FLIGHT NO: 3-8-16 DATE OF REPORT: August 9, 1962
PILOT: J. A. Walker DATE OF FLIGHT: August 2, 1962
CARRIER AIRCRAFT: B-52 #003 LAUNCH LAKE: Mud Lake
I. Discussion of Previous Operations
B. A "Q" meter was installed on the pilots instrument panel.
C. TM transducers were cold soaked to aid in locating the short on TM attributed to low temperatures. The #2 hydraulic system pressure transducer was discovered by the above means to be the cause of the short.
A review of the data obtained from the ground run on 7/25/62 showed that pressure switch S-29 did not function properly during one of its operations. Also it was observed that the purge network did not operate correctly and that there was a slight pump oscillation before the engine start. Engine S/N 103 was removed and engine S/N 107 installed. During the engine run on 7/27/62, a pump oscillation was again noticed. The H202 tank was then reserviced and the oscillation did not occur. The swing spout in the engine H2O2 tank was inspected and a leak was found. After replacing the swing spout another pump run was made on 7/27/62 with no evidence of pump oscillation.
B. NH3 Safety Valve Change
During the engine run on 7/27/62, an NH3 leak was observed at the mating flange on the engine NH3 safety valve. The valve was changed and no leak was observed during the pump run on 7/28/62.
C. B-52 LOX Vent Valve Inoperative
During the taxi out for the attempted flight 3-A-l5 the B-5 LOX vent valve for the cruise tank would not close. The B-52 returned to the service area and heat was applied to the valve from an external source. The valve then closed normally and the flight was continued after reservicing the B-52 with LN2 and source pressure.
D. The attempted flight 3-A-15 was aborted on 8/l/62 due to being unable to read NH3 tank pressure on the pilots panel and TM console. An apparent freezing of the sense line going to these transducers was believed to be the cause. A separate line was routed to the pilots NH3 tank pressure transducer and all the lines purged. No abnormal operation was observed during flight 3-8-16.
The pitch angle set indicator was replaced when the unit exhibited a polarity reversal during flight. This reversal was attributed to a malfunction of the polarity reversing micro-switch mechanism.
B. H202 Leakage Observed After Landing
An excessive amount of H202 was noticed coming out of
the Yaw-Pitch H202 valve drain. It was determined that the MH system Yaw-Pitch
BCS valve was leaking. This valve has been changed.
Perry V. Row John G. McTigue
X-15 Senior Project Engineer X-15 Project Engineer