1、AECMA PREN*3bbb 95 I L0123LL 0009856 741 = Edition approved for publication 1995-10-31 AECMA STANDARD prEN 3666 NORME AECMA Edition P 2 AECMA NORM October 1995 Comments should be sent within six months after the date of publication to AECMA Gulledelle 94 B-I 200 BRUXELLES PUBLISHED BY THE EUROPEAN A
2、SSOCIATION OF AEROSPACE INDUSTRIES IAECMA) Gulledelle 94 - 8-1200 BRUXELLES - Tel. (32) 2 775 81 10 - Fax. (32) 2 775 81 1 1 ICs : Supersedes Issue P1 March 1994 Descriptors : ENGLISH VERSION Aerospace series Heat resisting alloy NI-PH2601 Solution treated and cold worked Bar for forged fasteners DI
3、50mrn 1550 MPa I Rm I 1830 MPa Srie arospatiale Luft- und Raumfahrt Alliage rsistant chaud NI-PH2601 Mis en solution et croui Barres pour lments de fixations forgs 1550 MPa I R, I 1830 MPa Hochwarmfeste Legierung NI-PH260 1 Lsungsgeglht und kaltverestigt Stangen zum Stauchen fr Verbindungselemente 1
4、550 MPa I R, I 1830 MPa DI50mm DI50mm 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 conc
5、erned Technical Committee following 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 examinatio
6、n and signature of the AECMA Standard Checking Centre (NPSI 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. - Techn
7、opolis 54 - 199, rue Jean-Jacques Rousseau - 921 38 ICCY-LES-MOULINEAUX CEDEX C5 Chairman M. Odorico aecma 1995 Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from
8、 IHS-,-,-AECMA PREN+3666 75 103Z31L 0009858 514 m Page 3 prEN 3666 : 1995 O Introduction For the use of this standard, see EN 2500-3. 1 Scope This standard specifies the requirements relating to bar for forged fasteners, D I 50 mm, solution treated and cold worked, in heat resisting alloy NI-PH2601,
9、 1550 MPa I R, 5; 1830 MPa, for aerospace applications. 2 Normative references This European Standard incorporates by dated or undated reference provisions from other publications. These normative references are cited at the appropriate places in the text and the publications are listed hereafter. F
10、or 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 edition of the publication referred to applies. EN 2002-16 EN 2500-3 EN 3235-3 Aerospace se
11、ries - Test methods for metallic materials - Pari 16 : Penetrant inspection 1) Aerospace series - Instructions for the drafting and use of metallic material standards - Part 3 : Specific requirements for heat resisting alloys 2) Aerospace series - Heat resisting alloys - Wrought products - Technical
12、 specification - Part 3 : Bar and section 2) I) In preparation at the date of publication of this standard 2) 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 AECMAN
13、ot for ResaleNo reproduction or networking permitted without license from IHS-,-,-AECMA PREN*3bbb 95 W LOL23LL 0009859 450 8 Sample Test piece Heat treatment Page 4 prEN 3666 : 1995 Cut from bar Reference heat treatment : see line 29 - I Heat resisting alloy NI-PH2601 Dimenshsconcemed oneachface Thi
14、cknessofcladding Method of melting Vacuum induction melted and consumable electrode remelted (vacuum or slag) Fomi Bar for forged fasteners Method of produdion Cold worked, straightened and ground mm - % - Limit dimensions (mm) OS50 5.1 Technical qmcificafon EN 3235-3 5.2 Dimensional standards - 6.1
15、 Delivery dition and heat treatment Solution treated and cold worked 930 “C s 8s 1010 “CI t = 1 h /AC or faster +15% scoldworked S3%ati3s650C 6.2 Delivery condition code U use condition Delivery condition and heat treatment - - 9 10 - EGiifIoftestDieCe I L I I 11 Dii 12 Temperature 0 C 14 T Strength
16、 R, MPa 155O R, I 1830 15 Elonaatior -. 13 Proofstress Rw, MPa 2 1380 - -, - 16 17 Hardness Shearstrenuth I area I Temperature I e “C - Time h - SITOS8 ag MPa C Elongption a% - Rupturestress - Ekngaona A % - - OR MPa Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided
17、by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-AECIA PRENx3bbb 95 I LOL23LL 00098b0 172 Page 5 prEN 3666 : 1995 Reference heat treatment Grain size External defects Macrostnicture Internal defects Designation Notes Typical use Precip
18、itation treated Delivery condition + O= 720 “C It = 8 h I FC at 8= 50 C per h to 8= 620 “C It = 8 h I FC or faster See EN 3235-3 5 or finer - No duplex structure See EN 3235-3 EN 2002-16 See EN 32353 One per batch See EN 32353 Class 5 *) p.p.m. 1) The product cannot be rejected on the sole basis of
19、the hardness measurements if the measured tensile characteristics are in conformity with the requirements in line 14. 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-,-,-
