Hydraulic System Components, Aircraft and Missiles, General Specification for
|Publication Date:||1 July 1998|
This specification covers the general requirements that are common to most hydraulic components (see 6.2), used in aeronautical hydraulic systems (see 6.1).
Aircraft hydraulic systems in which components covered by this specification are to be used shall be of the following types, as specified:
Type I −65° to +160°F fluid temperature range
Type II −65° to +275°F fluid temperature range