S 864-085
(6)
Put the FLT CONTROL HYD POWER - TAIL switches No. 1, 2, 3, and 4 on P461, Pilot's Overhead Maintenance Panel in the NORM position.
S 094-086
WARNING:_______MAKE SURE THE NOSE WHEELS POINT FORWARD. IF THE NOSE WHEELS DO NOT POINT FORWARD, THE NOSE GEAR CAN QUICKLY TURN TO THE CENTERED POSITION WHEN YOU REMOVE THE TOW PIN. THIS CAN CAUSE INJURY TO PERSONS AND DAMAGE TO EQUIPMENT.
(7) Remove the TOW PIN from the nose landing gear (AMM 09-11-00/201).
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A
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MAINTENANCE MANUAL
UPPER RUDDER POWER CONTROL ACTUATOR - ADJUSTMENT/TEST
_____________________________________________________
1. General_______
A. There are two tasks in this procedure. There is an adjustment and an operational test of the upper rudder power control actuators (PCAs).
B. The airplane must be off of jacks when you do the adjustment of the power control actuators. A jack at the jack point III of the tail is permitted if the load on it is less than 2000 pounds.
TASK 27-21-15-835-001
2. Upper Rudder Power Control Actuator Adjustment (Fig. 501)______________________________________________
A. References
(1)
09-11-00/201, Towing
(2)
24-22-00/201, Manual Control
(3)
29-11-00/201, Main Hydraulic Supply System
(4)
31-61-00/201, Integrated Display System
B.
Access
(1)
Location Zone
324 Vertical Fin, Rear Spar to Trailing Edge
326 Upper Rudder
(2)
Access Panel
324UL Inspection Access Door
C.
Prepare for the Adjustment
S 495-029
WARNING:_______MAKE SURE THE NOSE WHEELS POINT FORWARD. IF THE NOSE WHEELS DO NOT POINT FORWARD, THE NOSE GEAR CAN QUICKLY TURN TO THE CENTERED POSITION 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 (Ref 09-11-00/201).
NOTE: The nose gear will turn during the rudder operation if you do
____
not install the TOW PIN.
S 865-003
(2)
Supply the electrical power (Ref 24-22-00/201).
(3)
Make sure the EICAS is serviceable (Ref 31-61-00/201).
(4)
Open the access panel 324UL to get access to the upper rudder PCAs.
S 865-004
S 015-005
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747-400
MAINTENANCE MANUAL
RUDDER CONTROL MECHANISM SEE A
RIG PIN E-2 SEE B
A A
POWER CONTROL
ACTUATOR FOR THE
UPPER RUDDER
UPPER RUDDER
RATIO CHANGER
INPUT ROD INPUT ROD FOR THEFOR THE POWER CONTROL MODULERUDDER RATIO CHANGER
POWER CONTROL RIG PIN ACTUATOR FOR THE R-4 UPPER RUDDER
FEEL, CENTERING AND TRIM MECHANISM
RUDDER CONTROL MECHANISM A Upper Rudder Power Control Package AdjustmentFigure 501 (Sheet 1)
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A
747-400
MAINTENANCE MANUAL
AUTOPILOT SERVO MODULES FOR THE ELEVATOR (3 LOCATIONS)
ELEVATOR AFT QUADRANT TORQUE TUBE
RIG PIN
E-2
RIG PIN E-2
TRAILING EDGE OF THE LOWER RUDDER
B
0.12 INCH (WIDTH OF THE INDEX GROOVE)
0.24 INCH (WIDTH OF THE INDEX TAB)
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本文鏈接地址：747-400 AMM 飛機維護手冊 飛行操縱 FLIGHT CONTROLS 2(136)
