1、STD.AECMA PREN 3553-ENGL 1797 m LOL23LL 00317238 5bb m AECMA STANDARD prEN 3553 NORME AECMA Edition P 2 AECMA NORM November 1999 I I aecma 1999 ICs: l PUBLISHED BY THE EUROPEAN ASSOCIATION OF AEROSPACE INDUSTRIES (AECMA) Gulledelle 94 - 6-1200 BRUXELLES - Tel. (+32) 2 775 81 IO - Fax. (+32) 2 775 81
2、 11 Superseding edition P 1 October 1988 Edition approved for publication Descriptors: C5 Chairman Comments should be sent within six months aer the date of oubiication to ENGLISH VERSION Aerospace series Aluminium alloy AL-PZ61 8A T651 I Extruded bar and section aor DS 160 mm Srie arospatiale Allia
3、ge daluminium AL-P2618A T651 I Barres et profils fils aou DI160mm Luft- und Raumfahrt Aluminiumlegierung AL-P2618A T651 I Stranggeprete Stangen und Profile a oder D I 160 mm This %Aerospace Series“ Prestandard has been drawn up under the responsibility of AECMA (The European Association of Aerospace
4、 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 Commiftee following comment by the Member countries. Subsequent to the publication of this Prestandard, the technical content shall not be changed t
5、o an extent that interchangeability is affected, physically or functionally, without re-identification of the stan dard. Affer examination and signature of the AECMA Standard Checking Centre (NPS) and formal agreement of the Oficial Services of the Member countries it will be submitted as a draft Eu
6、ropean Standard to CEN (European Committee for Standardization) for formal vote. 1999-1 1-30 AECMA Gulledelle 94 8-1200 BRUXELLES Mr Evetts STD*AECMA PREN 3553-ENGL 1999 W LOL231L OOL72L9 4T2 W Page 3 prEN 3553: 1999 O Introduction This standard is part of the series of EN metallic material standard
7、s 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-P2618A T651 I Extruded bar and section a or D I 160 mm for aer
8、ospace applications. This standard may also be used to supply material in the T6510 condition if specified by the purchaser on the order and the product is marked accordingly. 2 Normative references This European Standard incorporates by dated or undated reference provisions from other publications.
9、 These normative references are cited at the appropriate places in the text and the publications are kted 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 und
10、ated 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 aluminium alloy wrought products - T
11、echnical 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 EN 4500-2 Aerospace series - Metallic materials - Rules for drafting and presentation of material standards - P
12、art 2: Specific rules for aluminium, aluminium alloys and magnesium alloys 1) 1) Published as AECMA Prestandard at the date of publication of the present standard 1 Material designation 2 Chemical composition Element II Aluminium alloy AL-PZ61 8A Si Fe Cu Mn Mg Ni Zn Zr+Ti Ti AI Others Each Total %
13、min. 0,151 0,25 0,Q 1,8 - 1,2 0.8 - - - - - 1,4 2,7 0,25 1,8 1,4 0,15 0,25 0,20 0,05 0,15 1 Base 1 I - 1 3 I Method of melting I 5 14.1 I Form I Bar and section I Technical specification EN 2070-3 I 14.2 I Method of production Delivery condition T4511 T6511 , Heat treatment 525 C 5 I 535 “C I WO 80
14、“C 1) + 1 % I controlled stretched s 3 % + 0= ambient It 2 5d 525 C I er 535 C I WQ 0s 80 “C 1) + 1 % 2 controlled stretched 5 3 % + 187 C I 01 205 “C I 16 h 5 t 2 24 h Extruded Delivery condition code Use condition 14.3 1 Limit dirnension(s) I mm I a or D 2 160 I K U T6511 T651 I Test sample) See E
15、N 2070-3 Heat treatment Dimension concerned mm Heat treatment Use condition 10 a or D I 100 80rs10 100 8 or D 2 160 I Delivery condition + 187 C 05 205 “C I 16 h I t s 24 h I Thickness of cladding on each face Delivery condition I 0/6 - - - Characteristics Proof stress Rp0,2 MPa 2 340 T Strength R,
16、MPa 2 410 2 360 2 350 2 420 2410 18.2 I Test piece) I See EN 2070-3 I 16 17 Reduction of area Z I - Hardness - Bending I 11 I Direction of test piece I L I L I L I k- - I Ambient I Ambient I I12 I ITemperature I ,g I C I Ambient Impact strength Temperature le OC Time h Stress Elongation a O? MPa (Ja
17、 C, I I - - - - - 25 26 27 -. I I MPa - OR Rupture stress rupture Elongation at A% - Notes (see line 98) 1) 25 I 26 I 26 I -1 I 18 I Shear strength I R, 1 MPa I 19 20 21 22 23 24 - - - - - L I STD-AECMA PREN 3553-ENGL 1999 9 LOL23LL 0017221 050 1) A longer solution treatment time than is usual may b
18、e required for this alloy, typically 4 h st I 24 h. Page 5 prEN 3553: 1999 7 Electrical conductivity ! External defects I Y MSlm 21 ,O (typical value) iternal defects Hardness latch uniformity 135 (typical value) HB 6 5 20 per product A I30 per batch Marking inspection Dimensional inspection Notes 99 Typical use I - See EN 2070-3 - See EN 2070-3 -I - See EN 2070-3 See EN 2070-3 See EN 2070-3 - I STDeAECMA PREN 3553-ENGL 1999 LOL23LL 0037222 T97 - Page 6 prEN 3553: 1999 Product qualification See EN 2043 Qualification programme to be agreed between manufacturer and purchaser.
