X-15 OPERATIONS FLIGHT REPORT

FLIGHT NO: 3-17-28 DATE OF REPORT: May 21, 1963

PILOT: Maj. Rushworth DATE OF FLIGHT: May 14, 1963

CARRIER AIRCRAFT: B-52 #008 LAUNCH LAKE: Hidden Hills

PURPOSE OF FLIGHT: Aerodynamic Heating Rates at High Mach Number and High Angle of Attack

I. R. Experiment and U.V. Experiment

I. Discussion of Previous Operations

None II. Aircraft Configuration Changes A. Barnes spectrometer installed in place of Block spectrometer and the 35mm camera. III. Instrument Configuration Changes A. Calibration of associated parameters needed for reinstallation of the Barnes spectrometer. IV. Preflight Events A. No . 1 and No . 2 (S/N 20AN and S/N 26AN) APU's were removed for inspection following the previous high altitude flight and were found to be satisfactory APU's. S/N 20AN and S/N 17AN were returned to the airplane for installation. During ground checkouts the upper turbine seal deteriorated on S/N 17AN and loss of gear case pressurization was observed. APU S/N 26AN was installed in place of APU S/N 17AN and ground runs performed with no further problems.

B. The flight attempt on May 17, 1963, resulted in an abort when a hydraulic return line in the #1 system ruptured causing a drop in the hydraulic pressure to approximately 1000 psi. A cavitation to O psi was also observed for approximately 1 second. On May 18, 1963, the system was purged and hydraulic samples sent to NAA. Since there was some question on the pump, it was decided to run the APU for a total time of 10 minutes and observe the operation of the pump and inspect the hydraulic filters for contamination. This was done in four runs of from 2 to 3 minutes each, so as not to overheat the APU compartment. Since the pump operated satisfactorily and the contamination due to metals was minor, it was felt that the APU was qualified for flight.

C. Hydraulic oil samples sent to NAA on May 18, 1963, showed excessive contamination of fibrous material. The #2 system which had not been broken into since samples were sent on May 16, 1963, showed the greatest concentration. This necessitated a complete hydraulic system oil change and filter change which was accomplished before flight. An investigation is now being conducted to determine how this contamination is being introduced into the system. Some possible causes are material in sample bottles, and/or buildup of small particles already presently in supplied oil.

D. After the flight attempt on May 13, 1963, which resulted in a cancellation because of weather and TM problems, the cabin source pressure dropped off. Investigation disclosed a faulty relief valve. This was replaced and the system functioned properly during flight 3-17-28.

 V. Flight Events A. During mated portion of flight, the pilot experienced difficulty keying his mike when using the B-52 radio. Post-flight investigation showed a sticky relay in the B-52 intercom system.

B. Face plate heater intermittent before launch. Post-flight investigation did not reveal any discrepancies in the ship's system.

C. Engine shutdown after launch. A vibration shutdown was experienced 2 seconds after main chamber start. Post-flight inspection of the engine system revealed a faulty vibration indicator. This has been replaced and will be checked out during the next ground run.

 Approved By: Prepared by:

Perry V. Row John G. McTigue

X-15 Senior Project Engineer X-15 Project Engineer