X-15 OPERATIONS FLIGHT REPORT

FLIGHT NO: 1-42-67 DATE OF REPORT: 1/22/64

PILOT: Major R. Rushworth DATE OF FLIGHT: 12/5/63

CARRIER AIRCRAFT: B-52 #008 LAUNCH LAKE: Delamar

PURPOSE OF FLIGHT: 1. Phase II Optical Degradation and

2. Delta Cross Range Indicator Checkout

I. Discussion of Previous Operations

A. The "Mach 5" angle of attack vane installation on the RH forward fuselage was subjected to a wide Mach number range up to a maximum of 6. During this and previous flights, the vane angle of attack was recorded on the internal oscillograph. No physical deterioration was noted in the exposed portions of the vane, and the position synchro operated for all vane environments. II. Aircraft Configuration Changes A. Thermo lag 500 ablation material was applied to an approximate 4 foot square area including the LN2 bay cover, lox tank, and side fairing areas. Failure of adhesion in the area of the annulus chill vent caused cracking and separation during the first service following the ablation installation. The ablation material was removed from the LN2 bay and the structure surrounding the annulus vent to prevent undesirable thermal gradients. III. Instrumentation Changes None IV. Preflight Events A. The engine control box was removed to replace the lube oil pressure switch which had been leaking lube oil on previous operations.

B. A satisfactory engine run was accomplished with S/N 104 on November 21, 1963.

C. The #1 igniter plug was inoperative during the preflight engine functionals. The two remaining plugs were normal.

D. Flight l-A-66 was accomplished on December 3, 1963. The radio failed to operate during the captive flight radio checks. After flight all coaxial connectors, transmitter/receiver and power package disconnects were checked for proper engagement and found to be satisfactory. The power module was replaced; the T/R unit was thoroughly checked in the laboratory without indication of malfunction.

E. A flight attempt was canceled on December 4, 1963 when a radio malfunction was evident at pilot entry checks. An investigation was made to determine the effects of a revised radio cooling procedure. The T/R unit was found to be sensitive to a cold environment, however a replacement unit operated satisfactorily with the same conditions.

V. Flight Events A. Considerable difficulty was experienced with the inertial system range position control during the captive outbound track. In-flight procedures were executed which recovered the system in time to obtain a specification inertial system prior to launch.

B. The RH inner windshield cracked during the approach to high key. Canopy distortions due to high structural temperatures are the suspected cause. The windshield remained intact and exhibited the characteristic soda-lime glass cracks.

C. Smoke was noted issuing from the LN2 bay after landing. A shorted cabin source regulator heater was the cause.

Approved by: Prepared by:

Perry V. Row Ronald S. Waite

X-15 Senior Project Engineer X-15 Project Engineer