(f)
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.
(g)
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.
(h)
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.
(i)
If either or both rigging pins R-1 and R-2 cannot be inserted freely in pedal arms, proceed as follows:
500
May 01/03 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-21-1 Page 513
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.
(j)
Remove rigging pins R-1, R-2, R-3, R-4, and R-5.
(k)
Operate rudder pedals through one full travel cycle and check cable loads again.
(l)
Adjust pressure seals at aft pressure bulkhead to align with RA and RB cables. Adjust by loosening seal retainer bolts and positioning seal (AMM 27-09-121 and 27-10-101).
(m)
Install turnbuckle locking clips and apply a thin coat of grease to exposed threads.
(n)
Check for thread engagement on four tension rods and one bus rod. End of rod (10 places) must cover part of inspection hole.
500
May 01/03 B
O
E
I
NG
P
R
OP
R
I
E
T
A
R
Y
- Copyri
ght
. - Unpubl
i
s
hed
W
o
r
k
-
S
ee
t
i
t
l
e page f
o
r de
t
a
i
l
s
.
27-21-1 Page 514
(8) Adjust the input rods to the rudder power control unit.
(a)
Open this circuit breaker on the P6 panel and attach a DO-NOT-CLOSE tag: 1) FORCE FIGHT MON
WARNING: RUDDER, ELEVATOR, AND AILERONS ARE FULLY POWERED SYSTEMS. ALL THREE SYSTEMS ARE POWERED SIMULTANEOUSLY. CHECK TO ENSURE THAT PERSONNEL AND OBSTRUCTIONS ARE CLEAR OF ALL CONTROL SURFACES BEFORE TURNING POWER ON.
(b)
Provide rudder hydraulic systems A and B power (AMM 27-21-0/201).
(c)
Set the FLT CONTROL B switch to ON and A switch to OFF.
(d)
Make sure the YAW DAMPER switch on the P5-3 panel is in the OFF position and the YAW DAMPER light is illuminated.
(e)
Check that rudder trim is set at zero units of trim.
(f)
Jiggle the feel and centering unit input rod to ensure that system is centered.
(g)
Insert rig pin R-5 in the feel and centering unit output crank (Fig. 504).
1) Make sure you can install the rig pin freely without movement of the arm output crank.
(h)
Open this circuit breaker on the P6 panel and attach a DO-NOT-CLOSE tag: 1) FLIGHT CONTROL TRIM CONT RUD
(i)
Remove the rig pin R-5.
(j)
Do these steps to the lower control rod to put the rudder trailing edge to the left of the index plate:
NOTE: Always start the adjustment of the control rod with the rudder at this position.
1) Loosen the clamp nut on the lower control rod until you can rotate the sleeve.
2) Rotate the sleeve until the rudder trailing edge is between 0.20 to 0.30 inch (5.1 to 7.6 millimeters) to the left of the index plate.
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737 AMM 飛機維護手冊 飛行操縱 FLIGHT CONTROLS 2(10)
