P2 CENTER INSTRUMENT PANEL
AIRPLANES WITHOUT OIL SYSTEM PARAMETERS FOR DIGITAL FLIGHT RECORDER SYSTEM
AIRPLANES WITH OIL SYSTEM PARAMETERS FOR DIGITAL FLIGHT RECORDER SYSTEM
Oil Temperature Indicating System Schematic
Figure 2 (Sheet 3)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH THE ENGINE INSTRUMENT ú
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SYSTEM (EIS) DISPLAY P/N 10-62178-202 ú ú C01 Page 7 ú Nov 12/00
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737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
(2) Oil temperature is measured by the temperature sensitive resistance element in the oil temperature bulb. The resistance element is one leg of a wheatstone bridge circuit that controls current flow to the moving coil in the oil temperature indicator. The moving coil with the attached pointer rotates in proportion to the applied current.
B. AIRPLANES WITH THE ENGINE INSTRUMENT SYSTEM (EIS); Refer to the data that follows:
(1)
The indicating system is operational when 28 volt ac power is supplied to the Secondary Engine and Hydraulics Display from the P6-2 circuit breaker panel. Display lighting is 5 volts ac.
(2)
Oil temperature is measured by the temperature sensitive resistance element in the oil temperature bulb. A microprocessor processes the signal from the temperature bulb for display on the Secondary Engine and Hydraulics Display.
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
OIL TEMPERATURE INDICATING SYSTEM - ADJUSTMENT/TEST
___________________________________________________
1. General
_______
A. This procedure has two tasks. The first task is the operational test of the oil temperature indicating system. The second task is the system test of the oil temperature indicating system.
B. Do the operational test after you have replaced a component of the oil temperature indicating system to make sure the system functions. Do the system test to make sure the system indicates oil temperature accurately.
TASK 79-34-00-715-001-C00
2. Operational Test - Oil Temperature Indicating System
____________________________________________________
A. References
(1) AMM 71-00-00/201, Power Plant
B. Access
(1) Location Zone
101 Control Cabin
C. Procedure
S 865-026-C00
(1) Make sure these circuit breakers are closed:
(a) P6 Load Control Center 1) For Engine No. 1: a) AIRPLANES WITHOUT THE ENGINE INSTRUMENT SYSTEM (EIS); ENG 1 OIL TEMP & PRESS AC
b) AIRPLANES WITH THE ENGINE INSTRUMENT SYSTEM (EIS) AND SECONDARY ENGINE AND HYDRAULICS DISPLAY P/N 10-62178-201; EIS SEC 1 EIS SEC 2
c) AIRPLANES WITH THE ENGINE INSTRUMENT SYSTEM (EIS) AND SECONDARY ENGINE AND HYDRAULICS DISPLAY P/N 10-62178-202; EIS SEC 1 EIS SEC 2 EIS SEC 5
2) For Engine No. 2: a) AIRPLANES WITHOUT THE ENGINE INSTRUMENT SYSTEM (EIS); ENG 2 OIL TEMP & PRESS AC
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
b) AIRPLANES WITH THE ENGINE INSTRUMENT SYSTEM (EIS) AND SECONDARY ENGINE AND HYDRAULICS DISPLAY P/N 10-62178-201; EIS SEC 3 EIS SEC 4
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