______________________________________________________________________
A. General
(1)
If the airplane jacks are not available or you cannot lift the airplane on jacks, this procedure will permit you to bleed the actuator without landing gear extension and retraction.
B.
References
(1)
AMM 12-21-11/301, Main Landing Gear Lubrication
(2)
AMM 29-15-00/201, Hydraulic Systems A, B, and Standby
C.
Access
(1)
Location Zones
101 Left Control Cabin
102 Right Control Cabin
310 Left Main Landing Gear
410 Right Main Landing Gear
D.
Bleed the Actuator
S 864-064
(1) Make sure the hydraulic lines are installed correctly and they are not twisted.
S 864-065
WARNING: MAKE SURE THE GROUND LOCK ASSEMBLIES ARE INSTALLED ON THE MAIN
_______ LANDING GEAR BEFORE YOU MOVE THE CONTROL LEVER FOR THE LANDING GEAR. IF THE CONTROL LEVER IS MOVED WITHOUT THE GROUND LOCKS INSTALLED, THE LANDING GEAR CAN RETRACT AND CAUSE INJURY TO PERSONS OF DAMAGE TO EQUIPMENT.
(2)
Pressurize hydraulic system A (AMM 29-15-00/201).
S 874-066
(3)
Push the override button, and move the control lever for the landing gear from the DN position to the UP position and to the DN position three times.
NOTE: Hold the lever in each position for three seconds before you
____ move the control lever to the subsequent position.
S 864-067
(4) Move the control lever to the DN position.
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737-300/400/500MAINTENANCE MANUAL
(5) S 714-068When you move the control lever from the DN position to the OFF position, make sure the condition that follows occurs: (a) The rod end of the actuator tries to extend.
(6) S 864-069Move the control lever to the DN position.
(7) S 794-070Make sure there are no leaks at the hydraulic connections.
(8) S 864-071Remove the pressure from hydraulic system A (AMM 29-15-00/201).
(9) S 644-072Lubricate the attach points (AMM 12-21-11/301).
S 414-073
(10) Install the hydraulic access panel.
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MAIN GEAR ACTUATOR ASSEMBLY - INSPECTION/CHECK
______________________________________________
1. General_______
A. This procedure has illustrations and worn limit charts. No procedure in this section tells you how to get access to do the inspection. Refer to (Main Gear Actuator Assembly - Removal/Installation) for the removal procedures.
B. Consumable Materials
(1)
B00130 Isopropyl alcohol
(2)
A00028 BMS 5-92 Type I or III (Adhesive)
TASK 32-32-11-226-001
2. Main Gear Actuator Assembly Wear Limits (Fig. 601)_______________________________________
A. General
(1)
737-300 and 737-500 only: Examine the rub strip on the aft side of the actuator beam. If it is damaged, remove the rub strip and use the steps that follow to install the rub strip.
B.
Procedure
S 436-002
(1)
Install the rub strip:
(a)
Use solvent to clean the faying surfaces.
(b)
Apply a coat of BMS 5-92 with a spatula to the faying surface.
(c)
Apply sufficient finger pressure to the rub strip to maintain a continuous bead of extruded adhesive around the periphery of the mated surface.
(d) 中国航空网 www.aero.cn 航空翻译 www.aviation.cn 本文链接地址：737-300 400 500 AMM 飞机维护手册 起落架 LANDING GEAR 2(80)
