Rudder and Rudder Trim Control Schematic
Figure 1

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MAINTENANCE MANUAL

 D.  A trim tolerance of +/-0.5 unit of aileron and/or +/-2.0 units of rudder is allowed to keep a straight and level flight at cruise with the flaps up. If the trim is out of tolerance, these adjustments are necessary:
 (1)  
The aileron system adjustment (AMM 27-11-00/501) with the trim position indication (AMM 27-18-00/501). Carefully examine the surface position.

 (2)  
The rudder system adjustemnt (AMM 27-21-00/501) with trim position indication (AMM 27-28-00/501). Carefully examine the rudder surface position in the high airspeed position.

 2.  Rudder
______
 A.  The rudders are conventional frame structures consisting of aluminium spars and ribs with skins of fiberglass honeycomb construction. The upper and lower rudders are located on the aft side of the vertical stabilizer. Both the upper and lower rudders have no trim tabs and are moved by the triple and dual hydraulic actuators respectively. The upper and lower rudder are designed for a 31.5 degrees full travel left or right at low speed (below 150 knots) and a 5 degrees maximum travel left or right at high speed (above 450 knots). The lower rudder is attached to the vertical stabilizer by four hinges. The upper rudder is attached with seven hinges. Each of these hinges requires periodic lubrication.
 3.  Rudder Pedals
_____________
 A.  The captain and first officer are each provided with a pair of rudder pedals for controlling the airplane about its vertical axis. The rudder pedals are located below the captain's and first officer's instrument panel. Each pair of pedals consist of right and left pedals mounted on a shaft. The pedal shaft is attached to the upper end of the pedal arm assembly. The lower end of the pedal arm assembly is mounted on a support shaft which is attached to the structure below the floor. The rudder pedal support and quadrant assemblies are accessible through ceiling panels in the main deck compartment.
 B.  The two sets of rudder pedals are bussed together by means of a bus pushrod connecting the two jackshaft assemblies. Toe pressure on the rudder pedals causes the pedals to rotate about their shafts and initiate braking action.
 4.  Rudder Pedal Adjustment Mechanism
_________________________________
 A.  The two pairs of rudder pedals can be adjusted independently to suit the captain and the first officer by means of the rudder pedal adjustment mechanism. The rudder pedal adjustment mechanism consists of an adjustment crank, adjustment shaft, a jackscrew, and pedal adjustment nut attached to the jackshaft assembly.
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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747-400
MAINTENANCE MANUAL

FLT CONTROL HYD POWER
12 34

FLT CONTROL HYD
POWER MODULE

Rudder Control System Component Location

Figure 2 (Sheet 1)

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A

747-400
MAINTENANCE MANUAL

RUDDER PEDAL ADJUSTMENT CRANK
SEE  D  SEE  C  CAPTAIN'S RUDDER PEDALS  CAPTAIN'S CONTROL COLUMN 

RUDDER QUADRANT FORWARD 
C CAPTAIN'S RUDDER PEDALS 

RUDDER PEDAL  PUSHRODS FROM FIRST 
POSITION  OFFICER'S RUDDER PEDALS 
TRANSDUCER 

FIRST OFFICER'S RUDDER PEDALS D Rudder Control System Component Location Figure 2 (Sheet 2)
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