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SEE C
AA CABLE
AB CABLE MECHANISM AND FEEL AILERON TRIM (LEFT AUTOPILOT) RIG PIN A/S-2 CABLE AB LATERAL CONTROL PACKAGE LEFT CENTRAL RIGGING PIN A/S-3 2
(RIGHT AUTOPILOT) LATERAL CONTROL PACKAGE RIGHT CENTRAL 1 AA CABLE
2 1 INSTALLED IN THE LEFT WHEEL WELL INSTALLED IN THE RIGHT WHEEL WELL PROGRAMMER RIGHT AILERON C LATERAL CENTRAL PACKAGE QUADRANT CONTROL
Aileron Control Load Limiter Installation Figure 401 (Sheet 3)
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Control Wheels Neutral Positions
Figure 402
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TABLE 1
CABLE RIGGING ADJUSTMENT LOADS TENSION IN POUNDS
4
TEMPERATURE
(`F) 1 BODY/WING CABLE 2
5 6
123 153110 (43`C) 114 14190 (32`C) 110 13580 (27`C) 105 13070 (21`C) 101 12560 (16`C) 97 12050 (10`C) 93 11540 (4`C) 89 11030 (-1`C) 80 9910 (-12`C) 72 89-10 (-23`C) 64 79-30 (-34`C) 58 71-40 (-40`C)
AILERON TRIM AND FEEL
MECHANISM RIG PIN A/S-2
CABLE AA
CABLE AB
AILERON TRIM ACTUATOR
CONTROL WHEEL
BUS CABLE
3
93 84 80 75 71 67 63 59 50 42 34 28
1
2
3
4
5 6
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 TURNBUCKLES
CAPTAIN'S
AILERON CONTROL PILOTS'
CONTROL COLUMN CONTROL
DRUM STAND
CABLE AA
FIRST
CABLE AB OFFICER'S CONTROL COLUMN
BUS CABLE
ACBA CABLE AB
CABLE AA BUS CABLE ACBB
AILERON CONTR0L LOAD LIMITER RIG PIN A/S-1
CABLE AA
CABLE AB
CENTRAL LATERAL CONTROL PACKAGE QUADRANT RIG PIN A/S-26
Aileron System Adjustment Figure 403
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C. Parts ~.............................................................................. | MM | | IPC | ................. ...........................| | FIG | ITEM | NOMENCLATURE | SUBJECT | FIG | ITEM | ...............................................................................| | 401 | 3 | Load Limiter | 27-11-05 | 03 | 50 | | | 8 | Bolt | | | 20 | | | 9 | Bushing | | | 45 | | | 10 | Washer | | | 30 | | | 11 | Nut | | | 40 | | | 12 | Bolt | | | 110 | | | 13 | Washer | | | 115 | | | 14 | Nut | | | 120 | | | 14 | Bolt (Upper) | | | 15 | | | 15 | Bolt (Lower) | | | 10 | | | 16 | Washer | | | 25 | | | 17 | Nut | | | 35 | | | 18 | Lower Beam | | | 125 | | | 19 | Nut (Upper) | | | 105 | | | 19 | Nut (Lower) | | | 85 | | | 20 | Washer (Upper) | | | 100 | | | 20 | Washer (Lower) | | | 80 | | | 21 | Bolt (Upper) | | | 95 | | | 21 | Bolt (Lower) | | | 75 | | | 22 | Cable Guard (Upper) | | | 90 | | | 22 | Cable Guard (Lower) | | | 70 | 2......…........…...................................…...........….....…........1 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(97)
