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Specify the test requirements specific to active RFID tags for aircraft use, in addition to RTCA DO-160 compliance requirements separately called out in this document. Identify existing standards applicable to active RFID Tag.

The scope of this document is to: 1 Provide a requirements document for RFID tag manufacturers to produce passive-only UHF RFID tags for the aerospace industry. 2 Identify the minimum performance requirements specific to the Passive UHF RFID Tag to be used on airborne equipment, to be accessed only during ground operations. 3 Specify the test requirements specific to Passive UHF RFID tags for airborne equipment use, in addition to EUROCAE ED-14 / RTCA DO-160 compliance requirements separately called out in this document. 4 Identify existing standards applicable to Passive UHF RFID Tag. 5 Provide a certification standard for RFID tags which will use permanently-affixed installation on airborne equipment.

This document provides guidance for applying aircraft equipment electromagnetic, electrical, and mechanical qualification standards (i.e., DO-160, MIL-STD-461, MIL-STD-704, and MIL-STD-810) to civil aircraft certification intended for military use and for military aircraft equipment installed on civil aircraft.

The documents listed below are the major drivers in antiskid/aircraft integration: 1 ARP4754 2 ARP4761 3 RTCA DO-178 4 RTCA DO-254 5 RTCA DO-160 6 ARP490 7 ARP1383 8 ARP1598 In addition, it covers design and operational goals, general theory, and functions, which should be considered by the aircraft brake system engineer to attain the most effective skid control performance, as well as methods of determining and evaluating antiskid system performance.

Cells and batteries were tested under selected load, environmental, and temperature conditions using procedures adapted from RTCA DO-293 and DO-160. On-board aircraft testing verified performance compatibility. Safety tests verified inert failure mode and flight environment compatibility.

The scope of this document is to: 1 Provide a requirements document for RFID Tag Manufacturers to produce passive-only UHF RFID tags for the aerospace industry. 2 Identify the minimum performance requirements specific to the Passive UHF RFID Tag to be used on aircraft parts, to be accessed only during ground operations. 3 Specify the test requirements specific to Passive UHF RFID tags for airborne use, in addition to RTCA DO-160 compliance requirements separately called out in this document. 4 Identify existing standards applicable to Passive UHF RFID Tag. 5 Provide a certification standard for RFID tags which will use permanently-affixed installation on aircraft and aircraft parts.

The documents listed below are the major drivers in antiskid/aircraft integration: 1 ARP4754, Guidelines for Development of Civil Aircraft and Systems 2 ARP4761, Guidelines and Methods for Conducting the Safety Assessment Process on Civil Airborne Systems and Equipment 3 RTCA DO-178, Software Considerations in Airborne Systems and Equipment Certification 4 RTCA DO-254, Design Assurance Guidance for Airborne Electronic Hardware 5 RTCA DO-160, Environmental Conditions and Test Procedures for Airborne Equipment or MIL-STD-810, Environmental Engineering Considerations and Laboratory Tests 6 ARP490, Electrohydraulic Servovalves 7 ARP1383, Aerospace - Impulse Testing of Hydraulic Components In addition, it covers design and operational goals, general theory, and functions, which should be considered by the aircraft brake system engineer to attain the most effective skid control performance, as well as methods of determining and evaluating antiskid system performance.

Cabin electronic equipment can be effected by electrostatic discharge due to environmental and installation conditions, such as low relative humidity and the use of poor or non-conductive materials for carpets, seat textiles, arm rests etc., which exist in all locations within the aircraft. For ESD testing, different Human Body Models, such as the MIL-STD-833 and the RTCA DO-160D (comparable to IEC 1000-4-2) were applied to the passenger entertainment system to reproduce the same system failures observed by different customers. Comparison of the models showed that only the contact discharge with a modified network of the DO-160D standard is the appropriate test method to recreate the problems observed on current equipment and to obtain reproducable test results. Therefore it is recommanded that section 25 of the DO-160D for cabin electronic equipment be modifed.

This paper contains RF radiated emission and susceptibility data from passive Radio Frequency Identification (RFID) tags and readers operating at 13.56 MHz, 915 MHz, and 2.45 GHz. Laboratory test procedures incorporated the methods of RTCA DO-160D (test procedures for aviation electrical/electronic equipment) and DO-233 (test procedures for consumer portable electronic devices (PEDs)). Only one commercially available system was evaluated per established operating frequencies.

RTCA/DO-160G, Environmental Conditions and Test Procedures for Airborne Equipment, prepared by RTCA Special Committee 135, was issued on December 8, 2010, superseding the previous version, DO-160F [1]. DO-160G covers standard procedures and environmental test criteria for testing airborne electrical and electronic equipment (avionics). The tests specified in DO-160G are typically performed to meet Federal Aviation Administration (FAA) or other international regulations covering electrical or electronic equipment that is installed on commercial aircraft. The tests and test levels/limits (also referred to as “Equipment Categories”) found in DO-160G are applicable to virtually every type of aircraft in use today, including small general aviation aircraft, business jets, helicopters, regional jets, and “Jumbo Jets” such as the newest airliners from Airbus (the A350XWB) and Boeing (the 747-8).

The purpose of this SAE Aerospace Recommended Practice (ARP) is to describe key features that should be incorporated in the lavatory smoke detector system. Consideration has been given to existing requirements of the FAA and to recommendations of aircraft operators and manufacturers. This document is deliberately not specific in all areas in order to maximize the freedom to use state-of-the-art design and manufacturing technologies. Safe, reliable, and effective lavatory smoke detectors remain the primary goal of the document.

The purpose of this SAE Aerospace Recommended Practice (ARP) is to describe key features that should be incorporated in the lavatory smoke detector system. Consideration has been given to existing requirements of the FAA and to recommendations of aircraft operators and manufacturers. This document is deliberately not specific in all areas in order to maximize the freedom to use state-of-the-art design and manufacturing technologies. Safe, reliable, and effective lavatory smoke detectors remain the primary goal of the document.

This document defines the steps and documentation required to perform a digital fiber optic link loss budget. This document does not specify how to design a digital fiber optic link. This document does not specify the parameters and data to use in a digital fiber optic link loss budget.

This SAE Aerospace Recommend Practice (ARP) is intended to cover the external lights on fixed wing aircraft for illuminating the wing leading edge and engine nacelles and the upper surfaces of the wing. The addition of an ice detection system should be implemented when the areas to inspect are not visible from the aircraft cockpit. It is not intended that this recommended practice require the use of any particular light source such as halogen, LED, or other specific design of lamp.

This SAE Aerospace Recommend Practice (ARP) is intended to cover the external lights on fixed wing aircraft for illuminating the wing leading edge and engine nacelles and the upper surfaces of the wing. The addition of an ice detection system should be implemented when the areas to inspect are not visible from the aircraft cockpit. It is not intended that this Recommended Practice require the use of any particular light source such as Halogen, LED or other specific design of lamp.

This ARP covers the basic criteria for the design of cabin pressure control systems (CPCS) for general aviation, commercial and military pressurized aircraft.

This document recommends minimum requirements for antiskid brake control to provide total aircraft systems compatibility. Design and operational goals, general theory, and functions, which should be considered by the aircraft brake system engineer to attain the most effective skid control performance, are covered in detail. Methods of determining and evaluating antiskid system performance are discussed. While this document specifically addresses antiskid systems which are a part of a hydraulically actuated brake system, the recommended practices are equally applicable to brakes actuated by other means, such as electrically actuated brakes.

The purpose of this paper to is to review the methodology applied by Collins Aerospace to develop, test and qualify a more robust surface ply rubber compound that has demonstrable improvements in durability and performance at sub-freezing temperatures. Using in-service products as a reference, pneumatic deicers in use on regional turboprop applications were selected as a basis for operational characteristics and observed failure modes. Custom test campaigns were developed by Collins to comparatively evaluate key characteristics of the surface ply material including low temperature elasticity, erosion durability, and fluid susceptibility. Collins’ proprietary engineered rubber formulations were individually evaluated and built into fully functional test deicers for component level testing to DO-160G environmental exposure, comparative ice shed performance in Collins’ Icing Wind Tunnel and erosion in Collins’ Rain Erosion Silo.

This ARP provides detailed information, guidance, and methods in support of the Federal Aviation Administration (FAA) Advisory Circular (AC) 20-136. AC 20-136 provides a means, but not the only means, for demonstrating compliance with Title 14 of the Code of Federal Regulations (14 CFR) 23.1306 (Amendment 23-61), 23.2515 (Amendment 23-64), 25.1316, 27.1316, and 29.1316. It is also intended for this ARP to provide the same information, guidance, and methods, to the European Aviation Safety Agency (EASA) certification specifications CS 23.1306 (Amendment 23/4), 23.2515 (Amendment 23/5), 25.1316, 27.1316, and 29.1316, and associated Acceptable Means of Compliance (AMC) 20-136.

This document is one of a set covering the whole spectrum of aircraft interaction with lightning. This document is intended to describe how to conduct lightning direct effects tests and indirect system upset effects tests. Indirect effects upset and damage tolerance tests for individual equipment items are addressed in DO-160/ED-14. Documents relating to other aspects of the certification process, including definition of the lightning environment, zoning, and indirect effects certification are listed in Section 2. This document presents test techniques for simulated lightning testing of aircraft and the associated systems. This document does not include design criteria nor does it specify which items should or should not be tested. Acceptable levels of damage and/or pass/fail criteria for the qualification tests must be approved by the cognizant certification authority for each particular case.