English name: Hummingbird

TYPE: Four-seat lightplane.

PROGRAMME: Licence-built and uprated version of Socata Rallye 100 ST; original (Morane-Saulnier) Rallye flew 10 June 1959; main production in France until 1983.
First PZL-110, modified to receive 86.5 kW (116 hp) PZL-F (Franklin) engine, first flown 18 April 1978; total 40 built of earlier Series I, II and III.
First flight of Koliber 150 prototype (SP-PHA) 27 September 1988; Polish type certificate for 150 awarded January 1989, FAA certificate for 150A February 1995. Koliber 160A introduced in 1998; production deliveries from 1999. FAR Pt 23 certification 13 February 2001.

CURRENT VERSIONS: Koliber 160A: Introduced 1998 and is now the only production version. First flight (SP-WGF) 15 April 1998; second prototype (SP-WGG) followed 25 May 1998. Two stock 150As converted to 160A prototypes and delivered to UK as demonstrators in 1998. First two production aircraft delivered to PZL International at North Weald, UK, in September and October 1999 for onward sale.
Following description applies to Koliber 160A.
Koliber 235A (PZL-111): More powerful version. Prototype maiden flight 14 September 1995; no production by mid-2003, but continues to be promoted.

CUSTOMERS: Kolibers sold in Canada, Denmark, Germany, Netherlands, Sweden, UK and USA. Total of 79 Koliber 110/150/150As built by 1995, of which five held in stock during 1997; no production in 1996-98. Eight production 160As delivered by late 2001, including one development aircraft, three supplied to UK distributor and two to USA; no known production in 2002.

DESIGN FEATURES: Winner of French competition for ideal flying club aircraft (Rallye); side-by-side seating, nosewheel landing gear, leading-edge slats for low-speed safety (minimum tendency to stall) and simple, inexpensive construction. Constant-chord wing, tailplane and fin, last-mentioned with sweepback.
Wing section NACA 63A-416 (modified); dihedral 7° 7' 30"; incidence 4°.

FLYING CONTROLS: Conventional and manual. Pushrod-actuated, aerodynamically and mass-balanced ailerons, each with ground-adjustable tab; aerodynamically and mass-balanced elevator with central control tab, rudder with ground-adjustable tab; full-span automatic leading-edge slats; electrically actuated Fowler flaps. Aileron movement at MTOW 14° 30' up/11° 30' down; elevator 30° up/25° down; elevator trim tab 20° up/28° down; rudder 30° left/right; flaps 6° up/30° down.

STRUCTURE: All-metal; flaps, elevator and rudder have corrugated skins; wing torsion box and trailing-edge segments electrically spot-welded.

LANDING GEAR: Non-retractable tricycle type, with leg fairings and oleo-pneumatic shock-absorption; castoring nosewheel. Toe-operated hydraulic disc brakes. Parking brake.

POWER PLANT: One 119 kW (160 hp) Textron Lycoming O-320-D2A flat-four engine, driving a Sensenich 74DM6-0-58 two-blade fixed-pitch metal propeller. Fuel in two metal tanks in wings, with total usable capacity of 161 litres (42.5 US gallons; 35.4 Imp gallons). Refuelling points above wings. Oil capacity 7.6 litres (2.0 US gallons; 1.7 Imp gallons).

ACCOMMODATION: Two fore-and-aft adjustable, side-by-side seats, plus two-person bench seat at rear, under large rearward-sliding canopy. Dual controls. Heating, ventilation and soundproofing standard.

SYSTEMS: 14 V electrical system, with 70 Ah alternator and 70 Ah battery.

AVIONICS: Comms: Bendix/King KX 155 nav/com/glideslope; KT 76A transponder; SPA 400 intercom; ELT.
Flight: Bendix/King KI 204 VOR/LOC/GS and KMA 24 audio control/MKR. Audible stall warning system standard. Two optional Bendix/King avionics packages: Nav I (KLN 89 GPS, KX 155A nav/com/glideslope, KR 87 ADF and KI 209 VOR/LOC/glideslope; or Nav II (KLN 89B GPS/IFR, MD 41-228 GPS nav, KX 155A glideslope, KR 87 ADF and KI 209A VOR/LOC/glideslope with GPS interface).
Instrumentation: Standard VFR; IFR applied for.

EQUIPMENT: Position, anti-collision and landing/taxying lights; instrument panel, cabin and map lights; fixed cabin entrance steps; tiedown rings; fire extinguisher; winterisation kit.