WHITE PAPER RFI: YEMEN LIGHT OBSERVATION AIRCRAFT

COMPANY CONFIDENTIAL

SEABIRD AVIATION AUSTRALIA PTY LTD

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SBR75/12 22 NOVEMBER 2012 1 OF 21 This document and its contents are proprietary to S eabird Aviation an d shall not be communicated to any third parties an d/or reproduced without prior written permission fr om Seabird

Aviation.

Prepared by

Seabird Aviation Australia Pty Ltd PO Box 618, Hervey Bay

Queensland 4655 Australia

WHITE PAPER

RFI: YEMEN LIGHT OBSERVATION

AIRCRAFT



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DOCUMENT APPROVAL

AND

AMENDMENT RECORD

APPROVAL

Originator : Francois van Teijlingen Position : Program Manager

Checked By : Position :

Approved By : Position :

AMENDMENT RECORD

Rev No ECP Number. Changed By Date Release Note No

Change Description

1 N/A N/A 22/11/2012 All First Draft



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TABLE OF CONTENTS

1 PREAMBLE .......................................... ..................................................................... 6

2 CAPABILITY OVERVIEW ............................... ........................................................... 6

3 KEY ADVANTAGES TO THE SAA SB7L-360A3 SEEKER PROPOSA L .................. 7

3.1 OPTIMUM AERIAL PLATFORM ........................... ..................................................................... 7

3.2 SPECIAL FEATURES. ................................. ............................................................................... 7

3.2.1 Field of View ............................................................................................................................ 8

3.2.2 Exemplary flight handling, especially stall handling................................................................. 8

3.2.3 Field of view for EO equipment ................................................................................................ 8

3.2.4 It’s Rugged ............................................................................................................................... 9

3.2.5 Reliable piston engine ............................................................................................................. 9

3.3 VERSATILE SENSOR PLATFORM ......................... .................................................................. 9

3.4 LOGISTIC AND TRAINING SUPPORT ..................... ................................................................. 9

3.5 LOW THRU-LIFE COST ................................ ............................................................................. 9

3.6 SAFETY....................................................................................................................................... 9

4 PROCUREMENT ..................................................................................................... 10

4.1 PLATFORM .......................................... ..................................................................................... 10

4.2 PAYLOAD EQUIPMENT ................................. .......................................................................... 10

4.2.1 EO Surveillance System ........................................................................................................ 11

4.2.2 Video Downlink Transmission Systems ................................................................................. 11

5 DELIVERY ............................................................................................................... 11

5.1 TRAINING SERVICES .............................................................................................................. 11

5.2 MAINTENANCE SERVICES .............................. ....................................................................... 11

5.3 PROGRAM COSTS .................................................................................................................. 12

5.4 AIRCRAFT MODIFICATIONS ............................ ...................................................................... 12

5.5 SUPPLIER ................................................................................................................................. 13

5.5.1 Prime Contractor Role ........................................................................................................... 13

5.5.2 Political and Economic Factors.............................................................................................. 13

5.6 COMPLIANCE TO RFI REQUIREMENTS .................... ........................................................... 14

6 TECHNICAL DESCRIPTION OF AIRCRAFT.................. ......................................... 14

6.1 DESIGN PHILOSOPHY OF THE SB7L-360A3 SEEKER ........ ................................................ 14

6.1.1 Background and General Description. ................................................................................... 14

6.1.2 Design Goals. ........................................................................................................................ 14

6.1.3 Product Optimisation and Development. ............................................................................... 14

6.1.4 Line Drawings. ....................................................................................................................... 15

6.2 TECHNICAL DESCRIPTION. ............................ ....................................................................... 15

6.2.1 Type: ...................................................................................................................................... 15

6.2.2 Wings: .................................................................................................................................... 15

6.2.3 Fuselage: ............................................................................................................................... 15

6.2.4 Empennage:........................................................................................................................... 15

6.2.5 Undercarriage: ....................................................................................................................... 16

6.2.6 Power Plant: ........................................................................................................................... 16

6.2.7 Crew Seating: ........................................................................................................................ 16

6.2.8 Electrical System: .................................................................................................................. 16

6.2.9 Avionics: ................................................................................................................................. 16

6.2.10 Certification. ........................................................................................................................... 17

6.2.11 COTS Payload Equipment ..................................................................................................... 17

6.3 TECHNICAL SPECIFICATION ........................... ...................................................................... 17

6.4 RANGE AND ENDURANCE EXAMPLES ...................... .......................................................... 18

6.4.1 Example 1: ............................................................................................................................. 18

6.4.2 Example 2: ............................................................................................................................. 19

7 TRAINING OF AIRCREW AND MAINTENANCE PERSONNEL ..... ......................... 19

7.1 FLIGHT TRAINING PROVIDER .......................... ..................................................................... 19

7.1 FLIGHT TRAINING COURSES ........................... ..................................................................... 19



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8 SEEKER MAINTENANCE AND SUPPORT .................... ......................................... 20

8.1 SPARES HOLDINGS FOR OPERATIONS IN A DESERT ENVIRONM ENT .......................... 20

9 COMPLIANCE TO RFI REQUIREMENTS CHARACTERISTICS .... ......................... 21

LIST OF FIGURES Figure 1: SB7L-360A Seeker......................................................................................................................... 6

Figure 2: Superb Visibility .............................................................................................................................. 6

Figure 3: Loaded into a C-130H .................................................................................................................... 7

Figure 4: Seeker in flight .............................................................................................................................. 10

Figure 5: SB7L-360A Seeker JY-SEA at Marka Airbase ............................................................................ 13

Figure 6: SB7L-360A Seeker JY-SEA at Marka Airbase ............................................................................ 14

Figure 7: Seeker SB7L-360A3 Three Line View ......................................................................................... 15

Figure 8: Road Operations .......................................................................................................................... 16

Figure 9: SB7L-360A3 Modernised Avionics Suite ..................................................................................... 16

Figure 10: COTS units for payload equipment ............................................................................................ 17

Figure 11: Gimbal Installation ...................................................................................................................... 19

Figure 12: Austere Environment Operations ............................................................................................... 20

Figure 13: Digital Instrumentation ............................................................................................................... 20

LIST OF TABLES Table 1: EO Surveillance System Equipment ............................................................................................. 11

Table 2: Video Transmission Downlink Systems Equipment ...................................................................... 11

Table 3: Indicative Program Costs .............................................................................................................. 12

Table 4: Technical Specification .................................................................................................................. 18



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LIST OF ABBREVIATIONS

A Amps CAS Calibrated Airspeed CASA Civil Aviation Safety Authority CFR Code of Federal Regulations CG Centre of Gravity COTS Commercial Off-the-shelf EO Electro Optical FAA Federal Aviation Administration FAR Federal Aviation Regulations FMS Flight Manual Supplement FOB Free On-board FRP Fibreglass Reinforced Plastics IAS Indicated Airspeed IFR Instrument Flying Rules IMC Instrument Metrological Conditions IMP Imperial ITAR International Traffic in Arm Regulations MTOW Maximum Take-off Weight NACA National Advisory Committee for Aeronautics OEM Original Equipment Manufacturer PC Production Certificate POI Program of Instructions RFI Request for Information SAA Seabird Aviation Australia SAA EO SAA Engineering Order SBR Seabird Report STC Supplemental Type Certificate TC Type Certificate TIS Time in Service US United States USA United States of America V Volts VMC Visual Metrological Conditions VTOL Vertical take-off or landing ISA International Standard Atmosphere AMSL Above Mean Sea Level HD High Definition ISO International Organization for Standardization AKI Anti-Knock Index ASTM American Society for Testing and Materials AUW All Up Weight KCAS Knots Calibrated Airspeed Nm Nautical Mile m Meter ft Feet km Kilometre



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1 PREAMBLE

This White Paper is submitted by Seabird Aviation Australia (SAA) in response to the RFI: Yemen Light Observation Aircraft. It details the supply of non-western hemisphere procured, Yemen delivered new-build, manned aerial surveillance platforms, mission equipment payloads, pilot training packages, flight-line maintenance mechanic training packages, and associated logistics support.

Figure 1: SB7L-360A Seeker

2 CAPABILITY OVERVIEW

The Seabird SB7L-360A3 Seeker represents a cost effective and truly versatile manned platform optimized to provide aerial surveillance and allow for the timely reporting of potential threats, tampering and malfunctions to essential infrastructure elements. In June 2004, the Seeker was selected by the Coalition Provisional Authority for fielding with the Iraqi Air Force for border patrol, infrastructure and security missions. The Seeker has an agile and stealthy profile and so will enable its aircrew to identify potential threats and avoid ground fire and/or threats to low flying aircraft. The aircraft will be new at the time of purchase and will permit its aircrew to maintain day and night aerial surveillance of point and linear targets and report immediately their observations using line-of-sight communications. The inclusion of non and beyond-line-of sight communications are not part of this report, but can be provided, if required.

Figure 2: Superb Visibility



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The Seeker will provide the end-user with a capability to inspect visually and report immediately on disruption of, or threats to, national infrastructure nodes and lines of operation, as well as monitor and report on the status of national borders and coastlines. The EO surveillance and communications systems will enable the aircrew to assist in the rapid repair of key infrastructure assets by providing timely notification to the proper authorities in the event of damage or disruption, including information on the nature of the threat, the ground and the tactical situation, and to security forces tasked in response to an incident. The Seeker will provide a significant contribution to the fight against illegal immigration, smuggling and drug-trafficking. The Seeker’s reliability and maintainability characteristics will support an operational tempo of 8 hours per day, 7 days per week, 365 days per year, with an aircraft availability rate of 90% mission capable for completion of two 4-hour missions per aircraft per day under VMC and sustainment at an 80% mission capable rate for completion of a 4-hour mission under IMC, in the environmental conditions expected in the end-user’s theatre of operations. The Seeker is certificated in Australia to FAR Part-23 standard in the Normal category.

Figure 3: Loaded into a C-130H

3 KEY ADVANTAGES TO THE SAA SB7L-360A3 SEEKER PROPO SAL

3.1 OPTIMUM AERIAL PLATFORM The Seeker is a unique platform optimised for high visibility, long endurance, safe, stable low-level flight, offering the end-user excellent flight and handling characteristics combined with very low vibration levels and audible signature.

3.2 SPECIAL FEATURES. Whilst it might appear that, apart from its pusher configuration, the Seeker is at first sight “just another light aircraft”, such a perception is simplistic. The Seeker is a purpose-designed aerial-work aircraft, optimised for low-level patrol operations. It is less demanding of pilot skill than most single-engine light aircraft. There are good reasons for its unique layout. A deeper look at its detailed features shows how it differs from other light aircraft.



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3.2.1 Field of View The Seeker has a helicopter-like field of view. However, there is more to it than that. A strut-braced high-wing layout allows a high aspect ratio wing to be used, whilst avoiding the necessity for excess structural weight in order to achieve an excellent fatigue life in the low-level role. One can achieve an adequate field of view in turns, with a low-wing layout – but it pays a structural penalty. The Seeker has extraordinarily long fatigue lives for its critical components. The pusher layout allows the pilot to be located well forward of the wing leading edge (unlike a typical single-engine high winged tractor aircraft, in which one sits underneath the wing), whilst retaining the advantages of the high-wing structural layout, and the performance advantage of high aspect ratio that this allows. This means, the pilot can see what he is turning toward, in low-level operations. This is a critical advantage; the average high-wing single-engine light aeroplane is very dangerous in low-level manoeuvring, for this reason. The aircraft has a helicopter-style instrument panel, which does not obstruct the pilot’s forward/downward vision. In this regard, it is remarkable superior to any single-engine light aeroplane having a tractor engine. This means, the point at which the ground ahead, or any obstacles, disappear from the pilot’s field of view, is such that the pilot can manoeuvre around them with no more than the minimum necessary clearance. This is radically different from the situation in any conventional aeroplane, where hazards directly ahead of the aircraft disappear from view quite a long way ahead, resulting in the pilot feeling he needs to take avoiding action that would be unnecessary in a Seeker. This is a critical factor in any low-level application; the pilot must be able to see what’s coming. The pilot needs to be relaxed, not anxious because he can’t see adequately. The Seeker promotes this. Pilots having flown the Seeker aircraft find it a very easy “low adrenalin” aircraft to operate.

3.2.2 Exemplary flight handling, especially stall h andling Any aeroplane that is going to be aggressively manoeuvred at low level – and surveillance applications certainly demands this – must have a very high resistance to inadvertent “departure from controlled flight” – or in more common terms, to flick-rolling into the ground due to an asymmetric stall whilst manoeuvring. In this regard, an aircraft intended for an aerial work application is diametrically opposed to an aircraft that has general flying or flying training as part of its raison d’etre. For such an aircraft, the mission is simply to actively fly the aircraft. For the Seeker, the mission is to fly the mission, and the aircraft is designed to demand no more of the pilot’s concentration than absolutely necessary. The Seeker has extraordinary resistance to inadvertent departure from controlled flight; it exceeds the requirements of its FAR Part-23 design standard greatly, in regard to its insensitivity to any attempt to stall it, even with full crossed controls. This is the consequence of a highly-developed system of control over the lateral spread of separation over the wing, at high angles of attack. Such a system is not normally to be found on typical light aircraft. This system is more pronounced in the Seeker, as it remains effective over the full centre of gravity range. A pusher configuration aircraft, such as the Seeker, is at close to its forward CG when it is at maximum weight, so the effectiveness of the aerodynamic stall-resisting features is at its maximum in the normal operating configuration. By contrast, an aircraft of conventional tractor layout tends to approach its aft CG limit as it is loaded to maximum weight. Such an aircraft exhibits very docile stalling at light weight, because it’s at forward CG under that condition – but it’s another thing altogether if one stalls it with crossed controls at close to maximum weight The Seeker has good control response; it can be manoeuvred aggressively. Most conventional tractor layout aircraft exhibit a rather “doughy” response, by comparison. However, the control system weighting is rather different to that of a typical light aircraft; it is designed to resist overloading of the structure in moments of excitement. If the pilot over controls, he will not damage the airframe, or exceed the flight envelope in so doing.

3.2.3 Field of view for EO equipment In aircraft of a conventional tractor layout, the EO payload equipment is usually mounted under the belly at mid fuselage. In such a position, the equipment is prone to hot exhaust gas and possibly oil contamination flowing over it. In the Seeker layout, the engine does not deluge thermal imaging equipment with a flood of hot air or exhaust fumes or drops of oil, no matter how hard you sideslip it. It



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can’t, because the engine is behind. You won’t get an image of the nosewheel, because there isn’t one. There won’t be any interference from the propeller, because it’s above and behind.

3.2.4 It’s Rugged The Seeker is very solidly built. This is reflected by the critical component retirement values. It has surprisingly good crash survivability, and has proven itself to be “soldier-resistant”. The tail boom may appear slender, but it has been demonstrated to meet fail-safe criteria, and it has heavy-gauge skins. The empennage also has fail-safe design features. Both static strength and flutter tests were conducted with one simulated failed attachment bolt, for both the forward tailplane attachment and the empennage truss attachment to the tail boom. The main undercarriage is by steel spring-leg, and has been demonstrated to pass the ultimate FAR Part-23 drop-test without permanent set. It is not highly heat-treated, so they have a considerably lower crack-propagation rate. The structure is 6061-T6 aluminium alloy, which has far superior corrosion-resistance to the clad 2024 used in almost all other light aircraft.

3.2.5 Reliable piston engine The Seeker uses a Lycoming I0-390-A1B6 engine. It’s a direct-drive engine, and it drives a (FAR Part-35 certificated) fixed-pitch wood propeller via an increased-diameter eight-bolt flange; the installation has special provision to maintain clamping pressure on the propeller without special maintenance requirements. This propeller attachment has been demonstrated to be able to withstand the change in humidity from Hervey Bay to the Iraq desert at 500C, without needing any adjustment. The wood propeller is immune to fatigue-cracking, and its location protects it from foreign-object damage due to gravel (and from people walking into it). Wood propellers are, in principle, on-condition items and may be regarded as a consumable; however the Seeker propellers have proven quite long-lived. The result is a powerplant package that is simple and extremely reliable. In patrol mode, the engine operates at around 55% power – and it runs cool. It has, of course, dual magneto ignition and redundant fuel supply pumps. These features result in as reliable a single-engine system as can be achieved; the resultant level of safety is arguably superior to any twin-engine layout. One could hardly do better for low-level operations.

3.3 VERSATILE SENSOR PLATFORM The lack of slip stream buffet and vibration “prop-wash” enables “doors-off” operation ideally suited for photography, visual observation and electro-optic surveillance, with high precision sensors capable of being mounted from both wing hard-points as well as from an unobstructed under-fuselage installation.

3.4 LOGISTIC AND TRAINING SUPPORT The Seekers will be built in, supplied and supported from Australia. Training of aircrew and maintenance personnel will be conducted Sana’a or with existing regional training providers , with full logistic support available from Australia for depot level maintenance, repair and upgrade of platforms.

3.5 LOW THRU-LIFE COST The Seeker solution is highly cost-effective. The platform acquisition price and the direct operating and maintenance costs are extremely low.

3.6 SAFETY In the event of a powerplant failure during low-level, low speed flight, the Seeker can immediately initiate a glide to safety, unlike a helicopter which is unlikely to be able to transition safely into autorotation. The Seeker airframe was designed for continuous survey operations at low levels and offers a very high



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fatigue life. The Seeker has a very high resistance to any inadvertent departure from controlled flight when maneuvered aggressively at low speed and altitude.

4 PROCUREMENT

Subject to a mutually acceptable contract compliant with our standard terms and conditions of supply, SAA will offer the following:

Figure 4: Seeker in flight

4.1 PLATFORM SAA will be able to supply 25 new-build SB7L-360A3 IFR capable Seeker aircraft, as detailed in paragraph 6.

4.2 PAYLOAD EQUIPMENT The aircraft can be delivered in 2 buyer selectable configurations. It can be delivered as a turn-key solution, complete with payload systems supplied and installed, or delivered as “fitted-for-but-not-with” payload equipment, ready to accept the mounting of the buyer furnished payload units. As the RFI does not stipulate any performance requirements for the selection of payload equipment, it is not possible to propose a final equipment selection. The aircraft is suitable to accept the installation of payload equipment from a diverse range of suppliers. As the Type Certificate holder as well as the OEM of the aircraft, we have the engineering freedom to develop installations to integrate from the higher cost high end para-military range of payloads, down to the lower priced commercial range of equipment. For the purpose of completing this report, SAA will propose a range of equipment, specifying only parameters such as COTS, ITAR restrictions and performance trade-offs.



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4.2.1 EO Surveillance System The aircraft will be delivered pre-equipped to readily install a pre-selected Multi-mission, multi-sensor airborne gimbal system suitable for surveillance, reconnaissance, search and rescue, counter drug, homeland security, and law enforcement missions. Typical EO surveillance system equipment pre-selections possible are as follows:

Supplier Model Heritage Restrictions Performance Wescam MX-10 Para-Military ITAR High FLIR StarSapphire Para-Military ITAR High FLIR Talon Para-Military ITAR Medium PolyTech UltraForce Commercial Non-ITAR Medium CloudCap TASE-400 Commercial Non-ITAR Medium

Table 1: EO Surveillance System Equipment

4.2.2 Video Downlink Transmission Systems The aircraft will be delivered pre-equipped to readily install a pre-selected video monitoring and downlink system that can provide reliable, encrypted video transmission between the aircraft, vehicles, ships, fixed/portable receive/relay sites and man packs. The system will have a flexible open architecture that can grow as the requirements need. Typical video transmission downlink systems equipment pre-selections possible are as follows:

Supplier Model Technology Restrictions Performance Harris RF-7800W Radio ITAR High BMS HC-4 Microwave ITAR High Silvus SC-3500 Radio Non-ITAR High

Table 2: Video Transmission Downlink Systems Equipment

5 DELIVERY

Acceptance will be ex-works SAA premises, Hervey Bay Airport, Australia, and delivery after acceptance will be per 40ft ISO container shipment, Brisbane port to the Hodeidah container terminal in Yemen. From there, the containers will be road transported to the nearest military facility with a suitable prepared surface to act as a runway, for assembly.

5.1 TRAINING SERVICES Until an alternate facility is established, SAA would offer to conduct in Australia a comprehensive POI compliant to FAA standards, structured appropriately to the experience and competence of the end-user’s aircrew, surveillance systems operators and maintenance personnel, to include pre-flight screening, pilot aircraft qualification courses and special to role training. Course content and duration will be developed based upon experience gained in the training of end-user pilots and ground crew during the contract negotiations for the Seeker aircraft.

5.2 MAINTENANCE SERVICES Until an alternate facility is established, SAA would offer the supply from Australia of full logistic support for the Seeker aircraft appropriate to enable the desired operational tempo, including the supply of engines, main assemblies and spares. Depot level servicing and overhaul would be sub-contracted to a regional facility. Pricing will be based upon the requirements set during contract negotiations, the concept of operations and the maintenance philosophy adopted by the end-user.



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5.3 PROGRAM COSTS Indicative programme acquisition and support costs are detailed below. Indicative training costs are for training in Hervey Bay, in-country training and support will be costed after receiving firm requirements. Firm, fixed pricing will be subject to contracted terms and conditions.

INDICATIVE ACQUISITION, TRAINING AND SUPPORT COSTS Batch 1 Supply of five (5) SB7L-360A3 aerial surveillance platforms at

AU$801,000 each, FOB Hervey Bay Airport, Hervey Bay, Australia. AU$4,005,000

Batch 2 Supply of five (5) SB7L-360A3 aerial surveillance platforms at AU$710,000 each, FOB Hervey Bay Airport, Hervey Bay, Australia.

AU$3,550,000


AU$3,325,000


AU$3,085,000


AU$2,930,000

EO Payload Installation

Supply of five (5) EO Payload installation services at AU$50,000 each, Hervey Bay Airport, Hervey Bay, Australia.

AU$250,000

Aircraft Downlink Payload Installation

Supply of five (5) Downlink Payload installation services at AU$50,000 each, Hervey Bay Airport, Hervey Bay, Australia.

AU$250,000

Pilot Training

Supply of 5 (five) Pilot Aircraft Familiarization Flight Training Packages with 10 hours dual instruction per pilot at AU$40,000 each, including accommodation in Hervey Bay, but not including airfare, meals, incidentals and per diem.

AU$200,000

Observer Payload Training

Supply of 5 (five) Observer and Payload Training Packages at AU$30,000 each, including accommodation in Hervey Bay, but not including airfare, meals, incidentals and per diem.

AU$150,000

Maintainer Training

Supply of five (5) Maintenance Mechanic Training Packages at AU$30,000 each, including accommodation in Hervey Bay, but not including airfare, meals, incidentals and per diem.

AU$150,000

Spares Supply of Generic Spares Package, including “Initial Readiness Pack”, at AU$275,000 per package.

AU$275,000

Technical Support

Supply of in-country Technical Support on a call-out basis, at AU$10,000 per visit of 5 days

AU$10,000

EO Payload Optional supply of five (5) end-user selected EO Payloads, FOB Hervey Bay Airport, Hervey Bay, Australia.

TBD

Aircraft Downlink Payload

Optional supply of five (5) end-user selected Imagery Downlink Payloads, FOB Hervey Bay Airport, Hervey Bay, Australia.

TBD

Table 3: Indicative Program Costs

Notes:

• Aircraft can be ordered in batches. • Prices do not include delivery to Yemen. • Payloads installation provisioning will be installed as part of aircraft manufacturing. • Aircraft are SB7L-360A3, as per specification sheet. • Training is one week per training package, 5 students per package, presented at the Seabird

Aviation facility in Hervey Bay, Australia.

5.4 AIRCRAFT MODIFICATIONS SAA are currently working with the engine OEM, Lycoming, to make available a version of the IO-390-A1B6 engine used in the Seeker that runs on Mogas, i.e. 93AKI non-ethanol blended unleaded automotive fuels that conform to ASTM D4814 or Euronorm 228 specifications.



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We are also working with SAFRAN to offer their new SMA SR305-230E diesel engine as an option. The engine is FAA certificated, and installed as an OEM fit into production aircraft. This would enable the aircraft to run on Jet-A, Jet A1, TS-1 or RP-3 fuels. They are usually readily available, and do not pose the high flammability issues that Avgas or pump gas poses. Should any improvements need to be incorporated into the aircraft, SAA will work with the buyer to:

• Develop end-user avionics or communications requirements. • Develop mounting systems for alternate payloads, surveillance systems and data links. • Develop armour and protection systems for the Seeker. • Develop alternate engine systems.

Any modifications required to the aircraft shall be approved by TC Amendment, STC, SAA EO and FMS, as directed and guided by the Australian CASA regulations, a mirror of the FAA CFR-14 Part-23 regulations.

5.5 SUPPLIER SAA was established in Australia, in 1983. As the TC and PC holder of the entire Seeker range of aircraft, SAA is capable to market, manufacture, modify, supply and support this unique type of airborne platform that is fully coherent and compliant with the requirements outlined in the RFI. Although manufacturing licenses have been issued to other international entities, SAA currently is the only company with an up to date fully compliant and functioning production facility of Seeker aircraft.

5.5.1 Prime Contractor Role SAA will assume all responsibilities and duties as the program prime contractor, so as to coordinate and manage on behalf of the buyer, all aspects of the program regarding delivery of platforms, payload equipment installation, training and logistic support. We will provide a “one stop shop” service, working with the buyer and end-user to ensure maximum cost-effectiveness and value for money. “One focus, one point of contact, one accountability”.

Figure 5: SB7L-360A Seeker JY-SEA at Marka Airbase

5.5.2 Political and Economic Factors Over 80% of the bill of material for the SB7L-360A3 Seeker aircraft will be sourced from the USA, including the engine, avionics and other FAR Part-21 compliant components, as well as the surveillance and communications systems. The remaining material will be sourced from within Australia. The SB7L-360A3 Seeker will be manufactured and assembled by SAA, utilising our facilities in Hervey bay, Australia. A sale of the Seeker aircraft to Yemen will have a positive economic impact upon both the USA and Australia.



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5.6 COMPLIANCE TO RFI REQUIREMENTS The SB7L-360A Seeker’s rugged design, ease of production, development potential, hi-tech role equipment fit, and low cost of ownership, makes it a cost effective airborne surveillance platform solution. We offer therefore in the SB7L-360A3 Seeker, an affordable and highly appropriate solution to address the requirements as specified in the RFI.

6 TECHNICAL DESCRIPTION OF AIRCRAFT

6.1 DESIGN PHILOSOPHY OF THE SB7L-360A3 SEEKER

6.1.1 Background and General Description. The SB7L-360A3 Seeker is a two-seat observation and surveillance aircraft with excellent visibility. It was developed as a highly cost-effective alternative for many low-level observation tasks currently being carried out today by helicopters for which VTOL is not mission essential. In general terms, both the acquisition and running costs of a Seeker will be typically a third that of a comparable twin-seat helicopter, so permitting the affordable and cost-effective conduct of missions which are ‘Low, Slow and Often’.

6.1.2 Design Goals. The Seekers typical operating environment will be at low-altitude, flying close to obstacles and in turbulence, for protracted flight duration. Consequently, the design goals include outstanding crew visibility and safety, crisp manoeuvrability with stability at low speeds, benign and forgiving stall behaviour, low pilot handling fatigue, crew comfort and long endurance. The aircraft has ample power to provide additional safety at low levels and has good turbulence riding capabilities, which along with a lack of propeller slipstream gives high crew comfort levels. The welded steel fuselage gives excellent crew protection and the sturdy nature of the structure will ensure long aircraft life in adverse operating conditions.

Figure 6: SB7L-360A Seeker JY-SEA at Marka Airbase

6.1.3 Product Optimisation and Development. SAA maintains a policy of product improvement and as a result, development activity will be maintained in support of the Seeker fleet. As an example, Seabird Aviation Australia has completed further engineering and flight tests to address possible risks resulting from engine over-heating in the hot and high conditions expected in the Yemeni operating environment.



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6.1.4 Line Drawings.

Figure 7: Seeker SB7L-360A3 Three Line View

6.2 TECHNICAL DESCRIPTION.

6.2.1 Type: The Seeker is a purpose designed two-seat observation and surveillance aircraft.

6.2.2 Wings: The aircraft is a strut braced high-wing monoplane, with a modified NACA 632-215 constant chord aerofoil section. The wing dihedral is 2°, the inci dence angle is 4° at root, with a constant twist to 1° at the tip. There is no sweepback. The construction is an all-metal skinned, aluminium alloy structure, with top-hinged ailerons and mechanical slotted flaps. The wing mounting is supported by a single bracing and small jury strut on each side.

6.2.3 Fuselage: The fuselage consists of a pod and boom structure. The forward pod is a 4130 chrome molybdenum steel tubular fuselage, affording maximum crew protection. The non-load bearing forward fuselage skin consists of FRP composite. The tailboom is an aluminium alloy semi-monocoque boom.structure. Access is by horizontally hinged removable doors and the transparencies are polycarbonate windows.

6.2.4 Empennage: The vertical stabilizer consists of a swept fin (with dorsal fin) and balanced rudder. The horizontal stabilizer consists of a non-swept fixed incidence tailplane, with a one-piece horn balanced elevator. The construction of the empennage is similar to that of the wings.



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Figure 8: Road Operations

6.2.5 Undercarriage: The Seeker has a taildragger undercarriage configuration. The main landing gear consists of fixed, cantilever spring steel legs, fitted with Cleveland 8.00-6 mainwheels. The tail wheel is a Scott 8-inch tailwheel with an oleo strut.

6.2.6 Power Plant: The aircraft powerplant is a 210hp Lycoming IO-390-A1B6, driving a Bishton BB177 wooden 2-blade fixed pitch propeller. Fuel is stored in two integral wing tanks, with a combined usable capacity of 180 litres (48 US gallons, 40 Imp gallons). Filling points are by overwing flush fuel caps each tank.

6.2.7 Crew Seating: The seating configuration is two side-by-side seats, adjustable fore and aft, offering an enclosed and extensively glazed cabin, including chin and overhead transparencies, for pilot and observer/passenger. The right hand seat and/or controls are removable. The aircraft can be flown with both top opening doors removed. There is space for miscellaneous baggage aft of the seats.

6.2.8 Electrical System: The aircraft electrical system consists of two independent electrical systems. Electrical power generation is by twin 28V, 100A alternators.

Figure 9: SB7L-360A3 Modernised Avionics Suite

6.2.9 Avionics: The avionics system is state-of-the-art, featuring large sunlight viewable electronic (digital) instrument color displays.



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6.2.10 Certification. The Seeker aircraft delivered to Yemen will be fully IFR certified to FAA Part-23 standard.

6.2.11 COTS Payload Equipment SAA make use of as many as possible COTS electronic equipment building blocks, when compiling a sensor suite. Typically below, a fully sunlight viewable Panasonic CF-31 ToughBook computer serves as the removable operator MMI and viewer, while a Panasonic AG-HMR10P Solid State HD recorder is used to record the data imagery in 1080 High Definition.

Figure 10: COTS units for payload equipment

6.3 TECHNICAL SPECIFICATION

External Dimensions Wing Span 11.07 m 36 ft 4 in Overall Length 7.00 m 23 ft 0 in Height of Vertical Stabiliser 2.03 m 6 ft 7 in Wheelbase 2.04 m 6 ft 8 in Internal Dimensions Cabin Width 1.12 m 3 ft 8 in Doors - Long Axis 1.07 m 3 ft 6 in Weights Maximum T/O Mass 974 kg 2147 lb Speeds Min Patrol Speed (CAS) 121 km/h 65 kts Cruise 75% Power (CAS) 208 km/h 112 kts Never Exceed (CAS) 239 km/h 129 kts Stall (40° Flap)(IAS) 98 km/h 53 kts Climb Climb Rate SL: ISA 5m/s 990ft/min Ceiling AMSL 4650 m 15,250 ft Fuel Capacity Usable 184 litres 48.8 US gal



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Endurance (inc. reserve) Min. Patrol Speed 65 kts 7 h 15 min Cruise (65% Power) 90 kts 4 h 30 min Range Patrol Speed (65 kts) 880 km 476 nm Cruise (65% Power) 869 km 470 nm Fuel Flow Patrol Speed (65 kts) 22 l/h 5.80 US gal/h Cruise (65% Power) 34 l/h 9.00 US gal/h Take-off/Landing run at AUW (sea Level ISA)

T-O run 264 m 870 ft Landing run 198 m 654 ft Stressing Limit Load Factor +3.8 -1.52 Certification Certification Basis FAR 23 up to and including Amdt 51

Note: Specifications can change without notice

Table 4: Technical Specification

6.4 RANGE AND ENDURANCE EXAMPLES The following typical examples are based on the following aircraft configuration:

• Pilot (77 kg) • Crew (77 kg) • Baggage (10 kg) • Full Fuel (180 litres)

Calculations include allowances for taxi, climb to altitude, descent and 45 minutes reserve.

6.4.1 Example 1: Cruise at 5000 feet (1500 m), 65 % power, 104 KCAS.

5000 ft.1500 m.

TAXI

CLIMB6 nm5 mins.

CRUISE AT 65 % POWER469 nm270 mins.

DESCENT

RESERVE78 nm45 mins.

Range = 469 nm (869 km) Endurance = 270 mins.



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6.4.2 Example 2: Loiter at 500 feet (150 m), 20° flap, 30 % power, 6 5 KCAS

500 ft.150 m.

TAXI

CLIMB / DESCENT1 nm1 min.

LOITER (20° FLAP) AT 30 % POWER475 nm438 mins.

RESERVE49 nm45 mins.

Range = 475 nm (880 km) Endurance = 438 mins.

7 TRAINING OF AIRCREW AND MAINTENANCE PERSONNEL

7.1 FLIGHT TRAINING PROVIDER SAA will through a partnership with Horizon Flight Academy, based in Al-Ain, United Arab Emirates, provide the services of flight screening and training for aircrew and maintainers. The advantage will be the ability to teach the Yemini crew in their native language of Arabian Peninsula Arabic.

7.1 FLIGHT TRAINING COURSES Flying training can range from Private Pilot’s Licence, Commercial Pilots Licence, conversion training onto Seeker aircraft and special to role training on the surveillance system. Maintainer training can be for maintenance and support of the airframe, avionics and power plant.

Figure 11: Gimbal Installation



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8 SEEKER MAINTENANCE AND SUPPORT

8.1 SPARES HOLDINGS FOR OPERATIONS IN A DESERT ENVI RONMENT Although of unconventional appearance, Seeker's structure and systems are simple and easily maintained in the field. Maximum ease of maintainability and inspectability were two of the key Seeker design aims. Any competent workshop familiar with Cessna, etc., type aircraft would be able to carry out work on the Seeker. There is no mandatory component replacement until 13,000 hours (wing strut bolts), and 6 years for the boom attach bolts.

Figure 12: Austere Environment Operations

The Textron-Lycoming IO-390-A1B6 is a low-stressed engine that has proven extremely reliable. World-wide product support from Lycoming is available as required. Other consumable items such as filters, wheels, brakes, tires, hoses, and hardware, are common off-the-shelf items used widely in general aviation aircraft world-wide. Instruments are also common and familiar items, important flight instrumentation and avionics are Garmin. As well as the airframe’s alloy sheet and tubular steel, all these items are US sourced. SAA will supply a comprehensive spares and ground support package, and provide in-country field service support. All spare parts are readily available direct from SAA, with off-the–shelf rotables being commonly available from aircraft maintenance organizations.

Figure 13: Digital Instrumentation



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9 COMPLIANCE TO RFI REQUIREMENTS CHARACTERISTICS

The SB7L-360A3 Seeker is ideally suited to satisfy the requirements characteristics as defined in solicitation N68335-13-R-0091.

Requirement Characteristic Compliance

Deliver 25 aircraft directly to Yemen Compliant

Provide in-country Airworthiness, Pilot/Maintainer Training Compliant

Provide Field Service Representative Compliant

Provide initial allocation of Spare Parts Compliant

Provide Ground Support Equipment Compliant

COTS Design Compliant

Piston Engine Compliant

Pusher Prop Compliant

High Wing Compliant

Tail Dragger Compliant

FAA Certified Partly Compliant

With EO/IR Sensors and Downlink Compliant

2-seat side by side configuration Compliant

Single pilot IFR capable Compliant

Austere operational environment capability Compliant

Max Cruise 108kt Compliant

Normal Cruise 100kt Compliant

Minimum Patrol Speed 65kt Compliant

Initial Climb 1085ft/min Compliant

Service Ceiling 15,250ft Compliant

Take-off Run 870ft Compliant

Landing Roll 655ft Compliant

Range with reserves at normal cruise 570nm Compliant

Endurance with reserves at minimum patrol speed 6hr 30min Compliant

Delivery schedule 25 aircraft in <24 months Compliant

WHITE PAPER RFI: YEMEN LIGHT OBSERVATION AIRCRAFT

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