MIL-F-18372(Aer)
3.5.2 Experimental Aircraft - The following data shall be submitted:
a.
Simplified Schematic arrangement of the flight control system. (See 3.5.2.1)
b.
Flight control system design report. (See 3.5.2.2)
c.
Flight control system failure analysis report. (See 3.5.2.3)
d.
Flight control system teat. (See 3.5.2.4)
e.
Flight control system test reports. (See 3.5.2.5)
3.5.2.1 Schematic Arrangement - The simplified schematic drawing shall show the functions
of all elements (mechanical, hydraulic, electrical, pneumatic, aerodynamic, etc.,) which constitute
the flight control system of the aircraft. A description explaining the functioning of the complete
system, functions of the individual elements, and other necessary explanations of the flight control
system shall accompany the schematic arrangement.
3.5.2.2 Design Report - The design report shall be submitted prior to or concurrently with the
drawings of paragraph 3.5.2.1 and shall contain the following information:
For Type I Control Stystems - Curves or data shall be provided illustrating the
following:
a. Hinge moments developed at the reface for a unit load input at the pilot's
control for the full range of travel of the control.
b. Hinge moments developed at the surface for a unit load input at the pilot's
control but with the system assumed tO be deflected at design limit load for
the full range of travel of the control. The effects of force augmenting
devices such as spring bungees, centering springs, etc., shall be taken into
consideration for the above data.
c. Surface position versus cockpit control position for unit load input.
d. Surface position versus cockpit control Position for design limit load.
For Type II Control Systems
a. Same data as above for Type I Systems.
b. The results and a description of the methods of an analysis of the stability
and performance characteristics of the installed power boost unit. The
stability results shall be in the form of Nyquist, Bode, Root Locus or simi-
lar diagrams. Estimates of the effects of any significant non-linearities
shall be included. The performance results shall show the maximum rate of
surface travel as a function of the surface hinge moment and a graph of control
surface deflection versus time under design hinge moment.
The analysis shall be conducted for "on the ground stability" and for the
most critical flight condition. However, the submittal of the analysis for
the former should not be held up pending the availability of the latter.
The description of the methods of analysis shall be sufficiently detailed to
permit review. Derivation of equations, sources of parameter values, and
sample calculations shall be included.
For Type III Control Systems - Data similar to that required under Type II Control
Systems shall be submitted.
3.5.2.3 Failure Analysis Report - The failure analysis report shall include assumed failure of
each critical component in the most adverse position and/or condition. In addition, the report shall
consider failures of secondary flight control systems and flight path angle and drag control systems
and their effect on the primary control system. For Type II and Type III systems wherein the power
source is hydraulic, electric, etc., the report shall include a failure analysis of the hydraulic,
electric, etc., system and components. For each assumed failure the following shall be discussed:
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