X-15 OPERATIONS FLIGHT REPORT



FLIGHT NO: 2-49-86 DATE OF REPORT: September 2, 1966

PILOT: Maj. W. Knight DATE OF FLIGHT: August 30, 1966

CARRIER AIRCRAFT: B-52 #003 LAUNCH LAKE: Mud Lake #2

ENGINE: S/N 106 APU #1 21 AN APU #2 22AN

PURPOSE OF FLIGHT: Ventral On Stability Mission

I. Discussion of Previous Operations

A. Engine misalignment was partially corrected on the previous flight (Ref: report for Flight 2-48-85) since this flight (2-49-86) was programmed for low altitude and relatively high "q" it was decided not to make any further adjustment. The pilot reported no significant trim change at burnout. No further adjustment is being considered until high altitude flights are resumed. II. Configuration Changes A. The Startracker experiment was removed and the Maurer 500 camera experiment installed. III. Preflight Events A. No engine ground run was required for this flight. APU runs were conducted on Wednesday, August 24, 1966.

B. Consistent failure of the emergency hydraulic pump to operate correctly during preflight tests, resulted in several component changes, (hydraulic pump and its associated selector valve). These replacements failed to correct the problem. It was noted that the SAS servos were locking up prior to emergency pump engagement, thus resulting in frequent pump overspeed. Replacement of the SAS servo filters with new filters seemed to correct the problem. Apparently by lowering the pressure differential across the filters, the hydraulic pressure required to keep the servos from locking up was reduced to a point below the emergency pump engage pressure.

 IV. Flight Events A. Preflight servicing was generally . Some slight delay was encountered prior to B-52 engine start due to B-52 intercom failure.

B. During the flight the pilot noted a consistent right sideslip (approximately 2°). This condition seems to recur frequently in X-15-2 and an extensive alignment check will be made to determine if either the ventral, dorsal, or fuselage are out of line.

C. The recovery chute for the ventral fin deployed prematurely before the ventral was ejected, and was carried away. Thus, there was no recovery chute at ejection and the ventral was severely damaged. No explanation has been found for premature deployment of the chute.

D. During the stability test portions of the flight, two SAS tripouts occurred. No reason has yet been discovered for these failures.
 
 

 Approved By: Prepared by:

Perry V. Row William P. Albrecht

X-15 Senior Project Engineer X-15 Project Engineer