STC SR12192LA

SR12192LA MD Helicopters, LLC 4555 E. McDowell Road Mesa, AZ 85215 Part 27 Title 14, Code of Federal Regulations H3WE MD Helicopters, LLC 369D This installation should not be incorporated in any aircraft unless it is determined that the interrelationship between this installation and any previously approved configuration will not introduce any adverse effect upon the airworthiness of the aircraft. (See continuation Pages 3 through 5.)

08/16/2024 04/21/2026 10/23/2025 for Manager, West Certification Branch 5 Installation of MD Helicopters (MDH), LLC, Super D20B kit in accordance with FAA approved MDH Master Data List, 369D20204, Revision A, dated August 8, 2025 or later FAA approved revisions and FAA approved MDH Rotorcraft Flight Manual Supplement, CSP−D−S1, Revision -, dated October 2, 2025 or later FAA approved revisions.

SR12192LA 04/21/2026 5

SR12192LA 04/21/2026 Limitations and Conditions (Continued):

The approval of this modification applies only to the above noted rotorcraft model series equipped with the Rolls Royce Model 250-C20B engine installed.

Engine Limits Ratings for 250-C20B Takeoff (5 min) Max. Continuous Shaft Horsepower 375 350 Torque 327 ft. - lb. (89.8 psi) 305 ft. - lb.(81.7 psi) Gas Producer rpm, N1 53,519 (105%) 53,519 (105%) Output Shaft rpm, N2 6,016 (100%) 6,016 (100%) Measured Gas Temp. 1,490°F (810°C) 1,360°F (738°C)

Rotor Speed and Engine Operating Speeds for 250-C20B Power Off (Rotor) Power On (Rotor) Maximum: 508 rpm Maximum: 477 rpm/100 % N2 Minimum: 410 rpm Minimum: 473 rpm / 99% N2

Airspeed Limits:

VNE (Never Exceed Speed) at sea level is 156 knots (179 mph) CAS. For reduction of VNE with altitude and temperature: The 369D autorotation VNE at sea level is 134 knots (154 mph) CAS.

SR12192LA 04/21/2026 Limitations and Conditions (Continued):

Center of Gravity (C.G.) Range:

Longitudinal Lateral Gross Weight (lb.) Forward*(Sta.) Aft**(Sta.) Left(in.)*** Right(in.)*** 3350 99 103.3 -3 +3 3100 99 103.3 -3 +3 2600 99 104.8 -3 +3 1700 101.7 107.5 -1.7 +1.7

* Varies linearly between 2600 lbs. and 1700 lbs.

** Varies linearly between 3100 lbs. and 1700 lbs.

*** Varies linearly between 2000 lbs. and 1700 lbs.

NOTE: Facing forward, + indicates right and – indicates left of helicopter centerline.

Maximum Weight: 3,350 lb A current weight and balance report, including a list of equipment included in certificated empty weight and loading instructions, must be provided for each helicopter at the time of original airworthiness certification and at all times thereafter, except in the case of operators having an approved weight control system.

Horizontal Stabilizer Incidence:

7.50° to 8.00° measured relative to a line perpendicular to the main rotor mast centerline.

Certification Basis:

CAR 6 dated December 20, 1956, including Amendments 6-1 through 6-4 and Special Conditions, "Conditions Establishing Compensating Factors Providing an Equivalent Level of Safety Under Civil Air Regulations, Section 6.10, for Light Turbine Powered Helicopters," dated October 2, 1962, as revised February 8, 1966.

SR12192LA 04/21/2026 Limitations and Conditions (Continued):

FAA Accepted Instructions for Continued Airworthiness, CSP−106−ICA, Revision -, dated October 23, 2025, or later FAA Accepted revisions must be made available to the operator at the time of installation.

A copy of this Certificate, dated October 23, 2025 or later FAA Approved revision, 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 must give the other person written evidence of that permission.

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