(2)
The engine exhaust gas temperature (EGT) indicating system (AMM 77-21-00).
(3)
The airborne vibration monitoring (AVM) system (AMM 77-31-00).
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CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
EGT THERMOCOUPLE HARNESS EGT TERMINAL BLOCK
PMC (REF)
N1 SPEED
SENSOR
ACCESSORY GEAR BOX
N2 CONTROL (REF)OIL TANK ALTERNATOR (REF) SPEED SENSOR
MAN SET
12
UNLOCKED REVERSER UNLOCKED REVERSER INDICATOR N1 TACHOMETER N1 %RPM
12 0 12 0
% RPM X 10 % RPM X 10
8 8 10 2 10 2
N1 6 78812 0 N1 6 78812 0 N1 TACHOMETER 8 6 4 8 6 4
10 2 10 2 INDICATOR
86.48 4 86.48 4 EXHAUST GAS
TEMPERATURE EGT
INDICATOR `C
C X 100 C X 100
6 6
EGT4 574 10 0 EGT4 574 10 0 TEMPERATURE EXHAUST GAS
8 2 8 2 INDICATOR
6 4 6 4
N2 TACHOMETER N2
INDICATOR %RPM
% RPM X 10 % RPM X 10
8 8
N2 6 78812 10 2 0 N2 6 78812 10 2 0 N2 TACHOMETER INDICATOR
8 4 8 4 FF/FU X1000
6 6 12 0 12 0
11 1 11 1
PULL 10 2 10 2 PULL
TO 9 3 9 3 TO
N1 SET 8 7 6 5 4 8 7 6 5 4 N1 SET
PUSH FUEL USED RESET
PPH LBP2-1 CENTER INSTRUMENT PANEL 1
1 AIRPLANES WITHOUT
P2 CENTER INSTRUMENT PANEL 2
ENGINE INSTRUMENT SYSTEM (EIS)
2 AIRPLANES WITH EIS
Engine Indicating System Location Figure 1
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CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
ENGINE INDICATING - TROUBLE SHOOTING
____________________________________
1. Trouble Shoot the Engine Indicating System
__________________________________________
A. Procedure
(1) To trouble-shoot the Engine Indicating system, refer to the trouble-shooting diagrams in Chapter 71 (AMM 71-00-40/101).
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CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
ENGINE TACHOMETER SYSTEM - DESCRIPTION AND OPERATION
____________________________________________________
1. General
_______
A. The engine tachometer system measures the speed of the low speed (N1)
rotor and high speed (N2) rotor and provides the speed indication in the
flight compartment. N1 speed is a means of monitoring engine power
output, engine condition, and N1 rotor integrity overspeed. N2 rotor
speed is a means of controlling engine starting and monitoring engine
condition and N2 rotor integrity and overspeed. Power for the system is
28 volts dc from the main power circuit breaker panel P6.
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本文鏈接地址：737-300 400 500 AMM 飛機維護(hù)手冊 發(fā)動機指示 ENGINE INDICATIN(2)
