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A. The Air Traffic Control Radar Beacon System, (ATC system), provides airplane tracking, altitude and identification information to an ATC ground station. The ATC transponder responds to an interrogation from an ATC ground station. The ATC system responds to ground station interrogations in one of three different modes: mode-A, mode-C and mode-S. Mode-A and Mode-C provide identification and altitude information. Mode-S provides selective airplane identification and data link capabilities. After a ground station interrogation, the transponder automatically transmits a pulse coded reply signal in one of the above modes. The mode of reply is determined by the mode of interrogation.
B. Two ATC systems are installed on the airplane, each with its own transponder. Only one transponder operates at a time. A dual ATC control panel provides independent and isolated control for both systems. Control information is sent to either transponder by signal discretes and an ARINC 429, 572, 718, or 730 bus.
C. There are two ATC antennas on the airplane. The antennas are shared by the two transponders. Two rf relays switch both antennas from one transponder to the other.
D. Each transponder receives altitude data from both air data computers (ADCs). The altitude data is sent to the transponders by an ARINC data bus.
E. The ATC and DME systems operate in the same L-band frequency range. A suppression circuit is connected between the ATC transponders and the DME interrogators to prevent simultaneous transmissions.
F. The ATC system operates in three different modes: Mode-A, mode-C and mode-S. The mode of operation is determined by the mode of interrogation from a ground station and the current configuration of the altitude reporting function.
G. The No. 1 ATC system receives 115 volt, 400 Hz ac power from the electronics power bus No. 1. Power is supplied through the ATC-1 circuit breaker located on the left load control center circuit breaker panel P18.
H. The No. 2 ATC system receives 115 volt, 400Hz ac power from the electronics power No. 2 bus. Power is supplied through the ATC No. 2 circuit breaker which is located on the right load control center circuit breaker panel P6.
2. ATC Control Panel (Fig. 1)_________________
A. The ATC control panel is located on the aft electronic control panel (P8). The control panel contains switches and controls which provide reply codes and mode selection for two ATC/Mode S transponders. The control panel is divided into two operational sides left (No. 1) and right (No. 2). Each side operates independently of the other. Each side provides its respective transponder with tuning and control signals for system operation.
(1) The control panel has these switches and indicators:
(a) Four code switches which select the four-digit ATC identification code.
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A
737-300/400/500MAINTENANCE MANUAL
ATC NO. 1 TRANSPONDER
SEE B
ANTENNA SWITCH
SEE C
ELECTRONIC EQUIPMENT RACK
ATC NO. 2 TRANSPONDER
SEE B
ANTENNA AFT ELECTRONIC
SWITCH CONTROL PANEL SEE C SEE A
TRANSPONDER ALTITUDE SELECTED CODE SELECT IDENTIFICATION REPORTING DISPLAY SWITCH SWITCH SWITCH
ALT RPTG FAULT IDENT
1 2
OFF
ATC-S STBY
1 2 FAULT
TEST TEST INDICATOR
AB CD
CODE SELECT
SWITCHES ATC CONTROL PANEL
A
TEST SWITCH
ANTENNA SWITCH C ATC System Component Location Figure 1
ATC TOP ANTENNA (STA 430.25)
ATC BOTTOM ANTENNA (STA 355)
PASS
TPR
FAIL UPPER ANT LOWER ANT ALT CTL
TEST
ATC TRANSPONDER
B
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
(b)
A four-digit code display window which shows the selected identification code.
(c)
A five position transponder select switch (TEST/1/STBY/2/TEST) which set the left or right transponder for use, or set both transponders to standby. The TEST positions allow a self test either transponder to be performed.
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