Thrust Reverser ICV Test (Menu Mode) [CFML]

TASK 73-29-00-740-805-A
Thrust Reverser ICV Test (Menu Mode)

WARNING: MAKE SURE THAT:

THE TRAVEL RANGES OF THE THRUST REVERSERS OF ENGINE 1 (2) ARE CLEAR OF ALL TOOLS, EQUIPMENT AND PERSONS
THE THRUST REVERSER COWLS ARE CLOSED AND LATCHED
THE THROTTLE CONTROL LEVER OF ENGINE 1 (2) IS IN THE IDLE POSITION (ZERO ON THE SCALE).

IF YOU DO NOT OBEY THESE PRECAUTIONS, INJURY TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR.

ZONE: 400

1. Reason for the Job
The isolation control valve test will confirm that the isolation control valve is not failed in the open position. The isolation control valve test is similar to the Cycle test (73-29-00-740-804 Thrust Reverser Cycle Test Menu Mode), except during this test, the EEC will not energize the isolation control valve solenoid. The purpose of this test is to isolate whether the thrust reverser isolation control valve or the pressure switch is failed pressurized, without an engine start. This test will energize the Directional Control Valve (DCV) while the isolation control valve remains de-energized to determine whether or not the thrust reverser system is failed pressurized. Only the isolation control valve "failed open" and "dual pressure switch on" faults will be reported for this test.
2. Job Set-up Information
A. Work Zones and Access Panels

ZONE/ACCESS	ZONE DESCRIPTION
400	POWER PLANT, NACELLES AND PYLONS

B. Referenced Information

REFERENCE	DESIGNATION
TASK 24-41-00-861-002-A	Energize the Aircraft Electrical Circuits from the External Power
TASK 24-41-00-861-002-A-01	Energize the Aircraft Electrical Circuits from the APU
TASK 24-41-00-861-002-A-02	Energize the Aircraft Electrical Circuits from Engine 1(2)
TASK 24-41-00-862-002-A	De-energize the Aircraft Electrical Circuits Supplied from the External Power
TASK 24-41-00-862-002-A-01	De-energize the Aircraft Electrical Circuits Supplied from the APU
TASK 24-41-00-862-002-A-02	De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)
TASK 29-23-00-863-001-A	Pressurize the Green Hydraulic System from the Yellow Hydraulic System through the PTU with the Electric Pump
TASK 29-23-00-864-001-A	Depressurize the Green and Yellow Hydraulic Systems after Operation of the PTU
TASK 29-24-00-863-001-A	Pressurize the Yellow Hydraulic System with the Electric Pump
TASK 29-24-00-864-001-A	Depressurize the Yellow Hydraulic System
TASK 31-32-00-860-012-A	Procedure to Get Access to the SYSTEM REPORT/TEST/ENG Page
TASK 78-30-00-440-808-A	Reactivation of the Thrust Reverser System after Flight
Thrust Reverser ICV Test (Menu Mode)

3. Job Set-up
Subtask 73-29-00-861-067-A

A. Energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-861-002).

Subtask 73-29-00-865-078-A

B. Make sure that this(these) circuit breaker(s) is(are) closed:

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C ALL
FOR FIN: 4020KM1 (POWER PLANTDEMOUNTABLE, ENGINE 1)
49VU	ENGINE/1/FADEC A/AND EIU 1	2KS1	A04
121VU	ENGINE/ENG1/FADEC B/AND EIU 1	4KS1	R40
FOR FIN: 4020KM2 (POWER PLANTDEMOUNTABLE, ENGINE 2)
49VU	ENGINE/2/FADEC A/AND EIU 2	2KS2	A05
121VU	ENGINE/ENG2/FADEC B/AND EIU2	4KS2	R41

Subtask 73-29-00-860-092-A

C. Aircraft Maintenance Configuration
(1) On ENG panel 115VU:
(a) Make sure that the ENG MASTER switch 1(2) is set to OFF.
(b) Make sure that the ENG/MODE rotary selector switch is set to NORM.
(2) On the ENG section of maintenance panel 50VU:
(a) Release the FADEC GND PWR/1(2) pushbutton switch. The ON legend of this pushbutton switch comes on.

NOTE: After the FADEC is energized, wait ten seconds before you start the test. If you do not wait ten seconds, the interactive mode stops the EEC self-test and this can cause spurious faults.

(3) On the left or right MCDU, get the SYSTEM REPORT/TEST/ENG page (Ref. AMM TASK 31-32-00-860-012).
(4) Make sure that the thrust reverser system is in active configuration (Ref. AMM TASK 78-30-00-440-808)

(5) Pressurize the hydraulic system:
(a) On the lower ECAM Display Unit (DU) get the HYD page. Make sure that the Green (Yellow) pressure is zero.
(b) Release the HYD/LEAK MEASUREMENT VALVES/B/G/Y pushbutton switches (on the pushbutton switch the OFF legend comes on).
(c) For 4020KM1 (POWER PLANT-DEMOUNTABLE,ENG1) -Pressurize the Green hydraulic system with the Yellow hydraulic system through the Power Transfer Unit (PTU) with electric pump (Ref. AMM TASK 29-23-00-863-001)- On the lower ECAM DU, make sure that the HYD page shows that the pressure of the Green system is 3000 psi (206.8427 bar).
(d) For 4020KM2 (POWER PLANT-DEMOUNTABLE,ENG2) Pressurize the auxiliary Yellow hydraulic system with the electric pump (Ref. AMM TASK 29-24-00-863-001). - On the lower ECAM DU, make sure that the HYD page shows that the pressure of the yellow system is 3000 psi (206.8427 bar).

4. Procedure
Subtask 73-29-00-710-069-A

WARNING: MAKE SURE THAT AREA AROUND THE THRUST REVERSER IS CLEAR OF PERSONS AND EQUIPEMENT BEFORE YOU DO THIS TEST. THERE IS A RISK THAT THE THRUST REVERSER MOVES DURING THE TEST. IF YOU DO NOT OBEY THIS PRECAUTION, INJURY TO PERSONS AND/OR DAMAGE TO EQUIPEMENT CAN OCCUR.

A. Thrust Reverser ICV Test (Menu Mode)

NOTE: The EEC will not enter the menu mode (interactive mode) after an enquire command from the CFDS (Centralized Fault Display System) when any of the following conditions are set:

N2 more than ten percent or invalid
Engine not off
Engine not in default start state
TLA (Throttle Lever Angle) not at idle or invalid
Aircraft in the air
MASTER lever ON or invalid
BITE command code input label invalid.

NOTE: The EEC will abort the ICV test and display the test aborted screen screen when any of the following conditions becomes set:

N2 more than ten percent or invalid
Engine not in default start state
MASTER lever ON or invalid
You enter in the interactive mode of the other channel.

NOTE: If one of the following conditions occurs while menu mode is active, the Menu Mode session will be exited directly, without displaying a specific screen:

RETURN key selected on main menu screen
Channel in Menu Mode is not the active channel
Invalid BITE command or invalid equipment code received by EEC
A LOGOFF condition received by EEC
Engine start detected whereas function requiring idle speed (as idle test, vibration ground run) is not active
Selected mach more than 0.12 or invalid
Aircraft indicates in air.

(1) Do the test.

ACTION	RESULT
1.Initialize Menu Mode on the applicable engine and EEC, by selecting FADEC XY (X = Eng position, Y = channel number)	The ENGINE 1 MAIN MENU is shown.
2.On the ENGINE MAIN MENU screen:	The ENGINE TEST main menu screen will be shown.
Push the key adjacent to the ENGINE TESTS.
3.On the ENGINE TEST main menu screen: Press T/R TEST.	The THRUST REVERSER TEST screen will be shown.
4.On the THRUST REVERSER TEST screen: Press ICV TEST.	The ICV TEST first start screen will be shown.
5.On the ICV TEST screen: Press START TEST.	The ICV TEST second start screen will be shown.
6.On the ICV TEST screen: Press CONFIRM START OF TEST.	The ICV TEST deploy instruction screen will be shown.
Put throttle to max rev as indicated on the screen.	Do a visual check on ground to confirm the thrust reverser system does not deploy.
	NOTE: Normally, T/R will not move during this test (Isolation Control Valve (ICV) solenoid is not energized). However, as throttle is put at max reverser, there is a risk that T/R may move.
When 10 +/- 1 seconds have elapsed since DCV command.	The ICV TEST stow instruction screen will be shown.
Put throttle at forward idle as indicated on the screen.
When all the following conditions are true: (a) The thrust reverser is detected fully stowed. (b) When 25 +/- 1 seconds elapsed after TLA detected forward idle. (c) No ICV faults are active.	The ICV TEST passed screen will be shown.
NOTE: A restow option is available on ICV TEST passed screen, if ICV test needs to be performed again.
When all the following conditions are true: (a) The thrust reverser is detected fully stowed. (b) When 25 +/- 1 seconds elapsed after TLA detected forward idle: (c) ICV faults are active, or When 25 +/- 1 seconds elapsed after TLA detected forward idle AND ICV faults are active.	The ICV TEST failed screen will be shown. Put throttle at forward idle as indicated on the screen. Normally, T/R will not move during this test (ICV solenoid is not energized). However, as throttle is put at max reverser, there is a risk that T/R may move.
When there is a slow operator action or an abort condition detected.	ICV TEST not completed screen comes into view. NOTE: ICV TEST not completed screen is displayed if there is an abort condition detected or if there is a slow operator answer detected. Slow operator action means that T/R deploy instruction screen was displayed during 45s without throttle put at max reverse by the operator or T/R stow instruction screen was displayed during 45s without throttle put at forward idle by the operator.
7.Select RETURN key on ICV TEST passed screen or on ICV TEST failed screen or on ICV TEST not completed screen.	ICV TEST last screen is displayed. NOTE: Make sure T/R is stowed and select hydraulic pressure OFF, as indicated on the complete screen.
8.Select return again.	THRUST REVERSER TEST main screen is displayed.
9.Do the same procedure for the other EEC channel. In fact, each channel provides its own failures. To have a complete view of all EEC failures, both channels should be selected, one by one.

5. Close-up
Subtask 73-29-00-860-093-A

A. Put the aircraft back to its initial configuration.
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Depressurize the Green and Yellow Hydraulic System after operation on the PTU.
(a) FOR 4020KM1 (POWER PLANT-DEMOUNTABLE, ENG 1)
1 Depressurize the Green and Yellow hydraulic systems (Ref. AMM TASK 29-23-00-864-001)
(b) FOR 4020KM2 (POWER PLANT-DEMOUNTABLE, ENG 2)
1 Depressurize the auxiliary Yellow hydraulic-system (Ref. AMM TASK 29-24-00-864-001)
(3) On the ENG section of maintenance panel 50VU, push the HYD/LEAK/MEASUREMENT VALVAS/B/G/Y pushbutton switch.
-On the pushbutton switch the OFF legend goes off.

Subtask 73-29-00-862-067-A

B. De-energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-862-002).

[Rev.10 from 2021] 2026.04.01 13:13:23 UTC