SUBPART D — DESIGN AND CONSTRUCTION

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.

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 (VS0) of more than 45 knots, ASTM F3264-24, 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 VS0 greater 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]

ED Decision 2017/025/R

CS-23 Amdt 4

23.655 Installation

23.671(a) Control systems - General

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

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

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.

(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.

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]

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

ED Decision 2017/025/R

CS VLA Amdt 1

VLA.729 Landing gear extension and retraction system

VLA.735 Brakes

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.

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]

ED Decision 2017/025/R

CS-23 Amdt 4

23.751 Main float buoyancy

23.755 Hulls

23.757 Auxiliary floats

ED Decision 2017/025/R

CS VLA Amdt 1

VLA.751 Main float buoyancy

VLA.757 Auxiliary floats

OCCUPANT SYSTEM DESIGN PROTECTION

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.

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]

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

ED Decision 2017/025/R

CS VLA Amdt 1

VLA.783 Exits

VLA.787 Baggage compartments

VLA.807 Emergency exits

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 approach 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.

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

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]

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

ED Decision 2017/025/R

CS VLA Amdt 1

VLA.831 Ventilation

VLA.771 Pilot compartment

VLA.775 Windshields and windows

FIRE AND HIGH ENERGY 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.

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]

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

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

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.

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

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]

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

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

ED Decision 2017/013/R

For operations where the exposure to lightning is likely, the aeroplane must be protected against catastrophic effects of lightning.

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]

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

ED Decision 2017/025/R

CS VLA Amdt 1

VLA.857 Electrical bonding

VLA.1365 Electrical Cables and equipment

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.

ED Decision 2026/003/R

ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification

7.9Design 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]

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

ED Decision 2017/025/R

CS VLA Amdt 1

VLA.1529 Instructions for continued airworthiness

VLA.1541 Markings and placards: General