Purchase and installation of Health and Use Monitoring System (HUMS) for Rotary Wing Aircraft

The United States Department of State (DoS), Bureau for International Narcotics and Law Enforcement Affairs, Office of Aviation (INL/A) provides aviation support for, but not limited to, the eradication and interdiction of illicit drugs, training of contractor and host nation personnel, embassy support, movement of personnel and equipment, reconnaissance, personnel recovery, medical evacuation, security of personnel and equipment, and convoy escort.

The DoS INL/A Bureau has identified an immediate requirement for Health and Use Monitoring Systems
(HUMS) on the INL/A fleet consisting of Rotary Wing Aircraft. The intent is to start with the review of the
rotary wing UH-1 single and twin-engine platform but other aircraft within the fleet may be reviewed for implementation of a HUMS system in the future.

HUMS for rotary wing aircraft will provide diagnostic information required for optimum performance using
sensors and embedded diagnostic software to monitor and communicate the health and maintenance needs of the aircraft critical components.

Scope
For the initial effort, the selected contractor must provide the U.S. Department of State, Bureau for International Narcotics and Law Enforcement Affairs, Office of Aviation (DoS INL/A) with the most cost effective solution for adding Health and Use Monitoring Systems (HUMS) to the existing fleet of Rotary Wing (RW) aircraft.

The INL/A RW fleet consists of as many as forty-seven (47) single engine (UH-1HII) aircraft and seventeen
(17) twin-engine (UH-1ST) aircraft operating in various CONUS and OCONUS locations. The ideal HUMS system will possess a Supplemental Type Certificate (STC) for subject aircraft or proven experience on other Bell products and will be designed, packaged, and documented in a manner that accommodates third party installation using detailed instructions after an initial demonstration for installation by the selected contractor on one of each aircraft type at a CONUS operating location.

The desired system functions for rotary wing shall include, but are not limited to the following capabilities:
Ability to perform Rotor Track and Balance
Provide Flight Data Monitoring
Provide Engine Performance Monitoring and Trending Data
Ability to identify or predict when critical components require or may require maintenance
Offer Detailed Exceedance Information
Lightweight System Components, minimizing aircraft weight restrictions
Simple, Intuitive User Interface
Ability to provide diagnostic interface to mission software known as Management Information System (MIS) software
Sustainable for long term use (7+ years)

Tasks / Requirements
The Contractor selected with the most capable HUMS system, shall provide a team to perform a system installation prototype on one UH-1HII and one UH-1ST aircraft at a Central Florida location. Complete post-modification ground and flight-testing to ensure proper system operation and thorough system checks of all disturbed systems. Once all testing is complete, the aircraft will be returned to service. The documentation
package developed for the HUMS integration shall be verified by INL/A and INL/A's prime Contractor
once the prototype installation if verified. Consideration and planning shall be given to necessary revisions and/or upgrades to the Air Wing's Management Information System (MIS) to ensure the MIS software in use at the time of HUMS modification design and implementation is capable of HUMS software information input and/or integration.

The contractor shall include necessary training to INL/A and INL/A's prime Contractor including Quality Control
personnel to ensure a thorough understanding of system functionality, operation, and data collection processes.

Upon successful completion of aircraft modifications, the following documentation shall be delivered to INL/A:
(timelines for final document delivery will be determined prior to contract award however, initial documents
must be supplied upon completion of vendor modifications to ensure system maintainability)
Current Electrical Load Analysis (ELA) updated to correspond to the load changes created by the new
equipment installation.
Electrical Load Analysis documentation and Certificates of Conformance for all structural equipment fabricated and installed in the aircraft.
Test plan and results including operational checks of all newly installed equipment as well as disturbed systems caused by the modifications to include repairs required to return the systems to fully operational status (EMI/EMC and FCC checklists)
Instructions for Continued Airworthiness (ICA)
Flight Manual Supplements
Parts Manual Supplements
Airworthiness Limitations
Drawings and Schematics
Weight and balance analysis
Interface documentation for import and export of system monitoring

Contractor proposed electrical installations and modifications shall be accomplished in accordance with TM
1-1500-323-24-1, Installation and Repair Practices, Aircraft Electric and Electronic Wiring, Aerospace Standard AS50881, Rev (current) and FAA AC 21-99. Structural modifications and/or fabrications shall be accomplished in accordance with AC 43-13-2B, Acceptable Methods, Techniques, and Practices - Aircraft Modifications.

Although the requirements listed include numerous Non-Recurring Engineering (NRE) efforts, the ideal implementation plan will address a multiple-phased approach in which various groups of aircraft (identified by country program) will have the selected Health & Use and Monitoring System installed.
The Contractor shall be responsible for coordinating all personnel travel arrangements with the Contracting Officer and/or U.S. Government (USG) Contracting Officer Representative (COR) to ensure that any aircraft assessment or installation does not affect aircraft availability for Operations. The USG COR will coordinate contractor team access to the facilities where the aircraft are maintained.

Phase I Proof of Concept and delivery is to complete the prototype installation and verification of system integration. Phase II Delivery of the verified documentation of the prototype installation package to allow incorporation into the remaining fleet. Integration of each aircraft with the prototype approved package. The estimated time and tentative schedule for integration and number of aircraft which can be integrated at the same time should be identified. Phase III Hardware would be the kits for a third party to be able to install the Phase I & II equipment and documentation up to the quantities identified in the statement of work. The phase III effort will be contingent on the availability of funding and therefore multi-year rates are requested to allow the Dept. of State to complete this effort.

Contracting Office Address:

US Department of State - AirWing
6767 N. Wickham Road
Melbourne, FL 32940

Primary Point of Contact:

Renee Alexander
Management Analyst
AlexanderRK@state.gov

Michele Coccovizo
Management Analyst
CoccovizzoML@state.gov

Secondary Point of Contact:

Jamie A. Goewey
Contracting Officer
GoeweyJA@state.gov