1、CEN PREN*29bL 94 W 3404589 OOb2LL 432 AECMA STANDARD NORME AECMA AECMA NORM prEN 2961 Edition P2 March 1994 DIT PAR LASSOCIATION EUROPENNE DES CONSTRUCTEURS DE MATRIEL AROSPATIAL Technopolis - 175, rue Jean-Jacques Rousseau - F-92138 Issy-les-Moulineaux Cedex - Tl. (1) 47.36.98.76 Supersedes issue P
2、1 UDC : March 1988 Descriptors : ENGLISH VERSION Aerospace series Heat resisting alloy NI-PH2601 Solution treated Bar for machined fasteners DI50mm Rm 2 1270 MPa Srie arospatiale Alliage rsistant chaud NI-PH2601 Mis en solution Barres pour lments de fixations usins DI50mm R, 2 1270 MPa Luft- und Rau
3、mfahrt Hochwarmfeste Legierung NI-PH2601 Lsungsgeglht Stangen fr spanend hergestellte Verbindungselemente Ds50mm R, 2 1270 MPa This “Aerospace Series I Prestandard has been drawn up under the responsibility of AECMA IAssociation Europenne des Constructeurs de Matriel Arospatial). It is published on
4、green paper for the needs of AECMA-Members. It has been technically approved by the experts of the concerned 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 interchangeabili
5、ty is affected, physically or functionally, without re-identification of the standard. After examination and signature of the AECMA Standard 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
6、Committee for Standardization) for formal vote. Nota - Extra copies can be supplied by B.N.A.E. - Technopoiis 54 - 199, rue Jean-Jacques Rousseau - 921 38 ICSY-LES-MOULINEAUX CEDEX Comments should be sent within six months after the date of publication to I Edition approved for publication 1994-03-3
7、 1 AECMA Technopolis - 175, rue Jean-Jacques Rousseau 921 38 Issy-les-Moulineaux Cedex - FRANCE C5 Chairman M. Odorico aecma 1994 Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted wi
8、thout license from IHS-,-,-CEN PREN+29hL 94 3404589 0062382 379 M Page 3 prEN 2961 : 1994 O Introduction For the use of this standard, see EN 2500-3. 1 Scope This standard specifies the requirements relating to bar for machined fasteners, D 50 mm, solution treated, in heat resisting alloy NI-PH2601,
9、 R, 2 1270 MPa, for aerospace applications. 2 Normative references EN 2002-1 6 Aerospace series - Test methods for metallic materials - Part 16 : Penetrant inspection 1) EN 2500-3 Aerospace series - Instructions for the drafting and use of metallic material standards - Part 3 : Specific requirements
10、 for heat resisting alloys 2) EN 3235-3 Aerospace series - Heat resisting alloys - Wrought products - Technical specification - Part 3 : Bar and section 2) 1) In preparation at the date of publication of this standard 21 Published as AECMA Prestandard at the date of publication of this standard Prev
11、ious page is blank 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-,-,-CEN PRENx29bL 94 = 3404589 0062183 205 Page 4 prEN 2961 : 1994 3 Method of melting I
12、 Vacuum induction melted and consumable electrode remelted (vacuum or slag) I I I Limit dimensions (mm) I Bar for machined fasteners Softened, cold worked, solution treated, straightened and ground Di 60 6 6.1 Technical specification EN 3236-3 6.2 Dimensional standards - 6.1 Delivery condition Softe
13、ned, cold worked and solution treated I and Heat treatment 930CSs;10200C/t = IhIACorfastw + 16 Oh i cold worked i 30 % at 9 i 660 OC + 93OoC5i 101O0CIt = IhIACorfaster 6.2 Delivery condition code W Use condition and Heat treatment Delivery condition Solution treated and precipitation treated + 720OC
14、It = 8hIFCat60OCperh + 620 OC I t = 8h I AC or faster Characteristics 8 Sample Test piece Heat treatment Cut from bar Delivery condition Cut from bar Use condition I 9 I Dimensions concerned I mm I D S 60 I Di60 I 17 Harness HV i 277 337 S HB 5 460 or 36 i HRC S 46 18 Shear strength I & IhnPa 1Q Ben
15、dina IkI- 20 Impact strength 21 Temperature I I OC 660 22 Time 2 23 - - 23 Stress ea MPa 24 C Elongation a% 26 Rupture stress tq MPa 690 1) 21 26 Elongation at A % 26 27 Notes (see line 88) “1 1) 2) - - rupture Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS
16、 under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-CEN PREN*2961 94 = 3404589 0062384 141 = 2 Page 5 prEN 2961 : 1994 See EN 3236-3 One per batch Grain size 3 7 External defects L and LT 4 or finer - Isolated grain up to 2 - No duplex structur
17、e See EN 3236-3 Macrostructure 1 Internal defects EN 2002- 16 See EN 3236-3 Designation Notes 2 Typical use One per batch See EN 3236-3 7 Flat bottom hole D = 1,2 mm -I 1) Proportional round test piece 2) Stress may be increased after 48 h to promote the rupture. -1 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-,-,-
