(3)
Grease - BMS 3-24 (Ref 20-30-21)
REF NO. F70207 -( ) DIAMETER (INCHES) LENGTH (INCHES) FUNCTION
R-1 R-2 R-3 R-4 R-5 E-4 -14 -14 -11 -11 -11 -11 0.309-0.311 0.309-0.311 0.309-0.311 0.309-0.311 0.309-0.311 0.309-0.311 12.7 士0.25 12.7 士0.25 6.7 士0.25 6.7 士0.25 6.7 士0.25 6.7 士0.25 CAPTAIN'S RUDDER PEDAL ARM F/O'S RUDDER PEDAL ARM CAPTAIN'S FWD QUADRANT F/O'S FWD QUADRANT FEEL AND CENTERING MECHANISM ELEVATOR AND RUDDER FEEL COMPUTER
C. Adjust Rudder and Rudder Trim Control System
(1) Remove rudder hydraulic systems A, B, and standby power (Ref 27-21-0 MP).
WARNING: HYDRAULIC SYSTEMS MUST BE DEPRESSURIZED TO PREVENT INJURY TO PERSONNEL WORKING ON VERTICAL FIN AND RUDDER.
NOTE: After completing adjustment, restore airplane to normal hydraulic configuration (Ref 27-21-0 MP).
If rudder power control unit or standby power control unit only are to be adjusted, do not remove hydraulic power.
27-21-0 Feb 20/93 Page 504
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(2) Adjust rudder forward quadrants.
(a)
Check that rudder hydraulic systems A, B, and standby power are removed (Ref step (1)).
(b)
Position jackshaft yoke to midtravel by operating rudder pedal adjustment crank (Fig. 503).
NOTE: Midpoint of yoke travel is determined by counting equal turns of shaft from full forward and full aft adjustment.
(c)
Open lower nose compartment door 1103, and remove nose wheel well forward overhead access panels (Ref Chapter 12, Access Doors and Panels).
(d)
Insert rigging pins R-3 and R-4 in forward rigging pin holes in forward quadrants (Fig. 502). If rigging pins do not fit, adjust busrod as follows: 1) Loosen RA and RB cables using turnbuckles located in stabilizer jackscrew
compartment (Fig. 501).
CAUTION: CABLE TENSION MUST BE RELIEVED BEFORE ADJUSTING BUSROD. RELIEVE TENSION UNIFORMLY IN BOTH CABLES.
2) Remove busrod from jackshaft yoke (Fig. 502).
3) Install rigging pins R-3 and R-4 in forward rigging pin holes in forward quadrants.
4) Adjust length of busrod so that rod end attaching bolts fit freely through jackshaft yoke. Install washers, spacers, nuts, and cotter pins.
5) Check adjustment of pushrod to nose wheel steering (Ref Chapter 32, Landing Gear).
(e)
With rigging pins R-3 and R-4 in place, check that gap between cable guard block and quadrant is 0.03 to 0.05 inch (Fig. 502). Add or remove shims if necessary.
(f)
Remove rigging pins R-3 and R-4.
(g)
Position captain's forward quadrant so that rigging pin R-3 can be inserted through aft rigging pin hole in quadrant. Check that maximum gap between quadrant and quadrant stop is 0.06 inch. Add or remove shims as necessary.
501
Feb 15/81 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-21-0 Page 505
G06837
Rudder Pedal Adjustment 500
27-21-0 Figure 502 May 15/68
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BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(h) Remove rigging pin R-3. Position first officer's forward quadrant so that rigging pin R-4 can be inserted through aft rigging pin hole in quadrant. Check gap between quadrant and quadrant stop per step (g).
(3)
Adjust rudder pedals.
(a)
Check that rudder hydraulic systems A, B, and standby power are removed
(step (1)).
(b)
Insert rigging pin R-5 and position forward quadrants so that rigging pins R-3 and R-4 may be installed in forward rigging pin holes (Fig. 503).
NOTE: Rudder trim knob may be used to aid in positioning forward quadrants.
(c)
With rigging pins R-3 and R-4 in place, check that rigging pins R-1 and R-2 fit through rigging pin holes on pedal arm assembly. If one or both pins cannot be installed, adjust tension rods by loosening jamnuts on one or both ends of rod assembly and rotating tube to obtain desired length.
NOTE: Nominal tension rod dimension is 36.50 inches.
(d)
When rigging pins fit freely, tighten jamnuts.
(e)
Inspect adjustable rod ends for proper thread engagement. Rod ends must be visible through inspection holes in tubing.
(f)
Remove rigging pins R-1, R-2, R-3, R-4, and R-5.
(4)
Adjust rudder trim actuator.
(a)
Check that rudder hydraulic systems A, B, and standby power are removed (step (1)).
(b)
Remove access panels 9509 and 9510 from vertical fin and open door 3701 in aft body section.
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