MAIN GEAR TRUNNION LINK - REMOVAL/INSTALLATION
1. General
A.  Before the main gear trunnion link can be removed, the reaction link, upper end of drag strut, downlock spring assemblies, and hydraulic brake lines must be disconnected, and the main gear actuator and actuator walking beam removed. On the right gear, a ground speed brake cable must be disconnected in addition to all above items.
2.  Equipment and Materials
A.  Ground Lock Assemblies (Ref 32-00-01)
B.  Lead hammer
C.  Adapter Wrench, Trunnion Pin, Main Gear Nut - F80020
D.  Bullet-Shaped Thread Protector - F80115-1 or F80115-10
E.  Bullet-Shaped Thread Protector - F80115-2 or F80115-11
F.  Grease - Aero Shell 07 (Ref 20-30-21)
G.  Corrosion Inhibitor - Mastinox 6856K (Ref 20-30-21)
H.  Block and tackle
I.  Antiseize Compound - BMS 3-28 (Ref 20-30-21)
3.  Prepare for Removal
A.  Check that ground lock assemblies (Ref 32-00-01) are installed in all gear.
B.  Depressurize hydraulic system.
C.  Operate brakes to depressurize brake accumulator.
D.  Remove hydraulic access panel 8401 left, or 8501 right.
E.  Jack airplane (Ref Chapter 7, Jacking Airplane).
F.  Deflate shock strut (Ref 12-15-31, Servicing)
G.  Pull gear inboard about 45 degrees using block and tackle.
H.  Chock wheels.
4.  Remove Main Gear Trunnion Link
A.  Remove main gear actuator and actuator walking beam (Ref 32-32-11 R/I)
NOTE:  If the main landing gear stabilizing beam was removed to facilitate the removal of the main landing gear actuator assembly, reinstall the stabilizing beam.
B.  Disconnect hydraulic lines from swivels (23) on trunnion link (20). Plug lines and cap swivel connections (Fig. 401).
May 01/99 32-11-11 Page 401 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

C.  Remove swivel connections (24) from trunnion link (20).
D.  Remove downlock spring assemblies (25) (Ref 32-32-91 R/I).
E.  On right gear, disconnect ground spoiler interlock valve cable clamps from trunnion link.
F.  Disconnect drag strut (4) upper attachment.
(1)  Mark and retain drag strut upper attachment bolt (5) for installation in same location. On some airplanes, bolt is identified by a yellow head.
G.  Remove bolt keeper (31) retaining bolt (30).
H.  Remove bolt (30) attaching lock strut (28) to reaction link (29).
I.  Remove spring support shaft (26).
J.  Raise reaction link (29) just clear of trunnion pin (22) and secure in position.
K.  Remove nut and washer from lockbolt (17) protruding through trunnion pin nut retainer washer (18).
L.  Remove retainer washer (18), trunnion link pin nut (19), and special washer (18A). Install thread protector (21).
M.  DELETED.
N.  Remove actuator beam arm antirotation bolt (12).
O.  Remove nut and washer from trunnion pin lockbolt (16).
P.  Tap out trunnion pin (22).
Q.  Remove locking key (2) from bearing support fitting (8).
R.  Force aft end of trunnion link (20) up and clear of shock strut (14). Simultaneously unscrew bearing assembly (3) from bearing support fitting (8).
NOTE:  To facilitate removal of trunnion while performing step Q, the aft end of trunnion link should be deflected inboard as well as up.
S.  Apply a force to twist gear slightly and move drag strut and reaction link if needed to provide clearance when removing trunnion link from airplane.
T.  Remove lockwire from lockbolt (6) and remove lockbolt.
U.  Remove trunnion bearing bolt (7) and keywasher (1).
V.  Slide bearing assembly (3) from trunnion link.
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W.  If equipped W/65C31332 series or the 65-C32649 series bearing assy.
(1)  
Do a visual inspection of the bearing housing of the forward trunnion on the main landing gear (Fig.401).

(2)  
Examine the upset heads of all eight locking rivets (the interior side of the bearing race) of the bearing housing.

(3)  
If all eight rivets are correctly installed.  Do the inspection again at subsequent 4600 flight cycle intervals.

(4)  
Continue the inspection until the bearing assembly is changed per SB32-1217 or until 6 inspections are made with no deformed or distressed rivet found.

(5)  
If the bearing assembly is in one of the following conditions, schedule the bearing assembly to have changes made at the first maintenance opportunity, no more than 4,600 flight cycles.
　
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