D.  Place washer on each attachment bolt and insert bolts through fittings and hanger shaft with heads outboard. Add washer and nut.
E.  Swing beam hanger up to simulate gear retraction. Check that actuator walking beam attachment bolt (7) clears landing gear beam.
F.  If clearance between bolt and beam is insufficient, remove beam hanger shaft. Remove shims from forward end of shaft and add to aft end of shaft (Ref 32-32-101 R/I).
G.  Tighten nuts 130 to 180 pound-inches.
H.  Rotate walking beam arm (14) to align holes for insertion of antirotation bolt. Insert bolt from top, install washer, and tighten nut 30 to 40 pound-inches.
I.  Align inboard end of actuator walking beam (3) with walking beam arm on shock strut.
J.  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.

K.  Line inboard end of actuator with trunnion link pin (15). Insert attachment bolt (16) with head forward. Add washer and nut.
L.  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.
M.  Remove plugs and caps from hydraulic lines and actuator. Connect hydraulic lines (19).
N.  Connect hose guide (20) to hose guide clamp (21).
O.  Check tube support (22) is positioned with lower support attach bolt aligned with witness stripe on actuator body (rotated up and aft 600 from bottom center).
P.  Coat wing door hinge bolts (1) with primer. Keep primer off threads.
Q.  Install stabilizing beam (2) and insert hinge bolts (1) complete with wing door from inboard side. Add washers and nuts.
NOTE: Install stabilizing beam (2) with concave surface up.
R.  Tighten nuts 360 to 630 pound-inches.
S.  Connect outer wing door pushrod (10) to trunnion link (9).
(1)  
Insert bolt with head forward. Add washer and nut.

(2)  
Tighten nut 450 to 500 pound-inches. Back off to nearest locking position and install cotter key.

5B8
May 01/01 32-32-11 Page 403 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

Main Gear Actuator Assembly Installation  511 
32-32-11  Figure 401 (Sheet 1)  Feb 20/94 
Page 404 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

5B8  Main Gear Actuator Assembly Installation 
Feb 20/94  Figure 401 (Sheet 2)  32-32-11 
Page 405 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

7.  Bleed Main Gear Actuator (Airplane On Jacks)
A.  Jack airplane for gear retraction (Ref Chapter 7, Jacking Airplane).
B.  Pressurize hydraulic system. Place gear control lever in UP then DN positions. Check hydraulic connections for leaks (Ref 29-11-0 MP).
WARNING:  MAKE SURE GROUND LOCK ASSEMBLIES ARE INSTALLED IN ALL LANDING GEAR TO PREVENT INADVERTENT OPERATION OF THE GEAR. INJURY TO PERSONNEL AND/OR DAMAGE TO EQUIPMENT COULD RESULT IF THE GEAR RETRACTS.
C.  Correct any leakage.
D.  Place control lever in UP position, carefully loosen bleed plug in head end of actuator (on upper side of cylinder), and bleed actuator.
E.  Tighten plug to standard torque. Lockwire plug.
F.  Return control lever to DN position and remove ground lock assembly (Ref 32-00-01).
G.  Lubricate attachment points per Chapter 12, Main Gear Lubrication.
H.  Perform a retraction test of main landing gear only (Ref 32-32-0 A/T).
I.  Cycle gear several times to bleed air from piston rod end of actuator.
WARNING:  MAKE CERTAIN PERSONNEL AND EQUIPMENT ARE CLEAR OF LANDING GEAR PATH.
J.  Extend gear and install ground lock assemblies (Ref 32-00-01).
K.  Lower airplane and remove jacks.
L.  Install hydraulic access panel.
8.  Bleed Main Gear Actuator (Airplane On Ground)
　
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