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Feb 20/86  27-31-0 
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TROUBLE  PROBABLE CAUSE  ISOLATION PROCEDURE  REMEDY 
Moderate vertical vibration in aft and forward fuselage, (Usually above 250 knots indicated airspeed.)  Excessive play in elevator tab  Check for loose tab hinge fitting, tab horn fitting, worn bushings and/or bearings Check for insufficient torque on hinge fitting bolts Check tab rods for loose or worn rod ends, loose checknuts or loose bolt to rod end connection Check for loose or worn tab linkage, bearings, bushings and bolts Check tab free play per 27-31-0, Elevator and Tab Control System -Adjustment/Test. Maximum shall not exceed 0.030 inch (measured at inboard end of tab TE)  Replace worn or defective bearings and/or bushings. Tighten all loose bolts Tighten all hinge fitting bolts and hinge bolts per 27-31-31, Elevator Tabs -Removal/Installation Replace worn or defective rod ends. Tighten bolts and checknuts per 27-31-0, Elevator and Tab Control System -Adjustment/Test Replace worn or defective parts Replace bushings, bearings and/or bolts as necessary 

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27-31-0  Feb 20/87 
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TROUBLE  PROBABLE CAUSE  ISOLATION PROCEDURE  REMEDY 
Moderate vertical vibration in aft and forward fuselage, (Usually above 250 knots indicated airspeed.) (Cont)  Excessive play in elevator surface.  Check elevator free play per 27-31-0, A/T. Difference between elevator up and down positions shall not exceed 0.160 inch (AMM 27-31-11/601, 27-31-191/601) Check for loose connection in the center of the output torque tube where the inner and outer tubes are connected. To determine if connection is loose, observe if there is relative motion between output crank and outer torque tube.  Replace the eight center bolts in the output torque tube with oversize bolts and reduced clearance holes. 

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Feb 20/94  27-31-0 
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TROUBLE  PROBABLE CAUSE  ISOLATION PROCEDURE  REMEDY 
Moderate vertical vibration (Cont)  Excessive play in elevator surface (Cont) Loose or missing vortex generators. Damaged or delaminated tail cone. Loose or missing fairings, doors, seals, etc.  Check for worn or defective bearings, bushing and bolts at each end of elevator pushrod. Check for worn or defective bushings and/or bearings in the output torque tube, lower torque tube, centering unit input rod, neutral shift linkage and mach trim actuator. Check for worn or defective elevator hinge bearings. Check for loose or missing vortex generators. Check for damaged or delaminated tail cone. Check entire airplane for loose, damaged or missing parts.  Replace worn or defective bearings, bushings and bolts. Replace worn or defective bearings and bushings. Replace worn or defective bearings. Repair or replace as required, Replace or replace as required. Repair or replace as required. 

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27-31-0  Jun 20/87 
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TROUBLE  PROBABLE CAUSE  ISOLATION PROCEDURE  REMEDY 
Elevator feel differential hydraulic pressure light illuminates Over-sensitive pitch control in control wheel steering mode (Airplane overreacts to column input)  Hydraulic system A or B return filters clogged Hydraulic system A or B pressure too low or too high Pitot line to system A or system B side of feel computer clogged or leaking Elevator feel computer defective Cable rig load incorrect Excessive friction in cable system  Disassemble filter and check for debris (Ref Chapter 29) NOTE: Clogged hydraulic system return filters can cause illumination of the feel differential hydraulic pressure light by actuation of any hydraulic component Ref Chapter 29, Trouble-Shooting Check rig load on elevator control system Disconnect lower end of pushrods at elevator aft quadrant to power control units and feel and centering unit. If column force exceeds 4 pounds at mid-travel fwd or aft, check that cables clear all structure and do not contact pulley rims  Clean or replace filter, as applicable (Ref Chapter 29) Flush and test pitot lines (Ref 27-31-212, Maintenance Practices and Adjustment/Test)Replace elevator feel computer (Ref 27-31-131, Removal/Installation) Rerig cables (Ref 27-31-0, Adjustment/Test) Adjust as required 
　
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