DOC AIRBUS | TSM A320FLGCIU - VOR Interface Fault
TASK 32-31-00-810-852-A
LGCIU - VOR Interface Fault
1. Possible Causes
2. Job Set-up Information
A. Referenced Information
3. Fault Confirmation
Subtask 32-31-00-740-081-A
Subtask 32-31-00-810-110-A
[Rev.8 from Aug 2018]
2026.04.04 04:31:23 UTC
LGCIU - VOR Interface Fault
1. Possible Causes
2. Job Set-up Information
A. Referenced Information
| REFERENCE | DESIGNATION |
|---|---|
| AMM 32-31-71-000-001 | Removal of the LGCIU |
| AMM 32-31-71-400-001 | Installation of the LGCIU |
| AMM 32-69-00-740-001 | BITE Check of Landing-Gear Control Interface-Unit (LGCIU) With Use of MCDU to Ensure that Continuous BITE is Operative |
| AMM 32-69-00-860-001 | Simulation of Flight (With Aircraft on Ground) |
| AMM 34-55-00-740-002 | BITE Test of the VOR/MKR |
| ASM 345501 | |
| AMM 34-55-31-000-001 | Removal of the VOR/MKR Receiver |
| AMM 34-55-31-400-001 | Installation of the VOR/MKR Receiver |
Subtask 32-31-00-740-081-A
A. Test.
(1) Do a BITE TEST of the applicable LGCIU 1(2) AMM 32-69-00-740-001.
(a) Make sure that the faults that show are repaired before you continue.
(2) Do a BITE TEST of the VOR/MARKER with the applicable LGCIU simulated to flight AMM 34-55-00-740-002 AMM 32-69-00-860-001.
4. Fault Isolation(1) Do a BITE TEST of the applicable LGCIU 1(2) AMM 32-69-00-740-001.
(a) Make sure that the faults that show are repaired before you continue.
(2) Do a BITE TEST of the VOR/MARKER with the applicable LGCIU simulated to flight AMM 34-55-00-740-002 AMM 32-69-00-860-001.
Subtask 32-31-00-810-110-A
A. If the fault continues:
(1) Make sure that no Shock Absorber Proximity Faults show.
(2) Swop the LGCIU 1 and LGCIU 2 AMM 32-31-71-000-001 AMM 32-31-71-400-001
(3) Do the test in para.3.A.(2).
(4) If the fault moves to the other LGCIU position, replace the applicable LGCIU. LGCIU-1 [5GA1] LGCIU-2 [5GA2] AMM 32-31-71-000-001 AMM 32-31-71-400-001
(5) If the fault continues or the fault does not move:
(a) Swop the RECEIVER-VOR/MKR, 1 [3RS1] with the RECEIVER-VOR/MKR, 2 [3RS2] AMM 34-55-31-000-001 AMM 34-55-31-400-001
(6) Do the test in para 3.A.(2).
(a) If the fault moves to the other VOR/MARKER position, replace the applicable VOR/MARKER. AMM 34-55-31-000-001 AMM 34-55-31-400-001
(7) If the fault continues:
(8) Do a check and repair of the aircraft wiring between: ASM 345501
(a) VOR/MARKER 3RS2 rack connector AB, pin 15A, to LGCIU 2 rack connector AB, pin 8G.
(b) VOR/MARKER 3RS1 rack connector AB, pin 15A, to LGCIU 1 rack connector AB, pin 9C.
(9) Do the test in para 3.A.(2).
(1) Make sure that no Shock Absorber Proximity Faults show.
(2) Swop the LGCIU 1 and LGCIU 2 AMM 32-31-71-000-001 AMM 32-31-71-400-001
(3) Do the test in para.3.A.(2).
(4) If the fault moves to the other LGCIU position, replace the applicable LGCIU. LGCIU-1 [5GA1] LGCIU-2 [5GA2] AMM 32-31-71-000-001 AMM 32-31-71-400-001
(5) If the fault continues or the fault does not move:
(a) Swop the RECEIVER-VOR/MKR, 1 [3RS1] with the RECEIVER-VOR/MKR, 2 [3RS2] AMM 34-55-31-000-001 AMM 34-55-31-400-001
(6) Do the test in para 3.A.(2).
(a) If the fault moves to the other VOR/MARKER position, replace the applicable VOR/MARKER. AMM 34-55-31-000-001 AMM 34-55-31-400-001
(7) If the fault continues:
(8) Do a check and repair of the aircraft wiring between: ASM 345501
(a) VOR/MARKER 3RS2 rack connector AB, pin 15A, to LGCIU 2 rack connector AB, pin 8G.
(b) VOR/MARKER 3RS1 rack connector AB, pin 15A, to LGCIU 1 rack connector AB, pin 9C.
(9) Do the test in para 3.A.(2).