(4)  
Do this task "Ground Test - Torque Zero Function"

 TASK 32-42-00-715-297
 3.  Ground Test - Brake System Bite_______________________________
 A. General
 (1)  
The Brake System BITE Test has two parts, a configuration check and a subsystem test.

 (2)  
The configuration check does a check of inputs to the BSCU when the airplane is put into a given configuration. This configuration check makes sure that the inputs to the brake control system are correct. These inputs are necessary for correct operation of the brake control system.

 (3)  
The subsystem test does a test for correct operation of each subsystem of the brake control system.

 (4)  
If the results of the ground test are not satisfactory, refer to the Fault Isolation Manual (FIM 32-42-00/101 Fig. 104) for fault isolation procedures.

 (5)  
During the ground test, a time of 45 seconds without an input by the user will stop the test. The Control Display Unit (CDU) will then return to the GROUND TESTS menu. If this occurs, the ground test must be started again.

 (6)  
To successfully pass this test, the Autobrakes Select switch must remain in the "ARMED" until the test is completed. After the test is completed, the switch will go to "DISARM" itself. If you set the Autobrake switch in any of the five landing autobrake position (1,2,3,4 or MAX), the "AUTOBRAKES" advisory EICAS message will display and the Autobrake selector switch will move tothe "DISARM". If you perform the BRAKE SYSTEM BITE test with the Autobrakes select switch in the "RTO" position, the Autobrake selector switch will move to the "OFF" position with no EICAS message.

 B.
References

 (1)  
AMM 09-11-00/201, Towing

 (2)  
AMM 24-22-00/201, Manual Control

 (3)  
AMM 29-11-00/201, Main Hydraulic Supply System

 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 32-42-00
 ALL  ú ú 01 Page 502 ú Oct 10/96
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL

 (4)  
AMM 34-21-00/201, Inertial Reference System

 (5)  
FIM 32-42-00/101, Fig. 104.

 C.
Access

 (1)  
Location Zones
 221 Control Cabin, LH
 222 Control Cabin, RH
 730 Wing Landing Gear - Left and Doors
 740 Wing Landing Gear - Right and Doors
 750 Body Landing Gear - Left and Doors
 760 Body Landing Gear - Right and Doors

 D.
Preconditions

 S 865-409
 (1)  
These conditions are necessary for this task:

 (a)  
Electrical power is available (AMM 24-22-00/201).

 (b)  
The Integrated Display System (IDS) is serviceable (AMM 31-61-00/501).

 (c)  
The Intertial Reference System is serviceable (AMM 34-21-00/201).

 E.
Prepare for the Test

 S 845-298
 (1)  
Make sure that the landing gear ground locks are installed
 (AMM 09-11-00/201).

 S 845-299

 (2)  
Make sure that the wheel chocks are installed.

 S 845-300

 (3)  
Supply electrical power (AMM 24-22-00/201).

 S 845-301

 (4)  
Set the L, C, and R IRS mode selector switches on the Pilot's Overhead Panel, P5, to NAV to align the Inertial Reference Systems (AMM 34-21-00/201).

 S 845-302

 (5)  
Release the parking brake.

 (6)  
Make sure that all the thrust levers are set to the aft stop.

 S 845-304

 (7)  
Make sure that the landing gear control handle is in the DOWN/EXTEND position.

 (8)  
Make sure that the SPEED BRAKE lever is in the DOWN position.

 S 845-303
 S 845-305
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 32-42-00
 ALL  ú ú 01 Page 503 ú Jun 15/98
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
　
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