Levil Aviation BOM Bedienungsanleitung
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: (407) 542-3971
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
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