747-400 FAULT ISOLATION/MAINT MANUAL
BODY GEAR WHEEL WELL
SEE C SHT 3
CABLES
FLT COMPT
NOSE/BODY GEAR SEE A
SELECTOR VALVE
MECHANISM WING GEAR SELECTOR VALVE MECHANISM
LANDING GEAR CONTROL SYSTEM
LANDING GEAR
CONTROL HANDLE
MODULE, P2-3
SEE B SHT 2
P6 PANEL
FLT COMPT
A
Landing Gear Control System - Component Location Figure 102 (Sheet 1)
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 FAULT ISOLATION/MAINT MANUAL
A-A Landing Gear Control System - Component Location Figure 102 (Sheet 2)
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 FAULT ISOLATION/MAINT MANUAL
WING GEAR
SELECTOR VALVE
NOSE/BODY GEAR
MECHANISM
SELECTOR VALVE
MECHANISM
SEE E
SEE D
FWD
CABLE C FROM SHT 1 BODY GEAR WHEEL WELL CABLE CABLE
CABLE
QUADRANT SELECTOR VALVE QUADRANT SELECTOR VALVE
SELECTOR SELECTOR
VALVE VALVE
FWD
INBD INBD
SELINBD ECTOR VALVE MECHANISM NOSE/BODY GEAR SELECTO WING GEAR R VALVE MECHANISM
D E
Landing Gear Control System - Component Location
Figure 102 (Sheet 3)
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A
747-400 MAINTENANCE MANUAL
LANDING GEAR CONTROL SYSTEM - ADJUSTMENT/TEST
_____________________________________________
1. General_______
A. This procedure contains two tasks:
(1)
The adjustment of the control system for the landing gear
(2)
The test of the control system for the landing gear.
TASK 32-31-00-835-001
2. Adjustment of the Control System for the Landing Gear_____________________________________________________
A. General
(1)
You must adjust the control system for the landing gear when:
(a)
You replace a cable or a component
(b)
The tension in the cable is different than the values in the chart shown in Fig. 505.
(2)
If you install cable LGV1A, install the terminal that has left-hand threads in the forward position. Install the terminal that has right-hand threads in the aft position.
(3)
If you install cable LGV1B, install the terminal that has right-hand threads in the forward position. Install the terminal that has left-hand threads in the aft position.
(4)
You must not supply hydraulic pressure to the control valves while you adjust the control system.
(5)
Adjust the control system for the landing gear in the neutral position (control valves in the closed position).
(6)
Adjust the cable system until the rigging pins do not rub when you install and remove them.
(7)
All rigging pins are 0.309 to 0.311 inch diameter.
(8)
You can adjust the control system with the airplane on the ground or you can lift the airplane on jacks.
(9)
The difference between the internal airplane temperature and external airplane temperature must not be more than 5°F when you adjust the control system. Make sure that the temperature is stable for 1 hour before you adjust the system.
B.
Special Tools and Equipment
(1)
G12001 Kit (Rigging Pins) ~................................................................... | Rigging Pin No. | Length (inch) | Diameter (inch) | ..................................................................... | LG-1 | 4.0 | 0.309 to 0.311 | ..................................................................... | LG-2 | 4.0 | 0.309 to 0.311 | 2.....................….......................….....................1
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