* SEE WM EQUIPMENT LIST
Nose Wheel Steering System - Component Index
Figure 101
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A
747-400 FAULT ISOLATION/MAINT MANUAL
P7-2 PANEL
TILLER
SEE A
FORWARD PASSENGER FLIGHT COMPARTMENT CABIN SEE B
TILLER HANDLE (CAPTAIN'S)
QUADRANT
SIDEWALL
PANEL
TILLER
RUDDER PEDAL
A
INTERCONNECT RUDDER PEDAL
ACTUATOR NO. 2 INTERCONNECT RUDDER PEDAL ACTUATOR NO. 1 STEERING MECHANISM
FORWARD PASSENGER CABIN
B
Nose Wheel Steering System Figure 102 (Sheet 1)
NOSE LANDING
GEAR
SEE C SHT 2
STEERING CRANK (REF)
CLUTCH ARM
(REF)
INTERCONNECT LEVER (REF)
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A
747-400 FAULT ISOLATION/MAINT MANUAL
CABLE
COMPENSATOR
MECHANISM
SEE E
METERING
VALVE
ASSEMBLY
METERING VALVE
SEE F
METERING
VALVE
ACTUATOR STEERING
ASSEMBLY COLLAR
SEE D SEE G
NOSE LANDING GEAR RIGHT STEERING
C FROM SHT 1 ACTUATOR
LEFT FWD
CABLE DRUM STEERING
ASSEMBLY (REF) ACTUATOR
STEERING ACTUATOR ASSEMBLY D
METERING VALVE COMPENSATOR
FWD
ASSEMBLY CABLE COMPENSATOR
PIVOT LINKS
METERING
VALVE
CABLE COMPENSATOR MECHANISM
SHOCK
METERING VALVE
FWD E (REF) F STRUT
FORWARD STEERING COLLAR
AFT STERING COLLAR
FWD
STEERING COLLAR G
Nose Wheel Steering System - Component Location Figure 102 (Sheet 2)
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A
747-400 MAINTENANCE MANUAL
NOSE WHEEL STEERING SYSTEM - ADJUSTMENT/TEST
____________________________________________
1. General_______
A. This subject has these two tasks:
-Adjustment of the nose wheel steering system
-
Test of the nose wheel steering system.
B.
Procedures in this section include the system adjustment and a system test.
C.
All operational tests for system components are included in their removal/installation procedures.
D.
The system adjustment lists all the adjustments necessary on the steering system.
E.
The system test has these checks:
-System Clearance, Valve Freedom and Centering Check
-Tiller Steering Check
-Rudder Pedal Steering and Ground Sensing Check
-Towing Provisions Check.
TASK 32-51-00-835-001
2. Nose Wheel Steering System Adjustment_____________________________________
A. General
(1)
The adjustment of the nose wheel steering system includes rigging the nose wheel steering cables and adjusting the electric actuator clutch arm lever rods.
(a)
Generally, cables need rigging when tension values deviate more than |10 pounds from the value given in the rigging load chart of Fig. 502.
(b)
The steering system cables operate the steering metering valve while an electric actuator and lever operate the rudder pedal disconnect mechanism.
(2)
Make sure that the temperature inside and outside of the airplane have been equal within 5 degrees for a minimum of one hour before rigging cables.
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