1、AECMA STANDARD NORME AECMA AECMA NORM Edition approved for publication 15 May 2003 prEN 4283 Edition P 2 May 2003 Comments should be sent within six months after the date of publication to AECMA-STAN ICs: Descriptors: ENGLISH VERSION Supersedes edition P 1 April 1998 Aerospace series Aluminium alloy
2、 AL-P2219- T87 Plate 6 mm a 40 mm Srie arospatiale Alliage daluminium AL-P2219- T87 Tles paisses 6 mm al 40 mm Luft- und Raumfahrt Aluminiumlegierung AL-P2219- T87 Platten 6 mm al 40 mm This “Aerospace Series“ Prestandard has been drawn up under the responsibility of AECMA-STAN (The European Associa
3、tion of Aerospace Industries - 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 conten
4、t shall not be changed to an 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 St
5、andardization) for formal vote. Metallic Material Domain I I Copyright 2003 O by AECMA-STA1 Page 2 prEN 4283: 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 AE
6、CMA-STAN defined in AECMA- STANS General Process Manual, this standard has received approval for Publication. Page 3 prEN 4283: 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 i
7、n EN 4258. This standard has been prepared in accordance with EN 4500-2. 1 Scope This standard specifies the requirements relating to: Aluminium alloy AL-P2219- T87 Plate 6 mm a 40 mm for aerospace application. 2 Normative references This European Standard incorporates -y dated or undated reference
8、provisions from other publications. 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
9、 it by amendment or revision. For undated references the latest edition of the publication referred to applies. EN 4258, Aerospace series - Metallic materials - General organization of standardization - Links between types of EN standards and their use EN 4400-1, Aerospace series - Aluminium and alu
10、minium alloy wrought products - Technical specification - Part I: Plate 1) 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 4283: 2003 1 Material designation Aluminium alloy AL-P2219- 3 4.1 4.2 4.3 5 - - - - Form Method of production Limit dimension(s) mm Technical specification Method of melting I Plate Rolled 6a40 EN 4400-1 Delivery condition - 3.1 - 3.2 7 - - - 3.
12、1 3.2 3.3 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 - - - - - - - - - - - - - - - - - - - - - - T37 T87 Use condition Heat treatment T87 T87 530 OC e so OC 1 WQ e 40 OC + cold rolled 2 7 % + 1 % controlled stretched 3 % + 170 “C 6% 185 “C I 10 h t 30 h 530 OC e so OC 1 WQ e 40 OC + col
13、d rolled 2 7 % + 1 % controlled stretched 3 % Heat treatment Dimensions concerned mm Delivery condition code I K I U Use condition. 25 a 40 6a25 Thickness of cladding on each face Heat treatment % - - Delivery condition + 170 “C 6% 185 “C I 10 h t 30 h I I Reductionofarea Delivery condition Z % - Ch
14、aracteristics Hardness Shear strength R, MPa Bending k- Test sample(s) I See EN 4400-1. - - - Test piece(s) I See EN 4400-1. - Elongation Rupture stress a% - oR MPa - Elongation at rupture LT I L I LT I L I Direction of test piece A % - I Temperature I 0 I “C I Ambient I Ambient I Ambient I Ambient
15、2 350 I 2 350 I 2 350 I I Proof stress I RO, I MPa I 2 350 2 440 I 2 440 I 2 440 I T I Strength I R, I MPal 2 440 I Elongation I A I % I 27 I 27 I 26 I 26 - Impact strength I I Temperature I 0 I “C I - I Time Ihl Page 5 prEN 4283: 2003 - 3ain size See EN 4400-1. ntergranular corrosion 7 - Stress cor
16、rosion G21 See EN 4400-1. 3acture toughness (Klc) 6 7 ixternal defects ixfoliation corrosion O = 260 MPa t230d nternal defects - - 3atch uniformity See EN 4400-1. See EN 4400-1. Marking inspection 7 - Iimensional inspection Exfoliation corrosion shall not be greater than that of grade EB See EN 4400
17、-1. Votes 5 7 rypical use - T37 T87 Electrical conductivity y MSlm 17,5 (typical value) 20 (typical value) or - - 115 (typical value) 140 (typical value) Hardness 6 HB I 16 per product I 20 per product A I 24 per batch I 30 per batch See EN 4400-1. -I See EN 4400-1. - a The manufacturer shall mainta
18、in hydrogen content at: H2 I 0,25 mlll00 g. The “capability clause“ may apply. For a 123 mm, mm 2 6 %. -I See EN 4400-1. 71 Dimensions (mm) T-L MPa & 2 25 I 25 a 40 I -I See EN 4400-1. -I See EN 4400-1. -I 100 See EN 4400-1. Qualification programme to be agreed between manufacturer and purchaser. Page 6 prEN 4283: 2003 - Product qualification
