Hawker 125 (Series 1 through 900XP)

AC Main Inverters (Only Aircraft Equipped with Standby Inverter)

1. 
   Standby inverter is verified operative before each departure,
   

2. 
   For aircraft with two (2) AOA Vanes and SSU systems, both Engine Driven AC alternators are operative, and
   
3. 
   Flight is not conducted in known or forecast icing conditions.
   

1. 
   Perform inverter check prior to each departure.
   

2. 
   For aircraft with two (2) AOA Vanes and SSU systems, verify both Engine Driven AC alternators are operative.
   
3. 
   Planeach flight to avoid known or forecast icing conditions along entire route including alternate destination.
   

Standby Inverter (Except Pro Line 21)

(Pro Line 21 Only)

Inverter Fail Lights/ Annunciators

1. 
   Auto-changeover system is operative, and
   

2. 
   Both main inverters are operative, and
   
3. 
   AC voltmeter is installed and operative.
   

1. 
   Confirm both inverters are operative.
   

2. 
   Confirm AC powered equipment operates with either inverter selected OFF.
   
3. 
   Confirm AC voltmeter indicates correct voltage.
   

Standby Inverter “ON” Light / Annunciator

1. 
   Select STBY INV to ARM.
   
2. 
   Select INV 1 and INV 2 to STOP.
   
3. 
   Confirm normal Standby Inverter voltage on XE buss.
   

AC Voltmeter

1. 
   All inverters are operative, and
   

2. 
   All AC system Annunciators are operative.
   

1. 
   Prior to each departure, confirm INV and buss FAIL annunciators illuminate with all inverters OFF.
   
2. 
   Confirm annunciators extinguish with inverters ON.
   

AC Frequency Meter (Series 600 and 700 only)

AC Alternator(s)

1. 
   AFM Limitations are observed,
   

2. 
   Windshield fluid de-icing system is installed and operative, and
   
3. 
   Aircraft is not operated in known or forecast icing conditions.
   

1. 
   Observe AFM airspeed (birdstrike) limitations.
   
2. 
   Confirm windscreen fluid de-icing system is operative.
   
3. 
   Plan each flight to avoid known or forecast icing conditions along entire route including alternate destination.
   

1. 
   For aircraft with 2 AOA Vane and SSU systems, both Main AC inverters are operative, and
   

1. 
   Aircraft is not operated in known or forecast icing conditions.
   

1. 
   For aircraft with two (2) AOA Vane and SSU systems, both Main AC Inverters are operative.
   
2. 
   Plan each flight to avoid known or forecast icing conditions along entire route including alternate destination.
   

AC Alternator Fail Warning Light / Annunciator(s)

1. 
   With RH engine running select W/SCREEN HEAT ON.
   
2. 
   Verify by feel that windscreen heating is operative.
   

1. 
   Both AC alternators are operative, and
   
2. 
   Auto-changeover system is operative.
   

1. 
   Confirm both AC alternators are operative.
   
2. 
   With engines running, select screen heats and alternator ON, and verify screen heat is operative.
   
3. 
   Switch one alternator OFF and verify the “B” screens are no longer heated and the associated VANE HTR FAIL does not illuminate.
   

21-3

115 VAC / 60 Hertz (Hz) System

1. 
   Procedures do not require its use, and
   
2. 
   System is deactivated.
   

2. 
   Refer to applicable Hawker Aircraft Wiring Parts Catalog (Chapter 24).
   
3. 
   Remove fuse from affected inverter DC input.
   
4. 
   Place ‘INOP’ placard adjacent to affected inverter switch on CG Panel.
   

Battery Temperature (With NiCad Battery Only)

1. 
   Disconnect Batt Temp connector from both batteries.
   
2. 
   Jumper across Pins A & B.
   
3. 
   Verify BATT HOT lights illuminate.
   

1. 
   Battery Temperature Indicator is operative, and
   

2. 
   Battery temperatures are monitored in flight.
   

Not required for lead acid battery systems.

1. 
   Prior to flight, confirm No. 1 and No. 2 Battery Temperatures are normal.
   

2. 
   Regularly monitor No. 1 and No. 2 Battery Temperatures during flight.
   

Battery NO CHARGE Light (Series 1 through 700 only)

32-2

Battery Heater Muffs

1. 
   Battery Temperature Indicator is operative, and
   

2. 
   Battery temperature is monitored to ensure temperature remains above 10 °C at all times.
   

1. 
   Prior to flight, confirm No. 1 and No. 2 Battery Temperatures are normal.
   
2. 
   Regularly monitor No. 1 and No. 2 Battery Temperatures during flight.
   
3. 
   Battery temperatures must remain above -10°C.
   

Engine Driven Generators

APU Generator

DC Voltmeter

DC Generator Fail Lights / Annunciators

1. 
   Both ammeters are operative, and
   

2. 
   DC voltmeter is operative.
   

1. 
   Both ammeters indicating current, and
   

2. 
   Both DC voltmeters indicating proper voltage.
   

DC Bus Tie Light Annunciator

1. 
   Bus Tie system is operative,
   
2. 
   Both ammeters are operative, and
   
3. 
   Generator fail lights / annunciators are operative.
   

1. 
   Prior to each departure:
   

• 
  Select GEN 1 to TRIP.
  
• 
  Confirm current on GEN 2.
  
• 
  Confirm Power (PS)1 and PS2 voltage with Buss Tie CLOSED.
  
• 
  Open Buss Tie and verify voltage on PS2 only and GEN 1 FAIL annunciator.
  
• 
  Reset GEN 1 and Buss Tie.
  

2. 
   Repeat above for GEN 2 TRIP by substituting GEN 1 for GEN 2 and vice-versa, in above steps.
   

Battery Contactor Annunciators

(Series 1 through 700)

1. 
   Emergency contactor is verified operative, and
   
2. 
   Battery (Batt) contactor is verified operative.
   

1. 
   Confirm Batt 1 and Batt 2 voltage on overhead voltmeter.
   
2. 
   Select Battery switch to ON and confirm PE voltage on overhead voltmeter.
   
3. 
   Start APU or either engine.
   
4. 
   Confirm increase of Batt 1 and Batt 2 voltage on overhead voltmeter when generator is brought on line and Buss Tie switch is selected to CLOSE.
   
5. 
   Confirm charging current to Batt 1 and Batt 2 on overhead ammeter.
   

APU Generator Fail Light / Annunciator

APU Generator Overheat Light / Annunciator

External Power System

AC Bus Fail Lights / Annunciators (Standby Inverter- Equipped Aircraft only)

1. 
   Standby inverter (STBY INV) is verified operative before each departure,
   
2. 
   Inverter associated with the inoperative light / Annunciator is verified operative before each departure, and
   
3. 
   Voltmeter is operative.
   

1. 
   Turn off both main inverters and note that STBY INV ON light illuminates.
   
2. 
   Confirm standby inverter output voltage on XE bus.
   
3. 
   Confirm inverter output voltage for associated bus fail annunciator on XS1 or XS2.
   

50-2

26 VAC Bus Fail Annunciators

Bus Tie Contactor System (Split Bus Tie Contactor Aircraft only)

1. 
   Both engine driven DC generators are operative,
   
2. 
   Bus Tie contactor is verified to be open before each departure, and
   
3. 
   PS1 AND PS2 voltage is verified normal before each departure.
   

1. 
   Individually check #1 & #2 Generator voltage.
   
2. 
   Turn #2 Generator ON, turn #1 Generator OFF and confirm PS1 Buss voltage is zero.
   
3. 
   With both generators ON, confirm Generator (GEN) 1 FAIL and GEN 2 FAIL annunciators are both out.
   
4. 
   Confirm PS1 and PS2 voltage normal.
   

60-2

FIS Power Recovery System