M. With rudder pedals in neutral position, connect rudder pedal tension rods. If rod length adjustment is required, loosen jamnuts on both ends of rod assembly and rotate tube to obtain desired length. Retighten jamnuts. Rig pins are to fit freely.
N. Inspect adjustable rod ends for proper thread engagement. Rod ends must be visible through inspection holes in rod assembly.
O. Remove rigging pins R-1, R-2, R-3, and R-4.
P. Remove bolt through one rod end of quadrant bus rod. Shorten bus rod by turning rod end two full turns. Connect bus rod.
Q. Attach rudder cable to forward quadrant.
R. Adjust rudder control cables RA and RB to tension shown in table 1 of figure 402. Tension in cables RA and RB should be balanced. Check that rigging pins R-3 and R-4 can be freely installed in forward quadrants.
S. If both rigging pins cannot be inserted freely when cables have specified tension, proceed as follows:
(1)
Relieve cable tension.
(2)
Remove bolt through one rod end of forward quadrant bus rod.
(3)
Adjust bus rod as required and install bolt with spacers, washers, nut, and cotter pin.
(4)
Adjust cable tension to valve shown in table 1, figure 402, using turnbuckles. Check that rigging pins R-3 and R-4 can be installed freely in forward quadrants.
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Feb 15/72 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-21-51 Page 405
T. With rigging pins R-3, R-4, and R-5 installed, check that rigging pins R-1 and R-2 can be installed freely in pedal arms.
U. If either or both rigging pins R-1 and R-2 cannot be inserted freely in pedal arms, proceed as follows:
NOTE: Steps (1) through (6) may be required on all four tension rods.
(1)
Establish which pedal arm is out-of-line with rigging pin hole.
(2)
Loose n both checknuts on tension rod connected to affected pedal arm.
(3)
Remove bolt through forward tension rod end.
(4)
Adjust tension rod length until rigging pin R-1 or R-2 can be installed freely by turning rod end and/or rod as required, keeping lube fitting on rod end down.
(5)
Install tension rod end with bolt, washer, nut, and cotter pin.
(6)
Tighten checknuts.
V. Remove rigging pins R-1, R-2, R-3, R-4, and R-5.
W. Operate rudder pedals through one full travel cycle and check cable loads again.
X. Install turnbuckle locking clips and apply a thin coat of grease to exposed threads.
Y. Check for thread engagement on four tension rods and one bus rod. End of rod (10 places) must cover part of inspection hole.
Z. Operate pedals through full travel to check for binding and obstruction.
AA. Restore airplane to normal hydraulic configuration. Refer to 27-21-0.
AB. Check rudder travel per 27-21-0, Rudder and Rudder Trim Control System -Adjustment/Test.
AC. Close all access doors and panels.
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G07594 W37316
526 Rudder AFt Control Mechanism Adjustment
May 01/03 Figure 402 (Sheet 1) 27-21-51
Page 407
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
Rudder Aft Control Mechanism Adjustment 500
27-21-51 Figure 402 (Sheet 2) May 01/03
Page 408
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
RUDDER AFT CONTROL QUADRANT - REMOVAL/INSTALLATION
1. Equipment and Materials
A. Rigging Pins Kit - F70207-3, -52, -61, or -84:
REF NO. F70207-( ) DIAMETER (INCHES) LENGTH (INCHES) FUNCTION
R-1 R-3 R-4 R-5 -14 -11 -11 -11 0.309-0.311 0.309-0.311 0.309-0.311 0.309-0.311 12.7 +0.25 6.7 +0.25 6.7 +0.25 6.7 +0.25 CAPTAIN'S RUDDER PEDAL ARM CAPTAIN'S FWD QUADRANT F/O'S FWD QUADRANT FEEL AND CENTERING MECHANISM
B. Cable tensiometer - 0- to 300-pound range for 1/8-diameter cable.
2. Prepare for Removal
A. Remove rudder systems A, B, and standby hydraulic power (Ref 27-21-0 MP).
B. Install rigging pins R-1 and R-5 as shown in Fig. 402.
3. Remove Rudder Aft Control Quadrant
A. Disconnect cables RA and RB at turnbuckles (Fig. 401). Secure disconnected cables.
B. Disconnect cables from rudder aft control quadrant by removing cable retainers. Secure disconnected cables.
C. Disconnect input rod from input crank by removing nut, washers, and bolt.
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