DOC AIRBUS | TSM A320FFailure of the Stage 10 to HPT Air Valve on Engine 2
1. Possible Causes
· VALVE-STAGE 10 TO HPT AIR ( 4025KS )
· wiring from the EEC (4000KS) to the stage 10 to HPT air valve (4025KS)
· EEC ( 4000KS )
2 Job Set-up Information
A. Referenced Information
REFERENCE DESIGNATION
Ref. AMM 24-41-00-861-002 Energize the Aircraft Electrical Circuits from the External Power
Ref. AMM 24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied from the External
Power
Ref. AMM 31-60-00-860-002 EIS Stop Procedure
Ref. AMM 70-23-15-912-010 Connection of Electrical Connectors
Ref. AMM 71-00-00-710-018 Discontinued Start, Restart and Shutdown Procedures
Ref. AMM 71-00-00-710-043 Normal Engine Automatic Start Procedure
Ref. AMM 71-00-00-710-047 Normal Engine Manual Start Procedure
Ref. AMM 71-13-00-410-010 Closing of the Fan Cowls 437AL(447AL),438AR(448AR)
Ref. AMM 71-50-00-210-010 Wire Harness Visual Inspection - All Power Plant Electrical Cables
Ref. AMM 73-22-34-000-010 Removal of the Electronic Engine Control (EEC)
Ref. AMM 73-22-34-400-010 Installation of the Electronic Engine Control (EEC)
Ref. ASM 73-25-18
Ref. AMM 75-23-51-000-010 Removal of the Stage 10 to HPT Air Control Valve
Ref. AMM 75-23-51-400-010 Installation of the Stage 10 to HPT Air Control Valve
Ref. AMM 78-32-00-410-010 Closing of the Thrust Reverser Halves
Stage 10 to HPT Air Valve SHEET 1
Figure 75(IAE)-23-00-991-00200-A / SHEET 1/1 - Stage 10 to HPT Air Valve not printed, as per
printing preferences
3. Fault Confirmation
Subtask 75-23-00-860-060-A
A. Job Set-up
(1) Energize the aircraft electrical circuits
Ref. AMM 24-41-00-861-002 .
(2) On the panel 50VU, release the ENG FADEC GND PWR/2 pushbutton switch.
Subtask 75-23-00-710-076-A
B. Test
(1) On the panel 50VU, push the ENG FADEC GND PWR 2 pushbutton switch and release it again.
NOTE: This action resets the FADEC memory.
(2) Adjust the brightness of the MCDU screen.
(3) Push the INIT mode key. The INIT page comes into view.
(4) Enter a new flight number.
(5) Start the engine 2 by the normal engine automatic start procedure Ref. AMM 71-00-00-710-043 or
the normal engine manual start procedure Ref. AMM 71-00-00-710-047 and let it become stable for 5
minutes.
NOTE: Operation of the engine for at least 3 minutes erases the LAST LEG REPORT related to the
last flight and the new fault is recorded in the EEC LAST LEG REPORT.
(6) Do a shutdown of the engine 2 by the discontinued start, restart and shutdown procedure Ref.
AMM 71-00-00-710-018 .
(7) Read the LAST LEG REPORT of the FADEC (2A and 2B) menu on the MCDU (Ref. 70-00-00 Page
Block 301 Task Supporting Data).
(a) Make a record of the maintenance message.
(b) Make a record of the channel FADEC 2A or FADEC 2B which found the fault.
(8) Fully decrease the brightness of the MCDU screen (display off).
4. Fault Isolation
(Ref. Fig. Stage 10 to HPT Air Valve SHEET 1)
Subtask 75-23-00-810-063-A
A. If the test gives the maintenance message TCA VLV/HC/EEC2:
· examine the harness Ref. AMM 71-50-00-210-010 from the EEC (4000KS) to the stage 10 to HPT air
valve (4025KS) Ref. ASM 73-25-18.
(1) If the fault continues:
· disconnect the connector from the stage 10 to HPT air valve (4025KS)
· examine the connector and receptacle Ref. AMM 71-50-00-210-010
· connect the connector to the stage 10 to HPT air valve (4025KS) Ref. AMM 70-23-15-912-010 .
(2) If the fault continues:
· replace the VALVE-STAGE 10 TO HPT AIR ( 4025KS ) Ref. AMM 75-23-51-000-010 and Ref.
AMM 75-23-51-400-010 .
(3) If the channel which found the fault (when you did the test) was FADEC 2A and the fault continues:
· do a check and repair the wiring from the EEC (4000KS) to the stage 10 to HPT air valve
(4025KS) : pins J2/k, m to pins A/A, B Ref. ASM 73-25-18.
(4) If the channel which found the fault (during the test) was FADEC 2B and the fault continues:
· do a check and repair the wiring from the EEC (4000KS) to the stage 10 to HPT air valve
(4025KS) : pins J8/k, m to pins A/D, E Ref. ASM 73-25-18.
(5) If the fault continues:
· replace the EEC ( 4000KS ) Ref. AMM 73-22-34-000-010 and Ref. AMM 73-22-34-400-010 .
Subtask 75-23-00-710-077-A
B. Do the test given in Para. 3.
5. Close-up
Subtask 75-23-00-860-061-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.
Ref. AMM 31-60-00-860-002 .
(2) On the panel 50VU, push the ENG FADEC GND PWR/2 pushbutton switch.
(3) De-energize the aircraft electrical circuits
Ref. AMM 24-41-00-862-002 .
(4) Make sure that the thrust reverser halves 461AL and 462AR are closed Ref.
AMM 78-32-00-410-010 .
(5) Make sure that the fan cowls 447AL and 448AR are closed Ref. AMM 71-13-00-410-010 .
Figure 75(IAE)-23-00-991-00100-13-A- / SHEET 1/1 - Failure of the Turbine Cooling-Air Valve-Solenoid on Engine
1
Figure 75(IAE)-23-00-991-00300-13-A- / SHEET 1/1 - Failure of the Turbine Cooling-Air Valve-Solenoid on Engine
2
Figure 75(IAE)-23-00-991-00200-13-A- / SHEET 1/1 - Stage 10 to HPT Air Valve
75-24 - (IAE) - HP/LP TURBINE ACTIVE
CLEARANCE CONTROL (ACC) SYSTEM
75-24-00 - (IAE) - HP/LP TURBINE ACTIVE
CLEARANCE CONTROL (ACC) SYSTEM
75-24-00 PB 201 CONF 13 - HP/LP TURBINE ACTIVE CLEARANCE
CONTROL (ACC) SYSTEM - FAULT ISOLATION PROCEDURES [Rev.6 from Feb 2017] 2026.04.04 04:37:13 UTC