1 DO A VISUAL CHECK OF THE
ENGINE INSTRUMENTATION SYSTEM
(EIS).
IS THE EGT DISPLAY BLANK?
NO
2 DO AN ELECTRICAL LOOP RESISTANCE (RT) TEST OF THE EGT SYSTEM AT
THE INTERFACE CONNECTOR D2954, OR TERMINAL BLOCK, T1012.
IS RT IN THESE LIMITS?
_____________NO. OF PROBES ______________________INTERFACE CONNECTION AT__ ________RT, OHMS
SIX 12:00 O'CLOCK 1.0 |0.1
SIX 9:30 O'CLOCK 3.85 |0.4
NINE 9:30 O'CLOCK 2.55 |0.3
4 DO THE EGT INDICATION
SYSTEM TEST
(AMM 77-21-00/501).
DOES THE SYSTEM PERFORM SATISFACTORILY?
YES
SEE SHEET 4 (BLOCK 5)
EGT Indication Problem
Figure 103 (Sheet 3)
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FROM SHEET 3 (BLOCK 4) NO
5
MAKE SURE THE CIRCUIT BREAKERS FOR THE FLIGHT DATA ACQUISITION UNIT (FDAU) ARE CLOSED.
DOES ABNORMAL INDICATION OCCUR AGAIN?
YES
A
737-300/400/500MAINTENANCE MANUAL
NO
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CFM56 ENGINES
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25 EXAMINE THE CIRCUIT BETWEEN THE EIS PRIMARY DISPLAY, N182, AND THE EGT INTERFACE CONNECTOR D2954, OR TERMINAL BLOCK, T1012, ON THE ENGINE (WDM 77-21-11). REPAIR THE PROBLEMS THAT YOU FIND.
EGT Indication Problem
Figure 103 (Sheet 4)
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L17641
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CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
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 2 (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 2 (BLOCK 24)
AVM Indication Problem
Figure 104 (Sheet 1)
BEARING HARNESS FROM THE NO. 1 BEARING SENSOR, T332 AND THE TRF VIBRATION HARNESS FROM THETRF SENSOR, T331.
EXAMINE THE RECEPTACLES AND CONNECTORS FOR DAMAGED PINS AND CONTAMINATION OF THE PARTS THAT FOLLOW: . HARNESS CONNECTORS. VIBRATION SENSORS CONNECTORS
(AMM 77-31-02/601).. AVM
IF DAMAGED PINS OR CONNECTOR 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).
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CONDITIONERS, WITH AND WITHOUT EIS ú ú C03 Page 111 ú Jul 12/00
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737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
FROM SHEET 1 FROM SHEET 1 (BLOCK 1) (BLOCK 23)
NO
NO
YES 44 EXAMINE THE CIRCUIT BETWEEN THE AVM SIGNAL CONDITIONER, M1240, AND THE AVM INDICATORS, N160 OR N161
NO
OR THE SECONDARY EIS, N183.
EXAMINE THE CIRCUIT BETWEEN THE AVM SIGNAL CONDITIONER, M1240, AND THE ENG VIBRATION MONITOR CIRCUIT BREAKER (WDM 77-31-11).YES 中国航空网 www.aero.cn 航空翻译 www.aviation.cn 本文链接地址：737-300 400 500 AMM 飞机维护手册 动力装置 POWER PLANT 2(74)
