1、. Approved by COMITE DE NORMALISATION of A.E.C.M.A. 1982-11-10 A.E E.M.A. STANDARD NORME A.E.C.M.A. A.E.C.M.A. NORM I The equivalent versions in French and -German languages can be supplied by B.N.A.E., 8, rue Moreau-Vauthier . 92100 BOULOGNE-BILLANCOURT - FRANCE, pr EN238 1 Edition 1 September 1983
2、 ENGLISH VERSION Aluminium alloy 7009-T73652 Hand forgings a 150 mm Aerospace series Alliage daluminium 7009-T73652 Pices forges a 150 mm Srie arospatiale Luft- und Raumfahrt Aluminiumlegierung 7009-T3652 Freiformschmiedestcke a 150 mm This industrial standard for the aerospace sector has been drawn
3、 up under the responsibility of AECMA (Association Europenne des Constructeurs de Matriel Arospatial). It is published on yellow paper in three equivalent versions (English, French, German). It will be submitted to CEN (European Committee for Standardization) as a draft European Standard. Copyright
4、Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-AECWA- PREN234 3ppings I Dimensions :oncerned 6 75 75 C a Q i25 125 a S 150 rhickness of :laddino on each face I
5、% Direction of sample L LT ST . L LT ST L LT ST Room tenperature Temperature Proof Stress Strength Elongation Reduction of area Hardness -I - I - 115 (for infornationf Shear Strength C - k K - B Bending Impact Itemperature OC Ifime h APa* % - - a Stress o Elongation Rupture Stress w w re - - - *) IM
6、Pa = 1N/mm2 i), 2) see line 98. *= - APa* A _ % - Elongation at rupture Notes 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-,-,-AECMA PREN2381 83 - W L01
7、23LL 00030b7 3 W a prEN2381 Page 4 Electrical conductivity Stress corrosion 1 is/n - ypical usa 2 3 4 2 22 21,5 d y 22 21,5 EN2004-1 1) Acceptable The forgings are suspect and a stress corrosion test is required. Not acceptable The forgings shall be re-aged at 170 ageing at 170OC shall be t S 8 h, o
8、r completely re-heat treated following line 6. The forgings shall then meet the electrical conductivity requi- rements. 3OC, total ageing and re- EN2004-4 1) .i) In preparation. 2) Stress relieving by cold compressed is performed imGdiately after quenching. O 9 a 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-,-,-
