(Continued)
Reference Description Specification
B00083 Solvent - VM&P Naphthas TT-N-95 Type II, ASTM
D-3735 Type III
C. Location Zones
Zone Area
300 Empennage
D. Access Panels
Number Name/Location
311BL Stabilizer Trim Access Door
E. Prepare for the Installation
SUBTASK 53-31-21-140-001
(1) If there is bonding material on the fuselage skin, remove the bonding material with a hardwood
hard resin phenolic scraper, STD-1064.
SUBTASK 53-31-21-110-001
(2) Use solvent, B00083 to clean the mating surfaces.
F. Installation Procedure
SUBTASK 53-31-21-420-001
(1) Bond the vortex generator assembly [1] to the fuselage surface.
(a) Apply a thin, constant layer of sealant, A00247 to each mating surface.
NOTE: Make sure the sealant will cover all of the mating surfaces.
(b) Align the vortex generator assembly [1] to the fuselage (Figure 401).
(c) Make a 0.05 inch by 0.05 inch (1.27mm by 1.27 mm) fillet seal around the edge of the
assembly.
SUBTASK 53-31-21-420-002
(2) Attach the vortex generator assembly [1] to the empennage with 13 bolts [2] in the applicable
locations.
NOTE: The installation of permanent fasteners will hold the vortex generator assembly in
position. You do not have to wait for the full cure of the sealant before you return the
airplane to service.
G. Put the Airplane Back to its Usual Condition
SUBTASK 53-31-21-860-003
(1) Remove the lock, SPL-1672 on the stabilizer trim wheel at the control stand, (Figure 402).
SUBTASK 53-31-21-860-004
(2) Remove the safety tags and close these circuit breakers:
CAPT Electrical System Panel, P18-1
Row Col Number Name
C 2 C00849 AFCS STABILIZER TRIM
F/O Electrical System Panel, P6-2
Row Col Number Name
B 10 C00207 FLIGHT CONTROL STAB TRIM CONT
D 10 C00840 FLIGHT CONTROL STAB TRIM ACTUATOR
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
53-31-21
Page 403
D633A101-ILF Feb 15/2017
ECCN 9E991 BOEING PROPRIETARY - Copyright © Unpublished Work - See title page for details
EFFECTIVITY
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