27-11-09
ALL ú ú 01 Page 402 ú Feb 18/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL
(`F) TEMPERATURE 110 (43`C) -40 (-40`C) -30 (-34`C) -10 (-23`C) 10 (-12`C) 30 (-1`C) 40 (4`C) 50 (10`C) 60 (16`C) 70 (21`C) 80 (27`C) 90 (32`C) 1 BODY/WING CABLE CONTROL WHEEL BUS CABLE TABLE 1 101 105 63 67 71 75 115 120 125 130 110 114 123 80 84 93 135 141 153 TENSION IN POUNDS CABLE RIGGING ADJUSTMENT LOADS 28 34 42 50 59110 99 71 79 89 58 64 72 80 89 93 97 2 6 35 4 6 5 4 3 2 1 CONTROL WHEEL CAPTAIN'S AILERON STAND CONTROL PILOTS' IF POSSIBLE, MAKE THE LAST CABLE ADJUSTMENTS WHEN WHEN RIGGING THE SYSTEM, CABLE LOADS SHOULD BE THE SYSTEM MUST BE ADJUSTED WHEN THE CABLE LOADS WHEN RIGGING THE SYSTEM, CABLE LOADS SHOULD BE THE SYSTEM MUST BE ADJUSTED WHEN THE CABLE LOADS AIRFRAME TEMPERATURE IS STABLE (USE A TOLERANCE TO GET THE CORRECT CABLE TENSION, MAKE SURE THE RIGHT BODY CABLES WING CABLES & LEFT BODY CABLES THE TWO ENGINES ARE INSTALLED ON THE WING. |15 LBS FROM THE TABLE VALUES. ARE MORE THAN |20 LBS FROM THE TABLE VALUES. |5 LBS FROM THE TABLE VALUES. ARE MORE THAN |15 LBS FROM THE TABLE VALUES. OF |5`F) FOR A MINIMUM OF 1 HOUR.
RIG PIN A/S-2 MECHANISM TRIM AND FEEL SEE A RIG PIN A/S-1 LOAD LIMITER AILERON CONTROL
STRAIGHTEDGE
CABLES RIGHT BODY
CAPTAIN'S CONTROL WHEEL FIRST OFFICER'S CONTROL WHEEL
A
Aileron System Adjustment
Figure 402
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
27-11-09
ALL ú ú 01 Page 403 ú Oct 10/96
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 747-400 MAINTENANCE MANUAL
(3) S 864-004Manually move the captain's and first officer's control wheels to the neutral position.
(4) S 484-005Install rig pin A/S-2.
NOTE:____ Rig pin A/S-2 must stay in its hole to keep the trim system at the center for the subsequent adjustment.
(a) Make sure rig pin A/S-2 moves freely in its hole. 1) If it is necessary, use the trim system switches and move the control wheel until you can easily install rig pin A/S-2 (Fig. 401).
(5) S 494-021With a clamp, attach the straightedge across the thumbrests of the captain's and first officer's control wheels.
(6) S 864-007Do this task: "Hydraulic System Depressurization" (Ref 29-11-00/201).
(7) S 494-009Make sure the ground locks are installed on the landing gear.
S 494-010
WARNING: YOU MUST CAREFULLY DO THE STEPS IN THE TASK BELOW TO INSTALL
_______ THE DOOR LOCKS ON THE LANDING GEAR DOORS. THE DOORS CAN CLOSE QUICKLY IF YOU DO NOT INSTALL THE DOOR LOCKS CORRECTLY. THIS CAN CAUSE INJURY TO PERSONS OR DAMAGE TO EQUIPMENT.
(8)
Do this task: "Installation of the Door Locks on the Wing Landing Gear" (Ref 32-00-30/201).
E.
Procedure
S 024-011
(1)
Remove the central lateral control package (CLCP) quadrant
(Fig. 401):
(a)
Disconnect the turnbuckles on the right body cables AA and AB.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
27-11-09
ALL ú ú 03 Page 404 ú Feb 10/91
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL
(b)
Remove the cotter pins that connect the cables to the quadrant.
(c)
Remove the cables.
(d)
Disconnect the back drive control rod between the quadrant and the right programmer.
(e)
Disconnect the CLCP control rod between the quadrant and the CLCP.
(f)
Remove the bolt.
NOTE:____The bolt assembly is a double bolt. You must remove the two nuts before you can remove the bolt from the quadrant assembly.
(g)
Move the quadrant from the support bracket.
(h)
Remove the lever and the bushing from the quadrant.
(i)
Remove the back drive control rod clevis from the quadrant.
TASK 27-11-09-404-012
3. Central Lateral Control Package (CLCP) Quadrant Installation____________________________________________________________
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 1(120)
