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TROUBLE  PROBABLE CAUSE  ISOLATION PROCEDURE  REMEDY 
Control cable tension repeatedly checks low after flight following normal rig procedures  Excessive cable tension relaxation  Check control cable tension (Ref 27-41-0, A/T) If cable rig load is repeatedly more than 15 pounds below value listed in cable tension chart, cable is worn, or requires rerigging.  Rerig control cable as follows: 
1. Increase cable rig load to twice rig load listed in cable tension chart (Ref. 27-41-0, A/T). 
2. Cycle system 5 times while maintaining increased rig load. 
3. Reduce cable rig load to rig load listed in cable tension chart (Ref. 27-41-0 A/T). 
4. Cycle system 5 times while maintaining normal rig load (Sep 3). 
NOTE: Do not allow cable rig load to relax below rig load established in Step 3. 
5. After approximately one week of service rig cable to normal rig load (Step 3). 
6. Cycle system 5 times 
while maintaining normal 
rig load (Step 3). 
Check control cable for  Replace control cable (Ref. 
broken wires (Ref. 20-20-31, I/C).  20-10-01, R/I). 

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HORIZONTAL STABILIZER TRIM CONTROL SYSTEM - ADJUSTMENT/TEST
1.  General
A.  Adjustment and testing of the stabilizer trim system should be avoided with the stabilizer exposed to strong tail winds. Tail winds may cause loading of control surfaces that could be misinterpreted as erratic operation of one or more of the stabilizer trim control systems.
CAUTION:  DO NOT OPERATE RIGHT AND LEFT STABILIZER TRIM SWITCHES SIMULTANEOUSLY AND IN OPPOSITE DIRECTIONS. APPLICATION OF THIS PROCEDURE ENERGIZES BOTH ELECTROMAGNETIC CLUTCHES IN THE TRIM ACTUATOR, RESULTING IN MOTOR STALL. IT IS POSSIBLE DURING THIS CONDITION TO DAMAGE THE MOTOR DUE TO OVERHEATING. 
DO NOT EXCEED MAIN ELECTRICAL ACTUATOR DUTY CYCLE OF 2 MINUTES ON AND 13 MINUTES OFF.
NOTE:  A failure in which the motor has been damaged due to overheating may be recognized immediately since the manual trim wheel will not rotate when a stabilizer trim switch is actuated. Manual and autopilot operation of the trim system will not be affected.
B.  External painted markings on fuselage and leading edge of horizontal stabilizer are convenience-type reference points for stabilizer trim operations. Markings are for use by personnel to obtain a convenient ground visual indication of direction and extent of travel of stabilizer. Markings are not to be used as indexes for rigging of stabilizer.
C.  Stabilizer trim control wheels must be installed so that handles on the captain's and first officer's wheels are 90 (+ 15) degrees apart. This positioning of the wheels places the handles to allow continuous torque when two men are manually trimming the stabilizer.
2.  Horizontal Stabilizer Trim System Adjustment
A.  General
(1)  The stabilizer trim control system is properly adjusted when the individual components are adjusted to meet the following conditions:
(a)  Stabilizer Trim System Cables
1)  With approximately an equal number of turns of STA and STB cable on forward drum, cable tension is within limits of the required value. See figure 501, Table 1, for cable tension requirements. If not, these conditions may be met by adjusting turnbuckle in lower forward body section per paragraph 2.D.(3).
500 
May 15/81  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-41-0 Page 501 

G42369G42372
Horizontal Stabilizer Trim System Adjustment  500 
27-41-0  Figure 501 (Sheet 1)  Feb 20/90 
Page 502 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

500  Horizontal Stabilizer Trim System Adjustment 
Feb 20/90  Figure 501 (Sheet 2)  27-41-0 
Page 503 
　
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