After failing to obtain a license for manufacture of the Supercab and for the Aviamilano F.8L Falco, SRCM decided to design a completely new three-seat light monoplane. This materialized as the SRCM-153 Joigny, construction of the prototype commenced in April 1958 and it was first flown in June 1959, under the provisional registration F-WIRZ.
On June 29, 1960 the aircraft was reregistered F-BIRZ (Henk Wadman Collection) after it received its CofA; it was demonstrated at the 1963 Paris Air Salon. The sole SRCM-153 was deregistered on January 29, 1979 as condemned. It reappeared on the French register in the homebuilt category as F-PIRZ (Walter van Tilborg Collection) on November 23, 1983. Two years later, November 19, 1985 it was again deregistered, this time as 'destroyed', it had crashed near Coudeville the previous August 4.
WINGS. Cantilever low-wing monoplane. Wing section NACA 23015 at root, NACA 33010 at tip. Aspect ratio 6.6. Chord 5 ft 3 in (1.60 m) at root, 3 ft (0.91 m) at tip. Dihedral 6°. Incidence 4° at root, 2° 30' at tip. All-wood structure, integral with center fuselage, built around single main spar and an auxiliary rear spar, with leading-edge torsion box and plywood covering. Plain ailerons. Hydraulically-operated double-slotted flaps, supplemented by hydraulically-operated air-brake under fuselage.
FUSELAGE. All-wood structure. Cabin section integral with wing. Rear section is a plywood monocoque, integral with tail unit. Small tail bumper.
TAIL UNIT. Cantilever monoplane type, integral with fuselage. All-wood structure. Trim-tabs in rudder and port elevator. Elevator mass-balance moves inside fin.
LANDING GEAR. Retractable tricycle type of SRCM design and manufacture. Hydraulic retraction. Hydraulic shock-absorbers. All three wheels are same size and carry Dunlop tires size 400 X 100, inflated to 42.7 lb/sq.in (3 kg/sq.cm). Steerable nose-wheel. Simca V hydraulic brakes. Wheel track 9 ft 6 in (2.90 m). Wheelbase 5 ft 6 in (1.67 m).
POWER PLANT. One 150 hp Lycoming O-320-A1A four-cylinder horizontally-opposed air-cooled engine, driving a two-blade Hartzell metal constant-speed airscrew. Fuel in three Superflexit bag-type tanks; one in each center-wing outboard of the landing gear, with capacity of 15.85 gal (60 l) each, and one in centre-wing under cabin, with capacity of 31.7 gal (120 l).
ACCOMMODATION. Pilot and two passengers in enclosed cabin with large forward-sliding transparent canopy. Dual controls. Provision for blind-flying instruments, VHF radio, radio-compass and VOR.
Span: 27 ft 4.5 in (8.35 m)
Length: 21 ft 0 in (6.39 m)
Height: 7 ft 9.5 in (2.38 m)
Wing area: 113 sq.ft (10.50 sq.m)
Empty weight: 1,410 lb (640 kg)
Loaded weight: 2,315 lb (1,050 kg)
Max speed: 199 mph (320 kmh) at sea level
Econ cruise speed: 177 mph (285 kmh)
Landing speed: 50 mph (80 kmh)
Climb: 790 ft (240 m)/min
Takeoff run: 985 ft (300 m)
Landing run: 460 ft (140 m)
Service ceiling: 19,030 ft (5,800 m)
Range: 930 mls (1,500 km)