The last five of the nine spacecraft in this block carry a maritime mobile payload (seven additional transponders) for lease by Inmarsat. Spacecraft: 3-axis stabilized to 0.5 deg using momentum wheels. Hydrazine propulsion system. Passive thermal control. Dual solar arrays provide 1800 W BOL, NiCd or NiH batteries. Payload: 21 C-Band and 4 Ku-Band transponders.12000 voice circuits and 2 TV channels.
Financial/Operational:
5f series

Design Life: 7 years. Length: 2.00 m (6.50 ft). Maximum Diameter: 1.80 m (5.90 ft). Span: 15.90 m (52.10 ft). Mass: 2,000 kg (4,400 lb). Associated Launch Vehicle: Ariane 1, Atlas Centaur SLV-3D, Atlas G.

• 1980 December 6 - Intelsat 5 F-2 - Program: Intelsat. Launch Site: Cape Canaveral. Launch Vehicle: Atlas. Mass: 2,000 kg (4,400 lb). Perigee: 36,118 km (22,442 mi). Apogee: 36,242 km (22,519 mi). Inclination: 9.70 deg. Period: 1,456.20 min.

  Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle put payload into geosynchronous transfer orbit Positioned in geosynchronous orbit at 21 deg W in 1981; 27 deg W in 1981-1983; 34 deg W in 1983-1985; 27 deg W in 1985; 1 deg W in 1985-1989; 21 deg W in 1989-1994; 40 deg W in 1994-1998 As of 2 September 2001 located at 103.82 deg W drifting at 5.004 deg W per day. As of 2007 Mar 10 located at 81.84W drifting at 5.000W degrees per day.

• 1981 May 23 - Intelsat 5 F-1 - Program: Intelsat. Launch Site: Cape Canaveral. Launch Vehicle: Atlas. Mass: 1,928 kg (4,250 lb). Perigee: 36,151 km (22,463 mi). Apogee: 36,224 km (22,508 mi). Inclination: 10.10 deg. Period: 1,456.60 min.

  Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle put payload into geosynchronous transfer orbit Positioned in geosynchronous orbit at 24 deg W in 1981; 60 deg E in 1982-1984; 57 deg E in 1984-1986; 174 deg E in 1986-1988; 177 deg E in 1988-1990; 177 deg W in 1990-1992; 91 deg E in 1993-1996; 72 deg E in 1996-1997 As of 4 September 2001 located at 169.69 deg W drifting at 5.095 deg W per day. As of 2007 Mar 10 located at 13.28E drifting at 5.096W degrees per day.

• 1981 December 15 - Intelsat 5 F-3 - Program: Intelsat. Launch Site: Cape Canaveral. Launch Vehicle: Atlas. Mass: 1,870 kg (4,120 lb). Perigee: 35,894 km (22,303 mi). Apogee: 36,129 km (22,449 mi). Inclination: 9.40 deg. Period: 1,447.60 min.

  Positioned in geosynchronous orbit at 24 deg W in 1982-1985; 27 deg W in 1985; 53 deg W in 1985-1988; 174 deg E in 1988-1990; 177 deg E in 1990-1992; 177 deg W in 1992-1995; 157 deg E in 1995-1998 As of 5 September 2001 located at 57.52 deg W drifting at 2.890 deg W per day. As of 2007 Mar 9 located at 101.94W drifting at 2.904W degrees per day.

• 1982 March 5 - Intelsat 5 F-4 - Program: Intelsat. Launch Site: Cape Canaveral. Launch Vehicle: Atlas. Mass: 1,928 kg (4,250 lb). Perigee: 35,920 km (22,310 mi). Apogee: 36,243 km (22,520 mi). Inclination: 9.40 deg. Period: 1,451.20 min.

  Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle put payload into geosynchronous transfer orbit Positioned in geosynchronous orbit at 32 deg E in 1982; 63 deg E in 1982; 27 deg W in 1983-1985; 34 deg W in 1985-1992; 40 deg W in 1992; 31 deg W in 1993-1995; 29 deg W in 1995 As of 1 September 2001 located at 4.64 deg W drifting at 3.747 deg W per day. As of 2007 Mar 7 located at 4.34W drifting at 3.748W degrees per day.

• 1982 September 28 - Intelsat 5 F-5 - Program: Intelsat. Launch Site: Cape Canaveral. Launch Vehicle: Atlas. Mass: 2,000 kg (4,400 lb). Perigee: 36,228 km (22,510 mi). Apogee: 36,404 km (22,620 mi). Inclination: 9.00 deg. Period: 1,463.30 min.

  Positioned in geosynchronous orbit at 63 deg E in 1982-1990; 66 deg E in 1991-1996; 33 deg E in 1996; 72 deg E in 1997-on. As of 3 September 2001 located at 16.28 deg E drifting at 6.707 deg W per day. As of 2007 Mar 9 located at 163.88W drifting at 6.709W degrees per day.

• 1983 May 19 - Intelsat 5 F-6 - Program: Intelsat. Launch Site: Cape Canaveral. Launch Vehicle: Atlas. Mass: 1,928 kg (4,250 lb). Perigee: 36,076 km (22,416 mi). Apogee: 36,125 km (22,446 mi). Inclination: 8.30 deg. Period: 1,452.10 min.

  Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle put payload into geosynchronous transfer orbit Positioned in geosynchronous orbit at 29 deg E in 1983; 18 deg W in 1983-1992; 34 deg W in 1992; 50 deg W in 1992-1995; 31 deg W in 1995-1998 As of 4 September 2001 located at 47.96 deg E drifting at 3.999 deg W per day. As of 2007 Mar 10 located at 62.15W drifting at 3.995W degrees per day.

• 1983 October 19 - Intelsat 5 F-7 - Program: Intelsat. Launch Site: Kourou. Launch Vehicle: Ariane. Mass: 1,928 kg (4,250 lb). Perigee: 35,928 km (22,324 mi). Apogee: 35,972 km (22,351 mi). Inclination: 8.50 deg. Period: 1,444.50 min.

  Ariane third stage. Launched by European Space Agency. Launch time 0045:36 GMT. Launched spacecraft Intelsat V F7. Positioned in geosynchronous orbit at 60 deg E in 1984-1985; 66 deg E in 1985-1991; 57 deg E in 1991-1995; 47 deg E in 1995-1996 As of 28 August 2001 located at 140.34 deg E drifting at 2.062 deg W per day. As of 2007 Mar 9 located at 88.83W drifting at 2.097W degrees per day.

• 1984 March 5 - Intelsat 5 F-8 - Program: Intelsat. Launch Site: Kourou. Launch Vehicle: Ariane. Mass: 1,928 kg (4,250 lb). Perigee: 36,531 km (22,699 mi). Apogee: 36,755 km (22,838 mi). Inclination: 8.20 deg. Period: 1,480.10 min.

  Positioned in geosynchronous orbit at 53 deg W in 1984-1985; 180 deg E in 1985-1994 As of 28 August 2001 located at 164.20 deg W drifting at 10.735 deg W per day. As of 2007 Mar 11 located at 110.10E drifting at 10.740W degrees per day.

• 1984 June 9 - Intelsat 5 F-9 - Program: Intelsat. Launch Site: Cape Canaveral. Launch Vehicle: Atlas. FAILURE: Centaur structural failure. Mass: 1,091 kg (2,405 lb). Perigee: 180 km (110 mi). Apogee: 1,227 km (762 mi). Inclination: 29.20 deg. Period: 98.90 min.

  Failure of Centaur upper stage left stranded in useless orbit. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Launch vehicle was to have put payload into geosynchronous transfer orbit