(f)
Remove rigging pins R-3 and R-4.
(g)
Position captain's forward quadrant so that rigging pin R-3 can be inserted through aft rigging pin hole in quadrant. Check that maximum gap between quadrant and quadrant stop is 0.06 inch. Add or remove shims as necessary.
(h)
Remove rigging pin R-3. Position first officer's forward quadrant so that rigging pin R-can be inserted through aft rigging pin hole in quadrant. Check gap between quadrant and quadrant stop per step (g).
(3) Adjust rudder pedals.
(a)
Check that rudder hydraulic systems A, B, and standby power are removed
(step (1)).
(b)
Insert rigging pin R-5 and position forward quadrants so that rigging pins R-3 and R-4 may be installed in forward rigging pin holes (Fig. 503).
NOTE: Rudder trim knob may be used to aid in positioning forward quadrants.
(c)
With rigging pins R-3 and R-4 in place, check that rigging pins R-1 and R-2 fit through rigging pin holes on pedal arm assembly. If one or both pins cannot be installed, adjust tension rods by loosening jamnuts on one or both ends of rod assembly and rotating tube to obtain desired length.
NOTE: Nominal tension rod dimension is 36.50 inches.
(d)
When rigging pins fit freely, tighten jamnuts.
(e)
Inspect adjustable rod ends for proper thread engagement. Rod ends must be visible through inspection holes in tubing.
(f)
Remove rigging pins R-1, R-2, R-3, R-4, and R-5.
500
May 01/03 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-21-1 Page 505
W28863
Rudder Pedal Adjustment 500
27-21-1 Figure 502 May 01/03
Page 506
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(4) Adjust rudder trim actuator.
(a)
Check that rudder hydraulic systems A, B, and standby power are removed (step (1)).
(b)
Remove access panels 9509 and 9510 from vertical fin and open door 3701 in aft body section.
(c)
Disconnect feel and centering unit input rod from torque tube crank (Fig. 504).
(d)
Align center of painted index mark on cable drum extension with cotter pin hole on side of actuator housing (installed position) to place rudder trim actuator drum in neutral (Detail A, Fig. 504).
(e)
Check that dimension from bottom of actuator drum extension to end of actuator screw is 1.92 +0.03/-0.02 inches and that rigging pin R-5 can be freely inserted. If not, adjust as follows: 1) Disconnect screw from structure and rotate screw to proper length. 2) Connect screw to structure. If mounting holes do not align with rigging pin R-5
installed, remove bushing from threaded plug and rotate plug until mounting holes align. Maintain 1.92 (+0.03/-0.02)-inch dimension. Replace bushing and install bolt assembly.
NOTE: Actuator drum outer periphery may be rotated 0.50 inch maximum if nearest plug adjustment increment does not align mounting holes. Cotter pin hole on actuator housing must not be off paint index mark on actuator drum at zero trim.
(f)
Check that trim knob is at zero units and that cable tension is correct. If not, adjust per paragraphs (5) and (6).
(g)
Connect input rod between feel and centering unit and torque tube. Tighten nut on outer bolt to 50-60 pound-inches, then tighten nut on inner bolt 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
May 01/03 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-21-1 Page 507
(5) Adjust forward rudder trim cable drum.
(a)
Check that rudder hydraulic systems A, B, and standby power are removed. See step (1).
(b)
Hold trim knob at zero units trim, check that cable is wrapped on forward cable drum as shown in detail A, figure 503. With feel and centering unit input rod disconnected from torque tube crank, check that rigging pin R-5 is easily inserted. If rigging pin R-5 cannot be inserted freely, adjust RTA and RTB cables per paragraph (6).
(c)
Connect input rod between feel and centering unit and torque tube. Tighten nut on outer bolt to 50-60 pound-inches, then tighten nut on inner bolt 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.
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：737 AMM 飞机维护手册 飞行操纵 FLIGHT CONTROLS 2(8)
