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 S 714-011
 (4)  Do this replacement test for the module: (a) Do one of these steps: 1) Make sure the flap control lever is outside of the takeoff range. 2) Make sure the speedbrake handle is not in the down detent position. 3) Make sure the stabilizer is out of the green band range. 4) Make sure the leading edge flaps are not extended. 5) Make sure the parking brake is set. (b) Do the operational test of the aural warning module: 1) Move the thrust levers to the takeoff position. 2) Make sure you hear the warning horn. (c) Move the thrust levers to the idle position. 1) Make sure the warning horn stops.
 S 864-016
 (5)  Remove electrical power if it is not necessary (AMM 24-22-00/201).

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 31-26-41
 ALL  ú ú 01 Page 403 ú Nov 15/98
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
 ENGINE INSTRUMENT SYSTEM - DESCRIPTION AND OPERATION
____________________________________________________
 1.  General (Fig. 1)_______
 A.  The engine instrument system (EIS) is microprocessor-controlled instrument panels which display parameters of engines and hydraulic systems to monitor airplane engines and hydraulic systems operation. It also displays total air temperature and (for EFIS configured airplanes only) engine thrust mode annunciation messages.
 B.  The EIS is composed of two adjacent independent, solid state integrated displays: a Primary Display and a Secondary Display. Both displays are installed on the pilots' center instrument panel P2-2. The left-hand side is the Primary Display and the right-hand side is the Secondary Display.
 C.  The EIS receives 28v electrical power from the P6-2 LOAD CONTROL CENTER panel.
 2.  EIS Primary Display___________________
 A.  Physical Description
 (1)  
The instrument consists essentially of a chassis assembly which encloses thirteen electronic circuit boards. The front end of the chassis supports a display/driver module. The rear end supports a backplate which carries a case back assembly. The case back assembly carries the four electrical connectors which provide interconnection to the airplane wiring. Connectors J1 and J3 are assigned to engine 1 ("left" channel) and J2 and J4 to engine 2 ("right" channel).

 (2)  
The display/driver module incorporates various light emitting diode (LED) displays, external light sensors and integral lighting. The front bezel supports an unmarked confidence test button (BITE), a push-to-select fuel used button, a fuel used reset button and two pull-to-set N1 Limit knobs.

 (3)  
The display panel employs LED pointer/bug and digital counter to display engine parameters and TMA. The pointer, consisting of 3 LED bar chip in series, moves on the circular dial in sequential progression. The counter, formed by an LED dot matrix diode, simulates the action, appearance and counting of a four-drum mechanical counter.

 (4)  
Only N1 and FF/FU indicators have scale markings to give reference points for precise engine control.

 (5)  
The integral lighting consists of six lamps which are fed from an external 0-5v, 400 Hz single phase ac supply.

 (6)  
The unit is housed in a rectangular case assembly.

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 31-42-00
 ú ú 01 Page 1 ú Nov 15/90
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
P6-2 PANEL
SEE BSEE A AFT
RED WARNING
TMA LIGHT MESSAGE
MAN SET
DISPLAY
RED-LINE LIMIT
%RPM
120 120

N1
22
10 10
LIMIT
N1
88
44
66

BUG
LED
`C POINTER
EGT
0
%RPM
LED POINTER
N2
X1000
120 120
111 111

102 102
PULL
PULL
MANUAL

TO
93 93
TO
SET 84 84SET

75 75
N1

66
SET
FF/FU
N1
PPH/LB
BITE
KNOB
BUTTON

RESET
PUSH USED

FUEL
BITE
　
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