TCDS A00018CH

Page No. 1 2 3 4 5 Rev. No. 5 4 7 5 7 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A00018CH Revision 7 Cirrus Design Corporation SF50 December 26, 2025 TYPE CERTIFICATE DATA SHEET NO. A00018CH This data sheet, which is part of Type Certificate No. A00018CH, 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 SF50 (7PCLM, Normal Category), Approved October 28, 2016 Engine One (1) Williams International FJ33-5A turbofan engine Type Certificate E3GL Fuel Jet A, Jet A-1 or JP-8 Engine Limits Thrust Setting Thrust (lb) ITT °C N1 rpm (%) N2 rpm (%) Takeoff 1846 877 (10 sec.) 862 (5 min) 23,566 (104.7%) 23,791 (105.7%) for 30 sec. 51,703 (100.4%) 51,844 (100.7%) for 30 sec. Max Continuous 1846 836 Airspeed Limits VMO Maximum Operating Speed 250 KIAS MMO Maximum Operating Mach Number See Note 4 VO Operating Maneuvering Speed 150 KIAS VFE_50% Maximum Flap Extend Speed (50% flaps) 190 KIAS VFE_100% Maximum Flap Extend Speed (100% flaps) 150 KIAS VLE Maximum Landing Gear Extended Speed 210 KIAS VLO_Extend Maximum Landing Gear Extension Speed 210 KIAS VLO_Retract Maximum Landing Gear Retract Speed 150 KIAS Maximum Weight Maximum Ramp Weight 6040 lb Maximum Takeoff Gross Weight 6000 lb Maximum Landing Weight 5550 lb Maximum Zero Fuel Weight 4900 lb Maximum Baggage Aft Compartment 300 lb Refer to the Airplane Flight Manual for load distribution and moment arm Datum 89 inches in front of the flat surface of forward cabin bulkhead Leveling Means Refer to the Airplane Maintenance Manual (31448-001) A00018CH C.G. Range 6500 25.0% MAC Max. Ramp Weight 34.0% MAC FS 192.6 6040 lb FS 198.2 6000 lb 6000 - 23.2% MAC 34.0% MAC FS 191.07 FS 198.77 5500 - Max. Landing Weight 5550 lb Max. Zero Fuel Weigh 4900 lb 34.0% MAC Weight (Pounds) 5000 - FS 198.2 5200 Ib 20.0% MAC 4500 - FS 189.4 4700 lb 20.0% MAC FS 189.4 4000 lb 4000 - 31.0% MAC FS 196.3 3600 lb 3500 - 3000 T 15.0% 20.0% 25.0% 30.0% 35.0% C.G. (Percent MAC) SF50_FM02_0015 Empty Weight None C.G. Range Minimum Crew One (1) Pilot Number of Seats 7 maximum. Refer to the Airplane Flight Manual for seat configurations, moment arms and limitations. Fuel Capacity Total 298.5 US gal at 203 inches Usable 296 US gal Unusable 2.5 US gal Oil Capacity 2.2 quarts (full line) Refer to the Airplane Flight Manual for approved oils Maximum Operating S/N 0004 and subsequent for aircraft part numbers 26000-001 and 26000-003 Altitude 28,000 ft MSL S/N 0008, 0089, 0094 and subsequent except aircraft part number 26000-003 31,000 ft MSL -3- A000 18 CH Control Surface Aileron Up 15.0° ± 1.0° Down 11.5° ±1.0° Movements LH Aileron Trim Up 10.0° ± 1.0° Down 10.0° ±1.0° Ruddervator Pitch Up 20.0° ± 1.0° Down 15.0° ± 1.0° Ruddervator Yaw Up 9.0° ± 0.5° Down 9.0° ± 0.5° Ruddervator Trim Up 7.0° ± 1.0° Down 18.0° ± 1.0° Yaw SAS Up 15° ± 1.5° Down 15° ± 1.5° Wing Flaps Up 0°± 0.5° Down 50% 15.0°± 0.5° Down 100% 39.0°± 0.5° Serial Nos. Eligible 0004 and on Type Certificate Application September 9, 2008 Type Certificate Issuance Type Certificate A00018CH Issued October 28, 2016 Certification Basis 14 CFR Part 23 effective February 1, 1965, as amended by Amendments 23-1 through 23-62 14 CFR Part 34 effective September 10, 1990, as amended by Amendments 34-1 through 34-5A 14 CFR Part 36 effective December 1, 1969 as amended by Amendments 36-1 through 36-32 The aircraft certification basis is amended to include the following regulations at the amendment levels stated for crew, passenger, and bench seats (Effective SF50 S/N 717, 731 and subsequent) : 23.1529 (23-64); 23.2230 (23-64); 23.2235 (23-64); 23.2250 (23-64); 23.2255 (23-65); 23.2260 (23-64); 23.2265 (23-64); 23.2270 (23-64); 23.2315 (23-65); 23.2320 (23-64); 23.2325 (23-64); 23.2600 (23-65); 23.2605 (23-64); 23.2610 (23-64); 23.2620 (23-65); 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 741 and subsequent): 23.2325(f) (23-64); The detailed design standards used as a means of compliance in accordance with § 23.2010 are documented in Cirrus Model SF50 Detailed Design Standard Summary, Report No. E00006501. Special Conditions in accordance with 14 CFR Part 11: 23-261-SC, issued September 4, 2013, Inflatable Three-Point Restraint Safety Belt with an Integrated Airbag Device 23-267-SC, issued September 14, 2015, Full Authority Digital Engine Control System 23-272-SC, issued December 2, 2015, Auto Throttle 23-275-SC, issued July 6, 2016, Whole Airplane Parachute Recovery System 23-289-SC, issued August 3, 2018, Installation of Rechargeable Lithium Batteries Equivalent Level of Safety Findings in accordance with 14 CFR Part 21: ELOS number, date and subject Regulation modified by ELOS ACE-14-06, dated April 10, 2014: Electronic Placards §23.1559, §23.1567 ACE-15-04, dated October 17, 2016: Landing Gear Warning Horn §23.729(f) ACE-15-14, dated June 25, 2015: Cockpit Control Knob Shape §23.781(b) -4- A000 18 CH TC6444CH-A-F-2, dated July 12, 2016: Spin Requirements §23.221 TC06444CH-A-F-5, dated July 15, 2016: Amendment 62 Corrections §23.45, §23.51, §23.63, §23.67, §23.73, §23.77, §23.161, §23.181, §23.221, §23.251, §23.253, §23.571, §23.785, §23.831, §23.1195, §23.1197, §23.1199, §23.1201, §23.1527, §23.1545, §23.1583 TC6444CH-A-S-11, dated June 23, 2016: Storage Battery Design and Installation §23.1353(h) Exemptions from 14 CFR Part 23 in accordance with 14 CFR Part 11: Exemption No. 9948 dated October 23, 2009, §23.562(b) and §23.785(a), installation of seats limited to occupants weighing 90 pounds or less. Exemption No. 11092 dated October 23, 2014, §23.177(b), use of electric roll trim for static lateral stability Exemption No. 16970 dated June 23, 2016, §23.1419(a), 61-knot stall speed with critical ice accretions Other Certification Basis: Compliance has been shown for flight into known and forecast icing conditions Per the type design, S/N 0008, 0089, 0094 and subsequent meet the Reduced Vertical Separation Minima (RVSM) technical requirements except when configured as aircraft part number 26000- 003. The SF50 is defined by Cirrus document E00000474, SF50 Master Drawing List Production Basis Production Certificate 338CE issued June 12, 2000. Amended January 03, 2017 Production Limitation Record Issued June 12, 2000. Amended May 01, 2017 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. 31452-001 for aircraft serials 0004 and subsequent with aircraft part numbers 26000-001 and 26000-003, or Docoument No. 31452-002 for all other aircraft part numbers. 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 contained in the documents shown in the following table. These documents together meet the requirements of 14 CFR §23.1529. The Airworthiness Limitations are included in Section 4 of the Airplane Maintenance Manual. Effectivity Airplane Maintenance Manual Illustrated Parts Catalog Wiring Manual Component Maintenance Manuals S/N 0004 and subsequent 31448-001 31449-001 31450-001 31451-001 -5- A000 18 CH Note 4. MMO is 0.53 Mach except it is 0.54 Mach when Garmin system software version 006-B2881-E3 (09 July 2024) or subsequent version is installed. -- END --