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(3) Spring detents, force limiters and lost motion features are provided to permit system operation in the event of component failure. A spring detent is provided on the input link to each CLCP. In the event of jamming within a CLCP, the link will disengage at an aileron control wheel force of approximately 35 pounds, permitting full valve travel in the alternate CLCP. In either control system, jamming occurring between an aileron control wheel and the CLCP is bypassed by the aileron control load limiter. Overcoming the spring force in the limiter permits the left body cables to operate when the right body cable system is jammed. In this condition, the system can be operated by the captain's control wheel. If the left body cable system jams, the system can be operated by the first officer's control wheel through the right body cables. The right body cables will start to move after the spring force and 6 degrees of lost motion are overcome. After another 4 degrees of lost motion at the CLCP quadrant are taken up, input is provided to theleft CLCP (left autopilot). The force limiting pushrod between the CLCPs prevents the left body cable system from immobilizing the left CLCP (left autopilot). Force limiting pushrods between the programmers and the CLCP quadrant permit operation of the right aileron programmer.
EXTEND
28V DC
RIGHT BUS NO. 2 AILERON TRIM CONTROL
RETRACT P7 OVERHEAD CIRCUIT BREAKER PANEL
M254 AILERON TRIM MOTOR
CENTRAL WHEEL WELL, LEFT OF KEEL BEAM
Aileron Trim Actuator Schematic
Figure 5
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AB
PACKAGE
Aileron Control System Schematic
Figure 6
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(4)
In the event of complete hydraulic failure within one CLCP, the related programmer would not move, but with a signal into the opposite CLCP, the CLCP will respond, moving its programmer and providing the input to override the force limiting rod between the programmers, permitting aileron operation on the same side of the airplane as the operable CLCP. If there is hydraulic failure to one CLCP that does not prevent piston rod movement, the force limiting rod between the programmers, will provide operation of both programmers through the operable CLCP.
(5)
If trim is adjusted while both CLCP's have no hydraulic power, the aileron trim and feel mechanism will reposition but the control wheels will not. The drag of the unpowered CLCPs will not allow the input quadrant to rotate and will force the trim and feel mechanism cam follower out of the cam detent. Then, when hydraulic power is applied, the control wheels and ailerons will rapidly move to the newly trimmed position.
B.
Control
(1)
General
(a)
For maintenance purposes, any aileron may be powered by either one of the two main hydraulic supply systems serving it as shown in Fig. 4.
SRM (TYP)
Outboard Aileron Lockout Simplified SchematicFigure 7
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details. 中國航空網 www.k6050.com 航空翻譯 www.aviation.cn 本文鏈接地址：747-400 AMM 飛機維護手冊 飛行操縱 FLIGHT CONTROLS 1(50)
