W DOC AIRBUS | TSM A320F

Failure of the GLC 1 Control Circuit

TASK 24-20-00-810-892-A
Failure of the GLC 1 Control Circuit

1. Possible Causes
  • GCU-1 [1XU1]
  • P/BSW-ELEC/GEN 1 [3XU1]
  • wiring
  • P/BSW-EMER ELEC PWR/GEN1 LINE [13XU]
  • RELAY [20XU]
  • BTC-1 [11XU1]
  • GLC-1 [9XU1]
  • RELAY-GLC 1 AUX CTL [4XU1]
2. Job Set-up Information
 A. Fixtures, Tools, Test and Support Equipment
REFERENCE
QTY
DESIGNATION
No specific
AR
SAFETY CLIP - CIRCUIT BREAKER
 B. Referenced Information
REFERENCE
DESIGNATION
ASM 242202
AMM 24-22-34-000-001
Removal of the GCU-1(2)
AMM 24-22-34-400-001
Installation of the GCU-1(2)
AMM 24-22-55-000-001
Removal of the Contactors
AMM 24-22-55-400-002
Installation of the Contactors
AMM 24-41-00-740-002
Operational Check of the GAPCU via the CFDS
AMM 24-41-00-861-002
Energize the Aircraft Electrical Circuits from the External Power
AMM 24-41-00-862-002
De-energize the Aircraft Electrical Circuits Supplied from the External Power
AMM 31-60-00-860-001
EIS Start Procedure
AMM 31-60-00-860-002
EIS Stop Procedure
AMM 71-00-00-710-003
Engine Automatic Start
AMM 71-00-00-710-028
Engine Shutdown
AMM 71-00-00-860-814
Shutdown of the Engine
AMM 71-00-00-860-823
Start the Engine (Normal Automatic Start)
3. Fault Confirmation
Subtask 24-20-00-869-090-A ** ON A/C NOT FOR ALL
A. Test
Not applicable.
NOTE: As the GEN 1 was set to OFF because of a true failure, the fault confirmation is not necessary.
4. Fault Isolation
Subtask 24-20-00-810-157-A ** ON A/C NOT FOR ALL
A. If the fault symptom is identified by the CFDS message GLC AUX RLY (4XU1)/ GLC1 (9XU1)/ GCU1 (1XU1) and the upper ECAM-DU warning GEN 1 FAULT:
   (1) If the CFDS message comes into view associated with the fault code 19 (GLC CONTROL CKT keyword):
   (2) If the CFDS message comes into view associated with the fault codes 180 (PR SSR OC ACTIVE keyword) or 183 (GLC CONTROL CKT keyword):
  • Continue the trouble shooting procedure.
Subtask 24-20-00-865-070-A ** ON A/C NOT FOR ALL
B. Open, safety and tag this(these) circuit breaker(s):
PANELDESIGNATIONFINLOCATION
** ON A/C NOT FOR ALL
122VUELEC/GEN1/OFF/BTC2 SPLY14XUT30
Subtask 24-20-00-810-253-A ** ON A/C NOT FOR ALL
C. Do this procedure:
   (1) Make sure that the aircraft is de-energized AMM 24-41-00-862-002.
   (2) Remove GCU1 AMM 24-22-34-000-001.
   (3) Connect pin AC/4 (28VDC) and pin AB/10J of GCU1 (1XU1) together.
   (4) Remove the GLC1 auxiliary control-relay (4XU1).
   (5) Remove the relay (20XU).
   (6) On ELEC panel 35VU:
  • Push the BAT 1 pushbutton switch, and
  • Make sure GEN1 pushbutton switch (3XU1) is pushed.
   (7) On EMER ELEC PWR panel 21VU:
  • Make sure that the GEN1 line emergency electrical-power pushbutton-switch (13XU) is pushed (OFF legend off).
   (8) Do a check of 28VDC between pin A/A of the relay (20XU) and the ground.
     (a) If there is no 28VDC:
  • Replace the P/BSW-ELEC/GEN 1 [3XU1] .
       1 If the fault continues:
  • Do a check for continuity and repair the wiring ASM 242202 between:
    . Pin AB/10J of GCU1 (1XU1) and pin A/C3 of the GEN1 pushbutton switch (3XU1)
    . Pin A/C1 of the GEN1 pushbutton switch (3XU1) and pin A/A of the relay (20XU).
     (b) If there is 28VDC:
  • Continue the trouble shooting procedure.
   (9) Do a check of 28VDC at pin A/X of the relay (20XU).
     (a) If there is 28VDC:
  • Replace the GEN1 line emergency electrical-power pushbutton-switch (13XU) P/BSW-EMER ELEC PWR/GEN1 LINE [13XU] .
     (b) If there is no 28VDC:
  • Continue the trouble shooting procedure.
   (10) Connect pin A/1 and pin A/A of the relay (20XU) together.
  • Do a check of 28VDC between pin A/X1 of the GLC1 auxiliary control-relay (4XU1) and the ground.
     (a) If there is no 28VDC:
  • Do a check and repair the wiring ASM 242202 between pin A/1 of the relay (20XU) and pin A/X1 of the GLC1 auxiliary control-relay (4XU1).
     (b) If there is 28VDC:
  • Continue the trouble shooting procedure.
   (11) Remove the connection between pin A/1 and pin A/A of the relay (20XU).
   (12) Install the relay (20XU).
  • Do a check of 28VDC at pin A/X1 of the GLC1 auxiliary control-relay (4XU1).
     (a) If there is no 28VDC:
  • Replace the RELAY [20XU] .
     (b) If there is 28VDC:
  • Continue the trouble shooting procedure.
   (13) Do a check for continuity of the wiring ASM 242202 between pin A/X2 of the GLC1 auxiliary control-relay (4XU1) and the ground.
     (a) If there is no continuity:
  • Repair the wiring.
   (14) Do a check of the voltage between pin A/D2 of the GLC1 auxiliary control-relay (4XU1) and the ground.
     (a) If there is no voltage:
  • Disconnect electrical connector B of BTC1 and do a check of the voltage on pin B/10:
       1 If there is voltage:
         a If the fault continues:
  • Do a check for continuity and repair the wiring between pin B/12 of BTC1 and pin A/D2 of the GLC1 auxiliary control-relay (4XU1).
       2 If there is no voltage:
  • Replace diode module 2420VD.
         a If the fault continues:
  • Do a check for continuity and repair the wiring ASM 242202 between:
    . Pin B/10 of BTC1 and pin A/33 of diode module 2420VD
    . Pin AB/10J of GCU1 (1XU1) and pin A/34 of diode module 2420VD.
     (b) If there is voltage:
       1 Release the BAT 1 pushbutton switch.
       2 Connect pin A/D2 and pin A/D1 of the GLC1 auxiliary control relay (4XU1) together.
       3 Disconnect electrical connector B of GLC1.
       4 Do a check for continuity between pin B/5 of GLC1 (9XU1) and the ground.
         a If there is no continuity:
  • Repair the wiring.
       5 Push the BAT 1 pushbutton switch.
       6 Do a check of the voltage between pin B/3 of GLC1 (9XU1) and the ground.
         a If there is voltage:
         b If there is no voltage:
  • Do a check for continuity between pin B/3 of GLC1 (9XU1) and pin A/D1 of the GLC1 auxiliary control-relay (4XU1).
    * If there is no continuity:
    * Repair the wiring.
       7 Release the BAT 1 pushbutton switch.
   (15) Remove the connection between pin A/D2 and pin A/D1 of the GLC1 auxiliary control-relay (4XU1).
   (16) Install the GLC1 auxiliary control-relay (4XU1).
   (17) Push the BAT 1 pushbutton switch.
   (18) Push and release the GEN1 pushbutton switch many times. If you cannot hear the contacts that close/open on GLC1 (9XU1):
     (a) Replace the RELAY-GLC 1 AUX CTL [4XU1] .
   (19) Release the BAT 1 pushbutton switch.
   (20) Remove the connection between pin AC/4 (28VDC) and pin AB/10J of GCU1 (1XU1).
   (21) Install GCU-1 [1XU1] AMM 24-22-34-400-001.
Subtask 24-20-00-865-071-A ** ON A/C NOT FOR ALL
D. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):
PANELDESIGNATIONFINLOCATION
** ON A/C NOT FOR ALL
122VUELEC/GEN1/OFF/BTC2 SPLY14XUT30
Subtask 24-20-00-710-135-C ** ON A/C NOT FOR ALL
E. Do this operational test to make sure that the system operates correctly.
   (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.
   (2) In the cockpit, on the ELEC panel 35VU:
  • Push, release and push again the GEN 1 pushbutton switch (3XU1).
   (3) Do the BITE test of the GAPCU AMM 24-41-00-740-002.
   (4) Start engine 1 AMM 71-00-00-860-823.
   (5) Do this test:
ACTION
RESULT
On the ECAM control panel:
  • Push the ELEC key to get the ELEC page.
On the lower ECAM DU:
  • The correct electrical parameters of GEN 1 are shown and GEN 1 supplies the AC1 busbar.
Subtask 24-20-00-710-135-G ** ON A/C NOT FOR ALL
E. Do this operational test to make sure that the system operates correctly.
   (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.
   (2) On the ELEC panel 35VU:
  • push, release and push again the GEN 1 pushbutton switch (3XU1).
   (3) Do the operational test of the GAPCU AMM 24-41-00-740-002.
   (4) Start the engine 1 AMM 71-00-00-710-003.
   (5) Do this test:
ACTION
RESULT
On the ECAM control panel:
  • get the ELEC page.
On the lower ECAM DU:
  • the correct electrical parameters of the GEN 1 are shown and the AC1 busbar is supplied by the GEN 1.
5. Close-up
Subtask 24-20-00-860-160-C ** ON A/C NOT FOR ALL
A. Put the aircraft back to its initial configuration.
   (1) Stop engine 1 AMM 71-00-00-860-814.
   (2) Do the EIS stop procedure
AMM 31-60-00-860-002.
   (3) On the ECAM control panel, set the UPPER DISPLAY and LOWER DISPLAY potentiometers to OFF.
   (4) De-energize the aircraft electrical circuits
AMM 24-41-00-862-002.
Subtask 24-20-00-860-160-G ** ON A/C NOT FOR ALL
A. Put the aircraft back to its initial configuration.
   (1) Stop the engine 1 AMM 71-00-00-710-028.
   (2) Do the EIS stop procedure
AMM 31-60-00-860-002.
   (3) On the ECAM control panel, set the UPPER DISPLAY and LOWER DISPLAY potentiometers to OFF.
   (4) De-energize the aircraft electrical circuits
AMM 24-41-00-862-002.
[Rev.8 from Aug 2018] 2026.04.04 04:26:19 UTC
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