The Caproni C-22J is an Italian twin-engine two-seat jet designed by Carlo Ferrarin in the late seventies. This page will introduce you to the history of this aircraft, its specifications, and several very interesting pictures and drawings.
Many thanks to Carlo Ferrarin for providing me with first hand information.
The project Caproni C22J began in 1978 as a response to the Low Cost Aircraft draft specifications set by the USAF for jet training at minimal direct operating cost. The C22J was designed in compliance to the aerobatic category of FAR23.
The C22J development was principally based on the experienced gained by Caproni on the A21SJ self-launching glider.
The development, manufacturing and testing phase was accomplished by a team of 14 people led by Carlo Ferrarin. The engineer Marco Morganti and test pilot Paolo Barberis also contributed to the development of the C22J.
In 1983, the Caproni family sold the business to Agusta. The C22J program was canceled in 1988 as Agusta considered the (Agusta division's) Siai Marchetti S-211 more suitable for the jet training market. FAA certification under FAR23 category was under way, and there were a few unresolved hurdles such as noise limits. After a long period of inactivity, the two C22J prototypes were indefinitely grounded when Agusta sold the remaining TRS-18 engines in the US.
3. Technical description
The C22J had two turbojet engines installed in the fuselage and fed by a NACA inlet. The fuel was stored in the wings, and in wing tip tanks.
|Span||30 ft 2 1/4 in||9.2 m|
|Length||20 ft 6 1/2 in||6.264 m|
|Height||6 ft 2 in||1.88 m|
|Wing area||89 sqft||8.28 m2|
|Incidence||1 deg 9 min|
|Max. take-off weight||2760 lb||1255 kg|
|Empty weight||1628 lb||739 kg|
|Max. wing loading||31 lb/sq ft||152 kg/m2|
|Load factors||+ 7 g / - 3.5 g|
|Total take-off thrust||657 lb||298 kg|
|Maximum continuous thrust||528 lb||264 kg|
|Thrust loading||4.23 lb/lb||4.23 kg/kg|
|Max. dive speed (VD)||325 kts||600 km/h|
|Max. operating speed (VMO)||300 kts||555 km/h|
|Max. structural cruise speed SL (VC)||260 kts||480 km/h|
|Max. manoeuvre speed (VA)||225 kts||416 km/h|
|Max. speed landing gear ext.||143 kts||264 km/h|
|Stall speed (power off, flaps down) (VSC)||73 kts||135 km/h|
|Max. speed brake ext.||225 kts||416 km/h|
|Max. level speed (VH)||280 kts||518 km/h|
|TAKE-OFF (ISA, SL, 1100 kg / 2400 lb)|
|Ground roll||1148 ft||350 m|
|Obstacle clearance 15m / 50ft||1804 ft||550 m|
|Same obstacle at 1500m / 5000ft alt.||2624 ft||800 m|
|CLIMB AND ALTITUDE|
|Sea level||1930 ft/min||9.8 m/s|
|3000 m / 9840 ft||1515 ft/min||7.7 m/s|
|6000 m / 19680 ft||1062 ft/min||5.4 m/s|
|Service ceiling (FAR limit is 25000ft)||29500 ft||9000 m|
|Time to climb to 5000 m / 16400 ft||10 min|
|CRUISE (1255 kg / 2730 lb - tip tanks)|
|Cruise speed at 3000 m / 9840 ft||285 ktas||530 km/h|
|Maximum range||650 nm||1200 km|
The C22J has obviously its roots in gliders, much like the Fouga Magister. The fuselage was designed for laminar flow. The airfoil was a Wortmann FX-67K-170.
Powerplant : Two Microturbo TRS-18 turbojets.
Thrust range : 250 to 400 lbst
Powered by a pair of Microturbo TRS-18, these thirsty engines required the addition of tip tanks. The first prototype flew in 1980 without tip tanks.
The NACA inlets are known to generate turbulent flow to the engines and generate a poor pressure recovery, but this was of less concern in the case of the TRS-18 engines with its plenum inlets.
The landing gear was a particular design challenge.
The cockpit design made it very inviting.
6. PILOT OPERATING HANDBOOK
2.1 Mb PDF file. Click cover page to access:
6.2 Mb Windows WMV Video File, amateur video of the Paris Le Bourget flight demonstration routine.
Air International Feb 1981 Article
Last update : 02FEB11
Last update : 02FEB11