G03635
501 Index Plate Location
May 01/98 Figure 801 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-11-11 Page 801
AILERON BALANCE TAB - REMOVAL/INSTALLATION
1. General
A. The aileron balance tabs are balanced into the aileron system with tab adjust weights bolted to the lower surface of the aileron balance panel. The number of weights attached depends upon individual weight of each balance tab. A data plate, etched with exact tab weight and number of tab adjust weights required, is attached to the outboard end of the tab.
2. Equipment and Materials
A. Grease - MIL-G-23827 (Ref 20-30-21)
B. Sealant - BMS 5-95
C. Primer - BMS 10-11, Type I
D. Enamel - BMS 10-11, Type II
E. Stainless Steel Shim Stock - 1/2 inch x 1/2 inch, BACS40R05U05
F. Protractor - Aileron Tab Alignment - F80222-1 which consists of a -2 protractor assembly (Ref 27-09-700 MP)
G. Bonding Meter, Microhm Bridge, Type 2
Bonding Meter - 477W Avtron Meter
Avtron Manufacturing, Inc.
Cleveland, Ohio
3. Remove Aileron Balance Tab
A. Remove three screws attaching forward portion of tab fairing to tab and remove fairing (Fig. 402).
B. Remove two nuts, bolts, and washers attaching tab control rods to tab mast.
C. Collect and tag bolts, nuts, and washers.
D. If aileron tab hinge covers are installed, rotate tab to expose screws attaching tab hinge covers to nose cap. Loosen screws and slide tab hinge covers into nose caps to gain access to tab hinge bolts.
E. Disconnect bonding jumpers near inboard and outboard hinges.
F. Remove nuts from hinge bolts at four hinge locations.
G. Support tab and remove four hinge bolts.
H. Carefully withdraw tab from hinge assemblies and remove from aileron.
4. Install Aileron Balance Tab
A. Check aileron balance tab wear (Ref 27-11-21 I/C).
B. Check data plate on outboard end of tab for required number of tab adjust weights. Check balance panel bay for correct number of tab adjust weights. Add or remove weights as required and install bolts in holes not used for weight attachment (Fig. 401, 402).
C. Lubricate hinge bearings with grease.
May 01/99 27-11-21 Page 401 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
D. Position tab in place and engage four hinge fittings on tab with corresponding fittings on aileron (Fig. 402).
NOTE: The axial (inboard-outboard) play of the aileron tab should be between 0.010 and
0.020 inch.
E. Install four hinge bolts with two thin washers under each bolthead and one thick washer under nut.
F. Tighten nuts 7-17 pound-inches.
G. Install four cotter pins.
H. Connect bonding jumpers in a manner to avoid interference with moving parts with the steps that follow:
NOTE: If installed, slide hinge covers to close hinge bolt access areas. Tighten hinge cover screws.
(1)
Clean surface to give electrical bonding.
(2)
Fillet seal fastener and bonding jumper end with sealant.
(3)
Apply primer plus enamel to exposed bare metal not covered by faying surfaces.
(4)
Make sure the total resistance across the bond is no more than 0.001 ohm. I, Deleted
J.
Connect tab control rods to tab mast by installing bolts, washers and nuts. Tighten nuts 50-70 pound-inches.
NOTE: On airplanes not equipped with clamp-up bushings in the tab mast fitting lugs, excessive clamp-up stresses could be applied to the lugs. Therefore, check the gaps between these lugs and tab control rod ends, and install shims, if required, to limit each gap to 0.002 inch maximum with bolt untightened. Shims may be fabricated from 1/2 x 1/2 inch stainless steel stock (BACS40R05U05), or equivalent. An interference of 0.002 inch is permissible. On airplanes equipped with clamp-up bushings in lugs, shims are not required.
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