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Revision A, March 1, 2012

Complete Document

Electrical Actuation Systems for Aerospace and Other Applications

Includes all amendments and changes through Stabilization Notice (No longer revised / updated) , March 2012

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Product Details:

  • Revision: Revision A, March 1, 2012
  • Published Date: March 2012
  • Status: Active, Most Current
  • Document Language: English
  • Published By: SAE International (SAE)
  • Page Count: 20
  • ANSI Approved: No
  • DoD Adopted: No

Description / Abstract:

This Aerospace Recommended Practice (ARP) is intended as a guide in the preparation of Procurement Specifications for electrical actuator systems to be sued in aerospace and other applications. Detail requirements, as necessary to completely define a specific actuator, are the responsibility of the procuring agency.


An electrical actuation systems (EAS) is defined as consisting of all electrical, mechanical, optical, or fluidic components necessary to convert a command signal and electrical power from the vehicle into a controlled linear or rotary force while using an electromagnetic prime mover. For purposes of this document, the following definitions of an EAS apply.

ELECTROMECHANICAL ACUATOR: An electromechanically actuator is defined as an EAS that utilizes an electric motor mechanically coupled to the load.

ELECTROHYDRAULIC ACTUATOR: An electro hydraulic actuator is defined as a self-contained EAS that utilizes an electric motor driving a hydraulic pump to operate a hydraulic actuation system.

AIA/NAS Aerospace Standards