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This AIR provides information about the specific requirements for missile hydraulic pumps and their associated power sources.
The intent of this specification is for the procurement of 7781 glass fabric epoxy prepreg product with 250 °F (121 °C) cure for aerospace applications; therefore, no qualification or equivalency threshold values are provided. Users that intend to conduct a new material qualification or equivalency program must refer to the production quality assurance section (see 4.3).
This SAE Aerospace Information Report (AIR) developed by a broad cross section of personnel from the aviation industry and government agencies is offered to provide state-of-the-art information for the use of individuals and organizations designing new or upgraded turboshaft engine test facilities. This document is also applicable to turboprop engines tested with a dynamometer as load absorption device, as they are basically tested as turboshaft engines. For propeller-equipped turbofan testing facilities design considerations, see 2.1.7.
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 energy in a turbine or electric 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 document addresses rotary and fixed wing applications for rotor, turboprop, turbofan, prop fan, and lift fan
This specification covers the performance requirements for a plug and receptacle. The connector inserts may contain multiple termini or multiple termini and electrical contacts. The connectors use removable termini, or removable termini and electrical contacts, and are capable of operating within a temperature range of −65 to +200 °C (see 1.2.1.1). These connectors are supplied under AS9100 reliability assurance program.
This specification covers crimp style, insulated and uninsulated, shield terminating ferrules for RF cable and shielded cable.
This document provides a description of a process for development of fly-by-wire actuation systems. Included are (1) the development of requirements for the servo-actuator hardware and the electronics hardware and software, (2) actuator and servo-electronics interface definitions and, (3) the required communications and interactions between the servo-actuator and the servo-electronics designers.
The primary function of this specification is to cover the general requirements of one-, two-, and three-phase (often referred to as poles) trip-free circuit breakers for use in aircraft electric systems conforming to MIL-STD-704. As a secondary function, this specification may possibly cover the general requirements of one-, two- and three-phase circuit breakers for use in primary vehicles, other than aircraft, when mounted directly to the structure.
This specification covers 600 V heavy duty, portable, power, single and multiconductor, electrical cable for severe flexing service (see detail specifications for voltage limitations). The AS5756 insulation system has been used in aerospace ground power applications using 115/200 V (phase to neutral) at 400 Hz AC. Verification of the suitability of this product for use in other electrical system configurations (600 V, etc.) is the responsibility of the user.
This specification establishes the engineering requirements for producing thick coatings of polytetrafluoroethylene (PTFE) resin on parts and the properties of such coatings.
This Standard is intended to establish preferred abbreviations for use on panels, controls, instruments, displays, placards and markings. The recommendations apply to terms used in the flight deck of transport aircraft. The abbreviations, symbols and codes do not supersede those used in airworthiness regulations or aeronautical charts and documents. Where conflict is possible the operational context must be such as to resolve any ambiguity. If doubt exists, an alternative abbreviation or less truncated abbreviation should be used.
This SAE Standard provides test procedures, requirements, and guidelines for sidemarker lamps for vehicles less than 2032 mm in overall width.
This specification covers environment resistant, heat-shrinkable solder type shield terminations. They may be used on data-bus, RF, and shielded cables in applications. Operating temperature of each product are as indicated on detail specifications.
AS81714 covers Terminal Junction System (TJS) components which are used for interconnection of wiring and incorporation of passive components (see 6.1). These environment resistant components have in common the use of crimp type external pin contacts in accordance with AS39029/1 for Series I or crimp type external socket contacts in accordance with AS39029/22 for Series II. This family of TJS components is designed to operate continuously over a temperature range of -65 to 200 °C, using any combination of temperatures generated by the electrical load and ambient temperature so that the maximum internal hot spot, combined temperature, will not exceed the maximum specified for the class of TJS component, unless otherwise specified (1.2, 3.1). The maximum continuous temperature established by the electronic components in a component module (block) shall be limited to the block maximum continuous temperature. The components making up the system and covered by AS81714 include: a Terminal
This AS covers ULD utilized in finding flight data recorders, cockpit voice recorders or aircraft. Such ULDs are installed adjacent to the recorders in a manner that they are unlikely to become separated during crash conditions.
This SAE Recommended Practice provides laboratory test procedures, requirements, and guidelines for electronic siren systems with a single loudspeaker, and electromechanical sirens for use on authorized emergency vehicles, which call for the right-of-way. Test procedures and performance requirements for individual system components are not included in this version. Results obtained for a siren system with a speaker array that is greater than 0.5 m in any dimension shall apply to the system only when the array is in the same spatial configuration as tested (i.e., the same speaker separation and orientation).
This procurement specification covers bolts made from a corrosion-resistant, work-strengthened, cobalt-chromium-nickel alloy of the type identified under the Unified Numbering System as UNS R30159.
This specification covers a titanium alloy in the form of seamless tubing.
This document defines a set of standard application layer interfaces called JAUS Mission Spooling Services. JAUS Services provide the means for software entities in an unmanned system or system of unmanned systems to communicate and coordinate their activities. The Mission Spooling Services represent the physical platform-independent capabilities commonly found across all domains and types of unmanned systems. At present, one service is defined in this document (more services are planned for future versions of this document): Mission Spooler: Stores, manages, and executes lists of tasks The Mission Spooler service is described by a JAUS Service Definition (JSD) which specifies the message set and message protocol required for compliance. The JSD is fully compliant with the JAUS Service Interface Definition Language (JSIDL).
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