(d) Materials and processes review (see 126.96.36.199}.
(e) Critical components analyses review (see 188.8.131.52).
(3) Pre DT-IB design review (see 4.3.3).
Final engineering demonstration and validation, DT-IB. Final
engineering and validation shall consist of the track tests, in-
flight ejection tests, and aircraft canopy and escape path
clearance tests specified in 4.4. The configuratin of the test
articles shall be in accordance with the testing baseline
established in 184.108.40.206.
Component and subsystem full scale development, DT-IIA. Component
and subsystem full scale development shall include the component
and subsystem tests specified in 4.5.1 and the system design
compliance tests specified in 4.5.2. The configuration of the
test articles shall be in accordance with the testing baseline
established in 220.127.116.11. DT-IIA shall also include:
(1) Pre DT-IIB design review (see 4.5.3).
(a) Final functional configuration audit (FFCA) (see 18.104.22.168).
System full scale development tests, DT-IIB. The system full
scale development tests shall consist of the system track tests
specified in 4.6.1. Test article configureation shall be in
accordance with the final baseline established by 4.6.2. The
reviews and audits to be conducted during DT-IIB shall include
(1) Physical configuration audit (PCA) (see 4.6.2).
(a) Production proofing article (PPA) review (see 22.214.171.124).
(b) Field maintainability article II (FMA-II) review (see
The approximate time phase relationships of the test phases and other escape
system milestones and events specified herein are shown in figure 8.
4.3 Initial engineering demonstration and validation, DT-IA. The DT-IA
tests and inspections shall include, but not be limited to, the following:
a. Ballistic component tests. Cartridge and cartridge actuated
device (CAD) tests shall be accomplished in accordance with the
design verification testing (DVT) requirements of MIL-D-23615 and
MIL-D-21625. Rocket component testing shall be accomplished in
accordance with the DVT requirements of MIL-A-85041.
b. Static load tests. Design strength shall be validated by static
load tests which simulate the load conditions of 126.96.36.199. Loading
shall be applied incrementally to demonstrate structural integrity
under operational loading conditions as analytically determined