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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.

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 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.

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.

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 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.

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.

This standard sets forth the characteristics for a self-contained Electronic Chronometer for installation in all types of commercial transport aircraft. It provides the following indications to the flight crew, Time of Day, Day and Month, Elapsed Time and Chronograph.

This document describes the aircraft industry recommendations for a headset with integral boom microphone suitable for pilot use in all types of aircraft using conventional radio installations. This document, ARINC Characteristic 535B, is in addition to and does not supersede the older ARINC Characteristic 535A: Lightweight Headset and Boom Microphone, dated March 3, 1972.

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.

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 specfic 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-160E 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.

This document describes the aircraft industry recommendations for a handheld microphone and boom microphone for use with airborne radio installations. This document, ARINC Characteristic 538C, is in addition to and does not supersede the older ARINC Characteristic 538B: Hand-Held Microphone, dated February 16, 1983.

This standard provides the desired characteristics of a RALT intended for installation in all types of commercial transport aircraft. Its primary function is to determine the aircraft's height above terrain for visual display to the pilot (essentially ground level to 2500 feet), and for use by the AFCS during automatically controlled approaches and landings.