# STC SR01349LA - Type: Supplemental type certificate - Status: Current, Reissued - Holder: WSH, LLC, United States - Description: Installation of Honeywell (Lycoming) T53-L-13B/-13BA engine to replace General Electric T58-GE-3 engine or T53-L-703 engine to replace Honeywell (Lycoming) T53-L-13B/-13BA engine - Applied: March 29, 2002 - Status date: June 11, 2026 - Product: Aircraft, Rotorcraft - Certification basis: Part 29, Part 21 - Data sheets: [TCDS H12NM](https://openairdocs.org/tcds/H12NM), [TCDS H7NE](https://openairdocs.org/tcds/H7NE) - Certificate PDF: https://openairdocs.org/files/sha256/ea/fd/eafd1a01f9f7f8c4d2bd7d1a41648eff012a3108191cef1beb57f2e11fb62f4d - Approved model list and other attachments: [SR01349LA_AML.pdf](https://openairdocs.org/files/sha256/6d/9a/6d9a33874722bea738a8c52cde2c2f9452fb19e4d21450ef9c8fe54165f34213) - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID171412727920260824134602.0001 - DRS record last changed: August 31, 2026 - Page: https://openairdocs.org/stc/SR01349LA ## ADs that name it (0) None. ## Approved models (5) - Rotorcraft Development Corporation TH-1F ([TCDS H12NM](https://openairdocs.org/tcds/H12NM)) - Rotorcraft Development Corporation UH-1F ([TCDS H12NM](https://openairdocs.org/tcds/H12NM)) - Rotorcraft Development Corporation UH-1P ([TCDS H12NM](https://openairdocs.org/tcds/H12NM)) - Tamarack Helicopters Inc. TH-1F ([TCDS H7NE](https://openairdocs.org/tcds/H7NE)) - Tamarack Helicopters Inc. UH-1F ([TCDS H7NE](https://openairdocs.org/tcds/H7NE)) ## 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. SR01349LA WSH LLC 3255 S. Bodenburg Loop Palmer, AK 99645 Part 29 Title 14 CFR * *See attached Federal Aviation Administration (FAA) Approved Model List (AML) SR01349LA for appoved aircraft models and applicable airworthiness regulations. Approval of this change in type design applies to the rotorcraft models noted on associated AML SR01349LA only. This approval should not be extended to other specific rotorcraft of these model series on which other previously approved modifications are incorporated, unless it is determined that the relationship between this change and any of those other modifications, including changes in the type design, will introduce no adverse effect upon the airworthiness of those rotorcraft. Rotorcraft modified in accordance with this Supplemental Type Certificate must be Operated in accordance with a FAA approved copy of the Rotorcraft Flight Manual Supplement (RFMS), Tamarack Helicopters Inc. TAM015, dated June 1, 2011, or later FAA approved revision. (See Continuation Sheets 3 through 7) 03/29/2002 06/11/2026 07/16/2002 06/01/2011 6 Installation of Honeywell (Lycoming) T53-L-13B/-13BA engine to replace General Electric T58-GE-3 engine or T53-L-703 engine to replace Honeywell (Lycoming) T53-L-13B/ 13BA engine in accordance with Tamarack Helicopters, Inc. Federal Aviation Administration (FAA) approved Master Drawing List TAM016, Revision 1, dated April 26, 2011, or later FAA-approved revision. This modification must be Maintained in accordance with Tamarack Helicopters, Inc. Instructions for Continued Airworthiness (ICA) Manual T53 L 13B/ 703 Lycoming, Revision 1, dated September 15, 2010, or later FAA-approved revision. SR01349LA 06/11/2026 6 SR01349LA 06/11/2026 Limitations and Conditions Continued: A copy of this Certificate, the associated AML SR01349LA, the MDL, the ICA, and the RFMS, must be maintained as part of the permanent records for the modified rotorcraft. 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. Engine Honeywell (Lycoming) T53-L-13B or -13BA Engine Limits Torque Pressure: 50 p.s.i. (See Engine Data Plate for Torque setting) Horsepower: 1,100 h.p. Exhaust Gas Temperature: 400°C to 610°C Continuous 610°C to 625°C 30 Minutes 670°C Maximum (625°C to 675°C 10 second limit for starting and acceleration) (675°C to 760°C 5 second limit for starting and acceleration) Oil Pressure: 25 p.s.i. Minimum 80 to 100 p.s.i. Continuous 100 p.s.i. Maximum Oil Temperature: 93°C Maximum Below 30°C FAT 100°C Maximum Above 30°C FAT (See Note 4) Oil Capacity: 3.8 Gallons (0.8 Gallons unusable) Gas Producer Tachometer (N1): 101.5% Maximum Engine Tachometer (N2): 6000 to 6400 r.p.m. Transient 6400 to 6600 r.p.m. Continuous 6700 r.p.m. Maximum Continuous above 15 p.s.i. torque 6900 r.p.m. Maximum Continuous at 15 p.s.i. torque or less 6900 r.p.m. Maximum Transient (3 seconds) above 15 p.s.i. torque 6900 r.p.m. Maximum Rotor Limits: 294 to 324 r.p.m. Continuous 339 r.p.m. Maximum Fuel: Mil-T-5624 (JP-4) Mil-T-5624G (JP-5) ASTM Type B (Jet B) ASTM Type A-1 (Jet A) Fuel Quantity: 245 Gallons (3.0 Gallons unusable) Airspeed Limits: Consult Rotorcraft Flight Manual Engine: Honeywell (Lycoming) T53-L-703 Engine Limits: Torque Pressure: 50 p.s.i. (See Engine Data Plate for Torque setting) Horsepower: 1,100 h.p. SR01349LA 06/11/2026 Limitations and Conditions Continued: Turbine Gas Temperature: 400°C to 820°C Continuous 820°C to 880°C 30 Minutes 880°C Maximum (880°C to 950°C 5 second limit for starting and acceleration) Oil Pressure: 25 p.s.i. Minimum 80 to 100 p.s.i. Continuous 100 p.s.i. Maximum Oil Temperature: 93°C Maximum Below 30°C FAT 100°C Maximum Above 30°C FAT (See Note 4) Oil Capacity: 3.8 Gallons (0.8 Gallons unusable) Gas Producer Tachometer (N1): 105.8% Maximum Engine Tachometer (N2): 6000 to 6400 r.p.m. Transient 6400 to 6600 r.p.m. Continuous 6700 r.p.m. Maximum Continuous above 15 p.s.i. torque 6900 r.p.m. Maximum Continuous at 15 p.s.i. torque or less 6900 r.p.m. Maximum Transient (3 seconds) above 15 p.s.i. torque 6900 r.p.m. Maximum Rotor Limits: 294 to 324 r.p.m. Continuous 339 r.p.m. Maximum Fuel: Mil-T-5624 (JP-4) Mil-T-5624G (JP-5) ASTM Type B (Jet B) ASTM Type A-1 (Jet A) Fuel Quantity: 245 Gallons (3.0 Gallons unusable) Airspeed Limits: Consult Rotorcraft Flight Manual SR01349LA 06/11/2026 Limitations and Conditions Continued: Certification Basis: See associated AML SR01349LA 14 CFR part 36 through Amendment 23; 14 CFR part 34 through Amendment NOTES: Note 1. The helicopter shall be maintained in accordance with USAF T.O. 1H-1(U)F-2-1, Organizational Maintenance and Inspection program as modified as follows: See Tamarack Helicopters, Inc. Manual No. T53-L-13B/-703 Lycoming, Instructions for Continued Airworthiness for Installation of Lycoming T53-L-13B/BA and T53-L-703 On USAF Model UH-1F, UH-1P & TH-1F Helicopters, Revision 1, dated September 15, 2010, which has been reviewed and accepted by the FTW-AEG. Note 2. The helicopter shall be operated in accordance with USAF T.O. 1H-1(U)F-1 as supplemented by Tamarack Helicopters, Inc. FAA Approved Rotorcraft Flight Manual Supplement, Document No. TAM015. (See associated AML SR01349LA) Note 3. Limited life schedule for the helicopter components is included in the USAF T.O. 1H-(U)F-6 amended as follows: The Honeywell (Lycoming) T53-L-13B and -13BA engines component life limits and overhaul intervals are to be complied with in accordance with Honeywell Service Bulletin T53-L-13B-0020, Revision 3, dated October 25, 2001, or later revision. The Honeywell (Lycoming) T53-L-703 engine component life limits and overhaul intervals are to be complied with in accordance with Honeywell Service Bulletin T53-L-703-0020, Revision 2, dated November 25, 2002, or later revision. The main transmission assembly part number 204-040-016-5 component life limits and overhaul intervals are to be complied with in accordance with U.S. Army TM 55-1520-210-23. Note 4. At ambient temperatures below 30°C and the maximum “Oil In” temperature is 93°C, inspect oil filter when oil temperature exceeds 93°C for more than 10 minutes. At ambient temperatures of 30°C and above a steady state engine “Oil In” temperature of 100°C is acceptable provided the following requirements and limitations are observed: Inspect oil filter after 50 hours of engine operation for excessive accumulation of carbon or metal particles. ---End--- 6 6 Add Page ### SR01349LA_AML.pdf **FEDERAL AVIATION ADMINISTRATION (FAA) APPROVED MODEL LIST (AML) SR01349LA** FOR **INSTALLING HONEYWELL (LYCOMING) T53-L-13B/-BA AND T53-L-703 ENGINES** ISSUE DATE: June 1, 2011 Page 1 of 1 **ITEM AIRCRAFT MAKE** **AIRCRAFT MODEL** **ORIGINAL TC NUMBER** **CERTIFICATION** **BASIS FOR** **ALTERATION** **FAA APPROVED** **AIRCRAFT FLIGHT** **MANUAL SUPPLEMENT** **FAA APPROVED** **MASTER DRAWING LIST** AML AMEND DATE Number Revision* Drawing Revision* **1. TAMARACK** HELICOPTERS, INC UH-1F, TH-1F H7NE 14 CFR PART 29 AMENDMENTS 29-1 THRU 29-47 TAM015 Revision 2, June 1, 2011 TAM016 Revision 1, April 26, 2011 June 1, 2011 2. Rotorcraft Development Corp. UH-1F, UH-1P, TH-IF H12NM 14 CFR PART 29 AMENDMENTS 29-1 THRU 29-47 TAM015 Revision 2, June 1, 2011 TAM016 Revision 1, April 26, 2011 June 1, 2011 * Or later FAA Approved Revision FAA Approved: for Manager, West Certification Branch REISSUED: June 1, 2011; June 10, 2026 ## Every issue (2) - June 11, 2026: Reissued, Current. [certificate](https://openairdocs.org/files/sha256/ea/fd/eafd1a01f9f7f8c4d2bd7d1a41648eff012a3108191cef1beb57f2e11fb62f4d), [SR01349LA_AML.pdf](https://openairdocs.org/files/sha256/6d/9a/6d9a33874722bea738a8c52cde2c2f9452fb19e4d21450ef9c8fe54165f34213) - June 1, 2011: Amended, Historical. [certificate](https://openairdocs.org/files/sha256/4b/81/4b812f5c699f99bb3516ce73e0ce4f8cf889e6bf3499ed96d1dcb9493f0cbade), [AML SR01349LA.pdf](https://openairdocs.org/files/sha256/11/86/1186c2cdaf29f3e734c8cae07ed3d70b6ad44dc5da9f2492bb26fa498384042e) --- 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.