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Reservoirs complying with this recommended practice are designed for use in commercial and military aircraft and other aerospace applications. These devices store hydraulic fluid under pressure and are normally installed on the low pressure side of the hydraulic pump. The reservoirs provide for fluid volume changes due to temperature variation, unbalanced actuator operation and leakage. These devices are rated for EHA hydraulic system operating pressures up to 5,000 PSIG (34,474 KPa) and temperatures between -65°F and 275°F (-54°C and 135°C).

This document provides an overview of the tests and issues related to testing that are unique to Electrohydrostatic Actuators (EHAs). An EHA incorporates a linear or rotary hydraulic actuator and a variable speed, reversible electric servomotor driving a fixed displacement hydraulic pump for actuator control, and associated power drive electronics. The tests and issues documented are not necessarily all-inclusive. This document discusses both, the tests applicable to EHAs and the test methodologies to accomplish the test objectives. This document also lists tests that are not unique to EHAs, but are still applicable to EHAs. In these instances a discussion of such tests is not contained in this document, and as applicable, the reader may reference ARP1281 (Actuators: Aircraft Flight Controls, Power Operated, Hydraulic, General Specification For), which addresses test issues applicable to electrohydraulic flight control servoactuators.

This Aerospace Recommended Practice provides general requirements for Electrohydrostatic Module (EHM) that is used in Electrohydrostatic Actuator (EHA) for aerospace applications. This document includes design, performance and test (production and qualification) requirements.

This SAE Aerospace Information Report (AIR) has been compiled to provide information on: a. The particularities of EHAs and their derivatives that make their implementation useful to meet some specific system requirements, solve some system architecture issues, or provide system optimization within the flight control actuation and hydraulic generation/distribution perimeter. b. System architecture drivers and basic schematics, actuator principle schematics, and basic characteristics, for various civil and military aircraft.

This SAE Aerospace Recommended Practice (ARP) provides guidelines for the creation of specifications for the Motor Control Electronics (MCE) that are used for operating electrically powered actuators including: Electromechanical Actuators (EMAs) Electrohydrostatic Actuators (EHAs) Electric Back-Up Hydraulic Actuators (EBHAs)

This recommended practice provides a method of characterizing Electrohydrostatic Actuator (EHA)/Electrohydrostatic Module (EHM) duty cycles for the following purposes: a To enable the comparison of the severity of different EHA/EHM applications. This allows the use of previously qualified designs without the need for repeat testing. b To define parameters for endurance-test design of EHAs; e.g., a way of executing a life-equivalent test in a shorter duration by increasing the speed of cycles and/or the level of applied loads.

This Aerospace Recommended Practice (ARP) provides recommended test requirements for Electrohydrostatic Actuators. NOTE: This document does not address tests and issues of a higher system level, such as the primary flight control surface level where multiple EHAs and or EHSAs may be integrated.