MH-139 Rotor Brake

This Request for Information (RFI) is issued for informational and market research purposes only in accordance with Federal Acquisition Regulation (FAR) Part 10. It does not constitute a solicitation, a Request for Proposal (RFP), or a promise to issue an RFP in the future. The Government will not reimburse any company or individual for expenses associated with preparing or submitting information in response to this RFI. The information provided may be used by the U.S. Air Force in developing its acquisition strategy, Statement of Work (SOW), and performance specifications. Interested parties are responsible for adequately marking proprietary or competition-sensitive information.

BACKGROUND AND SCOPE The Air Force Life Cycle Management Center (AFLCMC), MH-139A Program Office (AFLCMC/WIH), is conducting market research to identify sources capable of designing, integrating, and testing a rotor brake for the MH-139A. The

objective of this effort is to integrate a rotor brake system on the MH-139A to support safe and efficient ground operations, particularly in high-wind environments. The addition of a rotor brake capability will optimize ground turn-around times, facilitate rapid refueling operations, reduce rotor system wear, and enhance overall ground safety for aircrew and support personnel. To meet this requirement, the Government intends to leverage the commercial baseline rotor brake system developed for the Leonardo AW139 (the commercial variant of the MH-139A). Technical support is expected during the initial implementation and testing of the new configuration. Subject matter expert support is expected for a period after initial implementation and testing. Key

requirements for the modified system include: Procurement & Installation: The

objective is to procure and install the commercial baseline Rotor Brake (e.g., P/N 3G6351F00113 per AW139 RFM Rev 27 Sup 1). Standardization: Installation must be standardized across all configurations of the MH-139A fleet. Systems & Software Integration: The installation must safely interface with the aircraft's existing avionics, hydraulic systems, and engine controls. This includes all necessary software interlocks (e.g., within the Operational Flight Program [OFP], Crew Alerting System [CAS], and Full Authority Digital Engine Control [FADEC]) to prevent inadvertent engagement during flight or high-power ground operations. Airworthiness & Structural Integrity: Follow all applicable Federal Aviation Administration (FAA) and MIL-HDBK-516C guidelines. The vendor must account for the added weight and vibration characteristics of the rotor brake assembly to ensure it does not negatively impact the fatigue life or structural limits of the transmission/main gearbox deck. Support & Fit-Testing: Provide technical support during initial installation and testing. The Government will provide scheduled access at a Government-designated facility for fit-checks. The contractor must provide all hardware required for fit-checks. The Government will not provide any Furnished Equipment (GFE). Certification & Airworthiness Pathway: Ability to deliver the complete engineering data package necessary to obtain an FAA-approved Supplemental Type Certificate (STC) and support a military Engineering Change Proposal (ECP). Certification Experience: Describe your company's process, timeline, and prior experience in executing ECPs and obtaining FAA STCs for dynamic/drive system modifications on vertical lift aircraft. Risk Mitigation: Identify potential engineering challenges (e.g., FADEC integration, dynamic load limits, hydraulic routing) associated with obtaining an FAA-approved STC and supporting a military ECP for this project, and provide recommended strategies to mitigate these risks. INSTRUCTION TO POTENTIAL RESPONDENTS Respondents are encouraged to provide comprehensive responses that demonstrate existing technology, qualifications, and experience. Please structure your response to address the following sections:

A. Company Information: Company Name, Address, CAGE Code, and Website URL.