(c)
Remove foot pressure on pedals to return rudders to neutral.
(d)
Remove systems No. 1 and 3, or 2 and 4 hydraulic power.
(2)
Rudder Trim Switch Control
(a)
Provide systems No. 1 and 3 hydraulic power for upper rudder and systems No. 2 and 4 hydraulic power for lower rudder.
(b)
Turn trim switch right for right rudder; turn trim switch left for left rudder.
(c)
Rudder stops moving when trim switch is release.
(d)
Operate trim switch to move rudder to neutral.
(e)
Remove systems No. 1 and 3, or 2 and 4 hydraulic power.
(3)
Autoflight Operation
(a)
Refer to 22-13-00/001 for rudder control in autoflight mode.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
27-21-00
ALL ú ú 02 Page 13 ú Jun 10/93
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
RUDDER AND RUDDER TRIM CONTROL SYSTEM - ADJUSTMENT/TEST
_______________________________________________________
1. General_______
A. This procedure gives the instructions to do these tasks:
-An operational test of the rudder system
-A rudder ratio changer existing faults check
-An adjustment of the rudder system
-
A system test of the rudder system.
The adjustment and test of the rudder position indicator and the rudder
position transmitter are in 27-28-00/501.
B.
The airplane can not be on jacks when you do these procedures. A jack at the tail jack point III is permitted if the load on it is less than 2000 pounds.
TASK 27-21-00-715-001
2. Rudder and Rudder Trim Control System Operational Test______________________________________________________
A. General
CAUTION:_______MOVE THE RUDDER PEDALS SMOOTHLY AND SLOWLY. THE MINIMUM TIME TO MOVE THE RUDDERS TO THE FULL TRAVEL POSITION FROM THE CENTER POSITION IS 2 SECONDS. THE MINIMUM TIME TO MOVE RUDDERS FROM THE CENTER POSITION TO THE FULL TRAVEL POSITION AND BACK TO THE CENTER POSITION IS 4 SECONDS. THE MINIMUM TIME TO MOVE THE RUDDERS THROUGH A FULL CYCLE IS 8 SECONDS. YOU CAN CAUSE DAMAGE TO POWER CONTROL PACKAGES IF YOU MOVE THE RUDDER PEDALS TOO FAST.
(1)
Obey this caution during all of this task.
B.
Special Tools and Equipment
(1)
2MIT65B04011-41, Nose Gear Rig and Tow Safety Pin
(referred to as the TOW PIN)
C.
References
(1)
AMM 09-11-00/201, Towing
(2)
AMM 24-22-00/201, Manual Control
(3)
AMM 29-11-00/201, Main Hydraulic Supply System
(4)
AMM 31-61-00/201, Integrated Display System
D.
Access
(1)
Location Zone
221-222 Control Cabin
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
27-21-00
ALL ú ú 02 Page 501 ú Feb 18/02
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
E. Prepare for the Test
S 495-002
WARNING:_______MAKE SURE THE NOSE LANDING GEAR IS POINTED FORWARD. IF THE TIRES ARE NOT PARALLEL WITH THE AIRPLANE, THEY CAN TURN QUICKLY WHEN YOU REMOVE THE TOW PIN. THIS CAN CAUSE INJURY TO PERSONS AND DAMAGE TO EQUIPMENT.
(1) Install the TOW PIN at the steering metering valve for the nose landing gear (AMM 09-11-00/201).
NOTE: You do this to make sure the nose landing gear does not turn.
____
S 495-121
(2)
Install the rig pin, E-1, at the bottom of the captain's control column (Fig. 501).
S 865-003
(3)
Supply electrical power to the AC buses (AMM 24-22-00/201).
S 865-004
(4)
Make sure that the EICAS is serviceable (AMM 31-61-00/201).
S 865-005
(5)
Find the switches for the FLT CONTROL HYD POWER on the Pilot's Overhead Maintenance Panel, P461.
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：747-400 AMM 飛機維護手冊 飛行操縱 FLIGHT CONTROLS 2(46)
