Installation of the Engine Vibration Monitoring Unit (EVMU) [CFMB]

TASK 77-32-34-400-042-A
Installation of the Engine Vibration Monitoring Unit (EVMU)

FIN: 2EV ** ON A/C NOT FOR ALL

1. Reason for the Job
Self explanatory
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment

REFERENCE	QTY	DESIGNATION
No specific	AR	WARNING NOTICE(S)

B. Work Zones and Access Panels

ZONE/ACCESS	ZONE DESCRIPTION
824

C. 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 31-32-00-860-012-A	Procedure to Get Access to the SYSTEM REPORT/TEST/ENG Page
TASK 52-41-00-410-002-A	Close the Avionics Compartment Doors after Access
TASK 77-32-34-710-040-B	Operational Check of EVMU through CFDS for Advisory Indication on ECAM
Engine Vibration Monitoring Unit

3. Job Set-up
Subtask 77-32-34-010-054-A ** ON A/C NOT FOR ALL

A. Get Access
(1) Make sure that the platform is in position at the access door 824.
(2) Make sure that the access door 824 is open.

Subtask 77-32-34-865-069-A ** ON A/C NOT FOR ALL

B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C NOT FOR ALL
121VU	ENGINE/ENG1 AND 2/EVMU	1EV	R44

4. Procedure
Subtask 77-32-34-420-052-A ** ON A/C NOT FOR ALL

A. Installation of the Engine Vibration Monitoring Unit
(1) Remove the CAP-BLANKING from each electrical connector and receptacle.
(2) Make sure that all the electrical connections are clean and in the correct condition.
(3) Put the engine vibration monitoring unit (1) in its support (2).
(4) Push the engine vibration monitoring unit (1) until the connector (6) engages correctly.
(5) Engage the knurled nuts (4) in the hooks (5) and tighten them.

Subtask 77-32-34-865-070-A ** ON A/C NOT FOR ALL

B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C NOT FOR ALL
121VU	ENGINE/ENG1 AND 2/EVMU	1EV	R44

Subtask 77-32-34-710-054-A ** ON A/C NOT FOR ALL

C. Do the test of the EVMU with the CFDS (Ref. AMM TASK 77-32-34-710-040).

Subtask 77-32-34-869-089-A ** ON A/C NOT FOR ALL

D. Enter the initial vibration values you wrote before the removal
(1) If you are in PRE AIRBUS SB77-1006 (P/N 241-191-000-031 and 241-191-000-041) it is not possible to enter the initial vibration values in the new installed EVMU. Go directly to Para. 5.
(2) If you are in POST AIRBUS SB77-1006 (P/N 241-246-022-004), do as follow:
(a) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002).
(b) Make sure that the circuit breaker 1EV is closed.
(c) Safety Precautions
1 On the center pedestal, on the ENG panel 115VU:
a Put a WARNING NOTICE(S) to tell persons not to start the engine.
2 Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.
3 On the overhead maintenance panel 50VU:
a Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.
b Put a WARNING NOTICE(S) to tell persons not to energize the FADEC 1(2).
(d) Aircraft Maintenance Configuration
1 On the MCDU 1(2), get the SYSTEM REPORT/TEST ENG page (Ref. AMM TASK 31-32-00-860-012).
2 Push the key adjacent to the EVMU indication: the first EVMU page comes into view.
3 Push the NEXT PAGE key.
4 Push the key adjacent to the ENGINE UNBALANCE indication.
5 The EVMU ENGINE UNBALANCE menu comes into view.
(e) Do the fan trim balance to assure the configuration is correct.

ACTION	RESULT
1.Push the line key adjacent to the ENG1(2) TRIM indication.	The EVMU ENG1(2) TRIM BALANCE menu comes into view.
2.Push the line key adjacent to the ONE SHOT CFM56-5B indication.	The EVMU ENG1(2) CURRENT VIB INPUT menu comes into view.
3.Push the line key related to the: FLIGHT DATA	The vibration data comes into view.
4.Push the line key adjacent to the CONT indication.	The INFLUENCE COEFF SELECT menu comes into view.
5.Push the line key adjacent to the GENERIC COEFF CFM56-5 indication.	The ENG1(2) INSTALLED CURRENT SCREWS menu comes into view.
6.Modify the hole/screw configuration in accordance with the current configuration gathered before the removal of the previous unit or gathered on the spinner rear cone.

5. Close-up
Subtask 77-32-34-410-052-A ** ON A/C NOT FOR ALL

A. Close Access
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Close the access door 824. (Ref. AMM TASK 52-41-00-410-002)
(3) Remove the access platform(s).

[Rev.10 from 2021] 2026.04.02 06:37:44 UTC