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. (Aerosonic Sensor Unit) (Magnetic Sensing Unit) Optional
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
ASU
(Aerosonic Sensor Unit)
MSU
(Magnetic Sensing Unit) Optional
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
Heading Window (optional)
Barometric Setting
Menu Select Keys

7. Red Cross-Hatched Line
OASIS: Part 27/29 Airspeed Window
Min Airspeed
Max Airspeed
Color
VCAUTION
Green
VNE Power ON
Yellow
Max Airspeed Value
Red
VNE Power OFF
Red Cross-Hatched Line

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: to 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