# STC SH4169NM - Type: Supplemental type certificate - Status: Current, Reissued - Holder: Cert Works, United States - Description: Installation of the Allison Model250-C20R/2 or R/4 engine. - Applied: April 16, 1987 - Status date: August 26, 2020 - Product: Aircraft, Rotorcraft - Certification basis: Part 21 - Data sheets: [TCDS H2SW](https://openairdocs.org/tcds/H2SW) - Certificate PDF: https://openairdocs.org/files/sha256/46/ce/46ce2abddd9adb7751a4924b89b50ded6f5f82ed745b39c05908e09bdc06c0bf - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/4689E833C122E85F862585DE003B86EB.0001 - DRS record last changed: December 6, 2025 - Page: https://openairdocs.org/stc/SH4169NM ## ADs that name it (1) - [AD 95-24-06](https://openairdocs.org/ad/95-24-06): Rfms Changes - Autorotation · Bell Helicopter Textron Canada 206B and 206L with STC SH4169NM or 2 others. Effective Dec 27, 1995. Named in the applicability ## Approved models (1) - Bell Helicopter Textron Canada Limited 206L ([TCDS H2SW](https://openairdocs.org/tcds/H2SW)) ## 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 SH4169NM This certificate, issued to Cert Works 5150 Front Range Parkway Watkins, CO 80137 Part 6 of the Civil Air Regulations. Original ProductType Certificate Number: H2SW Make: Bell Model: 206L Description of the Type Design Change: Installation of the Allison model 250-C20R/2 or R/4 engine in accordance with FAA sealed Soloy, LLC Master Drawing List No. 680-300, dated November 25, 1987, and Advance Drawing List Revision, dated December 18, 1987, or later FAA approved revisions. Limitations and Conditions: Approval of this change in type design applies to the aircraft only. This approval should not be extended to other aircraft of these models on which other previously approved modifications are incorporated unless it is determined by the installer that the relationship between this change and other previously approved modifications will introduce no adverse effect upon the airworthiness of that aircraft. A copy of this certificate and Continuation Sheets must be maintained as part of the permanent records for 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. Date of application: April 16, 1987 Date reissued August 25, 1995; December 28, 2006; May 31, 2012; August 26, 2020 Date of issuance: January 29, 1988 Date amended February 21, 1992 FAA FORM 8110-2 (5/14) PAGE 1 OF 5 PAGES By direction of the Administrator (Signature) For Manager, Seattle ACO Branch (Title) Transfer the ownership of Supplemental Type Certificate Number to (Name of Transferee) (Address of Transferee) (Number and Street) (City, State, and ZIP Code) from (Name of Grantor) (Print or Type) (Address of Grantor) (Number and Street) (City, State, and ZIP Code) Signature of Grantor (In Ink): U.S. GPO: 1987-763-289 Number SH4169NM Cert Works Date of issuance: January 29, 1988 Reissued: August 25, 1995; December 28, 2006; May 31, 2012; August 26, 2020 Amended: February 21, 1992 Limitations and Conditions: (cont’d) Certain limitations and conditions shown on Type Certification Data Sheet (TCDS) No. H2SW for the Model 206L remain applicable. The following list contains those additional limitations and conditions which have been modified and certain unmodified ones which are listed for clarity: Model: Bell 206L as modified by this STC (normal category rotorcraft) Engine: Rolls-Royce Model 250-C20R/2 or R4 Engine Limits: Power Ratings (Sea Level, ISA) Takeoff – 450 s.h.p. Max. Continuous – 450 s.h.p. Gas Generator Speeds Takeoff – 50537 RPM Max. Continuous – 50537 RPM Exhaust Gas Temperatures Takeoff - 810° C Max. Continuous - 810° C to 843° C (not to exceed 6 seconds) Max. Transient - 810° C to 899° C (not to exceed 12 seconds) (Maximum 3 occurrences per turbine wheel life) Max. Starting - 810° C to 927° C Transmission Limits: Max. Takeoff Power – Torque = 100 percent (420 s.h.p.) Max. Continuous – Torque= 88 percent (370 s.h.p.) Helicopter Limits: Max. Takeoff Power – Torque = 100 percent (420 s.h.p.) Max. Continuous – Torque= 88 percent (370 s.h.p.) Max. Continuous – EGT = 752° C **FAA FORM 8110-2 (5/14) PAGE 3 OF 5 PAGES** Number SH4169NM Cert Works Date of issuance: January 29, 1988 Reissued: August 25, 1995; December 28, 2006; May 31, 2012; August 26, 2020 Amended: February 21, 1992 Limitations and Conditions: (cont’d) Fuel: Normal Fuels MIL-T-5624, Grade JP-4 or JP5 ASTM-D-1655, Jet A, A1, or B; and Arctic Diesel Fuel DF-A (VV-F-800B), Jet A or A1 JP-1 conforming to ASTM D-1655, Jet A or A1 MIL-T-83133, Grade JP-8 Diesel # 1 fuel conforming to ASTM D-1655, Jet A Emergency Fuels MIL-G-5572, any grade, is permitted for a maximum of 6 hours per turbine overhaul period. MIL-G-5572 fuel containing TRICRESYL-PHOSPHATE (TCP) shall not be used. Lubricating Oil: MIL-L-7808G or MIL-L-23699 and subsequent revisions. **FAA FORM 8110-2 (5/14) PAGE 4 OF 5 PAGES** Number SH4169NM Cert Works Date of issuance: January 29, 1988 Reissued: August 25, 1995; December 28, 2006; May 31, 2012; August 26, 2020 Amended: February 21, 1992 Limitations and Conditions: (cont’d) Certification Basis: FAR 21.29 and CAR 6, effective December 20, 1956, Amendments 6-1 through 6-4, CAR 6.307(b) and 6.637 of Amendment 6-5, Special Conditions, dated October 2, 1962, revised February 8, 1966, plus the water/alcohol power augmentation special conditions dated November 14, 1967, revision September 15, 1975, Special Conditions for “IFR Instrument Flight Requirements for Bell Model 206B/L” submitted by Bell to FAA by letter dated July 16, 1975. Equipment: The basic required equipment as prescribed in the applicable airworthiness regulations (See Certification Basis) must be installed in the helicopter for certification. In addition, a Soloy, LLC Rotorcraft Flight Manual Supplement (RFMS), dated January 29, 1988, or later FAA approved revision is required. Note 1: Information essential to the proper maintenance of the helicopter is contained in the manufacturer’s maintenance manual provided with each helicopter. Note 2: Takeoff Torque Limit and Maximum Continuous Torque Limit Placards, as specified in the RFMS for this STC, must be placed in the cockpit in plain view of the pilot. -END- **FAA FORM 8110-2 (5/14) PAGE 5 OF 5 PAGES** ## Every issue (3) - August 26, 2020: Reissued, Current. [certificate](https://openairdocs.org/files/sha256/46/ce/46ce2abddd9adb7751a4924b89b50ded6f5f82ed745b39c05908e09bdc06c0bf) - May 31, 2012: Reissued, Historical. [certificate](https://openairdocs.org/files/sha256/77/d9/77d927abd8a30fc722f65a18725328de85114c11dfb533c1a721d566c43d92ff) - December 28, 2006: Amended, Historical. [certificate](https://openairdocs.org/files/sha256/ca/1e/ca1e10b684b8a781840584e5cc5c35265bac9ae74216e7308366ade9dca25213) --- 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.