spacecraft into a lunar orbit. Possible cause was malfunction of the coast-control
      system after third-stage spinup and separation
59.   Intelsat III A, 18 Sep 68, Response Mode 5, Flight Phase 1: Due to loss of rate gyro,
      undamped pitch oscillations began at 20 seconds. Vehicle began a series of
      violent maneuvers at 59 seconds. During the 13-second period while these
      maneuvers continued, the vehicle pitched down some 270°, then up 210°, and
      then made a large yaw to the left. At 72 seconds the vehicle regained control and
      flew stably in a down and leftward direction until 100 seconds. At this time, with
      the main engine against the pitch and yaw stops, the destabilizing aerodynamic
      forces became so large that quasi-control could no longer be maintained. The first
      stage broke up at 103 seconds. The second stage was destroyed by the RSO at
      110.6 seconds. Major pieces impacted about 12 miles downrange and 2 miles left
      of the flight line.           •

71.   Intelsat III E, 26 July 69, Response Mode NA, Flight Phase 3 and 5: Unknown but
      anomalous third-stage performance inserted payload into an erroneous orbit.
      Apogee was some 17,000 miles too low and orbital inclination was 1.5° above
      planned 28.8°
73.   Pioneer E, 27.Aug 69, Response Mode 5, Flight Phase 1: First-stage hydraulics
      system failed a few seconds before burnout (MECO). The vehicle pitched down,
      yawed left, rolled counterclockwise driving all gyros off limits, and then tumbled.
      Second-stage separation and ignition occurred while the vehicle was out of
      control. After about 20 seconds, the second stage regained control in a yaw-right,
      pitch-up attitude. The vehicle flew stably in this attitude for about 240 seconds
      until destroyed by the safety officer at T+484 seconds.
78.   Intelsat III G, 22 Apr 70, Response Mode NA, Flight Phase 1 and 5: The flight was
      considered a success, although low first-stage velocity resulted in a propellant-
      depletion shutdown of the second stage. As a result, the actual apogee was some
      2,220 miles below the planned value of 195,400 miles, and well outside three-
      sigma limits.
85.   0S0-H, 29 Sep 71, Response Mode NA, Flight Phase 2 and 5: Stage-2 hydraulic-
      system failure caused faulty control during second-stage bum. Spacecraft injected
      initially into an elliptical orbit, but was later maneuvered into a more satisfactory
      orbit although perigee was still about 93 miles below the planned value.
86.   ITOS-B (WTR), 21 Oct 71, Response Mode 4, Flight Phase 2: Contamination in the
      oxygen vent valve apparently prevented its proper operation throughout flight.
      This led to bulkhead rupture during second-stage bum and loss of vehicle control.




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