DOC AIRBUS | TSM A320FEngine 2 FADEC continuously powered on ground
1. Possible Causes
· wiring between the ENG panel 115VU and the EIU-2(1KS2)
· wiring between the ENG panel 115VU from pin A/D, to the ground
· CTL SW-ENG/MASTER 2 ( 2KC )
· SEL SW-ENG/MODE/CRANK/AUTO IGN/IGN ( 6KS )
· wiring between the LGCIU-2(5GA2) and the EIU-2(1KS2)
· wiring between the maintenance panel 50VU and the EIU-2(1KS2)
· FADEC PWR P/BSW(7KS2)
· EIU-2 ( 1KS2 )
2 Job Set-up Information
A. Referenced Information
REFERENCE DESIGNATION
Ref. ESPM 20-45-21
Ref. AWM 73-25-08
Ref. AWM 73-25-10
Ref. AWM 73-25-12
Ref. AWM 73-25-14
Ref. AMM 73-25-34-000-041 Removal of the Engine Interface Unit (EIU)
Ref. AMM 73-25-34-400-041 Installation of the Engine Interface Unit (EIU)
Ref. AMM 73-25-34-710-042 Operational Test of the EIU with the CFDS
3. Fault Confirmation
Subtask 73-22-00-710-260-A
A. Operational test of the EIU-2(1KS2)
(1) Do the operational test of the EIU-2(1KS2) with the CFDS Ref. AMM 73-25-34-710-042 .
4. Fault Isolation
Subtask 73-22-00-810-201-A
A. If the test gives a maintenance message:
· Do the applicable troubleshooting procedures in accordance with the TSM for maintenance message(s)
recorded.
· If the fault continues, go to step B.
Subtask 73-22-00-810-202-A
B. Fault isolation for EIU-2 Master Level (2KC) discrete input
(1) Do a check and repair:
(a) The wiring between the ENG panel 115VU and the EIU-2(1KS2) Ref. AWM 73-25-12:
· From pin A/G, to pin AA/5A.
· From pin A/L, to pin AA/4E.
(b) The wiring between the ENG panel 115VU from pin A/D, to the ground Ref. AWM 73-25-12.
(2) If the fault continues:
· Replace the CTL SW-ENG/MASTER 2 ( 2KC ) on the ENG panel 115VU Ref. ESPM 20-45-21.
(3) If the fault continues, go to step C.
Subtask 73-22-00-810-203-A
C. Fault isolation for EIU-2 Rotary Selector (6KS) discrete input
(1) Do a check and repair:
(a) The wiring between the ENG panel 115VU and the EIU-2(1KS2) from pin A/J, to pin AA/1A
Ref. AWM 73-25-10.
(2) If the fault continues:
· Replace the SEL SW-ENG/MODE/CRANK/AUTO IGN/IGN ( 6KS ) .
(3) If the fault continues, go to step D.
Subtask 73-22-00-810-206-A
D. Fault isolation for EIU-2(1KS2) Landing gear position discrete input
(1) Do a check and repair:
(a) The wiring between the LGCIU-2(5GA2) and the EIU-2(1KS2) Ref. AWM 73-25-08:
· From the pin AB/3G to the pin AA/5D.
· From the pin AB/3K to the pin AA/5E.
· From the pin AB/15B to the pin AA/3F.
(2) If the fault continues, go to step E.
Subtask 73-22-00-810-207-A
E. Fault isolation for EIU-2 ENG FADEC PWR P/BSW (7KS2) discrete input
(1) Do a check and repair:
(a) The wiring between the maintenance panel 50VU and the EIU-2(1KS2) from the pin A/V to the
pin AA/1D Ref. AWM 73-25-14.
(2) If the fault continues:
· Replace the FADEC PWR P/BSW(7KS2) .
Subtask 73-22-00-810-209-A
F. If the fault continues:
(1) Replace the EIU-2 ( 1KS2 ) Ref. AMM 73-25-34-000-041 and Ref. AMM 73-25-34-400-041 .
5. Close-up
Subtask 73-22-00-710-261-A
A. Put the Aircraft back to its initial configuration
Figure 73(IAE)-22-00-991-02200-13-A- / SHEET 1/1 - Failure of the Fuel Temperature Sensor on Engine 1(2)
Figure 73(IAE)-22-00-991-00200-13-B- / SHEET 1/1 - FMU Overspeed Valve
Figure 73(IAE)-22-00-991-00300-13-A- / SHEET 1/1 - Engine Dedicated Alternator Stator
Figure 73(IAE)-22-00-991-00400-13-A- / SHEET 1/1 - Engine Dedicated Alternator Stator
Figure 73(IAE)-22-00-991-00500-13-B- / SHEET 1/1 - P2/T2 Sensor
Figure 73(IAE)-22-00-991-00600-13-A- / SHEET 1/1 - P2/T2 Sensor
Figure 73(IAE)-22-00-991-00700-13-A- / SHEET 1/1 - Failure of the P3/T3 Sensor on Engine 1(2)
Figure 73(IAE)-22-00-991-00800-13-A- / SHEET 1/1 - Engine 1 Position Indication
Figure 73(IAE)-22-00-991-00900-13-A- / SHEET 1/1 - Failure of the T2.5 Sensor on Engine 1(2)
Figure 73(IAE)-22-00-991-01000-13-B- / SHEET 1/1 - Fuel Metering Unit
Figure 73(IAE)-22-00-991-01100-13-A- / SHEET 1/1 - Engine 2 Position Indication
Figure 73(IAE)-22-00-991-02400-13-B- / SHEET 1/1 - Fuel Shut-Off Valve
Figure 73(IAE)-22-00-991-01300-13-A- / SHEET 1/1 - FMU Overspeed Valve
Figure 73(IAE)-22-00-991-01400-13-A- / SHEET 1/1 - Aircraft 28 Volt Power Supply (Engine 1)
Figure 73(IAE)-22-00-991-01500-13-A- / SHEET 1/1 - Aircraft 28 Volt Power Supply (Engine 2)
Figure 73(IAE)-22-00-991-01600-13-A- / SHEET 1/1 - P2/T2 Sensor
Figure 73(IAE)-22-00-991-02300-13-A- / SHEET 1/1 - Failure of the Fuel Temperature Sensor on Engine 1(2)
73-25 - (IAE) - FUNCTIONAL INTERFACES
73-25-00 - (IAE) - FUNCTIONAL INTERFACES
73-25-00 PB 201 CONF 13 - FUNCTIONAL
INTERFACES - FAULT ISOLATION PROCEDURES [Rev.6 from Feb 2017] 2026.04.04 04:36:20 UTC