# STC SA00039SE - Type: Supplemental type certificate - Status: Current, Reissued - Holder: BLR Aerospace LLC, United States - Description: Vortex generators manufactured and installed. (T-1020) - Applied: June 30, 1993 - Status date: August 23, 2018 - Product: Aircraft, Small Airplane - Data sheets: [TCDS A20SO](https://openairdocs.org/tcds/A20SO) - Certificate PDF: https://openairdocs.org/files/sha256/a7/6f/a76f946211bb4118298a5fe85d7a19061f929c2e9558e702c5cc8bb8444c4a90 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID167901550820231031201258.0001 - DRS record last changed: December 5, 2025 - Page: https://openairdocs.org/stc/SA00039SE ## ADs that name it (0) None. ## Approved models (1) - Piper Aircraft Inc. PA-31-350 ([TCDS A20SO](https://openairdocs.org/tcds/A20SO)) ## 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 SA00039SE This certificate, issued to BLR Aerospace, LLC 11002 29th Ave. West Everett, WA 98204 Part 3 of the Civil Air Regulations. Original Product⎯Type Certificate Number: A20SO Make: Piper Model: PA-31-350 (T-1020) Description of the Type Design Change: Vortex generators manufactured in accordance with Document AA1161, Revision B, dated November 15, 1993, and installed in accordance with Document BL1162, Revision A, dated August 31, 1993, or later FAA-approved revisions. In order to be eligible for this modification aircraft must have Supplemental Type Certificate (STC) SA1151SO installed. Eligible Serial Numbers: 31-7305001 and on for PA-31-350; 31-8253001 and on for T-1020. 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 sheets, and the Flight Manual Supplement specified on page 3, must be maintained as part of the permanent records for the modified aircraft. (See Continuation Sheets on Pages 3 and 4) Date of application: June 30, 1993 Date reissued: November 23, 2009; August 23, 2018 Date of issuance: November 22, 1993 Date amended: (Signature) Manager, Seattle ACO Branch (Title) Number SA00039SE BLR Aerospace, LLC Issued: November 22, 1993 Reissued: November 23, 2009; August 23, 2018 Amended: This Continuation Sheet, which is part of STC No. SA00039SE, 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 No. A20SO and Supplemental Type Certificate SA1151SO apply except where superseded by the following: The system consists of eighty-six vortex generators on the wing and vertical tail of the airplane, two stall fences (one on each wing), and four strakes (two on each nacelle). 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 eighty-six vortex generators are missing, the airplane must be operated within the limitations of the basic airplane flight manual until replacements are installed. Flight Manual Supplement: Document AFMS-PCH-3, dated November 22, 1993, or later FAA-approved revision. (in addition to the supplement required by STC SA2262SO) Engine Limits: Maximum Take-off Power Maximum of 3 minutes except in emergency. 2575 RPM, 49.0 inches Hg manifold pressure below 15,000 feet MSL. Reduce manifold pressure by 0.64 inches for every 1000 feet of altitude above 15,000 feet MSL up to 22,300 feet MSL. Reduce manifold pressure by an additional 2.2 inches for every 1000 feet of altitude above 22,300 feet MSL up to maximum operating altitude of 24,000 feet MSL. Maximum Continuous Power 2400 RPM, 40.0 inches Hg manifold pressure below 18,700 feet MSL. Reduce manifold pressure by 1.7 inches for every 1000 feet of altitude above 18,700 feet MSL up to maximum operating altitude of 24,000 feet MSL. (See Continuation Sheet on Page 4) **FAA FORM 8110-2 (5/14) PAGE 3 OF 4 PAGES** United States of America Department of Transportation - Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number SA00039SE BLR Aerospace, LLC Issued: November 18, 1993 Reissued: November 23, 2009; August 23, 2018 Amended: Airspeed Indicator Normal Operating Range (green arc) ......................... 73 to 185 knots Markings (IAS): Flaps Operating Range (white arc) ............................ 68 to 132 knots Caution Range (yellow arc) ........................................ 185 to 226 knots Never Exceed Speed (red radial) ............................... 226 knots Maximum Weights: Ramp .......................................................................... 7245 pounds Takeoff ........................................................................ 7200 pounds Landing ....................................................................... 7000 pounds Zero Fuel .................................................................... 7000 pounds CG Range +130.4 inches to +135.0 inches at 7200 pounds (Landing Gear +126.0 inches to +135.0 inches at 7000 pounds Extended): +122.0 inches to +135.0 inches at 6200 pounds +120.0 inches to +135.0 inches at 5200 pounds or less Straight line variation between points given. Load Factor Limits Positive Maneuvers: .......................... +3.50 (g’s): Negative Maneuvers ......................... -1.40 - 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/a7/6f/a76f946211bb4118298a5fe85d7a19061f929c2e9558e702c5cc8bb8444c4a90) - November 23, 2009: Issued, Historical. [certificate](https://openairdocs.org/files/sha256/7e/73/7e7368ea88c54cdba07709c87cfc8d48ff4f0674665f3fc0ae328ae0c56d3e58) --- 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.