Inverter System / Inverter Bus Functional Check

    The following procedure checks and verifies proper operation of the Constant Frequency AC System on the G II and G II-B aircraft.  This check may be performed using APU Alternator, External AC, or External DC power.  If using External DC, however, operation of the B inverter may not be tested.  This is because the right alternator bus can not be powered by External DC, and there is no Inverter Alternate power switch for the B inverter.
 
 

Inverter Bus Control Switches
 
Action
Correct Ressult
1
    All Inverter Control Switches - OFF
   Mach Trim Switch - NORM		    SP-50G Airplanes - Mach Trim LIght - ON
   SPZ-800 Airplanes - TR Amps Increase
2
    Instrument INV Bus Switch - EMGY    E Inverter Powers Instrument AC Bus
3
    Instrumetn INV Bus Switch - NORM    E Inverter Powers Instrument AC Bus / Autochange
4
    Secondary INV Bus Switch - STBY    B INV Powers Secondary AC Bus
   E INV Powers Instrument AC Bus / Autochange
5
    Main INV Bus Switch - STBY    B INV Powers Main & Instrument AC Busses
   Secondary AC Bus - Unpowered
   E Inverter goes to standby
   SP-50G Airplanes - Mach Trim Light - OFF
   SPZ-800 Airplanes TR Amps Decrease
6
    Main Inverter Bus Switch - NORM    A Inverter Powers Main & Instrument AC Busses
   B Inverter Powers Secondary AC Bus
7
    Secondary Inverter Bus Switch - NORM    C Inverter Powers Secondary AC Bus
   B Inverter Shuts Down


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