X-15 OPERATIONS FLIGHT REPORT

FLIGHT NO: 3-24-41 DATE OF REPORT: January 13, 1964

PILOT: Milt Thompson DATE OF FLIGHT: November 27, 1963

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

PURPOSE OF FLIGHT: Pilot Checkout

I. Discussion of Previous Operations

A. Cooling of the inertial system computer has been inadequate for a number of recent flights on X-15-3. Monitor of computer internal temperatures has indicated a temperature rise of approximately one degree per minute during captive flight. Temperature levels have approached the 125 degree maximum limit at launch; the computer temperature decreases after launch. Platform overheat indication is anticipated when outbound captive time exceeds that of the Hidden Hills launch. A physical inspection of the cooling system has not revealed a cause for degradation of platform cooling. II. Aircraft Configuration Changes None III. Instrumentation Configuration Changes A. Calibration of the noise panel pickup was not completed and only qualitative data were obtained.

B. Manometers measuring the wing static pressures and the upper ventral rakes were operational.

C. Several ball nose installations were made before an acceptable system was obtained:

Date Ball Nose S/N Remarks

11/12 002 Removed for hydraulic seepage and 20 cycle b oscillation

11/13 003 70° static port capped

11/14 004 Replaced S/N 003 which was suspected of pitot pressure leakage

12/14 004 Removed to adjust pitot pressure

Q/D, the cause of pitot system leakage

Ball nose S/N 004 was subsequently qualified for flight.

 IV. Preflight Events A. Engine S/N 109 was qualified for flight without an engine run.

B. Flight 3-A-40 was aborted on 11/19/63 due to weather conditions at the launch lake.

C. H202 leakage from the #1 APU compartment drain was noted after captive flight. The pressure differential switch was leaking externally, and replacement of the switch was accomplished.

D. The flight scheduled for 11/20/63 was canceled by rain. Wet lake conditions delayed reschedule of the flight until 11/26/63.

E. The aircraft remained mated and was held in a preflight condition until the flight was accomplished.

 V. Flight Events A. A delay in the takeoff time occurred due to damage of an "0" ring on the pilots suit/seat disconnect on pilot entry.

B. Leakage of the engine #1 and #2 helium source was again noted during final system topoff procedures. Notable leakage was traced to inaccessible areas, and the flight was continued since rates were within acceptable limits.

C. The internal temperatures of the inertial system computer approached an overheat condition during the captive portion of the flight. Reference part I-A.

D. The pilot reported sticky operation of the center stick mic button.
 

 Approved By: Prepared by:

Perry V. Row Ronald S. Waite

X-15 Senior Project Engineer X-15 Project Engineer