(2)
Remove centering unit output crank rigging pin.
H. Connect following electrical cables:
(1)
Connect VOR cables in stabilizer jackscrew compartment above and aft of pressure bulkhead.
(2)
Connect rudder control cables at rudder control power unit.
(3)
Connect the electrical connectors to the flux valves.
(4)
Connect the electrical connectors to the elevator pitot tube heaters.
I. Connect hydraulic lines at base of fin.
J. Connect the pitot static lines to the elevator pitot tubes.
K. Remove sling and sling attachment fittings or strongbacks.
L. Install sling attachment positioning screws in fin surfaces.
M. Pressurize rudder hydraulic system and check for leaks (Ref Chapter 27, Rudder and Rudder Trim Control System - MP).
N. Remove rudder gust lock and warning streamer.
O. Rig rudder and check operation of rudder per Chapter 27, Rudder and Rudder Trim Control System - A/T.
P. Test VOR portion of VOR/GS system per Chapter 34, Navigation.
Q. Do a test of the elevator pitot static system (MM 27-31-212/501).
R. Do a test of the compass system (MM 34-21-0/501).
S. Do a test of the heaters on the elevator pitot tubes (MM 30-31-0/501).
7. Restore Airplane to Normal Configuration
A. Close circuit breakers.
B. Install access panels.
543
55-30-0 Page 410 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 01/95
VERTICAL STABILIZER (FIN) - INSPECTION/CHECK
1. General
A. This data consists of illustrations and wear limits charts. Additional wear limits and repair are given in Component Overhaul Manual - Horizontal Tail Center Section Assembly, 55-10-05. 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. Vertical Stabilizer (Fin) Wear Limits
543 Vertical Fin Wear Limits
Jan 20/82 Figure 601 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 55-30-0 Page 601
VERTICAL STABILIZER (FIN) ATTACH FITTINGS - APPROVED REPAIRS
1. General
A. Corrosion of vertical and horizontal stabilizer attachment lug bushings has been found on some airplanes. The corrosion is due to moisture collection and retention in the lugs of the attach fittings. Unchecked corrosion could result in cracked lugs or loose bushings requiring extensive unscheduled manhours and downtime to repair. For replacement of horizontal stabilizer bushings, refer to 27-41-131, Approved Repairs.
B. This procedure provides special locating tooling to establish and maintain centerline location of hole in bushing being removed so that special reamers also provided can be used to ream hole in replacement bushing with identical hole centerline location as removed bushing. This is necessary because the bushings may have eccentric outer and inner diameters. Be careful when removing bolts to avoid bushing rotation. If a bushing is loose or rotates, it is necessary to accomplish the alternative bushing replacement procedure per SB 55-1028, unless the bolthole centerline can be established. If at any time during bushing removal the bushing rotates, or it is suspected that the bushing has rotated, it is necessary to perform the alternative bushing replacement per SB 55-1028.
2. Equipment and Materials
A. Horizontal Stabilizer and Fin Bushing Replacement Kit - F80231
B. Primer - BMS 10-11, Type 1 (Ref 20-30-41)
C. Shimming putty
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