ShadowAir LTD- Product Specifications & Pricing -

PHONE: 1-888-731-3092 EMAIL: INFO@SHADOWAIR.COM WEBSITE: WWW.SHADOWAIR.COM

S10-VT OBSERVER

Typical Cockpit

CONTENTS

.................................................................................S10-VT Observer - General 6-7.......................................................................S10-VT Observer - Specifications 8-9

...............................................................................S10-VT Observer - Inclusions 10

S10-VT OBSERVER

Technologically superior manned system for providing persistent situational awareness 24/7/365. Engine-off glider mode operations capitalize upon the element of surprise for both conventional and asymmetrical missions worldwide.

Certified Glider Mode Operations EASA Part 22 certified engine-off

glider mode operations worldwide. The only recognized standard allow-

ing powered aircraft to be operated in engine-off glider mode.

Exceptionally high lift/drag (L/D) ratio ensures long duration glider flights absent updrafts or thermals.

Significant flight hours accrue for each hour of engine run time and significantly reduce the required maintenance events.

Optional Dual-Mode Capability Standard S10-VT Observer can be

easily upgraded to a Dual-Mode manned/unmanned aircraft system (UAS).

Standard low cost dual sensor belly mount EO/IR camera system and Wi-Fi Mesh Downlink provides VoIP communication and streaming video > 45 mile range per antenna.

Additional state-of-the-art belly mounted sensor packages designed to meet all mission requirements can be added as desired.

Crew Comfort and Safety Due to Observers low noise

signature, coupled with wings designed to flex and absorb turbulence, crews enjoy a very relaxed ride and significantly reduced fatigue.

Sailplane technology provides a safe, low-speed, tight turning radius to keep moving targets centered in the field of view.

In the unlikely event of a midair collision, the jettison-able canopy allows a parachute-equipped crew to bail out of the disabled aircraft.

S10-VT OBSERVER

6

OBSERVER can easily be upgraded to a Dual-Mode manned/unmanned aircraft system (UAS).

OBSERVER is designed to meet the patrol requirements of law enforcement agencies and news media networks.

OBSERVER is ideally suited for border and coastal patrol in very austere environments.

OBSERVER can be modified as required to meet all of your airborne IDMASINT and ISR requirements.

OBSERVER aircraft are certified for engine-off glider mode operation.

Conservative mission operational tempo (OPTEMPO): 365 x 0.90 = 329 days per year @ 8 flight hours per day @ maximum continuous power (MCP). No scheduled maintenance event to exceed 16 hours (i.e. overhaul/replacement).

OBSERVER aircraft are Conex box deployable and trailerable.

Dual-Mode capability allows a pilot to fly a manned mission, land, then fly the same aircraft as a UAS from a Ground Control Station (GCS).

While on-station in loiter mode at 36% power, OBSERVER consumes a mere 2.37 GPH of 100LL Avgas/premium unleaded gas.

OBSERVER can accrue several hundred flight hours between 100-hour maintenance events due to the low number of engine run hours required for sustained flight in all regimes.

7

Observer SpecificationsDIMENSIONS & AREAS

External dimensionsWing span 23.00 mWings, gross 18.70 mWing aspect ratio 29.29Length overall 8.42 mWheel track 1.15 mWheel base 5.42 m

POWER PLANT

Mid plane engine, drive shaft, front reduction-gear, two blade front propeller with diameter = 1.63 m Jointed propeller fitting into nose of fuselage driven via reduction gear and carbon prop shaft Engine 115 hp MTOP (Max Takeoff Power) & 100 hp MCP (Max Continuous Power)

STRUCTURES

Modular fuselage with mid steel frame module, housing the engine compartment, and carrying wing, main landing gear, forward fuselage and tail modules.

The Carbon Fiber Reinforced Plastic (CFRP) wing consists of three modules (LH, Center-Section and RH Wing) plus winglets. Camber-changing flaps are incorporated throughout the wingspan.

The center-section wing is detachable from the fuselage via four bolts and has quick-connectors for fuel lines, electrical components, and mechanical control components.

FUEL CAPACITY

Maximum of 120 liters of fuel: 2 x 60 liters (Center-Section wing tanks) 1 x 50 liters (optional tank in empennage baggage compartment) Tank Selection: Left - Right - Both

8

WEIGHT & LOADING

WEIGHTS

Maximum Take Off Weight 850 kgMaximum Landing Weight 850 kgEmpty weight Aircraft 660 kg

LOAD LIMITS

Crew total and crew support max 180 kgPayload total max 10 kgService Ceiling 30,000Fuel total max 120 ltr

TYPICAL LOAD CONFIGURATIONS

Surveillance & Utility mission: Crew (2x) total 180 kgEndurance 8 hrs Payload total 10 kgRange 800 nm Fuel total 120 ltr

Long range ferry flight: Crew (2x) total 180 kgEndurance 9+ hrs Payload total ----- kgRange 929 nm Fuel total 120 ltr

Full payload single mission: Crew (1x) total 105 kgEndurance 10+ hrs Payload total 10 kgRange 929+ nm Fuel total 120 ltr

For loading purposes, individual weight & balance computations are required before each flight mission

Observer Specifications

9

Observer InclusionsOne S10-VT Observer manned aircraft equipped as follows:

S10-VT Observer EO/IR Payload: SkyFusion Pak EO/IR simultaneous digital image capture based on altitude, speed, overlay and location. Camera can track or be locked on a specific point of interest (SPOI). Real-time camera control via ground control station or aircraft. Camera stabilization with programmable capture offsets. Multi-interface, all-weather, multi-platform capable.

My Location moving map display with flight path, image points and flight boundaries. Video and IR streaming from aircraft. Multiple user access to real-time data. Geo-rectified stitched image overlaid on Google map with image zoom.

SkyLINK Mesh Datalink with > 45 mile range per antenna. Full motion video. VoIP communication. Email specific JPEG or Google Earth snapshots with one button. Create large regional networks. No FCC license required. One antenna included (add antennas as required to increase range).

Internet connection in areas with 3G/EVDO cellular coverage. sDVR spatial recorder VMS-HD recorder Solid State Digital Avionics Oxygen Cylinder x (2) Oxygen Mask x (2) Headset x (2) Parachute x (2) Synthetic Vision EFIS VFR Instrumentation IFR Instrumentation Onboard satellite imagery Transponder ELT XM Data Link Weather Traffic Alert System Three-axis Autopilot All Weather JAXIDA covers GPS and INS VHF/FM radio system Communications relay

$ 773,174.00 (Price Subject to Change)

Hourly Lease Rate Schedule* Dry = $675 Wet = $725

Dry (Crew) = $975 Wet (Crew) = $1,025

*Rates based on 1,200 hours per year

10

PHONE: 1-888-731-3092 EMAIL: INFO@SHADOWAIR.COM WEBSITE: WWW.SHADOWAIR.COM

S10-VTX OSPREY

Propeller Mechanism

CONTENTS

.............................................................................S10-VTX Osprey - General 13-14...................................................................S10-VTX Osprey - Specifications 15-16

...............................................................................S10-VTX Osprey - Inclusions 17

S10-VTX OSPREY

Technologically superior manned system for providing persistent situational awareness 24/7/365. Engine-off glider mode operations capitalize upon the element of surprise for both conventional and asymmetrical missions worldwide.

Certified Glider Mode Operations EASA Part 22 certified engine-off

glider mode operations worldwide. The only recognized standard allow-

ing powered aircraft to be operated in engine-off glider mode.

Exceptionally high lift/drag (L/D) ratio ensures long duration glider flights absent updrafts or thermals.

Significant flight hours accrue for each hour of engine run time and significantly reduce the required maintenance events.

Optional Dual-Mode Capability Standard S10-VTX Osprey can be

easily upgraded to a Dual-Mode manned/unmanned aircraft system (UAS).

Under-wing hard-points can carry two 60 kg loads.

A lower cost belly mount sensor system is also an available option.

State-of-the-art sensor packages designed to meet all mission requirements can be carried in underwing quick-change pods.

Crew Comfort and Safety Due to Ospreys low noise signature,

coupled with wings designed to flex and absorb turbulence, crews enjoy a very relaxed ride and significantly reduced fatigue.

Sailplane technology provides a safe, low-speed, tight turning radius to keep moving targets centered in the field of view.

In the unlikely event of a midair collision, the jettison-able canopy allows a parachute-equipped crew to bail out of the disabled aircraft.

S10-VTX OSPREY

13

OSPREY can easily be upgraded to a Dual-Mode manned/unmanned aircraft system (UAS).

OSPREY is designed to meet the patrol and interdiction requirements of military and law enforcement agencies.

OSPREY is ideally suited for border and coastal patrol and interdiction missions in austere environments.

OSPREY can be modified as required to meet all of your airborne IDMASINT and ISR requirements.

OSPREY aircraft are certified for engine-off glider mode operation and capitalize upon the element of surprise for conventional and asymmetrical threat interdiction.

Conservative mission operational tempo (OPTEMPO): 365 x 0.90 = 329 days per year @ 8 flight hours per day @ maximum continuous power (MCP). No scheduled maintenance event to exceed 16 hours (i.e. overhaul/replacement).

OSPREY aircraft are Conex box deployable and trailerable.

Dual-Mode capability allows a pilot to fly a manned mission, land, then fly the same aircraft as a UAS from a Ground Control Station (GCS).

While on-station in loiter mode at 36% power, OSPREY consumes a mere 2.37 GPH of 100LL Avgas/premium unleaded gas.

OSPREY can accrue several hundred flight hours between 100-hour maintenance events due to the low number of engine run hours required for sustained flight in all regimes.

14

Osprey SpecificationsDIMENSIONS & AREAS

External dimensionsWing span 23.00 mWings, gross 18.70 mWing aspect ratio 29.29Length overall 8.42 mWheel track 1.15 mWheel base 5.42 m

POWER PLANT

Mid plane engine, drive shaft, front reduction-gear, two blade front propeller with diameter = 1.63 m Jointed propeller fitting into nose of fuselage driven via reduction gear and carbon prop shaft Engine 115 hp MTOP (Max Takeoff Power) & 100 hp MCP (Max Continuous Power)

STRUCTURES

Modular fuselage with mid steel frame module, housing the engine compartment, and carrying wing, main landing gear, forward fuselage and tail modules.

The Carbon Fiber Reinforced Plastic (CFRP) wing consists of three modules (LH, Center-Section and RH Wing) plus winglets. Camber-changing flaps are incorporated throughout the wingspan.

The center-section wing is detachable from the fuselage via four bolts and has quick-connectors for fuel lines, electrical components, and mechanical control components.

Two external payload stations are located inboard of the separation between center and outer wing sections.

FUEL CAPACITY

Maximum of 120 liters of fuel: 2 x 60 liters (Center-Section wing tanks) 1 x 50 liters (optional tank in empennage baggage compartment) Tank Selection: Left - Right - Both

15

WEIGHT & LOADING

WEIGHTS

Maximum Take Off Weight 980 kgMaximum Landing Weight 980 kgEmpty weight Aircraft 660 kg

LOAD LIMITS

Crew total and crew support max 200 kgPayload total max 120 kgExternal loads below wing max (at two stations) 2 x 60 kgFuel total max 120 ltr

TYPICAL LOAD CONFIGURATIONS

Surveillance & Utility mission: Crew (2x) total 200 kgEndurance 8 hrs Payload total 120 kgRange 800 nm Fuel total 120 ltr

Long range ferry flight: Crew (2x) total 200 kgEndurance 10+ hrs Payload total ----- kgRange 929 nm Fuel total 120 ltr

Full payload single mission: Crew (1x) total 100 kgEndurance 10 hrs Payload total 120 kgRange 900+ nm Fuel total 120 ltr

For loading purposes, individual weight & balance computations are required before each flight mission

Osprey Specifications

16

Osprey InclusionsOne S10-VTX Osprey manned aircraft equipped as follows:

S10-VTX Osprey EO/IR Payload: Three-axis IMU gyro stabilized (direct-drive brushless motors) three channel multi-spectral system with selectable spectral bands and optics (450 nm - 850 nm) and Field of Views (FOVs) from 10 degrees full angle to 40+ degrees predicated by target color/size/area search rate. Multiple lenses available (8 mm - 70 mm) delivering resolutions (GSD) from 2.2 - 19 inches at 2000 above ground level. Data rate 15 Hz (standard) or ~ 120 MBs. FOV 5.5 -50 degrees full angle predicated by lens selection (8-70 mm focal lengths). Optical Zoom 26x video (3.5 -91 mm) Super HAD NTSC video (30 Hz). Fixed FOV (50 mm) long-wave infrared (LWIR) camera for detecting thermal signatures and for general night ISR. Zoom video can also be used for situational awareness and verification of multi-spectral detections. Multi-interface, all-weather, multi-platform capable.

eNfusion Satellite Communications Downlink High Definition (HD) Target Tracker: simultaneous tracking of 100 targets (including beneath forest and dense canopy). In-mission Look-Ahead Video Awareness (LAVA) for on-the-ground real-time situational awareness. Four under-wing hard-points Two under-wing pods sDVR spatial recorder VMS-HD recorder Moving map display Solid State Digital Avionics Air Conditioning Oxygen Cylinder x (2) Oxygen Mask x (2) Headset x (2) Parachute x (2) Synthetic Vision EFIS VFR Instrumentation IFR Instrumentation Onboard satellite imagery Transponder ELT XM Data Link Weather Traffic Alert System Three-axis Autopilot All Weather JAXIDA covers GPS and INS VHF/FM radio system Satellite Phone Communications relay

$ 2,176,686.00 (Price Subject to Change)

Hourly Lease Rate Schedule* Dry = $1,250 Wet = $1,300

Dry (Crew) = $1,550 Wet (Crew) = $1,600

*Rates based on 1,200 hours per year

17

PHONE: 1-888-731-3092 EMAIL: INFO@SHADOWAIR.COM WEBSITE: WWW.SHADOWAIR.COM

S15 TALON

Typical Cockpit

CONTENTS

.........................................................................................S15 Talon - General 20-21...............................................................................S15 Talon - Specifications 22-25

...........................................................................................S15 Talon - Inclusions 26

S15 TALON

Technologically superior manned system for providing persistent situational awareness 24/7/365. Engine-off glider mode operations capitalize upon the element of surprise for both conventional and asymmetrical missions worldwide.

Certified Glider Mode Operations EASA Part 22 certified engine-off

glider mode operations worldwide. The only recognized standard allow-

ing powered aircraft to be operated in engine-off glider mode.

Exceptionally high lift/drag (L/D) ratio ensures long duration glider flights absent updrafts or thermals.

Significant flight hours accrue for each hour of engine run time and significantly reduce the required maintenance events.

Optional Dual-Mode Capability Standard S15 Talon can be easily

upgraded to a Dual-Mode manned/unmanned aircraft system (UAS).

Hard points can carry either four 60 kg loads or two 80 kg loads.

A lower cost belly mount sensor system is also an available option.

State-of-the-art sensor packages designed to meet all mission requirements can be carried in underwing quick-change pods.

Crew Comfort and Safety Due to Talons low noise signature,

coupled with wings designed to flex and absorb turbulence, crews enjoy a very relaxed ride and significantly reduced fatigue.

Sailplane technology provides a safe, low-speed, tight turning radius to keep moving targets centered in the field of view.

In the unlikely event of a midair collision, the jettison-able canopy allows a parachute-equipped crew to bail out of the disabled aircraft.

S15 TALON

20

TALON can easily be upgraded to Dual-Mode manned/unmanned aircraft system (UAS) capability.

TALON is designed to meet the patrol and interdiction requirements of military and law enforcement agencies.

TALON is ideally suited for border and coastal patrol and interdiction missions in austere environments.

TALON can be modified as required to meet all of your IDMASINT and ISR requirements.

Dual-Mode capability allows a pilot to fly a manned mission, land, then fly the same aircraft as a UAS from a Ground Control Station.

While on-station in loiter mode at 36% power, TALON consumes a mere 2.37 GPH of 100LLAvgas/premium unleaded gas.

The aircraft is capable of accruing several hundred hours of flight time between 100-hour maintenance events due to the low number of engine run hours required for sustained flight in all regimes.

TALON aircraft are certified for engine-off glider mode operation and capitalize upon the element of surprise for conventional and asymmetrical threat interdiction.

Conservative mission operational tempo (OPTEMPO): 365 x 0.90 = 329 days per year @ 8 flight hours per day @ maximum continuous power (MCP). No scheduled maintenance event to exceed 16 hours (i.e. overhaul/replacement).

TALON aircraft are Conex box deployable and trailerable.

21

Talon SpecificationsDIMENSIONS & AREAS

External dimensionsWing span 18.00 mWings, gross 17.4 mWing aspect ratio 18.6Length overall 8.50 mWheel track 1.90 mWheel base 2.00 m

POWER PLANT

Mid plane engine, drive shaft, front reduction-gear, three blade front propeller with diameter = 1.70 m Optional five-blade propeller to further reduce the noise signature Engine 115 hp MTOP (Max Takeoff Power) & 100 hp MCP (Max Continuous Power)

STRUCTURES

Modular fuselage with mid steel frame module, housing the engine compartment, and carrying wing, main landing gear, forward fuselage and tail modules.

The Carbon Fiber Reinforced Plastic (CFRP) wing consists of three modules (LH, Center-Section and RH Wing) plus winglets. Camber-changing flaps are incorporated throughout the wingspan.

The center-section wing is detachable from the fuselage via four bolts and has quick-connectors for fuel lines, electrical components, and mechanical control components.

Two of four external payload stations are at the separation between center and outer wing sections at 6 m wingspan. The two remaining stations are closer to the fuselage.

FUEL CAPACITY

Maximum of 290 liters of fuel: 2 x 75 liters (Center-Section wing tanks) 2 x 45 liters (outer RH/LH wing tanks) 1 x 50 liters (optional tank in empennage baggage compartment) Automatic fuel management system

22

WEIGHT & LOADING

WEIGHTS

Maximum Take Off Weight 1,050 kgMaximum Landing Weight 1,000 kgEmpty weight Aircraft 620 kg

LOAD LIMITS

Crew total and crew support max 220 kgPayload total max 240 kgExternal loads below wing max (at two stations) 2 x 50 kgFuel total max 290 ltr / 210 kg

TYPICAL LOAD CONFIGURATIONS

Surveillance & Utility mission: Crew (2x) total 180 kgEndurance 8 hrs Payload total 165 kgRange 800 nm Fuel total 118 ltr / 85 kg

Long range ferry flight: Crew (2x) total 220 kgEndurance 20 hrs Payload total ----- kgRange 2000 nm Fuel total 290 ltr / 210 kg

Full payload single mission: Crew (1x) total 105 kgEndurance 8 hrs Payload total 240 kgRange 800 nm Fuel total 118 ltr / 85 kg

For loading purposes, individual weight & balance computations are required before each flight mission

Talon Specifications

23

PERFORMANCE

TAKE OFF AND LANDING / CROSSWIND LIMITS Take-off distance on concrete runway at 1050 kg MTOW

Take-off run ~ 200 m ( 660)Take-off distance over 15 m (50) obstacle ~ 500 m (1660)

Landing distance on concrete runway at max landing weight 1000 kgLanding run ~ 200 m ( 660)Landing distance over 15 m (50) obstacle ~ 500 m (1660)

Crosswind component max 37 km/h (20 knots)

CRUISE / CLIMB / GLIDE / FUEL CONSUMPTION / SERVICE CEILING

Clean configuration data (i.e. gear retracted; no under wing pods) Range excludes climb and fuel reserves Range/cruise speed with pods approximately 10-15% less than clean configuration Best SBFC estimated 0.26 kg/kWh. All data 7.5% tolerance at time of brochure publication

Cruising speed at 5000 m (16,600) and 100% MCP 190 knots (350 km/h) TAS (fast to station)Cruising speed at 5000 m (16,600) and 75% MCP 145 knots (270 km/h) TAS (economy)Cruising speed at 5000 m (16,600) and 35% MCP 75 knots (140 km/h) TAS (typical loiter)Cruising speed at MSL and 100% MCP 150 knots (275 km/h) EAS/TASCruising speed at MSL and 75% MCP 110 knots (210 km/h) EAS/TASCruising speed at MSL and 35% MCP 60 knots (110 km/h) EAS/TAS

Max rate of climb at MSL and MTOW 5.0 m/s (1000 fpm)Max rate of climb at 16,600 and MTOW 4.0 m/s (800 fpm)Max rate of climb at 30,000 and MTOW 0.5 m/s (100 fpm)Min. rate of sink at MSL and MTOW (dead engine) < 1.0 m/s (200 fpm)Best glide ratio at MSL and MTOW (dead engine) > 35

Fuel consumption at 100% MCP 25.0 liters/hourFuel consumption at 75% MCP 15.0 liters/hourFuel consumption at 35% MCP 09.0 liters/hour

Service Ceiling ( 0.5 m/s) 25,000

Talon Specifications

24

FLIGHT CHARACTERISTICS

Static longitudinal stability Agile maneuverability due to high aileron differentiation Docile stall behavior in straight-and-level flight, as well as in turns, due to

airfoil characteristics and high aileron differentiation

DESIGN SPEEDS & G-LIMITS

STALL SPEEDS AT MTOW @ MSL

Stall speed in landing configuration 1000 kg VS0 = 46 knots (85 km/h) Stall speed in loiter configuration (neutral flaps) 1000 kg VS1 = 49 knots (90 km/h) Stall speed in fast cruise configuration (negative flaps) 1050 kg VS1 = 60 knots (110 km/h)

DESIGN SPEEDS

Design speed (IAS @ MSL) VD = 205 knots (380 km/h)

SPEED OPERATING LIMITATIONS

Never exceed speed (IAS @ MSL) VNE = 166 knots (310 km/h)

Maneuvering load factor nA = 3.8 (CS23)

CENTER OF GRAVITY

Allowable in-flight CG range will be approximately 200 mm Standardized ballast within the forward fuselage or the vertical tail can be used to trim nonstandard

loading conditions The CG limits of the under-wing pods have been designed to ensure the aircraft stays within allowable

CG-limits whether or not the pods are mounted

NOISE

The noise level will be measured according to EASA part 21, subpart I.

Design features for low altitude stealth missions: Upward emitting exhaust and cooling outlet system/emissions shielded to the ground Air cooler inlet has noise absorbers; mask hot surface of air cooler inlet (optional) 3-blade low-speed propeller with RPM-optimized through front-reduction-gear Optional 5-blade low-speed propeller to further reduce the noise signature Aerodynamically clean airframe surface

Talon Specifications

25

Talon InclusionsOne S15 Talon manned aircraft equipped as follows:

S15 Talon EO/IR Payload: Four-Axis, gyro stabilized, High Definition three-chip color CCD low light capability MWCIR camera with 20:1 continuous zoom/thermal lens (true optical zoom magnification). Inertial measurement unit provides situational awareness. Laser Range Finder determines target distance up to 20 km. Multi-interface, all-weather, multi-platform capable.

eNfusion Satellite Communications Downlink High Definition (HD) Target Tracker: simultaneous tracking of 100 targets (including beneath forest and dense canopy). In-mission Look-Ahead Video Awareness (LAVA) for on-the-ground real-time situational awareness. Four under-wing hard-points Two under-wing pods sDVR spatial recorder VMS-HD recorder Moving map display Solid State Digital Avionics Air Conditioning Oxygen Cylinder x (2) Oxygen Mask x (2) Headset x (2) Parachute x (2) Synthetic Vision EFIS VFR Instrumentation IFR Instrumentation Onboard satellite imagery Transponder ELT XM Data Link Weather Traffic Alert System Three-axis Autopilot All Weather JAXIDA covers GPS and INS VHF/FM radio system HF radio system Satellite Phone Communications relay

$ 3,932,438.00 (Price Subject to Change)

Hourly Lease Rate Schedule* Dry = $1,750 Wet = $1,800

Dry (Crew) = $2,050 Wet (Crew) = $2,100

*Rates based on 1,200 hours per year

26

2008-2009 SEASON

The HAVOC System

PHONE: 1-888-731-3092 EMAIL: INFO@SHADOWAIR.COM WEBSITE: WWW.SHADOWAIR.COM

The HAVOC System

CONTENTS

........................................................................The HAVOC System - General 29-30..............................................................The HAVOC System - Specifications 31-34

..........................................................................The HAVOC System - Inclusions 35

The HAVOC System

HAVOC is a technologically superior solution for providing persistent situational awareness to monitor conventional and asymmetrical threats.

The HAVOC System HAVOC = three specially equipped

S15 Talon Dual-Mode manned/unmanned aircraft systems and one mobile ground control station (GCS).

Computer algorithms instantly control each airborne task required for complex tactical flight.

HAVOC flies the aircraft and performs routine flight tasks.

The Mission Commander manages all sensors, weapons systems and mission updates.

IP-Based Open Architecture Modular planning tool creates and

executes operator defined mission plans.

Allows real-time modifications for rapidly changing tactical situations.

Control multiple UAS/sensors in an IP-based setting adaptable to wide-ranging communication networks.

Control up to 12 unmanned aircraft and as many as 20 sensors or ground control stations.

Rules-Based Expert System Technologically superior rules-based

expert system makes instantaneous decisions for all mission dynamics.

Control multiple aircraft and sensor systems in the same airspace while sharing information and working together as a rules-based team.

Individual aircraft share messages such that all know each others location, sensor information and current systems status.

The HAVOC System The HAVOC System

29

HAVOC is a turnkey solution of three Dual-Mode manned/UAS aircraft and one mobile Ground Control Station.

HAVOC is designed to meet the patrol and interdiction requirements of military and law enforcement agencies.

HAVOC is ideally suited for border and coastal patrol and interdiction missions in austere environments.

HAVOC can be modified as required to meet all of your IDMASINT and ISR requirements.

HAVOCs Dual-Mode capability allows a pilot to fly a manned mission, land, then fly the same aircraft as a UAS from a Ground Control Station.

While on-station in loiter mode at 36% power, the aircraft consumes a mere 2.37 GPH of 100LL Avgas/premium unleaded gas.

The aircraft is capable of accruing several hundred hours of flight time between 100-hour maintenance events due to the low number of engine run hours required for sustained flight in all regimes.

HAVOC aircraft are certified for engine-off glider mode operation and capitalize upon the element of surprise for conventional and asymmetrical threat interdiction.

Conservative mission operational tempo (OPTEMPO): 365 x 0.90 = 329 days per year @ 8 flight hours per day @ maximum continuous power (MCP). No scheduled maintenance event to exceed 16 hours (i.e. overhaul/replacement).

HAVOC aircraft are Conex box deployable and trailerable.

30

HAVOC SpecificationsDIMENSIONS & AREAS

External dimensionsWing span 18.00 mWings, gross 17.4 mWing aspect ratio 18.6Length overall 8.50 mWheel track 1.90 mWheel base 2.00 m

POWER PLANT

Mid plane engine, drive shaft, front reduction-gear, three blade front propeller with diameter = 1.70 m Optional five-blade propeller to further reduce the noise signature Engine 115 hp MTOP (Max Takeoff Power) & 100 hp MCP (Max Continuous Power)

STRUCTURES

Modular fuselage with mid steel frame module, housing the engine compartment, and carrying wing, main landing gear, forward fuselage and tail modules.

The Carbon Fiber Reinforced Plastic (CFRP) wing consists of three modules (LH, Center-Section and RH Wing) plus winglets. Camber-changing flaps are incorporated throughout the wingspan.

The center-section wing is detachable from the fuselage via four bolts and has quick-connectors for fuel lines, electrical components, and mechanical control components.

Two of four external payload stations are at the separation between center and outer wing sections at 6 m wingspan. The two remaining stations are closer to the fuselage.

FUEL CAPACITY

Maximum of 290 liters of fuel: 2 x 75 liters (Center-Section wing tanks) 2 x 45 liters (outer RH/LH wing tanks) 1 x 50 liters (optional tank in empennage baggage compartment) Automatic fuel management system

31

WEIGHT & LOADING

WEIGHTS

Maximum Take Off Weight 1,050 kgMaximum Landing Weight 1,000 kgEmpty weight Aircraft 620 kg

LOAD LIMITS

Crew total and crew support max 220 kgPayload total max 240 kgExternal loads below wing max (at two stations) 2 x 50 kgFuel total max 290 ltr / 210 kg

TYPICAL LOAD CONFIGURATIONS

Surveillance & Utility mission: Crew (2x) total 180 kgEndurance 8 hrs Payload total 165 kgRange 800 nm Fuel total 118 ltr / 85 kg

Long range ferry flight: Crew (2x) total 220 kgEndurance 20 hrs Payload total ----- kgRange 2000 nm Fuel total 290 ltr / 210 kg

Full payload single mission: Crew (1x) total 105 kgEndurance 8 hrs Payload total 240 kgRange 800 nm Fuel total 118 ltr / 85 kg

For loading purposes, individual weight & balance computations are required before each flight mission

HAVOC Specifications

32

PERFORMANCE

TAKE OFF AND LANDING / CROSSWIND LIMITS Take-off distance on concrete runway at 1050 kg MTOW

Take-off run ~ 200 m ( 660)Take-off distance over 15 m (50) obstacle ~ 500 m (1660)

Landing distance on concrete runway at max landing weight 1000 kgLanding run ~ 200 m ( 660)Landing distance over 15 m (50) obstacle ~ 500 m (1660)

Crosswind component max 37 km/h (20 knots)

CRUISE / CLIMB / GLIDE / FUEL CONSUMPTION / SERVICE CEILING

Clean configuration data (i.e. gear retracted; no under wing pods) Range excludes climb and fuel reserves Range/cruise speed with pods approximately 10-15% less than clean configuration Best SBFC estimated 0.26 kg/kWh. All data 7.5% tolerance at time of brochure publication

Cruising speed at 5000 m (16,600) and 100% MCP 190 knots (350 km/h) TAS (fast to station)Cruising speed at 5000 m (16,600) and 75% MCP 145 knots (270 km/h) TAS (economy)Cruising speed at 5000 m (16,600) and 35% MCP 75 knots (140 km/h) TAS (typical loiter)Cruising speed at MSL and 100% MCP 150 knots (275 km/h) EAS/TASCruising speed at MSL and 75% MCP 110 knots (210 km/h) EAS/TASCruising speed at MSL and 35% MCP 60 knots (110 km/h) EAS/TAS

Max rate of climb at MSL and MTOW 5.0 m/s (1000 fpm)Max rate of climb at 16,600 and MTOW 4.0 m/s (800 fpm)Max rate of climb at 30,000 and MTOW 0.5 m/s (100 fpm)Min. rate of sink at MSL and MTOW (dead engine) < 1.0 m/s (200 fpm)Best glide ratio at MSL and MTOW (dead engine) > 35

Fuel consumption at 100% MCP 25.0 liters/hourFuel consumption at 75% MCP 15.0 liters/hourFuel consumption at 35% MCP 09.0 liters/hour

Service Ceiling ( 0.5 m/s) 25,000

HAVOC Specifications

33

FLIGHT CHARACTERISTICS

Static longitudinal stability Agile maneuverability due to high aileron differentiation Docile stall behavior in straight-and-level flight, as well as in turns, due to

airfoil characteristics and high aileron differentiation

DESIGN SPEEDS & G-LIMITS

STALL SPEEDS AT MTOW @ MSL

Stall speed in landing configuration 1000 kg VS0 = 46 knots (85 km/h) Stall speed in loiter configuration (neutral flaps) 1000 kg VS1 = 49 knots (90 km/h) Stall speed in fast cruise configuration (negative flaps) 1050 kg VS1 = 60 knots (110 km/h)

DESIGN SPEEDS

Design speed (IAS @ MSL) VD = 205 knots (380 km/h)

SPEED OPERATING LIMITATIONS

Never exceed speed (IAS @ MSL) VNE = 166 knots (310 km/h)

Maneuvering load factor nA = 3.8 (CS23)

CENTER OF GRAVITY

Allowable in-flight CG range will be approximately 200 mm Standardized ballast within the forward fuselage or the vertical tail can be used to trim nonstandard

loading conditions The CG limits of the under-wing pods have been designed to ensure the aircraft stays within allowable

CG-limits whether or not the pods are mounted

NOISE

The noise level will be measured according to EASA part 21, subpart I.

Design features for low altitude stealth missions: Upward emitting exhaust and cooling outlet system/emissions shielded to the ground Air cooler inlet has noise absorbers; mask hot surface of air cooler inlet (optional) 3-blade low-speed propeller with RPM-optimized through front-reduction-gear Optional 5-blade low-speed propeller to further reduce the noise signature Aerodynamically clean airframe surface

HAVOC Specifications

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HAVOC InclusionsThree S15 Talon Dual-Mode manned/UAS aircraft and one Ground Control Station (GCS) equipped as follows:

HAVOC Mobile Ground Control Station (GCS) trailer, hardware and software. S15 Talon EO/IR Payload: Four-Axis, gyro stabilized, High Definition three-chip color CCD low light capability

MWCIR camera with 20:1 continuous zoom/thermal lens (true optical zoom magnification). Inertial measurement unit provides situational awareness. Laser Range Finder determines target distance up to 20 km. Multi-interface, all-weather, multi-platform capable.

Control/Data Links: C-Band Line-of-Sight (LOS); Ku-Band SATCOM Beyond-Line-of-Sight (BLOS). eNfusion Satellite Communications Downlink High Definition (HD) Target Tracker: simultaneous tracking of 100 targets (including beneath forest and dense canopy). In-mission Look-Ahead Video Awareness (LAVA) for on-the-ground real-time situational awareness. Manned/Remotely Piloted/Fully Autonomous Four under-wing hard-points Two under-wing pods sDVR spatial recorder VMS-HD recorder Moving map display Solid State Digital Avionics Air Conditioning Oxygen Cylinder x (2) Oxygen Mask x (2) Headset x (2) Parachute x (2) Synthetic Vision EFIS VFR Instrumentation IFR Instrumentation Onboard satellite imagery Transponder ELT XM Data Link Weather Traffic Alert System Three-axis Autopilot All Weather JAXIDA covers GPS and INS VHF/FM radio system HF radio system Satellite Phone Communications relay

$20,763,000 (Price subject to change)

Hourly Lease Rate Schedule* - 3 Talon UAS platforms - 1 Ground Control Station (GCS)

- For capabilities equal to a Predator A UAV at less than half the cost!

*Rates based on 1,200 hours per year per platform

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ShadowAir LTD Airborne ISR Solutions

Toll-Free: 1-888-731-3092 Email: info@ShadowAir.com Website: www.ShadowAir.com