DOC AIRBUS | AMM A320FVIBRATION INDICATING SYSTEM - DESCRIPTION AND OPERATION
** ON A/C NOT FOR ALL
1. Component Location
** ON A/C NOT FOR ALL 
Vibration Indicating System - Forward Vibration Sensor- Post SB C-72-00-0058A (Config-2 Optimized Vibration Signal Configuration)
The forward vibration sensor is attached to flange E, located at the 7 o'clock position. - The aft vibration sensor is attached to the engine core, located at the 3 o'clock position.
| FIN | FUNCTIONAL DESIGNATION | PANEL | ZONE | ACCESS DOOR | ATA REF |
|---|---|---|---|---|---|
| ** ON A/C NOT FOR ALL | |||||
| 4067KS | SENSOR-VIBRATION,AFT | 400 | 73-11-00 | ||
| 4068KS | SENSOR-VIBRATION,FWD | 400 | 73-11-00 | ||
| 4087KS | W03 HARNESS | 400 | 73-21-68 | ||
2. System Description
A. Vibration Monitoring
(1) The PHMU receives signal analysis from engine accelerometers to assess the health of rotating and the mechanical components. The PHMU reports this information to the aircraft as maintenance messages and cockpit caution, status and warning messages, if necessary.