STC SA04757NY

Tampa, FL, 33067 23 Title 14 Code of Federal Regulations A24CE Textron Aviation, Inc.

B300 & B300C Installation of a Lower-Fuselage Radome with Extended Nose & updated ECS in accordance with (1) Master Data List (MDL) R300Z016 Rev A, dated October 21, 2025, or later FAA approved revision. (2) Instructions for Continued Airworthiness (ICA) ICA3001 Rev IR, dated October 31, 2024, or later FAA accepted revision, shall be made availble to the operator at the time of installation and be incorporated into the operator's maintenance program. (3) Airplane Flight Manual Supplement (AFMS) F3000001 Rev IR, dated October 02, 2025, or later FAA approved revisions, is required and must be carried during all flights.

(1) The installer must determine whether this design change is compatible with previously approved modifications.

(2) If the holder agrees to permit another person to use the certificate to alter the product, the holder must give the other person written evidence of that permission.

(Limitations and Conditions Continued on Page 3 of 4) 11/3/23 10/23/25 ODA administrator, ODA-834634-NE 4

(3) This STC is applicable to all serial numbers for Textron Aviation Inc. B300/B300C with the following prerequisite STC's installed:

STC SA03525NY, Installation of the Model MTV-27-1-E-C-F-R(P)/CFR260-65() 5 bladed constant speed and reversing propellers.

STC SA03343CH, Extended Range Fuel Tanks.

STC SA01535WI-D, Installation of the Garmin G1000 Integrated Avionics System and GFC 700 Automatic Flight Control System and optional Electronic Stability and Protection (ESP).

STC SA8986SW, Installation of full turning contoured engine exhaust stacks on Pratt & Whitney Canada PT6A-38, PT6A-41, or PT6A-42 engines.

STC SA03342CH, Operating Weight Increase.

STC SA01902WI, Installation of Fuselage Underside Rail Mounting Provisions for Carriage of External Payload.

STC SA4175NM, Installation fully enclosed main landing gear door system for high-flotation gear equipped aircraft.

Certification Basis:

Based on 14 CFR § 21.115 and § 21.101, and FAA policy for design change that are identified as significant in FAA Order 8110.48, the certification basis for Textron Aviation Inc. Models:

B300 and B300C is as follows:

(1) The type certification basis for parts not changed or not affected by the change is shown on TCDS A24CE.

(2) The Modification certification basis for parts changed or affected by the changed since the reference application date, November 3, 2023, is based on the G-1 Issue paper dated October 16, 2025, as follows:

23.49 (a)(2)(3) (4)(5)(6)(b) amdt 23-62, 23.61(a)(b)(c) amdt 23-62, 23.141 amdt 23-45,

23.147 (a)(c) amdt 23-50, 23.149 (a)(b)(d)(e) amdt 23-50, 23.153 (a)(b)(c)(d) amdt 23-50,

23.157 (a)(2)(b)(1)(2)(4)(c)(2)(d) amdt 23-50, 23.161 (a)(b)(2)(c)(d) amdt 23-50, 23.175 (a)(b)

(2)(c) amdt 23-50, 23.177(a)(b)(d) amdt 23-62, 23.201(a)(b)(c)(d) (f)(1)(2)(5)(6)(7) amdt 23-62, 3 4 Add Page 10/23/25

FAA 8110-2 (10/24) Page ___ of ___ SA04757NY Certification Basis continued: 23.203 (a)(b)(c) (1)(2)(5)(6)(7) amdt 23-62, 23.207 (a)(b)(c)(d)(e) amdt 23-50, 23.233(a)(b)(c) amdt 23-50, 23.251 (a)(b) amdt 23-62, 23.301 (a)(b)(c) amdt 23-48,

23.305 (a)(b) amdt 23-45, 23.321 (a)(b) amdt 23-45, 23.331 (a)(b) amdt 23-42,

23.335 (a)(b)(c)(d) amdt 23-48, 23.337 (a)(b)(c) amdt 23-48, 23.341 amdt 23-48,

23.345 (a)(b)(c)(d) amdt 23-48, 23.347 amdt 23-48, 23.349 (a)(b) amdt 23-48, 23.351 amdt 23-42, 23.421 (a)(b) amdt 23-42, 23.423 (a)(b) amdt 23-42, 23.425 (a)(c)(d) amdt 23-42,

23.427 (a)(b)(c) amdt 23-42, 23.441 (a)(c) amdt 23-42, 23.443 (a)(b)(c) amdt 23-42,

23.445 (a)(b)(c) amdt 23-42, 23.473 (a)(b)(c)(d) (e)(f)(g) amdt 23-48, 23.479 (a)(b)(c)(d) amdt 23-45, 23.485, (a)(b)(c) amdt 23-45, 23.499 (a)(b)(c) amdt 23-48, 23.561 (a)(b)(c)(d)(e) amdt 23-62, 23.571(a) amdt 23-62, 23.607 (b) amdt 23-48, 23.611 amdt 23-48,

23.613 (a)(b)(c)(d)(e) amdt 23-45, 23.621(a)(b)(c)(d) amdt 23-45, 23.773 (a)(2) amdt 23-63,

23.777 (a)(b) amdt 23-62, 23.831 (a)(b) amdt 23-62, 23.853(a)(d)(3)(i)(ii) amdt 23-62,

23.867 (a)(b)(c) amdt 23-49, 23.1163(a)(1)(2)(a)amdt 23-42, 23.1183(a) amdt 23-51, 23.1191(c) amdt 23-51, 23.1309(a)(1)(i) (ii)(3)(4)(b)(3) amdt 23-49, 23.1322(a)(b)(c)(d)(e) amdt 23-43,

23.1351(a) amdt 23-49, 23.1353(h) amdt 23-62, 23.1357 (a)(b)(c)(d) amdt 23-43, 23.1359 amdt 23-49, 23.1431 (a)(b) amdt 23-49, 23.1525 amdt 23-45, 23.1557 (a) amdt 23-45,

23.1581 (a)(b)(1)(c)(d)(f) amdt 23-50, 23.1583 (a)(1)(2)(3)(i)(iii)(c)(1)(2)(4)(5)(6)(d)(f)(h)(i)(k)

(l)(m) amdt 23-50, 23.1585 (a)(1)(2)(3)(5)(i) amdt 23-62, 23.1589 (a)(b) amdt 23-50,

36.1 (a)(2)(b)(c) amdt 36-31, 36.2 (b) amdt 36-24, 36.9 (a) amdt 36-19, 36.501 (a)(2)(c) amdt 36-19, 36.9 (a) amdt 36-19, 36.501 (a)(2)(c) amdt 36-19, 36.1581(a)(2)(c) amdt 36-25, G36.1 amdt 36-16, G36.101 amdt 36-16, G36-103 amdt 36-16 G36.105 amdt 36-24, G36.107 amdt 36-22, G36.109 amdt 36.16, G36-111 amdt 36-27, G36.201 amdt 36-22, G36.203 amdt 36-16 ,G36.301 (b) amdt 36-28, 21.93(b) amdt 21-92.

(3) This alteration has been determined to have no acoustical change per 21.93(b).

(4) Equivalent Level of Safety Findings have been made for the following regulation(s):

§ 23.251 Vibration and buffeting (documented in P&S ELOS Memo ADC-0150-F1.)

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