(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
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A. Job Set-Up
(1) Aircraft Maintenance Configuration
(a) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002).
(b) Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only) (Ref. AMM TASK 31-60-00-860-001).
「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 204
May 01/05 CES
B. Test
Do the BITE test of the BSCU (Ref. AMM TASK 32-46-00-740-001).
4. Fault Isolation
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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
**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 7GW OR MONIT UNIT 3GW: - on the brake 2 disconnect the connector of the brake temperature sensor
7GW (Ref. AMM TASK 32-47-15-000-001)
- on the connector of the brake temperature sensor 7GW, 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
- Remove the safety clip(s) and the tag(s) and close this(these) circuit
breaker(s): 1GW - on the ECAM control panel, push the WHEEL key to get the WHEEL page - on the DC generator, increase the voltage.
(1) If the related temperature indication increases on the WHEEL page
- replace the SENSOR-BRK TEMP, WHEEL 2 (7GW) (Ref. AMM TASK 32-47-15-000-001) and (Ref. AMM TASK 32-47-15-400-001).
(2) If the related temperature indication does not increase on the WHEEL page:
- connect the connector of the brake temperature sensor (7GW) (Ref. AMM TASK 32-47-15-400-001).
- replace the MONITORING UNIT-BRK TEMP, L (3GW) (Ref. AMM TASK 32-47-18-000-001) and (Ref. AMM TASK 32-47-18-400-001).
(3) If the fault continues:
- do a check and repair the wiring from the BTMU (3GW) to the sensor (7GW) pins A/A, C (Ref. ASM 32-47/01).
(4) If the fault continues:
- do a check and repair the wiring from the BTMU (3GW) to the BSCU (10GG) pin A/D to pin AB/10C (Ref. ASM 32-47/01).
「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 205
Aug 01/05R
CES R **ON A/C 106-149, 221-299, 401-499,
B. If the test gives the maintenance message BRAKE TEMP SENSOR2(7GW)/BTMU(3GW): - on the brake 2 disconnect the connector of the brake temperature sensor
7GW (Ref. AMM TASK 32-47-15-000-001)
- on the connector of the brake temperature sensor 7GW, 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
- Remove the safety clip(s) and the tag(s) and close this(these) circuit
breaker(s): 1GW - on the ECAM control panel, push the WHEEL key to get the WHEEL page - on the DC generator, increase the voltage.
(1) If the related temperature indication increases on the WHEEL page
- replace the SENSOR-BRK TEMP, WHEEL 2 (7GW) (Ref. AMM TASK 32-47-15-000-001) and (Ref. AMM TASK 32-47-15-400-001).
(2) If the related temperature indication does not increase on the WHEEL page:
- connect the connector of the brake temperature sensor (7GW) (Ref. AMM TASK 32-47-15-400-001).
- replace the MONITORING UNIT-BRK TEMP, L (3GW) (Ref. AMM TASK 32-47-18-000-001) and (Ref. AMM TASK 32-47-18-400-001).
(3) If the fault continues:
- do a check and repair the wiring from the BTMU (3GW) to the sensor (7GW) pins A/A, C (Ref. ASM 32-47/01).
(4) If the fault continues:
- do a check and repair the wiring from the BTMU (3GW) to the BSCU (10GG) pin A/D to pin AB/10C (Ref. ASM 32-47/01).
**ON A/C ALL
C. Do the test given in Para. 3.A. (Ref. AMM TASK 32-46-00-740-001).
5. Close-up
________
A. Put the aircraft back to its initial configuration.
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本文鏈接地址：A320 Trouble Shooting Manual 排故手冊 起落架 LANDING GEAR 2(71)
