AeroVonics AV-30 Manuale utente
D-0031-0, AV-30, Installation Manual
3/21/2019 Page 1 of 17 Revision A
AV-30
Multi-Mode Indicator
Part Number U-1011-0
Installation Manual
(D-0031-0, AV-30, INSTALLATION MANUAL, REV A)
AeroVonics LLC
Albuquerque, New Mexico
D-0031-0, AV-30, Installation Manual
3/21/2019 Page 2 of 17 Revision A
Revisions
Revision
Date
Description of Change
Author
A 3/21/2019 Initial Release for AV-30-E unit. JDB
Table of Contents
1 System Description ...................................................................................................... 3
1.1 Model Applicability ................................................................................................ 4
2 Operating Modes & System Interfaces ........................................................................ 4
2.1 Operating Mode.................................................................................................... 4
2.2 Mode Feature Matrix ............................................................................................ 5
2.3 Equipment Connections ....................................................................................... 6
2.3.1 Power Input (Required) ................................................................................. 6
2.3.2 Pitot and Static Interfaces (Required/Optional) .............................................. 6
2.3.3 Outside Air Temp Input (Optional) ................................................................. 6
2.3.4 Audio Output (Optional)................................................................................. 7
2.3.5 GPS Interface (Optional) ............................................................................... 7
2.3.6 Manufacturing and Spare Ports ..................................................................... 7
3 Certification Basis ........................................................................................................ 8
4 Operating Limits .......................................................................................................... 8
5 System Specifications ................................................................................................. 9
6 Intended Function ........................................................................................................ 9
7 Internal Battery Operation ............................................................................................ 9
8 Installation ..................................................................................................................10
8.1 Overview .............................................................................................................10
8.2 Mechanical Drawing ............................................................................................10
8.3 Mounting Screw Length Restriction .....................................................................11
8.4 Wiring Diagrams ..................................................................................................12
9 Autopilot Integration ....................................................................................................15
10 Setup & Configuration ................................................................................................15
10.1 Pilot Configuration ...............................................................................................15
10.2 Install Configuration .............................................................................................15
11 Instructions for Continued Maintenance & Operation ..................................................16
11.1 Airspeed Calibration ............................................................................................16
11.2 Altitude Calibration ..............................................................................................16
11.3 Internal Battery ....................................................................................................16
11.4 Field Update Capability .......................................................................................17
D-0031-0, AV-30, Installation Manual
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1 System Description
The AeroVonics AV-30 is a highly capable, fully digital, multi-mode instrument that mounts in
the legacy 3 1/8” round instrument panel cutout. It can be field configured as either an
Attitude Indicator (AI) or a Direction Indicator (DG), contains an internal battery and allows
for a wide variety of pilot customization.
Figure 1 - AV-30-C Multi Mode AI/DG
When configured as an AI, primary attitude and slip are always displayed. The un-used
portions of the display area can be customized by the pilot to show a variety of textual and
graphical data-overlay fields. Up to 3 pages may be customized by the pilot with a forth
dedicated fully decluttered page.
When configured as a DG, non-slaved direction of flight or GPS track may be configured for
display. Multiple display presentations, including compass rose, GPS CDI, and GPS arc
view can be selected by the pilot. The un-used portions of the display area can similarly be
configured for a variety of textual data-overlays.
In both operating modes, the pilot may select from a variety of visual styles which are
intended to improve visual compatibility with legacy aircraft instrumentation and preserve the
look-and-feel of older aircraft applications. A wide variety of supplemental functions,
including audio envelope alerting, derived angle of attack presentation, g-load display, and
more are provided. An internal battery allows for operation for up to 2 hours in the event of
aircraft power loss.
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1.1 Model Applicability
The AV-30 is available in the following models:
Model Part Number Applications Modes
AV-30-E U-1011-0 Experimental Aircraft AI & DG
Figure 2 - Model Applicability
The AV-30 supports operation as an Attitude Indicator or a Directional Gyro with the
configuration determined during installation setup, or by pilot selection depending on the
installation configuration.
2 Operating Modes & System Interfaces
2.1 Operating Mode
The operating mode can be set as follows:
Unit locked as an Attitude Indicator (AI Mode)
Unit locked as a Direction Indicator (DG Mode)
Unit can be toggled between AI and DG mode by the pilot
Installations where dedicated functionality is required or desired, should set the
functionality and enable the lock the setting. If the functionality is not locked,
pressing and holding the rotary knob in will toggle between AI and DG mode. The
functionality and lock settings are described later in this document.
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2.2 Mode Feature Matrix
The following table describes the display data and data-overlays that are available in each
operating mode. The required external interfaces are also specified.
Feature AI Mode DG Mode Comment / Required Interface
Data
Blank Overlay Field Field can be left empty
Attitude Available as Rev Mode on DG
Non-Slaved Heading
Bus Voltage
G Load
Outside Air Temp (OAT) Requires Optional OAT Probe
True Airspeed Requires Optional OAT Probe
Density Altitude Requires Optional OAT Probe
Indicated Airspeed
Baro Corrected Altitude
Angle Of Attack
Vertical Trend
Vertical Speed
Set Altitude Reference Only (No AP Interface)
Graphical Course Indication (Non-Slaved Heading, or GPS Track – Pilot Selectable)
Direction Tape Heading or GPS Track
Direction Rose Heading or GPS Track
Direction Arc Heading or GPS Track
Direction CDI Heading or GPS Track
GPS Navigation / Route Data
Textual Nav Data Requires GPS Navigator Interface
Graphical CDI Deviation Requires GPS Navigator Interface
Flight Plan Leg Requires GPS Navigator Interface
Heading Bug
Heading Bug Reference Only (No AP Interface)
Audio and Visual Alerting
AoA Alerting Pitot and Static Pressure
G Limit Alerting
Excessive Roll Alerting
Misc.
Internal Battery
Operation
Auto / Manual
Brightness
Table 1 – Feature Matrix
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2.3 Equipment Connections
All connections are provided on the single 15-Pin D-sub connector and the two pneumatic
fittings. The unit connects to aircraft power via a normal power circuit with a dedicated 2
Amp, pilot resettable breaker. See wiring diagrams for additional information.
2.3.1 Power Input (Required)
Power input is required and connects to the aircrafts power bus. Input range is
compatible with both 12V and 24V aircraft. Internally, this power is diode or’ed with the
internal battery via a processor-controlled switch. This architecture allows the unit to
continue operation if external power fluctuates or is completely lost.
Each AV-30 must have a dedicated, pilot resettable circuit breaker as part of the
installation process. Power for the unit must not be supplied from the “avionics” bus but
instead should be tied to the essential or battery master bus.
2.3.2 Pitot and Static Interfaces (Required/Optional)
In addition to indicated airspeed and altitude, pitot and static inputs used to stabilize the
attitude solution during long-term accelerations such as takeoff and landing. They are
also utilized within the probeless Angle of Attack algorithm and provide the underlying
source for various air-data type data overlays.
If indicated airspeed and altitude are not desired (or available) for display, and potential
performance degradation is acceptable, the pitot and static lines may be left
disconnected. This may be applicable in certain installations, or when installation as a
dedicated DG is being performed.
Industry standard ¼” quick connect fittings are utilized. Reference the wiring diagram
for details on how to release the tubing from the fitting.
2.3.3 Outside Air Temp Input (Optional)
The optional outside air temperature interface requires a dedicated external analog
probe. This port connection is compatible with the Davtron probe analog probe P/N
C307PS (not supplied). This is a simple two-wire current source based on the Analog
Devices AD590KH component and supplies a current that corresponds to the ambient
temperature.
If two displays are connected to the same probe, the current will be split between the
two and incorrect readings will be shown by both.
The sensor reading must be trimmed during the installation process to
compensate for probe-to-probe variations.
Do not tap into an existing OAT system that is in use (the probes may not be
put in parallel or series).
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In a dual installation, dedicated OAT probes may be connected to both the AI and DG
units, but the DG wiring harness is not pre-wired for this connection.
2.3.4 Audio Output (Optional)
The optional audio panel connection is a low-voltage analog output that is designed to
connect directly to an audio panel (typically a non-switched input). High power outputs
capable of directly driving a cockpit speaker are not provided.
When installed as a DG, no audio output is supported.
2.3.5 GPS Interface (Optional)
The optional GPS interface is an RS-232 serial input that is compatible with the industry
standard “Moving Map / Aviation Protocol” output provided by most panel mounted GPS
units and various aviation handhelds. This data does not typically include vertical
guidance nor does it contain appropriate information to perform GPS approaches;
therefore its use is limited to VFR situational awareness use only.
This is a text/binary protocol output by the GPS navigator that contains basic
navigational data such as ground speed, track, distance to destination, cross track, etc.
This serial interface may be connected in parallel between multiple AV-30 units and is
supported in both the AI and DG modes.
2.3.6 Manufacturing and Spare Ports
A dedicated RS-232 bi-directional serial port is provided for manufacturing test and
calibration purposes, in addition to serial ports for future expansion purposes. These
lines are not connected in the aircraft installation.
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3 Certification Basis
The AV-30-E (Part Number U-1011-0) is to be used for experimental aircraft applications
only.
4 Operating Limits
Operating Limits
Angle of Attack Range 0° to +30°
Angle of Attack Resolution 1°
Angle of Attack Operation +35 to +300 Knots
Angle of Attack Accuracy 2.5°
Density Alt Range (Accuracy) -1,000 to +25,000 Feet (± 500ft)
TAS Range (Accuracy) +35 to +300 Knots (± 20 kts)
Attitude Angle No Limits
Attitude Rate Limit ±250 Degrees / Second
Attitude Accuracy 1° Static, 2.5° Dynamic
G Alert Limits ± 8 g
OAT Range -40°C to +70°C
OAT Accuracy ±4°C
Slip Range (Accuracy) ±7° (±2°)
Bus Voltage Range 7 to 35 Volts
Bus Voltage Accuracy ±1.0 Volt
Clock Accuracy ± 1 Second/Day
Timer Accuracy ± 1 Second/Hour
Table 2 - Operating Limits
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5 System Specifications
Electrical Attributes
Input Voltage Nominal +10 to +32 VDC
Input Voltage Max +60 VDC
Input Power Nominal 6 Watts (0.5 Amps @ 12VDC)
Input Power Max 12 Watts (1.0 Amps @ 12VDC)
Required Circuit Breaker 2 Amp
Operation on Battery 2 Hours Typ @ 20°C / 30 Minutes Min @ -20C
Physical Attributes
Mounting Configuration 3 1/8” Round Instrument Hole
Dimensions wo/Connector 3.38 x 3.38 x 1.6 Inches
Weight 0.50 Lbs.
Electrical Connector 15 Pin Male D-Sub
Pneumatic Connectors ¼” OD Quick Connect
Mounting (4X) #6-32 Machine Screws
Case Material Billet Aluminum
Environmental
Operating Temp -20°C to +55°C
Storage Temp (48 Hrs) -30°C to +80°C
Humidity (48 Hrs) 90% RH
Optical Characteristics
Diagonal Size 3” Circular
Contrast Ratio (Typical) 500
Brightness (Typical) 1000 cd/m2
Viewing Angle Left/Right 60°
Viewing Angle Up 45°
Viewing Angle Down 10°
Backlight Lifetime (Typical) 50,000 Hrs
Table 3 - System Specifications
6 Intended Function
Reference the Pilots Guide for intended functionality.
7 Internal Battery Operation
The internal battery allows for operation in the event of aircraft power loss. When in-flight
(airspeed above 40 KTS), and power is removed from the unit, the AV-30 will continue to
operate but indicate an “On Battery” status.
When the airspeed is below 40 KTS, the unit will automatically shut-down when power is
removed.
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8 Installation
8.1 Overview
Installation consists of the following steps:
Remove / relocate any old instrumentation
Add or locate an appropriate power source / breaker
Wire power and interfaces as needed
Mount the unit to the instrument panel with supplied screws
Apply power and perform setup
8.2 Mechanical Drawing
Figure 3 – Mechanical Drawing
Indice
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