Levil Aviation BOM User manual

201
8
D-0007
BOM (Broadcasting
Outer Module) Company
Standards
LEVL AVIATION
1704 KENNEDY POINT, SUITE 1124
OVIEDO, FL 32765

BOM (Broadcasting Outer Module) Company Standards
Effective Date 12/6/17 Page 1 of 12
Document No. 42 Revision 1 Code Number D-0005
This manual is the property of Levil Aviation. It may not be replicated in whole or in part or
otherwise divulged without prior written consent from Levil Aviation. All printed and electronic
copies and versions except the one electronically signed inside the Levil Aviation database, are
considered unofficial copies and may be used for reference only.
This is a controlled document, if any changes are made (even a single character) to any part of the
document it is considered an entirely different document. For this reason, a Revision Record page
is provided, documenting every single change done to the document.
Address: 1704 Kennedy Point, Suite 1124
Oviedo, FL 32765
Telephone: [phone]
Revision Date:
Approved by:
General Manager
______________________________ (Name) _________________________ (Signature)
_______________ (Initials) _________________ (Date)
Quality Assurance Department Manager
______________________________ (Name) __________________________ (Signature)
_______________ (Initials) _________________ (Date)

BOM (Broadcasting Outer Module) Company Standards
Effective Date 12/6/17 Page 2 of 12
Document No. 42 Revision 1 Code Number D-0005
AMENDMENT RECORD
This procedure is reviewed to ensure its continuing relevance to the systems and process that it
describes. A record of contextual additions or mission is given below:
Revision No. Date Responsable Person Description of Change
1 12/6/2017 Initial release
Warranty
Levil Aviation warrants this product to the original purchaser to be free from defects in material
and workmanship for a period of one year from the date of the original purchase. The following
are not covered: software, damage resulting from accident, neglect, misuse, fire, or flood, improper
voltage supply or failure to follow operational guidelines supplied with this product. Extended
warranty is available for purchase on our website.
Please register your product online at: http://aviation.levil.com
IN NO EVENT, SHALL LEVIL AVIATION BE LIABLE FOR ANY INCIDENTAL, SPECIAL,
INDIRECT OR CONSEQUENTIAL DAMAGES, WHETHER RESULTING FROM THE USE,
MIUSE OR INABILITY TO USE THE PRODUCT OR FROM DEFECTS IN THE PRODUCT.
SOME STATES DO NOT ALLOW THE EXCLUSION OF INCIDENTAL OR
CONSEQUENTIAL DAMAGES, SO THE ABOVE LIMITATIONS MAY NOT APPLY TO
YOU.

BOM (Broadcasting Outer Module) Company Standards
Effective Date 12/6/17 Page 3 of 12
Document No. 42 Revision 1 Code Number D-0005
Table of Contents
1. Compliance and Use ............................................................................................................................. 4
2. Technical Specifications ....................................................................................................................... 4
3. Design Specifications ............................................................................................................................ 5
3.1 Material Requirements .................................................................................................................. 5
3.2 Design Requirement ...................................................................................................................... 6
4. Flammability Testing Requirements ..................................................................................................... 6
5. Structural Strength Requirement ........................................................................................................... 6
6. Software Validation .............................................................................................................................. 6
7. Electronic Emissions ............................................................................................................................. 6
8. ADS-B IN ............................................................................................................................................. 6
9. Company Specifications ....................................................................................................................... 7
9.1 AD-AHRS ..................................................................................................................................... 8
9.1.1 Temperature Calibration ....................................................................................................... 8
9.1.2 Magnetic Heading ................................................................................................................. 8
9.1.3 Roll, Pitch and Yaw .............................................................................................................. 9
9.1.4 Indicated Airspeed and Altitude ........................................................................................... 9
9.2 Vibration Sensor ......................................................................................................................... 10
9.3 Angle of Attack ........................................................................................................................... 10
9.4 Micro SD Memory Card ............................................................................................................. 10
9.5 Position Source (GPS or GLONASS) ......................................................................................... 11
9.6 ADS-B Dual Band Receiver ....................................................................................................... 11
9.7 Wireless Transmission ................................................................................................................ 11
9.8 Power System .............................................................................................................................. 12
9.8.1 Turbine ................................................................................................................................ 12
9.8.2 Nose Heater ......................................................................................................................... 12

BOM (Broadcasting Outer Module) Company Standards
Effective Date 12/6/17 Page 4 of 12
Document No. 42 Revision 1 Code Number D-0005
1. Compliance and Use
The BOM meets the design and performance requirements of 14 CFR 21.137 and is produced
under a quality system that satisfies the requirements of the FAA Policy number PS-AIR-21.8-
1602. The BOM is not TSO’d and is pending NORSEE Certification. Upon NORSEE Certification
approval, the BOM will be approved for design and production for Aircraft Certified under 14
CFR 23 or earlier regulations. The BOM’s installation will be approved by a certified mechanic
using the installation guidelines provided by Levil Aviation.
2. Technical Specifications
Specification Description Industry
Standards
Wind Speed
Requirements 60 kt. (Min); 210 kt. (Max)
Temperature
Range -20 °C to 60 °C
Altitude (Absolute
Pressure)
Max: 30,000 ft.; 24-bit resolution; Pressure
Transducer range: 260 – 1260 hPa.
Pressure
Transducer: ISO
9001
Air Speed
(Pressure
Differential)
Range: 0-320 kt.; 14-bit resolution
Pressure
Transducer: ISO
9001
Angle of Attack 14-bit resolution
Pressure
Transducer: ISO
9001; ASTM
F3011-13
AHRS Max. Rotation Rate: 500 °/sec; Roll/Pitch accuracy:
±
3°; Magnetic Heading accuracy:
±
4°
WI-FI Qualified 2.4-GHz IEEE 802.11b/g transceiver FCC, CE, IC, and
RoHS
Battery -3.7V, 1300mAh, 4.81Wh; Over charge and
discharge protection with a charging manager; 2
UL1642

BOM (Broadcasting Outer Module) Company Standards
Effective Date 12/6/17 Page 5 of 12
Document No. 42 Revision 1 Code Number D-0005
Amp fast blown fuse protected; Battery life: 2
Hours (ADS-B Receiver ON), 5 Hour (ADS-B
Receiver OFF)
Turbine
Operation Voltage: 12 – 50 VDC; Output Current:
0.48 (Max. 0.72) A; Output Power: 5.76 (Max. 25)
W; Speed: 32,000 R.P.M.; Insulation Type: UL:
Class A; Life Expectance: 2,000 Hours continuous
operation at 40°C with 15 ~ 65 %RH
GPS Uses NAVSTAR GPS L1 C/A signal; WASS
Compatible; 48 verification channel GPS receiver;
Format Selectable Output Data: NMEA and OSP™
CSR/SiRF™
SiRFStar IV™
GPS Antenna Passive Antenna; 1575 MHz
±
3
𝑀𝐻𝑧
center
frequency RoHS
ADS-B Receiver
Transmission
Frequency
978/1090 MHz (Dual Band) RTCA 282-B
Weight 370 g
Length 250 mm
Outer Diameter 48 mm
Turbine Diameter 54 mm
Patent No. US 9,776,730 B1
Table 1. Technical Specifications
3. Design Specifications
3.1 Material Requirements
The outer housing of the BOM must use UV resistant and non-permeable materials including:
a. Delrin and Aluminum-Alloy 6061.
b. Assembly screws for the outer housing must be stainless steel.

BOM (Broadcasting Outer Module) Company Standards
Effective Date 12/6/17 Page 6 of 12
Document No. 42 Revision 1 Code Number D-0005
3.2 Design Requirement
All systems of the BOM must meet all the design parameters as set by the different system’s
operational requirements and/or drawing specifications. Engineering drawings must include
the information necessary to duplicate each product to comply with this standard.
4. Flammability Testing Requirements
The material of the BOM, produced under this design standard, must comply with the
requirements of Civil Aeronautics Regulation 3, definition of flame resistance, when tested as
a complete assembly.
5. Structural Strength Requirement
The structure must be able to sustain 6G pull test in the vertical axis when installed in test
fixture representative of an aircraft panel. The 6G requirement is based on the mass of the unit
for which the part is intended to accommodate.
6. Software Validation
Software/Hardware integration shall be designed and tested using ASTM F3153-15 practices
and reports.
7. Electronic Emissions
Wi-Fi equipment has been tested and found to comply with the limits for a Class digital device,
pursuant to Part 15 of the FCC rules. These limits are designed to provide reasonable protection
against harmful interference in a residential installation. This equipment generates uses and
can radiate radio frequency energy and, if not installed and used in accordance with the
instructions, may cause harmful interference to the radio communications. However, there are
no guarantees that interference will not occur in a particular installation. The Wi-Fi transceiver
must have a MAX of 10 mW output power.
8. ADS-B IN
Unit meets the performance requirements for the FAA TSO-C154C for sections appropriate
for ADS-B In operation. This will include:
 RTCA DO-282B (Section 2.2.8, 2.2.9 and 2.2.10) for 978 MHz receiver.

BOM (Broadcasting Outer Module) Company Standards
Effective Date 12/6/17 Page 7 of 12
Document No. 42 Revision 1 Code Number D-0005
9. Company Specifications
The BOM combines different avionic systems into one module and sends the information via
Wi-Fi to a tablet. All systems of the BOM are individually tested to meet certain performance
criteria and are then combined and tested as a whole system. The following diagram, shows
the different systems that make up the BOM and how they all integrate with one another.
Figure 1. BOM System Integration Diagram

BOM (Broadcasting Outer Module) Company Standards
Effective Date 12/6/17 Page 8 of 12
Document No. 42 Revision 1 Code Number D-0005
9.1 AD-AHRS
The AHRS Micro is an electronic device developed by Levil Aviation which consists of
sensors on three axes that provide attitude and heading information and air data for an aircraft.
It is designed and manufactured by Levil Aviation, guaranteeing each individual board is
calibrated to withstand extreme environmental conditions (turbulence, humidity, high-
temperatures, etc.) The AHRS information is sent by the IMU Microprocessor to the BOM’s
main Microprocessor which is then transmitted to a tablet via Wi-Fi and displayed accordingly.
Because of the AHRS component, the BOM must be aligned during installation to display
accurate Attitude with respect to the aircraft’s straight and level flight. The following listed
performance requirements must be met by the AHRS system:
9.1.1 Temperature Calibration
AHRS are individually calibrated in a wide range of temperatures so that their performance is
not affected by extreme temperatures during flight. The calibration process ranges from -10°C
to 80°C. Temperature matrixes are computed, and a plot of the temperature behavior of the
gyros and accelerometers is analyzed for linearity. Figure xxx. Shows an example of a
temperature calibration plot; each color represents a gyro or accelerometer.
Figure 2. Temperature Calibration plot example
9.1.2 Magnetic Heading
The AHRS uses a 3-axis magnetometer to calculate magnetic heading (even when airplane is
up-side-down). The magnetometer is calibrated individually using a Helmholtz Coil. Magnetic
readings are taken, values analyzed for accuracy and matrixes computed and sent to the IMU
microprocessor. The Magnetic heading is tested for accuracy after calibration. An AHRS
compass is considered to Fail if the compass is off by ±10° from the true value.

BOM (Broadcasting Outer Module) Company Standards
Effective Date 12/6/17 Page 9 of 12
Document No. 42 Revision 1 Code Number D-0005
Just like a compass, the magnetometer inside the AHRS is sensitive to ferrous metals, or
magnetic fields produced by Landing Lights Wiring etc. Placing the AHRS close to a magnetic
compass is not a good idea, as this would affect the readout on both the magnetic compass and
the AHRS inside the BOM. As a rule of thumb, one foot is recommended. However, this is not
always possible, thus, the AHRS has internal algorithms that “learn” your aircraft
configuration as you fly. The heading might be off during initialization, but as soon as the
airplane starts turning, the AHRS starts compensating for any errors.
Be aware that this is magnetic heading and there will always be a magnetic deviation
(declination) to true north that varies according to your latitude and longitude. If you are
comparing the heading output on the AHRS to a GPS source, take into consideration that GPS
may be reporting “True Track”. You can add/subtract the corresponding magnetic deviation at
your current location to obtain True Heading.
9.1.3 Roll, Pitch and Yaw
The AHRS has three MEMs gyros and a 3-axis accelerometer that measures your airplane’s
attitude. When the AHRS is turned on, it requires a two-minute interval to calibrate itself. You
might see the horizon shifting ± 5 °during this self-calibration process and a flashing behavior
of the horizon. To achieve better performance, it is recommended that the aircraft stays in a
steady position (or taxing) during this two-minute period. During flight, the instrument will
calculate the aircraft’s attitude based on accelerations and rotation rates and you can expect the
horizon to have an accuracy of ± 3 ° degrees. Fast airplanes such as Jets and airlines with high
acceleration rates at take-off and landings, may experience a pitch up error right after take-off
until the airplane stabilizes. In this situation, it is recommended to perform a + 15 ° bank turn
to the left for 10 seconds, then a + 15 ° bank turn to the right at the beginning of the flight. The
instrument will operate in a full 360 degrees of turn and may be used in light aerobatic type
maneuvers. The gyros are rated for 500 °/sec max turn rates. When the maximum turn rate is
exceeded, the AHRS is temporarily disabled. This is indicated by a flashing behavior (pitch
goes from 0 to 90 degrees, and roll from 0 to 180 degrees). The instrument automatically resets
itself within 4 seconds if kept steady during that time, otherwise the instrument will recover
within 15-40 seconds depending on the amount of error induced during recovery. This will not
cause any harm to the instrument. Note: Moving the instrument with your hand will most likely
trigger the excess rotation alarm unless simulating smooth aircraft behavior.
9.1.4 Indicated Airspeed and Altitude
The BOM has pressure transducers installed, one for static pressure and another one for the
dynamic pressure. Having access to pitot-static information the AHRS can transmit Indicated
Airspeed and Pressure altitude at 29.92 inHg. To adjust the altitude due to barometric pressure

BOM (Broadcasting Outer Module) Company Standards
Effective Date 12/6/17 Page 10 of 12
Document No. 42 Revision 1 Code Number D-0005
changes, your navigation software of choice will allow you to input the altimeter setting at
your current location.
Both the differential and absolute pressure sensors are calibrated using a previously calibrated
and tested pressure sensor as a reference. The altitude is calibrated from sea level to 18,000 ft.
and the deviation after calibration cannot be more than ±40 ft. The Air Speed is calibrated from
0 to 320 kt. and the deviation after calibration cannot be more than ±3 kt.
9.2 Vibration Sensor
The sensor is designed to aid the BOM determine when to wake up. The BOM is designed to
turn ON with power input from the turbine, but since this process requires a minimum speed
of 60Kts, the BOM will not start until after takeoff. For this reason, the Vibration sensor is
mean to recognize an “Engine ON” versus “Engine OFF” state based on vibrations caused by
propeller’s RPM. When “Engine ON”, the BOM will initialize all its systems using power
from an internal battery. If an “Engine OFF” state is measured, and there is no power provided
by the turbine, the BOM will shut off after 15 seconds. If the battery is not charged, the
vibration sensor will not work, thus The Vibration sensor is not a guaranteed method for power
ON and is meant only for enhancing the BOM, and NOT as a primary switch ON feature.
9.3 Angle of Attack
The AOA is based on differential pressure sensor, and indicated airspeed. The angle of attack
requires user calibration to set the “near stall” point and the “max L/D” point of the aircraft.
The AOA data will be disabled until these two values are calibrated. This calibration is
performed using Levil’s dedicated AHRS Utility App on a tablet. To measure near stall point,
the pilot must fly at a minimum controllable airspeed and “SET NEAR STALL” using the App
interface. To measure the “max L/D” point, the pilot must fly at the Speed that will allow for
the best rate of climb (Vy), and “SET MAX L/D” using the App interface. Once the two
calibration points have been determined, the AOA gauge will be enabled.
9.4 Micro SD Memory Card
There is an internal memory designed to record telemetry data during flight, thus the BOM can
be used as a “Black Box”. The internal memory is not meant to be removable. The stored data
is instead broadcasted via Wi-Fi upon commands. The user can request a list of stored files
and/or the contents of a specific file. The Filename must contain the unique serial number, date
and time for the flight. Data can be stored at a rate of 1Hz or 5Hz (user selectable). Data inside
the file includes but is not limited to Identification (Call sign), GPS telemetry (track, speed
altitude etc.) AHRS telemetry, pressure data, error messages, etc.

BOM (Broadcasting Outer Module) Company Standards
Effective Date 12/6/17 Page 11 of 12
Document No. 42 Revision 1 Code Number D-0005
9.5 Position Source (GPS or GLONASS)
A WAAS capable position source is standard in the BOM. The antenna is located in the front,
right behind the Heated Nose cone. Thus, the BOM’s nose requires view to the satellites to
obtain a position fix. Installations that require the BOM to be located under the wing, must be
aware of degraded GPS reception due to Aluminum structures for example. It is recommended
to follow installation procedures as suggested for the type of aircraft. If a valid fix is obtained,
information from GPS/GLONASS source is broadcasted over Wi-Fi and stored in memory,
including Latitude, Longitude, Geometric Altitude, Ground Speed, Track, Climb Rate UTC
time. If the GPS/GLONASS source is not able to get a position fix, the BOM will continue to
stream primary flight data (i.e. AHRS) since other systems are independent from GPS.
9.6 ADS-B Dual Band Receiver
The BOM is equipped with a dual band ADS-B Receiver. The ADS-B received can capture
the following data:
 Flight Information Services–Broadcast (FIS-B): Is the ground-to-air broadcast of
meteorological and aeronautical information. FIS-B allows the pilot to passively collect
and display real-time weather and other operational data such as METAR, TAF,
NOTAMs etc.
 Traffic Information Services-Broadcast (TIS-B): Is the broadcast of traffic information
to ADS-B-equipped aircraft from ADS-B ground based transceivers. For an aircraft to
receive TIS-B services, the following conditions must exist:
o Your aircraft (or an aircraft within range) must be equipped with an ADS-B
OUT
o The aircraft must fly within the coverage volume of a compatible ground station
that is configured for TIS-B uplinks.
o The target aircraft must be within the coverage of, and detected by, at least one
of the ATC radars serving the ground station in use.
 Air-To-Air Traffic: Is the traffic broadcasted by other ADS-B Out equipped aircraft on
978 MHz
If you or somebody close to you is equipped with ADS-B out, your chances of seeing the traffic
is greatly improved. The second band (1090 MHz) can detect Mode-S transponders with the
extended squitter.
9.7 Wireless Transmission
The BOM has an internal Wi-Fi transceiver that acts as an access point. You may connect as
many as 7 devices simultaneously regardless of the operating system (iOS or Android). Note:
You do NOT need an Internet or Cellular connection in the air for your BOM to work.

BOM (Broadcasting Outer Module) Company Standards
Effective Date 12/6/17 Page 12 of 12
Document No. 42 Revision 1 Code Number D-0005
Communications have been tested to up to 100ft in an open field. Wi-Fi usually provides
significantly more range than Bluetooth.
You can have two Wi-Fi devices turned ON without interfering with each other. However, the
tablets can only connect to one Wi-Fi network at a time. Thus, if you have two devices using
Wi-Fi communications, you would have to switch networks back and forth to be able to access
each device temporarily.
9.8 Power System
The BOM is self-powered and completely independent from the power of the aircraft or any
of its systems. The BOM turns On and Off using a vibration sensor and it has an internal battery
which is recharged using a turbine. The excess power of the turbine is dissipated to the nose
and the heat keeps the nose free of ice.
9.8.1 Turbine
 DC Brushless Axial Flow Fan
 The fan motor is with single phases and four poles
9.8.2 Nose Heater
The turbine AC power is rectified and converted to 5 V via switching power supply. The excess
power is dissipated to the nose with a 12 V Zener Diode to keep the nose free of ice.