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KEY OWNER/USER BENEFITS
All-digital, including computation, transmission and display Programmable analog outputs support a wide variety of user
systems Highly reliable ADC because of low-power CMOS parts and a
rugged solid-state piezoresistive sensor Enhanced fault isolation through the use of internal diagnostics
and nonvolatile memory Reduced cost of ownership by increased availability of the
system RVSM-compliant system Plug in compatible with ADC-80 ARINC 429/CSDB Ternary (419) and manchester capable
OVERVIEW
The ADS-87A Air Data System senses, computes and outputs 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-87A is capable of certifying to comply with the Reduced Vertical
Separation Minimum (RVSM) requirements. The ADC-87A Air Data Computer provides digital outputs for use by the
APS-65/80 Autopilot System, AHS-85 Attitude Heading Reference System, ADS-85
Air Data System instruments, EFIS-85/86 Electronic Flight Instrument System
and other interfacing aircraft systems. The ADC-87A is a form, fit and functional
replacement for the ADC-80( ). The ADS is compatible with the APS-65/80. It provides for optimal performance
of the flight guidance system in all vertical modes and can also display all
air data parameters essential to flight. The ADS-87A comes from a long lineage of proven performance. The ADS-8X
and ADS 85X families of solid-state air data systems are certified on over
a dozen different aircraft with more than 20,000 system deliveries. This system
is also standard equipment on many business, regional and air transport aircraft.
The central ADS brings air transport class capabilities and accuracy to business
aircraft.
DESCRIPTION
The ADC-87A uses a totally digital design approach. It digitizes pressure
and temperature information from the sensors, then 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 ADC can be tailored to fit specific customer requirements. It receives
pneumatic inputs from the pitot/static system and electrical signals from
the aircraft outside temperature probe and 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, as well as for the primary air data instruments.
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 air data components,
the Collins ADC has the capability to comply with RVSM requirements. Features of the ADS-87A include: Monitoring of all essential functions On-board fault isolation Solid-state piezoresistive pressure transducers 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-87A are: Mach Indicated airspeed True airspeed Vertical speed Vmo/Mmo Static air temperature Total air temperature Preselected altitude Overspeed warning contacts ADC valid contacts Uncorrected pressure altitude Barometric corrected altitude
OPERATION AND PERFORMANCE
ADC-87A Air Data Computer
The ADC-87A analyzes the parameters by processing pitot, static and
temperature information along with preprogrammed aircraft data. A configuration
memory module unique to the aircraft model type contains the preprogrammed
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. It continuously
monitors altitude and airspeed computation channels. To increase assurance
of normal operation, the pilot can activate a computer self-test on the ground
before takeoff. An overspeed warning test function is also provided.
Digital Sensor
The pressure transducer in the ADC-87A is a piezoresistive solid-state
pressure transducer. Rockwell Collins has many years of experience in solid-state
transducer technology and has supplied more than 50,000 solid-state sensors.
The sensors reduce the power input and weight of the ADC-87A and significantly
increase 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 computer. The computer calculates the absolute static pressure and differential
pressure between the static and pitot ports of the aircraft and converts them
to the familiar air data quantities such as altitude and airspeed. Collins piezoresistive
sensors are highly accurate, reliable and durable.
Outputs to the Flight Control System
The ADC-87A provides altitude, airspeed, vertical speed and other air
data outputs to the APS-65 or APS-80 Autopilot System.
Altitude information displayed on the altimeter is consistent with the
operation of the autopilot in altitude hold because the same pressure sensing
source supplies both systems. Airspeed is also consistent between the airspeed
instrument and the autopilot airspeed hold mode.
Outputs to Electronic Flight Instruments
The ADC supplies digital outputs to the electronic flight instruments
through serial digital buses going to each instrument. Each output is capable
of driving up to ten instrument loads.
Outputs to Aircraft Subsystems
The air data computer 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, a Commercial
Standard Data Bus (CSDB) and a terinary serial digital bus.
Air Data Configuration Module
The ACM is a separate unit that plugs into the computer. The module
stores information that is unique to the particular aircraft type. To assure
that the module is the correct one for the aircraft, it contains an aircraft
type code that must match the code wire information of the aircraft.
AIR DATA INSTRUMENTS
A complete set of air data displays is available for use as part of
the ADS. These instruments give the pilot assessment of aircraft performance
for vertical path and longitudinal speed control. The following is a description
of specific air data instruments and display configurations driven by the
ADC-87A.
ALI-80A Encoding Altimeter
The ALI-80A decodes the binary, self-clocking Manchester data transmitted
by the central ADC, corrects for a value (in feet) equal to the baroset display
and displays actual corrected altitude of the aircraft on the circular pointer/dial
scale and numeric counter drum readout.
PRE-80 Preselector/Alerter
The PRE-80 provides altitude preselect mode with the flight director
system. It accepts baro-corrected altitude data from the ALI-80A and provides
selected altitude display and altitude alert operation.
ASI-80D Airspeed Indicator
The ASI-80D has a dual pointer display of indicated airspeed and maximum
allowable airspeed. Scale markings are customized for the particular aircraft,
including colored arcs for gear, flap, stall speeds and others. This instrument
also has a mechanical bug and push-to-test function.
MSI-80F Mach Speed Indicator
The MSI-80F has a dual pointer display of indicated airspeed and maximum
allowable airspeed that is driven by independent servos. The Mach airspeed
indicator contains a servoed reference bug. Upon engaging airspeed hold, the
bug slews to match the airspeed pointer; new airspeed hold commands can be
set via the bug knob or the slew control of the autopilot.
VSI-80A Vertical Speed Indicator
The VSI-80A displays the actual vertical speed of the aircraft on the
circular pointer/dial scale. The pilot can set a vertical speed marker (bug)
by manual activation of the knob located in the lower right hand corner the
instrument, or the slew control of the autopilot.
TAI-80A True Airspeed Indicator
The TAI-80A receives, decodes and displays Total Air Temperature (TAT),
Static Air Temperature (SAT) and True Airspeed (TAS). The display has a pair
of three-digit, seven-bar incandescent
readouts simultaneously displaying SAT and TAS. A momentary push-for-TAT button
changes SAT display to TAT.
TYPICAL SYSTEM
ADC-87A | 1 | Air Data Computer | 822-1398-420 | ALI-80A | 1 | Encoding Altimeter | 622-3975-005 | MSI-80F | 1 | Mach Airspeed Indicator | 622-6785-015 | PRE-80C | 1 | Preselector/Alerter | 622-9462-035 | TAI-80A | 1 | True Airspeed/Temperature
Indicator | 622-2294-014 | VSI-80A | 1 | Vertical Speed Indicator | 622-4782-007 |
Note(s): | See Installation Hardware table for mounts and connectors
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SPECIFICATIONS
FAA TSO | C2c, C8b, C10b, C43a, C46a,
C52a, C95 | C10b
(SAE AS-392c) C88 (SAE AS-855) | | Environmental | DO-160B A2F2/BA/JY/EXXX
XXZ/BZ/AZZZZ | DO-160A A2A/PKS/XXX XXXA/AB/ A/ZA/ZA | DO-160A A2A/PKS/XXX
XXXA/AB/ A/ZA/ZA | EUROCAE | ED-14B | ED-14A | ED-14A |
Size | (1/2 ATR short/low) | | | Height | 85.1mm (3.35 in) | 85.85 mm (3.38 in) | 85.85 mm (3.38 in) | Width | 124.6
mm (4.91 in) | 85.85
mm (3.38 in) | 85.85 mm (3.38 in) | Length | 360.2 mm (14.2 in) | 235.4 mm (9.27 in) max | 236.14 mm (9.30 in) max | Weight | 2.70
kg (6.00 lb) | 1.4
kg (3.1 lb) | 1.29 kg (2.85 lb) | Mounting
Information | Unit mounts in Collins UMT-13 mount No
special mounting hardware is required | Panel-mounted, front or
rear | Panel-mounted,
front or rear |
Temperature | -55 to +70°C | -30 to +70°C | -30 to +70°C | Altitude | 55,000 ft | 15,000
ft | 15,000 ft |
Power | 28
V DC, 20 W | 28 V
DC, 20 W | 28 V DC, 14 W | Lighting | | 5 V AC/DC, 3 W | 5 V AC/DC, 3 W | | | | 28 V DC, 3 W | 28 V DC, 3 W |
FAA TSO | C52a | C43 | C8b (SAE AS-394a) | Environmental | DO-160A A2A/PKS
/XXX XXXZ/AB/ A/ZA/ ZA | DO-160A A2A/PKS /XXX XXXZ/AB/ A/ZA/ ZA | DO-160A A2A/PKS
/XXX XXXA/AB/ A/ZA/ ZA | EUROCAE | ED-14A | ED-14A | ED-14A |
Height | 42.47
mm (1.672 in) | 42.47 mm (1.672 in) | 85.85 mm (3.38 in) | Width | 86.11 mm (3.39 in) | 86.11 mm (3.39 in) | 85.85 mm (3.38 in) | Length | 197.25
mm (7.765 in) | 156.02
mm (6.14 in) | 235.4 mm (9.27 in) max | Weight | 0.6 kg (1.32 lb) | 0.6 kg (1.32 lb) | 1.09 kg (2.40 lb) | Mounting Information | Panel-mounted, front or rear | Panel-mounted, front or rear | Panel-mounted, front or rear |
Temperature | -30 to +70°C | -30 to +70°C | -30 to +70°C | Altitude | 15,000 ft | 15,000
ft | 15,000 ft |
Power | 28
V DC, 8 W | 28 V
DC, 6 W | 28 V
DC, 8 W | Lighting | 5 V AC/DC, 3 W | 5 V AC/DC, 3 W | 5 V AC/DC, 3 W | | | 28 V DC, 3 W | 28 V DC, 3 W | 28 V DC, 3 W |
Pressure Altitude | -1871 to +57,343
ft | 1 ft | 1 | Baro
Corrected Altitude | -1871 to +57,343 ft | 1 ft | 1 | Baro Altitude Correction | Baro setting 22.00 to 32.00 inHg | 0.01 inHg | | Vertical
Speed | -20,480 to +20,480 ft/min | 20 ft/min | | Indicated Airspeed | 30 to 510
kts | 0.125 kts | | Mach | 0.1
to 1.0 | 0.00025 | | True Airspeed | 100 to 600
kts | 0.125 kts | | Static
Air Temperature | -99°C to +60°C | 0.25°C | | Maximum Speed, Vmo | 120 to 500
kts | 0.25 kts | | Total
Air Temperature | -60°C to +99°C | 0.25°C | | IAS Reference | 30 to 510
kts | 1 kt | | VS
Reference | 0 to 10,000 ft/min | 100 ft/min | | Mach Reference | 0.1 to 0.99
M | 0.01 M | | IAS
Trend Vector | ±256 kts/10 | 1 kt | | Vyse | 30 to 500
kts | 1 kt | | Note(s): | To 46,500 ft, degrades
typically to 1.6 ft at 57,343
ft
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SELECTION GUIDE
ADC-87A | Various | X | X | 822-1398-XXX |
ALI-80A | | X | X | | X | | X | | | 622-3975-001 | | | | X | | X | X | | | X | | 622-3975-004 | | | | X | X | | | X | X | | | 622-3975-005 | | | X | | | X | X | | | X | X | 622-3975-014 | Note(s): | Provides static source error-corrected altitude Extended range baroset capability Push/pull baroset knob displays in HG and MB Self-test capability
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ASI-80F | X | 40-350 | X | | X | | X | | 622-6728-011 | MSI-80F | X | 60-420 | X | | | X | X | | 622-6785-015 | Note(s): | Displays indicated airspeed, Mach airspeed and Vmo/Mmo Servoed reference bug display Slanted airspeed pointer Mechanical reference rings and pointers which attach to the
MSI-80( ) are available from: Qualitair Inc.
5410 International Hwy
Minneapolis, MN 55428
Ref Ring P/N 900-000-05
Pointer P/N 400-6
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TAI-80A | X | | X | | | X | | X | 622-2294-002 | | | X | | X | | X | | X | | 622-2294-014 | TAI-80B | | X | X | | | X | X | | 622-3234-004 | Note(s): | Displays true airspeed and static air temperature or total air temperature |
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VSI-80A | X | X | | X | | X | | 622-4782-001 | | | X | X | | | X | X | | 622-4782-007 | | |
PRE-80C | X | | X | | X | | X | | X | | 622-9462-005 | | | X | | | X | | X | X | | | X | 622-9462-024 | | | X | | | X | X | | X | | X | | 622-9462-035 | PRE-80D | | X | | X | X | | X | | X | | 622-9722-035 | Note(s): | Preselects altitude to be captured and provides pilot with
aural and visual alerting signals when approaching or deviating from the selected
altitude Altitude select range goes to 49,900 ft on the PRE-80C and
56,900 ft on the PRE-80D and PRE-80L
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INSTALLATION HARDWARE
UMT-13 | | | |
Mount | 1 | | 622-5213-004 | Mating Connector
Kit | 3 | | 634-1021-001 |
Contact Pins, for insulation diameter up to 0.050 in | 180 | 1 | 372-2514-110 | | | or | | |
Contact Pins, for insulation diameter up to 0.080 in | 180 | 1 | 372-2514-180 | Note(s): | Choose as required for total quantity/unit
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Mating Connector | 1 | | 371-0213-030 | Mating
Connector Cable Clamp | 1 | | 371-0185-000 | Mating Connector Screw
Lock Assembly | 2 | | 371-0040-010 | Contact
Pins, Crimp | 25 | | 371-0213-110 | Key Plug Kit | 1 | | 629-8381-001 | HIRF
Kit | 1 | 1 | 827-5643-001 | HIRF Kit | 1 | 3 | 827-0313-001 | Plate,
Spacer | 1 | 2 | 827-6145-001 | Note(s): | Required for front mount ALI-80A for HIRF protection Use with ALI-80A 622-3975-01X Required for MSI-80( ) for HIRF protection Use with MSI-80C, 622-4382-1XX and MSI-80F, 622-6785-1XX Required for back mount ALI-80A for HIRF protection Use with ALI-80A, 622-3975-01X
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Mating Connector | 1 | 371-0213-020 | Mating
Connector Cable Clamp | 1 | 371-0184-000 | Mating Connector Screw
Lock Assembly | 2 | 371-0040-010 | Contact
Pins, Crimp | 15 | 371-0213-110 | Key Plug Kit | 1 | 629-8381-001 |
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