F. If clearance between actuator/walking beam attachment bolt (3) and beam is insufficient, add spacers (16) to aft end of beam hanger shaft.
CAUTION: DO NOT REDUCE CLEARANCE BETWEEN FORWARD SIDE OF BEAM HANGER AND AILERON CABLES TO LESS THAN 0.160 INCH. CABLE DAMAGE MAY RESULT.
G. Check for proper end play of beam hanger by moving hanger fully aft on tube. Check that clearance between beam hanger (15) and stud assembly (18) is 0.001 to 0.135 inch. If necessary, remove stud assembly (18) from shaft and add spacers (16) to obtain correct end play.
H. When end play and clearance of two preceding steps is correct, secure tube assembly (4) to brackets on structure.
CAUTION: BEAM HANGER SHAFT IS NOT SYMMETRICAL. CHECK THAT SHORT FLAT SIDE OF LUG ON BEAM HANGER SHAFT (4) IS INSTALLED FACING DOWN. IF SHAFT IS NOT PROPERLY POSITIONED, DAMAGE TO AIRPLANE MAY OCCUR WHEN GEAR IS RETRACTED.
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I. Place washer on each attachment bolt and insert bolt through brackets on structure and tube assembly (4) with heads outboard. Add washer and nut.
J. Tighten nuts 130 to 180 pound-inches.
K. Coat nuts, bolts, and spacers with grease (MIL-G-21164 or MIL-G-23827 optional to BMS 3-33).
L. Align inboard end of actuator walking beam (1) with walking beam arm on shock strut.
M. Insert actuator walking beam inboard attachment bolt (7) with head forward. Add washer and nut.
N. Insert attachment bolt (13) with head forward. Install washer and nut
(1)
With 65-46109-4 or -6 walking beam arm and 69-42199-1 attachment bolt, measure and record self-locking torque of nut. It should be 90 to 800 pound-inches. Add 250 to 300 pound-inches to the measured self-locking torque to determine the installation torque range. Torque the nut to within this range. Install cotter pin.
(2)
With 65-46109-4 or -6 walking beam arm and 69-42199-2 attachment bolt, torque nut 600 to 1800 pound-inches lube torque. Make sure torque remains in this range while making adjustments, and install cotter pin.
(3)
With 65-46109-( ) other than -4 or -6 and with BACB30LJ20 attachment bolt, torque nut 70 to 90 pound-feet. Back off and retorque 5 to 10 pound-feet. Back off to nearest locking position, and install cotter pin. Zero torque is acceptable.
O. Coat wing door hinge bolts (9) with primer. Keep primer off threads.
P. Install stabilizing beam (10) and insert wing door hinge bolts (9) complete with outer wing door
(14) from inboard side. Add washers and nuts.
Q. Tighten nuts 360-630 pound-inches.
R. Connect outer wing door pushrod (12) to trunnion link (11).
(1)
Insert bolt with head forward.
(2)
Tighten nut 100-140 pound-inches. Lock nut with cotter pin.
(3)
Connect bonding cable (13).
S. Jack airplane for gear retraction (Ref Chapter 7, Jacking Airplane).
T. Perform a retraction test of affected main gear only (Ref 32-32-0 A/T).
WARNING: MAKE CERTAIN PERSONNEL AND EQUIPMENT ARE CLEAR OF LANDING GEAR RETRACTION PATH.
U. Extend gear and install ground lock assemblies (Ref 32-00-01).
V. Lower airplane and remove jacks.
W. Install hydraulic access panel.
5A5
Sep 01/02 32-32-101 Page 405 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
MAIN GEAR ISOLATION VALVE MODULAR PACKAGE - REMOVAL/INSTALLATION
1. General
A. The main gear isolation valve modular package is located in the left main gear wheel well.
2. Equipment and Materials
A. Ground Lock Assemblies (Ref 32-00-01)
3. Remove Isolation Valve Modular Package (Fig. 401)
A. Check that landing gear ground lock assemblies are installed in all gear (Ref 32-00-01).
B. Depressurize hydraulic system.
C. Disconnect and plug hydraulic lines.
D. Remove handle stop bracket.
E. Remove isolation valve modular package.
F. Remove hydraulic unions and discard O-rings. Plug ports.
4. Install Isolation Valve Modular Package (Fig. 401)
A. Remove plugs and install hydraulic unions in isolation valve modular package with new O-rings.
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