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 (2)  
The fast/slow command function of the Autothrottle is also depicted in this illustration.

 (3)  
The name of most data words and discrete bits are self-explanatory. A/T BITE response is the alpha-numeric information and data displayed on the FMC control display unit, while performing A/T BITE.

 (4)  
The fast/slow indications are derived from the speed error function. It is the airspeed error, Mach error or minimum speed error. If the A/T is disengaged, versine and compensated acceleration are added.

 (5)  
The fast/slow pointers are enabled by the DFCS. The F/S enable signal from the DFCS system depends upon engagement of the A/T and mode of operation. When the A/T is engaged, the F/S pointer is enabled only in ALT HOLD or V NAV (altitude hold). If the A/T is not engaged or the A/T engages only to ARM, the DFCS enables the F/S pointer when in the GS, ALT ACQ, ALT HOLD or V/S.

 (6)  
The fast/slow pointers are biased out of view by the A/T when the fast/slow signal is not valid, the A/T is armed for takeoff or in A/T go-around.

 (7)  
Out of view bias direction is determined by program pin A25. A high on the program pin selects an out of view bias in the fast direction.

 (8)  
The speed flag on the ADI's is retracted from view by the F/S valid logic. When in view, the flag indicates a validity type failure in the A/T computer. Valid logic is described with the engage/disengage illustration.

 23. A/T BITE (Fig. 17)________
 A.  Tests
 (1)  
The Autothrottle built-in test equipment (BITE) provides for the ground maintenance testing of the Autothrottle system.

 (2)  
A/T BITE is contained in the A/T computer, and is accessed through the Flight Management Computer system CDU. In order to minimize ground test time, the BITE computer program is divided into three fault isolation routines: current status, LRU interface tests, and in-flight faults storage and display.

 (a)  Current Status Tests
 1)  This routine provides quick tests of the computer and its interfaces. It provides fault identification, and enables the interactive tests.
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AIRPLANES WITHOUT EFIS
AIRPLANES WITH EFIS
LEVERS AIRPLANES WITH A/T COMPUTER -11 AND ON
A/T Bite Introduction Figure 17
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737-300/400/500MAINTENANCE MANUAL
 (b)  
LRU Interface Tests

 1)  This test routine provides the evaluation of test data from interfacing systems and sensors. The routines do not test the interfacing systems, only the electrical interface.

 (c)  
In-Flight Faults

 1)  The A/T computer records the fault history for the last 10 flights, in non-volatile memory. This routine provides access to the record.
 (3)  In addition to the fault isolation routines described above, the A/T BITE program contains routines for the rigging of the throttle system. The rigging routines consist of: the A/T range check and A/T rigging adjust.
 (a)  
A/T Range Check

 1)  This routine provides instructions to perform the throttle range check, and displays the corresponding throttle position values.

 (b)  
A/T Rigging Adjust

 1)  This routine provides instructions to set up and adjust for the correct rigging positions; and displays the power lever angle synchro output.
　
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