Picture of product AFC001

Part #: AFC001

OEM:

Archangel

Desc:

Automatic Flight Control

Part Number :

ArchangelLogo2.jpg

FEATURES

  • Air Data Attitude Heading Reference System (ADAHRS) for use with analog flight Control systems 
  • The AFC is also the enabling technology for using the ADAHRS with 3 ATI and 4 ATI instruments using DC inputs, as wellas for reversionary instrument used in military, commercial, commuter and business aircraft
  • Receives data over both a Hi speed ARINC 429 Buss and a Lo Speed ARINC buss
  • The AFC forms scaled error signals appropriate to drive a wide variety of Automatic Flight Control Servos/Servo Amps
  • True airspeed and lateral acceleration are outputs of the system, which can be used by two wire displays
  • The AFC001 system consists of a single box, which is shown above
  • System architecture is based on the proven AHR150A-1 Inertial Sensing Unit
  • The AFC001 receives commands from discrete switches located on the instrument panel
  • Filtered Mil Spec Circular Connector 
  • Analog Outputs (2 wire Isolated)
  • Redundant Power Inputs with Failure Warning
  • All solid state
  • FAA/JAA Harmonized HIRF Testing
  • Application Notes: One AFC001 is required per ADAHRSA

 

 

SPECIFICATIONS

dimension:

5.25” x 4.25” x 4.25” (D x W x H)

WEIGHT:

3.1 lbs.

ELECTRICAL: Power 16-36 V DC, 0.3 A @ 28 V nominal Ride Through 200 ms Emissions DO-160E, level Z (conducted and radiated) Interference Harmonized FAA/JAA
inputs/outputs: ARINC 429 1 receive, ARINC 705-5 words 1 receive, ARINC 706-4 words , 
discrete input/outputs

Discrete Outputs AFC VALID, AHRS VALID, Discrete Inputs Roll Hold, Pitch Hold, Heading Hold, Altitude Hold

altitude: -1000 to 52,000 ft. pressure altitude, Altitude Error 20 mVDC/FT 
temperature:

-40 o C to +70 o C operating, -55 o C to +125 o C non-operating

RANGE DATA: Roll Angle 92.6 mVDC/° Pitch Angle 92.6 mVDC/° Yaw Rate 64.4 mVDC/°/s Roll Rate 64.4 mVDC/°/s Roll Error 411 mVDC/° Pitch Error 411 mVDC/° Heading Error 411 mVDC/° Altitude Error 20 mVDC/FT True Airspeed 67 mVDC/Knot Accelerations 1.053 VDC/g
airspeed: 20 to 425 NM/hr. indicated, True Airspeed 67 mVDC/Knot
MECHANICAL: Shock 6 g, sine wave half cycle, 20 g crash survivability Vibration DO-160E Category U, Humidity Severe Environment
RESOLUTION DATA:  Poll Angle ± 108°, ± 10 VDC Pitch Angle ± 108°, ± 10 VDC Yaw Rates ± 128 °/s , ± 8.89VDC Roll Rate ± 128 °/s , ± 8.89VDC Roll Error ± 24°, ± 10 VDC Pitch Error ± 24°, ± 10 VDC Heading Error ± 24°, ± 10 VDC Altitude Error ± 500 FT, ± 10 VDC True Airspeed 0-150 Knots, 0-10 VDC Accelerations ± 4g, ± 4.21 VDC

 

CERTIFICATIONS

environmental catagories: DO160E [D2]XABB[UK1]EWFDFSZZXAZZ[Y(QKL)]L[B4K44]XAAX
CERTIFICATION catagories: TSO C9c
software catagories: DO178B Level B
 

 

 

 

Part Number: Description:
AFC001 Automatic Flight Control


 

AFC001
- Automatic Flight Control
Price Condition Status
REQUEST NEW OUTRIGHT REQUEST LEAD TIME

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