1 engine

Philippine Aerospace Development Corp Defiant

TerryLeave a comment

In 1981 Gold Wings Aviation, a private company under Capt. Panfilo Villaruel Jr. (who later became chief of the Air Transportation Office (ATO) and president of the Philippine Aerospace Development Corporation (PADC)), conceived an aircraft research and development undertaking called the Norlindo program, named after one of its first engineers. The program covered a progressive development of a high-performance trainer primarily intended for use by the Philippine Air Force (PAF). The program was launched as an innovative step to build an aircraft of local design and utilizing indigenous materials. Out of these experiences, a single, piston engine trainer aircraft was conceived, designed, built and flown within three years.

The two-seat tandem Defiant prototype (registered as RP-X239) was a technical arrangement of various systems and parts taken from different types of aircraft in the PAF inventory. The landing gears, flight controls and flaps motor were taken from the Beechcraft T-34 Mentor, seats from the Cessna U-17B, rudder and brake pedals from the Boeing-Stearman PT-13 and various instrument items from the Britten-Norman BN-2 Islander, T-34 Mentor, Sikorsky S-76 and SIAI-Marchetti SF.260. The Defiant was powered by a single Lycoming IO-540-K1B5 piston engine on loan from the PADC, the same engine that powers the BN-2 Islander.

The airframe was fabricated from palosapis wood and the skin from tanguile veneer plywood. The engine mount was fabricated from chrome molybdenum steel and a one-piece plastic canopy was fabricated. Fuel tanks were constructed with 5052-H34 aluminum alloys. The development cost about 40 million.

Only one prototype was built, in 1986. The two-seater aircraft made its first flight on 22 February 1988, flying for about an hour.

Based on the successful flights of the prototype, Gold Wings planned to build another prototype of a modified Defiant (appropriately named Defiant 500) with an all-metal airframe and power rating increased to 500 hp. Due to lack of financial support from the government, the plan did not go ahead.

The Defiant 300 went on display in a hangar at the Philippine State College of Aeronautics.

Defiant 300
Engine: 1 × Textron Lycoming IO-540-K1B5, 224 kW (300 hp)
Wingspan: 9.52 m (31 ft 3 in)
Wing area: 12.55 m² (135.1 sq ft)
Airfoil: NACA 2418 (root), NACA 2412 (tip)
Length: 8.51 m (27 ft 11 in)
Height: 3.73 m (12 ft 3 in)
Empty weight: 1,278 kg (2,818 lb)
Max. takeoff weight: 1,583 kg (3,490 lb)
Maximum speed: 357 km/h (222 mph; 193 kn)
Stall speed: 110 km/h (68 mph; 59 kn) (flaps down)
Range: 1,896 km (1,178 mi; 1,024 nmi)
Service ceiling: 7,520 m (24,670 ft)
Rate of climb: 7.8 m/s (1,540 ft/min)
Crew: Two

Phelps Monoplane #1 / Z-281

TerryLeave a comment

Eber H Van Valkenberg Aircraft Co began building a three seat monoplane with side-by-side seating in a rear cabin and a forward cockpit that could be open or enclosed. It was sold to Dr Leland E Phelps of Toledo c.1928, who rebuilt and expanded the plane as a four place cabin. Designed by Dimas Ybarra using parts, instruments, etc, of the first plane, they built a new fuselage and wing, and received the same registration of NX4919 c/n 281. The old wing was destroyed and he gave the old fuselage to the Toledo Aviation Club for use in class work. It was never flown when called the Van Valkenberg.

Licensed as Phelps Monoplane #1 and also seen as Phelps Z-281, the registration was canceled on 10 September 1930.

Van Valkenberg
Engine: Ryan-Siemens SH-13, 70hp
Wingspan: 38’7″
Length: 24’7″
Seats: 3

Phelps
Wingspan: 41’6″
Length: 27’3″
Seats: 4

Pheasant Aircraft Traveler

TerryLeave a comment

The H-10 Pheasant was followed in 1928 by the Traveler single-seat cabin, high-wing monoplane with a cantilever gull-wing.

Following testing of the prototype NX174N by pilot Steve Wittman, two more Pheasant Travelers were built. One of them was equipped with a four-cylinder Cirrus Hermes engine producing 90 hp.

In 1929, Traveler was shown at the Detroit Air Show. In the same year, Steve Wittman participated in various air races in it, although without much success.

Engine: 55hp modified Ford A
Wingspan: 31’0″
Length: 23’6″
Max speed: 100 mph
Cruise: 85 mph
Stall: 35 mph
Seats: 1

Pheasant Aircraft Pheasant

TerryLeave a comment
Pheasant H-10 NC5609

Pheasant Aircraft Company’s first product in 1927 was the H-10 Pheasant (ATC 36) three-seat commercial biplane with 90 hp Curtiss OX-5 engine.

Designed by Lee Briggs and Orville Hickman and priced at $2,375-2,650, eleven were built.

Operations were sold and moved north in 1928 after Briggs was killed in a flying accident.

Engine: 90hp Curtiss OX-5
Wingspan: 32’4″
Length: 23’6″
Useful load: 785 lb
Max speed: 100 mph
Cruise: 85 mph
Stall: 35 mph
Range: 450-500 mi
Seats: 3

Phase 3 Eclipse

TerryLeave a comment

Single seat single engined high wing mono¬plane with conventional three axis control. Wing has elliptical planform and tapering chord; inverted V tail. Pitch/yaw control by elevon; roll control by wing warping; control inputs through stick for pitch/roll and pedals for yaw. Cantilever wing; wing profile; double surface. Undercarriage has three wheels in tricycle formation; suspension on all wheels. Push right go right nosewheel steering connected to yaw control. No brakes. Aluminium tube framework, without pod. Engine mounted below wing driving pusher propeller.

Conceived by J Bruce Emmons, the Eclipse was one of the new releases at Sun ‘n’ Fun of March 1983 at Lakeland, Florida. The Eclipse is also the first rigid wing ultralight to use wing warping for roll control (with the possible exception of the British Ladybird, which is not yet in production). With the Eclipse, the accent has been put on flight stability. The strength of the airframe has not been neglected, this ultralight having been static tested to as much as ± 9 g, more than the requirements for a light aircraft to be classed in the aerobatic category. The wings can be placed parallel with the framework by removing three bolts; demounted like that the machine can be transported either on a trailer or a roof rack. All the pieces in the kit are delivered pre formed, cut and drilled. Sold for $5495 in 1983, the kit thus provided is claimed to need only 30 h for completion.

Engine: KFM 107, 25 hp at 6000 rpm
Propeller diameter and pitch 54×23 inch, 1.37×0.58m
V belt reduction, ratio 2.0/1
Max static thrust 175 lb, 79 kg
Power per unit area 0.22 hp/sq.ft, 2.4hp/sq.m
Fuel capacity 5.0 US gal, 4.2 Imp gal, 18.9 litre
Length overall 14.0 ft, 4.27 m
Height overall 5.0ft, 1.52m
Wing span 32.2ft, 9.80m
Chord at root 4.0 ft, 1.22 m
Dihedral 0 deg
Tailplane span 8.0 ft, 2.44 m
Total wing area 114 sq.ft, 10.6 sq.m
Wing aspect ratio 9.1/1
Wheel track 4.0 ft, 1.22 m
Wheelbase 6.0 ft, 1.83 m
Nose¬wheel diameter overall 11 inch, 27 cm
Main wheels diameter overall 11 inch, 27 cm
Empty weight 165 lb, 75kg
Max take off weight 465 lb, 211kg
Payload 300 lb, 136kg
Max wing loading 4.071b/sq.ft, 19.9kg/sq.m
Max power loading 18.6 lb/hp, 8.4kg/hp
Load factors +6.0, 6.0 design; +9.0, 9.0 ulti¬mate
Max level speed 63 mph, 103kph
Max cruising speed 55 mph. 88kph
Economic cruising speed 50mph. 80kph
Stalling speed 25mph, 40kph
Best glide ratio with power off 15/1 at 35mph. 56kph
Range at average cruising speed 150 mile, 241 km

Phantom Aircraft Firecracker

TerryLeave a comment

Single seat single engined high wing monoplane with conventional three axis control. Wing has unswept leading and trailing edges, and constant chord; cruciform tail. Pitch control by elevator on tail; yaw control by fin mounted rudder; roll control by half span ailerons; control inputs through stick for pitch/roll and pedals for yaw. Wing braced from below by struts; wing profile; double surface. Undercarriage has three wheels in tricycle formation; suspension on all wheels. Push right go right nose-wheel steering connected to yaw control. Aluminium tube/steel tube framework, with optional pod. Engine mounted at wing height driving tractor propeller.

Phantom Aircraft Firecracker Article

This prototype was undergoing an intensive test flying programme in 1983.

Engine: Zenoah G25B, 22 hp at 6500 rpm
Power per unit area 0.14 hp/sq.ft, 1.6hp/sq.m
Fuel capacity 5.0 US gal, 4.2 Imp gal, 18.9 litre
Length overall 17.0 ft, 5.18 m
Height overall 7.0ft, 2.13m
Wing span 32.0ft, 9.75m
Constant chord 4.8 ft, 1.43 m
Sweepback 0 deg
Total wing area 150 sq.ft, 13.9 sq.m
Wing aspect ratio 6.8/1
Empty weight 216 lb, 98kg
Max take off weight 450 lb, 204kg
Payload 234 lb, 106kg
Max wing loading 3.0 lb/sq.ft, 14.6kg/sq.m
Max power loading 20.5 lb/hp, 9.3kg/hp
Load factors; +4.5, 3.0 ultimate
Max level speed 65 mph, 105 kph
Max cruising speed 55 mph, 88 kph
Stalling speed 25 mph, 40 kph
Max climb rate at sea level 600 ft/min, 3.0 m/s
Min sink rate 290 ft/min, 1. 5 m/s
Best glide ratio with power off 10/1
Take off distance 100ft, 30m
Landing distance 125ft, 38m
Service ceiling 10,000ft, 3050m
Range at average cruising speed 165 mile, 265 km

PGK PGK-1 Hirondelle

TerryLeave a comment

The PGK-1 Hirondelle was designed by Jean Peters, Glenn Gibb and John Kopala. The prototype aircraft C-GWYL (pictured) was six years in development and the designers main objectives were: to design a two-place aircraft that was safe and easy to fly; fast and maneuverable; comfortable and attractive; and easy and economical to build. The aircraft is well suited to first time builders. Engines of 100-125 hp.

Western Aircraft Supplies of Canada markets plans and some components to construct the PGK-1 Hirondelle two-seat monoplane.

Gross Wt. 1475 lb
Empty Wt. 933 lb
Fuel capacity approx. 28 USG
Wingspan 26’
Length 20’7”
Wing area: 117 sq.ft
Engine Lycoming O-235-CI8
Top speed 150 mph
Cruise 145 mph
Stall 61 mph
Climb rate 900 fpm
Takeoff run 750 ft
Ceiling 12,600 ft
Seats: 2