DOC AIRBUS | TSM A320FMultiple Dual Track Check Faults on the Engine 2
1. Possible Causes
· PUMPS-LP/HP FUEL (2001EM1)
· FMU ( 4000KC )
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 28-24-00-710-002 Operational Test of the ENG 1(2) LP Fuel Valve
Ref. AMM 28-24-41-000-001 Removal of the LP Fuel Valve
Ref. AMM 28-24-41-400-001 Installation of the LP Fuel Valve
Ref. AMM 28-24-51-000-001 Removal of the LP Fuel Valve Actuator
Ref. AMM 28-24-51-400-001 Installation of the LP Fuel Valve Actuator
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 71-00-00-710-018 Discontinued Start, Restart and Shutdown Procedures
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 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 73-22-52-000-010 Removal of the Fuel Metering Unit (FMU)
Ref. AMM 73-22-52-400-010 Installation of the Fuel Metering Unit (FMU)
Ref. AMM 78-32-00-410-010 Closing of the Thrust Reverser Halves
3. Fault Confirmation
Subtask 73-00-00-860-192-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 and 2 pushbutton switches.
Subtask 73-00-00-710-271-A
B. Test
CAUTION: FAILURE OF FUEL DRIVEN UNITS CAN RESULT IN AN OVERSPEED. DURING ENGINE
ACCELERATIONS, N2 MAY INCREASE MUCH MORE RAPIDLY THAN NORMAL.
WHEN DOING THE HIGH POWER ASSURANCE TEST BELOW (REF. TEST NO. 11 -
ATA 71 - ADJUSTMENT/TEST), MOVE THE THROTTLE SLOWLY (25 TO 30 SECONDS)
BETWEEN THE SPECIFIED POWER SETTINGS. CLOSELY OBSERVE N2 AT ALL
TIMES. DO NOT ALLOW SPEEDS TO EXCEED THE ROTOR OPERATION SPEED LIMITS
(REF. ATA 71 - MAINTENANCE PRACTICES).
(1) Do an operational test of the ENG 2 Low Pressure (LP) fuel valve Ref. AMM 28-24-00-710-002 .
(a) If a fault is found go to Para 4. A.
(2) On the panel 50VU, push the ENG FADEC GND PWR 2 pushbutton switch and release it again.
NOTE: This action resets the FADEC memory.
(3) Do the test No. 11: high power assurance test Ref. AMM 71-00-00-710-013 , except paragraph 4.A
which is modified as follows:
(a) Slowly increase the power of the test engine to 1.08 EPR and let the engine become stable for
two minutes.
Compare the indicated parameters of tested engine No.1 to the parameters of engine No.2
running at 1.08 EPR as well. If you see a significant parameter split, which cannot be explained
by the engines' deterioration condition, go to step (d).
NOTE: A split in EGT and rotor speeds between the engines can be caused by different deterioration
levels. Therefore the actual margin of EGT and rotor speeds of the two engines
needs to be taken into account for the parameter comparison.
(b) Slowly increase the power of the test engine to 1.25 EPR (or the nearest EPR required to ensure
that the engine is at or above 75 percent N1) and let the engine become stable for two minutes.
(c) If the power setting in step (b) did not reach the MAX CLIMB detent, then slowly increase the
power of the test engine to the MAX CLIMB detent and stabilize for one minute, otherwise go to
step (d).
(d) Slowly decrease the speed of the test engine to MIN IDLE.
(e) Decrease the power of the other engine to MIN IDLE.
(f) Operate both engines at MIN IDLE for five minutes to allow the engines to cool.
(g) Do a shutdown of the engines by the Discontinued Start, Restart and Shutdown Procedure Ref.
AMM 71-00-00-710-018 .
(4) 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) and make a record of the maintenance message.
(a) If the test gives a maintenance message, go to Para 4.B.
4. Fault Isolation
Subtask 73-00-00-810-279-A
A. Fault Isolation for the LP Fuel Valve
(1) Remove the ENG 2 LP fuel valve actuator Ref. AMM 28-24-51-000-001 .
(2) Remove the ENG 2 LP fuel valve Ref. AMM 28-24-41-000-001 .
(3) Install the ENG 2 LP fuel valve Ref. AMM 28-24-41-400-001 .
(4) Install the ENG 2 LP fuel valve actuator Ref. AMM 28-24-51-400-001 .
Subtask 73-00-00-810-193-A
B. If the test gives one of the following maintenance messages:
ACC ACT/HC/EEC2 or
ACOC AIR MOD VLV/HC/EEC2 or
FUL DIV RET VLV/HC/EEC2 or
CHA VSV ACT/HC/EEC2 or
CHB VSV ACT/HC/EEC2 or
CHA 2.5 BLD ACT/HC/EEC2 or
CHB 2.5 BLD ACT/HC/EEC2
· do the related trouble shooting procedure.
(1) If the test gives two or more of these messages at the same time, or one right after the other:
(a) Open the fan cowls 447AL and 448AR Ref. AMM 71-13-00-010-010 .
(b) Check if recent fuel system maintenance or Emergency Shutdown (Fire Handle) may have
caused low fuel pressure or air in fuel lines.
(c) If the fault continues:
· replace the PUMPS-LP/HP FUEL (2001EM1) Ref. AMM 73-12-41-000-010 and Ref.
AMM 73-12-41-400-010 .
(d) If the fault continues:
· replace the FMU ( 4000KC ) Ref. AMM 73-22-52-000-010 and Ref.
AMM 73-22-52-400-010 .
Subtask 73-00-00-710-272-A
C. Do the test given in Para. 3.
5. Close-up
Subtask 73-00-00-860-193-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 . [Rev.6 from Feb 2017] 2026.04.04 04:36:08 UTC