1、AECMA STANDARD NORME AECMA AECMA NORM Declassification approved 1998-04-30 prEN 2485 Edition 2 April 1998 The equivalent versions in French and German languages can be supplied by B.N.A.E. - Technopolis 54 - 199, rue Jean-Jacques Rousseau 92138 ISSY - LES - MOULINEAUX CEDEX - FRANCE PUBLISHED BY THE
2、 EUROPEAN ASSOCIATION OF AEROSPACE INDUSTRIES (AECMA) Gulledelle 94 - 8-1200 BRUXELLES - Tel. i+32) 2 775 8110 - Fax. (+32) 2 775 811 1 ICs : Supersedes edition 1 September 1981 Descriptors : ENGLISH VERSION ALUMINIUM ALLOY 221 4-F CAST OR EXTRUDED FORGING STOCKS AEROSPACE SERIES ALLIAGE DALUMINIUM
3、2214-F DEMI-PRODUITS COULES OU FILES A FORGER SERIE AEROSPATIALE LUFT-UND RAUMFAHRT ALUMINIUM-LEGIERUNG 2214-F GEGOSSENES ODER STRANGGEPRESSTES SCHMIEDEVORMATERIAL This “Aerospace series Standard has been drawn up under the resp European Associa tion of Aerospace Industries). It is published on yell
4、0 w paper in three equivalen It will be submitted as a draft European Stan for formal vote. of AECMA (The an). Standardization) I Replace page 1 of the previous edition by this page I Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANo
5、t for ResaleNo reproduction or networking permitted without license from IHS-,-,-Mn Others Mg Cr Ni Zn Ti Ti+Zr Al I to I 0,40 1.2 - - - - Remai der 0,20 - - - 0.8 o,io - 0.25 oJi5 0,20 0.05 0.15 See line 29 Forged test sample: 25 mm a 30 mm 100 L a 5 500 Soe !in: 79 Extrusion or forged sample: 425
6、mm a 30 mm 25 6 a c 175 L L A.E.C.M.A. STANDARD Cast or extruded forging stocks I . . ALUMINIUM ALLOY 22 14-F prEN2485 Page 3 Element Chemical Composition min. % I max. 1 2 3 dethod of melting Forging stocks Ex t ru de d 25 mm 6 a 6 175 mm . Forging stocks Cast 100 mm s a c 500 mm -arm iilethod of p
7、roduction -mit dimensions I EN2070-1 I , EN2010-2 and EN2070-3 5.1 Acceptance standards 5.2ndar ds :ondi ti on ind +eat treatment 3elivery F :ondition ind Heat treatment U se Delivery condition rest piece Heat treatment Sampling Dimensions :oncerned Thickness of rladding on each face Direction of sa
8、mple 1 % e ?P 0.2 _ Temperature Proof Stress Strength Elongation Reduction of area 4 z w a 380 i 380 fn - A B 450 1 r, 450 z % Ha rn ess H RC MPa Shear Strength Bending k J I rnpact i_ Time o Elongation Temperature oc h MPa - % MPa* % - Rupture Elongation *) 1MPa = 1Nlmm 1) In preparation. Previous
9、page Notes 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-,-,-prEN2485 Page 4 2 _ Condition and Heat treatment Reference 3 Solution treated 500 f 5CfWQ 40C O 80-C + artificially aged i60 5.Cf12 h t 20 h or 175 * 5*C/ 9 h t 12 h . 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-,-,-
