TH-1H Helicopter Health Usage and Monitoring System (HUMS)

TECHNOLOGY AREAS: Air Platform; Sensors; Information Systems The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with section 3.5 of the Announcement. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. OBJECTIVE: The HUMS must be custom configured for the TH-1H dynamic and structural components. Where feasible, the system will utilize the TH-1H's data bus and any HUMS will be designed to best capture and interface the TH-1H. The solution could be a combination of commercial of the shelf (COTS), newly designed/developed software/hardware, and/or other technologies that best capture the necessary data to comply with the need for live flight data and critical system and vibration data. Data will be recorded to a CVFDR system, recording as many parameters as technically and financially feasible IAW AFI 63-133. Additionally, HUMS should allow real time display of data with common interface to media viewing device for real-time on wing troubleshooting/analysis, also accommodate immediate on-ground download and analysis of crew reported vibrations to rapidly identify if a vibration is actually present. System software will identify which sensor(s) or component(s) is causing vibrations and default will be in inches-per-second (ips) for Rotary fleet standardization. System software will be open architecture modifiable by AETC/58 MXG using/owning agency Vibration Program Management Office. VPMO will have full rights to software for alarm/software tailoring and analysis for health of the fleet feedback. DESCRIPTION: Adding a HUMS system enables the TH-1H aircraft to be in compliance with mandatory AFI guidance, cost savings through mishap prevention, cost savings through reduced maintenance troubleshooting, reduction in unscheduled maintenance, and part-utilization efficiencies. Undetected anomalous vibrations have led to catastrophic failures of systems in-flight leading to increased maintenance downtime, serious mishaps, and loss of aircraft. Data from continuous monitoring serves as a diagnostic aid for time-consuming troubleshooting procedures, parts/system condition assessment, and engineering dispositions. A HUMS enables pinpointing many problems immediately and can monitor the degradation of items to allow for scheduling part inspection, overhauls, or replacement. The emphasis for an AF organically maintained HUMS system will minimize long term sustainment costs of the system, software, and the data analysis capabilities of the HUMS system going forward. Current HUMS systems on similarly sized helicopters include an integrated Cockpit Voice and Flight Data Recorder (CVFDR) which enables compliance with AFI 63-101 and AFI 63-133 aiding future mishap investigations. The HUMS will be able to perform rotor track and balance; assess engine, gearbox and drive-train health (full-time vibration monitoring); and provide data to enable structural usage and fatigue life tracking, and maintenance trending. The HUMS will allow continuous monitoring of critical systems/structure and record flight usage data enabling cross-referencing along a common time stamp/history. PHASE I: PHASE I: Each PHASE I submission will consist of system installation on at least 1(EA) assigned TH-1H aircraft, with follow-on testing of system and supporting software for effectiveness. Goal is to have a minimum of two-three Phase I submissions, in order to properly compete for effectiveness. PHASE II: PHASE II: Following Phase I, assuming positive results, the vendor(s) will pursue a Phase II, in which it will Test and Evaluate system improvements, as well as operational results additional subset of the TH-1H fleet, laying the groundwork for rollout of the system/software to other DoD platforms in the future. Planned Phase II product improvements for testing: Integration with Cockpit Voice Flight Data Recorder (CVFDR), crash resistant recording per DAF customer requirement. Cybersecurity protocols (on wireless data transfer and cloud-based application hosting). Integration with Mx tracking software (lowers load associated with multiple systems). PHASE III DUAL USE APPLICATIONS: PHASE III: Following Phase II, assuming positive results, the vendor will pursue Phase III operational metrics for testing on multiple assigned TH-1H aircraft (up to full fleet of 28): Reduction in Unscheduled Maintenance Improvement in Operational Readiness Change in Total Cost of Ownership REFERENCES: 1. INTEGRATED LIFE CYCLE MANAGEMENT (AFI 63-101); 2. AFI 63-140; 3. MIL-STD-1530 assessing various forms of Aircraft Integrity requirements. KEYWORDS: Health Usage and Monitoring; HUMS; TH-1H; Rotary; vibration monitoring; H-1;