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34-60-51 UNS-1Fw

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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.
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Page ROR-1
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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.
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Page ROTC-1
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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.
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UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual
List of Effective Pages
SUBJECT
PAGE
Title Page
DATE
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Record of Revisions
1
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Record of Temporary
Changes
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List of Effective Pages
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Table of Contents
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Description and
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SUBJECT
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UNS-1Fw Flight Management System SCN 1000/1100 Installation Manual
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System Data
Installation
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(“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited.
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Navigation Systems
601
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Fuel Flow Inputs
701
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The information contained herein is subject to the Export Administration Regulation
(“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited.
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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.
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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
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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
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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
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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
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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
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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(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.
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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
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34-60-51
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
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.
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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.
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(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.
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
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.
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(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.
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(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.
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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.
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(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.
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(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.
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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.
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(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.
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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.
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
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.
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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,
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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.
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
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.
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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.
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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.
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(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.
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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.
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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.
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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.
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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.
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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.
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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
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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
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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
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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
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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
-55C/-15C
4.5.2
4.5.3
A2E1
A2E1
-15C,-20C
+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
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
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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
-20C Operating, -55C Survival
A1D1
+55C Operating, +85C Survival (+70C 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.
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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
-15C Operating, -55C Survival
+55C Operating, +85C Survival (+70C 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
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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
+55C Operating, +85C Survival (+70C 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
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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
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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
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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
-20C Operating, -55C Survival
Low Operating Temperature
4.5.2
A1D1
+55C Operating, +85C 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
+55C Operating, +85C 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
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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
-55C/-40C
4.5.2
4.5.3
A2E1
A2E1
-20C
+70C
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
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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
0C
4.5.3
C4
+70C
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.
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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
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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
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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
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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
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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.
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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.
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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
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(“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited.
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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.
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<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.
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(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.
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The information contained herein is subject to the Export Administration Regulation
(“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited.
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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
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(“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited.
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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.
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(“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited.
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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).
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(“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited.
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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.
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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.
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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.
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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.
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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
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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
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(“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited.
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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
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(“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited.
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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
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(“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited.
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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
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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.
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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
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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.
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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
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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)
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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.
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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.
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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
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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
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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
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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
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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
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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
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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
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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
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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
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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
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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
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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
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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
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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
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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
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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.
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(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.
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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.
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The information contained 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)
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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
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L
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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.
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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.
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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.
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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.
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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.
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(“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited.
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(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)
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(“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited.
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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.
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(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.
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(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.
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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.
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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.
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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.
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(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.
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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.
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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
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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.
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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)
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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)
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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)
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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.
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(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
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(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
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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.
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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.
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(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
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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
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(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.
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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
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(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
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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
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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
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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
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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)
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(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)
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(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
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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
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(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
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(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)
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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)
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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
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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
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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
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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
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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)
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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
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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
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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.
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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.
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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
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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 (-)
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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
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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.
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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.
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(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.
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(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.
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(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.
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(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.
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(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.
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(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.
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(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.
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(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.
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(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.
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(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.
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(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.
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(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.
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(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.
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(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.
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(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.
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(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.
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(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.
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(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.
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(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.
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(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.
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(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.
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(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.
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(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.
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(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.
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(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.
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(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.
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(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.
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(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.
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(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.
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(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.
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(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.
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(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.
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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
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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.
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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.
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(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.
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(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:
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(“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited.
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(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.
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(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:
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(“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited.
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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.
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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.
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(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.
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(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.
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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:
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(“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited.
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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.
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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:
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(“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited.
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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:
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(“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited.
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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.
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(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:
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(“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited.
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(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:
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(“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited.
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(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:
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(“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited.
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(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.
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(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.
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(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.
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(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:
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(“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited.
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(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:
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(“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited.
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(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:
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(“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited.
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(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:
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(“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited.
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(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.
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(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.
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(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.
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(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.
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(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.
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(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.
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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.
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(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.
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(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.
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(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
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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.
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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.
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(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
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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.
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(“EAR”), 15 C.F.R. Parts 730-774. Diversion contrary to U.S. law is prohibited.
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(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
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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
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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
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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.
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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
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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
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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
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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.
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(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.
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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.
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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.
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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
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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.
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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.
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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.
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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
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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.
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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.
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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
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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
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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.
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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.
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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
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(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
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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™.ƒm
¬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®
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(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™.ƒm
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™.ƒm
x´+º™.ƒm
¬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
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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.
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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.
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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.
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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.
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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.
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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.
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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
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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
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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.
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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
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