MIL-F-18372(Aer)
3.3.1.3 Dirctional Control - Directional control shall be by means of foot pedals. Pushing
the right pedal shall cause the aircraft to rotate to the right. Pushing the left pedal shall cause
the aircraft to rotate to the left. The range of movement of the foot pedals shall be a maximum
of 4" forward and 4" aft of the neutral position. The foot pedals shall be interconnected to insure
positive movement of each pedal in both directions.
3.3.1.3.1 Adjustment - The foot pedals shall be readily adjustable in flight to at least 3"
forward and 3" aft of neutral, increments not exceeding 1". Both pedals shall be adjusted
simultaneously by means of a single control, and the control shall be located in accordance with
MIL-STD-203. The angle of the pedals shall be adjustable on the ground only.
3.3.1.4 Blade Coning Restrainers - Suitable provisions shall be made to restrain coning of the
blades when starting or stopping the rotor. It shall be possible to start or stop the rotor in wind
velocities up to 60 knots, from any horizontal direction, without physical contact of the rotor blades
with any part of the airframe. Means shall also be provided to prevent contact of the blades and
airframe during flight maneuvers and hard landings.
3.3.1.5 Wheel Brake Controls - See paragraphs 3.2.2 through 3.2.2.4 above.
3.4 Additional Design and Installation Requirements for Lighter-Than-Air Aircraft.
3.4.1 Primary Flight Controls
3.4.1.1 Longitudinal Control - Longitudinal control shall be by means of a wheel and column
(yoke type). Forward movement of the wheel and column shall cause the aircraft to nose down and aft
movement shall cause the aircraft to nose up. The range of movement of the longitudinal control
shall be a maximum of 14". The extreme aft position hall not be more than 9" from the neutral
position.
3.4.1.2 Directional Controls - Directional control shall be by means of the wheel on the column.
Rotation of the wheel clockwise shall cause the airship to turn to the right end rotation of the wheel
counter-clockwise shall cause the airship to turn to the left. The rotation of the wheel shall be a
maximum of 110° clockwise and 110° counter-clockwise.
3.4.1.3 Control Surface Locks - See paragraphs 3.2.3 through 3.2.3.1.1 above.
3.5 Tests and Design Data Requirements
3.5.1 General - The contract will specify the tests and design data of this Section 3.5, that
will be required; will amplify or modify the tests and design data of this Section 3.5; and may specify
other tests and design data under the appropriate section of this specification. The submittal
procedures for the design data shall be as indicated in Specification SR-6.
3.5.1.1 Addition of Test and Design Data- If the tests and design data required by the contract
are inadequate to prove that the flight control system and the flight control system installation
incorporates the specified requirements, the contractor shall proppse amendments to the contract to
include tests and design data which will prove adequately that the flight control system and the flight
control system installation incorporates the specified characteristics.
3.5.1.2 Deletion of Test and Design Data. If applicable test and design data are available,
the contractor shall in lieu of repeating tests and submitting design data, propose amendments to
the contract to require the submittal of these data, supplemented by sufficient information to sub-
stantiate, their applicability.
3.5.1.3 Test Witnesses - Before conducting a required test the Bureau of Aeronautics Represent-
ative skall be notified in sufficient time so that he or his representative may witness the test and
certify results and observation contained in the test report. When the Bureau of Aeronautics
Representative is notified, he shall be informed if the test is such that interpretation of the
behavior of the test article is likely to require engineering knowledge and experience, in which case
he will provide a qualified engineer who will witness the test and certify the results and observations
during the test.
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