(a) Make sure the ATC test set shows PASSED and the selected ATC code is shown on the code field.
(2)
Push and release the IDENT switch on the ATC control panel.
(a) Make sure the ATC test shows ID in the code field for 15 to 30 seconds.
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K. Altitude Reporting Test
(1)
On ATC control panel, select ALT RPT and ALT source.
(2)
Connect air data test set to captain's (No. 1) PITOT/STATIC system (AMM 34-11-0/501).
(3)
Adjust captain's altimeter to 29.92 inches of mercury.
(4)
Position test set mode switch to A/C ALT.
NOTE: In A/C ALT position, numerical display of test set will indicate airplane altitude in thousand feet, being reported by transponder.
In following tests ALT INVALID light shall remain off. When on, this light indicates an unassigned altitude code is being transmitted.
(5) Using air data test set, apply a static pressure to obtain altitude reading on test set as specified in following table. Verify captain's altimeter indicates士125 feet of test altitude.
TABLE ALTITUDE REPORTING TEST ALTITUDES
ALT Feet CODE
1,000 0320
4,100 4730
15,700 3440
31,000 1024
L. Repeat steps D thru K for No. 2 ATC transponder (if installed).
M. Repeat step K if ATC system has ALT source 1-2 selection. ATC SYSTEM DESCRIPTION AND OPERATION
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EFFECTIVITY
GJ B-2524
1. General (Fig. 1)
A. The ATC (Air Traffic Control) system, when interrogated by a signal from a ground station, automatically transmits a coded signal to the ground station. This coded signal is then displayed on the ground station radar indicator and shows the identity of the aircraft as well as its range and bearing.
B. Two complete systems are installed; each consisting of a transponder, a transponder adapter, and an antenna. A dual control panel is installed to operate the systems (Fig. 1). ATC No. 1 transponder receives 115-volt ac power through ATC-1 circuit breaker on P18 left load control center. ATC No. 2 transponder receives 115-volt ac power through ATC-2 circuit breakers on P6 right load control center.
2. ATC Control Panel (Fig. 1)
A. The ATC control panel is common to both ATC 1 and ATC 2 transponders. The control module contains controls, switches, and indicators to permit the pilot to operate and monitor the ATC system.
B. The four identification coding select switches set the 4-digit code in the display window. The TEST switch when pressed simulates a received interrogation. The REPLY light indicates that the transponder is transmitting coded replies. The fault light indicates that failure has been monitored in the ATC transponder or antenna. The IDENT switch when pressed causes an identification pulse to be inserted in each transmitted reply. The position of the function select switch determines the operational status of the ATC transponder - standby (STBY) or ON (1 or 2), The position of the ALT RPTG switch determines whether CADC 1 or CADC 2 (position 1 or 2) supplies altitude data to the ATC system or no-reporting is supplied (OFF).
C. The control module receives a 0- to 5-volt ac signal from the lights dimmer control through the 5V AC SEC circuit breaker on the P8 panel (Ref Chapter 33, Pilots' Panel Lights).
3. ATC Transponder (Fig. 1)
A. Each ATC transponder is a 3/8-ATR short shelf-mounted unit located on the electronic equipment rack E2, shelf No. 2. It contains solid-state components located on printed circuit card assemblies and a power supply. Electrical connections are made to the unit through a multipin connector on the rear panel. An auxiliary connector located on the upper portion of the rear panel is provided for automatic test equipment.
B. The ATC and DME systems operate in the same L-Band frequency. To prevent interference between systems, a suppression system is designed to allow only one interrogator or transponder to transmit at any one time.
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BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
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