1、AECMA PREN2031 77 m LOL231L 0001751 b m ,. Approved by COMITE DE NORMALISATION of A.E.C.M,A. 1976.10-29 _. . A. E .C .M .A. STAN DARD NORME A.E.C.M.A. A.E.C.M.A. NORM - r ,- The equivalent versions in French and German languages can v be supplied by B.N.A.E., 8, rue Moreau-Vauthier 92100 BOULOGNE-BI
2、LLANCOURT - FRANCE. DRAFT prE N203 1 Edition 1 October 1977 ACIER FE-PL3i BARRES SER I E A6 ROSPATI ALE TREMPE ET REVENU ENGLISH VERSION STEEL FE-PL31 HARDENED AND TEMPERED BARS AEROSPACE SERIES STAHL FE-PL31 GEHRTET UND ANGELASSEN STANGEN LU FT-UND RAUM FAH RT-R EIH E The text of this standard, whi
3、ch exists iii three cquivalent versions (English, Franch, Gerinnnl has been drawn up under the responsabiiity of A ECMA (Association Europenne des Constructeurs de Matriel Arospatial) and has been circulated to Official Services. An y reservations expressed by Official Services arid riot resolved in
4、 this issue, have beeii incorporated in the history sheet which has accompaiiied this prEN to CEN. It ispublished on yellow paper as a draft European Standard intended to receive, under the same presentation and according to its own rules, the approval of CEN (European Committee for Standardization)
5、 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-,-,-DRAFT EUROPEAN STANDARD - AEROSPACE SERIES STEEL FE-PL31 Hardened and tempered Bars *I prEN2Ojl Page
6、3 . - El4ment Chemical Composition min. 1 I I c,020 1 1.65 1 - 1 0.40 4 % max. 1 Method of molting _ Bars Form Method of production Limit dimensions EN2069-3 Spheroidised Acceptance Standards Condition and Heat treatmont Supply - t I Hardened and tempered Delivery condition + 83OoC 6 6 B 87OoC/0Q +
7、Temoer 15OOC d 8 S 190C . -.- Reference 1 Hardened and tempered See line 29 Disc a = 10 mn -.- - - -_ - Spheroidlsed - Condition and Heat treatment U93 Test piece Heat treatment Sampling mm Dimensions concerned Thickness of clddina on each face % Direction of sample Temperature Proof , Stress r! 2 W
8、 Strength Elongation Reduction of area + Hardness Shear Strength Bending lr=kxa) I mpact Time L O Rupture Stress Elongation A % L _I_- e) 1Mio= lNlmm2 . - 4 Opt o a 7.1 Medo2 Eot&jed In case of conflict. Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under
9、license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-AECMA PREN2031 77 m 1012321 and Heat treatncnt Ref e rence f-: Cros t ruc ture 0001753 T m 850 f 10 C/0.2. f . Temper 180 & 5.C Carbides shall be fine and non-aligned I I I a 2 I 1 Condit Ion i!ardcnrd and tempered Psignation - lotes 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-,-,-
