MIL-F-18372(Aer)
STANDARDS:
MIL-STD-203 Cockpit Controls; Location and Actuation Of, For Aircraft
PUBLICATIONS .
Air Force - Navy Aeronautical Bulletins
ANA-275 Guide for Lubrication of Aircraft
(When requesting specifications, standards, drawings, and publications
refer to both title and number. Copies of this spcification and
applicable specifications may be obtained upon application to the
Commanding Officer, U. S. Naval Air Station, Johnsville, Pennsylvania,
Attention Technical Records Division)
3. REQUIREMENTS
3.1 Desire and Installation Requirements for All Aircraft Types
3.1.1 Requirements That Apply to All Classes of Flight Controls
3.1.1.1 General - Flight control systems shall be as simple, direct and foolproof as possible with
respect to design, operation, inspection and maintenance. Early and careful consideration shall be
given the new designs to the arrangement of cables and other connecting elements that extend from the
cockpit to the control surfaces so as to effect the most direct and simple routing possible. The
number of bends or changes in direction shall be held to a minimum. All proacticable compromises in the
installation of equipment shall be the to favor the most direct control system possible. Workmanship
shall be of sufficiently high grade throughout to insure proper operation and adequate service life.
The strength of the flight control system shall be in accordance with Specification MIL-A-8629(Aer).
3.1.1.1.1 Power Operated Systems - Failure of any or all the engines in flight shall not result in the
pilot being unable to operate those powered services which are essential to the making of a safe descent
from altitude and an emergency landing.
3.1.1.1.2 Reserve Power for Emergency Use - An independent source of power shall be provided to operate
those powered services vital to the safe descent and landing of the airplane, which would otherwise be
put out of action by failure of any or all of the engines of the aircraft.
3.1.1.2 Pilot's Controls -
3.1.1.2.1 Location and actuation - The location and actuation of the pilot's controls shall be in
accordance with MIL-STD-203.
3.1.1.2.2 Stops - Stops shall be provided to limit the controls in the cockpit to the desired motion
ranges. The stops shall be located as near the control in the cockpit as possible. (See paragraph
3.1.1.21 for requirements regarding surface stops).
3.1.1.2.3 Removable Controls - Components provided with a disconnect feature for removal shall be so
designed as to prevent incorrect installation.
3.1.1.3 Structural Deflection - Defelection of the aircraft structure in flight shall not result in
excessive loss of cable rigging tension or in a change in position of any aerodynamic surface unless
such change is determined to be necessary and/or desirable for the purpose of improving the stability
and control characteristics of the aircraft.
3.1.1.4 Rigidity - The rigidity of the flight control systems shall be sufficient to provide satis-
factory operation and to enable the aircraft to meet its stability, control and flutter requirements.
Individual components shall be sufficiently rigid to withstand normal handling and servicing and shall
not become adversely deformed under operating loads or airframe structural deflections.
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