(2)
At the captain or observer crew station the No. 1 VHF radio would be operative; and at the F/O crew station the No. 2 VHF radio would be operative.
D. When a radio system is selected, the MIC SELECTOR switch will activate system audio and close circuit connections to allow the control wheel MIC or audio selector panel R/T switch to key the radio transmitter.
5C8
Jun 20/88 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 23-53-02 Page 3
DECOUPLED STATIC DISCHARGERS - DESCRIPTION AND OPERATION
1. General
A. Decoupled static dischargers are installed on the airplane to reduce interference in the radio receivers. This radio interference is caused by corona discharges emitted from the airplane surfaces as a result of precipitation static and engine charging. Precipitation static results from an electric charge accumulated by the airplane striking charged air and moisture particles. Static usually discharges at the wing and tail extremities and is coupled into the radio receiver antennas. The static dischargers are designed to discharge the static at points which are a critical length away from the wing and tail extremities where there is little or no coupling of static into the radio receiver antennas.
B. Each discharger installed along the trailing edges of the wing and tail surfaces consists of a bundle of metal needles at the end of a slender rod (Fig. 1). The rod is coated with a resistive (conducting) material and is attached to a metal base. The base is riveted and bonded to the trailing edge surface. The wingtip dischargers are smaller than the wing and tail dischargers, but have the same general construction and are attached in the same manner.
C. The vertical fin has a tip discharger and three trailing edge dischargers. Each horizontal stabilizer has a tip discharger and two trailing edge dischargers. Each wing has a tip discharger and three trailing edge dischargers (Fig. 1).
507
Aug 01/74 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 23-61-0 Page 1
H20712
Decoupled Static Discharger Locations 501
23-61-0 Figure 1 Aug 01/74
Page 2
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
DECOUPLED STATIC DISCHARGER - REMOVAL/INSTALLATION
1. Equipment and Materials
A. Sealant (Fiberglass Laminates) - BMS 5-95, Coast Pro-Seal Teledyne Co., 19451 Susanna, Compton, California 90221
B. Sealant (Aluminum Skin) - BMS 5-95, Products Research Corp., 5426 San Fernando Rd, Glendale, California 91203
C. Cleaning Solvent - B01008 Final cleaning of Metal Prior to Non-structural Bonding (Series 88) (Ref. 20-30-88).
D. Putty - DUXSEAL, Johns Manville Co.
E. Stripper - Turco 5351, Turco Products Inc., Wilmington, California
F. Aluminum oxide paper -600, 400, 180 grit
G. Infrared Lamp - 350 watts, or Heat Clamp, 610-1013 Granger Associates, or Hot Air Blower -Master Appliance Incorporated, Model 12500
H. Masking tape - 1 inch
I. Grease pencil -or other nondestructive marker
J. Polyvinyl Alcohol Film (if heat clamp is used) - 610-1018, Granger Associates
K. Thermocouple and temperature indicator -60- to 130-degree range
L. Shore A Durometer - Hardness 35 to 60
M. Megohmmeter (500 VDC Test Voltage, maximum 5 milliampere short circuit current) -Quadtech 1863 megohmmeter (or equivalent)
N. Rivets or screws
O. Bonding Meter (Ref 20-22-01)
P. Broad-bladed putty knife and plastic scraper
May 01/03 23-61-0 Page 401 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
H20735 H20737
Decoupled Static Discharger Base Replacement 501
23-61-0 Rivet or Screw Locations Aug 01/74
Page 402 Figure 401 (Sheet 1)
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
501 Decoupled Static Discharger Base Replacement
Aug 01/74 Rivet or Screw Locations 23-61-0
Figure 401 (Sheet 2) Page 403
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
2. Remove Static Discharger Base (Fig. 401)
A. Prepare to remove Static Discharger Base.
(1)
Remove pressure and power from the hydraulic systems for the applicable flight control surfaces (Ref 27-11-0 MP, 27-21-0 MP, 27-31-0 MP).
WARNING: MAKE SURE PRESSURE IS REMOVED FROM HYDRAULIC SYSTEMS. MAKE SURE HYDRAULIC POWER AND ELECTRICAL POWER ARE NOT SUPPLIED. IF HYDRAULIC PRESSURE IS PRESENT OR HYDRAULIC / ELECTRICAL POWER IS SUPPLIED, THE FLIGHT CONTROL SURFACES CAN MOVE. THIS CAN CAUSE INJURY TO PERSONS OR DAMAGE TO EQUIPMENT. 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 通讯 COMMUNICATIONS(47)
