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Page Title:
Demonstration Planning and Progress Report (cont) |
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|  MIL-D-23222A(AS)
3.19.2.2
(Cont)
(9) The following information as applicable to the
design:
All structural design gross weights.
(a)
(b)
Aerodynamic and structural design envelopes
and limits of helicopter gross weight versus
center-of-gravity position.
Level-flight and limit dive speeds.
(c)
(d)
Landing sinking speeds for demonstration.
Autorotative speeds, power-on and power-off,
(e)
versus gross weight in basic, landing; and
other pertient configurations.
Demonstration parameters for the tests of
(f)
Tables 1, 2, and 3 with indications, when the
proposed parameters are different from those
specified, whether the proposed parameters
are limited by actual strength, control power,
flight characteristics or other phenomenon.
Planned flight envelopes for Navy Preliminary
(g)
.
Evaluations.
(10) Summaries of safe boundaries of flight conditions
performed during the contractors flight tests
including, as a minimum, the following information:
(a) Information regarding the maximum and minimum
load factors and air speeds, control displace-
merit and times shall be presented in tabular
form indicating the most severe maneuvers
shown by flight tests to date that can be
safely achieved.
(b) Information concerning control movements, oper-
ation of appurtenances, and operation of pilot-
over-riding flight control system, that is
to be discussed during the pre-structural demon-
stration conference of 3.2.5.
(11) Summaries of static and fatigue failures, excessive
wear or other failures that occur in development
flight helicopters. In addition, a maintenance
history of dynamic components (e.g. pitch or flap
bearings, bushings, or rotor blades, etc.) which
have been changed on development helicopters, even
though no failures have occurred, shall be included
with reasons for the changes or unscheduled main-
tenance.
99
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