Mudrovcich Pearce 1903 replica

Aucklander Ivan Mudrovcich, a retired automotive engineer, has spent the past 10 years building a replica of the Canterbury farmer’s controversial aircraft, which some say pre-dated the first flight of the Wright brothers in December 1903.

Mudrovcich Pearce 1903, ZK-RPT

The fuel has to be mixed from kerosene, ethanol and paraffin to replicate what was used more than 100 years ago.
“Richard Pearse had to go to the chemist to buy his fuel,” said Mr Mudrovcich. Once it has started, its running time is short and the engine gets dangerously hot. “We’ve had eight minutes out of it. We have a rule after it has run that we don’t go near it for a quarter of an hour,” he said.

When not in use, the dismantled aircraft is stored at home. “I keep it in the garage at home. I also keep parts of it under the bed, in the living room, everywhere,” he said.
The replica takes up most of a small hangar at Hood Aerodrome and consists of an engine on a wooden tricycle undercarriage. The 13m wingspan is made of bamboo and steel tubes covered with linen. It is registered as a microlight and has a licence number, ZK-RPT. Whether it can actually fly is unknown.

“We haven’t explored its capabilities and we are reluctant to fly it here. We will be firing it up and maybe taxiing it,” said pilot Neville Hay. “Never fly higher than you can jump.”

Serial: 002

MTR / MAN/Rolls-Royce/Turboméca MTR390

The MTU Turbomeca Rolls-Royce MTR390 is a turboshaft developed for light helicopter applications by MTU Turbomeca Rolls-Royce (MTR). The engine is designed to power helicopters in the weight range of 5-7 tonnes in both single and twin engine configurations. So far the only application is the Eurocopter Tiger. Test runs of the MTR390 began in 1989 and the first test flight was performed in 1991. The MTR390 received military certification in May 1996 and civil approval in June 1997.
An uprated version, the MTR390-E (Enhanced), was being developed with Spain’s ITP.

Applications:
Eurocopter Tiger

Specifications:
MTR390
Type: Centrifugal Turboshaft
Length: 42.4 in (108 cm)
Diameter: 26.8 in (68 cm)
Dry weight: 372 lb (169 kg)
Compressor: Centrifugal, 2 stage
Combustors: Annular
Turbine: 1 stage high pressure turbine, 2 stage low pressure turbine
Maximum power output: 1465 shp
Overall pressure ratio: 13:1
Specific fuel consumption: 0.46 lb/shp-hr

MSW Aviation Votec Evolaris

The steel tube hull with carbon fiber covering is for the first time a divisible, also made of carbon fiber, wing. The plug-in wing halves allow for rapid assembly and dismantling, as well as the simple transport of the aircraft in a specially designed transport trailer.

At the AERO 2017 MSW presented the project Evolaris, an electric aerobatic plane with an empty weight of 500kg and 221Kw electric motor power.

Engine: Evo220, 221 kW / 300 hp
Wing span: 6.27m
Length: 6.0m
Wing area: 7.58 sq.m
Empty weight: 500kg
MTOW: 650kg
Roll rate: 460 ° / sec
Load: +/- 10g
Stall speed: 65mph
Never exceed speed: 270mph
Endurance: 20min + 5min reserve

MSW Aviation Votec 252T

The Votec 252T is a side-by side seat single engine kitbuilt light-sport development of MSW’s earlier tandem seat Votec 322 aircraft. The prototype, powered by a modified Lycoming IO-540-J3A5 flat-six engine, marries the wooden wings and empennage to a new, carbon fibre fuselage, though a carbon fibre wing is under development. All flying surfaces are straight tapered and square tipped, the wing low mounted and the tailplane located on the upper fuselage; the rudder extends down to the keel. The ailerons are balanced with external spades.

The Votec 252T has a cabin over the wing, with baggage space behind the seat, under a single piece canopy. It has a fixed tricycle undercarriage with fuselage mounted cantilever legs and with speed fairings on all wheels. The nosewheel casters; there is a small tailskid for rudder protection.

Designed by MSW Aviation and built by Wassmer Aviation in Switzerland, the first prototype flew on 26 June 2009, by October 2011 only the first prototype had flown. A second prototype with a 260 kW (350 hp) Lycoming AEIO-580 engine, redesignated the Votec 352T, was under development but had not flown by October 2011.

252T
Powerplant: 1 × Lycoming AEIO-540-X, 190 kW (250 hp)
Propellers: 4-bladed MT-Propeller MTV-14 constant speed, 1.95 m (6 ft 5 in) diameter
Length: 6.75 m (22 ft 2 in)
Wingspan: 7.70 m (25 ft 3 in)
Height: 2.20 m (7 ft 3 in)
Wing area: 11.28 sq.m (121.4 sq ft)
Aspect ratio: 5.3
Empty weight: 630 kg (1,389 lb)
Max takeoff weight: 950 kg (2,094 lb)
Fuel capacity: 166 kg / 365 lb / 240 lt
Cruising speed: 306 km/h (190 mph; 165 kn)
Stall speed: 106 km/h (66 mph; 57 kn)
Never exceed speed: 433 km/h (269 mph; 234 kn)
Range: 1,398 km (869 mi; 755 nmi)
g limits: +8/-8
Rate of climb: 17.8 m/s (3,500 ft/min) maximum from sea level
Landing and take-off runs: 300 m
Crew: one
Capacity: one passenger

MSW Aviation Votec 322

After 3 ½ years in the workshop of MSW Aviation AG in Wohlen came the first designs for the new kit airplane. A goal was to build in Switzerland an aerobatic aircraft. The prototype HB-YJY first flew on 6 April 2001 in Buochs, Switzerland. After 1 ½ years, the intensive test flight phase was completed without any incidents in November 2002.

On 9 April 2003 the second VOTEC 322 was completed, HB-YLA SN003. The airplane was built in approx. 12 months. Technically the airplane was revised and optimized, which led to that the machine approx. 30 kg lighter than the prototype YJY. HB-YLA was introduced to the public at the AERO 03 in Friedrichshafen.

The VOTEC 322 performs on the level of the Sukhoi and Cap. Weighing approximately 650 kg, it is powered by a 330 HP Lycoming engine. The maximum speed is 400 km/h. Accelerations of 10 G’s are problem-free in the ergonomic cabin layout for the pilot, with a cruising speed of 300 km/h and a range by approx. 1000 km. The span is 7,30 m.

The airplane was available in kit form for home building building.

MSW Aviation AG

Max Vogelsang
Rigackerstrasse 24
CH-5610 Wohlen
Switzerland

MSW Aviation was founded 1991 by Max Vogelsang in Wohlen. From his many years of experience in racing, aircraft construction and renovation of the most diverse types, the desire to create an own design for aerobatics resulted in the first Votec 322.

M-Squared Breese DS

The Breese DS and Breese 2 models are LSA legal.

Breese DS
Cruise: 65 mph
Stall: 34 mph
Range: 150 sm
Rate of climb: 625 fpm
Takeoff dist: 425 ft
Landing dist: 300 ft
Engine: Rotax 582, 65 hp
HP range: 42-75
Fuel capacity: 16 USG
Empty weight: 485 lb
Gross weight: 1000 lb
Length: 21.6 ft
Wing span: 30 ft
Wing area: 168 sq.ft
Cockpit width: 60
Seats: 1 in
Landing gear: nosewheel

Breese SS
Engine: Rotax 447, 42 hp
HP range: 42-65
Cruise: 46 mph
Stall: 24 mph
Range: 130 sm
Rate of climb: 975 fpm
Takeoff dist: 75 ft
Landing dist: 50 ft
Fuel capacity: 16 USG
Empty weight: 330 lb
Gross weight: 650 lb
Length: 19 ft
Wing span: 30 ft
Wing area: 168 sq.ft
Seats: 1
Landing gear: nosewheel

Breese 2
Engine: Rotax 503, 48 hp
HP range: 42-75
Cruise: 51 mph
Stall: 27 mph
Range: 150 sm
Rate of climb: 925 fpm
Takeoff dist: 80 ft
Landing dist: 60 ft
Fuel capacity: 16 USG
Empty weight: 335 lb
Gross weight: 650 lb
Length: 19 ft
Wing span: 30 ft
Wing area: 168 sq.ft
Cockpit width: 60 in
Seats: 1
Landing gear: nosewheel

M-Squared Sport 1000 / Sprint 1000

Designed in 1996.
The Sport 1000 is LSA legal.

Sport 1000
Engine: Rotax 582, 65 hp
HP range: 50-115
Cruise: 74 mph
Stall: 39 mph
Range: 260 sm
Rate of climb: 625 fpm
Takeoff dist: 425 ft
Landing dist: 300 ft
Fuel capacity: 16 USG
Empty weight: 625 lb
Gross weight: 1000 lb
Length: 21.6 ft
Wing span: 32.7 ft
Wing area: 180 sq.ft
Cockpit width: 50 in
Landing gear: nosewheel

Sprint 1000
Cruise: 58 mph
Stall: 27 mph
Range: 110 sm
Rate of climb: 650 fpm
Takeoff dist: 135 ft
Landing dist: 60 ft
Engine: Rotax 582, 65 hp
HP range: 50-115
Fuel capacity: 16 USG
Empty weight: 465 lb
Gross weight: 1400 lb
Wing span: 32.8 ft
Wing area: 180 sq.ft
Landing gear: nosewheel