(a)  
Open the front panel door of the QAR.

 (b)  
Insert a tape cartridge into the QAR.

 (c)  
Make sure the "POWER ON" Lamp comes on.

 (d)  
Close the front panel door of the QAR.

 (2)
Remove electrical power if it is not necessary (AMM 24-22-00/201).

 S 864-019
  GUN 051 ú

 31-35-01
 ú ú 02 Page 402 ú Mar 20/96

A

757 MAINTENANCE MANUAL
 ENGINE INDICATION AND CREW ALERTING SYSTEM - DESCRIPTION AND OPERATION
______________________________________________________________________
 1.  General (Fig. 1)_______
 A.  The Engine Indication and Crew Alerting System (EICAS) is an automatic engine monitoring and centralized alerting system. The system provides display for engine parameters and crew alerts. It also provides status information and ground maintenance data.
 B.  EICAS consists of two multicolored display cathode ray tubes, two control panels, and two redundant computers. Each computer receives analog and digital input signals from airplane systems and sensors. This information is analyzed and the desired data is displayed on the two CRTs. Only one computer drives the display units at any one time. The other computer is used as a backup.
 C.  The EICAS computers are software loadable. There are two types of software, the OPS and the OPC. The OPS (Operational Program Software) is the core software and application software that contains the EICAS functions. The OPS is installed in all airplanes with EICAS computers and will possibly not change. The OPC (Operational Program Configuration file) is the specified software that sets the EICAS configuration of your airplane. The OPC will change when your EICAS configuration changes.
 D.  The two display units are centrally located one above the other in the flight deck. The top display mainly provides primary engine thrust information and crew alerting messages. The bottom display provides secondary engine parameters and airplane status information. In addition, the bottom display can provide maintenance data while on the ground. All information can be shown on either the top or bottom display in case of in-flight failure of one of the units.
 E.  EICAS incorporates automatic display changes. These changes occur only to indicate engine or system abnormality. Continuous BITE monitoring circuits detect faults that can affect the integrity of the displays. If a fault is detected in EICAS, automatic failure modes and system redundancy provide for maximum data display.
 F.  Control of EICAS is provided by two different control panels in the flight deck. The EICAS display select panel is used for in-flight selection of display formats. The EICAS maintenance panel is used for selection of ground maintenance displays.
　
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