(7)
AMM 32-00-30/201, Landing Gear Door Locks

 (8)
AMM 32-09-03/501, Proximity Switch Electronics Unit

 (9)
AMM 32-13-01/601, Body Landing Gear

 (10)
 AMM 32-13-07/201, Body Gear Drag Strut Universal

 (11)
 AMM 32-13-15/401, Body Gear Truck Positioning Actuator

 (12)
 AMM 32-14-05/401, Body Gear Shock Strut Inboard Door

 (13)
 AMM 32-14-06/401, Body Gear Shock Strut Outboard Door

 (14)
 AMM 32-33-00/501, Body Gear and Door Extension and Retraction

 (15)
 AMM 32-33-01/401, Body Gear Actuator

 (16)
 AMM 32-35-00/501, Nose and Body Gear Alternate Extension System

 (17)
 AMM 32-41-00/201, Hydraulic Brake System

 (18)
 AMM 32-41-00/501, Hydraulic Brake System

 (19)
 AMM 32-42-00/501, Brake Control System

 (20)
 AMM 32-46-00/501, Brake Temperature Monitoring System

 (21)
 AMM 32-53-00/501, Body Gear Steering

 (22)
 SRM 53-40-08

 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

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 ALL  ú ú 03 Page 415 ú Oct 18/99
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL

 F.  Access
 (1)  
Location Zone
 755 Body Landing Gear, LH
 765 Body Landing Gear, RH

 (2)  
Access Panels
 193U Keel Beam Access Panel

 G.  
Prepare for Installation

 S 214-023
 (1)  
Do a check of the trunnion supports for corrosion between the bushing and support (SRM 53-40-08).

 S 214-024

 (2)  
Do a check of the trunnion bearing assemblies for wear
 (AMM 32-13-01/601).

 H.  
Install Body Landing Gear (Fig. 402)

 S 424-083
 CAUTION: WHEN REPLACING LANDING GEAR, ENSURE THAT ANTISKID TRANSDUCER IS
_______ COMPATIBLE WITH REMAINDER OF ANTISKID IN GEAR SYSTEM. BRAKE OVERHEAT AND IMPROPER BRAKING MAY OTHERWISE RESULT.
 (1)  
Install the body landing gear (24).

 (a)  
Install the inboard trunnion bushing (4) into the support fitting (1). 1) Fill the lubrication paths in the cap (7) with grease. 2) Use solvent to clean the support fitting (1), cap (7) and

 bushing (4 and 10) mating surfaces.
 3)  Apply a 0.02-inch thick (average) layer of sealant to the inside diameter surfaces of the support fitting (1), cap (7) and the outer diameter of the bushing assembly (4 and 10). a) Apply additional sealant to the edges of the support
 fitting, cap and the bushing assembly to ensure no voids exist at chamfered edges.
 4)  Place the bushing upper half (4) into the support fitting (1) and the bushing lower half (10) into the cap (7).
 5)  Use solvent to clean all sealant from the inside diameter of the bushing assembly (4 and 10) and the mating surfaces of the support fitting (1) and cap (7). a) Apply grease to these surfaces.
 6)  Install the bearing cap (7) with the bolts (9) finger tight.
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 32-13-01
 ALL  ú ú 04 Page 416 ú Feb 18/02
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL

 7) Install the G32005-9 (larger) Clamp Up Gage into the bushing and tighten the bearing cap bolts (9). a) Tighten the trunnion cap bolts in 200 pound-feet (271.2 newton-meters) increments at 5 minute intervals until the final maximun torque is reached.
 NOTE: This will allow the sealant more time to squeeze
____ out and spread evenly between the bushing and fitting.
 8)  Allow the sealant enough time to cure.
 NOTE: If yo want to speed up the curing time, use a heat
____ gun to increase the sealant surrounding temperature. For every 20 F degree temperature increase, you can decrease the curing time by one half.
 9)  Remove the trunnion bearing cap (7) and remove the G32005-9 Clamp Up Gage.
 10) Install the G32005-11 Rotation Check Gage and torque bearing cap bolts to 200 pounds-feet (271.2 Nm).
　
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