1、AECMA PREN2806 86 LOI12311 OOOL1209 2 9 A.E.C. M .A. STANDARD NORM E A.E,C. M .A. A.E.C.M.A. NORM prEN2806 Issue P 1 April 1986 DIT PAR LASSOCIATION EUROPEENNE DES CONSTRUCTEURS DE MATRIEL AROSPATIAL 88, boulevard Malesherbes, 75008 PARIS -TL. 45-63-82-85 ENGLISH VERSION Aerospace series Aluminium a
2、lloy 2024-T42 extruded section 1,2 Irectlon of sample - t % MPa - Room temperature 3 285 I + 310 I 5 300 Tempersturo Proof W Stress z Srrength w I- 2 Elongation Rm A Reduction of moa iardness ;hear Strength - i20 (for information) MPa 1 3 end i ng k K - O Tompersture Time Stress Elongation P UI w K
3、o - Ruptura stro1c Elongation ot tupture *) 1 MPa = 1 N/rnmz l), see line 98 Noteo AECMA PREN280b 8b 1012311 0004211 O m prEXu2806 Page 4 1 lestrical I y /,i, .onduct ivity eriphera! coarse grain -4. htergranular corrosion Designation Notes 4 -I_.- 2L ER2004-1 2) T42 : y & 19 : acceptable I_ EFi2070-3 Level A (Table 5) I EN2717 2, 6 rnm only the depth of attack must in principle For 1,2 s a not exceed the second layer of grains from the surface. i) 40 mm where a 5 10 mm. 2) In preparation. .I
