AECMA PREN 2709-1985 Aerospace Series Aluminium Alloy 2024-T3510 Bar and Section 1 2 Less Than or Equal to (a or D) less Than or Equal to 150 mm with Peripheral Coarse Grain Contro.pdf

1、4ECMA PREN2709 I35 lOl23Ll OOOLIOLB b U - A.E.C.M.A. STANDARD prE N 2709 NORME A.E.C.M.A. Edition 1 A.E.C.M.A. NORM May 1985 Approved by COMITE DE NORMALISATION of A.E.C.M.A. 1984-1 1-23 . ENGLISH VERSION The equivalent versions in French and German languages can be supplied by B.N.A.E., 8, rue More

2、au-Vauthier 92100 BOULOGNE-BILLANCOURT - FRANCE, - Aerospace series Aluminium alloy 2024-T351 O bar and section 1,2 (a or D) 150 mm with peripheral coarse grain control Srie arospatiale Luft- und Raumfahrt Alliage daluminium 2024-T351 O Aluminium-legierung 2024-T351 O barres et profils Stangen und P

3、rofile 1,2 (a ou D) G 150 mm 1,2 G (a oder D) G 150 mm limitation la zone priphrique gros grains mit Kontrolle der Grobkornrandzone This industrial standard for the aerospace sector has been drawn up under the responsibility of AECMA It is published on yellow paper in three equivalent versions (Engl

4、ish, French, German). It will be submitted to CEN- (European Committee for Standardization) as a draft European Standard. - (Association Europenne des Constructeurs de Matriel Arospatial). I I _. Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license

5、with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,- . AECMA PREN2709 45 LOL23LL 0004019 B prEhrS709 Page 3 Aluminium allov 2024-T3510 Previous page is blank bar and section 1,2 (a or D) 150 mm with peripheral coarse grain control - Hg Element Si Cr Ni Zn Ti

6、Ti+Zr Others Al Rem. Each Total 0,lO - 0,25 0,15 0,20 0,05 0.15 Chemlcal 1,2 Composition max. 1 41 51 61 7 Aethod of melting Bar and section Extruded -1,Zs a OF O) 150 mi EN2070-1 and EN2070-3 EN2047 to EN2050, EN2134 and EN2341 .orm net hod of product ion .mit dimensions 5. i .Technical spec if ;ca

7、t ions i.2 Dimenrlonai standards 2onditlon ind T3510 Solution treated 495 2 5OC / $iater quench 8 , 4OoC -F 1,5 ,C controlled stretched 6 3% / no straightening after stretching alloued + Naturally aged t b 5 d . T3510 Ieat treatment )ellvery :ondition 3nd -I eat treatment J se rest piece Heat treatm

8、ent Sampilng . Delivery condition T3510 Dimensions oncerned (i/ mm % hickness of iadding on each face iirection of sample - W rn z w I- r! - Temperetu re e g: Room temperature Proof Stress MPa - blPa Strength Rm Eiongation A Z % Reduction of area HB Re - - k ._ - MPa 120 (for information) - i ard ne

9、ss ;hear Strength lending mpact K J - a w w U U - e oc h - Temperature Tlme t MPs % - Stress El ongat ion OR A _. MPs - % Rupture Stress Elongation at rupture *) 1 MPa = 1 N/mmz i), see line 98 .- Nores Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under l

10、icense with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-prEN2709 Page 4 1 1 Y I ivS/m lectrical onductivi ty eripheral coarse grain Noter Typical use AECMA PREN2709 A5 m 1012311 0004020 4 m 2 I 3 I 4 5 6 7 I I I ; I I . EN2004-1 ) 17 &y& 20 (for information) EN2070-3 - Level A (Table 5) A50 mm 2) In preparation. 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-,-,-