X-15 OPERATIONS FLIGHT REPORT


FLIGHT NO: 1-33-54 DATE OF REPORT: 4/18/63

PIIOT: Major Rushworth DATE OF FLIGHT: 4/11/63

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

PURPOSE OF FLIGHT: APU Gearcase Pressure System Demonstration

KC-1 Camera Checkout

I. Discussion of Previous Operations

A. ECP X-15-155 was completed by NAA, Inc., on December 10, l962.

B. Post delivery work was accomplished per memorandum "X-15 #670 Status Following Compliance with ECP X-15-155" dated 1/8/63.

C. The APU pinion gear wear investigation was concluded with flight qualified APU's, S/N 16AN and 26AN, made available during the week of 3/25/63.

D. Exhaustive efforts to reseal the cockpit during wiring modifications produced a disappointing 70 CFM leakage prior to flight. The wire bundle glands, cockpit and elevator seal sills, and control cable glands were all reworked. A test was conducted to demonstrate the auxiliary pressurization system to buildup and maintain cockpit pressure with 70 CFM leakage.

 II. Aircraft Configuration Changes A. KC-l camera with ART 15A mount.

B. Operational RAS.

C. Revised heat and vent system as part of ECP X-15-155.

D. Relocated communications antenna to accommodate camera window.

 III. Instrumentation Configuration Changes The following additional instrumentation systems were operational:

A. FM-FM telemetry system.

B. Parsons tape recorder.

C. Solid state TM commutator.

D. APU vibration, gear case oil temp, and gear case pressure.

 IV. Preflight Events A. Four engine installations were made during flight preparations: 1. S/N 106 removed prior to ground runs for revised Rokide Limits.

2. S/N 104 ground run produced serious hydraulic leak at governor drain.

3. S/N 109 removed for governor actuator instability noted during preflight checks.

4. S/N 107 qualified for flight.

 B. The lox tank regulator malfunctioned during ground jettison checks prior to a flight attempt on 4/10/63. The aircraft was demated and the regulator replaced. The regulating function of the original regulator was satisfactory, however, the regulator did not close in vent, resulting in complete loss of fox source.

C. Fuel vapor leakage from the prime line was noted prior to taxi. The low quantity and other circumstances warranted continuing the operation.

D. The #l hydraulic temperature thermocouple was inoperative during servicing and flight.

 V. Flight Events A. The fuel vapor leakage noted during preflight activities resulted in precooling of the fuel system with an excessively low lox pump bearing temperature indication. The engine was placed in reset to operate the lube oil pump and maintain oil circulation. In the course of the flight the temperature dropped to -53°F, or the fuel service temperature. A modified prelaunch ignitor start was made to insure satisfactory pump bearing condition prior to launch. The pump was started at minus 30 seconds with igniter start at minus 10 seconds.

The bearing temperature rose normally during the prelaunch period and the launch was made. Post flight investigation revealed the lox pump bearing temperature probe was not properly bottomed against the bearing case.

B. The roll channel of SAS tripped out at launch and ASAS engaged. The pilot reengaged normal roll and rearmed ASAS without incident.

C. RAS was inoperative when the flight tests were initiated. The RAS system was engaged with the Auto Cutoff switch ON prior to launch. This setup resulted in the system disengaging during the first portion of the flight due to the "G" limiting feature. Flight operating procedures have been corrected.

D. The auxiliary cockpit pressure system actuated at the engine shutdown transient and provided adequate cockpit pressure for the remainder of the flight.

E. The pilot reported a "thump" on the rudder pedals during the latter portion of the flight. An inspection of the nose wheel well and forward bulkhead heatshield showed no permanent damage. The pedal support is part of the cockpit bulkhead structure and would transmit the structural effects of heating.
 
 

 Approved by: Prepared by:

Perry V. Row Ronald S. Waite

X-15 Senior Project Engineer X-15 Project Engineer