CS 23.2300 Flight control systems
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.
AMC1 23.2300 Flight control systems
ED Decision 2019/020/R
ASTM F44 F3264-18b Standard Specification for Normal Category Aeroplanes Certification
7.1 Flight Control Systems:
F3061/F3061M-17 Standard Specification for Systems and Equipment in Small Aircraft
F3232/F3232M-17 Standard Specification for Flight Controls in Small Aircraft
F3066/F3066M-18 Standard Specification for Aircraft Powerplant Installation Hazard Mitigation
Remarks
Except as follows:
For Level 1 single-engine airplanes with a stall speed in the landing configuration (VS0) of more than 45 knots, ASTM F3264-18b, paragraph 7.1 does not include means for showing that the airplane 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 airplane 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.
F3066 revised from -15 to -18
AMC2 23.2300 Flight control systems
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
AMC3 23.2300 Flight control systems
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
CS 23.2305 Landing gear systems
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.
AMC1 23.2305 Landing gear systems
ED Decision 2019/020/R
ASTM F44 F3264-18b Standard Specification for Normal Category Aeroplanes Certification
7.2 Landing Gear Systems:
F3061/F3061M-17 Standard Specification for Systems and Equipment in Small Aircraft
AMC2 23.2305 Landing gear systems
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
AMC3 23.2305 Landing gear systems
ED Decision 2017/025/R
CS VLA Amdt 1
VLA.729 Landing gear extension and retraction system
VLA.735 Brakes
CS 23.2310 Buoyancy for seaplanes and amphibians
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.
AMC1 23.2310 Buoyancy for seaplanes and amphibians
ED Decision 2019/020/R
ASTM F44 F3264-18b Standard Specification for Normal Category Aeroplanes Certification
7.3 Buoyancy for Seaplanes and Amphibians:
F3061/F3061M-17 Standard Specification for Systems and Equipment in Small Aircraft
AMC2 23.2310 Buoyancy for seaplanes and amphibians
ED Decision 2017/025/R
CS-23 Amdt 4
23.751 Main float buoyancy
23.755 Hulls
23.757 Auxiliary floats
AMC3 23.2310 Buoyancy for seaplanes and amphibians
ED Decision 2017/025/R
CS VLA Amdt 1
VLA.751 Main float buoyancy
VLA.757 Auxiliary floats