(2)
Make sure the landing gear ground lock assemblies are installed in the nose and main landing gear (Ref 32-00-01).
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.
(3)
Make sure the hoses are correctly routed through the hose guides and are not twisted.
(4)
Pressurize hydraulic system A to 3000 psi (Ref 29-11-00 MP).
(5)
Using the manual override, move the landing gear selector handle from DOWN to UP several times. When you move the landing gear selector handle, leave the handle in each position at least three seconds before you move it to the next position.
(6)
Move the landing gear selector handle to DOWN.
(7)
Watch the rod end of either main landing gear retract actuator while moving the landing gear selector handle to OFF. Make sure the rod end attempts to extend when the selector handle is moved from DOWN to OFF.
(8)
Move the landing gear selector handle to DOWN.
(9)
Check the hydraulic connections for leaks.
(10)
Add hydraulic fluid to the reservoir as necessary (Ref Chapter 12, Hydraulic Servicing).
(11)
Restore the airplane to normal.
5B8
32-32-11 Page 406 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Sep 01/02
MAIN GEAR ACTUATOR ASSEMBLY - INSPECTION/CHECK
1. General
A. This data consists of illustrations and wear limit charts. No procedure is given in this section for access to permit inspection. Refer to Main Gear Actuator Assembly - Removal/Installation for removal procedures.
2. Main Gear Actuator Assembly Wear Limits (Fig. 601)
A. 737-200 only: Examine the rub strip on the aft side of the actuator beam. If it is damaged, remove and replace the rub strip as specified in OHM 20-15-12, type 70.
501
Oct 20/92 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 32-32-11 Page 601
Main Gear Actuator Assembly Wear Limits 501
32-32-11 Figure 601 (Sheet 1) Feb 20/91
Page 602
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
501 Main Gear Actuator Assembly Wear Limits
Feb 20/91 Figure 602 (Sheet 2) 32-32-11
Page 603
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
Main Gear Actuator Assembly Wear Limits 501
32-32-11 Figure 601 (Sheet 3) Feb 20/91
Page 604
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
INDEX NO. PART NAME DIM. DESIGN LIMITS WEAR LIMITS REPLACE WORN PART REPAIR WORN PART REPAIR INSTR.
DIAMETER MAX WEAR DIM. MAX DIAM CLEAR-ANCE
MIN MAX
1 BUSHING ID 1.3000 1.3010 1.3025 0.005 X *[1]
TUBE OD 1.2985 1.3000 1.2975 X *[2]
2 BUSHING ID 1.5000 1.5010 1.5030 0.005 X
PIN OD 1.4970 1.4990 1.4960 X
3 BUSHING ID 1.6880 1.6890 1.691 0.010 X
BUSHING OD 1.6840 1.6860 1.683 X
4 BEARING ID 1.4995 1.5000 X *[4]
PIN OD 1.4970 1.4990 X *[4]
5 BUSHING ID 1.2500 1.2510 1.252 0.005 X
BOLT OD 1.2480 1.2490 1.247 X *[2]
6 BEARING BALL ID 1.2495 1.2500 1.2520 0.005 X *[3]
BOLT OD 1.2480 1.2490 1.2470 X
7 BUSHING ID 1.0000 1.0010 1.003 0.005 X *[5]
BOLT OD 0.9985 0.9990 0.997 X
8 BEARING BALL ID 0.9995 1.0000 1.002 0.005 X
BOLT OD 0.9985 0.9990 0.997 X
*[1] Install bushings with corrosion preventive compound on faying surfaces and with interference fit of 0.0005 to 0.0023 inch. 中国航空网 www.aero.cn 航空翻译 www.aviation.cn 本文链接地址：737 AMM 飞机维护手册 起落架 LANDING GEAR(89)
