G07596
Rudder Aft Control Quadrant Installation 503
27-21-61Page 402 Figure 401 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. May 01/74
C. Check rudder aft control quadrant at installation points for allowable wear. Refer to Rudder Aft Control Quadrant - Inspection/Check.
5. Install Rudder Aft Control Quadrant
A. Slide washer and right bearing housing over quadrant shaft. (See figure 401.)
B. Install washer and nut on right side of quadrant shaft. Tighten nut to torque value of 190 to 280 pound-inches. Install cotter pin.
C. Place shaft inside airplane and position quadrant on shaft with input crank to left.
D. Install bolts, washers and nuts to secure quadrant to shaft.
E. Place left bearing housing on shaft, and install bolts and washers to secure both bearing housings to structure.
F. Rotate quadrant and ensure shaft is not binding in bearing housings.
G. Connect cables RA and RB to quadrant and install cable retainers using crews, washers, and nuts.
H. Connect cables RA and RB at turnbuckles. Tighten each cable to remove slack, but maintain zero cable tension.
I. Connect input rod to input crank using bolt, washers, and nut.
J. Remove rigging pin R-1.
K. Adjust cables RA and RB to tension specified in figure 402 which permits simultaneous insertion of rigging pins R-3, R-4, and R-5. The rigging pins must fit without binding.
L. Remove rigging pins and install turnbuckle locking clips.
M. Provide rudder systems A and B hydraulic power. Refer to 27-21-0.
N. Disconnect pushrod to nose wheel steering. (See figure 402.)
NOTE: Nose gear steering need not be disconnected if airplane is jacked so that nose gear is fully extended.
O. Operate rudder pedals and check rudder for smooth operation and specified travel as shown in figure 403.
P. Reconnect pushrod to nose wheel steering, if disconnected.
Q. Remove systems A, B, and standby hydraulic power. Refer to 27-21-0.
R. Install access panels.
500
Feb 15/73 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-21-61 Page 403
G07599G07608 G07612
Rudder Rigging Pin Location 502
27-21-61 Figure 402 (Sheet 1) Feb 15/73
Page 404
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
526 Rudder Rigging Pin Location
Feb 15/72 Figure 402 (Sheet 2) 27-21-61
Page 405
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
Rudder Deflection Diagram 501
27-21-61 Figure 403 Nov 01/74
Page 406
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
RUDDER AFT CONTROL QUADRANT - INSPECTION/CHECK
1. General
A. This data consists of illustrations and wear limits charts. There will be no procedure given in this section for gaining access to, or removing and replacing the component after inspection for wear. Refer to component removal/installation for this information.
2. Rudder Aft Control Quadrant Wear Limits (See figure 601.)
500
May 15/68 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-21-61 Page 601
G09573
Rudder Aft Control Quadrant Wear Limits 501
27-21-61Page 602 Figure 601 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Aug 15/69
RUDDER CONTROL TORQUE TUBE - REMOVAL/INSTALLATION
EFFECTIVITY
Airplanes PRE-SB 27-1252
1. Equipment and Materials
A. Corrosion Preventive Compound - MIL-C-11796, Class 3 (Ref 20-30-21)
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