Page 1 of 14 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 Exe mption [Docket No. FAA

- 2015

- 0059]
To Whom it May Concern:
As you are aware, this office represents Vine Ranger s Inc. (" Vine Rangers ") regarding the above

- referenced Petition for Exemption, in which Vine Rangers seeks regulatory relief to allow commerci al 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 Robot ics 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 submit ting a UAS Operations Manual which contains additional information on these vehicles and their control sys tems. 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. Ad ditionally, 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. McKi nnon 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.comPage 2 of 14

Again, w e thank you for your prompt consider ation of the requested exemptions. Should you have any questions, or if you nee d 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.Page 3 of 14

(The following attached items contain proprietary and commercial information exempt from disclosure under the Freedom of Information Ac t, 5 U.S.C. § 522 et seq. , and should be held in a separate file pursuant to 14 C.F.R. § 11.35(b)).

Attachment s:
Vine Rangers' UAS Operations Manual
3DR X8+ Operation Manual

3DR RTF

- X8 Manual
3DR Flight Checklist
3DR PixHawk Autopilot

3DR Aero

- M Operation ManualPage 4 of 14 

### 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 co mpare 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. Instrumen tation 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 d ifferent 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 p lans, which must be uploaded to the aircraft prior to take

- off using the 3D Robotics Mission Planner software appli cation. The PIC may set the X8 to either an automatic takeoff or manual takeoff setting. At any time during the programmed flight, the PIC c an 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 zon es, 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 oper ational 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. Similar ly, 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 locatio n.

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.

M any advanced safety features were also designed into the aircraft, including intelligent fault handling that allows the aircraft to detect a syst em fault while airborne, and to automatically initiate the Return

- to

- Launch opera tions 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 th e aircraft’s operating altitude and operating distance.Page 5 of 14

Phy sical 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 Fli ght 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 : V ertical lift / manual or automatic landing avail able
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 th e 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 aircr aft.

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.Page 6 of 14

Reliability

– The X8 is designed for maximum reliability an d 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 conditi ons 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 los s o f communications between the X8 and the GCS will initiate a failsafe action of Return

- to

Launch 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 th e 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

 Mete rs 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 a nd 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 Nav igation Equipment

- The X8 can operate autonomously for take

off, inflight operations, and landing. In automatic takeoff, the PIC must first arm the X8 and its propellers in standard mod e. The PIC then switches the X8 to automatic mode and raises the throt tle. 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 fligh t plan that is loaded to the X8 prior to takeoff. In automatic la nding, 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 landin g. The PIC retains the ability to imm ediately take control of the X8 with manual flight mode.Page 7 of 14

Operating Modes: The X8 has three different operations modes:

 Auto : This is used for autonomous missions preprogrammed using the 3D Robotics Mission Planner softw are 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 switc h, the PIC directs the X8 to end its flight and land at the current position. The throttle joystick must be low ered 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 : Wi th this switch selected, the X8 returns to the launch point and initiates an automatic landing. The throttle joystick must be lo wered fully down so that the X8 automatically disarms its propellers upon touchdown. Du ring the automatic landing , the PIC may reposition the X8 using the right joystick. Note that the Return

- to

- Launch landing poin t is the location where the X8 was armed prior to takeoff.

Frequency Allocations

– 900 MHz, 2.4 GHz, and 5.8 GHz.

Takeoff and L anding

– Manual and automatic takeoff and la nding 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 throt tle. For manual takeoff, the X8 must be armed at which poin t the motors will spin. The X8 will also initiate an automatic landing when operating in an autonomous mode using the Mission Planner applicatio n. In th e Return

- to

- Launch mode, the X8 will return to its point of launch and automatically land. Simil arly, 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, a fter 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 t he 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 automa tically 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 si ngle sensor malfunction is likely to result in degraded performance rather than a fatal response.Page 8 of 14

Emergency Procedures and System Failures Airframe Failure

– Depending on the nature and severity, an airframe failure may result in decreased flight performan ce or a fatal response. Navigation System Failure

– The X8 requires GPS for operations. GPS must l ock 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 visua l 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 Retur n 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 yell ow status LED on the GCS.

Line

- of

- Sight Loss

– All flight operation s will be conducted with the X8 within visual l ine

- of

- sight of the PIC. The X8 is set to a default of a geo

- fe nce of 300m (984 ft). If the X8 travels beyond the 300m geo

- fence, it automatic ally 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 th e geo

- fence is exceeded, the X8 automatically switches to Return

- to

- Launc h. Security

– The X8 and communications links are encrypted by the manufacturer’s proprietary software.Page 9 of 14 

### 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. Th e 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. Thi s 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 oper ator 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 spe ed, 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” operatio ns mode, the PIC controls all axes of the Aero

M without any assistance from the system’s autopilot function. The remaining control methods are semi autonomous 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, t he 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 pre programmed flight, the PIC may utilize addit ional 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 operator

specified flight parameters

. This reduces the needed operating are a 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 t he 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, w hich 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 o peration, 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 t o monitor the location of the Aero

- M through the flight data screen.Page 10 of 14

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 automatic ally 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 flig ht 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 s tyle/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 tim e 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 t he 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.Page 11 of 14

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 no t 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 vehic le 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 monito red 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

v isual 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 prev ent 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 Return

to

- 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 ri ght 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.
Disp layed 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 Stat us

 Aero

- M Battery Status

 Local time

 UAS Failsafe Action (e.g., low battery, etc.)Page 12 of 14

Onboard Flight Instruments

- The Aero

- M is equipped with an Inertial Navigation System (3

- axis gyroscope, 3

- axis magnetometer, 3 axis accelerometers, GPS receiver, baromet ric 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 launche s 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 : Th is mode directs the aircraft to circle over the takeoff or la unch 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 Aero

M. 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 t he 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. InPage 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 fli ght), 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 ope rated 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 t hen 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 a llow 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 re quired 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 respons e 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 i n 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 Shutd

own

– A failure or shutdown of the GCS automatically initiates Return

- to

Launch 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

- of

sight 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 pro prietary software.