STC SA01878SE

(See Continuation Sheet Page 3 of 6 Pages) SA01878SE DV Aviation, Inc.

16384 Airport Rd. Suite 8 Brainerd, MN 56401 23 the Federal Aviation Regulations A4CE Textron Aviation Inc.

206H, T206H Installation of Rolls-Royce 250-B17F/2 series engine with a Hartzell Model HC-B3TF-7A/T10173FN(K)-11R Propeller in accordance with Fifty-Ten-Yankee, LLC Master Drawing List 766-100, Revision AA, dated March 28, 2020,or later Federal Aviation Administration (FAA) approved revision, and maintained in accordance with Maintenance & Overhaul Supplement S2012F, First Edition, Revision 0, dated October 2008, or later Federal Aviation Administration (FAA) accepted revisions.

Approval of this change in type design applies to the above model aircraft only. This approval should not be extended to other aircraft of this model series unless the installer determines that the relationship between this change and any other previously incorporated approved modifications will introduce no adverse effect upon the airworthiness of that aircraft. A copy of this Certificate and the FAA approved Aircraft Flight Manual Supplement must be maintained as part of the permanent records for the modified aircraft.

If the holder agrees to permit another person to use this certificate to alter the product, the holder shall give the other person written evidence of that permission.

January 28, 2005 October 7, 2019; May 14 2020; June 25, 2020; March 30, 2023 October 29, 2008 for Manager, West Certification Branch

SA01878SE

SA01878SE Certain limitations and conditions shown on the Type Certificate Data Sheet No. A4CE for the Cessna Models 206H and T206H remain applicable. The following list contains those limitations and conditions which are modified, and certain unmodified ones which are listed for clarity:

Model: 206H and T206H

Engine: Rolls-Royce 250-B17F/2 series

Fuel: Refer to Soloy Aircraft Flight Manual Supplement S2010F for approved fuels and additive specifications.

Engine Limits: Power Ratings (Sea Level, ISA) Takeoff (5 minutes) 417 S.H.P.

Maximum Continuous 322 S.H.P.

Gas Producer Speed, N1 (100% = 50970 RPM) Transient (15 seconds) 54028 RPM (106 %) Continuous Operation 53519 RPM (105 %)

Power Turbine Speed, Np (100% = 33290 RPM = 2030 RPM Propeller Shaft Speed)

Transient (15 seconds) 2233 RPM (110 %) Continuous Operation 2030 RPM (100 %)

Torque Takeoff (5 minutes) 101 PSI Continuous Operation 78 PSI

Turbine Outlet Temperature Limit, TOT: °F (°C)

Starting 1700 (927) Transient (6 seconds) 1550 (843) Takeoff (5 minutes) 1490 (810) Maximum Continuous Operation 1386 (752)

Oil Inlet Temperature: ºF (ºC)

Maximum (5 minutes) 225(107) Continuous Operation 180(82) Minimum for starting using:

MIL-L-7808 -65(-54) MIL-L-23699 -40(-40)

Page 4 of 6 SA01878SE Engine Limits: (continued)

Engine Lubricating Oil:

MIL-L-7808G or MIL-L-23699 and subsequent revisions (mixing of these oils is prohibited).

Propeller and Propeller Limits:

Hartzell: HC-B3TF-7A/T10173FN(K)-11R

Diameter: Not over 90.375 inches Not under 88.375 inches

Pitch Settings (at 30 inch station): Low Pitch 9º to 10° Feather 81º

Airspeed Limits: Maximum Operating 50 Knots IAS Maneuvering 125 Knots IAS Flaps Extended 100 Knots IAS Maximum Window Open Speed 150 Knots IAS

Center of Gravity Limits: Forward Limits: Linear variation from 42.5 inches aft of datum at 3600 lbs to 33.0 inches aft of datum at 2500 lbs: 33.0 inches aft of datum at 2500 lbs or less.

Aft Limit: 49.7 inches aft of datum at 3600 lbs or less.

Reference datum: Firewall, Front Face, Lower Portion (Station 0.0)

Weight Limit: Maximum Ramp Weight 3617 lb.

Maximum Takeoff Weight 3600 lb.

Maximum Landing Weight 3600 lb.

Fuel Capacity: 92 gallon (88 gallon usable) for units 20608001 through 20608173 and T20608001 through T20608361.

92 gallon (87 gallon usable) for units 20608174 and on and T20608362 and on.

(Two 46 gallon integral tanks in wings at 46.5 inches aft of datum) See note 1 for data on unusable fuel.

Oil Capacity: 7.8 quarts at 23.2 inches forward of datum.

SA01878SE Control Surface Movements:

Wing Flaps Up 0º Down 40º +1º, -2º Aileron Up 21º ±2º Down 14º 30' ±2º Elevator Up 21º ±1º Down 17º ±1º Elevator tabs Up 25º +1º, -0º Down 5º +1º, 0º Rudder Right 24º 57' ±1º Left 24º 57' ±1º (Measured perpendicular to rudder hinge line) Right 22º ±1º Left 22º ±1º (Measured parallel to 0.0. W. L.)

Serial Nos. Eligible: 20608001 and on T20608001 and on

Certification Basis: Part 23 of the Federal Aviation Regulations effective February 1, 1965, as amended by 23-1 through 23-6, except as follows:

FAR 23.423; 23.619; 23.623; 23.689; 23.775; 23.871 and 23.1563 as amended by Amendment 23-7. FAR 23.807 and 23.1524 as amended by Amendment 23-10. FAR

23.507; 23.771; 23.853(a), (b) and (c) and 23.1365 as amended by Amendment 23-14 FAR 23.675; 23.685; 23.733 and 23.787 as amended by Amendment 23-17. FAR

23.1301 as amended by Amendment 23-20. FAR 23.1559 as amended by Amendment 23-21. FAR 23.603; 23.605 and 23.613 as amended by Amendment

23-23. FAR 23.441 as amended by Amendment 23-28. FAR 23.779 and 23.781 as amended by Amendment 23-33. FAR 23.1 and 23.561 as amended by Amendment

23-34. FAR 23.331; 23.351; 23.427; 23.677; 23.701 and 23.831 as amended by Amendment 23-42 FAR 23.961; 23.1107(b); 23.1147(b); 23.1357; 23.1361 and

23.1385 as amended by Amendment 23-43. FAR 23.562(a), 23.562(b)2, 23.562(c)1,

23.562(c)2, 23.562(c)3, and 23.562(c)4 as amended by Amendment 23-44. FAR

23.305; 23.321; 23.485; 23.621; 23.655 and 23.731 as amended by Amendment

23-45.

The following regulations as amended by Amendments 23-7 through 23-54:

14 CFR 23.25, 23.29, 23.33, 23.45, 23.49, 23.51, 23.53, 23.63, 23.65, 23.69, 23.71,

23.73, 23.77, 23.141; 23.145, 23.153, 23.155, 23.161, 23.175, 23.177, 23.201, 23.203,

23.221, 23.233, 23.235, 23.251, 23.253, 23.301, 23.335, 23.343, 23.361, 23.371,

23.393, 23.399, 23.479, 23.572, 23.575, 23.607, 23.611, 23.629, 23.735, 23.777,

23.863, 23.865, 23.901, 23.903, 23.904, 23.905, 23.907, 23.925, 23.929, 23.933,

23.937, 23.939, 23.943, 23.951, 23.954, 23.955, 23.959, 23.965, 23.971, 23.973,

23.977, 23.991, 23.993, 23.994, 23.995, 23.997, 23.999, 23.1011, 23.1013, 23.1015,

23.1017, 23.1019, 23.1021, 23.1027, 23.1041, 23.1043, 23.1045, 23.1091, 23.1093,

23.1103, 23.1111, 23.1121, 23.1123, 23.1141, 23.1143, 23.1145, 23.1153, 23.1155,

23.1163, 23.1165, 23.1181, 23.1182, 23.1183, 23.1189, 23.1191, 23.1193, 23.1203,

23.1303, 23.1305, 23.1309, 23.1321, 23.1322, 23.1329, 23.1337, 23.1351, 23.1353,

23.1438, 23.1501, 23.1505, 23.1521, 23.1527, 23.1529, 23.1545, 23.1549, 23.1553,

23.1555, 23.1557, 23.1583, 23.1585 and 23.1587.

End Limitations and Conditions continued:

SA01878SE 14 CFR Part 34 - Fuel Venting and Exhaust Emission Requirements for Turbine Engine Powered Airplanes, Amendment 34-3, dated February 3, 1999.

14 CFR Part 36-Noise Standards: Aircraft Type and Airworthiness Certification, Amendment 36-25, dated July 2, 2004.

Equipment: The basic required equipment as prescribed in the applicable airworthiness regulations (See Certification Basis) must be installed in the aircraft for certification. The equipment must include the following:

a) FAA Approved Airplane Flight Manual (AFM) or Pilot's Operating Handbook and FAA approved Airplane Flight Manual (POH/AFM): Part number 206HPHUS00 (Model 206H) or T206HPHUS00 (Model T206H) or later FAA approved revisions.

b) FAA Approved Airplane Flight Manual Supplement, S2010F, Revision 0, dated October 24, 2008, or later FAA approved revision.

Note 1: Weight and Balance:

Serial Nos. 20608001 thru 20608173 and T20608001 thru T20608361; (Model 206H and Model T206H)

The certificated basic empty weight and corresponding center of gravity location must include unusable fuel of 26.8 pounds at 48 inches aft of datum.

Serial Nos. 20608174 and on and T20608362 and on; (Model 206H and Model T206H)

The certificated basic empty weight and corresponding center of gravity location must include unusable fuel of 33.5 pounds at 48 inches aft of datum.

Note 2: This airplane must be operated according to the appropriate AFM or POH/AFM and AFMS.

Note 3: Required placards are included in the FAA approved Flight Manual Supplement, S2010F.

Note 4: This supplemental type design change is not applicable for Model 206H or T206H aircraft equipped with the Garmin G1000 Integrated Cockpit System.