Elevator Control Force Transducer
Figure 401 (Sheet 2)
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22-12-03
WHEEL STEERING ú ú 03 Page 403 ú Dec 20/96
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
757 MAINTENANCE MANUAL
(b)
11E18, FLT CONT COMPUTER SERVO LEFT
(c)
11E20, FLIGHT CONT CMPTR PWR CENTER
(d)
11E21, FLIGHT CONT CMPTR SERVO CENTER
(e)
11E35, FLT CONT CMPTR PWR RIGHT
(f)
11E36, FLT CONT CMPTR SERVO RIGHT
(g)
11H17, FLT CONT SHUTOFF TAIL LEFT
(h)
11H18, FLT CONT SHUTOFF TAIL CENTER
(i)
11H28, FLT CONT SHUTOFF TAIL RIGHT
S 414-006
(5)
Get access to the control column torque tube through the access panel 119BL (Ref 06-41-00).
S 434-007
(6)
Install rig pin E/ST-6 in the Captain's column torque tube (Ref 20-10-24).
S 434-008
(7)
Attach DO-NOT-OPERATE tags on the pilots' elevator control columns.
E. Remove the Elevator Control Force Transducer
S 034-009
(1)
Disconnect the three electrical connectors from the transducer.
S 034-010
(2)
Remove the transducer wire bundle clamp.
S 034-011
(3)
Remove the bolts, the washers, and the nuts from the transducer rod ends.
(4)
Remove the transducer from the arm and crank assembly.
S 014-012
TASK 22-12-03-404-013
3. Install the Elevator Control Force Transducer (Fig. 401)_____________________________________________
A. Equipment
(1) Rig Pin E/ST-6 (Ref 20-10-24)
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22-12-03
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
757
MAINTENANCE MANUAL
(2)
Rigging Bushing - 0.647/0.646 O.D.,
0.3135/0.3125 I.D. inch; inner and outer
diameters to be concentric within 0.001 inch,
minimum length 0.26 inch
(3)
Rod or bolt, 0.312/0.311 diameter; can be
passed through rigging bushing.
B. References
(1)
06-41-00/201, Fuselage (Major Zones 100 and 200) Access Doors and Panels
(2)
20-10-24/201, Rig Pins
(3)
22-00-02/201, Autoflight BITE
(4)
24-22-00/201, Electrical Power - Control
(5)
29-11-00/201, Main (Left, Center and Right) Hydraulic Systems
(6)
34-11-00/201, Pitot - Static System
C. Access
(1)
Location Zones
113 Area Forward of NLG Wheel Well
119 Main Equipment Center
(2)
Access Panels 113AL Flight/Landing Gear/Engine Control Components 119BL Main Equipment Center
D. Install the Transducer
S 414-014
(1)
Install the transducer rod end that is not adjustable to the crank assembly with the bolt, the washers, and the nut.
(a) Tighten the nut to 20 inch-pounds maximum.
(2)
Loosen the locknut on the transducer.
S 434-016
(3)
Adjust the rod end length and install the transducer to the arm assembly with the bolt, the washers and the nut.
S 034-015
(a) Tighten nut to 20 inch-pounds maximum.
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22-12-03
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