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Electronic Standby Instruments System

Electronic Standby Instruments System. OASIS: Introduction. The OASIS is designed to serve as the secondary source of cockpit instrumentation and provides the following functions: Attitude Indicated Airspeed Barometric Corrected Altitude Slip/Skid

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Electronic Standby Instruments System

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  1. Electronic Standby Instruments System

  2. OASIS: Introduction • The OASIS is designed to serve as the secondary source of cockpit instrumentation and provides the following functions: • Attitude • Indicated Airspeed • Barometric Corrected Altitude • Slip/Skid • Heading (Optional, requires a magnetometer)

  3. OASIS: LRU’s/Modular Design The OASIS modular designed allows installation flexibility by separating the display from the ASU enhancing installation flexibility in congested cockpits MSU (Magnetic Sensing Unit) Optional ASU (Aerosonic Sensor Unit) DU-1 (Display Unit) DU-2 (Display Unit) Optional

  4. OASIS: Standard System and Options • Standard system includes: • ASU, 1ea. • DU, 1ea. • Enhanced system options: • Second DU • DU with NVS • ASU with internal standby battery • MSU for heading reference

  5. OASIS: System Block Diagram

  6. OASIS: Display Features Battery Status Slip-Turn Indicator Airspeed Tape Altimeter Tape Magnified Altitude Window Magnified Airspeed Window Barometric Setting Heading Window (optional) Menu Select Keys

  7. OASIS: Part 27/29 Airspeed Window

  8. OASIS: Display Unit The DU is installed on the instrument panel adjacent to the primary display or instruments and provides a secondary graphical display of all of critical, primary functions necessary for the continued safe flight and landing of an aircraft during a loss of primary instruments. The DU provides user interface for data entry and settings through a bezel keypad. The DU is directly connected to, and obtains power and sensor data from the remote mounted ASU. • Features: • 4 inch diagonal screen • 3 inch ATI opening • Chassis depth: 1.35 inches • Bezel: 4 inches x 3 inches • Weight: .75 lbs • NVS compatible (Option)

  9. OASIS: Display Unit

  10. OASIS: Aerosonic Sensor Unit The ASU is a separate remote mounted LRU that provides power and sensor data to the DU. It’s connected to aircraft power and the pitot/static pneumatic lines. The ASU contains sensors required for the computation of Indicated Airspeed, Barometric Corrected Altitude, Attitude, Slip/Skid. Heading is available with the installation of an Aerosonic Remote Magnetometer. Power to the remote magnetometer is provided by the ASU. In addition the ASU has an optional internal battery that allows the OASIS to operate for a minimum of 1 hour without aircraft power. • Features: • Dimensions: 3 x 3 x 6.25 inches • Weight: 2 lbs • Power: 28 Vdc nominal, 14 watts max (2 displays, 1 ASU) • Internal standby battery (Option)

  11. OASIS: Aerosonic Sensor Unit

  12. OASIS: Specification/Certification • Operating Specification • Altitude: -1,500 to +55,000 ft. • Airspeed: 20 to 450 kts • Max roll/pitch rate: 200 deg/sec • Operating temperature • DU: -20º to +55º C • ASU: -40º to +70º C • Baro setting: 28.00 to 30.99 mb • Reliability: 10,000 hrs MTBF • Certification • Software: DO178B level B • Environmental: DO 160F (Helicopter and Fixed Wing) • FAA /EASA TSO • TSO-C2d: Airspeed Instruments • TSO-C4c: Bank and Pitch Instruments • TSO-C6e: Direction Instrument, Magnetic • TSO-C10b: Altimeter, Pressure Actuated, Sensitive Type • TSO-C113: Airborne Multipurpose Electronic Displays • TSO-C3e: Turn and Slip Instruments • TSO-C46a Maximum Allowable Airspeed Indicators • TSO-C179 Rechargeable Lithium Cells and Lithium Batteries

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