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Piper PA-38 Tomahawk

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PA-38 Tomahawk
Role Light aircraft
Manufacturer Piper
Introduction 1978
Produced 1978–1982
Number built 2,484

The Piper PA-38-112 Tomahawk is a two-seat, fixed tricycle gear general aviation airplane, originally designed for flight training, touring and personal use.

Design and development

The axe logo was applied at the Piper factory to many PA-38s delivered

The Tomahawk is a single-engined low-wing cantilever monoplane with a T-tail and an enclosed cabin for two. It has a fixed tricycle landing gear and is powered by a Lycoming O-235 four-cylinder piston engine with a twin-bladed tractor propeller. The Tomahawk has two front-hinged doors for access to the cabin.

The Tomahawk was Piper's attempt at creating an affordable two-place trainer. Before designing the aircraft, Piper widely surveyed flight instructors for their input into the design. Instructors requested a more spinnable aircraft for training purposes, since other two-place trainers such as the Cessna 150 and 152 were designed to spontaneously fly out of a spin. The Tomahawk's NASA[1] GA(W)-1 Whitcomb airfoil addresses this requirement by making specific pilot input necessary in recovering from spins, thus allowing pilots to develop proficiency in dealing with spin recovery.

The Tomahawk was introduced in 1977 as a 1978 model. The aircraft was in continuous production until 1982 when production ended, with 2,484 aircraft built.

The 1981 and 1982 models were designated as the Tomahawk II. They incorporated improved cabin heating and windshield defroster performance, an improved elevator trim system, improved engine thrust vector, 100% airframe zinc-chromate anti-corrosion treatment, better cockpit soundproofing, larger 6" wheels and tires for greater propeller ground clearance and improved performance on grass and dirt runways, among other enhancements.

Operational history


As of 2020, a handful of Tomahawks are currently being used to train Australian Air Force Cadets in flight courses. These are operated from RAAF Base Amberley by 211 Squadron AAFC. These aircraft have been in service since the early 2000s.[2]

Safety record

Stall strips were applied to the leading edge.

According to the Aircraft Owners and Pilots Association Air Safety Foundation, which published a Safety Highlight report on the Piper Tomahawk, the Piper Tomahawk has a one-third lower accident rate per flying hour than the comparable Cessna 150/152 series of two-place benchmark trainers. The Tomahawk has a higher rate of fatal spin accidents per flying hour. The National Transportation Safety Board (NTSB) estimated that the Tomahawk's stall/spin accident rate was three to five times that of the Cessna 150/152.[3]

According to the NTSB, the Tomahawk's wing design was modified after FAA certification tests, but was not retested.[3] Changes included reducing the number of full wing ribs and cutting lightening holes in the main spar.[4] The aircraft's engineers told the NTSB that the changes made to the design resulted in a wing that was soft and flexible, allowing its shape to become distorted and possibly causing unpredictable behavior in stalls and spins.[4] The design engineers said that the GAW-1 airfoil required a rigid structure because it was especially sensitive to airfoil shape, and that use of a flexible surface with that airfoil would make the Tomahawk wing "a new and unknown commodity in stalls and spins."[4]

Airworthiness Directive 83-14-08 issued in September 1983 mandated an additional pair of stall strips to be added to the inboard leading edge of the PA-38 wing to "standardize and improve the stall characteristics".[5]

Specifications (PA-38-112 Tomahawk II)

3-view line drawing of the Piper PA-38 Tomahawk
3-view line drawing of the Piper PA-38 Tomahawk

Data from Janes's All The World's Aircraft 1982–83[6]

General characteristics

  • Crew: one
  • Capacity: one passenger
  • Length: 23 ft 1+14 in (7.042 m)
  • Wingspan: 34 ft 0 in (10.36 m)
  • Height: 9 ft 0+34 in (2.762 m)
  • Wing area: 124.7 sq ft (11.59 m2)
  • Aspect ratio: 9.27:1
  • Airfoil: NASA GAW-1
  • Empty weight: 1,128 lb (512 kg)
  • Max takeoff weight: 1,670 lb (757 kg)
  • Fuel capacity: 30 US gal (25 imp gal; 110 L) usable
  • Powerplant: 1 × Avco Lycoming O-235-L2C air-cooled flat-four piston engine, 112 hp (84 kW)
  • Propellers: 2-bladed Sensenich metal fixed-pitch propeller, 6 ft 0 in (1.83 m) diameter


  • Maximum speed: 126 mph (203 km/h, 109 kn) at sea level
  • Cruise speed: 115 mph (185 km/h, 100 kn) at 10,500 ft (3,200 m) (65% power)
  • Stall speed: 56.5 mph (90.9 km/h, 49.1 kn) (flaps down, IAS)
  • Never exceed speed: 159 mph (256 km/h, 138 kn) (IAS)
  • Range: 539 mi (867 km, 468 nmi) at 10,500 ft (3,200 m) (65% power)
  • Service ceiling: 13,000 ft (4,000 m)
  • Rate of climb: 718 ft/min (3.65 m/s)
  • Takeoff run to 50 ft (15 m): 1,460 ft (450 m)
  • Landing run from 50 ft (15 m): 1,544 ft (471 m)

See also


Aircraft of comparable role, configuration, and era


  1. ^ "Low Speed, Medium Speed, and Natural Laminar Flow Airfoils". Concept to Reality: Contributions of the NASA Langley Research Center to U.S. Civil Aircraft of the 1990s. Archived from the original on January 13, 2010. Retrieved 2006-08-08.
  2. ^ "ADF SERIALS". ADF Serials. 2019. Retrieved 20 April 2020.
  3. ^ a b Sweeny, Michael (July 25, 1997). "NTSB recommends new round of Tomahawk tests". GA News & Flyer. Archived from the original on 2000-10-21.
  4. ^ a b c "CHI94FA097". National Transportation Safety Board. July 12, 1995. Retrieved 2008-08-07.
  5. ^ Federal Aviation Administration (September 1983). "Airworthiness Directive 83-14-08". Archived from the original on 2016-11-23. Retrieved 2008-08-07.
  6. ^ Taylor 1982, pp. 446–447.


  • Taylor, John W.R. Jane's All The World's Aircraft 1982–83. London:Jane's Yearbooks, 1982. ISBN 0-7106-0748-2.