# STC SA00037SE - Type: Supplemental type certificate - Status: Current, Reissued - Holder: BLR Aerospace LLC, United States - Description: Installation of vortex generator(s) - 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/a1/a3/a1a361f155ae5d82e6e9355de3626586c63ecc50456fc77018b266fdcf615936 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID196251226820231031200831.0001 - DRS record last changed: December 5, 2025 - Page: https://openairdocs.org/stc/SA00037SE ## ADs that name it (0) None. ## Approved models (1) - Piper Aircraft Inc. PA-31 ([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 SA00037SE 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 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) SA970SO installed. Eligible Serial Numbers: 31-2 and on. 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 (FMS) specified on page 3, must be maintained as part of the permanent records for the modified aircraft. (See Continuation Sheet Page 3 and 4) Date of application: June 30, 1993 Date reissued: November 23, 2009; August 23, 2018 Date of issuance: November 18, 1993 Date amended: FAA FORM 8110-2 (5/14) PAGE 1 OF 4 PAGES By direction of the Administrator (Signature) Manager, Seattle ACO Branch (Title) Number SA00037SE BLR Aerospace, LLC Issued: November 18, 1993 Reissued: November 23, 2009; August 23, 2018 Amended: This continuation sheet, which is part of STC SA00037SE, 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 SA970SO apply except where superseded by the following: The system consists of eighty-six vortex generators on the wing and vertical tail of the airplane 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-NAV-3, dated November 18, 1993, or later FAA-approved revision. (in addition to the supplement required by STC SA970SO) 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 the maximum operating altitude of 24,000 feet MSL. Maximum Continuous Power 2400 RPM, 35.0 inches Hg manifold pressure below 21,100 feet MSL. Reduce manifold pressure by 1.7 inches for every 1000 feet of altitude above 21,100 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 SA00037SE BLR Aerospace, LLC Issued: November 18, 1993 Reissued: November 23, 2009; August 23, 2018 Amended: Airspeed Indicator Normal operating range (green arc) .......................... 78 to 183 knots Markings (IAS): Flaps operating range (white arc) ............................. 71 to 140 knots Caution range (yellow arc) ........................................ 183 to 219 knots Minimum single-engine control speed (red radial) .... 76 knots Best single-engine rate-of-climb speed (blue radial) 108 knots Never exceed speed (red radial) ............................... 219 knots Maximum Weights: Ramp ......................................................................... 6740 pounds Takeoff ...................................................................... 6700 pounds (see loading limitations below) Landing ...................................................................... 6500 pounds Zero Fuel ................................................................... 6200 pounds (Note: Aircraft must have been originally certificated for a maximum landing weight of 6500 pounds, or must have Piper Kit 763 801 installed to be eligible for this modification.) CG Range +136.0 inches to +138.0 inches at 6700 pounds (Landing Gear +134.0 inches to +138.0 inches at 6500 pounds Extended): +128.5 inches to +138.0 inches at 6000 pounds +120.0 inches to +138.0 inches at 4800 pounds or less Straight line variation between points given Loading Limitations: For aircraft with wingtip extensions: a minimum of 5 gallons of fuel per side must be in the outboard auxiliary fuel tanks when operating at weights above 6500 pounds. For aircraft with winglets: a minimum of 10 gallons of fuel per side must be In the outboard auxiliary fuel tanks when operating at weights above 6500 pounds. Load Factor Limits Positive maneuvers: +3.54 (g’s): Negative maneuvers: -1.41 Placards: Change all references to VMCA values on placards to 76 KIAS. Change all references to maneuver speed values on placards to 158 KIAS. - 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/a1/a3/a1a361f155ae5d82e6e9355de3626586c63ecc50456fc77018b266fdcf615936) - November 23, 2009: Reissued, Historical. [certificate](https://openairdocs.org/files/sha256/e8/54/e85483b395c66c3fd5c5d7633d27c230db6316de985d9ea93875286e22afd0e6) --- 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.