Piper Tomahawk

The Piper PA-38 Tomahawk is one of general aviation's most polarizing aircraft. Produced from 1978 to 1982 with approximately 2,484 airframes built, the Tomahawk was Piper's purpose-designed competitor to the Cessna 152 in the two-seat trainer market. What made it controversial was not its conception but its execution: Piper solicited input from thousands of flight instructors who asked for an airplane that would honestly demonstrate stall and spin behavior rather than hiding it, then delivered an aircraft whose production stall characteristics differed significantly from the prototype that earned its type certificate.

The Tomahawk features a distinctive T-tail configuration and a NASA-developed GAW-1 (General Aviation Whitcomb) airfoil, making it visually and aerodynamically unlike any other two-seat trainer. The T-tail provides excellent pitch authority in normal flight and the wide, car-like cabin offers outstanding visibility. The low wing gives the aircraft a sporty feel that many pilots genuinely enjoy, and its responsive handling makes it a more engaging airplane to fly than the Cessna 150/152. The same Lycoming O-235-L2C engine that powers the Cessna 152 produces 112 HP in the Tomahawk (vs. 110 HP in the 152), giving it essentially identical power.

Despite the well-publicized spin controversy, the AOPA Air Safety Foundation found that the Tomahawk actually has a one-third lower overall accident rate per flying hour than its Cessna counterparts. However, while overall accidents were lower, fatal spin accidents were disproportionately higher, which is what drove the aircraft's reputation. Today the Tomahawk survives as one of the cheapest certified aircraft you can buy, appealing to budget-minded pilots who appreciate its honest handling and distinctive character.

There was no 1980 model year production. Both labels describe the same certificated airplane -- one section, one model, on TCDS A18SO (see raw/tcds/cert-pa38-112-a18so-rev6-2026-09-08.md). "Tomahawk II" is Piper's production-run marketing name for the post-1980 airplane with the improvements above, not a distinct type-certificate model, and the splitting rule's Step 1 hard-split tests (engine, engine class, seats, gear, pressurization, type certificate) all fail to fire between them -- they belong on one page, with the difference carried in this table, exactly as written here.

The cruise/burn/range triple above is drawn from ONE labeled example on a nomogram, not a table row. POH Report 2126's Speed Power chart (Fig 5-19, Best Power Mixture) is a connected-line chart of pressure altitude, OAT and %power against true airspeed, and it carries exactly one fully worked example: OAT +3C, 3,300 ft pressure altitude, 65% power -- 93 KTAS, burning 5.75 gph (from the chart's own fuel-flow table) for 410 nm with a 45-minute reserve (Fig 5-23). 65% is used here instead of the house-preferred 75% because this chart states no example at 75% at all -- the curve is drawn but unlabeled, and tracing an unlabeled nomogram intersection is a guess wearing a citation, which this catalogue declines to do. The Best Economy Mixture chart (Fig 5-21) gives a genuine second row at the SAME conditions: 88.5 KTAS on 4.9 gph for 460 nm with reserve (Fig 5-25) -- slower and leaner than the Best Power row, as the economy row must be.

Rate of climb is deliberately left blank in frontmatter. The climb chart's (Fig 5-13) only labeled example is also away from sea level -- 3,300 ft / +3C, 580 fpm -- and the sea-level/standard-day crossing on the same chart is not itself labeled. That 580 fpm figure is recorded in performance/piper-pa38-tomahawk.climb.json rather than invented into the sea-level field.

Takeoff and landing ground roll come from the POH's own worked examples, at the POH's own (non-standard) conditions: 840 ft takeoff ground roll at +30C (a hot day, not ISA's +15C), zero flaps, 10 kt headwind, lift-off at 53 KIAS; 720 ft landing ground roll at +13C with a 2 kt TAILWIND, second-notch flaps, power-off approach at 62 KIAS, full stall touchdown. Neither over-50-ft companion chart was read this session -- those two fields carry forward the prior pass's unsourced figures and are flagged validator_exempt rather than claimed as sourced.

Stall speeds (Vs0 ~47, Vs1 ~52 KIAS) come from POH Fig 5-2's stall-speed-vs-bank-angle chart, 1670 lb. The chart's only exactly labeled point is 53 KIAS at 30 degrees of bank (flaps up); the wings-level reading used here carries roughly +/-1-2 knots of reading uncertainty at this scan's grid resolution, noted rather than hidden.

The Tomahawk's two-seat, low-payload configuration is the simplest weight-and-balance scenario in aviation.

Standard Tanks (30 gal usable / 180 lbs fuel)

Two average adults with full fuel leaves virtually no margin for baggage and approaches max gross weight; two larger adults will exceed gross weight with full fuel -- typical for this class of two-seat trainer.

The useful load of 542 lbs is comparable to the Cessna 152's 589 lbs; both max out at 1,670 lbs gross, so the Cessna's edge comes from a lighter empty weight rather than a higher gross weight.

Most Tomahawks in the used market have basic VFR panels reflecting their training heritage.

Budget VFR ($20,000-$30,000 aircraft): Original King or Narco nav/coms (often non-functional), basic transponder (may not be ADS-B compliant), portable GPS.

Updated VFR/IFR ($30,000-$45,000 aircraft): Garmin GTR 225 or GNC 255 com, Garmin GNS 430W or GTN 650Xi, Garmin GTX 345 transponder, Garmin G5 replacing a vacuum attitude indicator.

Panel space is tight -- a GTN 750Xi is a very tight fit. Most owners who invest in avionics keep it simple: one modern GPS/com, an ADS-B-compliant transponder, and perhaps a G5.

Sparrowhawk Engine Conversion -- the most notable performance STC. Raises the O-235's compression ratio to a net 125 hp, improving climb and cruise meaningfully.

Auto Fuel STC (Petersen Aviation SA02231LA and related approvals) -- as with the Cessna 152's O-235 family, the mogas STC is the single most cost-effective modification, allowing ethanol-free 87 AKI auto gasoline and cutting fuel cost meaningfully against 100LL.

Limited STC ecosystem otherwise. With only ~2,484 airframes built, the aftermarket for wheel pants, STOL kits and other common trainer modifications is sparse compared to the Cessna 150/152 line.

Parts availability: Declining. With only ~2,484 airframes built (against 7,500+ Cessna 152s and 23,000+ 150s), the parts ecosystem is thin and thinning. Piper/Textron support is inconsistent and pricey; third-party suppliers (Aircraft Spruce, Univair) carry common items; salvage yards are a real source for Tomahawk-specific parts. The Lycoming O-235 itself is universally supported (shared with the Cessna 152), so engine parts are not a concern.

Mechanic familiarity: Moderate. The T-tail, unique wing design and Tomahawk-specific systems reward finding a mechanic with real type experience, particularly for annuals.

Expensive items to watch: engine overhaul ($35,000 national specialty-shop tier for the O-235 family, per reference/engine-overhaul-pricing.md); vertical stabilizer attachment plate replacement (~40 hrs labor at the 3,000-hr life limit); nose gear shimmy damper (recurring, $500-$1,500); propeller overhaul ($1,500-$2,500 at 5-year/2,000-hr intervals, fixed-pitch).

Market snapshot, ASKING, dated 2026-07-14 (Trade-A-Plane + Barnstormers, 4 listings): $38,000-$59,950, average $45,950 from 3 priced listings. See Current Listings below. Per runbook rule 27, this is the TOP of a realistic range, not a settled sale price -- price_min_usd is set a little under the lowest observed listing to cover rougher, unlisted project airplanes.

Key value drivers: Tomahawk II vs. original (10-20% premium for cabin heat, corrosion protection and factory AD compliance); engine time (O-235 overhaul is the primary value driver); stall-strip AD compliance (non-negotiable, must be verified); corrosion condition (especially pre-1981 airplanes); ADS-B compliance (table stakes now); Sparrowhawk conversion (adds real value and real performance).

AD 83-14-08 (Stall Strips) -- see Safety Record above. Mandated September 1983; verify compliance on any pre-buy. Every Tomahawk II left the factory with it installed.

AD -- Vertical Stabilizer Attachment Plate -- a 3,000-hour life limit on the T-tail's vertical stabilizer attachment plate, replacement runs roughly 40 hours of labor. A real, structurally important inspection item on the T-tail design.

Other common issues:

• Cabin heat inadequacy on early (1978-1979) airplanes -- addressed in the Tomahawk II.
• Elevator trim system -- slow and imprecise on early airplanes, improved in the Tomahawk II.
• Nose gear shimmy -- common, addressed with shimmy-damper maintenance.
• Corrosion -- pre-Tomahawk-II airplanes lack the zinc-chromate treatment; inspect thoroughly, especially in humid or coastal environments.
• O-235 and 100LL -- the O-235-L2C is a high-compression variant Piper specifies at 100/130 minimum grade avgas; lead fouling, valve guide wear and spark-plug contamination are the same chronic O-235 issues discussed on the Cessna 152 page.

Pre-buy red flags: missing stall-strip AD compliance (walk away or price accordingly); vertical stabilizer attachment plate approaching 3,000 hours; pre-Tomahawk-II airplane with no visible corrosion treatment; high-time training engine with lead damage (borescope, check valve guides); logbook gaps (common on training aircraft that changed hands often).

The Tomahawk's insurance picture reflects awareness of the spin history even though the overall accident rate is reported lower than comparable types.

• Liability only: $225-$275/yr (qualified pilots, 500+ hours); $325-$530/yr (less experienced).
• Full hull + liability: $600-$800/yr (qualified pilots); $1,000-$1,500/yr (student/low-time); typical insured hull value $25,000-$40,000.
• Some insurers may require spin-training endorsements; flight-school use faces additional scrutiny versus a comparable Cessna trainer; low hull values keep absolute premium dollars manageable even at a somewhat higher rate.

See GA Insurance Underwriting for general GA insurance factors.