(n)
Install turnbuckle locking clips and apply a thin coat of grease to exposed threads.
(o)
Check for thread engagement on four tension rods and one bus rod. End of rod (10 places) must cover part of inspection hole.
(8)
Deleted.
(9)
Adjust input to rudder power control unit.
(a)
Provide rudder hydraulic systems A and B power (Ref 27-21-0).
CAUTION: PERSONNEL SHOULD STAND CLEAR OF ALL FLIGHT CONTROL SURFACES WHEN HYDRAULIC POWER IS APPLIED.
(b)
Check that rudder trim is set at zero units of trim.
(c)
Jiggle feel and centering unit input rod to ensure that system is centered.
(d)
Insert rigging pin R-5 in fell and centering unit output crank. Rigging pin shall enter easily without movement of arm output crank.
(e)
Measure rudder trailing edge deviation from neutral. (Rudder neutral position is defined as the position at which both sides of rudder trailing edge are within width of tab on rudder index plate.) 1) If rudder is at neutral, proceed to step (h). 2) If rudder trailing edge is outside of index tab, but less than 0.50 inch from
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27-21-0 Page 514A
nearest side of tab proceed to step (f). 3) If rudder trailing edge is more than 0.50 inch from nearest side of index tab proceed to step (g).
501
27-21-0 Page 514B BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. May 01/76
Figure 505
Deleted
526
Aug 15/69 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-21-0 Page 515
(f)
Adjust vernier control rod (fine adjustment) as follows: 1) Loosen both checknuts on rod assembly. 2) Turn adjustable sleeve to obtain rudder neutral position. (See step (e).) 3) Tighten both checknuts. 4) Proceed to step (h).
(g)
Adjust vernier control rod (coarse adjustment) as follows: 1) Position flight control switches A and B on forward overhead panel to OFF.
CAUTION: RUDDER POWER MUST BE OFF BEFORE DISCONNECTING VERNIER CONTROL ROD FROM ACTUATOR INPUT CRANK.
2) Loosen both checknuts on rod assembly.
3) Remove clevis bolt connecting forward end of rod to input crank on torque tube.
4) Adjust by turning sleeve and rod end together relative to tube, and rod end
relative to sleeve an equal number of turns in the same direction, keeping number of threads exposed approximately equal in both parts. The sum of one-half turn of each is equivalent to 1/2 inch approximately at rudder trailing edge. Lengthen rod for right rudder and shorten for left rudder.
5) Install clevis bolt connecting rod to input crank as follows: a) Position clevis of rod over lug on input crank. b) Install bolt assembly with washer under bolt head through clevis and
tongue. Tighten nut on outer bolt to 50-65 pound-inches. c) Install locknut with washer over end of inner bolt and tighten nut to 12-15 pound-inches.
CAUTION: AFTER TIGHTENING NUT ON INNER BOLT, DO NOT RESET TORQUE FOR NUT ON OUTER BOLT. NUT ON INNER BOLT MAY BECOME LOOSE.
500
27-21-0 Page 516 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 15/73
G06913
501 Rudder Travel and Index Plate
Nov 01/74 Figure 506 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-21-0 Page 517
6) Position flight control switches A and B to ON.
7) Repeat fine adjustment starting with step (b).
(h)
Check that combined total number of threads visible beyond checknuts on clevis and sleeve does not exceed 27.
(i)
Remove rigging pin R-5.
(10) Adjust input to standby rudder actuator.
NOTE: This procedure assumes that main rudder power control unit is correctly adjusted.
(a)
Provide rudder systems A and B hydraulic power (Ref 27-21-0).
WARNING: PERSONNEL SHOULD STAND CLEAR OF ALL FLIGHT CONTROL SURFACES WHEN HYDRAULIC POWER IS APPLIED.
(b)
Check that rudder trim is set at zero units of trim.
(c)
Jiggle feel and centering unit input rod to ensure that system is centered.
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