[2] The D.33 was developed in response to an initiative by the French Air Ministry to encourage advanced into the nation's industrial aeronautical capabilities.

Largely due to the record breaking performance achieved, this line of aircraft were highly regarded and attracted considerable commercial interest throughout the 1930s.

The origins of the D.33 can be traced back to 1929 and the implementation of a wider policy of ordering prototypes to encourage technical progress by French aircraft companies.

[8] The aircraft was typically flown by a crew of three (comprising a pilot, navigator and radio operator) that were seated in a tandem arrangement within an enclosed cabin.

[8] On account of the aircraft's long distance performance, various amenities and comfort features were provided for the crew; these included a couch that permitted rest breaks to be taken and a toilet.

[6] Its structure used only a single spar, positioned at one-third of the chord from the leading edge; the lateral boxes at the centre of this structure formed the aircraft's 16 fuel tanks as well; these tanks proved to be resistant against not only the routine impact stresses of many take-offs and landings, but also deformation when the wing was intentionally overloaded.

[12] The spar flanges, which differed in width across each section, were connected by sturdy hinges composed of high resistance steel able to withstand stresses of up to 100 tonnes (220,462 lb.).

The sole spar could absorb all bending stresses without buckling despite its comparatively small width, partially due to the strong flanges.

[6] Neither was any noticeable torsion of the wing tips present even in the event of an abrupt deflection of the ailerons while flown at high speeds.

[13] It was also quite easy to both take-off as well as to land, in part due to the centre of gravity of the empty aircraft being slightly behind that of its placement when fully loaded.

[3][14] Measures to maximise propeller efficiency included the unobstructed nose of the engine cowling as well as its positioning being well forward of the leading edge of the wing.

[15] Engine cooling was achieved via a honeycomb radiator that was located on the base of the fuselage; it could be partly retracted using tubular controls that worked in torsion and via a square-threaded screw.

[4] It consists of a bent axle of uniform strength supported in front by a biconical tube and vertically by a shock absorber.

The tail skid had a wheel, complete with a rubber tyre, that was supported by a multiple-braked spring type shock absorber in the stern post.

[18] The rear portion of the fuselage was strongly tapered as to increase the efficiency of the flight controls; this compact contact area did not permit the use of a cantilever stabilizer, thus it was instead braced by several small tubular struts.

[18] The elevator flaps consisted of a channel-section front spar on which were mounted two removable panels that were internally stiffened by section members.

[19] The primary buyer of this model was Air France; however, two of the three planes bought by the latter crashed while flying the distance between Toulouse and Dakar.