STC SA4142NM

Number SA4142NM

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

Part * of the* Regulations.

* See Pages 3 and 4 of this certificate for certification basis

Original ProductType Certificate Number: 3A15 Make: Textron Aviation Model: A36 and A36TC Description of the Type Design Change: Installation of an exhaust heated engine inlet in accordance with Fifty- Ten-Yankee, LLC Master Drawing List Number 886-300, Revision F, dated March 28, 2020, or later Federal Aviation Administration (FAA) approved revisions, on airplanes that have Rolls-Royce Model 250-B17C engines installed in accordance with STC SA3523NM.

Limitations and Conditions: The approval of this change in type design applies only to the above model aircraft which have been modified in accordance with STC SA3523NM but are otherwise unmodified. This approval should not be extended to other aircraft of this model that incorporate any other previously approved modification unless it is determined that the interrelationship between this change and any other modification will introduce no adverse effect on the airworthiness of these aircraft. A copy of this STC must be included in the permanent records of 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.

Date of application: September 15, 1986 Date reissued May 4, 1993; December 2, 2004;

October 7, 2019; May 14, 2020;

June 25, 2020

Date of issuance: November 10, 1987 Date amended April 20, 1989

FAA FORM 8110-2 (5/14) PAGE 1 OF 4 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

United States of America Department of Transportation - Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number SA4142NM

Fifty-Ten-Yankee, LLC Issued: November 10, 1987 Reissued: May 4, 1993; December 2, 2004; October 7, 2019; May 14, 2020; June 25, 2020 Amended: April 20, 1989

The limitations and conditions shown on Type Certificate Data Sheet Number 3A15, as modified by Supplemental Type Certificate Number SA3523NM, remain applicable except for the following list of limitations and conditions applicable to this modification.

Serial Numbers Eligible: The following Beech A36 and A36TC serial number airplanes are eligible when modified in accordance with Supplemental Type Certificate Number SA3523NM:

A36: E-1111, #-1241, and after A36TC: EA-1 through EA-241, EA-243 and after

Required Equipment: Equipment described in Supplemental Type Certificate SA3523NM are required to be on the aircraft except as modified by this STC. Other items of required equipment are listed in the FAA Approved Flight Manual Supplement for this STC. See Note 4.

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

a.) The applicable Beech A36 or A36TC Airplane Flight Manual plus FAA Approved Airplane Flight Manual Supplements for this STC and STC SA3523NM.

b.) Current weight and balance report including a list of equipment included in the certified empty weight.

The empty weight and center of gravity of the airplane shall be determined by actual weighing after modification prior to return to service.

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 2307 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 for 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 paragraph (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, 23.1017, 23.1019, 23.1027, 23.1041, 23.1043, 23.1045,

23.1091, 23.1093, 23.1103, 23.1005, 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.

FAA FORM 8110-2 (5/14) PAGE 3 OF 4 PAGES

United States of America Department of Transportation - Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number SA4142NM

Fifty-Ten-Yankee, LLC Issued: November 10, 1987 Reissued: May 4, 1993; December 2, 2004; October 7, 2019; May 14, 2020; June 25, 2020 Amended: April 20, 1989 Certification Basis continued:

Part 36 of the Federal Aviation Regulations

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

Note 1: Refer to the FAA Approved Airplane Flight Manual Supplement for required markings and placards.

Note 2: The engine ice protection system consists of an electrically heated propeller, engine bleed air heated compressor front bearing support and inlet guide vanes, exhaust heated engine inlet, and the use of engine continuous ignition and cowl flap. The engine ice protection system must be activated for ground an flight operation in visible moisture at an outside air temperature (OAT) of 5°C (41°F) and be low, or while operating in falling and blowing snow regardless of temperature.

Note 3: The maximum outside air temperature limit is 38°C (100°F) at sea level, with a reduction of 2°C (3.6°F) per 1,000 feet altitude, for all operations. For airplanes with a controllable exhaust air valve that conforms to Soloy Master Drawing List number 886-300 dated March 29, 1989, or later FAA approved revisions, the maximum outside air temperature limit is 47°C (117°F) at sea level, with a reduction of 2°C (3.6°F) per 1,000 feet altitude, for all operations.

Note 4: The applicable FAA Approved Airplane Flight Manual Supplement for this STC is Soloy Publication No.

S1034A for airplanes with the exhaust air valve locked open and S1043A for airplanes with a controllable exhaust air valve.

- END -

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