SUBPART C — STRUCTURES

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.

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]

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

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

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 requirements of this Subpart.

ED Decision 2026/003/R

ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification

6.2Interaction of Systems and Structure

Remarks

F3254-22 Standard Specification for Aircraft Interaction of Systems and Structures

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:

—Replace the probability label ‘remote’ with ‘${10}^{-5}$’

—Replace the label ‘Extremely Improbable’ as follows:

for Level 1, 2 and 3 aeroplanes, use $\mathrm{\text{'}}{10}^{-8}$’

for Level 4 aeroplanes, use ‘${10}^{-9}$’

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

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

ED Decision 2017/025/R

None

Remarks

Provision not included in CS 23 Amdt 4

ED Decision 2017/025/R

None

Remarks

Provision not included in CS VLA Amdt 1

STRUCTURAL 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.

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]

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

23.527 Hull and main float load factors (With Appendix I)

23.537 Seawing loads

23.753 Main float Design

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

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.

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]

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]

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]

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.

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]

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

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

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.

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]

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

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

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

VLA.459 Special devices

VLA.497 Supplementary conditions for tail wheels

VLA.499 Supplementary conditions for nose wheels

VLA.659 Mass Balance

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.

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]

ED Decision 2017/025/R

CS-23 Amdt 4

23.301(a) Loads

23.303 Factors of safety

ED Decision 2017/025/R

CS VLA Amdt 1

VLA.301 Loads

VLA.303 Factors of safety

STRUCTURAL PERFORMANCE

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.

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]

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

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

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 decompression 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.

ED Decision 2026/003/R

ASTM F44 F3264 Standard Specification for Normal Category Aeroplanes Certification

6.9Structural Durability & 9.11Equipment 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]

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

ED Decision 2017/025/R

CS VLA Amdt 1

VLA.572 Metallic wing, empennage, and associated structures

VLA.627 Fatigue strength

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.

(b)The applicants’ design must account for tolerances for all quantities that affect flutter.

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]

ED Decision 2017/025/R

CS-23 Amdt 4

23.629 Flutter

23.687 Spring devices

23.677(c) Trim systems

ED Decision 2017/025/R

CS VLA Amdt 1

VLA.629 Flutter

VLA.687 Spring devices

VLA.677 Trim systems

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.

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]

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

ED Decision 2017/025/R

CS VLA Amdt 1

VLA.601 General

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

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.

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]

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

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

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 structural 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 particular item will equal or exceed those used in the design.

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

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]

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

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

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;

(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 condition loading.

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]

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

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

VLA.681 Limit load static tests - Control System

VLA.693 Joints

VLA.785 Seats, safety belts, and harnesses

STRUCTURAL OCCUPANT PROTECTION

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.

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

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]

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

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