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 23.2235 Structural strength
ED Decision 2023/002/R
ASTM F44 F3264-21 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
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
AMC3 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 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.
AMC1 23.2240 Structural durability
ED Decision 2023/002/R
ASTM F44 F3264-21 Standard Specification for Normal Category Aeroplanes Certification
6.9 Structural Durability & 9.11 Equipment Containing High-Energy Rotors
F3061/F3061M-20 Standard Specification for Systems and Equipment in Small Aircraft
F3066/F3066M-18 Standard Specification for Aircraft Powerplant Installation Hazard Mitigation
F3115/F3115M-20 Standard Specification for Structural Durability for Small Aeroplanes
F3380-19 Standard Practice for Structural Compliance of Very Light Aeroplanes
F3116/F3116M-18e2 Standard Specification for Design Loads and Conditions
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
AMC3 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
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 2023/002/R
ASTM F44 F3264-21 Standard Specification for Normal Category Aeroplanes Certification
6.10 Aeroelasticity
F3061/F3061M-20 Standard Specification for Systems and Equipment in Small Aircraft
F3093/F3093M-21 Standard Specification for Aeroelasticity Requirements
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
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.
AMC1 23.2250 Design and construction principles
ED Decision 2023/002/R
ASTM F44 F3264-21 Standard Specification for Normal Category Aeroplanes Certification
6.11 Design and Construction Principles
F3061/F3061M-20 Standard Specification for Systems and Equipment in Small Aircraft
F3232/F3232M-20 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
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
AMC3 23.2250 Design and construction principles
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
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 23.2255 Protection of structure
ED Decision 2023/002/R
ASTM F44 F3264-21 Standard Specification for Normal Category Aeroplanes Certification
6.12 Protection of Structure
F3061/F3061M-20 Standard Specification for Systems and Equipment in Small Aircraft
F3232/F3232M-20 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
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
AMC3 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 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.
AMC1 23.2260 Materials and processes
ED Decision 2023/002/R
ASTM F44 F3264-21 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
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
AMC3 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;
(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.
AMC1 23.2265 Special factors of safety
ED Decision 2023/002/R
ASTM F44 F3264-21 Standard Specification for Normal Category Aeroplanes Certification
6.14 Special Factors of Safety
F3061/F3061M-20 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
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
AMC3 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
VLA.681 Limit load static tests - Control System
VLA.693 Joints
VLA.785 Seats, safety belts, and harnesses