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number of avionics systems.
ARINC 429 Tutorial ARINC 429 Electrical Characteristics
ARINC Protocol Tutorial 3
ARINC 429 Usage
ARINC 429 has been installed on most commercial transport aircraft
including; Airbus A310/A320 and A330/A340; Bell Helicopters; Boeing
727, 737, 747, 757, and 767; and McDonnell Douglas MD-11. Boeing is
installing a newer system specified as ARINC 629 on the 777, and some
aircraft are using alternate systems in an attempt to reduce the weight of
wire needed and to exchange data at a higher rate than is possible with
ARINC 429. The unidirectional ARINC 429 system provides high
reliability at the cost of wire weight and limited data rates. Military aircraft
generally use a high-speed, bi-directional protocol specified in Military
Specifications MIL-STD-1553.
Each aircraft may be equipped with different electronic equipment and
systems needing interconnection. A large amount of equipment may be
involved depending on the aircraft. These are identified in the
specification and are assigned digital identification numbers called
Equipment ID. A partial list of equipment identified in ARINC
Specification 429-15 can be found in Table 1 along with their digital
addresses.
The specification also identifies a number of systems, which are capable of
interchanging files of data in a bit-oriented format. Such files may require
the transmission of a number of messages in sequence. Systems capable of
bit-oriented communications and their addresses are listed in Table 10.
The SAL is used to identify the recipient of a bit oriented message.
ARINC 429 Electrical Characteristics
An ARINC 429 data bus uses two signal wires to transmit 32 bit words.
Transmission of sequential words is separated by at least 4 bit times of
NULL (zero voltage). This eliminates the need for a separate clock signal
wire. That’s why this signal is known as a self-clocking signal.
The nominal transmission voltage is 10 ±1 volts between wires
(differential), with either a positive or negative polarity. Therefore, each
signal leg ranges between +5V and -5V. If one leg is +5V, the other is -5V
and vice versa. One wire is called the “A” (or “+” or “HI”) side and the
other is the “B” (or “-” or “LO”) side. This is known as bipolar return-tozero
(BPRZ) modulation. The composite signal state may be one of three
levels:
HI which should measure between 7.25 and 11 volts between the two
wires (A to B).
NULL which should be between 0.5 and -0.5 (A to B).
LO which should be between -7.25 and -11 volts (A to B).
ARINC 429 Electrical Characteristics ARINC 429 Tutorial
4 ARINC Protocol Tutorial
The received voltage depends on line length and the number of receivers
connected to the bus. No more than 20 receivers should be connected to a
single bus. Since each bus is unidirectional, a system needs to have its own
transmit bus if it is required to respond or to send messages.
Table 1. Partial List of Equipment IDs
Eq. ID Equipment Type Eq. ID Equipment Type
001 Flight Control Computer (701) 029 ADDCS (729) and EICAS
002 Flight Management Computer (702) 02A Thrust Management Computer
003 Thrust Control Computer (703) 02B Perf. Nav. Computer System (Boeing 737)
004 Inertial Reference System (704) 02C Digital Fuel Gauging System (A310)
005 Attitude and Heading Ref. System (705) 02D EPR Indicator (Boeing 757)
006 Air Data system (706) 02E Land Rollout CU/Landing C & LU
007 Radio Altimeter (707) 02F Full Authority EEC-A
008 Airborne Weather Radar (708) 030 Airborne Separation Assurance System
009 Airborne DME (709) 031 Chronometer (731)
00A FAC (A310) 032 Passenger Entertain. Tape Reproducer
(732)
00B Global Positioning System 033 Propulsion Multiplexer (PMUX) (733)
00D AIDS Data Management System 034 Fault Isolation and Detection System (734)
010 Airborne ILS Receiver (710) 035 TCAS (735)
011 Airborne VOR Receiver (711) 036 Radio Management System (736)
012 Airborne ADF System (712) 037 Weight and Balance System (737)
016 Airborne VHF COM Receiver (716) 038 ADIRS (738)
017 DEFDARS-AIDS (717) 039 MCDU (739)
018 ATC Transponder (718) 03A Propulsion Discrete Interface Unit
019 Airborne HF/SSB System (719) 03B Autopilot Buffer Unit
01A Electronic Supervisory Control 03C Tire Pressure Monitoring System
01B Digital Flap/Slat Computer (A310) 03D Airborne Vibration Monitor (737/757/767)
01C Engine Parameter Digitizer (Engine) 03E Center of Gravity Control Computer
01D A/P & F/D Mode Control Panel -757/767 03F Full Authority EEC-B
01E Performance Data Computer (Boeing) 040 Cockpit Printer
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