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MIL-S-85419 (AS)
All reinforced plastic construction shall be in
conformance with the contractor's process specifications,
prepared in accordance with MIL-P-9400 and accepted by the
approving activity.
3.5.1.3 Metals.  All metals shall be compatible with the
intended temperature, functional, service and storage conditions
to which the starter/APU will be exposed,  Metals which are not
protected from corrosion by lubricating oil shall be of the
corrosion-resisting type, or shall be suitably treated to resist
corrosion in accordance with 3.5.1.4.
3.5.1.3.1 Steels (except corrosion-resistant).
Aircraft quality, vacuum-melted steel shall be used for
parts which are heat treated to an ultimate tensile strength
220,000 psi and above.  Such applications shall be subject to
specific acceptance by the approving activity.
b.  The ultimate tensile strength range in production parts
shall not exceed the following limits:
Minimum Ultimate
Tensile Strength
Permissible
Variation, P.S.I.
P.S.I.
-0 + 20,000
220,000
-0 + 20,000
260,000
-0 + 20,000
270,000
-0 + 20,000
280,000
c.  Preference shall be given, in selection of carbon and low
alloy steels, to compositions having the least hardenability
which will insure thorough-hardening of the part concerned.
d.  Compositions shall be selected such that heat treatment
to the required strength and service temperatures shall preclude
temper embrittlement.
Steels shall be selected having ductile-brittle fracture
transition temperatures as determined by impact test below the
minimum operating temperature.
f.  Steels whose mechanical properties are developed by cold
deformation shall be so selected that the recovery temperature
will be at least 50F (28C) above the expected operating
temperature range.
g.  Critical parts shall be designed and processed so as to
result in no decarburization of highly stressed areas.  Designs
7

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