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Final engineering demonstration and validation |
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|  MIL-S-18471G(AS)
the suitability of the escape system design for commencement of the DT-IB
tests (see 4.4) and the DT-IIA tests (see 4.5).
4.4 Final engineering demonstration and validation, DT-IB. The final
engineering demonstration and validation tests shall not commence prior to
completion and approval of the pre DT-IB design review (see 4.3.3). The
objective of the tests shall be to demonstrate the capability of the escape
system to meet the performance requirements of 3.3 and table II. Not all
table II conditions shall be demonstrated by testing; however, the specific
tests to be conducted shall be stipulated in the test plan (see 4.7.2).
Data from these tests shall be utilized to evaluate specification performance
requirement compliance at the pre DT-IIB design review (see 4.5.3). Test
article configuration shall be in compliance with the testing baseline (see
4.3.2.4).
4.4.1 Aircraft canopy and escape path clearance subsystem. DT-IB testing
of the aircraft canopy and escape path clearance subsystem shall be completed
as required prior to the start of DT-IB track tests. Test results shall be
used to demonstrate compliance with 3.2.2.12. Tests shall be conducted at
worst case temperature conditions, acceptable to the procuring activity, DT-
IB testing of the aircraft canopy and escape path clearance subsystem shall
include a minimum of four tests in the redundant primary mode, a minimum of
four tests in the automatic backup mode, and two tests for contingency purposes.
Test quantities may be adjusted downward depending on the technical, complexity
of the system. Data requirements applicable to demonstrating escape path
clearance shall be in accordance with the appendix.
4.4.2 Track tests. The DT-IB track tests shall consist of eight ground
level escape system tests throughout the speed range as specified by the
procuring activity~ The tests shall be conducted with fully instrumented
test articles and shall use both the maximum and minimum specified aircrew-
member test dummies or other population parameters if data indicates a
particular problem. Detailed test requirements shall be in accordance with
the appendix. Test resulsts shall also be used to determine compliance with
the detailed design requirements not specifically tested elsewhere in this
section, including but not limited to 3.2.1.5, 3.2.2.5, 3.2.2.9, and 3.2.2.10.
Compliance with the-requirements specified in 3.2.1.5 shall be demonstrated
as --part of of zero track tests. Test data requirements and acquisition
and analysis techniques shall be in accordance with the appendix. All
test hardware shall be furnished by the contractor.
4.4.3 Inflight ejection tests. The design verification inflight ejection
tests shall consist of a minimum of six ejection seat tests as specified in
the test plan (see 4.7.2). They shall demonstrate the ability of the ejection
seat to function at the highest practical test altitude condition and at
the highest practical test airspeed at the parachute opening altitude.
They shall demonstrate required sensor and timing control functioning under
actual airspeed and altitude conditions. Detailed test requirements shall be
in accordance with the appendix.
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