Pitcairn PA-34

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Pitcairn PA-33 / PA-34
Pitcairn PA-33 (YG-2) - "NACA 88" wreckage.jpg
The wreckage of the YG-2 after crashing on 20 March 1936
Role reconnaissance autogyro
National origin United States
Manufacturer Pitcairn
First flight 1936
Number built 1 x PA-34, 1x PA-33

The Pitcairn PA-34 and Pitcairn PA-33, given the United States Navy (USN) designation Pitcairn OP-2 and United States Army (US Army) designation Pitcairn YG-2 respectively were reconnaissance auto-gyros designed and built in 1936 for evaluation.

Design and development[edit]

The Pitcairn Aircraft Company built and developed auto-gyros under licence from the Cierva Autogiro Company, trading as the Pitcairn-Cierva Autogiro Company from the late 1920s. Interest in the auto-gyro by the USN resulted in the purchase of two Pitcairn PCA-2 autogyros, modified as two-seat observation platforms, designated XOP-1. Trials with the XOP-1s from 1931 had limited success, but included an operational deployment in Nicaragua from June 1932, with the United States Marine Corps (USMC).[1]

Following the development of much-improved rotor and control systems, further interest by US armed forces resulted in the Pitcairn PA-33 (YG-2) and Pitcairn PA-34 (XOP-2). These essentially identical aircraft differed mainly in undercarriage design; the PA-33 had fully cantilevered oleo-pneumatic undercarriage legs and the PA-34 had strut mounted split axles with oleo-pneumatic shock-absorbers attached to the top fuselage longerons.[1]

The fuselage was constructed of welded steel tube with fabric covering and light alloy fairings. The 3-bladed folding rotor was mounted on a braced bi-pod with legs fore and aft of the front cockpit. The tail unit consisted of a very wide chord fin and rudder with a strut supported tail-plane sporting up-turned wing-tips. Tail surfaces were constructed of wood with fabric covering and rotor blades were built with steel tube spars and plywood ribs with fabric covering.[1]

Accommodation was in tandem cockpits with the pilot in the rear cockpit aft of the rotor support bi-pod and the observer in the front cockpit beneath the rotor head.[1]

Power was supplied by a nose mounted 420 hp (310 kW) Wright R-975E-2 in a tight fitting wide chord cowling with blisters to accommodate rocker arms. The engine was mounted with considerable nose-down angle to ensure prop-wash over the rotor to maintain rotation and ease rotor starting.[1]

Control of the aircraft was achieved only by use of the throttle and the tilting rotor-head, operated by a hanging control stick in the rear cockpit.[1]

Operational history[edit]

The YG-2 and OP-2 were briefly tested by the US Army and US Navy with limited success. After completing tests with the US Army the YG-2 was taken over by the National Advisory Committee for Aeronautics (NACA). registered as NACA 88. On 30 March 1936, whilst on test, NACA 88 suffered a rotor failure, prompting the crew to perform the first successful bail-out from a rotary-winged aircraft.[2]

Variants[edit]

PA-33
Company designation of the YG-2 for the US Army
PA-34
Company designation of the OP-2 for the US Navy
YG-2
US Army trials autogyro (PA-33), 1 built.
XOP-2
US Navy trials autogyro (PA-34), one built.

Specifications (PA-33 / PA-34)[edit]

Data from Jane's all the World's Aircraft 1938[1]

General characteristics

  • Crew: 2
  • Length: 43 ft 5 in (13.23 m) blades folded
  • Width: 15 ft 0.1 in (4.575 m) blades folded
  • Height: 11 ft 7 in (3.52 m)
  • Empty weight: 2,300 lb (1,043 kg)
  • Gross weight: 3,300 lb (1,497 kg)
  • Fuel capacity: fuel 66 US gal (55 imp gal; 250 l); oil 6.5 US gal (5.4 imp gal; 25 l)
  • Powerplant: 1 × Wright R-975E-2 9 cylinder air-cooled radial piston engine, 420 hp (310 kW)
  • Main rotor diameter: 50 ft (15 m)
  • Propellers: 2-bladed variable pitch metal propeller

Performance

  • Maximum speed: 140 mph (225 km/h; 122 kn) at sea level, 128 mph (111 kn; 206 km/h) at 8,900 ft (2,700 m)
  • Cruise speed: 115 mph (185 km/h; 100 kn) at sea level
  • Minimum control speed: 22 mph (35 km/h; 19 kn)
  • Endurance: 3.26 hours at cruising speed
  • Service ceiling: 15,500 ft (4,700 m)
  • Time to altitude: 5,000 ft (1,500 m) in 3.8 mins
  • Take-off distance: 135 ft (41 m) in dead calm: 0 ft (0 m) in 28 mph (24 kn; 45 km/h) wind
  • Landing run: 0 ft (0 m)

References[edit]

  1. ^ a b c d e f g Grey, C.G.; Bridgman, Leonard, eds. (1938). Jane's all the World's Aircraft 1938. London: Sampson Low, Marston & company, ltd. p. 279c. 
  2. ^ "ASN Wikibase Occurrence # 120913". Aviation Safety Network. Retrieved 1 September 2017.