X-15 OPERATIONS FLIGHT REPORT

FLIGHT NO: 1-43-69 DATE OF REPORT: 1/22/64

PILOT: Capt. J. Engle DATE OF FLIGHT: 1/8/64

CARRIER AIRCRAFT: B-52 #008 LAUNCH LAKE: Mud Lake

PURPOSE OF FLIGHT: 1. Pilot Proficiency

2. High Angle of Attack with SAS off

I. Discussion of Previous Operations

None II. Aircraft Configuration Changes None III. Instrumentation Changes A The KS-25 experiment was removed for the flight as a result of in-flight malfunction of the V/H computer on flight l-A-68. Two V/H computer modules are available and each exhibited intermittent malfunctions during the course of system check out following the aborted flight. All KS-25 components were returned to the vendors for refurbishment. Additional testing was planned to select proper shock mounts and to determine mount performance at aircraft vibration and motion frequencies. IV. Preflight Events A. Engine S/N 104 was removed to replace faulty igniter plugs.

B. The RH inner windshield which failed during the previous flight was replaced.

C. The pitch-yaw manual BCS and RAS valves were replaced due to leakage.

D. An engine ground run was attempted on December 11, 1963. A fuel single point connector leaked excessively, canceling the run.

E. During the engine ground run on December 12, 1963, shutdowns occurred at chamber light and in igniter idle on the restart attempt. Helium injection was the cause. An "0" ring became dislodged in the fuel line slip joint.

F. A successful engine run was accomplished with S/N 104 on December 14, 1963. The APU, BCS, and RAS were also qualified for flight.

G. A misalignment of the lox elbow external service port and the panel was noted on closeout. The elbow assembly, constructed of 6061-T6, was deformed approximately 3/32 inch to provide the proper fit.

H. Flight l-A-68 was accomplished on December 18, 1963. The experiment green test light indicated failure of the KS-25 during the airborne test. Checks made after the flight using the ground test switch on the upper elevator indicated satisfactory operation of the KS-25; the ground test switch simulates a signal from the V/H computer. A check with the doppler malfunction setup of 800 fps at 2300 feet also showed V/H computer operation. The aircraft was demated for further tests. In the course of system operation an intermittent malfunction of the altitude loop was obtained in the V/H computer installed for flight. The spare V/H computer did not provide the correct output with various V/H ratios, and the flight was canceled.

I. Aircraft preflights were reaccomplished and a flight was scheduled without the KS-25 installation.

J. Preflight cabin leakage rate was checked at 75 cfm.

V. Flight Events A. The guard receiver was found to be inoperative during the pilot entry radio check. The daily preflight check was satisfactory. Guard frequency was set up manually on the auxiliary receiver for the flight.

B. The inertial system malfunctioned at the peak altitude with loss of the inertial flight parameter display and attitudes.

C. Leakage of steam from the pitch-yaw BCS/RAS system prior to launch produced a slight frosting of the X-15 windshield.

D. The #1 mixing chamber was erratic during the flight. System operation was monitored with the real time T/M display.

Approved by: Prepared by:

Perry V. Row Ronald S. Waite

X-15 Senior Project Engineer X-15 Project Engineer