(f)  
Set indicating arrow on rudder trim knob at zero units of trim and hold in that position.

(g)  
Check that rigging pin R-5 can be installed freely without binding. If correction is required adjust RTA and RTB turnbuckles in opposite direction, maintaining cable tension specified, until rigging pin can be installed freely. Also check that cotter pin hole on trim actuator is in center of paint mark on actuator drum.

(h)  
Remove rigging pin R-5.

(i)  
Adjust pressure seal at aft pressure bulkhead to align with RTA and RTB cables. Adjust by loosening seal retainer bolts and position seal properly (Ref 27-09-121 and 20-10-101).

(j)  
Install turnbuckle locking clips, and apply a thin coating of corrosive preventive material to exposed threads.

(k)  
Connect input rod between feel and centering unit and torque tube. Install bolts, washer, and nuts. Tighten nut on outer bolt to 50-60 pound-inches, then tighten nut on inner bolt to 12-15 pound-inches.

500 
27-21-0 Page 512  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Nov 15/80 

CAUTION:  AFTER TIGHTENING NUT ON INNER BOLT, DO NOT RESET TORQUE FOR NUT ON OUTER BOLT. NUT ON INNER BOLT MAY BECOME LOOSE.
(7)  Adjust rudder control cables RA and RB.
(a)  
Check that hydraulic systems A, B, and standby power are removed (Ref step (1)).

(b)  
Check that rudder trim knob is set at zero units of trim and cycle rudder pedals per par. 2.C. to check for full pedal travel.

(c)  
When installing new forward quadrant busrod, shorten busrod by turning rod end two full turns. Connect busrod by installing bolt with spacers, washers, nut, and cotter pin.

(d)  
If new cables are installed:

1)  Attach RA and RB cables to forward quadrants, then attach cables to aft quadrant and install rigging pin R-5 in feel and centering unit output crank.
2)  Adjust turnbuckles on RA and RB cables to 260 士20 pounds cable tension to prestretch cables. Keep adjustment on both sides of cables equal by checking that rigging pin R-3 can be inserted in captain's forward quadrant.
501 
Nov 15/80  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-21-0 Page 513 

3)  Remove rigging pins R-3 and R-5.
4)  Check that cables do not contact pulley or quadrant flanges for total cable travel, that cables lie within 2 degrees of plane of pulley or quadrant, that cables are installed through grommets in structure as required, that cables are not deflected by fairleads, rub strips or grommets from rigged or normal operating position, and that pulleys rotate freely with no interference with guards.
5)  Cycle rudder pedals 25 times through full stroke.
(e)  
Install rigging pin R-5 in feel and centering unit output crank.

(f) 
 Deleted.

(g)  
Adjust cable tension to value shown in table 1, Fig. 501, using turnbuckles. Check that rigging pins R-3 and R-4 can be installed freely in forward quadrants.

(h)  
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 busrod. 3) Adjust busrod as required and install bolt with spacers, washers, nut, and cotter

pin. 4) Adjust cable tension to valve shown in table 1, Fig. 501, using turnbuckles. Check that rigging pins R-3 and R-4 can be installed freely in forward quadrants.

(i)  
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.

(j)  
If either or both rigging pins R-1 and R-2 cannot be inserted freely in pedal arms, proceed as follows:

501 
27-21-0 Page 514  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Nov 15/80 

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) Loosen 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.
(k)  
Remove rigging pins R-1, R-2, R-3, R-4, and R-5.

(l)  
Operate rudder pedals through one full travel cycle and check cable loads again.

(m)
Adjust pressure seals at aft pressure bulkhead to align with RA and RB cables. Adjust by loosening seal retainer bolts and positioning seal (Ref 27-09-121 and 27-10-101).
　
中國(guó)航空網(wǎng) m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737 AMM 飛機(jī)維護(hù)手冊(cè) 飛行操縱 FLIGHT CONTROLS 1(112)