49.090 - On-board equipment and instruments
ICS 49.090 Details
On-board equipment and instruments
Instrumente. Ausrustungen
Équipement et instruments de bord
Oprema in instrumenti v zračnih in vesoljskih plovilih
General Information
Frequently Asked Questions
ICS 49.090 is a classification code in the International Classification for Standards (ICS) system. It covers "On-board equipment and instruments". The ICS is a hierarchical classification system used to organize international, regional, and national standards, facilitating the search and identification of standards across different fields.
There are 290 standards classified under ICS 49.090 (On-board equipment and instruments). These standards are published by international and regional standardization bodies including ISO, IEC, CEN, CENELEC, and ETSI.
The International Classification for Standards (ICS) is a hierarchical classification system maintained by ISO to organize standards and related documents. It uses a three-level structure with field (2 digits), group (3 digits), and sub-group (2 digits) codes. The ICS helps users find standards by subject area and enables statistical analysis of standards development activities.
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This document specifies a method of determining the attenuation variation of an optical cable during mechanical bending under load at the maximum and minimum operating temperatures.
- Standard9 pagesEnglish languagee-Library read for1 day
This document specifies a method of determining the attenuation variation of an optical cable during mechanical bending under load at the maximum and minimum operating temperatures.
- Standard9 pagesEnglish languagee-Library read for1 day
This document specifies the general characteristics, conditions for qualification, acceptance and quality assurance for a fibre optic cable with a 62,5 µm/125 µm simplex fibre, 2,74 mm outside cable diameter and of semi-loose construction. The basic construction is the cable specified in EN 4641-102 with added sheaths for ruggedized usages.
- Standard13 pagesEnglish languagee-Library read for1 day
This document specifies a method of determining the ability of elements of connection to withstand sinusoidal or random vibrations of specified severities.
It is used together with EN 2591-100.
This test is based on EN 60068-2-6 and EN 60068-2-64.
- Standard14 pagesEnglish languagee-Library read for1 day
This document specifies the dimensions, tolerances, required characteristics and the mass of an AWG 24 shielded quad cable, type KL, intended for high speed (100 Mbit/s) full duplex Ethernet networks.
Linked to this particular application, the operating temperatures of the cable are between −65 °C and 125 °C.
This cable is laser markable, this marking satisfies the requirements of EN 3838.
The characteristics impedance is 100 Ω ± 15 Ω.
- Standard19 pagesEnglish languagee-Library read for1 day
This document specifies the general characteristics, conditions for qualification, acceptance and quality assurance for a fibre optic cable with a 62,5 µm/125 µm graded index fibre nominal, 1,8 mm outside diameter and of semi-loose buffer construction.
- Standard17 pagesEnglish languagee-Library read for1 day
REN/MSG-TFES-1138
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This document specifies the general characteristics, conditions for qualification, acceptance and quality assurance for a fibre optic cable with a 62,5 µm/125 µm simplex fibre, 2,74 mm outside cable diameter and of semi-loose construction. The basic construction is the cable specified in EN 4641-102 with added sheaths for ruggedized usages.
- Standard13 pagesEnglish languagee-Library read for1 day
This document specifies a method of determining the ability of elements of connection to withstand sinusoidal or random vibrations of specified severities.
It is used together with EN 2591-100.
This test is based on EN 60068-2-6 and EN 60068-2-64.
- Standard14 pagesEnglish languagee-Library read for1 day
This document specifies the dimensions, tolerances, required characteristics and the mass of an AWG 24 shielded quad cable, type KL, intended for high speed (100 Mbit/s) full duplex Ethernet networks.
Linked to this particular application, the operating temperatures of the cable are between −65 °C and 125 °C.
This cable is laser markable, this marking satisfies the requirements of EN 3838.
The characteristics impedance is 100 Ω ± 15 Ω.
- Standard19 pagesEnglish languagee-Library read for1 day
This document specifies the general characteristics, conditions for qualification, acceptance and quality assurance for a fibre optic cable with a 62,5 µm/125 µm graded index fibre nominal, 1,8 mm outside diameter and of semi-loose buffer construction.
- Standard17 pagesEnglish languagee-Library read for1 day
This document specifies a method for checking the variation of attenuation of an optical cable during temperature cycling.
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This document specifies a method for checking the variation of attenuation of an optical cable during temperature cycling.
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This document details the dimensions and performance requirements of a multimode male size 12, non-physical contact expanded beam terminus. This terminus is suitable for use with connectors which have standard size 12 pin crimp contact cavities: connectors with cavities for contact of type EN 3155-008M12.
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This document details the dimensions and performance requirements of a multimode male size 16, non-physical contact expanded beam terminus. This terminus is suitable for use with connectors which have standard size 16 pin crimp contact cavities: connectors with cavities for contact of type EN 3155-008M16.
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This document details the dimensions and performance requirements of a multimode female size 12, non-physical contact expanded beam terminus. This terminus is suitable for use with connectors which have standard size 12 socket crimp contact cavities (series I and III): connectors with cavities for contact of type EN 3155-009F12.
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This document details the dimensions and performance requirements of a multimode female size 16, non-physical contact expanded beam terminus. This terminus is suitable for use with connectors which have standard size 16 socket crimp contact cavities (series I and III): connectors with cavities for contact of type EN 3155-009F16.
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This document specifies the general characteristics, the conditions for qualification, acceptance and quality assurance, as well as the test programs and groups for threaded ring coupling circular connectors with expanded beam termini, intended for use in a temperature range from −55 °C to 125 °C continuous.
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This document details the dimensions and performance requirements of a multimode female size 12, non-physical contact expanded beam terminus. This terminus is suitable for use with connectors which have standard size 12 socket crimp contact cavities (series I and III): connectors with cavities for contact of type EN 3155-009F12.
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This document specifies the general characteristics, the conditions for qualification, acceptance and quality assurance, as well as the test programs and groups for threaded ring coupling circular connectors with expanded beam termini, intended for use in a temperature range from −55 °C to 125 °C continuous.
- Standard46 pagesEnglish languagee-Library read for1 day
This document details the dimensions and performance requirements of a multimode male size 12, non-physical contact expanded beam terminus. This terminus is suitable for use with connectors which have standard size 12 pin crimp contact cavities: connectors with cavities for contact of type EN 3155-008M12.
- Standard13 pagesEnglish languagee-Library read for1 day
This document details the dimensions and performance requirements of a multimode female size 16, non-physical contact expanded beam terminus. This terminus is suitable for use with connectors which have standard size 16 socket crimp contact cavities (series I and III): connectors with cavities for contact of type EN 3155-009F16.
- Standard13 pagesEnglish languagee-Library read for1 day
This document details the dimensions and performance requirements of a multimode male size 16, non-physical contact expanded beam terminus. This terminus is suitable for use with connectors which have standard size 16 pin crimp contact cavities: connectors with cavities for contact of type EN 3155-008M16.
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This document specifies the general characteristics, conditions for qualification, acceptance and quality assurance for a fibre optic cable with a bend-insensitive, 50 µm/125 µm Graded Index fibre core, 1,8 mm outside diameter for non pull-proof contact designs.
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This document specifies the general requirements for the methods of testing elements of electrical, optical and data transmission system connections used in aerospace applications.
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This document specifies the general requirements for the methods of testing elements of electrical, optical and data transmission system connections used in aerospace applications.
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This document specifies the general characteristics, conditions for qualification, acceptance and quality assurance for a fibre optic cable with a bend-insensitive, 50 µm/125 µm Graded Index fibre core, 1,8 mm outside diameter for non pull-proof contact designs.
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This document specifies the general characteristics, conditions for qualification, acceptance and quality assurance for a fibre optic cable with a 50/125 µm Graded Index fibre core, 1,8 mm outside diameter for non-pull-proof contact designs.
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This document specifies the general characteristics, conditions for qualification, acceptance and quality assurance for a fibre optic cable with a 50/125 µm Graded Index fibre core, 1,8 mm outside diameter for non-pull-proof contact designs.
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This document specifies a method of measuring the semi loose effect of a semi loose cable.
Pull proof optical contacts are used. The optical contact (ferrule) is longitudinally moving to preserve the optical performance even when cables are pulled.
Consequently, the buffered fibre moves beneath the strength members (called semi loose effect).
This document describes a test methodology to assess the quality of the cable when contact is pulled or pushed.
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This document specifies a method of measuring the semi loose effect of a semi loose cable.
Pull proof optical contacts are used. The optical contact (ferrule) is longitudinally moving to preserve the optical performance even when cables are pulled.
Consequently, the buffered fibre moves beneath the strength members (called semi loose effect).
This document describes a test methodology to assess the quality of the cable when contact is pulled or pushed.
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SIGNIFICANCE AND USE
4.1 The purpose of this practice is to establish methods that can be used to satisfy the Function and Installation requirements, and the Safety Requirements, provided in 4.1 and 4.2, respectively, in Specification F3061/F3061M.
4.2 Threat conditions that can cause Hazardous or Catastrophic failure conditions, including those that can propagate through interconnected systems causing Hazardous or Catastrophic failure conditions, are required to be addressed using this practice.
SCOPE
1.1 This practice covers methods for addressing Aircraft System Information Security Protection (ASISP) risks caused by Intentional Unauthorized Electronic Interactions (IUEIs). This practice was developed considering Level 1, Level 2, Level 3, and Level 4 normal category aeroplanes. The content may be more broadly applicable. It is the responsibility of the applicant to substantiate broader applicability as a specific means of compliance. The topics covered within this practice are threat identification, identifying security measures, conducting a security risk assessment, and security documentation.
1.2 An applicant intending to use this practice as means of compliance for a design approval must seek guidance from their respective oversight authority (for example, published guidance from applicable civil aviation authority (CAA)) concerning the acceptable use and application thereof. For information on which oversight authorities have accepted this practice (in whole or in part) as an acceptable Means of Compliance to their regulatory requirements (hereinafter “the Rules”), refer to the ASTM Committee F44 web page (www.astm.org/COMMITTEE/F44.htm).
1.3 This standard does not purport to address all of the safety concerns, if any, associated with its use. It is the responsibility of the user of this standard to establish appropriate safety, health, and environmental practices and determine the applicability of regulatory limitations prior to use.
1.4 This international standard was developed in accordance with internationally recognized principles on standardization established in the Decision on Principles for the Development of International Standards, Guides and Recommendations issued by the World Trade Organization Technical Barriers to Trade (TBT) Committee.
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This document specifies the required characteristics of single braid, 120 ohms, size 26, electrical cable type WX, UV laser markable, intended for digital data transmissions.
It is used together with EN 3375 001.
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This document specifies methods of verifying adhesion of electrodeposited gold and gold alloy coatings on contacts.
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This document specifies methods of measuring thickness of electro-deposited gold or gold alloys coatings on contacts of elements of connection.
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This document specifies methods of measuring thickness of electro-deposited gold or gold alloys coatings on contacts of elements of connection.
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This document specifies methods of verifying adhesion of electrodeposited gold and gold alloy coatings on contacts.
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The present document is applicable to the Advanced Surface Movement Guidance and Control System (A-SMGCS)
Guidance Service. This service is based on the A-SMGCS surveillance service (as specified in ETSI EN 303 213-1 [3])
and generates individual guidance information for mobiles based on the surveillance and routing information and
known constraints (e.g. standard taxi routes, taxiway closures). In most cases these guidance information will be
provided to external partner systems of the A-SMGCS, such as the airfield ground lighting or electronic flight bag
display systems in the cockpit of the mobiles. The guidance information can be modified by the controller at any time.
The present document provides a European Standard for Air Navigation Service Providers, who have to demonstrate
and declare compliance of their systems and procedures to the Regulation (EU) 2018/1139 [i.3], and takes into account
Commission Implementing Regulation (EU) 2021/116 [i.2].
A mapping of requirements for the A-SMGCS guidance service to the relevant Essential Requirements of Regulation
(EU) 2018/1139 [i.3] is provided in Annex A.
Any software elements related to the software assurance level of an A-SMGCS are outside of the scope of the present
document. As such the essential requirements of the Regulation (EU) 2018/1139 [i.3] are not considered for software
elements within the present document.
The present document does not give presumption of conformity related to the maintenance requirements, environmental
constraints, procedure level, effect of harmful interference and civil/military coordination.
NOTE: For these ERs, refer to the Air Navigation Service Provider procedures.
Requirements in the present document which refer to "should" statements or recommendations in the normatively
referenced material (clause 2.1) are to be interpreted as fully normative ("shall") for the purpose of compliance with the
present document.
Currently there are no relevant Implementing Rules for A-SMGCS. The present document does not give presumption of
conformity to any current interoperability Implementing Rules.
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ABSTRACT
This specification prescribes the exposure limits and safe operating guidelines for infrared (IR) radiating devices to be mounted on N registered aircraft or any aircraft which is flown or operated in the United States or its territories. The American Conference of Governmental Industrial Hygienists (ACGIH) has established threshold limit values (TLVs) for IR radiation exposure. The TLVs represent a safe exposure limit without physical harm, even with daily exposure. For this specification, the safe exposure time has been set at 100 seconds to reach the TLV. Therefore, the safe operating distance is calculated by determining the maximum output radiation of the device such that 100 seconds of exposure does not exceed one TLV as established by ACGIH.
SCOPE
1.1 This specification establishes the manufacturing design, manufacturing quality system and installation requirements for airborne infrared (IR) searchlight equipment, systems, and devices. This specification applies only to IR devices that produce incoherent IR radiation and affixed to an aircraft which is N registered or operated and flown within the United States and its territories.
1.2 This specification establishes the minimum and maximum system performance and provides guidelines for an operator to develop functional operation requirements to ensure IR safety.
1.3 This specification covers IR device emissions in support of night vision goggles or other devices such as electro-optical/infrared (EO/IR) sensors capable of detecting IR radiation.
1.4 This specification covers IR device emissions that may pose a hazard to the flight crew, aircraft, and bystanders.
1.5 This specification covers IR device emissions and related safety controls such as duration, beam width, radiant intensity, and wavelength.
1.6 This specification encourages an Original Equipment Manufacturer (OEM) to maintain a robust quality assurance program and a well-documented configuration control process at the component level and continued through installation at the system level.
1.7 The OEM shall include the warnings, exposure limitations and corresponding data, and installation instructions described within this specification in their operation and installation manuals. These manuals shall be provided with the product or device.
1.8 Units—The values stated in SI units are to be regarded as the standard. No other units of measurement are included in this standard.
1.9 This standard does not purport to address all of the safety concerns, if any, associated with its use. It is the responsibility of the user of this standard to establish appropriate safety, health, and environmental practices and determine the applicability of regulatory limitations prior to use.
1.10 This international standard was developed in accordance with internationally recognized principles on standardization established in the Decision on Principles for the Development of International Standards, Guides and Recommendations issued by the World Trade Organization Technical Barriers to Trade (TBT) Committee.
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SIGNIFICANCE AND USE
4.1 The guide is intended to be used to assess competencies of qualified individuals who wish to become certified as an Automatic Flight Control System technician through a program such as the National Center for Aerospace and Transportation Technologies (NCATT).
4.2 The guide is intended to be used in concert with a certification provider’s structure and materials for management, exam delivery, and candidate preparation.
SCOPE
1.1 The purpose of this guide is to address the fundamental subject knowledge activities and functions for avionics professionals to be titled Automatic Flight Control System (AFCS) Technician.
1.2 This guide is the basis for the Automatic Flight Control System Technician (AFCS) certification, an endorsement to the Aircraft Electronics Technician (AET) certification. Candidates must be a certified AET to take the certification exam associated with this guide.
1.3 This standard does not purport to address all of the safety concerns, if any, associated with its use. It is the responsibility of the user of this standard to establish appropriate safety, health, and environmental practices and determine the applicability of regulatory limitations prior to use.
1.4 This international standard was developed in accordance with internationally recognized principles on standardization established in the Decision on Principles for the Development of International Standards, Guides and Recommendations issued by the World Trade Organization Technical Barriers to Trade (TBT) Committee.
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This document evaluates the resistance of the fiber optic cable to humidity changes at different
temperatures.
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This document specifies the required characteristics, test methods, qualification and acceptance conditions of signal data transmission electrical cables.
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ABSTRACT
This specification describes a process for verifying the intended function and compliance with safety objectives of avionics systems by means of system-level testing. This verification process includes functional verification planning, testing, resolution of test failures, and regression analysis and testing. It also covers organizational requirements and the process of product definition (function identification, classification, and specification) as well as the requirements for producing a statement of verification.
SCOPE
1.1 This specification provides a process for performing system level verification of aircraft systems and equipment. It provides a means of compliance that can be used for systems and equipment with software and Airborne Electronic Hardware (AEH) that have not been addressed by traditional development assurance methods.
1.2 This process can be used to show compliance to regulations that require a demonstration that functionality was implemented as intended, including safety mitigations that address failure conditions for software and AEH aspects for aircraft systems and equipment.
1.3 While this specification was developed with systems and equipment installed on aircraft certification level 1 and 2 (or class I and II in accordance with Advisory Circular (AC) 23.1309-1) normal category aeroplanes in mind, the content may be more broadly applicable. It is the responsibility of the Applicant to substantiate broader applicability as a specific means of compliance and obtain concurrence for its use from the applicable Civil Aviation Authority (CAA).
1.4 When using this specification, regulations that govern system safety requirements applicable to the aircraft still apply. In complying with those regulations, additional architectural mitigations such as redundancy, independence, separation, system monitors, etc., may be required in addition to the verification process specified in this specification.
1.5 The system level verification activities expected by this specification increase as the severity of the failure conditions applicable to or affected by the function increase. Those functions, which have hazardous and catastrophic failure conditions, receive additional activities through this process to provide detailed scrutiny. For normal category aircraft, refer to Practice F3309, Practice F3230, or AC 23.1309-1 for more information on the identification and classification of system failure conditions. Involvement of the applicable CAA personnel or their designees in this system verification process should be discussed early in the project.
1.6 This verification process specifically addresses definition, identification, and verification of system functions. Processes conducted under this specification may not satisfy all applicable external requirements; additional review on the part of the system developer, integrator, or installer may be required to meet specific requirements or the specified mission of the aircraft, or both.
1.7 The values stated in inch-pound units are to be regarded as standard. No other units of measurement are included in this standard.
1.8 This standard does not purport to address all of the safety concerns, if any, associated with its use. It is the responsibility of the user of this standard to establish appropriate safety, health, and environmental practices and determine the applicability of regulatory limitations prior to use.
1.9 This international standard was developed in accordance with internationally recognized principles on standardization established in the Decision on Principles for the Development of International Standards, Guides and Recommendations issued by the World Trade Organization Technical Barriers to Trade (TBT) Committee.
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The present document specifies technical characteristics and methods of measurements for the following equipment
types (which are parts of a Mobile Communication On Board Aircraft system):
1) The Onboard Base Transceiver Station (OBTS) supporting GSM and/or UMTS, and/or LTE communication
protocols including specific functions for restricting the transmit power of the MSs or UEs, associated with the
OBTS.
2) The Network Control Unit (NCU) preventing direct connection of the onboard mobile terminals with mobile
networks on the ground by raising the noise floor in the cabin.
The OBTSs are capable of operating in all or any part of the frequency bands given in table 1-1.
The present document applies only to radio equipment using a dedicated transmitting antenna that is designed as an
indispensable part of the system for usage on board an aircraft.
It applies to equipment for continuous and discontinuous transmission of data and digital speech.
Within the European Union, the system covered by the present document operates in accordance with the operational
requirements as outlined in the Commission Decision 2016/2317/EU [i.4] based on the former Decision 2013/654 [i.3].
In relation the NCU, some frequency bands are now optional while they were mandatory before. Due to this difference
the present document had to be reviewed.
The present document contains requirements to ensure that such Radio equipment both effectively uses and supports the
efficient use of radio spectrum in order to avoid harmful interference.
In addition to the present document, other ENs that specify technical requirements in respect of essential requirements
under other parts of article 3 of the Radio Equipment Directive [i.1] may apply to equipment within the scope of the
present document.
The present document does not cover equipment compliance with relevant civil aviation regulations. In this respect, a
MCOBA system, for its installation and operation on board an aircraft is subject to additional national or international
civil aviation airworthiness certification requirements, for example to EUROCAE ED-14G [i.7].
NOTE: The relationship between the present document and essential requirements of article 3.2 of Directive
2014/53/EU [i.1] is given in annex A.
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ABSTRACT
This specification establishes functional operation and minimum performance requirements for simple systems that provide angle-of-attack information to a pilot, aircraft, or other systems. Functional requirements cover basic operation, stall indication, startup of electronically driven systems, accessibility of controls, and software while environmental requirements include icing, deicing fluids, emissions of RF energy, electrical power input, and power input abnormal surge voltage.
SCOPE
1.1 This performance specification covers simple systems that provide angle-of-attack information to a pilot, aircraft, or other systems.
Note 1: More complex AoA systems can be addressed in annexes in the future.
1.2 In this performance specification, functional operation and minimum performance requirements for an angle-of-attack system are established.
1.3 The values stated in SI units are to be regarded as standard. No other units of measurement are included in this standard.
1.4 This standard does not purport to address all of the safety concerns, if any, associated with its use. It is the responsibility of the user of this standard to establish appropriate safety, health, and environmental practices and determine the applicability of regulatory limitations prior to use.
1.5 This international standard was developed in accordance with internationally recognized principles on standardization established in the Decision on Principles for the Development of International Standards, Guides and Recommendations issued by the World Trade Organization Technical Barriers to Trade (TBT) Committee.
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IEC PAS 63343:2021 specifies technical requirements, methods of test and required test results for equipment implementing ASM part of the VHF Data exchange system (VDES) as defined in ITU-R M.2092.
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The present document is applicable to deployed non-cooperative sensor as a constituent of an Advanced Surface
Movement Guidance and Control System (A-SMGCS).
The present document provides a European Standard for manufacturers, Air Navigation Service Providers and/or
Airport Operators, who have to demonstrate and declare compliance of their systems and constituents to the Essential
Requirements (ERs) of Annex VIII of Regulation (EU) 2018/1139 [i.7].
NOTE 1: The ERs in Annex VIII of Regulation (EU) 2018/1139 [i.7] covered by the present document are outlined
in Table A.1.
NOTE 2: Although the ERs of the SES Interoperability Regulation [i.1] have been repealed with effect from
11 September 2018 [i.7], a mapping of the requirements for the A-SMGCS Surveillance Service to this
same regulation [i.1] is provided in Annex B.
Any software elements related to the software assurance level of an A-SMGCS are out of scope of the present
document. As such the ERs of Regulation (EU) 2018/1139 [i.7] are not considered for software elements within the
present document.
The present document does not give presumption of conformity related to the maintenance requirements, environmental
constraints, procedure level, effect of harmful interference and civil/military coordination.
NOTE 3: For these ERs, the Air Navigation Service Provider will need to provide supplementary compliance
within their Interoperability Technical Files.
The present document does not give presumption of conformity to any current interoperability Implementing Rules
(IRs).
NOTE 4: Currently there are no relevant Implementing Rules for A-SMGCS.
Requirements in the present document which refer to "should" statements or recommendations in the normatively
referenced material (clause 2.1) are to be interpreted as fully normative ("shall") for the purpose of compliance with the
present document if they are unambiguously referred to from the present document.
The reference to particular requirements is done either by citing the unambiguous requirement number or range of
numbers (e.g. "[REQ 30.] to [REQ 35.]") or, if no requirement numbers are available, by indicating the paragraph and
clause of the reference material where the requirement can be found.
NOTE 5: Other requirements and other EU Regulations and/or Directives may be applicable to the product(s)
falling within the scope of the present document.
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The present document is applicable to deployed non-cooperative SMR sensor as a constituent of an Advanced Surface
Movement Guidance and Control System (A-SMGCS).
NOTE 1: Generic requirements for a non-cooperative sensor are defined in ETSI EN 303 213-4-1 [1].
The present document provides a European Standard for manufacturers, Air Navigation Service Providers and/or
Airport Operators, who have to demonstrate and declare compliance of their systems and constituents to the Essential
Requirements (ERs) of Annex VIII of Regulation EU 2018/1139 [i.6].
NOTE 2: The ERs in Annex VIII of Regulation EU 2018/1139 [i.6] covered by the present document are outlined
in Table A.1.
NOTE 3: Although the ERs of the SES Interoperability Regulation [i.1] have been repealed with effect from
11 September 2018 [i.6], a mapping of the requirements for the A-SMGCS Surveillance Service to this
same regulation [i.1] is provided in Annex B.
Any software elements related to the software assurance level of an A-SMGCS are out of scope of the present
document. As such the ERs of Regulation EU 2018/1139 [i.6] are not considered for software elements within the
present document.
The present document does not give presumption of conformity related to the maintenance requirements, environmental
constraints, procedure level, effect of harmful interference and civil/military coordination.
NOTE 4: For these ERs, the Air Navigation Service Provider will need to provide supplementary compliance
within their Interoperability Technical Files.
The present document does not give presumption of conformity to any current interoperability Implementing Rules
(IRs).
NOTE 5: Currently there are no relevant Implementing Rules for A-SMGCS.
Requirements in the present document which refer to "should" statements or recommendations in the normatively
referenced material (clause 2.1) are to be interpreted as fully normative ("shall") for the purpose of compliance with the
present document if they are unambiguously referred to from the present document.
The reference to particular requirements is done either by citing the unambiguous requirement number or range of
numbers (e.g. "[REQ 30.] to [REQ 35.]") or, if no requirement numbers are available, by indicating the paragraph and
clause of the reference material where the requirement can be found.
NOTE 6: Other requirements and other EU Regulations and/or Directives may be applicable to the product(s)
falling within the scope of the present document.
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1.1 General
Part 001 of EN 4533 examines the termination of optical fibre cables used in aerospace applications. Termination is the act of installing an optical terminus onto the end of a buffered fibre or fibre optic cable. It encompasses several sequential procedures or practices. Although termini will have specific termination procedures, many share common elements and these are discussed in this document. Termination is required to form an optical link between any two network or system components or to join fibre optic links together.
The fibre optic terminus features a precision ferrule with a tight tolerance central bore hole to accommodate the optical fibre (suitably bonded in place and highly polished). Accurate alignment with another (mating) terminus will be provided within the interconnect (or connector) alignment mechanism. As well as single fibre ferrules, it is noted that multi-fibre ferrules exist (e.g. the MT ferrule) and these will also be discussed in this part of the handbook.
Another technology used to connect 2 fibres is the expanded beam. 2 ball lenses are used to expand, collimate and then refocus the light from and to fibres. Contacts are not mated together. It helps reducing the wear between 2 contacts and allows more mating cycles. This technology is less sensitive to misalignments and dust. Losses are remaining more stable than butt joint contact even if the nominal loss is higher.
A Note on Terminology
Current terminology in the aerospace fibre optics community refers to an optical terminus or termini. The term optical contact may be seen in some documents and has a similar meaning. However, the term contact is now generally reserved for electrical interconnection pins. The optical terminus (or termini) is housed within an interconnect (connector is an equivalent term). Interconnects can be single-way or multi-way. The interconnect or connector will generally house the alignment mechanism for the optical termini (usually a precision split-C sleeve made of ceramic or metal). The reader should be aware of these different terms.
An optical link can be classified as a length of fibre optic cable terminated at both ends with fibre optic termini. The optical link provides the transmission line between any two components via the optical termini which are typically housed within an interconnecting device (typically a connector) with tight tolerancing within the alignment mechanisms to ensure a low loss light transmission.
Part 001 will explain the need for high integrity terminations, provide an insight into component selection issues and suggests best practice when terminating fibres into termini for high integrity applications. A detailed review of the termination process can be found in section 4 of this part and is organised in line with the sequence of a typical termination procedure.
The vast number of cable constructions and connectors available make defining a single termination instruction that is applicable to all combinations very difficult. Therefore, this handbook concentrates on the common features of most termination practices and defining best practice for current to near future applications of fibre optics on aircraft. This has limited the studies within this part to currently available ‘avionic’ silica fibre cables and adhesive filled butt-coupled type connectors. Many of the principles described however would still be applicable for other termination techniques. Other types of termination are considered further in the repair part of this handbook.
It is noted that the adhesive based pot-and-polish process is applicable to the majority of single-way fibre optic interconnects connectors and termini for multi-way interconnects and connectors. They share this commonality.
1.2 Need to high integrity terminations
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The present document is applicable to Advanced Surface Movement Guidance and Control System (A-SMGCS)
Surveillance Service. This system provides enhanced surveillance functionalities, as well as a display to controllers with
accurate and unambiguous identity and position information on the entire manoeuvring and movement area of
aerodromes.
The present document provides a European Standard for manufacturers, Air Navigation Service Providers and/or
Airport Operators, who have to demonstrate and declare compliance of their systems and constituents to the Essential
Requirements (ERs) of Annex VIII of Regulation (EU) No 2018/1139 [i.1].
NOTE 1: The ERs in Annex VIII of Regulation (EU) No 2018/1139 [i.5] covered by the present document are
outlined in Table A.1.
NOTE 2: Although the ERs of the SES Interoperability Regulation [i.1] have been repealed with effect from
11 September 2018 [i.5], a mapping of the requirements for a deployed cooperative sensor including its
interfaces to this same regulation [i.1] is provided in Annex B.
Any software elements related to the software assurance level of an A-SMGCS are out of scope of the present
document. As such the ERs of Regulation EU 2018/1139 [i.5] are not considered for software elements within the
present document.
The present document does not give presumption of conformity related to the maintenance requirements, constraints,
procedure level, effect of harmful interference and civil/military coordination.
NOTE 3: For these ERs, the Air Navigation Service Provider will need to provide supplementary compliance
within their Interoperability Technical Files.
The present document does not give presumption of conformity to any current interoperability Implementing Rules
(IRs).
NOTE 4: Currently there are no relevant Implementing Rules for A-SMGCS.
Requirements in the present document which refer to "should" statements or recommendations in the normatively
referenced material (clause 2.1) are only to be interpreted as fully normative ("shall") for the purpose of compliance
with the present document if they are unambiguously referred to from the present document.
The reference to particular requirements is done either by citing the unambiguous requirement number or range of
numbers (e.g. "[REQ 30.] to [REQ 35.]") or, if no requirement numbers are available, by indicating the paragraph and
clause of the reference material where the requirement can be found.
NOTE 5: Other requirements and other EU Regulations and/or Directives may be applicable to the product(s)
falling within the scope of the present document.
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