DOC AIRBUS | TSM A320FThrust Reverser Pressurized on Engine 1
1. Possible Causes
WARNING: THE THRUST REVERSER HYDRAULIC CONTROL UNIT (HCU) MUST BE DEACTIVATED BEFORE
WORKING ON OR AROUND THE THRUST REVERSER. FAILURE TO DEACTIVATE THE
HCU CAN RESULT IN INADVERTENT THRUST REVERSER OPERATION AND INJURY TO
PERSONNEL AND/OR DAMAGE TO EQUIPMENT.
· heat source in the fan zone
· HCU-THRUST REV (4101KS)
· LVDT-THRUST REV UPPER L ACTUATOR ( 4004KS )
· LVDT-THRUST REV UPPER R ACTUATOR ( 4003KS )
· LOCK IND/PROX SENSOR-THRUST REV LOWER R ACTUATOR ( 4006KS )
· LOCK IND/PROX SENSOR-THRUST REV LOWER L ACTUATOR ( 4007KS )
· EEC ( 4000KS )
2 Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
REFERENCE QTY DESIGNATION
No specific AR WARNING NOTICE(S)
B. Referenced Information
REFERENCE DESIGNATION
Ref. AMM 24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied from the External
Power
Ref. AMM 30-21-49-200-010 Detailed Visual Inspection of the Inlet Cowl Anti-Ice Supply Ducts and
Associated Hardware in the Core Compartment
Ref. AMM 30-21-49-790-010 Leak Test of the Inlet Cowl Anti-Ice Supply Ducts with the Engine in
Operation
Ref. AMM 31-36-00-740-008 Access to the Parameter Call-Up Menus
Ref. AMM 31-60-00-860-002 EIS Stop Procedure
REFERENCE DESIGNATION
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 73-22-34-000-010 Removal of the Electronic Engine Control (EEC)
Ref. AMM 73-22-34-400-010 Installation of the Electronic Engine Control (EEC)
Ref. AMM 73-22-49-220-040 Purge the Burner Pressure Sensor Tube
Ref. AMM 78-31-00-710-041 Operational Test of the Thrust Reverser System with the CFDS
Ref. AMM 78-31-51-000-010 Removal of the Thrust Reverser Hydraulic Control Unit
Ref. AMM 78-31-51-200-010 General Check of the Hydraulic Control Unit (HCU) General Condition
and Filter Indicator, without component removal
Ref. AMM 78-31-51-400-010 Installation of the Thrust Reverser Hydraulic Control Unit
Ref. AMM 78-32-43-000-010 Removal of the C-Duct Locking Actuator
Ref. AMM 78-32-43-400-010 Installation of the C-Duct Locking Actuator
Ref. AMM 78-32-48-000-010 Removal of the C-Duct Non-Locking Actuator
Ref. AMM 78-32-48-400-010 Installation of the C-Duct Non-Locking Actuator
Ref. AMM 80-13-49-200-010 General Check of the Starter Duct
Ref. AMM 80-13-49-700-010 Leak Test of the Starter Ducts with the Engine in Operation
3. Fault Confirmation
Subtask 78-30-00-710-170-B
A. Test
(1) Do the operational test of the thrust reverser system with the CFDS (through FADEC 1A and 1B
menus) Ref. AMM 78-31-00-710-041 .
4. Fault Isolation
Subtask 78-30-00-810-126-B
A. If the test confirms the fault:
(1) Check for signs of HCU overheat:
(a) examine the HCU for heat damage Ref. AMM 78-31-51-200-010 .
(b) make a record of any heat damage to the HCU.
(2) Make sure that there is no source of abnormal heat generation under the fan cowls:
(a) examine the under cowl area for evidence of fire.
(b) examine starter ducts for leaks Ref. AMM 80-13-49-200-010 .
(c) examine the thermal anti-ice ducts for leaks in the fan zone only Ref. AMM 30-21-49-200-010 .
(d) do a leak test of the starter duct Ref. AMM 80-13-49-700-010 .
(e) do a leak test of the thermal anti-ice ducts in the fan zone only Ref. AMM 30-21-49-790-010 .
(f) examine the Pb line for leaks Ref. AMM 73-22-49-220-040 .
(g) rectify any leak or heat source in the fan zone .
(3) Replace the HCU-THRUST REV (4101KS) Ref. AMM 78-31-51-000-010 and Ref.
AMM 78-31-51-400-010 .
(4) If the fault continues:
(a) On the maintenance panel 50VU:
1 Push the ENG FADEC GND PWR P/BSW.
2 Make sure that the ON legend of the ENG FADEC GND P/BSW is on.
(b) Enter the alpha call-up code Ref. AMM 31-36-00-740-008 : TRP
1 if the LVDT signal value is more than 3.19 per cent:
· replace the LVDT-THRUST REV UPPER L ACTUATOR ( 4004KS ) Ref.
AMM 78-32-48-000-010 and Ref. AMM 78-32-48-400-010 .
2 if the LVDT signal value is less than 3.19 per cent:
· open the fan cowl door Ref. AMM 71-13-00-010-010 .
· disconnect the plug connector 4004KS-A from the LVDT-THRUST REV UPPER L
ACTUATOR ( 4004KS ) .
· move the ENG MASTER 1 lever from ON to OFF position
NOTE: This action resets the FADEC memory.
a if the LVDT signal value is more than 3.19 per cent
· replace the LVDT-THRUST REV UPPER R ACTUATOR ( 4003KS ) Ref.
AMM 78-32-48-000-010 and Ref. AMM 78-32-48-400-010 .
(c) On the maintenance panel 50VU:
1 Release the ENG FADEC GND PWR P/BSW.
2 Make sure that the ON legend of the ENG FADEC GND PWR P/BSW is off.
3 Put a WARNING NOTICE(S) to tell persons not to energize the FADEC system 1(2).
(d) Connect the plug connector 4004KS-A to the LVDT-THRUST REV UPPER L
ACTUATOR ( 4004KS ) .
(e) Close the fan cowl door Ref. AMM 71-13-00-410-010 .
(5) If the fault continues:
· replace the LOCK IND/PROX SENSOR-THRUST REV LOWER R ACTUATOR ( 4006KS )
and the LOCK IND/PROX SENSOR-THRUST REV LOWER L ACTUATOR ( 4007KS ) Ref.
AMM 78-32-43-000-010 and Ref. AMM 78-32-43-400-010 .
(6) If the fault continues:
· replace the EEC ( 4000KS ) Ref. AMM 73-22-34-000-010 and Ref. AMM 73-22-34-400-010 .
Subtask 78-30-00-710-171-B
B. Do the test given in Para. 3.
5. Close-up
Subtask 78-30-00-860-096-B
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 maintenance panel 50VU:
(a) push the ENG FADEC GND PWR/1 pushbutton switch.
(b) remove the warning notice
(3) De-energize the aircraft electrical circuits
Ref. AMM 24-41-00-862-002 . [Rev.6 from Feb 2017] 2026.04.04 04:38:08 UTC