(b)  
Make sure that there is no failure indication shows on the CDU.

 (c)  
Continue with the instructions on the CDU until the POSITIVE LIMIT and NEGATIVE LIMIT page is shown.

 (d)  
Push the LSK adjacent to <POSITIVE LIMIT for the positive surface limit positions.

 (e)  
Write down the values for the aileron surface position:

 L ______ , C ______ , R ______ .
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747-400 MAINTENANCE MANUAL
 (f)  Make sure that the values for the left, center, and right
 channels are +16.0 degrees (minimum).
 (g)  Make sure that the control wheels stay at the positive limit
 and the AUTOPILOT DISC does not show on the main EICAS display.
 (h)  Push the LSK adjacent to <CONTINUE on the CDU to go back to the
 POSITIVE LIMIT and NEGATIVE LIMIT page.
 (i)  Push the LSK adjacent to <NEGATIVE LIMIT for the negative
 surface limit positions.
 (j)  Write down the values for the aileron surface position:
 L ______ , C ______ , R ______ .
 (k)  Make sure that the values for the left, center, and right
 channels are -16.0 degrees (minimum).
 (l)  Make sure that the control wheels stay at the negative limit
 and the AUTOPILOT DISC does not show on the main EICAS display.
 (m)  Push the LSK adjacent to <CONTINUE on the CDU to go back to the
 POSITIVE LIMIT and NEGATIVE LIMIT page.
 (n)  Push the LSK adjacent to <ADVANCE to complete the test.
 NOTE: An autopilot disconnect warning will occur at the end____
 of this test, which is permitted.
 (o)  Push the captain's or first officer's autopilot disconnect
 switch two times.

 X. Airplane to Its Initial Condition
 S 865-438
 (1)
Remove hydraulic power if it is not necessary (Ref 29-11-00/201).

 S 865-161

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

 TASK 22-10-00-715-165
 22. Automatic Stabilizer Trim Test
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MAINTENANCE MANUAL

 NOTE: This is a scheduled maintenance task.
____
 A. General
 (1)  This procedure is for the operational check of the automatic stabilizer trim system. It makes sure that the automatic stabilizer trim system which includes trim limits operates correctly.
 B. References
 (1)  
AMM 22-11-01/401, Flight Control Computer

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

 (3)  
AMM 27-51-51/401, Flap Control Unit

 (4)  
AMM 29-11-00/201, Main Hydraulic Supply System

 (5)  
AMM 34-61-00/501, Flight Management Computer System

 (6)  
AMM 34-61-02/401, Control Display Unit

 (7)  
AMM 45-10-00/501, Central Maintenance Computer System

 C. Access
 (1)  Location Zone
 221 Control Cabin, LH
 222 Control Cabin, RH

 D. Preconditions
 S 865-464
 (1)  These conditions are necessary for this task:
 (a)  
Electrical Power On (AMM 24-22-00/201).

 (b)  
Central Maintenance Computer (CMC), serviceable (AMM 45-10-00/501).

 (c)  
Control Display Unit (CDU), serviceable (AMM 34-61-02/401).

 (d)  
Flight Control Computer (FCC), serviceable (AMM 22-11-01/401).

 (e)  
Flight Management Computer (FMC), serviceable (AMM 34-61-00/501).

 (f)  
Hydraulic Pressure Supplied (AMM 29-11-00/201).
　
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