Skip to content

A gradual release of Avioverse begins in October 2026. Request early access →

APPENDICES TO CS-25

Large Aeroplanes (CS-25) · CS-25 · H25.1 – S25.60

On this page

  1. Appendix A

    [Figure or form omitted from this preview — available in the Avioverse workspace library.]

  2. Part I – Atmospheric Icing Conditions

    Continuous maximum icing. The maximum continuous intensity of atmospheric icing conditions (continuous maximum icing) is defined by the variables of the…

  3. Part II – Airframe Ice Accretions

    Ice accretions - General. The most critical ice accretion in terms of aeroplane performance and handling qualities for each flight phase must be used to…

  4. Appendix D

    Criteria for determining minimum flight crew. The following are considered by the Agency in determining the minimum flight crew under CS 25.1523.

  5. Part I – Test Criteria and Procedures for Showing Compliance with CS 25.853, 25.855 or 25.869

    Material test criteria – (1) Interior compartments occupied by crew or passengers.

  6. Part II – Flammability of Seat Cushions

    Criteria for Acceptance. Each seat cushion must meet the following criteria:

  7. Part III – Test Method to Determine Flame Penetration Resistance of Cargo Compartment Liners

    Criteria for Acceptance (1) At least three specimens of cargo compartment sidewall or ceiling liner panels must be tested.

  8. Part IV – Test Method to Determine the Heat Release Rate from Cabin Materials Exposed to Radiant Heat

    (See AMC to Appendix F, Part IV) (a) Summary of Method (1) The specimen to be tested is injected into an environmental chamber through which a constant…

  9. AMC to Appendix F, Part IV – Test Method to Determine the Heat Release Rate from Cabin Materials Exposed to Radiant Heat

    Appendix F, Part IV (b)(4) Air Distribution System. The air distribution is to be determined by the equipment design.

  10. Part V – Test Method to Determine the Smoke Emission Characteristics of Cabin Materials

    Summary of Method. The specimens must be constructed, conditioned, and tested in the flaming mode in accordance with American Society of Testing and…

  11. Part VI – Test Method to Determine the Flammability and Flame Propagation Characteristics of Thermal/Acoustic Insulation Materials

    Use this test method to evaluate the flammability and flame propagation characteristics of thermal/acoustic insulation when exposed to both a radiant…

  12. Part VII – Test Method to Determine the Burnthrough Resistance of Thermal/Acoustic Insulation Materials

    Use the following test method to evaluate the burnthrough resistance characteristics of aircraft thermal/acoustic insulation materials when exposed to a…

  13. Appendix H Instructions for Continued Airworthiness

    (See AMC to Appendix H)

  14. H25.1 General

    This Appendix specifies requirements for the preparation of Instructions for Continued Airworthiness as required by CS 25.1529 and CS 25.1729 (b) The…

  15. H25.2 Format

    The Instructions for Continued Airworthiness must be in the form of a manual or manuals as appropriate for the quantity of data to be provided.

  16. H25.3 Content

    The contents of the manual or manuals must be prepared in a language acceptable to the Agency.

  17. H25.4 Airworthiness Limitations Section

    The Instructions for Continued Airworthiness must contain a section titled Airworthiness Limitations that is segregated and clearly distinguishable from…

  18. AMC to Appendix H, H25.4(a)(3) Mandatory replacement time of EWIS components as defined in CS 25.1701

    In accordance with subparagraph H25.4(a)(3) applicants are required to include in the Airworthiness Limitations section of the Instructions for Continued…

  19. H25.5 Electrical Wiring Interconnection System Instructions for Continued Airworthiness

    The applicant must prepare Instructions for Continued Airworthiness applicable to Electrical Wiring Interconnection System as defined in CS 25.1701.

  20. AMC to Appendix H, H25.5 Instructions for Continued Airworthiness applicable to EWIS

    In accordance with subparagraph H25.5 the applicant must prepare Instructions for Continued Airworthiness (ICA) applicable to EWIS as defined by 25.1701…

  21. H25.6 Information system security Instructions for Continued Airworthiness

    The applicant must prepare Instructions for Continued Airworthiness (ICA) that are applicable to aircraft information system security protection as…

  22. I 25.1 General

    This Appendix specifies additional requirements and limitations for aeroplanes equipped with an engine control system that automatically resets thrust or…

  23. I 25.2 Definitions

    AutomaticTakeoff Thrust Control System (ATTCS). An ATTCS system is defined as a system which automatically resets thrust or power on the operating…

  24. I 25.3 Performance requirements

    All applicable performance requirements of CS-25 must be met with the ATTCS system functioning normally as designed, except that the propulsive thrust…

  25. I 25.4 Reliability requirements

    (See CS 25.1309 and AMC 25.1309) (a) The occurrence of an ATTCS system failure or a combination of failures in the ATTCS system during the critical time…

  26. I 25.5 Thrust or power setting

    The initial setting of thrust or power controls on each engine at the beginning of the take-off roll may not be less than the lesser of – (a) That…

  27. I 25.6 Powerplant controls

    General (1) In addition to the requirements of CS 25.1141, no single failure or malfunction, or probable combination thereof, of the ATTCS system…

  28. I 25.7 Powerplant instruments

    System Control and Monitoring. A means must be provided to indicate when the ATTCS system is in the armed or ready condition.

  29. Appendix J Emergency Demonstration

    The following test criteria and procedures must be used for showing compliance with CS 25.803:

  30. K25.1 General

    The following criteria must be used for showing compliance with CS 25.302 for aeroplanes equipped with flight control systems, autopilots, stability…

  31. K25.2 Effects of Systems on Structures

    General. The following criteria will be used in determining the influence of a system and its failure conditions on the aeroplane structure.

  32. Appendix L

    Element of System Strength Value Remarks Proof Ultimate Rigid pipes and ducts Couplings Flexible hoses Return line elements 1·5 PW 1·5 PW 2·0 PW – 3·0 PW…

  33. M25.1 Fuel tank flammability exposure requirements

    The Fleet Average Flammability Exposure level of each fuel tank, as determined in accordance with Appendix N of CS-25, must not exceed 3 percent of the…

  34. M25.2 Showing compliance

    The applicant must provide data from analysis, ground testing, and flight testing, or any combination of these, that:

  35. M25.3 Reliability indications and maintenance access

    Reliability indications must be provided to identify failures of the FRM that would otherwise be latent and whose identification is necessary to ensure…

  36. M25.4 Airworthiness limitations and procedures

    The FRM shall be subject to analysis using conventional processes and methodology to ensure that the minimum scheduled maintenance tasks required for…

  37. Appendix N Fuel Tank Flammability Exposure

    (See AMC to Appendix N)

  38. N25.1 General

    This appendix specifies the requirements for conducting fuel tank fleet average flammability exposure analyses required to meet CS 25.981(b) and Appendix…

  39. AMC to Appendix N, N25.1(a) Fuel tank flammability assessment method

    The Monte-Carlo program as well as the method and procedures set forth in FAA document, “Fuel Tank Flammability Assessment Method Users Manual”…

  40. AMC to Appendix N, N25.1(b) Qualitative fuel tank flammability assessment

    A conventional unheated aluminium wing tank is a conventional aluminium structure, integral tank of a subsonic transport aeroplane wing, with minimal…

  41. N25.2 Definitions

    Bulk Average Fuel Temperature means the average fuel temperature within the fuel tank or different sections of the tank if the tank is subdivided by…

  42. N25.3 Fuel tank flammability exposure analysis

    A flammability exposure analysis must be conducted for the fuel tank under evaluation to determine fleet average flammability exposure for the aeroplane…

  43. N25.4 Variables and data tables

    The following data must be used when conducting a flammability exposure analysis to determine the fleet average flammability exposure.

  44. Appendix O Supercooled Large Drop icing conditions

    Appendix O consists of two parts. Part I defines Appendix O as a description of supercooled large drop (SLD) icing conditions in which the drop median…

  45. Part I – Meteorology

    Appendix O icing conditions are defined by the parameters of altitude, vertical and horizontal extent, temperature, liquid water content, and water mass…

  46. Part II – Airframe ice accretions

    General. The most critical ice accretion in terms of aeroplane performance and handling qualities for each flight phase must be used to show compliance…

  47. Appendix P Mixed phase and ice crystal icing envelope (Deep convective clouds)

    The ice crystal icing envelope is depicted in Figure 1 below.

  48. Appendix Q Additional airworthiness requirements for approval of a Steep Approach Landing (SAL) capability

    (See AMC to Appendix Q)

  49. (SAL) 25.1 Applicability

    This Appendix contains airworthiness requirements that enable an aeroplane to obtain approval for a steep approach landing capability using an approach…

  50. (SAL) 25.2 Definitions

    For the purposes of this Appendix: Steep Approach Landing: An approach to land made using a glide path angle greater than or equal to 4.5°, as selected…

  51. (SAL) 25.3 Steep Approach Landing Distance

    (Applicable only if a reduced landing distance is sought, or if the landing procedure (speed, configuration, etc.) differs significantly from normal…

  52. (SAL) 25.4 Climb: One-engine-inoperative

    In a configuration corresponding to the normal all-engines-operating procedure in which VSR for this configuration does not exceed 110 % of the VSR for…

  53. (SAL) 25.5 Safe operational and flight characteristics

    It must be demonstrated that it is possible to complete a stabilised approach in calm air down to the commencement of the landing flare, followed by a…

  54. AMC to Appendix Q, (SAL) 25.5 Safe operational and flight characteristics

    For the approach demonstrations required by (SAL) 25.5(a), due account should be taken of:

  55. (SAL) 25.6 Aeroplane Flight Manual

    For steep approach landing, the AFM shall include the following:

  56. Appendix R HIRF Environments and Equipment HIRF Test Levels

    This Appendix specifies the HIRF environments and equipment HIRF test levels for electrical and electronic systems under CS 25.1317.

  57. Appendix S Airworthiness requirements for non-commercially operated aeroplanes and low-occupancy aeroplanes

    (See AMC to Appendix S)

  58. S25.1 General

    Applicability: unless otherwise specified within, the requirements of this Appendix are applicable to the passenger or crew compartments (interiors) of:

  59. AMC to Appendix S, S25.1 Passenger seating configuration

    Where this term is used in Appendix S: ‘Passenger seating configuration’ means the passenger seating capacity established during the certification…

  60. S25.10 General Cabin Arrangement

    Interior Doors on Non-Commercially Operated Aeroplanes (See AMC to Appendix S, S25.10(a)):

  61. AMC to Appendix S, S25.10(a) Interior Doors on Non-Commercially Operated Aeroplanes

    The following provides acceptable means to ensure that a door is open before entering any of the taxiing, take-off, and landing phase, as required by…

  62. AMC to Appendix S, S25.10(b) Interior Doors on Commercially Operated Aeroplanes

    In the case of an aeroplane which is not intended to be limited to non-commercial operations, the familiarity of the occupants with the specific cabin…

  63. AMC to Appendix S, S25.10(c) Isolated Compartments

    Cabin Compartments (a) Compartments to be considered as isolated Compartments in an aeroplane with an approved passenger capacity of less than 20 and a…

  64. AMC to Appendix S, S25.10(d) and (e) Deactivation of existing Emergency Exits

    General S25.10(d)(3) requires to ensure that the distance from each passenger seat to at least one non-deactivated emergency exit on each side of the…

  65. S25.20 Emergency Evacuation

    Flammability Requirements (1) Mattresses of permanent bed installations that are located in compartments isolated from the main passenger cabin by doors…

  66. AMC to Appendix S, S25.20(a)(1) Flammability of Bed Mattresses

    Mattresses of beds that are convertible to/from seats, regardless of their location in the aeroplane, and irrespective of whether or not the seat…

  67. AMC to Appendix S, S25.20(b) Exit as effective as a Type IV exit

    An acceptable means of compliance with the requirement that the remaining exit resulting from an obstruction shall be as effective as a Type IV emergency…

  68. AMC to Appendix S, S25.20(b)(1) Ensuring removal of in-flight obstructions before take-off and landing

    This paragraph provides guidelines regarding the criteria under which an item, although constituting an obstruction that does not comply to CS 25.813(c)…

  69. AMC to Appendix S, S25.20(b)(2) Comparative assessment of evacuation capability

    Use of the Latin square method as detailed in Appendix 4 to FAA Advisory Circular (AC) 25-17A Change 1 Transport Airplane Cabin Interiors Crashworthiness…

  70. S25.30 Circulation Inside Cabin During Flight

    Width of Aisle: for low-occupancy aeroplanes that have a passenger seating configuration of 19 or less, and for non-commercially operated aeroplanes, the…

  71. AMC to Appendix S, S25.30(a) Width of Aisle

    For compliance with the ‘Width of Aisle’ requirement, the following applies:

  72. AMC to Appendix S, S25.30(b) Firm Handholds

    Where the cabin layout is similar to a standard airline layout, firm handholds as normally expected for such seating areas should be provided.

  73. S25.40 Markings and Placards

    ‘No Smoking’ Placards and Lavatory Ashtrays: if smoking is to be prohibited, in lieu of the requirements of CS 25.791(a) and CS 25.791(d), a reduced…

  74. AMC to Appendix S, S25.40(b) Briefing Card Placard

    The instructions that may be reported on the briefing card referred to in S25.40(b) are limited to the instructions necessary to restore the…

  75. AMC to Appendix S, S25.40(c) Seats in Excess

    S25.40(c) requires the installation of a placard, adjacent to each possible passenger boarding door, on aeroplanes which have a greater number of seats…

  76. S25.50 Cabin Attendant Direct View

    In lieu of the requirements of CS 25.785(h)(2), compliance with the following cabin attendant direct view requirements may be shown:

  77. AMC to Appendix S, S25.50(b) Cabin Attendant Direct View

    For commercial operations, compliance with CS 25.785(h)(2) may be shown based on the criteria of FAA AC 25.785-1B, Flight attendant seat and torso…

  78. S25.60 Security

    Non-commercially operated aeroplanes do not need to comply with the security specifications of CS 25.795(b), (c) and (d).

Consolidated from the EASA Easy Access Rules (revision 26 Jan 2023, extracted 17 Aug 2026) for convenience. Not the official publication — verify against the Official Journal of the European Union and the EASA publications before operational use.

Ask Metis about H25.1 – S25.60 →

Metis opens with Avioverse in October 2026 · request early access.

ShareLinkedInX