Lancair IV-P
Single-Engine Four-Seat Low-Wing Tri-Gear Home-Built Pressurized Monoplane, USA

Archive Photos ¹

2002 Lancair IV-P (Frentzen Heinz-Harald, N111HH, s/n HHF001) on display 1/11/2009 at the 2009 Cable Air Show, Cable Airport, Upland, CA (Photos by John Shupek)

Overview

Lancair IV-P
• Role: Homebuilt aircraft
• Manufacturer: Lancair Group, Inc., Bend, Oregon, USA
• Produced: 325 (2007)
• Unit cost: USD $275,000 - $375,000
• Variants: Lancair Propjet

The Lancair IV and Lancair IV-P are a family of four-seat low-wing retractable-gear composite monoplanes powered by a 550 cubic inch Continental turbo-normalised piston engine.

Variants

The kit-plane is provided in either pressurized (Lancair IV-P) or non-pressurized (Lancair IV) variants. A turboprop called the Lancair Propjet can achieve cruise speeds in excess of 300 knots (556 km/h) at altitudes up to 30,000 feet (9,140 m). Normally powered by a Walter turbine, Pratt & Whitney Canada PT6s and other turbines are also used.

Production

By the fall of 2007 100 Lancair IVs and 225 IV-Ps had been completed and were flying.

Specifications and Performance Data — Lancair IV and Lancair IV-P

Type

• Four-seat performance kitbuilt.

Program

• Kit deliveries began 1990.
• On 20 February 1991, prototype set NAA world speed record between San Francisco and Denver of 314.7 kt (583.2 km/h; 362.4 mph).
• First kit completed July 1991.

Current Versions (2002)

• Lancair IV
• Standard version
• Lancair IV-P
• Pressurized version
• First flight 1 November 1993.
• Provides 0.34 bar (5.0 lb/sq in) differential
• Equipment from Dukes Research of CA.

Customers (2002)

• Total of 500 kits sold (2002); 110 flying by late 1998

Costs (2002)

• Standard US $52,400; New Fast-Build US $73,700.
• Pressurized version: Standard US$76,500; New Fast-Build US$97,800
• Wingmate US $3,000 extra
• Firewall Fast-Build options and builder workshop available.

Design Features

• Conventional seating for four persons in airframe of new design, but following Lancair formula for high cruising speeds.
• Optional winglets.
• Quoted Fast-Build construction time 2,000 hours.

Flying Controls

• Conventional and manual.
• Fowler flaps.
• Sidestick controllers for both pilots.
• Trim tabs in port aileron and port elevator.
• Optional speed brakes.

Structure

• Carbon fiber/epoxy airframe, with Nomex honeycomb cores.

Landing Gear

• Retractable tricycle type.
• Castoring nosewheel turns ±45° for ground handling.
• Differential breaks.
• Mainwheels 15 x 6.00-6; nosewheel is 5.00-5.
• Cleveland dual-piston caliper brakes.

Power Plant

• One 261 kW (350-hp) Teledyne Continental TSIO-550-E1B, -E2B or -E3B twin-turbocharged flat-six engine driving a three- or four-bladed MT or Hartzell constant-speed propeller.
• Fuel in integral wing tanks; total standard usable capacity 310 litres (82.0 US gallons; 68.3 Imp gallons); long-range tanks, total capacity 341 litres (90.0 US gallons; 74.9 Imp gallons), of which 333 litres (88.0 US gallons; 73.3 Imp gallons) are usable.
• Oil capacity 11.4 litres (3.0 US gallons; 2.5 Imp gallons).
• Two versions of PT-6A tested during 1999.

Systems

• Electro-Explosive Separation System electromagnetic de-icing system was tested during 1999.

Dimensions (external)

• Wing span (plain tips): 9.19 m (30 ft 2 in)
• Wing span (winglets): 9.93 m (32 ft 7 in)
• Wing chord at root: 1.18 m (3 ft 10-1/2 in)
• Wing chord at tip: 0.77 m (2 ft 6-1/4 in)
• Wing aspect ratio: 9.3
• Width, wings removed: 2.41 m (7 ft 11 in)
• Length overall: 7.62 m (25 ft 0 in)
• Height overall: 2.44 m (8 ft 0 in)
• Tailplane span: 3.35 m (11 ft 0 in)
• Wheel track: 2.13 m (7 ft 0 in)
• Wheelbase: 1.88 m (6 ft 2 in)
• Propeller diameter: 1.93 m (6 ft 4 in)

Dimensions (internal)

• Cabin: Length: 3.20 m (10 ft 6 in)
• Max width: 1.17 m (3 ft 10 in)
• Max height: 1.22 m (4 ft 0 in)

Areas

• Wings (gross with plain tips): 9.10 m² (98.0 ft²)
• Wings (gross with winglets): 10.03 m² (108.0 ft²)
• Winglets, total: 1.30 m² (14.00 ft²)
• Flaps, total: 1.12 m² (12.07 ft²)

Weights and Loadings

• Weight empty (IV): 907 kg (2,000 lb)
• Weight empty (IV-P): 998 kg (2,200 lb)
• Baggage capacity: 68 kg (150 lb)
• Max T-O weight: 1,451 kg (3,200 lb)
• Max landing weight: 1,360 kg (3,000 lb)
• Max wing loading (plain tips): 159.4 kg/m² (32.65 lb/ft²)
• Max power loading: 5.56 kg/kW (9.14 lb/hp)

Performance

• Never-exceed speed (VNE): 274 kt (507 km/h; 315 mph)
• Cruising speed at 75% power at 7,315 m (24,000 ft): 291 kt (539 km/h; 335 mph)
• Stalling speed: 66 kt (121 km/h; 75 mph)
• Max rate of climb at S/L: 792 m/min+ (2,600 ft/min)
• Service ceiling: 8,840 m (29,000 ft)
• T-O run: 457 m (1,500 ft)
• T-O to 15 m (50 ft): 549 m (1,800 ft)
• Landing run: 518 m (1,700 ft)
• Range, no reserves: 1,260 nm (2,334 km; 1,450 miles)
• Endurance: 4 h 48 min
• g limits: +4.4/-2.3 (allowable), +8/-4 ultimate

References

1. Photos, John Shupek
2. Wikepedia. "Lancair IV." [Online] Available https://en.wikipedia.org/wiki/Lancair IV, 23 September 2009
3. Jackson, Paul (ed.), Jane’s All The World’s Aircraft 2001-2002,2001 Jane’s Information Group Limited, ISBN 0 7106 2307 0. pp 669
4. Jackson, Paul (ed.), Jane’s All The World’s Aircraft 2000-2001, 2000 Jane’s Information Group Limited, ISBN 0 7106 2011 X. pp 682