Page 2 - HONEYWELL; Aerospace Electronic Systems
HONEYWELL Aerospace Electronic Systems Page 2 Use or disclosure of information on this page is subject to the restrictions on the title page of this document.
Page 3 - INTRODUCTION; Design the screen layouts
HONEYWELL Aerospace Electronic Systems Page 3 Use or disclosure of information on this page is subject to the restrictions on the title page of this document. 1 INTRODUCTION 1.1 Mark III CMU Overview Honeywell provides a family of Datalink products, ranging from the AFIS product for the business Jet...
Page 4 - Datalink Capability for Today and Tomorrow
HONEYWELL Aerospace Electronic Systems Page 4 Use or disclosure of information on this page is subject to the restrictions on the title page of this document. • Define uplink and downlink message formats • Define the format of printed messages • Specify trigger logic (i.e., OOOI) • Define the geogra...
Page 7 - SYSTEM OVERVIEW
HONEYWELL Aerospace Electronic Systems Page 7 Use or disclosure of information on this page is subject to the restrictions on the title page of this document. 2 SYSTEM OVERVIEW 2.1 Hardware Overview The Mark III CMU is based upon the Multiple Application Processing System (MAPS) platform which is th...
Page 8 - System Interfaces
HONEYWELL Aerospace Electronic Systems Page 8 Use or disclosure of information on this page is subject to the restrictions on the title page of this document. Figure 1 Mark III CMU Front Panel ARINC 607 defines the Aircraft Personality Module (APM) which contains all aircraft and systemconfiguration...
Page 10 - UHF
HONEYWELL Aerospace Electronic Systems Page 10 Use or disclosure of information on this page is subject to the restrictions on the title page of this document. Satellite Communications (SATCOM) The Mark III CMU can be configured to interface with one or two ARINC 741 compliant Satellite Data Units(S...
Page 11 - Printer; MCDU; Figure 4 Cockpit Printer
HONEYWELL Aerospace Electronic Systems Page 11 Use or disclosure of information on this page is subject to the restrictions on the title page of this document. Control and Display Unit (CDU) In the business jet and regional aircraft market place, there is limited cockpit pedestal real estate. Often,...
Page 12 - Figure 5 CMU/PZ Pass Through Interface; CDU
HONEYWELL Aerospace Electronic Systems Page 12 Use or disclosure of information on this page is subject to the restrictions on the title page of this document. 2.2.3 LRU Interfaces In general, the Mark III CMU can support any LRU that uses the ARINC 429 File Data Transfer Protocol orWilliamsburg Pro...
Page 13 - Cabin Terminal; The Mark III CMU also supports the following interfaces:; Dual CMU
HONEYWELL Aerospace Electronic Systems Page 13 Use or disclosure of information on this page is subject to the restrictions on the title page of this document. an extensive amount of ARINC 429 broadcast data providing aircraft performance related data. All of theARINC 429 broadcast data is available...
Page 14 - Ethernet; Software Overview
HONEYWELL Aerospace Electronic Systems Page 14 Use or disclosure of information on this page is subject to the restrictions on the title page of this document. future to define Warm and Hot spare requirements. This effort has not yet started. As the Mark III CMUhardware was designed to support Dual ...
Page 15 - Platforms; Mark III
HONEYWELL Aerospace Electronic Systems Page 15 Use or disclosure of information on this page is subject to the restrictions on the title page of this document. through an automated code generation system specific to the target environment. Automated test scriptsare also derived from the model databa...
Page 18 - FUNCTIONAL OVERVIEW; level; Service Function; Not specified at this time
HONEYWELL Aerospace Electronic Systems Page 18 Use or disclosure of information on this page is subject to the restrictions on the title page of this document. 3 FUNCTIONAL OVERVIEW The Mark III CMU is designed to provide complete datalink capability, providing interfaces and support totoday’s insta...
Page 19 - Application Functions; ACARS End System; Uplink Processing
HONEYWELL Aerospace Electronic Systems Page 19 Use or disclosure of information on this page is subject to the restrictions on the title page of this document. A758 Level Application Functions A Airline/AOC Applications and ATS Messages ACARS End System ARINC 620: AOC ARINC 620: AAC ARINC 623: ATIS ...
Page 20 - Downlink Processing
HONEYWELL Aerospace Electronic Systems Page 20 Use or disclosure of information on this page is subject to the restrictions on the title page of this document. Once an AOC message has been viewed by the flight crew (and any required user action has been taken), itcan be placed in one of 8 user defin...
Page 22 - Growth Functionality; VDL Mode 2; Honeywell APM
HONEYWELL Aerospace Electronic Systems Page 22 Use or disclosure of information on this page is subject to the restrictions on the title page of this document. • Maintenance Memory Integrity: Verify that faults that are written to the maintenance memory arecorrectly retained in memory. • Over-temper...
Page 24 - ATN; RRI
HONEYWELL Aerospace Electronic Systems Page 24 Use or disclosure of information on this page is subject to the restrictions on the title page of this document. support as part of the baseline the text Weather uplinks which has become standard use within the Airtransport industry. ATN The industry ha...
Page 26 - DATABASES
HONEYWELL Aerospace Electronic Systems Page 26 Use or disclosure of information on this page is subject to the restrictions on the title page of this document. 4 DATABASES Honeywell pioneered the concept of airline reconfiguration and partitioned software for datalink systems inthe early 1990s. The ...
Page 27 - Figure 10 FIDB Architecture; GEX; Master FIDB; Customer Aircraft Types:; APM
HONEYWELL Aerospace Electronic Systems Page 27 Use or disclosure of information on this page is subject to the restrictions on the title page of this document. Figure 10 FIDB Architecture The FIDB defines the same name for a given aircraft parameter (i.e., Air_Speed) regardless of aircraft type.In t...
Page 29 - Figure 12 Main Menu
HONEYWELL Aerospace Electronic Systems Page 29 Use or disclosure of information on this page is subject to the restrictions on the title page of this document. 4.2.1 Menus Since the AOC application is completely customizable, the user can define the set of menus that navigatethrough the various AOC ...
Page 30 - Figure 13 Main Menu Page 2
HONEYWELL Aerospace Electronic Systems Page 30 Use or disclosure of information on this page is subject to the restrictions on the title page of this document. Screens, including menus, can consist of multiple (up to 9) pages. Note the 1/2 in the upper right corner ofthe Main Menu display indicating...
Page 31 - Figure 14 CDU Main Menu (Supporting Regional / Business Jet CDUs)
HONEYWELL Aerospace Electronic Systems Page 31 Use or disclosure of information on this page is subject to the restrictions on the title page of this document. The GBST supports the screen layouts for both the standard ARINC 739 14 line MCDU/MIDU as well assupporting Honeywell’s 9 line CDU (used on ...
Page 32 - Figure 15 ATS Menu
HONEYWELL Aerospace Electronic Systems Page 32 Use or disclosure of information on this page is subject to the restrictions on the title page of this document. This discussion of the GBST and how it is used is equally applicable to both the AMI and the HGI. However,the HGI is only modifiable by Hone...
Page 33 - Figure 16 System Menu
HONEYWELL Aerospace Electronic Systems Page 33 Use or disclosure of information on this page is subject to the restrictions on the title page of this document. In addition to the AOC screens defined by the AMI, and ATC screens defined by the HGI, there areadditional menus screens within the Mark III...
Page 34 - Figure 17 Clearance Uplink
HONEYWELL Aerospace Electronic Systems Page 34 Use or disclosure of information on this page is subject to the restrictions on the title page of this document. 4.2.2 Uplinks For uplink messages, the user can define both the screen layout and the uplink message format. Figure 17depicts an example scr...
Page 35 - Figure 18 Clearance Message Elements
HONEYWELL Aerospace Electronic Systems Page 35 Use or disclosure of information on this page is subject to the restrictions on the title page of this document. When defining the format and characteristics of an uplink message (i.e., the decoding), the user can specifythe elements within the message ...
Page 36 - Figure 19 Clearance Message References
HONEYWELL Aerospace Electronic Systems Page 36 Use or disclosure of information on this page is subject to the restrictions on the title page of this document. Figure 19 Clearance Message References If a crew response is required, the user would typically create response action prompts, such as theA...
Page 37 - Figure 20 Reject Reasons
HONEYWELL Aerospace Electronic Systems Page 37 Use or disclosure of information on this page is subject to the restrictions on the title page of this document. The user can also specify a REJECT REASONS action prompt, which allows the flight crew to specify thereason for rejecting the Clearance (see...
Page 38 - Figure 21 Reject Reasons Values
HONEYWELL Aerospace Electronic Systems Page 38 Use or disclosure of information on this page is subject to the restrictions on the title page of this document. There are a number of different types of objects that can be placed on a display. As an example, for theMain Menu, page prompts are used to ...
Page 39 - Figure 22 Diversion Report Downlink
HONEYWELL Aerospace Electronic Systems Page 39 Use or disclosure of information on this page is subject to the restrictions on the title page of this document. 4.2.3 Downlinks The definition of the AOC downlinks is created using the GBST. The definition of downlink message screensand associated mess...
Page 40 - Figure 23 Diversion Reasons
HONEYWELL Aerospace Electronic Systems Page 40 Use or disclosure of information on this page is subject to the restrictions on the title page of this document. Like the Reject Reasons page, the Diversion Report Downlink display contains a scrolling prompt and aconditional display field that is only ...
Page 41 - Figure 24 Divert Message Elements
HONEYWELL Aerospace Electronic Systems Page 41 Use or disclosure of information on this page is subject to the restrictions on the title page of this document. Figure 24 Divert Message Elements Figure 25 Divert Properties
Page 42 - Figure 26 Print Format
HONEYWELL Aerospace Electronic Systems Page 42 Use or disclosure of information on this page is subject to the restrictions on the title page of this document. 4.2.4 Print Definition The user can define the print format for a message by specifying the field names and associatedparameters. Figure 26 ...
Page 43 - Figure 27 OOOI Logic Unit
HONEYWELL Aerospace Electronic Systems Page 43 Use or disclosure of information on this page is subject to the restrictions on the title page of this document. Logic units can be used to specify OOOI conditions. OOOI logic can be as simple or as complex as theuser requires. Figure 27 depicts a porti...
Page 44 - Figure 28 Regions
HONEYWELL Aerospace Electronic Systems Page 44 Use or disclosure of information on this page is subject to the restrictions on the title page of this document. to use for message transmission. The user also can specify the set of VHF frequencies to use for thatregion. Figure 28 shows an example. Fig...
Page 45 - Figure 29 US Map
HONEYWELL Aerospace Electronic Systems Page 45 Use or disclosure of information on this page is subject to the restrictions on the title page of this document. Figure 29 US Map
Page 46 - Figure 30 Areas
HONEYWELL Aerospace Electronic Systems Page 46 Use or disclosure of information on this page is subject to the restrictions on the title page of this document. Figure 30 Areas The Mark III CMU GBST provides the next generation in Airline reconfiguration. It is specifically designed toprovide airline...
Page 47 - HARDWARE DESCRIPTION; Figure 31 MARK III Top View
HONEYWELL Aerospace Electronic Systems Page 47 Use or disclosure of information on this page is subject to the restrictions on the title page of this document. 5 HARDWARE DESCRIPTION 5.1 Mechanical Design The MARK III is a modular design that consists of a number of circuit card assemblies (CCAs) wh...
Page 49 - Detailed Interface Definition
HONEYWELL Aerospace Electronic Systems Page 49 Use or disclosure of information on this page is subject to the restrictions on the title page of this document. • Patented multi-layer microstrip/fiberglass high reliability printed wiring board (PWB • Analog Output Discretes • PCI BUS-based Connector ...
Page 52 - Mechanical Packaging; The MARK III LRU maximum weight is twelve pounds.
HONEYWELL Aerospace Electronic Systems Page 52 Use or disclosure of information on this page is subject to the restrictions on the title page of this document. 5.3 Mechanical Packaging 5.3.1 Unit Weight The MARK III LRU maximum weight is twelve pounds. 5.3.2 Unit Size The MARK III LRU is a 4-MCU box...
Page 53 - Environmental Specifications
HONEYWELL Aerospace Electronic Systems Page 53 Use or disclosure of information on this page is subject to the restrictions on the title page of this document. 5.4 Environmental Specifications The following DO-160D categories will be used for the MARK III: Temperature and Altitude (DO-160D Section 4...
Page 54 - RRR
HONEYWELL Aerospace Electronic Systems Page 54 Use or disclosure of information on this page is subject to the restrictions on the title page of this document. Waterproofness (DO-160D Section 10.0) Category X, Not Applicable Fluids Susceptibility (DO-160D Section 11.0) Category X, Not Applicable San...
Page 55 - Power Requirements
HONEYWELL Aerospace Electronic Systems Page 55 Use or disclosure of information on this page is subject to the restrictions on the title page of this document. Category A2, Pin Injection Tests (DO-160C Section 22.5.1)Waveform 3 (DO-160D Section 22, Figure 22-4), Voc/Isc = 250V/10A, and Frequency = 1...
Page 56 - 28 Vdc Backup Input Power Requirements
HONEYWELL Aerospace Electronic Systems Page 56 Use or disclosure of information on this page is subject to the restrictions on the title page of this document. Nominal +27.5 Vdc Minimum +20.5 Vdc Maximum +32.2 Vdc Nominal 50 Watts Maximum 100 Watts 5.5.3 28 Vdc Backup Input Power Requirements The MA...
Page 57 - SUMMARY; , ATC unique applications, and the addition of new communication
HONEYWELL Aerospace Electronic Systems Page 57 Use or disclosure of information on this page is subject to the restrictions on the title page of this document. 6 SUMMARY The Mark III CMU is a high-end system which provides the latest in both hardware and software technology,unequalled in the industr...
