Loss of the Brake Temperature Monitoring on the Wheel 2

TASK 32-47-00-810-802-A
Loss of the Brake Temperature Monitoring on the Wheel 2

1. Possible Causes

SENSOR-BRK TEMP, WHEEL 2 [7GW]
MONITORING UNIT-BRK TEMP, L [3GW]
wiring from the BTMU (3GW) to the sensor (7GW) 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	AR	GENERATOR - DC (0 TO 0,05 V)
No specific	AR	SAFETY CLIP - CIRCUIT BREAKER
No specific	1	VOLTMETER - DC

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
ASM 324701
AMM 32-47-15-000-001	Removal of the Brake Temperature Sensor
AMM 32-47-15-400-001	Installation of the Brake Temperature Sensor
AMM 32-47-18-000-001	Removal of the Brake Temperature Monitoring Unit
AMM 32-47-18-400-001	Installation of the Brake Temperature Monitoring Unit

3. Fault Confirmation
Subtask 32-47-00-860-052-A

A. Job Set-Up
(1) Aircraft Maintenance Configuration
(a) Energize the aircraft electrical circuits
AMM 24-41-00-861-002.
(b) Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only)
AMM 31-60-00-860-001.

Subtask 32-47-00-740-052-A

B. Test
(1) Do a reset of the BSCU with the A/SKID AND NOSE WHEEL switch (5GG).
(2) Disconnect the connector from the brake temperature sensor.
(a) Make sure that the connector is clean and in the correct condition.
(3) Connect the connector to the brake temperature sensor.
(4) Do a reset of the BSCU with the A/SKID AND NOSE WHEEL switch (5GG).
(5) Do the BITE test of the BSCU AMM 32-46-00-740-001.

4. Fault Isolation
Subtask 32-47-00-865-051-A

A. Open, safety and tag this(these) circuit breaker(s):

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C ALL
121VU	HYDRAULIC/BRK/TEMP/DET/UNIT	1GW	M37
121VU	HYDRAULIC/BRAKING AND STEERING/SYS2/SPLY	4GG	M36

Subtask 32-47-00-810-051-C

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 AMM 32-47-15-000-001
on the connector of the brake temperature sensor 7GW, connect a GENERATOR - DC (0 TO 0,05 V) with the voltage adjusted to zero millivolt and a VOLTMETER - DC 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] AMM 32-47-15-000-001 and AMM 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) AMM 32-47-15-400-001.
replace the MONITORING UNIT-BRK TEMP, L [3GW] AMM 32-47-18-000-001 and AMM 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 ASM 324701.

(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 ASM 324701.

Subtask 32-47-00-740-053-A

C. Do the test given in Para. 3.B. AMM 32-46-00-740-001.

5. Close-up
Subtask 32-47-00-860-053-A

A. Put the aircraft back to its initial configuration.
(1) On the ECAM control panel, set the UPPER DISPLAY and LOWER DISPLAY potentiometers to OFF.
(2) De-energize the aircraft electrical circuits

[Rev.8 from Aug 2018] 2026.04.04 04:31:46 UTC