C.  Procedure
 S 862-095
 (1)  Supply electrical power (AMM 24-22-00/201).
 S 422-096
 CAUTION: MAKE SURE YOU HAVE THE CORRECT SOFTWARE DISK FOR THE DMU BEFORE
_______ YOU PUT IT IN THE DISK DRIVE. FOR THE DMU TO BE AN APPROVED INSTALLATION, THE CORRECT SOFTWRE MUST BE INSTALLED.
 (2)  Install the ACMS software:
 (a)  
AIRPLANES WITH ONE SWITCH ON THE DATA LOADER CONTROL PANEL; Set the selector switch on the data loader control panel to ACMS.

 (b)  
AIRPLANES WITH TWO SWITCHES ON THE DATA LOADER CONTROL PANEL; Do these steps at the data loader control panel: 1) Set the upper switch to SINGLE SYS. 2) Set the system select switch to ACMS.

 (c)  
Put the disk in the disk drive.

 NOTE: Software installation starts automatically when you put
____ the disk in the disk drive of the data loader.
 (d)  Make sure the data loader shows the percentage of software that is installed.
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747-400 MAINTENANCE MANUAL
 (e)  When the software installation is completed, make sure the COMPLETE indication shows on the data loader.
 S 712-097
 (3)  Make sure the correct software is installed:
 (a)  
Push the MENU key on the center CDU.

 (b)  
Push the line select key adjacent to <ACMS.

 (c)  
Push the line select key adjacent to <VERSIONS AND P/N.

 CAUTION: MAKE SURE YOU KNOW THE CORRECT SOFTWARE PART NUMBER FOR
_______ THE DMU WHEN YOU LOOK AT THE SOFTWARE PART NUMBER ON THE CDU. FOR THE DMU TO BE AN APPROVED INSTALLATION, THE CORRECT SOFTWRE PART NUMBER MUST BE INSTALLED.
 (d)  
Make sure the part number of the software you installed shows on the display.

 (e)  
Set the selector switch for the data loader to NORMAL.

 (f)  
Push the eject switch to remove the disk from the data loader.

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 1.

2.

3.

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747-400 MAINTENANCE MANUAL
 WEIGHT AND BALANCE SYSTEM - DESCRIPTION AND OPERATION
_____________________________________________________
General
_______
 A.  The weight and balance system (WBS) determines the gross weight, center of gravity, zero fuel weight, and zero fuel center of gravity of the airplane.
 B.  The WBS (Fig. 1) consists of these components:
 (1)
4 nose landing gear load sensors (axial type) with mounting adapters

 (2)
2 in-axle mount (IAM) assemblies (for nose gear sensors)

 (3)
16 main landing gear load sensors (right angle type)

 (4)
16 protective covers (for main gear sensors)

 (5)
1 pitch attitude sensor (PAS)

 (6)
1 calibration module (CM)

 (7)
1 weight and balance computer (WBC)

 (8)
1 remote dedicated display unit (RDDU)

 C.  At all times except during cargo handling (or when circuit breaker 415F18 CARGO HANDLING CONT MN DK is open), the WBS receives 115-volt, 400-Hz operating power through circuit breaker 414K20 WT & BAL on panel P414, Power Distribution Center - Left.
 D.  During cargo handling operations, (or when circuit breaker 415F18 CARGO HANDLING CONT MN DK is closed) the WBS receives 115-volt, 400-Hz operating power through circuit breaker 415G21 WBS CHB ALT on panel P415, Power Distribution Center - Right.
 E.  The WBC receives load sensor signals which represent weight on individual landing gear wheels. The WBC also receives individual and total tank fuel quantities, individual engine spar fuel valve positions, hydraulic system pressure data, all entry doors closed data, and air/ground indication from the electronic interface units (EIUs). The WBC uses the above inputs to calculate the airplane gross weight, center of gravity, zero fuel weight and zero fuel center of gravity. This information is displayed in the flight deck on the control display units (CDUs).
　
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