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airborne equipment of satellite navigation – appendix i

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1. word structure Bit No Information content Bit coding 1 8 Address 034 00 011 100 9 10 Identifier 00 all 01 Nel 10 Ne2 11 not used 11 Operability of antenna feeder 1 AFD failure device AFD 0 AFD operability 12 Reserved Zero 13 14 Operating mode 00 VOR 01 ILS 11 CII 50 15 18 Hundredths of MHz 19 22 Tenths of MHz 23 26 Ones of MHz 27 29 Tens of MHz 30 31 State matrix In accordance with Table E 1 5 32 Parity 0 if sum of ones is odd number 1 if sum of ones is even number Note All frequencies have ones in MHz hundred values 034 50 00 Appendix E Page 41 Dec 17 2009 4312 02 USER S MANUAL Table E 2 9 Magnetic azimuth word structure Bit No Information content Bit coding 1 8 Address 2228 10 010 010 9 10 Source identifier 00 all 01 1 10 2 11 not used 11 13 Fly by character of marker beacon 100 far 010 middle 001 close 14 16 Reserved 17 28 Magnetic azimuth 12 bits Range X180 m s bit 28 90 Negative values are transmitted additional code in 29 Sign 0 from 0 to 180 1 from 180 to 360 30 31 State matrix In accordance with Table E 1 5 32 Parity flag Table E 2 10 number word structure Bit No Information content Bit coding 1 8 Address 205s
2. Bit No Information content Bit coding 1 8 Address 304 11 000 100 305 11 000 101 9 15 Symbol 1 4 16 22 Symbol 2 5 23 29 Symbol 3 6 30 31 State matrix In accordance with Table E 1 5 32 Parity 0 if sum of 1 is odd number 1 if sum of 1 is even number Table E 1 48 Navigation point latitude Navigation point longitude word structure Bit No Information content Bit coding 1 8 Address 306s 11 000 110 307 11000111 9 28 Significant part is Range 180 10 bits m s bit 28 90 Negative values are transmitted in additional code 29 Sign 1 South West 0 North East 30 31 State matrix In accordance with Table E 1 5 32 Parity 0 if sum of 1 is odd number 1 if sum of 1 is even number Table 1 49 Current latitude Current longitude word structure Bit No Information content Bit coding 1 8 Address 310s 11 001 000 311 11001001 9 28 Significant part is Range 180 20 bits m s bit 28 90 Negative values are transmitted in additional code 29 Sign 0 North East 1 South West 30 31 State matrix In accordance with Table E 1 5 32 Parity 0 if sum of ones is odd number 1 if sum of ones is even number 034 50 00 Appendix E Page 31 Dec 17 2009 Table E 1 50 Ground speed word structure CH 43 12
3. Bit No Information content Bit coding 1 8 Address 062s 01 110 010 9 10 Identifier 00 all 01 71 10 2 11 not used 11 13 Reserved Zero 14 28 Significant part is Range 128 NM 15 bits m s bit 64 NM Negative values are transmitted in additional code 29 Sign 0 30 31 State matrix In accordance with Table E 1 5 32 Parity 0 if sum of ones is odd number if sum of ones is even number Table E 1 12 Remaining distance to WPT along DT word structure Bit No Information content Bit coding 1 8 Address 063 00 110 011 9 10 Identifier 00 all 01 1 10 2 11 not used 11 13 Reserved Zero 14 28 Significant part is Range 4096 NM 15 bits m s bit 28 2048 NM 29 Sign Zero 30 31 State matrix In accordance with Table E 1 5 32 Parity 0 if sum of ones is odd number if sum of ones is even number 034 50 00 Appendix E Page 11 Dec 17 2009 4312 02 USER S MANUAL Table E 1 13 Data record header word structure Bit No Information content Bit coding 1 8 Address 074 00 111 100 9 15 Total number of Max 127 records 16 20 Reserved Zero Updating of 1 yes 21 background 0 no information unit 22 29 Reserved Zero 30 31 Status matrix In accordance with Table E 1 5 22 Parity 0 if sum of ones is odd number if sum of ones is
4. Bit No Function Bit status 1 8 Address 147 01 100 111 00 all 01 1 9 10 Identifier 10 92 11 not used 11 16 Reserved Zero Range 180 17 28 Significant part is m s bit 28 90 12 bits Negative values are transmitted in additional code 0 from 0 to 180 di mee 1 from 180 to 360 30 31 Status matrix In accordance with Table E 1 6 32 Parity 0 if sum of 1 is odd number 1 if sum of 1 is even number 034 50 00 Appendix E Page 23 Dec 17 2009 4312 02 USER S MANUAL Table E 1 35 Current Greenwich time word structure Bit No Information content Bit coding 1 8 Address 150 01 101 000 00 all 01 1 9 10 Identifier 10 2 11 not used 11 Reserved Zero 12 17 Seconds Significant part is Range 60 s 6 bits m s bit 17 30s 18 23 Minutes Significant part is Range 60 min 6 bits m s bit 23 30 min 24 28 Hours Significant part is Range 24 hours 5 bits m s bit 28 12 hours 29 Reserved Zero 30 31 State matrix In accordance with Table E 1 5 32 Parity 0 if sum of ones is odd number 1 if sum of ones is even number Table E 1 36 Vertical speed word structure Bit No Information content Bit coding 1 8 Address 165 01 110 101 00 all 01 1 9 10 Identifier 10 2 11 not used 11 13 Re
5. Bit 31 30 Value 0 0 Plus North East right to above 0 1 No calculated data 1 0 Functional test 1 1 Minus south west left from under Table E 1 7 State matrix Discr Si 30 Value 0 0 Normal operation 0 1 No calculated data 1 0 Functional test 034 50 00 Appendix E Page 8 Dec 17 2009 4312 02 USER S MANUAL 0 1 Not used Table E 1 8 Desired track angle word structure Bit No Information content Bit coding 1 8 Address 024 00 010 100 9 10 Source identifier 00 all sets 10 set 1 01 set 72 11 set 3 11 18 Reserved Zero 19 22 Ones of degrees Desired 23 26 Tens of degrees track 27 29 Hundreds of degrees angle 30 31 State matrix In accordance with Table E 1 5 32 Parity 0 if sum of ones is odd number 1 if sum of ones is even number Table E 1 9 Tuning frequency of navigation and landing system command word word structure Bit No Information content Bit coding 1 8 Address 034 00 011 100 9 10 Source identifier 00 all sets 10 set 1 01 set 2 11 set 3 11 Operability of AFD 1 failure 0 AFD operability 12 Reserved Zero 13 14 Mode of operation 00 VOR 01 ILS 11 CII 50 15 18 Hundredths of MHz 19 22 Tenths of MHz 23
6. Bit No Information content Bit coding 1 8 Address 351 11 101 001 9 10 Identifier 00 all 01 1 10 2 11 not used 11 28 Significant part is Range 32768 NM 18 bits m s bit 28 16384 NM 29 Sign Zero 30 31 State matrix In accordance with Table E 1 5 32 Parity 0 if sum of ones is odd number 1 if sum of ones is even number 034 50 00 Appendix E Page 35 Dec 17 2009 4312 02 USER S MANUAL Table E 1 59 Time to go to destination WPT word structure Bit No Information content Bit coding 1 8 Address 352g 11 101 010 9 10 Identifier 00 all 01 1 10 2 11 not used 11 16 Reserved Zero 17 28 Significant part is Range 4096 min 12 bits m s bit 2048 min 29 Sign Zero 30 31 State matrix In accordance with Table E 1 5 32 Parity 0 if sum of ones is odd number if sum of ones is even number E 2 Information received by the equipment according to ARINC 429 Words received by the equipment according to ARINC 429 are given in Table E 2 1 Word structure received by the equipment according to ARINC 429 is given in Tables E 2 2 E 2 11 State matrices of words putting out and received by the equipment are given in Tables E 1 5 E 1 7 Table E 2 1 Parameter Ord Fusing our Table number address device Beacon adjustment frequency 035 Range
7. Contact Circuit Purpose 1 27 OUT Supply output voltage plus 27 V 2 Reserved 3 27_ Supply input voltage minus 27 V 4 27 OUT Supply input voltage plus 27 V 5 ON Equipment ON signal GND ON break OFF 6 27 OUT Supply input voltage minus 27 V 7 Reserved 8 GND Common Equipment power ON signal 9 ENCLOSURE UPS enclosure 10 ENCLOSURE UPS enclosure Two green LEDs for input and output voltage availability indication are installed on UPS enclosure UPS has 4 holes for its mounting UPS shall be earthed through the earthing rod UPS dimensions are given in Appendix D 034 50 00 Page 34 Dec 17 2009 4312 02 USER S MANUAL Installation Kit Installation kit 468911 020 02 is used for the equipment unit mounting on the object and for inter unit connections Installation kit components are listed in Table 11 Table 11 Name Designation Number pcs Note Bracket 301532 003 4 0 LNA SSF Enclosure 305154 001 1 RICU Washer IIKAH 754114 007 1 101 Screw B2 M5 6gx20 21 17473 80 4 101 5 6 21 5916 70 4 101 Spacer 5 30X13 6402 70 4 ATOIII Spacer 5 21 11371 78 8 101 143 008 000 3 LNA SSF Angle plug R 143 156 000 RADIALL 1 ATOIII Plug CHII 23 10 18B 6 B
8. Table E 1 16 Desired heading Drift angle word structure Bit No Information content Bit coding 1 8 Address 100s 01 000 000 321 11010001 9 10 Identifier 00 all 01 1 10 2 11 not used 11 16 Reserved Zero Range 180 17 28 Significant part is m s bit 28 90 12 bits Negative values are transmitted in additional code 0 from 0 to 180 di Sign 1 from 180 to 360 30 31 State matrix In accordance with Table E 1 5 32 Parity 0 if sum of ones is odd number if sum of ones is even number 034 50 00 Appendix E Page 13 Dec 17 2009 4312 02 USER S MANUAL Table E 1 17 word structure Bit No Information content Bit coding 1 8 Address 113 01 001 011 9 29 Identifier 00 all 01 1 10 2 11 not used 11 13 Reserved Zero 14 28 Significant part is Range 1024 15 bits m s bit 28 512 29 Reserved Zero 30 31 State matrix In accordance with Table E 1 5 32 Parity 0 if sum of ones is odd number 1 if sum of ones is even number Table E 1 18 V DOP word structure Bit No Information content Bit coding 1 8 Address 1028 01 000 010 9 10 Identifier 00 all 01 1 10 2 11 not used 11 13 Reserved Zero 14 28 Significant part is Range 1024 15 bits m s bit 28 512 29 Reserved Z
9. 467855 039 0 364 241 RADIALL I e0 364 241 RADIALL 0 364 241 0 364 241 0 364 241 0 364 241 0 364 241 4312 02 USER S MANUAL AIRBORNE EQUIPMENT OF SATELLITE NAVIGATION APPENDIX B reference RICU Outline Drawing outline drawing is shown in fig B 1 before serial C03908020 and before serial Ne 1516030 inclusive RICU outline drawing is shown in fig B 2 since serial Ne C03910021 gt 2 690 2 Plug 1 41 30 1 TNC 143324000 Earthing Plug 1 41 30 1 6 RADIALL rod 034 50 00 Figure B 1 page 1 of 2 Appendix B Page 1 Dec 17 2009 4312 02 USER S MANUAL 1 B 1 CR Seal Figure B 1 page 2 of 2 034 50 00 Appendix B Page 2 Dec 17 2009 4312 02 USER S MANUAL Plug 1 41 30 1 Plug 1 41 30 1 Sealing mark point Ground stud Plug 1 41 30 1 6 TNC R143324000 RADIALL Figure B 2 034 50 00 Appendix B Page 3 4 Dec 17 2009 4312 02 USER S MANUAL AIRBORNE EQUIPMENT OF SATELLITE NAVIGATION APPENDIX C reference 101 Antenna and LNA SSF Outline Drawing 101 antenna outline drawing is shown in fig C 1 LNA SSF outline drawing is shown in
10. 4312 02 USER S MANUAL Adjustment and Testing The equipment shall be capable during the units 101 antenna LNA SSF RICU UPS replacement with no supplementary adjustment This section describes the equipment testing technique and sequence Works for the equipment workability check up and stages of these operation are given in Table 202 Table 202 Operation Operation Stage FS At the first installation in the aircraft before each flight at periodical maintenance after 600 and de Operability extended testing Item MS 6000 operation hours at calendar maintenance 034 50 00b after 12 and 48 months and after repair Tra At the first installation in the aircraft at periodical T FS 4 Test of navigation task maintenance after 600 and Item MS solution 6000 operation hours at calendar maintenance 034 50 00 after 12 and 48 months and after repair ud Altimeter and heading system communications test s RICUS bas At the first installation in the aircraft before each Communications test with UN FS 5 Nt flight at periodical maintenance after 600 and MFD Communications test Item MS nM 6000 operation hours at calendar maintenance with airborne range finder 034 50 00c OR after 12 and 48 months and after repair Communications test with navigation and landing system Shaping test or huu At the first installation in the aircraft at periodical panel control signals F
11. unlock and disconnect the high frequency cable from 101 antenna install process cover on 101 antenna connector unscrew and remove 4 screws and 4 nuts remove 101 antenna from its site together with the gasket TVONVW 6 50 600c LI 99d 902 Sed 000 lt 0 Flow Sheet 1 for MS item 034 50 004 Continuation Operation and Technical Requirements TR Works performed with TR deviations Contr ol 3 LNA SSF removal For LNA SSF removal perform the operations as follows unlock and disconnect cables from LNA SSF install process covers on LNA SSF connectors disconnect the amplifier holder remove LNA SSF from its location 4 UPS removal For UPS removal perform the operations as follows disconnect earthing rod from the aircraft common earthing bar disconnect cables from UPS X1 X2 connectors install process covers on UPS connectors disconnect UPS holder remove UPS from its location Note Units shall not be obligatory removed from their sites during maintenance under condition of accessibility of high frequency pins and sockets connectors condition test without their removal Instruments Tools and accessories Expendables Screwdriver 7810 0977 X9 Screwdriver 7810 0982 X9 Spanner 7811 0006 9 TVONVW 6 50 cO CIEP HO 600 11 9d LOZ 998 4 007057760 Flow Sheet 2 fo
12. 364 241 1 UPS Socket CHI 23 10 18P 2 B 364 241 1 process connective Socket CHI 23 10 18P 6 B 364 241 TY 2 RICU UPS Socket CHI 23 41 30P 6 B 364 241 TY 1 RICU Socket CHI 23 41 30P 6 a B 364 241 TY 1 RICU Socket CHI 23 41 30P 6 6 B TEO 364 241 TY 1 RICU Cap 18 6 364 038 2 UPS process connective 034 50 00 Page 35 Dec 17 2009 4312 02 USER S MANUAL Table 11 continuation Name Designation Number pcs Note Wire 0 3 12X18H9T 18143 72 1 1 LNA SSF PANDUIT tube RICU 101 HSTTA 50 48 5 0 15 1 LNA SSF Tip 2 2 4 2 20 5 02 OCT 92 0528 70 2 RICU UPS 034 50 00 Page 36 Dec 17 2009 4312 02 USER S MANUAL Operation Equipment Units Installation and Mounting on Aircraft General Having received the equipment from storehouse or from manufacturer check up seals and package No mechanical damage or choke marks caused by the transportation provisions violation are acceptable after opening the packing check up all components availability consult Manual check up the equipment units for mechanical damages check up seals availability on RICU A101II antenna UPS take off process caps from the units connectors and examine plugs and sockets of HF connectors in accordance with FS 11 of this Manual If any damages are detected inform im
13. World Geodetic System 1984 Waypoint 034 50 00 Abbreviation List Page 3 Dec 17 2009 4312 02 USER S MANUAL Definitions Used For Equipment Operation Description Airway corridor in the airspace limited by altitude and width purposed for aircraft flights provided with intermediate airfield and equipped with radio navigation facilities air traffic monitoring and control facilities Airspeed airplane movement velocity relating the air Pop up part of the window or the form page indicated at MENU button pressing when parameters that suppose some specified values are being inserted and when confirmation or cancellation of any function IS required Desired Track projection of the aircraft assigned flight path onto the Earth horizontal surface Route desired track specified by the waypoints through which the airplane shall fly Airplane position point on the Earth surface where the airplane mass center is being projected at the present moment Viewpoint serial character cells range in the form line for one parameter or one function indication Track angle desired or true angle between the northwards direction taken as a reference point and a track desired or true Airplane Ground Speed velocity of travel of airplane mass center projection point on the Earth surface directed at a tangent to the track Form Page part of the form indicated simultaneously on the RICU display
14. e 27er our M f case ON OFF IN H T and TAWS s ON OFF_OUT AR 1 OUT Dr 7 2 To DME 27 BBP AR A2 QUT 710 CASE GND T AR ASOUT 1 ommon bar CASE 034 50 00 Appendix A Pagel Dec 17 2009 4312 02 USER S MANUAL 4 2 Plug 1 41 30 1 0 364 241 To lighting x2 Circuit RK0 OUT RK1 OUT GND GND RK2 OUT RK3 OUT 7 RK4_OUT RK5_OUT ARM1_RX ARM1_TX RK6_OUT RK7_OUT RK8_OUT 0 2 v x a OUT Z Sima 7 ta To ACS Pen uer ao H Lighting adjusting Al 101 Antenna A2 Uninterruptible power supply A3 LNA SSF Amplifier A4 indicator and control unit CHI 23 10 18P 6 B socket 2 143 156 000 TNC angle plug X3 23 10 18B 6 B plug X4 X6 X7 R 143 008 000 TNC plug X5 23 10 18P 6 B socket X8 23 41 30P 6 a B socket X9 23 10 18 2 socket 10 CHI 23 41 30P 6 B socket X11 CHL 23 41 30P 6 6 B socket Included into 468911 020 02 IK Figure 1 page 2 of 2 034 50 00 Appendix A Page 2 Dec 17 2009 Plug 1 41 30 1 A4 3 0 364 241 TY X11 1 From IRU From VOR AR_A7_IN 24 AR B7 IN Strut compression Air GND short circuit Earth breakage IIKAH 464656 005 436434 006 AIIMA 434816 034
15. In the absence of NT solution from GNSS sensor since power up time in one of the RICUs it is necessary to set coordinates in this RICU which were received by other RICU as initial ones AUX3 DATA CROSS BPIU 034 50 00 Page 6 Dec 17 2009 4312 02 USER S MANUAL To synchronize operation of both RICUs in case when a route is activated in one RICU and other RICU is turned off then at power up other RICU and after receiving valid coordinates it is necessary to reactivate an active leg of route in earlier operating RICU or activate a flight in DIRECT TO mode WARNING IN THE CASE OF OPERATION WITH TWO SETS OF EQUIPMENT NDB SHALL BE IDENTICAL Dimension of navigation parameters indication Dimension of the navigation parameters identified on RICU display is as follows geographical coordinates degrees minutes hundredth of a minute DT deviation kilometers NM The indication resolution of desired track error is 0 01 km NM at distance up to 9 99 km NM and it is 0 1 km NM at distance from 10 to 99 9 km NM distance kilometers NM The indication resolution of remaining distance value is 0 1 km NM at distance up to 999 9 km NM and it is 1 km NM at distance from 1000 to 99999 km NM altitude meters feet ground speed kilometers per hour knots path angle and ACA correction degrees current UTC time hours minutes seconds flight time to WP hours and minutes if
16. Operating mode selection depends on availability and quality of the navigation satellites signals information from course and vertical systems ASS VOR DME commands from the ground extended control Selected mode is indicated in the output information and on RICU Self control mode shall be set as soon as the power supply is on or if there was no power for more than 80 ms In Self control mode RAM and ROM testing control module and processor interface test are performed Search mode shall be set when Self control mode is successfully completed as well as if signals less than from four NSC are available As soon as Search mode is terminated the navigation mode of the equipment operation is set SNS navigation mode is set if signals from at least four NSC of one SNS are received 034 50 00 Page 48 Dec 17 2009 4312 02 USER S MANUAL SNS SBAS navigation mode is set at reception of signals from six NSC of SNS GPS at least signals from SBAS satellites WAAS EGNOS MSAS ASS Navigation mode shall be set if information of heading and airspeed from AES is available and if signals from less than 4 navigation satellites of the same system are available in the case if the navigation parameters evaluation precision in ASS navigation mode is higher than in the previous mode DME DME navigation mode is set when data are available from airborne radio range finder on the di
17. RK11_OUT Selected roll availability Check up Selected roll availability signal availability 27 V on contact 19 of connector X2 set the highlighting in GAMMA field install the verified value of Selected roll signal Selected roll has value 15 on default press ENT check up the accuracy of Selected roll shaping on the contact 35 of connector X2 Voltage shall meet the Selected roll set value in GAMMA field at a rate of 0 333 V per 1 degree positive value the right turn Voltage of 5 V meets the list of 15 degrees set the highlighting in RK OUT field set symbol 0 in the character cell corresponding to one time command RK11 OUT Selected roll availability Check up interruption of Selected roll availability output signal TVONVW 6 50 600c LI 0 c 6cc 03ed 00 0 70 Flow Sheet 6 Item MS 034 50 00k Continuation Works performed with TR Contr Operation and Technical Requirements TR deviations ol 4 Z signal forming test deviation from DT in RK OUT field set the symbol 1 in character location which meets RK10 OUT one time command Availability 7 Check for Availability Z signal voltage 27V on pin 16 of the connector X2 set the highlighting in XTK field set a testable Z signal value by default Z signal value is 2 5 km press ENT button check a validity of Z signal
18. calculation aircraft average speed SPEED boundary angle of list BANK gradient of altitude change GRAD boundary angle of list en MAX 034 50 00 Page 46 Dec 17 2009 4312 02 USER S MANUAL roll angle rate of rise slope of a signal Selected roll average speed in the terminal sides of departure arrival and en route used for RAIM function forecast calculation AVERAGE SPEED Figure 15 All parameters on Figure 15 are the nonvolatile parameters Factory settings of possible air sides AIRSPAGE and navigation references NAVAID draw on pages NAVI and NA V2 given on Figure 16 are the nonvolatile parameters AIRSPACE NAVAID Figure 16 034 50 00 Page 47 Dec 17 2009 4312 02 USER S MANUAL Equipment Operating Modes General Information The equipment is supplied with both automatic and manual on operator s discretion selection of the equipment operating modes as follows Self control Search navigation modes SNS navigation SNS SBAS navigation ASS navigation DME DME navigation VOR DME navigation Autonomous Control Ground Extended Control Note Do not use SNS SBAS navigation operating mode for the equipment As soon as the equipment operation in this mode is available you will receive the corresponding notification concerning this mode inclusion into Manual
19. wes wv Mounting panel 2M4 6gx25 21 screw 10337 80 4 pcs Figure H 1 page 1 of 5 034 50 00 Appendix H Page 1 Dec 17 2009 4312 02 USER S MANUAL 1 19 4 40 0 1 160 0 1 305154 001 40 0 1 Q 5 8792 enclosure 10 hol 3 BG 46 max 201 max 2 4 301532 003 bracket 0 3 12X18H9T wire 18143 72 143 008 000 plug RADIALL Figure H 1 page 2 of 5 034 50 00 Appendix H Page 2 Dec 17 2009 4312 02 USER S MANUAL B 2 C 1 41 30 plu 1 41 30 1 plug 364 241 364 241 1 41 30 6 plug 1 10 18 1 plug 364 241 TNC R 143 324 000 socket RADIALL 2 2 4 2 20 5 02 tip Enclosure mounting surface OCT 92 0528 70 305154 001 CHI 23 41 30P 6 a B socket CHI 23 10 18P 6 B socket 364 241 364 241 eee E Se A UU Lu L NW oG S M mT TTT SUT UNNA L 3 O T 7 9 Be CHI 23 41 30P 6 6 B socket CHI 23 41 30P 6 B socket 364 241 364 241 Figure H 1 page 3 of 5 034 50 00 Appendix H Page 3 Dec 17 2009 4312 02 U
20. mode Reception test of navigation parameters is WS E Meet TE Inspection and FS 9 Inspection of 101 Antenna radio transparent radome and unit appearance uq on emite deer Ere dA IUSTI FS 10 Check of nut tightening and locking in connectors Earthing quality er MEL atuq FS 11 Check of high frequency connector pins and FS 12 Replacement of detachable device for navigation database storage Cleaning and M NE RS SeEVIGHIIS Su dress ul qp edere Dri Storage TESDSDOFCUHOIE os Corin aH SORTA GU IVA RTI Pea E eda pou Appendix A Connection Appendix B RICU Outline Appendix A101II Antenna and LNA SSF Outline Drawing Appendix D UPS Outline Appendix E Information output and receiving according to 429 Appendix F A101II Antenna LNA SSF and process connector installation in Gan vsu etum Cav ae oed a ua Appendix Enclosure mounting
21. 2 2 4 ERR in indication field of ANT ERR in test results indication field in one or more lines RAM TEST 1PPS TEST N FLASH TEST CONNECT GNSS CONNECT EXT CF CONNECT INP CF XILINX CF TEST GNSS TEST ANT GNSS TEST DUAL PORT RAM TEST Replace RICU Disconnect high frequency cable from RICU Chek up cable no SC between central core and braiding GNSS TEST line Examine high frequency cable for any mechanical damages Cable damaged Cable OK Disconnect high frequency cable from LNA SSF and check up voltage availability on high frequency cable connector LNA SSF supply voltage is 11 9 12 1 V Repair high frequency cable yes Replace LNA SSF central core and braiding integrity Cable is damaged Repair high frequency cable Cable is Replace RICU No reliable solution for a navigation task during the navigation task solution for a long period exceeding 5 minutes RAIM parameter AUX2 DATA GNSS page will have NO value Checkup in accordance with fault indication scheme 2 2 034 50 00 Page 106 Dec 17 2 009 4312 02 USER S MANUAL AIRBORNE EQUIPMENT OF SATELLITE NAVIGATION MAINTENANCE TECHNIQUE This section includes the equipment maintenance technique for the online periodical and calendar maintenance The section includes Flow Sheets for each type of the equipment maintenance a bef
22. 26 Ones of MHz 27 29 Tens of MHz 30 31 State matrix In accordance with Table E 1 5 32 Parity 0 if sum of ones is odd number 1 if sum of ones is even number Note All frequencies have 1 in hundreds of MHz values 034 50 00 Appendix E Page 9 Dec 17 2009 4312 02 USER S MANUAL Table E 1 10 Tuning frequency of DME beacon command word word structure Bit No Information content Bit coding 1 8 Address 035 00 011 101 9 28 Identifier 00 all 01 1 10 2 11 not used 13 11 Operating mode Bits 13 12 11 000 not used 001 frequency 1 010 frequency 2 011 frequency 3 100 frequency 4 101 frequency 5 110 free scanning 111 not used 15 14 Coding of tuning frequency 00 paired with VOR pairing 01 paired with ILS 10 paired with MLS 11 not used 16 2015 word output 1 17 Identification signal character 1 18 0 05 MHz 1 0 05 MHz 0 0 00 MHz 19 Tenths of MHz 0 1 MHz 20 0 2 MHz 21 0 4 MHz 22 0 8 MHz 23 Ones of MHz 1 MHz 24 2 MHz 25 4 MHz 26 8 MHz 27 Tens of MHz 10 MHz 28 20 MHz 29 40 MHz 30 31 State matrix In accordance with Table E 1 5 32 Parity 0 if sum of ones is odd number if sum of ones is even number 034 50 00 Appendix E Page 10 Dec 17 2009 4312 02 USER S MANUAL Table E 1 11 Linear turn lead word structure
23. 29 Sign Zero 30 31 State matrix In accordance with Table E 1 5 32 0 if sum of ones is odd number if sum of ones is even number Table E 1 42 Date word structure Bit No Information content Bit coding 1 8 Address 260 10 110 000 9 10 Identifier 00 all 01 1 10 2 11 not used 11 Ones of years year 12 2 years 13 4 years 14 8 years 15 Tens of years 10 years 16 20 years 17 40 years 18 80 years 19 Ones of months 1 month 20 2 months 21 4 months 22 8 months 23 Tens of months 10 months 24 Ones of days 1 day 25 2 days 26 4 days 27 8 days 28 Tens of days 10 days 29 20 days 30 31 State matrix In accordance with Table E 1 6 32 Parity 0 if sum of 1 is odd number 034 50 00 Appendix E Page 27 Dec 17 2009 4312 02 USER S MANUAL 1 if sum of 1 is even number Table E 1 43 CHP 4312 status word structure Bit No Information content Bit coding 1 8 Address 273 10 111 011 00 all 01 1 9 10 Identifier 10 92 11 not used 11 Number of visible NSV 1 gt 15 most significant bit 0 lt 15 12 13 Reserved Zero 14 15 Operating modes see below 16 19 Number of visible NSV 1 5 bit 16 20 23 Number of used NSV Ls bit 20 Bit state duode 28 27 26 25 24 15 14 Self controll
24. 6002 1 99d ETT oed Flow Sheet 5 Item MS 034 50 00c Continuation Operation and Technical Requirements TR Works performed with TR deviations Contr ol 3 Communications test with MFD The test is performed in an aircraft if the equipment is connected to MFD switch on MFD switch on the equipment power supply on the airborne power board press ON OFF button in RICU As soon as NDB indication form appears on RICU display press ENT button set up DATA GNSS window wait for valid position finding which was proved by RAIM control YES value is displayed in the value indication field of RAIM control function turn on NAV mode indication in MFD compare current time indicated by RICU and MFD displays Current time should be identical 4 Communications test with aircraft rangefinder DME The test is performed in an aircraft if the equipment is connected to aircraft rangefinder To test the communication with aircraft rangefinder switch on aircraft rangefinder switch on the equipment power supply on the airborne power board press ON OFF button in RICU As soon as NDB indication form appears on RICU display press ENT button set up AUX2 page Turn on highlighting in TUNE VOR DME field and press ENT button RICU will display Tune VOR DME window 007057750 TVONVW 6 50 600c LI 99d PTT 9 4 000 6 lt 0 Flow Sheet 5 Item MS 034 50 00c Continua
25. 8002 lt 1 LEN pezoSed 00 0 70 Flow Sheet 8 item MS 034 50 00 Continuation Operation and Technical Requirements TR Works performed with TR deviations Contr ol press ENT button to confirm operation with the installed active NDB change NDB if necessary and then press ENT button NDB initialization form indication on RICU display INITIALIZATION when NDB initialization is terminated DATA GNSS window of AUX2 page indication on RICU display DATA GNSS window is displayed until coordinates will be received from GNSS receiver GNSS flag is displayed in the flag field of reference coordinate NP receiving and then NAV1 page is displayed Failing coordinates from GNSS sensor the transfer to other data cards is performed by the operator HSUHBHHEEEHASEBBEBEHHAS HE TVONVW 6 5 1 600c LI 99d 9 7 lt 6 lt 99 4 007057760 Flow Sheet 8 item MS 034 50 00a Continuation Works performed with TR Contr Operation and Technical Requirements TR deviations ol For navigation accessed parameters test press AUX button Set AUX2 page set the highlighting in DATA GNSS field press ENT button on RICU display DATA GNSS window indication IIIIIIIIIIIIIIIII make sure that the performed position is correct for this control the value of RAIM control function RAIM control function may take values as follows YES
26. CH 43 12 02 USER S MANUAL Bit No Information content Bit coding 1 8 Address 112 01 001 010 9 10 Identifier 00 all 01 1 10 2 11 not used 11 13 Reserved Zero 14 28 Significant part is Range 4096 knots 15 bits m s bit 28 2048 knots 29 Reserved Zero 30 31 State matrix In accordance with Table E 1 5 32 Parity 0 if sum of ones is odd number 1 if sum of ones is even number Table E 1 22 Check sum word structure Bit No Information content Bit coding 1 8 Address 113 01 001 011 9 29 Significant part is 21 bits 30 31 State matrix In accordance with Table E 1 5 32 0 if sum of ones is odd number if sum of ones is even number 034 50 00 Appendix E Page 16 Dec 17 2009 4312 02 USER S MANUAL Check sum A check sum of transmitted messages is sent in word 113s Check sum is calculated by summing words of message bits from 9 to 29 beginning from word 303 Message length and finishing by word 113 check sum excluding word 113g Math check sum calculation of message may be expressed by the following formula SUM Mod 2 2 gt _ Word i 2 i l where n is a number of words in the sentence If SUM 2097152 SUM Else SUM Notes 1 Summing is algebraic binary addition of words indicated by i index 2 2 module indicates that 21 less significant bits only p
27. Example of BIU data transfer Example of BIU data transfer for active flight plan containing 29 WPTs five nearest radio beacons and three nearest airports The transfer of each sentence occurs at 0 1 s interval Sentence 1 T 0 0 WPT 1 Address 74 Data record header Address 75 Active leg of the route Address 303 Message length Address 304 Symbols 1 3 Address 305 Symbols 4 6 Address 306 NP latitude Address 307 NP longitude Address 113 Check sum 034 50 00 Appendix E Page 5 Dec 17 2009 4312 02 USER S MANUAL Sentence 2 T 0 1 s WPT 2 Address 74 Data record header Address 75 Active route leg Address 303 Message length Address 304 Symbols 1 3 Address 305 Symbols 4 6 Address 306 NP latitude Address 307 NP longitude Address 113 Check sum 3 29 sentence transfer occurs similarly Sentence 30 T 2 9 s RB 1 Address 74 Data record header Address 75 Active route leg Address 303 Message length Address 304 Symbols 1 3 Address 305 Symbols 4 6 Address 306 NP latitude Address 307 NP longitude Address 113 Check sum 31 34 sentence transfer occurs similarly Sentence 35 T 3 4 s Airport 1 Address 74 Data record header Address 75 Active route leg Address 303 Message length Address 304 Symbols 1 3 Address 305 Symbols 4 6 Address 306 NP latitude Address 307 NP longitude Address 113 Check sum 36 37 sentence transfer occurs similarly 034 50 00 Appendix
28. Navigation mode at interfacing with the aircraft trajectory parameters sensors availability of flight from the current position to any desired WP via change of WP given in flight plan passing sequence return to the WP given in flight plan passing sequence new WP insertion flight on parallel DT with displacement given value relative to DT inserted into the flight plan within 99 km range with 1 km discreteness and possibility of flight by DTA insertion new path angle insertion without WP insertion insertion storage use updating and indication of WP given by user insertion and storage of 1000 waypoints at the most insertion and storage of 90 flight routes at the most quantity of WP in the route is 144 at the most delivery of information concerning NDB validity or its expiration maneuvering availability in accordance with the NDB procedures including Fly By and Fly Over turns availability of maneuvering the following paths control in accordance with ARINC 424 recommendations appearance in the point of the approach beginning flight in the line connecting two points flight to the desired point with the desired path angle flight from the desired point with the desired path angle flight from the current position directly to the desired point constant radius arc flight 034 50 00 Page 5 Dec 17 2009 4312 02 USER S MANUAL NDB st
29. indicated If any RAM failure is detected simultaneous lighting of B MENU AUX WPT buttons is on No forms indication on RICU display Instruments Tools and accessories Expendables TVONVW 6 50 600c LI 00 0 70 Flow Sheet 8 item MS 034 50 00a MS Flow Sheet 8 Page 233 235 Item MS Operation Work control 0 1 man hour 034 50 00a Equipment test in Selfcontrol mode Reception test of navigation parameters Operation and Technical Requirements TR Works performed with TR deviations Contr ol For equipment test in Self control mode connect the equipment power supply on the airborne power supply unit press ON OFF button on RICU Immediately after start Self control mode operation is set In Self control mode RAM and ROM testing control unit and processor communication testing are performed If any RAM or ROM failures are detected the simultaneous lighting of one of NRST OBS or MSG buttons is on and that of D MENU AUX WPT buttons lighting In the case of no communication between control unit and processor all buttons on the RICU front panel blink In the case of any failure in Self control mode no forms indication on RICU display When Self control mode termination is OK the start form indication then NDB form indication NAV DATABASES TVONVW 5 4951
30. max 4 5 Within range of frequencies 1573 1610 MHz dB max 4 0 input VSWR max 1 75 output VSWR max 1 75 Current consumption mA max 65 Power supply voltage V 4 5 14 4 Transfer ratio irregularity admissible value regarding the transfer ratio maximal value in GLONASS L1 sub range on frequencies from 1593 to 1597 MHz shall not exceed 3 5 dB Admissible value of transfer ratio irregularity in frequency sub range from 1582 MHz to 1585 MHz relatively transfer ratio value at frequency 1575 MHz is no more than 4 0 dB from 1593 MHz to 1597 MHz and from 1608 MHz to 1610 MHz relatively transfer ratio value at frequency 1602 MHz is no more than 4 0 dB Power is supplied to LNA SSF from RICU X5 connector through coaxial cable LNA SSF is connected to RICU via HF line with signal attenuation not more than 10 dB at 1600 MHz 034 50 00 Page 30 Dec 17 2009 4312 02 USER S MANUAL LNA SSF construction LNA SSF housing is made of aluminum alloy and has three layer protective coating Two TNC R143 557 000 RADIALL sockets are hermetically soldered at LNA SSF output and input for HF cables connection LNA SSF is earthed in accordance with OST 1 01025 93 requirements through the surface touching the aircraft fuselage at LNA SSF mounting LNA SSF outline drawing is shown in the Figure C 2 Appendix C of this Manual 034 50 00 Page 31 Dec 17 2009 4312 02 USER S MANUAL Uninterruptible Pow
31. word structure Bit No Information content Bit coding 1 8 Address 121 01 010 001 Identifier 00 all 01 1 in 10 42 11 not used 11 17 Reserved Zero Range t172 E 6 18 28 Longitude value m s bit 28 8 6 E less significant bits Negative values are transmitted in additional code 1 West 29 Sign 0 East 30 31 State matrix In accordance with Table E 1 5 32 Parity 0 if sum of ones is odd number if sum of ones is even number Table E 1 28 Y required word structure Bit No Information content Bit coding 1 8 Address 121 01 010 001 9 10 Identifier 00 all 01 1 10 2 11 not used 11 14 Reserved Zero 15 28 Significant part is Range 180 14 bits m s bit 28 90 Negative values are transmitted in additional code 29 Sign 1 left 0 right 30 31 State matrix In accordance with Table E 1 5 32 Parity 0 if sum of ones is odd number 1 if sum of ones is even number 034 50 00 Appendix E Page 20 Dec 17 2009 4312 02 USER S MANUAL Table E 1 29 word structure Bit No Information content Bit coding 1 8 Address 125 01 010 101 9 10 Identifier 00 all 01 1 10 Z2 11 not used 11 Tenths of minutes 0 1 min 12 0 2 min 13 0 4 min 14 0 8 min 15 Ones of minutes 1 0 min 16 2 0 min 17 4 0 min 18 8 0
32. 02 USER S MANUAL Bit No Information content Bit coding 1 8 Address 312 11 001 010 9 10 Identifier 00 all 01 1 10 422 11 not used 11 13 Reserved Zero 14 28 Significant part is Range 4096 knots 15 bits m s bit 28 2048 knots 29 Sign Zero 30 31 State matrix In accordance with Table E 1 5 22 Parity 0 if sum of ones is odd number if sum of ones is even number Table E 1 51 Path angle true word structure Bit No Information content Bit coding 1 8 Address 313 11 001 011 9 10 Identifier 00 all 01 1 10 2 11 not used 11 16 Reserved Zero 17 28 Significant part is Range 180 12 bits m s bit 28 90 Negative values are transmitted in additional code 29 Sign 0 from 0 to 180 1 from 180 to 360 30 31 State matrix In accordance with Table E 1 5 32 Parity 0 if sum of ones is odd number if sum of ones is even number 034 50 00 Appendix E Page 32 Dec 17 2009 4312 02 USER S MANUAL Table E 1 52 Wind speed word structure Bit No Information content Bit coding 1 8 315 11 001 101 9 10 00 all 01 1 10 2 11 not used 11 20 Reserved Zero 21 28 Significant part is Range 256 knots 8 bits m s bit 28 128 knots 29 Sign Zero 30 31 State matrix In acco
33. 077 02 The equipment shall meet requirements for AESN subclasses 1 pursuant to Qualified Requirements KT 34 01 the 3 edition and requirements for SBAS airborne equipment pursuant to SARPs The equipment is intended for On Condition Technical Maintenance OCTM OCTM technique shall identify the type and volume of maintenance works being specified in 034 50 00 Maintenance Technique Only personnel who learned thoroughly this Manual shall operate the equipment In order to exclude any contingencies that may affect the equipment functionality please consider the following warnings CAUTIONS 1 FOLLOW THE GOVERNING RULE OF AERONAVIGATION NEVER USE ONE AND THE ONLY NAVIGATION SYSTEM ERRORS OR FAILURES ARE POSSIBLE IN ANY SYSTEM SO DUPLICATION AND CROSS CHECKING OF NAVIGATION INFORMATION ARE COMPULSORY CONDITIONS OF A SAFE FLIGHT 034 50 00 Introduction Page 1 Dec 17 2009 4312 02 USER S MANUAL 2 THOUGH THE EQUIPMENT MAY EFFICIENTLY PERFORM THE NAVIGATION REQUIRED TASKS AND DISPLAY LOT OF NECESSARY AND USEFUL INFORMATION YOU SHOULD REMEMBER THAT THE GOVERNING RULE OF A SAFE FLIGHT IS TO SEE EVERYTHING AROUND AND THAT EVERYBODY AROUND CAN SEE YOU 3 THE EQUIPMENT SHALL BE USED STRICTLY ACCORDING TO THE USER S MANUAL IN ORDER TO PROVIDE ITS EFFECTIVE OPERATION 4 ALTITUDE CALCULATED BY THE EQUIPMENT AS A RESULT OF NAVIGATION COMPUTATIONS IS AN ALTITUDE OVER GEOID AND DIFFER S
34. 101 antenna installation For A101II antenna mounting perform the operations as follows remove the process cover from connector install 101 antenna on its site with the gasket surface for antenna installation shall meet OST 01025 82 requirements check up the earthing quality by measuring resistance between AIOIII antenna metallization surface and the earthing bar by means of E6 18milliohm meter the resistance value shall not exceed 2000 mcOhms fix antenna with 4 screws and 4 nuts see figure F 1 Appendix F screw torque is 0 9 0 09 newton meters connect A101II antenna high frequency cable X2 connector to X1 connector in accordance with the Connection Layout see Appendix A to immobilize connector install retaining bracket consult Figure F 1 Appendix F lock A101II antenna connector with safety wire 0 3 12X18H9T and lock it check up A101II antenna fixing on the site 3 LNA SSF installation For LNA SSF installation perform the operation as follows remove the process cover from connector install LNA SSF on the site surface for LNA SSF installation shall meet OST 01025 93 requirements TVONVW 6 50 cO CIEP HO 600 1 99d 017 607 8 4 000 lt lt 0 Flow Sheet 2 for MS item 034 50 001 Continuation Operation and Technical Requirements TR Works performed with TR deviations Contr ol 2000 microohms Connection Layout in Appendix A to f
35. 2 ARINC 429 line B input 100 KHz 0355 slant range word 202s m rw 11 f Common 12 E _ IN MII ae Channel 3 ARINC 429 line A input 13 AR AR IN IN Channel 3 ARINC 429 line B input 14 EUM Reserved Strut One time command 1 27 V input compression 15 AR A4 IN DDRE Channel 4 ARINC 429 line A input 16 AR B4 IN B4 IN Channel 4 ARINC 429 line B input Se c os 19 AR A5 IN Channel 5 ARINC 429 line A input 20 AR B5 IN Channel 5 ARINC 429 line B input 21 IN H 2 Exchange parameters One time command 2 27 V input identifier 0 breakage 1 short circuit at 27 V 22 Channel 6 ARINC 429 line A input 23 Channel 6 ARINC 429 line input 24 Channel 7 ARINC 429 line A input 25 Channel 7 ARINC 429 line B input IN 26 Exchange parameters One time command 3 27 V input 27 IN ae EZ identifier 0 breakage One time command 4 27 V input 28 IN H 5 TE Y One time command 5 27 V input 29 Reserved One time command 6 27 V input 30 Reserved One time command 7 27 V input 31 IN 8 Reserved One time command 8 27 V input 034 50 00 Page 21 Dec 17 2009 4312 02 USER S MANUAL Table 6 Continuation Contact Circuit Signal Purpose 32 GND Common 33 INL 1 Strut compression Air Earth One time command 1 GND input Air GND short circuit Earth br
36. 6 PANDUIT tube installation on connectors R143 008 000 and R 143 156 000 000 61 GOST 21931 76 B wire soldering into 23 connector contacts Figure F 3 Cable termination for installation in aircraft 034 50 00 Appendix F Page 3 Dec 17 2009 034 50 00 Appendix 4 17 2009 4312 02 USER S MANUAL 18 6PO 364 038 TY Mounting surface Site for 23 10 18P 2 B socket installation on the object R80 max M3 6H 923 599 20 375 120 1 4 holes Figure F 4 Process connector and cap installation in aircraft 4312 02 USER S MANUAL AIRBORNE EQUIPMENT OF SATELLITE NAVIGATION APPENDIX G reference Enclosure mounting points 4 40 0 1 160 0 1 It is admissible to fix an enclosure with 12 screws in points from two sides of enclosure Figure G 1 Enclosure mounting points on lateral walls 034 50 00 Appendix G Page 1 2 Dec 17 2009 4312 02 USER S MANUAL AIRBORNE EQUIPMENT OF SATELLITE NAVIGATION APPENDIX H reference RICU installation in aircraft RICU mounting method in aircraft is shown in fig H 1 since serial Ne C03910021 For RICU before serial Ne C03908020 and before serial Ne 516030 inclusive mounting method is similar to that one shown in fig 1 gt gt ped
37. 901 902 Dec 17 2009 Dec 17 2009 Appendix A Appendix B Dec 17 2009 Dec 17 2009 Dec 17 2009 Dec 17 2009 Dec 17 2009 Dec 17 2009 Appendix C 1 2 3 4 034 50 00 List of Effective Pages Page 2 Dec 17 2009 Dec 17 2009 Dec 17 2009 Dec 17 2009 Dec 17 2009 Dec 17 2009 Dec 17 2009 Dec 17 2009 Dec 17 2009 Dec 17 2009 Dec 17 2009 Dec 17 2009 Dec 17 2009 Dec 17 2009 Dec 17 2009 Dec 17 2009 Dec 17 2009 Dec 17 2009 Section Sub CH 43 12 02 USER S MANUAL LIST OF EFFECTIVE PAGES Section Sub section Paragraph Page Date section Page Date Paragraph Appendix E 38 Dec 17 2009 39 Dec 17 2009 40 Dec 17 2009 4 Dec 17 2009 42 Dec 17 2009 43 44 Dec 17 2009 Appendix F 1 17 2009 2 Dec 17 2009 3 Dec 17 2009 x 4 Dec 17 2009 1 Appendix 12 Dec 17 2009 Appendix 1 Dec 17 2009 2 Dec 17 2009 3 17 2009 4 Dec 17 2009 5 6 17 2009 Appendix I 1 Dec 17 2009 2 Dec 17 2009 34 Dec 17 2009 Appendix K 1 2 Dec 17 2009 I 034 50 00 List of Effective Pages Page 3 4 Dec 17 2009 4312 02 USER S MANUAL TABLE OF CONTENTS Part 1 Section subsection
38. Appendix RICU installation in Appendix I UPS installation in Appendix K Connection diagram of two equipment Airborne equipment of satellite navigation User s Manual Operator s Guide Part 2 461513 077 02 P31 Appendix J 034 50 00 Table of Contents Page 2 Dec 17 2009 ACS AD AE AES AESN AHS Aircraft ASPMS ASS AVPS BC BDC BIU CA CAIO CDM 94 CP CR CS 42 DDRE DIU DME DT DTA E W component EBA EGNOS EP 90 FAWP FCC FDE FNE FNI ABBREVIATION LIST CH 43 12 02 USER S MANUAL Actual Course Angle Automatic Control System Angle of Drift Airborne Equipment Airborne Equipment Set Airborne equipment of satellite navigation Airborne Heading Systems Aircraft Altitude and Speed Parameter Measurement System Air Signal System Altitude Velocity Parameters System Binary Code Binary Decimal Code Background Information Unit Civil Aviation Civil Aviation International Organization Compact Distance Meter Central Processor Customer Representation Coordinate System 1942 Differential Data Receiving Equipment Dynamic Information Unit Distance Measuring Equipment Desired Track Desired Track Angle Ground Speed Component for East West Direction Elect
39. Operation and Technical Requirements TR Works performed with TR deviations Contr ol 1 Check up the equipment unit fastenings condition on sites 2 Check up nuts tightening in the fastening units Nuts shall be tightened firmly 3 Check up connectors tightening tighten the loss high frequency connectors firmly 4 Check up connectors locking Replace the cables connectors locking if defect 5 Check up the units earthing quality by measuring resistance between the units earthing rods and the aircraft earthing bar with E6 18 milliohm meter Resistance value shall not exceed 2000 microohms Instruments Tools and accessories Expendables E6 18 TY 2 722 015 milliohm meter Screw driver 7810 0977 X9 Screw driver 7810 0982 9 Spanner 7811 0006 9 Wire 0 3 12 189 TVONVW 6 50 CO CI Y HO 600c LI vrtet 2924 00 0 70 Flow Sheet 11 Item MS 034 50 00 KMS Flow Sheet 11 Page 243 Item MS Operation 034 50 00e Check of high frequency connector pins and sockets Work control 0 3 man hour Operation and Technical Requirements TR Works performed with TR deviations Contr ol 1 Examine RICU A101II antenna and LNA SSF high frequency connectors pins and sockets condition as well as that of high frequency cables connectors connected to these units The high frequency connector pins and sockets shall contain neither any mechanical
40. and maximum relative humidity 80 during 5 years without re preservation The equipment requires no maintenance and technical condition testing during the storage period For storage of the equipment dismantled from the aircraft prepare the units for storage as follows a place the equipment units into a plastic bag b place some silica gel into this plastic bag c seal the plastic bags hermetically faulty fusion pinches and rapture of plastic bags are not permitted d place the plastic bags containing the units into the cardboard boxes e place the cardboard boxes containing the units into original packing box f shut the box with the cover and seal it 034 50 00 Page 901 902 Dec 17 2009 4312 02 USER S MANUAL AIRBORNE EQUIPMENT OF SATELLITE NAVIGATION TRANSPORTATION The equipment shall be transported packed and preserved in original packing The equipment in original packing shall be transported both by air and by any ground transport in accordance with the regulations on the corresponding transport The packing box shall be placed in accordance with the regulations on the corresponding transport The packing box containing the equipment shall be fixed so to avoid any displacement or strokes during the transportation The packing box containing the equipment shall be neither thrown nor turned over during handling 034 50 00 Page 1001 1002 Dec 17 2009 4312 02 USER S MANUAL AIRBORNE
41. damage nor shall be dirty Clean the high frequency connector pins and sockets with alcohol and brush In the case of any damage of the high frequency connectors pins and sockets replace the connector make soldering of the new connector in correspondence with the Connection Layout in Appendix A of this Manual 2 Examine cable insulation s external condition especially near the high frequency connectors and where cables pass openings and where they may rub against some aircraft parts Cables damaged insulation shall be protected with insulation tape Instruments Tools and accessories Expendables Flat brush N8 OST 17 888 81 Alcohol Insulation tape TVONVW 6 50 CO CI Y HO 600c LI 99d 9pc Spc 2824 00 0 70 12 12 Chart 12 Page 245 Operation Replacement of detachable device for navigation database storage Work control 0 1 man hour Operation and Technical Requirements TR Works performed with TR deviations Contr ol To replace the navigation database storage removable unit perform the operations as follows remove the navigation database storage removable unit out from RICU Note Remove or set detachable device for NDB storage in RICU only if RICU is turned off set the new navigation database storage removable unit into RICU connect RICU when NDB indication form appears on RICU display monitor NDB expiration date
42. display on off equipment button control buttons shaft encoder photoresistor and navigation database storage removable unit Display and photoresistor are protected with glass RICU is fixed on the enclosure by means of screws 4 pcs on RICU front panel See figure 4 for the RICU front panel appearance See Appendix B for RICU outline drawing 034 50 00 Page 24 Dec 17 2009 4312 02 USER S MANUAL 1 Navigation database storage removable unit 2 Equipment on off button 3 Display 4 6 Control buttons 5 Photoresistor adjusting display brightness 7 Shaft encoder external handle 8 Shaft encoder internal handle By pressing on the shaft coder internal handle edge CRSR button function shall be performed Figure 4 Controls Purpose RICU ON OFF button ON OFF button identification ON OFF for RICU before serial Ne 03908020 inclusive D for RICU since serial Ne 03910021 Note Hereinafter in the text ON OFF button is indicated for RICU turning on off ON OFF button operations refer also to 1 button NRST button NRST button is purposed for transition into the nearest navigation points form from the database Repeated pressing of NRST button shall return the form previous to NRST form call 034 50 00 Page 25 Dec 17 2009 4312 02 USER S MANUAL OBS button OBS button is designed for the flight task in OBS mode output in WP with desired angle of transit During OBS mode flight
43. fig C 2 before serial No 6516229 inclusive LNA SSF outline drawing is shown in fig C 3 since serial Ne 6516230 moving direction e gt lt E 5 Metallization v s surface 2 sealing place Multicomp Farnell 324 1610 socket 225 TNC R143 557 000 RADIALL socket 5 2 i s 83 8 0 1 119 4 Figure C 1 034 50 00 Appendix C Page 1 Dec 17 2009 4312 02 USER S MANUAL 118 5 50 0 0 1 10 gt 3 e 4 21 Multicomp Socket Farnell 324 1610 or TNC R143557000 RADIALL socket 2 pcs 142 0 Figure C 2 034 50 00 Appendix C Page 2 Dec 17 2009 4312 02 USER S MANUAL TNC R143557000 RADIALL socket 2 pes 50 0 0 1 945 YMIU POC PETTI 70 58 0 0 1 metallization surface of LNA SSF amplifier Figure C 3 034 50 00 Appendix C Page 3 4 Dec 17 2009 4312 02 USER S MANUAL AIRBORNE EQUIPMENT OF SATELLITE NAVIGATION APPENDIX D reference UPS Outline Drawing UPS outline drawing is shown in fig D 1 before serial Ne b516056 inclusive UPS outline drawing is shown in fig D 2 since serial Ne b516057 Plug CHII 23 10 18B 1 B Socket 23 10 18 1 Earthing rod Input and output voltage indicators feo A 140
44. forming on pin 33 of the connector X2 at the rate of 0 03 V per 1 km positive value is a set to the right 1 e DT is at the left Voltage 0 75 mV meets a deviation from DT 2 5 km set the highlighting in RK OUT field set the symbol 0 in character location which meets RK10 OUT one time command Availability Z Check a disconnection of Availability Z output signal Instruments Tools and accessories Expendables TVONVW 6 50 600c LI ZET TET 9894 00 0 70 Flow Sheet 7 Item MS 034 50 001 K Flow Sheet 7 On page 231 Item MS Operation 034 50 001 RAM extended test Work control 0 3 man hour Operation and Technical Requirements TR Works performed with TR deviations Contr ol For RAM extended test connect the equipment power supply on the airborne power supply unit press any button on RICU front panel except ON OFF button and while keeping it pressed press ON OFF button Immediately after start RAM extended test will be performed RAM extended test will last not longer than 10 minutes Duringtest D button shall be constantly lighted NRST OBS MSG NAV FPL PROC buttons will light in turn PROC button stays highlighted to the end of test If RAM extended test is OK NRST OBS MSG NAV FPL PROC buttons will be simultaneously lighted equipment test in Self control mode shall be performed and the start form shall be
45. from aircraft on board power system across uninterruptible power supply unit 034 50 00 Page 17 Dec 17 2009 4312 02 USER S MANUAL RICU Connectors Purpose There are five connectors on the RICU enclosure s rear panel X1 connector 1 10 18 1 plug is purposed for UPS connection connector contacts purpose is given in the Table 3 Connectors X2 1 41 30 1 plug 1 41 30 1 plug X4 OHu bI 1 41 30B 1M 6 B plug purpose is connection of RICU to the airborne equipment X2 X3 X4 connector contacts purpose is given in the Tables 4 5 6 respectively X5 connector TNC R 143 324 000 RADIALL socket is purposed for RICU connection to LNA SSF LNA SSF feed voltage is supplied via the connector central contact having minimal voltage of 12 1 V and maximal current consumption of 75 mA Table 3 X1 connectors purpose Contact Circuit 1 27_UPS Power source 27 V input 2 Equipment power on signal input reserved 3 Power source 27 V input 4 Power source 27 V input 5 Equipment power on signal input 6 Power source 27 V input 7 Equipment power on signal output reserved 8 Equipment power on signal output 9 Enclosure 10 ENCLOSURE Enclosure 034 50 00 Page 18 Dec 17 2009 4312 02 USER S MANUAL Table 4 X2 connector
46. heading reference unit 1 failure AHRU 0 normal operation 20 29 Reserved Zero 30 31 State matrix In accordance with Table E 1 5 32 Parity 0 if sum of ones is odd number 1 if sum of ones is even number Normal operation is the mode when attitude and heading reference system uses true airspeed data and barometric altitude data from AVPS system Basic mode is the mode when data from AVPS are not available or invalid for some reason Transition from one mode to another and vice versa is performed automatically Bit 13 at the test control is equal to 0 basic mode character GMH mode gyro magnetic heading mode GSMH mode gyro semicompass heading mode 034 50 00 Appendix E Page 40 Dec 17 2009 4312 02 USER S MANUAL Table E 2 7 Gyromagnetic heading gyro semicompass heading word structure Bit No Information content Bit coding 1 8 Address 320 11 010 000 9 10 Identifier 00 all 01 1 10 2 11 not used 11 13 Reserved Standard 14 28 Significant part is Range 180 15 bits m s bit 28 90 Negative values are transmitted in additional code 29 Sign 0 from 0 to 180 1 from 180 to 360 30 31 State matrix In accordance with Table E 1 5 32 Parity 0 if sum of ones is odd number if sum of ones is even number Table E 2 8 Adjustment frequency of navigation and landing system affirmative character
47. in ACTIVE field ACTIVE field shall contain no symbols NDB shall be not expired The list of regions in the active NDB indicates except the regions stipulated by Agreement of NDB supply the boarding regions as well NAV DATABASES Instruments Tools and accessories Expendables TVONVW 6 50 CO CI Y HO 4312 02 USER S MANUAL Cleaning and Painting The equipment requires no special cleaning or painting WARNING THE FOLLOWING LIQUIDS SHALL EXPOSURED ON A1010 ANTENNA ENCLOSURE UNDER NO CONDITIONS 5 HYDRAULIC FLUID ON BASE OF ORGANOPHOSPHORUS COMPOUND ETHER 1 1 1 TRYCHLORETHANE 034 50 00 Page 247 Dec 17 2009 4312 02 USER S MANUAL Servicing In the case of any troubles during the equipment operation the trouble shall be detected accurate within the unit following the Troubleshooting recommendations A faulty unit shall be repaired at the manufacturing factory Check up the seals availability before forwarding the faulty unit to the manufacturer WARNING FOR FAULTY UNIT REPLACEMENT TURN OFF IT FROM 27 V SUPPLY CIRCUIT 034 50 00 248 Dec 17 2009 4312 02 USER S MANUAL AIRBORNE EQUIPMENT OF SATELLITE NAVIGATION STORAGE CONDITIONS The entire equipment or separate units shall be stored packed and preserved in original packing The equipment shall be stored in heated rooms at temperatures from 5 C to 40 C
48. min 19 Tens of minutes 10 min 20 20 min 21 40 min 22 80 min 23 Ones of hours 1 0 hr 24 2 0 hrs 25 4 0 hrs 26 8 0 hrs 27 Tens of hours 10 0 hrs 28 20 0 hrs 29 Reserved Zero 30 31 Status matrix In accordance with Table E 1 6 32 Parity 0 if sum of ones is odd number if sum of ones is even number Table E 1 30 Integrity alarm threshold word structure Bit No Information ciontent Bit coding 1 8 Address 130s 01 011 000 9 10 Identifier 00 all 01 1 10 2 11 not used 11 RAIM detected an 1 yes unhealthy satellite 0 no 12 28 Significant part is Range 16 NM 17 bits m s bit 28 8 NM 29 Reserved Zero 30 31 State matrix In accordance with Table E 1 5 034 50 00 Appendix E Page 21 Dec 17 2009 4312 02 USER S MANUAL 32 Parity 0 if sum of ones is odd number 1 if sum of ones is even number Table E 1 31 Flight stage word structure Bit No Information content Bit coding 1 8 Address 1323 01 011 010 9 10 Identifier 00 all 01 1 10 2 11 not used 11 Integrity alarm threshold 0 is set manually 1 yes 100 en route 12 14 Flight stage 010 terminal area 110 approach 10 WGS 84 15 16 Coordinate system 01 EP 90 11 CS 42 Integrity alarm threshold 0 no 17 set manually exceeds 1 yes integrity alarm threshold of f
49. or during equipment operation MESSAGE window is displayed on RICU figure 10 In the presence of several messages MSG button lighting turns on To read the messages issued by the equipment press MSG button After reading all messages MSG button lighting will turn off To continue the operation press MSG button 034 50 00 Page 43 Dec 17 2009 4312 02 USER S MANUAL 1 Failure message window Figure 10 The equipment is operable if none of the below messages are not seen in MESSAGE window when initialization testing is terminated DATABASE EXPIRED DATABASE MISSING Antenna is bad Link with GNSS is bad Link with KVU is bad Receiver s testing is failed If 5 minutes after RICU switching on valid coordinates are not defined there are no data from GNSS sensor or they are not set manually by the operator Enter coordinates time and date message is displayed in MESSAGE box of RICU display If 5 minutes after RICU switching on valid coordinates date and time are set manually by the operator then in the presence of data from air data sensors SVS and heading reference system IRS and in the absence of wind parameters Enter wind speed message is displayed in MESSAGE box 034 50 00 Page 44 Dec 17 2009 4312 02 USER S MANUAL Operational procedure with the equipment is shown in Part 2 of Technical Maintenance Manual 461513 077 02 P91 User s Manual Active NDB Change Navigation databas
50. the reminded time exceeds one hour minutes and seconds if the remained time is less than one hour time of appearance in WP hours and minutes Note indicated parameters dimension shall be changed for the dimension given in parenthesis when metric system is changed for the British one 034 50 00 Page 7 Dec 17 2009 4312 02 USER S MANUAL Tolerance of Navigation Parameters Tolerance of navigation parameters detection shall correspond to KT 34 01 requirements 34 edition Navigation parameter errors with 0 95 probability if HDOP is lt 1 5 VDOP is lt 3 0 in SNS Navigation mode and operation using GLONASS SNS GPS SNS and mixed GLONASS GPS SNS is no more than horizontal coordinates 44 m altitude 70 m ground speed 0 3 m s In SNS Navigation mode the horizontal coordinates deviation shall be detected by calculations depending on airborne sensors deviation airspeed sensor and route sensor and operation time in SNS Navigation mode In DME DME navigation and VOR DME navigation modes errors are defined by calculation depending on the distance to radio beacons and geometric position of the aircraft and radio beacons Coordinates taking time The first reading of navigation parameters shall be taken in 2 5 minutes at the latest Work continuity The equipment continuous operation time is 24 hours Number of RR radio channels Number of RR radio channels 24 The equipment w
51. unit and airborne cable net The line maintenance before each flight shall be performed in the following scope Equipment test in Self control mode Reception test of navigation parameters FS 8 Operability extended testing FS 3 Altimeter and heading system communications test Two RICUs interaction test Communications test with MFD Communications test with airborne range finder Communications test with navigation and landing system FS 5 Routine maintenance after 600 20 running hours shall be performed on the aircraft without disassembly of units in the following scope Inspection of A101II antenna radio transparent radome and unit appearance FS 9 Check of nut tightening and locking in connectors Earthing quality check FS 10 RAM extended test FS 7 Operability extended testing FS 3 Test of navigation task solution FS 74 Altimeter and heading system communications test Two RICUs interaction test Communications test with MFD Communications test with airborne range finder Communications test with navigation and landing system FS 5 Shaping test of aircraft light panel control signals produced by the equipment Generation test of Selected roll and Z signals FS 6 034 50 00 Page 202 Dec 17 2009 4312 02 USER S MANUAL Routine maintenance after 6000 60 running hours shall be performed with 101 antenna LNA SSF disassembly if necessary and RIC
52. 034 50 00 Page 101 Dec 17 2009 4312 02 USER S MANUAL In the case of any mechanical damages a Cable damage where it is sealed into the connector cut the cable for 1 or 2 cm from the damage place die and seal it again into connector cable tension is not allowed when connecting with devices and units minimal banding radius shall be 5 cm cable splicing is prohibited b in the case of the earthing bar and the units earthing rod defective contact due to corrosion remove the corrosion signs from the earthing bar with abrasive cloth in the case of the earthing bar breakage replace it c if connector pins and sockets are dirty clean dirty and corrosive places with clean cloth or brush wetted in alcohol then dry the connector In the case if any defective pins or sockets are detected in the cable connector replace the connector d if connector tightening and locking are faulty tighten home connectors nuts and lock the nuts with safety wire To check up the equipment workability by means of the inbuilt control system start the equipment and perform the operability extended testing of the equipment workability see FS 3 Evaluate the testing results Replace defective units if necessary 034 50 00 Page 102 Dec 17 2009 Failure Symptom List CH 43 12 02 USER S MANUAL Table 101 Performed test test Failure symptom Scheme contents number Equipment 1 No
53. 17 2009 38 39 Dec 17 2009 Introduction 1 17 2009 40 2 17 2009 41 42 034 50 00 1 17 2009 43 2 Dec 17 2009 44 3 17 2009 45 4 17 2009 46 5 17 2009 47 6 17 2009 48 7 17 2009 49 50 8 17 2009 101 9 17 2009 102 10 Dec 17 2009 103 11 17 2009 104 12 Dec 17 2009 105 13 Dec 17 2009 106 14 Dec 17 2009 201 15 Dec 17 2009 202 16 Dec 17 2009 203 17 Dec 17 2009 204 18 Dec 17 2009 205 19 Dec 17 2009 206 20 Dec 17 2009 207 21 Dec 17 2009 208 22 Dec 17 2009 209 210 Dec 17 2000 034 50 00 List of Effective Pages Page 1 Dec 17 2009 Section Sub CH 43 12 02 USER S MANUAL LIST OF EFFECTIVE PAGES Section Sub Page Dec 17 2009 Dec 17 2009 Dec 17 2009 Dec 17 2009 Rage Pate section Paragraph 034 50 00 211 212 Dec 17 2009 Appendix D 213 Dec 17 2009 214 Dec 17 2009 215 Dec 17 2009 216 Dec 17 2009 217 218 Dec 17 2009 219 Dec 17 2009 220 Dec 17 2009 Appendix E 221 Dec 17 2009 222 Dec 17 2009 223 Dec 17 2009 224 Dec 17 2009 225 Dec 17 2009 226 Dec 17 2009 227 Dec 17 2009 228 Dec 17 2009 229 230 Dec 17 2009 231 232 Dec 17 2009 233 Dec 17 2009 234 Dec 17 2009 235 236 Dec 17 2009 241 242 243 244 Dec 17 2009 Dec 17 2009 Dec 17 2009 Dec 17 2009 245 246 247 Dec 17 2009 Dec 17 2009 248
54. 3 contact 2 1S signal positive polarity and to RICU s connector X3 contact 3 18 signal negative polarity Time marker signal form and load characteristics shall meet ARINC 743A 4 Figure 3 shows 1S output signal form regarding 1S signal output Note Voltage marks of time marker output signal on 1S output regarding 1S output delivered to connecting cable are identified as follows plus at logical binary 1 minus at logical binary 0 0 9 Vss Vss steady state voltages differential 1S signal regarding 1S signal Tb pulse duration Tr pulse rise time Tf pulse fall time Figure 3 034 50 00 Page 23 Dec 17 2009 4312 02 USER S MANUAL Vss voltage shall be deducted as differential between the two steady states of 1S output signal regarding 18 signal Vss voltage shall be measured 1007 10 Ohm on test load connected between outputs 1S and 18 Vss value shall be within the range from 1 4 to 6 0 V Tb pulse duration 1 00 0 01 ms pulse period 152 107 c Tr pulse rise and Tf pulse fall not more than 200 ns between the values 0 1 and 0 9 of the set signal level Receiver indicator and control unit Design RICU housing is made of aluminum alloy The rear panel contains connectors for RICU when installation in aircraft On the front panel there is a graphical LCD with adjustable lighting hereinafter referred to as
55. 312 02 USER S MANUAL Description Receiver indicator and control unit 467855 039 Receiver indicator and control unit s purpose is to process the received signals and deliver the results on the display and to external users External view of RICU front panel since serial Ne C03910021 is shown in fig 2 oM m MICE D MSG FPL PROC Figure 2 034 50 00 Page 16 Dec 17 2009 4312 02 USER S MANUAL Receiver indicator and control unit Operation GPS GLONASS SNS signals received by 101 antenna and amplified in LNA SSF enter the RICU input In RICU these signals are amplified filtered separated and their further analog and digital processing occurs RICU makes all calculations associated with formation of output control Y required signal generated in ACS and lateral deviation from desired track generated in FNI RICU forms word packages transferred in ARINC 429 format to aircraft systems interfaced with RICU RICU maintains data exchange control with interfaced airborne equipment Navigation database is stored in detachable storage device This navigation database storage device may contain information on two bases of navigation data RICU operating mode control its turning on and off is performed by means of the following controls keyboard shaft encoder and ON OFF button located on the front panel Navigation information is shown on RICU display RICU electric supply is performed
56. 5 1 8 0 9 1 034 50 00 Appendix 29 Dec 17 2009 4312 02 USER S MANUAL Table E 1 46 Message length word structure Bit No Information content Bit coding 1 8 Address 303 11 000 011 9 12 Number of words in Max 15 message 13 15 Point type Weaning 0 0 0 User WPT 0 0 1 Not used 0 1 0 Airport 0 1 1 NDB Beacon 1 0 0 Not used 1 0 1 Do not draw any symbol 1 1 0 VOR 1 1 1 Intersection 16 Belonging to the route 1 en route 0 not en route 17 223 Point number Max 127 24 FMS mode 1 selected 0 not selected always 0 25 Point in route center in center 0 not in center always 0 26 Space 1 set 0 not set 27 Graphics 1 graphical 0 not graphical 28 29 Reserved Zero 30 31 State matrix In accordance with Table E 1 5 22 Parity 0 if sum of 1 is odd number 1 if sum of 1 is even number Note Jn the case when the arc should be depicted whose original coordinates do not coincide with those of the last depicted point bit 26 shall be set in 1 for the time of this point representation and after that it shall be returned in 0 state at the arc original coordinate assignment 034 50 00 Appendix E Page 30 Dec 17 2009 4312 02 USER S MANUAL Table E 1 47 Symbols 1 2 3 identifier Symbols 4 5 6 identifier word structure
57. AIRBORNE EQUIPMENT OF SATELLITE NAVIGATION USER S MANUAL OPERATION PART 1 461513 077 02 4312 02 USER S MANUAL RECORD OF REVISIONS Section Sub tec HON Page Document document Sienat Dat Pararaki Ref Ref TS grap Revised Added Deleted and Date 034 50 00 Record of Revisions Page 1 Dec 17 2009 4312 02 USER S MANUAL RECORD OF REVISIONS Section Bev Subsection Document document Signature Date Ne Paes eh f Ref Ne Ref Ne and gn grap Revised Added Deleted date 034 50 00 Record of Revisions Page 2 Dec 17 2009 4312 02 USER S MANUAL LIST OF EFFECTIVE PAGES Section Sub section Section Sub section Title page 1 Dec 17 2009 034 50 00 23 Dec 17 2009 24 Dec 17 2009 Record of Revisions 1 Dec 17 2009 25 Dec 17 2009 2 17 2009 26 17 2009 List of Effective Pages 1 Dec 17 2009 28 2 Dec 17 2009 29 Dec 17 2009 3 4 Dec 17 2009 30 Dec 17 2009 Table of Contents 1 17 2009 31 17 2009 2 17 2009 32 17 2009 33 17 2009 Abbreviation list 1 17 2009 34 2 17 2009 35 17 2009 3 17 2009 36 4 17 2009 37 5 6 Dec
58. E Page 6 Dec 17 2009 4312 02 USER S MANUAL E 1 4 Information output via channel 2 The equipment outputs a command word 10 times per second via channel 2 for DME beacon adjusting word address 035s a command word for Course 93M navigation and landing system word address 034g and Required azimuth word word address 0243 024 word structure is given in Table E 1 8 034 word structure is given in Table E 1 9 035 word structure is given in Table E 1 10 E 1 5 Information output via channel 3 The equipment outputs information via channel 3 10 times per second The list of information delivered via channel 3 is given in the table E 1 4 Table E 1 4 Parameter Word address Table number Current latitude precisely 120 E 1 26 Current longitude precisely 121 1 27 Integrity alarm threshold 130 E 1 30 Vertical Figure of Merit VFOM 136 1 32 Current time UTC precisely 140 E 1 33 Current Greenwich time 1508 1 35 Vertical speed 1658 E 1 36 Ground speed component N S value 1668 E 1 37 Ground speed component E W value 174 1 38 Horizontal Figure of Merit HFOM 247 1 39 Remaining distance to the current WPT 2518 E 1 40 Time to go to the next WPT 252g E 1 41 Date 260 E 1 42 Magnetic track angle 317 E 1 19 Magnetic heading 320 1 19 Angle of drift 3213 E 1 16 Deviation from DT in horizontal pl
59. EQUIPMENT OF SATELLITE NAVIGATION 1 The attenuation is no more than 0 6 dB 1 2 L F 14 Socket TNC R143 557 000 RADIAL A2 Plug 23 10 18 1 0 364 241 x1 Le w Le Les 3 _ DC airborne mains 27V 55W Socket CHLI23 10 18P 1 B Te0 364 241 TY x2 cas 27 ouT 1 27 6 Socket CHLI23 10 18P 1 B 60 364 241 csr 27 OUT 27 OUT e oN 8 Socket TNC R143 324 000 PK50 3 23 TY 16 505 216 81 rT APPENDIX mandatory Connection Layout A4 1 Socket TNC R143 324 000 PK50 3 23 TY 16 505 216 81 RADIAL The attenuation is than 10 dB X7 Second marker no ARINC 743A 1 2 Plug 1 41 30 1 0 364 241 X9 Service Connector s 12 GD ewss m 6 HTEXZ2J ey S 4 GNSS TX1 Law gx s anun Aw s arm x sw CO PXA_RX0 s xx Hi es sd USB _OUT USBGND_OUT RX4 To the connector X3 15 X3 16 X3 19 X3 20 PLM_TX4 second RICU PLM_TX4 1 11 7 4 USB VCC OUT Plug OHLLBT 1 10 188 1M B x5 X1 re0 364 241 2 Circuit 7 1 1 TACS
60. Figure D 1 page 1 of 2 034 50 00 Appendix D Page 1 Dec 17 2009 4312 02 USER S MANUAL 5 2 CR sealing place 4 holes 173 max 155 QC sealing place Figure D 1 page 2 of 2 034 50 00 Appendix D Page 2 Dec 17 2009 4312 02 USER S MANUAL 160 140 Ground stud Input and output voltage indicators 52 max 23 10 18 1 plug 23 10 18 1 socket TEO 364 241 TY 364 241 2 Figure D 2 page 1 of 2 034 50 00 Appendix D Page 3 Dec 17 2009 4312 02 USER S MANUAL 05 5 4 holes QC sealing place CR sealing place Figure D 2 page 1 of 2 034 50 00 Appendix D Page 4 Dec 17 2009 4312 02 USER S MANUAL AIRBORNE EQUIPMENT OF SATELLITE NAVIGATION APPENDIX E reference Information output and receiving according to ARINC 429 E 1 Information output by the equipment according to ARINC 429 E 1 1 The equipment outputs the information to external consumers as serial bipolar code using asynchronous method in accordance with GOST 18977 79 PTM 1495 75 with amendment 3 ARINC 429 The equipment has 4 channels of digital information output channel 0 is designed for output in ACS of Y required signal and output of auxiliary signals with 100 KHz frequency contacts 29 and 30 of RICU X3 channel 1 is designed for information output to MFD Information out
61. I 994 SIZ Sed 007057760 Flow Sheet 3 MS Item 034 50 00b Continuation Operation and Technical Requirements TR Works performed with TR deviations Cont rol 3 GNSS receiver extended testing For reliable NSV signal reception maximum upward visibility should be provided This procedure should not be performed in a room For GNSS receiver extended testing set lighting on AUX4 page in GNSS TEST field press ENT button GNSS TEST pop up window is shown in AUX4 page set the highlighting in FUNCTIONAL TEST field press ENT button pop up window will disappear on AUX4 page control testing results after 3 minutes TVONVW 6 50 CO CI Y HO 600c LI 99d 912 9994 000 lt lt 0 Flow Sheet 3 MS Item 034 50 006 Continuation Operation and Technical Requirements TR Works performed with TR deviations Cont rol To control test results set the highlighting on AUX4 page in BACKGROUND TEST field press ENT button on RICU display FonTest 1 the first window of equipment background test shall be indicated with GNSS receiver extended test results GNSS TEST line and the equipment operation modules background test TVONVW 6 50 CO CI Y HO 600c Ll 99d 91 11 8 4 000 lt lt 0 Flow Sheet 3 MS Item 034 50 006 Continuation Operation and Technical Requirements TR Works performed with TRI Cont devi
62. IGNIFICANTLY FROM THE BAROMETRIC ALTITUDE NEVER USE IT FOR VERTICAL NAVIGATION 5 WHEN INFORMATION MESSAGE APPEARS HIGHLIGHT OF THE BUTTON MSG TURNED ON A PILOT SHOULD BECOME ACQUAINTED WITH ITS CONTENT AND TAKE A DECISION AS TO FURTHER ACTIONS 6THE EQUIPMENT INDICATES THE NAVIGATION DATABASE NDB EXPIRATION DATE STORED ON THE NDB STORAGE REMOVABLE UNIT THE DELIVERY SET INCLUDES THE DEMO NDB THE NDB SHALL BE UPDATED EACH 28 DAYS NDB SHALL BE SUPPLIED REGULARLY TO THE CUSTOMER UNDER THE SPECIAL AGREEMENT IN ACCORDANCE WITH AIRAC CYCLES THE PILOTS USING THE OUT OF DATE DATABASE DO IT ON THEIR OWN RISK 7 DETACHABLE NDB STORAGE DEVICE SHOULD BE REMOVED OR SET IN RICU ONLY IF RICU IS TURNED OFF WARNING THIS DOCUMENT SHALL BE COPIED REPRODUCED AND TRANSFERRED TO THE THIRD PERSONS SUBJECT TO WRITTEN CONSENT WITH DESIGNER 034 50 00 Introduction Page 2 Dec 17 2009 4312 02 USER S MANUAL AIRBORNE EQUIPMENT OF SATELLITE NAVIGATION DESCRIPTION AND OPERATION General Information Purpose The equipment is purposed for operation as an element of the radioelectronic aircraft equipment with information interchange digital lines The equipment is intended both for standalone installation and as element of the civil aircraft instrumentation The equipment tasks are as follows to resolve the navigation tasks and provide with aeronavigation control at all stages of flight from takeoff till approach airway fl
63. IND field and ENT button DATA SVS IRS WIND window is indicated on RICU display as follows in Habs TAS and GMK fields control whether altitude speed and gyro magnetic heading values are correct OK FAULT TVONVW 6 50 CO CI Y HO 600c LI 99d TCT 9 4 00 0 70 Flow Sheet 5 Item MS 034 50 00 Continuation Operation and Technical Requirements TR Works performed with TR deviations Contr ol OK value is indicated if two words come periodically from altimeter to the equipment no more rarely than once a second with the normal operation state matrix Note Habs TAS GMK values are checked according to User s Manual for specific interconnected systems Wind conditions are not checked 2 Two RICUs interaction test The test shall be performed in that case if two RICUs are installed on aircraft board To test two RICUs interaction press ON OFF button on both RICUs when NDB form appears on RICU display press ENT button open AUX2 page set the highlighting on DATA CROSS RICU field and press ENT button DATA CROSS RICU window shall be indicated on RICU display If two RICUs interact correctly in DATA CROSS RICU window in three top lines YES value shall be indicated The indication of NO value is evidence of failure of connection with another RICU or else of un synchronized databases of two RICUs TVONVW 6 50
64. Message length 303 BC E 1 46 Identifier 1 2 3 symbols 304 BC E 1 47 WP RB identifier Identifier 4 5 6 symbols 305 BC NP latitude 306 BC E 1 48 NP position NP longitude 307 BC Arc direction 330 BC 1 55 Arc radius 331 BC E 1 56 Arc track change angle 332 BC 1 57 Words with addresses 074 and 075 shall be the first BIU sentence and the word with address 113 should be the last one The equipment outputs DIU and one BIU sentence in each information output cycle The sentences should be transmitted as follows sentences describing WPTs from the first to the last one sentences describing navigation references Cyclogram of dynamic and background information output is shown in Figure E 1 1 034 50 00 Appendix E Page 4 Dec 17 2009 4312 02 USER S MANUAL o 8 8 g 8 5 5 S 5 5 5 2 D 5 S 5 5 72 9 0 2 m A 3 4a 2 8 N 2 2 2 2 2 m m m e a m ee Jq od al a 100 ms 100 ms 100 ms 100 ms 100 ms Figure E 1 1 Routing line on display 15 defined by the sequence of BIU output sentences Its contouring Is performed from the first WPT BIU first sentence to the last BIU last sentence Active leg of the route is marked with color The airplane position is contoured in accordance with aircraft current position from the dynamic information unit
65. NDUIT or Socket TNC R 143 557 000 RADIALL HSTTA 50 48 5 301532 003 Gasket R 143 156 000 RADIALL Wire 0 3 12 18 9 GOST 18143 72 Movement direction 301532 003 Gasket Wire 0 3 12X18H9T 83 8 0 1 Stopping recommended technique 1 1 antenna installation site on the object Figure F 1 AIOIII antenna installation 034 50 00 Appendix F Page 1 Dec 17 2009 4312 02 USER S MANUAL 301532 003 bracket 2 pcs 0 3 12X18H9T wire 18143 72 TNC R 143 008 000 plug 2 pcs RADIALL 118 5 50 0 15 el 58 0 15 TNC R 143 557 RADIALL socket 2 pcs PANDUIT tube HSTTA 50 48 5 A 19 5703 11 5 lt 46 50 0 0 1 LNA SSF installation site on the object Mounting surface Figure F 2 LNA SSF installation Note LNA SSF mounting method is shown in fig F 2 since serial Ne 6516230 LNA SSF mounting method before serial Ne B516229 inclusive is similar to that one which is shown in fig T 034 50 00 Appendix F Page 2 Dec 17 2009 4312 02 USER S MANUAL PK 50 3 23 cable TY 16 505 216 81 61 solder GOST 21931 76 a cable termination and soldering in connectors R143 008 000 and R 143 156 000 R143 008 000 plug R143 156 000 angle plug PANDUIT tube HSTTA 50 48 5 2 35 mm PANDUIT tube HSTTA 50 48 5 35 mm PANDUIT tubes shall be shrinked at 1215
66. R button functions shall be performed after pressing the shaft encoder internal handle edge Note Control buttons background lighting is constantly on Shaft Encoder Shaft encoder consists of two rotating handles external and internal Shaft encoder external handle is designed for selecting the edit element lighting moving in the pop up window fields Shaft encoder internal handle is designed for switch pages inside the form and to go over the option within the edit element s limits CRSR button functions shall be performed after pressing the shaft encoder internal handle edge Service Connector Purpose Service connector is used at the equipment software replacement at the aircraft X9 Service Connector 23 10 18P 2 B socket see Appendix A X9 service connector is connected to the counterpart of RICU X3 connector to 23 41 30P 6 a B socket from IK corresponding to Connection Layout see Appendix A 034 50 00 Page 28 Dec 17 2009 4312 02 USER S MANUAL A10111 Antenna 101 antenna IIKAH 464656 005 meets KT 34 01 the third edition by its electric parameters 101 antenna operating frequency range is from 1570 MHz to 1610 MHz 101 antenna VSWR within the operating frequencies range is 1 5 at the most 101 antenna directional diagram provides the reception of signals at frequencies from 1570 MHz to 1610 MHz in the upper hemisphere with angles of elevation of NSC not le
67. RAIM is accessible NO RAIM functions are lost The navigation parameters are correct if in RAIM control function indication field YES value is indicated Instruments Tools and accessories Expendables TVONVW 5 4951 4312 02 USER S MANUAL Inspection and Checkout The equipment shall be examined on various stages of the technical maintenance in order to test the units appearance their fastening cables and cable connectors condition as well as earthing bars condition All works connected with the equipment units examination and test together with stages of these works are listed in Table 203 Table 203 Operation Operation Stage FS Inspection of 101 antenna radio At periodical maintenance after 600 FS 9 item MS transparent radome and unit appearance and 6000 hours of operation at 034 50 00g calendar maintenance after 12 and 48 months after repair At periodical maintenance after 600 Check of nut tightening and locking in and 6000 hours of operation at FS 10 item MS connectors Earthing quality check calendar maintenance after 12 034 50 00h 48 months after repair Check of high frequency connector pins At periodical maintenance after 6000 and sockets hours of operation at calendar FS 11 item MS maintenance after 48 months after 034 50 00e repair Replacement of detachable device for Navigation database storage unitis FS 12
68. RICU display indication for more than workability testing one minute after the equipment start by at start preliminary pressing ON OFF button on RICU 1 test 2 Control buttons lighting fails to switch on 1 2 3 When preliminary test is finished Error Message indication on RICU display 1 3 034 50 00b Equipment 1 During the keyboard testing workability AUX4 KEYBOARD TEST page extended testing lightening on RICU display for the buttons corresponding to control buttons fails to switch on parameter values Encoder A Encoder B 0 63 do not change on 2 1 RICU display at shaft encoder rotation 2 After extended testing AUX4 GNSS TEST page ERR indication in FonTest windows on RICU display 2 2 034 50 00j Navigation task No navigation task solution RAIM parameter solution check AUX2 DATA GNSS page shall have NO value 3 1 034 50 00 Page 103 Dec 17 2009 4312 02 USER S MANUAL Fault Indication Scheme No BPIU display indication for more than one minute after the equipment start by pressing ON OFF button on RICU Checkup of the voltage availability on X5 1 3 and 6 4 cable connectors connected to RICU X1 connector Voltage limits 24 30 V yes Replace Check up voltage on UPS 2 connector 1 3 6 4 contacts Voltage range is from 24 V to 30 V Check up voltage the cable X1 Examine the cable connecting UPS with connector 1 3 and 6 4 contacts RICU visually fo
69. S 6 maintenance after 600 and equum 6000 operation hours at calendar maintenance Irem MS Generation test of Selected 034 50 00k after 12 and after repair roll and Z signals At the first installation in the aircraft after 600 and 6000 operation hours at calendar 1 RAM extended test Item MS maintenance after 12 and 48 months and after 034 50 00i repair Equipment test in Self FS 8 control mode Reception Before each flight Item MS test of navigation parameters 034 50 00a 034 50 00 Page 211 212 Dec 17 2009 600c Ll 99d EIZ osed 007057720 Flow Sheet 3 MS Item 034 50 00b MS Flow Sheet 3 On pages 213 217 MS Item Operation Work Content 0 4 man hour 034 50 00b Operability extended testing Operation and Technical Requirements TR 1 General Recommendations For the equipment workability extended test NSC signals consistent reception with minimal elevation angles 5 shall be provided Equipment workability extended test on the aircraft shall be performed as follows switch on the equipment power supply on the airborne power board press ON OFF button in RICU As soon as NDB indication form appears on the display press ENT button 2 Keyboard test For keyboard test set AUX4 page press CRSR button set lighting on KEYBOARD TEST field and press ENT button Keyboard Test window shall appear on RICU display W
70. SER S MANUAL Site for enclosure and receiver and control unit RICU installation in aircraft E 5 F E A A hole in control panel for installation hs e T 0 2 D Enclosure Enclosure mounting surface mounting surface F F 4x 40 0 2 160 0 2 Figure H 1 page 4 of 5 034 50 00 Appendix H Page 4 Dec 17 2009 4312 02 USER S MANUAL E E 4 4 40 0 2 160 0 2 1690 2 T 02E Figure H 1 page 5 of 5 034 50 00 Appendix H Page 5 6 Dec 17 2009 4312 02 USER S MANUAL AIRBORNE EQUIPMENT OF SATELLITE NAVIGATION APPENDIX I reference UPS installation in aircraft In fig UPS mounting method in aircraft is shown since serial Ne 6516057 For UPS before serial Ne b516056 inclusive mounting method is similar to that one shown in fig I 1 23 10 18 1 plug TEO 364 241 23 10 18 1 socket ground stud tip i OCT 92 0528 70 10 Figure 1 1 page 1 of 3 034 50 00 Appendix I Page 1 Dec 17 2009 034 50 00 Appendix I Page 2 Dec 17 2009 CH 43 12 02 USER S MANUAL CHII23 10 18B 1 B plu 364 241 18 23 10 18 6 s
71. T pop up window will be displayed in Test VOR DME window set the highlighting in CTRL field Press ENT button set the highlighting in ON OFF field Rotate shaft encoder internal knob for one position SELECT pop up window will display in Test VOR DME window set the highlighting in ON field for communications test with navigation and landing system press ENT button switch the flight navigation instrument connected to navigation and landing system into operating mode from VOR ILS observe arrow position change of the current azimuth A in flight navigation instrument The arrow of the current azimuth should be set sequentially into position of 135 0 225 on the scale of flight navigation instrument Indicated test is valid for navigation and landing system KYPC 93M Using other navigation and landing systems the control should be maintained according to applied system documentation Instruments Tools and accessories Expendables TVONVW 6 50 6002 1 99d LTZ Sed 007057720 Flow Sheet 6 Item MS 034 50 00k MS Flow Sheet 6 Pages 227 229 Item MS Operation Work control 0 4 man hour 034 50 00k Shaping test of aircraft light panel control signals produced by the equipment Generation test of Selected roll and Z signals Works performed with TR Contr Operation and Technical Requirements TR deviations ol 1 Test shall be performed on aircraf
72. The form pages should be overviewed rotating the shaft encoder handle clockwise or counterclockwise 034 50 00 Abbreviation List Page 4 Dec 17 2009 4312 02 USER S MANUAL Window part of the form page indicated simultaneously on RICU display Flight Path spatial track desired or true circumscribing by the airplane mass center during its movement Form range of parameters indicated on the RICU display after the corresponding button pressing on RICU Way point navigation point or waypoint where the flight is directed Nonvolatile parameters parameters whose last settings are saved when the equipment power supply is on off 034 50 00 Page 5 6 Abbreviation List Dec 17 2009 4312 02 USER S MANUAL This User s Manual involves 461513 077 02 code CH 4312 02 hereinafter referred to as equipment airborne equipment of satellite navigation purposed for operation in civil airplanes and helicopters included into the radioelectronic aircraft equipment with information interchange digital lines By means of this User s Manual Customer shall learn main specifications principle and rules of equipment operation User s Manual consists of two parts Airborne equipment of satellite navigation User s Manual Technical Maintenance Part 1 461513 077 02 Airborne equipment of satellite navigation User s Manual Operator s Guidance Part 2 461513
73. U removal from the aircraft within the following scope Removal of equipment components from aircraft FS 1 Check of high frequency connector pins and sockets FS 11 Installation of equipment components in aircraft FS 2 Inspection of 101 antenna radio transparent radome and unit appearance FS 9 Check of nut tightening and locking in connectors Earthing quality check FS 10 RAM extended test FS 7 Operability extended testing FS 3 Test of navigation task solution FS 4 Altimeter and heading system communications test Two RICUs interaction test Communications test with MFD Communications test with airborne range finder Communications test with navigation and landing system FS 5 Calendar maintenance shall be performed after 12 months within the periodical technical maintenance after 600 running hours Calendar maintenance shall be performed after 48 months within the periodical technical maintenance after 6000 running hours 034 50 00 Page 203 Dec 17 2009 Removal and Installation CH 43 12 02 USER S MANUAL This sub section includes technique and sequence of the equipment removal and installation in the aircraft and includes Flow Sheets 1 and 2 a FS 1 Removal of equipment components from aircraft meets MS 034 50 00d b FS 2 Installation of equipment components in aircraft meets MS 034 50 00f FS 1 and FS 2 provide the equipment removal and installat
74. a installation please consider 1 101 antenna shall be installed on the fuselage surface in airplane longitudinal axis 2 101 antenna shall be installed so to provide optimal overview in the upper hemisphere 3 101 antenna shall not be installed close to the airplane metal extensions that may impede the antenna visibility 4 there shall be no radiating antennas in immediate vicinity with 101 antenna especially within the operating frequencies range of the latter 5 during A101II antenna installation all necessary measures shall be taken for its protection against static electricity 6 rubber gasket from T IIIK 468911 020 02 installation kit shall be used for 101 antenna fastening closure 7 A101II antenna shall be installed in the places where its minimal icing 1s guaranteed e during UPS installation consider that length of the cable connecting UPS and RICU shall not exceed 5 m f UPS and LNA SSF operational position is free g X9 connector Process CH see Appendix 23 10 18 2 socket from installation kit shall be installed where it shall be easy available during equipment software replacement on the aircraft board 034 50 00 Page 38 Dec 17 2009 4312 02 USER S MANUAL Units Assemblage The equipment units electrical assemblage on the aircraft shall be performed in accordance with electrical connections scheme given in Appendix A The equipment units interconnection and
75. al deviation from runway axis m Y is a distance from runway threshold m Switch on ERLA signal is generated The equipment control and data insert are made by controls placed on RICU front board RICU receives the information from the route and airspeed airborne systems and on the ground of the received information makes the wind conditions calculations With automatic mode of aircraft control AUTOPILOT if the equipment is connected to ACS Selected roll signal is delivered to ACS for flight on DT With manual mode of aircraft control a pilot shall adjust the heading on the ground of information concerning deviation from DT received by CDI scale on RICU display If during the en route flight or DIRECT ON mode flight at the automatic mode of the airplane control AUTOPILOT the SNS signals are lost the equipment shall perform the navigation parameters automatic reckoning in accordance with the information from the plane course and speed sensors taking into consideration the last stored wind conditions The reckoning time shall be changed depending on the aircraft flight stage and speed The navigation parameters automatic reckoning shall stop in the case of the integrity signalization threshold coordinates definition accuracy crossing UPS must provide the equipment no break power supply during short time breaks in voltage supply of airborne mains with nominal voltage of 27 V 034 50 00 Page 15 Dec 17 2009 4
76. ane 116 1 25 Desired heading 100 E 1 16 Desired track angle 114 1 23 Desired magnetic track angle 057 E 1 23 Altitude over geoid 0768 E 1 15 HDOP 101 E 1 17 VDOP 1028 1 18 True path angle 103 E 1 19 Current latitude 1103 E 1 20 Current longitude 111 1 20 034 50 00 Appendix 7 Dec 17 2009 4312 02 USER S MANUAL Ground speed 112 1 21 Navigation information which is output via channels 0 1 and 3 during 100 millisecond period valid at the time specified by 260s 150s 140s The start of navigation data package navigation data package means words output in one 100 millisecond cycle in channel 3 is 0764 word All words from 0764 to 100g meet the time indicated in 150 140g words sent in this package E 1 6 Word structure output by the equipment according to ARINC 429 State matrix of words output and received by the equipment according to ARINC 429 are given in tables E 1 5 E 1 6 E 1 7 Word structure output by the equipment according to ARINC 429 is given in tables E 1 8 E 1 59 Identifier in output words digits 9 10 1 means operation from the 1 RICU 2 means operation from the 274 RICU Table E 1 5 State matrix BC Bit 31 30 Value 0 Failure warning 0 0 1 No calculated data 1 0 Functional test 1 1 Normal operation Table E 1 6 State matrix BDC
77. arameters may not meet to the required values Defects can be both of mechanical defect fastening destroyed parts bundles and cables defect insulation open circuit etc and electrical origin equipment radio elements breakage Mechanical defects are detected by detailed examination of units and connectors by test of chains insulation and metallization bares integrity Built in control system provides with electrical defects detection Aircraft Equipment Fault Indication and Troubleshooting Fault indication scheme is organized as a logical tree of troubleshooting sequential operation Each scheme has its code written on the right of the failure symptom formulation The defect unit search is explained on the example as follows E g no indication on RICU display when the equipment is switched on by pressing ON OFF button on RICU In accordance with the Table 101 troubleshooting is performed in accordance with scheme 1 1 Checkup of the voltage availability on X5 cable connector connected to RICU 1 connector If the test result on the no branch is negative the further scheme for troubleshooting is given In the case of the positive result on yes branch the command for RICU replacement shall be given During the troubleshooting in the aircraft accurate up to a unit check up the cables connecting the equipment units visually and as for their integrity in accordance with the electrical connections diagram
78. articipate in algebraic binary addition This means that bit carry to the 21 bit is ignored 3 Check sum shall be calculated as a supplement on two of the 21 bit word of the binary sum received SUM except special case when SUM 2097152 being this check sum 034 50 00 Appendix E Page 17 Dec 17 2009 4312 02 USER S MANUAL Table E 1 23 Desired track angle Desired magnetic track angle word structure Bit No Information content Bit coding 1 8 Address 114 01 001 100 057 00101111 9 10 Identifier 00 all 01 71 10 2 11 not used 11 16 Reserved Zero 17 28 Significant part is Range 180 12 bits m s bit 28 90 Negative values are transmitted in additional code 29 Sign 0 from 0 to 180 1 from 180 to 360 30 31 Status matrix In accordance with Table E 1 5 22 Parity 0 if sum of ones is odd number if sum of ones is even number Table E 1 24 Azimuth to WPT word structure Bit No Information content Bit coding 1 8 Address 115s 01 001 101 9 10 Identifier 00 all 01 1 10 2 11 not used 11 16 Reserved Zero 17 28 Significant part is Range 180 12 bits m s bit 28 90 Negative values are transmitted in additional code 29 Sign 0 from 0 to 180 1 from 180 to 360 30 31 State matrix In accordance with Table E 1 5 32 Parity 0 if sum of ones is odd n
79. ations rol rotating the shaft encoder external handle enter the second window of the equipment background test FonTest 2 to review test results If test is OK then in test results indication fields in FonTest 1 and FonTest 2 windows OK shall be seen If ERR indication appears this is the evidence of some functional module defect Instruments Tools and accessories Expendables TVONVW 6 50 CO CI Y HO 600Z LI 994 612 99 4 007067720 Flow Sheet 4 Item MS 034 50 00j MS Flow Sheet 4 On pages 219 220 Item MS Operation Work Content 0 4 man hour 034 50 001 Test of navigation task solution Works performed with TR Contr Operation and Technical Requirements TR deviations ol To have consistent reception of NSC signals maximum upward visibility should be provided This check should not be performed in a room To do the test of navigation task solution switch on the equipment on the airborne power supply unit press ON OFF button on RICU As soon as NDB indication form appears on the display press ENT button execute an operation of user position coordinate determination during 30 minutes make sure that generated coordinates are valid for this check the value of RAIM control function in DATA GNSS box of AUX2 page N TVONVW SAYASA CO CI Y HO 600c LI 99d Occ oed 000 lt 0 Flow Sheet 4 Item MS 034 50 00j Continuation Operation and Technica
80. c 10 000 101 9 10 Identifier 00 all 01 21 10 22 11 not used 11 12 Reserved Zero 13 28 Significant part is Range 4 096 14 bits m s bit 28 2 048 29 Sign Zero 30 31 State matrix In accordance with Table E 1 5 32 Parity 0 if sum of ones is odd number if sum of ones is even number 034 50 00 Appendix E Page 42 Dec 17 2009 4312 02 USER S MANUAL Table E 2 11 Outside air temperature word structure Bit No Information content Bit coding 1 8 Address 213sc 10 001 011 9 10 Identifier 00 all 01 1 10 2 11 not used 11 17 Reserved Zero Range 512 C 13 28 Significant part is m s bit 28 256 C 14 bits Negative values are transmitted in additional code 29 Sign Zero 30 31 State matrix In accordance with Table E 1 5 32 Parity 0 if sum of ones is odd number 1 if sum of ones is even number 034 50 00 Appendix E Page 43 44 Dec 17 2009 4312 02 USER S MANUAL AIRBORNE EQUIPMENT OF SATELLITE NAVIGATION APPENDIX F reference 101 Antenna LNA SSF and process connector installation in aircraft Screw B2 M5 6gx20 21 GOST 17473 80 Nut M5 6H 21 GOST 5916 70 Washer 5 30X13 GOST 6402 70 Washer 5 21 GOST T 754114 007 Gasket ES E LO LO Mounting surface Socket Bulkhead 50 Ohm Multicomp Tube PA
81. cation and Troubleshooting 101 Failure Symtoms uae ov eo Gee 103 Fault Indication Scheme 104 Maintenance Technique 201 Maintenant l tasas eet es 202 Removal and 204 FS 1 Removal of equipment components from 205 FS 2 Installation of equipment components in 207 Adjustment and 211 FS 3 Operability extended 213 FS 4 Test of navigation task 219 FS 5 Altimeter and heading system communications test Two RICUs interaction test Communications test with MFD Communications test with airborne range finder Communications test with navigation and landing 221 FS 6 lt Shaping test of aircraft light panel control signals produced by the equipment Generation test of Selected roll Z signals gt 227 034 50 00 Table of Contents Page 1 Dec 17 2009 4312 02 USER S MANUAL FS 7 RAM extended FS 8 Equipment test in Selfcontrol
82. commands receive channel 27 V short 8 circuit break One time commands receive channel enclosure short 8 circuit break Maximal One time commands delivery channel enclosure short g commutation circuit break current 200 mA Maximal One time commands delivery channel 27 V short g commutation circuit break current 100 mA Analog information delivery channel 150 MV 3 Current outputs Analog information delivery channel 10 V 1 Serial asynchronous ports RS 232 4 RS 422 2 automatic correction of aircraft current position using data of a radio range finder DME and omnidirectional radio beacons VOR SID STAR APPROACH procedures using the navigation database developed in accordance with procedures described in KT 200A displaying on RICU display flight route with displaying of navigation references route displaying indication is possible when the route is oriented in the northern direction or by desired path angle or actual path angle with the scale change graphical image of departure arrival and approach standard procedures route current segment operator selects between GLONASS or GPS working SNS with the selected SNS indication on RICU display The equipment operates by default on GLONASS GPS mixed SNS 034 50 00 Page 4 Dec 17 2009 4312 02 USER S MANUAL reckoning with navigation parameters characterization accuracy values delivery ASS
83. connection with the aircraft AE shall be performed through cables not included into the equipment set Cables shall be assembled at the units installation depending on the aircraft model the following requirements shall be considered at that a for TNC R143 008 000 and TNC R143 156 000 connectors assemblage a radio frequency cable shall be used with specification as below 1 inner conductor diameter 1 0 0 1 mm 2 diameter over insulation 3 0 0 2 mm 3 cable outer diameter from 4 mm to 5 mm It is recommended to use PK 50 3 23 radio frequency b oscillation damping in the high frequency cable from 101 antenna to LNA SSF shall not exceed 0 6 dB on 1600 MHz frequency c oscillation damping in the high frequency cable from LNA SSF to RICU shall not exceed 10 dB on 1600 MHz frequency For cable assemblage make the counterparts soldering included into IK set of UPS X2 connectors CHII 23 10 18P 6 B sockets and CHII 23 10 18B 6 B plugs in accordance with Connection Layout see Appendix A make the counterparts soldering included into IK set of RICU X1 X2 X3 X4 connectors CHII 23 10 18P 6 B sockets CHII 23 41 30P 6 B sockets CHII 23 41 30P 6 a B sockets CHII 23 41 30P 6 6 B sockets in accordance with Connection Layout see Appendix A make the 23 10 18 2 socket soldering included into IK set X9 process connector in accordance with Connection Layout see Appe
84. consists of 101 antenna LNA SSF Receiver indicator and control unit Uninterruptible power supply For equipment functional diagram see Fig 1 For equipment Connection Layout see Appendix A For units appearance and dimensions that are included into the equipment see Appendix B Appendix C and Appendix D Equipment 101 Antenna I I I I I I I LNA SSF I I I I I Amplifier Excitation Light signal Speed Suns display altitude RICU I gn ASPMS ARINC 429 I Navigation I parameters MFD TAWS 1 ARINC 429 Course AHS i ARINC 429 DT deviation approach descent 150 mV FNI I Selected roll 10 V ARINC 429 ACS DC airborne I mains 27V UPS I Ly un I Figure 1 034 50 00 Page 12 Dec 17 2009 4312 02 USER S MANUAL 101 antenna receives signals from GLONASS GPS SNS within the frequency range from 1570 to 1610 MHz Received signals are enhanced in 101 antenna and transferred for further processing to LNA SSF LNA SSF enhances signals coming from 101 passive antenna makes separate GLONASS and GPS SNS signal filtering From LNA SSF signals via the high frequency cable are transmitted to RICU input RICU processes the received signals and selects the useful information The selected information is processed in the navigation processor the results of definition are indicated on RICU display and is
85. contacts purpose Contact Circuit Signal GND Common One time command 0 common output 1 2 RKO OUT OFFSET 3 RK1 OUT One time command 1 common output 4 GND Common 5 GND Common 6 WPT One time command 2 common output 7 One time command 3 common output 8 SNS availability One time command 4 common output 9 ACTV One time command 5 common output 10 Reserved Free 11 1_ Reserved Free 12 One time command 6 common output 13 RK7_OUT Switch on ERLA One time command 7 common output 14 RK8 OUT Ek availability reserved One time command 8 27 V output RK9 OUT Eg availability reserved One time command 9 27 V output RK10 OUT Z availability One time command 10 27 V output op Bo op Common 19 Selected roll availability One time command 11 27 V output 20 Close RB reserved One time command 12 27 V output 21 Far RB reserved One time command 13 27 V output 22 One time command 14 27 V output 23 ARM One time command 15 27 V output m Common 25 Common 26 Analog common 27 Channel 1 150 mV analog output 28 Reserved Free 29 Channel 2 150 mV analog output 30 Analog common 5 op Common x op Common 5 Analog common 34 A3 OUT Z Signal Channel 3 150 mV analog output 35 4 OUT Selected roll signal Chan
86. crafts equipped with radio communication satellite systems As for interference generation and interference susceptibility except antenna the equipment corresponds to 8 1 4 1 requirements by 17 27 3Z rigidity categories The equipment shall correspond to KT 160D requirements regarding susceptibility to audio frequency interference coming through power supply inputs J category of rigidity susceptibility to induction interference exposed through the communication wiring in the equipment enclosure C category of rigidity radio frequency susceptibility W category of rigidity radio frequency energy emanation susceptibility H category of rigidity transient processes susceptibility caused by lighting category of rigidity By lightening direct action the antenna corresponds to 2B category KT 160D requirements Equipment Units For equipment units see Table 2 Table 2 Unit Code Quantity Receiver indicator and control unit 467855 039 1 101 Antenna 464656 005 1 pe LNA SSF AIIMA 4348 16 034 1 pe Uninterruptible power supply 436434 006 1 pe Installation kit 468911 020 02 1 set Operation and maintenance documents 461513 077 02 1 set Packing 305642 048 01 1 set 034 50 00 11 Dec 17 2009 4312 02 USER S MANUAL Operation Principle The equipment
87. ction 0 clockwise 1 counterclockwise 12 13 Reserved Zero 14 28 Significant part is Range 180 15 bits m s bit 28 90 Negative values are transmitted in additional code 29 Sign 0 from 0 to 180 1 from 180 to 360 30 31 State matrix In accordance with Table E 1 5 32 Parity 0 if sum of ones is odd number if sum of ones is even number 034 50 00 Appendix E Page 34 Dec 17 2009 4312 02 USER S MANUAL Table E 1 56 Arc radius word structure Bit No Information content Bit coding 1 8 Address 331 11 011 001 9 13 Reserved Zero 14 28 Significant part is Range 256 NM 15 bits m s bit 28 128 NM 29 Reserved Zero 30 31 State matrix In accordance with Table E 1 5 32 Parity 0 if sum of ones is odd number 1 if sum of ones is even number Table E 1 57 Angle of arc course change word structure Bit No Information content Bit coding 1 8 Address 3328 11 011 010 9 13 Reserved Zero 14 28 Significant part is Range 180 15 bits m s bit 28 90 Negative values are transmitted in additional code 29 Sign 0 from 0 to 180 1 from 180 to 360 30 31 State matrix In accordance with Table E 1 5 32 Parity 0 if sum of ones is odd number if sum of ones is even number Table E 1 58 Remaining distance to destination WPT word structure
88. e storage unit can store two NDBs Expiration date for both NDBs is shown in NDB indication form in ACTIVE and SECOND fields Figure 6 To change active NDB for the second database the procedure is as follows when NDB indication form is indicated display press MENU button PAGE MENU popup window shall be indicated in NDB indication form as shown in Figure 11 HANGE DATABASES Figure 11 press ENT button to confirm NDB change RICU display shall indicate NDB indication form in accordance with Fig 6 The second NDB shall be indicated instead of the active NDB 034 50 00 Page 45 Dec 17 2009 4312 02 USER S MANUAL Equipment Factory Settings The equipment system parameters factory settings are demonstrated on Figure 12 AUX3 page SETTING window Parameters units of measuring system UNITS coordinate system DATUM magnetic declination consideration MAG message delivery language LANGUAGE are nonvolatile parameters All GLONASS and GPS satellites are on for use Figure 13 2 USE USE USE USE USE USE USE USE USE Figure 12 Figure 13 Figure 14 shows factory settings of display and keyboard lighting brightness page AUX3 window BRIGHTNESS Display and keyboard highlight brightness parameters are nonvolatile parameters DISPLAY KEYBOARD Figure 14 Figure 15 AUX3 page LIMIT DATA window shows factory settings of SID STAR APPROACH standard procedures parameters
89. eakage 34 IN L 2 RICU identifier One time command 2 GND input 0 breakage 1 GND short circuit 35 INL3 One time command 3 GND input 36 IN L 4 Exchange parameters One time command 4 GND input 37 IN L 5 identifier One time command 5 GND input 38 IN L 6 0 breakage One time command 6 GND input 39 IN L 7 1 GND short circuit One time command 7 GND input 40 INLS One time command 8 GND input 41 12 OUT Pendant power supply 12 V output Exchange parameters identifier a if IN H 2 IN H 5 IN L 4 IN L 7 are set on 0 then information delivery rate in is 12 5 Kbit s if IN L 415 set on 1 IN H 2 IN H 5 IN L 5 IN L 7 set on 0 then information delivery rate in is 100 Kbit s RICU identifier a if IN L 215 set at 0 beak tha 0 is set in a bit of 9 words issued according to ARINC 429 if IN L 2 is set at 1 fault to GND then 1 is set in a bit of 9 words issued according to ARINC 429 b i IN L 3 is set at 0 break then 0 is set in a bit of 10 words issued according to ARINC 429 if IN L 3 is set at 1 fault to GND then 1 is set in a bit of 10 words issued according to ARINC 429 034 50 00 Page 22 Dec 17 2009 4312 02 USER S MANUAL Time Marker Signal Time marker signal synchronized with UTC time scale shall be brought out to RICU s connector X
90. er 27 PLM TX5 Channel 5 RS 232 transmitter Free 29 AR AO OUT See paragraph E 1 2 of Channel 0 ARINC 429 line A output 100 KHz 30 AR B0 OUT Channel 0 ARINC 429 line B output 100 KHz 31 GND Com 32 GND 11 Como 33 AR AI OUT Channel 1 ARINC 429 line A output 100 KHz 34 AR OUT Appendix E Channel 1 ARINC 429 line B output 100 KHz 35 AR A2 OUT See paragraph 1 4 of Channel 2 ARINC 429 line A output 12 5 KHz 36 AR B2 OUT Channel 2 ARINC 429 line B output 12 5 KHz 37 OND Common 38 GND OUT e S x07 1 l Common 39 AR A3 OUT See paragraph E 1 5 of Channel 3 ARINC 429 line A output 40 AR B3 OUT Channel 3 ARINC 429 line B output 41 ENCLOSURE Enclosure 034 50 00 Page 20 Dec 17 2009 4312 02 USER S MANUAL Table 6 X4 connector contacts purpose Contact Circuit Signal Purpose 1 GND 2 Course system Channel 0 ARINC 429 line A input 100 KHz 3 AR BO IN 55 2 or LCR 93 Channel 0 ARINC 429 line B input 100 KHz Hydromagnetic heading word 320 s op _ eomm 6 AR IN ASPMS Channel 1 ARINC 429 line A input 12 5 ASPMS 140 01 2 KHz 7 AR BI IN Has word 203s Channel 1 ARINC 429 line B input 12 5 word 210 KHz 8 AR A2 IN CDM 94 75 Channel 2 ARINC 429 line A input 100 KHZ 9 AR B2 IN Adjusting frequency word Channel
91. er Supply Uninterruptible power supply 436434 006 purpose is to maintain the equipment performance during any short term voltage supply interruptions and to protect the equipment against any voltage surge Uninterruptible power supply includes the following devices and functional units input filter control circuit energy storage charger energy storage system voltage transducer switch Uninterruptible power supply operation As soon as voltage is supplied the control circuit switches on the energy storage charger Storage charger can be charged up to 20 V maintained this voltage during all operation time Upon reception the command from RICU the control circuit by means of the switch shall connect input voltage for the equipment power supply system In the case if input voltage drops voltage supply depression under 18 V the control circuit shall switch on the voltage transducer which uses the accumulated energy transmitting it through the switch for the equipment energizing 034 50 00 Page 32 Dec 17 2009 4312 02 USER S MANUAL UPS Specifications UPS Specifications are given in the Table 8 Table 8 Value Parameter specification 1 Input voltage V 18 33 2 Input current A max 2 3 Output voltage at operation from DC airborne mains V 1 4 Output voltage at operation from reserved source V 18 1 5 Output voltage ripple
92. erminated NDB indication shall be indicated on RICU display See Figure 6 for NDB indication form view 034 50 00 Page 41 Dec 17 2009 4312 02 USER S MANUAL NAV DATABASES 1 Active NDB 2 Second NDB 3 List of active NDB regions Note NDB indication form in the list of active NDB regions except the regions guaranteed by the Agreement of NDB supply the bordering are also indicated Figure 6 press ENT button to confirm work with the set active NDB change NDB if necessary and then press ENT button NDB initialization form shall be indicated on RICU display See Figure 7 for NDB initialization form Simultaneously with NDB initialization form indication NDB initialization is performed INITIALIZATION Figure 7 upon completion of NDB initialization progress strip indication is 100 9 DATA GNSS window of AUX2 page will be displayed in RICU display Figure 8 DATA GNSS window is displayed until coordinates will be received from GNSS receiver GNSS flag is displayed in the flag field of reference coordinate NP receiving and then NAVI page is displayed 034 50 00 Page 42 Dec 17 2009 4312 02 USER S MANUAL Figure 9 Failing coordinates from GNSS sensor the transfer to other data cards is performed by the operator N e P d 1 Flag of reference coordinate NP receiving Figure 8 Figure 9 If messages are available upon completion of NDB initialization
93. ero 30 31 State matrix In accordance with Table E 1 5 32 Parity 0 if sum of ones is odd number 1 if sum of ones is even number 034 50 00 Appendix E Page 14 Dec 17 2009 4312 02 USER S MANUAL Table E 1 19 True track angle Magnetic track angle Magnetic heading word structure Bit No Information content Bit coding 1 8 Address 103 01 000 011 317 11001111 320 11010000 9 10 Identifier 00 all 01 1 10 2 11 not used 11 13 Reserved Zero 14 28 Significant part is Range 180 15 bits m s bit 28 90 Negative values are transmitted in additional code 29 Sign 0 from 0 to 180 1 from 180 to 360 30 31 State matrix In accordance with Table E 1 5 32 Parity 0 if sum of ones is odd number 1 if sum of ones is even number Table E 1 20 Current latitude Current longitude word structure Bit No Information content Bit coding 1 8 Address 110 01 001 000 1118 01001001 9 28 Significant part is Range 180 20 bits m s bit 28 90 Negative values are transmitted in additional code 29 Sign 1 South West 0 North East 30 31 State matrix In accordance with E 1 5 32 Parity 0 if sum of ones is odd number if sum of ones 15 even number 034 50 00 Appendix E Page 15 Dec 17 2009 Table E 1 21 Ground speed word structure
94. even number Table E 1 14 Active route leg word structure Bit No Information content Bit coding 1 8 Address 075 00 111 101 9 Mode manual 0 automatic always 0 10 Fly over with preset true angle 0 magnetic always 1 11 Reserved Zero 12 Coordinates azimuth distance 0 longitude latitude always 0 13 16 Most Significant part is Tens of WPT number to which aircraft flies 17 20 Most Significant part is Tens of WPT number from which aircraft flies 21 24 Least Significant part is Ones of WPT number to which aircraft flies 25 28 Least Significant part is Ones of WPT number from which aircraft flies 29 Reserved Zero 30 31 State matrix In accordance with Table E 1 6 32 Parity 0 if sum of ones is odd number if sum of ones is even number 034 50 00 Appendix E Page 12 Dec 17 2009 4312 02 USER S MANUAL Table E 1 15 Height above geoid word structure Bit No Information content Bit coding 1 8 Address 076 00 111 110 9 28 Significant part is Range 131072 feet 20 bits m s bit 28 65536 feet Negative values are transmitted in additional code 29 Sign 1 negative value of altitude 0 positive value of altitude 30 31 State matrix In accordance with Table E 1 5 32 Parity 0 if sum of ones is odd number if sum of ones is even number
95. evious to PROC form call RNG and RNG buttons RNG u RNG buttons are designed for change the indicated graphic data scale Button D Button B is designed for provide DIRECT TO mode flight to the desired WP AUX Button AUX button is designed for transit into AUX form Repeated pressing of AUX button shall return the form previous to AUX form call MENU Button MENU Button is designed for call PAGE MENU popup related to the form active page The button shall provide the selection of supplementary operations of the active page or for the current page settings Repeated pressing of MENU button shall close PAGE MENU popup WPT Button WPT Button is designed for transit to the database form Repeated pressing of WPT button shall return the form previous to WPT form call CLR Button CLR button is designed for refusing editing returning from the window to the correspondent form page and closing PAGE MENU popup 034 50 00 Page 27 Dec 17 2009 4312 02 USER S MANUAL ENT Button ENT Button is designed for confirming the entry of the typed information confirming the certain action execution or moving lighting to the next editing parameter CRSR Button CRSR Button is placed on the shaft encoder internal handle edge It is designed for activation deactivation of parameter indication field in the form window or page editing refusal return from the window to the correspondent form page and PAGE MENU popup closing CRS
96. finder E22 affirmative character Distance beacon 202 Rangefinder E 23 Barometric altitude Havs 203 AVPS 2 4 True airspeed Virue 210 AVPS E 2 5 Heading reception status word 270 Heading sensors E 2 6 heading 320 Heading sensors E 2 7 gyro semicompass heading Navigation landing system Navigation and 2 8 adjustment frequency 034 landing system affirmative character Magnetic azimuth 222 Navigation and E29 landing system Mach number 205g AVPS E 2 10 Outside air temperature 213 AVPS E 2 11 034 50 00 Appendix E Page 36 Dec 17 2009 4312 02 USER S MANUAL Table E 2 2 Beacon adjustment frequency affirmative character word structure Bit No Information content Bit coding 1 8 Address 035 00 011 101 9 10 Identifier 00 all 01 1 10 2 11 not used 11 13 Operating mode Bits 13 12 11 000 not used 001 frequency 1 010 frequency 2 011 frequency 3 100 frequency 4 101 frequency 5 110 free scanning 111 not used 14 15 Coding of adjustment frequency 00 paired with VOR pairing 16 201 word output 1 word is output 0 not available 17 Identification signal character 1 18 0 05 MHz 1 0 05 MHz 0 0 00 MHz 19 Tenths of MHz 0 1 MHz 20 0 2 MHz 21 0 4 MHz 22 0 8 MHz 23 Ones of MHz 1 MHz 24 2 MHz 25 4 MHz 26 8 MHz 2T Ten
97. g threshold In the case of automatic setting the integrity warning threshold shall be set in accordance with the flight stage 3 6 km for Route stage 1 8 km for Terminal Area stage 556 m for Approach stage in the case of non precision approach availability forecasting of RAIM function for navigation point shall be provided within 12 hours from the set time of calculation start with the desired pitch set by operator RAIM function availability forecasting shall be provided any time when the equipment has received the full almanac During the forecasting process NOTAM information may be used additionally relating the satellites status at the set time 034 50 00 Page 2 Dec 17 2009 4312 02 USER S MANUAL RAIM function availability forecasting for active route shall be provided within the route duration from the set time for en route traffic start time marker delivery with form and loading specifications corresponding to ARINC 743A 4 requirements pulse of 122 107 s period 1 00 0 01 ms duration 200 ns maximal rise and fall time between 0 1 and 0 9 maximal level values Leading edge of pulses of time marker is synchronized with UTC time scale providing with data continuous delivery exclusion of any possibility that incorrect data can be delivered when passing the 1024 reading GPS weekly cycle to the original status i e to the cycle Nr 0001 delivery for indication of additional parameters n
98. ight and arbitrary routes flight on the equipped unequipped airways day or night time by means of GLONASS and GPS navigation satellite systems control system delivery in ACS work with the standard worldwide and user s navigation databases alpha digital and graphical indication of aircraft information and operation modes airborne system centralized control of radio equipment VOR DME in automatic and manual modes navigation information formatting and delivery for its displaying on the aircraft instrumentation and on electronic system displays or multipurpose displays 034 50 00 Page 1 Dec 17 2009 4312 02 USER S MANUAL Performance Characteristics and Operating Conditions Intended Purpose Function The equipment shall provide with the intended purpose functions as follows automatic continuous in the true time at parking and in the flight navigation parameters detection by GLONASS GPS satellite radio navigation systems signals also using the information from the airborne equipment geographical coordinates of aircraft position aircraft geodetic altitude aircraft ground speed vector components ground speed path angle UTC scale time receiver autonomous integrity monitoring RAIM via HDOP VDOP HIL VIL HFOM and VFOM values calculation detection and elimination of failed navigation satellites signals FDE function automatic and manual setting of integrity warnin
99. ilability signal as DC voltage of 27 V nominal value on 1000 100 Ohm load specifying Selected roll analog signal availability TO FROM signal DC voltage of 27 V nominal value on 100045100 Ohm load specifying TO point direction RICU generates and delivers Second marker signal with 1 Hz frequency Signal specifications are given below at RICU description RICU generates and delivers control signals to the light alarm board in the case of impossibility of RAIM function performance RAIM signal parallel route movement OFFSET signal intermediate route point transition WPT signal warning or information message MSG signal when putting an aircraft on the first leg of APPROACH procedure signal is generated When canceling APPROACH procedure ACTV signal is turned off when an aircraft performs APPROACH procedure two miles before FAWP fly over ARM signal is generated When canceling APPROACH procedure or at missed approach ARM signal is turned off aircraft position in the airport area Airport area signal with navigation solution and positive results of testing SNS availability signal 034 50 00 Page 14 Dec 17 2009 4312 02 USER S MANUAL fulfillment of the following conditions for a selected terminal NA V5 page 400 lt H lt 1500 12000 lt Y lt 30000 lt 0 6 Y where H is aircraft altitude m X is later
100. ing 0 0 0 0 0 0 0 Search 0 0 0 0 0 0 24 28 SNS navigation 0 1 1 0 0 0 0 SBAS navigation 0 1 1 0 1 0 0 CBC navigation 1 1 0 0 0 0 0 DME DME navigation 1 1 1 0 0 0 0 VOR DME navigation 1 1 1 1 0 0 0 29 Number of used NSV most gt 15 significant bit 0 lt 15 In accordance with Table E 1 7 0 if sum of 1 is odd number 1 if sum of 1 is even number 034 50 00 Appendix E Page 28 Dec 17 2009 4312 02 USER S MANUAL Table E 1 44 Symbol 7 8 9 identifier Symbol 10 11 12 identifier word structure Bit No Information content Bit coding 1 8 Address 301 11 000 001 302 11 000 010 9 15 7 10 symbol 16 22 8 11 symbol 23 29 9 12 symbol 30 31 State matrix In accordance with Table E 1 5 32 Parity 0 if sum of 1 is odd number 1 if sum of 1 is even number Letter coding of WPT RB identifier is given in Table 1 45 Table 1 45 Symbol Symbol number in Bit No of output word number in Bit No of output word identifier identifier 1 4 7 10 9 1 4 7 10 9 2 5 8 11 16 2 5 8 11 16 3 6 9 12 29 28 27 26 25 24 23 3 6 9 12 29 28 27 26 25 24 23 A 1 0 0 U 1 1 0 0 W 1 1 X 0 F 0 Y 1 G 1 2 0 0 0 1 0 0 0 K 1 0 0 L 0 1 1 1 2 0 0 3 1 1 4 0 0 5 1 1 6 0 R 0 7 1
101. ion operations sequence in the aircraft These operations stages are shown in the Table 201 Table 201 Operation Operation Stage FS In the case of routine tests after 6000 running FS 1 Removal of equipment 4 components n s hours if necessary calendar maintenance 5 after 48 months if necessary after repair 034 50 00d ef eme At the first installation the aircraft at routine FS 22 aft tests after 6000 running hours calendar MS Item aa E maintenance after 48 months after repair 034 50 00f 034 50 00 Page 204 Dec 17 2009 6002 1 99d OZ 9 4 00705760 Flow Sheet 1 for MS item 034 50 004 MS Flow Sheet 1 Pages 205 206 MS Item Operation Work Content 1 0 man hour 034 50 00d Removal of equipment components from aircraft Works performed with Contr Operation and Technical Requirements TR TR deviations ol WARNING DE ENERGIZE 27 V POWER CIRCUIT ON THE AIRCRAFT POWER DISTRIBUTION UNIT BEFORE REMOVAL 1 RICU Removal For RICU removal perform the operations as follows unscrew and remove screws fastening enclosure to RICU front panel remove RICU out from the enclosure disconnect RICU earthing rod from the aircraft common earthing bar disconnect cables from RICU connectors install process covers on RICU connectors 2 101 Antenna removal For A101II Antenna removal perform the operations as follows
102. item Page AIRBORNE EQUIPMENT OF SATELLITE NAVIGATION 034 50 00 Description and 1 General OS dr ae riis La 1 Performance Characteristics and Operating 8 2 Equipment Units sagt e xe OUR NC a 11 Operation Principle ista oh d soe exo EM ue EP 12 Description e put ed a S 16 Receiver indicator and control unit 16 ALOU eda one P venio eee eee a eee sasa 29 Low Noise Amplifier with Signal Separate 30 Uninterruptible Power Supply 32 Installation it c coss uso t tbe MS sp notis 35 Operation sees Qe Vet eee tr AN S Up SOR RE CRN a HR 37 Equipment Units Installation and Mounting on 3T Equipment Start and Performance 41 Equipment Operating Modes General 48 Troubleshooting 101 General Instructions for Troubleshooting 101 Aircraft Equipment Fault Indi
103. ix the connectors install the brackets as shown on Fig F 2 Appendix F of this UM lock the connectors of LNA SSF with 0 3 12X18H9T safety wire and seal it check up LNA SSF fixing on the site 4 UPS installation For UPS installation perform the operations as follows Install UPS on the site and fix it with fastening bolts see figure 1 1 Appendix connect UPS earthing rod to the aircraft earthing bar remove process covers from UPS X1 X2 connectors connect cables to UPS X1 X2 connectors check up the earthing quality by measuring resistance between LNA SSF metallization surface and the earthing bar by means of E6 18 milliohm meter the resistance value shall not exceed fix LNA SSF with 4 screws and 4 nuts from the assemblage kit see figure F 2 Appendix F connect the high frequency cable X4 connector to LNA SSF BX connector the high frequency cable X6 connector to LNA SSF connector in correspondence with check up the earthing quality by measuring resistance between UPS earthing rod and the earthing bar by means of E6 18 milliohm meter the resistance value shall not exceed 2000 microohms Screwdriver 7810 0982 X9 Spanner 7811 0006 C1 X9 Instruments Tools and accessories Expendables Milliohm meter E6 18 Screwdriver 7810 0053 Wire 0 3 TR 2 722 015 Screwdriver 7810 0977 X9 12 18 9 Filler 0010 TVONVW 6 50 cO CIEP HO
104. ket included into IK and 18 cap included into IK installation on the aircraft is given on Figure F 4 Appendix F 18 cap installation included into IK installed on UPS X3 connector is given on Figure I 1 Appendix I Installation of equipment components in aircraft shall be performed in accordance with FS 2 RICU UPS earthing shall be performed by connection of earthing rod to the earthing bar Equipment units mounting and dismantling shall be performed in random sequence 034 50 00 Page 40 Dec 17 2009 4312 02 USER S MANUAL Equipment Start and Performance Test For equipment start and its performance test Switch on the equipment power on the aircraft standard power distribution unit INPUT indicator on UPS shall switch on Switch on the equipment by pressing ON OFF button on RICU at that OUTPUT indicator on UPS shall switch on NRST OBS MSG NAV FPL and PROC buttons lighting shall switch on and off in turn then background lighting of all buttons on the RICU front panel switches on as soon as Self control mode is successfully terminated start form is indicated on the RICU display See Figure 5 for the start form view During start form indication NDB test in the navigation database storage unit is performed Note Software version number and date on Figure 5 are given provisionally 1 Software version number 2 Software version date Figure 5 as soon as NDB test is t
105. l Requirements TR Works performed with TR deviations Contr ol RAIM control function may take the following values YES RAIM is accessible NO RAIM functions are lost The navigation task solution is performed correctly if during 30 minutes you have obtained a stable determination of position confirmed by RAIM control in RAIM control function indication field YES value is indicated Instruments Tools and accessories Expendables TVONVW 6 50 6002 1 99d IZZ 99894 007057760 Flow Sheet 5 Item MS 034 50 00c MS Flow Sheet 5 On pages 221 226 Item MS Operation Work control 0 2 man hour 034 50 00c Altimeter and heading system communications test Two RICUs interaction test Communications test with MFD Communications test with airborne range finder Communications test with navigation and landing system Works performed with TR Contr Operation and Technical Requirements TR deviations ol 1 Altimeter and heading system communication test Test is performed on aircraft board For altimeter and heading system communication test Switch on altimeter and heading system in accordance with FOM in aircraft connect the equipment power supply on the airborne power supply unit press ON OFF button on RICU As soon as NDB indication form appears on the display press ENT button open AUX2 page Set lighting on DATA SVS IRS W
106. light stage 000 GLONASS GPS 18 20 SNS type 100 GLONASS 010 GPS 21 24 GPS satellite number used in calculations GLONASS satellite 25 28 number used in calculations 29 Reserved 30 31 Status matrix In accordance with Table E 1 7 32 Parity 0 if sum of ones is odd number 1 if sum of ones is even number Note By default the following is set Enroute flight stage WGS 84 coordinate system GLONASS GPS SNS type 034 50 00 Appendix E Page 22 Dec 17 2009 4312 02 USER S MANUAL Table E 1 32 Vertical figure of merit VFOM word structure Bit No Information content Bit coding 1 8 Address 136 01011110 9 10 Identifier 00 all 01 1 10 2 11 not used 11 28 Significant part is Range 32768 feet 18 bits m s bit 28 16384 feet 29 Reserved Zero 30 31 State matrix In accordance with Table E 1 5 32 Parity 0 if sum of ones is odd number 1 if sum of ones is even number Table E 1 33 Current UTC precisely word structure Bit No Information content Bit coding 1 8 Address 140g 01 100 000 9 28 Significant part is Range 1s 20 bits m s bit 28 0 5s 29 Reserved Zero 30 31 State matrix In accordance with Table E 1 5 32 Parity 0 if sum of ones is odd number 1 if sum of ones is even number Table E 1 34 Magnetic declination word structure
107. mediately the equipment supplier Requirements for Units Installation To start the units installation in the aircraft take into consideration the following requirements a equipment units shall be installed in the areas specified in 1 Table 12 if the equipment shall be operated in an airplane 2 Table 13 if the equipment shall be operated in a helicopter Table 12 Units installation areas impose levels of Installation area Unit vibration test standards curve in in accord with accordance with KT 160D II8 1 2 3 RICU Instrumentation panels consoles gage boards 1 BIA UPS Fuselage C1A A LNA SSF Fuselage empennage group Z D Table 13 Units installation areas impose levels of Installation area Unit vibration test standards curve in in accord with accordance with KT 160D II8 1 2 RICU Instrumentation panels consoles gage b boards G UPS Fuselage G b LNA SSF Fuselage empennage group J D 034 50 00 Page 37 Dec 17 2009 4312 02 USER S MANUAL b equipment units shall not be installed 1 in areas containing explosives 2 in airplane efflux area c during RICU installation please consider 1 RICU shall be installed on the flight deck where its optimal operation is available 2 switch on the equipment when the temperature at RICU installation place is higher than 20 C d during A101II antenn
108. n Navigation Point Navigation Spacecraft Navigation Task On Condition Technical Maintenance Peripheral Control Unit Process Connector Quality Department Runway RICU RNAV RNP ROM RR SAR SARPs SBAS SC SD SDR SHF SNS SRNRS ST code SW TAWS TR TRTM UART UM UPS UTC VDOP VFOM VIL VOR VSWR WAAS WGS 84 WP CH 43 12 02 USER S MANUAL GNSS GPS Receiver Autonomous Integrity Monitoring Random Access Memory Radio Beacon Receiver and control unit Receiver indicator and control unit Area Navigation Required Navigation Performance Read Only Memory Radio Receiver Standard Arrival Route Standards and Recommended Practices Satellite Based Augmentation System Short Circuit Standard Deviation Standard Departure Route Superhigh frequencies Satellite Navigation System Short Range Navigation Radio System Standard Accuracy Code Software Terrain Awareness and Warning System Technical Requirements To Refusal Technical Maintenance Universal Asynchronous Receiver Transmitter User s Manual Uninterruptible power supply Universal Coordinated Time Vertical Dilution of Precision Vertical signals quality evaluation Vertical Integrity Limit VHF Omnidirectional Range radio beacon Voltage Standing Wave Ratio Wide Area Augmentation System US
109. navigation database storage updated each 28 days as agreed with the navigation database supplier 034 50 00 Page 237 238 Dec 17 2009 600c LI 99d OVZ 6ET 2994 000 6 lt 0 Flow Sheet 9 Item MS 034 50 006 MS Flow Sheet 9 Page 239 Item MS Operation 034 50 00g Inspection of 101 Antenna radio transparent radome and unit appearance Work control 0 2 man hour Operation and Technical Requirements TR Works performed with TR deviations Contr ol 1 Examine 101 antenna radio transparent radome external condition Clean the radome if dirty with dry cloth if very d detergent In the case of any cracks or chips on radome return A101II antenna to the manufacturing enterprise as provided by the normal procedure 2 Examine RICU UPS LNA SSF external condition The units shall have no mechanical damages irty wash it with warm water with domestic In the case of any mechanical damage repair the unit as provided by the normal procedure Instruments Tools and accessories Expendables Domestic detergent Cotton cloth TVONVW 6 50 600c LI 99d 2994 000 lt 0 Flow Sheet 10 MS 034 50 00h MS Flow Sheet 10 Page 241 Item MS Operation 034 50 00h Check of nut tightening and locking in connectors Earthing quality check Work control 0 3 man hour
110. ndix A Note For cable sealing in 23 connector contacts see Fig F 3 Appendix F perform the cable termination high frequency cable from A101II antenna to LNA SSF see Appendix A from one end for R143 156 000 RADIALL connector from another end for 034 50 00 Page 39 Dec 17 2009 4312 02 USER S MANUAL R143 008 000 RADIALL connector in accordance with provisions in the figure F 3 Appendix F of this Manual make the cable soldering and sealing into R143 156 000 RADIALL and R143 008 000 RADIALL connectors see figure F 3 Appendix F perform the cable termination HF high frequency cable from LNA SSF to RICU see Appendix A on both ends for R143 008 000 RADIALL connectors see Figure F 3 Appendix F make the cable soldering and sealing into R143 008 000 RADIALL connector see figure F 3 Appendix F Note At cable assemblage the due spare length of cables shall be provided for the possible three resolderings of connectors during the cable net maintenance fix the cables connectors PANDUIT HSTTA heat shrinkage tube shall guarantee their simultaneous fixing and sealing Note PANDUIT HSTTA heat shrinkage tube and TNC R143 156 000 R143 008 000 RADIALL plugs are included into 468911 020 02 IK 101 antenna LNA SSF RICU and UPS installation and assemblage on the aircraft are described in Appendix F Appendix G Appendix H Appendix I of this Manual Process connector CHII 23 10 18P 2 B soc
111. nel 4 10 V analog output 56 Analog common n op Common Lighting common 39 Lighting 5 V 40 Lighting 327 V 41 ENCLOSURE Enclosure 034 50 00 Page 19 Dec 17 2009 4312 02 USER S MANUAL Table 5 X3 connector contacts purpose Cont act Circuit Signal Purpose GND Common Common Channel 2 RS 232 receiver Channel 2 RS 232 transmitter Channel 1 RS 232 receiver Channel 1 RS 232 transmitter GNSS_RX2 GNSS_TX2 1 GNSS module port process 0 port PCU Arm7 process Common USB port positive output Process Channel 0 RS 232 receiver Channel 0 RS 232 transmitter Channel 4 RS 422 receiver direct input Channel 3 RS 422 receiver direct input RICU Channel 3 RS 422 receiver inverse input Inverse USB output USB port negative output reserved 18 USBGND OUT USB power supply USB port power supply common reserved 19 Connection with the second Channel 3 RS 422 transmitter direct output 20 PXA TX3 RICU Channel 3 RS 422 transmitter Inverse output 21 ZPLM 4 Reserved Channel 4 RS 422 receiver inverse input 22 PLM 4 Reserved Channel 4 RS 422 transmitter direct output 23 ZPLM TX4 Channel 4 RS 422 transmitter inverse output 24 USB VCC OUT USB power supply USB port power supply output reserved 25 GND Common 26 5 Reserved Channel 5 RS 232 receiv
112. ng 100 BC E 1 16 Azimuth of point 115 BC E 1 24 Horizontal deviation from DT 116 BC 1 25 Time UTC 125 BDC E 1 29 Magnetic declination 147 BC E 1 34 Current Greenwich time 150 BDC E 1 35 Remaining distance to the current WPT 251 BC E 1 40 Flight time to the next WPT 252 BC E 1 41 Date 260 BDC E 1 42 Current latitude 310 BC E 1 49 Current longitude 311 BC E 1 49 Ground speed 312 BC E 1 50 Path angle true 313 BC E 1 51 Magnetic heading 320 1 19 Angle of drift 321 BC E 1 16 LCTD scale 326 BC E 1 54 Remaining distance to the destination WPT 351 BC E 1 58 Time to go to the destination WPT 352 BC E 1 59 034 50 00 Appendix E Page 3 Dec 17 2009 4312 02 USER S MANUAL Background information includes the main navigation point specifications of flight plan All background information is integrated into the background information unit BIU In its turn background information unit is divided into a series of sentences each of which provides the information of a certain navigation point WPT RB etc Word list which can be used for BIU sentence forming are given in Table E 1 3 Table E 1 3 Parameter Address Table Note octal number Data record header 074 BC E 1 13 Active leg of the route 075 BDC E 1 14 Check sum 113 BC 1 22 Identifier 7 8 9 symbols 301 144 WP RB identifier Identifier 10 11 12 symbols 302 BC 2
113. number 034 50 00 Appendix E Page 25 Dec 17 2009 4312 02 USER S MANUAL Table E 1 39 Horizontal figure of merit HFOM word structure Bit No Information content Bit coding 1 8 Address 247 10 100 111 9 10 Identifier 00 all 01 1 10 2 11 not used 11 28 Significant part is Range 4096 NM 18 bits sen bit 28 2048 NM 29 Sign Zero 30 31 State matrix In accordance with Table E 1 5 32 Parity 0 if sum of ones is odd number if sum of ones is even number Table E 1 40 Distance remaining to the next WPT word structure Bit No Information content Bit coding 1 8 Address 251 10 101 001 9 10 Identifier 00 all 01 1 10 2 11 not used 11 13 Reserved Zero 14 28 Significant part is Range 4096 NM 15 bits m s bit 28 2048 NM 29 Sign Zero 30 31 State matrix In accordance with Table E 1 5 32 Parity 0 if sum of ones is odd number 1 if sum of ones is even number 034 50 00 Appendix E Page 26 Dec 17 2009 4312 02 USER S MANUAL Table E 1 41 Flight time to the next WPT Bit No Information content Bit coding 1 8 Address 2523 10 101 010 9 10 00 all 01 1 10 2 11 not used 11 13 Reserved Zero 14 28 Significant part is Range 512 min 15 bits m s bit 28 256 min
114. ocket 03 5 364 241 6PO 364 038 TY 0 eo Oe 1 0 12 25 5 u k la AN ia EPA 4 holes PN v 205 max 155 0 1 Figure I 1 page 2 of 3 4312 02 USER S MANUAL Site for UPS installation on object 1250 1 Figure I 1 page 3 of 3 034 50 00 Appendix I Page 3 4 Dec 17 2009 4312 02 USER S MANUAL AIRBORNE EQUIPMENT OF SATELLITE NAVIGATION APPENDIX K reference Connection diagram of two equipment sets serene on cower a iuis sama add wor SERXCEUPX PEP ZEX ewm nom ae uot J NIY ur JOIUUO Oo L L eel E i ZEN 06 ueuxdinb3 034 50 00 Appendix K SLUT S9TOR 9 2 9 LO L EC POS SW Py H7 3 L luc L xu L uu LS lx a ETIS AL wc recon LAN 198 Page 1 2 Dec 17 2009
115. orage The equipment has a standard and user online database The standard database is stored on the navigation database storage unit flash card inserted into the RICU front panel s notch The navigation database stotage unit has a permanent memory and provides with NDB storage for a certain region of the aircrafts flights The standard database information is updated each 28 days in accordance with AIRAC cycles and supplied to the customer under the agreement The online database contains the information of the online WP and the flight plans entered manually by the operator The online database information is accessible for any review amendment deleting and updating The online database is permanent Automatic interface of two RICUs To guarantee RNP 1 RNAV requirements two sets of equipment shall be installed on the aircraft board The equipment provides automatic interaction of two RICUs between them for data transfer and operation modes during the equipment control from one of the two RICUs Connection diagram of two equipment sets is shown in Appendix K When on one RICU the following operations are being processed parameter setting in Limit Data window user points creation edition routs creation edition route activation flight activation in DIRECT ON mode the same operations are processed automatically on the second RICU When you run these procedures in one RICU and in the second RICU set NAV data card
116. ore flight online maintenance A1 6 periodical maintenance routine maintenance after 600 and 6000 running hours B calendar maintenance after 12 and 48 months Any equipment maintenance shall be performed in accordance with Schedule of Maintenance 461513 077 02 PO The equipment is designed for on condition maintenance On condition maintenance is provided by the required control of operating conditions during the operation with all maintenance types With OCTM the equipment shall be replaced with all maintenance types for its rehabilitation or retirement in the case of the equipment refusal only With on condition technical maintenance the to refusal technical maintenance technique shall be applied With TFTM the equipment shall be operated till safe refusal and the equipment status management rehabilitation or retirement shall be performed on the ground of reliability analysis Safe refusal when the equipment refusal under condition of its single appearance at any flight stage will not result in more serious consequences than the flight harder conditions Operating condition control and the equipment refusals qualification is performed with all and any technical maintenance by means of the equipment workability extended testing 034 50 00 Page 201 Dec 17 2009 4312 02 USER S MANUAL Maintenance The equipment shall be connected to 27 V power source through the aircraft standard power distribution
117. orks performed with TR Cont deviations rol TVONVW 6 50 0 lt 600c LI 99d 9994 000 lt 6 lt 0 Flow Sheet 3 MS Item 034 50 006 Continuation Operation and Technical Requirements TR Works performed with TR Cont deviations rol Exit test lt CRSR gt INRS OBS MSG NAV FPL PRC IM lt gt press by turns buttons on RICU front panel After pressing the button a short term field lighting appears on RICU display corresponding to the pressed button start rotating the shaft encoder external handle clockwise On RICU display in Encoder A parameter field values from 0 to 63 shall be indicated by turns starting from the value which was indicated before turning During shaft encoder external handle turning symbol field shall be lightened on RICU display above CR field start rotating the shaft encoder external handle counter clockwise On RICU display in Encoder B parameter field values from 63 to 0 shall be indicated by turns starting from the value which was indicated before turning During shaft encoder external handle turning symbol field shall be lightened on RICU display under CR If the above indications are not performed decision of RICU replacement shall be taken To exit from the keyboard test press CRSR button then press ENT button AUXA page shall appear on RICU display TVONVW 6 50 CO CI Y HO 600Z L
118. orks with all NSCs within the radio visibility area Information interchange Electric signal types kinds and levels as well as one time commands shall correspond to requirements PTM 1495 75 with amendment 3 Information interchange between the equipment and AES shall be communicated via bipolar code to all asynchronous way when the information sensor delivers continuously the information as information words appearing in the line after the given time intervals and information consumer shall be ready to receive the necessary code words anytime 034 50 00 Page 8 Dec 17 2009 4312 02 USER S MANUAL Power Supply The equipment shall be powered from the airborne DC mains having 27 V nominal voltage Maximum power consumption is 30 W Note f power supply interrupts for more then 3 seconds in the case of defective work of the power supply system the equipment may stop and then restart automatically in the testing mode providing its output characteristics after 2 5 minutes The power voltage from the airborne mains shall be supplied to UPS X1 connector RICU switching ON OFF is executed by ON OFF locking button pressing Operation conditions The equipment shall resolve functional tasks at parking during movement within the airport limits and during flight day or nighttime in any physical and geographical conditions regardless weather conditions in any point of the Earth if the aircraft flight following parameter
119. peak to peak mV max 100 6 DC Output voltage ripple rate max 7 4 7 Maximal load current A 1 8 8 Operation time when input voltage is not available at 1 5 A load current s min 3 9 No load current mA max 50 10 No load output voltage V min 0 3 11 Consumption power at maximal load W max 60 UPS Construction UPS enclosure is made of aluminum alloy with oxide and enamel coating There are three connectors installed on UPS X1 connector 23 10 18B 1 B plug for power connection from DC airborne mains X2 connector 23 10 18P 1 B plug for connection X3 connector is not used in this equipment thus it is closed with 18 cap provided in IK Note Unauthorized connection of RICU to UPS X3 connector shall not result in the equipment failure X1 X2 connectors contacts purpose is described in Tables 9 10 034 50 00 Page 33 Dec 17 2009 4312 02 USER S MANUAL Table 9 X1 connector contacts purpose Contact Circuit Purpose 1 27 IN Supply input voltage plus 27 V 2 Reserved 3 27_IN Supply input voltage minus 27 V 4 27_IN Supply input voltage minus 27 V 5 Reserved 6 27 IN Supply input voltage plus 27 V 7 Reserved 8 Reserved 9 ENCLOSURE UPS enclosure 10 ENCLOSURE UPS enclosure Table 10 X2 connector contacts purpose
120. put frequency is 100 KHz contacts 33 and 34 of RICU X3 connector channel 2 is designed for output of control words for airborne rangefinders with 12 5 KHz frequency contacts 35 and 36 of RICU X3 connector channel 3 is designed for output of navigation information words with 100 KHz frequency contacts 39 and 40 of RICU X3 connector 034 50 00 Appendix E Page 1 Dec 17 2009 4312 02 USER S MANUAL E 1 2 Information delivered on the channel 0 List of information delivered on channel 0 is given in Table E 1 1 Table E 1 1 Parameter name Address Note octal number Y required 121 E 1 28 10 Hz Flight stage 1323 DISCR E 1 31 Flight stage system of coordinates SNS type 10 Hz CH 4312 state 2735 DISCR E 1 43 Mode of operation number of satellites 10 Hz Wind speed 315 amp BC E 1 52 10 Hz Wind angle 316s BC E 1 53 10 Hz Linear turn lead 062s BC E 1 11 10 Hz Remaining distance to WPT along 063 E 1 12 10 Hz desired track Header of data record 074 BC E 1 13 Active leg of the route 075 BDC E 1 14 Control sum 113 BC 1 22 Message length 303 BC E 1 46 Identifier 1 2 3 symbols 304 BC E 1 47 WPT RB identifier Identifier 4 5 6 symbols 305 BC NP latitude 306 BC E 1 48 NP coordinates NP longitude 307 BC Arc direction 330 BC E 1 55 ane Arc radius 331 BC E 1 56 Angle of arc heading al
121. r MS item 034 50 007 MS Flow Sheet 2 Pages 207 209 MS Item Operation Work Content 1 0 man hour 034 50 00f Installation of equipment components in aircraft Operation and Technical Requirements TR WARNING DE ENERGIZE 27 V POWER CIRCUIT ON THE AIRCRAFT POWER DISTRIBUTION UNIT BEFORE INSTALLATION 1 RICU Installation For RICU installation perform the operations as follows set RICU enclosure on its location secure it in 20 mounting points it is allowed to secure RICU in 12 points as directed in Appendix G of this Operating Manual check up seals availability and integrity on RICU upper and lower cover connect RICU earthing rod to the aircraft earthing bar check up the earthing quality between RICU earthing rod and the earthing bar by means of milliohm meter the resistance value shall not exceed 2000 mcOhms remove process covers from connectors connect cables to RICU connectors to fix connector X5 install the bracket as shown on Figure Appendix H Lock connector with 0 3 12 18 9 safety wire and seal it install RICU into enclosure by guideways tighten screws on RICU front panels Works performed with TR deviations Contr ol TIVONVW 5 4951 cO CIEP HO 600c LI 99d 802 33ed 00 0 70 Flow Sheet 2 for MS item 034 50 007 Continuation Operation and Technical Requirements TR Works performed with TR deviations Cont rol 2
122. r any mechanical damage connecting BBP to airborne mains check up the feed circuits resistance Voltage range is from 24 V to 30 V Resistance shall not exceed 0 5 Ohm yes Repair the cable Replace Examine the cable connecting UPS with the airborne mains for any mechanical damage check up the feed circuits resistance Resistance shall not exceed 0 5 Ohm Repair the cable 034 50 00 Page 104 Dec 17 2009 4312 02 USER S MANUAL RICU Control buttons lightening fails to switch on Replace RICU When preliminary test is terminated MESSAGE window with error message 1 3 indication on RICU display Link with GNSS DATABASE MISSING Link with is bad KVU is bad Install the checked navigation database storage device Replace RICU Replace RICU Switch off the equipment and then switch it on When repeated preliminary test is terminated MESSAGE window with error message indication DATABASE MISSING yes Replace RICU no Continue operation During the keyboard testing AUX4 KEYBOARD TEST page lightening on RICU display for the buttons corresponding to control buttons fails to switch on values Encoder 2 1 A Encoder B 0 63 do not change on RICU display at shaft encoder rotation parameter Replace BPIU 034 50 00 Page 105 Dec 17 2009 4312 02 USER S MANUAL After extended testing AUX4 GNSS TEST page indication on RICU display in FonTest windows
123. rdance with Table E 1 5 32 Parity 0 if sum of ones is odd number 1 if sum of ones is even number Table E 1 53 Wind angle word structure Bit No Information content Bit coding 1 8 Address 316 11 001 110 9 10 Identifier 00 all 01 1 10 2 11 not used 11 16 Reserved Zero 17 28 Significant part is Range 180 12 bits m s bit 28 90 Negative values are transmitted in additional code 29 Sign 0 from 0 to 180 1 from 180 to 360 30 31 accordance with Table E 1 5 32 0 if sum of ones is odd number if sum of ones is even number 034 50 00 Appendix E Page 33 Dec 17 2009 4312 02 USER S MANUAL Table E 1 54 scale range word structure Bit No Information content Bit coding 1 8 Address 326 11010 110 9 10 Identifier 00 all 01 1 10 2 11 not used 11 13 Reserved Zero 14 28 Significant part is Range 128 NM 15 bits m s bit 28 64 NM 29 Sign Zero 30 31 State matrix In accordance with Table E 1 5 32 Parity 0 if sum of ones is odd number if sum of ones is even number Table E 1 55 Arc direction word structure Bit No Information content Bit coding 1 8 Address 330 11 011 000 9 10 Reserved Zero 11 Arc dire
124. ronic Barometric Altimeter European Geostationary Navigation Overlay System Earth Parameters 1990 Final Approach Waypoint Frequency Code Channel Fault Detection and Exclusion Algorithm Flight amp Navigation Equipment Flight amp Navigation Instrument 034 50 00 Abbreviation List Page 1 Dec 17 2009 5 GLONASS C A code GNSS GPS HDOP HF HFOM HIL HVSS ILS IM IST LAAS LCTD LLT LNA SSF M MFD MLS MS MSAS n m NDB NOTAM NP NSC NT OCTM PCU Proc Con QD RA 034 50 00 Abbreviation List Page 2 Dec 17 2009 CH 4312 02 USER S MANUAL Flight Operation Manual Flow Sheet Global Navigation Satellite System GPS Law Range Accuracy Code GPS GLONASS Joint System US Global Positioning System Horizontal Dilution of Precision High Frequency Horizontal signals quality evaluation Horizontal Integrity Limit Heading and Vertical Strapdown System Installation Kit Instrumental Landing System Instructional Manuals integrity signaling threshold Local Area Augmentation System Linear Cross Track Deviation Linear Lead of Turn Low Noise Amplifier with Signal Separate System Maintenance Multifunctional Display A813 Microwave Landing System Maintenance Schedule Multi transport Satellite based Augmentation System Nautical Mile Navigation Database Notice To Airme
125. s change as follows ground speed 0 1300 km h angle of list and angle of pitch 30 30 vertical speed 50 50 m s drift angle 180 180 acceleration 30 30 m s path angle 0 360 barometer elevation 500 15000 m 034 50 00 Page 9 Dec 17 2009 4312 02 USER S MANUAL Environmental Influencing Factors Operating temperature range RICU UPS LNA SSF 101 antenna 20 55 C 40 55 C 55 55 C 55 85 C Higher short time operating temperature up to 30 min RICU UPS LNA SSF Limiting temperature lower RICU 101 antenna LNA SSF UPS upper Sinusoidal vibrations frequency range vibration acceleration range max RICU UPS 101 antenna LNA SSF 70 55 60 85 5 2000 Hz 3 g 3 amp 10 g The equipment efficiency in the case of ice formation shall be guaranteed if ice layer on 101 antenna surface does not exceed 1 3 mm Weight Equipment units weight RICU 101 antenna LNA SSF UPS 034 50 00 Page 10 Dec 17 2009 2 50 0 25 kg 0 180 0 015 kg 0 22 0 02 kg 1 10 0 11 kg 4312 02 USER S MANUAL Electromagnetic Compatibility The equipment by its noise immunity meets KT 34 01 3 edition requirements for GPS and GLONASS signals receivers considering operation conditions on air
126. s of MHz 10 MHz 28 20 MHz 29 40 MHz 30 31 State matrix In accordance with Table E 1 5 32 Parity 0 if sum of ones is odd number 1 if sum of ones is even number Note Normal operation character in state matrix is a termination character of the beacon adjustment 034 50 00 Appendix E Page 37 Dec 17 2009 4312 02 USER S MANUAL Table E 2 3 Beacon distance word structure Bit No Information content Bit coding 1 8 Address 202 10 000 010 9 10 Identifier 00 all 01 71 10 2 11 not used 11 Memory mode 1 0 12 Beacon in near field 1 beacon is available region 0 beacon is not available 13 28 Significant part is Range 512 NM 14 bits m s bit 256 NM 29 Sign Zero 30 31 State matrix In accordance with Table E 1 5 32 Parity 0 if sum of 1 is odd number if sum of 1 is even number Note Normal operation character in state matrix is a validity character of measured distance Table E 2 4 Barometric altitude word structure Bit No Information content Bit coding 1 8 Address 203g 10 000 011 9 10 Identifier 00 all 01 1 10 2 11 not used 11 Reserved Zero Significant part is Range 131072 feet 12 28 17 bits m s bit 65536 feet Negative values are transmitted by additional code 29 Sign 0 positive altitude 1 negative al
127. served Zero Range 32768 feet min 14 28 Significant part is m s bit 28 16384 feet min 15 bits Negative values are transmitted by additional code 0 up 29 Sign 30 31 State matrix In accordance with Table E 1 5 32 Parity 0 if sum of ones is odd number if sum of ones is even number 034 50 00 Appendix E Page 24 Dec 17 2009 4312 02 USER S MANUAL Table E 1 37 Ground speed component N S value word structure Bit No Information content Bit coding 1 8 01110110 00 all 01 1 219 10 2 11 not used 11 13 Zero Range 4096 knots 14 28 Significant part is m s bit 28 2048 knots T Negative values are transmitted in additional code 0 North i 1 South 30 31 In accordance with Table E 1 5 32 0 if sum of ones is odd number if sum of ones is even number Table E 1 38 Ground speed component E W value word structure Bit No Information content Bit coding 1 8 Address 174 01 111 100 00 all 01 1 9 10 Identifier 10 2 11 not used 11 13 Reserved Zero Range 4096 knots 14 28 Significant part is m s bit 28 2048 knots 15 bits Negative values are transmitted in addition code 0 East 29 Sign 1 West 30 31 State matrix In accordance with Table E 1 5 32 Parity 0 if sum of ones is odd number 1 if sum of ones is even
128. ss than 5 101 antenna is connected to LNA SSF with HF line having signal attenuation not more than 0 6 dB at frequency of 1600 MHz 101 Antenna construction AIOIII antenna structure meets the requirements of ARINC 743A 3 101 antenna is sealed 101 antenna shall be earthed in accordance with OST 1 01025 93 requirements through the surface touching the aircraft fuselage at mounting 101 antenna is mounted on the aircraft with 4 screws Rubber gasket available in T IIIK 468911 020 02 installation kit is used for sealing 101 antenna outline drawing is shown the Figure Appendix C of this Manual 034 50 00 Page 29 Dec 17 2009 4312 02 USER S MANUAL Low Noise Amplifier with Signal Separate Filtering LNA SSF AIIMA 434816 034 is used for amplification and separate filtration of GLONASS and GPS SNS NSC signals within the range from 1570 MHz to 1610 MHz of frequencies coming from 101 antenna LNA SSF technical specifications are given in the Table 7 Table 7 Specification Value Operating frequencies sub ranges GLONASS MHz 1593 1610 L1 GPS MHz 1570 1585 Pass band edge frequency at minus 30 dB level lower MHz min 1545 upper MHz max 1626 Coefficient of transmission on frequencies 1575 and 1602 MHz 30 0 3 5 2 5 dB Transmission coefficient unevenness dB max 3 0 Noise coefficient within range of frequencies 1570 1573 MHz dB
129. st frequency Indicated consistency of symbol displaying shown by aircraft rangefinder range indicator is valid for 75 range finder Using other aircraft rangefinders the control should be maintained according to applied rangefinder documentation 5 Communications test with navigation and landing system VOR The test is performed in an aircraft if the equipment is connected to navigation and landing system To test the communication with navigation and landing system switch on navigation and landing system and devices interacting with it switch on the equipment power supply on the airborne power board 007057760 TVONVW 6 50 CO CI Y HO 600c LI 9cc 8 000 lt 0 Flow Sheet 5 Item MS 034 50 00c Continuation Operation and Technical Requirements TR Works performed with TR deviations Contr ol press ON OFF button in RICU As soon as NDB indication form appears on RICU display press ENT button set up AUX2 page Set the highlighting in TUNE VOR DME field and press ENT button RICU will display Tune VOR DME window set the highlighting in SELECT field rotate shaft encoder internal knob for one position MODE pop up window will appear in Tune VOR DME window set the highlighting in TEST field Press ENT button RICU will display Test VOR DME window set the highlighting in VOR NAVAID table of MODE field Rotate shaft encoder internal knob for one position SELEC
130. stance to 2 radio beacons at least in case if definition accuracy of navigation parameters in DME DME navigation mode is higher than in the current mode VOR DME navigation mode is set when data are available from aircraft systems on the range and bearing to a radio beacon in case if definition accuracy of navigation parameters in VOR DME navigation mode is higher than in the current mode Autonomous Control mode is performed automatically during the entire time of the equipment operation In Autonomous Control mode the background testing of the equipment main units is performed In the case of any failures in Autonomous Control mode that may affect the equipment operability RICU display shall indicate MESSAGE window Figure 10 about a failure Information about the background testing results shall be indicated on AUXA page in FonTestl and FonTest2 windows and shall be controlled during the equipment operability extended testing Ground Extended Control mode is set in the case of Strut compression one time command in breaoff Earth state and if operator performs RAM extended test extended testing of the equipment operability 034 50 00 crp 49 50 15 2008 4312 02 USER S MANUAL AIRBORNE EQUIPMENT OF SATELLITE NAVIGATION TROUBLESHOOTING General Instructions for Troubleshooting The equipment malfunction may cause the equipment complete failure or the equipment p
131. sued via ARINC 429 interface For list of words transmitted and received via ARINC 429 and their format see Appendix E of this Manual RICU generates and delivers analog signals to the aircraft airborne systems Z signal deviation from DT as DC voltage changes within the range from 150 to 150 mV load from 200 to 1000 Ohm voltage right deviation voltage left deviation To the aircraft linear deviation from DT 5 minus 5 plus km in route 1 minus 1 plus km at flight in the airport area 0 5 minus 0 5 plus km at approach corresponds Z signal linear change 150 mV 150 mV 7 signal scale changes automatically depending on the flight stage Z signal description inclination depending on the flight stage 0 030 V km for the route stage 0 150 V km for the airport area stage 0 V km for the approach stage Availability Z signal deviation from DT availability as DC voltage of 27 V nominal value at 1000 100 Ohm load specifying deviation from DT analog signal availability 034 50 00 Page 13 Dec 17 2009 4312 02 USER S MANUAL Selected roll signal for automatic flight on the desired route changing from 10 1 V to minus 10 1 V on 1000 Ohm minimal load for aircraft roll control within the range 30 with 0 33 V degree gradient with information updating maximal period 0 1 second and 100 mV maximal ripple peak to peak Selected roll ava
132. t board To do this test connect the equipment power supply on the airborne power supply unit press ON OFF button on RICU As soon as NDB indication form appears on the display press ENT button open AUXA page Set the highlighting in IO TEST field and press ENT button IO TEST window is indicated on RICU display as follows TVONVW 6 50 600c LI 99d 8cc ase 00 0 70 Flow Sheet 6 Item MS 034 50 00k Continuation Operation and Technical Requirements TR Works performed with TR deviations Contr ol 2 Shaping test of aircraft light panel control signals produced by the equipment install lighting in RK OUT window In RK OUT filed the last symbol on the right meets the one time command 0 the last symbol the left corresponds to the one time command RK15_OUT place the symbol 1 by turns in the character cells corresponding to one time commands RK0 OUT OFFSET RK1 OUT RAIM RK2 OUT WPT RK3 OUT MSG 4 OUT Avail SNS 5 OUT RK6 OUT Airport area RK7 OUT Switch on ERLA RK15_OUT ARM Appropriate indicators will light on the airplane light alarm board Note It is allowed to modify the check sequence of one time commands Test control signals used in a specific aircraft 3 Selected roll signals generation test in RK OUT field install the symbol 1 in the character cells corresponding to one time commands
133. teration 332 BC 1 57 eee Tt is output only if an active route is available Output period depends on the length of active route and is determined by the formula 2 0 1 sec 1 where N is WPT number in the route Data output is performed in two serial 100 ms intervals in step with data output in MFD on channel 1 containing information about initial and final WPT of active leg of the route In the first interval information is output on initial WPT of active leg of the route in the second interval information is output on final WPT of active leg of the route Tt is output only in a sentence containing information on initial WPT Tt is output on arc leg having fixed radius 034 50 00 Appendix E Page 2 Dec 17 2009 4312 02 USER S MANUAL E 1 3 Information output via channel 1 The equipment outputs information to MFD via channel 1 The information delivered to MFD is divided in dynamic and background one Dynamic information includes all alternating parameters such as aircraft position time response of movement angular parameters of movement etc All dynamic information is integrated into one unit dynamic information unit DIU The equipment delivers DIU 10 times a second DIU composition is given in Table E 1 2 Table E 1 2 Parameter edness Table number octal Desired Track angle 114 BC E 1 23 Desired headi
134. the OBS button signal lighting is on When OBS mode flight is cancelled OBS background lighting is on Pressing OBS button when indication in the status line is SUSP the automatic switch to the next route segment is interrupted and transits to repeated flight through the holding area for STAR operation missed approach for APPROACH operation Note SUSP demand for interruption of the automatic switch to the next route segment when STAR or APPROACH operations are to be done MSG button MSG button is designed for delivering system messages and messages of conjugated equipment operation on the display As soon as message is delivered MSG button signal lighting is on If there is more than one message MSG button lighting blinks until the last message is read As soon as all messages are read MSG button background lighting is on NAV button NAV button is designed for transit into the navigation form This form is basic for the equipment thus repeated pressing on NAV button shall result in no actions FPL button FPL button is designed for transit into the routes procedure form Repeated pressing on FPL button shall return the form previous to FPL form call 034 50 00 Page 26 Dec 17 2009 4312 02 USER S MANUAL PROC button PROC button is designed for transit into the takeoff arrival and approach standard procedures selection and load form Repeated pressing on PROC button shall return the form pr
135. tion Operation and Technical Requirements TR Works performed with TR deviations Contr ol set the highlighting in SELECT field rotate shaft encoder internal knob for one position MODE pop up window will appear in Tune VOR DME window set the highlighting in TEST field Press ENT button RICU will display Test VOR DME window DHE NAVAID VOR NAVAID set the highlighting in DME NAVAID table of FREQ field Input tuning frequency of DME VOR device set the highlighting in DME NAVAID table of ON OFF field for the first beacon Rotate shaft encoder internal knob for one position SELECT pop up window will display in Test VOR DME window TVONVW 6 50 6002 1 99d STT 9 4 Flow Sheet 5 Item MS 034 50 00 Continuation Operation and Technical Requirements TR Works performed with TR deviations set the highlighting in ON field for communications test with aircraft rangefinder press ENT button set the highlighting in DME NAVAID table of MODE field for the first beacon Turn shaft encoder internal knob for one position SELECT pop up window will display in Test VOR DME window turn on highlighting in CTRL field Press ENT button For approximately 4 seconds aircraft rangefinder range indicator will display the consistency of zeroes and hyphens Thereafter 000 0 value should be displayed in Test VOR DME window of DIS field for the fir
136. titude 30 31 State matrix In accordance with Table E 1 5 32 Parity 0 if sum of ones is odd number 1 if sum of ones is even number 034 50 00 Appendix E Page 38 Dec 17 2009 Table E 2 5 True airspeed Virue word structure CH 43 12 02 USER S MANUAL Bit No Information content Bit coding 1 8 Address 210 10 001 000 9 10 Identifier 00 all 01 1 10 2 11 not used 11 13 Reserved Zero 14 28 Significant part is Range 2048 knots 15 bits m s bit 28 1024 knots 29 Sign Zero 30 31 State matrix In accordance with Table E 1 5 32 Parity 0 if sum of ones is odd number if sum of ones is even number 034 50 00 Appendix E Page 39 Dec 17 2009 4312 02 USER S MANUAL Table E 2 6 Heading reception state word structure Bit No Information content Bit coding 1 8 Address 270 10 111 000 9 10 Identifier 00 all 01 1 10 2 11 not used 11 Alignment Operation mode 1 alignment 0 operation 12 Reserved Zero 13 Normal Basic mode 1 normal 0 basic 14 GMH GSMH mode 1 gyro magnetic heading 0 gyro semicompass heading 15 Spatial position vertical 1 failure 0 normal operation 16 Autopilot heading locking 1 failure 0 normal operation 17 Reserved Zero 18 True airspeed failure 0 normal operation 19 Altitude
137. umber 1 if sum of ones is even number 034 50 00 Appendix E Page 18 Dec 17 2009 4312 02 USER S MANUAL Table E 1 25 Deviation from DT in horizontal plane word structure Bit No Information content Bit coding 1 8 Address 116 01 001 110 9 10 Identifier 00 all 01 1 10 2 11 not used 11 13 Flight stage 000 en route 001 terminal area 010 approach 14 28 Significant part is Range 128 NM 15 bits m s bit 64 NM Negative values are transmitted in additional code 29 Sign 1 left 0 right 30 31 State matrix In accordance with Table E 1 5 32 Parity 0 if sum of ones is odd number if sum of ones is even number Table E 1 26 Current latitude precisely word structure Bit No Information content Bit coding 1 8 Address 120 01 010 000 9 10 Identifier 00 all 01 1 10 2 11 not used 11 17 Reserved Zero Range 17 2 79 18 28 Significant part is m s bit 28 8 6 less significant bits Negative values are transmitted in additional code 1 South 22 Sign 0 North 30 31 State matrix In accordance with Table E 1 5 32 Parity 0 if sum of ones is odd number 1 if sum of ones is even number 034 50 00 Appendix E Page 19 Dec 17 2009 4312 02 USER S MANUAL Table E 1 27 Current longitude precisely
138. umbers of each tracking satellite azimuth angle of elevation S N ratio with reference to GLONASS SNS or GPS delivery for indication of current coordinates within WGS 84 CS 42 coordinate system or CR 90 on default within WGS 84 coordinate system delivery of current coordinates to external consumers within WGS 84 coordinate system updating with 10 Hz minimal frequency calculation on the ground of navigation parameters and inserted coordinates of route points particular coordinates of great circle aircraft position and Z distance from the aircraft current position to the next WP desired path angle true or magnetic actual path angle true or magnetic deflection angle route correction equal to difference between ACA true or magnetic ground speed flight time from aircraft position to the next WP and to the destination WP on the desired track the next WP and destination WP on the desired track passing time WP passing calculation and generation of signal for aircraft course change with or without turn lead data reception formatting and delivery for aircraft FNE via communication lines in accordance with the Table 1 034 50 00 Page 3 Dec 17 2009 4312 02 USER S MANUAL Table 1 RICU Interface Number ot Note channels Receive channel for ARINC 429 8 Appendix E Delivery channel for ARINC 429 4 Appendix E One time

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