(d)  
Fill the screw holes with the BMS 5-95 sealant.

 NOTE: Make the sealant smooth in relation to the antenna
____
 surface.

 F. GPS Antenna Installation Test
 S 864-019
 (1)  Supply electrical power (AMM 24-22-00/201).
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A 737-300/400/500MAINTENANCE MANUAL
 S 864-020
 (2)  Remove the DO-NOT-CLOSE tags and close these circuit breakers:
 (a)  
On the electronic load circuit breaker panel P6:
 1) GPS 1

 (b)  
On the electronic load circuit breaker panel P18:
 1) GPS 2

 S 584-021
 (3)  
Move the airplane to a position where the GPS antennas have a clear view of the GPS satellites.

 S 714-022

 (4)  
Do these steps to see the GPS position on an FMC CDU:

 (a)  
Push the INIT REF key on one of the CDUs.

 (b)  
Push the line select key (LSK) that is adjacent to <INDEX.

 (c)  
Push the LSK that is adjacent to <POS.

 (d)  
Push the NEXT PAGE key on the CDU. 1) Make sure the GPS R position is shown on the line above RADIO.

 2)  Make sure the GPS L position is shown on the line above the GPS R position.
 NOTE: As much as 10 minutes of time can be necessary for
____ the positions to show on the CDU.
 (e)  If the GPS position is not displayed after 10 minutes, check to see if the GPS is enabled. 1) Push the NEXT PAGE key on the CDU. 2) Push the LSK adjacent to NAV STATUS>. 3) Push the NEXT PAGE key on the CDU. 4) Make sure that the ON below GPS UPDATE is highlighted on
 the NAV OPTIONS 2/2 page. 5) If the OFF below GPS UPDATE is highlighted, push the adjacent LSK. 6) Make sure that the display changes so that the ON below GPS
 UPDATE is highlighted. 7) Push the NEXT PAGE key on the CDU. 8) Push the LSK adjacent to POS SHIFT>. 9) Push the PREV PAGE key on the CDU. 10) Make sure that the POS REF 2/3 page shows the position of
 GPS L and GPS R.

 S 864-023
 (5)  Remove electrical power if it is not necessary (AMM 24-22-00/201).
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A
737-300/400/500MAINTENANCE MANUAL
 FLIGHT MANAGEMENT COMPUTER SYSTEM - DESCRIPTION AND OPERATION
_____________________________________________________________
 1.  General (Fig. 1)_______
 A.  The Flight Management Computer System (FMCS) is one of four major subsystems of the Flight Management System (FMS). The other three major subsystems are: the Digital Flight Control System (DFCS), the Auto-throttle system (A/T), and the Inertial Reference System (IRS).
 B.  The FMCS provides the functions of navigation, lateral guidance (LNAV), vertical guidance (VNAV), flight planning, and airplane performance optimisation. These functions assist the pilot with the flight management and control of the airplane.
 C.  The FMCS allows the operator to preplan an entire flight. These procedures are simplified by FMCS integration of navigation, guidance, and performance management functions. In conjunction with other FMS components, the FMCS provides automatic lateral guidance, vertical guidance and speed control (within constraints of air traffic control). The flight preplan function allows a route to be preplanned from origin to destination. The preplan is from data stored in the navigation data base. The FMCS calculates minimum cost flight profiles for climb, cruise and descent, which may be used by the DFCS and the A/T for automatic flight control through the LNAV and VNAV modes. In addition all computed values are displayed to aid the pilot in flying the optimum profile using manual control.
 D.  A single Flight Management Computer System (FMCS) is installed in the airplane. The FMCS consists of two units: a Control Display Unit (CDU) and a Flight Management Computer (FMC) (Fig. 1).
　
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