The FDTU is an LRU designed for use in Mi-17 helicopter, IL-76 and IL-78 aircraft for recording flight data. This LRU operates in parallel with the existing Flight Data Recording System (FDR). The FDTU collects the stream of data from the existing Flight Data Acquisition Unit, decodes and records the same onto a removable compact flash memory (Compact Flash Card). Post flight the CFC is removed from the FDTU and transferred to ‘Ground Station Analysis System’ which hosts the application software, for analysis and reporting.

The TRVWS continuously monitors the tail rotor vibration of a rotary wing aircraft and gives a visual warning when vibration levels exceed preset limits. The unit monitors both the axial and radial vibrations on the tail rotor. This LRU features two warning levels indicated using AMBER and RED lamps in the cockpit. The thresholds for these warnings are preset in the unit. Accordingly, the unit triggers AMBER or RED warning lamp based on the current vibration level. The warnings of the radial and axial channels are ORed together for annunciation. Additionally, analog outputs are provided for recording on the aircraft’s FDR system.

The FDTU is an LRU designed for use in Mi-17 helicopter, IL-76 and IL-78 aircraft for recording flight data. This LRU operates in parallel with the existing Flight Data Recording System (FDR). The FDTU collects the stream of data from the existing Flight Data Acquisition Unit, decodes and records the same onto a removable compact flash memory (Compact Flash Card). Post flight the CFC is removed from the FDTU and transferred to ‘Ground Station Analysis System’ which hosts the application software, for analysis and reporting.

The TRVWS continuously monitors the tail rotor vibration of a rotary wing aircraft and gives a visual warning when vibration levels exceed preset limits. The unit monitors both the axial and radial vibrations on the tail rotor. This LRU features two warning levels indicated using AMBER and RED lamps in the cockpit. The thresholds for these warnings are preset in the unit. Accordingly, the unit triggers AMBER or RED warning lamp based on the current vibration level. The warnings of the radial and axial channels are ORed together for annunciation. Additionally, analog outputs are provided for recording on the aircraft’s FDR system.