Both test switches must be actuated simultaneously to allow ground operation of stall warning system
500 Air-Ground Sensing Functions
May 15/69 Figure 5 (Sheet 2) 32-00
Page 9
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
5. Structural Fuse Points
A. Certain connections are made with fasteners designed to fail first under excessive shock loads. The fasteners are designed to minimize damage to primary structure if attached components are subjected to severe impact loads. Figure 6 lists those connections in landing gear systems with the subject number where additional information may be found.
Subject No. Fastener Type Part Containing Fastener
32-11-0 32-11-0 32-11-31 32-51-21 (2) NAS1304-31 (2) NAS1306-31 69-42196-( ) 69-39476-( ) MS20426A5 MAIN GEAR REAR TRUNNION BEARINGMAIN GEAR FORWARD TRUNNION BEARING MAIN GEAR DRAG STRUT UPPER ATTACHMENT RUDDER PEDAL STEERING CONTROL ROD
Structural Fuse Points 500
32-00 Figure 6 May 15/68
Page 10
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
GROUND LOCK ASSEMBLIES - MAINTENANCE PRACTICES
1. Equipment and Materials
A. Ground Lock Assembly - F72735
B. Nose Gear Steering Lockout Pin - F72735-13 (airplanes with nose gear steering
depressurization valve installed)
2. Gear Ground Lock Assembly Removal/Installation (Fig. 201)
A. Install Gear Ground Lock Assembly
(1)
Insert ground lock assembly in lock brace.
(2)
Insert safety pin in ground lock assembly.
B. Remove Gear Ground Lock Assembly
(1)
Remove safety pin from ground lock assembly installed in main gear lock brace.
(2)
Pull ground lock assembly from lock brace.
3. Nose Gear Steering Lockout Pin Removal/Installation (Fig. 202 for effectivity)
A. Install Nose Gear Steering Lockout Pin.
(1)
Depress knob on nose gear steering depressurization valve and hold.
(2)
Depress button on lockout pin and insert pin in hole in side of depressurization valve until it bottoms.
(3)
Release button to secure pin in hole.
(4)
Release knob on nose gear steering depressurization valve.
B. Remove Nose Gear Steering Lockout Pin
(1)
Make certain nose gear is centered before removing lockout pin.
CAUTION: NOSE GEAR WILL MOVE TO CENTERED POSITION IF HYDRAULIC SYSTEM IS PRESSURIZED WHEN LOCKOUT PIN IS REMOVED.
(2)
Depress knob on nose gear steering depressurization valve and hold.
(3)
Depress button on lockout pin and remove.
(4)
Release knob on nose gear steering depressurization valve.
501
Feb 20/87 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 32-00-01 Page 201
Ground Lock Assembly 500
32-00-01 Figure 201 Feb 20/87
Page 202
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
500 Nose Gear Steering Lockout Pin Installation
Feb 20/87 Figure 202 32-00-01
Page 203
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
LANDING GEAR ELECTRICAL MODULE - DESCRIPTION AND OPERATION
1. General
A. The landing gear electrical module (Fig. 1) is a rack-mounted box containing the control and safety relays, solid-state circuits, and the necessary wiring and connectors. The module is located in the right equipment rack in the electrical/electronic equipment compartment.
B. Control and indication of the landing gear is accomplished primarily by proximity switches. The proximity switch is a solid-state switching circuit consisting of a sensor installed on the landing gear and solid-state circuits in the landing gear electrical module. The sensor is a proximity sensor that senses the proximity of a metal actuator, or conversely, the absence of the actuator, and thus provides the appropriate signal to a solid-state circuit in the module. The sensor and solid-state circuit function together as a switch. The solid-state circuit uses the signal from the sensor to control the relays. The relays in turn provide the required control and indication of the landing gear.
C. The module contains air and ground sensing test switches and lights to check for malfunction in the module and to isolate the safety relays for maintenance purposes. The air sensing test switch and the ground sensing test switch are also used to simulate an airplane-in-air condition. The various airplane systems normally used while the airplane is airborne, with the exception of landing gear operation, can be operated when the air and ground sensing test switches are actuated. When the switches are released, the systems return to airplane-in-ground position. The red air and ground sensing test lights show use of the test switches during maintenance and also indicate malfunction in the module. If a test light is on when the airplane is on the ground and the corresponding test switch is not being used, a malfunction in the module is indicated.
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