Piasecki HUP Retriever

This article is about the Piasecki PV-14. For other uses of "H25", see H25 (disambiguation).

H-25/HUP Retriever
A U.S. Navy HUP-1 Retriever aboard the USS Midway (CVB-41) in the early 1950s
Role	Utility helicopter
Manufacturer	Piasecki Helicopter
First flight	March 1948
Introduction	1949
Retired	1964
Primary users	United States Navy United States Army Royal Canadian Navy French Navy
Number built	339

The Piasecki H-25 Army Mule/HUP Retriever was a compact single radial engine, twin overlapping tandem rotor utility helicopter developed by the Piasecki Helicopter Corporation of Morton, Pennsylvania during the late 1940s and produced during the early 1950s. The company changed its name in the 1956 to Vertol Aircraft Corporation and subsequently was bought by Boeing Aircraft Company in 1960, and became Boeing-Vertol.

Design and development

The design was a product of a competition by the U.S. Navy in 1945 for a compact utility/rescue helicopter to operate from ships including aircraft carriers, battleships, and cruisers. The prototype was designated as the XHJP-1, and first flew in March 1948. It was selected for production, as the HUP-1 in a side-by-side flight evaluation against the Sikorsky XHJS-1. It entered service with the navy in 1949.

Operational history

H-25A Army Mule preserved in the US Army Aviation Museum, Alabama

A U.S. Navy HUP plane guard doing its work in 1953

Versions of the HUP built for the U.S. Army were designated H-25 Army Mule. The tandem overlapping rotor configuration was a development by Piasecki and was used in future helicopter designs by the company and successors including the H-21, HRB-1/CH-46, and CH-47.

The design featured two three-bladed, 35-foot-diameter (11 m) rotors in tandem in which blades could be folded for storage. The HUPs were powered by a single Continental R975-46 radial engine, with a take-off rating of 550 hp (410 kW). To provide rescue without crew assistance, an electrically-operated door, available after folding the copilot’s seat forward, opened through which a rescue sling could be lowered from an overhead winch.

The HUP was produced for the navy in four versions: HUP-1, -2, and -3. The HUP-2 was the first production helicopter equipped with an auto-pilot. The US Navy also tested a system called 'Raydist that allowed an unmanned HUP-2 to be directed from a ground station and by radio ordered to hover within five feet of the desired point. Edo tested a HUP-2 with a fiberglass hull and outrigger floats for amphibious operations. In addition to those delivered to the U.S. Navy and Army the HUP/H-25 helicopter was also delivered to the Canadian and French Navies. A total of 339 aircraft were delivered over the 20-year life of the aircraft.

The US Army H-25 designation was adopted by the other services in 1962. The final units were withdrawn from US service in 1964. It also served with the French Navy from 1953 to 1965.

Variants

XHJP-1

First prototype, beat out Sikorsky S-53/XHJS-1 in competition for a shipboard utility helicopter. Piasecki-Vertol designation was PV-14

XHUP-1

The first two pre-production examples. Piasecki-Vertol designation was PV-16.

HUP-1

Utility transport, search and rescue helicopter for the US Navy, powered by a 525 hp (391 kW) Continental R-975-34 piston engine. 32 built. Piasecki-Vertol designation was PV-18.

HUP-2

Improved version, powered by a 550 hp (410 kW) Continental R-975-46 piston engine. 165 built for the US Navy, 15 for French Aeronavale. Redesignated UH-25B in 1962.

HUP-2S

Anti-submarine warfare version of HUP-2 fitted with a dunking sonar. 12 built

HUP-3

Utility transport version powered by a 550 hp (410 kW) Continental R-975-46A piston engine. Similar to the H-25A, later redesignated UH-25C in 1962. 30 built, including 3 for the Royal Canadian Navy.

H-25A Army Mule

Utility transport helicopter for the US Army, powered by a 550 hp (410 kW) Continental R-975-46A piston engine, fitted with large doors, power-boosted controls and strengthened floors. Seventy were delivered from 1953, but they were unsuitable for front-line use, with 50 transferred to the navy from 1955, and the remaining helicopters used for training, being withdrawn from army service by 1958.

UH-25B

HUP-2 redesignated after 1962.

UH-25C

HUP-3 redesignated after 1962.

Operators

Royal Canadian Navy HUP-3 at the Canadian Museum of Flight

Canada

• Royal Canadian Navy

France

• French Navy

United States

• United States Army
• United States Navy

Aircraft on display

• UH-25B Retriever 128479 on display at the American Helicopter Museum in West Chester, Pennsylvania.
• UH-25B Retriever 128519 on display at the Intrepid Sea, Air & Space Museum in New York City, New York.
• UH-25B Retriever 128596 on display at the Flying Leatherneck Aviation Museum in San Diego, California.
• UH-25B Retriever 130059 on display at the USS Midway Museum in San Diego, California.
• HUP-3 Retriever 147595 on display at the Pima Air & Space Museum in Tucson, Arizona.
• UH-25C Retriever 147607 on display at the National Naval Aviation Museum in Pensacola, Florida.
• HUP-3 Retriever 147610 in storage at Yanks Air Museum in Chino, California.
• HUP-3 Retriever 147628 on display at the Mid-America Air Museum in Liberal, Kansas.
• HUP-3 Retriever RCN 622 on display at The Helicopter Museum in Weston-super-Mare, England.
• H-25A Army Mule 51-16616 on display at the United States Army Aviation Museum in Fort Rucker, Alabama.
• H-25A Army Mule 51-16621 on display at Shearwater Aviation Museum in Shearwater, Nova Scotia, Canada.
• HUP-3 Retriever 51-16623 on display at the Canada Aviation and Space Museum in Ottawa, Ontario, Canada.

Specifications (HUP-3)

Data from

General characteristics

• Crew: 2 pilots
• Capacity: 4 passengers
• Length: 56 ft 11 in (17.35 m)
• Rotor diameter: 35 ft 0 in (10.67 m)
• Height: 12 ft 6 in (3.81 m)
• Disc area: 1,924 ft² (179 m²)
• Empty weight: 3,928 lb (1,782 kg)
• Loaded weight: 5,750 lb (2,608 kg)
• Max. takeoff weight: 6,100 lb (2,767 kg)
• Powerplant: 1 × Continental R-975-46A radial, 550 hp (410 kW)

Performance

• Maximum speed: 105 mph (169 km/h)
• Range: 340 mi (547 km)
• Service ceiling: 10,000 ft (3,048 m)
• Rate of climb: 100 ft/min (5.01 m/s)
• Disc loading: 3 lb/ft² (15 kg/m²)
• Power/mass: 0.09 hp/lb (0.16 kW/kg)

See also

Related development

• Piasecki H-21
• CH-46 Sea Knight

Aircraft of comparable role, configuration and era

• Bristol Belvedere

References

Notes

Bibliography

• Harding, Stephen. U.S. Army Aircraft Since 1947. Shrewsbury, UK:Airlife, 1990. ISBN 1-85310-102-8.

External links

• H-25 US Army Aviation history fact sheet