Navigate / EASA

AMC1 to ASTM F2245-12d Sub-chapter 6.2 Materials

ED Decision 2013/015/R

Parts of Structure Critical to Safety

(a)     The use of the following stress levels may be taken as sufficient evidence — in conjunction with good design practices to eliminate stress concentrations — that structural items have adequate safe lives:

Material used

Allowable normal stress level of maximum limit load

—          Glass rovings in epoxy resin

—          Carbon fibre rovings in epoxy resin

—          Wood

—          Aluminium Alloy

—          Steel Alloy

25 daN/mm2

40 daN/mm2

According to ANC-18*

Half of rupture tensile strength

Half of rupture tensile strength

 

(b)     Higher stress levels need further fatigue investigation using one or a combination of the following methods:

(1)     By a fatigue test, based on a realistic operating spectrum.

(2)     By a fatigue calculation using strength values which have been proved to be sufficient by fatigue tests of specimens or components.

* ANC-18 is the ANC Bulletin ‘Design of wood aircraft structures’; issued June 1944 by the Army-Navy-Civil Committee on Aircraft Design Criteria (USA).

 

Material Strength Properties and Design Values (Interpretative material)

Material specifications should be those contained in documents accepted either specifically by the Agency or by having been prepared by an organisation or person that the Agency accepts has the necessary capabilities. In defining design properties these material specification values should be modified and/or extended as necessary by the constructor to take account of manufacturing practices (for example method of construction, forming, machining and subsequent heat treatment).

[Amdt LSA/1]