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This SAE Aerospace Recommended Practice (ARP) recommends a methodology to be used for the design, analysis and test evaluation of modern helicopter gas turbine propulsion system stability and transient response characteristics. This methodology utilizes the computational power of modern digital computers to more thoroughly analyze, simulate and bench-test the helicopter engine/rotor system speed control loop over the flight envelope. This up-front work results in significantly less effort expended during flight test and delivers a more effective system into service. The methodology presented herein is recommended for modern digital electronic propulsion control systems and also for traditional analog and hydromechanical systems.
This SAE Standard establishes a test method and a definition for disclosing the performance of suction/blower fans when applied to self-propelled sweepers that solely use a pneumatic conveyance means for the collection and transfer of “sweepings” into a collection hopper.
This SAE Aerospace Standard (AS) establishes the requirements for a grooved clamp coupling and flanges suitable for joining intermediate pressure and temperature ducting in aircraft pneumatic systems. The rigid coupling joint assembly, hereafter referred to as “the joint”, shall operate within the temperature range of -65 °F external ambient to +800 °F internal fluid.
This SAE Aerospace Standard (AS) establishes the requirements for 24° cone flareless fluid connection fittings and nuts and bite type flareless sleeves (see Section 6) for use in aircraft fluid systems at an operating pressure of 5000 psi for the fittings and nuts and 3000 psi for the bite type sleeves.
This specification classifies fusion welds according to structural integrity requirements and establishes inspection methods and acceptance standards for welded tubular assemblies used in aerospace applications.
The purpose of this document is to provide performance requirements for hydrogen dispensing systems used for fueling 35 MPa heavy duty hydrogen transit buses and vehicles (other pressures are optional). This document establishes the boundary conditions for safe heavy duty hydrogen surface vehicle fueling, such as safety limits and performance requirements for gaseous hydrogen fuel dispensers used to fuel hydrogen transit buses. For fueling light-duty vehicles SAE J2601 should be used. SAE J2601-2 is a performance based protocol document that also provides guidance to fueling system builders, manufacturers of gaseous hydrogen powered heavy duty transit buses, and operators of the hydrogen powered vehicle fleet(s). This fueling protocol is suitable for heavy duty vehicles with a combined vehicle CHSS capacity larger than 10 kilograms aiming to support all practical capacities of transit buses. It is non-prescriptive in how to achieve a full fill or 100% state of charge (SOC) in the
This specification covers a premium aircraft-quality, low-alloy steel in the form of bars, forgings, and forging stock.
This SAE Aerospace Recommended Practice (ARP) details the recommended process for correcting measured non-volatile particulate matter (nvPM) mass and number data for particle losses in the sampling and measurement system specified in ARP6320B. This technique is only recommended for conditions where both nvPM mass and number concentration measurements are in the valid measurement ranges of the instruments that are discussed in the tool limitations section. This ARP also supplies an Excel software tool with documentation to automate the process. The body of this ARP details the recommended calculation method, uncertainties, and limitations of the system loss correction factors. It explains, in detail, the required inputs and outputs from the supplied Excel software tool (developed on Windows 7, Excel 2016). Also included are: The Excel correction tools (refer to Attachments I and V). Installation instructions for a Windows-based computer (refer to Attachment II). A user technical manual
This document establishes dimensional, structural, and environmental requirements for Type II/2 interline pallet nets. Type II/2 covers NAS3610/AS36100 code sizes.
This SAE Standard was developed to provide a method for indicating the direction of engine rotation and numbering of engine cylinders. The document is intended for use in designing new engines to eliminate the differences which presently exist in industry.
Recent field experience has indicated significant problems with some types of wire and cables as routed on aircraft landing gear. This SAE Aerospace Information Report (AIR) is intended to identify environmental concerns the designer should consider, materials that appear to be most suitable for use in these areas, routing, clamping, and other protection techniques that are appropriate in these applications. In recent years aircraft certification regulatory agencies introduced new regulations regarding Electrical Wiring Interconnection Systems (EWIS) to further enhance safety of the associated systems and aircraft overall.
A recommended pilot-system integration (i.e., crew interface and system integration) approach for concept development is described in Figure 1. The approach emphasizes the fundamental need for a top-down design methodology with particular focus on clear operational performance requirements and functional integration. While this document is primarily aimed at aircraft systems design and integration, the methodology is applicable to a wide range of design and integration situations. It is derived from well established human factors engineering design principles.
This SAE Aerospace Standard (AS) provides standardized gland (groove) design criteria and dimensions for elastomeric seal glands for static applications. The glands have been specifically designed for applications using SAE AS568 size O-rings at pressures exceeding 1500 psi (10.3 MPa) utilizing one or two anti-extrusion (backup) rings and applications at pressures under 1500 psi (10.3 MPa) without backup rings. The glands have been sized to provide increased squeeze as compared to AS4716 for more effective sealing at low temperatures and low seal swell conditions. These glands are not recommended for dynamic use. Primary usage is for static external sealing. The rod dimensions are the same as AS4716. The cylinder bore dimensions are the same as AS4716 except for sizes -001 thru -011 and -104 thru -113.
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