NOTE: If rudder trim is adjusted with the power control unit depressurized, the drag of the unpowered rudder system will allow the system to remain out of center. This will force the rudder feel and centering mechanism cam follower out of the cam detent. Then when hydraulic power is applied, the rudder trim control knob and rudder will rapidly move to the newly trimmed position.
(2)
The rudder trim system is rigged by adjusting components to neutral position, and synchronizing adjustments from forward to aft. One tail section rigging pin, common to the rudder control system, is needed to adjust the system.
CAUTION: 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.
(3)
If an out-of-trim condition exists (Ref 27-09-400, Adjustment/Test).
(4)
The rudder and rudder trim control system is properly adjusted when the individual components are adjusted to meet the following conditions: (See Fig. 501 for rigging pin locations and cable tension requirements.)
(a) Rudder Forward Quadrants
1) With rudder pedals positioned to neutral with pedal adjustment crank, and using trim knob, and with rigging pin R-5 installed through feel and centering unit output crank, rudder forward quadrants shall be positioned so that rigging pins R-3 and R-4 fit through forward rigging pin holes in quadrants. If not, quadrants may be adjusted per par. 1.C.(2).
May 01/03 27-21-0 Page 501
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
G07257
Rudder Control System Adjustment 526
27-21-0 Figure 501 Aug 15/69
Page 502
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(b)
Rudder Pedals
1) With rigging pins R-3 and R-4 in place, rigging pins R-1 and R-2 shall fit through rigging pin holes on pedal arm assembly. If both pins cannot be installed, tension rods and cables may be adjusted per paragraph 1.C.(3).
(c)
Rudder Trim Actuator
1) With rigging pin R-5 installed (system should be centered and rigging pin should fit freely), cotter pin hole on right side of actuator shall fall within paint mark on housing. Dimension from upper end of actuator drum extension to end of actuator screw shall be 1.92 (+0.03/-0.02) inches. If either of these conditions is not met, actuator may be adjusted per paragraph 1.C.(4).
(d)
Forward Rudder Trim Cable Drum
1) With rigging pin R-5 installed (system should be centered and rigging pin should fit freely), forward rudder trim cable drum shall be in neutral per detail A, figure
503. If not, cables may be adjusted per paragraph 1.C.(5).
(e)
Rudder Trim Control Cables RTA and RTB
1) With rigging pin R-5 installed (system should be centered and rigging pin should fit freely), tension in cables RTA and RTB shall be within limits of value for ambient temperature given in table 2, figure 501. If not, tension may be adjusted per paragraph 1.C.(6).
(f)
Rudder Control Cables RA and RB
1) With rigging pins R-3, R-4, and R-5 installed (system should be centered and rigging pin should fit freely), tension in cables RA and RB shall be within limits of value for ambient temperature given in table 1, figure 501. If not, tension may be adjusted per paragraph 1.C.(7).
(g)
Rudder Power Control Unit
1) With rigging pin R-5 installed and rudder hydraulic system pressurized, rudder trailing edge shall fall within rudder index tab (Fig. 506). If either side of trailing edge falls outside width of index tab, power control unit may be adjusted per par. 1.C.(9).
(h)
Standby Rudder Actuator
526
Feb 15/72 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-21-0 Page 503
1) With rigging pin R-5 installed, and rudder hydraulic system pressurized, index marks on standby rudder actuator valve input crank and actuator body shall align (Detail B, Fig. 504). If index marks are not aligned, actuator may be adjusted per par. 1.C.(10).
B. Equipment and Materials
(1)
Rigging Pins Kit - F70207-3, -52, -61, or -84:
(2)
Cable Tensiometer - 0 to 300 pounds range for 1/8-inch diameter cable
中國航空網(wǎng) www.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 飛行操縱 FLIGHT CONTROLS 1(109)
