_______________
R A. If the test gives the maintenance message PARK BRAKE
R SELECTOR(102GG)/BSCU(10GG)
R - replace the CTL VALVE-PARK BRK, ELEC (102GG) (Ref. AMM TASK 32-45-53-R 000-001) (Ref. AMM TASK 32-45-53-400-001)
R B. Do the test given in Para.3.A.
「一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一1 EFF : 401-499, ∞∞32-45-00∞∞∞∞∞∞∞∞∞∞Page 227
Aug 01/05 CESR Parking Brake System with Parking Brake Set to on R Figure 201A/TASK 32-45-00-991-001-A
「一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一1 EFF : 401-499, ∞∞32-45-00∞∞∞∞∞∞∞∞∞∞Page 228
Aug 01/05 CES
BRAKE SYSTEM TEMPERATURE - FAULT ISOLATION PROCEDURES
_____________________________________________________
TASK 32-47-00-810-801
Loss of the Brake Temperature Monitoring on the Wheel 1
1. Possible Causes
_______________
- MONITORING UNIT-BRK TEMP, L (3GW)
- SENSOR-BRK TEMP, WHEEL 1 (5GW)
- wiring from the BTMU (3GW) to the sensor (5GW) pins A/A, C
- wiring from the BTMU (3GW) to the BSCU (10GG)
2. Job Set-up Information
______________________
A. Fixtures, Tools, Test and Support Equipment
-------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
No specific circuit breaker(s) safety clip(s)
No specific millivoltmeter
No specific DC Generator (0 to 50 mv)
B. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
AMM 24-41-00-861-002 Energize the Aircraft Electrical Circuits from the
External Power
AMM 31-60-00-860-001 EIS Start Procedure
AMM 32-46-00-740-001 BITE Test of the BSCU
AMM 32-47-15-000-001 Removal of the Brake Temperature Sensor
(4GW,5GW,6GW,7GW)
AMM 32-47-15-400-001 Installation of the Brake Temperature Sensor
(4GW,5GW,6GW,7GW) R AMM 32-47-18-000-001 Removal of the Brake Temperature Monitoring Unit R AMM 32-47-18-400-001 Installation of the Brake Temperature Monitoring Unit
ASM 32-47/01
3. Fault Confirmation
__________________
A. Job Set-Up
(1) Aircraft Maintenance Configuration
(a) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002).
「一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一1 EFF : ALL ∞∞32-47-00∞∞∞∞∞∞∞∞∞∞Page 201
May 01/05 CES
(b) Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only) (Ref. AMM TASK 31-60-00-860-001).
B. Test Do the BITE test of the BSCU (Ref. AMM TASK 32-46-00-740-001).
4. Fault Isolation
_______________
A. Open, safety and tag this(these) circuit breaker(s):
-------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION -------------------------------------------------------------------------------121VU HYDRAULIC/BRK/TEMP/DET/UNIT 1GW M37 121VU HYDRAULIC/BRAKING AND STEERING/SYS2/SPLY 4GG M36
R **ON A/C 001-049, 051-099, 101-105, 151-199, 201-220, 301-399,
B. If the test gives the maintenance message BRAKE TEMP SENSOR 5GW OR MONIT UNIT 3GW: - on the brake 1, disconnect the connector of the brake temperature
sensor 5GW (Ref. AMM TASK 32-47-15-000-001)
- on the connector of the brake temperature sensor 5GW, connect a DC Generator (0 to 50 mv) with the voltage adjusted to zero millivolt and a millivoltmeter with the polarity as follows: Terminal A: Negative. Terminal C: Positive.
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本文鏈接地址：A320 Trouble Shooting Manual 排故手冊 起落架 LANDING GEAR 2(69)
