CS 23.2100 Mass and centre of gravity
ED Decision 2017/013/R
(a) The applicant must determine limits for mass and centre of gravity that provide for the safe operation of the aeroplane.
(b) The applicant’s design must comply with each requirement of this Subpart at critical combinations of mass and centre of gravity within the aeroplane’s range of loading conditions using acceptable tolerances.
(c) The condition of the aeroplane at the time of determining its empty mass and centre of gravity must be well defined and easily repeatable.
AMC1 23.2100 Mass and centre of gravity
ED Decision 2019/020/R
ASTM F44 F3264-18b Standard Specification for Normal Category Aeroplanes Certification
5.1 Weight/Mass and Centre of Gravity:
F3082/F3082M-17 Standard Specification for Weights and Centers of Gravity of Aircraft
F3114-15 Standard Specification for Structures
AMC2 23.2100 Mass and centre of gravity
ED Decision 2017/025/R
CS-23 Amdt 4
23.21 Proof of compliance
23.23 Load distribution limits
23.25 Weight limits
23.29 Empty weight and corresponding center of gravity
23.31 Removable ballast
23.871 Levelling means
AMC3 23.2100 Mass and centre of gravity
ED Decision 2017/025/R
CS VLA Amdt 1
VLA.21 Proof of compliance
VLA.23 Load distribution limits
VLA.25 Weight limits
VLA.29 Empty weight and corresponding center of gravity
VLA.871 Levelling means
ED Decision 2017/013/R
(a) Unless otherwise prescribed, an aeroplane must meet the performance requirements of this Subpart in:
(1) still air and standard atmospheric conditions at sea level for all aeroplanes; and
(2) ambient atmospheric conditions within the operating envelope for:
(i) Level-1 high-speed and Level-2 high-speed aeroplanes; and
(ii) Level-3 and Level-4 aeroplanes.
(b) Unless otherwise prescribed, the applicant must develop the performance data required by this Subpart for the following conditions:
(1) airport altitudes from sea level to 3 048 m (10 000 ft); and
(2) temperatures above and below standard day temperature that are within the range of operating limitations if those temperatures could have a negative effect on performance.
(c) The procedures used for determining take-off and landing distances must be executable consistently by pilots of average skill in atmospheric conditions expected to be encountered in service.
(d) Performance data determined in accordance with CS 23.2105(b) must account for losses due to atmospheric conditions, cooling needs, and other demands on power sources.
ED Decision 2019/020/R
ASTM F44 F3264-18b Standard Specification for Normal Category Aeroplanes Certification
5.2 Performance Data:
F3179/F3179M-18 Standard Specification for Performance of Aircraft
Remarks
F3179 revised from -16 to -18
ED Decision 2017/013/R
The applicant must determine the aeroplane stall speed or the minimum steady flight speed for each flight configuration used in normal operations, including take-off, climb, cruise, descent, approach, and landing. The stall speed or minimum steady flight speed determination must account for the most adverse conditions for each flight configuration.
ED Decision 2019/020/R
ASTM F44 F3264-18b Standard Specification for Normal Category Aeroplanes Certification
5.3 Stall Speed:
F3179/F3179M-18 Standard Specification for Performance of Aircraft
Remarks
F3179 revised from -16 to -18
CS 23.2115 Take-off performance
ED Decision 2017/013/R
(a) The applicant must determine aeroplane take-off performance accounting for:
(1) stall speed safety margins;
(2) minimum control speeds; and
(3) climb gradients.
(b) For single-engine aeroplanes and Levels 1, 2, and 3 low-speed multi-engine aeroplanes, take-off performance includes the determination of ground roll and initial climb distance to 15 m (50 ft) above the take-off surface.
(c) For high-speed multi-engine aeroplanes of Levels 1, 2, and 3, and for all Level-4 multi-engine aeroplanes, take-off performance includes a determination of the following distances after a sudden critical loss of thrust:
(1) an aborted take-off at critical speed;
(2) ground roll and initial climb to 11 m (35 ft) above the take-off surface; and
(3) net take-off flight path.
AMC1 23.2115 Take-off performance
ED Decision 2019/020/R
ASTM F44 F3264-18b Standard Specification for Normal Category Aeroplanes Certification
5.4 Take-off Performance:
F3179/F3179M-18 Standard Specification for Performance of Aircraft
Remarks
F3179 revised from -16 to -18
AMC2 23.2115 Take-off performance
ED Decision 2017/025/R
CS-23 Amdt 4
23.51 Takeoff speeds
23.53 Takeoff performance
23.55 Accelerate-stop distance
23.57 Takeoff path
23.59 Takeoff distance and takeoff run
23.61 Takeoff flight path
ED Decision 2017/013/R
The design must comply with the following minimum climb performance out of ground effect:
(a) with all engines operating and in the initial climb configuration(s):
(1) for Level-1 and -2 low-speed aeroplanes, a climb gradient of 8.3 % for landplanes and 6.7 % for seaplanes and amphibians; and
(2) for Level-1 and -2 high-speed aeroplanes and all Level-3 and -4 aeroplanes, a climb gradient at take-off of 4 %.
(b) after a critical loss of thrust on multi-engine aeroplanes:
(1) for Level-1 and -2 low-speed aeroplanes that do not meet single-engine crashworthiness requirements, a climb gradient of 1.5 % at a pressure altitude of 1 524 m (5 000 ft) in the cruise configuration;
(2) for Level-1 and -2 high-speed aeroplanes, and Level-3 low-speed aeroplanes, a 1 % climb gradient at 122 m (400 ft) above the take-off surface with the landing gear retracted and flaps in the take-off configuration; and
(3) for Level-3 high-speed aeroplanes and all Level-4 aeroplanes, a 2 % climb gradient at 122 m (400 ft) above the take-off surface with the landing gear retracted and flaps in the approach configuration;
(c) a climb gradient of 3 % during balked landing, without creating undue pilot workload, with the landing gear extended and flaps in the landing configuration(s).
AMC1 23.2120 Climb requirements
ED Decision 2019/020/R
ASTM F44 F3264-18b Standard Specification for Normal Category Aeroplanes Certification
5.5 Climb Requirements:
F3179/F3179M-18 Standard Specification for Performance of Aircraft
Remarks
F3179 revised from -16 to -18
AMC2 23.2120 Climb requirements
ED Decision 2017/025/R
CS-23 Amdt 4
23.63 Climb: General
23.65 Climb: All engines operating
AMC3 23.2120 Climb requirements
ED Decision 2017/025/R
CS VLA Amdt 1
VLA.65 Climb: All engines operating
ED Decision 2017/013/R
(a) The applicant must determine, as applicable, climb and/or descent performance:
(1) for all engines operating;
(2) following a critical loss of thrust on take-off; and
(3) after a critical loss of thrust, during the en route phase of flight.
AMC1 23.2125 Climb information
ED Decision 2019/020/R
ASTM F44 F3264-18b Standard Specification for Normal Category Aeroplanes Certification
5.6 Climb Information:
F3179/F3179M-18 Standard Specification for Performance of Aircraft
Remarks
F3179 revised from -16 to -18
AMC2 23.2125 Climb information
ED Decision 2017/025/R
CS-23 Amdt 4
23.66 Takeoff climb: one engine inoperative
23.67 Climb: One engine inoperative
23.69 En route climb/descent
23.71 Glide: single engine airplanes
ED Decision 2017/013/R
The applicant must determine the following, for standard temperatures at critical combinations of mass and altitude within the operational limits:
(a) the distance, starting from a height of 15 m (50 ft) above the landing surface, required to land and come to a stop; and
(b) the approach and landing speeds, configurations, and procedures, which allow a pilot of average skill to land within the published landing distance consistently and without causing damage or injury, and which allow for a safe transition to the balked-landing conditions.
ED Decision 2019/020/R
ASTM F44 F3264-18b Standard Specification for Normal Category Aeroplanes Certification
5.7 Landing:
F3179/F3179M-18 Standard Specification for Performance of Aircraft
Remarks
F3179 revised from -16 to -18
ED Decision 2017/025/R
CS-23 Amdt 4
23.73 Reference landing approach speed
23.75 Landing distance
23.77 Balked landing
ED Decision 2017/025/R
CS VLA Amdt 1
VLA.75 Landing distance
VLA.77 Balked landing
ED Decision 2017/013/R
(a) The aeroplane must be controllable and manoeuvrable, without requiring exceptional piloting skills, alertness, or strength, within the operating envelope:
(1) at all loading conditions for which certification is requested;
(2) during all phases of flight;
(3) with likely reversible flight control or propulsion system failure; and
(4) during configuration changes.
(b) The aeroplane must be able to complete a landing without causing substantial damage or serious injury using the steepest approved approach gradient procedures and providing a reasonable safe margin below VREF or above approach angle of attack.
(c) VMC is the calibrated airspeed at which, following the sudden critical loss of thrust, it is possible to maintain control of the aeroplane. For multi-engine aeroplanes, the applicant must determine VMC, if applicable, for the most critical configurations used in take-off and landing operations.
(d) If the applicant requests certification of an aeroplane for aerobatics, the applicant must demonstrate those aerobatic manoeuvres for which certification is requested and determine entry speeds.
ED Decision 2019/020/R
ASTM F44 F3264-18b Standard Specification for Normal Category Aeroplanes Certification
5.8 Controllability:
F3173/F3173M-17 Standard Specification for Aircraft Handling Characteristics
Remarks
F3173 revised from -15 to -17
ED Decision 2017/025/R
CS-23 Amdt 4
23.141 Flight Characteristics -General
23.143 Controllability and Manoeuvrability - General
23.145 Longitudinal control
23.147 Directional and lateral control
23.149 Minimum control speed
23.151 Acrobatic manoeuvres
23.153 Control during landings
23.155 Elevator control force in manoeuvres
23.157 Rate of roll
ED Decision 2017/025/R
CS VLA Amdt 1
VLA.141 Flight Characteristics -General
VLA.143 Controllability and Manoeuvrability - General
VLA.145 Longitudinal control
VLA.153 Control during landings
VLA.155 Elevator control force in manoeuvres
VLA.157 Rate of roll
ED Decision 2017/013/R
(a) The aeroplane must maintain lateral and directional trim without further force upon, or movement of, the primary flight controls or corresponding trim controls by the pilot, or the flight control system, under the following conditions:
(1) for Level-1, -2, and -3 aeroplanes, in cruise;
(2) for Level-4 aeroplanes, in normal operations.
(b) The aeroplane must maintain longitudinal trim without further force upon, or movement of, the primary flight controls or corresponding trim controls by the pilot, or the flight control system, under the following conditions:
(1) climb,
(2) level flight,
(3) descent,
(4) approach.
(c) Residual control forces must not fatigue or distract the pilot during normal operations of the aeroplane and likely abnormal or emergency operations, including a critical loss of thrust on multi-engine aeroplanes.
ED Decision 2019/020/R
ASTM F44 F3264-18b Standard Specification for Normal Category Aeroplanes Certification
5.9 Trim:
F3173/F3173M-17 Standard Specification for Aircraft Handling Characteristics
Remarks
F3173 revised from -15 to -17
ED Decision 2017/013/R
(a) Aeroplanes not certified for aerobatics must:
(1) have static longitudinal, lateral, and directional stability in normal operations;
(2) have dynamic short period and Dutch roll stability in normal operations; and
(3) provide stable control feedback throughout the operating envelope.
(b) No aeroplane may exhibit any divergent longitudinal stability characteristic so unstable as to increase the pilot’s workload or otherwise endanger the aeroplane and its occupants.
ED Decision 2019/020/R
ASTM F44 F3264-18b Standard Specification for Normal Category Aeroplanes Certification
5.10 Stability:
F3173/F3173M-17 Standard Specification for Aircraft Handling Characteristics
Remarks
F3173 revised from -15 to -17
ED Decision 2017/025/R
CS-23 Amdt 4
23.171 Stability – General
23.173 Static longitudinal stability
23.175 Demonstration of static longitudinal stability
23.177 Static directional and lateral stability
23.181 Dynamic stability
ED Decision 2017/025/R
CS VLA Amdt 1
VLA.171 Stability – General
VLA.173 Static longitudinal stability
VLA.175 Demonstration of static longitudinal stability
VLA.177 Static directional and lateral stability
VLA.181 Dynamic stability
CS 23.2150 Stall characteristics, stall warning, and spins
ED Decision 2017/013/R
(a) The aeroplane must have controllable stall characteristics in straight flight, turning flight, and accelerated turning flight with a clear and distinctive stall warning that provides sufficient margin to prevent inadvertent stalling. A stall warning that is mutable for aerobatic flight phases is acceptable.
(b) Single-engine aeroplanes, not certified for aerobatics, must not have a tendency to hazardously depart from controlled flight inadvertently.
(c) Level-1 and -2 multi-engine aeroplanes, not certified for aerobatics, must not have a tendency to hazardously depart controlled flight inadvertently from thrust asymmetry after a critical loss of thrust.
(d) Aeroplanes certified for aerobatics that include spins must have controllable stall characteristics and the ability to recover within one and one-half additional turns after initiation of the first control action from any point in a spin, not exceeding six turns or any greater number of turns for which certification is requested, while remaining within the operating limitations of the aeroplane.
(e) Aeroplanes intended for aerobatics have the ability to recover from any approved manoeuvre, without exceeding limitations or exhibiting unsafe characteristics.
AMC1 23.2150 Stall characteristics, stall warning, and spins
ED Decision 2019/020/R
ASTM F44 F3264-18b Standard Specification for Normal Category Aeroplanes Certification
5.11 Stall Characteristics, Stall Warning, and Spins:
F3180/F3180M-18 Standard Specification for Low-Speed Flight Characteristics of Aircraft
Remarks
F3180 revised from -16 to -18
AMC2 23.2150 Stall characteristics, stall warning, and spins
ED Decision 2019/020/R
CS-23 Amdt 4
23.201 Wings level stall
23.203 Turning Flight and accelerated turning stalls
23.207 Stall Warning
23.221 Spinning
Remarks
CS 23.2150(b) and (c) are not covered by AMC2. Applicants may use the provision in ASTM F3180-18 to show compliance with CS 23.2150
AMC3 23.2150 Stall characteristics, stall warning, and spins
ED Decision 2019/020/R
CS VLA Amdt 1
VLA.201 Wings level stall
VLA.203 Turning Flight and accelerated turning stalls
VLA.207 Stall Warning
VLA.221 Spinning
Remarks
VLA.221(a) is not accepted as AMC to 23.2150 only VLA.221(b) can be used.
CS 23.2155 Ground- and water-handling characteristics
ED Decision 2017/013/R
(a) The aeroplane has controllable longitudinal and directional handling characteristics during taxi, take-off, and landing for the anticipated operation.
AMC1 23.2155 Ground- and water-handling characteristics
ED Decision 2019/020/R
ASTM F44 F3264-18b Standard Specification for Normal Category Aeroplanes Certification
5.12 Ground and Water Handling Characteristics:
F3173/F3173M-17 Standard Specification for Aircraft Handling Characteristics
Remarks
F3173 revised from -15 to -17
AMC2 23.2155 Ground- and water-handling characteristics
ED Decision 2017/025/R
CS-23 Amdt 4
23.231 Longitudinal stability and control
23.233 Directional stability and control
23.235 Operation on unpaved surfaces
23.237 Operation on water
23.239 Spray characteristics
AMC3 23.2155 Ground- and water-handling characteristics
ED Decision 2017/025/R
CS VLA Amdt 1
VLA.231 Longitudinal stability and control
VLA.233 Directional stability and control
VLA.235 Operation on unpaved surfaces
VLA.239 Spray characteristics
CS 23.2160 Vibration, buffeting, and high-speed characteristics
ED Decision 2017/013/R
(a) Vibration and buffeting, for operations up to VD/MD, must not interfere with the control of the aeroplane or cause excessive fatigue to the flight crew. Stall warning buffet within these limits is allowable.
(b) For high-speed aeroplanes and all aeroplanes with a maximum operating altitude greater than 7 625 m (25 000 ft) pressure altitude, there must be no perceptible buffeting in cruise configuration at 1 g and at any speed up to VMO/MMO, except stall buffeting.
(c) For high-speed aeroplanes, the applicant must determine the positive manoeuvring load factors at which the onset of perceptible buffet occurs in the cruise configuration within the operational envelope. Likely inadvertent excursions beyond this boundary must not result in structural damage.
(d) High-speed aeroplanes must have recovery characteristics that do not result in structural damage or loss of control, beginning at any likely speed up to VMO/MMO, following:
(1) an inadvertent speed increase; and
(2) a high-speed trim upset for aeroplanes where dynamic pressure can impair the longitudinal trim system operation.
AMC1 23.2160 Vibration, buffeting, and high-speed characteristics
ED Decision 2019/020/R
ASTM F44 F3264-18b Standard Specification for Normal Category Aeroplanes Certification
5.13 Vibration, Buffeting, and High-Speed Characteristics:
F3173/F3173M-17 Standard Specification for Aircraft Handling Characteristics
Remarks
F3173 revised from -15 to -17
AMC2 23.2160 Vibration, buffeting, and high-speed characteristics
ED Decision 2017/025/R
CS-23 Amdt 4
23.251 Vibration and buffeting
23.253 High-speed characteristics
AMC3 23.2160 Vibration, buffeting, and high-speed characteristics
ED Decision 2017/025/R
CS VLA Amdt 1
VLA.251 Vibration and buffeting
CS 23.2165 Performance and flight characteristics requirements for flight in icing conditions
ED Decision 2017/013/R
(a) An applicant who requests certification for flight in icing conditions must show the following in the icing conditions for which certification is requested under normal operation of the ice protection system(s):
(1) comply with each requirement of this Subpart, except those applicable to spins and any that must be demonstrated at speeds in excess of:
(i) 250 knots calibrated airspeed (KCAS);
(ii) VMO or MMO or VNE; or
(iii) a speed at which the applicant demonstrates the airframe will be free of ice accretion;
(2) the means by which stall warning is provided to the pilot for flight in icing conditions and non-icing conditions is the same.
(b) If an applicant requests certification for flight in icing conditions, the applicant must provide a means to detect any icing conditions for which certification is not requested and demonstrate the aeroplane’s ability to avoid or exit those conditions.
(c) The applicant must develop an operating limitation to prohibit intentional flight, including take-off and landing, into icing conditions for which the aeroplane is not certified to operate.
AMC1 23.2165 Performance and flight characteristics requirements for flight in icing conditions
ED Decision 2019/020/R
ASTM F44 F3264-18b Standard Specification for Normal Category Aeroplanes Certification
5.14 Performance and Flight Characteristics Requirements for Flight in Icing Conditions:
F3120/F3120M-15 Standard Specification for Ice Protection for General Aviation Aircraft
AMC2 23.2165 Performance and flight characteristics requirements for flight in icing conditions
ED Decision 2017/025/R
CS-23 Amdt 4
23.1419 Ice Protection
AMC3 23.2165 Performance and flight characteristics requirements for flight in icing conditions
ED Decision 2017/025/R
None