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Canon 1014XL-S Camcorder User Manual

1. A 10 B ENHANCED GROUND PROXIMITY WARNING SYSTEM EGPWS B 1 System Operation II WA AWA B 1 EGPWS Controls WA B 1 Related EGPWS System Operation B 3 EGPWS Operation B 3 EGPWS Display sseseseess B 4 EGPWS TOSI uetus te e eda on B 6 INDEX Index 1 List of Illustrations Figure Page 2 1 PRIMUS 660 Configurations 2 2 2 2 Typical PRIMUS 660 Weather Radar Components 2 5 3 1 Typical PRIMUS 660 Digital Weather Radar Display 3 1 3 2 WI 650 660 Weather Radar Indicator Front Panel MI NC 3 2 3 3 WI 650 660 Weather Radar Indicator Display Screen Features 3 5 3 4 WC 660 Weather Radar Controller Configurations 3 10 4 1 EFIS Test Pattern Typical 120 Scan Shown 4 3 4 2 Indicator Test Pattern 120 Scan WX With TEXT FAULT Enabled 4 3 A28 1146 111 Table of Contents REV2 TC 3 PRIMUS 660 Digital Weather Radar System Table of Contents cont List of Illustrations cont Figure Page 5 1 Positional Relationship of an Airplane and Storm Cells Ahead as Displayed on Indicator 5 2 5 2 Antenna Beam Slicing Out Cross Section of Storm During Horizontal Scan 5 3 5 8 Sea Returns 5 4 5
2. 60 40 lt gt AD 17720 R3 Symmetrical Ground Returns Good Roll Stabilization Figure 5 21 AD 17721 R2 0 Understabilization in a Right Turn Figure 5 22 Radar Facts A28 1146 111 5 20 REV2 PRIMUS 660 Digital Weather Radar System AD 17722 R2 0 Overstabilization in a Right Turn Figure 5 23 100 p NES Roll Stabilization Inoperative in a Turn Figure 5 24 AD 17723 R2 A28 1146 111 Radar Facts REV2 5 21 PRIMUS 660 Digital Weather Radar System Pitch Gain Error If the aircraft is in a pitch maneuver and you see ground returns that are not present in level flight the pitch gain is most likely misadjusted The procedure in table 5 5 and figures 5 25 5 26 and 5 27 can help you identify this type of problem PITCH STABILIZATION CHECK Once proper operation of the roll stabilization is established verify pitch stabilization using the procedure in table 5 5 and figures 5 25 5 26 and 5 27 Sep Pee Complete the steps listed in table 5 3 Place the aircraft between 5 and 10 pitch up 3 Note the radar display If it is correctly stabilized there is very little change in the ground returns 4 If the display of ground returns resembles figure 5 26 the radar is understabilized 5 If the display of ground returns resembles figure 5 27 the radar is overstabilized Pitch Stabilization In Flight Check Procedure Table 5 5 AD 17720 R3 Symmetrical Gr
3. 7 8 Roll Stabilization Check 7 9 Roll Gain Adjustment 7 11 Pitch Stabilization Check 7 12 Pitch Gain Adjustment 7 15 8 IN FLIGHT TROUBLESHOOTING 8 1 Test Mode With Text Faults Enabled 8 2 Pilot Event Marker 8 4 Fault Code and Text Fault Relationships 8 5 9 HONEYWELL PRODUCT SUPPORT 9 1 Publication Ordering Information 9 4 10 ABBREVIATIONS 10 1 l APPENDICES A FEDERAL AVIATION ADMINISTRATION FAA ADVISORY CIRCULARS A 1 Subject Recommended Radiation Safety Precautions For Ground Operation Of Airborne Weather Radar PUIPOSE EFC A 1 Cancellation A 1 Related Reading Material A 1 Background 02 cee eee eee eee A 1 Precautions A 2 Table of Contents A28 1146 111 TC 2 REV2 PRIMUS 660 Digital Weather Radar System Table of Contents cont A FEDERAL AVIATION ADMINISTRATION FAA ADVISORY CIRCULARS coNr Subject Thunderstorms A 3 PUIPOS IA thie PA pu ER RR ne yess A 3 Cancellation A 3 Related Reading Material A 3 Genera e ER A 3 TAZ ANOS cT rcp A 4 National Severe Storms Laboratory NSSL Thunderstorm Research
4. PRIMUS 660 Digital Weather _ Radar system Pilot s Manual a E E l Honeywell Honeywell Aerospace Electronic Systems CES Phoenix P O Box 21111 Phoenix Arizona 85036 1111 U S A TO HOLDERS OF THE PRIMUS 660 DIGITAL WEATHER RADAR SYSTEM PILOT S MANUAL HONEYWELL PUB NO A28 1146 111 REVISION NO 3 DATED AUGUST 2003 HIGHLIGHTS Pages that have been revised are outlined below Remove and insert the affected pages listed The revision number has been added to the bottom of the revised pages and revision bars have been used to indicate the revised or added text Insert this highlights letter in the manual in your possession ahead of page RR 1 RR 2 Record of Revisions The List of Effective Pages shows the order in which to insert the attached new pages of front material into your manual Page No Description of Change Title Page Revised to reflect revision 3 Update Proprietary Notice Changed S99 to S2003 and changed copyright from 1999 to 2003 RR 1 RR 1 Revised to reflect revision 3 LEP 1 thru Revised to reflect revision 3 LEP 3 LEP 4 6 1 6 2 Removed Inc in Honeywell in paragraph above figure Replaced art in Flgure 6 1 Highlights Page 1 of 1 August 2003 Honeywell Honeywell Aerospace Electronic Systems CES Phoenix P O Box 21111 Phoenix Arizona 85036 1111 U S A PRIMUS 660 Digital Weather Radar System Pilots Manual Revised August 2003 Printed in U S
5. vA fees E BEAM WIDTH AD 35702 Rules of Thumb Figure 5 17 Radar Facts A28 1146 111 5 14 REV2 PRIMUS 660 Digital Weather Radar System STABILIZATION The purpose of the stabilization system is to hold the elevation of the antenna beam relative to the earth s surface constant at all azimuths regardless of aircraft bank and pitch maneuvers The stabilization System uses the aircraft attitude source as a reference Several sources of error exist in any stabilization system Dynamic Error Dynamic error is the basis of the stabilization system Stabilization is a corrective process It logically follows that there must first be some error to correct In stabilization this error is called dynamic An example of dynamic error occurs when a gust lifts the right wing and the pilot instinctively raises the right aileron and lowers the left In this action the pilot detects a changing dynamic error in aircraft attitude and corrects it As the gust lifts the wing the aircraft attitude source sends a continuous stream of attitude change information to stabilization circuits that in turn control the motors that raise and lower the beam In short a dynamic error in aircraft attitude as seen by the radar is detected and the antenna attitude is corrected for it Extremely small errors of less than 1 can be detected and compensated However the point is ultimately reached where dynamic error is too small to be detected
6. 0 0 AAA Pitch Gain Error 0 00000 cece ene Interpreting Weather Radar Images Weather Display Calibration Variable Gain Control Rain Echo Attenuation Compensation Technique REACT amp xen Re Rr REPRERDR Ee IARE TR Shadowing ili aa Turbulence Probability Hail Size Probability Spotting Hail 0 0 eee eee eee Azimuth Resolution Radome ioc aes dead ace ta E RR REN Weather Avoidance Configurations of Individual Echoes Northern Hemisphere 000ceeeeeee ee eee Line Configurations yA BRBRRBA OnaARA A I LI LI LI LI LI ool ol 0 KINO 00010002 CQO1O1OC1C01C01C0101C6C1 CO1O101C01C10101010101 OK ARRAROA QOIIDIMD a VN ONMA NORRA ag Table of Contents TC 1 PRIMUS 660 Digital Weather Radar System Table of Contents cont Section Page 5 RADAR FACTS coNr Additional Hazards 5 55 Ground Mapping 5 56 6 MAXIMUM PERMISSIBLE EXPOSURE LEVEL MPEE A code cade ck ae dance ede nus cedas na eHs 6 1 7 IN FLIGHT ADJUSTMENTS 7 1 Pitch and Roll Trim Adjustments 7 1 Level Fight Stabilization Check 7 3 Roll Offset Adjustment 7 5 Pitch Offset Adjustment
7. 111 Enhanced Ground Proximity Warning System EGPWS REV2 B 5 PRIMUS 660 Digital Weather Radar System EGPWS Test When the EGPWS is selected for display it can be tested Push the remote mounted EGPWS TEST button to display the test format shown in figure B 2 EGPWS Test Display Figure B 2 Enhanced Ground Proximity Warning System EGPWS A28 1146 111 B 6 REV2 PRIMUS 660 Digital Weather Radar System Index A Abbreviations 10 1 Accelerative Error 5 15 Additional hazards 5 55 turbulence versus distance from storm core 5 55 turbulence versus distance from storm edge 5 55 Altitude A 10 relationship between turbulence and altitude A 10 Antenna mounting error 5 16 level flight stabilization check 5 17 stabilization in straight and level flight check procedure 5 17 Azimuth resolution 5 41 C Cockpit mounted equipment 2 4 Configurations of individual echoes northern hemisphere 5 47 avoid all crescent shaped echoes by 20 miles 5 51 avoid hook echoes by 20 miles 5 47 avoid pendant by 20 miles 5 50 avoid steep rain gradients by 20 miles 5 51 avoid V notch by 20 miles 5 49 Customer support centers 9 2 North America 9 2 Rest of the World 9 3 D Do s and don ts of thunderstorm flying A 8 Dynamic Error 5 15 A28 1146 111 REV2 E Effect on altimeters A 7 Enhanced ground proximity warning system EGPWS B 1 annunciators B 2 FAIL B 2 INHIB B 2 O
8. 24 HOUR EXCHANGE RENTAL SUPPORT CENTERS U S A DALLAS 800 872 7739 972 402 4300 FRANCE TOULOUSE 33 0 5 6171 9662 SINGAPORE 65 542 1313 CANADA OTTAWA 800 267 9947 613 728 4681 GERMANY AOA GAUTING 0172 8207300 in Germany 49 172 8207300 outside Germany CUSTOMER SUPPORT CENTERS NORTH AMERICA Dallas Support Center Honeywell Inc Commercial Aviation Systems 7825 Ridgepoint Dr IRVING TX 75063 TEL 972 402 4300 FAX 972 402 4999 Minneapolis Support Center Honeywell Inc Commercial Aviation Systems 8840 Evergreen Boulevard MINNEAPOLIS MN 55433 6040 Canada Support Center Honeywell Inc Commercial Aviation Systems 3 Hamilton Avenue North OTTAWA ONTARIO K1Y 4J4 TEL 613 728 4681 FAX 613 728 7084 Ohio Support Center Honeywell Inc Commercial Aviation Systems 8370 Dow Circle STRONGSVILLE OH 44136 TEL 612 957 4051 FAX 612 957 4698 Central Support Center Honeywell Inc Commercial Aviation Systems 1830 Industrial Avenue WICHITA KS 67216 TEL 316 522 8172 FAX 316 522 2693 Honeywell Product Support 9 2 TEL 440 243 8877 FAX 440 243 1954 Northwest Support Center Honeywell Inc Commercial Aviation Systems 4150 Lind Avenue Southwest RENTON WA 98055 TEL 425 251 9511 TLX 320033 FAX 425 243 1954 A28 1146 111 REV2 PRIMUS 660 Digital Weather Radar System CUSTOMER SUPPORT CENTERS N
9. Oc ooo00 I0O01 MPEL Boundaty c eei ERRARE EE 1 Symmetrical Ground Returns 6 7 4 7 4 Ground Return Indicating Misalignment Left 7 5 7 7 7 7 7 2 Ground Return Indicating Misalignment Right 7 3 7 4 Roll Offset Adjustment Display Initial 7 5 Roll Offset Adjustment Display Final 7 6 Symmetrical Ground Returns Level Flight and Good Roll Stabilization 7 10 7 7 Understabilization in a Right Roll 7 10 7 8 Overstabilization in a Right Roll 7 11 7 9 Level Flight and Good Pitch Stabilization 7 13 7 10 Understabilized in Pitch Up 7 14 7 11 Overstabilized in Pitch Up 7 14 8 1 Fault Annunciation on Weather Indicator With TEXT FAULT Fields casing cece ret 8 3 8 2 Fault Code on EFIS Weather Display With TEXT FAULTS Disabled 8 3 8 3 Radar Indication With Text Fault Enabled On Ground uiuo ick ea ne tr cesta 8 4 A 1 Schematic Cross Section of a Thunderstorm A 6 A28 1146 111 Table of Contents REV2 TC 5 PRIMUS 660 Digital Weather Radar System Figure B B 2 7 1 7 2 7 3 Table of Contents TC 6 Table of Contents cont List of Illustrations cont EHSI Display Over KPHX Airport With the EGPWS Display ii ia ka EGPWS Test Display List of Tables Dual Control Mode Truth
10. Without detection there is no compensation Accelerative Error One of the most common forms of error seen in a radar antenna stabilization system results from forces of acceleration on the aircraft equipped with a vertical gyroscope Acceleration forces result from speeding up slowing down or turning Radar stabilization accuracy depends upon the aircraft vertical gyroscope Therefore any gyroscopic errors accumulated through acceleration are automatically imparted to the antenna stabilization system NOTE LASEREF vertical reference systems do not suffer from these acceleration effects A28 1146 111 Radar Facts REV2 5 15 PRIMUS 660 Digital Weather Radar System A vertical gyroscope contains a gravity sensitive element a heavily dampened pendulous device that enables the gyro to erect itself to earth gravity at the rate of approximately 2 min The pendulous device is unable to differentiate between earth gravity and an acceleration force It tends to rest at a false gravity position where the forces of gravity and acceleration are equal As long as the acceleration force persists the gyroscope precesses toward a false gravity position at the rate of approximately 2 min The radar follows the gyroscope into error at the same rate When the acceleration force ceases the gyroscope precesses back to true gravity erection at the same rate Some vertical gyroscopes have provisions for deactivating the roll erection torque m
11. e WX GREEN RCT GREEN GMAP GREEN TGT ALERT ON RED WAIT AMBER TGT ALERT OFF FAIL N AMBER BLACK AND S FPEN NOISE BAND TEXT AREA ANTENNA TILT GRAY ANGLE MAGENTA REACT OFF BLACK BLUE REACT ON CYAN YELLOW RED WX RANGE GREEN ANNUNCIATOR WHITE NOTES 1 IF THE BITE DETECTS A FAULT IN TEST MODE FAIL N WILL BE SHOWN N IS A FAULT CODE 2 ANY FAULT CODE CAN ALSO BE DISPLAYED IN THE MAINTENANCE MODE IN THAT CASE IT REPLACES THE ANTENNA TILT ANGLE AD 51774 EFIS Test Pattern Typical 120 Scan Shown Figure 4 1 f AD 51773 Indicator Test Pattern 120 Scan WX With TEXT FAULT Enabled Figure 4 2 A28 1146 111 Normal Operation REV2 4 3 PRIMUS 660 Digital Weather Radar System NOTES 1 Refer to the specific EFIS manual for a detailed description 2 The example shown is for installations with TEXT FAULT disabled Standby When Standby is selected and the radar is not in dual control mode refer to table 2 1 dual control mode truth table for dual control operation the antenna is stowed in a tilt up position and is neither scanning nor transmitting Standby should be selected when the pilot wants to keep power applied to the radar without transmitting Radar Mode Weather For purposes of weather avoidance pilots should familiarize themselves with FAA Advisory Circular AC 00 24B 1 20 83 Subject Thunderstorms
12. 4812 IOP Mailbox 04 MAILBOK RAM PULL POWER 4818 DSP Mailbox RTA Text Faults Table 8 2 cont A28 1146 111 In Flight Troubleshooting REV2 8 5 PRIMUS 660 Digital Weather Radar System 4813 Timing FPGA RAM 4814 Timing FPGA REG FPGA RADAR PULL POWER ON 05 4815 IO FPGA RAM FAIL RTA 4828 FPGA Download 4906 IO FPGA REG 4847 STC Monitor STC DAC RADAR PULL POWER ON FAIL RTA 4830 HVPS Monitor HVPS MON RADAR PULL CONTINUOUS FAIL RTA 4816 DSP RAM 4817 DSP Video RAM POWER ON 4855 DSP Watchdog CONTINUOUS 4900 Mailbox Miscompare DSP RADAR PULL FAIL RTA 4901 DSP HOLDA Asserted 4902 DSP HOLDA Not POWER ON Asserted 07 10 4825 Filament Monitor MAGNETRON LATCHED 4827 Severe Magnetron RADAR PULL 11 FAIL RTA 4829 PFN Trim Monitor HVPS MON CONTINUOUS 12 4831 Pulse Width PULSE WIDTH RADAR PULL CONTINUOUS UNCAL RTA 13 4832 Elevation Error EL POSITION TILT CONTINUOUS UNCAL 14 15 20 4833 Azimuth Error AZ POSITION AZIMUTH CONTINUOUS UNCAL 4836 Over TEMP OVER TEMP RADAR PULL CONTINUOUS CAUTION RTA 4837 XMITTER Power XMTR POWER RADAR PULL CONTINUOUS UNCAL RTA 4839 No SCI Control CHK CHK NO CNTL IN CNTL CNTL PROBE 4911 No ARINC 429 Control SRC SRC Text Faults Table 8 2 cont In Flight Troubleshooting A28 1146 111 8 6 REV2 PRIMUS 660 Digital Weather Radar System 4840 AGC Limiting CA Eod CA PULL RTA 4927 AGC RX DAC Monitor AGC RADAR POWER ON FAIL 4928 AGC TX
13. GSPD HOLDA HVPS INHIB INT lO IOP IRS kt LEWP LSS LX MAINT MFD MON MPEL MSG N A NAV ND NM NSSL NWS OSC PFN POC PPI RCT REACT RCVR Abbreviations 10 2 DEFINITION Feet Foot Ground Mapping Global Positioning System Groundspeed Hold Acknowledge High Voltage Power Supply Inhibit Interrupt Input Output Inoperative Inertial Reference System Knot s Line Echo Wave Patterns Lightning Sensor System Maintenance Multifunction Display Monitor Maximum Permissible Exposure Level Message Not Applicable Navigation Navigation Display Nautical Mile National Severe Storms Laboratory National Weather Service Oscillator Pulse Forming Network Power on Count Plan Position Indicator Rain Echo Attenuation Compensation Technique Receiver A28 1146 111 REV2 TERMS REG RTA RX SBY STBY SCI SCT SECT SLV SPEX STAB STB STC TCAS TEMP TERR TGT TST TX UDI UNCAL VAR VIP WOW WX XMIT XMITTER XMTR XREF XSTC A28 1146 111 REV2 PRIMUS 660 Digital Weather Radar System DEFINITION Register Receiver Transmitter Antenna Receiver Standby Serial Control Interface Scan Sector Slave Spares Exchange Stabilization Sensitivity Time Control Traffic Alert and Crew Alerting System Temperature Terrain Target Test Transmitter Universal Digital Interface Uncalibration Variance Video Integrated Processor We
14. a line maintenance message are associated with each fault condition Faults can be accessed on the ground or while airborne e Display indicator or RTA malfunction e FAIL annunciation on weather indicator or EFIS display If the feature TEXT FAULTS is enabled the radar test pattern area displays plain English text fault information If it is not enabled only the fault code is shown one at a time on the indicator or EFIS display The PRIMUS 660 also contains a feature called Pilot Event Marker that enables the pilot to record a full set of BITE parameters at any time typically if the radar seems to be malfunctioning NOTES 1 In some EFIS installations radar failures are only annunciated with an amber WX if faults are not enabled 2 In EFIS installations with TEXT FAULTS enabled the fault codes are also presented as part of the FAIL annunciation e g FAIL 13 A28 1146 111 In Flight Troubleshooting REV2 8 1 PRIMUS 660 Digital Weather Radar System TEST MODE WITH TEXT FAULTS ENABLED When airborne if the radar is switched to TEST mode any current faults are displayed When on the ground weight on wheels active and the radar is switched to TEST mode any current faults are displayed followed by up to 32 faults from the last 10 power on cycles The historic faults are displayed going from the most recent to the oldest and are cycled every two antenna sweeps approximately 8 seconds The POC number indic
15. 111 5 34 REV2 PRIMUS 660 Digital Weather Radar System Although penetrating a storm with a red level three core appears to be an acceptable risk it is not At the lower end of the red zone there is no chance of extreme turbulence a slight chance of severe turbulence and a 4096 chance of moderate turbulence However the radar lumps all of the rainfall rates between 12 mm to 50 mm per hour into one group a level three red Once the rainfall rate reaches the red threshold it masks any additional information about the rainfall rate until the magenta threshold is reached A red return covers a range of turbulence probabilities and the worst case must be assumed especially since extreme destructive turbulence is born in the red zone Therefore once the red threshold is reached the risk in penetration becomes totally unacceptable Likewise once the magenta threshold is reached it must be assumed that more severe weather is being masked LEVEL 1 LEVEL 2 LEVEL 3 LEVEL 4 GREEN YELLOW RED MAGENTA 100 90 80 gt 5 70 oO a 60 o amp uj 50 o zZ 4 4096 2 a E 3096 p 20 10 0 4 mm Hr 12 mm Hr 50 mm Hr RAINFALL RATE AD 15357 R3 Probability of Turbulence Presence in a Weather Target Figure 5 32 A28 1146 111 Radar Facts REV2 5 85 PRIMUS 660 Digital Weather Radar System Turbulence levels are listed and described in table 5 8 REACTION INSIDE INTENSITY AIRCRAFT REACTIO
16. 4 Radar Beam Illumination High Altitude 12 Inch Radiator IA 0c eee eee eee 5 5 5 5 Radar Beam Illumination High Altitude 18 Inch Radiator 5 5 5 6 Radar Beam Illumination Low Altitude 12 Inch Radiator cece eee eee 5 6 5 7 Radar Beam Illumination Low Altitude 18 Inch Radiator 2 e eee eee 5 6 5 8 Ideal Tilt Angle 5 10 5 9 Earth s Curvature 5 10 5 10 Convective Thunderstorms 5 11 5 11 Unaltered Tilt 2 cece eee eee 5 11 5 12 Proper Tilt Technique 5 12 5 13 Tilt Management With Heading Changes 5 12 5 14 Fast Developing Thunderstorm 5 13 5 15 Low Altitude Tilt Management 5 13 5 16 Antenna Size and Impact on Tilt Management 5 14 5 1 Rules of Thumb 2m lI RR ERR 5 14 5 18 Symmetrical Ground Returns 5 17 5 19 Ground Return Indicating Misalignment Upper Right ose omes 5 18 5 20 Ground Return Indicating Misalignment Upper Left 1 sce teats a oem 5 18 5 21 Symmetrical Ground Returns Good Roll Stabilization WA aaa 5 20 5 22 Understabilization in a Right Turn 5 20 5 23 Overstabilization in a Right Turn 5 21 5 24 Roll Stabilization Inoperative in a Turn 5 21 5 25 Symmetrical Ground Returns Good Pitch Stabilization Ia 5 26 Understabilized in Pitth
17. A Pub No A28 1146 111 03 February 1998 PROPRIETARY NOTICE This document and the information disclosed herein are proprietary data of Honeywell Neither this document nor the information contained herein shall be used reproduced or disclosed to others without the written authorization of Honeywell except to the extent required for installation or maintenance of recipient s equipment NOTICE FREEDOM OF INFORMATION ACT 5 USC 552 AND DISCLOSURE OF CONFIDENTIAL INFORMATION GENERALLY 18 USC 1905 This document is being furnished in confidence by Honeywell The information disclosed herein falls within exemption b 4 of 5 USC 552 and the prohibitions of 18 USC 1905 All rights reserved No part of this book CD or PDF may be reproduced or transmitted in any form or by any means electronic or mechanical including photocopying recording or by any information storage and retrieval system without the written permission of Honeywell International except where a contractual arrangement exists between the customer and Honeywell 2003 ASSOCIATE MEMBER AIRCRAFT ELECTRONICS ASSOCIATION Ss Member of GAMA General Aviation Manufacturer s Association PRIMUS and LASEREF are U S registered trademarks of Honeywell DATA NAV is a U S trademarks of Honeywell 2003 Honeywell International Inc PRIMUS 660 Digital Weather Radar System Record of Revisions Upon receipt of a revision inser
18. DAC Monitor 4841 Selftest OSC Failure RCVR PICTURE PULL SELF TEST UNCAL RTA CONTINUOUS 4843 Multiple AFC Unlocks SPOKING CONTINUOUS 4845 AFC Sweeping LIKELY 24 AFC PULL RTA 4929 AFC RX DAC Monitor 4930 AFC Trim DAC Monitor 4848 AHRS IRS Source NO STAB SRC CHK ATT INSTALLATION R 4852 Analog STAB REF one 4853 Scan Switch Off SCAN SWITCH Pia CHK INSTALLATION WITCH SWITCH 4854 XMIT Switch Off XMIT SWITCH XMIT CHK INSTALLATION WITCH SWITCH 4914 Invalid Altitude Airspeed STAB Strapping INVALID RADAR CHK STRAPS UNCAL STRAPS 36 4915 Invalid Controller POWER ON Source Strapping 4916 Config1 Database Version Size Mismatch RADAR PULL FAIL RTA Text Faults Table 8 2 POWER ON A28 1146 111 In Flight Troubleshooting REV2 8 7 PRIMUS 660 Digital Weather Radar System Table 8 3 describes the pilot messages LINE NEN RADAR FAIL The radar is currently inoperable and should not be relied upon It needs to be replaced or repaired at the next opportunity RADAR CAUTION A failure has been detected that can compromise the calibration accuracy of the radar Information from the radar should be used only for advisory purposes such as ground mapping for navigation PICTURE UNCAL The radar functions are ok but receiver calibration is degraded Color level calibration should be assumed to be incorrect Have the RTA checked at the next opportunity TILT UNCAL An error in the antenna position system has been
19. LIGHT RAINFALL MODERATE RAINFALL HEAVY RAINFALL SEVERE RAINFALL s SN AZ scr 30 ZE W o 10 SBY ON rp SA n emm X GAN TH hg ZNS MIN S MAX QULA as AD 51780 Weather Display Figure 5 39 Step Procedure 1 Keep TGT alert enabled when using short ranges to be alerted if a new storm cell develops in the aircraft s flightpath 2 Keep the gain in preset The gain control should be in preset except for brief periods when variable gain is used for detailed analysis Immediately after the analysis switch back to preset gain WARNING DO NOT LEAVE THE RADAR IN VARIABLE GAIN SIG NIFICANT WEATHER CAN NOT BE DISPLAYED Severe Weather Avoidance Procedures Table 5 9 cont A28 1146 111 Radar Facts REV 2 5 43 PRIMUS 660 Digital Weather Radar System Step Procedure Any storm with feels va at or greater than 20 000 feet must be avoided by 20 N WARNING DRY HAIL CAN BE PREVALENT AT HIGHER ALTITUDES WITHIN NEAR OR ABOVE STORM CELLS AND SINCE ITS RADAR REFLECTIVITY IS POOR IT can NOT BE DETECTED For brief periods use increased gain rotate GAIN control to its maximum cw position when flying near storm tops This helps display the normally weaker returns that could be associated with hail When flying at high altitudes tilt downward frequently to avoid flying above storm tops Studies by the National Severe Storms Laboratory NSSL of Oklahoma have determined that thund
20. PRIMUS 660 Digital Weather Radar System RADOME Ice or water on the radome does not generally cause radar failure but it hampers operation The radome is constructed of materials that pass the radar energy with little attenuation Ice or water increases the attenuation making the radar appear to have less sensitivity Ice can cause refractive distortion a condition characterized by loss of image definition If the ice should cause reverberant echoes within the radome the condition might be indicated by the appearance of nonexisting targets The radome can also cause refractive distortion that would make it appear that the TILT control was out of adjustment or that bearing indications were somewhat erroneous A radome with ice or water trapped within its walls can cause significant attenuation and distortion of the radar signals This type of attenuation cannot be detected by the radar even with REACT on but it can in extreme cases cause blind spots If a target changes significantly in size shape or intensity as aircraft heading or attitude change the radome is probably the cause Radar Facts A28 1146 111 5 42 REV2 PRIMUS 660 Digital Weather Radar System WEATHER AVOIDANCE Figure 5 39 illustrates a typical weather display in WX mode Recommended procedures when using the radar for weather avoidance are given in table 5 9 The procedures are given in bold face explanations of the procedure follow in normal type face
21. SYSTEM OPERATION To display the EGPWS the weather system can be in any mode except OFF When the EGPWS is active the indicator range up and down arrows control the EGPWS display range The AZ button on the indicator is also active and the azimuth lines can be displayed or removed The other radar controls do not change the terrain display but if they are used while the EGPWS is displayed they control the radar receiver transmitter antenna RTA and the effect is displayed when the system returns to the radar display EGPWS Controls The typical EGPWS installation has remotely mounted push button controls and status annunciators that are related to the display on the radar indicator The paragraphs below give a functional description of the AlliedSignal recommended controls A28 1146 111 Enhanced Ground Proximity Warning System EGPWS REV2 B PRIMUS 660 Digital Weather Radar System PUSH BUTTON CONTROLS The following remotely mounted push buttons control the EGPWS display e INHIB Inhibit Button When active the push on push off INHIB button prevents terrain data from being displayed on the radar indicator When the button is active the INHIB annunciator lights e ON Terrain Button When active the push on push off ON button displays terrain on the radar indicator ANNUNCIATORS The following annunciators are displayed on the radar indicator to indicate EGPWS operation e FAIL The FAIL annunciator
22. Up 5 27 Overstabilized in Pitch Up 5 28 Weather Radar Images 5 29 Radar and Visual Cloud Mass 5 30 Squall Line 5 31 REACT ON and OFF Indications Tagga g UNNDNNNN Co 4 O0 I UOUN Table of Contents A28 1146 111 TC 4 REV2 Figure 5 32 5 33 5 34 5 35 5 36 5 37 5 38 5 39 5 40 5 41 5 42 5 43 5 44 5 45 5 46 5 47 6 1 7 1 PRIMUS 660 Digital Weather Radar System Table of Contents cont List of Illustrations cont g Co D Probability of Turbulence Presence in a Weather EE log c Hail Size Probability Rain Coming From Unseen Dry Hail Familiar Hailstorm Patterns Overshooting a Storm Short and Long Blind Alley Azimuth Resolution in Weather Modes Weather Display Typical Hook Pattern V Notch Echo Pendant Shape The Classic Pendant Shape Rain Gradients ii Aa Crescent Shape 00 e cece eee eee Line Echo Wave Pattern LEWP Bow Shaped Line of Thunderstorms Ground Mapping Display amp OQ Oi OO Oi Aa A A d o C2 Co Co Co CO1O1O01C01C01C01010101010101601010101 OAN O d00000
23. Video Integrator Processor VIP levels is being promoted A28 1146 111 Federal Aviation Administration FAA Advisory Circulars REV2 A 7 PRIMUS 660 Digital Weather Radar System The National Weather Service NWS radar observer is able to objectively determine storm intensity levels with VIP equipment These radar echo intensity levels are on a scale of one to six If the maximum VIP levels are 1 weak and 2 moderate then light to moderate turbulence is possible with lightning VIP Level 3 is strong and severe turbulence is possible with lightning VIP Level 4 is very strong and severe turbulence is likely with lightning VIP Level 5 is intense with severe turbulence lightning hail likely and organized surface wind gusts VIP Level 6 is extreme with severe turbulence lightning large hail extensive wind gusts and turbulence Thunderstorms build and dissipate rapidly Therefore do not attempt to plan a course between echoes The best use of ground radar information is to isolate general areas and coverage of echoes You must avoid individual storms from in flight observations either by visual sighting or by airborne radar It is better to avoid the whole thunderstorm area than to detour around individual storms unless they are scattered Airborne weather avoidance radar is as its name implies for avoiding severe weather not for penetrating it Whether to fly into an area of radar echoes depends on echo intensity spacing
24. Weather Radar System 2 System Configurations The PRIMUS 660 Digital Weather Radar System can be operated in many configurations to display weather or ground mapping information on a radar indicator electronic flight instrument system EFIS display multifunction display MFD or on a combination of these displays The various system configurations are summarized in the following paragraphs and shown in figure 2 1 NOTE Other configurations are possible but not illustrated The stand alone configuration consists of two units receiver transmitter antenna RTA and a dedicated radar indicator In this configuration the radar indicator contains all the controls to operate the PRIMUS 660 Digital Weather Radar System A single or dual Honeywell EFIS can be added to the stand alone configuration In such a case the electronic horizontal situation indicator EHSI repeats the data displayed on the radar indicator System control remains with the radar indicator The second system configuration uses an RTA and single or dual controllers The single or dual EFIS is the radar display Since there is no radar indicator in this configuration the radar system operating controls are located on the controller With a single controller all cockpit radar displays are identical The dual configuration gives the appearance of having two radar systems on the aircraft In the dual configuration the pilot and copilot each select independent radar
25. by 20 miles 5 54 avoid line echo wave patterns LEWP by 20 miles 5 53 avoid thunderstorm echoes at the south end of a line or at a break in a line by 20 miles 5 52 Low ceiling and visibility A 7 Maximum permissible exposure level MPEL 6 1 Maximum storm tops A 12 Modification of criteria when severe storms and rapid development are evident A 13 N National severe storms laboratory NSSL thunderstorm research A 10 extrapolation to different climbs A 13 desert areas A 13 tropical humid climates A 13 hail in thunderstorms A 12 maximum storm tops A 12 modification of criteria when Severe storms and rapid development are evident A 13 relationship between turbulence and altitude A 10 A28 1146 111 REV2 relationship between turbulence and reflectivity A 10 turbulence above storm tops A 11 turbulence and echo intensity on NWS radar WSR 57 A 11 turbulence below cloud base A 12 turbulence in relation to distance from storm core A 11 turbulence in relation to distance from the storm edge A 11 use of airborne radar A 13 visual appearance of storm and associated turbulence with them A 12 Normal operation 4 1 preliminary control settings 4 1 power up procedure 4 1 radar mode ground mapping 4 5 radar mode weather 4 4 standby 4 4 test mode 4 6 color bands 4 6 dedicated radar indicator 4 6 EFIS MFD ND 4 6 O Offset adjustment 7 5 pitch 7 8 adjustment
26. by contacting Honeywell Inc P O Box 29000 Business and Commuter Aviation Systems Phoenix Arizona 85038 9000 Attention Publication Distribution Dept M S V19A1 Telephone No 602 436 6900 FAX 602 436 1588 E MAIL CAS publications distribution CAS honeywell com Honeywell Product Support A28 1146 111 9 4 REV2 PRIMUS 660 Digital Weather Radar System 10 Abbreviations Abbreviations used in this manual are defined as follows TERMS AC ADC AFC AGC AGL AHRS API AZ BITE BRT ccw CHK CLR CNTL CONFIG CRC cw DAC DSP EEPROM EFIS EGPWS EHSI EL FAA FC FLTPLN FP FPLN FMS FPGA FSBY A28 1146 111 REV2 DEFINITION Advisory Circular Air Data Computer Automatic Flight Control Automatic Gain Control Above Ground Level Attitude Heading Reference System Antenna Position Indicator Azimuth Built in Test Equipment Brightness Counterclockwise Check Clear Control Configuration Cyclic Redundancy Check Clockwise Digital to Analog Converter Display Electrically Erasable Programmable Read Only Memory Electronic Flight Instrument System Enhanced Ground Proximity Warning System Electronic Horizontal Situation Indicator Elevation Federal Aviation Administration Fault Code Flight Plan Flight Management System Field Programmable Gate Array Forced Standby Abbreviations PRIMUS 660 Digital Weather Radar System TERMS ft GMAP GMP GPS
27. cells developing and decaying over a much longer period A single cell can start as a cumulus cloud only 1 mile in diameter rise to 15 000 ft grow within 10 minutes to 5 miles in diameter and tower to an altitude of 60 000 feet or more Therefore weather radar should not be used to take flash pictures of weather but to keep weather under continuous surveillance A28 1146 111 Radar Facts REV2 5 25 PRIMUS 660 Digital Weather Radar System VISIBLE CLOUD MASS RAIN AREA ONLY THIS IS VISIBLE ON RADAR RED ZONE WITHIN RAIN AREA RAINFALL RATE RED LEVEL 40 80 NAUTICAL MILES AD 12057 R3 Radar and Visual Cloud Mass Figure 5 29 As masses of warm moist air are hurled upward to meet the colder air above the moisture condenses and builds into raindrops heavy enough to fall downward through the updraft When this precipitation is heavy enough it can reverse the updraft Between these downdrafts shafts of rain updrafts continue at tremendous velocities It is not surprising therefore that the areas of maximum turbulence are near these interfaces between updraft and downdraft Keep these facts in mind when tempted to crowd a rain shaft or to fly over an innocent looking cumulus cloud Radar Facts A28 1146 111 5 26 REV2 PRIMUS 660 Digital Weather Radar System To find a safe and comfortable route through the precipitation area study the radar image of the squall line while closing in on the thunder
28. display of LSS data is inhibited but the LSS still accumulates data e LX Lightning Sensor System In this position the LSS is fully operational and it displays LSS data on the indicator e CLR TST Clear Test In this position accumulated data is cleared from the memory of the LSS After 3 seconds the test mode is initiated in the LSS SLV SLAVE DUAL INSTALLATIONS ONLY The SLV annunciator is only used in dual controller installations With dual controllers one controller can be slaved to the other by selecting OFF on that controller only with the RADAR mode switch This slaved condition is annunciated with the SLV annunciator The slave mode allows one controller to set the modes of the RTA for both sweep directions In the slave mode all EFIS WX displays are indentical and updated on each sweep With dual controllers both controllers must be off before the radar System turns off A28 1146 111 Operating Controls REV 2 3 13 PRIMUS 660 Digital Weather Radar System 9 RADAR This rotary switch is used to select one of the following functions e OFF This position turns off the radar system e STBY Standby This position places the radar system in standby a ready state with the antenna scan stopped the transmitter inhibited and the display memory erased STBY is displayed on the EFIS MFD e WX Weather This position selects the weather detection mode The system is fully operational and all interna
29. field Refer to Section 4 Normal Operation for a description of the test pattern WARNING IN THE TEST MODE THE TRANSMITTER IS ON AND RADIATING X BAND MICROWAVE ENERGY REFER TO SECTION 6 MAXI MUM PERMISSIBLE EXPOSURE LEVEL MPEL A28 1146 111 Operating Controls REV 2 3 15 PRIMUS 660 Digital Weather Radar System FSBY FORCED STANDBY FSBY is an automatic nonselectable radar mode As an installation option the RTA can be wired to the weight on wheels WOW squat switch When wired the RTA is in the FSBY mode when the aircraft is on the ground In FSBY mode the transmitter and antenna scan are both inhibited the display memory is erased and the FSBY legend is displayed in the mode field When in the FSBY mode pushing the STAB button four times in three seconds restores normal operation NOTE lfaWC 650 Weather Radar Controller is installed FSBY is overridden by simultaneously pushing both range arrow buttons The FSBY mode is a safety feature that inhibits the transmitter on the ground to eliminate the X band microwave radiation hazard Refer to Section 6 Maximum Permissible Exposure Level MPEL WARNING STANDBY OR FORCED STANDBY MODE MUST BE VERIFIED IN GROUND OPERATIONS BY THE OPERATOR TO ENSURE SAFETY FOR GROUND PERSONNEL In installations with two radar controllers it is only necessary to override forced standby from one controller If either controller is returned to standby mode while weight is
30. indicates that the EGPWS has failed e INHIB The INHIB annunciator indicates that the INHIB push button has been pushed and is active When INHIB is annunciated EGPWS is not displayed on the radar indicator and the aural annunciators do not sound NOTE The FAIL and INHIB annunciators are often incorporated into the INHIB push button e TERR Terrain The TERR annunciator indicates that the annunciator lamp power is on It does not indicate the operational status of the system e ON The ON annunciator indicates that the radar indicator is displaying terrain This ON push button lamp is lit if the ON push button has been pushed and is active or if an actual Terrain Alert is indicated by the EGPWS system and the terrain is automatically displayed NOTE The TERR and ON annunciators are often incorporated into the ON push button Some installation may not contain all of these controls and annunciators or they may have different names Most EGPWS installations have additional controls and or annunciators i e TEST Refer to the appropriate AlliedSignal publication for details Enhanced Ground Proximity Warning System EGPWS A28 1146 111 B 2 REV2 PRIMUS 660 Digital Weather Radar System Related EGPWS System Operation Some installations may have a DATA NAV navigation display and or checklist lightning sensor system LSS and or traffic alert and crew alerting system TCAS that already share the radar indic
31. middle heights in storms FL 200 300 turbulence beneath a storm is not to be minimized This is especially true when the relative humidity is low in any air layer between the surface and 15 000 feet Then the lower altitudes may be characterized by strong outflowing winds and severe turbulence where thunderstorms are present Therefore THE SAME TURBULENCE CONSIDERATIONS WHICH APPLY TO FLIGHT AT HIGH ALTITUDES NEAR STORMS APPLY TO LOW LEVELS AS WELL MAXIMUM STORM TOPS Photographic data indicates that the maximum height attained by thunderstorm clouds is approximately 63 000 feet Such very tall storm tops have not been explored by direct means but meteorological judgments indicate the probable existence of large hail and strong vertical drafts to within a few thousand feet of the top of these isolated stratosphere penetrating storms THEREFORE IT APPEARS IMPORTANT TO AVOID SUCH VERY TALL STORMS AT ALL ALTITUDES HAIL IN THUNDERSTORMS The occurrence of HAIL IS MUCH MORE CLEARLY IDENTIFIED WITH THE INTENSITY OF ECHOES THAN IS TURBULENCE AVOIDANCE OF MODERATE AND SEVERE STORMS SHOULD ALWAYS BE ASSOCIATED WITH THE AVOIDANCE OF DAMAGING HAIL VISUAL APPEARANCE OF STORM AND ASSOCIATED TURBULENCE WITH THEM On numerous occasions flight at NSSL have indicated that NO USEFUL CORRELATION EXISTS BETWEEN THE EXTERNAL VISUAL APPEARANCE OF THUNDERSTORMS AND THE TURBULENCE AND HAIL WITHIN THEM Federal Aviation Administration FAA Advisor
32. mode range tilt and gain settings for display on their respective display The dual configuration time shares the RTA On the right to left antenna scan the system switches to the mode range tilt and gain selected by the left controller and updates the left display On the reverse antenna scan the system switches to the mode range tilt and gain setting selected by the right controller and updates the right display Either controller can be slaved to the other controller to show identical images on both sides of the cockpit A28 1146 111 System Configurations REV2 2 1 PRIMUS 660 Digital Weather Radar System NOTES 1 When WAIT SECTOR SCAN or FORCED STANDBY are activated the radar operates as if in single controller configuration This is an exception to the ability of each pilot to independently select modes 2 Inthe dual configuration the pilots can use the slave feature to optimize the update rate of each side s weather radar display to meet the needs of the situation With one controller turned off both cockpit displays are updated on every sweep of the radar but control of the radar is only on one side With each controller operating each side has control but each side is updated with new radar information on every other sweep of the antenna STAND ALONE CONFIGURATION INDICATOR WI 660 SINGLE OR DUAL EF
33. of central United States In this region property lines fences roads houses barns and power lines tend to be laid out in a stringent north south east west orientation As a result radar returns from these cardinal points of the compass tend to be more intense than returns from other directions and the display shows these returns as bright north south east west spokes overlaying the ground map The second phenomenon is associated with radar returns from water surfaces generally called sea clutter as shown in figure 5 3 Calm water reflects very low radar returns since it directs the radar pulses onward instead of backward i e the angle of incidence from mirrored light shone on it at an angle The same is true when viewing choppy water from the upwind side The downwind side of waves however can reflect a strong signal because of the steeper wave slope A relatively bright patch of sea return therefore indicates the direction of surface winds REFLECTION P CALM WATER OR WATER WITH CHOPPY WATER PROVIDES SWELLS DOES NOT PROVIDE GOOD RETURN FROM GOOD RETURN DOWNWIND SIDE OF WAVES WIND DIRECTION AT SURFACE OF WATER AD 12056 R2 Sea Returns Figure 5 3 Radar Facts A28 1146 111 5 4 REV2 PRIMUS 660 Digital Weather Radar System TILT MANAGEMENT The pilot can use tilt management techniques to minimize ground clutter when viewing weather targets Assume the aircraft is flying over relatively smooth terrain
34. on wheels the system returns to the forced standby mode GAIN The GAIN is a single turn rotary control and push pull switch that is used to control the receiver gain When the GAIN switch is pushed the system enters the preset calibrated gain mode Calibrated gain is the normal mode and is used for weather avoidance In calibrated gain the rotary portion of the GAIN control does nothing When the GAIN switch is pulled out the system enters the variable gain mode Variable gain is useful for additional weather analysis and for ground mapping In WX mode variable gain can increase receiver sensitivity over the calibrated level to show weak targets or it can be reduced below the calibrated level to eliminate weak returns WARNING LOW VARIABLE GAIN SETTINGS CAN ELIMINATE HAZARDOUS TARGETS FROM THE DISPLAY Operating Controls A28 1146 111 3 16 REV2 PRIMUS 660 Digital Weather Radar System In GMAP mode variable gain is used to reduce the level of strong returns from ground targets Minimum gain is attained with the control at its full ccw position Gain increases as the control is rotated in a cw direction from full ccw at full cw position the gain is at maximum The VAR legend annunciates variable gain Selecting RCT or TGT forces the system into calibrated gain NOTE Some controllers have a preset position on the rotary knob Rotating the knob to PRESET provides calibrated gain functions Rotating the knob out of the P
35. procedure 7 8 roll 7 5 adjustment procedure 7 5 Operating controls 3 1 weather radar controller operation WC 660 3 10 GAIN 3 16 LSS lightning sensor system optional 3 13 RADAR 3 14 rainfall rate color coding 3 14 RANGE 3 11 Index Index 3 PRIMUS 660 Digital Weather Radar System Index cont weather radar controller operation WC 660 cont RCT rain echo attenuation compensation technique REACT 3 11 SECT scan sector 3 12 SLV slave dual installations only 3 13 STAB stabilization 3 11 target alert characteristics 3 12 TGT target 3 12 TILT 3 13 weather radar indicator operation WI 650 660 3 1 AZ azimuth 3 9 BRT brightness or BRT LSS lightning sensor system 3 9 display area 3 5 function switch 3 5 GAIN 3 8 GMP ground mapping button MAP 3 2 Rainfall rate color coding 3 6 RANGE 3 9 RCT rain echo attenuation compensation technique REACT 3 3 SCT scan sector 3 9 target alert characteristics 3 4 TGT target 3 4 TILT 3 8 WX weather button 3 2 pitch stabilization check 5 22 Pitch offset adjustment 7 8 adjustment procedure 7 8 Pitch stabilization check 7 12 check procedure 7 12 Preliminary control settings 4 1 power up procedure 4 1 radar mode ground mapping 4 5 radar mode weather 4 4 standby 4 4 Procedures in flight roll offset adjustment 7 5 pitch gain adjustment 7 15 pitch offset adjustment 7 8 pitc
36. storm should be considered severe while this erratic motion is in progress Splitting Echoes Sometimes a large 20 mile or larger diameter echo splits into two echoes The southernmost echo often slows turns to the right of its previous motion and becomes severe with large hail and extreme turbulence If a tornado develops it is usually at the right rear portion of the southern echo When the storm weakens it usually resumes its original direction of movement The northern echo moves left of the mean wind increases speed and often produces large hail and extreme turbulence Merging Echoes Merging echoes sometimes become severe but often the circulation of the merging cells interfere with each other preventing intensification The greatest likelihood of aviation hazards is at the right rear section of the echo Severe Weather Avoidance Procedures Table 5 9 cont Radar Facts A28 1146 111 5 46 REV2 PRIMUS 660 Digital Weather Radar System Step Procedure Never continue flight towards or into a radar shadow or the blue REACT field WARNING STORMS SITUATED BEHIND INTERVENING RAINFALL CAN BE MORE SEVERE THAN DEPICTED ON THE DIS PLAY If the radar signal can penetrate a storm the target displayed seems to cast a shadow with no visible returns This indicates that the storm contains a great amount of rain that attenuates the signal and prevents the radar from seeing beyond the cell under observation
37. target at the normal range Radar Facts A28 1146 111 5 28 REV2 PRIMUS 660 Digital Weather Radar System 300 NAUTICAL MILES MAXIMUM CALIBRATE MAXIMUM MAXIMUM D RANGE CALIBRATE CALIBRATE RAINFALL RAINFALL NM 10 IN D RANGE D RANGE DISPLAY RATE RATE AND 12 IN NM 18 IN NM 24 IN LEVEL MM HR IN HR FLAT PLATE FLAT PLATE FLAT PLATE GREATER GREATER GREATER GREATER GREATER ice THAN icu THAN THAN 50 2 YELLOW 0 17 0 5 33 40 1 GREEN 0 04 0 17 23 33 0 LESS THAN LESS THAN LESS THAN BLACK 1 0 04 23 Display Levels Related to dBZ Levels Typical Table 5 6 WARNING THE RADAR IS CALIBRATED FOR CONVECTIVE WEATHER STRATIFORM STORMS AT OR NEAR THE FREEZING LEVEL CAN SHOW HIGH REFLECTIVITY DO NOT PENETRATE SUCH TARGETS A28 1146 111 Radar Facts REV2 5 29 PRIMUS 660 Digital Weather Radar System Rainfall rate in Storm VIP Level mm hr Category dBZ Level Greater than Extreme Greater than 125 57 VIP Levels Related to dBZ Table 5 7 VARIABLE GAIN CONTROL The PRIMUS 660 Digital Weather Radar variable gain control is a single turn rotary control and a push pull switch that is used to control the radar s receiver gain With the switch pushed in the system is in the preset calibrated gain mode In calibrated gain the rotary control does nothing When the GAIN switch is pulled out the system enters the variable gain mode Variable gain is useful for additional weather analysis I
38. that is equivalent to sea level in altitude The pilot must make adjustments for the effects of mountainous terrain The figures below help to visualize the relationship between tilt angle flight altitude and selected range Figures 5 4 and 5 5 show the distance above and below aircraft altitude that is illuminated by the flat plate radiator during level flight with 0 tilt Figures 5 6 and 5 7 show a representative low altitude situation with the antenna adjusted for 2 8 up tilt 80 000 e W 70 000 5 60 000 ZERO TILT 41 800 FT 20 000 FT g 20000 10 500 FT E kamje inn p 72 CENTER OF RADAR BEAM 4 30 000 20 000 FT i 20 000 l lo 41 800 FT 10 000 NUBE 0 FERN A EH 0 25 50 ico RANGE NAUTICAL MILES AD 356930 Radar Beam Illumination High Altitude 12 Inch Radiator Figure 5 4 80 000 70 000 WW 60 000 ZERO TILT de Z 50 000 14 800 FT O 7 ee NK ka Aa CENTER OF RADAR BEAM S 30 000 ipa 29 000 FT 1 HE DES i 0 25 50 100 RANGE NAUTICAL MILES AD 17717 R1 Radar Beam Illumination High Altitude 18 Inch Radiator Figure 5 5 A28 1146 111 Radar Facts REV2 5 5 PRIMUS 660 Digital Weather Radar System 40 000 ANTENNA ADJUSTED m FOR 2 8 UPTILT iJ 30 000 z 14 800 FT par sem s 20 000 _ center di 32 15 000 14 800 FT em 5 000 0 0 10 20 30 40 50 60 70 80 RANGE NAUTICAL MILES AD 17719 Radar Beam Illumination Low Altitude 12 Inch Radiator Fig
39. within 3 seconds A display with text instruction is shown 7 To change the pitch gain value pull out the GAIN knob and rotate it The pitch gain adjustment range is from 90 to 110 From the roll offset entry menu push the STAB STB button 3 more times to bring up the pitch gain entry menu While flying with a steady pitch angle of gt 5 adjust so the contour of the ground returns follow the contour of the range arcs as closely as possible When change is completed push in the GAIN knob The display returns to the previous message 10 Push the STAB button to exit the mode and save the value in nonvolatile memory Pitch Gain Adjustment Procedure Table 7 8 A28 1146 111 In Flight Adjustments REV2 7 15 7 16 blank PRIMUS 660 Digital Weather Radar System 8 In Flight Troubleshooting The PRIMUS 660 Digital Weather Radar System can provide troubleshooting information on one of two formats e Fault codes e Text faults The selection is made at the time of installation This section describes access and use of this information If the fault codes option is selected they are shown in place of the tilt angle The text fault option provides English text as well as fault codes in the radar test pattern areas Critical functions in the receiver transmitter antenna RTA are continuously monitored Each fault condition has a corresponding 2 digit fault code FC Additionally a fault name a pilot message and
40. 10 000 feet AGL Select the 50 mile range and GMAP mode 3 Adjust the tilt control until your radar display shows a solid band of ground returns starting at the 40 mile range arc 4 After several antenna sweeps verify that ground returns follow the range arc closely and are equally displayed on both sides as shown in figure 7 1 If the ground returns are not equally displayed on both sides see examples in figures 7 2 and 7 3 perform the roll offset adjustment shown in table 7 3 Stabilization in Straight and Level Flight Check Procedure Table 7 2 NOTE A condition where the strongest ground targets move from side to side over a period of several minutes can be caused by the gyro erection circuits chasing a slow wingwalk in the flightpath Roll offset adjustment cannot compensate for this condition A28 1146 111 In Flight Adjustments REV2 7 3 PRIMUS 660 Digital Weather Radar System Symmetrical Ground Returns Figure 7 1 AD 17720 R3 AD 17721 R2 Ground Return Indicating Misalignment Right Figure 7 2 In Flight Adjustments A28 1146 111 7 4 REV2 PRIMUS 660 Digital Weather Radar System AD 17722 R2 Ground Return Indicating Misalignment Left Figure 7 3 ROLL OFFSET ADJUSTMENT You can make an in flight adjustment when level flight stabilization errors are detected This procedure is done by either the WC 660 Weather Radar Controller or the WI 650 660 Weather Rada
41. 11 PRIMUS 660 EAMUS GOO WA AA AA e Weather Radar System Procedure From the From the roll offset entry menu push the STAB STB offset entry menu push the STAB STB button twice more to bring up the roll gain entry menu To change the roll gain value pull out the GAIN knob and rotate it The roll gain adjustment range is from 90 to 11095 While flying with a steady roll angle of at least 20 adjust for symmetrical display of ground returns at the 40 NM range arc When change is completed push in the GAIN knob The display returns to the previous message Push the STAB STB button to go to the next menu pitch gain Roll Gain Adjustment Procedure Table 7 6 PITCH STABILIZATION CHECK This in flight adjustment is made in a bank when the ground returns do not remain symmetrical during turns The procedure is listed in table 7 7 e Pome 1 Trim the aircraft for straight and level flight in smooth clear air over level terrain at an altitude of at least 10 000 feet Select the 50 mile range and GMAP mode Place the aircraft between 5 and 10 pitch up If there is little change to the arc of ground returns the pitch stabilization is good 3 Adjust the TILT control until your radar display shows a solid band of ground returns starting at the 40 mile range arc See figure 7 9 Pitch Stabilization Check Procedure Table 7 7 cont In Flight Adjustments A28 1146 111 7 12 REV2 PRIMUS 660 D
42. 13 Familiar Hailstorm Patterns Figure 5 35 Radar Facts A28 1146 111 5 38 REV 2 PRIMUS 660 Digital Weather Radar System The more that is learned about radar the more the pilot is an all important part of the system The proper use of controls is essential to gathering all pertinent weather data The proper interpretation of that data the displayed patterns is equally important to safety and comfort This point is illustrated again in figure 5 36 When flying at higher altitudes a storm detected on the long range setting can disappear from the display as it is approached The pilot should not be fooled into believing the storm has dissipated as the aircraft approaches it The possibility exists that the radiated energy is being directed from the aircraft antenna above the storm as the aircraft gets closer If this is the case the weather shows up again when the antenna is tilted downward as little as 1 Assuming that a storm has dissipated during the approach can be quite dangerous if this is not the case the turbulence above a storm can be as severe as that inside it OVERFLYING A STORM AD 12061 R1 Overshooting a Storm Figure 5 36 A28 1146 111 Radar Facts REV2 5 39 PRIMUS 660 Digital Weather Radar System Another example of the pilot s importance in helping the radar serve its safety comfort purpose is shown in figure 5 37 This is the blind alley or box canyon situation Pilots can find themselves in thi
43. 16 0 Table of Contents 3 17 3 18 0 TC 1 0 TC 2 1 Normal Operation TC 3 1 4 1 0 TC 4 1 4 2 0 TC 5 1 4 3 0 TC 6 1 4 4 0 TC 7 TC 8 1 4 5 0 4 6 0 Introduction 1 1 0 Radar Facts 1 2 0 5 1 0 5 2 0 System Configurations 5 3 0 2 1 0 5 4 0 2 2 0 5 5 0 2 3 0 5 6 0 2 4 0 5 7 0 2 5 2 6 0 5 8 0 5 9 0 Operating Controls 5 10 0 3 1 0 5 11 0 3 2 0 5 12 0 3 3 0 m indicates changed added or deleted pages F indicates right foldout page with a blank back A28 1146 111 REV 3 List of Effective Pages LEP 1 PRIMUS 660 Digital Weather Radar System Subheading and Page Revision Subheading and Page Revision Radar Facts cont List of Effective Pages LEP 2 5 13 5 14 5 15 5 16 5 17 5 18 5 19 5 20 5 21 5 22 5 23 5 24 5 25 5 26 5 27 5 28 5 29 5 30 5 31 5 32 5 33 5 34 5 35 5 36 5 37 5 38 5 39 5 40 5 41 5 42 5 43 5 44 5 45 5 46 5 47 5 48 5 49 5 50 5 51 5 52 5 53 5 54 5 55 5 56 5 57 5 58 cO OO ococcococococococococoocoococococococcococococoocococoococoocococococococococococosocosoco Maximum Permissible Exposure Level MPEL 6 1 6 2 In Flight Adjustments 7 1 7 2 7 3 7 4 7 5 7 6 7 7 7 8 7 9 7 10 7 11 7 12 7 13 7 14 7 15 7 16 In Flight Troubelshooting 8 1 8 2 8 3 8 4 8 5 8 6 8 7 8 8 3 oooooocooooqoo0o III Oooococococoo Honeywell Product Support 9 1 9 2 9 3 9 4 Abbreviations 10 1 10 2 10 3 10 4 Appendix A A 1 A
44. 2 A 3 A 4 A 5 ch uns ums ume oOoooooco A28 1146 111 REV 3 PRIMUS 660 Digital Weather Radar System Subheading and Page Revision Subheading and Page Revision Appendix A cont A 6 A 7 A 8 A 9 A 10 A 11 A 12 A 13 A 14 III SIA AI NS Appendix B B 1 B 2 B 3 B 4 B 5 B 6 aA 32 oa lll Index Index 1 Index 2 Index 3 Index 4 Index 5 Index 6 Index 7 Index 8 a oe ce ce Cae a ae A28 1146 111 List of Effective Pages REV3 LEP 3 LEP 4 blank PRIMUS 660 Digital Weather Radar System Table of Contents Section 1 2 A28 1146 111 REV2 INTRODUCTION SYSTEM CONFIGURATIONS OPERATING CONTROLS WI 650 660 Weather Radar Indicator Operation WC 660 Weather Radar Controller Operation NORMAL OPERATION Preliminary Control Settings Slandby 222 deca eden cies ERE T rra Radar Mode Weather Radar Mode Ground Mapping Test Mode redima tasdain ca eb one RADAR FACTS kani eras Radar Operation 00 cee eee eee ee Tilt Management 0 0 eee eee eee StabilizatiOn eo soe ewe eR RE RTT ER Dynamic Error iios e RR RE RE RES Accelerative Error Antenna Mounting Error Wallowing Wing Walk and Yaw Error Roll Gain Error
45. 20 68B August 8 1980 Subject Recommended Radiation Safety Precautions for Ground Operation of Airborne Weather Radar The radius R to the maximum permissible exposure level boundary is calculated for the radar system on the basis of radiator diameter rated peak power output and duty cycle The greater of the distances calculated for either the far field or near field is based on the recommendations outlined in AC No 20 68B The advisory circular is reproduced without Appendix 1 in Appendix A of this manual The IEEE Standard for Safety Level with Respect to Human Exposure to Radio Frequency Electronic Fields SkHz to 300 GHz IEEE C95 1 1991 recommends an exposure level of no more than 6 mW cm Honeywell recommends that operators follow the 6 mW cm standard Figure 6 1 shows MPEL for both exposure levels RADIUS AIRCRAFT R NOSE AND RADOME DIAMETER 10 mW CM 5 mW CM OF FLAT RADIUS R RADIUS R PLATE OF MPEL OF MPEL RADIATOR BOUNDARY BOUNDARY AIRCRAFT LUBBER LINE 12 IN 6 FT 9 FT 30 5 CM 183 CM 275 CM 18 IN 8 FT 12 FT 45 7 CM 244 CM 366 CM e o Ez e MPEL BOUNDARY MPEL Boundary Figure 6 1 A28 1146 111 Maximum Permissible Exposure Level MPEL REV 3 6 1 6 2 blank PRIMUS 660 Digital Weather Radar System 7 In Flight Adjustments PITCH AND ROLL TRIM ADJUSTMENTS The PRIMUS 660 is delivered from the Honeywell factory or repair facility adjusted for correct pitch and roll stabilizati
46. AIN switch to enter the system into the variable gain mode with VAR variance displayed in the color bar Variable gain is useful for additional weather analysis and for ground mapping In WX mode variable gain can increase receiver sensitivity over the calibrated level to show very weak targets or it can be reduced below the calibrated level to eliminate weak returns WARNING HAZARDOUS TARGETS CAN BE ELIMINATED FROM THE DIS PLAY WITH LOW SETTINGS OF VARIABLE GAIN In the GMAP mode variable gain is used to reduce the level of the typically very strong returns from ground targets to allow details to be Seen Minimum gain is with the control at its full counterclockwise ccw position Gain increases as the control is rotated cw from full ccw At full clockwise cw position the gain is at maximum In variable gain the color bar legend contains the variable gain VAR annunciation Selecting RCT or TGT forces the system into calibrated gain TILT The TILT knob is a rotary control that is used to select the tilt angle of the antenna beam with relation to the horizon CW rotation tilts beam upward to 15 ccw rotation tilts beam downward to 15 WARNING TO AVOID FLYING UNDER OR OVER STORMS FREQUENTLY AD JUST THE TILT TO SCAN BOTH ABOVE AND BELOW YOUR FLIGHT LEVEL Stabilization is normally ON It can be turned OFF by pulling out the TILT knob The knob is also used to operate the hidden modes Refer to Section 8 In Fl
47. Facts REV2 5 51 PRIMUS 660 Digital Weather Radar System AD 22161 R1 Crescent Shape Figure 5 44 Line Configurations AVOID THUNDERSTORM ECHOES AT THE SOUTH END OF A LINE OR AT A BREAK IN A LINE BY 20 MILES The echo at the south end of a line of echoes is often severe and so too is the storm on the north side of a break in line Breaks frequently fill in and are particularly hazardous for this reason Breaks should be avoided unless they are 40 miles wide This is usually enough room to avoid thunderstorm hazards The above two locations favor severe thunderstorm formation since these storms have less competition for low level moisture than others nearby Radar Facts A28 1146 111 5 52 REV2 PRIMUS 660 Digital Weather Radar System AVOID LINE ECHO WAVE PATTERNS LEWP BY 20 MILES One portion of a line can accelerate and cause the line to assume a wave like configuration Figure 5 45 is an example of an LEWP The most severe weather is likely at S LEWPs form solid or nearly solid lines that are dangerous to aircraft operations and disruptive to normal air traffic flow 100 MILES AD 15562 R1 Line Echo Wave Pattern LEWP Figure 5 45 The S indicates the location of the greatest hazards to aviation The next greatest probability is anywhere along the advancing usually east or southeast edge of the line A28 1146 111 Radar Facts REV2 5 53 PRIMUS 660 Digital Weather Radar System AVOID BOW SHAPED LINE
48. INITY OF THUNDERSTORMS e Tropical Humid Climates When the atmosphere is moist and only slightly unstable though a great depth strong radar echoes may be received from towering clouds which do not contain vertical velocities as strong as those from storms over the U S plains Then it is a matter of the pilot being informed with respect to the general atmospheric conditions accompanying storms for it is well known that PRACTICALLY ALL GEOGRAPHIC AREAS HAVING THUNDERSTORMS ARE OCCASIONALLY VISITED BY SEVERE ONES USE OF AIRBORNE RADAR Airborne radar is a valuable tool HOWEVER ITS USE IS PRINCIPALLY AS AN INDICATOR OF STORM LOCATIONS FOR AVOIDANCE PURPOSES WHILE ENROUTE A28 1146 111 Federal Aviation Administration FAA Advisory Circulars REV2 A 13 A 14 blank PRIMUS 660 Digital Weather Radar System Appendix B Enhanced Ground Proximity Warning System EGPWS The AlliedSignal Mark VII EGPWS combines information from aircraft navigation equipment i e flight management system FMS inertial reference system IRS global positioning system GPS radio altimeter with a stored terrain data base that alerts the pilot to potentially dangerous ground proximity In addition to the verbal alert the EGPWS can display the terrain data on the weather radar indicator Depending on the installation the pilot pushes a button to display the terrain or the terrain data is automatically displayed when a Terrain Alert occurs
49. IS OPTION EFIS OR EFIS MFD CONFIGURATION CONTROLLER WC 660 Ice Ce Je Gain RADAR SLV Tur Ce JI gt Jf za E JI Ju OPTIONAL SINGLE OR DUAL 2ND CONTROLLER EFIS AND MFD ADSIT PRIMUS 660 Configurations Figure 2 1 System Configurations A28 1146 111 2 2 REV2 PRIMUS 660 Digital Weather Radar System The third system configuration is similar to the second except that a Honeywell multifunction display MFD system is added As before single or dual controllers can be used When a single controller is used all displays show the same radar data Dual controllers are used to operate in the dual mode The MFD can be slaved to either controller to duplicate the data displayed on the selected side Table 2 1 is a truth table for dual control modes Left Right Controller Controller Mode Mode OFF Standby SLV Standby Standby Standby Standby Standby SLV Standby M BEL o or o Standby S oid ON 2 EN ON 2 Standby 2 Standby Standby Standby Standby Standby Dual Control Mode Truth Table Table 2 1 2 SLV means that displayed data is controlled by opposite side controller That is the one controller that is operating is controlling both sweeps of the antenna on side control for the antenna sweep direction associated with that control 2 implies two controllers are ON upward tilt Video data is suppressed The transmitter is inhi
50. N B 2 TERR B 2 displays B 4 obstacle display color definitions B 4 EGPWS test B 6 push buttons controls B 2 INHIB button B 2 ON terrain button B 2 System operation B 1 controls B 1 EGPWS operation B 3 related EGPWS system operation B 3 Equipment list 2 4 cockpit mounted options 2 4 remote mounted 2 4 Errors 5 15 accelerative 5 15 antenna mounting error 5 16 level flight stabilization check 5 17 dynamic 5 15 pitch gain 5 22 pitch stabilization check 5 22 roll gain 5 19 roll stabilization while turning check 5 19 stabilization in turns check procedure 5 19 wallowing wing walk and yaw 5 19 Exchange and rental service 9 1 Extrapolation to different climbs A 13 desert areas A 13 tropical humid climates A 13 Index Index 1 PRIMUS 660 Digital Weather Radar System Index cont F Fault code and text fault relationships 8 5 pilot messages 8 8 Federal Aviation Administration FAA Advisory Circulars recommended radiation safety precautions for ground operation of airborne weather radar A 1 background A 1 cancellation A 1 precautions A 2 purpose A 1 related reading material A 1 Thunderstorms A 3 cancellation A 3 general A 3 hazards A 4 national severe storms laboratory NSSL thunderstorm research A 10 purpose A 3 related reading material A 3 G Gain adjustment 7 11 pitch 7 15 adjustment procedure 7 15 roll 7 11 adjustment pro
51. N AIRCRAFT MODERATE SEVERE Turbulence that momentarily causes slight erratic changes in altitude and or attitude pitch roll yaw Turbulence that is similar to light turbulence but of greater intensity Changes in altitude and or attitude occur but the aircraft remains in positive control at all times It usually causes variations in indicated airspeed Turbulence that causes large abrupt changes in altitude and or attitude It usually causes large variations in indicated airspeed Aircraft can be Occupants can feel a slight strain against seat belts or shoulder straps Unsecured objects can be displaced slightly Occupants feel definite strains against seat belts or shoulder straps Unsecured objects are dislodged Occupants are forced violently against seat belts or shoulder straps Unsecured objects are tossed about momentarily out of control Turbulence Levels From Airman s Information Manual Table 5 8 Hail Size Probability Whenever the radar shows a red or magenta target the entire storm cell should be considered extremely hazardous and must not be penetrated Further support for this statement comes from the hail probability graph shown in figure 5 33 The probability of destructive hail starts at a rainfall rate just above the red level three threshold Like precipitation the red and magenta returns should be considered as a mask over more severe hail probabilities By now it shou
52. OF ECHOES BY 20 MILES Sometimes a fast moving broken to solid thunderstorm line becomes bow shaped as shown in figure 5 46 Severe weather is most likely along the bulge and at the north end but severe weather can occur at any point along the line Bow shaped lines are particularly disruptive to aircraft operations because they are broken to solid and can accelerate to speeds in excess of 70 knots within an hour AD 15563 R1 Bow Shaped Line of Thunderstorms Figure 5 46 Radar Facts A28 1146 111 5 54 REV2 PRIMUS 660 Digital Weather Radar System Additional Hazards TURBULENCE VERSUS DISTANCE FROM STORM CORE The stronger the return the further the turbulence is encountered from the storm core at any altitude Severe turbulence is often found in the tenuous anvil cloud 15 to 20 miles downwind from a severe storm core Moreover the storm cloud is only the visible portion of a turbulent system whose up and down drafts often extend outside of the storm proper TURBULENCE VERSUS DISTANCE FROM STORM EDGE Severe clear air turbulence can occur near a storm most often on the downwind side Tornadoes are located in a variety of positions with respect to associated echoes but many of the most intense and enduring occur on the up relative wind side The air rising in a tornado can contribute to a downwind area of strong echoes while the tornado itself can or can not return an echo Echo hooks and appendages though useful inde
53. ORTH AMERICA cont Miami Support Center Honeywell Inc Commercial Aviation Systems 7620 N W 25th Street Bldg C Unit 6 MIAMI FL 33122 TEL 305 436 8722 FAX 305 436 8532 CUSTOMER SUPPORT CENTERS REST OF THE WORLD United Kingdom Support Center France Support Center Honeywell Avionics Systems Ltd Honeywell Aerospace Edison Road Ringway North 1 Rue Marcel Doret B P 14 BASINGSTOKE HANTS 31701 BLAGNAC CEDEX RG21 6QD FRANCE Toulouse ENGLAND TEL 33 5 6212 1500 TEL 44 1256 72 2200 FAX 33 5 6130 0258 FAX 44 1256 72 2201 AOG 33 5 6171 9662 AOG 44 1256 72 2200 TLX 521635F TLX 51 858067 Singapore Support Center Australia Support Center Honeywell Aerospace Pte Ltd Honeywell Ltd 2 Loyang Crescent Trade Park Drive SINGAPORE 1750 TULLAMARINE 3043 VICTORIA TEL 65 542 1313 AUSTRALIA Melbourne FAX 65 542 1212 TEL 61 3 9330 1411 AOG 65 542 1313 FAX 61 3 9330 3042 TLX RS 56969 HWLSSC AOG 61 3 9330 1411 TLX 37586 HWLTUL Germany Support Center AOA Apparatebau Gauting GimbH Ammerseestrasse 45 49 D82131 Gauting GERMANY TEL 49 89 89317 0 FAX 49 89 8931 7 183 After Hours AOG Service 0172 8207300 in Germany 49 172 8207300 outside Germany TLX 0521702 A28 1146 111 Honeywell Product Support REV2 9 3 PRIMUS 660 Digital Weather Radar System PUBLICATION ORDERING INFORMATION Additional copies of this manual can be obtained
54. ORY CIRCULARS TO PREVENT POSSIBLE HUMAN BODY DAMAGE FSBY FORCED STANDBY FSBY is an automatic nonselectable radar mode As an installation option the indicator can be wired to the weight on wheels WOW squat switch When wired the RTA is in the FSBY mode when the aircraft is on the ground In FSBY mode the transmitter and antenna scan are both inhibited and the forced standby legend is displayed in the mode field The FSBY mode is a safety feature that inhibits the transmitter on the ground to eliminate the X band microwave radiation hazard Refer to Section 6 Maximum Permissible Exposure Level MPEL When in FSBY mode you can restore normal operation by pulling the tilt control out pushing it in pulling it out and pushing it in within three seconds WARNING STANDBY OR FORCED STANDBY MODE MUST BE VERIFIED FOR GROUND OPERATION BY THE OPERATOR TO ENSURE SAFETY FOR GROUND PERSONNEL A28 1146 111 Operating Controls REV 2 3 7 PRIMUS 660 Digital Weather Radar System GAIN The GAIN knob is a single turn rotary control and push pull switch that is used to control the receiver gain Push in on the GAIN switch to enter the system into the preset calibrated gain mode Calibrated gain is the normal mode and is used for weather avoidance In calibrated gain the rotary portion of the GAIN control does nothing In calibrated gain the color bar legend is labeled 1 2 3 4 in WX mode or 1 2 3 in GMAP mode Pull out on the G
55. RESET position allows variable gain operation A28 1146 111 Operating Controls REV2 3 17 3 18 blank PRIMUS 660 Digital Weather Radar System 4 Normal Operation PRELIMINARY CONTROL SETTINGS Table 4 1 gives the power up procedure for the PRIMUS 660 Digital Weather Radar System Step Procedure Verify that the system controls are in the positions described below before powering up the radar system Mode control Off GAIN control Preset Position TILT control 15 Take the following precautions if the radar system is operated in any mode other than standby or forced standby while the aircraft is on the ground e Direct nose of aircraft so that antenna scan sector is free of large metallic objects such as hangars or other aircraft for a minimum distance of 100 feet 30 meters and tilt the antenna fully upwards Do not operate the radar system during aircraft refueling or during refueling operations within 100 feet 30 meters Do not operate the radar if personnel are standing too close to the 120 forward sector of aircraft Refer to Section 6 Maximum Permissible Exposure Level in this manual Operating personnel should be familiar with FAA AC 20 68B which is reproduced in Appendix A of this manual If the system is being used with an EFIS display power up by selecting the weather display on the EHSI Apply power to the radar system using either the indicator or controller power controls Selec
56. REV2 B PRIMUS 660 Digital Weather Radar System EGPWS Display The EGPWS displays is shown as variable dot patterns in green yellow or red The density and color is a function of how close the terrain is relative to the aircraft altitude above ground level AGL refer to table B 1 Terrain obstacle alerts are shown by painting the threatening terrain as solid or red Terrain that is more than 2000 feet below the aircraft is not displayed Areas where terrain data is not available are shown in magenta Elevation of Terrain in Feet AGL Color 2000 or more above the aircraft High density red 1000 2000 above the aircraft High density yellow dot pattern 0 1000 above the aircraft Medium Density yellow Dot Pattern 0 1000 below the aircraft Medium density green dot pattern 1000 2000 below the aircraft Low density green dot pattern 2000 or more below the aircraft black 0 NOTE Caution terrain 60 second warning is displayed as solid yellow Warning obstacle 30 second warning is displayed as solid red EGPWS Obstacle Display Color Definitions Table B 1 Enhanced Ground Proximity Warning System EGPWS A28 1146 111 REV2 PRIMUS 660 Digital Weather Radar System Figure B 1 shows the EGPWS over KPHX airport at 2000 feet mean sea level heading north The terrain shows the mountains to the north of Phoenix AD 62964 EHSI Display Over KPHX Airport With the EGPWS Display Figure B 1 A28 1146
57. T EVENT MARKER At any time a full set of BITE parameters can be recorded by going in and out of variable gain four times pull GAIN knob for VAR push for preset pull for VAR and push for preset within three seconds There is no annunciation on the display after this operation This feature can be useful if the radar appears to be malfunctioning and a fail annunciation is not shown on the display If the pilot event marker is used it is best to record several sets of data during the period of misoperation Refer to the PRIMUS 660 System Description and Installation Manual for information on constructing an interconnect cable for accessing this information In Flight Troubleshooting A28 1146 111 8 4 REV 2 PRIMUS 660 Digital Weather Radar System FAULT CODE AND TEXT FAULT RELATIONSHIPS Table 8 2 lists the relationship between e Fault codes FC e Pilot Maintenance MAINT Messages e Fault Name type description cross reference XREF PILOT LINE FAULT DESCRIPTION FAULT NAME MSG MAINT FAULT TYPE FLASH CRC RADAR PULL POWER ON FAIL RTA 4046 2V 2V ADC Reference Reference continuous 4903 IOP e RADAR PULL FAIL RTA 4908 INT ARINC 429 POWER ON Loopback 4910 E ARINC Interru E mem ADAR PULL 4913 ARINC 429 INT i L RTA Coupling POWER ON 4806 EEPROM Timer CRC FLASH CRC ri POWER ON ADAI U RT LL 4811 EEPROM POC FAIL A POWER ON 4842 STAB Trim CRC EEPROM REDO STAB TBI POWER 4912 Calibration CRC EJ ES
58. TC characteristics are altered to better equalize ground target reflections versus range As a result the preset gain position is generally used to display the desired map The pilot can manually decrease the gain to eliminate unwanted clutter Radar Facts A28 1146 111 5 56 REV2 PRIMUS 660 Digital Weather Radar System LINE OF SIGHT NM 40 000 sm 3 oe aa 2 000 Ls p m 5 TILT Setting for Maximal Ground Target Display 12 Inch Radiator Table 5 10 TILT LIMITED REGION AD 35710 NOTE The line of sight distance is nominal Atmospheric conditions and terrains offset this value A28 1146 111 Radar Facts REV2 5 57 PRIMUS 660 Digital Weather Radar System LINE OF 5 10 25 50 100 200 SIGHT 3 TILT LIMITED REGION IGHT LIMITED REGION INE OF AD 12041 TILT Setting for Maximal Ground Target Display 18 inch Radiator Table 5 11 NOTE The line of sight distance is nominal Atmospheric conditions and terrains offset this value Radar Facts A28 1146 111 5 58 REV2 PRIMUS 660 Digital Weather Radar System 6 Maximum Permissible Exposure Level MPEL Heating and radiation effects of weather radar can be hazardous to life Personnel should remain at a distance greater than R from the radiating antenna in order to be outside of the envelope in which radiation exposure levels equal or exceed 10 mW cm the limit recommended in FAA Advisory Circular AC No
59. Table PRIMUS 660 Weather Radar Equipment List Target Alert Characteristics Rainfall Rate Color Coding WC 660 Controller Target Alert Characteristics Rainfall Rate Color Coding PRIMUS 660 Power Up Procedure Approximate Tilt Setting for Minimal Ground Target Display 12 Inch Radiator Approximate Tilt Setting for Minimal Ground Target Display 18 Inch Radiator Stabilization in Straight and Level Flight Check PIA EPOD Stabilization in Turns Check Procedure Pitch Stabilization In Flight Check Procedure Display Levels Related to dBZ Levels Typical VIP Levels Related to dBZ Turbulence Levels From Airman s Information Manual xen ihr rtREULEERUE ena UR Severe Weather Avoidance Procedures TILT Setting for Maximal Ground Target Display 12 Inch Radiator TILT Setting for Maximal Ground Target Display 18 Inch Radiator Pitch and Roll Trim Adjustments Criteria Stabilization in Straight and Level Flight Check Procedure 22 cues sc nnde exe Beene dee In Flight Roll Offset Adjustment Procedure 5 8 5 9 5 17 5 19 5 22 5 29 5 30 5 36 5 43 5 57 5 58 7 1 7 3 7 5 A28 1146 111 REV2 PRIMUS 660 Digital Weather Radar System Table of Contents cont Li
60. The REACT blue field shows areas where attenuation could be hiding severe weather Both the shadow and the blue field are to be avoided by 20 miles Keep the REACT blue field turned on The blue field forms fingers that point toward the stronger cells Severe Weather Avoidance Procedures Table 5 9 Configurations of Individual Echoes Northern Hemisphere Sometimes a large echo develops configurations that are associated with particularly severe aviation hazards Several of these are discussed below AVOID HOOK ECHOES BY 20 MILES The hook is probably the best known echo associated with severe weather It is an appendage of a thunderstorm echo and usually only appears on weather radars Figure 5 40 shows a hook echo A28 1146 111 Radar Facts REV2 5 47 PRIMUS 660 Digital Weather Radar System AD 15560 R1 9 Typical Hook Pattern Figure 5 40 The hooks are located at the right rear side of the thunderstorm echo s direction of movement usually the southwest quadrant The hook is not the tornado echo A small scale low pressure area is centered at the right rear side of the thunderstorm echo near its edge The low usually ranges from about 3 to 10 miles in diameter Precipitation is drawn around the low s cyclonic circulation to form the characteristic hook shape Tornadoes form within the low near hook According to statistics from the NSSL almost 60 percent of all observed hook echoes have tornadoes associated with
61. The advisory circular is reproduced in Appendix A of this manual To help the pilot categorize storms as described in the advisory circular referenced above the radar receiver gain is calibrated in the WX mode with the GAIN control in the preset position The radar is not calibrated when variable gain is being used but calibration is restored if RCT or target alert TGT is selected To aid in target interpretation targets are displayed in various colors Each color represents a specific target intensity The intensity levels chosen are related to the National Weather Service NWS video integrated processor VIP levels In the WX mode the system displays five levels as black green yellow red and magenta in increasing order of intensity If RCT is selected the radar receiver adjusts the calibration automatically to compensate for attenuation losses as the radar pulse passes through weather targets on its way to illuminate other targets There is a maximum extent to which calibration can be adjusted When this maximum value is reached REACT compensation ceases At this point a cyan field is added to the display to indicate that no further compensation is possible Normal Operation A28 1146 111 4 4 REV2 PRIMUS 660 Digital Weather Radar System In the absence of intervening targets the range at which the cyan field starts is approximately 290 NM with a 12 inch antenna For the 18 inch antenna the cyan field starts beyon
62. Thunderstorms Figure 5 10 The aircraft in figure 5 10 has a clear radar indication of the thunderstorm probably with a shadow in the ground returns behind it e lf the tilt angle shown in figure 5 11 is not altered the thunderstorm appears to weaken as the aircraft approaches it tu FREEZING LEVEL AD 35697 Unaltered Tilt Figure 5 11 A28 1146 111 Radar Facts REV2 5 11 PRIMUS 660 Digital Weather Radar System e Proper tilt management demands that tilt be changed continually when approaching hazardous weather so that ground targets are not painted by the radar beam as shown in figure 5 12 T FREEZING LEVEL AD 35698 Proper Tilt Technique Figure 5 12 e After heading changes in a foul weather situation the pilot should adjust the tilt to see what was brought into the aircraft s flightpath by the heading changes as shown in figure 5 13 DISPLAY BEFORE TURN DISPLAY AFTER TURN THUNDERSTORM WAS OUT OF DISPLAY BEFORE TURN AND IS NOW UNDER BEAM AD 30429 Tilt Management With Heading Changes Figure 5 13 Radar Facts A28 1146 111 5 12 REV2 PRIMUS 660 Digital Weather Radar System e Under the right conditions a dangerous thunder bumper can develop in 10 minutes and can in fact spawn and mature under the radar beam as the aircraft approaches it as shown in figure 5 14 If flying at 400 kt groundspeed GSPD a fast developing thunderstorm that spawns 67 NM in front of the a
63. When RCT is selected the RCT legend is displayed on the EFIS MFD NOTES 1 REACT S three functions attenuation compensation cyan field and forcing targets to magenta are switched on and off with the RCT switch 2 Refer to Section 5 Radar Facts for a description of REACT 3 STAB STABILIZATION The STAB button turns the pitch and roll stability ON and OFF It is also used with the hidden modes NOTE Some controllers annunciate OFF when stabilization is OFF A28 1146 111 Operating Controls REV2 3 11 PRIMUS 660 Digital Weather Radar System 4 TGT TARGET The TGT switch is an alternate action button that enables and disables the radar target alert feature Target alert is selectable in all but the 300 mile range When selected target alert monitors beyond the selected range and 7 5 on each side of the aircraft heading If a return with certain characteristics is detected in the monitored area the target alert changes from the green armed condition to the yellow TGT warning condition This annunciation advises the pilot that a potentially hazardous target lies directly in front and outside of the selected range When this warning is received the pilot should select longer ranges to view the questionable target Note that target alert is inactive within the selected range Selecting target alert forces the system to preset gain Target alert can only be selected in the WX and FP modes In order to activate t
64. a line of echoes or a cluster of echoes moving 40 knots or more often contain severe weather Although nearby slower moving echoes can contain more intense aviation hazards all rapidly moving echoes warrant close observation Fast moving broken to solid line echoes are particularly disruptive to aircraft operations Avoid the entire cell if any portion of the cell is red or magenta by 20 NM The stronger the radar return the greater the frequency and severity of turbulence and hail Avoid all rapidly growing storms by 20 miles When severe storms and rapid development are evident the intensity of the radar return can increase by a huge factor in a matter of minutes Moreover the summit of the storm cells can grow at 7000 ft min The pilot cannot expect a flightpath through such a field of strong storms separated by 20 to 30 NM to be free of severe turbulence Avoid all storms showing erratic motion by 20 miles Thunderstorms tend to move with the average wind that exists between the base and top of the cloud Any motion differing from this is considered erratic and can indicate the storm is severe There are several causes of erratic motion They can act individually or in concert Three of the most important causes of erratic motion are 1 Moisture Source Thunderstorms tend to grow toward a layer of very moist air usually south or southeast in the U S in the lowest 1500 to 5000 ft above the earth s surface Moist air g
65. arget alert the target must have the depth and range characteristics described in table 3 3 Selected Range Minimum Target Target Range NM Depth NM NM 5 5 5 55 10 10 60 25 25 75 50 50 100 100 100 150 200 200 250 300 N A FP Flight Plan 5 55 WC 660 Controller Target Alert Characteristics Table 3 3 NOTE When on the ground in FSBY mode pushing STAB four times in three seconds overrides forced standby s SECT SCAN SECTOR The SECT switch is an alternate action button that is used to select either the normal 12 looks minute 120 scan or the faster update 24 looks minute 60 sector scan Operating Controls A28 1146 111 3 12 REV2 PRIMUS 660 Digital Weather Radar System 6 TILT The TILT knob is a rotary control that is used to select the tilt angle of antenna beam with relation to the horizon CW rotation tilts beam upward 0 to 15 ccw rotation tilts beam downward 0 to 15 The range between 5 and 5 is expanded for ease of setting A digital readout of the antenna tilt angle is displayed on the EFIS WARNING TO AVOID FLYING UNDER OR OVER STORMS FREQUENTLY ADJUST THE TILT TO SCAN BOTH ABOVE AND BELOW YOUR FLIGHT LEVEL 7 LSS LIGHTNING SENSOR SYSTEM OPTIONAL The LSS switch is an optional four position rotary switch that selects the LSS operating modes described below e OFF In this position all power is removed from the LSS e SBY Standby ln this position the
66. argets can no longer be calibrated The point where red level weather target calibration is no longer possible is highlighted by changing the background field from black to cyan Any area of cyan background is an area where attenuation has caused the receiver gain to reach its maximum value so further calibration of returns is not possible Extreme caution is recommended in any attempt to analyze weather in these cyan areas The radar cannot display an accurate picture of what is in these cyan areas Cyan areas should be avoided NOTE f the radar is operated such that ground targets are affecting REACT they could cause REACT to give invalid indications Any target detected inside a cyan area is automatically forced to a magenta color indicating maximum severity Figure 5 31 shows the same storm with REACT OFF and with REACT ON Radar Facts A28 1146 111 5 32 REV2 PRIMUS 660 Digital Weather Radar System BY gl og mune GAN 3 MNS NAN MAX AD 54262 Without REACT REACT ON and OFF Indications Figure 5 31 A28 1146 111 Radar Facts REV2 5 33 PRIMUS 660 Digital Weather Radar System Shadowing An operating technique similar to the REACT blue field is shadowing To use the shadowing technique tilt the antenna down until ground is being painted just in front of the storm cell s An area of no ground returns behind the storm cell has the appearance of a shadow behind the cell This shadow area indicates tha
67. at enables and disables REACT The REACT circuitry compensates for attenuation of the radar signal as it passes through rainfall The cyan field indicates areas where further compensation is not possible Any target detected within the cyan field cannot be calibrated and should be considered dangerous All targets in the cyan field are displayed as fourth level precipitation magenta REACT is available in the WX mode only and selecting REACT forces the system to preset gain When engaged the white RCT legend is displayed in the REACT field NOTES 1 REACT S three main functions attenuation compensation cyan field and forcing targets to magenta are switched on and off with the RCT switch 2 Refer to Section 5 Radar Facts for a description of REACT A28 1146 111 Operating Controls REV 2 3 3 PRIMUS 660 Digital Weather Radar System 4 TGT TARGET The TGT button is an alternate action switch that enables and disables the radar target alert feature Target alert is selectable in all but the 300 mile range When selected target alert monitors beyond the selected range and 7 5 on each side of the aircraft heading If a return with target alert characteristics is detected in the monitored area the target alert legend changes from the green T armed condition to the yellow TGT warning condition See the target alert characteristics in table 3 1 for a target description These annunciations advise the pilot of poten
68. ates how many power on counts back into the history the fault occurred After the last fault an END OF LIST message is displayed To recycle through the list again exit and re enter the TEST mode Table 8 1 describes the six fault data fields that are displayed in figure 8 1 reu meme s sepe NOTES 1 If airborne only fault fields 1 2 and 3 are displayed 2 Airborne only the current faults are displayed 3 Strap codes indicate the configuration that was done at the time of installation Refer to the System Description and Installation manual for further explanation Fault Data Fields Table 8 1 In Flight Troubleshooting A28 1146 111 8 2 REV2 PRIMUS 660 Digital Weather Radar System FAULT DISPLAY PILOT icis S MESSAGE MESSAGE DIVIDER FIELD S FAULT CODE LINE POWER ON 80 MAINTENANCE COUNT MESSAGE TRANSMIT FAULT ON OFF 6 NAME TEST 0 X STRAP 1 2 3 4 CODE WEATHER INDICATOR AD 46709 Fault Annunciation on Weather Indicator With TEXT FAULT Fields Figure 8 1 Figure 8 2 shows the fault codes displayed on EFIS with text faults disabled Honeywell AD 35708 R1 Fault Code on EFIS Weather Display With TEXT FAULTS Disabled Figure 8 2 A28 1146 111 In Flight Troubleshooting REV2 8 3 PRIMUS 660 Digital Weather Radar System sey ON rp or Aer tunm 9 AD 51783 Radar Indication With Text Fault Enabled On Ground Figure 8 3 PILO
69. ather Radar Controller 2 Controllers are available with and without the LSS function 3 When single or dual radar controllers are used the radar data is displayed on the EFIS and or an MFD or navigation display ND Operating Controls A28 1146 111 3 10 REV2 PRIMUS 660 Digital Weather Radar System RANGE The RANGE switches are two momentary contact buttons that are used to select the operating range of the radar and LSS if installed The system permits selection of ranges in WX mode from 5 to 300 NM full scale In the flight plan FPLN mode additional ranges of 500 and 1000 miles are permitted The up arrow selects increasing ranges while the down arrow selects decreasing ranges One half the selected range is annunciated at the one half scale range mark on the EHSI NOTE Some integrated avionics systems incorporate radar range with the map display range control on a MFD ND display RCT RAIN ECHO ATTENUATION COMPENSATION TECHNIQUE REACT This switch position turns on RCT The REACT circuitry compensates for attenuation of the radar signal as it passes through rainfall The cyan field indicates areas where further compensation is not possible Any target detected within the cyan field cannot be calibrated and should be considered dangerous All targets in the cyan field are displayed as fourth level precipitation magenta RCT is a submode of the WX mode and selecting RCT forces the system to preset gain
70. ator s display by way of the Universal Digital Interface UDI connector These systems have priority for access to the radar display screen These systems data may be overlaid on the EGPWS display or they may simply override the EGPWS display EGPWS Operation The EGPWS system may vary depending on the installed controls and software level of the EGPWS computer In some installations the EGPWS display on the radar indicator is manually operated It is only displayed if the pilot pushes the ON button and it is removed if the pilot pushes the ON button a second time In some installations the EGPWS display has a pop up mode in which the terrain display is automatically displayed when the EGPWS system detects a terrain alert situation The pilot can remove the ground display from the radar indicator or prevent the EGPWS system from displaying ground on the radar indicator by pushing the INHIB button The 1 and range buttons on the radar indicator control the range of the ground display The radar indicator AZ button is active and can display or remove azimuth buttons The other radar controls do not change the ground display but if they are used while EGPWS is displayed they control the radar RTA and the effects of any changes are seen when the radar image is re displayed For additional information refer to the appropriate AlliedSignal EGPWS operating manual A28 1146 111 Enhanced Ground Proximity Warning System EGPWS
71. between the echoes and the capabilities of you and your aircraft Remember that weather radar detects only precipitation drops it does not detect turbulence Therefore the radar scope provides no assurance of avoidance turbulence The radar scope also does not provide assurance of avoiding instrument weather from clouds and fog Your scope may be clear between intense echoes this clear does not mean you can fly Remember that while hail always gives a radar echo it may fall several miles from the nearest cloud and hazardous turbulence may extend to as much as 20 miles from the echo edge Avoid intense or extreme level echoes by at least 20 miles that is such echoes should be separated by at least 40 miles before you fly between them With weaker echoes you can reduce the distance by which you avoid them DO S AND DON TS OF THUNDERSTORM FLYING Above all remember this Never regard any thunderstorm lightly even when radar observers report the echoes are of light intensity Avoiding thunderstorms is the best policy Following are some do s and don ts of thunderstorm avoidance e Dont land or take off in the face of an approaching thunderstorm A sudden gust front of low level turbulence could cause loss of control Federal Aviation Administration FAA Advisory Circulars A28 1146 111 A 8 REV2 PRIMUS 660 Digital Weather Radar System Don t attempt to fly under a thunderstorm even if you can see through to the other side Tur
72. bited 5 The MFD if used can repeat either left or right side NOTES 1 ONis used to indicate any selected radar mode 3 XXX 2 means that display is controlled by appropriate 4 n standby the RTA is centered in azimuth with 15 data depending upon external switch selection A28 1146 111 System Configurations REV2 2 3 PRIMUS 660 Digital Weather Radar System Equipment covered in this manual is listed in table 2 2 and shown in figure 2 2 Cockpit Mounted Options WI 650 660 Weather Radar Indicator 7007700 VAR WC 660 Weather Radar Controller 7008471 VAR Remote Mounted Equipment WU 660 Receiver Transmitter Antenna 7021450 601 NOTES 1 Typically either the indicator or one of the remote controllers one or two is installed 2 Typical installed antenna sizes range from 12 to 18 inches in diameter PRIMUS 660 Weather Radar Equipment List Table 2 2 NOTE A WC 650 Weather Radar Controller can be installed Except as noted its operation is identical to the WC 660 Weather Radar Controller System Configurations A28 1146 111 2 4 REV2 PRIMUS 660 Digital Weather Radar System oe WU 660 RECEIVER TRANSMITTER ANTENNA D E gt C S D CJ O m g e s 5 WC 660 WEATHER RADAR WI 650 660 WEATHER RADAR CONTROLLER INDICATOR AD 51768 Typical PRIMUS 660 Weather Radar Component
73. bulence and wind shear under the storm could be disastrous Don t fly without airborne radar into a cloud mass containing scattered embedded thunderstorms Scattered thunderstorms not embedded usually can be visually circumnavigated Don t trust the visual appearance to be a reliable indicator of the turbulence inside a thunderstorm Do avoid by at least 20 miles any thunderstorm identified as severe or giving an intense radar echo This is especially true under the anvil of a large cumulonimbus Do circumnavigate the entire area if the area has 6 1 thunderstorm coverage Do remember that vivid and frequent lightning indicates the probability of a severe thunderstorm Do regard as extremely hazardous any thunderstorm with tops 35 000 feet or higher whether the top is visually sighted or determined by radar If you cannot avoid penetrating a thunderstorm the following are some do s BEFORE entering the storm Tighten your safety belt put on your shoulder harness if you have one and secure all loose objects Plan and hold your course to take you through the storm in a minimum time To avoid the most critical icing establish a penetration altitude below the freezing level or above the level of 15 C Verify that pitot heat is on and turn on carburetor heat or jet engine anti ice Icing can be rapid at any altitude and cause almost instantaneous power failure and or loss of airspeed indication Establish power settin
74. cedure 7 11 Ground mapping 5 56 TILT setting for maximal ground target display 5 57 12 inch radiator 5 57 18 inch radiator 5 58 H Hail A 6 Hail in thunderstorms A 12 Index Index 2 Hail size probability 5 36 Honeywell product support 9 1 customer support centers 9 2 North America 9 2 Rest of the World 9 3 publication ordering information 9 4 Icing A 5 In flight adjustments 7 1 pitch and roll trim adjustments 7 1 level flight stabilization check 7 3 pitch gain adjustment 7 15 adjustment procedure 7 15 pitch offset adjustment 7 8 adjustment procedure 7 8 pitch stabilization check 7 12 check procedure 7 12 roll gain adjustment 7 11 adjustment procedure 7 11 roll offset adjustment 7 5 adjustment procedure 7 5 roll stabilization check 7 9 while turning check procedure 7 9 in flight troubleshooting 8 1 fault code and text fault relationships 8 1 8 5 pilot messages 8 8 pilot event marker 8 1 8 4 test mode with TEXT FAULTS enabled 8 2 fault data fields 8 2 Interpreting weather radar images 5 24 radar and visual cloud mass 5 26 squall line 5 27 weather radar images 5 24 Introduction 1 1 A28 1146 111 REV2 PRIMUS 660 Digital Weather Radar System Index cont L Level flight stabilization check 5 17 7 3 stabilization in straight and level flight check procedure 5 17 7 3 Lightning A 7 Line configurations 5 52 avoid bow shaped line of echoes
75. ch has been written about the mechanics and life cycles of thunderstorms They have been studied for many years and while much has been learned the studies continue because much is not known Knowledge and weather radar have modified attitudes toward thunderstorms but one rule continues to be true any storm recognizable as a thunderstorm should be considered hazardous until measurements have shown it to be safe That means safe for you and your aircraft Almost any thunderstorm can spell disaster for the wrong combination of aircraft and pilot A28 1146 111 Federal Aviation Administration FAA Advisory Circulars REV2 A 3 PRIMUS 660 Digital Weather Radar System Hazards A thunderstorm packs just about every weather hazard known to aviation into one vicious bundle Although the hazards occur in numerous combinations let us look at the most hazardous combination of thunderstorm the squall line then we will examine the hazards individually SQUALL LINES A squall line is a narrow band of active thunderstorms Often it develops on or ahead of a cold front in moist unstable air but it may develop in unstable air far removed from any front The line may be too long to detour easily and too wide and severe to penetrate It often contains steady state thunderstorms and presents the single most intense weather hazard to aircraft It usually forms rapidly generally reaching maximum intensity during the late afternoon and the first fe
76. d 300 NM and therefore is not seen if there are no intervening targets The RCT feature includes attenuation compensation Refer to Section 5 Radar Facts for a description of attenuation compensation Rainfall causes attenuation and attenuation compensation modifies the color calibration to maintain calibration regardless of the amount of attenuation Modifying the color calibration results in a change in the point where calibration can no longer keep the radar system calibrated for red level targets The heavier the rainfall the greater the attenuation and the shorter the range where extended sensitivity time control XSTC runs out of control Therefore the range at which the cyan background starts varies depending on the amount of attenuation The greater the attenuation the closer the start of the cyan field The radar s calibration includes a nominal allowance for radome losses Excessive losses in the radome seriously affect radar calibration One possible means of verification are signal returns from known targets Honeywell recommends that the pilot report evidence of weak returns to ensure that radome performance is maintained at a level that does not affect radar calibration Target alert can be selected in any WX range The target alert circuit monitors for hazardous targets within 7 5 of the aircraft centerline Radar Mode Ground Mapping NOTE Refer to Tilt Management in Section 5 Radar Facts for additional informat
77. dar data so ancillary data can be displayed Examples of this data are Electronic checklists Navigation displays Electrical discharge lightning data NOTE n the FP mode the radar RTA is put in standby the alphanumerics are changed to cyan and the FLTPLN flight plan legend is shown in the mode field Operating Controls A28 1146 111 3 6 REV2 PRIMUS 660 Digital Weather Radar System The TGT alert mode can be used in the FP mode With target alert on and the FP mode selected the target alert armed annunciation green TGT is displayed The RTA searches for a hazardous target from 5 to 55 miles and 7 5 of the aircraft heading No radar targets are displayed If a hazardous target is detected the target alert armed annunciation switches to the alert annunciation yellow TGT This advises the pilot that a hazardous target is in his flightpath and the WX mode should be selected to view it NOTE The TGT function is inoperative when a checklist is displayed e TST Test The TST position selects the radar test mode A special test pattern is displayed to verify system operation The TEST legend is shown in the mode field Refer to Section 4 Normal Operations for a description of the test pattern WARNING IN THE TEST MODE THE TRANSMITTER IS ON AND RADIATING X BAND MICROWAVE ENERGY REFER TO SECTION 6 MAXIMUM PERMISSIBLE EXPOSURE LEVEL MPEL AND THE APPENDIX FEDERAL AVIATION ADMINISTRATION FAA ADVIS
78. detected The displayed tilt angle setting could be incorrect This can also cause ground spoking Have the RTA checked at the next opportunity SPOKING LIKELY A problem has been detected that can cause spoking to occur Have the system checked at the next opportunity STAB UNCAL An error in the antenna positioning system has been detected Groundspoking or excessive ground returns during roll maneuvers can occur This can be due either to the RTA or the source of pitch and roll information to the RTA SCAN SWITCH The SCAN SWITCH located on the RTA is off disabling the antenna scan Check at the next opportunity XMIT SWITCH The XMIT switch located on the RTA is off disabling the transmitter Check at the next opportunity Pilot Messages Table 8 3 In Flight Troubleshooting A28 1146 111 8 8 REV2 PRIMUS 660 Digital Weather Radar System 9 Honeywell Product Support Honeywell SPEX program for corporate operators provides an extensive exchange and rental service that complements a worldwide network of support centers An inventory of more than 9000 spare components assures that your Honeywell equipped aircraft will be returned to service promptly and economically This service is available both during and after warranty The aircraft owner operator is required to ensure that units provided through this program have been approved in accordance with their specific maintenance requirements All articles are return
79. djustment as shown in table 7 6 5 If ground returns come in closer on the right side and go out on the left side the roll is understabilized See figure Roll Stabilization While Turning Check Procedure Table 7 5 A28 1146 111 In Flight Adjustments REV2 7 9 PRIMUS 660 Digital Weather Radar System 60 40 lt gt AD 17720 R3 Symmetrical Ground Returns Level Flight and Good Roll Stabilization Figure 7 6 AD 17721 R2 Understabilization in a Right Roll Figure 7 7 In Flight Adjustments A28 1146 111 7 10 REV2 PRIMUS 660 Digital Weather Radar System AD 17722 R2 Overstabilization in a Right Roll Figure 7 8 ROLL GAIN ADJUSTMENT This in flight adjustment is made in a bank when the ground returns do not remain symmetrical during turns The procedure is listed in table 7 6 Step Procedure If two controllers are installed one must be turned off If an indicator is used as the controller the procedure is the same as given below Fly to an altitude of 10 000 feet AGL or greater 3 Set range to 50 NM Adjust the tilt down until a solid band of ground returns are shown on the screen Then adjust the tilt until the green region of the ground returns start at about 40 NM 5 Select STAB STB 4 times within 3 seconds A display with text instructions for roll offset is shown Roll Gain Adjustment Procedure Table 7 6 cont A28 1146 111 In Flight Adjustments REV2 7
80. e 120 scan or the faster update 24 looks minute 60 sector scan 11 AZ AZIMUTH The AZ button is an alternate action switch that enables and disables the electronic azimuth marks When enabled azimuth marks at 30 intervals are displayed The azimuth marks are the same color as the other alphanumerics 12 RANGE The RANGE buttons are two momentary contact buttons used to select the operating range of the radar The range selections are from 5 to 300 NM full scale In FP mode additional ranges of 500 and 1000 NM are available The up arrow selects increasing ranges and the down arrow selects decreasing ranges Each of the five range rings on the display has an associated marker that annunciates its range A28 1146 111 Operating Controls REV2 3 9 PRIMUS 660 Digital Weather Radar System WC 660 WEATHER RADAR CONTROLLER OPERATION The controls and display features of the WC 660 Weather Radar Controller are indexed and identified in figure 3 4 Brightness levels for all legends and controls on the indicator are controlled by the dimming bus for the aircraft panel PULL WX GMAP VAR STBY AD 51772 WC 660 Weather Radar Controller Configurations Figure 3 4 NOTES 1 AWC 650 Weather Radar Controller can be installed in the aircraft Consult the aircraft installed equipment configuration listing for details Except as noted operation of the WC 650 Weather Radar Controller is identical to the WC 660 We
81. e a corrected altimeter setting the altimeter may be more than 100 feet in error LIGHTNING A lightning strike can puncture the skin of an aircraft and can damage communication and electronic navigational equipment Lightning has been suspected of igniting fuel vapors causing explosion however serious accidents due to lightning strikes are extremely rare Nearby lightning can blind the pilot rendering him momentarily unable to navigate by instrument or by visual reference Nearby lightning can also induce permanent errors in the magnetic compass Lightning discharges even distant ones can disrupt radio communications on low and medium frequencies Though lightning intensity and frequency have no simple relationship to other storm parameters severe storms as a rule have a high frequency of lightning WEATHER RADAR Weather radar detects droplets of precipitation size Strength of the radar return echo depends on drop size and number The greater the number of drops the stronger is the echo and the larger the drops the stronger is the echo Drop size determines echo intensity to a much greater extent than does drop number Hailstones usually are covered with a film of water and therefore act as huge water droplets giving the strongest of all echoes Numerous methods have been used in an attempt to categorize the intensity of a thunderstorm To standardize thunderstorm language between weather radar operators and pilots the use of
82. ed to Reconditioned Specifications limits when they are processed through a Honeywell repair facility All articles are inspected by quality control personnel to verify proper workmanship and conformity to Type Design and to certify that the article meets all controlling documentation Reconditioned Specification criteria are on file at Honeywell facilities and are available for review All exchange units are updated with the latest performance reliability MODs on an attrition basis while in the repair cycle When contacting a Honeywell Dealer or Customer Support Center for service under the SPEX program the following information regarding the unit and the aircraft are required e Complete part number with dash number of faulty unit e Complete serial number of faulty unit e Aircraft type serial number and registration number e Aircraft Owner e Reported complaint with faulty unit e Service requested Exchange or Rental e Ship to address e Purchase order number e If faulty unit is IN WARRANTY Type of warranty NEW PRODUCT or Exchange Date warranty started e lf faulty unit is covered under a Maintenance Contract Type of contract Contract date Plan ID number e f faulty unit is NOT IN WARRANTY provide billing address A28 1146 111 Honeywell Product Support REV2 9 1 PRIMUS 660 Digital Weather Radar System The Honeywell Support Centers listed below will assist with processing exchange rental orders
83. enerates most of the energy for the storm s growth and activity Thus a thunderstorm can tend to move with the average wind flow around it but also grow toward moisture When the growth toward moisture is rapid the echo motion often appears erratic On at least one occasion a thunderstorm echo moved in direct opposition to the average wind Severe Weather Avoidance Procedures Table 5 9 cont A28 1146 111 Radar Facts REV2 5 45 PRIMUS 660 Digital Weather Radar System Step Procedure 2 Disturbed Wind Flow Sometimes thunderstorm updrafts block winds near the thunderstorm and act much like a rock in a shallow river bed This pillar of updraft forces the winds outside the storm to flow around the storm instead of carrying it along This also happens in wake eddies that often form downstream of the blocking updraft Interaction With Other Storms A thunderstorm that is located between another storm and its moisture source can cause the blocked storm to have erratic motion Sometimes the blocking of moisture is effective enough to cause the thunderstorm to dissipate Three of the most common erratic motions are 1 Right Turning Echo This is the most frequently observed erratic motion Sometimes a thunderstorm echo traveling the same direction and speed as nearby thunderstorm echoes slows and turns to the right of its previous motion The erratic motion can last an hour or more before it resumes its previous motion The
84. erstorms extending to 60 000 ft show little variation of turbulence intensity with altitude Ice crystals are poor reflectors Rain water at the lower altitudes produce a strong echo however at higher altitudes the nonreflective ice produces a week echo as the antenna is tilted up Therefore though the intensity of the echo diminishes with altitude it does not mean the severity of the turbulence has diminished NOTE Ifthe TILT control is left in a fixed position at the higher flight levels a storm detected at long range can appear to become weaker and actually disappear as it is approached This occurs because the storm cell that was fully within the beam at 100 NM gradually passes out of and under the radar beam When flying at low altitudes rotate tilt upward frequently to avoid flying under a thunderstorm There is some evidence that maximum turbulence exists at middle heights in storms 20 000 to 30 000 ft however turbulence beneath a storm is not to be minimized However the lower altitude can be affected by strong outflow winds and severe turbulence where thunderstorms are present The same turbulence considerations that apply to high altitude flight near storms apply to low altitude flight Severe Weather Avoidance Procedures Table 5 9 cont Radar Facts A28 1146 111 5 44 REV2 PRIMUS 660 Digital Weather Radar System Step Procedure Avoid all rapidly moving echoes by 20 miles A single thunderstorm echo
85. ghtpath as shown in figure 5 34 At lower altitudes the reverse is sometimes true The radar can be scanning below a rapidly developing storm cell that the heavy rain droplets have not had time to fall through the updrafts to the flight level Tilting the antenna up and down regularly produces the total weather picture A28 1146 111 Radar Facts REV2 5 37 PRIMUS 660 Digital Weather Radar System Using a tilt setting that has the radar look into the area of maximum reflectivity 5000 to 20 000 ft gives the strongest radar picture However the tilt setting must not be left at this setting Periodically the pilot should look up and down from this setting to see the total picture of the weather in the flightpath Often hailstorms generate weak but characteristic patterns like those shown in figure 5 35 Fingers or hooks of cyclonic winds that radiate from the main body of a storm usually contain hail A U shaped pattern is also frequently a column of dry hail that returns no signal but is buried in a larger area of rain that does return a strong signal Scalloped edges on a pattern also indicate the presence of dry hail bordering a rain area Finally weak or fuzzy protuberances are not always associated with hail but should be watched closely they can change rapidly BEAM IN IA WW DOWNWARD TILT POSITION WET HAIL AND RAIN AD 12059 R1 Rain Coming From Unseen Dry Hail Figure 5 34 FINGER HOOK U SHAPE AD 357
86. gnition of combustible materials by radiated energy Low tolerance parts of the body include the eyes and the testis A28 1146 111 Federal Aviation Administration FAA Advisory Circulars REV2 A 1 PRIMUS 660 Digital Weather Radar System 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 GENERAL e Airborne weather radar should be operated on the ground only by qualified personnel e Installed airborne radar should not be operated while other aircraft is in the 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 BODY DAMAGE To prevent possible human body damage the following precautions should be taken e Personnel should never stand nearby and in front of a radar antenna which is transmitting When the antenna is not scanning the danger increases e 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
87. gs for turbulence penetration airspeed recommended in your aircraft manual Turn up cockpit lights to highest intensity to lessen temporary blindness from lightning If using automatic pilot disengage altitude hold mode and speed hold mode The automatic altitude and airspeed controls of the aircraft increase maneuvers thus increasing structural stress A28 1146 111 Federal Aviation Administration FAA Advisory Circulars REV2 A 9 PRIMUS 660 Digital Weather Radar System e f using airborne radar tilt the antenna up and down occasionally This will permit you to detect other thunderstorm activity at altitudes other than the one being flown Following are some do s and don ts during thunderstorm penetration e Do keep your eyes on your instruments Looking outside the cockpit can increase danger of temporary blindness from lightning e Don t change power settings maintain settings for the recommended turbulence penetration airspeed e Do maintain constant attitude let the aircraft ride the waves Maneuvers in trying to maintain constant altitude increase stress on the aircraft e Don t turn back once you are in a thunderstorm A straight course through the storm most likely will get you out of the hazards most quickly In addition turning maneuvers increase stress on the aircraft National Severe Storms Laboratory NSSL Thunderstorm Research The NSSL has since 1964 been the focal point of our thunderstorm resea
88. h stabilization check 7 12 power up 4 1 roll gain adjustment 7 11 roll stabilization while turning check 7 9 severe weather avoidance 5 43 stabilization in straight and level flight check 5 17 7 3 stabilization in turns check 5 19 Publication ordering information 9 4 P Pilot event marker 8 4 Pitch and roll trim adjustments 7 1 level flight stabilization check 7 3 Pitch gain adjustment 7 15 adjustment procedure 7 15 Pitch gain error 5 22 Index Index 4 R Radar facts ground mapping 5 56 TILT setting for maximal ground target display 5 57 interpreting weather radar images 5 24 radar and visual cloud mass 5 26 squall line 5 27 weather radar images 5 24 radar operation 5 1 phenomenas 5 4 radome 5 42 rain echo attenuation compensation technique react 5 31 A28 1146 111 REV2 PRIMUS 660 Digital Weather Radar System Index cont azimuth resolution 5 41 hail size probability 5 36 shadowing 5 34 spotting hail 5 37 turbulence probability 5 34 stabilization 5 15 accelerative error 5 15 antenna mounting error 5 16 dynamic error 5 15 pitch gain error 5 22 roll gain error 5 19 wallowing wing walk and yaw error 5 19 tilt management 5 5 tilt setting for minimal ground target display 5 8 variable gain control 5 30 weather avoidance 5 43 additional hazards 5 55 configurations of individual echoes northern hemisphere 5 47 line configurations 5 52 se
89. he pendant shape shown in figure 5 42 represents one of the most severe storms the supercell One study concluded that in supercells e The average maximum size of hail is over 2 inches 5 3 cm e The average width of the hail swath is over 12 5 miles 20 2 km e Sixty percent produce funnel clouds or tornadoes The classic pendant shape echo is shown in figure 5 42 Note the general pendant shape the hook and the steep rain gradient This storm is extremely dangerous and must be avoided STORM MOTION N AD 35706 The Classic Pendant Shape Figure 5 42 Radar Facts A28 1146 111 5 50 REV2 PRIMUS 660 Digital Weather Radar System AVOID STEEP RAIN GRADIENTS BY 20 MILES Figure 5 43 shows steep rain gradients Refer to the paragraph Interpreting Weather Radar Images in this section for a detailed explanation of weather images ON WA Ge PULFORIAR A y GAIN Q i MASA MAX AD 51781 R1 Rain Gradients Figure 5 43 AVOID ALL CRESCENT SHAPED ECHOES BY 20 MILES A crescent shaped echo shown in figure 5 44 with its tips pointing away from the aircraft indicates a storm cell that has attenuated the radar energy to the point where the entire storm cell is not displayed This is especially true if the trailing edge is very crisp and well defined with what appears to be a steep rain gradient When REACT is selected the area behind the steep rain gradient fills in with cyan A28 1146 111 Radar
90. ied above the freezing level the water becomes supercooled When temperature in the upward current cools to about 15 C much of the remaining water vapor sublimates as ice crystals and above this level at lower temperatures the amount of supercooled water decreases e Supercooled water freezes on impact with an aircraft Clear icing can occur at any altitude above the freezing level but at high levels icing from smaller droplets may be rime or mixed with rime and clear The abundance of large supercooled droplets makes clear icing very rapid between O C and 15 C and encounters can be frequent in a cluster of cells Thunderstorm icing can be extremely hazardous A28 1146 111 Federal Aviation Administration FAA Advisory Circulars REV2 A 5 PRIMUS 660 Digital Weather Radar System MOTION OF STORM DRY AIR INFLOW UT AMOS WARM AIR INFLOW ih s I NY Ji WARM AIR INFLOW Pam COLDR AIR OUTFLOW GUST FRONT NAUTICAL MILES 0 AD 37561 Schematic Cross Section of a Thunderstorm Figure A 1 HAIL e Hail competes with turbulence as the greatest thunderstorm hazard to aircraft Supercooled drops above the freezing level begin to freeze Once a drop has frozen other drops latch on and freeze to it so the hailstone grows sometimes into a huge iceball Large hail occurs with severe thunderstorms with strong updrafts that have built to great heights Eventually the hailstones fall possibly so
91. ight Troubleshooting The radar antenna is normally attitude stabilized It automatically compensates for roll and pitch maneuvers refer to Section 5 Radar Facts for a description of stabilization The STAB OFF annunciator is displayed on the screen Operating Controls A28 1146 111 3 8 REV2 PRIMUS 660 Digital Weather Radar System 9 BRT Brightness or BRT LSS Lightning Sensor System The BRT knob is a single turn control that adjusts the brightness of the display CW rotation increases display brightness and ccw rotation decreases brightness An optional BRT LSS four position rotary switch selects the separate LSZ 850 Lightning Sensor System LSS operating modes and the brightness control on some models Its LSS control switch positions are as follows e OFF This position removes all power from the LSS e SBY Standby This position inhibits the display of LSS data but the system accumulates data in this mode e LX Lightning Sensor System In this position the LSS is fully operational and data is being displayed on the indicator e CLR TST Clear Test In this position accumulated data is cleared from the memory of the LSS After 3 seconds the test mode is initiated in the LSS Refer to the LSZ 850 Lightning Sensor System Pilot s Handbook for a detailed description of LSS operation SCT SCAN SECTOR The SCT button is an alternate action switch that is used to select either the normal 12 looks minut
92. ight on Wheels Weather Transmitter Cross Reference Extended Sensitivity Time Control Abbreviations 10 3 10 4 blank PRIMUS 660 Digital Weather Radar System Appendix A Federal Aviation Administration FAA Advisory Circulars NOTE This section contains a word for word transcription of the contents of the following FAA advisory circulars e AC 20 68B e AC 00 24B SUBJECT RECOMMENDED RADIATION SAFETY PRECAUTIONS FOR GROUND OPERATION OF AIRBORNE WEATHER RADAR Purpose This circular sets forth recommended radiation safety precautions to be taken by personnel when operating airborne weather radar on the ground Cancellation AC 20 664A dated April 11 1975 is cancelled Related Reading Material Barnes and Taylor radiation Hazards and Protection London George Newnes Limited 1963 p 211 U S Department of Health Education and Welfare Public Health Service Consumer Protection and Environmental Health Service Environmental health microwaves 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 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 Background Dangers from ground operation of airborne weather radar include the possibility of human body damage and i
93. igital Weather Radar System Step Procedure 5 If the display of ground returns goes out in range the pitch is understabilized See figure 7 10 If the display of ground returns comes in closer in range the pitch is overstabilized See figure 7 11 If the pitch is understabilized or overstabilized you can wish to perform an in flight pitch gain adjustment as shown in table 7 8 Pitch Stabilization Check Procedure Table 7 7 60 40 C s AD 17720 R3 Level Flight and Good Pitch Stabilization Figure 7 9 A28 1146 111 In Flight Adjustments REV2 7 13 PRIMUS 660 Digital Weather Radar System AD 53802 Understabilized in Pitch Up Figure 7 10 AD 53803 Overstabilized in Pitch Up Figure 7 11 In Flight Adjustments A28 1146 111 7 14 REV2 PRIMUS 660 Digital Weather Radar System PITCH GAIN ADJUSTMENT This in flight adjustment is made in a bank when the ground returns do not follow the contours of the range arcs during turns The procedure is listed in table 7 8 e mem 1 If two controllers are installed one must be turned off If an indicator is used as the controller the procedure is the same as given below Fly to an altitude of 10 000 feet AGL or greater Set range to 50 NM 4 Adjust the tilt down until a solid band of ground returns are shown on the screen Then adjust the tilt until the green region of the ground returns start at about 40 NM Push STAB STB 4 times
94. ion on the use of tilt control Ground mapping operation is selected by setting the controls to GMAP The TILT control is turned down until a usable amount of navigable terrain is displayed The degree of down tilt depends on the aircraft altitude and the selected range The receiver sensitivity time control STC characteristics are altered to equalize ground target reflection versus range As a result selecting preset GAIN generally creates the desired mapping display However the pilot can control the gain manually by selecting manual gain and rotating the GAIN control to help achieve an optimum display With experience the pilot can interpret the color display patterns that indicate water regions coast lines hilly or mountainous regions cities or even large structures A good learning method is to practice ground mapping during flights in clear visibility where the radar display can be visually compared with the terrain A28 1146 111 Normal Operation REV2 4 5 PRIMUS 660 Digital Weather Radar System Test Mode The PRIMUS 660 Digital Weather Radar System has a self test mode and a maintenance function In the self test TST mode a special test pattern is displayed as illustrated earlier in this section The functions of this pattern are as follows Color Bands A series of black green yellow red cyan white magenta blue bands indicate that the signal to color conversion circuits are operating normally The main
95. ions and terrain offset this value A28 1146 111 Radar Facts REV2 5 9 PRIMUS 660 Digital Weather Radar System Tilt management is often misunderstood It is crucial to safe operation of airborne weather radar If radar tilt angles are not properly managed weather targets can be missed or underestimated The upper levels of convective storms are the most dangerous because of the probability of violent windshears and large hail But hail and windshear are not very reflective because they lack reflective liquid water The figures that follow show the relationship between flight situations and the correct tilt angle The first describes a high altitude situation the second describes a low altitude situation e The ideal tilt angle shows a few ground targets at the edge of the display as shown in see figure 5 8 Tu onee i GROUND emm RETURN AD 35694 Ideal Tilt Angle Figure 5 8 e Earth s curvature can be a factor if altitude is low enough or if the selected range is long enough as shown in figure 5 9 ou 200 GROUND lt m Pun RETURN AD 35695 Earth s Curvature Figure 5 9 Radar Facts A28 1146 111 5 10 REV2 PRIMUS 660 Digital Weather Radar System e Convective thunderstorms become much less reflective above the freezing level This reflectivity decreases gradually over the first 5000 to 10 000 feet above the freezing level as shown in figure 5 10 Gem FREEZING LEVEL AD 35696 Convective
96. ircraft can be large enough to damage the aircraft by the time it arrives at the storm Oo THUNDERSTORM MATURES AS IT APPROACHES gt FREEZING LEVEL AD 35699 Fast Developing Thunderstorm Figure 5 14 e At low altitude the tilt should be set as low as possible to get ground returns at the periphery only as shown in figure 5 15 CORRECT WRONG FREEZING LEVEL AN AAA AD 35700 Low Altitude Tilt Management Figure 5 15 Excess up tilt should be avoided as it can illuminate weather above the freezing level NOTE The pilot should have freeze level information as a part of the flight planning process A28 1146 111 Radar Facts REV2 5 13 PRIMUS 660 Digital Weather Radar System e The antenna size used on the aircraft alters the best tilt settings by about 1 However tilt management is the same for either size as shown in figure 5 16 10 IN ANTENNA HAS 10 BEAM 12 IN ANTENNA HAS 7 9 BEAM 18 IN ANTENNA HAS 5 6 BEAM 24 IN ANTENNA HAS 4 2 BEAM AD 46703 Antenna Size and Impact on Tilt Management Figure 5 16 NOTE The 10 and 24 inch antennas are shown for illustration purposes only e Some ofthe rules of thumb are described below and shown in figure 5 17 A1 look down angle looks down 100 ft per mile Bottom of beam is 1 2 beam width below tilt setting A 12 inch antenna grazes the ground at 100 NM if set to 0 tilt at 40 000 ft TILT boe wc
97. is not able to compensate Radar Facts A28 1146 111 5 16 REV2 PRIMUS 660 Digital Weather Radar System LEVEL FLIGHT STABILIZATION CHECK Check stabilization in level flight using the procedure in table 5 3 O OO ee Trim the aircraft for straight and level flight in smooth clear air over level terrain Select the 50 mile range 3 Rotate the tilt control until a band of ground returns starts at the 40 NM range arc 4 After several antenna sweeps verify that ground returns are equally displayed figure 5 18 If returns are only on one side of the radar screen or uneven across the radar screen a misalignment of the radar antenna mounting is indicated Stabilization in Straight and Level Flight Check Procedure Table 5 3 NOTE Refer to Section 7 In Flight Adjustments for procedures to adjust pitch and roll offsets AD 17720 R3 Symmetrical Ground Returns Figure 5 18 A28 1146 111 Radar Facts REV2 5 17 PRIMUS 660 Digital Weather Radar System AD 17721 R2 0 Ground Return Indicating Misalignment Upper Right Figure 5 19 AD 17722 R2 0 Ground Return Indicating Misalignment Upper Left Figure 5 20 Radar Facts A28 1146 111 5 18 REV2 PRIMUS 660 Digital Weather Radar System Wallowing Wing Walk and Yaw Error A condition where the greatest intensity of ground targets wanders around the screen over a period of several minutes should not be confused with antenna mounting erro
98. l parameters are set for enroute weather detection If WX is selected before the initial RTA warmup period is complete approximately 45 to 90 seconds the WAIT legend is displayed on the EFIS MFD In WAIT mode the transmitter and antenna scan are inhibited and the display memory is erased When the warmup is complete the system automatically switches to the WX mode The system in preset gain is calibrated as described in table 3 4 Rainfall Rate Color Rainfall Rate Color Coding Table 3 4 e GMAP Ground Mapping The GMAP position puts the radar System in the ground mapping mode The system is fully operational and all parameters are set to enhance returns from ground targets NOTE REACT or TGT modes are not selectable in GMAP WARNING WEATHER TYPE TARGETS ARE NOT CALIBRATED WHEN THE RADAR IS IN THE GMAP MODE BECAUSE OF THIS DO NOT USE THE GMAP MODE FOR WEATHER DETECTION Operating Controls A28 1146 111 3 14 REV2 PRIMUS 660 Digital Weather Radar System As a constant reminder that GMAP is selected the GMAP legend is displayed in the mode field and the color scheme is changed to cyan yellow and magenta Cyan represents the least reflective return yellow is a moderate return and magenta is a strong return If GMAP is selected before the initial RTA warmup period is complete approximately 45 to 90 seconds the white WAIT legend is displayed in the mode field In wait mode the transmitter and anten
99. ld be clear that the only safe way to operate in areas of thunderstorm activity is to AVOID ALL CELLS THAT HAVE RED OR MAGENTA RETURNS A28 1146 111 REV2 Radar Facts 5 36 PRIMUS 660 Digital Weather Radar System 100 80 gt o z 5 Z 60 uw DE LL W E 40 EN Lu tc 20 ES 3 4 AND LAGER HAIL 0 LEVEL 2 LEVEL 3 LEVEL 4 YELLOW RED MAGENTA AD 15358 R1 Hail Size Probability Figure 5 33 Spotting Hail As previously stated dry hail is a poor reflector and therefore generates deceptively weak or absent radar returns When flying above the freezing level hail can be expected in regions above and around wet storm cells found at lower altitudes The hail is carried up to the tropopause by strong vertical winds inside the storm In large storms these winds can easily exceed 200 kt making them very dangerous Since the core of such a storm is very turbulent but largely icy the red core on the radar display is weak or absent and highly mobile The storm core can be expected to change shapes with each antenna scan On reaching the tropopause the hail is ejected from the storm and falls downward to a point where it is sucked back into the storm When the hail falls below the freezing level however it begins to melt and form a thin surface layer of liquid detectable by radar A slight downward tilt of the antenna toward the warmer air shows rain coming from unseen dry hail that is directly in the fli
100. limiting exposure of humans to an average power density not greater than 10 milliwatts per square centimeter e Personnel should be advised to avoid the end of an open waveguide unless the radar is turned off e 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 e 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 Federal Aviation Administration FAA Advisory Circulars A28 1146 111 A 2 REV2 PRIMUS 660 Digital Weather Radar System COMBUSTIBLE MATERIALS To prevent possible fuel ignition an insulated airborne weather radar should not be operated while an aircraft is being refueled or defueled M C Beard Director of Airworthiness SUBJECT THUNDERSTORMS Purpose This advisory circular describes the hazards of thunderstorms to aviation and offers guidance to help prevent accidents caused by thunderstorms Cancellation Advisory Circular 00 24A dated June 23 1978 is cancelled Related Reading Material Advisory Circulars 00 6A Aviation Weather 090 45B Aviation Weather Services 00 50A Low Level Wind Shear General We all know what a thunderstorm looks like Mu
101. ll in red less severe rainfall in yellow moderate rainfall in green and little or no rainfall in black background If selected at installation the antenna sweep position indicator is a yellow band at the top of the display Range marks and identifying numerics displayed in contrasting colors are provided to facilitate evaluation of storm cells Selection of the GMAP function causes the system parameters to be optimized to improve resolution and enhance identification of small targets at short ranges The reflected signal from ground surfaces is displayed as magenta yellow or cyan most to least reflective NOTE Section 5 Radar Facts describes a variety of radar operating topics It is recommended that you read Section 5 Radar Facts before learning the specific operational details of the PRIMUS 660 Digital Weather Radar System A28 1146 111 Introduction REV2 PRIMUS 660 Digital Weather Radar System The radar indicator is equipped with the universal digital interface UDI This feature expands the use of the radar indicator to display information such as checklists short and long range navigation displays when used with a Honeywell DATA NAV system and electrical discharge data from Honeywell s LSZ 850 Lightning Sensor System LSS NOTE Refer to Honeywell Pub 28 1146 54 LSZ 850 Lightning Sensor System Pilot s Handbook for more information Introduction A28 1146 111 REV2 PRIMUS 660 Digital
102. me distance from the storm core Hail may be encountered in clear air several miles from dark thunderstorm clouds e Ashailstones fall through air whose temperature is above 0 C they begin to melt and precipitation may reach the ground as either hail or rain Rain at the surface does not mean the absence of hail aloft You should anticipate possible hail with any thunderstorm especially beneath the anvil of a large cumulonimbus Hailstones larger than one half inch in diameter can significantly damage an aircraft in a few seconds Federal Aviation Administration FAA Advisory Circulars A28 1146 111 A 6 REV2 PRIMUS 660 Digital Weather Radar System LOW CEILING AND VISIBILITY Generally visibility is near zero within a thunderstorm cloud Ceiling and visibility may also be restricted in precipitation and dust between the cloud base and the ground The restrictions create the same problem as all ceiling and visibility restrictions but the hazards are increased many fold when associated with other thunderstorm hazards of turbulence hail and lightning which make precision instrument flying virtually impossible EFFECT ON ALTIMETERS Pressure usually falls rapidly with the approach of a thunderstorm then rises sharply with the onset of the first gust and arrival of the cold downdraft and heavy rain showers falling back to normal as the storm moves on This cycle of pressure change may occur in 15 minutes If the pilot does not receiv
103. n the WX mode variable gain can increase receiver sensitivity over the calibrated level to show very weak targets or it can be reduced below the calibrated level to eliminate weak returns WARNING LOW VARIABLE GAIN SETTINGS CAN ELIMINATE HAZARDOUS TARGETS Radar Facts A28 1146 111 5 30 REV2 PRIMUS 660 Digital Weather Radar System RAIN ECHO ATTENUATION COMPENSATION TECHNIQUE REACT Honeywell s REACT feature has three separate but related functions e Attenuation Compensation As the radar energy travels through rainfall the raindrops reflect a portion of the energy back toward the airplane This results in less energy being available to detect raindrops at greater ranges This process continues throughout the depth of the storm resulting in a phenomenon known as attenuation The amount of attenuation increases with an increase in rainfall rate and with an increase in the range traveled through the rainfall i e heavy rain over a large area results in high levels of attenuation while light rain over a small area results in low levels of attenuation Storms with high rainfall rates can totally attenuate the radar energy making it impossible to see a second cell hidden behind the first cell In some cases attenuation can be so extreme that the total depth of a single cell cannot be shown Without some form of compensation attenuation causes a single cell to appear to weaken as the depth of the cell increases Honey
104. na scan are inhibited and the memory is erased When the warmup period is complete the system automatically switches to the GMAP mode NOTE Some installations have controllers that have a WX GMAP select switch In this case the radar mode switch provides an ON selection The separate WX GMAP switch is used to select either WX weather or GMAP ground mapping e FP Flight Plan The FP position puts the radar system in the flight plan mode that clears the screen of radar data This allows the radar controller to select a range for display on EFIS of mapping information at very long ranges NOTE In the FP mode the radar RTA is put in standby and the FLTPLN legend is displayed in the mode field The target alert mode can be used in the FP mode With target alert on and the FP mode selected the target alert armed annunciation green TGT is displayed The RTA searches for a hazardous target from 5 to 55 miles and 7 5 degrees of dead ahead No radar targets are displayed If a hazardous target is detected the target alert armed annunciation switches to the alert annunciation amber TGT This advises the pilot that a hazardous target is in his flightpath and he should select the WX mode to view it NOTE When displaying checklist the TGT function is inoperative e TST Test The TST position selects the radar test mode A special test pattern is displayed to verify system operation The TEST legend is displayed in the mode
105. nderstorms and a severe thunderstorm can destroy an aircraft Strongest turbulence within the cloud occurs with shear between updrafts and downdrafts Outside the cloud shear turbulence has been encountered several thousand feet above and 20 miles laterally from a severe thunderstorm A low level turbulent area is the shear zone associated with the gust front Often a roll cloud on the leading edge of a storm marks the top of the eddies in this shear and it signifies an extremely turbulent zone Gust fronts move far ahead up to 15 miles of associated precipitation The gust front causes a rapid and sometimes drastic change in surface wind ahead of an approaching storm Advisory Circular 00 50A Low Level Wind Shear explains in greater detail the hazards associated with gust fronts Figure 1 shows a schematic cross section of a thunderstorm with areas outside the cloud where turbulence may be encountered e lt is almost impossible to hold a constant altitude in a thunderstorm and maneuvering in an attempt to do so produces greatly increased stress on the aircraft It is understandable that the speed of the aircraft determines the rate of turbulence encounters Stresses are least if the aircraft is held in a constant attitude and allowed to ride the waves To date we have no sure way to pick soft spots in a thunderstorm ICING e Updrafts in a thunderstorm support abundant liquid water with relatively large droplet sizes and when carr
106. o the radar receiver Electronic circuits measure the elapsed time between the transmission and the reception of the echo to determine the distance to the target range Because the antenna beam is scanning right and left in synchronism with the sectoring sweep on the indicator the bearing of the target is found as shown in figure 5 1 The indicator with the radar is called a plan position indicator PPI type When an architect makes a drawing for a house one of the views he generally shows is a plan view a diagram of the house as viewed from above The PPI aboard an airplane presents a cross sectional picture of the storm as though viewed from above In short it is NOT a horizon view of the storm cells ahead but rather a MAP view This positional relationship of the airplane and the storm cells as displayed by the indicator is shown in figure 5 1 A28 1146 111 Radar Facts REV2 PRIMUS 660 Digital Weather Radar System AIRCRAFT HEADING t 0 AD 12055 R2 Positional Relationship of an Airplane and Storm Cells Ahead as Displayed on Indicator Figure 5 1 The drawing is laid out to simulate the face of the indicator with the semicircular range marks To derive a clearer concept of the picture that the indicator presents imagine that the storm is a loaf of sliced bread standing on end From a point close to the surface of earth it towers to a high altitude summit Without upsetting the loaf of bread the radar remo
107. offset entry menu and rotate it The offset range is from 2 0 to 2 0 When flying straight and level adjust so the contour of the ground returns follow the contour of the range arcs as closely as possible When change is completed push in the GAIN knob The display returns to the previous message 10 Push the STAB STB button to go to the next menu roll gain To change the pitch offset value pull out the GAIN knob Pitch Offset Adjustment Procedure Table 7 4 In Flight Adjustments A28 1146 111 7 8 REV2 PRIMUS 660 Digital Weather Radar System ROLL STABILIZATION CHECK Once proper operation in level flight has been established you can verify correct roll stabilization using the procedures in table 7 5 e meme 1 Trim the aircraft for straight and level flight in smooth clear air over level terrain at an altitude of at least 10 000 feet Select the 50 mile range and GMAP mode Adjust the TILT control until your radar display shows a solid band of ground returns starting at the 40 mile range arc See figure 7 6 Place the aircraft in a 20 degree or greater roll to the right If there is little change to the arc of ground returns the roll stabilization is good 7 7 If the ground returns go out on the right side and come in closer on the left side the roll is overstabilized See figure 7 8 If the roll is understabilized or overstabilized you can perform an in flight roll gain a
108. oid pendant by 20 miles 5 50 avoid steep rain gradients by 20 miles 5 51 avoid v notch by 20 miles 5 49 line configurations 5 52 avoid bow shaped line of echoes by 20 miles 5 54 avoid line echo wave patterns LEWP by 20 miles 5 53 avoid thunderstorm echoes at the south end of a line or at a break in a line by 20 miles 5 52 severe weather avoidance procedures 5 43 Weather display calibration 5 28 Weather radar A 7 Weather radar controller operation WC 660 3 10 GAIN 3 16 LSS lightning sensor system optional 3 13 CLR TST clear test 3 13 LX lightning sensor system 3 13 OFF 3 13 SBY standby 3 13 RADAR 3 14 FP flight plan 3 15 GMAP ground mapping 3 14 OFF 3 14 rainfall rate color coding 3 14 STBY standby 3 14 TST test 3 15 WX weather 3 14 RANGE 3 11 RCT rain echo attenuation compensation technique REACT 3 11 SECT scan sector 3 12 Index Index 7 PRIMUS 660 Digital Weather Radar System Index cont Weather radar controller operation WC 660 cont SLV slave dual installations only 3 13 STAB stabilization 3 11 target alert characteristics 3 12 TGT target 3 12 TILT 3 13 Weather radar indicator operation WI 650 660 3 1 AZ azimuth 3 9 BRT brightness or BRT LSS lightning sensor system 3 9 CLR TST clear test 3 9 LX lightning sensor system 3 9 OFF 3 9 SBY standby 3 9 display area 3 5 display screen features 3 5 function swi
109. on and should be ready for use However due to the tolerances of some vertical reference sources make a final adjustment whenever the radar or vertical reference is replaced on the aircraft or if stabilization problems are observed in flight The four trim adjustments and their effects are summarized in table 7 1 Effect On Ground Trim Return Display Over Adjustment Flight Condition Level Terrain Roll offset Straight and level Nonsymmetrical display Pitch offset Straight and level Ground displays do not follow contour of range arcs Roll gain Constant roll angle Nonsymmetrical display gt 20 Pitch gain Constant pitch angle Ground displays do not follow contour of range arcs NOTE Generally it is recommended to perform trim adjustments only if noticeable effects are being observed Pitch and Roll Trim Adjustments Criteria Table 7 1 A28 1146 111 In Flight Adjustments REV2 7 1 PRIMUS 660 Digital Weather Radar System NOTES 1 Depending on the installation not all of the adjustments shown in table 7 1 are available If STAB TRIM ENABLE programming pin is open only the roll offset adjustment is available If STAB TRIM ENABLE programming pin is grounded all four adjustments are available Consult the installation configuration information for details After any adjustment procedure is completed monitor the ground returns displayed by the radar during several pitch and roll maneuvers Verify
110. otor whenever the airplane banks more than approximately 6 to reduce the effect of lateral acceleration during turns To some extent stabilization error is displayed in the radar image after any speed change and or turn condition If the stabilization system seems to be in error because the radar begins ground mapping on one side and not the other or because it appears that the tilt adjustment has slipped verify that aircraft has been in nonturning constant speed flight long enough to let the gyroscope erect on true earth gravity When dynamic and acceleration errors are taken into account maintaining accuracy of 1 2 of 1 or less is not always possible Adjust the antenna tilt by visually observing the ground return Then slowly tilt the antenna upward until terrain clutter no longer enters the display except at the extreme edges Antenna Mounting Error If the radar consistently displays more ground returns on one side or the other during level flight over level ground the antenna is probably scanning on a slight diagonal rather than level with the earth The usual cause is that the radar antenna is physically mounted slightly rotated from the vertical axis of the aircraft The procedure in table 5 3 and figures 5 18 5 19 and 5 20 can help you identify this type of problem On a vertical gyro equipped aircraft the condition could be caused by mistrim flying one wing low The gyro erects to this condition and the stabilization
111. ound Returns Good Pitch Stabilization Figure 5 25 Radar Facts A28 1146 111 5 22 REV2 PRIMUS 660 Digital Weather Radar System Understabilized in Pitch Up Figure 5 26 AD 53798 Overstabilized in Pitch Up Figure 5 27 Refer to Section 7 In Flight Adjustments for adjustment procedures A28 1146 111 Radar Facts REV2 5 23 PRIMUS 660 Digital Weather Radar System INTERPRETING WEATHER RADAR IMAGES From a weather standpoint hail and turbulence are the principal obstacles to a safe and comfortable flight Neither of these conditions is directly visible on radar The radar shows only the rainfall patterns that these conditions are associated The weather radar can see water best in its liquid form as shown in figure 5 28 not water vapor not ice crystals not hail when small and perfectly dry It can see rain wet snow wet hail and dry hail when its diameter is about 8 10 of the radar wavelength or larger At X band this means that dry hail becomes visible to the radar at about 1 in diameter REFLECTIVE LEVELS WILL NOT REFLECT WET HAIL GOOD VAPOR RAIN GOOD 29 Po 050 ICE CRYSTALS ope eo O80 WET SNOW GOOD con o SMALL DRY HAIL DRY HAIL POOR ah g ooo09 3 DRY SNOW VERY POOR AD 46704 R1Q Weather Radar Images Figure 5 28 Radar Facts A28 1146 111 5 24 REV2 PRIMUS 660 Digital Weather Radar System The following are some truths about weather and flying as sho
112. r This phenomenon is caused by the tendency for many aircraft to slowly wallow roll and yaw axes movement with a cycle time of several minutes The erection circuits of the gyro chasing the wallow can intensify the effect of wandering ground targets IRS equipped aircraft are less likely to show this condition Roll Gain Error If when the aircraft is in a turn you see ground returns on one side or the other that are not present in level flight the roll gain is most likely misadjusted The procedure in table 5 4 and figures 5 21 5 22 and 5 23 can help you identify this type of problem Figure 5 24 shows a total lack of roll stabilization in a turn ROLL STABILIZATION WHILE TURNING CHECK Once proper operation is established in level flight verify stabilization in a turn using this procedure 9m Pte OO SSS Place the aircraft in 20 roll to the right Note the radar display It should contain appreciably no more returns than found during level flight See figure 5 24 3 If returns display on the right side of radar indicator the radar system is understabilizing 4 Targets on the left side of the radar display indicate the System is overstabilizing See figure 5 23 NOTE Proper radar operation in turns depends on the accuracy and stability of the installed attitude source Stabilization in Turns Check Procedure Table 5 4 A28 1146 111 Radar Facts REV2 5 19 PRIMUS 660 Digital Weather Radar System
113. r Indicator During this procedure described in table 7 3 the GAIN control acts as roll offset control After the procedure the GAIN control reverts to acting as a gain control Step Procedure If two controllers are installed one must be turned off If an indicator is used as the controller the procedure is the same as given below 2 Fly to an altitude of 10 000 feet above ground level AGL or greater 3 Set range to 50 NM In Flight Roll Offset Adjustment Procedure Table 7 3 cont A28 1146 111 In Flight Adjustments REV2 7 5 PRIMUS 660 Digital Weather Radar System Step Procedure NOTE Adjust the tilt down until a solid band of ground returns are shown on the screen Then adjust the tilt until the green region of the ground returns start at about 40 NM Select STAB STB 4 times within 3 seconds A display with text instructions is displayed See figure 7 4 The radar unit is in the roll offset adjustment mode Pull out the GAIN knob to make a roll offset adjustment See figure 7 5 for a typical display The offset range is from 2 0 to 2 0 and is adjustable by the GAIN knob The polarity of the GAIN knob is such that clockwise rotation of the knob causes the antenna to move down when scanning on the right side While flying straight and level adjust the GAIN knob until ground clutter display is symmetrical Push in the GAIN knob When the GAIN knob is pushed in the display returns
114. r and antenna scan is inhibited and the memory is erased Upon completion of the warmup period the system automatically switches to WX mode WX can only be selected when the function switch is in the ON position 2 GMP GROUND MAPPING OR MAP GMP button selects the ground mapping mode The system is fully operational and all parameters are set to enhance returns from ground targets NOTE REACT or TGT modes are not selectable in GMP Operating Controls A28 1146 111 3 2 REV2 PRIMUS 660 Digital Weather Radar System WARNING WEATHER TYPE TARGETS ARE NOT CALIBRATED WHEN THE RADAR IS IN THE GMAP MODE BECAUSE OF THIS DO NOT USE THE GMAP MODE FOR WEATHER DETECTION As a constant reminder the GMP is selected the alphanumerics are changed to green the GMP legend is shown in the mode field and the color scheme is changed to cyan yellow and magenta Cyan represents the least reflective return yellow is a moderated return and magenta is a strong return If GMP is selected before the initial RTA warmup period is complete the white WAIT legend is shown in the mode field In wait mode the transmitter and antenna scan are inhibited and the memory is erased When the warmup period is complete the system automatically switches to the GMP mode GMP can only be selected when the function switch is in the ON position RCT RAIN ECHO ATTENUATION COMPENSATION TECHNIQUE REACT The RCT switch is an alternate action switch th
115. r exchange rental support centers 9 2 Index Index 5 PRIMUS 660 Digital Weather Radar System Index cont System configurations 2 1 dual configuration 2 1 dual control mode truth table 2 3 equipment list 2 4 cockpit mounted options 2 4 remote mounted 2 4 stand alone 2 1 T Test mode 4 6 color bands 4 6 dedicated radar indicator 4 6 EFIS MFD ND 4 6 Test mode with TEXT FAULTS enabled 8 2 Thunderstorms A 3 Cancellation A 3 general A 3 hazards A 4 do s and don ts of thunderstorm flying A 8 effect on altimeters A 7 hail A 6 icing A 5 lightning A 7 low ceiling and visibility A 7 schematic cross section of a thunderstorm A 6 squall lines A 4 tornadoes A 4 turbulence A 5 weather radar A 7 national severe storms laboratory NSSL thunderstorm research A 10 extrapolation to different climbs A 13 hail in thunderstorms A 12 maximum storm tops A 12 modification of criteria when Severe storms and rapid development are evident A 13 Index Index 6 relationship between turbulence and altitude A 10 relationship between turbulence and reflectivity A 10 turbulence above storm tops A 11 turbulence and echo intensity on NWS radar WSR 57 A 11 turbulence below cloud base A 12 turbulence in relation to distance from the storm edge A 11 turbulence in relation to distance from storm core A 11 use of airborne radar A 13 visual appearance of storm and associated turb
116. rch In flight conditions obtained from thunderstorm penetration by controlled especially equipped high performance aircraft are compared by the NSSL with National Weather Service NWS type ground based radar and with newly developed doppler radar The following comments are based on NSSL s interpretation of information and experience from this research RELATIONSHIP BETWEEN TURBULENCE AND REFLECTIVITY Weather radar reflects precipitation such as rain and hail It has been found however that the intensity level of the precipitation reflection does correlate with the degree of turbulence in a thunderstorm The most severe turbulence is not necessarily found at the same place that gives the greatest radar reflection RELATIONSHIP BETWEEN TURBULENCE AND ALTITUDE The NSSL studies of thunderstorms extending to 60 000 feet show little variation of turbulence intensity with altitude Federal Aviation Administration FAA Advisory Circulars A28 1146 111 A 10 REV2 PRIMUS 660 Digital Weather Radar System TURBULENCE AND ECHO INTENSITY ON NWS RADAR WSR 57 The frequency and severity of turbulence increases with radar reflectivity a measure of the intensity of echoes from storm targets at a standard range Derived gust velocities exceeding 2 100 feet per minute classified as severe turbulence are commonly encountered in level 3 storms In level 2 storms gusts of intensity between 1 200 and 2 100 feet per minute classified as moderate t
117. re storms The tornado itself is often associated with only a weak echo Echo hooks and appendages are useful qualitative indicators of tornado occurrence but are by no means infallible guides Severe turbulence should be anticipated up to 20 miles from the radar edge of severe storms these often have a well defined radar echo boundary The distance decreases to approximately 10 miles with weaker storms which may sometimes have indefinite radar echo boundaries THEREFORE AIRBORNE RADAR IS A PARTICULARLY USEFUL AID FOR PILOTS IN MAINTAINING A SAFE DISTANCE FROM SEVERE STORMS A28 1146 111 Federal Aviation Administration FAA Advisory Circulars REV2 A 11 PRIMUS 660 Digital Weather Radar System TURBULENCE ABOVE STORM TOPS Flight data shows a relationship between turbulence above storm tops and the airspeed of upper tropospheric winds WHEN THE WINDS AT STORM TOP EXCEED 100 KNOTS THERE ARE TIMES WHEN SIGNIFICANT TURBULENCE MAY BE EXPERIENCED AS MUCH AS 10 000 FEET ABOVE THE CLOUD TOPS THIS VALUE MAY BE DECREASED 1 000 FEET FOR EACH 10 KNOT REDUCTION OF WIND SPEED This is especially important for clouds whose height exceeds the height of the tropopause It should be noted that flight above severe thunderstorms is an academic consideration for today s civil aircraft in most cases since these storms usually extend up to 40 000 feet and above TURBULENCE BELOW CLOUD BASE While there is little evidence that maximum turbulence exists at
118. s Figure 2 2 A28 1146 111 System Configurations REV2 2 5 2 6 blank PRIMUS 660 Digital Weather Radar System 3 Operating Controls There are two basic controllers that are described in this section They are in order of description e WI 650 660 Weather Radar Indicator e WC 660 Weather Radar Controller WI 650 660 WEATHER RADAR INDICATOR OPERATION All controls used to operate the system display shown in figure 3 1 are located on the WI 650 660 Weather Radar Indicator front panel CU aa 9 We AD 51769 R1 Typical PRIMUS 660 Digital Weather Radar Display Figure 3 1 The controls and display features of the WI 650 660 Weather Radar Indicator are indexed and identified in figure 3 2 Brightness levels for all legends and controls on the indicator are controlled by the dimming bus for the aircraft panel A28 1146 111 Operating Controls REV2 3 1 PRIMUS 660 Digital Weather Radar System Honeywell AD 51770 WI 650 660 Weather Radar Indicator Front Panel View Figure 3 2 O WX WEATHER The WX button is used to select the weather mode of operation When WX is pushed the system is fully operational and all internal parameters are set for enroute weather detection Alphanumerics are white and WX is displayed in the mode field If WX is selected prior to the expiration of the initial RTA warm up period the white WAIT legend is displayed in the mode field In wait mode the transmitte
119. s situation if they habitually fly with the radar on the short range The short range returns show an obvious corridor between two areas of heavy rainfall but the long range setting shows the trap Both the near and far weather zones could be avoided by a short term course change of about 45 to the right Always switch to long range before entering such a corridor THE BLIND ALLEY LONG RANGE SHORT RANGE AD 12062 R1 Short and Long Blind Alley Figure 5 37 Radar Facts A28 1146 111 5 40 REV2 PRIMUS 660 Digital Weather Radar System Azimuth Resolution When two targets such as storms are closely adjacent at the same range the radar displays them as a single target as shown in figure 5 38 However as the aircraft approaches the targets they appear to separate In the illustration the airplane is far away from the targets at position A At this distance the beam width is spreading As the beam scans across the two targets there is no point that the beam energy is not reflected either by one target or the other because the space between the targets is not wide enough to pass the beam width In target position B the aircraft is closer to the same two targets the beam width is narrower and the targets separate on the display INDICATOR DISPLAY A ER BR NS 3o 30 10 INDICATOR DISPLAY B AD 35705 Azimuth Resolution in Weather Modes Figure 5 38 A28 1146 111 Radar Facts REV2 5 41
120. st of Tables cont Table Page 7 4 Pitch Offset Adjustment Procedure 7 8 7 5 Roll Stabilization While Turning Check Procedure 0 cc cece cece nemias 7 9 7 6 Roll Gain Adjustment Procedure 7 11 7 7 Pitch Stabilization Check Procedure 7 12 7 8 Pitch Gain Adjustment Procedure 7 15 8 1 Fault Data Fields 8 2 8 2 Text Faults 8 5 8 3 Pilot Messages 8 8 B 1 EGPWS Obstacle Display Color Definitions B 4 A28 1146 111 Table of Contents REV 2 TC 7 TC 8 blank PRIMUS 660 Digital Weather Radar System 1 Introduction The PRIMUS 660 Digital Weather Radar System is a lightweight X band digital radar with alphanumerics designed for weather detection WX and ground mapping GMAP The primary purpose of the system is to detect storms along the flightpath and give the pilot a visual indication in color of their rainfall intensity After proper evaluation the pilot can chart a course to avoid these storm areas WARNING THE SYSTEM PERFORMS THE FUNCTIONS OF WEATHER DETECTION OR GROUND MAPPING IT SHOULD NOT BE USED NOR RELIED UPON FOR PROXIMITY WARNING OR ANTICOLLISION PROTECTION In weather detection mode storm intensity levels are displayed in four bright colors contrasted against a deep black background Areas of very heavy rainfall appear in magenta heavy rainfa
121. st tilt angle lies where ground targets are barely visible or just off the radar image Tables 5 1 and 5 2 give the approximate tilt settings required for different altitudes and ranges If the altitude changes or a different range is selected adjust the tilt control as required to minimize ground returns A28 1146 111 Radar Facts REV2 PRIMUS 660 Digital Weather Radar System LINE OF 5 100 200 SIGHT 40 000 zial 4 JEJ 3500 Ewp3pypr 200 EILE 25 000 pejal 20 000 4 0 1 wm poje a wx epe pes som sepe CEEE 300 2 1 48 8 200 o 2 8 3 p wo eee os Approximate Tilt Setting for Minimal Ground Target Display 12 Inch Radiator Table 5 1 a LL EZ O a Foc Lus LINE OF SIGHT LIMITED REGION AD 29830 R2 Tilt angles shown are approximate Where the tilt angle is not listed the operator must exercise good judgment NOTE The line of sight distance is nominal Atmospheric conditions and terrain offset this value Radar Facts A28 1146 111 5 8 REV2 PRIMUS 660 Digital Weather Radar System LINE OF SIGHT MILES 3m psp psp TILT LIMITED REGION IGHT LIMITED REGION INE OF Si AD 35711 Approximate Tilt Setting for Minimal Ground Target Display 18 Inch Radiator Table 5 2 Tilt angles shown are approximate Where the tilt angle is not listed the operator must exercise good judgment NOTE The line of sight distance is nominal Atmospheric condit
122. storm area In the example shown in figure 5 30 radar observation shows that the rainfall is steadily diminishing on the left while it is very heavy in two mature cells and increasing rapidly in a third cell to the right The safest and most comfortable course lies to the left where the storm is decaying into a light rain The growing cell on the right should be given a wide berth GROWING AREAS OF MAXIMUM TURBULENCE CELLS DECAYING CELLS MATURE CELLS OUTLINE OF RAIN AREA VISIBLE TO RADAR BEST DETOUR AD 12058 R1 Squall Line Figure 5 30 A28 1146 111 Radar Facts REV2 5 27 PRIMUS 660 Digital Weather Radar System WEATHER DISPLAY CALIBRATION Ground based Nexrad radars of the National Weather Service display rainfall levels in dBZ a decibel scaling of an arbitrary reflectivity factor Z The formula for determining dBZ is dBZ 16 log R 23 where R is the rainfall rate in millimeters per hour The Nexrad radar displays rainfall in 15 color coded levels of 5 dBZ per step There is a close correspondence in rainfall rates between the colors in the PRIMUS airborne radars and color families in a Nexrad display To help the pilot in comparing them table 5 6 shows PRIMUS radar colors rainfall rates and dBZ The dBZ rainfall intensity scale replaces the video integrated processor VIP intensity scale used in the previous generation ground based radars Table 5 7 compares the classic VIP levels rainfall rates and
123. storm categories with the new dBZ levels Refer to Section 6 of FAA Advisory Circular AC 00 24B for additional information on VIP levels Table 5 6 also shows maximum calibrated range for each color level This is the maximum range where the indicated rainfall rate can be detected if there is no intervening radar signal attenuation caused by other precipitation Beyond calibrated range the precipitation appears at a lower color level than it actually is For example with a 12 inch antenna a red level storm can appear as a green level at 200 miles as you fly closer it becomes yellow and then red at 130 miles As covered in the RCT description intervening rainfall reduces the calibrated range and the radar can incorrectly depict the true cell intensity The radar calibration includes a nominal allowance for radome losses Excessive losses in the radome seriously affect radar calibration One possible means of verification is signal returns from known ground targets It is recommended that you report evidence of weak returns to ensure that radome performance is maintained at a level that does not affect radar calibration To test for a performance loss note the distance that the aircraft s base city a mountain or a shoreline can be painted from a given altitude When flying in familiar surroundings verify that landmarks can still be painted at the same distances Any loss in performance results in the system not painting the reference
124. t either standby or test mode as shown in figure 4 1 PRIMUS 660 Power Up Procedure Table 4 1 cont A28 1146 111 Normal Operation REV2 4 1 PRIMUS 660 Digital Weather Radar System Step Procedure When power is first applied the radar is in WAIT for approximately 90 seconds to allow the magnetron to warm up Power interruptions lasting less than 3 seconds result in a 6 second wait period NOTE If forced standby is incorporated it is necessary to exit forced standby WARNING OUTPUT POWER IS RADIATED IN TEST MODE After the warm up select the test mode and verify that the test pattern is displayed as shown in figure 4 2 If the radar is being used with an EFIS the test pattern is similar The antenna position indicator API is shown as a yellow arc at the top of the display NOTE The API a strap option paints and unpaints on alternate sweeps to supply a continuous indication of picture bus activity The color of the text does not change on alternate sweeps Bd Verify that the azimuth marks target alert TGT and sector scan controls are operational PRIMUS 660 Power Up Procedure Table 4 1 Normal Operation A28 1146 111 4 2 REV2 PRIMUS 660 Digital Weather Radar System TGT OR VAR ANNUNCIATOR TGT TARGET ALERT P660 WX GREEN SELECTED ANNUNCI HONS WX RANGE AMBER TGT DETECTED WHITE VAR VARIABLE GAIN AMBER e STBY GREEN e TEST GREEN
125. t the latest revised pages and dispose of superseded pages Enter revision number and date insertion date and the incorporator s initials on the Record of Revisions The typed initials H are used when Honeywell is the incorporator Revision Revision Number Date 1 Aug 1999 2 Dec 1999 3 Aug 2003 A28 1146 111 REV3 Insertion Date Aug 1999 Dec 1999 Aug 2003 By HI HI Record of Revisions RR 1 RR 2 blank PRIMUS 660 Digital Weather Radar System Record of Temporary Revisions Upon receipt of a temporary revision insert the yellow temporary revision pages according to the filing instructions on each page Then enter the temporary revision number issue date and insertion date on this page Date the Temporary Revision Was Insertion of Removal of Temporary Incorporated Temporary Temporary Revision by a Regular Revision Revision No Issue Date Revision Date By Date By A28 1146 111 Record of Temporary Revisions REV2 RTR 1 RTR 2 blank PRIMUS 660 Digital Weather Radar System List of Effective Pages Original 0 Feb 1998 Revision 1 Aug 1999 Revision 2 Dec 1999 Revision 3 Aug 2003 Subheading and Page Revision Subheading and Page Revision Title Page 3 3 4 0 3 5 0 Record of Revisions 3 6 0 RR 1 RR 2 3 3 7 0 3 8 0 Record of Temporary Revisions 3 9 0 RTR 1 RTR 2 0 3 10 0 3 11 0 List of Effective Pages 3 12 0 LEP 1 3 3 13 0 LEP 2 3 3 14 0 LEP 3 LEP 4 3 3 15 0 3
126. t the storm cell has totally attenuated the radar energy and the radar cannot show any additional targets WX or ground behind the cell The cell that produces a radar shadow is a very strong and dangerous cell It should be avoided by 20 miles WARNING DO NOT FLY INTO THE SHADOW BEHIND THE CELL Turbulence Probability The graph of turbulence probability is shown in figure 5 32 This graph shows the following e There is a 100 probability of light turbulence occurring in any area of rain e Alevel one storm all green has virtually no chance of containing severe or extreme turbulence but has between a 5 and 2096 chance that moderate turbulence exists e A level two storm one containing green and yellow returns has virtually no probability of extreme turbulence but has a 20 to 40 chance of moderate turbulence and up to a 596 chance of severe turbulence e Alevelthree storm green yellow and red radar returns has a 4096 to 85 chance of moderate turbulence a 5 to 10 chance of severe turbulence and a slight chance of extreme turbulence e A level four storm one with a magenta return has moderate turbulence a 1096 to 5096 chance of severe turbulence and a slight to 2596 chance of extreme turbulence WARNING THE AREAS OF TURBULENCE CAN NOT BE ASSOCIATED WITH THE MAXIMUM RAINFALL AREAS THE PROBABILITIES OF TURBULENCE ARE STATED FOR THE ENTIRE STORM AREA NOT JUST THE HEAVY RAINFALL AREAS Radar Facts A28 1146
127. tch 3 5 FP flight plan 3 6 FSBY forced standby 3 7 OFF 3 5 ON 3 6 SBY standby 3 5 TST test 3 7 GAIN 3 8 GMP ground mapping button or MAP 3 2 rainfall rate color coding 3 6 RANGE 3 9 RCT rain echo attenuation compensation technique REACT 3 3 SCT scan sector 3 9 TGT target 3 4 target alert characteristics 3 4 TILT 3 8 WX weather button 3 2 Index Index 8 A28 1146 111 REV2
128. tenance function lets the pilot or the line maintenance technician determine the major fault areas The fault data can be displayed in one of two ways selected at the time of installation TEXT FAULT A plain English text indicating the failure is placed in the test band FAULT CODE A fault code is displayed refer to the maintenance manual for an explanation The indicator or EFIS display indicates a fault as noted below Dedicated Radar Indicator A FAIL annunciation is shown at the top left corner of the test pattern It indicates that the built in test equipment BITE circuitry is detecting a malfunction The exact nature of the malfunction can be seen by selecting TEST Refer to Section 8 In Flight Troubleshooting EFIS MFD ND Faults are normally shown when test is selected NOTES 1 Some weather failures on EFIS are annunciated with an amber WX 2 Some EFIS installations can power up with an amber WX if weather radar is turned off 3 If the fault code option is selected they are shown with the FAIL annunciation e g FAIL 13 Normal Operation A28 1146 111 4 6 REV2 PRIMUS 660 Digital Weather Radar System 5 Radar Facts RADAR OPERATION The PRIMUS 660 Digital Weather Radar works on an echo principle The radar sends out short bursts of electromagnetic energy that travel through space as a radio wave When the traveling wave of energy strikes a target some of the energy reflects back t
129. that the ground returns stay somewhat constant during changes in aircraft orientations If not repeat the adjustment procedure After the trim adjustment feature is selected more than one adjustment can be made They are available in the sequence shown in table 7 2 and can be done in the sequence of first finishing one adjustment then proceeding to do the next by pushing the STAB button The in flight stabilization adjustment range is limited If you cannot achieve a satisfactory adjustment in flight a ground adjustment is required Proper radar stabilization depends on the accuracy and stability of the installed attitude source The procedures in tables 7 3 7 4 7 6 and 7 8 that instruct you to push the STAB button assume that you are using a controller rather than an indicator If you are using an indicator pulling the TILT knob out or pushing it in is equal to pushing the STAB button on a controller When you finish the in flight stabilization procedures the STAB can be OFF stab light on an additional push of the button is required to turn stab back on In Flight Adjustments A28 1146 111 7 2 REV2 PRIMUS 660 Digital Weather Radar System Level Fight Stabilization Check Follow the procedure in table 7 2 to determine if you need to perform the roll offset adjustment e meme 1 Trim the aircraft for straight and level flight in smooth clear air over level terrain at an altitude of at least
130. them A tornado is always suspected when a hook echo is seen A hook can form with no tornadoes and vice versa However when a bona fide hook is observed on a weather radar moderate or greater turbulence strong shifting surface winds and hail are often nearby and aircraft should avoid them There are many patterns on radar that resemble hook echoes but are not associated with severe weather Severe weather hook echoes last at least 5 minutes and are less than 25 miles in diameter The favored location for hook echoes is to the right rear of a large and strong cell however in rare cases tornadoes occur with hooks in other parts of the cell Radar Facts A28 1146 111 5 48 REV2 PRIMUS 660 Digital Weather Radar System AVOID V NOTCH BY 20 MILES A large isolated echo sometimes has the configuration that is shown in figure 5 41 This echo is called V notch or flying eagle although some imagination may be needed by the reader to see the eagle V notch echoes are formed by the wind pattern at the leading edge left front of the echo Thunderstorm echoes with V notches are often severe containing strong gusty winds hail or funnel clouds but not all V notches indicate severe weather Again severe weather is most likely at S in figure 5 41 echo movement AD 15561 R1 V Notch Echo Pendant Shape Figure 5 41 A28 1146 111 Radar Facts REV2 5 49 PRIMUS 660 Digital Weather Radar System AVOID PENDANT BY 20 MILES T
131. tially hazardous targets directly in front of the aircraft that are outside the selected range When a yellow warning is received the pilot should select longer ranges to view the questionable target Note that target alert is inactive within the selected range Selecting target alert forces the system to preset gain Target alert can be selected only in the WX or FP flight plan modes NOTE In order to activate the target alert warning the target must have the depth and range characteristics described in table Selected Range Minimum Target Target Range NM Depth NM NM 5 5 5 55 10 10 60 25 25 75 50 50 100 100 100 150 200 200 250 300 N A FP Flight Plan 5 55 Target Alert Characteristics Table 3 1 Operating Controls A28 1146 111 3 4 REV2 PRIMUS 660 Digital Weather Radar System s DISPLAY AREA See figure 3 3 and the associated text that explains the alphanumeric display T ARM GREEN TGT ALERT YELLOW INVERTED VIDEO i ET TARGET ALERT FAIL NOTE et REACT RCT RANGE RING MARKERS MODE 120 DEGREE SCAN SHOWN STBY FSBY m COLOR BAR WX WX CALIBRATED GAIN FLTPLN V A R WX VARIABLE GAIN GMAP GMAP CALIBRATED GAIN V A R CMAP VARIABLE GAIN NOTE MESSAGES ARE LISTED IN PRIORITY ORDER AD 51771 WI 650 660 Weather Radar Indicator Display Screen Features Figure 3 3 6 FUNCTION SWITCH A rotary switch is used to select the following f
132. to the previous message Push the STAB STB button to exit or to go to the next menu pitch offe Gb if he full stab trim mode is enabled in your installation Once set the roll compensation is stored in nonvolatile memory in the RTA It is remembered when the system is powered down In Flight Roll Offset Adjustment Procedure Table 7 3 In Flight Adjustments A28 1146 111 7 6 REV2 PRIMUS 660 Digital Weather Radar System Honeywell AD 51776 Roll Offset Adjustment Display Initial Figure 7 4 AD 51777 R1 Roll Offset Adjustment Display Final Figure 7 5 A28 1146 111 In Flight Adjustments REV2 7 7 PRIMUS 660 Digital Weather Radar System PITCH OFFSET ADJUSTMENT This in flight adjustment is made in straight and level flight when the ground returns do not follow the contours of the radar display range arcs The procedure is listed in table 7 4 e meme 1 If two controllers are installed one must be turned off If an indicator is used the procedure is the same as given Fly to an altitude of 10 000 feet AGL or greater Set range to 50 NM Adjust the tilt down until a solid band of ground returns are shown on the screen Then adjust the tilt until the green region of the ground returns start at about 40 NM Select STAB STB 4 times within 3 seconds The roll offset display is shown From the roll offset entry menu push the STAB STB button once more to bring up the pitch
133. ulence with them A 12 purpose A 3 related reading material A 3 Tilt management 5 5 tilt setting for minimal ground target display 5 8 12 inch radiator 5 8 18 inch radiator 5 9 Tornadoes A 4 Trim adjustments 7 1 Turbulence above storm tops A 11 and echo intensity on NWS radar WSR 57 A 11 below cloud base A 12 in relation to distance from storm core A 11 in relation to distance from the storm edge A 11 relationship between turbulence and altitude A 10 relationship between turbulence and reflectivity A 10 A28 1146 111 REV2 PRIMUS 660 Digital Weather Radar System Index cont versus distance from storm core 5 55 versus distance from storm edge 5 55 visual appearance of storm and associated turbulence with them A 12 Turbulence probability 5 34 turbulence levels from airman s information manual 5 36 24 hour exchange rental support centers 9 2 U Use of airborne radar A 13 V Variable gain control 5 30 Visual appearance of storm and associated turbulence with them A 12 WwW Wallowing wing walk and yaw error 5 19 Warranty 9 1 Weather avoidance 5 43 additional hazards 5 55 turbulence versus distance from storm core 5 55 turbulence versus distance from storm edge 5 55 configurations of individual echoes northern hemisphere 5 47 avoid all crescent shaped echoes by 20 miles 5 51 A28 1146 111 REV2 avoid hook echoes by 20 miles 5 47 av
134. unctions e OFF This position turns off the radar system e SBY Standby This position places the radar system in standby a ready state with the antenna scan stopped the transmitter inhibited and the display memory erased STBY in white is shown in the mode field If SBY is selected before the initial RTA warmup period is complete approximately 90 seconds the white WAIT legend is shown in the mode field When warmup is complete the system changes the mode field to SBY A28 1146 111 Operating Controls REV2 3 5 PRIMUS 660 Digital Weather Radar System e ON Places the system in the operational mode selected by the WX or MAP GMP button When WX is selected the system is fully operational and all internal parameters are set for enroute weather detection The alphanumerics are white and WX is shown in the mode field If ON is selected before the initial RTA warmup period is over approximately 90 seconds the white WAIT legend is displayed in the mode field In wait mode the transmitter and antenna scan are inhibited and the display memory is erased When the warmup is complete the system automatically switches to the WX or MAP mode as selected The system in preset gain with WX selected is calibrated as listed in table 3 2 Rainfall Rate Color Rainfall Rate Color Coding Table 3 2 e FP Flight Plan The FP position puts the radar system in the flight plan mode that clears the screen of ra
135. urbulence are encountered approximately once for each 10 nautical miles of thunderstorm flight TURBULENCE IN RELATION TO DISTANCE FROM STORM CORE NSSL data indicates that the frequency and severity of turbulence encounters decrease slowly with distance from storm cores Significantly the data indicates that within 20 miles from the center of severe storm cores moderate to severe turbulence is encountered at any altitude about one fifth as often as in the cores of Level 3 or greater thunderstorms Further the data indicates that moderate turbulence is encountered at any altitude up to 10 miles from the center of level 2 thunderstorms SEVERE TURBULENCE IS OFTEN FOUND IN TENUOUS ANVIL CLOUDS 15 TO 20 MILES DOWNWIND FROM SEVERE STORM CORES Our findings agree with meteorological reasoning that THE STORM CLOUD IS ONLY THE VISIBLE PORTION OF A TURBULENT SYSTEM WHOSE UPDRAFTS AND DOWN DRAFTS OFTEN EXTEND OUTSIDE OF THE STORM PROPER TURBULENCE IN RELATION TO DISTANCE FROM THE STORM EDGE THE CLEAR AIR ON THE INFLOW SIDE OF A STORM IS A PLACE WHERE SEVERE TURBULENCE OCCURS At the edge of a cloud the mixing of cloudy and clear air often produces strong temperature gradients associated with rapid variation of vertical velocity Tornado activity is found in a wide range of spacial relationships to the strong echoes with which they are commonly associated but many of the most intense and enduring tornadoes occur on the south to west edges of seve
136. ure 5 6 40 000 ANTENNA ADJUSTED m FOR 2 8 UPTILT iJ 30 000 z o z 20 000 a 10 000 ea 5 000 3 000 FT 0 0 10 20 30 40 50 60 70 80 RANGE NAUTICAL MILES AD54258 Radar Beam Illumination Low Altitude 18 Inch Radiator Figure 5 7 Radar Facts A28 1146 111 5 6 REV2 PRIMUS 660 Digital Weather Radar System Tables 5 1 and 5 2 give the approximate tilt settings that the ground targets begin to be displayed on the image periphery for 12 and 18 inch radiators The range that the ground targets can be observed is affected by the curvature of the earth the distance from the aircraft to the horizon and altitude above the ground As the tilt control is rotated downward ground targets first appear on the display at less than maximum range To find the ideal tilt angle after the aircraft is airborne adjust the TILT control so that groundclutter does not interfere with viewing of weather targets Usually this can be done by tilting the antenna downward in 1 increments until ground targets begin to appear at the display periphery Ground returns can be distinguished from strong storm cells by watching for closer ground targets with each small downward increment of tilt The more the downward tilt the closer the ground targets that are displayed When ground targets are displayed move the tilt angle upward in 1 increments until the ground targets begin to disappear Proper tilt adjustment is a pilot judgment but typically the be
137. vere weather avoidance procedures 5 43 weather display calibration 5 28 Radiation Safety Precautions A 1 Radome 5 42 Rain echo attenuation compensation technique REACT 5 31 related functions 5 31 attenuation compensation 5 31 cyan REACT field 5 31 Recommended radiation safety precautions for ground operation of airborne weather radar A 1 background A 1 cancellation A 1 precautions A 2 body damage A 2 combustible materials A 3 general A 2 purpose A 1 A28 1146 111 REV2 related reading material A 1 Reflectivity A 10 relationship between turbulence and reflectivity A 10 Relationship between turbulence and altitude A 10 Remote mounted equipment 2 4 Roll gain adjustment 7 11 adjustment procedure 7 11 Roll offset adjustment 7 5 adjustment procedure 7 5 Roll stabilization check 7 9 while turning check procedure 7 9 S Shadowing 5 34 Spotting hail 5 37 Squall lines A 4 Stabilization 5 15 accelerative error 5 15 antenna mounting error 5 16 level flight stabilization check 5 17 dynamic error 5 15 pitch gain error 5 22 pitch stabilization check 5 22 roll gain error 5 19 roll stabilization while turning check 5 19 wallowing wing walk and yaw error 5 19 Stabilization check 7 9 Pitch 7 12 Check procedure 7 12 Roll 7 9 While turning check procedure 7 9 Support centers 9 2 customer support centers 9 2 North America 9 2 Rest of the World 9 3 24 hou
138. ves a single slice from the middle of the loaf and places this slice flat upon the table Looking at the slice of bread from directly above a cross section of the loaf can be seen in its broadest dimension In the same manner the radar beam literally slices out a horizontal cross section of the storm and displays it as though the viewer was looking at it from above as shown in figure 5 2 The height of the slice selected for display depends upon the altitude and also upon the upward or downward TILT adjustment made to the antenna Radar Facts A28 1146 111 REV2 PRIMUS 660 Digital Weather Radar System ANTENNA THUNDERSTORM TRANSMITTER INDICATOR THUNDERSTORM AD 17716 R2 Antenna Beam Slicing Out Cross Section of Storm During Horizontal Scan Figure 5 2 Weather radar can occasionally detect other aircraft but it is not designed for this purpose and should never be considered a collision avoidance device Nor is weather radar specifically designed as a navigational aid but it can be used for ground mapping by tilting the antenna downward Selecting the GMAP mode enhances returns from ground targets A28 1146 111 Radar Facts 5 3 REV2 PRIMUS 660 Digital Weather Radar System When the antenna is tilted downward for ground mapping two phenomena can occur that can confuse the pilot The first is called The Great Plains Quadrant Effect that is seen most often when flying over the great plains
139. w hours of darkness TORNADOES e The most violent thunderstorms draw into their cloud bases with great vigor If the incoming air has any initial rotating motion it often forms an extremely concentrated vortex from the surface well into the cloud Meteorologists have estimated that wind in such a vortex can exceed 200 knots pressure inside the vortex is quite low The strong winds gather dust and debris and the low pressure generates a funnel shaped cloud extending downward from the cumulonimbus base If the cloud does not reach the surface it is a funnel cloud if it touches the land surface it is a tornado e Tornadoes occur with both isolated and squall line thunderstorms Reports for forecasts of tornadoes indicate that atmospheric conditions are favorable for violent turbulence An aircraft entering a tornado vortex is almost certain to suffer structural damage Since the vortex extends well into the cloud any pilot inadvertently caught on instruments in a severe thunderstorm could encounter a hidden vortex e Families of tornadoes have been observed as appendages of the main cloud extending several miles outward from the area of lightning and precipitation Thus any cloud connected to a severe thunderstorm carries a threat of violence Federal Aviation Administration FAA Advisory Circulars A28 1146 111 REV2 PRIMUS 660 Digital Weather Radar System TURBULENCE e Potentially hazardous turbulence is present in all thu
140. well has incorporated attenuation compensation that adjusts the receiver gain by an amount equal to the amount of attenuation That is the greater the amount of attenuation the higher the receiver gain and thus the more sensitive the receiver Attenuation compensation continuously calibrates the display of weather targets regardless of the amount of attenuation With attenuation compensation weather target calibration is maintained throughout the entire range of a single cell The cell behind a cell remains properly calibrated making proper calibration of weather targets at long ranges possible e Cyan REACT Field From the description of attenuation it can be seen that high levels of attenuation caused by cells with heavy rainfall causes the attenuation compensation circuitry to increase the receiver gain at a fast rate Low levels of attenuation caused by cells with low rainfall rates cause the receiver gain to increase at a slower rate A28 1146 111 Radar Facts REV2 5 31 PRIMUS 660 Digital Weather Radar System The receiver gain is adjusted to maintain target calibration Since there is a maximum limit to receiver gain strong targets high attenuation levels cause the receiver to reach its maximum gain value in a short time short range Weak or no targets low attenuation levels cause the receiver to reach its maximum gain value in a longer time longer range Once the receiver reaches its maximum gain value weather t
141. wn in figure 5 29 e Turbulence results when two air masses at different temperatures and or pressures meet e This meeting can form a thunderstorm e The thunderstorm produces rain e The radar displays rain thus revealing the turbulence e In the thunderstorm s cumulus stage echoes appear on the display and grow progressively larger and sharper The antenna can be tilted up and down in small increments to maximize the echo pattern e n the thunderstorm s mature stage radar echoes are sharp and clear Hail occurs most frequently early in this stage e Inthe thunderstorm s dissipating stage the rain area is largest and shows best with a slight downward antenna tilt Radar can be used to look inside the precipitation area to spot zones of present and developing turbulence Some knowledge of meteorology is required to identify these areas as being turbulent The most important fact is that the areas of maximum turbulence occur where the most abrupt changes from light or no rain to heavy rain occur The term applied to this change in rate is rain gradient The greater the change in rainfall rate the steeper the rain gradient The steeper the rain gradient the greater the accompanying turbulence More important however is another fact storm cells are not static or stable but are in a constant state of change While a single thunderstorm seldom lasts more than an hour a squall line shown in figure 5 30 can contain many such storm
142. xes of tornadoes are not infallible guides The appearance of a hook warns the pilot to stay away but just because the tornado cannot be seen is no assurance that there is no tornado present Expect severe turbulence up to 20 NM away from severe storms this turbulence often has a well defined radar echo boundary This distance decreases somewhat with weaker storms that display less well defined echo boundaries Appendix A Federal Aviation Administration FAA Advisory Circulars of this manual contains several advisory circulars It is recommended that you become familiar with them A28 1146 111 Radar Facts REV2 5 55 PRIMUS 660 Digital Weather Radar System GROUND MAPPING Ground mapping operation is selected with the GMAP button An example of ground map display is shown in figure 5 47 Turn the TILT control down until the desired amount of terrain is displayed The degree of down tilt depends upon the type of terrain aircraft altitude and selected range Tables 5 10 and 5 11 show tilt settings for maximal ground target display at selected ranges MOST REFLECTIVE LEAST REFLECTIVE MODERATELY REFLECTIVE spy ON rp OFF IST PULL FOR VAR MA S AD 51782 R1 Ground Mapping Display Figure 5 47 For the low ranges 5 10 25 and 50 NM the transmitter pulsewidth is narrowed and the receiver bandwidth is widened to enhance the identification of small targets In addition the receiver S
143. y Circulars A28 1146 111 A 12 REV2 PRIMUS 660 Digital Weather Radar System MODIFICATION OF CRITERIA WHEN SEVERE STORMS AND RAPID DEVELOPMENT ARE EVIDENT During severe storm situations radar echo intensities may grow by a factor of ten each minute and cloud tops by 7 000 feet per minute THEREFORE NO FLIGHTPATH THROUGH A FIELD OF STRONG OR VERY STRONG STORMS SEPARATED BY 20 30 MILES OR LESS MAY BE CONSIDERED TO REMAIN FREE FROM SEVERE TURBULENCE EXTRAPOLATION TO DIFFERENT CLIMBS General comment Severe storms are associated with an atmospheric stratification marked by large values of moisture in low levels relative dryness in middle levels and strong wind shear It is well known that this stratification of moisture permits excessive magnitudes of convective instability to exist for an indefinite period until rapid overturning of air is triggered by a suitable disturbance Regions of the atmosphere which are either very dry or very moist throughout substantial depths cannot harbor great convective instability Rather a more nearly neutral thermal stratification is maintained partially through a process of regular atmospheric overturning e Desert Areas In desert areas storms should be avoided on the same basis as described in the above paragraphs While nonstorm turbulence may in general be expected more frequently over desert areas during daylight hours than elsewhere THE SAME TURBULENCE CONSIDERATIONS PREVAIL IN THE VIC

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