(d)
If the part (54 and 55) is out of tolerance, replace the part.
(e)
Install all the parts that you removed to do the inspection/check.
(3)
Install the aileron programmer (14 and 21) (par. 3).
S 422-039
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
27-11-10
ALL ú ú 02 Page 215 ú Oct 10/90
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
INBOARD AILERON QUADRANT - REMOVAL/INSTALLATION
_______________________________________________
1. General_______
A. There are two tasks in this procedure. There is one task for the removal and one task for the installation of the inboard aileron quadrant. The procedure has these parts:
(1)
The installation of the door locks on the doors for the main landing gear
(2)
The removal of the inboard aileron quadrant
(3)
The installation of the inboard aileron quadrant
(4)
The adjustment of the aileron control and trim system
B.
The removal and installation procedure is the same for the left or right inboard aileron quadrant.
TASK 27-11-11-004-001
2. Inboard Aileron Quadrant Removal________________________________
A. Special Tools and Equipment
(1)
G12001-50 Rig Pin Kit
(2)
MIT65B04001-41 Control Wheel Straightedge
(3)
ME65B04001 Inboard Aileron Rigging Straightedge
B.
References
(1)
06-09-08/201, Wing Access Doors and Panels
(2)
24-22-00/201, Manual Control
(3)
29-11-00/201, Main Hydraulic Supply System
(4)
32-00-30/201, Landing Gear Door Locks
(5)
IPC 27-11-11, Fig. 2
C.
Access
(1)
Location Zone
579 Inboard Aileron, LH
679 Inboard Aileron, RH
(2)
Access Panel
573AB Inboard Aileron Actuator, LH
573BB Inboard Aileron Actuator, LH
573CB Hydraulic, LH
673AB Inboard Aileron Actuator, RH
673BB Inboard Aileron Actuator, RH
673CB Hydraulic, RH
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
27-11-11
ALL ú ú 01 Page 401 ú Jun 10/95
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL
1
TABLE 1
CABLE RIGGING ADJUSTMENT LOADS TENSION IN POUNDS
42
TEMPERATURE (`F)
BODY/WING CONTROL WHEEL
2
CABLE BUS CABLE
1 33 5
6
123 153
93
90 (32`C)
110 (43`C) 114 141
84
4
110 135
80
70 (21`C)
80 (27`C) 105 130
75
60 (16`C)
101 125
71 5 50 (10`C)
97 120 67
6
93 115
63
30 (-1`C)
40 (4`C)
89 110
59
10 (-12`C)
80 99
50 -10 (-23`C)
72 89
42 -30 (-34`C)
64 79
34 -40 (-40`C)
58 71 28
RIG PIN A/S-2
CABLE AB TO GET THE CORRECT CABLE TENSION, MAKE SURE THE AIRFRAME TEMPERATURE IS STABLE (USE A TOLERANCE OF |5`F) FOR A MINIMUM OF 1 HOUR.
THE SYSTEM MUST BE ADJUSTED WHEN THE CABLE LOADS ARE MORE THAN |15 LBS FROM THE TABLE VALUES. WHEN RIGGING THE SYSTEM, CABLE LOADS SHOULD BE |5 LBS FROM THE TABLE VALUES.
THE SYSTEM MUST BE ADJUSTED WHEN THE CABLE LOADS ARE MORE THAN |20 LBS FROM THE TABLE VALUES. WHEN RIGGING THE SYSTEM, CABLE LOADS SHOULD BE |15 LBS FROM THE TABLE VALUES.
IF POSSIBLE, MAKE THE LAST CABLE ADJUSTMENTS WHEN THE TWO ENGINES ARE INSTALLED ON THE WING.
WING CABLES & LEFT BODY CABLES
RIGHT BODY CABLES
SEE B
SEE A
CABLE AA
TRIM AND FEEL
MECHANISM
RIGHT AILERON
LEFT AILERON PROGRAMMER
PROGRAMMER
RIG PIN A/S-6
CABLE AA
RIG PIN A/S-7
CABLE AB
A TURNBUCKLE
中國航空網(wǎng) m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：747-400 AMM 飛機(jī)維護(hù)手冊(cè) 飛行操縱 FLIGHT CONTROLS 1(128)
