# STC SA00047SE - Type: Supplemental type certificate - Status: Current, Reissued - Holder: BLR Aerospace LLC., United States - Description: Vortex generators manufactured and installed. - Applied: October 11, 1994 - Status date: August 23, 2018 - Product: Aircraft, Small Airplane - Certification basis: Part 3, Part 21 - Data sheets: [TCDS A20SO](https://openairdocs.org/tcds/A20SO) - Certificate PDF: https://openairdocs.org/files/sha256/a8/f9/a8f9c22eec928791d4f6e32dfb9c31d6b85a346dbc9ab8447d80cda2b18cd524 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/14E83DF4A1D61EC9862582F7005E2E8C.0001 - DRS record last changed: December 6, 2025 - Page: https://openairdocs.org/stc/SA00047SE ## 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. Un ited S tates of Am erica Department of Transportation - Federal Aviation Administration Supplemental Type Certificate Number SA00047SE 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 AA1187, no revision, dated October 19, 1993, or later Federal Aviation Administration (FAA) approved revision, and installed in accordance with Document BL1130, Revision B, dated September 15, 1993, 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 and the Flight Manual Supplement (FMS) specified on the continuation sheet must be maintained as part of the permanent records for the modified aircraft. (See Continuation Sheets Pages 3 through 5) Date of application: October 11, 1994 Date reissued: November 23, 2009; August 23, 2018 Date of issuance: April 21, 1995 Date amended: March 04, 1996; May 30, 2013 FAA FORM 8110-2 (5/14) PAGE 1 OF 5 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 SA00047SE BLR Aerospace, LLC Issued: April 21, 1995 Reissued: November 23, 2009; August 23, 2018 Amended: March 04, 1996; May 30, 2013 This Continuation Sheet, which is part of Supplemental Type Certificate (STC) SA00047SE, 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 apply except where super seded by the following: 1. The system consists of eighty-six vortex generators on the wing and vertical tail of the airplane and four strakes (two on each nacelle). 2. There may be a maximum combined total of four vortex generators missing from the wing an d/or vertical tail before replacements must be installed. 3. 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. STC Compatibility: This increased gross weight STC has not been shown compatible with any wing extension or winglet modifications and is only valid to the weights specified on this modification. The installer is responsible for assessing the impact of concurrently installed STCs which may affect wing loads, particularly fatigue and static requirements. Additional analysis, FAA approved data, and FAA approved inspections may be needed to meet these requirements. Eligibility: Piper Model PA-31 aircraft with serial numbers 31-2 and on are eligible for this modification provided the aircraft was either originally certified with a maximum landing weight of 6500 pounds or has Piper Kit 763 801 installed. Required Aircraft without wing lockers: Flight Manual Document No. AFMS-NAV-7, Revision “A,” dated January 21, 1994, Supplement: or later FAA-approved revision. Aircraft with wing lockers: Document Number AFMS-NAV-8, Revision “A,” dated January 21, 1994, or later FAA-approved revision. (See Continuation Sheets Pages 4 and 5) **FAA FORM 8110-2 (5/14) PAGE 3 OF 5 PAGES** Un ited S tates of Am erica Department of Transportation - Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number SA00047SE BLR Aerospace, LLC Issued: April 21, 1995 Reissued: November 23, 2009; August 23, 2018 Amended: March 04, 1996; May 30, 2013 Engine Limits: Maximum Take-off Power (Aircraft serial Maximum of 3 minutes except in emergency. Numbers 31-2 2575 RPM, 43 inches Hg manifold pressure below 15,000 feet MSL. Reduce manifold through 31-751, pressure by 1.6 inches Hg for every 1,000 feet of altitude above 15,000 feet MSL up to equipped with maximum operating altitude of 24,000 feet MSL. TIO-540-A1A, -A1B, -A2A, or Maximum Continuous Power -A2B engines) 2400 RPM, 36.5 inches Hg manifold pressure below 19,000 feet MSL. Reduce manifold pressure by 1.6 inches Hg of every 1,000 feet of altitude above 19,000 feet MSL up to maximum operating altitude of 24,000 feet MSL. Engine Limits: Maximum Take-off Power (Aircraft serial Maximum of 3 minutes except in emergency. numbers 31-712 2575 RPM, 46 inches Hg manifold pressure below 15,800 feet MSL. Reduce manifold and on, equipped pressure by 1.6 inches Hg for every 1,000 feet of altitude above 15,800 feet MSL up to with TIO-540-A2C maximum operating altitude of 24,000 feet MSL. engines) Maximum Continuous Power 2400 RPM, 39.5 inches Hg manifold pressure below 19,700 feet MSL. Reduce manifold pressure by 1.6 inches Hg for every 1,000 feet of altitude above 19,700 feet MSL up to maximum operating altitude of 24,000 feet MSL. Airspeed Indicator Aircraft without wing lockers: Markings (IAS): Normal Operating Range (green arc) ......................... 78 to 188 knots Flaps Operating Range (white arc) ............................ 71 to 140 knots Best Single-Engine Rate-of-Climb Speed (blue radial) 97 knots Aircraft with wing lockers: Normal Operating Range (green arc) ......................... 77 to 188 knots Flaps Operating Range (white arc) ............................ 71 to 140 knots Best Single-Engine Rate-of-Climb Speed (blue radial) 100 knots **FAA FORM 8110-2 (5/14) PAGE 4 OF 5 PAGES** Un ited S tates of Am erica Department of Transportation - Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number SA00047SE BLR Aerospace, LLC Issued: April 21, 1995 Reissued: November 23, 2009; August 23, 2018 Amended: March 04, 1996; May 30, 2013 Maximum Weights: Aircraft without wing lockers: Ramp .......................................................................... 6880 pounds Takeoff ........................................................................ 6840 pounds Landing ....................................................................... 6500 pounds Zero Fuel .................................................................... 6200 pounds Aircraft with wing lockers: Ramp .......................................................................... 6770 pounds Takeoff ........................................................................ 6730 pounds Landing ....................................................................... 6500 pounds Zero Fuel .................................................................... 6200 pounds CG Range Aircraft without wing lockers: (Landing Gear +135.6 inches to +138.0 inches at 6840 pounds Extended): +134.0 inches to +138.0 inches at 6500 pounds +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. Aircraft with wing lockers: +135.1 inches to +138.0 inches at 6730 pounds +134.0 inches to +138.0 inches at 6500 pounds +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. Load Factor Limits Positive Maneuvers: +3.53 (g’s): Negative Maneuvers: -1.41 Required Placards: Change all references to maneuver speed (VP) values on placards to 158 KIAS (182 MPH IAS) - END - **FAA FORM 8110-2 (5/14) PAGE 5 OF 5 PAGES** ## Every issue (3) - August 23, 2018: Reissued, Current. [certificate](https://openairdocs.org/files/sha256/a8/f9/a8f9c22eec928791d4f6e32dfb9c31d6b85a346dbc9ab8447d80cda2b18cd524) - May 30, 2013: Amended, Historical. [certificate](https://openairdocs.org/files/sha256/66/96/66967758c239ec60d5dcbdf6d99f0f23509de25c82cca2ea01377827b0d8a4b7) - November 23, 2009: Reissued, Historical. [certificate](https://openairdocs.org/files/sha256/e7/0d/e70d7d1b0ea8a2e91e6468b12bd810f938808b378d84bc3c1c219eab80521911) --- 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.