Launched in 1968 it was operated in geostationary orbit at a longitude of 24 degrees west for around eighteen months.

It was a 293 kg (646 lb) spacecraft, with its mass reducing to 151 kg (333 lb) by entry into service as it burned propellant to reach its final orbit.

The satellite carried an SVM-2 apogee motor for propulsion and was equipped with two transponders powered by body-mounted solar cells generating 183 watts of power.

The launch took place at 00:32 GMT on 19 December 1968, with the spacecraft entering a geosynchronous transfer orbit.

[1] Intelsat III F-2 subsequently fired its apogee motor to achieve geostationary orbit.