EIS SINGLE DISPLAY PACKAGE

EFIS is an acronym for "Electronic Flight Information System". The EFIS Horizon

Series I provides primary flight data (attitude, altitude, airspeed, vertical speed, steering), graphical engine data, and a moving map. It is designed as a cost-effective replacement of traditional vacuum-powered mechanical gyros. Unlike mechanical gyros, no maintenance is required, and installation is much quicker, easier, and lighter. Aerobatics, vibration, and temperature do not affect the life of the EFIS, as it is completely electronic.

In addition to these benefits, the EFIS Horizon Series I provides data not available with mechanical gyros, such a navigation steering data integrated with the attitude display, an artificial view of the world showing airports and obstacles just the way they appear out the window, continuously computed winds, and much, much more.

Its easy to get excited about the functionality of the Horizon EFIS, but it’s more than just features.

The Horizon EFIS is engineered from the ground up without compromises. Small details, like a sunlight readable display, wide –15 to +160 deg F operating temperature range, and an attitude/heading reference system (AHRS) that is built to aerospace standards could easily go unnoticed…and that is exactly the idea.

Instead, what you notice is how naturally all flight information is communicated…how seamlessly navigation and attitude are combined with a highway in the sky presentation, and the flexibility of the user-configurable features.

Even more important are the details that go unnoticed, such as the continuous built-in test functions, the consideration for failure modes and effects, the validation and cross-check of flight critical data...in short the details you would expect in avionic equipment that gives it the integrity making it suitable for flight...details some other manufacturers are unaware of...details that come from our extensive aviation/aerospace experience.

The Horizon EFIS goes far beyond the functions of conventional instruments. The elimination of mechanical instrumentation provides advantages not only in the reliability and freedom from maintenance, but also the ability to provide data not previously available, and in a format that more naturally communicates the state of the aircraft to the pilot.

Designed to Eliminate Vacuum Systems
The Horizon EFIS is designed from the ground up to eliminate vacuum systems. Its low power consumption (0.5 amps), and dual isolated power inputs (allowing it to be powered by either of 2 buses) pose little demands on the aircraft’s electrical system design. This allows for a simple, two bus electrical system, requiring only a single alternator and our optional charging diode. Actual size: 6.0" D x 4.0" W x 3.375" H, 1.75 lbs

Automatic Logbook and 
Engine Data Recording
It’s the end of tedious logbook entries. The Horizon EFIS detects the beginning and end of a flight, and records the date, time, start and end locations, and time of flight automatically. This data is recorded in non-volatile memory, and can be reviewed on the display, or downloaded using via a USB flashdrive.

Extensive engine and air data can also be recorded and downloaded, allowing precise evaluation of airplane and engine performance, and provides an outstanding aid for the troubleshooting of intermittent engine problems

Independent AHRS Processor
Even a momentary interruption in processing can jeopardize the integrity of AHRS data. That is why the Horizon EFIS utilizes an processor dedicated solely to performing AHRS sensor measurement and processing. This processor does not have the overhead or a large operating system, nor any tasks unrelated to the calculation of attitude, heading, and related data. Its designed purely to provide high integrity, high reliability, flight-critical data.

Mode S Traffic Display

TIS based traffic via the Garmin GTX330 transponder is available using our optional ARINC 429 interface adapter. The mode S featureavailable at no charge (the optional Arinc 429 Interface adapter is required however),and eliminates the need topurchase a Garmin 430/530 to display traffic provided by the transponder. Our experience with the traffic provided by the GTX330 has been very positive, providing much more benefit than simply collision avoidance.

GPS-Independent AHRS
For obvious reasons of safety, the pitch, roll and gyro-stabilized heading sensed by the attitude/heading reference system (AHRs) must be of high integrity. That is why our AHRs is based on high quality sensors, proven mathematical algorithms, and is not dependent on outside sources, such as GPS.

Some AHRs are dependent on GPS data for proper operation. Introducing GPS into the attitude calculations has many drawbacks. Loss of GPS data can mean unexpected loss of attitude data. Degradation of the GPS data, such as can occur with various atmospheric or satellite constellation configurations, due to the re-activation of selective availability, airframe icing of the GPS antenna, interference from radar, etc., can have unexpected effects on attitude data which relay upon it. Redundancy is meaningless in aircraft that use 2 AHRs systems which are both GPS dependent. In short, attitude data should not be dependent on GPS, or any other sensor source whose integrity or availability cannot be assured.

Magnetometers (flux gates) provide the heading reference source needed to allow independence from GPS data. This is the reason a magnetometer for sensing magnetic heading is a standard with the Horizon EFIS. Our attitude data is based on its own sensors, including a 3-axis flux gate sensor, and 3-axis accelerometers, and 3-axix angular rate gyros, and is not dependent any external signals, such as GPS. Loss of GPS data will not result is loss of attitude data with the Horizon EFIS. It is perfectly acceptable to operate the Horizon EFIS without any GPS data.

For fully independent AHRS, such as the Horizon EFIS, GPS data can aid in the self-testing of the AHRS system. In effect, the addition of GPS data, along with the fully independent AHRS set of electronic gyros, magnetometers, and accelerometers, provides more data than is required for the calculation of attitude and heading. The Horizon EFIS takes advantage of this data redundancy by using sophisticated mathematical algorithms that are able to provide self-testing of the AHRS system whenever GPS data is available…even when taxiing.

 is intended to provide the data necessary for VFR flight. Free database updates are available from our website. Database regions and detail levels can be selected by the user to provide the area of coverage vs. detail desired. Databases are available for 

Two other moving map modes are also provide, both which show the aircraft position in the middle of the screen, and a 360 degree compass rose around the airplane. The first of these two screens allows you to see airports and navaids that are behind, as well as in front of the airplane. When the aircraft is not moving, the magnetic heading up mode (instead of the usual ground track up) is used to show runway orientation based on the direction the airplane is currently pointing. This can be quite helpful when taxing to runways at unfamiliar airports.

The third moving map mode is the equivalent of an HSI function, with moving map features also displayed. The HSI provides 2 VOR bearing pointers, GPS course, and localizer/glideslope displays.

Navigation inputs are provided for two navigation radios (VOR/ILS), and two GPS inputs. The navigation modes are easily selected from the softkeys. The ability to select the navigation mode from the EFIS allows consistent navigation data, steering, and auto-pilot coupling.

Specifications:
Max Angular Rate: 200 degrees/second, all axis simultaneously. 
Pitch and Roll Angles Range : Unlimited
Operating Temperature Range: -15 to +160 deg F ( -25 to +70 deg C)
Storage Temperature Range: -25 to +185 deg F (-30 to + 85 deg C)
Maximum rate of change of temperature: Unlimited
Long Term Reference : Accelerometer and Magnetometer (not GPS dependent - functions without aiding of any type)
Display: Direct sunlight readable, backlit, wide temperature range, transflective display (not dependent on high power backlights for sunlight readability) Min Backlight intensity : 3 nits.
Airspeed Ranges : Low speed version is 35-290 mph indicated, and the high speed version is 50-600 mph indicated.
Altimeter: -1000 to +35,000 feet. Meets IFR accuracy requirements.
Magnetic Heading : <5 degrees error – gyro-stabilized

MFD Physical Dimensions:
Overall Size of Faceplate : 7.25" wide x 4.75" high
Size of opening required in instrument panel : 6.25" wide x 4.65" high.
Maximum Depth 3.0"
Weight: 2.25 lbs

Electrical Requirements:

12V Version : 9-20 Vdc 1.5 amp
28V Version : 18-36V 1.0 amp
Isolated, triple power inputs are provided.