1 U N I TED STA T ES O F A ME R I CA

DEPARTMENT O F T R ANSPORTA T I ON

F ED E R A L A V I AT I O N AD M I N I STRA T I ON

W AS H I N G T ON, DC

Re g ulato r y Do c k e t No.

_ ______________

IN THE MATTER OF THE P ETI T ION F OR EXEM P TION O F :

EAGLE EYE INTELLIGENCE

, LLC

F OR AN EXE M P TION SE E K ING RELIEF FRO M THE RE Q UIR E M ENTS OF

TI T LE 14 OF THE C O DE OF F EDER A L R E G ULATIONS

S E CTIONS 61.113(a) & ( b), 91.7(a )

, 91.121, 9 1.151(b), 91.405(a )

, 91. 4 07(a)(1 )

, 91.40 9 (a)(1) & (a ) ( 2 ), A N D 91.41 7 ( a ) & (b) CON C ERN I NG COM M ER C IAL

O P ERATION OF U N MANNED AIR C RA F T SYS T EM (UAS), SPECIFICALLY THE

EAGLE EYE MERLIN, LOCKHEED MARTIN INDAGO LE , 3DR DIY QU AD,

LATITUDE HQ40 , P HOENIX 30 and LATITUDE MC 120 MICR OCOPTER DRONE

P U RSUANT TO S E C T ION 333 OF

THE F AA M ODER N I Z ATION AND R E F O RM A C T O F 2012 ( P U BL IC LAW 112

- 95)

Subm i t t ed on December 29

, 2015

Dean Attridge

Director of Fight Operations

Eagle Eye Intelligence

, LLC

1001 Broken Sound Parkway NW

S uite C

Boca Raton

, Florida 334872 TAB L E OF CONTEN T S

Pa g e

G LO S S ARY OF A BB REV I AT I O N S 3

SUMMAR Y 4

I N TRODUC T I O N AND I N TERESTS OF PE T I T IONER 4

B ACK G RO U N D 5

B A S I S F OR PE T I T I ON 11

N A ME A N D A D D RESS OF PE T I T I ONE R 13

THE SPECIFIC SECTIONS OF 14 C.F.R. FORM WHICH E AGLE EYE 1 4

INTELLIGENCE LLC SEEKS EXEMPTION

THE EXTENT OF RELIEF EAGLE EYE INTELLIGENCE

, LLC SEEKS AND THE 1 7

REASON EAGLE EYE

, INTELLIGENCE

, LLC SEEKS RELIEF

THE REASONS WHY GRANTING EEI, LLC REQUEST WOULD 1 9

BE I N THE PUBLIC INTEREST

THE REASONS WHY GRANTING THE EXEMPTION WOULD NOT 21

ADVERS ELY AFFECT SAFETY

SUMMARY THAT CAN BE PUBLISHED IN THE FEDERAL REGISTER 49

ANY ADDITIONAL INFORMATION, VIEWS OR ARGUMENTS AVAILABLE

TO SUPPORT REQUEST 49

CONCLUSION 493 G LOS S ARY OF ABB R EVIATIONS

AGL

A O I

ATC

ATO

AV

C.F.R.

COA

F AA

F AR

GCS

GPS

HUD

L O L

N A S

N O TAM

P I C

Se c tion

SP

333 SOP

UA

U A S

V F R

V LO S

VMC

VO

VTOL Above Ground Level

A re a o f I nterest

Air Tr a ffic Control

Air Tr a ffic O rgani z ation

A e ri a l V e h i cle

Code of F e d e r al Re g u l atio n s

Certifi ca te of Authori z ation

F eder a l A viation Adminis t r a tion

Fe deral Aviation R e g ula t ion

G r ound Control S tation

Global Posi t ion i ng S y s t e m

Heads Up Display

L oss of L ink

Nat i onal Airsp ac e S y stem

Notice to Airman

Pi l ot in Command

F AA Moderni z ation and Re f orm A c t of 2012 ( F M RA) Se c tion

Supplemental Pilot

333 Standard O p e rating Pr oc edur e s

Unmann e d Aircraft

Unmann e d Ai r craft S y stem

Visual F li g ht Rules

Visual L ine o f S i te

Visual Meteo r ol o g ic a l C ondi t ions

Visual Obs e rver

V e rtic a l T ak e o f f a nd La n ding4 SUM M A R Y

Eagle Eye Intelligence

, LLC se e ks exemption from the re quirements of 14 C

. F .R §§

61.113( a ) & ( b )

, 91.7( a ), 91.121, 91.151 ( b ), 91.405 (a ), 91.40 7 ( a ) (1), 91.409( a ) ( 1 ) & ( a )(2), a nd

91.417(a) & ( b), to ope ra te Unmann e d Air c raft S y stem s purs u ant to Se c tion 333 of the F A A

Modernization and Refo r m A c t of 2012 ( F MR A). This e x empt i on w i ll p e rmit Eagle Eye

Intelligence

, LLC to oper a te Unmann e d Aircraft S y st e m s ( U AS) under strict protocols for the

purpose of conducti n g training, security, concept development and Personal Safety Device

( PSD ) support flights in t h e United S tates in compliance with conditions and limitations the

FAA has included in standard exemptions under section 33 3

. We accordingly seek summary

processing of this petition and thus the FAA need not publish a summary of this petition in the

Federal Register or se ek public comment.

INTRODU C TION A N D INTERE ST S OF THE P ETITION E R

Eagle Eye Intelligence

, LLC (h e r e i n after re f erred to as “ EEI ”) is a technology company

that provides security and law enforcement agencies with advanced technology to

, “Protect

Property and Save Lives”. We intend to pursue fe d er a l, state, l o cal, and commer c ial c lients.

EEI is fo c used on p r ovid i ng solutions for util i zing unmann e d a i r c r aft to saf e l y a nd ef f i cien tl y

provide situational awareness and safety enhancements to its customers utilizing Unmanned

Aircraft where appropriate.

As s e t forth in this P etition, EEI se e ks to c o mmer c ial l y o p er a t e i t s listed aircraft (Exhibit

1 ) over c ertain areas o f the United S t ates for t h e purpose o f c ondu c ti n g training, security,

concept development and Personal Safety Device ( PSD ) support flights

.5 BACK G ROU N D

Unmann e d Aircraft S

y st e m: EEI Merlin UAS

EEI s ee ks an ex emption to oper a te the EEI Merlin UAS (see F igure 1) for

compens a tion or hire within the N a tio n al Airspace S y stem ( NA S ). The Merlin U AS i s

built by EEI from commercially available parts and is comprised of a Fixed Wing

Un m ann e d A ircr a ft (UA) and a Ground Control S ta t ion (GCS). The Merlin UA h as a

ma x imum gro s s w e i g h t of 30 pounds, a wingspan of 102 inch e s , Nose to Tail is 77

inches, and ma x i m um speed of 100 mph. The Merlin UA is equipp e d wi t h a single

pro p eller, dri v en b y a L ithium P o l y m er b atte r y pow e r e d ele c tr i c motor.

The Merlin UA that wi l l be oper a ted b y EEI will be re g ister e d in a cc or d ance with 49

U.S. C . 44103, R egistrat i on of Aircraf

t , as w e ll as 14 C

. F .R Part 4 7

, Aircraft R e gistrat i o n

, and ma r k e d in ac c o r d an c e with 14 C

. F .R. Part 4 5

, Id e ntif i cation and R e gistrat

i on

Markin g

. If processing is after 31 March 2016, EEI will comply with Part 48 electronic

registration requirements.

F igure 1 : T h e Merlin UA.6

Unmann e d Aircraft S

y st e m: Lockheed Martin Indago LE

EEI s ee ks an ex emption to oper a te the Lockheed Martin Indago LE UAS

(see Fi gure 2) for compens a tion or hire within the NA S

. The Lockheed Martin LE U AS

i s a Quadcopter Un m ann e d A ircr a ft and a Ground Control S ta t ion (GCS). The

Lockheed Martin LE UA h as a ma x imum gro s s w e i g h t of approxi m ate l y 4.85 pounds

and a ma x i m um speed of 30 mph. The Lockheed Martin Indago LE UA is dri v en b y a

L ithium P o l y m er b atte r y pow e r ing 4 ele c tr i c moto rs.

The Lockheed Martin Indago LE that wi l l be oper a ted b y EEI will be re g ister e d in

a cc or d ance with 49 U.S. C . 44103, R egistrat i on of Aircraf

t , as w e ll as 14 C

. F .R Part 4 7

, Aircraft R e gistrat

i o n , and ma r k e d in ac c o r d an c e with 14 C

. F .R. Part 4 5

, Id e ntif i cation

and R e gistrat

i on Markin g

. If processing is after 31 March 2016, EEI will comply with

Part 48 electronic registration requirements.

Figure 2: The Lockheed Martin Indago LE7

Unmann e d Aircraft S

y st e m: 3DR DIY Quadcopter

EEI s ee ks an ex emption to oper a te th e 3DR DIY Quad UAS (see F igure 3) for

compens a tion or hire within the NA S

. The 3DR DIY Quad i s a Quadcopter U A and a

GCS. The 3DR DIY Quad UA h as a ma x imum gro s s w e i g h t of approximate ly 5 .5

p ounds and a ma x i m um speed of 30 mph. The 3DR DIY Quad UA is dri v en b y a

L ithium P o l y m er b atte r y pow e r ing 4 ele c tr i c moto rs.

The 3DR DIY Quad that wi l l be oper a ted b y EEI will be re g ister e d in a cc or d ance with

49 U.S. C . 44103, R egistrat i on of Aircraf

t , as w e ll as 14 C

. F .R Part 4 7

, Aircraft

R e gistrat i o n , and ma r k e d in ac c o r d an c e with 14 C

. F .R. Part 4 5

, Id e ntif i cation and

R e gistrat i on Markin g

. If processing is after 31 March 2016, EEI will comply with Part 48

electronic registration requirements.

Figure 3: The 3DR DIY Quad8

Unmann e d Aircraft S

y st e m: Phoenix 30 Quadrotor

EEI s ee ks an ex emption to oper a te the Phoenix 30 Quadrotor UAS (see F igure 4) for

compens a tion or hire within the NA S

. The Phoenix 30 Quadrotor i s a multi

- rotor

Un m ann e d A ircr a ft and a GCS. The Phoenix 30 Quadrotor UA h as a ma x imum gro s s

w e i g h t of 12 p ounds and a ma x i m um speed of 30 mph. The Phoenix 30 Quadrotor UA

is dri v en b y a L ithium P o l y m er b atte r y pow e r ing 4 ele c tr i c moto rs.

The Phoenix 30 Quadrotor that wi l l be oper a ted b y EEI will be re g ister e d in

a cc or d ance with 49 U.S. C . 44103, R egistrat i on of Aircraf

t , as w e ll as 14 C

. F .R Part 4 7

, Aircraft R e gistrat

i o n , and ma r k e d in ac c o r d an c e with 14 C

. F .R. Part 4 5

, Id e ntif i cation

and R e gistrat

i on Markin g

. If processing is after 31 March 2016, EEI will comply with

Part 48 electronic registration requirements.



### Figure 4: Phoenix 30 Quadrotor9

Unmann e d Aircraft S

y st e m: Latitude HQ

- 40 Hybrid Quadrotor

EEI s ee ks an ex emption to oper a te the Latitude HQ

- 40 Hybrid Quadrotor UA S (see

figure 5) for compens a tion or hire within the N a tio n al Airspace S y stem ( NA S ). The

Latitude HQ

- 40 Hybrid Quadrotor i s a multi

- rotor / fixed wing Un m ann e d A ircr a ft (UA)

and a Ground Control S ta t ion (GCS). The Latitude HQ

- 40 Hybrid Quadrotor UA h as a

ma x imum gro s s w e i g h t of 42 p ounds and a ma x i m um speed of 80 knots. The Latitude

HQ

- 40 Hybrid Quadrotor UA is dri v en b y a L ithium P o l y m er b atte r y pow e r ing 4 ele c tr i c

moto rs and a 4

- cycle reciprocating engine for forward flight.

The Latitude HQ

- 40 Hybrid Quadrotor that wi l l be oper a ted b y EEI will be re g ister e d

in a cc or d ance with 49 U.S. C . 44103, R egistrat i on of Aircraf

t , as w e ll as 14 C

. F .R Part

4 7

, Aircraft R e gistrat

i o n , and ma r k e d in ac c o r d an c e with 14 C

. F .R. Part 4 5

, Id e ntif i cation and R e gistrat

i on Markin g

. If processing is after 31 March 2016, EEI will

comply with Part 48 electronic registration requirements.



### Figure 5: Latitude HQ

- 40 Hybrid Quadrotor10

Unmann e d Aircraft S

y st e m: Latitude MC 120 Microcopter

EEI s ee ks an ex emption to oper a te the Latitude MC 120 Microcopter UAS (see

F igure 6) for compens a tion or hire within the N a tio n al Airspace S y stem ( NA S ). The

Latitude Microcopter i s a multi

- rotor Un m ann e d A ircr a ft (UA) and a Ground Control

S ta t ion (GCS). The Latitude Microcopter UA h as a ma x imum gro s s w e i g h t of .26

p ounds and a ma x i m um speed of 30 mph. The Latitude Microcopter UA is dri v en b y a

L ithium P o l y m er b atte r y pow e r ing 4 ele c tr i c moto rs. The Latitude Microcopter is still

under development and first flights are due in early 2016.

The Latitude Microcopter that wi l l be oper a ted b y EEI will be re g ister e d in

a cc or d ance with 49 U.S. C . 44103, R egistrat i on of Aircraf

t , as w e ll as 14 C

. F .R Part 4 7

, Aircraft R e gistrat

i o n , and ma r k e d in ac c o r d an c e with 14 C

. F .R. Part 4 5

, Id e ntif i cation

and R e gistrat

i on Markin g

. If processing is after 31 March 2016, EEI will comply with

Part 48 electronic registration requirements.



### Figure 6: Latitude MC 120 Microcopter (Prototype)11 BASIS F OR P ETI T ION

Petit i oner, EEI , LLC I n c

., b y a nd t h ro u g h und e rs i gned c ounsel, purs u ant to the

p r ovisions of the F ede r al Aviation Re g u l ations (14 C. F .R. § 11.61) and the F AA Mod e rni z ation

and Re f o r m A c t of 2012, Se c tion 33 3

, Spe c ial Rules for C ertain Unmann e d Aircraft Sy s tem s

, her e b y petitions t he Admini s tr at or to ope ra te EEI listed aircraft in the NAS, a nd for a n

e x emption f r om the re qui r ements of 14 C.F.R §§ 61.113(a) & (b), 91.7(a), 91.121, 91

. 151(b),

91.405(a), 91.407( a ) ( 1 ), 91.409(a) ( 1 ) & ( a) ( 2 ), a nd 91.417 ( a) & ( b).

I n consid e r a tion of t h e si z e, w e i g ht, sp e ed, a nd l i m i ted oper a ting area a ss o ciat e d with

the unmann e d a ircraft and its oper a tion, EEI ’ s o p er a tion of UAS ’s me e ts the conditions of

Se c tion 333 and the r efor e , will not r equire a n airwo r thiness c ertifi ca te in a cc o r d anc e with 14

C. F .R

. P art 21, Subpart H , with regard to Part 23 and 27 as appropriate

. A cc o r di n g l y

, EEI

requests r e lief from Se c tions 91.405(a), 91

. 407(a) ( 1 ), 91.409( a )(1) & ( a)(2 )

, and 91.417(a) &

( b )

, as these s e c tions set fo r th r e qui r ements for maintenan c e that on l y app l y to ai r c r aft with an

airwo r thiness certific a t e. EEI submits that t he re qu e sted relief is pro p er since a n e quiva l ent

l e vel of saf e t y will be e nsur e d. EEI

, will use at minimum FAA certified p ilots to operate the

aircraft. In addition, EEI will use FAA qualified technici a ns to per f o r m supervision of

mainte n an c e, alter a tio n s, or p r ev e ntive m ainten a n c e on EEI listed UAS ’s u sing the methods,

te c hniques, a nd pr a c ti c es pr e scrib e d in EEI’s General Operations Manual Section 7

“M a int e nance” ( see attachment F) and following FAA maintenance procedures and principles

whenever appropriate. Fu r th e rmor e

, EEI will document and maintain all maintenan c e r e c o r ds

f or each UAS it operates. Maintenance of the listed UAV’s will be accomplished by the

owner/operator pursuant to the T raining/ M aintenance manuals , such as provided in the

attachments. EEI will follow the Manufa ctures User guide s as a reference document in

conjunction with the Maintenance protocol established in the EEI General Operations Manual

section 7 “Maintena nce”. Relief f rom c ert a in r e q uirements of Se c tion 61.1 1 3(a) a nd (b),

entit l ed Pri v

ate pilot privileg e s and limi t ation s : P ilot i n com m an d

, is r e quested b y EEI to the

e x tent ne ce ssa r y to allow a Pi l ot in Co m ma n d ( P I C ) holdi n g a p rivate pilot c e rtifi ca te a nd a

s econd

- c lass a ir m an medic a l certific a te, and who h a s complet e d the UAS training and

c u r r en c y r e quir e ments, to cond u ct the pro p osed U A S op e r a t ion s

. EEI submi t s t h a t the

conditions and lim i tations set fo r th he re in will ensure the s a fe t y o f the N A S, as w e ll as t h e

saf e t y of persons or prop e r t y on the g roun d

.

EEI s ee ks r elief fr o m S e c tion 91.7( a ) , entitl e d Civil A i rcraft A irworth i

n e s s , be ca u s e

EEI’ s listed UAS’s d o not r e quire an a irw o rthiness c e rtificate in a cco r dan c e with 14 C.F.R.Part

21, Subpart H , with regard to Part 23 and 27 as appropriate

. As s uch, EEI submits that i t will

ensure that the EEI listed UAS’s are i n an a irwo r t h y c onditio n , prior to e v e r y fli g ht, b y

determining that the UAS i s in comp l iance with the UAS specific O per a tor s M a n u al in cluding

the PIC’s pre

- flight safety review

, (see A ttachment B) performance of all scheduled

maintenance, and the restriction of all flights to VLOS and Visual Flight Rules (VFR)

conditions.12

EEI a lso se e ks an e x emption from the re qui r e ments of Se c tion 91.121, entit l ed

Alt i m e ter S e tting s , as all EEI listed UAS’s are equipped with a b a r o me t er a n d Glob a l

Posi t ion i ng S y stem ( G PS) equipmen t , which e nsur e s t h at a g r o und lev e l pr e ssu r e setting will

be e stablished prior to eac h f l i g ht. T h e U A S’s bar o meter a nd GPS equipm e nt ensu r e safe t y b y

providing the P I C with a dequ a te in f o r m ation con c erning a lti t ude of the U A S , above g round

le v el ( A G L ), as shown on the he a ds

- up displ a y of the GC S

.

Additional l y

, EEI seeks an e x emption from the re qui r ements of S e c ti o n 91.151(b),

Fu e l require m ents for fl i ght i n VFR c ondition s

. EEI request this exemption because it relies

mainly upon battery power rather than fuel. Depending upon the model used, the batteries

necessary to power the UAS allow for the durations listed as follows:

a. EEI submi t s that saf e t y w ill not be a ffected b y te r minati n g f l i g hts of the batte r y

power e d Merlin UA a fter approximately 9 0 minu t es of continuous fli g ht with at least

2 0 per c e n t of batt e r y power re m aining

.

b. EEI submits that safety will not be affected by terminating flights of the battery

powered Lockheed Martin Indago LE after approximately 45 minutes continuou s

flight with at least 20 percent of battery power remaining.

c. EEI submits that safety will not be affected by terminating flights of the battery

powered 3DR DIY Quad after approximately 20 minutes of continuous flight with at

least 20 percent of battery pow er remaining.

d. EEI submits that safety will not be affected by terminating flights of the gasoline

powered Latitude Engineering HQ

- 40 Hybrid UAS after approximately 4 hours and

30 minutes of continuous flight with at least 3 0 minutes of endurance remaining.

e. EEI submits that safety will not be affected by terminating flights of the battery

powered Latitude Engineering MC 120 after approximately 1 0 minutes of continuous

flight with at least 20 percent of battery power remaining.13

I n a cc o rd a n ce with 14 C. F .R. § 11.81, EEI provides the following inf o rmation in

support of its petition for e xe mption:

A. N a m e a nd Ad d r e ss o f t h e P e t i tioner.

The n a me a nd add r ess of the Peti t ioner is:

Eagle Eye Intellige n ce

, LLC

1001 Broken Sound Parkway NW

, Ste C

Boca Raton , Florida 33487

The point of conta c t f o r t his P etit i on and sp ec ific c onta c t information is as follows:

Dean Attridge

Director of Flight Operations

Eagle Eye Intelligence , LLC

Boca Raton , Florida 33487

dattridge@eagleeyeintelligence.com

702.755.9825

EEI submits several attachments with this request :

Attachment A

- EEI Training Manual

Attachment B

- PIC Pre

- flight Safety Review

Attachment C

- Lockheed Martin Procerus Technologies Indago User Guide and Kestrel

Autopilot System User Guid e

Attachment D

- EEI Merlin User Guide

Attachment E

- EEI 3DR DIY User Guide

Attachment F

- EEI General Operations Manual Section 7

Attachment G

- UAV Solutions Phoenix 30 User Guide

Attachment H

- Latitude MC 120 Microcopter User Guide

Attachment I

- Latitude HQ 40 User Guide

Because the manuals are proprietary information, EEI requests confidential treatment per 14

CFR. §11.35(b) and protection from release under the Freedom of Information Act.14

B. T h e Spe c i f ic Sections o f 14 C. F .R. F r o m Which EEI S e e ks Exe m ption.

1. EEI S e e ks Exe m pt i on F r o m The R eq u irements Of S e c tion

61.113 ( a) a nd (b).

Se c tion 61.11 3 , entitled Pri v ate pilot privileg e s and limi t at i ons: Pilot in co m man d

, subse c tions (a) and ( b ) pres c ribe t h e followin g , in part:

( a ) N o p erson w ho holds a priv a te pilot c e rtif i c a te m a y ac t as a pilot

in co m mand ( P I C) o f an a i r craft that is c a r r y i n g p a s s e n ge rs o r

prop e r t y f or compens a ti o n or hir e ; nor m a y that p e rson, for

compen s ation or hir e

, ac t as P I C of an a ircr a f t.

(b) A p r ivate pi l ot ma y

, f or c ompens a tion or hi r e, a c t as P I C of

a n air c raft i n conn ec tion with a n y bus i ness or e mpl o y m ent i f

— (1) The f l i g ht is on l y inc i dental to that business or e mpl o y ment; and

(2) The a i r c r a ft do e s not c a r r y p assen g ers or proper t y for c om p ensation or

hire.

2. EEI S e e ks Exe m pt i on Fr o m The R equir e m e nts Of Se c tion 91.7(a).

Se c tion 91.7, entitled C ivil a i rcraft air w

o r thines s

, subse c tion ( a ), st a tes t h e followin g :

( a ) N o p erson m a y opera t e a c ivil air c r a ft unless it is i n an a irwo r t h y c ondition.

3. EEI S e e ks Exe m pt i on Fr o m The R equir e m e nts Of Se c tion 91.121.

Se c tion 91.121, entitled A l t i m e ter s e tting s , subsection ( a ), st a tes the follo w in g , in

rele v ant part:

( a ) E ach p e rson op e r ating a n air c r a ft sh a ll mainta i n the cruising a lti t ude or fli g ht

lev e l of that air c raft, a s the case m a y b e, b y ref e r en c e to a n alti m eter that is set,

w h e n oper a ti n g

- -

(1) Below 18,000 f eet M S L , t o

-- (i) The c u r re nt r eport e d a lti m eter setting of a stati o n along the

route a nd wi t hin 100 nauti c al miles of the a i r c r aft;

(ii) I f th e re is no stati o n within the ar e a p r e scr i bed i n pa r a g r aph

(a) ( 1 ) ( i ) o f t his se c tion, the c u r r ent r e por t ed a lti m eter s etti n g of a n

appropriate a vail a ble station; or

(iii) I n the c a s e of a n aircraft not equipp e d with a r adio, the

e lev a tion of the dep a rtu r e airpo r t or a n appro p ri a t e alti m eter

setti n g a v ailab l e b e fore d e p artu re

.15

4. EEI S e e ks Exe m pt i on Fr o m The R equir e m e nts Of S e c tion 91.15 1 (b).

Se c tion 91.151, entitled Fuel require me nts for f l i ght i n VFR c ondition s , s u bse c tion (b),

states the f ollowin g :

(b) No person m a y be g in a f li g ht in a n airplane u n der V F R conditions unless

( c onsideri n g wind and f o re c a s t w e a th e r c onditions) there is en o u g h f u el to f l y to

t h e first point of intend e d landing a nd, a s s um i ng norm a l c ruising s pe e d, to f l y a f t er

th a t for at le a st 3 0 minutes.

5. EEI S e e ks Exe m pt i on F r o m T h e R equir e m e nt O f S e c tion 91.405(a).

Se c tion 91

. 405, entitled Main t enan c e req u ired

, s ubsection (a ) , sta t es the fol l ow i n g :

E ac h owner or o p er a tor o f an a i r craf t

—

( a ) Sh a ll have t h at aircr a ft i nspe c ted a s pr e s crib e d in su b part E of this pa r t a nd

shall betw ee n requir e d insp e c t ions, e x c e pt as provided in p a ra g raph (c) of this

s e ction, have discr e p a n cies re p air e d as pr e scrib e d in p art 43 of t his chapter [ .]

6. EEI S e e ks Exe m pt i on F r o m T h e Req u ir e m e nts Of S e c tion 91.407(a)(1 )

.

Se c tion 91

. 407, entitled Operation af t er maint e nanc e

, prev

e ntive mainten a nc e

, rebuilding, or al t

eratio n

, subse c tion ( a ) (1), states the followin g :

( a ) N o p erson m a y oper a t e a n y a i r craft that has u n der g one

mainte n an ce

, p r ev e ntive mainten a n ce

, r e buildin g

, or a lter a tion

unles s

- - (1) I t has been a p p roved for re turn to s ervi c e b y a person

a uthori z ed und e r § 43.7 of this ch a pte r

.

7. EEI S e e ks Exe m pt i on F r o m T h e Req u ir e m e nts Of S e c tions

91.409(a)(1) And 91.409(a)(2).

Se c tion 91.409, entitled Inspe c tions , subsection (a), states the followi n g :

( a ) E x c e pt as p r ovided in para g raph (c) of this sec t ion, no person m a y

op e r a te an aircraft unless, within the pr ece d i ng 12 calendar months, i t has

had

-- (1) An a nn u al inspe c tion in a c co r d an c e with part 4 3 of this

chapter and h as be e n appro ve d for r e tu r n to se r vice b y a

p e rson a uthori z ed b y § 43.7 o f this chap t er; or

(2) An insp ec tion f o r the is s uan c e of a n airw o rthiness c e rtificate in

a c co r da nce with pa r t 21 of this ch a pte r (with regard to Part 23 and

27 as appropriate)

.16

8. EEI S e e ks Exe m pt i on Fr o m The R equir e m e nts Of Se c tio n s

91.417(a) And 91.41 7 (b).

Se c tion 91.41 7 , entitled Main t enan c e records , s u bse c tions ( a ) and ( b ), sta t e the

followin g :

( a ) E x c e pt for w o rk perf o rmed in a cc o rd a nc e with §§ 91.411 and 91.413,

e a ch re g istered own e r or o p er a tor s h all ke e p the f ollowi n g re c ords for the

p e riods s p e c ified in para g r aph (b) of this se c tion:

(1) Re c o r ds o f the maint e nan ce , p r eventive maint e nan ce

, and

a lteration and re c o r ds o f the 100

- hour, a nnu a l, p r o g ressive, a nd

other r equir e d or a ppro ve d ins p e c tions, as approp r ia t e, for e ach

air c raft ( including the air f r ame) and e ach e n g i n e, pro pe ll e r, rotor, and

a ppliance of a n a i r craft. The re c or d s must i nclude

--

(i) A d e s c ription (or r eferen c e to da t a a cc e ptable t o the

Adminis t r a tor) of t he wo r k per f o r med; and

(ii) The d a te o f c ompletion of the w o r k p e r f or me d; a nd

(iii) The si g n atur e

, a nd c ertific a te number of the person a ppro v i n g

the a i r c raft for return to servic e

.

(2) Re c o r ds containing t h e following inf o rmation:

(i) The total ti m e in se r

v i ce of the air f r ame, ea c h en g ine, e ac h p rop e ller,

a n d e ac h rot o r.

(ii) The c urrent status of l i fe

- lim i ted p a rts of e ach air f r a m e, e n g ine,

p rop e l l er, r otor, a nd appli a nc e

.

(iii) The time since last o verh a ul of all items insta l led on the a ircr a ft

w h ich are r equir e d to be ov e rh a uled on a sp e cified time basis.

(iv) The c u r re nt insp e ction status of the a ir c raft, i n cluding the time

since t h e la s t inspe c tion requir e d b y t h e inspe c tion pr o g r a m un d er

w hich the air c raft a nd i t s applian ce s are maintain e d.

(v) The c u rr e nt status of applic a ble a i r wo r thiness dire c tives (AD)

a nd s af e t y directive s includin g

, f or e a ch, the method of

c omplianc e , t h e AD or s a fe t y directive number a nd r e vision date.

I f t h e AD o r s a f e t y di r e c tive involv e s r e curring a c tion, the t i me and

d a te wh e n the n e x t action is r e quir e d.17 (vi) Copies of the f o r ms pre s crib e d b y § 43.9 ( d) o f this chapter f o r

each m a jor alt e r a tion to the a irfr a m e a nd c u rrent l y installed

e n g ines, r o t ors, prop e llers, and a pplian ce s.

(b) The ow n er or o p er a t o r shall r e tain the f ollowi n g re c ords for the periods

pr e s c rib e d:

(1) The reco r ds s p ecified in para g raph (a) ( 1) of th i s section shall

be re tai n e d until t he wo r k is r e p e ated or s u p erseded b y other w o rk

or for 1 y ear aft e r the wo r k i s pe r fo r med.

(2) The reco r ds s p ecified in para g raph (a) ( 2) of th i s section

shall be re tai n e d and tr a nsf e rred with the a i rcraft a t the time

the a i r craft is sold.

(3) A list of d e f e c ts furn i shed to a re g iste r ed owner or op e r ator

under § 43

. 11 of this ch a pter s h all be re tai ne d unt i l the d e f ec ts

are r e pa i red a nd the air c raft is ap p rov e d for r e turn to se r vic e

.

C. T h e Ext e nt Of Relief EEI S e e ks And T he Reason EEI Se e ks Th e R e lie f

.

1. Ext e nt of R e lief EEI S e e ks And T he R e ason EEI S e e ks R e lief

F r o m Se c tion 61.113( a ) And (b).

Relief f rom Se c tion 61. 1 13( a ) a nd (b ) , entitled P r ivate pilot pr

i vileg e s and limitat

i ons:

Pilot in comman d

, is r e qu e sted to the e x ten t ne ce s sa r y to allow a P I C holding a p rivate pilot

c ertificate a nd a second

- c l a ss airman m e dic a l c ertif i c a te, a nd who has comp l eted the EEI

training and c urre nc y r e qui r ements, t o con d uct the pro p osed U A S fl i g ht op e r atio n s for

compens a tion.

This r e lief is r e q u ested since the lim i tations set forth in Se c tion 61.113(a) and ( b ) state

that a p r ivate pilot m a y , for compens a tion or hi r e, a c t as P I C of a n air c raft i n conn ec tion with

a n y business or e mpl o y ment if (1) The fl i g ht i s on l y i n cident a l to that bus i ness or e mpl o y ment;

and (2) The a i r c r a ft do e s not c a r r y p asse n g e rs or pro p er t y for c om p ensation or hire.

As s e t forth more f ul l y b elow, EEI submi t s that an e quival e nt le v el of saf e t y will be

maintained b eca u s e no P I C wi l l be allo w ed to op e rate EEI UAS’s unless that P I C h a s

demonstr a ted, thro u g h t h e Type specific U A S trai n ing a nd curren c y requiremen t s , that the P I C

is able to s a f e l y o p er a te t he EEI UAS in a manner c onsistent with the op er a tions spe c ific a tions

a s d es c ribed in th i s e x emp t ion, incl u ding e v asive a nd e m er g en c y m an e uv e rs, a s w e ll as

maintaining appropriate distan ce s from p e ople, v e ssels, vehicl e s a n d s t ru c tur e s.

F u r the r

, EEI submi t s that all fli g hts of EEI UAS ’s are con du c t e d b y the P I C pursuant to

the gr a nt of t his P etition (1) will be i n c ident a l to EEI ’ s b u siness; and ( 2 ) w ill not c a r r y

p asse n g e rs or pro p er t y for c om p ensation or hire.18

2. Ext e nt of R e lief EEI S e e ks And T he R e ason EEI S e e ks R e lief

F r o m Se c tion 91

. 7( a ).

Relief f rom S ec tion 91

. 7 ( a), e ntitled Civil a i rcraft air w orth i nes s , is requ e sted to the

e x tent r e quir e d to allow EEI to determine that each UAS is in an airwo r t h y condition prior to

ev e r y fl i g ht b y e nsuri n g that each UAS is in compliance with their respective Operator s

Manual /Users Guide

, a n d that the UA S is in c ondition for sa f e fli g h t

. C opi e s of the manu a l

, which c ontain p r opr i etary infor m ation, are atta c h ed h e r e to as Attachments C, D, E , G, H and I

a re to b e h e ld in a separ a te file pursuant to 14 C

. F .R. § 11.35(b)

.

EEI s ee ks the requ e s ted r eli e f b e ca u s e the listed UAS’s do not r e quire an airwo r thiness

c ertifi ca t e in a c co r d ance with 14 C.F.R. Part 21, Subpart H with regard to Part 23 and 27 as

appropriate

. Ther e for e

, EEI will ensure that the EEI UAS’s are i n an a irwo r t h y condition bas e d

u pon i t s c omplian c e with the op e r a ti n g do c u ments prior to ev e r y f l i g h t, and as st a ted in the

c o n di t ions and l i m i tations below.

3. Ext e nt of R e lief EEI S e e ks And T he R e ason EEI Seeks R e lief F r o m

Se c tion 91.12 1

.

Relief f rom Se c tion 91. 1 2 1 , entit l ed Altimeter s e tting s , m a y be r e quir e d to allow fli g ht

oper a tions of EEI UAS’s which u til iz e s a b a rom e t e r a nd GPS e quip m ent, to ensure that a

g r ound lev e l p r es s ure setting wil l be established p r ior to e ach fl i g ht, in order to r e p o rt altitude

to the P I C. EEI se e ks the requ e sted r e lief bec a use t h e EEI UAS’s do not util iz e a t y pical

ba r omet r ic altimeter onbo a rd th a t m a y b e set as c on t emplated by S e ction 91.121. As more

f ul l y set f o r th b elow, an e quiva l ent lev e l of saf e t y will be mainta i ned since EEI UAS’s are

equipped with a b a rom e ter and G P S equipment, which will ensure that a g round lev e l pr e ssu r e

s e tting wi l l be established p r ior to e a c h fl i g ht, and provid e s t he P I C with alti t ude information of

the U A, above ground lev e l ( A G L )

, on the h ea ds

- up displ a y of the g r ound c ontrol station

(GCS).

4. Ext e nt Of Reli e f EEI S e e ks And T he R e ason EEI Seeks R e lief Fr o m

Se c tion 91.151( b ).

Relief f rom S ec tion 91. 1 51 ( b), entitled Fuel Re q u irem e nts for f l i ght i n V F R c ondition s

, is r e qu e sted to the e x tent r e quir e d to allow fli g hts of EEI’s b a tte r y power e d UAS’s duri n g

d a y l i g ht hours in visual meteorolo g i cal conditio n s under visual fli g ht ru l e s (V F R), to continue

for the following duration :

Merlin UA S

– approximately 60 minutes

. Lockheed Martin Indago LE

– approximately 45 minutes

. 3DR DIY Quad

– 20 minutes.

Phoenix 30 Quadrotor

– 25 minutes

Latitude Engineering MC 120

– 10 minutes.

Latitude Engineering HQ

- 40

– Able to comply with 91.151(b)

.19

This will ensure that the U A will land with 20 per c e n t of endurance remaining. EEI

se e ks the re q uested r eli ef , be ca u s e without an e x emption from Se c tion 91.151 ( b), the fl i g ht

time dur a tion of the batte r y p ow e r e d UA S ’s will sever e l y c onstrain the pr ac tic a li t y of conducting

training, security, concept development and PSD support flights

, which EEI pr o pos e s to

conduct pursu a nt to this P etit i on. Si g nific a nt l y

, a s set f o rth in the supporting documentation

attached , the technical sp e cific a tions of each EEI UAS and their associated Oper a tions

Manu a l / Users Guide , and EEI ’ s propo se d oper a ti n g lim i tation s , ensure that EEI will saf e l y

o p er a t e the bat t ery po w e r ed UA s duri n g d a y l i g ht hours in V F R conditions for a total flight

duration not to exceed 80% of the battery power with 20 p e r c e nt o f batt e r y power r e maini n g

after landing.

5. Ext e nt Of R e lief EEI See k s And The R e as o n EEI S e e ks Relief F r o m

Se c tions 91.405(a), 91. 4 07(a ) (1 )

, 91.40 9 (a)(1) & (a ) (2 )

, And 91.417(a) &

(b).

Since Se c tions 91.405( a ), 91.407( a ) ( 1 ), 91.409(a)(1) & (a) ( 2 ), and 91.417 (a ) & ( b ) on l y

app l y to ai r c r aft with an airwo r thiness c ertifi ca t e, EEI r e qu e sts r elief from these Se c tions

be ca use EEI UAS’s do not have an airwo r thiness certific a t e. As set fo r th more ful l y b e low, EEI

UAS’s me e t the c on d itions o f Se c tion 333 of the F MRA for oper a tion without an a i r wo r thiness

c e rtificat e

. A c c ordi n g l y

, EEI will use qualified tech n icians and certificated Private Pilots to

per f o r m mainte n anc e

, a l t er a tio n s, or pr e v e ntive mainte n an c e on the UAS using the me t hods,

techniques, a nd p r a c tic e s p r es c ri b ed in the EEI General Operation Manual section 7

“M ainten a nce ” ( see A ttachment F ). EEI will follow the Manufacture r s User guide s as a

reference document in conjunction with the Maintenance protocol established in the EEI

General Operations Manual S ection 7 “Maintenance”. Fu r thermore, EEI will doc u ment and

maintain all mainten a n c e r ec o rds for each UAS it operates.

D. The R e asons W h y Gr an ting EEI ’s R e qu e s t Would Be In T he P u b l i c

Inte re s t ; That Is, H o w I t Would Benefit T he P ubl i c As A Whole.

G ra nting t h e pr e s ent P e tition will further the public inter e st b y a llowi n g EEI to

s af e l y

, e f ficient l y

, a nd e c onom i c a l l y p e r f o r m commercial training, security, concept

development and PSD support over are a s of the United States

.

i. Training

.

ii. Commercial Security Operations

.

iii. Security Concept Development for US and International security requirements

.

iv. Personal Safety Device (PSD) support.20

These operations will provide si g nifi c ant ben e fits to US public security and safety by

providing enhanced situational awareness, improved risk and threat management, minimizing

operating costs and reducing response times.

1. T h e P u b lic Will B enef i t F r o m T h e Training, Concept Development, and

Security P er f o r m e d.

EEI submits th i s P e t ition t o commer c ial l y o p er a te the listed UAS’s to conduct

commercial security, training and international security concept development flights t h ro u g ho u t

are a s of the Unit e d States

. EEI UAS’s will provide s a f e

, e f f ici e nt, and e c onomic a l training and

security t o fu r ther ea c h of these fields, a ll of which are critical to the w e l l

- be ing of the g e n e ral

public.

I n government training

, the listed UAS will be used to provide government agency

training to support their CoA applications and Public Use concept development studies,

available to them outside of their jurisdiction. This will allow government entities increased

access to training, shared training facilities, standards and operating procedures. This will

allow efficiencies to be realized to these agencies, increasing safety and security to the public.

A s Commercial S ecurity Services UAS flights EEI will conduct flights to integrate UAS

into commercial security operations

, providing additional security options to commercial

security companies.

I n S ecurity C oncept D evelopment

, EEI will develop services and equipment to offer

International C ommercial S ecurity S ervices ( such as oil and g a s indust r y ) to enable use of UAS

to increase security operations

. D evelopment of these concepts will increase stability and

security to foreign countries ’ infrastructure and citizens.

For Personal Safety Device (PSD) support, these commercial flights would benefit

public safety by allowing rapid detection and location of persons equipped with personal safety

location devices. These radio based devices can be detected from the elevated U AS (max

400ft) over greater range s than traditional detection means and with greater flexibility, allowing

rapid location and thus saving lives. Typical examples would the location of those likely to

wander (Alzheimer and Autism) or those persons likely to be missing over land or sea

.

The spe c ific o p e r ations that EEI will per f o r m with t he listed U AS

, demonstr a te how the

re q uested e x emption wi l l d i r ec t l y be n e fit the abov e

- refer e n c e d industries and the public.

2. T h e P u b lic Will B enef i t F r o m T h e Sa f ety A nd Ef f iciency O f EEI UAS’s.

Conducting training, security, concept development and PSD support wi t h EEI UAS’s

ins t e a d of m a n n ed a ircraft, will g re a t l y b en e fit the p ubl i c b y re d uci ng the l e v els of a ir a nd n oise

pol l ut i on g e n e r ated during t r aditional manned a e ri a l f l i g ht ope ra tions. B y using b atte r y po w er

and ele c tric motors, the smaller UAS ha ve no a ir pollution, and are the most viable

e nvironmental l y c on s cious alt e rn a tive to helicopter or fixed wing manned aircraft

. The listed

UAS can all operate while r e du c i n g the carbon fo o tprint of a e ri a l support and r e du ce d noise

po l lut i on. B y using t h e UA S to pe r fo r m training, security, concept development and PSD

support flights

, t he subst a ntial risk to l i fe and p r op e r t y in the air a n d on the ground, w hich is

usual l y a ss o ciat e d with tr a di t ional mann e d air c r aft f l i g ht ope ra tions, will be substanti a l l y

re d u ced or c omple t e l y e liminated. Notwithstanding f r om t he la c k of fl i g ht crew mem b ers

lo c ated onboard the a ir c r a ft, the UA S ’s ( w e i g hi n g less than 55 pou n ds)

, h ave less p h y sic a l21

pot e ntial for coll a t e r a l dam a g e to life and prop e r t y on the g roun d

, a nd in t he a ir, c ompared t o

the mann e d a i r craft th a t t y pic a l l y c ond u ct a e ri a l security.

3

. P er f o r m ing T h e training, security, concept development and PSD support

P er f o r m e d W ith EEI UAS’s W ill B enefit T he Econ o m y.

I n addition to being s a fe and ef f i cient, EEI UAS’s are also an ec o nom i c a l alt e rn a tive to

usi n g man n ed a ircraft to c ond u ct similar a e r ial services

. As such, op e r a tion of UAS’s will allow

United S t ates b a s e d companie s , l i ke EEI

, to remain competitive a nd c ontrib u te to g r o wth of the

U .S. e cono m y

. Sp e cific a l l y , w i th the rising c ost of aviation fu e l and the En v ironmental

Prote c tion A gen c y ( EPA) r e g ulato r y ac tions phasing out le a d e d a v i ation fuels, U .S . own e d a nd

op e r ated companies must adopt new and a lternative te c hnolo g y in or d er to r e main

competitive. T he listed UAS operate such te c hnol o g ies that not on l y a llow compan i es gr ea t er

oper a tional fl e x ibili t y c om p ar e d to mann e d a ircraft, but provides such fl e x ibi l i t y wit h out t he hi g h

op e r ation a l c ost of a tr a ditional mann e d a ircraft. B y op e rating t h e listed UA S

, companies s u ch

a s EEI c an rema i n competitive and p r o f itable, and the r e f ore, provide gre a ter job st a bili t y to

empl o y ees and contr a ctors, which will ul t i m ate l y c on t ribute to g ro w th of t h e U.S. econo m y

. I mpro v ed fin a n c ial per f ormance o f U.S. companie s , thro u g h commer c ial use o f the UAS,

provid e s a stable w ork f o r c e that inc r e a s es co n sumer s pendin g ; improves lo c al, stat e

, a nd

f e d er a l tax r e v enu e s; and a llows compani e s to invest in resear c h and d e v elopment in ord e r to

re ma in comp e t i t ive both in t he United States a nd a br o a d

.

4

. T h e r e A r e No Pr ivacy I ss u es.

Si m i l ar to the mann e d a erial fli g ht op e r a tions that have been c o nducted for

de ca d es, EEI ’ s p r o p osed oper a tion of UAS’s will not i mplicate a n y priva c y issues. S pe c ific a l l y

, the listed UAS will be op e r a t ed primarily in private secure a r ea s, and in a cc o r d anc e with all

Fe d e r a l Aviation R e g ulations, including the minimum a l t i tude re quir e ments of 14 C. F .R. §

91.119. Most signifi ca nt l y , EEI’s UA S’s will not be op e r a t ed closer t h an 5 00 f ee t to a n y

person, v essel, vehicl e , or st r u ctu re , which is no t dire c t l y i n volved in the oper a tion.

E. T he R e asons W h y G r an ting T h e Ex e m ption W o u ld No t Ad ve r s e ly A f f e c t

Sa f ety, O r H ow T he Ex e m ption W o u ld P rovide A L e v e l O f S a f ety A t L e ast

E qual To T h at P rovided B y T h e Rule F r o m W hich EEI S e e ks Ex e m ption.

1. R e asons W h y EEI’s UAS’s M e e t T h e Conditio n s O f T he F A A

Mod er nizati o n A n d R e form Act O f 2012 (F M R A) Se c tion 333.

I n consid e r a tion of t h e si z e, w e i g ht, sp e ed, a nd l i m i ted oper a ting area a ss o ciat e d with

the unmann e d a ircraft and its oper a tion, EEI ’ s o p er a tion of the listed UAS

, me e ts the

conditions of F MRA Sec t ion 33 3 , and will not r e quire a n a i r worthiness cer t ific a te in a c co r d a n ce

with 14 C

. F .R. Part 21, Subpart H

, with regard to Part 23 and 27 as appropriate

. Se c tion 333

provides a u t hori t y f or a U A S to ope r ate w ithout airwo r thiness c e rtification and s e ts fo r th

r equir e me n ts for consideri n g w h eth e r a U A S will cre a te a h azard to user s of t h e N A S or the

public, or ot h er w ise pose a thr e at to n a tional se c uri t y

. Sp e cifical l y

, F MRA S e c tion 333 states

the followin g

, in part:22

( a ) I n G en e ral.

-- Notwi t

hstanding any o t

her requi r em e nt of th i

s sub t it l e, a n d not

later than 180 days after the date of ena c tm e nt of th i s Act, the S ec r

e ta r y of

Transpo r ta t ion shall determine if c e rtain unmanned aircraft syst e ms may op e rate

safe l y in the national airspace syst e m b e fo r e completion of t

he p l an and

ru l ema k ing required by section 332 of this Act or the guidance req u ired by s e ction

334 of this Ac t

. ( b ) Asses s m e nt of Unma n ned Aircraft Syste m s

. -- In making the

d e ter m inati o n under subse c tion (

a )

, the Secr

e t ary shall determin e

, at a

minimu m

--

( 1 ) which typ e s of unm a nned aircraft systems, if an y

, as a result of t

heir

size, weight, spe e d, op e rational capabil i ty, proximity to airports and

popu l ated areas, and operation w i thin vi s ual line of sight do not c r e ate a

hazard to us e rs of the national a i rspace syst

e m or the p ublic or pose a

threat to national s e c urity; and

( 2 ) whether a certif

i cate of waiv

e r, c e rtif i cate of authorizat

i on, or

a i r wort h iness c e rtification under se c tion 44704 of t itle 49, United States

Code, is required for the op e ration of unmann e d aircraft systems id e ntif i ed

und e r paragraph ( 1 )

.

(c) R e qui

r em e nts for Sa f

e Op e ration

. -- If the S e c r etary d e ter m ines un d

er this

section that c e rtain unmann e d aircr a ft systems m ay operate s a fely i n the

na t ional air s p a c e syst

e m, the S ec retary shall estab l ish r equire me nts for t

he safe

op e rat i on of such aircraft systems in the national a i rspace s ystem.

I n s e e ki n g this e x empti o n, EEI submi t s that t he listed U A S

, ca n oper a te s af e l y in the

N A S pursuant to F MRA S e c tion 333, as d e monstrated b y : ( a) the c h ar a c t eristics of

each UAS; (b) t h e pilot c e rtifi ca tion r equir e ment; and ( c) the speci f ic oper a ti n g

lim i tation s

.

a. T h e Spe c i f ications O f T he Merlin UAS To D e m ons t rate I t s

Sa f e Chara c teristics.

The Merlin UAS d oes not create a h azard to users o f the N AS or t h e publ i c, or

othe r wise pose a thr ea t to national se c u r i t y c onsid e ring its si z e, w e i g ht, s p eed, and

op e r a tional c a p a bili t y

.

i. Te c h n ical S p e c i f icatio n s Of T he Merlin U A S.

Unmann e d

Aircraft S y stem The Merlin is an U nmanned Ai r craft S y st e m t hat is comprised

of fixed wing unm a n ne d air c r aft a nd a tr a nsport a ble g round

co n trol stati o n.23

Unmann e d

Aircraft

Dimensions Wing Span: 102 inch e s

Nose to Tail: 77 inch e s

En g ine

(Propulsive

Unit) En g ine (Propulsive Unit)

Manufacture r

- Scorpion P/N:SII

- 4035

- 250 (Ele c tri c )

F AA E n g ine T y p e C e rt: None

Propulsive Unit T y p e : 3.6 hp Peak P ower Direct Drive

Weight

– 15 .87oz

Max RPM

– 12,600

Motor, Ele c tric Sub

- A s s e mb l y :

Manuf a c tu r er: Castle Creations

Model: Castle Talon HV120

Part Number: CSE010013100

Type: Electronic Speed Controller 120amps

Weight

– 6.56oz

F u e l Not Applic a ble.

N O TE: The Merlin UAS is pow e r e d b y 4 L it h i um Po l y m er

r e c h ar gea b l e ba t terie s

, P/N HC30C

Propell e r a nd

Propell e r

L imits F AA Prop e ll e r T y pe C e rtific a te: None

Propell e r T y p e : One 2

- bla d e, Bee chwood , fi xe d pit c h, tractor

Manuf a c tu r er: X oar

Model: 1506

Diamet e r (Nom i nal): 19 in.

Ba tte r y Comm a nd

& Control 4 Turnigy Multistar Ba tt e ries P /N HC30C pow e r the motors,

and c ommand a n d control.

Capacity

– 4S 14.8V 10,000 mAh

T e mpe ra tur e :

- 30° / +120° F

N O TE: The motor temp e r a ture is not displ a y e d

to the oper a tor.

Weight

– 804 g

Dimensions

– 160mm x 65mm x 36mm

Max Charge

– 2C (22 Amps)

Max Discharge

– 10 C (110)

Airsp ee d L imits Vne ( N ev e r E x ce e d S p e e d) 100 kno t s24

Emp t y Wei g ht

C.G. Ran g e 34.75”

D a tum Nose of Aircraft

Ma x i m um Wei g hts Ram p 30 lbs.

T a k e off 30 lbs.

L a ndi n g 30 lbs.

Emp t y Wei g ht 14 .8 5 lbs.

N O TE: Emp t y w e i g ht e x cludes we i g ht of b a tt e r ies

and p a y l o ad modules.

F r e q u en c ies 902

- 928 MHz ( I SM Ba n d)

1.3 G H z ( I SM Ba nd)

2.4 G H z (ISM Band)

5.8 G H z (ISM Band)

Compu t er Softw a re Avionics e mbedd e d pro c essor

Mini m um C r e w 1

- EEI Merlin UAS c a n be op e r ated b y a s i n g le oper a tor

accompanied by a visual observer.

Number of Se a ts 0

- N ot Applic a ble.

F u e l Capaci t y Not Applic a ble.

Oil C ap ac i t y Not Applic a ble.

Ma x . Op e r a ting Altitude 4 00 ft. AGL

Rotor B lade a nd

Control Movem e nts F i x ed Rotor Control. V e hicle c ontrol is a c hieved throu g h

v a r y i n g thrust of ea ch motor ind i vidual l y

.25

Nominal Endur a nce 60 minutes with 200g payload

Ambient Outside

Air T e mpe ra tu r e

(OAT) Ma x i m um OAT: 120 °F ( 49 °C)

Mini m um OAT At Altit u d e :

- 3 0 °F (

- 34 °C)

W ind L imi t ation 25 mph

Mainten a n c e This EEI Merlin UAS must be maintain e d in acco r d a n c e with

the manu fa ctur e r ’ s Users Guide , or la ter F AA a c c epted

re vision.

b

. T h e Spe c i f ications O f T he Lockheed Martin Indago LE

De m ons t rate I t s Sa f e Chara c teristics.

The Lockheed Martin Indago LE d oes not create a h azard to users o f the N AS or

t h e publ i c, or othe r wise pose a thr ea t to national se c u r i t y c onsid e ring its si z e, w e i g ht,

s p eed, and op e r a tional c a p a bili t y

.

i. T e c h n ical S p e c i f icatio n s of t he Lockheed Martin Indago LE.

Unmann e d

Aircraft S y stem The Lockheed Martin Indago LE is an U nmanned Ai r craft

S y st e m t hat is comprised of a v e rtic a l ta k eoff and l a nding

( V TO L ) unm a n ne d air c r aft a nd a tr a nsport a ble g round co n trol

stati o n.

Unmann e d

Aircraft

Dimensions Diamet e r: 42 inch e s

Rotor span: 16.25 inch e s

En g ine

(Propulsive

Unit) En g ine (Propulsive Unit)

4 Electric Motors

F u e l Not Applic a ble.

N O TE: The Lockheed Martin Indago LE is powered by

1 L it h i um

- polymer re c h ar gea b l e ba t tery EEI S/N 0290, 0294.26

Battery Capacity: 4s 11,000 mAh (162.8 Wh)

Maximum Operating Voltage: 16.8V

Minimum Operating Voltage: 13.8

T e mpe ra tur e :

- 30° / +120° F Dimensions

– 7 x 2.5 x 1.875 in

Max Charge

– 2C (22 Amps) Max Discharge

– 5C (55

Amp mps)

Duration in Minutes display on Hand Controller

Propell e r (4) EEI I n c. P/N 3590

F AA Prop e ll e r T y pe C e rtific a te: None

Propell e r T y p e : Four 2 bla d e (foldable), carbon fiber, fi xe d

pit c h, tr ac tor

Propell e r Ass e mb l y Manufacturer :

Lockheed Martin P rop e ller

Diamet e r (Nom i nal): 16.25 in.

Airsp ee d L imits Max Cruise Speed 30 mph

Emp t y Wei g ht

C.G. Ran g e Centroid of Vehicle / no adjustable limits

D a tum Centroid of V e hicle

Ma x i m um Wei g hts Ramp 4.9 lbs.

T a k e off 4.9lbs.

L a ndi n g 4.9 lbs.

Emp t y Wei g ht 2.57 lbs.

N O TE: Emp t y We i g ht Ex cludes we i g ht of b a tt e r ies and

p a y l o ad modules.

F r e q u en c ies 900 MHz ( I SM Ba n d)

1.3 G H z ( I SM Ba nd)

N O TE: F CC l i c e nse is n ot requir e d to uti l i z e the a bove

f re qu e n cies; uplink and d ownlink are on the 900 M hz band. I f

video is uti l i zed, uplink, downlink, and vid e o a re all on 1.3

G H z.27

Compu t er Softw a re Avionics e mbedd e d pro c essor

Handcontroller

– Quad Core 1.2 GHz Processor

Mini m um C r e w (1) The Lockheed Martin Indago LE c a n be op e r ated b y a

s i n g le oper a tor.

Number of Se a ts (0) Not Applic a ble.

F u e l Capaci t y Not Applic a ble.

Oil C ap ac i t y Not Applic a ble.

Ma x . Op e r a ting Altitude 400 ft. AGL

Rotor B lade a nd

Control Movem e nts F i x ed Rotor Control. V e hicle c ontrol is a c hieved throu g h

v a r y i n g thrust of ea ch motor ind i vidual l y

Nominal Endur a nce 45 minutes with 200g payload

Ambient Outside

Air T e mpe ra tu r e

(OAT) Ma x i m um OAT: 120 °F ( 49 °C)

Mini m um OAT At Altit u d e :

- 30 °F (

- 34 °C)

W ind L imi t ation 25 mph

Mainten a n c e This Lockheed Martin Indago LE must be maintain e d in

acco r d a n c e with the manu fa ctur e r ’ s Users Guide, or la ter F AA

a c c epted re vision.28 c. T h e Spe c i f ications O f T he EEI 3DR DIY Quad UAS

D e m ons t rate I t s Sa f e Chara c teristics.

The EEI 3 DR DIY Quad d oes not create a h azard to users o f the N AS or t h e publ i c,

or othe r wise pose a thr ea t to national se c u r i t y c onsid e ring its si z e, w e i g ht, s p eed, and

op e r a tional c a p a bili t y

.

i. Te c h n ical S p e c i f icatio n s of t he 3DR DIY Quad U A S.

Unmann e d

Aircraft S y stem The 3DR is an U nmanned Ai r craft S y st e m t hat is comprised

of a Quadrotor unm a n ne d air c r aft a nd a tr a nsport a ble g round

co n trol stati o n.

Unmann e d

Aircraft

Dimensions 13.7 in x 20.1 in x 11.8 in

(35 cm x 51 cm x 20 cm)

En g ine

(Propulsive

Unit) En g ine (Propulsive Unit)

Manufacturer

– 3DR 880 KV AC2836

- 358 motors

F AA E n g ine T y p e C e rt: None

Propulsive Unit T y p e : Peak Power Direct Drive

Weight

– 72 gr

Max RPM//V

– 880 KV

Motor, Ele c tric Sub

- A s s e mb l y :

Manuf a c tu r er: 3DR

Model: AC2836

- 358

Type: Electronic Speed Controller 20amps

F u e l Not Applic a ble.

N O TE: The 3DR DIY Quad is pow e r e d b y a L it h i um Po l y m er

re c h ar gea b l e ba t terie s , P/N 3S

- 8000 RMRC

Propell e r a nd

Propell e r

L imits F AA Prop e ll e r T y pe C e rtific a te: None

Propell e r T y p e : 4

– 2 bla d e fi xe d pit c h propellers

Manuf a c tu r er: 3DR

Model: SF and SFP

APC: 10 x 4.729

Ba tte r y Comm a nd

& Control 1 ReadyMade RC Ba tt e ries ( P /N 3S

- 8000 RMRC) 3S1P

11.1V pow e r the motors, and c ommand a n d control.

Capacity

– 3S 11.1V 8,000 mAh

T e mpe ra tur e :

- 30° / +120° F

N O TE: The motor temp e r a ture is not displ a y e d

to the oper a tor.

Weight

– 560g

Dimensions

– 1900mm x 52mm x 25mm

Max Charge

– 1C (8 Amps)

Max Discharge

– 70C (560)

Airsp ee d L imits N/A

Emp t y Wei g ht

C.G. Ran g e Centroid of Vehicle

D a tum Centroid of Vehicle

Ma x i m um Wei g hts Ramp 6 lbs.

T a k e off 6 lbs.

L a ndi n g 6 lbs.

Emp t y Wei g ht 3 lbs. 1oz.

N O TE: Emp t y We i g ht Ex cludes we i g ht of b a tt e r ies

and p a y l o ad modules.

F r e q u en c ies 902

- 928 MHz ( I SM Ba n d)

1.3 G H z ( I SM Ba nd)

2.4 G H z (ISM Band)

Compu t er Softw a re Avionics e mbedd e d pro c essor

Mini m um C r e w 1

- EEI 3DR Quad UAS c a n be op e r ated b y a s i n g le oper a tor

accompanied by a visual observer.

Number of Se a ts 0

- N ot Applic a ble.

F u e l Capaci t y Not Applic a ble.30

Oil C ap ac i t y Not Applic a ble.

Ma x . Op e r a ting Altitude 400 ft. AGL

Nominal Endur a nce 20 minutes No payload

Ambient Outside

Air T e mpe ra tu r e

(OAT) Ma x i m um OAT: 120 °F ( 49 °C)

Mini m um OAT At Altit u d e :

- 30 °F (

- 34 °C)

W ind L imi t ation 25 mph

Mainten a n c e This 3DR DIY Quad UAS must be maintain e d in acco r d a n c e

with the manu fa ctur e r ’ s Users Guide, or la ter F AA a c c epted

re vision.

d. T h e Spe c i f ications Of T he Latitude HQ

- 40 UAS

De m ons t rate It s Sa f e Chara c teristics.

The Latitude HQ40 UAS d oes not create a h azard to users o f the N AS or t h e publ i c, or

othe r wise pose a thr ea t to national se c u r i t y c onsid e ring its si z e, w e i g ht, s p eed, and

op e r a tional c a p a bili t y

.

i. Te c h n ical S p e c i f icatio n s O f T he Latitude HQ40.

Unmann e d

Aircraft S y stem The Latitude HQ40 is a Hybrid Quadrotor / fixed wing

U nmanned Ai r craft S y st e m and a tr a nsport a ble g round co n trol

stati o n.

Unmann e d

Aircraft

Dimensions Wing Span: 99.25 inches

Nose to Tail: 35 inch e s31 En g ine

(Propulsive

Unit) En g ine (Propulsive Unit)

Manufacturer

– Honda GX 4 stroke 35cc

1.6 hp engine / onboard Generator

F AA E n g ine T y p e C e rt: None

Weight

– 15.87oz

Electric: Manufacturer

– Hacker A60 Brushless DC motors

1500 watt motor

Current Draw

– 95 Amps Max

F u e l Unleaded Gas

N O TE: The Latitude HQ40 Quadrotors are pow e r e d b y 2

Lit h i um Po l y m er re c h ar gea b l e ba t terie s

Propell e r a nd

Propell e r

L imits F AA Prop e ll e r T y pe C e rtific a te: None

Propell e r T y p e : One 2

- bla d e, fixed pit c h, tractor

Manuf a c tu r er: Latitude

Model: N/A

Diamet e r (Nom i nal):

Ba tte r y Comm a nd

& Control 4 Turnigy Multistar Ba tt e ries P /N HC30C pow e r the motors,

and c ommand a n d control.

Capacity

– 4S 14.8V 10,000 mAh

T e mpe ra tur e :

- 30° / +120° F

N O TE: The motor temp e r a ture is not displ a y e d

to the oper a tor.

Weight

– 804g

Dimensions

– 160mm x 65mm x 36mm

Max Charge

– 2C (22 Amps)

Max Discharge

– 10C (110)32

Airsp ee d L imits Cruise 38 kts / Max 80 kts

Emp t y Wei g ht

C.G. Ran g e

D a tum

Ma x i m um Wei g hts Ramp 42 lbs.

T a k e off 42 lbs.

L a ndi n g 42 lbs.

Emp t y Wei g ht 30 lbs.

N O TE: Emp t y We i g ht Ex cludes we i g ht of b a tt e r ies

and p a y l o ad modules.

F r e q u en c ies 902

- 928 MHz ( I SM Ba n d)

1.3 G H z ( I SM Ba nd)

N O TE: F CC l i c e nse is n ot requir e d to uti l i z e the a bove

f re qu e n cies; uplink and d ownlink are on the 900 M H z

band. I f video is uti l i zed, uplink, downlink, and vid e o a re

all on 1.3 G H z.

Compu t er Softw a re Avionics e mbedd e d pro c essor

Mini m um C r e w 1

- Latitude HQ40 c a n be op e r ated b y a s i n g le oper a tor.

Number of Se a ts 0

- N ot Applic a ble.

F u e l Capaci t y 100 ounces33

Oil C ap ac i t y 3 ounces

Ma x . Op e r a ting Altitude 400 ft. AGL

Rotor B lade a nd

Control Movem e nts F i x ed Rotor Control. V e hicle c ontrol is a c hieved throu g h

v a r y i n g thrust of ea ch motor ind i vidual l y

Nominal Endur a nce 5 hours

Ambient Outside

Air T e mpe ra tu r e

(OAT) Ma x i m um OAT: 104 °F

Mini m um OAT At Altit u d e : 23 °F

W ind L imi t ation 30 kts

Mainten a n c e This Latitude HQ40 must be maintain e d in acco r d a n c e with

the manu fa ctur e r ’ s Users Guide, or la ter F AA a c c epted

re vision.34 e

. T h e Spe c i f ications Of T he Latitude MC

- 120 UAS

De m ons t rate It s Sa f e Chara c teristics.

The Latitude MC

- 120 UAS d oes not create a h azard to users o f the N AS or t h e publ i c,

or othe r wise pose a thr ea t to national se c u r i t y c onsid e ring its si z e, w e i g ht, s p eed, and

op e r a tional c a p a bili t y

.

i. Te c h n ical S p e c i f icatio n s of T he Latitude MC

- 120.

Unmann e d

Aircraft S y stem The Latitude MC

- 120 is a Microcopt e r U nmanned Ai r craft

S y st e m and a tr a nsport a ble g round co n trol stati o n.

Unmann e d

Aircraft

Dimensions 86mm x 141 x 59

En g ine

(Propulsive

Unit) En g ine (Propulsive Unit)

Manufacturer

– Latitude

– 4 brushless electric

motors with electronic speed controllers

F AA E n g ine T y p e C e rt: None

Weight

– TBD

F u e l N O TE: The Latitude MC

- 120 Quadrotors are pow e r e d b y 1

Lit h i um Po l y m er re c h ar gea b l e ba t tery

Propell e r a nd

Propell e r

L imits F AA Prop e ll e r T y pe C e rtific a te: None

Propell e r T y p e : Four 2

- bla d e, fi xe d pit c h, tractor

Manuf a c tu r er: Latitude

Model: N/A

Diamet e r (Nom i nal):35

Ba tte r y Comm a nd

& Control 2 Cell 470 mAh LiPo Battery

N O TE: The motor temp e r a ture is not displ a y e d

to the oper a tor.

Weight

– Dimensions

- Max Charge

– Max Discharge

–

Airsp ee d L imits Max 33mph

Emp t y Wei g ht

C.G. Ran g e

D a tum

Ma x i m um Wei g hts Ramp .26 lbs.

T a k e off .26 lbs.

L a ndi n g .26 lbs.

Emp t y Wei g ht

F r e q u en c ies 902

- 928 MHz ( I SM Ba n d)

2.4 G H z ( I SM Ba nd)

N O TE: F CC l i c e nse is n ot requir e d to uti l i z e the a bove

f re qu e n cies; uplink and d ownlink are on the 900 M H z

band. I f video is uti l i zed, uplink, downlink, and vid e o a re

all on 2.4 G H z.

Compu t er Softw a re Avionics e mbedd e d pro c essor36

Mini m um C r e w 1

- Latitude MC120 c a n be op e r ated b y a s i n g le oper a tor.

Number of Se a ts 0

- not Applic a ble.

F u e l Capaci t y N/A

Oil C ap ac i t y N/A

Ma x . Op e r a ting Altitude 400 ft. AGL

Rotor B lade a nd

Control Movem e nts F i x ed Rotor Control. V e hicle c ontrol is a c hieved throu g h

v a r y i n g thrust of ea ch motor ind i vidual l y

.

Nominal Endur a nce 10 minutes

Ambient Outside

Air T e mpe ra tu r e

(OAT) Ma x i m um OAT: 104 °F

Mini m um OAT At Altit u d e : 23 °F

W ind L imi t ation

Mainten a n c e This Latitude MC120 must be maintain e d in acco r d a n c e with

the manu fa ctur e r ’ s Users Guide, or la ter F AA a c c epted

re vision.37 f

. T h e Spe c i f ications of the Phoenix 30 Quadrotor

demonstrate i t s Sa f e Chara c teristics.

The Phoenix 30 Quadrotor d oes not create a h azard to users o f the N AS or t h e publ i c,

or othe r wise pose a thr ea t to national se c u r i t y c onsid e ring its si z e, w e i g ht, s p eed, and

op e r a tional c a p a bili t y

.

I. Te c h n ical S p e c i f icatio n s of t he Phoenix 30 Quadrotor.

Unmann e d

Aircraft S y stem The Phoenix 30 is an U nmanned Ai r craft S y st e m t hat is

comprised of a v e rtic a l ta k eoff and l a nding ( V TO L ) unm a n ne d

air c r aft a nd a tr a nsport a ble g round co n trol stati o n.

Unmann e d

Aircraft

Dimensions Length and width 42 x 42

inch e s

En g ine

(Propulsive

Unit) En g ine (Propulsive Unit)

Manufacturer: T

- Motor / Model MN4014

- 9

400KV

4 Electric Motors

F u e l Not Applic a ble.

N O TE: The Phoenix 30 is powered by

1 L it h i um

- polymer re c h ar gea b l e ba t tery

Battery Capacity: Tattu 6s 22 ,000 mAh

(355.2 Wh)

Maximum Operating Voltage: 25.2V

Nominal Operating Voltage: 22.2

T e mpe ra tur e :

- 30° / +120° F

Weight

– 1932g (4.4lb)

Dimensions

– 180 x 74 x 65 mm

Max Charge

– 16C

Max Discharge

– 15C

Duration in Minutes display on Hand Controller

Airsp ee d L imits Max Cruise Speed 30 mph3 8

Emp t y Wei g ht

C.G. Ran g e Centroid of Vehicle / no adjustable limits

D a tum Centroid of V e hicle

Ma x i m um Wei g hts Ramp 12 lbs.

T a k e off 12lbs.

L a ndi n g 12 lbs.

Emp t y Wei g ht 5.1 lbs.

N O TE: Emp t y We i g ht Ex cludes we i g ht of b a tt e r ies and

p a y l o ad modules.

F r e q u en c ies 900 MHz ( I SM Ba n d)

2.4 G H z (ISM Band)

Compu t er Softw a re Avionics e mbedd e d pro c essor

Handcontroller

– Shuttle DS81

Mini m um C r e w (1) The Phoenix 30 c a n be op e r ated b y a s i n g le oper a tor

accompanied by a visual observer.

Number of Se a ts (0) Not Applic a ble.

F u e l Capaci t y Not Applic a ble.

Oil C ap ac i t y Not Applic a ble.

Ma x . Op e r a ting Altitude 400 ft. AGL

Rotor B lade a nd

Control Movem e nts F i x ed Rotor Control. V e hicle c ontrol is a c hieved throu g h

v a r y i n g thrust of ea ch motor ind i vidual l y39

Nominal Endur a nce 25 minutes with 2lb payload

Ambient Outside

Air T e mpe ra tu r e

(OAT) Ma x i m um OAT: 100 °F ( 38 °C)

Mini m um OAT At Altit u d e : 32 °F (0 °C)

W ind L imi t ation 25 mph

Mainten a n c e This Phoenix 30 must be maintain e d in acco r d a n c e with the

manu fa ctur e r ’ s Users Guide, or la ter F AA a c c epted re vision.

II

. T h e L isted U A S

, Autono m ous F light And

Navigation Mod e s.

A c omplete d e scripti o n of the autonomous modes and methods of n a v i g a ti o n for the

listed UAS

, is provided in the UAS s pecific Operations Man ual 1

. A c o p y of each of th ese

manuals Section which contain proprieta r y info r mation, is att a ch e d and is to be h e ld in a

sep a r a t e f ile p ursuant to 14 C

. F .R. §11.35(b).

III

. T h e L isted U A S

, A re Desig n ed F or Co m p l ete Auton o m y

F r o m La un ch To L a n d i ng Even In T he Unli k e l y Event Of

Loss Of The C ont r ol Li n k Or N avigation.

Althou g h a de g r a d ation or loss of the c ontrol lin k , and/or d e g r ad a tion or lo s s of the

sour c e of n av i ga tion is un l ik e l y , it is a si t uation that is well plann e d for and ther e fore, is a

b e n i g n ev e nt. EEI’s UAS’s are desi g ne d for c omplete a utono m y f r om lau n ch to landing with a

line of si g ht operator in t he loop moni t oring the a i r craft

. The listed UAS all u s e a two

- st a g e

f ailsafe ap p ro ac h f o r a ll avionics failure conditions, including the ev e nt of a loss of

communications (“ L ost L in k ”). Upon loss of the communic a tion si g n a l, t h e listed UAS will

a t t empt to re

- ac quire the l i nk while maintaining the current altitude and navigating to the home

waypoint, which is likely the same location as the ground station

. Once at the home waypoint,

the M erlin UA , Latitude HQ40, will orbit the area while the Lockheed Martin Indago LE

, 3DR

DIY Quad , Phoenix 30 and Latitude MC 120 will hover. Once at the home waypoint, the

UA S ’s will continue their attempt to re

- acquire the link for a configurable amount of time

(usually 10

- 30 seconds ) to allow for rebooting of the ground s tation, if needed . The UA S ’s will

then continue to attempt to re

- acquire the link while they navigate through the landing

procedure. The landing p ro c edure f o r L ost L ink is identic a l to a norm a l landi n g proc e d ur e

. The Merlin UAS, Lockheed Martin Indago LE

, Latitude HQ40, Phoenix 30, 3DR DIY Quad

and Latitude MC 120 will en t er into a n auto

- land p r oc edur e ; descendi n g while r e du c i n g sp e ed

until conta c t with the g round. During this d e c e nt and t o uchdown, all will remain in controll e d

fli g ht.

1 E x hibits to th i

s Petit i on c ontain propri

e ta r y info r mation, and in a cc o r

d ance with 14 C.F.R. § 11.35(b )

,

a r e not to be includ

e d in the F

e d e r al D o ck e t Management S

y st e m ( F DMS).40

L oss of GPS si g n al will result in a tw o

- tier e d re c o ve r y approa c h. Upon lo s s of a GPS

si g n a l, the Merlin UA , Lockheed Martin Indago LE, Latitude HQ40, Phoenix 30, Latitude MC

120

, and 3DR DIY Quad will i m mediate l y h o ld position in a n a ttempt to r e

- a c q uire a s i g n a l. I f

after 15 se c onds, a GPS sig n al is not r e

- ac quir e d, t h e U A ’s will enter tie r

- two r ec o ve r y

. At

a n y time during e ith e r ti e r

- o n e or t ier

- two re c ov e r y , the operator can take o v er w ith

a u g ment e d control and utili z e its onboard m a g n etometer to nav i gate ba c k to the home

w a y po i nt t hrou g h dead

- r ec koni n g

. Duri n g this f ailure mode, the obs e rv e r will c a ll out the UA

position a nd movem e nt ba c k to the op e r a tor. O n ce the UA S is close e no u g h to re solve

orient a tio n , or if o p er a ti n g with a live video p a y l o ad, the oper a t or c a n e n g a g e manu a l c o ntrol

and p e r f o rm a manual landing at the pr e

- de c ided l a ndi n g site.

I f a cas c a d e of failur e s h as oc c urr e d a nd L ost

- L i n k has also o cc u rr e d d u ring tie r

- two

r ec ove r y , the Merlin UA , Lockheed Martin Indago LE, Latitude HQ40, Phoenix 30, Latitude

MC 120 and 3DR DIY Quad will enter into a n auto

- land p r o c e d u r e ; descending w hile redu c i n g

spe e d until conta c ti n g the g r ound. Thro u g hout t h is dec e nt and touchdo w n, the Merlin UA

, Lockheed Martin Indago LE , Phoenix 30, Latitude HQ40, Latitude MC 120 and 3DR DIY

Quad will remain in cont r olled fli g ht. EEI is submitting the following documents in support of

this Section (III) The Merlin UAS User Guide “Safety and Failsafes” . Lockheed Martin Indago

LE User Guide at Chapter 6.8 “Emergency Procedures ” . T he 3DR DIY Quad User Guide

“ Safety and Failsafes ”

, Latitude HQ Manual pg 20, Latitude Microcopter MC 120 pg 12, which

f ul l y des c rib e s the f ea tu r es of each model , a n d sets forth the U A S ’s o pe ration in the e v e nt of

a pow e r loss, loss of c o m mun i c a tions, loss of GPS si g n a l, loss of vid e o lin k , or softw a r e

c rash. Each copy the Oper a tor s M anu a l / Users Guides c ontains propri e t ary info r m ation, and

is att a ch e d h er e to as E x hib i t A, and is to be h e ld in a sep a r a t e f ile pursu a nt to 14 C.F.R. §

11.35 ( b) 2

.

iv. T h e Merlin G r ound Control Station and i ts O p e r a t ion.

The EEI Merlin UA, Lockheed Martin Indago LE, Latitude HQ40, Latitude MC 120

, Phoenix 30 and 3DR DIY Quad G r ound C ontrol S tation s are similar. A complete

description of the operati o n and sp ec ifi c ations of each g round control station (GC S )

a nd fli g ht c ont r ol software f o r the EEI UAS ’s is provided in the a ttached a ircraft

Operating Manuals

.

___________________________________ 2 Exhi bits to th i

s Petit i on c ontain propri

e ta r y info r mation, and in a cc o r

d ance with 14 C.F.R. § 11.35(b )

,

a r e not to be includ

e d in the F

e d e r al D o ck e t Management S

y st e m ( F DMS).41 v. Sa f e Op e r a t ion o f EEI UAS

The EEI UAS m a y b e sa f e l y op e rated b y a Pi l o t

- in

- Command ( P I C) supported by a

Supplemental Pilot (SP) a nd /or visual a Visual O bse r v e r (VO).

EEI intend s to use an internal and external pilot for flight operations. The PIC may be located

in a vehicle with a SP and/or a VO remaining outside the vehicle with a clear line of sight to

the aircraft as directed in FAA FSIMS 8900.1 Vol 16, Ch 5, Sec 3, Para 7. T he crew (PIC and

SP/VO) must remain in verbal contact throughout the flight by use of Cell Phone, Radio or

Voice. Flights must be terminated if direct communication is lost between the two flight crew.

EEI General Operations Manual at p a g e 6 .1

- 6.2 (Attachment F) describes a dditional

l i m i tations and r e qui r ements that a p p l y to oper a tions of the EEI UAS ’s , including the following:

The vehicle must be o r g a ni z ed and c l ear of an y un n ecessa r y d ebris and or

distractors prior to the oper a tion , to maintain a “sterile cockpit

. ”

Equipment and p e rsonn e l pos i tioning within the vehicle must be p r e d e t ermined

and ag ree d upon b y t h e crew

. Ea c h crew m e m b er must use a ppro p ri a t e saf e t y

restraint equipm e nt, and su c h e qu i pment sh o u l d not in t er fe re with safe fl i g ht.

A c o p y of the EEI General Operation Manual Section 7 , whi c h c ontains propri

e ta r y

information, is atta c h e d h er e to as Attachment F

, a nd is to be h e ld in a separ a te f ile pursu a nt to 14 C.F.R. §

11.35(b )

.

b. F light O p e r a t io n s Of EEI UAS’s A r e Li m i t ed To T h e Li n e

Of Sig h t O f A C er tificat e d P ilot i n C o mmand With

A Sa f ety Obse r v er

.

EEI will on l y utili z e FAA c e rtifi c ated pilots who possess a v a lid Class II airman medi c a l

c e rtificate to ac t as a pilot in command ( P I C) of t h e UAS ’s

. A d di t ional l y

, a safe t y Visual

O bse r v e r (VO) will assist all pilot s

. B oth the P I C and VO must compl e te the EEI

UAS Oper a tors Course specific to airframe a nd meet the e x peri e nce r equir e ments as set

f o rth in t he EEI General Operation Manual. A c o p y of the applicable sections of the General

Operations Manua l , which contains p r opri e t a r y infor m atio n , is attach e d h e r eto as Attachment

F

, a nd is to be h e ld in a separ a te file pu r suant to 14 C. F .R. § 11.35(b )

.

c. F ligh t s of EEI UAS’s M ust B e Co nd uct e d P u r sua n t To

S p e c i f i c Ope r ating L i m ita t io n s.

I n s e e ki n g this e x empti o n, EEI propos e s to c om m er c ial l y o p e r ate UAS’s for the special

pu r p ose of c ondu c ti n g training, security, concept development and PSD support over the

United States, pursu a nt to the following sp e cific o p e r ating l i mitat i ons:

1) Op e r ations authoriz e d b y the g r ant of e x emption must be lim i ted to the

following air c r aft listed in ( Exhibit 1 )

. P ropos e d oper a t i ons of a n y other air c r aft will42

r e quire a new p e tit i on or a p e tit i on to amend the g r a nt.

2) EEI UAS’s must not be flown a t an i n dic a ted a irs p e e d e x ce e d i ng 90 kno t s.

3) EEI UAS’s must be op e r a ted a t an a l t i tude of no more than 400 fe e t abo v e

g round l e vel ( A G L ) in COA approved areas and 200ft AGL elsewhere, a ll

alti t udes r e port e d to A T C must be in f ee t.

4) EEI UAS’s must be op e r a ted w ithin visual l ine of si g ht ( V L O S) of the Pilot in

C ommand ( P I C) a t all t i mes. Using h um an vision unaided b y a n y d e v i ce o t her

th a n c o r r ective lens e s , as spe c ified on the P I C ’ s FA A

- issued airman medi ca l

c e rtificate.

5) All ope ra tions must ut i li z e a Visu a l Obs e rv e r (V O ). The V O must be u s ed to

s a tis f y the V L OS r e qui r ement, a s long a s the P I C a l w a y s maintains V L OS

c ap a bil i t y

. The VO and P I C must be a ble to co m mun i c a te v e rbal l y a t all times.

The P I C must be d e si g n ated befo r e and during t h e f li g ht

. The P I C must ensu r e

that t he VO c a n p er f o rm the fun c tions pr e s c ribed in the op e r a ti n g documents.

6) Supplemental pilots could be used to operate the UAS . These p ilots must

be assigned UAS fli ght duties to augment the PIC for relief

, however, the PIC

retains complete and overall responsibility of the flight, regardless of who may

be piloting the UAS

. It is common for operators to have both an internal and an

external UAS pilot. The supplemental pilot can assume either of these

positions. The supplemental pilot may also assume duties of the PIC if the

s pecified qualifications are met as designated in Order 8900 .1 Vol 1 6.

7 ) The op e rating d o cum e nts and t h e g ra nt of e x e m pt i on must be maintained a nd

made av a ilable to the A dminis t r a tor upon re q uest. I f a d iscr e p a n c y e x is t s

betw e e n the conditions and lim i tatio n s i n the e x emption and t h e pro c e d u re s

outl i ned in the op e r a ti n g documents, the c onditions and l i m i tations in t he g r a nt of

e x emption take prec e d e n ce a nd must be f ollow e d. Oth e r wise, the op e rator must

follow the pro ce dures as o ut l ined in i ts oper a ti n g documents. T h e op e r a t o r m a y

upd a te o r r e vise its oper a ti n g do c u ments. I t is the op e r a tor’s r e sponsibi l i t y to

tr ac k s u ch r e visio n s and pr e s e nt u p d ated a n d r e vised documents to the

A dminis t r a tor upon r eq u est. The op e r a t o r must also pre s ent updat e d and

r e vised d o cuments if it petit i ons for e x tension or a mend m ent to the g ra nt of

e x emption. I f the op e r a t or d e te r mines that a n y u p date or revis i on would aff ec t

the b a sis upon which the F AA g ranted the e x emption, t hen the op e r a tor will

petition for amen d ment to its g r ant of e x emption. The F A A ’s UAS I n t e g r a tion

O f fice (A F S

- 80) m a y be c onta c t ed if qu e stions arise regardi n g upda t es or

re visions t o the op e r a ti n g do c u m ents.

8 ) Prior to e a c h fl i g h t , t h e P I C must inspect the UAS to ensu r e it is in a

condition for safe fli g ht. I f t he inspe c tion r ev ea ls a c ondition t hat a f fects the

sa f e oper a tion of the UAS, the UAS is prohibited f rom oper a ti n g until t he

n ece ssa r y main t en a nce h a s b e en p e rfor m ed a nd the UAS is found to be in a43

c ondition for safe f l i g ht. The Ground Control S tation must b e included in the

pr e fl i g ht inspe c tion. All mainten a nce a nd alter a tions must b e prop e r l y

document e d in the a i r craft re co r ds.

9 ) A n y U A S maintenan c e or alter a t i ons that a f fect the U A S o pe r ation or fli g ht

char a cte r istics ( e

. g

. r e placement of a fli g ht c ritical compon e n t ), must u n der g o a

fun c tional test fli g ht. T h e P I C who condu c ts the functional test fli g ht must m ake

an e nt r y in the UA S aircr a ft re c o rd of the f l i g h t

.

10 ) I n a ddition to t he p r e

- f l i g ht inspe c tion section in the op e r a ti n g do c umen t s, the

pr e fl i g ht inspe c tion mu s t also a c count for all disc re p an c ie s , i.e. inoper a ble

compon e nts, i tems, or equipm e nt, not alr ea d y cove r ed in the relev a nt s ec t i ons of

the op e r a ti n g documents.

1 1 ) The op e rator must f ol low the manuf ac tu r er ’ s U AS air c raf t/ component,

mainten a n ce , o v erh a ul, r epla ce m ent, inspe c tion, a nd l i fe lim i t requir e ments.

1 2 ) The op e rator must car r y out its maintenan ce

, i nspe c tions, and reco r d keeping

r e quir e ments, in a c c o r da n c e with the op e r a ting d o cuments. Mainten a n c e,

i nspection, and alt e r a tions must be noted in the air c r aft lo g book, i ncluding total

fl i g ht hou r s, battery cycles, des c ription of wo r k ac c omplished, a nd the si g n a tu r e

of the a u thori z ed UAS mainten a nce personn e l or P I C r e t u rning the UAS to

servic e

.

1 3 ) EEI authori z ed mainten a n c e p ersonn e l or P I C must make a r ec o r d ent r y in

the U A S l o g book or equivalent document of the c orre c tive ac tion tak e n ag a inst

discr e p a n cies di s cov e r e d be tween insp ec t i ons.

1 4 ) EEI authori z ed mainten a n c e p ersonn e l, P I C, a n d VO must r ece i v e a nd

do c u m ent tra i ning r eferen ce d in the o per a ti n g documents.

1 5 ) The U A S op e r a ted u nder the e x emption m ust comp l y with all manufa c turer

S y s t em and S a f e t y B ulletins.

1 6 ) The P I C must posse s s at le a st a FAA

- issued p rivate pilot c e rtifi c ate a n d a

v a lid F A A

- issued class II airman medi ca l certificate. The P I C must a lso m e e t the

f li g ht r eview r e quir e ments spe c ified in 14 C.F.R. 6 1 .56 i n an a ir c r a ft in which the

P I C is rated on his or her pilot c e rtificate.

1 7 ) Prior to ope ra ti n g for hire, the P I C

, and VO m ust hav e successful l y

c o mp l eted EEI ’ s tr a ini n g s y l l a b us as outlined in the op e r ating do c u m ents. I n

a ddi t ion, t he P I C and V O must also have s uc ce ssful l y c ompleted a n nual

( r ecu r r ent) tr a ini n g i n a cc o r d an c e with the op e r a ti n g do c u ments. A r ec o rd of

tr a in i ng must be do c umen t ed a nd made av a ilable up o n r equ e st b y the

A dminis t r a tor. T r a inin g , pro f ic i en c y

, a nd e x peri e n c e

- building fli g hts f o r the

p urpose of tr a ini n g pilots and VOs to c ondu c t fl i g h ts authori z ed b y the e x emption

are p e r mi t ted und e r the te r ms of the e x emption.44

1 8 ) I f the U A S loses communic a tions or loses its GPS sign a l, it must return to a

p re

- d ete r mined loc a tion within the plann e d op e r a ti n g a r ea and lan d , or be

rec o v e r ed in a cc or d an c e with t he op e r a ti n g do c uments.

1 9 ) The P I C must ab o rt the fli g ht in the e v ent of u npr e dict e d obst a cles or

emerg e n c ies in a cc o r d anc e with the op e r ating do c u m ents.

20 ) The op e rator must obtain familiarity with the issued Cert i fic a te of W aiver or

A uthori z ation (COA) p r ior to cond u cting a n y o p er a tions und e r the g ra nt of

e x emption. Th e C OA m ay also r e quire the oper a t or to r e qu e st a Notice to

Airman ( N OT A M) not mo r e than 72 hours in adv a nce, but not less than 48 hours

p r ior to the oper a tion.

2 1 ) All UAS oper a ted in a c c o rd a nc e with the e x emption must be identifi e d b y serial

number, r e g istered in a cc o rd a n c e with 14 C

. F .R. P art 47, a nd h a ve identification ( N

N umb e r) ma r ki n g s in ac c o r d ance with 14 C .F

. R Part 45, Subpart C.

2 2 ) B efore condu c ti n g fl i g ht ope r ations, the r adio fr e qu e n c y spe c t rum used for

op e ration and c ontrol of the UA S must c omp l y with the Fe der a l Com m unications

Com m iss i on ( F CC) or o t her a ppropriate g overn m ent ove r s i g ht a ge n c y

re q uirements.

2 3 ) The do c uments r e qu i red und e r 14 C

. F.R §§ 91.9 a nd 91.203 must b e a v ailable

to the P I C at the G round Control S tation of the UAS a n y time the a ir c r a ft is

oper a ti n g . Th e se d o cum e nts must be made a v a ila b le to the Adminis t rato r , or a n y

law en f o r cement off i cial, up o n requ e st.

2 4 ) The U A S must r e main c le a r a nd y i eld the r i g ht o f w a y to all other a ircraft

oper a tions and activi t ies at all ti m es.

2 5 ) I f the U AS i s oper a ted f rom a moving d e vi c e or v e h i cle, t he op e r a tion must be

in a c co r d an c e with t he op e r a ti n g do c u me n ts.

2 6 ) UAS o p er a tions m a y not be c on d ucted du r i n g ni g ht, as defined in 14 C.F.R.

§ 1.1.

2 7 ) All ope ra tions must be condu c ted un d er visu a l meteo r olo g i c a l conditio n s (VMC).

The UA S may not be op e r a ted l ess th a n 500 fe e t below or less than 2,000 fee t

hori z ontal l y f r om a c loud or wh e n visibi l i t y is less than 3 statute miles f rom the P I C.

2 8 ) Du r i n g op e rations i n the N a tional Airsp a ce S y stem, the UA S m a y not ope ra te

w ithin 5 nauti c al miles of the ge o g r aphic center of an a ir p ort as d e n oted on a

cu r re nt FAA

- published a e ron a uti c al c h art unless a letter o f a g re ement w i th t hat

air p ort’s man a g e ment is obtained, a nd the op e r ation is condu c ted in a cc ordance

with a NOT A M as r e quir e d b y the op e r a tor’s COA. The letter of a g re e ment with t he

a irpo r t ma na ge ment must be made av a ilable to the A dminis t r a tor upon re q uest.45

2 9) The U A S m a y not be o p er a t ed over c o n ge sted or dense l y p o pulated a reas.

Th e se a re a s inclu d e, but are not li m ited, to t he y e l low ar ea s d epict e d on W orld

A e ron a uti c al C harts (WAC), Se c tional A e ronautic a l Charts (Se c tion a ls), o r T e rmin a l

A re a Ch a rts (TAC). H o w ev e r, aeronautic a l charts m a y not r eflect pe r tinent local

information. Ultimate l y

, it is t he P I C’s re s ponsibi l i t y to maintain the min i mum sa f e

altitudes r e quir e d b y 14 C.F.R. § 91.119.

30 ) Op e r ation of the UA S must be c o n ducted a t le a st 500 f e e t f r om all

person s , v e ssels, vehic l e s , and stru c tur e s not dir e c t l y involved in the

op e r ation.

3 1 ) Op e r ations of the UA S m a y b e c ondu c t ed a t distanc e s less th a n 500 f ee t f rom

particip a ting p ersons, v e s sels, vehicles or stru c tu re s that perfo r m an essenti a l

function in conn ec tion with t h e spe c i al purpose operations. O per a tions closer t h an

500 f e et f r om the P I C, VO, oper a tor t r ainees and e ssential persons, are p e rmit t ed

wh e n op e rat i onal l y ne ce ssa r y ; but n ev e r so c lose as to pr e s e nt an un d ue h a zard,

per 14 C

. F .R. § 91.119( a ).

3 2 ) Op e r ations of the UA S m a y b e c ondu c t ed a t distanc e s less th a n 500 fe e t f rom

unoc c upied v e s s els, vehicl e s or stru c tu r es own e d b y the l a nd o wner/ c on t r o l l er

w h e n the land own e r/ c ontroller g rants s uch p e rmission and the P I C ma k es a

saf e t y a s sessment of the r isk from operations closer to these obj e cts.

3 3 ) All ope ra tions shall b e c ondu c ted with permiss i on f r om the land

o w n e r / controller or authorized r e p re s entativ e

. Permission from land

own e r/ c ontroller or autho r i z ed r e p re s entative must be ob t ained f or e a ch fli g ht to b e

c ondu c ted.

3 4 ) A n y incid e nt, accid e nt, or fli g ht operation th a t t r a ns g resses the l at er a l or

vertic a l boundari e s of the o p er a t i onal a r e a a s defined b y t he appli c able COA must

be re por t ed to the F AA’s UAS I nt e g r ation O ffice (AFS

- 80) w ithin 24 hours.

A cc idents m eeting t h e r e quir e ments of 49 C

. F.R. Part 830 must be r eport e d to the

N a tional T r ansport a tion Saf e t y B o ard ( NTSB) pe r instructions contain e d o n th e

NTSB Web site: w w w.ntsb. g ov.

2. R e asons W h y a n E xe m ption f r o m t he R e qui r e m e nts o f S e c tion

61.113(a) a nd (b) Would Not A d ve r s e ly Af f e c t Sa f ety.

EEI submits that an equival e nt lev e l of s af e t y e stablished b y S e ction 61.113(a) a nd (b)

will be maintain e d be c a use n o P I C will be a ll o wed to ope ra t e the UAS unless that P I C has

demonstr a t e d, throu g h the type specific UAS training and c ur r en c y re qu i r e ment s

, that the P I C

is able to safe l y o p er a te t h e UAS in a mann e r co n sistent with t his e x emption, including

e vasive and e mergen c y ma n euv e rs a nd m aintaining a ppropri a te distances f r om peopl e

,

v e s s els, ve h icles and stru c tu r es.

C onsid e ring EEI ’s p r oposed a rea of o p er a t i o n s and the op e r ating lim i tations set fo r th

a bov e ; the p ar a ll e l nature of p r i v ate pilot a e r onautic a l knowle d g e re q uirements to those of

comm e r c ial pilot r e qui re ments ( S e e E x emption No. 1106 2 ); and the a irm a nship sk i l l s46

ne ce ssa r y to saf e l y op e r ate the EEI UAS, EEI submi t s that the additional mann e d a irma n ship

e x peri e n c e of a c omme rc ial l y certifi c ated pilot w o uld not co r r e late to the airma n ship ski l ls

ne ce ssa r y for EEI ’ s spe c ific proposed fli g ht o per a tions.

Additional l y , the FAA h a s pr e viou s l y g ranted reli e f from Se c tion 61.113(a) and ( b )

spe c ific to U AS, in cir c u ms t an ce s sim i lar, in all mate r ial r e s p e c ts, to t hose pr e sen t ed herein

( e

. g

. E x emption Nos. 1106 2

, 11063, 11064, 11065, 11066, 11067, 11080, 11109, 11110,

11112,11136, 11138).

As in E x emption No. 1 1 109, EEI will not allow a n y P I C to op e r a te t he EEI U A S unless

tha t P I C has demonstr a ted thro u g h the type specific UAS training a nd curren c y r e quir e ments

th a t the P IC is able to s a f e l y op e r a te the EEI U A S i n a mann e r consistent with th i s e x emp t ion,

inc l uding e v asive a nd e m e r gen c y man e u v ers a nd m aintaining a ppropr i a te dis t an ce s f r om

peop l e, vessels, vehicles and stru c t ur e s.

A c omplete d e scripti o n of the EEI UAS Training a nd Qu a lifi c ation requireme n ts is set

fo r th at p a g e s 3

- 5 t hrou g h 3

- 6 of the EEI General Op e r ations Manu a l

, a tt ac h ed her e to as

Attachment F

. Attachment F c ontains prop r ieta r y info r m ation and is to be h e ld in a separ a te

file pu r suant to 14 C. F .R. § 11.35(b).

3. R e asons W h y a n E xemption F r o m The R e q u i r e m e nts Of Section

91

. 7(a) Would Not Adve r s e ly A f f e c t Sa f ety.

The lev e l of safe t y e stab li shed b y S e ction 91.7( a ) will be maintain e d b e c a u se prior to

ev e r y f l i g ht, EEI wi l l ensure that the EEI UAS is i n an a irwo r th y c ondition and safe for f li g ht

b as e d upon the EEI U A S’s co m pl i an c e with i t s oper a ti n g documents ( e

. g

., the Lockheed

Martin User Guide,) and a s stated i n the conditions and l i mit a tions her e i n

. Additional l y , the

FAA h a s pr e vious l y g r anted reli e f from S ec tion 91

. 7(a), s pe c ific to U A S, in circumstan ce s

s i m i lar, in all mate r ial r e s p e c ts, to t hose pr e sen t ed h er e in ( e

. g . E x emption Nos. 11062,

11063, 11064, 11065, 11066, 11067, 11080, 11109, 11110, 11112, 11136, 11138).

4. R e asons W h y an E xe m ption F r o m The R e q u i r e m e nts Of Section

91

. 121 Would Not Adve r s e ly A f f e c t Sa f ety.

The e quivalent le v el of s af e t y e stablished b y S e ction 91.121 will be maintained

b eca u s e the EEI U A S is equipped with a d i g ital l y e ncod e d b arom e tric alti m eter a nd GPS

trian g ulation equipment, with a z ero a lti t ude initiation point being e stablished p r ior to each

fli g ht. As such, the P I C o n the EEI UAS i s provided the a ltitude of the UA a bo v e g round l e vel

( A G L ) via a he a d s

- up displ a y of the g round control station (G CS ). Spe c ific a l l y , the P I C of the

EEI UAS is provided thr e e d i ff e r ent t y p es of a ltitude i nformation:

(1) D e si r ed Altitude, indicating t h e c ommand e d alti t ude, l oc a ted a t the top r i g ht co r n er of HUD

as we ll as ab o v e the H UD; (2) Alt i tude Above Gr ound L e v el ( A G L ), indi c ating a ctual a lti t ude

r e lative to h e i g ht above l aun c h lev e l on the grou n d, loc a ted in the center of the ri g ht side of

t h e H U D; and (3) Climb R ate, indi c a ting t h e c urrent r ate of c limb, loc a ted in t h e cent e r of the

r i g ht side of the H U D

. A c c o r din g l y , the P I C o f the EEI U A S will be pro v ided w ith all of the

ne ce ssa r y a lti t ude info r m ation ne ce ss a r y to maint a in safe op e r ation of the UA S in t he NA S

. The F AA h a s p revious l y g r a n ted r e lief from S e c tion 9 1. 1 21 spe c ific to UAS, in c ir c umstan c es

si m ilar, in a ll materi a l respects, to those pr e sented h e r e in ( e

. g . E x emption Nos. 11062,

11063, 11064, 11065, 11066, 11067, 11080, 11109, 11112, 11136, 11138).47

5. R e asons W h y a n E xe m ption f r o m t he R e qui r e m e nts o f

S e c tion 91.151(b) Would Not Adve r s e ly A ff e c t Sa f ety.

A g ra nt of this e x emption would ensure the equival e nt level of saf e t y e s ta bl ished b y 14

C.F.R. Se c tion 91.151(b) be ca use of t h e te c hni c al s p e c ific a tions of EEI UAS ’s. EEI ’ s

propos e d o p e r ating lim i tations will ensure that EEI m a y saf e l y op e r ate the b atte r y pow e r e d

U A S’s during d a y li g ht hours i n V F R c onditions f or a tot a l fli g ht du r ation that does not exceed

80% of the battery power provided

. This will ensure a landi n g with 20 percent b a tte r y po w er

r e maining. F u rth e rmo r e, p r e vious e x emptions g r a n t ed b y t h e F A A con ce rni n g S e ction

91.151(b) e stablish that sa f e t y is not adv e rs e l y a f f e c t ed wh e n the te c hn i c a l ch a ra c te r istics

and o p er a t ing lim i tations of a U A S are c onsi d er e d. EEI UA S’s are power e d b y L it h i um

polymer batteri e s, and are prote c ted b y two low b atte r y fa ils a fes. T he gr o und control station

(GCS) provides a b atte r y indicator on the h ea d s

- up disp la y , whi c h indi c ates the U A S’s c u rr e nt

r e m aining batt e r y power me a su r ed i n volt s , and thus pro v ides the P I C with constant

a war e n ess of the re a l

- time battery volt a ge dur i ng a fli g ht.

The two low b a tte r y f ailsaf e s that prot e ct the UAS a re a “ L ow A V batte r y ”

f a ilsafe and a “ Criti c al l y low AV b a tte r y ” f a ilsa f e. The “ L ow AV b a tte r y ” failsafe flies the U A S

to the loc a tion of the g r o und control station ( G C S ), or identified Ral l y point, when the UA S

batt e ri e s rea c h a c ertain thr e shold of tim e a s co n f i g u r ed b y the oper a to r , or 22.2V. The

“Critic a l l y low A V batter y ” f a ilsa f e lands the UA S at its cu r r e nt loc a tion. T h is failsafe is

tr i g g e r ed if a b a tte r y drops b elow t he c ritic a l batt e r y volt a g e as co n f i g u re d b y the oper a tor, or

21.2V.

F u r the r m o r e

, a n e x empt i on from the re qui r ements of Se c tion 91.151(b) would not

adv e rs e l y a ffe c t safe t y because EEI will on l y c ondu c t fli g hts duri n g d a y li g ht hours in VMC,

with the dur a tion of e a ch fli g ht not t o e x c ee d the early suggested endurance of 20 p e r c e nt of

batt e r y power r e maini n g

. L ike w i s e, a s set f o rth a b ov e

, EEI h a s propo s ed sp ec ific o p er a ti n g limitations in t his

Petit i on that will maintain the equival e nt lev e l of saf e t y e stablished b y S ec t i on 91.151(b),

including the f ollowi n g :

(1) EEI UAS’s on l y b e op e rated du r ing d a y l i g ht hours (i.e. betw ee n the e nd of morn i ng

c ivil t wili g ht and the be g inni n g of ev e ni n g ci v il twi l i g ht, as published in the Ameri c a n Air

Alman ac

, conv e r te d to l oc a l t i me)

.

(2) EEI UAS’s will on l y be op e r a t ed pursu a nt to v isual fli g ht rules (VFR) i n vis u al

meteo r olo g i cal condi t ions (VMC )

.

(3) T he dur a tion of e a ch fl i g ht shall not e x c ee d 80% of battery power provided

. Si g nific a nt l y , p re vious e x emptions g r a nted b y the F AA co n cer n ing S e ction 91.151

establish that sa fe t y is not adv e rs e l y affected w h e n the te c hnic a l cha r a c te r i st i cs and op e r a ti n g

lim i tations of the U A S are c onsidered. Relief h a s be e n g r a n t ed for man n ed a ir c r aft to op e r ate

a t less than the minimums pr e s c rib e d in S e ct i on 91.151, including E x emption Nos. 2689,

5745, and 10650. Mor e ov e r, t h e FAA h a s pr e vious l y g ranted re lief f r om Section 9 1 .15 1

,48

specific to U AS in cir c umstan ce s sim i lar, in all m ate r ial r e sp e cts, to those pr e sented h er e in

( e

. g

. E x emption Nos.8811, 10808, 10673, 11042, 11062, 11063, 11064, 11065, 11066,

11067, 11080, 1110 9 , 11110, 11136, 11138).

6. R e asons W h y An E xe m ption Fr o m The R e qui r e m e nts Of S e c tions

91.405(a )

, 91.407 ( a ) (1 )

, 91.409(a)(1) & (a)(2), An d 91.417(a) & ( b)

Wo u ld Not Adve r s e ly A ff e c t Sa f ety.

I n s e e ki n g this e x empti o n, EEI submits that a n e quival e nt lev e l o f safe t y with re ga rd

to the re g ulato r y mainte n an c e and a lteration requi r ements established b y S e ctions 91.405( a ),

91.407( a ) ( 1 ), 91.409 ( a ) ( 1 ) & (a) ( 2 ), and 91.417(a) & (b) will b e met b e cause EEI , the

operator , will use its t r a ined technicians to per f o r m mainte n an ce

, alt e r a tions, or p r ev e ntive

maintenan c e on t h e unmanned a i r craft s y stem us i ng the m e thods, te c hniques, a nd pr a c ti c es

pr e scribed in the ma nufa c tur e r ’ s ma int e nance ma nual. Furthermor e

, EEI will document and

maintain all maintenan c e r e c o r ds for all of its UA S

.

Since EEI UA S wi l l be inspe c ted a s p r e scrib e d b y t h e Operators

ma n ual, EEI w i l l m aintain the e quivalent level of s a fe t y e stablished b y Se c tio n s 91.405( a)

, 91. 4 09( a ) ( 1 ), and 91.409( a ) ( 2 ). The Manufacture ` s Operator M anu a l s set

fo r th Sch e duled M a inte n an c e I ns p e c tion P ro ce d u r es for e a c h s y stem a nd c omponent.

I ns p e c tion interv a ls for the EEI UAS ’s include p re fl i ght and post fli g ht inspect i on s , as w e ll as

sch e duled insp ec tions ev e r y 25 hou r s, 50 hours, 7 5 hours, and 100 hou r s of oper a tion.

L ike w i s e, the e x emption sou g ht will not adv e rs e l y af f ect sa f e t y b ecause EEI will per f o r m

mainte n an ce

, alter a tio n s or p r ev e ntive ma i nten a nce on the UAS using the m e thods,

te c hniques, a nd pr a c ti c es pr e s c rib e d b y t h e manu f a c turer ’ s mainten a n ce m anu a l s

. T he

Manufacturer `s Operator Manual s detail pro ce d u r e s f o r e a ch component of the UA S

, including the components of the propuls i on s y s t em, le gs / arms, avionics s y stem, and p a y load

s y stem.

A c o p y of the Manufacturer `s Maintenan c e M anu a l s

, which contain propri e t a r y

in fo r m ation, is atta c hed her e to as Attachment C, D, E

, G, H, I and are to be h e ld in a sep a rate

f ile p u rsuant to 14 C.F.R. § 11.35(b )

. F u r the r m o r e , the e x emption sou g ht would mainta i n an e quival e nt le v el of s af e t y

established b y S e ctions 91.407, 91.417( a ) a nd 91

. 417(b) because a ll main t en a n c e of EEI

UAS ’s will be supervised b y EEI A&P certified technici a ns, who w ill d ocument a nd maintain

mainten a n c e r ec o rds for each EEI U A S. EEI t ra ined te c hn i cia n s are qu a lified to

condu c t a n y a nd all maintenan c e to ensure the s a f e oper a tion of each UA S

, condu c t all s e rvice insp e ctions, and authorize the use of e ach UA S bas e d upon c ompletion o f

appro p ri a t e inspe c tions. The proc e dur e s for maintaining t h e mainten a nce lo g s for the U AS

are f ul l y set f o rth in t he EEI General Operating Manual ( Attachment F a t Section 7 )

Si g nific a nt l y , pr e vious e x emptions g r a nted b y the FAA c o n c e rning S e ctions 91.405( a ),

91.407( a ) ( 1 ), 91.409 ( a ) ( 1 ) & (a) ( 2 ), 91.417(a) & ( b) e stablish that sa fe t y is no t adv e rs e l y

af f ected w h en the t ec hn i c a l char ac t eristics and o p er a ti n g lim i tations of a UA S are c onsidered.

The F A A h a s p r evious l y g ranted r e li e f specific to UAS in cir c umstanc e s s i m i la r , in all materi a l

r e spe c ts, to tho s e presen t ed h e r e in (e

. g . E x emption Nos. 11062, 11063, 11064, 11065,

1 1 066, 11067, 11080, 11109, 11110, 11112, 11136, 11138).49

F

. A S u m m a r y That Can B e P ubl i s h ed i n t he Fed e ral Register, stating:

T h e Rule s f r o m Which EEI S e e ks E xe m p t io n :

Eagle Eye Intelligence

, LLC seeks ex e m pt i on from the require m ents of 14

C .F.R Se c tions 61.113 ( a ) & ( b ), 91. 7 ( a )

, 91.121, 91. 1 51 (

b ), 91.40 5 (

a )

, 91.40 7 ( a)( 1 )

, 91.40 9 (

a ) ( 1 ) & ( a) ( 2 ), and 91.417(

a ) & (b )

.

A Brief D e sc r iption O f The Na t ure Of T h e Exe m ption EEI S e e ks:

This ex e mption wi

l l permit Eagle Eye Intelligence LLC to commer c ially operate an U

n m anned

Aircraft System (

UA S ) for the purpose of commercial training, security, concept development

and PSD support flights o ve r c e rtain areas of the United State s

.

G

. Any A d d itio n al In forma t ion, Vie w s, Or A r gum e nts Available t o

Su p port EEI ’s R e q u est.

This P etition is made pu r suant to t he F A A M od er ni z ation and Re f o r m Act of 2012

( F MRA) Se c tion 333, w h ich dire c ts the Secr e ta r y of T ra nsport a tion to det e rmine if c ert a in

UAS m a y o p er a te s af e l y in the NA S

. As such, EEI ’s r e qu e st f o r e x emption m a y b e g r a nted

pursu a nt to the authori t y of F MRA S e c tion 333 a n d 14 C.F.R. Part 11, a s set forth abov e

. F MRA Se c tion 333 sets f orth the re quire m ents for consid e ri n g wh e th e r a U AS will cr e a te a

h a zard to us e rs o f the N AS or the public, or otherwise pose a th r e a t to national se c u r i t y ; and

fu r the r , pro v i d es the a ut h ori t y f or s u ch U A S to o p er a te w ithout ai r worthin e ss certifi ca tion.

As discuss e d in detail a b ove, EEI will oper a t e each UAS s af e l y in the

N A S without cr ea ti n g a h azard to users of the N A S , or the public, or otherwise pose a th r e a t

to nation a l se c uri t y

.

CON C LUSI O N

As s e t forth h e r ein, EEI se e ks an e x emption p u r suant to 14 C. F .R. § 11.61 and

Se c tion 333 of the F A A Moderni z ation a nd Reform Act of 2012 ( F MR A ), which will permit safe

oper a tion of each EEI UAS commer c ial l y

, without an a irwo r thiness c e rtificat e

, for the

lim i ted purpose of c ond u cting training, security, concept development and PSD support over

c ertain ar e a s o f the United States

. B y g r a nti n g this Petit i on, the F AA Administrator wil l be

fulfil l ing the Con g r essional mandate of the F AA Mo d ernization and Re f o r m A ct of 2012, while

also adv a n c i n g the in t er e sts of the public, b y a llowi n g EEI to saf e l y

, e fficient l y

, and

ec onomi c al l y o p er a t e each EEI U A S commer c ial l y within t he NAS.

WH E RE F ORE , in ac c o rd a n c e with the Fe d eral Aviation Re g ulations and the F AA

Mode r ni z ation and Re f orm Act of 2012, Se c tion 333, EEI r e sp e ctful l y r e qu e sts tha t the

Administrator g rant this Pe tition for a n e x emption from the r e qui r ements of 14 C

. F .R Sections

61.113( a ) & (b ) , 91. 7 (a), 91.121, 91.151(b), 91.4 0 5( a ), 91.407(a) ( 1 ), 91.4 0 9(a) ( 1 ) & ( a )(2),

a nd 91.417( a ) & (b )

, and pe r m i t EEI to ope ra te U A S ’s for the purpose of condu c ting training,

security, concept development and PSD support over c ert a in are a s of the United S t ates.50

D a ted: 1 2 / 2 9 / 1 5

Respe c tful l y submitted,

Dean Attridge

Director of Flight Operations

EagleEye Intelligence, LLC

Cell#: 702 755 9825

Email: dattridge@eagleeyeintelligence.com

www.eagle eyeintelligence.com