STC SA2353NM

(See Continuation Sheet Page 3 of 10 Pages) *See Type Data Sheet A4CE SA2353NM DV Aviation, Inc.

16384 Airport Rd. Suite 8 Brainerd, MN 56401 3 the Civil Air Regulations A4CE Textron Aviation Inc.

U206G, TU206G, 206H, T206H Installation of the Soloy Turbine Pac (Rolls-Royce 250-C20S engine modified STC SE2352NM) and related changes in accordance with Fifty-Ten-Yankee, LLC Master Drawing List Number 763-300, Revision AT, dated March 28, 2020, or later Federal Aviation Administration (FAA) approved revisions.

Approval of this change in type design applies to the above model aircraft which are otherwise unmodified. This approval should not be extended to other aircraft of these models on which other previously approved modifications are incorporated unless it is determined that the relationship between this change and any of those other previously approved modifications, including changes in type design, will introduce no adverse effect upon the airworthiness of that aircraft. A copy of this Certificate must be maintained as part of the permanent records for the modified engine.

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.

October 21, 1982 August 15, 1985; August 7, 1995; November 10, 2004; October 7, 2019;

May 14, 2020; June 25, 2020; March 30, 2023 May 22, 1984 January 17, 1984; January 7, 1985; January 23, 1985; August 15, 1985;

February 18, 1986; March 29, 1990; May 11, 1992; July 31, 1992;

May 23, 2003; November 10, 2004; July 31, 2008; August 19, 2008 for Manager, West Certification Branch

SA2353NM

SA2353NM Certain limitations and conditions shown on Type Certificate Data Sheet No. A4CE for the Cessna Models U206G, TU206G, 206H and T206H remain applicable: The following list contains those limitations and conditions which have been modified and certain unmodified ones which are listed for clarity:

Model: U206G, TU206G, 206H and T206H as modified by this STC (normal category).

Engine: Soloy Turbine Pac Model 780-1000-1 (Rolls-Royce Model 250-C20S modified per STC No.SE2352NM)

Engine Limits: Takeoff Rating (5 min.) 418 hp

Max. Continuous Rating 321 hp

Gas Producer (N 1) Continuous Operation 105% (53,519 RPM) Transient Overspeed (15 Sec.) 106% (54,028 RPM)

Propeller Shaft (Np) Continuous Operation 100% (1,810 RPM) Transient Overspeed (15 Sec.) 110% (1,990 RPM)

Torque: Takeoff Rate (5 Min.) 101.4 PSI Maximum Continuous Rating 78.0 PSI

Turbine Outlet Temperature:

Takeoff Rating (5 min.) 810°C (1,490°F) Maximum Continuous Rating 738°C (1,360°F) Transient (6 sec.) 843°C (1,550°F)

Oil Inlet Temperature:

Maximum 107°C (225°F) Minimum for starting using

MIL-L-7808G -54°C (-65°F) MIL-L-23699B -40°C (-40°F)

Oil: Oils approved to MIL-L-7808G or MIL-L-23699B

SA2353NM Fuel: MIL-T-5624, Grade JP4 or JP5 MIL-T-83133, Grade JP-8 ASTM D-1655, Jet B ASTM D-1655, Jet A or A1 JP-1 fuel conforming to ASTM D-1655, Jet A Diesel #1 fuel conforming to ASTM D-1655, Jet A

Propeller and Propeller Limits:

Hartzell: HC-C3YN-5A/FC9587D-2

Diameter: Not over 95 in.

Not under 93 in.

Pitch Settings: (At 30 inch station) High Pitch 81° Low Pitch 5°

Hartzell Spinner: D-3273

Soloy Corporation Prop Governor 780-3356-3 Soloy Corporation Prop Overspeed Governor 780-3360-1

Airspeed Limits (IAS): Maximum Operating 149 knots Maneuvering 120 knots (125 knots for 206H, T206H) Flaps extended 96 knots

Center of Gravity Limits: Center of Gravity Range:

Forward: +33.0 inches aft of datum at 2500 lbs. or less, with straight line variation to +42.5 inches aft of datum at 3600 lbs.

Aft: +49.7 inches aft of datum at all weights.

Reference Datum: Lower portion of front face of firewall.

SA2353NM Weight Limit: Maximum Ramp Weight 3617 lbs. (206H, T206H) Maximum Takeoff Weight 3,600 lbs.

Maximum Landing Weight 3,600 lbs.

Fuel Capacity: (U20603522 through U20604649) 80 gal. (76 gal. usable) two 40 gal., tanks in wing at +48.

(U20602589, U20604650 and up, 20608001 through 20608173, T20608001 through T20608361) 92 gal. (88 gal. usable) two 46 gal. integral tanks in wings at +46.5.

(20608174 and up, T20608362 and up) 92 gal. (87 gal. usable) two 46 gal. integral tanks in wings at +46.5.

Oil Capacity: 9 quarts at -29 (see Note 1 for data on system fuel and oil)

Control Surface Movements:

Wing flaps Up 0° Down 40° +1°, -2° Aileron Up 21° ±2° Down 14° 30' ±2° Elevator Up 21° ±1° Down 17° ±1° Elevator tabs Up 25° +1°, -0° Down 5° +1°, -0° Rudder Right 24° 57' ±1° Left 24° 57' ±1° Right 24° ±1° Left 24° ±1° (206H, T206H) (measured perpendicular to rudder hinge line) Right 22° ±1° Left 22° ±1° (measured parallel to 0.0.W.L)

Landing Gear Limitations:

Nose Wheel Size 6.00-6, with Main Wheel sizes

6.00-6, 8.00-6 and 8.50-6.

OR Nose Wheel Size 5.00-5, with Main Wheel size 6.00-6 only

SA2353NM Flight Idle Limits:

Flight Operations with the power control retarded below FLIGHT IDLE (14-psi torque minimum) are prohibited.

Flap Limitations

Approved Takeoff Range: 0° to 20° Approved Landing Range: 0° to 40°

Cessna Serial Nos. Eligible:

U206G, TU206G: U20603522 through U20604074 (1977) U206G, TU206G: U20604075 through U20604649 (1978) U206G, TU206G: U20602589 and U20604650 through U20605309 (1979) U206G, TU206G: U20605310 through U20605919 (1980) U206G, TU206G: U20605920 through U20606439 (1981) U206G, TU206G: U20606440 through U20606699 (1982) U206G, TU206G: U20606700 through U20606788 (1983) U206G, TU206G: U20606789 through U20606846 (1984) U206G, TU206G: U20606847 through U20606920 (1985) U206G, TU206G: U20606921 through U20607020 (1986) 206H: 20608001 and up T206H: T20608001 and up

Certification Basis:

Basis: (U206G, TU206G) Part 3 of the Civil Air Regulations, effective May 25, 1956, as amended by 3-1 through 3-8.

In addition, effective Serial Numbers U20602589 and U20604650 and up, FAR 23.1559, effective March 1, 1978; plus the following sections of FAR Part 23, effective December 8, 1980, which are required to maintain the airplane's existing level of airworthiness with the turboprop engine installed. The specific sections of FAR Part 23 are:

FAR 23 dated February 1, 1965, including amendments 23-1 through 23-27, thereto:

23.45, 23.49, 23.65, 23.75(d), 23.77, 23.173, 23.175, 23.201, 23.251, 23.253, 23.335, 23.361, 23.371, 23.629(f),

23.901, 23.903, 23.905, 23.907, 23.929, 23.937, 23.939, 23.943, 23.951, 23.955, 23.977, 23.991, 23.997, 23.1013,

23.1015, 23.1017, 23.1019, 23.1027, 23.1041, 23.1043, 23.1045, 23.1091, 23.1093, 23.1103, 23.1105, 23.1111,

23.1121, 23.1141, 23.1143, 23.1145, 23.1155, 23.1165, 23.1183, 23.1305, 23.1337, 23.1505, 23.1521, 23.1527,

23.1529, 23.1545, 23.1549, 23.1557.

SA2353NM (206H, T206H) 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, 23.611, 23.619, 23.623, 23.689, 23.775, 23.871; 23.1111, 23.1121, and 23.1323 as amended by 23-7;

FAR 23.807 and 23.1524 as amended by 23-10; FAR 23.507, 23.771, 23.853(a)(b)(c) and 23.1365 as amended by 23-14; FAR 23.607, 23.675, 23.687, 23.733, 23.787, 23.951, 23.1309, 23.1322 and 23.1559 as amended by 23-17;

FAR 23.1301 as amended by 23-20; FAR 23.1353 as amended by 23-21; FAR 23.603, 23.605, 23.613 and 23.1329 as amended by 23-23; FAR 23.45, 23.49, 23.65, 23.75(d), 23.77, 23.173, 23.175, 23.201, 23.251, 23.335, 23.361,

3.629(e)(f), 23.901, 23.903, 23.905, 23.907, 23.925, 23.929, 23.937, 23.939, 23.943, 23.955, 23.977, 23.991, 23.997,

23.1013, 23.1015, 23.1017, 23.1019, 23.1027, 23.1041, 23.1043, 23.1045, 23.1091, 23.1103, 23.1105, 23.1141,

3.1143, 23.1145, 23.1155, 23.1165, 23.1305, 23.1337, 23.1505, 23.1521, 23.1527, 23.1529, 23.1545 and 23.1557 as amended by 23-27; FAR 23.441 and 23.1549 as amended by 23-28; FAR 23.1093 as amended by 23-29; FAR

23.779 and 23.781 as amended by 23-33; FAR 23.1 and 23.561 as amended by 23-34; FAR 23.301, 23.331, 23.351,

23.427, 23.677, 23.701, 23.735 and 23.831 as amended by 23-42; FAR 23.961, 23.1107(b), 23.1143(g), 23.1147(b),

23.1303, 23.1357, 23.1361 and 23.1385 as amended by 23-43; FAR 23.562(a)(b)(2)(c)(1)(c)(2)(c)(3)(c)(4) as amended by 23-44; FAR 23.305, 23.321, 23.485, 23.621, 23.655 and 23.731 as amended by 23-45.

An equivalent level of safety finding applies with respect to FAR 23.955(f)(2), with airplanes incorporating a modified fuel selector valve which allows individual left or right fuel tank selection.

Part 36 of the Federal Aviation Regulations (FAR).

Special Federal Aviation Regulation 27, as amended by 27-1 and 27-2.

In addition, a special condition to evaluate whirl mode, which incorporates the essential features of FAR

23.629(e)(1) and (2)

SA2353NM Equipment:

The following must be installed in the aircraft for airworthiness certification:

a. The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis).

b. The equipment must include a current airplane flight manual plus FAA approved Soloy, LLC Airplane Flight Manual Supplement.

c. Stall warning indicator, Cessna Drawing 0511062-4.

d. Floatplane parts for vertical fin and rudder assembly:

Cessna P/N Item

1231034-9 Rudder Assembly 1231062-7 Rib Assembly - Fin Upper 1231040-1 Cover - Fin Tip 1212600-7 Stinger Assembly

e. The aircraft must be equipped with 28 - volt electrical systems.

NOTE 1: Current weight and balance data including list of equipment included in certified empty weight and loading instructions when necessary, must be provided for each aircraft at the time of airworthiness certification for return to service. The certificated empty weight and corresponding center of gravity location must include unusable fuel and full oil as follows:

Unusable fuel:

U206G, TU206G: 26.8 lb. (4 gallons) at +46 20608001 - 20608173, T20608001 - T20608361: 26.8 lb. (4 gallons) at +48 20608174 and up, T20608362 and up: 33.5 lb. (5 gallons) at +48 Full oil, 18 lb. (9 quarts) at -29.0

NOTE 2: The rating shown for the Soloy Turbine Pac 780-1000-1 engine is based on zero ram, dry inlet air, no accessory loads, and no bleed air; and is available at sea level to approximately 40°F.

NOTE 3: Information essential to the maintenance and servicing of aircraft modified in accordance with this STC is contained in the applicable Cessna maintenance and overhaul instructions and in the Soloy, LLC supplements to these documents.

SA2353NM NOTE 4: This change in type design is applicable to land plane operation of the Cessna Models U206G and TU206G S/N's U20602589, and U20603522 through U20607020, and 20608001 and up, and T20608001 and up.

NOTE 5: The maximum flight altitude 20,000 ft., except:

The maximum flight altitude is restricted to 8,000 ft. when using any cold weather fuel and the fuel temperature is 4°C or above.

NOTE 6: Cold weather fuels and fuel additive:

a. MIL-T-5624, Grade JP-4

b. ASTM D-1655, Jet B

c. AVGAS/Jet A, Jet A1, or JP-5 mixture.

d. For flight at ambient temperatures of 40°F and below, the fuel used in this aircraft MUST have an anti_icing additive in compliance with MIL-1-27686D or E, or Phillips PF A55MB.

NOTE 7: Minimum Fuel

Due to the possibility of fuel starvation, takeoff or steep climbs at speeds below Vy (86 KIAS at sea level) with either fuel quantity gauge indicating in the yellow arc (1/8 fuel quantity) are prohibited. For airplanes equipped with a fuel selector valve capable of left, or right, or both fuel tank selection, takeoff and landings must be accomplished with the fuel selector valve in the "both" position.

NOTE 8: Engine Inlet and Induction System Ice Protection

Engine Inlet and Induction system ice protection must be accomplished by the operation of the engine alternate air system alone or in conjunction with the engine inlet anti_ice system as follows:

a. Alternate air (without engine inlet anti-ice operation).

The engine alternate air must be activated for flight or ground operation in the following conditions:

1. Invisible moisture at an OAT of 5°C (41°F) and below.

2. While operating in falling or blowing snow regardless of ambient temperature

End Page 10 of 10 Limitations and Conditions Continued:

SA2353NM

b. Alternate air (with engine inlet anti-ice operation)

The engine alternate air and engine inlet anti-ice systems must be operated for flight or ground operation as follows:

1. In visible moisture at an OAT of 5°C (41°F) to 1°C (34°F) actuate the engine inlet anti-ice system.

2. In visible moisture at an OAT of 1 °C (34°F) and below activate the engine alternate air system. While operating on engine alternate air the engine inlet anti-ice may be deactivated.

3. While operating in falling or blowing snow regardless of ambient temperature, activate the engine alternate air system.

Deactivation of the above systems shall not be made until the above mentioned conditions have been left and all accumulated airframe ice and/or snow has dissipated.

NOTE 9: Placards must be displayed as indicated in the FAA approved Soloy, LLC Airplane Flight Manual Supplement.