1、AECMA STANDARD NORME AECMA AECMA NORM Edition approved for publication 14 March 2003 prEN 4209 Edition P 2 March 2003 Comments should be sent within six months after the date of publication to AECMA-STAN ICs: Descriptors: Supersedes edition P 1 June 1995 ENGLISH VERSION Aerospace series Aluminium al
2、loy AL-P2219- T851 Plate 6 mm a 50 mm Srie arospatiale Alliage daluminium AL-P2219- T851 Tles paisses 6 mm a I 50 mm Luft- und Raumfahrt Aluminiumlegierung AL-P2219- T851 Platten 6 mm ai 50 mm This “Aerospace Series“ Prestandard has been drawn up under the responsibility of AECMA-STAN (The European
3、Association 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
4、 content 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
5、 for Standardization) for formal vote. Metallic Material Domain I I Copyright 2003 O by AECMA-STA1 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-,-,-Page
6、 2 prEN 4209: 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- STANS General Process Manual, this standard has received approval for
7、 Publication. 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-,-,-Page 3 prEN 4209: 2003 O Introduction This standard is part of the series of EN metallic
8、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 requirements relating to: Aluminium alloy AL-P2219- T851 Plate 6 mm a 50 mm for aerospace
9、application. 2 Normative references This European Standard incorporates by dated or undated refere ce provisia s from other publicatic S. These normative references are cited at the appropriate places in the text and the publications are listed hereafter. For dated references, subsequent amendments
10、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. EN 4258, Aerospace series - Metallic materials - General organization of standardizati
11、on - Links between types of EN standards and their use EN 4400-1, Aerospace series - Aluminium and aluminium 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: Spec
12、ific rules for aluminium, aluminium alloys and magnesium alloys 1) 1) Published as AECMA Prestandard at the date of publication of this standard Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networki
13、ng permitted without license from IHS-,-,-Page 4 prEN 4209: 2003 530 OC e so OC 1 WQ e 40 OC + 1,5 % controlled stretched 3 % + O= ambientlt 25 d Form Plate Method of production Rolled Limit dimension(s) mm 6a50 Technical specification EN 4400-1 530 OC e so OC 1 WQ e 40 OC + 13 controlled stretched
14、3 % + 171 “C 6% 182 “C I 16 h t 20 h I T351 I T851 I 3.1 I Delivery condition Test piece(s) Heat treatment Dimensions concerned mm each face Direction of test piece Thickness of cladding on % Heat treatment See EN 4400-1. Use condition. 123 a 25 25 a 50 6 a 12,5 - - - LT LT LT Reductionofarea I U I
15、K I 3.2 I Delivery condition code Z % - I T851 I T851 I 7 I Use condition Hardness Shear strength R, MPa Bending k- Heat treatment - - - I Delivery condition + 171 “C 6% 182 “C I 16 h t 20 h I - Elongation Rupture stress Delivery condition a% - oR MPa - - 3.1 3.2 3.3 9 10 11 12 13 14 15 16 17 18 19
16、20 21 22 23 24 25 26 27 - - - - - - - - - - - - - - - - - - - - - - Elongation at rupture Characteristics A % - Test sample(s) I See EN 4400-1. Notes (see line 98) - Ambient I Ambient I Temperature I 0 I “C I Ambient 2 315 I 2 315 I Proof stress I RO, I MPa I 2 315 2 425 I 2 425 I Strength I Rm I MP
17、al 2 425 Elongation I A I % I hmm 2 8 I 27 I 26 - Impact strength I I Temperature I 0 I “C I - I Time Ihl 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-,
18、-,-Page 5 prEN 4209: 2003 - ixternal defects See EN 4400-1. nternal defects 3atch uniformity 7 Marking inspection Iimensional inspection Electrical conductivity y MSlm 16,5 (typical value) 19 (typical value) Votes - - rypical use See EN 4400-1 See EN 4400-1 -I See EN 4400-1. See EN 4400-1. -I 51 - I
19、 T351 I T851 -I -I 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-,-,-100 See EN 4400-1. Qualification programme to be agreed between manufacturer and purchaser. Page 6 prEN 4209: 2003 - Product qualification 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-,-,-
