Audio International, Inc.
AV-4595-0x-x Installation & Operation
Document #540158, Rev IR, 10/1999
Page 6 of 18
There is ONLY 16 audio or video sources possible. If more than 16 audio or video
stations are needed, multiple-unit configurations are possible on the RS-485 data bus.
This allows selection of any Audio/Video sources from any station. The number of
possible units in a system is dependent on other modules used within the cabin audio
system – up to eight (8) can be used on the same RS-485 line, yielding a potential of
128 audio and video stations.
2.5
Data Bus Control
2.5.1
There are no controls on the distribution module. Switching control of the unit is
handled by commands via the RS-485 serial data bus.
2.5.2 Programmable
Features
A software program, using an external PC (typically a laptop) and a MSM2912,
designed by Audio International specifically for this task sets the following
configurations:
•
Power-up state for each audio and video station
•
Video Briefer source unit
•
Trim levels for each audio input source
3.0 Installation
3.1
Prior to Installation
The AV-4595-0x-x is a simple module to install. Prior to installation the following items
should be considered:
3.1.1 During the design and layout of the aircraft cabin, careful consideration of the
location of this and all other audio/video modules is necessary. Some of the
items to consider include:
•
Space
•
Proximity to other devices (i.e. source equipment)
•
Available power supply
•
Length of cable runs
•
Environmental conditions (temperature, humidity, etc.)
•
Location of other aircraft systems (i.e. oxygen delivery)
•
Access for service repair (if applicable)
•
Convenience for user interface (if applicable)
3.1.2 The module shall be installed to conform to the standards designated by the
customer, installing agency, or other specified requirements.
3.1.3 Prior to installation, select a mounting location for the AV-4595-0x-x. User
access is NOT a consideration when placing unit into the suitable mounting
location. Refer to Section 7.0 for dimensions and attachment points. The unit
shall be bonded to the aircraft frame.
3.2
Unpacking and Inspection
