AECMA PREN 3337-1988 Aerospace Series Aluminium Alloy (7010) Solution Treated and Artificially Aged (T74511) Extruded Bars and Sections (a or D) Less Than or Equal to 130 mm with P.pdf

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1、AECMA PREN3337 88 1iOl123LL 0005q73 2 = A.E.C.M.A. STANDARD NORME A.E.C.M.A. A.E.C.M.A. NORM prEN 3337 Issue P 1 October 1988 DIT PAR LASSOCIATION EUROPENNE DES CONSTRUCTEURS DE MATRIEL AROSPATIAL 88, boulevard Malesherbes, 75008 PARIS -TL. 45-63-82-85 UDC : Key words : ENGLISH VERSION Aerospace ser

2、ies Aluminium alloy (701 O) Solution treated and artificially aged (T7451 I) Extruded bars and sections (a or D) d 130 mm with peripheral coarse grain control Srie arospatiale Luft- und Raumfahrt Mis en solution Isungsgeglht Alliage daluminium (701 O) et revenu (T74511) Barres et profils fils (a ou

3、D) Aerospace series Designatiur! Gf inetal1 ic semi-fitished products - Rules 1) Aercspace ser-ies - K&thodc dessai - Mtertniriaticx ce la succepti bi f 5 3 1 a corros: OH feui Il etante des pwdui tc corrcys en alliiiyes da1iiininii:m des series fXXX et 7XXX. -C_-. i In prepam-cion Previous page is

4、blank 1 - 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 PREN3337 88 10123L1 0005q75 b prEN 3337 Page 4 Element !E 0,12 0,15 qqq-? 2,O 0,lO 2,6

5、0,05 Ti Zr each total Al Ot li er s - 0,lO - 0,06 0,16 0,05 0,15 Rem. Chemlcal Composition max. 1 2 Method of meltlng Form Method of production Llmlt dlmenslons Bar and section Extruded (a or D) 130 nnn EN 2070-3 6.1 Technlcal speclficetiori 6.2 Dlmenslonal standard EN 2047 I EN 2048 I EN 2049 I EN

6、2050 I EN 2134 I EN 2341 I 6.3 Dlmenslonal standard code 15 16 17 31 37 I l4 I 6.1 Conditlon and T74511 Solution treated 475 + 5C / WQ 6 435 Proof w Stress J - Strength Elongatlon Reductlon of area w I- Rm A - - 505 LlPa *I % - 7 Hard ness Shear Strength E end Ins Impact 140 (for information only) -

7、 Tompereture Time Stress a Elongatlon Rupture Stress Elongation at rupture IS see Ilne 98 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-,-,-2 1 EN 2004-1

8、 I Clectrical 8 MS/m :onductivi ty Wipheral coarse irain i) itress corrosion -esi stance ixfol iation :orrocion *esistanCe Designation Notes Typical use EN 2070-3 level A (table 5) The niaterial shall be capable of withstanding a stress of 240 MPa in the short transverse direction for 20 days to EN

9、2004-4. EN 2720 Exfoliation corrosion of the extrusion inust be less than shown in EN 2720 (ASTM G 34-86, figure 2, picture B) The rules governing the designation of semi-finished products are indicated in standard EN 2600. When the codified designation is used, the identification code shall be as f

10、ollows : iEN 33371, U irXX ni- I Katerial standard number Letter code (see 6.2) Appropriate dimensional standard code (see 5.3) Dta concerning dimension (see EN 2600) 1) This is a capability requirement 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-,-,-