TYPE: Four-seat lightplane.

PROGRAMME: Launched as Instytut Lotnictwa development programme June 1992; funded by grant from State Committe for Scientific Research; construction started January 1994 of one static test (001) and two flying prototypes; first flight, by 002/SP-PIL, 20 February 1999; original name Ibis changed to Manager 1999; Polish type certificate BB-215 awarded 3 October 2001; second prototype had not been produced by early 2002, at which time first aircraft was re-registered SP-GIL; planned certification to Normal category FAR Pt 23 Amendment 42. PZL-Świdnik seeking production launch investment in 2003.

CURRENT VERSIONS (planned): I-23N: Standard Normal category, retractable gear IFR version with dual controls.
Description applies to this version except where indicated.
I-23D: Normal category IFR executive or patrol version of I-23N with single controls and uprated, fuel-injection engine.
I-23S: Utility category basic trainer. Lower-powered engine, dual controls, VFR instrumentation, fixed landing gear and reinforced structure.

CUSTOMERS: Two ordered by Polish Ministry of Defence.

DESIGN FEATURES: Intended as safe, low-cost, low fuel consumption private owner aircraft. Conventional low-wing, tricycle-gear design with fully enclosed cabin.
Wing has ILL-217 (root) and ILL-213 (tip) aerofoil sections, 2° 30' leading-edge sweepback, 4° dihedral, 2° 30' incidence and -1° twist. Tailplane NACA 015 profile; fin NACA 0018.
Design permits use of any Textron Lycoming flat-four engine from 119 to 149 kW (160 to 200 hp), option for fixed or retractable landing gear, and equipment to customer's specifications.

FLYING CONTROLS: Conventional and manual. Ailerons deflect 22° up/17° down, elevators 30° up/24° down, rudder 21° left/right. Trim tab in port elevator. Flap settings 0/20/30°.

STRUCTURE: Mainly GFRP/CFRP/epoxy, with sandwich skins; CFRP for main spar and in region of landing gear attachments. Wing ribs and landing gear support plate of duralumin; steel fittings. Skin panels attached by abhesives, reinforced by bolts and rivets. First Polish aircraft with prepreg composites.

LANDING GEAR: Electrohydraulically retractable tricycle type on I-23N and D, with oleo-pneumatic shock-absorbers; steerable (±25°) nosewheel; mainwheels retract inward, nosewheel rearward, latter remaining half exposed when retracted; Parker wheels and brakes; Goodrich 5.00-5 tyres (main and nose), pressure 3.80 bar (55 lb/sq in) on mainwheels and 3.10 bar (45 lb/sq in) on nosewheel. Non-retractable gear on I-23S.

POWER PLANT: I-23N: One Textron Lycoming O-360-A1A flat-four (134 kW; 180 hp at 2,700 rpm), driving an MT-built Hartzell HC-C2YR-1BF/F766A-4 two-blade constant-speed propeller.
I-23D: 147 kW (200 hp) Lycoming IO-360-A1A.
I-23S: 118 kW (160 hp) Lycoming O-320-D2A and Sensenich fixed-pitch propeller.
Integral fuel tank in each wing, combined capacity 190 litres (50.2 US gallons; 41.8 Imp gallons) in I-23N/I-23D, 110 litres (29.1 US gallons; 24.2 Imp gallons) in I-23S. Gravity fuelling points on each wing. Oil capacity (all versions) 7.6 litres (2.0 US gallons; 1.7 Imp gallons).

ACCOMMODATION: Four persons (pilot and three passengers) on two rows of seats. Upward-opening door each side. Cabin heated and ventilated.

SYSTEMS: Electrohydraulic system for landing gear actuation; hydraulic system for mainwheel brakes only. Electrical power from 14 V 70 A alternator and 12 V 35 Ah battery. Heated pilot head.

AVIONICS: Comms: Bendix/King com transceiver and ATC transponder standard.
Flight: Bendix/King nav transceiver, ADF, GPS and directional gyro standard; optional full IFR system with KNS 81 integrated nav/RNav, DME and KCS 55A HSI.