### Applewhite Aero ● applewhiteaero.com ● PO Box 46955 Seattle WA 98146 ● 206.762.5285

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# Applewhite Aero

Safety Checklist

Oculus UAS

### Applewhite Aero

Oculus Safety Checklist

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PROPRIETARY Rev. Date Pages Affected REVISIONS AUTHOR CHECK AP PROVE D

1 6/01/2015 ALL Updated Document J DP J M E PGA

Source Document

This document addresses requirements of 14 CFR 91.

Reference Document

This document references FAA Order 8130.34C.

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# Table of Contents

1. Introduction

................................ ................................ ................................ ................................ ............... 5

2. Aircraft Segment

................................ ................................ ................................ ................................ ........ 5

A. Airframe

................................ ................................ ................................ ................................ .............. 5

B. UA Performance Characteristics

................................ ................................ ................................ ......... 7

C. Propulsion System

................................ ................................ ................................ ............................... 9

D. Fuel System

................................ ................................ ................................ ................................ ......... 9

E. Electrical System

................................ ................................ ................................ ................................ . 9

F. Flight Control Surfaces and Actuators

................................ ................................ .............................. 11

G. Payloads

................................ ................................ ................................ ................................ ............ 14

3. Control and Communications Segment

................................ ................................ ................................ ... 14

A. Avionics

................................ ................................ ................................ ................................ ............ 14

B. Navigation

................................ ................................ ................................ ................................ ......... 14

C. UA Flight Controls

................................ ................................ ................................ ............................ 16

D. Aut opilot

................................ ................................ ................................ ................................ ........... 17

E. Control Link

................................ ................................ ................................ ................................ ...... 17

F. Lost Link and Flight Recovery

................................ ................................ ................................ .......... 20

G. Control Station

................................ ................................ ................................ ................................ .. 21

4. Ground Support Equipment

................................ ................................ ................................ ..................... 23

5. Processes and Procedures

................................ ................................ ................................ ........................ 24

A. Configuration Management

................................ ................................ ................................ .............. 24

B. Software Management

................................ ................................ ................................ ...................... 24

C. Ele ctronic Hardware Design and Testing

................................ ................................ .......................... 25

6. Operations

................................ ................................ ................................ ................................ ................ 26

A. National Airspace System (NAS) Integration and Interaction

................................ .......................... 26

B. Flight Phases

................................ ................................ ................................ ................................ ..... 27

C. Operating Areas

................................ ................................ ................................ ................................ 31

D. Flight Envelope and Test Plans

................................ ................................ ................................ ......... 37

E. Operating History

................................ ................................ ................................ .............................. 38

F. Manuals

................................ ................................ ................................ ................................ ............. 39

7. Organizational Considerations

................................ ................................ ................................ ................. 39

A. Pilot/Crew Qualifications/Training

................................ ................................ ................................ ... 39

B. Maintenance

................................ ................................ ................................ ................................ ...... 41

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# Table of Figures

Figure 1: The Oculus UAS

................................ ................................ ................................ ........................... 5
Figure 2: Front

- Top View

................................ ................................ ................................ ............................. 6
Figu re 3: Right Side View

................................ ................................ ................................ ............................ 6
Figure 4: Wiring Diagram

................................ ................................ ................................ ........................... 10
Figure 5: Ground Control Station Sample Screen

................................ ................................ ...................... 10
Figure 6: Oculus UAS Electrical Diagram (battery capacity may vary)

................................ ..................... 11
Figure 7: Oculus Control Surfaces

................................ ................................ ................................ .............. 12
Figure 8: Oculus Wing Surface Servos

................................ ................................ ................................ ....... 12
Figure 9: Oculus Tail Servos

................................ ................................ ................................ ...................... 13
Figure 10: Avionics Architecture

................................ ................................ ................................ ................ 14
Figure 11: RC Transmitter

................................ ................................ ................................ .......................... 16
Figure 12: Communications Diagram

................................ ................................ ................................ ......... 18
Figure 13: GCS Flight Plan Screen

................................ ................................ ................................ ............. 22
Figure 14: Pendleton Location Sectional

................................ ................................ ................................ .... 32
Figure 15: Pendleton Primary Test Area

................................ ................................ ................................ ..... 33
Figure 16: Pendleton Secondary Test Area

................................ ................................ ................................ . 34
Figure 17: R

- 6701

................................ ................................ ................................ ................................ ....... 35
Figure 18: Whidbey Island Primary Test Area

................................ ................................ ........................... 36
Figure 19: Whidbey Island Secondary Test Area

................................ ................................ ....................... 37



# List of Abbreviations and Acronyms

ATC Air Traffic Control

COTS Commercial Off

- the

- Shelf

ESC Electronic Speed Control

FCC Federal Communications Commission

FRS Flight Recovery System

GCS Ground Control Station

GPS Global Positioning System

HIL Hardware

- in

- the

- Loop

IAW In Accordance With

IMU Inertial Measurement Unit

LOS Line of Sight

NAS National Airspace System

NOTAM Notice s to Airm e n OPA Optionally Piloted Aircraft

PIC Pilot in Command

RC Radio Control

RF Radio Frequency

SIL Software

- in

- the

- Loop

STA Special Temporary Authority

UA Unmanned Aircraft

UAS Unmanned Aerial System

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### VFR Visual Flight Rules

VMC Visual Meteorological Conditions

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## 1. Introduction

The safety checklist is designed to help the FAA evaluate those hazards that are unique to UAS, OPA, or OPA/UAS in support of issuing a special airworthiness certificate. Some safety items only require brief responses and others may not be applicable to a specific pr ogram. Additional information and supporting documentation may be required during the evaluation process.

Note: The applicant must identify all responses that contain information deemed proprietary, confidential, company

- sensitive, subject to International Traffic in Arms Regulations (22 CFR subchapter M), or subject to any other classification that would restrict or prevent the information from public or foreign disclosure.



## 2. Aircraft Segment

A. Airframe

(1) Structure. Describe in detail the physical characteri stics of the unmanned aircraft ( UA ) . Include diagrams and schematics, as necessary.

The Oculus UAS is made up of five separate sections. The separate portions include the two wings, the tail, the cockpit cover, and the fuselage. The Oculus UAS can be compactly stored in a carrying case allowing for easy assembly, disassembly, storage and

transport.

Figure 1 : The Oculus UAS

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PROPRIETARY Figure 2 : Front

- Top View

Figure 3 : Right Side View

(2) Composition. Describe the various materials and where they are used in the construction of the UA. Include details of the fabrication and construction processes and procedures.

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PROPRIETARY The Oculus UAS is mostly composed of Styrofoam. The fuselage and all flying surfaces are Styrofoam with an inner structure made of light ply. A hollow carbon tube 1” in diameter connects the fuselage to the “T”

- tail. The wings and tail also have smaller carbon tubing to take all the loading. The airframe is purchased from a commercial supplier.

(3) Ability to Withstand Flight Loads. Describe the capability of the airframe structure to withstand expected flight loads and provide data/analysis to show that it is flutter

- free throughout the flight envelope. Include any loads or stress analysis that demonstrates positive structural margins of safety during flight.

The airframe is a commercially available hobby plane that has been widely used by radio control (RC) hobbyists around the world. Applewhite Aero may gather f light

p erformance data during experimental flight testing.

(4) Unique Characteristics. Identify and describe any unique design characteristic(s) such as a hydraulic system, environmental control system, parachute, or brakes.

The Oculus UAS does not have any uni que design characteristics.

(5) Measurements :

(a) Wingspan : 102 inches

(b) Fuselage length : 45 inches

(c) Body diameter : ≈ 7 inches at widest point

(6) Weight :

(a) Empty: ≈ 2.75 pound

(b) Maximum gross takeoff weight: ≈ 7 pounds



### B. UA Performance Characteristics

(1) Maximum altitude: 5,000 feet AGL

(2) Maximum endurance: ≈ 120 minutes

(3) Maximum range : ≈ 27 mile

(4) Airspeed:

(a) Cruise: ≈ 32 knots

(b) Maximum : ≈ 55 knots

(5) Maximum rate of climb :

2000 ft/min @ 27.2 degrees. Limited to 15 degrees by autopilot.

(6) Maximum rate of descent :

1376 ft/min. Limited to

- 25 degrees by autopilot

.

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PROPRIETARY (7) Maximum bank angle :

Lim ited to 45 degrees by autopilot.

(8) Turn rate limits :

The Oculus UAS is designed to fly at maximum true airspeed of 32. 2 knots . When taking into account a maximum bank angle of 45 degrees

, the aircraft is limited to a maximum

turn rate of 34 degree s /sec.

(9) Identify any performance limitations due to environmental and meteorological conditions. Specifically, address the following ite ms:

Performance limitations are intended to be investigated during experimental flight testing.

(a) Wind speed limitations :

(i) Crosswind :

T he Oculus UAS has been demonstrated to fly in conditions up to 20

knot winds

. The Oculus UAS requires very short take

- off and landing distance which minimizes risk during crosswind critical flight periods.

(ii) Gusts :

Unknown. Gust limitations are intended to be investigated during flight testing.

(b) Turbulence restrictions :

Unknown. Turbulence restrictions are intended to be investigated during flight testing.

(c ) Minimum visibility conditions:

Visual Flight Rules ( VFR )

Visual Meteorological Conditions ( VMC )

(d) Lighting (for example, daytime flights only):

Daytime only

(e) Outsi de air temperature (OAT) limits:

- 1 0o C to 54 o C ( 14 o F to 1 30 o F) , base d on recommended battery limits

(f) In

- flight icing:

T he proposed operating environment does not include operations in icing

conditions.

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### C. Propulsion System

(1) Describe the propulsion system a nd its ability to provide reliable and sufficient power to takeoff, climb, and maintain flight at expected mission altitudes.

The propulsion system for the Oculus UAS consists of:

1) Motor: Hacker B rushless Electric Motor, kV = 68 0 rpm/V or similar

2) Battery: 4 Cell Li

- Po, 14.8 V, 5000 mAh or similar

3) ESC: Turnigy 30 A Brushless Electronic Speed Control or similar

4) Prop: 12x8 pusher prop or similar , direct drive

The static thrust ( 3.16 lbs ) to weight ( typical flight weight 7 lbs ) ratio is 0.45 :1, which

will result in short take

- off runs. At the best lift

- to

- drag ratio a irspeed, the excess

- thrust (1.896 lbs) to weight (7 lbs) ratio is 0.27 :1, which will give enough power for maneuvering and all emergency procedures

.

(2) Fuel

- powered propulsion systems.

The Oc ulus UAS is electrically powered.

(3) Electric

- powered propulsion systems.

(a) What type of motor is used? Hacker Brushless Electric Motor or similar

(b) What is the power output of the motor? Up to 60 0 Watts

(c) What current draw range does the motor have?

The propulsion system for the Oculus UAS has a current draw range of 3 to 25 Amps. This corresponds to 0

- 100% throttle. During autonomous flight the throttle is limited to 75%, which corresponds to a maximum curr ent draw of

18.75 A.

(d) Does the system have a separate electrical source? If not, how is UA power managed?

The Oculus UAS does not have a separate power source. UA power is managed through the ESC. The ESC contains a battery elimination circuit (BEC) which regulates power to the autopilot.



### D. Fuel System

The Oculus UAS is electrically powered.



### E. Electrical System

(1) Describe t he electrical system and how it distributes adequate power to meet the requirements of the receiving systems. Provide a system level diagram showing electrical power distribution throughout the aircraft. Specifically, address the following items:

The entir e Oculus UAS electrical system is powered by a single battery source. Power is supplied from the battery to the ESC. The ESC distributes power to the motor and the autopilot. The autopilot supplies power to the RC receiver, Global Positioning System ( GPS ) , and servos. A basic wiring diagram is shown in Figure 4

.

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PROPRIETARY Figure 4 : Wiring Diagram

(2) How is power generated onboard the aircraft (for example, generator, alternator, batteries)?

Power onboard the Oculus UAS is generated via 2 Lithium Polymer 4

- Cell batteries

.

(a) If a limited life power source such as batteries is used, what is the useful life of th e power source during normal and emergency conditions? How was this determined?

The useful life of the battery is, typically , 120 minutes , depending on the battery and charge . Typically, flights will not exceed 9 0 minutes so as to av oid failures due to pow er loss. Flight times were determined by previous flight testing

.

(b) How are electrical power status and power remaining information displayed to the pilot?

Remaining battery power is displayed to the user by the g round c ontrol s tation (GCS) during flight. The remaining battery power percentage can be seen in Figure 5 on the middle left of the screen.

Figure 5 : Grou nd Control Station Sample Screen

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PROPRIETARY (3) Describe the source(s) of backup power in the event of loss of the primary power source.

(a) What systems are powered during backup power operation?

The Oculus UAS does not feature a battery backup system.

(b) Is there any automatic or manual load shedding?

The Oculus UAS does not have load shedding capabilities

.

(c) How much operational time does the backup power source provide? Include the assumptions used to make this determination.

The Oculus UAS does not feature a battery backup system.

(4) Describe the electrical distribution architecture including all busses, regulators, switches, and

converters.

The Oculus UAS electrical system is shown below in Figure 6 . The entire UAS is, typically, powered by a single battery ( 14.8 V

, 50 00 mAh or similar ) . 14.8 V is supplied to the ESC. The ESC pr ovides 14.8 V to electric motor. The ESC acts as a voltage regulator and provides 5V to the auto

- pilot. The auto

- pilot supplies 5V to each servo.

Figure 6 : Oculus UAS Electrical Diagram (battery capacity may vary)



### F. Flight Control Surfaces and Actuators

(1) Describe the design and operation of the flight control surfaces and servos/actuators.

Include a diagram showing the location of the control surfaces and servos/actuators.

The Oculus UAS utilizes four control surfaces to control flight. The control surfaces consist of right and left ailerons, elevator, and rudder. Each control surface is controlled

b y an independent servo which receives a control signal from the autopilot. See Figure 7 Figure 8 , and Figure 9 for a diagram of the control surfaces and corresponding servos.

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PROPRIETARY Figure 7 : Oculus Control Surfaces

Figure 8 : Oculus Wing Surface Servos

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PROPRIETARY Figure 9 : Oculus T ail Servos

(2) Describe any potential failure modes and corresponding mitigations.

Failure modes for the Oculus UAS include:

1) Lost communications with the GCS : The Autopi lot is equipped with a failsafe

that allows for a lost communication fli ght plan.

2) Po wer loss: The loss of power may result in a flight failure. All UAS flights must
adhere to a strict flight time limit as determined by the battery capacity. Ear ly
warning for a power loss may be indicated by reduced performance of the motor.

3) E SC failure: Failure of the ESC may result in flight failure. The ESC has been
selected to provide the necessary current requirements without overheating.

4) Servo or control surface failure: Fail ure of the control surfaces may result in
flight failure. Contr ol surfaces and servo linkage must be inspected prior to each
flight. Servo travel must be verified before flight operations.

(3) How does the system respond to a servo failure?

Failure of a servo may result in flight failure.

(4) What indications alert the pilot that a servo is stuck or malfunctioning?

A malfunctioning servo is indicated by erratic flight behavior, such as difficulty establishing level flight.

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### G. Payloads

Several payload modules are in development which may be used to collect or independent ly stream video or telemetry. Payload modules may be externally or internally mounted. Payload modules may include one or more of self

- contained video (e.g. go

- cam), streaming video, and sensors (e.g. temperature). Power consumption, weight and balance, an d impact on aerodynamic efficiency will be considered when payloads are used in flight testing.



## 3. Control and Communications Segment

A. Avionics

The avionics architecture can be seen in Figure 10 . The Oculus UAS fea tures a radio module with

a mounted communications antenna. A GPS antenna is located in the bay of the aircraft near the autopilot. An RC rece iver connects to the autopilot.

Figure 10 : Avionics Architecture



### B. Navigation

(1) How does the UA determine where it is? How does it navigate to its intended destination?

The Oculus UAS is equipped with an autopilot with an integrated GPS. The GPS device is used to determine latitude, longitude, and altitude. The autopilot attempts to navigate the aircraft along a waypoint driven flight plan.

(2) How does the pilot respond to the following directions from air traffic control ( ATC ) , a visual observer, or other crew member?

(a) Change of aircraft heading.

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PROPRIETARY The vehicle will be reprogrammed for the new heading and the new configuration will be uploaded to the vehicle. If the instruction is required to be immediately followed , manual control will be implemented on the aircraft and

the aircraft will be maneuvered to the new heading.

(b) Change of aircraft altitude.

The aircraft will be reprogrammed for the altitude and the new configuration will be uploaded to the aircraft. If the instruction is immediate, manual control will

be taken and the vehicle w ill be maneuvered to the instructed altitude.

(3) What are the causes and effects of loss of heading or altitude?

Loss of Control of the Aircraft

Hazard Action Implementation

Loss of Propulsion Pilot will take manual control and land.

External Pilot

Manual Override Loss of Lift Due to

Structural Failure or

Weather Factors Pilot will take manual control and land.

Loss of Heading, Altitude, and Position

Information Pilot will take manual control and land.

Loss of Radio Control

Link T he autopilot will execute a preprogrammed lost link flight plan. Automatic

Loss of Control

Surface Performance Pilot will take manual control and land. Operator Training,

External Pilot

Manual Override

Loss of UAS Electrical

Power The UAS’s inherent stability will allow

it to ride out a short blackout. Otherwise, the electric motor will shutoff and the flight will be

terminated. Automatic

Loss of

GCS /Telemetry Link No effect to manual control. In autonomous mode, the aircraft will

execute a preprogra mmed lost link flight plan. External Pilot Manual Override,

Automatic

(4) How does the system identify and respond to a loss of the primary means of navigation? Is there a backup means of navigation? How does the system respond to a loss of the secondary means of navigation?

If the primary means of navig ation is lost, the aircraft may be manually piloted . The aircraft will only be operated within visual range of the pilot

.

(5) Describe the procedures to test the altimeter system (see § 91.411).

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PROPRIETARY The Oculus UAS uses a GPS to determine altitude . Altimeter system tests can be performed by raising and lower the aircraft and checking for correct response.



### C. UA Flight Controls

(1) Describe how the control surfaces respond to commands from the flight control computer.

During flight the autopilot send s control signals to each servo that correspond to the desired angular displacement of the servo. The autopilot measures the current roll, pitch

, and yaw values and sends corresponding control signals to bo th stabilize flight and steer

the aircraft.

(2) Describe how the pilot provides input to the control surfaces.

The pilot may control the aircraft through the use of flight plans or manual flight. Flight plans are entered through the GCS and consist of a se ries of waypoints which include GPS coordinates and altitude. Flight plans may be created or modified dynamically during flight. Flight plans may be changed by qualified members of the ground crew, but must be checked by the PIC prior to being uploaded to the autopilot. Manual flight is controlled through the

use of a RC transmitter shown in Figure 11 . Thumb

- sticks are used to control the roll, pitch, yaw and throttle.

Figure 11 : RC Transmitter

(3) Flight control computer.

(a) Does the flight control computer interface with auxiliary controls that might cause an

unintended action?

The flight control computer does not interface with any auxiliary controls.

(b) Describe the flight control computer interfaces required to determine flight status and to issue appropriate commands.

Flight status is determined by the autopilot in conjunction with the GPS sensor. Flight data is transmitted thro ugh a 2

- way transmitter to the GCS

.

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### D. Autopilot

(1) How was the autopilot system developed? What industry or regulatory standards were used in the development process?

The autopilot system was develo ped by DIY Drones using the A rd uMega board.

(2) Is the auto pilot a commercial off

- the

- shelf (COTS) product? If so, name the type/manufacturer and provide the criteria that was used in selecting the system.

Yes. The Oculus UAS is equipped with Ardu Pilot Mega autopilot. The Ardu Pilot Mega

is an open source, low

- cost autopilot, developed by DIY Drones.

(3) Describe the procedures you use to install the autopilot. How is correct installation verified? Reference any documents or procedures provided by the manufacturer and/or developed by your

company.

The autopi lot is installed by sliding the autopilot into fuselage compartment and connecting the wiring harnesses. In order to ensure correct installation the preflight inspection will be conducted

. Refer to the Oculus Aircraft Flight Manual or Flight

Checklists f

or more information.

(4) Does the autopilot employ input limit parameters to keep the aircraft within structural limits? If so, provide a table of these limits. How were these limits validated?

PARAMETER DESCRIPTION LIMIT VALUE REMARKS

THR_MIN MINIMUM THROTTLE 0% GLIDING DESCENT

THR_MAX MAXIMUM THROTTLE 75%

TRIM_THROTTLE CRUISE THROTTLE 35% LEVEL FLIGHT

LIM_ROLL_CD MAX BANK ANGLE 45°

LIM_PITCH_MAX MAX PITCH ANGLE 15°

LIM_PITCH_MIN MIN PITCH ANGLE

- 25°

Limits are validated through field testing.

(5) Where do the autopilot commands reside once they are input by the pilot?

Autopilot commands are transmitted to the autopilot from the GCS where they are stored in the internal memory of the autopilot.

(6) What type of software

- in

- the

- loop (SIL) and hardware

- in

- the

- loop (HIL) simulations have been performed? What was the outcome of the simulations?

Fully autonomous flight of the Oculus UAS has been performed successfully. HIL testing has been performed to verify the correct sensor reading, control surface response, and

GPS link.



### E. C ontrol Link

(1) Provide a detailed control system architecture diagram that includes informational or data

flow s and subsystem performance. Include values for data rates and latencies, if known.

Figure 12 is a diagram of the communication system . The Oculus UAS is subject to two minor latency issues. The first is the GPS signal which updates at rate of 10 Hz. The

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PROPRIETARY second is the MAVLink protocol that manages data transmission between the GCS and the autopilot, which is sent at a rate of 50 packets per second.

Figure 12 : Communications Diagram

(2) Describe the control link(s) connecting the UA and the control station. Specifically address the following items:

(a) What spectrum will be used for the communications and how has the use of this

spec trum been coordinated? If spectrum approval is not required, under what regulation is the use of the frequency authorized?

2.40 2

- 2.4 78 GHz, 902

- 928 MHz

The use of this spectrum has been coordinated with the Federal Communications Commission and a Spec ial Temporary Authorization has been obtained.

(b) What type of signal processing and/or link security (that is, encryption) is employed?

The Oculus UAS uses the MAVlink communications protocol which has been demonstrated effectively in over 255 small ai rcraft.

(c) What is the data link margin in terms of the overall link budget at the maximum anticipated distance from the control station? How was it determined?

The primary test area, Figure 14, has a maximum distance possible of 1.4 miles.

The antenna u sed in the GCS has a specified maximum distance of 1.8 miles (2896 meters), which corresponds to a minimum detectable power of

- 10 0 dBm.

At a distance of 1.4 mile s (2253 meters) the power received by the GCS is

– 98.6 dBm. This provides the Oculus UAS with a data link margin of 1.4 dBm. All data used in the calculation of data link margin and link budget is calculated from using the Friis Transmission Equation.

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PROPRIETARY (d) Is there a radio signal strength and/or health indicator or similar display to the pilot ? How is the signal strength and health value determined and what are the threshold values that represent a critically degraded signal?

Radio signal strength is displayed to the user via the w ireless t elemetry

c onnection in the GCS. This can be seen in Fig ure 6 at the top middle of the

screen. The w ireless t elemetry c onnection is presented to the user as a percentage of bad data packets. During operation the aut opilot receive s “MAVLink heartbeat messages” from the GCS. If no heartbeat message is received wi thin a time limit (specified by a configuration file) , the autopilot will execute a preprogrammed lost link flight plan.

(e) Does the system employ redundant and/or independent communications links? If so, how dissimilar are they?

RC communications and GCS communications are independent.

(f) For satellite links, estimate the latencies associated with using the satellite link for aircraft control and for air traffic control (ATC) communications.

The Oculus UAS uses a MediaTek GPS , or similar, antenna with a 10 Hz update

rate.

(g) What are the potential sources of radio frequency (RF) interference within the proposed operating area and how are they monitored, managed and/or mitigated?

Access to the f

l ight area is controlled by the Navy. Flights are coordinated so as

to avoid interference. When interference is detected or suspected, flight

termination should be considered.

(3) What design characteristics or procedures are in place to prevent or mitigate the loss of the

control datalink due to the following:

(a) RF or other interference?

A pilot will take manual control of the aircraft.

(b) Flight beyond communications range?

A pilot will take manual control of the aircraft.

(c) Antenna masking during turns and pitch angles?

The Oculus UAS airframe is comprised almost entirely of Styrofoam. RC radio signals will not be masked by the airframe.

(d) Loss of control station functionality?

A pilot will take manual control of the aircraft.

(e) Loss of UA functionality?

The loss of UA functionali ty may result in a lost data link depending on the particular failure . In the event of control surface failure or structural failure of the

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PROPRIETARY airframe, the autopilot will continue to receive and transmit data as long as the autopilot is powered and within ra nge of the GCS.

(f) Atmospheric attenuation including precipitation?

A pilot will take manual control of the aircraft.



### F. Lost Link and Flight Recovery

(1) Lost link.

(a) How is it determined that the UA is experiencing lost link and how is this displayed to the pilot?

Dur ing operation the autopilot receive s “MAVLink heartbeat messages” from the

GCS. If no heartbeat message is received within a time limit (specified by a configuration file)

, the GCS considers the UAS to have lost the communication

link. This i s displayed to the user on GCS screen with a red ‘X’ covering the Wireless Telemetry Connection value.

(b) Describe the operational procedures in the event of a lost link.

During the programming of the flight plan, a lost link flight plan is also programmed into the autopilot. In the event that a lost link occurs during autonomous flight, the autopilot will execute what is programmed into its flight plan. If the aircraft executes any maneuver that does not adhere to its flight plan,

manual control will be taken by the pilot until the link is reestablished.

(c) Describe the sequence the UA will follow in the event control link is lost.

The autopilot has two main options for lost link programming. The first will continue with the pre

- programmed mission even though the link is lost. The second will send the aircraft to a recovery location immediately.

(d ) Describe how the aircraft will re act during takeoff, climb, cruise, descent, and landing

in the event of a lost link.

The autopilot has two main options for lost link programming. The first will continue with the pre

- programmed mission even though the link is lost. The

second will send th e aircraft to a recovery location immediately.

(e ) How is it determined that the lost link functionality of the system is operational?

In the event of a return to launch flight plan operation the Oculus UAS will visually alter current flight plan and re turn to the launch site.

(f ) How does the UA navigate when in the lost link mode?

During lost link mode the aircraft will use the onboard GPS to navigate.

(g ) What parameters are used to define the lost link or return home point? How is this point selecte d? How is this point entered? What happens when the UA reaches this point?

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PROPRIETARY The lost link/return home point is pre

- designated as the recovery point. When the aircraft reaches this point, it will be instructed to circle until manual control is

taken and the aircraft is landed.

(h) Under what conditions is a return home mode both manually and automatically

activated?

Return home mode will be automatically activated if it is pre

- programmed to return home during the lost link procedures. Return home mode will be manually

activated if weather falls below minimum VMC or for operation al reasons , such as out of line of sight

.

(i ) What do the control station displays indicate during lost link? Is it clear that the data is

stale or invalid?

In the event of lost link a red ‘X’ will display over the Wireless Telemetry Connection. (See Figure 6) Additionally, lost link may be evident to the crew when the orientation and GPS data will no longer update

.

(2) Flight R ecovery S ystem (FRS).

The Oculus UAS does not include a FRS.



### G. Control Station

(1) Describe or diagram the control station configuration. Include screen captures of the control station displays.

The UAS is controlled by the GCS using the following functionality :

1) Fligh t Planner: Before a UAS flight, an appropriate crew member must first
create flight plans and mission limits using the GCS Flight Planner screen. Prior
to uploading them to the UAS, the PIC will check the flight plan. An example
screen of the Flight Planner can be seen in Figu re 12. This sc reen consists of
three sections. The first section displays an overhead image of the flight zone.
The second section consists of a list of waypoints for a flight plan. The final
section is the action section where the crew members can send a flight plan to the
UAS. Flight plans and flight boundaries can be created and sent to the autopilot
from this screen. The Flight Planner can also be used to create and edit flight
plans mid

- flight.

2) Flight Data: After flight plans and mission limits are set

, the pilot will monitor
and control the UAS from the Flight Data screen. An example screen of Flight
data is shown in Figure 6 . The Flight Data screen consists of three sections. The
first section is the Telemetry Data section in the upper left corner of the screen.
The section directly below the Telemetry Data is the Action Section where the
ground crew would control the UAS by changing the flight plan or flight mode.
The final section consists of an overhead representation of the UAS along the
flight plan.

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PROPRIETARY Figure 13 : GCS Flight Plan Screen

(2) Does the pilot have a standardized screen set up at the initiation of each phase of flight?

Each phase of flight is considered an individual flight plan. Every flight plan entered by a qualified crew member is done through the Actions tab on Flight Data screen. (See Figure 6) The Actions tab set up remains constant at every point during UAS operation.

(3) How accurately can the pilot determine the attitude and position of the UA?

The attitude and posi tion of the UA is determined by 3 sensors on the autopilot. A GPS

device is used determine the latitude

, longitude , and altitude of the UAS to within 3 meters. The attitude of the aircraft is determined by the Inertial Measurement Unit (IMU) which will produce an accurate attitude to within 1 degree.

(4) What commands are safeguarded from inadvertent activation and how is th at ach ieved (for example, a two

- step process to command “kill engine”)?

The Oculus UAS contains two major safeguards to protect the aircraft from inadvertent

activation.

The first failsafe is the throttle failsafe. In order for the pilot to completely stop

th e engine the pilot must first set the UAS in manual operation via a switch on

the RC transmitter. The second step is to pull the throttle to 0%, only then will the engine stop.

The second failsafe is a 2

- step flight plan change safeguard. This consist of 1 ) altering a flight plan waypoint, 2) sending the updated flight plan the UAS.

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PROPRIETARY (5) What kind of inadvertent input could the pilot enter to cause an undesirable outcome (for example, accidentally hitting the “kill engine” command in flight)?

Even with the existing safeguards a crew member still has ability to send the UAS

undesirable commands

. These consist of sending the UAS an incorrect flight plan or setting the UAS into manual mode and performing a piloting error.

(6) Are any other programs running con currently on the ground control computer? If so, what precautionary measures are used to ensure that flight

- critical processing will not be adversely

affected?

No other programs will be running concurrently other than background programs such as

anti

- virus programs.

(7) What are the possible conditions that would cause a ground control station display or interface

lock

- up?

A lock

- up could occur due to a random error in the operating system or the GCS software. The only way to mitigate this is to limit the n umber of programs the computer is running during flight operations.

(8) Are any of the primary flight controls based on the Windows operating system?

The GCS is a Windows operating system that the flight control software is run on.

(9) What alarms or warni ngs does the system provide to the pilot (for example, low fuel or battery, failure of critical systems, departure from operational boundary)?

The GCS features the following visual warnings to the UAS ground crew . A large red ‘X’

over the Wireless Telemetry Connection will be displayed in the event of a lost

communication link. In the event of a lost GPS link the GCS will display “No GPS” in

the GPS field of the GCS.

(10) Describe the means of providing primary and backup power to the ground control station.

The GCS consists of a laptop (with an attached radio transmitter/receiver) and an RC transmitter for manual flight. The primary source of power for the system will be a generator. The laptop itself has a battery that will provide uninterrupted power supply and backup power. The RC transmitter is battery powered, failure of RC control will trigger return to home from autopilot.

(11) What procedures are in place should the control station lose primary and secondary power?

If the control station sh ould lose primary and secondary power, the pilot will take manual

control of the aircraft and land.



## 4. Ground Support Equipment

Describe all the support equipment that is used on the ground. Include any launch or recovery systems, ground data terminals, gener ators, and power supplies.

Launch/Recovery: Hand launch, recovered on foot.

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PROPRIETARY Generators: Generator used to provide primary power source for GCS.

RC Transmitter: Used to manually control the aircraft. Powered by internal battery.



## 5. Processes and Procedures

A. Con figuration Management

(1) What procedures are in place to manage change configuration? Is it documented?

See the Applewhite Aero Configuration Management document.

(2) Describe the procedures used for controlling drawings, test procedures, engineering changes,

etc.

See the Applewhite Aero Document Management document.

(3) Describe the quality assurance system, methods and procedures used, and structure within the organization.

See the Applewhite Aero Quality Control document.



### B. Software Management

(1 ) Describe what software functions were developed by the applicant or the applicant’s suppliers, and what functions are implemented by COTS software.

All functions are implemented by the COTS software.

(2) What software development process(es) have been us ed in the development of software components for the aircraft and the ground control station, and what software lifecycle data is

available for review?

None. The Oculus UAS is equipped with COTS software only.

(3) How will updates to system software (inc luding COTS software) be implemented?

The autopilot software is open source and is updated through the supplier ’ s website. Applewhite Aero will research any changes to the autopilot software, and decide if the new software should be implemented. After so ftware is updated a systems check will be done to ensure proper functionality of the UAS.

(4 ) Describe how the software requirements are validated a nd how the software is verified

.

The software is verified by system checks on the ground that are done when software is updated.

(5 ) For aspects of software development that are allocated to suppliers, describe the process of supplier oversight.

There is no software development allocated to suppliers past their initial release of the

software

.

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PROPRIETARY (6 ) How is softwa re load control implemented for the system to ensure that the correct software components are loaded onto the system?

There is no software load control. System checks are required when new software is loaded to prevent any issues.

(7 ) What software quality assurance processes are used in the development of the system software? How are suppliers a part of the process?

Suppliers are not a part of the process, they release the product only. For quality assurance with our systems, the ground checks are done to make sure each component

works as it should.

(8 ) Is there a system for reporting and tracking problems? How are suppliers integrated into the problem reporting system?

Yes, refer to the Applewhite Aero Flight Reporting document.

(9 ) What procedures are i n place to manage configuration changes? How are they documented?

See the Applewhite Aero Documentation Management document.

(10 ) What programming language(s) are used?

The ArduPilot Mega is programmed using the Ardui no programming language.

(11 ) What r equirements standards, design standards, and coding standards are used in the software development process? What ensures that the standards are followed?

The software is released from the supplier, and then Applewhite Aero adjusts certain parameters to fit the airframe and mission profile.



### C. Electronic Hardware Design and Testing

(1) Describe the standards and processes used to design, test, and modify electronic hardware system elements such as line replaceable units, circui t board assemblies, and COTS components.

The Oculus UAS is comprised of almost entirely of COTS components. Assembly of the autopilot components, wiring harnesses, and final assembly of the Oculus UAS is completed by Applewhite Aero . Every COTS compo nent undergoes a system and

functionalit y test prior to flight of aircraft . The autopilots undergo testing to ensure

accurate communications with the GCS and accurate measurement of the IMU

.

(2) How is safety critical hardware components considered in the design, test, and modification processes described above relative to non

- safety critical hardware components?

The most safety critical components of the Oculus UAS consist of the autopilot, RC receiver, servos, ESC

, and battery. Each of these safety cri tical components is a COTS component. Each component is selected to meet or exceed the flight demands of the

system.

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PROPRIETARY 

## 6. Operations

A. National Airspace System (NAS) Integration and Interaction

(1) Surveillance and Aircraft Visibility.

Since the Oculus UAS is scheduled to be flown in an active restricted airspace, no transponder is deemed necessary.

1) Is the UA equipped with TSO approved Mode

- C or Mode

- S transponder? If yes,
under what TSO and Class of equipment was the transponder approved?

No.

2) Is the UA equipped with a non

- TSO approved Mode

- C or Mode

- S transponder?
If yes, describe the method used to determine that the transponder meets the
performance and environment requirements of any class of TSO

- C74d (Mode C)

or TSO

- C112 (Mode S). Highlight any TSO deviations or non

- TSO functions.

No.

3) What functions and/or settings of the transponder can be changed by the pilot?

N/A.

4) Describe the transponder test procedures (Reference § 91.413).

N/A.

5) Does the UA have a high

- visibility paint scheme that enables other pilots to see
and avoid the UA and enables the observer(s) to visually acquire and track the

UA?

The Oculus UAS is highly visible in its off

- the

- shelf state.

6) What characteristics of the aircraft shape or structure increase its ability to be

seen and tra cked?

The Oculus UAS does not have any physical characteristics that increase its ability to be seen and tracked.

7) Does the UA have anti

- collision lights? Does the UA have position lights? What
are the procedures if the lights are inoperative?

The Oculus UAS is not equipped with lights. The aircraft will only operate in daylight VMC conditions.

8) For optionally piloted aircraft ( OPA ) , does the cockpit have instrument and
cockpit lighting?

The Oculus UAS is not optionally piloted.

(2) ATC and crewmember communications.

(a) How does the pilot communicate with ATC?

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PROPRIETARY The pilot will use cell phone co mmunications to contact the ATC, or the Range Safety Officer will coordinate between ATC and the pilot.

(b) How does the pilot communicate with other users of the airspace?

The Oculus UAS will be flown in active restricted airspace ; no aircraft should be in the airspace. Evasive action will be taking to avoid any other users. If there are multiple groups utilizing the restricted airspace at one time, the flights will be coordinated through the Range Safety Officer.

(c) Describe the communications equipment (that is, radios), including any equipment on

the aircraft.

Manufacturer: Model: Frequency Range:

Transceiver Digi International XBEE09P 902

- 928 MHz

Transmitter Spektrum DX7 2402

- 2478 MHz

Transmitter Spektrum DX18 2402

- 2476 MHz

(d) Is there an intercommunication system that allows for communication between the pilot(s), ground support personnel, crewmembers, and observers?

Due to small team size, verbal communication should be adequate. Intercoms or

s hort

- range radios will be available

, if needed.

(e) What procedures have been established in the event of intercom failure?

In the event of intercom failure, verbal communicatio n will be used

. If this backup method is not adequate, a pilot will land the aircraft.

(3) Sense and avoid.

(a) Describe the method(s) in place for sense and avoid, and if applicable, identify the members of the flight crew that hold this responsibility.

The method is to visually scan the airspace for potential conflicts. It is the responsibility of the pilot in command ( PIC ) and observer (s) to avoid conflicts.

(b) What are the minimum traffic detection capabilities in azimuth and elevation?

N/A

(c) Describe the procedures that will be implemented should an aircraft enter the operating area.

If another aircraft should enter the flight area, a pilot will take manual control of

the Oculus UAS and immediately initiate a traffic avoidance maneuver.

(4) Chase aircraft operations.

Oculus UAS testing will not include chase aircraft operations.



### B. Flight Phases

(1) Pre

- flight/taxi operations.

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PROPRIETARY (a) Describe the entire flight planning process, including how weather briefings and updates are obtained.

1) Flight pla nning will begin with a list of tasks to be completed during the flight

test.

2) These tasks will be used to generate a mission profile.

3) The flight control software will be programmed with the mission profile taking
into account the physical geometry of the t est area.

4) Prior to or on the day of the proposed flight profile, a preflight crew briefing will
take place with all parties involved.

5) Weather will be obtained from NOAA (www.aviationweather.gov) to verify

current and forecast area weather. NOTAMS, PIREPS a nd any other pertinent

information will be researched.

6) The vehicl e will be assembled, inspected , programmed for the flight profile, and
a complete systems check will be performed.

7) The test range safety officer will be informed of an impending flight.

8) The c ognizant ATC will be i nformed of an impending flight for at least the first
flight of the day. That is, unless the range safety officer does not handle this duty.

9) All crew members of the flight team need to agree to proceed with the flight.

10) The aircraft wi ll then be launched according to the flight plan.

11) Since the vehicle has a short duration flight envelop e , several flights can be made

within one area forecast.

12) Updates for weather and NOTAMS will be obtained every four hours via
www.aviationweather.gov.

13) Upon conclusion of the flight test plan for the day, the test range officer and the
cognizant ATC will be informed that no more flights are to be conducted that
day.

(b) Describe your coordination procedures with ATC before takeoff by addressing at a

minim um:

1) Notices to Airmen (NOTAM).

The cognizant ATC will be contacted prior to any flight operations and

relevant NOTAMS will be researched. Including local and FDC.

2) Filing the flight plan.

Flight plan filing is not required for the specified airspace.

3) Transponder codes.

The Oculus UAS is not equipped with a transponder.

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PROPRIETARY (c) Describe UAS preflight activities and the system and support equipment required by addressing at a minimum:

1) The process by which the system is prepared for flight.

The system will undergo a pre

- flight inspection. Information regarding the pre

- flight inspection can be found in Maintenance Section of this

document.

2) The systems required to prepare the system for flight.

The systems required to prepare the Oculus UAS for flight inclu de the portable GCS and the RC transmitter.

3) What critical process points are established, such as system configuration files
needed to establish flight controls calibration?

Configuration files are noted on the flight plan datasheet for both the

aircraft c onfiguration and for the mission profile. (See Flight Reporting document).

(d) Describe how mapping updates are performed on the control station.

The ArduPilot Mega utilizes Google Earth for mapping which installs updates automatically when connected to th e Internet. Prior to flight, automatic updating will be disabled in order to prevent any issues during flight

.

(e) Describe the flightline/operations safety program, if any.

Sterile Cockpit will be observed. For further information see the Flightline Safety Program document.

(f) How do you ensure the area is clear for taxi?

Taxi will not be required. The aircraft is hand

- launched.

(g) Describe the procedures to ensure the engine isn’t started in a manner that coul d cause injury to ground personnel.

A ircraft will be hand launched by a crew member who has been trained by Applewhite Aero on how to safely launch the aircraft. The aircraft is light and easy to handle which minimizes risk of a crew member not being able to control the aircraft during laun ch.

(2) Take off/launch. Provide a description of system equipment required for this operation. Identify unique system performance and procedures.

The Oculus UAS will be hand

- launched.

(3) Flight.

( a) Identify the components of the system, including supp ort equipment that is required

for the UA to conduct safe flight operations. Information presented in response to this

item shall address at a minimum:

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PROPRIETARY 1) The process by which the system is operated during flight.

A ground station is required for initial programming of the vehicle. Once programmed, the vehicle can operate independently of any ground station in a completely autonomous mode. Ground stations are provided to monitor the progress or change the mission profile during flight.

2) The systems required to operate the system during flight.

The systems required to operate the Oculus UAS during flight include

the portable GCS and the RC transmitter.

3) Critical process points that are established.

Monitor progress of the UAS during flight.

( b) Describe the method for switching between pilot

- controlled (manual) and autonomous flight modes. At what points during the flight will this happen?

A switch on the RC transmitter switches between manual and autopilot mode.

Manual control will be taken in the event ; ano ther aircraft enters the flight area, and an evasive maneuver cannot quickly be programmed into the autopilot, the lost link or any other flight mode behaves in a way counter to the programmed flight plan.

( c) What indication does the pilot have that they are in control of the aircraft?

The observed behavior is in alignment with the mission profile and the pilot can demonstrate manual control and a return to automated flight.

( d) For OPA, describe how the remote control equipment will be engaged and disenga ged during ground and flight operations.

The Oculus UAS is not optionally piloted.

( e) How are changes made to the flight plan during flight?

The new flight plan is programmed into the ground control station and then sent to the UAS, the autopilot will a djust its flight path/plan accordingly.

( f) Describe the procedures in the event of lost communication with ATC (if applicable).

Notification with ATC is either via phone call or relayed via the RSO. Constant communication is not required.

(4) Landing/recovery. Provide a description of system equipment required for this operation. Identify unique system performance and procedures.

The Oculus UAS will belly land and will be recovered on foot. There is no additional equipment needed for landing/ recovery.

(5) Post

- flight.

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PROPRIETARY (a) This subsection intends to identify the parts of the system, including support equipment required for the UAS to conduct safe operations. Information presented in response to this item shall address at a minimum:

1) The proce ss by which the system is operated post

- flight.

a. Verify landing site is safe for recovery

b. Recovery

c. Perform po st

- flight inspection/maintenance

d. Post

- flight debrief

e. Document flight “lessons learned” if applicable

f. Prepare system for next flight , if applicable

g. A fter the final flight, the system may be dismantled and packed into its

case

2) The systems required to operate the system post

- flight.

None.

3) Critical process points that are established.

a. Verify that landing site is safe for recovery.

b. Post

- flight inspection

(b) Describe the process for a post

- flight inspection.

The post

- flight inspection is follows the same procedures as the pre

- flight inspection described above.

(c) Describe the process for incident/accident reporting.

Any incident, accident, or any flight o peration that transgresses the lateral or vertical boundaries of the flight test area or any restricted airspace must be reported to the UAS Integration Office (AFS

- 80) within 24 hours. AFS

- 80 can be reached by telephone at 202

- 385

- 4636 or by fax at 202

- 38 5

- 4559. Accidents that result in death or serious injury to any person, or accidents that cause substantial damage to a UA with a maximum gross takeoff weight of 300 pounds or more must be reported to the National Transportation Safety Board (NTSB) per

ins tructions on their website: www.ntsb.gov. Further flight operations must not be conducted until the incident is reviewed by AFS

- 80 and authorization to resume operations is provided to Applewhite Aero

.



### C. Operating Areas

(1) How do you ensure that there is no unusual ground activity under the flight operations area? For example, are there any weekend events scheduled? Are there housing areas or public gathering places?

An initial visual scan of the bay will be conducted prior to flight for potential conflict s. Ongoing scans will be conducted during flight and potential conflicts will be avoided.

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PROPRIETARY (2) Identify any military or civilian routes through the proposed operational area.

( a) Pendleton, OR : The testing sites are located north

- northeast of H olden, OR, just outside of Pendleton, as can be seen in figure 13. There are a few minor roadways passing near the boundaries of the Primary and Secondary Pendleton sites as can be seen from figures 14 and 15 below. The roadway’s include Hartle Rd, Highway 37, Co 891 Rd, Co 888 Rd, and N. Juniper

Rd.

(b) Whidbey Island, WA: V287 passes through R

- 6701. The activation of R

- 6701 s hould preclude the use of V287

at or below 50 0 0 ft. MSL.

(3) Identify the proposed operating area on an aeronautical chart. The proposed area needs to define lateral boundaries and requested altitudes.

(a ) Pendleton Airport

– Class G , Active Restricted Pendleton, OR

Testing will occur in the airspace indicated in Figure 13 , below. Most testing will be conducted within the primary test area as defined in Fi gure 14 . A secondary t est area is defined in Figure 15

. The testing will stay at least 400 feet away from all roadways as an extra precaution, despite the fact that no traffic is expected.

Figure 14 : Pendleton Location Sectional

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PROPRIETARY Figure 15 : Pendleton Primary Test Area



### Northeast Test Area:

Point P1: N45.930 ° W118.902 °

Point P2: N45.932° W118.896 °

Point P3: N4 5.932 ° W118.887 °

Point P4 : N4 5.935 ° W118.887 °

Point P5 : N4 5.936 ° W118.870 °

Point P6 : N4 5.914 ° W118.870 °

Point P7 : N4 5.914 ° W118.881 °

Point P8 : N4 5.921 ° W118.881 °

Point P 9 : N4 5.921 ° W118.902 °

Leg 1

– P1 to P2: 0.33 miles Leg 2

– P2 to P3: 0. 46 miles Leg 3

– P3 to P4 : 0. 22 miles Leg 4

– P4 to P5 : 0. 78 miles Leg 5

– P 5 to P6 : 1.51 miles Leg 6

– P6 to P7 : 0.52 miles Leg 7

– P 7 to P8 : 0. 49 miles Leg 8

– P 8 to P9 : 1.00 miles Leg 9

– P 9 to P1 : 0.62 miles

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PROPRIETARY Figure 16 : Pendleton Secondary Test Area



### Southwest Test Area:

Point P1: N45.921 ° W118.964 °

Point P2: N45.921° W118.944 °

Point P3: N4 5.914 ° W118.944 °

Point P4 : N4 5.914 ° W118.953 °

Point P5 : N4 5.885 ° W118.954 °

Point P6 : N4 5.885 ° W118.975 °

Point P7 : N4 5.914 ° W118.975 °

Point P8 : N4 5.914 ° W118.964 °

Leg 1

– P1 to P2: 1.00 miles Leg 2

– P2 to P3: 0.49 miles Leg 3

– P3 to P4 : 0.47 miles Leg 4

– P4 to P5 : 1.98 miles Leg 5

– P 5 to P6 : 0.99 miles Leg 6

– P6 to P7 : 2.00 miles Leg 7

– P 7 to P8 : 0.50 miles Leg 8

– P 8 to P1 : 0.49 miles

(b) R

- 6701 (Admiralty Bay)

– Class E

, A ctive R estricted Whidbey Island, Washington

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PROPRIETARY Testing will occur under the R

- 6701 airspace indicated in Figure 1 6 , below. Most testing will be conducted within the primary test area as defined in Figure 1 7 . A secondary test area is defined in Figure 1 8

.

Figure 17 : R

- 6701



### R

- 6701:

Northwest Corner: N48°10’ W122°41’

East to: N48°10’ W122°34.9’

Southeast to: N48°05.7’ W122°31.6’

West to: N48°06.1’ W122°41.3’

North to: N48°10’ W122°41’

Leg 1

- Northwest Corner to Northeast Corner: 4.72 miles Leg 2

– Northeast Corner to Southeast Corner: 5.52 miles Leg 3

– Southeast Corner to Southwest Corner: 7.49 miles Leg 4

– Southwest Corner to Northwest Corner: 4.50 miles

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PROPRIETARY Figure 18 : Whidbey Island Primary Test Area



### Primary Test Area:

Launch Area: N48°07.1’ W122°35.9’

Point P1: N48°07.1’ W122°35.2’

Point P2: N48°06.5’ W122°34.9’

Point P3: N48°06.5’ W122°35.9’

Leg 1

– Launch to P1 : 0.50 miles Leg 2

– P1 to P2: 0.76 miles Leg 3

– P2 to P3: 0.76 miles Leg 4

– P3 to Launch: 0.73 miles

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PROPRIETARY Figure 19 : Whidbey Island Secondary Test Area



### Secondary Test Area:

Point S1: N48°09.1’ W122°41.1’

Point S2: N48°09.9’ W122°38.9’

Point S3: N48°09.2’ W122°36.7’

Launch Area: N48°07.1’ W122°35.9’

Point P3 N48°06.5’ W122°35.9’

Point S4: N48°05.9’ W122°36.3’

Point R4: N48°06.1’ W122°41.3’

Leg 1

– S1 to S2 : 2.00 miles Leg 2

– S2 to S3: 1.87 miles Leg 3

– S3 to Launch: 2.53 miles Leg 4

– Launch to P3: 0.73 miles Leg 5

– P3 to S4: 0.68 miles Leg 6

– S4 to R4: 3.89 miles Leg 7

– R4 to S1: 3.45 miles



### D. Flight Envelope and Test Plans

(1) Describe the conditions under which flight envelopes will be tested. How close will operations be to any populated areas and major highways?

Conditions: VFR and VMC

.

Primary Test Area

(a) Pendleton, OR: 17 miles north

- northwest of Pendleton, OR and just north

northeast of Holden, OR

.

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PROPRIETARY (b) Whidbey Island: 150 feet from a local highway, SR

- 525

, at closest point

.

Secondary Test Area

(a) Pendleton, OR: As defined above.

(b) Whidbey Island: Over the water, Admiralty Bay

.

(2) Describe how you plan to meet test objectives under the proposed flight envelope and operating area. Include test plans, if possible.

Purpose: To perform research and development evaluations of the Oculus UAS

.

Activity: Operation of the Oculus UAS

.

Specifically, overall flight performance and autopilot will be evaluated by taking the

Oculus UAS through increasingly complex flight paths i n maneuvers. The evaluation

may also entail endurance testing, adjusting the cen ter of gravity to measure stability, and effects of speed variations on the airframe. Secondary purposes are to perform crew training in the operation of the Oculus UAS and market research.

Max Operating Altitude: 500 0 feet MSL

Oculus UAS flight testing will be conducted under VFR in VMC conditions, and will maintain LOS communication and operation. A pilot will be on

- site to take control of the

UAS should the autopilot lose its link with the ground station or if the UAS does not perform as expec ted.

The maxim

um operating altitude will be 500 0 feet MS L. The flight endurance of the

Oculus UAS is between 30

– 45 minutes, typical . Flights will vary in duration but will typically not exceed 30 minutes. The quantity and frequency of experimental flig hts will be dependent on the re sults of the preceding flights, weather/ sea conditions, and operational readiness.



### E. Operating History

Describe the operational history of the UAS

. Include details of the following items:

The airframe is a Dynam HawkSky which is a well

- established RC hobby plane. It is commonly used throughout the wo rld as a low

- cost UAS with an open

- source autopilot.

1) Total number of flights and flight hours on the UA.

A total of 5 hours and 16 minutes of flight time have been put into the

Inve nio in the King George Airpark, Canada. Tests were done analyzing both the RC configuration of the plane as well as the auto

- pilot features: including auto

take

- offs, auto waypoint flight, auto loiter, and auto landing.

2) Any system failures, inciden ts, accidents, or emergencies, and the resultant
system modifications or corrective actions.

No major system failures or emergencies arose during the flight testing. Minor errors in the system were corrected during the 26 flights that were made with this aircraft, allowing all bugs in mechanical and electronic system to be fixed. The goals outline d by the Invenio Initial Flight Test Plan were met.

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PROPRIETARY 

### F. Manuals

Is there an operating manual for the aircraft?

Yes , refer to Oculus Aircraft Flight Manual

.

Does the manual have a section with all of the aircraft limitations in one location?

Yes.

Does the op erating manual have bolded or underlined procedures for emergencies for memory item steps?

Yes.

Is there an operation checklist for all phases of the operation?

Yes

.

Are here separate checklist items for normal, abnormal, or emergency procedures?

Yes

.



## 7. Orga nizational Considerations

A. Pilot/Crew Qualifications/Training

Reference: 14 CFR part 61

– Certification: pilots, flight instructors, and ground instructors; part

63

– Certification: flight crewmembers other than pilots; part 65

– Certification: airmen other than flight crewmembers.

(1) Crew. Is there a crew resource management training program? If so, describe the program.

Crew resource management IAW AC 120

- 51E

.

(2) Pilot s

.

(a) Do the pilots have a current pilot certificate? If so, what type of pilot certi ficate?

Paul Applewhite:
ATP, CFI, CFII, MEI with over 1 1 ,000 hours flying experience

Dave Beardsley:

Private Pilot Certificate

(b) Do the pilots have a current medical certificate? If so, what class of medical

certificate?

Paul: First Class

Dave: Second Class

(c) Describe in detail and reference any procedures that show that the pilots are properly

trained.

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PROPRIETARY All pilots and observers will complete training as required by the FAA. Pilots and observers will also complete Applewhite Aero internal trai ning in the operation

of the Oculus UAS.

(d) Is there an established formal training curriculum for all pilots including PIC, supplemental, or chase pilots(s)?

Yes. (Chase pilots are not required)

(e) Is the pilot type rated for the aircraft being flown?

Yes.

(3) Observer.

(a) Do the observers have a current pilot certificate? If so, what type of pilot certificate?

No.

(b) Do the observers have a current medical certificate? If so, what class of medical

certificate?

Yes, all observers have a curren t second class medical certificate.

(c) Does the observer understand the applicable aviation regulations such as see and avoid, clear of clouds, and right of way rules?

Yes.

(d) Is the observer a current pilot or have a training curriculum? Is there an est ablished formal training curriculum for all observers? If so, please provide it during the site visit.

Yes.

(e) Describe, in detail, how the observer is properly trained to be an effective member of the flight team.

Observers receive same the training as a pilot and the same process is used to qualify/certify a pilot.

(f ) Does the observer understand:

1) Proper communications and phraseology?

Yes.

2) Proper visual scan techniques?

Yes.

3) Standard flight operations at non

- towered airports?

Yes.

4) Containment areas an d how to determine whether the UA is operating within that

area?

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PROPRIETARY Yes.



### B. Maintenance

(1) Provide an inspection and maintenance program.

Refer to Oculus Inspection and Maintenance Program document.

(2) Provide information on unique system maintenance activities, such as maintenance of a pneumatic launcher system.

The Oculus UAS does not have any unique systems requiring maintenance.