ATTACHMENT 2 
ASN 2014-ESA-198-COA

Case Status VALIDATED

Date Created 11/07/2014

Date Submitted 12/08/2014

Proponent 

Organization Sponsor Florida State University Center for Disaster Risk Policy

Attn Of David Merrick

Address 113 Collegiate Loop

Address2 637 Bellamy

City Tallahassee

State FL

Postal Code 32306-2250

Telephone (850) 644-9961

Email dmerrick@cdrp.net

Declaration Declaration(a) Yes

Declaration(b) Yes

Point of 

Contact Representative David Merrick

Address 113 Collegiate Loop

Address2 Bellamy 638

City Tallahassee

State FL

Postal Code 32306-2250

Telephone (850) 644-9961

Email dmerrick@cdrp.net

Operational 

Description

Requested 

Effective Period Beginning

End

Light out operation No

VFR operation Yes

IFR operation No

Day operation Yes

Night operation No

Program Executive 

Summary

The Center for Disaster Risk Policy at Florida State University will conduct 

research on the use of small unmanned aerial systems (sUAS) in the field of 

emergency and disaster management. Use cases include aerial photography 

and creation of digital elevation models and video and still photography. The 

objective is to model the integration of sUAS remote sensing capabilities with 

local, state, and federal disaster management operations.

Operational Summary

The Lynx UAS will operate under 400ft AGL, in Class "G" airspace north of 

Tallahassee, Florida. Flights are daytime only, within visual observation 

distance. Research flights will be conducted approximately 4 days each 

calendar month. Each flight day will include approximately 2 flights of 60 

minutes each. 

Location State FL

County Leon

Nearest Airport RUTTEN DUSTING STRIP

AOR Florida - Northern

Class Of Airspace Class-A

Class-B

Class-C

Class-D

Class-E

Class-G Yes

System 

Description Aircraft Type

Aircraft Type And Model 

Description Attachment 1

Control Station Attachment 1

Communications System 

Attachment 1

List Certified Components 

(TSO) Attachment 1

Other Attachment 0

Performance 

Characteristi

cs Climb Rate (feet/Minute) N914FS

Descent Rate (feet/Minute) 800

Turn Rate 

(Degrees/Second) 800

Cruise Speed Maximum 35.0

Minimum 42

Approach Speed 0

Operating 

Attributes Maximum MSL 23

Minimum MSL 8000

Gross Takeoff Wt 0

Launch/Recovery 

Attachment 12.2

Airworthines

s FAA Type Certificate 1

If No FAA Certificate 

(Public Aircraft Only) 

Attachment

Page 1 of 4
Procedures

Lost Link/Mission 

Procedures Attachment 1

Lost Communications 

Procedures Attachment 1

Emergency Procedures 

Attachment 1

Avionics/Equ

ipment Equipment Suffix Type 1

GPS X

Moving map indicator 

(Command Station) Yes

Tracking capability Yes

TCA/MCAS Yes

ELT No

Transponder Transponder No

On No

Off

Standby

Ident

Mode S

Mode C

Transponder Retuneable in 

Flight

Lights Landing

Position/Navigation No

Anti-collision No

Infrared (IR) No

Spectrum 

Analysis 

Approval Data Link No

Data Link Attachment Yes

Control Link(s) 0

Control Link Attachment Yes

Operations utilizing Radio 

Control (R/C) frequencies 

as described in Title 47 

CFR 95 0

NTIA/FCC Authorization 

Attachment Yes

ATC 

Communicati

ons

Transmitter VHF 

Band VHF Band 0

Quantity No

In-Flight Retunable

Transmitter UHF 

Band UHF Band No

Quantity No

In-Flight Retunable

Transmitter HF 

band HF Band No

Quantity No

In-Flight Retunable

Receiver VHF 

Band VHF Band No

Quantity No

In-Flight Retunable

Receiver UHF 

Band UHF Band No

Quantity No

In-Flight Retunable

Receiver HF 

band HF Band No

Quantity No

In-Flight Retunable

Guard 

(Emergency) 

Frequencies VHF 

Band VHF Band No

Quantity No

Guard 

(Emergency) 

Frequencies UHF 

Band UHF Band

Quantity No

Instantaneous 

Two-Way Voice Direct to pilot

SATCOM No

Relay via aircraft No

Page 2 of 4
Electronic 

Surveillance/

Detection 

Capability EO/IR No

Terrain detection Yes

Weather/icing detection No

Radar No

Other Attachment No

Electronic detection 

systems 0

Electronic detection 

systems attachment No

Radar observation 0

NAS Operational Capability 

Attachment No

Visual 

Surveillance/

Detection 

Capability

Maximum 

Distance from UA Vertical 0

Horizontal 400 Feet

Airborne based (Chase 

Aircraft) 0.54 Nautical Miles

Ground based No

Visual observation from 

one or more ground sites Yes

Forward or side looking 

cameras Yes

Attachment for All Yes

Aircraft 

Performance 

Recording Flight data recording 0

Control station recording Yes

Voice Recording Yes

Flight 

Aircrew 

Qualification

s Pilots Private (Written) No

Private (Certified) Yes

Instrument No

Commercial No

Air Transport No

Unique Trained Pilot No

Unique Trained Pilot 

Description No

DOD certified/trained

UAV pilots will have an understanding of and comply with Federal Aviation 

Regulations applicable to the airspace where the UAV will operate. Pilots must 

have in their possession a current second class (or higher) airman medical 

certificate that has been issued under 14CFR 67, Medical Standards and 

Certification. 14CFR 91.17, alcohol or drugs, applies to UAV pilots. UAV Pilots 

will have completed a recognized private pilot ground school course and 

passed FAA Private Pilots basic knowledge test.

Other Certified Training No

Trained on Part 91 

Requirement Yes

Medical Certification Class 

(FAA or DOD equivalent) Yes

Currency Status 2

Duty Time Restrictions Pilots and observers will possess a Class 2 or higher FAA medical certificate.

Single UAS Control Daylight operations only. 

UAS Description Yes

Total Numbers of UAS 

Controlled

Observers Private (Written) 1

Private (Certified) Yes

Instrument No

Commercial No

Air Transport No

Unique Trained Pilot No

Unique Trained Pilot 

Description No

DOD certified/trained

Observers will meet and comply with the same stated requirements for UAV 

pilots.

Other Certified Training No

Trained on Part 91 

Requirement Yes

DOD Certified Training 

Attachment Yes

Medical Certification Class 

(FAA or DOD equivalent) 0

Currency Status 2

Duty Time Restrictions Pilots and observers will possess a Class 2 or higher FAA medical certificate.

Single UAS Control Daylight operations only.

UAS Description Yes

Total Numbers of UAS 

Controlled

Page 3 of 4
Special 

Circumstanc

es Special Circumstances 1

Page 4 of 4
CDRP sUAS in Emergency Management Research Project

Florida State University

637 Bellamy, Tallahassee, Florida 32306­2250

850.644.9961

Data Sheet for Swift Radioplanes Lynx Small

Unmanned Aerial System (sUAS)

The Swift Radioplanes Lynx is a fixed­wing remotely operated unmanned aircraft

designed to carry still cameras for mapping applications.

Physical Information

Dimensions

Width (Wingspan): 99 in.

Height: 16 in.

Length: 47 in.

Weight & Payload

sUAS Weight: 10.2 lbs

Effective Payload: 2 lbs.

Maximum Gross Take­Off Weight: 12.2 lbs

Typical Gross Take­Off Weight: 11.4 lbs.

Construction

Closed­cell foam

Kevlar wrap skin

Carbon fiber

ABS plastic

Landing Gear

None ­ Belly landing

Electric Motor

Motors: One 1100kv Brushless Motor

Configuration: Direct Drive (One Motor per Propellor)

Voltage: 22.2V nominal

Weight: 158g
CDRP sUAS in Emergency Management Research Project

Florida State University

637 Bellamy, Tallahassee, Florida 32306­2250

850.644.9961

Operating Requirements

Operating Temperature: 14° to 105°F (­10° to 41°C)

Relative Humidity: 0% to 92% Noncondensing

Maximum Wind Speed: 25 knots (28 mph)

Flight Characteristics

Climb Rate: 4 m/s (800 ft/min)

Descent Rate: 4 m/s (800 ft/min)

Turn Rate: 35°/second

Cruise Speed: 16 m/s (36 mph)

Maximum Speed (VNE): 22 m/s (49 mph)

Minimum Speed: 9 m/s (20 mph)

Approach Speed: 12 m/s (27 mph)

Launch Type: Hand launched

Maximum Altitude MSL: 8,000ft (2438m)

Standard Battery: 10000 mAh 6S Lithium Polymer (LiPo) 22.2 volt

Maximum Flight Time: 90 minutes

Autopilot and Onboard Sensors

Autopilot: 3DRobotics Ardupilot version 2.6

MPU­6000 3D Accelerometer and Gyroscope3

MS5611­01BA03 Barometric Pressure Sensor

u­Blox External Global Positioning System Receiver

4MB on board solid state memory

Autopilot Flight Modes

“Stabilized” ­ Manual flight mode with autopilot stabilization assistance.

“Guided” ­ Aircraft will fly to and orbit designated coordinates at designated altitude.

“Return to Launch” ­ Aircraft will return to launch point using GPS navigation assistance.

“Autonomous” ­ Aircraft will fly pre­programmed mission waypoints using GPS

navigation.
CDRP sUAS in Emergency Management Research Project

Florida State University

637 Bellamy, Tallahassee, Florida 32306­2250

850.644.9961

Flight Logging (Black Box)

Flight Data Recording: On­Board

Storage: Internal 4MB autopilot memory

Data Recorded: Pitch, Yaw, Climb/Descent Rate, Altitude, Heading, Airspeed, GPS

Location, Flight Mode, Data Link Status

Flight Data Recording: Ground Control Station

Storage: 340GB Hard Drive

Data Recorded: Pitch, Yaw, Climb/Descent Rate, Altitude, Heading, Airspeed, GPS

Location, Flight Mode, Data Link Status

RF Communications

Flight Controller

Purpose: Ground to air transmission of flight control commands

Frequency: 2.4GHz Digital Spectrum Modulation (DSM)

sUAS Antenna: Two (2) Whip Antennas

Controller Antenna: Dual Omni­Directional Antennas

Transmission Power (North America): 100mW

Telemetry

Purpose: Two way transmission of flight telemetry data and mission planning

commands

Frequency: 915MHz

sUAS Antenna: Omni­Directional

Ground Control Station (GCS) Antenna: Omni­Directional

Transmission Power (sUAS Transmitter): 100mW

Transmission Power (GCS Transmitter): 100mW

Transmission Technique: Frequency Hopping Spread Spectrum (FHSS)

Data Rate: 57,600 baud

Protocol: Full Duplex MAVLink

Video Transmission

Purpose: Air to ground transmission of video signal

Frequency: 5.8GHz
CDRP sUAS in Emergency Management Research Project

Florida State University

637 Bellamy, Tallahassee, Florida 32306­2250

850.644.9961

7 Selectable Channels: 5740MHz, 5760MHz, 5780MHz, 5800MHz, 5820MHz,

5840MHz, 5860MHz

sUAS Antenna: Omni­Directional Helix

Standard Camera Payloads

24 mega­pixel (MP) Canon EOS­M Digital Still Camera in nadir photo configuration

480p Standard Definition Video Camera with Remote Controlled Tilt (optional)
CDRP sUAS in Emergency Management Research Project

Florida State University

637 Bellamy, Tallahassee, Florida 32306­2250

850.644.9961

Ground Control Station

The Lynx UAS Ground Control Station (GCS) is a Hewlett Packard laptop computer running

Microsoft Windows 8.1 and Mission Planner (version 1.3.5), a FatShark “Attitude”

First­Person­View (FPV) video headset, and the 3DR telemetry radio module and

omni­directional antenna. The laptop and

omni­directional antenna are mounted on a

tripod stand for ease of use in the field.

The video goggles contain the video

downlink receiver and are connected to the

GCS laptop via USB cable. This set up

allows the video from the UAV to be

displayed on the GCS laptop screen.

The Mission Planner software utilizes the

Micro Air Vehicle Communication Protocol

(MAVLink) to communicate with the 3DR

Y6 via the telemetry module radio link.

The Mission Planner software allows for

pre­mission planning of flights, displays

real­time flight information from the 3DR

Y6, and allows in­flight changes of mission

parameters.

While in flight, Mission Planner displays

current flight mode, altimeter, heading,

airspeed, ground speed, GPS coordinates,

time of flight, battery status, rate of climb,

and a moving map displaying the realtime

UAV position, heading, and programmed

mission. Mission Planner can be used in

flight to update the mission in the UAV, as

well as simple ‘go to’ navigation on the

moving map.

CDRP owns two (2) complete Ground

Control Stations.
CDRP sUAS in Emergency Management Research Project

Florida State University

637 Bellamy, Tallahassee, Florida 32306­2250

850.644.9961

Communications

Communications systems for the Swift Radioplanes Lynx UAS.

Flight Controller

Purpose: Ground to air transmission of flight control commands

Frequency: 2.4GHz Digital Spectrum Modulation (DSM)

sUAS Antenna: Two (2) Whip Antennas

Controller Antenna: Dual Omni­Directional Antennas

Transmission Power (North America): 100mW

Flight Controller Channel Assignments

Channel 1 ­ Throttle Channel 5 ­ Flight Mode

Channel 2 ­ Roll Channel 6 ­ Deep Stall

Channel 3 ­ Pitch Channel 7 ­ [unused]

Channel 4 ­ [unused] Channel 8 ­ [unused]
CDRP sUAS in Emergency Management Research Project

Florida State University

637 Bellamy, Tallahassee, Florida 32306­2250

850.644.9961

Telemetry

Purpose: Two way transmission of flight telemetry data and mission planning

commands

Frequency: 915MHz

sUAS Antenna: Omni­Directional

Ground Control Station (GCS) Antenna: Omni­Directional

Transmission Power (sUAS Transmitter): 100mW

Transmission Power (GCS Transmitter): 100mW

Transmission Technique: Frequency Hopping Spread Spectrum (FHSS)

Data Rate: 57,600 baud

Protocol: Full Duplex MAVLink
CDRP sUAS in Emergency Management Research Project

Florida State University

637 Bellamy, Tallahassee, Florida 32306­2250

850.644.9961

Video Transmission

Purpose: Air to ground transmission of video signal

Frequency: 5.8GHz

7 Selectable Channels: 5740MHz, 5760MHz, 5780MHz, 5800MHz, 5820MHz,

5840MHz, 5860MHz

sUAS Antenna: Omni­Directional Helix
CDRP sUAS in Emergency Management Research Project

Florida State University

637 Bellamy, Tallahassee, Florida 32306-2250

850.644.9961

TSO

There are no TSO components in this UAV
CDRP sUAS in Emergency Management Research Project

Florida State University

637 Bellamy, Tallahassee, Florida 32306­2250

850.644.9961

Lost Link Procedures

Launch and Recovery Areas

Prior to the mission, the PIC and Observer will designate safe landing areas for the Lynx

UAS. All personnel involved in the mission (including the PIC and Observer) will see and

understand the location of these landing areas and the circumstances in which they may be

used.

Loss of Signal Procedures

There are three distinct (and separate) radio links between the Lynx UAS and the

PIC/Observer. Loss of Signal (LoS) on any of these radio links will trigger different

procedures.

Flight Controller Radio Loss of Signal

In the event the Lynx UAS loses link with the Primary Flight Control radio system, the

autopilot will initiate an automatic ‘failsafe’ mode and return the UAS to the launch location.

Telemetry Radio Loss of Signal

The Lynx UAS maintains a telemetry radio link between the UAS and the Ground Control

Station (GCS) laptop. In the event of a LoS on the telemetry radio, the PIC will immediately:

1. Declare verbally “Telemetry Loss of Signal”.

2. Attempt to reestablish telemetry link.

3. If the telemetry link cannot be re­established, the UAS will be manually flown to the

launch point and land.

If the link is reestablished, the mission may continue.

Video Downlink Loss of Signal

The Lynx UAS maintains a one­way radio link from the onboard video camera system to the

Ground Control Station (GCS). This link is informational only, and a LoS event on this radio

linkage does not necessarily threaten the mission or the safety of the UAS, ground crew, or

other personnel in the area.

In the event of a video downlink LoS, the PIC will:
CDRP sUAS in Emergency Management Research Project

Florida State University

637 Bellamy, Tallahassee, Florida 32306­2250

850.644.9961

1. Declare verbally “Video Loss of Signal”

2. Monitor Telemetry and Flight Controller radio links ­ LoS on the video downlink often

precedes LoS on other (more critical) radio linkages.

3. If required, order the UAS to return to the launch area or initial a landing at a

predefined landing area.
CDRP sUAS in Emergency Management Research Project

Florida State University

637 Bellamy, Tallahassee, Florida 32306­2250

850.644.9961

Lost Communications

Primary communications between the PIC and Observer is verbal (if co­located) or GMRS

(General Mobile Radio Service) handheld two­way radio.

Secondary communications between PIC and Observer is cellular telephone.

Primary communications between PIC and ATC when required is telephone. All operations of

the UAV will be in Class G airspace, below 400 feet AGL.

In the event of lost communications between the PIC and Observer, two options are available

to the PIC:

Lost Communications Option 1

The PIC will put the UAS into “GUIDED” mode and hold position and altitude. PIC will attempt

to re­establish communications. If successful, the mission can continue. If unsuccessful, the

PIC will immediately abort the mission and return the UAS to the launch location.

Lost Communications Option 2

The PIC will put the UAS into “GUIDED” mode and hold position and altitude. PIC will attempt

to re­establish communications. If successful, the mission can continue. If unsuccessful, the

PIC will immediately abort the mission and land the UAS at the current position.
CDRP sUAS in Emergency Management Research Project

Florida State University

637 Bellamy, Tallahassee, Florida 32306­2250

850.644.9961

Emergency Procedures

There are several different hazards that may create unsafe or dangerous conditions for the

operation of the UAS. These may occur in or around the UAS itself, or near the Ground

Control Station and associated personnel.

Each of these hazards will result in the PIC and/or Observer to initiate one or more

emergency procedures to ensure the safety of the UAS crew, bystanders, property and the

UAS system.

Hazards and Responses

Weather (wind, temperature, or precipitation)

In case of weather conditions that develop during the flight that are outside of safe operation

parameters, the PIC will execute either: ABORT TO LAUNCH or ABORT TO GROUND

After the UAS is on the ground, crew will recover the aircraft, disassemble the GCS, and

move to a safe/dry location.

Low Voltage / Low Battery

In the event a low voltage condition develops (defined as the primary flight battery reporting

19.2volts or less) the PIC will execute either: ABORT TO LAUNCH or ABORT TO GROUND

The decision as to which emergency procedure to execute will be determined by the PIC and

depend on current battery levels, range from the UAS to the GCS, wind, and other factors.

Loss of Motor/Prop

In the event the UAS suffers a motor failure or power loss, the PIC will execute ABORT TO

GROUND.

The Lynx UAS has significant glide capability, enabling the PIC to choose a landing site that

poses reduced risk to the aircraft or people/material on the ground.

Loss of Flight Control Link

If the UAS loses the radio linkage to the Flight Controller, the autopilot will automatically

command a FAILSAFE: ABORT TO LAUNCH.
CDRP sUAS in Emergency Management Research Project

Florida State University

637 Bellamy, Tallahassee, Florida 32306­2250

850.644.9961

Even if a Flight Controller radio link is reestablished, the mission will not continue.

Loss of GPS Signal

If the UAS loses the GPS position lock, the autopilot will automatically attempt to hold

position. The PIC will execute ABORT TO LAUNCH or ABORT TO GROUND. In this

condition, RETURN TO LAUNCH (RTL) mode is not available, only manual flight is possible.

Loss of Telemetry Link

In the event the UAS oses the telemetry radio link, there is not an immediate emergency

condition ­ the UAS can and will continue any automated missions without telemetry to the

ground. However, loss of telemetry is often a precursor to loss of Flight Control Link.

Ground Control Station Security

In the event of an unsafe situation at or near the GCS, the PIC may execute: LOITER AND

HOLD, ABORT TO LAUNCH, or ABORT TO GROUND.

UAS out of Line of Sight

If the PIC and Observer lose visual contact with the UAV, the following procedures will be

initiated.

1. PIC will initiate LOITER AND HOLD.

2. The Observer will LOG LAST LOCATION

3. If the PIC and/or Observer can regain visual contact, the mission may proceed.

Otherwise, the PIC will execute ABORT TO LAUNCH or ABORT TO GROUND

Crash

In the event of a crash:

1. The Observer will LOG LAST LOCATION

2. The crew will move to the crash site with a blanket or towel and a fire extinguisher and

RENDER UAS SAFE
CDRP sUAS in Emergency Management Research Project

Florida State University

637 Bellamy, Tallahassee, Florida 32306­2250

850.644.9961

Defined Emergency Procedures

LOITER AND HOLD

The PIC will place the UAV into GUIDED flight mode, and hold current position and altitude.

ABORT TO GROUND

PIC will assume manual control by placing the UAS in MANUAL mode and descend to an

immediate landing. Alternatively, the PIC may engage DEEP STALL mode, which will initiate

immediate descent and landing.

ABORT TO LAUNCH

PIC will return the UAS to the launch point (the GCS location) and land immediately. This

may be accomplished via RETURN TO LAUNCH (RTL) mode or manually using MANUAL

mode.

LOG LAST LOCATION

The Observer will immediately log the last/current position coordinates of the UAS from the

GCS, as well as altitude, heading, and airspeed.

RENDER UAS SAFE

The PIC, Observer, or other personnel should use caution with approaching a crashed UAS ­

it may present an immediate or delayed fire hazard. The UAS propeller will be covered by a

towel or blanket until the motor power safety key can be attached and the battery can be

disconnected and removed.

FAILSAFE: ABORT TO LAUNCH

If the UAS loses radio link to the Flight Controller on the ground, the autopilot will engage

RETURN TO LAUNCH (RTL) mode. The UAS will then proceed back to the launch point (the

GCS location) and loiter.

FAILSAFE: ABORT TO GROUND

In a low voltage (low battery) situation, the autopilot will automatically land the UAS at the

current location.