VSV System Interaction Issue on Engine 2

1. Possible Causes
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
75-30-00-810-844-A Failure of the Variable Stator Vane Actuator on Engine 2, Channel A
75-30-00-810-846-A Failure of the Variable Stator Vane Actuator on Engine 2, Channel B
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 31-60-00-860-001 EIS Start Procedure
Ref. AMM 31-60-00-860-002 EIS Stop Procedure
Ref. AMM 75-32-42-640-010 Lubrication of HP Compressor Variable Stator Vane (VSV) Mechanism
Ref. AMM 75-32-42-640-802 Lubrication of the HP Compressor Variable Stator Vane (VSV) Mechanism
70-00-00-03-13 STANDARD PRACTICES - ENGINE - GENERAL - TASK SUPPORTING
DATA
3. Fault Confirmation
Subtask 75-30-00-860-144-A
A. Job Set-Up
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, the 2.5 Bleed Master Actuator, 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) .
(1) Check the post flight report for ECAM and associated failure message.
(2) If the post flight report is not available:
(a) Energize the aircraft electrical circuits
Ref. AMM 24-41-00-861-002 .
(b) On the overhead panel 50VU, select ENG FADEC GND PWR 1 and 2 to the ON position.
(c) On the ECAM control panel, set the UPPER DISPLAY and LOWER DISPLAY potentiometers to
ON Ref. AMM 31-60-00-860-001 .
(d) Read the LAST LEG REPORT of the FADEC 2A menu and the LAST LEG REPORT of the
FADEC 2B menu on the MCDU (Ref. TSM 70-00-00-03) and make a record of the maintenance
message and fault codes.
4. Fault Isolation
Subtask 75-30-00-810-124-A
A. A VSV system interaction fault has occurred and no further maintenance is required on this engine if the
following are true:
NOTE: Single or Dual Track Check Faults can occur as a result of a VSV system interaction problem on
Pre-SB 75-0122 engine. The problem is caused by a combination of factors including: VSV system
friction, pull-back from high power condition, outside air temperature, fuel pressure available, fuel
pressure required to move the VSV system and the scheduling of the PRSOV in the FMU.
(1) The engine has a Pre-SB 75-0122 VSVA installed.
(2) Maintenance status ENG2 FADEC and the ECAM warning ENG2 COMPRESSOR VANE is set with
either or both of the two failure messages:
(a) CHA VSV ACT/HC/EEC2 (Fault Acronym: SVATK)
(b) CHB VSV ACT/HC/EEC2 (Fault Acronym: SVATK)
(3) The following conditions are true:
(a) The ECAM warning appears for less than 60 seconds at transition from take-off to climb power
(Flight phase 5 or Flight phase 6).
(b) ECAM warning may reappear at Flight phase 9 (landing).
NOTE: This is to indicate a class 1 warning was set in flight. It is possible for flight crews or maintenance
personnel to mistake the appearance of this warning on landing (Flight phase 9)
as indicative of a fault at landing rather than when it originally occurred during early climb
(Flight phase 5/6). If no other compressor-related warnings have been set in flight, it is
acceptable to link this Flight phase 9 warning to the Flight phase 5/6 warning/message
set and no log book recording/maintenance for this phase 9 message is necessary.
(c) No apparent surge, over temperature, over limit or obvious change in engine parameters.
(d) No sustained difference in parameters between engine 1 and engine 2.
(4) If all items in step 4.A.(1) through 4.A.(3)(d) are true then continue to step 4.A.(6).
(5) If any items in step 4.A.(1) through 4.A.(3)(d) are not true then proceed to step 4.B.
(6) If this engine is experiencing repeated VSV system interaction faults, then complete a lubrication
of the VSV system at next maintenance opportunity but within 600FH or 750FC, whichever occurs
sooner.
(a) Do the lubrication procedure for Pre-SB 72-0564 for A5 Basic (non-SelectOne) and SelectOne
retrofit engines Ref. AMM 75-32-42-640-010 .
(b) Do the lubrication procedure for Post-SB 72-0564 SelectOne production standard engines Ref.
AMM 75-32-42-640-802 .
NOTE: A rate of four or more events within a calendar month would be considered as repeated
VSV system interaction faults.
NOTE: If the engine is experiencing repeated VSV system interaction faults, consider scheduling
the engine to incorporate a new Post-SB 75-0122 VSVA.
(7) Go to Close Up.
Subtask 75-30-00-810-206-A
B. If the maintenance status ENG2 FADEC and the ECAM warning ENG2 COMPRESSOR VANE is set with
either or both of the two failure messages:
(1) CHA VSV ACT/HC/EEC2 and/or
(2) CHB VSV ACT/HC/EEC2 and one or more of the conditions in step A are not true:
· Do the troubleshooting procedure (Ref. TSM 75-30-00-810-844) and/or
(Ref. TSM 75-30-00-810-846) as applicable.
5. Close-up
Subtask 75-30-00-860-145-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 1 and 2 pushbutton switches.
(3) De-energize the aircraft electrical circuits
Ref. AMM 24-41-00-862-002 . [Rev.6 from Feb 2017] 2026.04.04 04:37:17 UTC