Rudder Hinges Installation 5D1
27-21-22 Figure 401 (Sheet 1) Feb 20/87
Page 402
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
5D1 Rudder Hinges Installation
Feb 20/87 Figure 401 (Sheet 2) 27-21-22
Page 403
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
Rudder Hinges Installation 500
27-21-22 Figure 401 (Sheet 3) Feb 20/87
Page 404
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
J. Tighten bolts equally to secure rudder bearing bar to structure. Tighten hinge No. 1 and 2 bearing bar bolts 90 to 160 pound-inches and No. 3, 4, 5, 6 and 7 bearing bar bolts 60 to 95 pound-inches.
K. Tighten hinge pivot nut on hinges No. 1 and 2, 95 to 110 pound-inches. Shim hinge No. 2 to control gap (0.005-inch maximum) between fin hinge fitting and rudder bearing bar before tightening nut. Continue to turn nut to align cotter pin hole. Maximum alignment torque permitted is 190 pound-inches. Install cotter pin.
L. Tighten hinge pivot nut on hinges No. 3, 4, 5, 6, and 7 60 to 85 pound-inches. Continue to turn nut to align cotter pin hole. Maximum alignment torque permitted is 140 pound-inches. Install cotter pin.
M. Install hinge coverplates.
N. Remove rigging pin R-3.
O. Use the milliohmmeter to make sure there is a maximum of 0.01 ohms between the rudder and the vertical fin.
P. Restore airplane to normal hydraulic configuration (Ref 27-21-0 MP).
5D1
Apr 01/97 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-21-22 Page 405
RUDDER PEDAL ASSEMBLIES - REMOVAL/INSTALLATION
1. Equipment and Materials
A. Rigging Pins Kit - F70207-3, -52, -61, or -84:
REF NO. F70207 -( ) DIAMETER (INCHES) LENGTH (INCHES) FUNCTION
R-1 R-2 R-3 R-4 -14 -14 -11 -11 0.309-0.311 0.309-0.311 0.309-0.311 0.309-0.311 12.7 +0.25 12.7 +0.25 6.7 +0.25 6.7 +0.25 CAPTAIN'S RUDDER PEDAL ARM F/O'S RUDDER PEDAL ARM CAPTAIN'S FWD QUADRANT F/O's FWD QUADRANT
B. Corrosion Preventive Compound - MIL-C-11796, Class 3
C. Scale - 0 to 2 feet, graduated in inches, tenths and hundredths of an inch
2. Remove Rudder Pedal Assemblies
A. Remove rudder systems A, B and standby hydraulic power (Ref 27-21-0 MP).
B. Insert rigging pins R-3 and R-4 through rigging pin holes of both forward quadrants.
C. Open lower nose compartment door 1103 and remove nose wheel well forward overhead access panels.
D. Disconnect brake pushrods from bellcranks (Fig. 401).
E. Remove bolts holding upper rudder pedal cover to heel rest and remove pedal cover (Fig. 402).
F. Airplanes with retainers; remove retainers from pedal arms (Fig. 401)
G. Disconnect quadrant pushrods from pedal arms (Fig. 401).
H. Remove four bolts securing rudder pedal support shaft bracket to structure.
I. Support rudder pedals and remove rudder pedal support shaft.
CAUTION: DO NOT STRIKE AUTOBRAKE SWITCHES WHEN REMOVING OR INSTALLING FIRST OFFICER'S RUDDER PEDALS AS SWITCHES MAY BE DAMAGED.
J. Remove pedal assemblies by pulling up through floor. Left and right foot pedal assemblies and shaft support bracket will separate after removal.
NOTE: The outer bearing will be free to fall from pedal bellcrank when pedal assembly is removed from supporting structure.
531
May 01/99 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-21-31 Page 401
3. Install Rudder Pedal Assemblies
A. Remove rudder systems A, B and standby hydraulic power. Refer to 27-21-0.
B. Position rudder pedal assemblies in supporting structure with pedal assembly shaft support bracket positioned between left foot and right foot pedal assembly bellcranks per figure 401.
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