REPLACE THE BEARING IF IT DOES NOT TURN FREELY.
THIS IS A CLAMP-UP JOINT. THERE IS NO CLEARANCE AFTER YOU TIGHTEN THE BOLT.
THE LIMITS SHOWN ARE BEFORE THE BEARING RETENTION. NO CLEARANCE IS PERMITTED AFTER YOU SWAGE.
USE A 69-38919 SLEEVE OR AN EQUIVALENT WHEN YOU REPLACE THE BEARING.
Elevator Feel Unit Wear Limits
Figure 601 (Sheet 2)
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747-400 MAINTENANCE MANUAL
(d)
Replace the parts that are not in the tolerance.
(e)
Install the parts.
S 426-004
(3) Do this task: "Elevator Feel Unit Installation" (Ref 27-31-17/201).
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747-400 MAINTENANCE MANUAL
INBOARD TO OUTBOARD ELEVATOR SLAVE LINKAGE - REMOVAL/INSTALLATION
_________________________________________________________________
1. General_______
A. There are two tasks in this procedure. There is one task for the removal and one task for installation of the inboard to outboard slave linkage assembly. The procedure has these parts:
(1)
The removal of the control rod
(2)
The removal of the lever assembly
(3)
The removal of the adjustment control rod
(4)
The installation of the lever assembly
(5)
The installation of the control rod
(6)
The installation of the adjustment control rod
(7)
Put the Airplane to its Usual Condition
(8)
The adjustment of the slave linkage assembly
(9)
The operational test of the slave linkage assembly.
B.
The removal and installation procedure is the same for the left or the right slave linkage assembly
C.
A control rod or lever assembly can be removed independently of the other slave linkage assembly components.
D.
The adjustment control rod must not be changed while a slave linkage assembly component is removed or installed.
TASK 27-31-19-004-001
2. Inboard to Outboard Slave Linkage Assembly Removal (Fig. 401)__________________________________________________
A. Special Tools and Equipment
(1)
G12001-50 Rig Pin Kit
B.
References
(1)
AMM 06-09-06/201, Stabilizer and Elevator Access Doors and Panels
(2)
AMM 24-22-00/201, Manual Control
(3)
AMM 29-11-00/201, Main Hydraulic Supply System
(4)
AIPC 27-31-56, Fig. 1
C.
Access
(1)
Location Zone 334 Horizontal Stabilizer Rear Spar to Trailing Edge 344 Horizontal Stabilizer Rear Spar to Trailing Edge
D.
Procedure
(1)
Do this task: "Supply Electrical Power" (AMM 24-22-00/201).
(2)
Do this task: "Supply Hydraulic Power" (AMM 29-11-00/201).
S 864-002
S 864-003
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27-31-19 中國航空網 www.k6050.com 航空翻譯 www.aviation.cn 本文鏈接地址：747-400 AMM 飛機維護手冊 飛行操縱 FLIGHT CONTROLS 3(97)
