Failure of the Variable Stator Vane Actuator on Engine 2, Channel B

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1. Possible Causes
NOTE: This task is to troubleshoot the clear language message CHB VSV ACT/HC/EEC2. The fault codes listed
in the fault confirmation section below will help you focus on the correct cause of this clear language message.
· ACTUATOR-VSV ( 4022KS )
· EEC ( 4000KS )
· PUMP-HP/LP FUEL ( 2001EM )
2 Job Set-up Information
A. Referenced Information
REFERENCE DESIGNATION
73-00-00-810-901-B Multiple Dual Track Check Faults on the Engine 2
75-30-00-810-853-A VSV System Interaction Issue on Engine 2
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 71-00-00-710-013 Test No.11 : High Power Assurance Test
Ref. AMM 71-13-00-010-010 Opening of the Fan Cowls 437AL(447AL),438AR(448AR)
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 73-12-41-000-010 Removal of the Low Pressure (LP)/High Pressure (HP) Fuel Pump
Ref. AMM 73-12-41-400-010 Installation of the Low Pressure (LP)/High Pressure (HP) Fuel Pump
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 75-32-41-000-010 Removal of the Variable Stator Vane (VSV) Actuator
Ref. AMM 75-32-41-400-010 Installation of the Variable Stator Vane (VSV) Actuator
Ref. AMM 78-30-00-440-012 Re-activation of the Thrust Reverser Hydraulic Control Unit (HCU) after
Ground Maintenance
Ref. AMM 78-32-00-010-010 Opening of the Thrust Reverser Halves
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
REFERENCE DESIGNATION
** ON A/C
POST SB 72-1036 for A/C 0101-0102, 0951-0951
Variable Stator Vane Actuator
VSV Actuator - Channel B SHEET 1
Figure 75(IAE)-30-00-991-00200-A / SHEET 1/2 - Variable Stator Vane Actuator not printed, as per
printing preferences
Figure 75(IAE)-30-00-991-00200-A / SHEET 2/2 - Variable Stator Vane Actuator not printed, as per
printing preferences
Figure 75(IAE)-30-00-991-01100-A / SHEET 1/1 - VSV Actuator - Channel B not printed, as per printing
preferences
3. Fault Confirmation
Subtask 75-30-00-810-134-A
A. Check
NOTE: Multiple dual track check faults can occur on A5 engines Pre-SB 75-0122 as a result of a VSV system
interaction problem. The problem is caused by a combination of factors including: VSV system,
friction, pull-back from high power condition, a hot and/or high airfield, fuel pressure available,
fuel pressure required to move the VSV system and the scheduling of the PRSOV in the FMU.
The fault disappears usually before 6000 cycles. This can also occur on overhauled engines.
(1) Engine Pre SB 75-0122, refer to (Ref. TSM 75-30-00-810-853) to confirm system interaction fault
problem. Otherwise, continue with Para. 3.B.
NOTE: If ECAM Warning ENG 2 COMPRESSOR VANE also appears, this is not a system interaction
fault problem.
Subtask 75-30-00-860-112-A
B. Job Set-Up
(1) Energize the aircraft electrical circuits
Ref. AMM 24-41-00-861-002 .
(2) On the ENG section of maintenance panel 50VU, put the FADEC GND PWR 2 pushbutton switch in
the ON position.
Subtask 75-30-00-710-164-A
C. Identification of the Test to Make Sure that the Fault is Present
NOTE: Troubleshooting can start immediately without doing the fault confirmation if the clear language
message was shown in multiple flight or ground legs.
(1) Do the CFDS message decoding to identify the fault code related to the clear language message
(Ref. TSM 70-00-00-03) .
(2) If the readout gives the fault acronym SVAWAF or the fault acronym SVAL in FADEC 2B, do the
FADEC system operational test for fault confirmation Ref. AMM 73-22-00-710-040 .
(a) If the test gives the fault acronym SVAWAF in FADEC 2B, or there are two or more occurrences
in fault history, continue with fault isolation Para. 4.A.
(b) If the test gives the fault acronym SVAL in FADEC 2B, or there are two or more occurrences in
fault history, continue with fault isolation Para. 4.B.
(c) If the test does not give the fault acronym SVAWAF or the fault acronym SVAL, and there is no
history of faults, return the engine to service.
(3) If the readout gives the fault acronym SVATK in FADEC 2B, do the steps in Para. 3.D. for fault
confirmation.
(a) If the test gives the fault acronym SVATK or there are two or more occurrences in fault history,
continue with fault isolation Para. 4.C.
(b) If the test does not give the fault acronym SVATK, and there is no history of faults, return the
engine to service.
Subtask 75-30-00-710-286-A
D. Test for Fault Acronym SVATK
(1) Do a high power assurance test for fault confirmation as follows:
(a) On the ENG section of maintenance panel 50VU, put the FADEC GND PWR 2 pushbutton switch
in the ON position.
NOTE: This action resets the FADEC memory.
(b) Do the test No. 11: high power assurance test Ref. AMM 71-00-00-710-013 .
(c) Read the LAST LEG REPORT of the FADEC 2B menu on the MCDU (Ref. TSM 70-00-00-03) .
1 Make a record of the failure message.
2 Make a record of the channel FADEC 2B which found the fault.
3 Do the CFDS message decoding and read the flight data and ground data to identify the
fault code.
NOTE: Multiple dual track check faults may indicate a failed fuel pump. Four control units on
the engine are driven by HP fuel: the VSV actuator (4022KS), the 2.5 bleed controller,
the ACOC air modulating valve and the active clearance control actuator. If you
have faults with two or more of these units, you must follow the multiple dual track
check faults procedure (Ref. TSM 73-00-00-810-901) .
4. Fault Isolation
** ON A/C
POST SB 72-1036 for A/C 0101-0102, 0951-0951
(Ref. Fig. Variable Stator Vane Actuator)
Figure 75(IAE)-30-00-991-00200-A / SHEET 1/2 - Variable Stator Vane Actuator not printed, as per printing
preferences
Figure 75(IAE)-30-00-991-00200-A / SHEET 2/2 - Variable Stator Vane Actuator not printed, as per printing
preferences
(Ref. Fig. VSV Actuator - Channel B SHEET 1)
Subtask 75-30-00-810-115-A
A. Fault Isolation for Fault Acronym SVAWAF
A torque motor Wrap Around Fault (WAF) was found in channel B. The circuit for the VSV actuator is
open, short-to-ground, or has a wire-to-wire short.
NOTE: At any time during this procedure, you can do the steps in Para. 3. to make sure that the fault is
corrected.
NOTE: Removal and installation of the electrical connectors can correct this fault.
(1) If the fault was found in channel B, do the following steps:
(a) Visually examine the harness from the EEC connector (4000KS-J9) to the VSV actuator
(4022KS) 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 as necessary.
(b) If no problems are found with the harness, disconnect the electrical connector (4022KS-B) from
the VSV actuator (4022KS) 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 elongated sockets in the connector.
NOTE: This can be done by inserting a harness connector pin into each suspect socket. You
must feel friction when inserting and removing the pin.
4 Repair as necessary.
(c) Do this electrical check of the channel B torque motor circuit in the VSV actuator (4022KS) Ref.
ASM 73-25-18:
1 Make sure that contacts A and C are not shorted to ground.
2 Make sure that contacts A and C are not shorted to any other contacts in the connector.
3 Make sure that the resistance from contact A to contact C is between 30 and 36 ohms.
4 If a problem was found, remove and replace the ACTUATOR-VSV ( 4022KS ) Ref.
AMM 75-32-41-000-010 and Ref. AMM 75-32-41-400-010 .
(d) If no problems were found, disconnect the electrical connector (4000KS-J9) 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 elongated sockets in the connector.
NOTE: This can be done by inserting a harness connector pin into each suspect socket. You
must feel friction when inserting and removing 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 need to be repaired.
· Wire-to-ground short check: Measure the resistance between the wire and engine metal or
ground. If the resistance is below 100000 (100K) ohms, then the wire is shorted-to-ground
and needs to be repaired.
2 Continuity
· Continuity check: Measure the resistance between the ends of the same wire. If the
resistance is above 10 ohms, then the wire needs to be repaired.
NOTE: An incorrectly wired harness can cause this problem. When testing these circuits,
make sure that the contacts are in the correct positions in each connector as specified
in the wiring diagram.
VSV Actuator Torque Motor Circuit Channel B Harness
VSV Actuator (4022KS) EEC (4000KS)
4022KS-B 4000KS-J9
Contacts Contacts
A H
C G
3 If a problem is found with the harness, repair or replace as necessary Ref. ASM 73-25-18.
(f) Install all 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 acronym SVAWAF, return the engine to service.
2 If the test gives the fault acronym SVAWAF, remove and replace the ACTUATORVSV
( 4022KS ) Ref. AMM 75-32-41-000-010 and Ref. AMM 75-32-41-400-010 .
3 If the fault continues, remove and replace the EEC ( 4000KS ) Ref.
AMM 73-22-34-000-010 and Ref. AMM 73-22-34-400-010 .
PRE SB 72-1036 for A/C 0101-0102, 0951-0951
Subtask 75-30-00-810-201-A
B. Fault Isolation for Fault Acronym SVAL
The VSV actuator LVDT signal is out of range. This is caused by an open, short-to-ground, or a wire-towire
short in this circuit.
NOTE: At any time during this procedure, you can do the steps in Para. 3. to make sure that the fault is
corrected.
NOTE: Removal and installation of the electrical connectors can correct this fault.
(1) If the fault was found in channel B, do the following steps:
(a) Visually examine the harness from the EEC connector (4000KS-J8) to the VSV actuator
(4022KS) 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 as necessary.
(b) If no problems are found with the harness, disconnect the electrical connector (4022KS-D) from
the VSV actuator (4022KS) 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 elongated sockets in the connector.
NOTE: This can be done by inserting a harness connector pin into each suspect socket. You
must feel friction when inserting and removing the pin.
4 Repair as necessary.
(c) Do the electrical check of the channel B LVDT circuit in the VSV actuator Ref. ASM 73-25-18.
1 Make sure that contacts A, B, D and E are not shorted-to-ground.
2 Make sure that contacts A, B, D and E are not shorted to any other contacts in the
connector.
3 Make sure that the resistance from contact A to contact B is between 850 and 1100 ohms.
4 Make sure that the resistance from contact D to contact E is between 250 and 340 ohms.
5 If a problem was found, remove and replace the ACTUATOR-VSV ( 4022KS ) Ref.
AMM 75-32-41-000-010 and Ref. AMM 75-32-41-400-010 .
(d) If no problems were found, disconnect the electrical connector (4000KS-J8) 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 elongated sockets in the connector.
NOTE: This can be done by inserting a harness connector pin into each suspect socket. You
must feel friction when inserting and removing the pin.
4 Repair as necessary.
(e) Do this electrical check of the LVDT wiring in the channel B. 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 need to be repaired.
· Wire-to-ground short check: Measure the resistance between the wire and engine metal or
ground. If the resistance is below 100000 (100K) ohms, then the wire is shorted-to-ground
and needs to be repaired.
2 Continuity
· Continuity check: Measure the resistance between the ends of the same wire. If the
resistance is above 10 ohms, then the wire needs to be repaired.
NOTE: An incorrectly wired harness can cause this problem. When testing these circuits,
make sure that the contacts are in the correct positions in each connector as specified
in the wiring diagram.
VSV Actuator LVDT Circuit Channel B Harness
VSV Actuator (4022KS) EEC (4000KS)
4022KS-D 4000KS-J8
Contacts Contacts
A h
B s
D U
E T
3 If a problem is found with the harness, repair or replace as necessary Ref. ASM 73-25-18.
(f) Install all 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 acronym SVAL, return the engine to service.
2 If the test gives the fault acronym SVAL, remove and replace the ACTUATORVSV
( 4022KS ) Ref. AMM 75-32-41-000-010 and Ref. AMM 75-32-41-400-010 .
3 If the fault continues, remove and replace the EEC ( 4000KS ) Ref.
AMM 73-22-34-000-010 and Ref. AMM 73-22-34-400-010 .
** ON A/C
POST SB 72-1036 for A/C 0101-0102, 0951-0951
Subtask 75-30-00-810-201-B
B. Fault Isolation for Fault Acronym SVAL
The VSV actuator LVDT signal is out of range. This is caused by an open, short-to-ground, or a wire-towire
short in this circuit.
NOTE: At any time during this procedure, you can do the steps in Para. 3. to make sure that the fault is
corrected.
NOTE: Removal and installation of the electrical connectors can correct this fault.
(1) If the fault was found in channel B, do the following steps:
(a) Visually examine the harness from the EEC connector (4000KS-J8) to the VSV actuator
(4022KS) 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 as necessary.
(b) If no problems are found with the harness, disconnect the electrical connector (4022KS-D) from
the VSV actuator (4022KS) 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 elongated sockets in the connector.
NOTE: This can be done by inserting a harness connector pin into each suspect socket. You
must feel friction when inserting and removing the pin.
4 Repair as necessary.
(c) Do the electrical check of the channel B LVDT circuit in the VSV actuator Ref. ASM 73-25-18.
1 Make sure that contacts A, B, D and E are not shorted-to-ground.
2 Make sure that contacts A, B, D and E are not shorted to any other contacts in the
connector.
3 Make sure that the resistance from contact A to contact B is between 840 and 1260 ohms.
4 Make sure that the resistance from contact D to contact E is between 328 and 482 ohms.
5 If a problem was found, remove and replace the ACTUATOR-VSV (4022KS) Ref.
AMM 75-32-41-000-010 and Ref. AMM 75-32-41-400-010 .
(d) If no problems were found, disconnect the electrical connector (4000KS-J8) 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 elongated sockets in the connector.
NOTE: This can be done by inserting a harness connector pin into each suspect socket. You
must feel friction when inserting and removing the pin.
4 Repair as necessary.
(e) Do this electrical check of the LVDT wiring in the channel B. 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 need to be repaired.
· Wire-to-ground short check: Measure the resistance between the wire and engine metal or
ground. If the resistance is below 100000 (100K) ohms, then the wire is shorted-to-ground
and needs to be repaired.
2 Continuity
· Continuity check: Measure the resistance between the ends of the same wire. If the
resistance is above 10 ohms, then the wire needs to be repaired.
NOTE: An incorrectly wired harness can cause this problem. When testing these circuits,
make sure that the contacts are in the correct positions in each connector as specified
in the wiring diagram.
VSV Actuator LVDT Circuit Channel B Harness
VSV Actuator (4022KS) EEC (4000KS)
4022KS-D 4000KS-J8
Contacts Contacts
A h
VSV Actuator LVDT Circuit Channel B Harness
VSV Actuator (4022KS) EEC (4000KS)
B s
D U
E T
3 If a problem is found with the harness, repair or replace as necessary Ref. ASM 73-25-18.
(f) Install all 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 acronym SVAL, return the engine to service.
2 If the test gives the fault acronym SVAL, remove and replace the ACTUATORVSV
( 4022KS ) Ref. AMM 75-32-41-000-010 and Ref. AMM 75-32-41-400-010 .
3 If the fault continues, remove and replace the EEC ( 4000KS ) Ref.
AMM 73-22-34-000-010 and Ref. AMM 73-22-34-400-010 .
Subtask 75-30-00-810-202-A
C. Fault Isolation for Fault Acronym SVATK
A track-check fault was found in channel B. The VSV actuator (4022KS) cannot move to its commanded
position or it is moving slower than normal.
NOTE: At any time during this procedure, you can do the steps in Para. 3. to make sure that the fault is
corrected.
NOTE: This fault is typically caused by a mechanical problem and not an electrical problem.
(1) Open the thrust reverser halves Ref. AMM 78-32-00-010-010 and fan cowls as necessary Ref.
AMM 71-13-00-010-010 .
(2) Remove and replace the ACTUATOR-VSV ( 4022KS ) Ref. AMM 75-32-41-000-010 and Ref.
AMM 75-32-41-400-010 .
(3) Do the test listed in Para. 3. for fault confirmation.
(4) If the test was satisfactory, return the engine to service.
(5) If the fault continues, remove and replace the PUMP-HP/LP FUEL ( 2001EM ) Ref.
AMM 73-12-41-000-010 and Ref. AMM 73-12-41-400-010 .
(6) If the fault continues, remove and replace the EEC ( 4000KS ) Ref. AMM 73-22-34-000-010 and
Ref. AMM 73-22-34-400-010 .
(7) If the fault continues, do the following:
(a) Do the steps for the fault acronym SVAWAF listed in Para. 4.A. above.
(b) Do the steps for the fault acronym SVAL listed in Para. 4.B. above.
5. Close-up
Subtask 75-30-00-860-113-A
A. Put the aircraft back to its initial configuration.
(1) If opened, close the thrust reverser halves Ref. AMM 78-32-00-410-010 .
(2) Activate the thrust reverser HCU Ref. AMM 78-30-00-440-012 .
(3) If opened, close the fan cowls 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 ENG section of maintenance panel 50VU, push the FADEC GND PWR 2 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 04:37:16 UTC