the h.230.01 was powered by two salmson 6af engines and its configuration included a short crew canopy faired into the upper decking of the rear fuselage and a conventional strut-braced tail unit, and the fixed main landing gear units incorporated spatted wheel fairings. during further tests it was decided to introduce considerable dihedral at the wingtips to improve stability, but the h.231.01 which followed in may 1938 had dihedral increased over the whole wing span, and the unusual wingtip arrangement of the modified h.230 was eliminated. twin fins and rudders were introduced and the power was increased with new salmson 6af-02 engines. the hanriot h.232.01 had a single fin and rudder and was equipped with twin renault 6q-02/03, (left and right hand propeller rotation), engines plus retractable landing gear. the h.232.02, which made its maiden flight in august 1938, introduced a redesigned cockpit. the aircraft was tested between october 1938 and may 1939. the type was then given a twin fin and rudder tail assembly and was flown in this new configuration in december 1939, then redesignated h.232/2.01.