27-21-00
ALL ú ú 01 Page 521 ú Feb 18/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL
C-C
Rudder Power Control Package Adjustment
Figure 505 (Sheet 2)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
27-21-00
ALL ú ú 01 Page 522 ú Feb 18/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL
2) Disconnect the input rod from the input crank of the rudder ratio changer. 3) Turn the rod end or the knurled adjuster nut.
NOTE: One full turn of the rod end and the knurled
____ adjuster nut together is equivalent to 2.1 inches of travel at the rudder trailing edge. One full turn of the rod end (when the knurled adjuster nut does not move) is equivalent to 1.6 inches of travel at the rudder trailing edge.
4) Connect the input rod to the input crank of the rudder ratio changer with the bolt, washer, and nut.
(e) Small adjustment: 1) Loosen the clamp bolt on the input rod.
NOTE: This is at the rudder ratio changer end of the input
____
rod.
2) Turn the knurled adjuster nut.
NOTE: One full turn of the knurled adjuster nut is
____ equivalent to 0.5 inches of travel at the rudder trailing edge.
CAUTION:_______MAKE SURE THE ROD ENDS ARE ENGAGED CORRECTLY. IF THE ROD ENDS ARE NOT ENGAGED CORRECTLY, THE ROD CAN BREAK.
(f)
Make sure you can see the threads of the rod end through the inspection holes and that no more than 10 threads are visible adjacent to the checknut.
(g)
Tighten the clamp bolt on the input rod to 80-110 pound-inches.
(h)
If procedure 1 was used, push the LSK that is adjacent to END TEST> on the CDU.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
27-21-00
ALL ú ú 01 Page 523 ú Feb 18/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
(i) If procedure 2 was used, slowly release the pressure from the pitot-static system (Ref 34-11-00/201).
S 735-137
(11)
Do these steps to make sure the lower rudder moves to the center position correctly (Fig. 504, and 505).
(a)
Make sure rig pin R-4 is installed in the feel, centering, and trim mechanism.
WARNING:_______ MAKE SURE THAT PERSONS AND EQUIPMENT ARE CLEAR OF ALL
CONTROL SURFACES BEFORE YOU SUPPLY HYDRAULIC POWER. THE
AILERONS, RUDDERS, ELEVATORS, FLAPS, SPOILERS, LANDING
GEAR, AND THRUST REVERSERS CAN MOVE QUICKLY WHEN YOU
SUPPLY HYDRAULIC POWER. THIS CAN CAUSE INJURY TO PERSONS
AND DAMAGE TO EQUIPMENT.
(b)
Supply hydraulic power (Ref 29-11-00/201).
(c)
Find the switches for the FLT CONTROL HYD POWER on the Pilot's Overhead Maintenance Panel, P461. 1) Put the TAIL switches 2 and 4 in the NORM position.
(d)
Make sure the trailing edge of the lower rudder is aligned with the rudder index tab.
NOTE: The rudder is aligned with the rudder index tab if the
____ trailing edge is in the width of the rudder index tab.
1) If the lower rudder is not aligned with the rudder index tab, adjust the power control package for the lower rudder (AMM 27-21-16/501).
(e) Remove hydraulic power (AMM 29-11-00/201).
S 735-138
(12)
Do Procedure 1 or Procedure 2 to extend the servo units for the rudder ratio changers (AMM 27-21-12/501).
S 735-154
(13)
Procedure 1 (airplanes with two SRM's P/N 285U0015-108 or later)
NOTE: This is a procedure which extends the upper and lower
____ rudder ratio changer actuators. Once started, this "ground test" will hold the actuators in the extend position until the operator stops the test. The aileron lockout actuators will lockout during this procedure.
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：747-400 AMM 飞机维护手册 飞行操纵 FLIGHT CONTROLS 2(55)
