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CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
A.  The AVM signal conditioner processes inputs from vibration sensors, N1 and N2 speed sensors. The monitor unit is programmed to determine the N1 and N2 rotor vibration from the fan and core sensors. The unit is a microprocessor with BITE, self-test and flight data history functions.
 (1)  
AIRPLANES WITH A S332T304 AVM; Have a linear scale for flight compartment indication. The scale from 0 - 5 scalar units can be compared to a scale of 0 - 10 mils DA (Double Amplitude) of vibration.

 (2)  
AIRPLANES WITH A S360N021-100, -102, -113, -114, -201, -202 OR -213 AVM; Have these features:

 (a)  
This AVM has a bi-linear scale for flight compartment indication. The scale from 0 - 2.5 units compares to a scale of 0 - 5 mils DA (Double Amplitude) of vibration. The scale from 2.5 - 5 units compares to 5 - 20 mils DA of vibration.

 (b)  
This AVM has a 2 minute time delay at the engine start, so that the transient engine start up vibration is not recorded on the flight history data.

 

 4.  AVM Indicator (Fig. 4)
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 A.  The AVM indicator shows the vibration level of the two engines.
 (1)  
AIRPLANES WITH A S332T304 AVM; The AVM indicator displays constantly the highest measured vibration values of the Fan or High Pressure Compressor (HPC). The indicator value for the Fan is normalized (converted to scaler units) and the HPC value is linear. The indicator values are displayed in scaler units (s.u.) from 0 to 5 s.u.

 (2)  
AIRPLANES A WITH S360N021-100, -102, -113, -114, -201, -202 OR -213 AVM; The AVM indicator displays constantly the highest measured vibration values of the Fan, Low Pressure Turbine (LPT), High Pressure Compressor (HPC) or High Pressure Turbine (HPT). Indicator values for the Fan and LPT vibrations are normalized (converted to scaler units) and the HPC and LPT values are linear. The indicator values are displayed in scaler units (s.u.) from 0 to 5 s.u.

 (3)  
AIRPLANES WITHOUT THE ENGINE INSTRUMENT SYSTEM (EIS); The AVM vibration indicator is a dc microammeter coupled to a pointer.

 (a)  The loss of signal input to the vibration indicator will turn the pointer to the mark under zero.

 (4)  
AIRPLANES WITH THE ENGINE INSTRUMENT SYSTEM (EIS); The AVM indicator is shown on the secondary EIS display as a simulated electro-mechanical device.

 (a)  The loss of signal input will cause the AVM indicator to go blank.

 (5)  
Separate indicators are provided for each engine on the pilots' center instrument panel, P2.

 5.  Operation (Fig. 4)
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 77-31-00
 ALL  ú ú C03 Page 8 ú Mar 12/02
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////

SIGNAL CONDITIONER (E1)
(P2)
AVM System Simplified Schematic
Figure 4 (Sheet 1)

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 77-31-00
 INSTRUMENT SYSTEM (EIS)  ú ú C19 Page 9 ú Nov 12/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////

TAT

`C ENG OIL PRESS
QTY
%FULL
RF 88%
ENG 2  M1240 AIRBORNE VIBRATION MONITOR (AVM)
SIGNAL CONDITIONER (E1)  N183 SECONDARY ENGINE DISPLAY (P2)

 

AVM System Simplified Schematic
Figure 4 (Sheet 2)

EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH THE ENGINE ú

 77-31-00
 INSTRUMENT SYSTEM (EIS)  ú ú C24 Page 10 ú Nov 12/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
　
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