UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual The information contained herein is subject to Export Administration Regulations (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. This publication is available at www.uasc.com. ©2007, 2019 UNIVERSAL AVIONICS SYSTEMS CORPORATION (UA) ALL RIGHTS RESERVED Universal Avionics 3260 East Universal Way Tucson, AZ 85756 +1 520 295 2300 • 800 321 5253 34-60-51 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual Record of Revisions Rev. No. Issue Date Insertion Date Initials Original 27 August 2007 27 August 2007 UA 1 1 October 2007 1 October 2007 UA 2 23 January 2011 23 January 2011 UA 3 6 December 2016 6 December 2016 UA 4 10 July 2019 10 July 2019 UA Retain this record in front of the manual. Upon receipt of revision, insert and remove pages according to the List of Effective Pages. Then enter on this page the revision number, issue date, insertion date and your initials. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page ROR-1 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual Record of Temporary Changes Change No. Issue Date Insertion Date & Initials TC-1 24 October 2019 24 October 2019 / UA Removal Date & Initials Retain this record in the front of this manual. Upon receipt of a Temporary Change, insert pages into manual and enter the Temporary Change number, issue date, insertion date and your initials. Also, record the removal of each temporary change. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page ROTC-1 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual Change No. Issue Date Insertion Date & Initials Removal Date & Initials Retain this record in the front of this manual. Upon receipt of a Temporary Change, insert pages into manual and enter the Temporary Change number, issue date, insertion date and your initials. Also, record the removal of each temporary change. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page LOEP-2 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual List of Effective Pages SUBJECT PAGE Title Page DATE 10 Jul/19 Record of Revisions 1 10 Jul/19 Record of Temporary Changes 1 2 10 Jul/19 10 Jul/19 List of Effective Pages 1 2 3 4 10 Jul/19 10 Jul/19 10 Jul/19 7 July/19 Table of Contents 1 2 3 4 5 6 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 Introduction 1 2 3 10 Jul/19 10 Jul/19 10 Jul/19 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 Description and Operation SUBJECT The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. PAGE DATE 24 25 26 27 28 29 30 31 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 FAA Approval 101 102 103 104 105 106 107 108 109 110 111 112 113 114 115 116 117 118 119 120 121 122 123 124 125 126 127 128 129 130 131 132 133 134 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 Equipment Specifications 201 202 10 Jul/19 10 Jul/19 34-60-51 Page LOEP-1 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual SUBJECT Installation And Wiring PAGE DATE 203 204 205 206 207 208 209 210 211 212 213 214 215 216 217 218 219 220 221 222 223 224 225 226 227 228 229 230 231 232 233 234 235 236 237 238 239 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 301 302 303 304 305 306 307 308 309 310 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. SUBJECT PAGE 311 312 313 314 315 316 317 318 319 320 321 322 323 324 325 326 327 328 329 330 331 332 333 334 335 336 337 338 339 340 341 342 343 344 345 346 347 348 349 350 351 352 353 354 355 356 357 358 34-60-51 DATE 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 Page LOEP-2 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual SUBJECT PAGE DATE 359 360 361 362 363 364 365 366 367 368 369 370 371 372 373 374 375 376 377 378 379 380 381 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 System Data Installation 401 10 Jul/19 Maintenance, Checkout, and Troubleshooting 501 502 503 504 505 506 507 508 509 510 511 512 513 514 515 516 517 518 519 520 521 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. SUBJECT PAGE 522 523 524 525 526 527 528 529 530 531 532 533 534 535 536 537 538 539 540 541 542 543 544 545 546 547 548 549 550 551 552 553 554 555 556 557 558 559 560 561 562 563 564 565 566 567 568 569 34-60-51 DATE 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 Page LOEP-3 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual SUBJECT PAGE DATE 570 571 572 573 574 575 576 577 578 579 580 581 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 10 Jul/19 Navigation Systems 601 10 Jul/19 Fuel Flow Inputs 701 10 Jul/19 The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page LOEP-4 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual Table of Contents Record of Revisions .............................................................................................. ROR-1 Record of Temporary Revisions ......................................................................... ROTC-1 List of Effective Pages .........................................................................................LOEP-1 Table of Contents ................................................................................................... TOC-1 Introduction ....................................................................................................... INTRO-1 Makeup and Use of This Manual ....................................................................................... INTRO-1 Application................................................................................................................... INTRO-1 Organization................................................................................................................. INTRO-2 Abbreviations and Terminology ........................................................................................ INTRO-2 Contact Information ........................................................................................................... INTRO-3 Description and Operation .............................................................................................. 1 Description .......................................................................................................................................1 General .......................................................................................................................................1 System Components...................................................................................................................7 System Interfaces .....................................................................................................................11 FMS Components ....................................................................................................................13 FMS Functions .........................................................................................................................18 Operation .......................................................................................................................................25 General .....................................................................................................................................25 Flat Panel Control Display Unit...............................................................................................25 Data Transfer Unit (DTU-100) ................................................................................................28 Solid State Data Transfer Unit .................................................................................................28 EFIS Radar Panel (ERP) ..........................................................................................................31 FAA Approval ............................................................................................................ 101 General .........................................................................................................................................101 Applicable TSOs ....................................................................................................................101 Applicable Advisory Circulars ..............................................................................................101 Reference Documents ............................................................................................................102 Universal Avionics Publications and Documents ..................................................................103 TSO Deviations......................................................................................................................104 Software Criticality ......................................................................................................................106 Instructions for Continuous Airworthiness ..................................................................................107 General Information ...............................................................................................................107 The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page TOC-1 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual Airworthiness Limitations ..................................................................................................... 107 Environmental Qualification Forms ............................................................................................ 108 Sample Airplane Flight Manual Supplement .............................................................................. 122 Equipment Specifications ........................................................................................... 201 Equipment Identification ............................................................................................................. 201 UNS-1Fw FMS Equipment ................................................................................................... 201 Compatible Peripheral Equipment ......................................................................................... 202 Technical Manuals ................................................................................................................. 203 UNS-1Fw Part Number Matrix.............................................................................................. 204 Configuration Module ........................................................................................................... 204 5-Inch FPCDU Part Number Matrix...................................................................................... 204 4-Inch FPCDU (P/N 1117-XX) Part Number Matrix............................................................ 205 4-Inch FPCDU (P/N 1117-X-XXX) Part Number Matrix..................................................... 205 Multifunction Control Display Unit (MCDU) Part Number Matrix ..................................... 205 Data Transfer Unit (DTU-100) Part Number Matrix ............................................................ 206 Portable Data Transfer Unit (PDTU-100) Part Number Matrix ............................................ 206 Solid State Data Transfer Unit Part Number Matrix ............................................................. 206 Portable SSDTU Part Number Matrix ................................................................................... 206 UNS-1Fw Part Number Configuration .................................................................................. 207 Power Specifications ................................................................................................................... 209 Equipment Specifications ............................................................................................................ 210 UNS-1Fw FMS ...................................................................................................................... 210 LP/LPV Monitor .................................................................................................................... 210 5-Inch FPCDU ....................................................................................................................... 210 4-Inch FPCDU ....................................................................................................................... 211 DTU-100 ................................................................................................................................ 211 SSDTU ................................................................................................................................... 211 Portable SSDTU .................................................................................................................... 212 GPS Antenna.......................................................................................................................... 213 WAAS (SBAS) GPS/Sirius Antenna ..................................................................................... 214 WAAS (SBAS) GPS/XM Weather and Radio Antenna ........................................................ 215 WAAS FMS Annunciators .................................................................................................... 216 Installation Kits ............................................................................................................................ 217 UNS-1Fw Installation Kit ...................................................................................................... 217 4-Inch and 5-Inch FPCDU Installation Kit ............................................................................ 217 The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page TOC-2 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual DTU-100 Installation Kit .......................................................................................................218 Portable DTU-100 Installation Kit ........................................................................................218 SSDTU Installation Kit ..........................................................................................................219 Portable SSDTU Installation Kit ...........................................................................................219 GPS 10708 Antenna Installation Kit .....................................................................................220 GPS 10709/10710 Antenna Installation Kit ..........................................................................220 Required Tools .............................................................................................................................221 Crimping Tools Required ......................................................................................................221 Pin Insertion/Extraction Tools Required ...............................................................................221 Insertion/Extraction Tool Manufacturers.....................................................................................222 Wire and Cable Manufacturers ....................................................................................................222 Alternate Part Vendors.................................................................................................................223 Equipment Drawings ...................................................................................................................224 UNS-1Fw ...............................................................................................................................224 UNS-1Fw 2MCU Rack ..........................................................................................................225 Configuration Module............................................................................................................226 Configuration Module Installation.........................................................................................226 5-Inch FPCDU .......................................................................................................................227 4-Inch FPCDU .......................................................................................................................229 LP/LPV Monitor ....................................................................................................................233 LP/LPV Monitor 2MCU Rack ...............................................................................................234 DTU-100 ................................................................................................................................235 SSDTU ...................................................................................................................................236 GPS Antenna 10708 ...............................................................................................................237 WAAS (SBAS) GPS/Sirius Antenna 10709 ..........................................................................238 WAAS (SBAS) GPS/XM Weather and Radio Antenna 10710 .............................................239 Installation and Wiring ............................................................................................... 301 General .........................................................................................................................................301 Form – Dimensions and Communications .............................................................................301 Sensor/Equipment Compatibility/Selection ...........................................................................301 Electrical Connectors .............................................................................................................307 Remote Annunciators.............................................................................................................307 FMS Mounting .......................................................................................................................307 GPS (WAAS) Antenna Mounting .........................................................................................308 Solid State Data Transfer Unit ...............................................................................................311 The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page TOC-3 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual FMS Interfaces ............................................................................................................................ 313 Analog Inputs......................................................................................................................... 313 Discrete Inputs ....................................................................................................................... 315 Digital Inputs ......................................................................................................................... 316 Analog Outputs ...................................................................................................................... 320 Discrete Outputs .................................................................................................................... 322 Digital Outputs....................................................................................................................... 324 Pin Assignment ........................................................................................................................... 327 UNS-1Fw – All Digital (P/N 3192-XX-111102) .................................................................. 327 UNS-1Fw – ASCB (3192-XX-111103) ................................................................................ 332 UNS-1Fw – Analog (P/N 3192-XX-111106) ....................................................................... 337 5-Inch FPCDU ....................................................................................................................... 342 4-Inch FPCDU ....................................................................................................................... 343 LP/LPV Monitor ................................................................................................................... 345 SSDTU ................................................................................................................................... 346 DTU-100 ................................................................................................................................ 347 UNS-1Fw Wiring ........................................................................................................................ 348 Power and Configuration Module ......................................................................................... 349 Dual WAAS FMS – Analog Configuration .......................................................................... 350 Dual WAAS FMS – Digital Configuration ........................................................................... 352 Dual WAAS FMS – EFI-890R Digital Configuration ......................................................... 354 LP/LPV Monitor Power Installation ...................................................................................... 355 Single WAAS FMS – Analog Configuration to LP/LPV Monitor........................................ 356 Single WAAS FMS – Digital Configuration to LP/LPV Monitor ........................................ 357 Single WAAS FMS Analog/Digital Configuration to LP/LPV Monitor .............................. 358 4-Inch FPCDU without Video and Graphics ......................................................................... 360 4-Inch FPCDU with Video and Graphics .............................................................................. 361 Dual 4-Inch FPCDU (without Video and Graphics) ............................................................. 362 Dual 4-Inch FPCDU with Video and Graphics ..................................................................... 363 Single 5-Inch FPCDU ............................................................................................................ 365 Dual 5-Inch FPCDU .............................................................................................................. 366 DTU-100 ................................................................................................................................ 368 Portable DTU ......................................................................................................................... 369 SSDTU ................................................................................................................................... 370 SSDTU Installation and DTU-100 Retrofit ........................................................................... 371 The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page TOC-4 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual Portable SSDTU.....................................................................................................................372 Portable SSDTU (Portable DTU-100 Retrofit) .....................................................................373 Fuel Flow and Roll Steering ..................................................................................................374 Heading and Radio Tune .......................................................................................................375 Analog Configuration ............................................................................................................376 ARINC Input Ports ................................................................................................................377 ARINC Output Ports ..............................................................................................................378 Discrete Inputs .......................................................................................................................379 Discrete Outputs ....................................................................................................................380 ASCB Version A....................................................................................................................381 System Data Installation ............................................................................................. 401 Maintenance, Checkout and Troubleshooting ............................................................ 501 Maintenance .................................................................................................................................501 Installation Checkout ...................................................................................................................502 Ground Test Plan ...................................................................................................................502 Flight Test Plan ......................................................................................................................515 Operational Checkout ..................................................................................................................532 CDU/FMS Self-Test ..............................................................................................................532 CDU Keyboard and Display Offset .......................................................................................536 FMS Configuration Verification ............................................................................................536 Static Test ..............................................................................................................................537 Interface Checkout .......................................................................................................................539 HSI Test .................................................................................................................................539 Winds Display (EFIS Only) ...................................................................................................539 DME Interface Test ...............................................................................................................539 VOR Test (without RRS) .......................................................................................................540 DTU-100 Test ........................................................................................................................540 SSDTU Test ...........................................................................................................................541 Approach Mode Test .............................................................................................................542 Sensor Checkout ..........................................................................................................................543 IRS .........................................................................................................................................543 GPIRS ....................................................................................................................................543 LORAN C ..............................................................................................................................544 GPS-1 .....................................................................................................................................544 WAAS1 ..................................................................................................................................544 The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page TOC-5 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual UASC Radio Reference Sensor ............................................................................................. 545 Air Data ................................................................................................................................. 545 Fuel Flow ............................................................................................................................... 545 GPIRS Checkout .................................................................................................................... 546 UASC GPS Checkout ............................................................................................................ 551 GPS/WAAS Checkout ................................................................................................................. 558 FMS Power On Self-Test – Initialization and LPV Annunciation Test ................................ 558 GPS/WAAS Sensor Evaluation ............................................................................................. 558 WAAS Flight Plan with LPV Approach................................................................................ 559 CDU Display of RNP/ANP ................................................................................................... 560 GPS/WAAS Dynamic Test .................................................................................................... 560 WAAS Antenna Offsets Test ................................................................................................. 563 Troubleshooting ........................................................................................................................... 565 Self-Test ................................................................................................................................. 566 System Failure Messages ....................................................................................................... 567 Database Update Error Messages .......................................................................................... 576 Configuration Verification..................................................................................................... 577 FMS Self-Test Output Checkout ........................................................................................... 578 FMS Output to HSI Checkout ............................................................................................... 578 DIST/GS Checkout ................................................................................................................ 578 HSI From Checkout ............................................................................................................... 578 DIST/BRG Checkout ............................................................................................................. 578 Roll Steering Checkout .......................................................................................................... 579 Input and Selected Cross-track Checkout .............................................................................. 579 DME Checkout ...................................................................................................................... 579 Winds Display Checkout ....................................................................................................... 579 Sensor Checkout .................................................................................................................... 579 GPS Antenna Inspection and Troubleshooting...................................................................... 581 Navigation Systems .................................................................................................... 601 Fuel Flow Inputs ......................................................................................................... 701 The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page TOC-6 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual Introduction 1. Makeup and Use of this Manual A. Application This Technical Manual for the UNS-1Fw is applicable to the components and software control numbers (SCN) noted below. The SCN is stamped on the component data plate. The “w” reference in the FMS name implies that these FMS systems are combined with the Wide Area Augmentation System (WAAS) subsystem. This Technical Manual is used for installation and basic wiring. Refer to the WAAS FMS Interface Manual, Report No. 34-60-53 for wiring diagrams covering specific installations. Refer to the WAAS FMS Configuration Manual SCN 1000/1100, Report No. 34-61-01, for detailed FMS/MMMS software configuration instructions. UNS-1Fw Navigation Computer Unit, P/N 3192-XX-11110X Configuration Module, P/N 31921 5-Inch Flat Panel CDU, P/N 1018-X-XXX (SCN 10.X and later SCNs) 4-Inch Flat Panel CDU, P/N 1117-XX or 1117-X-XXX (SCN 20.X and later SCNs) LP/LPV Monitor, P/N 3116-5X-1110 (Precision Approach Software SCN 10.1 and later SCNs) NOTE: When an LP/LPV Monitor is used in conjunction with a WAAS FMS to provide precision approach functions, the Precision Approach Software (PAS) SCN must be the same for both the WAAS FMS and LP/LPV Monitor. The PAS SCN is indicated on the identification plate of both components. Data Transfer Unit DTU-100 (Iomega ZIP Drive), P/N 1406-01-0X, 1407-01-0X Solid State Data Transfer Unit, SSDTU, P/Ns 1408-00-X, 1409-00-2 The following table shows the allowable combinations of UNS-1Fw FMS part numbers, PAS and SCNs: UNS-1Fw FMS Part No. 3192-0X-11110X – 1000.X 3192-3X-11110X – 1100.X SCN X= .1 .2 .3 .4 .5 .6 .7 .8 PAS (Precision Approach Software) 10.0 10.1 10.2 10.3 NOTE: Refer to the UNS-1Fw part number matrix in the Equipment Specifications section of this manual for a detailed explanation of the part numbers. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page INTRO-1 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual B. Organization This Technical Manual provides the information about: 2. (1) Description and operation of the components of the UNS-1Fw FMS. (2) FAA Approval including Environmental Qualification Forms. (3) Equipment Specifications to support selection of compatible peripherals and planning for the installation of UNS-1Fw components. (4) Detailed installation and wiring requirements. (5) Maintenance, Checkout and Troubleshooting of the UNS-1Fw and peripheral sensors as well as outputs from the UNS-1Fw to the Flight Guidance System. (6) Navigation Sensors – where to find scheduled outages and current status of long-range navigation systems. (7) Fuel Flow Inputs to the UNS-1Fw for various sensors. Abbreviations and Terminology This manual contains no abbreviations or terms that have varying interpretations in the industry. However, the use of 1000.X and 1100.X are used to indicate passages that may be applicable to one or more, but not all SCNs. Some components have multiple names that are used interchangeably. The terms FMS and UNS-1Fw are used to refer to the Flight Management System and Multi-Mission Management System. Throughout this manual the term “FMS” is used to refer to the UNS-1Fw as well as the Multi-Mission Management System. The exception to this is if the product, part number or multi-mission is specifically required. The terms FPCDU and CDU refer to the 5-Inch Flat Panel Control Display Unit 1018-XXXX and the 4-Inch Flat Panel Control Display Unit, P/N 1117-XX or 1117-X-XXX. Part numbers refer to specific configurations of a component. An X in a part number indicates there are several variations of the part number. The front panel of the CDU contains an array of push buttons or keys that are used to operate the system. Instructions in this manual refer to specific keys by name, for example [ENTER], [A], etc. Throughout this manual reference is made to the "DTU-100" and "disk". The term “disk” used herein now refers to any of the data storage devices (Zip disk, USB or SD) and the term “DTU” will be used to refer to either the DTU-100 or SSDTU. Procedures in this manual and displayed on the FMS will still use the term “DISK” and will remain unchanged regardless of the data storage device being used. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page INTRO-2 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual 3. Contact Information Please submit comments, suggestions, errors or other concerns about this manual to our Technical Publications Department at techpubs@uasc.com. To order copies or request changes in address and distribution information, contact info@uasc.com. For technical questions, please contact customersupport@uasc.com. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page INTRO-3 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual Description and Operation 1. Description The information contained within this installation manual describes the administrative and technical aspects, features, functions, and components of Universal Avionics (UA) Flight Management System (FMS) and Multi-mission Management System (MMMS). All comments or recommendations regarding the installation, acceptance or operation of the FMS/MMMS or its accessories and components can be directed to the Product Support Department at Universal Avionics. The information, drawings and wiring diagrams contained in this manual are intended as a reference for engineering planning only. The drawings and wiring diagrams contained herein do not represent any specific STC or Form 337 aircraft installation. It is the installer’s responsibility to compose installation drawings specific to the aircraft. This manual and the drawings and wiring diagrams contained herein may not be used as a substitute for an STC or Form 337 drawing package. A. General Universal Avionics FMS and MMMS are fully integrated navigation and flight management systems designed to provide the pilot with centralized control of the aircraft navigation sensors, lateral and vertical flight guidance and steering, fuel management, database management and flight planning. The UNS-1Fw FMS contains a Wide Area Augmentation System (WAAS) subsystem. The WAAS subsystem provides a navigation solution using GPS augmented by WAAS. The WAAS FMS is categorized as Class Gamma 3, which covers navigation and guidance functions for all flight phases through Localizer Performance with Vertical guidance (LPV) approach level of service. The WAAS subsystem provides three-dimensional position and velocity, time, and WAAS protection levels. The WAAS subsystem also provides ARINC I/O and critical analog output and discrete I/O. The WAAS Subsystem operates in single or dual FMS installations. The following installation options are available based on the severity of failure conditions on different classes of aircraft. Single FMS/WAAS – For aircraft that have LPV approach disabled. Dual FMS/WAAS – For classes of aircraft for which criticality of LPV approach operation is classified as ‘Severe-Major’. This requires dual WAAS subsystems for cross-channel monitoring. Single FMS/WAAS with LP/LPV Monitor - Same as the dual WAAS FMS installation but the cross-channel monitoring is provided by a LP/LPV Monitor. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 1 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual The FMS accepts position information from up to five long-range navigation sensors as well as a VOR, TACAN, or scanning DME sensor. The data from these sensors is used to determine the best computed position. This position is used by the FMS for navigating the aircraft along a programmed flight plan. Flight plans are created using the navigation database. The database locates waypoints along an entered route and combines these waypoints to form a flight plan. Current capability includes lateral great circle and vertical navigational guidance and display, from aircraft departure to arrival. This includes enroute as well as terminal and approach capabilities that are integrated with real time fuel management monitoring data. An incorporated Radar/Multi-Function Display (MFD) interface allows selection and display of flight plan waypoints on compatible weather radar or MFD displays. Both the computed and raw sensor data are output for display to the flight crew on the CDU. Flight Guidance system installations, switching and pilot annunciations are streamlined, as all output data comes from one source, the FMS NCU, which represents all interfaced sensors. Each type of navigation sensor has unique capabilities and functions. The type and number of sensors can be tailored to optimize for specific operational requirements using Loran C (LCS), GPS, GNSS and laser- or gyro-referenced inertial navigation sensors. VOR and TACAN receivers are optional for either enroute navigation or as an approach reference. The system also accepts data from a Radio Reference Sensor (RRS) in lieu of DME/VOR/TACAN receivers. The FMS also has the ability to tune and receive data from communication and navigation radios. The user may tune commands to COM (3), NAV (2), ADF (2), ATC, or TAC radios depending on the configuration. The FMS receives true airspeed (TAS) and altitude information from an air data computer. The FMS receives fuel flow data from the aircraft fuel flow sensors, and optionally, heading data from an analog gyro. The fuel management function of the FMS accepts input from the aircraft fuel flow sensors as well as information supplied by the pilot. It uses this data to continuously update and display fuel management information during flight. This also assists the pilot in planning fuel requirements while on the ground. The FMS may contain up to six databases: navigation, company route, checklists, performance, pilot-defined, and FMS flight plan. All databases can be updated via a Data Transfer Unit (DTU). This DTU is housed within a protective case that may be panel mounted in the cockpit for convenient access. The FMS will have the ability to store two cycles of the Navigation and Company Routes databases. A self-contained worldwide NAV database stored in non-volatile memory provides the FMS with information on over 100,000 waypoints, navaids, airports, and over 12,000 SIDs, STARs and approaches. The operator may choose from a worldwide database with airport runways of >2000 feet or >4000 feet. A special helicopter database is available for helicopter operators. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 2 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual The pilot-defined database is stored in nonvolatile memory. It has the capacity to store up to 200 pilot-defined enroute waypoints, 200 pilot-defined routes and 100 each pilot-defined enroute alignment points, airport reference points, runways, and approaches. The system will store 100 average-size, pilot-entered SIDs and STARs as well. The FMS flight plan database is erased when the FMS is turned off. The FMS supports the checklist function as an external FMS in the Collins ProLine 4 800 avionics system. The user generates the checklist data on a personal computer (PC) program, loads it into the FMS, and maintains it. The checklist database and the status information on the active checklist reside in nonvolatile memory. Aircraft configured for the advanced performance feature require an aircraft specific database that contains the data pertinent to their operation. The FMS employs an Ethernet connection for rapid transfer of data to such systems as the Terrain Awareness Warning System (TAWS) and Application Server Unit (ASU). The Ethernet also provides 10 MB per second database loading from a Data Transfer Unit. Along with all the features of the FMS, the MMMS provides the capability to automatically steer along any of six different search patterns. Refer to the applicable Operator's Manual, Special Missions section for more information on the MMMS search patterns. The FMS is configured to a specific aircraft installation through a configuration module which is part of each aircraft installation. At the time of installation, the configuration module is programmed through the CDU to define the sensor input ports, fuel flow type, air data type, EFIS interface, etc. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 3 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual Single FMS Installation Description The FMS computes position and provides selected information to the associated flight instruments and sensor control to all sensors. The FMS houses an internal database which includes charted data from suppliers such as Jeppesen and pilot input data such as routes and approaches. NOTE: Single FMS installations not utilizing an LP/LPV Monitor or second WAAS FMS will not provide precision approach functions. NOTE: The block diagram illustrates the various types of inputs and outputs to and from the FMS. The actual set of inputs and outputs in any particular installation is dependent on the suite of avionics equipment on the aircraft. 5-Inch FPCDU UNIVERSAL Video DATA NAV VNAV DTO LIST PREV FUEL FPL PERF TUNE MENU NEXT A B H C D 1 2 3 4 5 6 7 8 9 E F G I J K L M N BACK O P Q R S T ON / OFF DIM U V W X Y Z 0 MSG ENTER MFD Vision-1 TAWS WAAS/GPS Antenna Cabin Display Configuration Module ASU UniLink Internal GPS/WAAS UniVision GPS/GNSS IRS or GPIRS Radar Doppler UNIVERSAL UNS-1Fw FMS FGS Display Air Data AFIS Fuel Flow TACAN VOR DME UNIVERSAL SSDTU The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 4 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual Dual FMS Installation Description In dual installations, each FMS communicates with the other, sharing flight plan and navigational information. Typically, in dual FMS installations, all long-range navigation sensors are interfaced with both units. Each FMS computes an independent position using all available navigational sensors and provides selected information to the associated flight instruments. Each FMS shares its best best-computed position with the other system and continuously monitors the other system's position output. NOTE: The block diagram shows the various types of inputs and outputs to and from the FMS. The actual set of inputs and outputs in any particular installation is dependent on the suite of avionics equipment on the aircraft. FPCDU FPCDU UNIVERSAL UNIVERSAL Video DATA NAV VNAV DTO LIST PREV FUEL FPL PERF TUNE MENU NEXT A B H I C J D E F G M DATA NAV VNAV DTO LIST PREV 1 2 3 4 5 6 7 8 9 K L N BACK O P Q R S T ON / OFF DIM U V W X Y Z 0 FUEL FPL PERF TUNE MENU NEXT A H MSG ENTER B I C J D E F G M 1 2 3 4 5 6 7 8 9 K L N BACK O P Q R S T ON / OFF DIM U V W X Y Z 0 MSG ENTER MFD Vision-1 TAWS Cabin Display WAAS/GPS Antenna ASU Configuration Module Configuration Module UniLink Internal GPS/WAAS WAAS/GPS Antenna Internal GPS/WAAS UniVision GPS/GNSS IRS or GPIRS Radar Doppler Display UNIVERSAL UNIVERSAL UNS-1Fw FMS UNS-1Fw FMS FGS Air Data UNS-1Fw NCU AFIS Fuel Flow UNS-1Fw NCU TACAN VOR DME UNIVERSAL SSDTU The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 5 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual Single WAAS FMS with LP/LPV Monitor Installation Description The use of an LP/LPV Monitor is an optional feature that can be used in an aircraft with a single WAAS FMS which requires LP/LPV capability but may not have room for a second WAAS FMS. The LP/LPV Monitor operates without a CDU or configuration module. The LP/LPV Monitor functions as an independent sensor in which redundant equipment is required to meet the integrity goals for precision approach types. The LP/LPV Monitor has its own GPS/WAAS sensor which can be wired and configured as a second GPS sensor with the single FMS. NOTE: The block diagram illustrates the various types of inputs and outputs to and from the FMS. The actual set of inputs and outputs in any particular installation is dependent on the suite of avionics equipment on the aircraft. FPCDU UNIVERSAL Video DATA NAV VNAV DTO LIST PREV FUEL FPL PERF TUNE MENU NEXT A B H C D 1 2 3 4 5 6 7 8 9 E F G I J K L M N BACK O P Q R S T ON / OFF DIM U V W X Y Z 0 MSG ENTER MFD Vision-1 TAWS Configuration Module Internal GPS/WAAS Cabin Display Internal GPS/WAAS ASU UniLink WAAS/GPS ANTENNA WAAS/GPS ANTENNA UniVision GPS/GNSS IRS or GPIRS Radar Doppler FGS UNIVERSAL UNIVERSAL LP/LPV MONITOR UNS-Fw FMS Display Air Data AFIS Fuel Flow LP/LPV MONITOR UNS-1FW WAAS FMS TACAN VOR DME UNIVERSAL SSDTU The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 6 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual B. System Components The basic UNS-1Fw installation consists of the FMS (containing the navigation computer and GPS/WAAS sensor), Control Display Unit (CDU), configuration module, Data Transfer Unit and a GPS/WAAS antenna. (1) Navigation Computer Unit (NCU), P/N 3192-XX-11110X The UNS-1Fw FMS NCU is an ARINC 600, 2MCU size, remotely mounted unit which houses the system’s central processing unit (CPU), the navigation sensor interface circuits, the flight guidance system interface, fuel flow interface, and the navigation database. The unit processes data from DME, TACAN, VOR, Air Data, Fuel Flow and up to five long-range navigation sensors. A radar joystick input can also be accommodated. The long-range Nav sensors act in addition to the multichannel scanning DME and VOR sensing capability integrated into the basic circuit. At installation the system is configured with the number and type of long-range navigation sensors which will optimize the FMS to the aircraft’s specific requirements. The NCU can be removed from the aircraft rack without loss of the database memory. The NCU is available in different sensor compatibility configurations with five optional fuel flow configurations: Analog (AC or DC), Digital (Pulse or Frequency), and ARINC 429 Digital. It incorporates an Ethernet connection for transfer of data to Terrain Awareness Warning System (TAWS), Application Server Unit (ASU), Universal Cockpit Display (UCD) and Vision-1 as well as future systems. (2) Configuration Module, P/N 31921 The configuration module is a serially connected EEPROM designed to store configuration data that is specific to the aircraft installation, The EEPROM is attached to the NCU mounting rack. The user is able to view and initialize the aircraft configuration through specially designed menus that can be accessed through the CDU. Subsequent modifications to the configuration are possible but restricted through software interlocks. The Configuration Module receives and transmits data to the NCU via private serial communications busses. (3) Flat Panel Control Display Unit The UNS-1Fw can use a 5-Inch FPCDU or 4-Inch FPCDU for the primary and remote displays. The CDU provides the operator with all the controls necessary to communicate with the navigation computer and all associated navigation sensors. The CDU allows manual data entry, system mode selection, computed and raw data displays, control (selection and deselection) of navigation sensors, and system message displays. The CDU also provides remote control and tuning of the TACAN and aircraft radios with the RTU installed. Certain annunciations concerning system and sensor faults are also included in the CDU displays. The Configuration Module is programmed through the CDU at installation. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 7 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual The CDU features a full alphanumeric keyboard. Keys for backspace, +/-, ON/OFF/DIM, MSG, and ENTER are also provided. Five line select keys are located on the left and right sides of the eleven-line display for cursor control and menu selection. Below the display is a set of keys for operations control and data display. These keys include mode keys for data display and selection (DATA), fuel management (FUEL), lateral steering (NAV), vertical navigation (VNAV), flight planning (FPL), access to performance data (PERF), direct-to operations (DTO) and radio tuning functions (TUNE). In addition, special mode keys provide access to active mode menus (MENU) and to lists of applicable items (LIST). Two operation keys provide access the next and previous page of the active mode (NEXT and PREV). The CDU supports data display on eleven lines with 24 characters each in two different character sizes. Graphics displays for special photo, search and surveillance flight patterns are presented, and are available for future graphic growth capabilities. Mode selection and data organization is in a “chapter and page” format with menu selections being made by the use of the mode select keys and/or “soft” line select keys. This allows two levels of selections to exist on the same page (screen). Data is always entered into the system at a cursor location, which is determined by the system computer program, with certain operator-selected options. The CDU receives all required power for operation from the NCU (with the exception of 5 or 28 V keyboard backlighting which is provided from the aircraft dimmer bus). (4) LP/LPV Monitor, P/N 3116-5X-1110 The LP/LPV Monitor is an optional feature that can be used in an aircraft with a single WAAS FMS which requires LP/LPV capability but may not have room for a second WAAS FMS. The LP/LPV Monitor operates without a CDU or configuration module. The LP/LPV Monitor functions as an independent sensor in which redundant equipment is required to meet the integrity goals for precision approach types. The LP/LPV Monitor has its own GPS/WAAS sensor which can be wired and configured as a second GPS sensor with the single FMS. (5) Data Transfer Unit (DTU), P/N 1406–( ), 1407–( ) The Data Transfer Unit (DTU-100) is an IOMEGA ZIP drive housed within a protective case. Model 1406 may be panel mounted in the cockpit for convenient access. Model 1407 consist of a DTU-100, housed in a portable carrying case. The wire harness plugs into sockets mounted in the aircraft that are wired to the NCU. The DTU-100 is used to update the navigation databases within minutes. The update is contained on Zip disks that are distributed periodically to subscribers. Database updates are loaded into the FMS over a 10base-T Ethernet connection from the DTU100. The DTU-100 receives power from the NCU and communicates directly with it through a digital bus. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 8 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual The DTU-100 is also used to load aircraft specific performance data. The DTU-100 may also load pilot-defined flight plans and checklists created with off-line flight planning software loaded into an IBM compatible computer. FMS in-flight data parameters can be written to a disk utilizing the DTU-100. The Maintenance Log stored in non-volatile memory also may be written to a disk. FMS configuration data can be written to a disk and be loaded to another FMS to update its configuration data. (6) Solid State Data Transfer Unit (SSDTU), P/N 1408-( ), 1409-( ) The SSDTU is designed to replace the DTU-100 as a data upload and download device interfacing with other Universal Avionics’ line replaceable units (LRU). The SSDTU replaces ZIP disk technology with flash memory technology. Two accessible data storage device ports are built into the faceplate of the SSDTU. These ports support Universal Serial Bus (USB) and Secure Digital (SD) data storage devices and function as disk drives. The SSDTU transfers data files between the selected data storage device and other LRUs using an Ethernet bus. The SSDTU has three serial digital buses that are each capable of receiving and transmitting data. The first is a single EIA-485 (RS-422) bus which can be used to exchange data between FMSs. The second is an Ethernet bus, which consists of an eight port Ethernet switch used to exchange data with up to eight UA Ethernet network compatible LRUs such as the FMS, TAWS and Vision-1 systems. The transfer rate to the client is the same or better than a DTU-100. The third is an EIA232 bus that provides access to the diagnostic interface. The SSDTU is available in two models, the fixed installation model that is permanently installed in the aircraft and the portable model which is carried into the aircraft, attached to an interface connector, used, then disconnected and removed prior to flight. The SSDTU is the same fit as a DTU-100, although using USB and SD data storage devices allows more flexibility for SSDTU installations. The functions of the discrete inputs that were used to enable or disable Ethernet or EIA-485 data bus communications in the DTU-100 have been disabled in the SSDTU. The functions are now enabled by software. (7) EFIS Radar Panel, P/N 1015-1-XX (Lear 60 Pro Line 4 Installations only) The EFIS Radar Panel (ERP) provides two knobs with push buttons and six buttons for pilot control of various EFIS and RADAR functions of the Collins Pro Line 4 Avionics System. The ERP also receives pilot inputs from the Pro Line 4 Altitude Awareness Panel (AAP) and the Pro Line 4 Course Heading Panel (CHP). All pilot/user inputs are forwarded to the FMS navigation computer via a CSDB interface. The FMS/ERP combination replaces the Collins CDU. The FMS becomes the navigation control or External Navigator. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 9 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (8) WAAS (SBAS) GPS Antennas A WAAS (SBAS) GPS antenna approved under TSO C190 must be installed for each WAAS (SBAS) FMS system. There are three approved antennas to choose from: P/N 10708 WAAS (SBAS) GPS antenna, P/N 10709 WAAS (SBAS) GPS/Sirius antenna and P/N 10710 WAAS (SBAS) GPS/XM Weather and Radio antenna. If replacing an existing FMS system with a WAAS (SBAS) FMS system, the antenna must be replaced with a TSO C190 approved antenna. None of the previous antenna part numbers, 10705, 10706, etc., are compatible with the WAAS (SBAS) FMS GPS. The WAAS (SBAS) GPS antenna P/N 10708 is a single element antenna. The 10708 antenna has the same footprint as the 10705 and 10706 antennas and can be directly replaced by the 10708 antenna without any modifications. WAAS (SBAS) GPS/Sirius antenna P/N 10709 is a dual element antenna which can provide reception for WAAS (SBAS) GPS and WSI InFlight weather. This antenna is ideal for aircraft that have limited locations for antennas. If The 10709 is used as a replacement for a previous antenna installation, the 10709 has the same footprint as the 10705, 10706 and 10708 antennas, although modification to the aircraft is necessary to accommodate the dual connectors. P/N 10709 is not a replacement for antenna P/N 10705 when used for GLONASS. WAAS (SBAS) GPS/XM Weather and Radio antenna P/N 10710 is a dual element antenna which can provide reception for WAAS (SBAS) GPS and XM Weather and Radio. This antenna is ideal for aircraft that have limited locations for antennas. If The 10710 is used as a replacement for a previous antenna installation, the 10709 has the same footprint as the 10705, 10706 and 10708 antennas, although modification to the aircraft is necessary to accommodate the dual connectors. P/N 10710 is not a replacement for antenna P/N 10705 when used for GLONASS. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 10 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual C. System Interfaces (1) Navigation Sensor Interface The FMS is capable of interfacing with the following short-range sensors: DME, Radio Reference Sensor (RRS), TACAN, and VOR radio inputs. The FMS is also capable of interfacing with the following long-range sensors: Doppler, LORAN C, Inertial Reference sensors, GPS, GPS aided Inertial Reference System (GPIRS), GNSS, WAAS, and GPS Landing System (GLS). (2) Fuel Flow Interface The system is capable of accepting five types of fuel flow signals: DC, AC RMS voltage, pulse width, pulse frequency, and digital. (3) Analog DC fuel flow inputs will not exceed 12 Volts AC RMS fuel flow inputs will be in the range of 0-8 VRMS Pulse frequency fuel flows will have a scaling of 1-400.0 pph/Hz while pulse width fuel flows will be in the range of 1-400.0 pph/msec The required accuracy for pulse width and pulse frequency signals will be sufficient to measure signals in the input range 1-800 msec or 1-2000 Hz with an accuracy of 1% Digital fuel flow may be received over a digital input bus Auxiliary Power Unit Interface Auxiliary power unit (APU) fuel flow is a configurable option on the FMS. The FMS accepts automatic APU fuel flow signals and computes the APU fuel flow rate. The FMS also accepts manual APU fuel information. (4) Ethernet Interface The FMS is capable of interfacing with an Avionics Local Area Network. The FMS has an Ethernet controller that connects to a 10base-T twisted shielded pair cable. (5) External Systems Management The FMS interfaces with the Terrain Awareness Warning System (TAWS). The FMS contains a configuration option that tells the FMS the source of the TAWS user interface pages. The FMS interfaces with the Universal Cockpit Display (UCD) and Application Server Unit (ASU). The FMS sends flight plan information to the UCD or ASU via the FMS crossfill bus. The FMS AFIS mode supports interface with the Airborne Flight Information System and provides support for remote messaging, terminal weather, winds aloft, and remote flight plan services. The FMS interfaces with an external UniLink unit that supports air-to-ground digital data communications. UniLink uses a variety of media, such as VHF radio and in-flight telephones to exchange data with a ground base computer. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 11 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual The FMS tunes the following radios: VHF NAV #1 and VHF NAV #2 (navigation); VHF COM #1, VHF COM #2, and VHF COM #3 if installed (voice communication); ADF #1 and ADF #2 (automatic direction finder); and ATC (air traffic control). The FMS supports 25 kHz or 8.33 kHz tuning for the VHF COM radios. For COM tuning, the FMS interfaces with both a Radio Tuning Unit and a Radio Control Unit. COM radio tuning and feedback is accomplished via a CSDB interface. The FMS provides the capability to configure the system for advanced performance which will work with an aircraft specific database to provide takeoff reference speeds and engine limits, climb/cruise engine limits, and landing reference speeds. This function is incorporated as a table driven series of interpolations that use the charts from the AFM in a digitized form. The performance database is stored in the FMS non-volatile memory. The FMS provides the capability to compute and display Equal Time Point information on the CDU. The Equal Time Point is computed as a point along the entered flight plan where it will take an equal amount of time to fly direct to either of the two pilot-specified enroute alternate airports. The FMS provides the capability to compute and display Point-of-No-Return information on the CDU. The Point-of-No-Return is computed as a point along the entered flight plan where the fuel remaining is equal to the amount of fuel needed to fly directly back to a pilot-specified Coast Out airport with fuel reserves. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 12 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual D. FMS Components (1) CPU Board The CPU board is the master processor within the FMC. The processor is a Motorola PowerPC 8270 microprocessor operating at 400 MHz. The CMOS system RAM serves as a non-volatile scratchpad used to preserve specific data in the event of an in-flight power interrupt. Flash memory is used for database storage because it does not require battery backup, proving a more efficient and economical storage medium than battery backed CMOS static RAM. The following functions are incorporated into the CPU board: 16 Megabyte Flash EEPROM memory for program storage 32 Megabyte Flash EEPROM memory for database storage 2 Megabyte EEPROM for bootstrap program 4 Megabyte battery backed static RAM 2 Kbytes Serial EPROM for internal Configuration Module Battery backed real time clock device for system time keeping and timer interrupt generation One I2C port for communication with external Configuration Module One TTL level serial port for communication with the front panel display Two RS–232 communications ports (One of these ports does not leave the CPU board and is used for download of software via a remote computer while the other port is used for connection to a remote terminal.) One 10base-T Ethernet port for communications with the System-1 local area network Thirteen discrete input signals and eleven discrete output signals 28 V input bus power failure detection signal connected to the processor’s nonmaskable interrupt One JTAG (Joint Test Action Group) port that contains 128 bytes of serial EEPROM with the Ethernet MAC address for the LAN One analog to digital converter which is 8 bits and has a full-scale value of 5V One set of system configuration jumpers (comprised of 16 individual jumpers) Temperature sensor for over temperature alerting The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 13 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (2) WAAS/ARINC and WAAS/Analog Subsystem Boards The WAAS/ARINC board includes a MPC8270 central processor, dual-port RAM (DPRAM), and two field programmable gate arrays (FPGA) with dissimilar design. The MPC8270 communicates with the GG12W receiver on the WAAS/Analog board through two RS-232 connections. It controls the analog I/O and discrete I/O on the WAAS/Analog board through a serial peripheral interface (SPI). ARINC I/O functionality is accomplished on the WAAS/ARINC board through FPGA #1. FPGA #2 is used to monitor critical ARINC output buses for faulty transmission. An RS232 serial port is used to provide diagnostic display and flight data recording (FDR). The WAAS/Analog board contains a GG12W receiver. The receiver is the source of three-dimensional position and velocity, time, and WAAS protection levels. The WAAS/Analog board also provides critical analog output and discrete I/O. Critical analog/discrete output including deviations, alert flags and level of service (LOS) are monitored internally for faulty transmission. The WAAS subsystem interfaces with a configuration module through the FMS via DPRAM. The WAAS subsystem obtains the following information from the FMS configuration module: Aircraft information (antenna offset). The Antenna offset translates the GPS/WAAS antenna position to the aircraft navigation center (typically the glideslope antenna). Approved Satellite Based Augmentation System (SBAS) service provider(s) ARINC I/O ports configuration Display bus type configuration High/low level analog deviation output configuration Cross-channel monitoring enabled or disabled I/O Capabilities of the WAAS Subsystem Boards Discrete Inputs – XChan Fail In, XChan LOS1, XChan Nav Valid, XChan Vert Valid Discrete Outputs – Nav Flag, Nav Valid, Vert Flag, Vert Valid, LOS1, LOS2, LOS3, XChan Fail Out, WAAS Fault, Time Marks NOTE: Alert (Nav Flag or Vert Flag) and Valid (Nav Valid or Vert Valid) Flags can be either high or low level outputs depending on the FMS part number. NOTE: The levels of service (LOS) in use by the WAAS Subsystem are LPV, LNAV/VNAV, LNAV, and Not Available. Analog Outputs – Lateral Dev and Vertical Dev NOTE: Lateral and Vertical Deviations can be scaled high or low depending on the FMS configuration. Analog Inputs – XChan Lateral Dev and XChan Vertical Dev NOTE: Lateral and Vertical Deviations can be scaled high or low depending on the FMS configuration. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 14 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual ARINC 429 Inputs/Outputs – Configurable Transmitters and Receivers, 2 Transmitters (743A Output, XChan Out), 4 Receivers (Offside FMS, XChan In, XChan Guidance Bus1, XChan Guidance Bus2). NOTE: The number of ARINC429 transmitters and receivers available is dependent on the FMS configuration. (3) Auxiliary Board The Auxiliary Board uses a Motorola 68332 processor with 256 KB of RAM and 256 KB of flash EEPROM. Two CSDB transmitters and four receivers 128 Kilobyte by 16 Flash EEPROM for program storage 4 Kilobyte by 16 of dual port RAM for communication with the main processor Four pulse/analog fuel flow inputs Input signals for analog heading Input signals for board type detection The four differential fuel flow inputs incorporated in the Auxiliary board, in an alldigital aircraft, allows the elimination of the analog board and possible replacement by a second ARINC board. The fuel flow multiplexer switches these inputs to a RMS converter, a counter, or an A/D converted depending on the type of input. Analog Heading is located on the Auxiliary board to allow an all-digital aircraft access to this variable without an Analog board. The Roll Steering command is under control of the CPU even though it is located on the Auxiliary board. I/O Capabilities of the Auxiliary Board Discrete Inputs – HDG Mag/True Switch, HDG Valid Analog Inputs – Autopilot Reference Analog Outputs – Roll Steering Synchro In – Heading Synchro Pulse/Analog FF – 4 Fuel Flow Sensors NOTE: Accepts either pulsed or analog differential fuel flow sensors. CSDB In – 4 Input Ports (VOR, ADF/MFD, DME) CSDB Out – 2 Output Ports The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 15 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (4) Analog Board (Optional) The Analog board communicates with the CPU through dual port memory. All processing is accomplished using an on-board Motorola 68332 processor. The Analog board converts four types of analog inputs to digital for processing through DPRAM by the FMC: Discrete, Synchro/Resolver AC, DC, and analog air data and provides analog, discrete, and synchro outputs. I/O Capabilities of the Analog Board Discrete Inputs – Altitude Valid, Attitude Valid, TAS Valid, SAT Valid Discrete Outputs – Digital Valid, Pitch Valid Analog Outputs – Pitch Command, To/From Synchro Inputs – Instrument Reference (Altitude/Attitude Reference), Alt Coarse, Alt Fine or Pitch Synchro Outputs – Bearing, Desired Track ARINC 561 – Refer to the Label descriptions for this output in the WAAS FMS Interface Manual, Report Number 34-60-53 Digital to analog converters are used to generate PITCMD, TO/FR, and Synchro Resolver outputs. In addition, the discrete outputs PITCHVAL and DIGVAL are implemented using a discrete latch. (5) NOTE: If the FMS is configured with an Analog board, the WAAS/ARINC I/O capabilities are reduced. Refer to the Equipment Specification section of this manual for details. ASCB Version A Board (Optional) The ASCB board provides the FMS with an interface to the ASCB Version A data bus that was developed by Honeywell and supplements ARINC, CSDB and analog interfaces of the FMS. The ASCB board hardware supports data bus Version A only. ASCB is a multi-user serial synchronous digital communications bus. The ASCB board provides an interface between the FMC and ASCB bus. When configured with the ASCB board, the FMS provides the following capabilities: Transmit navigation display on the ASCB bus. Transmit guidance and mode data on the ASCB bus. Transmit flight plan and map background data on the ASCB bus. Transmit Vspeeds on the ASCB bus. Create and store radar waypoints using the MFD input data on the ASCB bus. Receive FGS, EFIS, and MFD data on the ASCB bus. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 16 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (6) Power Supply The Power Supply converts 28 VDC aircraft power to +5 VDC, +15 VDC and –15 VDC for FMS circuitry and the Configuration Module and provides output voltage monitoring and current limiting. If power is lost or low voltage is detected, an interrupt will be generated. The CPU will then store the necessary registers in non-volatile memory for an orderly shutdown. Enough capacity is designed into the power supply to provide system power for a minimum of 10 milliseconds following a power fail warning. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 17 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual E. FMS Functions (1) Power Control, Initialization, and Configuration At power up, the FMS determines the installed configuration of the computer. The FMS uses data from the configuration module to configure the FMS if the configuration data is valid. At power up, the FMS performs self-tests to ensure system integrity and proper operation. The FMS provides power-up initialization after a normal power down, after a standby power down, and after a power failure. The FMS provides power-down control for manual power down, standby power down, and power failure. (2) Navigation The FMS best computed aircraft position is determined by using position inputs from all available navigation sensors and DME distance information from the scanning DME. If either an RRS or one of the supported TACAN receivers is installed, TACAN information is also used. The system searches the navigation database to determine which DME or TACAN stations are within range (approximately 250 nm) and sequentially tunes each station. The aircraft position is computed by interrogating multiple DME or TACAN stations and correlating the tuned stations with their known geographic coordinates. Correction for slant range is accomplished by using known station elevation and aircraft altitude. The DME derived position is then integrated with the position information derived from available long-range sensors. If the aircraft is out of DME range, the FMS relies on long-range sensors for position information. The FMS provides the pilot with course to waypoint, ETA, distance to waypoint, maximum airspeed (VMAX) for curved legs, wind, and ground speed information. In addition the FMS provides desired track, bearing, crosstrack, lateral deviation, vertical deviation, related data to the flight guidance system (FGS) for the HSI displays, and roll and pitch steering commands for the autopilot/flight director system. (3) Position Uncertainty The FMS calculates position uncertainty and displays the resulting value as ANP. The FMS uses as the alerting limit either the operator manually entered RNP (required navigation performance), the procedural RNP as defined in the navigation database, or the system defaults based upon the phase of flight. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 18 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (4) Vertical Navigation The FMS provides vertical guidance and steering data for a Path Descent mode. This includes the Enroute, STAR, and Approach segments of the flight plan up to the Missed Approach Point. All ARINC 424 leg types are supported, including procedure turns, holding patterns, and floating terminator type legs. The FMS allows up to six Vertical Navigation (VNAV) fixed terminator type waypoints to be displayed and edited on the VNAV Path pages. All waypoints that are pre-filled are automatically pre-filled in reference to the flight plan waypoints. On the VNAV Path pages the operator may also define an Offset, which is a vertical waypoint referenced off a particular flight plan waypoint. The offset may be in either a positive or negative direction along the defined flight plan, and will have an altitude defined by the operator. The Flight Plan pages have been designed to allow the operator to enter and edit altitudes for any leg in the flight plan that has a fixed waypoint terminator. In addition, a prompt will be provided on the Flight Plan pages to allow access to the VNAV pages in order to define a VNAV Offset waypoint. The FMS automatically converts all STAR and Approach procedural crossing altitude constraints from the database that are variable (At/Below, At/Above, and Window) to fixed altitudes. These altitudes will be displayed on the Flight Plan pages and automatically pre-filled into the VNAV pages. The FMS provides tactical VNAV modes. These modes allow the operator to use the FMS to maneuver the aircraft vertically without regard to the lateral path of the aircraft. Flight Level Change (VFLC) mode uses a set of preprogrammed airspeed/Mach profiles selected by the operator to climb and descend the aircraft. In VFLC mode, the FMS outputs an airspeed target so the aircraft FGS can pitch the aircraft to achieve the target airspeed. VNAV modes are mutually exclusive; the FMS can be in only one vertical mode at a time. The FMS is capable of synchronized VNAV operation. In synchronized operation, all flight crew entries on the CDU pertaining to the VNAV function are synchronized between the left and right FMS. The FMS provides a selectable altitude correction function to compensate for extreme cold temperatures. Temperature compensation applies only to approach altitudes, including approach transition and missed approach. (5) Lateral Guidance and Steering The lateral guidance and steering function provides guidance displays showing the relative position of the aircraft to the desired flight path. This function also provides a steering command to make the aircraft follow the desired flight path. These capabilities are provided for the entire ARINC 424, path terminator leg set. The FMS is capable of synchronized LNAV operation. In synchronized operation, all flight crew entries on the CDU pertaining to the LNAV function are synchronized between the left and right FMS. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 19 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (6) Waypoint Sequencing The FMS incorporates automatic turn anticipation for leg changes along the flight plan. Turns are initiated at a distance based on ground speed, leg change magnitude, and roll steering bank limits for the present altitude. Turns at "fly-over" waypoints are initiated over the waypoint. (7) Direct-To The FMS is capable of initiating Direct-To maneuvers to waypoints and airports on or off the flight plan. If the Direct-To waypoint is off the flight plan, the system prompts the pilot to redefine the next (NX) waypoint so that it may be linked to the flight plan. The FMS will provide the capability to divert to the nearest airports. (8) Heading Mode The pilot is allowed to select and fly a desired heading using the CDU keyboard. If the IMS-02, ProLine 2, ProLine 4, or Primus 1000 EFIS is installed, the system will accept heading inputs from the heading bug knob. The Heading Mode provides the ability to be armed so that it may automatically intercept the current navigation leg. (9) Selected Crosstrack The FMS provides the ability to select and fly a course parallel to a leg defined by two FROM-TO waypoints. When this feature is selected, the system indicates the selection via the crosstrack annunciator. This feature is not available for Pseudo VOR outbound legs or in approach mode. The mode will be maintained when sequencing onto a fixed track leg, provided the course change is such that it is possible to do so. (10) Holding Patterns The FMS provides Holding Pattern selection and definition using graphical depiction of the available holding pattern on the display. The pilot defines the pattern or selects one from a database via the CDU keyboard. The FMS provides the ability to arm a holding pattern at a waypoint in the flight plan that is ahead of the current position of the aircraft. The FMS provides the capability to define holding patterns at present position. The hold may be manually or automatically activated. Once the holding pattern is activated, the aircraft proceeds to the holding fix and automatically performs the appropriate entry to the pattern. The pilot must manually terminate the hold if it is an HM (Hold Manual) leg type. If it is an HA (Hold at an Altitude) or HF (Hold at a Fix) leg type, then the FMS will automatically sequence the leg after the appropriate procedure is flown. (11) Flight Planning The FMS facilitates flight planning and includes features such as SIDs, STARs, and Approaches for use in terminal areas and Victor/Jet airways for the enroute portion. Flight plans can be dynamically defined, crossfilled from another FMS, selected from a previously defined pilot route or company route database, or loaded from a disk or AFIS unit. The FMS is able to synchronize the flight plan with the offside FMS. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 20 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual The flight planning includes custom lists from which the pilot can easily select desired options, eliminating time consuming keyboard entries and associated errors. The FMS provides a Fix Page function, which allows the operator to enter up to nine waypoints and obtain dynamic range and bearing from each of these waypoints. In addition, this function determines the location at which each of these waypoints is abeam the flight plan. The FMS provides the ETA and distance to the Abeam Point, as well as messaging to alert the pilot when the aircraft is approaching the Abeam Point. The FMS provides a Lat/Long Crossing function, which allows the operator to enter up to four latitudes or longitudes. The FMS then computes the corresponding latitude or longitude of the intersection point along the flight plan. The FMS provides the ETA and distance to the Lat/Long Crossing Point, as well as messaging to alert the pilot when the aircraft is approaching the Lat/Long Crossing Point. (12) Terminal Area Procedures The FMS is capable of flying published SIDs and STARs with procedural legs such as heading-to-radial, heading-to-altitude, course-from-fix-to-DME-distance, and DME-arcs. Up to nineteen additional leg types (combinations) are available. (13) Approach Mode The FMS approach mode provides the pilot with ILS-like guidance while flying FMS approaches. During an FMS approach, the system provides signals like those of an ILS for flight director or autopilot coupled approaches. The approach is accessed from the navigation database or the pilot may define it by entering the approach waypoint and the reference NAVAID (if required). The system is capable of defining and flying VOR, RNV (VOR DME), RNV (GPS), NDB, TACAN, ILS, LOC, BC, VFR, GLS, and GWS (FAA FIAS configuration only) type approaches. During an ILS, LOC, or BC approach, the FMS uses the localizer signal for roll steering. (14) Precision Approaches (RNAV (GPS)) The WAAS subsystem adds the capability to fly precision RNAV (GPS) approaches to the LPV Approach Category (Level of Service). During the final phase of the precision approach (between the FAF and EOA), the WAAS subsystem independently provides the guidance both laterally and vertically. (15) Integrity Monitoring The WAAS subsystem monitors the integrity of the position output using a step detector, WAAS-provided integrity monitoring, and RAIM-based fault detection and exclusion (FDE) algorithms. (16) RAIM Prediction The WAAS subsystem supports predicting the availability of fault detection (FD) receiver autonomous integrity monitoring (RAIM), at a single space-time point. It also supports the prediction of RAIM availability for a period of +/-15 minutes around the estimated time of arrival (ETA) at a fix. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 21 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (17) Cross-Channel (XChan) Monitoring The WAAS subsystem provides XChan monitoring for LP/LPV approaches flown in the offside FMS. This improves the overall system integrity so as to meet the required integrity for LP/LPV approaches. Based on its own position, the WAAS subsystem monitors the guidance data from the offside FMS for discrepancies. If an intolerable discrepancy is detected, the WAAS subsystem sends a LON alert to the offside FMS. As a result, the offside FMS sets its guidance flags in view. If the offside FMS fails to set the guidance flags in view, the WAAS subsystem further disconnects the digital guidance bus of the offside FMS from display systems and sets the analog guidance flags of the offside FMS in view. XChan monitoring can be disabled through the FMS configuration that is confirmed by the installer. (18) RNP RNAV Functionality The WAAS FMS provides an ANP/RNP display on the Nav pages that depicts FMS calculated Actual Navigation Performance (ANP) and Required Navigation Performance (RNP). RNP represents the maximum allowable value for the current procedure or flight phase. The computed ANP algorithm represents the 95% Total System Error (TSE) as required in DO-236B, Minimum Aviation System Performance Standards: Required Navigation Performance for Area Navigation, par. 2.1.1 and as described in par. 1.7.2.1. RNP boundary settings may be manually entered (priority 1), coded in the navigation database (priority 2), or determined by phase of flight. The following table describes RNP boundary settings as a function of the above criteria. Priority Source RNP Boundary Settings 1** Manually Entered (Refer to “FMS RNP Annunciation” section below) 5.0 nm Maximum 2 Navigation database Procedure dependent 3 Default Phase of Flight Oceanic 4.0 nm Enroute 2.0 nm Terminal 1.0 nm Approach 0.3 nm **The manually entered RNP value will remain and the WAAS FMS will use that value until it is manually removed or overwritten, within a given power up cycle. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 22 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual Dual multi-sensor FMS installations which integrate GPS/WAAS sensors in the WAAS FMSs meet the equipment and accuracy requirements of 90-105A. Operational approval must be obtained from the appropriate authority. The WAAS FMSs also complies with equipment and accuracy requirements of AC 90-96A paragraph Appendix 1 for BRNAV (RNP-5) when operating in Class I airspace, without time limits. Inclusion of this function in the FMS does not constitute an Operational Approval for RNAV RNP SAAAR procedures. FMS RNP Annunciations The following annunciations are associated with ANP/RNP criteria: POSITION UNCERTAIN Any time the ANP value exceeds the RNP value, a Position Uncertain message is provided. Under this condition, a POS annunciation is displayed on the CDU. If the Position Uncertain condition occurs during an approach, the lateral and vertical deviation flags are placed in view and will remain in view until the FMS position is no longer uncertain. VERIFY MANUAL RNP This message displayed on the FMS CDU will be removed after it is displayed once. (19) 1. A manual RNP has been entered on the NAV pages, a flight phase transition occurs and the new flight phase RNP Limit is less than the manual RNP. 2. A manual RNP has been entered on the NAV pages and a leg with a lower database RNP value is sequenced to in a linked flight plan. WAAS Subsystem Functions Navigation solution: The WAAS subsystem provides a navigation solution for all phases of flight using GPS augmented by WAAS. The navigation solution includes antenna position, time, velocity, and other pertinent data. Guidance for approaches with final approach segment data block (FAS DB): The FAS DB stored in the FMC navigation database contains the designated SBAS service provider ID, the waypoints defining the FAS path and alert limits for the approach. Based on the information, the WAAS subsystem determines the available approach service level LNAV, LNAV/VNAV or LPV). The WAAS subsystem further provides lateral/vertical guidance for the selected approach relative to the aircraft navigation center position. The navigation center position is translated from the antenna position using the antenna offset stored and confirmed in the FMS configuration module. The WAAS subsystem then continuously monitors whether the applicable alert limit requirements are met. The WAAS subsystem notifies the pilot via guidance flags if loss of navigation (LON) occurs. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 23 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual ARINC I/O and critical analog/discrete output: In order to meet the criticality level for precision approaches, the WAAS subsystem processes all FMS ARINC I/O and critical analog/discrete outputs. The WAAS subsystem configures its ARINC I/O and analog/discrete output based on the information in the FMS configuration module. For oceanic, en route, terminal, and approach (without FAS DB) phases of flight, the FMS transmits the guidance data and other ARINC data to external systems. For approaches with FAS DB, the WAAS subsystem substitutes the FMC guidance data with its own computed deviations and guidance flags. WAAS CPU monitor: The WAAS subsystem monitors the FMS CPU Integrity by comparing its computed position output to the FMS System Position. If there is a discrepancy, the WAAS subsystem will independently flag the FMC guidance busses. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 24 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual 2. Operation A. General Detailed operating procedures for the FMS are provided in the Operator’s Manual for the specific software loaded into your NCU, for example, SCN 1000.X or 1100.X. The operating procedures presented here are intended to provide information necessary to perform tasks later in this manual. B. Flat Panel Control Display Unit The FMS Operator’s Manuals introduces the CDU, explains the CDU operating philosophy, and provides a detailed explanation of the keyboard keys and their associated functions. The CDU, as part of a Flight Management System (FMS) provides the operator with all the controls necessary to communicate with the navigation computer and associated navigation sensors. The CDU presents an eleven-line display using two-character sizes and has a full color, liquid crystal display. The operator may adjust display brightness. Line select keys are located on either side of the display. Individual Line Select Keys are referred to as [1L] through [5L] and [1R] through [5R]. Function keys are immediately below the display and an alphanumeric keyboard is below and to the right of the function keys. The CDU provides for manual data entry, system mode selection, computed and raw data displays, control (selection and deselection) of navigational sensors, and system message displays. The following paragraphs provide general information about operator–CDU interface which is applicable to installation and checkout of the FMS. (1) Cursor Data is always entered into the system at a cursor location. The cursor marks variable parameters by means of reverse field. When appropriate, the cursor location aligns with one of the ten line select keys used to control the cursor. The home position of the cursor is usually off the display when a page is initially accessed, although some pages have a cursor default position that is on the screen. Pushing the ENTER key completes the entry of data. If there is a logical next field for data entry, the cursor will automatically advance to this next field when [ENTER] is pushed. (2) Item Selection 1 2 3 4 5 6 OPT LIST 1/ 1 select #no sensor dc linear ac linear pulse freq pulse width digital RETURN® Sample Display Selections are made with the line select keys whenever possible. In some cases a combination of line select keys and reference numbers are used on the same display page. This allows two levels of selection to exist simultaneously on the same display. For example, while the content or nature of a list is controlled by the line select keys, The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 25 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual an item from that list can be selected by using a reference number. In this illustration (OPT LIST 1/ 1) the reference numbers appear to the left of the items available for selection. The cursor is on the dash in the data entry field next to the pound (#) sign. To make a selection, input the number corresponding to your choice and push [ENTER]. The arrow next to the word RETURN points to the adjacent line select key [5R]. Pushing [5R] will return the display to the previous page. Any selection that will change the active flight plan, guidance of the aircraft, or the stored database requires confirmation. Confirmation is accomplished by pushing the line select key a second time or by pushing [ENTER]. Selection of fields that do not require confirmation will cause the page or mode change to occur immediately when the corresponding line select key is pushed. (3) Information Display Color and graphics are used to draw attention to the most important items on a display. Background colors and/or boxes are used to group data into important areas such as control or selection boxes. (4) Display Control Pushing [ON/OFF DIM] for initial power-up energizes the system and initiates self test of the navigation computer. When self-test is initiated, the Self-test page is displayed. The Self-test page is followed automatically by the Initialization page if all tests are successfully completed. If a failure that would cause the system to be unusable occurs, the Initialization page will not appear. Once the Initialization page appears, no other page can be displayed until the initialization data is accepted. (5) Power/Display Control Page BRIGHT® DIM® CANCEL® DISPLAY® OFF/STBY® Power/Display Control Page After the system is turned on, pushing [ON/OFF DIM] displays the options BRIGHT, DIM, CANCEL, DISPLAY and OFF/STBY. Pushing the associated line select key to one of these options selects the option. BRIGHT – Pushing LSK [1R] BRIGHT slowly increases the brightness of the display as the key is held down until reaching maximum brightness. DIM – Pushing LSK [2R] DIM slowly dims the display as the key is held down until reaching minimum brightness. CANCEL – Pushing LSK [3R] CANCEL will cause the control page to be removed from the active display page. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 26 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual DISPLAY – Pushing LSK [2R] DISPLAY will cause the parallax adjustment page to be displayed. OFF/STBY – Pushing LSK [5R] OFF/STBY displays the CONFIRM OFF/STBY page. This page has two options (CONFIRM OFF and CANCEL) selectable using the line select keys. Selecting CONFIRM OFF will turn the system off. Selecting CANCEL will return the display to the Power/Display Control page. UP® DOWN® CANCEL® Parallax Adjustment Page To adjust the parallax for the line select keys the adjustment page presents three options (UP, DOWN, and CANCEL) using the line select keys. UP – Pushing LSK [1R] UP adjusts the entire display upward by as much as one-half character. DOWN – Pushing LSK [2R] DOWN adjusts the entire display downward by as much as one-half character. CANCEL – Pushing LSK [3R] CANCEL returns the display to the Power/Display Control page. CONFIRM® OFF CANCEL® CONFIRM STANDBY® Confirm Off Page This page has three options (CONFIRM OFF, CANCEL and CONFIRM STANDBY) selectable using the line select keys. CONFIRM OFF – Pushing LSK [1R] CONFIRM OFF turns the system off. CANCEL – Pushing LSK [3R] CANCEL returns the display to the Power/Display Control page. CONFIRM STANDBY – Pushing LSK [5R] CONFIRM STANDBY allows the FMS to be powered up with position information intact. This is a configurable feature. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 27 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual C. Data Transfer Unit (DTU-100) The following paragraphs provide general information about operating the DTU (Models 1406 and 1407). Refer to the Operator’s Manual applicable for the Flight Management System and software program version for detailed operating procedures. When using the Portable DTU, connect the DTU cable to the appropriate panel-mounted connectors before turning the unit on. (1) Power With external power applied to the DTU, the red LED illuminates. (2) D. Disk Insertion and Removal Open the Dust Cover by pulling out and upward on the tabs. The pivot arms and latch mechanisms will hold the Dust Cover in the fully open position. Grasp the disk by the edge away from the metal shutter so that the arrow points away from you. Orient the disk so that the arrow points toward the slot in the Disc Drive and the face of the disk is toward the top of the unit and then insert the disk into the drive. Push on the exposed edge of disk until it is fully inserted. Push on the small button on the Disc Drive to eject the disk. Grasp the disk and pull it out of the drive. Push the Dust Cover toward the unit until it snaps closed. The pivot arms and latch mechanisms will hold the Dust Cover closed. Solid State Data Transfer Unit (SSDTU) The following paragraphs provide general information about operating the SSDTU, models 1408-( ) and 1409-( ). Refer to the Operator’s Manual applicable to the Flight Management System and software version for detailed operating procedures. (1) Power NOTE: When using the Portable SSDTU, connect the SSDTU cable to the appropriate panel-mounted connectors before applying power to the aircraft. When power is applied, the SSDTU undergoes a Lamp Test and Power-on Built-InTest (PBIT). The SSDTU operates the front panel LED indicators in the following order. (a) All LEDs Off: Power supply not present. (b) All LEDs Amber: Power supply good, processor initializing. (c) All LEDs Green: Loading and verifying the operating system image and verifying the file system image. (d) All LEDs Blue: Initializing operating system. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 28 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual During PBIT, all three indicators will display the same status at any given time. The purpose of the operation is to test the LEDs and to give a clear indication of which PBIT step failed, should the SSDTU fail to begin normal operation. Following PBIT (normal operation), the SSDTU operates the front panel LED indicators as shown in the following table. Indicator Color and Action Indicator Type (2) Blank Green Solid Green Blinking Amber Solid Blue Solid Blue Blinking STATUS (Front) SSDTU Off Operational N/A CBIT has detected an error (SSDTU will reboot) Self-Test N/A USB (Front) No device present Device OK, not in use Device is being accessed Bad or unsupported device Device OK, in use (Indicates Primary Storage Device) Device is being accessed SD (Front) No device present Device OK, not in use Device is being accessed Bad or unsupported device Device OK, in use (Indicates Primary Storage Device) Device is being accessed NET (Front) Not yet operational N/A N/A N/A N/A N/A Ethernet (Rear) No device present A network link is established on this port Network activity N/A N/A N/A Flash Memory (a) Insertion Open the Dust Cover by pulling upward on the tabs. The pivot arms and latch mechanisms will hold the Dust Cover in the fully open position. Insert the flash memory card. Push on the exposed edge until it is fully inserted, the memory card will remain seated all the way in the slot when pressure is released. NOTE: If the card does not slide into the slot easily, do not try to force it; the card will not fit in backwards. Turn the card around 180º and reinsert card. Close the dust cover. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 29 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (b) (3) Removal of Data Storage Device NOTE: If the data storage device is removed during a read operation, the read operation will fail. If the data storage device is removed during a write operation, the device may become corrupt and will require the data storage device to be formatted on a personal computer (not an FMS format command which only deletes files from the media). Open the Dust Cover by pulling upward on the tabs. The pivot arms and latch mechanisms will hold the Dust Cover in the fully open position. Push on the exposed edge of the memory card, release pressure and the memory card will eject slightly out of the slot. Grasp the edge of the flash memory and pull it out of the SSDTU. Close the dust cover. USB Memory Insertion (a) Insertion Open the Dust Cover by pulling upward on the tabs. The pivot arms and latch mechanisms will hold the Dust Cover in the fully open position. Insert USB memory all the way into the USB slot until seated. NOTE: If the USB Memory does not slide into the slot easily, do not try to force it; the card will not fit in backwards. Turn the memory card around 180º and reinsert. (b) NOTE: Do not close dust cover. Removal NOTE: If the data storage device is removed during a read operation, the read operation will fail. If the data storage device is removed during a write operation, the device may become corrupt and will require the data storage device to be formatted on a personal computer (not an FMS format command which only deletes files from the media). Pull USB Memory card straight out of memory slot. Close dust cover. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 30 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual E. EFIS Radar Panel (ERP), P/N 1015–1–X (Lear 60 Pro Line 4 Installations Only) The supplement to the FMS Operator’s Manual introduces the ERP and provides a detailed explanation of the radar controls and MFD keys and their associated functions. (1) ERP Radar Controls The ERP faceplate contains several Weather Radar System controls. Control functions are identical from one weather radar to another. When any of these controls are activated the ERP sends the input to the FMS. PUSH RDR ON – Located in the center of the RANGE knob, this switch is used to activate the weather display on the MFD. When the MAP mode is displayed on the MFD, pressing this switch will superimpose weather radar on the map display. Pressing this switch again will remove superimposed weather radar from the map display. Also, when this switch is pressed while the MFD is in HSI format, weather only format will be displayed on the MFD. RANGE – Turning this knob selects radar/map display range from 5 nm to 300 nm and up to 600 nm in plan map. Range annunciation will be displayed on the MFD. RDR – This key provides display of the Radar Functions page. (RADAR CNTRL) on the onside FMS. Pressing this key a second time displays the second Radar Function page. Radar functions are selected from these two pages. PUSH ZERO – Located in the center of the TILT knob, this switch is pressed to set the vertical tilt of the weather radar antenna to zero degrees. TILT – Turning this knob selects the tilt angle of the weather radar antenna from –14 degrees to +14 degrees. Tilt annunciation is displayed on the ND/MFD. (2) ERP/MFD Keys and Switches HSI – This key provides display of a conventional compass rose on the MFD. A traditional Horizontal Situation Indicator will be displayed. Radar targets will not display in HSI format. MAP – This key is sued to display a present position map on the MFD. TFC – This is only active if TCAS is installed. If so, it will display a traffic map on the MFD. NAV – This key is sued to display a navigation source menu (NAV SOURCE 1/1) on the onside FMS from which navigation sensors may be selected for onside display on the PFD/MFD. BRG – This key is used to display a Bearing Pointers (BRG PTRS) menu. The menu lists sensors which may be selected for driving bearing pointers on the PFD/MFD. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 31 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual FAA Approval 1. General Approval of the FMS System is not authorized by this Installation Manual. Acceptance for the installation and use of the FMS and its associated components must be sought through the appropriate offices of the Federal Aviation Administration or other certifying agency. It is recommended that all proposed installations be coordinated with the local jurisdiction of the Federal Aviation Administration or other certifying agency prior to performing the installation. NOTE: The TSO identifies the minimum performance standards, tests and other conditions applicable for issuance of design and production approval of the article. The TSO does not specifically identify acceptable conditions for installation of the article. The TSO applicant is responsible for documenting all limitations and conditions suitable for installation of the article. An applicant requesting approval for installation of the article within a specific type or class of product is responsible for determining environmental and functional compatibility. It is recommended that when certifying (SCN 1000 or 1100) use the variable X (1000.X) in the original certification package to ensure point changes will not affect future certification requirements and to assure that the AFMS will not need to be changed with point changes. NOTE: All first time approvals using performance Vspeeds and engine thrust rating computations for a specific aircraft model must be approved by TC or STC process. A. B. Applicable TSOs (1) TSO-C109 (12/09/85): Airborne Navigation Data Storage System (2) TSO-C115b (9/30/94): Airborne Area Navigation Equipment using Multi-sensor Inputs (3) TSO-C146c (2/14/08): Stand-Alone Airborne Navigation Equipment Using the Global Positioning System Augmented by the Satellite Based Augmentation System (4) TSO-C190 (03/20/07): Active Airborne Global Navigation Satellite System (GNSS) Antenna Applicable Advisory Circulars and Other References (1) AC 20-138D (3/28/14): Airworthiness Approval of Global Navigation Satellite System (GNSS) Equipment (2) AC 25-15 (11/20/89): Approval of Flight Management Systems in Transport Category Airplanes (3) AC 90-96A (11/12/10): Approval of U.S. Operators and Aircraft to Operate Under Instrument Flying Rules (IFR) in European Airspace Designated for Basic Area Navigation (B-RNAV)/RNAV 5 and Precision Area Navigation (P-RNAV) (4) AC 90-100A (03/01/07): U.S Terminal and En Route Area Navigation (RNAV) Operations The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 101 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual C. (5) AC 90-105A (03/7/16): Approval Guidance for RNP Operations and Barometric Vertical Navigation in the U.S. National Airspace System and in Oceanic and Remote Continental Airspace (6) AC 120-33 (6/24/77): Operational Approval of Airborne Long Range Navigation Systems for Flight within the North Atlantic Minimum Navigation Performance Specifications Airspace (7) EASA AMC 20-4A: Airworthiness Approval and Operational Criteria For the Use of Navigation Systems in European Airspace Designated For Basic RNAV Operations (8) EASA AMC 20-5: Airworthiness Approval and Operational Criteria for the use of the Navstar Global Positioning System (GPS) (9) EASA AMC 20-12: Recognition of FAA Order 8400.12a For RNP-10 Operations (10) JAA TGL-10 (11-Jan-2000): Airworthiness and Operational Approval for Precision RNAV Operations in Designated European Airspace Reference Documents (1) RTCA/DO-160E (12/9/04): Environmental Conditions and Test Procedures for Airborne Equipment (2) RTCA/DO-178B (12/1/92): Software considerations in Airborne Systems and Equipment Certification (3) RTCA/DO-187 (11/13/84): Minimum Operational Performance Standards for Airborne Area Navigation Equipment Using Multi-Sensor Inputs (4) RTCA/DO-229D (2/1/13): Minimum Operational Performance Standards for Global Positioning System/Wide Area Augmentation System Airborne Equipment (5) RTCA/DO-236B (10/28/03): Minimum Aviation System Performance Standards: Required Navigation Performance for Area Navigation (6) RTCA/DO-254 (4/19/00): Design Assurance Guidance for Airborne Electronic Hardware (7) RTCA/DO-283B (12/15/15): Minimum Operational Performance Standards for Required Navigation Performance for Area Navigation (8) RTCA/DO-301 (12/13/06): Minimum Operational Performance Standards for Global Navigation Satellite System (GNSS) Airborne Active Antenna Equipment for the L1 Frequency Band (9) EUROCAE ED-58 (June 1988): Minimum Operational Performance Specification for Area Navigation Equipment Using Multi-Sensor Inputs The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 102 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual D. Universal Avionics Publications and Documents (1) 34-60-53: WAAS FMS Interface Manual (2) 34-61-01: WAAS/SBAS FMS Configuration Manual for SCN 1000/1100 (3) Service Letter No. 2753: Basic RNAV (BRNAV)/RNP-5 Operation in European Airspace (4) Service Letter No. 2758: RNP-10 Operations in the North and Central Pacific (5) Service Letter No. 2792: JAA PRNAV UASC Compliance Evaluation Summary (6) Service Letter No. 2804: UASC FMS Compliance with FAA Advisory Circular 90-100A (7) Service Letter No. 2814: Compliance Summary for RNP-4 Operations (FAA Order 8400.33) (8) Service Letter No. 2818: UASC FMS Compliance with RNP and RNAV Requirements (9) Service Letter No. 2855: AC 20-138D SBAS Flight Management System (FMSs) Compliance with AC 20-138D (10) Universal Avionics Report No. RPRT-2016-1002, Field Approval Process for the Installation or Upgrade of Universal Avionics SBAS FMS with LPV Approach Capability IAW FAA Order 8300.16. This report describes the process for FAA Field Approval of a new or upgraded UASC UNS-1( )w SBAS FMS in 14 CFR Part 23 and Part 25 aircraft, as defined in FAA Order 8300.16 (Chg. 1 or later), Major Repair and Alteration Data Approval. Prior to the release of FAA Order 8300.16 (Chg. 1), FAA Field Approvals of an upgrade from a conventional GPS based UNS-1( ) FMS to a UASC UNS-1( )w SBAS based FMS leveraged the FAA approved Engineering Assisted Field Approval Process described in UASC RPRT-2009-1004. The release of FAA Order 8300.16 (Chg. 1) adopted the concepts developed between the FAA and UASC from this process, expanding the Field Approval options available to the UASC dealers. While RPRT-2009-1004 Engineering Assisted Field Approval Process has not been revoked, UASC does not intend to revise the report to support new models of the UNS-1( )w SBAS FMS. Rather, UASC encourages its dealers to leverage the current information described in RPRT-2016-1002. RPRT-2016-1002 defines a process for an FAA Field Approval of a new installation or upgrade of a Universal Avionics UNS-1( )w SBAS FMS installation with 3D coupled LPV approach capability. Under the previous Engineering Assisted Field Approval Process, installation upgrades were classified by the FAA as a Minor change to Type Design but a Major Alteration to the aircraft. Reference FAA Order 8300.16 Chg. 1, section 1-4.b Definitions for additional details. The most recent revision of RPRT-2016-1002 can be found on the UASC UniNet website at: https://secure.uasc.com/documents/Eng/RPRT-2016-1002_wFMS-FieldApproval-Process.pdf The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 103 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual E. TSO Deviations In accordance with the provisions outlined in 14 CFR 21.609, Universal Avionics has been granted deviations from TSO-C146c for the following paragraphs within RTCA/DO-229D. (1) Paragraph 2.1.3.2.2.3 – FDE Prediction The FMS will continue to remove satellites from the position solution when deselected by the pilot. This protocol is used in Universal’s TSO-C129a GPS-1000, GPS-1200 and GNSS-2400 products as well as throughout the FMS product line. Universal Avionics’ position is that this feature is a valuable aid in demonstrating compliance to the MPS accuracy and integrity requirements, both in the lab and flight testing. (2) Paragraph 2.2.1.1.4.5 - Alphanumerics The FMS identifies each waypoint as per the charted procedure. The waypoints are not specifically labeled as IAW, FAWP, MAWP or Missed Approach Holding Fix. The FAWP is readily identifiable to the crew by the corresponding approach label “GPS 08” or “ILS 27”. MAWP is identified by the runway identifier, waypoint name when applicable, and the End of Approach label *EOA*. The missed approach holding fix is identified by the waypoint name and holding pattern annunciation. (3) Paragraph 2.2.1.1.6 – Set of Standard Function Labels Universal Avionics consistently employs the same set of labels and messages across the entire FMS product line. Universal chooses to retain the human interface currently in use throughout our product line and operated by thousands of flight crews today. The modified MPS Table 2-6 shown below identifies current Universal labels and messages where deviations were granted. Table 2-6 Labels and Messages (Modified) Function Label/Message Universal Label/Message/Function Suspend / unsuspend automatic waypoint sequencing Suspend (SUSP) Universal’s FMSs do not support the suspend/unsuspend function as it is unnecessary in our family of FMSs. The suspend functionality may be accomplished at any point on the flight plan by entering the FMS heading mode. This allows maneuvering off the flight plan or onto subsequent leg via the intercept mode The pilot may also enter a GAP into the active flight plan. This functionality is accessed from the flight plan pages. When a GAP has been inserted, the flight plan will not auto-sequence to the next leg. Rather, the aircraft will fly an extension of the last leg. The pilot can then enter into a heading mode and vector as required. To reestablish waypoint sequencing to the original flight plan, the pilot may go "Direct To" or edit the “gap” out of the flight plan. Access to selecting a course to or from a waypoint OBS, CRS Universal’s FMS uses a well-established “PVOR” function for this procedure, which allows the creation of courses to or from any waypoint in the flight plan. The PVOR is accessed from either the NAV MENU page or the DTO mode key. The pilot then is given the option to enter a waypoint and select the desired track to or from the selected waypoint. Clear previous entry, no, or delete Clear (CLR) Universal’s FMS utilizes the “BACK” key. The back key is analogous to the Backspace key on a computer keyboard. CDU Keys The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 104 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual Table 2-6 Labels and Messages (Modified) Function Label/Message Universal Label/Message/Function Access Direct-To function Direct To Universal’s FMS utilizes the “DTO” Key for this function. Access to nearest airports or other fixes Nearest (NRST) Universal’s FMS utilizes a “DIVERT” line select key on the DTO page for this function. The DIVERT page displays a list of up to 12 of the closest airports with associated bearing, range, and longest runway based on current present position. There is a prompt where the pilot can select the airport for automatic insertion into the flight plan. Select Vectors-toFinal (Section 2.2.3.2.1) Vectors-to-Final (VTF) The flight crew can initiate this function by pressing the “ACT APPR” Line Select key any time the approach is armed. Once the approach is activated, the option to intercept the Final Approach course becomes available via FMS heading mode. Indication of loss of integrity monitoring LOI “Loss of Integrity - Cross Check NAV.” Universal’s FMS uses an amber “INTEG” annunciation on EFIS or a separate annunciator. Indication of impending turn WPT (flashing) or “Turn to [next heading] in [distance] nm” Universal’s FMS uses the message “WAYPOINT ALERT. The Universal FMS provides a discrete that flashes at waypoint sequencing. In the UASC King Air certification aircraft, the waypoint name that is being sequenced flashes on the EFI-890R map display and lower left hand corner where the TO waypoint is displayed. The EFI-890R primary flight display also flashes the TO waypoint name in the lower left corner upon waypoint sequencing. CDU Keys Annunciations (4) Paragraph 2.2.1.3.16 - Parallel Offsets The FMS provides bearing, distance, time and To/From to the original flight plan waypoint to comply with SAE 4102/9, Flight Management Systems (FMS), paragraph 3.2.2.17. Universal’s philosophy is that situational awareness is best served by referencing the original flight plan since the map display and ATC directions both reference the original flight plan path. Offset reference points are not named nor shown on any chart. It should also be noted that some map displays used bearing and distance to draw the TO waypoint. Subsequent waypoints are drawn using geo-referenced coordinates or other means independent of bearing and distance. With these displays, the effect of this requirement would be that the map display would show the TO waypoint as an offset, and subsequent waypoints on the original path. The FMS meets the requirement of not propagating through unreasonable path geometries. The FMS terminates the offset when the approach becomes active rather than at the IAF. FMS offsets are not terminated at leg discontinuities. Guidance will be provided to an extension of the previous leg and the pilot is presented with a “Current Leg Extended” message. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 105 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (5) Paragraph 2.2.3.3.1 - Approach Path Definition The FMS has the capability for activating a VTF function throughout the product line. When an approach is manually activated by a line select key labeled ACT APPR all waypoints in the approach are sequenced and a CF leg is created to the FAF (FAWP) or the FACF if one is present in the approach coding. This allows the FMS Heading Mode (FHDG) to be entered and a heading to intercept the final approach course programmed. Regardless of heading, the deviations are always provided to the first approach leg according to the procedure. This MPS requirement does not allow conformance to the published procedure when a FACF is present. Universal understands the inclusion of this requirement because of concerns with overshoot of the lateral approach path. However, Universal is able to demonstrate acceptable performance up to 80 degrees course change at the FAF when it is not designated as “Overfly”. Suspending sequencing means that if the pilot takes no action the aircraft will most certainly overshoot the approach course. (6) Paragraph 2.1 – General Requirements (LP Approach Limitation) The UNS-1( )w does not implement LP approaches. While a formal FAA TSO deviation was not requested, the FAA was aware of the absence of LP approach capability and issued the TSO Authorization without issue. LP Approach types are removed from the navigation databases at every cycle, and therefore, cannot be added to a flight plan directly in the FMS or using the off-line flight planning (UFP) software. No safety hazards have been identified with the lack of LP approach support. 2. Software Criticality The software embedded in the FMS is categorized as DO-178B Level C (Major). Level C software is defined as “software whose anomalous behavior, as shown by the system safety assessment process, would cause or contribute to a failure of system function resulting in a major failure condition for the aircraft.” TSO-C146b designates erroneous guidance during an LPV approach to be a severe-major hazard. Therefore, all software involved in LPV, guidance, and I/O processing is categorized as DO-178B Level B (Hazardous/Severe-Major) with redundant hardware to support required integrity. UA chose to meet this level with dual FMS/WAAS in which all precision approach guidance, I/O, and cross-channel monitoring is performed by the DO-178B Level B WAAS subsystem. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 106 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual 3. Instructions for Continuous Airworthiness, FAR 23.1529, 25.1529, 27.1529 and 29.1529 Permission is hereby granted to use all or part of our statement for STC/337 certification purposes. Our statement in compliance with FAR 23.1529, 25.1529, 27.1529 and 29.1529 follows: A. General Information SYSTEM: UNS-1Fw Flight Management System Modification of an aircraft by this Supplemental Type Certificate or Form 337 obligates the aircraft operator to include the maintenance information provided by this document in the operator’s Aircraft Maintenance Manual and the operator’s Aircraft Scheduled Maintenance Program. B. (1) Maintenance Manual information for the UNS-1Fw (system description, removal, installation, testing, etc.) is contained in Universal Avionics (UA) Installation Manual 34-60-51. System operation is described fully in the UA Operator’s Manual Report No. 2423sv1000 where 1000 equals the system software. (2) Line Replaceable Unit (LRU) part numbers and other necessary part numbers contained in the installation data package should be placed in the aircraft operator’s appropriate aircraft Illustrated Parts Catalog (IPC). (3) Wiring diagram information contained in this data package should be placed into the aircraft operator’s appropriate aircraft Wiring Diagram Manuals. (4) Revision to this document will be accomplished via Service Bulletin and /or Installation Manual Revision. Airworthiness Limitations Scheduled Maintenance Program tasks to be added to the aircraft operator’s appropriate aircraft maintenance program are as follows: (1) Recommended Periodic Scheduled Servicing Tasks: None Required. (2) Recommended Periodic Scheduled Preventative Maintenance Tests/Checks to Determine System Condition and/or Latent Failures: None Required. (3) Recommended Periodic Inspections: None Required. (4) Recommended Periodic Structural Inspections: None Required. (5) Recommended Replacement Interval: None Required Unscheduled Maintenance Unscheduled maintenance may include upgrade of the program software contained in the FMS. If the FMS is removed and the software changed, the configuration settings should be checked and amended as necessary in accordance with the instructions contained in applicable manuals. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 107 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual 4. Environmental Qualification Forms The environmental categories under which the FMS is approved (reference RTCA DO-160E) are listed on the accompanying Environmental Qualification Forms in this section. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 108 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual ENVIRONMENTAL QUALIFICATION FORM NOMENCLATURE: UNS-1Fw Flight Management System and Configuration Module PART NO.: 3192-XX-11110X & 31921 TSO NUMBER: UNS-1Fw FMS – C115b & C146c CONFIGURATION MODULE – C115c & C146c DO178B: Level B/Level C MANUFACTURER'S SPECIFICATION AND/OR OTHER APPLICABLE SPECIFICATION: Contained in the appropriate Technical Manual MANUFACTURER: Universal Avionics 3260 E. Universal Way Tucson, AZ. 85756-5097 Conditions Ground Survival Low Temperature Operating Low Temperature Low Operating Temperature Ground Survival High Temperature Short Term High Operating Temperature High Operating Temperature In-flight Loss of Cooling Altitude Decompression Overpressure Temperature Variation Humidity Operational Shocks and Crash Safety Vibration Explosion Proofness Waterproofness Fluid Susceptibility Sand and Dust Fungus Resistance Salt Spray Magnetic Effect Power Input Voltage Spike Audio Frequency Conducted Susceptibility Induced Signal Susceptibility Radio Frequency Susceptibility Emission of Radio Frequency Lightning Induced Transient Susceptibility Lightning Direct Effects Icing Electric Discharge Fire, Flammability DO-160E Section 4.5.1 Category Description of Conducted Tests A2E1 -55C/-15C 4.5.2 4.5.3 A2E1 A2E1 -15C,-20C +85C/+70C 4.5.4 4.5.5 4.6.1 4.6.2 4.6.3 5.0 6.0 7.0 8.0 9.0 10.0 11.0 12.0 13.0 14.0 15.0 X W A2E1 A2E1 A2E1 B A B SB,SM H W X X X X Z 16.0 17.0 18.0 Z A Z 19.0 20.0 21.0 22.0 Z R M A3,J33 23.0 24.0 25.0 26.0 X X A C The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. Not Required +15,000 feet, +70,000 feet +70,000 feet -15,000 feet 5°C per minute Not Required Not Required Not Required Not Required Less than 0.3m to cause deflection of 1 degree Not Required Not Required 34-60-51 Page 109 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual ENVIRONMENTAL QUALIFICATION FORM NOMENCLATURE: 4-Inch Flat Panel Control Display Unit PART NO.: 1117-XX TSO NUMBER: C115b & C129a DO-178B: Level C MANUFACTURER'S SPECIFICATION AND/OR OTHER APPLICABLE SPECIFICATION: Contained in the appropriate Installation Manual MANUFACTURER: Universal Avionics 3260 E. Universal Way Tucson, AZ 85756-5097 Conditions Low Temperature High Temperature In-flight Loss of Cooling Altitude Decompression Overpressure Temperature Variation Humidity Operational Shock and Crash Safety Operational Shocks Crash Safety Vibration Explosion Waterproofness Fluid Susceptibility Sand and dust Fungus Resistance Salt Spray Magnetic Effect Power Input Voltage Spike Audio Frequency Conducted Susceptibility Induced Signal Susceptibility Radio Frequency Susceptibility (radiated and conducted) Emission of Radio Frequency Lightning Induced Transient Susceptibility Lightning Direct Effects Icing DO-160C Section 4.5.1 Category 4.5.2 and 4.5.3 4.5.4 4.6.1 4.6.2 4.6.3 5.0 6.0 7.0 Description of Conducted Tests A1D1 -20C Operating, -55C Survival A1D1 +55C Operating, +85C Survival (+70C Short Term) Not Applicable 50,000 FT 50,000 FT -15,000 FT X A1D1 A1 A1 B A 7.2 7.3 8.0 9.0 10.0 B, M & N X X 11.0 12.0 13.0 14.0 15.0 16.0 17.0 18.0 X X X X Z Z A Z 19.0 20.0 Z R 21.0 22.0 Z A3E3 23.0 24.0 X X 55°C, 95%, 48 HOURS Equipment Tested per DO-160C, Para. 7 6.0 g 15.0g, 12.0 g The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. N/A, not spark producing and no hot surfaces N/A, no exposed to falling water in normal operation N/A, fluid containment no commonly encountered N/A, not exposed to blowing sand and dust N/A, not exposed to severe fungus contamination N/A, not subjected to salt atmosphere Equipment Tested to Category XXE3 with Method of AC 20-136 Equipment not externally mounted. Equipment not externally mounted. 34-60-51 Page 110 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual ENVIRONMENTAL QUALIFICATION FORM NOMENCLATURE: 4-Inch Flat Panel Control Display Unit PART NO.: 1117-X-XX3 and 1117-X-XX4 TSO NUMBER: C115b & C129a DO-178B: Level C MANUFACTURER'S SPECIFICATION AND/OR OTHER APPLICABLE SPECIFICATION: Contained in the appropriate Installation Manual MANUFACTURER: Universal Avionics 3260 E. Universal Way Tucson, AZ 85756-5097 Conditions Low Temperature High Temperature DO-160D Section 4.5.1 Category A1 4.5.2 and 4.5.3 4.5.4 4.6.1 4.6.2 4.6.3 5.0 6.0 7.0 8.0 V D1 A1 A1 B A B SM & SB Explosion Waterproofness 9.0 10.0 X X Fluid Susceptibility Sand and dust Fungus Resistance Salt Spray Magnetic Effect Power Input Voltage Spike 11.0 12.0 13.0 14.0 15.0 16.0 17.0 X X X X Z Z A Audio Frequency Conducted Susceptibility – Power Inputs Induced Signal Susceptibility Radio Frequency Susceptibility (radiated and conducted) Emission of Radio Frequency 18.0 Z 19.0 20.0 Z R&V 21.0 M In-flight Loss of Cooling Altitude Decompression Overpressure Temperature Variation Humidity Shock Vibration A1D1 Lightning Induced Transient Susceptibility Lightning Direct Effects Icing 22.0 XXE3 23.0 24.0 X X ESD 25.0 A The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. Description of Conducted Tests -15C Operating, -55C Survival +55C Operating, +85C Survival (+70C Short Term) 30 Minute Minimum 50,000 FT 50,000 FT -15,000 FT 5°C per minute 55°C, 95%, 48 HOURS Equipment Tested per DO-160D, Para. 7 Fixed Wing Turbo Jet , Turbo Fan (SB) Fixed Wing Reciprocating, Turboprop (SM) N/A, not spark producing and no hot surfaces N/A, no exposed to falling water in normal operation N/A, fluid containment no commonly encountered N/A, not exposed to blowing sand and dust N/A, not exposed to severe fungus contamination N/A, not subjected to salt atmosphere Less than 0.3m to cause deflection of one degree 28 VDC operating with a low capacity or no battery High degree of protection against voltage spikes req’d 28 VDC operating with a low capacity or no battery Interference free operation is required Ref. DO-160D Equipment not in direct view of receiver antenna. Equipment located in cabin or cockpit Equipment Tested to Category XXE3 with Method of AC 20-136 N/A, equipment not mounted externally N/A, equipment mounted in temperature controlled area 15,000 Volts 34-60-51 Page 111 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual ENVIRONMENTAL QUALIFICATION FORM NOMENCLATURE: 4-Inch Flat Panel Control Display Unit PART NO.: 1117-X-XX5 and 1117-X-XX6 (without Mod 14) TSO NUMBER: C115b & C129a DO-178B: Level C MANUFACTURER'S SPECIFICATION AND/OR OTHER APPLICABLE SPECIFICATION: Contained in the appropriate Installation Manual MANUFACTURER: Universal Avionics 3260 E. Universal Way Tucson, AZ 85756-5097 Conditions Low Temperature High Temperature In-flight Loss of Cooling Altitude Decompression Overpressure Temperature Variation Humidity Shock Vibration DO-160D Section 4.5.1 4.5.2 and 4.5.3 4.5.4 4.6.1 4.6.2 4.6.3 5.0 6.0 7.0 8.0 Category Description of Conducted Tests A1D1 A1D1 -55°C Survival , -15°C (A1), -20°C (D1) Operating +55C Operating, +85C Survival (+70C Short Term) X A1D1 A1 A1 B A B SB & SM 15,000 ft (A1), 50,000 ft (D1) 50,000 FT -15,000 FT 5°C per minute 55°C, 95%, 48 HOURS Equipment tested per DO-160D, Para. 7 Fixed Wing Turbo Jet , Turbo Fan (SB) Fixed Wing Reciprocating, Turboprop (SM) Not spark producing and no hot surfaces N/A, no exposed to falling water in normal operation N/A, fluid containment no commonly encountered N/A, not exposed to blowing sand and dust N/A, not exposed to severe fungus contamination N/A, not subjected to salt atmosphere Less than 0.3m to cause deflection of one degree 28 VDC operating with a low capacity or no battery High degree of protection against voltage spikes required Explosion Waterproofness 9.0 10.0 X X Fluid Susceptibility Sand and dust Fungus Resistance Salt Spray Magnetic Effect Power Input Voltage Spike 11.0 12.0 13.0 14.0 15.0 16.0 17.0 X X X X Z Z A Audio Frequency Conducted Susceptibility Induced Signal Susceptibility Radio Frequency Susceptibility (radiated and conducted) Emission of Radio Frequency 18.0 Z 19.0 20.0 Z R Interference free operation is required 21.0 M Equipment not in direct view of receiver antenna. Equipment located in cabin or cockpit Lightning Induced Transient Susceptibility Lightning Direct Effects Icing 22.0 A3, J33 23.0 24.0 X X ESD 25.0 A The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 28 VDC operating with a low capacity or no battery HIRF conditions are part of normal environment Ref. DO-160D N/A, equipment not mounted externally N/A, equipment mounted in temperature controlled area 15,000 Volts 34-60-51 Page 112 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual ENVIRONMENTAL QUALIFICATION FORM NOMENCLATURE: 4-Inch Flat Panel Control Display Unit PART NO.: 1117-X-XX5 and 1117-X-XX6 (with Mod 14) TSO NUMBER: C115b & C129a DO-178B: Level C MANUFACTURER'S SPECIFICATION AND/OR OTHER APPLICABLE SPECIFICATION: Contained in the appropriate Installation Manual MANUFACTURER: Universal Avionics 3260 E. Universal Way Tucson, AZ 85756-5097 DO-160E Section 4.5.1 4.5.1 Category Description of Conducted Tests A1D1 A1D1 -55°C Survival , -15°C (A1), -20°C (D1) Operating 4.5.2 4.5.3 4.5.3 A1D1 A1D1 A1D1 -15°C (A1), 20°C (D1) +85°C +70°C 4.5.4 4.5.5 4.6.1 4.6.2 4.6.3 5.0 6.0 7.0 8.0 A1D1 X A1D1 A1 A1 B A B SB SM U +55°C Explosion Waterproofness 9.0 10.0 X X Fluid Susceptibility Sand and dust Fungus Resistance Salt Spray Magnetic Effect Power Input Voltage Spike 11.0 12.0 13.0 14.0 15.0 16.0 17.0 X X X X Z Z A Audio Frequency Conducted Susceptibility Induced Signal Susceptibility Radio Frequency Susceptibility (radiated and conducted) 18.0 Z 19.0 20.0 Z R Conditions Low Temperature Survival Low Temperature Short Term Operating Low Temperature Operating High Temperature Survival High Temperature Short Term Operating High Temperature Operating In-flight Loss of Cooling Altitude Decompression Overpressure Temperature Variation Humidity Shock Vibration The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. +85°C Survival, +70°C Short Term 15,000 ft (A1), 50,000 ft (D1) 50,000 FT -15,000 FT 5°C per minute 55°C, 95%, 48 HOURS Fixed Wing Turbo Jet , Turbo Fan Fixed Wing Reciprocating, Turboprop Helicopters with unknown rotor related frequencies Not spark producing and no hot surfaces N/A, no exposed to falling water in normal operation N/A, fluid containment no commonly encountered N/A, not exposed to blowing sand and dust N/A, not exposed to severe fungus contamination N/A, not subjected to salt atmosphere Less than 0.3m to cause deflection of one degree 28 VDC operating with a low capacity or no battery High degree of protection against voltage spikes required 28 VDC operating with a low capacity or no battery Interference free operation is required HIRF conditions are part of normal environment 34-60-51 Page 113 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual Conditions Emission of Radio Frequency DO-160E Section 21.0 Category M Lightning Induced Transient Susceptibility Lightning Direct Effects Icing 22.0 A3, J33 23.0 24.0 X X ESD Fire, Flammability 25.0 26.0 A X The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. Description of Conducted Tests Equipment not in direct view of receiver antenna. Equipment located in cabin or cockpit N/A, equipment not mounted externally N/A, equipment mounted in temperature controlled area 15,000 Volts N/A 34-60-51 Page 114 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual ENVIRONMENTAL QUALIFICATION FORM NOMENCLATURE: 5-Inch Flat Panel Control Display Unit PART NO.: 1018-XX-XXX TSO NUMBER: C115b & C129a DO-178B: Level C MANUFACTURER'S SPECIFICATION AND/OR OTHER APPLICABLE SPECIFICATION: Contained in the appropriate Technical Manual MANUFACTURER: Universal Avionics 3260 E. Universal Way Tucson, AZ. 85756-5097 Conditions Low Temperature DO-160C Section 4.5.1 Category Description of Conducted Tests A1D1 -20C Operating, -55C Survival Low Operating Temperature 4.5.2 A1D1 +55C Operating, +85C Survival High Temperature 4.5.3 A1D1 In-flight Loss of Cooling Altitude Decompression Overpressure Temperature Variation Humidity Shock Vibration Explosion Waterproofness Fluid Susceptibility Sand and dust Fungus Resistance Salt Spray Magnetic Effect Power Input Voltage Spike Audio Frequency Conducted Susceptibility Induced Signal Susceptibility Radio Frequency Susceptibility (radiated and conducted) Emission of Radio Frequency Lightning Induced Transient Susceptibility Lightning Direct Effects Icing ESD 4.5.4 4.6.1 4.6.2 4.6.3 5.0 6.0 7.0 8.0 9.0 10.0 11.0 12.0 13.0 14.0 15.0 16.0 17.0 18.0 X A1D1 A1D1 A1D1 B A B S X X X X X X Z Z A Z +55C Operating, +85C Survival N/A 50,000 FT 50,000 FT -15,000 FT 19.0 20.0 Z R, R 21.0 22.0 M A3, J33 23.0 24.0 25.0 X X A The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 55°C, 95%, 48 HOURS Equipment Tested per DO-160C 34-60-51 Page 115 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual ENVIRONMENTAL QUALIFICATION FORM NOMENCLATURE: LP/LPV Monitor PART NO.: 3116-5X-1110 TSO NUMBER: C115b and C146c DO178B: Level B MANUFACTURER'S SPECIFICATION AND/OR OTHER APPLICABLE SPECIFICATION: Contained in the appropriate Technical Manual MANUFACTURER: Universal Avionics 3260 E. Universal Way Tucson, AZ. 85756-5097 Conditions Ground Survival Low Temperature Operating Low Temperature Low Operating Temperature Ground Survival High Temperature Short Term High Operating Temperature In-Flight Loss of Cooling Altitude Decompression Overpressure Temperature Variation Humidity Operational Shocks and Crash Safety Vibration DO-160E Section 4.5.1 Category Description of Conducted Tests A2E1 -55C/-40C 4.5.2 4.5.3 A2E1 A2E1 -20C +70C 4.5.4 4.6.1 4.6.2 4.6.3 5.0 6.0 7.0 8.0 Explosion Proofness Waterproofness Fluid Susceptibility Sand and Dust Fungus Resistance Salt Spray Magnetic Effect 9.0 10.0 11.0 12.0 13.0 14.0 15.0 A2E1 A2E1 A2E1 A2E1 B A B SB SM H W X X X X Z Power Input Voltage Spike Audio Frequency Conducted Susceptibility Induced Signal Susceptibility Radio Frequency Susceptibility Emission of Radio Frequency Lightning Induced Transient Susceptibility Lightning Direct Effects Icing Electric Discharge Fire, flammability 16.0 17.0 18.0 Z A Z 19.0 20.0 21.0 22.0 Z R M A3 J33 X X A C 23.0 24.0 25.0 26.0 The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. +70,000 feet +70,000 feet -15,000 feet 5°C per minute Not Required Not Required Not Required Not Required Less than 0.3m to cause deflection of 1 degree Not Required Not Required 34-60-51 Page 116 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual ENVIRONMENTAL QUALIFICATION FORM NOMENCLATURE: Data Transfer Unit DTU-100 PART NO.: 1406-( ) TSO NUMBER: C109 DO-178B: Level D MANUFACTURER'S SPECIFICATION AND/OR OTHER APPLICABLE SPECIFICATION: Contained in the appropriate Technical Manual MANUFACTURER: Universal Avionics 3260 E. Universal Way Tucson, AZ 85756-5097 Low Temperature DO-160D Section 4.5.1 High Temperature Conditions Category Description of Conducted Tests C4 0C 4.5.3 C4 +70C In-flight Loss of Cooling Altitude Decompression Overpressure Temperature Variation Humidity Shock Vibration 4.5.4 4.6.1 4.6.2 4.6.3 5.0 6.0 7.0 8.0 X C4 C4 +35,000 ft. +35,000 ft. Explosion Waterproofness Fluid Susceptibility Sand and dust Fungus Resistance Salt Spray Magnetic Effect Power Input Voltage Spike Audio Frequency Conducted Susceptibility Induced Signal Susceptibility Radio Frequency Susceptibility (radiated and conducted) Emission of Radio Frequency Lightning Induced Transient Susceptibility Lightning Direct Effects Icing ESD 9.0 10.0 11.0 12.0 13.0 14.0 15.0 16.0 17.0 18.0 B A E SM SB E2 X X X X X Z Z A Z 19.0 20.0 Z V 21.0 22.0 M XXE3 23.0 24.0 25.0 X X A The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 117 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual ENVIRONMENTAL QUALIFICATION FORM NOMENCLATURE: Solid State Data Transfer Unit PART NO.: 1408-( ) TSO NUMBER: C109 DO178B: Level D MANUFACTURER'S SPECIFICATION AND/OR OTHER APPLICABLE SPECIFICATION: Contained in the appropriate Technical Manual MANUFACTURER: Universal Avionics 3260 E. Universal Way Tucson, AZ. 85756-5097 Conditions Ground Survival Low Temperature Operating Low Temperature Ground Survival High Temperature Short Term High Operating Temperature In-Flight Loss of Cooling Altitude Decompression Overpressure Temperature Variation Humidity Operational Shocks and Crash Safety Vibration Explosion Proofness Waterproofness Fluid Susceptibility Sand and Dust Fungus Resistance Salt Spray Magnetic Effect Power Input Voltage Spike Audio Frequency Conducted Susceptibility Induced Signal Susceptibility DO-160E Section 4.5.1 Category C4 4.5.3 C4 4.5.4 4.6.1 4.6.2 4.6.3 5.0 6.0 7.0 8.0 9.0 10.0 11.0 12.0 13.0 14.0 15.0 16.0 17.0 18.0 X C4 C4 B A B SM, SB H X X X X X Z Z A Z 19.0 ZC Radio Frequency Susceptibility Emission of Radio Frequency Lightning Induced Transient Susceptibility Lightning Direct Effects Icing Electric Discharge 20.0 21.0 22.0 R M E3 23.0 24.0 25.0 X X A Fire, Flammability 26.0 X The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. Description of Conducted Tests -55° C Survival Low Temperature -20° C Operating Low Temperature +85° C Survival High Temperature +70° C Operating High Temperature Not Required +35,000 feet +35,000 feet -15,000 feet Standard humidity environment Standard vibration test Hot spot non-spark producing surfaces Not Required Not Required Not Required Not Required Not Required Deflection distance is less than 0.3 m DO-160E allows Z in place of B High degree of protection required. DO-160E allows Z in place of B Interference-free operation is required primary power is a constant freq. or DC Installed in normal HIRF environment Not Required Not Required Air discharge applied to normally accessible surfaces Not required 34-60-51 Page 118 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual ENVIRONMENTAL QUALIFICATION FORM NOMENCLATURE: WAAS (SBAS) GPS Antenna PART NO.: 10708 TSO NUMBER: C190 MANUFACTURER'S SPECIFICATION AND/OR OTHER APPLICABLE SPECIFICATION: Contained in the appropriate Technical Manual MANUFACTURER: Universal Avionics 3260 E. Universal Way Tucson, AZ. 85756-5097 Conditions Temperature & Altitude Temperature Variation Humidity Shock Vibration Explosion Waterproofness Fluid Susceptibility Sand and dust Fungus Resistance Salt Spray Magnetic Effect Power Input Voltage Spike Audio Frequency Conducted Susceptibility Induced Signal Susceptibility Radio Frequency Susceptibility (radiated and conducted) Emission of Radio Frequency Lightning Induced Transient Susceptibility Lightning Direct Effects Icing ESD Fire, Flammability DO-160E Section 4.0 5.0 6.0 7.0 8.0 Category 9.0 10.0 11.0 12.0 13.0 14.0 15.0 16.0 17.0 18.0 F2 A B BD S(C,L,M,Y) U (FF1) X SY F S X S Z X X X 19.0 20.0 ZCZW Y 21.0 22.0 H A4 J44 2A C A C 23.0 24.0 25.0 26.0 The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. Description of Conducted Tests 34-60-51 Page 119 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual ENVIRONMENTAL QUALIFICATION FORM NOMENCLATURE: WAAS (SBAS) GPS/Sirius Antenna PART NO.: 10709 TSO NUMBER: C190 MANUFACTURER'S SPECIFICATION AND/OR OTHER APPLICABLE SPECIFICATION: Contained in the appropriate Technical Manual MANUFACTURER: Universal Avionics 3260 E. Universal Way Tucson, AZ. 85756-5097 Conditions Temperature and Altitude Temperature Variation Humidity Shock Vibration Explosion Proofness Waterproofness Fluid Susceptibility Sand and Dust Fungus Resistance Salt Spray Magnetic Effect Power Input Voltage Spike Audio Frequency Conducted Susceptibility Induced Signal Susceptibility Radio Frequency Susceptibility Emission of Radio Frequency Lightning Induced Transient Susceptibility Lightning Direct Effects Icing Electric Discharge Fire, Flammability DO-160E Section 4.0 5.0 6.0 7.0 8.0 9.0 10.0 11.0 12.0 13.0 14.0 15.0 16.0 17.0 18.0 19.0 20.0 21.0 22.0 23.0 24.0 25.0 26.0 The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. Category Description of Conducted Tests F2 A B BD S(C,L,M,Y) U (FF1) X SY F S X S Z X X X ZCZW Y H A4 J44 2A C A C 34-60-51 Page 120 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual ENVIRONMENTAL QUALIFICATION FORM NOMENCLATURE: WAAS (SBAS) GPS/XM Antenna PART NO.: 10710 TSO NUMBER: C190 MANUFACTURER'S SPECIFICATION AND/OR OTHER APPLICABLE SPECIFICATION: Contained in the appropriate Technical Manual MANUFACTURER: Universal Avionics 3260 E. Universal Way Tucson, AZ. 85756-5097 Conditions Temperature and Altitude Temperature Variation Humidity Shock Vibration Explosion Proofness Waterproofness Fluid Susceptibility Sand and Dust Fungus Resistance Salt Spray Magnetic Effect Power Input Voltage Spike Audio Frequency Conducted Susceptibility Induced Signal Susceptibility Radio Frequency Susceptibility Emission of Radio Frequency Lightning Induced Transient Susceptibility Lightning Direct Effects Icing Electric Discharge Fire, flammability DO-160E Section 4.0 5.0 6.0 7.0 8.0 9.0 10.0 11.0 12.0 13.0 14.0 15.0 16.0 17.0 18.0 19.0 20.0 21.0 22.0 23.0 24.0 25.0 26.0 The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. Category Description of Conducted Tests F2 A B BD S(C,L,M,Y) U (FF1) X SY F S X S Z X X X ZCZW Y H A4 J44 2A C A C 34-60-51 Page 121 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual 5. Sample Airplane Flight Manual Supplement [100X.X] Prepare an Airplane Flight Manual Supplement using the following sample as a guide. NOTE: Comments in angle brackets, < >, and italics are explanatory only and should not appear in the final supplement. <Name of Applicant> AFM Supplement for <Aircraft Model> <Address> Supplement No. {SAMPLE} FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT FOR AIRCRAFT MAKE: ___________________________________________ AIRCRAFT MODEL: __________________________________________ AIRCRAFT REG: _____________________________________________ AIRCRAFT S/N: ______________________________________________ This supplement must be attached to the FAA Approved Airplane Flight Manual when the airplane is modified by the installation of a Universal Avionics (UA) UNS-1Fw Flight Management System (FMS), in accordance with STC ____________________________, (or Form 337). The information contained herein supplements or supersedes the basic manual only in those areas listed herein. For limitations, procedures, and performance information not contained in this supplement, consult the appropriate basic Airplane Flight Manual. FAA Approved: <Name> <Title> FEDERAL AVIATION ADMINISTRATION <Name of Aircraft Certification Office> <Address> FAA Approved Date: Page 1 of y The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 122 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual LOG OF REVISIONS REV PAGES 00 Title DATE DESCRIPTION FAA APPROVED Initial revision ii ii _____________________ Date: xx-xxx-2014 1 2 3 4 5 6 7 8 Page x of y The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 123 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual TABLE OF CONTENTS Section Page LOG OF REVISIONS TABLE OF CONTENTS SECTION I – GENERAL SECTION II – LIMITATIONS SECTION III - EMERGENCY AND ABNORMAL PROCEDURES SECTION IV - NORMAL PROCEDURES SECTION V - PERFORMANCE DATA Page x of y The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 124 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual Section I A. Installation Description <The following is a sample of how the introduction could read. Fully describe all interfaces with the UNS-1Fw.> The UNS-1Fw is a multi-sensor navigator that uses an optimal combination of sensor types to provide unparalleled accuracy, integrity and availability. It contains an internal GNSS sensor capable of using GPS augmented by WAAS and any other compatible Space Based Augmentation System (SBAS). Outside SBAS coverage can integrate GPS with scanning DME, VOR, TACAN, LORAN and IRS to provide continued navigation under any circumstances. The Universal Avionics UNS-1Fw installation is interfaced with a DME sensor and a VOR sensor for short-range navigation data. An internal GNSS provides long-range position data, which is integrated with the VOR/DME position data. The internal GNSS incorporates Receiver Autonomous Integrity Monitoring (RAIM). The UNS-1Fw receives air data from an approved Air Data Computer. The system provides navigation and steering data to the pilot’s EFIS and Flight Control System. The UNS-1Fw contains software 1000/1100, which provides capability for point-to-point navigation, and approaches. Lateral and vertical steering is provided for enroute, terminal area, and approach operation. B. Lateral Navigation Approvals The Universal Avionics FMSs have been installed in accordance with AC 20 138( ). Provided the FMS multi-sensor navigation system is receiving usable signals, it has been demonstrated capable of and has been shown to meet the accuracy requirements of: (1) <The following is applicable to all dual installations or single WAAS/SBAS FMS installations with a Universal LPV Monitor for SCN 1000.0/1100.0 through 1000.5/1100.5.> This installation complies with AC 20-138( ) for navigation using GPS and WAAS (within the coverage of a Space-Based Augmentation System complying with ICAO Annex 10) for enroute, terminal area, non-precision approach operations (including “GPS”, “or GPS” and “RNAV” approaches), approach procedures with vertical guidance (including “LNAV/VNAV” and “LPV”) with the following exceptions. Vertical navigation does not meet the requirements with respect to vertical waypoint offset the bisector of the lateral course and total system error. [AC 20-138( )] FMS does not support fixed-radius transitions. [AC 20-138( )] Navigation information is referenced to the WGS-84 reference system, and should only be used for approach where the Aeronautical Information Publication (including electronic data and aeronautical charts) conform to WGS-84 or equivalent. Page x of y The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 125 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual <The following is applicable to all dual installations or single WAAS/SBAS FMS installations with a Universal LPV Monitor for SCN 1000.6/1100.6 or later.> This installation complies with AC 20-138( ) for navigation using GPS and WAAS (within the coverage of a Space-Based Augmentation System complying with ICAO Annex 10) for enroute, terminal area, non-precision approach operations (including “GPS”, “or GPS” and “RNAV” approaches), approach procedures with vertical guidance (including “LNAV/VNAV” and “LPV”) with the following exception. (2) (3) (4) (5) FMS does not support fixed-radius transitions. [AC 20-138( )] Navigation information is referenced to the WGS-84 reference system, and should only be used for approach where the Aeronautical Information Publication (including electronic data and aeronautical charts) conform to WGS-84 or equivalent. NOTES: 1. For single FMS installations without the LPV Monitor, LPV approaches are not available. 2. Reference UA SL2838 Rev. B or later for details and mitigation strategy regarding compliance to AC 20-138( ). 3. [Text in brackets] is for information only, and should not be inserted into the AFMS. <The following is applicable to dual installations.> This dual installation complies with equipage and accuracy requirements of FAA Order 8400.12A par 12(b)4 for Required Navigation Performance 10 (RNP10). This does not constitute an operational approval. <The following is applicable to dual installations with two long-range sensors in accordance with the NAT MNPS Advisory Circulars. Note that the internal GPS/WAAS can be used as one of the two long range sensors, since it does incorporate RAIM.> Flight in the North Atlantic (NAT) Minimum Navigation Performance Specifications (MNPS) airspace in accordance with AC 120-33. <The following is applicable to all installations.> This installation complies with equipage and accuracy requirements of AC 90-96A Appendix 1 paragraph 1,d,(3),(a) for B-RNAV in designated B-RNAV airspace, and Appendix 2 paragraph 2,a,(3),(a) for P-RNAV in designated P-RNAV airspace. This does not constitute an operational approval. <The following is applicable to all installations.> This installation complies with equipage and accuracy requirements of AC 90-100A Paragraph 7,c,(4) for operations on U.S. Area Navigation (RNAV) routes (Q-routes and T-routes), Departure Procedures (Obstacle Departure Procedures and Standard Instrument Departures), and Standard Terminal Arrivals (STARs). This does not constitute an operational approval. Page x of y The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 126 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (6) <The following is applicable to dual installations.> This installation complies with equipage and accuracy requirements of FAA Order 8400.33 paragraph 9.b.(1).(c), Required Navigation Performance 4 (RNP-4) Oceanic and Remote Area Operations when used in conjunction with the Universal Flight Planning Program, which provides FDE prediction, SCN 25.1 or later FAA approved version. This does not constitute an operational approval. (7) <The following is applicable to all installations.> This installation complies with equipage and accuracy requirements of FAA Order 8400.10 Volume 4, Chapter 1, Section 2, paragraph 52,D,(4), Required Navigation Performance RNP-2, RNP-1 and RNP-0.3 when in enroute mode, terminal mode, or non-precision approach modes respectively and the installed equipment provides annunciation to the pilot of the mode that is in use. This does not constitute an operational approval. (8) <The following is applicable to Remote/Oceanic approval per Notice 8110.6.> installations.> The FMS installation with internal GPS/WAAS sensor has been found to comply with the requirements for GPS primary means of navigation in oceanic and remote airspace, when used in conjunction with the Universal Flight Panning RAIM prediction program SCN 25 or later FAA approved versions. This does not constitute operational approval. (9) <The following is applicable to all installations.> This installation complies with equipage and accuracy requirements of FAA Order 8900.1 CHG Par 4-32D, Required Navigation Performance RNP-2, RNP-1 and RNP0.3 when in enroute mode, terminal mode, or non-precision approach modes respectively and the installed equipment provides annunciation to the pilot of the mode that is in use. This does not constitute an operational approval. (10) <The following is applicable for all installations.> This FMS installation complies with the RNAV requirements of AC 90-105A for RNP approach, Terminal, and Enroute operations with the exception of fixed radius turns. (11) <The following is applicable to installations with approved INS/IRS sensor(s).> FAR Part 121, Appendix G Section 6 and AC 20-138( ). The table details time limitations placed on RNP-10 and BRNAV operations with minimum sensors in NAV mode. Page x of y The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 127 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual C. Vertical Navigation Approval This installation meets the requirements for VFR/IFR enroute, terminal area and approach barometric VNAV operations in accordance with the criteria of AC 90-105 for use of DA in lieu of MDA in accordance with 14 CFR §91.175 and 91.205. Page x of y The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 128 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual Section 2 A. B. C. D. E. F. <The following limitations are representative. Refer to additional FAA guidance in Advisory Circular 20-138D as applicable to your installation.> Operator’s Manual The FMS Operator’s Manual, Report No. 2423sv1000/1100 must be available to the flight crew whenever navigation is predicated upon the use of the Universal Avionics Flight Management System. Navigation Equipment Both FMSs or FMS and LP/LPV Monitor must be powered on and operational to fly RNAV (GPS) approaches with LPV minima. Annunciations The pilot shall, while flying an RNAV(GPS) approach with LPV minima and annunciation, verify that “LPV” is properly annunciated on the PFD (or LOS annunciators) and that there are no navigation flags visible. This check shall take place inside the final approach fix and in no case later than 1000 feet above the runway threshold. Software Requirements The system must utilize software version SCN 1000.X/1100.X, where X represents FAA approved minor changes. Database/Waypoint Verification IFR, enroute and terminal navigation are prohibited unless the pilot verifies the currency of the database or verifies each selected Waypoint for accuracy by reference to current approved data. Instrument Approaches Instrument approaches must be accomplished in accordance with approved instrument approach procedures that are retrieved from the FMS database. (1) Instrument approaches must be conducted in the Approach mode, and GPS Integrity monitoring (when using GPS/WAAS including “GPS”, “or GPS”, and “RNAV” approaches) must be available at the Final Approach Fix, as indicated to the pilot by the ‘INTEG’ amber annunciator being off. (2) GPS/WAAS can only be used for approach guidance when navigation information is referenced to the WGS-84 reference system, and should only be used where the Aeronautical Information Publication (including electronic data and aeronautical charts) conform to WGS-84 or equivalent. (3) GPS/WAAS sensors will be retained for all GPS approaches and any approach with a “G” suffix to the approach identifier on the approach arrival page. GPS will be deselected for any pilot-defined “VOR” or “VOR/DME” RNAV approaches. (4) Pilot-defined IFR approaches must be defined using Waypoints from the FMS navigation database. (5) The FMS is approved for pilot-defined VFR approaches as a VFR pilot aid only. NOTE: All sensors remain selected for VFR approaches. Page x of y The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 129 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual G. Latitude Limits Displayed FMS navigation parameters are referenced to Magnetic North, and operation of the aircraft is limited to latitudes between N73o and S60o, unless magnetic variation is manually entered by the flight crew. <Add appropriate comments about Mag/True switch if installed with IRS as a heading source.> H. VNAV Altitude Reference When using VNAV, the Altimeter on each pilot’s panel must be used as the altitude reference for all operations. I. Fuel Display Fuel display parameters are advisory only and do not replace primary fuel quantity or fuel flow gauges for fuel load and range planning. J. AFCS Limitations The UNS-1Fw is approved for lateral Flight Director and autopilot coupled GPS, NDB, RNAV, VOR-DME and VOR approaches only when the UNS-1Fw is in the FMS Approach Mode (which provides expanded HSI deviations). K. Long Range Sensors Navigation cannot be predicated on the use of non-GPS long range sensors alone while in terminal areas or during departures from or approaches to airports or into valleys; e.g., between peaks in mountainous terrain or below Minimum Enroute Altitude (MEA). Page x of y The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 130 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual Section 3 A. Emergency Procedures No change to FAA Approved Airplane Flight Manual. B. Abnormal Procedures (1) If GPS RAIM becomes unavailable (indicated by a message and GPS INTEG amber annunciator), the pilot should monitor position by cross reference to other navigation sources as necessary. (2) Should an FMS system component fail, in most cases the display will go blank or the remote MSG light will flash. Pushing the MSG key will display the Message Page, which will indicate the component which has failed. (3) The FMS and associated components are protected by the following circuit breakers: COMPONENT NAME BUS LOCATION FMS DC FMS AC FMS ADC TAT Probe HTR FMS SIU (4) In the event that a circuit breaker should “open”, the corresponding unit will be switched off internally. (5) If sensor information is intermittent or lost, use the remaining operational navigation equipment as required. (6) If VNAV information is intermittent or lost, disengage VNAV and use the altimeter for vertical reference. Page x of y The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 131 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual Section 4 A. Operation Normal operating procedures are outlined in the FMS Operator’s Manual Report 2423sv1000/1100. B. Navigation Database Verification After power-on self-tests have been completed, the INITIALIZATION page will appear. The expiration date of the database will appear at the bottom of the display. If the actual date is later than the expiration date, the FMS will notify the pilot with a “DATABASE EXPIRED” message. Refer to the operator’s manual for navigation database update instructions. C. System Annunciators <Describe all external annunciators installed as part of the FMS> The FMS generates outputs for the following annunciators on the pilot's and copilot’s instrument panels located in or adjacent to the HSI and ADI ANNUNCIATOR DESCRIPTION MSG (amber) Indicates a message is to be acknowledged on the MSG page. WPT (Amber) Indication is displayed two minutes prior to waypoint in enroute mode and 15 seconds prior in approach mode. When this annunciator flashes, it indicates that an upcoming vertical Flight Path Angle (FPA) change is within two minutes. SXT (Amber) Selected crosstrack is active. HDG (Blue) The FMS is in heading sub. APP (White) An approach has been activated. GPS INTEG (Amber) GPS Integrity exceeds the allowable limit for phase of flight. See also Section 3B, ABNORMAL PROCEDURES. LP/LPV Indicates LP or LPV Approach is armed or activated. FMS APPR (See Note) FMS Approach Mode is active. FMS LOS Indicates the available level of service based on the selected SBAS Approach in the flight plan and WAAS Subsystem integrity predictions. LPV (Green) Indicates LPV Approach is armed or activated. LNAV (Green) Indicates the available level of service based on the selected SBAS Approach in the flight plan and WAAS Subsystem integrity predictions. VNAV (Green) Indicates the available level of service based on the selected SBAS Approach in the flight plan and WAAS Subsystem integrity predictions. NOTE: Color varies depending on installation requirements. Page x of y The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 132 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual D. Aircraft Integration <The following is a sample of what the integration discussion could represent. Fully and accurately describe all switching procedures and display options where applicable.> (1) Collins EHSI-74 EHSI display of FMS Nav Information NOTE: FMS can only be selected for use when a VOR frequency is tuned on the #1 Navigation receiver. Selection of an ILS frequency will cause the display to revert to VHF Navigation. When a valid navigation leg is selected on the FMS, guidance information can be selected for display on the pilot's or copilot’s EHSI and ADI by selecting [FMS] on the [FMS/NAV] switch on the Instrument Panel, adjacent to the ADI. Left/Right, TO/FR, Nav Valid, Desired Track, Bearing to Waypoint, and Distance to Waypoint will be depicted on the EHSI. With a valid VNAV leg defined on the FMS, vertical deviation will be displayed HSI DEVIATION SCALE FACTORS FOR 2 DOTS MODE LATERAL VERTICAL Enroute 2.0 nm 1500 ft. Terminal 1.0 nm 492 ft. Approach 2 degrees to 0.3 nm, then linear GPA/4 NOTE: (0.3 nm is the default and me be designated by database.) (2) Enroute Flight Director and Autopilot Operation When a valid navigation leg is selected on the FMS, flight director lateral V-Bar steering can be selected on the pilot’s ADI by selecting [NAV] mode on the APS-65 Flight Guidance Panel. Pushing [ENG] will couple the FMS steering to the autopilot. NOTE: Only lateral steering is provided from the FMS. Select an appropriate vertical mode on the APS-65. (3) Approach Operation Instrument approaches may be linked into the flight plan and laterally coupled to the autopilot by selecting heading mode [HDG] then approach mode [APPR] on the autopilot mode selector. A remote panel mounted APRCH annunciator illuminates whenever FMS Approach Mode is active. Refer to Approach Procedures in the Operator's Manual. (4) Vertical Navigation Vertical Navigation (VNAV) mode is available for descent only. Pitch steering commands for ENROUTE VNAV descent are not provided. Page x of y The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 133 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual Section 5 No change to FAA Approved Airplane Flight Manual. Page y of y The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 134 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual Equipment Specifications 1. Equipment Identification A. UNS-1Fw FMS Equipment UNS-1Fw FMS Equipment Component Name Part Number NCU – Navigation Computer Unit 3192–XX–11110X (see part number matrix for explanation of variables) Configuration Module 31921 5-Inch FPCDU (optional) 1018-X-XXX 4-Inch FPCDU (optional) 1117-XX, 1117-X-XXX Multifunction Control Display Unit (MCDU) (optional) 1025-01-X11 LP/LPV Monitor 3116-5X-1110 DTU-100 – Data Transfer Unit 1406–01–1X 1407–01–1X (Portable Unit) SSDTU – Solid State Data Transfer Unit 1408-00-X 1409-00-2 (Portable Unit) GNSS Antenna 10708 GPS/Sirius Antenna 10709 GPS/XM Weather and Radio Antenna 10710 The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 201 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual B. Compatible Peripheral Equipment Compatible Peripheral Equipment Component Name Part Number Application Server Unit (ASU) 3040-06-0X LCS Loran-C Sensor 1040 LCS-850 Loran-C Sensor 1045–01 LCS – Loran–C Antenna 10401 10402 (LCS–850) GPS-1000 GPS Sensor 1075–01 GPS-1000A GPS Sensor 1078-01 GPS-1200 GPS Sensor 1080–01 GLS-1250 GPS Landing System 1086-01-00 GNSS-2400 GPS/GLONASS Sensor 1078-02 RRS – Radio Reference Sensor 1058–01–1X RTU – Radio Tuning Unit Collins CSDB ARINC RTU 1055 1056–01–1X Terrain Awareness Warning System (TAWS) 3010-0X-0X UL-600 UniLink 1065-XX-0X0 UL-601 UniLink 1066-XX-0X0 UL-800 UniLink 10800-XX UL-801 UniLink 10801-XX UL-700 UniLink 1067-XX-XXX UL-701 UniLink 1068-XX-XXX UniVision 3070-0X-0X Vision-1 3015-00-00 The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 202 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual C. Technical Manuals NOTE: Refer to the following manuals for further information about compatible peripheral equipment. These manuals are available from Universal Avionics Systems Corporation. Technical Manuals Component Report Number Application Server Unit (ASU) Report No. 46-20-03 FMS Configuration Manual Report No. 34-61-XX FMS Interface Manual Report No. 34-60-53 LCS - Loran–C Antenna Report No. 34-50-13 LCS – Loran-C Sensor Report No. 34-50-13 GPS-1000 GPS Sensor Report No. 34-50-03 GPS-1000A GPS Sensor Report No. 34-50-08 GPS-1200 GPS Sensor Report No. 34-50-04 GLS-1250 GPS Landing System Report No. 34-30-01 GNSS-2400 GPS/GLONASS Sensor Report No. 34-50-08 RRS - Radio Reference Sensor Report No. 34-50-10 RTU – Radio Tuning Unit Collins CSDB ARINC RTU Report No. 23-80-05 Terrain Awareness and Warning System Report No. 34-40-01 UL-600 UniLink Report No. 23-20-01 UL-601 UniLink Report No. 23-20-02 UL-700 UniLink Report No. 23-20-03 UL-701 UniLink Report No. 23-20-04 UniVision Report No. 23-30-03 UL-800 UniLink (SCN 30.X) Report No. 23-20-05 UL-801 UniLink (SCN 30.X) Report No. 23-20-06 UL-800 UniLink (SCN 31.X) Report No. 23-20-16 UL-801 UniLink (SCN 31.X) Report No. 23-20-17 Universal Cockpit Display (UCD) Report No.46-20-01 Vision-1 Report No. 34-40-03 The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 203 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual D. UNS-1Fw Part Number Matrix E. Configuration Module The part number of the Configuration Module is 31921. F. 5-Inch FPCDU 1018 - X - X X X Basic Part Number No Video = 1 Video = 2 Gray = 1 Black = 2 Gray, NVG = 5 Black, NVG = 6 No Graphics = 0 UniLink Graphics Capable = 1 Standard Glass = 0 Hi-Resolution Glass = 3 The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 204 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual G. 4-Inch FPCDU (P/N 1117-XX) 1117 - X X Basic P/N Aft Position = 5 Forward Position = 6 Gray = 1 Black = 2 H. 4-Inch FPCDU (P/N 1117-X-XXX) I. Multifunction Control Display Unit (MCDU) 1018 - 0 1 - X 1 1 Basic P/N Future Use Variable = 0 Future Use Variable = 1 Gray = 1 Black = 2 Gray, NVG = 5 Black, NVG = 6 Future Use Variable = 1 Future Use Variable = 1 The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 205 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual J. Data Transfer Unit (DTU-100) 1406 - 01 - X Basic Part Number for Cockpit DTU-100 Future Use Gray Faceplate = 1 Black Faceplate = 2 K. Portable Data Transfer Unit (PDTU-100) 1407 - 01 - 1 Basic Part Number for Portable DTU-100 Future Use L. Solid State Data Transfer Unit (SSDTU) 1408 - 00 - X Basic Part Number for Cockpit SSDTU Future Use Gray Faceplate = 1 Black Faceplate = 2 M. Portable SSDTU 1409 - 00 - 2 Basic Part Number for Portable SSDTU Future Use Black Faceplate = 2 The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 206 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual N. UNS-1Fw Part Number Configuration (1) All Digital Configuration (P/N 3192–XX–111102) This configuration has a CPU board, WAAS/ARINC board, WAAS/Analog board and Auxiliary board. This option supports aircraft which do not require analog interfaces other than annunciators and fuel flow inputs. (2) ASCB Version A Configuration (P/N 3192-XX-111103) This configuration has a CPU board, WAAS/ARINC board, WAAS/Analog board, ASCB board and Auxiliary board. The ASCB board provides the FMS with an interface to the ASCB Version A data bus that was developed by Honeywell and supplements ARINC, CSDB and analog interfaces of the FMS. The ASCB board hardware supports data bus Version A only. (3) Digital and Analog Configuration (P/N 3192-XX-111106) This configuration has a CPU board, WAAS/ARINC board, WAAS/Analog board, Analog board and Auxiliary board. The Analog board supplies AC pitch steering outputs. These options are wired for analog navigational signals. (4) Standard Digital Interface Capabilities: Long Range Nav Sensors (ARINC) IRS, IRGPS, LCS, GPS and GNSS Radar Joystick Interfaces – ARINC 429, 571 or CSDB Air Data Computer Input – ARINC 429 or 575 Sensor Inputs in Various Combinations of: – Up to 3IRS or IRGPS – 1 LCS – 1 DME – Up to 3 GPS/GNSS (two external and one internal) Airborne Flight Information System (AFIS) FMS Crossfill (Push or Pull) ARINC Digital Data Output Buses – 429 High–Speed – 561 (6 wire) – 429 Low–Speed – 571 Analog Interface Capabilities – Synchro Heading Input – Roll Command Steering Output – Standard Analog Outputs Including: Desired Track – Synchro Bearing To Waypoint – Synchro Lateral and Vertical Deviation Flags and Valids TO/FROM The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 207 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual Fuel Flow Interface Capabilities – Fuel Flow Processing Available. – Interfaces with fuel flow systems outputting: DC Analog G.E. AC pickoff Pulse Width and Frequency Intertechnique Pulse ARINC Digital – Interfaces include some models of the following manufacturers: Ametek, Canadian Marconi (CMA), Eldec, X & O Engineering, General Electric (G.E.), Gull, Howell, Intertechnique, J.E.T., Ragen, and Simmons fuel flow systems. – For fuel flow systems compatible with the NCU, refer to the Fuel Flow Inputs section. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 208 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual 2. Power Specifications Power specifications for the components of the FMS and compatible peripherals are as follows: NOTE: Current and power values for the FMS include powering one integrated FPCDU. In addition, FMS power specifications are based on the particular configuration that will consume the most power. All other configurations use less. Component Current (A @ V) Power (W @ V) Type Part Number 19.0 V Min 27.5 V Nominal 32.0 V Max 19.0 V Min 27.5 V Nominal 32.0 V Max FMS 3192–XX–11110X 3.21 2.70 2.64 60.99 74.25 84.48 5-Inch FPCDU 1018-X-XXX 0.9 0.6 0.6 17.1 16.5 19.2 4-Inch FPCDU 1117-XX 0.9 0.6 0.6 17.1 16.5 19.2 4-Inch FPCDU 1117-X-XX3 1117-X-XX4 w/o Mod 9 0.9 0.87 0.75 17.1 23.93 24.0 4-Inch FPCDU 1117-X-XX3 1117-X-XX4 with Mod 9 1.15 1.50 1.55 21.85 41.25 49.60 4-Inch FPCDU 1117-X-XX5 1117-X-XX6 0.74 0.51 0.44 14.06 14.03 14.08 LP/LPV Monitor 3116-5X-1110 3.21 2.70 2.64 60.99 74.25 84.48 RTU 1055 0.5 0.3 0.3 9.5 8.3 9.6 RTU (ARINC) 1056-01-XX 0.7 0.5 0.4 13.8 13.2 12.8 DTU-100 1406 0.3 0.3 0.2 5.7 11.0 6.4 Portable DTU-100 1407 0.3 0.4 0.2 5.7 11.0 6.4 SSDTU Portable SSDTU RRS 1408-00-X 1409-00-2 0.41 0.41 0.3 0.3 0.28 0.28 7.79 7.79 8.4 8.4 8.96 8.96 1058 1.1 0.8 0.7 20.9 22.0 19.2 LCS 1040 1.1 0.7 0.6 20.9 19.3 19.2 GPS-1000 1075-01 0.33 0.23 0.20 6.27 6.33 6.40 GPS-1200 1080-01 0.4 0.3 0.3 7.6 8.3 9.6 The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 209 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual 3. Equipment Specifications The following tables list the physical, environmental and electrical parameters of the Flight Management System. A. UNS-1Fw FMS (P/N 3192–XX–11110X) Characteristics B. Size 2MCU – 2.24” W x 7.64” H x 15.26" D Weight: 6.7 lbs. Mounting 2MCU Rack Power Requirements (nominal) 27.5 VDC, 2.66 A, 73.15 W LP/LPV Monitor (P/N 3116–5X–1110) Characteristics Size Weight: Mounting Power Requirements (nominal) C. Specifications Specifications 2MCU – 2.24” W x 7.64” H x 15.26" D 6.7 lbs. 2MCU Rack 27.5 VDC, 2.70 A, 74.25 W 5-Inch FPCDU (P/N 1018-X-XXX) Characteristics Specifications Size 5.75" W x 6.37" H x 4.177" D Component Weight 3.8 lbs. 4.1 lbs. 3.3 lbs. 2.87 lbs. Mounting 1/4 turn Dzus Fasteners Power Requirements Power input from NCU 19.2 W maximum (Startup may be higher) Panel Lighting 0.46 A @ 28 V maximum or 1.54 A @ 5 V maximum The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. (1018-X-XX0) (1018-X-XX3 w/o Mod 9) (1018-X-XX3 with Mod 9) (1018-X-XX3 with Mod 18) 34-60-51 Page 210 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual D. 4-Inch FPCDU (P/N 1117-XX & 1117-X-XXX) Characteristics Specifications Size 5.75" W x 4.50" H x 3.25" D Component Weight 2.6 lbs. 2.9 lbs. 2.9 lbs. 2.41 lbs. 2.41 lbs. 2.47 lbs. 2.47 lbs. (1117-XX) (1117-X-XX3) (1117-X-XX4) (1117-X-X05) (1117-X-X06) (1117-X-X15) (1117-X-X16) Mounting 1/4 turn Dzus Fasteners Power Requirements Power input from NCU 19.2 W maximum (Startup may be higher) 1117-XX, 1117-X-XX3, 1117-X-XX4 - 0.5 A @ 28 V maximum 1.6 A @ 5 V maximum Panel Lighting 1117-X-XX5, 1117-X-XX6 - 0.4 A @ 28 V maximum 2.07 A @ 5 V maximum, also an internal heater for brightness stabilization draws approximately 1.0 amp E. Data Transfer Unit (DTU-100) Characteristics Specifications Size 5.750" W x 2.124" H x 8.14" D Component Weight 3.25 lbs. 5.8 lbs. Power Requirements 18 VDC @ 0.22 A (P/N 1406–01–X) (P/N 1407–01–1) 27.5 VDC @ 0.350 A Nominal Mounting F. 1/4 Turn DZUS Fasteners (1406–01–X only) SSDTU (P/N 1408-00-X) Characteristics Specifications Size 5.750” W x 2.250” H x 7.764" D Weight 2.4 lbs. Mounting 1/4 Turn Dzus Fastener Power Requirements (nominal) 27.5 VDC, 0.3 A, 8.4 W The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 211 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual G. Portable SSDTU (P/N 1409-00-2) Characteristics Specifications Unit Size 6” W x 12.5” H x 5.5" D Weight N/A Power Requirements 27.5 VDC, 0.3 A, 8.4 W Cooling N/A Mounting SSDTU mounted in portable carrying case Interconnect Wiring Harness Part Numbers (see NOTE) P/N 81304072 – PSSDTU J1 to aircraft bulkhead J1 (New installation and previous Portable DTU-100 connection) Contact Universal Avionics for more information. P/N 81140811 – PSSDTU J2 to aircraft bulkhead J2 (Previous Portable DTU-100 connection) P/N 81140821 – PSSDTU J2 to aircraft bulkhead J2 (New installation) NOTE: When using the Portable SSDTU in new installations or upgrading the Portable DTU-100 bulkhead connectors to the Portable SSDTU bulkhead connectors, up to 8 Ethernet ports may be wired and configured. When bulkhead connectors from a prior Portable DTU-100 installation are used for the Portable SSDTU, up to 4 Ethernet ports may be available for use and configuration. Consult aircraft wiring diagrams to verify the number of Ethernet ports that are wired. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 212 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual H. GPS Antenna (P/N 10708) Characteristics Weight Frequency VSWR Polarization Radiation Pattern Impedance Gain Stability Power Handling Power Requirements Power Consumption Rejection @ SatCom frequency of 1625 MHz Icing TSO The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. Specifications 0.5 lbs. 1575.42 10.23 MHz ≤ 1.5:1 Right Hand Circular Elevation Angle Gain (dBic) (degrees 0 -5 5 -3.5 10 0 20 2 30 2 30<Elev.<75 2.5 >75 3.0 50 Ohms 30 ±3 dB Unconditionally stable for any source or load impedance 1 Watt 4.5-15 VDC 60.0 mA (max) >60 dB With 0.050” thick hard ice on radome, a gain decrease of no greater than 2 dB from no ice condition when signal viewed at 30 degrees or greater elevation with respect to horizon. C190 34-60-51 Page 213 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual I. WAAS (SBAS) GPS/Sirius Antenna (P/N 10709) Overall Antenna Specifications Characteristics Weight Altitude Operating Temperature Storage Temperature GPS Connector SIRIUS Connector Specifications 0.5 lbs. 55,000 ft. -55ºC to +71ºC -55ºC to +85ºC TNCF TNCF WAAS (SBAS) GPS Antenna Specifications Characteristics Frequency Polarization Axial Ratio Radiation Pattern Gain Impedance VSWR Power Handling Power Requirements Power Consumption Specifications 1575.42 10.23 MHz Right Hand Circular 3 dB Max at Bore Site Elevation Angle 0º 5º 10º 20º 30º 30º< Elev. ≤75º >75º 30 ±3 dB 50 Ohms ≤ 1.5:1 1 Watt 4.5-15 VDC 60.0 mA (Max) Gain (dBic) -5 -3.5 0 2 2 2.5 3.0 Sirius Antenna Specifications Characteristics Frequency Polarization Axial Ratio Radiation Pattern Gain Impedance VSWR Power Requirements Power Consumption Specifications 2319.5 – 2332.5 MHz Left Hand Circular 3 dB Max at Bore Site Elevation Angle 5º 15º 5º Increments 30º≤ Elev. ≤60º Bore Site 24.5 ±2 dB 50 Ohms ≤ 1.5:1 3.6-5.5 VDC 55.0 mA (Max) The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Gain (dBic) -10 -3 0 5 Page 214 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual J. WAAS (SBAS) GPS/XM Weather and Radio Antenna (P/N 10710) Overall Antenna Specifications Characteristics Weight Altitude Operating Temperature Storage Temperature GPS Connector XM Connector Specifications 0.5 lbs. 55,000 ft. -55ºC to +70ºC -55ºC to +85ºC TNCF TNCF WAAS/SBAS GPS Antenna Specifications Characteristics Frequency Polarization Axial Ratio Radiation Pattern Gain Impedance VSWR Rejection at SatCom Freq 1625 MHz Power Handling Power Requirements Power Consumption Specifications 1575.42 10.23 MHz Right Hand Circular 3 dB Max at Bore Site Elevation Angle 0º 5º 10º 20º 30º 30º< Elev. ≤75º >75º 30 ±3 dB 50 Ohms ≤ 1.5:1 50 dB 1 Watt 4.5-15 VDC 60.0 mA (Max) Gain (dBic) -5 -3.5 0 +2 +2 +2.5 +3.0 XM Weather and Radio Antenna Specifications Characteristics Frequency Polarization Axial Ratio Radiation Pattern Gain Impedance VSWR Band Rejection Power Requirements Power Consumption The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. Specifications 2332.5 – 2345 MHz Left Hand Circular 3 dB Max at Bore Site Elevation Angle 20º 25º 5º Increments 30º≤ Elev. ≤60º Bore Site 24 ±2 dB 50 Ohms ≤ 1.5:1 25 dB @ F±230 3.6-5.5 VDC 55.0 mA (Max) 34-60-51 Gain (dBic) 0.0 +0.5 +2.0 -2.35 Page 215 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual K. WAAS FMS Annunciators The following annunciator is an example of what is available from the manufacturers listed below: FMS2 LPV LOS LNAV VNAV NOTE: Annunciators are not available from Universal Avionics System Corporation. NOTE: When installing an SBAS FMS that is not intended to be LPV capable, an LNAV/VNAV and LNAV annunciator must be installed. This is required to alert the pilot whether SBAS or baro-corrected altitude is being used for vertical component of the approach. If vertical is not coupled or displayed these annunciators are not required. The following is a suggested list of manufacturers that have annunciators available:. Aerospace Optics 3201 Sandy Lane Fort Worth, TX 76112 (888) 848 4786 Eaton Corporation Aerospace Controls Division 1640 Monrovia Ave. Costa Mesa , CA 92627 (800) 300-9320 (949) 642-2427 The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 216 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual 4. Installation Kits A. UNS-1Fw/1Lw (LP/LPV Monitor) FMS Installation Kit P/N K12075 NOTE: Use this Installation Kit for installation of the LP/LPV Monitor. NOTE: Configuration Module, P/N 31921, is not part of the NCU installation kit. Quantity 1 1 4 2 4 NOTE: B. Part Number 80009000 or 93921-1 83303130 or S612MGLNW2P0004AN SB612MGLNW2P0004AN 88600063 or MS51957-28 88600200 (see Note) or MS51957-35 88640094 or MS21083C06 Description Tray, 2 MCU Barry Controls ARINC Plug, 2 MCU Souriau Souriau Screw, 6-32 x 3/8” Pan Head Screw, 6-32 x 1.25” Pan Head Nut, #6, Hex, Self-Locking The 1.25” screws (P/N 88600200) included with the kit are not used for the installation of the LP/LPV Monitor. 4-Inch and 5-Inch FPCDU Installation Kit P/N K12026-4 Quantity 1 1 1 1 Part Number or Equivalent 83001150 (UASC) or 91-577049-15S (Amphenol) 83002086 (UASC) or MS27473T12F8S or MS27473T12A8S or MS27473T12B8S 83002087 or M85049/49-2-12W or M85049/49-2-12A or M85049/49-2-12N 83001087-02 (UASC) or MS27473T12F8SC The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. Description FPCDU connector Video connector Amphenol/Bendix, Burndy/Souriau, ITT Cannon, or Matrix Science Video connector backshell UniLink connector 34-60-51 Page 217 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual C. Data Transfer Unit (DTU-100) Installation Kit P/N K12050 Quantity 1 Part Number 83001150 Description Connector J1 or 1 91-577049-15S JT06RE-14-15S(SR) JT06RT-14-15S(SR) MS27473E14F15S(SR) Amphenol Amphenol Amphenol 83002152 Connector, J2, Plug 15P Circular Size 14 (C CLKD) or MS27473T14F15SC 1 83001157-02 or Strain Relief, Crimp Circular, Plug, Size 14, Olive Drab M85049/49-2-14W D. Portable DTU-100 Installation Kit P/N K12050-1 Quantity 1 Part Number 83000131 or MS27472E10A35S Description DTU Connector, J1, Receptacle, Size 10, 13-SKT, Crimp, Wall Mount, (STD CLK) MS27472E10B35S MS27472E10F35S 1 83002154 or MS27472E14B15PC The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. DTU Connector, J2, Receptacle, Circular, Size 14, 15P Male Crimp Type, Panel Mount W/ Flange 34-60-51 Page 218 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual E. SSDTU Installation Kit P/N K12079-1 Quantity 1 Part Number 83000255 Description Connector J2 or MS27473T16A35S MS27473T16B35S 1 83000257 Backshell J2 or M85049/49-2S16N 1 83001150 Connector J1 or 1 91-577049-15S JT06RE-14-15S(SR) JT06RT-14-15S(SR) MS27473E14F15S(SR) Amphenol Amphenol Amphenol 83001157-1 Bushing for J1 Strain Relief or 687-340-14 F. Glenair Inc. Portable SSDTU Installation Kit P/N K12079-2 Quantity 1 Part Number 83000131 Description Connector SZ10 or MS27472E10A35S MS27472E10B35S MS27472E10F35S 1 83000558 Cadmium Finish Olive Drab Finish Electroless Nickel Finish Connector SZ16 or MS27472E16A35S MS27472E16B35S MS27472E16F35S The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. Cadmium Finish Olive Drab Finish Electroless Nickel Finish 34-60-51 Page 219 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual G. GPS 10708 Antenna Installation Kit P/N K12080 Quantity 1 1 H. Part Number Description 83211018 or 225791-2 Connector, RF Coax, Crimp 83217010 or 31-2381 Plug, TNC Angle, Crimp Tyco Electronics Amphenol GPS 10709/10710 Antenna Installation Kit P/N K12082 Quantity 2 2 Part Number Description 83211018 or 225791-2 Connector, RF Coax, Crimp 83217010 or 31-2381 Plug, TNC Angle, Crimp The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. Tyco Electronics Amphenol 34-60-51 Page 220 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual 5. Required Tools A. Crimping Tools Required for Souriau Connectors Quantity 1 and 1 1 and 1 1 and 1 1 and 1 and 1 1 or 1 1 B. Description Crimping Tool/AF8 Turret Die or Positioner Crimping Tool Turret Die or Positioner Crimping Tool Turret Die or Positioner Crimping Tool/AFM8 Positioner Positioner Crimp Gauge Crimp Gauge Crimping tool for RRS coax connector Manufacturer Daniels Mfg. Daniels Mfg. Part Number M22520/1-01 M22520/1-04 Daniels Mfg. Daniels Mfg. M22520/2-01 M22520/2-10 Daniels Mfg. Daniels Mfg. M22520/7-01 M22520/7-08 Daniels Mfg. Daniels Mfg. Daniels Mfg. Daniels Mfg. Souriau AMP M22520/2-01 K13-1 K181 G-125 8660/162 220066-2 Pin Insertion/Extraction Tools Required Quantity Used For NCU Top/Middle Plug (All Pins) Description Insert/Extract Tool 1 NCU Bottom Plug (Pins 1, 4, 5 and 6) Insert/Extract Tool 1 NCU Bottom Plug (Pins 9, 10 and 11) Insert/Extract Tool 1 NCU Bottom Plug (Pins 2, 3, 7 and 8) Insert/Extract Tool 1 NCU Bottom Plug (Pins 12 and 13) Insert/Extract Tool 1 5-Inch FPCDU Video Connector 5-Inch FPCDU Video Connector Insert/Extract Tool 1 5-Inch FPCDU Video Connector Turret Die or Positioner 1 5-Inch FPCDU Video Connector 5-Inch FPCDU Video Connector Crimp Contacts Size 20 Crimp Contacts Size 20 1 1 1 Manufacturer Souriau AMP MIL SPEC Souriau AMP MIL SPEC Souriau AMP MIL SPEC Souriau AMP MIL SPEC Souriau ITT Cannon AMP Crimping Tool The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. Part Number 8660-160 91066-1 MS3156-22 8522-20 91066-4 MS3447-20 8522-16 91066-3 MS3447-16 8522-12 91078-1 MS27534-12 8660-187 CET-C8 91074-1 M81969/14-10 MS22520/1-01 MS22520/2-01 MS22520/7-01 MS22520/1-4 MS22520/2-10 MS22520/7-8 M39029/58-363 Bendix 34-60-51 10-251215-205 Page 221 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual 6. Insertion/Extraction Tool Manufacturers The following is a list of connector manufacturers and representatives that can supply tools necessary for installation: Name and Address AMP Inc. P.O. Box 3608 Harrisburg, PA 17105 ITT Cannon Daniels Mfg. Corporation 526 Thorpe Rd. Orlando, FL 32859 Souriau – Manufacturer’s Rep Con–Tek Marketing 7. Tool Suppliers and Manufacturers Mailing Address P.O. Box 3608 Harrisburg, PA 17105 Phone and Fax (800) 722–1111 Fax (717) 540–2310 (800) 845–7000 (407) 855–6161 Fax (407) 855–6884 P.O. Box 593872 Orlando, FL 32859 (303) 202–0212 Fax (303) 202–0253 Wire and Cable Manufacturers The following is a list of wire and cable manufacturers that can supply, but are not the only sources of, multi-conductor cables for use during installations. Name and Address A.E. Petsche Company, Inc. 2112 W. Division Arlington, TX 76012 Calmont Engineering and Electronics Corporation 420 E. Alton Ave. Santa Ana, CA 92707 Electronic Cable Specialists 5300 W. Franklin Dr. Franklin, WI 53132-8642 PIC Wire and Cable Supply, Inc. N63 W22619 Main St. Sussex, WI 53089 Wire and Cable Manufacturers Mailing Address Phone and Fax (817) 461-9473 2112 W. Division Arlington, TX 76012 (714) 549-0336 420 E. Alton Ave. Santa Ana, CA 92707 P.O. Box 37497 Milwaukee, WI 53237-0497 P.O. Box 330 Sussex, WI 53089-0330 The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. (414) 421-5300 Fax: (414) 421-5301 (414) 246-0500 (800) 742-3191 Fax (414) 246-0450 34-60-51 Page 222 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual 8. Alternate Vendor Part Numbers UASC Part Number 1219 Description Connector 1219-1 1220 Coaxial Insert Connector 1254 1255 Rack, 1/4 ATR Connector Barry Controls Cannon 1256 Connector Amphenol 1257 1328 80009000 83001150 83303130 83303139 Connector Connector 2MCU Rack Connector, 4-Inch FPCDU Connector Connector FPCDU Video Connector Deutsch Cannon Barry Controls Amphenol Souriau Souriau Amphenol/Bendix, Burndy/Souriau, ITT Cannon or Matrix Science Glenair, Inc. FPCDU Video Connector Backshell The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. Alternate Vendor AMP, Inc. Tri-Star AMP, Inc. Alternate Part Number 208597-1 G0681-0101-1100 225791-2 MS27467T11F35P with MS27506F-10-2 404A-25S D/D PXB-0 DPBX MA40-33S-0001 with 30 each contacts 031-9134-001 48-06R-14-15S-300 with 482343 or MS27291-3 AFD56-12-10SN-059 BKAD1-065-30022 067400-0024 93921-1 91-577049-15S(SR) SB612-MGLNW2P0004AN SB612-MG13W2PL301AN MS27473T12F8S or MS27473T12A8S or MS27473t12b8s 620FS012M18 or M85049/49-2-12W or M85049/49-2-12A or M85049/49-2-12N 34-60-51 Page 223 10 July 2019 The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 13 8 10 3 11 7 2 12 9 5 1 11 7 2 12 9 5 1 34-60-51 12.672 REAR CONNECTOR OF UNS-1Fw FMS IS KEYED AT #98 POLARIZATION PER ARINC 600 FOR P/N 3192-XX-111103. 5 0.120 1.37 REAR CONNECTOR OF UNS-1Fw FMS IS KEYED AT #99 POLARIZATION PER ARINC 600 FOR P/N 3192-XX-111102 AND 3192-XX-111106. 15.23 4.10 4 3. MATING CONNECTOR: SEE INSTALLATION KIT K12075. 2. WEIGHT: APPROXIMATELY 6.7 LBS. 1. ALL DIMENSIONS ARE IN INCHES. NOTES: 13 8 6 10 3 4 6.36 UNIVERSAL 1.10 UNS-1Fw (P/N 3192-X0-11110X) 6 5 7.64 7.50 A. 4 ABCDEFGHJK Equipment Drawings 4 ABCDEFGHJK 9. 15 10 5 15 1 10 5 1 2.170 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual Page 224 10 July 2019 1.50 The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 0.69 5 4 12.756 0.20 DIA 2 PLCS CONNECTOR OF UNS-1Fw RACK IS KEYED AT #98 POLARIZATION PER ARINC 600 FOR P/N 3192-XX-111103. 5 1.77 CONNECTOR OF UNS-1Fw RACK IS KEYED AT #99 POLARIZATION PER ARINC 600 FOR P/N 3192-XX-111102 AND 3192-XX-111106. 12.457 2.38 4 3. MATING CONNECTOR: SEE INSTALLATION KIT K12075. 2. WEIGHT: RACK = 11.2 ozs., CONNECTOR = 9.0 ozs. 1. ALL DIMENSIONS ARE IN INCHES. NOTES: 1.312 2 PLACES 14.92 9.00 2.50 7.28 B. 0.20 DIA 2 PLCS 0.18 DIA 4 PLCS UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual UNS-1Fw 2MCU Rack (P/N 80009000) Page 225 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual C. Configuration Module (P/N 31921) 0.315 2.055 ± .02 0.325 1.425 0.480 0.650 ± .02 0.375 ±.02 WIRE LENGTH APPROX, 6.00 0.142 TO 0.148 DIA. (2 PLCS.) NOTES: 1. ALL DIMENSIONS ARE IN INCHES. 2. WEIGHT: APPROXIMATELY 1.0 oz. D. Configuration Module Installation SELF LOCKING NUT P/N 88640094 SCREW P/N 88600200 RACK CONNECTOR P/N 83303130 CONFIGURATION MODULE P/N 31921 CONNECTOR PINS ARE NOT SHOWN ON THIS DRAWING RACK P/N 80009000 SCREW P/N 88600063 The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 226 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual E. 5-Inch FPCDU (P/N 1018-X-XXX) TOP VIEW 5.000 3.617 SIDE VIEW FRONT VIEW UNIVERSAL 6.380 6.260 5.250 DATA NAV VNAV DTO LIST PREV 1 2 3 FUEL FPL PERF TUNE MENU NEXT 4 5 6 7 8 9 BACK 0 MSG ON/OFF DIM ± A B C D E H L M N I J K F G O P Q R S T U V W X Y Z ENTER 5.365 0.560 5.750 3.25 REAR VIEW J3 J2 J1 NOTES: 1. ALL DIMENSIONS ARE IN INCHES 2. WEIGHT: APPROXIMATELY 3.8 LBS 3. MATING CONNECTOR: SEE INSTALLATION KIT K12026-4 The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 227 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual Viewing Angles for the 5-Inch FPCDU P/N 1018-X-XX3 (Mod 10) TOP VIEW 10 45 35 SIDE VIEW NOTE: WHEN VIEWING TAWS ON THE 5-INCH FPCDU, THE MAXIMUM BOTTOM VIEWING ANGLE IS 25 DEGREES. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 228 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual F. 4-Inch FPCDU (P/N 1017-( )) (1) P/N 1117-XX and 1117-1-X0X 0.884 4.985 J1 2.300 BACK VIEW TOP VIEW 5.750 5.365 0.585 3.634 3.250 UNIVERSAL 4.500 3.375 MSG NAV DATA DTO FUEL FPL TUNE VNAV PREV LIST NEXT A B C D E F G PWR DIM H I J K L M N O P Q R S T U V W X Y Z 0.560 ENTER 1 4 7 BACK 2 5 8 0 3 6 9 4.370 MENU PERF FRONT VIEW SIDE VIEW NOTES: 1. ALL DIMENSIONS ARE IN INCHES The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 229 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (2) P/N 1117-2-XXX and 1117-X-X1X 4.974 3.787 2.662 0.874 4.974 3.049 4.370 J3 J1 2.300 1.549 J2 TOP VIEW BACK VIEW 5.750 5.365 0.585 3.634 3.250 UNIVERSAL 4.500 3.375 0.560 MSG NAV DATA DTO FUEL FPL TUNE VNAV PREV LIST NEXT A B C D E F G PWR DIM H I J K L M N O P Q R S T U V W X Y Z ENTER 1 4 7 BACK 2 5 8 0 3 6 9 4.370 MENU PERF FRONT VIEW SIDE VIEW NOTES: 1. ALL DIMENSIONS ARE IN INCHES The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 230 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (3) Forward and Aft Mount Top View (P/N 1117-X-XXX) X P/N 1117-X-XX5 and P/N 1117-X-XX6 LE G EW VI AN MA 45 deg. CENTER LINE SCREEN BOUNDRY VI EW 45 deg. AN GL E (4) MA X FWD AND AFT MOUNT TOP VIEW Aft Mount Side View (P/N 1117-X-XX3 and 1117-X-XX5) X MA E GL P/N 1117-X-XX5 W E VI AN 35 deg. SCREEN BOUNDRY CENTER LINE 10 deg. VIEW A NGLE M AX AFT MOUNT - SIDE VIEW The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 231 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (5) Forward Mount Side View (P/N 1117-X-XX4 and 1117-X-XX6) P/N 1117-X-XX6 VIEW ANGLE MAX 10 deg. CENTER LINE SCREEN BOUNDRY 35 deg. EW VI E GL AN X MA FWD MOUNT - SIDE VIEW The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 232 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual G. LP/LPV Monitor (P/N 3116-5X-1110) The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 233 10 July 2019 The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 1.50 0.69 4 0.20 DIA 2 PLCS 14.92 12.756 4 12.457 2.38 REAR CONNECTOR OF THE LP/LPV MONITOR IS KEYED TO #02 POLARIZATION PER ARINC 600. 3. MATING CONNECTOR: SEE INSTALLATION KIT K12075. 2. WEIGHT: RACK = 11.2 ozs., CONNECTOR = 9.0 ozs. 1. ALL DIMENSIONS ARE IN INCHES. NOTES: 1.312 2 PLACES 9.00 14.92 1.77 2.50 7.28 H. 0.20 DIA 2 PLCS 0.18 DIA 4 PLCS UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual LP/LPV Monitor 2MCU Rack (P/N 80009000) Page 234 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual I. DTU-100 (P/N 1406-01-X) UNIVERSAL 5.750 2.250 0.562 7.762 1.88 3.60 0.38 2.124 5.00 DTU CONNECTOR PIN IDENTIFICATION NOTES: 1. ALL DIMENSIONS ARE IN INCHES 2. WEIGHT: APPROXIMATELY 3.25 LBS The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. A M B N C R J P D H G F E K L A M B N C R J P D H G F E J1 J2 34-60-51 K L Page 235 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual J. SSDTU (P/N 1408-00-X) 5.750 2.250 0.604 2.90 6.66 2.50 4.99 0.385 0.88 2.100 5.365 1.495 2.000 NOTES: 1.125 1. ALL DIMENSIONS ARE IN INCHES 2. WEIGHT: APPROXIMATELY 2.4 LBS The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 236 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual K. GPS Antenna (P/N 10708) 4X MOUNTING SCREWS 10-32 UNF-2A X 1.00 LONG CROSS RECESSED FLATHEAD S.S. P/N MS24694-C276 0.50 0.75 TNC FEMALE CONNECTOR NITRILE O-RING 2.375 ID X 0.130 WIDE X .070 DEEP P/N MS28775-142 0.75 4.700 3.000 1.600 0.800 0.70 CONNECTOR CLEARANCE HOLE: 0.63 DIA. 1.040 4X 0.22 THRU 0.385 DIA. 100 DEGREE 0.610 3.300 NOTES: 1. ALL DIMENSIONS ARE IN INCHES 2. WEIGHT APPROXIMATELY 0.5 LBS The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 237 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual L. WAAS (SBAS) GPS/Sirius Antenna (P/N 10709) 4X MOUNTING SCREWS 10-32 UNF-2A X 1.00 LONG CROSS RECESSED FLATHEAD S.S. P/N MS24693-C276 0.65 0.75 YELLOW BLUE SIRIUS TNC FEMALE CONNECTOR GPS TNC FEMALE CONNECTOR CONNECTOR CLEARANCE HOLE: 0.63 DIA. NITRILE O-RING 2.375 ID X 0.130 WIDE X 0.070 DEEP P/N MS28775-142 0.88 4.700 3.000 GPS 0.800 SIRIUS 1.600 0.70 1.040 0.610 4X 0.22 THRU 0.385 DIA. 100 DEGREE 0.700 3.300 NOTES: 1. ALL DIMENSIONS ARE IN INCHES 2. WEIGHT APPROXIMATELY 0.5 LBS The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 238 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual M. WAAS (SBAS) GPS/XM Weather and Radio Antenna (P/N 10710) 4X MOUNTING SCREWS 10-32 UNF-2A X 1.00 LONG CROSS RECESSED FLATHEAD S.S. P/N MS24693-C276 0.65 0.75 YELLOW BLUE XM TNC FEMALE CONNECTOR GPS TNC FEMALE CONNECTOR CONNECTOR CLEARANCE HOLE: 0.63 DIA. NITRILE O-RING 2.375 ID X 0.130 WIDE X 0.070 DEEP P/N MS28775-142 0.88 4.700 3.000 1.600 XM GPS 0.800 0.70 0.70 1.040 0.610 4X 0.22 THRU 0.385 DIA. 100 DEGREE 0.700 3.300 NOTES: 1. ALL DIMENSIONS ARE IN INCHES 2. WEIGHT APPROXIMATELY 0.5 LBS The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 239 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual Installation and Wiring 1. General The basic Flight Management System architecture is shown in the Description and Operation section for single and dual systems. Non-shielded wires are MIL-W-22759, and shielded wires are MIL-W-27500 or equivalent. A. Form – Dimensions and Communications This FMS is designed to comply with the dimensional standards specified in ARINC Specification 600, Air Transport Avionics Equipment Interfaces. Inter-unit communications between navigation sensors/equipment and the FMS, as well as between the FMS and the flight guidance system are transmitted and received in two-wire ARINC 429 digital format. The digital ARINC 571 and 575 are also standard formats for interface with navigation and air data systems. The FMS utilizes an aircraft mounted or portable DTU-100 Data Transfer Unit (DTU) connected through a 10base-T Ethernet for data loading and downloading from Iomega Zip disks. A representative listing of compatible sensors and systems with which the FMS can communicate, are in the Digital Inputs, Analog Inputs, Digital Outputs, and Analog Outputs tables. Information about the formats/types of input and output data required and used for each of the sensors/systems is also indicated in the table. The tables are used to determine and select compatible sensors/systems for use with the FMS, and obtain data format/type information for system interconnection strapping when installing the sensors/systems. The FMS is configured to a specific aircraft installation by the use of a Configuration Module that is a part of the aircraft installed FMS rack. At the time of installation, the configuration module is programmed through CDU keypad inputs to completely define the sensor input ports, fuel flow types, air data type, EFIS interface etc. A replacement FMS of both the same part number and SCN can be installed without having to reprogram the FMS because the configuration module retains the programmed information for the aircraft. B. Sensor/Equipment Compatibility/Selection When determining compatibility and selecting sensors, the following information applies: The FMS is capable of receiving inputs from a variety of short and long-range sensors. The signal input type from these sensors must be in a digital format to properly interface with the FMS. The number of sensors the FMS is capable of using is determined by the type of FMS and the number of available input ports. Some sensor inputs are port specific. This must be a consideration when multiple sensor inputs are used. (1) IRS or IRS/GPS Sensors A maximum of three may be used configured in any order or combination. All IRS or IRS/GPS sensors are to be of the same type. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 301 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (2) GPS Sensors A maximum of three GPS sensors, including GLS, GNSS, GPS, GPS/WAAS and Hybrid GPS and IRS sensors may be used. These sensors can be configured in any order or combination. The FMS, in conjunction with either an internal GPS/WAAS or an appropriate external GPS, is certifiable for use as a primary means of navigation in remote/oceanic airspace using GPS in accordance with the provisions of AC 20-138A Appendix 1. There are specific FMS hardware and software requirements as well as GPS/WAAS hardware and software requirements. Additionally, a RAIM prediction program is required to verify that adequate integrity will exist for the proposed flight. (3) RRS Sensor An RRS may be used in place of DME/VOR/TACAN receivers. (The RRS contains the electronics of a multi–channel DME/TACAN receiver-transmitter with a VOR receiver. The RRS is tuned remotely by the FMS using the ARINC 429 data bus.) (4) RRS/RTU The RRS and RTU can be installed and used in the same aircraft. The RRS provides radio navigation inputs and the RTU is used for pilot command tuning of radios. In the event of an RRS failure, the pilot must select CSDB tuning of the DME (if installed) to allow uninterrupted DME–DME navigation. The FMS provides optional radio tuning of COM, NAV, ADFs and transponders via CSDB or ARINC 429, depending on radio manufacture and type. It may also be dependent on the use of Universal’s Radio Tuning Unit (RTU). If an RTU is used, the RTU software version must be compatible with the FMS software. Tuning of the VHF NAV and DME for navigation does not require an external RTU because tuning is handled by the FMS. (5) Air Data Air data must be supplied in ARINC 429 or 575 formats. If an analog air data computer is installed in the aircraft, an Air Data Converter Unit (ACU) may be an option. The ACU will convert the analog air data to ARINC 429. If the aircraft has no TAS source, an air data computer must be installed. The type of air data input (barometric altitude, pressure altitude or both) provided by the air data source must be verified. The FMS must be configured to exactly match these inputs. Both barometric altitude and pressure altitude must be configured if the advanced performance option is enabled with the FMS. The accuracy of the air data is also a consideration when the FMS will be certified for VNAV or 3D coupled approaches. If the accuracy is not sufficient, then only lateral approach operation will be possible. Universal Avionics requires the use of barometric altitude. Without barometric altitude, SIDs and STARs with altitude terminators and missed approach procedures cannot be flown. Also, VNAV operation below 18,000 feet is not possible and the system is limited to enroute navigation and 2D approaches only. Flight manual supplement limitations will be required. ARINC Radio Tune Unit (ARTU) The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 302 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual The ARTU provides interface between the FMS and the Collins 429 radios using the Collins RTU-870 Radio Tuning Unit. Radios may be tuned via the UASC FMS or the Collins RTU-870. The UASC FMS and the Collins RTU-870 are interactive and no external switching is required. (7) Display Interfaces Instrument display input signal type must be determined (either analog or digital) and if digital, the format (ARINC 429, 561, 571) must also be determined. (a) Universal’s Electronic Flight Instrument (EFI) and Multi-Function Display (MFD) Universal EFIs (ND/HSI and ADI) and MFD when interfaced with Universal’s FMS are capable of correctly displaying navigation and flight plan data. EFI and MFD displays give the operator the capability to select and display needed information on demand as flight data changes occur. (b) Electro-mechanical Instruments Aircraft that incorporate electro-mechanical instruments may not have autocourse slewing. This requires the flight crew to manually position the course pointer to display desired track. Bearing pointers may also not be compatible due to load problems and may require the addition of an amplifier. (c) EFIS CAUTION: IF 429 ADV IS PROGRAMMED WITHOUT A COMPATIBLE EFIS, THE FLIGHT PLAN WILL BE DRAWN INCORRECTLY. 429 GAMA MUST BE PROGRAMMED WITH ANALOG INSTRUMENT INTERFACES OR NON-COMPATIBLE EFIS. Collins EFIS 85/86 status B-4, B-14, C-4, C-14, E-F, E-14 or Bendix/King EFIS 40/50 (SG 65 symbol generators) or equivalent can be configured for interface by selecting 429 ADV. When 429 ADV is selected, the EFIS will be capable of correctly displaying a flight plan on the map display when the flight plan contains a gap or procedural leg. The map display will draw the flight plan line to the last fixed waypoint before the gap or procedural leg and end there. The flight plan display will start again at the next fixed waypoint after the gap and be drawn to the following waypoints. When interfaced to EFIS displays the FMS must be correctly configured for signal type (429 ADV, 429 GAMA, EDZ 705, 429 DHC, ASCB, etc.). Display scaling for each EFIS display must be addressed, not all EFIS displays meet the necessary criteria for approaches. With ARINC 429 EFIS interfaces where the EFIS is not compliant with TSO C-129 scaling requirements, the system may be restricted to the use of flight director steering only for terminal and approach operations. The installer should discuss the issue with the certification agency before proceeding with the installation. Analog and ARINC 561 displays usually present no problems. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 303 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (8) Universal Avionics Terrain Awareness Warning System (TAWS) When interfaced with a Universal Avionics FMS, the TAWS system is able to provide terrain awareness information based on information from the FMS. The information from the FMS provides TAWS with the ability to determine the aircraft’s state and intent and provide caution and warning alerts. The FMS is capable of displaying maps and symbology generated by TAWS. TAWS provides “Flight Plan Look Ahead” terrain alerts by comparing the FMS flight plan to terrain databases. (9) Radar The FMS can be configured to accept input from one or two radar sensors. When two radar sensors are used, one must be a Doppler radar and the other must be a 429, 571, or 1500 radar. The FMS supports the following radar systems: Collins WXR–300 MFD Sperry Data Nav III Bendix Radar Nav IU–2023B Bendix Radar 1500 IU–1507A Racal Avionics Limited Doppler 91 AN/ASN–137 Doppler NOTE: For further compatibility information on specific equipment, refer to the applicable sensor manual. (10) Annunciators Standard annunciations provided by the FMS are: FMS HDG (heading), FMS SXTK (selected crosstrack), MSG (message), WPT (waypoint), DR (dead reckoning) and FMS APPR (approach). If utilizing GPS for approach or for GPS Primary Means of Navigation, then GPS INTEG (GPS integrity) will be required. Universal’s FMS outputs discretes for these annunciations. Annunciator signals are also provided on the applicable busses for use in EFIS installations when desired. On EFIS systems which display G/S (glideslope) in lieu of VNAV (vertical deviation) during FMS approach mode, a PSEUDO ILS annunciator may be required to alert the flight crew that the vertical display is FMS generated information and not sourced or provided glideslope information. There may be minor variations to the actual nomenclature displayed but the FMS modes must be in some way displayed and annunciated. Level of Service (LOS) discretes are provided by the WAAS subsystem for SBAS approaches. These non-configurable discretes are LPV, LNAV/VNAV and LNAV (LOS 1, LOS 2 and LOS 3 respectively). These provide annunciation for the LOS in installations not interfaced with Universal’s EFI-890R or EFI-550. It is required that the approach type be annunciated in the pilot's primary field of view. For aircraft that have LPV approval, LPV, LNAV/VNAV and LNAV annunciators must be installed. Aircraft that do not have LPV approval, LNAV/VNAV and LNAV annunciators must be installed. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 304 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (11) Enroute Steering Interfaces Many existing long-range navigation systems have been interfaced in the past to flight guidance/autopilot systems via left/right deviation steering only. This was adequate for those systems capable of only enroute navigation. However, new and advanced systems require that roll steering be used. By using a roll command interface the FMS can provide steering for all procedural leg types including heading to altitude, DME arcs, holding patterns, turn anticipation, procedure turns and other complex maneuvers. The FMS outputs roll command steering at 393 mV/deg for enroute and terminal navigation and roll steering only approaches. Interface with flight director/autopilot normally uses a designated LRN input to the F/D and A/P equipment or through the HDG channel with external switching. F/D and A/P coupled operation utilizing L/R deviation only is not recommended and is not certifiable. If a designated LRN F/D and A/P input is not available (specifically the J.E.T. FC200 F/D and A/P) a Universal Steering Interface Unit (SIU) can be utilized to switch the roll command steering signal to the F/D and A/P and properly scale the 393 mV/deg. The SIU will also command the necessary logic to annunciate the appropriate modes of operation. (12) Approach Functions and Options Universal FMS systems have been certified in the United States and other countries for GPS only, GPS overlay, VOR, VOR/DME, TACAN, RNAV and NDB nonprecision approaches using GPS as the navigation sensor. Approaches of these types are contained in the FMS published navigation database include approach transitions and missed approach segments. The FMS systems use GPS combined with other navigation sensors and baro corrected altitude data to provide lateral and vertical guidance from the Final Approach Fix (FAF) to the runway and then to the missed approach and missed approach holding waypoints. At approach initiation, when the approach mode is selected on the Control Display Unit by the pilot, the GPS will remain selected when the approach definition data used is contained within the FMS on-board published database as an approved GPS approach. If the approach from the database is not a published GPS approach then the sensor will automatically be deselected at approach initiation. Generally there are several ways of installing Universal’s FMS for approach operations. It must be decided how the FMS is to be certified concerning approaches; whether or not the FMS approach capability will be roll steering only, or roll steering with VDEV displayed, fully 3D coupled or RNAV(GPS) approach procedures using a WAAS/GPS sensor calculated position. This determination will dictate which additional annunciation(s) will be required to be added to the cockpit for certification, which strapping will be required on certain EFIS systems, etc. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 305 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual Using the WAAS/GPS sensor calculated position, the FMS provides localizer performance and vertical guidance for WAAS approach procedures. A WAAS approach is one that is charted as RNAV (GPS) and approved for WAAS. In addition to standard Lateral Navigation (LNAV) guidance, the FMS provides lateral and vertical guidance for Lateral Navigation/Vertical Navigation (LNAV/VNAV) and Localizer Performance with Vertical Guidance (LPV) approach minimums for WAAS approaches. LNAV/VNAV approaches use lateral and vertical guidance from the FMS for a controlled descent to the runway. An LPV approach is similar to an LNAV/VNAV approach except it has lower approach minimums and requires dual FMS installation. The FMS can also provide 2D coupled (along track and crosstrack) operation using the roll steering input channel to the FGS. The approach gain for the roll steering output from the FMS is configurable to provide a more aggressive path following for approaches. A gain of ’3X’ is recommended. The FGS will remain in NAV mode; the FMS will steer the approach transition segments and final approach using the same roll steering command input that is used for enroute operations. In this case, it is very desirable to provide a vertical display on the HSI of the pseudo glideslope VNAV deviation. Coupled vertical approach will not be possible with this interface design and it will be up to the flight crew to make the descent using another FGS mode. From an interface standpoint, this is the simplest method to interface for approaches. The limitation of this interface is the lack of coupled vertical ILS-like operation. Some installations such as the LR-60, LR-31, Dash 8, Falcon 2000 and Astra SPX do use pitch command for approach mode but this is not the typical scenario for retrofit installations. A third method of interfacing the FMS for approach involves 3D fully coupled pseudo ILS approaches. This is accomplished by switching FMS analog lateral and vertical deviation signals in place of real ILS data to the HSI and FGS. During the approach transition segments with NAV mode selected on FGS and LRN selected for display, the FMS (established inbound and less than 0.2nm cross track for autoactivation) the FMS approach active annunciator output from the FMS is used to provide relay logic to switch the FMS deviation to the HSI and FGS along with simulated Tune-to-Localizer. FMS lateral and vertical deviations are switched to the FGS and approach arm/capture functions are available for F/D and A/P operation. The HSI and FGS will use the simulated ILS and thus ILS control laws of the FGS are used. This generally results in approaches with better path following than roll steering approaches. This type of installation obviously adds complexity and requires detailed description in the AFM supplement as well as proper aircrew training. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 306 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual C. Electrical Connectors The FMS uses low insertion force, size 2 shell, ARINC 600 service connectors. The connector guide pins of the FMS are arranged differently to prevent their connection to noncompatible racks. For the ARINC 600 index pin coding of the FMS connector, refer to the FMS outline drawing in the Equipment Specifications section of this manual. D. Remote Annunciators The FMS provides outputs to remotely mounted panel annunciators. These include remote Message, Waypoint Alert, Selected Crosstrack, GPS Integrity, FMS Heading and FMS Approach advisories. In addition, a “System On” discrete output is available to the installer for use in activating remote switching (if required). Level of Service (LOS) discretes are provided by the WAAS subsystem for SBAS approaches. These non-configurable discretes are LPV, LNAV/VNAV and LNAV (LOS 1, LOS 2 and LOS 3 respectively). These provide annunciation for the LOS in installations not interfaced with Universal’s EFI-890R or EFI-550. E. FMS Mounting The FMS must not be mounted next to excessive heat producing equipment or in such a way as to impede normal convection cooling. The FMS can however be mounted in any orientation with respect to the aircraft longitudinal axis. The FMS racks must be grounded to the airframe by wire braid. This provides a positive grounding of the racks to which data shields are connected. The Configuration Module is mounted on the FMS rack. Refer to the Configuration Module Installation drawing in the Equipment Specifications section of this manual. The FPCDU is instrument or pedestal mounted using standard configuration Dzus rails. Consideration should be given to the depth of the FPCDU and wire bundles when planning installation. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 307 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual F. GPS (WAAS) Antenna Mounting (1) Installation Considerations The antenna should be mounted on top of the fuselage near the cockpit. Avoid mounting the antenna near any projections, the propeller, the T–Tail, and minimize shadowing by the wing during maneuvers. The antenna should also be located with proper spacing to other system antennas such that no performance degradation will occur due to shadowing of signals and/or RF interference. Minimum Antenna Separation Antennas Distances GPS-GPS 12 inches GPS-SATCOM (INMARSAT, 1625 MHz) 4 feet GPS-all other antennas 4 feet Limited by aircraft dimensions, valid range is defined for each axis component of antenna offset. The table below lists the valid range, standard offset values, and the positive sense for the antenna offset. NOTE: For the LPV/LP Monitor, antenna offsets cannot be changed through configuration and the standard offsets are used. Navigational Center (NC) is defined as the navigational center of the aircraft, typically the ILS glideslope antenna. Valid Range, Standard Offset and Positive Sense for Antenna Offset Configuration Antenna Offset Valid Range Standard Positive Sense Offset Axis (relative to the NC) (a) Longitudinal (X) +90 m, -30 m +3 m Lateral (Y) +4 m, -4 m 0m AFT of the NC Right of the NC (aircraft cockpit in the front) Vertical (Z) +15 m, 0 m +2 m Above the NC Acceptable Antenna Placement When using the standard antenna offsets (X = 3.0 m, Y = 0.0 m, Z = 2.0 m), It is intended that for most aircraft it is acceptable to use the standard antenna offsets as a default. Y axis: It is acceptable to place the antenna anywhere on the Y axis and still use the standard offset of Y = 0. X axis: It is acceptable to place the antenna anywhere on the X axis and still use the standard offset of X = 3. The assumption is that the antenna is not generally installed forward of the aircraft's forward bulkhead which is usually associated with the NC (navigation center). Z axis: It is acceptable to place the antenna up to 5 meters above ground level (bottom of the aircraft wheels) and still use the standard offset of Z = 2. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 308 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (b) Recommended configurations: Dual WAAS FMS installations: For any antennas that are installed within 5 meters of the ground, use the standard offsets for those antennas. For any antennas that are installed higher than 5 meters above the ground, configure the actual antenna offsets in the FMS. WAAS FMS with a LP/LPV Monitor Installations: If both antennas are installed within 5 meters of the ground, use the standard offset in the FMS. If one antenna is installed higher than 5 meters above the ground and one antenna is within 5 meters of the ground, wire the antenna that is within 5 meters of the ground to the LP/LPV Monitor box and the antenna that is higher than 5 meters to the FMS. Use the standard offsets for the LP/LPV Monitor and use actual antenna offsets in the FMS. If both antennas are installed higher than 5 meters, use of the LP/LPV Monitor box is not acceptable. NOTE: It is possible for antennas installed higher than 5 meters to use the standard offsets, but the placement of the antenna will need to be analyzed. The analysis will depend upon aircraft length, fuselage height, location of the NC and the pitch attitude when the aircraft flies on the glideslope. Generally, in this case, the further aft the antenna is installed, the better. (2) Installation Instructions Total attenuation losses due to antenna cabling and connections must not exceed the minimum recommended specifications listed below. Attenuation losses will vary depending on the type of RF cable connected to the antenna. The gain of the antenna/preamplifier minus the loss of the cable and end connectors should be between 20 (minimum) and 30 dB for optimum performance. For instance, if the GPS is being connected to antenna P/N 10708, which has a nominal gain of 30 dB, total attenuation losses, must not exceed 10 dB. To ensure a minimum 20 dB of gain from the antenna input to the GPS/WAAS sensor. It is also highly recommended that only high quality, low-loss cable such as ECS or PIC RG-142, RG-400 or equivalent coax cable is used in the installation. Refer to the following table for the maximum allowable cable loss specifications based on the amount of antenna gain. Gain/Loss Specifications Antenna Part Number Antenna Gain Maximum Cable Loss 10708 30 2 dB 10 dB 10709 30 3 dB 10 dB 10710 30 3 dB 10 dB The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 309 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual Mechanical structure modifications to install GPS antenna(s) should be carried out in accordance with the guidelines of FAA Advisory Circular AC 43.13. Installation of the antenna, its electrical bonding to the structure, coaxial cable routing and clamping should also be accomplished per this advisory. Refer to the antenna installation drawing contained in the Equipment Specifications section of this manual for detailed information. The design of the GPS antenna is such that a ground plane is required. To assure maximum protection from a possible lightning strike, the antenna base should conduct to the mounting surface. This can be accomplished by removing paint in the area of contact between the antenna base and the aircraft skin. The hole for TNC connector should be about 0.75-inch diameter. Make the smallest practical hole in the pressure vessel. Fasten the antenna with four screws of sufficient length to assure that at least two full threads protrude beyond the locking nut or threaded backing plate (if used). Apply a maximum torque of 10 in. lbs. to avoid cracking the plastic radome of the antenna. Apply a sealant (RTV is recommended) over screw heads and around the periphery of the antenna to exclude moisture. Check bonding of the antenna to the aircraft skin by measuring the resistance between the skin of the aircraft and the antenna connector housing using a shunt-type ohmmeter such as a Wheatstone Bridge or Kelvinometer. There should be no more than 100 milliohms resistance measured. This measurement is accomplished from the inside of the aircraft with the antenna installed. (3) Long Cable Runs In installations with very long cable runs, it is permissible to use a low loss coax cable (such as Electronic Cable Specialists P/N 311501) for the run from the antenna to a bulkhead connector. Then use a smaller coax (such as ECS P/N 3C3160 M17/113-RG316) from the bulkhead connector to the UNS–1Fw. Components for this application are listed below. Coax cable P/N 311501 3C3160 Attenuation 1.575 GHz = 0.087 dB/ft. 1.575 GHz = 0.405 dB/ft. Minimum Bend Radius 1.22 in. (nominal) 1.02 in. (nominal) TNC Straight CTS922 31-2315-1000 TNC 90º CTR922 KA-59-281 Bulkhead TNC BTS922 N/A BNC Straight CBS922 225395-7 BNC 90º CBR922 KC-59-318 RF Connectors P/Ns Complete FMS GPS cable assemblies as well as bulk coax cable and connectors are available from Electronic Cable Specialists. Refer to Wire and Cable Manufacturers in the Equipment Specifications section of this manual. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 310 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual G. Solid State Data Transfer Unit (SSDTU) Installation Considerations The SSDTU is available in two models, a fixed installation model that is permanently installed in the aircraft and a portable model which is carried into the aircraft, attached to an interface connector, used, then disconnected and removed prior to flight. The SSDTU is the same fit as a DTU-100. The SSDTU may be used as a replacement for a DTU-100 and can be directly installed without any modifications to the aircraft or wiring using connector P1, which allows the use of a single Ethernet connection. If the aircraft is wired for the DTU-100 using four Ethernet ports, connector P2 must be replaced with connector P/N 83000255 which is included in the SSDTU installation kit P/N K12079-1, no additional wiring is needed. To have all eight Ethernet ports available on the SSDTU, the P2 connector must be replaced and additional wiring must be installed. If the aircraft is wired for a Portable DTU-100, use the wiring harness (P/N 81304072) to connect bulkhead connector P1 to the Portable SSDTU J1 and the retrofit wiring harness (P/N 81140811) to connect bulkhead P2 to J2 of the Portable SSDTU. This allows one Ethernet connection on P1 and three Ethernet connections on P2. For the additional four Ethernet ports to be available to the Portable SSDTU, the existing P2 bulkhead connector must be replaced with connector P/N 83000558 and additional wiring must be installed. Refer to the applicable pin identification tables and wiring diagrams in this section. J1 Pin Crossover SSDTU Functions SSDTU Pins DTU-100 Functions DTU-100 Pins EIA-485 (Side A) (FMS 485 A) A RS-422 A A EIA-485 (Side B) (FMS 485 B) B RS-422 B B Ethernet #1 RX (+) C Ethernet #0 RX (+) C Ethernet #1 RX (-) D Ethernet #0 RX (-) D Ethernet #1 Shield E Ethernet #0 Shield E Ethernet #1 TX (+) F Ethernet #0 TX (+) F Ethernet #1 TX (-) G Ethernet #0 TX (-) G H Option Pin 0 H J Option Pin 1 J K K Chassis Ground L Chassis Ground L Power 28 VDC M Power 28 VDC M EIA-232 RX N Aux Port RX (RS-232 RX) N Ground P Ground P EIA-232 TX R Aux Port TX (RS-232 TX) R The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 311 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual J2 Pin Crossover NOTE: Pin numbers/letters not listed are not used or assigned any function. SSDTU Functions SSDTU Pins DTU-100 Functions DTU-100 Pins Ethernet #3 RX (+) 1 Ethernet #2 RX (+) E Ethernet #3 TX (+) 2 Ethernet #2 TX (+) G Ethernet #2 RX (-) 4 Ethernet #1 RX (-) B Ethernet #3 RX (-) 6 Ethernet #2 RX (-) F Ethernet #3 TX (-) 7 Ethernet #2 TX (-) H Ethernet #4 TX (-) 8 Ethernet #3 TX (-) N Ethernet #4 TX (+) 9 Ethernet #3 TX (+) L Ethernet #2 TX (-) 10 Ethernet #1 TX (-) D Ethernet #2 RX (+) 11 Ethernet #1 RX (+) A Ethernet #3 Shield 13 Ethernet #4 RX (-) 15 Ethernet #3 RX (-) K Ethernet #4 RX (+) 16 Ethernet #3 RX (+) J Ethernet #2 TX (+) 18 Ethernet #1 TX (+) C Ethernet #2 Shield 19 Ethernet Shield P Ethernet #4 Shield 23 Ethernet #8 TX (-) 27 Ethernet #8 RX (-) 28 Ethernet #8 Shield 29 Ethernet #5 Shield 30 Ethernet #5 TX (+) 31 Ethernet #8 TX (+) 35 Ethernet #8 RX (+) 36 Ethernet #5 RX (+) 38 Ethernet #5 TX (-) 39 Ethernet #7 RX (+) 40 Ethernet #7 RX (-) 41 Ethernet #7 Shield 42 Ethernet #6 Shield 44 Ethernet #5 RX (-) 46 Ethernet #7 TX (+) 47 Ethernet #7 TX (-) 48 Ethernet #6 TX (+) 50 Ethernet #6 RX (+) 51 Ethernet #6 TX (-) 54 Ethernet #6 RX (-) 55 The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 312 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual 2. FMS Interfaces Interconnection wiring information between the aircraft, FMS, CDU, DTU is provided in the following paragraphs and wiring diagrams. Information about the connection to VOR, DME, TACAN, radar, flight control and fuel flow systems is provided in the WAAS FMS Interface Manual, 34-60-53. Configuration of the FMS can be found in the WAAS FMS Configuration Manual 34-61-01. A. Analog Inputs Input Description Altitude Coarse Synchro/Roll Altitude Fine Synchro/Pitch Altitude Synchro Reference Autopilot Reference Plug/Pin TP 1H TP 1J TP 1K TP 1D TP 1E TP 1F TP 1A TP 1B MP 11D MP 11E Characteristics (X) DC ARINC 565 Coarse Synchro (Y) Reference or Coarse Altitude (Z) Common or Roll (X) Sin ARINC 565 Fine Synchro (Y) Cos or Fine Resolver Altitude (Z) Common or Pitch (H) 26 VAC 400 Hz (C) 26 VAC 400 Hz (H) 26 VAC, 400 Hz (C) 26 VAC, 400 Hz Input Voltage: Fuel Flow #1 Fuel Flow #2 Fuel Flow #3 Fuel Flow #4 Heading Synchro Heading Reference MP 15A MP 15B MP 15C MP 15D MP 15E MP 15F MP 15G MP 15H MP 9A MP 9B MP 9C 26 VAC RMS ± 10%, 400 Hz ± 20 Hz Input Impedance: 80 kΩ (minimum) Input Load: 2 mA (maximum) (H) Depends on Configuration (L) (H) Depends on Configuration (L) (H) Depends on Configuration (L) (H) Depends on Configuration (L) (X) Impedance = 33 kΩ (Y) Impedance = 33 kΩ (Z) Impedance = 24 kΩ MP 9D MP 9E Standard ARINC 407 three–wire synchro transmitter (or equivalent) with two–wire reference signal from aircraft compass system. (H) 26 VAC, 400 Hz (Common) 26 VAC, 400 Hz Input Voltage: Input Impedance: Input Load: The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 26 VAC RMS ± 10%, 400 Hz ± 20 Hz 80k Ω (minimum) 2 mA (maximum) Page 313 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual A. Analog Inputs (continued) Input Description Instrument Synchro Reference (Applicable to Analog configuration only) Static Air Temperature True Airspeed WAAS Crosschannel Lateral Deviation (Applicable to Analog configuration only) WAAS Crosschannel Vertical Deviation (Applicable to Analog configuration only) The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. Plug/Pin MP 1E MP 1F Characteristics (H) 26 VAC, 400 Hz (Common) 26 VAC, 400 Hz Input Voltage: TP 3E TP 3F TP 3G TP 3A TP 3B TP 3C TP 2G TP 2H 26 VAC RMS ± 10%, 400 Hz ± 20 Hz Input Impedance: 80k Ω (minimum) Input Load: 2 ma (maximum) Reference Voltage ARINC 565 DC Return Reference and Signal Signal Voltage ARINC 565 Reference Voltage ARINC 565 DC Return Reference and Signal Signal Voltage ARINC 565 (H) (L) TP 2J TP 2K (H) (L) 34-60-51 Page 314 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual B. Discrete Inputs Input Description Discrete Input 1 Plug/Pin MP 6G Discrete Input 2 MP 6H Discrete Input 3 MP 6J Discrete Input 4 MP 15J Discrete Input 5 MP 11H Discrete Input 6 MP 15K Discrete Input 7 MP 6A Discrete Input 8 MP 6E Discrete Input 9 MP 6F Discrete Input 10 MP 11G Discrete Input 11 MP 6B Altitude or Attitude Valid Altitude Valid FMS #2 FMS #3 Heading Input MAG/TRUE TP 3J TP 3K MP 11J MP 11K MP 9G Heading Input Valid SAT Valid TAS Valid WAAS Crosschannel Level of Service WAAS Crosschannel Fail Steering Valid WAAS Crosschannel Vertical Guidance Monitor WAAS Crosschannel Lateral Guidance Monitor Power Control MP 9F TP 5E TP 5A TP 4H TP 4G MP 11C TP 4J The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. Characteristics Ground / Open (Configurable) See System Data Installation for list of discrete inputs. Ground / Open (Configurable) See System Data Installation for list of discrete inputs. Ground / Open (Configurable) See System Data Installation for list of discrete inputs. Ground / Open (Configurable) See System Data Installation for list of discrete inputs. Ground / Open (Configurable) See System Data Installation for list of discrete inputs. Ground / Open (Configurable) See System Data Installation for list of discrete inputs. Ground / Open (Configurable) See System Data Installation for list of discrete inputs. Ground / Open (Configurable) See System Data Installation for list of discrete inputs. Ground / Open (Configurable) See System Data Installation for list of discrete inputs. 28VDC / Open (Configurable) See System Data Installation for list of discrete inputs. Ground / Open (Configurable) See System Data Installation for list of discrete inputs. 28 VDC / Open Ground / Open Ground / Open (Ground = FMS #2) Ground / Open (Ground = FMS #3) 28 VDC / Open (Open = MAG / 28 VDC = TRUE) 28 VDC / Open 28 VDC / Open 28 VDC / Open Ground / Open Ground / Open 28 VDC / Open (28 VDC = Valid) 28 VDC / Open TP 4K 28 VDC / Open BP 4 Ground / Open (FMS Power On/Off) 34-60-51 Page 315 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual C. Digital Inputs (1) ASCB Inputs (SCN 1000.5/1100.5 and later) The ASCB board provides the FMS with an interface to the ASCB Version A data bus developed by Honeywell and supplement the ARINC, CSDB, and analog interfaces of the FMS. Input Description ASCB Discrete In 1 ASCB Discrete In 2 ASCB Discrete In 3 ASCB Discrete In 4 ASCB Discrete In 5 ASCB Discrete In 6 ASCB Discrete In 7 ASCB Discrete In 8 ASCB A Clock 1 + ASCB A Clock 1 – ASCB A Data 1 + ASCB A Data 1 – ASCB B Clock 2 + ASCB B Clock 2 – ASCB B Data 2 + ASCB B Data 2 – NOTE: Plug/Pin TP 9A TP 9B TP 9D TP 9F MP 3A MP 3B MP 5J TP 9C MP 1C MP 3C MP 1A MP 1B MP 1G MP 1H MP 5G MP 5K Characteristics Ground / Open Ground / Open Ground / Open Ground / Open Ground / Open Ground / Open Ground / Open Ground / Open Assuming NCU #1 is to be configured for TX/RX on Left ASCB bus, ASCB A Port (On-Side) is connected to the Left ASCB Bus and ASCB B Port (Off-Side) is connected to the Right ASCB Bus. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 316 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (2) CSDB Inputs Some sensors are restricted to certain input ports. The allowable CSDB port assignments and their pin numbers are found in the WAAS FMS Configuration Manual, Report No. 34-61-01. Input Description Receive From External CDU #1 (Note) Receive From External CDU #2 (Note) CSDB Receiver Port 1 CSDB Receiver Port 2 CSDB Receiver Port 3 CSDB Receiver Port 4 WAAS Differential Timemark A WAAS Differential Timemark B The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. Plug/Pin Characteristics MP 2A MP 2B MP 2C MP 2D MP 14C MP 14D MP 2G MP 2H MP 14A MP 14B MP 14E MP 14F TP 10A TP 10B (H) External CDU (L) (H) External CDU (L) (A) Depends on Configuration (B) (A) Depends on Configuration (B) (A) Depends on Configuration (B) (A) Depends on Configuration (B) (A) RS-422 (B) RS-422 34-60-51 Page 317 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (3) ARINC Input Ports Some sensors are restricted to certain input ports. The allowable ARINC port assignments and their pin numbers are found in the WAAS FMS Configuration Manual, Report No. 34-61-01. Port Plug/Pin Description Notes Port 0 TP 10C TP 10D MP 4G MP 4H MP 12C MP 12D MP 12G MP 12H MP 8A MP 8B MP 8C MP 8D MP 8E MP 8F MP 8G MP 8H TP 13C TP 13D TP 13G TP 13H TP 13J TP 13K TP 14A TP 14B TP 14E TP 14F TP 14G TP 14H TP 15A TP 15B TP 15E TP 15F MP 10F MP 10E MP 10G MP 10H TP 2A TP 2B (A) ARINC 429 or 419 (LS) (B) (A) ARINC 429 or 419 (LS) (B) (A) ARINC 429 or 419 (LS) (B) (A) ARINC 429 or 419 (LS) (B) (A) ARINC 429 or 419 (LS or HS) (B) (A) ARINC 429 or 419 (LS or HS) (B) (A) ARINC 429 or 419 (LS or HS) (B) (A) ARINC 429 or 419 (LS or HS) (B) (A) ARINC 429 or 419 (LS) (B) (A) ARINC 429 or 419 (LS) (B) (A) ARINC 429 or 419 (LS) (B) (A) ARINC 429 or 419 (LS) (B) (A) ARINC 429 or 419 (LS or HS) (B) (A) ARINC 429 or 419 (LS or HS) (B) (A) ARINC 429 or 419 (LS or HS) (B) (A) ARINC 429 or 419 (LS or HS) (B) (A) WAAS Offside FMS (B) (A) WAAS Cross-channel Receive (B) (A) WAAS Cross-channel Monitor #1 (Guidance Bus) (B) 1, 2, 4 Port 1 Port 2 Port 3 Port 4 Port 5 Port 6 Port 7 Port 8 Port 9 Port 10 Port 11 Port 12 Port 13 Port 14 Port 15 WAAS Port 0 WAAS Port 1 WAAS Port 2 The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 3 3 3 3 3 3 3 3 5 5 5 Page 318 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual Port Plug/Pin Description Notes WAAS Port 3 TP 2C TP 2D (A) WAAS Cross-channel Monitor #2 (Guidance Bus) (B) 5 NOTES: 1. In all dual WAAS FMS installations, RX Port 0 must be configured to WAAS n (where n represents 1 for FMS#1 or 2 for FMS#2) This is required because internal WAAS subsystem uses the configuration information for RX Port #0 to set up the speed for the WAAS ARINC 743A TX port. 2. In single WAAS FMS with LP/LPV Monitor installations, RX Port #0 must be configured for WAAS 1. In this installation, the configuration information for RX Port #0 is used to set up the speed for the WAAS ARINC 743A TX port of the internal WAAS subsystem and the LP/LPV Monitor. 3. Available in Dual ARINC configuration only. 4. Port #0 should not be connected to any external system. 5. For WAAS use only, not a configurable port. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 319 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual D. Analog Outputs Output Description Desired Track Lateral Deviation Pitch Command Roll Steering To/From Vertical Deviation Waypoint Bearing/Drift Angle (1) Plug/Pin Characteristics MP 3A MP 3B MP 3C MP 3F MP 3G (X) Synchro X (Y) Synchro Y (Z) Synchro Z (H) +R – Fly Right, Left of Course (L) +L – Fly Left, Right of Course See Lateral Deviation Characteristics Table Below (H) AC or DC pitch (L) Pitch Return (H) 0.393 VAC RMS/Degree (L) Right Roll in Phase (H) + To 180-250 mV Output (L) + From (H) +Up – Fly Up, Below Course (L) +Down– Fly Down, Above Course See Vertical Deviation Characteristics Table Below (X) Synchro X (Y) Synchro Y (Z) Synchro Z MP 1G MP 1H MP 11A MP 11B MP 5J MP 5K MP 7F MP 7G MP 1A MP 1B MP 1C Lateral Deviation Characteristics Range 2 Dot Value Invalid Stow Value Low Level Configuration Enroute –250 to +250 mVDC 2NM –150 to +150 mVDC 0.0 VDC N/A Terminal –250 to +250 mVDC 1NM –150 to +150 mVDC 0.0 VDC N/A 0.3 NM –250 to +250 mVDC 0.3NM –150 to +150 mVDC 0.0 VDC N/A Approach –250 to +250 mVDC Angular –150 to +150 mVDC 0.0 VDC N/A High Level Configuration Enroute –10 to +10 VDC 2NM –6 to +6 VDC 0.0 VDC N/A Terminal –10 to +10 VDC 1NM –6 to +6 VDC 0.0 VDC N/A 0.3 NM –10 to +10 VDC 0.3NM –6 to +6 VDC 0.0 VDC N/A Approach –10 to +10 VDC Angular –6 to +6 VDC 0.0 VDC N/A The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 320 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (2) Vertical Deviation Characteristics Range 2 Dot Value Invalid Stow Value Low Level Configuration Enroute –205 to +205 mVDC 1476 ft. –150 to +150 mVDC 750 mVDC 1.3 VDC Terminal –250 to +250 mVDC 492 ft. –150 to +150 mVDC 750 mVDC 1.3 VDC 0.3 NM –250 to +250 mVDC 200 ft. –150 to +150 mVDC 750 mVDC 1.3 VDC Approach –250 to +250 mVDC Angular –150 to +150 mVDC 750 mVDC 1.3 VDC High Level Configuration Enroute –2.78 to +2.78 VDC 1476 ft. –2 to +2 VDC 3.5 VDC 8.12 VDC Terminal –3.33 to +3.33 VDC 492 ft. –2 to +2 VDC 3.5 VDC 8.12 VDC 0.3 NM –3.33 to +3.33 VDC 200 ft. –2 to +2 VDC 3.5 VDC 8.12 VDC Approach –3.33 to +3.33 VDC Angular –2 to +2 VDC 3.5 VDC 8.12 VDC The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 321 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual E. Discrete Outputs All discrete outputs, except the NAV Flag and Vertical Flag, are of two types: Ground/Open and 28VDC/Open. Both the Ground/Open and 28VDC/Open discrete outputs may be either configurable or non-configurable. Non-configurable discretes must be assigned to a specific pin. Configurable discretes may be assigned to any one of a specific set of pins. (1) Non-Configurable Discretes Output Description Plug/Pin Digital Valid Message Annunciator Output MP 5G MP 13A Nav Valid MP 3H MP 3K MP 3J Nav Flag Pitch Command Valid Steering Valid Vertical Valid Vertical Flag Level of Service 1 Level of Service 2 Level of Service 3 WAAS Cross-channel Fail The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. MP 1J MP 1K MP 11C MP 7H MP 7K MP 7J TP 4A TP 4B TP 4C TP 4E Characteristics 28 VDC / Open (28 VDC = Valid) Ground / Open (GND = Message, 350mA is the maximum allowable load) 28 VDC / Open (28 VDC = Valid) 800 mV to 1.2 V (Circuitry in the motherboard converts the 28V to a voltage within the specified range to set the flag.) 28 VDC / Open (28 VDC = Valid) 28 VDC / Open (28 VDC = Valid) 28 VDC / Open (28 VDC = Valid) 800 mV to 1.2 V (Circuitry in the motherboard converts the 28V to a voltage within the specified range to set the flag.) Ground / Open Ground / Open Ground / Open Ground / Open 34-60-51 Page 322 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (2) Configurable Discretes Discrete Output 1 MP 6K Discrete Output 2 MP 13B Discrete Output 3 MP 13C Discrete Output 4 MP 13D Discrete Output 5 MP 13E Discrete Output 6 MP 7A Discrete Output 7 MP 7B Discrete Output 8 MP 6C Discrete Output 9 28 V MP 13F The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. Ground / Open (Configurable) See System Data Installation for list of discrete inputs. Ground / Open (Configurable) See System Data Installation for list of discrete inputs. Ground / Open (Configurable) See System Data Installation for list of discrete inputs. Ground / Open (Configurable) See System Data Installation for list of discrete inputs. Ground / Open (Configurable) See System Data Installation for list of discrete inputs. Ground / Open(Configurable) See System Data Installation for list of discrete inputs. Ground / Open (Configurable) See System Data Installation for list of discrete inputs. Ground / Open (Configurable) See System Data Installation for list of discrete inputs. 28 VDC / Open (Configurable) See System Data Installation for list of discrete inputs. 34-60-51 Page 323 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual F. Digital Outputs The following tables show a list of the configurable CSDB and ARINC 429 outputs along with the ports to which they default when the configuration module is initialized. Each of these ports is configurable. Some sensors are restricted to certain output ports. The allowable ARINC port assignments and their pin numbers are found in the WAAS FMS Configuration Manual, Report No. 34-61-01. (1) CSDB Output Ports Output Description CSDB TX 1 CSDB TX 2 (2) Plug/Pin MP 2J MP 2K MP 10A MP 10B Characteristics (A) (B) (A) (B) ASCB Outputs (SCN 1000.5/1100.5 and later) The ASCB board provides the FMS with an interface to the ASCB Version A data bus developed by Honeywell and supplement the ARINC, CSDB, and analog interfaces of the FMS. Input Description ASCB Discrete Out 1 ASCB Discrete Out 2 ASCB Discrete Out 3 ASCB Discrete Out 4 NOTE: Plug/Pin MP 5E MP 5A MP 5C MP 1J Characteristics ASCB Discrete Out 1 (28 V/OPN) ASCB Discrete Out 2 (28V/OPN Spare) ASCB Discrete Out 3 (GND/OPN Spare) ASCB Discrete Out 4 (GND/OPN) Assuming NCU #1 is to be configured for TX/RX on Left ASCB bus, ASCB A Port (OnSide) is connected to the Left ASCB Bus and ASCB B Port (Off-Side) is connected to the Right ASCB Bus. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 324 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (3) ARINC Output Ports The following table shows a list of the configurable ARINC 429 outputs along with the ports to which they default when the configuration module is initialized. Each of these ports is configurable. Some sensors are restricted to certain output ports. The allowable ARINC port assignments and their pin numbers are found in the WAAS FMS Configuration Manual, Report No. 34-61-01. Port Plug/Pin Port 0A MP-4A (A) ARINC 429 HS MP-4B (B) MP-12A (A) MP-12B (B) MP-4E (A) ARINC 571 MP-4F (B) MP-4J (A) ARINC 429 LS MP-4K (B) MP-12J (A) MP-12K (B) MP-10C (A) MP-10D (B) MP-12E (A) ARINC 429 Crossfill HS Port 0B Port 1 Port 2A Port 2B Port 2C Port 3 Port 4A Port 4B Port 5 Port 6A Port 6B Port 7 WAAS Port 0 WAAS Port 1A WAAS Port 1B Default Configuration MP-12F (B) TP-13A (A) ARINC 429 Tune LS TP-13B (B) TP-15C (A) TP-15D (B) TP-13E (A) TP-13F (B) TP-14C (A) TP-14D (B) TP-15G (A) TP-15H (B) TP-14J (A) TP-14K (B) TP-10J (A) WAAS Crosschannel Transmit TP-10K (B) MP-10J (A) WAAS Transmit ARINC 743A Data MP-10K (B) MP-4C (A) WAAS Transmit ARINC 743A Data MP-4D (B) The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Notes 1, 2, 3, 4, 6 5 5 5 Page 325 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual NOTES: 1. (SCN 1000.2/1100.2 and earlier) In dual WAAS FMS Installations, Transmit Port #2 must be configured for one of the following bus types: 429 HS, 429 LS, HS429 MOD 1, HS429 MOD 2, 429 LS GPS/XPDR or UNS HS429-1 to set up the speed for the WAAS OFFSIDE RECEIVE. 2. (SCN 1000.3/1100.3 and later) In dual WAAS FMS Installations, Transmit Port #2 must be configured for one of the following bus types: 429 HS, 429 LS, HS429 MOD 2, HS429 MOD 3, HS429 MOD 4, GPS XPDR LS, GPS XPDR HS or UNS HS429-1 to set up the speed for the WAAS OFFSIDE RECEIVE. 3. (SCN 1000.2/1100.2 and earlier) In single WAAS FMS with LP/LPV Monitor Installations, Transmit Port #2 must be configured for one of the following bus types: 429 HS, 429 LS, HS429 MOD 1, HS429 MOD 2, 429 LS GPS/XPDR or UNS HS429-1 to set up the speed for the WAAS OFFSIDE RECEIVE of the internal WAAS subsystem and the LP/LPV Monitor. 4. (SCN 1000.3/1100.3 and later) In single WAAS FMS with LP/LPV Monitor Installations, Transmit Port #2 must be configured for one of the following bus types: 429 HS, 429 LS, HS429 MOD 2, HS429 MOD 3, HS429 MOD 4, GPS XPDR LS, GPS XPDR HS or UNS HS429-1 to set up the speed for the WAAS OFFSIDE RECEIVE of the internal WAAS subsystem and the LP/LPV Monitor. 5. Not a configurable port. 6. (SCN 1000.3/1100.3 and later) Configuring any of the following bus types will cause manual de-selection of geostationary satellites to not be supported: HS429 MOD 2, HS429 MOD 3, UNS HS429-1, GPS XPDR LS and GPS XPDR HS. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 326 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual 3. Pin Assignment A. UNS-1Fw – All Digital (P/N 3192-XX-111102) (1) Pin Connector TP (Top Plug) Function Pin 1A NC 4G Function WAAS Discrete In XChannel Fail Monitor 1B NC 4H WAAS Discrete In XChannel LOS Monitor 1C NC 4J WAAS Discrete In XChannel Vertical Guidance Flag Monitor 1D NC 4K WAAS Discrete In XChannel Lateral Guidance Flag Monitor 1E NC 5A NC 1F NC 5B NC 1G NC 5C NC 1H NC 5D NC 1J NC 5E NC 1K NC 5F NC 2A WAAS XChannel Monitor (H) (Guidance Bus) 1 (WAAS RX Port 2) 5G NC 2B WAAS XChannel Monitor (L) (Guidance Bus) 1 (WAAS RX Port 2) 5H NC 2C WAAS XChannel Monitor (H) (Guidance Bus) 2 (WAAS RX Port 3) 5J NC 2D WAAS XChannel Monitor (L) (Guidance Bus) 2 (WAAS RX Port 3) 5K NC 2E NC 6A NC 2F NC 6B NC 2G WAAS XChannel Lateral Deviation (H) 6C NC 2H WAAS XChannel Lateral Deviation Return 6D NC 2J WAAS XChannel Vertical Deviation (H) 6E NC 2K WAAS XChannel Vertical Deviation Return 6F NC 3A NC 6G NC 3B NC 6H NC 3C NC 6J NC 3D NC 6K NC 3E NC 7A NC 3F NC 7B NC 3G NC 7C NC 3H NC 7D NC 3J NC 7E NC 3K NC 7F WAAS Monitor Return 4A WAAS Level of Service (LOS) 1 7G RS232 WAAS Monitor Transmit 4B WAAS Level of Service (LOS) 2 7H RS232 WAAS Monitor Receive 4C WAAS Level of Service (LOS) 3 7J NC 4D WAAS Discrete Out Spare #3 7K NC 4E WAAS Discrete Out XChannel Fail Output 8A NC 4F WAAS Discrete Out Spare #1 8B NC The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 327 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (1) Pin Connector TP (Top Plug) (continued) Function Pin Function 8C NC 12B NC 8D NC 12C NC 8E NC 12D NC 8F NC 12E NC 8G NC 12F Ethernet TX 0 (H) 8H NC 12G Ethernet TX 0 (L) 8J NC 12H Ethernet 0 Shield 8K NC 12J Ethernet RX 0 (H) 9A NC 12K Ethernet RX 0 (L) 9B NC 13A ARINC TX Port 4A (A) 9C NC 13B ARINC TX Port 4A (B) 9D NC 13C ARINC RX Port 8 (A) 9E NC 13D ARINC RX Port 8 (B) 9F NC 13E ARINC TX Port 5 (A) 9G NC 13F ARINC TX Port 5 (B) 9H NC 13G ARINC RX Port 9 (A) 9J NC 13H ARINC RX Port 9 (B) 9K NC 13J ARINC RX Port 10 (A) 10A WAAS Differential Timemark 1A 13K ARINC RX Port 10 (B) 10B WAAS Differential Timemark 1B 14A ARINC RX Port 11 (A) 10C ARINC RX Port 0 (A) 14B ARINC RX Port 11 (B) 10D ARINC RX Port 0 (B) 14C ARINC TX Port 6A (A) 10E NC 14D ARINC TX Port 6A (B) 10F NC 14E ARINC RX Port 12 (A) 10G NC 14F ARINC RX Port 12 (B) 10H NC 14G ARINC RX Port 13 (A) 10J WAAS ARINC TX Port 0 (A) 14H ARINC RX Port 13 (B) 10K WAAS ARINC TX Port 0 (B) 14J ARINC TX Port 7 (A) 11A NC 14K ARINC TX Port 7 (B) 11B NC 15A ARINC RX Port 14 (A) 11C NC 15B ARINC RX Port 14 (B) 11D NC 15C ARINC TX Port 4B (A) 11E NC 15D ARINC TX Port 4B (B) 11F NC 15E ARINC RX Port 15 (A) 11G NC 15F ARINC RX Port 15 (B) 11H NC 15G ARINC TX Port 6B (A) 11J NC 15H ARINC TX Port 6B (B) 11K NC 15J NC 12A NC 15K NC The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 328 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (2) Pin 1A 1B 1C 1D 1E 1F 1G 1H 1J 1K 2A 2B 2C 2D 2E 2F 2G 2H 2J 2K 3A 3B 3C 3D 3E 3F 3G 3H 3J 3K 4A 4B 4C 4D 4E 4F Connector MP (Middle Plug) Function NC NC NC NC NC NC NC NC NC NC CDU 1 RX (H) CDU 1 RX (L) CDU 2 RX (H) CDU 2 RX (L) CDU TX (H) CDU TX (L) CSDB RX Port 2 (A) CSDB RX Port 2 (B) CSDB TX Port 1 (A) CSDB TX Port 1 (B) NC NC NC NC NC NC NC NC NC NC ARINC TX Port 0A (A) ARINC TX Port 0A (B) WAAS TX Port 1B (A) ARINC 743A Data WAAS TX Port 1B (B) ARINC 743A Data ARINC TX Port 1 (A) ARINC TX Port 1 (B) The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. Pin 4G 4H 4J 4K 5A 5B 5C 5D 5E 5F 5G 5H 5J 5K 6A 6B 6C 6D 6E 6F 6G 6H 6J 6K 7A 7B 7C 7D 7E 7F 7G 7H 7J 7K 8A 8B Function ARINC RX Port 1 (A) ARINC RX Port 1 (B) ARINC TX Port 2A (A) ARINC TX Port 2A (B) NC NC NC NC NC NC NC NC NC NC Discrete In 7 (GND/Open) Discrete In 11 (GND/Open) Discrete Out 8 (GND/Open) NC Discrete In 8 (GND/Open) Discrete In 9 (GND/Open) Discrete In 1 (GND/Open) Discrete In 2 (GND/Open) Discrete In 3 (GND/Open) Discrete Out 1 (GND/Open) Discrete Out 6 (GND/Open) Discrete Out 7 (GND/Open) NC NC NC NC NC NC NC NC ARINC RX Port 4 (A) ARINC RX Port 4 (B) 34-60-51 Page 329 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (2) Pin 8C 8D 8E 8F 8G 8H 8J 8K 9A 9B 9C 9D 9E 9F 9G 9H 9J 9K 10A 10B 10C 10D 10E 10F 10G 10H 10J 10K 11A 11B 11C 11D 11E 11F 11G 11H 11J 11K 12A Connector MP (Middle Plug) (continued) Function ARINC RX Port 5 (A) ARINC RX Port 5 (B) ARINC RX Port 6 (A) ARINC RX Port 6 (B) ARINC RX Port 7 (A) ARINC RX Port 7 (B) NC NC Heading X Heading Y Heading Z Heading Reference (H) Heading Reference Return Heading Valid Input (28 V/Open) Heading Input True/Magnetic (28 V/Open) NC NC NC CSDB TX Port 2 (A) CSDB TX Port 2 (B) ARINC TX Port 2C (A) ARINC TX Port 2C (B) WAAS RX Port 0 (B) – Offside FMS WAAS RX Port 0 (A) – Offside FMS WAAS RX Port 1 (A) – XChannel RX WAAS RX Port 1 (B) – XChannel RX WAAS TX Port 1A (A) – ARINC 743A Data WAAS TX Port 1A (B) – ARINC 743A Data Roll Steering (H) Roll Steering (L) Steering Valid Discrete Autopilot Reference (H) Autopilot Reference (L) NC Discrete In 10 (28 V/Open) Discrete In 5 (GND/Open) FMS 2 Discrete Input FMS 3 Discrete Input ARINC TX Port 0B (A) The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. Pin 12B 12C 12D 12E 12F 12G 12H 12J 12K 13A 13B 13C 13D 13E 13F 13G 13H 13J 13K 14A 14B 14C 14D 14E 14F 14G 14H 14J 14K 15A 15B 15C 15D 15E 15F 15G 15H 15J 15K Function ARINC TX Port 0B (B) ARINC RX Port 2 (A) ARINC RX Port 2 (B) ARINC TX Port 3 (A) ARINC TX Port 3 (B) ARINC RX Port 3 (A) ARINC RX Port 3 (B) ARINC TX Port 2B (A) ARINC TX Port 2B (B) Message Annunciator (GND/Open) Discrete Out 2 (GND/Open) Discrete Out 3 (GND/Open) Discrete Out 4 (GND/Open) Discrete Out 5 (GND/Open) Discrete Out 9 (28 V/Open) Monitor Transmit Monitor Receive NC NC CSDB RX Port 3 (A) CSDB RX Port 3 (B) CSDB RX Port 1 (A) CSDB RX Port 1 (B) CSDB RX Port 4 (A) CSDB RX Port 4 (B) Configuration Module Ground Configuration Module VDC Configuration Module Data Clock Configuration Module Data I/O Fuel Flow 1 (H) Fuel Flow 1 (L) Fuel Flow 2 (H) Fuel Flow 2 (L) Fuel Flow 3 (H) Fuel Flow 3 (L) Fuel Flow 4 (H) Fuel Flow 4 (L) Discrete In 4 (GND/Open) Discrete In 6 (GND/Open) 34-60-51 Page 330 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (3) Pin 1 2 3 4 5 6 7 Connector BP (Bottom Plug) Function On Battery Annunciator Discrete Output 28 VDC Input 28 VDC Input Battery Power Control NC CDU 28 VDC Power FMS Chassis Ground The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. Pin 8 9 10 11 12 13 Function FMS DC Return NC NC CDU DC Power Return NC GPS Coax 34-60-51 Page 331 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual B. UNS-1Fw – ASCB Version A (P/N 3192-XX-111103) (1) Connector TP (Top Plug) Pin 1A 1B 1C NC NC NC Pin 4G 4H 4J 1D NC 4K 1E 1F 1G 1H 1J 1K 2A NC NC NC NC NC NC WAAS XChannel Monitor (H) (Guidance Bus) 1 (WAAS RX Port 2) WAAS XChannel Monitor (L) (Guidance Bus) 1 (WAAS RX Port 2) WAAS XChannel Monitor (H) (Guidance Bus) 2 (WAAS RX Port 3) WAAS XChannel Monitor (L) (Guidance Bus) 2 (WAAS RX Port 3) NC NC WAAS XChannel Lateral Deviation (H) WAAS XChannel Lateral Deviation Return WAAS XChannel Vertical Deviation (H) WAAS XChannel Vertical Deviation Return NC NC NC NC NC NC NC NC NC NC WAAS Level of Service (LOS) 1 WAAS Level of Service (LOS) 2 WAAS Level of Service (LOS) 3 WAAS Discrete Out Spare #3 WAAS Discrete Out XChannel Fail Output WAAS Discrete Out Spare #1 5A 5B 5C 5D 5E 5F 5G Function WAAS Discrete In XChannel Fail Monitor WAAS Discrete In XChannel LOS Monitor WAAS Discrete In XChannel Vertical Guidance Flag Monitor WAAS Discrete In XChannel Lateral Guidance Flag Monitor NC NC NC NC NC NC NC 5H NC 5J NC 5K NC 6A 6B 6C 6D 6E 6F 6G 6H 6J 6K 7A 7B 7C 7D 7E 7F 7G 7H 7J 7K 8A 8B NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC WAAS Monitor Return RS232 WAAS Monitor Transmit RS232 WAAS Monitor Receive NC NC NC NC 2B 2C 2D 2E 2F 2G 2H 2J 2K 3A 3B 3C 3D 3E 3F 3G 3H 3J 3K 4A 4B 4C 4D 4E 4F Function The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 332 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (1) Pin 8C 8D 8E 8F 8G 8H 8J 8K 9A 9B 9C 9D 9E 9F 9G 9H 9J 9K 10A 10B 10C 10D 10E 10F 10G 10H 10J 10K 11A 11B 11C 11D 11E 11F 11G 11H 11J 11K 12A Connector TP (Top Plug) (continued) Function NC NC NC NC NC NC NC NC ASCB Discrete In 1 ASCB Discrete In 2 ASCB Discrete In 8 ASCB Discrete In 3 NC ASCB Discrete In 4 NC NC NC NC WAAS Differential Timemark 1A WAAS Differential Timemark 1B ARINC RX Port 0 (A) ARINC RX Port 0 (B) NC NC NC NC WAAS ARINC TX Port 0 (A) WAAS ARINC TX Port 0 (B) NC NC NC NC NC NC NC NC NC NC NC The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. Pin 12B 12C 12D 12E 12F 12G 12H 12J 12K 13A 13B 13C 13D 13E 13F 13G 13H 13J 13K 14A 14B 14C 14D 14E 14F 14G 14H 14J 14K 15A 15B 15C 15D 15E 15F 15G 15H 15J 15K Function NC NC NC NC Ethernet TX 0 (H) Ethernet TX 0 (L) Ethernet 0 Shield Ethernet RX 0 (H) Ethernet RX 0 (L) ARINC TX Port 4A (A) ARINC TX Port 4A (B) ARINC RX Port 8 (A) ARINC RX Port 8 (B) ARINC TX Port 5 (A) ARINC TX Port 5 (B) ARINC RX Port 9 (A) ARINC RX Port 9 (B) ARINC RX Port 10 (A) ARINC RX Port 10 (B) ARINC RX Port 11 (A) ARINC RX Port 11 (B) ARINC TX Port 6A (A) ARINC TX Port 6A (B) ARINC RX Port 12 (A) ARINC RX Port 12 (B) ARINC RX Port 13 (A) ARINC RX Port 13 (B) ARINC TX Port 7 (A) ARINC TX Port 7 (B) ARINC RX Port 14 (A) ARINC RX Port 14 (B) ARINC TX Port 4B (A) ARINC TX Port 4B (B) ARINC RX Port 15 (A) ARINC RX Port 15 (B) ARINC TX Port 6B (A) ARINC TX Port 6B (B) NC NC 34-60-51 Page 333 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (2) Pin 1A 1B 1C 1D 1E 1F 1G 1H 1J 1K 2A 2B 2C 2D 2E 2F 2G 2H 2J 2K 3A 3B 3C 3D 3E 3F 3G 3H 3J 3K 4A 4B 4C 4D 4E 4F Connector MP (Middle Plug) Function ASCB A Data + ASCB A Data ASCB A Clock + NC NC NC ASCB B Clock + ASCB B Clock ASCB Discrete Out 4 (GND/Open Spare) NC CDU 1 RX (H) CDU 1 RX (L) CDU 2 RX (H) CDU 2 RX (L) CDU TX (H) CDU TX (L) CSDB RX Port 2 (A) CSDB RX Port 2 (B) CSDB TX Port 1 (A) CSDB TX Port 1 (B) ASCB Discrete In 5 ASCB Discrete In 6 ASCB A Clock NC NC NC NC NC NC NC ARINC TX Port 0A (A) ARINC TX Port 0A (B) WAAS TX Port 1B (A) ARINC 743A Data WAAS TX Port 1B (B) ARINC 743A Data ARINC TX Port 1 (A) ARINC TX Port 1 (B) The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. Pin Function 4G 4H 4J 4K 5A 5B 5C 5D 5E 5F 5G 5H 5J 5K 6A 6B 6C 6D 6E 6F 6G 6H 6J 6K 7A 7B 7C 7D 7E 7F 7G 7H 7J 7K 8A 8B ARINC RX Port 1 (A) ARINC RX Port 1 (B) ARINC TX Port 2A (A) ARINC TX Port 2A (B) ASCB Discrete Out 2 (28 VDC/Open Spare) NC ASCB Discrete Out 3 (GND/Open Spare) NC ASCB Discrete Out 1 (28 VDC/Open) NC ASCB B Data + NC ASCB Discrete In 7 ASCB B Data Discrete In 7 (GND/Open) Discrete In 11 (GND/Open) Discrete Out 8 (GND/Open) NC Discrete In 8 (GND/Open) Discrete In 9 (GND/Open) Discrete In 1 (GND/Open) Discrete In 2 (GND/Open) Discrete In 3 (GND/Open) Discrete Out 1 (GND/Open) Discrete Out 6 (GND/Open) Discrete Out 7 (GND/Open) NC NC NC NC NC NC NC NC ARINC RX Port 4 (A) ARINC RX Port 4 (B) 34-60-51 Page 334 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (2) Pin 8C 8D 8E 8F 8G 8H 8J 8K 9A 9B 9C 9D 9E 9F 9G 9H 9J 9K 10A 10B 10C 10D 10E 10F 10G 10H 10J 10K 11A 11B 11C 11D 11E 11F 11G 11H 11J 11K 12A Connector MP (Middle Plug) (continued) Function ARINC RX Port 5 (A) ARINC RX Port 5 (B) ARINC RX Port 6 (A) ARINC RX Port 6 (B) ARINC RX Port 7 (A) ARINC RX Port 7 (B) NC NC Heading X Heading Y Heading Z Heading Reference (H) Heading Reference Return Heading Valid Input (28 V/Open) Heading Input True/Magnetic (28 V/Open) NC NC NC CSDB TX Port 2 (A) CSDB TX Port 2 (B) ARINC TX Port 2C (A) ARINC TX Port 2C (B) WAAS RX Port 0 (B) – Offside FMS WAAS RX Port 0 (A) – Offside FMS WAAS RX Port 1 (A) – XChannel RX WAAS RX Port 1 (B) – XChannel RX WAAS TX Port 1A (A) – ARINC 743A Data WAAS TX Port 1A (B) – ARINC 743A Data Roll Steering (H) Roll Steering (L) Steering Valid Discrete Autopilot Reference (H) Autopilot Reference (L) NC Discrete In 10 (28 V/Open) Discrete In 5 (GND/Open) FMS 2 Discrete Input FMS 3 Discrete Input ARINC TX Port 0B (A) The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. Pin 12B 12C 12D 12E 12F 12G 12H 12J 12K 13A 13B 13C 13D 13E 13F 13G 13H 13J 13K 14A 14B 14C 14D 14E 14F 14G 14H 14J 14K 15A 15B 15C 15D 15E 15F 15G 15H 15J 15K Function ARINC TX Port 0B (B) ARINC RX Port 2 (A) ARINC RX Port 2 (B) ARINC TX Port 3 (A) ARINC TX Port 3 (B) ARINC RX Port 3 (A) ARINC RX Port 3 (B) ARINC TX Port 2B (A) ARINC TX Port 2B (B) Message Annunciator (GND/Open) Discrete Out 2 (GND/Open) Discrete Out 3 (GND/Open) Discrete Out 4 (GND/Open) Discrete Out 5 (GND/Open) Discrete Out 9 (28 V/Open) Monitor Transmit Monitor Receive NC NC CSDB RX Port 3 (A) CSDB RX Port 3 (B) CSDB RX Port 1 (A) CSDB RX Port 1 (B) CSDB RX Port 4 (A) CSDB RX Port 4 (B) Configuration Module Ground Configuration Module VDC Configuration Module Data Clock Configuration Module Data I/O Fuel Flow 1 (H) Fuel Flow 1 (L) Fuel Flow 2 (H) Fuel Flow 2 (L) Fuel Flow 3 (H) Fuel Flow 3 (L) Fuel Flow 4 (H) Fuel Flow 4 (L) Discrete In 4 (GND/Open) Discrete In 6 (GND/Open) 34-60-51 Page 335 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (3) Pin 1 2 3 4 5 6 7 Connector BP (Bottom Plug) Function On Battery Annunciator Discrete Output 28 VDC Input 28 VDC Input Battery Power Control NC CDU 28 VDC Power FMS Chassis Ground The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. Pin 8 9 10 11 12 13 Function FMS DC Return NC NC CDU DC Power Return NC GPS Coax 34-60-51 Page 336 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual C. UNS-1Fw – Analog (P/N 3192-XX-111106) (1) Connector TP (Top Plug) Pin 1A 1B 1C Function Altitude/Attitude Reference (H) Altitude/Attitude Reference Return NC Pin 4G 4H 4J 1D Altitude Fine/Pitch Synchro X 4K 1E 1F 1G 1H 1J 1K 2A Altitude Fine/Pitch Synchro Y Altitude Fine/Pitch Synchro Z NC Altitude Coarse/Roll Synchro X Altitude Coarse/Roll Synchro Y Altitude Coarse/Roll Synchro Z WAAS XChannel Monitor (H) (Guidance Bus) 1 (WAAS RX Port 2) WAAS XChannel Monitor (L) (Guidance Bus) 1 (WAAS RX Port 2) WAAS XChannel Monitor (H) (Guidance Bus) 2 (WAAS RX Port 3) WAAS XChannel Monitor (L) (Guidance Bus) 2 (WAAS RX Port 3) NC NC WAAS XChannel Lateral Deviation Monitor (H) WAAS XChannel Lateral Deviation Monitor Return WAAS XChannel Vertical Deviation Monitor (H) WAAS XChannel Vertical Deviation Monitor Return TAS Reference Voltage TAS Reference Return TAS DC Voltage NC SAT Reference Voltage SAT Reference Return SAT DC Voltage NC Altitude/Attitude Valid Discrete (28 V/Open) Altitude Valid Discrete Return WAAS Level of Service (LOS) 1 WAAS Level of Service (LOS) 2 WAAS Level of Service (LOS) 3 WAAS Discrete Out Spare #3 WAAS Discrete Out XChannel Fail Output WAAS Discrete Out Spare #1 5A 5B 5C 5D 5E 5F 5G Function WAAS Discrete In XChannel Fail Monitor WAAS Discrete In XChannel LOS Monitor WAAS Discrete In XChannel Vertical Guidance Flag Monitor WAAS Discrete In XChannel Lateral Guidance Flag Monitor TAS Valid Discrete (28 V/Open) NC NC NC SAT Valid Discrete (28 V/Open) NC NC 5H NC 5J NC 5K NC 6A 6B 6C NC NC NC 6D NC 6E NC 6F NC 6G 6H 6J 6K 7A 7B 7C 7D 7E 7F 7G 7H 7J 7K NC NC NC NC NC NC NC NC NC WAAS Monitor Return RS232 WAAS Monitor Transmit RS232 WAAS Monitor Receive NC NC 2B 2C 2D 2E 2F 2G 2H 2J 2K 3A 3B 3C 3D 3E 3F 3G 3H 3J 3K 4A 4B 4C 4D 4E 4F The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 337 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (1) Pin 8A 8B 8C 8D 8E 8F 8G 8H 8J 8K 9A 9B 9C 9D 9E 9F 9G 9H 9J 9K 10A 10B 10C 10D 10E 10F 10G 10H 10J 10K 11A 11B 11C 11D 11E 11F 11G 11H 11J 11K Connector TP (Top Plug) (continued) Function NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC NC WAAS Differential Timemark 1A WAAS Differential Timemark 1B ARINC RX Port 0 (A) ARINC RX Port 0 (B) NC NC WAAS TX Port 0 (A) WAAS TX Port 0 (B) NC NC NC NC NC NC The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. Pin 12A 12B 12C 12D 12E 12F 12G 12H 12J 12K 13A 13B 13C 13D 13E 13F 13G 13H 13J 13K 14A 14B 14C 14D 14E 14F 14G 14H 14J 14K 15A 15B 15C 15D 15E 15F 15G 15H 15J 15K Function NC NC NC NC NC Ethernet TX 0 (H) Ethernet TX 0 (L) Ethernet 0 Shield Ethernet RX 0 (H) Ethernet RX 0 (L) ARINC TX Port 4A (A) ARINC TX Port 4A (B) ARINC RX Port 8 (A) ARINC RX Port 8 (B) ARINC TX Port 5 (A) ARINC TX Port 5 (B) ARINC RX Port 9 (A) ARINC RX Port 9 (B) ARINC RX Port 10 (A) ARINC RX Port 10 (B) ARINC RX Port 11 (A) ARINC RX Port 11 (B) ARINC TX Port 6A (A) ARINC TX Port 6A (B) ARINC RX Port 12 (A) ARINC RX Port 12 (B) ARINC RX Port 13 (A) ARINC RX Port 13 (B) ARINC TX Port 7 (A) ARINC TX Port 7 (B) ARINC RX Port 14 (A) ARINC RX Port 14 (B) ARINC TX Port 4B (A) ARINC TX Port 4B (B) ARINC RX Port 15 (A) ARINC RX Port 15 (B) ARINC TX Port 6B (A) ARINC TX Port 6B (B) NC NC 34-60-51 Page 338 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (2) Pin Connector MP (Middle Plug) Function Pin 1A 1B 1C 1D 1E 1F 1G 1H 1J 1K 2A 2B 2C 2D 2E 2F 2G 2H 2J 2K 3A 3B 3C 3D 3E 3F 3G 3H 3J 3K 4A 4B Waypoint Bearing X Waypoint Bearing Y Waypoint Bearing Z NC Instrument Reference (H) Instrument Reference (L) Pitch Command (H) Pitch Command Return Pitch Valid Pitch Valid Return CDU 1 RX (H) CDU 1 RX (L) CDU 2 RX (H) CDU 2 RX (L) CDU TX (H) CDU TX (L) CSDB RX Port 2 (A) CSDB RX Port 2 (B) CSDB TX Port 1 (A) CSDB TX Port 1 (B) Desired Track X Desired Track Y Desired Track Z NC NC Lateral Deviation (H) Lateral Deviation Return Navigation Valid Discrete Out (28 V) Nav Valid Flag Nav Valid Return ARINC TX Port 0A (A) ARINC TX Port 0A (B) 4G 4H 4J 4K 5A 5B 5C 5D 5E 5F 5G 5H 5J 5K 6A 6B 6C 6D 6E 6F 6G 6H 6J 6K 7A 7B 7C 7D 7E 7F 7G 7H 4C 4D 4E 4F WAAS TX Port 1B (A) ARINC 743A Data WAAS TX Port 1B (B) ARINC 743A Data ARINC TX Port 1 (A) ARINC TX Port 1 (B) 7J 7K 8A 8B The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. Function ARINC RX Port 1 (A) ARINC RX Port 1 (B) ARINC TX Port 2A (A) ARINC TX Port 2A (B) ARINC 561 Sync (H) ARINC 561 Sync Return ARINC 561 Data (H) ARINC 561 Data Return ARINC 561 Clock (H) ARINC 561 Clock Return Digital Valid NC To/From (H) To/From Return Discrete In 7 (GND/Open) Discrete In 11 (GND/Open) Discrete Out 8 (GND/Open) NC Discrete In 8 (GND/Open) Discrete In 9 (GND/Open) Discrete In 1 (GND/Open) Discrete In 2 (GND/Open) Discrete In 3 (GND/Open) Discrete Out 1 (GND/Open) Discrete Out 6 (GND/Open) Discrete Out 7 (GND/Open) NC NC NC Vertical Deviation (H) Vertical Deviation Return Vertical Deviation Valid Discrete Out (28 V/Open) Vertical Flag Vertical Valid Return ARINC RX Port 4 (A) ARINC RX Port 4 (B) 34-60-51 Page 339 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (2) Pin 8C 8D 8E 8F 8G 8H 8J 8K 9A 9B 9C 9D 9E 9F 9G 9H 9J 9K 10A 10B 10C 10D 10E 10F 10G 10H 10J 10K 11A 11B 11C 11D 11E 11F 11G 11H 11J 11K 12A Connector MP (Middle Plug) (continued) Function ARINC RX Port 5 (A) ARINC RX Port 5 (B) ARINC RX Port 6 (A) ARINC RX Port 6 (B) ARINC RX Port 7 (A) ARINC RX Port 7 (B) Heading X Heading Y Heading Z Heading Reference (H) Heading Reference Return Heading Valid Input (28 V/Open) Heading Input True/Magnetic (28 V/Open) NC NC NC CSDB TX Port 2 (A) CSDB TX Port 2 (B) ARINC TX Port 2C (A) ARINC TX Port 2C (B) WAAS RX Port 0 (B) – Offside FMS WAAS RX Port 0 (A) – Offside FMS WAAS RX Port 1 (A) – XChannel RX WAAS RX Port 1 (B) – XChannel RX WAAS TX Port 1A (A) – ARINC 743A Data WAAS TX Port 1A (B) – ARINC 743A Data Roll Steering (H) Roll Steering (L) Steering Valid Discrete Autopilot Reference (H) Autopilot Reference (L) NC Discrete In 10 (28 V/Open) Discrete In 5 (GND/Open) FMS 2 Discrete Input FMS 3 Discrete Input ARINC TX Port 0B (A) The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. Pin 12B 12C 12D 12E 12F 12G 12H 12J 12K 13A 13B 13C 13D 13E 13F 13G 13H 13J 13K 14A 14B 14C 14D 14E 14F 14G 14H 14J 14K 15A 15B 15C 15D 15E 15F 15G 15H 15J 15K Function ARINC TX Port 0B (B) ARINC RX Port 2 (A) ARINC RX Port 2 (B) ARINC TX Port 3 (A) ARINC TX Port 3 (B) ARINC RX Port 3 (A) ARINC RX Port 3 (B) ARINC TX Port 2B (A) ARINC TX Port 2B (B) Message Annunciator Discrete Out 2 (GND/Open) Discrete Out 3 (GND/Open) Discrete Out 4 (GND/Open) Discrete Out 5 (GND/Open) Discrete Out 9 (28 V/Open) Monitor Transmit Monitor Receive NC NC CSDB RX Port 3 (A) CSDB RX Port 3 (B) CSDB RX Port 1 (A) CSDB RX Port 1 (B) CSDB RX Port 4 (A) CSDB RX Port 4 (B) Configuration Module Ground Configuration Module VDC Configuration Module Data Clock Configuration Module Data Fuel Flow 1 (H) Fuel Flow 1 (L) Fuel Flow 2 (H) Fuel Flow 2 (L) Fuel Flow 3 (H) Fuel Flow 3 (L) Fuel Flow 4 (H) Fuel Flow 4 (L) Discrete In 4 (GND/Open) Discrete In 6 (GND/Open) 34-60-51 Page 340 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (3) Pin 1 2 3 4 5 6 7 Connector BP (Bottom Plug) Function On Battery Annunciator Discrete Output 28 VDC Input 28 VDC Input Battery Power Control NC CDU 28 VDC Power FMS Chassis Ground The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. Pin 8 9 10 11 12 13 Function FMS DC Return NC NC CDU DC Power Return NC GPS Coax 34-60-51 Page 341 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual D. 5-Inch FPCDU Pin Identification Chart P/N 1018-X-XXX Pin A B C D E F G H J1 Connector Description Red Red Return Green Green Return Blue Blue return Sync Sync Return J2 Connector Pin Function CDU Receive Data (H) A CDU Receive Data (L) B CDU Receive Data Shield C D +28 VDC Keypad Lighting E Ground Keypad Lighting F +5 VDC or 5 VAC Keypad Lighting G CAUTION: Use 5 V or 28 V power for keypad lighting but not both. H CDU Transmit Data (H) J CDU Transmit Data (L) K CDU Transmit Data Shield L +28 VDC Power Input M N P R Pin A B C D E F G H Power +28 VDC Return Power On Control Output J3 Connector Description RS-422 Display Data TX (H) RS-422 Display Data TX (L) Ground RS-422 Display Data RX (H) RS-422 Display Data RX (L) Remote (Repeater) CDU when grounded Ground The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 342 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual E. 4-Inch FPCDU Pin Identification Chart (1) P/N 1117-XX, 1117-1-X0X (No Video or Graphics Capability) J1 Connector Pin Function CDU Receive Data (H) A CDU Receive Data (L) B CDU Receive Data Shield C #2 CDU Strap D +28 VDC Keypad Lighting E Ground Keypad Lighting F +5 VDC or 5 VAC Keypad Lighting G CAUTION: Use 5 V or 28 V power for keypad lighting but not both. H CDU Transmit Data (H) J CDU Transmit Data (L) K CDU Transmit Data Shield L +28 VDC Power Input M Ground N NOTE: Do not connect Pin N when using the 4-inch FPCDU with the UNS-1Fw Power +28 VDC Return P Power On Control Out R (2) 1117-2-X1X (With Video and Graphics Capability) J1 Connector Pin Function CDU Receive Data (H) A CDU Receive Data (L) B CDU Receive Data Shield C #2 CDU Strap D +28 VDC Keypad Lighting E Ground Keypad Lighting F +5 VDC or 5 VAC Keypad Lighting G CAUTION: Use 5 V or 28 V power for keypad lighting but not both. H CDU Transmit Data (H) J CDU Transmit Data (L) K CDU Transmit Data Shield L +28 VDC Power Input M Ground N NOTE: Do not connect Pin N when using the 4-inch FPCDU with the UNS-1Fw Power +28 VDC Return P Power On Control Output R The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 343 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual J2 Connector Description Pin A B C D E F G H Pin A B C D E F G H Red Input Red Return Green Input Green Return Blue Input Blue Return Sync Input Sync Return J3 Connector Description RS-422 Display Data TX (H) RS-422 Display Data TX (L) Ground RS-422 Display Data RX (H) RS-422 Display Data RX (L) Remote (Repeater) CDU when grounded Ground The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 344 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual F. LP/LPV Monitor – Pin Assignment (1) Pin 2A 2B 2C 2D 2G 2H 2J 2K 4D 4E 4F Connector – Top Plug Function WAAS XChannel Monitor (H) (Guidance Bus 1 WAAS XChannel Monitor (L) (Guidance Bus 1 WAAS XChannel Monitor (H) (Guidance Bus 1 WAAS XChannel Monitor (L) (Guidance Bus 2 WAAS XChannel Lateral Deviation (H) WAAS XChannel Lateral Deviation Return WAAS XChannel Vertical Deviation (H) WAAS XChannel Vertical Deviation Return WAAS Form Factor Select WAAS Discrete Out XChannel Fail Out WAAS SDI Select (2) Pin Function 4H WAAS Discrete In XChannel LOS Monitor 4J WAAS XChannel Vertical Guidance Flag Monitor WAAS XChannel Lateral Guidance Flag Monitor WAAS Monitor Return 4K 7F 7G 7H 10A 10B 10J 10K RS-232 WAAS Monitor Transmit RS-232 WAAS Monitor Receive WAAS Differential Timemark 1A WAAS Differential Timemark 1B ARINC 429 WAAS Transmit 0 (A) ARINC 429 WAAS Transmit 0 (B) Connector – Middle Plug Pin Function Pin Function 4C 4D 8J 8K 10E WAAS Transmit 1B (H) – ARINC 743A Data WAAS Transmit 1B (L) – ARINC 743A Data WAAS Flight Data Recording – Lab Only WAAS Flight Data Recording – Lab Only WAAS Receive 0 (L) – Offside FMS 10F 10G 10H 10J 10K WAAS Receive 0 (H) – Offside FMS WAAS Receive 1 (H) – X-Channel Receive WAAS Receive 1 (L) – X-Channel Receive WAAS Transmit 1A (H) – ARINC 743A Data WAAS Transmit 1A (L) – ARINC 743A Data Pin Function (3) Pin 1 2 3 4 Connector – Bottom Plug Function On Battery Annunciator Discrete Output +28 VDC Input +28 VDC Battery Input Power Control The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 7 8 13 FMS Chassis Ground FMS DC Power Return GPS Coax 34-60-51 Page 345 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual G. SSDTU – Pin Assignment (1) Pin A B C D E F G H Function EIA-485 (Side A) (FMS 485 A) EIA-485 (Side B) (FMS 485 B) Ethernet #1 RX (+) Ethernet #1 RX (-) Ethernet #1 Shield Ethernet #1 TX (+) Ethernet #1 TX (-) (2) Pin 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 Connector – J1 Pin J K L M N P R Function Chassis Ground SSDTU Power 28 VDC EIA-232 RX SSDTU Ground EIA-232 TX Connector – J2 Function Ethernet #3 RX (+) Ethernet #3 TX (+) Ethernet #2 RX (-) Ethernet #3 RX (-) Ethernet #3 TX (-) Ethernet #4 TX (-) Ethernet #4 TX (+) Ethernet #2 TX (-) Ethernet #2 RX (+) Ethernet #3 Shield Ethernet #4 RX (-) Ethernet #4 RX (+) Ethernet #2 TX (+) Ethernet #2 Shield Ethernet #4 Shield Ethernet #8 TX (-) Ethernet #8 RX (-) The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. Pin 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 Function Ethernet #8 Shield Ethernet #5 Shield Ethernet #5 TX (+) Ethernet #8 TX (+) Ethernet #8 RX (+) Ethernet #5 RX (+) Ethernet #5 TX (-) Ethernet #7 RX (+) Ethernet #7 RX (-) Ethernet #7 Shield Ethernet #6 Shield Ethernet #5 RX (-) Ethernet #7 TX (+) Ethernet #7 TX (-) Ethernet #6 TX (+) Ethernet #6 RX (+) Ethernet #6 TX (-) Ethernet #6 RX (-) 34-60-51 Page 346 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual H. DTU-100 – Pin Assignment (1) Pin A B C D E F G H Function RS-422 (A) RS-422 (B) Ethernet #0 RX (+) Ethernet #0 RX (-) Ethernet #0 Shield Ethernet #0 TX (+) Ethernet #0 TX (-) Option Pin 0 (2) Pin A B C D E F G H Connector – J1 Pin J K L M N P R Function Option Pin 1 Option Pin 2 (Not Used) Chassis Ground Power 28 VDC Aux Port RS-232 RX Power Return Aux Port RS-232 TX Connector – J2 Function Ethernet #1 RX (+) Ethernet #1 RX (-) Ethernet #1 TX (+) Ethernet #1 TX (-) Ethernet #2 RX (+) Ethernet #2 RX (-) Ethernet #2 TX (+) Ethernet #2 TX (-) The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. Pin J K L M N P R Function Ethernet #3 RX (+) Ethernet #3 RX (-) Ethernet #3 TX (+) Not Used Ethernet #3 TX (-) Ethernet Shield Not Used 34-60-51 Page 347 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual 4. UNS–1Fw Wiring The following wiring diagrams represent the basic FMS wiring, including ARINC, discrete, CSDB, analog and other inputs and outputs. The diagrams also include ancillary equipment such as the FPCDU and Data Transfer Unit. For all other interfaces such as radar and radios, refer to WAAS FMS Interface Manual, Report No. 34-60-53. Wiring diagrams apply to all versions of the UNS-1Fw unless otherwise noted on the wiring diagram. Reference to the Pin Identification Charts found later in this section will be helpful in understanding the differences between FMS versions. There is also an FMS Part Number Matrix in the Equipment Specifications section of this manual, which will further aid in understanding FMS differences. The information, drawings and wiring diagrams contained in this manual are intended as a reference for engineering planning only. The drawings and wiring diagrams contained herein do not represent any specific STC or Form 337 aircraft installation. It is the installer’s responsibility to compose installation drawings specific to the aircraft. This manual and the drawings contained herein may not be used as a substitute for an STC or Form 337 drawing package. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 348 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual A. UNS-1Fw All Configurations (1) Power and Configuration Module The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 349 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (2) Dual WAAS FMS – Analog Configuration (page 1 of 2) The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 350 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (3) Dual WAAS FMS – Analog Configuration (page 2 of 2) The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 351 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (4) Dual WAAS FMS – Digital Configuration (page 1 of 2) The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 352 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (5) Dual WAAS FMS – Digital Configuration (page 2 of 2) The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 353 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (6) Dual WAAS FMS – EFI-890R Digital Configuration The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 354 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (6) LP/LPV Monitor Power Installation The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 355 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (7) Single WAAS FMS Analog Configuration to LP/LPV Monitor The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 356 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (8) Single WAAS FMS Digital Configuration to LP/LPV Monitor The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 357 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (9) Single WAAS FMS Analog/Digital Configuration to LP/LPV Monitor (page 1 of 2) The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 358 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (10) Single WAAS FMS Analog/Digital Configuration to LP/LPV Monitor (page 2 of 2) The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 359 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (12) 4-Inch Flat Panel Display Control Unit (FPCDU) (without Video and Graphics) (P/N 1117-XX and 1117-1-X0X) The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 360 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (13) 4-Inch FPCDU with Video and Graphics Display (P/N 1117-2-X1X) The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 361 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (14) Dual 4-Inch FPCDUs (without Video and Graphics) (P/N 1117-XX and 1117-1-X0X) The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 362 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (15) Dual 4-Inch FPCDUs with Video and Graphics (P/N 1117-2-X1X) (page 1 of 2) The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 363 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (16) Dual 4-Inch FPCDUs with Video and Graphics (P/N 1117-2-X1X) (page 2 of 2) The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 364 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (17) Single 5-Inch FPCDUs (P/N 1018-X-XXX) The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 365 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (18) Dual 5-Inch FPCDUs (P/N 1018-X-XXX) (page 1 of 2) The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 366 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (19) Dual 5-Inch FPCDUs (P/N 1018-X-XXX) (page 2 of 2) The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 367 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (20) DTU-100 The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 368 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (21) Portable DTU-100 The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 369 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (22) SSDTU The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 370 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (23) SSDTU Installation and DTU-100 Retrofit The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 371 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (24) Portable SSDTU The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 372 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (25) Portable SSDTU (Portable DTU-100 Retrofit) The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 373 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (26) Fuel Flow and Roll Steering The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 374 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (27) Heading and Radio Tune The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 375 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (28) Analog Configuration (P/N 3192-XX-111106) The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 376 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (29) ARINC 429 Input Ports The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 377 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (30) ARINC 429 Output Ports The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 378 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (31) Discrete Inputs The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 379 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (32) Discrete Outputs The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 380 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (33) ASCB Version A The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 381 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual System Data Installation System data installation and system configuration instructions are contained in the WAAS FMS Configuration Manual. Applicable SCN SCN 1000.X/1100.X The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. Configuration Manual Report Number 34-61-01 34-60-51 Page 401 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual Maintenance, Checkout and Troubleshooting 1. Maintenance A. Flight Management System (FMS), P/N 3192-XX-11110X Do not schedule maintenance for the FMS. No maintenance is needed unless a problem is found. B. Configuration Module, P/N 31921 Do not schedule maintenance for the Configuration Module. No maintenance is needed unless a problem is found. C. Data Transfer Unit (DTU-100), P/N 1406-XX or 1407-XX Do not schedule maintenance for the DTU-100. No maintenance is needed unless a problem is found. D. Solid State Data Transfer Unit (SSDTU), P/N 1408-00-X or 1409-00-2 E. Do not schedule maintenance for the SSDTU. No maintenance is needed unless a problem is found. Control Display Unit (5-Inch FPCDU), P/N 1018-X-XXX Do not schedule maintenance for the CDU. No maintenance is needed unless a problem is found. F. Control Display Unit (4-Inch FPCDU), P/N 1117-XX or 1117-X-XXX Do not schedule maintenance for the CDU. No maintenance is needed unless a problem is found. G. LP/LPV Monitor, P/N 3116-5X-1110 Do not schedule maintenance for the LP/LPV Monitor. No maintenance is needed unless a problem is found. H. GPS Antenna, P/Ns 10708, 10709, 10710 Do not schedule maintenance for the SBAS/WAAS GPS Antenna. No maintenance is needed unless a problem is found. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 501 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual 2. Installation Checkout Use these procedures as necessary to approve the Universal Avionics WAAS/SBAS FMSs or WAAS/SBAS FMS and LP/LPV Monitor installations. Interfaces not included in the aircraft may be omitted. A. Ground Test Plan UNS-1( )w NCU System #1 System #2 or Monitor System #1 System #2 or Monitor System #1 System #2 or Monitor Part Number: Mod Status: FMC SCN: PAS SCN: Serial Number: GPS Antenna Part Number: Mod Status: Serial Number: Config Module Part Number: Mod Status: Serial Number: The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 502 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (1) Pre-Test Requirements Test: 1 Phase of Flight: Ground Test Operation: Pre -Test Requirements Function: Required equipment is installed and operational Remarks: Test Condition: Verify that all of the required equipment and compatible SCNs are installed and operational. (DO-187§ 3.4.1.1) Outcome: 1. FMSs (#1 and #2) 2. DTU 3. Pilot displays 4. Copilot displays 5. TAWS 6. Flight Director / Autopilot 7. Radio Altimeter 8. Air Data Computer(s) 9. VHF com systems 10. VHF NAV Receivers (#1 and #2). 11. ASU/EFB if installed 12. ACARS if installed 13. Attitude and heading sources Findings: Time: System #1: System #2: The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 503 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (2) Installation Test: 2 Phase of Flight: Ground Test Operation: Installation Function: General Operation Remarks: Test Condition: General Requirements (DO-229D §2.1.1.1), (DO-187§ 3.1.3) Outcome: 1. Airworthiness (DO-229D §2.1.1.1.1) 2. Design and manufacture of the airborne equipment shall support installation so as not to impair the airworthiness of the aircraft. 3. General Performance (DO-229D §2.1.1.1.2 ), (DO-187§ 3.4.1.2) The equipment shall perform its intended function. 4. Equipment Interfaces (DO-229D §2.1.1.1.4 ),(AC-20-138A §12.f.(2)), (DO187§ 3.4.1.3) 5. The interfaces with other aircraft equipment shall be designed such that, properly installed with other adequately designed equipment, normal or abnormal GPS/SBAS equipment operation shall not adversely affect the operation of other equipment. Nor shall normal or abnormal operation of other equipment adversely affect the GPS/SBAS equipment except as specifically allowed. Findings: Time: System #1: System #2: The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 504 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (3) Initialization and LPV Annunciation Test Test: 3 Phase of Flight: Ground Test Operation: Initialization & LPV Annunciation Test Function: FMS Power On Self Test Remarks: Test Condition: Power up and initialize the FMSs. Outcome: 1. Power up and initialize the FMSs. 2. Verify that each FMS has the current database. 3. On DATA Page 3/4 Verify that the FMS positions on each unit correspond to ramp position 4. Verify all data on DATA page 2/4 is accurate and reflects the configuration and sensors installed. Findings: Time: System #1: System #2: The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 505 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (4) Configuration Test: 4 Phase of Flight: Ground Test Operation: Configuration Function: Confirm Configuration Remarks: Test Condition: Configuration (AC-20-138A §18.a) Antenna Offset (DO-229D §2.2.4.3.3) Outcome: 1. Verify that the configurations comply with the configuration data for the syatem. Findings: Time: System #1: System #2: The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 506 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (5) DTU Test: 5 Phase of Flight: Ground Test Operation: DTU Function: DATABASE Remarks: Test Condition: 1. Load a navigation database into both FMSs from the DATA DISK MENU page. Outcome: 1. Verify proper operation and database loading. (DO-229D §2.2.1.5.1) & (DO-229D §2.2.1.5.2) Findings: Time: System #1: System #2: The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 507 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (6) Air Data Computer Test: 6 Phase of Flight: Ground Test Operation: Air Data Computer Function: Sensors Remarks: Test Condition: 1. On DATA page 2/4 verify that the ADC is deselected on each FMS. 2. Pull the ADC #1 and ADC #2 CBs. 3. Reset ADC #1 and ADC #2 CBs. Outcome: 2. Verify that the ADC INPUT FAIL message appears on each FMS. 3. Verify that the values are returned to normal. Findings: Time: System #1: System #2: The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 508 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (7) SBAS GPS Sensor Evaluation Test: 7 Phase of Flight: Ground Test Operation: SBAS GPS Sensor Evaluation Function: Sensors Remarks: Test Condition: 1. Inspect Data page 2/4 on FMS. 2. On #1 FMS deselect WAAS #1. 3. Reselect WAAS. 4. Repeat above steps for #2 FMS and by deselecting WAAS #2. Outcome: 1. On FMS, verify onside WAAS displays RNP/ANP factor. 2. On FMS, verify offside WAAS is in SBAS mode. 3. On offside FMS, verify WAAS displays RNP/ANP. 4. After reselection verify onside WAAS returns to normal. Findings: Time: System #1: System #2: The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 509 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (8) DME/VOR Tuning and Inhibiting Test: 8 Phase of Flight: Ground Test Operation: DME/VOR tuning and navaid inhibiting.(If applicable) Function: Sensors Remarks: Normally on the ground VOR and DME are automatically deselected. (Test set may be required) Test Condition: 1. Access the DME page via DATA page 2/4 on each FMS. 2. Select the DME sensor. 3. Access the NVD INHBT page. Input a DME station to inhibit. 4. Access the VOR page via DATA page 2/4 on both FMSs. 5. Tune the VHF NAV to a local VOR, and select the VOR sensor. 6. After test deselect both the DME and VOR sensors. 1. Verify that the page indicates the DME is deselected. 2. Verify reception of local DMEs. 3. Verify proper operation of the navaid inhibit function. 4. Verify that the page indicates the VOR is deselected. 5. Verify proper radial display. Outcome: Findings: Time: System #1: System #2: The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 510 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (9) Power Loss Test Test: 9 Phase of Flight: Ground Test Operation: Power Loss Test Function: FMS Remarks: Test Condition: 1. Locate and Pull each FMS circuit breaker. 2. Reset the circuit breakers within 5 seconds. 3. Pull each FMS circuit breaker. Reset the breakers after 20 seconds. Outcome: 1. Verify that the FMS loses power and that loss of navigation is output. (DO229D §2.1.1.13.2),(AC-20-138A §18.e), (DO-187§ 3.4.1.4) 2. Verify that the FMS returns to the page displayed prior to pulling the circuit breaker. Verify that SYNC is not lost. (If Configured for SYNC) 3. Verify that each FMS requires pressing the ON key to power up. Verify that the POWER FAIL page appears. 4. Verify that the FMS which was powered down properly Syncs to the other FMS. Findings: Time: System #1: System #2: The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 511 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (10) ACARS Test: 10 Phase of Flight: Ground Test Operation: ACARS (if installed) Function: ACARS Remarks: NOTE: This test point can be deferred to flight if unable to accomplish on the ground. Test Condition: 1. Upload text weather 2. Upload graphics weather (if available). 3. Send text messaging. Outcome: Verify that each FMS can send and receive ACARS messages over all networks configured. Findings: Time: System #1: System #2: The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 512 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (11) TAWS Control Test: 11 Phase of Flight: Ground Test Operation: TAWS Control (If configured) Function: TAWS Remarks: Test Condition: 1. On the DATA TAWS MAINT page engage the test modes. 4. Add several altitudes to waypoints in the lateral flight plan. Outcome: 1. Verify that the MAINT functions operate normally. 2. Verify line select keys for test functions operate normally. 3. Verify that the TAWS display on the specified display is as expected. 4. Verify the TAWS profile view accurately depicts intermediate crossing waypoints. Findings: Time: System #1: System #2: The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 513 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (12) Overall Evaluation of Pilot Interface Test: 12 Phase of Flight: Ground Test Operation: Overall evaluation of Pilot Interface. Function: General Operation Remarks: Test Condition: Verify the following items: Outcome: Annunciators (DO-229D §2.2.1.1.5.1) 1. Brightness is controllable. 2. Capability to test external Annunciators. Findings: Time: System #1: System #2: The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 514 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual B. Flight Test Plan The following should be considered when the Universal Avionics WAAS/SBAS FMS with LPV approach capability enabled is interfaced with the Flight Guidance System. In a new WAAS/SBAS FMS installation or when upgrading an existing FMS to a WAAS/SBAS FMS with LPV approach capability enabled, it is the applicant’s responsibility to evaluate the equipment when interfaced with a Flight Guidance System (FGS) through the use of properly authorized Systems and Equipment, Flight Test, or Flight Analyst DER. The objective is to ensure that the WAAS/SBAS FMS equipment interface is compatible with the aircraft. The Systems and Equipment, Flight Test, or Flight Analyst DER should evaluate the effects when the FGS de-gains during an LPV approach. Some FGS use a radio altimeter input, and will use glide slope capture and passage over the middle marker beacon to reduce the gain if the radio altimeter is failed. Certain FGS depend upon such inputs to enable the "glideslope extension" function to reduce "porpoising" or aerodynamic instability when coupled to a glideslope signal during the final approach phase. WAAS/SBAS FMS equipment designs do not provide such signals UNS-1( )w NCU System #1 System #2 or Monitor System #1 System #2 or Monitor System #1 System #2 or Monitor Part Number: Mod Status: FMC SCN: PAS SCN: Serial Number: GPS Antenna Part Number: Mod Status: Serial Number: Config Module Part Number: Mod Status: Serial Number: The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 515 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (1) Pre-Flight – Required Documents On-Board Test: 1 Phase of Flight: Before Engine Start Operation: Pre-Flight Function: Required Documents on Board Remarks: Test Condition: Check for proper documentation aboard aircraft. Outcome: 1. Registration Airworthiness Certificate 2. Current Weight and Balance 3. Required Flight Manuals and Supplements 4. Aircraft Flight Log 5. Aircraft Open Discrepancies 6. Aircraft Status Checked R&D/Show Compliance/Market Survey Findings: Time: System #1: System #2: The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 516 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (2) Pre-Flight - Briefing Test: 2 Phase of Flight: Before Engine Start Operation: Pre-Flight Function: Briefing Remarks: Test Condition: Brief the flight test Outcome: 1. Review Flight Test Requirements 2. Review any limitations 3. Brief the purpose of the test 4. Brief the intended route of flight 5. Brief TFRs 6. Brief weather Findings: Time: System #1: System #2: The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 517 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (3) Pre-Test Requirements – Required Equipment is Installed and Operational Test: 3 Phase of Flight: Before Engine Start Operation: Pre-Test Requirements Function: Required equipment is installed and operational Remarks: Test Condition: Verify that all of the required equipment and compatible SCNs are installed and operational. (DO-187§ 3.3.2) Outcome: 1. FMSs (#1 and #2) 2. DTU 3. Pilot displays 4. Copilot displays 5. TAWS 6. Flight Director / Autopilot 7. Radio Altimeter 8. Air Data Computer(s) 9. VHF com systems 10. VHF NAV Receivers (#1 and #2). 11. ASU/EFB if installed 12. ACARS if installed 13. Attitude and heading sources Findings: Time: System #1: System #2: The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 518 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (4) All – Flight Guidance Interface Test: 4 Phase of Flight: Before Engine Start/Duration of flight Operation: All Function: Flight Guidance Interface Remarks: Test Condition: During the course of the flight test observe and verify that the interface between the FMS and flight guidance does not alter the cockpit design philosophy or intended function of an FGS mode, switch or annunciation. (AC 20-138A §18.g),(AC 20-138A §23.b.(4)) Outcome: 1. Verify that the FMS or the FGS keeps the aircraft within the approved operational envelope. (AC 20-138A §18.g.(2)) 2. Verify that a positive, continuous and unambiguous indication is provided of the FGS modes actually in operation. (AC 20-138A §18.g.(3)) 3. Verify that there is consistent annunciation of engage/disengage timing of the FGS. (AC 20-138A §18.g.(4)) 4. Verify that those aircraft that have incorporated bank angle limiting, consideration should be given to whether the GNSS equipment is defining a path that cannot be flown. (AC 20-138A §18.g.(7)) Findings: Time: System #1: System #2: The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 519 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (5) All – Crew Workload Test: 5 Phase of Flight: Before Engine Start/During flight Operation: All Function: Crew Workload Remarks: Test Condition: An analysis of crew workload when operating the GNSS equipment in association with other piloting requirements should be conducted during all phases of flight, including those non-normal procedures that can be evaluated in flight. (AC 20-138A §23.b.(8)) Outcome: Before Engine Start/During flight Findings: Time: System #1: System #2: The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 520 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (6) Initialization and LPV Annunciation Test – FMS Power On Self-Test Test: 6 Phase of Flight: After Engine Start Operation: Initialization & LPV Annunciation Test Function: FMS Power On Self Test Remarks: Test Condition: 1. Power up and initialize both FMSs. 2. Enter information on Fuel pages as needed on only one FMS. 3. Enter a flight plan with the a SID and make the appropriate entries on the FPL SUMMARY page. Outcome: 1. Power up and initialize both FMSs. 2. Verify that both FMSs pass all items on the self test page. 3. Verify position matches the aircraft . Verify that the time and date are correct. 4. Accept the position on FMS #1 and FMS #2 and verify that the reverse video “I” disappears on both FMSs for SYNC operation. 5. Verify that FMS #1 and #2 have the current database. 6. Verify all data on DATA page 2/4 is accurate and reflects the configuration and sensors installed. 7. Verify data on Fuel Pages 1 through 5 are correct. Verify that all fuel data SYNC across. 8. Verify all data on FMS #2. 9. On Sensor page, verify WAAS1 Selected, WAAS2 “SBAS”" 10. Verify FMS #2 data was transferred from FMS #1. either by SYNC or XFILL Findings: Time: System #1: System #2: The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 521 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (7) Fly the Assigned SID – Take-off and SID Test: 7 Phase of Flight: Departure Operation: Fly the assigned SID Function: TAKE-OFF & SID Remarks: Approach scaling on first leg of Missed Approach and on the first leg of a SID Test Condition: Take off and fly the legs of the SID. (DO-187§ 3.4.2.3.c), (DO-187§ 3.4.2.3.b) Outcome: 1. Verify proper leg sequencing (DO-229D §2.2.1.2.4) with turn anticipation. (AC 20-138A §23.b.(2)),(AC 20-138A §23.b.(4).(ii)) 2. After takeoff verify ADC, DME, and VOR selected 3. Verify the data on NAV page 1/3. 4. Verify proper navigation of this procedure. Findings: Time: System #1: System #2: The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 522 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (8) Antenna Placement – Antenna Shadowing Test: 9 Phase of Flight: Enroute Operation: Antenna placement Function: Airframe Shadowing Remarks: Test Condition: 1. Perform 30 degree bank turns both left and right. 2. On the GPS STATUS page monitor the satellite health. Outcome: 1. Verify the airborne system receives differential SBAS correction. 2. INTEG should remain in SBAS throughout the entire maneuver. (AC 20138A §23.a.) Findings: Time: System #1: System #2: The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 523 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (9) Manual Leg Changes – NAV Test: 10 Phase of Flight: Enroute Operation: Manual Leg Changes Function: NAV Remarks: Test Condition: From NAV page 1/3, perform a manual leg change. Outcome: 1. Verify proper interception of new active NAV leg 2. Verify the data on NAV page 1/2. 3. Verify proper indications on EFIS consistent with NAV page 1/3. Findings: Time: System #1: System #2: The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 524 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (10) SXTK Test: 11 Phase of Flight: Enroute Operation: SXTK Function: SXTK Remarks: Test Condition: 1. Perform a SXTK. 3. Cancel SXTK Outcome: 1. Verify that SXTK mode is allowed. 2. Verify that it is correct and reasonable. 3. Verify that up to a 45 degree intercept is flown to the new offset course. 4. Verify that non-numeric cross-track deviation is readable and discernable. (AC 20-138A §13.b.(5)) 5. Verify that SXTK cancels and the aircraft returns to the original course via up to a 45 degree intercept. Findings: Time: System #1: System #2: The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 525 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (11) VTO and TOD Calculations – VNAV Test: 12 Phase of Flight: Enroute Operation: VTO & TOD Calculations Function: VNAV Remarks: Test Condition: 1. Go to VNAV PATH 1/2 and VTO to a FPL WPT. 2. Perform a DTO to a waypoint downstream of the VNAV WPT. 3. Press the VNAV key to access the PATH VNAV. Select a waypoint on the FPL with an altitude and finish the VNAV entries. 4. Go to VNAV PATH 1/1 and cancel VNAV Outcome: 1. Verify VNAV display is correct and recalculated. 3. Verify VNAV display goes invalid and proper message is pushed. 4. Verify computed TOD distance is reasonable. 5. Two minutes prior to TOD, verify "TOP OF DESCENT ALERT" message is displayed. 6. Upon reaching TOD, verify "VERTICAL WPT ALERT" message is displayed. 7. Verify that the VNAV indicator on the EFIS display becomes armed and will show proper deviation from and to the VPATH. 8. Verify VNAV display goes invalid and pushes an appropriate message. Findings: Time: System #1: System #2: The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 526 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (12) VHF and SATCOM Systems – ACARS Test: 13 Phase of Flight: Enroute Operation: VHF & SAT COM systems (if installed) Function: ACARS Remarks: Test Condition: 1. Request several VHF TEXT ONLY weather requests. 2. Request several weather maps. Outcome: 1. Verify weather message received. 2. NOTE: If this was accomplished in the ground test, this step can be skipped. Findings: Time: System #1: System #2: The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 527 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (13) Course TO or FROM Operations Test: 14 Phase of Flight: Enroute Operation: Course TO or FROM Operations Function: PVOR Remarks: Test Condition: Create a PVOR using one or more of the following functions, from or to any given WPT. 1. TRACK 2. INBOUND 3. OUTBOUND Outcome: 1. Verify that the NAV display is correct 2. Verify that the aircraft flys the proper direction. (AC 20-138A §23.b.(2)) 3. Cancel with the use of a DTO 4. Cancel with the use of a manual leg change Findings: Time: System #1: System #2: The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 528 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (14) Holding Patterns – HOLD Test: 15 Phase of Flight: Enroute Operation: Holding Patterns Function: HOLD Remarks: Test Condition: 1. Define a standard holding pattern at the TO waypoint using the current course as the inbound leg of the hold and Activate. (TSO-C115b a.(2),(ix)) or 2. Define a standard holding pattern at a TO waypoint using a course as the inbound leg of the hold so as to create a PARALLEL entry and Activate or 3. Define a standard holding pattern at a TO waypoint using a course as the inbound leg of the hold so as to create a TEAR DROP entry and Activate. Outcome: 1. Verify entry is as expected. 2. Verify aircraft enters and flies the holding pattern correctly. (AC 20-138A §23.b.(2)) 3. Verify the data on NAV page 1/3. Findings: Time: System #1: System #2: The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 529 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (15) SBAS Approach – Approach LOS as Required Test: 16 Phase of Flight: Approach Operation: SBAS Approach ( minimum 3 approaches) Function: Approach LOS as required Remarks: SBAS APPROACH Note: Verify that flight technical error (FTE) can be maintained at less than 1.0 NM for enroute and approach transition operating modes, and less than 0.25 NM for non-precision approaches, both with and without autopilot and/or flight director use. (AC 20-138A §23.b.(3)),(AC 20-138A §23.b.(4).(vi).(A)) Test Condition: 1. Assure that the correct LOS is selected and annunciated. 2. Continue the approach to the DA. 3. At the DA select TOGA and fly the missed approach procedure to the hold. Repeat This Test Condition as necessary. Outcome: 1. Verify that on the Approach Category Selection Page all available LOS are listed. 2. Verify that the correct LOS is annunciated on the CDU. (DO-229D §2.2.5.2.4),(AC 20-138A §19.c.(1)) 3. Verify that the LOS is annunciated on the proper external light or display. (DO-229D §2.2.1.6.1) 4. Verify that the aircraft properly follows the FMS HDG commands. (DO229D §2.2.3.2.1) 5. Verify that the aircraft properly intercepts the final approach course and flys the approach with both vertical and lateral guidance.(DO-229D §2.2.3.3.1) 6. Upon commencing the missed approach confirm that the scaling remains at 0.3 NM until the first turn point of the missed procedure.(DO-229D §2.2.3.7.1.2) 7. Verify that the CDU displays Missed Approach and leg sequences properly.(DO-229D §2.2.3.2.2) 8. Verify that the LPV annunciation extinguishes (if performing LPV LOS). 9. Verify that the aircraft enters and flys the hold as expected. (DO-229D §2.2.1.3.11) Findings: Time: System #1: System #2: The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 530 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (16) Non SBAS Approach – Additional Approaches Test: 17 Phase of Flight: Approach Operation: Non SBAS Approach (as req) Function: Additional approaches (GPS, NDB, VOR, VOR DME, ILS or LOC BC) as required for the specific installation. Remarks: SBAS APPROACH Note: Verify that flight technical error (FTE) can be maintained at less than 1.0 NM for enroute and approach transition operating modes, and less than 0.25 NM for non-precision approaches, both with and without autopilot and/or flight director use. (AC 20-138A §23.b.(3)),(AC 20-138A §23.b.(4).(vi).(A)) Test Condition: 1. Load the selected approach into the FMS 2. Continue the approach to the DA. 3. At the DA select TOGA and fly the missed approach procedure to the hold. Repeat This Test Condition as necessary. Outcome: Verify that the selected approach is execuited successfully Findings: Time: System #1: System #2: The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 531 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual 3. Operational Checkout You may make a copy of this section for recording the results of your checkout of the Flight Management System. Mark the PASS or FAIL spaces and fill in the blanks as appropriate. The contents of this section constitute the minimum Return to Service Procedures. You should perform these checks when you install a new or repaired component of the Flight Management System or related avionics equipment. You must know the aircraft’s navigational configuration before you checkout the Flight Management System. If the equipment fails any check, refer to the Troubleshooting section for corrective troubleshooting procedures. A. CDU / FMS Self-Test These functional and self-tests should be performed after replacement of the FMS and/or the 4-Inch or 5-Inch FPCDU. (1) Ensure that all system component connectors are connected and units are seated in mounting racks where applicable. For GPS tests the aircraft must be located outside the hangar and the antenna must have an unobstructed view of the sky. (2) Reset any circuit breakers that may have been opened for replacement. (3) Ensure that 28 VDC primary power is available on the bus supplying power to the FMS. (4) Ensure that 26 VAC power is available to supply reference voltages to the FMS. (5) Ensure that the Air Data Computer system and Air Data Converter (if installed) are powered up and functioning. (6) Ensure that the Heading source system supplying heading data to the FMS is powered up and valid. (7) Select FMS for display on the flight instruments. (8) Ensure that power for the FMS system annunciators is available and tested. (9) Turn on all sensors having independent power control such as IRS. (10) Push [ON/OFF DIM] on the CDU keypad. After a five-second warm-up, the self-test page will be displayed. Pass (11) The aircraft type appears on line two. Pass (12) Fail Fail Check that all items on the self-test page display “PASS”. Pass Fail Record failures: __________________________________________________________________________________ __________________________________________________________________________________ The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 532 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (13) Observe system annunciators during self-test. The following annunciators, which are remote from the CDU, should illuminate for about 45 seconds during FMS self-test. NOTE: This test is not supported on the EFI displays. (14) WPT ALERT (Waypoint Alert) Pass Fail N/A SXTK (Selected Crosstrack) Pass Fail N/A APPR (Approach) Pass Fail N/A HDG (Heading) Pass Fail N/A MSG (Message) Pass Fail N/A GPS INTEG (GPS Integrity) Pass Fail N/A LNAV Pass Fail N/A LNAV/VNAV Pass Fail N/A LP/LPV Pass Fail N/A During the self-tests, with the FMS selected for display on the HSI, verify the following indications: NOTE: This test is not supported on the EFI-890 displays. NAV FLAG – pulls out of view during self-test Pass Fail N/A TO/FR FLAG – indicates TO condition Pass Fail N/A COURSE POINTER – slews to 045 degrees Pass Fail N/A BEARING POINTER – slews to 135 degrees Pass Fail N/A LATERAL DEVIATION – moves 1 dot right (3.75 NM) Pass Fail N/A VERTICAL DEVIATION – moves 1 dot up (1600 ft.) Pass Fail N/A DISTANCE DISPLAY – shows 123.4 NM (or 123) Pass Fail N/A ROLL COMMAND – 10 degree right bank Pass Fail N/A NOTE: 1. Indications may differ with some equipment types and EFIS installations. 2. The terms Desired Track and Course Pointer are used interchangeably. 3. The terms Course Deviation Indicator (CDI) and Lateral Deviation Needle are used interchangeably. 4. The terms Glide Slope Needle and Vertical Deviation Needle are used interchangeably. Record any discrepancies: ____________________________________________________________________ ____________________________________________________________________ NOTE: After completion of self-tests, the CDU will display the copyright page followed by the Initialization page [INIT 1/1]. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 533 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (15) Push [MSG] to display any system messages. Verify that no “FAIL” messages or “DEMONSTRATION MODE” messages are displayed. “POSITION UNCERTAIN” is normal until the system has been initialized. If any fail messages are displayed, refer to the Messages Section in the Operator’s Manual for possible causes. Push [MSG] again to return to the INIT 1/1 page. Pass Fail (16) The latitude and longitude of the field should be displayed. Push ACCEPT line select key (LSK) [5L] or [ENTER] to initialize the position. The cursor will advance to the date field. (17) If the date is correct push [ENTER] or enter the date numbers (DDMMYY), then push [ENTER]. The cursor will advance to the UTC field. (18) If the time is correct, push [ENTER] or enter the time numbers (HHMM), then push [ENTER]. The cursor will advance to the ACCEPT line select location. Push ACCEPT, LSK [5L]. (19) Fill in the following blanks with information from the last two lines of the INIT 1/1 page: NAV DATABASE EXPIRES _______________________________________________ FMC VER _______________________________________________________________ NOTE: You may test the FMS with an expired database. (20) Push [DATA] four times to display DATA 4/4 page. Verify that the correct aircraft heading is displayed in the HDG data field. Pass Fail (21) Manually slew the heading off 10 degrees using the slave switch. Verify that the heading tracks correctly in both directions. Pass Fail N/A The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 534 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (22) Push [NEXT] to display DATA 1/4 page and push MAINT, LSK [5R] to display MAINT 1/1 page. From MAINT 1/1 push S/W VERS, LSK [5L] and observe the version identification of the various software installed on the system. The FMC version should match the version approved for the installation in the Airplane Flight Manual Supplement or other approved documentation. Record the software versions below. FMC ____________________ CDU ____________________ AUX ____________________ ANA ____________________ RRS ____________________ BSTRP ____________________ WAAS ____________________ ASCB ____________________ RTU ____________________ Pass (23) Fail Activate the panel lighting system that powers the CDU faceplate lighting for the FMS and verify proper operation. Pass The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. Fail 34-60-51 Page 535 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual B. CDU Keyboard Dimming and Display Offset BRIGHT® DIM® CANCEL® DISPLAY® OFF/STBY® Dimming Control Window (1) With any page displayed, push [ON/OFF DIM]. Verify the dimming control window is displayed on the right side of the active page with the options BRIGHT, LSK [1R], DIM, LSK [2R], CANCEL, LSK [3R], DISPLAY, LSK [4R] and OFF/STBY, LSK [5R]. Pass (2) Push and hold BRIGHT, LSK [1R], push and hold DIM, LSK [2R]. Verify that the display brightens and dims. Pass (3) Fail Fail Press DISPLAY, LSK [4R]. Verify the Display control window is displayed on the right side of the active page with the UP, DOWN, CANCEL and (optional) VIDEO, line select keys. Push and hold UP, LSK [1R], push and hold DOWN, LSK [2R]. Verify that the display moves up and down and can be adjusted to minimize parallax between the arrows and line select keys. Pass (4) C. Fail Push [ON/OFF DIM] or any mode key to return to the previous display. FMS Configuration Verification The FMS’s Configuration Module was programmed to allow the FMS to interface with the installed sensors, databases, etc. The CDU displays which aircraft hardware the Configuration Module is programmed for. To verify proper programming, check the Aircraft Configuration Data Sheets against the CDU configuration displays. Refer to the applicable Configuration Module Programming Procedures located in the WAAS FMS Configuration Manual for SCN 1000/1100 and subsequent, Report No. 34-60-XX. Pass Fail The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 536 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual D. Static Test Selected analog and discrete static tests are available while the aircraft is on the ground. NOTE: Static tests may not function correctly with some EFIS installations. Static tests are selected from the maintenance page and confirm data exchange synchronization between the aircraft and FMS during operation. Static tests verify two sources of output: analog and digital. (1) Analog Tests (P/N 3192-X0-111106) Analog tests are available only for FMSs equipped with an analog board. (a) From DATA 1/4 page, press the MAINT line select key and select STATIC TEST from MAINT 1/1. Then press ANALOG Line select Key. ANALOG 1/2 page is displayed. (b) Outputs to the flight guidance system are checked by pressing each line select key and verifying the proper display on the HSI or ADI. NOTE: Each option must be turned off by again pressing the line select key before a new option can be tested. ANALOG TESTS 1/2 (c) BEARING 90 Pass Fail N/A BEARING 45 Pass Fail N/A BEARING 135 Pass Fail N/A DSRTK 90 Pass Fail N/A DSRTK 45 Pass Fail N/A DSRTK 135 Pass Fail N/A XTK LEFT Pass Fail N/A XTK RIGHT Pass Fail N/A XTK CENTER Pass Fail N/A Press [NEXT] for ANALOG TESTS 2/2. ANALOG TESTS 2/2 (d) VERT UP Pass Fail N/A VERT DN Pass Fail N/A VERT CTR Pass Fail N/A TO Pass Fail N/A FROM Pass Fail N/A ROLL 20 DEG R Pass Fail N/A ROLL 20 DEG L Pass Fail N/A ROLL 0 DEG Pass Fail N/A Press RETURN for STATIC TEST 1/1. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 537 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (2) Discrete Tests (a) Press the DISCRETE line select key. DISCRETE 1/2 page is displayed. Each discrete is labeled as it was configured and can be tested. DISCRETE TST 1/2 (b) DISC OUT 1 Pass Fail N/A DISC OUT 2 Pass Fail N/A DISC OUT 3 Pass Fail N/A DISC OUT 4 Pass Fail N/A DISC OUT 5 Pass Fail N/A DISC OUT 6 Pass Fail N/A DISC OUT 7 Pass Fail N/A Press [NEXT] for DISCRETE TESTS 2/2. DISCRETE TST 2/2 DISC OUT 8 Pass Fail N/A DISC OUT 9 Pass Fail N/A DISC OUT 10 Pass Fail N/A DISC OUT 11 Pass Fail N/A The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 538 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual 4. Interface Checkout A. HSI Test (1) Press the DTO key then the LIST key. The LIST 1/10 page with VOR/PLT waypoints will be displayed. (2) Select any one of the waypoints by entering its corresponding number at the cursor and pressing ENTER twice. NAV 1/3 will be displayed. (3) Verify the desired track, bearing, distance and crosstrack (XTK) displayed on the HSI is the same as on the CDU. Pass Fail (4) On DATA page 2 press the ADC line select key to display ADC 1/1. (5) Press the line select key next to the TAS field and enter 100. Press ENTER. NOTE: You must deselect GPS and INS before entering TAS as 100. (6) On NAV 1/3 verify that the groundspeed displayed on the CDU matches that on the HSI (if the HSI supports this option). Pass B. N/A Winds Display (EFIS Only) (1) Display NAV 1/2. (2) Select Wind Display on the EFIS. Verify that the winds displayed on the HSI correspond to those on the CDU. Pass (3) C. Fail Fail N/A Turn the FMS off, then on before proceeding with additional tests. DME Interface Test Valid DME signals must be received by the DME or RRS system when testing the DME interface. Local DME station signals, if available on the ground, are adequate to verify operation of the interface. Otherwise a DME signal generator is required. Manual signal generators capable of providing DME test frequencies of 108.00 and 108.05 can also provide a lock-on and DME test of the DDC frequency of 108.20. Otherwise, a generator capable of manually tuning this frequency should be used. (1) If a local DME station can be received at the aircraft’s location, turn on and initialize the FMS to the local airport reference point identifier. If a DME signal cannot be received and a ramp tester is used, initialize the FMS to KDDC. (2) Select DATA page 2. Press the DME line select key to display DME 1/1 page. Verify that the STATUS field displays NORMAL (D). (3) Press the SELECT DME line select key. The (D) will extinguish and the DME identifiers will change on a four-second interval as the DME scan tunes to stations in the area. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 539 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (4) Press the MAN DME line select key to place the cursor over the data field. NOTE: Two MAN DME LSKs are displayed, select only one. (5) Press the LIST key to display a list of DME stations in the area. If local DME is used, choose the local DME from the list. If a signal generator is used and the FMS was initialized to KDDC, select DDC from the list and press ENTER. (6) Verify that the local distance to station or distance provided by the DME generator is displayed. Pass (7) Fail N/A If the FMS was initialized to KDDC, turn it off and then on again and initialize to the local airport reference point to prevent confusion. NOTE: The following steps apply to TACAN (RRS only). (8) Display DATA page 2 (if applicable). (9) Select TACAN Status page. (10) Check radial displayed on CDU for reasonableness. (11) Compare distance displayed on CDU with aircraft TACAN distance. Pass D. VOR Test (without RRS) (1) From DATA page 2 press the VOR line select key. (2) Verify that the frequency displayed in the FREQ field corresponds to the active frequency of the appropriate Nav Control Head. Pass E. Fail Fail N/A DTU-100 Test NOTE: 1. This test can only be performed on the ground. 2. It is necessary to have the correct Universal Avionics Database disk. (1) From DATA page 1 press the DISK line select key. (2) Insert the data disk into the DTU-100. (3) Press DISK CONTENTS line select key. (4) Verify that the DTU-100 reads the disk and the disk information is displayed on the CDU. Pass Fail The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. N/A 34-60-51 Page 540 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual F. SSDTU Test NOTE: This test can only be performed on the ground. NOTE: It is necessary to have a correct Universal Database on a USB or Secure Digital (SD) data storage device. (1) From DATA page 1 press the DISK line select key. (2) Insert a mass storage device into the SSDTU. (3) Press DISK CONTENTS line select key. (4) Verify that the SSDTU reads the storage device and that database information is displayed on the FMS CDU. Pass (5) Fail N/A Verify indicators are illuminated in accordance with the following table. Pass Indicator Type Fail N/A Indicator Color and Action Blank STATUS (Front) SSDTU Off Green Solid Operational USB (Front) No device present Device OK, not in use Device is being accessed Amber Solid CBIT has detected an error (SSDTU will reboot) Bad or unsupported device SD (Front) No device present Device OK, not in use Device is being accessed Bad or unsupported device NET (Front) Not yet operational N/A N/A N/A Device OK, in use (Indicates Primary Storage Device) Device OK, in use (Indicates Primary Storage Device) N/A Ethernet (Rear) No device present A network link is established on this port Network activity N/A N/A The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. Green Blinking N/A 34-60-51 Blue Solid Self Test Blue Blinking N/A Device is being accessed N/A N/A Device is being accessed Page 541 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual G. Approach Mode Test NOTE: This test does not operate correctly on some EFIS types. (1) Turn on and initialize the FMS (position does not matter for this test). (2) From DATA page 1, press the MAINT line select key. (3) From MAINT 1/1, press the DYNAMIC TEST line select key. (4) From DYNAMIC TEST 1/1 press the APPROACH line select key. (5) As the test begins, select the proper mode of the flight director. NOTE: The radio altimeter should be disabled for vertical coupling. (6) As the CDI returns to center, Nav mode will capture. Pass (7) Fail N/A Fail N/A The lateral mode of the flight director drops during FLAG STEER test (if roll steering for approach). Pass (11) N/A The glideslope flag comes into view during FLAG VERT test. Pass (10) Fail The V-bars will follow the lateral and vertical commands as specified for the test. Pass (9) N/A As the glideslope needle returns to center, the glideslope function will capture. Pass (8) Fail Fail N/A Nav flag drops into view during NAV FLAG test. Pass Fail The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. N/A 34-60-51 Page 542 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual 5. Sensor Checkout A. IRS NOTE: Inertial Reference System must be in Nav mode before conducting the following tests. (1) From DATA page 2 press the line select key for any IRS. (2) From IRS 1/1 note the following: Status 1. _______________________ 2. _______________________ 3. _______________________ Pass B. Fail Hdg _______ _______ _______ N/A GPIRS (1) From DATA 2/4 press the line select key for IRS/GPS. (2) From GPIRS1 1/3 note the following: GPS __________ IRS ___________ EPU __________ HDG ___________ # Sats __________ Integ __________ HIL __________ Pass Fail N/A (3) If additional GPIRS are installed repeat the above procedure selecting the appropriate IRS/GPS. GPIRS2 GPS __________ IRS ___________ EPU __________ HDG ___________ # Sats __________ Integ __________ HIL __________ Pass Fail N/A GPIRS3 GPS __________ IRS ___________ EPU __________ HDG ___________ # Sats __________ Integ __________ HIL __________ Pass Fail N/A The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 543 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual C. LORAN C NOTE: Aircraft must be outside for this test. (1) From DATA page 2 press the line select key for LCS. (2) From LCS 1/3 note the following: Status (NAV, Noncert or Search) _____________________________ LOA (Inside or Outside) ____________________________________ D. GRI Stations __________ __________ __________ __________ __________ __________ GPS-1 NOTE: Aircraft must be outside for this test. (1) From DATA page 2 press the line select key for GPS1. (2) From GPS 1/4 note the following: GPS (ACQ, ALT, NAV) __________ EPU __________ #SATS ________________________ INTEG __________ HIL ___________________________ 273 __________ 277 ___________________________ Pass E. Fail N/A WAAS1 NOTE: Aircraft must be outside for this test. (1) From DATA page 2 press the line select key for WAAS1. (2) From WAAS 1/4 note the following: MODE (ACQ, ALT, NAV) __________ #SATS ________________________ INTEG __________ HPL ___________________________ HAL __________ VPL ___________________________ VAL __________ HFOM _________________________ VFOM __________ 352 ___________________________ 354 __________ VER ___________________________ Pass Fail The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. N/A 34-60-51 Page 544 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual Temporary Change No. 34.60.51-1 Manual Affected Universal Avionics UNS-1Fw Flight Management System Installation Manual, Report No. 34-60-51 dated 10 July 2019. Filing Instructions Insert this Temporary Change adjacent Page 544 in the Maintenance, Checkout and Troubleshooting section. Purpose To correct WAAS1 checkout procedures. Instructions Replace E. WAAS1 instructions with the following: E. WAAS1 NOTE: Aircraft must be outside for this test. (1) From DATA page 2, press adjacent line select key for WAAS1. (2) On WAAS1 1/4, note the following: The elements on this page are dynamic and vary based upon the geographic location of the test, the quality of the GPS signal, the number of satellites, and flight plan entered. There are no pass/fail criteria for this section. The values below are only for illustration purposes. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34.60.51-1 Page 1 of 1 24 October 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual F. Universal Avionics Radio Reference Sensor (RRS) NOTE: The following Checkout Procedures may be accomplished in flight and all data can be compared to aircraft DME, VOR and (if applicable) TACAN. (1) Display DATA page 2. (2) Select VOR Status page. (3) Tune test station by frequency (Test) or by ID (line select key adjacent to IDENT). Check radial displayed on CDU for reasonableness. Pass G. Fail Air Data NOTE: This test requires the use of a pitot/static tester and approved procedures. (1) From DATA page 2 press the ADC line select key. (2) With pitot static test unit applied to the aircraft, run the airspeed up to approximately 200 knots. Confirm that the TAS displayed on the CDU is correct. Pass (3) Change the baro setting on the appropriate altimeter and confirm that the baroaltitude reading on the CDU coincides with the altimeter reading. Pass (4) H. Fail Confirm that the SAT displayed on the CDU is reasonable. Pass (5) Fail Fail N/A Turn off FMS and turn it back on before proceeding with additional tests. Fuel Flow (1) Press the FUEL key until FUEL 5/5 is displayed. (2) With all engines running, ensure that the fuel flow displayed on the CDU matches the aircraft’s fuel flow gauges. Check this on at least two different power settings. Pass Fail The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. N/A 34-60-51 Page 545 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual I. GPIRS Checkout (1) GPIRS Status GPIR1 1/3 gps HYB [D] irs NAV [D] q 01 hdg 101Ø #sata 06 integ RAIM set hdg ---ø hil 0.06nm select velocity irs ® fms1 s123 e420 select irs s124 e421 gps ® gps s123 e422 hyb s125 e423 RETURN® GPIR1 1/3 This page is accessed from DATA page 2 and provides data on the GPS and IRS sensors. NOTE: The page layout may differ in some installations. Status (GPS) HYB Navigation mode is using hybrid position from IRS and GPS. NAV GPS position alone is being used without IRS aiding. ALT Altitude aiding mode (ADC altitude being used to supplement poor satellite geometry). INIT GPS/IRS is initializing position. ACQ GPS is acquiring satellite for navigation. TEST GPS is in test mode. FAIL GPS has failed or no 429 data is being received. Status (IRS) NAV IRS has correctly aligned and is in NAV. ALIGN IRS is in alignment mode. FAIL No ARINC 429 data received from GPIRS or else GPIRS is sending FAIL status on the 429 bus. ATT IRS is in ATTITUDE mode. Sensor will not be used for navigation. This page will also show number of satellites being tracked as well as the North and East component velocities from the IRS, GPS, FMD and HYBrid IRS/GPS. SET HDG (2R) The value entered is displayed and transmitted on ARINC 429 label 043 for 12 seconds. Then dashes are displayed in the field again and label stops transmitting. This is used for setting IRS heading when in ATT mode. The display will indicate (degree symbol) for magnetic and T for true heading. The GPS and IRS can be independently selected or deselected from this page. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 546 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (2) GPIRS Comparison Page GPIR1 2/3 fms1 pos irs pos n 33 54.0 n 33 54.8 w 117 57.3 w 117 57.8 diff n 00 00.8 w 000 00.5 ¬GPS 20.2 irs 15.2® ¬HYB 20.7 RETURN® GPIR1 2/3 This page is similar to DATA 3/4 but only Hybrid, GPS and IRS positions are shown for comparison to FMS positions. Pushing the line select key next to GPS, HYB or IRS will display that position in the upper right hand field and show the difference from the FMS position. (3) GPIRS Diagnostics Page GPIR1 3/3 gpirs diagnostics 270 08DA10 273 056789 274 8745AF 350 604344 352 873243 353 6A7EC2 355 05A5A5 RETURN® GPIR1 3/3 This page shows contents of ARINC 429 labels from GPIRS as shown in left hand column. Data is in hexadecimal and is for diagnostic purposes only. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 547 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (4) GPIRS Diagnostics GPIRS BUS 270 – IRS Status ARINC 429 Hi Speed Transmission Rate: 500 milliseconds GPIRS Diagnostic Bit Assignments 01 1 1 1 02 03 04 0 0 0 05 06 SDI 07 08 Status Bits 09 10 11 12 13 14 15 16 17 18 18 20 21 22 23 24 25 26 27 28 29 30 31 32 P MM 0 1 Status bit meanings if set to one: Bit 17: IRS on DC power Bit 15: IRS attitude is invalid, IRS is failed Bit 13: IRS in NAV (navigation mode) Bit 12: IRS in ARR (attitude mode) Bit 11: IRS in ALIGN mode Where MM is 0: 0 = valid else = invalid Where P is bit which causes sum of 32 bits to be odd. GPIRS BUS 273 – Autonomous GPS Status ARINC 429 Hi Speed Transmission Rate: 500 milliseconds The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 548 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual GPIRS Autonomous GPS Status Bit Assignments 01 Status Bits 02 03 04 05 06 07 08 09 10 11 12 13 14 15 16 17 18 18 20 21 22 23 24 25 26 27 28 29 30 31 32 P MM 0 0 0 1 1 1 0 1 Status bit meanings if set to one: Bit 29: Reserved Bit 28: 000 = Self Test 001 = Initialization 010 = Acquisition 011 = Navigation 100 = Altitude Aiding 101 = Spare 110 = Spare 111 = Fault Bit 25 Bit 23 Bit 19 Bit 15: Secondary IRS/FMS source used Bit 14: IRS/FMS not present Bit 13: Secondary DADS source used Bit 12: DADS not present Bit 11 Where MM is 0: 0 = valid else = invalid Where P is bit which causes sum of 32 bits to be odd. GPIRS BUS 274 – Hybrid GPS Status ARINC 429 Hi Speed Transmission Rate: 500 milliseconds The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 549 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual GPIRS Hybrid GPS Status Bit Assignments 01 Status Bits 02 03 04 05 06 07 08 09 10 11 12 13 14 15 16 17 18 18 20 21 22 23 24 25 26 27 28 29 30 31 32 P MM 0 0 0 1 1 1 0 1 Status bit meanings if set to one: Bit 29: Reserved Bit 28 000 = Self Test 001 = Initialization 010 = Acquisition 011 = Navigation 100 = Altitude Aiding 101 = Spare 110 = Spare 111 = Fault Bit 25 Bit 23 Bit 19: Active GPSSU Source: 0 = GPSSU #1 1 = GPSSU #2 Bit 18 00 = Valid 01 = Inactive 10 = Functional Test 11 = Fail Bit 16 00 = Valid 01 = Inactive 10 = Functional Test 11 = Fail Bit 14 Where MM is 0: 0 = valid else = invalid Where P is bit which causes sum of 32 bits to be odd. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 550 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual J. Universal Avionics GPS Checkout Except where indicated, this checkout applies to the internal GPS and GPS 1000: (1) Test Preparation (2) Apply aircraft power to the FMS and GPS sensor(s) system. (3) Power up the FMS and initialize by verifying or entering proper date, time and present position. (4) Access DATA 2/n page (sensor select page) and select GPS. GPS 1/3 page will appear. (5) Status will display either ACQ (acquiring) or INIT (initializing). NOTE: At times it may take up to 30 minutes to acquire a valid almanac from the satellites present. (6) Wait until NAVB appears on GPS 1/3 status page. GPS1 1/4 Status Page stat q #sats integ hil hdop vdop 273 277 ver GPS1 1/4 NAV [D] address 01 ----06 data RADIO ---0.06nm select 1.57 gps only® 2.46 063580 select gps® 000000 0001 RETURN® GPS1 1/4 Status Page NOTE: GPS label 277 shown on the screen above applies only to the internal GPS and GPS-1000. NOTE: The page layout may be different in some installations. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 551 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (a) GPS Status: NAV GPS is NAV mode ACQ GPS is acquiring satellites INIT GPS is initializing first position from internal almanac ALT GPS is using altitude to compensate for poor satellite geometry TEST GPS is in TEST mode FAIL GPS has failed or 429 data is not received from GPS (b) GPS Q factors: These are error estimates in tenths of nautical miles (a Q factor of 01 is equal to 0.1 NM circular error estimate). A Q factor of 99 indicates that the sensor is not usable by the FMS. (c) # SATELLITES: The number of satellites currently being tracked by the GPS. This page shows ARINC 429 data on labels 273 and 277 from the GPS sensor. The operator may enter a five-digit hex ADDRESS field to view four-digit hex data in DATA field. This page is to be used for diagnostics and troubleshooting. HDOP and VDOP are for reference only. (d) SELECT/DESELECT GPS: Used to manually select or deselect the GPS sensor. (e) Label 273 GPS Sensor Status (discrete) APPROX. RESOLUTION N/A UNITS: N/A MAXIMUM VALUE N/A DATA FORMAT: TBD MINIMUM VALUE N/A FULL SCALE: N/A The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 552 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual Label 273 GPS Sensor Status (discrete) FIELD NAME BIT WEIGHT LABEL 6th 1 2 4 BIT NUMBER 01 02 03 04 05 06 07 08 09 10 11 DESCRIPTION 1 0 1 1 1 0 1 1 0 0 0 CODE = 273 OCTAL SPARE SPARE MSB of Satellite Visible (16X) 1 > 15 visible; 0 8 12 0 DADC STATUS 0 = PRESENT, 1 = NOT PRESENT 5th 1 13 X DADC SOURCE 0 = PRIMARY, 1 = SECONDARY 2 14 X FMS STATUS 0 = PRESENT, 1 = NOT PRESENT 4 15 X FMS SOURCE 0 = PRIMARY, 1 = SECONDARY 8 16 X NUMBER OF SATELLITES VISIBLE (1X) LSB 4th 1 17 X NUMBER OF SATELLITES VISIBLE (2X) 2 18 X NUMBER OF SATELLITES VISIBLE (4X) 4 19 X NUMBER OF SATELLITES VISIBLE (8X) MSB (See bit number 11) 8 20 X NUMBER OF SATELLITES TRACKED (1X) LSB 3rd 1 21 X NUMBER OF SATELLITES TRACKED (2X) 2 22 X NUMBER OF SATELLITES TRACKED (4X) 4 23 X NUMBER OF SATELLITES TRACKED (8X) MSB (See bit number 29) 8 24 X SPARE 2nd 1 25 X SPARE 2 26 X GPS OPERATIONAL MODE Note 1 4 27 X GPS OPERATIONAL MODE Note 1 8 28 X GPS OPERATIONAL MODE Note 1 1st 1 29 X MSB of SATELLITES TRACKED (16X) 1 > 15 tracked; 0 2 30 X SSM Note 4 31 X SSM Note 8 32 X PARITY (ODD) NOTE: The meanings of the bit combinations for GPS OPERATIONAL MODE and SSM are shown in the following tables. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 553 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual GPS OPERATIONAL MODE BIT 28 BIT 27 BIT 26 MEANING 0 0 0 SELF TEST MODE 0 0 1 INITIALIZATION MODE 0 1 0 ACQUISITION MODE 0 1 1 NAVIGATION MODE 1 0 0 ALTITUDE AIDING MODE 1 0 1 SPARE 1 1 0 SPARE 1 1 1 FAULT BIT 31 BIT 30 0 0 NORMAL OPERATION 0 1 NO COMPUTED DATA 1 0 FUNCTIONAL TEST 1 1 NOT USED MEANING The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 554 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (f) Label 277 GPS Diagnostics This label applies to the internal GPS and GPS 1000. APPROX. RESOLUTION N/A UNITS: N/A MAXIMUM VALUE N/A DATA FORMAT: TBD MINIMUM VALUE N/A FULL SCALE: N/A 277 GPS Diagnostics DIGIT BIT WEIGHT BIT NO. 1 2 1 2 1 2 3 4 4 1 2 4 5 6 7 8 6th 1 2 4 8 9 10 11 12 Unused Unused Unused Unused 5th 1 2 4 8 13 14 15 16 Unused Unused Unused Low Battery Voltage (for Sensor II battery backed up RAM) 4th 1 2 4 8 17 18 19 20 ARINC Receiver Parity Errors Noisy Interrupt Exception Spurious Interrupt Exception Uninitiated Interrupt Exception 3rd 1 21 2 4 22 23 8 24 Bus Error, Address Error, Illegal Instruction, Privilege Violation or Divide By Zero Trap Exception Message Negatively or Not Acknowledged by Sensor II Satellite Status, GPS Satellite Range Residual, Satellite Measurement Data, Ephemeris, Data, Almanac Data or MEC Support Message Not Received from Sensor II GPS Pos Data, GPS Lat/Lon or GPS Pos Fix Sol/Variables or Binary Position Data Message Not Received from Sensor II 2nd 1 2 4 8 25 26 27 28 Sensor II Communications Failure ARINC Transmitter or Receiver Failure RAM Addressing or Data Storage Failure GPS Board Software Checksum Failure 1st 1 2 29 Unreasonable Alt or Unreasonable Ground Speed or Dup Sat Elevations and Azimuths SSM 01 = Invalid SSM 10 = Unused Parity Bit 4 8 30 31 32 DESCRIPTION Octal Label = 277 The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 555 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual GPS1 2/4 and 3/4 Pages sv# 04 06 29 22 16 13 09 15 GPS1 2/4 az el snr stat 122ø 38ø 54 5 93ø 87ø 23 4 248ø 11ø 18 2 248ø 22ø 26 4 223ø 45ø 33 9 180ø 02ø 04 7 127ø 53ø 34 4 35ø 67ø 36 4 RETURN® GPS1 2/4 This page applies to the internal GPS and GPS-1000 sv# 05 07 24 21 26 23 19 11 GPS1 3/4 az el snr stat 22ø 48ø 54 5 193ø 57ø 23 4 148ø 21ø 18 2 241ø 27ø 26 4 210ø 35ø 33 9 150ø 62ø 04 7 237ø 43ø 34 4 100ø 07ø 36 4 RETURN® GPS1 3/4 This page applies to the internal GPS and GPS 1000 These pages display the twelve satellites most likely in current use by the GPS. Each line displays SV# (Satellite Vehicle Number). Azimuth will always be true direction from the aircraft. Elevation is in degrees above the horizon (90 degrees is directly overhead the aircraft position). EL may be negative indicating a satellite below the horizon. SNR is a number from 0 to 63 in dB Hz. Status is a number from 0 top 9 and is defined as follows: GPS SATELLITE STATUS STATUS DEFINITION 0 Satellite is assigned to a channel 1 FIND command issued 2 Waiting to receive almanac and ephemeris data 3 Waiting to receive complete pseudo range data block 4 Performing the tracking/acquisition process 5 Fast sequencing of satellite signal (tracking mode) 6 Satellite is not assigned to a channel 7 Lost satellite lock during sequencing process 8 Waiting for clock message 9 Satellite not found The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 556 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual GPS1 4/4 Page GPS1 4/4 deselected satellites stat 5 23 17 8 des des auto req desel sv#-- select sv#-- RETURN® GPS1 4/4 This page applies to the internal GPS and GPS-1000 This page displays a list of satellites that have been deselected by the GPS or requested deselected by the FMS. You should verify that individual satellites can be deselected and selected manually by entering the satellite vehicle number in the appropriate filed and then pushing [ENTER]. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 557 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual 6. GPS/WAAS Checkout NOTE: In a single FMS installation interfaced with an LP/LPV monitor, skip tests which require using FMS #2. A. FMS Power On Self-Test - Initialization and LPV Annunciation Test NOTE: In Step 4, the annunciators will only be lit during the start up sequence if both the onside FMS and the offside FMS or LPV Monitor are powered up at the same time. Subsequent power cycles of the FMS may not produce the same light sequence if the offside FMS or LPV Monitor is not powered down and up at the same time. B. (1) Apply aircraft power to the FMS and sensor(s) systems. (2) Power up and initialize both FMSs. (3) Confirm that the LPV WAAS lights are lit momentarily. (4) Confirm that installed LOS annunciators are lit momentarily. (5) Verify the displayed position matches the aircraft location. (6) Verify both FMSs pass all items on the self-test page. (7) Accept the position on FMS #1 and FMS #2 and verify that the reverse video ‘I’ disappears on both FMSs for SYNC operation. (8) Verify that both FMSs have the current database. (9) On DATA 3/4 page verify that the FMS positions on each unit correspond to the aircraft location and is consistent with the sensor positions and with the other FMS position. (10) Verify all data on DATA 2/4 page is accurate and reflects the configuration and sensors installed. GPS/WAAS Sensor Evaluation NOTE: At times it may take up to 30 minutes to acquire a valid almanac from the satellites present. (1) Display DATA 2/4 page on FMS #1. Verify Onside WAAS displays an EPU value, Offside displays a Nav mode. (2) On FMS #1 deselect WAAS #1. Verify Offside WAAS displays an EPU value. (3) Reselect WAAS #1. On Offside FMS, verify WAAS displays a Nav mode. (4) Display DATA 2/4 page on FMS #2. Verify Onside WAAS displays an EPU value. (5) On FMS #2, deselect WAAS #2. Verify Offside WAAS #1displays an EPU value. (6) Reselect WAAS #2. Verify Onside WAAS displays an EPU value. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 558 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual C. WAAS Flight Plan with LPV Approach NOTE: A list of WAAS Channel IDs may be obtained from the following web site: https://www.faa.gov/about/office_org/headquarters_offices/ato/service_units/t echops/navservices/gnss/approaches (1) With a destination airport in the flight plan, select FPL-MENU-ARRIVE and enter the data on the page as normal to add the RNAV approach. Make selections as prompted. (2) With a destination airport in the flight plan, select FPL-MENU-ARRIVE and enter the WAAS Channel ID in the APPR ID field LSK-4R. If the Channel ID does not match the destination airport in flight plan, the field will flash. (3) Verify that the choice selections are correct for the airport and that the flight plan is properly displayed after approach selection. Verify the WAAS Channel ID is correct and matches the printed chart. Verify that the Path ID is correct on APPR PLAN page 1/3. (FPL-MENU-NEXT-LSK-5L). NOTE: WAAS Channel ID is not available if there is no FASDB. (4) Verify that the Flight Plan is modified, adding the approach chosen by the WAAS Channel ID and that it is correct and reasonable. (5) Verify that the approach navigation source selected for the approach is positively indicated in the normal field of view at each pilot station. (6) Verify that the flight plan data is synchronized to the offside. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 559 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual D. CDU Display of RNP/ANP (1) E. Observe the RNP/ANP on CDU NAV 1/1 page. GPS/WAAS Dynamic Test Whenever any WAAS Critical Configuration Data is changed (FMS Transmit Bus, Analog Bus (DEVs) or the Cross-Channel Monitor), this test verifies that the WAAS subsystem has the appropriate scale factors, timing and other requirements for the WAAS critical guidance parameters and that the state of the Cross-Channel monitoring is as desired. NOTE: When the WAAS system is configured with Universal Avionics EFI-890R displays, a flight plan must be entered and linked to the navigation legs prior to running GPS/WAAS Dynamic Test. (1) Open MAINT 1/1 page by selecting MAINT from DATA 1/4 page. (2) Select WAAS LSK [2L] test. DATA 1/4 ¬NAV DATA CABIN DISP® ¬PILOT DATA ¬DISK MFD DISP® MSTR XFILL® ¬HOLD POS MAINT® MAINT 1/1 ¬CONFIG ¬WAAS ¬STATIC TEST ¬DYNAMIC TEST ¬S/W VERS (3) RETURN® Select WAAS GUIDANCE BUS LSK [1L] to display the GUIDANCE BUS STATUS page. WAAS 1/1 ¬WAAS GUIDANCE BUS ¬ANTENNA CONFIRM ¬RESET GG12W ALMANAC ¬RESET GG12W EPHEMERIS RETURN® The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 560 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (4) Select DYNAMIC TEST LSK [4R] to run the WAAS Dynamic Tests which will confirm any WAAS critical configuration data changes. GUIDANCE BUS STATUS waas onside UNCONFIRMED xc-monitor ENABLED offside UNCONFIRMED DYNAMIC TEST® RETURN® (5) The FMS will indicate to the WAAS subsystem to begin the Dynamic Test and display the progress of this test on the DYNAMIC TEST page as illustrated in the following: (6) Observe the aircraft displays and/or indicators verifying that the displays match the indication from the FMS. DYNAMIC TESTS waas IN PROGRESS RIGHT UP ¬CANCEL Test Output Test Duration RIGHT UP 10 seconds HOLD 5 Seconds CTR XTK 10 seconds CTR VDEV 10 seconds LEFT-DOWN 10 seconds HOLD 5 Seconds CENTER 10 seconds FLAG VERT 5 Seconds FLAG LAT 5 Seconds LPV LIGHT ON 5 Seconds LPV LIGHT OFF 5 Seconds X-C MONITOR 5 Seconds TEST COMPLETE End of Test The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. FMS #1 34-60-51 FMS #2 Page 561 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (7) When the WAAS subsystem completes the Dynamic Tests successfully and the FMS displays TEST COMPLETED message, a Confirmation Code and entry field are displayed as illustrated in the following: NOTE: If the Dynamic Test fails, the WAAS subsystem will exit the test and the FMS will display TEST FAILED. LP and LPV will then be inhibited. The WAAS configuration and/or aircraft wiring must be re-verified. DYNAMIC TESTS waas TEST COMPLETED confirm code 1234 enter confirm code ¬CONFIRM (8) RETURN® Enter the alphanumeric equivalent value (i.e. ONETWOTHREEFOUR) for each of the four numerical values of the displayed CONFIRM CODE (with leading zeros, if any, no spaces, no decimals), press ENTER. Press the CONFIRM key LSK [5L] to send data to the WAAS Subsystem. NOTE: This confirmation applies to the Onside FMS only. DYNAMIC TESTS waas TEST COMPLETED confirm code 1234 enter confirm code ONETWOTHREEFOUR ¬CONFIRM RETURN® (9) The WAAS subsystem(s) (both Onside and Offside ) verify the result for both the Onside/Offside configurations and report the status back to the FMS. (10) The FMS displays the WAAS GUIDANCE BUS STATUS page displaying the status of both the Onside and Offside systems. NOTE: If the Offside is still unconfirmed, run the Guidance Bus Test on the other FMS to enable LPV. GUIDANCE BUS STATUS waas onside CONFIRMED xc-monitor ENABLED offside UNCONFIRMED DYNAMIC TEST® RETURN® The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 562 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual F. WAAS Antenna Offsets Test This test must be run whenever the WAAS Antenna Offsets are changed. (1) Open MAINT 1/1 page by selecting MAINT from DATA 1/4 page. DATA 1/4 ¬NAV DATA CABIN DISP® ¬PILOT DATA ¬DISK MFD DISP® MSTR XFILL® ¬HOLD POS MAINT® MAINT 1/1 ¬CONFIG ¬WAAS ¬STATIC TEST ¬DYNAMIC TEST ¬S/W VERS (2) RETURN® Select WAAS LSK [2L] test. WAAS 1/1 ¬WAAS GUIDANCE BUS ¬ANTENNA CONFIRM ¬RESET GG12W ALMANAC ¬RESET GG12W EPHEMERIS RETURN® (3) Select ANTENNA CONFIRM LSK [2L] to display the ANTENNA CONFIRM page. The FMS displays the Antenna Offsets, confirmed or unconfirmed, for both onside and offside as received from the WAAS subsystem. ANTENNA 1/2 onside waas UNCOMFIRMED x´+º£.ºm x´+ºº.m x´+º.m ¬STANDARD The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. RETURN® 34-60-51 Page 563 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (4) Enter the alphanumeric equivalent value (i.e. ONETWOTHREE) for each of the numerical values of the Onside displayed antenna offsets, including the sign and leading/trailing zeros (no spaces or decimals). The ‘P’ and ‘M’ keys are used to represent plus/minus respectively. The ENTER key is used to advance the cursor to the next field. (5) When the last string has been entered, the ENTER key causes the data to be sent to the WAAS Subsystem. (6) Press NEXT LSK [5L] to display ANTENNA 2/2 confirm page. ANTENNA 2/2 offside waas UNCOMFIRMED CONFIRM® x´+º£.ºm PZEROTHREEZERO x´+ºº.m PZEROZEROEIGHT x´+º.m MZEROTWOFIVE ¬PREV RETURN® (7) Enter the Offside confirmation data. (8) Press CONFIRM LSK [1R], this sends the Onside and Offside data to the WAAS subsystem for confirmation. (9) The WAAS subsystem determines that the data is valid, confirms the data and the FMS displays that both the Onside and Offside Antenna data pages as confirmed by the WAAS subsystem. (10) The WAAS subsystem cross-compares these Antenna Offsets with what it receives from the Offside FMS. The WAAS subsystem determines that both Antenna Offsets match with the other WAAS subsystem is transmitting. The WAAS subsystem then sets both Onside and Offside data to Confirmed and the WAAS CONFIG UNCONFIRMED message is removed from the FMS. ANTENNA 1/2 onside waas COMFIRMED x´+º£.ºm ANTENNA 2/2 offside waas COMFIRMED x´+º£.ºm x´+ºº.m x´+ºº.m x´+º.m x´+º.m ¬NEXT RETURN® The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. ¬PREV 34-60-51 RETURN® Page 564 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual 7. Troubleshooting When an FMS fails any of the tests in the checkout section, troubleshoot it per the procedures below. Troubleshooting instructions are provided in the following three-column table, in which the first column lists equipment symptoms or describes the portion of the checkout procedure that the unit did not pass. These Malfunction/Symptoms are listed in approximately the same sequence as the checkout procedures. The second column lists probable causes. The third column describes the corrective action(s) for the malfunction. After performing the listed corrective action, repeat the failed test to ensure that the problem has been corrected. Then complete the checkout procedure from the point where it was interrupted. Should the corrective action affect tests already passed, perform those tests again. Where more than one corrective action is listed, the first action listed is the most probable repair that will correct the malfunction. However, when replacement of a major component such as the FMS is recommended, it is permissible to replace individual circuit boards instead if personnel are authorized by Universal Avionics to do so. If there is more than one corrective action listed and performing the first action does not correct the problem, perform the next action listed. NOTE: Ensure that you have eliminated all other potential causes of trouble before returning the FMS, 5-Inch FPCDU or other major component for repair. Verify that the installation wiring is correct. Determine whether the correct input and output voltages are present. Verify that the required ARINC labels are present on the data busses. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 565 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual A. Self-Test TROUBLE PROBABLE CAUSE CORRECTION The Self-Test Page displays a FAIL next to one or more of the items but after a short time, the Self-Test Page is replaced by the Initialization Page. May indicate fault in Self-Test. Push [MSG] to display failure information, troubleshoot indicated fault. The Self-Test Page displays a FAIL but is not replaced by the Initialization Page. FMS is defective. Replace the FMS. CDU MSG indicator does not illuminate. CDU is defective. Replace the CDU. One or more of the annunciators does not illuminate during self-test. The annunciator is defective. Troubleshoot annunciator per manufacturer’s instructions. CRT brightness does not respond properly to dimming feature. CDU is defective. Replace the CDU. Keyboard brightness cannot be controlled by the radio lighting. 1. Fault in radio lighting circuit. 2. CDU is defective. 1. Repair radio lighting circuit. 2. Replace CDU. Software is not the correct version. FMS has the wrong software program. Reconfigure or upgrade software. DEXP is out of date. 1. System date or time is wrong. 2. Wrong database. 1. Enter the correct date and time on Initialization page. 2. Update database per Operator’s Manual. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 566 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual B. System Failure Messages During normal FMS operations, numerous background tests are run continuously to assure normal operations. Should failures occur, the FMS system will notify the operator with a flashing message light on the panel or on the associated EFIS display. Pressing the MSG key will display a message with information about the failure detected. Many failures can be a result of problems other than the FMS systems components. The following table lists failure messages that can be displayed by the FMS, their meanings and possible causes / remedies to assist the maintenance technician with troubleshooting pilot reported failure messages. This table lists only failure messages, not normal system status messages that are not indicative of component failures. Refer to the applicable Operator’s Manual for a complete listing of messages. System Failure Messages Failure Message 400 Hz REF FAIL Probable Cause 1. No power to circuit. 2. 400 Hz AC power has failed. 3. Wiring faults. 4. Defective FMS. Action/Correction 1. Check/reset 26 VAC circuit breaker(s). 2. 26 VAC voltage/frequency out of tolerance. 3. Troubleshoot wiring and repair. 4. Replace FMS. ABNORMAL CKLIST DB FAIL The abnormal checklist database has failed. (Only with Collins Pro Line 4 800 configuration) Reload checklist database. A/D CODE # Analog/Digital board failed selftest. Replace FMS. A/D HEADING FAIL 1. Present system heading source, A/D (synchro analog-to-digital), has failed. 2. Wiring faults. 3. Defective FMC. 1. Check heading source to FMS, switch sources/reset system as required. 2. Troubleshoot wiring and repair. 3. Replace FMS. ADC INPUT FAIL 1. An Air Data Computer (ADC) failure is detected. 1. Check circuit breakers for Air Data Computer/ACU if installed. Select alternate sources if available. 2. Troubleshoot wiring and repair. 3. Replace FMS. 2. Wiring faults. 3. Defective FMS. AFIS ARINC FAILURE The FMS has determined that a failure is present on the AFIS ARINC bus. Troubleshoot bus and AFIS and repair. AFIS VHF MODEM FAILURE The VHF modem in the AFIS DMU has failed Replace AFIS DMU. AHRS # HEADING FAIL AHRS Heading has failed while in use as the FMS heading source. Troubleshoot AHRS and repair. AHRS # INPUT FAIL The AHRS input has failed or its status word indicates failure. Troubleshoot AHRS and repair. AIRPORT DATABASE FAIL A problem has been found in the airport section of the standard database. Reload Navigation Database diskettes. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 567 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual System Failure Messages Failure Message Probable Cause Action/Correction AIRWAY DATABASE FAIL A problem has been detected in the Airways database. Reload Navigation Database. ALIGN PT DATABASE FAIL A problem has been detected in the Align Points database. Reload pilot database diskette. ALTITUDE INVALID 1. The altitude portion of the Air Data Computer is unusable. 2. Wiring faults. 3. Defective FMS. 1. Check circuit breakers/status of Air Data Computer/ACU if installed. 2. Troubleshoot wiring and repair. 3. Replace FMS. ANALOG BOARD FAIL Faults on analog data outputs from FMS. Replace analog board. ANALOG INST FAIL 1. No power to circuit. 3. Wiring faults. 4. Defective FMS. 1. Check/reset 26 VAC circuit breaker(s). 2. 26 VAC voltage/frequency out of tolerance. 3. Troubleshoot wiring and repair. 4. Replace FMS. APC INPUT FAIL Aircraft performance computer (APC) is configured, but no signal has been received for three seconds. (RC-135 Aircraft only) 1. Check circuit breakers/status of APC. 2. Troubleshoot wiring and repair. 3. Replace FMS. APPROACH DATABASE FAIL A failure has been detected in the approach database. Reload navigation database. ARPT COMS DATABASE FAIL A failure has been detected in the communications section of the database. Reload navigation database. ARPT NAME DATABASE FAIL A failure has been detected in the geographical airport names database. Reload navigation database. ARINC # FAIL 1. Faults in wiring from/to FMS ARINC inputs/outputs. 2. Defective FMS. 1. Troubleshoot wiring and repair. 1. Faults on Roll Steering, CSDB or Fuel Flow wiring. 2. Defective FMS. 1. Troubleshoot wiring and repair. BACKUP DATABASE FAIL A fault in the Database software. Reload FMS Software. CKLST DATABASES FAIL All checklist databases have hailed. Reload checklist database. CLOCK TIMER FAIL The clock timer on the CPU board has failed self-test. Replace CPU board. COMP ARPTS DATABASE FAIL The Company Airport database has failed error checking. 1. Reload the Company Airports database. 2. Replace FMS. COMP ROUTE DATABASE FAIL The Company Routes database has failed error checking. 1. Reload the Company Routes database. 2. Replace FMS. 2. 400 Hz (AC) power has failed. AUXILIARY BOARD FAIL The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 2. Replace FMS. 2. Replace FMS. 34-60-51 Page 568 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual System Failure Messages Failure Message Probable Cause Action/Correction COMP WPTS DATABASE FAIL The Company Waypoints database has failed error checking. 1. Reload the Company Waypoints database. 2. Replace FMS. CONFIG DATA FAILED 1. Wiring faults on configuration module. 2. Defective configuration module 1. Troubleshoot wiring and repair. 3. Defective FMS. CONFIG MODULE FAILED 1. Wiring faults on configuration module. 2. Defective configuration module 3. Defective FMS. 2. Troubleshoot configuration module. 3. Replace FMS. 1. Troubleshoot wiring and repair. 2. Troubleshoot configuration module. 3. Replace FMS. CONFIG UPDATE REQUIRED Configuration module and FMS configuration data has failed requiring the FMS to be configured for installation. Reconfigure module to correct settings. CREW CKLIST DATABASE FAIL The crew notes database has failed. Reload checklist database. CROSSFILL FAIL: BAD DATA (Dual or triple installations only) 1. Wiring faults in crossfill data lines between FMS systems. 2. Defective FMS. 1. Troubleshoot wiring and repair. 1. Wiring faults in crossfill data lines between FMS systems. 2. Defective FMS. 1. Troubleshoot wiring and repair. DATABASE EXPIRED The current date is past the Nav Database expiration date. Load current Nav Database diskettes. DATABASE FAIL A part or the entire navigation database has failed. Reload Nav Database diskettes. DEMONSTRATION MODE The aircraft identification is configured as “DEMO” and sensor data is simulated internally. Reconfigure system to normal mode before flight. DISCRETE I/O FAIL 1. Faults on wiring to FMS discrete input/output wiring. 2. Defective FMS. 1. Troubleshoot wiring and repair. DOPPLER FAIL Doppler is selected and has failed. Check status of Doppler sensor and wiring. EFIS #n SEL HDG FAIL The FMS has detected that the CSDB bus from the MPU has gone inactive or failed. The bus would have had to be active for this message to be displayed. 1. Verify the MPU/MFD is operational. 2. Troubleshoot and repair wiring. 3. Replace FMS. COMP WPTS DATABASE FAIL The Company Waypoints database has failed error checking. 1. Reload the Company Waypoints database. 2. Replace FMS. EMERGENCY CKLIST The emergency checklist Reload checklist database. CROSSFILL FAIL: BUS (Dual or triple installations only) The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 2. Replace FMS. 2. Replace FMS. 2. Replace FMS. 34-60-51 Page 569 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual DATABASE FAIL database has failed. System Failure Messages Failure Message Probable Cause Action/Correction ENROUTES COMS DATABASE FAIL A failure has been detected in the enroute communications section of the database. Reload navigation database. ENROUTES DATABASE FAIL The Navigation Database containing enroute intersections has failed. Reload Nav Database diskettes. ERP # FAIL The EFIS radar panel (ERP) associated with this FMS has failed. Replace the failed ERP. FMC BATTERY LOW Defective FMS. Replace FMS. FMS DATALINK QUEUE FULL Datalink messages are not being sent resulting in a full message queue. Troubleshoot and repair Datalink system. FMS NETWORK COMM FAIL The FMS internally programmed Ethernet address has failed. There is no communication with the DTU. Replace FMS. FMS PART NUMBER MISMATCH The FMS installed has a different part number than the configuration stored. Verify correct part number FMS is installed. Reconfigure as required. FUELFLOW FAIL 1. Defective fuel flow input source. This will be indicated if engine is shut down or flow signal is lost for four minutes. 2. Faults on fuel flow wiring. 1. Troubleshoot and repair fuel flow input source if necessary. FUEL FLOW SELF TEST FAIL 1. Faults on fuel flow input ports. 2. Defective FMS. 1. Verify configuration is correct. 2. Replace FMS. GLS # CONFIG MODULE FAIL The GLS #n configuration module has failed. 1. Troubleshoot configuration module wiring. 2. Replace configuration module. GLS # FAIL The GPS Landing System LRU has failed Troubleshoot and repair the GLS. GLS # VDL FAIL The VHF data link board internal to the GLS LRU has failed. Troubleshoot the GLS. GNSS # FAIL 1. Defective or inoperative GNSS sensor. 2. Wiring faults on GNSS input to FMS. 1. Check status of GNSS sensor. 1. Defective or inoperative GPIRS sensor. 2. Wiring faults on GPIRS input to FMS. 1. Check status of GPIRS sensor. GPIR # FAILED The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 2. Troubleshoot and repair wiring. 2. Troubleshoot and repair wiring. 2. Troubleshoot and repair wiring. 34-60-51 Page 570 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual System Failure Messages Failure Message GPS # FAILED Probable Cause Action/Correction 1. GPS position data is missing or invalid or the status label indicates a FAIL status exists. 2. GPS antenna coax is damaged or disconnected. 1. Check status of GPS sensor on DATA pages. 3. Wiring faults on GPS input/output wiring. 4. Defective GPS sensor. HEADING REF FAIL 1. No power to circuit. 2. Check condition of GPS antenna/coax and repair as required. 3. Troubleshoot and repair wiring. 4. Replace GPS sensor. If GPS is internal to the FMS, replace FMS. 3. Wiring faults. 4. Defective FMS. 1. Check/reset 26 VAC circuit breaker(s). 2. 26 VAC voltage/frequency out of tolerance. 3. Troubleshoot and repair wiring. 4. Replace FMS. IC600L HEADING FAIL The left heading source has failed (Honeywell Primus 1000 only) Troubleshoot and repair the left heading source. IC600R HEADING FAIL The right heading source has failed (Honeywell Primus 1000 only). 1. Troubleshoot and repair the right heading source. 2. Replace FMS IC600-L BUS FAIL The left IC600 bus has failed (Honeywell Primus 1000 only). 1. Troubleshoot and repair the Primus 1000 system. 2. Replace the FMS. IC600-R BUS FAIL The right IC600 bus has failed (Honeywell Primus 1000 only). 1. Troubleshoot and repair the Primus 1000 system. 2. Replace the FMS. INVALID ARINC VERSION Two ARINC boards, which do not have the same software version numbers, are installed in the FMS. Replace the FMS. INVALID CONFIGURATION FMS configuration data is incorrect. Reconfigure module to correct settings. INVALID FUEL CONFIG The fuel flow sensor configuration is invalid or incomplete. Reconfigure to correct settings. IRS # FAIL 1. An inertial reference system failure is detected. 2. Faults in input wiring to the FMS. 1. Check status of the IRS system. Repair or replace IRS as required. The system heading source has failed. 1. Check status of the IRS system. Repair or replace IRS as required. 2. 400 Hz (AC) power has failed. IRS # HEADING FAIL 2. Troubleshoot and repair wiring. 2. Troubleshoot and repair wiring. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 571 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual System Failure Messages Failure Message LCS FAIL # Probable Cause Action/Correction 1. The message displayed where # is the failure code for the type failure the LCS has detected as follows: 1 = LCS Program Checksum fail. 2 = LCS ARINC Self Test Fail. 3 = LCS Memory Test Fail 9 = LCS not communicating with the FMS. 2. Wiring faults in input wiring to the FMS. 1. Check status of the LCS sensor. LEFT IOC -…FAIL The left input/output concentrator (onside or offside) has failed. Replace the failed IOC. MEMORY BANK # FAIL The internal memory bank has failed error checking. Replace the FMS. MOT WPT MEMORY FAIL The Mark On Target waypoint memory section has failed power up and self-test. Replace the FMS. NAV DATABASES FAILED All of the navigation databases have failed. Reload navigation database. NDB DATABASE FAIL A problem has been found in the NDB database. Reload navigation database. NDB NAME DATABASE FAIL An error was detected in the NDB plain language name database. Reload navigation database. NEW MAINT LOG EXISTS This message is displayed one minute after landing when any diagnostic history event has been recorded during the previous flight. Download maintenance log to a blank DOS formatted diskette and view with ASCII text editor for analysis. NONVOLATILE MEMORY FAIL 1. The nonvolatile memory has failed the power up test due to voltage transients corrupting system RAM. 1. Recycle power to FMS to attempt to clear. Pilot, performance and checklist databases will likely be lost and have to be reloaded as required. 2. Replace FMS. 2. Defective FMS. 2. Troubleshoot and repair wiring. NORMAL CKLIST DATABASE FAIL The normal checklist database has failed (only with Collins Pro Line 4 interface). Reload checklist database as required. OFFSIDE FLAP POS FAILED The offside flap position input to the Primus 1000 has failed (LR45 only). Troubleshoot and repair the flap position input to the Primus 1000. ONSIDE FLAP POS FAILED The onside flap position input to the Primus 1000 has failed (LR45 only). Troubleshoot and repair the flap position input to the Primus 1000. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 572 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual System Failure Messages Failure Message Probable Cause Action/Correction OTHER FMS HEADING FAILED (dual or triple FMS installations only) The FMS is using heading from the other FMS and that heading has failed. Troubleshoot and repair heading input sources to specified FMS. PERF DATABASE FAILED The performance database has failed. Reload performance database. PERF DB ID MISMATCH The performance database ID entered on the configuration pages does not agree with the performance database ID on the disk that is loaded. Reload correct performance database or reconfigure ID code in configuration module to correct data. PILOT APPR DATABASE FAIL A problem has been detected in the pilot defined approach database. Reload pilot database. PILOT ARPT DATABASE FAIL A problem has been detected in the pilot defined airport database. Reload pilot database. PILOT DATABASES FAILED The database of all pilot defined locations has failed. Reload pilot database. PILOT RNWY DATABASE FAIL A problem has been detected in the pilot defined runway database. Reload pilot database. PILOT ROUTE DATABASE FAILED The database of pilot defined routes has failed. Reload pilot database. PILOT SID DATABASE FAIL A problem has been detected in the pilot defined SID database. Reload pilot database. PILOT STAR DATABASE FAIL A problem has been detected in the pilot defined STAR database. Reload pilot database. PILOT WPT DATABASE FAIL A problem has been detected in the pilot defined waypoint database. Reload pilot database. n VOLT PWER SUPPLY # FAIL (n = 3 VDC, 5 VDC, +8 VDC or –8VDC) 1. Wiring faults on configuration module. 2. DTU wiring faults. 3. Defective FMS. 1. Troubleshoot wiring and repair. PROGRAM CHECK FAIL A fault in the FMS Software. Reload the FMS Software. PRO LINE 21-L BUS FAIL The left PL-21 bus has failed or is invalid (Collins Pro Line 21 EFIS only). 1. Troubleshoot and repair the Pro Line 21 system 2. Replace the FMS. PRO LINE 21-R BUS FAIL The right PL-21 bus has failed or is invalid (Collins Pro Line 21 EFIS only). 1. Troubleshoot and repair the Pro Line 21 system 2. Replace the FMS. RCU # FAIL 1. Wiring faults in RCU to FMS interface. 2. Defective RCU. 1. Troubleshoot wiring and repair. RIGHT IOC-…FAIL The right input/output concentrator (onside or offside) has failed. Replace the failed IOC. ROUTES FAIL The route database has failed. Reload pilot database. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 2. Troubleshoot wiring and repair. 3. Replace FMS. 2. Replace RCU. 34-60-51 Page 573 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual System Failure Messages Failure Message Probable Cause Action/Correction RRS DATA BUS FAIL 1. Wiring faults in RRS interface. 2. Defective RRS. 1. Troubleshoot wiring and repair. 2. Replace RRS. RRS (DME, TACAN, VOR) SELF TEST FAIL 1. Wiring faults in RRS interface. 2. Defective RRS. 1. Troubleshoot wiring and repair. 2. Replace RRS. RRS TUNE BUS FAIL 1. Faults in tune data wiring from FMS to RRS. 2. Defective RRS. 1. Troubleshoot wiring and repair. 1. Faults in tune data wiring from FMS to RRS. 2. Wiring faults between the RRS and DME, TACAN, and/or VOR. 3. Defective RRS. 1. Troubleshoot wiring and repair. 1. Wiring faults in RTU to FMS interface. 2. Defective RTU. 1. Troubleshoot wiring and repair. RUNWAY DATABASE FAIL The runway database has failed. Reload navigation database. SBAS DATABASE FAIL A problem has been found in the SBAS approach database. The FMS will limit SBAS Approach to the LNAV level of service. Reload navigation database. SID DATABASE FAIL The Navigation SID database has failed. Reload navigation database. SOFTWARE CONFIG MISMATCH The loaded version of software does not match the Software Control Number (SCN) stored in the configuration module. 1. Reconfigure FMS. 2. Replace FMS. SPCL MISSION MEMORY FAIL The special missions memory section has failed power up self test. Replace the FMS. STAR DATABASE FAIL The Navigation STAR database has failed. Reload navigation database. STEERING FAIL This failure may be reset by positioning the cursor over the ROLL CMD line on DATA page 5 (General Data) and then pushing [BACK] and then [ENTER]. 1. Loss of TAS input to the FMS from the ADC. 2. Faulty wiring on roll steering output from FMS. 3. Defective FMS. 1. Check TAS output and repair as required. 2. Troubleshoot wiring and repair. SYNC CONFIG MISMATCH FMS detects mismatch in one of the configuration settings (VNAV, Fuel, Temp Comp, Lateral Steering, Approach Types, Heading Select, TGT FPA) Check configuration of all FMSs. TACAN FAIL Defective TACAN unit. 1. Troubleshoot wiring and repair 2. Replace TACAN unit. RRS (DME, TACAN, VOR) TUNE FAIL RTU # FAIL The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 2. Replace RRS. 2. Troubleshoot wiring and repair. 3. Replace RRS. 2. Replace RTU. 3. Replace FMS. 34-60-51 Page 574 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual System Failure Messages Failure Message TAS INVALID Probable Cause 1. Faulty ADC/ACU system. 2. Wiring faults in ADC/TAS input to FMS. Action/Correction 1. Check ADC/ACU system and repair as required. 2. Troubleshoot wiring and repair. TAWS FAIL TERMINALS DATABASE FAIL The terminal intersection database has failed error checking. Access to data is denied. 1. Reload the NAV database. 2. Replace the FMS. UNILINK FAIL 1. Defective UniLink unit. 2. Defective FMS. 1. Replace UniLink unit. 2. Replace FMS. VHF NAME DATABASE FAIL The navigation VHF plain language name database has failed Reload navigation database. VHF NAVAID DATABASE FAIL The navigation navaid database has failed. Reload navigation database. VOR TUNE FAIL AN ARINC VOR has not tuned the selected frequency. 1. Attempt to tune another VOR station. 2. Troubleshoot and repair the ARINC VOR. 3. Replace the FMS. WAAS # FAIL A failure has been determined for the indicated WAAS 1. Check FMS and repair as required. 2. Troubleshoot wiring and repair. WAAS/ANALOG FAIL Self-test for WAAS/Analog board has failed. 1. If initial installation, troubleshoot wiring to Level of Service annunciators. WAAS/ARINC FAIL Self-test for WAAS/ARAINC board has failed. Replace FMS. (WAAS) UNCONFIRMED GUIDANCE New or changed critical guidance information. Run WAAS Dynamic Test to enter the confirmation code for the guidance information. (WAAS) UNCONFIRMED GUIDANCE MONITOR New or changed critical guidance monitor information. Run WAAS Dynamic Test to enter the confirmation code for the guidance monitor information. XFILL CONFIG MISMATCH Crossfill data has been sent to and FMS that is not configured to receive this data. This message alerts the operator that crossfill data was sent but not accepted. Verify FMS configuration. 2. Replace FMS. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 575 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual C. Database Update Error Messages The system provides notification of errors that occur during the database update process which prevent successful completion of the database load procedure. The system provides notification of errors that occur during the database update process which prevent successful completion of the database load procedure. The use of the term “DTU” is used to reference the DTU, DTU-100 or SSDTU and the use of the terms “DISK” displayed on the FMS and “data storage device” are used to reference floppy disk, Zip disk, USB or Secure Digital data storage devices. Database Update Error Messages Trouble Probable Cause Action/Correction COMMUNICATION ERROR: DTU STOPPED RESPONDING 1. DTU power interrupted. 2. DTU wiring faults. 3. Defective DTU 1. Restore power to DTU. 2. Troubleshoot wiring and repair. 3. Replace DTU. COMMUNICATION ERROR: FMS AND DTU ARE OUT OF SYNC 1. DTU power interrupted. 2. DTU wiring faults. 3. Defective DTU 1. Restore power to DTU. 2. Troubleshoot wiring and repair. 3. Replace DTU. COMMUNICATION ERROR: OPERATION ABORTED BY DTU 1. DTU power interrupted. 2. DTU wiring faults. 3. Defective DTU 1. Restore power to DTU. 2. Troubleshoot wiring and repair. 3. Replace DTU. COMMUNICATION ERROR: UNRECOVERABLE ERRORS IN TRANSFERRED DATA 1. DTU power interrupted. 2. DTU wiring faults. 3. Defective DTU 1. Restore power to DTU. 2. Troubleshoot wiring and repair. 3. Replace DTU. COULD NOT LOAD ALL DATABASES – TOO LARGE FOR AVAILABLE MEMORY Attempting to load incorrect database. Obtain and load correct database. DISK FORMAT ERROR 1. Bad data storage device. 2. DTU wiring faults. 3. Defective DTU. 1. Replace data storage device. 2. Troubleshoot wiring and repair. 3. Replace DTU. DISK IS FULL An attempt is made to write flight data to the data storage device and there is not enough free space available. Insert a blank formatted data storage device. DISK IS WRITE PROTECTED The DTU detects that the data storage device is write protected. Reset the write protect device on the data storage device. DISK MUST BE EMPTY USE ANOTHER DISK OR PUSH FORMAT DISK ON DISK MENU TO DELETE ALL FILES ON THIS DISK An attempt is made to do a Pilot Database Save and the data storage device already contains at least one DOS file. Use blank formatted data storage device to perform pilot database save function. DISK READ OR WRITE ERROR 1. Bad data storage device 2. Electrical noise on DTU data lines. 3. Defective DTU. 1. Replace data storage device. 2. Troubleshoot wiring and repair. 1. DTU is not connected. 2. DTU is not turned on and finished with self-test. 3. Defective DTU. 1. Check DTU connections and repair as required. 2. Turn on the DTU and wait until it has finished self-test. DTU NOT DETECTED The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 3. Replace DTU. 34-60-51 Page 576 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual 3. Replace DTU. Database Update Error Messages Trouble Probable Cause Action/Correction EMPTY DISK OR NON-FMS DISK The data storage device does not contain a header file. Use correct data storage device. INVALID DATA ON DISK Faulty or incorrect data storage device. Use correct data storage device. INVALID DISK VERSION 1. The disk version field in the header does not agree with the FMS SCN. 2. Faulty or incorrect data storage device. 1. Verify that FMS configuration shows correct SCN. LOAD CANCELLED BY ANOTHER FMS 1. Errors in loading. 2. Defective FMS. 1. Cancel and restart load. 2. Replace FMS. LOAD CANCELLED 1. Errors in loading. 2. Defective FMS. 1. Cancel and restart load. 2. Replace FMS. MISSING OR UNFORMATTED DISK 1. No data storage device in DTU 1. Use correct data storage device. 2. If appropriate format the diskette or use correct diskette. 2. Incorrect type data storage device or is not DOS formatted to correct data size. 2. Use correct data storage device. MUST FIRST UPDATE NAV DATABASE BEFORE THIS EXTENDED OR COMPANY ROUTE DATABASE CAN BE LOADED An attempt is made to load a NAV extended database before the NAV standard database of the same cycle is loaded. Load the NAV standard database first and then load the NAV extended database. MUST FIRST UPDATE NAV DATBASE BEFORE THIS PLT DATABASE CAN BE LOADED An attempt is made to load a pilot database that is more recent than the one currently stored. Update the FMS to the same navigation database cycle used to create the pilot database. Then load the pilot database. POWER FAIL A power failure has interrupted the operation. Reset power and restart the load as required. D. Configuration Verification Trouble Data value fails to match the corresponding data value on the Aircraft Configuration Data Sheets. Probable Cause 1. Configuration Module is programmed incorrectly. 2. Mount rack or FMS connector pins, insulation or wiring is defective. 3. FMS is defective. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. Action/Correction 1. Reprogram per System Data Installation section in this manual. 2. Determine fault and replace. 3. Replace FMS. 34-60-51 Page 577 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual E. FMS Self-Test Output Checkout Trouble HSI does not show required output. Probable Cause 1. Configuration is incorrect. 2. FMS to HSI wiring is incorrect 3. HSI is defective. 4. FMS is defective. Flight director does not command 10 degree right bank. F. 1. FMS to autopilot/flight director is incorrect. 2. Flight director is defective. 3. FMS is defective. HSI does not show required output. 2. Replace the flight director. 3. Replace FMS. 1. Configuration is incorrect. 2. FMS to HSI wiring is incorrect. Action/Correction 1. Reprogram. 2. Check and correct wiring (see Troubleshooting Synchro: Wiring to Receiver). 3. Replace HSI. 4. Replace FMS. DIST/GS Checkout Trouble DIST is not counting down or GS (Ground Speed) is not approx. 150 knots. Probable Cause FMS is defective. Action/Correction Replace the FMS. HSI From Checkout Trouble HSI does not show FROM indication. I. 1. Rewire correctly. Probable Cause 3. HSI is defective 4. FMS is defective. H. 1. Reprogram. 2. Check and correct wiring (see Troubleshooting Synchro: Wiring to Receiver). 3. Replace HSI. 4. Replace FMS. FMS Output to HSI Checkout Trouble G. Action/Correction Probable Cause 1. HSI is defective. 2. FMS is defective. Action/Correction 1. Replace HSI. 2. Replace FMS. DIST/BRG Checkout Trouble Probable Cause Action/Correction CDU does not show correct distance or bearing. 1. Fault in wiring. 2. CDU is defective. 3. FMS is defective 1. Troubleshoot and repair wiring. 2. Replace CDU. 3. Replace FMS. HSI does not show above values. 1. Fault in wiring. 2. HSI is defective. 3. FMS is defective 1. Troubleshoot and repair wiring. 2. Replace HSI. 3. Replace FMS. Multifunction display (MFD) does not show correct display. 1. Wiring to MFD is incorrect. 2. MPU is defective. 3. MFD is defective. 1. Check and correct. 2. Replace the MPU. 3. Replace the MFD. 4. FMS is defective. 4. Replace the FMS. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 578 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual J. Roll Steering Checkout Trouble Control yoke does not rotate in specified direction. FMS HDG panel annunciator does not illuminate. K. Probable Cause Action/Correction 1. FMS to autopilot/flight director wiring is reversed. 2. Flight guidance equipment is defective. 3. FMS is defective. 1. Rewire. 1. Annunciator or its wiring is defective. 2. FMS is defective 1. Repair as required. 2. Check out and correct. 3. Replace FMS. 2. Replace FMS. Input of a Selected Crosstrack Checkout Trouble Probable Cause Action/Correction CDU displays are not as required. FMS is defective. Replace FMS. MFD display is incorrect. MFD is defective. Take corrective action. HSI CDI does not deflect as required. 1. HSI is defective. 2. FMS is defective. 1. Replace the HSI. 2. Replace the FMS. L. DME Checkout Trouble DME Sensor Status Page does not show correct distance to DME. M. 1. DME sensor or wiring is defective. 2. FMS is defective Action/Correction 1. Determine which and correct. 2. Replace FMS. Winds Display Checkout Trouble Winds Display on EHSI does not agree with that on CDU. N. Probable Cause Probable Cause 1. EHSI drive computer is defective. 2. FMS is defective. Action/Correction 1. Replace the EHSI drive computer. 2. Replace FMS. Sensor Checkout (1) Checkout of Inertial Sensor Status and Heading Displays Trouble Probable Cause Action/Correction CDU does not show FAILED when ISS is off. FMS is defective. Replace FMS. CDU does not show ALIGN when MSU is set to Align. 1. IRS or its wiring is defective. 2. FMS is defective 1. Repair as required. 2. Replace FMS. CDU does not show NAV when IRS is in NAV mode. 1. IRS or its wiring is defective. 2. FMS is defective 1. Repair as required. 2. Replace FMS. CDU HDG IN does not agree with the reference heading. IRS is defective. Replace IRS. CDU HDG IN does not agree with the HSI HDG 1. IRS or its wiring is defective. 2. FMS is defective 1. Repair as required. 2. Replace FMS. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 579 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual (2) Checkout of LORAN C Sensor Trouble LCS display does not show expected values. Probable Cause 1. Required LORAN station(s) is off the air. 2. Sensor system is defective. 3. FMS is defective. (3) Action/Correction 1. Check station maintenance chart in Navigation Systems section, Page 601. 2. Repair the sensor system. 3. Replace FMS. Checkout of Sensor Lat/Long Coordinates vs. CDU – Calculated Position Trouble Sensor supplied coordinates do not agree with CDU calculated position. Probable Cause 1. Required VLF station(s) is off the air. 2. Sensor system is defective. 3. FMS is defective. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. Action/Correction 1. Check station maintenance chart in Navigation Systems section, Page 601. 2. Repair the sensor system. 3. Replace FMS. 34-60-51 Page 580 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual O. GPS Antenna Inspection and Troubleshooting (1) Antenna Damage Paint degradation or small dings on the surface of the radome will not affect the antenna performance or function. Antennas with indentations or depressions larger than 0.100” in diameter or 0.020” maximum depth should be reported for further investigation. Antennas with any crack in the radome should be reported for further investigation. (2) Antenna Troubleshooting There are too many parameters for a proper antenna check to take place on the airplane, and there is no other simple way to determine that the antenna performs acceptably. Resistance testing alone will not indicate good or bad status. If a FMS is having repeatable GPS failures or problems the simplest troubleshooting technique for a dual FMS system would be to swap antenna leads at the LRUs. If that is not possible, using a new or known good antenna outside the aircraft and running the coax directly to the LRU would also be a reliable test. (3) Painting Antenna The antenna manufacturer, AeroAntenna Technology Inc., does not recommend painting the GPS antenna. Painting will cause a RF shift and impact the antenna performance. The antenna is clearly marked by the manufacturer “DO NOT PAINT”. Any part with a paint concern should be returned to Universal Avionics for evaluation. Reference: FAA AC 43.13-2B, Acceptable Methods, Techniques, and Practices Aircraft Alterations “312. ANTENNA REPAIR. Painting an antenna or applying protective coatings or devices that are not approved are not allowed under this AC. Paint is an RF de-tuner. If an antenna is painted in the field, paint type and paint thickness present uncontrolled variables that will affect an antenna’s performance, and may result in the antenna no longer meeting its specifications or Technical Standard Order (TSO).” The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 581 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual Navigation Systems 1. Scheduled Maintenance Periods of Navigation Systems Maintenance periods are subject to change. Information about DGPS and GPS may be obtained on the Internet at www.navcen.uscg.gov Additional information about DGPS, GPS and LORAN is available from: 703-313-5900 U.S. Coast Guard Navigation Center 7323 Telegraph Road Alexandria, VA 22315 A. DGPS Maintenance Schedules Differential GPS maintenance schedules are not available. B. GPS Maintenance Schedules The Global Positioning System has no scheduled maintenance that affects the availability of the system. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 601 10 July 2019 UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual Fuel Flow Inputs 1. Fuel Flow Sensors The FMS accepts up to four fuel flow inputs directly from the engine fuel flowmeter sensors. Sensor types which may be operated with the FMS include but are not limited to the following: I.D.C. fuel flow indicators Canadian Marconi indicators Eldec Flowmeter Transmitters Ragen X & O Engineering Flowmeter Transmitters Gull Airborne Ametek fuel flow indicators Howell fuel flow indicators Simmons Precision transmitters General Electric AC voltage pickoff Learjet/E.T. Fuel Management Computer (Pulse). All Learjet models require J.E.T. S.B. #542-1158-7 Learjet DC Fuel Management Intertechnique Totalizer NOTE: For information on Aircraft Type vs. Fuel Flowmeter Type Reference Chart and Fuel Flow Scaling, refer to the WAAS FMS Configuration Manual, Report No. 3461-01. NOTE: For wiring diagrams, pin assignments and other specific information, refer to the WAAS FMS Interface Manual, Report No. 34-60-53. The information contained herein is subject to the Export Administration Regulation (“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited. 34-60-51 Page 701 10 July 2019