1、AECMA STANDARD NORME AECMA AECMA NORM Edition approved for publication 31 March 2003 prEN 3335 Edition P 3 March 2003 Comments should be sent within six months after the date of publication to AECMA-STAN ICs: Descriptors: ENGLISH VERSION Aerospace series Al um i ni um alloy AL-P7475- 02 Sheet for su
2、perplastic forming (SPF) 0,8 mm I al 6 mm Supersedes edition P 2 February 1999 Srie arospatiale Luft- und Raumfahrt Alliage daluminium AL-P7475- Aluminiumlegierung AL-P7475- 02 02 Tles pour formage superplastique (FSP) 0,8 mm I ai 6 mm Bleche fr superplastische Formgebung (SPF) 0,8 mm I a I 6 mm Thi
3、s “Aerospace Series“ Prestandard has been drawn up under the responsibility of AECMA-STAN (The European 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 conc
4、erned Domain following member comments. 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 review by users and for
5、mal agreement of AECMA-STAN it will be submitted as a draft European Standard to CEN (European Committee 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 l
6、icense with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Page 2 prEN 3335: 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 rul
7、es of AECMA-STAN defined in AECMA- STANS General Process Manual, this standard has received approval for Publication. Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without licens
8、e from IHS-,-,-Page 3 prEN 3335: 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 has been prepared in accordance with EN 4500-2. 1 Scope This standard
9、specifies the requirements relating to: Aluminium alloy AL-P7475- 02 Sheet for superplastic forming (SPF) 0,8 mm gag6 mm for aerospace application. 2 Normative references This European Standard incorporates by dated or undated refere ce provisia s from other publicatic S. These normative references
10、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 undated references the latest
11、 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 4400-2, Aerospace series - Aluminium and aluminium alloy wrought products - Technical specification - Part
12、2: Sheet and strip 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 at the date of publication of this standard Copyright
13、 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 4 prEN 3335: 2003 Heat treatment Delivery condition code - 3.1 - 3.2 7 - - - 3.1 3.2 3.3 9 10 11 12 13 14 1
14、5 16 17 18 19 20 21 22 23 24 25 26 27 - - - - - - - - - - - - - - - - - - - - - - Thermomechanically processed to enhance superplastic forming capability F Form Sheet Method of production Limit dimension(s) mm 0,8 a 6 Rolled and thermomechanically processed to enhance superplastic forming capability
15、 Technical specification EN 4400-2 Test sample(s) Test piece(s) Delivery condition I 02 a See EN 4400-2. See EN 4400-2. Dimensions concerned each face Thickness of cladding on 02 I Use condition mm % - 0,8 a 6 I Delivery condition I Heat treatment Proof stress Strength Elongation Reductionofarea Cha
16、racteristics Rp0,2 MPa 2 410 2 410 R, MPa 2 490 2 490 A% &omm29c &mm 2 9 Z % - Time Stress oa Elongation Rupture stress oR T762 (see line 29.) I Heat treatment - h MPa - a% - MPa - Elongation at ru Dtu re Direction of test piece I L I LT A % - Ambient I Temperature I 0 I “C I Ambient - I Hardness Sh
17、ear strength I R, I MPa I - Bending 1kl-l - - Impact strength I I Temperature I 0 I “C I - i a, b, c Notes (see line 98) I Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without l
18、icense from IHS-,-,-Page 5 prEN 3335: 2003 y 2 22,5 MSlm ieference heat treatment Acceptable Microstructure y 22,O MSlm ilectrical conductivity Not acceptable 3ain size ixternal defects 3uperplastic forming capability Marking inspection Iimensional inspection Votes rypical use Delivery condition + 1
19、15 “C 6% 125 “Cl3 h t 6 h + 158 “C 6% 168 “C I 14 h t 20 h See EN 4400-2. + 460 oc e 485 oc I WQ e 40 oc One sample per batch unless agreement is reached between the manufacturer and purchaser that the “capability clause“ may apply. The sample shall be taken from a region of the test specimen tested
20、 at line 63 representing a level of strain to be agreed between manufacturer and puchaser. The sample shall be examined in the un-etched condition. Intergranular cavitation acceptance levels shall be agreed between manufacturer and purchaser See EN 4400-2. 22,O MSlm y 22,5 MSlm I Acceptable if Rp0,2
21、 470 MPa One sample per batch unless agreement is reached between the manufacturer and purchaser that the “capability clause“ may apply. See EN 4400-2. See EN 4400-2. Two samples per direction per batch Superplastic forming capability shall be assessed by an elevated temperature tensile test. Delive
22、ry condition: 02 - Testing temperature: 510 “C 6% 520 “C - Soaking time: 15 min t 45 min - Constant crosshead velocity: v = & x hrt where: Lbrt = i, + 2R and strain rate, &26.104s- Elongation I AL, I % I 2 300 See EN 4400-2. See EN 4400-2. a Cold working or straightening only acceptable when strain
23、3 %. The properties of the superplastically formed parts are defined by the drawing. This heat treatment and specified minimum mechanical properties relate to release testing by the manufacturer. The minimum mechanical properties may not necessarily be achieved in superplastically formed components.
24、 Superplastically formed components. 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 4400-2. Qualification programme to be agreed between manufacturer and purchaser. Page 6 prEN 3335: 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-,-,-
