Failure of the HPC Stage 10 Bleed Solenoid Valve on Engine 1

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1. Possible Causes
NOTE: This task is to troubleshoot the Clear Language Message (CLM) 10TH BLD VLV SOL/HC/EEC1. The fault
codes or fault acronyms listed in the fault confirmation section below will help you to focus on the correct
cause of this CLM.
· harness from the EEC connector (4000KS-J5) to the HPC stage 10 bleed solenoid valve (4023KS)
· SOL VALVE-HP COMPRESSOR STAGE 10 ( 4023KS )
· EEC ( 4000KS )
· harness from the EEC connector (4000KS-J11) to the HPC stage 10 bleed solenoid valve (4023KS)
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
REFERENCE DESIGNATION
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 71-13-00-410-010 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 73-22-00-710-040 Operational Test of the FADEC SYSTEM on the Ground
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 75-32-53-000-010 Removal of the HPC Stage 10 Solenoid Valve
Ref. AMM 75-32-53-400-010 Installation of the HPC Stage 10 Solenoid Valve
Ref. AMM 78-30-00-440-012 Re-activation of the Thrust Reverser Hydraulic Control Unit (HCU) after
Ground Maintenance
Ref. AMM 78-32-00-410-010 Closing of the Thrust Reverser Halves
70-00-00-03-13 STANDARD PRACTICES - ENGINE - GENERAL - TASK SUPPORTING
DATA
Failure of the HPC Stage 10 Bleed Solenoid Valve on Engine 1(2) SHEET 1
HPC Stage 10 Bleed Solenoid Valve on Engine 1(2) SHEET 1
Figure 73(IAE)-00-00-991-01500-A / SHEET 1/1 - Failure of the HPC Stage 10 Bleed Solenoid Valve
on Engine 1(2) not printed, as per printing preferences
Figure 73(IAE)-00-00-991-02900-A / SHEET 1/1 - HPC Stage 10 Bleed Solenoid Valve on Engine 1(2)
not printed, as per printing preferences
3. Fault Confirmation
Subtask 73-00-00-860-114-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 1 pushbutton switch.
Subtask 73-00-00-710-324-A
B. Identify the Test for Fault Confirmation
NOTE: Troubleshooting can start immediately without doing the fault confirmation if this CLM was shown
in multiple flight or ground legs.
(1) Do the CFDS message decoding and read the scheduled maintenance report to identify the fault
code (for A1 engines) or fault acronym (for A5 engines) related to the CLM (Ref. TSM 70-00-00-03) .
(2) If the readout gives the fault code 67 (for A1 engines) or fault acronym B10WAF (for A5 engines)
in FADEC 1A or FADEC 1B, do the operational test of the FADEC system on the ground for fault
confirmation Ref. AMM 73-22-00-710-040 .
(a) If the test gives the fault code 67 (for A1 engines) or fault acronym B10WAF (for A5 engines) in
FADEC 1A or FADEC 1B or there are two or more occurrences in fault history, continue with fault
isolation Para 4.A.
(b) If the test does not give the fault code 67 (for A1 engines) or fault acronym B10WAF (for A5
engines), and there is no history of faults, send the engine back to service.
4. Fault Isolation
(Ref. Fig. Failure of the HPC Stage 10 Bleed Solenoid Valve on Engine 1(2) SHEET 1) (Ref. Fig. HPC Stage
10 Bleed Solenoid Valve on Engine 1(2) SHEET 1)
Subtask 73-00-00-810-088-A
A. Fault Isolation for Fault Code 67 (for A1 Engines) or Fault Acronym B10WAF (for A5 Engines)
· A wrap around fault was found in channel A or B. The circuit for the HPC stage 10 bleed solenoid valve
is open, shorted to ground or has a wire-to-wire short.
NOTE: After each step that is done during this procedure, you can do the steps in Para 3 to make sure
the fault is corrected.
NOTE: Disconnection and connection of the electrical connectors can correct this fault.
(1) If the fault code or fault acronym was found in channel A, do the steps that follow:
(a) Visually examine the harness from the EEC connector (4000KS-J5) to the HPC stage 10 bleed
solenoid valve (4023KS) Ref. AMM 71-50-00-210-010 .
1 Look for harness damage.
2 Look for loose or damaged connectors.
3 Look for loose or damaged backshells.
NOTE: Loose backshells must be disassembled and examined for internal wiring chafing.
4 If a problem is found with the harness, repair or replace it as necessary.
(b) If no problems were found with the harness, disconnect the electrical connector (4023KS-A) from
the HPC stage 10 bleed solenoid valve (4023KS) Ref. AMM 71-50-00-210-010 . Examine the
male and female parts of the connection:
1 Examine the pins and sockets (contacts) for alignment and damage.
2 Look for contacts pushed rearward into the connector face.
3 Look for ovalized sockets in the connector.
NOTE: This can be done by inserting a harness connector pin into each socket. You must
feel friction when you insert and remove the pin.
4 Repair as necessary.
(c) Do this electrical check of the channel A solenoid circuit in the HPC stage 10 bleed solenoid
valve (4023KS) Ref. ASM 73-25-18:
1 Make sure that contacts 3 and 4 are not shorted to ground.
2 Make sure that contacts 3 and 4 are not shorted to other contacts in the connector.
3 Make sure the resistance from contact 3 to contact 4 is between 41 and 77 ohms.
4 If a problem is found, remove and replace the SOL VALVE-HP COMPRESSOR STAGE
10 ( 4023KS ) Ref. AMM 75-32-53-000-010 and Ref. AMM 75-32-53-400-010 .
(d) If no problems were found, disconnect electrical connector (4000KS-J5) from the EEC (4000KS)
Ref. AMM 71-50-00-210-010 . Examine the male and female parts of the connection:
1 Examine the pins and sockets (contacts) for alignment and damage.
2 Look for contacts pushed rearward into the connector face.
3 Look for ovalized sockets in the connector.
NOTE: This can be done by inserting a harness connector pin into each socket. You must
feel friction when you insert and remove the pin.
4 Repair as necessary.
(e) Do this electrical check of the torque motor wiring in the channel A harness. Look for:
1 Wire to wire shorts and shorts to ground
· Wire-to-wire short check: measure the resistance between the wires. If the resistance is
below 100000 (100K) ohms, then the wires are shorted and must be repaired.
· Wire-to-ground short check: measure the resistance between the wire and the engine
metal or ground. If the resistance is below 100000 (100K) ohms, then the wire is shorted
to ground and must be repaired.
2 Continuity
· Continuity check: measure the resistance between the ends of the same wire. If the
resistance is more than 10 ohms, then the wire must be repaired.
NOTE: An incorrectly wired harness can cause this problem. When you test these circuits,
make sure the contacts are installed in the correct positions in each connector as
specified in the wiring diagram.
HPC Stage 10 Bleed Solenoid Valve Torque Motor Circuit Channel A Harness
HPC Stage 10 Bleed
Solenoid Valve (4023KS)
EEC (4000KS)
(4023KS-A) (4000KS-J5)
Contacts Contacts
3 H
4 C
3 If a problem is found with the harness, repair or replace it as necessary Ref. ASM 73-25-18.
(f) Install all the removed connectors Ref. AMM 70-23-15-912-010 .
(g) Do the test for this fault, listed in Para 3 for fault confirmation.
1 If the test does not give the fault code 67 (for A1 engines) or fault acronym B10WAF (for A5
engines), send the engine back to service.
2 If the test gives the fault code 67 (for A1 engines) or fault acronym B10WAF (for A5
engines), remove and replace the SOL VALVE-HP COMPRESSOR STAGE 10 ( 4023KS )
Ref. AMM 75-32-53-000-010 and Ref. AMM 75-32-53-400-010 .
3 If this fault continues, remove and replace the EEC ( 4000KS ) Ref.
AMM 73-22-34-000-010 and Ref. AMM 73-22-34-400-010 .
(2) If the fault code or fault acronym was found in channel B, do the steps that follow:
(a) Visually examine the harness from the EEC connector (4000KS-J11) to the HPC stage 10 bleed
solenoid valve (4023KS) Ref. AMM 71-50-00-210-010 :
1 Look for harness damage.
2 Look for loose or damaged connectors.
3 Look for loose or damaged backshells.
NOTE: Loose backshells must be disassembled and examined for internal wiring chafing.
4 If a problem is found with the harness, repair or replace it as necessary.
(b) If no problems were found with the harness, disconnect the electrical connector (4023KS-A) from
the HPC stage 10 bleed solenoid valve (4023KS) Ref. AMM 71-50-00-210-010 . Examine the
male and female parts of the connection:
1 Examine the pins and sockets (contacts) for alignment and damage.
2 Look for contacts pushed rearward into the connector face.
3 Look for ovalized sockets in the connector.
NOTE: This can be done by inserting a harness connector pin into each socket. You must
feel friction when you insert and remove the pin.
4 Repair as necessary.
(c) Do this electrical check of the channel B solenoid circuit in the HPC stage 10 bleed solenoid
valve (4023KS) Ref. ASM 73-25-18:
1 Make sure that contacts 6 and 7 are not shorted to ground.
2 Make sure that contacts 6 and 7 are not shorted to other contacts in the connector.
3 Make sure the resistance from contact 6 to contact 7 is between 41 and 77 ohms.
4 If a problem is found, remove and replace the SOL VALVE-HP COMPRESSOR STAGE
10 ( 4023KS ) Ref. AMM 75-32-53-000-010 and Ref. AMM 75-32-53-400-010 .
(d) If no problems were found, disconnect the electrical connector (4000KS-J11) fromthe EEC
(4000KS) Ref. AMM 71-50-00-210-010 . Examine the male and female parts of the connection:
1 Examine the pins and sockets (contacts) for alignment and damage.
2 Look for contacts pushed rearward into the connector face.
3 Look for ovalized sockets in the connector.
NOTE: This can be done by inserting a harness connector pin into each socket. You must
feel friction when you insert and remove the pin.
4 Repair as necessary.
(e) Do this electrical check of the torque motor wiring in the channel B harness. Look for:
1 Wire-to-wire shorts and shorts to ground.
· Wire-to-wire short check: measure the resistance between the wires. If the resistance is
below 100000 (100K) ohms, then the wires are shorted and must be repaired.
· Wire-to-ground short check: measure the resistance between the wire and the engine
metal or ground. If the resistance is below 100000 (100K) ohms, then the wire is shorted
to ground and must be repaired.
2 Continuity
· Continuity check: measure the resistance between the ends of the same wire. If the
resistance is more than 10 ohms, then the wire must be repaired.
NOTE: An incorrectly wired harness can cause this problem. When you test these circuits,
make sure the contacts are installed in the correct positions in each connector as
specified in the wiring diagram.
HPC Stage 10 Bleed Solenoid Valve Torque Motor Circuit Channel B Harness
HPC Stage 10 Bleed
Solenoid Valve (4023KS)
EEC (4000KS)
(4023KS-A) (4000KS-J11)
Contacts Contacts
6 H
7 C
3 If a problem is found with the harness, repair or replace it as necessary Ref. ASM 73-25-18.
(f) Install all the removed connectors Ref. AMM 70-23-15-912-010 .
(g) Do the test for this fault, listed in Para 3 for fault confirmation.
1 If the test does not give the fault code 67 (for A1 engines) or fault acronym B10WAF (for A5
engines), send the engine back to service.
2 If the test gives the fault code 67 (for A1 engines) or fault acronym B10WAF (for A5
engines), remove and replace the SOL VALVE-HP COMPRESSOR STAGE 10 ( 4023KS )
Ref. AMM 75-32-53-000-010 and Ref. AMM 75-32-53-400-010 .
3 If this fault continues, remove and replace the EEC ( 4000KS ) Ref.
AMM 73-22-34-000-010 and Ref. AMM 73-22-34-400-010 .
5. Close-up
Subtask 73-00-00-860-115-A
A. Put the aircraft back to its initial configuration.
(1) Make sure that the thrust reverser halves are closed Ref. AMM 78-32-00-410-010 .
(2) Activate the thrust reverser HCU Ref. AMM 78-30-00-440-012 .
(3) Make sure that the fan cowls 437AL and 438AR are closed Ref. AMM 71-13-00-410-010 .
(4) On the ECAM control panel, set the UPPER DISPLAY and LOWER DISPLAY potentiometers to OFF.
Ref. AMM 31-60-00-860-002 .
(5) On the panel 50VU, push the ENG FADEC GND PWR 1 pushbutton switch.
(6) De-energize the aircraft electrical circuits
Ref. AMM 24-41-00-862-002 .
(7) Remove the warning notice(s). [Rev.6 from Feb 2017] 2026.04.04 04:36:06 UTC