# STC SR00364SE - Type: Supplemental type certificate - Status: Current, Reissued - Holder: Hillsboro Aviation, Inc., United States - Description: Relocation of pilot instruments and mounting of external load release switch on left seat cyclic control. - Applied: February 5, 1996 - Status date: March 9, 1998 - Product: Aircraft, Rotorcraft - Certification basis: Part 21 - Data sheets: [TCDS H2SW](https://openairdocs.org/tcds/H2SW) - Certificate PDF: https://openairdocs.org/files/sha256/5e/41/5e41004a4afd201cf4abef9befaafce8d32c0f96e3d850bc40b52c199b5c9a9a - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/B5A4C76510880ECD862579AB007411F9.0001 - DRS record last changed: December 6, 2025 - Page: https://openairdocs.org/stc/SR00364SE ## ADs that name it (0) None. ## Approved models (1) - Bell Helicopter Textron (Canada) 206L-1 ([TCDS H2SW](https://openairdocs.org/tcds/H2SW)) ## What the certificate says This is OCR from the scanned FAA certificate. OCR can misread letters and numbers. United States of America Book Department of Transportation Federal Aviation Administration Supplemental Type Certificate Number SRO0364SE This certificate issued to: Hillsboro Aviation, Inc. 3565 NE Cornell Road Hillsboro, OR 97124 Part 6 of the Civil Air Regulation'd Original Product -Type Certificate Number: H2SW Make: Bell Model: 206L-1 Description of Type Design Change: The Pilot-in-Command position is relocated to the left seat, in accordance with Columbia Helicopters, Inc., Drawing List No. 206-1, Revision "A", dated June 20, 1996. NOTE: This STC requires the relocation of the pilot instruments and the mounting of the external load release switch on the left seat cyclic control. The left seat collective pitch control includes: throttle, start button, flight idle release control, engine governor trim switch, water bucket open/close switch and other items. Limitations and Conditions: This approval should not be extended to other aircraft of this model on which other previously approved modifications are incorporated unless it is determined by the installer that the relationship between this change and any of those other previously approved modifications will introduce no adverse effect upon the airworthiness of that aircraft. This determination should include consideration of significant changes in weight distribution, such as an increase in the fixed disposable weight in the fuselage. FAA Approved Rotorcraft Flight Manual Supplement (RFMS) No. CHI-206L1-RFMS-2, dated August 9, 1996, or later FAA approved revisions is required. A copy of this Certificate and FAA approved RFMS must be maintained as part of the permanent records for the modified aircraft. Date of Application: February 5, 1996 Date Reissued: March 9, 1998 Date of Issuance: August 9, 1996 Date Amended: EDERAL AVIATION directio! of the Stainis DOMINIST RATIOT Acting Manager, Seattle Aircraft (Signature) Certification Office (Title) or imprisonment not exceeding 3 years, or both. **FAA FORM 8110-2(10-68** ## Every issue (1) - March 9, 1998: Reissued, Current. [certificate](https://openairdocs.org/files/sha256/5e/41/5e41004a4afd201cf4abef9befaafce8d32c0f96e3d850bc40b52c199b5c9a9a) --- 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.