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49 Aircraft and space vehicle engineering
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EVS-EN 4709-004:2026
Aerospace series - Unmanned Aircraft Systems - Part 004: Lighting requirements
Scope:
This document will provide means of compliance to cover lighting related requirements for Parts 2 to 4 of the Annex to the Commission Delegated Regulation (EU) 2019/945 on unmanned aircraft and on third country UAS operators.
The purpose is to be able to verify that an UA is equipped with lights:
— for the controllability of the UA (the effectiveness of those lights is not part of the lighting requirement but is covered by the controllability requirement; therefore, its verification is covered by the clause addressing the controllability requirement of EN 4709-001:2026);
— that ensure conspicuity of the unmanned aircraft at night (see 3.45 of ISO 21384-4:2025), the design of the light shall allow a person on the ground to distinguish a UA from a manned aircraft.
This document addresses:
— definition of types, technical requirements, and technical parameters of UA lights (e.g. position of lights for different UA categories, intensity for different operation modes);
— definition of purpose, test procedures, requirements, and compliance rules to evaluate UA lights
The purpose is to be able to verify that an UA is equipped with lights:
— for the controllability of the UA (the effectiveness of those lights is not part of the lighting requirement but is covered by the controllability requirement; therefore, its verification is covered by the clause addressing the controllability requirement of EN 4709-001:2026);
— that ensure conspicuity of the unmanned aircraft at night (see 3.45 of ISO 21384-4:2025), the design of the light shall allow a person on the ground to distinguish a UA from a manned aircraft.
This document addresses:
— definition of types, technical requirements, and technical parameters of UA lights (e.g. position of lights for different UA categories, intensity for different operation modes);
— definition of purpose, test procedures, requirements, and compliance rules to evaluate UA lights
Base documents:
EN 4709-004:2026
EVS-EN 4709-006:2026
Aerospace series - Unmanned Aircraft Systems - Part 006: Means to terminate flight, requirements, and verification
Scope:
This document provides technical specification and verification methods to support compliance with Commission Delegated Regulation (EU) 2019/945 of 12 March 2019 on unmanned aircraft systems and on third-country operators of unmanned aircraft systems.
This part provides requirements, test methods and pass criteria for the means to terminate flight (flight termination) for unmanned aircraft systems, in particular addressing:
— safety related aspects of the architecture;
— descent performance;
— means to reduce the effects of impact on ground; and
— manufacturer’s instructions.
Even if security, including IT security, may be useful from an operational point of view, it falls outside the scope of this document.
An activation of the means to terminate the flight by a visual observer is also outside the scope of this document.
This document provides voluntary means of demonstrating compliance with the requirements laid out in Regulation (EU) 2019/945.
Additional hazards that occur from the characteristics of the payload are excluded and are, conversely, under the responsibility of the UAS manufacturer and UAS operator.
This part provides requirements, test methods and pass criteria for the means to terminate flight (flight termination) for unmanned aircraft systems, in particular addressing:
— safety related aspects of the architecture;
— descent performance;
— means to reduce the effects of impact on ground; and
— manufacturer’s instructions.
Even if security, including IT security, may be useful from an operational point of view, it falls outside the scope of this document.
An activation of the means to terminate the flight by a visual observer is also outside the scope of this document.
This document provides voluntary means of demonstrating compliance with the requirements laid out in Regulation (EU) 2019/945.
Additional hazards that occur from the characteristics of the payload are excluded and are, conversely, under the responsibility of the UAS manufacturer and UAS operator.
Base documents:
EN 4709-006:2026
EVS-EN 4709-005:2026
Aerospace series - Unmanned Aircraft Systems - Part 005: Verification method for the Geocaging function
Scope:
This document specifies requirements, test methods and pass criteria for the:
— implemented static geocage function used to prevent the UA from breaching the horizontal and vertical limits of the planned operational volume;
— information to be provided in the manufacturer’s instructions describing this function, its limits and the required size of the contingency volume after accounting the errors, reaction time and corrections.
This document does not cover the dynamic geocage function.
In addition, this document only covers the termination of the flight of the UA by the geo-caging function when breaching the OV. It does not address the compliance to the technical requirements imposed by Regulation (EU) 2019/945 on the Flight Termination System which are fully addressed by standard EN 4709-006, including the automatic triggering of the termination performed independently from the geo-caging function.
— implemented static geocage function used to prevent the UA from breaching the horizontal and vertical limits of the planned operational volume;
— information to be provided in the manufacturer’s instructions describing this function, its limits and the required size of the contingency volume after accounting the errors, reaction time and corrections.
This document does not cover the dynamic geocage function.
In addition, this document only covers the termination of the flight of the UA by the geo-caging function when breaching the OV. It does not address the compliance to the technical requirements imposed by Regulation (EU) 2019/945 on the Flight Termination System which are fully addressed by standard EN 4709-006, including the automatic triggering of the termination performed independently from the geo-caging function.
Base documents:
EN 4709-005:2026
EVS-EN 4709-007:2026
Aerospace series - Unmanned Aircraft Systems - Part 007: General product requirements for UAS of classes C5 and C6
Scope:
This document provides technical specification and specifies verification methods to support compliance with Commission Delegated Regulation (EU) 2019/945 of 12 March 2019 amended by Commission Delegated Regulation (EU) 2020/1058 of 27 April 2020 on unmanned aircraft systems (UAS) and on third-country operators of unmanned aircraft systems.
This includes compliance with product requirements for UAS intended to be operated under a standard scenario in the ‘specific’ category (class C5 and class C6 UAS).
This document is only applicable for unmanned aircraft (UA) with energy sources based on electro-chemical technologies.
Additional hazards that occur from the characteristics of the payload are excluded and are under the responsibility of the manufacturer and operator.
The present document covers requirements expressed in Annex, Part 16 requirements (1), (3), (4) and (6) and Part 17 requirements (1), (3), (6) and (7) of the Regulation 2020/1058.
This includes compliance with product requirements for UAS intended to be operated under a standard scenario in the ‘specific’ category (class C5 and class C6 UAS).
This document is only applicable for unmanned aircraft (UA) with energy sources based on electro-chemical technologies.
Additional hazards that occur from the characteristics of the payload are excluded and are under the responsibility of the manufacturer and operator.
The present document covers requirements expressed in Annex, Part 16 requirements (1), (3), (4) and (6) and Part 17 requirements (1), (3), (6) and (7) of the Regulation 2020/1058.
Base documents:
EN 4709-007:2026
EVS-EN 6046:2026
Aerospace series - Bearing, spherical, plain, in corrosion resisting steel - Narrow series - Dimensions and loads - Inch series
Scope:
This document specifies the characteristics of inch based spherical plain bearing, metal to metal, in corrosion resisting steel, narrow series.
They are intended for use in fixed or moving parts of the aircraft structure and their control mechanisms.
They are used in the temperature range as determined by the grease capability as below:
- code A: greased as per MIL-PRF-23827 Type I, operating temperature range −73 °C to 121 °C;
- code B: greased as per MIL-PRF-81322, operating temperature range −54 °C to 177 °C.
The range of application for bearings lubricated with grease per code A is limited to 121 °C.
In both cases the spherical surface of the outer or inner ring are provided with a dry-film lubricant as per MIL-PRF-46010 or equivalent (anti-seizing protection).
The slide hole treatment either at the outer ring or inner ring.
They are intended for use in fixed or moving parts of the aircraft structure and their control mechanisms.
They are used in the temperature range as determined by the grease capability as below:
- code A: greased as per MIL-PRF-23827 Type I, operating temperature range −73 °C to 121 °C;
- code B: greased as per MIL-PRF-81322, operating temperature range −54 °C to 177 °C.
The range of application for bearings lubricated with grease per code A is limited to 121 °C.
In both cases the spherical surface of the outer or inner ring are provided with a dry-film lubricant as per MIL-PRF-46010 or equivalent (anti-seizing protection).
The slide hole treatment either at the outer ring or inner ring.
Base documents:
EN 6046:2026
Replaces:
EVS-EN 6046:2020
EVS-EN 3475-701:2026
Aerospace series - Cables, electrical, aircraft use - Test methods - Part 701: Strippability and adherence of insulation to the conductor
Scope:
This document specifies methods of measuring the strippability and adherence of the insulation to a conductor of a finished cable.
When a particular method is not specified in the detail product specification, method A is the default test method.
Method B is suitable for wires insulated with materials showing a low adhesion to the conductor due to the poor repeatability of the test method A with this type of wires.
This document is intended to be used together with EN 3475-100.
When a particular method is not specified in the detail product specification, method A is the default test method.
Method B is suitable for wires insulated with materials showing a low adhesion to the conductor due to the poor repeatability of the test method A with this type of wires.
This document is intended to be used together with EN 3475-100.
Base documents:
EN 3475-701:2026
Replaces:
EVS-EN 3475-701:2017
EVS-EN 2133:2026
Aerospace series - Cadmium plating of steels with specified tensile strength ≤ 1 450 MPa, copper, copper alloys and nickel alloys
Scope:
This document specifies the electrolytic cadmium plating of parts and fasteners in steel of tensile strength UTS ≤ 1 450 MPa, copper, copper alloys and nickel alloys, whose temperature in service does not exceed 235 °C.
Base documents:
EN 2133:2026
Replaces:
EVS-EN 2133:2020
EVS-EN 4500-005:2026
Aerospace series - Metallic materials - Rules for drafting and presentation of material standards - Part 005: Specific rules for steels
Scope:
The EN 4500 series specifies the rules for the drafting and presentation of metallic material standards for aerospace applications.
This Part 005 specifies the "Specific rules for steels".
This Part 005 specifies the "Specific rules for steels".
Base documents:
EN 4500-005:2026
Replaces:
EVS-EN 4500-005:2024
EVS-EN 4500-002:2026
Aerospace series - Metallic materials - Rules for drafting and presentation of material standards - Part 002: Specific rules for aluminium, aluminium alloys and magnesium alloys
Scope:
The EN 4500 series specifies the rules for the drafting and presentation of metallic material standards for aerospace applications.
This Part 002 specifies the "Specific rules for aluminium, aluminium alloys and magnesium alloys".
This Part 002 specifies the "Specific rules for aluminium, aluminium alloys and magnesium alloys".
Base documents:
EN 4500-002:2026
Replaces:
EVS-EN 4500-002:2024
IEC TR 62240-2:2026
Process management for avionics - Electronic components capability in operation - Part 2: Semiconductor microcircuit lifetime
Scope:
IEC TR 62240-2:2026 focuses on original equipment manufacturers (OEMs) using commercial off the shelf (COTS) semiconductor microcircuits for high performance, high reliability and long duration applications. This document supports OEMs in the preparation and maintenance of their semiconductor electronic component management plan (ECMP). IEC TR 62240-2:2026 describes a process and a method for selecting digital semiconductor microcircuits by ensuring that their lifetime is compatible with the requirements of aerospace, defence and high performance (ADHP) applications (generally in connection with functional environments). Methods and guidelines are provided to assess the long-term reliability of COTS semiconductor microcircuits in such applications; they mainly apply during the electronic design phase when selecting semiconductor microcircuits and assessing the application reliability. Moreover, this document focuses on the intrinsic wear-out and the lifetime of COTS semiconductor microcircuits processed of less than or equal to 90 nm feature size (also called deep sub-micron (DSM) semiconductor microcircuits) and puts aside, at this time, packaging wear-out and random failure mechanisms. In this view, physics of failure (PoF) is at the heart of the approach.
This edition includes the following significant technical changes with respect to the previous edition:
a) introduction of an additional alternative path and approach where lifetime is assessed by the original component manufacturer based on user or original equipment manufacturer microcircuit mission profile;
b) update of Figure 1 with regard to the introduction of the additional alternative path & approach;
c) removal of the mention of SiC & GaN technologies from the considerations in 4.2.2 as the Scope indicates that the principles (process and method) described in this document can be applied to all types of semiconductor technologies.
This edition includes the following significant technical changes with respect to the previous edition:
a) introduction of an additional alternative path and approach where lifetime is assessed by the original component manufacturer based on user or original equipment manufacturer microcircuit mission profile;
b) update of Figure 1 with regard to the introduction of the additional alternative path & approach;
c) removal of the mention of SiC & GaN technologies from the considerations in 4.2.2 as the Scope indicates that the principles (process and method) described in this document can be applied to all types of semiconductor technologies.
Base documents:
Replaces:
IEC TR 62240-2:2018
Replaced standards
EVS-EN 3475-701:2017
Aerospace series - Cables, electrical, aircraft use - Test methods - Part 701: Strippability and adherence of insulation to the conductor
Scope:
This European Standard specifies methods of measuring the strippability and adherence of the insulation to a conductor of a finished cable.
When a particular method is not specified in the detail product specification, method A shall be used.
Method B is recommended for wires insulated with materials showing a Low adhesion to the conductor due to the poor repeatability of the test Method A with this type of wires.
It shall be used together with EN 3475-100.
When a particular method is not specified in the detail product specification, method A shall be used.
Method B is recommended for wires insulated with materials showing a Low adhesion to the conductor due to the poor repeatability of the test Method A with this type of wires.
It shall be used together with EN 3475-100.
Base documents:
EN 3475-701:2017
Replaced:
EVS-EN 3475-701:2026
IEC TR 62240-2:2018
Process management for avionics – Electronic components capability in operation – Part 2: Semiconductor microcircuit lifetime
Scope:
IEC TR 62240-2:2018(E) describes a process and a method for selecting digital semiconductor microcircuits by ensuring that their lifetime is compatible with the requirements of aerospace, defence and high performance (ADHP) applications (generally in connection with functional environments). Methods and guidelines are provided to assess the long term reliability of COTS semiconductor microcircuits in such applications; they mainly apply during the electronic design phase when selecting semiconductor microcircuits and assessing the application reliability. focuses on original equipment manufacturers (OEMs) using commercial off the shelf (COTS) semiconductor microcircuits for high performance, high reliability and long duration applications. This document supports OEMs in the preparation and maintenance of their semiconductor electronic component management plan (ECMP).
Base documents:
Replaced:
IEC TR 62240-2:2026
EVS-EN 6046:2020
Aerospace series - Bearing, spherical, plain, in corrosion resisting steel - Narrow series - Dimensions and loads - Inch series
Scope:
This European standard specifies the characteristics of inch based spherical plain bearing, metal to metal, in corrosion resisting steel, narrow series.
They are intended for use in fixed or moving parts of the aircraft structure and their control mechanisms.
They shall be used in the temperature range as determined by the grease capability as below:
- code A: grease as per MIL PRF 23827 Type I, operating temperature range −73 °C to 121 °C;
- code B: grease as per MIL PRF 81322, operating temperature range −54 °C to 177 °C.
The range of application for bearings lubricated with grease per code A is limited to 121 °C.
In both cases the spherical surface of the outer or inner ring have to be provided with a dry film lubricant as per MIL PRF 46010 or equivalent (anti seizing protection).
They are intended for use in fixed or moving parts of the aircraft structure and their control mechanisms.
They shall be used in the temperature range as determined by the grease capability as below:
- code A: grease as per MIL PRF 23827 Type I, operating temperature range −73 °C to 121 °C;
- code B: grease as per MIL PRF 81322, operating temperature range −54 °C to 177 °C.
The range of application for bearings lubricated with grease per code A is limited to 121 °C.
In both cases the spherical surface of the outer or inner ring have to be provided with a dry film lubricant as per MIL PRF 46010 or equivalent (anti seizing protection).
Base documents:
EN 6046:2020
Replaced:
EVS-EN 6046:2026
EVS-EN 2133:2020
Aerospace series - Cadmium plating of steels with specified tensile strength ≤ 1 450 MPa, copper, copper alloys and nickel alloys
Scope:
This document specifies the electrolytic cadmium plating of parts and fasteners in steel of tensile strength UTS ≤ 1 450 MPa, copper, copper alloys and nickel alloys, whose temperature in service does not exceed 235 °C.
Base documents:
EN 2133:2020
Replaced:
EVS-EN 2133:2026
EVS-EN 4500-006:2024
Aerospace series - Metallic materials - Rules for drafting and presentation of material standards - Part 006: Specific rules for filler metals for brazing
Scope:
The EN 4500 series specifies the rules for the drafting and presentation of metallic material standards for aerospace applications. This Part 006 specifies the "Specific rules for filler metals for brazing".
Base documents:
EN 4500-006:2024
Replaced:
EVS-EN 4500-006:2026
EVS-EN 4500-001:2024
Aerospace series - Metallic materials - Rules for drafting and presentation of material standards - Part 001: General rules
Scope:
The EN 4500 series specifies the rules for the drafting and presentation of metallic material standards for aerospace applications.
This Part 001 specifies the "General rules" framework valid for all parts.
This Part 001 specifies the "General rules" framework valid for all parts.
Base documents:
EN 4500-001:2024
Replaced:
EVS-EN 4500-001:2026
EVS-EN 4500-002:2024
Aerospace series - Metallic materials - Rules for drafting and presentation of material standards - Part 002: Specific rules for aluminium, aluminium alloys and magnesium alloys
Scope:
The EN 4500 series specifies the rules for the drafting and presentation of metallic material standards for aerospace applications.
This Part 002 specifies the "Specific rules for aluminium, aluminium alloys and magnesium alloys".
This Part 002 specifies the "Specific rules for aluminium, aluminium alloys and magnesium alloys".
Base documents:
EN 4500-002:2024
Replaced:
EVS-EN 4500-002:2026
EVS-EN 4500-003:2024
Aerospace series - Metallic materials - Rules for drafting and presentation of material standards - Part 003: Specific rules for heat resisting alloys
Scope:
The EN 4500 series specifies the rules for the drafting and presentation of metallic material standards for aerospace applications. This Part 003 specifies the "Specific rules for heat resisting alloys".
Base documents:
EN 4500-003:2024
Replaced:
EVS-EN 4500-003:2026
EVS-EN 4500-004:2024
Aerospace series - Metallic materials - Rules for drafting and presentation of material standards - Part 004: Specific rules for titanium and titanium alloys
Scope:
The EN 4500 series specifies the rules for the drafting and presentation of metallic material standards for aerospace applications. This Part 004 specifies the "Specific rules for titanium and titanium alloys".
Base documents:
EN 4500-004:2024
Replaced:
EVS-EN 4500-004:2026
EVS-EN 4500-005:2024
Aerospace series - Metallic materials - Rules for drafting and presentation of material standards - Part 005: Specific rules for steels
Scope:
The EN 4500 series specifies the rules for the drafting and presentation of metallic material standards for aerospace applications. This Part 005 specifies the "Specific rules for steels".
Base documents:
EN 4500-005:2024
Replaced:
EVS-EN 4500-005:2026