The KL-1 is a composite fuselage cantilever high-wing cabin monoplane designed to meet the requirements of the utility and normal categories of Part 23 of the Federal Aviation Regulations.[1] It had a fixed tricycle landing gear and a conventional four-seat cabin layout.[1] The prototype designated KL-1A and registeredN960KA first flew on 19 November 1995 and was powered by a 160 hp (119 kW) Lycoming O-320-D2G piston engine driving a two-bladed fixed pitch propeller.[1]
A number of improved variants of the KL-1 were planned including an armed observation or forward air control version with underwing weapon pylons.[1]
While the prototype was test flying to gain certification the programme was abandoned.
Variants
KL-1A
Baseline four-seat production variant with a 160 hp (119 kW) Lycoming O-320-D2G piston engine, one built.[1]
KL-1B
Proposed de-luxe four-seat variant with a 190 hp (142 kW) Lycoming IO-360-ES piston engine, not built.[1]
KL-1C
Proposed high-performance variant with a 250 hp (186 kW) Continental TSIO-360C piston engine, 2 built.[1][2]
KL-1D
Proposed six-seat utility and cargo variant with a 325 hp (242 kW) Continental TSIO-550-B engine, and an optional floatplane conversion, not built.[1]
KL-1R
Proposed retractable landing gear variant of the KL-1B with a 190 hp (142 kW) Lycoming IO-360-ES piston engine, not built.[1]
K250A
Proposed military armed observation or forward area control variant of the KL-1C with additional observation windows and underwing weapons pods, not built.[1]
Specifications (KL-1A)
Data from Jane's All the World's Aircraft 1995-1996
