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The purpose of this document is to establish the requirements for Real-Time Communication Protocols (RTCP). Systems for real-time applications are characterized by the presence of hard deadlines where failure to meet a deadline must be considered a system fault. These requirements have been driven predominantly, but not exclusively, by aerospace type military platforms and commercial aircraft, but are generally applicable to any distributed, real-time, control systems. These requirements are primarily targeted for the Transport and Network Layers of peer to peer protocols, as referenced in the Open System Interconnect Reference Model (2.2.1 and 2.2.2), developed by the International Standards Organization (ISO). These requirements are intended to complement SAE AS4074 (2.1.1) and AS4075 (2.1.2), and future SAE communications standards. Although information transfer objectives herein concentrate primarily on digital data flow attributes, efforts have been made such as not to preclude
This Aerospace Information Report (AIR) has been prepared by the Systems Applications and Requirements Subcommittee of SAE Committee AS-2. It is intended to provide guidance primarily, but not exclusively, for specifiers and designers of data communication systems for real time military avionics applications within a platform. The subject of high speed data transmission is addressed from two standpoints: (1) the influence of developments in technology on avionics architectures as a whole and (2) the way in which specific problems, such as video, voice, closed loop control, and security may be handled. While the material has been prepared against a background of experience within SAE AS-2 relating to the development of a family of high speed interconnect standards, reference to specific standards and interconnect systems is minimized. It should be noted, however, that many of the concepts described require interconnect systems with advanced operational and performance characteristics
The emphasis in this standard is the development of data word and message formats for AS15531 or MIL-STD-1553 data bus applications. This standard is intended as a guide for the designer to identify standard data words and messages for use in avionics systems and subsystems. These standard words and messages, as well as the documentation format for interface control document (ICD) sheets, provide the basis for defining 15531/1553 systems. Also provided in this standard is the method for developing additional data word formats and messages that may be required by a particular system but are not covered by the formats provided herein. It is essential that any new word formats or message formats that are developed for a 15531/1553 application follow the fundamental guidelines established in this standard in order to ease future standardization of these words and messages. The standard word formats presented represent a composite result of studies conducted by the U.S. Army, Navy, and Air
This SAE Aerospace Standard (AS) establishes the requirements for externally swaged aluminum tube fittings on aluminum tubing with flareless separable fitting ends for use in hydraulic supply and return aerospace fluid systems including pneumatic, coolants, and fire extinguishers up to a maximum operating pressure of 1500 psig (10340 kPa) and a maximum operating temperature range of -65 to +225 °F (-54 to +107 °C). This specification covers a common aluminum fitting that may be used for a range of operating pressures up to 1500 psi with different tubing materials and tubing wall thicknesses, and is assembled with the same tooling in accordance with AS6124. Table 12 shows applicable aerospace fitting part number standard and tubing materials and operating pressures.
This SAE Aerospace Recommended Practice (ARP) defines recommended planning and substantiation procedures and associated reviewing and approval processes to confirm that proposed changes do not compromise the demonstrated safety of the originally certified aircraft, and performance and aircraft compatibility are appropriately addressed in aircraft documentation. Successful demonstration also requires that failure modes be identified and mitigation provided for each. These procedures apply to modifications made by the original component or assembly supplier as well as approval of an alternate supplier.
This SAE Aerospace Standard (AS) establishes the basic requirements for the design, construction and testing of air mode 2.44 m × 2.44 m (8 ft × 8 ft) cross-section containers. These containers are to be used exclusively in conjunction with the air mode in freighter versions of wide-body commercial transport aircraft. Air mode containers will normally be on aircraft roller conveying systems and/or on similarly equipped ancillary ground handling devices. Similar requirements for air/surface (intermodal) containers are provided in AS832.
The tow vehicle should be designed for towbarless movement of aircraft on the ground. The design will ensure that the unit will safely secure the aircraft nose landing gear within the coupling system for any operational mode.
The methodology for maximum package size loading is based on a mathematical method allowing the calculation of maximum package size tables. This method does not in principal differentiate between bulk loading and cargo system loading. However, some restrictions have to be considered: Some cargo systems generate pre-determined pallet trajectories. Envelope curves depending on the pallet size and the possible trajectories have to be determined first. Door geometric limitations (with or without cargo loading system) Turning limitations due to weight, load geometry and conveyance capability Securing requirements This document is not intended for airline operational use. It should be used by engineers performing calculations or developing computer programs to produce Maximum Package Size tables specified in AS1825.
This document contains recommended practices for the effective control of non-deliverable software. It addresses practices for control during the development, production, release maintenance, and retirement of non-deliverable software, as well as for software procured from outside manufacturers and incorporated in the production, evaluation, test, acceptance or calibration of processes. For the purposes of this document, the terms software and non-deliverable software are considered synonymous.
This SAE Aerospace Recommended Practice (ARP) addresses the characteristics required for the definition, development, and acquisition of a satisfactory airframe mounted accessory gearbox (AMAG).
This supplement forms a part of the Aerospace Standard AS1946, Hose Assembly, Polytetrafluoroethylene, Metallic Reinforced, up to 1500 psi and 450 ° F, Hydraulic and Pneumatic, and shall be used to identify hose assembly standards citing this procurement specification.
This supplement forms a part of the Aerospace Standard AS4468, Hose Assembly, 125 psi, Lined Silicone, Potable Water, Procurement Specification. It shall be used to identify hose assembly standards that are governed by this procurement specification.
In lieu of TSO-C135, this SAE Aerospace Standard (AS) prescribes the minimum performance standards for wheels, brakes, and wheel and brake assemblies using electric power actuation for transport category (14 CFR Part 25) airplanes. Testing is limited to that necessary to establish minimum performance related to strength, robustness, stopping capability, and energy absorption to ensure measurable, repeatable industry accepted standards for these aspects of wheel and brake performance. The test parameters associated with electric braking actuation are defined around the state of the technology at this time, typically comprised of an Electro-Mechanical Actuator (EMA) controlled by a control system delivering electric power and effecting motor control. This document does not address qualification of the EMAs or brake assembly to the landing gear environmental threats including, but not limited to, EMI/HIRF, failure mode operation or other application specific performance, or the
This SAE Aerospace Standard (AS) defines the requirements for a polytetrafluoroethylene (PTFE) lined, para-aramid fiber reinforced, hose assembly suitable for use up to 4000 psi, and up to 275 °F, aircraft and missile hydraulic and pneumatic systems.
This SAE Aerospace Standard (AS) specifies the general requirements for data recording procedures, packaging, and storing of elastomeric seals and seal assemblies which include an elastomeric element prior to the seal being assembled into hardware components. NOTE: The requirement for packaging is an integral part of the controlled storage procedure and provides a means of positive product identity from the time of manufacture to the time of assembly into a component.
This standard defines a system for the qualification of standard products for aviation, space, and defense applications. It defines the principles that shall be adhered to when carrying out product qualification; applied in conjunction with the rules and procedures of the CA. The system enables the CA to confirm compliance is achieved and maintained, in accordance with the requirements of its product definition and associated controlling technical specifications by an Original Component Manufacturer (OCM) of standard products. This standard requires an OCM that has been granted product qualification approval to ensure applicable approvals are maintained and renewed in accordance with the CA’s quality system for that qualified product. OCMs and OCM designated Value Added Distributors (VADs) requesting product qualification to this standard, shall as a prerequisite, maintain 9100 standard quality management system certification approval. This certification shall be visible in the Online
This document is intended to cover the design of plastic lighted panels, mounting plates, and their installation.
This Aerospace Recommended Practice (ARP) is intended as a guide in the preparation of Procurement Specifications for electrical actuator systems to be used in aerospace and other applications. Detail requirements, as necessary to completely define a specific actuator, are the responsibility of the procuring agency.
This standard defines the requirements and characteristics of electrical power for spacecraft. This standard also defines analysis, verification, and testing methodologies to be used to ensure that the loads operate when connected to the specified power quality and performance as defined by this standard.
This SAE Aerospace Recommended Practice (ARP) is broken into various categories for convenience and ease of identification. It is the purpose of this document to provide certain criteria for the design and selection of stairways, for the boarding of passengers onto an aircraft. The criteria presented are limited to those factors which affect the safety of the passengers and are coordinated, where applicable, with the practices of the architectural profession, with respect to the design of stairways. The recommended practices are applicable to both mobile variable-elevation type stairways and to fixed-elevation stairways of the type built into an aircraft fuselage.
This SAE Aerospace Recommended Practice (ARP) specifies guidelines for calculating and performing shoring (load spreading) required on board civil transport aircraft whenever a piece of cargo to be carried exceeds the aircraft's maximum allowable limits in area load, running load, or both. It provides both the engineering methods needed to properly design a shoring arrangement, and the main practical dos and donts known from experience to ensure its effectiveness in protecting the aircraft's structure against overload.
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