Telephonics Corporation
R
A D A R
S
Y S T E M S
D
I V I S I O N
TM113806 (3/10)
2-27
2.4.2
Location of Equipment
The locations chosen for units of the RDR-1700A Radar System, and the method of installation, will
vary with each particular type of aircraft.
The units should be installed in a convenient location for ease of operation and accessibility for
inspection and maintenance. The area should be free from excessive vibration, heat, and noise
generating sources. In addition, since all radar receiver-transmitter units are high-power pulse
generating devices, they are potential sources of radio-frequency interference (RFI); consequently,
consideration to this factor should be given when selecting a location for the RT unit. The cable should
not be bundled with automatic-direction-finder (ADF) loop lines. Other restrictions on unit locations
are those imposed by transmission line and waveguide length limits. It is recommended that total
waveguide length should be held to a maximum of 10 feet, including bends.
2.4.3 Lighting
Bus
The aircraft lighting bus will control the menu select push buttons on the bezel of the display. The
lighting bus will not control the brightness of the display. Control buttons on the display will control
the brightness of the display. Each display will require 0 to 5 Vdc, 20 mW.
2.4.4 Power
Requirements
The aircraft shall provide 28 VDC at 9 Amps (252 Watts) when dual indicators are installed. It is
recommended that a 15 Amp Circuit Breaker be used to protect the radar system.
The aircraft shall also provide 115 VAC, 400 Hz at 220 mA (25.3 VA). Since the IU-1507B will
generate the Pitch and Roll signals used by the DA-1503B, the phase may be different than the Gyro
Reference phase. It is recommended that a 2 Amp circuit breaker be used to protect the radar system.
2.4.5
Roll and Pitch Information
The system requires roll and pitch output voltages from the vertical gyro for operation of the antenna
stabilization system. It is important that the connections to the vertical gyro outputs be made according
to the system inter-wiring diagram, Figure 2.4.1-11. The stabilization servo system of the RDR-
1500B+ Radar System requires ARINC 429 AHRS data. Phase relationship between the 115V 400 Hz
reference and the pitch and roll input signals is important.
For pitch, an aircraft nose-down attitude
must result in a signal at the antenna connector that is in phase with the 115V 400 Hz reference.
Similarly, a right roll attitude must result in a roll signal that is in phase with the reference.
The document reference is online, please check the correspondence between the online documentation and the printed version.
