DOC AIRBUS | AMM A320FAccelerometer Configuration via the Menu Mode [CFML]
TASK 73-29-00-740-824-A
Accelerometer Configuration via the Menu Mode
The Accelerometer Configuration Menu Mode function is used to select the necessary accelerometer configuration. This function also allows to disable the number 1 bearing accelerometer if the sensor is faulted or the signal presents noise. The Accelerometer Configuration Menu Mode function is only available on EEC channel B.
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
B. Work Zones and Access Panels
C. Referenced Information
3. Job Set-up
Subtask 73-29-00-860-136-A Subtask 73-29-00-941-082-A
Subtask 73-29-00-710-096-A
Subtask 73-29-00-410-081-A
[Rev.10 from 2021]
2026.04.01 13:07:12 UTC
Accelerometer Configuration via the Menu Mode
ZONE: 400
1. Reason for the JobThe Accelerometer Configuration Menu Mode function is used to select the necessary accelerometer configuration. This function also allows to disable the number 1 bearing accelerometer if the sensor is faulted or the signal presents noise. The Accelerometer Configuration Menu Mode function is only available on EEC channel B.
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
| REFERENCE | QTY | DESIGNATION |
|---|---|---|
| No specific | AR | WARNING NOTICE(S) |
| ZONE/ACCESS | ZONE DESCRIPTION |
|---|---|
| 400 | POWER PLANT, NACELLES AND PYLONS |
| 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 31-32-00-860-012-A | Procedure to Get Access to the SYSTEM REPORT/TEST/ENG Page |
Main Menu Screen Format (Screen 1)Subtask 73-29-00-860-136-A Subtask 73-29-00-941-082-A
B. Safety Precautions
(1) On the center pedestal, on ENG panel 115VU:
(a) Make sure that the ENG/MODE selector switch is in the NORM position.
(b) Make sure that the ENG/MASTER 1(2) control switch was in the OFF position not less than five minutes before you do this procedure.
(c) Put a WARNING NOTICE(S) in position to tell persons not to operate:
Subtask 73-29-00-865-105-A (1) On the center pedestal, on ENG panel 115VU:
(a) Make sure that the ENG/MODE selector switch is in the NORM position.
(b) Make sure that the ENG/MASTER 1(2) control switch was in the OFF position not less than five minutes before you do this procedure.
(c) Put a WARNING NOTICE(S) in position to tell persons not to operate:
- The ENG/MODE selector switch
- The ENG/MASTER 1(2) control switch.
C. Make sure that this(these) circuit breaker(s) is(are) closed:
Subtask 73-29-00-941-083-A | PANEL | DESIGNATION | FIN | LOCATION |
|---|---|---|---|
| ** ON A/C ALL | |||
| 49VU | ENGINE/1 AND 2/IGN/SYS A | 1JH | A03 |
| 49VU | L/G/LGCIU/SYS1/NORM | 1GA | C09 |
| 121VU | HYDRAULIC/LGCIU/SYS2 | 2GA | Q35 |
| 121VU | HYDRAULIC/LGCIU/SYS1/GRND SPLY | 52GA | Q34 |
| FOR FIN: 4020KM1 (POWER PLANTDEMOUNTABLE, ENGINE 1) | |||
| 49VU | ENGINE/1/FADEC A/AND EIU 1 | 2KS1 | A04 |
| 121VU | ENGINE/IGN/ENG1/SYS B | 3JH1 | P41 |
| 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/IGN/ENG2/SYS B | 3JH2 | P42 |
| 121VU | ENGINE/ENG2/FADEC B/AND EIU2 | 4KS2 | R41 |
D. Aircraft Maintenance Configuration
(1) On the ENG section of maintenance panel 50VU:
(3) On the left or right Multipurpose Control and Display Unit (MCDU), get the SYSTEM REPORT/TEST/ENG page (Ref. AMM TASK 31-32-00-860-012).
(4) Make sure that the landing gear system is not simulated in the flight configuration.
4. Procedure(1) On the ENG section of maintenance panel 50VU:
- Release the FADEC GND PWR 1(2) pushbutton switch (the ON legend comes on).
(3) On the left or right Multipurpose Control and Display Unit (MCDU), get the SYSTEM REPORT/TEST/ENG page (Ref. AMM TASK 31-32-00-860-012).
(4) Make sure that the landing gear system is not simulated in the flight configuration.
Subtask 73-29-00-710-096-A
A. General
(1) The accelerometer configuration menu mode function is used to select the necessary accelerometer configuration. This function allows the operator to indicate whether a PX36 kit is installed in place of the number 1 bearing accelerometer. This function also allows to disable the number 1 bearing accelerometer if the sensor is faulted or the signal presents noise. The accelerometer configuration menu mode function is only available on EEC channel B.
5. Close-up(1) The accelerometer configuration menu mode function is used to select the necessary accelerometer configuration. This function allows the operator to indicate whether a PX36 kit is installed in place of the number 1 bearing accelerometer. This function also allows to disable the number 1 bearing accelerometer if the sensor is faulted or the signal presents noise. The accelerometer configuration menu mode function is only available on EEC channel B.
NOTE: The EEC will not enter the menu mode (interactive mode) after an enquire command from the centralized fault display system when any of the following conditions are set:
- N2 more than ten percent or invalid
- Rotary selector on CRANK or on IGN/START or invalid
- Manual start button on ON or invalid
- Throttle Lever Angle (TLA) 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 oil debris function and show the FUNCTION TERMINATED SCREEN when any of the conditions that follow become set:
- N2 more than ten percent or invalid
- Engine not in default start state
- TLA not at idle or invalid
- MASTER lever ON or invalid
- You enter in the interactive mode of the other channel
- RETURN key is selected on the MCDU during a running test or special function.
NOTE: If one of the following conditions occurs while the menu mode is active, the Menu Mode session will be exited directly, without displaying a specific screen:
- RETURN key selected on the main menu screen
- Channel in menu mode is not the active channel
- Invalid BITE command or invalid equipment code received by the EEC
- A LOGOFF condition received by the EEC
- Engine start detected whereas function requiring idle speed (as idle test, vibration ground run) is not active
- Selected Mach is more than 0.12 or invalid
- Aircraft indicates in air.
| ACTION | RESULT |
|---|---|
| 1.Initialize the Menu Mode on the applicable engine and EEC, by selecting FADEC XY (X = engine position, Y = channel number). For this test, Y shall be set to B because this function is only available on channel B. | |
2.On the MCDU ENGINE MAIN MENU screen:
| The SPECIAL FUNCTIONS screen comes into view. |
3.On the MCDU Special Functions Main screen:
| The ACCELEROMETER CONFIGURATION INITIAL page SCREEN 3 comes into view. |
4.On the MCDU Accelerometer Configuration Initial screen:
| The ACCELEROMETER CONFIGURATION SELECTION page SCREEN 4 comes into view. |
5.On the MCDU Accelerometer Configuration Selection screen, select the desired configuration:
| If the configuration was successfully stored in the NVM, the ACCELEROMETER CONFIGURATION CONFIRMATION page SCREEN 5 comes into view. Wait a minimum of 4 seconds. If the configuration was not stored in the NVM, the ACCELEROMETER NVM FAILED page SCREEN 6 comes into view. Select RETURN (6L) and the FUNCTION TERMINATED page SCREEN 7 comes into view. NOTE: If the number 1 bearing accelerometer is disabled, the Turbine Center Frame (TCF) accelerometer will be used to measure and display the fan vibration. |
6.On the MCDU Accelerometer Configuration Confirmation screen:
| The Special Functions Main screen comes into view. NOTE: "NORM" indicates that the nominal configuration is installed, with the number 1 bearing and TCF accelerometer installed/enabled. "TCF" indicates that the number 1 bearing accelerometer is disconnected/disabled and only TCF is used. "PX36" indicates that a PX36 sensor is installed in place of the number 1 bearing accelerometer. The PX36 sensor is not introduced into service. |
7.On the Special Functions Main screen:
| The MCDU Home page comes into view. |
Subtask 73-29-00-410-081-A
A. Close Access
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Remove the WARNING NOTICE(S).
Subtask 73-29-00-860-137-A (1) Make sure that the work area is clean and clear of tools and other items.
(2) Remove the WARNING NOTICE(S).
B. Put the aircraft back to its initial configuration.
(1) On the overhead maintenance panel 50VU:
Subtask 73-29-00-862-090-A (1) On the overhead maintenance panel 50VU:
- Push the ENG/FADEC GND PWR 1(2) pushbutton switch (the ON legend goes off).