1、AECMA STANDARD NORME AECMA AECMA NORM Edition approved for publication 30 September 2004 prEN 4616 Edition P 1 September 2004 Comments should be sent within six months after the date of publication to AECMA-STAN ICs: Descriptors: ENGLISH VERSION Aerospace series Magnesium alloy MG-CI8002 T4 Chill ca
2、sting Srie arospatiale Alliage de magnsium MG-CI8002 T4 Produit coul en coquille Luft- und Raumfahrt Magnesiumlegierung MG-CI8002 T4 Kokillengustck This Xerospace Series“ Prestandard has been drawn up under the responsibility of AECMA-STAN (The European Association of Aerospace Industries - Standard
3、ization). It is published 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 an extent that interchangeab
4、ility 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 (prEN) to CEN (European Committee for Standardization) for formal vote and transformat
5、ion to full European Standard (EN). The CEN national members have then to implement the EN at national level by giving the EN the status of a national standard and by withdrawing any national standards conflicting with the EN. Metallic Material Domain Copyright 2004 O by AECMA-STA/ Page 2 prEN 461 6
6、:2004 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- STANS General Process Manual, this standard has received approval for Publication.
7、 Page 3 prEN 461 6:2004 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 has been prepared in accordance with EN 4500-2. 1 Scope This standard specifies the
8、requirements relating to: Magnesium alloy MG-CI 8002 T4 Chill casting for aerospace application. 2 Normative references This European Standard incorporates by dated or undated reference, provisions from other publications. These normative references are cited at the appropriate places in the text an
9、d 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 undated references the latest edition of the publication referred to applies (i
10、ncluding amendments). 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 organization of standardization - Links between types of EN standa
11、rds 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) Published as AECMA Prestandard at the date of publication of this standard Page 4 prEN 461 6
12、:2004 Limit dimension(s) mm Technical specification Magnesium alloy MG - CI8002 a I Material designation - EN 2076-3 Chemical composition % 3.1 Element min. Cut-up, undesignated location, Cut-up, designated location Test sample(s) Separately cast gated or integral Method of melting I 3.2 3.3 9 - -or
13、m I Chill casting Test piece(s) See EN 2076-3. See EN 2076-3. See EN 2076-3. Heat treatment Use condition Use condition Use condition Dimensions concerned mm See EN 2076-3. as20 as20 Method of production Thickness of cladding on each face Chill casting % - - - Elongation Reduction of area I T4 I 6.1
14、 I Delivery condition A% 27 25c 25c Z % - I U I 6.2 I Delivery condition code 17 18 19 I T4 I 7 I Use condition Hardness - Shear strength R, MPa - Bending k- - I Heat treatment I Delivery condition I 23 -c 24 25 26 27 - - Characteristics Stress oa MPa - Elongation a% - Rupture stress oR MPa - Elonga
15、tion at A % - rupture abc Notes (see line 98) - I - I - I 11 I Direction of test piece Ambient I Ambient I Temperature I 0 I “C I Ambient Proof stress I I MPa I 2 80 I 260 I 260 Strength I R, I MPal 2 200 I 2 120 I 2 120 - 20 I Impact strength I 21 I ITemperature I 0 I “C I - 22 I ITime Ihl - Page 5
16、 prEN 461 6:2004 Hardness ixternal defects 55 (Typical value) 20 per batch HB nternal defects 3atch uniformity Marking inspection 3imensional 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 alloy designation IS0 - MgA18Zn and alloy
17、 designations AZ81A and AZ80 but has tighter controls on impurity elements in order to promote maximum corrosion resistance. Unless otherwise advised by the purchaser, the manufacturer may, at his discretion, and especially to minimize distortion in thin sections, alternatively air cool to ambient t
18、emperature 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. b 100 Page 6 prEN 461 6:2004 - Product qualification
