-
Make sure the pogos are extended at least 0.20 inches (5 mm).

 -
Make sure the elevator PCU is in rig.

 -make sure the control column was not moved after the test was started.
 (j)  
Use the tail flight control shutoff valve to remove the power from the left hydraulic system.

 (k)  
Remove the pogo tools from the left middle and left outboard PCA pogos.

 (l)  
Open the tail flight control shutoff valves to supply power to the left and right hydraulic systems.

 (m)  
Make sure that the elevator goes to the neutral position mark by less than | 0.10 inch (+/- 2.5 mm).

 (n)  
Use the tail flight control shutoff valves to remove power from the left and center hydraulic systems.

 (o)  
Use pogo tools to extend the pogos at the left middle and left inboard PCAs by 0.20 to 0.25 inch (5.1-6.3 mm).

 (p)  
Open the tail flight shutoff valve to supply power to the left hydraulic system.

 (q)  
Make a mark on the tape at the elevator position three seconds after you open the tail flight shutoff valve.

 (r)  
After 28 to 32 seconds, make sure the elevator travels less than 1.0 inch (25.4 mm).

 (s)  
Use the tail flight control shutoff valve to remove power from the left hydraulic system.

 (t)  
Remove the pogo tools from the left middle and left inboard PCAs.

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A

757 MAINTENANCE MANUAL
 (u)  
Use the tail flight control shutoff valves to supply power to the left and center hydraulic systems.

 (v)  
Remove the pressure from the left, right, and center hydraulic systems (Ref 29-11-00/201).

 H.
Put the Airplane Back to Its Usual Condition

 S 864-026
 (1)  
Remove the DO-NOT-CLOSE tags and close these circuit breakers on the overhead panel, P11:

 (a)  
11H17, FLT CONT SHUTOFF TAIL LEFT

 (b)  
11H18, FLT CONT SHUTOFF TAIL CTR

 (c)  
11H28, FLT CONT SHUTOFF TAIL RIGHT

 S 864-027
 (2)  
Put the R, L, and C FLT CONTROL SHUTOFF valve switches on the right side panel, P61, to the ON position.

 S 614-028

 (3)  
Fill the applicable hydraulic reservoir if necessary
 (Ref 12-12-01/301).

 S 414-029

 (4)  
Close the access door for the pressure reducer valves and bypass valve (Ref 06-42-00/201).

 (5)
Remove electrical power if it is not necessary (Ref 24-22-00/201).

 S 864-030
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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757
MAINTENANCE MANUAL

 ELEVATOR AFT QUADRANTS - REMOVAL/INSTALLATION
_____________________________________________
 1.  General
_______
 A.  This procedure contains steps to remove and install the aft quadrants in the elevator control system.
 TASK 27-31-15-024-001
 2.  Remove the Aft Quadrants
________________________
 A.  Equipment
 (1)  
Rig Pins from Set B20003-XX (Ref 20-10-24):

 (a)  
E/ST6 - P/N B20003-21

 (b)  
E/ST8 - P/N B20003-21

 (c)  
E/ST9 - P/N B20003-21

 (2)  
Gage Assembly - B27039-3, Part of Elevator and
 Stabilizer Rigging Equipment, B27039-1

 (3)  
Removal Tool, Decentering Springs, Elevator - B27060-1

 B.  
References

 (1)  
06-42-00/201, Empennage Access Doors and Panels

 (2)  
20-10-24/201, Rig Pins

 (3)  
27-31-03/401, Asymmetry Limiter Actuator

 (4)  
29-11-00/201, Main (Left, Right, and Center) Hydraulic Systems
　
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