Control and Monitoring - Component Location
 Figure 001

 CES

 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). The aircraft power supply allows the ECB 59KD to continue to control the APU during short power interruptions on the battery busbar 301PP. It will do this when the APU speed is more than 95 %. The PMG supply installed in the cooling fan (Ref. 49-52-00) allows the ECB 59KD to continue to control the APU during short power interruptions on the battery busbar 301PP. It will do this when the APU speed is more than 70%.

 5.
 Interface

_________
 A. Aircraft (A/C) Input Signals to the ECB 59KD
 ------------------------------------------------------------------------INPUT SIGNAL SIGNAL ------------------------------------------------------------------------Master Switch/Stop Ground Start 28 V DC Environmental Control System (ECS) ARINC 429 BUS Main Engine Start (MES) 28 V DC Emergency Shutdown Ground Bleed Control 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 A320/A321 PIN A320 Open/A321 Closed Air Intake Actuator BITE Signals 2 x 28 V DC APU Fuel LP Valve Open/Ground for enabled

 ECB Supply - Schematic
 Figure 002

 CES  (1) A/C Sensors connected to the ECB 59KD:

 -low fuel pressure switch 5030 QM,
 -generator oil-temperature sensor,
 -air-intake position switches.
 B. ECB 59KD Output Signals to the A/C
 --------------------------------------------------------------------LOAD OUTPUT SIGNAL SIGNAL STEADY CONDITION STATE --------------------------------------------------------------------
APU AVAILABLE  28 V DC 
Start Contactor  28 V DC 
Back-Up Start Contactor  28 V DC 
APU Fault  28 V DC 
Start in Progress  28 V DC 
Bleed Control Valve  28 V DC 
(open position)
 APU Main Relay  Ground 
Air Intake Actuator  28 V DC 
(open CMD)
 Air Intake Actuator  28 V DC 
(close CMD)
 APU Fuel LP Valve  28 V DC 
APU System Bus  ARINC 429

150 mA1 A1 A
50 mA50 mA10 mA (Ref. 49-51-51
100 mA
1.6 A (Ref. 49-16-51
1.6 A (Ref. 49-16-51
200 mA (Ref. 26-22-00
 (1)
 ECB 59KD Output Signals to APU loads:

 -
fuel solenoid,

 -
fuel servo valve,

 -ignition unit driver,
 -inlet guide vanes servo valve,
 -de-oil solenoid,
 -bleed control valve servo valve, - oil level RTD,
 -pressure transducer excitation,
 -IGV and bleed control valve LVDT, - oil filter and LOP switches.

 (2)
 APU Input Signals to the ECB 59KD:

 -EGT (T5) chromel-alumel thermocouples (redundant),
 -monopole transducer (APU speed) (redundant), - oil temperature sensor,
 -low-oil pressure switch,
 -
load-compressor inlet temperature sensor,

 -
load-compressor discharge temperature sensor,

 -inlet pressure transducer (P2),

 -
load-compressor delta pressure transducer (DELTA P),

 -
load-compressor discharge static pressure-transducer (PT),

 -inlet-guide vane actuator-position (LVDT),
 -starter voltage sensor,
 - oil filter bypass switch,

 -engine ID module
 -bleed control valve position LVDT,
 -redundant speed from PMG,
 - oil level sensor,

 -PMG power supply.
 C. Explanations to the Parameter List The parameter list is organized according to the connected ARINC 429 data buses. The connected systems (e.g. FAC, ECU, EEC, etc.) and the corresponding ATA chapter numbers are stated in the header on the left side of each page of the parameter lists. The columns are described as follows:
 ---------------------------------------------------------------Column | Description ---------------|-----------------------------------------------1st | EQ.SYS.LAB.SDI = Parameter number
 SYS.LAB.SDI  | | System number: According to the system which is | sending out the corresponding parameter: | 1 for system one | 2 for system two | 3 for system three | Label of the parameter, octal value | according to ARINC 429. | SDI states the Source/Destination Identifier | which is used by the system for the | corresponding parameter: | 00 means SDI 00 (0) | 01 means SDI 01 (1) | 10 means SDI 10 (2) | 11 means SDI 11 (3)
　
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：A320飛機維護手冊 AMM 機載輔助動力 AIRBORNE AUXILIARY POWER5(97)