INDEX NO. PART NAME DIM. DESIGN LIMITS WEAR LIMITS REPLACE PART WORN REPAIR WORN PART REPAIR INSTR.
DIAMETER MITTED PER-DIM. WEAR DIAM CLEAR-ANCE MAX
MIN MAX
1 PEDAL ID 1.1248 1.1253 1.135 0.0115 X 1
BEARING OD 1.1245 1.1250 1.1245 X
2 PEDAL ID 1.6248 1.6253 1.735 0.0110 X
BEARING OD 1.6245 1.6250 1.6245 X
3 PEDAL ID 0.250 0.252 0.260 0.013 X 1
BOLT OD 0.2485 0.2495 0.247 X
4 PEDAL ID 0.3766 0.3781 0.383 0.010 X 1
SPACER OD 0.3756 0.3761 0.373 X
5 BELLCRANK ID 0.250 0.252 0.260 0.013 X 1
BOLT OD 0.2485 0.2495 0.247 X
6 BELLCRANK ID 0.3766 0.3781 0.383 0.010 X 1
SPACER OD 0.3756 0.3761 0.373 X
7 BELLCRANK ID 2.3125 2.3135 2.3175 0.006 X 1
BEARING OD 2.3115 2.3125 2.3115 X
8 TERMINAL ID 1.3736 1.3743 1.381 0.0055 X 1
BEARING OD 1.3745 1.3750 1.3745 X
9 TERMINAL ID 1.1875 1.1880 1.1930 0.005 X 1
BEARING OD 1.1870 1.1875 1.1870 X
10 ARM ID 0.3120 0.3140 0.319 0.010 X 1
BOLT OD 0.3110 0.3120 0.3090 X
REFER TO OVERHAUL MANUAL FOR REPAIR PROCEDURE
Rudder Pedal Assembly Wear Limits
Figure 601 (Sheet 3)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
27-21-07
ALL ú ú 01 Page 605 ú Feb 10/91
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL
RUDDER AFT QUADRANT - REMOVAL/INSTALLATION
__________________________________________
1. General
_______
A. There are two tasks in this procedure. There is a task for the removal and a task for the installation of the rudder aft quadrant.
B. The rudder aft quadrant is installed in the vertical fin near the point where the rudders come together. The aft end of the rudder cables attach to the aft quadrant. There is a pushrod that connects the aft quadrant to the feel and centering mechanism.
C. The removal procedure has these parts:
(1)
Make sure the airplane is in the correct configuration
(2)
The removal of the access panels
(3)
The installation of the rig pins
(4)
The removal of the rudder aft quadrant.
D.
The installation procedure has these parts:
(1)
The installation of the rudder aft quadrant
(2)
The adjustment of the control cables
(3)
An operational test of the rudder aft quadrant
(4)
The installation of the access panels.
TASK 27-21-08-004-001
2. Rudder Aft Quadrant Removal
___________________________
A. Special Tools and Equipment
(1)
G12001-50 Rig Pin Kit
B.
References
(1)
24-22-00/201, Manual Control
(2)
25-22-01/401, Main Passenger Cabin Ceiling Panel
C.
Access
(1)
Location Zone 211 Passenger Cabin-Nose to First Door, LH 311 Area Aft of Pressure Bulkhead, LH 312 Area Aft of Pressure Bulkhead, RH 323 Vertical Stabilizer, Front Spar to Rear Spar 324 Vertical Stabilizer, Rear Spar to Trailing Edge
(2)
Access Panel 312A Horizontal Stabilizer Jackscrew Access Door 324FR Centering Mechanism Access Panel 324FL Centering Mechanism Access Panel
D.
Procedure
(1)
Supply the electrical power (Ref 24-22-00/201).
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：747-400 AMM 飞机维护手册 飞行操纵 FLIGHT CONTROLS 2(98)
