(3)
Clockwise rotation of the knob moves the N1 bug clockwise in unison with changing numeric values on the MAN SET counter to show increasing limit N1.
E. FUEL USED PUSH button
(1) The FUEL USED PUSH button is located in the bottom of the front bezel. Normally the FF/FU indicator displays fuel flow parameter, when the FUEL USED PUSH button is pressed, the display shows fuel used parameter value for a period of 10 seconds. After this time, the display will revert to fuel flow parameter display. The pushbutton is a momentary action.
F. RESET FUEL USED button
(1) The RESET FUEL USED button is located in the bottom of the front bezel. This button is used to reset the fuel used value to zero.
G. Display Range of the Engine Parameters
(1) The pointers and digital counters for displaying engine parameters have their upper and lower limits. The display ranges for each individual parameter are as follows:
(a)
Display Range for N1
Actual N1 Pointer 0 ----- 120% RPM Actual N1 Numerics .0 ----- 120.0% RPM Command N1 Bug 55 ----- 106% RPM Command Manual Set N1 Numerics 55.0 ----- 106.0% RPM
(b)
Display Range for EGT
EGT Pointer 0° ----- 1,150°C EGT Numerics -50° ----- 1,150°C
(c)
Display Range for N2
N2 Pointer 0 ----- 120% RPM N2 Numeric Counter .0 ----- 120.0% RPM
(d)
Display Range for FF/FU (Pound Version)
FF Pointer 0 ----- 12,000 PPH FF Numerics 0 ----- 12,000 PPH FU Numerics 0 ----- 65,000 LBS
(e)
Display Range for FF/FU (Kilogram Version)
FF Pointer 0 -----6,000 KGPH FF Numerics 0 -----5,500 KGPH FU Numerics 0 ----- 30,000 KG
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH EIS ú
31-42-00
ú ú 02 Page 7 ú Jul 15/96
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
3. EIS Secondary Display_____________________
A. Physical Description
(1)
The instrument consists essentially of a chassis assembly which encloses four electronic circuit boards. The front end of the chassis supports the display 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.
(2)
The display module incorporates various light emitting diode (LED) displays, external light sensors and the integral lighting. The front bezel supports an unmarked confidence test button (BIT).
(3)
The integral lighting consists of six lamps which are fed from an external 0-5v, 400 Hz single phase ac supply.
(4)
The unit is housed in a rectangular case assembly.
B. Functional Description (Fig. 3)
(1)
The EIS Secondary Display provides displays of engine 1 and 2 oil pressure (OIL PRESS), oil temperature (OIL TEMP), oil quantity (OIL QTY), vibration (VIB), and total air temperature (TAT). It also displays hydraulic system A and B pressure (HYD PRESS) and quantity (QTY).
(2)
Engine OIL PRESS, OIL TEMP, VIB and HYD PRESS parameters are displayed by LED pointer moving on the dial face. TAT, engine OIL QTY and hydraulic QTY parameters are displayed by a numeric digital counter.
(3)
All displayed engine and hydraulic system parameters are output on an ARINC 429 digital data bus.
(4)
The Secondary Display also provides an independent analog output of engine oil pressure for use by the DFDAU.
(5)
The EIS Secondary Display is also capable of monitoring input signals for failure. Any input sensor fails in any detectable manner, the secondary display will provide failure indication of the affected parameter in the same manner as the EIS Primary Display.
(6)
Secondary Display Parameters Indication
(a) TAT Parameter
1) The total air temperature (TAT) input signal is from the digital air data computer (DADC) via an ARINC 429 digital data bus.
2) The TAT parameter value is displayed by a digital counter. The TAT indicator will show dashes if no computed data (NCD) is being received from the DADC.
(b) OIL PRESS Parameter
1) The OIL PRESS signal is derived from an engine oil transmitter. The parameter value is displayed by an LED pointer moving on the dial.
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