Two-seat light training and utility aircraft, certified in FAA Utility Category and approved for spinning. Suggested retail price of the standard aircraft in 1979 was 16 840 USD. Aircraft could be ordered with a Special Training Package (STP), which included a vacuum system and instruments, avionics, lighting and many other small additions to the aircraft. Almost all aircraft ordered were equipped with it. The STP costed 4180 USD and added 22 kg (48 lb) to the empty weight.
ICAO type designation is ‘PA38’.

last update: 4 October 2025

Aircraft is derived from single PA-38-100 prototype (which see). Prototype (N38PA, c/n 38-7738001) first flew in 1977. Company announced program in October 1977. Aircraft certified to FAR 23 on 23 March 1978, when production started. In 1980 the Tomahawk II was developed with more equipment and better soundproofing, production of the 'II' superseded the original model in 1981. A total of 2519 aircraft (Tomahawk and Tomahawk II) were manufactured between 1978 and 1982.

Shorts of Northern Ireland agreed to assemble the Tomahawk for the European market in early 1979, however, market conditions led to the abandonment of this plan.

wing: Cantilever low-wing monoplane, of all-metal construction with plastic wingtips, NASA GAW-1 section. Plain ailerons with no trim tabs. Thickness/chord ratio 17%, dihedral 5°, incidence 2° at wing root, wash-out 2°. Plain, manually actuated flaps.
fuselage: Light alloy, semi-monocoque structure, some plastics used in non-structural parts.
tail: Light alloy cantilever T-tail, elevator trim uses bungee, rudder has ground-adjustable tab.
landing gear: Fixed tricycle undercarriage with steerable nosewheel. Hydraulic disc brakes on main wheels.

engine: One Lycoming O-235-L2C horizontally-opposed, aircooled 4-cylinder engine, delivering 112 hp (84 kW) at 2600 rpm. Engine drives a 2-blade fixed-pitch metal propeller, manufactured by Sensenich. Propeller diameter 1.83 m (6.00 ft)
fuel system: Total fuel capacity 121 l (32 US gallon), usable capacity 114 l (30 US gallon) in two integral wing tanks; refueling point on top of each wing.

electrical system: 14V DC, 25Ah battery and 60A alternator.
hydraulic system: wheel brakes only.
vacuum system: engine-driven pump optional; standard with STP.

A wide selection of avionics was available; aircraft could be equipped for VFR, Night VFR and IFR flight. Piper offered avionics packages from several manufacturers consisting of a NAV/COM with indicator and associated wiring. Second NAV/COM, ADF, glideslope and marker beacon receiver, transponder, encoding altimeter and ELT could be ordered seperately.

Two seats, side-by-side, bubble cabin roof, with two forward-opening doors. Seats adjust fore and aft, and vertical. Ventilation, heating, and windscreen defrosting standard. Luggage space behind seats, capacity 45 kg (100 lb). Cabin has an integral roll-over support structure.

Not applicable.

External:
· wing span: 10.36 m / 34.00 ft
· overall length: 7.04 m / 23.10 ft
· overall height: 2.76 m / 9.06 ft
· wing chord, constant: 1.12 m / 3.67 ft
· tailplane span: 3.20 m / 10.50 ft
· wing area: 11.6 sq m / 125 sq ft
· wing aspect ratio: 9.3
· landing gear, wheelbase: 1.45 m / 4.76 ft
· landing gear, track: 3.05 m / 10.00 ft
· propeller ground clearance: 0.18 m / 0.60 ft

Internal:
· cabin length, instrument panel to rear bulkhead: 1.74 m / 5.71 ft
· cabin width: 1.07 m / 3.51 ft
· cabin height: 1.28 m / 4.20 ft
· luggage volume: 0.57 cu m / 20.1 cu ft

· max. t-o weight: 757 kg / 1670 lb
· empty weight: 512 kg / 1129 lb
· useful load: 245 kg / 540 lb
· max. luggage weight: 45 kg / 100 lb
· max. landing weight: 757 kg / 1670 lb
· wing loading: 65 kg/sq m / 13.4 lb/sq ft
· power loading: 6.8 kg/hp / 14.9 lb/hp

· never-exceed speed:
138 kts / 256 km/h
· max. speed, S/L:
109 kts / 202 km/h
· max. cruise speed, 75% power, 7100 ft:
108 KTAS / 200 km/h
· economy cruise speed, 65% power, 10500 ft:
100 kts / 185 km/h
· max. range, max. cruise speed, 7100 ft, with reserves:
452 nm / 837 km
· max. range, 65% power, 10500 ft, with reserves:
468 nm / 867 km
· service ceiling:
13000 ft / 3960 m
· max. rate of climb:
718 fpm / 3.7 m/s
· stall speed, all up:
52 kts / 96 km/h
· stall speed, flaps down:
49 kts / 91 km/h
· t-o run:
250 m / 820 ft
· t-o distance over 15 m (50 ft) obstacle:
445 m / 1460 ft
· landing distance over 15 m (50 ft) obstacle:
471 m / 1545 ft
· landing run:
215 m / 705 ft