ASD-STAN PREN 3552-2003 Aerospace Series Aluminium Alloy AL-P2618A T6 or T62 Clad sheet and strip 0 4 Less Than or Equal to a Less Than or Equal to 6 mm (Issue P 2)《航空航天系列 0 4mm≤a≤.pdf

1、AECMA STANDARD NORME AECMA AECMA NORM Edition approved for publication 15 May 2003 prEN 3552 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 October 1988 Aerospace series Aluminium all

2、oy AL-P2618A T6 or T62 Clad sheet and strip 0,4 mm a 6 mm Srie arospatiale Alliage daluminium AL-P2618A T6 ou T62 Tles et bandes plaques 0,4 mm i ai 6 mm Luft- und Raumfahrt Aluminiumlegierung AL-P2618A T6 oder T62 Bleche und Bnder, plattiert 0,4 mm i ai 6 mm This “Aerospace Series“ Prestandard has

3、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 concerned Domain following member comment

4、s. 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 formal agreement of AECMA-STAN it will b

5、e 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 Page 2 prEN 3552: 2003 Foreword This standard was reviewed by the Domain Technical Coordinator of AECMA-STANS Metallic Material Domain

6、. 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. Page 3 prEN 3552: 2003 O Introduction This standard is part of the series of EN metallic material standards for aero

7、space 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-P2618A T6 or T62 Clad sheet and strip 0,4 mm a 6 mm for aerospace applic

8、ation. 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 to or

9、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 standardization - L

10、inks between types of EN standards and their use EN 4400-2, Aerospace series - Aluminium and aluminium alloy wrought products - Technical specification - Part 2: Sheet and strip 1 ) EN 4500-2, Aerospace series - Metallic materials - Rules for drafting and presentation of material standards - Part 2:

11、 Specific rules for aluminium, aluminium alloys and magnesium alloys 1) 1) Published as AECMA Prestandard at the date of publication of this standard Page 4 prEN 3552: 2003 Heat treatment - 3.1 3.2 3.3 - - Delivery condition + 525 OC e 535 OC 1 WQ e 40 OC + 195 “C Os205 “CI 16 h t 24 h Delivery cond

12、ition Form Clad sheet and strip Method of production Rolled Limit dimension(s) mm 0,4 a 6 Technical specification EN 4400-2 Test sample(s) Test piece(s) I T6 I O I F I Delivery condition See EN 4400-2. See EN 4400-2. Heat treatment 9 I 525 OC e 535 OC 1 WQ e 40 OC + 180 “C 6% 205 “C I 16 h t 24 h I

13、Dimensions concerned mm 0,4 a 3 3a6 Thickness of cladding on % each face 24 22 I U I A I F I Delivery condition code Strength Elongation Reductionofarea I T62 a I T6 I Use condition R, MPa 2 390 2 395 A% hmm 2 7 A50mm 2 5 Z % - Time Stress oa Elongation Rupture stress oR Characteristics - h MPa - a%

14、 - MPa - Elongation at ru Dtu re Use condition: T6 or T62 I Heat treatment A % - I LT I LT 11 I Direction of test piece I I Ambient I Temperature I 0 I “C I Ambient Proof stress I Rp0,2 I MPa I 2 310 I 2 325 I I - I 17 I Hardness I 18 I Shearstrength I R, I MPa I - I 19 I Bending 1kl-l - - 20 I Impa

15、ct strength I 21 I ITemperature I 0 I “C I - -1 I I I 22 23 24 25 26 - - - - C 27 I Notes (see line 98) I a ixternal defects - 2ladding chemical mmposition % See EN 4400-2. 3atch uniformity 7 Marking inspection Iimensional inspection Aluminium alloy AL-P7072- Material designation Votes - rypical use

16、 Others Each Total Element Si+Fe Cu Mn Mg Zn AI - - - - - - 03 min. max. 0,7 0,lO 0,lO 0,lO 1,3 0,05 0,15 Base See EN 4400-2. 7 -I See EN 4400-2. Electrical conductivity See EN 4400-2. - - See EN 4400-2. See EN 4400-2. 51 T6 a Repeated resolution heat treatment is not recommended due to the effects of copper diffusion in the cladding upon elevated temperature properties. -I -I 100 See EN 4400-2. Qualification programme to be agreed between manufacturer and purchaser. Page 6 prEN 3552: 2003 - Product qualification