B. Some trouble was encountered after mating when it was discovered that the power umbilical in the X-15 had been oriented approximately 45° counter clockwise from proper position during reassembly, (having been removed several days earlier to repair a broken wire). By removing one spring from the pylon umbilical and readjusting the remaining 3 springs it was possible to twist the pylon umbilical to fit the X-15. Both will be returned to correct position before the next flight.

C. An attempt to fly on Friday 8/17 was canceled due to weather.

D. During engine functionals on Saturday 8/18 an intermittent throttle micro switch was found. This condition was proved to be the cause for several prior intermittent "Pump ON" signals coincident with prime switch operation. New micro switches were installed, and the problem eliminated.

B. SAS pitch channel failed to trip out on inflight test of the working channel. This is not a real malfunction. Roll channel usually trips out before pitch, locking in ASAS before pitch has the opportunity to trip. This problem is one of procedure during in-flight test and will be eliminated.

C. SAS roll channel failed just after launch, and several attempts to reengage were unsuccessful. Postflight inspection showed failure of the roll notch module. This module is being disassembled by Westinghouse personnel to pinpoint the failure.

D. The pilot reported some stiffening of the speed brake controls during the high heat portion of flight. This condition is similar to that encountered during Flight 2-24 and is due to insufficient travel in the cable tension regulator to compensate for the high heat condition.

E. Postflight inspection of the engine (S/N 111) shows that a detonation occurred in the 2nd stage igniter injector. This detonation burst the He purge check valve and produced a brief flash fire in the engine compartment. No damage was sustained by the X-15 but the engine is not serviceable. Engine S/N 110 will be installed for the next flight. Investigation is under way to determine the cause of the igniter detonation.

F. Except as noted subsystem operation was normal. The new cabin regulator (see item II above) had no significant effect on the flight drop-off in cabin pressure at about engine burnout which has been characteristic of most of the X-15 flights. The lower ventral was recovered. The airframe sustained no physical damage and no new wrinkles or deformations were noted.