G10777G10782
Horizontal Stabilizer Center Section Hinge Fitting Installation 500
27-41-31 Figure 801 (Sheet 1) Apr 01/97
Page 804
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
500 Horizontal Stabilizer Center Section Hinge Fitting Installation
Apr 01/97 Figure 801 (Sheet 2) 27-41-31
Page 805
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
STABILIZER FORWARD CONTROL MECHANISM - REMOVAL/INSTALLATION
1. Equipment and Materials
A. Tensiometer - 0 to 200 pounds capacity
B. Spring scale - 0 to 50 pounds capacity
C. Primer - BMS 10-11, Type I (Ref 20-30-41)
D. Actuator Trammel Bar - F80055-1
2. Remove Forward Mechanism
A. Provide electrical power.
B. Close stabilizer trim actuator and stabilizer trim control circuit breakers on panel P6.
C. Actuate stabilizer to full AIRPLANE NOSEUP.
D. Open stabilizer trim actuator and autopilot stabilizer trim servo circuit breakers on panel P6.
E. Adjust forward mechanism aft support linkage to provide slack in chain (Fig. 401).
CAUTION: SLACK IN CHAIN IS NECESSARY BEFORE RELEASING CABLE TENSION TO AVOID EXCESSIVE RIGGING LOADS IN CHAIN.
F. Release cable tension by loosening turnbuckle (7).
G. Remove equipment drip shield (not on all airplanes).
H. Remove cable guards (3).
I. Remove STA cable from bottom edge of drum (4) and tag for installation.
NOTE: A 50-pound load may be applied to stabilizer trim control wheel to stretch STB cable to facilitate detachment of STA cable.
J. Disconnect position indicator flexible drive shaft from forward mechanism.
535
Oct 20/89 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-41-41 Page 401
G10795 G10799
Forward Mechanism and Chain Installation 535
27-41-41 Page 402 Figure 401 (Sheet 1) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Oct 20/92
501 Forward Mechanism and Chain Installation
May 01/75 Figure 401 (Sheet 2) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-41-41 Page 403
K. Rotate stabilizer trim control wheel until chain connector link is between idler sprocket (9) and forward mechanism sprocket (5).
L. Disconnect chain assembly (10) at connector link and secure loose ends of chain clear of forward mechanism (Detail A).
M. Remove STB cable from top edge of drum (4) and tag for installation.
N. Remove aft turnbuckle mounting bolt (6).
O. Support forward mechanism assembly and detach from aircraft structure.
(1)
Remove support mounting bolts (1), bushings, washers, and nut from aft support link assembly.
(2)
Remove bolt (8), bushing, washers from lower end of forward support link assembly and remove forward mechanism.
3. Install Forward Mechanism
A. Position forward mechanism.
B. Install mounting bolts (l, Fig. 401), bushings, washers, and nuts through aft support linkage assembly and aircraft structure.
NOTE: Bushings, installed in left and right eyebolts on aft support link assembly are of different diameters. Larger bushing installed in right eyebolt.
C. Install bolt (8), washers, bushing, and nut through lower end of forward support link assembly eyebolt and forward mechanism casting. Apply primer to contact surface areas of forward mechanism casting just prior to installation of bolt.
WARNING: PRIMER IS TOXIC AND FLAMMABLE. USE ONLY IN WELL VENTILATED AREA. DO NOT GET IN EYES OR ON SKIN.
NOTE: Install washers in following order: Bolthead, washer, support mechanism casting, washer, eyebolt, washer, support mechanism casting, washer, and nut.
D. Position turnbuckle (7) and install bolt, washers, bushing, and nut. Apply primer to contact surface area of forward mechanism casting just prior to installation of bolt.
NOTE: Install washers in following order. One washer between head of bolt and forward mechanism casting and one washer between forward mechanism casting and nut.
500
27-41-41 Page 404 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 20/87
G10810
535 Forward Mechanism and Chain Installation Oct 20/89 Figure 401 (Sheet 3) 27-41-41 Page 404A/404B BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
E. Adjust turnbuckle (7) to approximately 12.50 inches between centers.
NOTE: To facilitate further adjustment, adjust turnbuckle to provide approximately equal extension of screws on each side of sleeve.
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