# STC SA01805SE - Type: Supplemental type certificate - Status: Current, Amended - Holder: AeroAcoustics Aircraft Systems Inc., United States - Description: Fabrication of AeroAcoustics Aircraft Systems, Inc. (AASI) Aircraft Payload Extender STOL System - Applied: June 29, 2007 - Status date: October 28, 2016 - Product: Aircraft, Small Airplane - Certification basis: Part 3, Part 21, Part 23, Part 36 - Data sheets: [TCDS A37CE](https://openairdocs.org/tcds/A37CE) - Certificate PDF: https://openairdocs.org/files/sha256/4c/8d/4c8d5493b1a347230a770585c7bdbe879e39d4d57e82d77de20886b6c473c9e3 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/1241527AB71904FE8625805A00724AE8.0001 - DRS record last changed: December 5, 2025 - Page: https://openairdocs.org/stc/SA01805SE ## ADs that name it (0) None. ## Approved models (1) - Cessna Aircraft Company 208B ([TCDS A37CE](https://openairdocs.org/tcds/A37CE)) ## What the certificate says Read from the PDF's text layer, without the form's printed wording; the layout is lost and the order can differ. The PDF is the record. United States of America Department of Transportation - Federal Aviation Administration Supplemental Type Certificate Number SA01805SE This certificate, issued to AeroAcoustics Aircraft Systems, Inc. 9802 29th Avenue West, Hangar B-104 Everett, WA 98204 Part 23 of the Federal Aviation Regulations. Original Product Type Certificate Number: A37CE Make: Textron Aviation, Inc. Model: 208B Description of the Type Design Change: Fabrication of AeroAcoustics Aircraft Systems, Inc. (AASI) Aircraft Payload Extender STOL System, in accordance with AASI Master Drawing List No. AA1977, Revision J, dated July 22, 2016, or later Federal Aviation Administration (FAA) approved revision, and installed in accordance with AASI Installation and Maintenance Manual (ICA) No. AA1976, Revision J, dated March 16, 2016, or later FAA-approved revision. Limitations and Conditions: Approval of this change in type design applies to the above model aircraft only. This approval should not be extended to other aircraft of these models on which other previously approved modifications are incorporated unless it is determined that the relationship between this change and any of those other previously approved modifications, including changes in type design, will introduce no adverse effect upon the airworthiness of that aircraft. This installation must be maintained in accordance with Section 3.0 of AASI ICA and operated in accordance with the Pilot’s Operating Handbook and FAA-Approved Aircraft Flight Manual Supplement (AFMS) as listed on the continuation sheets of this certificate. A copy of this certificate, the FAA-Approved AFMS, and ICA, must be maintained as part of the permanent records for 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: June 29, 2007 Date reissued: Date of issuance: December 5, 2007 Date amended: 8/10/10; 7/26/11; 7/12/12; 11/22/13; 9/17/14; 8/18/16; 10/28/16 (Signature) Manager, Seattle Aircraft Certification Office (Title) Number SA01805SE AeroAcoustics Aircraft Systems, Inc. Issued: December 5, 2007 Reissued: Amended: 8/10/10; 7/26/11; 7/10/12; 11/22/13; 9/17/14; 8/18/16; 10/28/16 Limitations and Conditions continued: APPLICABILITY: This modification is limited to the following LAND PLANES only: MODEL SERIAL NUMBER ADDITIONAL REQUIREMNTS 208B 208B0001 to 208B0178, 208B0180 to 208B0229 Aircraft must be modified by Cessna Kit SK208-80 (Conversion from 600 SHP to 675 SHP PT6A-114A), or aircraft must be modified by Blackhawk STC SA02357LA or Standard Aero STC SA03393CH 208B 208B0179, 208B0230 to 208B2196, 208B2198 to 208B4999 Aircraft must have the PT6A-114A (675 SHP Engine) or be modified by Blackhawk STC SA02357LA or Standard Aero STC SA03393CH 208B 208B0001 to 208B1999 excluding 208B1190 and 208B1216 Aircraft must be modified by Blackhawk STC SA02546LA 208B 208B2197, 208B5000 and up Aircraft listed with the PT6A-140 (867 SHP), No additional requirements COMPATABILITY: This Aircraft Payload Extender STOL System STC has been shown compatible with Blackhawk Modifications Inc. (Blackhawk) engine conversion STC SA02357LA and SA02546LA and the Standard Aero Engine conversion STC SA03393CH. AASI Appendix 1 (Document AFMS-C208-43 APP 1), Appendix 2 (Document AFMS-C208-43 APP 2) and Appendix 3 (Document AFMS-C208-43 APP 3) supplements are not compatible with the Blackhawk STC SA02357LA. APPROVED AIRCRAFT FLIGHT MANUAL SUPPLEMENTS: SN 208B0001 to 208B2196, and 208B2198 to 208B4999, and aircraft modified by Cessna Kit SK208-80 Required Flight Manual Aircraft with PT6A-114A (675 SHP engine): AFMS, Document No. AFMS-C208-43, Revision F, dated June 22, 2012, or later FAA approved revision Option (Incorporated): AFMS Appendix 1 “Aircraft Payload Extender STOL System and Approved Standard Size Main Landing Gear Tires” incorporated. Document No. AFMS-C208-43 APP 1, Revision IR, dated July 21, 2010, or later FAA-approved revision Appendix Intermix Applicability: None AFMS Appendix 2 “Aircraft Payload Extender STOL System with Reduced Maximum Landing Weight” incorporated. Document No. AFMS-C208-43 APP 2, Revision IR, dated June 22, 2012, or later FAA- approved revision Appendix Intermix Applicability: 4 or 7. AFMS Appendix 3 “Aircraft Payload Extender STOL System with Approved Alternate Main Landing Gear Tires” incorporated. Document No. AFMS-C208-43 APP 3, Revision IR, dated September 4, 2014, or later FAA-approved revision Appendix Intermix Applicability: None (See Continuation Sheet Page 4 of 5 Pages) **FAA FORM 8110-2-1 (10-69) PAGE 3 OF 5 PAGES** Number SA01805SE AeroAcoustics Aircraft Systems, Inc. Issued: December 5, 2007 Reissued: Amended: 8/10/10; 7/26/11; 7/10/12; 11/22/13; 9/17/14; 8/18/16; 10/28/16 Limitations and Conditions continued: APPROVED AIRCRAFT FLIGHT MANUAL SUPPLEMENTS (CONTINUED): SN 208B0001 to 208B2196, and 208B2198 to 208B4999, and aircraft modified by Cessna Kit SK208-80 (Continued) AFMS Appendix 4 “Aircraft Payload Extender STOL System and a Pratt & Whitney of Canada PT6A-140 Engine STC SA03393CH” incorporated. Document No. AFMS-C208-43 APP 4, Revision IR, dated August 9, 2016, or later FAA-approved revision. Appendix Intermix Applicability: 2 SN 208B0001 to 208B1999 with Blackhawk STC SA02546LA excluding 208B1190 and 208B1216 AFMS Appendix 7 “Aircraft Payload Extender STOL System and a Pratt & Whitney of Canada PT6A-140 Engine STC SA02546LA” incorporated. Document No. AFMS-C208-43 APP 7, Revision IR, dated October 18, 2016, or later FAA-approved revision. Appendix Intermix Applicability: 2 SN 208B0001 to 208B2196, and 208B2198 to 208B4999 with Blackhawk STC SA02357LA AFMS, Document No. AFMS-C208-43, Revision F, dated June 22, 2012, or later FAA approved revision superseded by current FAA-Approved Blackhawk AFMS. SN 208B2197, 208B5000 and up Required Flight Manual Aircraft with PT6A-140 (867 SHP engine): AFMS, Document No. AFMS-C208-76, Revision IR, dated November 7, 2013, or later FAA approved revision. Option (Incorporated): AFMS Appendix 1 “Aircraft Payload Extender STOL System and Approved Standard Size Main Landing Gear Tires” incorporated. Document No. AFMS-C208-76, APP 1, Revision IR, dated November 7, 2013, or later FAA-approved revision. AFMS Appendix 2 “Aircraft Payload Extender STOL System with Reduced Maximum Landing Weight” incorporated. Document No. AFMS-C208-76 APP 2, Revision IR, dated November 7, 2013, or later FAA-approved revision. AFMS Appendix 3 “Aircraft Payload Extender STOL System with Approved Alternate Main Landing Gear Tires” incorporated. Document No. AFMS-C208-76, APP 3, Revision IR, dated September 4, 2014, or later FAA-approved revision. Operation per any combination of AFMS Appendix 1, 2, or 3, at the same time is PROHIBITED. INSTALLATION AND MAINTENANCE INSTRUCTIONS (ICA): All serial numbers: This configuration must be installed in accordance with AASI Installation and Maintenance Manual No. AA1976, Revision H, dated January 3, 2013, or later FAA-approved revision. This configuration must be maintained in accordance with Section 3.0 of AASI Installation and Maintenance Manual No. AA1976, Revision H, dated January 3, 2013, or later FAA-approved revision. **FAA FORM 8110-2-1 (10-69) PAGE 4 OF 5 PAGES** Number SA01805SE AeroAcoustics Aircraft Systems, Inc. Issued: December 5, 2007 Reissued: Amended: 8/10/10; 7/26/11; 7/10/12; 11/22/13; 9/17/14; 8/18/16; 10/28/16 Limitations and Conditions continued: INSTALLATION AND MAINTENANCE INSTRUCTIONS (ICA) (CONTINUED): Option (Appendix 2 Incorporated): This configuration must be maintained in accordance with Section 3.0 of AASI Installation and Maintenance Manual No. AA1976, Revision H, dated January 3, 2013, and Maintenance Manual Addendum No. AA1976A, Revision A, dated January 3, 2013, or later FAA-approved revision. Option (Appendix 3 Incorporated): This configuration must be maintained in accordance with Section 3.0 of AASI Installation and Maintenance Manual No. AA1976, Revision I, dated June 25, 2014, and Maintenance Manual Addendum No. AA1976B, Revision IR, dated May 22, 2014, or later FAA-approved revision. LIMITATIONS PERTAINING TO ALL ELIGIBLE MODELS: LIMIT SPEEDS (IAS): Maneuvering Speed at 9062 lb, 143 KIAS LIMIT FACTORS (g’s): Flaps up: +3.36, -1.34 LIMITS (g’s): Flaps Down (all settings): +2.00 REQUIRED PLACARDS: On each side of nose strut fairing, near tow limit marking: “DO NOT JACK OR TOW THIS AIRCRAFT AT GROSS WEIGHTS ABOVE 8785 LB” Near the airspeed indicator, to overlay the existing airspeed limitation placard: “143 KIAS” CERTIFICATION BASIS: Aircraft serial numbers 208B0001 to 208B4999: For areas affected by change, 14 CFR Part 23, thru amendment 23-51, Except for: 23.143 and 23.145 thru amendment 23-17; 14 CFR Part 36, thru amendment 36-28 Aircraft serial numbers 208B5000 and up: For areas affected by change, 14 CFR Part 23, thru amendment 23-51, Except for: 23.143 and 23.145 thru amendment 23-17; 23.1419 thru amendment 23-14; 14 CFR Part 36, thru amendment 36-28 - END - **FAA FORM 8110-2-1 (10-69) PAGE 5 OF 5 PAGES** ## Every issue (8) - October 28, 2016: Amended, Current. [certificate](https://openairdocs.org/files/sha256/4c/8d/4c8d5493b1a347230a770585c7bdbe879e39d4d57e82d77de20886b6c473c9e3) - August 18, 2016: Amended, Historical. [certificate](https://openairdocs.org/files/sha256/83/e7/83e74a64b8d2541f5eb6e7adf4c08d139bd032b0096b2f00821f4983cadaafa5) - September 17, 2014: Amended, Historical. [certificate](https://openairdocs.org/files/sha256/88/ef/88ef88e47b44a8e88b6e90c3a767b93ebd8c27b9f2b79d2a4a68c1d6883d0415) - November 22, 2013: Amended, Historical. [certificate](https://openairdocs.org/files/sha256/88/bc/88bc00031549d7b2e5d39a1cd01e8583f566417042e236a16ea9c328409e00eb) - July 10, 2012: Amended, Historical. [certificate](https://openairdocs.org/files/sha256/19/38/193837b781a4b74efc218d9a7092417f65f97720d4c41c8aa6b0d9451b2e9146) - July 26, 2011: Amended, Historical. [certificate](https://openairdocs.org/files/sha256/4d/c4/4dc42e89c2ad085d4457dfd6bda8868c8c1ef38477230f68eb032abe15560e51) - August 10, 2010: Amended, Historical. [certificate](https://openairdocs.org/files/sha256/bb/bd/bbbd2043177dbd7f965c348c65d30827227be7590de71d12958942a11e461933) - December 5, 2007: Issued, Historical. [certificate](https://openairdocs.org/files/sha256/25/46/25467339a902edb9d13d80295b2fd60bf4cb1cc0a749d3482caea4b3f4514c75) --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.