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1、 AN DOCUMENT Prepared by AIRLINES ELECTRONIC ENGINEERING COMMITTEE Published by AERONAUTICAL RADIO, INC. 2551 RIVA ROAD, ANNAPOLIS, MARYLAND 21401-7435 CABIN EQUIPMENT INTERFACES (CEI) PART 4C CABIN MANAGEMENT AND ENTERTAINMENT SYSTEM CABIN DISTRIBUTION SYSTEM 2ND GENERATION DAISY CHAIN ARINC SPECIF
2、ICIATION 628P4C PUBLISHED: September 15, 2005 This document is based on material submitted by various participants during the drafting process. Neither AEEC nor ARINC has made any determination whether these materials could be subject to valid claims of patent, copyright or other proprietary rights
3、by third parties, and no representation or warranty, express or implied, is made in this regard. Any use of or reliance on this document shall constitute an acceptance thereof “as is” and be subject to this disclaimer. 2005 BY AERONAUTICAL RADIO, INC. 2551 RIVA ROAD, ANNAPOLIS, MARYLAND 21401-7435 U
4、SA Prepared by the Airlines Electronic Engineering Committee Specification 628P4C Adopted by the Airlines Electronic Engineering Committee April 26, 2005 ARINC SPECIFICATION 628P4C CABIN EQUIPMENT INTERFACES (CEI) PART 4C CABIN MANAGEMENT AND ENTERTAINMENT SYSTEM CABIN DISTRIBUTION SYSTEM 2ND GENERA
5、TION DAISY CHAIN Published: September 15, 2005 -,-,- ii FOREWORD Aeronautical Radio, Inc., the AEEC, and ARINC Standards Aeronautical Radio, Inc. (ARINC) was incorporated in 1929 by four fledgling airlines in the United States as a privately-owned company dedicated to serving the communications need
6、s of the air transport industry. Today, the major U.S. airlines remain the Companys principal shareholders. Other shareholders include a number of non-U.S. airlines and other aircraft operators. ARINC sponsors aviation industry committees and participates in related industry activities that benefit
7、aviation at large by providing technical leadership and guidance and frequency management. These activities directly support airline goals: promote safety, efficiency, regularity, and cost-effectiveness in aircraft operations. The Airlines Electronic Engineering Committee (AEEC) is an international
8、body of airline technical professionals that leads the development of technical standards for airborne electronic equipment-including avionics and in-flight entertainment equipment-used in commercial, military, and business aviation. The AEEC establishes consensus-based, voluntary form, fit, functio
9、n, and interface standards that are published by ARINC and are known as ARINC Standards. The use of ARINC Standards results in substantial benefits to airlines by allowing avionics interchangeability and commonality and reducing avionics cost by promoting competition. There are three classes of ARIN
10、C Standards: a) ARINC Characteristics Define the form, fit, function, and interfaces of avionics and other airline electronic equipment. ARINC Characteristics indicate to prospective manufacturers of airline electronic equipment the considered and coordinated opinion of the airline technical communi
11、ty concerning the requisites of new equipment including standardized physical and electrical characteristics to foster interchangeability and competition. b) ARINC Specifications Are principally used to define either the physical packaging or mounting of avionics equipment, data communication standa
12、rds, or a high-level computer language. c) ARINC Reports Provide guidelines or general information found by the airlines to be good practices, often related to avionics maintenance and support. The release of an ARINC Standard does not obligate any airline or ARINC to purchase equipment so described
13、, nor does it establish or indicate recognition or the existence of an operational requirement for such equipment, nor does it constitute endorsement of any manufacturers product designed or built to meet the ARINC Standard. In order to facilitate the continuous product improvement of this ARINC Sta
14、ndard, two items are included in the back of this volume: An Errata Report solicits any corrections to the text or diagrams in this ARINC Standard. An ARINC IA Project Initiation/Modification (APIM) form solicits any recommendations for addition of substantive material to this volume which would be
15、the subject of a new Supplement. -,-,- ARINC SPECIFICATION 628 PART 4C TABLE OF CONTENTS iii 1.0 INTRODUCTION AND DESCRIPTION 1 1.1 Purpose of this Document 1 1.2 Related Documents . 1 1.3 Cabin Distribution System Description. 4 1.3.1 Data Network 4 1.3.2 Power Network 4 1.3.3 Cabin Electronics Com
16、partment 5 1.3.4 Remote Control Center . 5 1.3.5 Electronics/Avionics Bay . 5 1.4 Cable Assembly Letters/Legend 6 1.5 Differences Concerning Single-Aisle Aircraft . 6 2.0 POWER NETWORK 7 2.1 Introduction 7 2.2 Unit Specification. 9 2.2.1 Area Distribution Box (ADB) 9 2.2.2 Cabin Electronics Compartm
17、ent (CEC). 9 2.2.3 Master Control Unit (MCU) 9 2.2.3.1 Design Requirements 9 2.2.3.1.1 Function . 9 2.2.3.1.2 Optional Function . 10 2.2.3.1.3 Mechanical Connection 10 2.2.3.1.4 Electrical Power 12 2.2.3.1.4.1 Power Supply. 12 2.2.3.1.4.1.1 Power Switching Device 12 2.2.3.1.4.1.2 Circuit Protection.
18、 12 2.2.1.1.4.1.3 Power Cut-Off . 14 2.2.3.1.4.2 Ground Fault Interrupt (GFI) 16 2.2.3.1.5 MCU Data Interfaces 17 2.2.3.1.5.1 Discretes 17 2.2.3.1.5.1.1 PED Power Discretes 17 2.2.3.1.5.1.1.1 Other Discretes. 18 2.2.3.1.5.2 Data for In-Seat Systems. 19 2.2.3.1.5.2.1 PED Power Limit P2 20 2.2.3.1.5.2
19、.2 Signal Characteristics 20 2.2.3.1.5.2.3 DTMF Symbols and Coding 21 2.2.3.1.5.3 Data Bus Interfaces . 24 2.2.3.1.5.3.1 MCU Pin-Coded Address . 25 -,-,- ARINC SPECIFICATION 628 PART 4C TABLE OF CONTENTS iv 2.2.3.1.5.3.2 MCU IFE: Ethernet Interface.25 2.2.3.1.6 Configuration Module (CM).25 2.2.3.1.7
20、 Default Parameters.26 2.2.3.1.8 Built-in Test Equipment.27 2.2.3.1.9 Indicators 27 2.2.3.1.10 Connectors Definition28 2.2.3.1.10.1 Column Output Connector J1, J2, J3, J4, J528 2.2.3.1.10.2 Connector J630 2.2.3.1.10.3 Connector J732 2.2.3.1.10.4 Input Power Connector J832 2.2.3.1.10.5 Connector J933
21、 2.2.3.1.11 Size.34 2.2.3.1.12 Maximum Mass and Center of Gravity 34 2.2.4 Power Floor/Wall Disconnect (PFD/PWD).34 2.2.4.1 Mechanical Interface.34 2.2.4.2 Electrical Interface 34 2.2.5 Seat Electronic Box (SEB).35 2.2.5.1 Mechanical Interface.35 2.2.5.2 Electrical Interface.35 2.2.6 Tapping Unit (T
22、U)36 2.2.7 Display Unit (DU).36 3.0 DATA NETWORK37 3.1 Introduction 37 3.2 Unit Specification39 3.2.1 Cabin Electronics Compartment (CEC) .39 3.2.1.1 Mechanical Interface.39 3.2.1.2 Electrical Interface 39 3.2.2 Master Control Unit (MCU) 39 3.2.3 Area Distribution Box (ADB) 39 3.2.3.1 Mechanical Int
23、erface.39 3.2.3.2 Electrical Interface 41 3.2.3.2.1 Connectors .41 3.2.3.2.2 Pin Arrangement.41 3.2.4 Floor/Wall Disconnect Interface (FDI/WDI)43 3.2.4.1 Mechanical Interface.43 3.2.4.2 Electrical Interface 44 3.2.4.2.1 Connectors .44 ARINC SPECIFICATION 628 PART 4C TABLE OF CONTENTS v 3.2.4.2.2 Pin
24、 Arrangement 44 3.2.5 Seat Electronic Box (SEB) 45 3.2.5.1 Mechanical Interface 45 3.2.5.2 Electrical Interface 45 3.2.6 Tapping Unit (TU) . 46 3.2.6.1 Mechanical Interface 46 3.2.6.2 Electrical Interface 48 3.2.7 Display Unit (DU) 50 3.2.7.1 Mechanical Interface 50 3.2.7.2 Electrical Interface 50 3
25、.2.8 Flight Crew Rest (FCR). 50 3.2.8.1 Mechanical Interface 50 3.2.8.2 Electrical Interface 50 4.0 CONNECTIONS 51 4.1 Wiring Specification. 51 4.1.1 Wiring Between A/C Power Supply and ADB 51 4.1.2 Wiring Between A/C Power Supply and MCU . 51 4.1.3 Wiring Between MCU and PFD/PWD 52 4.1.4 Wiring Bet
26、ween PFD/PWD and SEB 52 4.1.5 Wiring Between SEB (power) and SEB (power) 53 4.1.6 Wiring Between MCU and TU. 53 4.1.7 Wiring Between TU and TU 54 4.1.8 Wiring Between TU and DU 55 4.1.9 Wiring Between CEC and MCU. 55 4.1.10 Wiring Between MCU and MCU 56 4.1.11 Wiring Between CEC and ADB . 56 4.1.12
27、Wiring Between ADB and ADB . 57 4.1.13 Wiring Between ADB and FDI/WDI. 57 4.1.14 Wiring Between FDI/WDI and SEB. 58 4.1.15 Wiring Between SEB (data) and SEB (data) . 59 4.1.16 Wiring Between ADB and TU 60 4.1.17 Wiring Between ADB and FCR (Prov.) 60 5.0 SINGLE-AISLE CONFIGURATION . 61 5.1 Introducti
28、on 61 5.2 Differences in the CDS 61 5.2.1 Area Distribution Box (S/A) . 64 ARINC SPECIFICATION 628 PART 4C TABLE OF CONTENTS vi 5.2.2 Tapping Unit65 5.2.3 Single-Aisle Connections.66 5.2.3.1 S/A-Wiring Between A/C Power Supply and ADB.66 5.2.3.2 S/A-Wiring Between A/C Power Supply and TU66 5.2.3.3 S
29、/A-Wiring Between TU and TU .67 5.2.3.4 S/A-Wiring Between TU and DU.67 5.2.3.5 S/A-Wiring Between CEC and MCU68 5.2.3.6 S/A-Wiring Between CEC and ADB 68 5.2.3.7 S/A-Wiring Between ADB and ADB 69 5.2.3.8 S/A-Wiring Between ADB and FDI/WDI69 5.2.3.9 S/A-Wiring Between CEC and TU.70 6.0 IFE TO MCU DA
30、TA COMMUNICATION INTERFACE .71 6.1 Introduction 71 6.1.1 Scope71 6.1.2 Definition and Terms72 6.1.3 Naming Convention.74 6.2 Interfaces and Protocol 74 6.2.1 Protocol Layers75 6.2.2 Subnet Addresses .76 6.3 MIB Structure and Definition.77 6.3.1 MCU MIB Structure77 6.3.2 MCU MIB Definition .79 6.3.3
31、Trap Definition.79 6.4 System Communication Synchronization .80 ATTACHMENTS 1 MCU PRIVATE MIB DEFINITION 87 APPENDICES A List of Acronyms.115 B Link Margin Analysis instructions117 C Wiring Diagram Symbols118 ARINC Standard Errata Report ARINC IA Project Initiation/Modification (APIM) -,-,- ARINC SP
32、ECIFICATION 628 Part 4C - Page 1 1.0 INTRODUCTION 1.1 Purpose of this Document ARINC Specification 628 defines general architectural philosophy and aircraft infrastructure for the proper use and interface of various cabin related IFE equipment. Consistency with ARINC Specification 628 allows each re
33、spective system to operate in concert when integrated with other relevant cabin equipment. ARINC Specification 628 Part 4 defines standards for the aircraft IFE Cabin Distribution System (CDS) wiring, connectors, power, identification codes, space envelopes and mounting principles. The equipment its
34、elf is not a subject of this specification because it may be unique to the system manufacturer or marketplace- driven. Design guidelines are included for informational purposes as these guidelines impact the interfaces and installation of cabin equipment aboard the aircraft. The CDS, in daisy chain
35、architecture, is the content of both Parts 4A and 4C of ARINC Specification 628. Part 4C presents the second generation also known as 2GCN of the daisy chain topology, as an evolution based on the experience gained with the first version of the CDS. The main difference is that the system in Part 4C
36、is divided into two separated networks, one for data, connected to the CEC, and the other one for power, connected to the Aircraft Power Supply. The second generation of the CDS was mainly introduced because of the need for more bandwidth (via quad-cables) and a newer version of the MCU, which allow
37、s for greater control over power distribution. Fiber-optic cables are not defined, because the new quad-cables were deemed more than sufficient for the expected bandwidths. The primary reason for the separation of data and power was the limiting factor of the power lines. If both data and power are
38、bound together in one cable, the whole network would be constrained by the limits arising from maximum distances or number of supplied components resulting from both of them (mainly power). When separating power and data from each other, both networks do not have to be identical and can be optimized
39、 individually, allowing for better overall performance and fewer components. The detailed separation of data and power is described in Sections 2.0 and 3.0. Functional improvements are capable of being performed through the addition or enhancement of modules without modification on the aircraft. The
40、 CDS should be designed to support an airplane configuration, but scaleable to all commercial aircraft types. A generic configuration of cabin subsystems interconnection is shown in the block diagrams of ARINC Specification 628: Cabin Equipment Interfaces (CEI), Part 1, Cabin Management and Entertai
41、nment System Peripherals and ARINC Specification 628: Cabin Equipment Interfaces (CEI), Part 2, Cabin Management and Entertainment Systems - Seat Interfaces. The block diagrams also include connection with avionics that contribute to the operation of the cabin. 1.2 Related Documents This document is
42、 intended to be used in conjunction with ARINC Specification 628, “Cabin Equipment Interfaces, Parts 1, 2, 3, and 5, Cabin Management and Entertainment System.” Part 1 defines the interfaces between cabin management -,-,- ARINC SPECIFICATION 628 Part 4C - Page 2 1.0 INTRODUCTION and entertainment sy
43、stems and selected peripheral equipment. Part 2 defines the interfaces of the seat-mounted equipment. Part 3 defines the electrical interface between the CDS and the aircraft. Part 5 defines the in-seat wiring installation practices. The latest revision of the following documents is pertinent to the
44、 design of equipment intended to meet this standard. AC 43.13: Acceptable Methods, Techniques, and Practices-Aircraft Inspection and Repair ARINC Specification 413: Guidance for Aircraft Electrical Power Utilization reset of connected electrical systems - controlled by IFE or via other control panel
45、s). ON status means: Switching device(s) closed and power available at all outputs. OFF status means: Switching device(s) open and no power at all outputs. 2. LEVEL 2 - Column level: Switching the power of any of the five MCU ports. (Example for possible use: switching because of maintenance; reset
46、of in-seat systems - controlled by IFE or via other control panels). ON status means: Switching device(s) closed and power available at the selected output(s). OFF status means: Switching device(s) open and no power at the selected output(s). ARINC SPECIFICATION 628 Part 4C - Page 15 2.0 POWER NETWO
47、RK The MCU output power should be switchable on both levels (MCU level and Column level) via following signals: 1. Six Discrete Inputs at each MCU a. One discrete for switching on MCU level b. Five discretes for switching each MCU port separately 2. Keyline discrete(s) a. Ground signal means MCU/por
48、t power cut-OFF b. Open signal means MCU/port power ON 3. Data signals via data bus (refer to Section 2.2.3.1.5.3.2) During power up there should be, as default condition, no power available at the five MCU ports. After a successful BITE test, the devices (e.g., contactor(s) are closed and the columns are powered. Two possible switching realizations could be considered in the design: 1. One type of power switching device for switching on LEVEL 1 and LEVEL 2: a. If the (five) power switching devices of the columns (LEVEL 2), described under Section 2.2.3.1.4.2.1, are als