(2)
If rods exhibit permanent deformation greater than 0.10 inch but less than 0.25 inch, it is allowable to retain rods in service until the next "C" check, approximately 1800 hours.
(3)
If rods exhibit permanent deformation greater than 0.25 inch, remove from service.
B. If corrosion exists, refer to Corrosion Prevention Manual for examination for corrosion and cleanup of corrosion.
500
May 15/80 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-21-31 Page 601
G07164
Rudder Pedal Assemblies 500
27-21-31Page 602 Figure 601 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. May 15/80
RUDDER PEDAL ADJUSTMENT CRANK INSTALLATION - REMOVAL/INSTALLATION
1. Remove Rudder Pedal Adjustment Crank
A. Open lower nose compartment access door 1103, and remove nose wheel well forward overhead access panels.
B. Loosen shaft retaining nut (Fig. 401).
C. Remove all clamps which attach shaft to structure. Note clamp locations for installation. Captain's and first officer's clamp installations are not the same.
D. Pull shaft forward until end of shaft clears rudder control jackshaft.
E. Remove shaft retaining nut and washer from end of shaft and pull free of support structure.
F. Remove four retaining bolts from bearing housing and move rudder pedal adjustment crank down to clear crank support bracket.
G. Pull crank and shaft free of structure and remove unit.
H. Remove 13-inch nylon tube from outside of shaft if first officer's shaft is being removed and replaced with new shaft.
2. Install Rudder Pedal Adjustment Crank
A. Run shaft (Fig. 401) through openings provided in airplane structure from crank support bracket to rudder control jackshaft.
B. Attach bearing housing and retainer to crank mounting bracket by installing the four retaining bolts with heads of bolts aft.
C. Push shaft through hole in support channel and slip nut and washer over end of shaft.
D. Insert end of shaft in rudder control jackshaft and rotate fork end of shaft until it slips over pi n in jackshaft.
E. Tighten nut on shaft.
F. If first officer's shaft is being installed, install 13-inch nylon tube on outside of shaft in location shown in Fig. 401. Tube is slit along its length. Install by spreading open along slit and installing over shaft.
553
Aug 1/75 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-21-41 Page 401
G07168
Rudder Pedal Adjustment Crank Installation 500
27-21-41 Figure 401 (Sheet 1) May 15/68
Page 402
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
G. Install all clamps attaching shaft to airplane structure. Clamp shaft in such a manner that radius of curvature at any point on shaft will not be less than 5.0 inches. A smaller radius will cause binding of shaft.
H. Rotate crank through one cycle to check for binding.
I. Check rudder pedal travel per 27-21-0, Rudder and Rudder Trim Control System -Adjustment/Test.
J. Close all access doors and panels.
G07172
500 Rudder Pedal Adjustment Crank Installation
Feb 15/72 Figure 401 (Sheet 2) 27-21-41
Page 403
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
RUDDER FORWARD QUADRANTS - REMOVAL/INSTALLATION
1. General
A. The maintenance practices for either quadrant are similar and apply to both quadrants except as noted. The following procedures include rudder forward quadrant removal/installation and quadrant bearing replacement.
2. Equipment and Materials
A. Rigging Pins Kit - F70207-3, -52, -61, or -84:
REF NO. F70207-( ) DIAMETER (INCHES) LENGTH (INCHES) FUNCTION
R-1 -14 0.309-0.311 12.7 +0.25 CAPTAIN'S RUDDER PEDAL ARM
R-2 -14 0.309-0.311 12.7 +0.25 F/O'S RUDDER PEDAL ARM
R-3 -11 0.309-0.311 6.7 +0.25 CAPTAIN'S FWD QUADRANT
R-4 -11 0.309-0.311 6.7 +0.25 F/O'S FWD QUADRANT
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