STC SA02741SE

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SA02741SE Raisbeck Engineering, Inc.

2811 South 102nd Street, Suite 100 Tukwila, WA 98168 23 Title 14, Code of Federal Regulations A37CE Textron Aviation, Inc.

208B Configuration A: Installation of Raisbeck Engineering Drag Reduction System in accordance with Installation Manual document 19CS-3253-053 Revision B or later FAA-approved revision and Master Drawing List document 19CS-3253-052 Revision IR or later FAA-approved revision; Operated in accordance with Aircraft Flight Manual Supplement document 19-208-106 Revision IR or later FAA-approved revision; and maintained in accordance with Maintenance Manual Supplement document 19-120 Revision B or later FAA-accepted revision. See Continuation sheet 3 of 4

1. Configurations A and B: Approval of this change in type design applies to the above model aircraft, Serial Numbers 208B0001 through 208B0178 and 208B0180 through 208B0229 when modified by Cessna Kit SK208-80 (Conversion from 600 SHP to 675 SHP PT6A-114A) 208B0179, 208B0230 through 208B2196 and 208B2198 through 208B4999 only. See Continuation sheet 3 of 4 April 19, 2019 July 24, 2023; November 8, 2023; April 5, 2026;

April 22, 2026 April 1, 2022 July 10, 2023; April 4, 2026 ODA administrator ODA-834634-NE 4

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Date oI transfer:

SA02741SE 4

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Description of the Type Design Change, continued:

Configuration B: Installation of Aft Body Strakes in accordance with

(1) Master Data List, Document Number 19CS-3253-052, Revision V, Dated July 7, 2023 or later FAA-approved revision.

(2) Aircraft Maintenance Manual Supplement & Instructions for Continued Airworthiness for Aft Body Strakes, Document Number 19-120-1, Revision IR dated March 7, 2023 or later FAA-accepted revision.

Configurations C and D: Installation of Raisbeck Engineering Drag Reduction System in accordance with (1) Master Data List, Document Number 19CS-3253-052, Revision AD, Dated April 4, 2026 or later FAA-approved revision.

(2) Aircraft Maintenance Manual Supplement & Instructions for Continued Airworthiness for Drag Reduction System, Document Number 19-120-3, Revision A dated Jan 13, 2025 or later FAA-accepted revision.

Limitations and Conditions, continued:

2. Configuration B: This alteration is applicable to Textron Aviation Inc. Model 208B with the PT6A-114A engine and OEM installed Cargo Pod.

3. The installer must determine whether this design change is compatible with previously approved modifications.

4. 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.

5. Configuration C: Is applicable to Textron Aviation Inc., Model 208B with (867SHP) PT6A-140 engine (S/Ns 208B2197, 208B5000 and on).

6. Configuration D: Is applicable to Textron Aviation Inc., Model 208B aircraft (S/N 208B0001 through 208B1999) with TAI Service Kit SK208-165A 300 Amp Generator installed or S/N 208B2000 through 208B2196, 208B2198 through 208B4999 with the OEM NACA Duct installed.

7. Configurations C and D are not applicable to Textron Aviation Inc. Model 208B with the TKS anti-icing system installed.

8. In accordance with FAA Central Certification Branch letter dated April 21, 2026, [Refer to: FAA letter 763-25-00248], this modification is FAA approved as an Alternative Method of Compliance (AMOC) with paragraph(s) (e)(5)(i) and (e)(6) of Airworthiness Directive (AD) 2006-01-11 R1.

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Based on 14 CFR §§ 21.115 and 21.101, and the FAA policy for significant changes in FAA Order 8110-48, the certification basis for all eligible aircraft models is as follows:

(1) The type certification basis for Textron Aviation Inc. Model 208B is shown on TCDS A37CE for parts not changed or not affected by change.

(2) For Configuration A (original STC), certification basis for parts changed or affected by the change since the reference date of the application, April 19, 2019, based upon 14 CFR § 23 is Amendment 23-62.

(3) For Configuration B, the certification basis for parts changed or affected by the change since the reference date of the application, January 27, 2023, is based upon 14 CFR § 23 as amended by amendment 23-62 per 14 CFR § 21.101(b)(1) (original certification basis from TCDS A37CE remained at original FAA approved certification basis for Configuration A), for applicable sections.

(4) For Configurations C and D, certification basis for parts changed or affected by the change since the reference date of the application, November 16, 2023, based upon 14 CFR § 23 is Amendment 23-62.

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