STC SR12310LA

SR12310LA MD Helicopters, LLC 4555 E. McDowell Road Mesa, AZ 85215 Part 27 Title 14 CFR H3WE MD Helicopters, LLC 500N 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. (continued) 01/15/2025 04/10/2026 for Manager, West Certification Branch 5 Installation of MD Helicopters (MDH), LLC, 530N configuration kit in accordance with FAA approved MDH Master Data List, 500N0200, Revision :-, dated November 25, 2025 or later FAA approved revisions and FAA approved MDH Rotorcraft Flight Manual Supplement, CSP−530N −S1, Revision -, dated April 2, 2026 or later FAA approved revisions.

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SR12310LA 04/10/2026 Limitations and Conditions (Continued):

The approval of this modification applies only to the above noted 500N rotorcraft model series when the Rolls Royce Model 250-C30 engine is installed.

Ratings for Rolls Royce Model 250-C30 Takeoff (5 min) Max. Continuous Shaft Horsepower 425 375 Torque 371 ft. - lb. (59.6 psi) 327.4 ft. - lb.(52.5 psi) Gas Producer rpm, N1 53,550 (105%) 53,550 (105%) Output Shaft rpm, N2 6,016 (100%) 6,016 (100%) Measured Gas Temp. 1,414°F (768°C) 1,281°F (694°C)

Transient Limits for 250-C30 Measured Gas Temp. (12 sec. limit) 1,414°F (768°C) to 1,661°F (905°C) Measured Gas Temp. During Start 1,518°F (826°C) to and Shutdown (10 sec. limit) 1,700°F (927°C) (1 Sec. 1700°F) Gas Producer rpm, N1 (10 Sec. limit) 54,060 (106%) Output Shaft rpm, N2 (10 Sec. limit) 6,407 (106.5%)

Rotor Speed and Engine Operating Speeds for 250-C30:

Power Off (Rotor) Power On (Rotor) Maximum: 508 rpm Maximum: 477 rpm /100 % N2 Minimum: 410 rpm Minimum: 473 rpm / 99% N2 3 5 Add Page

SR12310LA 04/10/2026 Airspeed Limits VNE (Never Exceed Speed) at sea level is 152 knots (175 mph) CAS. For reduction of VNE with altitude and temperature see Rotorcraft Flight Manual. Autorotation VNE at sea level is 130 knots (149 mph) CAS.

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.

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. In addition, height velocity testing is required to 7000 feet, in accordance with paragraphs 6.111 and 6.116, as amended by Amendment 6-7, issued October 8, 1963.

14 CFR Part 36, amendments 36-1 through 36-18, Appendix J.

SR12310LA 04/10/2026

FAA Accepted Instructions for Continued Airworthiness, CSP-107-ICA, Revision -, dated January 28, 2026, or later FAA Accepted revisions must be made available to the operator at the time of installation.

Rotorcraft Flight Manual Supplement, CSP-530N-S1, Revision -, dated April 2, 2026, or later FAA revisions must be made available to the operator.

A copy of this Certificate, dated April 10, 2026 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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