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Easy Access Rules for Normal-Category Aeroplanes (CS-23)

CS-23 Amendment 6 / AMC & GM Issue 5 · EASA · 2026

EU reuse — source acknowledged · EASAEasy Access Rules

Overview

The consolidated EASA certification specifications and acceptable means of compliance for normal-category aeroplanes (CS-23) — the design and airworthiness requirements covering most piston singles, twins and light turboprops.

Publisher
EASA
Document
CS-23 Amendment 6 / AMC & GM Issue 5
Year
2026
Pages
118
Chapters
13

Key points

  • The Easy Access Rules (EAR) for Normal-Category Aeroplanes (CS-23) are consolidated versions of EU regulations and EASA decisions.
  • The EAR books are available in PDF, dynamic online formats, and XML for easy access and navigation.
  • This document is not an official publication and EASA accepts no liability for its use.
  • The content is organized into certification specifications (CSs), acceptable means of compliance (AMC), and guidance material (GM), each color-coded for identification.
  • The document is regularly updated to incorporate amendments and feedback can be sent to EASA.
Frequently asked questions
What is the purpose of the Easy Access Rules?

The Easy Access Rules aim to provide stakeholders with an updated, consolidated, and easy-to-read publication of aviation safety rules.

How often are the Easy Access Rules updated?

The EAR books are regularly updated following the adoption of an official publication.

What formats are the Easy Access Rules available in?

The EAR books are available in PDF format, as dynamic online publications, and in XML format.

Is the document considered an official publication?

No, this document is not an official publication and EASA accepts no liability for damage resulting from its use.

How is the content of the document organized?

The content is organized into certification specifications (CSs), acceptable means of compliance (AMC), and guidance material (GM), with each element color-coded.

EASA eRules

Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) EASA eRules

EASA E R ULES

EASA eRules: aviation rules for the 21st century Rules are the core of the EU civil aviation system. The aim of the EASA eRules project is to make them accessible to stakeholders in an efficient and reliable way.

EASA eRules is a comprehensive, single system for structuring, sharing, and storing of rules. It is the single, easy - access online database for all aviation safety rules applicable to persons and organisations subject to Basic Regulation ( Regulation (EU) 2018/1139 ).

The Easy Access Rules (EAR) are the output of the eRules project. The EAR books are consolidated versions of those rules, combining EU regulations with the related EASA Executive Director (ED) decisions in an easy - to - read format with advanced navigation featur es through links and bookmarks.

The EAR books are regularly updated, following the adoption of an official publication.

The EAR books are available: — in PDF format; — as dynamic online publications with optimised performance for fast and seamless navigation, permalinks of all rule articles, as well as a wide range of functionalities, such as filters to obtain regulatory material tailored to one’s needs, a search function through the table of contents to quickly access the relevant sections, and easy navigation for computers, tablets, and mobiles; and — in XML (machine - readable ) format that can be easily processed and automated by recipients, producing output that is compatible and can be synchronised with local applications, search databases, etc.

The EASA eRules system is developed and implemented in close cooperation with the Member States and aviation industry to ensure that all its capabilities are relevant and effective.

Published May 2026 Copyright notice © European Union, 1998 - 202 6 Unless otherwise specified, you can re - use the legal documents published in EUR - Lex for commercial or non - commercial purposes […] ('© European Union, http://eur - lex.europa.eu , 1998 - 202 6 ') .

The published date represents the date when the consolidated version of the EAR book was generated.

Euro - Lex, Important Legal Notice: http://eur - lex.europa.eu/content/legal - notice/legal - notice.html .

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Disclaimer

Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) Disclaimer

D ISCLAIMER

This document is issued by the European Union Aviation Safety Agency (referred to as both ‘EASA’ and ‘the Agency’) to provide its stakeholders with an updated, consolidated, and easy - to - read publication.

It has been prepared by putting together the officia lly published EU regulations with the related EASA certification specifications (CSs), acceptable means of compliance (AMC) and guidance material (GM) (including their amendments) adopted so far. However, this document is not an official publication, and E ASA accepts no liability for damage of any kind resulting from the risks inherent in its use.

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Note from the editor

Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) Note from the editor

N OTE FROM THE EDITOR

The content of this document is arranged as follows: certification specifications (CSs), followed by the related acceptable means of compliance ( AMC) and guidance material (GM ).

All elements (i.e. CSs, AMC and GM ) are colour - coded and can be identified according to the illustration below. The EASA Executive Director (ED) decision through which the CS, AMC, or GM was introduced or last amended is indicated below the CS, AMC, or GM title in italics .

Certification specification

ED decision

Acceptable means of compliance

ED decision

Guidance material

ED decision This document will be updated regularly to incorporate further amendments.

The format of this document has been adjusted to make it user - friendly and for reference purposes.

Any comments should be sent to erules@easa.europa.eu .

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Incorporated amendments

Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) Incorporated amendments

I NCORPORATED A MENDMENTS

CS ( ED DECISIONS )

Incorporated ED Decision CS/AMC Issue No, Amendment No Applicability date ED Decision 2003/14/RM CS - 23 / Initial i ssue 1 4/11 /200 3 ED Decision 2009/001/R CS - 23/ Amendment 1 12/2/2009 ED Decision 2010/008/R CS - 23/ Amendment 2 28/9/2010 ED Decision 2012/012/R CS - 23/ Amendment 3 20/7/2012 ED Decision 2015/018/R CS - 23/ Amendment 4 17/7/2015 ED Decision 2017/013/R CS - 23/ Amendment 5 15/8/2017 ED Decision 2023/002/R CS - 23/ Amendment 6 8 /3/ 2023

AMC/GM (ED DECISIONS )

Incorporated ED Decision AMC /GM Issue No, Amendment No Applicability date ED Decision 2017/025/R AMC & GM to CS - 23/ Issue 1 21/12/2017 ED Decision 2019/020/R AMC & GM to CS - 23/ Issue 2 9/10/2019 ED Decision 2020/006/R AMC & GM to CS - 23/ Issue 3 1/1/2021 ED Decision 2023/002/R AMC & GM to CS - 23/ Issue 4 8/3/2023 ED Decision 2025/019/R AMC & GM to CS - 23/ Issue 4 - 1/10/2025 correction ED Decision 2026/003/R AMC & GM to C S - 23 / Issue 5 16/4/2026 Note: To access the official versions , please click on the hyper links provided above.

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Table of contents

Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) Table of contents

T ABLE OF CONTENTS

SUBPART B — FLIGHT ................................ ................................ ... 30 Powered by EASA eRules Page 7 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) Table of contents AMC1 23.2120 Climb requirements ................................ ................................ ... 34 AMC2 23.2120 Climb requirements ................................ ................................ ... 34 AMC3 23.2120 Climb requirements ................................ ................................ ... 34 Powered by EASA eRules Page 8 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) Table of contents CS 23.2165 Performance and flight characteristics requirements for flight AMC1 23.2165 Performance and flight characteristics requirements for flight in icing conditions ................................ ................................ ................................ . 43 AMC2 23.2165 Performance and flight characteristics requirements for flight in icing conditions ................................ ................................ ................................ . 43 AMC3 23.2165 Performance and flight characteristics requirements for flight in icing conditions ................................ ................................ ................................ . 43 Powered by EASA eRules Page 9 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) Table of contents CS 23.2230 Limit and ultimate loads ................................ ................................ .. 54 AMC1 23.22 30 Limit and ultimate loads ................................ ................................ ... 54 AMC2 23.2230 Limit and ultimate loads ................................ ................................ ... 54 AM C3 23.2230 Limit and ultimate loads ................................ ................................ ... 54 CS 23.2260 Materials and processes ................................ ................................ .. 61 AMC1 23.22 60 Materials and processes ................................ ................................ ... 62 AMC2 23.2260 Materials and processes ................................ ................................ ... 62 AM C3 23.2260 Materials and processes ................................ ................................ ... 62 Powered by EASA eRules Page 10 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) Table of contents CS 23.2265 Special factors of safety ................................ ................................ ... 62 AMC1 23.2305 Landing gear systems ................................ ................................ . 69 AMC2 23.2305 Landing gear systems ................................ ................................ . 69 AM C3 23.2305 Landing gear systems ................................ ................................ . 69 Powered by EASA eRules Page 11 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) Table of contents

SUBPART E — POWERPLANT INSTALLATION ................................ . 78

Powered by EASA eRules Page 12 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) Table of contents CS 23.2430 Powerplant installation, energy storage and distribution AMC1 23.2430 Powerplant installation, energy storage and distribution systems AMC2 23.2430 Powerplant installation, energy storage and distribution systems AM C3 23.2430 Powerplant installation, energy storage and distribution systems CS 23.2445 Powerplant installation information ................................ .. 93 CS 23.2500 General requirements on systems and equipment function 94 Powered by EASA eRules Page 13 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) Table of contents Powered by EASA eRules Page 14 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) Table of contents CS 23.2555 Installation of recorders (e.g. cockpit voice recorders and AMC1 23.2555 Installation of recorders (e.g. cockpit voice reco rders and flight AMC2 23.2555 Installation of recorders (e.g. cockpit voice recorders and flight AMC3 23.2555 Installation of recorders (e.g. cockpit voice recorders and flight

SUBPART G — FLIGHT CREW INTERFACE AND OTHER INFORMATION

Powered by EASA eRules Page 15 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) Table of contents AMC1 23.2625 Instructions for Continued Airworthiness ................................ . 118 AMC2 23.2625 Instructions for Continued Airworthiness ................................ . 118 AM C3 23.2625 Instructions for Continued Airworthiness ................................ . 118 Powered by EASA eRules Page 16 of 118 | May 2026

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Preamble

Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) Preamble

P REAMBLE

ED Decision 202 6 / 003 /R CS - 23 Amendment 6 and AMC & GM to CS - 23 Issue 5 The following is a list of paragr aphs affected by this amendment: Subpart A GM1 23.2010 Accepted means of compliance Amended GM2 23.2010 Accepted means of compliance Amended GM3 23.2010 Accepted means of compliance Amended Subpart B AMC1 23.2100 Mass and centre of gravity Amended AMC1 23.2105 Performance data Amended AMC1 23.2110 Stall speed Amended AMC1 23.2115 Take - off performance Amended AMC1 23.2120 Climb requirements Amended AMC1 23.2125 Climb information Amended AMC1 23.2130 Landing Amended AMC1 23.2135 Controllability Amended AMC1 23.2140 Trim Amended AMC1 23.2145 Stability Amended AMC1 23.2150 Stall characteristics, stall warning, Amended and spins AMC2 23.2150 Stall characteristics, stall warning, Amended and spins AMC1 23.2155 Ground - and water - handling Amended characteristics AMC1 23.2160 Vibration, buffeting, and high - speed Amended characteristics AMC1 23.2165 Performance and flight Amended characteristics requirements for flight in icing conditions AMC1 23.2170 Operating limitations Amended Subpart C AMC1 23.2200 Structural design envelope Amended AMC1 23.2205 Interaction of systems and structures Amended AMC1 23.2210 Structural - design loads Amended AMC1 23.2215 Flight load conditions Amended AMC2 23.2215 Flight load conditions Amended AMC3 23.2215 Flight load conditions Amended AMC1 23.2220 Ground and water load conditions Amended AMC1 23.2225 Component loading conditions Amended AMC1 23.2230 Limit and ultimate loads Amended AMC1 23.2235 Structural strength Amended AMC1 23.2240 Structural durability Amended AMC1 23.2245 Aeroelasticity Amended AMC1 23.2250 Design and construction principles Amended AMC1 23.2255 Protection of structure Amended Powered by EASA eRules Page 17 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) Preamble AMC1 23.2260 Materials and processes Amended AMC1 23.2265 Special factors of safety Amended AMC1 23.2270 Emergency conditions Amended Subpart D AMC1 23.2300 Flight control systems Amended AMC1 23.2305 Landing gear systems Amended AMC1 23.2310 Buoyancy for seaplanes and Amended amphibians AMC1 23.2315 Means of egress and emergency exits Amended AMC1 23.2320 Occupant physical environment Amended AMC1 23.2325 Fire protection Amended AMC1 23.2330 Fire protection in designated fire Amended zones AMC1 23.2335 Lightning protection Amended AMC1 23.2340 Design and construction information Amended Subpart E AMC1 23.2400 Powerplant installation Amended AMC1 23.2405 Power or thrust control systems Amended AMC1 23.2410 Powerplant installation hazard Amended assessment AMC1 23.2415 Powerplant installation ice Amended protection AMC1 23.2425 Powerplant operational Amended characteristics AMC1 23.2430 Powerplant installation, energy Amended storage and distribution systems AMC1 23.2435 Powerplant installation support Amended systems AMC1 23.2440 Powerplant installation fire Amended protection AMC1 23.2445 Powerplant installation information Amended Subpart F AMC1 23.2500 General requirements on systems Amended and equipment function GM 23.2500(b) General requirements on systems Removed and equipment function AMC1 23.2505 General requirements on equipment Amended installation AMC1 23.2510 Equipment, systems, and Amended installations AMC1 23.2515 Electrical and electronic system Amended lightning protection AMC1 23.2520 High - intensity radiated fields (HIRF) Amended protection AMC1 23.2525 System power generation, storage, Amended and distribution AMC1 23.2530 External and cockpit lighting Amended AMC1 23.2535 Safety equipment Amended AMC1 23.2540 Flight in icing conditions Amended Powered by EASA eRules Page 18 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) Preamble AMC1 23.2545 Pressurised systems elements Amended AMC1 23.2555 Installation of recorders (e.g. cockpit Amended voice recorders and flight data recorders) Subpart G AMC1 23.2600 Flight crew compartment Amended AMC1 23.2605 Installation and operation Amended information AMC1 23.2610 Instrument markings, control Amended markings and placards AMC1 23.2615 Flight, navigation, and powerplant Amended instruments AMC2 23.2615 Flight, navigation, and powerplant Amended instruments AMC3 23.2615 Flight, navigation, and powerplant Amended instruments AMC1 23.2620 Aeroplane Flight Manual Amended AMC1 23.2625 Instructions for Continued Amended Airworthiness ED Decision 2023/00 2/R Amendment 6 The following is a list of paragr aphs affected by this amendment: Subpart A GM1 23.2010 Amended ( NPA 2022 - 103 ) GM2 23.2010 Amended (NPA 2022 - 103) GM3 23.2010 Created (NPA 2022 - 103) Subpart B AMC1 23.2100 Amended ( NPA 2022 - 103 ) AMC1 23.2105 Amended (NPA 2022 - 103) AMC1 23.2110 Amended (NPA 2022 - 103) AMC1 23.2115 Amended (NPA 2022 - 103) AMC1 23.2120 Amended (NPA 2022 - 103) AMC1 23.2125 Amended (NPA 2022 - 103) AMC1 23.2130 Amended (NPA 2022 - 103) CS 23. 2135 Amended (NPA 2022 - 103) AMC1 23.2135 Amended (NPA 2022 - 103) AMC1 23.2140 Amended (NPA 2022 - 103) AMC1 23.2145 Amended (NPA 2022 - 103) AMC1 23.2150 Amended (NPA 2022 - 103) AMC2 23.2150 Amended (NPA 2022 - 103) AMC1 23.2155 Amended (NPA 2022 - 103) AMC1 23.2160 Amended (NPA 2022 - 103) AMC1 23.2165 Amended (NPA 2022 - 103) AMC2 23.2165 Amended (NPA 2022 - 103) AMC1 23.2170 Amended (NPA 2022 - 103) Subpart C Powered by EASA eRules Page 19 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) Preamble AMC1 23.220 0 Amended ( NPA 2022 - 103 ) AMC1 23.2205 Amended (NPA 2022 - 103) AMC1 23.2210 Amended (NPA 2022 - 103) AMC1 23.2215 Amended (NPA 2022 - 103) AMC1 23.2220 Amended (NPA 2022 - 103) AMC1 23.2225 Amended (NPA 2022 - 103) AMC1 23.2230 Amended (NPA 2022 - 103) AMC1 23.2235 Amended (NPA 2022 - 103) AMC1 23.2240 Amended (NPA 2022 - 103) AMC1 23.2250 Amended (NPA 2022 - 103) AMC1 23.2255 Amended (NPA 2022 - 103) AMC1 23.2260 Amended (NPA 2022 - 103) AMC1 23.2265 Amended (NPA 2022 - 103) AMC1 23.2270 Amended (NPA 2022 - 103) Subpart D AMC1 23.2300 Amended ( NPA 2022 - 103 ) AMC1 23.230 5 Amended (NPA 2022 - 103) AMC1 23.23 10 Amended (NPA 2022 - 103) AMC1 23.23 15 Amended (NPA 2022 - 103) AMC1 23.23 20 Amended (NPA 2022 - 103) AMC1 23.23 25 Amended (NPA 2022 - 103) AMC1 23.23 30 Amended (NPA 2022 - 103) AMC1 23.23 35 Amended (NPA 2022 - 103) AMC1 23.23 40 Amended (NPA 2022 - 103) Subpart E AMC1 23.240 0 Amended ( NPA 2022 - 103 ) AMC1 23.240 5 Amended (NPA 2022 - 103 ) AMC1 23.24 10 Amended (NPA 2022 - 103 ) AMC1 23.24 15 Amended (NPA 2022 - 103 ) AMC 2 23.2415 Amended (NPA 2022 - 103 ) AMC1 23.24 25 Amended (NPA 2022 - 103 ) CS 23.2430 Amended (NPA 2022 - 103) AMC1 23.24 30 Amended (NPA 2022 - 103 ) AMC1 23.24 35 Amended (NPA 2022 - 103 ) AMC1 23.24 40 Amended (NPA 2022 - 103 ) AMC1 23.24 45 Amended (NPA 2022 - 103 ) Subpart F AMC1 23.2500 Amended ( NPA 2022 - 103 ) AMC1 23.2505 Amended (NPA 2022 - 103 ) AMC1 23.2510 Amended (NPA 2022 - 103 ) CS 23.2515 Amended (NPA 2022 - 103) AMC1 23.2515 Amended (NPA 2022 - 103 ) AMC1 23.2520 Amended (NPA 2022 - 103 ) AMC1 23.2525 Amended (NPA 2022 - 103 ) AMC2 23.2525 Amended (NPA 2022 - 103 ) AMC3 23.2525 Amended (NPA 2022 - 103 ) Powered by EASA eRules Page 20 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) Preamble AMC1 23.2530 Amended (NPA 2022 - 103 ) AMC1 23.2535 Amended (NPA 2022 - 103 ) AMC1 23.2540 Amended (NPA 2022 - 103 ) AMC2 23.2540 Amended (NPA 2022 - 103 ) AMC1 23.2545 Amended (NPA 2022 - 103 ) AMC1 23.2555 Amended (NPA 2022 - 103 ) Subpart G AMC1 23.2600 Amended ( NPA 2022 - 103 ) AMC1 23.2605 Amended (NPA 2022 - 103 ) AMC1 23.2610 Amended (NPA 2022 - 103 ) AMC1 23.2615 Amended (NPA 2022 - 103 ) AMC2 23.2615 Amended (NPA 2022 - 103 ) AMC3 23.2615 Amended (NPA 2022 - 103 ) AMC1 23.2620 Amended (NPA 2022 - 103 ) AMC1 23.2625 Amended (NPA 2022 - 103 ) ED Decision 2017/013/R Amendment 5 The following is a list of paragr aphs affected by this amendment: Subpart A CS 23.1 through CS 23.3 Deleted and moved to AMC ( NPA 2016 - 05 ) CS 23.2000 through CS 23.2010 Created ( NPA 2016 - 05 ) Subpart B CS 23.21 through CS 23.253 Deleted and moved to AMC ( NPA 2016 - 05 ) CS 23.2100 through CS 23.2170 Created ( NPA 2016 - 05 ) Subpart C CS 23.301 through CS 23.575 Deleted and moved to AMC ( NPA 2016 - 05 ) CS 23.2200 through CS 23.2270 Created ( NPA 2016 - 05 ) AMC — Subpart C Deleted and moved to AMC ( NPA 2016 - 05 ) Subpart D CS 23.601 through CS 23.871 Deleted and moved to AMC ( NPA 2016 - 05 ) CS 23.2300 through CS 23.2340 Created ( NPA 2016 - 05 ) AMC — Subpart D Deleted and moved to AMC ( NPA 2016 - 05 ) Subpart E CS 23.901 through CS 23.1203 Deleted and moved to AMC ( NPA 2016 - 05 ) CS 23.2400 through CS 23.2445 Created ( NPA 2016 - 05 ) AMC — Subpart E Deleted and moved to AMC ( NPA 2016 - 05 ) Subpart F CS 23.1301 through CS 23.1461 Deleted and moved to AMC ( NPA 2016 - 05 ) CS 23.2500 through CS 23.2555 Created ( NPA 2016 - 05 ) AMC — Subpart F Deleted and moved to AMC ( NPA 2016 - 05 ) Subpart G CS 23.1501 through CS 23.1589 Deleted and moved to AMC ( NPA 2016 - 05 ) Powered by EASA eRules Page 21 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) Preamble CS 23.2600 through CS 23.2625 Created ( NPA 2016 - 05 ) AMC — Subpart G Deleted and moved to AMC ( NPA 2016 - 05 ) Appendices Appendix A through K Deleted and moved to AMC ( NPA 2016 - 05 ) AMC — Appendix A Deleted and moved to AMC ( NPA 2016 - 05 ) Flight Test Guide (FTG) Deleted and moved to AMC ( NPA 2016 - 05 ) ED Decision 2015/018/R Amendment 4 The following is a list of paragr aphs affected by this amendment: Subpart F CS 23.1306 Created ( NPA 2014 - 16 ) CS 23.130 8 Created ( NPA 2014 - 16 ) Appendix K Created ( NPA 2014 - 16 ) CS 23.1309 Amended ( NPA 2014 - 16 ) ED Decision 2012/012/R Amendment 3 The following is a list of paragr aphs affected by this amendment: Subpart D CS 23.851 Amended ( NPA 2011 - 14 ) AMC 23.851(c) Amended ( NPA 2011 - 14 ) Subpart E CS 23.1197 Amended ( NPA 2011 - 14 ) AMC 23.1197 Created ( NPA 2011 - 14 ) ED Decision 2010/008/R Amendment 2 The following is a list of paragr aphs affected by this amendment: Subpart B CS 23. 221 Amended (Editorial correction) Subpart C Appendix D Amended (Editorial correction) AMC 23.573(a)(1)&(3) Amended ( NPA 2009 - 06 ) Subpart D CS 23.603 Amended ( NPA 2009 - 06 ) AMC 23.603 Deleted ( NPA 2009 - 06 ) AMC 23.613 Amended ( NPA 2009 - 06 ) AMC 23.629 Amended ( NPA 2009 - 06 & Editorial correction) CS 23.813(b)(4) Amended (Editorial correction) Subpart E CS 23.909 Amended (Editorial correction) Flight Test Guide (FTG) Powered by EASA eRules Page 22 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) Preamble 192 Paragraph 23.909 Amended (Editorial correction) 207 Paragraph 23.959 Amended (Editorial correction) 208 Paragraph 23.961 Amended (Editorial correction) 307 Paragraph 23.1329 Amended (Editorial correction) E D Decision 2009/001 /R Amendment 1 The following is a list of paragr aphs affected by this amendment: Preamble Preamble added Subpart B CS 23.49(c) Amended ( NPA 2008 - 08 ) CS 23.49(d) Creat ed ( NPA 2008 - 08 ) Subpart C CS 23.562(d) Created ( NPA 2008 - 08 ) CS 23.562(e) Amended ( NPA 2008 - 08 ) Powered by EASA eRules Page 23 of 118 | May 2026

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SUBPART A — GENERAL

Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART A — GENERAL

SUBPART A — GENERAL

CS 23.2000 Applicability and definitions

ED Decision 2017/013/R (a) This Certification Specification prescribes airworthiness standards for the issuance of type certificates, and changes to those certificates, for aeroplanes in the normal category.

(b) For the purposes of this Certification Specification, the following definition applies: ‘Continued safe flight and landing’ means an aeroplane is capable of continued controlled flight and landing, possibly using emergency procedures, without requiring exceptional pilot skill or strength. Upon landing, some aeroplane damage may occur as a res ult of a failure condition.

AMC1 23.2000 Applicability

ED Decision 2017/025/R The applicability of the acceptable means of compliance (AMC) is limited to the scope of CS - 23 (Amendment 5 and later). The applicability of the individual AMC that are provided in Subpart B through G can be restricted to a specific type of design, type of operation or any other criterion. The applicability of each AMC is therefore specified within that AMC. Demonstration of compliance using a published AMC outside of that applicability does not provide for presumption of compliance with the related requirement.

CS 23.2005 Certification of normal - category aeroplanes

ED Decision 2017/013/R (a) Certification in the normal category applies to aeroplanes with a passenger seating configuration of 19 or less and a maximum certified take - off mass of 8 618 kg (19 000 pounds) or less.

(b) Aeroplane certification levels are: (1) Level 1 — for aeroplanes with a maximum seating configuration of 0 to 1 passengers; (2) Level 2 — for aeroplanes with a maximum seating configuration of 2 to 6 passengers; (3) Level 3 — for aeroplanes with a maximum seating configuration of 7 to 9 passengers; and (4) Level 4 — for aeroplanes with a maximum seating configuration of 10 to 19 passengers.

(c) Aeroplane performance levels are: (1) Low speed — for aeroplanes with a V or V ≤ 250 knots calibrated airspeed (KCAS) or NO MO MO a M ≤ 0.6; and (2) High speed — for aeroplanes with a V or V > 250 KCAS or an M > 0.6.

NO MO MO (d) Aeroplanes not certified for aerobatics may be used to perform any manoeuvre incident to normal flying, including: (1) stalls (except whip stalls); and (2) lazy eights, chandelles, and steep turns, in which the angle of bank is not more than 60 degrees.

Powered by EASA eRules Page 24 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART A — GENERAL (e) Aeroplanes certified for aerobatics may be used to perform manoeuvres without limitations, other than those limitations established under Subpart G.

CS 23.2010 Accepted means of compliance

ED Decision 2017/013/R (a) An applicant must comply with this CS using an acceptable means of compliance (AMC) issued by EASA, or another means of compliance which may include consensus standards, when specifically accepted by EASA.

(b) An applicant requesting EASA to accept a means of compliance must provide the means of compliance to EASA in an acceptable form and manner.

GM1 23.2010 Accepted means of compliance

ED Decision 2026/003/R For compliance demonstration, applicants will use the issue of the AMC & GM which is current on the date of application, as reflected in the certification programme for the certification basis determined by EASA.

This current issue, however, does not automatically invalidate the previous and later issues of the AMC & GM to CS - 23, unless this is specifically identified as such in the AMC & GM. Applicants can, therefore, agree with EASA in the certification programme to use such previous issues of the AMC & GM to demonstrate compliance with the certification basis.

Whenever an earlier AMC is no longer considered to be acceptable for the demonstration of compliance, the restrictions on its use will be stated in a remark o n the specific line of that CS and the related AMC. In particular, AMC2&3 to CS - 23/CS - VLA Subpart B to Subpart G (which reflect respectively CS - 23 Amendment 4 and CS - VLA Amendment 1) will not be updated to cover new technologies or methods. However, they are still accepted as m eans of compliance. EASA will restrict their use in the AMC only when they n o longer appropriately address new safety concerns or the associated safety levels.

[AMC & GM to CS - 23: Issue 3 ] [AMC & GM to CS - 23: Issue 4 ] [AMC & GM to CS - 23: Issue 5]

GM2 23.2010 Accepted means of compliance

ED Decision 2026/003/R The AMC to certification specifications (CS) for Normal - Category Aeroplanes (CS - 23 Amendment 5 and later) illustrate means, but not the only means, by which a requirement contained in CS - 23 can be met. Satisfactory demonstration of compliance using the AMC shall prov ide for presumption of compliance with the related requirement. The AMC are a way to facilitate certification tasks for the applicant and the competent authority. Due to changes in technology or application of technology in a way that has not been consider ed or not (yet) included in the AMC, the appropriate application of this AMC in the certification of a design requires a review by the authority.

CS - 23 Amendment 5 and later maintains the existing level of safety of CS - 23 Amendment 4 and CS - VLA Amendment 1, except for areas addressing loss of control and icing, for which the safety level was increased. Achieving this level of safety through compliance with CS - 23 Amendment 5 and later for a Powered by EASA eRules Page 25 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART A — GENERAL given certification project may require the use of additional means of compliance beyond those provided in this AMC, depending on the details of the specific design.

Applicants may propose designs with novel or unusual feat ures for which neither AMC1 nor the EASA Certification Specifications (CS - 23 Amendment 4 and CS - VLA Amendment 1) contain appropriate AMC for showing compliance with CS - 23 Amendment 5 and later . Therefore, applicants proposing the use of this AMC to CS - 23 as a means of complying with CS - 23 Amendment 5 and later for aeroplanes with novel or unusual design features may need to gain acceptance of additional means of compliance under CS 23.2010 .

AMC1 CS - 23 Subpart B through Subpart G contains means of compliance that consist of a listing of consensus standards at their specific revisions that have been reviewed by EASA and accepted as AMC to CS - 23. The scope and content of the referenced consensus standard can, however, differ from the overall scope of CS - 23 or the objectives of the requirement. Therefore, using such a referenced consensus standard requires the applicant to identify what is applicable within that consensus standard and to seek agre ement with the authority for agreement of the selected consensus standard and applied paragraphs. This is the so - called building - block flexibility that is built into CS - 23.

Applicable revision of ASTM F3264 For the purpose of AMC1 to CS - 23, EASA has assessed and accepted the most recent available revision of ASTM F3264, currently ASTM F3264 - 24 .

Where more recent revisions of individual consensus standards were available at the time of assessment, EASA also considered them with the aim of closing existing remarks in AMC1. As a result, some standards listed in AMC1 may refer to a revision that diff ers from the one included in ASTM F3264 - 24 . It is expected that these revisions will be incorporated into a future update of ASTM F3264 .

Deviations from consensus standards Where EASA determines that a deviation from a referenced consensus standard is necessary to achieve the level of safety required by the respective CS - 23 Amendment, this is indicated by a corresponding remark in AMC1.

AMC2 CS - 23 Subpart B through Subpart G contains means of compliance that refer to the previous Amendment 4 of CS - 23. These AMC are included for the (administrative) convenience of both the applicant and EASA when using an existing cer tification basis. AMC2 in Sections B through G identify which CS - 23 Amendment 4 requirements contain an accepted demonstration of compliance with the requirement. This AMC2 CS - 23 Subpart B through Subpart G is applicable for fixed wing aeroplanes with a passenger - seating config uration of 19 or less and a maximum certificated take - off mass of 8 618 kg (19 000 pounds) or less.

Before the entry into force of Amendment 5 of CS - 23, CS - 23 was included in the certification basis that often required complementing special conditions (refer to point 21.A.16B of Part 21 ) when the certification specification did not contain adequate or appropriate safety standards for the product.

These special conditions can be applied to complement AMC2 when required.

AMC3 CS - 23 Subpart B through Subpart G contains means of compliance that refer to the previous Amendment 1 of CS - VLA. These AMC are included for the (administrative) convenience of both the applicant and EASA when using an existing certification basis. AMC3 that are provided in Sections B through G identify which CS - VLA Amendment 1 requirement ( s ) contain an accepted demonstration of compliance with the requirement. This AMC3 CS - 23 Subpart B through Subpart G is applicable to Regulation (EU) No 748/2012 of 3 August 2012 laying down implementing rules for the airworthiness and environmental certification of aircraft and related products, parts and appliances, as well as for the certification of design and production organisatio n s (OJ L 224, 21.8.2012, p. 1). http://eur - lex.europa.eu/legal - content/EN/TXT/?qid=1473415871666&uri=CELEX:32012R0748 Powered by EASA eRules Page 26 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART A — GENERAL aeroplanes with a single engine (spark - or compression - ignition) having not more than two seats, with a maximum certificated take - off weight of not more than 750 kg and a stalling speed in the landing configuration of not more than 83 km/h (45 knots)(CAS), to be approved for day VFR only. This AMC3 is applicable for non - aerobatic operations including: — any manoeuvre incident to normal flying; — stalls (except whip stalls); and — lazy eights, chandelles, and steep turns, in which the angle of bank is not more than 60°.

Before the entry into force of Amendment 5 of CS - 23, CS - VLA was included in the certification basis that often required complementing special conditions (refer to point 21.A.16B in Part 21) when the certification specification did not contain adequate or a ppropriate safety standards for the product.

These special conditions can be applied to complement AMC3 when required.

Availability of referenced consensus standards The referenced consensus standard documents are available from their issuing standards body: — ASTM documents may be purchased from: ASTM International 100 Barr Harbor Drive, PO Box C700 West Conshohocken, Pennsylvania 19428 - 2959, USA (Website: www.astm.org ) [AMC & GM to CS - 23: Issue 3 ] [AMC & GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5] Powered by EASA eRules Page 27 of 118 | May 2026 Easy Access Rules for Normal - Category Aeroplanes (CS - 23) CS Amendment 6, AMC/GM Issue 5 SUBPART A — GENERAL

GM3 23.2010 Accepted means of compliance

ED Decision 2026/003/R The following table provides an overview of the ASTM International Technical Committee F44 (hereinafter ‘ASTM F44’) consensus standards that are included in AMC1 as an acceptable means of compliance with CS - 23. It also gives the revision number of the ASTM consensus standards as changed between Issue 4 and Issue 5 of AMC1 to CS 23.

AMC & GM to CS - 23 Issue 5 AMC & GM to CS - 23 Issue 4 (ED Decision 202 6 / 003 /R) (ED Decision 2023/002/R , ED Decision 2025/019/R* ) ASTM consensus standard number and title ASTM consensus standard ASTM consensus standard revision revision F2490 Standard Guide for Aircraft Electrical Load and Power Source Capacity Analysis 20 20 F3061/F3061M Standard Specification for Systems and Equipment in Small Aircraft 24a 20 F3062/F3062M Standard Specification for Aircraft Powerplant Installation 20 20 F3063/F3063M Standard Specification for Aircraft Fuel Storage and Delivery 21 20 F3064/F3064M Standard Specification for Aircraft Powerplant Control, Operation, and Indication 21 21 F3065/F3065M Standard Specification for Aircraft Propeller System Installation 21a 21a F3066/F3066M Standard Specification for Aircraft Powerplant Installation Hazard Mitigation 18 18 F3082/F3082M Standard Specification for Weights and Centers of Gravity of Aircraft 22 17 F3083/F3083M Standard Specification for Emergency Conditions, Occupant Safety and 20a 20a Accommodations F3093/F3093M Standard Specification for Aeroelasticity Requirements 21 21 F3114 Standard Specification for Structures 21 21 F3115/F3115M Standard Specification for Structural Durability for Small Aeroplanes 15 15* F3116/F3116M Standard Specification for Design Loads and Conditions 24 18e2 F3117/F3117M Standard Specification for Crew Interface in Aircraft 24a 20 F3120/F3120M Standard Specification for Ice Protection for General Aviation Aircraft 20 20 F3173/F3173M Standard Specification for Aircraft Handling Characteristics 21a 21 F3174/F3174M Standard Specification for Establishing Operating Limitations and Information for 21 19 Aeroplanes Powered by EASA eRules Page 28 of 118 | May 2026 Easy Access Rules for Normal - Category Aeroplanes (CS - 23) CS Amendment 6, AMC/GM Issue 5 SUBPART A — GENERAL F3179/F3179M Standard Specification for Performance of Aircraft 22e1 20 F3180/F3180M Standard Specification for Low - Speed Flight Characteristics of Aircraft 25 21 F3227/F3227M Standard Specification for Environmental Systems in Aircraft 25 21 F3228 Standard Specification for Flight Data and Voice Recording in Small Aircraft 21 17 F3229/F3229M Standard Practice for Static Pressure System Tests in Small Aircraft 23a 17 F3230 Standard Practice for Safety Assessment of Systems and Equipment in Small Aircraft 25 20a F3231/F3231M Standard Specification for Electrical Systems for Aircraft with Combustion Engine 24 21 Electrical Power Generation F3232/F3232M Standard Specification for Flight Controls in Small Aircraft 25 20 F3233/F3233M Standard Specification for Flight and Navigation Instrumentation in Aircraft 23b 21 F3234/F3234M Standard Specification for Exterior Lighting in Small Aircraft 21 17 F3235 Standard Specification for Aircraft Storage Batteries 22 17a F3236 Standard Specification for High Intensity Radiated Field (HIRF) Protection in Small Aircraft 21a 17 F3254 Standard Specification for Aircraft Interaction of Systems and Structures 22 19 F3309/F3309M Standard Practice for Simplified Safety Assessment of Systems and Equipment in Small 24a 21 Aircraft F3331 Standard Practice for Aircraft Water Loads 18 18 F3367 Standard Practice for Simplified Methods for Addressing High Intensity Radiated Fields (HIRF) 23 / and Indirect Effects of Lightning on Aircraft F3380 Standard Practice for Structural Compliance of Very Light Aeroplanes 19 19 F3396/F3396M Standard Practice for Aircraft Simplified Loads Criteria 20 20 F3397/F3397M Standard Practice for Aeroplane Turbine Fuel System Hot Weather Operations 21 / F3408/F3408M Standard Specification for Aircraft Emergency Parachute Recovery Systems 21 21 F3432 Standard Practice for Powerplant Instruments 20a 20a F3498 Standard Practice for Developing Simplified Fatigue Load Spectra 21 / F3532 Standard Practice for Protection of Aircraft Systems from Intentional Unauthorized Electronic 25 / Interactions [AMC & GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5] Powered by EASA eRules Page 29 of 118 | May 2026

Next: SUBPART B — FLIGHT →

SUBPART B — FLIGHT

Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART B — FLIGHT

SUBPART B — FLIGHT

CS 23.2100 Mass and centre of gravity

ED Decision 2017/013/R (a) The applicant must determine limits for mass and centre of gravity that provide for the safe operation of the aeroplane.

(b) The applicant’s design must comply with each requirement of this Subpart at critical combinations of mass and centre of gravity within the aeroplane’s range of loading conditions using acceptable tolerances.

(c) The condition of the aeroplane at the time of determining its empty mass and centre of gravity must be well defined and easily repeatable.

AMC1 23.2100 Mass and centre of gravity

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 5.1 Weight/Mass and Centre of Gravity 5.1.1 F3082/F3082M - 22 S tandard Specification for Weights and Centers of Gravity of Aircraft 5.1.2 F3114 - 21 Standard Specification for Structures [AMC & GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5]

AMC2 23.2100 Mass and centre of gravity

ED Decision 2017/025/R CS - 23 Amdt 4 23.21 Proof of compliance 23.23 Load distribution limits 23.25 Weight limits 23.29 Empty weight and corresponding center of gravity 23.31 Removable ballast 23.871 Levelling means

AMC3 23.2100 Mass and centre of gravity

ED Decision 2017/025/R CS VLA Amdt 1 VLA.21 Proof of compliance VLA.23 Load distribution limits Powered by EASA eRules Page 30 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART B — FLIGHT VLA.25 Weight limits VLA.29 Empty weight and corresponding center of gravity VLA.871 Levelling means

CS 23.2105 Performance data

ED Decision 2017/013/R (a) Unless otherwise prescribed, an aeroplane must meet the performance requirements of this Subpart in: (1) still air and standard atmospheric conditions at sea level for all aeroplanes; and (2) ambient atmospheric conditions within the operating envelope for: (i) Level - 1 high - speed and Level - 2 high - speed aeroplanes; and (ii) Level - 3 and Level - 4 aeroplanes.

(b) Unless otherwise prescribed, the applicant must develop the performance data required by this Subpart for the following conditions: (1) airport altitudes from sea level to 3 048 m (10 000 ft); and (2) temperatures above and below standard day temperature that are within the range of operating limitations if those temperatures could have a negative effect on performance.

(c) The procedures used for determining take - off and landing distances must be executable consistently by pilots of average skill in atmospheric conditions expected to be encountered in service.

(d) Performance data determined in accordance with CS 23.2105(b) must account for losses due to atmospheric conditions, cooling needs, and other demands on power sources.

AMC1 23.2105 Performance data

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 5.2 Performance Data F3179/F3179M - 22e1 Standard Specification for Performance of Aircraft [AMC & GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5]

AMC2 23.2105 Performance data

ED Decision 2017/025/R CS - 23 Amdt 4 23.45 Performance – General Powered by EASA eRules Page 31 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART B — FLIGHT

AMC3 23.21 0 5 Performance data

ED Decision 2017/025/R CS VLA Amdt 1 VLA.45 Performance - General

CS 23.2110 Stall speed

ED Decision 2017/013/R The applicant must determine the aeroplane stall speed or the minimum steady flight speed for each flight configuration used in normal operations, including take - off, climb, cruise, descent, approach, and landing. The stall speed or minimum steady flight speed determination must account for the most adverse conditions for each flight configuration.

AMC1 23.2110 Stall speed

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 5.3 Stall Speed F3179/F3179M - 22e1 Standard Specification for Performance of Aircraft Remarks For stall speed, use no later revision than F3179 - 22e1.

[AMC & GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5]

AMC2 23.2110 Stall speed

ED Decision 2017/025/R CS - 23 Amdt 4 23.49 Stalling speed

AM C3 23.2110 Stall speed

ED Decision 2017/025/R CS VLA Amdt 1 VLA.49 Stalling speed

CS 23.2115 Take - off performance

ED Decision 2017/013/R (a) The applicant must determine aeroplane take - off performance accounting for: (1) stall speed safety margins; (2) minimum control speeds; and (3) climb gradients.

Powered by EASA eRules Page 32 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART B — FLIGHT (b) For single - engine aeroplanes and Levels 1, 2, and 3 low - speed multi - engine aeroplanes, take - off performance includes the determination of ground roll and ini tial climb distance to 15 m (50 ft) above the take - off surface.

(c) For high - speed multi - engine aeroplanes of Levels 1, 2, and 3, and for all Level - 4 multi - engine aeroplanes, take - off performance includes a determination of the following distances after a sudden critical loss of thrust: (1) an aborted take - off at critical speed; (2) ground roll and initial climb to 11 m (35 ft) above the take - off surface; and (3) net take - off flight path.

AMC1 23.2115 Take - off performance

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 5.4 Take - off Performance F3179/F3179M - 22e1 Standard Speci fication for Performance of Aircraft [AMC & GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5]

AMC2 23.2115 Take - off performance

ED Decision 2017/025/R CS - 23 Amdt 4 23.51 Takeoff speeds 23.53 Takeoff performance 23.55 Accelerate - stop distance 23.57 Takeoff path 23.59 Takeoff distance and takeoff run 23.61 Takeoff flight path

AM C3 23 .2115 Take - off performance

ED Decision 2017/025/R CS VLA Amdt 1 VLA.51 Takeoff speeds

CS 23.2120 Climb requirements

ED Decision 2017/013/R The design must comply with the following minimum climb performance out of ground effect: (a) with all engines operating and in the initial climb configuration(s): (1) for Level - 1 and - 2 low - speed aeroplanes, a climb gradient of 8.3 % for landplanes and 6.7 % for seaplanes and amphibians; and Powered by EASA eRules Page 33 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART B — FLIGHT (2) for Level - 1 and - 2 high - speed aeroplanes and all Level - 3 and - 4 aeroplanes, a climb gradient at take - off of 4 %.

(b) after a critical loss of thrust on multi - engine aeroplanes: (1) for Level - 1 and - 2 low - speed aeroplanes that do not meet single - engine crashworthiness requirements, a climb gradient of 1.5 % at a pressure altitude of 1 524 m (5 000 ft) in the cruise configuration; (2) for Level - 1 and - 2 high - speed aeroplanes, and Level - 3 low - speed aeroplanes, a 1 % climb gradient at 122 m (400 ft) above the take - off surface with the landing gear retracted and flaps in the take - off configuration; and (3) for Level - 3 high - speed aeroplanes and all Level - 4 aeroplanes, a 2 % climb gradient at 122 m (400 ft) above the take - off surface with the landing gear retracted and flaps in the approach configuration; (c) a climb gradient of 3 % during balked landing, without creating undue pilot workload, with the landing gear extended and flaps in the landing configuration(s).

AMC1 23.2120 Climb requirements

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 5.5 Climb Requirements F3179/F3179M - 22e1 Standard Specification for Performance of A ircraft [AMC & GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5]

AMC2 23.2120 Climb requirements

ED Decision 2017/025/R CS - 23 Amdt 4 23.63 Climb: General 23.65 Climb: All engines operating

AMC3 23.2120 Climb requirements

ED Decision 2023/002/R CS - VLA Amdt 1 CS - VLA 65 ‘ Climb s’ : All engines operating Remarks To demonstrate compliance with CS 23.2120 , the climb gradient should be determined, using F3179M 20 ‘Standard Specification for Performance of Aircraft’.

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CS 23.2125 Climb information

ED Decision 2017/013/R (a) The applicant must determine, as applicable, climb and/or descent performance: (1) for all engines operating; (2) following a critical loss of thrust on take - off; and (3) after a critical loss of thrust, during the en route phase of flight.

AMC1 23.2125 Climb information

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 5.6 Climb Information F3179/F3179M - 22e1 Standard Specificati on for Performance of Aircraft [AMC & GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5]

AMC2 23.2125 Climb information

ED Decision 2017/025/R CS - 23 Amdt 4 23.66 Takeoff climb: one engine inoperative 23.67 Climb: One engine inoperative 23.69 En route climb/descent 23.71 Glide: single engine airplanes

AMC3 23.2125 Climb information

ED Decision 2017/025/R None

CS 23.2130 Landing

ED Decision 2017/013/R The applicant must determine the following, for standard temperatures at critical combinations of mass and altitude within the operational limits: (a) the distance, starting from a height of 15 m (50 ft) above the landing surface, required to land and come to a stop; and (b) the approach and landing speeds, configurations, and procedures, which allow a pilot of average skill to land within the published landing distance consistently and without causing damage or injury, and which allow for a safe transition to the balked - land ing conditions.

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AMC1 23.2130 Landing

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 5.7 Landing F3179/F3179M - 22e1 Standard Specificati on for Performance of Aircraft [AMC & GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5]

AMC2 23.2130 Landing

ED Decision 2017/025/R CS - 23 Amdt 4 23.73 Reference landing approach speed 23.75 Landing distance 23.77 Balked landing

AM C3 23.2130 Landing

ED Decision 2017/025/R CS VLA Amdt 1 VLA.75 Landing distance VLA.77 Balked landing

CS 23.2135 Controllability

ED Decision 2023/002/R (a) The aeroplane must be controllable and manoeuvrable, without requiring exceptional piloting skills, alertness, or strength, within the operating envelope: (1) at all loading conditions for which certification is requested; (2) during all phases of flight; (3) with likely reversible flight control or propulsion system failure; and (4) during configuration changes.

(b) The aeroplane must be able to make a safe landing , using the steepest approved approach gradient procedures and providing a reasonable safe margin below V or above the approach REF angle of attack.

(c) V is the calibrated airspeed at which, following the sudden critical loss of thrust, it is possible MC to maintain control of the aeroplane. For multi - engine aeroplanes, the applicant must determine V , if applicable, for the most critical configurations used in take - off and landing MC operations.

(d) If the applicant requests certification of an aeroplane for aerobatics, the applicant must demonstrate those aerobatic manoeuvres for which certification is requested and determine entry speeds.

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AMC1 23.2135 Controllability

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 5.8 Controllability F3173/F3173M - 21a Standard Specification for Aircraft Handling Characteristics [AMC & GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5]

AMC2 23.2135 Controllability

ED Decision 2017/025/R CS - 23 Amdt 4 23.141 Flight Characteristics - General 23.143 Controllability and Manoeuvrability - General 23.145 Longitudinal control 23.147 Directional and lateral control 23.149 Minimum control speed 23.151 Acrobatic manoeuvres 23.153 Control during landings 23.155 Elevator control force in manoeuvres 23.157 Rate of roll

AM C3 23.2135 Controllability

ED Decision 2017/025/R CS VLA Amdt 1 VLA.141 Flight Characteristics - General VLA.143 Controllability and Manoeuvrability - General VLA.145 Longitudinal control VLA.153 Control during landings VLA.155 Elevator control force in manoeuvres VLA.157 Rate of roll

CS 23.2140 Trim

ED Decision 2017/013/R (a) The aeroplane must maintain lateral and directional trim without further force upon, or movement of, the primary flight controls or corresponding trim controls by the pilot, or the flight control system, under the following conditions: (1) for Level - 1, - 2, and - 3 aeroplanes, in cruise; (2) for Level - 4 aeroplanes, in normal operations.

Powered by EASA eRules Page 37 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART B — FLIGHT (b) The aeroplane must maintain longitudinal trim without further force upon, or movement of, the primary flight controls or corresponding trim controls by the pilot, or the flight control system, under the following conditions: (1) climb, (2) level flight, (3) descent, (4) approach.

(c) Residual control forces must not fatigue or distract the pilot during normal operations of the aeroplane and likely abnormal or emergency operations, including a critical loss of thrust on multi - engine aeroplanes.

AMC1 23.2140 Trim

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 5.9 Trim F3173/F3173M - 21a Standard Specification for Aircraft Handling Characteristics [AMC & GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5]

AMC2 23.2140 Trim

ED Decision 2017/025/R CS - 23 Amdt 4 23.161 Trim

AM C3 23.2140 Trim

ED Decision 2017/025/R CS VLA Amdt 1 VLA.161 Trim

CS 23.2145 Stability

ED Decision 2017/013/R (a) Aeroplanes not certified for aerobatics must: (1) have static longitudinal, lateral, and directional stability in normal operations; (2) have dynamic short period and Dutch roll stability in normal operations; and (3) provide stable control feedback throughout the operating envelope.

(b) No aeroplane may exhibit any divergent longitudinal stability characteristic so unstable as to increase the pilot’s workload or otherwise endanger the aeroplane and its occupants.

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AMC1 23.2145 Stability

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 5.10 Stability F3173/F3173M - 21a Standard Specification for Aircraft Handling Characteristics [AMC & GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5]

AMC2 23.2145 Stability

ED Decision 2017/025/R CS - 23 Amdt 4 23.171 Stability – General 23.173 Static longitudinal stability 23.175 Demonstration of static longitudinal stability 23.177 Static directional and lateral stability 23.181 Dynamic stability

AM C3 23.2145 Stability

ED Decision 2017/025/R CS VLA Amdt 1 VLA.171 Stability – General VLA.173 Static longitudinal stability VLA.175 Demonstration of static longitudinal stability VLA.177 Static directional and lateral stability VLA.181 Dynamic stability

CS 23.2150 Stall characteristics, stall warning, and spins

ED Decision 2017/013/R (a) The aeroplane must have controllable stall characteristics in straight flight, turning flight, and accelerated turning flight with a clear and distinctive stall warning that provides sufficient margin to prevent inadvertent stalling. A stall warning that is mutable for aerobatic flight phases is acceptable.

(b) Single - engine aeroplanes, not certified for aerobatics, must not have a tendency to hazardously depart from controlled flight inadvertently.

(c) Level - 1 and - 2 multi - engine aeroplanes, not certified for aerobatics, must not have a tendency to hazardously depart controlled flight inadvertently from thrust asymmetry after a critical loss of thrust.

(d) Aeroplanes certified for aerobatics that include spins must have controllable stall characteristics and the ability to recover within one and one - half additional turns after initiation of the first control action from any point in a spin, not exceeding si x turns or any greater number of turns Powered by EASA eRules Page 39 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART B — FLIGHT for which certification is requested, while remaining within the operating limitations of the aeroplane.

(e) Aeroplanes intended for aerobatics have the ability to recover from any approved manoeuvre, without exceeding limitations or exhibiting unsafe characteristics.

AMC1 23.2150 Stall characteristics, stall warning, and spins

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 5.11 Stall Characteristics, Stall Warning, and Spins F3180/F3180M - 25 Standard Specification for Low - Speed Flight Characteristics of Aircraft [AMC & GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5]

AMC2 23.2150 Stall characteristics, stall warning, and spins

ED Decision 2026/003/R CS - 23 Amdt 4 23.201 Wings level stall 23.203 Turning Flight and accelerated turning stalls 23.207 Stall Warning 23.221 Spinning Remarks CS 23.2150 (b) and (c) are not covered by this AMC2. Applicants may us e the provision in ASTM F3180 - 2 5 to show compliance with CS 23.2150 .

[AMC & GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5]

AM C3 23.2150 Stall characteristics, stall warning, and spins

ED Decision 2019/020/R CS VLA Amdt 1 VLA.201 Wings level stall VLA.203 Turning Flight and accelerated turning stalls VLA.207 Stall Warning VLA.221 Spinning Remarks VLA.221(a) is not accepted as AMC to 23.2150 only VLA.221(b) can be used.

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CS 23.2155 Ground - and water - handling characteristics

ED Decision 2017/013/R (a) The aeroplane has controllable longitudinal and directional handling characteristics during taxi, take - off, and landing for the anticipated operation.

AMC1 23.2155 Ground - and water - handling characteristics

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 5.12 Ground and Water Handling Characteristics F3173/F3173M - 21a Standard Specification for Aircraft Handling Characteristics [AMC & GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5]

AMC2 23.2155 Ground - and water - handling characteristics

ED Decision 2017/025/R CS - 23 Amdt 4 23.231 Longitudinal stability and control 23.233 Directional stability and control 23.235 Operation on unpaved surfaces 23.237 Operation on water 23.239 Spray characteristics

AM C3 23.2155 Ground - and water - handling characteristics

ED Decision 2017/025/R CS VLA Amdt 1 VLA.231 Longitudinal stability and control VLA.233 Directional stability and control VLA.235 Operation on unpaved surfaces VLA.239 Spray characteristics

CS 23.2160 Vibration, buffeting, and high - speed characteristics

ED Decision 2017/013/R (a) Vibration and buffeting, for operations up to V /M , must not interfere with the control of the D D aeroplane or cause excessive fatigue to the flight crew. Stall warning buffet within these limits is allowable.

(b) For high - speed aeroplanes and all aeroplanes with a maximum operating altitu de greater than 7 625 m (25 000 ft) pressure altitude, there must be no perceptible buffeting in cruise configuration at 1 g and at any speed up to V /M , except stall buffeting.

MO MO (c) For high - speed aeroplanes, the applicant must determine the positive manoeuvring load factors at which the onset of perceptible buffet occurs in the cruise configuration within the operational Powered by EASA eRules Page 41 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART B — FLIGHT envelope. Likely inadvertent excursions beyond this boundary must not result in structural damage.

(d) High - speed aeroplanes must have recovery characteristics that do not result in structural damage or loss of control, beginning at any likely speed up to V /M , following: MO MO (1) an inadvertent speed increase; and (2) a high - speed trim upset for aeroplanes where dynamic pressure can impair the longitudinal trim system operation.

AMC1 23.2160 Vibration, buffeting, and high - speed characteristics

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 5.13 Vibration, Buffeting, and High - Speed Characteristics F3173/F3173M - 21a Standard Specification for Aircraft Handling Characteristics [AMC & GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5]

AMC2 23.2160 Vibration, buffeting, and high - speed characteristics

ED Decision 2017/025/R CS - 23 Amdt 4 23.251 Vibration and buffeting 23.253 High - speed characteristics

AM C3 23.2160 Vibration, buffeting, and high - speed characteristics

ED Decision 2017/025/R CS VLA Amdt 1 VLA.251 Vibration and buffeting

CS 23.2165 Performance and flight characteristics requirements for

flight in icing conditions

ED Decision 2017/013/R (a) An applicant who requests certification for flight in icing conditions must show the following in the icing conditions for which certification is requested under normal operation of the ice protection system(s): (1) comply with each requirement of this Subpart, except those applicable to spins and any that must be demonstrated at speeds in excess of: (i) 250 knots calibrated airspeed (KCAS); (ii) V or M or V ; or MO MO NE (iii) a speed at which the applicant demonstrates the airframe will be free of ice accretion; Powered by EASA eRules Page 42 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART B — FLIGHT (2) the means by which stall warning is provided to the pilot for flight in icing conditions and non - icing conditions is the same.

(b) If an applicant requests certification for flight in icing conditions, the applicant must provide a means to detect any icing conditions for which certification is not requested and demonstrate the aeroplane’s ability to avoid or exit those conditions.

(c) The applicant must develop an operating limitation to prohibit intentional flight, including take - off and landing, into icing conditions for which the aeroplane is not certified to operate.

AMC1 23.2165 Performance and flight characteristics requirements

for flight in icing conditions

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 5.14 Performance and Flight Characteristics Requirements for Flight in Icing Conditions F3120/F3120M - 20 Standard Specification for Ice Protection for General Aviation Aircraft [AMC & GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5]

AMC2 23.2165 Performance and flight characteristics requirements

for flight in icing conditions

ED Decision 2023/002/R CS - 23 Amdt 4 23.1419 Ice Protection Following the cancellation of Federal Aviation Administration (FAA) Advisory Circular (AC) - 1419 - 2D, applicants should now use AMC1 23.2165 .

AMC3 23.2165 Performance and flight characteristics requirements

for flight in icing conditions

ED Decision 2017/025/R None Powered by EASA eRules Page 43 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART B — FLIGHT

FLIGHT INFORMATION

CS 23.2170 Operating limitations

ED Decision 2017/013/R (a) The following flight information is established: (1) operating limitations, procedures and instructions necessary for the safe operation of the aeroplane; and (2) essential speed and performance information.

AMC1 23.2170 Operating limitations

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 5.15 Operating Limitations F3174/F3174M - 21 Standard Specification for Establishing Operating Limitations and Information for Aeroplanes F3408/F3408M - 21 Standard Specification for Aircraft Emergency Parachute Recovery Systems [AMC & GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5]

AMC2 23.2170 Operating limitations

ED Decision 2017/025/R CS - 23 Amdt 4 23.1501 General 23.1505 Airspeed limitations 23.1507 Manoeuvring speed 23.1511 Flap extended speed 23.1513 Minimum control speed 23.1519 Weight and centre of gravity 23.1527 Maximum operating altitude

AM C3 23.2170 Operating limitations

ED Decision 2017/025/R CS VLA Amdt 1 VLA.1501 General VLA.1505 Airspeed limitations VLA.1507 Manoeuvring speed VLA.1511 Flap extended speed VLA.1519 Weight and centre of gravity Powered by EASA eRules Page 44 of 118 | May 2026

Next: SUBPART C — STRUCTURES →

SUBPART C — STRUCTURES

Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART C — STRUCTURES

SUBPART C — STRUCTURES

CS 23.2200 Structural design envelope

ED Decision 2017/013/R The applicant must determine the structural design envelope, which describes the range and limits of aeroplane design and operational parameters for which the applicant will show compliance with the requirements of this Subpart. The applicant must account for all aeroplane design and operational parameters that affect structural loads, strength, durability, and aeroelasticity, including: (a) structural design airspeeds to be considered when determining the corresponding manoeuvring and gust loads must: (1) be sufficiently greater than the stalling speed of the aeroplane to safeguard against loss of control in turbulent air; and (2) provide sufficient margin for the establishment of practical operational limiting airspeeds.

(b) flight load conditions to be expected in service; (c) mass variations and distributions over the applicable mass and centre of gravity envelope, within the operating limitations; (d) loads in response to all designed control inputs; and (e) redistribution of loads if deflections under load would significantly change the distribution of external or internal loads.

AMC1 23.2200 Structural design envelope

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 6.1 Structural Design Envelope F3116/F3116M - 24 Standard Specification for Design Loads and Conditions F3396/F3396M - 20 Standard Practice for Aircraft Simplified Loads Criteria [AMC & GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5]

AMC2 23.2200 Structural design envelope

ED Decision 2017/025/R CS - 23 Amdt 4 23.321(b), (c) Flight Loads - General 23.333(a), (b), (d) Flight envelope 23.335 Design airspeeds 23.337 Limit manoeuvring load factors 23.341 Gust load factors Powered by EASA eRules Page 45 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART C — STRUCTURES

AM C3 23.2200 Structural design envelope

ED Decision 2017/025/R CS VLA Amdt 1 VLA.321 Flight Loads - General VLA.333 Flight envelope VLA.335 Design airspeeds VLA.337 Limit manoeuvring load factors VLA.341 Gust load factors

CS 23.2205 Interaction of systems and structures

ED Decision 2017/013/R For aeroplanes equipped with systems that affect structural performance, either directly or as a result of failure or malfunction, the applicant must account for the influence and failure conditions of these systems when showing compliance with the require ments of this Subpart.

AMC1 23.2205 Interaction of systems and structures

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 6.2 Interaction of Systems and Structure Remarks F3254 - 22 Standard Specification for Aircraft Interaction of Systems and Structure s To demonstrate compliance with 23.2205, the following of F3254 - 22 should be adjusted.

Chapter 4 - Interaction of System and Structure: Modifications are required in Figures 2, 3 and 4: − 5 — Replace the probability label ‘remote’ with ‘ 10 ’ — Replace the label ‘Extremely Improbable’ as follows: − 8 — for Level 1, 2 and 3 aeroplanes, use ′ 10 ’ − 9 — for Level 4 aeroplanes, use ‘ 10 ’ [AMC & GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5]

AMC2 23.2205 Interaction of systems and structures

ED Decision 2017/025/R None Remarks Provision not included in CS 23 Amdt 4 Powered by EASA eRules Page 46 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART C — STRUCTURES

AMC3 23.2205 Interaction of systems and structures

ED Decision 2017/025/R None Remarks Provision not included in CS VLA Amdt 1 Powered by EASA eRules Page 47 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART C — STRUCTURES

STRUCTURAL LOADS

CS 23.2210 Structural design loads

ED Decision 2017/013/R (a) The applicant must: (1) determine structural design loads resulting from likely externally or internally applied pressure, force or moment which may occur in flight, ground and water operations, ground - and water - handling, and while the aeroplane is parked or moored; (2) determine the loads required by CS 23.2210(a)(1) at all critical combinations of parameters, on and within the boundaries of the structural design envelope; and (3) the magnitude and distribution of these loads must be based on established physical principles within the structural design envelope.

AMC1 23.22 10 Structural - design loads

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 6.3 Structural Design Loads F3116/F3116M - 24 Standard Specification for Design Loads and Conditions F3396/F3396M - 20 Standard Practice for Aircraft Simplified Loads Criteria F3408/F3408M - 21 Standard Specification for Aircraft Emergency Parachute Recovery Systems [AMC & GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5]

AMC2 23.2210 Structural - design loads

ED Decision 2017/025/R CS - 23 Amdt 4 23.301(b), (c), (d) Loads (With Appendix A) 23.321(a) Flight Loads - General 23.343 Design fuel loads 23.345 High lift devices 23.471 Ground Loads - General 23.473 Ground load conditions and assumptions 23.507 Jacking loads 23.509 Towing loads 23.511 Ground load: unsymmetrical loads on multiple - wheel units 23.521 Water load conditions 23.523 Design weights and center of gravity positions 23.525 Application of loads Powered by EASA eRules Page 48 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART C — STRUCTURES 23.527 Hull and main float load factors (With Appendix I) 23.537 Seawing loads 23.753 Main float Design

AM C3 23.2210 Structural - design loads

ED Decision 2017/025/R CS VLA Amdt 1 VLA.301 Loads (With Appendix A) VLA.321 Flight Loads - General VLA.345 High lift devices VLA.471 Ground Loads - General VLA.473 Ground load conditions and assumptions VLA.521 Water load conditions

CS 23.2215 Flight load conditions

ED Decision 2017/013/R (a) Critical flight loads are established for symmetrical and asymmetrical loading from all combinations of airspeeds and load factors at and within the boundaries of the manoeuvre and gust envelope: (1) at each altitude within the operating limitations, where the effects of compressibility are taken into account when significant; (2) at each mass from the design minimum mass to the design maximum mass; and (3) at any practical but conservative distribution of disposable load within the operating limitations for each altitude and weight.

(b) Vibration and buffeting does not result in structural damage up to dive speed.

(c) Flight loads resulting from a likely failure of an aeroplane system, component, or engine are determined.

AMC1 23.22 15 Flight load conditions

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 6.4 Flight Load Conditions F3116/F3116M - 24 Standard Specification for Design Loads and Conditions F3396/F3396M - 20 Standard Practice for Aircraft Simplified Loads Criteria [AMC & GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5] Powered by EASA eRules Page 49 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART C — STRUCTURES

AMC2 23.2 2 15 Flight load conditions

ED Decision 2026/003/R CS - 23 Amdt 4 23.331 Symmetrical flight conditions 23.333(c) Flight envelope 23.347 Unsymmetrical flight loads 23.349 Rolling conditions 23.351 Yawing conditions 23.367 Unsymmetrical loads due to engine failure [AMC & GM to CS - 23: Issue 5]

AM C3 23.2 2 15 Flight load conditions

ED Decision 2026/003/R CS VLA Amdt 1 VLA.331 Symmetrical flight conditions VLA.333 Flight envelope VLA.347 Unsymmetrical flight loads VLA.349 Rolling conditions VLA.351 Yawing conditions [AMC & GM to CS - 23: Issue 5]

CS 23.2220 Ground and water load conditions

ED Decision 2017/013/R The applicant must determine the structural design loads resulting from taxi, take - off, landing, and handling conditions on the applicable surface in normal and adverse attitudes and configurations.

AMC1 23.22 20 Ground and water load conditions

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 6.5 Ground and Water Load Conditions F3116/F3116M - 24 Standard Specification for Design Loads and Conditions F3331 - 18 Standard Practice for Aircraft Water Loads [AMC & GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5] Powered by EASA eRules Page 50 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART C — STRUCTURES

AMC2 23.2220 Ground and water load conditions

ED Decision 2017/025/R CS - 23 Amdt 4 23.477 Landing gear arrangement (With Appendix C) 23.479 level landing conditions (With Appendix C, D) 23.481 Tail down landing conditions 23.483 One - wheel landing conditions 23.485 Side load conditions 23.493 Braked roll conditions 23.505 Supplementary conditions for skiplanes 23.529 Hull and main float landing conditions 23.531 Hull and main float takeoff conditions 23.731 Wheels

AM C3 23.2220 Ground and water load conditions

ED Decision 2017/025/R CS VLA Amdt 1 VLA.477 Landing gear arrangement ( With Appendix C ) VLA.479 level landing conditions VLA.481 Tail down landing conditions VLA.483 One - wheel landing conditions VLA.485 Side load conditions VLA.493 Braked roll conditions VLA.505 Supplementary conditions for skiplanes VLA.731 Wheels

CS 23.2225 Component loading conditions

ED Decision 2017/013/R (a) The applicant must determine the loads acting upon all relevant structural components, in response to: (1) interaction of systems and structures; (2) structural design loads; (3) flight load conditions; and (4) ground and water load conditions.

(b) The complete pressurised cabin, including doors, windows, canopy and valves, is exposed as a pressure vessel for the maximum relief valve setting multiplied by a factor of 1.33, without considering other loads.

Powered by EASA eRules Page 51 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART C — STRUCTURES

AMC1 23.22 25 Component loading conditions

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 6.6 Component Loading Conditions F3061/F3061M - 24a Standard Specification for Systems and Equipment in Small Aircraft F3232/F3232M - 25 Standard Specification for Flight Controls in Small Aircraft F3116/F3116M - 24 Standard Specification for Design Loads and Conditions F3396/F3396M - 20 Standard Practice for Aircraft Simplified Loads Criteria [AMC & GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5]

AMC2 23.2225 Component loading conditions

ED Decision 2017/025/R CS - 23 Amdt 4 23.302 Canard or tandem wing configurations 23.361 Engine torque 23.363 Side load on engine mount 23.365 Pressurized cabin loads 23.369 Rear lift truss 23.371 Gyroscopic and aerodynamic loads 23.373 Speed control devices 23.391 Control surface loads 23.393 Loads parallel to hinge line 23.395 Control system loads 23.397 Limit control forces and torques 23.399 Dual control system 23.405 Secondary control system 23.407 Trim tab effects 23.409 Tabs 23.415 Ground gust conditions 23.421 Balancing loads 23.423 Manoeuvring loads 23.425 Gust loads 23.427 Unsymmetrical loads 23.441 Manoeuvring loads 23.443 Gust loads Powered by EASA eRules Page 52 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART C — STRUCTURES 23.445 Outboard fins or winglets 23.455 Ailerons 23.459 Special devices 23.497 Supplementary conditions for tail wheels 23.499 Supplementary conditions for nose wheels 23.533 Hull and main float bottom pressures (With Appendix I) 23.535 Auxiliary float loads 23.659 Mass Balance

AM C3 23.2225 Component loading conditions

ED Decision 2017/025/R CS VLA Amdt 1 VLA.361 Engine torque VLA.363 Side load on engine mount VLA.369 Rear lift truss VLA.373 Speed control devices VLA.391 Control surface loads ( With Appendix B ) VLA.395 Control system loads VLA.397 Limit control forces and torques VLA.399 Dual control system VLA.405 Secondary control system VLA.407 Trim tab effects VLA.409 Tabs VLA.415 Ground gust conditions VLA.421 Balancing loads ( With Appendix B ) VLA.423 Manoeuvring loads ( With Appendix B ) VLA.425 Gust loads VLA.427 Unsymmetrical loads VLA.441 Manoeuvring loads ( With Appendix B ) VLA.443 Gust loads ( With Appendix B ) VLA.445 Outboard fins or winglets VLA.447 Combined loads on tail surfaces VLA.449 Additional loads applicable to V - tails VLA.455 Ailerons ( With Appendix B ) VLA.457 Wing flaps Powered by EASA eRules Page 53 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART C — STRUCTURES VLA.459 Special devices VLA.497 Supplementary conditions for tail wheels VLA.499 Supplementary conditions for nose wheels VLA.659 Mass Balance

CS 23.2230 Limit and ultimate loads

ED Decision 2017/013/R (a) Unless special or other factors of safety are necessary to meet the requirements of this Subpart, the applicant must determine: (1) the limit loads, which are equal to the structural design loads; and (2) the ultimate loads, which are equal to the limit loads multiplied by a 1.5 factor of safety, unless otherwise provided.

(b) Some strength specifications are specified in terms of ultimate loads only, when permanent detrimental deformation is acceptable.

AMC1 23.22 30 Limit and ultimate loads

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 6.7 Limit and Ultimate Loads F3114 - 21 Standard Specification for Structures F3408/F3408M - 21 Standard Specification for Aircraft Emergency Parachute Recovery Systems [AMC & GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5]

AMC2 23.2230 Limit and ultimate loads

ED Decision 2017/025/R CS - 23 Amdt 4 23.301(a) Loads 23.303 Factors of safety

AM C3 23.2230 Limit and ultimate loads

ED Decision 2017/025/R CS VLA Amdt 1 VLA.301 Loads VLA.303 Factors of safety Powered by EASA eRules Page 54 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART C — STRUCTURES

STRUCTURAL PERFORMANCE

CS 23.2235 Structural strength

ED Decision 2017/013/R The structure must support: (a) limit loads without: (1) interference with the safe operation of the aeroplane; and (2) detrimental permanent deformation.

(b) ultimate loads.

AMC1 23.22 35 Structural strength

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 6.8 Structural Strength F3114 - 21 Standard Specification for Structures F3408/F3408M - 21 Standard Specification for Aircraft Emergency Parachute Recovery Systems [AMC & GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5]

AMC2 23.2235 Structural strength

ED Decision 2017/025/R CS - 23 Amdt 4 23.305 Strength and deformation 23.307 Proof of structure 23.641 Proof of strength - Wings 23.651 Proof of strength - Control surfaces 23.659 Mass Balance 23.681 (a) Limit load static tests - Control System 23.723 Shock absorption tests 23.725 Limit drop tests 23.726 Ground load dynamic tests 23.727 Reserve energy absorption drop tests 23.729(a) Landing gear extension and retraction system 23.737 Skis 23.843(a) Pressurization tests 23.1435(a)(1) Hydraulic Systems Powered by EASA eRules Page 55 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART C — STRUCTURES

AM C3 23.2235 Structural strength

ED Decision 2017/025/R CS VLA Amdt 1 VLA.305 Strength and deformation VLA.307 Proof of structure VLA.641 Proof of strength - Wings VLA.651 Proof of strength - Control surfaces VLA.659 Mass Balance VLA.681 Limit load static tests - Control System VLA.723 Shock absorption tests VLA.725 Limit drop tests VLA.726 Ground load dynamic tests VLA.727 Reserve energy absorption drop tests VLA.729 Landing gear extension and retraction system VLA.737 Skis VLA.1436 Hydraulic manually - powered brake systems

CS 23.2240 Structural durability

ED Decision 2017/013/R (a) The applicant must develop and implement inspections or other procedures to prevent structural failures due to foreseeable causes of strength degradation, which could result in serious or fatal injuries, or extended periods of operation with reduced safety margins. Each of the inspections or other procedures developed under CS 23.2240 must be included in the Airworthiness Limitations Section of the Instructions for Continued Airworthiness required by CS 23.2625 .

(b) For Level - 4 aeroplanes, the procedures developed for compliance with CS 23.2240(a) must be capable of detecting structural damage before the damage could result in structural failure.

(c) For pressurised aeroplanes: (1) the aeroplane must be capable of continued safe flight and landing following a sudden release of cabin pressure, including sudden releases caused by door and window failures; (2) for aeroplanes with maximum operating altitude greater than 12 497 m (41 000 ft), the procedures developed for compliance with CS 23.2240(a) must be capable of detecting damage to the pressurised cabin structure before the damage could result in rapid dec ompression that would result in serious or fatal injuries.

(d) The aeroplane must be designed to minimise hazards to the aeroplane due to structural damage caused by high - energy fragments from an uncontained engine or rotating - machinery failure.

Powered by EASA eRules Page 56 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART C — STRUCTURES

AMC1 23.22 40 Structural durability

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 6.9 Structural Durability & 9.11 Equipment Containing High - Energy Rotors F3061/F3061M - 24a Standard Specification for Systems and Equipment in Small Aircraft F3066/F3066M - 18 Standard Specification for Aircraft Powerplant Installation Hazard Mitigation F3115/F3115M - 15 Standard Specification for Structural Durability for Small Aeroplanes F3380 - 19 Standard Practice for Structural Compliance of Very Light Aeroplanes F3116/F3116M - 24 Standard Specification for Design Loads and Conditions F3498 - 21 Standard Practice for Developing Simplified Fatigue Load Spectra [AMC & GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5]

AMC2 23.2240 Structural durability

ED Decision 2017/025/R CS - 23 Amdt 4 23.571 Metallic pressurized cabin structures 23.572 Metallic wing, empennage, and associated structures 23.573 Damage tolerance and fatigue evaluation of structure 23.574 Metallic damage tolerance and fatigue evaluation of commuter category airplanes 23.575 Inspections and other procedures 23.627 Fatigue strength 23.1461 Equipment containing high - energy rotors

AM C3 23.2240 Structural durability

ED Decision 2017/025/R CS VLA Amdt 1 VLA.572 Metallic wing, empennage, and associated structures VLA.627 Fatigue strength

CS 23.2245 Aeroelasticity

ED Decision 2017/013/R (a) The aeroplane must be free from flutter, control reversal, and divergence: (1) at all speeds within and sufficiently beyond the structural design envelope; (2) for any configuration and condition of operation; (3) accounting for critical degrees of freedom; and (4) accounting for any critical failures or malfunctions.

Powered by EASA eRules Page 57 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART C — STRUCTURES (b) The applicants’ design must account for tolerances for all quantities that affect flutter.

AMC1 23.22 45 Aeroelasticity

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 6.10 Aeroelasticity F3061/F3061M - 24a Standard Specification for Systems and Equipment in Small Aircraft F3093/F3093M - 21 Standard Specification for Aeroelasticity Requirements [AMC & GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5]

AMC2 23.2245 Aeroelasticity

ED Decision 2017/025/R CS - 23 Amdt 4 23.629 Flutter 23.687 Spring devices 23.677(c) Trim systems

AM C3 23.2245 Aeroelasticity

ED Decision 2017/025/R CS VLA Amdt 1 VLA.629 Flutter VLA.687 Spring devices VLA.677 Trim systems

CS 23.2250 Design and construction principles

ED Decision 2017/013/R (a) Each part, article, and assembly must be designed for the expected operating conditions of the aeroplane.

(b) Design data must adequately define the part, article, or assembly configuration, its design features, and any materials and processes used.

(c) The suitability of each design detail and part having an important bearing on safety in operations must be determined.

(d) The control system must be free from jamming, excessive friction, and excessive deflection when the aeroplane is subjected to expected limit air loads.

(e) Doors, canopies, and exits must be protected against inadvertent opening in flight, unless shown to create no hazard, when opened in flight.

Powered by EASA eRules Page 58 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART C — STRUCTURES

AMC1 23.22 50 Design and construction principles

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 6.11 Design and Construction Principles F3061/F3061M - 24a Standard Specification for Systems and Equipment in Small Aircraft F3232/F3232M - 25 Standard Specification for Flight Controls in Small Aircraft F3114 - 21 Standard Specification for Structures F3380 - 19 Standard Practice for Structural Compliance of Very Light Aeroplanes F3408/F3408M - 21 Standard Specification for Aircraft Emergency Parachute Recovery Systems [AMC & GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5]

AMC2 23.2250 Design and construction principles

ED Decision 2017/025/R CS - 23 Amdt 4 23.601 General 23.603 Materials and workmanship 23.683 Operation tests 23.687 Spring devices 23.689 Cable systems 23.731 Wheels 23.733(a), (c) Tires 23.735(b) Brakes 23.775(b), (c), (d) Windshields and windows 23.783(b), (c)(1), (e) Doors 23.807(d)(2) Emergency Exits 23.859(b) through (i) Combustion heater fire protection 23.1323 Airspeed indicating system 23.1325(a) through (e) Static Pressure System 23.1435(a)(3), (c) Hydraulic Systems 23.1445(a), (b) Oxygen distribution system

AM C3 23.2250 Design and construction principles

ED Decision 2017/025/R CS VLA Amdt 1 VLA.601 General Powered by EASA eRules Page 59 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART C — STRUCTURES VLA.603 Materials and workmanship VLA.683 Operation tests VLA.687 Spring devices VLA.689 Cable systems VLA.731 Wheels VLA.733 Tires VLA.735 Brakes VLA.775 Windshields and windows VLA.783 Exits VLA.807 Emergency Exits VLA.1323 Airspeed indicating system VLA.1325 Static Pressure System VLA.1436 Hydraulic manually - powered brake systems

CS 23.2255 Protection of structure

ED Decision 2017/013/R (a) Each part of the aeroplane, including small parts such as fasteners, must be protected against deterioration or loss of strength due to any cause likely to occur in the expected operational environment.

(b) Each part of the aeroplane must have adequate provisions for ventilation and drainage.

(c) For each part that requires maintenance, preventive maintenance, or servicing, the applicant must incorporate a means into the aeroplane design to allow such actions to be accomplished.

AMC1 23.22 55 Protection of structure

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 6.12 Protection of Structure F3061/F3061M - 24a Standard Specification for Systems and Equipment in Small Aircraft F3232/F3232M - 25 Standard Specification for Flight Controls in Small Aircraft F3114 - 21 Standard Specification for Structures F3380 - 19 Standard Practice for Structural Compliance of Very Light Aeroplanes F3066/F3066M - 18 Standard Specification for Aircraft Powerplant Installation Hazard Mitigation F3408/F3408M - 21 Standard Specification for Aircraft Emergency Parachute Recovery Systems [AMC & GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5] Powered by EASA eRules Page 60 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART C — STRUCTURES

AMC2 23.2255 Protection of structure

ED Decision 2017/025/R CS - 23 Amdt 4 23.607 Fasteners 23.609 Protection of Structure 23.611 Accessibility 23.689(a)(3) Cable systems

AM C3 23.2255 Protection of structure

ED Decision 2017/025/R CS VLA Amdt 1 VLA.607 Self - locking nuts VLA.609 Protection of Structure VLA.611 Accessibility VLA.689 Cable systems

CS 23.2260 Materials and processes

ED Decision 2017/013/R (a) The applicant must determine the suitability and durability of materials used for parts, articles, and assemblies, the failure of which could prevent continued safe flight and landing, accounting for the effects of likely environmental conditions expected in service.

(b) The methods and processes of fabrication and assembly used must produce consistently sound structures. If a fabrication process requires close control to reach this objective, the applicant must define the process with an approved process specification as part of the design data.

(c) Except as provided for in CS 23.2260(f) and (g), the applicant must select design values that ensure material strength with probabilities that account for the criticality of the structural element. Design values must account for the probability of structu ral failure due to material variability.

(d) If material strength properties are required, a determination of those properties must be based on sufficient tests of material meeting specifications to establish design values on a statistical basis.

(e) If thermal effects are significant on a critical component or structure under normal operating conditions, the applicant must determine those effects.

(f) Design values, greater than the minimums specified by CS 23.2260, may be used, where only guaranteed minimum values are normally allowed, if a specimen of each individual item is tested before use to determine that the actual strength properties of that p articular item will equal or exceed those used in the design.

(g) An applicant may use other material design values if specifically approved by EASA.

Powered by EASA eRules Page 61 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART C — STRUCTURES

AMC1 23.22 60 Materials and processes

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 6.13 Materials and Processes F3114 - 21 Standard Specification for Structures F3380 - 19 Standard Practice for Structural Compliance of Very Light Aeroplanes F3408/F3408M - 21 Standard Specification for Aircraft Emergency Parachute Recovery Systems [AMC & GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5]

AMC2 23.2260 Materials and processes

ED Decision 2017/025/R CS - 23 Amdt 4 23.603 Materials and workmanship 23.605 Fabrication methods 23.613 Material strength properties and design values

AM C3 23.2260 Materials and processes

ED Decision 2017/025/R CS VLA Amdt 1 VLA.603 Materials and workmanship VLA.605 Fabrication methods VLA.613 Material strength properties and design values

CS 23.2265 Special factors of safety

ED Decision 2017/013/R (a) The applicant must determine a special factor of safety for each critical design value for each part, article, or assembly for which that critical design value is uncertain, and for each part, article, or assembly that is: (1) likely to deteriorate in service before normal replacement; or (2) subject to appreciable variability because of uncertainties in manufacturing processes or inspection methods.

(b) The applicant must determine a special factor of safety using quality controls and specifications that account for each: (1) type of application; (2) inspection method; Powered by EASA eRules Page 62 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART C — STRUCTURES (3) structural test requirement; (4) sampling percentage; and (5) process and material control.

(c) The applicant must multiply the highest pertinent special factor of safety in the design for each part of the structure by each limit load and ultimate load, or ultimate load only, if there is no corresponding limit load, such as occurs with emergency con dition loading.

AMC1 23.22 65 Special factors of safety

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 6.14 Special Factors of Safety F3061/F3061M - 24a Standard Specification for Systems and Equipment in Small Aircraft F3114 - 21 Standard Specification for Structures F3380 - 19 Standard Practice for Structural Compliance of Very Light Aeroplanes [AMC & GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5]

AMC2 23.2265 Special factors of safety

ED Decision 2017/025/R CS - 23 Amdt 4 23.619 Special factors 23.621 Casting factors 23.623 Bearing factors 23.625 Fitting factors 23.657 Hinges 23.681(b) Limit load static tests - Control System 23.693 Joints 23.785 Seats, berths, litters, safety belts, and shoulder harnesses

AM C3 23.2265 Special factors of safety

ED Decision 2017/025/R CS VLA Amdt 1 VLA.619 Special factors VLA.621 Casting factors VLA.623 Bearing factors VLA.625 Fitting factors VLA.657 Hinges Powered by EASA eRules Page 63 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART C — STRUCTURES VLA.681 Limit load static tests - Control System VLA.693 Joints VLA.785 Seats, safety belts, and harnesses Powered by EASA eRules Page 64 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART C — STRUCTURES

STRUCTURAL OCCUPANT PROTECTION

CS 23.2270 Emergency conditions

ED Decision 2017/013/R (a) The aeroplane, even when damaged in an emergency landing, must protect each occupant against injury that would preclude egress when: (1) properly using safety equipment and features provided for in the design; (2) the occupant experiences ultimate static inertia loads likely to occur in an emergency landing; and (3) items of mass, including engines or auxiliary power units (APUs), within or aft of the cabin, that could injure an occupant, experience ultimate static inertia loads likely to occur in an emergency landing.

(b) The emergency landing conditions specified in CS 23.2270(a) must: (1) include dynamic conditions that are likely to occur in an emergency landing; and (2) not generate loads experienced by the occupants, which exceed established human - injury criteria for human tolerance due to restraint or contact with objects in the aeroplane.

(c) The aeroplane must provide protection for all occupants, accounting for likely flight, ground, and emergency landing conditions.

(d) Each occupant protection system must perform its intended function and not create a hazard that could cause a secondary injury to an occupant. The occupant protection system must not prevent occupant egress or interfere with the operation of the aeroplane when not in use.

(e) Each baggage and cargo compartment must: (1) be designed for its maximum loading and for the critical load distributions at the maximum load factors corresponding to the flight and ground load conditions determined under this CS; (2) have a means to prevent the contents of the compartment from becoming a hazard by impacting occupants or shifting; and (3) protect controls, wiring, lines, equipment, or accessories whose damage or failure would prevent continued safe flight and landing.

AMC1 23.22 70 Emergency c onditions

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 6.15 Emergency Conditions F3061/F3061M - 24a Standard Specification for Systems and Equipment in Small Aircraft F3232/F3232M - 25 Standard Specification for Flight Controls in Small Aircraft F3083/F3083M - 20a Standard Specification for Emergency Conditions, Occupant Safety and Accommodations Powered by EASA eRules Page 65 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART C — STRUCTURES F3408/F3408M - 21 Standard Specification for Aircraft Emergency Parachute Recovery Systems [AMC & GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5]

AMC2 23.2270 Emergency Conditions

ED Decision 2017/025/R CS - 23 Amdt 4 23.561 Emergency Landing Conditions - General (With Appendix J ) 23.562 Emergency landing dynamic conditions 23.785 Seats, berths, litters, safety belts, and shoulder harnesses 23.787 Baggage and cargo compartments 23.1411(b) Safety equipment - General

AM C3 23.2270 Emergency Conditions

ED Decision 2017/025/R CS VLA Amdt 1 VLA.561 Emergency Landing Conditions - General VLA.785 Seats, safety belts, and harnesses VLA.787 Baggage compartments VLA.1411 Safety equipment - General Powered by EASA eRules Page 66 of 118 | May 2026

Next: SUBPART D — DESIGN AND CONSTRUCTION →

SUBPART D — DESIGN AND CONSTRUCTION

Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART D — DESIGN AND CONSTRUCTION

SUBPART D — DESIGN AND CONSTRUCTION

CS 23.2300 Flight control systems

ED Decision 2017/013/R (a) The flight control systems are designed to: (1) operate easily, smoothly, and positively enough to allow proper performance of their functions; (2) protect against likely hazards.

(b) Trim systems, if installed, are designed to: (1) protect against inadvertent, incorrect, or abrupt trim operation; (2) provide information that is required for safe operation.

AMC1 23.2300 Flight control systems

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 7.1 Flight Control Systems F3061/F3061M - 24a Standard Specification for Systems and Equipment in Small Aircraft F3232/F3232M - 25 Standard Specification for Flight Controls in Small Aircraft F3066/F3066M - 18 Standard Specification for Aircraft Powerplant Installation Hazard Mitigation F3117/F3117M - 24a Standard Specification for Crew Interface in Aircraft Remarks Except as follows: For Level 1 single - engine aeroplanes with a stall speed in the landing configuration (V ) of m ore than S0 45 knots, ASTM F3264 - 2 4 , paragraph 7.1 does not include means for showing that the aeroplane is protected from loss of control when any one connecting or transmitting element in the primary flight control system fails. If applying for certification of a Level 1 single - engine aeroplane with a V greater S0 than 45 knots, applicants may use the requirements of CS 23.677(b)(1) at Amendment 4 as a means of complying with this aspect of CS 23.2300 , or may propose a different means of compliance in accordance with CS 23.2010 .

For powered trim, applicants may use the provisions of CS 23.677(d) at Amendment 4 as a means of complying with CS 23.2010 .

[AMC & GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5]

AMC2 23.2300 Flight control systems

ED Decision 2017/025/R CS - 23 Amdt 4 23.655 Installation 23.671(a) Control systems - General Powered by EASA eRules Page 67 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART D — DESIGN AND CONSTRUCTION 23.672(b), (c) Stability augmentation and automatic and power - operated systems 23.673 Primary flight controls 23.675 Stops 23.677(a), (b) Trim systems 23.679(c) Control system locks 23.683 Operation tests 23.685 Control system details 23.687 Spring devices 23.697 Wing flap controls 23.701 Flap interconnection 23.1329(b) Automatic Pilot System

AM C3 23.2300 Flight control systems

ED Decision 2017/025/R CS VLA Amdt 1 VLA.655 Installation VLA.671 Control systems - General VLA.673 Primary flight controls VLA.675 Stops VLA.677 Trim systems VLA.679 Control system locks VLA.683 Operation tests VLA.685 Control system details VLA.687 Spring devices VLA.697 Wing flap controls VLA.701 Flap interconnection

CS 23.2305 Landing gear systems

ED Decision 2017/013/R (a) The landing gear is designed to: (1) provide stable support and control to the aeroplane during surface operation; and (2) account for likely system failures and likely operation environment (including anticipated limitation exceedances and emergency procedures).

(b) Aeroplanes must have a reliable means of stopping the aeroplane with sufficient kinetic energy absorption to account for landing. Aeroplanes that are required to demonstrate aborted take - off capability must account for this additional kinetic energy.

Powered by EASA eRules Page 68 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART D — DESIGN AND CONSTRUCTION (c) For aeroplanes that have a system that actuates the landing gear, there is: (1) a positive means to keep the landing gear in the landing position; and (2) an alternative means available to bring the landing gear in the landing position when a non - deployed system position would be a hazard.

AMC1 23.2305 Landing gear systems

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 7.2 Landing Gear Systems F3061/F3061M - 24a Standard Specification for Systems and Equipment in Small Aircraft [AMC & GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5]

AMC2 23.2305 Landing gear systems

ED Decision 2017/025/R CS - 23 Amdt 4 23.721 General 23.729(b), (c), (g) Landing gear extension and retraction system 23.735(a), (b), (c), (e) Brakes 23.745 Nose/Tail wheel steering

AM C3 23.2305 Landing gear systems

ED Decision 2017/025/R CS VLA Amdt 1 VLA.729 Landing gear extension and retraction system VLA.735 Brakes

CS 23.2310 Buoyancy for seaplanes and amphibians

ED Decision 2017/013/R Aeroplanes intended for operations on water must: (a) provide buoyancy of 80 % in excess of the buoyancy required to support the maximum weight of the aeroplane in fresh water; and (b) have sufficient margin so that the aeroplane will stay afloat at rest in calm water without capsizing in case of a likely float or hull flooding.

Powered by EASA eRules Page 69 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART D — DESIGN AND CONSTRUCTION

AMC1 23.2310 Buoyancy for seaplanes and amphibians

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 7.3 Buoyancy for Seaplanes and Amphibians F3061/F3061M - 24a Standard Specification for Systems and Equipment in Small Aircraft [AMC & GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5]

AMC2 23.2310 Buoyancy for seaplanes and amphibians

ED Decision 2017/025/R CS - 23 Amdt 4 23.751 Main float buoyancy 23.755 Hulls 23.757 Auxiliary floats

AM C3 23.2310 Buoyancy for seaplanes and amphibians

ED Decision 2017/025/R CS VLA Amdt 1 VLA.751 Main float buoyancy VLA.757 Auxiliary floats Powered by EASA eRules Page 70 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART D — DESIGN AND CONSTRUCTION

OCCUPANT SYSTEM DESIGN PROTECTION

CS 23.2315 Means of egress and emergency exits

ED Decision 2017/013/R (a) With the cabin configured for take - off or landing, the aeroplane is designed to: (1) Facilitate rapid and safe evacuation of the aeroplane in conditions likely to occur following an emergency landing, excluding ditching for Level - 1, Level - 2 and single - engine Level - 3 aeroplanes.

(2) Have means of egress (openings, exits or emergency exits) that can be readily located and opened from the inside and outside. The means of opening must be simple and obvious.

(3) Have easy access to emergency exits when present.

(b) Aeroplanes approved for aerobatics must have a means to egress the aeroplane in flight.

AMC1 23.231 5 Means of egress and emergency exits

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 7.4 Means of Egress and Emergency Exits F3061/F3061M - 24a Standard Specification for Systems and Equipment in Small Aircraft F3083/F3083M - 20a Standard Specification for Emergency Conditions, Occupant Safety and Accommodations [AMC & GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5]

AMC2 23.2315 Means of egress and emergency exits

ED Decision 2017/025/R CS - 23 Amdt 4 23.783(a), (b), (c)(2), (c)(3), (c)(4), (c)(5), (c)(6), (d), (f), (g) Doors 23.787 Baggage and cargo compartments 23.803 Emergency evacuation 23.805 Flight crew emergency exits 23.807(a), (b)(1), (b)(2), (b)(3), (b)(4), (b) (5), (b)(6) (d)(1), (d)(3), (d)(4), (c), (e) Emergency exits 23.811 Emergency exit marking 23.812 Emergency lighting 23.813 Emergency exit access 23.815 Width of aisle Powered by EASA eRules Page 71 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART D — DESIGN AND CONSTRUCTION

AM C3 23.2315 Means of egress and emergency exits

ED Decision 2017/025/R CS VLA Amdt 1 VLA.783 Exits VLA.787 Baggage compartments VLA.807 Emergency exits

CS 23.2320 Occupant physical environment

ED Decision 2017/013/R (a) The applicant must design the aeroplane to: (1) allow clear communication between the flight crew and passengers; (2) protect the pilot against serious injury due to hazards originating from high energy, associated with systems and equipment; and (3) protect the occupants from serious injury due to breakage of windshields, windows, and canopies.

(b) For Level - 4 aeroplanes, each windshield and its supporting structure directly in front of the pilot must withstand, without penetration, the impact equivalent to a two - pound bird when the velocity of the aeroplane is equal to the aeroplane’s maximum appro ach flap speed.

(c) The aeroplane must provide each occupant with air at a breathable pressure, free of hazardous concentrations of gases, vapours and smoke during normal operations and likely failures.

(d) If a pressurisation system is installed in the aeroplane, it must be designed to protect against: (1) decompression to an unsafe level; and (2) excessive differential pressure.

(e) If an oxygen system is installed in the aeroplane, it must: (1) effectively provide oxygen to each user to prevent the effects of hypoxia; and (2) be free from hazards in itself, in its method of operation, and its effect upon other components.

AMC1 23.2320 Occupant physical environment

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 7.5 Occupant Physical Environment F3061/F3061M - 24a Standard Specification for Systems and Equipment in Small Aircraft F3083/F3083M - 20a Standard Specification for Emergency Conditions, Occupant Safety and Accommodations F3114 - 21 Standard Specification for Structures F3117/F3117M - 24a Standard Specification for Crew Interface in Aircraft Remarks F3227/F3227M - 25 Standard Specification for Environmental Systems in Aircraft Powered by EASA eRules Page 72 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART D — DESIGN AND CONSTRUCTION At variance with F3227 - 25, Oxygen Fire Hazards Analysis is not completely covered in the current ASTM standards. At variance, additional means of compliance have been developed by EASA for the specific application.

[AMC & GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5]

AMC2 23.2320 Occupant physical environment

ED Decision 2017/025/R CS - 23 Amdt 4 23.831(a), (b), (c) Ventilation 23.841(a), (b)(1), (b)(2), (b)(3), (b)(4), (b)(8), (c), (d)(1), (d)(2),(d)(3) Pressurized cabins 23.843 Pressurization tests 23.771(b), (c) Pilot compartment 23.775(a), (h)(1) Windshields and windows 23.791 Passenger information signs 23.1441 Oxygen Equipment and supply 23.1443 Minimum mass flow of supplemental oxygen 23.1445 Oxygen distribution system 23.1447 Equipment standards for oxygen dispensing units 23.1449 Means for determining use of oxygen 23.1450(a), (b) Chemical oxygen generators 23.1451 Fire protection for oxygen equipment 23.1461 Equipment containing high - energy rotors

AM C3 23.2320 Occupant physical environment

ED Decision 2017/025/R CS VLA Amdt 1 VLA.831 Ventilation VLA.771 Pilot compartment VLA.775 Windshields and windows Powered by EASA eRules Page 73 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART D — DESIGN AND CONSTRUCTION

FIRE AND HIGH ENERGY PROTECTION

CS 23.2325 Fire protection

ED Decision 2017/013/R (a) The aeroplane is designed to minimise the risk of fire initiation due to: (1) anticipated heat or energy dissipation or system failures or overheat that are expected to generate heat sufficient to ignite a fire; (2) ignition of flammable fluids, gases or vapours; and (3) fire - propagating or - initiating system characteristics (e.g. oxygen systems).

(b) The aeroplane is designed to minimise the risk of fire propagation by: (1) providing adequate fire or smoke awareness and extinguishing means when practical; (2) application of self - extinguishing, flame - resistant, or fireproof materials that are adequate to the application, location and certification level; or (3) specifying and designing designated fire zones that meet the specifications of CS 23.2330 .

AMC1 23.2325 Fire protection

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 7.6 Fire Protection F3061/F3061M - 24a Standard Specification for Systems and Equipment in Small Aircraft F3231/F3231M - 24 Standard Specification for Electrical Systems for Aircraft with Combustion Engine Electrical Power Generation F3234/F3234M - 21 Standard Specification for Exterior Lighting in Small Aircraft F3066/F3066M - 18 Standard Specification for Aircraft Powerplant Installation Hazard Mitigation F3083/F3083M - 20a Standard Specification for Emergency Conditions, Occupant Safety and Accommodations F3408/F3408M - 21 Standard Specification for Aircraft Emergency Parachute Recovery Systems Remarks ASTM F44 published standards for showing compliance for electrical systems that are installed on aeroplanes with electric or hybrid - electric propulsion systems. EASA has not yet accepted F3316 - 19 ; however, EASA would take into consideration applications from applicants that use this standard as the basis for the development of their means of compliance subject to agreement with EASA.

[AMC & GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5] Powered by EASA eRules Page 74 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART D — DESIGN AND CONSTRUCTION

AMC2 23.2325 Fire protection

ED Decision 2017/025/R CS - 23 Amdt 4 23.1453 Protection of oxygen equipment from rupture 23.851 Fire extinguishers 23.853 Passenger and crew compartment interiors (With Appendix F) 23.855 Cargo and baggage compartment fire protection (With Appendix F) 23.859(a) Combustion heater fire protection 23.863 Flammable Fluid Fire Protection 23.1337(a) Powerplant instruments installation 23.1351 Electrical system: General 23.1359(a), (c) Electrical System fire protection 23.1383(d) Taxi and landing lights (With Appendix F) 23.1385(d) Position light system installation

AM C3 23.2325 Fire protection

ED Decision 2017/025/R CS VLA Amdt 1 VLA.853 Passenger and crew compartment interiors (With Appendix F) VLA.857 Electrical bonding VLA.863 Flammable Fluid Fire Protection VLA.1337 Powerplant instruments installation VLA.1351 Electrical system: General VLA.1384 External lights

CS 23.2330 Fire protection in designated fire zones

ED Decision 2017/013/R (a) Flight controls, engine mounts, and other flight structures within or adjacent to designated fire zones must be capable of withstanding the effects of a fire.

(b) A fire in a designated fire zone must not preclude continued safe flight and landing.

(c) Terminals, equipment, and electrical cables used during emergency procedures must be fire - resistant.

AMC1 23.2330 Fire protection in designated fire zones

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 7.7 Fire Protection in Designated Fire Zones and Adjacent Areas Powered by EASA eRules Page 75 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART D — DESIGN AND CONSTRUCTION F3061/F3061M - 24a Standard Specification for Systems and Equipment in Small Aircraft F3231/F3231M - 24 Standard Specification for Electrical Systems for Aircraft with Combustion Engine Electrical Power Generation F3066/F3066M - 18 Standard Specification for Aircraft Powerplant Installation Hazard Mitigation F3114 - 21 Standard Specification for Structures [AMC & GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5]

AMC2 23.2330 Fire protection in designated fire zones

ED Decision 2017/025/R CS - 23 Amdt 4 23.865 Fire protection of flight controls, engine mounts, and other flight structure 23.1359(a), (b) Electrical System fire protection (With Appendix F) 23.1365(b) Electrical Cables and equipment

AM C3 23.2330 Fire protection in designated fire zones

ED Decision 2017/025/R CS VLA Amdt 1 VLA.865 Fire protection of flight controls and other flight structure VLA.1365 Electrical Cables and equipment

CS 23.2335 Lightning protection

ED Decision 2017/013/R For operations where the exposure to lightning is likely, the aeroplane must be protected against catastrophic effects of lightning.

AMC1 23.2335 Lightning protection

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 7.8 Lightning Protection F3061/F3061M - 24a Standard Specification for Systems and Equipment in Small Aircraft [AMC & GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5]

AMC2 23.2335 Lightning protection

ED Decision 2017/025/R CS - 23 Amdt 4 23.867 Electrical bonding and protection against lightning and static electricity 23.1365 Electrical Cables and equipment Powered by EASA eRules Page 76 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART D — DESIGN AND CONSTRUCTION

AM C3 23.2335 Lightning protection

ED Decision 2017/025/R CS VLA Amdt 1 VLA.857 Electrical bonding VLA.1365 Electrical Cables and equipment

CS 23.2340 Design and construction information

ED Decision 2017/013/R The following design and construction information is established: (a) operating limitations, procedures and instructions necessary for the safe operation of the aeroplane; (b) the need for instrument markings or placards; (c) any additional information necessary for the safe operation of the aeroplane; and (d) inspections or maintenance to assure continued safe operation.

AMC1 23.234 0 Design and construction information

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 7.9 Design and Construction Information F3117/F3117M - 24a Standard Specification for Crew Interface in Aircraft [AMC & GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5]

AMC2 23.234 0 Design and construction information

ED Decision 2017/025/R CS - 23 Amdt 4 23.1523 Minimum Flight Crew 23.1524 Maximum passenger seating configuration 23.1529 Instructions for continued airworthiness (With Appendix G) 23.1541 Markings and placards: General

AM C3 23.2340 Design and construction information

ED Decision 2017/025/R CS VLA Amdt 1 VLA.1529 Instructions for continued airworthiness VLA.1541 Markings and placards: General Powered by EASA eRules Page 77 of 118 | May 2026

Next: SUBPART E — POWERPLANT INSTALLATION →

SUBPART E — POWERPLANT INSTALLATION

Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART E — POWERPLANT INSTALLATION

SUBPART E — POWERPLANT INSTALLATION

CS 23.2400 Powerplant installation

ED Decision 2017/013/R (a) For the purpose of this Subpart, the aeroplane powerplant installation must include each component that is necessary for propulsion, affects propulsion safety, or provides auxiliary power to the aeroplane.

(b) Each aeroplane engine, propeller and auxiliary power unit (APU) must be type certified, or meet accepted specifications.

(c) The applicant must construct and arrange each powerplant installation to account for: (1) all likely operating conditions, including foreign object threats; (2) sufficient clearance of moving parts to other aeroplane parts and their surroundings; (3) likely hazards in operation, including hazards to ground personnel; and (4) vibration and fatigue.

(d) Hazardous accumulations of fluids, vapours or gases are isolated from the aeroplane and personnel compartments and are safely contained or discharged.

(e) Installations of powerplant components that deviate from the component limitations or installation instructions must be shown to be safe.

(f) For the purposes of this Subpart, ‘energy’ means any type of energy for the powerplant, including, for example, fuels of any kind or electric current.

AMC1 23.2400 Powerplant installation

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 8.1 Powerplant Installation F3062/F3062M - 20 Standard Specification for Aircraft Powerplant Installation F3063/F3063M - 21 Standard Specification for Aircraft Fuel Storage and Delivery F3064/F3064M - 21 Standard Specification for Aircraft Powerplant Control, Operation, and Indication F3065/F3065M - 21a Standard Specification for Aircraft Propeller System Installation F3066/F3066M - 18 Standard Specification for Aircraft Powerplant Installation Hazard Mitigation Remarks ASTM F44 published standards for showing compliance for electric propulsion systems. EASA has not yet accepted F3239 - 22a ; however, EASA would take into consideration applications from applicants that use this standard as the basis for the development of their means of compliance subject to agreement with EASA.

[AMC & GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5] Powered by EASA eRules Page 78 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART E — POWERPLANT INSTALLATION

AMC2 23.2400 Powerplant installation

ED Decision 2019/020/R CS - 23 Amdt 4 23.33 Propeller speed and pitch limits 23.901 Installation 23.903(a), (b), (d) through (g) Engines and auxiliary power units 23.905(a), (b), (d) through (h) Propellers 23.907 Propeller vibration 23.909(a), (c), (d), (e) Turbocharger systems 23.925 Propeller clearance 23.934 Turbojet and turbofan engine thrust reverser systems tests 23.943 Negative acceleration 23.951 Fuel System - General 23.955 Fuel Flow 23.957(b) Flow between interconnected tanks 23.963(b), (c) Fuel tanks: general 23.967(a), (b) Fuel tank installation 23.975 Fuel tank vents and carburettor vapour vents 23.979 Pressure fuelling systems 23.997(a), (c), (d) Fuel strainer or filter 23.999 Fuel system drains 23.1001(a) through (f) Fuel jettisoning system 23.1011 Oil system General 23.1013 Oil tanks 23.1015 Oil tank tests 23.1017 Oil lines and fittings 23.1019 Oil strainer or filter 23.1021 Oil system drains 23.1023 Oil radiators 23.1027 Propeller feathering system 23.1041 Cooling – General 23.1043 Cooling tests 23.1045 Cooling test procedures for turbine engine powered airplanes 23.1047 Cooling test procedures for reciprocating engine powered airplanes 23.1061 Installation Powered by EASA eRules Page 79 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART E — POWERPLANT INSTALLATION 23.1063 Coolant tank tests 23.1097 Carburettor de - icing fluid system capacity 23.1099 Carburettor de - icing fluid system detail design 23.1101 Induction air preheater design 23.1103 Induction system ducts 23.1105 Induction system screens 23.1107 Induction system filters 23.1109 Turbocharger bleed air system 23.1111 Turbine engine bleed air system 23.1121 Exhaust System - General 23.1125 Exhaust heat exchangers 23.1141(b), (c), (d) Powerplant controls: general 23.1163 Powerplant accessories 23.1165 Engine ignition systems 23.1193 Cowling and nacelle 23.1197 Fire extinguishing agents 23.1199 Extinguishing agent containers 23.1201 Fire extinguishing system materials 23.1203(b), (c) Fire detector system

AM C3 23.2400 Powerplant installation

ED Decision 2017/025/R CS VLA Amdt 1 VLA.33 Propeller speed and pitch limits VLA.901 Installation VLA.903 Engine VLA.905 Propeller VLA.907 Propeller vibration VLA.909 Supercharger VLA.925 Propeller clearance VLA.943 Negative acceleration VLA.951 Fuel System - General VLA.955 Fuel Flow VLA.957 Flow between interconnected tanks VLA.963 Fuel tanks: general Powered by EASA eRules Page 80 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART E — POWERPLANT INSTALLATION VLA.967 Fuel tank installation VLA.975 Fuel tank vents and carburettor vapour vents VLA.999 Fuel system drains VLA.1011 Oil system General VLA.1013 Oil tanks VLA.1015 Oil tank tests VLA.1017 Oil lines and fittings VLA.1019 Oil strainer or filter VLA.1021 Oil system drains VLA.1023 Oil radiators VLA.1041 Cooling – General VLA.1047 Cooling test procedures for reciprocating engine powered airplanes VLA.1061 Installation VLA.1063 Coolant tank tests VLA.1101 Carburettor air preheater design VLA.1103 Induction system ducts VLA.1105 Induction system screens VLA.1121 Exhaust System - General VLA.1125 Exhaust heat exchangers VLA.1141 Powerplant controls: general VLA.1163 Powerplant accessories VLA.1165 Engine ignition systems VLA.1193 Cowling and nacelle

CS 23.2405 Power or thrust control systems

ED Decision 2017/013/R Power or thrust control systems are systems that intervene with the power selection commanded by the direct power settings.

(a) Power or thrust control systems must be designed so no unsafe condition will result during normal operation of the system.

(b) Any single failure or likely combination of failures of a power or thrust control system must not prevent continued safe flight and landing of the aeroplane.

(c) Inadvertent operation of a power or thrust control system by the flight crew must be prevented, or if not prevented, must not result in an unsafe condition.

(d) Unless the failure of an automatic power or thrust control system is ‘extremely remote’, the system must: (1) provide a means for the flight crew to verify that the system is in an operating condition; Powered by EASA eRules Page 81 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART E — POWERPLANT INSTALLATION (2) provide a means for the flight crew to override the automatic function if the hazard outweighs the safety benefits; and (3) prevent inadvertent deactivation of the system.

AMC1 23.2405 Power or thrust control systems

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 8.2 Power or Thrust Control Systems & 8.5 Reversing Systems F3062/F3062M - 20 Standard Specification for Aircraft Powerplant Installation F3064/F3064M - 21 Standard Specification for Aircraft Powerplant Control, Operation, and Indication F3065/F3065M - 21a Standard Specification for Aircraft Propeller System Installation F3117/F3117M - 24a Standard Specification for Crew Interface in Aircraft Remarks ASTM F44 published standards for showing compliance for electric propulsion systems. EASA has not yet accepted F3239 - 22a ; however, EASA would take into consideration applications from applicants that use this standard as the basis for the development of their means of compliance subject to agreement with EASA.

[AMC & GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5]

AMC2 23.2405 Power or thrust control systems

ED Decision 2017/025/R CS - 23 Amdt 4 23.904 Automatic power reserve system (With Appendix H) 23.933 Reversing systems

AMC3 23.2405 Power or thrust control systems

ED Decision 2017/025/R None

CS 23.2410 Powerplant installation hazard assessment

ED Decision 2017/013/R The applicant must assess each installation separately and in relation to other aeroplane systems and installations to show that any hazard resulting from the likely failure of any system component or accessory will not: (a) prevent continued safe flight and landing or, if continued safe flight and landing cannot be ensured, the hazards have been minimised; (b) cause serious injury that may be avoided; and Powered by EASA eRules Page 82 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART E — POWERPLANT INSTALLATION (c) require immediate action by crew members for continued operation of any remaining powerplant system.

AMC1 23.2410 Powerplant installation hazard assessment

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 8.3 Powerplant Installation Hazard Assessment F3061/F3061M - 24a Standard Specification for Systems and Equipment in Small Aircraft F3062/F3062M - 20 Standard Specification for Aircraft Powerplant Installation F3063/F3063M - 21 Standard Specification for Aircraft Fuel Storage and Delivery F3064/F3064M - 21 Standard Specification for Aircraft Powerplant Control, Operation, and Indication F3065/F3065M - 21a Standard Specification for Aircraft Propeller System Installation F3066/F3066M - 18 Standard Specification for Aircraft Powerplant Installation Hazard Mitigation F3117/F3117M - 24a Standard Specification for Crew Interface in Aircraft Remarks ASTM F44 published standards for showing compliance for electric propulsion systems. EASA has not yet accepted F3239 - 22a ; however, EASA would take into consideration applications from applicants that use this standard as the basis for the development of their means of compliance subject to agreement with EASA.

[AMC & GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5]

AMC2 23.2410 Powerplant installation hazard assessment

ED Decision 2017/025/R CS - 23 Amdt 4 23.903(b) through (g) Engines and auxiliary power units 23.909(b), (c) Turbocharger systems 23.937 Powerplant operating characteristics 23.953 Fuel system independence 23.955 Fuel flow 23.959 Unusable fuel supply 23.991 Fuel pumps 23.1001(h) Fuel jettisoning system 23.1011 General 23.1027 Propeller feathering system 23.1109 Turbocharger bleed air system Powered by EASA eRules Page 83 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART E — POWERPLANT INSTALLATION 23.1141(e) Powerplant controls: general 23.1143(g) Engine controls 23.1147 Mixture controls 23.1163 Powerplant accessories 23.1437 Accessories for twin - engine aeroplanes

AM C3 23.2410 Powerplant installation hazard assessment

ED Decision 2017/025/R CS VLA Amdt 1 VLA.903 Engine VLA.909 Supercharger VLA.955 Fuel flow VLA.959 Unusable fuel supply VLA.991 Fuel pumps VLA.1011 General VLA.1141 Powerplant controls: general VLA.1143 Engine controls VLA.1147 Mixture controls VLA.1163 Powerplant accessories

CS 23.2415 Powerplant installation ice protection

ED Decision 2017/013/R (a) The aeroplane design must prevent foreseeable accumulation or shedding of ice or snow that adversely affect powerplant operation.

(b) The powerplant installation design must prevent any accumulation of ice or snow that adversely affects powerplant operation in those icing conditions for which certification is requested.

AMC1 23.2415 Powerplant installation ice protection

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 8.4 Powerplant Installation Ice Protection F3062/F3062M - 20 Standard Specification for Aircraft Powerplant Installation F3063/F3063M - 21 Standard Specification for Aircraft Fuel Storage and Delivery F3066/F3066M - 18 Standard Specification for Aircraft Powerplant Installation Hazard Mitigation Remarks Powered by EASA eRules Page 84 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART E — POWERPLANT INSTALLATION ASTM F44 published standards for showing compliance for electric propulsion systems. EASA has not yet accepted F3239 - 22a ; however, EASA would take into consideration applications from applicants that use this standard as the basis for the development of their means of compliance subject to agreement with EASA.

[AMC & GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5]

AMC2 23.2415 Powerplant installation ice protection

ED Decision 2023/002/R CS - 23 Amdt 4 23.929 Engine installation ice protection 23.1093 Induction system icing protection 23.975 Fuel tank vents and carburettor vapour vents 23.997 Fuel strainer or filter 23.1105 Induction system screens Remarks Following the cancellation of FAA AC - 1419 - 2D, applicants should now use the icing conditions that are outlined in AMC1 23.2165 .

AM C3 23.2415 Powerplant installation ice protection

ED Decision 2017/025/R CS VLA Amdt 1 VLA.1093 Induction system icing protection VLA.975 Fuel tank vents and carburettor vapour vents VLA.1105 Induction system screens

CS 23.2420

ED Decision 2017/013/R (reserved)

CS 23.2425 Powerplant operational characteristics

ED Decision 2017/013/R (a) The installed powerplant must operate without any hazardous characteristics during normal and emergency operation within the range of operation limitations for the aeroplane and powerplant installation.

(b) The design must allow the shutdown and restart of the powerplant in flight within an established operating envelope.

Powered by EASA eRules Page 85 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART E — POWERPLANT INSTALLATION

AMC1 23.2425 Powerplant operational characteristics

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 8.6 Powerplant Operational Characteristics F3062/F3062M - 20 Standard Specification for Aircraft Powerplant Installation F3064/F3064M - 21 Standard Specification for Aircraft Powerplant Control, Operation, and Indication F3065/F3065M - 21a Standard Specification for Aircraft Propeller System Installation F3066/F3066M - 18 Standard Specification for Aircraft Powerplant Installation Hazard Mitigation F3117/F3117M - 24a Standard Specification for Crew Interface in Aircraft Remarks ASTM F44 published standards for showing compliance for electric propulsion systems. EASA has not yet accepted F3239 - 22a ; however, EASA would take into consideration applications from applicants that use this standard as the basis for the development of their means of compliance subject to agreement with EASA.

[AMC & GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5]

AMC2 23.2425 Powerplant operational characteristics

ED Decision 2017/025/R CS - 23 Amdt 4 23.903(b), (d) through (g) Engines 23.905(c) Propellers 23.909(a) Turbocharger systems 23.934 Turbojet and turbofan engine thrust reverser systems tests 23.939 Turbopropeller - drag limiting systems 23.943 Negative acceleration 23.1142 Auxiliary power unit controls 23.1145 Ignition switches 23.1165 Engine ignition systems

AM C3 23.2425 Powerplant operational characteristics

ED Decision 2017/025/R CS VLA Amdt 1 VLA.903 Engine VLA.905 Propeller VLA.909 Supercharger Powered by EASA eRules Page 86 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART E — POWERPLANT INSTALLATION VLA.943 Negative acceleration VLA.1145 Ignition switches VLA.1165 Engine ignition systems

CS 23.2430 Powerplant installation, energy storage and distribution

systems

ED Decision 2023/002/R (a) Each system must: (1) Be designed to provide independence between multiple energy storage and supply systems so that a failure of any one component in one system will not result in the loss of energy storage or supply of another system.

(2) Be designed to prevent catastrophic events due to lightning strikes taking into account direct and indirect effects for aeroplanes where the exposure to lightning is likely.

(3) Provide energy to the powerplant installation with adequate margins to ensure safe functioning under all permitted and likely operating conditions, and accounting for likely component failures.

(4) Provide the information established in CS 23.2445(g) to the flight crew and provide uninterrupted supply of that energy when the system is correctly operated, accounting for likely energy fluctuations.

(5) Provide a means to safely remove or isolate the energy stored within the system.

(6) Be designed to retain the energy under all likely operating conditions and minimise hazards to the occupants during any survivable emergency landing. For Level - 4 aeroplanes, failure due to overload of the landing system must be taken into account.

(7) Prevent hazardous contamination of the energy supplied to each powerplant installation.

(b) Each storage system must: (1) withstand the loads under likely operating conditions without failure, accounting for installation; (2) be isolated from personnel compartments and protected from likely hazards; (3) be designed to prevent significant loss of stored energy due to energy transfer or venting under likely operating conditions; (4) provide energy for at least one - half hour of operation at maximum continuous power or thrust; and (5) be capable of jettisoning energy safely if this functionality is provided.

(c) Each energy - storage - refilling or - recharging system must be designed to: (1) prevent improper refilling or recharging; (2) prevent contamination of the stored energy during likely operating conditions; and (3) prevent the occurrence of any hazard to the aeroplane or to persons during refilling or recharging.

(d) Likely errors during ground handling of the aeroplane must not lead to a hazardous loss of stored energy.

Powered by EASA eRules Page 87 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART E — POWERPLANT INSTALLATION

AMC1 23.2430 Powerplant installation, energy storage and

distribution systems

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 8.7 Fuel and Energy Storage and Distribution Systems F3062/F3062M - 20 Standard Specification for Aircraft Powerplant Installation F3063/F3063M - 21 Standard Specification for Aircraft Fuel Storage and Delivery F3064/F3064M - 21 Standard Specification for Aircraft Powerplant Control, Operation, and Indication F3066/F3066M - 18 Standard Specification for Aircraft Powerplant Installation Hazard Mitigation F3114 - 21 Standard Specification for Structures F3397/F3397M Standard Practice for Aeroplane Turbine Fuel System Hot Weather Operations Remarks ASTM F44 published standards for showing compliance for electric propulsion systems. EASA has not yet accepted F3239 - 22a ; however, EASA would take into consideration applications from applicants that use this standard as the basis for the development of their means of compliance subject to agreement with EASA.

[AMC & GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5]

AMC2 23.2430 Powerplant installation, energy storage and

distribution systems

ED Decision 2017/025/R CS - 23 Amdt 4 23.951 Fuel System - General 23.953 Fuel system independence 23.954 Fuel system lightning protection 23.955 Fuel flow 23.957 Flow between interconnected tanks 23.959 Unusable fuel supply 23.961 Fuel system hot weather operation 23.963(a), (d), (e) Fuel tank: general 23.965 Fuel tank tests 23.967(a), (c), (d), (e) Fuel tank installation 23.969 Fuel tank expansion space 23.971 Fuel tank sump 23.973 Fuel tank filler connection Powered by EASA eRules Page 88 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART E — POWERPLANT INSTALLATION 23.975 Fuel tank vents and carburettor vapour vents 23.977 Fuel tank outlet 23.979 Pressure fuelling systems 23.991 Fuel pumps 23.993 Fuel system lines and fittings 23.994 Fuel system components 23.997(b), (d), (e) Fuel strainer or filter 23.999 Fuel system drains 23.1001(a) through (f) Fuel jettisoning system 23.1337(a) Powerplant instruments installation 23.721 Landing gear systems - General Remarks Provisions of AMC2 cover only fuel systems

AM C3 23.2430 Powerplant installation, energy storage and

distribution systems

ED Decision 2017/025/R CS VLA Amdt 1 VLA.951 Fuel System - General VLA.955 Fuel flow VLA.957 Flow between interconnected tanks VLA.959 Unusable fuel supply VLA.961 Fuel system hot weather operation VLA.963 Fuel tank: general VLA.965 Fuel tank tests VLA.967 Fuel tank installation VLA.969 Fuel tank expansion space VLA.971 Fuel tank sump VLA.973 Fuel tank filler connection VLA.975 Fuel tank vents and carburettor vapour vents VLA.977 Fuel strainer or filter VLA.991 Fuel pumps VLA.993 Fuel system lines and fittings VLA.999 Fuel system drains VLA.1337 Powerplant instruments Powered by EASA eRules Page 89 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART E — POWERPLANT INSTALLATION Remarks Provisions of AMC3 cover only fuel systems

CS 23.2435 Powerplant installation support systems

ED Decision 2017/013/R (a) Powerplant installation support systems are all systems whose direct purpose is to support the powerplant or the energy storage device in its intended function as part of the powerplant installation.

(b) Powerplant installation support systems that have a direct effect on the engine availability are considered in the engine reliability.

(c) Powerplant installation support systems are designed for the operating conditions applicable to the location of installation.

(d) Systems must be capable of operating under the conditions likely to occur.

(e) System function and characteristics that have an effect on the powerplant installation system performance are established.

(f) Ingestion of likely foreign objects that would be hazardous to the engine is prevented.

(g) The pilot must be aware of the air intake configuration and able to influence it.

(h) Any likely single failures of powerplant installation support systems that result in a critical loss of thrust are mitigated.

AMC1 23.2435 Powerplant installation support systems

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 8.8 Powerplant Induction, Exhaust, and Support Systems F3062/F3062M - 20 Standard Specification for Aircraft Powerplant Installation Remarks ASTM F44 published standards for showing compliance for electric propulsion systems. EASA has not yet accepted F3239 - 22a ; however, EASA would take into consideration applications from applicants that use this standard as the basis for the development of their means of compliance subject to agreement with EASA.

[AMC & GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5]

AMC2 23.2435 Powerplant installation support systems

ED Decision 2017/025/R CS - 23 Amdt 4 23.1091 Air induction system 23.1101(a) Induction air preheater design 23.1103(a) through (d) Induction system ducts Powered by EASA eRules Page 90 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART E — POWERPLANT INSTALLATION 23.1111(b) Turbine engine bleed air system 23.1121 Exhaust System - General 23.1123 Exhaust system 23.1125 Exhaust heat exchangers Remarks Provisions of AMC2 cover only induction and exhaust systems

AM C3 23.2435 Powerplant installation support systems

ED Decision 2017/025/R CS VLA Amdt 1 VLA.1091 Air induction VLA.1101 Carburettor air preheater design VLA.1103 Induction system ducts VLA.1121 Exhaust System - General VLA.1123 Exhaust manifold VLA.1125 Exhaust heat exchangers Remarks Provisions of AMC3 cover only induction and exhaust systems

CS 23.2440 Powerplant installation fire protection

ED Decision 2017/013/R There must be means to isolate and mitigate hazards to the aeroplane in the event of a powerplant system fire or overheat in operation.

AMC1 23.2440 Powerplant installation fire protection

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 8.9 Powerplant Installation Fire Protection F3061/F3061M - 24a Standard Specification for Systems and Equipment in Small Aircraft F3062/F3062M - 20 Standard Specification for Aircraft Powerplant Installation F3063/F3063M - 21 Standard Specification for Aircraft Fuel Storage and Delivery F3064/F3064M - 21 Standard Specification for Aircraft Powerplant Control, Operation, and Indication F3066/F3066M - 18 Standard Specification for Aircraft Powerplant Installation Hazard Mitigation Remarks Powered by EASA eRules Page 91 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART E — POWERPLANT INSTALLATION ASTM F44 published standards for showing compliance for electric propulsion systems. EASA has not yet accepted F3239 - 22a ; however, EASA would take into consideration applications from applicants that use this standard as the basis for the development of their means of compliance subject to agreement with EASA.

[AMC & GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5]

AMC2 23.2440 Powerplant installation fire protection

ED Decision 2017/025/R CS - 23 Amdt 4 23.995 Fuel valves and controls 23.1103(e), (f) Induction system ducts 23.1141(f) Powerplant controls: general 23.1181 Designated fire zones: regions included 23.1182 Nacelle areas behind firewalls 23.1183 Lines, fittings, and components 23.1189 Shutoff means 23.1191 Firewalls 23.1192 Engine accessory compartment diaphragm 23.1193 Cowling and nacelle 23.1195 Fire extinguishing systems 23.1197 Fire extinguishing agents 23.1201 Fire extinguishing system materials 23.1203(a), (e) Fire detector system 23.1435(c) Hydraulic Systems

AM C3 23.2440 Powerplant installation fire protection

ED Decision 2017/025/R CS VLA Amdt 1 VLA.995 Fuel valves and controls VLA.1103 Induction system ducts VLA.1141 Powerplant controls and accessories: general VLA.1182 Nacelle areas behind firewalls VLA.1183 Lines, fittings, and components VLA.1191 Firewalls VLA.1193 Cowling and nacelle Powered by EASA eRules Page 92 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART E — POWERPLANT INSTALLATION

CS 23.2445 Powerplant installation information

ED Decision 2017/013/R The following powerplant installation information is established: (a) operating limitations, procedures and instructions necessary for the safe operation of the aeroplane; (b) the need for instrument markings or placards; (c) any additional information necessary for the safe operation of the aeroplane; (d) inspections or maintenance to assure continued safe operation; (e) information related to the air intake configuration; (f) techniques and associated limitations for engine starting and stopping; and (g) energy level information to support energy management, including consideration of a likely component failure within the system.

AMC1 23.2445 Powerplant installation information

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 8.10 Powerplant Installation Information F3117/F3117M - 24a Standard Specification for Crew Interface in Aircraft F3174/F3174M - 21 Standard Specification for Establishing Operating Limitations and Information for Aeroplanes [AMC & GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5]

AMC2 23.2445 Powerplant installation information

ED Decision 2017/025/R CS - 23 Amdt 4 23.1521 Powerplant limitations 23.1522 Auxiliary power unit limitations 23.1529 Instructions for continued airworthiness (With Appendix G )

AM C3 23.2445 Powerplant installation information

ED Decision 2017/025/R CS VLA Amdt 1 VLA.1521 Powerplant limitations VLA.1529 Instructions for continued airworthiness Powered by EASA eRules Page 93 of 118 | May 2026

Next: SUBPART F — SYSTEMS AND EQUIPMENT →

SUBPART F — SYSTEMS AND EQUIPMENT

Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART F — SYSTEMS AND EQUIPMENT

SUBPART F — SYSTEMS AND EQUIPMENT

CS 23.2500 General requirements on systems and equipment

function

ED Decision 2017/013/R (a) Requirements CS 23.2500, CS 23.2505 and CS 23.2510 are general requirements applicable to systems and equipment installed in the aeroplane, and should not be used to supersede any other specific CS - 23 requirement.

(b) Equipment and systems required to comply with type certification requirements, airspace requirements or operating rules, or whose improper functioning would lead to a hazard, must be designed and installed so that they perform their intended function thro ughout the operating and environmental limits for which the aeroplane is certified.

AMC1 23.2500 General requirements on systems and equipment

function

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 9.1 Systems and Equipment Function Requirements F3231/F3231M - 24 Standard Specification for Electrical Systems for Aircraft with Combustion Engine Electrical Power Generation F3235 - 22 Standard Specification for Aircraft Storage Batteries F3232/F3232M - 25 Standard Specification for Flight Controls in Small Aircraft F3233/F3233M - 23b Standard Specification for Flight and Navigation Instrumentation in Aircraft F3229/F3229M - 23a Standard Practice for Static Pressure System Tests in Small Aircraft F3064/F3064M - 21 Standard Specification for Aircraft Powerplant Control, Operation, and Indication F3066/F3066M - 18 Standard Specification for Aircraft Powerplant Installation Hazard Mitigation F3117/F3117M - 24a Standard Specification for Crew Interface in Aircraft F3120/F3120M - 20 Standard Specification for Ice Protection for General Aviation Aircraft F3408/F3408M - 21 Standard Specification for Aircraft Emergency Parachute Recovery Systems Remarks — F3061/F3061M - 24a Standard Specification for Systems and Equipment in Small Aircraft At variance with F3061 - 24a, paragraph 4.4.2, use of system level verification is usually not acceptable, and it should be discussed with EASA.

— F3532 - 25 Standard Practice for Protection of Aircraft Systems from Intentional Unauthorized Electronic Interactions At variance with F3532 and F3061 - 24a, paragraph 4.3, for showing compliance with CS 23.2500(b) for equipment and systems whose improper functioning could lead to an intentional unauthorised electronic interaction (IUEI) Powered by EASA eRules Page 94 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART F — SYSTEMS AND EQUIPMENT — For an aeroplane with assessment level IV, the applicant may consider AMC 20 - 42.

— For an aeroplane with assessment level I, level II or level III, the applicant may consider ASTM F3532 - 25.

For an aeroplane with certification level 1, operated in visual flight rules (VFR) day or night, considerations of cybersecurity threats as potential sources of improper functioning of the equipment and systems are not required.

ASTM F44 published standards for showing compliance for electrical systems that are installed on aeroplanes with electric or hybrid - electric propulsion systems. EASA has not yet accepted F3316 - 19 ; however, EASA would take into consideration applications from applicants that use this standard as the basis for the development of their means of compliance subject to agreement with EASA.

[AMC & GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5]

AMC2 23.2500 General requirements on systems and equipment

function

ED Decision 2019/020/R CS - 23 Amdt 4 23.1301 Function and installation 23.1303 Flight and navigation instruments 23.1305 Powerplant instruments 23.1309(a) Equipment, systems, and installations 23.1311 Electronic display instrument systems 23.1321 Arrangement and visibility 23.1323 Airspeed indicating system 23.1325 Static pressure system 23.1327 Magnetic direction indicator 23.1329 Automatic pilot system 23.1335 Flight director systems 23.1351(b), (e), (f), (g) Electrical Systems - General 23.1357 Circuit protective devices 23.1361 Master switch arrangement 23.1367 Switches 23.1381(c) Instrument lights 23.1416 Pneumatic de - icer boot system 23.729(d) Landing gear extension and retraction system 23.843(b) Pressurization tests 23.1141(b), (c), (d) Powerplant controls: general Powered by EASA eRules Page 95 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART F — SYSTEMS AND EQUIPMENT 23.1201 Fire extinguishing system materials 23.1203(e) Fire detector system Remarks 23.1305 must be complemented. F3064 - 18 § 6.2.1.6 provides this AMC.

AM C3 23.2500 General requirements on systems and equipment

function

ED Decision 2019/020/R CS VLA Amdt 1 VLA.1301 Function and installation VLA.1303 Flight and navigation instruments VLA.1305 Powerplant instruments VLA.1307 Miscellaneous equipment VLA.1309 Equipment, systems, and installations VLA.1321 Arrangement and visibility VLA.1323 Airspeed indicating system VLA.1325 Static pressure system VLA.1327 Magnetic direction indicator VLA.1351 Electrical Systems - General VLA.1357 Circuit protective devices VLA.1361 Master switch arrangement VLA.1367 Switches VLA.729 Landing gear extension and retraction system VLA.1141 Powerplant controls and accessories: general Remarks VLA.1305 must be complemented. F3064 - 18 § 6.2.1.6 provides this AMC.

CS 23.2505 General requirements on equipment installation

ED Decision 2017/013/R (a) Each item of installed equipment is installed according to limitations specified for that equipment.

(b) On multi - engine aeroplanes, engine - driven accessories essential to safe operation must be distributed among multiple engines.

Powered by EASA eRules Page 96 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART F — SYSTEMS AND EQUIPMENT

AMC1 23.2505 General requirements on equipment installation

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 9.2 Equipment Function and Installation Requirements F3061/F3061M - 24a Standard Specification for Systems and Equipment in Small Aircraft F3231/F3231M - 24 Standard Specification for Electrical Systems for Aircraft with Combustion Engine Electrical Power Generation F3235 - 22 Standard Specification for Aircraft Storage Batteries F3232/F3232M - 25 Standard Specification for Flight Controls in Small Aircraft F3233/F3233M - 23b Standard Specification for Flight and Navigation Instrumentation in Aircraft F3408/F3408M - 21 Standard Specification for Aircraft Emergency Parachute Recovery Systems Remarks ASTM F44 published standards for showing compliance for electrical systems that are installed on aeroplanes with electric or hybrid - electric propulsion systems. EASA has not yet accepted F3316 - 19 ; however, EASA would take into consideration applications from applicants that use this standard as the basis for the development of their means of compliance subject to agreement with EASA.

[AMC&GM to CS - 23: Issue 4] [AMC&GM to CS - 23: Issue 5]

AMC2 23.2505 General requirements on equipment installation

ED Decision 2017/025/R CS - 23 Amdt 4 23.1301 Function and installation 23.1437 Accessories for twin - engine aeroplanes

AM C3 23.2505 General requirements on equipment installation

ED Decision 2017/025/R CS VLA Amdt 1 VLA.1301 Function and installation

CS 23.2510 Equipment, systems, and installations

ED Decision 2017/013/R (a) The equipment and systems identified in CS 23.2500 , considered separately and in relation to other systems, must be designed and installed such that: (1) each catastrophic failure condition is extremely improbable; and (2) each hazardous failure condition is extremely remote; and (3) each major failure condition is remote.

Powered by EASA eRules Page 97 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART F — SYSTEMS AND EQUIPMENT (b) The operation of equipment and systems not covered by CS 23.2500 does not cause a hazard to the aeroplane or its occupants throughout the operating and environmental limits for which the aeroplane is certified.

AMC1 23.2510 Equipment, systems, and installations

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 9.3 Equipment, Systems, and Installation F3233/F3233M - 23b Standard Specification for Flight and Navigation Instrumentation in Aircraft F3309/F3309M - 24a Standard Practice for Simplified Safety Assessment of Systems and Equipment in Small Aircraft F3408/F3408M - 21 Standard Specification for Aircraft Emergency Parachute Recovery Systems Remarks — F3061/F3061M - 24a Standard Specification for Systems and Equipment in Small Aircraft At variance with F3061 - 24a, paragraph 4.4.2, use of system level verification is usually not acceptable, and it should be discussed with EASA.

— F3230 - 25 Standard Practice for Safety Assessment of Systems and Equipment in Small Aircraft For aircraft that are powered by electric motors, EASA has not yet accepted Table 3 of F3230 - 25, and its use should be discussed with EASA.

— F3227/F3227M - 25 Standard Specification for Environmental Systems in Aircraft At variance with F3227 - 25, Oxygen Fire Hazards Analysis is not completely covered in current ASTM standards. At variance, additional means of compliance have been developed by EASA for the specific application [AMC & GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5]

AMC2 23.2510 Equipment, systems, and installations

ED Decision 2017/025/R CS - 23 Amdt 4 23.1309 Equipment, systems, and installations 23.1323 Airspeed indicating system 23.1325 Static pressure system 23.1329 Automatic pilot system 23.1331(b), (c) Instruments using a power source 23.1335 Flight director systems 23.1337(b), (c) Powerplant instruments installation 23.1357 Circuit protective devices Powered by EASA eRules Page 98 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART F — SYSTEMS AND EQUIPMENT 23.1431 Electronic equipment 23.1437 Accessories for twin - engine aeroplanes 23.672(c) Stability augmentation and automatic and power - operated systems 23.677(d) Trim systems 23.701 Flap interconnection 23.735(d) Brakes 23.775(g) Windshields and windows 23.831(d) Ventilation 23.841(b)(8), (c), (d)(2), (d)(3) Pressurised cabins

AM C3 23.2510 Equipment, systems, and installations

ED Decision 2017/025/R CS VLA Amdt 1 VLA.1309 Equipment, systems, and installations VLA.1323 Airspeed indicating system VLA.1325 Static pressure system VLA.1331 Instruments using a power supply VLA.1337 Powerplant instruments VLA.1357 Circuit protective devices VLA.1431 Electronic equipment VLA.677 Trim systems VLA.701 Flap interconnection VLA.735 Brakes VLA.775 Windshields and windows VLA.831 Ventilation

CS 23.2515 Electrical and electronic system lightning protection

ED Decision 2023/002/R For an aeroplane where the exposure to lightning is likely: (a) each electrical or electronic system that performs a function, the failure of which would prevent the continued safe flight and landing of the aeroplane, must be designed and installed such that: (1) the function at the aeroplane level is not adversely affected during and after the time the aeroplane is exposed to lightning; and (2) the system recovers normal operation of that function in a timely manner after the aeroplane is exposed to lightning unless the system’s recovery conflicts with other operational or functional requirements of the system; Powered by EASA eRules Page 99 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART F — SYSTEMS AND EQUIPMENT (b) each electrical and electronic system that performs a function, the failure of which would reduce the capability of the aeroplane or the ability of the flight crew to respond to an adverse operating condition, must be designed and installed such that the system recovers normal operation of that function in a timely manner after the aeroplane is exposed to lightning.

AMC1 23.2515 Electrical and electronic system lightning protection

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 9.4 Electrical and Electronic System Lightning Protection F3061/F3061M - 24a Standard Specification for Systems and Equipment in Small Aircraft F3367 - 23 Standard Practice for Simplified Methods for Addressing High Intensity Radiated Fields (HIRF) and Indirect Effects of Lightning on Aircraft [AMC & GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5]

AMC2 23.2515 Electrical and electronic system lightning protection

ED Decision 2017/025/R CS - 23 Amdt 4 23.1306 Electrical and electronic system lightning protection

AMC3 23.2515 Electrical and electronic system lightning protection

ED Decision 2017/025/R None

CS 23.2520 High - intensity radiated fields (HIRF) protection

ED Decision 2017/013/R (a) Each electrical and electronic system that perform a function, the failure of which would prevent the continued safe flight and landing of the aeroplane, must be designed and installed such that: (1) the function at the aeroplane level is not adversely affected during and after the time the aeroplane is exposed to the HIRF environment; and (2) the system recovers normal operation of that function in a timely manner after the aeroplane is exposed to the HIRF environment, unless the system’s recovery conflicts with other operational or functional requirements of the system.

(b) For aeroplanes approved for instrument flight rules (IFR) operations, each electrical and electronic system that performs a function, the failure of which would reduce the capability of the aeroplane or the ability of the flight crew to respond to an adve rse operating condition, must be designed and installed such that the system recovers normal operation of that function in a timely manner after the aeroplane is exposed to the HIRF environment.

Powered by EASA eRules Page 100 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART F — SYSTEMS AND EQUIPMENT

AMC1 23.2520 High - intensity radiated fields (HIRF) protection

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 9.5 High - Intensity Radiated Fields (HIRF) Protection F3061/F3061M - 24a Standard Specification for Systems and Equipment in Small Aircraft F3236 - 21a Standard Specification for High Intensity Radiated Field (HIRF) Protection in Small Aircraft F3367 - 23 Standard Practice for Simplified Methods for Addressing High Intensity Radiated Fields (HIRF) and Indirect Effects of Lightning on Aircraft [AMC & GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5]

AMC2 23.2520 High - intensity radiated fields (HIRF) protection

ED Decision 2017/025/R CS - 23 Amdt 4 23.1308 High - Intensity Radiated Fields (HIRF) protection

AMC3 23.2520 High - intensity radiated fields (HIRF) protection

ED Decision 2017/025/R None

CS 23.2525 System power generation, storage, and distribution

ED Decision 2017/013/R The power generation, storage, and distribution for any system must be designed and installed to: (a) supply the power required for operation of connected loads during all intended operating conditions; (b) ensure no single failure or malfunction will prevent the system from supplying the essential loads required for continued safe flight and landing; and (c) have enough capacity, if the primary source fails, to supply essential loads, including non - continuous essential loads for the time needed to complete the function, required for safe flight and landing.

AMC1 23.2525 System power generation, storage, and distribution

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 9.6 System Power Generation, Storage, and Distribution F3061/F3061M - 24a Standard Specification for Systems and Equipment in Small Aircraft F3231/F3231M - 24 Standard Specification for Electrical Systems for Aircraft with Combustion Engine Electrical Power Generation F2490 - 20 Standard Guide for Aircraft Electrical Load and Power Source Capacity Analysis Powered by EASA eRules Page 101 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART F — SYSTEMS AND EQUIPMENT F3233/F3233M - 23b Standard Specification for Flight and Navigation Instrumentation in Aircraft F3117/F3117M - 24a Standard Specification for Crew Interface in Aircraft F3120/F3120M - 20 Standard Specification for Ice Protection for General Aviation Aircraft Remarks ASTM F44 published standards for showing compliance for electrical systems that are installed on aeroplanes with electric or hybrid - electric propulsion systems. EASA has not yet accepted F3316 - 19 ; however, EASA would take into consideration applications from applicants that use this standard as the basis for the development of their means of compliance subject to agreement with EASA.

[AMC & GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5]

AMC2 23.2525 System power generation, storage, and distribution

ED Decision 2023/002/R CS - 23 Amdt 4 23.1303 Flight and navigation instruments 23.1331(b), (c) Instruments using a power source 23.1351(a), (b), (c) Electrical Systems – General 23.1353 Storage battery design and installation 23.1357 Circuit protective devices Remarks At variance with CS 23.1357(b) and (d), EASA does not accept a protective device for a circuit essential to flight safety in designs applications after the date of entry into force of the AMC & GM to CS - 23 Issue 4; automatic fuses or circuit breakers should b e used instead.

AM C3 23.2525 System power generation, storage, and distribution

ED Decision 2023/002/R CS - VLA Amdt 1 VLA 1303 Flight and navigation instruments VLA 1331 Instruments using a power supply VLA 1351 Electrical Systems – General VLA 1353 Storage battery design and installation VLA 1357 Circuit protective devices Powered by EASA eRules Page 102 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART F — SYSTEMS AND EQUIPMENT Remarks At variance with CS - VLA 1357(b) and (d), EASA does not accept a protective device for a circuit essential to flight safety in designs applications after the date of entry into force of the AMC & GM to CS - 23 Issue 4; automatic fuses or circuit breakers should be used instead.

CS 23.2530 External and cockpit lighting

ED Decision 2017/013/R (a) The applicant must design and install all lights to minimise any adverse effects on the performance of flight crew duties.

(b) Any position and anti - collision lights, if required by operational rules, must have the intensities, flash rate, colours, fields of coverage, and other characteristics to provide sufficient time for another aircraft to avoid a collision.

(c) Any position lights, if required by operational rules, must include a red light on the left side of the aeroplane, a green light on the right side of the aeroplane, spaced laterally as far apart as practicable, and a white light facing aft, located on an aft portion of the aeroplane or on the wing tips.

(d) Taxi and landing lights, if required, must be designed and installed so they provide sufficient light for night operations.

(e) For seaplanes or amphibian aeroplanes, riding lights must provide a white light visible in clear atmospheric conditions.

AMC1 23.2530 External and cockpit lighting

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 9.7 External and Cockpit Lighting F3061/F3061M - 24a Standard Specification for Systems and Equipment in Small Aircraft F3233/F3233M - 23b Standard Specification for Flight and Navigation Instrumentation in Aircraft F3234/F3234M - 21 Standard Specification for Exterior Lighting in Small Aircraft F3117/F3117M - 24a Standard Specification for Crew Interface in Aircraft F3120/F3120M - 20 Standard Specification for Ice Protection for General Aviation Aircraft [AMC & GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5]

AMC2 23.2530 External and cockpit lighting

ED Decision 2017/025/R CS - 23 Amdt 4 23.1381 Instrument lights 23.1383(a), (b), (c) Taxi and landing lights 23.1385(a), (b), (c) Position light system installation 23.1387 Position light system dihedral angles Powered by EASA eRules Page 103 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART F — SYSTEMS AND EQUIPMENT 23.1391 Minimum intensities in the horizontal plane of position lights 23.1393 Minimum intensities in any vertical plane of position lights 23.1395 Maximum intensities in overlapping beams of position lights 23.1397 Colour specifications 23.1399 Riding light 23.1401 Anti - collision light system

AM C3 23.2530 External and cockpit lighting

ED Decision 2017/025/R CS VLA Amdt 1 VLA.1384 External lights

CS 23.2535 Safety equipment

ED Decision 2017/013/R Safety and survival equipment, required by the operating rules, must be reliable, readily accessible, easily identifiable, and clearly marked to identify its method of operation.

AMC1 23.2535 Safety equipment

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 9.8 Safety Equipment F3061/F3061M - 24a Standard Specification for Systems and Equipment in Small Aircraft F3083/F3083M - 20a Standard Specification for Emergency Conditions, Occupant Safety and Accommodations F3117/F3117M - 24a Standard Specification for Crew Interface in Aircraft [AMC & GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5]

AMC2 23.2535 Safety equipment

ED Decision 2017/025/R CS - 23 Amdt 4 23.1411 Safety Equipment - General 23.1415 Ditching equipment

AM C3 23.2535 Safety equipment

ED Decision 2017/025/R CS VLA Amdt 1 VLA.1411 Safety Equipment - General Powered by EASA eRules Page 104 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART F — SYSTEMS AND EQUIPMENT

CS 23.2540 Flight in icing conditions

ED Decision 2017/013/R An applicant who requests certification for flight in icing conditions must show the following in the icing conditions for which certification is requested: (a) the ice protection system provides for safe operation; and (b) the aeroplane design must provide protection from stalling when the autopilot is operating.

AMC1 23.2540 Flight in icing conditions

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 9.9 Flight in Icing Conditions F3061/F3061M - 24a Standard Specification for Systems and Equipment in Small Aircraft F3233/F3233M - 23b Standard Specification for Flight and Navigation Instrumentation in Aircraft F3120/F3120M - 20 Standard Specification for Ice Protection for General Aviation Aircraft [AMC & GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5]

AMC2 23.2540 Flight in icing conditions

ED Decision 2023/002/R CS - 23 Amdt 4 23.1323 Airspeed indicating system 23.1325(b), (g) Static pressure system 23.775(f) Windshields and windows Remarks Following the cancellation of FAA AC - 1419 - 2D, applicants should now use the icing conditions that are outlined in AMC1 23.2165 .

AMC3 23.2540 Flight in icing conditions

ED Decision 2017/025/R None

CS 23.2545 Pressurised systems elements

ED Decision 2017/013/R Pressurised systems must withstand appropriate proof and burst pressures.

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AMC1 23.2545 Pressurised systems elements

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 9.10 Pressurized System Elements F3061/F3061M - 24a Standard Specification for Systems and Equipment in Small Aircraft F3229/F3229M - 23a Standard Practice for Static Pressure System Tests in Small Aircraft [AMC & GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5]

AMC2 23.2545 Pressurised systems elements

ED Decision 2017/025/R CS - 23 Amdt 4 23.1438 Pressurization and pneumatic systems 23.1435(a)(4), (b) Hydraulic Systems 23.1453 Protection of oxygen equipment from rupture

AMC3 23.2545 Pressurised systems elements

ED Decision 2017/025/R None

CS 23.2550

ED Decision 2017/013/R (reserved)

CS 23.2555 Installation of recorders (e.g. cockpit voice recorders

and flight data recorders)

ED Decision 2017/013/R If recording is required by the operating rules, the system: (a) is installed so as to ensure accurate and intelligible recording and safeguarding of the required data, also in conditions encountered during crash, water immersion or fire; (b) is powered by the most reliable power source and remains powered for as long as possible without jeopardising service to essential or emergency loads and emergency operation of the aeroplane; (c) includes features to facilitate the localisation of a memory medium after an accident; and (d) is installed so that it automatically records when the aeroplane is capable of moving under its own power.

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AMC1 23.2555 Installation of recorders (e.g. cockpit voice reco rders

and flight data recorders)

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 9.12 Installation of Cockpit recorders F3061/F3061M - 24a S tandard Specification for Systems and Equipment in Small Aircraft F3228 - 21 S tandard Specification for Flight Data and Voice Recording in Small Aircraft 9.13 Installation of Flight Data Recorders: F3061/F3061M - 24a S tandard Specification for Systems and Equipment in Small Aircraft F3228 - 21 Standard Specification for Flight Data and Voice Recording in Small Aircraft [AMC & GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5]

AMC2 23.2555 Installation of recorders (e.g. cockpit voice recorders

and flight data recorders)

ED Decision 2017/025/R CS - 23 Amdt 4 23.1457 Cockpit voice recorders 23.1459 Flight recorders

AMC3 23.2555 Installation of recorders (e.g. cockpit voice recorders

and flight data recorders)

ED Decision 2017/025/R None Powered by EASA eRules Page 107 of 118 | May 2026

Next: SUBPART G — FLIGHT CREW INTERFACE AND OTHER INFORMATION →

SUBPART G — FLIGHT CREW INTERFACE AND OTHER INFORMATION

Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART G — FLIGHT CREW INTERFACE AND OTHER INFORMATION

SUBPART G — FLIGHT CREW INTERFACE AND OTHER

INFORMATION

CS 23.2600 Flight crew compartment

ED Decision 2017/013/R (a) The pilot compartment arrangement, including pilot view, and its equipment must allow the flight crew to perform their duties within the operating envelope of the aeroplane, without excessive concentration, skill, alertness, or fatigue.

(b) The applicant must install flight, navigation, surveillance, and powerplant installation controls and displays so that a qualified flight crew can monitor and perform defined tasks associated with the intended functions of systems and equipment. The syste m and equipment design must minimise flight crew errors, which could result in additional hazards.

(c) For Level - 4 aeroplanes, the flight crew interface design must allow for continued safe flight and landing after the loss of vision through any one of the windshield panels.

AMC1 23.2600 Flight crew compartment

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 10.1 Flight Crew Compartment Interface F3061/F3061M - 24a Standard Specification for Systems and Equipment in Small Aircraft F3232/F3232M - 25 Standard Specification for Flight Controls in Small Aircraft F3062/F3062M - 20 Standard Specification for Aircraft Powerplant Installation F3063/F3063M - 21 Standard Specification for Aircraft Fuel Storage and Delivery F3064/F3064M - 21 Standard Specification for Aircraft Powerplant Control, Operation, and Indication F3114 - 21 Standard Specification for Structures F3408/F3408M - 21 Standard Specification for Aircraft Emergency Parachute Recovery Systems Remarks F3117/F3117M - 24a Standard Specification for Crew Interface in Aircraft Hydrophobic coating is not completely covered in current ASTM standards. At variance, additional means of compliance have been developed by EASA for this specific application.

ASTM F3264 - 24 does not contain standards that ensure that the required pilot compartment view is provided in conditions of fog or frost formation on the internal portion of the windshield and side windows. Pilot compartment view with formation of fog or frost must be addressed in showing compliance with CS 23.2600(a) . Applicants may use the provisions of CS 23.773(b) at Amendment 4 as a means of c omplying with this aspect of CS 23.2600(a) , or may propose a different means of compliance in accordance with CS 23.2010 .

[AMC & GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5] Powered by EASA eRules Page 108 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART G — FLIGHT CREW INTERFACE AND OTHER INFORMATION

AMC2 23.2600 Flight crew compartment

ED Decision 2017/025/R CS - 23 Amdt 4 23.671 Control systems - General 23.677(a) Trim systems 23.699 Wing flap position indicator 23.729(e) Landing gear extension and retraction system 23.745 Nose/Tail wheel steering 23.771(a) Pilot compartment 23.773 Pilot compartment view 23.775(e), (h)(2) Windshields and windows 23.777 Cockpit controls 23.779 Motion and effect of cockpit controls 23.781 Cockpit control knob shape 23.831(c) Ventilation 23.1141(g) Powerplant controls: general 23.1142 Auxiliary power unit controls 23.1143(a) through (f) Engine controls 23.1145 Ignition switches 23.1147 Mixture controls 23.1149 Propeller speed and pitch controls 23.1153 Propeller feathering controls 23.1155 Turbine engine reverse thrust and propeller pitch settings below the flight regime 23.1157 Carburettor air temperature controls 23.1203(d) Fire detector system 23.1329(d) Automatic pilot system 23.1335 Flight director systems 23.1367 Switches 23.1381(a), (b) Instrument lights 23.1419(d) Ice protection 23.1435(a)(2) Hydraulic Systems 23.1523 Minimum Flight Crew Powered by EASA eRules Page 109 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART G — FLIGHT CREW INTERFACE AND OTHER INFORMATION

AM C3 23.2600 Flight crew compartment

ED Decision 2017/025/R CS VLA Amdt 1 VLA.671 Control systems - General VLA.677 Trim systems VLA.699 Wing flap position indicator VLA.729 Landing gear extension and retraction system VLA.745 Nose/Tail wheel steering VLA.771 Pilot compartment VLA.773 Pilot compartment view VLA.775 Windshields and windows VLA.777 Cockpit controls VLA.779 Motion and effect of cockpit controls VLA.781 Cockpit control knob shape VLA.831 Ventilation VLA.1141 Powerplant controls: general VLA.1143 Engine controls VLA.1145 Ignition switches VLA.1147 Mixture controls VLA.1367 Switches

CS 23.2605 Installation and operation information

ED Decision 2017/013/R (a) Each item of installed equipment related to the flight crew interface must be labelled, if applicable, as for its identification, function, or operating limitations, or any combination of these factors.

(b) There must be a discernible means of providing system operating parameters required to operate the aeroplane, including warnings, cautions, and normal indications, to the responsible crew member.

(c) Information concerning an unsafe system operating condition must be provided in a timely manner to the crew member responsible for taking corrective action. The information must be clear enough to avoid likely crew member errors.

(d) Information related to safety equipment is easily identifiable and its method of operation is clearly marked.

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AMC1 23.2605 Installation and operation information

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 10.2 Installation and Operation Information F3061/F3061M - 24a Standard Specification for Systems and Equipment in Small Aircraft F3232/F3232M - 25 Standard Specification for Flight Controls in Small Aircraft F3233/F3233M - 23b Standard Specification for Flight and Navigation Instrumentation in Aircraft F3231/F3231M - 24 Standard Specification for Electrical Systems for Aircraft with Combustion Engine Electrical Power Generation F3062/F3062M - 20 Standard Specification for Aircraft Powerplant Installation F3063/F3063M - 21 Standard Specification for Aircraft Fuel Storage and Delivery F3064/F3064M - 21 Standard Specification for Aircraft Powerplant Control, Operation, and Indication F3117/F3117M - 24a Standard Specification for Crew Interface in Aircraft F3120/F3120M - 20 Standard Specification for Ice Protection for General Aviation Aircraft F3408/F3408M - 21 Standard Specification for Aircraft Emergency Parachute Recovery Systems Remarks F3227/F3227M - 25 Standard Specification for Environmental Systems in Aircraft At variance with F3227 - 25, Oxygen Fire Hazards Analysis is not completely covered in current ASTM standards. At variance, additional means of compliance have been developed by EASA for this specific application.

[AMC & GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5]

AMC2 23.2605 Installation and operation information

ED Decision 2019/020/R CS - 23 Amdt 4 23.671(b) Control systems - General 23.672(a) Stability augmentation and automatic and power - operated systems 23.679(a), (b) Control system locks 23.703 Take - off warning system 23.729(f) Landing gear extension and retraction system 23.783(e)(3) Doors 23.841(b)(5), (b)(6), (d)(4), (d)(5) Pressurised cabins 23.991(c) Fuel pumps 23.1142 Auxiliary power unit controls 23.1301(b) Function and installation Powered by EASA eRules Page 111 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART G — FLIGHT CREW INTERFACE AND OTHER INFORMATION 23.1305 Powerplant instruments 23.1309(d) Equipment, systems, and installations 23.1322 Warning, caution and advisory lights 23.1326 Pitot heat indication systems 23.1329(h) Automatic pilot system 23.1331(a) Instruments using a power source 23.1335 Flight director systems 23.1337(b), (d) Powerplant instruments installation 23.1351(c), (d) Electrical Systems - General 23.1416(c) Pneumatic de - icer boot system 23.1441(c) Oxygen Equipment and supply 23.1561 Safety equipment Remarks 23.1305 must be complemented. F3064 - 18 § 6.2.1.6 provides this AMC.

AMC3 23.2605 Installation and operation information

ED Decision 2019/020/R CS VLA Amdt 1 VLA.671 Control systems - General VLA.679 Control system locks VLA.729 Landing gear extension and retraction system VLA.783 Doors VLA.991 Fuel pumps VLA.1301 Function and installation VLA.1305 Powerplant instruments VLA.1309 Equipment, systems, and installations VLA.1322 Warning, caution and advisory lights VLA.1331 Instruments using a power supply VLA.1337 Powerplant instruments VLA.1351 Electrical Systems - General VLA.1561 Safety equipment Remarks VLA.1305 must be complemented. F3064 - 18 § 6.2.1.6 provides this AMC.

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CS 23.2610 Instrument markings, control markings and placards

ED Decision 2017/013/R (a) Each aeroplane must display in a conspicuous manner any placard and instrument marking necessary for operation.

(b) The design must clearly indicate the function of each cockpit control, other than primary flight controls.

(c) The applicant must include instrument marking and placard information in the Aeroplane Flight Manual.

AMC1 23.2610 Instrument markings, control markings and placards

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 10.3 Instrument Markings, Control Markings, and Placards F3061/F3061M - 24a Standard Specification for Systems and Equipment in Small Aircraft F3063/F3063M - 21 Standard Specification for Aircraft Fuel Storage and Delivery F3117/F3117M - 24a Standard Specification for Crew Interface in Aircraft F3120/F3120M - 20 Standard Specification for Ice Protection for General Aviation Aircraft F3408/F3408M - 21 Standard Specification for Aircraft Emergency Parachute Recovery Systems [AMC&GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5]

AMC2 23.2610 Instrument markings, control markings and placards

ED Decision 2017/025/R CS - 23 Amdt 4 23.733 Tires 23.777 Cockpit controls 23.841(b)(7) Pressurised cabins 23.1001(g) Fuel jettisoning system 23.1321 Arrangement and visibility 23.1337(d) Powerplant instruments installation 23.1450(c) Chemical oxygen generators 23.1501 General 23.1505 Airspeed limitations 23.1507 Operating manoeuvring speed 23.1511 Flap extended speed 23.1513 Minimum control speed 23.1519 Weight and center of gravity Powered by EASA eRules Page 113 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART G — FLIGHT CREW INTERFACE AND OTHER INFORMATION 23.1521 Powerplant limitations 23.1522 Auxiliary power unit limitations 23.1523 Minimum flight crew 23.1524 Maximum passenger seating configuration 23.1525 Kinds of operation 23.1527 Maximum operating altitude 23.1541 Marking and Placards - General 23.1543 Instrument marking: general 23.1545 Airspeed indicator 23.1547 Magnetic direction indicator 23.1549 Powerplant and auxiliary power unit instruments 23.1551 Oil quantity indicator 23.1553 Fuel quantity indicator 23.1555 Control markings 23.1557 Miscellaneous marking and placards 23.1559 Operating limitations placard 23.1561 Safety equipment 23.1563 Airspeed placards 23.1567 Flight manoeuvre placard

AM C3 23.2610 Instrument markings, control markings and placards

ED Decision 2017/025/R CS VLA Amdt 1 VLA.777 Cockpit controls VLA.1321 Arrangement and visibility VLA.1337 Powerplant instruments VLA.1501 General VLA.1505 Airspeed limitations VLA.1507 Manoeuvring speed VLA.1511 Flap extended speed VLA.1519 Weight and center of gravity VLA.1521 Powerplant limitations VLA.1525 Kinds of operation VLA.1541 Marking and Placards - General VLA.1543 Instrument marking: general Powered by EASA eRules Page 114 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART G — FLIGHT CREW INTERFACE AND OTHER INFORMATION VLA.1545 Airspeed indicator VLA.1547 Magnetic direction indicator VLA.1549 Powerplant instruments VLA.1551 Oil quantity indicator VLA.1555 Control markings VLA.1557 Miscellaneous marking and placards VLA.1559 Operating limitations placard VLA.1561 Safety equipment

CS 23.2615 Flight, navigation, and powerplant instruments

ED Decision 2017/013/R (a) Installed systems must provide the flight crew member who sets or monitors parameters for the flight, navigation, and powerplant the information necessary to do so during each phase of flight. This information must: (1) be presented in a manner that the crew members can monitor the parameters and trends, as needed to operate the aeroplane; and (2) include limitations, unless the limitation cannot be exceeded in all intended operations.

(b) Indication systems that integrate the display of flight or powerplant parameters required to safely operate the aeroplane, or required by the operating rules, must: (1) not inhibit the primary display of flight or powerplant parameters needed by any flight crew member in any normal mode of operation; and (2) in combination with other systems, be designed and installed so information essential for continued safe flight and landing will be available to the flight crew in a timely manner after any single failure or probable combination of failures.

AMC1 23.2615 Flight, navigation, and powerplant instruments

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 10.4 Flight, Navigation, and Powerplant Instruments F3061/F3061M - 24a Standard Specification for Systems and Equipment in Small Aircraft F3062/F3062M - 20 Standard Specification for Aircraft Powerplant Installation F3064/F3064M - 21 Standard Specification for Aircraft Powerplant Control, Operation, and Indication F3432 - 20a Standard Practice for Powerplant Instruments F3117/F3117M - 24a Standard Specification for Crew Interface in Aircraft [AMC&GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5] Powered by EASA eRules Page 115 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART G — FLIGHT CREW INTERFACE AND OTHER INFORMATION

AMC2 23.2615 Flight, navigation, and powerplant instruments

ED Decision 2026/003/R CS - 23 Amdt 4 23.1141(g) Powerplant controls: general 23.1142 Auxiliary power unit controls 23.1303 Flight and navigation instruments 23.1305 Powerplant instruments 23.1311 Electronic display instrument systems 23.1323 Airspeed indicating system 23.1325 Static pressure system 23.1327 Magnetic direction indicator 23.1337 Powerplant instruments installation [AMC&GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5]

AM C3 23.2615 Flight, navigation, and powerplant instruments

ED Decision 2026/003/R CS - VLA Amdt 1 VLA 1141 Powerplant controls – general VLA 1303 Flight and navigation instruments VLA 1305 Powerplant instruments VLA 1323 Airspeed indicating system VLA 1325 Static pressure system VLA 1327 Magnetic direction indicator VLA 1337 Powerplant instruments [AMC&GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5]

CS 23.2620 Aeroplane Flight Manual

ED Decision 2017/013/R The applicant must provide an aeroplane flight manual that must be delivered with each aeroplane and contains the following information: (a) operating limitations and procedures; (b) performance information; (c) loading information; Powered by EASA eRules Page 116 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART G — FLIGHT CREW INTERFACE AND OTHER INFORMATION (d) instrument marking and placard information; and (e) any other information necessary for the safe operation of the aeroplane.

AMC1 23.2620 Aeroplane Flight Manual

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 10.5 Aeroplane Flight Manual F3117/F3117M - 24a Standard Specification for Crew Interface in Aircraft F3174/F3174M - 21 Standard Specification for Establishing Operating Limitations and Information for Aeroplanes F3120/F3120M - 20 Standard Specification for Ice Protection for General Aviation Aircraft F3408/F3408M - 21 Standard Specification for Aircraft Emergency Parachute Recovery Systems [AMC&GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5]

AMC2 23.2620 Aeroplane Flight Manual

ED Decision 2017/025/R CS - 23 Amdt 4 23.1581 Airplane Flight Manual and Approved Manual Material - General 23.1583 Operating limitations 23.1585 Operating procedures 23.1587 Performance information 23.1589 Loading information

AM C3 23.2620 Aeroplane Flight Manual

ED Decision 2017/025/R CS VLA Amdt 1 VLA.1581 Airplane Flight Manual and Approved Manual Material - General VLA.1583 Operating limitations VLA.1585 Operating procedures VLA.1587 Performance information VLA.1589 Loading information Powered by EASA eRules Page 117 of 118 | May 2026 Easy Access Rules for Normal - Category CS Amendment 6, AMC/GM Issue 5 Aeroplanes (CS - 23) SUBPART G — FLIGHT CREW INTERFACE AND OTHER INFORMATION

CS 23.2625 Instructions for Continued Airworthiness

ED Decision 2017/013/R (a) The applicant must prepare Instructions for Continued Airworthiness that are appropriate for the certification level and performance level of the aeroplane.

(b) If Instructions for Continued Airworthiness are not supplied by the manufacturer of an appliance or product installed in the aeroplane, the Instructions for Continued Airworthiness for the aeroplane must include the information essential to the continued airworthiness of the aeroplane.

(c) The Instructions for Continued Airworthiness must contain a Section titled ‘Airworthiness limitations’ that is segregated and clearly distinguishable from the rest of the document. This Section must set forth each mandatory replacement time, structural in spection interval, and related structural inspection procedure required for type certification. This Section must contain a legible statement in a prominent location that reads: ‘The Airworthiness limitations Section is approved and variations must also be approved’.

(d) The applicant must develop and implement procedures to prevent structural failures due to foreseeable causes of strength degradation, which could result in serious or fatal injuries, loss of the aeroplane, or extended periods of operation with reduced saf ety margins. The Instructions for Continued Airworthiness must include procedures developed under CS 23.2255 .

AMC1 23.2625 Instructions for Continued Airworthiness

ED Decision 2026/003/R ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification 10.6 Instructions for Continued Airworthiness F3120/F3120M - 20 Standard Specification for Ice Protection for General Aviation Aircraft F3117/F3117M - 24a Standard Specification for Crew Interface in Aircraft F3408/F3408M - 21 Standard Specification for Aircraft Emergency Parachute Recovery Systems [AMC&GM to CS - 23: Issue 4] [AMC & GM to CS - 23: Issue 5]

AMC2 23.2625 Instructions for Continued Airworthiness

ED Decision 2017/025/R CS - 23 Amdt 4 23.1529 Instructions for Continued Airworthiness (With Appendix G)

AM C3 23.2625 Instructions for Continued Airworthiness

ED Decision 2017/025/R CS VLA Amdt 1 VLA.1529 Instructions for Continued Airworthiness Powered by EASA eRules Page 118 of 118 | May 2026

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Document details

Doc number
CS-23 Amendment 6 / AMC & GM Issue 5
Publisher
EASA
Year
2026
Pages
118
File size
1.8 MB
Chapters
13
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