DOC AIRBUS | TSM A320FN2 more than the Limit on Engine 1
1. Possible Causes
· HP compressor
· HP turbine
· VSV mechanism
· HPC bleed valve system
· FMU ( 4000KC )
· EEC ( 4000KS )
2 Job Set-up Information
A. Referenced Information
REFERENCE DESIGNATION
75-30-00-810-843-A Failure of the Variable Stator Vane Actuator on Engine 1, Channel A
75-30-00-810-845-A Failure of the Variable Stator Vane Actuator on Engine 1, Channel B
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 71-00-00-710-013 Test No.11 : High Power Assurance Test
Ref. AMM 71-00-00-860-010 Engine Operation Limits, Guidelines and Special Procedures (Pre SB
79-0070)
Ref. AMM 72-00-00-200-013 Borescope Inspection of inside of Combustion Chamber and HP turbine
stage 1 Vanes
Ref. AMM 72-00-00-200-014 Borescope Inspection of the Stage 1 High Pressure Turbine (HPT)
Blades and Duct Segments
Ref. AMM 72-00-00-200-015 Borescope Inspection of the Stage 2 HPT Blades and Duct Segments
Ref. AMM 72-00-00-200-016 Inspection of the HP Compressor
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. AMM 73-22-52-000-010 Removal of the Fuel Metering Unit (FMU)
Ref. AMM 73-22-52-400-010 Installation of the Fuel Metering Unit (FMU)
Ref. AMM 75-32-42-200-010 Inspection of the VSV Mechanism
Ref. AMM 77-00-00-710-041 Reset of the N1, N2 and EGT Max Pointers
70-00-00-03-13 STANDARD PRACTICES - ENGINE - GENERAL - TASK SUPPORTING
DATA
3. Fault Confirmation
Subtask 77-00-00-710-232-A
A. Test
(1) Get the EIS (DMC1) ENGINE OVER SPD/TEMP menu on the MCDU Ref. AMM 77-00-00-710-041 .
(2) On the EIS (DMC1) ENGINE OVER SPD/TEMP menu, push the line key adjacent to N2 E1 to get the
N2 E1 OVERSPEED menu.
(3) On the N2 E1 OVERSPEED menu, do a check to see if there is or not an overspeed record.
Subtask 77-00-00-710-233-A
B. Check for N2 Rotor Speed Limits
· do the engine operation limits, guidelines and special procedures Ref. AMM 71-00-00-860-010 .
NOTE: You can get the overlimit/time from the exceedance report.
4. Fault Isolation
Subtask 77-00-00-810-174-A
A. If the test shows that N2 is more than the limit:
(1) Correct the cause of the overspeed:
· Do an inspection of the HP compressor Ref. AMM 72-00-00-200-016 and the HP turbine Ref.
AMM 72-00-00-200-013 , Ref. AMM 72-00-00-200-014 and Ref. AMM 72-00-00-200-015 .
(2) Do the inspection/check for the N2 rotor speed overlimit Ref. AMM 71-00-00-860-010 .
(3) If there is no fault:
· Read the LAST LEG REPORT of the FADEC 1A and the FADEC 1B menu on the MCDU
(Ref. TSM 70-00-00-03) and make a record of the maintenance message.
(a) If you have received the following maintenance message CHA VSV ACT/HC/EEC1 for FADEC
1A:
· Do the following task (Ref. TSM 75-30-00-810-843) as necessary by the engine build
standard.
(b) If you have received the following maintenance message CHB VSV ACT/HC/EEC1 for FADEC
1B:
· Do the following task (Ref. TSM 75-30-00-810-845) as necessary by the engine build
standard.
(c) If you do not receive one of the above fault messages:
· Do an inspection of the VSV mechanism Ref. AMM 75-32-42-200-010 .
(d) If there is no fault, do an functional test of the HPC bleed valve system and repair as necessary:
· Do the high power assurance test Ref. AMM 71-00-00-710-013 .
(e) If there is no fault:
· Replace the FMU ( 4000KC ) , Ref. AMM 73-22-52-000-010 and Ref.
AMM 73-22-52-400-010 .
· Replace the EEC ( 4000KS ) , Ref. AMM 73-22-34-000-010 and Ref.
AMM 73-22-34-400-010 .
5. Close-up
Subtask 77-00-00-860-085-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) De-energize the aircraft electrical circuits
Ref. AMM 24-41-00-862-002 . [Rev.6 from Feb 2017] 2026.04.04 04:37:48 UTC