TCDS A00021CH

Page No. 1 2 3 Rev. No. 1 1 3 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A00021CH Revision 3 Cirrus Design Corporation SR10 May 21, 2025 TYPE CERTIFICATE DATA SHEET NO. A00021CH This data sheet, which is part of Type Certificate No. A00021CH, prescribes conditions and limitations under which the product for the 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 SR10 (3PCLM, Normal Category), Approved November 17, 2022 Engine One (1) ROTAX 915 iSc3 C24 Type Certificate E00051EN Fuel 100LL minimum grade aviation gasoline Engine Ratings Max. takeoff power rating (5 min.): 139 HP (104 kW) at 5,800 rpm Max. continuous power rating: 132 HP (99 kW) at 5,500 rpm Propeller and One (1) MT-Propeller Company two-blade, constant speed propeller Propeller Limits Type Certificate P16BO Model Designation MTV-21-A/195-80 Max. Continuous Power 139 HP (104 kW) Max. Continuous Speed 2279 RPM Max. Diameter 76.97 inches (195.5 cm) Min. Diameter 76.57 inches (194.5 cm) Low Pitch: 13°+/-0.2° High Pitch: 34°+/-1.0° Airspeed Limits VNE Never Exceed Speed 179 KIAS VNO Maximum Structural Cruising Speed 139 KIAS VO Operating Maneuvering 125 KIAS VFE Maximum Flap Extension Speed (50%) 115 KIAS VFE Maximum Flap Extension Speed (100%) 105 KIAS VPD Maximum Parachute Deployment Speed 138 KIAS -2- A00021CH Center of Gravity (C.G.) Range CG Envelope Weight (lb) FS (Inches) Forward Light 1477 42.71 Forward Intermediate 1900 42.71 Forward Gross 2150 44.44 Aft Gross 2150 48.77 Aft Intermediate 1900 48.77 Aft Light 1477 46.94 Empty Weight None C.G. Range Datum Firewall (at FS 0.0) Leveling Means Refer to the Airplane Maintenance Manual (40069-001) Maximum Weight Maximum Takeoff Gross Weight 2150 lb (975 kg) Minimum Crew One (1) Pilot Number of Seats 3 maximum. (2 at 41.4 inches aft of datum, 1 at 82.0 inches aft of datum) Maximum Baggage Refer to the Airplane Flight Manual (40065-001) for rear seat occupant/baggage loading. Fuel Capacity Total 35.75 US gal at 58.0 inches Usable 33.5 US gal Unusable 2.25 US gal Oil Capacity 4.2 U.S. quarts (4 L) at -18.6 inches Refer to the Airplane Flight Manual (40065-001) for approved oils. Maximum Operating 14,000 ft MSL Altitude Control Surface Aileron Up 20.7° ± 1.0° Down 14.6° ±1.0° Movements Elevator Up 22.5° ± 0.5° Down 17.5° ± 1.0° Elevator Trim Up 12.5° ± 1.0° Down 17.5° ± 2.0° Rudder Right 22.5° ± 1.0° Left 17.5° ± 1.0° Wing Flaps Up 0°± 0.5° Down 50% 15.0°± 1.0° Down 100% 32.0°± 0.5° Serial Nos. Eligible 0001 and on Type Certificate Information The original application for type certificate was dated December 14, 2020. Provisional Type Certificate A00021CH was issued on November 17, 2022 for market surveys and flight crew training. The Provisional Type Certificate was subsequently cancelled when the Type Certificate was reissued on April 4, 2023. Certification Basis 14 CFR Part 23, effective August 30, 2017, Amendment 23-64 The detailed design standards used as a means of compliance in accordance with § 23.2010 are documented in Cirrus Model SR10 Detailed Design Standard Summary, Report No. E00004974. Special Conditions in accordance with 14 CFR Part 11: None. -3- A00021CH Equivalent Level of Safety Findings in accordance with 14 CFR Part 21: None. Exemptions from 14 CFR Part 23 in accordance with 14 CFR Part 11: None. Additional Design Requirements and Conditions. At this time, no additional design requirements have been identified. Operational Restrictions: Not approved for flight into known icing. Acrobatic maneuvers and spins are prohibited. § 23.2005 Certification Level and Performance Level: Level 2, Low Speed Environmental Standards Noise Standards: 14 CFR Part 36 effective December 1, 1969 as amended by Amendments 36-1 through 36-31 Design Data The SR10 is defined by Cirrus document E00002352, SR10 Master Drawing List Production Basis TC Holder: Cirrus Design Corporation headquartered in Duluth, Minnesota. Production Certificate 338CE issued June 12, 2000. Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (See Certification Basis) must be installed in the aircraft for certification. In addition to the above required equipment, the following equipment are also required: 1. The latest revision of the “FAA APPROVED AIRPLANE FLIGHT MANUAL”, Document No. 40065-001 for aircraft serials 0001 and subsequent. Note 1. A current weight and balance report, including list of equipment included in the certificated empty weight and loading instructions when necessary, must be provided for each aircraft at the time of original certification. Note 2. All placards required by either the FAA-approved Airplane Flight Manual, the applicable operating rules, or the certification basis must be installed as specified. Note 3. The Instructions for Continued Airworthiness are found in 40069-001, 44046-001, 40071-001, and 40072-001. The Airworthiness Limitations are found in 40069-001, Section 4. -- END --