MIL-F-18372(Aer)
3.2.4.1.4 Indicator - An approved type indicator shall be provided in the cockpit to indicate
flap positions.
3.2.4.2 Speed Brake Controls - A suitable control system shall be provided for actuating
the speed brakes. The speed brake control system must be capable of withstanding frequent operation
at all flight speeds up to the terminal velocity of the airplane.
3.2.4.2.1 Emergency Ststems - Emergency retraction is required on those speed brakes that will
not automatically retract, as a result of air loads, when the control is moved to the retract position.
3.2.4.2.2 Positioning - The speed brake control system shall be of such design as to permit
infinite variable positioning.
3.2.4.2.3 Operating Time - It shall be possible to completely extend the speed brakes in not
less than two (2) seconds and not more than three (3) seconds. Time of operation specified shall
apply at Vt at sea level and at all ambient air temperatures between -20°F (-29°C) and +120°F (+49°C).
Between -20°F (-4&°C) and -65°F (-54°C), and between +120°F (+49°C) and +160°F (+72°C), the time of
operation shall not exceed 4½ seconds. The above values shall be met with all components of the
actuating mechanism stabilized at the extreme temperature, and without assuming time for warm-up of
the components.
3.2.4.2.4 Location of Control - The pilot's control for the speed brake shall be located in
accordance with MIL-STD-203.
3.2.4.2.5 Actuation - The pilot's actuating mechanism shall be a three-position device with a
stop position in neutral, momentary aft position to extend, and a maintained forward position for
retraction.
3.2.4.2.6 Indicator - An indicator shall be provided to indicate whether speed brakes are
extended.
3.3 Additional Design and Installation Requirements for Rotary Wing Aircraft
3.3.1 Primary Controls
3.3.1.1 Cyclic Pitch Controls - The cyclic pitch control shall be by means of a stick. Move-
ment of the stick forward shall direct the resultant rotor thrust in the forward direction; movement
of the stick aft shall direct the resultant rotor thrust in the aft direction; movement of the stick
to the right shall direct the resultant rotor thrust to the right; and movement of the stick to the
left shall direct the resultant rotor thrust to the left. The range of movement of th ecyclic pitch
control shall not be more than 14 inches in the fore and aft direction, with a maximum of 9 inches
aft of the neutral position, and not more than 7 inches to the right, and 7 inches to the left, of the
neutral postion. If the control stick iS removable it shall be psitively latched in place when
installed. It shall be possible to install the stick only in the correct manner, and suitable means
shall be provided to prevent rotation of the stick.
3.3.1.2 Collective Pitch Control - The collective pitch control shall be by means of a lever.
Movement of the lever in an upward direction shall increase the resultant rotor thrust, and movement
of the lever in a downward direction shall decrease the rotor thrust.
3.3.1.2.1 Throttle Interconnection - The collective pitch control shall be interconnected with
the throttle control, and synchronized to provide the proper throttle setting as collective pitch is
increased or decreased. Means shall also be provided to permit throttle control independent of lever
movement, by rotation of the grip on the lever.
3.3.1.2.2 Locks - An adjustable friction type lock, or equivalent, shall be provided to retain
the collective pitch lever in any desired position. A lock shall also be provided to lock the
collective pitch lever in the down position.
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