STC SR01647SE

Number SR01647SE

This certificate, issued to Cert Works 5150 Front Range Parkway Watkins, CO 80137

Part 27 of the Federal Aviation Regulations.

Original ProductType Certificate Number: H9EU Make: Airbus Helicopters Model: AS350 B2

Description of the Type Design Change: Installation of Honeywell LTS101-700D-2 engine; manufactured and installed in accordance with Soloy Master Drawing List 900-100, Revision C, dated September 25, 2006 and maintained in accordance with Maintenance & Overhaul Supplement S2021H, Revision 1, dated September, 2006 or later FAA approved revisions.

Limitations and Conditions: Approval of this change in type design applies to the above model rotorcraft only.

This approval should not be extended to other rotorcraft of these models 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 rotorcraft. Compatibility of this modification with previously approved modifications must be determined by the installer. A copy of this Certificate and the FAA-approved Rotorcraft Flight Manual Supplement 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.

Date of application: September 8, 2004 Date reissued August 26, 2020 Date of issuance: February 21, 2006 Date amended September 27, 2006

FAA FORM 8110-2 (5/14) PAGE 1 OF 4 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)

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(City, State, and ZIP Code)

Signature of Grantor (In Ink):

U.S. GPO: 1987-763-289

Number SR01647SE

Cert Works Date of issuance: February 21, 2006 Reissued: August 26, 2020 Amended: September 27, 2006 Limitations and Conditions: (cont’d)

Certain limitations and conditions shown on the Type Certificate Data Sheet No. H9EU for Model AS 350 B2 remain applicable. The following list contains those limitations and conditions which are modified, and certain unmodified ones which are listed for clarity.

Model: AS350B2 Engine: Honeywell LTS101-700D-2 Engine Limits: Power Ratings (Sea Level, ISA) Takeoff (five minutes) 732 s.h.p.

Max. Continuous 650 s.h.p.

Gas Generator Speed, NG (100% = 47,870 RPM) Transient 51,313 RPM (107.2 %) Takeoff Rating 51,026 RPM (106.6 %) Max. Continuous Rating and Below 50,164 RPM (104.8 %) Output Shaft Speed, Npt (100% =6120 RPM = 37,000 Power Turbine RPM) Transient 6780 RPM (110.8 %) Takeoff Rating 6780 RPM (110.8 %) Max. Continuous Rating and Below 6780 RPM (110.8 %)

Note: The takeoff output shaft speed must not be exceeded for more than 30 seconds.

Measured Gas Temperature Limit, MGT: °F (°C) Starting 1731 (944) Transient 1731 (944) Takeoff Rating 1694 (923) Max. Continuous Rating and Below 1553 (845) Note: Transient MGT must not exceed the takeoff steady state limit for more than 30 seconds. Transient limits are not to be used for increased power during normal takeoff.

(See Continuation Sheet Page 4 of 4 Pages) FAA FORM 8110-2 (5/14) PAGE 3 OF 4 PAGES

Number SR01647SE

Cert Works Date of issuance: February 21, 2006 Reissued: August 26, 2020 Amended: September 27, 2006

Limitations and Conditions: (cont’d) Transmission Limits: Airspeed Lower Than 40 Kt Max. Transient Torque (10 sec) 107% Max. Continuous Torque 100% Airspeed Equal to or Higher Than 40 Kt Max. Continuous Torque 94% Helicopter Limits: Same as Transmission Limits Fuel: Refer to Soloy Rotorcraft Flight Manual Supplement S2020H for approved fuels and additive specifications.

Engine Lubricating Oil: MIL-L-7808G OR MIL-L-23699 and subsequent revisions (Mixing of these oils is prohibited) Limitations and Conditions: 14 CFR §§ 21.29 and 14 CFR Part 27 dated February 1, 1965, with Amendments 1 through 10, plus FAA Special Conditions No. 27-29-EU-23, dated August 13, 1977.

Equivalent safety, in lieu of direct compliance, found with respect to 14 CFR §§ 27.1189, Shutoff Means.

14 CFR Part 36 dated July 2, 2004 with Amendments 1 through 25.

Equipment: The basic required equipment as prescribed in the applicable airworthiness regulations (See Certification Basis) must be installed in the helicopter for certification. The equipment must include the FAA Approved Rotorcraft Flight Manual AS-350B2, dated June 8, 1990, and Rotorcraft Flight Manual Supplement S2020H, Revision 1, dated April 6, 2006 or later FAA approved revisions.

Note 1: The rotorcraft must be maintained in accordance with the AS-350B2 Master Servicing Recommendations (MSR), AS350B2/LTS101-700D-2 Maintenance and Overhaul Manual Supplement, S2021H, revision 1, dated September 2006 or later revisions and Airworthiness Limitations. Life limited components and the associated retirement times are presented in the manuals and components must be replaced in accordance therewith.

Note 2: An Ng indicator placard, as specified in the Rotorcraft Flight Manual Supplement, S2020H, for this Supplemental Type Certificate must be in plain view of the pilot.

Note 3: If optional AFS 112000-101 Inlet Air Filter kit is installed, Rotorcraft Flight Manual Supplement S2025H, Revision 0, dated September 25, 2006 must be included with the basic required equipment for the helicopter.

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