B. After the subsequent flight, make sure that the fault does not continue.
1 -EFF : ALL
-∞∞36-11-00∞∞∞∞∞∞∞∞∞∞Page B251
--Feb 01/05 ---CES - Loss of Bleed Air from the Engine 2 because of Starter-Valve Opening Indication
1. Possible Causes
_______________
-VALVE-PNEUMATIC STARTER (4005KS)
-BMC-2 (1HA2)
-P/BSW-ENG 2 BLEED (4HA2)
-ENG/APU FIRE PNL (1WD)
-SOLENOID-BLEED PRESS REG V CTL, ENG 2 (10HA2)
-wiring
2. Job Set-up Information
______________________
A. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION
-------------------------------------------------------------------------------
AMM 26-12-12-000-001 Removal of the ENG/APU Fire Panel (1WD)
AMM 26-12-12-400-001 Installation of the ENG/APU Fire Panel (1WD)
AMM 36-11-34-000-001 Removal of the BMC (1HA1, 1HA2)
AMM 36-11-34-400-001 Installation of the BMC (1HA1, 1HA2)
AMM 36-11-55-000-001 Removal of the Bleed-Pressure-Regulator Valve
Control-Solenoid (10HA1,10HA2) AMM 36-11-55-400-001 Installation of the Bleed-Pressure-Regulator Valve
Control-Solenoid (10HA1,10HA2) AMM 80-11-20-000-003 Removal of the Starter Shutoff Valve AMM 80-11-20-400-003 Installation of the Starter Shutoff Valve ASM 36-11/02
3. Fault Confirmation
__________________
A. Test
(1) Not applicable, the fault is evident.
1 -EFF : ALL
-∞∞36-11-00∞∞∞∞∞∞∞∞∞∞Page B252
--Feb 01/05 ---CES -
4. Fault Isolation
_______________
A. If the fault symptom is identified by the crew observation: ENG BLEED AIR - Loss of bleed air from engine 2
-Replace the engine 2 VALVE-PNEUMATIC STARTER (4005KS) (Ref. AMM TASK 80-11-20-000-003) and (Ref. AMM TASK 80-11-20-400-003).
(1) If the fault continues:
-Replace the BMC-2 (1HA2) (Ref. AMM TASK 36-11-34-000-001) and (Ref. AMM TASK 36-11-34-400-001).
(a) If the fault continues:
-Do a check of the wiring (Ref. ASM 36-11/02) between: . Pin 2 of the AIR BLEED/ENG 2/CTL circuit breaker (3HA2) and pin AA/8A of the BMC 2 (1HA2) . Pin 2 of the AIR BLEED/ENG 2/CTL circuit breaker and pin A/D2 of the ENG 2 BLEED pushbutton switch (4HA2) . Pin AA/7A of the BMC 2 and pin A/D1 of the ENG 2 BLEED pushbutton switch . Pin A/D3 of the ENG 2 BLEED pushbutton switch and pin A/1 of the bleed pressure regulator valve control solenoid (10HA2) . Pin A/2 of the engine 2 bleed pressure regulator valve control solenoid and the ground.
1 If the wiring is not correct:
_ -Repair the wiring.
2 If the wiring is correct:
_ -Replace the P/BSW-ENG 2 BLEED (4HA2).
a If the fault continues:
_
-Replace the ENG/APU FIRE PNL (1WD) (Ref. AMM TASK 26-12-12-000-001) and (Ref. AMM TASK 26-12-12-400-001).
* If the fault continues:
* - Replace the SOLENOID-BLEED PRESS REG V CTL, ENG 2
(10HA2) (Ref. AMM TASK 36-11-55-000-001) and (Ref. AMM
TASK 36-11-55-400-001).
B. After the subsequent flight, make sure that the fault does not continue.
1 -EFF : ALL
-∞∞36-11-00∞∞∞∞∞∞∞∞∞∞Page B253
--Feb 01/05 ---CES -
1. BMC output data bus (numerical word)
____________________________________
These tables contain all the output parameters in the digital form. The
following tables give:
-SYS LABEL SDI: output label for which the parameter is available
-PARAMETER DEFINITION: parameter name
-RANGE ACCURACY: measurement range. Maximun value transmitted. When the digital value changes, the change step is equal to the accuracy
-UNIT: unit in which the digital value is transmitted
-SIG BIT: indicates whether a sign bit is available
-DATA BITS: number of bits used by the parameter in the label
-XMSN INTV: output transmission interval. The refresh rate is given in milliseconds (MIN/MAX)
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本文鏈接地址：A320 Trouble Shooting Manual 排故手冊 PNEUMATIC(102)
