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March 17, 2015

U.S. Department of Transportation

Docket Management System

1200 New Jersey Ave., SE

Washington, DC 20590

Re: Additional Information —Vine Rangers, Inc., Section 333 Petition for

Exemption [Docket No. FAA-2015-0059]

To Whom it May Concern:

As you are aware, this office represents Vine Rangers Inc. ("Vine Rangers") regarding the 

above-referenced Petition for Exemption, in which Vine Rangers seeks regulatory relief to allow 

commercial operation of small unmanned aircraft system ("sUAS"). Please accept this letter as a 

supplement to Vine Rangers' Petition for Exemption filed on January 13, 2015 [Docket No. 

FAA-2015-0059].

Vine Rangers has determined that it will operate the 3D Robotics RTF X8 (rotorcraft) and 

the 3D Robotics Aero-M (fixed-wing) vehicles to conduct the proposed operations in the Petition 

for Exemption. A description of the physical and operating characteristics for the 3D Robotics 

RTF X8 is attached as Appendix A. A description of the physical and operating characteristics 

for the 3D Robotics Aero-M is attached as Appendix B. 

Vine Rangers is also submitting a UAS Operations Manual which contains additional 

information on these vehicles and their control systems. Vine Rangers submits these supporting 

materials as confidential documents pursuant to 14 C.F.R. § 11.35(b), as the materials contain 

confidential commercial and/or proprietary information that Vine Rangers has not and will not 

share with others. Additionally, these documents contain operating conditions and procedures 

that are not generally available to the public and are protected from release under the Freedom of 

Information Act, 5 U.S.C. § 552 et seq.

Albany

Atlanta

Brussels

Denver

Los Angeles

Miami

New York

1676 International Drive • Penthouse

McLean, VA 22102

Tel: 703.336.8800

mckennalong.com

Northern Virginia

Orange County

Rancho Santa Fe

San Diego

San Francisco

Seoul

Washington, DC

Mark E. McKinnon

703.336.8714

Matthew J. Clark

703.336.8714

Lisa M. Ellman

202.496.7184

Email Address

mmckinnon@mckennalong.com

mclark@mckennalong.com

lellman@mckennalong.com
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Again, we thank you for your prompt consideration of the requested exemptions. Should 

you have any questions, or if you need any additional information relating to Vine Rangers' 

Petition for Exemption, please do not hesitate to contact the undersigned.

Very truly yours, 

Matthew J. Clark

Lisa M. Ellman

Mark E. McKinnon 

 

Counsel for Vine Rangers, Inc.
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(The following attached items contain proprietary and commercial information exempt from 

disclosure under the Freedom of Information Act, 5 U.S.C. § 522 et seq., and should be held in a 

separate file pursuant to 14 C.F.R. § 11.35(b)). 

Attachments:

Vine Rangers' UAS Operations Manual

3DR X8+ Operation Manual 

3DR RTF-X8 Manual 

3DR Flight Checklist 

3DR PixHawk Autopilot 

3DR Aero-M Operation Manual
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APPENDIX A

3D Robotics RTF X8

Systems Overview

The X8 can carry payloads up to 1.7 lbs. The system contains two full Inertial Measurement Unit 

("IMU") sensor suites, one acting as the primary flight sensor and the other used to compare data 

inflight and failover functionality, if it becomes necessary. The system also contains a barometer 

sensor. This eliminates the difficult portion of flying. The PIC has the ability to control the speed, 

roll, yaw and pitch of the aircraft.

The X8 was designed to be flown within the direct VLOS of the operator at all times. All flight 

operations take place as a result of direct input by the PIC. Flight adjustments are made based on a 

two control stick system that is located on the GCS. Instrumentation indicating heading, altitude, 

horizontal speed, GPS position, battery level, data link, and GPS accuracy are additional aids made 

available to the PIC through the flight data screen located on the GCS. The aircraft was designed to 

operate in three different flight modes. In the basic “Manual” operations mode, the PIC controls all 

axes of the X8 without any assistance from the system’s autopilot function.

An autonomous operations, or “Auto,” mode is available through available pre-programmed flight 

plans, which must be uploaded to the aircraft prior to take-off using the 3D Robotics Mission Planner 

software application. The PIC may set the X8 to either an automatic takeoff or manual takeoff 

setting. At any time during the programmed flight, the PIC can provide inputs to abort and/or 

override the programmed flight to take immediate control of the aircraft. For pre-programmed flight, 

the PIC may utilize additional navigation settings, including landing spots and flight area (including 

visual no-fly zones, maximum altitude, and minimum altitude), so that the aircraft operates only 

within operator-specified flight parameters. In other words, Vine Ringers will set up virtual fencing 

around the operational area, preventing the X8 and the PIC from operating outside the planned flight 

area, including altitude. This reduces the needed operating area by omitting the need to factor in 

additional room for PIC operating error. In addition to the pre-programmable parameters, the X8 is 

also set to default limits of 300 meters in distance and 100 meters in altitude.

In a “Return-to-Launch” mode, the X8 returns to the position where it acquired GPS lock and 

completes an automatic landing. Similarly, in the “Loiter” mode, the X8 enters a hover at its current 

altitude, which is again directed by the PIC on the GCS. In “Land” operations mode, the X8 initiates

an automatic landing at its current location.

The X8 utilizes GPS for many modes of operation, making the system easy to navigate. In the case of 

lost or degraded GPS signal, the aircraft automatically switches to Manual operations mode so that the 

PIC may navigate the aircraft to a safe landing point. At all times through the GCS, the PIC is able to

monitor the location of the X8 through the flight data screen.

Many advanced safety features were also designed into the aircraft, including intelligent fault 

handling that allows the aircraft to detect a system fault while airborne, and to automatically initiate 

the Return-to-Launch operations mode. For example, the X8 detects a loss of GPS, warns the PIC 

of the status and automatically enters Manual operations mode. Other faults that can be detected 

include loss of communication, and low battery levels. The PIC also comes with default geo-fence 

settings that limit the aircraft’s operating altitude and operating distance.
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Physical Characteristics of the X8

Dimensions

 Width: 35 cm

 Length: 51 cm

 Height: 20 cm

Weight and payload

 Aircraft weight w/battery: 5.6 lbs

 Payload capacity: 1.7 lbs

 Max take-off weight: 7.3 lbs

Flight characteristics

 Maximum Turbulence Rating: light

 Radio Range: .6 miles

 Flight Time: 15 minutes

 Airspeed: 14.5 mph default (6.5 m/s)

 Max altitude ASL: approximately 8,000 feet (MSL)1

Landing style/type: Vertical lift / manual or automatic landing available

Propulsion System

 Engines - The X8 is powered by SunnySky V2216-12 KV800 II motors that are 

connected to 8 APC propellers.

 Batteries - The X8 utilizes a removable, rechargeable, lithium-polymer battery. 

The charge level status from the battery on the aircraft is continually monitored and 

real time levels are displayed on the control system used by the PIC. Predefined 

voltage levels indicate a low battery warning, which provides the PIC with a 

warning alarm that is both visual and audible. In such an instance, the aircraft will 

automatically initiate a landing at its current location. At any time during the 

battery warnings, full control of the aircraft is maintained. The battery is charged 

using a standard wall charger that is provided with the aircraft.

Maintenance - The X8 is nearly maintenance free. Maintenance consists of inspections and 

verification of communications performed by a qualified person prior to each flight. Preflight 

checklist includes but is not limited to:

 Visual inspection of the aircraft, including the airframe, the front and rear arms, 

the propellers, and GPS mast;

 All payload system connections and components;

 Check charge of all batteries (aircraft and control system).

 

1 As provided operational conditions and limitations No. 6 of the Vine Rangers Petition for 

Exemption, flights will be operated at an altitude of no more than 400 feet AGL and will never 

enter navigable controlled airspace without prior written authorization and approval from the 

FAA.
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Reliability – The X8 is designed for maximum reliability and to maintain performance over its life. 

The only components that experience routine wear are the propeller, batteries, motor, and servos. 

Battery conditions are monitored by the system with deviations reported to the PIC.

Contact with other objects during flight may cause other components, particularly the propeller, 

wings and servos to become damaged. Damaged components are likely to be detected during the full 

visual inspection of the airframe performed before each flight.

The X8 detects numerous conditions which may make flying unsafe, such as reduced GPS 

accuracy, low battery charge, and lost-link with the GCS. Automatic pre-flight calibration checks 

prevent the aircraft from taking off if such conditions are present. During flight, a degradation or 

loss of communications between the X8 and the GCS will initiate a failsafe action of Return-toLaunch and complete an automatic landing. This is displayed visually on the GCS.

Command and Control Systems - The GCS allows the PIC simultaneous control over the aircraft 

and any payloads. The right and left control sticks are located on the GCS and permit quick 

navigation. The flight data display screen provides all essential flight data to the PIC. The 

transmission of telemetry data to the GCS is selectable to the PIC at a rate up to 20 hz.

Displayed on GCS:

 Barometric Altitude

 Ground Speed

 Flight Time

 Ground Station Signal

 Position (Latitude and Longitude)

 Mode of Operation

 GPS Satellite (number of satellites)

 GPS Status

 GCS Battery Status

 X8 Battery Status

 Meters from Launch Point

 UAS Failsafe Action (e.g., low 

battery, etc.)

Onboard Flight Instruments - The X8 is equipped with an Inertial Navigation System (3-axis 

gyroscope, 3-axis magnetometer, 3 axis accelerometers, GPS receiver, barometric pressure 

sensor and GPS module).

Onboard Computer Systems - The X8 is equipped with on-board computer systems to 

monitor (sensors, battery, etc.), control (speeds, altitude, position, etc.), and communicate 

(control, telemetry, etc.) with the PIC.

On-board Guidance and Navigation Equipment - The X8 can operate autonomously for takeoff, inflight operations, and landing. In automatic takeoff, the PIC must first arm the X8 and its 

propellers in standard mode. The PIC then switches the X8 to automatic mode and raises the 

throttle. For autonomous inflight operations 3D Robotics utilizes the Mission Planner software 

application. Mission Planner is a computer-based application for the PIC or operator to build a 

flight plan that is loaded to the X8 prior to takeoff. In automatic landing, the PIC must input a 

landing waypoint into a mission prior to takeoff. The aircraft will land automatically at the 

landing waypoint, but the PIC must lower the throttle fully down so that the propellers disarm 

after the aircraft completes the landing. The PIC retains the ability to immediately take control of 

the X8 with manual flight mode.
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Operating Modes: The X8 has three different operations modes:

 Auto: This is used for autonomous missions preprogrammed using the 3D Robotics 

Mission Planner software application.

 Loiter: By selecting this mode, the PIC directs the aircraft to enter a hover.

 Standard: This is full manual control without assistance of the autopilot.

Landing Modes: The X8 has two additional landing modes:

 Land: By selecting this switch, the PIC directs the X8 to end its flight and land at the 

current position. The throttle joystick must be lowered fully down so that the X8 

automatically disarms the propellers upon touchdown. During the land sequence, the PIC 

may reposition the X8 using the right joystick.

 Return-to-Launch: With this switch selected, the X8 returns to the launch point and

initiates an automatic landing. The throttle joystick must be lowered fully down so that the 

X8 automatically disarms its propellers upon touchdown. During the automatic landing, the 

PIC may reposition the X8 using the right joystick. Note that the Return-to-Launch landing 

point is the location where the X8 was armed prior to takeoff.

Frequency Allocations – 900 MHz, 2.4 GHz, and 5.8 GHz.

Takeoff and Landing – Manual and automatic takeoff and landing functions exist on the X8. 

Automatic takeoff requires the use of the Mission Planner software application. To initiate the 

automatic takeoff, the PIC must arm the aircraft and its propellers and then switch the aircraft into 

automatic mode and raise the throttle. For manual takeoff, the X8 must be armed at which point the 

motors will spin. The X8 will also initiate an automatic landing when operating in an autonomous 

mode using the Mission Planner application. In the Return-to-Launch mode, the X8 will return to its 

point of launch and automatically land. Similarly, in the Land mode, the X8 will land at its current 

location.

Navigation System – The X8 requires GPS lock prior to operation. The X8 is capable of 

navigation solely by the visual line-of-sight of the PIC and in manual mode operation. However, 

the aircraft may also be operated through pre-programmed flight plans, which are uploaded to the 

aircraft prior to take-off. An auto takeoff may be performed, after which the aircraft then begins its 

preprogrammed flight plan. Alternatively, the PIC may conduct a manual takeoff and then initiate 

the preprogrammed flight plan. At any time during the preprogrammed flight, the PIC can override 

the autopilot, abort the mission, and take immediate control of the aircraft. The X8 is set to default 

geo-fence settings that prevent the aircraft from exceeding an altitude of 100m (328 ft), and a 

distance of 300m (984 ft) from the GCS. If those limitations are exceeded, the aircraft 

automatically initiates the Return-to-Launch mode and lands.

Redundant Systems – The X8 combines the input from a multitude of sensors. Even though the 

data from all sensors is required for optimal system performance, dependent on the sensor, a single 

sensor malfunction is likely to result in degraded performance rather than a fatal response.
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Emergency Procedures and System Failures

Airframe Failure – Depending on the nature and severity, an airframe failure may result in 

decreased flight performance or a fatal response.

Navigation System Failure – The X8 requires GPS for operations. GPS must lock prior to takeoff. If 

the X8 loses GPS lock in flight, an aural and visual warning is provided to the PIC. The aircraft 

automatically switches into manual control (altitude hold mode) on the GCS. The PIC may also 

change this failsafe from manual control to an automatic landing.

Power Failure – A complete battery failure which results in power loss to the aircraft will result in a 

fatal response.

Low Battery Condition – The PIC is alerted of a low battery condition through both a visual and 

aural warning, and the X8 initiates an immediate landing mode at its current location.

GCS Fail or Shutdown – A failure or shutdown of the GCS automatically initiates Return to Launch 

mode. In “Auto” mode, the aircraft will continue on its mission.

GCS Signal Loss – If the X8 loses contact with the GCS, the aircraft returns to the launch point and 

lands automatically. The PIC is alerted to this situation with a blinking yellow status LED on the 

GCS.

Line-of-Sight Loss – All flight operations will be conducted with the X8 within visual line-of-sight 

of the PIC. The X8 is set to a default of a geo-fence of 300m (984 ft). If the X8 travels beyond the 

300m geo-fence, it automatically returns to its launch point and lands. The default setting may be 

disabled by the PIC.

Altitude Failsafe – The X8 has a 100m (328 ft) altitude geo-fence enabled by default. If the geo-fence 

is exceeded, the X8 automatically switches to Return-to-Launch.

Security – The X8 and communications links are encrypted by the manufacturer’s proprietary 

software.
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APPENDIX B

3D Robotics Aero-M 

The 3D Robotics Aero-M system can carry payloads up to 1.1 lbs. It operates with a maximum 

wind threshold of 25 mph. The system contains two full IMU sensor suites, one acting as the 

primary flight sensor and the other used as a comparison for monitoring IMU health and full 

failover functionality, if it becomes necessary. The system also contains two barometer sensors. 

This eliminates the difficult portion of flying. The PIC has the ability to control the speed, roll, yaw 

and pitch of the aircraft.

The Aero-M has an operational range of approximately 250 acres, but was designed to be flown 

within the direct VLOS of the operator at all times. All flight operations take place as a result of 

direct input by the PIC. Flight adjustments are made based on a two control stick system that is 

located on the GCS. Instrumentation indicating heading, altitude, climb rate, horizontal speed, GPS 

position, battery level, data link, and GPS accuracy are additional aids made available to the PIC 

through the flight data screen located on the GCS. The aircraft was designed to operate in six 

different flight modes. In the basic “Manual” operations mode, the PIC controls all axes of the AeroM without any assistance from the system’s autopilot function. The remaining control methods are 

semiautonomous in functionality.

An autonomous operations, or “Auto,” mode is available through available pre-programmed flight 

plans, which must be uploaded to the aircraft prior to take-off using the 3D Robotics Mission 

Planner software application. The PIC may set the Aero-M to either an automatic takeoff or manual 

takeoff setting. After departing the ground, the aircraft initiates the preprogramed flight. At any time 

during the programmed flight, the PIC can provide inputs to abort and/or override the programmed 

flight to take immediate control of the Aero-M. For preprogrammed flight, the PIC may utilize 

additional navigation settings, including landing zones and flight area (including visual no-fly zones, 

maximum altitude, and minimum altitude), so that the Aero-M operates only within operatorspecified flight parameters. This reduces the needed operating area by omitting the need to factor in 

additional room for PIC operating error.

In a “Fly by Wire” mode, the autopilot manages the control surfaces and navigates the Aero-M 

based on direction by the PIC. In a “Return to Launch” mode, the Aero-M returns to the position 

where it acquired GPS lock and enters a circle pattern at an altitude of 100 meters which is 

programmable by the operator. Similarly, in the “Loiter” mode, the Aero-M enters a circle pattern 

with a radius of 60 meters at its current altitude, which is again programmable by the PIC. Finally, 

“Stabilize” mode allows for manual control by the PIC. When the PIC releases the right control 

stick, however, the Aero-M will automatically return to level flight.

The Aero-M utilizes GPS for many modes of operation, making the system easy to navigate. In the 

case of lost or degraded GPS signal, the PIC may enable either the Manual or Fly by Wire 

operations modes to navigate the aircraft to a safe landing point. At all times through the GCS, the 

PIC is able to monitor the location of the Aero-M through the flight data screen.
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Many advanced safety features were also designed into the aircraft, including intelligent fault 

handling that allows the aircraft to detect a system fault while airborne, and to automatically initiate 

the Return-to-Launch operations mode. For example, the Aero-M detects a loss of GPS and warns 

the PIC of the status. Other faults that can be detected include loss of communication, and low 

battery levels. The PIC can also create maximum flight altitudes so the Aero-M cannot go above a 

pre-set maximum altitude.

Physical Characteristics of the Aero-M

Dimensions

 Width: 188 cm (74 in) (wingspan)

 Length: 129 cm (51 in)

Weight and payload

 Aircraft weight w/battery: 6.8 lbs

 Payload capacity: 1.1 lbs

 Max take-off weight: 7.9 lbs

Flight characteristics

 Maximum Turbulence Rating: light

 Radio Range: .6 miles

 Flight Time: 40 minutes

 Max Operational Wind Speed: 25 mph (11 m/s)

 Approx. max airspeed: 56 mph (90 kmh)

 Approx. min airspeed: 22 mph (35 kmh)

 Max altitude ASL: approximately 8,000 feet

 Landing Accuracy: 6.5 feet latitude x 131 feet longitude (2 m x 40 m)

Landing style/type – Approach and controlled descent / manual or automatic landing available

Propulsion System

 Engines - The Aero-M is powered by 1 Tiger AT2820-7, 830 kV motor that is 

connected to a Gemfan 11x7 propeller.

 Batteries - The Aero-M utilizes a removable, rechargeable, lithium-polymer 

battery. The charge level status from the battery on the aircraft is continually 

monitored and real time levels are displayed on the control system used by the 

PIC. Predefined voltage levels indicate a low battery warning, which provides the 

PIC with a warning alarm that is both visual and audible. In such an instance, the 

aircraft will automatically return to circle above the point of launch/take-off and 

circle overhead. If the battery reaches 25% of charge, the aircraft will result in an 

additional low battery alarm that is both visual and audible. At any time during 

the battery warnings, full control of the aircraft is maintained. Ignoring the 

critical battery warning could result in a critical flight system failure. The battery 

is charged using a standard wall charger that is provided with the aircraft.
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Maintenance - The Aero-M is nearly maintenance free. The airframe has only 2 ceramic bearings 

in its motor and, thus, has very few moving parts. Maintenance consists of inspections and 

verification of communications performed by a qualified person prior to each flight.

Preflight checklist includes but is not limited to:

 Visual inspection of the airframe, including the airframe, tail and tail boom, the servo 

rods, airspeed sensor, and proper balance of the aircraft;

 All payload system connections and components;

 Check charge of all batteries (aerial vehicle and control system).

Reliability – The Aero-M is designed for maximum reliability and to maintain performance over 

its life. The only components that experience routine wear are the propeller, batteries, motor, and 

servos. Battery conditions are monitored by the system with deviations reported to the operator.

Contact with other objects during flight may cause other components, particularly the propeller, 

wings and servos to become damaged. Damaged components are likely to be detected during the full 

visual inspection of the airframe performed before each flight.

The Aero-M detects numerous conditions which may make flying unsafe, such as reduced GPS 

accuracy, low battery charge, and lost-link with the GCS. Automatic pre-flight calibration checks 

prevent the aircraft from taking off if such conditions are present. During flight, a degradation or 

loss of communications between the Aero-M and the GCS may initiate a failsafe action of Returnto-Launch. This is displayed visually on the GCS. At that point, the PIC may land the aircraft, or an 

auto-land is initiated in which the aircraft descends at a controlled rate from its current position.

Command and Control Systems - The GCS allows the PIC simultaneous control over the 

aircraft and any payloads. The right and left control sticks are located on the GCS and permit 

quick navigation. The flight data display screen provides all essential flight data to the PIC. The 

transmission of telemetry data to the GCS is selectable to the PIC at a rate up to 20 hz.

Displayed on GCS:

 Barometric Altitude

 Heading

 Bank Angle

 Altitude

 Ground Speed

 Climb Rate

 Flight Time

 Ground Station Signal

 Position (Latitude and 

Longitude)

 Mode of Operation

 GPS Satellite (number 

of satellites)

 GPS Satellite HDOP

 GPS Status

 GCS Battery Status

 Aero-M Battery Status

 Local time

 UAS Failsafe Action 

(e.g., low battery, etc.)
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Onboard Flight Instruments - The Aero-M is equipped with an Inertial Navigation System (3-

axis gyroscope, 3-axis magnetometer, 3 axis accelerometers, GPS receiver, barometric pressure 

sensor and GPS module).

On-board computer systems - The Aero-M is equipped with on-board computer systems to 

monitor (sensors, battery, etc.), control (speeds, altitude, position, etc.), and communicate (control, 

telemetry, etc.) with the PIC.

On-board Guidance and Navigation Equipment - The Aero-M can operate autonomously for 

take-off, inflight operations, and landing. In automatic takeoff, the PIC must set the aircraft to 

autonomous mode and it then senses direction of movement and launches the aircraft in that 

direction. For autonomous inflight operations 3D Robotics utilizes the Mission Planner software 

application. Mission Planner is a computer-based application for the PIC or operator to build a 

flight plan that is loaded to the Aero-M prior to takeoff. In automatic landing, the PIC must input a 

pattern of waypoints into a mission prior to takeoff. The waypoints are set at different locations and 

altitudes so that the aircraft gradually descends in a controlled and gradual manner to land safely. 

The PIC retains the ability to immediately take control of the Aero-M with a manual flight mode.

The Aero-M has six different operations modes:

 Auto: This is used for autonomous missions preprogrammed using the 3D Robotics 

Mission Planner software application.

 Fly by Wire: An assisted manual control where the autopilot system manages the 

flight control surfaces and navigates the aircraft based on inputs from the PIC.

 Return-to-Launch: This mode directs the aircraft to circle over the takeoff or launch 

point. The aircraft will enter a circle pattern at an altitude of 100 meters.

 Loiter: By selecting this mode, the PIC directs the aircraft to enter a circle pattern with a 

radius of 60 meters at the current altitude. The PIC may adjust the position of the circle 

pattern with the right control stick.

 Stabilize: This mode consists of manual control by the PIC with an additional 

safeguard that returns the aircraft to a level flight orientation with release of the right 

control stick.

 Manual: This is full manual control without assistance of the autopilot.

Frequency Allocations - 900 MHz, 2.4 GHz, and 5.8 GHz.

Takeoff and Landing – Manual and automatic takeoff and landing functions exist on the AeroM. In automatic takeoff, the PIC must set the aircraft to autonomous mode and it then senses 

direction of movement. The PIC stands into the wind holding the aircraft above his or her head. 

The PIC then runs and throws the Aero-M at an upwards angle. The aircraft senses the throw, 

powers the motor, and climbs to the altitude specified by the “takeoff” waypoint preprogrammed 

in the Mission Planner application uploaded to the aircraft prior to flight. In manual mode, the 

Aero-M is launched into the air from the same running position used in automatic takeoff, 

however, the PIC must immediately adjust the GCS to control the aircraft once it is airborne.

In automatic landing, the PIC must input a pattern of waypoints into a mission, using the Mission 

Planner software application, prior to takeoff. The waypoints are set at different locations and 

altitudes so that the aircraft gradually descends in a controlled and gradual manner to land safely. In 
Page 13 of 14

manual landing mode, the PIC directs the Aero-M to a circle pattern (similar to a traffic pattern 

used in manned aircraft flight), followed by a final approach pattern flown into the wind at 

decreasing altitude.

Navigation System – The Aero-M is capable of navigation solely by the visual line-of-sight of the 

PIC and in manual mode operation. However, the aircraft may also be operated through preprogrammed flight plans, which are uploaded to the aircraft prior to take-off. An auto takeoff may be 

performed, after which the aircraft then begins its preprogrammed flight plan. Alternatively, the PIC 

may conduct a manual takeoff and then initiate the preprogrammed flight plan. At any time during 

the preprogrammed flight, the PIC can override the autopilot, abort the mission, and take immediate 

control of the aircraft. The aircraft supports complex and simple geo-fencing features that allow the 

PIC to create vertical and horizontal virtual walls to prevent the aircraft from operating outside that 

preprogrammed area.

Redundant Systems — The Aero-M combines the input from a multitude of sensors. Even though 

the data from all sensors is required for optimal system performance, dependent on the sensor, a 

single sensor malfunction is likely to result in degraded performance rather than a fatal response.

Emergency Procedures and System Failures

Motor Failure - This will cause a fatal response in flight performance if the motor fails. 

However, the flight control surfaces will remain responsive and the aircraft can glide to the 

ground under manual control.

Airframe Failure – Depending on the nature and severity, an airframe failure may result in 

decreased flight performance or a fatal response.

Navigation System Failure – In a navigation system failure, or loss of communications 

channels required for autonomous operations, a failsafe visual and aural warning will display 

on the GCS and the Aero-M will initiate Return to Launch mode. Manual control may also be 

initiated on the GCS.

Power Failure – A complete battery failure which results in power loss to the aircraft will 

result in a fatal response.

Low Battery Condition – The PIC is alerted of a low battery condition through both a visual 

and aural warning, and the Aero-M initiates Return to Launch mode where it enters a circle 

pattern. In a critical battery condition, the PIC is again alerted through an aural and visual 

warning.

GCS Fail or Shutdown – A failure or shutdown of the GCS automatically initiates Return-toLaunch mode. In “Auto” mode, the aircraft will continue on its mission.

Line-of-Sight Loss – All flight operations will be conducted with the Aero-M within visual line-ofsight of the PIC. If the PIC's view becomes obstructed and line-of-sight is lost, the PIC may 

immediately place the aircraft into the Return to Launch or Loiter modes of operations.
Page 14 of 14

Security – The Aero-M and communications links are encrypted by the manufacturer’s proprietary 

software.