|
Click to Enlarge
KEY OWNER/USER BENEFITS Ideal for RVSM applications All-digital for unsurpassed accuracy and reliability Low power consumption Reduced weight and size for mounting close to pitot/static
system Enhanced BITE for lower cost of ownership Highly reliable rugged solid-state piezoresistive sensor Designed for the latest EMI, HIRF and lightning requirements TSO'd to the latest FAA software standards ARINC 429 digital outputs
OVERVIEW
The ADS-3000 Air Data System senses, computes and displays all parameters
associated with aircraft movement through the atmosphere. It meets the demanding
performance requirements of high-performance business jets and regional aircraft.
The ADS-3000 is capable of being certified to comply with the Reduced Vertical
Separation Minimum (RVSM) requirements. The system is totally digital from the Air Data Computer (ADC) to the
air data displays on the Primary Flight Display (PFD) and Multifunction Display
(MFD). The ADC-3000 provides ARINC 429 digital
outputs for use by the AHS-3000 Attitude Heading Reference System, flight
data recorders, navigation computers, altitude transponders, ground proximity
warning systems and auxiliary aircraft subsystems. The ADS-3000 comes from a long lineage of proven performance. The ADS-85/86/850
family of solid-state air data computers is certified on over a dozen different
aircraft with more than 10,000 system deliveries. Before introducing the ADS-3000
family, Rockwell Collins sold more than 20,000 of the highly successful ADS-8X
and ADC-85X systems. The ADS-3000 is standard equipment
on many business, regional and air transport aircraft. The ADS brings air
transport-class capabilities and accuracy to business aircraft.
DESCRIPTION
The ADC-3000 uses a totally digital design approach. It digitizes pressure
and temperature information from the sensors then digitally computes and transmits
the data throughout the system. Transmissions to other on-board systems are also digital. This unique
digital design offers reduced size, weight and power consumption; continuous
monitoring of all functions and internal diagnostics; increased system integrity
and simplified installation. The system can be tailored to fit specific customer requirements. The
ADC receives pneumatic inputs from the pitot/static system and electrical
signals from the aircraft outside temperature probe. It uses these to compute
altitude, airspeed, Mach and temperature parameters. In turn, this information
provides outputs for the flight control system, navigation system, aircraft
control system and ATC transponder. The use of digital display instruments
reduces the maze of pneumatic plumbing behind the instrument panel to only those
lines needed for the standby instruments. The Collins ADS far exceeds the FAA Technical Standard Order (TSO) accuracy
requirements. In addition, when included with aircraft system efforts, the
Collins ADS complies with RVSM requirements. Features of the system include: Monitoring of all essential functions On-board fault isolation Solid-state piezoresistive pressure transducers Digital computational and display accuracy Solid-state synchronization circuits Low power consumption components Internal diagnostics and nonvolatile memory 28 V DC operation RVSM compliance Computed and available parameters from the ADC-3000 are: Indicated airspeed/calibrated airspeed True airspeed Vertical speed Vmo/Mmo Static air temperature Total air temperature Pressure altitude (corrected for static source errors) Barometric corrected altitude(1) Mach Total pressure Static pressure Impact pressure Internal Standard Atmosphere (ISA) Delta Temperature (1) Requires external control to provide
barometric pressure
OPERATION AND PERFORMANCE ADC-3000 Air Data Computer
The ADC-3000 computes the parameters by processing pitot, static and
temperature information along with preprogrammed aircraft data. The computer
provides digital outputs to the flight control system, air data instruments,
attitude heading reference system, electronic flight control displays, aircraft
subsystems and navigation systems.
The computer self-monitors the altitude and airspeed computation channels.
An overspeed warning test function is also provided. Collins Digital Sensor
The pressure transducer in the ADC-3000 is a piezoresistive solid-state
pressure transducer. Rockwell Collins has many years experience in solid-state
transducer technology and has supplied more than 9,000 solid-state sensors.
The sensors reduce the power input and weight of the ADC-3000, significantly
increasing reliability.
The sensor element itself is a tiny silicon chip with piezoresistive
elements diffused into its surface. Pressure applied across the chip strains
the piezoresistive elements and the resistance of each element changes. The
sensor converts these changes to a digital signal which is then processed
by a digital computer. The computer calculates the absolute static pressure
and differential pressure between the static and pitot ports of the aircraft
and converts them to familiar air data quantities such as altitude and airspeed. Collins
piezoresistive sensors are highly accurate and reliable. Outputs to the Autopilot
The ADC-3000 provides altitude, airspeed, Mach, vertical speed and other
air data outputs to the autopilot on an ARINC 429 serial
digital bus.
Outputs to Electronic Flight Instruments
The ADC supplies digital outputs to the Electronic Flight Instrument
Systems (EFIS) through ARINC 429 serial digital buses going to each instrument.
Each output is capable of driving up to ten instrument loads.
Outputs to Aircraft Subsystems
The ADC provides separate auxiliary outputs to various aircraft subsystems
including overspeed warn, external aircraft warning systems and ARINC 429
serial digital bus for auxiliary aircraft systems.
ADC-3000 Aircraft Specific Data
The aircraft specific data is integral to the ADC-3000. The ADC-3000
stores information that is unique to the particular aircraft type. To assure
that the ADC is the correct one for the aircraft, it contains an aircraft
type code that must match the code wire information of the aircraft.
TYPICAL SYSTEM ADC-3000 | 1 | Air Data Computer | 822-1109-007 |
Note(s): | See Installation Hardware table for mounts and connectors
|

SPECIFICATIONS FAA TSO | C-106 | Environmental | DO-160D [(A2)(F2)]XBBB[(TCC1R)(SLM)EWXXXXZ[BZ]
[AZC][WYP]H[Z3Z3]XAA | Software | DO-178B Level A |
Height | 88.9 kg (3.5 in) | 102.87 kg (4.05 in) | Width | 88.9
kg (3.5 in) | 96.27 kg (3.79 in) | Length | 203.2 kg (8.0 in) | 215.9 kg (8.5 in) | Weight | 53.34
kg (2.1 lb) | 58.42 kg (2.3 in) |
Temperature | -55 to +70°C | | Altitude | 55,000
ft | |
Digital | Six buffered
ARINC 429, 12.5 kBd buses, one ARINC 429 100 kBd bus | | | Parameter | Units | MSB | LSB | | | Pressure Altitude | Ft | 65536 | 1 | | | Baro
Altitude | Ft | 65536 | 1 | | | Mach | Mach No | 2.048 | 6.26E-05 | | | Airspeed
(Default Unfiltered) | kts | 512 | 0.0625 | | | Maximum Operating Airspeed (Vmo) | kts | 512 | 0.25 | | | True
Airspeed | kts | 1024 | 0.0625 | | | Total Air Temperature | Degree° C | 256 | 0.25 | | | Vertical
Speed (Default Unfiltered) | Ft/min | 16384 | 16 | | | Static Air Temperature | ° C | 256 | 0.25 | | | Maximum
Operating Mach (Mmo) | Mach No | 2.048 | 6.26E-05 | | | Static Pressure | inHg | 32 | 0.001 | | | Vertical
Speed (Uncomplemented) | Ft/min | 16384 | 16 | | | Airspeed | kts | 512 | 0.0625 | | | Total
Pressure | inHg | 32 | 0.001 | | | Impact Pressure | inHg | 32 | 0.001 | | | | | | | | | BCD Data Parameter | Units | MSB | LSB | | | ISA-XX
Temperature | ° C | 80 | 1 | | | True Airspeed | kts | 400 | 1 | | | Total
Air Temperature | ° C | 80 | 1 | | | Static Air Temperature | ° C | 80 | 1 | | | Baro
Set | hPa | 1000 | 0.1 | | | Baro
Set | InHg | 10 | 0.001 |
SELECTION GUIDE | ADC-3000 | Various | 822-1109-XXX |
INSTALLATION HARDWARE MMT-3000 | 1 | Mount | 822-1227-001 | | | 1 | Connector (MS27484T18F35SB) (66 contacts supplied with
connector) | 359-0645-220 | | | 1 | Strain
Relief (MS85049/49-218N | 859-6604-150 |
Pitot fitting, No.
4 | 332-0395-000 | Pitot
O-ring, No. 4 | 200-2333-030 | Pitot fitting, 90 ° -
No. 4 | 332-1922-170 | Note(s): | Only one part is needed Correct part can be determined at installation
|
|
Static fitting, No.
6 | 332-0389-000 | Static
O-ring, No. 6 | 200-2333-050 | Static fitting, 90 ° -
No. 6 | 332-1922-180 | Note(s): | Only one part is needed Correct part can be determined at installation
|
|
|