Ibis Ae 270 Spirit Propjet

The Ibis Aerospace Ae 270 Spirit is a pressurized, single-engine turboprop utility aircraft with one of the most convoluted—and unsuccessful—development histories in modern general aviation. Conceived as a direct competitor to the Pilatus PC-12 and Socata TBM, it was developed by Czech manufacturer Aero Vodochody, who in 1997 partnered with Taiwan's Aerospace Industrial Development Corporation (AIDC) to form the joint venture Ibis Aerospace for manufacturing and marketing. Wings and landing gear were built in Taiwan by AIDC; fuselages, engine compartments, tail surfaces, and final assembly were performed in the Czech Republic at Aero Vodochody.

The prototype first flew on 25 July 2000. EASA type certification was achieved in 2005, FAA type certification on 24 February 2006. By that point, however, AIDC had already publicly shifted its priorities from civil to military aviation (2004), and Aero Vodochody's upper management followed suit. Only eight airframes were ever built before the project was formally suspended in 2008. The remaining jigs and tooling were removed, and three unfinished fuselages were moved to the Air Park Zruč u Plzně museum in the Czech Republic. The surviving aircraft were divided between the two former partners.

Today the Ae 270 exists almost exclusively as a museum curiosity and a cautionary tale about orphan turboprops. Anyone flying the reputation is largely academic—extremely few, if any, operate commercially in North America. The design itself was sound: a large cabin (up to 10 seats), PT6A-66A power, Honeywell Primus Apex integrated flight deck, and numbers that roughly matched the PC-12 on paper. But without a supported production line, parts network, or service ecosystem, the type has effectively no market value relative to certified competitors.

Only the Ae 270 HP Propjet achieved EASA and FAA certification. This is the variant reflected in the frontmatter.

On paper the Ae 270 HP matches the Pilatus PC-12's era-appropriate performance envelope: 270 KTAS maximum cruise at FL200, roughly 1,610 nm range with reserves, 30,000 ft service ceiling, and a climb rate near 1,800 fpm at gross. Real-world numbers from the handful of demonstrator flights suggested long-range cruise closer to 230 KTAS at economy power settings, with fuel burns in the 44–50 gph band depending on altitude and ISA conditions.

The PT6A-66A is the same thermodynamic-rating family used in the Piaggio P.180 and derated for long life. In the Ae 270 it is rated to 850 SHP for takeoff, swinging a 96-inch Hartzell four-blade reversing prop with full feathering and electric boot de-ice. That derating is theoretically good news for hot-and-high performance and engine longevity—TBO is 3,600 hours—but with no operational fleet there is essentially no field data on actual in-service reliability of the installation.

With 3,165 lb of useful load and 2,072 lb of fuel at full tanks, a full-fuel payload is approximately 1,093 lb—about five adults and light bags at FAA standard weights, or four adults with reasonable luggage for the full 1,610 nm range. This is respectable for the class and comparable to an early PC-12.

Load all ten seats (say 1,800 lb of people and bags) and fuel drops to roughly 1,365 lb, or about 204 gallons usable—good for approximately 900–1,000 nm with reserves at long-range cruise. This is the pressurized-single sweet spot that the PC-12 built its reputation on: the Ae 270 matches it on paper. The gap is everything that happens after you land—see business-travel and cross-country for how the mission-fit math compares when fleet support is factored in.

Business Travel (6/10): The Ae 270's design mission. Pressurized, 10-seat, 1,600 nm, Honeywell Apex glass panel. Would be a 7–8 if the type were supported; the orphan status drags it down sharply because unscheduled downtime could easily become terminal to the airframe.

Cross-Country (7/10): Real pressurized range and speed. Same caveat: you'd better not break anything exotic far from home.

Cargo Hauling (5/10): Large cabin and 3,165 lb useful load make it theoretically capable, but no operator has ever built a freight-dog reputation on this type.

Surveying (3/10): Pressurized single turboprops can do survey work, but the Ae 270's lack of any installed sensor STCs or operator experience means a survey buyer would pick a Caravan or PC-12 every time.

Backcountry (2/10): Low wing, retractable gear, high wing loading. Not the mission.

Flight Training / Local Fun / Aerobatics (1/10): Entirely wrong airplane for these missions and also wrong price point.

The certified Ae 270 HP shipped exclusively with the Honeywell Primus Apex integrated flight deck: three 10.4-inch LCDs, integrated FMS, digital autopilot, dual digital nav/comms, color weather radar, TCAS I, EGPWS, radio altimeter, Mode S transponder, DME, and ADF. This was a genuinely modern glass panel for the 2005–2006 timeframe and remains perfectly capable for IFR single-pilot Part 91 operation today.

The catch: Primus Apex is a supported product, but the AE 270-specific software loads, configuration files, and LRU part numbers were only ever produced in tiny numbers. Any failure that requires a line-replaceable unit with a type-specific dash number is a significant sourcing exercise. An ADS-B Out upgrade path exists in principle via Honeywell's Apex roadmap but has never been accomplished on this type, meaning a US-based operator would face custom engineering work to comply with 14 CFR 91.225/.227.

There is no "upgrade tier" structure here—you get what the aircraft left Vodochody with, and modifications are bespoke. See valuation-methodology for how orphan avionics factor into market value.

Essentially none. The Ae 270 program ended before any third-party STC ecosystem developed. There are no aftermarket gross-weight increases, no alternative prop STCs, no cargo-door conversions, no aerial-work kits, no winglets, no engine upgrades. Any modification to an Ae 270 in the United States would have to proceed through a field approval or a new STC application, with the owner bearing the entire engineering burden. This is a major operational liability compared to the PC-12 (hundreds of STCs) or the TBM.

The Ae 270 has no active manufacturer support. Ibis Aerospace no longer functions as a product-support organization. Aero Vodochody retains type certificate responsibility in principle but produced no fleet-support infrastructure after 2008. AIDC has no civil-aircraft support role. There is:

• No authorized service center in North America
• No parts distribution chain for airframe-specific parts; sheet metal, composites, interior components, and flight-control parts must be custom-sourced
• No type-club to pool knowledge across owners
• No A&P with current type experience readily available; a Pratt-trained engine shop can handle the PT6A-66A, but airframe work defaults to improvisation

Annual inspections on an Ae 270 routinely exceed $50,000–$100,000 when any squawks require custom parts sourcing. Hot sections and overhauls on the PT6A-66A follow standard Pratt & Whitney Canada pricing (~$150,000 HSI, ~$450,000 overhaul) and are the one reliable cost line item.

See maintenance-ecosystem for how parts availability and mechanic familiarity affect real-world ownership economics, and note that the Ae 270 sits at the extreme "poor / rare" end of both scales.

This is the hardest GA aircraft in the world to put a meaningful price on, because the market is effectively nonexistent. The original 2006 list price was $2.195 million base IFR and approximately $2.5 million with executive interior, weather radar, and air conditioning. When the aircraft have traded since 2008, they have moved through specialty brokers at heavy discounts to that original list, typically in the $1.2M–$2.2M range depending on total time, cosmetic condition, and—critically—whether any major LRU has failed.

Valuation drivers unique to this type:

• Engine time-since-overhaul dominates everything. A PT6A-66A mid-life is worth more than the airframe surrounding it. A runout engine on an Ae 270 is close to a total loss.
• Avionics currency: no ADS-B Out = US airspace restricted = additional $50k–$150k of engineering and install work before the aircraft is usable.
• Provenance / logbook completeness: with so few airframes, individual aircraft histories are highly specific. A museum-stored hull is worth dramatically less than an actively flown example.
• Essentially zero blue book comparables. Vref, Aircraft Bluebook, and JETNET have thin or no data. See valuation-methodology for generalized turboprop valuation frameworks.

With only eight airframes built and virtually no fleet hours accumulated in revenue service, the AD record is effectively empty—not because the design is mature, but because there is no fleet to generate service difficulty reports. Known concerns from the limited flight-test program included:

• Prolonged systems-integration work on the Honeywell Apex avionics during 2000–2003 testing
• Iterative refinement of pressurization and flight-control systems
• Significant weight growth during development (initial design targeted 3,950 lb empty / 6,600 lb MTOW, final aircraft came in near 5,650 lb empty / 8,818 lb MTOW)

The biggest "common problem" with an Ae 270 today is the airframe itself: no manufacturer support, no factory service bulletins after 2008, and no continued airworthiness authority actively monitoring the fleet. A prospective buyer must assume that any discovered defect will be on them to diagnose and fix.

Insurance is the single biggest practical obstacle to flying an Ae 270 in the US. As an orphan turboprop with fewer than ten airframes produced, it falls outside every mainstream underwriter's standard rating table. Hull insurance, when it can be bound at all, is typically written through a specialty market at rates well above comparable PC-12 or TBM coverage. Expect:

• Annual hull premiums in the $30,000–$50,000 range for a $1.5M–$2M hull, versus roughly $15,000–$25,000 for an equivalent-value PC-12
• Mandatory type-specific recurrent training—which does not exist as a formal course, meaning owner-pilots typically must satisfy underwriters with a custom training plan
• Minimum total-time requirements in the 2,500–5,000 hour range, with significant turboprop and pressurized time
• Liability limits often capped below the $5M/$10M combined single limits owners typically want for business use

See insurance-underwriting for orphan-type insurance considerations.