(j)  
Push the LSK adjacent to <NEGATIVE LIMIT for the negative surface limit positions.

 (k)  
Write down the values for the elevator surface position:

 L ______ , C ______ , R ______ .

 (l)  
Make sure that the values for the left, center, and right channels are -20.0 degrees (minimum).

 (m)  
Make sure that the control columns stay at the negative limit and the AUTOPILOT DISC does not show on the main EICAS display.

 (n)  
Push the LSK adjacent to <CONTINUE on the CDU to go back to the POSITIVE LIMIT and NEGATIVE LIMIT page.

 (o)  
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.
 (p)  Push the captain's or first officer's autopilot disconnect switch two times.
 G. Put the Airplane in Its Usual Condition
 S 865-415
 (1) Remove hydraulic power if it is not necessary (AMM 29-11-00/201).
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 S 865-417
 (2)  Remove the electrical power if it is not necessary
 (AMM 24-22-00/201).

 TASK 22-10-00-745-355
 20. Ground Test - Rudder Surface Limit__________________________________
 A. General
 (1)  This test is for a check of the rudder surface limit. During this test, the rudder servos move the rudder surface to its limits in the two directions and show the final surface position.
 B. References
 (1)  
AMM 09-11-00/201, Towing

 (2)  
AMM 22-11-01/401, FCC Software Installation

 (3)  
AMM 24-22-00/201, Manual Control

 (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 Zones
 221 Control Cabin, LH
 222 Control Cabin, RH

 D. Preconditions
 S 865-462
 (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)  
Hydraulic Pressure Supplied (AMM 29-11-00/201).

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

 (e)  
Tow pin installed at the nose landing gear (AMM 09-11-00/201).

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

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

 E. Prepare for the Test
 S 865-356
 (1)  Supply electrical power (AMM 24-22-00/201).
 S 865-357
 WARNING: MAKE SURE THAT PERSONS AND EQUIPMENT ARE CLEAR OF ALL CONTROL
_______ SURFACES BEFORE YOU SUPPLY HYDRAULIC POWER. AILERONS, RUDDERS, ELEVATORS, FLAPS, SPOILERS, LANDING GEAR, AND THRUST REVERSERS CAN MOVE QUICKLY WHEN YOU SUPPLY HYDRAULIC POWER. THIS CAN CAUSE INJURY TO PERSONS AND DAMAGE TO EQUIPMENT.
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 (2)  
Supply the hydraulic pressure to the hydraulic systems NO. 1, 2, 3, and 4 (AMM 29-11-00/201).

 S 865-358

 (3)  
Make sure the FLT CONTROL HYD POWER TAIL 1, 2, 3, and 4 switches are in the NORM position. These switches are on the Pilots' Overhead Maintenance Panel (P461).

 S 865-359

 (4)  
Make sure the FLT CONTROL HYD POWER WING 1, 2, 3, and 4 switches are in the NORM position. These switches are on the Pilots' Overhead Maintenance Panel (P461).
　
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