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 5.  Lift Devices (Fig. 9)
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 A.  The lift devices consist of 2 triple slotted trailing edge flaps and 14 leading edge flaps on each wing. The three inboard leading edge flaps on each wing are krueger flaps with a folding nose which extends as the flaps are extended. The remaining eleven leading edge flaps on each wing are variable camber flaps with camber which is changed by mechanical linkages as the flaps are extended.
 B.  The trailing edge flaps are normally operated from a flap control lever on the pilots' control stand. Flap lever position is converted to an electrical signal by an RVDT transmitter assembly and is sent to three flap control units in the main electrical equipment center. The flap control units output a flap extend or retract signal to the flap actuator in the body gear wheel well. The flap actuator positions input cranks on the inboard and outboard flap power packages which operate control valves to port fluid to hydraulic motors. Output of the power units is transmitted through torque tubes, angle gearboxes and transmission assemblies to position the flaps.
 C.  An electric motor in each power package can drive the trailing edge flaps as an alternate to hydraulically powered operation. If flaps fail to move under hydraulic power, the flap control units automatically activate the alternate electric motors to position the flaps. The motors can also be controlled independently of the flap control units with switches on the pilots' center instrument panel.
 D.  The flap control units automatically retract the TE flaps to relieve aerodynamic loads on the flaps if they are extended at an excessive airspeed. Load relief is activated based on flap position and on airspeed data supplied by the air data computers.
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747-400
MAINTENANCE MANUAL

 E.  The leading edge flaps are extended automatically by the flap control units when the trailing edge flaps are deployed. They may also be manually controlled with the trailing edge flaps by the alternate flaps switches on the pilots' center instrument panel. The leading edge flaps are positioned by four power drive units in each wing. Each power drive unit contains a pneumatic motor for the primary power source and an electric motor for an alternate means of power. The power drive units are connected to a torque tube system which positions the flaps through rotary actuators. All leading edge flaps are two position surfaces, positioned either full up or full down.
 F.  The flap control units continuously provide flap system failure protection including asymmetry detection, uncommanded motion detection, flaps-moving-away detection, and hydraulic and electric control disable functions. Protection is provided separately for inboard and outboard trailing edge flaps, and for group A and group B leading edge flaps. The flap control units will disable their control and failure protection functions when the alternate system is engaged, but will continue to provide position information for flight deck displays and user systems.
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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747-400 MAINTENANCE MANUAL
 FLIGHT CONTROL CABLES - DESCRIPTION AND OPERATION
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 1.  Flight Control Cables (Fig. 1 through Fig. 6)_____________________
 A.  This section provides flight control cable lengths and fittings. The following illustrations and tables provide cable dimensions for aileron and aileron trim control system, rudder control system, spoiler control system and speed brake control system. Cable references are from fitting to fitting. For cable removal and/or installation, refer to AMM 20-11-03/401.
CONTROL SYSTEM  CABLE CODE  CABLE FUNCTION 
AILERON  ACBA ACBB AA AB  AILERON CONTROL BUS - LEFT AILERON DOWN, RIGHT AILERON UP AILERON CONTROL BUS - LEFT AILERON UP, RIGHT AILERON DOWN AILERON CONTROL - LEFT AILERON DOWN, RIGHT AILERON UP AILERON CONTROL - LEFT AILERON UP, RIGHT AILERON DOWN 
RUDDER  RA RB  RUDDER CONTROL - RUDDER LEFT RUDDER CONTROL - RUDDER RIGHT 
　
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