Aircraft Monitoring System PMS39

PMS39

PMS39 consists of:

  • cockpit unit
    • central measuring and control unit MU39 for data collecting and processing
    • crash data recorder with protected solid-state service and back-up memory ZJ39 where records are written to both memories simultaneously

  • ground unit

    • PMS system testing
    • calibration of sensors of physical quantities on the aircraft
    • the PANDA program system with corresponding configuration of GEE and GSU is designed for monitoring and evaluation of registered PMS flight parameters from the ZJ39 record unit
    • it is possible to read data from ZJ39 either directly to GSU (interface RS-232C) or using the PMU-F (interface RS-422) portable memory unit without dismounting ZJ39
    • harmonic analysis of aircraft engine vibrations

Communication interface:

  • RS-232C
  • RS-422

PMS39 meets the following standards:

  • MIL-STD-461D - electromagnetic compatibility
  • MIL-STD-462D - electromagnetic compatibility
  • MIL-STD-704E - aircraft electric power supply properties
  • MIL-STD-810E - methods of testing external effects and technical guides
  • MIL-HDBK-217E - reliability
  • TSO-C51a - flight data recorders

MU39 measuring and control unit is designed to:

  • process information about selected airborne systems including GPS and digitize it for transfer via RS-422 serial cabel to ZJ39 record unit
  • record data about aircraft vibrations into the MU39 internal memory for the consecutive harmonic analysis
  • evaluate all internal functioning checks (MU39 and ZJ39) and to signalize functioning and working mode correctness and to write data to the cockpit

ZJ39 record unit is designed to:

  • record service and crash parameters of L39ZA and L39C aircrafts acquired over the RS-422 serial link from the MU39 unit
  • protect recorded data in extreme situations including fire during aircraft crash
  • save calibration constants for conversion of saved data to physical quanities of measured parameters