1、AECMA STANDARD NORME AECMA AECMA NORM Edition approved for publication 14 March 2003 prEN 2731 Edition P 2 March 2003 Comments should be sent within six months after the date of publication to AECMA-STAN ICs: Descriptors: ENGLISH VERSION Supersedes issue P 1 April 1986 Aerospace series Magnesium all
2、oy MG446001 T6 Sand casting Srie arospatiale Alliage dmagnsium MG446001 T6 Produit coul en sable Luft- und Raumfahrt Magnesiumlegierung MG446001 T6 Sandgustck This “Aerospace Series“ Prestandard has been drawn up under the responsibility of AECMA-STAN (The European Association of Aerospace Industrie
3、s - Standardization). It is published on green paper for the needs of the European Aerospace Industry. It has been technically approved by the experts of the concerned Domain following member comments. Subsequent to the publication of this Prestandard, the technical content shall not be changed to a
4、n extent that interchangeability is affected, physically or functionally, without re-identification of the standard. After examination and review by users and formal agreement of AECMA-STAN it will be submitted as a draft European Standard to CEN (European Committee for Standardization) for formal v
5、ote. Metallic Material Domain I I Copyright 2003 O by AECMA-STA1 Page 2 prEN 2731 : 2003 Foreword This standard was reviewed by the Domain Technical Coordinator of AECMA-STANS Metallic Material Domain. After inquiries and votes carried out in accordance with the rules of AECMA-STAN defined in AECMA-
6、 STANS General Process Manual, this standard has received approval for Publication. Page 3 prEN 2731: 2003 O Introduction This standard is part of the series of EN metallic material standards for aerospace applications. The general organization of this series is described in EN 4258. This standard h
7、as been prepared in accordance with EN 4500-2. 1 Scope This standard specifies the requirements relating to: Magnesium alloy MG-C46001 T6 Sand casting for aerospace application. 2 Normative references This European Standard incorporates by dated or undated reference provisions from other publication
8、s. These normative references are cited at the appropriate places in the text and the publications are listed hereafter. For dated references, subsequent amendments to or revisions of any of these publications apply to this European Standard only when incorporated in it by amendment or revision. For
9、 undated references the latest edition of the publication referred to applies. EN 2076-3, Aerospace series - Aluminium and magnesium alloy ingots and castings - Technical specification - Part 3: Pre-production and production castings EN 4258, Aerospace series - Metallic materials - General organizat
10、ion of standardization - Links between types of EN standards and their use EN 4500-2, Aerospace series - Metallic materials - Rules for drafting and presentation of material standards - Part 2: Specific rules for aluminium, aluminium alloys and magnesium alloys 1) 1) Published as AECMA Prestandard a
11、t the date of publication of this standard Page 4 prEN 2731: 2003 Ag 2,o 3,O Others Each Total Cu Fe Mn Ni RE Si Zn Zr Mg - - - 1,8 - - 0,40 - - - Base 0,03 0,lO 0,15 0,005 3,O 0,Ol 020 1,O 085 020 Form Method of production Limit dimension(s) mm Technical specification Sand casting Sand casting - EN
12、 2076-3 Test piece(s) Heat treatment Dimensions concerned mm See EN 2076-3. See EN 2076-3. See EN 2076-3. Use condition. Use condition. Use condition. See EN 2076-3. as20 as20 Thickness of cladding on each face % - - - Reductionofarea Z % - Hardness Shear strength R, MPa Bending k- - - - Magnesium a
13、lloy MG - C46001 a I Material designation Chemical composition % I Element I min. I max. - Method of melting I I T6 I 3.1 Delivery condition I Heat treatment 510 “c 545 “c14 h t 8 h IWQ 60 “c 80 “c + 195 “c s e s 205 “c 18 h s t s 16 h /Air cool I U I 3.2 I Delivery condition code I T6 I 7 I Use con
14、dition I Delivery condition I I Heat treatment Characteristics - 3.1 3.2 3.3 9 10 11 12 13 14 15 16 17 18 19 - - - - - - - - - - - - - - - I - I - I Direction of test piece Ambient I Ambient I Temperature I I “C I Ambient 2 175 I 2 140 I Proof stress I Rp0,2 I MPa I 2 185 2 240 I 2 200 I Strength I
15、R, I MPal 2 240 Elongation I A I % I 22 I 21 I 22 - I Impact strength - I Temperature I I “C I I Time Ihl - Elongation a% - Rupture stress OR MPa - Elongation at A % - rupture abc Notes (see line 98) Page 5 prEN 2731 : 2003 Hardness ixternal defects 70 (Typical value) A 20 per batch HB nternal defec
16、ts 3atch uniformity Marking inspection Iimensional inspection Votes rypical use See EN 2076-3. See EN 2076-3. See EN 2076-3. See EN 2076-3. See EN 2076-3. a Similar to alloys MSR-B and QE22A Unless otherwise advised by the purchaser, the manufacturer may, at his discretion, and especially to minimiz
17、e distortion in thin sections, alternatively air cool to ambient temperature from the solution heat treatment temperature or use water with quench additives (polymer quench) at 6% 30 OC. The tensile properties stated may not be consistently achievable in all parts of all castings. Any differing requirements stated on the drawing shall take precedence over those of this material standard. 100 See EN 2076-3. Qualification programme to be agreed between manufacturer and purchaser. Page 6 prEN 2731: 2003 - Product qualification
