1、STD-AECMA PREN 4273-ENGL 1998 1012311 OO145b4 417 = AECMA STANDARD NORME AECMA AECMA NORM prEN 4293 Edition P 1 April 1998 PUBLISHED BY THE EUROPEAN ASSOCIATION OF AEROSPACE INDUSTRIES (AECMA) Gulledelle 94 - 5-1 200 BRUXELLES - Tel. +32) 2 775 81 1 O - Fax. (+32) 2 775 81 1 1 ICs: Descriptors: ENGL
2、ISH VERSION Aerospace series Aluminium alloy AL-P7 1 75- T73511 Extruded bar and section a or D I 150 mm Srie arospatiale Alliage daluminium AL-P7175- T73511 Barres et profils fils a ou D I 150 mm Luft- und Raumfahrt Aluminiumlegierung AL-P7175- T73511 Stranggeprete Stangen und Profile a oder D I 15
3、0 mm This “Aerospace Series Prestandard has been drawn up under the responsibility of AECMA (The European Association of Aerospace Industries). It is published on green paper for the needs of AECMA-Members. It has been technically approved by the experts of the concerned Technical Committee followin
4、g comment by the Member countries. Subsequent to the publication of this Prestandard, the technical content shall not be changed to an extent that interchangeability is affected, physically or functionally, without re-identification of the standard. After examination and signature of the AECMA Stand
5、ard Checking Centre (NPS) and formal agreement of the Official Services of the Member countries it will be submitted as a draft European Standard to CEN (European Committee for Standardization) for formal vote. Nota - Extra copies can be supplied by B.N.A.E. - Technopolis 54 - 199, rue Jean-Jacques
6、Rousseau - 921 38 ISSY-LES-MOULINEAUX CEDEX Edition approved for publication 1998-04-30 Comments should be sent within six months after the date of publication to AECMA Gulledelle 94 B-1200 BRUXELLES C5 Chairman Mr Evetts I aecrna 1998 Copyright Association Europeene des Constructeurs de Materiel Ae
7、rospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-STD-AECMA PREN Li273-ENGL 1778 LOL231L 00145b5 353 w Page 3 prEN 4293: 1998 O Introduction This standard is part of the series of EN metallic material standards for ae
8、rospace 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-P7175- T73511 Extruded bar and section a or D 5 150 mm for aerospace a
9、pplications. This standard may also be used to supply material in the T73510 and T6510 condition if the purchaser specifies either of these conditions on the order and the product is marked accordingly. 2 Normative references This European Standard incorporates by dated or undated reference provisio
10、ns 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 it by a
11、mendment or revision. For undated references the latest edition of the publication referred to applies. EN 2043 Aerospace series - Metallic materials - General requirements for semi-finished product qualification (excluding forgings and castings) 1) EN 2070-3 Aerospace series - Aluminium and alumini
12、um alloy wrought products - Technical specification - Part 3: Bar and section EN 4258 Aerospace series - Metallic materials - General organization of standardization - Links between types of EN standards and their use 1) EN 4500-2 Aerospace series - Metallic materials - Rules for drafting and presen
13、tation of material standards - Part 2: Specific rules for aluminium, aluminium alloys and magnesium alloys 1) 1) Published as AECMA Prestandard at the date of publication of this standard previous page is blank - - Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by
14、 IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-STD-AECMA PREN 1i273-ENGL L778 D 1012311 OOLq5bb 27T Page 4 prEN 4293: 1998 Element min. max. Si Fe Cu Mn Mg Cr Zn Ti Others AI Each Total 2,l 0,18 5,l - - - Base 1,2 - - - 0,15 0,20 2,O 0
15、,lO 2,9 0,28 6,l 0,lO 0,05 0,15 3 4.1 4.2 4.3 5 - Method of melting Form Bar and section Method of production Extruded Limit dimension(s) mm a or D I 150 Technical specification EN 2070-3 8. I 8.2 8.3 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 - - - - - - - - - - - - - - - - - - - - - Hard
16、ness Shear strength Rc MPa Bending k- - - - Impact strength Temperature e “C Time h Stress I Ga MPa - - - - Elongation at rupture - A % Notes (see line 98) 1) 2) I Aluminium alloy AL-P7175- 1 I Material designation I composition - 6.1 TiG$GDeliverycondition I T6511 T7351 I Heat treatment r 460 “C I
17、81 480 “CI WQ 6% 80 “C + I % 5 controlled stretched I 3 % + minor straightening + 105 C I 81 125 “C I6 h I t I 24 h + 172 “C I 81 182 “C 16 h I t I 16 h U T73511 Delivery condition 460 “C a 81 480 “CI WQ 81 80 “C I) + 1 % I controlled stretched I3 % + minor straightening + 105 “C 5 85 125 “C 120 h a
18、 t a 30 h 6.2 I Delivery condition code I P 7 I Use condition I T7351 I I Delivery condition + 172 “C I 81 182 “C 16 h I t I 16 h Heat treatment Characteristics I See EN 2070-3 I Test sample(s) I I See EN 2070-3 I 1 Heat treatment I Use condition I I 50 a or D I 75 I 75 a or D 5 120 120 a or D 5 150
19、 I Dimensions concerned mm a or D s 10 10 a or D I20 20 a or D I50 Thickness of cladding on 01, - - - L L L “C Ambient Ambient Ambient Ambient Ambient Ambient MPa 2400 2 420 2 415 2 410 t 390 t 370 Temperature Proof stress Strength MPa 2470 2 485 2 485 2 475 2 470 2 450 % 2 8 *) 28 28 28 27 27 Elong
20、ation A z - Reduction of area JI I I I ICI Elongation I a 1 % I - AI 1 I I I Rupture stress I UR I MPa( - 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-,
21、-,-STD-AECMA PREN 4293-ENGL 1998 I LU1231L 00L45b7 12b a Electrical conductivity Page 5 prEN 4293: 1998 Stress corrosion Fracture toughness (Kid I -I See EN 2070-3 3 I Measurement on the surface of the sample from which tensile specimens are taken. I 71 y 2 23 MSm I Acceptable I 1 21 The “capability
22、 clause“ applies or as per line 32 I a orDz25mm I 31 6 7 t=20d o= 75 % Rp0,2 min. L , See EN 2070-3 I - 2 The “capability clause“ applies 7 Dimensions T-L (mm) MPafi -1 See EN 2070-3 Electrical conductivity Y MSlrn 19 (typical value) See EN 2070-3 Hardness - HB 6 A 150 (typical value) I 20 per produ
23、ct 5 30 per batch 140 (typical value) I 20 per product 2 30 per batch 99 Typical use 22 MSm I y 23 MS/m I Acceptable if Rp0,Z L 2 Rp0.2 min. L + 85 MPa or if stress corrosion test acceptable I y 22 MSm I Non acceptable -I See EN 2070-3 401 a or D I 150 I 2 25 I External defects Macrostructure See EN
24、 2070-3 Internal defects See EN 2070-3 Batch uniformity See EN 2070-3 I T6511 I T73511 l See EN 2070-3 95 I Marking inspection See EN 2070-3 1) The use of quench additives or higher quenchant temperature shall be subject to agreement between manufacturer and purchaser. 2) i Ajomm 2 7% Copyright Asso
25、ciation Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-STDaAECMA PREN Li273-ENGL 2778 2012322 00LqSb8 Ob2 D Page 6 prEN 4293: 1998 3roduct qualification See EN 2043 Qualification programme to be agreed between manufacturer and purchaser. 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-,-,-
