STC SA3523NM

FAA Form 8110-2 (5/14) Page 1 of 8

Number: SA3523NM

Part * of the Federal Aviation Regulations.

 See Continuation Sheet page 8 of 8 pages for Certification Basis.

Original Product – Type Certificate Number: 3A15 Make: Textron Aviation Model: A36 and A36TC

Option 1. Installation of an Allison 250-B17C turbine engine and related changes in accordance with Fifty-Ten-Yankee, LLC Master Drawing List Number 771-300, Revision AA, dated March 28, 2020, or later Federal Aviation Administration (FAA) approved revisions. Option 2. Installation of an Allison 250-B17F/2 turbine engine and related changes in accordance with Fifty- Ten-Yankee, LLC Master Drawing List Number 871-300, Revision A, dated March 28, 2020, or later FAA approved revisions.

Date of Application: December 14, 1984 Date Reissued: January 23, 1995; May 12, 2003;

October 5, 2016; October 7, 2019; May 14, 2020;

June 25, 2020

Date of Issuance: July 3, 1986 Date Amended: November 9, 1987; May 1, 1992 Revision 2

Signature For Manager, Seattle ACO Branch Fifty-Ten-Yankee, LLC 7600 Terminal Street SW Olympia, WA 98501

FAA Form 8110-2 (5/14) Page 2 of 8

Transfer the ownership of Supplemental Type Certificate Number: SA3523NM

To (Name and address of transferee)

From (Name and address of grantor)

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA3523NM

FAA Form 8110-2 (5/14) Page 3 of 8

Date of Issuance: July 3, 1986 Date Amended: May 1, 1992 Date of Reissuance: October 5, 2016; October 7, 2019; May 14, 2020; June 25, 2020

The approval of this change in type design applies to the above model aircraft which are otherwise unmodified. Option 1. FAA Approved Airplane Flight Manual Supplement, Rev. 1 dated 06/18/87 or later FAA approved revision required. Option 2. FAA Approved Airplane Flight Manual Supplement, Rev. 2 dated 02/13/92 or later FAA approved revision required.

The installer must determine whether this design change is compatible with previously approved modifications. 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. A copy of this STC must be included in the permanent records of the modified aircraft. Certain limitations and conditions shown on Type Certificate Data Sheet No. 3A15 for Textron Aviation Models A36 and A36TC remain applicable. The following list contains those limitations and conditions applicable to this modification and certain unmodified ones from 3A15 which are listed for clarity.

Model: A36 and A36TC (Utility Category; Normal Category with optional tip tanks installed, see note 6).

Engine: Allison 250-B17C or Allison 250-B17F/2

Fuel: (1) Primary Fuels MIL-T5624, Grade JP-5 MIL-T-83133, Grade JP-8 ASTM D-1655, Jet A or A1 JP-1 Fuel Conforming to ASTM D-1655, Jet A Diesel #1 Fuel Conforming to ASTM D1655, Jet A

(2) Cold Weather Fuels (See note 4) MIL-T-5624, Grade JP-4 ASTM D-1655, Jet B AVGAS/Jet A, Jet A1, or JP-5 Mixture defined in FAA Approved Flight Manual Supplement

Maximum Cold Weather Fuel Temperature Limit:

38°C (100°F)

Engine Ratings: Takeoff (5 minutes) 420 SHP Maximum Continuous 369 SHP

Engine Limits: Torque 1b-ft T/M Pressure Takeoff (5 minutes) 1138 107 psi Maximum Continuous 955 89 psi Transient (10 sec) 1165 110 psi

Propeller Speed (NP) RPM Percent Takeoff and Maximum Continuous 2030 100 Transient (15 seconds) 2233 110

Turbine Outlet Temperature Takeoff and Maximum Continuous 810°C (1490°F) Transient (6 seconds) 843°C (1550°F)

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA3523NM

FAA Form 8110-2 (5/14) Page 4 of 8

Starting (10 seconds) 927°C (1700°F)

Date of Issuance: July 3, 1986 Date Amended: May 1, 1992 Date of Reissuance: October 5, 2016; October 7, 2019; May 14, 2020; June 25, 2020

Propeller and Propeller Limits: Model Hartzell HC-B3T Hub HC-B3TF-7A Blade T9212K-2 Diameter 88 to 90 inches

Airspeed Limits: CAS IAS (knots) (knots) Maximum Operating Speed Vmo (Decrease 165 167 3 Knots per 1000 ft. above 16,000 feet)

Maneuvering 139 141 Va

Maximum Flap Extension/Extended Vfe 122 126 (Prior to S/N E-1371)

A36TC and A36 (S/N E-1371 and after) Approach (15°) 152 154 Above 20,000 137 139 Full Down (30°) 122 126

Maximum Landing Gear Operating/Extended 152 154 Vlo/Vle Above 20,000 feet 137 139

Maximum Outside Air Temperature Limits: 127°F (53°C) at sea level, with a reduction of 3.6°F (2°C) per 1000 ft. altitude, for all operations.

Weight Limits: (See note 5 for weight limits with optional tip tank installation)

A36 (S/N E-1111, A36TC and A36 E-1241 through (S/N E-1946, E-2110 except E-2104, E-2111 E-1946 and E-2104 and after)

Maximum Ramp Weight 3612 lb. 3666 lb.

Maximum Takeoff Weight 3600 lb. 3650 lb.

Maximum Landing Weight 3600 lb. 3650 lb.

Maximum Baggage/Cargo Compartment Rear Cabin Compartment 400 lb. 400 lb.

Aft Compartment 70 lb. 70 lb.

Forward Compartment 120 lb. 120 lb.

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA3523NM

FAA Form 8110-2 (5/14) Page 5 of 8

Date of Issuance: July 3, 1986 Date Amended: May 1, 1992 Date of Reissuance: October 5, 2016; October 7, 2019; May 14, 2020; June 25, 2020

C. G. Range A36 S/N E-1111, E-1241 though E-2110 except E-1946 & E-2104 (Landing Gear Extended) (+81.0) to (+87.7) at 3600 lb.

See note 5 for C. G. range with optional tip (+74.0) to (+87.7) at 3100 lbs.

tank installation. or less Straight line variation between points given.

A36TC and A36 (S/N E-1946, E-2104, E-2111 and after) (+81.0) to (+87.7) at 3650 lb.

(+74.0) to (+87.7) at 3100 lbs.

or less Straight line variation between points given.

Reference Datum: 83.1 inches forward of center line through forward jack points.

Fuel Capacity: Standard Fuel System 81 U.S. Gal.

Usable 74 U.S. Gal.

With Optional Wing Tip Tanks (See note 5) 121 U.S. Gal.

Usable 114 U.S. Gal.

Oil Capacity: Total System Capacity 12 U.S. Qts.

Tank Capacity 6 U.S. Qts.

Maximum Operating Altitude: 25,000 ft.

Control Surface Movements:

Wing Flaps (A36 S/N E-1111, E-1241 through E-1370) Down 30° (A36TC and A36 S/N E-1371 through E-2110 except E-1946 and E-2104) Approach 15° Down 30° (A36 S/N E-1946, E-2104, E-2111 and after) Approach 12° Down 30°

Right Aileron Tab Fixed

Left Aileron Tab

(A36 S/N E-1111 through E-2110 except E-1946 and E-2104) Fixed (A36 S/N E-1946, E-2104, E-2111 and after) Up 9° Down 9°

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA3523NM

FAA Form 8110-2 (5/14) Page 6 of 8

Aileron Tab (A36TC) Fixed

Date of Issuance: July 3, 1986 Date Amended: May 1, 1992 Date of Reissuance: October 5, 2016; October 7, 2019; May 14, 2020; June 25, 2020

Control Surface Movements (continued):

Aileron Up 20° Down 20°

Rudder Tab Fixed

Rudder Left 23° Right 23°

Elevator Tab Up 10° Down 27°

Elevator Up 23° Down 20°

Serial Numbers Eligible: A36: S/N E-1111, E-1241 and after A36TC: EA-1 through EA-241, EA-243 and after

Required Equipment: Equipment described in Type Certificate Data Sheet 3A15 for the A36 and A36TC are required to be on the aircraft except as modified by this STC. Other items of required equipment are listed in the FAA Approved Airplane Flight Manual Supplement.

In addition, the following must be in the airplane for airworthiness certification:

(a) The applicable Textron Aviation A36 or A36TC Airplane Flight Manual plus FAA Approved Airplane Flight Manual Supplement.

(b) Current weight and balance report including a list of equipment included in the certificated empty weight (See note 1).

NOTE 1: The Empty Weight and Center of Gravity of the airplane shall be determined by actual weighing after modification in accordance with this STC and prior to return to service. This weight and center of gravity shall be recorded in the appropriate place in the airplane weight and balance report.

The certificated empty weight and corresponding center of gravity locations must include full system engine oil of 24 lbs. at 8.2 inches aft of datum and unusable fuel of 47 lbs. at 77.7 inches aft of datum.

Note 2: Refer to the FAA Approved Airplane Flight Manual Supplement for required markings and placards.

Note 3: The engine ice protection system consists of an electrically heated inlet and propeller, engine bleed air heated compressor front bearing support hub and inlet guide vanes, continuous ignition, and cowl flap. The engine ice protection system must be activated for ground and flight operation in visible moisture at an OAT of 5°C (41°F) and below, or while operating in falling and blowing snow regardless of ambient temperature.

The engine ice protection system must not be deactivated until the above mentioned conditions have been left and all accumulated

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA3523NM

FAA Form 8110-2 (5/14) Page 7 of 8

airframe ice has dissipated.

Date of Issuance: July 3, 1986 Date Amended: May 1, 1992 Date of Reissuance: October 5, 2016; October 7, 2019; May 14, 2020; June 25, 2020

Note 4: For flight at ambient temperatures of 40°F (4.5°C) and below, the fuel used in this airplane must have an anti-icing additive that conforms to MIL-I-27686D or E, or Phillips PF A55MB, incorporated or added into the fuel during refueling in accordance with the additive manufacturer’s instructions.

Note 5: Optional wing tip fuel tanks may be installed in accordance with Soloy Conversions, Ltd. Master Drawing List No. 772-100 dated June 30, 1986, or later FAA approved revisions. The following weight and center of gravity limits apply with the tip tanks installed.

Weight Limits: A36 (S/N E-1111, E-1241 A36TC and A36 (S/N E-1946, through E-2110 except E-2104, E-2111 E-1946 & E-2104) and after) Maximum Ramp Weight 3792 lb. 3849 lb.

Maximum Takeoff Weight 3780 lb.* 3833 lb.* Maximum Landing Weight 3600 lb. 3650 lb.

Maximum Baggage/Cargo Compartment Rear Cabin Compartment 400 lb. 400 lb.

Aft Compartment 70 lb. 70 lb.

Forward Compartment 120 lb. 120 lb.

*All weights in excess of 3600 lb. for the A36 (S/N E-1111, E-1241 through E-2110 except E-1946 and E-2104) and 3650 lb. for the A36TC and A36 (S/N E-1946, E-2104, E-2111 and after) must be in tip tank fuel.

C. G. Range:

A36 S/N E-1111, E-1241through E-2110 except E-1946 & E-2104 (+83.5) to (+87.3) at 3780 lb.

(+81.0) to (+87.7) at 3600 lb.

(+74.0) to (+87.7) at 3100 lbs.

or less Straight line variation between points given.

A36TC and A36 and (S/N E-1946, E-2104, E-2111 and after) (+83.3) to (+87.3) at 3833 lb.

(+81.0) to (+87.7) at 3650 lb.

(+74.0) to (+87.7) at 3100 lbs.

or less Straight line variation between points given.

Note 6: This airplane is certificated in the utility category. With optional wing tip fuel tanks installed and with fuel in the tip tanks, the airplane is certificated in the normal category only.

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA3523NM

FAA Form 8110-2 (5/14) Page 8 of 8

Date of Issuance: July 3, 1986 Date Amended: May 1, 1992 Date of Reissuance: October 5, 2016; October 7, 2019; May 14, 2020; June 25, 2020

Note 7: This airplane has been evaluated with a Norton Radome pod installed in accordance with Supplemental Type Certificate SA180GL and it was determined that the interrelationship between these two modifications introduces no adverse effect on the airworthiness of this aircraft. Compatibility was demonstrated with a 10 lb. radar antenna installed in the pod. Antenna s of other weights were not evaluated This finding does not constitute approval of any specific radar installation.

Certification Basis:

Part 3 of the Civil Air Regulations as amended to May 15, 1956, and Amendment, 3-8. For the Model A36TC only, section

23.1583(a) as amended by Amendment 23-7 and sections 23.959, 23.967(a)(5), and 23.1121(b) as amended by Amendment 23-18 of the Federal Aviation Regulations Part 23, dated February 1, 1965. The following specific sections of FAR 23 are required to maintain the airplane’s existing level of airworthiness with the turboprop engine installed.

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), 23.863, 23.901, 23.903, 23.905 except para (d), 23.907, 23.929,

23.933, 23.937, 23.939, 23.943, 23.951, 23.955, 23.959, 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, 23.1303, 23.1305, 23.1337, 23.1505, 23.1521, 23.1527, 23.1529, 23.1545, 23.1549, 23.1557. Additionally, 23.629(e) Amendment 23-31.

Part 36 of the Federal Aviation Regulations.

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

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