H31465
515 Typical Skin Reinforcements
May 01/74 Figure 1 53-31-0
Page 1
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
VORTEX GENERATORS - REMOVAL/INSTALLATION
1. Equipment and Materials
A. Hardwood stick
B. Nonmetallic scraper
C. Solvent - Final Cleaning of Metal Prior to Non-structural Bonding (Series 88) (Ref AMM/SOPM 20-30-88).
D. Adhesive - BMS 5-19, Class B-1/2, Type 44 (Ref 20-30-31)
E. Vortex Generator Installation Tool - MIT69-58847-43 (Left Side) MIT69-58847-44 (Right Side)
2. Remove Vortex Generator
A. Drill out rivets, or remove bolts.
B. Pry off vortex generator with hardwood stick.
3. Prepare for Installation
A. Remove residual bonding agent with nonmetallic scraper and solvent.
B. Clean faying surfaces with solvent.
4. Install Vortex Generator
A. If installing lower vortex generators, locate generators.
(1)
Orient vortex generator installation tool along skin trim lines at stringer S-12 and station 1088 per Fig. 401.
(2)
Check edge distance of holes where fasteners were removed and orient tool to provide best edge distance for new fasteners. Secure tool with tape.
(3)
Measure offset between upper and lower edges of tool and edge of skin at station 1088. Ensure difference between these measurements is less than 0.68 inch.
(4)
Locate vortex generator in tool cutouts.
B. If installing upper vortex generator, orient vortex generator per Fig. 402.
527
May 01/98 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 53-31-21 Page 401
C. Bond vortex generator or vortex generator assembly to fuselage surface with 100% coverage. Form 0.05 by 0.05 inch fillet around edge with excess adhesive.
(1)
Thoroughly blend base compound with activator according to manufacturer's instructions. Do not thin adhesive.
(2)
Apply thin, uniform coat of blended adhesive to each faying surface.
(3)
Assemble immediately, applying sufficient pressure to ensure complete contact of faying surfaces. A continuous bead of extruded adhesive usually indicates proper contact.
D. Remove installation tool.
E. Install rivets, or bolts.
(1) Rivet vortex generator assembly to stringers S-2, S-3, S-4, and S-5A.
NOTE: Installation of rivets will hold vortex generator in place and it is not necessary to wait for full cure of sealant before dispatching airplane. Airplane may be dispatched after sealant has set until it is firm. Although not fully cured, the sealant will not be blown out by the airstream.
F. Cure at 75 to 80°F.
(1) The time to obtain handling strength is 16 hours. Full cure is not obtained for a week or more.
2) Curing may be accelerated by applying heat not to exceed a bond line temperature of 120°F. As a rough rule of thumb the cure time will be reduced 50% for each 20°F rise in temperature. Conversely, temperatures below 75°F will greatly increase the required cure time.
527
53-31-21 Page 402 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 20/92
H26708 H26719 H26697
544 Fuselage Vortex Generator Installation
Aug 01/74 Figure 401 (Sheet 1) 53-31-21
Page 403
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
Fuselage Vortex Generator Installation 544
53-31-21 Figure 401 (Sheet 2) Aug 01/74
Page 404
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
501 Fuselage T-Section Vortex Generator Installation
May 15/72 Figure 402 53-31-21
Page 405
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
STABILIZER TO BODY FRONT SPAR SLIDING SEAL - REMOVAL/INSTALLATION
1 General
A. The stabilizer to body front spar sliding seal covers the opening where the forward stabilizer attach fitting travels. Approved repair of the seal may be accomplished by removing the seal plates and applying a spray coating of abrasion resistant teflon finish per 51-21-81, Abrasion Resistant Teflon Finish - Application.
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