X-15 OPERATIONS FLIGHT REPORT



FLIGHT NO: 1-39-63 DATE OF REPORT: 11/5/63

PILOT: Capt. J. Engle DATE OF FLIGHT: 10/7/63

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

PURPOSE OF FLIGHT: 1. Pilot Checkout  2. Optical Degradation Experiment

Functional Demonstration

I. Discussion of Previous Operations

A. Revisions were made to the inertial system 28V DC wiring to retain power to the gyros during the ground power to B-52 power change-over.

B. Further analysis of the engine malfunction which occurred after the throttle shutdown of the previous flight indicated actuation of the lube oil low pressure switch produced the malfunction. Pressure variations in the lube oil system under near zero "G" condition are suspected.

 II. Aircraft Configuration Changes A. The period of July 22 through August 19, 1963 was required to modify the electrical equipment elevator and electrical system to accept the KS-25 experiment, to incorporate a new revised "standard" cockpit panel, to install a window boundary-layer rake, and to install the high temperature alpha-vane on the RH side of the fuselage in the nose wheel area. NAA personnel accomplished the structural rework of the elevator at Los Angeles and the alpha-vane installation provisions at FRC.

B. Main landing gear struts incorporating the beefed-up design were installed because of deterioration of strut attachment hole diameters. Other parts of this design were not included since parts were not available.

C. Emerson Electric Thermolag 500 was applied to the leading edge and side panels of the lower stub ventral and to each lower speed-brake surface.

D. As part of the fuselage window boundary-layer rake installation, the communications antenna was relocated to the C. G bay lower access door (previous lower bug-eye camera location).

E. The mixing-chamber pneumatic control-gas converter capacity was increased by reinstalling the tubing coils around the blower motors. The temperature of the gas is now considered satisfactory for extended mixing-chamber operation.

F. The lower ventral actuator and related mechanism were removed to reduce weight.

 III. Instrumentation Changes A. The lox pump bearing temperature was transferred to the T/M data system.

B. A display of delta cross-range using inertial system outputs was provided in the cockpit center pedestal to assist in course correction for the KS-25 experiment.

C. The pilot's blood pressure system was installed.

D. Provisions for recording the output of the Air Force high temperature alpha-vane were incorporated.

 IV. Preflight Events A. APU S/N 25AN was removed after the previous flight to investigate the turbine shaft upper seal leakage encountered during preflight ground runs. Inspection of the disassembled unit did not reveal a physical cause for the intermittent seal operation.

B. The left hand inner windshield was replaced due to surface scratches.

C. A successful engine run was accomplished on August 21, 1963.

D. APU S/N 25AN was reinstalled in the #l position following test stand requalification. The APU was removed at a later date for use in X-15-3 due to lack of spare units. APU S/N 25AN was returned again and installed.

E. The KS-25 experiment encountered a shutter failure requiring the shutter assembly to be sent to Fairchild for repair. The unit was rapidly returned, which allowed closeout and mating on Tuesday, September 4, 1963.

F. Rain occurred on September 4, 1963, canceling the proposed flight and the aircraft was demated.

G. Preflights were reinitiated following the rain, however, rains on September 17, 1963 again delayed flight preparations. Preflights were reinitiated on September 23, 1963.

H. Flight l-A-62 was accomplished on October 4, 1963. The flight was canceled due to complete failure of the X-l5 communications system. A loose coaxial connection and inadequate power-supply antenna connector engagement were located and corrected.

 V. Flight Events A. The cockpit angle-of-attack indicator was inoperative during the first launch attempt. The malfunction corrected itself at four minutes past simulated launch. A sixteen minute turn was initiated, and APU shutdown accomplished. The pilot reverted to B-52 oxygen and pylon LN2 supply. The systems were reactivated per checklist at ten minutes to launch. During both outbound turns T/M data was lost from approximately 7 minutes to 4 minutes prior to launch.

B. The angle-of-attack indicator malfunction recurred after launch and the indicator remained inoperative throughout flight.

C. Hydrogen Peroxide was observed leaking from the LN2 compartment area after flight. The leak was traced to the upper flange of the #1 APU tank and attributed to permanent set of the RTV88 material which acts as a sealing gasket at this point.

D. The LH electrical umbilical disconnect removed with the X-15 at launch. Separation occurred at the soldered connections at the back of the plug. This disconnect assembly did not incorporate a strengthened lanyard attach point, and failure to disconnect was due to separation of the metal eye. The replacement disconnect incorporated the revised pin design.
 
 

 Approved by: Prepared by:

Perry V. Row Ronald S. Waite

Senior X-15 Project Engineer X-15 Project Engineer