This document describes fluids used in landing gear shock struts with extreme pressure and antiwear additives that have been added for improved lubrication.
This document discusses the relative merits of the physical and chemical properties of hydraulic fluids in relation to the aerospace hydraulic system design, and the related materials compatibility. The discussion in this report applies both to hydrocarbon and phosphate ester based aircraft hydraulic fluids. In some cases, numerical limits are suggested, but, in general, the significance and effect of a property is noted qualitatively.
This specification establishes the requirements for physical and chemical properties and the minimum tests to evaluate suitability of phosphate ester hydraulic fluids for use in aircraft systems where fire resistance is required. Additional tests may be specified by procuring agencies to demonstrate compliance with specific requirements.
This SAE Aerospace Information Report (AIR) presents data on hydraulic fluids which are of interest to detail designers of hydraulic systems and components for aerospace flight vehicles. The data pertain to fluids conforming to specifications MIL-H-5606, MIL-H-8446, MIL-PRF-27601, MIL-PRF-83282, MIL-H-53119, MIL-PRF-87257, Aerospace Standard 1241 Type IV, Classes 1 and 2, and Type V. The relative merits of hydraulic fluid properties in relation to the fluid formulation, aerospace hydraulic system design and the related materials compatibility are discussed in AIR81, Hydraulic Fluid Properties. This document is essentially a metric document with English units available in the data charts for convenience. There is a treatment of conversions between ISO and English units in AIR1657.
Recent Salt-Fog environmental qualification testing in accordance with RTCA/DO-160G, Paragraph 14, Category S identified both discrepancies in the performance specification documents and potential in-service corrosion problems with the charging valve. Revising and updating AS28889 - Valve; Aircraft, Pneumatic, High-Pressure Charging is necessary to resolve these items.
Recommendations for EHA Pump and Motor sizing based on considerations for various actuator performance requirements, including no-load speed, breakout torque, low temperature, stiffness, dynamic response, maximum pressure-velocity capability, and other conditions.
Recommendation Guidelines and Practices for the Design and Validation of EHA Thermal Management Considerations, particularly for Low Temperature Operation.
This document will maintain a listing of all current and new EHA/EBHA aircraft applications, including parameters such as power, force, rate, etc, as is permissible for public offering.
This procedure applies to directional control valves or other valves which in various positions direct or block fluid flow as applied to Off-Road Self-Propelled Work Machines as referenced in SAE J1116.
This SAE Recommended Practice defines a procedure, which will aid in assessing the contaminant sensitivity of hydraulic valves. The approach taken defines a test procedure with flexibility for testing valves in a wide range of contamination levels. The user of this procedure must establish the contamination levels for testing. Three levels are suggested which should cover the range for most valve applications. This procedure does not establish the contaminant sensitivity requirements for any valve. The user of this procedure needs to be aware of the system contamination level that the valve will operate in and select test contamination levels significantly higher than the operating level to assess the suitability of the valve. The test procedure permits a valve to be tested without disassembly and therefore permits protection of proprietary design information. This procedure assesses the contamination sensitivity of valves by contaminant lock.
The SAE Recommended Practice specifies a standardize method and test procedure to measure low pressure differential (< 1bar) brake component brake fluid flow performance. The standard can be utilized for flow measurements across hydraulic brake components such as master cylinders, apply system to chassis controls piping, or other sources of flow restriction in the low pressure side of the hydraulic brake system. It covers materials, manufacturing processes, and general properties required to meet the wide range of service encountered in automotive application. This specification covers only low pressure differential fluid flow and does not include measurement recommended practice for High Pressure differential (> 1 bar) flows.
This Recommended Practice provides a guide for specifying general design, performance, and test requirements for Power Drive Units (PDUs) for aerospace flight controls or other aerospace applications.
This SAE Aerospace Information Report (AIR) contains Lessons Learned from aerospace actuation, control and fluid power systems technologies. The lessons were prepared by engineers from the aerospace industry and government services as part of the work of SAE Committee A-6, Aerospace Actuation, Control and Fluid Power Systems.
This Aerospace Information Report (AIR) provides information on the thrust vectoring flight control systems incorporated on various aircraft development programs and production military aircraft. This report includes V/STOL aircraft thrust vector applications in addition to recommendations for use of thrust vectoring for the improvement of low speed maneuverability in conventional aircraft. Descriptions of each aircraft are provided along with a summary of the thrust vector control system, and, mechanical design methodologies used. Block diagrams, system schematics, and, several system level components are presented.
This SAE Aerospace Recommended Practice (ARP) establishes the requirements for the design, manufacture, and qualification of four hydraulic switching valves used in airborne applications. Two are pressure operated, Type IA and IB and two are solenoid/pilot operated, Type IIA and IIB. They are applicable to four pressure classes 3000, 4000, 5000 and 8000 psi. The equipment as designed is intended to be installed in hydraulic systems designed to AS5440 for military applications or ARP4752 and ARP4925 depending on the type of aircraft for commercial applications. Additional or refined requirements shall be contained in the detail (procurement) specification and these shall take precedence over any potentially conflicting requirements of this ARP or documents referenced by this ARP.
A hydraulic purifier is used in remediation of contaminated fluids by removing air, particulate and water to clean the fluid to within the requirements of the system where the fluid is being used. This standard provides requirements for standard tests to evaluate purifier performance so that users can determine the best purifier for their use.
This information report is intended to provide reference material for the selection and use of fire-resistant fluids in the hydraulic systems of off-road work machinery with separate hydraulic oil sump.
This SAE Aerospace Recommended Practice (ARP) presents a procedure for evaluating cleaning methods with respect to contaminant removal and element degradation particularly for metallic filter elements. A procedure for checking durability of cleaning equipment and a referee cleaning method are also included. It is applicable only to the evaluation of cleaning methods proposed for removal of service dirt and not for built-in dirt, liquid oxygen (LOX) cleaning, etc. Supporting information for use with the ARP is also included.
This SAE Aerospace Recommended Practice (ARP) establishes a method for evaluating the particulate matter extracted from theh working fluid of a hydraulic system or component using a membrane. The amount of particulate matter deposited on the membrane due to filtering a given quantity of fluid is visually compared against a standard membrane in order to provide an indication of the cleanliness level of the fluid. A particular feature of this method is the membrane preparation to achieve an even particulate distribution on the membrane suitable for other applications. Membrane evaluation using standard membranes, described in this document, is an alternative technique to counting with either an optical microscope (ARP598) or an automatic particle counter (ISO 11500). The latter particle counting procedures are considered more rpecise.
This document reviews briefly the subject of woven metal screens. Conditions that can promote damaging corrosion in stainless steel filter screens are discussed and recommendations are listed for minimizing corrosion damage. This is a general document only; for specific applications it is suggested that the reader refer to the technical literature, and selected references listed below.
This Recommended Practice establishes a uniform fluid specification for reference usage in specific documents, such as fluid power component test procedures, where a fluid designation is required.
In May 1979 Martin Marietta Aerospace, Denver Division, completed a survey of missile hydraulic system cleanliness and contamination control procedures and practices as several aerospace companies. The intent of this survey was to gather and assemble the data from companies that manufacture missiles with hydraulic systems, similar to the Titan III System, from a contamination control standpoint. The survey concentrated on 15 subject areas of interest.
This procedure will be generally applicable to three classes of hydraulic components as listed below: Class A - Motors, Pumps, Actuators, Accumulators, Reservoirs, and Non-metering Valves Class B - Servo Valves and Metering Valves Class C - Special short Life Duration Components
This SAE Aerospace Recommended Practice (ARP) provides guidance for the design and installation of a commercial aircraft hydraulic system to meet the applicable requirements, including the applicable airworthiness regulations that affect the hydraulic system design. This ARP also provides information and guidelines on the many factors that arise in the design process to provide cost effectiveness, reliability, maintainability and accepted design and installation practices.
This SAE Aerospace Recommended Practice (ARP) shall provide guidelines for the maintenance, inspection, and support of rotary and linear mechanical actuators on in-service and aging aircraft.
This document provides an overview of the tests, and issues related to testing, that are unique to Electromechanical Actuators (EMAs). The tests, and issues documented, are not necessarily all-inclusive. This document discusses both the tests applicable to EMAs and the test methodologies to accomplish the test objectives. EMAs may be used in a wide variety of applications such as utility, secondary flight controls and primary flight controls, in a wide variety of markets including manned and unmanned civil and military aircraft, small missile fin and thrust vector control applications up to high powered utility and flight controls. EMAs may also have either a rotary or a linear output, be servo controlled or use simple open loop point-to-point or other control topologies. As such this document covers a wide range of potential applications, the application of any given test requirement is determined by the application and the user.
Much of the available long-term storage test data has been reviewed and topically separated to enable the independent discussion of storage effects on fluids, seals, hydraulic components, and hydraulic systems. Comments are made in Section 4 concerning the applicability of the test results and regarding design practices for storability. Conclusions are drawn in Section 5 regarding inactive storage of hydraulic systems for at least a 7 year period.
This SAE Aerospace Recommended Practice (ARP) provides analytical and test methods for determining pressure drop in fluid systems such as hydraulic, fluid, oil, and coolant used in aerospace vehicles. Determining pressure drop by analytical and test results will be discussed.
The purpose of this SAE Aerospace Recommended Practice (ARP) is to provide guide lines for allowable leakage for in-service aircraft hydraulic components at a nominal 100 °F (38 °C) temperature and to outline the procedure for measuring such leakage. The limits to be applied to any specific aircraft should be adjusted before inclusion in a maintenance manual.
This SAE Aerospace Information Report (AIR) provides design data reliability information relative to the long-term storage of gas containers or pressure vessels charged with nitrogen or helium at pressures ranging from 6000 to 12 000 psi. The gas containers are cylindrical, spherical, or toroidal in shape. Internal volumes range up to 1385 in3. Applications for this type cold gas actuation system include tactical missiles, guided projectiles, and smart bombs. A typical system is described.