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ARINC 858 Part 2 provides aviation ground system gateway considerations necessary to transition to the Internet Protocol Suite (IPS). ARINC 858 Part 2 describes the principles of operation for an IPS gateway that enables ACARS application messages to be exchanged between an IPS aircraft and a ground ACARS host. ARINC 858 Part 2 also describes the principles of operation for an IPS gateway that enables OSI-based application messages to be exchanged between an IPS host and an OSI end system. This product was developed in coordination with ICAO WG-I, RTCA SC-223, and EUROCAE WG-108
Airlines Electronic Engineering Committee
This ARP describes recommended sampling conditions, instrumentation, and procedures for the measurement of nonvolatile particle number and mass concentrations from the exhaust of aircraft gas turbine engines. Procedures are included to estimate sampling system loss performance. This ARP is not intended for in-flight testing, nor does it apply to engines operating in the afterburning mode. This ARP is intended as a guide toward standard practice and is subject to change to keep pace with experience and technical advances
E-31P Particulate Matter Committee
This document extends SAE J3068 and SAE J3068/1 to include multiple ways to control charging and discharging to an EPS, managed charging, and other related capabilities. Capabilities are designed to support both site electrical limits and power grid management
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This guide provides detailed information, guidance, and methods related to the Federal Aviation Administration (FAA) Advisory Circular (AC) 20-158 and European Aviation Safety Agency (EASA) draft Advisory Material Joint (AMJ), both titled "The Certification of Aircraft Electrical and Electronic Systems for Operation in the High-Intensity Radiated Fields (HIRF) Environment". The AC provides acceptable means, but not the only means, of compliance with Title 14, Code of Federal Regulations (14 CFR) 23.1308, 25.1317, 27.1317, and 29.1317, High-Intensity Radiated Fields (HIRF) protection for Aircraft Electrical and Electronic Systems, and applicable FAA HIRF Special Conditions to prevent hazards to aircraft electrical and electronic systems due to HIRF produced by external transmitters. It is also intended for this guide to provide the same information, guidance, and methods to the European Aviation Safety Agency (EASA) interim HIRF policies certification requirements. This guide is neither
AE-4 Electromagnetic Compatibility (EMC) Committee
Recommended Failure Modes and Effects Analysis (FMEA) Practices For Non-Automobile Applications describes the basic procedures for performing a Failure Modes and Effects Analysis (FMEA). It encompasses functional, interface, and detailed FMEA, as well as certain pre-analysis activities (FMEA planning and functional requirements analysis), post-analysis activities (failure latency analysis, FMEA verification, and documentation), and applications to hardware, software, and process design. It is intended for use by organizations whose product development processes use FMEA as a tool for assessing the safety and reliability of system elements, or as part of their product improvement processes. A separate, Surface Vehicle Recommended Practice, J1739, is intended for use in automobile applications
G-41 Reliability
This document provides guidance for a means of showing compliance with regulations for protection against lightning direct effects for aircraft of conventional design, as well as for those involving advanced composite structures or other new technologies. This guidance also applies to those aspects of aircraft systems and components not addressed in the regulations covering the protection of electrical/electronic systems (for example, FAR/JAR xx.1316) or fuel systems (for example, xx.954). The guidance provided in this document applies to initial designs as well as modifications
AE-2 Lightning Committee
This SAE Aerospace Recommended Practice (ARP) provides information and guidance for the control of hazardous laser energy in the navigable airspace. This ARP does not address techniqies that pilots can apply to mitigate laser illuminations during a critical phase of flight. Such mitigation strategies are described in ARP6378
G-10T Laser Safety Hazards Committee
This Aerospace Recommended Practice (ARP) provides general requirements for a generic, integrated rudder and brake pedal unit, incorporating a passive force-feel system that could be used for fixed-wing fly-by wire transport and business aircraft. This ARP addresses the following: The functions to be implemented The mechanical interconnection between captain and F/O station The geometric and mechanical characteristics The mechanical, electrical, and electronic interfaces The safety and certification requirements
A-6A3 Flight Control and Vehicle Management Systems Cmt
The task of chemical process operator in the parts cleaning area is generally considered unskilled labor and in the past, little or no training had been provided or recommended. Since overhaul cleaning is a critical process step prior to visual and fluorescent penetrant inspection processes, consideration must be given to minimum levels of training for these process operators. It is the responsibility of the department supervisor to ensure that all personnel within the department are trained to acceptable level in all general aspects of health and safety and basic operating procedures. This document is intended to augment the local quality control system which will control the application and frequency of the guidelines stated within
AMS J Aircraft Maintenance Chemicals and Materials Committee
This SAE Aerospace Recommended Practice (ARP) shall be limited to information about corrosion caused by fluoride offgassing of fluoropolymer-based wire insulation. It reviews published reports of corrosion caused by this phenomenon, describes scenarios where this may be a concern, mitigation options, and references a test method which can be used to evaluate wire insulations where needed
AE-8D Wire and Cable Committee
This standard applies to pressure reducers for gaseous breathing oxygen systems and for all performance profiles without regard to particular inlet or outlet pressures. Attention is given, however, to construction requirements for reducers with maximum supply pressures to 2250 psig (155 bar) and reduced pressures of 50 to 150 psig (3.4 to 10.5 bar
A-10 Aircraft Oxygen Equipment Committee
This specification covers three types of flanges for magneto mountings as follows: 1. Two-bolt Flange, 2. Three-bolt Flange, and 3. Four-bolt Flange
E-30 Propulsion Ignition Systems Committee
This standard defines the minimum requirement for the design, construction and performance of continuous flow oxygen masks for crew and passengers of general aviation civil aircraft
A-10 Aircraft Oxygen Equipment Committee
This SAE Aerospace Recommended Practice (ARP) describes a method for classifying the frequencies of analysis of solutions used in the processing of metals, such as electroplating, anodizing, and conversion coating and associated processes but usage is not limited to such applications
AMS B Finishes Processes and Fluids Committee
This document is intended to cover the design of plastic lighted panels, mounting plates, and their installation
A-20A Crew Station Lighting
G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies
This SAE Aerospace Recommended Practice (ARP) specifies the requirements of balancing machines that make them suitable for the subject class of work. It was developed for soft-bearing balancing machines but may also be used for hard-bearing machines until ARP4050 is issued for that type of machine
EG-1A Balancing Committee
The specific performance requirements preceding each test in Section 9 have been written to define certain characteristics of the machine. Conformance with the tests constitutes what is considered minimum proof that the machine will meet these requirements. The test procedures will not prove conformance with all requirements over the full range of all variables, neither will they measure nor define the exact reasons for nonconformance in a given test. Failure of a machine to conform may be due to shortcomings in specific components or to more general reasons such as lack of ruggedness, improper leveling or anchoring to the floor, etc
EG-1A Balancing Committee
This SAE Aerospace Standard (AS) establishes three classes of pallets: a Type A, Air only Pallet b Type B, Platform Pallet (Air/Surface Intermodal) c Type C, Adapter Pallet Pallets will have nominal dimension of: a Size F pallet (10 ft) (NAS 3610-2F1P) - 2.44 m × 2.99 m (96 in × 117.75 in) b Size R pallet (16 ft) (NAS 3610-2R1P) - 2.44 m × 4.98 m (96 in × 196 in) c Size G pallet (20 ft) (NAS 3610-2G1P) - 2.44 m × 6.06 m (96 in × 238.5 in) d Size H pallet (30 ft) (NAS 3610-2H1P) - 2.44 m × 9.12 m (96 in × 359.25 in) e Size J pallet (40 ft) (NAS 3610-2J1 P) - 2.44 m × 12.19 m (96 in × 480 in) Type A, Air only pallets, will normally be on aircraft equivalent roller conveying systems and/or on similarly equipped ancillary ground handling devices. Type B, Platform pallets, are suitable for air/surface handling and transport systems. Supplementary requirements for Type B version are found in Section 4. Type C, Adapter pallets, are used to adapt 2.44 m × 2.44 m (8 ft × 8 ft) surface mode only
AGE-2 Air Cargo
This document includes requirements of installations of adequate landing and taxiing lighting systems in aircraft of the following categories: a Single engine personal and/or liaison type b Light twin engine c Large multiengine propeller d Large multiengine turbojet/turbofan e Military high-performance fighter and attack f Helicopter This document will cover general requirements and recommended practices for all types of landing and taxi lights. More specific recommendations for LED lights in particular can be found in ARP6402
A-20B Exterior Lighting Committee
This test method provides procedures for exposing specimens of elastomer material (slab form) representative to those used in gas turbine engines to aviation lubricants under extended duration and engine relevant thermal conditions. For AS5780 requirements the time is at least 1800 hours and temperatures are 100 °C to 160 °C. Positive volume change is an indication of specimen swell and subsequent negative volume change is an indication of specimen deterioration, both properties are important in the evaluation of the compatibility of the lubricant with elastomers used in the construction of the gas turbine
E-34 Propulsion Lubricants Committee
This document is intended for use by designers, reliability engineers, and others associated with the design, production, and support of electronic sub-assemblies, assemblies, and equipment used in AADHP applications to conduct lifetime assessments of microcircuits with the potential for early wearout; and to implement mitigations when required; and by the users of the AADHP equipment to assess those designs and mitigations. This document focuses on the LLM wearout assessment process. It acknowledges that the AADHP system design process also includes related risk mitigation and management; however, this document includes only high-level reference and discussion of those topics, in order to show their relationship to the LLM assessment process
APMC Avionics Process Management
This SAE Aerospace Recommended Practice (ARP) provides technical recommendations for the lighting applications for Unmanned Aircraft Systems (UAS). The technical content of this ARP discusses the unique trade-offs that are necessary to maintain commonality to the U.S. Federal Aviation Regulations (FARs)1 for aerospace lighting. The recommendations set forth in this document are to aid in the design of Unmanned Aircraft (UA) lighting for the size of aircraft and operation for which the aircraft is intended. In addition, certain concepts of operation for which UASs are suited will require unique lighting solutions
A-20B Exterior Lighting Committee
This document is for establishing and addressing anomalies on appearance of new and newly retreaded tires prior to installation on aircraft. It is intended to use cosmetics as well as functionality to make a determination of acceptability. However, if cosmetic appearance is not a requirement, use the inspection criteria from ARP6225. This ARP does not supersede (E)TSO-C62 minimum requirements, including marking requirements
A-5C Aircraft Tires Committee
The test procedure and related limit value are intended to apply to new, previously untested designs of fixed ground pressure fuel dispensing systems
AE-5C Aviation Ground Fueling Systems Committee
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
S-12 Powered Lift Propulsion Committee
This SAE Aerospace Recommended Practice (ARP) establishes methods for testing airframe plain bearings. The purpose of ARP5448 and its associated slash sheets is to document test methods commonly used to evaluate airframe bearings. These test methods may be referenced in specifications, part standards, purchase orders, etc., when the test is deemed appropriate to the intended use of the bearing by the end user of the bearing. These test methods are not intended to encompass every conceivable requirement for an airframe bearing. The end user of the bearing must exercise engineering judgment to determine the most appropriate standard and/or nonstandard tests for the application
ACBG Plain Bearing Committee
This test method establishes a standard procedure for using plug gages to evaluate dimensional conformance of lined inside diameters of bearings. Bearings covered by this test method include sleeve bearings and lined bore spherical bearings. Note that this method gives no indication of true cylindricity
ACBG Plain Bearing Committee
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