Mustang Aeronautics Mustang II
Two-seat light homebuilt sporting aircraft

Archive Photos ¹

2007 Mustang Aeronautics Mustang II (N193BC, s/n M-II 193, Burt R. Cassazza) on display (1/11/2009) at the Cable Air Show, Cable Airport, Upland, California (Photos by John Shupek)

Overview ²

Design of this side by side two-seat derivative of the Midget Mustang was started in 1963. Construction of a prototype began in 1965 and it flew for the first time on 9 July 1966. During 1968 Mr. Bushby designed an alternative non-retractable tricycle landing gear for the Mustang II, and amateur constructors have the option of either configuration. Another option is wing folding, to permit storage in a home garage. About 1,200 Mustang IIs were being built by amateurs in early 1987, at which time 290 had been completed.

The description applies to the deluxe model, which is stressed for +6g, and the empty weight quoted includes IFR instrumentation and nav/com equipment. The M-II can also be operated as an aerobatic aircraft in what Bushby Aircraft calls the ’Sport’ configuration. This is identical to the deluxe model except that the electrical system, radio, additional IFR instrumentation, soundproofing and upholstery, wheel fairings, and some baggage capacity are deleted. The ’Sport’ model has an empty weight of 340 kg (750 lb), T-O weight of 567 kg (1,250 lb) and is stressed for +9g.

A Hartzell controllable pitch propeller replaced the original fixed pitch propeller as standard, and the performance figures quoted for the 119 kW (160 hp) engine are obtained with this propeller. The figures quoted for the 93 kW (125 hp) engine are those obtained with the fixed pitch propeller.

Specifications ²

Type

• Two-seat light homebuilt sporting aircraft.

Airframe

• Cantilever low-wing monoplane.
• Outer wings similar to those of Midget Mustang, attached to new constant chord center-section of short span.
• Wing section NACA 64A212 at root, NACA 64A210 at tip.
• Dihedral 5° on outer wings only.
• Incidence 1° 30’.
• Two-spar flush riveted stressed skin aluminum structure.
• Wing folding optional.
• Aluminum statically balanced ailerons and plain trailing-edge flaps.
• No trim tabs.
• Aluminum flush riveted stressed skin monocoque fuselage.
• Cantilever all-metal tail unit.
• Fixed incidence tailplane.
• Controllable trim tab in starboard elevator

Landing Gear

• Standard version has non-retractable tail-wheel type.
• Cantilever spring steel main legs.
• Goodyear 5.00 x 5 mainwheels and tires, pressure 1.38 bars (20 psi).
• Goodyear hydraulic disc brakes.
• Steerable tailwheel.
• Alternatively, non-retractable tricycle type.
• Cantilever spring steel main legs.
• Cleveland or Goodyear mainwheels and tires size 5.00 x 5.
• Non-steerable nosewheel, mounted on oleo-pneumatic shock strut and free to swivel up to 16° either side.
• Goodyear nosewheel and tire size 5.00 x 5.
• Goodyear or Cleveland hydraulic disc brakes.
• Wheel fairings optional on either type of landing gear.

Powerplant

• Normally one 119 kW (160 hp) Avco Lycoming O-320 flat-four engine, driving a Hartzell two-blade controllable-pitch metal propeller.
• Provision for other engines including a 93 kW (125 hp) Avco Lycoming O-290, driving a two-blade fixed-pitch metal propeller.
• Fuel tank aft of firewall, capacity 94.6 liters (25 US gallons; 21 Imp gallons).
• Optional integral wing fuel tanks, each with a capacity of 45 liters (12 US gallons; 10 Imp gallons).
• Refuelling point on starboard side of fuselage aft of firewall.
• Provision for wingtip tanks.
• Oil capacity 7.5 liters (2 US gallons; 1.7 Imp gallons).

Accommodation

• Two seats side by side, under large rearward sliding transparent canopy.
• Dual controls.
• Baggage space aft of seats, capacity 34 kg (75 lb).

Systems

• 12V electrical system, supplied by Delco-Remy 15A generator and Exide 33A battery.

Avionics and Equipment:

• Provision for full IFR instrumentation and dual nav/com system.

Dimensions, External

• Wing span: 7.37 m (24 ft 2 in)
• Width folded: 2.44 m (8 ft 0 in)
• Wing chord: at root 1.47 m (4 ft 10 in); at tip 0.79 m (2 ft 7 in)
• Wing aspect ratio: 6.01
• Length overall: 5.94 m (19 ft 6 in)
• Height overall: 1.60 m (5 ft 3 in)
• Height folded: 1.73 m (5 ft 8 in)
• Tailplane span: 2.29 m (7 ft 6 in)
• Wheel track: 2.08 m (6 ft 10 in)
• Propeller diameter: 93 kW (125 hp) 1.73 m (5 ft 8 in); 119 kW (160 hp) 1.83 m (6 ft 0 in)

Dimensions, Internal

• Cabin: Max width: 1.02 m (3 ft 4 in)
• Baggage space: 0. 16 m³ (5.5 ft³)

Area

• Wings, gross: 9.02 m² (97.12 ft²)

Weights and Loadings

• Weight empty, equipped (N: nosewheel, T: tailwheel landing gear):
• N: 93 kW (125 hp) engine: 413 kg (911 lb)
• T: 93 kW (125 hp) engine: 408 kg (900 lb)
• N: 119 kW (160 hp) engine: 425 kg (938 lb)
• T: 119 kW (160 hp) engine: 420 kg (927 lb)
• Max T-O and landing weight: 680 kg (1,500 lb)
• Max wing loading (160 hp): 75.4 kg/M2 (15.44 lb/ft²)
• Max power loading (160 hp): 5.71 kg/kW (9.38 lb/hp)

Performance (with tailwheel, at max T-O weight)

• Never-exceed speed: 93 kW (125 hp): 173 knots (322 km/h; 200 mph); 119 kW (160 hp): 211 knots (391 km/h; 243 mph)
• Max level speed at S/L: 93 kW (125 hp): 156 knots (290 km/h; 180 mph); 119 kW (160 hp): 200 knots (370 km/h; 230 mph)
• Max cruising speed at 2,285 m (7,500 ft): 93 kW (125 hp): 152 knots (282 km/h; 175 mph); 119 kW (160 hp): 181 knots (335 km/h; 208 mph)
• Stalling speed, flaps down: 93 kW (125 hp): 47 knots (87 km/h; 54 mph); 119 kW (160 hp): 51 knots (94 km/h; 58 mph)
• Stalling speed, flaps up: 93 kW (125 hp): 51 knots (94 km/h; 58 mph); 119 kW (160 hp): 53 knots (96 km/h; 60 mph)
• Max rate of climb at S/L: 93 kW (125 hp): 305 m (1,000 ft)/min; 119 kW (160 hp): 670 m (2,200 ft)/min
• Service ceiling: 93 kW (125 hp): 4,875 m (16,000 ft); 119 kW (160 hp): 6,400 m (2 1,000 ft)
• T-O run: 93 kW (125 hp): 198 m (650 ft); 119 kW (160 hp): 137 m (450 ft)
• T-O to 15 m (50 ft): 93 kW (125 hp): 320 m (1,050 ft); 119 kW (160 hp): 198 m (650 ft)
• Landing from 15 m (50 ft): 93 kW (125 hp): 290 m (950 ft); 119 kW (160 hp): 259 m (850 ft)
• Landing run: 93 kW (125 hp): 215 m (700 ft); 119 kW (160 hp): 168 m (550 ft)
• Range with standard fuel (75% power): 93 kW (125 hp): 416 nm (770 km; 480 miles); 119 kW (160 hp): 373 nm (692 km; 430 miles)
• Range with optional wingtip tanks: 119 kW (160 hp): 542 nm (1,005 km; 625 miles)

References

1. Photos, John Shupek, Copyright © 2009 Skytamer Images. ALL RIGHTS RESERVED
2. Taylor, John W.R. (ed.) Jane’s All The World’s Aircraft 1987-88. London, Jane’s Yearbooks, 1988, ISBN 0 7106-0850-0, pp 647.

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