Easy Access Rules for Normal, Utility, Aerobatic and Commuter Category Aeroplanes (CS-23)

CS 23.59 Take-off distance and take-off run .................................................................... 31 CS 23.61 Take-off flight path ............................................................................................ 31 CS 23.63 Climb: general .................................................................................................... 31 CS 23.65 Climb: all engines operating .............................................................................. 32 CS 23.66 Take-off climb: one-engine-inoperative ............................................................ 32 CS 23.67 Climb: one-engine-inoperative .......................................................................... 33 CS 23.69 En-route climb/descent ..................................................................................... 35 Easy Access Rules for Normal, Utility, Aerobatic and Commuter Category Aeroplanes (CS-23) (Initial issue) Table of contents Powered by EASA eRules Page 7 of 505| Jun 2018 CS 23.71 Glide (Single-engined aeroplanes)..................................................................... 35 CS 23.73 Reference landing approach speed ................................................................... 35 CS 23.75 Landing distance ................................................................................................ 36 CS 23.77 Balked landing ................................................................................................... 36 FLIGHT CHARACTERISTICS ................................................................................................. 38 CS 23.141 General ............................................................................................................ 38 CONTROLLABILITY AND MANOEUVRABILITY ..................................................................... 39 CS 23.143 General ........................................................................................................... 39 CS 23.145 Longitudinal control......................................................................................... 39 CS 23.147 Directional and lateral control......................................................................... 41 CS 23.149 Minimum control speed ................................................................................. 42 CS 23.151 Aerobatic manoeuvres ................................................................................... 43 CS 23.153 Control during landings .................................................................................. 43 CS 23.155 Elevator control force in manoeuvres ............................................................ 43 CS 23.157 Rate of roll ...................................................................................................... 44 TRIM ................................................................................................................................ 46 CS 23.161 Trim ................................................................................................................. 46 STABILITY ......................................................................................................................... 48 CS 23.171 General ........................................................................................................... 48 CS 23.173 Static longitudinal stability ............................................................................. 48 CS 23.175 Demonstration of static longitudinal stability ................................................ 48 CS 23.177 Static directional and lateral stability ............................................................. 49 CS 23.181 Dynamic stability ............................................................................................ 50 STALLS ............................................................................................................................. 51 CS 23.201 Wings level stall .............................................................................................. 51 CS 23.203 Turning flight and accelerated turning stalls .................................................. 51 CS 23.207 Stall warning ................................................................................................... 52 SPINNING ......................................................................................................................... 54 CS 23.221 Spinning .......................................................................................................... 54 GROUND AND WATER HANDLING CHARACTERISTICS ........................................................ 55 CS 23.231 Longitudinal stability and control ................................................................... 55 CS 23.233 Directional stability and control ..................................................................... 55 CS 23.235 Operation on unpaved surfaces ..................................................................... 55 CS 23.237 Operation on water ........................................................................................ 55 CS 23.239 Spray characteristics ....................................................................................... 55 Easy Access Rules for Normal, Utility, Aerobatic and Commuter Category Aeroplanes (CS-23) (Initial issue) Table of contents Powered by EASA eRules Page 8 of 505| Jun 2018 MISCELLANEOUS FLIGHT REQUIREMENTS ......................................................................... 56 CS 23.251 Vibration and buffeting .................................................................................. 56 CS 23.253 High speed characteristics .............................................................................. 56 SUBPART C — STRUCTURE ........................................................... 57 GENERAL .......................................................................................................................... 57 CS 23.301 Loads ............................................................................................................... 57 Appendix A – Simplified Design Load Criteria for Conventional, Single-Engine Airplanes of 2722 kg (6 000 Pounds) or Less Maximum Weight ................................................................ 58 A23.1 General .................................................................................................................. 58 AMC-A23.1 General............................................................................................................... 58 A23.3 Special symbols ..................................................................................................... 59 A23.5 Certification in more than one category ............................................................... 60 A23.7 Flight loads ............................................................................................................ 60 A23.9 Flight conditions .................................................................................................... 61 A23.11 Control surface loads .......................................................................................... 63 AMC-A23.11(c) Control surface loads .................................................................................... 64 A23.13 Control system loads ........................................................................................... 65 CS 23.302 Canard or tandem wing configurations .......................................................... 70 CS 23.303 Factor of safety ............................................................................................... 70 CS 23.305 Strength and deformation .............................................................................. 71 CS 23.307 Proof of structure ........................................................................................... 71 AMC 23.307 Proof of structure ............................................................................................. 71 FLIGHT LOADS .................................................................................................................. 73 CS 23.321 General ........................................................................................................... 73 AMC 23.321(c) Flight loads – General ................................................................................... 73 CS 23.331 Symmetrical flight conditions ......................................................................... 73 CS 23.333 Flight envelope ............................................................................................... 73 CS 23.335 Design airspeeds ............................................................................................. 75 CS 23.337 Limit manoeuvring load factors .................................................................... 77 CS 23.341 Gust load factors ............................................................................................. 77 AMC 23.341(b) Gust loads factors......................................................................................... 78 CS 23.343 Design fuel loads ............................................................................................. 78 AMC 23.343(b) Design fuel loads .......................................................................................... 78 ACJ 23.343(c) Design fuel loads.............................................................................................. 79 CS 23.345 High lift devices............................................................................................... 79 AMC 23.345(d) High lift devices ............................................................................................ 79 CS 23.347 Unsymmetrical flight conditions .................................................................... 79 AMC 23.347(b) Unsymmetrical flight conditions .................................................................. 80 CS 23.349 Rolling conditions ........................................................................................... 80 Easy Access Rules for Normal, Utility, Aerobatic and Commuter Category Aeroplanes (CS-23) (Initial issue) Table of contents Powered by EASA eRules Page 9 of 505| Jun 2018 CS 23.351 Yawing conditions ........................................................................................... 81 CS 23.361 Engine torque ................................................................................................. 81 CS 23.363 Sideload on engine mount .............................................................................. 81 CS 23.365 Pressurised cabin loads .................................................................................. 81 CS 23.367 Unsymmetrical loads due to engine failure.................................................... 82 3CS 23.369 Rear lift truss................................................................................................. 82 CS 23.371 Gyroscopic and aerodynamic loads ................................................................ 83 AMC 23.371 Method of evaluation of gyroscopic loads ....................................................... 83 AMC 23.371(a) Gyroscopic and aerodynamic loads .............................................................. 83 CS 23.373 Speed control devices ..................................................................................... 84 CONTROL SURFACE AND SYSTEM LOADS ........................................................................... 85 CS 23.391 Control surface loads ...................................................................................... 85 CS 23.393 Loads parallel to hinge line ............................................................................. 85 AMC 23.393(a) Loads parallel to hinge lines .......................................................................... 85 AMC 23.393(b) Loads parallel to hinge lines .......................................................................... 85 CS 23.395 Control system loads ...................................................................................... 86 CS 23.397 Limit control forces and torques .................................................................... 86 CS 23.399 Dual control system ........................................................................................ 87 CS 23.405 Secondary control system .............................................................................. 87 AMC 23.405 Secondary control system ................................................................................ 87 CS 23.407 Trim tab effects............................................................................................... 88 CS 23.409 Tabs................................................................................................................. 88 CS 23.415 Ground gust conditions .................................................................................. 88 HORIZONTAL TAIL SURFACES ............................................................................................ 90 CS 23.421 Balancing loads ............................................................................................... 90 CS 23.423 Manoeuvring loads ......................................................................................... 90 AMC 23.423 Manoeuvring loads – Horizontal surfaces ......................................................... 90 CS 23.425 Gust loads ....................................................................................................... 91 CS 23.427 Unsymmetrical loads ...................................................................................... 91 VERTICAL SURFACES ......................................................................................................... 93 CS 23.441 Manoeuvring loads ......................................................................................... 93 AMC 23.441 Manoeuvring loads – Vertical surfaces ............................................................. 94 CS 23.443 Gust loads ....................................................................................................... 94 AMC 23.443 Gust loads – Vertical surfaces ........................................................................... 95 CS 23.445 Outboard fins or winglets ............................................................................... 95 AILERONS AND SPECIAL DEVICES....................................................................................... 97 CS 23.455 Ailerons ........................................................................................................... 97 AMC 23.455(a)(2) Ailerons .................................................................................................... 97 CS 23.459 Special devices ................................................................................................ 97 Easy Access Rules for Normal, Utility, Aerobatic and Commuter Category Aeroplanes (CS-23) (Initial issue) Table of contents Powered by EASA eRules Page 10 of 505| Jun 2018 GROUND LOADS ............................................................................................................... 98 CS 23.471 General ............................................................................................................ 98 CS 23.473 Ground load conditions and assumptions ...................................................... 98 CS 23.477 Landing gear arrangement ............................................................................. 99 Appendix C – Basic Landing Conditions ................................................................................ 100 C23.1 Basic landing conditions ...................................................................................... 100 CS 23.479 Level landing conditions ............................................................................... 101 Appendix D – Wheel Spin-Up Loads ..................................................................................... 103 D23.1 Wheel spin-up loads............................................................................................ 103 CS 23.481 Tail down landing conditions ........................................................................ 104 CS 23.483 One-wheel landing conditions ...................................................................... 104 CS 23.485 Sideload conditions....................................................................................... 104 CS 23.493 Braked roll conditions ................................................................................... 104 CS 23.497 Supplementary conditions for tail wheels .................................................... 105 CS 23.499 Supplementary conditions for nose wheels ................................................. 105 CS 23.505 Supplementary conditions for ski-planes ..................................................... 106 CS 23.507 Jacking loads ................................................................................................. 106 CS 23.509 Towing loads ................................................................................................. 106 CS 23.511 Ground load; unsymmetrical loads on multiple-wheel units ....................... 107 WATER LOADS ................................................................................................................ 108 CS 23.521 Water load conditions .................................................................................. 108 CS 23.523 Design weights and centre of gravity positions ............................................ 108 CS 23.525 Application of loads ...................................................................................... 108 CS 23.527 Hull and main float load factors ................................................................... 108 Appendix I ............................................................................................................................ 110 Seaplane Loads ............................................................................................................... 110 CS 23.529 Hull and main float landing conditions ......................................................... 112 CS 23.531 Hull and main float take-off condition ......................................................... 112 CS 23.533 Hull and main float bottom pressures .......................................................... 113 CS 23.535 Auxiliary float loads ...................................................................................... 114 CS 23.537 Seawing loads ............................................................................................... 115 EMERGENCY LANDING CONDITIONS ............................................................................... 116 CS 23.561 General ......................................................................................................... 116 CS 23.562 Emergency landing dynamic conditions ....................................................... 117 AMC 23.562 Emergency landing dynamic conditions .......................................................... 118 Appendix J – Anthropomorphic Test Dummies for showing compliance with 23.562 ......... 119 Subpart A - GENERAL ............................................................................................................... 119 Easy Access Rules for Normal, Utility, Aerobatic and Commuter Category Aeroplanes (CS-23) (Initial issue) Table of contents Powered by EASA eRules Page 11 of 505| Jun 2018 J23.1 Scope ..................................................................................................................... 119 J23.2 Purpose ................................................................................................................. 119 J23.3 Application ............................................................................................................ 119 J23.4 Terminology .......................................................................................................... 119 Subpart B - 50TH PERCENTILE MALE ........................................................................................ 119 J23.5 General description. .............................................................................................. 119 J23.6 Head ...................................................................................................................... 120 J23.7 Neck....................................................................................................................... 120 J23.8 Thorax.................................................................................................................... 121 J23.9 Lumbar spine, abdomen, and pelvis ..................................................................... 122 J23.10 Limbs ................................................................................................................... 124 J23.11 Test conditions and instrumention ..................................................................... 124 FATIGUE EVALUATION .................................................................................................... 133 CS 23.571 Metallic pressurised cabin structures ........................................................... 133 CS 23.572 Metallic wing, empennage and associated structures ................................. 133 AMC to 23.571 and 23.572 Fatigue evaluation: metallic pressurised cabin structures, metallic wing, empennage and associated structures ....................................................................... 134 CS 23.573 Damage tolerance and fatigue evaluation of structure ............................... 134 AMC 23.573(a)(1)&(3) Damage tolerance and fatigue evaluation of structure – composite airframe structure ................................................................................................................ 136 AMC 23.573(b) Damage tolerance and fatigue evaluation of structure – Metallic airframe structure .............................................................................................................................. 136 CS 23.574 Metallic damage tolerance and fatigue evaluation of commuter category aeroplanes ...................................................................................................................... 137 CS 23.575 Inspections and other procedures ................................................................ 137 SUBPART D — DESIGN AND CONSTRUCTION .............................. 138 GENERAL ........................................................................................................................ 138 CS 23.601 General .......................................................................................................... 138 CS 23.603 Materials and workmanship ......................................................................... 138 AMC 23.603 Material and workmanship Composite Aeroplane Structure (Acceptable Means of Compliance) ..................................................................................................................... 138 CS 23.605 Fabrication methods ...................................................................................... 144 CS 23.607 Fasteners ....................................................................................................... 144 AMC 23.607(b) Fasteners ..................................................................................................... 145 CS 23.609 Protection of structure .................................................................................. 145 CS 23.611 Accessibility provisions .................................................................................. 145 AMC 23.611 Accessibility provisions ................................................................................... 145 CS 23.613 Material strength properties and design values ........................................... 145 AMC 23.613 Metallic strength properties and design values.............................................. 146 CS 23.619 Special factors ............................................................................................... 146 Easy Access Rules for Normal, Utility, Aerobatic and Commuter Category Aeroplanes (CS-23) (Initial issue) Table of contents Powered by EASA eRules Page 12 of 505| Jun 2018 CS 23.621 Casting factors ............................................................................................... 147 CS 23.623 Bearing factors .............................................................................................. 148 CS 23.625 Fitting factors ................................................................................................ 148 CS 23.627 Fatigue strength............................................................................................. 148 CS 23.629 Flutter ........................................................................................................... 149 AMC 23.629 Flutter ............................................................................................................. 150 WINGS ........................................................................................................................... 151 CS 23.641 Proof of strength ........................................................................................... 151 CONTROL SURFACES ....................................................................................................... 152 CS 23.651 Proof of strength ........................................................................................... 152 CS 23.655 Installation .................................................................................................... 152 CS 23.657 Hinges ........................................................................................................... 152 CS 23.659 Mass balance ................................................................................................ 152 CONTROL SYSTEMS......................................................................................................... 153 CS 23.671 General ......................................................................................................... 153 AMC 23.671 Control systems – General............................................................................... 153 CS 23.672 Stability augmentation and automatic and power operated systems ......... 153 CS 23.673 Primary flight controls .................................................................................. 154 CS 23.675 Stops ............................................................................................................. 154 CS 23.677 Trim systems ................................................................................................. 154 CS 23.679 Control system locks ..................................................................................... 155 CS 23.681 Limit load static tests .................................................................................... 155 CS 23.683 Operation tests ............................................................................................. 155 AMC 23.683 Operation tests ............................................................................................... 156 CS 23.685 Control system details ................................................................................... 156 CS 23.687 Spring devices ............................................................................................... 157 CS 23.689 Cable systems ............................................................................................... 157 CS 23.693 Joints ............................................................................................................. 157 CS 23.697 Wing flap controls......................................................................................... 157 CS 23.699 Wing flap position indicator ......................................................................... 158 CS 23.701 Flap interconnection ..................................................................................... 158 CS 23.703 Take-off warning system .............................................................................. 158 LANDING GEAR............................................................................................................... 160 CS 23.721 General ......................................................................................................... 160 CS 23.723 Shock absorption tests ................................................................................. 160 CS 23.725 Limit drop tests ............................................................................................. 160 Easy Access Rules for Normal, Utility, Aerobatic and Commuter Category Aeroplanes (CS-23) (Initial issue) Table of contents Powered by EASA eRules Page 13 of 505| Jun 2018 CS 23.726 Ground load dynamic tests ........................................................................... 161 CS 23.727 Reserve energy absorption drop tests.......................................................... 162 CS 23.729 Landing gear extension and retraction system ............................................ 162 AMC 23.729(g) Equipment Located in the Landing Gear Bay .............................................. 163 CS 23.731 Wheels .......................................................................................................... 163 CS 23.733 Tyres ............................................................................................................. 163 CS 23.735 Brakes ........................................................................................................... 164 AMC 23.735(c) Brakes .......................................................................................................... 165 CS 23.737 Skis ................................................................................................................. 165 CS 23.745 Nose/tail-wheel steering .............................................................................. 165 FLOATS AND HULLS ........................................................................................................ 166 CS 23.751 Main float buoyancy ..................................................................................... 166 CS 23.753 Main float design .......................................................................................... 166 CS 23.755 Hulls .............................................................................................................. 166 CS 23.757 Auxiliary floats .............................................................................................. 166 PERSONNEL AND CARGO ACCOMMODATIONS ................................................................ 167 CS 23.771 Pilot compartment ........................................................................................ 167 CS 23.773 Pilot compartment view ............................................................................... 167 AMC 23.773 Pilot compartment view ................................................................................. 167 CS 23.775 Windshields and windows ............................................................................ 168 AMC 23.775(f) Windshields and windows .......................................................................... 169 AMC 23.775(g) Windshields and windows .......................................................................... 169 CS 23.777 Cockpit controls ............................................................................................ 169 CS 23.779 Motion and effect of cockpit controls .......................................................... 171 CS 23.781 Cockpit control knob shape .......................................................................... 172 CS 23.783 Doors............................................................................................................. 172 AMC 23.783(b) Doors ........................................................................................................... 174 CS 23.785 Seats, berths, litters, safety belts and shoulder harnesses .......................... 174 CS 23.787 Baggage and cargo compartments ............................................................... 175 CS 23.791 Passenger information signs ......................................................................... 176 CS 23.803 Emergency evacuation ................................................................................. 176 CS 23.805 Flight crew emergency exits ......................................................................... 176 CS 23.807 Emergency exits ............................................................................................ 177 CS 23.811 Emergency exit marking ............................................................................... 179 CS 23.812 Emergency lighting ....................................................................................... 180 CS 23.813 Emergency exit access .................................................................................. 181 CS 23.815 Width of aisle ................................................................................................ 182 Easy Access Rules for Normal, Utility, Aerobatic and Commuter Category Aeroplanes (CS-23) (Initial issue) Table of contents Powered by EASA eRules Page 14 of 505| Jun 2018 CS 23.831 Ventilation .................................................................................................... 182 PRESSURISATION ............................................................................................................ 183 CS 23.841 Pressurised cabins ........................................................................................ 183 CS 23.843 Pressurisation tests....................................................................................... 183 FIRE PROTECTION ........................................................................................................... 185 CS 23.851 Fire extinguishers .......................................................................................... 185 AMC 23.851(c) Fire extinguishers ........................................................................................ 185 CS 23.853 Passenger and crew compartment interiors ................................................ 185 CS 23.855 Cargo and baggage compartment fire protection ........................................ 187 Appendix F ........................................................................................................................... 188 Test Procedure for Self-Extinguishing Materials in accordance with CS 23.853, 23.855 and 23.1359 .................................................................................................................... 188 CS 23.859 Combustion heater fire protection............................................................... 190 CS 23.863 Flammable fluid fire protection .................................................................... 191 CS 23.865 Fire protection of flight controls, engine mounts and other flight structure ........................................................................................................................................ 192 AMC 23.865 Fire protection of flight controls, engine mounts and other flight structure .. 192 ELECTRICAL BONDING AND LIGHTNING PROTECTION ...................................................... 193 CS 23.867 Electrical bonding and protection against lightning and static electricity ... 193 MISCELLANEOUS ............................................................................................................ 194 CS 23.871 Levelling means ............................................................................................ 194 SUBPART E — POWERPLANT ...................................................... 195 GENERAL ........................................................................................................................ 195 CS 23.901 Installation .................................................................................................... 195 CS 23.903 Engines and auxiliary power units ................................................................ 195 CS 23.904 Automatic power reserve system ................................................................. 197 Appendix H – Installation of an Automatic Power Reserve (APR) System ........................... 198 H23.1 General ................................................................................................................ 198 H23.2 Terminology ........................................................................................................ 198 H23.3 Reliability and performance requirements ......................................................... 199 H23.4 Power setting ...................................................................................................... 199 H23.5 Powerplant control-general ................................................................................ 199 H23.6 Powerplant instruments ..................................................................................... 200 CS 23.905 Propellers ...................................................................................................... 203 AMC 23.905(e) Propellers .................................................................................................... 203 AMC 23.905(g) Propeller ..................................................................................................... 203 CS 23.907 Propeller vibration ........................................................................................ 203 AMC 23.907(a) Propeller vibration...................................................................................... 204 Easy Access Rules for Normal, Utility, Aerobatic and Commuter Category Aeroplanes (CS-23) (Initial issue) Table of contents Powered by EASA eRules Page 15 of 505| Jun 2018 CS 23.909 Turbo charger systems ................................................................................. 204 AMC 23.909(d)(1) Turbo charger systems........................................................................... 204 CS 23.925 Propeller clearance ....................................................................................... 205 CS 23.929 Engine installation ice protection ................................................................. 205 CS 23.933 Reversing systems......................................................................................... 205 CS 23.934 Turbojet and turbofan engine thrust reverser system tests ........................ 206 CS 23.937 Turbopropeller-drag limiting systems .......................................................... 206 CS 23.939 Powerplant operating characteristics........................................................... 207 CS 23.943 Negative acceleration ................................................................................... 207 FUEL SYSTEM.................................................................................................................. 208 CS 23.951 General ......................................................................................................... 208 CS 23.953 Fuel system independence ........................................................................... 208 CS 23.954 Fuel system lightning protection .................................................................. 208 CS 23.955 Fuel flow ....................................................................................................... 208 CS 23.957 Flow between interconnected tanks ............................................................ 210 CS 23.959 Unusable fuel supply .................................................................................... 210 AMC 23.959(a) Unusable fuel supply .................................................................................. 210 CS 23.961 Fuel system hot weather operation ............................................................. 212 AMC 23.961 Fuel system hot weather operation ............................................................... 212 CS 23.963 Fuel tanks: general........................................................................................ 214 CS 23.965 Fuel tank tests............................................................................................... 214 CS 23.967 Fuel tank installation .................................................................................... 215 CS 23.969 Fuel tank expansion space ............................................................................ 216 CS 23.971 Fuel tank sump ............................................................................................. 216 CS 23.973 Fuel tank filler connection ............................................................................ 217 CS 23.975 Fuel tank vents and carburettor vapour vents ............................................. 217 CS 23.977 Fuel tank outlet............................................................................................. 218 CS 23.979 Pressure fuelling systems ............................................................................. 218 FUEL SYSTEM COMPONENTS........................................................................................... 219 CS 23.991 Fuel pumps ................................................................................................... 219 CS 23.993 Fuel system lines and fittings ....................................................................... 219 CS 23.994 Fuel system components .............................................................................. 220 CS 23.995 Fuel valves and controls ............................................................................... 220 CS 23.997 Fuel strainer or filter ..................................................................................... 220 CS 23.999 Fuel system drains ........................................................................................ 221 CS 23.1001 Fuel jettisoning system ............................................................................... 221 Easy Access Rules for Normal, Utility, Aerobatic and Commuter Category Aeroplanes (CS-23) (Initial issue) Table of contents Powered by EASA eRules Page 16 of 505| Jun 2018 OIL SYSTEM .................................................................................................................... 223 CS 23.1011 General ....................................................................................................... 223 AMC 23.1011(b) Oil System – General ................................................................................ 223 CS 23.1013 Oil tanks ...................................................................................................... 224 CS 23.1015 Oil tank tests ............................................................................................... 224 CS 23.1017 Oil lines and fittings .................................................................................... 225 CS 23.1019 Oil strainer or filter ..................................................................................... 225 CS 23.1021 Oil system drains ........................................................................................ 225 CS 23.1023 Oil radiators ................................................................................................ 226 CS 23.1027 Propeller feathering system ....................................................................... 226 COOLING ........................................................................................................................ 227 CS 23.1041 General ........................................................................................................ 227 CS 23.1043 Cooling tests ............................................................................................... 227 CS 23.1045 Cooling test procedures for turbine engine-powered aeroplanes ............. 228 AMC 23.1045(b) Cooling test procedures for turbine engine-powered aeroplanes ........... 228 CS 23.1047 Cooling test procedures for reciprocating engine-powered aeroplanes ... 228 LIQUID COOLING ............................................................................................................ 229 CS 23.1061 Installation .................................................................................................. 229 CS 23.1063 Coolant tank tests ....................................................................................... 230 INDUCTION SYSTEM ....................................................................................................... 231 CS 23.1091 Air induction system ................................................................................... 231 CS 23.1093 Induction system icing protection .............................................................. 231 CS 23.1095 Carburettor de-icing fluid flow rate ............................................................ 233 CS 23.1097 Carburettor de-icing fluid system capacity................................................. 233 CS 23.1099 Carburettor de-icing fluid system detail design ......................................... 233 CS 23.1101 Induction air preheater design ................................................................... 233 CS 23.1103 Induction system ducts ............................................................................... 233 CS 23.1105 Induction system screens ........................................................................... 234 CS 23.1107 Induction system filters .............................................................................. 234 CS 23.1109 Turbocharger bleed air system ................................................................... 235 CS 23.1111 Turbine engine bleed air system ................................................................ 235 EXHAUST SYSTEM ........................................................................................................... 236 CS 23.1121 General ....................................................................................................... 236 CS 23.1123 Exhaust system ........................................................................................... 236 CS 23.1125 Exhaust heat exchangers ............................................................................ 236 POWERPLANT CONTROLS AND ACCESSORIES .................................................................. 238 Easy Access Rules for Normal, Utility, Aerobatic and Commuter Category Aeroplanes (CS-23) (Initial issue) Table of contents Powered by EASA eRules Page 17 of 505| Jun 2018 CS 23.1141 Powerplant controls: general ..................................................................... 238 AMC 23.1141(g)(2) Powerplant controls: general................................................................ 238 CS 23.1142 Auxiliary power unit controls ..................................................................... 238 CS 23.1143 Engine controls ........................................................................................... 239 AMC 23.1143(g) Engine controls .......................................................................................... 239 CS 23.1145 Ignition switches ......................................................................................... 239 CS 23.1147 Mixture controls ......................................................................................... 239 AMC 23.1147(b) Mixture controls........................................................................................ 240 CS 23.1149 Propeller speed and pitch controls............................................................. 240 CS 23.1153 Propeller feathering controls...................................................................... 240 CS 23.1155 Turbine engine reverse thrust and propeller pitch settings below the flight regime............................................................................................................................. 240 CS 23.1157 Carburettor air temperature controls ........................................................ 240 CS 23.1163 Powerplant accessories .............................................................................. 241 CS 23.1165 Engine ignition systems .............................................................................. 241 POWERPLANT FIRE PROTECTION..................................................................................... 243 CS 23.1181 Designated fire zones; regions included ..................................................... 243 CS 23.1182 Nacelle areas behind firewalls .................................................................... 243 AMC 23.1182 Nacelle areas behind firewalls ....................................................................... 243 CS 23.1183 Lines, fittings and components ................................................................... 243 CS 23.1189 Shut-off means ........................................................................................... 244 AMC 23.1189(a)(5) Shut-off means ..................................................................................... 244 CS 23.1191 Firewalls ...................................................................................................... 244 CS 23.1192 Engine accessory compartment diaphragm ............................................... 245 CS 23.1193 Cowling and nacelle .................................................................................... 245 CS 23.1195 Fire extinguishing systems .......................................................................... 246 CS 23.1197 Fire extinguishing agents ............................................................................ 246 CS 23.1199 Extinguishing agent containers................................................................... 247 CS 23.1201 Fire extinguishing system materials ........................................................... 247 CS 23.1203 Fire detector system ................................................................................... 247 SUBPART F — EQUIPMENT ......................................................... 249 GENERAL ........................................................................................................................ 249 CS 23.1301 Function and installation ............................................................................ 249 CS 23.1303 Flight and navigation instruments .............................................................. 249 CS 23.1305 Powerplant instruments ............................................................................. 250 CS 23.1309 Equipment, systems and installations ........................................................ 251 INSTRUMENTS: INSTALLATION ........................................................................................ 254 Easy Access Rules for Normal, Utility, Aerobatic and Commuter Category Aeroplanes (CS-23) (Initial issue) Table of contents Powered by EASA eRules Page 18 of 505| Jun 2018 CS 23.1311 Electronic display instrument systems ....................................................... 254 CS 23.1321 Arrangement and visibility.......................................................................... 255 CS 23.1322 Warning, caution and advisory lights ......................................................... 255 CS 23.1323 Airspeed indicating system ......................................................................... 256 CS 23.1325 Static pressure system ................................................................................ 256 CS 23.1326 Pitot heat indication systems ..................................................................... 257 CS 23.1327 Magnetic direction indicator ...................................................................... 258 CS 23.1329 Automatic pilot system ............................................................................... 258 CS 23.1331 Instruments using a power source ............................................................. 259 CS 23.1335 Flight director systems ............................................................................... 259 CS 23.1337 Powerplant instruments installation .......................................................... 259 ELECTRICAL SYSTEMS AND EQUIPMENT .......................................................................... 261 CS 23.1351 General ....................................................................................................... 261 AMC 23.1351(a)(2) Electrical Systems and Equipment, General.......................................... 263 AMC 23.1351(b)(5)(iv) Electrical Systems and Equipment, General .................................... 263 CS 23.1353 Storage battery design and installation...................................................... 263 CS 23.1357 Circuit protective devices ........................................................................... 264 CS 23.1359 Electrical system fire protection ................................................................. 265 CS 23.1361 Master switch arrangement ....................................................................... 265 CS 23.1365 Electric cables and equipment.................................................................... 265 CS 23.1367 Switches ...................................................................................................... 266 LIGHTS ........................................................................................................................... 267 CS 23.1381 Instrument lights ........................................................................................ 267 CS 23.1383 Taxi and landing lights ................................................................................ 267 CS 23.1385 Position light system installation ................................................................ 267 CS 23.1387 Position light system dihedral angles ......................................................... 267 CS 23.1389 Position light distribution and intensities ................................................... 268 CS 23.1391 Minimum intensities in the horizontal plane of position lights ................. 269 CS 23.1393 Minimum intensities in any vertical plane of position lights...................... 269 CS 23.1395 Maximum intensities in overlapping beams of position lights ................... 269 CS 23.1397 Colour specifications................................................................................... 270 CS 23.1399 Riding light .................................................................................................. 270 CS 23.1401 Anti-collision light system ........................................................................... 270 SAFETY EQUIPMENT ....................................................................................................... 272 CS 23.1411 General ....................................................................................................... 272 CS 23.1415 Ditching equipment .................................................................................... 272 Easy Access Rules for Normal, Utility, Aerobatic and Commuter Category Aeroplanes (CS-23) (Initial issue) Table of contents Powered by EASA eRules Page 19 of 505| Jun 2018 CS 23.1416 Pneumatic de-icer boot system .................................................................. 272 CS 23.1419 Ice protection.............................................................................................. 272 AMC 23.1419 Ice protection ................................................................................................ 273 MISCELLANEOUS EQUIPMENT ......................................................................................... 274 CS 23.1431 Electronic equipment ................................................................................. 274 AMC 23.1431(e) Electronic equipment ............................................................................... 274 CS 23.1435 Hydraulic systems ....................................................................................... 274 CS 23.1437 Accessories for twin-engine aeroplanes ..................................................... 275 CS 23.1438 Pressurisation and pneumatic systems ...................................................... 275 CS 23.1441 Oxygen equipment and supply ................................................................... 275 CS 23.1443 Minimum mass flow of supplemental oxygen ........................................... 276 CS 23.1445 Oxygen distributing system ........................................................................ 277 CS 23.1447 Equipment standards for oxygen dispensing units .................................... 277 CS 23.1449 Means for determining use of oxygen........................................................ 278 CS 23.1450 Chemical oxygen generators ...................................................................... 278 CS 23.1451 Fire protection for oxygen equipment ....................................................... 279 CS 23.1453 Protection of oxygen equipment from rupture .......................................... 279 CS 23.1457 Cockpit voice recorders .............................................................................. 279 CS 23.1459 Flight recorders ........................................................................................... 281 AMC 23.1459(b) Flight Recorders ........................................................................................ 282 CS 23.1461 Equipment containing high energy rotors .................................................. 282 SUBPART G — OPERATING LIMITATIONS AND INFORMATION .... 283 GENERAL ........................................................................................................................ 283 CS 23.1501 General ....................................................................................................... 283 CS 23.1505 Airspeed limitations .................................................................................... 283 CS 23.1507 Manoeuvring speed .................................................................................... 283 CS 23.1511 Flap extended speed................................................................................... 284 CS 23.1513 Minimum control speed ............................................................................. 284 CS 23.1519 Weight and centre of gravity ...................................................................... 284 CS 23.1521 Powerplant limitations ............................................................................... 284 CS 23.1522 Auxiliary power unit limitations .................................................................. 285 CS 23.1523 Minimum flight crew .................................................................................. 285 CS 23.1524 Maximum passenger seating configuration ............................................... 285 CS 23.1525 Kinds of operation ...................................................................................... 285 CS 23.1527 Maximum operating altitude...................................................................... 285 Easy Access Rules for Normal, Utility, Aerobatic and Commuter Category Aeroplanes (CS-23) (Initial issue) Table of contents Powered by EASA eRules Page 20 of 505| Jun 2018 CS 23.1529 Instructions for continued airworthiness ................................................... 286 Appendix G – Instructions For Continued Airworthiness ..................................................... 287 G23.1 General ................................................................................................................ 287 G23.2 Format .................................................................................................................. 287 G23.3 Content ............................................................................................................... 287 G23.4 Airworthiness Limitations section ....................................................................... 288 MARKINGS AND PLACARDS............................................................................................. 289 CS 23.1541 General ....................................................................................................... 289 CS 23.1543 Instrument markings: general .................................................................... 289 AMC 23.1543(b) Instrument Markings: General .................................................................. 289 CS 23.1545 Airspeed indicator ...................................................................................... 289 CS 23.1547 Magnetic direction indicator ...................................................................... 290 CS 23.1549 Powerplant and auxiliary power unit instruments ..................................... 290 CS 23.1551 Oil quantity indicator .................................................................................. 291 CS 23.1553 Fuel quantity indicator ............................................................................... 291 CS 23.1555 Control markings ........................................................................................ 291 AMC 23.1555(e)(2) Control markings .................................................................................. 292 CS 23.1557 Miscellaneous markings and placards ........................................................ 292 CS 23.1559 Operating limitations placard ..................................................................... 293 CS 23.1561 Safety equipment ....................................................................................... 293 CS 23.1563 Airspeed placards ....................................................................................... 293 CS 23.1567 Flight manoeuvre placard ........................................................................... 293 AEROPLANE FLIGHT MANUAL ......................................................................................... 295 CS 23.1581 General ....................................................................................................... 295 CS 23.1583 Operating limitations .................................................................................. 295 CS 23.1585 Operating procedures ................................................................................. 298 CS 23.1587 Performance information ............................................................................ 299 CS 23.1589 Loading information ................................................................................... 300 Flight Test Guide (FTG) for Certification of CS-23 Aeroplanes ...... 302 CHAPTER 1 GENERAL............................................................................................................ 302 CHAPTER 2 FLIGHT.......................................................................................................... 303 CHAPTER 3 DESIGN AND CONSTRUCTION ..................................................................... 392 CHAPTER 4 POWERPLANT .............................................................................................. 397 CHAPTER 5 EQUIPMENT ................................................................................................. 416 CHAPTER 6 OPERATING LIMITATIONS AND INFORMATION .......................................... 432 Appendices to Flight Test Guide ...................................................................................... 444 Easy Access Rules for Normal, Utility, Aerobatic and Commuter Category Aeroplanes (CS-23) (Initial issue) Table of contents Powered by EASA eRules Page 21 of 505| Jun 2018 Appendix 1 POWER AVAILABLE ........................................................................................... 444 Appendix 2 CLIMB DATA REDUCTION ................................................................................. 450 Appendix 3 STATIC MINIMUM CONTROL SPEED EXTRAPOLATION TO SEA LEVEL .............. 454 Appendix 4 CS-23 MANUALS, MARKINGS & PLACARDS CHECKLIST .................................... 457 Appendix 5 ........................................................................................................................... 467 Appendix 6 SAMPLE KINDS OF OPERATING EQUIPMENT LIST ............................................ 467 Appendix 7 USEFUL INFORMATION .................................................................................... 470 Appendix 8 CONVERSION FACTORS TABLE ......................................................................... 484 Appendix 9 AIRSPEED CALIBRATIONS ................................................................................. 487 Appendix 10 GUIDE FOR DETERMINING CLIMB PERFORMANCE AFTER STC MODIFICATIONS ............................................................................................................................................. 504 Easy Access Rules for Normal, Utility, Aerobatic and Commuter Category Aeroplanes (CS-23) (Initial issue) SUBPART A — GENERAL Powered by EASA eRules Page 22 of 505| Jun 2018 SUBPART A — GENERAL CS 23.1 Applicability ED Decision 2003/14/RM (a) This airworthiness code is applicable to – (1) Aeroplanes in the normal, utility and aerobatic categories that have a seating configuration, excluding the pilot seat(s), of nine or fewer and a maximum certificated take-off weight of 5670 kg (12 500 lb) or less; and (2) Propeller-driven twin-engined aeroplanes in the commuter category that have a seating configuration, excluding the pilot seat(s), of nineteen or fewer and a maximum certificated take-off weight of 8618 kg (19 000 lb) or less. CS 23.3 Aeroplane categories ED Decision 2003/14/RM (a) The normal category is limited to nonaerobatic operations. Non-aerobatic operations include – (1) Any manoeuvre incident to normal flying; (2) Stalls (except whip stalls); and (3) Lazy eights, chandelles and steep turns or similar manoeuvres, in which the angle of bank is not more than 60°. (b) The utility category is limited to any of the operations covered under sub-paragraph (a); plus – (1) Spins (if approved for the particular type of aeroplane); and (2) Lazy eights, chandelles, and steep turns, or similar manoeuvres in which the angle of bank is more than 60° but not more than 90°. (c) The aerobatic category is without restrictions, other than those shown to be necessary as a result of required flight tests. (d) Commuter category operation is limited to any manoeuvre incident to normal flying, stalls (except whip stalls) and steep turns in which the angle of bank is not more than 60°. (e) Except for commuter category, aeroplanes may be certificated in more than one category if the requirements of each requested category are met. Easy Access Rules for Normal, Utility, Aerobatic and Commuter Category Aeroplanes (CS-23) (Initial issue) SUBPART B — FLIGHT GENERAL Powered by EASA eRules Page 23 of 505| Jun 2018 SUBPART B — FLIGHT GENERAL CS 23.21 Proof of compliance ED Decision 2003/14/RM (a) Each requirement of this subpart must be met at each appropriate combination of weight and centre of gravity within the range of loading conditions for which certification is requested. This must be shown – (1) By tests upon an aeroplane of the type for which certification is requested, or by calculations based on, and equal in accuracy to, the results of testing; and (2) By systematic investigation of each probable combination of weight and centre of gravity, if compliance cannot be reasonably inferred from combinations investigated. (b) The following general tolerances are allowed during flight testing. However, greater tolerances may be allowed in particular tests – Item Tolerance Weight +5%, –10% Critical items affected by weight +5%, –1% C.G. ±7% total travel CS 23.23 Load distribution limits ED Decision 2003/14/RM (a) Ranges of weight and centres of gravity within which the aeroplane may be safely operated must be established and must include the range for lateral centres of gravity if possible loading conditions can result in significant variation of their positions. (b) The load distribution must not exceed – (1) The selected limits; (2) The limits at which the structure is proven; or (3) The limits at which compliance with each applicable flight requirement of this subpart is shown. CS 23.25 Weight limits ED Decision 2003/14/RM (a) Maximum weight. The maximum weight is the highest weight at which compliance with each applicable requirement of CS-23 (other than those complied with at the design landing weight) is shown. The maximum weight must be established so that it is – (1) Not more than the least of – (i) The highest weight selected by the applicant; or Easy Access Rules for Normal, Utility, Aerobatic and Commuter Category Aeroplanes (CS-23) (Initial issue) SUBPART B — FLIGHT GENERAL Powered by EASA eRules Page 24 of 505| Jun 2018 (ii) The design maximum weight, which is the highest weight at which compliance with each applicable structural loading condition of CS-23 (other than those complied with at the design landing weight) is shown; or (iii) The highest weight at which compliance with each applicable flight requirement is shown, and, (2) Not less than the weight with:- (i) Each seat occupied, assuming a weight of 77 kg (170 lbs) for each occupant for normal and commuter category aeroplanes, and 86 kg (190 lbs) for utility and acrobatic category aeroplanes, except that seats other than pilot seats may be placarded for a lesser weight; and (A) Oil at full capacity, and (B) At least enough fuel for maximum continuous power operation of at least 30 minutes for day-VFR approved aeroplanes and at least 45 minutes for night-VFR and IFR approved aeroplanes; or (ii) The required minimum crew, and fuel and oil to full tank capacity. (b) Minimum weight. The minimum weight (the lowest weight at which compliance with each applicable requirement of CS-23 is shown) must be established so that it is not more than the sum of – (1) The empty weight determined under CS 23.29; (2) The weight of the required minimum crew (assuming a weight of 77 kg (170 lb) for each crew member); and (3) The weight of – (i) For turbojet powered aeroplanes, 5% of the total fuel capacity of that particular fuel tank arrangement under investigation; and (ii) For other aeroplanes, the fuel necessary for one-half hour of operation at maximum continuous power. CS 23.29 Empty weight and corresponding centre of gravity ED Decision 2003/14/RM (a) The empty weight and corresponding centre of gravity must be determined by weighing the aeroplane with – (1) Fixed ballast; (2) Unusable fuel determined under CS 23.959; and (3) Full operating fluids, including – (i) Oil; (ii) Hydraulic fluid; and (iii) Other fluids required for normal operation of aeroplane systems, except potable water, lavatory precharge water, and water intended for injection in the engines. (b) The condition of the aeroplane at the time of determining empty weight must be one that is well defined and can be easily repeated. Easy Access Rules for Normal, Utility, Aerobatic and Commuter Category Aeroplanes (CS-23) (Initial issue) SUBPART B — FLIGHT GENERAL Powered by EASA eRules Page 25 of 505| Jun 2018 CS 23.31 Removable ballast ED Decision 2003/14/RM Removable ballast may be used in showing compliance with the flight requirements of this subpart, if – (a) The place for carrying ballast is properly designed and installed, and is marked under CS 23.1557; and (b) Instructions are included in the aeroplane flight manual, approved manual material, or markings and placards, for the proper placement of the removable ballast under each loading condition for which removable ballast is necessary. CS 23.33 Propeller speed and pitch limits ED Decision 2003/14/RM (a) General. The propeller speed and pitch must be limited to values that will assure safe operation under normal operating conditions. (b) Propellers not controllable in flight. For each propeller whose pitch cannot be controlled in flight – (1) During take-off and initial climb at the all-engine(s)-operating climb speed specified in CS 23.65, the propeller must limit the engine rpm, at full throttle or at maximum allowable take-off manifold pressure, to a speed not greater than the maximum allowable takeoff rpm; and (2) During a closed throttle glide at VNE, the propeller may not cause an engine speed above 110% of maximum continuous speed. (c) Controllable pitch propellers without constant speed controls. Each propeller that can be controlled in flight, but that does not have constant speed controls, must have a means to limit the pitch range so that – (1) The lowest possible pitch allows compliance with sub-paragraph (b)(1); and (2) The highest possible pitch allows compliance with sub-paragraph (b)(2). (d) Controllable pitch propellers with constant speed controls. Each controllable pitch propeller with constant speed controls must have – (1) With the governor in operation, a means at the governor to limit the maximum engine speed to the maximum allowable takeoff rpm; and (2) With the governor inoperative, the propeller blades at the lowest possible pitch, with take-off power, the aeroplane stationary, and no wind, either:- (i) A means to limit the maximum engine speed to 103 percent of the maximum allowable take-off r.p.m., or (ii) For an engine with an approved overspeed, means to limit the maximum engine and propeller speed to not more than the maximum approved overspeed. Easy Access Rules for Normal, Utility, Aerobatic and Commuter Category Aeroplanes (CS-23) (Initial issue) SUBPART B — FLIGHT PERFORMANCE Powered by EASA eRules Page 26 of 505| Jun 2018 PERFORMANCE CS 23.45 General ED Decision 2003/14/RM (a) Unless otherwise prescribed, the performance requirements of this subpart must be met for – (1) Still air and standard atmosphere; (2) Ambient atmospheric conditions, for commuter category aeroplanes, for reciprocating engine-powered aeroplanes of more than 2 722 kg (6 000 lb) maximum weight and for turbine engine-powered aeroplanes. (b) Performance data must be determined over not less than the following ranges of conditions – (1) Aerodrome altitude from sea-level to 3048 m (10 000 ft); and (2) For reciprocating engine-powered aeroplanes of 2 722 kg (6 000 lb) or less maximum weight, temperatures from standard to 30°C above standard; or (3) For reciprocating engine-powered aeroplanes of more than 2 722 kg (6 000 lb) maximum weight and turbine engine-powered aeroplanes, temperature from standard to 30°C above standard, or the maximum ambient atmospheric temperature at which compliance with the cooling provisions of CS 23.1041 to 23.1047 is shown, if lower. (c) Performance data must be determined with the cowl flaps or other means for controlling the engine cooling air supply in the position used in the cooling tests required by CS 23.1041 to 23.1047. (d) The available propulsive thrust must correspond to engine power, not exceeding the approved power, less – (1) Installation losses; and (2) The power absorbed by the accessories and services appropriate to the particular ambient atmospheric conditions and the particular flight condition. (e) The performance as affected by engine power must be based on a relative humidity of – (1) 80% at and below standard temperature; and (2) 34% at and above standard temperature plus 28°C (plus 50°F). Between the two temperatures listed in sub-paragraphs (e)(1) and (e)(2) the relative humidity must vary linearly. (f) Unless otherwise prescribed in determining the take-off and landing distances, changes in the aeroplane’s configuration, speed and power must be made in accordance with procedures established by the applicant for operation in service. These procedures must be able to be executed consistently by pilots of average skill in atmospheric conditions reasonably expected to be encountered in service. (g) The following, as applicable, must be determined on a smooth, dry, hard-surfaced runway – (1) Take-off distance of CS 23.53(b); (2) Accelerate-stop distance of CS 23.55; (3) Take-off distance and take-off run of CS 23.59; and (4) Landing distance of CS 23.75. Easy Access Rules for Normal, Utility, Aerobatic and Commuter Category Aeroplanes (CS-23) (Initial issue) SUBPART B — FLIGHT PERFORMANCE Powered by EASA eRules Page 27 of 505| Jun 2018 The effect on these distances of operation on other types of surface (e.g. grass, gravel) when dry, may be determined or derived and these surfaces listed in accordance with CS 23.1583(p). (h) For commuter category aeroplanes, the following also apply: (1) Unless otherwise prescribed, the take-off, en-route, approach and landing configurations for the aeroplane must be selected; (2) The aeroplane configuration may vary with weight, altitude and temperature, to the extent that they are compatible with the operating procedures required by sub- paragraph (h)(3); (3) Unless otherwise prescribed, in determining the critical-engine-inoperative take-off performance, take-off flight path and accelerate-stop distance, changes in the aeroplane’s configuration, speed and power must be made in accordance with procedures established by the applicant for operation in service. (4) Procedures for the execution of discontinued approaches and balked landings associated with the conditions prescribed in CS 23.67(c)(4) and 23.77(c) must be established; and (5) The procedures established under sub-paragraphs (h)(3) and (h)(4) must – (i) Be able to be consistently executed by a crew of average skill in atmospheric conditions reasonably expected to be encountered in service; (ii) Use methods or devices that are safe and reliable; and (iii) Include allowances for any reasonably expected time delays in the execution of the procedures. CS 23.49 Stalling speed ED Decision 2003/14/RM (a) VSO and VS1 are the stalling speeds or the minimum steady flight speed (CAS) at which the aeroplane is controllable with – (1) For reciprocating engine-powered aeroplanes, engine(s) idling, the throttle(s) closed or at not more than the power necessary for zero thrust at a speed not more than 110% of the stalling speed; and (2) For turbine engine-powered aeroplanes, the propulsive thrust may not be greater than zero at the stalling speed, or, if the resultant thrust has no appreciable effect on the stalling speed, with engine(s) idling and throttle(s) closed; (3) Propeller(s) in the take-off position; (4) The aeroplane in the condition existing in the test in which VSO and VS1 are being used; (5) Centre of gravity in the position which results in the highest value of VSO and VS1; and (6) Weight used when VSO or VS1 are being used as a factor to determine compliance with a required performance standard. (b) VSO and VS1 must be determined by flight tests using the procedure and meeting the flight characteristics specified in CS 23.201. (c) VSO at maximum weight must not exceed 113 km/h (61 knots) for – (1) Single-engined aeroplanes; and Easy Access Rules for Normal, Utility, Aerobatic and Commuter Category Aeroplanes (CS-23) (Initial issue) SUBPART B — FLIGHT PERFORMANCE Powered by EASA eRules Page 28 of 505| Jun 2018 (2) Twin-engined aeroplanes of 2 722 kg (6 000 lb) or less maximum weight that cannot meet the minimum rate of climb specified in CS 23.67(a)(1) with the critical engine inoperative. CS 23.51 Take-off speeds ED Decision 2003/14/RM (a) For normal utility and aerobatic category aeroplanes, the rotation speed VR, is the speed at which the pilot makes a control input with the intention of lifting the aeroplane out of contact with the runway or water surface. (1) For twin-engined landplanes, VR must not be less than the greater of 1·05 VMC or 1·10 VS1; (2) For single engined landplanes, VR, must not be less than VS1; and (3) For seaplanes and amphibians taking off from water, VR, must be a speed that is shown to be safe under all reasonably expected conditions, including turbulence and complete failure of the critical engine. (b) For normal utility and aerobatic category aeroplanes, the speed at 15 m (50 ft) above the take- off surface level must not be less than – (1) For twin-engined aeroplanes, the highest of – (i) A speed that is shown to be safe for continued flight (or land-back, if applicable) under all reasonably expected conditions, including turbulence and complete failure of the critical engine; or (ii) 1.10 VMC; or (iii) 1.20 VS1 (2) For single-engined aeroplanes, the higher of – (i) A speed that is shown to be safe under all reasonably expected conditions, including turbulence and complete engine failure; or (ii) 1.20 VS1. (c) For commuter category aeroplanes the following apply: (1) V1 must be established in relation to VEF as follows: (i) VEF is the calibrated airspeed at which the critical engine is assumed to fail. The VEF must be selected for the aeroplane, but must not be less than 1.05 VMC determined under CS 23.149(b) or, at the option of the applicant, not less than VMCG determined under CS 23.149(f). (ii) The take-off decision speed, V1, is the calibrated airspeed on the ground at which, as a result of engine failure or other reasons, the pilot is assumed to have made a decision to continue or discontinue the take-off. The take-off decision speed, V1, must be selected for the aeroplane but must not be less than VEF plus the speed gained with the critical engine inoperative during the time interval between the instant at which the critical engine is failed and the instant at which the pilot recognises and reacts to the engine failure, as indicated by the pilot’s application of the first retarding means during the accelerate-stop determination of CS 23.55. (2) The rotation speed, VR, in terms of calibrated airspeed, must be selected for the aeroplane and must not be less than the greatest of the following: (i) V1; or Easy Access Rules for Normal, Utility, Aerobatic and Commuter Category Aeroplanes (CS-23) (Initial issue) SUBPART B — FLIGHT PERFORMANCE Powered by EASA eRules Page 29 of 505| Jun 2018 (ii) 1.05 VMC determined under CS 23.149(b); or (iii) 1.10 VSI; or (iv) The speed that allows attaining the initial climb-out speed, V2, before reaching a height of 11 m (35 ft) above the take-off surface in accordance with CS 23.57(c)(2). (3) For any given set of conditions, such as weight, altitude, temperature and configuration, a single value of VR must be used to show compliance with both the one-engine- inoperative take-off and all-engine-operating take-off requirements. (4) The take-off safety speed, V2, in terms of calibrated airspeed, must be selected for the aeroplane so as to allow the gradient of climb required in CS 23.67(c)(1) and (c)(2) but must not be less than 1.10 VMC or less than 1.20 VSI. (5) The one-engine-inoperative take-off distance, using a normal rotation rate at a speed 9.3 km/h (5 knots) less than VR established in accordance with sub-paragraph (c)(2), must be shown not to exceed the corresponding oneengine-inoperative take-off distance determined in accordance with CS 23.57 and 23.59(a)(1) using the established VR. The take-off, otherwise performed in accordance with CS 23.57 must safely be continued from the point at which the aeroplane is 11 m (35 ft) above the take-off surface, at a speed not less than the established V2 minus 9.3 km/h (5 knots). (6) With all engines operating, marked increases in the scheduled take-off distances determined in accordance with CS 23.59(a)(2) may not result from over-rotation of the aeroplane or out-of-trim conditions. CS 23.53 Take-off performance ED Decision 2003/14/RM (a) For normal, utility and aerobatic category aeroplanes the take-off distance must be determined in accordance with sub-paragraph (b), using speeds determined in accordance with CS 23.51(a) and (b). (b) For normal, utility and aerobatic category aeroplanes the distance required to take-off and climb to a height of 15 m (50 ft) above the take-off surface must be determined for each weight, altitude and temperature within the operational limits established for take-off with – (1) Take-off power on each engine; (2) Wing flaps in the take-off position(s); and (3) Landing gear extended. (c) For commuter category aeroplanes, takeoff performance as required by CS 23.55 to CS 23.59 must be determined with the operating engines within approved operating limitations. CS 23.55 Accelerate-stop distance ED Decision 2003/14/RM For each commuter category aeroplane, the accelerate-stop distance must be determined as follows: (a) The accelerate-stop distance is the sum of the distances necessary to – (1) Accelerate the aeroplane from a standing start to VEF with all engines operating; (2) Accelerate the aeroplane from VEF to V1, assuming the critical engine fails at VEF; and (3) Come to a full stop from the point at which V1 is reached. Easy Access Rules for Normal, Utility, Aerobatic and Commuter Category Aeroplanes (CS-23) (Initial issue) SUBPART B — FLIGHT PERFORMANCE Powered by EASA eRules Page 30 of 505| Jun 2018 (b) Means other than wheel-brakes may be used to determine the accelerate-stop distances if that means – (1) Is safe and reliable; and (2) Is used so that consistent results can be expected under normal operating conditions. CS 23.57 Take-off path ED Decision 2003/14/RM For each commuter category aeroplane, the take-off path is as follows; (a) The take-off path extends from a standing start to a point in the take-off at which the aeroplane is 457 m (1 500 ft) above the take-off surface, at or below which height the transition from the take-off to the en-route configuration must be completed; and (1) The take-off path must be based on the procedures prescribed in CS 23.45; (2) The aeroplane must be accelerated on the ground to VEF at which point the critical engine must be made inoperative and remain inoperative for the rest of the take-off; and (3) After reaching VEF, the aeroplane must be accelerated to V2. (b) During the acceleration to speed V2, the nose gear may be raised off the ground at a speed not less than VR. However, landing gear retraction must not be initiated until the aeroplane is airborne. (c) During the take-off path determination, in accordance with sub-paragraphs (a) and (b) – (1) The slope of the airborne part of the take-off path must not be negative at any point; (2) The aeroplane must reach V2 before it is 11 m (35 ft) above the take-off surface and must continue at a speed as close as practical to, but not less than, V2, until it is 122 m (400 ft) above the take-off surface; (3) At each point along the take-off path, starting at the point at which the aeroplane reaches 122 m (400 ft) above the take-off surface, the available gradient of climb must not be less than 1.2%; and (4) Except for gear retraction and automatic propeller feathering, the aeroplane configuration must not be changed, and no change in power that requires action by the pilot may be made, until the aeroplane is 122 m (400 ft) above the take-off surface. (d) The take-off path to 11 m (35 ft) above the take-off surface must be determined by a continuous take-off. (e) The take-off flight path from 11 m (35 ft) above the take-off surface must be determined by synthesis from segments; and (1) The segments must be clearly defined and must be related to distinct changes in configuration, power or speed; (2) The weight of the aeroplane, the configuration and the power must be assumed constant throughout each segment and must correspond to the most critical condition prevailing in the segment; and (3) The take-off flight path must be based on the aeroplane’s performance without ground effect. Easy Access Rules for Normal, Utility, Aerobatic and Commuter Category Aeroplanes (CS-23) (Initial issue) SUBPART B — FLIGHT PERFORMANCE Powered by EASA eRules Page 31 of 505| Jun 2018 CS 23.59 Take-off distance and take-off run ED Decision 2003/14/RM For each commuter category aeroplane, the take-off distance must be determined. The determination of the take-off run is optional. (a) The take-off distance is the greater of – (1) The horizontal distance along the take-off path from the start of the take-off to the point at which the aeroplane is 11 m (35 ft) above the take-off surface, determined under CS 23.57; or (2) 115% of the horizontal distance, with all engines operating, from the start of the take-off to the point at which the aeroplane is 11 m (35 ft) above the take-off surface, determined by a procedure consistent with CS 23.57. (b) The take-off run is the greater of – (1) The horizontal distance along the take-off path from the start of the take-off to a point equidistant between the lift off point and the point at which the aeroplane is 11 m (35 ft) above the take-off surface, determined under CS 23.57; or (2) 115% of the horizontal distance, with all engines operating, from the start of the take-off to a point equidistant between the lift-off point and the point at which the aeroplane is 11 m (35 ft) above the take-off surface, determined by a procedure consistent with CS 23.57. CS 23.61 Take-off flight path ED Decision 2003/14/RM For each commuter category aeroplane, the take-off flight path must be determined as follows: (a) The take-off flight path begins 11 m (35 ft) above the take-off surface at the end of the take-off distance determined in accordance with CS 23.59. (b) The net take-off flight path data must be determined so that they represent the actual takeoff flight paths, as determined in accordance with CS 23.57 and with sub-paragraph (a), reduced at each point by a gradient of climb equal to 0.8%. (c) The prescribed reduction in climb gradient may be applied as an equivalent reduction in acceleration along that part of the take-off flight path at which the aeroplane is accelerated in level flight. CS 23.63 Climb: general ED Decision 2003/14/RM (a) Compliance with the requirements of CS 23.65, 23.66, 23.67, 23.69 and 23.77 must be shown – (1) Out of ground effect; and (2) At speeds which are not less than those at which compliance with the powerplant cooling requirements of CS 23.1041 to 23.1047 has been demonstrated. (3) Unless otherwise specified, with one engine inoperative, at a bank angle not exceeding 5 degrees. (b) For normal, utility and aerobatic category reciprocating engine-powered aeroplanes of 2 722 kg (6 000 lb) or less maximum weight, compliance must be shown with CS 23.65(a), 23.67(a), Easy Access Rules for Normal, Utility, Aerobatic and Commuter Category Aeroplanes (CS-23) (Initial issue) SUBPART B — FLIGHT PERFORMANCE Powered by EASA eRules Page 32 of 505| Jun 2018 where appropriate and CS 23.77(a) at maximum take-off or landing weight, as appropriate in a standard atmosphere. (c) For normal, utility and aerobatic category reciprocating engined aeroplanes of more than 2 722 kg (6 000 lb) maximum weight and turbine engine-powered aeroplanes in the normal, utility and aerobatic category, compliance must be shown, at weights, as a function of aerodrome altitude and ambient temperature, within the operational limits established for take-off and landing respectively, with – (1) CS 23.65(b) and 23.67(b)(1) and (2), where appropriate, for take-off; and (2) CS 23.67(b)(2), where appropriate, and CS 23.77(b), for landing. (d) For commuter category aeroplanes, compliance must be shown, at weights as a function of aerodrome altitude and ambient temperature within the operational limits established for take- off and landing respectively, with – (1) CS 23.67(c)(1), 23.67(c)(2) and 23.67(c)(3) for take-off; and (2) CS 23.67(c)(3), 23.67(c)(4) and 23.77(c) for landing. CS 23.65 Climb: all engines operating ED Decision 2003/14/RM (a) Each normal, utility and aerobatic category reciprocating engine-powered aeroplane of 2 722 kg (6 000 lb) or less maximum weight must have a steady gradient of climb at sea level of at least 8.3% for landplanes or 6.7% for seaplanes and amphibians with – (1) Not more than maximum continuous power on each engine; (2) The landing gear retracted; (3) The wing flaps in the take-off position(s); and (4) A climb speed not less than the greater of 1.1 VMC and 1.2 VS1 for twinengined aeroplanes and not less than 1.2 VS1 for single-engined aeroplanes. (b) Each normal, utility and aerobatic category reciprocating engine-powered aeroplanes of more than 2 722 kg (6 000 lb) maximum weight and turbine engine-powered aeroplanes in the normal, utility and aerobatic c