EGT Indicator Installation
Figure 401

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F40499
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CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
CAUTION: POSITIVELY IDENTIFY CONNECTIONS BEFORE YOU CONNECT THEM
_______ AND DO FUNCTION CHECK UPON COMPLETION OF CONNECTION. CROSS-CONNECTION OF THE EGT INDICATOR (ON THE P2 INSTRUMENT PANEL) IS A POSSIBILITY WHEN YOU WORK WITH THIS COMPONENT.
 (a)  
Connect the electrical connector to the indicator.

 (b)  
Push the indicator into the instrument panel.

 (c)  
Turn the face of the indicator so that the mark on the face of the indicator for 900 degrees C is on the horizontal centerline of the panel.

 (d)  
Tighten the adjustment screw of the clamp that attaches the indicator to the instrument panel.

 S 864-007-C00
 (2)  For the applicable engine, close these circuit breakers and attach the DO-NOT-CLOSE identifiers:
 (a)  P6 Load Control Center
 1) EGT IND ENG 1
 2) EGT IND ENG 2

 S 714-008-C00
 (3)  Do the operational test for the EGT indication system (AMM 77-21-00/501).
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CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
AIRBORNE VIBRATION MONITOR (AVM) SYSTEM - DESCRIPTION AND OPERATION
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 1.  General
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 A.  The airborne vibration monitoring (AVM) system continuously shows the engine vibration level. The system consists of two accelerometers (vibration sensors) and a vibration indicator for each engine and an AVM signal conditioner. Power for the system is 115 volts ac supplied from transfer bus 1.
 B.  Abnormal engine vibration, sudden or progressive, is a positive indication of engine malfunction. Abnormal vibration can be caused by compressor or turbine blade damage, rotor imbalance, or other problems. Early warning of engine malfunction permits corrective action before extensive damage results.
 C.  With the engine operating, the engine accelerometers generate signals proportional to engine motion in radial direction. These signals are received by the AVM signal conditioner, where they are converted to signals suitable for indicator operation. Signals are then sent to the vibration indicator.
 D.  AIRPLANES WITH THE ENGINE INSTRUMENT SYSTEM (EIS); The AVM indicator is shown on the secondary EIS display as a simulated electro-mechanical device.
 2.  Engine Vibration Sensors (Fig. 1 and 2)
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 A.  The engine accelerometers sense engine vibration in terms of engine acceleration in a radial direction and generate electrical signals proportional to the engine acceleration. The accelerometers are of the piezoelectric type.
 B.  The turbine rear frame (TRF) vibration (core) sensor is mounted on the forward flange of the turbine rear frame at about the 12:00 o'clock position.
 (1) The TRF vibration (core) sensor has a charge sensitivity of 50 pc/G.
 C.  The No. 1 Bearing (NOB) vibration (fan) sensor is mounted on the number one bearing housing at the 9 o'clock position. This sensor senses low speed rotor motion.
 (1) The NOB vibration (fan) sensor has a charge sensitivity of 100 pC/g.
 D.  The lead connector is on the fan frame mid-box structure aft frame at the 3 o'clock position.
 3.  AVM Signal Conditioner (Fig. 3)
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