Evolved from the Vidervol-Szaraz VS-1, the Szaraz SD-1A Daphne is a homebuilt aircraft that was designed by Art Szaraz and Bernie Darmstadt for efficiency competitions.
The Daphne is a two place side-by-side configuration strut-braced high-wing, conventional landing gear equipped homebuilt. The fuselage uses welded steel tubing with aircraft fabric covering. The wings are wood, with one-piece plywood ribs. Both ailerons and flaperons have been installed on the design.
The first three examples were built on the same jigs at Art Szaraz’s workshop. At least fifteen were built. At least 26 were under construction by Jan 1970.
Known examples: N960Z (c/n 1) built by Arpad Szaraz, ff: 1963 N962Z built by Nick Stanich, ff: 2/28/65 N961Z built by B D Darmstadt, ff: 6/18/65
SD-1A Daphne Engine: 1 × Continental C-85-12F, 85 hp (63 kW) Propeller: 2-blade Wingspan: 26 ft (7.9 m) Wing area: 130 sq ft (12 sq.m) Airfoil: NACA 4412 Length: 19 ft 7 in (5.97 m) Empty weight: 820 lb (372 kg) Gross weight: 1,300 lb (590 kg) Maximum speed: 130 kn; 241 km/h (150 mph) Cruise speed: 104 kn; 193 km/h (120 mph) Stall speed: 35 kn; 64 km/h (40 mph) Never exceed speed: 148 kn; 274 km/h (170 mph) Service ceiling: 14,500 ft (4,400 m) Rate of climb: 1,000 ft/min (5.1 m/s) Capacity: 2
An evolution of the Catto CA 15 by Craig Catto, Dominique Loup built all the pre-series equipment of Swiss Aerolight Nimbus 001 in 1985 and John Bonvin built all the other pre-series equipment. For advanced pilots, the only two European copies were ordered by Dominique Loup and John Bonvin.
John Bonvin made structural modifications in the static distribution of constraints. A better distribution of the loads was obtained by redrawing the rear spar and the stabilizers of the trapezium.
Bonvin developed the Nimbus 2. The geometry has been completely redesigned to get + 8g’s in positive without permanent deformation and without breaking. The structure is to 11g ultimate.
Nimbus 2
Development was abandoned.
Nimbus Wing area: 15 m² Wing span: 10.20 m Aspect ratio: 7 Hang glider weight: 40 kg Minimum speed: 28 km/h
The Tango features a composite fuselage with a large cockpit and large doors. The wooden wings are strut braced. The pilot is almost lying down, with a Cessna style steering column.
BTA 4 Tango Empty weight: 276 kg Wing span: 10.2 m Wing area: 12.9 sq.m Fuel capacity: 75 lt Certification: vVz Engine: Rotax 912, 80 hp MAUW: 450 kg Seats: 2 Max speed: 220 kph Cruise speed: 160 kph Minimum speed: 65 kph Climb rate: 6 m/s Fuel consumption: 10 lt/hr Price (1998): 73,500 DM
The GFRP Swift, which first flew in 1991, was designed as a sailplane for contest aerobatics (about 10 g). It has optional wingtip extensions which increase the span to 15.0 m / 49.2 ft. The main wheel is retractable. Approach control is by top surface Schempp-Hirth type airbrakes. Moving tail surfaces are fabric covered.
The SX300 was originally designed by Ed Swearingen in San Antonio, TX, as a two place, all metal, single engine low wing monoplane with fully enclosed retractable landing gear. First flown on 11 July 1984, the aircraft was marketed as a kit from 1984 to 1989.
By the end of 1989 approximately 80 kits had been sold, although there were only 48 sets of landing gear, which were built by the landing gear vendor, Airight Inc. in Wichita, KS.
The basic concept was to set new standards for Homebuilt or Amateur Built Aircraft as a dependable, fast mode of transportation; using all metal construction and proven techniques to provide an airframe that was equal to advanced jet aircraft. Fundamentally this was accomplished, however, the complexity and the labor intensive kit proved to be too challenging for the Homebuilt Market. The kit was high quality but the aircraft was never kit-proofed by the factory, so there were numerous glitches from the beginning. If the aircraft had been offered as a “fast build kit” it may well have survived.
In 1994, Jim Ryan, the owner of Airight, acquired the SX300 tooling, aircraft kit components and production/manufacturing rights (except military application). Jim planned to continue supporting the existing builders and to supply kits, fast build kits and possibly a fixed gear version which he called the SX200. Unfortunately Jim died in early 1996 before he could implement his new program.
The inventory of SX300 parts were bought by Bill Johns and now reside with Doug Poli at his facility in Ft. Worth, TX.
Engine: Lycoming IO-540-L1C-5, 300 hp Propeller: Hartzell Constant Speed 3-blade, 74 in. diameter Overall Length: 21 ft. 1.5 in. Overall Height: 7 ft. 6.5 in. Wing Span: 24 ft. 4.5 in. Wing Area: 70.73 sq. ft. Aspect Ratio: 8.4 Structural Cabin Width Inside: 41 in. Load Factor: 6G + 3G – Cruise Speed @ 75% Power, 8000 ft: 240 Kts. Stall Speed @ Gross Wt. (2400lbs.) flaps down: 75 Kts. Rate of Climb @ Gross Wt. Sea Level: 2400 ft./min Range (66 gal): 900 miles. Empty Weight: 1600 lbs. Baggage Capacity: 70 lbs. Power Loading: 8 lbs./hp Vne: 280 KIAS
The prototype (N6Y) of this compact trainer design made its first flight at San Antonio, Texas, on 31 May 1989. Powered by a 420 shp (313 kW) Allison 250-B17D turbo-prop, the SA-32T has been developed by Swearingen in conjunction with Jaffe Aircraft Corp. Despite its relatively small size, the SA-32T incorporates a retractable undercarriage, a limited amount of composite material in the airframe and a NASA-designed laminar-flow wing. Jaffe Aircraft abandoned the program.
N6Y is still flying. Purchased from Jaffe in 2002. My wingtip design lower the full-flaps stall to 68 kts. Trues out a 280 kts. William B Acheff, April 2020
Swearingen announced the official formation of Sino-Swearingen to complete development and construct the eight place SJ30 business jet. The company is a joint venture between Swearingen and Sino Aerospace Investment Corporation, a grouping of Taiwanese investors, including Taiwan Aerospace Corporation. With the formation of the new company construction will start on a new 18, 600sq.m (200,000 sq ft) assembly plant in Martinsburg, West Virginia (major components will be manufactured in Taiwan and shipped to the US), while the original SJ30 prototype has returned to full test and certification flying duties.
Originally the SA-30, renamed SJ30, first flew on 13 February 1991.
Sino Swearingen Aircraft Corporation has flown their SJ30-2 business jet (first flown 1996) at an altitude of 49,000 ft. This cruise level of the aircraft exceeds that of most of the business twinjets or commercial airliners in production. The SJ30-2 is a seven-place twin jet aircraft with an IFR range of 2,500 nm. The aircraft will cruise at speeds in excess of Mach 0.80 and will maintain a “sea level cabin” to 41,000 ft (owing to its pressurization differ¬ential being 12.0 psi).
SA-30 / SJ30 Engines: 2 x 1900 lb Williams Intl FJ44 turbofan Wingspan: 36’4″ Length: 42’4″ Useful load: 4150 lb Max speed: 541 mph Cruise: 512 mph Range: 2390 mi Ceiling: 41,000′ Seats: 8
SJ30-2 Engines: (2) FJ44-2A Williams Rolls Overall Length: 46.80 ft (14.26 m) Overall Height: 14.19 ft (4.33 m) Wing: Span: 42.33 ft (12.90 m) Sweep (@ 1/4 Chord): 30.1 deg Dihedral: 2.3 deg Area: 190.69 sq ft (17.71 sq m) Aspect Ratio: 9.40 Mean Aerodynamic Chord (MAC): 5.12 ft (1.56 m) High Speed Cruise: Mach 0.83 / 560 MPH / 486 KTAS / 901 Km/H Long Range Cruise 2,875 sm (2500 nm): 0.76Mach / 502MPH / 436KTAS / 807Km/H Stall Speed: 91 KCAS FAA Take-Off Balanced Field Length GW: 3,939 ft (1200 m) FAA Landing Distance: 2,941 ft (896 m) Seats: Seven Place w/Pilot Take-Off Thrust: 4,600 lbs total (2,300 lbs ea) Pressurization: 12.0 psi Max. Certified Altitude: 49,000 ft Cabin Altitude is Sea Level Up To: 41,000 ft Mmo Above 29,500 ft: Mach 0.83 Vmo Up To 29,500 ft: 320 KCAS (593 km/h) Vref: 105 KCAS Speed Brake Operation: No Speed Limit Max. Ramp Wt: 14,050 lbs (6373 kgs) Max. Take-Off Wt: 13,950 lbs (6327 kgs) Max. Landing Wt: 12,725 lbs (5772 kgs) Max. Zero Fuel Wt: 10,500 lbs (4763 kgs) Basic Operating Wt: 8,650 lbs (3923 kgs) Max. Fuel Quantity: 4,850 lbs (2199 kgs) Max. Baggage Compartment Wt: 500 lbs (227 kgs) Horizontal Tail: Span: 14.56 ft (4.44 m) Sweep (@ 1/4 Chord): 33 deg Dihedral: 0 deg Area: 36.72 sq ft (3.41 sq m) Aspect Ratio: 5.77 Mean Aerodynamic Chord (MAC): 2.72 ft (0.83 m) Vertical Tail: Span: 7.21 ft (2.20 m) Sweep (@ 1/4 Chord): 55.5 deg Dihedral: 46.80 sq ft (4.35 sq m) Area: 11.56 sq ft (1.07 sq m) Aspect Ratio: 1.11 Mean Aerodynamic Chord (MAC): 7.10 ft (2.17 m) Ventral Fin: Total Area: 11.56 sq ft (1.07 sq m) Ventral Rudder Area: 1.95 sq ft (0.18 sq m) Landing Gear: Width Between Main Gear: 6.85 ft (2.09 m) Wheelbase: 18.84 ft (5.74 m) Tire Size: 16 in x 4.4 in
The evolution of the Merlin started in the early 1960s, with an air stair door and engine conversion for the Beech Twin Bonanza. Swearingen was also fitting bigger engines on Queen Airs, and the first Merlin strongly reflects his background with these two Beech conversions. The Merlins I and II consisted of a new fuselage mounted on modified Queen Air or Twin Bonanza wings and landing gear. The Merlin I was to be a pressurized piston powered airplane, the Merlin II a turboprop. The model I was never produced because Swearingen couldn’t find a piston engine that satisfied him. The II made its debut with Pratt & Whitney PT6 turboprops in 1969, but by the time it reached the IIB version, it was powered by Garrett AiResearch TPE 331s with a shaft horsepower of 665 each, and it had a takeoff weight of 10,000 pounds.
The next step had to be the development of a new wing. There just weren’t that many Twin Bonanzas and Queen Airs out there, waiting to donate their wings to a Merlin. There may also have been some reluctance on the part of prospective buyers to consider a new airplane with used wings. Thus came the Merlins III and IV.
Dramatically improved performance, extended payload-range capability and a host of safety features transformed the Metro II into the Metro III. Providing the the improved performance is a 10 foot extension to the earlier model’s wing, combined with an uprating of the twin Garrett AiResearch TPE turbo-props from 840 SHP to 1,100 SHP. Water methanol injection is standard for hot and high take-offs, as well as being available for power augmentation during normal take-offs. Rated at 1,100 SHP wet, 1,000 SHP dry, power is now absorbed by new four-bladed Dowty Rotol props. Turning at 1,590 rpm (compared with 2,000 rpm on the Metro II), the interior noise level has been dramatically reduced to about half that of the previous model about a 6 Db drop.
Fairchild was building the Merlin’s wings under contract to Swearingen when the recession of 1970 squeezed the airplane business. Fairchild wound up with both an interest in the company and an in¬terest in keeping the airplanes going. The Merlin III was under development at about the time the small jets were first coming to market; to be a viable offering, it had to offer something the jets lacked. This had to be range, for there was no way a turboprop could match the jets’ speed. The first Merlin III had AiResearch 840 shp engines and a fuel capacity of 662 USG. The maximum range at economy cruise, with a 45 minute reserve, was 2,353 nautical.
Other changes to the Metro II include a cleaning up of the engine nacelle and improved fire containment. The gear doors now close when the wheels are lowered, which not only improves the single-engine gear-down performance, but also assists in lowering the Vmca to 5 knots slower than the series II aircraft. Cowlings are stainless steel for improved fire resistance, while all flammable fluid lines are physically isolated from electrical componentry and wiring. Fire extinguishers are located in each engine nacelle.
In all there are some 1070 major engineering changes over the Metro II, mainly covering safety related items, and this effectively ups the new aircraft’s empty weight by about 550 lbs.
The Metro III is certified to 14,000 pounds (6,350 Kg.) MAUW, with a 12,500 lb zero fuel weight. Approved by both F.A.A. under new SFAR 41 and by ICAO Annex 8.
Swearingen Merlin IIIA
The Merlin IIIB has 900 shp Garrett AiResearch TPE 331-10U-501G engines, four blade instead of three blade props, and an extra gear in the reduction system that limits the prop to 1,591 rpm and makes the props turn to the left. Prop rpm for the III was 2,000, so this is a significant reduction.
Certification of the IIIB by the FAA was confirmed on 3 November and the first production example was delivered to Teterboro Aircraft Services on 1 December.
The Merlin IIIB is normally flown in the 25,000 to 28,000 foot range. At gross weight, it takes 17 or 18 minutes to reach 26,000 feet. Flight Level 260 is close to where the maximum range and maximum speed lines meet on the chart. The speed up there at 12,000 pounds is 269 knots at .52 nautical miles per pound of fuel burned, for a flow of about 530 pounds an hour. At 10,000 pounds, a more common mid cruise weight, the specific range can be as high as .6 nautical miles per pound of fuel consumed, with a cruise speed still over 260 knots, at 30,000 or 31,000 feet.
The Merlin IIIB is a purpose-built, high capability executive aircraft. Powered by a brace of 900 s.h.p. Garrett Ai-Research turboprops, the IIIB can wind out to a 300 knot cruise, carry eight passengers and crew of two for over a thousand miles. (Initial rate of climb at gross is 2,782 fpm, while over a thousand feet per minute can be averaged right on through to the service ceiling of 31,000 feet.) Single engine rate of climb at gross is 700 fpm; service ceiling with one out 16,500 feet. The Metro III also exists in an all-cargo configuration, known as the Expediter, with changes which permit payloads of 5,000 lb (2 268 kg). Fairchild, by 1990, had begun delivery of 13 C-26A versions to the US ANG.
The Merlin III is like the VI, only shorter, lighter and faster. It has a six passen¬ger cabin with a slide out potty in the rear. An equipped III will weigh, 7,200 to 7,300 pounds empty, 12,500 at gross. It has a maximum cruise speed of 275 knots, nine knots faster than the IV. Both aircraft have a 12,560 pound ramp weight and a landing weight of 11,500 pounds.
The primary difference in the two airplanes is range. The IV will carry crew, three passengers and baggage 1,875 nm at 226 knots, or at high cruise it will take the three 1,390 nm at 265 knots. The III will carry three passengers 2,255 nm at 257 knots in economy cruise, or 1,610 nm at 275 knots in high cruise.
Sharing the same wing and fuselage section with that of its big brother the Metroliner, the 17 foot shorter Merlin fuselage is pressurised to 7 psi differential, allowing cabin pressure to remain at sea level during a 17,000 foot cruise, or a 7,300 foot cabin at 31,000 feet. Going hand in hand with the capable pressurisation system, interior sound levels too have been designed with comfort in mind. Big slow turning four-bladed props, coupled with increased sound-proofing over earlier models, results in remarkably low cabin noise levels — similar in fact to a jet, and with a silky, vibration-free smoothness in flight that would hardly ruffle the surface of the boss’s gin and tonic. Elbow room in the cabin too is excellent. Maximum cabin width is a generous 5.2 feet; headroom is 4.8 feet.
Range and payload combinations are flexible. With a crew of two and virtually no payload, range is better than 2,000 miles (this with 4,342 pounds of fuel total), while with a full payload of 1,770 pounds on board the Merlin achieves 1,100 miles at 288 knots, still retaining a 45 minute reserve. Fuel flow shows around 600 pph.
Fully reversing prop blades and powered anti-skid braking assist with the field performance. Low pressure tyres are fitted and the Garretts can be equipped with water-methanol injection as an optional extra.
Developed from the Metro II, the Metro III version is operated by several air forces as a utility transport. The US Air National Guard designates its variant the C-26A. Other models are the Metro III(H) with a 16,000-lb (7,258-kg) maximum take-off weight (ANG C-26B), and the Expediter all-freight model with a 4,780-lb (2,168-kg) payload.
For specialized military roles, the manufacturer provides the Metro III Special Missions Version – A Special Missions aircraft based on the Metro III airframe is available for various maritime patrol/surveillance and ASW duties. Mission equipment includes a Litton 360 deg scan APS-504(V) or AIL APS-128D search radar in an underfuselage radome for maritime surveillance, and a sonobuoy acoustic processor and a MAD tailboom for the ASW role. Optional equipment in both cases comprises low-light TV, infrared linescanner, Flir, Doppler radar, and a searchlight. Maximum take-off weight is 7,257kg (16,000lb), and endurance with auxiliary fuel tanks is ten hours. Also operated by the Swedish Air Force as Tp 88s.
The Merlin IV has the same basic airframe/engine combination as the Swearingen Metro commuter airliner, but there the similarity ends. The IV systems are so different from the Metro, and the capabilities of the airplanes are so distinct, that the two have separate type certificates.
The IV is a 10 passenger airplane in standard corporate configuration. It weighs 12,500 pounds maximum for takeoff and cruises at 265 knots. The design has what engineers sometimes call “maximum mission capability”: that is, with full tanks, full avionics and miscellaneous equipment, it will accommodate only the crew for maximum range ferry purposes. From this condition you trade off range for payload to a maximum of 2,800 2,900 pounds in passengers and baggage and 1,500 pounds of fuel.
Behind the rear cabin bulkhead is a pressurized, 136 cubic foot, 500 pound limit baggage/cargo compartment accessible through a 53 inch wide door on the left side of the fuselage. A second, un-pressurized, 45 cubic foot baggage compartment in the nose will hold up to 800 pounds, less the weight of avionics boxes. Cabin pressure differential is seven psi, which gives the IV a sea level cabin at 16,000 feet, its maximum cruise speed altitude. There are dual pressurization, heat and air conditioner systems.
The Swearingen Aviation Corporation, a subsidiary of Fairchild Industries, added 17 feet to the length of an executive turboprop fuselage to create an airplane for both airlines and corporate operators. The 1976 models of the long Swearingen were called the Merlin IVA and the Metro II. The former is a corporate airplane, the latter is used for airline operations. The Merlin and Metro 4 are air conditioned and pressurized. When it is used as an executive transport, the Merlin’s passenger load is usually lower and larger fuel loads can handle much longer trips with the average executive load. When cargo carrying missions are combined with passenger operations, a Metro II “Expediter” version of the airplane is available. Its movable bulkheads and removable interiors facilitate a quick change from passenger to cargo operations or to any mixture of the two. The Swearingen Metro II and Merlin IVA received a restricted category certification that will permit them to operate at gross weights of up to 14,000 pounds. Special mission editions of the turboprops, designed for patrols or aerial photography, are able to carry 648 gallons of fuel, for up to 10 hours of endurance.
Fairchild’s SA 227-DC Metro 25 flew for the first time on 25 September 1989.
The Fairchild RC-26 offered an aerial surveillance option for local and federal law enforcement agencies, allowing them to cut down on high-speed chases and more easily gather evidence on drug trafficking organizations. During the eight-year span of operations, the RC-26 flying flew over 4000 hours contributing the seizure of one billion dollars’ worth of narcotics and leading to over one thousand arrests.
RC-26
In addition to supporting counter-narcotics operations, the RC-26 crew supported emergency management agencies during natural disasters including forest fires on the west coast, flooding in the Midwest and hurricane Maria in Puerto Rico. The aircraft provided vital imagery of affected areas to emergency crews on the ground.
Fairchild Metro III two/three-crew light transport Engines: two l,000-shp (746-kW) Garrett TPE33I-l1U-611G turboprops Maximum speed 320 mph (515 km/h) at 12,500 ft (3,810 m) Initial climb rate 2,350 ft (716 m) per minute Service ceiling 27,500 ft (8,380 m) Range 1,000 miles (1,609 km) with maximum passenger payload Empty weight 8,737 lb (3,963 kg) Maximum take-off 14,500 lb (6,577 kg) Wing span 57 ft 10 in (17.37 m) Length 59 ft 4.25 in (18.09 m) Height 16 ft 8 in (5.08 m) Wing area 309.0 sq ft (28.71 sq.m) Payload: 20 passengers or 4,880 lb (2,214 kg) of freight
Metro IIIA Engines: Garrett, 840 shp TBO: 2500 hr Max cruise: 278 mph Econ cruise: 244 mph Stall: 83 mph Fuel cap: 4342 lb Service ceiling: 28,900 ft SE service ceiling: 15,000 ft ROC: 2530 fpm SE ROC: 620 fpm Min field length: 2150 ft Payload with full fuel: 389 lb Max range: 2487 sm High speed range: 1953 sm Max payload: 2060 lb Range with max payload: 1154 sm Pressurisation diff: 7.0 psi Seats: 11 Gross wt: 12,500 lb Equipped empty wt: 7769 lb Useful load: 4731 lb
SA227-AC Metro III-41 Engines: 2 x Garrett TPE-331-IIU-601G, 1000 shp Props: Dowty-Rotol 4-blade, 106-in Seats: 22 Length: 59.4 ft Height: 16.7 ft Wingspan: 57 ft Wing area: 309 sq.ft Wing aspect ratio: 10.5 Maximum ramp weight: 14,100 lb Maximum takeoff weight: 14,000 lb Standard empty weight: 8397 lb Maximum useful load: 5703 lb Zero-fuel weight: 12,500 lbs Maximum landing weight: 14,000 lb Wing loading: 45.3 lbs/sq.ft Power loading: 7 lbs/hp Maximum usable fuel: 4342 lb Best rate of climb: 2500 fpm Certificated ceiling: 31,000 ft Max pressurisation differential: 7 psi. 8000 ft cabin alt @: 32,400 ft Maximum single-engine rate of climb: 760 fpm @ 133 kts Single-engine climb gradient: 344 ft/nm Single-engine ceiling: 16,000 ft Maximum speed: 271 kts Normal cruise @ 25,000ft: 264 kts Fuel flow @ normal cruise: 509 pph Endurance at normal cruise: 8 hrs Stalling speed clean: 97 kts Stalling speed gear/flaps down: 87 kts Turbulent-air penetration speed: 174 kts
SA227-AC Metro III-41B Engines: 2 x Garrett TPE-331-IIU-601G, 1000 shp Props: Dowty-Rotol 4-blade, 106-in Seats: 22 Length: 59.4 ft Height: 16.7 ft Wingspan: 57 ft Wing area: 309 sq.ft Wing aspect ratio: 10.5 Maximum ramp weight: 14,100 lb Maximum takeoff weight: 14,000 lb Standard empty weight: 8397 lb Maximum useful load: 5703 lb Zero-fuel weight: 12,500 lb Maximum landing weight: 14,000 lb Wing loading: 45.3 lbs/sq.ft Power loading: 7 lbs/hp Maximum usable fuel: 4342 lb Best rate of climb: 2500 fpm Certificated ceiling: 31,000 ft Max pressurisation differential: 7 psi 8000 ft cabin alt @: 32,400 ft Maximum single-engine rate of climb: 760 fpm @ 133 kts Single-engine climb gradient: 344 ft/nm Single-engine ceiling: 16,000 ft Maximum speed: 271 kts Normal cruise @ 25,000ft: 264 kts Fuel flow @ normal cruise: 509 pph Endurance at normal cruise: 8 hrs Stalling speed clean: 97 kts Stalling speed gear/flaps down: 87 kts Turbulent-air penetration speed: 174 kts
Merlin IIIA Engine: 2 x TPE 331-3U-303G, 840 hp Seats: 11 Length: 42.159 ft / 12.85 m Height: 16.732 ft / 5.1 m Wingspan: 46.26 ft / 14.1 m Wing area: 277.496 sq.ft / 25.78 sq.m Wing loading: 45 lb/sq.ft 220.0 kg/sq.m Pwr loading: 7.44 lb/hp Gross wt: 12,500 lb / 5670.0 kg Empty wt: 7600 lb Equipped useful load: 4531 lb Payload max fuel: 189 lb Range max fuel/cruise: 1720nm/6.3hr Range max fuel / range: 2266nm/9.3hr Ceiling: 31,000 ft Max cruise: 272 kt Max range cruise: 245 kt Vmc: 104 kt Stall: 84-97 kt 1.3 Vso: 109 kt ROC: 2530 fpm SE ROC: 620 fpm @ 143 kt SE ceiling: 13,500 ft Min field length: 3075 ft Take off distance: 3051 ft / 930 m Landing distance: 2854 ft / 870 m Fuel cap: 4342 lb Cabin pressure: 7 psi Crew: 2
Merlin IIIB Engines: 2 x AiResearch TPE 331 1OU 501G, 900 shp Props: Full feathering, reversible, 106 in, dia TBO: 3,000 hrs Length: 42 ft. 1 in Height: 16 ft. 9 in Wingspan: 46 ft. 3 in Wing area: 277.5 sq. ft Max ramp wt: 12,600 lbs Max takeoff wt: 12,500 lbs Standard empty wt: 7,600 lbs Max useful load: 4,900 lbs Max landing wt: 11,500 lbs Zero fuel wt: 10,000 lbs Wing loading: 45 lb/sq.ft Power loading: 6.9 lb/hp Max usable fuel: 648 USG/4,342 lbs Max rate of climb: 2,782 fpm Service ceiling: 31,400 ft Single engine rate of climb: 700 fpm Single engine climb gradient: 304 ft/nm Single engine service ceiling: 16,500 ft Max speed: 309 kts Normal cruise (@ 22,000 ft. and 12,000 lbs.): 280 kts Fuel flow at normal cruise: 600 pph Endurance at normal cruise, no reserve: 7.2 hrs Stalling speed, clean: 103 kts Stalling speed, flaps down: 89 kts Turbulent air penetration speed: 190 kts Max pressurization differential: 7 psi. 8,000 ft. cabin altitude @: 32,400 ft.
Merlin IVA Engines: 2 x Garrett AiResearch TPE 331 3U-303G,840 shp Prop: Hartzell 3 blade,constant speed, full feathering, reversing, 102 in. dia Length: 59 ft. 4 in Height: 16 ft, 8 in Wingspan: 46 ft. 3 in Airfoil: NACA 652A215 at root 642A425 at tip Aspect ratio: 7.71 Wing area: 277.5 sq. ft Wing loading: 45 lbs/sq.ft Empty weight: 8,553 lbs Useful load: 3,947 lbs Payload with full fuel: 235 lbs Ramp weight: 12,560 lbs Maximum takeoff weight: 12,500 lb Power loading: 7.44 lbs./hp Usable fuel capacity: 554 gals/13,712 lbs Baggage area: 143 cu. Ft Minimum runway requirement: 2,050 ft Rate of climb: 2,400 fpm Single engine rate of climb: 650fpm Service ceiling: 27,000 ft Single engine service ceiling: 14,700 ft Maximum cruise (@ 16,000 ft.): 269 knots High altitude cruise (@ 24,000 ft.): 240 knots Maximum range (45 minute reserve): 1,810 nm Stall speed, clean: 97 knots Stall speed, gear and flaps down: 86 knots
SA227-AT Merlin IVC-41 Engines: 2 x Garrett TPE-331-IIU-601G, 1000 shp Props: Dowty-Rotol 4-blade, 106-in Seats: 13/16 Length: 59.4 ft Height: 16.7 ft Wingspan: 57 ft Wing area: 309 sq.ft Wing aspect ratio: 10 Maximum ramp weight: 14,100 lbs Maximum takeoff weight: 14,000 lbs Standard empty weight: 9100 lbs Maximum useful load: 5000 lbs Zero-fuel weight: 12,500 lbs Maximum landing weight: 14,000 lbs Wing loading: 45.3 lbs/sq.ft Power loading: 7 lbs/hp Maximum usable fuel: 4342 lbs Best rate of climb: 2500 fpm Certificated ceiling: 31,000 ft Max pressurisation differential: 7 psi. 8000 ft cabin alt @: 32,400 ft Maximum single-engine rate of climb: 760 fpm @ 133 kts Single-engine climb gradient: 344 ft/nm Single-engine ceiling: 16,000 ft Maximum speed: 297 kts Normal cruise @ 25,000ft: 268 kts Fuel flow @ normal cruise: 527 pph Endurance at normal cruise: 7.7 hrs Stalling speed clean: 97 kts Stalling speed gear/flaps down: 87 kts Turbulent-air penetration speed: 174 kts
SA227-AT Merlin IVC-41B Engines: 2 x Garrett TPE-331-IIU-601G, 1000 shp Props: Dowty-Rotol 4-blade, 106-in Seats: 13/16 Length: 59.4 ft Height: 16.7 ft Wingspan: 57 ft Wing area: 309 sq.ft Wing aspect ratio: 10.5 Maximum ramp weight: 14,100 lbs Maximum takeoff weight: 14,000 lbs Standard empty weight: 9100 lbs Maximum useful load: 5000 lbs Zero-fuel weight: 12,500 lbs Maximum landing weight: 14,000 lbs Wing loading: 45.3 lbs/sq.ft Power loading: 7 lbs/hp Maximum usable fuel: 4342 lbs Best rate of climb: 2500 fpm Certificated ceiling: 31,000 ft Max pressurisation differential: 7 psi. 8000 ft cabin alt @: 32,400 ft Maximum single-engine rate of climb: 760 fpm @ 133 kts Single-engine climb gradient: 344 ft/nm Single-engine ceiling: 16,000 ft Maximum speed: 297 kts Normal cruise @ 25,000ft: 268 kts Fuel flow @ normal cruise: 527 pph Endurance at normal cruise: 7.7 hrs Stalling speed clean: 97 kts Stalling speed gear/flaps down: 87 kts Turbulent-air penetration speed: 174 kts
SA227-TT Merlin IIIC-23 Engines: 2 x Garrett TPE-331-IOU-530G, 900 shp Props: Dowty-Rotol 4-blade, 106-in Seats: 8/11 Length: 42.2 ft Height: 16.8 ft Wingspan: 46.3ft Wing area: 277.5 sq.ft Wing aspect ratio: 7.7 Maximum ramp weight: 12,600 lbs Maximum takeoff weight: 12,500 lbs Standard empty weight: 8090 lbs Maximum useful load: 4510 lbs Zero-fuel weight: 12,500 lbs Maximum landing weight: 12,500 lbs Wing loading: 45.0 lbs/sq.ft Power loading: 7 lbs/hp Maximum usable fuel: 4342 lbs Best rate of climb: 2800 fpm Certificated ceiling: 31,000 ft Max pressurisation differential: 5.5 psi 8000 ft cabin alt @: 32,400 ft Maximum single-engine rate of climb: 780 fpm @ 135 kts Single-engine climb gradient: 346 ft/nm Single-engine ceiling: 16,500 ft Maximum speed: 309 kts Normal cruise @ 25,000ft: 290 kts Fuel flow @ normal cruise: 525 pph Endurance at normal cruise: 7.7 hrs Stalling speed clean: 102 kts Stalling speed gear/flaps down: 89 kts Turbulent-air penetration speed: 189 kts
SA227-DC Metro 23 Engines: 2 x Garrett TPE-331-12 MTOW: 7484 kg
SA227-TT Merlin IIIC-41 Engines: 2 x Garrett TPE-331-IOU-530G, 900 shp Props: Dowty-Rotol 4-blade, 106-in Seats: 8/10 Length: 42.2 ft Height: 16.8 ft Wingspan: 46.3 ft Wing area: 277.5 sq.ft Wing aspect ratio: 7.7 Maximum ramp weight: 13,330 lb Maximum takeoff weight: 13,230 lb Standard empty weight: 8150 lb Maximum useful load: 5180 lb Zero-fuel weight: 12,500 lb Maximum landing weight: 13,230 lb Wing loading: 47.7 lbs/sq.ft Power loading: 7.4 lbs/hp Maximum usable fuel: 4342 lb Best rate of climb: 2650 fpm Certificated ceiling: 31,000 ft Max pressurisation differential: 7 psi 8000 ft cabin alt @: 32,400 ft Maximum single-engine rate of climb: 680 fpm @ 138 kt Single-engine climb gradient: 296 ft/nm Single-engine ceiling: 14,500 ft Maximum speed: 309 kt Normal cruise @ 25,000ft: 290 kt Fuel flow @ normal cruise: 525 pph Endurance at normal cruise: 7.7 hrs Stalling speed clean: 104 kt Stalling speed gear/flaps down: 92 kt Turbulent-air penetration speed: 189 kts
Fairchild (Swearingen) C 26 Metroliner Engines: 2 x TPE 331 11U, 809 shp Length: 59.383 ft / 18.1 m Height: 16.732 ft / 5.1 m Wingspan: 57.087 ft / 17.4 m Wing area: 308.927 sq.ft / 28.70 sq.m Max take off weight: 14502.3 lb / 6577.0 kg Weight empty: 9181.6 lb / 4164.0 kg Max. payload weight: 5300.8 lb / 2404.0 kg Max. speed: 278 kts / 515 km/h Landing speed: 87 kts / 161 km/h Cruising speed: 248 kts / 460 km/h Initial climb rate: 2362.20 ft/min / 12.00 m/s Service ceiling: 27428 ft / 8360 m Wing loading: 46.95 lb/sq.ft / 229.00 kg/sq.m Range: 575 nm / 1065 km Crew: 2 Payload: 20 pax
All Aero 