1、STD-AECMA PREN 2b82-ENGL 1798 W LO12311i 001q3t5 571 9 AECMA STANDARD NORME AECMA AECMA NORM prEN 2682 Edition 2 April 1998 PUBLISHED BY THE EUROPEAN ASSOCIATION OF AEROSPACE INDUSTRIES (AECMA) Gulledelle 94 - B-1200 BRUXELLES - Tel. ( + 32) 2 775 81 1 O - Fax. (+ 32) 2 775 81 1 1 ICs : Supersedes e
2、dition 1 Descriptors : November 1984 ENGLISH VERSION Aerospace series Aluminium alloy 701 0-T73652 Forgings 50IaI150mm Srie arospatiale Alliage daluminium 701 0-T73652 Pices forges ou matrices 50 I a I 150 mrn Luft- und Raumfahrt Aluminium-legierung 701 O-T73652 Freiform- oder Gesenkschmiedestcke 50
3、 I a 150 mm This “Aerospace series“ Standard has been drawn up under the European Association of Aerospace Industries). It will be submitted as a draft European Standard for formai vote. of AECMA (The Replace page 1 of the previous edition by this page Declassification approved 1998-04-30 The equiva
4、lent 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 aecrna 1998 Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot f
5、or ResaleNo reproduction or networking permitted without license from IHS-,-,- - - 5TD.AECMA PREN 2b82-ENGL 1778 4 lU12311. 00li3Lb 428 nrf7S?)3? P,iop L: Aluminium alloy 701 0-T73652 Forgings 50 a 150 rnm Fe - O,15 Others 1 Ni Zn Ti Zr Cu Mn Mg Cr tach Total 1,5 - 2,l - - 5,7 - 0,lO - - - . -en. 2,
6、0 0,lO 2,G 0,05 0,05 6,) 0,06 O,16 0,05 0,15 50 c a 6 75 75 c a s 100 100 a s 125 125 a 153 L LT ST L LT CT L ST L LT LT ST Si Element Chcm cal Composition min. 1 ma. -_ % 0,12 1 2 1 3 I 4 I 5 lethod of melting Forgings - 6 a 6 150 mm 50 EN2082-1; EN2082-2; EN7082-3 1 _ - orm lethod of production .m
7、it dimensions #,i Technicz! Specifications .2 Dimenrional standards :ond it ion nd T73652 Solution treat 475 5 5% Water quench O = 70 -+ 10C Controlled compression : 1 to 5% Artificial aoe 2 110 to !20C / 8 to 24 h + 172 I 5OC / 10 to 14 h T73652 ieat treatment )el ivery :ondit ion i nd i eat treatm
8、ent J se Delivery condition rest piece ieat treatment ;am piing 3 imensions :oncerned i almm rhickness of :ladding on each face 3irection of sample Temperatu re Proof Stress 435 435 I 420 L20 I 420 I 405 I 410 I 410 I 390 I 400 I I 375 35 490 480 475 485 470 460 475 Strength 495 9 - 490 i 480 4 75 E
9、 I onga ti on 91 61 41 9 I51 41 8151 4 Reduction of area Hard ness Shear Strength Bending -_ Impact Tlme Stress Rupture Stress i KI -I- h ) 1 MPo= 1 N/mm2 i), 2), 31, see line sa 1 Previous page is blank Notes Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS
10、under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-1 d MS/m ilectrical :onduct iv i t y tress. MPa :orrosion 20 d ypical usa 2 3 4 5 1 I- EN2004-1 I 3 23,2 Acceptable 23*2 Non acceptable Additional ageing at 17PC may be given to meet requiremen
11、t. EN20064 ) ST direction : 240 i) in preparation. 2) Aternatively artificiallyage byleafing at a rate ,200C/h up to 172 2 5OC and maintain-at this temperture for 10 to 14 h. 3) Minimum value3. 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-,-,-
