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 23.2210 Structural-design loads
ED Decision 2023/002/R
ASTM F44 F3264-21 Standard Specification for Normal Category Aeroplanes Certification
6.3 Structural Design Loads
F3116/F3116M-18e2 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
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
23.527 Hull and main float load factors (With Appendix I)
23.537 Seawing loads
23.753 Main float Design
AMC3 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 23.2215 Flight load conditions
ED Decision 2023/002/R
ASTM F44 F3264-21 Standard Specification for Normal Category Aeroplanes Certification
6.4 Flight Load Conditions
F3116/F3116M-18e2 Standard Specification for Design Loads and Conditions
F3396/F3396M-20 Standard Practice for Aircraft Simplified Loads Criteria
AMC2 23.2015 Flight load conditions
ED Decision 2017/025/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
AMC3 23.2015 Flight load conditions
ED Decision 2017/025/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
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 23.2220 Ground and water load conditions
ED Decision 2023/002/R
ASTM F44 F3264-21 Standard Specification for Normal Category Aeroplanes Certification
6.5 Ground and Water Load Conditions
F3116/F3116M-18e2 Standard Specification for Design Loads and Conditions
F3331-18 Standard Practice for Aircraft Water Loads
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
AMC3 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.
AMC1 23.2225 Component loading conditions
ED Decision 2023/002/R
ASTM F44 F3264-21 Standard Specification for Normal Category Aeroplanes Certification
6.6 Component Loading Conditions
F3061/F3061M-20 Standard Specification for Systems and Equipment in Small Aircraft
F3232/F3232M-20 Standard Specification for Flight Controls in Small Aircraft
F3116/F3116M-18e2 Standard Specification for Design Loads and Conditions
F3396/F3396M-20 Standard Practice for Aircraft Simplified Loads Criteria
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
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
AMC3 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
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 23.2230 Limit and ultimate loads
ED Decision 2023/002/R
ASTM F44 F3264-21 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
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
AMC3 23.2230 Limit and ultimate loads
ED Decision 2017/025/R
CS VLA Amdt 1
VLA.301 Loads
VLA.303 Factors of safety