This specification defines basic physical, chemical, and performance limits for 5 cSt grades of gas turbine engine lubricating oils used in aero and aero-derived marine and industrial applications, along with standard test methods and requirements for laboratories performing them. It also defines the quality control requirements to assure batch conformance and materials traceability, and the procedures to manage and communicate changes in oil formulation and brand. This specification invokes the Performance Review Institute (PRI) product qualification process. Requests for submittal information may be made to the PRI at the address in Appendix D Section D.2, referencing this specification. Products qualified to this specification are listed on a Qualified Products List (QPL) managed by the PRI. Additional tests and evaluations may be required by individual equipment builders before an oil is approved for use in their equipment.
This document establishes the minimum requirements for ground based aircraft deicing/anti-icing Methods and procedures to ensure the safe operation of aircraft during icing conditions. This document does not specify requirements for particular airplane models. NOTE: Particular airline or aircraft manufacturers' published manuals, procedures, or methods supplement the information contained in this document.
This SAE Aerospace Recommended Practice (ARP) identifies the minimum requirements for the testing of insulated electrical wiring for on-aircraft, aeronautical and aerospace applications. The testing requirements defined herein, ensure that a wire fault can be found safely when using a high potential voltage tester (hipot). This test is intended to aid in finding a breach in the wire insulation, and not for the identification of the resistance of the insulation. The test method defined herein is limited to equipment which ia able to control and limit the DC output to 1500 VDC maximum. This type of wire dielectric tester is typically designed to trip on current leakage and not necessarily on arc detection. This test method is solely designed to identify gross/large wire insulation damage or degradation. For additional related information on this topic and related test methods, refer to the documents cited in Section 2.
The purpose of this SAE Aerospace Information Report (AIR) is to provide management, designers, and operators with information to assist them to decide what type of power train monitoring they desire. This document is to provide assistance in optimizing system complexity, performance and cost effectiveness. This document covers all power train elements from the point at which aircraft propulsion energy in a turbine or reciprocating engine is converted via a gear train to mechanical energy for propulsion purposes. The document covers aircraft engine driven transmission and gearbox components, their interfaces, drivetrain shafting, drive shaft hanger bearings, and associated rotating accessories, propellers, and rotor systems as shown in Figure 1. For guidance on monitoring additional engine components not addressed, herein (e.g., main shaft bearings and compressor/turbine rotors), refer to ARP1839.
This SAE Aerospace Recommended Practice (ARP) covers the general requirements and test procedures recommended for use with white incandescent integrally lighted instruments. Its use should provide uniformity of illumination from instrument to instrument and legibility under daylight operation. An appendix is provided to familiarize the designer with some of the techniques used to obtain uniformity of color and illumination in various types of instruments.
This SAE Aerospace Recommended Practice (ARP) provides the technical terms and nomenclature, together with their definitions and abbreviations/acronyms that are used in aerospace fluid power, actuation and control systems. NOTE: ARP490 and ARP4493 are sources for definitions specifically for electrohydraulic servovalves.
This SAE Aerospace Information Report (AIR) describes the performance of plating’s and coatings for landing gear that potentially provide environmental compliance benefits versus the current baseline processes. The hazardous systems addressed in this version of the document include cadmium plating, chromated primers, and high VOC (volatile organic compounds) topcoats. The AIR applies to landing gear structures and mechanisms for all types of civil and military aircraft. The potential replacements apply to both Original Equipment Manufacturer (OEM) hardware and overhaul of in-service landing gears.
This recommended practice covers the fixed structure, or independent energy absorbing system affixed to the airframe to afford protection to the control surfaces, engine and other portions during ground handling, take-off and landing.