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A
747-400
MAINTENANCE MANUAL

TABLE 1  1  TO GET THE CORRECT CABLE TENSION, MAKE SURE THE 
AIRFRAME TEMPERATURE IS STABLE (USE A TOLERANCE 
CABLE RIGGING ADJUSTMENT LOADS  OF |5`F) FOR A MINIMUM OF 1 HOUR. 
(`F) TEMPERATURE 1  BODY/WING CABLE CONTROL WHEEL BUS CABLE TENSION IN POUNDS 2 4  2  WHEN RIGGING THE SYSTEM, CABLE LOADS SHOULD BE ARE MORE THAN |15 LBS FROM THE TABLE VALUES. THE SYSTEM MUST BE ADJUSTED WHEN THE CABLE LOADS |5 LBS FROM THE TABLE VALUES. 
5  6  3  3  ARE MORE THAN |20 LBS FROM THE TABLE VALUES. THE SYSTEM MUST BE ADJUSTED WHEN THE CABLE LOADS 
WHEN RIGGING THE SYSTEM, CABLE LOADS SHOULD BE 
110 (43`C)  123  153  93  |15 LBS FROM THE TABLE VALUES. 
90 (32`C) 70 (21`C) 80 (27`C)  105 110 114  130 135 141  75 80 84  4  THE TWO ENGINES ARE INSTALLED ON THE WING. IF POSSIBLE, MAKE THE LAST CABLE ADJUSTMENTS WHEN 
60 (16`C)  101  125  71  5  WING CABLES & LEFT BODY CABLES 
40 (4`C) 50 (10`C)  97 93  115 120  63 67  6  RIGHT BODY CABLES 
30 (-1`C)  89  110  59 
10 (-12`C)  80  99  50 
-10 (-23`C)  72  89  42 
-30 (-34`C)  64  79  34 
-40 (-40`C)  58  71  28 

SEE D
RIG PIN A/S-2
TRIM AND FEEL MECHANISM
CABLE AB
CABLE AA
CABLE AA
LEFT AILERON RIG
PROGRAMMER  RIGHT AILERON
PIN A/S-6 PROGRAMMER
CABLE AB
RIG
D PIN A/S-7
Inboard Aileron Vertical Reaction Link Installation Figure 401 (Sheet 2)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

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747-400 MAINTENANCE MANUAL
 D. Prepare for Removal
 S 864-002
 (1)  Do this task: "Hydraulic System Pressurization" (Ref 29-11-00/201).
 NOTE: No. 1 or 3 hydraulic systems supply the left control package.
____ No. 2 or 4 hydraulic systems supply the right control package.
 S 494-003
 (2)  Make sure the ground locks are installed on the landing gear.
 S 494-004
 WARNING: YOU MUST CAREFULLY DO THE STEPS IN THE TASK BELOW TO INSTALL
_______ THE DOOR LOCKS ON THE LANDING GEAR DOORS. THE DOORS CAN CLOSE QUICKLY IF YOU DO NOT INSTALL THE DOOR LOCKS CORRECTLY. THIS CAN CAUSE INJURY TO PERSONS OR DAMAGE TO EQUIPMENT.
 (3)  
Do this task: "Installation of the Door Locks on the Wing Landing Gear" (Ref 32-00-30/201).

 S 014-018

 (4)  
Open panels 573AB, 573BB and 573CB for the left inboard aileron and panels 673AB, 673BB and 673CB for the right inboard aileron (Ref 06-09-08/201).

 E.
Procedure

 S 024-006
 (1)  
Remove the vertical reaction link (Fig. 401):

 (a)  
Remove four bolts, washers and nuts to disconnect the quadrant mounting bracket from the vertical reaction link.

 (b)  
Remove the attach bolt, washers and nuts to disconnect the vertical reaction link from the left side of the structure (Detail A).

 (c)  
Remove the attach bolt, washers, bushings and nut to disconnect the vertical reaction link from the right side of the structure (Detail B).

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 (d)  
Use spanner wrenches to remove the forward mounting bolt, bushings, and nuts.

 (e)  
Remove the forward mounting bolt, bushings, and nuts that attach the lower forward end of the power control package to the vertical reaction link (Detail C).

 TASK 27-11-07-404-007
 3.  Inboard Aileron Vertical Reaction Link Installation___________________________________________________
　
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