STC SE02769LA

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate FAA Form 8110-2 (4/20) SUPERSEDES PREVIOUS EDITION Page 1 of 4

Number: SE02769LA Blackhawk Modifications, Inc.

30 Birkdale Place Moraga, CA 94556 Part 23 * of the Federal Aviation Regulations. *See Certification Basis on page 4.

Original Product Type Certificate Number: A24CE Make: Textron Aviation, Inc.

Model: B200, B200C

Description of Type Design Change: Replacement of the original Pratt and Whitney PT6A-41 or -42 engines and propellers with Pratt and Whitney PT6A-52 engines and MT Propeller model MTV-27-1-E-C-F-R(P)/ CFR225-55f propellers, installation of Raisbeck Engineering Ram Air Recovery System (RARS) and Raisbeck Engineering Lower Aft Fuselage Strakes in accordance with FAA Approved Installation Instructions 202010-001, Rev. A dated March 4, 2022, or later FAA approved revision. Pilot's Operating Handbook and FAA Approved Airplane Flight Manual Supplement AFMS 202010-07, Rev. IR dated June 23, 2022, or later FAA Approved revisions are required. The Instructions for Continued Airworthiness are contained in Document Number ICA 202010-10, Rev. IR, dated December 2021, or later FAA accepted revisions.

Limitations and Conditions: This approval should not be extended to other specific airplanes of this model series on which other approved modification are incorporated, unless it is determined that the interrelations between this change and any of those other previously approved modifications will introduce no adverse effect upon the airworthiness of the 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. A copy of this STC must be included in the permanent records of each airplane modified in accordance with this STC. (Continued on page 3).

Date of Application: January 27, 2021

Date of Issuance: June 30, 2022 Date Reissued:

Title: Manager, Propulsion Section, Los Angeles ACO Branch

FAA Form 8110-2 (4/20) SUPERSEDES PREVIOUS EDITION Page 2 of 4

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate Number: SE02769LA

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SE02769LA FAA Form 8110-2 (4/20) Page 3 of 4

The following engine and propeller limitations are for reference only.

See prerequisite STCs listed on page 4 for the approved limitations.

Engine Engine Limits Two Pratt & Whitney PT6A-52

The maximum propeller shaft overspeed limit is 110% (2200 RPM) of all ratings. 100% propeller shaft speed is defined as 2000 RPM and is the normal steady state operating limit.

At low altitude and low ambient temperature, the engines may produce more power at takeoff than that for which the airplane has been certificated. Under these conditions the placarded torque meter limitations shall not be exceeded.

Oil Temperatures: Minus 40°C Minimum Starting Minus 40°C to 110°C: Low Idle 0°C to 110°C Takeoff and Maximum Continuous

Propeller and Propeller Limits Two MT-Propeller MTV-27-1-E-C-F-R(P) hubs with MT-Propeller CFR225-55f blades.

Diameter: 88.6 in. (maximum); minimum allowable for repair: 86.6 in. No cutoff is allowed if nickel alloy erosion sheath is installed.

Pitch Settings:

Reverse:

-20° ±1° Feathered: +81° ±1°

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SE02769LA FAA Form 8110-2 (4/20) Page 4 of 4

The following STCs are prerequisites and required to be installed on the aircraft:

- SA10824SC (Installation of P&W PT6A-52 engines)

- SA03209NY (Installation of MT Propeller composite five-blade propellers)

- SA3366NM (Installation of Ram Air Recovery System)

- SA3591NM (Installation of lower aft fuselage strakes)

Certification Basis:

The certification basis for this modification is the same as the basic aircraft as outlined in FAA TCDS A24CE with the following exceptions:

14 CFR part 23 paragraphs: 23.55, 23.57(a)(2),(a)(3),(b) as amended by Amendment 23-34.

14 CFR part 23 paragraphs: 23.1, 23.29, 23.33, 23.45, 23.49, 23.53, 23.63, 23.69, 23.77, 23.141, 23.143, 23.145,

23.147, 23.161, 23.171, 23.173, 23.175, 23.177, 23.181, 23.201, 23.203, 23.207, 23.251, 23.301, 23.303, 23.305,

23.307, 23.337, 23.341, 23.361, 23.363, 23.371, 23.471, 23.473, 23.479, 23.572, 23.601, 23.603, 23.605, 23.627,

23.629, 23.901, 23.903, 23.905, 23.907, 23.925, 23.929, 23.939, 23.951, 23.955, 23.1041, 23.1043, 23.1045,

23.1091, 23.1103, 23.1105, 23.1107, 23.1111, 23.1121, 23.1123, 23.1141, 23.1143, 23.1149, 23.1153, 23.1155,

23.1163, 23.1165, 23.1181, 23.1183, 23.1189, 23.1301, 23.1305, 23.1309, 23.1321, 23.1337, 23.1351, 23.1357,

23.1359, 23.1365, 23.1501, 23.1505, 23.1519, 23.1521, 23.1525, 23.1527, 23.1529, 23.1541, 23.1543, 23.1549,

23.1581, 23.1583, 23.1585, 23.1587 and 23.1589 as amended by Amendment 23-57.

14 CFR part 34 paragraphs: 34.1, 34.2, 34.3, 34.5, 34.6, 34.7, 34.10 and 34.11 as amended by Amendment 34-3.

14 CFR part 36 through amendment 36-31.

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