No. 10748. Heliopolis Gomhouria Mk.6 (285) Egyptian Air Force
Photographed at Gilze-Rijen AFB, The Netherlands, June 17, 2005, by Loet Kuipers

Heliopolis Gomhouria Mk.6

07/31/2011. Remarks by Johan Visschedijk: "Shown in the static display of the Open Dagen Koninklijke Luchtmacht (Open Days Royal Air Force) on June 17 and 18, this aircraft arrived disassembled aboard an Egyptian AF C-130H on the 16th. Reportedly it was one of the last three within the Egyptian AF.

The Gomhouria (Republic) was a version of the 1939 Bücker Bü 181 Bestmann produced by the in 1950 formed Heliopolis Air Works as a part of the Egyptian General Aero Organization. At least 300 Gomhouria's were produced for Egypt, Jordan, Libya, Saudi Arabia, Somalia and the Sudan in the following versions:

Gomhouria Mk 1. Initial series for Egyptian AF with 105 hp Walter Minor engine.
Gomhouria Mk 2. Basically similar to Mk 1, but with 145 hp Continental C145 engine. Supplied to civil flying institutes, Royal Arab AF, Sudan and Saudi Arabia.
Gomhouria Mk 3. As Mk 2, but with castoring tail-wheel and double-disc brakes. Fuel capacity 35.66 gal (135 l).
Gomhouria Mk 4. As Mk 3, but with fuel capacity of 40.95 gal (125 l).
Gomhouria Mk 5. With 105 hp Walter Minor 4-III engine, mounted further forward than on Mk I, and fuel capacity of 29.06 gal (110 l). Fully aerobatic.
Gomhouria Mk 6. As Mk 2, but with 145 hp Continental O-300 engine. Fuel capacity 40.95 gal (125 l). Suitable for restricted aerobatics.

The following description refers specifically to the Gomhouria Mk 2, but is generally applicable to other versions:

TYPE: Two-seat trainer.
WINGS: Cantilever low-wing monoplane. Wing section NACA 23017 at root, NACA 4412 at tip. Aspect ratio 8.3. Chord 5 ft 11 in (1.8 m) at root, 2 ft 1 in (0.63 m) at tip. Dihedral 5° 30'. Incidence 4° at root. Two-spar all-wood structure. Fabric-covered Frise ailerons. Split flaps of metal construction.
FUSELAGE: Front section is a welded steel-tube structure, rear section a wooden monocoque.
TAIL UNIT: Cantilever wood structure, with fixed surfaces plywood-covered and control surfaces fabric covered.
LANDING GEAR: Non-retractable tail-wheel type. Cantilever main legs with hydraulic shock-absorbers. Mechanical single-disc brakes.
POWER PLANT: One 145 hp Continental C145 six-cylinder horizontally-opposed air-cooled engine, driving a two-blade fixed-pitch wood propeller, diameter 6 ft 6 in (2.0 m). Fuel tank in fuselage, capacity 40.95 gal (125 l). Oil capacity 2.01 gal (7.6 l).
ACCOMMODATION: Enclosed cockpit seating two side-by-side with dual controls. Adjustable seats. Baggage compartment behind cabin.

Created July 31, 2011