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SAE AS5440
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SAE AS5440 Revision A, January 1, 2011
(R) Hydraulic Systems, Military Aircraft, Design and Installation,
Requirements For
Description / Abstract:
The design and installation requirements covered by this
specification are intended for use in aircraft hydraulic systems,
such as the utility system, the flight control system, various
subsystems, and with component installation procedures for
temperatures from –65 °F (-54 °C) to 275 °F (+135 °C). Type III
systems, -65 °F (-54 °C) to 450 °F (+232 °C), are covered by
MIL-H-8891.
SAE AS5440 Revision A, January 1, 2011
(R) Hydraulic Systems, Military Aircraft, Design and Installation,
Requirements For