This document describes the procedures for training personnel who will be involved in the operation of unmanned aircraft systems (UAS). This document defines: a) knowledge, skill, attitude and qualification criteria that are needed for UAS pilots and training organizations that provide training to UAS remote pilots and other personnel involved in UAS operations; b) training curriculum and contents for specific learning courses; c) qualification and confirmation criteria for the training organizations; d) general procedures for providing training of UAS personnel; the requirements for a specific course as described in Annex A can be more restrictive in some cases.

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This document establishes basic requirements for interface control documents (ICD) writing and interface control procedures for the following items included in the launch system: payload, launch vehicle, ground support equipment (according to ISO 14625) and launch site (buildings with utility systems), specifically: a) ICD between the ground support equipment and the payload; b) ICD between the ground support equipment and the launch vehicle; c) ICD between items of the ground support equipment; d) ICD between the ground support equipment and the launch site. This document is applicable to organizations developing ground support equipment and to operators performing space activity.

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This document specifies the procedures for testing flight stability of a multi-copter unmanned aircraft system (UAS) and is applicable to multi-copter type UAS that can take-off and land vertically. A commercial multi-copter UAS weighing over 250 g to less than 150 kg is discussed in this document. Further, this document is applicable to military and civilian multi-copter UAS. However, quantitatively specific stability criteria for the test are not specified in this document.

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This document specifies the dimensions of self-locking, silver-coated bi-hexagonal nuts with MJ-thread in heat resisting nickel base alloy NI-P101HT for aerospace applications.
Maximum test temperature of the material 730 °C.

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IEC 61820-3-4:2023 specifies protective provisions for the operation of lamp systems powered by series circuits in aeronautical ground lighting.
The protective provisions described here refer only to secondary supply systems for loads that are electrically separated from the series circuit.
This document specifies the level of SELV, and alternatively PELV, under consideration of additional personnel protection during work on live secondary circuits by electrically skilled persons. This document also covers the special operational features of aeronautical ground lighting and addresses the level of training and the requirements for maintenance procedures detailed in IEC 61821 and other national or regional regulation.
The requirements and tests are intended to set a specification framework for system designers, system installers, users, and maintenance personnel to ensure a safe and economic use of electrical systems in installations for the beaconing of aerodromes.
This document complements existing IEC aeronautical ground lighting (AGL) standards and can be used as a design specification.

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This standard defines the requirements for selection, control, procurement and
usage of EEE commercial components for space projects.
This standard is applicable to commercial parts from the following families:
• Ceramic capacitors chips
• Solid electrolyte tantalum capacitors chips
• Discrete parts (transistors, diodes, optocouplers)
• Fuses
• Magnetic parts
• Microcircuits
• Resistors chips
• Thermistors
In addition for families of EEE components not addressed by the present ECSS
standard, it can be used as guideline on case by case basis.
The requirements of this document are applicable to all parties involved at all
levels in the integration of EEE commercial components into space segment
hardware and launchers.
This standard may be tailored for the specific characteristics and constrains of a
space project in conformance with ECSS-S-ST-00

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This document defines a number of conditions common to rectangular electrical modular connectors for receptacles, plugs and rack and panel, with interchangeable modules and continuous operating temperature 175 °C.

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This document applies to GSE when used in civil air transport as intended by the manufacturer and contains safety requirements relating to the equipment in general.
This document specifies the technical requirements to minimise the hazards listed in Clause 4 which can arise during the commissioning, operation and maintenance of GSE when used as intended including any reasonably foreseeable misuse by the manufacturer, when carried out in accordance with the specifications given by the manufacturer or his authorised representative. It also takes into account some requirements recognised as essential by authorities, aircraft and ground support equipment (GSE) manufacturers as well as airlines and handling agencies.
This part of EN 1915 is intended to be used in conjunction with EN 1915-2:2001+A1:2009, EN 1915-3:2004+A1:2009 (for self-propelled GSE) and EN 1915-4:2004+A1:2009, and with the relevant part of EN 12312 to give the requirements for the types of GSE within the scope of EN 12312.
When EN 12312 does not contain a relevant part for a GSE, EN 1915 (all parts) gives general requirements that may apply, although additional machine specific requirements, to be determined by the manufacturer, are likely to be required.
This part of EN 1915 does not apply to automotive parts approved for public vehicles in the EU and EFTA, when used on GSE for the purpose for which they are designed.
This part of EN 1915 does not establish additional requirements for the following:
a)   operation elsewhere than in an airport environment;
b)   operation in severe conditions, e.g. ambient temperature below -20 °C or over 50 °C, tropical or saturated salty atmospheric environment, strong magnetic or radiation field;
c)   operation subject to special rules, e.g. potentially explosive atmosphere except as regards operation in the vicinity of an aircraft fuel tank during fuelling operation;
d)   hazards caused by power supply other than from electrical networks;
e)   hazards occurring during construction, transportation, decommissioning and disassembly of the GSE;
f)   hazards caused by wind velocity in excess of the figures given in this document;
g)   direct contact with food stuffs;
h)   earthquake, flood, landslide, lightning and more generally any exceptional natural event;
i)   electromagnetic compatibility (EMC);
j)   hazards caused by noise and vibration, see EN 1915-3:2004+A1:2009 and EN 1915-4:2004+A1:2009.
While this standard gives some basic requirements for wireless remote controls, additional requirements will be necessary.
This part of EN 1915 is not applicable to GSE which are manufactured before the date of publication by CEN of this document.

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This standard defines the requirements for selection, control, procurement and usage of EEE components for space projects.
This standard differentiates between three classes of components through three different sets of standardization requirements (clauses) to be met.
The three classes provide for three levels of trade-off between assurance and risk. The highest assurance and lowest risk is provided by class 1 and the lowest assurance and highest risk by class 3. Procurement costs are typically highest for class 1 and lowest for class 3. Mitigation and other engineering measures may decrease the total cost of ownership differences between the three classes. The project objectives, definition and constraints determine which class or classes of components are appropriate to be utilised within the system and subsystems.
a.   Class 1 components are described in Clause 4.
b.   Class 2 components are described in Clause 5
c.   Class 3 components are described in Clause 6.
The requirements of this document apply to all parties involved at all levels in the integration of EEE components into space segment hardware and launchers.

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This Standard specifies the processing and quality assurance requirements for
brazing processes for space flight applications. Brazing is understood as the
joining and sealing of materials by means of a solidification of a liquid filler
metal.
The term brazing in this standard is used as equivalent to soldering, in cases that
the filler materials have liquidus temperatures below 450 °C.
Brazing and soldering are allied processes to welding and this standard is
supplementing the standard for welding ECSS-Q-ST-70-39.
This standard does not cover requirements for:
• Joining processes by adhesive bonding (ECSS-Q-ST-70-16),
• Soldering for electronic assembly purposes (ECSS-Q-ST-70-61),
• Soldering used in hybrid manufacturing (ESCC 2566000).
The standard covers but is not limited to the following brazing processes:
• Torch brazing,
• Furnace brazing,
• Dip Brazing and Salt-bath brazing,
• Induction Brazing.
This Standard does not detail the brazing definition phase and brazing pre-
verification phase, including the derivation of design allowables.
This standard may be tailored for the specific characteristic and constraints of a
space project in conformance with ECSS-S-ST-00.

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This document sets forth the general rules applying to the justification of the definition of a product (tangible or intangible) and specifies the content of the Definition Justification Plan (DJP) and the Definition Justification Dossier (DJD).
It is applicable to all products designed and developed to fulfil the requirements of a customer expressed in a (Need) Technical Specification. Industrials are advised to apply the following principles to their own needs for justification in their internal customer/supplier relations.
Clause 5 presents the concepts and the documents associated with the justification of the definition and qualification processes.
Clause 6 summarizes the role and the contractual nature of the qualification of the definition.
Clause 7 gives details of the qualification of the definition process, while Clause 8 positions this process in the programme development logic.
The document also describes the differences between the justification and the qualification of the definition and other notions, such as verification, validation or acceptance (Clause 9).
Clause 10 is a guide to the establishment and maintenance of the documents associated with the justification of the definition and qualification processes. Information related to the certification process, even if it is out of the scope of the present document, is also presented in Clause 10, because this process has certain similarities with the justification of the definition and qualification process.
This document belongs to the documents supporting the EN 9200 relating to Project Management Specification.

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This document specifies the characteristics of self-locking, floating, two lug anchor nuts, reduced series,
with counterbore, in steel, cadmium plated, MoS 2 lubricated.
Classification: 1 100 MPa1/235 °C2

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The following documents, in whole or in part, are normatively referenced in ISO 20785-3:2015 and are indispensable for its application. For dated references, only the edition cited applies. For undated references, the latest edition of the referenced document (including any amendments) applies.
ISO/IEC Guide 98‑1, Uncertainty of measurement ? Part 1: Introduction to the expression of uncertainty in measurement
ISO/IEC Guide 98‑3, Uncertainty of measurement ? Part 3: Guide to the expression of uncertainty in measurement (GUM:1995)
ISO 20785‑1, Dosimetry for exposures to cosmic radiation in civilian aircraft ? Part 1: Conceptual basis for measurements
ISO 20785‑2, Dosimetry for exposures to cosmic radiation in civilian aircraft ? Part 2: Characterization of instrument response

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This document provides the test requirements of three typical separation test methods, which are the combined separation test, the horizontal separation test, the individual falling separation test, for the separation between the launch vehicle (LV) and the spacecraft (or between stages of a prototype LV model). It also provides the requirements for the separation test unit, test data, test timing and sequence, pre-test simulation, test environment, exception handling, test results assessment, test documentation, test facilities, test installation, preliminary adjustment of the test setup, measurement and data acquisition. This document is applicable to test providers and interested parties to implement the separation test between the launch vehicle and the spacecraft.

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This document specifies processes, requirements and recommendations for the breakdown of project management structures, collectively called project breakdown structures, in terms of the various specification (i.e. requirements), functional, product, work, cost, business and organizational breakdown structures that are established and implemented to contribute to the success of a space programme, which is often composed of one or more projects. It specifies the various types of project breakdown structures and gives processes, requirements and guidance concerning the composition of these breakdown structures. This document is applicable to project breakdown structures for a project, including at the top level of a programme, i.e. level 0, as indicated in ISO 14300-1. It is intended to be used either by an independent developer as a partial basis for programme processes or as a basis for an agreement between a supplier and a customer. This document also provides descriptions of the kinds of project breakdown structures that are commonly useful in contributing to the success of a space project. Other project breakdown structures not described in this document also often contribute to the success of a space project.

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This document specifies the composition, functional and performance requirements for a payload interface of civil unmanned aircraft systems (UAS), with the maximum take-off mass of 0,25 kg to 25 kg which relates to level II through IV according to ISO 21895. This document is applicable to the design and manufacture of physically independent payload interfaces which connect an external payload to an unmanned aircraft (UA).

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This document applies to GSE when used in civil air transport as intended by the manufacturer and contains safety requirements relating to the equipment in general.
This document specifies the technical requirements to minimise the hazards listed in Clause 4 which can arise during the commissioning, operation and maintenance of GSE when used as intended including any reasonably foreseeable misuse by the manufacturer, when carried out in accordance with the specifications given by the manufacturer or his authorised representative. It also takes into account some requirements recognised as essential by authorities, aircraft and ground support equipment (GSE) manufacturers as well as airlines and handling agencies.
This part of EN 1915 is intended to be used in conjunction with EN 1915-2:2001+A1:2009, EN 1915-3:2004+A1:2009 (for self-propelled GSE) and EN 1915-4:2004+A1:2009, and with the relevant part of EN 12312 to give the requirements for the types of GSE within the scope of EN 12312.
When EN 12312 does not contain a relevant part for a GSE, EN 1915 (all parts) gives general requirements that may apply, although additional machine specific requirements, to be determined by the manufacturer, are likely to be required.
This part of EN 1915 does not apply to automotive parts approved for public vehicles in the EU and EFTA, when used on GSE for the purpose for which they are designed.
This part of EN 1915 does not establish additional requirements for the following:
a)   operation elsewhere than in an airport environment;
b)   operation in severe conditions, e.g. ambient temperature below -20 °C or over 50 °C, tropical or saturated salty atmospheric environment, strong magnetic or radiation field;
c)   operation subject to special rules, e.g. potentially explosive atmosphere except as regards operation in the vicinity of an aircraft fuel tank during fuelling operation;
d)   hazards caused by power supply other than from electrical networks;
e)   hazards occurring during construction, transportation, decommissioning and disassembly of the GSE;
f)   hazards caused by wind velocity in excess of the figures given in this document;
g)   direct contact with food stuffs;
h)   earthquake, flood, landslide, lightning and more generally any exceptional natural event;
i)   electromagnetic compatibility (EMC);
j)   hazards caused by noise and vibration, see EN 1915-3:2004+A1:2009 and EN 1915-4:2004+A1:2009.
While this standard gives some basic requirements for wireless remote controls, additional requirements will be necessary.
This part of EN 1915 is not applicable to GSE which are manufactured before the date of publication by CEN of this document.

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This document specifies the dimensions of self-locking, silver-coated bi-hexagonal nuts with MJ-thread in heat resisting nickel base alloy NI-P101HT for aerospace applications.
Maximum test temperature of the material 730 °C.

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This document provides a method for evaluating the resonance vibration frequency of the multi-copter unmanned aircraft (UA). This document specifies a method of designing the UA so as to avoid the resonance generated by the coincidence of the natural frequency of the UA body and the rotational frequency of the rotor. This document is applicable to multi-copter UA weighing less than 150 kg.

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This document sets forth the general rules applying to the justification of the definition of a product (tangible or intangible) and specifies the content of the Definition Justification Plan (DJP) and the Definition Justification Dossier (DJD).
It is applicable to all products designed and developed to fulfil the requirements of a customer expressed in a (Need) Technical Specification. Industrials are advised to apply the following principles to their own needs for justification in their internal customer/supplier relations.
Clause 5 presents the concepts and the documents associated with the justification of the definition and qualification processes.
Clause 6 summarizes the role and the contractual nature of the qualification of the definition.
Clause 7 gives details of the qualification of the definition process, while Clause 8 positions this process in the programme development logic.
The document also describes the differences between the justification and the qualification of the definition and other notions, such as verification, validation or acceptance (Clause 9).
Clause 10 is a guide to the establishment and maintenance of the documents associated with the justification of the definition and qualification processes. Information related to the certification process, even if it is out of the scope of the present document, is also presented in Clause 10, because this process has certain similarities with the justification of the definition and qualification process.
This document belongs to the documents supporting the EN 9200 relating to Project Management Specification.

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This document defines a number of conditions common to rectangular electrical modular connectors for receptacles, plugs and rack and panel, with interchangeable modules and continuous operating temperature 175 °C.

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This document specifies the characteristics of self-locking, floating, two lug anchor nuts, reduced series,
with counterbore, in steel, cadmium plated, MoS 2 lubricated.
Classification: 1 100 MPa1/235 °C2

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2021-04-21: This EN is based on ECSS-Q-ST-70-40C

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The Scope of the Standard remains unchanged.
This standard defines the requirements for selection, control, procurement and usage of EEE components for space projects.
This standard differentiates between three classes of components through three different sets of standardization requirements (clauses) to be met.
The three classes provide for three levels of trade-off between assurance and risk. The highest assurance and lowest risk is provided by class 1 and the lowest assurance and highest risk by class 3. Procurement costs are typically highest for class 1 and lowest for class 3. Mitigation and other engineering measures may decrease the total cost of ownership differences between the three classes. The project objectives, definition and constraints determine which class or classes of components are appropriate to be utilised within the system and subsystems.
a.   Class 1 components are described in Clause 4.
b.   Class 2 components are described in Clause 5
c.   Class 3 components are described in Clause 6.
The requirements of this document apply to all parties involved at all levels in the integration of EEE components into space segment hardware and launchers.

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2021-04-21: This EN is based on ECSS-Q-ST-60-13C Rev.1

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This document gives the basis for the measurement of ambient dose equivalent at flight altitudes for the evaluation of the exposures to cosmic radiation in civilian aircraft.

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This document specifies class codes to classify global navigation satellite system (GNSS) receivers. The class codes represent how signals transmitted from radionavigation satellites are processed. This document applies to all types of GNSS receiver devices. The class codes in this document are not applicable to the following items: — condition of radionavigation satellites; — radio propagation environment including multipath, masking and obstacle; — additional antenna of a receiver device; — additional application software in a receiver device.

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This document gives the basis for the measurement of ambient dose equivalent at flight altitudes for the evaluation of the exposures to cosmic radiation in civilian aircraft.

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This document, when used together with ISO 16119-1, specifies the requirements and the means for verification of the design and performance of unmanned aerial spraying systems (UASS) mounted on unmanned aircraft systems (UAS) for application of plant protection products (PPPs) in agriculture, forestry, turf and amenity areas, with regard to minimising the potential risk of environmental contamination during use, including misuse foreseeable by the UASS manufacturer. The requirements of this document take precedence over those of ISO 16119-1. The ISO 23117 series does not cover human safety aspects of UASS’s or safety aspects concerning UAS’s, remote pilots or bystanders. This document is not applicable to UASS mounted on UASs with a maximum take-off mass greater than 150 kg. This document is not applicable to UASSs manufactured before the date of its publication.

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This document defines the requirements for constructing a vertiport. This document applies to vertiports of type A (micro) as defined in ISO 5015-2.

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This document specifies test equipment and techniques used to identify interactions resulting from exposure of a material to an aerospace fluid. It is applicable for determining interactive reactions between propellants and materials used in the design, construction, and operation of propellant storage, transfer, and flight systems.

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This document specifies the requirements for a dependability (reliability, availability and maintainability) assurance programme for space projects. It defines the dependability requirements for space products as well as for system functions implemented in software, and the interaction between hardware and software. This document is applicable to all programme phases.

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This document specifies requirements for constant wear lifejackets for use by helicopter crew members and passengers in the event of a ditching or water impact, to ensure minimum levels of performance. It only applies to constant wear lifejackets for use by adults and that are intended to be manually inflated after leaving the helicopter.
Helicopter constant wear lifejackets are designed to be worn with or without a helicopter immersion suit and/or emergency breathing system.

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This technical document specifies requirements for immersion suits for use by helicopter crew members and passengers in the event of a ditching or water impact, to ensure minimum levels of performance. It applies to immersion suits for use by adults only.

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This document establishes a scheme for the marking of components (other than pipelines, hoses and fittings) used in aircraft hydraulic systems, so that the correct type of fluid is readily apparent during any assembly or testing operations in workshops. The marking is not intended to serve any purpose when a component is installed in an aircraft.

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This document specifies the composition, functional and performance requirements of flight controls for civil multicopter unmanned aircrafts (UAs) with the maximum take-off mass (MTOM) less than or equal to 25 kg corresponding to unmanned aircraft systems (UAS) at levels I, II, III and IV as graded in ISO 21895 which does not include fully autonomous flights. The flight control system in this document consists of flight control unit, navigation unit, fault diagnosis and management unit, flight planning, flight recorder, etc. This document is applicable to the design and manufacture of other UA flight control systems or subsystems.

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This document provides spacecraft (SC) organizations with the general format for presenting the interface requirement document (IRD) for launch vehicle services. The IRD provides a list of the major technical requirements spacecraft agencies provide to launch vehicle (LV) agencies when submitting an application for launch services. The IRD addresses the definition of the SC mission, the mechanical and electrical interfaces, the overall environment requirements (mechanical, thermal, cleanliness, radio-electrical), the SC development and test programme and, finally, launch range facilities and support requirements. This document is applicable to all existing commercial LV and related launch facilities so as to permit SC contractors to prepare a single interface requirement document for a given SC mission, independently of the LV contractor to be selected. The IRD, as defined in this document, includes the basic SC input data needed by LV agencies to prepare the interface control document defined in ISO 15863.

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This document provides technical requirements and test methods for small unmanned aircraft electric energy systems (EESs). This document applies to the EES of small unmanned aircrafts (UAs) with the maximum take-off mass (MTOM) less than 25 kg corresponding to unmanned aircraft systems (UASs) at level I, II, III and IV as graded in ISO 21895:2020, and with secondary lithium batteries. This document can apply to new type of batteries to be used in the UA electric energy system in the future.

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This document specifies test methods for civil electric multi-copter unmanned aircraft systems (UAS). This document is intended to be a general standard for testing the overall UAS functionality with the support of subsystems. It is applicable to the category of civil electric multi-copter UAS with maximum take-off mass (MTOM) level I to level V according to ISO 21895. The configuration control and subsystem (e.g. energy system and flight control system tests) test methods are out of the scope of this document. In addition, test methods for operations in snow and icing conditions are not included either, manufacturers have procedures identified to cope with flight in those conditions.

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This document defines the primary space debris mitigation requirements applicable to all elements of unmanned systems launched into, or passing through, near-Earth space, including launch vehicle orbital stages, operating spacecraft and any objects released as part of normal operations.

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This document is dedicated to establishing a common understanding of UTM core functions and functional structure. It provides a detailed description of the UTM system layer given in the UTM Framework. This document excludes: — role-sharing among entities constituting UTM, which is left to implementations; — technical methodology of communication or data transaction among core functions; — business model of players engaging in a function of UTM.

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This document defines the generic concept and common framework of unmanned aircraft system (UAS) remote identification, which is mainly used to electronically identify an in-flight unmanned aircraft (UA). This document sets the minimum performance standards for direct remote identification. This document does not cover requirements for modules installed in UA or requirements for network remote identification. This document does not cover the identity of other information technology (IT) entities, such as the station of the remote pilot, the workstation of the fleet manager or any other connected entity.

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This document specifies process requirements for project reviews as a set of required functions. It establishes requirements and recommendations on the function inputs, outputs, mechanisms and controlling conditions. This document specifies the responsibilities of a review board and gives guidance concerning review board composition. This document also provides descriptions of the kinds of reviews that are commonly useful in assuring the success of a space project. This document is applicable to status reviews for a project at any level within a larger project, as well as for major milestone reviews at the top level of a major project. It is intended to be used either by an independent developer as a basis for enterprise processes, or as a basis for an agreement between a supplier and a customer. It is intended for use in implementing the review requirements of ISO 14300-1, and ISO 14300-2, ISO 15865 and such other space systems and operations standards that require formal reviews.

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This document contains requirements and guidelines for the utilization of off-the-shelf (OTS) items, their selection, acquisition, integration, qualification and implementation related to a space product or system. This document doesn't cover piece parts and materials, such as electrical, electronic and electromechanical (EEE) parts, thermocouples, rivets, fasteners, connectors, fittings, adhesives, insulation, wiring and plumbing.

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This document specifies a list of procurement specifications and standards for welding products authorized for the welding of parts.

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This document is applicable to the marking of aerospace vehicle electrical wires and cables using ultraviolet (UV) lasers.
This document specifies the process requirements for the implementation of UV laser marking of aerospace electrical wire and cable and fibre optic cable to achieve an acceptable quality mark using equipment designed for UV laser wire marking of identification codes on aircraft wire and cable subject to EN 3475-100, Aerospace series - Cables, electrical, aircraft use - Test methods - Part 100: General. Wiring specified as UV laser markable and which has been marked in accordance with this document will conform to the requirements of EN 3838.
This document is applicable to the marking of airframe electrical wires and cables using ultraviolet (UV) lasers. The laser process practices defined in this document are mandatory.

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This document specifies a method of measuring the tensile properties of stranded conductors, strands, solid conductors and braids.
When required, it can be used also on finished cables.
It is intended to be used together with EN 3475-100.

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This document describes a communication model and requirements for unmanned aircraft area network (UAAN), which is a wireless distributed communication network for units related with UA services in level II. It describes: — the communication structure and operation; — the purpose of the three types of communication and related services; — the interoperation of the three types of communication; — the interworking with upper layers.

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This document specifies communication protocols for the physical and data link layer for control communication, which is wireless distributed communication network for units related with unmanned aircrafts (UAs) in level II. This document describes control communication, which is one-to-one communication between a UA and a controller.

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