(b)
Turn tube until index marks align. One full turn at tube moves index mark
approximately 0.006 inch.
(c)
Tighten both checknuts.
(d)
Proceed to step (8).
(7)
Adjust control rod (coarse adjustment) as follows:
(a)
Position flight control switches A and B to OFF.
CAUTION: HYDRAULIC POWER MUST BE OFF FOR THIS PROCEDURE.
(b)
Loosen both checknuts on rod assembly.
(c)
Remove bolt connecting aft end of rod to actuator.
(d)
Turn aft rod end and tube together and/or aft rod end alone in the same direction. Half a turn of one rod end moves index mark approximately 0.015 inch.
(e)
Install clevis bolt at aft end of rod.
(f)
Position flight control switches A and B to ON.
(g)
Repeat fine adjustment starting at step (2).
(8)
Check for minimum thread engagement on rod. Rod end threads must be visible through inspection holes in tube at both ends.
(9)
Remove rigging pin R-5.
501
27-21-72 Page 504 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 15/73
500
Feb 15/73 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-21-72 Page 505
3. Rudder Control Torque Tube Test
A. Test rudder travel.
(1)
Set rudder trim knob to neutral.
(2)
Disconnect pushrod to nose wheel steering. (See figure 503.)
NOTE: Nose gear steering need not be disconnected if airplane is jacked so that nose gear is fully extended.
(3)
Check that rudder hydraulic systems A and B power is provided. Refer to 27-21-0. Position flight control switch A to ON and flight control switch B to OFF.
(4)
Move captain's left pedal until forward quadrant stop is contacted. Measure rudder travel. Required movement is 21.82 (+ 0.80) inches. (See figure 501.)
(5)
Move captain's right pedal until forward quadrant stop is contacted. Measure rudder travel. Required movement is 21.82 (+ 0.80) inches.
(6)
Repeat steps (4) and (5) under following conditions:
(a)
Flight control switch A OFF and flight control switch B ON.
(b)
Flight control switch A OFF and flight control switch B in STDBY RUD position.
(7)
Restore airplane to normal hydraulic configuration. Refer to 27-21-0.
(8)
Reconnect pushrod to nose wheel steering, if disconnected.
(9)
Close all access doors and install panels.
501
27-21-72 Page 506 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 15/73
G13691
500 Rudder Forward Quadrant Installation
Feb 15/73 Figure 503 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-21-72 Page 507
RUDDER CONTROL TORQUE TUBE - INSPECTION/CHECK
EFFECTIVITY
AIRPLANES PRE-SB 27-1252
1. General
A. This data consists of illustrations and wear limits charts. There wil1 be no procedure given in this section for gaining access to, or removing and replacing the component after inspection for wear. Refer to component removal/installation for this information.
2. Rudder Control Torque Tube Wear Limits (See figure 601.)
May 01/03 27-21-72 Page 601
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
G53165
Rudder Control Torque Tube Wear Limits 501
27-21-72 Figure 601 Aug 15/69
Page 602
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
RUDDER CONTROL TORQUE TUBE - REMOVAL/INSTALLATION
EFFECTIVITY
AIRPLANES POST-SB 27-1252
1. General
A. This procedure contains the removal and the installation tasks for the rudder control torque tube.
B. The rudder control torque tube is referred to as the "torque tube" in this procedure.
2. Equipment and Materials
A. Corrosion Preventive Compound -MIL-C-11796, Class 3
B. Grease - BMS 3-24
3. Prepare for Removal
A. Remove rudder systems A, B, and standby hydraulic power (AMM 27-21-0/201).
B. Remove access panels 9512, 9515, and 9514 (AMM 12-31-51/201).
4. Torque Tube Removal (Fig. 401)
A. Remove the nuts, washers, and bolts to disconnect the standby PCU control rod and main PCU control rods from the upper crank and center cranks.
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