# STC SA01672SE

- Type: Supplemental type certificate
- Status: Current, Amended
- Holder: Northwest Turbine LLC, United States
- Description: Installation of two Pratt & Whitney PT6A-35 engines and two Hartzell HC-E4N-3N/D8292B-2 propellers and associated hardware.
- Applied: December 15, 2000
- Status date: November 20, 2008
- Product: Aircraft, Single-Engine
- Certification basis: Part 21, Part 23, Part 36
- Data sheets: [TCDS A12CE](https://openairdocs.org/tcds/A12CE)
- Certificate PDF: https://openairdocs.org/files/sha256/b0/7a/b07a79b30a5a2c78f0f8d3ee2a4fd629891c6f06486a1638d75b2a76a38e8c0a
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/3EDAF2D74971798986257512007FE844.0001
- DRS record last changed: December 6, 2025
- Page: https://openairdocs.org/stc/SA01672SE

## ADs that name it (0)

None.

## Approved models (1)

- Raytheon Aircraft Company 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.

Number SA01672SE

This certificate, issued to Northwest Turbine LLC E. 6427 Rutter Road, Suite D Spokane, WA 99212

Part 23 of the Federal Aviation Regulations.

Original Product⎯Type Certificate Number: A12CE Make: Raytheon Beech Model: B-60

Description of the Type Design Change: Installation of two Pratt & Whitney PT6A-21 or two Pratt & Whitney PT6A-35 engines, two Hartzell HC-E4N-3N/D8292B-2 propellers and associated hardware in accordance with Rocket Engineering Master Drawing List 600.00.000, Rev H, dated March 31, 2007, or later FAA-approved revision.

Limitations and Conditions: Modification of the above model airplane requires concurrent or prior incorporation of STC SA00370SE (Strakes), STC SA5761NM (Vortex Generators), and STC SA00112SE (Winglets). Airplanes modified in accordance with this STC must be operated in the Normal Category. Airplanes modified in accordance with this STC must be maintained in accordance with Northwest Turbine, LLC document

**600.101.DOC.**

(continued on pages 3, 4, and 5)

Date of application: December 15, 2000 Date reissued:

Date of issuance: May 12, 2006 Date amended: May 11, 2007, November 20, 2008

(Signature)

Acting Manager, Seattle Aircraft Certification Office (Title)

Number SA01672SE

Northwest Turbine, LLC Issued: May 12, 2006 Reissued:

Amended: May 11, 2007, November 20, 2008

Limitations and Conditions: (cont’d)

Additionally, 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, dated November 20, 2008 and the Aircraft Flight Manual Supplement, dated May 12, 2006 or later FAA-approved revision, must be maintained as part of the permanent records of the modified aircraft.

If the holder agrees to permit another person to use this certificate to alter the product, the holder shall give the other person written evidence of that permission.

AIRPLANE LIMITS Altitude Limit ……………………………………………………………….. 28000 ft

Maximum Weights Maximum Ramp Weight…………………………………………………... 7039 Lb Maximum Takeoff Weight ………………………………………………… 7000 Lb Maximum Landing Weight ………………………………………………… 6775Lb Maximum Zero Fuel Weight ………………………………………….…… 5900 Lb

**ENGINE LIMITS**

Number of Engines……………… … 2

Engine Manufacturer………………………………………………….. Pratt & Whitney Engine Model………………….……………………………………..... PT6A-35, or PT6A-21(The same model engine must be installed in both p o s i t i o n s . ) Takeoff Torque (PT6A-21 and PT6A-35)………………………….. 1260 ft-lb @ 2190 RPM Maximum Gas Generator Speed (%) for both PT6A-21 and PT6A-35 Continuous ……………………………………………………………. 101.5 Acceleration (Two second limit) ……….……………………………. 102.6 Reverse ………………………………………………………….…….. 101.5 Maximum Interturbine Temp (ITT, deg C) PT6A-35 PT6A-21 Takeoff …………………………………………………………………. 805 695 Maximum Climb/Maximum Cruise ………….………………………. 770 680 Starting (Two second limit) ………………………………………….. 1090 1090 Acceleration (Two second limit) ……………………………………... 880 825 Reverse ………………………………………………………………… 805 695 Idle………………………………………………………………………. 685 660

**FAA FORM 8110-2- 1 (10-69)**

Number SA01672SE

Northwest Turbine LLC Issued: May 12, 2006 Reissued:

Amended: May 11, 2007, November 20, 2008

Limitations and Conditions: (cont’d)

PROPELLER LIMITS Number of Propellers …………………………………………………. 2 Propeller Manufacturer ………….……………………………………. Hartzell Blade Model ……………………………………………………………. D8292(B)-2 Number of Blades ……………………………………………………... 4 Hub Model ……………………………………………………………… HC-E4N-3N Propeller Diameter (Inches) ………………………………………….. 80.0 Min, 80.5 Max.

FUEL Approved Fuels ……………………………………………………………… JP4, JP5, JET A, JET A-1, JET B Fuel Temperature Limit …………………………………………………….. 100 deg F

Fuel Capacity (U.S. Gallons) T o t a l Usable Left Wing Tank 138.4 135.9 Right Wing Tank 132.5 130.0 Totals 270.9 265.9 Total unusable fuel (5 gallons) must be added to the empty weight of the aircraft.

Note 1: The Certification Basis for this modification is FAR Part 23, effective February 1, 1965, as amended by 23-1, 23-2, 23-3, and paragraph 23.959 of Amendment 27. Paragraphs 23.1385(c), 23.1387(a), 23.1387(e) of Amendment 23-12, Part 36, latest Amendment, and special Conditions, dated May 16, 1967 forwarded with FAA letter, dated June 1, 1967.

Additionally the applicant has volunteered compliance with the following:

FAR 23.23, 23.25 23.33, 23.45, 23.49, 23.65, 23.67, 23.77, 23.145, 23.149, 23.155, 23.161, 23.175, 23.177,

23.201, 23.203, 23.231, 23.233, 23.251, 23.253, 23.301, 23.305, 23.307, 23.335, 23.361, 23.363, 23.367,

23.371, 23.457, 23.479, 23.572(b)(3), 23.603, 23.627, 23.629(e), 23.629(f), 23.735(b), 23.777(d), 23.781, 23.831,

23.863., 23.865, 23.901, 23.903, 23.905, 23.907, 23.925, 23.929, 23.933, 23.937, 23.939, 23.943, 23.951,

23.953, 23.955, 23.959, 23.961, 23.965, 23.967, 23.973, 23.967(a)(5), 23.977, 23.991, 23.993, 23.994, 23.995,

23.997, 23.1011, 23.1013, 23.1015, 23.1017, 23.1019, 23.1021, 23.1023, 23.1027, 23.1041, 23.1043, 23.1045,

23.1091, 23.1093, 23.1103, 23.1111, 23.1121, 23.1123, 23.1141, 23.1143, 23.1145, 23.1149, 23.1153, 23.1155,

23.1163, 23.1165, 23.1181, 23.1182, 23.1183, 23.1189, 23.1191, 23.1193, 23.1203, 23.1301, 23.1303, 23.1305,

23.1309, 23.1321, 23.1322, 23.1329, 23.1337, 23.1351, 23.1353, 23.1357, 23.1438, 23.1501, 23.1505, 23.1521,

23.1527, 23.1529, 23.1545, 23.1549, 23.1551, 23.1555, 23.1557, 23.1583, 23.1585, 23.1587, at the amendment levels in effect on December 15, 2000, the date of application.

**FAA FORM 8110-2- 1 (10-69)**

Number SA01672SE

Northwest Turbine LLC Issued: May 12, 2006 Reissued:

Amended: May 11, 2007, November 20, 2008

Limitations and Conditions: (cont’d)

Note 2: This airplane/engine/propeller combination is life limited. Incorporation of this STC does not affect that life limit.

Note 3: Aircraft modified in accordance with this Supplemental Type Certificate have been shown by test to comply with the requirements of FAR Part 36 Appendix G.

- END-

**FAA FORM 8110-2- 1 (10-69)**

## Every issue (2)

- November 20, 2008: Amended, Current. [certificate](https://openairdocs.org/files/sha256/b0/7a/b07a79b30a5a2c78f0f8d3ee2a4fd629891c6f06486a1638d75b2a76a38e8c0a)
- May 12, 2006: Issued, Historical. [certificate](https://openairdocs.org/files/sha256/f4/89/f489dd367293c1059b86b247a8c7889e4f641e253af05e0e85282c0c42837365)

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