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32-35-21 ALL ú ú 01 Page 404 ú Mar 15/92 BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details. A 737-300/400/500MAINTENANCE MANUAL (b) Bend one end of the cotter pin into the end of the drum. S 434-017 (6) Connect the cable MNGEA at turnbuckle. S 834-018 (7) Adjust the cable to 100 pound rig load. NOTE:____ When you do step G, make sure that the release handle is correctly engaged in the V-slot of the manual extension control.
S 434-019 (8) Connect the return spring to the torque tube quadrant (7).
(9) Adjust the manual extension system (Ref 32-35-00/501).
(10) Do a test on the manual extension system (Ref 32-35-00/501).
(11) Install the seal (8) on the wheel well ceiling of the nose landing gear.
(12) Install the cabin floor panel (12).
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32-35-21 ALL ú ú 01 Page 405 ú Mar 15/92 BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details. A 737-300/400/500MAINTENANCE MANUAL WHEELS AND BRAKES - DESCRIPTION AND OPERATION _____________________________________________ 1. General_______ A. The airplane is supported during landing, takeoff, and ground operations on six wheel and tubeless tire assemblies. Four are on the main landing gear and two on the nose landing gear. Each main wheel is provided with a brake unit bolted to a flange on the axle. The brakes are multiple disc type, with stationary carrier and divided lining discs, and segmented rotating brake discs. Each brake is provided with pistons which actuate the brakes when hydraulic pressure is applied. The brakes are also provided with combination return springs and automatic adjusters. The automatic adjusters compensate for brake wear. EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
32-40-00 ALL ú ú 01 Page 1 ú Jun 25/84 BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details. A 737-300/400/500MAINTENANCE MANUAL HYDRAULIC BRAKE SYSTEM - DESCRIPTION AND OPERATION __________________________________________________ 1. General_______ A. The hydraulic braking system aids airplane control during ground operations. The Brakes hold the airplanes during parking, mooring, and engine run. They stop the wheel spin after takeoff, shorten the landing run, and assist in turning when the airplane is taxied. B. The brake system is manually controlled by the captain's or first officer's rudder pedals through linkage and cables to the brake metering valve for each main gear. Each brake metering valve directs B system hydraulic pressure up to 3000 psi to the brakes of the main gear it serves. An antiskid system and an automatic braking system are incorporated into the manual braking system (AMM 32-42-00, Antiskid System - Description and Operation; and 32-43-01, Automatic Braking System - Description and Operation). C. The hydraulic brake system consists of system control cables and linkages, alternate brake selector valve, accumulator isolation valve, brake metering valves, brake feel augmentors, related antiskid/autobrake units, shuttle valves, hydraulic fuses, main gear brake swivels, disk-type brakes, hydraulic pressure accumulator, transmitters and gages (Fig. 1). A parking brake shutoff valve, covered in 32-44-00, and antiskid control valves, covered in 32-42-00, are mentioned in the operation of the brake system, but are considered components of the parking brake system and the antiskid system, respectively. Automatic braking system components, autobrake control panel, two shuttle valves, autobrake digital circuits, an autobrake pressure control module and four pressure switches are installed in the hydraulic system. These components are mentioned in operation of the brake system, but are part of the automatic braking system and are covered in 32-43-01. The brakes are of the rotating disk type and are self-adjusting. The hydraulic pressure accumulator is charged to 3000 psi to provide braking pressure for parking or whenever the main hydraulic systems are depressurized. The accumulator pressure transmitter provides a brake system hydraulic pressure indication on a remote gage in the control cabin. The brakes are applied automatically to stop the spinning main gear wheels when the landing gear is retracted. A snubber is provided in the nose wheel well to stop the spinning nose wheels (AMM 32-45-00). 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 3
