R EFF : 001-049, 101-105, 107-107, 151-199, 49-40-00Page 1 201-210, Config-2 Aug 01/05
CES
Ignition and Starting - Component Location
Figure 001
CES
IGNITION AND STARTING - DESCRIPTION AND OPERATION
_________________________________________________
1.
General
_______ (Ref. Fig. 001) The ignition and starting systems are necessary to start the APU. They operate electrically and are supplied from the aircraft electrical system. The two aircraft batteries are assisted by the APU Transformer Rectifier Unit (TRU) if powered through the external power or if the main engine generator supplies sufficient power to start the APU. The two aircraft batteries are installed in the avionics compartment, below the cockpit. A starter cable supplies electrical current to the starter motor. This cable is routed through the aircraft, along the ceiling of the cabin. The APU has an inflight restart capability within an established altitude and airspeed envelope. In this case, the aircraft's batteries or the TRUs rectifier supply electrical power to the starter motor.
2.
System Description
__________________
A. Ignition System The ignition system is a dual system with two igniter plugs, which gives the constant high-energy ignition which ignites the fuel/air mixture in the combustion chamber. It operates during the start sequence when the APU speed is below 55%. The Electronic Control Box (ECB) controls the ignition system fully automatically.
B. Starting System The starting system rotates and accelerates the rotor of the APU to 55% of the APU's usual speed. You can operate the starting system from the APU panel in the cockpit. The Electronic Control Box (ECB) 59KD controls the start sequence of the APU. Three consecutive start attempts are permitted without cooldown. After the third start attempt the starter motor must cool down for at least 60 minutes.
Ignition and Starting - Components
Figure 001
CES IGNITION AND STARTING ((131-9(A))) - ADJUSTMENT/TEST
____________________________________________________
TASK 49-40-00-740-001
Read CFDS for APU Class 3 Fault(s) of BACK-UP START CONTACTOR (10KA) and START
CONTACTOR (5KA) (131-9(A))
1. Reason for the Job__________________ Self Explanatory
2. Job Set-up Information______________________
A. Referenced Information
-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------
24-41-00-861-002 Energize the Aircraft Electrical Circuits from the External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power TS 49400081080700 TS 49400081080800
3. Job Set-up
__________ Subtask 49-40-00-860-050
A. Aircraft Maintenance Configuration
(1)
Energize the aircraft electrical circuits
(Ref. TASK 24-41-00-861-002)
(2)
On the overhead panel, push the APU MASTER/SW to the ON position.
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CES Subtask 49-40-00-865-054
B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):
-------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION -------------------------------------------------------------------------------49VU AUTO FLT/MCDU/1 11CA1 B01 121VU PTR/SPLY 6TW J21 121VU CFDS/CFDIU/SPLY 2TW J18 121VU APU/APU/CTL 2KD L42 121VU APU/ECB/SPLY 1KD L41
R **ON A/C 001-049, 101-105, 107-107, 151-199, 201-210,
Post SB 31-1163 For A/C 155-156,208-209,
121VU CFDS/CFDIU/BACK/UP 8TW J17
R **ON A/C 001-049, 101-105, 107-107, 151-199, 201-210,
4. Procedure
_________
Subtask 49-40-00-740-050
A. Do this procedure:
-------------------------------------------------------------------------------ACTION RESULT -------------------------------------------------------------------------------
1. On the MCDU 1(2):
-Turn the BRT knob to change
brightness.
2. Push the MCDU MENU mode key. On the MCDU 1(2):
-The MCDU MENU page comes into view.
3.
Push the line key adjacent to the - The CFDS menu page comes into view. CFDS indication.
4.
Push the line key adjacent to the - The SYSTEM REPORT/TEST page comes SYSTEM REPORT/TEST indication. into view.
R EFF : 001-049, 101-105, 107-107, 151-199, 49-40-00Page 502 201-210, Aug 01/05 中國(guó)航空網(wǎng) m.k6050.com 航空翻譯 www.aviation.cn 本文鏈接地址：A320飛機(jī)維護(hù)手冊(cè) AMM 機(jī)載輔助動(dòng)力 AIRBORNE AUXILIARY POWER4(65)
