TYPE: Multisensor surveillance lightplane

PROGRAMME: Design (by Bill Whitney) began January 1985. Seabird Aviation Australia began construction January 1988, first flight of first (SB5N) prototype (VH-SBI, c/n 001, with Norton rotary engine) 1 October 1989, and of SB5E second prototype (VH-SBU, c/n 003, with Emdair engine) 11 January 1997 (c/n 002 was structural test airframe); fourth aircraft (c/n 004, VH-ZIG) was SB7L Seeker prototype, making first flight 6 June 1991; Seabird SB7L-235 certified by CASA 12 March 1993; definitive SB7L-360A (VH-OPT; first flight early 1993) has Textron Lycoming O-360 engine for higher performance and received Australian CAA type approval on 24 January 1994 and certification to FAR Pt 23 on 24 March 1999. Operational testing of Seeker included use as an airborne surveillance platform in October 1995 trials by the Australian Army. Components for an initial production batch of five aircraft completed by December 1997. Project then frozen and franchised producer sought, apparently being achieved in July 2000, on signature of agreement with Evektor Aerotechnik. Negotiations were said to be continuing up to early 2003, at which time commercial discussions opened with KADDB in Jordan.
Fifth aircraft (VH-SBO c/n 006) registered June 2003, being first to conform to production certification. On 17 August 2003 KADDB and Seabird Australia revealed joint venture (Seabird Jordan) for assembly of Seekers at Marka. First aircraft, JY-SEE (the former VH-ZIG), shipped from Australia in September 2003 and flew in Jordan on 2 October. Second arrival in Jordan March 2004, was former VH-OPT, joined in July 2004 by VH-SBO. After integration of communications equipment, avionics and surveillance systems by Seabird Jordan, two last mentioned supplied to Iraqi Air Force. First locally built aircraft were due in mid-2006, with manufacture transferring to new plant at Queen Alia International Airport in late 2006.
Australian certification revised on 18 January 2006 to incorporate MTOW increase from 897 kg (1,977 lb) to 925 kg (2,039 lb) and additional fuel capacity, effective from seventh aircraft, previous having 160 litres (42.3 US gallons; 35.2 Imp gallons) gross. In 2006, further improvements under development for Royal Jordanian Air Force Seekers including Dyneema ballistic protection system for fuselage at weight penalty of 5 kg (11 lb); improved cooling system; and replacement of BB177 propeller by Hoffmann unit offering 10 per cent more thrust, increasing climb rate by 91 m (300 ft) per minute and endurance at cruising power from 4 h 30 min to 5 h 40 min. Later improvements intended to include 134 kW (180 hp) Vantage fuel-injected engine and three-blade, constant speed propeller.

CURRENT VERSIONS: SB7L: As described.
Four-seat: Reportedly under development by 2006.

CUSTOMERS: Initial Jordanian order placed mid-2003 for two (2004 and 2005 deliveries for Aqaba Special Economic Zone Authority in maritime surveillance role. Royal Jordanian Air Academy ordered two on 8 October 2003 and holds option on further pair for 2005 delivery. On 10 June 2004, Iraq Air Force purchased two Seekers from KADDB; requirement existed for fleet of 16 in surveillance role but these orders were assigned, instead, to rival JAI and its SAMA 2000. Initial two aircraft, registered YI-101 and YI-102, both from previous Australian production, handed over 29 July 2004 and delivered from Jordan to Basrah, Iraq, by USAF C-130 Hercules on 3 August 2004, as equipment of 1 Air Reconnaissance Squadron.
In October 2004, Paramount Group of South Africa ordered five Seekers, for immediate delivery and placed option on further five to be supplied in 2006: two of initial order for operation by Ghana Air Force, while another to be South African-based demonstrator. Two ordered December 2005 by Jordan Aviation on behalf of two countries “with close ties to Jordan”. Deliveries of new-built Jordanian aircraft began early 2006 with JY-SE1 to South Africa. Demonstrator (N94399) shipped to US in July 2006 for promotion by Seabird Aviation America at Albuquerque.
Jordanian Air Force ordered six Seekers in March 2006.

COSTS: USD269.000 in basic configuration (2006).

DESIGN FEATURES: Braced high-wing monoplane with pod and boom fuselage, extensively glazed cabin and slightly sweptback vertical tail. Ventral and auxiliary fins added early 1993. Primary applications are observation/reconnaissance, offering helicopter-like view from cockpit and good low-speed handling and loiter capabilities: training and agricultural use also foreseen.
Wing section NACA 63₂-215 (modified); wedge tips; twist 3°, incidence 4° at root, 1° at tip; dihedral 2° 30' from roots.

FLYING CONTROLS: Conventional and manual. Rod-actuated slotted ailerons, one-piece horn-balanced elevator (with trim tab) and horn-balanced rudder; three-position (0, 20, 40°) slotted flaps on wing trailing-edge; fixed incidence tailplane. Inboard stall strips; vortex generators on wing upper surface near leading-edge and lower surface forward of ailerons; elevator bias trim.

STRUCTURE: Front fuselage mainly of 4130 chromoly steel tube with Kevlar non-load-bearing skin; aluminium alloy tubular tailboom; wings and tail unit conventional aluminium alloy stressed skin structures, former with single bracing strut and jury strut each side.

LANDING GEAR: Tailwheel type; fixed. Fuselage-mounted spring steel cantilever mainwheel legs with cutaway wheel fairings. Cleveland 8.00-6 mainwheels and fairings on cantilever spring steel legs; fully castoring Scott 8 in tailwheel with oil/nitrogen oleo strut and 210x65 McCreary tyre. Mainwheel tyre pressure 1.38 bar (20 lb/sq in); Cleveland disc brakes. Float gear to be developed.

POWER PLANT: One Textron Lycoming O-360-B2C flat-four engine, derated to 125 kW (168 hp) from 134 kW (180 hp) with lower compression ratio of 7.5:1 for Mogas fuel. Low propeller tip speed for minimal noise; Bishton BB177_ two-blade fixed-pitch wood/composites pusher propeller. Fuel in two 92 litre (24.3 US gallon; 20.2 Imp gallon) integral wing tanks, each with overwing gravity filling point. Total 172 litres (45.4 US gallons; 37.8 Imp gallons) usable. Provision for auxiliary fuel tanks on underwing hardpoints. Oil capacity 7,5 litres (2.0 US gallons; 1.6 Imp gallons).

ACCOMMODATION: Side-by-side seats, adjustable fore and aft, for pilot and co-pilot or observer/passenger in extensively glazed cabin. Dual controls and four-point inertia reel seatbelts standard. Split (upward/downward-hinged) door each side, both removable. Ram air cabin ventilation. Space for 43 kg (95 lb) of baggage aft of seats.

SYSTEMS: 28 V electrical system, with 70 A alternator and Gill 246 battery, for engine start, instruments and lighting.

AVIONICS: Comms: Garmin GMA 340 audio panel. GL 40 VHF, GNS 430/530 com/nav. GTX 327 transponder.
Flight: Garmin GI 106 VOR/GS/LOC.
Mission: Iraqi aircraft have FLIR Systems 8500 surveillance system. Jordanian Air Force aircraft to have L-3 Wescam MX-15 and NVG capability.
Self-defence: Lacroix flare dispensing system under development in 2006, one eight-round unit under each wing.

EQUIPMENT: Hardpoint for 60 kg (132 lb) of external stores beneath each wing. Quick-change photo/survey modules, stretcher or 100 litre (26.4 US gallon; 22.0 Imp gallon) spraytank optional in place of right-hand seat.

DIMENSIONS, EXTERNAL:

• Wing span: 11.07 m (36 ft 4 in)
• Wing chord, constant: 1.22 m (4 ft 0 in)
• Wing aspect ratio: 9.4
• Length overall: 7.01 m (23 ft 0 in)
• Fuselage max width: 1.14 m (3 ft 9 in)
• Height: to fintip: 2.03 m (6 ft 8 in)
• overall, propeller vertical: 2.49 m (8 ft 2 in)
• Tailplane span: 2.90 m (9 ft 6 in)
• Wheel track: 2.03 m (6 ft 8 in)
• Wheelbase: 4.75 m (15 ft 7 in)
• Propeller diameter: 1.77 m (5 ft 9¾ in)
• Cabin doors (two, each): Height: 0.83 m (2 ft 8¾ in)
• Width: 0.98 m (3 ft 2½ in)
• Height to still: 0.98 m (3 ft 2½ in)

DIMENSIONS, INTERNAL:

• Cabin, incl baggage space:
• Length: 2.21 m (7 ft 3 in)
• Max width: 1.12 m (3 ft 8 in)
• Max height: 1.09 m (3 ft 7 in)
• Baggage compartment volume: 0.75 m³ (26.5 cu ft)

AREAS:

• Wings, gross: 13.06 m² (140.6 sq ft)

WEIGHTS AND LOADINGS:

• Basic weight empty: 604 kg (1,332 lb)
• Max fuel weight: 132 kg (292 lb)
• Baggage capacity: 45 kg (99 lb)
• Max T-O and landing weight: 925 kg (2,039 lb)
• Max wing loading: 70.8 kg/m² (14.50 lb/sq ft)
• Max power loading: 7.39 kg/kW (12.14 lb/hp)

PERFORMANCE:

• Never-exceed speed (V_NE): 134 kt (248 km/h; 154 mph) CAS
• Cruising speed at 75% power: 108 kt (200 km/h; 124 mph)
• Minimum patrol speed: 65 kt (120 km/h; 75 mph) CAS
• Stalling speed, flaps down: 53 kt (99 km/h; 61 mph) IAS
• Rate of climb: at S/L: 330 m (1,085 ft)/min
• at FL60: 190 m (650 ft)/min
• Service ceiling: 4,648 m (15,250 ft)
• T-O run: 265 m (870 ft)
• Landing run: 199 m (655 ft)
• Range with reserves:
• at min patrol speed: 423 n miles (783 km; 487 miles)
• at 65% power: 570 n miles (1,056 km; 656 miles)
• Endurance, with reserves:
• at min patrol speed: 6 h 30 min
• at 65% power: 5 h 42 min
• g limits: +3.8/-1.52

The article appears in the following publication:
Jane's All the World's Aircraft 2007-2008. Jane's Information Group Ltd. 2007. ISBN: 0-7106-2792-0