# STC SA05761NM - Type: Supplemental type certificate - Status: Current, Reissued - Holder: BLR Aerospace LLC., United States - Description: Vortex generators generator kit manufactured - Applied: July 10, 1992 - Status date: November 23, 2009 - Product: Aircraft, Large Multi-Engine - Certification basis: Part 21, Part 23 - Data sheets: [TCDS A12CE](https://openairdocs.org/tcds/A12CE) - Certificate PDF: https://openairdocs.org/files/sha256/74/bb/74bbab614c55d503d62314bcf6d8795eea23f717f1d3e966f3cf839b1c13d5c6 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/73FB843EB599EDA7862576800075F379.0001 - DRS record last changed: December 6, 2025 - Page: https://openairdocs.org/stc/SA05761NM ## ADs that name it (0) None. ## Approved models (3) - Hawker Beechcraft Corporation 60 ([TCDS A12CE](https://openairdocs.org/tcds/A12CE)) - Hawker Beechcraft Corporation A60 ([TCDS A12CE](https://openairdocs.org/tcds/A12CE)) - Hawker Beechcraft Corporation B60 ([TCDS A12CE](https://openairdocs.org/tcds/A12CE)) ## 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. Number SA05761NM This certificate, issued to: BLR Aerospace, LLC 3102 100th Street SW Everett, WA 98204 Part 23 of the Federal Aviation Regulations. Original ProductType Certificate Number: A12CE Make: Beech Model: 60, A60, and B60 Description of the Type Design Change: Vortex generators generator kit manufactured in accordance with Document Number AA1101, no revision, dated August 17, 1992, and installed in accordance with Document Number AA1102, no revision, dated August 17, 1992, using option three as specified in that document, or later FAA-approved revisions. 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 this model 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. A copy of this Certificate, Continuation Sheet, and the approved Flight Manual Supplement (FMS), dated August 20, 1992, or later FAA-approved revision, must be maintained as part of the permanent records for the modified aircraft. (See Continuation Sheet on Page 3).. Date of application: July 10, 1992 Date reissued: November 23, 2009 Date of issuance: August 25, 1992 Date amended: **FAA FORM 8110-2-1 (10-69) PAGE 1 OF 3 PAGES** (Signature) Acting Manager, Seattle Aircraft Certification Office (Title) Number SA05761NM BLR Aerospace, LLC Issued: August 25, 1992 Reissued: November 23, 2009 This Continuation Sheet, which is part of STC SA5761NM, prescribes the conditions and limitations under which the product for which the STC was issued meets the airworthiness requirements of the Federal Aviation Regulations. The conditions and limitations of the Type Certificate Data Sheet No. A12CE apply except where superseded by the following: The modification approved in this STC may only be installed on aircraft which were originally certified for a maximum landing weight of 6775 pounds. (Refer to Type Certificate Data Sheet Number A12CE) The system consists of ninety-eight vortex generators on the wing and vertical tail of the airplane. There may be a maximum combined total of four vortex generators missing from the wing and/or vertical tail before replacements must be installed. If any of the ninety-eight vortex generators are missing, the airplane must be operated within the limitations of the basic airplane flight manual until replacements are installed. Airspeed Indicator Normal operating range (g reen arc)................................... 77 to 207 knots Markings (IAS): Flaps operating range (white arc) (60/A60 series, S/N P-3 thru P246)............................. 69 to 137 knots (B60 series, S/N P247 thru P597) ............................... 69 to 140 knots Single-engine best rate-of-climb speed (blue radial) ......... 111 knots Minimum single-engine control speed (red radial)............. 77 knots Maximum Weights: Takeoff .................................................... 6965 pounds Landing....................................................6775 pounds Zero fuel ..................................................6775 pounds CG Range(Landing +137.8 inches to + 139.2 inches at ...... 6965 pounds Gear Extended): +134.6 Inches to + 139.2 inches at...... 6775 pounds +128.0 inches to +139.2 inches at ...... 5100 pounds or less Straight line variation between points given Placards: Change all references to V MCA values on placards to 77 KIAS. On inside of cabin door: **DO NOT JACK OR TOW THIS AIRCRAFT AT GROSS WEIGHTS ABOVE 6819 POUNDS.** **FOR TAKE-OFF WEIGHTS OVER 6775 POUNDS, ADDITIONAL WEIGHT MUST BE** **ADDED IN FUEL ONLY** - END - **FAA FORM 8110-2-1 (10-69) PAGE 3 OF 3 PAGES** ## Every issue (1) - November 23, 2009: Reissued, Current. [certificate](https://openairdocs.org/files/sha256/74/bb/74bbab614c55d503d62314bcf6d8795eea23f717f1d3e966f3cf839b1c13d5c6) --- 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.