Aircraft

Alisport Yuma

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Alisport initiated development of the STOL YUMA in 1994. A single engine, two-seater side-by-side, high-wing monoplane with a metal structure, all aircraft structural parts are heat-treated and corrosion inhibiting coatings are used throughout. All aluminum skins are bonded to the underlying structure prior to final riveting.
The cockpit structure is a welded tubular steel frame, and aluminum is used for the wings, tail-cone, and empennage. The control surfaces are fabric-covered.
The flight characteristics of the YUMA are enhanced by an optimized wing profile and carbon-fiber leading edge slats (Handley-Page type) that directly address the requirements of S.T.O.L. flight. The large flaps permit steep final approaches to facilitate descent over tall obstacles.
The fuel system is two wing tanks and a header tank at the firewall providing a total endurance of up to five hours.

Engine: Rotax 912 UL (80 HP)
Wing span: 9,75 m
Cabin width: 1,18 m
Length: 6,45 m
Height: 2,45 m
Wheelbase: 2,00 m
Wing area: 13,4 sq.m
Aspect ratio: 6,6
Empty weight: 282 kg
Max takeoff weight: 450 kg
Wing loading: 33,5 kg/sq.m
Maximum speed: 175 kph
Cruise speed 75%: 150 Km/h
Stall (without flaps): 55 Km/h
Stall speed (with flaps): 50 Km/h
VNE: 105 kt / 121 mph / 195 kmh
Rate of climb: 6 m/s
TO dist (with 1 pob): 40 m
TO dist (full load): 45 m
Landing distance: 55 m
Max ceiling: 5000 m
Fuel capacity: 85 lt
Endurance max payload at cruise speed 75%(5000 rpm): 5,2 hr

Engine: Rotax 912 ULS (100 HP)
Wing span: 9,75 m
Cabin width: 1,18 m
Length: 6,45 m
Height: 2,45 m
Wheelbase: 2,00 m
Wing area: 13,4 sq.m
Aspect ratio: 6,6
Empty weight: 282 kg
Max takeoff weight: 450 kg
Wing loading: 33,5 kg/sq.m
Maximum speed: 185 Km/h
Cruise speed 75%: 160 Km/h
Stall (without flaps): 55 Km/h
Stall speed (with flaps): 50 Km/h
VNE: 105 kt / 121 mph / 195 kmh
Rate of climb: 8 m/s
TO dist (with 1 pob): 30 m
TO dist (full load): 40 m
Landing distance: 55 m
Max ceiling: 5000 m
Fuel capacity: 85 lt
Endurance with max payload at cruise speed 75%(5000 rpm): 4,5 hr

Engine: Rotax 914 UL (115 HP)
Wing span: 9,75 m
Cabin width: 1,18 m
Length: 6,45 m
Height: 2,45 m
Wheelbase: 2,00 m
Wing area: 13,4 sq.m
Aspect ratio: 6,6
Empty weight: 282 kg
Max takeoff weight: 450 kg
Wing loading: 33,5 kg/sq.m
Maximum speed: 195 Km/h
Cruise speed 75%: 170 Km/h
Stall (without flaps): 55 Km/h
Stall speed (with flaps): 50 Km/h
Rate of climb: 10 m/s
TO dist (with 1 pob): 30 m
TO dist (full load): 40 m
Landing distance: 55 m
Max ceiling: 7000 m
Fuel capacity: 85 lt
Endurance with max payload at cruise speed 75%(5000 rpm): 4,1 hr

Alisport Silent

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Silent Club

The Silent Club is a light sailplane with 12-meter fiberglass wings for recreational flying. It has a blend of agility/control responsiveness, climb performance, safety, and fun. The two-position flaps have a reflex position to maintain good glide performance at higher airspeeds. The pure sailplane and fuel-injected self-launcher versions were available as quick-build kits. Assembly is simple, both due to all controls having fully automatic connections and due to the light weight of the wings. The airframe is built entirely of composite materials, with use of carbon fiber in the aft portions of the fuselage pod, the tail boom, and various critical locations of the structure. The cockpit is completely built of glass fibre. The Silent Club’s low sink rate and its stability while thermalling allow it to fly with hang-gliders and to be practically unbeatable in climb when compared with Standard class or 15m class sailplanes. It is easy to both launch and to land, and is particularly suitable for new pilots performing their first single-seat flights. The Silent Club has very efficient conventional air brakes and can be landed in less than 70 m (230 ft). Due to its span of only 12 m (39 ft) it can be stored in a small space. A fully enclosed “clam-shell” trailer is available for road transportation.
The Silent 2 is a high-performance light sailplane with 13-meter wings for recreational and sport flying.
The carbon-fiber wings have an elliptical planform, removable winglets, and five flap settings to cover the entire speed range. The pure sailplane and fuel-injected self-launcher versions were available as quick-build kits. Several World records have been set with the Silent 2 in the FAI Class-DU. A basic airframe combined with reasonable pilot weight will generally result in a take-off weight under the 220kg (485 lbs) maximum allowable required for the FAI’s DU Class. The Silent 2’s airframe is built entirely of composite materials, with use of carbon fiber in the aft portions of the fuselage pod, the tail boom, and various critical locations of the structure. The oven-cured wing structure includes extensive use of carbon-fiber. The sandwich skins use vacuum-bagged carbon fabric for the interior layer and glass fabric for the exterior layer while the wing spar uses pultruded carbon rods for the spar caps. It tows well behind trikes, sport-aircraft, and regular towplanes, making it versatile for all types of glider operations.
The Silent 2 TARGA is a high-performance light sailplane for recreational and sport flying. It has retractable landing gear, vertical-design winglets, and horizontal stabilizer with automatic trim. The pure sailplane and fuel-injected self-launcher versions were available as quick-build kits.

Powered by the proven Alisport A302efi engine producing 28hp at 6200rpm, this single-lever FADEC engine has electronic ignition, fuel-injection, electric start, and flywheel generator. The counterweighted monoblade carbon-fiber propeller has a swept diameter of 1.4m and electrically retracts into the fuselage along with the engine pylon. The wings have an elliptical planform, vertical design winglets, and a span of 13.3 meters. The wing structure includes extensive use of carbon fiber, both in the sandwich skins and in the tapered I-beam wing spar which uses pultruded carbon rods for the spar caps. The wing geometry is unique in that it varies non-linearly from the root to the tip, both in overall planform shape and in wing section profile. The flaperons stretch for 11.0 meters of the full wingspan and their range of motion varies from positive landing L, to +40 for thermalling, to 00, -40, and S reflex positions for cruising. The sailplane is trimmed in pitch via an innovative variable-position horizontal stabilizer. The stabilizer position is governed by the flaperon setting: the five settings of the flap control produce corresponding changes to the stabilizer incidence, thus defining the trim airspeed in relation to the flap requirements. The conventional elevator remains in trail, minimizing trim drag.

The Silent OP version has the engine mounted on a fixed pylon. Power is the Konig SD 570 or retractable Zanzoterra FZ 34 and single blade prop.

Silent OP
Silent-1N launching with two jet engines

Silent
Light sailplane circa 1998.
Weight: 130 kg
Wing span: 12 m
Wing area: 10.3 sq.m
Vne: 200 km
Stall: 54km
Vz min: 0.6 m/sec
Glide Ratio: 32 @ 90 kph

Silent Club
Length: 20.8 ft.
Wingspan: 12m / 39.3 ft.
Wing area: 10.3sq.m / 110.9 sq.ft.
Aspect ratio: 14-1
Seats: 1
Cockpit width: 22 in
Empty wt: 135kg / 300 lbs.
Mtow: 240kg / 530 lbs.
Payload: 105kg
Cruise: 60 mph.
Stall: 36 mph
L/D: 31-1@ 85 km/h
Min sink: 126 fpm / 0.64 m/s @ 65 kph.
Structure: all composite

Silent Club Self-Launch
Engine: A302 EFI, 28 hp.
Length: 20.8 ft.
Wingspan: 39.3 ft.
Wing area: 110.9 sq.ft.
Aspect ratio: 14-1.
Seats: 1.
Cockpit width: 22 inch.
Empty wt: 375 lbs.
Mtow: 639 lbs.
Fuel cap: 4.5 USG.
Cruise: 53 mph.
Stall: 38 mph.
L/D: 31-1.
Min sink: 138 fpm.

Silent 2
Length: 20.8 ft.
Wingspan: 13m / 42.6 ft.
Wing area: 8.8sq.m / 94.7 sq.ft.
Aspect ratio: 19.2-1.
Seats: 1.
Cockpit width: 22 in
Empty wt: 125kg / 275 lbs.
Mtow: 245kg / 540 lbs.
Payload: 105kg
Cruise: 50 mph.
Stall: 37 mph.
L/D: 39-1 at 81 kph.
Min sink: 106 fpm / 0.54 m/s at 77 kph.
Structure: All composite

Silent 2 Electric
Engine: Air Energy DC, 13 kw.
Length: 20.8 ft.
Wingspan: 42.6 ft.
Wing area: 94.7 sq.ft.
Aspect ratio: 19.2-1.
Seats: 1.
Cockpit width: 22 in
Empty wt: 385 lbs.
Mtow: 660 lbs.
Cruise: 56 mph.
Stall: 40 mph.
L/D: 39-1.
Min sink: 118 fpm.

Silent 2 Self-Launch
Engine: A302 EFI, 28 hp.
Length: 20.8 ft.
Wingspan: 42.6 ft.
Wing area: 94.7 sq.ft.
Aspect ratio: 19.2-1.
Seats: 1.
Cockpit width: 22 in
Empty wt: 385 lbs.
Mtow: 660 lbs.
Fuel cap: 4.5 USG.
Cruise: 56 mph.
Stall: 40 mph
L/D: 39-1.
Min sink: 118 fpm.

Silent 2 Targa Self-Launch
Engine: Alisport A302efi 28 Hp single-cylinder air-cooled
Wing span: 13.3 m / 43.6 ft
Length: 20.8 ft.
Wing area: 8.9sq.m /95.7 sq.ft.
Aspect ratio: 20
Empty Weight: 185kg / 385 lbs.
Payload: 105kg
MTOW: 300kg / 660 lbs
Fuel cap: 4.2 USG
L/DMax: 40 at 90 km/h
MinSink: 0.60 m/s / 118 fpm @ 85km/h
Cruise: 56 mph
Stall: 40 mph
No. of Seats: 1
Cockpit width: 22 in

Silent OP
Engine: Konig SD 570, 28 hp
Wing span: 12 m
Wing area: 10.30 sq.m
MAUW: 270 kg
Empty weight: 165 kg
Fuel capacity: 2 x 20 lt
Seats: 1
Max speed: 200 kph

Alfa HB207 Alfa

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The Alfa is a European kit built aircraft designed by Heino Breditschka. An all-metal low-wing, tri-cycle gear airplane with side-by-side seating, the aircraft is 19.35 t in length and has a wing span of 29.5 ft. Suggested engine for the plane is a 110 HP Volkswagen Porsche G 2 2.400 air cooled boxer engine. The HB207 cruises at 140 kts with an fuel burn of 3.5 US Gal/hr and stalls (flaps down) at 40 kts. It features a 5 blade constant speed prop, retractable landing gear, and detachable wings.

Alexander Eaglerock

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Designed by Daniel Noonan the Eaglerock was extensively redesigned as the A-1 by Al Mooney in 1926. The design had folding wings, and Warren-truss wing struts with no wire rigging, and based on surplus Longren components.

The name came about from an injured Golden Eagle cared for as a pet by factory employees, appended with “Rock,” honoring the nearby Rocky Mountains.

The 1925 Alexander Eaglerock had trouble get¬ting off the ground at Denver, where it was being built, because its wing area was too small. Mooney improved and lengthened the wing. He made the up¬per and lower wings exactly alike and left out the center section. So where the fuselage fitted into the bottom set, it gave them a longer span.

Eaglerock Combo-Wing

First flying on 19 September 1925, powered with a 100 hp Kinner engine the Eaglerock sold at $3907 flyaway factory. The craft was available with $1562.80 down and the balance in twenty semi-monthly installments of $128.94. Powered by a 150 hp Hisso A the flyaway price was $3230, or $1800.00 down and twenty semi-monthly installments of $107.25. Powered by a 165 hp Wright J-6 the flyaway price was $3397, or $2238.80 down and twenty semi-monthly installments of $182.71.

Eaglerock Kinner 100 hp

The second Eaglerock design, the 1926 Eaglerock A-1 or New Eaglerock, had 40’0″ lower wing.

Alexander Eaglerock A-1 NC10035

First flying on 7 January 1926, piloted by Capt Cordner, the A-1 sold for $6,500, or $2,250 less motor, receiving DoC approval (ATC 57) in 1928.

895 of all Eaglerocks were built 1927-32. Company records claim a total of about 450 Eaglerock models built by the end of 1928.

Gallery

Engine: Curtiss OX-5

Eaglerock A-1
Engine: 220hp Wright J-5
Wingspan: 36’8″
Length: 23’11”
Useful load: 786 lb
Max speed: 126 mph
Cruise: 108 mph
Stall: 39 mph
Range: 580mi
Seats: 3

Air Mechanics Inc D-2Alexander Flyabout D-1 / Flyabout D-2 / Aircraft Mechanics Flyabout D-2

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Alexander Flyabout D-2 NC528Y

The 1931 Flyabout D-1 (ATC 439) was designed by Proctor Nichols as a two-place cabin monoplane, priced at $1,465. Four Flyabout D-1 were built; one unlicensed static test model, one prototype – NX447V, and two converted to D-2 – NC528Y and NC11061.

The Flyabout D-2 of 1931 featured a larger fin and rudder and was priced at $1,590.

The 1935 Aircraft Mechanics Flyabout D-2 (ATC 449) improved production model varied slightly in length and was priced at $1,450.

Seventeen D-2 were built of which two were converted from D-1.

Flyabout D-1
Engine: 40hp Continental A-40
Wingspan: 37’10”
Length: 21’9″
Useful load: 389 lb
Max speed: 80 mph
Cruise: 70 mph
Stall: 28 mph
Range: 175 mi
Seats: 2

Flyabout D-2
Engine: 45hp Szekely SR-3
Wingspan: 37’10”
Length: 21’7″
Useful load: 392 lb
Max speed: 90 mph
Cruise: 77 mph
Stall: 32 mph
Seats: 2

Aircraft Mechanics Flyabout D-2
Engine: 45hp Szekely SR-3
Wingspan: 37’10”
Length: 21’9″
Useful load: 399 lb
Max speed: 93 mph
Cruise: 80 mph
Stall: 32 mph
Seats: 2

Alexander Aircraft Co / Air Mechanics Inc

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1923: (Julian Don) Alexander Film Co
3385 So Broadway
Englewood CO.
USA

1924: Purchase of Longren Aircraft Co as Alexander Industries, and Alexander Flying School.

1925: Alexander Aircraft Co
Formed August 1925 at Colorado Springs, Colorado, as division of Alexander Industries Inc. then of Denver.

1928: Colorado Springs CO.

Concentrated on Eaglerock three-seat civil biplane with Curtiss OX-5 engine. When supplies of this cheap engine exhausted (1928), redesigned aircraft for other engines. Eleven Eaglerock biplanes still registered in USA in 1960s. D-2 was two-seat strut-braced high-wing cabin monoplane. Low-wing Bullet series designated by firearm calibers (.22, .32, .45 etc.).

Company succumbed to US financial depression, but continued manufacture as Air Mechanics Inc., and in 1934 designed a five-seat low-wing monoplane.

1932: Aircraft operations into bankruptcy.

1934: Reorganized as Aircraft Mechanics Inc
fdr: Proctor W Nichols, W F Theis
3200 N Nevada St
Colorado Springs.
USA

Air Mechanics Inc was a revival of Alexander Aircraft Company, partly by former employees. Conducted service department of Alexander products, and during the 1930s made D-1 and D-2 two-seater monoplanes of new design.

Alenia C-27J Spartan

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The C 27 J is a joint-venture of Alenia and Lockheed Martin based on the FIAT G222 transport, but with engines and avionics redesigned and made common with the Lockheed C-130J Hercules.
The maiden flight of the prototype (I-CERX) took place from Turin, Italy, on September 25, 1999, and lasted 1 hr 32 min. Crewed by Alenia test pilots the prototype reached 15,000 ft.
The first and second C-27 were converted G.222 aircraft, the third was the first new build.

Alenia C-27J Spartan Article

MC-27J is a multimission transport aircraft jointly produced and marketed by Alenia Aermacchi and ATK. It is an armed, roll on/roll off (RO/RO) aircraft based on the C-27J Spartan. Alenia unveiled a new version of the C-27J Spartan battlefield air-lifter, the MC-27J, at the Farnborough International Air Show in July 2012.

The C-27J base platform is slightly modified, while the airlift capabilities of C-27J are retained. The new aircraft is incorporated with pallet-based systems for additional mission-specific capabilities.

The MC-27J can be configured to conduct troop / cargo transport, paratroops / material air-drop, medical evacuation (MEDVAC) and VIP / passenger transport. The gun barrel on the aircraft can be removed to allow reconfigurations for other missions. The aircraft also integrates a fire protection system and an ice protection system.

The two-pilot glass cockpit of the MC-27J is equipped with off-the-shelf avionics and is fully compatible with night vision imaging systems. The avionics suite integrates colour multipurpose displays, multifunction control and display units, optional head-up display units, digital auto-pilot, GPS/INS, identification friend or foe (IFF) transponder, recording systems, terrain awareness warning system (TAWS) and traffic alert and collision avoidance system (TCAS).

The onboard PaWS (palletized weapon system) provides combat capabilities for the MC-27J aircraft. The PaWS is specifically designed for the ATK GAU-23 30mm cannon and other precision guided light munitions. The system minimises collateral damages. The palletised system can be loaded / unloaded through the rear ramp of aircraft. It can be installed in the aircraft within four hours.

MC-27J gunship

The GAU-23 Bushmaster 30mm cannon mounted on the PaWS RO/RO pallet is a chain gun that incorporates features of the M242 and Mk44 25mm cannons. The gun can fire 30mm x 173mm, PGU-13, PGU-15, and PGU-46 ammunition at a rate of 200 rounds a minute. The ammunition is fed into the gun through a dual feed system.

The palletised system also accommodates a reconfigurable mission suite incorporating sensors, communications and mission management system. The aircraft is equipped with electro-optical / infrared targeting sensors, and command, control and communications equipment.

The MC-27J serves as an independent command and control centre interfaced with the ground command network. The aircraft is also equipped to provide signal intelligence (SIGINT) intelligence surveillance and reconnaissance (ISR) capabilities. The target identification systems and weapons systems aboard the aircraft support ground missions.

The MC-27J is powered by two Rolls-Royce AE2100D2A turboprop engines. Each engine, generating 4,637shp power, drives two Dowty six-blade, all-composite propellers. Two full authority digital electronic control units control the engines and propellers.

The onboard electricity is supplied by three generators. The auxiliary power unit (APU) allows the engines to be restarted in flight during emergency conditions.

The fuel system includes four wing tanks and two dedicated fuel feed systems. The aircraft can be optionally fitted with an air-to-air refuelling probe for performing aerial refuelling.

Gallery

Prototype
Engine : 2 x Allison AE 2100 D2, 4142 shp
Props: Dowty 6 blade

Alenia C 27 J Spartan
Engine : 2 x Allison AE 2100 D3, 4142 shp
Length : 74.475 ft / 22.7 m
Height : 32.152 ft / 9.8 m
Wingspan : 94.16 ft / 28.7 m
Wing area : 882.648 sq.ft / 82.0 sq.m
Max take off weight : 66150.0 lb / 30000.0 kg
Weight empty : 36382.5 lb / 16500.0 kg
Max. speed : 305 kt / 565 km/h
Cruising speed : 270 kt / 500 km/h
Initial climb rate : 1968.5 ft/min / 10.0 m/s
Service ceiling : 26247 ft / 8000 m
Cruising altitude : 19685 ft / 6000 m
Wing load : 75.03 lb/sq.ft / 366.0 kg/sq.m
Maximum range : 2484 nm / 4600 km
Range : 1350 nm / 2500 km
Range (max. weight) : 540 nm / 1000 km
Crew : 2
Payload : 53 pax (max 10.000kg)

MC-27J
Engines: 2 x Rolls-Royce AE2100D2A turboprop, 4,637shp
Propellers: Dowty six-blade, all-composite
Length: 22.7m
Wing span: 28.7m
Height: 9.6m
Maximum take-off weight: 30,500kg
Maximum altitude: 30,000ft
Cruising speed: 583km/h
Maximum speed: 602km/h
Maximum range: 1,852km
Ferry range: 5,926km