STC SE00482SE

Number SE00482SE

This certificate, issued to Fifty-Ten-Yankee, LLC 7600 Terminal Street SW Olympia, WA 98501

Part 33 of the Federal Aviation Regulations.

Original ProductType Certificate Number: E4EA Make: Pratt & Whitney Canada Model: PT6D-114A Description of the Type Design Change: Incorporation of the Pratt and Whitney Canada PT6D-114A turbine engine into a twin power section turboprop assembly in accordance with Fifty-Ten-Yankee, LLC Master Drawing List Number 785-300, dated March 28, 2020, or later Federal Aviation Administration (FAA) approved revisions.

Limitations and Conditions: Approval of this change in type design applies to the basic Pratt and Whitney Canada PT6D-114A engines which are otherwise unmodified. This approval should not be extended to other engines of this model that incorporate any other previously approved modifications unless it is determined that the interrelationship between this change and any other modification will introduce no adverse effect on the airworthiness of these engines. A copy of this STC must be included with the permanent records of the modified airplane.

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.

Date of application: November 9, 1990 Date reissued December 2, 2004; October 7, 2019;

May 14, 2020; June 25, 2020

Date of issuance: November 18, 1997 Date amended

FAA FORM 8110-2 (5/14) PAGE 1 OF 6 PAGES By direction of the Administrator

(Signature)

For Manager, Seattle ACO Branch (Title)

Transfer the ownership of Supplemental Type Certificate Number

to (Name of Transferee)

(Address of Transferee)

(Number and Street)

(City, State, and ZIP Code)

from (Name of Grantor) (Print or Type)

(Address of Grantor)

(Number and Street)

(City, State, and ZIP Code)

Signature of Grantor (In Ink):

U.S. GPO: 1987-763-289

Number SE00482SE Fifty-Ten-Yankee, LLC Issued: November 18, 1997 Reissued: December 2, 2004; October 7, 2019; May 14, 2020; June 25, 2020 Amended:

Model: Dual Pac 785-1000-1

Type: Twin Power Section Turboprop

Propeller Drive Ratio: .0515:1

Ratings (See Note 1):

Maximum Continuous: Total Output Shaft Horsepower, SHP 1330 Single Power Section Shaft Horsepower, SHP 660 Output Shaft Speed, RPM 1700 Total Equivalent Shaft Horse, ESHP 1397 Single Power Section Shaft Horsepower, ESHP 694 Total Jet Thrust, LB 172 Single Power Section Jet Thrust, LB 86

Takeoff: Total Output Shaft Horsepower, SHP 1330 Single Power Section Shaft Horsepower, SHP 660 Output Shaft Speed, RPM 1700 Total Equivalent Shaft Horsepower, ESHP 1397 Single Power Section Shaft Horsepower, ESHP 694 Total Jet Thrust, LB 172 Single Power Section Jet Thrust, LB 86

Maximum Reverse: Left Engine Only, Shaft Horsepower, SHP 634 Output Shaft Speed, RPM 1632

Principal Dimensions: Length Overall, inches 76.48 Width, inches 49.54 Height, inches 29.75

Center of Gravity (CG): CG location, aft of propeller flange face, inches 35.5 CG location, below propeller axis, inches 4.2 CG location right of propeller axis, inches .3

Weight: Basic Dual Pac (dry), LB 1125.2

FAA FORM 8110-2 (5/14) PAGE 3 OF 6 PAGES

Number SE00482SE

Fifty-Ten-Yankee, LLC Issued: November 18, 1997 Reissued: December 2, 2004; October 7, 2019; May 14, 2020; June 25, 2020 Amended:

Propeller Drive: Flanged, 5.125 inch bolt circle, twelve holes, 0.593+0.006 inch diameter Oil:

Gearbox:

Oil Type: MIL-L-23699 Quantity: 1.6 gallons total

0.5 gallons usable

Auxiliary Oil System Inlet Limits:

Type: MIL-L-23699 Temperatures: 7°C to 99°C Flow Rate: 2 gallons per hour minimum

Control System: Soloy Propeller Governor 785-2141-1 Soloy Free Turbine Governor 785-2140-1

Certification Basis: FAR 21.29; FAR 21.115(a); FAR part 34 dated September 10, 1990, as amended by 34-1; FAR part 33 dated February 1, 1965, as amended by 33-1 through 33-5, plus the following sections:

Section 33.7, Amdt 33-12 Section 33.68, Amdt 33-10 Section 33.75, Amdt 33-10 and, Special Conditions 33-ANE-01, dated February 19, 1997

Note 1: The engine ratings are based on calibrated stand performance, under static sea level conditions:

Compressor inlet air (dry) 59°F, 29.92 in Hg No external accessory loads and no air bleed Compressor screen installed

Note 2: Permissible Oil Temperatures:

Gearbox, Takeoff and Maximum Continuous: 0°C to 99°C Auxiliary Oil System Inlet: 7°C to 99°C (See Continuation Sheet Page 5 of 6 Pages)

FAA FORM 8110-2 (5/14) PAGE 4 OF 6 PAGES

United States of America Department of Transportation - Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number SE00482SE Fifty-Ten-Yankee, LLC Issued: November 18, 1997 Reissued: December 2, 2004; October 7, 2019; May 14, 2020; June 25, 2020 Amended:

Note 3: The maximum output shaft overspeed limit is 108 percent at all ratings and may be employed for sustained periods in emergencies. 100% output shaft speed is defined as 1700 RPM.

Note 4: Maximum Allowable Torque:

The maximum allowable steady state and acceleration torque, as measured by torquemeter pressure, for either or both power sections are:

Continuous, PSIG 53.0 Transient Acceleration, Both Engines, PSIG 58.3

Note 5: Gearbox Oil Pressure Limits:

70 to 105 PSIG output speeds 1500 to 1700 RPM. Pressure will vary between 0 PSIG at zero output speed and 150 PSIG at 1700 RPM.

Note 6: In addition to accessory drives available on the power sections, the following accessory drive or mounting provisions are available on the gearbox:

DRIVEN BY POWER ROTATION SPEED RATIO MAX TORQUE (IN-LB) MAXIMUM TURBINE FACING DRIVE (TO PROP SPEED) CONT. STATIC OVERHUNG MOM

PAD (IN-LB) Propeller Governor Clockwise 2.474 50 850 25 Propeller Overspeed Clockwise 2.474 50 850 25 Governor Tachometer, Clockwise 2.474 7 100 10 Combining Gearbox

Note 7: This engine is certificated as a unit comprising two separate power sections with the capability of single engine operation with either power section alone in multi -engine airplanes. The unit is also approved as a single engine with either or both engines operating continuously.

Note 8: The engine meets FAA requirements for emergency oil out operation when auxiliary oil system conforms with the Soloy 785-100 Installation Manual instructions.

Note 9: This engine meets FAA requirements for operation in icing conditions and foreign object ingestion when the intake system conforms with the Pratt and Whitney Canada Installation Manual instruction for inertial separation of snow and icing particles. The engine also meets FAA requirements for adequate disk integrity and does not require external armoring.

(See Continuation Sheet Page 6 of 6 Pages) FAA FORM 8110-2 (5/14) PAGE 5 OF 6 PAGES

Number SE00482SE

Fifty-Ten-Yankee, LLC Issued: November 18, 1997 Reissued: December 2, 2004; October 7, 2019; May 14, 2020; June 25, 2020 Amended:

Note 10: Reverse propeller operations are available using the left power section only.

Note 11: Certain gearbox parts are life limited. These limits are listed in Soloy Service Bulletin Number 785-02 as revised. Permissible overhaul and inspection intervals are listed in Soloy Service Bulletin Number 785-03 as revised.

Note 12: For installation on a normal, commuter, or transport category airplane, a fuel filtration system which complies with 14 CFR §§ 23.997 and 23.1305, Amendment 23-15 or later, or 14 CFR §§ 25.997 and 25.1305, Amendment 25-36 or later, is required

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FAA FORM 8110-2 (5/14) PAGE 6 OF 6 PAGES