caused yaw and roll rates that the flight control system could not correct. As a
     result, attitude control was lost and the thrusting sustainer pivoted the missile to a
     retrofire attitude before the vehicle could be stabilized. After the booster package
     was jettisoned, the missile was stabilized and decelerating in the retrofire mode
     by 148 seconds. The sustainer continued thrusting in this attitude until 282.9
     seconds when reentry heating apparently caused sustainer shutdown and vehicle
     breakup.
464. 5039D AC-59 (FLTSATCOM), 6 Aug 81, Response Mode NA, Flight Phase 1 and 5:
     The basic mission was accomplished although three increasingly severe shock
     events were recorded at 56.2, 70,7, and 120.8 seconds. The structural damage
     sustained by the spacecraft severely limited on-orbit operations.

466. 76E (NAVSTAR VII), 18 Dec 81: Response Mode 2, Flight Phase 1: Shortly after
     clearing the launch tower at an altitude of about two tower heights, the thrust
     performance of the Bl engine began to decay. The engine was shut down
     completely by 7.4 seconds. The unbalanced thrust caused the missile to pitch over
     to the right, and travel horizontally for about one second. It then pitched toward
     the ground. A small explosion .occurred about one-third of the way down,
     followed by a larger explosion when the missile impacted the ground directly
     behind the launch pad about 19 seconds after liftoff. Cause of the engine failure
     was plugging of the gas-generator fuel-cooling parts that resulted in a gas-
     generator bum-through.
477. 5042G AC-62 (Intelsat V), 9 Jun 84, Response Mode 4T, Flight Phase 4:
     Performance was normal until an abnormal shock event occurred at
     Atlas/Centaur separation. Subsequent data indicated that a Centaur oxygen tank
     leak resulted in a loss of 1483 pounds of LOX during Centaur first burn. The leak
     resulted in the LOX tank pressure falling below the LH2 tank pressure, which led
     to collapse of the intermediate bulkhead during the coast phase. Bulkhead
     collapse caused unexpected tumbling forces during coast. The Centaur engines
     restarted after coast, but burned for only 6 or 7 secorids of a planned 90-second
     bum.
489. 5048G AC-67 (FLTSATCOM F-6), 26 Mar 87, Response Mode 4T, Flight Phase 1:
     Vehicle performance was normal till 48.4 seconds, when the vehicle was struck by
     lightning. As a result, the guidance computer commanded a hard right tum
     which caused vehicle breakup due to inertial and aerodynamic loads. RSO sent
     destruct at 70.7 seconds.
498. 5050 AC-70 (BS-3H COMSAT), 18 Apr 91, Response Mode 4T, Flight Phase 3:
     Atlas performance was normal. Although both Centaur main engines began the
     start sequence properly, the C-1 turbo-machinery decelerated and stopped,
     leaving the C-1 engine thrust at the ignition level. Air entering through the stuck-
     open check valve liquefied and froze in the LH2 pump and gear box of the C-1


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