B.
References
(1)
AMM 09-11-00/201, Towing
(2)
AMM 24-22-00/201, Manual Control
C.
Access
(1)
Location Zone
324 Vertical Fin, Rear Spar to Trailing Edge
325 Lower Rudder
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27-21-16
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL
(2)
Access Panel
324DL Inspection Access Panel
324DR Rudder Actuator Access Panel
324HL Inspection Access Panel
324HR Centering Mechanism Access Panel
324UL Inspection Access Panel
324UR Inspection Access Panel
D.
Procedure
S 094-054
(1)
Remove the holding clamp from the trailing edge of the upper and lower rudder.
S 094-055
(2)
Remove the lock and release the left rudder pedal.
S 864-056
(3)
Remove the electrical power (AMM 24-22-00/201).
S 864-057
(4)
Remove the DO-NOT-CLOSE tags and close these circuit breakers:
(a)
P7, Overhead Circuit Breaker Panel
1) 7B11, UPR RUD RATIO AC PWR
2) 7B12, UPR RUD RATIO CONT
3) 7B13, UPR RUD RATIO DC PWR
4) 7B14, LWR RUD RATIO AC PWR
5) 7B15, LWR RUD RATIO CONT
6) 7B16, LWR RUD RATIO DC PWR
7) 7D16, RUD TRIM CONT
(b)
P180, DC Power Distribution Panel
1) 180E7, ELEV/RUD VLV SYS 2
2) 180E22, ELEV/RUD VLV SYS 4
3) 180H8, ELEV/RUD VLV SYS 1
4) 180E23, ELEV/RUD VLV SYS 3
S 414-070
(5)
Close the applicable access panels.
S 864-058
(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 094-065
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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27-21-16
ALL ú ú 01 Page 416 ú Oct 18/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
LOWER 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 power control actuators (PCAs) for the lower rudder.
B. The airplane must be off of jacks when you adjust the power control actuator. A jack at jack point III of the tail is permitted if the load on it is less than 2000 pounds.
TASK 27-21-16-835-001
2. Lower Rudder Power Control Actuator Adjustment (Fig. 501)______________________________________________
A. Special Tools and Equipment
(1)
G12001-50 Rig Pin Kit
B.
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
C.
Access
(1)
Location Zone 324 Vertical Fin, Rear Spar to Trailing Edge 325 Lower Rudder
(2)
Access Panel
324DL Inspection Access Panel
324FL Inspection Access Panel
D.
Prepare for the Adjustment
S 015-002
(1)
Open the access door 315A to get access to the elevator aft quadrant.
S 015-003
(2)
Remove these access panels:
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本文链接地址：747-400 AMM 飞机维护手册 飞行操纵 FLIGHT CONTROLS 2(146)
