EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH S332T304 AVM SIGNAL ú

 71-00-54
 CONDITIONERS  ú ú C03 Page 114 ú Jul 12/00
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CFM56 ENGINES
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55 (CONTINUED)
(FRONT FAULT CODE PANEL)  FAULT  ACTION 
B1  N1 SPEED SENSOR SIGNAL  IF THE FLIGHT DECK N1 INDICATION IS DISCREPANT, REPLACE THE
 LOSS - ENGINE 1  AVM SIGNAL CONDITIONER (WDM 77-12-11 AND 77-31-11). REPAIR THE WIRING* BETWEEN THE ENGINE 1 N1 SPEED SENSOR AND (AMM 77-31-03/401). IF THE FAULT CONTINUES, CHECK AND ENGINE 1 N1 SPEED SENSOR, T421 (AMM 77-12-01/401). IF THE DISCREPANT, REPLACE THE AVM SIGNAL CONDITIONER, M1240 FAULT CONTINUES OR IF THE FLIGHT DECK INDICATION IS NOT
B2  N2 SPEED SENSOR SIGNAL IF THE FLIGHT DECK N2 INDICATION IS DISCREPANT, REPLACE THE
 LOSS - ENGINE 1  AVM SIGNAL CONDITIONER (WDM 77-12-21 AND 77-31-11). REPAIR THE WIRING* BETWEEN THE ENGINE 1 N2 SPEED SENSOR AND (AMM 77-31-03/401). IF THE FAULT CONTINUES, CHECK AND DISCREPANT, REPLACE THE AVM SIGNAL CONDITIONER, M1240 FAULT CONTINUES OR IF THE FLIGHT DECK INDICATION IS NOT ENGINE 1 N2 SPEED SENSOR, T422 (AMM 73-21-08/401). IF THE 
B3 N1 SPEED SENSOR SIGNAL  SAME AS FAULT CODE B1, EXCEPT FOR ENGINE 2. 
LOSS - ENGINE 2 
B4 N2 SPEED SENSOR SIGNAL  SAME AS FAULT CODE B2, EXCEPT FOR ENGINE 2. 
LOSS - ENGINE 2 

* INCLUDES CONNECTORS ON ALL WIRING AND SHIELD ON VIBRATION SENSOR WIRING
AVM Indication Problem
Figure 104 (Sheet 5)

EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH S332T304 AVM SIGNAL ú

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 CONDITIONERS  ú ú C02 Page 115 ú Jul 12/00
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CFM56 ENGINES
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AVM INDICATION PROBLEM
PREREQUISITES
MAKE SURE THESE CIRCUIT BREAKERS ARE CLOSED: ENG VIBRATION MONITOR AIRPLANES WITH ENGINE INSTRUMENTATION SYSTEM (EIS); EIS SEC 1, EIS SEC 2, EIS SEC 3, EIS SEC 4;AIRPLANES WITH -201 EIS, PRESS IND SYS A,
PRESS IND SYS B;
AIRPLANES WITH -202 EIS, EIS SEC 5, EIS SEC 6

MAKE SURE THE AIRPLANE IS IN THIS CONFIGURATION: ELECTRICAL POWER IS ON (AMM 24-22-00/201)
EQUIPMENT: BRISTLE BRUSH
CONSUMABLE MATERIALS: STODDARD SOLVENT (CP 2011)
YES

1 DO THE VIBRATION
INDICATORS, N160 OR N161,
POINT TO THE BLUE LINE OR DOES
THE SECONDARY EIS, N183 SHOW A
BLANK DISPLAY OR ARE THERE LOG
BOOK REPORTS FOR SUCH
BEHAVIOR?

NO
SEE SHEET 7 (BLOCK 2)

43 DISCONNECT THE NO. 1
VIBRATION GREATER THAN 4 UNITS OF LESS THAN ONE MINUTE IN DURATION THAT REPEATED DURING THE FLIGHT OR ON SUBSEQUENT FLIGHTS?

NO
SEE SHEET 7 (BLOCK 24)
AVM Indication Problem
Figure 104 (Sheet 6)

BEARING HARNESS FROM THE NO. 1 BEARING SENSOR, T332 AND THE TRF VIBRATION HARNESS FROM THE TRF SENSOR, T331.
EXAMINE THE RECEPTACLES AND CONNECTORS FOR DAMAGEDPINS AND CONTAMINATION OF THE PARTS THAT FOLLOW: . HARNESS CONNECTORS . VIBRATION SENSORS CONNECTORS
(AMM 77-31-02/601). . AVM
IF DAMAGED PINS ORCONNECTOR OXIDATION IS FOUND, REPAIR THE CIRCUIT IF IT IS NECESSARY (WDM 77-31-11).
 IF NO DAMAGE IS FOUND, CLEAN THE CONNECTORS WITH A BRISTLE BRUSH AND STODDARD SOLVENT (CP 2011).
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH S360N021-201 OR -202 AVM ú

 71-00-54
 SIGNAL CONDITIONERS, WITH AND WITHOUT ú EIS ú C02 Page 116 ú Jul 12/00
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CFM56 ENGINES
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FROM SHEET 6 FROM SHEET 6 (BLOCK 1) (BLOCK 23)
　
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