In upcoming months, a collaborative effort between NAVAIRSYSCOM (PMA-226), Diagnostic Solutions, Honeywell, and NOETIC, will be underway to expand the capability of AIMS. Such expansions include
Torque System Monitoring, which will provide a secondary means of generating audible overtorque tones in the event of an impending dual-engine overtorque. Also, both torque signal isolation assemblies (TSIA) will be removed, and AIMS will utilize the engine’s 70Hz tachometer or, if installed, AIMS will utilize the speed reference supplied by new torque system.
Engine Performance Monitoring and Alarming, which will eliminate or significantly reduce pilot initiated single and four-point performance checks. This added feature will facilitate a means of real-time monitoring and alarming of engine performance. The aircrew and maintainers will have automated feedback in the event an engine degrades below minimum engine performance specifications due to erosion, salt encrustation, foreign object damage (FOD), internal failure, etc. Furthermore, aircrew will be provided real-time engine performance status via the Control Display Navigation Unit (CDNU).
AU/CDNU Synchronization, which will resolve the rare, but troublesome communication errors between the AU and CDNU after initialization. With this capability, these two components will synchronize on initialization and continue to “share” states.
Stick Position Check, which will provide a means of executing cross wind hover and stick position checks via the CDNU. AIMS will receive the longitudinal stick position via the addition of a triple output CPT, which will be installed as part of the hardware modification. This check will provide a PASS/FAIL status on the CDNU, along with the associated solution, if applicable.
Auto-Rotation Check, which will provide a means of executing autorotation checks via the CDNU. This check will provide a PASS/FAIL status on the CDNU, along with the associated solution, if applicable.
Auxiliary Power Unit (APU) Trigger Removal, which will remove the APU tachometer as an AIMS “monitor” trigger. Once implemented, the amount of faults and alarms generated during troubleshooting evolutions will be substantially reduced.
Trend Check Vibration Sensor Validity, which will test the vibe sensors prior to trend check (Vibsigcheck, #1 HSS, and #2 HSS) data collection. Vibe sensors will be tested prior to trend check data collection in all regimes (Ground, Hover, 120 knots), ensuring data fidelity/accuracy. During the sensor test, if faults are detected, data collection will be halted and a “Sensor Fail” annunciation will be displayed to the aircrew.
Misc Expansion Features: removing engine trim receptacles (NP-600) from the aircraft; placing the entire DC bus on a time delay relay, which will avoid power cycling of the CDNU during power cross-over; installing in-line charge amps in engine bay for high-temp accelerometers (HTA).
