28.   J-9, 20 Dec 60, Response Mode 4, Flight Phase 2: No Stage-Ilignition due to failure
      of gas generator to start.
29. J-10, 20 Jan 61, Response Mode 4, Flight Phase 2: No- Stage-II operation due to
    erroneous signal that appeared at umbilical disconnect. Impact some 420 miles
    downrange.

32. J-12, 3 Mar 61, Response Mode 4, Flight Phase 2: Stage-II terminated prematurely
    after 54-second burn, apparently due to failure of pump drive assembly. Impact
    was 730 miles downrange.

34.   J-15, 31 Mar 61, Response Mode 4, Flight Phase 1: Booster shut down prematurely
      at 74 seconds. Missile subsequently tumbled and broke up.

37.   M-1, 24 Jun 61, Response Mode 4T, Flight Phase 2: Stage II engine shut down
      prematurely after 12 seconds of operation due to loss of Stage II hydraulic power.
      Loss of hydraulic power occurred during Stage I flight, so failure led to loss of
      control of sustainer and vernier actuators, producing excessive missile motion and
      tumbling.

42.   M-3, 7 Sep 61, Response Mode 5, Flight Phase 2: A transient in guidance computer
      at 218.35 seconds (SECO at 297.7 seconds) caused impact 20 miles short and 2.8
      miles left of target.
45.   M-4, 6 Oct 61, Response Mode 5, Flight Phase 2: A one-bit error in the W velocity
      accumulation caused impact 86 miles short and 14 miles right of target.
50.   M-6, 15 Dec 61, Response Mode 4, Flight Phase 2: Start signal for Stage II was not
      generated. Stage II did not ignite.
51.   I, 20 Jan 62, Response Mode 4, Flight Phase 2: Missile self-destructed, apparently
      after Stage 2 failed to ignite. A backup automatic fuel-cutoff signal was sent at
      248 Seconds.                                                         •
53.   I, 23 Feb 62, Response Mode 4, Flight Phase 2: Missile sell-destructed, apparently
      after Stage 2 failed to ignite. A backup automatic fuel cutoff signal was sent at 240
      Seconds.
56.   N-1, 7 Jun 62, Response Mode 4, Flight Phase 2: Sustainer engine performance was
      subnormal due to reduced oxidizer flow through the gas generator. RSO
      terminated flight after a prolonged sustainer bum. Impact only 1100 miles
      downrange.

58.   N-4, 25 July 62, Response Mode 4, Flight Phase 2: After about 60 seconds of Stage
      II bum, a fuel leak between the thrust chamber valve and the injector resulted ·in a



9/10/96                                    158                                         RTI