X353-5B Propulsion System Flightworthiness Test Report (Penalty Test). Volume 1 Supplement 1
Abstract
The required 10-hour penalty test to evaluate design modifications to the X353-5B lift fan inlet vanes and aluminum exit louvers was completed in accordance with the schedule of test recommended to the Army in the X353-5B Propulsion System Flightworthiness Test Report. The test was completed on a slave X353-5B lift fan which was also an acceptance test vehicle. This report is a supplement to the X353-5B Propulsion System Flightworthiness Test Report and documents the penalty test and results. It is submitted to the U. S. Army (TRECOM) in accordance with Specification 114 to form the basis for establishing a flightworthiness rating for the complete propulsion system including lift fan inlet vanes, aluminum exit louvers and diverter valves. Upon completion of the test, the inspection results showed all lift fan components including inlet vanes and aluminum exit louvers to be in satisfactory condition. The new rotor assembly technique recommended in the FWT Report and described in FRV specification 124 was completely successful in avoiding fretting. Partial disassembly of the rotor following the test, witnessed by an Army (TRECOM) representative, showed all of the rotor hardware to be in excellent condition. The XV-5A flight type diverter valve actuation successfully completed the penalty test plus two acceptance tests without incident and is in excellent condition.
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 01, 1963
- Accession Number
- AD0634950
Entities
Organizations
- General Electric