SYSTEM NO. 2:
SYSTEM NO. 3:
ONE ENGINE-DRIVEN PUMP (EDP)
ONE ENGINE-DRIVEN PUMP (EDP)
ONE AC MOTOR-DRIVEN PUMP (ACMP)
ONE AC MOTOR-DRIVEN PUMP (ACMP)
MAIN HYDRAULIC SYSTEM RESERVOIR,
MAIN HYDRAULIC SYSTEM RESERVOIR,
RESERVOIR PRESSURIZATION MODULE,
RESERVOIR PRESSURIZATION MODULE,
AND FILTERS LOCATED IN NACELLE
AND FILTERS LOCATED IN NACELLE

Hydraulic Systems
Figure 1

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747-400
MAINTENANCE MANUAL

LEADING EDGE FLAPS
Flight Control Surfaces
Figure 2

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747-400
MAINTENANCE MANUAL

 A.  The primary flight controls consist of 10 movable surfaces for the three control axes:
 (1)  
Roll control - Inboard and outboard ailerons,
 two surfaces attached to each wing

 (2)  
Pitch control - Inboard and outboard elevators, two surfaces attached to each horizontal stabilizer

 (3)  
Directional (Yaw) control - Upper and lower rudder, two surfaces attached to vertical stabilizer

 B.  The secondary flight controls consist of 46 movable surfaces for four functions:
 (1)  
Lift and drag device augmenting roll control - Flight and ground spoilers, six surfaces on each wing

 (2)  
High lift device for takeoff, approach, and landing - Leading edge flaps, 14 surfaces on each wing; trailing edge flaps, two surfaces attached to each wing

 (3)  
Pitch trim device augmenting pitch control - horizontal stabilizer, one surface each side

 C.  All primary flight control surfaces are moved by hydraulic power control packages. Mechanical and hydraulic devices are used to provide normal control system feel. The power control packages are controlled by movement of mechanical linkage as a result of:
 (1)  
Conventional manual flight controls consist of control columns, control wheels, cables and quadrants, etc.

 (2)  
Actuators and power control packages responding to either manual or autopilot input signals.

 D.  Each primary flight control surface is moved by two or more power control packages. Each power control package is powered by only one hydraulic system; this provides each primary flight control surface with dual or triple path control. In the event of single hydraulic system or power control package failure, control of the airplane is preserved.
 E.  Autopilot power control packages and servos operate similarly except when electrically engaged, the input command is electrical rather than mechanical. Position feedback signal from the power control packages and servos neutralizes the input command signal from the autopilot (flight control) computer when the control surface reaches new position.
 4.  Hydraulic System Controls (Fig. 3)
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MAINTENANCE MANUAL

FLT CONTROL HYD
POWER MODULE
(EXAMPLE)

Hydraulic System Controls - Component Location
Figure 3

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