1、AECMA PREN2633 5 m L0123LL 00037qb L m r- Ln CO A op i I- l E? 8 m w U a m O O In I- I i? d - 3 C c a a I o - d c a U 6 U - E U u d =i U C U o: - U t a c U : f 2 ! u !? - U - L C i c C 8 O O u t C O A.E.C.M.A. STANDARD prEN2633 NORME A.E.C.M.A. Edition 1 A.E .C .M.A. NORM May 1985 ENGLISH VERSION Ae
2、rospace series Aluminium alloy 2024-T3511 bar and section 1,2 (a or D) 150 mm with peripheral coarse grain control Srie arospatiale Luft- und Raumfahrt Alliage daluminium 2024-T3511 Aluminium-legierung 2024-T3511 barres et profils I Stangen und Profile 1.2 G (a ou D) 150 mm limitation la zone priphr
3、ique gros grains 1,2 (a oder D) 150 mm mit Kontrolle der Grobkornrandzone This industrial standard for the aerospace sector has been drawn up under the responsibility of AECMA (Association Europenne des Constructeurs de Matriel Arospatial). It is published on yellow paper in three equivalent version
4、s (English, French, German). It will be submitted to CEN (European Committee for Standardization) as a draft European Standard. , I 7 The equivalent versions in French and German languages COMIT DE NORMALISATION can be supplied by B.NA.E., 8, rue Moreau-Vauthier r Approved by I _ - = of A.E.C.M.A. 1
5、984-11-23 92100 BOULOGNE-BILLANCOURT -FRANCE, 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-,-,-AECMA PREN2633 85 W 3032333 0003747 3 prEN2633 Page 3 Pre
6、vious page Aluminium alloy 2024-T3511 bar and section 1,2 (a or D) 150 mm with peripheral coarse grain control is blank e e Element Chemical Others Each Total Si Fe Cu bln t4g Cr Ni Zn Ti Ti+Zr - - - - - - 398 0930 132 - - - 0,50 0,50 4,9 O,!? 198 0,lO - 0,25 0,15 0,20 0905 0,15 I I I Composition I
7、min. I max. % 1 I 5 I 6 1 7 2 3 4 Method o melting . Bar and section Extruded 1,2 d (a or D) 150 mm . EN20704 and EN2070-3 EN2047 to EN2050, .EN2134 and EN2341 T3511 Form Method of production Limit dimensions 5.1 .T.eehnical-ipecifications 52 Dimensional standards Condition and Solution treated 495
8、5 5OC / Water quench 0 1 40C + 1,5 s controlled stretched $ 3% / minor straightening is allowed + naturally aged t r, 5 d T3511 t Heat treatment Delivery Condition, and Heat treatment UW Test piece Heat treatment Sampling . Delivery condition T351l mm Dimenslons concerned % Thickness of cladding on
9、each face - i L L L L L Room temperature I 330 b 340 k 340 3 350 2, -345 2 325 2 440 5 460 a 460 3 480 3 470 3 450 3 10 3 10 5 10 98 a 12 -9 z 11 4 Direction of sample 1 I Tempereture I 0 oc WPa ulPa 1 % - - Proof Stress - Strength R, - Elongation A z Reduction of area r % - 120 (for information) Ha
10、rdness 1 Shear Strength - MPa Bending fk I impact IK - L W w U o - - Tempereture 0 Time t - h WPe - Elongation LI - Rupture stress FI HPa Elongation at ruphire 1 -* - % - - *) 1 MPa = 1 N/mmz 27 Notes I l), see line 98 Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provide
11、d by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-AECMA PREN2b33 85 I 10L23LL 0003748 5 I . 1 I I Zlectrical :onductivity I y I MC/m 2 3 4 5 6 7 EN2004-1 17s y3 - Level. A (Table 5) _- Notes 1 *50 mm 2.) In preparation. I. Typical use 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-,-,-
