STC SA5968NM

Un ited S tates of Am erica Department of Transportation - Federal Aviation Administration Supplemental Type Certificate

Number SA5968NM

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-31-325

Description of the Type Design Change: Vortex generators manufactured in accordance with Document AA1150, Revision A, dated June 04, 1993, and installed in accordance with Document AA1151, Revision A, dated June 04, 1993, or later FAA-approved revision.

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 o ther previously approved modifications are incorporated unless it is determined that the relationship between this change and any of the 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) dated July 06, 1993, or later FAA-approved revision, must be maintained as part of the permanent records for the modified aircraft.

(See Continuation Sheets on Pages 3 and 4)

Date of application: January 5, 1993 Date reissued: November 23, 2009; August 23, 2018 Date of issuance: July 7, 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)

Un ited S tates of Am erica Department of Transportation - Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet)

Number SA5968NM

BLR Aerospace, LLC Issued: July 07, 1993 Reissued: November 23, 2009; August 23, 2018

This continuation sheet, which is part of STC SA5968NM, prescribes the conditions and limitations under which the product for which the STC was issued meets the standards for airworthiness of the Federa l Aviation Regulations.

The conditions and limitations of Type Certificate Data Sheet Number A20SO apply except where superseded by the following: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.

Engine Limits: Maximum Take-off Power Maximum of 3 minutes except in emergency.

2575 RPM, 49.0 inches Hg manifold pressure below 14,000 feet MSL.

Reduce manifold pressure by 1.6 inches for every 1000 feet of altitude above 14,000 feet MSL up to maximum operating altitude of 24,000 feet MSL.

Maximum Continuous Power 2400 RPM, 39.5 inches Hg manifold pressure below 19,700 feet MSL.

Reduce manifold pressure by 1.6 inches for every 1000 feet of altitude above 19,700 feet MSL up to maximum operating altitude of 24,000 feet MSL.

Airspeed Indicator Normal operating range (green arc) ................................... 77 to 183 knots Markings (IAS): Flaps operating range (white arc) ...................................... 71 to 127 knots Best single-engine rate-of-climb speed (blue radial) ......... 98 knots.

(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 SA5968NM

BLR Aerospace, LLC Issued: July 07, 1993 Reissued: November 23, 2009; August 23, 2018

Maximum Weights: Ramp ....................................................... 6770 pounds Takeoff .................................................... 6730 pounds Landing.................................................... 6500 pounds Zero Fuel ................................................. 6200 pounds

CG Range(Landing +137.3 inches to +138.0 inches at ......... 6730 pounds Gear Extended): +134.0 inches to +138.0 inches at ......... 6500 pounds +128.5 inches to +138.0 inches at ......... 6000 pounds +121.4 inches to +138.0 inches at ......... 5000 pounds or less Straight line variation between points given

Load Factor Limits Positive maneuvers: ................................ +3.53 (g’s): Negative maneuvers: .............................. -1.41

- END -

FAA FORM 8110-2 (5/14) PAGE 4 OF 4 PAGES