(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.
500
Aug 01/95 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-21-0 Page 507
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.
(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.
500
27-21-0 Page 508 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 15/73
G06857 G06880F53060
500 Rudder Forward Quadrant Adjustment
May 15/68 Figure 503 27-21-0
Page 509
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
Rudder Aft Control Mechanism Adjustment 527
27-21-0 Figure 504 (Sheet 1) May 01/76
Page 510
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
500 Rudder Aft Control Mechanism Adjustment
Feb 01/96 Figure 504 (Sheet 2) 27-21-0
Page 511
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(6) Adjust rudder trim control cables RTA and RTB.
(a)
Check that rudder hydraulic systems A, B, and standby are removed. See step (1).
(b)
Disconnect feel and centering unit input rod from torque tube crank. Move rod to one side and secure (Fig.504).
(c)
Set indicating arrow on rudder trim knob at zero units of trim and hold in that position, with forward cable drum in neutral position per step (5).
(d)
If new cables are installed:
1) Tighten RTA and RTB cables to 100 士10 pounds tension to prestretch cables using turnbuckles located in stabilizer jackscrew compartment. Tighten turnbuckles on each cable an equal amount. If turnbuckle travel is inadequate for complete adjustment, further adjustment is possible by using turnbuckles located in ceiling of forward cargo compartment at fuselage station 451.
2) (Applicable to new cable installations only. Check that rigging pin R-5 can be installed freely without binding. If adjustment is required, adjust RTA and RTB turnbuckles in opposite direction, maintaining cable tension specified in step (d), until rigging pin can be installed freely.
3) Cycle the system 10 times through full travel. Then reduce cable tension to load specified in table 2, Fig. 501 by adjusting turnbuckles on RTA and RTB cables an equal amount.
(e)
Operate rudder trim knob through one full travel cycle and check cable tension per table 2, Fig. 501. If necessary, readjust cable tension and repeat.
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 1(111)
