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.
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. TM106601_(7/01) FMi USE OR DISCLOSURE OF DATA CONTAINED ON THIS PAGE IS SUBJECT TO THE RESTRICTION ON THE TITLE PAGE OF THIS DOCUMENT.
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.
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.
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.
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.
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.
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.
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.
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 ....
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.
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.........................................
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 ........................................
COMMAND SYSTEMS DIVISION RECORD OF REVISIONS Revision No. Revision Date Insertion Date Notes Original Issue – July 2001 TM106601_(7/01) v USE OR DISCLOSURE OF DATA CONTAINED ON THIS PAGE IS SUBJECT TO THE RESTRICTION ON THE TITLE PAGE OF THIS DOCUMENT.
COMMAND SYSTEMS DIVISION LIST OF EFFECTIVE PAGES Page(s) Subject Date Title July 2001 Copyright July 2001 FMi Radiation Warning July 2001 FMii Max.
COMMAND SYSTEMS DIVISION SERVICE BULLETIN LIST Service Bulletin No. Related Equipment Date Purpose No RDR-1600 SB’s have been issued TM106601_(7/01) vii USE OR DISCLOSURE OF DATA CONTAINED ON THIS PAGE IS SUBJECT TO THE RESTRICTION ON THE TITLE PAGE OF THIS DOCUMENT.
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.
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.
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).
COMMAND SYSTEMS DIVISION Table 1.2-1.
COMMAND SYSTEMS DIVISION 1.2.2 CP-113 Unit Description 1.2.2.1 CP-113 Function Select Switch Table 1.2-2.
COMMAND SYSTEMS DIVISION 1.2.2.2 CP-113 Mode Push Buttons Table 1.2-3.
COMMAND SYSTEMS DIVISION 1.2.2.3 CP-113 Additional Switches and Controls Table 1.2-4.
COMMAND SYSTEMS DIVISION 1.3 ADDITIONAL EQUIPMENT REQUIRED FOR COMPLETE INSTALLATION 1.3.1 Additional Available Equipment Table 1.3-1.
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.
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 1 0.5, 1 2 0.5, 1, 1.5, 2 5 1.25, 2.5, 3.75, 5 10 2.5, 5, 7.
COMMAND SYSTEMS DIVISION 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.
COMMAND SYSTEMS DIVISION 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.
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.
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.
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.
COMMAND SYSTEMS DIVISION 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.
COMMAND SYSTEMS DIVISION 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.
COMMAND SYSTEMS DIVISION 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 0 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.
COMMAND SYSTEMS DIVISION 60 ON TST WX BCN ONLY WXA SBY BCN FMT SRCH OFF SRCH BCN CODE GAIN UP TILT 0 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.
COMMAND SYSTEMS DIVISION 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.
COMMAND SYSTEMS DIVISION 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.
COMMAND SYSTEMS DIVISION 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.
COMMAND SYSTEMS DIVISION 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.
COMMAND SYSTEMS DIVISION 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.
COMMAND SYSTEMS DIVISION 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.
COMMAND SYSTEMS DIVISION 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).
COMMAND SYSTEMS DIVISION 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.
COMMAND SYSTEMS DIVISION 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.
COMMAND SYSTEMS DIVISION 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.
COMMAND SYSTEMS DIVISION Table 1.6-5.
COMMAND SYSTEMS DIVISION 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).
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.
COMMAND SYSTEMS DIVISION 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.
COMMAND SYSTEMS DIVISION 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.
COMMAND SYSTEMS DIVISION 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.
COMMAND SYSTEMS DIVISION (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.
COMMAND SYSTEMS DIVISION 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.
COMMAND SYSTEMS DIVISION 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.
COMMAND SYSTEMS DIVISION 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.
COMMAND SYSTEMS DIVISION 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.
COMMAND SYSTEMS DIVISION 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.
COMMAND SYSTEMS DIVISION Figure 2.7-1. Generic MFD Display TM106601_(7/01) 2-11 USE OR DISCLOSURE OF DATA CONTAINED ON THIS PAGE IS SUBJECT TO THE RESTRICTION ON THE TITLE PAGE OF THIS DOCUMENT.
COMMAND SYSTEMS DIVISION Figure 2.7-2. Radar Control Panel TM106601_(7/01) 2-12 USE OR DISCLOSURE OF DATA CONTAINED ON THIS PAGE IS SUBJECT TO THE RESTRICTION ON THE TITLE PAGE OF THIS DOCUMENT.
COMMAND SYSTEMS DIVISION 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°.
COMMAND SYSTEMS DIVISION 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).
COMMAND SYSTEMS DIVISION 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.
COMMAND SYSTEMS DIVISION 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.
COMMAND SYSTEMS DIVISION (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.
COMMAND SYSTEMS DIVISION 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.
COMMAND SYSTEMS DIVISION (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".
COMMAND SYSTEMS DIVISION 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.
COMMAND SYSTEMS DIVISION (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.
COMMAND SYSTEMS DIVISION 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 TM106601_(7/01) 2-22 USE OR DISCLOSURE OF DATA CONTAINED ON THIS PAGE IS SUBJECT TO THE RESTRICTION ON THE TITLE PAGE OF THIS DOCUMENT.
COMMAND SYSTEMS DIVISION 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 TM106601_(7/01) 2-23 USE OR DISCLOSURE OF DATA CONTAINED ON THIS PAGE IS SUBJECT TO THE RESTRICTION ON THE TITLE PAGE OF THIS DOCUMENT.
COMMAND SYSTEMS DIVISION This Page Intentionally Left Blank TM106601_(7/01) 2-24 USE OR DISCLOSURE OF DATA CONTAINED ON THIS PAGE IS SUBJECT TO THE RESTRICTION ON THE TITLE PAGE OF THIS DOCUMENT.
TM106601_(7/01) USE OR DISCLOSURE OF DATA CONTAINED ON THIS PAGE IS SUBJECT TO THE RESTRICTION ON THE TITLE PAGE OF THIS DOCUMENT.
COMMAND SYSTEMS DIVISION Figure 2.9-5. RT-1601 Receiver Transmitter Outline Drawing (Drawing No. 379-2011-001) (Sheet 2 of 2) TM106601_(7/01) 2-27/(2-28 blank) USE OR DISCLOSURE OF DATA CONTAINED ON THIS PAGE IS SUBJECT TO THE RESTRICTION ON THE TITLE PAGE OF THIS DOCUMENT.
COMMAND SYSTEMS DIVISION Figure 2.9-6. DA-1203A Antenna Drive Outline Drawing (Drawing No. 4000504) TM106601_(7/01) 2-29/(2-30 blank) USE OR DISCLOSURE OF DATA CONTAINED ON THIS PAGE IS SUBJECT TO THE RESTRICTION ON THE TITLE PAGE OF THIS DOCUMENT.
COMMAND SYSTEMS DIVISION Figure 2.9-7. CP-113 Radar Control Panel Outline Drawing (Drawing No. 3614278) TM106601_(7/01) 2-31/(2-32 blank) USE OR DISCLOSURE OF DATA CONTAINED ON THIS PAGE IS SUBJECT TO THE RESTRICTION ON THE TITLE PAGE OF THIS DOCUMENT.
COMMAND SYSTEMS DIVISION Figure 2.9-8. RDR-1600 System Wiring Diagram With Analog Gyros (Drawing No. WD379-2015-001) TM106601_601b2 2-31/(2-32 blank) USE OR DISCLOSURE OF DATA CONTAINED ON THIS PAGE IS SUBJECT TO THE RESTRICTION ON THE TITLE PAGE OF THIS DOCUMENT.
COMMAND SYSTEMS DIVISION Figure 2.9-9. RDR-1600 System Wiring Diagram With AHRS System (Drawing No. WD379-2016-001) TM106601_(7/01) 2-35/(2-36 blank) USE OR DISCLOSURE OF DATA CONTAINED ON THIS PAGE IS SUBJECT TO THE RESTRICTION ON THE TITLE PAGE OF THIS DOCUMENT.
Figure 2.9-10. DA-1203A Antenna Mount Hole Pattern TM106601_(7/01) 2-39/(2-40 blank) USE OR DISCLOSURE OF DATA CONTAINED ON THIS PAGE IS SUBJECT TO THE RESTRICTION ON THE TITLE PAGE OF THIS DOCUMENT.
