-
the IGV position,

 -
the load control valve,

 -
the surge control valve position.
 The ECB also controls the subsequent systems:

 -
the starter motor,

 -
the igniters,

 -
the fuel control shutoff valve,

 -
the air intake flap.
 The ECB communicates with the aircraft systems through the ARINC 429
 busses.
 The subsequent LRUs are controlled by separate torque motor currents:

 -
the fuel control assembly,

 -
the IGV actuator,

 -
the surge control valve.

R  **ON A/C 401-499, 
R  A. Electronic Control Box 59KD 
R  (1) The ECB is installed adjacent to the BULK cargo compartment on the 
R  right side, between FR54 and FR55. It is held in an ARINC 600-6 
R  mounting rack. 
R  The ECB provides full authority digital APU control from the start 
R  initialization, during the acceleration, at the governor speed to the 
R  shutdown. The ECB monitors the APU speed, the APU temperatures, the 
R  load compressor air flow, and other critical parameters based on 
R  signal inputs from the accessory sensors and the control switches. 
R  These data are used for the calculation and to continuously control: 
R  - the fuel flow, 
R  - the IGV position, 
R  - the load control valve, 
R  - the surge control valve position. 
R  The ECB also controls the subsequent systems: 
R  - the starter motor, 
R  - the igniters, 
R  - the fuel control shutoff valve, 
R  - the air intake flap. 
R  The ECB communicates with the aircraft systems through the ARINC 429 
R  busses. 
R  The subsequent LRUs are controlled by separate torque motor currents: 
R  - the fuel control assembly, 
R  - the IGV actuator, 
R  - the surge control valve. 
R  **ON A/C 001-003, 051-099, 401-499,
 4. Power Supply____________
 (Ref. Fig. 002)
 The battery bus 301PP supplies 28VDC to the ECB 59KD through the circuit
 breaker ECB SPLY 1KD and the relay APU MAIN 4KD. The 28VDC supply for the
 APU MAIN relay is through the circuit breaker APU CTL 2KD. The ECB
 continuously monitors its internal voltages and starts an APU shutdown if a
 voltage failure occurs (that would result in an unsafe operation of the
 APU).
 5. Interface_________ 

 CES

 ECB Supply - Electrical Schematic
 Figure 002

 CES

 **ON A/C 001-003, 051-062,

 A. Aircraft (A/C) Input Signals to the ECB 59KD
 ------------------------------------------------------------------------
INPUT SIGNAL SIGNAL
 ------------------------------------------------------------------------
Master Switch/Stop  Ground/Open
 Start  28 V DC
 Environmental Control System (ECS)  ARINC 429 BUS
 air demand
 Main Engine Start (MES)  28 V DC
 Emergency Shutdown  Ground
 Bleed-air Valve Operation  Ground
 Air/ground Signal  Ground for ground
 condition
 A/C Parameter and Centralized Fault  ARINC 429 BUS
 Display System (CFDS)
 Start Contactor Monitor Signal  Open/28 V/ground
 TSO/JAR Configuration  Open/Ground
 for TSO Configuration
 Air Intake Actuator BITE Signals  2 x 28 V DC
 Start Valve Command  28 V DC
 Low Fuel Pressure Valve enable  GND for BITE enable
 APU Oil Heater BITE enable  GND for BITE enable
 (1) A/C Sensors connected to the ECB 59KD:
 - low-level pressure switch 5030 QM
 - generator oil-temperature sensor,
 - air-intake position switches.
 (2) ECB 59KD Output Signals to the A/C

 --------------------------------------------------------------------LOAD OUTPUT SIGNAL SIGNAL STEADY CONDITION STATE --------------------------------------------------------------------
APU AVAILABLE  28 V DC  150 mA
 Start Contactor  28 V DC  1 A
 Back-Up Start Contactor  28 V DC  1 A
 APU Fault  28 V DC  50 mA
　
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