# STC SA00112SE - Type: Supplemental type certificate - Status: Current, Reissued - Holder: BLR Aerospace LLC., United States - Description: System includes vortex generators, winglets, and gross weight increase. - Applied: March 9, 1994 - Status date: August 23, 2018 - Product: Aircraft, Small Multi-Engine - Certification basis: Part 21, Part 23 - Data sheets: [TCDS A12CE](https://openairdocs.org/tcds/A12CE) - Certificate PDF: https://openairdocs.org/files/sha256/39/28/392861032bed52b72f850b403a213c492b6e865ca4a24d4141fefccbd4622870 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/C82ECC42787CBC20862582F7005E335C.0001 - DRS record last changed: December 6, 2025 - Page: https://openairdocs.org/stc/SA00112SE ## 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. Un ited S tates of Am erica Department of Transportation - Federal Aviation Administration Supplemental Type Certificate Number SA00112SE This certificate, issued to BLR Aerospace, LLC 11002 29th Ave. West 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: System includes vortex generators , winglets, and gross weight increase defined by the data listed below or later FAA-approved revisions. Winglets: Manufactured in accordance with Document AA1199, Revision A, dated August 08, 1994. Installed in accordance with Document AA1200, Revision A, dated August 01, 1994. Maintained in accordance with Document AA1203, initial release, dated August 01, 1994. Vortex generators must have been installed in accordance with STC SA5761NM. 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 intro duce no adverse effect upon the airworthiness of that aircraft. A copy of this Certificate, the Continuation Sheets, and FAA -Approved Flight Manual Supplement (FMS) as listed on the continuation sheets, must be maintained as part of the permanent records for the modified aircraft. (See Continuation Sheets on Pages 3 and 4) Date of application: March 09, 1994 Date reissued: November 23, 2009; August 23, 2018 Date of issuance: August 23, 1994 Date amended: FAA FORM 8110-2 (5/14) PAGE 1 OF 4 PAGES By direction of the Administrator (Signature) Manager, Seattle ACO Branch (Title) Un ited S tates of Am erica Department of Transportation - Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number SA00112SE BLR Aerospace, LLC Issued: August 23, 1994 Reissued: November 23, 2009; August 23, 2018 Amended: Limitations and Conditions continued: This Continuation Sheet, which is part of STC SA00112SE, prescribes the conditions and limitations under which the product for which the STC was issued meets the standards for airworthiness of the Federal Aviation Regulations. The conditions and limitations of Type Certificate Data Sheet Number A12CE apply except where superseded by the following: Flight Manual Supplement (FMS) Number AFMS-B60-2 (required by vortex generator STC SA5761NM) must be replaced with AFMS-B60-3, dated August 23, 1994, or later FAA-approved revision when this modification is installed. The modification approved in this STC may only be installed on aircraft which were originally certi fied for a maximum landing weight of 6775 pounds and are equipped with 10 ply rated tires. (Refer to Type Certificate Data Sheet Number A12CE) The system consists of two winglets and 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 Never Exceed Speed (red radial) ................................... 230 knots Markings and Caution Range (yellow arc) ............................................ 199 to 230 knots Airspeed Normal Operating Range (green arc) ............................ 78 to 199 knots Limitations (IAS): Flaps Operating Range (white arc) (60/A60 series, S/N P-3 thru P-246) ........................ 70 to 137 knots (B60 series, S/N P-247 thru P-597) ......................... 70 to 140 knots Single-Engine Best Rate-of-Climb Speed (blue radial) .. 112 knots Minimum Single-Engine Control Speed (red radial) ...... 77 knots Maneuvering Speed (VA) ................................................ 159 knots Maximum Weights: Ramp .............................................................................. 7039 pounds Takeoff ........................................................................... 7000 pounds Landing........................................................................... 6775 pounds Zero Fuel ........................................................................ 6775 pounds (See Continuation Sheet on Page 4).. **FAA FORM 8110-2 (5/14) PAGE 3 OF 4 PAGES** Un ited S tates of Am erica Department of Transportation - Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number SA00112SE BLR Aerospace, LLC Issued: August 23, 1994 Reissued: November 23, 2009; August 23, 2018 Amended: CG Range +138.0 inches to +139.2 inches at 7000 pounds (Landing Gear +134.6 inches to +139.2 inches at 6775 pounds Extended): +128.0 inches to +139.2 inches at 5100 pounds or less Straight line variation between points given. Placards: Change all references to VA values on placards to 159 KIAS. Change all references to VMCA 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 (5/14) PAGE 4 OF 4 PAGES** ## Every issue (2) - August 23, 2018: Reissued, Current. [certificate](https://openairdocs.org/files/sha256/39/28/392861032bed52b72f850b403a213c492b6e865ca4a24d4141fefccbd4622870) - November 23, 2009: Reissued, Historical. [certificate](https://openairdocs.org/files/sha256/3e/76/3e7677d9ea433eb6bfb8a3b62e5f255d19cfe0be6f29b3c1af3cdc968c56bf0a) --- 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.