Evektor EV-55 Outback

The Evektor EV-55 Outback is a twin-turboprop, high-wing, unpressurized utility aircraft designed and built in the Czech Republic by Evektor-Aerotechnik in Kunovice. Conceived as a lower-cost, more economical alternative to the Cessna Grand Caravan 208B and de Havilland Canada DHC-6 Twin Otter, the EV-55 targets the 9-to-14 seat light utility market for passenger, cargo, parachute, medevac, surveillance, and bush operations. The prototype first flew on 24 June 2011, a second prototype followed, and a static test airframe was built — three airframes total. Despite over a decade of development and a high-profile Malaysian investment partnership, the aircraft has never achieved type certification and no production examples exist. As of 2026, the program remains in limbo and the two flying prototypes are used primarily for research programs (including the EU Clean Sky 2 COAST avionics demonstrator). Buyers encountering an EV-55 for sale should understand they are acquiring an uncertified prototype, not a production utility twin comparable to the Britten-Norman BN-2B Islander.

Book numbers reflect manufacturer claims from the prototype flight test program, not certified AFM data — and even those claims are thinner than they first look. Evektor's own technical specification publishes a maximum speed of 220 kt at 10,000 ft, not a cruise speed at any stated power setting — its cruise-speed field is blank. Quoting 220 kt as "cruise," as this page previously did, describes a flight the manufacturer itself never claimed; it is not stored as cruise_speed_ktas for that reason. The same spec sheet publishes no climb rate, no service ceiling, and no fuel burn at all — the 1,673 fpm and 29,000 ft this page previously carried had no citation and are removed rather than repeated.

The aircraft was designed for short, unimproved strip operations — the manufacturer's own prose (not its spec table) claims a 410 m takeoff and 520 m landing, but does not say whether that is ground roll or the distance over a 50 ft obstacle, so it is not filed into either schema field (see validator_exempt) and is quoted here only as a manufacturer claim: a 410 m distance at 10,141 lb max gross would be aggressive either way for a twin this size. Single-engine climb (~450 fpm, sometimes quoted for this type) and the unpressurized cabin's practical altitude ceiling (well below any stated service ceiling) are likewise carried in prose only, as unsourced manufacturer-adjacent claims rather than stored figures, because no document located this session states them.

With a 4,416 lb useful load and 3,651 lb of max fuel (545 gal of Jet-A at 6.7 lb/gal — corrected this session from a previous, understated 380 gal that did not match Evektor's own published fuel weight), the EV-55 has genuinely impressive cabin load capability:

• Full fuel + cabin load: 545 gal fuel = 3,651 lb, leaving 765 lb for crew, passengers, and cargo — enough for 2 pilots (400 lb) and roughly two passengers, well short of a full 9-seat cabin. Evektor's own published range figure (925 nm) is stated at a 2,000 lb payload condition, not full fuel plus a full cabin — those are two different loadings, and the page does not combine them into one claim.
• Full cabin, reduced fuel: With 9 passengers plus 2 pilots at 180 lb each (1,980 lb) and the balance of the 4,416 lb useful load as fuel (2,436 lb = 364 gal), the airplane is well within its fuel tankage; no fuel burn figure is published anywhere located this session, so an endurance or range for this loading is not stated here (the page previously estimated one from an uncited 70 gph figure — removed rather than repeated).
• Cargo maximum: Pulling seats and running the cabin as a freighter with minimum fuel, the airplane's useful load (4,416 lb) sets a theoretical ceiling on cargo weight competitive with a Grand Caravan, though the exact split against a minimum-fuel reserve is not computable without a published burn rate.

These figures reflect prototype-quoted performance only — Evektor's own technical specification, itself dated to a program that was suspended in 2017 with no certified flight test program ever completed. No certified loading chart exists, and any real-world operation would require individual aircraft weighing and a non-standard flight manual.

• Cargo hauling (7): Large 5.02m x 1.61m x 1.37m cabin is the biggest in class — bigger internal volume than a Grand Caravan — with a rear cargo door designed for bulky loads. Useful load around 4,400 lb is strong. This was the design target. See Cargo Hauling.
• Backcountry/bush (6): High wing, rugged gear, STOL numbers, and twin-engine redundancy make it theoretically well-suited for remote operations. See Backcountry / Bush Flying. Reality check: zero operator base, no field service network, and uncertified status eliminate it from serious consideration.
• Cross-country (5): A 220 kt maximum speed and 925 nm range (at a 2,000 lb payload) are respectable but unpressurized cabin is a major drawback for passenger comfort on longer legs.
• Business travel (4): Unpressurized, 9-seat unproven airframe cannot compete with King Air 90/200 or PC-12 for this role.
• Surveying (5): High wing gives good downward visibility, twin reliability is a plus, but the lack of sensor integration ecosystem and certified status hurts.
• Flight training / local fun / aerobatics (1): Wholly unsuitable — wrong scale, wrong mission, and no fleet exists to train on.

The second prototype was equipped with a Garmin G1000-based integrated glass cockpit from Garmin's certified turboprop lineup, with dual PFDs and an MFD. In 2021, one prototype participated in the EU Clean Sky 2 COAST program testing advanced avionics concepts, though that work did not feed a certification effort. Because no production aircraft exist, there is no "common panel configuration" — any hypothetical production aircraft would likely ship with G1000 NXi or G3000. Retrofit pricing is moot.

None. The aircraft is uncertified. No STCs exist, no field modifications have been documented, and no third-party mod ecosystem has developed around the type. Any owner-modifier would be operating an experimental/prototype airframe with no approval pathway.

Parts availability is poor and mechanic familiarity is rare — see Maintenance Ecosystem. The PT6A-21 engine itself is very well supported by P&WC's global network (universal PT6 coverage, well-understood hot section and overhaul pipeline at roughly $250-300k per engine at TBO), so powerplant maintenance is actually the strongest part of the equation. Airframe support is where the EV-55 collapses: Evektor has never stood up a production line, never published an approved maintenance manual under a valid TC, never trained an A&P/IA network outside the prototype team in Kunovice, and has no spares distribution. Any structural component failure would require one-off fabrication in the Czech Republic at Evektor's discretion. Annual inspection is undefined — the airframe would be maintained under experimental/research rules, not a certified maintenance program.

Valuation is essentially speculative. 2012 pricing guidance from Evektor targeted $2.1-2.2M per aircraft; by 2016 the projected sticker had risen to roughly $4M. No production aircraft have sold. Occasional listings for "2017 EV-55 Outback" on broker sites represent either the prototypes themselves or aspirational listings; any transaction would be a prototype sale with no residual value model, no comparables, and no Aircraft Valuation Methodology framework that cleanly applies. Standard airframe-plus-engines-plus-avionics build-up gives roughly $1.2M for two mid-life PT6A-21s, $400-600k for the Garmin panel, and the remainder is airframe goodwill — but without a type certificate, the goodwill component rounds toward zero. Treat any acquisition as a research/collector purchase, not an operational aircraft investment.

No Airworthiness Directives exist because the aircraft has no type certificate. The major "common problem" with the EV-55 is program-level: development was suspended in March 2017 following a collapse in the Malaysian investment partnership with Aspirasi Pertiwi, and two of three Czech shareholders reportedly faced legal disputes (described in trade press as a "shareholders' war"). EASA CS-23 certification — originally targeted for Q1 2017 following a November 2014 application — has not been completed. Prototype-specific issues (landing gear cycling, engine integration, avionics qualification) were documented during the flight test program but never fully resolved to certification standards. For any prospective buyer, the overwhelming red flag is that no supply chain, no approved maintenance program, no service bulletins, and no technical support infrastructure exist.

Effectively uninsurable through standard GA hull/liability markets. The EV-55 has no type certificate, no approved pilot training program, no loss history, and no actuarial basis. Underwriters cited in GA Insurance Underwriting require a valid type certificate and an approved training curriculum to bind a twin turboprop hull. A prospective owner would need a bespoke aviation underwriter (Lloyd's syndicate or similar) willing to write a prototype/experimental policy, likely at hull rates well above the 3-5% of hull value typical for certified twin turboprops, with very high deductibles and restricted operating envelopes. The $45,000 estimate in the frontmatter is a rough guess at what a specialty underwriter might quote on a $4M hull if they took the risk at all.