G08305
Rudder Forward Quadrant Installation 500
27-21-91Page 506 Figure 503 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 15/73
C. Test Rudder Travel (Fig. 501)
(1)
Position flight control switch B to OFF, leave flight control switch A in ON position.
(2)
Move captain's left pedal until forward quadrant stop is contacted. Measure rudder travel. Check that rudder travel is 21.82 +0.80 inches.
(3)
Move captain's right pedal until forward quadrant stop is contacted. Measure rudder travel. Check that rudder travel is 21.82 +0.80 inches.
(4)
Position flight control switch A to OFF, and flight control switch B to ON.
(5)
Repeat steps (2) and (3).
D. Do a test of the secondary slide on the dual servo valve of the rudder power control unit:
(1)
Supply the rudder hydraulic power systems A and B (Ref 27-21-0/201).
(2)
Slowly push the captain's left pedal forward until it touches the stop then release.
(3)
As fast as possible, push the captain's right pedal forward. The right pedal should move smoothly forward until it touches the stop.
(a) If the right pedal moves in the opposite direction of the applied force, replace the rudder power control unit (Ref 27-21-91/401).
(4)
Release the right pedal.
(5)
Slowly push the captain's right pedal forward until it touches the stop then release.
(6)
As fast as possible, push the captain's left pedal forward. The left pedal should move smoothly forward until it touches the stop.
(a) If the left pedal moves in the opposite direction of the applied force, replace the rudder power control unit (Ref 27-21-91/401).
(7)
Release the left pedal.
(8)
Slowly push the first officer's left pedal forward until it touches the stop then release.
(9)
As fast as possible, push the first officer's right pedal forward. The right pedal should move smoothly forward until it touches the stop.
(a) If the right pedal moves in the opposite direction of the applied force, replace the rudder power control unit (Ref 27-21-91/401).
(10)
Release the right pedal.
(11)
Slowly push the first officer's right pedal forward until it touches the stop then release.
(12)
As fast as possible, push the first officer's left pedal forward. The left pedal should move smoothly forward until it touches the stop.
(a) If the left pedal moves in the opposite direction of the applied force, replace the rudder power control unit (Ref 27-21-91/401).
(13)
Release the left pedal.
E. Restore airplane to normal.
(1)
Remove rudder systems A and B hydraulic power (Ref 27-21-0).
(2)
Connect pushrod to nose wheel steering, if disconnected.
(3)
Close access doors and install access panels.
501
Apr 01/97 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-21-91 Page 507
RUDDER POWER CONTROL UNIT - INSPECTION/CHECK
EFFECTIVITY
AIRPLANES PRE-SB 27-1252
1. General
A. This data consists of illustrations and wear limits charts. There will be no procedure given in this section for gaining access to, or removing and replacing the component after inspection for wear. Refer to component removal/installation for this information.
2. Rudder Power Control Unit Wear Limits
G08343
503 Rudder Power Control Unit Wear Limits
May 01/03 Figure 601 (Sheet 1) 27-21-91
Page 601
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
G08356 G44606
Rudder Power Control Unit Wear Limits 500
27-21-91 Page 602 Figure 601 (Sheet 2) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. May 15/68
501 Rudder Power Control Unit Wear Limits
May 01/76 Figure 601 (Sheet 3) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-21-91 Page 603
RUDDER POWER CONTROL UNIT - REMOVAL/INSTALLATION
EFFECTIVITY
AIRPLANES POST-SB 27-1252
1. General
A. The rudder power control unit (PCU) is located in the lower area of the vertical fin (Fig. 401).
B. Replaceable components of the rudder power control unit include three solenoid valves, two transfer valves, two position transducers and four filters.
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(38)
