S 034-016-C00
 (3)  Loosen the adjustment screw of the clamp that attaches the indicator to the panel.
 NOTE: The screws that are on the top left side of the indicator
____
 are adjustment screws.

 S 024-017-C00
 (4)  Carefully pull the indicator from the instrument panel to get access to the electrical connector.
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITHOUT ENGINE INSTRUMENT ú

 77-12-02
 SYSTEM (EIS) DISPLAY  ú ú C04 Page 403 ú Mar 12/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / /
CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
S 034-042-C00
 CAUTION:  CLEARLY IDENTIFY CONNECTIONS BEFORE YOU DISCONNECT THEM.
_______ CROSS-CONNECTION OF THE TACHOMETER INDICATOR (ON THE P2 INSTRUMENT PANEL) IS A POSSIBILITY WHEN YOU WORK WITH THIS COMPONENT.
 (5)  
Disconnect the electrical connector from the indicator.

 S 024-019-C00

 (6)  
Remove the indicator from the instrument panel.

 TASK 77-12-02-424-020-C00
 5.  N2 Indicator Installation_________________________
 A. References
 (1)  AMM 77-12-00/501, Engine Tachometer System
 B. Access
 (1)  Location Zone
 101, 102 Control Cabin

 C. Procedure
 S 434-043-C00
 CAUTION: POSITIVELY IDENTIFY CONNECTIONS BEFORE YOU CONNECT THEM AND DO
_______ FUNCTION CHECK UPON COMPLETION OF CONNECTION. CROSS-CONNECTION OF THE TACHOMETER INDICATOR (ON THE P2 INSTRUMENT PANEL) IS A POSSIBILITY WHEN YOU WORK WITH THIS COMPONENT.
 (1)  
Connect the electrical connector to the indicator.

 S 424-023-C00

 (2)  
Install the indicator into the panel.

 S 434-024-C00

 (3)  
Tighten the adjustment screw on the clamp that attaches the
 indicator.

 S 864-025-C00

 (4)  
For the left engine, close these circuit breakers and remove DO-NOT-CLOSE tags:

 (a)  P6 Main Power Distribution Panel
 1) C00734 TACH IND ENG 1 N2

 S 864-030-C00
 (5)  For the right engine, close these circuit breakers and remove DO-NOT-CLOSE tags:
 (a)  P6 Main Power Distribution Panel
 1) C00735 TACH IND ENG 2 N2

 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITHOUT ENGINE INSTRUMENT ú

 77-12-02
 SYSTEM (EIS) DISPLAY  ú ú C04 Page 404 ú Mar 12/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / /
CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
S 714-026-C00
 (6)  Do the operational test of the N2 tachometer system (AMM 77-12-00/501).
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITHOUT ENGINE INSTRUMENT ú

 77-12-02
 SYSTEM (EIS) DISPLAY  ú ú C02 Page 405 ú Mar 12/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / /
CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
EXHAUST GAS TEMPERATURE (EGT) INDICATION SYSTEM - DESCRIPTION AND OPERATION
___________________________________________________________________________
 1.  General
_______
 A.  The exhaust gas temperature (EGT) indicating system provides a visual indication in the flight compartment of the total exhaust temperature monitored in the low pressure turbine inlet of each engine. EGT is measured by 9 thermocouple probes installed in stage 2 LPT nozzle assembly. The signals transmitted by these probes are routed through rigid thermocouple harnesses and one or three extension leads which make up the EGT thermocouple harness assembly.
 2.  Thermocouple Harness Assembly (9 Probe EGT System) (Fig. 1 and Fig. 2)
　
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737-300 400 500 AMM 飛機維護手冊 發動機指示 ENGINE INDICATIN(14)