27-21-91
ALL ú ú 02 Page 503 ú Nov 15/94
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500
MAINTENANCE MANUAL
TORQUE TUBE
SEE A
STANDBY RUDDER ACTUATOR
RIG PIN R-5
CONTROL UNIT POWER LEVER EXTERNAL SUMMING
ROD VERNIER CONTROL
TORQUE TUBE
FWD
TORQUE TUBE A Rudder Power Control Unit Adjustment Figure 502
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27-21-91
ALL ú ú 02 Page 504 ú Jul 15/91
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
6) Move the FLT CONTROL A and B switches to ON. 7) Turn the sleeve of the vernier control rod until the rudder aligns with the tab. 8) Tighten the two checknuts on the vernier control rod.
NOTE: Make sure the total number of threads that you can
____ see on the sleeve and the rod end is not more than 27 turns.
S 085-006
(5)
Remove the rig pin R-5.
S 725-007
(6)
Do the functional test of the rudder PCU.
S 415-008
(7)
Install the access panels 9512 and 9514.
TASK 27-21-91-725-009
3. Rudder Power Control Unit Functional Test
_________________________________________
A. References
(1)
22-12-00/501, Yaw Damper System
(2)
27-21-00/201, Rudder Control System
(3)
32-00-01/201, Ground Lock Assemblies
B.
Access
(1)
Location Zone
101, 102 Control Cabin
706 Vertical Stabilizer
C.
Prepare for the Functional Test
S 485-010
(1) Install the lockout pin for the nose gear steering
(AMM 32-00-01/201).
NOTE: It is not necessary to disconnect the steering if the
____ airplane is on jacks and the nose landing gear is fully extended.
S 865-011
(2)
Supply hydraulic power system A and B to the rudder system. (AMM 27-21-00/201).
(3)
Make sure there are no leaks at the hydraulic lines on the PCU.
(4)
Set the rudder trim to zero units of trim (Fig. 503).
S 795-012
S 865-013
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27-21-91
ALL ú ú 01 Page 505 ú Jul 15/98
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
RUDDER TRIM
INDICATOR
PEDAL ASSEMBLY
SEE A
FORWARD RIG PIN HOLE (R-3 ON THE CAPTAIN'S QUADRANT R-4 ON THE FIRST OFFICER'S QUADRANT)
ADJUSTMENT
AFT RIG PIN CRANK FOR THE
HOLE (R-3) RUDDER PEDALS
FORWARD QUADRANT
ADJUSTMENT BUSROD (TO THESHAFT
FIRST OFFICER'S PEDALS)
CAPTAIN'S RUDDER PEDALS
PUSHROD TO THE NOSE WHEEL STEERING
RIG PIN HOLE
(R-1 ON THE CAPTAIN'S PEDAL ARM,
BRAKE R-2 ON THE FIRST OFFICER'S PEDAL ARM) 中国航空网 www.aero.cn 航空翻译 www.aviation.cn 本文链接地址:737-300 400 500 AMM 飞机维护手册 飞行操纵 FLIGHT CONTROLS 2(75)