EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
22-13-01
ALL ú ú 01 Page 408 ú Feb 18/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 747-400 MAINTENANCE MANUAL
(4) S 864-066Put the FLT CONTROL HYD POWER WING 1, 2, 3,AND 4 switches to the NORM position. The switches are on the Pilot's Overhead Maintenance Panel (P461).
(5) S 864-047Make sure the flaps are at the zero detent position.
(6) S 864-067Set the aileron trim to the center position: (a) Operate the aileron trim switches until the rig pin A/S-2 can go into the rig-hole freely.
NOTE:____ For the rig-hole position, refer to Fig. 401.
(b) Remove the rig pin.
(7) S 744-068Do this task: Ground Test - XDUCER OUTPUTS (Ref 22-10-00/501).
NOTE:____ Only do a check on the aileron surface position.
(a) (b) Monitor the center aileron surface position display value.Make sure that the display value is between -0.1 and +0.1 degree.
(8) S 834-069Adjust the LAS as follows if it is necessary: (a) Adjust the length of the control rod from the autopilot actuator to the trim and feel mechanism (Ref 27-11-08/201) until the center display value is between -0.1 and +0.1 degree.
(9) S 744-070Do this task: Ground Test - Aileron Servo (Ref 22-10-00/501). (a) Push the LSK that is adjacent to <SERVO-AILERON. (b) Continue with the instructions shown on the CPU until this message shows:
(c) (d) (e) ENGAGE AUTOPILOT L C R TO CMD POSITIONPush the center autopilot CMD button on the Mode Control Panel.Push the LSK that is adjacent to <CONTINUE.Make sure that these fault messages show:
(f) ENGAGE FAIL RIGHT ENGAGE FAIL LEFTContinue with the instructions on the CPU to complete the test.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
22-13-01
ALL ú ú 03 Page 409 ú Jun 10/93
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
(g) Make sure that the SERVO-AILERON test is completed with no failure for the center channel.
NOTE: An autopilot disconnect warning will occur at the end of
____ the test, which is permitted.
(h) Push the captain's or first officer's autopilot disconnect switch two times.
S 864-052
(10) Remove the hydraulic pressure from hydraulic systems 1, 2, 3, and 4 (Ref 29-11-00/201)
(a) Open the following circuit breakers and attach DO-NOT-CLOSE identifiers: 1) P180 DC Power Distribution Panel
a) 180E6, LATERAL CONT VLV SYS 2 b) 180E21, LATERAL CONT VLV SYS 4 c) 180H7, LATERAL CONT VLV SYS 1 d) 180H22, LATERAL CONT VLV SYS 3
S 864-053
(11)
Put the FLT CONTROL HYD POWER WING 1, 2, 3, and 4 switches to the SHUTOFF postion. The switches are on the Pilot's Overhead Maintenance Panel (P461).
S 794-051
(12)
Make a visual inspection of the LAS to make sure there are no hydraulic leaks.
I. Put the airplane back to its initial condition.
S 864-072
(1)
Close these circuit breakers and remove the DO-NOT-CLOSE tags.
(a) P180 DC Power Distribution Panel
1) 180E6, LATERAL CONT VLV SYS 2
2) 180E21, LATERAL CONT VLV SYS 4
3) 180H7, LATERAL CONT VLV SYS 1
4) 180H22, LATERAL CONT VLV SYS 3
(2)
Remove electrical power if it is not necessary (Ref 24-22-00/201).
S 864-055
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
22-13-01
ALL ú ú 03 Page 410 ú Feb 18/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
LATERAL AUTOPILOT SERVO MECHANICAL LINKAGE - INSPECTION/CHECK
_____________________________________________________________
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 空调 AUTO FLIGHT(113)
