Results
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. They are intended to aid the reader in the direction of this ARP and
This test method outlines the recommended procedure for performing static axial limit and ultimate load tests on rolling element bearings used in airframe applications. Bearings covered by this document shall be antifriction ball bearings and spherical roller bearings in either annular or rod end configurations.
This specification covers a titanium alloy in the form of bars and forgings up through 10.000 inches (254.00. mm), inclusive, in diameter or least distance between parallel sides with a maximum cross-sectional area of 79.0 in2 (506.45 cm2) and forging stock of any size (see 8.7).
Wire and cable products progress through a series of handling or operational steps from the time they leave the manufacturer, and until a finished harness or assembly is ready for installation on a vehicle. Throughout these many steps, environmental or processing conditions may be present which can generate damage detrimental to the wire or cable and/or its intended application.
This standard specifies the characteristics of the MJ profile metric series of screw threads, altered from ISO 68 M Profile, to include a mandatory controlled radius of 0.18042P to 0.15011P at the root of the external thread and with the minor diameter of both external and internal threads increased to provide a basic thread height of 0.5625H in order to accommodate the external thread maximum root radius. The following detailed requirements are included: a MJ basic profile and design profiles b Standard series of diameter-pitch combinations for nominal thread diameters from 1.6 to 200 mm c Standard thread classes and form tolerances d Formulae for thread dimensions and tolerances e Method of designating MJ threads f Inspection requirement g Tables for selected diameter-pitch combinations for aerospace screws, bolts, nuts, shaft and bearing retaining screw threads, and fluid fittings thread sizes h Tables for MJ screw threads limiting dimensions and tolerances i Symbols for MJ thread
This document describes: a The preparatory steps to test experimental Type II, III, and IV fluids according to AMS1428 b The recommendations for the preparation of samples for endurance time testing according to ARP5485 c A short description of wind tunnel testing d A short description of the recommended field spray test e The protocol to generate draft holdover time guidelines from endurance time data obtained from ARP5485 f The protocol for inclusion of Type II, III, and IV fluids on the FAA and Transport Canada lists of fluids and the protocol for updating the lists of fluids g The role of the SAE G-12 Aircraft Deicing Fluids Committee h The role of the SAE G-12 Holdover Time Committee i The process for the publication of Type II, III, and IV holdover time guidelines This document does not describe laboratory testing procedures. This document does not include the qualification requirements for AMS1424 Type I fluids (these are provided in ARP6207).
This SAE Aerospace Recommended Practice (ARP) defines the test set-up requirements, general analysis procedures, and test report documentation for impact tests where photometric analysis of the high speed film or digital video will be required to obtain target paths (typically the Anthropomorphic Test Dummy (ATD) head path and knee path). Such tests support the requirements of AS8049 - Performance Standard for Seats in Civil Rotorcraft, Transport Aircraft and General Aviation Aircraft. These setup and analysis procedures are applicable to conventional, geometry based, two-dimensional analysis. If a more sophisticated technique that allows cameras to be installed at oblique angles for two or three-dimensional analysis is used, then the specific procedures required by that technique supersede any conflicting procedures contained herein. Some of the requirements that could be superseded include camera placement, optical data channel evaluation, camera to subject measurements, and scaling
This document describes a process that may be used to perform the ongoing safety assessment for (1) GAR aircraft and components (hereafter, “aircraft”), and (2) commercial operators of GAR aircraft. The process described herein is intended to support an overall safety management program. It is associated with showing compliance with regulations and also establishing and meeting internal company safety standards. The process described herein identifies a systematic means, but not the only means, to assess continuing airworthiness. Ongoing safety management is an activity dedicated to assuring that risk is identified and properly eliminated or controlled. The safety management process includes both safety assessment and economic decision-making. While economic decision-making (factors related to scheduling, parts, and cost) is an integral part of the safety management process, this document addresses only the ongoing safety assessment process. This ongoing safety assessment process
This specification covers a corrosion resistant steel in the form of wire type identified under the Unified Numbering System as UNS S30500.
The objective of this ARP is to provide a set of user-centered design guidelines for the implementation of data driven electronic aeronautical charts, which dynamically create charts from a database of individual elements. The data driven chart is intended to provide information required to navigate, but it is not intended to supplant the aircraft’s primary navigation display. These guidelines seek to provide a balance between standardization of equipment with similar intended functions and individual manufacturer innovation. This ARP provides guidelines for the display of an electronic chart that can replace existing paper. This document addresses what information is required, when it is required, and how it should be displayed and controlled. This document does not include all the detailed specifications required to generate an electronic aeronautical chart. This document primarily addresses the human factors aspects of electronic chart display, and does not address the software
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 Standard covers dimensional, material, and general specifications and methods of test for two types of general purpose conical spring washers, designated type L and type H, for use as loose washers over screws and bolts, and also for use as pre-assembled washers in screw and washer assemblies.
This recommended practice defines a procedure for the construction and testing of a 180 deg peel specimen for the purpose of determining the bondability of glass to elastomeric material in automotive modular glass. This test method suggests that elastomeric material of less than 172 mpa modulus be used as the encapsulating material. The present practice of encapsulating automotive glass is described as molded-in-place elastomeric material onto the outer edge of the glass using thermoplastic or thermosetting material that quickly sets in the mold. The glass is removed from the mold with the cured elastomeric material bonded to the perimeter of the glass. This encapsulated glass module can now be bonded with a sealant adhesive into the body opening of a vehicle.
This SAE Aerospace Information Report presents a glossary of terms commonly used in the ground delivery of fuel to an aircraft and pertinent terms relating to the aircraft being refueled.
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