Telephonics MCB-RT-1601 Color Weather and Search and Rescue Radar User Manual 106601 601

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RADAR 1600
WEATHER RADAR SYSTEM
INSTALLATION MANUAL
July 2001
Prepared by:
TELEPHONICS CORPORATION
815 Broad Hollow Road
Farmingdale, New York 11735
USA
TM106601 (7/01)
C OMMAND S YSTEMS D IVISION
RDRRDR-1600
WEATHER RADAR SYSTEM
INSTALLATION MANUAL
Copyright © 1995/2001 Telephonics Corporation
Publication No.: TM106601
All Rights Reserved
Printed in U.S.A.
Telephonics Corporation, Command Systems Division (CSD)
815 Broad Hollow Road, Farmingdale, New York 11735
Telephone: (877) 517-2327 Fax: (877) 755-7701
This publication may not be reproduced in part or in whole without the
expressed written consent of Telephonics Corporation.
TM106601 (7/01)
COMMAND SYSTEMS DIVISION
CAUTION
Maintain prescribed safe distance when standing
in front of radiating antenna.
Never expose eyes or any part of the body to an
unterminated wave guide.
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COMMAND SYSTEMS DIVISION
MAXIMUM PERMISSIBLE EXPOSURE LEVEL (MPEL)
In order to avoid the envelope in which the radiation level exceeds the U.S. Government standard of
1 mW per square centimeter, all personnel should remain beyond the distance indicated in the
illustration below. The distance to the MPEL boundary is calculated upon the basis of the largest
antenna available with the RDR-1600 system, rated output power of the transmitter and in the nonrotating or boresight position of the antenna. With a scanning beam, the power density at the MPEL
boundary is significantly reduced.
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COMMAND SYSTEMS DIVISION
INSTALLATION MANUAL
RDR-1600 WEATHER RADAR SYSTEM
AC
DATE
20-68B
8/8/80
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
Washington, D.C.
—————————————————————————————————
—————————————————————————————————
Subject:
RECOMMENDED RADIATION SAFETY PRECAUTIONS FOR GROUND OPERATION OF
AIRBORNE WEATHER RADAR
1.
PURPOSE. This circular sets forth recommended radiation safety precautions to be taken by
personnel when operating airborne weather radar on the ground.
2,
CANCELLATION. Ac 20-68A, dated April 11, 1975, is canceled.
3.
RELATED READING MATERIAL.
a. Barnes and Taylor, Radiation Hazards and Protection (London: George Nevnes Limited, 1963).
P. 211.
b. U.S. Department of Health, Education and Welfare, Public Health Service, Consumer
Protection and Environmental Health Service, “Environmental health microwave, ultraviolet radiation and
radiation from lasers and television receivers – An Annotated Bibliography,” FS 2.300: RH-35,
Washington, U.S. Government Printing Office, pp. 56-57.
c. Mumford, W.W., “Some technical aspects of microwave radiation hazards,” Proceedings of the
IRE, Washington, U.S. Government Printing Office, February 1961, pp. 427-447.
4.
BACKGROUND. Dangers from ground operation of airborne weather radar include the possibility
of human body damage and ignition of combustible materials by radiated energy. Low tolerance parts of
the body include the eyes and testes.
5.
PRECAUTIONS. Management and supervisory personnel should establish procedures for advising
personnel of dangers from operating airborne weather radars on the ground. Precautionary signs should
be displayed in affected areas to alert personnel of ground testing.
a. GENERAL.
(1)
Airborne weather radar should be operated on the ground only by qualified personnel.
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COMMAND SYSTEMS DIVISION
INSTALLATION MANUAL
RDR-1600 WEATHER RADAR SYSTEM
AC 20-68B
8/8/80
(2) Installed airborne radar should not be operated while the aircraft is in a hangar or other
enclosure unless the radar transmitter is not operating, or the energy is directed toward an absorption
shield which dissipates the radio frequency energy. Otherwise, radiation within the enclosure can be
reflected throughout the area.
b. Body Damage. To prevent possible human body damage, the following precautions should be
taken:
(1) Personnel should never stand nearby and in front of a radar antenna which is
transmitting. When the antenna is not scanning, the danger increases.
(2) A recommended safe distance from operating airborne weather radars should be
established. A safe distance can be determined by using the equations in Appendix 1 or the graphs of
figures 1 and 2. This criterion is now accepted by many industrial organizations and is based on limiting
exposure of humans to an average power density not greater than 10 milliwatts per square centimeter.
(3)
turned off.
Personnel should be advised to avoid the end of an open waveguide unless the radar is
(4) Personnel should be advised to avoid looking into a waveguide, or into the open end of a
coaxial connector or line connector to a radar transmitter output, as severe eye damage may result.
(5) Personnel should be advised that when high power radar transmitters are operated out of
their protective cases, X-rays may be emitted. Stray X-rays may emanate from the glass envelope type
pulser, oscillator, clipper, or rectifier tubes, as well as magnetrons.
c. Combustible Materials. To prevent possible fuel ignition, an installed airborne weather radar
should not be operated while an aircraft is being refueled or defueled.
M.C. BEARD
Director of Airworthiness
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COMMAND SYSTEMS DIVISION
INSTALLATION MANUAL
RDR-1600 WEATHER RADAR SYSTEM
AC NO:
43-14
DATE:
2/24/77
DEPARTMENT OF TRANSPORTATION
FEDERAL AVIATION ADMINISTRATION
SUBJECT: MAINTENANCE OF WEATHER RADAR RADOMES
—————————————————————————————————
1.
PURPOSE. This advisory circular provides guidance material useful to repair facilities in the
maintenance of weather radar radomes.
2.
CANCELLATION. AC 43-202, dated 6/11/65, and AC 90-20, dated 11/12/64, are cancelled.
3.
GENERAL. A radome is a covering whose primary purpose is to protect a radar antenna from the
elements. It is a part of the airframe and, therefore, should have certain physical as well as
electrical properties. Physically, a radome should be strong enough to withstand the airloads that it
will encounter and it should be contoured to minimize drag. These properties vary with the shape,
design speed, and size of the airplane on which it is to be installed. Electrically, a radome should
permit the passage of the radar’s transmitted signals and return echoes with minimum distortion
and absorption. In order to do this, it should have a certain electrical thickness. The electrical
thickness of a radome is related to the physical thickness, operating frequency, and the types of
material and construction used. This relationship is defined by a number of complex mathematical
equations which are of interest only to radome design engineers. These equations show that, for
given physical properties, a radome should have a certain electrical thickness for a certain narrow
range of operating frequencies. (This is the reason why C-band radomes will not give optimum
performance with X-band radars and vice versa.) Also, a very small variation in physical thickness
may cause a sizable variation in electrical thickness. Radar efficiency, definition, and accuracy of
display depend upon a clear, nondistorted, reflection-free antenna view through the radome.
Consequently, a radome should be precisely built for optimum performance.
4.
RADOME CHARACTERISTICS. There are two general types of radomes, the “thin wall” and
“sandwich” types. Thin wall radomes are considered to be thin relative to the wavelength of the
radar. They are generally useful when the radar frequency is low enough to permit a skin
thickness which will satisfy the structural requirements. Sandwich radomes consist of two
—————————————————————————————————
Initiated by: AFS-804
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COMMAND SYSTEMS DIVISION
INSTALLATION MANUAL
RDR-1600 WEATHER RADAR SYSTEM
AC 43-14
2/24/77
or more plastic skins separated by a dielectric core. The core may consist of honeycomb plastic
section, hollow flutes, or foam plastic. The dielectric and separation of the skins will depend
upon the wavelength of the radar frequency or frequencies.
5.
RADOME DAMAGE. Probably the most frequent damage to radomes is holes in the structure
caused by static discharges. These can be large holes that are readily apparent, or small pin
holes that are almost imperceptible. Any hole, regardless of size, can cause major damage to a
radome since moisture can enter the radome wall and cause internal delamination. If the
moisture freezes, more serious damage may occur. If enough moisture collects, the radiation
pattern will be distorted and the transmitted signals and return echoes seriously attenuated.
Ram air through a hole can delaminate and break the inner surface of the radome and result in
separation of the skins or faces of the material from the core, weakening the radome structure.
Other types of damage are characterized as dents and scratches caused by impact with stones
and birds and improper handling of the radome when it is removed for maintenance of the radar
antenna. This type of damage is easily found by inspection.
6.
MAINTENANCE.
a. High performance radar radomes are very precisely constructed and sometimes the
slightest change in their physical characteristics, such as excessive layers of paint, can
adversely affect radar system performance. All repairs to radomes, no matter how minor,
should return the radome to its original or properly altered condition, both electrically and
structurally. The performance of proper maintenance to precision radomes requires special
knowledge and techniques and the use of proper tools and materials. An improper minor
repair can eventually lead to an expensive major repair. A radome having undergone major
repairs should be tested to ascertain that its electrical properties have not been impaired.
The testing of radomes requires test equipment that usually is found only in repair facilities
specializing in radome maintenance. Even minor repairs may affect one or all of the
following:
(1) Transmissivity. Which is the ability of a radome to pass radar energy through it.
(2) Reflection. Which is the return or reflection of the outgoing radar energy from the
radome back into the antenna and waveguide system
(3) Diffraction. Which is the bending of the radar energy as it passes through the radome.
b. These electrical properties, when altered by improper repair, may cause loss of signal,
distortion and displacement of targets, and can clutter the display to obscure the target. Poor
radome
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COMMAND SYSTEMS DIVISION
INSTALLATION MANUAL
RDR-1600 WEATHER RADAR SYSTEM
2/24/77
AC 43-14
electrical performance can produce numerous problems which may appear to be symptoms of
deficiencies in other units of the radar system. The following are examples of improper repair:
(1)
Use of wrong materials - not compatible with original radome materials.
(2)
Patches of different thickness.
(3)
Poor fabrication techniques.
(4)
Nonvoid-free patches
(5)
Repairs overlapping.
(6)
‘Holes plugged with resin, screws, metal, wood, and plastic plugs.
(7)
Cuts or cracks simply coated with resin
(8)
Tape (including electrical tape) over hole or crack and covered with resin.
(9)
Oversize patches.
(10)
Too much or too little resin
(11)
Exterior coatings - too many coats, too thick, uneven thickness - metallic base paints
(12)
Filled honeycomb cells.
(13)
Repairs made without removing moisture or moisture contamination from inside of
radome wall.
(14)
Abrupt changes in cross-sectional areas.
(15)
Patches projecting above outside contour lines.
(16)
Improper cure.
(17)
Wrong size cells or density of honeycomb.
(18)
Excessive overlap in honeycomb joints.
(19)
poor bonding of skin to core.
(20)
Gaps in honeycomb core.
Par 6
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COMMAND SYSTEMS DIVISION
INSTALLATION MANUAL
RDR-1600 WEATHER RADAR SYSTEM
AC 43-14
2/24/77
7. RECOMMENDATION. Both the physical and electrical properties of radomes should be given
careful consideration during repair operations. These properties are carefully controlled during
manufacture and should not be altered by improper repairs.
J.A. FERRARESE
Acting Director, Flight Standards Service
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COMMAND SYSTEMS DIVISION
TABLE OF CONTENTS
PARAGRAPH
CHAPTER 1.
1.1
1.1.1
1.1.2
1.1.2.1
1.1.2.2
1.1.2.3
1.1.2.4
1.2
1.2.1
1.2.2
1.2.2.1
1.2.2.2
1.2.2.3
1.3
1.3.1
1.3.2
1.4
1.4.1
1.4.2
1.4.3
1.4.4
1.4.5
1.5
1.5.1
1.5.2
1.5.3
1.5.4
1.5.5
1.6
1.6.1
1.6.2
1.6.3
1.6.3.1
1.6.3.2
1.6.4
1.6.4.1
1.6.4.2
1.6.4.3
1.6.4.4
1.6.4.5
TITLE
PAGE
GENERAL INFORMATION ....................................................................................... 1-1
GENERAL ERROR! BOOKMARK NOT DEFINED.
Basic System Functions ..................................................1-Error! Bookmark not defined.
Operational Modes..........................................................1-Error! Bookmark not defined.
Search Modes ..................................................................1-Error! Bookmark not defined.
Weather Avoidance Modes .............................................1-Error! Bookmark not defined.
Beacon Mode...................................................................1-Error! Bookmark not defined.
Dual Mode of Operation .................................................1-Error! Bookmark not defined.
EQUIPMENT PART NUMBERS AND DESCRIPTIONS .............................................. 1ERROR! BOOKMARK NOT DEFINED.
RDR-1600 System Components.....................................1-Error! Bookmark not defined.
CP-113 Unit Description ................................................1-Error! Bookmark not defined.
CP-113 Function Select Switch ......................................1-Error! Bookmark not defined.
CP-113 Mode Push Buttons ...........................................1-Error! Bookmark not defined.
CP-113 Additional Switches and Controls.....................1-Error! Bookmark not defined.
ADDITIONAL EQUIPMENT REQUIRED FOR COMPLETE INSTALLATION........ 1ERROR! BOOKMARK NOT DEFINED.
Additional Available Equipment ....................................1-Error! Bookmark not defined.
Equipment Required But Not Supplied ..........................1-Error! Bookmark not defined.
LEADING PARTICULARS ......................1-ERROR! BOOKMARK NOT DEFINED.
RDR-1600 Radar System ...............................................1-Error! Bookmark not defined.
RT-1601 Receiver Transmitter.......................................1-Error! Bookmark not defined.
DA-1203A Antenna Drive..............................................1-Error! Bookmark not defined.
CP-113 Radar Control Panel ..........................................1-Error! Bookmark not defined.
Antennas..........................................................................1-Error! Bookmark not defined.
SYSTEM COMPONENT DESCRIPTION1-ERROR! BOOKMARK NOT DEFINED.
General ............................................................................1-Error! Bookmark not defined.
RT-1601 Receiver Transmitter.......................................1-Error! Bookmark not defined.
DA-1203A Antenna Drive..............................................1-Error! Bookmark not defined.
CP-113 Radar Control Panel ..........................................1-Error! Bookmark not defined.
Antennas..........................................................................1-Error! Bookmark not defined.
EQUIPMENT OPERATION AND CONTROLS ............................................................. 1ERROR! BOOKMARK NOT DEFINED.
Operating Precautions.....................................................1-Error! Bookmark not defined.
License Requirements .....................................................1-Error! Bookmark not defined.
Operating Controls and Display Features.......................1-Error! Bookmark not defined.
CP-113 Operating Controls ............................................1-Error! Bookmark not defined.
MFD Display...................................................................1-Error! Bookmark not defined.
Operating Procedures......................................................1-Error! Bookmark not defined.
General ............................................................................1-Error! Bookmark not defined.
Turn On Procedure..........................................................1-Error! Bookmark not defined.
Primary Mode Selection Procedures (WX, WXA, SR1, SR2, SR3, BCN) ....................... 1Error! Bookmark not defined.
Range Selection Procedure..............................................1-Error! Bookmark not defined.
Stabilization (STAB OFF) Control Procedure ...............1-Error! Bookmark not defined.
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COMMAND SYSTEMS DIVISION
1.6.4.6
1.6.4.7
1.6.4.8
1.6.4.9
TEST Pattern Selection Procedure..................................1-Error! Bookmark not defined.
60° Scan Selection Procedure .........................................1-Error! Bookmark not defined.
Beacon Mode Selection (BCN).......................................1-Error! Bookmark not defined.
Two-Pulse Beacon Interrogation and Codes ..................1-Error! Bookmark not defined.
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COMMAND SYSTEMS DIVISION
TABLE OF CONTENTS
[continued]
PARAGRAPH
1.6.4.10
1.6.4.11
1.7
CHAPTER 2.
2.1
2.2
2.3
2.4
2.4.1
2.4.2
2.4.3
2.4.4
2.5
2.5.1
2.5.1.1
2.5.1.2
2.6
2.6.1
2.6.2
2.6.3
2.6.3.1
2.6.3.2
2.7
2.7.1
2.7.2
2.7.3
2.7.4
2.7.4.1
2.7.4.2
2.7.4.3
2.7.5
2.7.6
2.8
2.8.1
2.8.1.1
2.8.1.2
2.8.2
2.8.2.1
2.8.2.2
2.8.2.3
2.8.2.4
2.8.2.5
2.9
TITLE
PAGE
DO-172 Six-Pulse Beacon Interrogation........................1-Error! Bookmark not defined.
Target Alert Function......................................................................................................1-31
ASSOCIATED PUBLICATIONS ...........1-3ERROR! BOOKMARK NOT DEFINED.
INSTALLIATION.......................................................................................................... 2-1
GENERAL ........................................................................................................................2-1
UNPACKING ...................................................................................................................2-1
PRE-INSTALLATION CHECK ......................................................................................2-1
INSTALLATION PLANNING........................................................................................2-1
Outline and Interconnect Drawings ..................................................................................2-1
Location of Equipment......................................................................................................2-2
Primary Power Requirements ...........................................................................................2-2
Roll and Pitch Information................................................................................................2-2
INSTALLATION OF SYSTEM COMPONENTS .........................................................2-3
Radar Antenna...................................................................................................................2-3
Assembly of Antenna Array and Antenna Drive Assembly Procedure............................2-3
Installation of DA-1203A Antenna Assembly Procedure ................................................2-3
POST-INSTALLATION CHECK ...................................................................................2-4
Installation of RT-1601 Receiver Transmitter .................................................................2-5
Installation of CP-113 Radar Control Panel.....................................................................2-5
Installation of Waveguide and Cables ..............................................................................2-6
Cabling ..............................................................................................................................2-6
Waveguide.........................................................................................................................2-6
POST-INSTALLATION CHECK ...................................................................................2-8
Visual Inspection Procedure .............................................................................................2-9
Control Panel and MFD Display Check Procedure in Test Mode....................................2-9
Antenna Stabilization Check...........................................................................................2-10
Antenna Checkout Aids ..................................................................................................2-13
Tilt Check Procedure.......................................................................................................2-13
Pitch Calibration Check Procedure .................................................................................2-13
Roll Calibration Check Procedure ..................................................................................2-14
RF Operation Check Procedure ......................................................................................2-15
Interference Test Procedure ............................................................................................2-16
PREFLIGHT CHECK AND FLIGHT CHECK PROCEDURES ................................2-16
Preflight Check Procedure ..............................................................................................2-16
Single Indicators..............................................................................................................2-16
Multiple Displays............................................................................................................2-19
Flight Check Procedure...................................................................................................2-19
Check Test Pattern ..........................................................................................................2-19
Check And Adjust Antenna Stabilization.......................................................................2-20
Check Weather Alert Mode ............................................................................................2-21
Check Target Alert..........................................................................................................2-21
Testing Completed ..........................................................................................................2-22
ILLUSTRATIONS AND DRAWINGS.........................................................................2-22
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COMMAND SYSTEMS DIVISION
LIST OF ILLUSTRATIONS
FIGURE
Figure 1.5-1.
Figure 1.6-1.
Figure 1.6-2.
Figure 1.6-3.
Figure 1.6-4.
Figure 1.6-5.
Figure 2.7-1.
Figure 2.7-2.
Figure 2.9-1.
Figure 2.9-2.
Figure 2.9-3.
Figure 2.9-4.
Figure 2.9-5.
Figure 2.9-6.
Figure 2.9-7.
Figure 2.9-8.
Figure 2.9-9.
Figure 2.9-10.
TITLE
PAGE
1 RDR-1600 Radar System ............................................. 1-Error! Bookmark not defined.
CP-113A Radar Control Panel ........................................ 1-Error! Bookmark not defined.
CP-113K Radar Control Panel (With Brightness Pots) .. 1-Error! Bookmark not defined.
CP-113K Radar Control Panel (Without Brightness Pots)1-Error! Bookmark not defined.
CP-113P Radar Control Panel ......................................... 1-Error! Bookmark not defined.
Generic MFD Display (Radar Only Mode) ..................... 1-Error! Bookmark not defined.
Antenna Checkout Aids ....................................................................................................2-11
Radar control Panel...........................................................................................................2-12
Video Pattern, Level Flight ...............................................................................................2-23
Video Pattern With Stab Error..........................................................................................2-23
Video Pattern With Stab Error..........................................................................................2-23
Video Pattern, No Stabilization ........................................................................................2-23
RT-1601 Receiver Transmitter Outline Drawing.............................................................2-25
DA-1203A Antenna Drive Outline Drawing....................................................................2-27
CP-113 Radar Control Panel Outline Drawing ................................................................2-29
RDR-1600 System Wiring Diagram With Analog Gyros................................................2-31
RDR-1600 System Wiring Diagram With AHRS System...............................................2-33
DA-1203A Antenna Mount Hole Pattern.........................................................................2-35
LIST OF TABLES
TITLE
TABLE
Table 1.2-1.
Table 1.2-2.
Table 1.2-3.
Table 1.2-4.
Table 1.3-1.
Table 1.3-2.
Table 1.4-1.
Table 1.4-2.
Table 1.4-3.
Table 1.4-4.
Table 1.4-5.
Table 1.6-1.
Table 1.6-2.
Table 1.6-3.
Table 1.6-4.
Table 1.6-5.
PAGE
RDR-1600 System Components...................................... 1-Error! Bookmark not defined.
CP-113 Function Select Switch ....................................... 1-Error! Bookmark not defined.
CP-113 Mode Push Buttons ............................................ 1-Error! Bookmark not defined.
CP-113 Additional Switches and Controls...................... 1-Error! Bookmark not defined.
Additional Equipment Available ..................................... 1-Error! Bookmark not defined.
Equipment Required But Not Supplied ........................... 1-Error! Bookmark not defined.
RDR-1600 Radar System ................................................ 1-Error! Bookmark not defined.
Leading Particulars-8 RT-1601 Receiver Transmitter.... 1-Error! Bookmark not defined.
DA-1203A Antenna Drive............................................... 1-Error! Bookmark not defined.
CP-113 Radar Control Panel ........................................... 1-Error! Bookmark not defined.
Antennas........................................................................... 1-Error! Bookmark not defined.
CP-113 Function Select Switch Description ................... 1-Error! Bookmark not defined.
CP-113 Mode Button Description ................................... 1-Error! Bookmark not defined.
CP-113 Additional Switches Description........................ 1-Error! Bookmark not defined.
Typical Two-Pulse Beacon Transponder Pulse Spacing. 1-Error! Bookmark not defined.
DO-172 Beacon Transponder Codes............................... 1-Error! Bookmark not defined.
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COMMAND SYSTEMS DIVISION
RECORD OF REVISIONS
Revision
No.
Revision
Date
Insertion
Date
Notes
Original Issue – July 2001
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COMMAND SYSTEMS DIVISION
LIST OF EFFECTIVE PAGES
Page(s)
Subject
Date
Title
July 2001
Copyright
July 2001
FMi
Radiation Warning
July 2001
FMii
Max. Permissible
Exposure Level
July 2001
FMiii
AC 230-68B
July 2001
FMv
AC-43-14
July 2001
i – ii
Table of Contents
July 2001
iii
List of Illustrations
July 2001
iii
List of Tables
July 2001
List of Effective Pages
July 2001
vi
Service Bulletin List
July 2001
1-1 to 1-31
General Information
July 2001
2-1 to 2-37
Installation
July 2001
TM106601_(7/01)
Notes
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COMMAND SYSTEMS DIVISION
SERVICE BULLETIN LIST
Service Bulletin
No.
Related
Equipment
Date
Purpose
No RDR-1600 SB’s have been issued
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COMMAND SYSTEMS DIVISION
1.1
GENERAL
The Telephonics RDR-1600 Weather and Search and Rescue Radar System provides six primary
modes of operation: three air-to-surface search and detection modes, two radar weather avoidance
modes, and one navigational beacon mode. The navigational beacon has the capability to receive and
decode both standard 2-pulse and DO-172 6-pulse transponders.
The Telephonics RDR-1600 Weather and Search and Rescue Radar System are primarily designed
for fixed and rotary wing aircraft engaged in patrol, search and rescue missions, and for transporting
personnel and equipment to remote sites (off-shore oil rigs, etc.).
1.1.1
Basic System Functions
The RDR-1600 Radar System consists of three flight-line replaceable units (LRU): a ReceiverTransmitter (RT), Radar Control Panel (CP), and an Antenna Drive unit with antenna (DA). In
addition to the above LRUs, additional equipment (not supplied by Telephonics) is necessary to
operate the radar system. This additional equipment includes one or two Multifunction Displays
(MFD) which are necessary to display the radar data, modes of operation and controls. For antenna
stabilization, a gyro or Attitude Heading Reference System (AHRS) system is required.
The beacon mode requires that a tight tolerance magnetron be employed in the Receiver Transmitter for
reliable interrogation of beacon transponders. Also, special circuitry is incorporated in the Receiver
Transmitter unit to optimize the receiver portion to process narrow bandwidth weather targets.
All system controls are located on either the Radar Control Panel or the EFIS Display Unit. The
Radar Display Unit provides search gain, beacon gain, mode of operation, and antenna tilt control.
The EFIS Display Unit provides range information. Only one Radar Control Panel can be used in the
RDR-1600 radar system, but two EFIS displays can be employed. This will allow the pilots to select
gain, mode and tilt on the control panel. Different range values can be selected on each display for
the pilot and for the co-pilot.
The presentation of data on the MFD will vary from manufacturer to manufacturer. Refer to the
MFD manufacturer for the exact presentation of data on the display. In general, the MFD display
shall display in text format the modes of operation, beacon code selected, fault codes, antenna tilt,
search gain, and beacon gain. The range rings, range ring markers in nautical miles, and target data
shall be displayed in graphical format.
Built-in-test (BIT) circuits provide rapid checkout of system performance in the air or on the ground.
A TEST function, as selected on the radar control panel, is a user - initiated BIT to validate the
system operation. The RDR-1600 radar system runs Continuous BIT to detect a fault within the
system. If a fault should occur within the system, then a fault will be displayed in all modes of
operation.
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COMMAND SYSTEMS DIVISION
1.1.2
Operational Modes
1.1.2.1 Search Modes
There are 3 search modes available to the operator. Each mode has features to enhance detectability
in different scenarios. Search Mode 1 (SR1) can detect and display surface targets down to a
minimum range of 500 feet when a range selection of 10 nm or less has been selected. This mode
uses a short transmitted pulse and special clutter rejection circuitry and is designed for short-range
(i.e. 0.5, 1, 2, 5, and 10 nm) mapping of targets in a sea clutter environment. Once a range of 20 nm
or greater has been selected, then the transmitter will switch to a long pulse and the clutter rejection
circuit is disengaged (effectively becomes search mode 3).
Search Mode 2 (SR2) can detect and display surface targets down to a minimum distance of 500 feet
when a range of 10 nm or less has been selected. This mode uses a short transmitted pulse and is
designed for short-range (i.e. 0.5, 1, 2, 5, and 10 nm) precision ground mapping. Once a range of 20
nm or greater has been selected, then the transmitter will switch to a long pulse. Under these
conditions, SR2 effectively becomes search mode 3.
Search Mode 3 (SR3) is used for long-range ground mapping or searching for topographical features
such as bodies of water, islands, high ground, bridges, etc. This mode will return the greatest amount
of ground clutter. This mode can also be used for oil slick detection in calm to moderate sea states.
1.1.2.2 Weather Avoidance Modes
Weather Mode (WX) will display continuous enroute weather information relative to rain cloud
formation, rainfall rate, thunderstorms with moisture, and areas of icing conditions. Digital circuitry
provides a means for determining the relative density of the rainfall areas. With the display, the pilot
can see storm areas in the flight path and can also distinguish corridors of relative calm through the
storms.
The system detects the strong returns from high-density rainfall and converts them into red areas on
the radar display. Yellow areas that represent areas of lower rainfall rates usually surround these
areas. Areas with the lightest rainfall are green in the display.
A sensitivity timing control (STC) circuit ensures that the echo signals are displayed with approximately
equal intensity from similar targets at distances from near zero range to approximately 45 nm (12 inch
antenna array). The gain control for the weather mode is preset, and not selectable by the operator.
Weather Alert Mode (WXA) will cause the red areas of the display to flash at approximately 1.25 Hz
rate. The flashing of the red areas is a MFD function, and some MFDs are not capable of flashing the
red areas. If the MFD is not capable of flashing the red areas, then this function will not operate.
This mode will also active the Target Alert function within the RT-1601. The target alert function
will be activated if a red storm cell is detected within 25 nm beyond the selected range and within
±10° of boresight. This feature warns the pilot that a danger exists on the present flight path beyond
the selected range. This feature is also necessary to warn the pilot in the event that the pilot is not
looking at weather (navigation information, checklist, etc.) on the MFD display.
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COMMAND SYSTEMS DIVISION
1.1.2.3 Beacon Mode
In the beacon mode, the system can interrogate and receive pulses from a fixed transponder(s)
located within a range up to 160 nm. Maximum range will vary depending upon the receiver
sensitivity of the beacon, and transmitted power of the beacon. The coded replies are received on a
special beacon frequency (9310 MHz). The MFD will display the location, in range and bearing
relative to the aircraft, of beacon returns from both 2-pulse and DO-172 6-pulse transponders.
A special beacon code is assigned to each beacon signal received. The code can be displayed to
identify a particular beacon reply on the screen. The beacon decoding ranges are different for the
two types of beacons. The 2-pulse beacon can only be identified when the indicator is in the 2, 5, 10,
20, 40 or 80 nm range. The DO-172 6-pulse beacon replies can only be identified when the indicator
is in the 2, 5, 10, or 40 nm range.
1.1.2.4 Dual Mode of Operation
The RDR-1600 radar system can operate in single mode or dual modes of operation. The Dual
modes of operation consist of WX/BCN, WXA/BCN, SR1/BCN, SR2/BCN, or SR3/BCN. Weather
and search modes are not allowed to operate at the same time.
1.2
EQUIPMENT PART NUMBERS AND DESCRIPTIONS
1.2.1
RDR-1600 System Components
Table 1.2-1. RDR-1600 System Components
Telephonics
Part Number
Type
Description
379-2011-001
RT-1601
Provides pulsed X-band output signal to sector scanned antenna.
Reflected signal is amplified by receiver, filtered, digitized, and
sent on to the display. The magnetron frequency is tunable and is
designed to operate at 9375 ± 5 MHz to permit reliable triggering
of the beacon transponder. Operating parameters permit optimum
performance in each of the five primary modes (three search,
weather, and beacon).
4000504-0301
DA-1203A
Radar Antenna Drive unit. Positions antenna array in azimuth and
elevation axis. Motor driven, with line-of-sight stabilization.
Scans 120° sector. Stabilization in accordance with pitch and roll
signals from the aircraft vertical gyro and control panel Tilt
control. The tilt is selectable ± 15° from horizontal. Mates with
the 10-inch and 12-inch antenna arrays.
4000504-0302
DA-1203A
Same as the –0301 except for inverted mounting.
4000504-0303
DA-1203A
Same as the –0301 except includes counterweights which are
necessary for the larger antenna. Mates with the 18-inch antenna
array.
4000504-0304
DA-1203A
Same as the –0301. Special customer label.
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COMMAND SYSTEMS DIVISION
Table 1.2-1. RDR-1600 System Components (Cont)
Telephonics
Part Number
4000504-0305
Type
DA-1203A
4000525-4510
AA-4510A
4000525-4512
AA-4512A
4000525-4518
AA-4518A
4000525-5510
AA-5510A
4000525-5512
AA-5512A
4000525-5518
AA-5518A
4000525-1812
AA-1812A
4005094-0502
Mounting Adaptor
3614278-1101
3614278-1102
3614278-1201
3614278-1119
3614278-1120
3614278-1219
3614278-1220
3614278-1319
3614278-1320
3614278-1419
3614278-1420
3614278-1520
3614278-1619
3614278-1620
3614278-1719
3614278-1819
3614278-1919
3614278-1127
3614278-1128
3614278-1130
CP-113A
CP-113A
CP-113A
CP-113K
CP-113K
CP-113K
CP-113K
CP-113K
CP-113K
CP-113K
CP-113K
CP-113K
CP-113K
CP-113K
CP-113K
CP-113K
CP-113K
CP-113P
CP-113P
CP-113P
Description
Same as the –0301 except includes counterweights
which are necessary for the larger antenna. Mates with
the 18-inch by 12-inch antenna array.
Phased array antenna; 45,000 feet; 10-inch diameter
round; mates with DA-1203A.
Phased array antenna; 45,000 feet; 12-inch diameter
round; mates with DA-1203A.
Phased array antenna; 45,000 feet; 18-inch diameter
round; mates with DA-1203A.
Phased array antenna; 55,000 feet; 10-inch diameter
round; mates with DA-1203A.
Phased array antenna; 55,000 feet; 12-inch diameter
round; mates with DA-1203A.
Phased array antenna; 55,000 feet; 18-inch diameter
round; mates with DA-1203A.
Phased array antenna; 30,000 feet; 18-inches wide by
12-inches high; mates with DA-1203A.
Mounts DA-1203A antenna drive to allow for bulkhead
clearance when using an AA-4518A, AA5518A, or
AA1812A antenna arrays.
Black 28 VDC
Gray 28 VDC
Black 28 VDC NVG YEL
Black 5 VAC
Gray 5 VAC
Black 5 VAC NVG GRN
Gray 5 VAC NVG GRN
Black 5 VAC NVG GRN
Gray 5 VAC NVG GRN
Black 5 VAC
Gray 5 VAC
Gray 28 VDC
Black 28 VDC NVG GRN
Gray 28 VDC NVG GRN
Black 28 VDC
Black 28 VDC NVG YEL
Black 28 VDC NVG YEL
Black 28 VDC
Gray 28 VDC
Black 28 VDC NVG GRN COMPATIBLE
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COMMAND SYSTEMS DIVISION
1.2.2
CP-113 Unit Description
1.2.2.1 CP-113 Function Select Switch
Table 1.2-2. CP-113 Function Select Switch
Telephonics Part
Number
Model Name
OFF
STBY
TEST
ON
60°°
LOG
3614278-1101
CP-113A
3614278-1102
CP-113A
3614278-1201
CP-113A
3614278-1119
CP-113K
3614278-1120
CP-113K
3614278-1219
CP-113K
3614278-1220
CP-113K
3614278-1319
CP-113K
3614278-1320
CP-113K
3614278-1419
CP-113K
3614278-1420
CP-113K
3614278-1519
CP-113K
3614278-1520
CP-113K
3614278-1619
CP-113K
3614278-1620
CP-113K
3614278-1719
CP-113K
3614278-1819
CP-113K
3614278-1919
CP-113K
3614278-1127
CP-113P
3614278-1128
CP-113P
3614278-1130
CP-113P
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COMMAND SYSTEMS DIVISION
1.2.2.2 CP-113 Mode Push Buttons
Table 1.2-3. CP-113 Mode Push Buttons
Telephonics
Part Number
Model Name
WX
(RDR)
RNG
UP/DN
SRCH
OBS
BCN
3614278-1101
CP-113A
3614278-1102
CP-113A
3614278-1201
CP-113A
3614278-1119
CP-113K
3614278-1120
CP-113K
3614278-1219
CP-113K
3614278-1220
CP-113K
3614278-1319
CP-113K
3614278-1320
CP-113K
3614278-1419
CP-113K
3614278-1420
CP-113K
3614278-1519
CP-113K
3614278-1520
CP-113K
3614278-1619
CP-113K
3614278-1620
CP-113K
3614278-1719
CP-113K
3614278-1819
CP-113K
3614278-1919
CP-113K
3614278-1127
CP-113P
3614278-1128
CP-113P
3614278-1130
CP-113P
WXA NAV (MAP)
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COMMAND SYSTEMS DIVISION
1.2.2.3 CP-113 Additional Switches and Controls
Table 1.2-4. CP-113 Additional Switches and Controls
Telephonics
Part Number
Model Name
TILT
PULL
STAB OFF BCN GAIN
SRCH
GAIN
CODE
BRT
OFF
3614278-1101
CP-113A
3614278-1102
CP-113A
3614278-1201
CP-113A
3614278-1119
CP-113K
Note 2
3614278-1120
CP-113K
Note 2
3614278-1219
CP-113K
Note 2
3614278-1220
CP-113K
Note 2
3614278-1319
CP-113K
3614278-1320
CP-113K
3614278-1419
CP-113K
3614278-1420
CP-113K
3614278-1519
CP-113K
3614278-1520
CP-113K
3614278-1619
CP-113K
3614278-1620
CP-113K
3614278-1719
CP-113K
3614278-1819
CP-113K
Note 1
3614278-1919
CP-113K
3614278-1127
CP-113P
3614278-1128
CP-113P
3614278-1130
CP-113P
Notes
1. Tilt Pot zero is at the 9 o’clock position
2. Dual Brightness Pots
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COMMAND SYSTEMS DIVISION
1.3
ADDITIONAL EQUIPMENT REQUIRED FOR COMPLETE INSTALLATION
1.3.1
Additional Available Equipment
Table 1.3-1. Additional Equipment Available
Accessory
RDR-1600
Installation Kit
Telephonics
Part Number
4007550-0508
Description
4007261-0502
4007261-0503
4007543-0502
4007543-0506
Telephonics
Part Number
Kit Includes:
•
RT-1601
Mounting Trays
Type
RT-1601 J1 mating
connector
• RT-1601 J3 mating
connector
• RT-1601 Waveguide
Quick Disconnect
• DA-1203A mating
connector
• CP-113K mating
connector
Standard Mount
without vibration isolators
Standard Mount
with vibration isolators
Side Mount
without vibration isolators
Side Mount
with vibration isolators
MS3126F1626S(SR)
D38999/26WE35SN
(MIL-C-38999/26)
---
2088376-0013
KPT06F16-23S
2088376-0037
Positronics
HDC50F20JVL0
1-8
--4005095-0501
24220-0013
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COMMAND SYSTEMS DIVISION
1.3.2
Equipment Required But Not Supplied
Table 1.3-2. Equipment Required But Not Supplied
Accessory
Description
Radome
Radome kits and installation directions must be ordered directly from
the radome manufacturer or supplied by aircraft manufacturer. The
radome provides a radar window for the radar signal while retaining
the original nose configuration of the aircraft. The DA-1203A is
mounted directly behind the radome. The radome must have a
transmisstivity of 90% or better for proper radar operation. Refer to
Advisory Circular AC No.43-14 in the front portion of this manual.
Electrical Cables
The radar system wiring harness shall be constructed as shown in the
System Wiring Diagram (see paragraph 2.9).
Quadraxial cable (024-00064-0000) is required for transmission of
ARINC 453 data from the RT to the MFD display system.
Stabilization Requirements
The RDR-1600 radar system will work with vertical gyros with an
output of 40 to 220 mV/°.
The RDR-1600 radar system will accept ARINC 429 Pitch and Roll
data from an AHRS system.
Waveguide
Flexible or rigid waveguide may be used between the RT and the DA.
The following types of waveguide shall be used:
EIA
WR90
MIL-W 85E
RG52/U (Copper/Bronze)
MIL-W 85E
RG67/U (Aluminum)
British
WG16
IEC
R100
This waveguide must have a plate (flat) flange on one end and a choke
flange on the other.
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COMMAND SYSTEMS DIVISION
1.4
LEADING PARTICULARS
1.4.1
RDR-1600 Radar System
Table 1.4-1. RDR-1600 Radar System
Characteristic
Description
System Power Requirements
System
5.0 Amps at 28 VDC. 3.0 VA at 115 VAC, 400 Hz
(power factor 0.68)
Panel Lighting
0.4 Amps at 5 Volt
0.1 Amps at 28 VDC
Display Range / Range Marks [nm]
0.5
0.25, 0.5
0.5, 1
0.5, 1, 1.5, 2
1.25, 2.5, 3.75, 5
10
2.5, 5, 7.5, 10
20
5, 10, 15, 20
40
10, 20, 30, 40
80
20, 40, 60, 80
160
40, 80, 120, 160
240
60, 120, 180, 240
Minimum Tracking Range
500 feet
Displayed Modes of Operation
Standby (STBY)
Test (TEST)
Weather (WX)
Weather Alert (WXA)
Search 1 (SR1)
Search 2 (SR2)
Search 3 (SR3)
System Self Test
Initiated BIT
Test Mode – The display will show the radar test pattern.
Continuous BIT
Monitors faults in the Receiver Transmitter, Antenna
Drive, and Radar Control Panel.
Transmitted Power
10 KW Peak Power
Transmit and Receive Frequencies
Transmit
Weather Mode
9375 ± 5 MHz
9375 ± 5 MHz
Search Mode
9375 ± 5 MHz
9375 ± 5 MHz
Beacon Mode
9375 ± 5 MHz
9310 ± 5 MHz
Receive
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Table 1.4-1. RDR-1600 Radar System (Cont)
Characteristic
Description
Transmitted Pulse Width and Pulse Repetition Frequency (PRF)
Pulse Width
PRF
Search 1 (10 nm or less)
0.2 µ Sec
1500 Hz
Search 2 (10 nm or less)
0.2 µ Sec
1500 Hz
Search 3, Search 1, Search 2
2.35 µ Sec
200 Hz
Beacon
2.35 µ Sec
200 Hz
Weather
2.35 µ Sec
200 Hz
Weather Performance Index and Avoidance Range
PI
10 inch Antenna
208.7 dB
190 nm
12 inch Antenna
212.9 dB
229 nm
18 inch Antenna
219.7 dB
305 nm
18 inch by 12 inch Antenna
216.3 dB
265 nm
Avoidance
Sensitivity Timing Control (STC)
10 inch Antenna
40 nm
12 inch Antenna
40 nm
18 inch Antenna
45 nm
18 inch by 12 inch Antenna
45 nm
Antenna Gain and Beam Width
Gain
10 inch Antenna
25.5 dBi
10°
10°
12 inch Antenna
27.6 dBi
8.0°
8.0°
18 inch Antenna
31.0 dBi
5.5°
5.5°
18 inch by 12 inch Antenna
29.3 dBi
5.5°
8.0°
Antenna Scan Angle
120° or 60°
Antenna Scan Rate
28° / Sec
Antenna Tilt Control
± 15°
Antenna Stabilization
± 30°
Antenna Stabilization Accuracy
± 1°
1-11
Azimuth
Elevation
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1.4.2
RT-1601 Receiver Transmitter
Table 1.4-2. Leading Particulars RT-1601 Receiver Transmitter
Characteristic
Description
Size
Short ½ATR
Weight (maximum)
17.3 lbs (7.8 kg)
Mounting
Mounting Tray
Pressurization
None Required
TSO
C63c, Class 7
C102
RTCA Documents
DO-172
DO-173
DO-178A, Level 2
DO-160A
1.4.3
DO-160A Environmental Categories
D1A/MON/XXXXXXBBABA
DO-160C Environmental Categories
[D1]WBA(MON)XXXXXXBBABAAAXXX
DA-1203A Antenna Drive
Table 1.4-3. DA-1203A Antenna Drive
Characteristic
Description
Size
See Figure 2.9-6 DA-1203A Antenna Drive Outline
Drawing
Weight (maximum)
See Figure 2.9-6 DA-1203A Antenna Drive Outline
Drawing
Mounting
Directly to bulkhead, inverted or standard, 18” and
18”x12” antennas require special mounting adaptor.
TSO
C63b
RTCA Documents
DO-172
DO-173
DO-160A
DO-160A Environmental Categories
F2A/JLY/XXXXXXABABA (-50°C)
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COMMAND SYSTEMS DIVISION
1.4.4
CP-113 Radar Control Panel
Table 1.4-4. CP-113 Radar Control Panel
Characteristic
Description
Size
See Figure 2.9-7 CP-113 Radar Control Panel Outline Drawing
Weight (maximum)
1.7 lbs (0.77 kg)
Mounting
Panel Mounted, DZUS
TSO
C63c
RTCA Documents
DO-172
DO-173
DO-178A, Level 2
DO-160A
DO-160A Environmental Categories
1.4.5
F1A/PKS/XXXXXXABABA
Antennas
Table 1.4-5. Antennas
Characteristic
Description
Size
See Figure 2.9-6 DA-1203A Antenna Drive Outline
Drawing
Weight (maximum)
See Figure 2.9-6 DA-1203A Antenna Drive Outline
Drawing
Mounting
Mounts directly to the Antenna Drive
TSO
C63b
RTCA Documents
DO-172
DO-173
DO-160A
DO-160A Environmental Categories
AA-4510A
C2A/JLM/XXXXXXABABA, 45,000 FT.
AA-4512A
C2A/JLM/XXXXXXABABA, 45,000 FT.
AA-4518A
C2A/JLM/XXXXXXABABA, 45,000 FT.
AA-5510A
F2A/JLY/XXXXXXABABA, 55,000 FT.
AA-5512A
F2A/JLY/XXXXXXABABA, 55,000 FT.
AA-5518A
F2A/JLY/XXXXXXABABA, 55,000 FT.
AA-1812A
B1AYXXXXXXABABA, 20,000 FT.
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COMMAND SYSTEMS DIVISION
1.5
SYSTEM COMPONENT DESCRIPTION
1.5.1
General
The RDR-1600 Radar System consists of three flight-line replaceable units (LRU): a ReceiverTransmitter (RT-1601), radar Control Panel (CP-113), and an Antenna Drive unit with antenna (DA1203A). In addition to the above LRUs, additional equipment is necessary to operate the radar
system. One or two Multifunction Displays (MFD) are necessary to display the radar data and modes
of operation. For antenna stabilization, a gyro or Attitude Heading Reference System (AHRS)
system is required.
EFIS Control
Panel Number 1
EFIS Display System
Number 1
AA-4510A
AA-4512A
AA-4518A
AA-1812A
DA-1203A
Antenna Drive
RT-1601 Receiver Transmitter
CP-113 Radar
Control Panel
EFIS Display System
Number 2
(Optional)
Vertical Gyro*
* The RT-1601 can accept
ARINC 429 data from an
AHRS system and drive
the DA-1203A
EFIS Control
Panel Number 2
(Optional)
Figure 1.5-1. RDR-1600 Radar System
1.5.2
RT-1601 Receiver Transmitter
The RT-1601 Receiver Transmitter is housed in a short ½ ATR form factor case. Overall dimensions
can be found on the receiver-transmitter outline drawing. The RT unit’s mounting tray, which is
designed for front loading, provides positive positioning and holding of the unit to the aircraft. The
mounting tray is mounted to the aircraft, and the RT unit can easily be removed and replaced for
servicing. Depending upon installation requirements different models of the mounting tray are
available.
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COMMAND SYSTEMS DIVISION
The RT-1601 contains a tight tolerance magnetron that is required to operate with a beacon
transponder. This lightweight X-band transmitter provides a peak power of 10 KW with the
capability of transmitting a long and short pulse. The long pulse is for weather, beacon, and longrange search. A short pulse is used in short-range search to provide for high resolution of small
targets.
Within the RT, there are two receivers: one for weather returns and one for beacon returns. Target
data from the receivers are filtered and converted into digital data that can be displayed on the MFD.
There are two ARINC 453 data busses to provide radar target data to two MFDs.
Note
Previous Telephonics Weather Radar Systems
contained an NC-104B Navigation
concentrator LRU. The NC-104B allowed the
radar system to operate in various control and
display configurations employing nonTelephonics equipment. This function has
been incorporated in the RT-1601. This
eliminates the need for using an NC-104B.
The RT-1601 is fully compatible with systems
that previously used NC-104B and RT-1401B.
Two versions of NC-104B are available:
•
NC-104B (Previously used part number
3614331-1004) is the preferred version.
It is described as NC-104B (-1004) in
this manual.
•
NC-104B (Previously used part number
3614331-1005). In this manual, it is
described as NC-104B (-1005). Use of
this version should only be considered
after consultation with Telephonics
engineering and engineering personnel of
the non-Telephonics equipment to be
used.
The RT can be configured with a strapping pin on the unit connector to simulate either the NC-104B
(-1004) or the NC-104B (-1005). The radar operation is identical in either configuration, but the
digital ARINC 429 control data is different. The primary configuration of the RT-1601 should be
NC-104B (-1004). This configuration is compatible with numerous MFD systems. The NC-104B (1005) configuration is not recommended unless required by the MFD system.
The configuration of the RT will determine which version of the radar control panel is used. See the
radar control panel section to determine which version of the CP-113 should be used based upon the
configuration of the RT.
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1.5.3
DA-1203A Antenna Drive
The DA-1203A Antenna Drive unit scans and stabilizes the flat plate antenna array in 120° or 60°
sectors. The antenna array can consist of several sizes: 10 inch round, 12 inch round, 18 inch round,
and 18 inch by 12 inch rectangular. The RT provides control signals and power supply voltages to
scan the antenna drive.
The antenna drive can receive pitch and roll stabilization signals from either an analog gyro or a
digital AHRS system. If an AHRS system is used, then the digital ARINC 429 pitch and roll
information must be applied to the RT-1601 where the digital data is converted into analog pitch and
roll information used by the DA-1203A.
Where it is inconvenient to make waveguide connections at the top of the antenna (standard
mounting), an inverted version is available which permits making connections at the bottom. This
version has internal wiring changes to accommodate the inverted operation.
1.5.4
CP-113 Radar Control Panel
The CP-113 radar control panel is DZUS mounted to the aircraft panel and provides mode and
control data to the RT-1601 and mode information to the MFD. The controls to the RT consist of
both analog and digital signals. The basic controls consist of RT on/off, modes of operation, antenna
tilt, search gain, and beacon gain.
Depending upon the configuration of the RT, panel color, functions, and back lighting, there are
several versions of the CP-113 radar control panel that can be used within the RDR-1600 radar
system. If the RT-1601 is configured as an NC-104B (-1004), then either a CP-113A or CP-113K
shall be used. When the RT-1601 is configured as an NC-104B (-1005) then a CP-113P shall be
used.
The RDR-1600 may consist of two MFD displays. The MFD system is used to display radar data
and to provide the RT-1601 with range information. The two MFD displays can select separate
ranges, but there can only be one radar control panel in the system. This system will allow for
independent ranges on each display, but both displays will have the same mode, search gain, beacon
gain, and antenna tilt.
The customer-selected MFD system must be compatible with the RDR-1600 radar system. This
system must provide compatible ARINC 429 control and range data, and must be able to correctly
interpret the ARINC 453 radar data information. To determine compliance, contact the MFD system
manufacturer.
1.5.5
Antennas
The RDR-1600 radar system uses flat plate, fixed phased array antennas that are mounted to the
DA-1203A antenna drive assembly. The antenna is used for both transmitting and receiving, and can
be remotely controlled from the tilt control on the radar control panel to any position of beam tilt
between 15° above and 15° below the horizontal (zero degrees attitude).
The antenna is shipped separately from the DA-1203A and must be assembled by the installation
agency. When using the 18" and 18"x12" antennas, a Mounting Adaptor must be used to provide
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clearance between the bulkhead and the antenna. This mounting adaptor is not necessary when using
a 10" or 12" antenna.
1.6
EQUIPMENT OPERATION AND CONTROLS
WARNING
Do not operate the radar during refueling
operations or in the vicinity of trucks or
containers containing flammables or
explosives; do not allow personnel within 15
feet of area being scanned by antenna when
the system is transmitting.
CAUTION
Tests involving the radiation of RF energy by the
radar antenna must not be made while the radar
antenna is directed toward close-by large metal
objects such as hangers, doors, or the inside of
the hanger. Use test or standby mode where
applicable.
1.6.1
Operating Precautions
Flash bulbs can be exposed by radar energy.
Since storm patterns are never stationary, the display is constantly changing, and continued
observation is always advisable where areas of turbulence prevail.
1.6.2
License Requirements
A Private Aircraft Radio Station License is required to operate this system when installed in an
aircraft. The Federal Communication Commission (FCC) has type-accepted and entered this
equipment as "Telephonics Type RT-1601 Radar Receiver Transmitter". When completing Form
404, Station License Application, the exact description must be used.
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1.6.3
Operating Controls and Display Features
1.6.3.1 CP-113 Operating Controls
ON
60 LOG
BRT
WX
WXA
NAV
RNG
SRCH
OBS
BCN
RNG
TST
SBY
OFF
SRCH
BCN
CODE
OFF
UP
TILT
DN
GAIN PULL STAB OFF
GAIN
Figure 1.6-1. CP-113A Radar Control Panel
ON
60
BRT 1
WX
WXA
SRCH
BCN
BRT 2
TST
SBY
OFF
SRCH GAIN
BCN GAIN
PUSH
CODE
PULL STAB OFF
UP
TILT
DN
Figure 1.6-2. CP-113K Radar Control Panel (With Brightness Pots)
ON
60
WX
WXA
SRCH
BCN
TST
SBY
OFF
SRCH GAIN
BCN GAIN
PUSH
CODE
PULL STAB OFF
UP
TILT
DN
Figure 1.6-3. CP-113K Radar Control Panel (Without Brightness Pots)
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60
ON
TST
WX
BCN
ONLY
WXA
SBY
BCN
FMT
SRCH
OFF
SRCH
BCN
CODE
GAIN
UP
TILT
DN
GAIN PULL STAB OFF
Figure 1.6-4. CP-113P Radar Control Panel
Table 1.6-1. CP-113 Function Select Switch Description
Function Select Switch
Description
OFF
Deactivates the weather radar system by removing power to the
radar R/T. This switch is hardwired to the radar system.
STBY
Places the radar R/T in Standby mode. Radar displayed data is not
present in Standby. Standby mode is used during the warm-up
period of the radar system and when the aircraft is on the ground.
TST
Causes the radar R/T unit to send a radar test pattern to the radar
display system. The radar transmitter is not active in Test mode.
ON
In this position, the radar system is turned on. The radar will scan
120° (or 90° in some systems), the transmitter is active, and the
receiver will send weather (target) data to the display system.
60°
Directs the antenna to sector scan 60° about the boresight of the
aircraft. This position will work in weather, search (map), and
beacon modes.
LOG
Selects Flight Log mode to be displayed on the Multi Function
Display (MFD). In Flight Log mode, the MFD will display the log of
waypoints stored in the Navigation system.
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Table 1.6-2. CP-113 Mode Button Description
Radar Mode
Push Buttons
Description
WX
Places the radar in Weather mode.
WXA
Places the radar in Weather Alert mode. This will cause the areas of highest
displayed precipitation to flash. In some radar systems the color Red will
flash and in other radar systems the color magenta will flash.
In some EFIS display systems this function will not work. These systems do
not have the ability to flash the color on and off. In the RDR-1400C
radar system using an NC-104B, this will also cause Target Alert to be
activated.
NAV
Sequentially selects the following display modes on an Multi Function
Display (MFD):
120° sectored mode with no navigation data
120° non-map CDI display of navigation data
120° map mode display of navigation data
360° map mode display of navigation data
RNG (UP)
Increments the selected range to next higher range setting for a sectored map
display on the Multi Function Display (MFD). This is not functional if not
connected to an MFD.
RNG (DN)
Decrements the selected range to next lower range setting for sectored map
display on the Multi Function Display (MFD). This is not functional if not
connected to an MFD.
BCN
Pressing this button will select the two Beacon type formats to be selected.
Sequentially pressing the Beacon button will select the following beacon
modes:
Beacon A, Beacon B, Beacon Off, …
The Beacon modes are as follows:
Beacon A - DO-172 compatible beacon
Beacon B - Standard two-pulse beacon
Beacon Off – Removes beacon identification from the display.
OBS
Selects Omni Bearing Select (OBS) mode on the sector map display on the
Electron Horizontal Situation Indicator (EHSI) and Multi Function Display
(MFD). OBS mode displays aircraft course pointer on weather mode radar
displays. The course pointer position is manually controlled from the CRS
knob on the EFIS display.
SRCH
Pressing this push button selects the three Search modes in sequential cyclic
manner (i.e. Search 1, Search 2, Search 3, Search 1, Search 2, Search 3,
etc.). Search modes are as follows:
Search 1 - Sea clutter rejection. Active on the ten mile range or less.
Search 2 - Short range precision mapping. Active on the ten mile range or
less.
Search 3 - Normal surface mapping
Search mode is compatible with both Beacon mode and Navigation mode.
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Table 1.6-3. CP-113 Additional Switches Description
Additional Switches
and Controls
TILT UP / DN
Description
The Tilt control is a rotary potentiometer that controls the tilt of the
antenna ± 15°. For radar systems that use the DA-1203A, this pot
is hardwired to the DA-1203A.
The Tilt Control of the CP-113K, which is used with the RDR1400C radar system (DA-1203A), will be hardwired to the DA1203A and will also output ARINC 429 Tilt information. This is
the only CP-113 that will allow both analog and digital tilt control.
PULL STAB OFF
This switch is connected to the Tilt Control knob. When the Tilt
Control Knob is pressed in, then the stabilization function is active.
When this knob is pulled out, the stabilization function is turned off.
(ROLL TRIM ADJ)
This is a recessed pot that will adjust the antenna in the azimuth axis
so that the antenna will scan parallel to the earth when no roll is
applied to the radar system. This is to adjust out any mechanical
errors that may exist between the gyro’s platform and the antenna
drive that is mounted on the bulkhead.
BCN GAIN
The Beacon Gain is a rotary potentiometer that controls the gain of
the Beacon receiver.
SRCH GAIN
The Search Gain is a rotary potentiometer that controls the gain of
the Search receiver.
CODE
Pressing this switch selects Beacon Codes in a sequential cyclic
fashion (i.e. Code 0, Code 1, Code 2, … Code 15 or Code 0, Code
1, Code 2, … Code 9). The selected code is annunciated on the
display.
When DO-172 Beacon (Beacon Mode A) is selected via the BCN
switch, the total of sixteen codes (0-15) can be selected by the Code
switch. Selecting a Standard two-pulse Beacon (Beacon Mode B)
via the BCN switch, the total of ten codes (0-9) can be selected by
the Code switch. The Code button is not active unless the Beacon
mode has been selected.
BRT
This potentiometer controls the brightness of the Multi Function
Display (MFD). The Brightness control has no function within the
CP-113.
(BRT) OFF
This switch blanks the Multi Function Display (MFD). This switch
has no function within the CP-113.
STAB OFF
When the slide switch is in the STAB position the stabilization
function is active. When the slide switch is in the OFF position the
stabilization function is turned off.
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1.6.3.2 MFD Display
Figure 1.6-5. Generic MFD Display (Radar Only Mode)
The formatting of the display will vary from manufacturer to manufacturer. Refer to the MFD
manufacturers "Pilot’s Guide" for proper operation of the MFD control panel and display formatting.
As shown above in the Generic MFD Display, there are several required features that should be
provided on all MFD displays. Depending upon the MFD display, the text fields may be in other
locations within the display area.
1.6.4
Operating Procedures
1.6.4.1 General
The operator can perform or select several system functions using the controls on the display. For all
discussions in this section, the CP-113K will be used. The basic operating procedures are described
in the following paragraphs.
Operation of GAIN and TILT controls is similar to the controls on other airborne radar systems. In
the WX, WXA, and TEST modes, the gain is preset to obtain a calibrated (red display) function at a
predetermined storm cell level. In the search modes (SR1, SR2, SR3), the SRCH GAIN control
setting is an operator function and is important in obtaining a definitive picture during varying
topographic conditions. Also, in the beacon mode (BCN), the BCN GAIN control is used to adjust
the beacon receiver gain.
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Operating the TILT control is covered in pilot’s manuals for radar systems. This control is important.
Improper use can allow a potentially dangerous storm to remain undetected. For additional
information, refer to Bendix publication ACS-927, Airborne Weather Radar Antenna Stabilization
Criteria.
The Control Panel pushbuttons are of the push-on/push-off type. The first time the button is pressed
and released, it turns on a function. The next time the button is pressed, it turns off the function. The
mode select buttons are all push-on/push-off type.
The four primary mode buttons on the Control Panel (WX, WXA, SRCH, BCN) are all electrically
interlocked by internal circuitry. If one of the buttons has been pressed to select a mode, pressing one
of the other four mode buttons will override the previous selection. Only one of the four mode
buttons can operate at a time.
If the WX mode is selected, and then (say) the SRCH mode is pressed, the display will go to SR1
mode. However, if the SRCH button is pressed again the display will go to SR2 mode. If the WX
button is pressed again, the mode will change to the WX mode.
The currently selected mode (or modes) shall always be displayed. Refer to the MFDs Pilot’s Guide
for the location of the mode on the display.
1.6.4.2 Turn On Procedure
(a) Turn the Function Select Switch from the OFF to the STBY position.
(b) Wait about 100 seconds for the equipment to warm up and then move the Function Select
Switch to the TEST position.
(c) Check the display. The test pattern should appear approximately l00 seconds after the Function
Select Switch is rotated from the OFF position to the TEST position. The range should be 80
miles. The test pattern will be for 120-degree scan, and will also contain the alphanumerical
information for mode, range, range marks, etc. RT FAULT should appear on the display (this is
normal operation when in the TEST mode). The word TEST should appear on the display.
(d) Adjust brightness control on the MFD for desired screen brightness.
(e) When safe conditions exist (see operating precautions in previous paragraph), place Function
Select Switch in the ON position to activate the radar system. The display will automatically
appear in the WX mode.
1.6.4.3 Primary Mode Selection Procedures (WX, WXA, SR1, SR2, SR3, BCN)
1.6.4.3.1
Weight-on-Wheels (WOW) Override
If the system has been installed to use the weight on wheels function during ground operation and taxi
situations, the transmitter will not go to the ON position but remains in the test mode displaying the
test pattern until the aircraft is airborne.
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WOW Override
The WOW switch may be overridden by rotating the control knob on the Control Panel from TEST
to ON to TEST to ON in less than 2 seconds. Upon completion of that action the system shall go into
normal radiate ON condition and permit selection of normal operating modes. If the Control panel
switch is returned to TEST or Standby modes, then system operation shall return to normal. If the
WOW switch has been overridden and the WOW switch is in the airborne condition, the system
modes shall operate normally and any override conditions deleted.
(a) Observe the existing mode; indicated in the display.
Note
When the indicator is first turned ON, the WX
mode will occur at 80 nm range.
(b) To change the existing mode to one of the other primary modes, simply press the new mode
button. It is not necessary to press-off the previous mode button.
Note
The RT-1601 Receiver Transmitter has a
special feature. In SR1 or SR2 mode, at 2 NM
range or less, a red band will appear, with the
outer edge at the 500 foot point in the display.
This area will not be detected.
1.6.4.4 Range Selection Procedure
The range selection is controlled by the MFD. The range buttons are located on the MFD control
panel (except if using a CP-113A). Refer to the MFDs Pilot’s Guide for details on the range
selection.
(a) Momentarily press the RNG UP button to increase the maximum range displayed by one
increment (for example, 20 to 40).
Note
Display will erase completely and rewrite on
the new selected range.
(b) Observe that the range selected is shown on the display, along the last range mark.
(c) Observe that the distance to each of the other range marks is shown at the right side of each
concentric range arc.
(d) To decrease the maximum range displayed, momentarily press the RNG DN button.
(e) Repeat step (a) or (d) as necessary to obtain the desired range.
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1.6.4.5 Stabilization (STAB OFF) Control Procedure
(a) Pull the TILT Control knob out to turn off the antenna stabilization off.
(b) Observe that the words STAB OFF appear on the display.
Note
The antenna is not stabilized in the horizontal
plane, and will cause the display to vary with
aircraft attitude.
(c) Push the TILT Control knob in to restore antenna stabilization.
(d) Observe that the words STAB OFF disappear from the display.
Note
The STAB OFF function is normally not used.
It is employed only when the antenna
stabilization system or gyro fails, or is
suspected of failure.
1.6.4.6 TEST Pattern Selection Procedure
(a) Initially, turn Function Select Switch from OFF to TEST position.
(b) Check the display. The test pattern should appear approximately 100 seconds after the Function
Select Switch was rotated from the OFF position to the TEST position. The exact point of test
pattern termination or range duration of each color is not important. The presence of three
distinct colors, in proper order, is important. See the RDR-1600 Pilot’s Guide for the pattern
that will appear in the-80-mile range.
1.6.4.7 60° Scan Selection Procedure
(a) To change the display from 120° to a 60° scan, turn Function Select Switch from ON to 60°.
(b) Observe that the antenna now scans only 60° and the display indicates a 60° sector scan.
(c) To return the system to the 120° scan, turn Function Select Switch from 60° to ON.
Note
If the antenna BORESIGHT signal is not
being received by the RT-1601, the fault ANT
FAIL will appear in the display’s fault field.
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1.6.4.8 Beacon Mode Selection (BCN)
The RDR-1600 radar system will receive, decode, and display beacon replies from a standard 2-pulse
beacon transponder and from a DO-172 6-pulse beacon transponder when the beacon mode is
selected. All beacon transponders within the selected range (160 mile maximum) will be displayed.
Each beacon transponder is assigned a numerical code, based upon the pulse spacing (2-pulse) or
based upon a binary number (6-pulse). The display range must be set for 2,5,10,20, or 40 miles to
obtain identification of the DO-172 beacon reply on the screen. The 2-pulse beacon can be identified
up to the 80-mile range.
(a) Press-on the BCN button to select the beacon mode. The beacon mode can be selected at any
time, with any other mode also selected (WX, WXA, SRI, SR2, SR3). The word BCN will
appear on the display.
(b) Press the BCN (on BCN GAIN knob) button to select the desired beacon format. Sequentially
pressing the Beacon button will select the following beacon modes: Beacon A, Beacon B, Beacon
Off, … The Beacon modes are as follows:
Beacon A
DO-172 compatible beacon
Beacon B
Standard two-pulse beacon
Beacon Off Removes beacon identification from the display.
(c) To identify a DO-172 6-pulse beacon, press the BCN button until A1 appears on the display.
The characters B1 will be displayed when the standard 2-pulse beacon has been selected. The
displaying of the beacon format will vary depending upon the MFD manufacturer. Please refer to
the MFD Pilot’s Guide for beacon format display.
(d) Press the PUSH CODE (located on the BCN GAIN knob) button to select the desired beacon
code number. The beacon codes are displayed sequentially (Al through A15 for the DO-172
format and B1 through B9 for the 2-pulse format) in the lower left corner of the display.
(e) Set the display range to between 2 and 40 miles for DO-172 codes, or between 2 and 80 miles
for 2-pulse codes. When a beacon reply is received that corresponds to the selected code, the
number (e.g. B3) will appear within the beacon symbol.
Note
With either beacon format, the first mark in the
beacon reply indicates the location (range) of
the beacon. The beacon display will flash if a
primary mode is also selected (providing the
MFD is capable – see MFD Pilot’s Guide for
display details).
(f) Adjust the BCN GAIN control as required. Beacon returns are frequently very strong and the
gain must be reduced as the beacon is approached.
(g) To remove the beacon display, press the BCN button until the beacon mode is off.
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1.6.4.9 Two-Pulse Beacon Interrogation and Codes
The transmitter of the RT-1601 sends an interrogation signal to the ground-based beacon
transponders when the BCN B mode is selected on the display. All of the ground beacons that
receive the signal reply by sending a two-pulse signal back to the aircraft. All beacons operate at the
same frequency. Each beacon transponder in a given area is assigned a different code (spacing
between the two pulses) that they emit upon each interrogation.
All of the responding beacons within the area of the display will appear on the indicator screen. Each
beacon location will appear as two short curved lines on the screen. The two curved lines will be
spaced corresponding to the pulse spacing from the transponder.
The first pulse received from the transponder generates the curved line closest to the aircraft as the
antenna scans the beacon. The actual beacon location will be at the center of this curved line.
There is a delay between the time that the beacon transponder receives a radar pulse and then sends a
reply (first of two pulses). The delay time will affect the beacon range location on the display, and is
usually adjustable on the beacon.
If the transponder delay is too long, the beacon will appear farther away than it actually is. If the
transponder delay is less, the beacon will appear closer on the screen than it actua1ly is.
Note
Refer to the beacon transponder manual for
correct delay adjustment.
The PUSH CODE button on the radar control panel permits identifying each beacon displayed.
Repeatedly pressing the button will sequence through 9 beacon codes. The spacing between the two
pulses of a beacon's reply determines the beacon’s code (see Table 1.6-4).
Assume you are looking for a beacon with pulse spacing of 6.0 miles. This beacon signal is coded
"B3" on the display. To find the beacon proceed as follows.
(a) Turn on the system and press the BCN mode button.
(b) Observe that the word B1 appears on the display.
Table 1.6-4. Typical Two-Pulse Beacon Transponder Pulse Spacing
CODE
DISPLAYED
SPACING
BETWEEN
BEACON PULSES
(IN MILES)
CODE
DISPLAYED
SPACING
BETWEEN
BEACON PULSES
(IN MILES)
3.6 to 4.3
8.3 to 9.3
4.4 to 5.3
9.3 to 10.3
5.3 to 6.3
10.3 to 11.3
6.3 to 7.3
11.3 to 13.0
7.3 to 8.3
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Note
Pulse spacing is determined by Motorola
specifications for the SST-181E X-band radar
transponder.
(c) Sequentially press the PUSH CODE button, and observe the code number that appears on the
display. (e.g. B1, B2, B3, …, B9).
(d) Stop pressing the PUSH CODE button when code B3 appears
(e) Fly the aircraft until a beacon symbol appears on the screen. If it is the desired beacon, B3 will
appear above the first mark in the beacon return.
Note
Range must be set between 2 miles minimum
and 80 miles maximum for 2-pulse beacon
identification to function. No decoding will
occur beyond 80 miles or less than 2 miles.
Also, for optimum identification, adjacent
numbered codes should not be assigned to
transponders in the same area. Refer to
Table 1.6-4.
1.6.4.10 DO-172 Six-Pulse Beacon Interrogation
The DO-172 6-pulse beacon transponder produces a display (reply) similar to the standard 2-pulse
beacon transponder reply previously described. Each DO-172 beacon location will appear as two
curved lines (frame marks) on the screen, with one, two, three, or four additional curved lines
between the two frame marks. The number of curved lines between the frame marks, and the
spacing of the lines, is determined by the beacon code of the transponder. For example, assume that
the reply for beacon code A15 is being displayed. The binary code for 15 is 1111, so there will be
four equally spaced lines between the two frame marks. Beacon code A13 would appear as a line,
then a space, then two more lines between the frame marks, for binary number 13. The first line after
the first frame mark represents the least significant bit in the binary number (e.g. number 1101 will
appear as 1011).
Depending upon the display range selected and the location of the beacon, the lines between the
frame marks may be too close to distinguish or properly identify the number, and should not be used
for identifying the reply. The PUSH CODE button on the radar control panel permits identifying each
DO-172 beacon reply in the same manner as the 2-pulse beacon reply previously described, except
15 beacon codes are possible with the DO-172 6-pulse beacon.
A pulse from the radar transmitter interrogates the DO-172 beacon. The interrogation frequency is
between 9370 MHz and 9380 MHz. The pulse width is between 2.20 µsec and 2.65 µsec. When the
DO-172 beacon transponder receives the pulse at the proper amplitude, a reply is transmitted at 9310
MHz ±5 MHz after a fixed delay of 4.7 µsec. The beacon reply signal consists of two-to-six pulses
spaced at intervals of 3.0 µsec between leading edges. Each pulse is 0.5 µsec wide. The f irst pulse is
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the first frame pulse and establishes the beacon range as previously described. The final pulse,
occurs 15 µsec after the first pulse; this is the other framing pulse. The pulses between the first and
last pulse establish the beacon code. Table 1.6-5 lists all the possible pulse combinations. Observe
that a condition exists for a zero code, when only the two frame marks would be transmitted. This
zero code reply is reserved for fault indications.
When an unknown beacon reply appears on the screen while flying in the BCN mode, the reply can
easily be identified by stepping through the beacon codes with the PUSH CODE button until the
selected code appears in the beacon symbol on the screen. If both a 2-pulse reply and a 6-pulse reply
are being received and the two beacons are assigned the same code (e.g. B3), they can still be
identified, since only the beacon replies that agree with the format selected by the BCN button will be
identified on the screen.
Note
Range must be set between 40 miles maximum
and 2 miles minimum for DO-172 beacon
identification to function. No decoding will
occur beyond 40 miles or under 2 miles
1-29
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Table 1.6-5. DO-172 Beacon Transponder Codes
FOUR CODE PULSES
IN BINARY CODE
BEACON
FIRST
SECOND
IDENTIFICATION
FRAME
CODE
PULSE
(LSB)
FRAME
(MSB)
PULSE
A (10)
B (11)
C (12)
D (13)
E (14)
F (15)
TX Pulse
F1
B1
B2
B3
B4
F2
0.5 +/- 0.1 uSec
3.0 +/- 0.1 uSec
128.2 +/- 0.2 uSec
4.7 uSec delay
10 nm Range
15.0 +/- 0.2 uSec
1-30
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1.6.4.11 Target Alert Function
The RDR-1600 system has the capability to detect high-density (red level) storm cells that are present
beyond the range being displayed on the indicator when operating in the WXA mode. At each
selected range, the system looks ahead for an additional 25 miles. If a high-density storm cell (red
level) is present, the word TGT ALRT will flash on the display (The display of Target Alert will vary
with MFD – See MFDs Pilot’s Guide for more information). The function is automatic on all ranges
except the 240 nautical mile range.
When TGT ALRT occurs, the operator should increase the range setting on the display to locate the
storm and take the necessary actions to avoid the storm cell. This feature is particularly useful when
operating at short ranges during search modes.
1.7
ASSOCIATED PUBLICATIONS
P/N
Title
Application
MFD Pilot’s Guide
MFD Display Information
MFD Installation Manual
and control panel operation
RT-1601 Maintenance Manual
RT-1601
Maintenance Overhaul
006-05953-005
Weathervision Radar
Antenna Maintenance
Manual (IB 21000A)
DA-1203A Antenna Drive
Maintenance Overhaul
006-05314-002
CP-113 Radar Control Panel
Maintenance Manual
CP-113
Maintenance Overhaul
RDR-1600 Pilot’s Guide
RDR-1600 Operation
TM106701
TM106801
*Refer to associated MFD manufacturer’s documentation.
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COMMAND SYSTEMS DIVISION
2.1
GENERAL
This chapter contains information for the installation of the Telephonics RDR-1600 Weather Radar
System. Included are equipment outline drawings, installation pictorials and electrical interconnect
diagrams of the different system configurations. These drawings should be reviewed by the installing
agency and requirements peculiar to a particular airframe established before installation is begun.
2.2
UNPACKING
Use care when unpacking the Telephonics RDR-1600 Weather Radar System components. Open
shipping cartons and carefully remove all items. Check the components to ensure that all items
ordered have been included. Retain shipping cartons and packing material for future shipping or
storage.
Visually inspect all units for any possible damage that may have occurred during shipment, such as
dents, deep abrasions, chipped paint, cracked glass, etc. If any equipment has been damaged in
transit report the extent of damage to the transportation carrier immediately.
2.3
PRE-INSTALLATION CHECK
Bench test the equipment to ensure that it is operable before installation. Bench test procedures are
given in the RDR-1600 Maintenance Manual. A continuity and insulation test should be made on all
cables and wiring harnesses fabricated by the installing agency.
2.4
INSTALLATION PLANNING
2.4.1
Outline and Interconnect Drawings
Outline drawings of the units in the RDR-1600 radar system and the interconnect diagrams are
located at the end of this chapter. Interconnect diagrams provide for either an analog gyro system or
an AHRS system installation.
For interconnecting information, refer to Figure 2.9-8 for an analog gyro system and Figure 2.9-9 for
an AHRS system installation.
The installer must fabricate cable assemblies. Mating connectors are not supplied with each unit of
the system. See Table 1.3-1.
2.4.2
Location of Equipment
The locations chosen for units of the RDR-1600 Weather Radar System, and the method of
installation will vary with each particular type of aircraft. The units should be installed in a
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convenient location for ease of operation and accessibility for inspection and maintenance. The area
should be free from excessive vibration, heat and electronic noise generating sources. If the system is
to be deployed in hot climate areas, additional air circulation/cooling around the RT1601 is
recommended. In addition, since all weather radar receiver-transmitter units are high power pulse
generating devices, they are potential sources of RFI. Consider this factor when selecting a location
for the RT unit. The cable should not be bundled with 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.
Note
2.4.3
When the transmitter is keyed, a magnetic field
occurs, created by the heavy dc current drawn. A
magnetic shield P/N 4004660-0501 is available
when the R-T unit interferes with the magnetic
compass. The indicator contains a magnetic
shield that encloses the unit, eliminating this type
interference.
Primary Power Requirements
The RDR-1600 Weather Radar System operates primarily from the aircraft's 28 VDC power system.
Power to the control panel is needed depending on which model number has been selected for use.
In addition to the dc power requirement, the system requires roll and pitch output voltages from the
aircraft's vertical gyro for operation of the antenna stabilization system. The associated 115V, 400
Hz power requirements must be in phase with the reference voltage. DC, AC, and vertical gyro
connections to the RDR-1600 Weather Radar System are shown in the interconnect diagrams, at the
end of this chapter.
2.4.4
Roll and Pitch Information
It is important that the connections to the vertical gyro outputs be made according to the system
interconnect diagram, Figure 2.9-8 and Figure 2.9-9. The DA-1203A stabilization servo system
requires a two-wire pitch input signal within a range of 40 to 220 mV per degree. Roll information
requires a two-wire input voltage within the range of 40 to 220 mV per degree. This requirement is
met by most vertical reference sources. It is important to remember that phasing must be such that
aircraft nose down and right roll gives signals at the antenna plug which shall be in-phase with
reference (115V input power to antenna) voltage.
The Pitch and Roll information to the DA-1203A may come form an analog vertical gyro or from an
ARINC 429 AHRS system. If the information is coming from an AHRS system, the ARINC 429
data must be converted to analog data by the RT-1601.
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2.5
INSTALLATION OF SYSTEM COMPONENTS
2.5.1
Radar Antenna
2.5.1.1 Assembly of Antenna Array and Antenna Drive Assembly Procedure
(a) Remove the V-band coupling assembly (see Figure 2.9-6) from the antenna drive assembly.
(b) Butt the antenna array against the antenna drive assembly making certain that the array engages
the two guide pins located on the drive assembly. Secure the array/drive assembly together by reinstalling the V-band coupling assembly.
CAUTION
Antenna arrays are available with different
altitude specifications. Be sure that the array
altitude rating is greater than the desired
maximum aircraft operating altitude. Refer to
Table 1.2-1.
(c) Torque the two cap screws on the V-band coupling assembly 22 to 24-inch-pounds.
2.5.1.2 Installation of The Antenna and Antenna Drive (DA-1203A) Assembly Procedure
The radar antenna assembly is designed for mounting to the forward bulkhead, in the nose section of
the aircraft, behind a radome fabricated for the operating frequency of the radar system. The total
space required for the radar antenna can be determined from the dimensional information contained
on the radar antenna drawing, Figure 2.9-6.
CAUTION
Check that antenna is free to move in azimuth
(retaining pin removed) prior to applying power.
The antenna base hole pattern (see Figure 2.9-10) is compatible with the mounting holes provided by
the airframe manufacturers. The standard mounting provisions provided in the aircraft should
include a means for adjustment of the antenna, approximately ±2.0 degrees in the pitch axis, by the
use of shims under the mounting pads.
Using an accurate spirit level prior to the actual mounting of the antenna can check alignment of the
mounting pads. Antenna alignment can be checked in service by means of the electrical tests outlined
in Paragraph 2.6.
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2.6
POST-INSTALLATION CHECK
Note
When an 18-inch array is installed on the
antenna drive unit, a spacer is required between
the bulkhead and the drive unit to prevent the
array from hitting the bulkhead during the 120°
scans. Refer to Table 1.2-1.
(a) Shock Mounting and Ventilation
Shock mounting is not required. The antenna is designed to operate in the unpressurized nose section
of aircraft and ventilation is not required.
(b) Pressurization
The antenna with a high altitude array is designed to operate within ambient air pressures ranging
from sea level (and below) to an altitude of 55,000 feet, without pressurization. The antenna is
installed in the nose section of the aircraft, which is not normally pressurized. Thus, if the RT
unit is installed in the pressurized cabin section, the electrical and RF transmission lines feeding
the antenna must be brought into the nose section through the use of an airtight seal at the
bulkhead feed through. A pressure window should also be placed in the installation waveguide.
(c) Orientation
The mounting position of the antenna must satisfy the following conditions:
(1) Centerline of antenna must be located at aircraft centerline or within three inches below
horizontal centerline on vertical centerline.
(2) Azimuth scan axis of antenna must parallel spin axis of the stabilizing vertical gyro.
(3) Tilt axis of antenna must parallel pitch axis of aircraft. This should result in the azimuth
spin axis of the antenna lying mutually perpendicular to the roll and pitch axes of the
aircraft.
(4) To insure that targets are displayed in their proper relative positions with respect to the
aircraft, the radar beam must radiate forward, perpendicular to the pitch axis of the aircraft,
and in the plane of flight path when the antenna is positioned at zero degrees in both azimuth
and tilt. The antenna stabilization system will function properly only when the azimuth spin
axis of the antenna parallels the spin axis of the stabilizing vertical gyro. Should an
ambiguity exist between the two spin axes, an inherent error is developed in the system. The
error is evidenced by uneven azimuth illumination of terrain as the antenna scans. This
condition is undesirable and may cause some confusion when interpreting the radar display.
Therefore, it is important that the antenna and gyro spin axes be in coincidence (both pitch
and roll planes) when the antenna is being mounted. THE SAME REFERENCE
CRITERION FOR MOUNTING THE GYRO SHOULD BE EMPLOYED FOR
LEVELING AND MOUNTING THE ANTENNA.
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(d) Waveguide RF Connection
The waveguide input flange, shown oriented to the rear of the antenna housing (Figure 2.9-6,
DA-1203A Antenna Drive Outline Drawing), has a quick-disconnect assembly to facilitate
waveguide connection. The guide pins on the quick-disconnect assembly are offset; assuring that
the waveguide will be connected only in the proper position.
(e) Radome
Refer to Advisory Circular AC No.43-14 in the front portion of this manual.
To allow the most satisfactory radar beam radiation, the nose section in front of the antenna (radome)
should be fabricated for X-band (9375 MHz, 3.2 cm wavelength) signals. A radome having less
than 90% transmisstivity, at all incidence angles defined by the scan and tilt coverage, will result
in some degradation of system performance, and should not be used.
The radome installed should allow the widest possible angle of useful beam radiation (120 degrees,
60 degrees to each side of aircraft heading). Radar range, in terms of that attainable without a
radome, is equal to the square of the radome transmisstivity percentage.
If in doubt of the quality of radome material, a flight test may be performed that evaluates
performance over the anticipated ranges and tilt angles that are desired for the type of aircraft.
2.6.1
Installation of RT-1601 Receiver Transmitter
The receiver-transmitter may be installed in any convenient location within the limits imposed by the
waveguide lengths and environmental criteria. Mounting trays provide for either horizontal or vertical
mount. See Figure 2.9-5, RT-1601 Receiver Transmitter Outline Drawing.
The mounting tray for the receiver-transmitter is designed for front loading. Clean all mounting
surfaces before installing the mounting tray to ensure a good electrical bond to the airframe. See
Figure 2.9-5.
The total mounting space required can be determined from dimensional information contained in the
RT unit outline drawing, Figure 2.9-5. At least three (3) inches of free space must be allowed to the
front left side of the R-T unit's cooling hole areas.
2.6.2
Installation of CP-113 Radar Control Panel
All control panels use DZUS fasteners to secure them to the instrument panel. Use the CP-113
outline drawing, Figure 2.9-7, as a guide to position the control panel and to cut and drill the
instrument panel. Attach the DZUS fastener brackets behind the instrument panel in the location
shown on the CP-113 outline drawing.
The control panel connector assemblies have slide locking lever tabs. To install the connector,
depress the locking lever tab, insert the connector, and release the tab. To remove the connector,
depress the tab and pull the connector out.
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2.6.3
Installation of Waveguide and Cables
2.6.3.1 Cabling
The cables should be supported firmly enough to prevent movement. They should be carefully
protected wherever one may chafe against another, or against some other object. Extra protection
should be provided in all locations where the cables may be subject to abuse. Shields on shielded
wires should be grounded as shown on the system interconnect diagrams, Figure 2.9-8 and
Figure 2.9-9.
Shields on shielded wires should not be grounded to the airframe. Ordinarily, shields will be carried
through any obstruction via a thru-bulkhead connector and grounded internally to the R-T or
associated unit. If shielding cannot be carried through by use of a bulkhead connector pin,
precautions should be taken to insure that each segment of the shielded lead be grounded at only one
point using a ground connection of not more than two inches in length. The above consideration
does not apply to coaxial cable.
2.6.3.2 Waveguide
A transmission line, composed of waveguide sections, must be installed in the aircraft. The
waveguide should be installed in as direct path as possible between the R-T unit and the antenna.
Note
Waveguide runs between transmitter and
antenna should be designed for minimum
length to avoid unnecessary attenuation of the
radar signal. Runs in excess of 10 feet are not
recommended.
The following installation information is provided (for those who may not be familiar with installing
waveguide in aircraft) to help devise a transmission line that will provide proper performance. If
special parts must be used to solve installation problems, the exact configuration of these parts should
be carefully determined during the mock up. When a satisfactory mock up system has been designed,
make a drawing to help describe the complete list of parts to be ordered. The drawing should
indicate the length and part numbers of the standard component sections of waveguide and should
identify special nonstandard components. Drawings with sufficient dimensioning to completely
define the non-standard part should be submitted when ordering such components.
The following points should be observed in the use of rigid waveguide components:
n Use standard rigid components wherever possible.
n Minimize the number of joints in the waveguide run to minimize the overall VSWR value.
n Clamp rigid waveguide to a solid portion of the aircraft structure at least once in each three feet
of waveguide run.
n Use clamps so designed so that they will not distort the waveguide walls.
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n Before ordering nonstandard large radius waveguide bends, see if the same result can be obtained
by using standard bends with additional length in the straight sections.
n When specifying unavoidable special bends in rigid waveguide, use an exact radius of 2.214
inches to the waveguide centerline for all shaft bends in either E or H plane and seven inches
centerline radius or greater in large bends.
n Each individual section of rigid waveguide should contain no more than one bend. This
procedure simplifies maintenance of the transmission line.
n Remember to allow sufficient clearance to permit access to flange connecting screws.
n Use waveguide quick disconnects wherever joints are to be broken repeatedly for maintenance,
inspection, or access to other equipment, or to assure good joint sealing in relatively inaccessible
locations.
n Be certain that the mating of a choke flange and a cover flange makes each joint in the waveguide
run. This type joint will permit proper RF sealing of the line. Each waveguide section should
have a choke flange and a cover flange at its opposite ends, where possible. Carefully avoid
specifying nonstandard flanges, such as choke flanges with tapped screw holes.
n Axial twists in rigid waveguide, up to 90 degrees, should be considered as being made in
approximately an eight-inch length of waveguide. Before specifying twists in rigid waveguide,
make certain that the same result cannot be more easily accomplished by properly oriented bends
in a section of flexible waveguide.
The following points should be observed in the use of flexible waveguide components:
Use standard flexible components wherever possible. Minimize the number of joints in the
waveguide run.
Locate a flexible section at the points of attachment to the antenna unit and the RT unit. These
sections will provide expansion joints in positions where the installation or removal or rigid
waveguide would be exceedingly difficult.
Flexible waveguide should be used instead of rigid sections containing complex bends wherever
possible. Compound bends and apparent twists can be obtained through the use of flexible
waveguide, usually at lower cost and with some simplification of installation.
In any single installation, attempt to use the same length of flexible waveguide for all flexible
sections of the transmission line.
Clamp flexible waveguide firmly to a solid portion of the aircraft structure at least once in each
18 inches of waveguide run.
Design flexible waveguide clamps carefully so that they do not distort the waveguide walls.
Use waveguide quick disconnects wherever joints are to be broken repeatedly or to assure good
joint sealing in relatively inaccessible locations.
Use flexible waveguide to produce the same effect as a twist in rigid waveguide components.
Any combination of two alternate (right and left) 90-degree bends in either the E or H plane
(broad or narrow wall) with any 90-degree bend in the opposite plane between them will
produce an effective waveguide twist. Such flexible components are less expensive and more
easily installed than rigid twists.
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With an antenna connected to the waveguide installation, it may be desirable to test the entire
waveguide run including antenna for total VSWR. This must be done with the antenna pointing into
free space to avoid the possibility of reflective target interference. The total VSWR will be the result
of many factors in the waveguide and antenna. A long waveguide run may tend to increase the
VSWR. Therefore, a short run is more desirable. Ratios as high as 2:1 have been experienced
without noticeably disturbing the system operation, however, a lower VSWR is desirable. Insertion
loss is also increased with excessive waveguide length. The suggested maximum waveguide length,
including bends, should not exceed 10 feet for best performance.
2.7
POST-INSTALLATION CHECK
WARNING
Tests involving radiation of RF energy by the
radar antenna must not be made in the
vicinity of refueling operations, or when
personnel are standing directly in front of the
radar antenna. RF energy is generated in all
modes except standby and test. Do not allow
personnel within 15 feet of area being scanned
by antenna when system is transmitting.
CAUTION
Tests involving the radiation of RF energy by the
radar antenna must not be made while the radar
antenna is directed toward close-by large metal
objects such as hangars, doors, or the inside of
the hangar. Use test mode or turn the indicator
function switch to off where applicable.
Note
Two persons with a means of communication
between them can perform the following
procedures efficiently. One person stationed in
the cockpit, and the second person mobile
between the transmitter location and the
antenna. The radome should not be installed
when performing these procedures.
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2.7.1
Visual Inspection Procedure
(1) Manually rotate the antenna in tilt and azimuth axes to verify that no binding action exists, and
that aircraft structure does not interfere with free movement.
(2) Check the waveguide, cable, and black box installation to determine they are mechanically and
electrically secure.
(3) Check for free and proper operation of all indicator controls.
(4) Check that primary power sources are functioning.
2.7.2
Control Panel and MFD Display Check Procedure in Test Mode
CAUTION
After elapse of the turn-on delay, the "RT fault"
indication should not appear on the MFD display
in any mode except test. If "RT fault" appears in
any mode except test (or does not appear in the
test mode), a malfunction exists and corrective
action should be taken.
(1) Rotate the Function Select Switch on the Radar Control Panel to the TEST position. Observe
that RT FAULT appears in the fault field and TEST appears in the mode field on the display(s).
(2) Observe that the complete test pattern appears after approximately 100 seconds from turn on.
Check that the red area in the test pattern is steady. See RDR-1600 Pilot’s Guide for typical test
pattern. The range will automatically set to 80 miles.
(3) Check that the test pattern displays the colored bands in the sequence shown. Width of the bands
is not significant.
(4) Observe that "ripple" moves along the outer band on the display(s), indicating that up dating is
occurring.
(5) Adjust the TILT control on the Radar Control Panel to +5°, then +10°, then +15° checking that
the array plate tilts upward smoothly, and without interference.
(6) Adjust TILT control on the Radar Control Panel to -5°, then -10°, then -15°, checking that the
array plate tilts downward smoothly, and. without interference. Return the TILT control on the
Radar Control Panel to 0° position.
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2.7.3
Antenna Stabilization Check
Note
The following tests require accurate
positioning of the vertical gyro in both pitch
and roll. If a tilt table is not available, the gyro
may be positioned by reference to the flight
director or artificial horizon, or some other
method of accurately tilting the gyro in the
aircraft. See Figure 2.7-1 for location of
antenna checkout aids. This calibration
procedure should be performed after any
period of gyro or antenna maintenance.
Note
When the RDR-1600 weather radar system is
being calibrated to the aircraft’s gyros, the
antenna scan, in the azimuth axis, must be
stopped, but the stabilization must be enabled.
When the RDR-1600 weather radar system is in
Standby mode, the antenna will stop scanning.
When the RT-1601 is configured as a NC-104B1005, stabilization will be allowed in the Standby
mode (Stab Disable pin from the DA-1203A - Pin
A is high). Whereas, when the RT-1601 is
configured as a NC-104B-1004, stabilization will
not be allowed in the Standby mode (Stab Disable
pin from the DA-1203A - Pin A is grounded).
This creates a problem if calibrated to the gyros
when the RT-1601 is configured as a NC-104B1004. If the unit is in Standby mode, the antenna
is not scanning, but the stabilization is off. If the
unit is turned to Test mode the stabilization is
enabled, but the antenna is scanning.
To calibrate the gyros when the RT-1601 is
configured as a NC-104B-1004, the following
steps shall be performed. Disconnect the Stab
Disable pin from the DA-1203A (Pin A). Place
the unit in Standby mode, and then follow the
instructions listed below. Reconnect the Stab
Disable pin to the DA-1203A (Pin A) when
finished.
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Figure 2.7-1. Generic MFD Display
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Figure 2.7-2. Radar Control Panel
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2.7.4
Antenna Checkout Aids
2.7.4.1 Tilt Check Procedure
(a) Rotate the Function Select Switch on the Radar Control Panel to STBY.
(b) Place the aircraft vertical gyro to zero degrees pitch and zero degrees roll.
(c) Set the TILT control on the Radar Control Panel to position the antenna at 0°. The antenna
elevation position should be 0° ±1°.
(d) Set the TILT control to position the antenna to the 10° up. The antenna elevation position should
be +10° ±3°.
(e) Set the TILT control to position the antenna at the 10° down reference mark. The antenna
elevation position should be -10° ±3°.
2.7.4.2 Pitch Calibration Check Procedure
(a) With the Function Select Switch on the Radar Control Panel in STBY position, manually position
the antenna to zero degrees azimuth and insert the retaining pin into the 0° slot to lock the
antenna in azimuth.
(b) Adjust the TILT control on the Radar Control Panel to position the antenna exactly at zero
degrees in elevation.
Note
Do not make further adjustments to the TILT
control until pitch and roll calibration is
completed.
(c)
Position the aircraft vertical gyro for 10° nose up and zero degrees bank. The antenna elevation
position should be 10° down. If not, adjust the PITCH gain potentiometer on the antenna drive
assembly for proper deflection.
(d)
Position the aircraft vertical gyro for 10° nose down and zero degrees bank. The antenna
elevation position should be 10° ±1.5° up.
(e)
Momentarily (10 seconds maximum) rotate the function switch to the TEST position on the
radar indicator. The antenna should return to 0° elevation position. Return the function switch
to the STBY position.
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CAUTION
Do not leave function switch in the test position
for more than 10 seconds or antenna azimuth
drive will engage.
(f)
Unlock the antenna azimuth drive by disengaging the retaining pin.
2.7.4.3 Roll Calibration Check Procedure
(a) Set the ROLL-TRIM (recessed pot below the SRCH button) potentiometer on the Radar Control
Panel to midrange (see Figure 1.6-3 for location).
(b) With the Function Select Switch on the Radar Control Panel in the STBY position, manually
position the antenna to 60° clockwise and lock the azimuth drive by inserting the retaining pin
into the 60° CW slot.
(c) Position the aircraft vertical gyro to zero degrees pitch and 30° right roll. The antenna elevation
position should be 26° up. If not, adjust the ROLL gain potentiometer on the antenna drive
assembly for 26° deflection.
(d) Position the aircraft vertical gyro to zero degrees pitch and 30° left roll. The antenna elevation
position should be 26° ±1.5° down.
(e) Momentarily (10 seconds maximum) rotate the function switch to the TEST position on the
Radar Control Panel. The antenna should return to 0° elevation position. Return the function
switch to the STBY position.
CAUTION
Do not leave function switch in the test position
for more than 10 seconds or antenna azimuth
drive will engage.
(f)
Unlock the azimuth drive by disengaging the retaining pin. Store the retaining pin for future
use.
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2.7.5
RF Operation Check Procedure
WARNING
Whenever the function switch is in the "ON"
or "60°°" position, RF energy is being radiated.
Do not allow personnel to stand within 15 feet
of the area being scanned by antenna. Tests
involving the radiation of RF energy must not
be made in the vicinity of refueling operations.
Always use "test" or "standby' positions as
applicable.
(1) Rotate the Function Select Switch on the Radar Control Panel to the TEST position. Rotate the
Function Select Switch on the Radar Control Panel to the ON position after the system has been
in TEST for at least 100 seconds. Use WOW override if WOW function is installed.
(2) Check for target reflections of local weather (if any) by indexing the RANGE pushbuttons on the
MFD Control Panel(s) (or CP-113A) to each range position while tilting the antenna upward
above the horizon, using the TILT control on the Radar Control Panel.
(3) Index the RANGE pushbuttons through the ten range positions. Note that the corresponding
range and range mark intervals appear in the alphanumeric area of the display. Note that targets
on display (if any) shift their relative position.
(4) Change the mode setting and note that display(s) change accordingly.
(5) For two display configurations only: Change the range on both displays and note that each display
changes range independently of each other (providing that the system configuration allows for
both displays to range independently of one another).
Note
(6)
When the radar system is operating in a search
1 or 2 mode, and display number one’s range is
at 10 nautical miles or less, and display number
two’s range is greater than 10 nautical miles,
the radar system will convert to dual scan mode.
The antenna scan from right to left will update
display number one, and the antenna scan form
left to right will update display number two.
Rotate the function switch to STBY.
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2.7.6
Interference Test Procedure
(1) Operate the system on all functions and modes, and check that this does not affect other
electronic equipment in the aircraft.
(2) Operate the system on all functions and check that it is not affected by any of the functions of the
other electronic or electrical equipment in the aircraft.
(3) Upon successful completion of the foregoing post-installation tests, install the radome
preparatory to preflight checkout of the system.
2.8
PREFLIGHT CHECK AND FLIGHT CHECK PROCEDURES
2.8.1
Preflight Check Procedure
2.8.1.1 Single Indicators
Note
The preflight check assumes that the system
has been properly installed and passed the
post-installation checks, that the aircraft is
pointed toward a non-reflective area, and that
fuel trucks or personnel are not close to the
radar line-of-sight.
CAUTION
After elapse of the turn-on time delay, the "RT
fault" indication should not appear on the display
in any mode except test. If "RT fault" appears in
any mode except test (or does not appear in the
test mode), a malfunction exists and corrective
action should be taken.
(1) Energize the radar bus and vertical gyro reference bus. Ensure that 28 VDC and 115 VAC power
is being supplied to the system. Check that the vertical (stabilization) gyro is erected.
(2) Vary the external panel lighting voltage (dim control) for maximum panel brightness. Check the
white panel markings for even light distribution. Reduce the lighting voltage. The panel lighting
should dim.
(3) Rotate the Function Select Switch on the Radar Control Panel to the TEST position.
(4) Set the TILT control on the Radar Control Panel to any position.
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(5) Note that RT FAULT appears in the fault field on the MFD display. The word TEST should
appear in the mode field on the MFD display. The test pattern should appear on the display
within 100 seconds. Adjust BRT control on the MFD display as required.
Note
(a)
(b)
The width of the test pattern bands is not
critical, nor is the position of the bands relative
to the range marks.
Check that the test pattern displays five colored bands. Starting with the closest band to
the origin, the bands will be green, yellow, red, yellow, and green. The red band
represents the most intense level. All range marks will be visible and displayed in blue
letters.
Observe the update action as a small "ripple" moving along the outer green band,
indicating that the antenna is scanning the full 120°.
Note
Basically, the test pattern can be thought of as
a weather target. Therefore, when in the TEST
mode and switching through the ranges, the
test pattern position will be altered on the
screen.
(6)
Change the range to 2 miles. The test pattern will be beyond the area being scanned. Increase
the range, one step at a time and observe that the test pattern appears in the correct ranges.
Observe that the proper range marks appear in the display.
(7)
Rotate the Function Select Switch on the Radar Control Panel to the STBY position, then taxi
the aircraft to a clear-ahead area where metal buildings, aircraft, etc., are not in the line-ofsight. Observe the warning at the beginning of paragraph 2.7.
(8)
Rotate the Function Select Switch on the Radar Control Panel to the ON position. Use WOW
override if WOW is installed. The display will automatically be in the WX mode.
(9)
Adjust the TILT control up (+ degrees) in small increments until a clear picture develops of any
local weather. Close-in ground targets may also appear in the display. A +15°, no ground
target should appear on the display.
(10) Repeat TILT control adjustment to check remaining ranges.
(11) Sequentially change the modes through SR1, SR2 and SR3. Observe that for each mode
selected, SRCHl, SRCH2, or SRCH3 appears in the mode field on the MFD display, and for
each mode the fault field remains off. Example: if in SR1 mode, the display should show
"SRCHl".
(12) Set the mode to SR1 and the range to 20. Observe that the four range marks are identified.
Index range selector to 20, 10, 5, 2, 1, and .5 NM and note that the range marks are identified
properly in each range.
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Note
The RT-1601 Receiver Transmitter has a
special feature. In SRI or SR2 mode, at 2 NM
range or less, a 500-foot-wide red band will
appear, with the outer edge at the 500-foot
point in the display.
(13) Set the mode to BCN and the range to 20. Observe that the characters "BCN" appear in the
mode field on the MFD display. The fault field should be off and the display should be free of
all noise and ground clutter. If a beacon station of 9310 MHz is within range, a beacon reply
may be observed on the screen.
(14) Proceed as follows to check the DO-172 6-pulse beacon format.
(a)
With the indicator in the BCN mode, press and release the BCN button until the word A1
appears on the display. This selects the 6-pulse beacon format.
(b)
Press the PUSH CODE button and observe that the beacon code displayed in the lower
left corner changes sequentially from A1 to A15, then changes to A1, and then repeats
the sequence.
(c)
Observe the display for any 6-pulse beacon replies. The 6-pulse beacon transponder
reply will be displayed by two frame marks with either 1,2,3, or 4 other closely spaced
marks between the two frame marks.
Note
(d)
The marks between the frame marks represent
the beacon code number in 4-bit binary format,
with each mark a logic 1 and the closest mark
to the origin being the least significant bit.
If a beacon reply is observed, repeatedly press the PUSH CODE button until a beacon
code (e.g. A12) appears in the display between the frame marks.
Note
The selected range must be set for 2,5,10,20, or
40 miles to identify the DO-172 beacon reply.
(e)
Observe the beacon code number selected and the beacon code number displayed by the
beacon marks are the same number.
(f)
Press the BCN button until the beacon-selected character changes from A to B. Only the
two-pulse beacon replies will now be identified.
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(15) Proceed as follows to check the two-pulse beacon format.
(a)
Press and hold the PUSH CODE button and observe that the beacon code displayed in the
lower left corner changes sequentially from Bl to B9, and then repeats the sequence.
(b)
Observe the display for any 2-pulse beacon replies.
(c)
If a 2-pulse beacon reply is observed, repeatedly press the PUSH CODE button until a
beacon code (e.g. B3) appears in the display between the "hash marks".
Note
The selected range must be set for 2,5,
10,20,40, or 80 mile range to identify 2-pulse
beacon replies.
(d)
Observe the beacon code number selected and the beacon code number displayed by the
beacon marks are the same number.
(e)
Rotate the Function Select Switch on the Radar Control Panel to the TEST position.
2.8.1.2 Multiple Displays
Repeat paragraph 2.8.1-1 for display number 2.
2.8.2
Flight Check procedure
Note
Vertical gyro precession may be experienced
during take-off or during prolonged aircraft
maneuvers. Antenna stabilization may
therefore suffer a 3° to 5° error for as long as
five minutes after the maneuver.
2.8.2.1 Check Test Pattern
Rotate the Function Select Switch on the Radar Control Panel to the TEST position. Set the range to
80 miles. Adjust the brightness (BRT) control on the MFD display as necessary to evaluate the test
pattern. Basically, check that update is occurring and that the five colored bands are correct.
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2.8.2.2 Check And Adjust Antenna Stabilization
Note
The pitch and roll output levels from the
vertical gyro are governed by the 115 volt, 400
Hz excitation, the linearity of the gyro, plus the
ability of the gyro to follow the motion of the
aircraft. The accuracy contributed by the
antenna is its ability to respond to the gyro
outputs. As a result of these factors, the
stabilization system accuracy can vary up to
±10% of the pitch or roll angle of the aircraft.
This accuracy can be tested in flight by
performing the following procedure.
(1)
Fly to a convenient altitude above 10,000 feet.
(2)
Select a range of 80 nautical miles, or 40-mile range for 12-inch antennas. Set the mode to
SRCH 3.
(3)
Pull the PULL STAB OFF switch (on tilt control pot) out on the Radar Control Panel to
remove antenna stabilization.
(4)
While flying level (0° pitch, 0° roll), adjust the TILT control on the Radar Control Panel to
obtain the video pattern shown in Figure 2.9-1, then note TILT control setting. The terrain
band should be displayed about the third range mark.
If the inner ring of video is not parallel to the range mark, the error is caused by mechanical
displacement of the antenna about the roll axis of the aircraft. Use TILT control to determine
exact error. Correction on the ground, if necessary, must be performed prior to further in-flight
calibration.
(5)
Push the PULL STAB OFF switch (on tilt control pot) in on the Radar Control Panel to restore
antenna stabilization.
(6)
The pattern observed in step (4) should not change. If the pattern shifts as in Figure 2.9-2 or
Figure 2.9-3, it will be necessary to ground-check leveling of the gyro and accuracy of the
Horizon Situation Indicator. Use TILT control to find exact error.
(7)
Roll the aircraft 20° right. For perfect stabilization, the terrain band shown in Figure 2.9-1
should not shift.
(8)
In step (7), if the terrain band shifts as shown in Figure 2.9-2, increase the tilt angle, by means
of the TILT control on the Radar Control Panel, until the pattern is similar to Figure 2.9-1.
Note
Note the new position of the TILT control. It
should not be more than two degrees above
that noted in step (4).
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(9)
In step (7), if the terrain band shifts as shown decrease the tilt angle (using the TILT control) is
similar to Figure 2.9-1. Note the new position control. It should not be more than two
degrees in step (4).
(10)
If the differences between steps (8) and (4) or steps (9) and (4) are greater than two degrees,
recalibrate the roll stabilization circuitry to the gyro using the following procedure:
(a) Reset the TILT control under the flight conditions of step (4) with stab on. Then roll the
aircraft 20° right.
(b) If the pattern shifts per Figure 2.9-2, slowly adjust the ROLL TRIM potentiometer on the
Radar Control Panel (recessed pot below SRCH button) until the terrain band display is as
shown in Figure 2.9-1. Usually a clockwise adjustment is required.
(c) If the pattern shifts per Figure 2.9-3, slowly adjust the ROLL TRIM potentiometer on the
Radar Control Panel (recessed pot below SRCH button) until the terrain band display is as
shown in Figure 2.9-1. Usually a counterclockwise adjustment is required.
(11) If the pattern shifts per Figure 2.9-4, there is no roll stabilization and the system should be
ground-checked per the post-installation tests of this manual, Paragraph 2.7.3, "Antenna
Stabilization Check".
2.8.2.3 Check Weather Alert Mode
(1) Rotate the Function Select Switch on the Radar Control Panel to the ON position, and adjust the
TILT control to obtain a strong red level ground return.
(2) Select the WXA mode by pressing the WXA button on the Radar Control Panel.
(3) Observe that the red area flashes on and off approximately once per second (the red areas will
flash if the MFD display has the ability to perform this function).
(4) Return the tilt control to the normal position.
2.8.2.4 Check Target Alert
(1) Select the WXA mode by pressing the WXA button on the Radar Control Panel.
(2) Locate a distant red level storm or adjust the TILT control down until a red level ground return
appears near the outer edge.
(3) Reduce the range until the red level return is off the screen, but not more than 25 miles beyond
the selected range.
(4) Observe that the word TGT ALRT flashes on the MFD display.
(5) Return the TILT control to the normal position.
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2.8.2.5 Testing Completed
This completes the flight check procedures; however, refer to the RDR-1600 Pilot’s Guide
(TM106101) for additional details relating to operation of the RDR-1600 Weather Radar System.
2.9
ILLUSTRATIONS AND DRAWINGS
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Figure 2.9-1. Video Pattern, Level Flight
Figure 2.9-2. Video Pattern With Stab Error
Figure 2.9-3. Video Pattern With Stab Error
Figure 2.9-4. Video Pattern, No Stabilization
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This Page Intentionally Left Blank
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Figure 2.9-5. RT-1601 Receiver Transmitter Outline Drawing
(Drawing No. 379-2011-001) (Sheet 2 of 2)
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Figure 2.9-6. DA-1203A Antenna Drive Outline Drawing
(Drawing No. 4000504)
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Figure 2.9-7. CP-113 Radar Control Panel Outline Drawing
(Drawing No. 3614278)
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Figure 2.9-8. RDR-1600 System Wiring Diagram With Analog Gyros
(Drawing No. WD379-2015-001)
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Figure 2.9-9. RDR-1600 System Wiring Diagram With AHRS System
(Drawing No. WD379-2016-001)
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Figure 2.9-10. DA-1203A Antenna Mount Hole Pattern
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