmiedestcke a I 150 rnm This “Aerospace series“ Standard has been drawn up under the European Association of Aerospace industries). It w
4、ill be submitted as a draft European Standard for formal vote. of AECMA (The Replace page 1 of the previous edition by this page aecrna 1998 Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking p
5、ermitted without license from IHS-,-,-Aluminium alloy 7050-T736 Die forgings a 150 mm I Chemkal Element I Composition 1 min. Others Each Total Al Si Fe Cu Mn Mg Cr Ni Zn Ti Zr - - 2,0 - 1,9 - - 5,7 - 0,08 - - Rem. 0,12, 0915 2,6 0,10 2,6 0,04 - 6,l 0,06 0,15 0,05 0,15 1 I I 1 4 1 5 2 3 Method of mel
6、ting Die forgings a J 150 mm EN2082-1; EN2082-2; EN2082-3 - A Form Method of production Limit dimensions 5.1 Technical Specifications 5.2 Dimensional standards -_ - 1736 Condition and Solution treat 475 5OC Water quench Artificial age 120 2 E,OC / 24 + 1 h + T736 6 = 6G to 7OoC 177 2 5OC / 12 2 1 h
7、Heat treatment D el ivery Condition and Heat treatment U se Delivery condition Test piece Heat treatment Sampling Dimensions concerned Thickness of cladding on each face 1% L LT CT L LT Si L LT Sl L LT ST I Direction of sample Temperature Room temperature Proof Stress J 433 385 385 420 380 380 415 3
8、70 370 LO5 370 370 495 470 470 490 460 460 485 455 455 480 455 455 I 5 5 7 4 4 7 3 3 7 3 3 I Strength w I- UPa * E longation Reduction of area q 1- - I Hard ness % % _ - -_ b 145 Shear Strength MPa - _ J Bending Impact Temperature ac _ h MPe Stress W U U Elongation Rupture Stress Elongation MPa % -
9、1 at rupture 27 Notes 1), Z), .see line 98 I I Previous page is blank I I 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-,-,-I prEN2688 Page 4 2 1 3 4 5 l
10、. Electrical conductlvlty 23,2 Stress corrosion Rp0,2 L direction 7 Rp0,2 3, + 62 MPa Not acceptable Additional ageing at 177OC may be given to meet requirements 7 - U HSln MPa 20d rypiesl um EN2004-1 ) 3, + 62 Ra 2 23,2 I RD0,2 direction .S Rp0,2 Rp0,2 L direction 7 Rpo,2 3, + 62 MPa Not acceptable
11、 Additional ageing at 177% may be given to meet requirements 5 2372 EN20044 ) ST direction : 50% Rp0,2 3, measured in L direction - i) In preparation. 2) Minimum values. 3) Value indicated in line 13. . 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-,-,-
