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LOW OIL PRESSURE
OIL P

REDLINE LIMIT OIL PRESSURE

66
65 65 12
HIGH OIL TEMPERATURE REDLINE LIMIT
OIL
OIL T
TEMPERATURE

105 105 103
107 HIGH OIL TEMPERATURE

OIL QUANTITY

15 15 OIL Q 19
15 AMBER BAND LIMIT

LOW OIL TEMPERATURE AMBER BAND LIMIT
EICAS Secondary - Partial Display Figure 37
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 (3)  
Fuel-On Command

 (a)  The "fuel on" bug is displayed with the N2 feature whenever an engine is not running. During any engine start (on ground or in the air), the "fuel on" bug is displayed as a magenta colored horizontal bar which indicates the N2 rpm at which fuel should be applied to the engine.

 (4)  
Cross-Bleed Start Message

 (a)  For in-flight engine restarts, if the in-flight start data is being displayed on the EICAS primary format, and the airspeed and altitude conditions are within the cross bleed envelope for engine restart, the message X-BLD will be displayed with the N2 feature.

 (5)  
Fuel Flow

 (a)  The fuel flow for each engine is indicated by a digital readout in units of kgm/hr divided by 1000.

 (6)  
Oil Pressure

 (a)  Indicated by digital readouts and triangular pointers which translate along ungraduated vertical scales. The color of the readout and pointer changes from white to amber and red as the respective amber band and redline limits are exceeded. Display of the low oil pressure amber limit is inhibited if the engines are not running.

 (7)  
Oil Temperature

 (a)  Indicated by digital readouts and triangular pointers which translate along ungraduated vertical scales. The color of the readout and pointer changes from white to amber and red as the respective amber and redline limits are exceeded.

 (8)  
Oil Quantity

 (a)  Indicated by a white colored digital readout in units of liters. The readout changes from white to magenta in color if the low oil quantity level (3.78 liters) is exceeded.

 (9)  
Vibration

 (a)  Indicated by digital readouts and triangular pointers which translate along vertical scales. The range of each scale is from zero to five units. The display indicates the highest rotor vibration measured by the Airborne Vibration Monitor (AVM) system. A message (N1 or N2) is displayed above the readouts to indicate the rotor vibration which is presently being displayed. If the tracking filter of the AVM is inoperative, broadband vibration is indicated and the associated message (BB) is displayed above the readouts.
 D. EICAS Compacted Display (Fig. 38)
 (1)  General
 (a)  
The EICAS compacted engine parameter format is a combination of the EICAS primary and EICAS secondary display parameters. These engine parameters are presented on a single DU.

 (b)  
The compacted engine format may be displayed on the main DU if a maintenance format is being presented on the auxiliary DU.

 (c)  
For single EICAS DU operation (degraded), all engine parameters are displayed on the remaining EICAS DU in a compacted format.

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 (d)  The EICAS compacted engine parameter display is presented in either a full or partial format. If all the secondary engine parameters are displayed, the format is termed compacted-full (Fig. 38). If some, but not all of the secondary engine parameters are displayed, the format is termed compacted-partial (Fig. 39).
 (2)  
The format for the display of primary thrust data such as EPR, thrust mode and selected temperature is identical to that presented on the EICAS primary display. N1 and EGT are indicated by digital readouts enclosed in boxes. The remaining engine parameters are indicated by digital readouts only.
　
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