TCDS A00009CH

Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 Rev. No. 24 22 22 22 19 21 19 17 22 25 25 25 24 25 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A00009CH Revision 25 Cirrus Design Corportation SR20 SR22 SR22T December 26, 2025 TYPE CERTIFICATE DATA SHEET NO. A00009CH This data sheet, which is part of Type Certificate No. A00009CH, prescribes conditions and limitations under which the product for the which type certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. Type Certificate Holder: Cirrus Design Corporation 4515 Taylor Circle Duluth, MN 55811 I - MODEL SR20, (NORMAL CATEGORY), APPROVED OCTOBER 23, 1998 Engine 1. One (1) Continental Motors, Inc. IO-360-ES engine, Type Certificate Data Sheet (TCDS) E1CE 2. One (1) Lycoming Engines IO-390-C3B6 engine, Type Certificate Data Sheet (TCDS) E00006NY Fuel 100/100LL minimum grade aviation gasoline Engine Limits Continental Motors, Inc. IO-360-ES Maximum Take-off 2700 RPM (200 hp) Maximum Continuous Power 2700 RPM (200 hp) Lycoming Engines IO-390-C3B6 Maximum Take-off 2700 RPM (215 hp) Maximum Continuous Power 2700 RPM (215 hp) Propeller and 1. Hartzell Propeller Inc. P/N BHC-J2YF-1BF/F7694 (See Note 8) Propeller limits TCDS P37EA Maximum Diameter: 76 inches Minimum Diameter: 73 inches Number of Blades: 2 Low Pitch: 14.6°+/-0.5° High Pitch: 35.0°+/-1.0° High Pitch: 35.0°+/-1.0° Not to be operated above 24 inches of manifold pressure between 1900 and 2200 RPM. Spinner: Hartzell P/N A-2295(P) NOTE: Spinner may be painted or polished. 2. Hartzell Propeller Inc. P/N PHC-J3YF-1MF/F7392-1 (See Note 8) TCDS P36EA Maximum Diameter: 74 inches Minimum Diameter: 72 inches Number of Blades: 3 Low Pitch: 14.1°+/-0.5° High Pitch: 35.0°+/-1.0° No operating limitations to 2800 RPM Spinner: Hartzell P/N A-2295-1P 3. Hartzell Propeller Inc. P/N PHC-J3YF-1RF/F7392-1 (See Note 8) TCDS P36EA Maximum Diameter: 74 inches Minimum Diameter: 72 inches Number of Blades: 3 Low Pitch: 13.9°+/-0.5° High Pitch: 35.0°+/-1.0° No operating limitations to 2800 RPM Spinner: Hartzell P/N A-2295-1(P) NOTE: Spinner may be painted or polished. Page 2 of 14 A00009CH 4. Hartzell Propeller Inc. P/N HC-E3YR-1RF/F7392S-1 (See Note 9) TCDS P33EA Maximum Diameter: 74 inches Minimum Diameter: 73 inches Number of Blades: 3 Low Pitch: 13.4°+/-0.5° High Pitch: 30.0°+/-1.0° No operating limitations to 2850 RPM Spinner: Hartzell P/N A-2295-1(P) NOTE: Spinner may be painted or polished. 5. Hartzell Propeller Inc. P/N 3C1-R919A1/76C03-2 (See Note 9) TCDS P00016CH Maximum Diameter: 74 inches Minimum Diameter: 74 inches Number of Blades: 3 Low Pitch: 11.9°+/-0.5° High Pitch: 30.0°+/-1.0° No operating limitations to 2700 RPM Spinner: Hartzell P/N 105890 NOTE: Spinner may be painted or polished. Airspeed Limits S/N 1005 thru 1147: Vne Never Exceed Speed 200 KIAS Vno Maximum Structural Cruising Speed 165 KIAS Vo (2900 lbs) Operating Maneuvering Speed 135 KIAS Vo (2600 lbs) Operating Maneuvering Speed 126 KIAS Vo (2200 lbs) Operating Maneuvering Speed 116 KIAS Vfe Maximum Flap Extension Speed 100 KIAS Vpd Maximum Parachute Deployment Speed 135 KIAS S/N 1148 thru 1877, 1879 thru 1885, and S/N 1005 thru 1147 if Cirrus Service Bulletin SB 20-01-00 is complied with: Vne Never Exceed Speed 200 KIAS Vno Maximum Structural Cruising Speed 165 KIAS Vo (3000 lbs) Operating Maneuvering 131 KIAS Vo (2600 lbs) Operating Maneuvering 122 KIAS Vo (2300 lbs) Operating Maneuvering 114 KIAS Vfe Maximum Flap Extension Speed 100 KIAS Vpd Maximum Parachute Deployment Speed 135 KIAS S/N 1878, 1886 thru 2219, and S/N 2221 thru 2338 (See Note 8): Vne Never Exceed Speed 200 KIAS Vno Maximum Structural Cruising Speed 163 KIAS Vo (3050 lbs) Operating Maneuvering 130 KIAS Vfe Maximum Flap Extension Speed (50%) 119 KIAS Vfe Maximum Flap Extension Speed (100%) 104 KIAS Vpd Maximum Parachute Deployment Speed 133 KIAS S/N 2220, 2339 and subsequent (See Note 9): Vne Never Exceed Speed 201 KIAS Vno Maximum Structural Cruising Speed 164 KIAS Vo (3150 lbs) Operating Maneuvering 133 KIAS Vfe Maximum Flap Extension Speed (50%) 150 KIAS Vfe Maximum Flap Extension Speed (100%) 110 KIAS Vpd Maximum Parachute Deployment Speed 133 KIAS C.G. Range S/N 1005 thru 1147: Forward Limits: 138.7 inches at 2110 lbs with a straight line taper to 141.0 inches at 2694 lbs, and 143.0 inches at 2900 lbs. Aft Limits: 144.6 inches at 2110 lbs, with straight line taper to 147.4 inches at 2570 lbs, and to 147.9 inches at 2745 lbs, and 148.2 inches at 2900 lbs. Page 3 of 14 A00009CH S/N 1148 thru 1877, 1879 thru 1885, and S/N 1005 thru 1147 if Cirrus Service Bulletin SB 20-01-00 is complied with: Forward Limits: 138.7 inches at 2110 lbs with a straight line taper to 141.0 inches at 2694 lbs, and 144.1 inches at 3000 lbs. Aft Limits: 144.6 inches at 2110 lbs, with straight line taper to 147.4 inches at 2570 lbs, and to 148.1 inches at 2900 lbs, and 148.0 inches at 3000 lbs. S/N 1878, 1886 thru 2219, and S/N 2221 thru 2338 (See Note 8): Forward Limits: 137.8 inches at 2100 lbs with a straight line taper to 139.1 inches at 2700 lbs, and to 140.7 inches at 3050 lbs Aft Limits: 148.1 inches at 2100 lbs, with straight line to 148.1 inches at 3050 lbs. S/N 2220, 2339 and subsequent (See Note 9): Forward Limits: 137.8 inches at 2100 lbs with a straight line taper to 139.1 inches at 2700 lbs, and to 141.1 inches at 3150 lbs Aft Limits: 148.1 inches at 2100 lbs, with straight line to 148.1 inches at 3150 lbs. Empty Weight C.G. Range None Maximum Weights S/N 1005 thru 1147: Takeoff and Landing: 2900 lbs. S/N 1148 thru 1877, 1879 thru 1885, and S/N 1005 thru 1147 if Cirrus Service Bulletin SB 20-01-00 is complied with: Takeoff: 3000 lbs. Landing: 2900 lbs. Zero Fuel: 2900 lbs. S/N 1878, 1886 thru 2219, and S/N 2221 thru 2338 (See Note 8): Takeoff and Landing: 3050 lbs. S/N 2220, 2339 and subsequent (See Note 9): Takeoff and Landing: 3150 lbs. Minimum Crew One (1) Pilot Number of Seats S/N 1005 thru 2126: 4 (2 at 143.5 inches aft of datum, 2 at 180 inches aft of datum) S/N 2127 thru 2219, and S/N 2221 thru 2338: 4+1 (2 at 143.5 inches aft of datum, 2+1 at 180 inches aft of datum) S/N 2220, 2339 and subsequent: 4+1 (2 at 143.5 inches aft of datum, 2+1 at 180 inches aft of datum) 3 (2 at 143.5 inches aft of datum, 1 at 180 inches aft of datum) 2 (2 at 143.5 inches aft of datum) Maximum Baggage: 130 Lbs. at 208 inches Fuel Capacity Total: S/N 1005 thru 1877, 1879 thru 1885: 60.5 gal at 153.75 inches Usable: 56 gal (See Note 1) S/N 1878, 1886 and subsequent: 58.5 gal at 154.9 inches Usable: 56 gal (See Note 1) Page 4 of 14 A00009CH Oil Capacity S/N 1005 thru 2219, and S/N 2221 thru 2338 (See Note 8): 8 quarts at 76.2 inches S/N 2220, 2339 and subsequent (See Note 9): 7 quarts at 80.5 inches Maximum Operating Altitude The aircraft is limited to 17,500 ft MSL. Control Surface Movements Wing Flaps: Up 0°± 0.5° Down 50% 16°± 0.5° Down 100% 32°± 0.5° Aileron: Up 12.5° ± 1.0° Down 12.5° ±1.0° Elevator: Up 25.0° +0°/-1.0° Down 15° ± 1.0° Elevator Trim: Up 17.0° Minimum Down 10.5° ± 1.0° Rudder: Right 20.0° ± 1.0° Left 20.0° ± 1.0° Additional Limitations: Airframe life limit: 12,000 flight hours Design Data: The airplane shall be manufactured in accordance with the latest FAA approved revision of “Master Drawing List”, Document No. 13750, or other FAA approved data. NOTE: Document No. 12609 is the predecessor document to Document No. 13750. Serial Nos. Eligible 1005 and on II - MODEL SR22, NORMAL CATEGORY, APPROVED NOVEMBER 30, 2000 Engine One (1) Continental Motors, Inc. IO-550-N engine, Type Certificate Data Sheet E3SO Fuel 100/100LL minimum grade aviation gasoline Engine Limits Maximum Take-off 2700 RPM (310 hp) Maximum Continuous Power 2700 RPM (310 hp) Propeller and Propeller limits 1. Hartzell Propeller Inc. P/N PHC-J3YF-1RF/F7694 or F7694B TCDS P36EA Hartzell Maximum Diameter: 78 inches Minimum Diameter: 76 inches Number of Blades: 3 Low Pitch: 14.1°+/-0.5° High Pitch: 35.0°+/-1.0° No operating limitations to 2700 RPM Spinner: Hartzell P/N A-2295-1(P) NOTE: Spinner may be painted or polished. 2. McCauley Propeller Systems P/N D3A34C443/78CYA-0 TCDS P47GL McCauley Maximum Diameter: 78 inches Minimum Diameter: 76 inches Number of Blades: 3 Low Pitch: 11.8°+/-0.5° at 30” station High Pitch: 31.5° at 30” station No operating limitations to 2700 RPM Spinner: McCauley D-7779-1 (Polished) or D-7779-2 (Satin) Page 5 of 14 A00009CH 3. Hartzell Propeller Inc. P/N PHC-J3YF-1RF/F7693DF or F7693DFB TCDS P36EA Hartzell Maximum Diameter: 78 inches Minimum Diameter: 76 inches Number of Blades: 3 Low Pitch: 13.9°+/-0.5° High Pitch: 40.0°+/-1.0° No operating limitations to 2700 RPM Spinner: Hartzell P/N A-2295-1(P) NOTE: Spinner may be painted or polished. 4. Hartzell Propeller Inc. P/N PHC-J3YF-1N/N7605 or N7605B TCDS P36EA Hartzell Maximum Diameter: 78 inches Minimum Diameter: 78 inches Number of Blades: 3 Low Pitch: 12.2°+/-0.5° High Pitch: 35.0°+/-1.0° No operating limitations to 2700 RPM Spinner: Hartzell P/N A-2295-11(P) NOTE: Spinner may be painted or polished. 5. Hartzell Propeller Inc. P/N PHC-J3Y1F-1N/N7605, N7605B, N7605C or N7605CB TCDS P36EA Hartzell Maximum Diameter: 78 inches Minimum Diameter: 78 inches Number of Blades: 3 Low Pitch: 12.2°+/-0.5° High Pitch: 35.0°+/-1.0° No operating limitations to 2700 RPM when using type design throttle-propeller controls Spinner: Hartzell P/N 102870() or A-2295-11() NOTE: () indicates various finish options. 6. MT-Propeller Entwicklung GmbH P/N MTV-9-D/198-52 TCDS P24NE MT-Propeller Maximum Diameter: 78 inches Minimum Diameter: 76 inches Number of Blades: 3 Low Pitch: 12.5°+/-0.2° High Pitch: 38.0°+/-1.0° No operating limitations to 2700 RPM Spinner: MT-Propeller P/N P-187 NOTE: Spinner may be painted or polished. Airspeed Limits S/N 0002 thru 3914: Vne Never Exceed Speed 204 KIAS Vno Maximum Structural Cruising Speed 180 KIAS Vo (3400 lbs) Operating Maneuvering 133 KIAS Vo (2900 lbs) Operating Maneuvering 124 KIAS Vo (2400 lbs) Operating Maneuvering 112 KIAS Vfe Maximum Flap Extension Speed (50%) 119 KIAS Vfe Maximum Flap Extension Speed (100%) 104 KIAS Vpd Maximum Parachute Deployment Speed 133 KIAS S/N 3915 and subsequent: Vne Never Exceed Speed 208 KIAS Vno Maximum Structural Cruising Speed 179 KIAS Vo (3600 lbs) Operating Maneuvering 140 KIAS Vo (3400 lbs) Operating Maneuvering 133 KIAS Vo (2900 lbs) Operating Maneuvering 124 KIAS Vo (2400 lbs) Operating Maneuvering 112 KIAS Vfe Maximum Flap Extension Speed (50%) 150 KIAS Vfe Maximum Flap Extension Speed (100%) 110 KIAS Vpd Maximum Parachute Deployment Speed 140 KIAS C.G. Range S/N 0002 thru 3914: Forward: 137.8 inches at 2100 lbs with a straight line taper to 139.1 inches at 2700 lbs, and to 142.3 inches at 3400 lbs. (See Note 6) Aft:148.1 inches at 2100 lbs, with straight line to 148.1 inches at 3400 lbs. Page 6 of 14 A00009CH S/N 3915 and subsequent: Forward: 137.8 inches at 2100 lbs with a straight line taper to 139.1 inches at 2700 lbs, and to 143.2 inches at 3600 lbs. Aft:148.1 inches at 2100 lbs, with straight line to 148.1 inches at 3600 lbs Empty Weight C.G. Range None Maximum Weights S/N 0002 thru 3914: 3400 lbs S/N 3915 and subsequent: Takeoff and Landing: 3600 lbs Zero Fuel: 3400 lbs Minimum Crew One (1) Pilot Number of Seats S/N 0002 thru 3827: 4 (2 at 143.5 inches aft of datum, 2 at 180 inches aft of datum) S/N 3828 and subsequent: 4+1 (2 at 143.5 inches aft of datum, 2+1 at 180 inches aft of datum) Maximum Baggage 130 Lbs. at 208 inches Fuel Capacity Total: S/N 0002 thru 2333, 2335 thru 2419, and 2421 thru 2437: 84 gallon at 154.9 inches Usable: 81 gallon (See Note 1) S/N 2334, 2420, 2438 and subsequent: 94.5 gallon at 154.9 inches Usable: 92.0 gallon (See Note 1) Oil Capacity 8 quarts at 77.1 inches Maximum Operating Altitude The aircraft is limited to 17,500 ft MSL. Control Surface Movements S/N 0002 thru 3914: Wing Flaps: Up 0°±0.5° Down 50% 16° ± 0.5° Down 100% 32° ±0.5° Aileron: Up 12.5° ± 1.0° Down 12.5° ± 1.0° Elevator: Up 25.0° +0°/-1.0° Down 15° ± 1.0° Elevator Trim: Up 17.0° Minimum Down 10.5° ± 1.0° Rudder: Right 20.0° ± 1.0° Left 20.0° ± 1.0° S/N 3915 and subsequent: Wing Flaps: Up 0°±0.5° Down 50% 16° ± 0.5° Down 100% 35.5° ±0.5° Aileron: Up 12.5° ± 1.0° Down 12.5° ± 1.0° Elevator: Up 25.0° +0°/-1.0° Down 15° ± 1.0° Elevator Trim: Up 17.0° Minimum Down 10.5° ± 1.0° Rudder: Right 20.0° ± 1.0° Left 20.0° ± 1.0° Additional Limitations: Airframe life limit: 12,000 flight hours Design Data: The airplane shall be manufactured in accordance with the latest FAA approved revision of “Master Drawing List”, Document No. 13750, or other FAA approved data. Serial Nos. Eligible Eligible 0001 and on. Page 7 of 14 A00009CH III - MODEL SR22T, NORMAL CATEGORY, APPROVED FEBRUARY 10, 2010 Engine One (1) Continental Motors, Inc. TSIO-550-K engine, Type Certificate Data Sheet E5SO Fuel 100/100LL minimum grade aviation gasoline Engine Limits Maximum Take-off 2500 RPM (315 hp) Maximum Continuous Power 2500 RPM (315 hp) Propeller and Propeller limits Hartzell Propeller Inc. P/N PHC-J3Y1F-1N/N7605, N7605B, N7605C or N7605CB TCDS P36EA Hartzell Maximum Diameter: 78 inches Minimum Diameter: 78 inches Number of Blades: 3 Low Pitch: 12.2°+/-0.5° High Pitch: 35.0°+/-1.0° No operating limitations to 2700 RPM Spinner: Hartzell P/N 102870() or A-2295-11() NOTE: () indicates various finish options. Airspeed Limits S/N 0001 thru 0441: Vne Never Exceed Speed 204 KCAS from S/L to 17,500 ft MSL linearly reducing from 204 KCAS @ 17,500 ft to 173 KCAS @ 25,000 ft Vno Maximum Structural Cruising Speed 180 KCAS from S/L to 17,500 ft MSL linearly reducing from 180 KCAS @ 17,500 ft to 153 KCAS @ 25,000 ft Vo (3400 lbs) Operating Maneuvering 133 KIAS Vo (2900 lbs) Operating Maneuvering 124 KIAS Vo (2400 lbs) Operating Maneuvering 112 KIAS Vfe Maximum Flap Extension Speed (50%) 119 KIAS Vfe Maximum Flap Extension Speed (100%) 104 KIAS Vpd Maximum Parachute Deployment Speed 133 KIAS S/N 0442 and subsequent: Vne Never Exceed Speed 208 KCAS from S/L to 17,500 ft MSL linearly reducing from 208 KCAS @ 17,500 ft to 178 KCAS @ 25,000 ft Vno Maximum Structural Cruising Speed 179 KCAS from S/L to 17,500 ft MSL linearly reducing from 179 KCAS @ 17,500 ft to 152 KCAS @ 25,000 ft Vo (3600 lbs) Operating Maneuvering 140 KIAS Vo (3400 lbs) Operating Maneuvering 133 KIAS Vo (2900 lbs) Operating Maneuvering 124 KIAS Vo (2400 lbs) Operating Maneuvering 112 KIAS Vfe Maximum Flap Extension Speed (50%) 150 KIAS Vfe Maximum Flap Extension Speed (100%) 110 KIAS Vpd Maximum Parachute Deployment Speed 140 KIAS C.G. Range S/N 0001 thru 0441: Forward: 137.8 inches at 2100 lbs with a straight line taper to 139.1 inches at 2700 lbs, and to 142.3 inches at 3400 lbs. (See Note 6) Aft:148.1 inches at 2100 lbs, with straight line to 148.1 inches at 3400 lbs. S/N 0442 and subsequent: Forward: 137.8 inches at 2100 lbs with a straight line taper to 139.1 inches at 2700 lbs, and to 143.2 inches at 3600 lbs. Aft:148.1 inches at 2100 lbs, with straight line to 148.1 inches at 3600 lbs Empty Weight C.G. Range None Maximum Weights S/N 0001 thru 0441: 3400 lbs Page 8 of 14 A00009CH S/N 0442 and subsequent: Takeoff and Landing: 3600 lbs Zero Fuel: 3400 lbs Minimum Crew One (1) Pilot Number of Seats S/N 0001 thru 0250, and 0252 thru 0267: 4 (2 at 143.5 inches aft of datum, 2 at 180 inches aft of datum) S/N 0251, 0268 and subsequent: 4+1 (2 at 143.5 inches aft of datum, 2+1 at 180 inches aft of datum) Maximum Baggage 130 Lbs. at 208 inches Fuel Capacity Total: 94.5 gallon at 154.9 inches Usable: 92.0 gallon (See Note 1) Oil Capacity 8 quarts at 77.1 inches Maximum Operating Altitude The aircraft is limited to 25,000 ft MSL. Control Surface Movements S/N 0001 thru 0441: Wing Flaps: Up 0°±0.5° Down 50% 16° ± 0.5° Down 100% 32° ±0.5° Aileron: Up 12.5° ± 1.0° Down 12.5° ± 1.0° Elevator: Up 25.0° +0°/-1.0° Down 15° ± 1.0° Elevator Trim: Up 17.0° Minimum Down 10.5° ± 1.0° Rudder: Right 20.0° ± 1.0° Left 20.0° ± 1.0° S/N 0442 and subsequent: Wing Flaps: Up 0°±0.5° Down 50% 16° ± 0.5° Down 100% 35.5° ±0.5° Aileron: Up 12.5° ± 1.0° Down 12.5° ± 1.0° Elevator: Up 25.0° +0°/-1.0° Down 15° ± 1.0° Elevator Trim: Up 17.0° Minimum Down 10.5° ± 1.0° Rudder: Right 20.0° ± 1.0° Left 20.0° ± 1.0° Additional Limitations: Airframe life limit: 12,000 flight hours Design Data: The airplane shall be manufactured in accordance with the latest FAA approved revision of “Master Drawing List”, Document No. 13750, or other FAA approved data. Serial Nos. Eligible Eligible 0001 and on Page 9 of 14 A00009CH DATA PERTINENT TO ALL MODELS Reference Datum 100 inches in front of the forward face of firewall bulkhead Leveling Means Door sill and leveling points as defined in AFM Certification Basis Model SR20: 14 CFR Part 23 of the Federal Aviation Regulations effective February 1, 1965, as amended by 23-1 thru 23-47, except as follows: 14 CFR 23.573, 23.575, 23.611, 23.657, 23.673 thru Amendment 23-48; 14 CFR 23.783, 23.785, 23.867, 23.1303, 23.1307, 23.1309, 23.1311, 23.1321, 23.1323, 23.1329, 23.1361, 23.1383, 23.1401, 23.1431, 23.1435 thru Amendment 23-49; 14 CFR 23.3, 23.25, 23.143, 23.145, 23.155, 23.1325, 23.1521, 23.1543, 23.1555, 23.1559, 23.1567, 23.1583, 23.1585, 23.1589 thru Amendment 23-50; 14 CFR 23.777, 23.779, 23.901, 23.907, 23.955, 23.959, 23.963, 23.965, 23.973, 23.975, 23.1041, 23.1091, 23.1093, 23.1107, 23.1121, 23.1141, 23.1143, 23.1181, 23.1191, 23.1337 thru Amendment 23-51; 14 CFR 23.1305 thru Amendment 23-52 14 CFR Part 36 dated December 1, 1969 as amended by 36-1 thru 36-21. In addition to the certification basis stated above, for SR20 S/N 1423 thru 1877 and SR20 serials 1879 and subsequent the certification basis is amended to include the following regulations at the amendment levels stated for the SR20 Fuselage Redesign (G2 marketing designation): 14 CFR 23.561, 23.607, 23.629 thru Amendment 23-48. 14 CFR 23.853 thru Amendment 23-49. 14 CFR 23.161, 23.177, 23.201, 23.203, 23.233, 23.1581 thru Amendment 23-50. 14 CFR 23.925, 23.1043, 23.1047, 23.1183 thru Amendment 23-51. 14 CFR 23.901 thru Amendment 23-53. In addition to the certification basis stated in the paragraphs above, for SR20 S/N 1878, 1886 and subsequent the certification basis is amended to include the following regulations at the amendment levels stated for SR20 Wing Redesign (G3 marketing designation): 14 CFR 23.473, 23.499, 23.725, 23.865 thru Amendment 23-48. 14 CFR 23.677, 23.723, 23.735, 23.1351, 23.1353, 23.1359, 23.1365 thru 23-49. 14 CFR 23.45, 23.49, 23.51, 23.53, 23.63, 23.71, 23.75, 23.77, 23.147, 23.157, 23.175, 23.1511, 23.1553, 23.1563 thru Amendment 23-50. For aircraft equipped with Garmin G1000 avionics or Garmin G1000 avionics with Garmin GFC-700 autopilot system, the certification basis, for installation specific items only, is amended to include the following regulation at the amendment level stated: (Effective S/N 2016 thru S/N 2219 and S/N 2221 thru 2338): 14 CFR 23.1308 thru Amendment 23-57. For aircraft equipped with Garmin G1000 NXi avionics or Garmin G1000 NXi avionics with Garmin GFC-700 autopilot system, the certification basis, for installation specific items only, is amended to include the following regulation at the amendment level stated (Effective S/N 2220, 2339 and subsequent): 14 CFR 23.207 thru Amendment 23-50. 14 CFR 23.1308 thru Amendment 23-57. 14 CFR 23.1306 thru Amendment 23-61 For aircraft equipped with Lycoming Engines IO-390-C3B6 the certification basis is amended to include the following regulations at the amendment levels stated (Effective S/N 2220, 2339 and subsequent): 14 CFR 23.572 thru Amendment 23-48. 14 CFR 23.697, 23.701, 23.787, 23.865, thru Amendment 23-49. 14 CFR 23.33, 23.65, 23.69, 23.73, 23.153, 23.207, 23.235, 23.562, 23.1545, 23.1587 thru Amendment 23-50. 14 CFR 23.925, 23.1043, 23.1047, 23.1183 thru Amendment 51. 14 CFR 23.903 thru Amendment 23-54. Page 10 of 14 A00009CH 14 CFR 23.905, 23.907 thru Amendment 23-59. 14 CFR 23.1308 thru Amendment 23-57. 14 CFR 23.1306 thru Amendment 23-61. 14 CFR 36 dated December 1, 1969 as amended by 36-1 thru 36-30. The aircraft certification basis is amended to include the following regulation at the amendment level stated (Effective S/N 2650 and subsequent): (Note: The amended certification basis allows for the optional removal of the wet compass.) 14 CFR 23.1303 thru Amendment 23-62 The aircraft certification basis is amended (effective S/N 9750 and subsequent) to include only : 14 CFR 23.2610 (a)(c) thru Amendment 23-64 effective S/N 9750 and subsequent 14 CFR 23.853, 23.1311 and 23.1555 thru Amendment 23-62 effective S/N 9750 and subsequent For aircraft with a Lithium-ion Battery 14 CFR 23.2505, 23.2510 (a)(b)(c), 23.2525 (a)(b)(c), Amendment 23-64 with MOC per Issue Paper included with cert project. For aircraft equipped with A337 Halotron BrX fire extinguisher, the aircraft certification basis, for installation specific items only, is amended to include the following regulation at the amendment levels stated: (Effective S/N 11118 and subsequent): 23.2325(f) (23-64); Model SR22: 14 CFR Part 23 of the Federal Aviation Regulations effective February 1, 1965, as amended by 23-1 thru 23-53, except as follows: 14 CFR 23.301 thru Amendment 23-42 14 CFR 23.855, 23.1326, 23.1359, not applicable 14 CFR Part 36 dated December 1, 1969, as amended by 36-1 thru 36-22 For aircraft equipped with Garmin G1000 avionics or Garmin G1000 avionics with Garmin GFC-700 autopilot system, the certification basis, for installation specific items only, is amended to include the following regulation at the amendment level stated: (Effective S/N 2979, 2992, 3002 and subsequent): 14 CFR 23.1308 thru Amendment 23-57. For aircraft equipped with Garmin G1000 NXi avionics or Garmin G1000 NXi avionics with the Garmin GFC-700 autopilot system, the certification basis, for installation specific items only, is amended to include the following regulation at the amendment level stated: (Effective S/N 4433 and subsequent): 14 CFR 23.1308 thru Amendment 23-57. 14 CFR 23.1306 thru Amendment 23-61. For aircraft equipped for optional Flight Into Known Icing operation, the certification basis, for installation specific items only, is amended to include the following regulation at the amendment level stated: (Effective S/N 3003, 3310, 3326, 3403 and subsequent), 14 CFR 23.1326, 23.1359 thru Amendment 23-49. 14 CFR 23.1308 thru Amendment 23-57. For aircraft with 3600 lb max takeoff and landing weight limitation, the certification basis, for installation specific items only, is amended to include the following regulation at the amendment level stated: (Effective S/N 3915 and subsequent): 14 CFR 23.1308 thru Amendment 23-57. Page 11 of 14 A00009CH 14 CFR Part 36 thru Amendment 36-28. For aircraft equipped with Special Missions provisions (ref. AFM supplement 13772-157), the certification basis, for installation specific items only, is amended to include the following regulation at the amendment level stated: 14 CFR Part 36 thru Amendment 36-30. The aircraft certification basis is amended to include the following regulation at the amendment level stated (Effective S/N 4993 and subsequent): (Note: The amended certification basis allows for the optional removal of the wet compass.) 14 CFR 23.1303 thru Amendment 23-62 The aircraft certification basis is amended (effective S/N 9750 and subsequent) to include only : 14 CFR 23.2610 (a)(c) thru Amendment 23-64 effective S/N 9750 and subsequent 14 CFR 23.853, 23.1311 and 23.1555 thru Amendment 23-62 effective S/N 9750 and subsequent For aircraft with a Lithium-ion Battery 14 CFR 23.2505, 23.2510 (a)(b)(c), 23.2525 (a)(b)(c),